AE 3007A Series Fault Isolation Manual PDF [PDF]
FAULT ISOLATION MANUAL Initial issue March 1/2003 Revision 66 Oct.20/2016 Publication ref. CSP34064 Export controlled
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FAULT ISOLATION MANUAL
Initial issue March 1/2003 Revision 66 Oct.20/2016
Publication ref. CSP34064
Export controlled These commodities, technology or software are subject to the Export Administration Regulations. Diversion contrary to U.S. Law prohibited.
AE 3007A AE 3007A1 AE 3007A1/1 AE 3007A1/2 AE 3007A1/3 AE 3007A1E AE 3007A1P AE 3007A2 AE 3007A3 Notice The procedures and guidelines set forth in this publication are based solely upon the Rolls-Royce FAA approved type design and is intended only for the operation, maintenance, repair and overhaul of Rolls-Royce type design parts. Rolls-Royce has no knowledge regarding the applicability of these procedures and guidelines or subsequent revisions thereof to parts designed and/or manufactured by entities other than Rolls-Royce or Rolls-Royce approved vendors and suppliers.
Liability disclaimer This information is given in good faith, based on the latest information available. No warranty or other representation is given concerning such information, which must not be taken as establishing any contractual or other commitment by the company or any of its subsidiaries or associated companies
© COPYRIGHT 2003, 2016 Rolls-Royce Corporation (unpublished) Printed in USA
Date
Oct.20/2016
FAULT ISOLATION MANUAL
Publication Ref: CSP34064 TRANSMITTAL LETTER No.66
List of Service Bulletins
Remove:
Incorporate:
Pages 1 to 26
Pages 1 to 26
Reason For Change:
CHAPTER 75 CONTENTS
Pages 1 and 2
CHAPTER 79 List of Effective Pages
Page 1/2
Page 1/2
79-37-00-810-807
All Pages
Pages 201 to 209/210 Revised to add reference of AGB oil pressure test (MM task) - WP 354163
Record of Revisions Sheet
Record incorporation of TL 66 and date of incorporation on RECORD OF CERTIFIED REVISIONS
EXPORT CONTROLLED
Front Matter Table of Contents
SUBJECT
PAGE
TITLE PAGE
1
RECORD OF REVISIONS
1
LIST OF EFFECTIVE PAGES
1
R TABLE OF CONTENTS
1
LIST OF SERVICE BULLETINS
1
INTRODUCTION
1
-
General
1
-
The Specification of this Manual
1
-
Manual Content
1
-
Central Maintenance Computer
5
-
Effectivity
10
-
Revisions and Service Bulletins
10
-
Customer Service
11
-
List of Abbreviations
11
FIM USAGE
1
-
General
1
-
Use of the Fault Isolation Manual
1
EICAS Message List
1
Maintenance Message List
1
FADEC Discrete List
1
R Observed Fault List
1
Front Matter Table of Contents Page 1/2 Jan 20/11
EXPORT CONTROLLED
Front Matter List of Effective Pages Remove and insert the affected pages and complete the Record of Revisions and the Record of Temporary Revisions as necessary. SUBJECT
PAGE
DATE
SUBJECT
PAGE
DATE
Front Matter List of Effective Pages
1
Jan 20/12
Intro (continued)
14
Feb 15/06
2
Jan 20/12
15
Feb 15/06
Front Matter Table of Contents
1/2
Jan 20/11
16
Feb 15/06
List of Service Bulletins
1
Feb 15/03
17
Feb 15/06
2
Feb 15/03
18
Feb 15/06
3
Feb 15/03
19
Feb 15/06
4
Feb 15/03
20
Feb 15/06
5
Feb 15/03
21
Feb 15/06
6
Feb 15/03
22
Feb 15/06
7
Feb 15/03
23
Feb 15/06
8
Feb 15/03
24
Feb 15/06
9
Feb 15/03
25
Feb 15/06
10
Feb 15/03
26
Feb 15/06
11/12
Feb 15/03
27
Feb 15/06
1
Feb 15/06
28
Feb 15/06
2
Feb 15/06
29
Feb 15/06
3
Feb 15/06
30
Feb 15/06
4
Feb 15/06
31/32
Feb 15/06
5
Feb 15/06
Maintenance Message 1 List
Jul 20/07
6
Feb 15/06
2
Jul 20/07
7
Feb 15/06
3
Jul 20/07
8
Feb 15/06
4
Jul 20/07
9
Feb 15/06
5/6
Jul 20/07
10
Feb 15/06
1
Jul 20/07
11
Feb 15/06
2
Jul 20/07
12
Feb 15/06
3
Jul 20/07
13
Feb 15/06
4
Jul 20/07
Intro
FADEC Discrete List
Front Matter List of Effective Pages Page 1 Jan 20/12
EXPORT CONTROLLED
SUBJECT
PAGE
DATE
SUBJECT
PAGE
DATE
FADEC Discrete List (continued)
5
Jul 20/07
EICAS Message List (continued)
2
Apr 20/09
6
Jul 20/07
3/4
Apr 20/09
7
Jul 20/07
1
Jan 20/12
8
Jul 20/07
2
Jan 20/12
9
Jul 20/07
1
Sep 15/03
10
Jul 20/07
2
Sep 15/03
11/12
Jul 20/07
3
Sep 15/03
1
Apr 20/09
4
Sep 15/03
EICAS Message List
Observed Fault List FIM Usage
Front Matter List of Effective Pages Page 2 Jan 20/12
EXPORT CONTROLLED
List of Service Bulletins Bulletin Number AE 3007A-72-001
Incorporated in Manual
Rev Subject 1
Superceded by AE 3007A-72-067
AE 3007A-72-002
Cancelled Prior to Publication
AE 3007A-72-003
Cancelled Prior to Publication
AE 3007A-72-004
Cancelled Prior to Publication
AE 3007A-72-005
1
Engine - New Forward Ground-handling Bracket
No Effect
AE 3007A-72-006
5
Engine - New Borescope Plugs for the 3rd- and 5th-stage Compressor Variable Vanes
No Effect
AE 3007A-72-007
Cancelled Prior to Publication
AE 3007A-72-008
Cancelled Prior to Publication
AE 3007A-72-009
1
AE 3007A-72-010
Superceded by AE 3007A-72-037 Cancelled Prior to Publication
AE 3007A-72-011
3
Engine - New Low-Pressure-Turbine Forward Shaft
No Effect
AE 3007A-72-012
1
Engine - Seal Break-in Procedure
No Effect
AE 3007A-72-013
Cancelled Prior to Publication
AE 3007A-72-014
2
Engine - New 1st-stage Low-pressure Turbine Vane Ring No Effect
AE 3007A-72-015
1
Superceded by AE 3007A-72-191
No Effect
AE 3007A-72-016
1
Engine - Rework the LP Turbine Case Assembly
No Effect
Engine - Front Sump Housing
No Effect
AE 3007A-72-017 AE 3007A-72-018
1
Engine - Aluminum Actuator Ring Clevis
No Effect
AE 3007A-72-019
4
Engine - New 1st-stage Compressor Wheel Assembly
No Effect
AE 3007A-72-020
4
Engine - Inspect for Cracks in the Compressor Diffuser
No Effect
AE 3007A-72-021
Cancelled Prior to Publication
AE 3007A-72-022
Engine - New Center-sump Housing Assembly and Center-sump Forward Stationary Seal
No Effect No Effect
AE 3007A-72-023
6
Engine - Chem-milled Diffuser
AE 3007A-72-024
1
Superceded by AE 3007A-72-104
AE 3007A-72-025
2
Engine - Fan Spanner Nut Lock Plug
No Effect
AE 3007A-72-026
Engine - Fan Drive Shaft Serial Number Verification
No Effect
AE 3007A-72-027
Engine - Replace the Shroud in the Accessory Drive Gearbox
No Effect
AE 3007A-72-028
Cancelled Prior to Publication
AE 3007A-72-029
1
Superceded by AE 3007A-72-037
AE 3007A-72-030
4
Engine - Rework the Compressor-to-turbine Shaft
No Effect
List of Service Bulletins R
Page 1 Oct 20/16
EXPORT CONTROLLED
Bulletin Number AE 3007A-72-031
Incorporated in Manual
Rev Subject 1
Engine - New Compressor-to-turbine Shaft and Liner with Locking Spiral Retaining Ring
AE 3007A-72-032
Cancelled Prior to Publication
AE 3007A-72-033
Cancelled Prior to Publication
No Effect
AE 3007A-A-72-034 ALERT
1
Engine - Examine the Mid-span Roller Bearing
No Effect
AE 3007A-72-035
2
Engine - Mid-span Roller Bearing
No Effect
Engine - Rework the Fan Drive Shaft
No Effect
AE 3007A-72-036 AE 3007A-72-037
1
Superceded by AE 3007A-72-052 and AE 3007A-72-064
AE 3007A-72-038
1
Engine - New 3rd-stage Low Pressure Turbine Bladed Wheel Assembly
AE 3007A-72-039
1
Superceded by AE 3007A-72-050
AE 3007A-72-040
No Effect
Engine - IGV and 1st thru 5th-stage Actuation Ring and Button Assemblies
No Effect No Effect
AE 3007A-72-041
3
Engine - 1st- thru 5th-stage Compressor Inner-Ring Segment End Gap
AE 3007A-72-042
1
Superceded by AE 3007A-72-097
AE 3007A-72-043
Cancelled Prior to Publication
AE 3007A-A-72-044 ALERT
Engine - 1st- to 2nd-stage Turbine Spacer Life Limit Change
No Effect
AE 3007A-72-045
2
Engine - Replace the Accessory-Drive Gearbox
No Effect
AE 3007A-72-046
2
Engine - Cover Plate Gasket on the Diffuser
No Effect
AE 3007A-72-047 AE 3007A-72-048
Cancelled Prior to Publication 2
AE 3007A-72-049
Superceded by AE 3007A-72-118
No Effect
Cancelled Prior to Publication
AE 3007A-72-050
2
Engine - New 1st-stage High Pressure Turbine Blade Tracks and Seal Strips
No Effect
AE 3007A-72-051
3
Engine - Rework the Accessory Drive Gearbox - Add Vent Tube Fitting
No Effect
AE 3007A-72-052
2
Superceded by AE 3007A-72-182
AE 3007A-72-053
Cancelled Prior to Publication
AE 3007A-72-054
2
Superceded by AE 3007A-72-067
AE 3007A-72-055
1
Engine - Replace the Split-inner-race Ball Bearing
AE 3007A-72-056
Cancelled Prior to Publication
AE 3007A-72-057
Cancelled Prior to Publication
AE 3007A-A-72-058 ALERT
Cancelled Prior to Publication
No Effect
List of Service Bulletins R
Page 2 Oct 20/16
EXPORT CONTROLLED
Bulletin Number AE 3007A-72-059
Incorporated in Manual
Rev Subject 1
Superceded by AE 3007A-72-126
AE 3007A-72-060
Cancelled Prior to Publication
AE 3007A-72-061
Cancelled Prior to Publication
No Effect
AE 3007A-72-062
2
Superceded by AE 3007A-72-154
AE 3007A-72-063
5
Engine - Low-pressure-turbine Module (23064286) to (23067850) - Rework
No Effect
AE 3007A-72-064
2
Engine - No. 6 Carbon Seal Assembly with Steel Sleeve
No Effect
Engine - New Compressor Vane Assembly Nuts
No Effect
AE 3007A-72-065 AE 3007A-72-066
1
Superceded by AE 3007A-72-109
No Effect
AE 3007A-72-067
1
Engine - New 1st-stage High-Pressure Turbine Blades
No Effect
AE 3007A-72-068
1
Superceded by AE 3007A-A-72-156
AE 3007A-72-069 AE 3007A-72-070
Cancelled Prior to Publication 1
AE 3007A-72-071 AE 3007A-72-072
Superceded by AE 3007A-72-072 Cancelled Prior to Publication
4
Superceded by AE 3007A-72-321
AE 3007A-72-073
Cancelled Prior to Publication
AE 3007A-72-074
Cancelled Prior to Publication
AE 3007A-72-075
Cancelled Prior to Publication
AE 3007A-72-076
1
No Effect
Superceded by AE 3007A-72-135
AE 3007A-72-077
Cancelled Prior to Publication
AE 3007A-72-078
Cancelled Prior to Publication
AE 3007A-72-079
Cancelled Prior to Publication
AE 3007A-72-080
1
Engine - New Effusion-cooled Combustion Liner
No Effect
AE 3007A-72-081
5
Engine - Improved 2nd-stage High-pressure-turbine Vane Assembly and High-pressure-turbine Inner Case Assembly
No Effect
AE 3007A-72-082 AE 3007A-72-083
Cancelled Prior to Publication 2
Engine - New No. 4 Carbon Seal (23070366 or 23071880)
AE 3007A-72-084
Cancelled Prior to Publication
AE 3007A-72-085
Cancelled Prior to Publication
AE 3007A-72-086
Cancelled Prior to Publication
AE 3007A-72-087
Cancelled Prior to Publication
AE 3007A-72-088
Cancelled Prior to Publication
AE 3007A-72-089
Cancelled Prior to Publication
AE 3007A-72-090
Cancelled Prior to Publication
No Effect
List of Service Bulletins R
Page 3 Oct 20/16
EXPORT CONTROLLED
Bulletin Number
Incorporated in Manual
Rev Subject
AE 3007A-72-091
Cancelled Prior to Publication
AE 3007A-72-092
Cancelled Prior to Publication
AE 3007A-72-093
Cancelled Prior to Publication
AE 3007A-72-094
2
Superceded by AE 3007A-72-165
AE 3007A-72-095
Cancelled Prior to Publication
AE 3007A-72-096
Cancelled Prior to Publication
AE 3007A-72-097
1
AE 3007A-72-098
Engine - New Center-sump Housing
No Effect
Cancelled Prior to Publication
AE 3007A-A-72-099 ALERT
4
Engine - Monitor the High Pressure Turbine Condition
AE 3007A-72-100
4
Engine - Improved 1st-stage High-pressure-turbine Vane No Effect Assembly
AE 3007A-72-101
Cancelled Prior to Publication
AE 3007A-72-102
Cancelled Prior to Publication
No Effect
AE 3007A-72-103
3
Engine - New Effusion-cooled Combustion Liner Assembly (23071148)
No Effect
AE 3007A-72-104
4
Engine - New Upper and Lower Rear Turbine Bearing Support Heat Shields
No Effect
Engine - 1st- and 2nd-stage High Pressure Turbine Wheels - Life Limit Decrease.
No Effect
AE 3007A-A-72-105 ALERT AE 3007A-72-106
1
Engine - Improved Low-Pressure-Turbine Rear Shaft
No Effect
AE 3007A-72-107
1
Superceded by AE 3007A-72-126
No Effect
AE 3007A-72-109
2
Engine - New No. 4 Teflon Lip Seal (23070367)
No Effect
AE 3007A-72-110
2
Engine - New 2nd-stage High-pressure Turbine Blade Track (23070945)
No Effect
AE 3007A-72-111
6
Superceded by AE 3007A-72-135 and AE 3007A-72-153 No Effect
AE 3007A-72-112
1
Engine - AE 3007A1/1 and AE 3007A1/2 High-Pressure-Turbine Inner Casing - Rework to the AE 3007A1 Configuration
No Effect
AE 3007A-72-113
2
Engine - AE 3007A1/1 and AE 3007A1/2 1st-stage High-pressure-turbine Inner Casing - Rework to the AE 3007A1 Configuration
No Effect
AE 3007A-72-114
5
Engine - AE 3007A to AE 3007A1 Conversion
No Effect
AE 3007A-72-115
2
Engine - Accessory Drive Gearbox - New Mounting Stud No Effect Washers
AE 3007A-72-116
Cancelled Prior to Publication
AE 3007A-72-117
Engine - AE 3007A1/1 2nd-stage High-pressure-turbine Vane Assembly - Rework to the AE 3007A1 Configuration
No Effect
List of Service Bulletins R
Page 4 Oct 20/16
EXPORT CONTROLLED
Bulletin Number AE 3007A-72-118
Incorporated in Manual
Rev Subject 2
AE 3007A-72-119
Engine - Split-inner-race Ball Bearing - New Bearing (23061084 or 23071692)
No Effect
Cancelled Prior to Publication
AE 3007A-72-120
2
Engine - Rework the Low Pressure Turbine Case Assembly
AE 3007A-A-72-121 ALERT
2
Superceded by AE 3007A-A-72-099
AE 3007A-A-72-122 ALERT
3
Engine - Outer Bypass Duct Molded Insert Assembly Pull No Effect Test
AE 3007A-72-123
No Effect
Cancelled Prior to Publication
AE 3007A-72-124
1
Superceded by AE 3007A-72-193
No Effect
AE 3007A-72-125
1
Engine - Outer Bypass-Duct Assembly - Molded Insert Test
No Effect
AE 3007A-72-126
7
Engine - AE 3007A1 to AE 3007A1/1 Engine Reidentification
No Effect
AE 3007A-72-127
Cancelled Prior to Publication
AE 3007A-72-128
Cancelled Prior to Publication
AE 3007A-72-129
Engine - Seal Retainer (23059830) to (23069646) Rework
AE 3007A-72-130
1
Superceded by AE 3007A-72-126
AE 3007A-A-72-131 ALERT
7
Superceded by AE 3007A-72-321
AE 3007A-72-132
Cancelled Prior to Publication
AE 3007A-72-133
Cancelled Prior to Publication
AE 3007A-72-134
Cancelled Prior to Publication
AE 3007A-72-135
5
No Effect
No Effect
Engine - AE 3007A1/1 to AE 3007A1 Engine Reidentification
No Effect
AE 3007A-72-136
Cancelled Prior to Publication
AE 3007A-72-137
Cancelled Prior to Publication
AE 3007A-72-138
Cancelled Prior to Publication
AE 3007A-72-139
Engine - 1st-stage High Pressure Turbine Wheel - Shot Peening
No Effect
AE 3007A-72-140
1
Engine - 2nd-stage High-pressure Turbine Wheel - Shot Peening
No Effect
AE 3007A-72-141
3
Superceded by AE 3007A-72-321
No Effect
AE 3007A-A-72-142 ALERT
5
Engine - Fan Spinner Assembly - Inspection
No Effect
AE 3007A-A-72-143 ALERT
6
Engine - Front Frame Assembly - Rework
No Effect
List of Service Bulletins R
Page 5 Oct 20/16
EXPORT CONTROLLED
Bulletin Number
Incorporated in Manual
Rev Subject
AE 3007A-72-144
5
Engine - AE 3007A1 to AE 3007A1/3 Engine Re-Identification
No Effect
AE 3007A-72-145
5
Engine - AE 3007A1/3 to AE 3007A1 Engine Re-Identification
No Effect
AE 3007A-72-146
Cancelled Prior to Publication
AE 3007A-72-147
Engine - Replace the 1st-stage High Pressure Turbine Blades
No Effect
AE 3007A-72-148
4
Engine - AE 3007A1 to AE 3007A1P Engine Reidentification
No Effect
AE 3007A-72-149
4
Engine - AE 3007A1P to AE 3007A1 Engine Reidentification
No Effect
AE 3007A-72-151
Cancelled Prior to Publication
AE 3007A-A-72-152 ALERT
Engine - Compressor Shaft Cone Assembly - Life Limit Decrease
No Effect
AE 3007A-72-153
4
Engine - AE 3007A1/1 High-pressure-turbine Assembly and Combustion Liner Upgrade to the AE 3007A1 Configuration
No Effect
AE 3007A-72-154
2
Engine - AE 3007A to AE 3007A1/1 Engine Conversion
No Effect
AE 3007A-72-155 AE 3007A-A-72-156
Cancelled Prior to Publication 5
Engine - New Fan Teflon Lip Seal (23072308)
No Effect
AE 3007A-72-157
Engine - 1st- to 2nd-stage Turbine Spacer Serial Number No Effect Marking
AE 3007A-72-158
Cancelled Prior to Publication
AE 3007A-72-159
4
Engine - AE 3007A1 to AE 3007A3 Engine Reidentification
No Effect
AE 3007A-72-160
3
Engine - AE 3007A3 to AE 3007A1 Engine Reidentification
No Effect
AE 3007A-72-161 AE 3007A-72-162
Cancelled Prior to Publication 5
Engine - New Rear Turbine Bearing Support (23073081) No Effect (Aft Sump Rework)
AE 3007A-72-163
Cancelled Prior to Publication
AE 3007A-72-164
Cancelled Prior to Publication
AE 3007A-72-165
4
Superceded by AE 3007A-72-332
No Effect
AE 3007A-72-166
5
Engine - New 1st- and 2nd-stage Low Pressure Turbine Blades and 2nd-stage Low Pressure Turbine Vane Ring
No Effect
AE 3007A-72-167
3
Engine - New Fan Spinner Assembly (23070964)
No Effect
AE 3007A-72-168
2
Engine - New Inlet Housing Hub Flowpath Extension (23073167)
No Effect
AE 3007A-72-169
Cancelled Prior to Publication
List of Service Bulletins R
Page 6 Oct 20/16
EXPORT CONTROLLED
Bulletin Number
Incorporated in Manual
Rev Subject
AE 3007A-72-171
3
Engine - New Center Sump Hardware to Reduce High Main Oil Pressure
No Effect
AE 3007A-72-172
3
Engine - New Compressor Stub Shaft (23072226)
No Effect
Engine - Inspect the Coating on the Stationary Labyrinth Spacer (23057980)
No Effect
AE 3007A-A-72-173 ALERT AE 3007A-72-174
1
Engine - Install the ITT Trim Plug (23058854-01)
No Effect
AE 3007A-72-175
2
Engine - New 1st-stage High-pressure Turbine Blades with Anti-fret Coating
No Effect
AE 3007A-72-176
5
Engine - Remove the 2nd-stage High Pressure Turbine Wheel Balance Weights
No Effect
AE 3007A-72-177
1
Superceded by AE 3007A-72-261
AE 3007A-A-72-178 ALERT
3
Engine - Reset the Inlet Guide Vanes
No Effect
AE 3007A-A-72-179 ALERT
3
Engine - Acid Etch Inspection of the 2nd-stage High Pressure Turbine Wheel
No Effect
Engine - New LH and RH Core External Engine Service Manifold Assemblies
No Effect
AE 3007A-72-180 AE 3007A-72-181
1
Engine - Inspect the HP-LP Turbine Seal Installation
No Effect
AE 3007A-72-182
1
Engine - New No. 5 Carbon Seal (23073831)
No Effect
AE 3007A-72-184
Engine - New Center Sump Forward Stationary Seal (23073794)
No Effect
AE 3007A-72-185
Cancelled Prior to Publication
AE 3007A-72-186
1
Engine - New 1st-stage High-pressure Turbine Vane Assembly (23073494)
No Effect
AE 3007A-72-187
2
Engine - New 8th- thru 13th-stage Compressor Vane Assemblies
No Effect
Engine - Remove the Cruciform Bolts from the Fan-bearing Support Housing
No Effect No Effect
AE 3007A-72-188 AE 3007A-72-189
1
Engine - New 2nd-stage High-pressure Turbine Blades with Anti-fret Coating
AE 3007A-72-190
3
Superceded by AE 3007A-75-020
AE 3007A-72-191
Engine - Accessory Gearbox - Install the Drain Plug
No Effect
AE 3007A-72-192
1
Engine - Replace the 1st-stage High-pressure Compressor Blades
No Effect
AE 3007A-72-193
1
Engine - Replace the Identification Plate
No Effect
AE 3007A-72-194
1
Engine - Outer Bypass Duct - New Threaded Insert Assembly (23071788)
No Effect
AE 3007A-72-195
1
Engine - Fan Wheel Inspection
No Effect
List of Service Bulletins R
Page 7 Oct 20/16
EXPORT CONTROLLED
Bulletin Number
Incorporated in Manual
Rev Subject
AE 3007A-72-196
Engine - RTBS Oil Supply Tube Wear Prevention Kit (23074075)
No Effect
AE 3007A-A-72-197 ALERT
Engine - New Stationary Labyrinth Seal (23073906)
No Effect
AE 3007A-72-198
2
Engine - New Rear Turbine Bearing Support Oil Supply Tube (23073941)
No Effect
AE 3007A-72-199
4
Engine - New HP to LP Turbine Seal Assembly (23073953)
No Effect
AE 3007A-A-72-201 ALERT
3
Superceded by AE 3007A-72-230
AE 3007A-72-202
3
Engine - New Compressor-to-turbine Shaft (23073165) No Effect and Compressor Shaft Cone Assemblies (23073282 and 23076016)
AE 3007A-72-203
1
Engine - New Fan (No. 0) Bearing Support Housing
AE 3007A-72-205
No Effect
Cancelled Prior to Publication
AE 3007A-A-72-207 ALERT
2
Engine - New Fan Carbon Seal Internal Retaining Ring
No Effect
AE 3007A-72-208
2
Engine - New 1st-stage Compressor Blade Rear Retainer Ring (23074307)
No Effect
Engine - New Outer Bypass Duct Bleed Port Adapter
No Effect
AE 3007A-72-209 AE 3007A-72-210
3
Engine - Inspect the High-pressure Turbine 1st-stage Vanes and Blades
No Effect
AE 3007A-72-211
1
Engine - No. 6 Carbon Seal Assembly Test
No Effect
AE 3007A-72-212
3
Engine - Inspect the Low-pressure Turbine Forward Shaft (23059694 and 23067076)
No Effect
AE 3007A-72-213
3
Engine - New HP-LP Low Diameter Seal Kit
No Effect
Engine - New No. 4 Bearing Spanner Nut (23074208)
No Effect No Effect
AE 3007A-72-214 AE 3007A-72-215
2
Engine - Install the 2nd-stage High-pressure Turbine Wheel Balance Weights (23038853)
AE 3007A-72-216
1
Engine - New Rear Turbine Bearing Support (23073940) No Effect
AE 3007A-72-217
Engine - Install the ITT Trim Plug (23058854-01) for the AE 3007A Series Engines
AE 3007A-72-218
Cancelled Prior to Publication
AE 3007A-72-219
1
AE 3007A-72-220
No Effect
Superceded by AE 3007A-74-005 Engine - Inspect the Fan Blades
No Effect
AE 3007A-A-72-225 ALERT
2
Engine - Monitor the High-pressure Turbine 1st-stage Vane Assembly
No Effect
AE 3007A-72-226
1
Engine - Front Frame Mounting-pad Bores Inspection and Repair
No Effect
List of Service Bulletins R
Page 8 Oct 20/16
EXPORT CONTROLLED
Bulletin Number
Incorporated in Manual
Rev Subject
AE 3007A-72-227
Cancelled Prior to Publication
AE 3007A-72-228
Engine - Test the Upper Bevel-gear Oil Manifold Assembly for Flow and Target
No Effect
AE 3007A-72-229
Engine - Install the Mid-span Bearing with Loctite 290
No Effect
Engine - New Mid-span Bearing Housing Cover
No Effect
AE 3007A-72-230
2
AE 3007A-72-231
Cancelled Prior to Publication
AE 3007A-72-232
Engine - New 1st, 2nd, and 3rd-stage LP Turbine Blade Tracks
No Effect
AE 3007A-72-234
Engine - New Front Frame Assembly (23074816) and Retention Plates (23075057)
No Effect
AE 3007A-72-235
2
Superceded by AE 3007A-72-321
AE 3007A-72-237
Engine - Accessory Gearbox Identification Plate
No Effect
AE 3007A-72-238
Engine - Outer Bypass Duct - New Composite Flange Reinforcement Plate
No Effect No Effect
AE 3007A-72-239
1
Engine - Rework the No. 6 Bearing Insert
AE 3007A-72-240
5
Engine - New 6th- thru 13th-stage Chrome Carbide No Effect Coated Knife Seal Compressor Wheels and Honeycomb Vanes
AE 3007A-72-241
8
Engine - New Cool Air Buffered Center Sump
Jan 20/13
AE 3007A-72-242
1
Engine - New Mid-span Bearing Housing with Retaining Cover
No Effect
AE 3007A-72-243
2
Engine - Front Sump Housing Assembly Inspection
No Effect
AE 3007A-72-244
3
Engine - 1st-stage Compressor Wheel Bore Inspection
No Effect
AE 3007A-72-246
1
Superceded by AE 3007A-72-327
AE 3007A-72-247
8
Engine - Reinforcing Plates (23075877) for plug Repaired Front Frame Forward Flange
No Effect
AE 3007A-72-248
3
Engine - New HP-LP Low-diameter Turbine Seal Kit (23074649)
No Effect
Engine - New 7th-stage Compressor Wheel (23074217)
No Effect No Effect
AE 3007A-72-250 AE 3007A-72-251
1
Engine - Inspection of the Front Sump
AE 3007A-72-253
3
Superceded by AE 3007A-72-321
AE 3007A-72-254
Engine - Thick Bore 13th and 14th-stage Compressor Wheels
No Effect
AE 3007A-72-255
4
Engine - Compressor Cone Shafts and Tie Bolt - Rework No Effect
AE 3007A-72-256
2
Engine - New Center Sump Forward Stationary Seal
No Effect
AE 3007A-72-257
1
Engine - New Center Sump Rear Stationary Seal
No Effect
Engine - Replace Harness Support Bracket on the Forward and Aft Front Frame Splitline
No Effect
AE 3007A-72-258
List of Service Bulletins R
Page 9 Oct 20/16
EXPORT CONTROLLED
Bulletin Number
Incorporated in Manual
Rev Subject
AE 3007A-72-259
Engine - New No. 5 Carbon Seal Kit
No Effect Apr 20/15
AE 3007A-72-260
11
Engine - New High Pressure Turbine Upgrade (Block III)
AE 3007A-72-261
1
Engine - Two Piece Compressor Rear Air Seal Assembly No Effect
AE 3007A-72-262
1
Engine - Accessory Drive Gearbox Assembly - New Starter Mounting Pad Cover Configuration
AE 3007A-72-263
2
Superceded by AE 3007A-72-284
AE 3007A-72-264
No Effect
Engine - New One Piece Rear Compressor Seal
No Effect
AE 3007A-A-72-265
3
Engine - 1st to 2nd-stage High Pressure Turbine Spacer Inspection
No Effect
AE 3007A-72-266
1
Engine - No. 4 Ball Bearing Inspection
No Effect
AE 3007A-72-267
1
Engine - AE 3007A1E to AE 3007A1 Engine Reidentification
No Effect
AE 3007A-72-268
1
Superceded by AE 3007A-72-324
AE 3007A-72-269
2
Engine - AE 3007A1 to AE 3007A1E Engine Reidentification
AE 3007A-72-270
1
Superceded by AE 3007A-72-325
AE 3007A-72-272
No Effect
Cancelled Prior to Publication
AE 3007A-72-273
1
Engine - Change the Location of the Compressor Vibration Accelerometer
AE 3007A-72-274
1
Engine - Accessory Gearbox Starter Pad Drain - Remove No Effect the Drain Cap or Starter Drain Adapter
AE 3007A-72-275
4
Engine - New Front Sump Assembly
No Effect
AE 3007A-72-276
4
Engine - New Right and Left Hand Coverplates and Transfer Tubes
Apr 20/10
Engine - Radial Quill Shaft Screening (23056789)
No Effect
AE 3007A-72-277
Oct 20/12
AE 3007A-72-278
4
Engine - Accessory Drive Gearbox Assembly - New FPMU Drive Gear
No Effect
AE 3007A-72-279
2
Engine - New Front Frame Assembly
No Effect
AE 3007A-72-280
8
Engine - 1st-stage High Pressure Turbine Blade Rework
No Effect
Engine - 2nd-stage High Pressure Turbine Blade Rework
No Effect
Engine - Effusion-cooled Combustion Liner Assembly Re-release (23071148)
No Effect
AE 3007A-72-284
Engine - Rework the HP to LP Turbine Seal Assembly
No Effect
AE 3007A-72-285
Engine - New Diffuser to HPT Case Tube Support Bracket
No Effect
AE 3007A-72-286
Engine - Compressor Diffuser (23073092) - Chamfer the No Effect Aft End of Inner Flange
AE 3007A-72-281 AE 3007A-72-283
2
List of Service Bulletins R
Page 10 Oct 20/16
EXPORT CONTROLLED
Bulletin Number
Incorporated in Manual
Rev Subject
AE 3007A-72-287
3
Engine - Rear Outer-bypass-duct Support Assembly Rework
No Effect
AE 3007A-72-288
1
Engine - New 1st-stage Compressor Inner Ring Segment No Effect Assembly with XPT Coating - Rework
AE 3007A-72-289
1
Engine - Rework the Front Frame Assembly and Install the New Single Forward Ground Handling Bracket
No Effect
AE 3007A-72-290
3
Engine - New Front Frame and Lifting Bracket
No Effect
AE 3007A-72-291
2
Engine - New Rear Turbine Bearing Support and Forced No Effect Mixer Core Flow Path Support Assembly
AE 3007A-72-292
Engine - New Low-pressure Turbine Case Assembly (23079336)
No Effect
AE 3007A-72-293
Engine - New 1st-stage Low Pressure Turbine Wheel (23076801) with Brush Seal Land Removed
No Effect
AE 3007A-72-294
1
Engine - Center Sump Scavenge and Pressure/Vent Oil Tubes - High Temperature O-rings Installation
No Effect
AE 3007A-72-295
1
Engine - New Outer-bypass Duct and Access Covers
No Effect
AE 3007A-72-296
Cancelled Prior to Publication
AE 3007A-72-297
Engine - New Effusion - Cooled Combustion Liner Assemblies (23077461 and 23078026)
No Effect
AE 3007A-72-298
4
Engine - AE 3007A1/1, AE 3007A1/3, AE 3007A1, AE 3007A1P, or AE 3007A3 to AE 3007A1E Engine Conversion
No Effect
AE 3007A-72-299
2
Engine - New Radial Drive Quill Shaft (23077207)
No Effect
AE 3007A-72-300
Engine - Inspection of the Fan Blade Forward Retainer Assembly (23062491)
No Effect
AE 3007A-72-301
Cancelled Prior to Publication
AE 3007A-72-302
Engine - New O-ring (M83485/1-047) for the No. 3 Bearing Damper
No Effect
AE 3007A-72-303
2
Engine - New Fan (No. 0) Bearing Oil Nozzle (23076966) Oct 20/09
AE 3007A-72-304
1
Superceded by AE 3007A-72-361
AE 3007A-72-305
1
Engine - New Compressor-to-turbine Shaft Heat Shield (23078706, 23079062)
No Effect
AE 3007A-72-306
2
Engine - New Combustion Liner - Cast Bracket
No Effect
Engine - Increased Compressor Tie Bolt Stretch Value
No Effect
AE 3007A-72-308 AE 3007A-72-309
2
Engine - New 2nd-stage Low Pressure Turbine Vane and No Effect Seal Assembly
AE 3007A-72-310
4
Engine - Measure the Stretch of the Compressor Tie Bolt No Effect
AE 3007A-72-311
Engine - New Compressor Diffuser Assembly (23079071)
No Effect
List of Service Bulletins R
Page 11 Oct 20/16
EXPORT CONTROLLED
Bulletin Number
Incorporated in Manual
Rev Subject
AE 3007A-A-72-312 ALERT
1
Superceded by AE 3007A-A-72-313
AE 3007A-A-72-313 ALERT
2
Superceded by AE 3007A-72-314
AE 3007A-72-314
1
Engine - Inspection of 3rd-stage Low Pressure Turbine Blades
No Effect
AE 3007A-72-315
2
Engine - Combustion Liner Inner-wall Borescope Inspection
No Effect
AE 3007A-72-321
2
Engine - Accessory Drive Gearbox Assembly - New Starter Shaft Seal
No Effect
AE 3007A-72-322
Engine - New Glass-peened 1st-stage Compressor Blade (23079367)
No Effect
AE 3007A-72-323
Engine - New 1st-stage HPT Blade (23079436)
No Effect
AE 3007A-72-324
Engine - No. 4 Ball Bearing Inspection
No Effect
AE 3007A-72-325
Engine - No. 4 Ball Bearing Inspection
No Effect
AE 3007A-72-326
Engine - New 1st-stage HPT Blade (23079576)
No Effect
AE 3007A-72-327
Engine - New Teflon Seal (23080495)
No Effect
AE 3007A-72-328
1
Engine - New Front Sump Housing (23080647) without Anti-rotation Pin
No Effect
AE 3007A-72-329
1
Engine - Front Sump Assembly and Related Components Inspection for Oil Leakage
No Effect
AE 3007A-72-330
1
Engine - Accessory Gearbox Starter Pad Drain - Install No Effect the Open Starter Drain Adapter (23083402 or 23077526)
AE 3007A-72-331
3
Engine - New Fan Bearing Support Housing Assembly (23081557) and Liner (23080768)
No Effect
AE 3007A-72-332
1
Engine - New Low Pressure Turbine Rear-shaft Plug O-ring (23078077-5)
No Effect
AE 3007A-72-333
6
Engine - Inspection of 3rd, 4th, 5th, & 13th-stage Compressor Wheels
No Effect
AE 3007A-72-334
2
Superceded by AE 3007A-72-348
AE 3007A-72-335
1
Superceded by AE 3007A-72-348
AE 3007A-72-336
Engine - Upper and Lower Rear Turbine-bearing-support No Effect Heat Shield Washer (MS14151-3)
AE 3007A-72-337
2
Superceded by AE 3007A-72-348
AE 3007A-72-338
3
Engine - Inspection of the Fan Spinner Assembly
No Effect
AE 3007A-72-339
1
Engine - Bevel Pinion Gearshaft - Rework
No Effect
AE 3007A-72-341
2
Engine - Examine the Front Frame at the Front Sump Mounting Surface
No Effect
List of Service Bulletins R
Page 12 Oct 20/16
EXPORT CONTROLLED
Bulletin Number AE 3007A-72-343 AE 3007A-72-345
Incorporated in Manual
Rev Subject
3
AE 3007A-A-72-346 ALERT
Engine - New Bypass Duct Rear Support Assembly (23079823)
No Effect
Engine - Bolted 2nd- and 3rd-stage Low Pressure Turbine Vane-and-seal Assembly
No Effect
Engine - 2nd- & 3rd-stage Compressor Wheels - Life Limit Decrease
No Effect
AE 3007A-72-347
2
Superceded by AE 3007A-72-376
AE 3007A-72-348
5
Superceded by AE 3007A-72-401
AE 3007A-72-349
2
Engine - Front Sump Bevel Gear Retaining Ring Inspection
No Effect
AE 3007A-72-350
2
Engine - Rework of the Accessory Gearbox Input Bevel Gearshaft
No Effect
AE 3007A-72-351
3
Engine - Rework the Front Sump Bevel Gear
No Effect
AE 3007A-72-352
1
Engine - 2nd-stage High Pressure Turbine Wheel (23074462) - Fluorescent Penetrant Inspection
No Effect
AE 3007A-72-353
Cancelled Prior to Publication
AE 3007A-72-354
Engine - Replace Suspect 3rd-stage Compressor Wheels
No Effect
AE 3007A-72-355
1
Engine - Replace Specific 3rd-, 5th-, and 6th-stage Compressor Wheels
No Effect
AE 3007A-72-356
1
Engine - 1st- and 2nd-stage High Pressure Turbine Wheel - Fluorescent Penetrant Inspection
No Effect
AE 3007A-72-357
Engine - Compressor Cone Shaft Assembly Inspection
No Effect
AE 3007A-72-358
Cancelled Prior to Publication
AE 3007A-72-359
1
Engine - Reworked Combustion Liners with New Ferrule Swirler Assembly (23088816)
No Effect
AE 3007A-72-360
3
Superceded by AE 3007A-72-045
AE 3007A-72-361
2
Engine - Redesigned One Piece Fan Spinner (23087826)
No Effect
AE 3007A-72-363
3
Engine - Rework the Outer Bypass Duct - Molded Insert Assembly with New Self-locking Square Nut (23088288)
No Effect
AE 3007A-72-364
3
Engine - Outer Bypass Duct Molded Insert Assembly with New Self-locking Square Nut (23088288)
No Effect
AE 3007A-72-365
Engine - New Access Cover (23088582) (with Bleed Port No Effect Adapter) with New Blind Insert Square Nuts (23088288)
AE 3007A-72-366
Engine - 2nd-stage High Pressure Turbine Wheel Fluorescent Penetrant Inspection
AE 3007A-A-72-367 ALERT
2
No Effect
Engine - 2nd-stage High Pressure Turbine Wheel - Eddy No Effect Current Inspection
List of Service Bulletins R
Page 13 Oct 20/16
EXPORT CONTROLLED
Bulletin Number
Incorporated in Manual
Rev Subject
AE 3007A-72-368
3
Engine - 2nd-stage High Pressure Turbine Wheel Ultrasonic Testing Inspection
No Effect
AE 3007A-72-369
2
Engine - 2nd-stage High Pressure Turbine Wheel Ultrasonic Testing Inspection in an Engine Shipping Stand
No Effect
AE 3007A-72-370
Engine - Alternate Input Bevel Gear Ball Bearing (23064227)
No Effect
AE 3007A-72-371
Engine - New 2nd-stage Low Pressure Turbine Blade (23088549) and Smashplate (23087913)
No Effect
AE 3007A-72-372
Engine - Non-slotted 2nd-stage Low Pressure Turbine Bladed Wheel Assemblies (23088283 and 23088284)
No Effect
Engine - Replace Specific 5th- and 6th-stage Compressor Wheels
No Effect
AE 3007A-72-373
2
AE 3007A-72-375
Engine - New Center Sump Forward Impeller (23089048) No Effect
AE 3007A-72-376
Engine - Change the Configuration of the Front Sump Housing Assembly
No Effect
Engine - 2nd-stage High Pressure Turbine Wheel Inspection Cycles
No Effect
Engine - Peened 2nd-stage High Pressure Turbine Wheel - Eddy Current Inspection
No Effect
Engine - Cool Front Sump Housing Assembly Configuration for the AE 3007A1E Engine
No Effect
AE 3007A-72-380
Engine - New Split Inner-race (No. 1) Ball Bearing (23087679)
No Effect
AE 3007A-72-381
Engine - Examine the 6th- thru 13th-stage Compressor Vanes for Missing Braze Fillet
No Effect
AE 3007A-A-72-377 ALERT
2
AE 3007A-72-378 AE 3007A-72-379
AE 3007A-72-382
2
2
AE 3007A-72-383
Superceded by AE 3007A-72-411 Engine - No. 4 Carbon Seal Runner (23087178)
No Effect
AE 3007A-72-384
1
Engine - Accessory Gearbox Cable Assemblies (23089681 and 23089682)
No Effect
AE 3007A-72-385
1
Engine - Air Distribution Ring Chamfer Dimensional Inspection
No Effect
AE 3007A-A-72-386 ALERT
5
Engine - 6th- thru 13th-stage Chrome-carbide Coated and Uncoated Compressor Wheel Knife Edge Seals Jentek Eddy Current Inspection
No Effect
AE 3007A-72-388
4
Engine - 6th- thru 13th-stage Compressor Wheel Knife Edge Seals - Jentek Eddy Current Inspection
No Effect
AE 3007A-72-389
1
Engine - Development Components Removal from AE 3007A2 Flight Test Engines
No Effect
AE 3007A-A-72-390 ALERT
3
Engine - Inspection of 6th- thru 13th-stage Compressor Wheel Circumferential Pocket Area
No Effect
List of Service Bulletins R
Page 14 Oct 20/16
EXPORT CONTROLLED
Bulletin Number
Incorporated in Manual
Rev Subject
AE 3007A-72-391
Engine - New Center Sump Stud Nut (23087278-09) with No Effect Lower Torque Values
AE 3007A-72-392
2
Superceded by AE 3007A72-397
AE 3007A-72-393
2
Superceded by AE 3007A-72-397
AE 3007A-72-394
1
Engine - Change the Test Development Engines to AE 3007A2 Production Standard
AE 3007A-72-395 AE 3007A-72-397
Cancelled Prior to Publication 1
AE 3007A-72-398
Engine - Rework the Honeycomb Seal of the 6th- thru 13th-stage Compressor Vane Assemblies
1
Superceded by AE 3007A-72-401
AE 3007A-72-401
1
Superceded by AE 3007A-72-415
AE 3007A-72-402 2
AE 3007A-72-404 AE 3007A-72-405
No Effect
Cancelled Prior to Publication
AE 3007A-72-399
AE 3007A-72-403
No Effect
1
AE 3007A-72-406
Engine - New Aft Sump Cover Packing (23090504)
No Effect
Engine - Shot Peen Rework of Unpeened Low Pressure Turbine Wheels
No Effect
Engine - One-piece Compressor Rear Stationary Seal (23089859)
No Effect
Engine - Improved Non-cooled Front Sump Configuration No Effect Engine - New 6th- thru 13th-stage Aluminum Oxide Compressor Wheel Knife Edge Seals and Increased Honeycomb Compressor Vane Radii
No Effect
AE 3007A-A-72-407 ALERT
2
Engine - 1st- and 2nd-stage High Pressure Turbine Wheel Life Limit Decrease
No Effect
AE 3007A-A-72-408 ALERT
3
Engine - High Pressure Turbine 2nd-stage Wheel Bore Eddy Current Inspection
No Effect
AE 3007A-72-409
Engine - New Fan Wheel (23077611)
No Effect
AE 3007A-72-410
Engine - Alternate No. 2A Roller Bearing Retaining Bolts No Effect (MS9556-08) with Loctite 242
AE 3007A-72-411
Engine - Inspection of 6th- thru 13th-stage Compressor Wheel Knife Edge Seals - Ultrasonic Testing Inspection
No Effect
AE 3007A-72-412
Engine - Cool Air Buffered Center Sump Diffuser Scavenge Oil Tube Notched Sleeve (23091543)
No Effect
AE 3007A-72-413
1
Engines - Accessory Gearbox Retention Cables (23090244)
No Effect
AE 3007A-A-72-414 ALERT
1
Engine - Unpeened or Partially Peened 2nd-stage High Pressure Turbine Wheel Life limit Decrease
No Effect
AE 3007A-72-415
3
Engine - Compressor Front Sump No. 4 Dual (High Temp) Carbon Seal (23089654) with No. 3 Bearing Spacer (23075612)
No Effect
List of Service Bulletins R
Page 15 Oct 20/16
EXPORT CONTROLLED
Bulletin Number AE 3007A-72-416
Incorporated in Manual
Rev Subject Engine - New Fan Bearing Support Housing Assembly (23091498) with Bolted Bearing Cage (23091495)
Oct 20/14
AE 3007A-72-417
Engine - Fan Drive Shaft Bearing Nut (23091119)
No Effect
AE 3007A-A-72-419 ALERT
Engine - High Pressure Turbine 1st-stage Wheel Life Limit Decrease Due to Possible Steel Contamination
No Effect
AE 3007A-72-420
Glass-peened 1st-stage Compressor Blade (23079367) - No Effect Introduction of Soft Life Limits
AE 3007A-72-421
1
1
Engine - High Pressure Turbine 1st and 2nd-stage Wheel Bore Eddy Current Inspection
No Effect
AE 3007A-72-422
Engine - Compressor Non-cooled Front Sump Fabricated No Effect Housing (23090801)
AE3007A-72-425
Engine - New Center Sump Aft Stud Nut (23087278-09) With Improved High Temperature Characteristics
No Effect
Engine - Ultrasonic Inspection of the Fan Wheel
No Effect
AE 3007A-72-429
Engine - Non-CABCS Diffuser Bottom Oil Drain Hole
No Effect
AE 3007A-72-430
Engine - 3rd-Stage Low-Pressure-Turbine Blade Replacement
No Effect
AE 3007A-72-431
Engine - Rework the Compressor Diffuser Assembly
No Effect
AE 3007A-A-72-427 ALERT
AE 3007A-72-432
1
1
Engine - Compressor Front Sump No. 4 Carbon Tandem No Effect Seal Runner with 24 Holes
AE 3007A-73-001
Cancelled Prior to Publication
AE 3007A-73-002
Cancelled Prior to Publication
AE 3007A-73-003
3
Engine Fuel and Control - New Right Hand and Left Hand Fuel Manifold, Fuel Manifold-to-service Manifold Tubes and Pressure Scavenge, and Vent Oil Tubes
AE 3007A-73-004
Cancelled Prior to Publication
AE 3007A-73-005
Engine Fuel and Control - Fuel Tube and FADEC A Harness Clamping
AE 3007A-73-006
Cancelled Prior to Publication
AE 3007A-73-007
Cancelled Prior to Publication
AE 3007A-73-008
Cancelled Prior to Publication
No Effect
No Effect
AE 3007A-73-009
2
Engine Fuel and Control - New Fuel Pump-and-metering No Effect Unit (FPMU 106)
AE 3007A-73-010
2
Superceded by AE 3007A-73-014
AE 3007A-73-011
Cancelled Prior to Publication
AE 3007A-A-73-012 ALERT
Engine Fuel and Control - Examine the Fuel Manifold and Install Additional Clamps
No Effect
List of Service Bulletins R
Page 16 Oct 20/16
EXPORT CONTROLLED
Bulletin Number
Incorporated in Manual
Rev Subject
AE 3007A-73-013
2
Engine Fuel and Control - Fuel Pump-and-metering Unit (FPMU) Intermediate Drive Shaft Inspection
AE 3007A-A-73-014 ALERT
4
Superceded by AE 3007A-73-021
AE 3007A-73-015
No Effect
Cancelled Prior to Publication
AE 3007A-73-016
4
Superceded by AE 3007A-73-021
AE 3007A-73-017
1
Superceded by AE 3007A-73-021
AE 3007A-73-018
1
Superceded by AE 3007A-73-014
AE 3007A-73-019
1
Superceded by AE 3007A-73-044
AE 3007A-73-020
2
Engine Fuel and Control - New Fuel Pump-and-metering No Effect Unit Impending Fuel Filter Blockage Indicator
AE 3007A-73-021
3
Superceded by AE 3007A-73-025
AE 3007A-73-022
3
Engine Fuel and Control - New FADEC with Software Version II.6 for the AE 3007A1 Engine
AE 3007A-73-023
No Effect
Cancelled Prior to Publication
AE 3007A-A-73-024 ALERT
2
Engine Fuel and Control - N1/N2 Over-speed Annunciation FADEC Self-test - Inspection
AE 3007A-73-025
5
Engine Fuel and Control - New FADEC with Software No Effect Version VI.7 for the AE 3007A and AE 3007A1/1 Engines
AE 3007A-73-026
1
Engine Fuel and Control - Label the FADEC
No Effect
AE 3007A-73-027
1
Engine Fuel and Control - New FADEC with Software Version IV.2 for the AE 3007A1/3 Engine
No Effect
AE 3007A-73-028
2
Engine Fuel and Control - New FADEC with Software Version IV.2 for the AE 3007A1 Engine
No Effect
AE 3007A-73-029
1
Engine Fuel and Control - New FADEC with Software Version IV.2 for the AE 3007A1P Engine
No Effect
AE 3007A-73-030
1
Engine Fuel and Control - New FADEC with Software Version B4.3 for the AE 3007A3 Engine
No Effect
AE 3007A-73-031
Cancelled Prior to Publication
AE 3007A-73-032
Engine Fuel and Control - New FPMU Magnetic Seal
AE 3007A-73-033
Cancelled Prior to Publication
AE 3007A-73-034
Cancelled Prior to Publication
AE 3007A-73-035
Cancelled Prior to Publication
AE 3007A-73-036
Cancelled Prior to Publication
AE 3007A-73-037
Cancelled Prior to Publication
AE 3007A-73-038
Cancelled Prior to Publication
AE 3007A-73-039
Cancelled Prior to Publication
AE 3007A-73-040
Cancelled Prior to Publication
No Effect
No Effect
List of Service Bulletins R
Page 17 Oct 20/16
EXPORT CONTROLLED
Bulletin Number
Incorporated in Manual
Rev Subject
AE 3007A-A-73-041 ALERT
2
Engine Fuel and Control - Replace the FADEC
No Effect
AE 3007A-A-73-042 ALERT
1
Engine Fuel and Control - Repair the FADEC
No Effect
AE 3007A-73-043
3
Engine Fuel and Control - New FADEC with Software Version B5.1.1 for the AE 3007A and AE 3007A1/1 Engines
No Effect
AE 3007A-73-044
2
Engine Fuel and Control - New FADEC with Software Version B5.1.1 for the AE 3007A1 Engine
No Effect
AE 3007A-73-045
2
Engine Fuel and Control - New FADEC with Software Version B5.1.1 for the AE 3007A1P Engine
No Effect
AE 3007A-73-046
2
Engine Fuel and Control - New FADEC with Software Version B5.1.1 for the AE 3007A1/3 Engine
No Effect
AE 3007A-73-047
2
Engine Fuel and Control - New FADEC with Software Version B5.1.1 for the AE 3007A3 Engine
No Effect
AE 3007A-73-048
2
Superceded by AE 3007A-73-053
AE 3007A-73-049 AE 3007A-73-050
Engine Fuel and Control - Fuel Pump and Metering Unit - No Effect Main Metering Valve Servo Valve 1
Engine Fuel and Control - Clearance Inspection between No Effect the Fuel Manifold and the Aft-sump Forward Pressure Oil Tube
AE 3007A-73-051
Engine Fuel and Control - Repair the FADEC with the Suspect A02 Digital Card
No Effect
AE 3007A-73-052
Engine Fuel and Control - Repair the FADEC with the Suspect A03 Digital Card
No Effect
Engine Fuel and Control - Replace the Fuel Pump-and-metering Unit
No Effect
Engine Fuel and Control - Replace the Fuel Pump and Metering Unit
No Effect
Engine Fuel and Control - Fuel Supply Nozzle
No Effect
Engine Fuel and Control - Replace the Fuel Pump-and-metering Unit
No Effect No Effect
AE 3007A-73-053
3
AE 3007A-73-054 AE 3007A-73-055
1
AE 3007A-73-056 AE 3007A-73-057
2
Engine Fuel and Control - Fuel Pump-and-metering Unit - Fuel Filter Electrical Impending-bypass Indicator Inspection
AE 3007A-73-058
3
Engine Fuel and Control - FADEC CA Identification Label No Effect
AE 3007A-73-059
Engine Fuel and Control - New FADEC with Software Version B7.5 for the AE 3007A1 Engine
No Effect
AE 3007A-73-060
Engine Fuel and Control - New FADEC with Software Version B7.5 for the AE 3007A1/1 Engine
No Effect
List of Service Bulletins R
Page 18 Oct 20/16
EXPORT CONTROLLED
Bulletin Number
Incorporated in Manual
Rev Subject
AE 3007A-73-061
Engine Fuel and Control - New FADEC with Software Version B7.5 for the AE 3007A1/3 Engine
No Effect
AE 3007A-73-062
Engine Fuel and Control - New FADEC with Software Version B7.5 for the AE 3007A3 Engine
No Effect
AE 3007A-73-063
Engine Fuel and Control - New FADEC with Software Version B7.5 for the AE 3007A1P Engine
No Effect
AE 3007A-73-064
Engine Fuel and Control - New FADEC with Software Version B7.5 for the AE 3007A1E Engine
No Effect
AE 3007A-73-065
Cancelled Prior to Publication
AE 3007A-73-066
Engine Fuel and Control - New FADEC Hardware for the No Effect AE 3007A, AE 3007A1/1, AE 3007A1, AE 3007A1P, AE 3007A3, AE 3007A1/3 Engines
AE 3007A-73-067
Engine Fuel and Control - New FADEC with Software Version B7.6 for the AE 3007A1 Engine
No Effect
AE 3007A-73-068
1
Engine Fuel and Control - New FADEC with Software Version B7.6 for the AE 3007A3 Engine
No Effect
AE 3007A-73-069
1
Engine Fuel and Control - New FADEC with Software Version B7.6 for the AE 3007A1/3 Engine
No Effect
AE 3007A-73-070
Engine Fuel and Control - New FADEC with Software Version B7.6 for the AE 3007A1P Engine
No Effect
AE 3007A-73-071
Engine Fuel and Control - New FADEC with Software Version B7.6 for the AE 3007A1/1 Engine
No Effect
AE 3007A-73-072
Engine Fuel and Control - New FADEC with Software Version B7.6 for the AE 3007A1E Engine
No Effect
AE 3007A-73-073
2
Engine Fuel and Control - New FADEC Diode Adapter
No Effect
AE 3007A-73-074
1
Engine Fuel and Control - Compressor Variable Geometry Actuator Fuel Transfer Manifold
No Effect
AE 3007A-73-075
1
Engine Fuel and Control - New FADEC with Software Version B8.0 for the AE 3007A1 Engine
Apr 20/08
AE 3007A-73-076
1
Engine Fuel and Control - New FADEC with Software Version B8.0 for the AE 3007A1/1 Engine
Apr 20/08
AE 3007A-73-077
1
Engine Fuel and Control - New FADEC with Software Version B8.0 for the AE 3007A1/3 Engine
Apr 20/08
AE 3007A-73-078
1
Engine Fuel and Control - New FADEC with Software Version B8.0 for the AE 3007A1E Engine
Apr 20/08
AE 3007A-73-079
1
Engine Fuel and Control - New FADEC with Software Version B8.0 for the AE 3007A1P Engine
Apr 20/08
AE 3007A-73-080
1
Engine Fuel and Control - Remove the Inner Duct Aft Support Assemblies
No Effect
AE 3007A-73-081
1
Engine Fuel and Control - New CVG Actuator Front Frame Inner Fuel Cap Assembly (23084070)
No Effect
List of Service Bulletins R
Page 19 Oct 20/16
EXPORT CONTROLLED
Bulletin Number
Incorporated in Manual
Rev Subject
AE 3007A-73-082
2
Engine Fuel and Control - New FADEC with Software Version B8.0.5 for the AE 3007A1 Engine
No Effect
AE 3007A-73-083
3
Engine Fuel and Control - New FADEC with Software Version B8.0.5 for the AE 3007AP1 Engine
No Effect
Engine Fuel and Control - New FADEC with Software Version B8.1 for the AE 3007A1 Engine
No Effect
AE 3007A-73-084 AE 3007A-73-085
1
Engine Fuel and Control - Replace Suspect Fuel Nozzles No Effect (23075904 and 23077006)
AE 3007A-73-086
1
Engine Fuel and Control - Rework the Fuel Pump and Metering Unit (23076368)
No Effect
AE 3007A-73-087
1
Engine Fuel and Control - Rework the Fuel Pump and Metering Unit (23077658)
No Effect
AE 3007A-73-088
1
Engine Fuel and Control - Replace the Fuel Pump and Metering Unit 106
No Effect
AE 3007A-73-089
Engine Fuel and Control - New FADEC with Software Version B9.2 for the AE 3007A2 Engine
No Effect
AE 3007A-73-090
Engine Fuel and Control - Install the High Speed ITT Trim Plug for the AE3007A Series Engines
Apr 20/14
AE 3007A-73-091
Engine Fuel and Control - Rework the Fuel Pump and metering Unit (FPMU 106 to FPMU 108)
No Effect
AE 3007A-73-092
Engine Fuel and Control - Reidentification of FADEC Assembly for the AE 3007A1 and AE 3007A1/3 Engines
No Effect
AE 3007A-73-093
1
Engine Fuel and Control - New FADEC with Software Version B9.4 for the AE 3007A2 Engine
No Effect
AE 3007A-73-094
2
Engine Fuel and Control - New FADEC with Software Version B9.4 for the AE 3007A1 Engine
No Effect
AE 3007A-73-095
2
Engine Fuel and Control - New FADEC with Software Version B9.4 for the AE 3007A1/1 Engine
No Effect
AE 3007A-73-096
2
Engine Fuel and Control - New FADEC with Software Version B9.4 for the AE 3007A1/1 Engine
No Effect
AE 3007A-73-097
2
Engine Fuel and Control - New FADEC with Software Version B9.4 for the AE 3007A1/1 Engine
No Effect
AE 3007A-73-098
2
Engine Fuel and Control - New FADEC with Software Version B9.4 for the AE 3007A1/1 Engine
No Effect
AE 3007A-73-099
Engine Fuel and Control - Fuel Pump and Metering Unit, No Effect Type: FPMU 200
AE 3007A-73-100
Engine Fuel and Control - Replacement of Piloted Flow Fuel Nozzles (23065950 and 23062915)
No Effect
AE 3007A-73-101
Engine Fuel & Control - New FADEC with Software Version B9.4.1 for the AE 3007A2 Engine
No Effect
List of Service Bulletins R
Page 20 Oct 20/16
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Bulletin Number
Incorporated in Manual
Rev Subject
AE 3007A-73-102
Engine Fuel & Control - New FADEC with Software Version B9.4.1 for the AE 3007 A1 Engine
No Effect
AE 3007A-73-103
Engine Fuel & Control - New FADEC with Software Version B9.4.1 for the AE 3007A1 Engine
No Effect
AE 3007A-73-104
Engine Fuel & Control - New FADEC with Software Version B9.4.1 for the AE 3007A1/3 Engine
No Effect
AE 3007A-73-105
Engine Fuel & Control - New FADEC with Software Version B9.4.1 for the AE 3007A1/3 Engine
No Effect
AE 3007A-73-106
Engine Fuel & Control - New FADEC with Software Version B9.4.1 for the AE 3007A1/3 Engine
No Effect
AE 3007A-74-001
Cancelled Prior to Publication
AE 3007A-74-002
Cancelled Prior to Publication
AE 3007A-74-003
1
Ignition - Permanent-magnet Alternator-stator and Rotor Inspection
AE 3007A-74-004
1
Superceded by AE 3007A-74-006 and AE 3007A-74-007
AE 3007A-74-005
5
Ignition - Permanent Magnet Alternator Rotor and Stator Inspection
No Effect
AE 3007A-74-006
3
Ignition - Replace the Permanent Magnet Alternator Stator
No Effect
AE 3007A-74-007
2
Ignition - Permanent Magnet Alternator Rotor Inspection
No Effect
Ignition - Permanent Magnet Alternator Rotor Inspection and Replacement
No Effect
AE 3007A-74-008
No Effect
AE 3007A-74-009
8
Ignition - New Ignition Exciter (23077617) and External Engine Indicating (EEI) Harness (23077618)
No Effect
AE 3007A-74-010
2
Igniter - Replace the Igniter (23084762) with Tungsten Electrode
No Effect
AE 3007A-75-001
4
Air - Improved Engine Bleed Control System
No Effect
AE 3007A-75-002
Cancelled Prior to Publication
AE 3007A-A-75-003 ALERT
3
Superceded by AE 3007A-75-005
AE 3007A-75-004
3
Superceded by AE 3007A-75-015
No Effect
AE 3007A-A-75-005 ALERT
2
Air - Compressor Variable Geometry System Dynamic Pressure Test
No Effect
AE 3007A-75-006
3
Superceded by AE 3007A-75-004
AE 3007A-75-007 AE 3007A-75-008
Cancelled Prior to Publication 1
AE 3007A-75-009 AE 3007A-75-010 AE 3007A-75-011
Air - New Service Bleed Manifold Adapter
No Effect
Cancelled Prior to Publication 3
Superceded by AE 3007A-75-020
No Effect
Cancelled Prior to Publication
List of Service Bulletins R
Page 21 Oct 20/16
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Bulletin Number
Incorporated in Manual
Rev Subject
AE 3007A-75-012
1
Superceded by AE 3007A-75-015
AE 3007A-75-013
1
Air - New Compressor Variable Vane Torquetube System Assembly Hardware
AE 3007A-75-014
No Effect
Cancelled Prior to Publication
AE 3007A-75-015
1
Air - New Torquetube Assembly (23071270)
No Effect
AE 3007A-75-016
2
Air - Bleed Control Tube - Clamping
No Effect
AE 3007A-75-017
Air - Inspect the Torquetube Assembly (23069629)
No Effect
AE 3007A-75-018
Air - Compressor Air Bleed Valve Assembly - Rework
No Effect
AE 3007A-75-019
Air - New Compressor Acceleration Bleed Valve and Adapter Kit
Apr 20/10
AE 3007A-75-020
4
Air - New Start Bleed Control Valve Support Bracket and Apr 20/10 Inlet Flexible Tube
AE 3007A-75-021
2
Air - New Compressor Bleed Manifold Assembly
Apr 20/10
AE 3007A-75-022
1
Air - Compressor Variable Geometry Inspection Using the Turnbuckle Length
No Effect
AE 3007A-75-023
1
Superceded by AE 3007A-75-027
AE 3007A-75-024
5
Superceded by AE 3007A-75-033
AE 3007A-75-025
1
Air - New Customer-services Outer Manifold Attachment Bolts (MS9565-08)
No Effect
AE 3007A-75-026
1
Air - Lockwire or Safety Cable the Customer-services Outer Manifold Attachment Bolts
No Effect
AE 3007A-75-027
2
Superceded by AE 3007A-75-037
AE 3007A-75-028
Cancelled Prior to Publication
AE 3007A-75-029
Air - Replace the Compressor Variable Geometry (CVG) Actuator, Type: VGA 200
No Effect
AE 3007A-75-030
Air - Customer-services Outer Manifold - New Outer Bypass Duct Gasket (23079466)
No Effect
AE 3007A-75-031
Air - New Compressor Variable Geometry Actuator (23079713)
No Effect
AE 3007A-75-032
1
Air - Remove the Lower-center-sump No Effect Buffer-exhaust-pipe Assembly (23073117) and Install the New Diffuser Coverplate (23080138)
AE 3007A-75-033
1
Air - Customer-services Outer Manifold Inspection
Apr 20/10
AE 3007A-75-034
1
Air - Rework the Customer-services Core Manifold (23073458)
No Effect
AE 3007A-75-035
1
Air - New CVG Actuating Cylinder Mounting Bracket (23084046)
No Effect
AE 3007A-75-036
1
Air - Outer Bypass Duct - Customer-service Outer Manifold Molded Insert Inspection and Repair
No Effect
List of Service Bulletins R
Page 22 Oct 20/16
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Bulletin Number
Incorporated in Manual
Rev Subject
AE 3007A-75-037
3
Air - New Outer Customer Services Manifold (23084756) No Effect
AE 3007A-75-038
2
Superceded by AE 3007A-75-040
AE 3007A-75-039
4
Air - 14th-stage Compressor Discharge Air Tube Inspection
No Effect
Air - Left-hand Compressor Discharge Air Tube V-band Clamp Inspection
No Effect
AE 3007A-75-040 AE 3007A-75-041
2
Air - 14th-stage Compressor Discharge Air Tube Bracket No Effect
AE 3007A-75-042
Air - Right-hand 14th-stage Compressor Discharge Air Tube Inspection
No Effect
AE 3007A-75-043
Air - New Angle Bracket (MS9600-058) at the No. 11 Fuel Nozzle Location
No Effect
Air - New Center-sump Buffer-vent-air Tube Restrictor Plug (23091076)
Jul 20/15
AE 3007A-75-045
Air - Compressor Bleed Air RH Discharge Tube (23092525)
No Effect
AE 3007A-76-001
Cancelled Prior to Publication
AE 3007A-76-002
Cancelled Prior to Publication
AE 3007A-75-044
AE 3007A-76-003
3
3
Engine Controls - New Harness Routing and Clamping
No Effect
AE 3007A-76-004
Cancelled Prior to Publication
AE 3007A-76-005
Engine Controls - External Engine Control (B) Harness Assembly - New Clamping
No Effect
AE 3007A-76-006
2
Engine Controls - Install the Heat-shrinkable Tubing Around, or Tape the ITT Harness Connectors
No Effect
AE 3007A-76-007
1
Engine Controls - Install the Heat-shrinkable Tubing Around, or Tape the P2.5 Sensor Harness Connectors (For Engines That Do not Have FADEC Software Version IV.2, V1.7, B4.3 or Subsequent installed)
No Effect
AE 3007A-76-008
2
Engine Controls - Install the Heat-shrinkable Tubing No Effect Around, or Tape the P2.5 Sensor Connectors (For Engines That Have FADEC Software Version IV.2, V1.7, B4.3 or Subsequent installed)
AE 3007A-76-009
Engine Controls - Spiral Wrap the External Engine Control Harnesses
No Effect
AE 3007A-76-010
Engine Controls - Re-route External Engine Wiring Harnesses on Forward Lower Left Side of Engine
No Effect
AE 3007A-76-011
4
Engine Controls - Electrical Connectors - Inspection and Wrapping
No Effect
AE 3007A-77-001
2
Engine Indicating - Fan-speed-sensor Hole Plug
No Effect
AE 3007A-77-002
1
Superceded by AE 3007A-77-004
No Effect
AE 3007A-77-003
Cancelled Prior to Publication
List of Service Bulletins R
Page 23 Oct 20/16
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Bulletin Number AE 3007A-77-004
1
AE 3007A-77-005 AE 3007A-77-006
Incorporated in Manual
Rev Subject Engine Indicating - Tighten the ITT Harness Connectors Cancelled Prior to Publication 1
Superceded by AE 3007C-76-006
AE 3007A-77-007
Cancelled Prior to Publication
AE 3007A-77-008
Cancelled Prior to Publication
AE 3007A-77-009
Cancelled Prior to Publication
AE 3007A-77-010
No Effect
Engine Indicating - New Quad Element N1 Speed Sensor (23076155 or 23087704)
No Effect
AE 3007A-77-011
Engine Indicating - Examine the Vibration Sensors
No Effect
AE 3007A-77-012
Engine Indicating - Replace a Suspect Group of Thermocouple Wiring Harnesses (23059920 and 23059921)
No Effect
AE 3007A-78-001
Cancelled Prior to Publication
AE 3007A-78-002
1
1
AE 3007A-78-003 AE 3007A-78-004
9
AE 3007A-78-005 AE 3007A-78-006
Exhaust - New Rear Turbine Bearing Support and Exhaust Cone Assembly
No Effect
Exhaust - New Core Flowpath Forced Mixer Support Assembly (23076313)
No Effect
Exhaust - New Forced Core-to-bypass Mixer (23077972) Jul 20/13 Exhaust - New Forced Core-to-bypass Mixer (23077972) Jul 20/13 with RTBS Heat Shields
1
Superceded by AE 3007A-78-007
AE 3007A-78-007
Exhaust - Forced Core-to-bypass Mixer Inspection
AE 3007A-79-001
Cancelled Prior to Publication
AE 3007A-79-002
2
AE 3007A-79-003 AE 3007A-79-004
3
AE 3007A-79-005
No Effect
Oil - Oil Tank Vent Hole
No Effect
Oil - New Lube-and-scavenge Pump
No Effect
Oil - Replace the Oil-level-and-low-oil-Warning Sensor
No Effect
Cancelled Prior to Publication
AE 3007A-79-006
2
Oil - Rework the Fuel-cooled Oil Cooler (FCOC)
No Effect
AE 3007A-79-007
2
Oil - Rework the Oil-filter Unit
No Effect
AE 3007A-79-008
Cancelled Prior to Publication
AE 3007A-79-009
1
Oil - Oil Tank Inspection For Operation With Increased MOP
AE 3007A 79-010
5
Oil - New Vent System Tubes (23065523 and 23065524) Jul 15/99
AE 3007A-A-79-011 ALERT
1
Superceded by AE 3007A-A-79-014
AE 3007A-79-012
Cancelled Prior to Publication
AE 3007A-79-013
Cancelled Prior to Publication
No Effect
No Effect
List of Service Bulletins R
Page 24 Oct 20/16
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Bulletin Number
Incorporated in Manual
Rev Subject
AE 3007A-A-79-014 ALERT
4
Oil - Inspection for Center Sump Oil Debris
No Effect
AE 3007A 79-015
4
Oil - Plug the Oil Tank Vent Hole
No Effect
AE 3007A-79-016 AE 3007A 79-017
Cancelled Prior to Publication 4
Oil - Inspect the Scavenge Oil Aft-sump Rear and Forward Oil Scavenge Tubes
No Effect
AE 3007A-79-018
Cancelled Prior to Publication
AE 3007A-79-019
Cancelled Prior to Publication
AE 3007A-A-79-020 ALERT
Oil - Monitor the Engine Oil Temperature
No Effect
AE 3007A-79-021
7
Oil - New Center Sump Vent Tubes
No Effect
AE 3007A-79-022
2
Oil - Remove the Oil Tube (23061066)
No Effect
AE 3007A-A-79-023 ALERT
2
Oil - Superceded by AE 3007A-79-026
No Effect
AE 3007A-A-79-024 ALERT
1
Oil - Superceded by AE 3007A-79-026
No Effect
AE 3007A-79-025
2
Oil - New Oil Tank Pressure Relief Kit
No Effect
AE 3007A-79-026
2
Oil - New Oil Pressure Sensor (23073475)
No Effect
AE 3007A-A-79-027 ALERT
2
Superceded by AE 3007A-79-033
No Effect
Oil - Inspect the Oil Pressure Sensor (23073475)
No Effect
AE 3007A-79-028 AE 3007A-79-029
1
Oil - New Oil Pressure Sensor (23073715)
Jan 20/11
AE 3007A-79-030
1
Oil - New Aft Sump Oil Scavenge Tubes and Multiple Tube Support Bracket Assembly
No Effect
AE 3007A-79-032 AE 3007A-79-033
Cancelled Prior to Publication 1
AE 3007A-79-034
Superceded by AE 3007A-79-034 Oil - Oil Inspection for Debris
No Effect
AE 3007A-79-035
2
Oil - Oil Pressure/Temperature Sensor Inspection
No Effect
AE 3007A-79-037
2
Oil - New Low Oil-pressure Switch
No Effect
AE 3007A-79-039
2
Oil - New Line Tee-to-accessory Gearbox Pressure Oil tube (23080854)
Jan 20/12
AE 3007A-79-040
2
Oil - Air-cooled Oil Cooler (ACOC) Bolts (MS9556-18)
No Effect
AE 3007A-79-041
1
Superceded by AE 3007A-79-040
AE 3007A-79-042
1
Oil - New Accessory Gearbox Scavenge Outlet Screen (23086796)
AE 3007A-79-043
No Effect
Oil - New Fuel Cooled Oil Cooler-to-line Tee Pressure Oil No Effect Tube (23086653)
List of Service Bulletins R
Page 25 Oct 20/16
EXPORT CONTROLLED
Bulletin Number
Incorporated in Manual
Rev Subject
AE 3007A-79-044
1
Oil - Change the Position of the Rear Turbine Bearing Support (RTBS) Aft Vent Tube Clamp
No Effect
AE 3007A-79-045
1
Oil - New Oil Tank Mounting Bracket (23090111)
No Effect
AN ASTERISK (*) IN THE REVISION COLUMN INDICATES THAT THE BULLETIN HAS NOT YET BEEN PUBLISHED AS OF THIS MANUALS CURRENT REVISION DATE.
List of Service Bulletins R
Page 26 Oct 20/16
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INTRODUCTION 1.
General A.
The Fault Isolation Manual (1) The AE 3007A Series Fault Isolation Manual (FIM) is part of a set of manuals that helps the operator do the necessary maintenance to the engine. It is written so a technician who does not know the engine can isolate and correct failures of engine systems and components. Use the FIM when the engine is installed on the aircraft.
B.
Related Manuals (1) The manuals included in the set are the: -
Fault Isolation Manual (FIM)
-
Illustrated Tool and Equipment Manual (ITEM)
-
Engine Manual (EM)
-
Engine Illustrated Parts Catalog (EIPC)
(2) The other manuals referred to by the FIM are the:
2.
Aircraft Maintenance Manual (AMM) for the Embraer EMB 145
-
Fault Isolation Manual (FIM) for the Embraer EMB 145
-
Wiring Manual (WM) for the Embraer EMB 145
The Specification of this Manual A.
3.
-
This manual is written to the Air Transport Association of America Specification No. 100 (ATA 100), Revision 33. The writing rules and the vocabulary are in accordance with the AECMA Simplified English document No. PSC-85-16598 Revision 5. All the spelling is in American English.
Manual Content A.
Manual Frontmatter. (1) The FIM contains a set of manual frontmatter and a set of chapters. The manual frontmatter includes: -
Title page
-
Record of Revisions
-
List of Effective Pages
-
Table of Contents
-
List of Service Bulletins
-
Introduction
-
FIM Usage
-
EICAS Message List
-
Maintenance Message List
EFFECTIVITY: ALL
INTRO Page 1 Oct 20/15
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B.
-
FADEC Discrete List
-
Observed Fault List
The Chapter Number System. (1) Each chapter has a List of Effective Pages and a Record of Temporary Revisions. The FIM has the following chapters:
C.
-
Chapter 72 - Engine
-
Chapter 73 - Engine Fuel and Control
-
Chapter 74 - Ignition
-
Chapter 75 - Air
-
Chapter 76 - Engine Controls
-
Chapter 77 - Engine Indicating
-
Chapter 78 - Exhaust
-
Chapter 79 - Engine Oil
-
Chapter 80 - Starting
Identification Code. (1) An identification code that has six numbers divides the chapter into its related parts. This identification code is divided into three elements. Each element contains two numbers. the code divides the data into:
D.
-
Chapter/System (First element)
-
Section/Sub-system (Second element)
-
Subject/Unit (Third element)
Page Block and Topic Contents (1) Page Block 101 - Fault Code Index. (a) This index gives the correct fault isolation task number for each fault code. (2) Page Block 201 - Fault Isolation Tasks. (a) These fault isolation diagrams give the technician the data necessary to isolate and correct faults in the engine or its systems. (3) Page Block 301 - Task Support. (a) These diagrams give the technician the data about each engine system and/or component necessary to isolate and correct the faults. These include wiring diagrams and system block diagrams.
E.
The Figure Number System. (1) The figure number system in a page block is the same as the page number system. For example, the second figure in a Task Support page block is Figure 302. The figures for the fault isolation tasks are found at the end of each CH-SE-SU.
EFFECTIVITY: ALL
INTRO Page 2 Oct 20/15
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F.
Tab Dividers. (1) At the front of each chapter there is a yellow tab card. The chapter number and title are printed on the tab. There is also a yellow tab card at the front of the Introduction, FIM Usage, EICAS Message List, Maintenance Message List, FADEC Discrete List, and the Observed Fault List.
G.
The List of Effective Temporary Revisions. (1) The List of Effective Temporary Revisions (LETR) is issued with a Temporary Revision (TR). The LETR lets the operator make a record of the TRs that are applicable to this manual. (2) The page identification code, which includes the CH-SE-SU code, is given at the bottom right side of each page.
H.
The Chapter List of Effective Pages. (1) The List of Effective Pages (LEP) of a chapter gives a list, in page block sequence, of pages contained in the chapter. The LEP includes a list of the Contents and the LEP pages. (2) The data adjacent to each page number on the LEP shows the correct revision date for that page. The number of pages contained in a chapter and the data on each page must agree with the LEP data. (3) Each time a chapter has a revision, a new LEP is issued to give the new revision date of the changed pages.
I.
Data in this Manual. (1) EICAS Message List. (a) This is an alphabetically-sequenced list of all engine-related alert and status messages that you can see on the EICAS. (b) The level of each message (Caution, Warning, or Advisory), a description of the conditions necessary for the message to be set, a fault code number, and a fault isolation task number are given. The fault code numbers for EICAS messages use a letter M(731M001 00) to show that they are related to a message. (2) Maintenance Message List. (a) This is an alphabetically-sequenced list of all the engine-related maintenance messages recorded in the central maintenance computer (CMC). (b) A maintenance message number and a fault isolation task number are given for each message. (3) FADEC Discrete List. (a) This is a numerically-sequenced list of all the FADEC fault discrete labels, and their related fault bits, that can be accessed from the CMC. (b) The label name (acronym) and number are given.
EFFECTIVITY: ALL
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(c) The field name (acronym), a description of the field name and the fault isolation task number are given for each fault bit. (4) Observed Fault List. (a) This is an alphabetically-sequenced list of engine-related faults that are not found through an EICAS or maintenance message. (b) A description of the fault, a fault code, and a fault isolation task number are given for each observed fault. (c) Engine exceedance events recorded on the CMC are considered observed faults. (5) Fault Code Index. (a) This is a numerically-sequenced list of all the engine-related fault codes, found at the front of each chapter. (b) These fault codes are given only to observed faults and those faults related to an EICAS message. Faults related to a maintenance message are not given fault codes. (c) This index references you from a fault code to any related maintenance messages and the correct FIM task. (6) Fault Isolation Tasks. (a) These are the procedures used to isolate and correct the fault. (b) The fault isolation procedures are given in diagrams. (c) Each fault isolation task includes the following: 1
A title, identifying the method of fault indication or detection; an EICAS message, a maintenance message, or an observed fault.
2
A description of the fault and the conditions necessary for the fault to occur.
3
A list of possible causes is given.
4
A sequence of numbered blocks, each containing instructions to do the tasks or tests, followed by a question. All of the blocks will refer to a procedure necessary to accomplish the task or test. 1 You must start in the block at the upper left-hand corner of the page, and move down and/or to the right. The YES or NO answer to the question in the previous block will show the direction to move. 2 The right column of blocks contain the final corrective action(s). In some instances, the column on the left will refer you to a task in the MM. The task in the MM can contain procedures that give the final corrective action(s).
5
EFFECTIVITY: ALL
A task number, using the AMTOSS (Aircraft Maintenance Task Oriented Support System) numbering system (Ref. Fig. 1).
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(7) Task Support (chapter level). (a) These figures are given to help the technician understand each system or subsystem. (b) The wiring and block diagrams for each system (if applicable) can be found at the end of each CH-SE-SU. (8) For data related to on-wing maintenance and/or special maintenance, use the applicable manual. Refer to the list given in para A.(2) of this Introduction. 4.
Central Maintenance Computer A.
Function of the Central Maintenance Computer (CMC) (aircraft component). (1) The CMC processes and stores maintenance messages, engine exceedance data, engine trend data, flight leg summary data, and a FADEC fault word snapshot for the 10 most recent flights. This data can be downloaded to a personal computer (PC), through an RS-232 interface, using the data acquisition software (DAS). Most engine-related maintenance messages can also be seen on the multi-function display (MFD), when the aircraft is on the ground. The FADEC analog and discrete parameters can be viewed, in real-time, on the PC during all of the aircraft operating conditions (ground/flight), and are automatically downloaded with the maintenance messages and/or the trend and exceedance data. The DAS will automatically create a file and store the CMC data, that is being accessed, onto the hard drive of the PC. The default directory in which the DAS stores data is C:\PROGRAM FILES\DAS\Aircraft\Aircraft_Tail_number. The title of the files created are: E0000DDMMMYYI.dat
Exceedance data
F0000DDMMMYYI.1/2/A/B/C/D.dat
FADEC Analog and FADEC Discrete Label
F0000DDMMMYYI.dat
Flight leg summary data
M0000DDMMMYYI.dat
Maintenance data
N0000DDMMMYYI.dat
FADEC fault word snapshot
T0000DDMMMYYI.dat
Trend data
(2) Performing a CMC download of each FADEC before power is shutdown will record all faults that occurred during a flight. The data can be stored on the hard drive of a PC or on a floppy disk. Performing a CMC download is an essential source of information for fault isolation. (3) The CMC can put 100 maintenance messages in its history. The DOWNLOAD REQUIRED message is given, during a download, when the CMC memory is 80% full. If the CMC is not downloaded before the memory is full, then the maintenance messages in the memory will be overwritten by the new messages. (4) The storage of new maintenance messages, caused by the fault isolation procedures, can be prevented by putting the CMC switch, on the maintenance panel, in the INHIBIT position. Some of the fault isolation tasks will tell you to make sure the CMC switch is not in the INHIBIT position during the fault isolation procedure (Ref. Fig. 4).
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B.
How to Get Access to the CMC Data (Ref. 45-45-00 AMM). (1) Using the MFD to see the maintenance messages. (a) Supply electrical power to the aircraft, if necessary. (b) Make sure the CMC system is operating. (c) Push the MFD MENU button on MFD 1, and then push the MAINT button (Ref. Fig. 2). (d) Not all of the engine-related maintenance messages can be seen on the MFD. You must download the maintenance messages to the PC to see all of the possible messages. (2) Using the PC to download the maintenance messages. (a) Supply electrical power to the aircraft, if necessary. (b) Connect the PC to the RS-232 interface (on the maintenance panel) with the interconnect cable (Ref. Fig. 3, Fig. 4). (c) Make sure the CMC system is operating. (d) Put the power switch for the PC in the ON position. (e) Get access to the DAS. (f)
Select Maint Exceed Message from the Download menu (Ref. Fig. 6).
(g) To see the maintenance messages that have been downloaded, select Maint Exceed Message from the Preview menu (Ref. Fig. 7). (h) Select Exit from the Exit menu to exit from the DAS software. (i)
Put the power switch for the PC in the OFF position.
(j)
Remove electrical power from the aircraft.
(k) Disconnect the PC from the maintenance panel. (3) Using the PC to access the FADEC fault word snapshot. (a) Supply electrical power to the aircraft, if necessary. (b) Connect the PC to the RS-232 interface (on the maintenance panel) with the interconnect cable (Ref. Fig. 3, Fig. 4). (c) Make sure the CMC system is operating. (d) Put the power switch for the PC in the ON position. (e) Get access to the DAS. (f)
Select FADEC Snapshot from the Download menu (Ref. Fig. 6).
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(g) To see the FADEC fault word snapshots that have been downloaded, select FADEC Snapshot from the Preview menu (Ref. Fig. 7). 1
The CMC stores the 10 most recent FADEC fault word snapshots.
2
Each FADEC fault word snapshot contains: 1 A flight identification number. 2 The time (HH:MM) and the date (MM:DD) when the snapshot was taken.
(h) Select Exit from the Exit menu to exit from the DAS software. (i)
Put the power switch for the PC in the OFF position.
(j)
Remove electrical power from the aircraft.
(k) Disconnect the PC from the maintenance panel. (4) Using the PC to download the engine exceedance data. (a) Supply electrical power to the aircraft, if necessary. (b) Connect the PC to the RS-232 interface (on the maintenance panel) with the interconnect cable (Ref. Fig. 3, Fig. 4). (c) Make sure the CMC system is operating. (d) Put the power switch for the PC in the ON position. (e) Get access to the DAS. (f)
Select Trend/Exceedance/FLS from the Download menu (Ref. Fig. 6).
(g) To see the exceedances that have been downloaded, select Exceedance from the Preview menu (Ref. Fig. 7). (h) Select Exit from the Exit menu to exit from the DAS software. (i)
Put the power switch for the PC in the OFF position.
(j)
Remove electrical power from the aircraft.
(k) Disconnect the PC from the maintenance panel.
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C.
How to Use the CMC Data. Rolls-Royce recommends that you do a CMC download before power to the FADECs is shut down. This allows the technician to view currently active faults. If the aircraft has been powered down, then the faults for the 10 most recent flights can be accessed by doing the FADEC fault word snapshot download (Ref. Fig. 7). The oldest flight is displayed first in the FADEC fault word snapshot. Fault isolation tasks frequently require the technician to access the CMC data. When a download is performed, the technician will have the stored information available when the fault isolation task requires the use of the CMC data. All CMC data including maintenance messages, exceedance messages, trend data, flight leg summary data, FADEC analog and FADEC discrete data, and the FADEC fault word snapshot can be viewed from within the CMC for the most recently performed download DAS (Ref. Fig. 7). (1) Maintenance Messages. (a) The maintenance message display includes the following data: -
The date and time of the first occurrence of the message.
-
The date and time of the most recent occurrence of the message.
-
The number of occurrences of the message.
-
The maintenance message text (Ref. Fig. 5).
(b) If the fault that caused a maintenance message to be set is removed, and then occurs again, the occurrence count for the message will be increased and the time of the most recent occurrence will be updated. A new message will not be put in the CMC memory. When the fault that caused a message to be set is present before electrical power is removed from the CMC, and is still present when electrical power is supplied again, the occurrence count will not be increased (Ref. Fig 5). (c) When you access the maintenance messages, the DAS will automatically create a file titled M0000DDMMMYYI.dat. This file will store the maintenance message faults on the hard drive of the PC (Ref. Fig. 8). (2) FADEC Discrete Labels. (a) These discrete labels supply data on the status of the FADEC fault bits. A number 1 shows that the fault bit is set (fault present). A number 0 shows that a fault bit is not set. The FADEC discrete labels are seen in real-time. (b) The maintenance messages do not always contain all of the data necessary to isolate and correct a fault. A maintenance message can be set by many different FADEC fault bits. It is necessary to find the FADEC fault bit that is causing the maintenance message to be set. When you know what fault bit is set, you can go the FADEC Discrete List chapter to locate the FIM task number used to fault isolate the label and bit that is set to 1. (c) The function of some fault bits are to indicate aircraft settings. Therefore, not all bits that are set to 1 require troubleshooting. The shaded areas in (Ref. Fig. 10) represent the fault bits that require no further maintenance action.
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(d) Viewing and storing discrete labels. 1
When you access the discrete label, each label is viewed individually along with its bit settings. Use the data sheet (Ref. Fig. 10) to record the bit settings of each label. The data sheet can then be used as a quick reference for fault isolation tasks.
2
To store the FADEC discrete labels along with their bit settings you must select the FADEC Labels from the Download menu (Ref. Fig. 6). The DAS will automatically create a file (Ref. Fig. 9) titled F0000DDMMMYY.1/2/A/B/C/D.dat. This file will store the FADEC analog and discrete data on the hard drive of the PC. A FADEC fault word snapshot can also be taken by selecting FADEC Snapshot from the Download menu (Ref. Fig. 6). The FADEC fault word snapshot contains a snapshot of all FADEC fault words for the 10 most recent flights. When a FADEC fault word snapshot is taken, a file called N0000DDMMMYYI.dat is stored on the hard drive of the PC. Each FADEC fault word snapshot contains a flight identification number, the time (HH:MM) and the date (MM:DD) of the moment when the snapshot was taken.
3
The file that is created will look similar to Fig. 9. The discrete data is on the bottom half of the page. The column to the right of the Label column will indicate the status of bits 11 through 29 for each label. Each bit will either be a 0 or a 1. For example, in Fig. 9, bits 25, 26, 27, and 28 are set to 1 for label 340. Use the data sheet (Ref. Fig. 10) to record the bit settings of each label. The data sheet can then be used as a quick reference for fault isolation tasks.
(3) The FADEC Analog Label. (a) The FADEC analog label supplies the analog data processed by the FADEC. (b) The fault isolation tasks frequently require the technician to access the FADEC analog label. The FADEC analog label is seen in real-time, and supplies data such as; thrust lever angle, ITT value, N1 RPM, and ITT trim resistance. (c) To access the FADEC analog data select FADEC Label from the Download menu (Ref. Fig. 6). When you access the analog data, the DAS will automatically create a file called F0000DDMMMYYI.1/2/A/B/C/D.dat on the hard drive of the PC (Ref. Fig. 9). (4) Engine Exceedance Data. (a) The CMC monitors the following engine parameters: -
N1
-
N2
-
ITT
-
Vibration (fan)
-
Vibration (core)
-
High oil temperature
-
High fuel temperature
-
Low oil pressure
-
FADEC Overtemperature
(b) The CMC stores the engine data if an engine parameter is more than the limit. EFFECTIVITY: ALL
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(c) The fault isolation tasks frequently require the technician to access the engine exceedance data. Use the exceedance data to make sure of the faults found from other sources. (d) When you access the engine exceedance data by selecting Trend/Exceedance/FLS from the Download menu (Ref. Fig. 6), the DAS will automatically create a file titled E0000DDMMMYYI.dat. This file will store the exceedance data on the hard drive of the PC (Ref. Fig. 9). 5.
Ruggedized Service Unit (RSU). A.
Function of the Ruggedized Service Unit (RSU). The RSU can receive FADEC fault code stores (FCS) from the FADEC memory. The FADEC fault code is caught by the FADEC when a fault is found and is kept in non-volatile memory. If electrical power is removed, the FADEC will not erase this fault history. The RSU will automatically make a file and keep it in the FCS, that is being accessed, on the flash disk of the RSU. The default directory on the RSU flash in which the data is kept is F:\UPLOAD\. A file will be made for each FADEC accessed.
B.
How to get access to the FCS Data.
NOTE: The FCS data must only be accessed by trained personnel. (1) Apply aircraft power to the FADEC. (2) Remove power from the FADEC at the cockpit circuit breaker. (3) Disconnect J5 from the FADEC. (4) The Glenair connectors on the RSU harness are connected in-line, between the FADEC and the aircraft harness. Power to the FADEC will be supplied through this in-line connector. Connect the RSU harness between the aircraft harness and J5 on the FADEC. (5) Connect the 9 pin harness connector to the 9 pin connector on the rear of the RSU. (6) From the RSU Main Menu Screen, set to AIRCRAFT FUNCTIONS. (7) From the Aircraft Selection Screen, type the AIRCRAFT NUMBER. (8) From the Menu Screen, set to READ FADEC DATA. (9) Apply power to the FADEC at the cockpit FADEC circuit breaker. (10) From the FADEC Part Number List, use the RSU number pad to set to the FADEC PART NUMBER that is installed on the aircraft. (11) Type the FADEC Serial Number in the format BXxxxxx. Use the touch pen to push on the screen to type the Alpha characters. Numbers can be typed with the touch pen or on the RSU keypad. Push the green ENT key.
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(12) Type the Rig #. The Rig # is the same as the aircraft tail number and the FADEC's position put together. The Rig # of FADEC 2A on Aircraft N272 will be N2722A. IMPORTANT: The FCS download's filename will be the same as what is typed for the Rig #. Push the green ENT key. (13) Type the aircraft tail number. Push the green ENT key. (14) Type the date the download is done in the configuration of DD-MMM-YYYY. For example, the 16th of August 2001 will be typed as 16-AUG-2001 (you must include the dashes). Push the green ENT key. (15) The FCS file is available on the PCMIA card below the cap on the top of the RSU and can be read with an ASCII text file reader on a PC available with a PCMIA slot. The file will be found at and named as follows: \upload\rig#.txt NOTE: Only qualified personnel can make an analysis of the FCS contents. C.
How to Use the FCS Data. The FCS data contains two primary parts of data used to isolate and correct a fault. The first part is the MMV data recorder and must only be used and have an analysis by Rolls-Royce and Goodrich personnel. The second part of data is the fault code history, given by the newest faults first and are not connected by applying power to the FADEC. This data can be used to do the troubleshooting of maintenance faults. When a fault is found, the FADEC discrete list (S/W Name) must be used to get the FIM troubleshooting task to correct the fault. If a fault in the FCS does not show in the FADEC Discrete List, troubleshooting must be done by direction from Rolls-Royce.
6.
Effectivity A.
The EFFECTIVITY Block. (1) The effectivity block is located in the lower left corner of the page. The effectivity block identifies engine model, maintenance data, or other maintenance information that applies to an applicable version of software. The data must be considered satisfactory for all of the software versions when the effectivity block has been removed or is blank.
7.
Revisions and Service Bulletins A.
Issue of Revisions. (1) The manufacturer regularly issues revisions to the Fault Isolation Manual to keep it at the correct standard. The revisions add, remove and/or change data as necessary. All revisions are by replacement of tasks. You must not use hand-written revisions. (2) A Letter of Transmittal is sent with each revision. The transmittal letter: -
Is the authority to put the revision into the manual.
-
Gives instructions on how to put the revision into the manual.
(3) You are recommended to keep the transmittal letters at the front of the manual for reference.
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(4) Each revision has a specified number and date. Revisions start at No. 1 and have numbers in sequence after that. (5) A Record of Revisions page is located at the front of the manual. When you put a revision into the manual, you must write the revision number and its issue date on the Record of Revisions page. B.
Temporary Revisions. (1) When it is necessary to include data in the manual quickly, a Temporary Revision (TR) is issued. The first page of the TR gives the transmittal instructions. The data/instructions in a TR replace the equivalent data/instructions in Each TR is printed on yellow paper. The TR numbers are in sequence and start at - 1 in each chapter. The chapter number goes in front of the TR number to give each TR an identification code. For example 72-1, 72-2, 72-3, and so on, 79-1, 79-2, 79-3, and so on. (2) The data/instructions in a TR are included in a revision (usually, the subsequent revision to the manual) or a subsequent TR replaces it. When a revision includes the data/instructions of a TR, the transmittal letter includes an instruction to remove the applicable TR. When a subsequent TR replaces a TR, the subsequent TR includes an instruction to remove the applicable TR. You must not remove a TR from the manual unless you get an instruction to do so in the Transmittal Letter of a revision or on the first page of a subsequent TR. (3) In each chapter, immediately after the List of Effective Pages page, is a Record of Temporary Revisions page. When you put a TR into the manual, you must write the TR number and the date you put the TR into the manual on the Record of Temporary Revisions. When you remove a TR from the manual, you must write the date you removed the TR from the manual on the Record of Temporary Revisions.
C.
Service Bulletins. (1) At the front of this manual, immediately after the Table of Contents, is the Service Bulletin List. The data given includes the service bulletin (SB) number, title, date, and the date of incorporation into this manual, if applicable.
8.
Customer Service A.
R R R R R
If you find it necessary to write to Rolls-Royce about the manual, please write to: Rolls-Royce Corporation Manager, Technical Publications 450 South Meridian Street Mail Code MC-S2-08 Indianapolis, IN 46206-0420
9.
List of Abbreviations A.
The following is a list of abbreviations used in this manual. A/C
Aircraft
ACOC
Air-cooled Oil Cooler
ADC
Air Data Computer
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AGB
Accessory-drive Gearbox
A/I
Anti-ice
AMM
Aircraft Maintenance Manual
ARINC
Aeronautical Radio Inc.
ATS
Air Turbine Starter
AVSV
Air-vent Solenoid Valve
°C
Degrees Celsius
CABV
Compressor-air Bleed Valve
CABCV
Compressor-acceleration Bleed-control Valve
CB
Circuit Breaker
CCDL
Cross-channel Data Link
CIP
Compressor Inlet Pressure
CIT
Compressor Inlet Temperature
CMC
Central Maintenance Computer
CVG
Compressor Variable Geometry
DAS
Data Acquisition Software
DC
Direct Current
DEC
Decrement
EEPROM
Electronically-Erasable Programmable Read-Only Memory
EICAS
Engine Indicating and Crew Alerting System
EMB
Embraer
°F
Degrees Fahrenheit
FADEC
Full-authority Digital-electronic Control
FCOC
Fuel-cooled Oil Cooler
FIM
Fault Isolation Manual
FPMU
Fuel Pump and Metering Unit
FPMU
Fuel Pump and Metering Unit
HP
High Pressure
HPT
High Pressure Turbine
INC
Increment
IPS
Inches Per Second
ITT
Interstage Turbine Temperature
LH
Left Hand
LP
Low Pressure
LPT
Low Pressure Turbine
LSOV
Latching Shut-off Valve
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LVDT
Linear Variable-Differential Transducer
LVIT
Linear Variable-Inductance Transducer
MFD
Multi-function Display
MM
Maintenance Manual
MMV
Main Metering Valve
MN
Mach Number
N1
Low Pressure Rotor RPM
N2
High Pressure Rotor RPM
P2.5
Air Pressure at the Compressor Inlet
PALT
Pressure Altitude
PC
Personal Computer
PMA
Permanent Magnet Alternator
PRV
Pressure Raising Valve
PSIA
Pounds-per-Square Inch Absolute
PSIG
Pounds-per-Square Inch Gauge
RPM
Revolutions-per-Minute
RH
Right Hand
RTD
Resistance Temperature Device
SB
Service Bulletin
T2.5
Air Temperature at the Compressor Inlet
TAT
Total Air Temperature
TLA
Thrust Lever Angle
TR
Thrust Reverser
VDC
Volts Direct Current
WOW
Weight-on-Wheels
WM
Wiring Manual
10. Electrical Symbol Definition A.
Electrical symbols can be found in (Ref. Fig. 11).
11. Component Location A.
Components and locations can be found in (Ref. Fig. 12 thru Ref. Fig. 17).
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AMTOSS Codes FIG. 1 EFFECTIVITY: ALL
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Multi-funtion Display (MFD) FIG. 2 EFFECTIVITY: ALL
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Central Maintenance Computer (CMC) / PC Interface FIG. 3 EFFECTIVITY: ALL
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Maintenance Panel / CMC Switch FIG. 4 EFFECTIVITY: ALL
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Maintenance Message Display / MFD FIG. 5 EFFECTIVITY: ALL
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PC Screen Maintenance Message Download FIG. 6 EFFECTIVITY: ALL
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DAS Preview FIG. 7 EFFECTIVITY: ALL
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Maintenance Message FIG. 8 EFFECTIVITY: ALL
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Example of an Analog Label Download Page FIG. 9 EFFECTIVITY: ALL
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FADEC Discrete Label Bit Settings Data Sheet FIG. 10 EFFECTIVITY: ALL
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Electrical Symbol Definition FIG. 11 EFFECTIVITY: ALL
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Component Location (Right-hand Engine) FIG. 12 EFFECTIVITY: ALL
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Component Location (Right-hand Engine) FIG. 13 EFFECTIVITY: ALL
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Component Location (Right-hand Engine) FIG. 14 EFFECTIVITY: ALL
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Component Location (Right-hand Engine) FIG. 15 EFFECTIVITY: ALL
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FADEC Location FIG. 16 EFFECTIVITY: ALL
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P0 Sensor Location FIG. 17 EFFECTIVITY: ALL
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EICAS Message List
MESSAGE R ATTCS FAIL
LEVEL
DESCRIPTION
FAULT CODE
FIM TASK
Warning LEI bit is set and ATTCS is not 732M14 10 73-25-00-810-858 armed.
ENG ATTCS FAIL
Warning Either left engine, right engine 732M14 10 73-25-00-810-845 engine, or both running, TLA is more than 46 degrees, an alternate-takeoff thrust mode is selected and ATTCS is not armed.
E1 ATTCS NO MRGN
Warning Aircraft on ground, ITT above 894°C, and alternate-takeoff thrust mode is selected.
731M10 00 73-25-00-810-846
E2 ATTCS NO MRGN
Warning Aircraft on ground, ITT above 894°C, and alternate-takeoff thrust mode is selected.
731M11 00 73-25-00-810-846
E1 CTL FAIL (FADEC SOFTWARE VER. B5.1.1, B7.5 AND B7.6)
Caution Engine 1 MMCVFL bit (28) set; 732M06 00 73-21-00-810-817-A01 MMV failed fixed or CVG failed open.
E1 CTL FAIL Caution Engine 1 MMCVFL bit (28) set; 732M06 00 73-21-00-810-817-B01 (FADEC SOFTWARE VER. B8 MMV failed fixed, High N1 OR LATER) failure or CVG failed open. E2 CTL FAIL (FADEC SOFTWARE VER. B5.1.1, B7.5 AND B7.6)
Caution Engine 2 MMCVFL bit (28) set; 732M07 00 73-21-00-810-817-A01 MMV failed fixed or CVG failed open.
E2 CTL FAIL Caution Engine 2 MMCVFL bit (28) set; 732M07 00 73-21-00-810-817-B01 (FADEC SOFTWARE VER. B8 MMV failed fixed, High N1 OR LATER) failure or CVG failed open. E1 EXCEEDANCE
Caution Engine 1 ITT (or N2) is more than the current ITT (N2) limit.
720M0151
72-00-00-810-823
E2 EXCEEDANCE
Caution Engine 2 ITT (or N2) is more than the current ITT (N2) limit.
720M0152
72-00-00-810-823
E1 FPMU NO DISP (FADEC SOFTWARE VER. B7.5 OR LATER)
Caution Engine 1 has FPMU106 732M0251 installed with A1E thrust rating.
73-21-00-810-822
E2 FPMU NO DISP (FADEC SOFTWARE VER. B7.5 OR LATER)
Caution Engine 2 has FPMU106 732M0252 installed with A1E thrust rating.
73-21-00-810-822
E1 FUEL IMP BYP
Advisory Engine 1 impending-bypass switch open; pressure differential across fuel filter above 9±1 psid.
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733M07 00 73-37-00-810-801
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LEVEL
E2 FUEL IMP BYP
Advisory Engine 2 impending-bypass switch open; pressure differential across fuel filter above 9± 1 psid.
E1 FUEL LOW TEMP
Caution Engine 1 fuel temperature (exit 733M03 00 73-31-00-810-802 of FCOC) below 5°C and N2 above 53%.
E2 FUEL LOW TEMP
Caution Engine 2 fuel temperature (exit 733M04 00 73-31-00-810-802 of FCOC) below 5°C and N2 above 53%.
E1 LOW N1
Warning Engine 1 thrust lever angle 732M1400 moved above 60 degrees and the engine experiences an uncommanded deceleration or when it is unable to achieve its target N1 speed.
E2 LOW N1
Warning Engine 2 thrust lever angle 732M15 00 73-25-00-810-851-B01 moved above 60 degrees and the engine experiences an uncommanded deceleration or when it is unable to achieve its target N1 speed.
E1 NO DISP
Caution Engine 1 No dispatch fault bit set by collector bit FLTGP1.
720M01 00 72-00-00-810-805
E2 NO DISP
Caution Engine 2 No dispatch fault bit set by collector bit FLTGP1.
720M02 00 72-00-00-810-805
ENG NO TO DATA
Caution Aircraft is on the ground or N2 732M11 00 73-25-00-810-835 is above 53%, and takeoff temperature data has not been accepted by the FADEC.
E1 OIL IMP BYP (POST SB EMB 145-79-0001)
Advisory Engine 1 impending-bypass 793M73 00 79-37-00-810-802-A02 switch open; pressure differential across oil filter above 22 ±3 psid, or the circuit for the magnetic indicating plug (oil tank) is competed.
E2 OIL IMP BYP (POST SB EMB 145-79-0001)
Advisory Engine 1 impending-bypass 793M74 00 79-37-00-810-802-A02 switch open; pressure differential across oil filter above 22 ±3 psid, or the circuit for the magnetic indicating plug (oil tank) is competed.
EFFECTIVITY: ALL
DESCRIPTION
FAULT CODE
MESSAGE
FIM TASK
733M08 00 73-37-00-810-801
73-25-00-810-851-B01
EICAS Message List Page 2 Apr 20/09
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LEVEL
E1 OIL LOW PRESS
Warning Engine 1 low oil-pressure 793M01 00 79-37-00-810-803 switch open (34 psig or below) and N2 at or above 53.6%, or low oil-pressure switch closed, N2 below 10% and aircraft on the ground.
E2 OIL LOW PRESS
Warning Engine 2 low oil-pressure 793M02 00 79-37-00-810-803 switch open (34 psig or below) and N2 at or above 53.6%, or low oil-pressure switch closed, N2 below 10% and aircraft on the ground.
ENG1 OUT
Caution Engine 1 has gone out. Shown 720M05 00 72-00-00-810-809 at all times except from V1 to 400ft above the ground.
ENG2 OUT
Caution Engine 2 has gone out. Shown 720M06 00 72-00-00-810-809 at all times except from V1 to 400ft above the ground.
ENG REF A/I DISAG
Caution Position of anti-ice control switches (engine inlet) not the same as position entered during takeoff-data setting procedure, aircraft on the ground and parking brake released, or thrust lever angle moved above 45 degrees.
732M10 00 73-25-00-810-836
E1 SHORT DISP
Advisory Engine 1 Short term dispatch fault bit set by collector bit FLTGP2.
720M03 00 72-00-00-810-806
E2 SHORT DISP
Advisory Engine 2 Short term dispatch fault bit set by collector bit FLTGP2.
720M04 00 72-00-00-810-806
E1 TLA FAIL
Caution No data on thrust lever angle 761M93 00 76-11-00-810-806 available to the FADEC on engine 1, thrust lever angle set to last controlled position.
E2 TLA FAIL
Caution No data on thrust lever angle 761M94 00 76-11-00-810-806 available to the FADEC on engine 2, thrust lever angle set to last controlled position.
FADEC ID NO DISP
Caution FADEC IDs disagree; No dispatch
732M15 10 73-25-00-810-859-A01
FADEC ID NO DISP
Caution FADEC IDs disagree; No dispatch
732M15 10 73-25-00-810-859-B01
EFFECTIVITY: ALL
DESCRIPTION
FAULT CODE
MESSAGE
FIM TASK
EICAS Message List Page 3/4 Apr 20/09
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FIM Usage 1.
General A.
This section supplies the data on how to use the Fault Isolation Manual (FIM)to isolate and correct the faults that can occur.
B.
The engine faults are divided into the following categories: (1) Faults found through the EICAS messages. (2) Faults found through the maintenance messages. (3) Faults found by accessing the FADEC discrete labels on the central maintenance computer (CMC) via the personal computer. (4) Faults found by the observations of the flight crew or maintenance technicians (this includes exceedance events, recorded on the CMC).
C. 2.
When a fault has been found, use the lists in the front of this manual and the Fault Code Index found at each chapter level to find the correct fault isolation task.
Use of the FIM A.
Do the following steps for a fault found through an EICAS message (Ref. FIG. 1): (1) Find the EICAS message on the EICAS Message List. (2) Find the FIM task reference, in the right-hand column of the list. (3) Go to the FIM task.
B.
Do the following steps for a fault found through a maintenance message (Ref. FIG. 1): (1) Find the maintenance message on the Maintenance Message List. (2) Find the FIM task reference in the right-hand column. (3) Go to the FIM task.
C.
Do the following steps for a fault observed by the flight crew or maintenance technicians (Ref. FIG. 1): (1) Find the fault on the Observed Fault List. (2) Find the FIM task reference in the right-hand column. (3) Go to the FIM task.
EFFECTIVITY: ALL
FIM Usage Page 1 Sep 15/03
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D.
Do the following steps to find the FIM task for a FADEC discrete = 1 (Ref. FIG. 1): (1) Find the discrete label number / name on the FADEC Discrete List. (2) Find the discrete field name in the left-hand column. (3) Find the FIM task reference in the right-hand column. (4) Got to the FIM task.
E.
How to use the fault isolation tasks. (1) Each fault isolation task includes the following: (a) A title, identifying the method of fault indication or detection; an EICAS message, a maintenance message or an observed fault. (b) A description of the fault and the conditions necessary for the fault to occur. (c) A list of possible causes is given. (d) A sequence of numbered blocks, each containing instructions to do the tasks or tests, followed by a question. All of the blocks will refer to a procedure necessary to accomplish the task or test. 1
You must start in the block at the upper left-hand corner of the page, and move down and/or to the right. The YES or NO answer to the question in the previous block will show the direction to move.
2
The right column of blocks contains the final corrective action(s). In some instances, the column on the left will refer you to a task in the MM. The task in the MM can contain procedeures that give the final corrective action(s).
(2) Most of the fault isolation tasks have a reference to a figure number (e.g., Ref. Fig. 301). These figures are found in the Task Support section. (a) These figures are given to help the technician understand each system or subsystem. (b) The wiring and block diagrams for each system (if applicable) can be found at the end of each CH-SE-SU. (3) The wiring harness test, found in the fault isolation tasks, must be done as follows: (a) Continuity/resistance -
Pin-to-pin resistance test. The resistance measured must be below the limit given.
(b) Internal shorts -
EFFECTIVITY: ALL
Pin-to-pin resistance test. The resistance between the isolated conductors in a wiring harness must be above the limit given.
FIM Usage Page 2 Sep 15/03
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(c) Shorts to ground -
Pin-to-backshell resistance test. The resistance between the conductors and the overbraid/backshell must be above the limit given.
(4) The fault isolation tasks are based on the following assumptions: (a) The damaged system was operating normally before the fault occurred. (b) The applicable circuit breakers have been examined. (c) All applicable electrical harnesses are connected. (d) Multiple faults have not occurred. (e) The aircraft electrical busses are energized when electrical power is supplied to the aircraft. (f)
The sensors or fault detection and reporting systems are functioning correctly, unless there is an indication that they are damaged.
(g) The maintenance technician knows how to use the FIM and how to access the data in the CMC. (h) The work is being done by an experienced maintenance technician.
EFFECTIVITY: ALL
FIM Usage Page 3 Sep 15/03
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Finding the Fault Isolation Task FIG. 1 EFFECTIVITY: ALL
FIM Usage Page 4 Sep 15/03
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Maintenance Message List
CENTRAL MAINTENANCE COMPUTER (CMC) MAINTENANCE MESSAGE MAINTENANCE MESSAGE TEXT NUMBER
FIM TASK REFERENCE
ENG1 FADEC IN CONTROL PARAMT FAIL (FADEC SOFTWARE VER. B5.1.1)
73PWM63
73-25-00-810-821-A01
ENG1 FADEC IN CONTROL PARAMT FAIL (FADEC SOFTWARE VER. B7.5 OR LATER)
73PWM63
73-25-00-810-821-B01
ENG1 FADEC NOT IN CONTROL 73PWM64 PARAMT FAIL (FADEC SOFTWARE VER. B5.1.1)
73-25-00-810-821-A01
ENG1 FADEC NOT IN CONTROL 73PWM64 PARAMT FAIL (FADEC SOFTWARE VER. B7.5 OR LATER)
73-25-00-810-821-B01
ENG2 FADEC IN CONTROL PARAMT FAIL (FADEC SOFTWARE VER. B5.1.1)
73PWM65
73-25-00-810-821-A01
ENG2 FADEC IN CONTROL PARAMT FAIL (FADEC SOFTWARE VER. B7.5 OR LATER)
73PWM65
73-25-00-810-821-B01
ENG2 FADEC NOT IN CONTROL 73PWM66 PARAMT FAIL (FADEC SOFTWARE VER. B5.1.1)
73-25-00-810-821-A01
ENG2 FADEC NOT IN CONTROL 73PWM66 PARAMT FAIL (FADEC SOFTWARE VER. B7.5 OR LATER)
73-25-00-810-821-B01
ENG1 FUEL HIGH TEMP
72PXM114
73-31-00-810-801
ENG2 FUEL HIGH TEMP
73PWM79
73-31-00-810-801
ENG1 IGNITION SWITCH FAIL
74PWM21
74-30-00-810-801
ENG2 IGNITION SWITCH FAIL
74PWM22
74-30-00-810-801
ENG1 IGNITION SYSTEM FAIL
74PWM53
74-30-00-810-801
ENG2 IGNITION SYSTEM FAIL
74PWM54
74-30-00-810-801
ENG1 ITT SENSOR FAIL
74PWM49
77-21-00-810-801
EFFECTIVITY: ALL
Maintenance Message List Page 1 Jul 20/15
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CENTRAL MAINTENANCE COMPUTER (CMC) MAINTENANCE MESSAGE MAINTENANCE MESSAGE TEXT NUMBER
FIM TASK REFERENCE
ENG2 ITT SENSOR FAIL
74PWM50
77-21-00-810-801
ENG1 LT FAULT
72PXM112
72-00-00-810-807
ENG2 LT FAULT
72PXM113
72-00-00-810-807
ENG1 OIL DEBRIS
79PWM77
79-37-00-810-801
ENG2 OIL DEBRIS
79PWM78
79-37-00-810-801
ENG1 PALTXP0 DIFF FAULT
75PWM23
75-43-00-810-805
ENG2 PALTXP0 DIFF FAULT
75PWM24
75-43-00-810-805
ENG1 PMA POWER FAIL
73PWM61
73-25-00-810-817
ENG2 PMA POWER FAIL
73PWM62
73-25-00-810-817
ENG1 SCHED MAINT REPAIR (FADEC SOFTWARE VER. B4.3 OR LATER)
73PWM80
72-00-00-810-808-B01
ENG2 SCHED MAINT REPAIR (FADEC SOFTWARE VER. B4.3 OR LATER)
72PXM115
72-00-00-810-808-B01
ENG1 T/O SWITCH FAIL
73PWM27
73-25-00-810-841
ENG2 T/O SWITCH FAIL
73PWM28
73-25-00-810-841
ENG1 TR/DEPL/STOW SIGNAL
78PWM51
78-30-00-810-801
ENG2 TR/DEPL/STOW/SIGNAL
78PWM52
78-30-00-810-801
LT - ENG ADC DATA SYS (FADEC SOFTWARE VER. B5.1.1)
73PWM63A
73-10-00-810-811-A01
LT - ENG ADC DATA SYS (FADEC SOFTWARE VER. B7.5 OR LATER)
73PWM63A
73-10-00-810-811-B01
LT - ENG A/G LGDAL SYS
76PWM97A
76-11-00-810-808
LT - ENG A/I SYS DIFF
73PWM05A
73-25-00-810-864
LT - ENG1 CTL I/O SYS
73PWM25A
73-25-00-810-865
LT - ENG2 CTL I/O SYS
73PWM26A
73-25-00-810-865
LT - ENG1 IGN OFF SYS
74PWM27A
74-30-00-810-801
LT - ENG2 IGN OFF SYS
74PWM28A
74-30-00-810-801
LT - ENG1 IGN SYS
74PWM53A
74-13-00-810-801
LT - ENG2 IGN SYS
74PWM54A
74-13-00-810-801
LT - ENG1 ITT TRIM SYS
77PWM57A
77-21-00-810-809
LT - ENG2 ITT TRIM SYS
77PWM58A
77-21-00-810-809
LT - ENG MODE SYS DIF
73PWM06A
73-25-00-810-863
EFFECTIVITY: ALL
Maintenance Message List Page 2 Jul 20/15
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CENTRAL MAINTENANCE COMPUTER (CMC) MAINTENANCE MESSAGE MAINTENANCE MESSAGE TEXT NUMBER
FIM TASK REFERENCE
LT - ENG1 MMV / WF SYS
73PWM55A
73-21-00-810-818
LT - ENG2 MMV / WF SYS
73PWM56A
73-21-00-810-818
LT - ENG1 N1 SYS
77PWM37A
77-11-00-810-823
LT - ENG2 N1 SYS
77PWM38A
77-11-00-810-823
LT - ENG1 N2 SYS
77PWM39A
77-11-00-810-824
LT - ENG2 N2 SYS
77PWM40A
77-11-00-810-824
LT - ENG1 PR / TMP DATA SYS (FADEC SOFTWARE VER. B5.1.1)
75PWM95A
75-43-00-810-806-A01
LT - ENG1 PR / TMP DATA SYS (FADEC SOFTWARE VER. B7.5 OR LATER)
75PWM95A
75-43-00-810-806-B01
LT - ENG2 PR / TMP DATA SYS (FADEC SOFTWARE VER. B5.1.1)
75PWM96A
75-43-00-810-806-A01
LT - ENG2 PR / TMP DATA SYS (FADEC SOFTWARE VER. B7.5 OR LATER)
75PWM96A
75-43-00-810-806-B01
LT - ENG1 STOP SYS
73PWM176
73-25-00-810-866
LT - ENG2 STOP SYS
73PWM177
73-25-00-810-866
R LT - ENG1 TLA SYS R (AIRCRAFT CMC SOFTWARE R VERSION 15 OR EARLIER)
76PWM98A
76-11-00-810-810-A01
R ST - ENG1 TLA SYS R (AIRCRAFT CMC SOFTWARE R VERSION 16 OR LATER)
76PWM98A
76-11-00-810-810-B01
R LT - ENG2 TLA SYS R (AIRCRAFT CMC SOFTWARE R VERSION 15 OR EARLIER)
76PWM99A
76-11-00-810-810-A01
R ST - ENG2 TLA SYS R (AIRCRAFT CMC SOFTWARE R VERSION 16 OR LATER)
76PWM99A
76-11-00-810-810-B01
LT - ENG1 T/R POS SYS
78PWM51A
78-30-00-810-801
LT - ENG2 T/R POS SYS
78PWM52A
78-30-00-810-801
ND - ENG1 A/G SYS DIFF
76PWM71A
76-11-00-810-809
ND - ENG2 A/G SYS DIFF
76PWM72A
76-11-00-810-809
ND - ENG1 COMM A
77PWM23
77-40-00-810-807
ND - ENG1 COMM B
77PWM24
77-40-00-810-807
ND - ENG2 COMM A
77PWM25
77-40-00-810-807
EFFECTIVITY: ALL
Maintenance Message List Page 3 Jul 20/15
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CENTRAL MAINTENANCE COMPUTER (CMC) MAINTENANCE MESSAGE MAINTENANCE MESSAGE TEXT NUMBER
FIM TASK REFERENCE
ND - ENG2 COMM B
77PWM26
77-40-00-810-807
ND - ENG1 CVG SYS DIFF
75PWM47A
75-33-00-810-805
ND - ENG2 CVG SYS DIFF
75PWM48A
75-33-00-810-805
ND - ENG1 DUAL PMA SYS
73PXM61A
73-25-00-810-860
ND - ENG2 DUAL PMA SYS
73PXM62A
73-25-00-810-860
ND - ENG1 FADEC A CCDL
73PXM67A
73-25-00-810-861
ND - ENG1 FADEC B CCDL
73PXM68A
73-25-00-810-861
ND - ENG2 FADEC A CCDL
73PXM69A
73-25-00-810-861
ND - ENG2 FADEC B CCDL
73PXM70A
73-25-00-810-861
ND - ENG 1 FADEC A OVERTEMP
73PWM67A
73-25-00-810-820
ND - ENG 1 FADEC B OVERTEMP
73PWM68A
73-25-00-810-820
ND - ENG 2 FADEC A OVERTEMP
73PWM69A
73-25-00-810-820
ND - ENG 2 FADEC B OVERTEMP
73PWM70A
73-25-00-810-820
R ND - ENG 1 FADEC A R (AIRCRAFT CMC SOFTWARE R VERSION 16 OR LATER)
73PXM87A
73-25-00-810-862-C01
R ND - ENG 1 FADEC B R (AIRCRAFT CMC SOFTWARE R VERSION 16 OR LATER)
73PXM88A
73-25-00-810-862-C01
R ND - ENG 2 FADEC A R (AIRCRAFT CMC SOFTWARE R VERSION 16 OR LATER)
73PXM89A
73-25-00-810-862-C01
R ND - ENG 2 FADEC B R (AIRCRAFT CMC SOFTWARE R VERSION 16 OR LATER)
73PXM90A
73-25-00-810-862-C01
ND - ENG1 HPC SYS 75PXM27 FADEC SOFTWARE VER. B5.1.1)
75-41-00-810-803-A01
ND - ENG1 HPC SYS (FADEC SOFTWARE VER. B7.5 OR LATER)
75PXM27
75-41-00-810-803-B01
ND - ENG2 HPC SYS (FADEC SOFTWARE VER. B5.1.1)
75PXM28
75-41-00-810-803-A01
ND - ENG2 HPC SYS (FADEC SOFTWARE VER. B7.5 OR LATER)
75PXM28
75-41-00-810-803-B01
EFFECTIVITY: ALL
Maintenance Message List Page 4 Jul 20/15
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CENTRAL MAINTENANCE COMPUTER (CMC) MAINTENANCE MESSAGE MAINTENANCE MESSAGE TEXT NUMBER
FIM TASK REFERENCE
ND - ENG1 OVSPD PROT SYS
77PXM65A
77-11-00-810-822
ND - ENG2 OVSPD PROT SYS
77PXM66A
77-11-00-810-822
ND - ENG1 P0 SYS
75PXM23A
75-43-00-810-807
ND - ENG2 P0 SYS
75PXM24A
75-43-00-810-807
ND - ENG1 PRV SYS
73PWM45A
73-21-00-810-820
ND - ENG2 PRV SYS
73PWM46A
73-21-00-810-820
ND - ENG1 SOI SYS
73PXM33A
73-21-00-810-819
ND - ENG2 SOI SYS
73PXM34A
73-21-00-810-819
ND - ENG1 STOP SYS DIFF
73PWM178
73-25-00-810-867
ND - ENG2 STOP SYS DIFF
73PWM179
73-25-00-810-867
ND - ENG1 TLA SYS DIFF
76PWM35A
76-11-00-810-811
ND - ENG2 TLA SYS DIFF
76PWM36A
76-11-00-810-811
ST - ENG1 ADC COMM SYS
73PWM59A
73-10-00-810-812
ST - ENG2 ADC COMM SYS
73PWM56A
73-10-00-810-812
ST - ENG1 CTL A SYS (FADEC SOFTWARE VER. B5.1.1)
73PXM87A
73-25-00-810-862-A01
ST - ENG1 CTL A SYS (FADEC SOFTWARE VER. B7.5 OR LATER)
73PXM87A
73-25-00-810-862-B01
ST - ENG1 CTL B SYS (FADEC SOFTWARE VER. B5.1.1)
73PXM88A
73-25-00-810-862-A01
ST - ENG1 CTL B SYS (FADEC SOFTWARE VER. B7.5 OR LATER)
73PXM88A
73-25-00-810-862-B01
ST - ENG2 CTL A SYS (FADEC SOFTWARE VER. B5.1.1)
73PXM89A
73-25-00-810-862-A01
ST - ENG2 CTL A SYS (FADEC SOFTWARE VER. B7.5 OR LATER)
73PXM89A
73-25-00-810-862-B01
ST - ENG2 CTL B SYS (FADEC SOFTWARE VER. B5.1.1)
73PXM90A
73-25-00-810-862-A01
ST - ENG2 CTL B SYS (FADEC SOFTWARE VER. B7.5 OR LATER)
73PXM90A
73-25-00-810-862-B01
ST - ENG1 CVG SYS
75PWM41A
75-33-00-810-806
EFFECTIVITY: ALL
Maintenance Message List Page 5 Jul 20/15
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CENTRAL MAINTENANCE COMPUTER (CMC) MAINTENANCE MESSAGE MAINTENANCE MESSAGE TEXT NUMBER
FIM TASK REFERENCE
ST - ENG2 CVG SYS
75PWM42A
75-33-00-810-806
ST - ENG1 IGN ON SYS DIFF
74PWM21A
74-30-00-810-806
ST - ENG2 IGN ON SYS DIFF
74PWM22A
74-30-00-810-806
ST - ENG1 ITT SYS
77PWM49A
77-21-00-810-801
ST - ENG2 ITT SYS
77PWM50A
77-21-00-810-801
ST - ENG1 MMV / CVG SYS
73PWM43A
73-21-00-810-821
ST - ENG2 MMV / CVG SYS
73PWM44A
73-21-00-810-821
ST - ENG1 PMA SYS
73PWM31A
73-25-00-810-817
ST - ENG2 PMA SYS
73PWM32A
73-25-00-810-817
ST - ENG T/O SYS DIFF
73PWM64A
73-25-00-810-841
EFFECTIVITY: ALL
Maintenance Message List Page 6 Jul 20/15
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FADEC Discrete List
NAME (S/W NAME) / Bit No.
NAME DESCRIPTION (DISCRETE LABEL NUMBER / NAME - DESCRIPTION)
FIM TASK REFERENCE
(146 / ECSWRD - Engine Control System Status Word) IGNEN (IGNEN) / 11
Ignition Enabled (i.e. ignition switch in AUTO or ON).
For Reference Only
IGNON (IGNRFG) / 12
Ignition ON (relay commanded de-energized).
For Reference Only
FSOACT (SHUTDN) / 13
Fuel shutoff active (i.e. stop coil energized).
For Reference Only
TFIC (TLIC) / 14
This FADEC in control.
For Reference Only
LGTOFD (LITEUP) / 15
Lightoff detected.
For Reference Only
AUTRER (AUTRER) / 16
Autorelight requested.
For Reference Only
MTRREQ (MOTOR) / 17
Dry Motor requested.
For Reference Only
STRTRQ (STRQFG) / 18
Engine start requested.
For Reference Only
SHUTRQ (SDRQFG) / 19
Engine shutdown requested indication flag.
For Reference Only
MODE3 (MODE3) / 20
Engine running.
For Reference Only
SSW1 (SSW1) / 21
N2 speed switch drive active.
For Reference Only
WFRST (WFRST) / 23
Fuel on active (i.e. start coil energized).
For Reference Only
CVGDON (FPMDEB) / 25
CVG drive active (i.e. supplying current to torque motor).
For Reference Only
MMVON (TMDEB) / 26
Wf drive active (i.e. supplying current to torque motor).
For Reference Only
SHUTEN (SDSQFG) / 27
Engine shutdown enabled.
For Reference Only
WNSTENV (WSTENV) / 28
Engine inside windmill start envelope.
For Reference Only
NOTRIM (NOTRIM) / 29
No ITT trim applied.
For Reference Only
(147 / TMWRD - Thrust Management Status Word) CURMOD (CURMOD) / 11-14
Used to indicate current thrust mode.
For Reference Only
ANMEON (ANMEON) / 15
Insufficient margin for ATTCS if ECS ON.
For Reference Only
ANMEOF (ANMEOF) / 16
Insufficient margin for ATTCS if ECS OFF.
For Reference Only
ATTCSC (ATTCAP) / 18
ATTCS capable.
For Reference Only
ATTCSA (ATTARM) / 19
ATTCS armed.
For Reference Only
EFFECTIVITY: ALL
FADEC Discrete List Page 1 Jul 20/15
EXPORT CONTROLLED
NAME (S/W NAME) / Bit No.
NAME DESCRIPTION (DISCRETE LABEL NUMBER / NAME - DESCRIPTION)
FIM TASK REFERENCE
ATTTRG (ATTRIG) / 20
ATTCS triggered.
For Reference Only
TREVLV (THS3CV) / 22
Aircraft thrust reverser stored indication.
For Reference Only
TREVFP (THD3CV) / 23
Aircraft thrust reverser deployed indication.
For Reference Only
TMPSRC / 24-25
Indicate TAT selection for N1 target calculation.
For Reference Only
T2SYNA (T2SYNA) / 26
TAT synthesis active (i.e. when TAT has been set equal to T2SYN).
For Reference Only
RBREQ (RBREQ) / 27
Reduced bleed request drive active.
For Reference Only
AISIPD (AISIPD) / 29
Aircraft anti-ice system is on.
For Reference Only
(264 / AIDIF1 - Aircraft Interface Difference Fault Status Word 1) STRTDF (STRTDF) / 11
Start-switch difference fault.
80-10-00-810-803
STPDIF (STPDIF) / 12
Stop-switch difference fault.
73-25-00-810-854
IGONDF (IGONDF) / 13
Ignition-ON-switch difference fault. 74-30-00-810-804
IGOFDF (IGOFDF) / 14
Ignition-OFF-switch difference fault.
74-30-00-810-805
MTOSDF (MTOSDF) / 16
Maximum-takeoff-mode switch difference fault.
73-25-00-810-841
TRDPDF (TRDPDF) / 17
Thrust-reverser fully-deployed feedback-difference fault.
78-30-00-810-804
TRSTDF (TRSTDF) / 18
Thrust-reverser fully-stowed feedback-difference fault.
78-30-00-810-805
WOWDF (WOWDF) / 19
Weight-on-wheels-switch difference fault.
76-11-00-810-805
LGDLDF (LGDLDF) / 20
Landing gear down and locked switch difference fault.
73-25-00-810-806
AISIDF (AISIDF) / 21
Aircraft anti-ice system-indication difference fault.
73-25-00-810-803
TOTIDF (TOTIDF) / 22
Takeoff-data increase-data-switch difference fault.
73-25-00-810-813
TOTDDF (TOTDDF) / 23
Takeoff-data decrease-data-switch 73-25-00-810-814 difference fault.
TOTSDF (TOTSDF) / 24
Takeoff-data store-switch difference fault.
CLBDIF (CLBDIF) / 26
Climb-mode switch difference fault. 73-25-00-810-844
EFFECTIVITY: ALL
73-25-00-810-816
FADEC Discrete List Page 2 Jul 20/15
EXPORT CONTROLLED
NAME (S/W NAME) / Bit No.
NAME DESCRIPTION (DISCRETE LABEL NUMBER / NAME - DESCRIPTION)
FIM TASK REFERENCE
CRZDIF (CRZDIF) / 27
Cruise-mode switch difference fault.
73-25-00-810-843
MXCDIF (MXCDIF) / 28
Maximum-continuous-mode switch 73-25-00-810-842 difference fault.
FDRDIF (FDRDIF) / 29
FADEC fault-reset-switch difference fault.
73-25-00-810-810
(265 / AIDIF2 - Aircraft Interface Difference Fault Status Word 2) ALTDIF (ADW2CV) / 11
Alternate FADEC-select-switch difference fault.
73-25-00-810-809
TLADIF (XC7NOK) / 16
TLA-resolver difference fault.
76-11-00-810-802
PALDIF (XA1NOK) / 17
Pressure-altitude-data difference fault.
73-10-00-810-807
TATDIF (XA2NOK) / 18
Total-air-temperature-data difference fault.
73-10-00-810-808
MNDIF (XA3NOK) / 19
Mach number-data difference fault. 73-10-00-810-809
SSW1DF / 25
N2-speed-switch output-driver difference fault.
73-25-00-810-832
SPARE / 25
Spare. (FADEC SOFTWARE VER. B7.5 OR LATER)
For Reference Only
RBRQDF / 26
Reduced-bleed-request output-driver difference fault. (FADEC SOFTWARE VER. B5.1.1)
73-25-00-810-833
SPARE / 26
Spare. (FADEC SOFTWARE VER. B7.5 OR LATER)
For Reference Only
(340 / CLIND - Control Loop / and Thrust Mode Word) CURMOD / 11-14
Used to indicate current thrust mode.
For Reference Only
TFAIID / 15-18
Used to indicate current engine application ID. (CMC 9 and 10)
For Reference Only
FADVSN / 19-24
FADEC software version number (FADEC SOFTWARE VER. B7.5 OR LATER)
For Reference Only
CLND1-4 / 25-28
Engine control logic control loop For Reference Only indicator, and current thrust mode. (350 / TDSWRD - Takeoff Data Setting Word)
REF.MODE / 11-12
REFMODE
For Reference Only
TDSIP (TTSIP) / 13
Takeoff data setting in progress.
For Reference Only
EFFECTIVITY: ALL
FADEC Discrete List Page 3 Jul 20/15
EXPORT CONTROLLED
NAME (S/W NAME) / Bit No.
NAME DESCRIPTION (DISCRETE LABEL NUMBER / NAME - DESCRIPTION)
TDSPAS (TTSPAS) / 14
Takeoff data entered successfully. For Reference Only
TFIN2R (TFIN2R) / 15
This FADEC transmits ITT and N2 For Reference Only redlines.
TDLIML (TTLIML) / 16
Attempt to decrement temperature For Reference Only too low.
TDLIMH (TTLIMH) / 17
Attempt to increment temperature too high.
For Reference Only
TDFLT (TTFLT) / 18
Takeoff data setting fault.
For Reference Only
BLDPOS (BLDPOS) / 21
Bleed selected on in takeoff data setting function.
For Reference Only
TDSMAS (TDSMAS) / 22
This FADEC is a temp setting master.
For Reference Only
WOW (WOW) / 24
Weight-on-wheels is true.
For Reference Only
TDICBL (TTICBL) / 25
This FADEC incapable of setting takeoff data.
For Reference Only
TDSTAT (TTSTAT) / 27
Takeoff temperature setting function.
For Reference Only
TDSTAT (TTSTAT) / 28-29
Indicate takeoff data setting status. For Reference Only
FIM TASK REFERENCE
(351 / AILRU1 - Aircraft Interface Fault Status Word 1) STRTFT (STRNOK) / 11
Start switch fault.
80-10-00-810-802
STPFLT (STPNOK) / 12
Stop switch fault.
73-25-00-810-853
IGONFT (IGNNOK) / 13
Ignition-ON switch fault.
74-30-00-810-802
IGOFFT (IGFNOK) / 14
Ignition-OFF switch fault.
74-30-00-810-803
MTOSFT (MXTFLT) / 16
Maximum-takeoff-mode switch fault.
73-25-00-810-837
SPARE / 15
Spare. (FADEC SOFTWARE VER. B5.1.1, B7.5 AND B7.6)
For Reference Only
PMAPWF (PMPNOK) / 15
PMA power fault. (FADEC SOFTWARE VER. B8 AND LATER)
73-25-00-810-817
TRDPFT (THDFLT) / 17
Thrust-reverser fully-deployed feedback-indication fault.
78-30-00-810-802
TRSTFT (THSFLT) / 18
Thrust-reverser fully-stowed feedback-indication fault.
78-30-00-810-803
WOWFT (RWOFLT) / 19
Weight-on-wheels switch fault.
76-11-00-810-804
LGDLFT (RLGFLT) / 20
Landing gear down and locked switch fault.
73-25-00-810-805
EFFECTIVITY: ALL
FADEC Discrete List Page 4 Jul 20/15
EXPORT CONTROLLED
NAME (S/W NAME) / Bit No.
NAME DESCRIPTION (DISCRETE LABEL NUMBER / NAME - DESCRIPTION)
FIM TASK REFERENCE
AISIFT (EASNOK) / 21
Aircraft anti-ice system-indication switch fault.
73-25-00-810-802
TOTIFT (TTIFLT) / 22
Takeoff-data increase-switch fault. 73-25-00-810-811
TOTDFT (TTDFLT) / 23
Takeoff-data decrease-switch fault. 73-25-00-810-812
TOTSFT (TTSFLT) / 24
Takeoff-data store-switch fault.
73-25-00-810-815
CLBFT (CLBFLT) / 26
Climb-mode switch fault.
73-25-00-810-838
CRZFT (CRUFLT) / 27
Cruise-mode switch fault.
73-25-00-810-839
MXCFT (MCNFLT) / 28
Maximum-continuous-mode switch 73-25-00-810-840 fault.
FDRFT (FRSNOK) / 29
FADEC fault-reset-switch fault.
73-25-00-810-808
(352 / AILRU2 - Aircraft Interface Fault Status Word 2) ALTFSF (SOTNOK) / 11
Alternate FADEC select switch fault.
73-25-00-810-807
AIDNOK / 12
Application identity fault. (FADEC SOFTWARE VER. B5.1.1)
73-25-00-810-868-A01
AFINOK (AFINOK) / 12
Application identity fault. (FADEC SOFTWARE VER. B7.5 OR LATER)
73-25-00-810-868-B01
TLAFLT (TLANOK) / 16
TLA resolver fault.
76-11-00-810-807
ADCFLT (ADCRX) / 17
ADC bus-receiver fault.
73-10-00-810-802
PALTFT / 18
Pressure-altitude data fault. (FADEC SOFTWARE VER. B5.1.1)
73-10-00-810-803-A01
ALTNOK (ALTNOK) / 18
Confirmed pressure altitude data fault. (FADEC SOFTWARE VER. B7.5 OR LATER)
73-10-00-810-803-B01
TATFLT / 19
Total-air-temperature data fault. (FADEC SOFTWARE VER. B5.1.1)
73-10-00-810-804-A01
TATNOK (TATNOK) / 19
Confirmed total-air-temperature data fault. (FADEC SOFTWARE VER. B7.5 OR LATER)
73-10-00-810-804-B01
MNFLT / 20
Mach-number data fault. (FADEC SOFTWARE VER. B5.1.1)
73-10-00-810-805-A01
EFFECTIVITY: ALL
FADEC Discrete List Page 5 Jul 20/15
EXPORT CONTROLLED
NAME (S/W NAME) / Bit No.
NAME DESCRIPTION (DISCRETE LABEL NUMBER / NAME - DESCRIPTION)
FIM TASK REFERENCE
MNNOK (MNNOK) / 20
Confirmed mach-number data fault. (FADEC SOFTWARE VER. B7.5 OR LATER)
73-10-00-810-805-B01
ACSYFT / 21
Aircraft-system-status word-transmission fault. (FADEC SOFTWARE VER. B5.1.1)
73-10-00-810-806-A01
ACSNOK (ACSNOK) / 21
Confirmed aircraft-system-status word-transmission fault. (FADEC SOFTWARE VER. B7.5 OR LATER)
73-10-00-810-806-B01
T25BLF / 22
Dual T2.5 sensor failure. (FADEC SOFTWARE VER. B5.1.1)
75-41-00-810-804-A01
T25DCF (T25DCF) / 22
Confirmed dual T2.5 sensor failure. (FADEC SOFTWARE VER. B7.5 OR LATER)
75-41-00-810-804-B01
P25BLF / 23
Dual P2.5 sensor failure. (FADEC SOFTWARE VER. B5.1.1)
75-43-00-810-809-A01
P25DCF (P25DCF) / 23
Confirmed dual P2.5 sensor failure. (FADEC SOFTWARE VER. B7.5 OR LATER)
75-43-00-810-809-B01
P0BLF (P0BLF) / 24
Dual P0 sensor failure.
75-43-00-810-807
SOIBLF (SOIBLF) / 25
Dual shutoff interlock output drive fault.
73-21-00-810-819
(353 / EILRU - Engine Interface Fault Status Word) N1PSFT (N1PNOK) / 11
N1 primary-sensor fault.
77-11-00-810-802
N1SSFT (N1SNOK) / 12
N1 secondary-sensor fault.
77-11-00-810-803
N2PSFT (N2PNOK) / 13
N2 primary-sensor fault.
77-11-00-810-807
N2SSFT (N2SNOK) / 14
N2 PMA speed-sensor fault.
77-11-00-810-827
ITTFLT (MGTNOK) / 15
Inter-turbine-temperature sensor fault.
77-21-00-810-802
T25DIF (T25DIF) 20
Compressor-inlet 75-41-00-810-802 temperature-sensor fault. Signal sent to one FADEC is more than 25 °F different from that received by the other FADEC.
EFFECTIVITY: ALL
FADEC Discrete List Page 6 Jul 20/15
EXPORT CONTROLLED
NAME (S/W NAME) / Bit No.
NAME DESCRIPTION (DISCRETE LABEL NUMBER / NAME - DESCRIPTION)
FIM TASK REFERENCE
T25FLT / 16
Compressor-inlet temperature-sensor fault. (FADEC SOFTWARE VER. B5.1.1)
75-41-00-810-801-A01
T25NOK (T25NOK) / 16
Confirmed compressor-inlet temperature-sensor fault. (FADEC SOFTWARE VER. B7.5 OR LATER)
75-41-00-810-801-B01
P25FLT / 17
Compressor-inlet pressure-sensor fault. (FADEC SOFTWARE VER. B5.1.1)
75-43-00-810-801-A01
P25NOK (P25NOK) / 17
Confirmed compressor-inlet pressure-sensor fault. (FADEC SOFTWARE VER. B7.5 OR LATER)
75-43-00-810-801-B01
P25DIF (P25DIF) / 21
Confirmed compressor-inlet 75-43-00-810-802 pressure-sensor fault. Signal sent to one FADEC is more than 2 psia different from that received by the other FADEC.
CVGFBF (CVGNOK) / 18
CVG feedback-sensor fault.
75-33-00-810-802
MMVFBF (MMVNOK) / 19
Main-metering-valve feedback-sensor fault.
73-21-00-810-802
CJCNOK / 20
Cold junction compensation fault.
For Reference Only
MMVTMF (TMFNOK) / 21
Main-metering-valve torquemotor fault.
73-21-00-810-803
CVGTMF (CTMNOK) / 22
CVG torquemotor fault.
73-21-00-810-804
IGNFLT (IGWNOK) / 23
Ignition relay fault.
74-13-00-810-801
SOSFLT (SHWNOK) / 24
Wf shutoff solenoid-coil fault.
73-21-00-810-805
STSFLT (FRWNOK) / 25
Wf start solenoid-coil fault.
73-21-00-810-806
AVSFLT / 26
Air vent solenoid-coil fault. (FADEC SOFTWARE VER. B5.1.1)
73-21-00-810-807-A01
FPSNOK (FPSNOK) / 26
FPMU detection solenoid circuit fault. (FADEC SOFTWARE VER. B7.5 OR LATER)
73-21-00-810-807-B01
TRMFMD (TRMFMD) / 27
ITT-trim circuit fault.
77-21-00-810-803
P0SFT (P0NOK) / 28
P0 sensor fault.
75-43-00-810-803
EBFFLT / 29
Electronic bleed valve feedback switch fault.
For Reference Only
EFFECTIVITY: ALL
FADEC Discrete List Page 7 Jul 20/15
EXPORT CONTROLLED
NAME (S/W NAME) / Bit No.
NAME DESCRIPTION (DISCRETE LABEL NUMBER / NAME - DESCRIPTION)
FIM TASK REFERENCE
(354 / CFPLRU - Connector/FPMU/CVG/PMA Fault Status Word) XTLKFT (CDTNOE) / 11
CCDL receiver fault.
77-40-00-810-803
NCNCFT (NCNNOE) / 12
Nacelle-to-nacelle ARINC-429 receiver fault.
77-40-00-810-802
IDFLT (IDPNOK) / 13
FADEC ID jumper fault. (parity failure)
73-25-00-810-850
MMVCFT (MVTFG1) / 14
MMV-closed-position check failure. 73-21-00-810-808
MMVPFT (MVTFG2) / 15
MMV-prime-position check failure.
73-21-00-810-808
MMVTFT (MVTNOK) / 16
MMV-tracking-check failure.
73-21-00-810-809
FPMUFT (FPMUFL) / 17
FPMU system failure.
73-21-00-810-801
CVGTFT (CVTNOK) / 18
CVG-tracking check failure.
73-21-00-810-810
PMAPWF (PMPNOK) / 19
PMA power fault.
73-25-00-810-817
AIDPFT (AIDPFT) / 20
Application ID parity fault.
73-25-00-810-869
MMVFIX (MVTBLF) / 21
MMV failed fixed.
73-21-00-810-816
CVGFIX (CVTBLF) / 22
CVG failed fixed.
For Reference Only
J3CFT / 23
Loss of J3 connector (Inter-FADEC For Reference Only communication). (FADEC SOFTWARE VER. B5.1.1)
FPMNOK (FPMNOK) / 23
FPMU hardware standard fault. (FADEC SOFTWARE VER. B7.5 OR LATER)
73-21-00-810-822
PRVFLT (PRVFLT) / 24
PRV failed.
73-21-00-810-811
PMABFL (PMABLF) / 25
Dual PMA power fault.
73-25-00-810-860
SPARE / 27
Spare. (FADEC SOFTWARE VER. B5.1.1, B7.5 AND B7.6
For Reference Only
HIN1FG (HIN1FG) / 27
High N1 failure. (FADEC SOFTWARE VER. B8.0 OR LATER)
73-21-00-810-823
(355 / SFLTS1 - System Fault Status Word 1) SBSDSI (SBSDSI) / 14
LP shaft break shutdown.
73-25-00-810-818
CHNFLT (CAPBAR) / 15
This FADEC incapable.
73-25-00-810-855
REVMRQ (REVMRQ) / 16
Loss of ADC data, synthesized value(s) active.
73-10-00-810-810
TLALIM (TLALTD) / 17
TLA limited to idle.
For Reference Only
TLAFIX (TLABLF) / 18
TLA currently failed fixed.
76-11-00-810-806
EFFECTIVITY: ALL
FADEC Discrete List Page 8 Jul 20/15
EXPORT CONTROLLED
NAME (S/W NAME) / Bit No.
NAME DESCRIPTION (DISCRETE LABEL NUMBER / NAME - DESCRIPTION)
FIM TASK REFERENCE
N1OSTR (OSN1FG) / 19
N1 overspeed logic tripped (software detected).
77-11-00-810-809
N2OSTR (OSN2FG) / 20
N2 overspeed logic tripped (software detected).
77-11-00-810-810
STFAIL (STFAIL) / 21
This FADEC unable to start engine.
73-25-00-810-818
FLTGP2 (FLTGP2) / 22
Short-term dispatch fault. (CMC 9 72-00-00-810-806 and 10)
FLAMED (FLMIND) / 23
Flameout detected (indication for pilot).
For Reference Only
AUTREF (AUTREF) / 24
Failure to autorelight detected.
For Reference Only
NOLITE (LITESD) / 25
No lightoff detected.
For Reference Only
N1LRMD (N1BLNF) / 26
N1 loss of speed measurement mode active.
77-11-00-810-821
STGSTR (STAGFG) / 27
Stagnated start detected.
For Reference Only
LEI (LEI) / 28
Local engine inoperative.
73-25-00-810-851-B01
FLTGP1 (FLTGP1) / 29
No dispatch fault. (CMC 9)
72-00-00-810-805
(356 / SFLTS2 - System Fault Status Word 2) POWINT (POWINT) / 14
FADEC power interrupt detected.
For Reference Only
OSTRIP (OSTRIP) / 15
Software detection of FADEC hardware overspeed tripped.
For Reference Only
REI (REI) / 16
Remote engine inoperative.
For Reference Only
IFPOWINT (IFPOWINT) / 17
In flight FADEC power interrupt detected.
73-25-00-810-856
MVTDIS (MMVDIS) / 18
MMV tracking test disabled.
For Reference Only
CVGDIS (CVGDIS) / 19
CVG tracking test disabled.
For Reference Only
INHFLB (INHFLB) / 20
EEPROM WRITE INHIBIT accommodation disabled.
73-25-00-810-834
LN1OSP (LN1OSP) / 21
Loss of N1 overspeed protection.
77-11-00-810-825
LN2OSP (LN2OSP) / 22
Loss of N2 overspeed protection.
77-11-00-810-826
TXATNM (TXATNM) / 23
This FADEC transmits ATTCS NO For Reference Only MRGN message.
TXHOPL (TXHOPL) / 24
This FADEC transmits high oil pressure red-lines.
For Reference Only
TXSCVG (TXSCVG) / 25
This FADEC transmits smart CVG in use.
For Reference Only
FLTGP3 (FLTGP3) / 26
Long-term dispatch fault.
72-00-00-810-807
EFFECTIVITY: ALL
FADEC Discrete List Page 9 Jul 20/15
EXPORT CONTROLLED
NAME (S/W NAME) / Bit No.
NAME DESCRIPTION (DISCRETE LABEL NUMBER / NAME - DESCRIPTION)
FIM TASK REFERENCE
FLTGP4 (FLTGP4) / 27
Non-LOTC fault. (FADEC SOFTWARE VER. B4.3 OR LATER)
72-00-00-810-808-B01
MMCVFL (MMCVFL) / 28
MMV failed fixed or CVG open.
73-21-00-810-817
ENGOUT (ENGOUT) / 29
Engine underspeed shutdown.
72-00-00-810-809
(357 / EIDIF - Engine Interface Difference Fault Status Word) N1PDIF (FLFG31) / 11
N1 primary-sensors cross-check difference fault.
77-11-00-810-812
N1SDIF (FLFG51)/ 12
N1 secondary-sensors cross-check difference fault.
77-11-00-810-814
N1PSTD (FLFG21) / 13
N1 primary vs secondary-sensors cross-check difference fault (this FADEC).
77-11-00-810-813
N1PSOD (FLFG41) / 14
N1 primary vs secondary-sensors cross-check difference fault (other FADEC).
77-11-00-810-815
N2PDIF (G45NOK) / 15
N2 primary-sensors cross-check difference fault.
77-11-00-810-817
N2SDIF (G55NOK) / 16
N2 secondary-sensors cross-check difference fault.
77-11-00-810-819
N2PSTD (G35NOK) / 17
N2 primary vs secondary-sensors cross-check difference fault (this FADEC).
77-11-00-810-818
N2PSOD (G65NOK) / 18
N2 primary vs secondary-sensors cross-check difference fault (other FADEC).
77-11-00-810-820
ITTDIF (XC8NOK) / 19
Inter-turbine-temperature sensor difference fault.
77-21-00-810-804
CVGFBD (XC9NOK) / 22
CVG-feedback-sensor difference fault.
75-33-00-810-803
MMVFBD (XCANOK) / 23
MMV-feedback-sensor difference fault.
73-21-00-810-812
TRMDMX (TRMDMX) / 25
ITT-trim cross-check difference 77-21-00-810-805 between ITT trim value provided to this FADEC and ITT trim value from the other FADEC.
TRMEDF (TRMEDF) / 26
ITT-trim-resistor difference fault 77-21-00-810-806 (ITT trim value provided to this FADEC vs ITT trim value stored in this FADEC EEPROM).
P0SDIF (XC4NOK) / 27
P0-sensor difference fault.
EFFECTIVITY: ALL
75-43-00-810-804
FADEC Discrete List Page 10 Jul 20/15
EXPORT CONTROLLED
NAME (S/W NAME) / Bit No.
NAME DESCRIPTION (DISCRETE LABEL NUMBER / NAME - DESCRIPTION)
FIM TASK REFERENCE
P0ADCF (P0ADCF) / 29
P0-to-ADC difference fault.
75-43-00-810-805
(360 / FADLRU - FADEC Fault Status Word) SOIFLT (SIWNOK) / 11
Shutoff-interlock output-drive fault. 77-40-00-810-804
CAPOFT (CAPNOK) / 12
FADEC-capable output-drive fault. 77-40-00-810-805
TLICFT (TLWNOK) / 13
This FADEC-in-control output drive 77-40-00-810-806 fault.
N1OSF (LIOSN1) / 14
Loss of software-independent N1 overspeed protection.
73-25-00-810-822-B01
N2OSF (LIOSN2) / 15
Loss of software-independent N2 overspeed protection.
73-25-00-810-823-B01
ACDCFT (ACVNOK) / 16
Aircraft 28 Volts DC fault.
73-25-00-810-819
CSETMF (CSETMF) / 17
FADEC case overtemp.
73-25-00-810-820
FADTMF (FADTMP) / 18
FADEC temperature exceeded.
73-25-00-810-820
V5RFLT (R5VNOK) / 19
5 volt sense fault.
73-25-00-810-824
V15RFT (R15NOK) / 20
15 volt sense fault.
73-25-00-810-825
SEXFLT (SEXFLT) / 21
Sensor excitation fault.
73-25-00-810-826
TLAEXF (TLFNOK) / 22
TLA-resolver excitation fault.
73-25-00-810-827
EPROMF (EPROMF) / 23
EEPROM fault.
For Reference Only
IDTFL (IDTFL) / 24
FADEC ID indeterminate.
73-25-00-810-848
ARNCTX (ACTXSF) / 25
ARINC transmitter fault.
73-25-00-810-829
ARNCRX (ACRXSF) / 26
ARINC receiver fault.
73-25-00-810-830
R FADFLT (FADNOK) / 27 R (AIRCRAFT CMC SOFTWARE R VERSION 15 OR EARLIER)
FADEC failed (internal fault).
73-25-00-810-831-A01
R FADFLT (FADNOK) / 27 R (AIRCRAFT CMC SOFTWARE R VERSION 16 OR LATER)
FADEC failed (internal fault).
73-25-00-810-831-B01
MMVDLF (FTMDLF) / 28
MMV wrap test failed on dummy load (standby FADEC).
73-21-00-810-813
CVGDLF (CTMDLF) / 29
CVG wrap test failed on dummy load (standby FADEC).
73-21-00-810-814
EFFECTIVITY: ALL
FADEC Discrete List Page 11/12 Jul 20/15
EXPORT CONTROLLED
Observed Fault List
FAULT DESCRIPTION
FAULT CODE
FIM TASK REFERENCE
Active ignition system after engine RPM slows 7430O1 00 to ground idle (ENG1/ENG2 IGN A/B message on EICAS)
74-30-00-810-807
Bleed Leak Alert
75300100
75-31-00-810-801
753103 00
75-31-00-810-804
Combustion Liner Distress Alert
720017 00
72-00-00-810-827
CVG Hydraulic Actuator Seal Drain Accumulation
753301 00
75-33-00-810-804
Decrease in N2 Margin
720016 00
72-00-00-810-826
Engine Does Not Start (Fast N2 Indication)
720020 00
72-00-00-810-829
Engine Does Not Start (No Lightoff/Delayed Lightoff) For engines with Piloted Fuel Nozzle Assemblies
720004 00
72-00-00-810-803-A01
Engine Does Not Start (No Lightoff/Delayed Lightoff) For engines with Non-Piloted Fuel Nozzle Assemblies
720004 00
72-00-00-810-803-A02
Engine Does Not Start (No Lightoff/No Fuel Flow)
720009 00
72-00-00-810-824
Engine Does Make Necessary Thrust
720010 00
72-00-00-810-816
Engine Noise on FADEC Lane Change
720019 00
72-00-00-810-822
Step change in fuel flow exceeding 3% For engines with Non-piloted Fuel Nozzle Assemblies
720018 00
72-00-00-810-828
Engine Shutdown
720009 00
72-00-00-810-815
Engine Shutdown After FADEC ALTN Selected 720005 00
72-00-00-810-811
Engine Surge/Stall
720011 00
72-00-00-810-817
FADEC Circuit Breaker Does Not Reset
720008 00
72-00-00-810-813
R Bleed Leak Alert and Low ITT Margin
FADEC Does Not Alternate Lanes On Start
73-25-00-810-870
FPMU Seal Drain Accumulation
732101 00
73-21-00-810-815
Fuel Flow Greater Than 800 pph (363 kgph) During Start
720012 00
72-00-00-810-818
High-pressure Turbine Deterioration
720013 00
72-00-00-810-819
ITT Instrumentation Alert
720014 00
72-00-00-810-820
Noise During Hand Rotation of Fan
720015 00
72-00-00-810-821
EFFECTIVITY: ALL
Observed Fault List Page 1 Jul 20/15
EXPORT CONTROLLED
FAULT DESCRIPTION
FAULT CODE
FIM TASK REFERENCE
Hot Start/Torching On Start
720002 00
72-00-00-810-801-A01 72-00-00-810-801-A02
Stagnated Start (Hung Start)
720003 00
72-00-00-810-802
ITT Fluctuations
772102 00
77-21-00-810-811
ITT Indication Difference (Split) Between Left and Right Engines (Static)
772101 00
77-21-00-810-810
ITT Margin Decreases Quickly or in Steps with a Fuel Flow Increase of 1% or More and a Flat or Decreasing N2 Margin
753101 00
75-31-00-810-801
Low ITT Margin Alert
753102 00
75-31-00-810-803
Oil Consumption High / Oil Leakage
793001 00
79-37-00-810-807
Oil Pressure Display Shows Dashes
793005 00
79-37-00-810-809
Oil Pressure High (displayed on EICAS)
793002 00
79-37-00-810-805
Oil Pressure Low (display)
793003 00
79-37-00-810-804
Oil or Fuel Smell / Haze in the Cabin
720008 00
72-00-00-810-814
Oil Temperature High
793004 00
79-37-00-810-806
Overspeed (N1)
771001 00
77-11-00-810-809
Overspeed (N2)
771002 00
77-11-00-810-810
Smoke from Engine Exhaust at Shutdown
720007 00
72-00-00-810-812
Sudden Increase in ITT
772001 00
77-21-00-810-807
Thrust Oscillations / Fluctuations
720006 00
72-00-00-810-804
Vibration High (LP rotor)
774001 00
77-41-00-810-801
Vibration High (HP rotor)
774002 00
77-41-00-810-802
LP or HP Rotor Vibration Level of 0.00/unreadable
774003 00
77-41-00-810-803
EFFECTIVITY: ALL
Observed Fault List Page 2 Jul 20/15
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CHAPTER 71 LIST OF EFFECTIVE PAGES
CHAPTER SECTION OTHER SUBJECT PAGE IDENT DATE 71 Contents 1/ Jan.20/11 2 00-00 201 Jan.20/11 00-00 202 Jan.20/11 00-00 201 Jan.20/11 00-00 202 Jan.20/11 00-00 203 Jan.20/11 00-00 204 Jan.20/11 00-00 205/ Jan.20/11 206 R 00-00 201 Apr.20/14 R 00-00 202 Apr.20/14 R 00-00 203/ Apr.20/14 204 00-00 201 Jan.20/11 00-00 202 Jan.20/11 00-00 203 Jan.20/11 00-00 204 Jan.20/11 00-00 201 Dec.1/04 00-00 202 Dec.1/04 00-00 201 Aug.15/06 00-00 202 Aug.15/06 00-00 203/ Aug.15/06 204 --------------- END ---------------
CHAPTER SECTION SUBJECT PAGE 71
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C=CONFIG B=BREAKOUT
CHAPTER SECTION SUBJECT PAGE 71
OTHER IDENT
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LIST OF EFFECTIVE PAGES-71 Page 1/2 Oct 20/16
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CHAPTER 71 TABLE OF CONTENTS
SUBJECT
CH-SE-SUB
POWER PLANT Do the Test of the Engine Do the Test of the Engine Do the Test of the Engine POST-SB AE3007A-79-029 Do the Test of the Engine Do the Test of the Engine
71-00-00
PAGE
EFFECTIVITY
201 201 201 201 201 201
71−CONTENTS Page 1/2 Jan 20/16
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POWER PLANT MAINTENANCE PRACTICES TASK 71-00-00-810-801 1.
Do the Test of the Engine A.
General This task gives you the procedures to do the test of the engine for an indication of an oil pressure above normal limits. Do this test when specified by the Fault Isolation Manual.
B.
Materials None
C.
Consumable Materials None
D.
Expendable Parts None
E.
Standard Tools and Equipment (1) Signs, warning.
F.
Special Tools and Equipment None
G. R
References (1) TASK 79-37-00-810-805, Observed Fault: Oil Pressure High. (2) TASK 72-00-00-860-801, Start the Engine, AE 3007A Series Maintenance Manual (MM). (3) TASK 72-00-00-860-802, Stop the Engine, AE 3007A Series Maintenance Manual (MM).
H.
Job Set-Up SUBTASK 71-00-00-860-001 (1) Make the aircraft safe. (a) Open the applicable circuit breakers. (b) Put up the applicable warning signs.
I.
Procedure
EFFECTIVITY:ALL
TASK 71−00−00−810−801 Page 201 Jan 20/11
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SUBTASK 71-00-00-710-001 (1) Do the low-power screening run to determine the action necessary for the oil pressure over the limit condition. Do this task only when specified by the task for high oil pressure (Ref. TASK 79-37-00-810-805).
R
CAUTION: DO NOT EXCEED THE ENGINE OPERATION LIMITS. CAUTION: IF THE ENGINE DOES NOT START, DO NOT TRY TO START IT AGAIN UNTIL YOU DRY MOTOR IT FOR AT LEAST 30 SECONDS (REF. DRY MOTOR THE ENGINE, AE3007A OPERATIONS MANUAL, CSP 30002). THIS WILL REMOVE THE FUEL THAT POSSIBLY WENT IN THE ENGINE DURING THE FAILED START. (a) Start the engine (Ref. TASK 72-00-00-860-801, MM). (b) Operate the engine at idle for 15 minutes. (c) Snap accelerate the engine to 88% N2. NOTE: Snap acceleration is accelerating the engine to to the specified power within 3 seconds. (d) Record: -
Peak oil pressure ______________________________ psig.
-
Oil temperature _______________________________ °C.
(e) Continue to run the engine at 88% N2 until the oil pressure is stabilized. (f)
Record: -
Time for oil pressure to drop below 83 psig ____________ seconds.
-
Steady-state oil pressure _____________ psig.
(g) Decrease power to Ground Idle to allow engine temperatures to decrease. (h) Stop the engine (Ref. TASK 72-00-00-860-802, MM). J.
Job Close-up SUBTASK 71-00-00-860-002 (1) Close the circuit breakers and remove the warning signs. (a) Close the applicable circuit breakers. (b) Remove the warning signs.
R
(c) Continue to do the fault isolation task for observed high pressure (Ref. TASK 79-37-00-810-805).
EFFECTIVITY:ALL
TASK 71−00−00−810−801 Page 202 Jan 20/11
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POWER PLANT MAINTENANCE PRACTICES TASK 71-00-00-810-802 1.
Do the Test of the Engine A.
General This task gives you the procedures to do the test of the engine for an indication of an oil pressure above normal limits. Do this test when specified by the Fault Isolation Manual.
B.
Materials None
C.
Consumable Materials None
D.
Expendable Parts None
E.
Standard Tools and Equipment (1) Signs, warning.
F.
Special Tools and Equipment None
G. R
References (1) TASK 79-37-00-810-805, Observed Fault: Oil Pressure High. (2) TASK 72-00-00-860-801, Start the Engine, AE 3007A Series Maintenance Manual (MM). (3) TASK 72-00-00-860-802, Stop the Engine, AE 3007A Series Maintenance Manual (MM). (4) TASK 79-31-10-000-801, Remove the Oil Temperature/Pressure Sensor, AE 3007A Series Maintenance Manual (MM). (5) TASK 79-31-10-400-801, Install the Oil Temperature/Pressure Sensor, AE 3007A Series Maintenance Manual (MM).
H.
Job Set-Up SUBTASK 71-00-00-860-003 (1) Make the aircraft safe. (a) Open the applicable circuit breakers. (b) Put up the applicable warning signs.
EFFECTIVITY:ALL
TASK 71−00−00−810−802 Page 201 Jan 20/11
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SUBTASK 71-00-00-900-001 PRE-SB AE 3007A-79-029 (2) Install the extended range oil temperature/pressure sensor. (a) Remove the oil temperature/pressure sensor (Ref. TASK 79-31-10-000-801, MM). (b) Install the extended range oil temperature/pressure sensor (Ref. TASK 79-31-10-400-801, MM). NOTE: The extended range oil temperature/pressure sensor is the sensor introduced by SB AE 3007A-79-029. I.
Procedure SUBTASK 71-00-00-701-002 (1) Perform the test on the engine. (a) Verify the drain mast is clean.
R
(b) Do the thrust set screening run to determine the action necessary for the oil pressure over the limit condition. Do this task only when specified by the task for high oil pressure (Ref. TASK 79-37-00-810-805). WARNING:
MAKE SURE THAT THE AIRCRAFT IS CORRECTLY CHOCKED AND/OR TIED BEFORE YOU APPLY HIGH POWER TO THE ENGINE(S). INJURY TO PERSONS OR DAMAGE TO THE AIRCRAFT COULD OCCUR IF THE AIRCRAFT BEGINS TO ROLL AT HIGH POWER.
CAUTION: DO NOT EXCEED THE ENGINE OPERATION LIMITS. CAUTION: IF THE ENGINE DOES NOT START, DO NOT TRY TO START IT AGAIN UNTIL YOU DRY MOTOR IT FOR AT LEAST 30 SECONDS (REF. DRY MOTOR THE ENGINE, AE3007A OPERATIONS MANUAL, CSP 30002). THIS WILL REMOVE THE FUEL THAT POSSIBLY WENT IN THE ENGINE DURING THE FAILED START. 1
Start the engine (Ref. TASK 72-00-00-860-801, MM).
2
Operate the engine at idle for 15 minutes.
3
Record oil pressure and oil temperature.
4
Snap accelerate the engine to Thrust Set. NOTE: Snap acceleration is accelerating the engine to the specified power within 3 seconds.
5
Record: -
Peak oil pressure ______________________________ psig.
-
Oil temperature _______________________________ °C.
6
Continue to run the engine at Thrust Set for two minutes until the oil pressure is stabilized.
7
Record: -
Steady-state oil pressure _______________ psig (after two minutes at Thrust Set).
8
Decrease power to Ground Idle to allow engine temperatures to decrease.
9
Stop the engine (Ref TASK 72-00-00-860-802, MM).
(c) Check the drain mast for oil. EFFECTIVITY:ALL
TASK 71−00−00−810−802 Page 202 Jan 20/11
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J.
Job Close-up SUBTASK 71-00-00-900-002 PRE-SB AE 3007A-79-029 FIG. 201/TASK 71-00-00-990-801 FIG. 202/TASK 71-00-00-990-802 (1) Remove the extended range oil temperature/pressure sensor. (a) Remove the extended range oil temperature/pressure sensor (Ref. TASK 79-31-10-400-801, MM). (b) Install the oil temperature/pressure sensor (Ref. TASK 79-31-10-000-801, MM). PRE-SB AE 3007A-79-026 1
R
Use FIG. 201, the peak oil pressure, and the oil temperature to determine the region of oil pressure versus oil temperature and continue with the fault isolation for observed high oil pressure (Ref. TASK 79-37-00-810-805).
POST-SB AE 3007A-79-026 2 R
Use FIG. 202, the peak oil pressure, and the oil temperature to determine the region of oil pressure versus oil temperature and continue with the fault isolation for observed high oil pressure (Ref. TASK 79-37-00-810-805).
SUBTASK 71-00-00-860-004 (2) Return the engine to service. (a) Close the applicable circuit breakers (b) Remove the warning signs.
EFFECTIVITY:ALL
TASK 71−00−00−810−802 Page 203 Jan 20/11
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Maintenance Action Regions for Peak High Main Oil Pressure FIG. 201/TASK 71-00-00-990-801 EFFECTIVITY:ALL
TASK 71−00−00−810−802 Page 204 Jan 20/11
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Maintenance Action Regions for Peak High Main Oil Pressure FIG. 202/TASK 71-00-00-990-802 EFFECTIVITY:ALL
TASK 71−00−00−810−802 Page 205/206 Jan 20/11
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POWER PLANT MAINTENANCE PRACTICES TASK 71-00-00-810-803 1.
Do the Test of the Engine A.
General This task gives you the procedures to do the test of the engine for oil leakage from the drain tubes. Do this test only when specified by the Fault Isolation Manual.
B.
Materials (1) None
C.
Consumable Materials (1) None
D.
Expendable Parts (1) None
E.
Standard Tools and Equipment (1) Signs, warning.
F.
Special Tools and Equipment (1) None
G.
References (1) TASK 12-10-79-600-801, Service the Oil System of the Engine, AE 3007A Maintenance Manual, CSP 34022. (2) Dry Motor the Engine, AE 3007A Operations Manual, CSP 30017. (3) EMB-145 Aircraft Maintenance Manual (AMM).
H.
Job Set-up SUBTASK 71-00-00-860-805 (1) Make the aircraft safe. (a) Open the applicable circuit breakers. (b) Put up the applicable warning signs. SUBTASK 71-00-00-860-806 (2) Prepare the engine for run. (a) Service the oil system of the engine, if necessary (Ref. TASK 12-10-79-600-801, MM).
I.
Procedure
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TASK 71−00−00−810−803 Page 201 Apr 20/14
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SUBTASK 71-00-00-710-003 REF. TABLE 101 REF. TABLE 102 REF. TABLE 103 (1) Do the engine run. CAUTION: IF THE ENGINE DOES NOT START, DO NOT TRY TO START IT AGAIN UNTIL YOU DRY MOTOR IT FOR AT LEAST 30 SECONDS (REF. DRY MOTOR THE ENGINE, AE3007A OPERATIONS MANUAL, CSP 30017). THIS WILL REMOVE THE FUEL THAT POSSIBLY WENT IN THE ENGINE DURING THE FAILED START. (a) Start the engine (Ref. AMM). NOTE: When you operate the engine, monitor the cockpit indicators to determine that the engine is within normal limits. Make sure that there are no FADEC EICAS fault messages displayed. If there are any fault messages, do the troubleshooting for the message shown before doing the engine run. CAUTION: DO NOT OPERATE THE ENGINE AT GROUND IDLE FOR LESS THAN FIVE MINUTES BEFORE YOU DO THE LEAKAGE INSPECTION OR YOU WILL GET AN INCORRECT LEAKAGE INDICATION. IF YOU OPERATE THE ENGINE AT GROUND IDLE FOR LESS THAN FIVE MINUTES, INCORRECT TROUBLESHOOTING OR ENGINE REPLACEMENT THAT IS NOT NECESSARY CAN OCCUR. (b) Operate the engine at ground idle for a minimum of five. (c) Examine the engine drain tubes for leaks. Record the results in Table 101. TABLE 101 - Leak Rate for Engine Drain Tubes DRAIN TUBE LEAKAGE (YES/NO)
LEAK RATE (cc/minute or drops in a minute)
Hydraulic Pump Generators FPMU Drain Pressure Relief Valve Starter Pad (d) Move the throttle levers to maximum takeoff power within three seconds (transient state). Examine the pressure relief valve drain tube for oil leakage. Record the results in Table 102. R R R
NOTE: Spraying the area with a non-aqueous aerosol developer can help find the source of the leak. When finished, make sure that the developer is removed from the engine. TABLE 102 - Pressure Relief Valve Drain Tube Oil Leakage During Transient State DRAIN TUBE LEAKAGE (YES/NO) Pressure Relief Valve (e) Operate the engine at maximum takeoff power for two minutes.
EFFECTIVITY:ALL
TASK 71−00−00−810−803 Page 202 Apr 20/14
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(f)
R R R
Examine the pressure relief valve, hydraulic pump, generators, starter pad, and FPMU drain tubes for oil leakage. Record the oil pressure below and the results of the leak check in Table 103. NOTE: Spraying the area with a non-aqueous aerosol developer can help find the source of the leak. When finished, make sure that the developer is removed from the engine. -
Oil Pressure ______________ psi.
TABLE 103 - Pressure Relief Valve, Hydraulic pump, Generators, Starter Pad, and FPMU Drain Tubes Oil Leakage During Steady State DRAIN TUBE LEAKAGE (YES/NO) LEAK RATE (cc/minute or drops in a minute) Pressure Relief Valve Hydraulic Pump Generators FPMU Starter Pad (g) Decrease power to ground idle to allow engine temperatures to decrease. (h) Stop the engine (Ref. AMM).
EFFECTIVITY:ALL
TASK 71−00−00−810−803 Page 203/204 Apr 20/14
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POWER PLANT MAINTENANCE PRACTICES TASK 71-00-00-810-804 POST-SB AE3007A-79-029 1. Do the Test of the Engine A.
General This task gives you the procedures to do the test of the engine for an indication of an oil pressure above normal limits. Do this test when specified by the Fault Isolation Manual.
B.
Materials None
C.
Consumable Materials None
D.
Expendable Parts None
E.
Standard Tools and Equipment (1) Signs, warning.
F.
Special Tools and Equipment None
G. R
References (1) TASK 79-37-00-810-805, Observed Fault: Oil Pressure High. (2) TASK 72-00-00-860-801, Start the Engine, AE 3007A Series Maintenance Manual (MM). (3) TASK 72-00-00-860-802, Stop the Engine, AE 3007A Series Maintenance Manual (MM).
H.
Job Set-Up SUBTASK 71-00-00-860-008 (1) Make the aircraft safe. (a) Open the applicable circuit breakers. (b) Put up the applicable warning signs.
I.
Procedure
EFFECTIVITY:ALL
TASK 71−00−00−810−804 Page 201 Jan 20/11
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SUBTASK 71-00-00-710-004 (1) Do the test on the engine. (a) Make sure the drain mast is clean. (b) Do the thrust set screening run to find the action necessary for the oil pressure over the limit condition. Do this task only when specified by the task for high oil pressure (Ref. TASK 79-37-00-810-805).
R
WARNING:
MAKE SURE THAT THE AIRCRAFT IS CORRECTLY CHOCKED AND/OR TIED BEFORE YOU APPLY HIGH POWER TO THE ENGINE(S). INJURY TO PERSONS OR DAMAGE TO THE AIRCRAFT COULD OCCUR IF THE AIRCRAFT BEGINS TO ROLL AT HIGH POWER.
CAUTION: DO NOT EXCEED THE ENGINE OPERATION LIMITS. CAUTION: IF THE ENGINE DOES NOT START, DO NOT TRY TO START IT AGAIN UNTIL YOU DRY MOTOR IT FOR AT LEAST 30 SECONDS (REF. DRY MOTOR THE ENGINE, AE3007A OPERATIONS MANUAL). THIS WILL REMOVE THE FUEL THAT POSSIBLY WENT IN THE ENGINE DURING THE FAILED START. 1
Start the engine (Ref. TASK 72-00-00-860-801, MM).
2
Operate the engine at idle for 15 minutes.
3
Record oil pressure and oil temperature.
4
Snap accelerate the engine to Thrust Set. NOTE: Snap acceleration is accelerating the engine to the specified power within 3 seconds.
5
Record: -
Peak oil pressure ______________________________ psig.
-
Oil temperature _______________________________ °C.
6
Continue to run the engine at Thrust Set for two minutes.
7
Record: -
Oil pressure _______________ psig (after two minutes at Thrust Set).
8
Continue to run the engine at Thrust Set for three minutes.
9
Record: -
Steady-state oil pressure _______________ psig (after five minutes at Thrust Set).
10
Decrease power to Ground Idle to allow engine temperatures to decrease.
11
Stop the engine (Ref. TASK 72-00-00-860-802, MM).
(c) Check the drain mast for oil. (d) Use FIG. 201, the peak oil pressure, and the oil temperature to find the region of oil pressure versus oil temperature and continue with the fault isolation for observed high oil pressure (Ref. TASK 79-37-00-810-805).
R J.
Job Close-up
EFFECTIVITY:ALL
TASK 71−00−00−810−804 Page 202 Jan 20/11
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SUBTASK 71-00-00-860-009 (1) Return the engine to service. (a) Close the applicable circuit breakers. (b) Remove the warning signs.
EFFECTIVITY:ALL
TASK 71−00−00−810−804 Page 203 Jan 20/11
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Maintenance Action Regions for Peak High Main Oil Pressure FIG. 201/TASK 71-00-00-990-803 EFFECTIVITY:ALL
TASK 71−00−00−810−804 Page 204 Jan 20/11
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POWER PLANT MAINTENANCE PRACTICES TASK 71-00-00-810-805 1.
Do the Test of the Engine A.
General This task gives you the procedure to do the test of the engine for an ATTCS NO MRGN indication. Do this task only when specified by the Fault Isolation Manual.
B.
Materials None
C.
Consumable Materials None
D.
Expendable Parts None
E.
Standard Tooling and Equipment (1) Signs, warning
F.
Special Tools and Equipment None
G.
References (1) TASK 72-00-00-860-801, Start the Engine, AE3007A Series Maintenance Manual (MM) (2) TASK 72-00-00-860-802, Stop the Engine, AE3007A Series Maintenance Manual (MM)
H.
Job Set-Up SUBTASK 71-00-00-860-010 (1) Make the aircraft safe (a) Open the applicable circuit breakers (b) Put up applicable warning signs
I.
Procedure
EFFECTIVITY:ALL
TASK 71−00−00−810−805 Page 201 Dec 1/04
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SUBTASK 71-00-00-710-005 (1) Do the test on the engine. CAUTION: IF THE ENGINE DOES NOT START, DO NOT TRY TO START IT AGAIN UNTIL YOU DRY MOTOR IT FOR AT LEAST 30 SECONDS (REF. DRY MOTOR THE ENGINE, OPERATIONS MANUAL). IF YOU DO NOT DRY MOTOR THE ENGINE A HOT OR TORCHING START COULD OCCUR AND DAMAGE THE ENGINE. (a) Point the airplane into the wind and align the heading within 20 degrees of the prevailing wind direction. (b) Set the brakes. WARNING:
MAKE SURE THAT THE AIRCRAFT IS CORRECTLY CHOCKED AND/OR TIED BEFORE YOU APPLY HIGH POWER TO THE ENGINE(S). INJURY TO PERSONS OR DAMAGE TO THE AIRCRAFT COULD OCCUR IF THE AIRCRAFT BEGINS TO ROLL AT HIGH POWER.
(c) Set the most current tower temperature available. (d) Select an alternate takeoff mode (ALT T/O-1, T/O or E T/O) . (e) Start the engine (Ref. TASK 72-00-00-860-801, MM) (f)
Operate the engine at idle for four minutes.
(g) Move the throttle lever to the THRUST SET detent for at least 20 seconds, or until ITT peaks and then reduces 5 degrees C below peak ITT. (h) Monitor and record EICAS messages.
J.
(i)
Decrease power to ground idle to let engine temperatures to decrease.
(j)
Stop the engine (Ref. TASK 72-00-00-860-802, MM)
Job Close-Up SUBTASK 71-00-00-860-011 (1) Close the circuit breakers and remove the warning signs (a) Close the applicable circuit breakers (b) Remove the warning signs
EFFECTIVITY:ALL
TASK 71−00−00−810−805 Page 202 Dec 1/04
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POWER PLANT MAINTENANCE PRACTICES TASK 71-00-00-810-806 1.
Do the Test of the Engine A.
General This task gives you the procedure to do the test of the engine when there is an indication that the oil pressure is below limits. Do this test only when sent here by the Fault Isolation Manual.
B.
Materials None
C.
Consumable Materials None
D.
Expendable Parts None
E.
Standard Tools and Equipment (1) Signs, warning.
F.
Special Tools and Equipment None
G.
References (1) TASK 72-00-00-860-801, Start the Engine, MM. (2) TASK 72-00-00-860-802, Stop the Engine, MM. (3) Engine Dry Motoring, Section 10: Normal Operation, Operations Manual.
H.
Job Set-up SUBTASK 71-00-00-860-012 (1) Make the aircraft safe. (a) Open the applicable circuit breakers. (b) Put up the applicable warning signs.
I.
Procedure
EFFECTIVITY:ALL
TASK 71−00−00−810−806 Page 201 Aug 15/06
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SUBTASK 71-00-00-710-003 REF. TABLE 201 REF. TABLE 202 REF. TABLE 203 (1) Do the test of the engine. WARNING:
MAKE SURE THAT THE AIRCRAFT IS CORRECTLY CHOCKED AND/OR TIED BEFORE YOU APPLY HIGH POWER TO THE ENGINE(S). INJURY TO PERSONS OR DAMAGE TO THE AIRCRAFT CAN OCCUR IF THE AIRCRAFT STARTS TO MOVE AT HIGH POWER.
CAUTION: DO NOT GO ABOVE THE ENGINE OPERATION LIMITS. DAMAGE TO THE ENGINE CAN OCCUR. CAUTION: IF THE ENGINE DOES NOT START, DO NOT TRY TO START IT AGAIN UNTIL YOU DRY MOTOR THE ENGINE. TOO MUCH FUEL IN THE COMBUSTION CHAMBER CAN CAUSE DAMAGE TO THE ENGINE. (a) Make sure the drain mast is clean. (b) Do the test to find the action necessary for a low oil pressure indication. 1
Start the engine (Ref. 72-00-00-860-801, MM). a
If the engine does not start, dry motor the engine for a minimum of 30 seconds (Ref. Section 10, Operations Manual.
2
Operate the engine at Ground Idle for 15 minutes.
3
Record the oil pressure and oil temperature.
TABLE 201 - Oil pressure and oil temperature Oil pressure (psig (kPag)) Oil temperature (°F (°C)) 4
Increase the engine to Thrust Set.
5
Continue to operate the engine at Thrust Set for three minutes until the oil pressure is stable
6
Quickly decrease the engine to Ground Idle.
7
Record the lowest oil pressure and temperature:
TABLE 202 - Lowest oil pressure and oil temperature Minimum oil pressure (psig (kPag)) Oil temperature (°F (°C)) 8
Keep the engine at Ground Idle for five minutes.
9
Record steady-state oil pressure and steady-state oil temperature.
TABLE 203 - Steady-state oil pressure and steady-state oil temperature Oil pressure (psig (kPag)) Oil temperature (°F (°C)) 10
Stop the engine (Ref. 72-00-00-860-802, MM).
(c) Examine the drain mast for oil. J.
Job Close-Up
EFFECTIVITY:ALL
TASK 71−00−00−810−806 Page 202 Aug 15/06
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SUBTASK 71-00-00-860-013 (1) Close the circuit breakers and remove the warning signs. (a) Close the applicable circuit breakers. (b) Remove the applicable warning signs.
EFFECTIVITY:ALL
TASK 71−00−00−810−806 Page 203/204 Aug 15/06
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CHAPTER 72 LIST OF EFFECTIVE PAGES
CHAPTER SECTION SUBJECT PAGE 72 Contents 1 Contents 2 00-00 101 00-00 102 00-00 201 00-00 202 00-00 203 00-00 204 00-00 201 00-00 202 00-00 203 00-00 204 00-00 201/ 202 00-00 201 00-00 202 00-00 203 00-00 204 00-00 205 00-00 206 00-00 207/ 208 00-00 201 00-00 202 00-00 203 00-00 204 00-00 201 00-00 202 00-00 201 00-00 202 00-00 201/ 202 00-00 201 00-00 202 00-00 201 00-00 202 00-00 203 00-00 204 00-00 201 00-00 202 00-00 203/ 204 00-00 201/ 202 00-00 201 00-00 202 00-00 203/ 204 00-00 201 00-00 202 00-00 201 00-00 202 00-00 203 00-00 204 00-00 205 00-00 206 00-00 207/ 208 00-00 201 00-00 202
OTHER IDENT
CHAPTER SECTION OTHER DATE SUBJECT PAGE IDENT DATE 72 Jul.20/15 00-00 203 Jul.20/10 Jul.20/15 00-00 204 Jul.20/10 Jul.20/14 00-00 201 Feb.15/03 Jul.20/14 00-00 202 Feb.15/03 Apr.20/08 00-00 201 Oct.20/14 Apr.20/08 00-00 202 Oct.20/14 Apr.20/08 00-00 201 Jul.20/15 Apr.20/08 00-00 202 Jul.20/15 Jul.20/10 00-00 203/ Jul.20/15 Jul.20/10 204 Jul.20/10 00-00 201/ Oct.20/07 Jul.20/10 202 Feb.15/05 00-00 201 Jul.20/13 00-00 202 Jul.20/13 Jan.20/11 00-00 201/ Oct.20/10 Jan.20/11 202 Jan.20/11 00-00 201/ Feb.15/06 Jan.20/11 202 Jan.20/11 00-00 201 Jul.20/13 Jan.20/11 00-00 202 Jul.20/13 Jan.20/11 00-00 201/ Jun.15/05 202 Oct.20/14 00-00 201 Jan.20/10 Oct.20/14 00-00 202 Jan.20/10 Oct.20/14 00-00 203 Jan.20/10 Oct.20/14 00-00 204 Jan.20/10 Jul.20/14 R 00-00 201 Jan.20/16 Jul.20/14 R 00-00 202 Jan.20/16 Oct.20/15 00-00 201/ Oct.20/07 Oct.20/15 202 Oct.20/15 00-00 201 Jul.20/13 00-00 202 Jul.20/13 Oct.20/14 00-00 201/ Jan.20/12 Oct.20/14 202 Oct.15/06 00-00 201/ Oct.20/13 Oct.15/06 202 Oct.15/06 00-00 301 Jul.20/08 Oct.15/06 00-00 302 Jul.20/08 Jun.15/05 00-00 303 Jul.20/08 Jun.15/05 00-00 304 Jul.20/08 Jun.15/05 00-00 305 Jul.20/08 00-00 306 Jul.20/08 Jun.15/05 --------------- END ---------------
CHAPTER SECTION SUBJECT PAGE 72
OTHER IDENT
DATE
Oct.20/15 Oct.20/15 Oct.20/15 Aug.15/04 Aug.15/04 Oct.20/09 Oct.20/09 Oct.20/09 Oct.20/09 Oct.20/09 Oct.20/09 Oct.20/09 Jul.20/10 Jul.20/10
C=CONFIG B=BREAKOUT
LIST OF EFFECTIVE PAGES-72 Page 1/2 Oct 20/16
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CHAPTER 72 TABLE OF CONTENTS
SUBJECT
CH-SE-SUB
ENGINE - GENERAL FAULT CODE INDEX Observed Fault: Hot Start / Torching On Start For engines with Piloted Fuel Nozzle Assemblies Observed Fault: Hot Start / Torching On Start For engines with Non-Piloted Fuel Nozzle Assemblies Observed Fault: Stagnated Start (Hung Start) Observed Fault: No Lightoff/Delayed Lightoff For engines with Piloted Fuel Nozzle Assemblies Observed Fault: No Lightoff/Delayed Lightoff For engines with Non-Piloted Fuel Nozzle Assemblies Observed Fault: Thrust Oscillations / Fluctuations EICAS Message: E1/E2 NO DISP (set by FADEC Discrete: FLTGP1 (bit 29) / (355 / SFLTS1) = 1) EICAS Message: E1/E2 SHORT DISP (set by FADEC Discrete: FLTGP2 (bit 22) / (355 / SFLTS1) = 1) Maintenance Message: ENG1/ENG2 LT FAULT (set by FADEC Discrete: FLTGP3 (bit 26) / (356 / SFLTS2) = 1) Maintenance Message: ENG1 / ENG2 SCHED MAINT REPAIR EICAS Message: ENG1/ENG2 OUT Observed Fault: Engine Shutdown After FADEC ALTN Selected Observed Fault: Smoke from Engine Exhaust at Shutdown Observed Fault: FADEC Circuit Breaker Does Not Reset Observed Fault: Oil or Fuel Smell/Haze in the Cabin Observed Fault: Engine Shutdown Observed Fault: Engine Does Not Make Necessary Thrust Observed Fault: Engine Surge/Stall
72-00-00
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EFFECTIVITY
101 201 201 201 201 201 201 201 201 201 201 201 201 201 201 201 201 201 201
72−CONTENTS Page 1 Jul 20/15
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SUBJECT
R
R R
Observed Fault: Fuel Flow Greater than 800 pph (363 kgph) During Start High-pressure Turbine Deterioration Alert ITT Instrumentation Alert Observed Fault: Noise during hand rotation of fan Observed Fault: Engine Noise on FADEC Lane Change EICAS Message: E1(2) Exceedance Observed Fault: No Lightoff/Delayed Lightoff For engines with Piloted or Non-Piloted Fuel Nozzle Assemblies Observed Fault: Power Fluctuations Observed Fault: Decrease in HP Speed Margin Combustion Liner Distress Alert Observed Fault: Step change in fuel flow exceeding 3% For engines with Non-piloted Fuel Nozzle Assemblies Observed Fault: Engine Does Not Start (Fast N2 Indication) Takeoff Power Setting Exceeds 5 Minute Duration Task Support
CH-SE-SUB
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EFFECTIVITY
201 201 201 201 201 201 201 201 201 201 201 201 201 301
72−CONTENTS Page 2 Jul 20/15
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FAULT CODE INDEX FAULT CODE
FAULT DESCRIPTION
7200O2 00
Hot Start / Torching On Start
72-00-00-810-801-A01 72-00-00-810-801-A02
7200O3 00
Stagnated Start (Hung Start)
72-00-00-810-802
7200O4 00
No Lightoff/Delayed Lightoff
72-00-00-810-803-A01 72-00-00-810-803-A02
7200O9 00
Engine Does Not Start (No Lightoff/No Fuel Flow)
72-00-00-810-824
7200O5 00
Engine Shutdown After FADEC ALTN Selected
72-00-00-810-811
7200O6 00
Thrust Oscillations / Fluctuations
72-00-00-810-804
7200O7 00
Smoke from Engine Exhaust at Shutdown
72-00-00-810-812
7200O8 00
Oil or Fuel Smell / Haze in the Cabin
72-00-00-810-814
720008 00
FADEC Circuit Breaker Does Not Reset
72-00-00-810-813
720009 00
Engine Shutdown
72-00-00-810-815
720010 00
Engine Does Not Make Necessary Thrust
72-00-00-810-816
720011 00
Engine Surge/Stall
72-00-00-810-817
720012 00
Fuel Flow Greater Than 800pph (363 kgph) During Start
72-00-00-810-818
720013 00
High-pressure Turbine Deterioration Alert
72-00-00-810-819
720014 00
ITT Instrumentation Alert
72-00-00-810-820
720015 00
Noise during hand rotation of fan
72-00-00-810-821
720019 00
Engine Noise on FADEC Lane Change
72-00-00-810-822
720016 00
Decrease in N2 Margin
72-00-00-810-826
720017 00
Combustion Liner Distress Alert
72-00-00-810-827
EFFECTIVITY:ALL
MAINT. MESSAGE
GO TO FIM TASK
72−FAULT CODE INDEX Page 101 Jul 20/14
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FAULT CODE
FAULT DESCRIPTION
720018 00
Step change in fuel flow exceeding 3% For engines with Non-piloted Fuel Nozzle Assemblies
72-00-00-810-828
720020 00
Engine Does Not Start (Fast N2 Indication)
72-00-00-810-829
R 720012 00 R
Takeoff Power Setting Exceeds 5 minutes
72-00-00-810-830
720M01 00
E1 NO DISPATCH (Caution)
72-00-00-810-805
720M02 00
E2 NO DISPATCH (Caution)
72-00-00-810-805
720M01 51
E1 EXCEEDANCE (Caution)
72-00-00-810-823
720M01 52
E2 EXCEEDANCE (Caution)
72-00-00-810-823
720M03 00
E1 SHORT DISP (Advisory)
72-00-00-810-806
720M04 00
E2 SHORT DISP (Advisory)
72-00-00-810-806
720M05 00
ENG1 OUT (Caution)
72-00-00-810-809
720M06 00
ENG2 OUT (Caution)
72-00-00-810-809
EFFECTIVITY:ALL
MAINT. MESSAGE
GO TO FIM TASK
72−FAULT CODE INDEX Page 102 Jul 20/14
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Observed Fault: Hot Start / Torching On Start For engines with Piloted Fuel Nozzle Assemblies DESCRIPTION: A hot start occurs when the ITT is above the temperature usually seen during engine starts, or is above 800°C. A torch start occurs when a flame is seen in the exhaust during an engine start.
POSSIBLE CAUSES: 1. Residual ITT high 2. Stagnated start (hung start) 3. Igniter 4. Fuel nozzles 5. FPMU 6. PMA stator 7. Ignition exciter 8. Worn combustion liner alignment pins
R CAUTION: MAKE SURE THAT YOU DO NOT MIX PILOTED FUEL NOZZLES WITH NON-PILOTED FUEL R NOZZLES. DAMAGE TO THE ENGINE CAN OCCUR.
01 Was the residual ITT above 210°C when the start attempt was initiated?
18 Dry motor the engine to decrease the ITT before initiating an engine start. The risk of a -Yes hot start occurring increases when residual ITT is above 210°C.
| No 02 Did a stagnated (hung) start also occur on this start attempt?
-Yes 19 Do the troubleshooting for a stagnated (hung) start (Ref. 72-00-00-810-802).
| No 03 Attempt an engine start (Ref.AMM). Did a torching start occur?
20 When torching only occurs when the engine has been static for a long period of time, a slow -Yes leak in the fuel nozzles is likely. Replace all 16 fuel nozzles (Ref. 73-11-10-000-801/ 73-11-10-400-801 MM) within 150 flight hours.
| No 04 Go to block 05.
Observed Fault: Hot Start / Torching On Start For engines with Piloted Fuel Nozzle Assemblies EFFECTIVITY:ALL
TASK 72−00−00−810−801−A01 Page 201 Apr 20/08
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05 Attempt an engine start with the other FADEC in control (ignition switch in the AUTO position) (Ref.AMM). Did a torching start occur?
21 Go to block 14. -Yes
| No 06 Replace the bottom or top igniter (Ref. 74-21-10-000-801/74-21-10-400-801 or 74-21-10-000-802/74-21-10-400-802 MM). Attempt an engine start (Ref.AMM). Did a torching start occur?
22 Remove the igniter from service. -No
| Yes 07 Replace the ignition exciter (Ref. 74-13-10-000-801/74-13-10-400-801 MM). Attempt an engine start (Ref.AMM). Did a torching start occur?
23 Remove the ignition exciter from service. -No
| Yes 08 Replace igniter lead (Igniter A ref. 74-21-15-000-801/74-21-15-400-801 MM) (74-21-20-000-801/74-21-20-400-801 MM). Attempt an engine start (Ref.AMM). Did a torching start occur?
24 Remove the igniter lead from service. -No
| Yes 09 Interchange harness connectors PMAA and 25 Replace the PMA stator (Ref. PMAB on the PMA stator. Determine which 74-11-10-000-801/74-11-10-400-801 MM). FADEC (chanel) is in control when this fault -Yes occurs, and attempt an engine start (Ref.AMM) with the FADEC in control. Did a torching start occur? | No 10 Go to block 11.
Observed Fault: Hot Start / Torching On Start For engines with Piloted Fuel Nozzle Assemblies EFFECTIVITY:ALL
TASK 72−00−00−810−801−A01 Page 202 Apr 20/08
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11 Do a test for continuity/resistance (1 ohm max./harness), internal shorts, and shorts to ground (1,000 ohms min.) on the FADEC A/B (W11/14) harness (Ref. Fig. 301/302). Is there a fault with the harness?
26 Replace the harness (Ref. 76-00-00 MM). -Yes
| No 12 Do a borescope inspection of the combustion liner outer wall mouning brackets (Ref. 72-40-00-200-801 MM). Are any of the brackets damaged?
-Yes
27 Remove the engine (Ref. AMM) from service within 100FH.
| No | 13 Remove the combustion liner alignment pins one at a time (Ref. TASK 72-45-12-000-801/72-45-12-400-801 MM). Examine the combustion liner alignment pins (Ref. TASK 72-45-12-200-801 MM). Are the alignment pins serviceable?
28 Replace unserviceable alignment pin(s) (Ref. TASK 72-45-12-400-801 MM). -No
| Yes |
29 Replace the fuel nozzles (Ref. 73-11-10-000-801/73-11-10-400-801 MM).
Observed Fault: Hot Start / Torching On Start For engines with Piloted Fuel Nozzle Assemblies EFFECTIVITY:ALL
TASK 72−00−00−810−801−A01 Page 203 Apr 20/08
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14 Use a borescope to examine all 16 fuel nozzles for hard carbon deposits at AREA B (Ref. FIG. 303/TASK 72-00-00-990-803) (Ref. 72-40-00-200-801 MM). Are deposits found?
30 Replace the fuel nozzle(s) with the hard carbon deposits (Ref. 73-11-10-000-801/73-11-00-400-801 MM). Do -Yes not disturb the deposits on the fuel nozzle(s). Contact Rolls-Royce customer support for further instructions.
| No 15 Use a borescope to examine the combustion liner outer wall mounting brackets -No (Ref. 72-40-00-200-801 MM). Are the mounting brackets within the serviceable limits?
31 Remove the engine (Ref. AMM) from service within 100FH.
| Yes 16 Remove the combustion liner alignment pins one at a time (Ref. TASK 72-45-12-000-801/72-45-12-400-801 MM). Examine the combustion liner alignment pins (Ref. TASK 72-45-12-200-801 MM). Are the alignment pins serviceable?
32 Replace unserviceable alignment pin(s) (Ref. TASK 72-45-12-400-801 MM). -No
| Yes | 17 Do an engine start (Ref.AMM). Did a hot/torch start occur?
-Yes
33 Replace the FPMU (Ref. 73-21-10-000-801/73-21-10-400-801 MM).
| No |
34 Replace the fuel nozzles (Ref. 73-11-10-000-801/73-11-10-400-801 MM).
Observed Fault: Hot Start / Torching On Start For engines with Piloted Fuel Nozzle Assemblies EFFECTIVITY:ALL
TASK 72−00−00−810−801−A01 Page 204 Apr 20/08
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Observed Fault: Hot Start / Torching On Start For engines with Non-Piloted Fuel Nozzle Assemblies DESCRIPTION: A hot start occurs when the ITT is above the temperature usually seen during engine starts, or is above 800°C. A torch start occurs when a flame is seen in the exhaust during an engine start.
POSSIBLE CAUSES: 1. Residual ITT high 2. Stagnated start (hung start) 3. Igniter 4. FPMU 5. PMA stator 6. Ignition exciter 7. Worn combustion liner alignment pins
01 Was the residual ITT above 210°C when the start attempt was initiated?
17 Dry motor the engine to decrease the ITT before initiating an engine start. The risk of a -Yes hot start occurring increases when residual ITT is above 210°C.
| No 02 Did a stagnated (hung) start also occur on this start attempt?
-Yes 18 Do the troubleshooting for a stagnated (hung) start (Ref. 72-00-00-810-802).
| No 03 Attempt two (2) engine starts with the ignition switch in the AUTO position (Ref. -No AMM). One on FADEC A, and one on FADEC B (Ref.AMM). Did a torching start occur?
19 Go to block 13.
| Yes 04 Go to block 05.
Observed Fault: Hot Start / Torching On Start For engines with Non-Piloted Fuel Nozzle Assemblies EFFECTIVITY:ALL
TASK 72−00−00−810−801−A02 Page 201 Jul 20/10
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05 Replace the bottom or top igniter (Ref. 74-21-10-000-801/74-21-10-400-801 or 74-21-10-000-802/74-21-10-400-802 MM). Attempt an engine start (Ref.AMM). Did a torching start occur?
20 Remove the igniter from service. -No
| Yes 06 Replace the ignition exciter (Ref. 74-13-10-000-801/74-13-10-400-801 MM). Attempt an engine start (Ref.AMM). Did a torching start occur?
21 Remove the ignition exciter from service. -No
| Yes 07 Replace igniter lead (Igniter A ref. 74-21-15-000-801/74-21-15-400-801 MM) (74-21-20-000-801/74-21-20-400-801 MM). Attempt an engine start (Ref.AMM). Did a torching start occur?
22 Remove the igniter lead from service. -No
| Yes 08 Interchange harness connectors PMAA and 23 Replace the PMA stator (Ref. PMAB on the PMA stator. Determine which 74-11-10-000-801/74-11-10-400-801 MM). FADEC (chanel) is in control when this fault -Yes occurs, and attempt an engine start (Ref.AMM) with the FADEC in control. Did a torching start occur? | No 09 Do a test for continuity/resistance (1 ohm max./harness), internal shorts, and shorts to ground (1,000 ohms min.) on the FADEC A/B (W11/14) harness (Ref. Fig. 301/302). Is there a fault with the harness?
24 Replace the harness (Ref. 76-00-00 MM). -Yes
| No 10 Go to block 11.
Observed Fault: Hot Start / Torching On Start For engines with Non-Piloted Fuel Nozzle Assemblies EFFECTIVITY:ALL
TASK 72−00−00−810−801−A02 Page 202 Jul 20/10
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11 Do a borescope inspection of the 25 Remove the engine (Ref. AMM) from combustion liner outer wall mouning brackets service within 100FH. -No (Ref. 72-40-00-200-801 MM). Are the mounting brackets within the serviceable limits? | Yes 12 Remove the combustion liner alignment pins one at a time (Ref. TASK 72-45-12-000-801/72-45-12-400-801 MM). Examine the combustion liner alignment pins (Ref. TASK 72-45-12-200-801 MM). Are the alignment pins serviceable?
26 Replace unserviceable alignment pin(s) (Ref. TASK 72-45-12-400-801 MM). -No
| Yes |
27 Return the engine to service.
Observed Fault: Hot Start / Torching On Start For engines with Non-Piloted Fuel Nozzle Assemblies EFFECTIVITY:ALL
TASK 72−00−00−810−801−A02 Page 203 Jul 20/10
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13 Use a borescope to examine the combustion liner outer wall mounting brackets -No (Ref. 72-40-00-200-801 MM). Are the mounting brackets within the serviceable limits?
28 Remove the engine (Ref. AMM) from service within 100FH.
| Yes 14 Remove the combustion liner alignment pins one at a time (Ref. TASK 72-45-12-000-801/72-45-12-400-801 MM). Examine the combustion liner alignment pins (Ref. TASK 72-45-12-200-801 MM). Are the alignment pins serviceable?
29 Replace unserviceable alignment pin(s) (Ref. TASK 72-45-12-400-801 MM). -No
| Yes | 15 Do an engine start (Ref.AMM). Did a hot/torch start occur?
-Yes
30 Contact Rolls-Royce.
| No | R
16 If the engine has been static for a period of 31 Replace the FPMU (Ref. time with the boost pumps on, a slow leak can 73-21-10-000-801/73-21-10-400-801 MM). occur due an AVSV failure in the FPMU. -Yes Remove the FPMU out fuel line, turn the boost pumps on, check for fuel leak. Did fuel leak out of the FPMU? | No |
32 Contact Rolls-Royce.
Observed Fault: Hot Start / Torching On Start For engines with Non-Piloted Fuel Nozzle Assemblies EFFECTIVITY:ALL
TASK 72−00−00−810−801−A02 Page 204 Jul 20/10
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Observed Fault: Stagnated Start (Hung Start) DESCRIPTION: The engine has a successful light-off, but is slow to reach idle (63% N2 RPM) or does not reach idle at all.
POSSIBLE CAUSES: 1. CABVs dirty or damaged 2. CABCV dirty 3. 9th-stage air-bleed check valve 4. FPMU
01 Do the fault isolation procedures in the Embraer FIM for a Stagnated Start (Hung Start) (Ref. Task 72-00-00-810-803-A, EMB FIM) before you do the fault isolation procedures in the Rolls-Royce FIM. | Yes R R R R
02 Do the test of the CABVs (Ref. 75-31-10-700-801MM). Did the valves open?
05 Clean (Ref. 75-31-10-100-801 MM), repair (Ref. 75-31-10-300-801 MM), or replace (Ref. -No 75-31-10-000-801/75-31-10-400-801 MM) the CABV(s).
| Yes 03 Examine the CABCV and the compressor air-bleed-control tubes (Ref. 75-31-10-100-801 MM). Are they dirty?
06 Clean the CABCV and the compressor -No air-bleed-control tubes (Ref. 75-31-10-100-801 MM).
| Yes 04 Examine the 9th-stage air-bleed check valve (Ref. 36-11-01/601 AMM). Is the check valve serviceable?
07 Replace the 9th-stage air-bleed check -No valve (Ref. 36-11-01/401 AMM).
| Yes |
08 Replace FPMU (Ref. 73-21-10-000-801/73-21-10-400-801 MM).
Observed Fault: Stagnated Start (Hung Start) EFFECTIVITY:ALL
TASK 72−00−00−810−802 Page 201/202 Feb 15/05
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Observed Fault: No Lightoff/Delayed Lightoff For engines with Piloted Fuel Nozzle Assemblies DESCRIPTION: A no lightoff event occurs when an ITT does not increase within the abort start time limit. A delayed lightoff event occurs when an excessive amount of fog or smoke is produced during start.
POSSIBLE CAUSES: 1. ATS system fault 2. Fuel nozzle(s) 3. FPMU 4. PMA stator 5. Wiring harness 6. Igniter 7. Exciter 8. Worn combustion liner alignment pins
CAUTION: MAKE SURE THAT YOU DO NOT MIX PILOTED FUEL NOZZLES WITH NON-PILOTED FUEL NOZZLES. DAMAGE TO THE ENGINE CAN OCCUR.
01 Supply electrical power to the aircraft. 21 Do the troubleshooting for the maintenance Access the maintenance messages from the messages displayed. central maintenance computer (CMC) (Ref. -Yes Introduction). Are there engine, fuel system, or PMA related messages displayed? | No 02 Try two (2) engine starts with the ignition switch in the AUTO position (Ref. AMM). One on FADEC A, and one on FADEC B. Monitor the N2 RPM and the fuel flow rate during each start. Did a no start, delayed lightoff occur?
22 Go to block 17. -No
| Yes 03 Was the N2 Speed at least 28% when fuel was first shown?
-No
23 Do the troubleshooting on the ATS system (valve, air supply, starter, controls) (Ref. AMM).
| Yes 04 Go to Block 05.
Observed Fault: No Lightoff/Delayed Lightoff For engines with Piloted Fuel Nozzle Assemblies EFFECTIVITY:ALL
TASK 72−00−00−810−803−A01 Page 201 Jan 20/11
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R
05 After 10 seconds of fuel flow indication with no light-off, was the fuel flow rate at between 250 and 400 pph (113 and 181 kgph).
-No
24 Go to block 19.
| Yes 06 Does the problem occur on both FADEC A and FADEC B?
-Yes
25 Go to block 18.
| No 07 Replace the exciter on the FADEC system that has the problem (Ref TASK 74-13-10-000-801/74-13-10-400-801, MM). Try -No an engine start on the FADEC system that had the problem. Does the problem repeat?
26 Remove the exciter from service.
| Yes 08 Replace the igniter on the FADEC system that has the problem (Ref TASK 74-21-10-000-801/74-21-10-400-801, MM) . Try an engine start on the FADEC system that had the problem. Does the problem repeat?
27 Remove the igniter from service. -No
| Yes 09 Replace the 3 fuel nozzles adjacent to the igniter on the FADEC system that has the problem (Ref. TASK -No 73-11-10-000-801/73-11-10-400-801, MM). Try an engine start on the FADEC system that had the problem. Does the problem repeat?
28 Remove the 3 fuel nozzles from service.
| Yes 10 Go to Block 11
Observed Fault: No Lightoff/Delayed Lightoff For engines with Piloted Fuel Nozzle Assemblies EFFECTIVITY:ALL
TASK 72−00−00−810−803−A01 Page 202 Jan 20/11
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11 Replace the igniter lead on the FADEC system that has the problem (Ref. TASK 74-21-15-000-801/74-21-15-400-801 or -No 74-21-20-000-801/74-21-20-400-801 MM). Try an engine start on the FADEC system that had the problem. Does the problem repeat?
29 Remove the igniter lead from service.
| Yes 12 Interchange harness connectors PMA A and PMA B on the PMA stator.Try an engine start -No on the FADEC system that had the problem. Does the problem repeat?
30 Replace the PMA stator (Ref. TASK 73-11-10-000-801/73-11-10-400-801, MM).
| Yes 13 Do a test for continuity/resistance (1 ohm max./harness), internal shorts, and shorts to ground (1000 ohms min.) on the FADEC A/B (W11/14) harness (Ref. FIG. 301/TASK 72-00-00-990-801 /FIG. 302/TASK 72-00-00-990-802. Is there a fault with the harness?
31 Replace the defective harness (Ref. TASK 76-00-00, MM). -Yes
| No 14 Do a borescope inspection of the combustion liner outer wall mounting brackets (Ref. TASK 72-40-00-200-801, MM). Are the mounting brackets within the serviceable limits?
-No
32 Remove the engine from service within 100 flight hours.
| Yes 15 Go to Block 16
Observed Fault: No Lightoff/Delayed Lightoff For engines with Piloted Fuel Nozzle Assemblies EFFECTIVITY:ALL
TASK 72−00−00−810−803−A01 Page 203 Jan 20/11
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16 Remove the combustion liner alignment pins one at a time (Ref. TASK 72-45-12-000-801/72-45-12-400-801, MM). Examine the combustion liner alignment pins (Ref. TASK 72-45-12-200-801, MM). Are the alignment pins serviceable?
33 Replace unserviceable alignment pin(s) (Ref. TASK 72-45-12-400-801, MM). -No
| Yes
34 Return the engine to service.
Observed Fault: No Lightoff/Delayed Lightoff For engines with Piloted Fuel Nozzle Assemblies EFFECTIVITY:ALL
TASK 72−00−00−810−803−A01 Page 204 Jan 20/11
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17 Did you see the problem after the engine had been static for a long period of time (more than 90 minutes had elasped since the last engine shutdown) or when the outside air temperature was below 10°C (50°F)?
35 When delayed lightoffs or torched starts occur primarily after the engine was shutdown for a long period of time, or when the air -Yes temperature is below 10°C (50°F), degraded (dirty) fuel nozzles are likely. Replace the 3 fuel nozzles adjacent to the igniter on the FADEC system that has the problem
| No
36 Return the engine to service.
Observed Fault: No Lightoff/Delayed Lightoff For engines with Piloted Fuel Nozzle Assemblies EFFECTIVITY:ALL
TASK 72−00−00−810−803−A01 Page 205 Jan 20/11
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18 Replace all 16 fuel nozzles (Ref. TASK 37 Remove the fuel nozzles from service. 73-11-10-000-801/73-11-10-400-801, MM). Try -No an engine start on each FADEC system. Does the problem repeat? | Yes
38 Do a borescope inspection of the combustion liner outer wall mounting brackets (Ref. TASK 72-40-00-200-801, MM). Remove the engine within 100 flight hours if any of the brackets are damaged more than the serviceable limits.
Observed Fault: No Lightoff/Delayed Lightoff For engines with Piloted Fuel Nozzle Assemblies EFFECTIVITY:ALL
TASK 72−00−00−810−803−A01 Page 206 Jan 20/11
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19 Was there a fuel flow indication during the start try?
39 Do the troubleshooting for the observed -No fault: No Lightoff/No Fuel Flow (Ref. TASK 72-00-00-810-824).
| Yes 20 Remove the filter bowl on the FPMU (Ref. TASK 73-21-10-000-802, MM). Is there fuel at the FPMU?
40 Do the troubleshooting on the aircraft fuel -No system (Ref. AMM).
| Yes
41 Replace the FPMU (Ref. TASK 73-21-10-000-801/73-21-10-400-801, MM).
Observed Fault: No Lightoff/Delayed Lightoff For engines with Piloted Fuel Nozzle Assemblies EFFECTIVITY:ALL
TASK 72−00−00−810−803−A01 Page 207/208 Jan 20/11
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Observed Fault: No Lightoff/Delayed Lightoff For engines with Non-Piloted Fuel Nozzle Assemblies DESCRIPTION: A no lightoff event occurs when an ITT does not increase within the abort start time limit. A delayed lightoff event occurs when an excessive amount of fog or smoke is produced during start.
POSSIBLE CAUSES: 1. ATS system fault 2. FPMU 3. PMA stator 4. Wiring harness 5. Igniter 6. Exciter 7. Worn combustion liner alignment pins
01 Supply electrical power to the aircraft. 18 Do the troubleshooting for the maintenance Access the maintenance messages from the messages displayed. central maintenance computer (CMC) (Ref. -Yes Introduction). Are there engine, fuel system, or PMA related messages displayed? | No 02 Try two (2) engine starts with the ignition switch in the AUTO position (Ref. AMM). One on FADEC A, and one on FADEC B. Monitor the N2 RPM and the fuel flow rate during each start. Did a no start, delayed lightoff occur?
19 Go to block 16. -No
| Yes 03 Was the N2 Speed at least 28% when fuel was first shown?
-No
20 Do the troubleshooting on the ATS system (valve, air supply, starter, controls) (Ref. AMM).
| Yes 04 Go to Block 05.
Observed Fault: No Lightoff/Delayed Lightoff For engines with Non-Piloted Fuel Nozzle Assemblies EFFECTIVITY:ALL
TASK 72−00−00−810−803−A02 Page 201 Oct 20/14
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05 After 10 seconds of fuel flow indication with no light-off, was the fuel flow rate at between 250 and 400 pph (113 and 181 kgph).
-No
21 Go to block 16.
| Yes 06 Does the problem occur on both FADEC A and FADEC B?
-Yes
22 Go to block 09.
| No R R R R R
07 Interchange harness connectors PMA A and PMA B on the PMA stator. Try an engine start -No on the FADEC system that had the problem. Does the problem repeat?
R R R
| Yes
R R R R R R R
08 Do a test for continuity/resistance (1 ohm max./harness), internal shorts, and shorts to ground (1000 ohms min.) on the FADEC A/B (W11/14) harness (Ref. FIG. 301/TASK 72-00-00-990-801 /FIG. 302/TASK 72-00-00-990-802). Is there a fault with the harness?
R R R
| No
R R R R R
09 Do a borescope inspection of the combustion liner outer wall mounting brackets (Ref. TASK 72-40-00-200-801, MM). Are the mounting brackets within the serviceable limits?
23 Replace the PMA stator (Ref. TASK 73-11-10-000-801/73-11-10-400-801, MM).
24 Replace the defective harness (Ref. TASK 76-00-00, MM). -Yes
-No
25 Remove the engine from service within 100 flight hours.
| Yes 10 Go to Block 11.
Observed Fault: No Lightoff/Delayed Lightoff For engines with Non-Piloted Fuel Nozzle Assemblies EFFECTIVITY:ALL
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R R R R R R
11 Remove the combustion liner alignment pins one at a time (Ref. TASK 72-45-12-000-801/72-45-12-400-801, MM). Examine the combustion liner alignment pins (Ref. TASK 72-45-12-200-801, MM). Are the alignment pins serviceable?
26 Replace unserviceable alignment pin(s) (Ref. TASK 72-45-12-400-801, MM). -No
| Yes 12 Replace the exciter on the FADEC system that has the problem (Ref. TASK 74-13-10-000-801/74-13-10-400-801, MM). Try -No an engine start on the FADEC system that had the problem. Does the problem repeat?
27 Remove the exciter from service.
| Yes 13 Replace the igniter on the FADEC system that has the problem (Ref. TASK 74-21-10-000-801/74-21-10-400-801, MM) . Try an engine start on the FADEC system that had the problem. Does the problem repeat?
28 Remove the ignitor from service. -No
| Yes 14 Replace the igniter lead on the FADEC system that has the problem (Ref. TASK 74-21-15-000-801/74-21-15-400-801 or -No 74-21-20-000-801/74-21-20-400-801, MM). Try an engine start on the FADEC system that had the problem. Does the problem repeat?
29 Remove the igniter lead from service.
| Yes 15 Go to Block 16.
Observed Fault: No Lightoff/Delayed Lightoff For engines with Non-Piloted Fuel Nozzle Assemblies EFFECTIVITY:ALL
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16 Was there a fuel flow indication during the start try?
30 Do the troubleshooting for the observed -No fault: No Lightoff/No Fuel Flow (Ref. TASK 72-00-00-810-824).
| Yes 17 Remove the filter bowl on the FPMU (Ref. TASK 73-21-10-000-802, MM). Is there fuel at the FPMU?
31 Do the troubleshooting on the aircraft fuel -No system (Ref. AMM).
| Yes |
32 Replace the FPMU (Ref. TASK 73-21-10-000-801/73-21-10-400-801, MM).
Observed Fault: No Lightoff/Delayed Lightoff For engines with Non-Piloted Fuel Nozzle Assemblies EFFECTIVITY:ALL
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Observed Fault: Thrust Oscillations / Fluctuations DESCRIPTION: A thrust oscillation/fluctuation is a multi-cycle event, occurring during steady-state operation, where parameters used by the FADEC for controlling engine thrust are continuously changing. N1 (fan speed), N2 (core speed) and thrust lever angle are the primary parameters used by the FADEC for scheduling engine thrust.
POSSIBLE CAUSES: 1. External engine-control harness (W11/14) 2. Fan speed (N1) sensor 3. N2 speed sensor 4. Fuel pump-and-metering unit (FPMU) 5. Thrust lever resolver/harness 6. FADEC
R
(1) Notify the Rolls-Royce field service representative of the power fluctuation as soon as possible.
R
(2) Do the following before you start to do the troubleshooting procedure:
R
(a) Record the messages from the EICAS display.
R R R
(b) If power to the FADECs has not been removed, get the FADEC discrete labels from Central Maintenance Computer (CMC) (Ref. Introduction) and record them (Ref. TABLE 1, Introduction).
R
(c) Record the maintenance messages from the Multi-function Display (MFD).
R
(d) Download the maintenance messages from the CMC (Ref. 45-45-00-970-802A, AMM).
R
(e) Download the Trend & Exceed messages from the CMC (Ref. 45-45-00-970-802A, AMM).
R
(f)
Download the Digital Flight Data Recorder (DFDR) data (Ref. 31-31-00-700-803A, AMM).
01 Supply electrical power to the aircraft. 06 Do the troubleshooting for the maintenance Access the maintenance messages from the message(s). -Yes central maintenance computer (CMC) (Ref. Introduction). Are there any engine messages? | No 02 Operate the engine with FADEC A in control, then with FADEC B in control. Do the thrust fluctuations occur when each FADEC is in control?
-Yes
07 Replace the FPMU (Ref. 73-21-10-000-801/73-21-10-400-801 MM).
| No 03 Go to block 04
Observed Fault: Thrust Oscillations / Fluctuations EFFECTIVITY:3007/ALL
TASK 72−00−00−810−804 Page 201 Jul 20/14
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04 Interchange the position of the FADECs 08 Replace the FADEC that has the fault (Ref. (Ref. 73-25-10-000-801/73-25-10-400-801 73-25-10-000-801/73-25-10-400-801 MM). -Yes MM). Do the thrust fluctuations now occur with the opposite channel in control? | No 05 Examine all of the harness connectors for 09 Correct the harness connector fault (Ref. the fan speed (N1) sensor, N2 speed sensor, 70-00-00-910-804 MM) (Ref. 20-50-00 WM). thrust lever resolver, FPMU, FADEC J2 and J4 -Yes receptacles, and the pylon firewall receptacles. Are they loose, damaged, or dirty? | No
10 Operate the engine, and access the FADEC analog label for the channel with the fault. Monitor N1, N2, and TLA. Determine which parameter changes first when a power fluctuation occurs. Do the troubleshooting for the sensor circuit with the first indication of a fluctuation.
Observed Fault: Thrust Oscillations / Fluctuations EFFECTIVITY:3007/ALL
TASK 72−00−00−810−804 Page 202 Jul 20/14
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EICAS Message: E1/E2 NO DISP (set by FADEC Discrete: FLTGP1 (bit 29) / (355 / SFLTS1) = 1) DESCRIPTION: This message occurs when the FADEC finds a non-dispatchable (ND) fault. This message will always be displayed by the CMC when fault conditions exists that set any non-dispatch (ND) maintenance message. Go to Chapter 05 of the maintenance manual for appropriate dispatch time limits for the message displayed (Ref. 05-14-00 MM).
POSSIBLE CAUSES:
R
R
1. Aircraft / FADEC interface fault 2. Engine / FADEC interface fault 3. FADEC / FADEC interface fault 4. FADEC internal fault 5. Incorrect FPMU installation (AE3007A1E and AE3007A2 engines)
01 Supply electrical power to the aircraft. 05 Do the troubleshooting for the maintenance Display the maintenance messages from the message(s) (Ref. Maintenance Message List). central maintenance computer (CMC) on the multifunction display (MFD) unit (Ref. -Yes Introduction). Are there any non-dispatch (ND) or ST-ENG1(2) CTL A(B) SYS maintenance messages displayed? | No 02 For AE3007A1E engines: Cycle power to 06 Verify that the correct FPMU for this engine FADECs and check central maintenance is installed. Change the FPMU if necessary -Yes computer (CMC) label 353 bit 26 (FPSNOK). Is (Ref. 73-21-10-000-801 / 73-21-10-400-801 FPSNOK=1? MM). | No 03 Go to block 04.
EICAS Message: E1/E2 NO DISP (set by FADEC Discrete: FLTGP1 (bit 29) / (355 / SFLTS1) = 1) EFFECTIVITY:ALL
TASK 72−00−00−810−805 Page 201 Oct 20/15
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04 If equipped with CMC version 11 or higher, then examine the FADEC fault word snapshot file N0000DDMMMYYI.dat (Ref. Introduction Section 4). Use the FADEC Discrete Label Bit Settings Data Sheet (Ref. Introduction Section 4) to troubleshoot for all identified bits that require maintenance action (Ref. FADEC Discrete List). -No If not equipped with CMC version 11 or higher, download the FADEC Fault Code Stores (FCS) (Ref. Introduction Section 5). Use the FADEC Discrete Label Bit Settings Data Sheet (Ref. Introduction Section 4) to troubleshoot for all identified bits that require maintenance action (Ref. FADEC Discrete List). If you are not able to view these bits, speak with Rolls-Royce.
07 Remove power from the aircraft and reset the FADEC circuit breakers. If the message occurs again, do not remove electrical power from the FADECs, and repeat the procedure.
EICAS Message: E1/E2 NO DISP (set by FADEC Discrete: FLTGP1 (bit 29) / (355 / SFLTS1) = 1) EFFECTIVITY:ALL
TASK 72−00−00−810−805 Page 202 Oct 20/15
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EICAS Message: E1/E2 SHORT DISP (set by FADEC Discrete: FLTGP2 (bit 22) / (355 / SFLTS1) = 1) DESCRIPTION: This message occurs when the FADEC finds a short-term (ST) dispatch fault. This message will always be displayed by the CMC when fault conditions exists that set any short-term (ST) dispatch maintenance message. Go to Chapter 05 of the maintenance manual for appropriate dispatch time limits for the message displayed (Ref. 05-14-00 MM).
POSSIBLE CAUSES: 1. Aircraft / FADEC interface fault 2. Engine / FADEC interface fault 3. FADEC / FADEC interface fault 4. FADEC internal fault
R R
01 Supply electrical power to the aircraft. Display the maintenance messages from the central maintenance computer (CMC) on the multi-function display (MFD) unit (Ref. Introduction). Are there any short-dispatch (ST) or LT-ENG1(2) TLA SYS maintenance messages displayed?
02 Do the troubleshooting for the maintenance message(s) (Ref. Maintenance Message List). -Yes
| No |
03 Remove power from the aircraft and reset the FADEC circuit breakers. If the message occurs again, do not remove electrical power from the FADECs, and repeat the procedure.
EICAS Message: E1/E2 SHORT DISP (set by FADEC Discrete: FLTGP2 (bit 22) / (355 / SFLTS1) = 1) EFFECTIVITY:3007/ALL
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Maintenance Message: ENG1/ENG2 LT FAULT (set by FADEC Discrete: FLTGP3 (bit 26) / (356 / SFLTS2) = 1) DESCRIPTION: This message occurs when the FADEC finds a long-term (LT) dispatch fault. This message will always be displayed by the CMC when fault conditions exists that set any long-term (LT) dispatch maintenance message. Go to Chapter 05 of the maintenance manual for appropriate dispatch time limits for the message displayed (Ref. 05-14-00 MM).
POSSIBLE CAUSES: 1. Aircraft / FADEC interface fault 2. Engine / FADEC interface fault 3. FADEC / FADEC interface fault 4. FADEC internal fault
01 Supply electrical power to the aircraft. Display the maintenance messages from the central maintenance computer (CMC) on the multi-function display (MFD) unit (Ref. Introduction). Are there any long term (LT) maintenance message displayed?
05 Do the troubleshooting for the maintenance message(s) (Ref. Maintenance Message List). -Yes
| No R R R R R R R R R R R R R R R
02 If the aircraft is equipped with CMC version 06 Do the troubleshooting for the FADEC 11 or higher, then examine the FADEC fault power interrupt detected fault (Ref. TASK word snapshot file N0000DDMMMYYI.dat (Ref. -Yes 73-25-00-810-856). Introduction Section 4) for SFLTS2 Bit 17 (POWINT) being set. | No 03 If the aircraft is not equipped with CMC 07 Do the troubleshooting for the FADEC version 11 or higher, then examine the FADEC power interrupt detected fault (Ref. TASK fault word snapshot file, download the FADEC 73-25-00-810-856). -Yes A and FADEC B fault code stores (FCS) data (Ref. Introduction Section 5), and determine if IFPOWINT is set to a value of between 192 and 255.
R R R
| No
R R R R
04 Remove power from the aircraft and reset the FADEC circuit breakers. If the message occurs again, do not remove electrical power from the FADECs, and do the procedure again. Maintenance Message: ENG1/ENG2 LT FAULT (set by FADEC Discrete: FLTGP3 (bit 26) / (356 / SFLTS2) = 1) EFFECTIVITY:3007/ALL
TASK 72−00−00−810−807 Page 201 Oct 20/14
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Maintenance Message: ENG1/ENG2 LT FAULT (set by FADEC Discrete: FLTGP3 (bit 26) / (356 / SFLTS2) = 1) EFFECTIVITY:3007/ALL
TASK 72−00−00−810−807 Page 202 Oct 20/14
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Maintenance Message: ENG1 / ENG2 SCHED MAINT REPAIR DESCRIPTION: This message occurs when the FADEC finds a no loss of thrust control (NLOTC) fault.
POSSIBLE CAUSES: 1. Aircraft/FADEC interface fault 2. Engine/FADEC interface fault 3. FADEC/FADEC interface fault 4. FADEC internal fault
01 Supply electrical power to the aircraft. Access FADEC discrete label 264 for both FADECs. Does STRTDF (bit 11) = 1?
29 Do the troubleshooting for FADEC discrete -Yes STRTDF (bit 11) (Ref. 80-10-00-810-803).
| No 02 Does TOTIDF (bit 22) = 1?
-Yes
30 Do the troubleshooting for FADEC discrete TOTIDF (bit 22) (Ref. 73-25-00-810-813).
-Yes
31 Do the troubleshooting for FADEC discrete TOTDDF (bit 23) (Ref. 73-25-00-810-814).
-Yes
32 Do the troubleshooting for FADEC discrete TOTSDF (bit 24) (Ref. 73-25-00-810-816).
-Yes
33 Do the troubleshooting for FADEC discrete FDRDIF (bit 29) (Ref. 73-25-00-810-810).
| No 03 Does TOTDDF (bit 23) = 1? | No 04 Does TOTSDF (bit 24) = 1? | No 05 Does FDRDIF (bit 29) = 1? | No 06 Go to block 07.
Maintenance Message: ENG1 / ENG2 SCHED MAINT REPAIR R EFFECTIVITY:FADEC SOFTWARE VER. B4.3 OR R LATER
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07 Access FADEC discrete label 265 from the 34 Do the troubleshooting for FADEC discrete CMC for both FADECs. Does ALTDIF (bit 11) = -Yes ALTDIF (bit 11) (Ref. 73-25-00-810-809). 1? | No 08 Access FADEC discrete label 351 from the CMC for both FADECs. Does STRTFT (bit 11) = 1?
35 Do the troubleshooting for FADEC discrete -Yes STRTFT (bit 11) (Ref. 80-10-00-810-802).
| No 09 Does IGONFT (bit 13) = 1?
-Yes
36 Do the troubleshooting for FADEC discrete IGONFT (bit 13) (Ref. 74-30-00-810-802).
-Yes
37 Do the troubleshooting for FADEC discrete MTOSFT (bit 16) (Ref. 73-25-00-810-837).
-Yes
38 Do the troubleshooting for FADEC discrete LGDLFT (bit 20) (Ref. 73-25-00-810-805).
-Yes
39 Do the troubleshooting for FADEC discrete AISIFT (bit 21) (Ref. 73-25-00-810-802).
-Yes
40 Do the troubleshooting for FADEC discrete TOTIFT (bit 22) (Ref. 73-25-00-810-811).
| No 10 Does MTOSFT (bit 16) = 1? | No 11 Does LGDLFT (bit 20) = 1? | No 12 Does AISIFT (bit 21) = 1? | No 13 Does TOTIFT (bit 22) = 1? | No 14 Go to block 15.
Maintenance Message: ENG1 / ENG2 SCHED MAINT REPAIR R EFFECTIVITY:FADEC SOFTWARE VER. B4.3 OR R LATER
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15 Does TOTDFT (bit 23) = 1?
-Yes
41 Do the troubleshooting for FADEC discrete TOTDFT (bit 23) (Ref. 73-25-00-810-812).
-Yes
42 Do the troubleshooting for FADEC discrete TOTSFT (bit 24) (Ref. 73-25-00-810-815).
-Yes
43 Do the troubleshooting for FADEC discrete CLBFT (bit 26) (Ref. 73-25-00-810-838).
-Yes
44 Do the troubleshooting for FADEC discrete CRZFT (bit 27) (Ref. 73-25-00-810-839).
-Yes
45 Do the troubleshooting for FADEC discrete MXCFT (bit 28) (Ref. 73-25-00-810-840).
-Yes
46 Do the troubleshooting for FADEC discrete FDRFT (bit 29) (Ref. 73-25-00-810-808).
| No 16 Does TOTSFT (bit 24) = 1? | No 17 Does CLBFT (bit 26) = 1? | No 18 Does CRZFT (bit 27) = 1? | No 19 Does MXCFT (bit 28) = 1? | No 20 Does FDRFT (bit 29) = 1? | No 21 Access FADEC discrete label 352 from the CMC for both FADECs. Does ALTFSF (bit 11) = 1?
47 Do the troubleshooting for FADEC discrete -Yes ALTFSF (bit 11) (Ref. 73-25-00-810-807).
| No 22 Go to block 23.
Maintenance Message: ENG1 / ENG2 SCHED MAINT REPAIR R EFFECTIVITY:FADEC SOFTWARE VER. B4.3 OR R LATER
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23 Does ACSNOK (bit 21) = 1?
48 Do the troubleshooting for FADEC discrete -Yes ACSNOK (bit 21) (Ref. 73-10-00-810-806-B01).
| No 24 Access FADEC discrete label 353 from the CMC for both FADECs. Does STSFLT (bit 25) = 1?
49 Do the troubleshooting for FADEC discrete -Yes STSFLT (bit 25) (Ref. 73-21-00-810-806).
| No 25 Does FPSNOK (bit 26) = 1?
-Yes
50 Do the troubleshooting for FADEC discrete FPSNOK (bit 26) (Ref. 73-21-00-810-807-B01).
| No 26 Access FADEC discrete label 354 from the CMC for both FADECs. Does IDFLT (bit 13) = 1?
51 Do the troubleshooting for FADEC discrete -Yes IDFLT (bit 13) (Ref. 73-25-00-810-850).
| No 27 Operate the engine and shutdown. Do not remove electrical power from the FADECs. Access FADEC discrete label 353 from the CMC. Does STSFLT (bit 25) = 1?
-Yes
52 Do the troubleshooting for FADEC discrete STSFLT (bit 25) (Ref. 73-21-00-810-806).
| No 28 Does FPSNOK (bit 26) = 1?
53 Do the troubleshooting for FADEC discrete -Yes FPSNOK (bit 26) (Ref. 73-21-00-810-807-B01).
| No |
54 If the message occurs again, during future flights, do not remove electrical power from the FADECs, and repeat the procedure.
Maintenance Message: ENG1 / ENG2 SCHED MAINT REPAIR R EFFECTIVITY:FADEC SOFTWARE VER. B4.3 OR R LATER
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EICAS Message: ENG1/ENG2 OUT DESCRIPTION: R R
This message occurs when the FADEC finds an engine shutdown has occured, and the STOP/RUN/START switch is not in the STOP position, or, the FADEC has not received the engine master switch Start/Stop input correctly and reports the engine shutdown while the engine is running.
POSSIBLE CAUSES:
R
R R R
1. Engine system/component 2. Aircraft fuel system fault 3. Throttle quadrant fault 4. Engine mechanical failure 5. STOP/RUN/START switch fault 6. FADEC
01 Was the engine running when the ENG1/ENG2 OUT message was displayed?
R R R
-Yes
08 Go to block 07.
| No 02 Supply electrical power to the aircraft. Display the maintenance messages from the central maintenance computer (CMC) on the multifunction display (MFD) unit for both FADECs on this engine (Ref. Introduction). Are there any messages shown?
09 Do the troubleshooting for the maintenance message(s) (Ref. Maintenance Message List). -Yes
| No 03 Manually turn the N1 and N2 rotors. Do the 10 Remove the engine (Ref. AMM). -No rotors turn freely? | Yes 04 Try to start the engine (Ref. AMM). Does the engine start?
11 Do the troubleshooting for the observed -No fault, Engine Does Not Start (No Lightoff) (Ref. 72-00-00-810-803).
| Yes 05 Go to block 06.
EICAS Message: ENG1/ENG2 OUT EFFECTIVITY:3007/ALL
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06 Did the engine shutdown occur when the throttle lever was put in the IDLE detent?
-Yes
12 Do the throttle quadrant adjustment / test (Ref. AMM).
| No |
13 Do the troubleshooting on the aircraft fuel system and the STOP/RUN/START switch (Ref. AMM). Repair any faults found.
EICAS Message: ENG1/ENG2 OUT EFFECTIVITY:3007/ALL
TASK 72−00−00−810−809 Page 202 Jun 15/05
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R R R R R R R
07 Cycle electrical power to the FADECS. Display the maintenance messages from the Central Maintenance Computer (CMC) on the MFD. Are new engine related messages displayed or did the number of previous messages increase?
R R R
| No |
R
14 Do the troubleshooting for the maintenance message(s) (Ref. Maintenance Message List). -Yes
15 Return the engine to service.
EICAS Message: ENG1/ENG2 OUT EFFECTIVITY:3007/ALL
TASK 72−00−00−810−809 Page 203/204 Jun 15/05
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Observed Fault: Engine Shutdown After FADEC ALTN Selected DESCRIPTION: R R
This fault occurs when the stand-by FADEC has not received the engine master switch Start/Stop input correctly and entered the overspeed test mode during the last engine start. The fault does not affect the controlling FADEC, but if the stand-by FADEC is selected, the engine will shutdown. The AFTER START procedure to select ALTN FADEC detects this nuisance fault.
POSSIBLE CAUSES: R
R R R R R
1. FADEC
01 Keep electrical power to the aircraft. Display and record all themaintenance messages from the central maintenance computer (CMC) on the multifunction display (MFD) unit (Ref. Introduction). Is LT-ENG1/ENG2 N2 SYS message displayed?
-Yes
02 Do the troubleshooting for the maintenance message LT-ENG1/ENG2 N2 SYS (Ref. TASK 77-11-00-810-824).
| No R
03 Return the engine to service.
Observed Fault: Engine Shutdown After FADEC ALTN Selected EFFECTIVITY:ALL
TASK 72−00−00−810−811 Page 201/202 Jun 15/05
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Observed Fault: Smoke from Engine Exhaust at Shutdown DESCRIPTION: This condition is observed at engine shutdown. When oil that has leaked from the aft sump into the LPT, it is burned off as smoke.
POSSIBLE CAUSES: 1. O-ring on the shaft plug in the LPT rear shaft 2. Excessive oil leak from the No. 7 carbon seal
R R R
01 Was an exhaust fire reported and verified during this smoke-on-shutdown event?
R R R R R R R R
02 Inspect the LPT3 blades and RTBS for oil pooling. Is there oil pooling?
09 Remove the engine (72-00-00-000-801, MM) and replace the No. 7 carbon seal -Yes (72-59-21-300-802, MM) before the next revenue flight.
| No 03 Has the engine previously smoked on shutdown within the last 200 flight hours?
R R R R R R
08 Remove the engine (72-00-00-000-801, MM).
| No
R R R R R R
-Yes
-Yes
10 Go to Block 05.
| No 04 Inspect the LPT3 blades for oil. Are the blades wet?
R R R
-No
11 Return the engine to service. No action necessary.
| Yes
R R R R R
12 Replace the LPT shaft plug O-ring (72-59-15-000-801/72-59-400-801, MM) before the next revenue flight. One repositioning ferry flight is permitted.
Observed Fault: Smoke from Engine Exhaust at Shutdown EFFECTIVITY:ALL
TASK 72−00−00−810−812 Page 201 Oct 20/15
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R R R
05 Inspect the LPT3 blades for oil. Are the blades wet?
R R R R R R R R
-Yes
13 Go to Block 07.
| No 06 Was the LPT shaft plug O-ring replaced in the last 200 flight hours?
R R R
14 Replace the LPT shaft plug O-ring -No (72-59-15-000-801/72-59-15-400-801, MM) within 50 flight hours
| Yes
R R R R R
15 Remove the engine (72-00-00-000-801, MM) and replace the No. 7 carbon seal (72-59-21-300-802, MM) within 100 flight hours.
Observed Fault: Smoke from Engine Exhaust at Shutdown EFFECTIVITY:ALL
TASK 72−00−00−810−812 Page 202 Oct 20/15
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R R R R R
07 Was the LPT shaft plug O-ring replaced in the last 200 flight hours?
R R R
-No
16 Replace the LPT shaft plug O-ring (72-59-15-000-801/72-59-15-400-801, MM) before the next revenue flight. One repositioning ferry flight is permitted.
| Yes
R R R R R
17 Remove the engine (72-00-00-000-801, MM) and replace the No. 7 carbon seal (72-59-21-300-802, MM) before the next revenue flight. One repositioning ferry flight is permitted.
Observed Fault: Smoke from Engine Exhaust at Shutdown EFFECTIVITY:ALL
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Observed Fault: FADEC Circuit Breaker Does Not Reset DESCRIPTION: This fault occurs when the aircraft/FADEC electrical system requires more than five (5) amps (nominal).
POSSIBLE CAUSES: 1. Aircraft 28 VDC power fault 2. FADEC
CAUTION: DO NOT INSTALL A REPLACEMENT FADEC IN THE POSITION OF THE AFFECTED FADEC UNTIL THE PAM STATOR AND THE W11/14 AND W7 HARNESSES HAVE BEEN TESTED. DAMAGE TO THE FADEC COULD RESULT.
R R R
01 Disconnect the FADEC harness (W11/14) from the PMA stator housing and the W7 harness from the J4 receptacle of the FADEC. Use an ohmmeter to do a test for continuity between the harness PMA stator (pins C, D, E, G, H, and J) and the connector backshells of the W11/14 harness (Ref. FIG. 302/TASK 72-00-00-990-802 /FIG. 304/TASK 72-00-00-990-804). Is there infinite resistance?
08 Replace the harness that does not test satisfactorily (Ref. 76-00-00 MM) (Ref. AMM) (Ref. 73-21-50/73-21-51 EMB WM) and the associated FADEC (Ref. -No 73-25-10-000-801/73-25-10-400-801 MM).
| Yes
R R
02 Use the ohmmeter to do a test for continuity between the PMA stator windings (pins C, D, E, G, H, and J) and the stator housing (Ref. FIG. 304/TASK 72-00-00-990-804). Is there infinite resistance?
09 Replace the PMA stator (Ref. 74-11-15-000-801/74-11-15-400-801 MM) and the associated FADEC (Ref. -No 73-25-10-000-801/73-25-10-400-801 MM).
| Yes 03 Go to block 04.
Observed Fault: FADEC Circuit Breaker Does Not Reset EFFECTIVITY:ALL
TASK 72−00−00−810−813 Page 201 Aug 15/04
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04 Disconnect the W11/14 harness from the PMA. Disconnect the W7 harness from the engine pylon. Use a mega-ohmmeter to do a test of pins C, D, E, G, H, and J on the W11/14 harness for shorts to the connector backshell. Apply 500 VDC (max. 1 second). Is the resistance at least 5 megaohms?
10 Replace the harness that does not test satisfactorily (Ref. 76-00-00 MM) (Ref. AMM) and the associated FADEC (Ref. -No 73-25-10-000-801/73-25-10-400-801 MM).
| Yes 05 Disconnect the W7 harness from the W11/14 harness at the engine pylon and at the J4 receptacle of the FADEC. Use a mega-ohmmeter to do a test of pins N, P, R, S, T, and U on the W7 harness for shorts to the connector backshell (Ref. 73-21-50/73-21-51 EMB WM). Does the harness test satisfactorily?
11 Replace the W7 harness (Ref. AMM) and the associated FADEC (Ref. 73-25-10-000-801/73-25-10-400-801 MM). -No
| Yes R R R
06 Disconnect the W2/W3 harness connector (FADEC J5 receptacle) (Ref. FIG. 302/TASK 72-00-00-990-802/FIG. 304/TASK 72-00-00-990-804). Supply 28 VDC electrical power to the aircraft bus. Make sure the FADEC circuit breaker is closed. Measure the voltage at the W2/W3 harness connector between pins A and C and between pins B and D. Is the voltage measured more than 16 VDC?
12 Do the troubleshooting on the aircraft electrical system (Ref. AMM).
-No
| Yes 07 Examine the harness connector to the FADEC J5 receptacle for correct attachment, corrosion, or contamination. Is the connector loose or contaminated?
-No
13 Replace the FADEC (Ref. 73-25-10-000-801/73-25-10-400-801 MM).
| Yes |
14 Clean, repair, or replace the harness / connector (Ref. AMM).
Observed Fault: FADEC Circuit Breaker Does Not Reset EFFECTIVITY:ALL
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Observed Fault: Oil or Fuel Smell/Haze in the Cabin DESCRIPTION: This condition is possible when engine oil or fuel is smelled in the cabin or when a haze is seen in the cabin. Engine related oil smell is caused by excessive oil leakage from either the No. 0 carbon seal, the front sump, or the fan frame to front sump oil port O-rings. Engine related fuel smell is caused by fuel nozzles contaminated with hard carbon deposits on the primary and secondary fuel discharge ports and air paths. NOTE: This does not usually occur with non-piloted (pure-air blast) fuel nozzles.
POSSIBLE CAUSES: 1. Airframe related component 2. APU oil leakage into the environmental control system 3. Front sump 4. Fan frame-to-front sump oil port O-rings 5. No. 0 fan carbon seal/seal runner 6. Fan spanner lock-nut plug 7. Fuel nozzles (not a frequent cause for smell, but usually from piloted nozzles)
CAUTION: MAKE SURE THAT YOU DO NOT MIX PILOTED FUEL NOZZLES WITH NON-PILOTED FUEL NOZZLES. DAMAGE TO THE ENGINE CAN OCCUR.
01 Do the fault isolation procedures in the Embraer FIM (Ref. 21-20-00-810-801-A, EMB FIM) to isolate the source of the smell. | 02 Has the engine been washed or the aircraft de-iced recently?
-No
18 Go to block 06.
| Yes 03 Go to block 04.
Observed Fault: Oil or Fuel Smell/Haze in the Cabin EFFECTIVITY:ALL
TASK 72−00−00−810−814 Page 201 Oct 20/09
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04 Do the following to purge the system of residual deicing or engine wash fluid: 1. Start the engines (Ref. AMM). 2. Turn the APU off. 3. Make sure both ECU packs are on with HIGH TEMPERATURE selected (Ref. AMM). 4. Make sure the engine bleed valve is closed for the other engine (Ref. AMM). 5. Run the engine at ground idle for two minutes and 30 seconds (Ref. AMM). 6. Advance the throttle lever to 75° TLA for another two minutes and 30 seconds (Ref. AMM). After the purge is completed, with TLA at 75°, is the fault corrected?
19 Go to block 06.
-No
| Yes 05 Go to block 14.
Observed Fault: Oil or Fuel Smell/Haze in the Cabin EFFECTIVITY:ALL
TASK 72−00−00−810−814 Page 202 Oct 20/09
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R R
06 Do an engine run using the checklist in 20 Do the fault isolation procedures in the FIG. 306/TASK 72-00-00-990-806. A gas Embraer FIM (Ref. 21-20-00-810-803-A, EMB analyzer can be used during engine run. Was -No FIM). the smell produced during steps 3 or 4 and 5 or 6, or during steps 7 or 8 and 9 or 10? | Yes
R R
07 Was a gas analyzer used and engine oil ratings found?
R R R
-Yes
21 Contact Rolls-Royce.
| No 08 If the smell occurred in steps 3, 4, 5 or 6 22 Go to block 17. troubleshoot the left-hand engine. If the smell occurred in steps 7, 8, 9 or 10 troubleshoot the -Yes right-hand engine. Is the smell only at idle or with anti-ice on? | No 09 Is there an indication of leakage from the fan seal or oil puddling at the fan blade tips or dripping off the back of the fan wheel (Ref. 72-00-00-200-802, MM)?
23 Go to block 13. -Yes
| No 10 Use a borescope to examine the 24 Replace the engine (Ref. AMM). compressor inlet, on the engine you think is the possible cause of the fault, for an indication of -Yes oil from the centerline or oil that collects at the six o'clock position of the inlet (behind the IGVs). Is there an indication of oil collecting? | No R
11 Go to block 12.
Observed Fault: Oil or Fuel Smell/Haze in the Cabin EFFECTIVITY:ALL
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12 Remove the fan spinner (Ref. 74-21-10-000-801, MM). Is the fan spanner lock-nut plug diaphram (Ref. FIG. 305/TASK 72-00-00-990-805) damaged or missing?
-Yes
25 Replace the fan spanner lock-nut plug (Ref. 72-21-05-000-801/72-21-05-400-801, MM).
| No
26 Replace the engine (Ref. AMM).
Observed Fault: Oil or Fuel Smell/Haze in the Cabin EFFECTIVITY:ALL
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13 Replace the No. 0 carbon seal (Ref. 75-25-25-000-801/72-25-25-400-801, MM). Do the following to purge the system of remaining oil or fuel smell: 1. Start the engines (Ref. AMM). 2. Turn the APU off. 3. Make sure both ECU packs are on with HIGH TEMPERATURE selected (Ref. AMM). 4. Make sure the engine -Yes bleed valve is closed for the other engine (Ref. AMM). 5. Run the engine at ground idle for two minutes and 30 seconds (Ref. AMM). 6. Advance the throttle lever to 75° TLA for another two minutes and 30 seconds (Ref. AMM). After the purge is completed, with TLA at 75°, is the fault corrected?
27 Decrease the power to ground idle to allow the engine temperatures to decrease and then stop the engine (Ref. AMM). Return the engine to service.
| No |
28 Replace the engine (Ref. AMM).
Observed Fault: Oil or Fuel Smell/Haze in the Cabin EFFECTIVITY:ALL
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14 With TLA at 75°, turn A/I on for the maximum amount of time permitted (Ref. 30-00-00-710-002-A, AMM). Is the fault corrected?
29 Decrease the power to ground idle and allow engine temperatures to decrease. Stop the engines (Ref. AMM). Go to the Embraer -No FIM to troubleshoot for airframe related components that cause an oil or fuel smell in the cabin.
| Yes 15 Open the engine bleed valve for the other engine and close the engine bleed valve for this engine (Ref. AMM). With TLA at 75°, is the fault corrected?
30 Decrease the power to ground idle to allow the engine temperatures to decrease and then -No stop the engines (Ref. AMM). Go to block 02 to troubleshoot the other engine.
| Yes 16 With TLA at 75°, turn A/I on for the maximum amount of time permitted (Ref. 30-00-00-710-002-A, AMM). Is the fault corrected?
31 Decrease the power to ground idle to allow the engine temperatures to decrease and then -No stop the engines (Ref. AMM). Go to block 02 to troubleshoot the other engine.
| Yes |
32 Decrease the power to ground idle to allow the engine temperatures to decrease and then stop the engines (Ref. AMM). Return the engine to service.
Observed Fault: Oil or Fuel Smell/Haze in the Cabin EFFECTIVITY:ALL
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17 Replace all 16 fuel nozzles (Ref. AE 33 Go to block 14. 3007A-SL-053) (Ref. 73-11-00-000-801/73-11-00-400-801, MM). (If 16 fuel nozzles are not avaliable, replace the No. 3, 4, 5, 6, 13, and 14 nozzles at a minimum). Do the steps that follow to purge the system of the fuel smell that remains: 1. Start the engine (Ref. AMM). 2. Turn the APU off. Make sure both ECU packs are on with HIGH -Yes TEMPERATURE selected (Ref. AMM). 4. Make sure the engine bleed valve is closed for the other engine (Ref. AMM). 5. Run the engine at ground idle for two minutes and 30 seconds (Ref. AMM). 6. Move the throttle levers to 75° TLA again for two minutes and 30 seconds (Ref. AMM). After the purge is completed, with TLA at 75°, is the fault corrected? | No |
34 Replace the engine (Ref. AMM).
Observed Fault: Oil or Fuel Smell/Haze in the Cabin EFFECTIVITY:ALL
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Observed Fault: Engine Shutdown DESCRIPTION: This condition occurs when the engine control system commands a shutdown or the crew makes a decision to shut the engine down.
POSSIBLE CAUSES: 1. This task will isolate the possible cause of the engine shutdown.
R
CAUTION: DO NOT ATTEMPT ENGINE START WHILE TROUBLESHOOTING ON THE GROUND UNLESS THIS TASK TELLS YOU TO DO SO. DAMAGE TO THE ENGINE CAN OCCUR. NOTE: Notify the Rolls-Royce field service representative of the engine shutdown as soon as possible.
01 Do the following before you begin troubleshooting: 1. Record the EICAS messages displayed in the cockpit. 2. If power to the FADECs has not been removed, access the FADEC discrete labels from the CMC (Ref. Introduction) and record them (Ref. Table 1, Introduction). 3. Record the maintenance messages from the MFD and download the maintenance messages from the CMC (Ref. Introduction). 4. Download the Trend & Exceed messages from the CMC (Ref. 45-45-00-970-802A AMM). 5. Download the Flight Data Recorder data (Ref. 31-31-00-700-803A AMM). | 02 Was the engine shutdown crew commanded?
-Yes
25 Go to block 04.
| No 03 Go to block 18.
Observed Fault: Engine Shutdown EFFECTIVITY:3007/ALL
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04 Was the engine shutdown because of an inflight thrust reverser deployment?
-Yes
26 Go to Embraer FIM.
| No 05 Was the engine shutdown because of an air bleed leak?
-Yes
27 Go to Embraer FIM.
| No 06 Was the engine shutdown because there was a fire indication?
-Yes
28 Go to Embraer FIM.
| No 07 Was the engine shutdown because of low oil pressure?
-Yes
29 Go to Task 79-37-00-810-804.
| No 08 Was the engine shutdown because of high oil temperature?
-Yes
30 Go to Task 79-37-00-810-806.
| No 09 Was the engine shutdown because of low oil quantity?
-Yes
31 Go to Task 79-37-00-810-807.
| No 10 Was the engine shutdown because of high vibration to the LP rotor?
-Yes
32 Go to Task 77-41-00-810-801.
| No 11 Go to block 12.
Observed Fault: Engine Shutdown EFFECTIVITY:3007/ALL
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12 Was the engine shutdown because of high vibration to the HP rotor?
-Yes
33 Go to Task 77-41-00-810-802.
| No 13 Was the engine shutdown because of unstable/unresponsive engine operation?
-Yes
34 Go to Task 72-00-00-810-804.
| No 14 Was the engine shutdown because of high ITT?
-Yes
35 Go to Task 77-21-00-810-807.
| No 15 Was the engine shutdown because of an N1 overspeed?
-Yes
36 Go to Task 77-11-00-810-809.
| No 16 Was the engine shutdown because of an N2 overspeed?
-Yes
37 Go to Task 77-11-00-810-810.
| No 17 Go to block 18.
Observed Fault: Engine Shutdown EFFECTIVITY:3007/ALL
TASK 72−00−00−810−815 Page 203 Jul 20/10
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18 Do the General Visual Inspection of the Engine (Ref. 72-00-00-200-801 MM). Is a fault found?
-Yes
38 Correct the fault.
| No 19 Is there evidence of internal engine damage or evidence that the engine suddenly stopped?
39 Do the inspection of the Engine after a -Yes sudden stop (Ref. 05-50-00-200-807 MM).
| No 20 Were there Trend & Exceed messages?
-Yes 40 Do the troubleshooting for the message(s).
| No 21 Were there maintenance messages displayed on the MFD or downloaded from the CMC? R
-Yes
41 Do the troubleshooting for the message(s).
| No 22 Were there EICAS messages displayed?
-Yes 42 Do the troubleshooting for the message(s).
| No 23 Do the engine start test (Ref. 72-00-00-700-801 MM). Is there a fault?
-Yes
43 Correct the fault.
| No 24 Do the operational test of the engine at maximum takeoff power (Ref. 72-00-00-700-801 MM). Is there a fault?
-Yes
44 Correct the fault.
| No |
45 Return the engine to service.
Observed Fault: Engine Shutdown EFFECTIVITY:3007/ALL
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Observed Fault: Engine Does Not Make Necessary Thrust DESCRIPTION: This condition is possible when the engine is not producing sufficient thrust
POSSIBLE CAUSES: 1. Engine 2. Control System
01 Do the following before you begin troubleshooting: 1. Record the EICAS messages displayed in the cockpit. 2. If power to the FADECs has not been removed, access the FADEC discrete labels from the CMC (Ref. Introduction) and record them (Ref. Table 1, Introduction). 3. Record the maintenance messages from the MFD and download the maintenance messages from the CMC (Ref. Introduction). 4. Download the Trend & Exceed messages from the CMC (Ref. Introduction). | No 02 Were there EICAS messages displayed?
-Yes
08 Do the troubleshooting for the EICAS message(s).
| No 03 Were there maintenance messages displayed on the MFD or downloaded from the CMC?
-Yes
09 Do the troubleshooting for the maintenance message(s).
| No |
10 Go to block 4.
Observed Fault: Engine Does Not Make Necessary Thrust EFFECTIVITY:3007/ALL
TASK 72−00−00−810−816 Page 201 Feb 15/03
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04 Were there Trend & Exceed messages?
11 Do the troubleshooting for the Trend & -Yes Exceed message(s).
| No 05 Do the General Visual Inspection of the Engine (Ref. 72-00-00-200-801 MM). Is a fault found?
12 Correct the fault. -Yes
| No 06 Is there evidence of internal engine damage?
13 Do the borescope inspection of the compressor (Ref. 72-30-00-200-801 MM), combustion liner (Ref. 72-40-00-200-801 MM), -Yes and turbine (Ref. 72-50-00-200-801-001 MM) or (Ref. 72-50-00-200-801-002 MM).
| No 07 Do the performance run of the engine (Ref. 14 Correct the fault. 72-00-00-700-801 MM). Is there a fault? -Yes | No |
15 Return the engine to service.
Observed Fault: Engine Does Not Make Necessary Thrust EFFECTIVITY:3007/ALL
TASK 72−00−00−810−816 Page 202 Feb 15/03
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Observed Fault: Engine Surge/Stall DESCRIPTION: This fault is manifested by an audible “banging” noise during engine operation. ITT and N2 fluctuations are often associated with this fault. With this fault, one or more of the conditions that follow can subsequently occur: -
A flameout or an uncommanded shutdown
-
A flameout followed by an auto-relight and return to its prior operating condition; or,
-
A command shutdown
POSSIBLE CAUSES: 1. Foreign objects in the engine inlet 2. 9th stage air bleed check valve 3. CVG control system 4. CVG hardware
01 Inspect the engine for Foreign Object 10 Replace the engine (Ref. AMM) Damage (Ref. 05-50-00-200-804 MM). Is there -Yes any evidence of damage or wear beyond acceptable limits? | No 02 Is the 9th stage air bleed check valve 11 Replace the 9th stage bleed air check valve serviceable? (Ref. TASK 36-11-01/601, AMM)? -No (Ref. TASK 36-11-01/401, AMM). Go to block 06 to continue troubleshooting. | Yes R R
03 Access the maintenance messages form the central maintenance computer (CMC). Is the CMC message ENG1/ENG2 CVG SYS displayed?
12 Do the FIM procedure for message ENG1/ENG2 CVG FAIL (Ref. -Yes 75-33-00-810-802 and 75-33-00-810-803). Go to block 06 to continue troubleshooting.
| No 04 Visually inspect the CVG torque tube assembly. Is there evidence that the CVG actuator arm is damaged/cracked?
-Yes
13 Replace the engine (Ref. AMM).
| No 05 Go to block 06 Observed Fault: Engine Surge/Stall EFFECTIVITY:ALL
TASK 72−00−00−810−817 Page 201 Oct 20/14
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06 Access the maintenance messages from the CMC. Is the maintenance message ITT High/Low ITT Margin displayed?
14 Do the inspection for an ITT over -Yes temperature condition (Ref. 77-00-00-200-801 MM).
| No | 07 Do the borescope inspection of the 15 Replace the engine (Ref. AMM). compressor (Ref. 72-30-00-200-801 MM). Is -Yes there evidence of compressor damage or wear beyond serviceable limits? | No | 08 Do the borescope inspection of the turbine section (Ref. 72-50-00-200-801-001 MM) or (Ref. 72-50-00-200-801-001 MM). Is there evidence of turbine damage or wear beyond serviceable limits?
16 Replace the engine (Ref. AMM). -Yes
| No | 09 Do the performance run of the engine (Ref. 72-00-00-700-801 MM). Are there any faults found?
-Yes
17 Correct the faults.
| No |
18 Return the engine to service
Observed Fault: Engine Surge/Stall EFFECTIVITY:ALL
TASK 72−00−00−810−817 Page 202 Oct 20/14
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Observed Fault: Fuel Flow Greater than 800 pph (363 kgph) During Start DESCRIPTION: This fault can occur if a main metering valve feedback fault occurs, which results in the FADEC commanding the main metering valve fully open until lightoff is detected.
POSSIBLE CAUSES: 1. Wiring Harness Connections 2. Wiring Harness 3. Fuel Pump and Metering Unit (FPMU) 4. FADEC
CAUTION: FUEL FLOW MUST NOT BE MORE THAN 800 PPH (363 KGPH) DURING ENGINE START. ABORT THE START OPERATION IF FUEL FLOW IS MORE THAN 800 PPH (363 KGPH) OR DAMAGE TO THE ENGINE CAN OCCUR.
R R
01 Examine all of the harness connectors between the FPMU and the FADEC J4 receptacle for looseness, corrosion, contamination, or damage (Ref. FIG. 301/TASK 73-21-00-990-801) (Ref. 73-21-50/73-21-51 WM). Are defects present?
08 Clean, replace or tighten the defective harness connectors as necessary. Apply Stabilant 22 to harness connector pins (Ref. -Yes 70-00-00-910-804 MM). Go to block 07.
| No 02 Try an engine start (Ref. AMM). Was fuel flow more than 800 pph (363 kgph)?
-No
11 Go to block 07
| Yes 03 Replace both external harness (Ref. 76-11-00 MM). Attempt four more engine starts. Was fuel flow more than 800 pph (363 kgph)?
-No
12 Remove the harnesses from service and return to Rolls-Royce.
| Yes 04 Go to block 05
Observed Fault: Fuel Flow Greater than 800 pph (363 kgph) During Start EFFECTIVITY:ALL
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05 Replace the FPMU (Ref. 73-21-10-000-801/ 13 Remove the FPMU from service and return 73-21-10-400-801 MM). Attempt four more to B.F. Goodrich for investigation. -No engine starts. Was fuel flow more than 800 pph (363 kgph)? | Yes 06 Interchange the positions of the FADEC A to the other engine. Attempt four more engine starts. Did the fault follow FADEC A?
14 Replace FADEC A and return to B.F. -Yes Goodrich (Ref. 73-25-10-000-801/ 73-25-10-400-801 MM).
| No |
15 Replace FADEC B and return to B.F. Goodrich (Ref. 73-25-10-000-801/ 73-25-10-400-801 MM).
Observed Fault: Fuel Flow Greater than 800 pph (363 kgph) During Start EFFECTIVITY:ALL
TASK 72−00−00−810−818 Page 202 Jul 20/15
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07 Try four more engine starts. Was fuel flow more than 800 pph (363 kgph)?
-No
16 Monitor engine for future occurrences.
| Yes | 08 Replace both external harness (Ref. 76-11-00 MM). Attempt four more engine starts. Was fuel flow more than 800 pph (363 kgph)?
-No
17 Remove the harnesses from service and return to Rolls-Royce.
| Yes 09 Replace the FPMU (Ref. 73-21-10-000-801/ 18 Remove the FPMU from service and return 73-21-10-400-801 MM). Attempt four more to B.F. Goodrich for investigation. -No engine starts. Was fuel flow more than 800 pph (363 kgph)? | Yes 10 Interchange the positions of the FADEC A 19 Replace FADEC A and return to B.F. to the other engine. Did the fault follow FADEC -Yes Goodrich (Ref. 73-25-10-000-801/ A? 73-25-10-400-801 MM). | No |
20 Replace FADEC B and return to B.F. Goodrich (Ref. 73-25-10-000-801/ 73-25-10-400-801 MM).
Observed Fault: Fuel Flow Greater than 800 pph (363 kgph) During Start EFFECTIVITY:ALL
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High-pressure Turbine Deterioration Alert Observed Fault: ITT margin decreases gradually to 15°C (59°F)/1000 hours or more with a 1% or more change in fuel flow and a flat or increasing N2 margin. DESCRIPTION: This fault occurs when the ITT trend data shows ITT margin is decreasing gradually by 15°C (59°F)/1000 hours or more, with a related fuel flow increase of 1% or more and either a flat or increasing N2 margin.
POSSIBLE CAUSES: 1. 1st-stage high-pressure turbine vane burn through 2. Combustion liner distress 3. High-pressure compressor bleed leak
01 Read the engine logbook. Was maintenance done before the ITT margin change (for example, fuel nozzle change, thermocouple change, or compressor wash)?
04 Continue to monitor ITT trend through the subsequent trending period and fault isolate as -Yes necessary.
| No
R
02 Borescope the combustion liner (Ref. 72-40-00-200-801, MM) and the high-pressure turbine (Ref. 72-50-00-200-805, MM). Was the combustion liner and high-pressure turbine serviceable?
05 Remove the engine (Ref. 71-00-00-000-801, AMM) and install the -No replacement engine (Ref. 71-00-00-400-801, AMM). Make sure the engine logbook shows the cause for engine removal.
| Yes 03 Do the Bleed Leak Alert Task (Ref. 75-31-00-810-801).
High-pressure Turbine Deterioration Alert EFFECTIVITY:ALL
TASK 72−00−00−810−819 Page 201/202 Oct 20/07
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ITT Instrumentation Alert Observed Fault: ITT margin increases or decreases in steps of more than 15°C (59°F) with a 1% or less change in fuel flow and no large change in N2 margin. DESCRIPTION: This fault occurs when the ITT trending data shows ITT is increasing or decreasing in steps of more than 15°C (59°F) with a 1% or less change in fuel flow and no large change in N2 margin.
POSSIBLE CAUSES: 1. ITT Sensor circuit fault 2. Turbine interstage thermocouples 3. 1st-stage high-pressure turbine vane burn through 4. Combustion liner distress
01 Review maintenance records of the engine. 08 Continue to monitor ITT trend through the Was maintenance action done before the ITT subsequent trending period and fault isolate as margin change (for example, fuel nozzle -Yes necessary. change, thermocouple change, compressor wash)? | No R R R R R
02 Do the borescope inspection of the 09 Remove the engine (Ref. combustion liner (Ref. 72-40-00-200-801, MM). 71-00-00-000-801, AMM) and install the Is the combustion liner serviceable? -No replacement engine (Ref. 71-00-00-400-801, AMM). Make sure that the engine records show the cause for engine removal.
R R R
| Yes 03 Examine the thermocouple harnesses for signs of chafing, loose connections, damaged connector pins, etc. Were the thermocouple harnesses and related hardware serviceable?
-No
10 Replace the damaged or defective hardware as necessary and continue to monitor ITT trend through the subsequent trending period to make sure the fault was corrected.
| Yes R
04 Go to Block 05.
ITT Instrumentation Alert EFFECTIVITY:ALL
TASK 72−00−00−810−820 Page 201 Jul 20/13
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05 Remove all thermocouples (Ref. 77-21-10-000-801, MM). Examine each thermocouple (Ref. 77-21-10-200-801, MM). Were the thermocouples serviceable?
11 Replace the unserviceable thermocouples as necessary. Continue to monitor ITT trend -No through the subsequent trending period to make sure the fault was corrected.
| Yes R R R
06 Install the thermocouples (Ref. 77-21-10-400-801, MM). Borescope the high-pressure turbine (Ref. 72-50-00-200-805, MM). Was the high-pressure turbine serviceable?
12 Remove the engine (Ref. 71-00-00-000-801, AMM) and install the -No replacement engine (Ref. 71-00-00-400-801, AMM). Make sure that the engine records show the cause for engine removal.
| Yes 07 Continue to monitor ITT trend through the subsequent trending period and fault isolate as necessary.
ITT Instrumentation Alert EFFECTIVITY:ALL
TASK 72−00−00−810−820 Page 202 Jul 20/13
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Observed Fault: Noise during hand rotation of fan DESCRIPTION: R R
It is not unusual for brush seals and honeycomb seals in the Low Pressure Turbine area to make noise during fan rotation until the seal knives are cut-in. It can be 200 hours for the seals to cut-in after they are replaced. Thus, the noise that the fan makes when it is turned by hand is permitted if the fan is free to turn easily.
POSSIBLE CAUSES: 1. Brush Seals 2. Honeycomb Seals
01 Rotate the fan by hand. Does the fan rotate 02 Seal knives are cut-in. Put the engine back -Yes freely with no heavy drag? in service. | No 03 Has the engine come from an AMC and has 04 Seal knives are not cut-in. Put the engine -Yes less than 200 flight hours? back in service. | No
05 Replace the engine (Ref. 71-00-00-000-801/71-00-00-400-801 AMM).
Observed Fault: Noise during hand rotation of fan EFFECTIVITY:ALL
TASK 72−00−00−810−821 Page 201/202 Oct 20/10
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Observed Fault: Engine Noise on FADEC Lane Change DESCRIPTION: An audible “banging” noise during FADEC lane change at idle.
R R
01 Does noise occur during FADEC lane change at idle?
-No
06 Do the troubleshooting for Engine Surge/Stall (Ref. TASK 72-00-00-810-817).
-Yes
07 Do the troubleshooting for Engine Shutdown (Ref. TASK 72-00-00-810-815).
-Yes
08 Do the troubleshooting for ITT High/Low ITT Margin (Ref. TASK 77-21-00-810-807).
| Yes R R
02 Did the engine shutdown? | No
R R
03 Was the engine ITT more than the ITT limit? | No
R R R R R R
04 Does the “banging” noise occur on the FADEC lane change from A to B?
R R R R R R R R R
09 The “banging” noise is not harmful to the engine. The engine can be returned to service. The “banging” noise can be prevented. When -Yes possible, replace the FADEC B with a FADEC that has S/N BX55600 or higher or a modified FADEC.
| No 05 Does the “banging” noise occur on the FADEC lane change from B to A?
R R R
| No |
R
10 The “banging” noise is not harmful to the engine. The engine can be returned to service. The “banging” noise can be prevented. When -Yes possible, replace the FADEC A with a FADEC that has S/N BX55600 or higher or a modified FADEC.
11 Return the engine to service.
Observed Fault: Engine Noise on FADEC Lane Change EFFECTIVITY:ALL
TASK 72−00−00−810−822 Page 201/202 Feb 15/06
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EICAS Message: E1(2) Exceedance DESCRIPTION: This message is displayed when the aircraft is on the ground, based on an exceedance that occurs during the flight. This message indicates that the ITT (or N2) was more than the current ITT (or N2) limit during an interval of the flight.
POSSIBLE CAUSES: 1. High ITT 2. High N2
R R R
01 Does this engine have open EHM 09 Go to Block 04 and do the troubleshooting -Yes advisories that are related to ITT or N2 margin? recommended in the open EHM advisory.
R R R R R R
| No 02 Is the ITT margin for this engine stable and less than 46°C?
R R R
| Yes
R R R R R
03 Was there a Master Caution message during the flight or did the crew report high ITT, high N2, or abnormal engine operation during the flight?
-No
10 Go to Block 04.
11 Put the engine back in service if you cannot download CMC before subsequent flight. Go to -No Block 04 in two or less flight cycles.
| Yes 04 Supply electrical power to the aircraft. Access the engine exceedance data from the CMC (Ref. Introduction). Was an exceedance recorded?
12 Put the engine back in service. -No
| Yes R
05 Go to Block 06
EICAS Message: E1(2) Exceedance EFFECTIVITY:
TASK 72−00−00−810−823 Page 201 Jul 20/13
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06 Was the engine N2 more than the red line limit on the EICAS display (Ref. TASK 71-00-00-200-801)?
13 Do the troubleshooting for N2 overspeed -Yes (Ref. TASK 77-11-00-810-810), and then go to Block 03.
| No 07 Was the engine ITT more than the red line limit on the EICAS display (Ref. TASK 71-00-00-200-801)?
14 Do the troubleshooting procedure for ITT -Yes high (Ref. TASK 77-21-00-810-807).
| No 08 Was the peak ITT value larger than the ITT Limit for more than five seconds?
-Yes
15 Do the troubleshooting for ITT high (Ref. TASK 77-21-00-810-807).
| No | R R R R R
16 Put the engine back in service. In two or less days, look at the performance trends to see if the engine has N2 and ITT margin (Ref. TASK 05-13-00-800-801, MM).
EICAS Message: E1(2) Exceedance EFFECTIVITY:
TASK 72−00−00−810−823 Page 202 Jul 20/13
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Observed Fault: No Lightoff/Delayed Lightoff For engines with Piloted or Non-Piloted Fuel Nozzle Assemblies DESCRIPTION: A no lightoff event occurs when an ITT does not increase within the abort start time limit. Fuel fow is not detected during the engine start.
POSSIBLE CAUSES: 1. FADEC
01 Supply electrical power to the aircraft. 03 Do the troubleshooting for the maintenance Access the maintenance messages from the messages displayed. central maintenance computer (CMC) (Ref. -Yes Introduction). Are there engine, fuel system, or PMA related messages displayed? | No 02 Cycle electrical power to the FADECs. Try two (2) engine starts with the ignition switch in the AUTO position (Ref. AMM). One on FADEC A and one on FADEC B. Monitor the N2 RPM and the fuel flow rate during each start. Did a no start occur?
-Yes
04 Do the troubleshooting for the observed fault: No Lightoff/Delayed Lightoff (Ref. TASK 72-00-00-810-803).
| No
05 Return the engine to service.
Observed Fault: No Lightoff/Delayed Lightoff For engines with Piloted or Non-Piloted Fuel Nozzle Assemblies EFFECTIVITY:ALL
TASK 72−00−00−810−824 Page 201/202 Jun 15/05
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Observed Fault: Power Fluctuations DESCRIPTION: A power fluctuation is a single-cycle event, occurring during operation where parameters used by the FADEC for controlling engine thrust (N1 (fan speed), N2 (core speed), thrust, ITT, or fuel flow) change without being commanded to do so by the flight crew.
POSSIBLE CAUSES: 1. Fuel Pump-and-metering Unit (FPMU) 2. FADEC 3. W11 or W14 Harness 4. Outer Bypass Duct Access Panel 5. Bleed Air Leak 6. P2.5 Sensor 7. Air Data Computer (ADC) 8. Thrust Reverser Fault 9. Thrust Lever Angle (TLA) Fault
(1) Notify the Rolls-Royce field service representative of the power fluctuation as soon as possible. (2) Do the following before you start to do the troubleshooting procedure: (a) Record the messages from the EICAS display. (b) If power to the FADECs has not been removed, get the FADEC discrete labels from the Central Maintenance Computer (CMC) (Ref. Introduction) and record them (Ref. TABLE 1, Introduction). (c) Record the maintenance messages from the Multi-function Display (MFD). (d) Download the maintenance messages from the CMC (Ref. 45-45-00-970-802A, AMM). (e) Download the Trend & Exceed messages from the CMC (Ref. 45-45-00-970-802A, AMM). (f)
Download the Digital Flight Data Recorder (DFDR) data (Ref. 31-31-00-700-803A, AMM).
01 Supply electrical power to the aircraft. Access the maintenance messages from the CMC (Ref. Introduction). Are there engine messages?
-Yes
20 Do the troubleshooting for the maintenance message(s).
| No 02 Send the performance data to OSYS for analysis. Does the engine have drifted P2.5?
21 Remove and replace the the P2.5 sensor for the affected FADEC (Ref. -Yes 75-43-10-000-801/75-43-10-400-801, MM) and do SB AE 3007A-76-008.
| No 03 Go to Block 04. Observed Fault: Power Fluctuations EFFECTIVITY:ALL
TASK 72−00−00−810−825 Page 201 Jan 20/10
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04 Does the engine have sufficient N2 margin?
-No
22 Do the troubleshooting for a decrease in N2 margin (Ref. 72-00-00-810-826).
-No
23 Do the troubleshooting for a bleed air leak (Ref. 75-31-00-810-801).
| Yes 05 Does the engine have sufficient ITT margin? | Yes 06 Is there an Engine Health Monitoring (EHM) 24 Do the troubleshooting for the applicable alert open on this engine for Low N2 or ITT -Yes EHM alert. Margin? | No 07 Do the inspection of the outer bypass duct access panel (Ref. 72-73-25-200-801, MM). -No Are all of the access panels correctly installed?
25 Install the access cover for the outer bypass duct (Ref. 72-73-10-400-801, MM).
| Yes 08 Can you review DFDR and CMC data?
-No
26 Send the DFDR and CMC data to your Rolls-Royce representative for analysis as soon as possible.
| Yes 09 During the power fluctuation, does the MFD 27 Remove and replace the FPMU (Ref. show a message for the affected engine of -Yes 73-21-10-000-801/73-21-10-400-801). ENG1(2) CLIND (Control Loop) = 9 or 13? | No 10 Go to Block 11.
Observed Fault: Power Fluctuations EFFECTIVITY:ALL
TASK 72−00−00−810−825 Page 202 Jan 20/10
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11 During the power fluctuation at altitudes above FL300, does the MFD show a message for the affected engine of ENG1(2) CLIND (Control Loop) = 7 for more than 5 seconds when no acceleration is requested?
28 Remove and replace the the P2.5 sensor for the affected engine (Ref. -Yes 75-43-10-000-801/75-43-10-400-801, MM) and do SB AE 3007A-76-008.
| No 12 During the power fluctuation, does the MFD show a message for the affected engine of -No ENG1(2) CLIND (Control Loop) = 1?
29 Go to Block 13.
| Yes | 30 Go to Block 14.
13 Were the fuel boost pumps on?
-No
31 Do the troubleshooting of the aircraft fuel system to find if the fuel pumps are serviceable.
| Yes 14 Was the throttle changing during the power fluctuation?
-Yes
32 Do the troubleshooting of the TLA.
| No R
15 Did the N1 Target change by more than 10 percent during the power fluctuation?
-Yes
33 Go to Block 18
| No 16 Did the N1 Request change to flight idle during the power fluctuation?
-Yes
34 Do the troubleshooting of the thrust reverser (Ref. AMM).
| No 17 Return the engine to service.
Observed Fault: Power Fluctuations EFFECTIVITY:ALL
TASK 72−00−00−810−825 Page 203 Jan 20/10
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18 Did the power fluctuation occur on engine 1?
R R R
| No
R R R R
19 Replace FADEC 2B (Ref. 73-25-10-000-801/73-25-10-400-801, MM) and do the troubleshooting of the Air Data Computer (Ref. AMM).
-Yes 35 Replace FADEC 1A (Ref. 73-25-10-000-801/73-25-10-400-801, MM) and do the troubleshooting of the Air Data Computer (Ref. AMM).
Observed Fault: Power Fluctuations EFFECTIVITY:ALL
TASK 72−00−00−810−825 Page 204 Jan 20/10
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Observed Fault: Decrease in HP Speed Margin DESCRIPTION: There have been some AE 3007A aborted take-offs due to insufficient N2 margin as annunciated by ATTCS. The aborted take-offs usually occur in the summer months when the engine is operated near the break point. To help prevent more ATTCS aborted take-offs, it is necessary that an advisory notice be sent when smoothed worse case HP speed margin is less than 1.1% for A1E/A1P and 1.6% for all other AE 3007A engine variants.
POSSIBLE CAUSES: 1. Binding in external compressor variable geometry (CVG) system 2. Broken or damaged external CVG hardware 3. Bleed air leak 4. Compressor-inlet-temperature (T2.5) sensor
R
01 Examine the torquetube, CVG actuator mounting bracket and the actuation rings. Are the CVG components serviceable?
07 Lubricate the compressor CVG components -Yes (Ref. 72-30-00-600-803 MM).
| No 02 Repair or replace the component with the fault. Is the HP speed margin performance back to the usual condition?
-Yes
08 Put the engine back in service.
| No 03 Examine the compressor bleed system components for air leakage (Ref. 75-31-00-810-801). Is there air leakage?
09 Repair or replace the component with the -Yes fault.
| No 04 Go to block 05.
Observed Fault: Decrease in HP Speed Margin EFFECTIVITY:ALL
TASK 72−00−00−810−826 Page 201 Jan 20/16
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05 Do the procedure to wash the HP compressor (Ref. 72-00-00-100-801 MM). Do not clean the fan blades. Is HP speed margin performance back to the usual condition?
10 Put the engine back in service. -Yes
| No 06 Examine the compressor-inlet-temperature sensor (CIT) (Ref. 75-41-10-200-801 MM). Is the CIT sensor damaged? R | No
11 Remove the CIT sensor (Ref. 75-41-10-000-801 MM). Install the replacement CIT sensor (Ref. 75-41-10-400-801 MM). Is the -Yes HP speed margin performance back to the usual condition? If yes, put the engine back in service. If no, go to block 12. 12 Schedule the engine for removal within 50 flight hours (Ref. 71-00-00-000-801 AMM). Install the replacement engine (Ref. 71-00-00-400-801 AMM).
Observed Fault: Decrease in HP Speed Margin EFFECTIVITY:ALL
TASK 72−00−00−810−826 Page 202 Jan 20/16
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Combustion Liner Distress Alert Observed Fault: ITT margin increases gradually or sudden increases of 15°C (59°F) or more with a fuel flow increase of 2% or more with no change in N2 margin. DESCRIPTION: This fault occurs when the ITT trend data shows ITT margin has increased or decreased gradually by 15°C (59°F)/1000 hours or sudden increases of 15°C (59°F) or more, with a related fuel flow increase of 2% or more and no change in N2 margin.
POSSIBLE CAUSES: 1. Combustion liner distress 2. 1st-stage high-pressure turbine vane burn through 3. ITT sensor circuit fault 4. Turbine-interstage thermocouples
01 Read the engine logbook. Was maintenance done before the ITT margin change (for example, fuel nozzle change, thermocouple change, or compressor wash)?
04 Continue to monitor ITT trend through the subsequent trending period and fault isolate as -Yes necessary.
| No
R
02 Borescope the combustion liner (Ref. 72-40-00-200-801, MM) and the high-pressure turbine (Ref. 72-50-00-200-805, MM). Was the combustion liner and high-pressure turbine serviceable?
05 Remove the engine (Ref. 71-00-00-000-801, AMM) and install the -No replacement engine (Ref. 71-00-00-400-801, AMM). Make sure the engine logbook shows the cause for engine removal.
| Yes 03 Do the ITT Instrumentation Alert Task (Ref. 72-00-00-810-820).
Combustion Liner Distress Alert EFFECTIVITY:ALL
TASK 72−00−00−810−827 Page 201/202 Oct 20/07
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Observed Fault: Step change in fuel flow exceeding 3% For engines with Non-piloted Fuel Nozzle Assemblies DESCRIPTION: This fault occurs when the fuel flow during steady-state condition increases by 3% or more with no change in ITT or N2 margin.
POSSIBLE CAUSES: 1. Fuel line leak 2. Cracked or broken fuel nozzle gasket 3. Fuel flow sensor reading incorrectly 4. Cracked fuel nozzle
CAUTION: MAKE SURE THAT YOU DO NOT MIX PILOTED FUEL NOZZLES WITH NON-PILOTED FUEL NOZZLES. DAMAGE TO THE ENGINE CAN OCCUR.
R R
01 Is this engine POST-SB AE 3007A-78-004 or POST-SB AE 3007A-005?
-Yes 09 Go to Block 03.
| R
No
R R R
02 Are the heat shields installed?
R R R
10 Do not fly the aircraft until the cause of the -No fuel flow increase is found and corrected. Go to Block 03.
| Yes 03 Do the general visual inspection of the 11 Correct the fault. Go to Block 04. engine (Ref. 72-00-00-200-801, MM). Is a fault -Yes found? | No
R
04 Do the performance run of the engine (Ref. 72-00-00-700-801, MM). Is the fuel flow increase still shown?
-No
12 Go to Block 16.
| Yes 05 Go to Block 06
Observed Fault: Step change in fuel flow exceeding 3% For engines with Non-piloted Fuel Nozzle Assemblies EFFECTIVITY:ALL
TASK 72−00−00−810−828 Page 201 Jul 20/13
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R
06 Remove the fuel flow sensor (Ref. 73-35-10-000-801, MM). Install the replacement fuel flow sensor (Ref. 73-35-10-400-801, MM). Do the performance run of the engine (Ref. 72-00-00-700-801, MM). Is a fault found?
13 Correct the fault. Go to Block 07. -Yes
| No R
07 Is the fuel flow increase still shown?
-No
14 Go to Block 16.
| Yes 08 Remove all of the non-piloted fuel nozzles (Ref. 73-11-10-000-801, MM). Install the replacement non-piloted fuel nozzles (Ref. 73-11-10-400-801, MM). Do the performance run of the engine (Ref. 72-00-00-700-801, MM). Is a fault found?
15 Correct the fault. -Yes
| No |
16 Return the engine to service.
Observed Fault: Step change in fuel flow exceeding 3% For engines with Non-piloted Fuel Nozzle Assemblies EFFECTIVITY:ALL
TASK 72−00−00−810−828 Page 202 Jul 20/13
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Observed Fault: Engine Does Not Start (Fast N2 Indication) DESCRIPTION: This fault occurs when there is a fast N2 indication and the engine does not start.
POSSIBLE CAUSES: 1. Internal spiral retaining ring loose 2. Radial-drive bevel-pinion gearshaft failure
01 Try to start the engine. Does N2 indication show faster N2 with no apparent turn of N2?
02 Do the borescope inspection of the internal spiral retaining ring and the radial-drive -Yes bevel-pinion gearshaft (Ref. 72-25-42-200-801, MM).
| No |
03 Speak to Rolls-Royce Service Engineering for instructions.
Observed Fault: Engine Does Not Start (Fast N2 Indication) EFFECTIVITY:ALL
TASK 72−00−00−810−829 Page 201/202 Jan 20/12
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Takeoff Power Setting Exceeds 5 Minute Duration DESCRIPTION: The engine was operated at takeoff power for a duration of more than five minutes.
POSSIBLE CAUSES: -
Operator error
01 Reference EICAS - Was there a Master Caution triggered during flight? or Did the crew report high ITT, high N2, or Abnormal Engine Operation during flight?
-No
05 Record in the engine logbook that the 5 minute takeoff limit was exceeded. Go to Block 04.
| Yes 02 Supply electrical power to the aircraft. Access the engine exceedance data from the CMC (Ref. Introduction). Was an exceedance recorded?
-Yes
06 Perform troubleshooting for the exceedance(s) recorded in the CMC.
| No 03 Does the thrust control panel function properly?
-No
07 Troubleshoot thrust control panel per aircraft FIM.
| Yes 04 Put the engine back in service. Notify Rolls-Royce and review Performance Trends within 10 days.
Takeoff Power Setting Exceeds 5 Minute Duration EFFECTIVITY:ALL
TASK 72−00−00−810−830 Page 201/202 Oct 20/13
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Permanent Magnetic Alternator / Ignition Exciter Interface Diagram FIG. 301/TASK 72-00-00-990-801 EFFECTIVITY:ALL
72−00−TASK SUPPORT Page 301 Jul 20/08
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Engine Wiring Diagram FIG. 302/TASK 72-00-00-990-802 EFFECTIVITY:ALL
72−00−TASK SUPPORT Page 302 Jul 20/08
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Fuel Nozzle FIG. 303/TASK 72-00-00-990-803 EFFECTIVITY:ALL
72−00−TASK SUPPORT Page 303 Jul 20/08
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FADEC Power Source Diagram FIG. 304/TASK 72-00-00-990-804 EFFECTIVITY:ALL
72−00−TASK SUPPORT Page 304 Jul 20/08
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Fan Spinner Lock-nut Plug FIG. 305/TASK 72-00-00-990-805 EFFECTIVITY:ALL
72−00−TASK SUPPORT Page 305 Jul 20/08
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R
R R
Engine Performance Run Checklist FIG. 306/TASK 72-00-00-990-806 EFFECTIVITY:ALL
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CHAPTER 73 LIST OF EFFECTIVE PAGES
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CHAPTER SECTION SUBJECT PAGE 73 Contents 1 Contents 2 Contents 3 Contents 4 Contents 5/ 6 00-00 101/ 102 10-00 201 10-00 202 10-00 201/ 202 10-00 201/ 202 10-00 201 10-00 202 10-00 201 10-00 202 10-00 201/ 202 10-00 201/ 202 10-00 201/ 202 10-00 201/ 202 10-00 201/ 202 10-00 201/ 202 10-00 201/ 202 10-00 201/ 202 10-00 201 10-00 202 10-00 201 10-00 202 10-00 201/ 202 10-00 301/ 302 21-00 201 21-00 202 21-00 201/ 202 21-00 201/ 202 21-00 201/ 202 21-00 201/ 202 21-00 201/ 202 21-00 201/ 202 21-00 201/ 202 21-00 201/ 202
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DATE Jul.20/15 Jul.20/15 Jul.20/15 Jul.20/15 Jul.20/15 Jun.15/05 Aug.15/04 Aug.15/04 Oct.15/05 Oct.15/05 Oct.15/05 Oct.15/05 Oct.15/05 Oct.15/05 Oct.15/05 Jul.20/07 Oct.15/05 Oct.15/05 Aug.15/04 Aug.15/04 Aug.15/04 Feb.15/03 Oct.15/05 Oct.15/05 Oct.15/05 Oct.15/05 Aug.15/04 Aug.15/04 Mar.15/03 Mar.15/03 Aug.15/04 Aug.15/04 Aug.15/04 Aug.15/04 Aug.15/04 Oct.15/05 Oct.15/05 Feb.15/03
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OTHER IDENT
DATE Aug.15/04 Aug.15/04 Aug.15/04 Aug.15/04 Jul.20/07 Jul.20/07 Jul.20/07 Oct.20/14 Aug.15/04 Mar.15/03 Oct.15/05 Oct.15/05 Oct.15/05 Oct.15/05 Aug.15/04 Aug.15/04 Oct.15/05 Oct.15/05 Feb.15/03 Feb.15/03 Aug.15/06 Feb.15/03 Feb.15/03 Feb.15/03 Jul.20/15 Jul.20/15 Oct.15/05 Oct.15/05 Jul.20/10 Feb.15/03 Feb.15/03 Aug.15/04 Aug.15/04 Aug.15/04 Aug.15/04 Aug.15/04 Aug.15/04 Aug.15/04 Aug.15/04 Aug.15/04 Aug.15/04
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CHAPTER SECTION SUBJECT PAGE 73 25-00 201/ 202 25-00 201/ 202 25-00 201/ 202 25-00 201 25-00 202 25-00 201/ 202 25-00 201/ 202 25-00 201 25-00 202 25-00 201 25-00 202 25-00 201/ 202 25-00 201/ 202 25-00 201/ 202 25-00 201 25-00 202 25-00 201/ 202 25-00 201/ 202 25-00 201/ 202 25-00 201/ 202 25-00 201 25-00 202 25-00 201 25-00 202 25-00 201 25-00 202 25-00 201/ 202 25-00 201/ 202 25-00 201 25-00 202 25-00 201/ 202 25-00 201/ 202 25-00 201 25-00 202 25-00 201 25-00 202 25-00 201/ 202 25-00 201/ 202 25-00 301 25-00 302 25-00 303 25-00 304 25-00 305 25-00 306 25-00 307 25-00 308 25-00 309 25-00 310 25-00 311 25-00 312
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DATE Aug.15/04
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CHAPTER 73 TABLE OF CONTENTS
SUBJECT
CH-SE-SUB
ENGINE FUEL AND CONTROL FAULT CODE INDEX
73-00-00
DISTRIBUTION FADEC Discrete: ADCFLT (bit 17) / (352 / AILRU2) = 1 FADEC Discrete:PALTFT (bit 18) / (352 / AILRU2) = 1 FADEC Discrete: ALTNOK (bit 18) / (352 / AILRU2) = 1 FADEC Discrete: TATFLT (bit 19) / (352 / AILRU2) = 1 FADEC Discrete: TATNOK (bit 19) / (352 / AILRU2) = 1 FADEC Discrete: MNFLT (bit 20) / (352 / AILRU2) = 1 FADEC Discrete: MNNOK (bit 20) / (352 / AILRU2) = 1 FADEC Discrete: ACSYFT (bit 21) / (352 / AILRU2) = 1 FADEC Discrete: ACSNOK (bit 21) / (352 / AILRU2) = 1 FADEC Discrete: PALDIF (bit 17) / (265 / AIDIF2) = 1 FADEC Discrete: TATDIF (bit 18) / (265 / AIDIF2) = 1 FADEC Discrete: MNDIF (bit 19) / (265 / AIDIF2) = 1 FADEC Discrete: REVMRQ (bit 16) / (355 / SFLTS1) = 1 Maintenance Message: LT-ENG ADC DATA SYS Maintenance Message: LT-ENG ADC DATA SYS Maintenance Message: ST-ENG1/ENG2 ADC COMM SYS Task Support
73-10-00
FUEL PUMP-AND-METERING UNIT FADEC Discrete: FPMUFT (bit 17) / (354/CFPLRU) = 1) FADEC Discrete: MMVFBF (bit 19) / (353 / EILRU) = 1
73-21-00
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EFFECTIVITY
101
201 201 201 201 201 201 201 201 201 201 201 201 201 201 201 201 301
201 201
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SUBJECT FADEC Discrete: MMVTMF (bit 21) / (353 / EILRU) = 1 FADEC Discrete: CVGTMF (bit 22) / (353 / EILRU) = 1 FADEC Discrete: SOSFLT (bit 24) / (353 / EILRU) = 1 FADEC Discrete: STSFLT (bit 25) / (353 / EILRU) = 1 FADEC Discrete: AVSFLT (bit 26) / (353 / EILRU) = 1 FADEC Discrete: FPSNOK (bit 26) / (353 / EILRU) = 1 FADEC Discrete: MMVPFT (bit 15), MMVCFT (bit 14) / (354 / CFPLRU) = 1 FADEC Discrete: MMVTFT (bit 16) / (354 / CFPLRU) = 1 FADEC Discrete: CVGTFT (bit 18) / (354 / CFPLRU) = 1 FADEC Discrete: PRVFLT (bit 24) / (354 / CFPLRU) = 1 FADEC Discrete: MMVFBD (bit 23) / (357 / EIDIF) = 1 FADEC Discrete: MMVDLF (bit 28) / (360 / FADLRU) = 1 FADEC Discrete: CVGDLF (bit 29) / (360 / FADLRU) = 1 Observed Fault: FPMU Seal Drain Accumulation FADEC Discrete: MMVFIX (bit 21) / (354 / CFPLRU) = 1 EICAS Message:: E1/E2 CTL FAIL (set by FADEC Discrete: MMCVFL (bit 28) / (356 / SFLTS2) = 1) EICAS Message:: E1/E2 CTL FAIL (set by FADEC Discrete: MMCVFL (bit 28) / (356 / SFLTS2) = 1) Maintenance Message: LT-ENG1/ENG2 MMV / WF SYS Maintenance Message: ND-ENG1/ENG2 SOI SYS (set by FADEC Discrete: SOIBLF (bit 25) / (352/AILRUZ) = 1) Maintenance Message: ND-ENG1/ENG2 PRV SYS Maintenance Message: ST-ENG1/ENG2 MMV/CVG SYS EICAS Message: E1(2) FPMU NO DISP (set by FADEC Discrete FPMNOK (bit 23) / 354 CFPLRU) FADEC Discrete: HIN1FG (bit 27) / (354 / CFPLRU) = 1
CH-SE-SUB
PAGE
EFFECTIVITY
201 201 201 201 201 201 201 201 201 201 201 201 201 201 201 201 201 201 201 201 201 201 201
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SUBJECT
CH-SE-SUB
Task Support FULL-AUTHORITY DIGITAL ENGINE CONTROL FADEC Discrete: AISIFT (bit 21) / (351 / AILRU1) = 1 FADEC Discrete: AISIDF (bit 21) / (264/ AIDIF1) = 1 FADEC Discrete: LGDLFT (bit 20) / (351 / AILRU1) = 1 FADEC Discrete: LGDLDF (bit 20) / (264 / AIDIF1) = 1 FADEC Discrete: ALTFSF (bit 11) / (352 / AILRU2) = 1 FADEC Discrete: FDRFT (bit 29) / (351 / AILRU1) = 1 FADEC Discrete: ALTDIF (bit 11) / (265 / AIDIF2) = 1 FADEC Discrete: FDRDIF (bit 29) / (264 / AIDIF1) = 1 FADEC Discrete: TOTIFT (bit 22) / (351 / AILRU1) = 1 FADEC Discrete: TOTDFT (bit 23) / (351 / AILRU1) = 1 FADEC Discrete: TOTIDF (bit 22) / (264 / AIDIF1) = 1 FADEC Discrete: TOTDDF (bit 23) / (264 / AIDIF1) = 1 FADEC Discrete: TOTSFT (bit 24) / (351 / AILRU1) = 1 FADEC Discrete: TOTSDF (bit 24) / (264 / AIDIF1) = 1 Maintenance Message: ENG1/ENG2 PMA POWER FAIL or ST - ENG1/ENG2 PMA SYS FADEC Discrete: STFAIL (bit 21) / (355 / SFLTS1) = 1 FADEC Discrete: ACDCFT (bit 16) / (360 / FADLRU) = 1 FADEC Discretes: CSETMF (bit 17) or FADTMF (bit 18) / 360 / FADLRU) = 1 Maintenance Message: ENG1/ENG2 FADEC IN CONTROL / NOT IN CONTROL PARAMT FAIL or ENG1/ENG2 FADEC A/B FAIL Maintenance Message: ENG1/ENG2 FADEC IN CONTROL / NOT IN CONTROL PARAMT FAIL or ENG1/ENG2 FADEC A/B FAIL FADEC Discrete: N1OSF (bit 14) / (360 / FADLRU) = 1
PAGE
EFFECTIVITY
301 73-25-00 201 201 201 201 201 201 201 201 201 201 201 201 201 201 201 201 201 201 201 201 201
73−CONTENTS Page 3 Jul 20/15
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SUBJECT
R R R R R R R R R R R R R R R R R R R R R R R R R R R R
FADEC Discrete: N2OSF (bit 15) / (360 / FADLRU) = 1 FADEC Discrete: V5RFLT (bit 19) / (360 / FADLRU) = 1 FADEC Discrete: V15RFT (bit 20) / (360 / FADLRU) = 1 FADEC Discrete: SEXFLT (bit 21) / (360 / FADLRU) = 1 FADEC Discrete: TLAEXF (bit 22) / (360 / FADLRU) = 1 FADEC Discrete: ARNCTX (bit 25) / (360 / FADLRU) = 1 FADEC Discrete: ARNCRX (bit 26) / (360 / FADLRU) = 1 FADEC Discrete: FADFLT (bit 27) / (360 / FADLRU) = 1 FADEC Discrete: FADFLT (bit 27) / (360 / FADLRU) = 1 FADEC Discrete: SSW1DF (bit 25) / (265 / AIDIF2) = 1 FADEC Discrete: RBRQDF (bit 26) / (265 / AIDIF2) = 1 FADEC Discrete: INHFLB (bit 20) / (356 / SFLTS2) = 1 EICAS Message: ENG NO TO DATA EICAS Message: ENG REF A/I DISAG FADEC Discrete: MTOSFT (bit 16) / (351 / AILRU1) = 1 FADEC Discrete: CLBFT (bit 26) / (351 / AILRU1) = 1 FADEC Discrete: CRZFT (bit 27) / (351 / AILRU1) = 1 FADEC Discrete: MXCFT (bit 28) / (351 / AILRU1) = 1 Maintenance Message: ENG1/ENG2 T/O SWITCH FAIL or ST-ENG T/O SYS DIFF FADEC Discrete: MXCDIF (bit 28) / (264/AIDIF1) = 1 FADEC Discrete: CRZDIF (bit 27) / (264/AIDIF1) = 1 FADEC Discrete: CLBDIF (bit 26) / (264/AIDIF1) = 1 EICAS Message: ENG ATTCS FAIL EICAS Message: E1/E2 ATTCS NO MRGN FADEC Discrete: IDTFL (bit 24) / (360/FADLRU) = 1 FADEC Discrete: IDFLT (bit 13) / (354 / CFPLRU) = 1 EICAS Message: E1/E2 LOW N1
CH-SE-SUB
PAGE
EFFECTIVITY
201 201 201 201 201 201 201 201 201 201 201 201 201 201 201 201 201 201 201 201 201 201 201 201
-`
201 201 201
73−CONTENTS Page 4 Jul 20/15
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SUBJECT
R R R R R R R R R R R R R R R R R R R R R R R R R R R R R R R R R R
CH-SE-SUB
FADEC Discrete: STPFLT (bit 12) / (351 / AILRU1) = 1 FADEC Discrete: STPDIF (bit 12) / (264 / AIDIF1) = 1 FADEC Discrete: CHNFLT (bit 15) / (355 / SFLTS1) = 1 FADEC Discrete: IFPOWINT (bit 17) / (356 / SFLTS2) = 1 EICAS Message: ATTCS FAIL EICAS Message: FADEC ID NO DISP EICAS Message: FADEC ID NO DISP Maintenance Message: ND - ENG1/ENG2 DUAL PMA SYS Maintenance Message: ND-ENG1 / ENG2 FADEC A/B Maintenance Message: ST-ENG1/ENG2 CTL A/B SYS Maintenance Message: ST-ENG1/ENG2 CTL A/B SYS Maintenance Message: ND-ENG1/ENG2 FADEC A/B Maintenance Message: LT-ENG MODE SYS DIFF Maintenance Message: LT-ENG A/I SYS DIFF Maintenance Message: LT-ENG1/ENG2 CTL I/O SYS Maintenance Message: LT-ENG1/ENG2 STOP SYS Maintenance Message: ND-ENG1/ENG2 STOP SYS DIFF FADEC Discrete: AIDNOK (bit 12) / (352 / AILRU2) = 1 FADEC Discrete: AFINOK (bit 12) / (352 / AILRU2) = 1 FADEC Discrete: AIDPFT (bit 20) / (354/CFPLRU) = 1 Observed fault: FADEC Does Not Change Lanes On Start Task Support
PAGE
EFFECTIVITY
201 201 201 201 201 201 201 201 201 201 201 201 201 201 201 201 201 201 201 201 201 301
R FUEL TEMPERATURE SENSOR INDICATIONS R Maintenance Message: ENG1/ENG2 FUEL HIGH R TEMP R EICAS Message: E1/E2 FUEL LOW TEMP R Task Support
73-31-00
R FUEL FILTER BYPASS INDICATIONS R EICAS Message: E1/E2 FUEL IMP BYP R Task Support
73-37-00
201 201 301
201 301
73−CONTENTS Page 5/6 Jul 20/15
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FAULT CODE INDEX FAULT CODE
FAULT DESCRIPTION
731M09 00
ENG ATTCS FAIL (Warning)
73-25-00-810-845
731M10 00
E1 ATTCS NO MRGN (Warning)
73-25-00-810-846
731M11 00
E2 ATTCS NO MRGN (Warning)
73-25-00-810-846
7321O1 00
FPMU Seal-drain Accumulation
73-21-00-810-815
R 732M0251 R
E1 FPMU NO DISP (Caution)
73-21-00-810-822
R 732M0252 R
E2 FPMU NO DISP (Caution)
73-21-00-810-822
732M10 00
ENG REF A/I DISAG (Caution)
73-25-00-810-836
732M11 00
ENG NO T/O DATA (Caution)
73-25-00-810-835
732M14 00
E1 LOW N1 (Warning)
73-25-00-810-851-B01
732M15 00
E2 LOW N1 (Warning)
73-25-00-810-851-B01
732M14 10
ATTCS FAIL (Warning)
73-25-00-810-858
732M15 10
FADEC ID NO DISP (Caution)
73-25-00-810-859
733M03 00
E2 FUEL LOW TEMP (Caution)
73-31-00-810-802
733M04 00
E2 FUEL LOW TEMP (Caution)
73-31-00-810-802
733M07 00
E1 FUEL IMP BYP (Advisory)
73-37-00-810-801
733M08 00
E2 FUEL IMP BYP (Advisory)
73-37-00-810-801
EFFECTIVITY:ALL
MAINT. MESSAGE
GO TO FIM TASK
73−FAULT CODE INDEX Page 101/102 Jun 15/05
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FADEC Discrete: ADCFLT (bit 17) / (352 / AILRU2) = 1 DESCRIPTION:
R
The FADEC monitors the transmission rate of data being received from the air data computer (ADC). This discrete is set to 1 (fault sensed) when the data transmission rate for all of the four ADC parameters monitored by the FADEC (TAT, MN, PALT, and TAT heater-element condition (ON/OFF)) is less than the limit (Ref. FIG. 301/TASK 73-10-00-990-801).
POSSIBLE CAUSES: 1. ADC 2. ARINC data bus 3. FADEC
01 Supply electrical power to the aircraft. Do the test of the aircraft avionics systems for invalid data (Ref. 34-15-00/501 AMM). Is there an indication of invalid ADC data on the primary flight display?
-Yes
07 Do the troubleshooting on the aircraft systems (Ref. 34-22-00 EMB FIM).
| No 02 Access FADEC discrete label 360 from the 08 Do the troubleshooting for FADEC discrete CMC for both FADECs (Ref. Introduction). ARNCTX (bit 25) or ARNCRX (bit 26) (Ref. -Yes Does ARNCTX (bit 25) or ARNCRX (bit 26) = 73-25-00-810-829 or 73-25-00-810-830). 1? | No 03 Disconnect the harness (data bus) from the 09 Clean or repair the connector (Ref. FADEC J2 receptacle and the ADC. Examine 20-50-00-WM). Rotate the FADEC reset/select the connectors for damage, corrosion, or -Yes switch to the RESET position to remove the contamination. Are the connectors fault (ADCFLT (bit 17) = 0). contaminated or damaged? | No 04 Go to Block 5
FADEC Discrete: ADCFLT (bit 17) / (352 / AILRU2) = 1 EFFECTIVITY:ALL
TASK 73−10−00−810−802 Page 201 Aug 15/04
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05 Interchange the positions of the FADECs 10 Replace the FADEC that has the fault (Ref. (Ref. 73-25-10-000-801/73-25-10-400-801 73-25-10-000-801/73-25-10-400-801 MM). MM). Rotate the FADEC reset/select switch to -Yes the RESET position. Does ADCFLT (bit 17) = 1 occur on the opposite channel? | No
R R
06 Do a test for continuity/resistance, internal shorts, and shorts to ground on the ADC/FADEC harness (data bus) (Ref. FIG. 301/TASK 73-10-00-990-801) (Ref. 34-15-51/34-15-52 WM). Is there a harness fault?
11 Replace or repair the aircraft harness (Ref. 20-21-00 WM). -Yes
| No
12 the troubleshooting on the aircraft systems (Ref. 34-15-01/401 AMM).
FADEC Discrete: ADCFLT (bit 17) / (352 / AILRU2) = 1 EFFECTIVITY:ALL
TASK 73−10−00−810−802 Page 202 Aug 15/04
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FADEC Discrete:PALTFT (bit 18) / (352 / AILRU2) = 1 DESCRIPTION: This discrete is set to 1 (fault sensed) when the FADEC finds that the pressure altitude (PALT) data it is receiving from the air data computer (ADC) is not valid (Ref. FIG. 301/TASK 73-10-00-990-801).
POSSIBLE CAUSES: 1. ADC 2. FADEC 3. Aircraft static system
01 Did an invalid data indication occur on the primary flight display, for pressure altitude?
-Yes
03 Do the troubleshooting on the aircraft system (Ref. 34-22-00 EMB FIM).
| No 02 Interchange the positions of the FADECs 04 Replace the FADEC that has the fault (Ref. (Ref. 73-25-10-000-801/73-25-10-400-801 73-25-10-000-801/73-25-10-400-801 MM). MM). Rotate the FADEC reset/select switch to -Yes the RESET position. Does PALTFT (bit 18) = 1 occur on the opposite channel? | No 05 Do the troubleshooting on the aircraft ADC/pitot-static system (Ref. 34-22-00 EMB FIM).
FADEC Discrete:PALTFT (bit 18) / (352 / AILRU2) = 1 R EFFECTIVITY:FADEC SOFTWARE VER. B5.1.1
TASK 73−10−00−810−803−A01 Page 201/202 Oct 15/05
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FADEC Discrete: ALTNOK (bit 18) / (352 / AILRU2) = 1 DESCRIPTION: This discrete is set to 1 (fault sensed) when the FADEC finds that the pressure altitude (PALT) data it is receiving from the air data computer (ADC) is not valid (Ref. FIG. 301/TASK 73-10-00-990-801).
POSSIBLE CAUSES: 1. ADC 2. FADEC 3. Aircraft static system
01 Did an invalid data indication occur on the primary flight display, for pressure altitude?
-Yes
03 Do the troubleshooting on the aircraft system (Ref. 34-22-00 EMB FIM).
| No 02 Interchange the positions of the FADECs 04 Replace the FADEC that has the fault (Ref. (Ref. 73-25-10-000-801/73-25-10-400-801 73-25-10-000-801/73-25-10-400-801 MM). MM). Rotate the FADEC reset/select switch to -Yes the RESET position. Does ALTNOK (bit 18) = 1 occur on the opposite channel? | No
05 Do the troubleshooting on the aircraft ADC/pitot-static system (Ref. 34-22-00 EMB FIM).
FADEC Discrete: ALTNOK (bit 18) / (352 / AILRU2) = 1 EFFECTIVITY:FADEC SOFTWARE VER. B7.5 OR LATER
TASK 73−10−00−810−803−B01 Page 201/202 Oct 15/05
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FADEC Discrete: TATFLT (bit 19) / (352 / AILRU2) = 1 DESCRIPTION: This discrete is set to 1 (fault sensed) when the FADEC finds that the total air temperature (TAT) data it is receiving from the air data computer (ADC) is not valid, or there is no indication that the heater element for the TAT sensor is ON. The FADEC does these tests when the aircraft is in flight (Ref. FIG. 301/TASK 73-10-00-990-801).
POSSIBLE CAUSES: 1. TAT sensor/circuit 2. ADC 3. FADEC
R
01 Supply electrical power to the aircraft. Access FADEC discrete label 352 from the central maintenance computer (CMC) (Ref. Introduction). Does ACSYFT (bit 21) = 1? (Weight-on-wheels must be false for this fault to be set.)
06 Do the troubleshooting for FADEC discrete ACSYFT (bit 21) (Ref. 73-10-00-810-806-A01). -Yes
| No 02 Does TATFLT (bit 19) = 1 change to 0 for both FADECs when the anti-ice switch is turned off?
07 Repair the circuit for the TAT current sensing relay (check the grounding stud) (Ref. -Yes 30-33-50 EMB WM). Rotate the FADEC reset/select switch to the RESET position to remove the fault (TATFLT (bit 19) = 0).
| No 03 Was the caution, TAT 1/2 HEAT INOP, displayed on the EICAS?
08 Repair the circuit for the TAT sensor heater (Ref. 30-33-00 EMB FIM). Rotate the FADEC -Yes reset/select switch to the RESET position to remove the fault (TATFLT (bit 19) = 0).
| No 04 Go to Block 5
FADEC Discrete: TATFLT (bit 19) / (352 / AILRU2) = 1 R EFFECTIVITY:FADEC SOFTWARE VER. B5.1.1
TASK 73−10−00−810−804−A01 Page 201 Oct 15/05
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05 Interchange the positions of the FADECs 09 Replace the FADEC that has the fault (Ref. 73-25-10-000-801/73-25-10-400-801 (Ref. 73-25-10-000-801/73-25-10-400-801 MM). Rotate the FADEC reset/select switch to -Yes MM). the RESET position. Does TATFLT (bit 19) = 1 occur on the opposite channel? | No 10 Do the troubleshooting on the aircraft system (Ref. 34-22-00 EMB FIM).
FADEC Discrete: TATFLT (bit 19) / (352 / AILRU2) = 1 R EFFECTIVITY:FADEC SOFTWARE VER. B5.1.1
TASK 73−10−00−810−804−A01 Page 202 Oct 15/05
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FADEC Discrete: TATNOK (bit 19) / (352 / AILRU2) = 1 DESCRIPTION: This discrete is set to 1 (fault sensed) when the FADEC finds that the total air temperature (TAT) data it is receiving from the air data computer (ADC) is not valid, or there is no indication that the heater element for the TAT sensor is ON. The FADEC does these tests when the aircraft is in flight (Ref. FIG. 301/TASK 73-10-00-990-801).
POSSIBLE CAUSES: 1. TAT sensor/circuit 2. ADC 3. FADEC
01 Supply electrical power to the aircraft. Access FADEC discrete label 352 from the central maintenance computer (CMC) (Ref. Introduction). Does ACSNOK (bit 21) = 1? (Weight-on-wheels must be false for this fault to be set.)
-Yes
06 Do the troubleshooting for FADEC discrete ACSNOK (bit 21) (Ref. 73-10-00-810-806-B01).
| No 02 Does TATNOK (bit 19) = 1 change to 0 for both FADECs when the anti-ice switch is turned off?
07 Repair the circuit for the TAT current sensing relay (check the grounding stud) (Ref. -Yes 30-33-50 EMB WM). Rotate the FADEC reset/select switch to the RESET position to remove the fault (TATNOK (bit 19) = 0).
| No 03 Was the caution, TAT 1/2 HEAT INOP, displayed on the EICAS?
08 Repair the circuit for the TAT sensor heater (Ref. 30-33-00 EMB FIM). Rotate the FADEC -Yes reset/select switch to the RESET position to remove the fault (TATNOK (bit 19) = 0).
| No 04 Go to block 05.
FADEC Discrete: TATNOK (bit 19) / (352 / AILRU2) = 1 EFFECTIVITY:FADEC SOFTWARE VER. B7.5 OR LATER
TASK 73−10−00−810−804−B01 Page 201 Oct 15/05
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05 Interchange the positions of the FADECs 09 Replace the FADEC that has the fault (Ref. (Ref. 73-25-10-000-801/73-25-10-400-801 73-25-10-000-801/73-25-10-400-801 MM). MM). Rotate the FADEC reset/select switch to -Yes the RESET position. Does TATNOK (bit 19) = 1 occur on the opposite channel? | No
10 Do the troubleshooting on the aircraft system (Ref. 34-22-00 EMB FIM).
FADEC Discrete: TATNOK (bit 19) / (352 / AILRU2) = 1 EFFECTIVITY:FADEC SOFTWARE VER. B7.5 OR LATER
TASK 73−10−00−810−804−B01 Page 202 Oct 15/05
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FADEC Discrete: MNFLT (bit 20) / (352 / AILRU2) = 1 DESCRIPTION: This discrete is set to 1 (fault sensed) when the FADEC finds that the mach number (MN) data it is receiving from the air data computer (ADC) is not valid (Ref. FIG. 301/TASK 73-10-00-990-801).
POSSIBLE CAUSES: 1. ADC 2. FADEC 3. Aircraft pitot/static system
01 Did an invalid data indication occur on the primary flight display, for mach number or airspeed?
03 Do the troubleshooting on the aircraft -Yes system (Ref. 34-22-00 EMB FIM).
| No 02 Interchange the positions of the FADECs 04 Replace the FADEC that has the fault (Ref. (Ref. 73-25-10-000-801/73-25-10-400-801 73-25-10-000-801/73-25-10-400-801 MM). MM). Rotate the FADEC reset/select switch to -Yes the RESET position. Does MNFLT (bit 20) = 1 occur on the opposite channel? | No 05 Do the troubleshooting on the aircraft ADC/pitot-static system (Ref. 34-22-00 EMB FIM).
FADEC Discrete: MNFLT (bit 20) / (352 / AILRU2) = 1 R EFFECTIVITY:FADEC SOFTWARE VER. B5.1.1
TASK 73−10−00−810−805−A01 Page 201/202 Oct 15/05
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FADEC Discrete: MNNOK (bit 20) / (352 / AILRU2) = 1 DESCRIPTION: This discrete is set to 1 (fault sensed) when the FADEC finds that the mach number (MN) data it is receiving from the air data computer (ADC) is not valid (Ref. FIG. 301/TASK 73-10-00-990-801).
POSSIBLE CAUSES:
R
R
1. ADC 2. FADEC 3. Aircraft pitot/static system 4. P2.5 sensor
01 Did an invalid data indication occur on the primary flight display, for mach number or airspeed?
04 Do the troubleshooting on the aircraft -Yes system (Ref. 34-22-00 EMB FIM).
| No R
02 Interchange the positions of the FADECs 05 Replace the FADEC that has the fault (Ref. (Ref. 73-25-10-000-801/73-25-10-400-801 73-25-10-000-801/73-25-10-400-801 MM). MM). Rotate the FADEC reset/select switch to -Yes the RESET position. Does MNNOK (bit 20) = 1 occur on the opposite channel? | No
R R R R R R R R R
03 Interchange the positions of the P2.5 sensors (Ref. 75-43-10-000-801/75-43-10-400-801 MM). Rotate the FADEC reset/select switch to the RESET position. Does the fault move to the opposite channel?
-Yes
06 Replace the P2.5 sensor that has the fault. (Ref. 75-43-10-000-801/75-43-10-400-801 MM).
| No
R
07 Do the troubleshooting on the aircraft ADC/pitot-static system (Ref. 34-22-00 EMB FIM).
FADEC Discrete: MNNOK (bit 20) / (352 / AILRU2) = 1 EFFECTIVITY:FADEC SOFTWARE VER. B7.5 OR LATER
TASK 73−10−00−810−805−B01 Page 201/202 Jul 20/07
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FADEC Discrete: ACSYFT (bit 21) / (352 / AILRU2) = 1 DESCRIPTION: This discrete is set to 1 (fault sensed) when the FADEC is not receiving valid data from the air data computer (ADC) about the heater element (ON/OFF) for the total air-temperature sensor (Ref. FIG. 301/TASK 73-10-00-990-801).
POSSIBLE CAUSES: 1. ADC 2. FADEC
01 Interchange the positions of the FADECs 02 Replace the FADEC that has the fault (Ref. (Ref. 73-25-10-000-801/73-25-10-400-801 73-25-10-000-801/73-25-10-400-801 MM). MM). Rotate the FADEC reset/select switch to the RESET position. Does ACSYFT (bit 21) = -Yes 1 occur on the opposite channel? (Weight-on-wheels must be false for this fault to be set.) | No
03 Do the troubleshooting on the aircraft system (Ref. 34-22-00 EMB FIM).
FADEC Discrete: ACSYFT (bit 21) / (352 / AILRU2) = 1 R EFFECTIVITY:FADEC SOFTWARE VER. B5.1.1
TASK 73−10−00−810−806−A01 Page 201/202 Oct 15/05
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FADEC Discrete: ACSNOK (bit 21) / (352 / AILRU2) = 1 DESCRIPTION: This discrete is set to 1 (fault sensed) when the FADEC is not receiving valid data from the air data computer (ADC) about the heater element (ON/OFF) for the total air-temperature sensor (Ref. FIG. 301/TASK 73-10-00-990-801).
POSSIBLE CAUSES: 1. ADC 2. FADEC
01 Interchange the positions of the FADECs (Ref. 73-25-10-000-801/73-25-10-400-801 MM). Rotate the FADEC reset/select switch to the RESET position. Does ACSNOK (bit 21) = 1 occur on the opposite channel? (Weight-on-wheels must be false for this fault to be set.)
02 Replace the FADEC that has the fault (Ref. 73-25-10-000-801/73-25-10-400-801 MM). -Yes
| No
03 Do the troubleshooting on the aircraft system (Ref. 34-22-00 EMB FIM).
FADEC Discrete: ACSNOK (bit 21) / (352 / AILRU2) = 1 EFFECTIVITY:FADEC SOFTWARE VER. B7.5 OR LATER
TASK 73−10−00−810−806−B01 Page 201/202 Oct 15/05
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FADEC Discrete: PALDIF (bit 17) / (265 / AIDIF2) = 1 DESCRIPTION: R
This discrete is set to 1 (fault sensed) when this FADEC finds that the pressure altitude (PALT) data it is receiving from the air data computer (ADC) is different from that received by the other FADEC, by more than 400 feet (Ref. FIG. 301/TASK 73-10-00-990-801).
POSSIBLE CAUSES: 1. ADC 2. Aircraft static system 3. FADEC
01 Supply electrical power to the aircraft. Compare the pressure altitude values on both primary flight displays (PFD). Are the values the same, or different by less than 350 feet?
-No
04 Do the troubleshooting on the ADC/static system (Ref. 34-22-00 EMB FIM).
| Yes 02 Access the FADEC analog label from the 05 Replace the FADEC showing PALDIF (bit central maintenance computer (CMC) for both 17) = 1 (Ref. -No FADECs (Ref. Introduction). Are the values for 73-25-10-000-801/73-25-10-400-801 MM). PALT different, by more than 400 feet? | Yes 03 Interchange the positions of the FADECs (Ref. 73-25-10-000-801/73-25-10-400-801 MM). Do the PALT values move to the opposite channels?
06 Replace the FADEC with the largest PALT error, compared to the PFD value (Ref. -Yes 73-25-10-000-801/73-25-10-400-801 MM).
| No
07 Do the troubleshooting on the aircraft ADC/pitot-static systems (Ref. 34-15-01/401 AMM).
FADEC Discrete: PALDIF (bit 17) / (265 / AIDIF2) = 1 EFFECTIVITY:ALL
TASK 73−10−00−810−807 Page 201/202 Aug 15/04
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FADEC Discrete: TATDIF (bit 18) / (265 / AIDIF2) = 1 DESCRIPTION: R
This discrete is set to 1 (fault sensed) when this FADEC finds that the total air-temperature (TAT) data it is receiving from the air data computer (ADC) is different from that received by the other FADEC, by more than 4 °C (Ref. FIG. 301/TASK 73-10-00-990-801).
POSSIBLE CAUSES: 1. ADC 2. Total air-temperature circuit 3. FADEC
01 Supply electrical power to the aircraft. 03 Replace the FADEC showing TATDIF (bit Access the FADEC analog label from the 18) = 1 (Ref. central maintenance computer (CMC) for both -Yes 73-25-10-000-801/73-25-10-400-801 MM). FADECs (Ref. Introduction). Are the values for TAT different by more than 4 °C? | No 02 Interchange the positions of the FADECs 04 Replace the FADEC with the largest TAT (Ref. 73-25-10-000-801/73-25-10-400-801 error, compared to the ambient temperature MM). Do the TAT values move to the opposite -Yes (Ref. 73-25-10-000-801/73-25-10-400-801 channels? (Weight-on-wheels must be false MM). for this fault to be set.) | No
05 Do the troubleshooting on the aircraft systems (Ref. 34-22-00 EMB FIM).
FADEC Discrete: TATDIF (bit 18) / (265 / AIDIF2) = 1 EFFECTIVITY:ALL
TASK 73−10−00−810−808 Page 201/202 Aug 15/04
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FADEC Discrete: MNDIF (bit 19) / (265 / AIDIF2) = 1 DESCRIPTION: R
This discrete is set to 1 (fault sensed) when this FADEC finds that the mach number (MN) data it is receiving from the air data computer (ADC) is different from that received by the other FADEC, by more than .04 mach (Ref. FIG. 301/TASK 73-10-00-990-801).
POSSIBLE CAUSES: 1. ADC 2. Aircraft pitot/static system 3. FADEC
01 Supply electrical power to the aircraft. Do the functional test of the pitot/static system. Compare the mach number values on both primary flight displays (PFD). Are the values the same, or different by less than 0.04 mach?
-No
04 Do the troubleshooting on the aircraft systems (Ref. 34-22-00 EMB FIM).
| Yes 02 Access the FADEC analog labels from the central maintenance computer (CMC) for both FADECs (Ref. Introduction). Are the values for MN different, by more than 0.04 mach?
05 Replace the FADEC showing MNDIF (bit 19) = 1 (Ref. 73-25-10-000-801/ -No 73-25-10-400-801 MM).
| Yes 03 Interchange the positions of the FADECs (Ref. 73-25-10-000-801/73-25-10-400-801 MM). Do the MN values move to the opposite channels?
06 Replace the FADEC with the largest MN error, compared to the PFD value (Ref. -Yes 73-25-10-000-801/73-25-10-400-801 MM).
| No
07 Do the troubleshooting on the aircraft ADC/pitot-static systems (Ref. 34-15-01/401 AMM).
FADEC Discrete: MNDIF (bit 19) / (265 / AIDIF2) = 1 EFFECTIVITY:ALL
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FADEC Discrete: REVMRQ (bit 16) / (355 / SFLTS1) = 1 DESCRIPTION: This discrete is set to 1 (fault sensed) when no valid pressure altitude (PALT) or mach number (MN) data is available to this FADEC from either of the two air data computers (ADC). The FADEC will use PALT and MN values synthesized from engine sensor data for controlling thrust in this reversionary control mode.
POSSIBLE CAUSES: 1. ADC 2. ARINC 429 data bus 3. FADEC
01 Supply electrical power to the aircraft. 02 Do the troubleshooting for the FADEC Access FADEC discrete labels 265 and 352 discretes = 1. from the central maintenance computer (CMC) (Ref. Introduction). Is PALDIF (bit 17) or -Yes MNDIF (bit 19) = 1 (label 265) and/or is PALTFT (bit 18), MNFLT (bit 20) or ADCFLT (bit 17) = 1 (label 352)? | No
03 Replace the FADEC showing REVMRQ (bit 16) = 1 (Ref. 73-25-10-000-801/73-25-10-400-801 MM).
FADEC Discrete: REVMRQ (bit 16) / (355 / SFLTS1) = 1 EFFECTIVITY:ALL
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Maintenance Message: LT-ENG ADC DATA SYS DESCRIPTION: This message occurs when the FADEC finds a fault in the data received from the air data computer (ADC), or data is not being received from the ADC (Ref. FIG. 301/TASK 73-10-00-990-801). This message can be incorrectly set by a momentary power supply interruption to the ADC.
POSSIBLE CAUSES: 1. Failure of aircraft inputs to the ADC (MN, TAT, PALT) 2. ARINC bus (ADC/FADEC) 3. FADEC
R
01 Supply electrical power to the aircraft. Access FADEC discrete label 352 from the central maintenance computer (CMC) (Ref. Introduction). Does PALTFT (bit 18) = 1?
09 Do the troubleshooting for FADEC discrete PALTFT (bit 18) = 1 (Ref. -Yes 73-10-00-810-803-A01).
| No
R
02 Does TATFLT (bit 19) = 1? (Weight-on-wheels must be false for this fault to be set.)
10 Do the troubleshooting for FADEC discrete -Yes TATFLT (bit 19) = 1 (Ref. 73-10-00-810-804-A01).
| No 03 Does MNFLT (bit 20) = 1? R
11 Do the troubleshooting for FADEC discrete -Yes MNFLT (bit 20) = 1 (Ref. 73-10-00-810-805-A01).
| No 04 Access FADEC discrete label 265 from the 12 Do the troubleshooting for FADEC discrete -Yes PALDIF (bit 17) = 1 (Ref. 73-10-00-810-807). CMC for both FADECs (Ref. Introduction). Does PALDIF (bit 17) = 1? | No 05 Go to Block 06
Maintenance Message: LT-ENG ADC DATA SYS R EFFECTIVITY:FADEC SOFTWARE VER. B5.1.1
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06 Does TATDIF (bit 18) = 1? (Weight-on-wheels must be false for this fault to be set.)
13 Do the troubleshooting for FADEC discrete -Yes TATDIF (bit 18) = 1 (Ref. 73-10-00-810-808).
| No 07 Does MNDIF (bit 19) = 1?
-Yes
14 Do the troubleshooting for FADEC discrete MNDIF (bit 19) = 1 (Ref. 73-10-00-810-809).
| No 08 Examine the harness connectors at the FADEC, ADC, and ADC sensors for condition. Are they damaged?
15 Clean or repair the connectors and harness -Yes as necessary (Ref. 20-50-00 WM).
| No 16 Access the CMC for this message after subsequent flights. Do not remove electrical power from the FADECs. Repeat the procedures.
Maintenance Message: LT-ENG ADC DATA SYS R EFFECTIVITY:FADEC SOFTWARE VER. B5.1.1
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Maintenance Message: LT-ENG ADC DATA SYS DESCRIPTION: This message occurs when the FADEC finds a fault in the data received from the air data computer (ADC), or data is not being received from the ADC (Ref. FIG. 301/TASK 73-10-00-990-801). This message can be incorrectly set by a momentary power supply interruption to the ADC.
POSSIBLE CAUSES: 1. Failure of aircraft inputs to the ADC (MN, TAT, PALT) 2. ARINC bus (ADC/FADEC) 3. FADEC
01 Supply electrical power to the aircraft. Access FADEC discrete label 352 from the central maintenance computer (CMC) (Ref. Introduction). Does ALTNOK (bit 18) = 1?
09 Do the troubleshooting for FADEC discrete ALTNOK (bit 18) = 1 (Ref. -Yes 73-10-00-810-803-B01).
| No 02 Does TATNOK (bit 19) = 1? (Weight-on-wheels must be false for this fault to be set.)
10 Do the troubleshooting for FADEC discrete -Yes TATNOK (bit 19) = 1 (Ref. 73-10-00-810-804-B01).
| No 03 Does MNNOK (bit 20) = 1?
11 Do the troubleshooting for FADEC discrete -Yes MNNOK (bit 20) = 1 (Ref. 73-10-00-810-805-B01).
| No 04 Access FADEC discrete label 265 from the CMC for both FADECs (Ref. Introduction). Does PALDIF (bit 17) = 1?
12 Do the troubleshooting for FADEC discrete -Yes PALDIF (bit 17) = 1 (Ref. 73-10-00-810-807).
| No 05 Go to Block 06.
Maintenance Message: LT-ENG ADC DATA SYS EFFECTIVITY:FADEC SOFTWARE VER. B7.5 OR LATER
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06 Does TATDIF (bit 18) = 1? (Weight-on-wheels must be false for this fault to be set.)
13 Do the troubleshooting for FADEC discrete -Yes TATDIF (bit 18) = 1 (Ref. 73-10-00-810-808).
| No 07 Does MNDIF (bit 19) = 1?
-Yes
14 Do the troubleshooting for FADEC discrete MNDIF (bit 19) = 1 (Ref. 73-10-00-810-809).
| No 08 Examine the harness connectors at the FADEC, ADC, and ADC sensors for condition. Are they damaged?
15 Clean or repair the connectors and harness -Yes as necessary (Ref. 20-50-00 WM).
| No 16 Access the CMC for this message after subsequent flights. Do not remove electrical power from the FADECs. Repeat this procedures.
Maintenance Message: LT-ENG ADC DATA SYS EFFECTIVITY:FADEC SOFTWARE VER. B7.5 OR LATER
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Maintenance Message: ST-ENG1/ENG2 ADC COMM SYS DESCRIPTION:
R
The FADEC monitors the transmission rate of data being received from the air data computer (ADC). This discrete is set to 1 (fault sensed) when the data transmission rate for all of the four ADC parameters monitored by the FADEC (TAT, MN, PALT and TAT heater-element condition (ON/OFF)) is less than the limit (Ref. FIG. 301/TASK 73-10-00-990-801). This message can be incorrectly set by a momentary power supply interruption to the ADC.
POSSIBLE CAUSES: 1. ADC 2. ARINC bus (ADC/FADEC) 3. FADEC
01 Supply electrical power to the aircraft. Access FADEC discrete label 352 from the central maintenance computer (CMC) (Ref. Introduction). Does ADCFLT (bit 17) = 1?
-Yes
03 Do the troubleshooting for FADEC discrete ADCFLT (bit 17) = 1 (Ref. 73-10-00-810-802).
| No 02 Examine the harness connectors at the FADEC, ADC, and ADC sensors for condition. Are they damaged?
04 Clean or repair the connectors and harness -Yes as necessary (Ref. 20-50-00 WM).
| No
05 Look at the CMC maintenance page on the MFD for this message after the next flight. Do not remove electrical power from the FADECs. Repeat the procedure starting from block 01.
Maintenance Message: ST-ENG1/ENG2 ADC COMM SYS EFFECTIVITY:ALL
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Air Data Computer / FADEC Interface Diagram FIG. 301/TASK 73-10-00-990-801
R EFFECTIVITY:ALL
73−10−TASK SUPPORT Page 301/302 Aug 15/04
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R FADEC Discrete: FPMUFT (bit 17) / (354/CFPLRU) = 1) DESCRIPTION: This message occurs when the FADEC finds a fault in the fuel pump-and-metering unit (FPMU) or the FADEC control circuits for the FPMU.
POSSIBLE CAUSES: 1. FPMU 2. FADEC/FPMU harness 3. CVG hydraulic actuator 4. FADEC
01 Supply electrical power to the aircraft. Access FADEC discrete label 353 from the central maintenance computer (CMC) for both FADECs (Ref. Introduction). Does MMVFBF (bit 19) = 1?
-Yes
13 Do the troubleshooting for FADEC discrete MMVFBF (bit 19) (Ref. 73-21-00-810-802).
| No 02 Does MMVTMF (bit 21) = 1?
-Yes
14 Do the troubleshooting for FADEC discrete MMVTMF (bit 21) (Ref. 73-21-00-810-803).
| No 04 Access FADEC discrete label 354 from the 16 Do the troubleshooting for FADEC CMC for both FADECs. Does MMVCFT (bit -Yes discretes MMVCFT (bit 14) or MMVPFT (bit 15) 14) or MMVPFT (bit 15) = 1? (Ref. 73-21-00-810-808). | No 05 Does MMVTFT (bit 16) = 1?
-Yes
17 Do the troubleshooting for FADEC discrete MMVTFT (bit 16) (Ref. 73-21-00-810-809).
-Yes
18 Do the troubleshooting for FADEC discrete CVGTFT (bit 18) (Ref. 73-21-00-810-810).
| No 06 Does CVGTFT (bit 18) = 1? | No 07 Go to block 08. FADEC Discrete: FPMUFT (bit 17) / (354/CFPLRU) = 1) EFFECTIVITY:ALL
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08 Does PRVFLT (bit 24) = 1?
-Yes
19 Do the troubleshooting for FADEC discrete PRVFLT (bit 24) (Ref. 73-21-00-810-811).
| No 09 Access FADEC discrete label 357 from the 20 Do the troubleshooting for FADEC discrete CMC for both FADECs (Ref. Introduction). -Yes MMVFBD (bit 23) (Ref. 73-21-00-810-812). Does MMVFBD (bit 23) = 1? | No 10 Access FADEC discrete label 360 from the 21 Do the troubleshooting for FADEC discrete CMC for both FADECs (Ref. Introduction). -Yes MMVDLF (bit 28) (Ref. 73-21-00-810-813). Does MMVDLF (bit 28) = 1? | No 11 Does CVGDLF (bit 29) = 1?
-Yes
22 Do the troubleshooting for FADEC discrete CVGDLF (bit 29) (Ref. 73-21-00-810-814).
-Yes
17 Do the troubleshooting for FADEC discrete MMVTFT (bit 16) (Ref. 73-21-00-810-809).
| No 05 Does MMVTFT (bit 16) = 1? | No 12 Operate the engine (Ref. AMM). Do not remove electrical power from the FADECs. Repeat the procedures in blocks 01 through 11. Do any of the FADEC discretes = 1?
-Yes
23 Do the troubleshooting for the FADEC discrete(s) (Ref. FADEC Discrete List).
| No |
24 Examine all of the harness connectors between the FADEC J4 receptacle and the FPMU, for dirty or damaged condition. Clean or replace the harness as necessary (Ref. 73-21-50/73-21-51 WM).
FADEC Discrete: FPMUFT (bit 17) / (354/CFPLRU) = 1) EFFECTIVITY:ALL
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FADEC Discrete: MMVFBF (bit 19) / (353 / EILRU) = 1 DESCRIPTION: The FADEC monitors the signal received from the position sensor for the main metering valve of the fuel pump-and-metering unit (FPMU). This discrete is set to 1 (fault sensed) when the position of the valve sensed is not within the limits.
POSSIBLE CAUSES: R
1. Harness (W11/14, W7) 2. FPMU 3. FADEC
01 Supply electrical power to the aircraft. 04 Do the troubleshooting for FADEC discrete Access FADEC discrete label 360 from the SEXFLT (bit 21) = 1 (Ref. 73-25-00-810-826). -Yes CMC (Ref. Introduction). Does SEXFLT (bit 21) = 1? | No R
02 Interchange the position of the FADECs 05 Replace the FADEC that has the fault (Ref. 73-25-10-000-801/73-25-10-400-801 (Ref. 73-25-10-000-801/73-25-10-400-801, MM). Move the FADEC reset/select switch to -Yes MM). the RESET position. Does the fault move to the opposite channel? | No
R R R R R
03 Do a test for continuity/resistance (1 ohm max./harness), internal shorts, and shorts to ground (1,000 ohms min.) on the external FADEC A/B (W11/14) and the FADEC/engine interconnect (W7) harnesses (Ref. FIG. 301/TASK 73-21-00-990-801/FIG. 303/TASK 73-21-00-990-803). Do the harnesses test satisfactorily?
06 Replace the FPMU (Ref. 73-21-10-000-801/73-21-10-400-801, MM). -Yes
| No |
R
07 Replace the bad harness (Ref. Ch. 76-00-00, MM) (Ref. AMM).
FADEC Discrete: MMVFBF (bit 19) / (353 / EILRU) = 1 EFFECTIVITY:ALL
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FADEC Discrete: MMVTMF (bit 21) / (353 / EILRU) = 1 DESCRIPTION: The FADEC in control does a test for open and shorted conditions on the circuit for the main metering valve (MMV) torquemotor of the fuel pump-and-metering unit). The FADEC also monitors its driver voltage for the MMV torquemotor, to find if it is correct for the fuel flow commanded. This discrete is set to 1 (fault sensed) when one or both of these tests are failed.
POSSIBLE CAUSES: R
R
1. Harness (W11/14, W7) 2. FPMU 3. FADEC
01 Interchange the position of the FADECs 03 Replace the FADEC that has the fault (Ref. 73-25-10-000-801/73-25-10-400-801, (Ref. 73-25-10-000-801/73-25-10-400-801, MM). Move the FADEC reset/select switch to MM). the RESET position. Does the fault move to -Yes the opposite channel (the FADEC for the opposite channel must be selected as the controlling FADEC for this message to be set)? | No
R R R R R
02 Do a test for continuity/resistance (1 ohm max./harness), internal shorts, and shorts to ground (1,000 ohms min.) on the external FADEC A/B (W11/14) and the FADEC/engine interconnect (W7) harnesses (Ref. FIG. 301/TASK 73-21-00-990-801/FIG. 303/TASK 73-21-00-990-803) (Ref. 73-21-50/73-21-51, WM). Do the harnesses test satisfactorily?
04 Replace the FPMU (Ref. 73-21-10-000-801/73-21-10-400-801, MM). -Yes
| No | R
05 Replace the bad harness (Ref. 76-00-00, MM) (Ref. AMM).
FADEC Discrete: MMVTMF (bit 21) / (353 / EILRU) = 1 EFFECTIVITY:ALL
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FADEC Discrete: CVGTMF (bit 22) / (353 / EILRU) = 1 DESCRIPTION: The FADEC in control does a test for open and shorted conditions on the circuit for the compressor variable-geometry (CVG) torquemotor in the fuel pump-and-metering unit (FPMU). The FADEC also monitors its driver voltage for the CVG torquemotor, to find if it is correct for the commanded CVG-actuator position. This discrete is set to 1 (fault sensed) when one or both of these tests are failed.
POSSIBLE CAUSES: R
R
1. Harness (W11/14, W7) 2. FPMU 3. FADEC
01 Interchange the position of the FADECs 03 Replace the FADEC that has the fault (Ref. 73-25-10-000-801/73-25-10-400-801, (Ref. 73-25-10-000-801/73-25-10-400-801, MM). Move the FADEC reset/select switch to MM). the RESET position. Does the fault move to -Yes the opposite channel (the FADEC for the opposite channel must be selected as the controlling FADEC for this message to be set)? | No
R R R R R R
02 Do a test for continuity/resistance (1 ohm max./harness), internal shorts, and shorts to ground (1,000 ohms min.) on the external FADEC A/B (W11/14) and the FADEC/engine interconnect (W7) harnesses (Ref. FIG. 301/TASK 73-21-00-990-801/FIG. 303/TASK 73-21-00-990-803) (Ref. 73-21-50/73-21-51, WM). Do the harnesses test satisfactorily?
04 Replace the FPMU (Ref. 73-21-10-000-801/73-21-10-400-801, MM). -Yes
| No | R
05 Replace the bad harness (Ref. 76-00-00, MM) (Ref. AMM).
FADEC Discrete: CVGTMF (bit 22) / (353 / EILRU) = 1 EFFECTIVITY:ALL
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FADEC Discrete: SOSFLT (bit 24) / (353 / EILRU) = 1 DESCRIPTION: The FADEC does a test for open and shorted conditions on the stop circuit for the latching (fuel) shutoff valve (LSOV) in the fuel pump-and-metering unit (FPMU). The FADEC also monitors its driver voltage for the stop coil, to find if it is correct for the commanded LSOV position. This discrete is set to 1 (fault sensed) when one or both of these tests are failed.
POSSIBLE CAUSES: R
R
1. Harness (W11/14, W7) 2. FPMU 3. FADEC
01 Interchange the position of the FADECs (Ref. 73-25-10-000-801/73-25-10-400-801, MM). Move the FADEC reset/select switch to the RESET position. Does the fault move to the opposite channel?
03 Replace the FADEC that has the fault (Ref. 73-25-10-000-801/73-25-10-400-801, -Yes MM).
| No R R R R R
02 Do a test for continuity/resistance (1 ohm max./harness), internal shorts, and shorts to ground (1,000 ohms min.) on the external FADEC A/B (W11/14) and the FADEC/engine interconnect (W7) harnesses (Ref. FIG. 301/TASK 73-21-00-990-801/FIG. 303/TASK 73-21-00-990-803) (Ref. 73-21-50/73-21-51, WM). Do the harnesses test satisfactorily?
04 Replace the FPMU (Ref. 73-21-10-000-801/73-21-10-400-801, MM). -Yes
| No | R
05 Replace the bad harness (Ref. 76-00-00, MM) (Ref. AMM).
FADEC Discrete: SOSFLT (bit 24) / (353 / EILRU) = 1 EFFECTIVITY:ALL
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FADEC Discrete: STSFLT (bit 25) / (353 / EILRU) = 1 DESCRIPTION: The FADEC does a test for open and shorted conditions on the start coil circuit for the latching (fuel) shutoff valve (LSOV) in the fuel pump-and-metering unit (FPMU). The FADEC also monitors its driver voltage for the start coil, to find if it is correct for the commanded LSOV position. This discrete is set to 1 (fault sensed) when one or both of these tests are failed.
POSSIBLE CAUSES: R
R
1. Harness (W11/14, W7) 2. FPMU 3. FADEC
01 Interchange the position of the FADECs (Ref. 73-25-10-000-801/73-25-10-400-801, MM). Move the FADEC reset/select switch to the RESET position. Does the fault move to the opposite channel?
03 Replace the FADEC that has the fault (Ref. 73-25-10-000-801/73-25-10-400-801, -Yes MM).
| No R R R R R
02 Do a test for continuity/resistance (1 ohm max./harness), internal shorts, and shorts to ground (1,000 ohms min.) on the external FADEC A/B (W11/14) and the FADEC/engine interconnect (W7) harnesses (Ref. FIG. 301/TASK 73-21-00-990-801/FIG. 303/TASK 73-21-00-990-803) (Ref. 73-21-50/73-21-51, WM). Do the harnesses test satisfactorily?
04 Replace the FPMU (Ref. 73-21-10-000-801/73-21-10-400-801, MM). -Yes
| No | R
05 Replace the bad harness (Ref. 76-00-00, MM) (Ref. AMM).
FADEC Discrete: STSFLT (bit 25) / (353 / EILRU) = 1 EFFECTIVITY:ALL
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FADEC Discrete: AVSFLT (bit 26) / (353 / EILRU) = 1 DESCRIPTION: The FADEC does a test for open and shorted conditions on the circuit for the air-vent solenoid (AVS) coil in the fuel pump-and-metering unit (FPMU). The FADEC also monitors its driver voltage for the coil, to find if it is correct for the commanded AVS position. This discrete is set to 1 (fault sensed) when one or both of these tests are failed. This message can be incorrectly set if aircraft power to the FADEC is momentarily lost.
POSSIBLE CAUSES: 1. FADEC power supply interruption 2. Harness (W11/14, W7) 3. FPMU 4. FADEC 5. Incorrect FPMU installation (AE3007A1E engines)
01 Interchange the position of the FADECs (Ref. 73-25-10-000-801/73-25-10-400-801, MM). Move the FADEC reset/select switch to the RESET position. Does the fault move to the opposite channel?
04 Replace the FADEC that has the fault (Ref. 73-25-10-000-801/73-25-10-400-801, -Yes MM).
| No 02 For AE3007A1E engines: Cycle power to 05 Verify that the correct FPMU for this engine FADECs and check central maintenance is installed. Change the FPMU if necessary -Yes computer (CMC) label 353 bit 26 (AVS FLT). Is (Ref. 73-21-10-000-801/73-21-10-400-801, AVS FLT=1? MM). | No | 03 Do a test for continuity/resistance (1 max./harness), internal shorts, and shorts to ground (1,000 min.) on the external FADEC A/B (W11/14) and the FADEC/engine interconnect (W7) harnesses (Ref. FIG. 301/TASK 73-21-00-990-801/FIG. 303/TASK 73-21-00-990-803) (Ref. 73-21-50/73-21-51, WM). Do the harnesses test satisfactorily?
06 Replace the FPMU (Ref. 73-21-10-000-801/73-21-10-400-801, MM). -Yes
| No | 07 Replace the bad harness (Ref. 76-00-00, MM) (Ref. AMM).
FADEC Discrete: AVSFLT (bit 26) / (353 / EILRU) = 1 R EFFECTIVITY:FADEC SOFTWARE VER. B5.1.1
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FADEC Discrete: FPSNOK (bit 26) / (353 / EILRU) = 1 DESCRIPTION: This discrete is set to 1 (fault sensed) when the FADEC's channels cannot find the hardware stardard of the FPMU. There are two possible FPMU hardware standards: a high flow FPMU, and a low flow FPMU.
POSSIBLE CAUSES: 1. FADEC power supply interruption 2. Harness (W11/14, W7) 3. FPMU 4. FADEC 5. Incorrect FPMU installation (AE3007A1E engines)
01 For AE3007A1E engines: Cycle power to FADECs and check central maintenance computer (CMC)(Ref. Introduction) label 353 bit 26 (FPSNOK). Is FPSNOK=1?
05 Verify that the correct FPMU for this engine is installed. Replace the FPMU if necessary -Yes (Ref. 73-21-10-000-801/73-21-10-400-801, MM).
| No | 02 Interchange the position of the FADECs (Ref. 73-25-10-000-801/73-25-10-400-801, MM). Move the FADEC reset/select switch to the RESET position. Does the fault move to the opposite channel?
-Yes
04 Replace the FADEC that has the fault (Ref. 73-25-10-000-801/73-25-10-400-801, MM).
| No 03 Do a test for continuity/resistance (1 max./harness), internal shorts, and shorts to ground (1,000 min.) on the external FADEC A/B (W11/14) and the FADEC/engine interconnect (W7) harnesses (Ref. FIG. 301/TASK 73-21-00-990-801/FIG. 303/TASK 73-21-00-990-803) (Ref. 73-21-50/73-21-51, WM). Do the harnesses test satisfactorily?
06 Replace the FPMU (Ref. 73-21-10-000-801/73-21-10-400-801, MM). -Yes
| No | 07 Replace the bad harness (Ref. 76-00-00, MM) (Ref. AMM).
FADEC Discrete: FPSNOK (bit 26) / (353 / EILRU) = 1 EFFECTIVITY:FADEC SOFTWARE VER. B7.5 OR LATER
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FADEC Discrete: MMVPFT (bit 15), MMVCFT (bit 14) / (354 / CFPLRU) = 1 DESCRIPTION: The FADEC monitors the position of the main metering valve (MMV) during an engine start. These discretes are set to 1 (fault sensed) when the FADEC finds the MMV is not in the prime (MMVPFT) or closed (MMVCFT) position, as commanded. The FADEC will not do these tests if the MMV position sensor has a fault, or an engine shutdown sequence has started.
POSSIBLE CAUSES: 1. FPMU 2. FADEC
01 Interchange the position of the FADECs (Ref. 73-25-10-000-801/73-25-10-400-801 MM). Move the FADEC reset/select switch to the RESET position. Does the fault move to the opposite channel?
02 Replace the FADEC that has the fault (Ref. 73-25-10-000-801/73-25-10-400-801 -Yes MM).
| No |
03 Replace the FPMU (Ref. 73-21-10-000-801/73-21-10-400-801 MM).
FADEC Discrete: MMVPFT (bit 15), MMVCFT (bit 14) / (354 / CFPLRU) = 1 EFFECTIVITY:ALL
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FADEC Discrete: MMVTFT (bit 16) / (354 / CFPLRU) = 1 DESCRIPTION: The FADEC in control monitors the position of the main metering valve (MMV). This discrete is set to 1 (fault sensed) when the FADEC finds the MMV is not moving to the position commanded. The FADEC will not do this test if the MMV position sensor has a fault, or an engine shutdown sequence has started.
POSSIBLE CAUSES: 1. FPMU 2. Harness (W11/14, W7) 3. FADEC
01 Operate the engine (Ref. AMM). Do not remove electrical power from the FADECs. Access FADEC discrete label 354 from the central maintenance computer (CMC) for both FADECs (Ref. Introduction). Does MMVTFT (bit 16) = 1?
05 Replace the FPMU (Ref. 73-21-10-000-801/73-21-10-400-801 MM). -Yes
| No
R R R
02 Do a test for continuity/resistance (1 ohm max./harness), internal shorts, and shorts to ground (1,000 ohms min.) on the MMV torquemotor circuit for the external FADEC A/B (W11/14) and the FADEC/engine interconnect (W7) harnesses (Ref. FIG. 301/TASK 73-21-00-990-801/FIG. 303/TASK 73-21-00-990-803) (Ref. 73-21-50/73-21-51 WM). Do the harnesses test satisfactorily?
06 Replace the harness that has the fault (Ref. 76-00-00 MM) (Ref. 20-50-00 WM). -No
| Yes 03 Go to Block 04
FADEC Discrete: MMVTFT (bit 16) / (354 / CFPLRU) = 1 EFFECTIVITY:ALL
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04 Interchange the position of the FADECs 07 Replace the FADEC that has the fault (Ref. 73-25-10-000-801/73-25-10-400-801 (Ref. 73-25-10-000-801/73-25-10-400-801 MM). Move the FADEC reset/select switch to MM). the RESET position. Operate the engine (Ref. -Yes AMM). Do not remove electrical power from the FADECs. Does the fault move to the opposite channel? | No |
08 Replace the FPMU (Ref. 73-21-10-000-801/73-21-10-400-801 MM).
FADEC Discrete: MMVTFT (bit 16) / (354 / CFPLRU) = 1 EFFECTIVITY:ALL
TASK 73−21−00−810−809 Page 202 Aug 15/04
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FADEC Discrete: CVGTFT (bit 18) / (354 / CFPLRU) = 1 DESCRIPTION: The FADEC in control monitors the position of the compressor variable-geometry (CVG) actuator. This discrete is set to 1 (fault sensed) when the FADEC finds the CVG piston is not moving to the position commanded. The FADEC will not do this test if the CVG position sensor has a fault, an engine shutdown sequence has started, or N2 is less than 56%.
POSSIBLE CAUSES: 1. Harness (W11/14, W7) 2. Harness (W11/14, W7) 3. CVG actuator 4. FADEC
R R R
01 Do a test for continuity/resistance (1 ohm max./harness), internal shorts, and shorts to ground (1,000 ohms min.) on the CVG torquemotor circuit for the external FADEC A/B (W11/14) and the FADEC/engine interconnect (W7) harnesses (Ref. FIG. 301/TASK 73-21-00-990-801/FIG. 303/TASK 73-21-00-990-803) (Ref. 73-21-50/73-21-51 WM). Do the harnesses test satisfactorily?
05 Replace the harness that has the fault (Ref. 76-00-00 MM) (Ref. 20-50-00 WM). -No
| Yes 02 Interchange the position of the FADECs 06 Replace the FADEC that has the fault (Ref. 73-25-10-000-801/73-25-10-400-801 (Ref. 73-25-10-000-801/73-25-10-400-801 MM). Rotate the FADEC reset/select switch to MM). the RESET position. Operate the engine (Ref. AMM). Do not remove electrical power from -Yes the FADECs. Does the fault move to the opposite channel (the FADEC for the opposite channel must be selected as the controlling FADEC for this discrete to = 1)? | No 03 Go to Block 04
FADEC Discrete: CVGTFT (bit 18) / (354 / CFPLRU) = 1 EFFECTIVITY:ALL
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04 Replace the FPMU (Ref. 07 Remove the FPMU from service. 73-21-10-000-801/73-21-10-400-801 MM). Rotate the FADEC reset/select switch to the RESET position. Operate the engine (Ref. AMM). Do not remove electrical power from -Yes the FADECs. Access FADEC discrete label 354 from the central maintenance computer (CMC) (Ref. Introduction). Does CVGTFT (bit 18) = 1? | No |
08 Replace the CVG actuator (Ref. 75-33-10-000-801/75-33-10-400-801 MM).
FADEC Discrete: CVGTFT (bit 18) / (354 / CFPLRU) = 1 EFFECTIVITY:ALL
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FADEC Discrete: PRVFLT (bit 24) / (354 / CFPLRU) = 1 DESCRIPTION: The FADEC in control monitors the position of the pressure raising valve (PRV), in the fuel pump-and-metering unit (FPMU), during an engine shutdown. This discrete is set to 1 (fault sensed) when the FADEC finds that the control circuit for the stop coil of the latching shutoff valve is in its commanded condition, but N2 rpm is above 56%. This is an indication that the PRV is not closing, and stopping fuel flow to the engine. The FADEC stops fuel flow by closing the main metering valve when the PRV has failed.
POSSIBLE CAUSES: 1. FPMU 2. FADEC
01 Interchange the position of the FADECs 02 Replace the FADEC that has the fault (Ref. 73-25-10-000-801/73-25-10-400-801 (Ref. 73-25-10-000-801/73-25-10-400-801 MM). Rotate the FADEC reset/select switch to MM). the RESET position. Operate the engine (Ref. -Yes AMM). Do not remove electrical power from the FADECs. Does the fault move to the opposite channel? | No |
03 Replace the FPMU (Ref. 73-21-10-000-801/73-21-10-400-801 MM).
FADEC Discrete: PRVFLT (bit 24) / (354 / CFPLRU) = 1 EFFECTIVITY:ALL
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FADEC Discrete: MMVFBD (bit 23) / (357 / EIDIF) = 1 DESCRIPTION: R
This discrete is set to 1 (fault sensed) when the signal received from the main-metering valve (MMV) position sensor for this FADEC is different (more than 0.040 in. (1.02 mm)) from that received by the other FADEC. This test is not done if either channel's MMV position sensor or the cross-channel data link fault discretes are set to 1.
POSSIBLE CAUSES: R
R R R R
1. Harness (W11/14, W7) 2. FPMU 3. FADEC
01 Remove and install the harness connectors at the FADEC J4 receptacles, the firewall and the FPMU (Ref. FIG. 301/TASK 73-21-00-990-801/FIG. 303/TASK 73-21-00-990-803). Rotate the FADEC reset/select switch to the RESET position. Access label 357 from the central maintenance computer (CMC) for both FADECs. Does MMVFBD (bit 23) = 1?
06 Examine all the harness connectors between the FADEC J4 receptacles and the FPMU for damage, corrosion, or contamination (Ref. FIG. 301/TASK 73-21-00-990-801/FIG. -No 303/TASK 73-21-00-990-803). Repair or clean the connectors as necessary (Ref. 70-00-00-910-804, MM).
| Yes
R
02 Access the FADEC analog label from the CMC for both FADECs. Is MMVPOS different, by more than 0.040 in. (1.02 mm)?
07 Replace the FADEC showing MMVFBD -No (bit 23) = 1 (Ref. 73-25-10-000-801/73-25-10-400-801, MM).
| Yes R R
03 Interchange the position of the FADECs 08 Replace the FADEC showing the MMVPOS (Ref. 73-25-10-000-801/73-25-10-400-801, with the greatest difference, compared to the MM). Move the FADEC reset/select switch to other three values (including the other engine) the RESET position. Does the fault move to (Ref. 73-25-10-000-801/73-25-10-400-801, -Yes the opposite channel (the FADEC for the MM). opposite channel must be selected as the controlling FADEC for this message to be set)? | No 04 Go to Block 05
FADEC Discrete: MMVFBD (bit 23) / (357 / EIDIF) = 1 EFFECTIVITY:ALL
TASK 73−21−00−810−812 Page 201 Aug 15/04
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R R R R R
05 Do a test for continuity/resistance (1 ohm max./harness), internal shorts, and shorts to ground (1,000 ohms min.) on the external FADEC A/B (W11/14) and the FADEC/engine interconnect (W7) harnesses (Ref. FIG. 301/TASK 73-21-00-990-801/FIG. 303/TASK 73-21-00-990-803) (Ref. 73-21-50/73-21-51, WM). Do the harnesses test satisfactorily?
09 Replace the harness that has the fault (Ref. 76-00-00, MM)(Ref. AMM). -No
| Yes |
R
10 Replace the FPMU (Ref. 73-21-10-000-801/73-21-10-400-801, MM).
FADEC Discrete: MMVFBD (bit 23) / (357 / EIDIF) = 1 EFFECTIVITY:ALL
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FADEC Discrete: MMVDLF (bit 28) / (360 / FADLRU) = 1 DESCRIPTION: The standby FADEC does a test for open and shorted conditions on the circuit for the main-metering valve (MMV) torquemotor located in the fuel pump-and-metering unit (FPMU). The FADEC also monitors the driver voltage for the MMV torquemotor, to find if it is correct for the fuel flow commanded. This discrete is set to 1 (fault sensed) when one or both of these tests have failed.
POSSIBLE CAUSES: R
R
1. Harness (W11/14, W7) 2. FPMU 3. FADEC
01 Interchange the position of the FADECs (Ref. 73-25-10-000-801/73-25-10-400-801, MM). Rotate the FADEC reset/select switch to the RESET position. Does the fault move to the opposite channel (the FADEC for the opposite channel must be selected as the standby FADEC for this message to be set).
-Yes
03 Replace the FADEC that has the fault (Ref. 73-25-10-000-801/73-25-10-400-801, MM).
| No R R R R R
02 Do a test for continuity/resistance (1 ohm max./harness), internal shorts, and shorts to ground (1,000 ohms min.) on the external FADEC A/B (W11/14) and the FADEC/engine interconnect (W7) harnesses (Ref. FIG. 301/TASK 73-21-00-990-801/FIG. 303/TASK 73-21-00-990-803) (Ref. 73-21-50/73-21-51, WM). Do the harnesses test satisfactorily?
04 Replace the FPMU (Ref. 73-21-10-000-801/73-21-10-400-801, MM). -Yes
| No |
R
05 Replace the harness that has the fault (Ref. 76-00-00, MM) (Ref. AMM).
FADEC Discrete: MMVDLF (bit 28) / (360 / FADLRU) = 1 EFFECTIVITY:ALL
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FADEC Discrete: CVGDLF (bit 29) / (360 / FADLRU) = 1 DESCRIPTION: The standby FADEC does a test for open and shorted conditions on the circuit for the compressor variable-geometry (CVG) torquemotor located in the fuel pump-and-metering unit (FPMU). The FADEC also monitors the driver voltage for the CVG torquemotor, to find if it is correct for the commanded CVG actuator position. This discrete is set to 1 (fault sensed) when one or both of these tests have failed.
POSSIBLE CAUSES: R
R
1. Harness (W11/14, W7) 2. FPMU 3. FADEC
01 Interchange the position of the FADECs (Ref. 73-25-10-000-801/73-25-10-400-801, MM). Rotate the FADEC reset/select switch to the RESET position. Does the fault move to the opposite channel (the FADEC for the opposite channel must be selected as the standby FADEC for this message to be set)?
-Yes
03 Replace the FADEC that has the fault (Ref. 73-25-10-000-801/73-25-10-400-801, MM).
| No R R R R R
02 Do a test for continuity/resistance (1 ohm max./harness), internal shorts, and shorts to ground (1,000 ohms min.) on the external FADEC A/B (W11/14) and the FADEC/engine interconnect (W7) harnesses (Ref. FIG. 301/TASK 73-21-00-990-801/FIG. 303/TASK 73-21-00-990-803) (Ref. 73-21-50/73-21-51, WM). Do the harnesses test satisfactorily?
04 Replace the FPMU (Ref. 73-21-10-000-801/73-21-10-400-801, MM). -Yes
| No |
R
05 Replace the harness that has the fault (Ref. 76-00-00, MM) (Ref. AMM).
FADEC Discrete: CVGDLF (bit 29) / (360 / FADLRU) = 1 EFFECTIVITY:ALL
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Observed Fault: FPMU Seal Drain Accumulation DESCRIPTION: The fuel pump-and-metering unit (FPMU) has an integral drain cavity. This cavity allows the fuel leakage past the magnetic carbon seal, on the gear-pump drive shaft, and/or the oil leakage past the magnetic carbon seal, on the FPMU gearshaft (in the accessory drive gearbox (AGB)), to accumulate and be drained. A tube connects the FPMU drain cavity to a drain sight-glass, located below the AGB.
POSSIBLE CAUSES: 1. AGB magnetic carbon seal 2. FPMU 3. FPMU magnetic seal assembly
R R R R R R
01 Operate the engine at ground idle for a minimum of five minutes before you do the leakage inspection or you will get an incorrect leakage indication (Ref. TASK 72-00-00-700-801). Does engine oil accumulate in the sight-glass at a rate of more than 0.15 cc or three drops in three minutes?
03 Examine the magnetic carbon seal, O-ring and the retaining ring in the AGB (Ref. 72-63-10-000-802/72-63-10-400-802 MM). -Yes Replace any damaged components. Go to task 72-00-00-700-801 MM, TABLE 502 for oil leakage rate limits.
| No R R
02 Does fuel accumulate in the sight-glass at a 04 Replace the FPMU magnetic seal rate of more than 0.51 cc or 10 drops in three assembly (Ref. minutes? -Yes 73-21-10-000-803/73-21-10-400-803 MM) or the FPMU (Ref. 73-21-10-000-801/73-21-10-400-801 MM). | No |
R
05 Up to 0.51 cc or 10 drops in three minutes is an allowable leakage rate. Continue to monitor the sight-glass for an increase in the leakage rate.
Observed Fault: FPMU Seal Drain Accumulation EFFECTIVITY:ALL
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FADEC Discrete: MMVFIX (bit 21) / (354 / CFPLRU) = 1 DESCRIPTION: This discrete is set to 1 (fault sensed) when there is no valid signal to the FADEC-in-control from the main-metering-valve (MMV) position sensor, in the fuel pump-and-metering unit (FPMU). The MMV will stay in the last controlled position and the engine thrust will not change with thrust lever movement.
POSSIBLE CAUSES: 1. FPMU 2. Harness 3. FADEC
01 Supply electrical power to the aircraft. Access FADEC discrete label 357 from the central maintenance computer (CMC) (Ref. Introduction). Is MMVFBD (bit 23) = 1?
-Yes
03 Do the troubleshooting for MMVFBD (bit 23) = 1 (Ref. 73-21-00-810-812).
| No R R R R
02 Access FADEC discrete label 353 and 355 04 Do the troubleshooting for MMVFBF (bit from the CMC, and the maintenance messages 19) = 1 (Ref. 73-21-00-810-802). (Ref. Introduction). Does MMVFBF (label 353, -Yes bit 19) = 1, and does CHNFLT (label 355, bit 15) =1? | No |
05 Replace the FADEC showing MMVFIX (bit 21) =1 (Ref. 73-25-10-000-801/73-25-10-400-801 MM).
FADEC Discrete: MMVFIX (bit 21) / (354 / CFPLRU) = 1 EFFECTIVITY:ALL
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EICAS Message:: E1/E2 CTL FAIL (set by FADEC Discrete: MMCVFL (bit 28) / (356 / SFLTS2) = 1) DESCRIPTION: This message occurs when the FADEC detects that the other FADEC is incapable and one of the following faults has been set, the master metering valve (MMV) has failed fixed or the CVG has failed open. The MMV failed fixed (MMVFIX) fault occurs when the MMV tracking test has failed and the other FADEC is incapable. The CVG failed open (CVGFOF) fault occurs when the CVG tracking test is failed and the other FADEC is incapable and CVG feedback (CVGFB) position is greater than 1.75 inches (44.5 mm). NOTE: If the FADECs have been de-energized prior to troubleshooting, the engine must be run at the maximum power setting to duplicate the fault. Do not remove power to the FADECs prior to troubleshooting or troubleshooting will be unsuccessful.
POSSIBLE CAUSES: 1. FPMU 2. Compressor variable geometry (CVG) actuator 3. FADEC 4. Harness
01 Has power to the FADECs been removed since the last engine run ?
04 Operate the engine at the maximum thrust practical (Ref. AMM). Do not remove power to -Yes the aircraft and do the fault isolation procedure again.
| No 02 Access FADEC discrete label 354 from the 05 Do the troubleshooting for MMVFIX (bit 21) central maintenance computer (CMC) for both (Ref. 73-21-00-810-816). -Yes FADECs (Ref. Introduction). Does MMVFIX (bit 21) = 1 ? | No 03 Does CVGTFT (bit 18) = 1 ?
-Yes
06 Do the troubleshooting for CVGTFT (bit 18) (Ref. 73-21-00-810-810).
| No |
R
07 Examine all of the harness connectors between the FPMU, the CVG actuator, and the FADEC for looseness, corrosion, contamination or damage. Tighten, clean, or repair the harness as necessary (Ref. 70-00-00-910-804 MM).
EICAS Message:: E1/E2 CTL FAIL (set by FADEC Discrete: MMCVFL (bit 28) / (356 / SFLTS2) = 1) R EFFECTIVITY:FADEC SOFTWARE VER. B5.1.1, R B7.5 and B7.6
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EICAS Message:: E1/E2 CTL FAIL (set by FADEC Discrete: MMCVFL (bit 28) / (356 / SFLTS2) = 1) DESCRIPTION: This message occurs when the FADEC detects that the other FADEC is incapable and one of the following faults has been set, A High N1 Failure (HIN1FG), the main metering valve (MMV) has failed fixed or the CVG has failed open. A high N1 failure occurs when there is an uncommmanded speed increase. The MMV failed fixed (MMVFIX) fault occurs when the MMV tracking test has failed and the other FADEC is incapable. The CVG failed open (CVGFOF) fault occurs when the CVG tracking test is failed and the other FADEC is incapable and CVG feedback (CVGFB) position is greater than 1.75 inches (44.5 mm). NOTE: If the FADECs have been de-energized prior to troubleshooting, the engine must be run at the maximum power setting to duplicate the fault. Do not remove power to the FADECs prior to troubleshooting or troubleshooting will be unsuccessful.
POSSIBLE CAUSES: 1. FPMU 2. Compressor variable geometry (CVG) actuator 3. FADEC 4. Harness
01 Has power to the FADECs been removed since the last engine run ?
06 Operate the engine at the maximum thrust practical (Ref. AMM). Do not remove power to -Yes the aircraft and do the fault isolation procedure again.
| No 02 Access FADEC discrete label 354 from the 07 Do the troubleshooting for MMVFIX (bit 21) central maintenance computer (CMC) for both (Ref. 73-21-00-810-816). -Yes FADECs (Ref. Introduction). Does MMVFIX (bit 21) = 1 ? | No 03 Access Label 354 from the central 08 Do the troubleshooting for HIN1FG (bit 27) maintenance computer (CMC) for both (Ref. 73-21-00-810-823). -Yes FADECs (Ref. Introduction). Does HIN1FG (bit 27) =1? | No 04 Go to block 05.
EICAS Message:: E1/E2 CTL FAIL (set by FADEC Discrete: MMCVFL (bit 28) / (356 / SFLTS2) = 1) EFFECTIVITY:FADEC SOFTWARE VER. B8.0 OR LATER
TASK 73−21−00−810−817−B01 Page 201 Oct 15/05
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05 Access FADEC discrete label 354 from the 09 Do the troubleshooting for CVGTFT (bit 18) central maintenance computer (CMC) for both (Ref. 73-21-00-810-810). -Yes FADECs (Ref. Introduction). Does CVGTFT (bit 18) = 1 ? | No |
10 Examine all of the harness connectors between the FPMU, the CVG actuator, and the FADEC for looseness, corrosion, contamination or damage. Tighten, clean, or repair the harness as necessary (Ref. 70-00-00-910-804 MM).
EICAS Message:: E1/E2 CTL FAIL (set by FADEC Discrete: MMCVFL (bit 28) / (356 / SFLTS2) = 1) EFFECTIVITY:FADEC SOFTWARE VER. B8.0 OR LATER
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Maintenance Message: LT-ENG1/ENG2 MMV / WF SYS DESCRIPTION: This message occurs when the FADEC finds a fault in the fuel pump-and-metering unit (FPMU) or the FADEC control circuits for the FPMU. This message can be incorrectly set if aircraft power to the FADEC is momentarily lost.
POSSIBLE CAUSES: 1. FADEC power supply interruption 2. Harness 3. FPMU 4. FADEC
01 Supply electrical power to the aircraft. 04 Do the troubleshooting for SOSFLT (bit 24) Access FADEC discrete label 353 from the = 1 (Ref. 73-21-00-810-805). central maintenance computer (CMC) for both -Yes FADECs (Ref. Introduction). Does SOSFLT (bit 24) = 1? | No 02 Access FADEC discrete label 357 from the 05 Do the troubleshooting for MMVFBD (bit CMC for both FADECs (Ref. Introduction). -Yes 23) = 1 (Ref. 73-21-00-810-812). Does MMVFBD (bit 23) = 1? | No 03 Operate the engine to the maximum thrust practical and do a normal shutdown (Ref. AMM). Do not remove electrical power from the FADECs. Do the procedure again. Are any faults found?
06 Do the troubleshooting for the faults found. -Yes
| No |
R R
07 Examine all of the harness connectors between the FPMU and the FADEC J4 receptacle for looseness, corrosion, contamination or damage (Ref. FIG. 303/TASK 73-21-00-990-803) (Ref. 73-21-50/73-21-51 WM). Tighten, clean, or repair the harness as necessary (Ref. 70-00-00-910-804 MM).
Maintenance Message: LT-ENG1/ENG2 MMV / WF SYS EFFECTIVITY:ALL
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Maintenance Message: ND-ENG1/ENG2 SOI SYS (set by FADEC Discrete: SOIBLF (bit 25) / (352/AILRUZ) = 1) DESCRIPTION: This message occurs when this FADEC has detected a shutoff interlock fault (label 360, bit 11) and, either a shutoff interlock fault has been detected in the other FADEC or a cross-channel data link (CCDL) fault has been detected.
POSSIBLE CAUSES: 1. FADEC 2. CCDL 3. FPMU
01 Supply electrical power to the aircraft. Access FADEC discrete label 354 from the central maintenance computer (CMC) for both FADECs (Ref. Introduction). Does XTLKFT (bit 11) = 1 for either FADEC?
-Yes
03 Do the troubleshooting for XTLKFT (bit 11) = 1 (Ref. 77-40-00-810-803, block 02).
| No 02 Access FADEC discrete label 360 from the 04 Do the troubleshooting for FADEC discrete CMC for both FADECs (Ref. Introduction). -Yes SOIFLT (bit 11) = 1 (Ref. 77-40-00-810-804). Does SOIFLT (bit 11) = for either FADEC? | No |
05 Examine all of the harness connectors between the FPMU and the FADEC J4 receptacle (W11, W14, W7 harnesses) for looseness, corrosion, contamination and damage. Tighten, clean or repair the harness as necessary (Ref. 70-00-00-910-804 MM).
Maintenance Message: ND-ENG1/ENG2 SOI SYS (set by FADEC Discrete: SOIBLF (bit 25) / (352/AILRUZ) = 1) EFFECTIVITY:ALL
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Maintenance Message: ND-ENG1/ENG2 PRV SYS DESCRIPTION: This message occurs when the FADEC senses a failure in the control of the pressure raising valve (PRV), inside the fuel pump-and-metering unit (FPMU), to stop fuel flow during engine shutdown. This message can occur during pilot commanded engine in-flight shutdown.
POSSIBLE CAUSES: 1. FPMU 2. FADEC 3. Harness
01 Did the flight crew report a pilot commanded engine in-flight shutdown?
-Yes
07 Go to Block 04
| No 02 Supply electrical power to the aircraft. Access FADEC discrete label 354 from the central maintenance computer (CMC) for both FADECs (Ref. Introduction). Does PRVFLT (bit 24) = 1?
-Yes
08 Do the troubleshooting for FADEC discrete PRVFLT (bit 24) = 1 (Ref. 73-21-00-810-811).
| No 03 Operate the engine and shutdown (Ref. AMM). Do not remove electrical power from the FADECs. Access label 354 from the CMC for both FADECs (Ref. Introduction). Does PRVFLT (bit 24 = 1?
-Yes
09 Do the troubleshooting for FADEC discrete PRVFLT (bit 24) = 1 (Ref. 73-21-00-810-811).
| No |
10 Examine all of the harness connectors between the FPMU and the FADECs (W11, W14, and W7 harnesses) for looseness, corrosion, contamination, or damage. Tighten, clean, or repair the harness as necessary (Ref. 70-00-00-910-804 MM).
Maintenance Message: ND-ENG1/ENG2 PRV SYS EFFECTIVITY:ALL
TASK 73−21−00−810−820 Page 201 Feb 15/03
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04 Record the number of occurrences of this message from the CMC. Operate the engine and shutdown. Does the number of message occurrences increase?
11 This message has been incorrectly set. If the message occurs again during future flights, -No do not remove electrical power from the FADECs and repeat the procedure in Block 04.
| Yes 05 Supply electrical power to the aircraft. Access FADEC discrete label 354 from the central maintenance computer (CMC) for both FADECs (Ref. Introduction). Does PRVFLT (bit 24) = 1
-Yes
12 Do the troubleshooting for FADEC discrete PRVFLT (bit 24) = 1 (Ref. 73-21-00-810-811).
| Yes 06 Operate the engine and shutdown (Ref. AMM). Do not remove electrical power from the FADECs. Access label 354 from the CMC for both FADECs (Ref. Introduction). Does PRVFLT (bit 24 = 1?
-Yes
13 Do the troubleshooting for FADEC discrete PRVFLT (bit 24) = 1 (Ref. 73-21-00-810-811)
| No |
14 Examine all of the harness connectors between the FPMU and the FADECs (W11, W14, and W7 harnesses) for looseness, corrosion, contamination, or damage. Tighten, clean, or repair the harness as necessary (Ref. 70-00-00-910-804 MM).
Maintenance Message: ND-ENG1/ENG2 PRV SYS EFFECTIVITY:ALL
TASK 73−21−00−810−820 Page 202 Feb 15/03
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Maintenance Message: ST-ENG1/ENG2 MMV/CVG SYS DESCRIPTION: This message occurs when the FADEC finds a fault in the fuel pump-and-metering unit (FPMU) or the FADEC control circuits for the FPMU.
POSSIBLE CAUSES: 1. FPMU 2. FADEC/FPMU harness 3. CVG hydraulic actuator 4. FADEC
01 Operate the engine to maximum thrust and 08 Do the troubleshooting for FADEC discrete shutdown (Ref. AMM). Do not remove MMVFBF (bit 19) = 1 (Ref. 73-21-00-810-802). electrical power from the FADECs. Access FADEC discrete label 353 from the central -Yes maintenance computer (CMC) for both FADECs (Ref. Introduction). Does MMVFBF (bit 19) = 1? | No 02 Does MMVTMF (bit 21) = 1?
-Yes
09 Do the troubleshooting for FADEC discrete MMVTMF (bit 21) = 1 (Ref. 73-21-00-810-803).
-Yes
10 Do the troubleshooting for FADEC discrete CVGTMF (bit 22) = 1 (Ref. 73-21-00-810-804).
| No 03 Does CVGTMF (bit 22) = 1? | No 04 Access FADEC discrete label 354 from the 11 Do the troubleshooting for FADEC discrete CMC for both FADECs (Ref. Introduction). MMVCFT (bit 14) = 1 or MMVPFT (bit 15) = 1 -Yes Does MMVCFT (bit 14) or MMVPFT (bit 15) = (Ref. 73-21-00-810-808). 1? | No 05 Go to Block 06.
Maintenance Message: ST-ENG1/ENG2 MMV/CVG SYS EFFECTIVITY:ALL
TASK 73−21−00−810−821 Page 201 Oct 15/05
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06 Does MMVTFT (bit 16) = 1?
-Yes
12 Do the troubleshooting for FADEC discrete MMVTFT (bit 16) = 1 (Ref. 73-21-00-810-809).
-Yes
13 Do the troubleshooting for FADEC discrete CVGTFT (bit 18) = 1 (Ref. 73-21-00-810-810).
| No 07 Does CVGTFT (bit 18) = 1? | No |
14 Examine all of the harness connectors between the FADEC J4 receptacle and the FPMU (W11, W14, and W7 harnesses), for looseness, corrosion, contamination, or damage. Tighten, clean, or repair the harness as necessary (Ref. 73-21-50/73-21-51 WM) (Ref. 70-00-00-910-804 MM).
Maintenance Message: ST-ENG1/ENG2 MMV/CVG SYS EFFECTIVITY:ALL
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R EICAS Message: E1(2) FPMU NO DISP (set by FADEC Discrete FPMNOK (bit 23) / 354 CFPLRU) DESCRIPTION: This message is displayed when an FPMU106 is installed with an A1E thrust rating.
POSSIBLE CAUSES: 1. FPMU 2. FADEC
01 Make sure FPMU part number is a mark 200. Is the FPMU a mark 200?
R
R
04 Replace the FPMU with a mark 200 FPMU -No (Ref. TASK 73-21-10-000-801/73-21-10-400-801, MM).
| Yes 02 Access the FADEC discrete label 354 from the CMC (Ref. Introduction). Does FPMNOK (bit 23) = 1?
-No
05 Return the engine to service.
| Yes 03 Do a test for continuity/resistance (1 ohm 06 Replace the FADEC with the fault (Ref. max./harness), internal shorts, and shorts to TASK 73-25-10-000-801/73-25-10-400-801, ground (1,000 ohms min.) on the external MM). FADEC A/B (W11/14), internal FADEC A/B (W12/13), and the FADEC/engine interconnect -Yes (W7) harnesses (Ref. FIG. 301/TASK 73-21-00-990-801/FIG. 303/TASK 73-21-00-990-803) (Ref. 73-21-50/73-21-51, WM). Do the harnesses test satisfactorily? | No |
07 Replace the harness that has the fault (Ref. 76-00-00, MM).
EICAS Message: E1(2) FPMU NO DISP (set by FADEC Discrete FPMNOK (bit 23) / 354 CFPLRU) R EFFECTIVITY:FADEC SOFTWARE VER. B7.5 OR R LATER
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FADEC Discrete: HIN1FG (bit 27) / (354 / CFPLRU) = 1 DESCRIPTION: This discrete is set to 1 (fault sensed) when an uncommanded N1 speed increase is detected.
POSSIBLE CAUSES: 1. FPMU 2. Harness
01 Replace the FPMU (Ref. 73-21-10-000-801/73-21-10-400-801, MM) and examine all of the harness connectors between the FADEC J4 receptacle and the FPMU (W11, W14 and W7 harnesses), for looseness, corrosion, contamination or damage. Tighten, clean or repair the harness as necessary (Ref. 73-21-50/73-21-51 WM) (Ref. 70-00-00-910-804 MM). | 02 Operate the engine at the maximum thrust 03 Do the troubleshooting for the faults found. practical (Ref. AMM). Do not remove power to -Yes the aircraft and do the fault isolation procedure again. Are there still faults found? | No |
04 Return the engine to service.
FADEC Discrete: HIN1FG (bit 27) / (354 / CFPLRU) = 1 EFFECTIVITY:FADEC SOFTWARE VER. B8.0 OR LATER
TASK 73−21−00−810−823 Page 201/202 Oct 15/05
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Fuel Pump-and-metering Unit/FADEC Interface Diagram FIG. 301/TASK 73-21-00-990-801
R EFFECTIVITY:ALL
73−21−TASK SUPPORT Page 301 Aug 15/04
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CVG Position Sensor (LVDT) / FADEC Interface Diagram FIG. 302/TASK 73-21-00-990-802
R EFFECTIVITY:ALL
73−21−TASK SUPPORT Page 302 Aug 15/04
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Engine Wiring Diagram FIG. 303/TASK 73-21-00-990-803
R EFFECTIVITY:ALL
73−21−TASK SUPPORT Page 303/304 Aug 15/04
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FADEC Discrete: AISIFT (bit 21) / (351 / AILRU1) = 1 DESCRIPTION: The FADEC does a test of the circuit for the anti-ice system-indication switch. This discrete is set to 1 (fault sensed) when an open or shorted circuit is detected.
POSSIBLE CAUSES: 1. Aircraft circuit fault 2. FADEC
R R
01 Disconnect the harness (W1) from the FADEC J2 receptacle (Ref. FIG. 307/TASK 73-25-00-990-807). Examine the harness connector for damage, corrosion, or contamination. Is the connector contaminated or damaged?
07 Clean or repair the connector (Ref. 20-50-00 WM). Rotate the FADEC reset/select switch to the RESET position to remove the -Yes fault (AISIFT (bit 21) = 0).
| No
R R
02 Supply electrical power to the aircraft and do a test for voltage at pin S of the FADEC J2 receptacle (Ref. FIG. 301/TASK 73-25-00-990-801). Is there 12-15 VDC measured?
08 Replace the FADEC that has the fault (Ref. 73-25-10-000-801/73-25-10-400-801 -No MM).
| Yes
R R
03 Make sure the engine air-inlet ice-protection switch is in the ON position (the ice-detection override switch must be in the ALL or ENG position) and do a test for continuity between pins S and b at the W1 harness connector (Ref. FIG. 301/TASK 73-25-00-990-801) (Ref. 30-20-50/30-20-51 WM). Is there continuity, with resistance less than 10 ohms?
-No
09 Repair the aircraft circuit fault (Ref. 30-20-50/30-20-51 WM). Rotate the FADEC reset/select switch to the RESET position to remove the fault (AISIFT (bit 21) = 0).
| Yes 04 Go to block 05.
FADEC Discrete: AISIFT (bit 21) / (351 / AILRU1) = 1 EFFECTIVITY:ALL
TASK 73−25−00−810−802 Page 201 Aug 15/04
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R
05 With the engine air-inlet ice protection switch in the ON position (the ice-detection override switch must be in the ALL or ENG position), do a test for continuity between -Yes ground and pin S at the W1 harness connector (Ref. FIG. 301/TASK 73-25-00-990-801) (Ref. 30-20-50/30-20-51 WM). Is there continuity?
10 Repair the aircraft circuit fault (Ref. 30-20-50/30-20-51 WM). Rotate the FADEC reset/select switch to the RESET position to remove the fault (AISIFT (bit 21) = 0).
| No
R R
06 Make sure that the engine air-inlet ice-protection switch is in the OFF position and do a test for continuity between pins b and S at the W1 harness connector (Ref. FIG. 301/TASK 73-25-00-990-801) (Ref. 30-20-50/30-20-51 WM). Is there continuity, with resistance between 9.5K and 10.5K?
11 Repair the aircraft circuit fault (Ref. 30-20-50/30-20-51 WM). Rotate the FADEC reset/select switch to the RESET position to -No remove the fault (AISIFT (bit 21) = 0).
| Yes |
R
12 Replace the FADEC that has the fault (Ref. 73-25-10-000-801/73-25-10-400-801 MM).
FADEC Discrete: AISIFT (bit 21) / (351 / AILRU1) = 1 EFFECTIVITY:ALL
TASK 73−25−00−810−802 Page 202 Aug 15/04
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FADEC Discrete: AISIDF (bit 21) / (264/ AIDIF1) = 1 DESCRIPTION: The FADECs do a lane difference test of the two anti-ice system-indicator circuits. This fault occurs when the condition of the circuits (ON/OFF) sensed by FADEC A and B is not the same. The FADECs will not do this test if one of the two circuits has a fault.
POSSIBLE CAUSES: 1. Aircraft circuit fault 2. FADEC
R R
01 Disconnect the harness (W1) from the J2 receptacle on both FADECs (Ref. FIG. 307/TASK 73-25-00-990-807). Examine the harness connectors for damage, corrosion, or contamination. Are the connectors contaminated or damaged?
04 Clean or repair the connector (Ref. 20-50-00 WM). Rotate the FADEC reset/select switch to the RESET position to remove the -Yes fault (AISIDF (bit 21) = 0).
| No
R R
02 Disconnect the harness from the switch 05 Repair the aircraft harness fault (Ref. and do a test for continuity between pins b and 30-20-50/30-20-51 WM). Rotate the FADEC S at both W1 harness connectors (Ref. FIG. -Yes reset/select switch to the RESET position to 301/TASK 73-25-00-990-801) (Ref. remove the fault (AISIDF (bit 21) = 0). 30-20-50/30-20-51 WM). Is there continuity? | No 03 Supply electrical power to the aircraft. Access FADEC discrete label 264 from the central maintenance computer (CMC) for both FADECs (Ref. Introduction). Does AISIDF (bit 21) = 1 for both FADECs?
06 Repair the aircraft circuit fault (Ref. 30-20-50/30-20-51 WM). Rotate the FADEC -Yes reset/select switch to the RESET position to remove the fault (AISIDF (bit 21) = 0).
| No |
07 Replace the FADEC that shows AISIDF (bit 21) = 1 (Ref. 73-25-10-000-801/ 73-25-10-400-801 MM).
FADEC Discrete: AISIDF (bit 21) / (264/ AIDIF1) = 1 EFFECTIVITY:ALL
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FADEC Discrete: LGDLFT (bit 20) / (351 / AILRU1) = 1 DESCRIPTION: The FADEC does a test of the circuit for the landing gear down and locked-position switch. This discrete is set to 1 (fault sensed) when an open or shorted circuit is detected.
POSSIBLE CAUSES: 1. Aircraft circuit fault 2. FADEC
R R
01 Disconnect the harness (W1) from the FADEC J2 receptacle (Ref. FIG. 307/TASK 73-25-00-990-807). Examine the harness connector for damage, corrosion or contamination. Is the connector contaminated or damaged?
07 Clean or repair the connector (Ref. 20-50-00 WM). Rotate the FADEC reset/select switch to the RESET position to remove the -Yes fault (LGDLFT (bit 20) = 0).
| No
R R
02 Supply electrical power to the aircraft and do a test for voltage at pin S of the FADEC J2 receptacle (Ref. FIG. 302/TASK 73-25-00-990-802) (Ref. 76-12-52/ 76-12-53 WM). Is there 12-15 VDC measured?
08 Replace the FADEC that has the fault (Ref. 73-25-10-000-801/73-25-10-400-801 -No MM).
| Yes
R R
03 Make sure the switch is in the down & locked position and do a test for continuity between pins S and p at the W1 harness connector (Ref. FIG. 302/TASK 73-25-00-990-802) (Ref. 76-12-52/ 76-12-53 WM). Is there continuity, with resistance less than 10 ohms?
09 Repair the aircraft circuit fault (Ref. 76-12-52/76-12-53 WM). Rotate the FADEC reset/select switch to the RESET position to -No remove the fault (LGDLFT (bit 20) = 0).
| Yes 04 Go to Block 05
FADEC Discrete: LGDLFT (bit 20) / (351 / AILRU1) = 1 EFFECTIVITY:ALL
TASK 73−25−00−810−805 Page 201 Aug 15/04
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R
05 With the switch in the down & locked 10 Repair the aircraft circuit fault (Ref. position, do a test for continuity between 76-12-52/76-12-53 WM). Rotate the FADEC ground and pin S at the W1 harness connector -Yes reset/select switch to the RESET position to (Ref. FIG. 302/TASK 73-25-00-990-802) (Ref. remove the fault (LGDLFT (bit 20) = 0). 76-12-52/76-12-53 WM). Is there continuity? | No
R R
06 Make sure that the switch is in the NOT down & locked position and do a test for continuity between pins p and S at the W1 harness connector (Ref. FIG. 302/TASK 73-25-00-990-802) (Ref. 76-12-52/76-12-53 WM). Is there continuity, with resistance between 9.5K and 10.5K ohms?
-Yes
11 Replace the FADEC that has the fault (Ref. 73-25-10-000-801/73-25-10-400-801 MM).
| No |
12 Repair the aircraft circuit fault (Ref. 76-12-52/76-12-53 WM). Rotate the FADEC reset/select switch to the RESET position to remove the fault (LGDLFT (bit 20) = 0)
FADEC Discrete: LGDLFT (bit 20) / (351 / AILRU1) = 1 EFFECTIVITY:ALL
TASK 73−25−00−810−805 Page 202 Aug 15/04
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FADEC Discrete: LGDLDF (bit 20) / (264 / AIDIF1) = 1 DESCRIPTION: R R
The FADECs does a lane difference test of the two landing gear down and locked-position switch circuits. This fault occurs when the condition of the circuits (Down & Locked/Not Down & Locked) sensed by the FADEC A and B is not the same. The FADECs will not do this test if one of the two circuits has a fault.
POSSIBLE CAUSES: 1. Aircraft circuit fault 2. FADEC
01 Disconnect the harness (W1) from the J2 receptacles on both FADECs. Examine the harness connectors for damage, corrosion, or contamination. Are the connectors contaminated or damaged?
04 Clean or repair the connector (Ref. 20-50-00 WM). Rotate the FADEC reset/select -Yes switch to the RESET position to remove the fault (LGDLDF (bit 20) = 0).
| No
R R
02 Disconnect the harness from both switches 05 Repair the aircraft harness fault (Ref. and do a test for continuity between pins p and 76-12-52/76-12-53 WM). Rotate the FADEC S at both W1 harness connectors (Ref. FIG. -Yes reset/select switch to the RESET position to 302/TASK 73-25-00-990-802) (Ref. remove the fault (LGDLDF (bit 20) = 0). 76-12-52/76-12-53 WM). Is there continuity? | No 03 Supply electrical power to the aircraft. 06 Repair the aircraft circuit fault (Ref. Access FADEC discrete label 264 from the 76-12-52/76-12-53 WM). Rotate the FADEC central maintenance computer (CMC) for both -Yes reset/select switch to the RESET position to FADECs (Ref. Introduction). Does LGDLDF = remove the fault (LGDLDF (bit 20) = 0). 1 for both FADECs? | No |
07 Replace the FADEC that shows LGDLDF (bit 20) = 1 (Ref. 73-25-10-000-801/ 73-25-10-400-801 MM).
FADEC Discrete: LGDLDF (bit 20) / (264 / AIDIF1) = 1 EFFECTIVITY:ALL
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FADEC Discrete: ALTFSF (bit 11) / (352 / AILRU2) = 1 DESCRIPTION: The FADEC does a test of the circuit for the FADEC alternate-select switch. This discrete is set to 1 (fault sensed) when an open or shorted circuit is detected.
POSSIBLE CAUSES: 1. Aircraft circuit fault 2. FADEC
R R
01 Disconnect the harness (W1) from the FADEC J2 receptacle (Ref. FIG. 307/TASK 73-25-00-990-807). Examine the harness connector for damage, corrosion, or contamination. Is the connector contaminated or damaged?
07 Clean or repair the connector (Ref. 20-50-00 WM). Rotate the FADEC reset/select switch to the RESET position to remove the -Yes fault (ALTFSF (bit 11) = 0).
| No
R R
02 Supply electrical power to the aircraft and do a test for voltage at pin P of the FADEC J2 receptacle (Ref. FIG. 303/TASK 73-25-00-990-803) (Ref. 74-10-50/ 74-10-51 WM). Is there 12-15 VDC measured?
-No
08 Replace the FADEC that has the fault (Ref. 73-25-10-000-801/73-25-10-400-801 MM).
| Yes
R
03 Make sure the switch is held in the ALTN position and do a test for continuity between pins P and T at the W1 harness connector (Ref. FIG. 303/TASK 73-25-00-990-803) (Ref. 74-10-50/74-10-51 WM). Is there continuity, with resistance less than 10 ohms?
09 Repair the aircraft circuit fault (Ref. 76-12-52/76-12-53 WM) (Ref. 74-10-50/74-10-51 WM). Rotate the FADEC -No reset/select switch to the RESET position to remove the fault (ALTFSF (bit 11) = 0).
| Yes 04 Go to Block 05
FADEC Discrete: ALTFSF (bit 11) / (352 / AILRU2) = 1 EFFECTIVITY:ALL
TASK 73−25−00−810−807 Page 201 Aug 15/04
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R R
05 With the switch held in the ALTN position, 10 Repair the aircraft circuit fault (Ref. do a test for continuity between ground and pin 76-12-52/76-12-53 WM) (Ref. P at the W1 harness connector (Ref. FIG. -Yes 74-10-50/74-10-51 WM). Rotate the FADEC 303/TASK 73-25-00-990-803) (Ref. reset/select switch to the RESET position to 74-10-50/74-10-51 WM). Is there continuity? remove the fault (ALTFSF (bit 11) = 0). | No
R
06 Make sure the switch is not in the ALTN position and do a test for continuity between pins T and P at the W1 harness connector (Ref. FIG. 303/TASK 73-25-00-990-803) (Ref. 74-10-50/74-10-51 WM). Is there continuity, with resistance between 9.5K and 10.5K ohms?
11 Repair the aircraft circuit fault (Ref. 76-12-52/76-12-53 WM) (Ref. 74-10-50/74-10-51 WM). Rotate the FADEC -No reset/select switch to the RESET position to remove the fault (ALTFSF = 0).
| Yes |
12 Replace the FADEC that has the fault (Ref. 73-25-10-000-801/73-25-10-400-801 MM).
FADEC Discrete: ALTFSF (bit 11) / (352 / AILRU2) = 1 EFFECTIVITY:ALL
TASK 73−25−00−810−807 Page 202 Aug 15/04
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FADEC Discrete: FDRFT (bit 29) / (351 / AILRU1) = 1 DESCRIPTION: The FADEC does a test of the circuit for the FADEC reset switch. This discrete is set to 1 (fault sensed) when an open or shorted circuit is detected.
POSSIBLE CAUSES: 1. Aircraft circuit fault 2. FADEC
R R
01 Disconnect the harness (W1) from the FADEC J2 receptacle (Ref. FIG. 307/TASK 73-25-00-990-807). Examine the harness connector for damage, corrosion, or contamination. Is the connector contaminated or damaged?
07 Clean or repair the connector (Ref. 20-50-00 WM). Rotate the FADEC reset/select switch to the RESET position to remove the -Yes fault (FDRFT (bit 29) = 0).
| No
R R
02 Supply electrical power to the aircraft and do a test for voltage at pin P of the FADEC J2 receptacle (Ref. FIG. 303/TASK 73-25-00-990-803) (Ref. 74-10-50/ 74-10-51 WM). Is there 12-15 VDC measured?
08 Replace the FADEC that has the fault (Ref. 73-25-10-000-801/73-25-10-400-801 -No MM).
| Yes
R
03 Make sure the switch is held in the RESET position and do a test for continuity between pins P and U at the W1 harness connector (Ref. FIG. 303/TASK 73-25-00-990-803) (Ref. 74-10-50/74-10-51 WM). Is there continuity, with resistance less than 10 ohms?
09 Repair the aircraft circuit fault (Ref. 76-12-52/76-12-53 WM) (Ref. 74-10-50/74-10-51 WM). Rotate the FADEC -No reset/select switch to the RESET position to remove the fault (FDRFT (bit 29) = 0).
| Yes 04 Go to Block 05
FADEC Discrete: FDRFT (bit 29) / (351 / AILRU1) = 1 EFFECTIVITY:ALL
TASK 73−25−00−810−808 Page 201 Aug 15/04
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R R
05 With the switch held in the RESET position, 10 Repair the aircraft circuit fault (Ref. do a test for continuity between ground and pin 76-12-52/76-12-53 WM) (Ref. P at the W1 harness connector (Ref. FIG. -Yes 74-10-50/74-10-51 WM). Rotate the FADEC 303/TASK 73-25-00-990-803) (Ref. reset/select switch to the RESET position to 74-10-50/74-10-51 WM). Is there continuity? remove the fault (FDRFT (bit 29) = 0). | No
R
06 Make sure the switch is not in the RESET position and do a test for continuity between pins U and P at the W1 harness connector (Ref. FIG. 303/TASK 73-25-00-990-803) (Ref. 74-10-50/74-10-51 WM). Is there continuity, with resistance between 9.5K and 10.5K ohms?
11 Repair the aircraft circuit fault (Ref. 76-12-52/76-12-53 WM) (Ref. 74-10-50/74-10-51 WM). Rotate the FADEC -No reset/select switch to the RESET position to remove the fault (FDRFT (bit 29) = 0).
| Yes |
12 Replace the FADEC that has the fault (Ref. 73-25-10-000-801/73-25-10-400-801 MM).
FADEC Discrete: FDRFT (bit 29) / (351 / AILRU1) = 1 EFFECTIVITY:ALL
TASK 73−25−00−810−808 Page 202 Aug 15/04
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FADEC Discrete: ALTDIF (bit 11) / (265 / AIDIF2) = 1 DESCRIPTION: The FADECs do a lane difference test of the two FADEC alternate-select switch circuits. This fault occurs when the condition of the circuits (Alternate Selected/Not Selected) sensed by FADEC A and B is not the same. The FADECs will not do this test if one of the two circuits has a fault.
POSSIBLE CAUSES: 1. Aircraft circuit fault 2. FADEC
R
01 Disconnect the harness (W1) from the FADEC J2 receptacle on both FADECs (Ref. FIG. 307/TASK 73-25-00-990-807). Examine the harness connector for damage, corrosion, or contamination. Is the connector contaminated or damaged?
06 Clean or repair the connector (Ref. 20-50-00 WM). Rotate the FADEC reset/select switch to the RESET position to remove the -Yes fault (ALTDIF (bit 11) = 0).
| No
R R
02 Disconnect the harness from the switch 07 Repair the aircraft harness fault (Ref. and do a test for continuity between pins P and 76-12-52/76-12-53 WM) (Ref. T at the W1 harness connectors (Ref. FIG. -Yes 74-10-50/74-10-51 WM). Rotate the FADEC 303/TASK 73-25-00-990-803) (Ref. reset/select switch to the RESET position to 74-10-50/74-10-51 WM). Is there continuity? remove the fault (ALTDIF (bit 11) = 0). | No 03 Supply electrical power to the aircraft. 08 Repair the aircraft circuit fault (Ref. Access FADEC discrete label 265 from the 76-12-52/76-12-53 WM) (Ref. central maintenance computer (CMC) for both -Yes 74-10-50/74-10-51 WM). Rotate the FADEC FADECs (Ref. Introduction). Does ALTDIF (bit reset/select switch to the RESET position to 11) = 1 for both FADECs? remove the fault (ALTDIF (bit 11) = 0). | No 04 Go to Block 05
FADEC Discrete: ALTDIF (bit 11) / (265 / AIDIF2) = 1 EFFECTIVITY:ALL
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05 Record the number of occurances for this 09 Repair the aircraft circuit fault (Ref. maintenance message. Make sure the CMC 76-12-52/76-12-53 WM) (Ref. INHIBIT is not selected. Rotate the switch to 74-10-50/74-10-51 WM). Rotate the FADEC the ALTN position (no more than two seconds) reset/select switch to the RESET position to -Yes and release. Access the maintenance remove the fault (ALTDIF (bit 11) = 0). messages from the CMC for both FADECs (Ref. Introduction). Is there a new occurance of the message for both FADECs? | No |
10 Replace the FADEC with the new occurance (Ref. 73-25-10-000-801/ 73-25-10-400-801 MM).
FADEC Discrete: ALTDIF (bit 11) / (265 / AIDIF2) = 1 EFFECTIVITY:ALL
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FADEC Discrete: FDRDIF (bit 29) / (264 / AIDIF1) = 1 DESCRIPTION: The FADECs do a lane difference test of the two FADEC reset switch circuits. This fault occurs when the condition of the circuits (Reset/Not Reset) sensed by FADEC A and B is not the same. The FADECs will not do this test if one of the two circuits has a fault.
POSSIBLE CAUSES: 1. Aircraft circuit fault 2. FADEC
R
01 Disconnect the harness (W1) from the FADEC J2 receptacle on both FADECs (Ref. FIG. 307/TASK 73-25-00-990-807). Examine the harness connector for damage, corrosion, or contamination. Is the connector contaminated or damaged?
06 Clean or repair the connector (Ref. 20-50-00 WM). Rotate the FADEC reset/select switch to the RESET position to remove the -Yes fault (FDRDIF (bit 29) = 0).
| No
R R
02 Disconnect the harness from the switch 07 Repair the aircraft harness fault (Ref. and do a test for continuity between pins P and 76-12-52/76-12-53 WM) (Ref. U at the W1 harness connectors (Ref. FIG. -Yes 74-10-50/74-10-51 WM). Rotate the FADEC 303/TASK 73-25-00-990-803) (Ref. reset/select switch to the RESET position to 74-10-50/74-10-51 WM). Is there continuity? remove the fault (FDRDIF (bit 29) = 0). | No 03 Supply electrical power to the aircraft. Access FADEC discrete label 264 from the central maintenance computer (CMC) for both FADECs (Ref. Introduction). Does FDRDIF (bit 29) = 1 for both FADECs?
08 Repair the aircraft circuit fault (Ref. 76-12-52/76-12-53 WM) (Ref. -Yes 74-10-50/74-10-51 WM). Rotate the FADEC reset/select switch to the RESET position to remove the fault (FDRDIF (bit 29) = 0).
| No 04 Go to Block 05
FADEC Discrete: FDRDIF (bit 29) / (264 / AIDIF1) = 1 EFFECTIVITY:ALL
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05 Record the number of occurances for this 09 Repair the aircraft circuit fault (Ref. maintenance message. Make sure the CMC 76-12-52/76-12-53 WM) (Ref. INHIBIT is not selected. Rotate the switch to 74-10-50/74-10-51 WM). Rotate the FADEC the ALTN position (no more than two seconds) reset/select switch to the RESET position to -Yes and release. Access the maintenance remove the fault (FDRDIF (bit 29) = 0). messages from the CMC for both FADECs (Ref. Introduction). Is there a new occurance of the message for both FADECs? | No |
10 Replace the FADEC with the new occurance (Ref. 73-25-10-000-801/ 73-25-10-400-801 MM).
FADEC Discrete: FDRDIF (bit 29) / (264 / AIDIF1) = 1 EFFECTIVITY:ALL
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FADEC Discrete: TOTIFT (bit 22) / (351 / AILRU1) = 1 DESCRIPTION: The FADEC does a test of the increment circuit for the takeoff data set switch. This discrete is set to 1 (fault sensed) when an open or shorted circuit is detected, or when the circuit is in a closed condition for more than three seconds.
POSSIBLE CAUSES: 1. Aircraft circuit fault 2. FADEC
R R
01 Disconnect the harness (W1) from the FADEC J2 receptacle (Ref. FIG. 307/TASK 73-25-00-990-807). Examine the harness connector for damage, corrosion, or contamination. Is the connector contaminated or damaged?
07 Clean or repair the connector (Ref. 20-50-00 WM). Rotate the FADEC reset/select switch to the RESET position to remove the -Yes fault (TOTIFT (bit 22) = 0).
| No
R R
02 Supply electrical power to the aircraft and do a test for voltage at pin N of the FADEC J2 receptacle (Ref. FIG. 304/TASK 73-25-00-990-804) (Ref. 80-10-50/ 80-10-51 WM). Is there 12-15 VDC measured?
08 Replace the FADEC that has the fault (Ref. 73-25-10-000-801/73-25-10-400-801 -No MM).
| Yes
R R
03 Make sure the switch is in the INC position 09 Repair the aircraft circuit fault (Ref. and do a test for continuity between pins N and 76-12-52/76-12-53 WM). Rotate the FADEC f at the W1 harness connector (Ref. FIG. reset/select switch to the RESET position to -No 304/TASK 73-25-00-990-804) (Ref. remove the fault (TOTIFT (bit 22) = 0). 76-12-52/76-12-53 WM). Is there continuity, with resistance less than 10 ohms? | Yes 04 Go to Block 05
FADEC Discrete: TOTIFT (bit 22) / (351 / AILRU1) = 1 EFFECTIVITY:ALL
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R R
05 With the switch in the INC position, do a 10 Repair the aircraft circuit fault (Ref. test for continuity between ground and pin N at 80-10-50/80-10-51 WM). Rotate the FADEC the W1 harness connector (Ref. FIG. -Yes reset/select switch to the RESET position to 304/TASK 73-25-00-990-804) (Ref. remove the fault (TOTIFT (bit 22) = 0). 80-10-50/80-10-51 WM). Is there continuity? | No
R
06 Make sure the switch is not in the INC position and do a test for continuity between pins N and f at the W1 harness connector (Ref. FIG. 304/TASK 73-25-00-990-804) (Ref. 76-12-52/76-12-53 WM). Is there continuity, with resistance between 9.5K and 10.5K ohms?
11 Repair the aircraft circuit fault (Ref. 76-12-52/76-12-53 WM). Rotate the FADEC reset/select switch to the RESET position to -No remove the fault (TOTIFT (bit 22) = 0).
| Yes |
12 Replace the FADEC that has the fault (Ref. 73-25-10-000-801/73-25-10-400-801 MM).
FADEC Discrete: TOTIFT (bit 22) / (351 / AILRU1) = 1 EFFECTIVITY:ALL
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FADEC Discrete: TOTDFT (bit 23) / (351 / AILRU1) = 1 DESCRIPTION: The FADEC does a test of the decrement circuit for the takeoff data set switch. This discrete is set to 1 (fault sensed) when an open or shorted circuit is detected, or when the circuit is in a closed condition for more than three seconds.
POSSIBLE CAUSES: 1. Aircraft circuit fault 2. FADEC
R R
01 Disconnect the harness (W1) from the FADEC J2 receptacle (Ref. FIG. 307/TASK 73-25-00-990-807). Examine the harness connector for damage, corrosion, or contamination. Is the connector contaminated or damaged?
07 Clean or repair the connector (Ref. 20-50-00 WM). Rotate the FADEC reset/select switch to the RESET position to remove the -Yes fault (TOTDFT (bit 23) = 0).
| No
R R
02 Supply electrical power to the aircraft and do a test for voltage at pin N of the FADEC J2 receptacle (Ref. FIG. 304/TASK 73-25-00-990-804) (Ref. 80-10-50/ 80-10-51 WM). Is there 12-15 VDC measured?
08 Replace the FADEC that has the fault (Ref. 73-25-10-000-801/73-25-10-400-801 -No MM).
| Yes
R R
03 Make sure the switch is in the DEC position 09 Repair the aircraft circuit fault (Ref. and do a test for continuity between pins N and 76-12-52/76-12-53 WM). Rotate the FADEC g at the W1 harness connector (Ref. FIG. reset/select switch to the RESET position to -No 304/TASK 73-25-00-990-804) (Ref. remove the fault (TOTDFT (bit 23) = 0). 76-12-52/76-12-53 WM). Is there continuity, with resistance less than 10 ohms? | Yes 04 Go to Block 05
FADEC Discrete: TOTDFT (bit 23) / (351 / AILRU1) = 1 EFFECTIVITY:ALL
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R R
05 With the switch in the DEC position, do a 10 Repair the aircraft circuit fault (Ref. test for continuity between ground and pin N at 80-10-50/80-10-51 WM). Rotate the FADEC the W1 harness connector (Ref. FIG. -Yes reset/select switch to the RESET position to 304/TASK 73-25-00-990-804) (Ref. remove the fault (TOTDFT (bit 23) = 0). 80-10-50/80-10-51 WM). Is there continuity? | No
R
06 Make sure the switch is not in the DEC position and do a test for continuity between pins N and g at the W1 harness connector (Ref. FIG. 304/TASK 73-25-00-990-804) (Ref. 76-12-52/76-12-53 WM). Is there continuity, with resistance between 9.5K and 10.5K ohms?
11 Repair the aircraft circuit fault (Ref. 76-12-52/76-12-53 WM). Rotate the FADEC reset/select switch to the RESET position to -No remove the fault (TOTDFT (bit 23) = 0).
| Yes |
12 Replace the FADEC that has the fault (Ref. 73-25-10-000-801/73-25-10-400-801 MM).
FADEC Discrete: TOTDFT (bit 23) / (351 / AILRU1) = 1 EFFECTIVITY:ALL
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FADEC Discrete: TOTIDF (bit 22) / (264 / AIDIF1) = 1 DESCRIPTION: The FADECs do a lane difference test of the increment circuits for the takeoff data set switch. This fault occurs when the condition of the circuits (INC/Not INC) sensed by FADEC A and B is not the same. The FADECs will not do this test if one of the two circuits has a fault.
POSSIBLE CAUSES: 1. Aircraft circuit fault 2. FADEC
R
01 Disconnect the harness (W1) from the FADEC J2 receptacle on both FADECs (Ref. FIG. 307/TASK 73-25-00-990-807). Examine the harness connector for damage, corrosion, or contamination. Is the connector contaminated or damaged?
06 Clean or repair the connector (Ref. 20-50-00 WM). Rotate the FADEC reset/select switch to the RESET position to remove the -Yes fault (TOTIDF (bit 22) = 0).
| No
R R
02 Disconnect the harness from the switch 07 Repair the aircraft harness fault (Ref. and do a test for continuity between pins N and 76-12-52/76-12-53 WM) (Ref. f at the W1 harness connectors (Ref. FIG. 80-10-50/80-10-51 WM). Rotate the FADEC -Yes 304/TASK 73-25-00-990-804) (Ref. reset/select switch to the RESET position to 76-12-52/76-12-53 WM) (Ref. remove the fault (TOTIDF (bit 22) = 0). 80-10-50/80-10-51 WM). Is there continuity? | No 03 Supply electrical power to the aircraft. Access FADEC discrete label 264 from the central maintenance computer (CMC) for both FADECs (Ref. Introduction). Does TOTIDF (bit 22) = 1 for both FADECs?
08 Repair the aircraft circuit fault (Ref. 76-12-52/76-12-53 WM). Rotate the FADEC -Yes reset/select switch to the RESET position to remove the fault (TOTIDF (bit 22) = 0).
| No 04 Go to Block 05
FADEC Discrete: TOTIDF (bit 22) / (264 / AIDIF1) = 1 EFFECTIVITY:ALL
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05 Record the number of occurances for this maintenance message. Make sure the CMC INHIBIT is not selected. Rotate the switch to the INC position (no more than two seconds) and release. Access the maintenance messages from the CMC for both FADECs (Ref. Introduction). Is there a new occurance of the message for both FADECs?
-Yes
09 Repair the aircraft circuit fault (Ref. 76-12-52/76-12-53 WM). Rotate the FADEC reset/select switch to the RESET position to remove the fault (TOTIDF (bit 22) = 0).
| No |
10 Replace the FADEC with the new occurance (Ref. 73-25-10-000-801/ 73-25-10-400-801 MM).
FADEC Discrete: TOTIDF (bit 22) / (264 / AIDIF1) = 1 EFFECTIVITY:ALL
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FADEC Discrete: TOTDDF (bit 23) / (264 / AIDIF1) = 1 DESCRIPTION: The FADECs do a lane difference test of the two decrement circuits for the takeoff data set switch. This fault occurs when the condition of the circuits (DEC/Not DEC) sensed by FADEC A and B is not the same. The FADECs will not do this test if one of the two circuits has a fault.
POSSIBLE CAUSES: 1. Aircraft circuit fault 2. FADEC
R
01 Disconnect the harness (W1) from the FADEC J2 receptacle on both FADECs (Ref. FIG. 307/TASK 73-25-00-990-807). Examine the harness connector for damage, corrosion, or contamination. Is the connector contaminated or damaged?
06 Clean or repair the connector (Ref. 20-50-00 WM). Rotate the FADEC reset/select switch to the RESET position to remove the -Yes fault (TOTDDF (bit 23) = 0).
| No
R R
02 Disconnect the harness from the switch 07 Repair the aircraft harness fault (Ref. and do a test for continuity between pins N and 76-12-52/76-12-53 WM) (Ref. g at the W1 harness connectors (Ref. FIG. 80-10-50/80-10-51 WM). Rotate the FADEC -Yes 304/TASK 73-25-00-990-804) (Ref. reset/select switch to the RESET position to 76-12-52/76-12-53 WM) (Ref. remove the fault (TOTDDF (bit 23) = 0). 80-10-50/80-10-51 WM). Is there continuity? | No 03 Supply electrical power to the aircraft. Access FADEC discrete label 264 from the central maintenance computer (CMC) for both FADECs (Ref. Introduction). Does TOTDDF (bit 23) = 1 for both FADECs?
08 Repair the aircraft circuit fault (Ref. 76-12-52/76-12-53 WM). Rotate the FADEC -Yes reset/select switch to the RESET position to remove the fault (TOTDDF (bit 23) = 0).
| No 04 Go to Block 05
FADEC Discrete: TOTDDF (bit 23) / (264 / AIDIF1) = 1 EFFECTIVITY:ALL
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05 Record the number of occurances for this maintenance message. Make sure the CMC INHIBIT is not selected. Rotate the switch to the DEC position (no more than two seconds) and release. Access the maintenance messages from the CMC for both FADECs (Ref. Introduction). Is there a new occurance of the message for both FADECs?
-Yes
09 Repair the aircraft circuit fault (Ref. 76-12-52/76-12-53 WM). Rotate the FADEC reset/select switch to the RESET position to remove the fault (TOTDDF (bit 23) = 0).
| No |
10 Replace the FADEC with the new occurance (Ref. 73-25-10-000-801/ 73-25-10-400-801 MM).
FADEC Discrete: TOTDDF (bit 23) / (264 / AIDIF1) = 1 EFFECTIVITY:ALL
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FADEC Discrete: TOTSFT (bit 24) / (351 / AILRU1) = 1 DESCRIPTION: The FADEC does a test of the increment circuit for the takeoff data set switch. This discrete is set to 1 (fault sensed) when an open or shorted circuit is detected, or when the circuit is in a closed condition for more than three seconds.
POSSIBLE CAUSES: 1. Aircraft circuit fault 2. FADEC
R R
01 Disconnect the harness (W1) from the FADEC J2 receptacle (Ref. FIG. 307/TASK 73-25-00-990-807). Examine the harness connector for damage, corrosion, or contamination. Is the connector contaminated or damaged?
07 Clean or repair the connector (Ref. 20-50-00 WM). Rotate the FADEC reset/select switch to the RESET position to remove the -Yes fault (TOTSFT (bit 24) = 0).
| No
R R
02 Supply electrical power to the aircraft and do a test for voltage at pin N of the FADEC J2 receptacle (Ref. FIG. 305/TASK 73-25-00-990-805) (Ref. 80-10-50/ 80-10-51 WM). Is there 12-15 VDC measured?
08 Replace the FADEC that has the fault (Ref. 73-25-10-000-801/73-25-10-400-801 -No MM).
| Yes
R
03 Make sure the switch is held in the STORE position and do a test for continuity between pins N and h at the W1 harness connector (Ref. FIG. 305/TASK 73-25-00-990-805) (Ref. 76-12-52/76-12-53 WM). Is there continuity, with resistance less than 10 ohms?
09 Repair the aircraft circuit fault (Ref. 76-12-52/76-12-53 WM). Rotate the FADEC reset/select switch to the RESET position to -No remove the fault (TOTSFT (bit 24) = 0).
| Yes 04 Go to Block 05
FADEC Discrete: TOTSFT (bit 24) / (351 / AILRU1) = 1 EFFECTIVITY:ALL
TASK 73−25−00−810−815 Page 201 Aug 15/04
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R R
05 With the switch held in the STORE position, 10 Repair the aircraft circuit fault (Ref. do a test for continuity between ground and pin 80-10-50/80-10-51 WM). Rotate the FADEC N at the W1 harness connector (Ref. FIG. -Yes reset/select switch to the RESET position to 305/TASK 73-25-00-990-805) (Ref. remove the fault (TOTSFT (bit 24) = 0). 80-10-50/80-10-51 WM). Is there continuity? | No
R R
06 Make sure the switch is not held in the STORE position and do a test for continuity between pins N and f at the W1 harness connector (Ref. FIG. 305/TASK 73-25-00-990-805) (Ref. 76-12-52/ 76-12-53 WM). Is there continuity, with resistance between 9.5K and 10.5K ohms?
11 Repair the aircraft circuit fault (Ref. 76-12-52/76-12-53 WM). Rotate the FADEC reset/select switch to the RESET position to -No remove the fault (TOTSFT (bit 24) = 0).
| Yes |
12 Replace the FADEC that has the fault (Ref. 73-25-10-000-801/73-25-10-400-801 MM).
FADEC Discrete: TOTSFT (bit 24) / (351 / AILRU1) = 1 EFFECTIVITY:ALL
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FADEC Discrete: TOTSDF (bit 24) / (264 / AIDIF1) = 1 DESCRIPTION: The FADECs do a lane difference test of the two takeoff-data store switch circuits. This fault occurs when the condition of the circuits (Store/Not Store) sensed by FADEC A and B is not the same. The FADECs will not do this test if one of the two circuits has a fault.
POSSIBLE CAUSES: 1. Aircraft circuit fault 2. FADEC
R
01 Disconnect the harness (W1) from the FADEC J2 receptacle on both FADECs (Ref. FIG. 307/TASK 73-25-00-990-807). Examine the harness connector for damage, corrosion, or contamination. Is the connector contaminated or damaged?
06 Clean or repair the connector (Ref. 20-50-00 WM). Rotate the FADEC reset/select switch to the RESET position to remove the -Yes fault (TOTSDF (bit 24) = 0).
| No
R R
02 Disconnect the harness from the switch 07 Repair the aircraft harness fault (Ref. and do a test for continuity between pins N and 76-12-52/76-12-53 WM) (Ref. h at the W1 harness connectors (Ref. FIG. 80-10-50/80-10-51 WM). Rotate the FADEC -Yes 305/TASK 73-25-00-990-805) (Ref. reset/select switch to the RESET position to 76-12-52/76-12-53 WM) (Ref. remove the fault (TOTSDF (bit 24) = 0). 80-10-50/80-10-51 WM). Is there continuity? | No 03 Supply electrical power to the aircraft. Access FADEC discrete label 264 from the central maintenance computer (CMC) for both FADECs (Ref. Introduction). Does TOTSDF (bit 24) = 1 for both FADECs?
08 Repair the aircraft circuit fault (Ref. 76-12-52/76-12-53 WM). Rotate the FADEC -Yes reset/select switch to the RESET position to remove the fault (TOTSDF (bit 24) = 0).
| No 04 Go to Block 05
FADEC Discrete: TOTSDF (bit 24) / (264 / AIDIF1) = 1 EFFECTIVITY:ALL
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05 Record the number of occurances for this maintenance message. Make sure the CMC INHIBIT is not selected. Push the takeoff-data store switch (no more than two seconds) and release. Access the maintenance messages from the CMC for both FADECs (Ref. Introduction). Is there a new occurance of the message for both FADECs?
-Yes
09 Repair the aircraft circuit fault (Ref. 76-12-52/76-12-53 WM). Rotate the FADEC reset/select switch to the RESET position to remove the fault (TOTSDF (bit 24) = 0).
| No |
10 Replace the FADEC with the new occurance (Ref. 73-25-10-000-801/ 73-25-10-400-801 MM).
FADEC Discrete: TOTSDF (bit 24) / (264 / AIDIF1) = 1 EFFECTIVITY:ALL
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Maintenance Message: ENG1/ENG2 PMA POWER FAIL or ST - ENG1/ENG2 PMA SYS (set by FADEC Discrete: PMAPWF (bit 19) / (354 / CFPLRU) = 1) or PMAPWF (bit 15) / (351 / AILRU1) = 1) DESCRIPTION: This message occurs when the FADEC finds that the PMA is not providing sufficient electrical power to a FADEC (N2 greater than 54%). The FADEC will operate on 28 VDC, provided by the aircraft electrical system, when the PMA power source has failed.
POSSIBLE CAUSES: 1. PMA stator 2. Harness 3. FADEC 4. PMA rotor CAUTION: DO NOT INSTALL A REPLACEMENT FADEC IN THE POSITION OF THE AFFECTED FADEC UNTIL THE PMA STATOR AND THE FADEC A/B (W11/14) AND FADEC/ENGINE INTERCONNECT (W7) HARNESS HAVE BEEN TESTED. DAMAGE TO THE FADEC COULD RESULT.
01 Access the central maintenance computer (CMC) Maintenance Messages (Ref. Introduction). Did an ND - ENG1/ENG2 DUAL PMA SYS message occur?
12 Do the troubleshooting for maintenance message ND - ENG1/ENG2 DUAL PMA SYS -Yes (Ref. 73-25-00-810-860).
| No 02 Disconnect the FADEC A/B (W11/14) harness from the PMA stator housing and the FADEC/engine interconnect (W7) harness from the J4 receptacle of the FADEC (Ref. FIG. 307/TASK 73-25-00-990-807). Use an ohmmeter to do a test for continuity between -No the harness PMA stator (pins C, D, E, G, H, and J) and the connector backshells of the FADEC A/B harness (Ref. FIG. 306/TASK 73-25-00-990-806). Is there infinite resistance?
13 Replace the harness that does not test satisfactorily (Ref. 76-00-00 MM) (Ref. AMM) (Ref. 73-21-50//73-21-51 WM) and the associated FADEC (Ref. 73-25-10-000-801/ 73-25-10-400-801 MM).
| Yes 03 Go to Block 04.
Maintenance Message: ENG1/ENG2 PMA POWER FAIL or ST - ENG1/ENG2 PMA SYS EFFECTIVITY:FADEC SOFTWARE VER. B8.0 OR LATER
TASK 73−25−00−810−817 Page 201 Jul 20/07
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04 Use the ohmmeter to do a test for continuity between the PMA stator windings (pins C, D, E, G, H, and J) and the stator housing (Ref. FIG. 306/TASK 73-25-00-990-806). Is there infinite resistance?
14 Replace the PMA stator (Ref. 74-11-15-000-801/74-11-15-400-801 MM) and -No the associated FADEC (Ref. 73-25-10-000-801/73-25-10-400-801 MM).
| Yes 05 Disconnect the FADEC A/B (W11/14) harness from the PMA (Ref. Fig. 307). Disconnect the FADEC/engine interconnect (W7) harness from the engine pylon. Use a mega-ohmmeter to do a test of pins C, D, E, G, -No H, and J on the FADEC A/B harness for shorts to the connector backshell (Ref. FIG. 306/TASK 73-25-00-990-806). Apply 500 VDC (max. 1 second). Is the resistance at least 5 megaohms?
15 Replace the harness that does not test satisfactorily (Ref. 76-00-00 MM) (Ref. AMM) and the associated FADEC (Ref. 73-25-10-000-801/73-25-10-400-801 MM).
| Yes 06 Disconnect the FADEC/engine interconnect (W7) harness from the FADEC A/B (W11/14) harness at the engine pylon and at the J4 receptacle of the FADEC. Use a mega-ohmmeter to do a test of pins N, P, R, S, T, and U on the W7 harness for shorts to the connector backshell (Ref. 73-21-50/73-21-51 WM). Does the harness test satisfactorily?
-No
16 Replace the FADEC/engine interconnect (W7) harness (Ref. AMM) and the associated FADEC (Ref. 73-25-10-000-801/ 73-25-10-400-801 MM).
| Yes 07 Do a test for continuity/resistance (1 ohm 17 Replace the harness that does not test max./harness) and internal shorts (1,000 ohms satisfactorily (Ref. 76-00-00 MM) (Ref. AMM) min.) on the FADEC A/B (W11/14) and the and if a short was found, replace the -No FADEC/engine interconnect (W7) harnesses associated FADEC (Ref. 73-25-10-000-801/ (Ref. Fig. 306/307) (Ref. 73-21-50/73-21-51 73-25-10-400-801 MM). WM). Do the harnesses test satisfactorily? | Yes 08 Go to Block 09.
Maintenance Message: ENG1/ENG2 PMA POWER FAIL or ST - ENG1/ENG2 PMA SYS EFFECTIVITY:FADEC SOFTWARE VER. B8.0 OR LATER
TASK 73−25−00−810−817 Page 202 Jul 20/07
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09 Do not install the PMA stator from this engine on the opposite engine or damage to the FADECs could result. 1. Install a serviceable PMA stator on this engine (Ref. 74-11-10-000-801/ 74-11-10-400-801 MM). 2. Start the engine and operate it at ground idle power and then shutdown the engine, but do not remove power from the FADECs (Ref. AMM). 3. Access FADEC discrete label 354 from the CMC (Ref. Introduction). Does PMAPWF (bit 19) = 1 for either FADEC?
18 Go to block 11.
-Yes
| No 10 Repeat steps 2 and 3 from block 09 two more times. Did PMAPWF (bit 19) = 1 during either check?
19 Remove the PMA stator from service. Monitor the engine for 10 days. If PMAPWF -No (bit 19) = 1 displays on the CMC within this time period, go to block 11.
| Yes 11 Does PMAPWF (bit 19) = 1 for both FADECs?
-Yes
20 Replace the PMA rotor (Ref. 74-11-10-000-801/74-11-10-400-801 MM).
| No R R R
21 Replace the FADEC that has the fault (Ref. 73-25-10-000-801/73-25-10-400-801 MM). Do not remove the diode adapter from the J4 connector.
Maintenance Message: ENG1/ENG2 PMA POWER FAIL or ST - ENG1/ENG2 PMA SYS EFFECTIVITY:FADEC SOFTWARE VER. B8.0 OR LATER
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FADEC Discrete: STFAIL (bit 21) / (355 / SFLTS1) = 1 DESCRIPTION:
R R R
This message occurs when the signal for main metering-valve position to this FADEC has failed, and the other FADEC is incapable of controlling the engine, or no valid signal for ITT is avail able to this FADEC (from it's dedicated set of 8 thermocouples or the other FADEC's set of 8 thermocouples). When the message occurs this FADEC will not initiate an engine start sequence. For FADEC software version B9.2 or later, a STFAIL bit will set to annunciate a LP shaft break. A specific LP shaft break bit will also be set. The FADEC will not allow and engine to restart with a LP shaft break.
POSSIBLE CAUSES:
R
1. ITT sensors/circuit 2. FPMU/circuit 3. FADEC 4. LP shaft break
01 Supply electrical power to the aircraft. Access the maintenance messages from the central maintenance computer (CMC) (Ref. Introduction). Is there an ENG1/2 ITT SENSOR FAIL message?
-Yes
03 Do the troubleshooting for the maintenance message (Ref. 77-21-00-810-801).
| No R R R R R R R
02 If the aircraft is equipped with CMC version 04 Speak with Rolls-Royce. 11 or higher, then examine the FADEC fault word snapshot file N0000DDMMMYYI.dat (Ref. Introduction Section 4) for SFLTS2. Download -Yes the FADEC A and FADEC B fault code stores (FCS) data (Ref. Introduction Section 5) and determine if SBSDSI is set.
FADEC Discrete: STFAIL (bit 21) / (355 / SFLTS1) = 1 EFFECTIVITY:ALL
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FADEC Discrete: ACDCFT (bit 16) / (360 / FADLRU) = 1 DESCRIPTION: This discrete is set to 1 (fault sensed) when the FADEC finds that the DC electrical power provided by the aircraft electrical system is 16 volts, or less.
POSSIBLE CAUSES: 1. Aircraft electrical-system fault 2. Harness 3. FADEC
01 Interchange the position of the FADECs 02 Replace the FADEC that has the fault (Ref. 73-25-10-000-801/73-25-10-400-801 (Ref. 73-25-10-000-801/73-25-10-400-801 MM). Rotate the FADEC reset/select switch to MM). the RESET position. Operate the engine (Ref. -Yes AMM). Do not remove electrical power from the FADECs. Does the fault move to the opposite channel? | No | R R
03 Do the troubleshooting on the aircraft electrical system (Ref. FIG. 306/TASK 73-25-00-990-806) (Ref. Chapter 24 EMB FIM).
FADEC Discrete: ACDCFT (bit 16) / (360 / FADLRU) = 1 EFFECTIVITY:ALL
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R FADEC Discretes: CSETMF (bit 17) or FADTMF (bit 18) / 360 / FADLRU) = 1 DESCRIPTION: This message occurs when internal temperature of the FADEC is between 80 °C and 105 °C or is above 105 °C.
POSSIBLE CAUSES: 1. Internal FADEC failure 2. Rear electronics-compartment temperature high
01 Replace the FADEC that has the fault (Ref. 73-25-10-000-801/73-25-10-400-801 MM). Examine the aircraft rear electronics compartment for blockage of cooling airflow or over temperature condition (Ref. AMM).
FADEC Discretes: CSETMF (bit 17) or FADTMF (bit 18) / 360 / FADLRU) = 1 EFFECTIVITY:ALL
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Maintenance Message: ENG1/ENG2 FADEC IN CONTROL / NOT IN CONTROL PARAMT FAIL or ENG1/ENG2 FADEC A/B FAIL DESCRIPTION: This message occurs when the FADEC self-test finds an engine-control system fault.
POSSIBLE CAUSES: 1. FADEC 2. N1 speed sensor (primary) 3. N2 speed sensor (primary)
01 Supply electrical power to the aircraft. Access FADEC discrete label 265 from the CMC for both FADECs (Ref. Introduction). Does AIINDF (bit 27) = 1?
-Yes
13 Ignore this maintenance message. AIINDF (bit 27) = 1 incorrectly sets this message.
| No 02 Access FADEC discrete label 360 from the 14 Do the troubleshooting for FADEC discrete CMC for both FADECs (Ref. Introduction). -Yes N1OSF (bit 14) = 1 (Ref. Does N1OSF (bit 14) = 1? 73-25-00-810-822-B01). | No 03 Does N2OSF (bit 15) = 1?
15 Do the troubleshooting for FADEC discrete -Yes N2OSF (bit 15) = 1 (Ref. 73-25-00-810-823-B01).
| No 04 Does V5RFLT (bit 19) = 1?
-Yes
16 Do the troubleshooting for FADEC discrete V5RFLT (bit 19) = 1 Ref. 73-25-00-810-825).
-Yes
17 Do the troubleshooting for FADEC discrete V15RFT (bit 20) = 1 (Ref. 73-25-00-810-825).
| No 05 Does V15RFT (bit 20) = 1? | No 06 Go to Block 07
Maintenance Message: ENG1/ENG2 FADEC IN CONTROL / NOT IN CONTROL PARAMT FAIL or ENG1/ENG2 FADEC A/B FAIL R EFFECTIVITY:FADEC SOFTWARE VER. B5.1.1
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07 Does MMVDLF (bit 28) = 1?
-Yes
18 Do the troubleshooting for FADEC discrete MMVDLF (bit 28) = 1 (Ref. 73-21-00-810-813).
-Yes
19 Do the troubleshooting for FADEC discrete CVGDLF (bit 29) = 1 (Ref. 73-21-00-810-814).
| No 08 Does CVGDLF (bit 29) = 1? | No 09 Access FADEC discrete label 265 from the 20 Do the troubleshooting for FADEC discrete CMC for both FADECs (Ref. Introduction). -Yes SSW1DF (bit 25) = 1 (Ref. 73-25-00-810-832). Does SSW1DF (bit 25) = 1? | No 10 Does RBRQDF (bit 26) = 1?
-Yes
21 Do the troubleshooting for FADEC discrete RBRQDF (bit 26) = 1 (Ref. 73-25-00-810-833).
| No 11 Access FADEC discrete label 356 from the 22 Do the troubleshooting for FADEC discrete CMC for both FADECs (Ref. Introduction). -Yes INHFLB (bit 20) = 1 (Ref. 73-25-00-810-834). Does INHFLB (bit 20) = 1? | No 12 Operate the engine (Ref. AMM). Do not remove electrical power from the FADECs. Repeat the procedures in blocks 01 through 12. Do any of the FADEC discrete(s) = 1?
-Yes
23 Do the troubleshooting for the FADEC discrete(s) (Ref. FADEC Discrete List).
| No |
24 Access the CMC after the next flight (Ref. Introduction). Repeat the procedures in blocks 01 through 12.
Maintenance Message: ENG1/ENG2 FADEC IN CONTROL / NOT IN CONTROL PARAMT FAIL or ENG1/ENG2 FADEC A/B FAIL R EFFECTIVITY:FADEC SOFTWARE VER. B5.1.1
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Maintenance Message: ENG1/ENG2 FADEC IN CONTROL / NOT IN CONTROL PARAMT FAIL or ENG1/ENG2 FADEC A/B FAIL DESCRIPTION: This message occurs when the FADEC self-test finds an engine-control system fault.
POSSIBLE CAUSES: 1. FADEC 2. N1 speed sensor (primary) 3. N2 speed sensor (primary)
01 Supply electrical power. Access FADEC 10 Do the troubleshooting for FADEC discrete discrete label 360 from the CMC for both N1OSF (bit 14) = 1 (Ref. -Yes FADECs (Ref. Introduction). Does N1OSF (bit 73-25-00-810-822-B01). 14) = 1? | No 02 Does N2OSF (bit 15) = 1?
11 Do the troubleshooting for FADEC discrete -Yes N2OSF (bit 15) = 1 (Ref. 73-25-00-810-823-B01).
| No 03 Does V5RFLT (bit 19) = 1?
-Yes
12 Do the troubleshooting for FADEC discrete V5RFLT (bit 19) = 1 (Ref. 73-25-00-810-824).
-Yes
13 Do the troubleshooting for FADEC discrete V15RFT (bit 20) = 1 (Ref. 73-25-00-810-825).
-Yes
14 Do the troubleshooting for FADEC discrete MMVDLF (bit 28) = 1 (Ref. 73-21-00-810-813).
| No 04 Does V15RFT (bit 20) = 1? | No 05 Does MMVDLF (bit 28) = 1? | No 06 Go to Block 07.
Maintenance Message: ENG1/ENG2 FADEC IN CONTROL / NOT IN CONTROL PARAMT FAIL or ENG1/ENG2 FADEC A/B FAIL EFFECTIVITY:FADEC SOFTWARE VER. B7.5 OR LATER
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07 Does CVGDLF (bit 29) = 1?
-Yes
15 Do the troubleshooting for FADEC discrete CVGDLF (bit 29) = 1 (Ref. 73-21-00-810-814).
| No 08 Access FADEC discrete label 356 from the CMC for both FADECs (Ref. Introduction). Does INHFLB (bit 20) = 1?
16 Do the troubleshooting for FADEC discrete -Yes INHFLB (bit 20) = 1 (Ref. 73-25-00-810-834).
| No 09 Operate the engine (Ref. AMM). Do not remove electrical power from the FADECs. Repeat the procedures in blocks 01 through 12. Do any of the FADEC discrete(s) = 1?
-Yes
17 Do the troubleshooting for the FADEC discrete(s) (Ref. FADEC Discrete List).
| No |
18 Access the CMC after the next flight (Ref. Introduction). Repeat the procedures in blocks 01 through 12.
Maintenance Message: ENG1/ENG2 FADEC IN CONTROL / NOT IN CONTROL PARAMT FAIL or ENG1/ENG2 FADEC A/B FAIL EFFECTIVITY:FADEC SOFTWARE VER. B7.5 OR LATER
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FADEC Discrete: N1OSF (bit 14) / (360 / FADLRU) = 1 DESCRIPTION: The FADEC does a test of its N1 overspeed-protection circuit (independent of the software overspeed protection). This discrete is set to 1 (fault sensed) when this self-test has failed, or a failure of the N1 speed sensor (primary) has occurred.
POSSIBLE CAUSES: 1. N1 speed-sensor (primary) circuit fault 2. FADEC
01 Operate the engine to the maximum thrust 06 Do the troubleshooting for N1PSFT = 1 practical and do a normal shutdown (Ref. (Ref. 77-11-00-810-802). AMM). Do not remove electrical power from -Yes the FADEC. Access label 353 from the central maintenance computer (CMC) (Ref. Introduction). Does N1PSFT (bit 11) = 1? | No
R R
02 Examine all of the harness connectors between the N1 sensor and the FADEC J4 receptacle (Ref. FIG. 307/TASK 73-25-00-990-807) for looseness, corrosion, contamination, or damage. Are the connectors loose, dirty, or damaged?
-Yes
07 Tighten or clean the connectors (Ref. 70-00-00-910-804 MM) or replace the harness (Ref. 76-00-00 MM) (Ref. AMM).
| No 03 Access label 360 from the CMC (Ref. Introduction). Does N1OSF (bit 14) = 1?
08 Replace the FADEC that has the fault -Yes (Ref. 73-25-10-000-801/73-25-10-400-801 MM).
| No 04 Go to Block 05
FADEC Discrete: N1OSF (bit 14) / (360 / FADLRU) = 1 EFFECTIVITY:ALL
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05 Did the maintenance message ND ENG1/ENG2 OVSPD PROT SYS occur more than once?
09 Replace the FADEC that has the fault -Yes (Ref. 73-25-10-000-801/73-25-10-400-801 MM).
| No |
10 Access the CMC in the next 150 flight hours. If N1OSF (bit 14) = 1, or the maintenance message occurs again, replace the FADEC that has the fault (Ref. 73-25-10-000-801/73-25-10-400-801 MM).
FADEC Discrete: N1OSF (bit 14) / (360 / FADLRU) = 1 EFFECTIVITY:ALL
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FADEC Discrete: N2OSF (bit 15) / (360 / FADLRU) = 1 DESCRIPTION: The FADEC does a test of its N2 overspeed-protection circuit (independent of the software overspeed protection). This discrete is set to 1 (fault sensed) when this self-test has failed, or a failure of the N2 speed sensor (primary) has occurred.
POSSIBLE CAUSES: 1. N2 speed-sensor (primary) circuit fault 2. FADEC
01 Operate the engine to the maximum thrust 07 Do the troubleshooting for N2PSFT = 1 practical and do a normal shutdown (Ref. (Ref. 77-11-00-810-807). AMM). Do not remove electrical power from -Yes the FADEC. Access label 353 from the central maintenance computer (CMC) (Ref. Introduction). Does N2PSFT (bit 13) = 1? | No R
02 Access the central maintenance computer (CMC) FADEC discrete label 352 bit 12. Does AIDNOK = 1?
08 Do the FIM task for Application ID Mismatch -Yes (Ref. 73-25-00-810-868-A01)
| No 03 Examine all of the harness connectors between the N2 sensor and the FADEC J4 receptacle (Ref. FIG. 307/TASK 73-25-00-990-807) for looseness, corrosion, contamination, or damage. Are the connectors loose, dirty, or damaged?
-Yes
09 Tighten or clean the connectors (Ref. 70-00-00-910-804 MM) or replace the harness (Ref. 76-00-00 MM) (Ref. AMM).
| No 04 Access label 360 from the CMC (Ref. Introduction). Does N2OSF (bit 15) = 1?
10 Replace the FADEC that has the fault -Yes (Ref. 73-25-10-000-801/73-25-10-400-801 MM).
| No 05 Go to Block 06
FADEC Discrete: N2OSF (bit 15) / (360 / FADLRU) = 1 EFFECTIVITY:ALL
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06 Did the maintenance message ND ENG1/ENG2 OVSPD PROT SYS occur more than once?
11 Replace the FADEC that has the fault -Yes (Ref. 73-25-10-000-801/73-25-10-400-801 MM).
| No |
12 Access the CMC in the next 150 flight hours. If N2OSF (bit 15) = 1, or the maintenance message occurs again, replace the FADEC that has the fault (Ref. 73-25-10-000-801/73-25-10-400-801 MM).
FADEC Discrete: N2OSF (bit 15) / (360 / FADLRU) = 1 EFFECTIVITY:ALL
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FADEC Discrete: V5RFLT (bit 19) / (360 / FADLRU) = 1 DESCRIPTION: The FADEC monitors its internal 5 volt electrical power supply. This discrete is set to 1 (fault sensed) when the voltage is not between the limits.
POSSIBLE CAUSES: 1. FADEC
01 Supply electrical power to the aircraft. 03 Replace the FADEC that has the fault Rotate the FADEC reset/select switch to the (Ref. 73-25-10-000-801/73-25-10-400-801 RESET position. Access FADEC discrete label MM). -Yes 360 from the central maintenance computer (CMC) (Ref. Introduction). Does V5RFLT (bit 19) = 1? | No 02 Did the maintenance message FADEC IN CONTROL/NOT IN CONTROL PARAMT FAIL occur more than once?
04 Replace the FADEC that has the fault -Yes (Ref. 73-25-10-000-801/73-25-10-400-801 MM).
| No |
05 Access the CMC (Ref. Introduction) in the next 3 days (72 hours) of operation. If V5RFLT (bit 19) = 1, or the maintenance message occurs, replace the FADEC (Ref. 73-25-10-000-801/73-25-10-400-801 MM).
FADEC Discrete: V5RFLT (bit 19) / (360 / FADLRU) = 1 EFFECTIVITY:ALL
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FADEC Discrete: V15RFT (bit 20) / (360 / FADLRU) = 1 DESCRIPTION: The FADEC monitors its internal 15 volt electrical power supply. This discrete is set to 1 (fault sensed) when the voltage is not between the limits.
POSSIBLE CAUSES: 1. FADEC
01 Supply electrical power to the aircraft. 03 Replace the FADEC that has the fault Rotate the FADEC reset/select switch to the (Ref. 73-25-10-000-801/73-25-10-400-801 RESET position. Access FADEC discrete label MM). -Yes 360 from the central maintenance computer (CMC) (Ref. Introduction). Does V15RFT (bit 20) = 1? | No 02 Did the maintenance message FADEC IN CONTROL/NOT IN CONTROL PARAMT FAIL occur more than once?
04 Replace the FADEC that has the fault -Yes (Ref. 73-25-10-000-801/73-25-10-400-801 MM).
| No |
05 Access the CMC (Ref. Introduction) in the next 3 days (72 hours) of operation. If V15RFT (bit 20) = 1, or the maintenance message occurs, replace the FADEC. (Ref. 73-25-10-000-801/73-25-10-400-801 MM).
FADEC Discrete: V15RFT (bit 20) / (360 / FADLRU) = 1 EFFECTIVITY:ALL
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FADEC Discrete: SEXFLT (bit 21) / (360 / FADLRU) = 1 DESCRIPTION: The FADEC monitors the excitation voltage that it provides to the engine sensors. This discrete is set to 1 (fault sensed) when the voltage is not between the limits.
POSSIBLE CAUSES: R
R
1. Harness 2. FADEC
01 Supply electrical power to the aircraft. 04 Access the CMC (Ref. Introduction) in the Rotate the FADEC reset/select switch to the next 120 days of operation. If SEXFLT (bit 21) RESET position. Access FADEC discrete label = 1, replace the FADEC (Ref. -No 360 from the central maintenance computer 73-25-10-000-801/73-25-10-400-801, MM). (CMC) (Ref. Introduction). Does SEXFLT (bit 21) = 1? | Yes
R R R R R R R R R R
02 Examine all of the harness connectors between the FADEC J4 receptacle and the CVG actuator, T2.5 Sensor and P2.5 Sensor for looseness, damage, corrosion, or contamination (Ref. FIG. 314/TASK 73-25-00-990-814, FIG. 315/TASK 73-25-00-990-815, FIG. 316/TASK 73-25-00-990-816). Are the connectors loose, dirty, or damaged?
R R R R R R R R R R R R
05 Tighten, repair, or clean the connectors as necessary (Ref. 70-00-00-910-804, MM). -Yes
| No 03 Do a test for continuity/resistance (1 ohm 06 Replace the FADEC that has the fault max./harness), internal shorts, and shorts to (Ref. 73-25-10-000-801/73-25-10-400-801, ground (1,000 ohms min.) between the FADEC MM). J4 receptacle and the CVG actuator, T2.5 -Yes Sensor and the P2.5 Sensor (Ref. FIG. 314/TASK 73-25-00-990-814, FIG. 315/TASK 73-25-00-990-815, FIG. 316/TASK 73-25-00-990-816). Do all harnesses test satisfactorily?
R R R
| No |
R R
07 Replace the harness that has the fault (Ref. 76-00-00, MM).
FADEC Discrete: SEXFLT (bit 21) / (360 / FADLRU) = 1 EFFECTIVITY:ALL
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FADEC Discrete: TLAEXF (bit 22) / (360 / FADLRU) = 1 DESCRIPTION: The FADEC monitors the excitation voltage that it provides to the thrust lever resolvers. This discrete is set to 1 (fault sensed) when the voltage is not between the limits.
POSSIBLE CAUSES: 1. FADEC
01 Supply electrical power to the aircraft. 02 Replace the FADEC that has the fault Rotate the FADEC reset/select switch to the (Ref. 73-25-10-000-801/73-25-10-400-801 RESET position. Access FADEC discrete label MM). -Yes 352 from the central maintenance computer (CMC) (Ref. Introduction). Does TLAFLT (bit 16) = 1? | No |
03 Access the CMC (Ref. Introduction) in the next 120 days. If TLAEXF (bit 22) = 1, replace the FADEC (Ref. 73-25-10-000-801/ 73-25-10-400-801 MM).
FADEC Discrete: TLAEXF (bit 22) / (360 / FADLRU) = 1 EFFECTIVITY:ALL
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FADEC Discrete: ARNCTX (bit 25) / (360 / FADLRU) = 1 DESCRIPTION: The FADEC does a self-test of its internacelle ARINC data bus transmitter. This discrete is set to 1 (fault sensed) when the test has failed.
POSSIBLE CAUSES: 1. FADEC
01 Supply electrical power to the aircraft. Remove electrical power from the FADECs, and then supply power again. Access FADEC discrete label 360 from the central maintenance computer (CMC) (Ref. Introduction). Does ARNCTX (bit 25) = 1?
-Yes
02 Replace the FADEC that has the fault (Ref. 73-25-10-000-801/73-25-10-400-801 MM).
| No |
03 Access the CMC (Ref. Introduction) in the next 120 days of operation. If ARNCTX (bit 25) = 1, replace the FADEC (Ref. 73-25-10-000-801/73-25-10-400-801 MM).
FADEC Discrete: ARNCTX (bit 25) / (360 / FADLRU) = 1 EFFECTIVITY:ALL
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FADEC Discrete: ARNCRX (bit 26) / (360 / FADLRU) = 1 DESCRIPTION: The FADEC does a self-test of the internacelle and the air data computer ARINC data bus receivers. This discrete is set to 1 (fault sensed) when the test has failed.
POSSIBLE CAUSES: 1. FADEC
01 Supply electrical power to the aircraft. Remove electrical power from the FADECs, and then supply power again. Access FADEC discrete label 360 from the central maintenance computer (CMC) (Ref. Introduction). Does ARNCRX (bit 26) = 1?
-Yes
02 Replace the FADEC that has the fault (Ref. 73-25-10-000-801/73-25-10-400-801 MM).
| No |
03 Access the CMC (Ref. Introduction) in the next 120 days of operation. If ARNCRX (bit 26) = 1, replace the FADEC (Ref. 73-25-10-000-801/73-25-10-400-801 MM).
FADEC Discrete: ARNCRX (bit 26) / (360 / FADLRU) = 1 EFFECTIVITY:ALL
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FADEC Discrete: FADFLT (bit 27) / (360 / FADLRU) = 1 DESCRIPTION: The FADEC does a self-test. This discrete is set to 1 (fault sensed) when the test has failed, or when the FADEC finds an ignition relay circuit fault.
POSSIBLE CAUSES: 1. FADEC
01 Access the central maintenance computer (CMC) Maintenance Messages (Ref. Introduction). Did an LT-ENG1/ENG2 IGN SYS message occur at the same time as the ST-ENG1/ENG2 CTL A/B SYS message?
03 Do the troubleshooting for Maintenance Message LT-ENG1/ENG2 IGN SYS (Ref. -Yes 74-13-00-810-801).
| No 02 Remove electrical power from the FADECs, 04 Replace the FADEC that has the fault and then supply power again. Access FADEC (Ref. 73-25-10-000-801/73-25-10-400-801 -Yes discrete label 360 from the CMC (Ref. MM). Introduction). Does FADFLT (bit 27) = 1? | No |
05 Access the CMC (Ref. Introduction) in the next 120 days of operation. If FADFLT (bit 27) = 1, replace the FADEC (Ref. 73-25-10-000-801/73-25-10-400-801 MM).
FADEC Discrete: FADFLT (bit 27) / (360 / FADLRU) = 1 EFFECTIVITY:AIRCRAFT CMC SOFTWARE VERSION 15 OR EARLIER
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FADEC Discrete: FADFLT (bit 27) / (360 / FADLRU) = 1 DESCRIPTION: The FADEC does a self-test. This discrete is set to 1 (fault sensed) when the test has failed, or when the FADEC finds an ignition relay circuit fault.
POSSIBLE CAUSES: 1. FADEC
01 Access the central maintenance computer (CMC) Maintenance Messages (Ref. Introduction). Did an LT-ENG1/ENG2 IGN SYS message occur at the same time as the ND-ENG1/ENG2 FADEC A/B message?
03 Do the troubleshooting for Maintenance Message LT-ENG1/ENG2 IGN SYS (Ref. -Yes 74-13-00-810-801).
| No 02 Remove electrical power from the FADECs, 04 Replace the FADEC that has the fault and then supply power again. Access FADEC (Ref. 73-25-10-000-801/73-25-10-400-801 -Yes discrete label 360 from the CMC (Ref. MM). Introduction). Does FADFLT (bit 27) = 1? | No |
05 Access the CMC (Ref. Introduction) in the next 120 days of operation. If FADFLT (bit 27) = 1, replace the FADEC (Ref. 73-25-10-000-801/73-25-10-400-801 MM).
FADEC Discrete: FADFLT (bit 27) / (360 / FADLRU) = 1 EFFECTIVITY:AIRCRAFT CMC SOFTWARE VERSION 16 OR LATER
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FADEC Discrete: SSW1DF (bit 25) / (265 / AIDIF2) = 1 DESCRIPTION: The FADECs monitor their output signal to the relay for the air-turbine starter control valve. This discrete is set to 1 (fault sensed) when the output signal for this FADEC is different from the other FADEC.
POSSIBLE CAUSES: 1. FADEC
01 Supply electrical power to the aircraft. 03 Replace the FADEC that has the fault Rotate the FADEC reset/select switch to the (Ref. 73-25-10-000-801/73-25-10-400-801 RESET position. Access FADEC discrete label MM). -Yes 265 from the central maintenance computer (CMC) (Ref. Introduction). Does SSW1DF (bit 25) = 1? | No 02 Did the maintenance message FADEC IN CONTROL/NOT IN CONTROL PARAMT FAIL occur more than once?
04 Replace the FADEC that has the fault -Yes (Ref. 73-25-10-000-801/73-25-10-400-801 MM).
| No |
05 Access the CMC (Ref. Introduction) after the next flight. If SSW1DF (bit 25) = 1, or the maintenance message occurs, replace the FADEC (Ref. 73-25-10-000-801/ 73-25-10-400-801 MM).
FADEC Discrete: SSW1DF (bit 25) / (265 / AIDIF2) = 1 EFFECTIVITY:ALL
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FADEC Discrete: RBRQDF (bit 26) / (265 / AIDIF2) = 1 DESCRIPTION: The FADECs monitor their output signal to the relay for the aircraft environmental control system. This discrete is set to 1 (fault sensed) when the output signal for this FADEC is different from the other FADEC.
POSSIBLE CAUSES: 1. FADEC
01 Supply electrical power to the aircraft. 03 Replace the FADEC that has the fault Rotate the FADEC reset/select switch to the (Ref. 73-25-10-000-801/73-25-10-400-801 RESET position. Access FADEC discrete label MM). -Yes 265 from the central maintenance computer (CMC) (Ref. Introduction). Does RBRQDF (bit 26) = 1? | No 02 Did the maintenance message FADEC IN CONTROL/NOT IN CONTROL PARAMT FAIL occur more than once?
04 Replace the FADEC that has the fault -Yes (Ref. 73-25-10-000-801/73-25-10-400-801 MM).
| No |
05 Access the CMC (Ref. Introduction) in the next 3 days (72 hours) of operation. If RBRQDF (bit 26) = 1, or the maintenance message occurs, replace the FADEC (Ref. 73-25-10-000-801/73-25-10-400-801 MM).
FADEC Discrete: RBRQDF (bit 26) / (265 / AIDIF2) = 1 R EFFECTIVITY:FADEC SOFTWARE VER. B5.1.1
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FADEC Discrete: INHFLB (bit 20) / (356 / SFLTS2) = 1 DESCRIPTION: R
This discrete is set to 1 (fault sensed) when the FADEC finds that its non-volatile memory (EEPROM) can be damaged.
POSSIBLE CAUSES: 1. FADEC
01 Replace the FADEC that has the fault (Ref. 73-25-10-000-801/73-25-10-400-801 MM).
FADEC Discrete: INHFLB (bit 20) / (356 / SFLTS2) = 1 EFFECTIVITY:ALL
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EICAS Message: ENG NO TO DATA DESCRIPTION: This message occurs when the aircraft is on the ground (weight-on-wheels is true), N2 rpm is above 53%, thrust lever angle is above 45 degrees and takeoff temperature (set during the takeoff-data setting procedure) is not available to the FADECs for computing engine thrust. The FADECs will not accept the takeoff temperature value entered if it is not between 65 °C and -65 °C, is above or below the FADEC-synthesized T2.5 value, by more than 10 °C, or if all four of the FADEC values do not agree.
POSSIBLE CAUSES: 1. Takeoff temperature not set correctly 2. Aircraft/FADEC circuit failure 3. FADEC 4. ARINC data bus
01 Do the takeoff data setting procedure 02 Return the aircraft to service. again. Be sure the takeoff temperature entered -No is within the limits. Does the message occur again? | Yes |
03 Examine the maintenance messages from the central maintenance computer (CMC) (Ref. Introduction). Do the troubleshooting for any messages related to the takeoff data increment/decrement or store switch circuits, FADEC faults or ARINC data bus receiver or transmitter faults.
EICAS Message: ENG NO TO DATA EFFECTIVITY:ALL
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EICAS Message: ENG REF A/I DISAG DESCRIPTION: This message occurs when the condition of the anti-ice system (ON/OFF) entered during the takeoff-data setting procedure is different from the actual position of the anti-ice system control switches (ON/OFF).
POSSIBLE CAUSES: 1. Anti-ice system takeoff-data not set correctly 2. Aircraft/FADEC circuit failure 3. FADEC
01 Do the takeoff data setting procedure again. Be sure the anti-ice system condition entered is the same as the position of the control switches for the anti-ice system. Does the message occur again?
02 Return the aircraft to service. -No
| Yes |
03 Access the maintenance messages from the central maintenance computer (CMC) (Ref. Introduction). Do the troubleshooting for any messages related to the anti-ice position-indicator switch circuits or FADEC faults.
EICAS Message: ENG REF A/I DISAG EFFECTIVITY:ALL
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FADEC Discrete: MTOSFT (bit 16) / (351 / AILRU1) = 1 DESCRIPTION: The FADEC does a test of the circuit for the maximum takeoff mode switch. This discrete is set to 1 (fault sensed) when an open or shorted circuit is detected, or when the circuit is in a closed condition for more than three seconds.
POSSIBLE CAUSES: 1. Aircraft circuit fault 2. FADEC
R R
01 Disconnect the harness (W1) from the FADEC J2 receptacle (Ref. FIG. 307/TASK 73-25-00-990-807). Examine the harness connector for damage, corrosion, or contamination. Is the connector contaminated or damaged?
07 Clean or repair the connector (Ref. 20-50-00 WM). Rotate the FADEC reset/select switch to the RESET position to remove the -Yes fault (MTOSFT (bit 16) = 0).
| No
R R
02 Supply electrical power to the aircraft and do a test for voltage at pin R of the FADEC J2 receptacle (Ref. FIG. 308/TASK 73-25-00-990-808) (Ref. 76-12-57/ 76-12-58 WM). Is there 12-15 VDC measured?
08 Replace the FADEC that has the fault (Ref. 73-25-10-000-801/73-25-10-400-801 -No MM).
| Yes
R R
03 Make sure the maximum takeoff mode switch is held in, and do a test for continuity between pins R and j at the W1 harness connector (Ref. FIG. 308/TASK 73-25-00-990-808) (Ref. 76-12-57/ 76-12-58 WM). Is there continuity, with resistance less than 10 ohms?
09 Repair the aircraft circuit fault (Ref. 76-12-57/76-12-58 WM). Rotate the FADEC reset/select switch to the RESET position to -No remove the fault (MTOSFT (bit 16) = 0).
| Yes 04 Go to Block 05
FADEC Discrete: MTOSFT (bit 16) / (351 / AILRU1) = 1 EFFECTIVITY:ALL
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R
05 With the maximum takeoff mode switch 10 Repair the aircraft circuit fault (Ref. held in, do a test for continuity between ground 76-12-57/76-12-58 WM). Rotate the FADEC and pin R at the W1 harness connector (Ref. -Yes reset/select switch to the RESET position to FIG. 308/TASK 73-25-00-990-808) (Ref. remove the fault (MTOSFT (bit 16) = 0). 76-12-57/76-12-58 WM). Is there continuity? | No
R R
06 Make sure the switch is not held in, and do a test for continuity between pins R and j at the W1 harness connector (Ref. FIG. 308/TASK 73-25-00-990-808) (Ref. 76-12-57/76-12-58 WM). Is there continuity, with resistance between 9.5K and 10.5K ohms?
11 Repair the aircraft circuit fault (Ref. 76-12-57/76-12-58 WM). Rotate the FADEC reset/select switch to the RESET position to -No remove the fault (MTOSFT (bit 16) = 0).
| Yes |
12 Replace the FADEC that has the fault (Ref. 73-25-10-000-801/73-25-10-400-801 MM).
FADEC Discrete: MTOSFT (bit 16) / (351 / AILRU1) = 1 EFFECTIVITY:ALL
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FADEC Discrete: CLBFT (bit 26) / (351 / AILRU1) = 1 DESCRIPTION: The FADEC does a test of the circuit for the climb mode switch. This discrete is set to 1 (fault sensed) when an open or shorted circuit is detected, or when the circuit is in a closed condition for more than three seconds.
POSSIBLE CAUSES: 1. Aircraft circuit fault 2. FADEC
R R
01 Disconnect the harness (W1) from the FADEC J2 receptacle (Ref. FIG. 307/TASK 73-25-00-990-807). Examine the harness connector for damage, corrosion, or contamination. Is the connector contaminated or damaged?
07 Clean or repair the connector (Ref. 20-50-00 WM). Rotate the FADEC reset/select switch to the RESET position to remove the -Yes fault (CLBFT (bit 26) = 0).
| No
R R
02 Supply electrical power to the aircraft and do a test for voltage at pin R of the FADEC J2 receptacle (Ref. FIG. 309/TASK 73-25-00-990-809) (Ref. 76-12-57/ 76-12-58 WM). Is there 12-15 VDC measured?
08 Replace the FADEC that has the fault (Ref. 73-25-10-000-801/73-25-10-400-801 -No MM).
| Yes
R R
03 Make sure the climb mode switch is held in, 09 Repair the aircraft circuit fault (Ref. and do a test for continuity between pins R and 76-12-57/76-12-58 WM). Rotate the FADEC Z at the W1 harness connector (Ref. FIG. reset/select switch to the RESET position to -No 309/TASK 73-25-00-990-809) (Ref. remove the fault (CLBFT (bit 26) = 0). 76-12-57/76-12-58 WM). Is there continuity, with resistance less than 10 ohms? | Yes 04 Go to Block 05
FADEC Discrete: CLBFT (bit 26) / (351 / AILRU1) = 1 EFFECTIVITY:ALL
TASK 73−25−00−810−838 Page 201 Aug 15/04
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R R
05 With the climb mode switch held in, do a 10 Repair the aircraft circuit fault (Ref. test for continuity between ground and pin R at 76-12-57/76-12-58 WM). Rotate the FADEC the W1 harness connector (Ref. FIG. -Yes reset/select switch to the RESET position to 309/TASK 73-25-00-990-809) (Ref. remove the fault (CLBFT (bit 26) = 0). 76-12-57/76-12-58 WM). Is there continuity? | No
R R
06 Make sure the switch is not held in, and do a test for continuity between pins R and Z at the W1 harness connector (Ref. FIG. 309/TASK 73-25-00-990-809) (Ref. 76-12-57/76-12-58 WM). Is there continuity, with resistance between 9.5K and 10.5K ohms?
11 Repair the aircraft circuit fault (Ref. 76-12-57/76-12-58 WM). Rotate the FADEC reset/select switch to the RESET position to -No remove the fault (CLBFT (bit 26) = 0).
| Yes |
12 Replace the FADEC that has the fault (Ref. 73-25-10-000-801/73-25-10-400-801 MM).
FADEC Discrete: CLBFT (bit 26) / (351 / AILRU1) = 1 EFFECTIVITY:ALL
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FADEC Discrete: CRZFT (bit 27) / (351 / AILRU1) = 1 DESCRIPTION: The FADEC does a test of the circuit for the cruise mode switch. This discrete is set to 1 (fault sensed) when an open or shorted circuit is detected, or when the circuit is in a closed condition for more than three seconds.
POSSIBLE CAUSES: 1. Aircraft circuit fault 2. FADEC
R R
01 Disconnect the harness (W1) from the FADEC J2 receptacle (Ref. FIG. 307/TASK 73-25-00-990-807). Examine the harness connector for damage, corrosion, or contamination. Is the connector contaminated or damaged?
07 Clean or repair the connector (Ref. 20-50-00 WM). Rotate the FADEC reset/select switch to the RESET position to remove the -Yes fault (CRZFT (bit 27) = 0).
| No
R R
02 Supply electrical power to the aircraft and do a test for voltage at pin R of the FADEC J2 receptacle (Ref. FIG. 310/TASK 73-25-00-990-810) (Ref. 76-12-57/ 76-12-58 WM). Is there 12-15 VDC measured?
08 Replace the FADEC that has the fault (Ref. 73-25-10-000-801/73-25-10-400-801 -No MM).
| Yes
R R
03 Make sure the cruise mode switch is held in, and do a test for continuity between pins R and e at the W1 harness connector (Ref. FIG. 310/TASK 73-25-00-990-810) (Ref. 76-12-57/76-12-58 WM). Is there continuity, with resistance less than 10 ohms?
09 Repair the aircraft circuit fault (Ref. 76-12-57/76-12-58 WM). Rotate the FADEC reset/select switch to the RESET position to -No remove the fault (CRZFT (bit 27) = 0).
| Yes 04 Go to Block 05
FADEC Discrete: CRZFT (bit 27) / (351 / AILRU1) = 1 EFFECTIVITY:ALL
TASK 73−25−00−810−839 Page 201 Aug 15/04
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R R
05 With the cruise mode switch held in, do a 10 Repair the aircraft circuit fault (Ref. test for continuity between ground and pin R at 76-12-57/76-12-58 WM). Rotate the FADEC the W1 harness connector (Ref. FIG. -Yes reset/select switch to the RESET position to 310/TASK 73-25-00-990-810) (Ref. remove the fault (CRZFT (bit 27) = 0). 76-12-57/76-12-58 WM). Is there continuity? | No
R R
06 Make sure the switch is not held in, and do a test for continuity between pins R and e at the W1 harness connector (Ref. FIG. 310/TASK 73-25-00-990-810) (Ref. 76-12-57/76-12-58 WM). Is there continuity, with resistance between 9.5K and 10.5K ohms?
11 Repair the aircraft circuit fault (Ref. 76-12-57/76-12-58 WM). Rotate the FADEC reset/select switch to the RESET position to -No remove the fault (CRZFT (bit 27) = 0).
| Yes |
12 Replace the FADEC that has the fault (Ref. 73-25-10-000-801/73-25-10-400-801 MM).
FADEC Discrete: CRZFT (bit 27) / (351 / AILRU1) = 1 EFFECTIVITY:ALL
TASK 73−25−00−810−839 Page 202 Aug 15/04
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FADEC Discrete: MXCFT (bit 28) / (351 / AILRU1) = 1 DESCRIPTION: The FADEC does a test of the circuit for the maximum continuous mode switch. This discrete is set to 1 (fault sensed) when an open or shorted circuit is detected, or when the circuit is in a closed condition for more than three seconds.
POSSIBLE CAUSES: 1. Aircraft circuit fault 2. FADEC
R R
01 Disconnect the harness (W1) from the FADEC J2 receptacle (Ref. FIG. 307/TASK 73-25-00-990-807). Examine the harness connector for damage, corrosion, or contamination. Is the connector contaminated or damaged?
07 Clean or repair the connector (Ref. 20-50-00 WM). Rotate the FADEC reset/select switch to the RESET position to remove the -Yes fault (MXCFT (bit 28) = 0).
| No
R R
02 Supply electrical power to the aircraft and do a test for voltage at pin R of the FADEC J2 receptacle (Ref. FIG. 311/TASK 73-25-00-990-811) (Ref. 76-12-57/ 76-12-58 WM). Is there 12-15 VDC measured?
08 Replace the FADEC that has the fault (Ref. 73-25-10-000-801/73-25-10-400-801 -No MM).
| Yes
R R
03 Make sure the maximum continuous mode switch is held in, and do a test for continuity between pins R and d at the W1 harness connector (Ref. FIG. 311/TASK 73-25-00-990-811) (Ref. 76-12-57/ 76-12-58 WM). Is there continuity, with resistance less than 10 ohms?
09 Repair the aircraft circuit fault (Ref. 76-12-57/76-12-58 WM). Rotate the FADEC reset/select switch to the RESET position to -No remove the fault (MXCFT (bit 28) = 0).
| Yes 04 Go to Block 05
FADEC Discrete: MXCFT (bit 28) / (351 / AILRU1) = 1 EFFECTIVITY:ALL
TASK 73−25−00−810−840 Page 201 Aug 15/04
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R
05 With the maximum continuous mode switch 10 Repair the aircraft circuit fault (Ref. held in, do a test for continuity between ground 76-12-57/76-12-58 WM). Rotate the FADEC and pin R at the W1 harness connector (Ref. -Yes reset/select switch to the RESET position to FIG. 311/TASK 73-25-00-990-811) (Ref. remove the fault (MXCFT (bit 28) = 0). 76-12-57/76-12-58 WM). Is there continuity? | No
R R
06 Make sure the switch is not held in, and do a test for continuity between pins R and d at the W1 harness connector (Ref. FIG. 311/TASK 73-25-00-990-811) (Ref. 76-12-57/76-12-58 WM). Is there continuity, with resistance between 9.5K and 10.5K ohms?
11 Repair the aircraft circuit fault (Ref. 76-12-57/76-12-58 WM). Rotate the FADEC reset/select switch to the RESET position to -No remove the fault (MXCFT (bit 28) = 0).
| Yes |
12 Replace the FADEC that has the fault (Ref. 73-25-10-000-801/73-25-10-400-801 MM).
FADEC Discrete: MXCFT (bit 28) / (351 / AILRU1) = 1 EFFECTIVITY:ALL
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Maintenance Message: ENG1/ENG2 T/O SWITCH FAIL or ST-ENG T/O SYS DIFF (set by FADEC Discrete: MTOSDF (bit 16) / (264/AIDIF1) =1) DESCRIPTION: The FADECs do a lane difference test of the two maximum-takeoff-mode switch circuits. This message occurs when the condition of the circuits (active/not active) sensed by FADEC A and B is not the same. The FADECs will not do this test if one of the two circuits has a fault.
POSSIBLE CAUSES: 1. Aircraft circuit fault 2. FADEC
R R
01 Disconnect the harness (W1) from the J2 04 Clean or repair the connector (Ref. receptacle of both FADECs (Ref. FIG. 20-50-00 WM). Rotate the FADEC reset/select 307/TASK 73-25-00-990-807). Examine the switch to the RESET position to remove the -Yes harness connectors for damage, corrosion, or fault (MTOSDF (bit 16) = 0). contamination. Is a connector contaminated or damaged? | No
R
02 Disconnect the harness (W1) from the 05 Repair the aircraft circuit fault (Ref. switch and do a test for continuity between pins 76-12-57/76-12-58 WM). Rotate the FADEC R and j at the W1 harness connector (Ref. -Yes reset/select switch to the RESET position to FIG. 308/TASK 73-25-00-990-808) (Ref. remove the fault (MTOSDF (bit 16) = 0). 76-12-57/76-12-58 WM). Is there continuity? | No 03 Access FADEC Discrete label 264 from the 06 Repair the aircraft circuit fault (Ref. central maintenance computer (CMC) for both 76-12-57/76-12-58 WM). Rotate the FADEC -Yes FADECs (Ref. Introduction). Does MTOSDF reset/select switch to the RESET position to (bit 16) = 1 for both FADECs? remove the fault (MTOSDF (bit 16) = 0). | No |
07 Replace the FADEC showing MTOSDF (bit 16) = 1 (Ref. 73-25-10-000-801/ 73-25-10-400-801 MM).
Maintenance Message: ENG1/ENG2 T/O SWITCH FAIL or ST-ENG T/O SYS DIFF EFFECTIVITY:ALL
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FADEC Discrete: MXCDIF (bit 28) / (264/AIDIF1) = 1 DESCRIPTION: The FADECs do a lane difference test of the two maximum-continuous-mode switch circuits. This message occurs when the condition of the circuits (active/not active) sensed by FADEC A and B is not the same. The FADECs will not do this test if one of the two circuits has a fault.
POSSIBLE CAUSES: 1. Aircraft circuit fault 2. FADEC
R R
01 Disconnect the harness (W1) from the J2 04 Clean or repair the connector (Ref. receptacle of both FADECs (Ref. FIG. 20-50-00 WM). Rotate the FADEC reset/select 307/TASK 73-25-00-990-807). Examine the switch to the RESET position to remove the -Yes harness connectors for damage, corrosion, or fault (MXCDIF (bit 28) = 0). contamination. Is a connector contaminated or damaged? | No
R R
02 Disconnect the harness (W1) from the 05 Repair the aircraft circuit fault (Ref. switch and do a test for continuity between pins 76-12-57/76-12-58 WM). Rotate the FADEC R and d at the connector (Ref. FIG. 311/TASK -Yes reset/select switch to the RESET position to 73-25-00-990-811) (Ref. 76-12-57/76-12-58 remove the fault (MXCDIF (bit 28) = 0). WM). Is there continuity? | No 03 Access FADEC Discrete label 264 from the 06 Repair the aircraft circuit fault (Ref. central maintenance computer (CMC) for both 76-12-57/76-12-58 WM). Rotate the FADEC -Yes FADECs (Ref. Introduction). Does MXCDIF reset/select switch to the RESET position to (bit 28) = 1 for both FADECs? remove the fault (MXCDIF (bit 28) = 0). | No |
07 Replace the FADEC showing MXCDIF (bit 28) = 1 (Ref. 73-25-10-000-801/ 73-25-10-400-801 MM).
FADEC Discrete: MXCDIF (bit 28) / (264/AIDIF1) = 1 EFFECTIVITY:ALL
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FADEC Discrete: CRZDIF (bit 27) / (264/AIDIF1) = 1 DESCRIPTION: The FADECs do a lane difference test of the two cruise mode switch circuits. This message occurs when the condition of the circuits (active/not active) sensed by FADEC A and B is not the same. The FADECs will not do this test if one of the two circuits has a fault.
POSSIBLE CAUSES: 1. Aircraft circuit fault 2. FADEC
R R
01 Disconnect the harness (W1) from the J2 04 Clean or repair the connector (Ref. receptacle of both FADECs (Ref. FIG. 20-50-00 WM). Rotate the FADEC reset/select 307/TASK 73-25-00-990-807). Examine the switch to the RESET position to remove the -Yes harness connectors for damage, corrosion, or fault (CRZDIF (bit 27) = 0). contamination. Is a connector contaminated or damaged? | No
R R
02 Disconnect the harness (W1) from the 05 Repair the aircraft circuit fault (Ref. switch and do a test for continuity between pins 76-12-57/76-12-58 WM). Rotate the FADEC R and e at the connector (Ref. FIG. 310/TASK -Yes reset/select switch to the RESET position to 73-25-00-990-810) (Ref. 76-12-57/76-12-58 remove the fault (CRZDIF (bit 27) = 0). WM). Is there continuity? | No 03 Access FADEC Discrete label 264 from the 06 Repair the aircraft circuit fault (Ref. central maintenance computer (CMC) for both 76-12-57/76-12-58 WM). Rotate the FADEC -Yes FADECs (Ref. Introduction). Does CRZDIF reset/select switch to the RESET position to (bit 27) = 1 for both FADECs? remove the fault (CRZDIF (bit 27) = 0). | No |
07 Replace the FADEC showing CRZDIF (bit 27) = 1 (Ref. 73-25-10-000-801/ 73-25-10-400-801 MM).
FADEC Discrete: CRZDIF (bit 27) / (264/AIDIF1) = 1 EFFECTIVITY:ALL
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FADEC Discrete: CLBDIF (bit 26) / (264/AIDIF1) = 1 DESCRIPTION: The FADECs do a lane difference test of the two climb mode switch circuits. This message occurs when the condition of the circuits (active/not active) sensed by FADEC A and B is not the same. The FADECs will not do this test if one of the two circuits has a fault.
POSSIBLE CAUSES: 1. Aircraft circuit fault 2. FADEC
R R
01 Disconnect the harness (W1) from the J2 04 Clean or repair the connector (Ref. receptacle of both FADECs (Ref. FIG. 20-50-00 WM). Rotate the FADEC reset/select 307/TASK 73-25-00-990-807). Examine the switch to the RESET position to remove the -Yes harness connectors for damage, corrosion, or fault (CLBDIF (bit 26) = 0). contamination. Is a connector contaminated or damaged? | No
R R
02 Disconnect the harness (W1) from the 05 Repair the aircraft circuit fault (Ref. switch and do a test for continuity between pins 76-12-57/76-12-58 WM). Rotate the FADEC R and Z at the connector (Ref. FIG. 309/TASK -Yes reset/select switch to the RESET position to 73-25-00-990-809) (Ref. 76-12-57/76-12-58 remove the fault (CLBDIF (bit 26) = 0). WM). Is there continuity? | No 03 Access FADEC Discrete label 264 from the 06 Repair the aircraft circuit fault (Ref. central maintenance computer (CMC) for both 76-12-57/76-12-58 WM). Rotate the FADEC -Yes FADECs (Ref. Introduction). Does CLBDIF reset/select switch to the RESET position to (bit 26) = 1 for both FADECs? remove the fault (CLBDIF (bit 26) = 0). | No |
07 Replace the FADEC showing CLBDIF (bit 26) = 1 (Ref. 73-25-10-000-801/ 73-25-10-400-801 MM).
FADEC Discrete: CLBDIF (bit 26) / (264/AIDIF1) = 1 EFFECTIVITY:ALL
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EICAS Message: ENG ATTCS FAIL DESCRIPTION: This message occurs when the engine is running, the thrust lever angle (TLA) is more than 46 degrees (below the midpoint between the IDLE detent and the THRUST SET detent), an alternate takeoff-thrust mode is selected and the automatic takeoff-thrust-control system (ATTCS) is not armed on either the left engine, the right engine, or both.
POSSIBLE CAUSES: 1. Air/ground-position switch circuit fault 2. FADEC 3. Aircraft avionics-system fault
01 Supply electrical power to the aircraft. Access the maintenance messages for all of the FADECs (Ref. Introduction). Is there an E1/2 AIR/GND INPUT FAIL message?
-Yes
04 Do the troubleshooting for the maintenance message (Ref. 76-11-00-810-803).
| No 02 Operate both engines, select AT/O thrust mode and move the thrust levers above 46 degrees TLA (access the FADEC analog label on the CMC to view TLA (Ref. Introduction)). Access FADEC discrete label 147 for the FADEC-in-control on both engines. Does ATTCSC (bit 18) = 0 for either FADEC?
-Yes
05 Replace the FADEC with ATTCSC (bit 18) = 0 (Ref. 73-25-10-000-801/73-25-10-400-801 MM).
| No 03 Does ATTCSA (bit 19) = 0 for either FADEC?
06 Replace the FADEC with ATTCSA (bit 19) -Yes = 0 (Ref. 73-25-10-000-801/73-25-10-400-801 MM).
| No |
07 Do the troubleshooting on the aircraft avionics system (data acquisition unit, IC-600) (Ref. 31-42-00/201 EMB FIM).
EICAS Message: ENG ATTCS FAIL EFFECTIVITY:ALL
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EICAS Message: E1/E2 ATTCS NO MRGN DESCRIPTION: This message occurs when the aircraft is on the ground, the alternate takeoff-thrust mode is selected and one of the following takes place: -
the engine exceeded one of the computed ATTCS limits for ITT or N2
-
or
-
the interstage turbine temperature (ITT) reached the engine redline of 921°C (A, A1/1), 948°C (A1, A1/3, A3, A1P) or 992°C (A1E)
-
or
-
the core engine speed (N2) reached the engine redline of 102.5% (non-A1E) or 103.8% (A1E).
NOTE: If an engine failure occurs the automatic takeoff-thrust control system (ATTC) will not be able to achieve rated thrust on the remaining engine since there is a reduced margin to the maximum ITT of N2.
POSSIBLE CAUSES: 1. High ITT 2. High N2
R R R
01 After the E1/E2 ATTCS NO MRGN message occured, was a thrust assurance check performed?
07 Do the test of the engine (Ref. TASK -No 71-00-00-810-805). Go to block 02.
| Yes R R R R R
02 Were exceedances found during the thrust assurance check?
| Yes
R R R R R
08 Put the engine back in service. Supply Rolls-Royce with DFDR data of the event -No before the data is overridden (Approx. 25 FH). Go to block 06.
03 Supply electrical power to the aircraft. Access the engine exceedance data from the CMC (Ref. Introduction). Did the engine exceed the ITT redline limit on the EICAS display (Ref. TASK 71-00-00-200-801, MM)?
-Yes
09 Do the troubleshooting for ITT high (Ref. TASK 77-21-00-810-807).
| No 04 Go to block 05.
EICAS Message: E1/E2 ATTCS NO MRGN EFFECTIVITY:ALL
TASK 73−25−00−810−846 Page 201 Jan 20/13
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R R R
05 Did the engine exceed the N2 redline limit on the EICAS display (Ref. TASK 71-00-00-200-801, MM)? | No
R R R R
10 Do the troubleshooting for overspeed (N2) -Yes (Ref. TASK 77-11-00-810-810).
06 Review performance trends for the engine. Does this engine have N2 or ITT margin (Ref. TASK 05-13-00-800-801, MM)?
-No
11 Schedule the engine for removal.
| Yes |
R
12 Return the engine to service.
EICAS Message: E1/E2 ATTCS NO MRGN EFFECTIVITY:ALL
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R FADEC Discrete: IDTFL (bit 24) / (360/FADLRU) = 1 DESCRIPTION: This message occurs when this FADEC can not determine its identity (A or B, right or left engine).
POSSIBLE CAUSES: 1. Harness 2. FADEC
01 Supply electrical power to the aircraft. Access FADEC discrete label 354 from the central maintenance computer (CMC) for both FADECs (Ref. Introduction). Does IDFLT (bit 24) = 1?
-Yes
03 Do the troubleshooting for IDFLT (bit 24) = 1 (Ref. 73-25-00-810-850).
| No 02 Replace FADEC A with a FADEC from the opposite engine (Ref. 73-25-10-000-801/ 73-25-10-400-801 MM). Is the fault removed?
04 Remove the FADEC that has the fault from -Yes service.
| No |
05 Replace FADEC B (Ref. 73-25-10-000-801/73-25-10-400-801 MM).
FADEC Discrete: IDTFL (bit 24) / (360/FADLRU) = 1 EFFECTIVITY:ALL
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FADEC Discrete: IDFLT (bit 13) / (354 / CFPLRU) = 1 DESCRIPTION: Each FADEC determines its identity (A or B, right or left engine) by reading its address jumper. This FADEC discrete is set to 1 (fault sensed) when this FADEC can not determine its identity from the address jumpers.
POSSIBLE CAUSES: 1. Harness (W2/W3) 2. FADEC
R R
01 Do a test for continuity between the pins for 02 Repair or replace the harness (Ref. this FADEC's ID jumper, in the W2/W3 harness 76-12-50/76-12-51 WM). -Yes connector (Ref. FIG. 312/TASK 73-25-00-990-812). Is there an open circuit? | No |
03 Replace the FADEC (Ref. 73-25-10-000-801/73-25-10-400-801 MM).
FADEC Discrete: IDFLT (bit 13) / (354 / CFPLRU) = 1 EFFECTIVITY:ALL
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EICAS Message: E1/E2 LOW N1 DESCRIPTION: This message occurs when the FADEC detects a "Local Engine Inoperative" (LEI) condition while the aircraft is on the ground and the engine throttle lever is greater than 60 degrees. An LEI condition is detected when the engine experiences an uncommanded deceleration or when it is unable to achieve its target N1 speed.
POSSIBLE CAUSES: 1. FPMU 2. FADEC 3. ITT high / ITT circuit 4. Aircraft fuel system 5. N1 or N2 sensors
R R
01 Was there a compressor stall or banging noises that you could hear?
R R R
-Yes 08 Do the troubleshooting for the power fluctuations (Ref. TASK 72-00-00-810-817).
| No 02 Supply electrical power to the aircraft. Access the maintenance messages from the central maintenance computer (CMC) (Ref. Introduction). Are there any FADEC or FPMU related maintenance messages?
-Yes
09 Do the troubleshooting for the maintenance messages.
| No 03 Are there any engine speed sensor (N1 or N2) messages?
-Yes
10 Do the troubleshooting for the maintenance messages.
-Yes
11 Do the troubleshooting for the maintenance messages.
| No 04 Are there any engine temperature sensor (ITT) messages? | No 05 Go to Block 06
EICAS Message: E1/E2 LOW N1 EFFECTIVITY:ALL
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06 For AE3007A, A1/1: was ITT over 921 °C? For AE3007A1, A1/3, A1P: was ITT over 948 °C? For AE3007A1E : was ITT over 970 °C?
-Yes 12 Do the troubleshooting for ITT High (Ref. 77-21-00-810-807).
| No 07 Replace the FPMU (Ref. 73-21-10-000-801/ 73-21-10-400-801 MM). Operate the engine to maximum thrust (Ref. AMM). Does the E1/E2 LOW N1 message appear?
-No
13 Remove the FPMU from service from the engine identified in the message.
| Yes |
14 Do the troubleshooting on the aircraft fuel system (Ref. CH. 28 EMB FIM). Make sure the fuel system is delivering sufficient fuel to the engine.
EICAS Message: E1/E2 LOW N1 EFFECTIVITY:ALL
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FADEC Discrete: STPFLT (bit 12) / (351 / AILRU1) = 1 DESCRIPTION: The FADEC does a test of the start/stop switch STOP circuit. This discrete is set to 1 (fault sensed) when an open or shorted circuit is detected.
POSSIBLE CAUSES: 1. Aircraft circuit fault 2. FADEC
R R
01 Disconnect the harness (W1) from the FADEC J2 receptacle (Ref. FIG. 307/TASK 73-25-00-990-807). Examine the harness connector for damage, corrosion, or contamination. Is the connector contaminated or damaged?
07 Clean or repair the connector (Ref. 20-50-00 WM). Rotate the FADEC reset/select switch to the RESET position to remove the -Yes fault (STPFLT (bit 12) = 0).
| No
R R
02 Supply electrical power to the aircraft and do a test for voltage at pin N of the FADEC J2 receptacle (Ref. FIG. 313/TASK 73-25-00-990-813) (Ref. 80-10-50/ 80-10-51 WM). Is there 12-15 VDC measured?
08 Replace the FADEC that has the fault (Ref. 73-25-10-000-801/73-25-10-400-801 -No MM).
| Yes
R
03 Put the start/stop switch in the STOP position and do a test for continuity between pins N and W at the W1 harness connector (Ref. FIG. 313/TASK 73-25-00-990-813) (Ref. 80-10-50/80-10-51 WM). Is there continuity, with resistance less than 10 ohms?
09 Repair the aircraft circuit fault (Ref. 80-10-50/80-10-51 WM). Rotate the FADEC reset/select switch to the RESET position to -No remove the fault (STPFLT (bit 12) = 0).
| Yes 04 Go to Block 05
FADEC Discrete: STPFLT (bit 12) / (351 / AILRU1) = 1 EFFECTIVITY:ALL
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R
05 With the start/stop switch in the STOP 10 Repair the aircraft circuit fault (Ref. position, do a test for continuity between 80-10-50/80-10-51 WM). Rotate the FADEC ground and pin N at the W1 harness connector -Yes reset/select switch to the RESET position to (Ref. FIG. 313/TASK 73-25-00-990-813) (Ref. remove the fault (STPFLT (bit 12) = 0). 80-10-50/80-10-51 WM). Is there continuity? | No
R
06 Put the start/stop switch in the RUN position and do a test for continuity between pins N and W at the W1 harness connector (Ref. FIG. 313/TASK 73-25-00-990-813) (Ref. 80-10-50/80-10-51 WM). Is there continuity, with resistance between 9.5K and 10.5K ohms?
11 Repair the aircraft circuit fault (Ref. 80-10-50/80-10-51 WM). Rotate the FADEC reset/select switch to the RESET position to -No remove the fault (STPFLT (bit 12) = 0).
| Yes |
12 Replace the FADEC that has the fault (Ref. 73-25-10-000-801/73-25-10-400-801 MM).
FADEC Discrete: STPFLT (bit 12) / (351 / AILRU1) = 1 EFFECTIVITY:ALL
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FADEC Discrete: STPDIF (bit 12) / (264 / AIDIF1) = 1 DESCRIPTION: The FADECs do a lane difference test of the two STOP circuits for the start/stop switch. This fault occurs when the condition of the circuits (START/STOP/RUN) sensed by FADEC A and B is not the same. The FADECs will not do this test if one of the two STOP circuits has a fault.
POSSIBLE CAUSES: 1. Aircraft circuit fault 2. FADEC
R R
01 Disconnect the harness (W1) from the J2 receptacles on both FADECs (Ref. FIG. 307/TASK 73-25-00-990-807). Examine the harness connectors for damage, corrosion or contamination. Are the connectors contaminated or damaged?
04 Clean or repair the connector (Ref. 20-50-00 WM). Rotate the FADEC reset/select switch to the RESET position to remove the -Yes fault (STPDIF (bit 12) = 0).
| No
R
02 Disconnect the harness (W1) from the 05 Repair the aircraft harness fault (Ref. switch and do a test for continuity between pins 80-10-50/80-10-51 WM). Rotate the FADEC N and W at both W1 harness connectors (Ref. -Yes reset/select switch to the RESET position to FIG. 313/TASK 73-25-00-990-813) (Ref. remove the fault (STPDIF (bit 12) = 0). 80-10-50/80-10-51 WM). Is there continuity? | No 03 Supply electrical power to the aircraft. 06 Repair the aircraft circuit fault (Ref. Access FADEC discrete label 264, for FADEC 80-10-50/80-10-51 WM). Rotate the FADEC A and B, from the central maintenance -Yes reset/select switch to the RESET position to computer (CMC) (Ref. Introduction). Does remove the fault (STPDIF (bit 12) = 0). STPDIF (bit 12) = 1 for both FADECs? | No |
07 Replace the FADEC that shows STPDIF (bit 12) = 1 (Ref. 73-25-10-000-801/ 73-25-10-400-801 MM).
FADEC Discrete: STPDIF (bit 12) / (264 / AIDIF1) = 1 EFFECTIVITY:ALL
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FADEC Discrete: CHNFLT (bit 15) / (355 / SFLTS1) = 1 DESCRIPTION: This discrete is set to 1 (fault sensed) when one of the following faults occur: a complete loss of N2 signal to the FADEC, no signal to the FADEC for the position of the CVG actuator, no signal to the FADEC for the position of the main metering valve, or there is a complete loss of electrical power to the FADEC.
POSSIBLE CAUSES: 1. FPMU/circuits 2. FADEC 3. CVG hydraulic actuator/circuit 4. N2 speed sensor/circuit 5. Permanent magnet alternator (PMA)/circuit 6. Failure of aircraft 28 VDC power supply to the FADEC
R R R R
01 Supply electrical power to the aircraft. Access the maintenance messages from the central maintenance computer (CMC) (Ref. Introduction). Is there an ENG 1/2 FAD A/B N2 SENSOR FAIL and an N2 PMA SIGNAL FAIL message?
03 Do the troubleshooting for the maintenance messages (Ref. 77-11-00-810-807 and 77-11-00-810-808) and (Ref. -Yes 74-11-00-810-818, 74-11-00-810-819, and 74-11-00-810-827).
| No R R
02 Is there an ENG1/2 CVG FAIL message?
04 Do the troubleshooting for the maintenance -Yes message (Ref. 75-33-00-810-802 and 75-33-00-810-803).
| No |
05 Do the troubleshooting for the maintenance message ENG1/2 FPMU FAIL (Ref. 73-21-00-810-801).
FADEC Discrete: CHNFLT (bit 15) / (355 / SFLTS1) = 1 EFFECTIVITY:ALL
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FADEC Discrete: IFPOWINT (bit 17) / (356 / SFLTS2) = 1 DESCRIPTION:
R
This message occurs when a FADEC central-processing-unit (CPU) reset has occurred (an indication of a microprocessor fault) or there is an interruption of electrical power supplied to the FADEC, from both the permanent magnet alternator and the aircraft 28 VDC bus, and N2 is more than 8950 rpm, and weight on wheels (WOW) is false. A short to ground in the permanent magnet alternator (PMA) stator circuit can cause this fault to occur.
POSSIBLE CAUSES: 1. FADEC
R R
Remove the FADEC (Ref. TASK 73-25-10-000-801/73-25-10-400-801, MM) within the time allotment for a Long Term (LT) Time Limited Dispatch (TLD) fault.
FADEC Discrete: IFPOWINT (bit 17) / (356 / SFLTS2) = 1 EFFECTIVITY:ALL
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EICAS Message: ATTCS FAIL DESCRIPTION:
R
This message occurs when the automatic takeoff thrust control system (ATTCS) is armed [engine is running, the thrust lever angle (TLA) for both engines is greater than or equal to 45 degrees (below the midpoint between the IDLE detent and the THRUST SET detent), and an alternate takeoff-thrust mode is selected] and an uncommanded engine shutdown [local engine inoperative, LEI = true] has occurred. When an LEI occurs, the ATTCS automatically disarms. If ATTCS remains armed, it indicates that the ATTCS has not tripped when it was suppose to.
POSSIBLE CAUSES: 1. Air/ground-position switch circuit 2. FADEC 3. Aircraft avionics system fault
01 Supply electrical power to the aircraft. Access the maintenance messages for all of the FADECs (Ref. Introduction). Is there an ND-ENG1/ENG2 A/G SYS DIFF message?
-Yes
06 Do the troubleshooting for the maintenance message (Ref. 76-11-00-810-809).
| No 02 Is there an ND-ENG1/ENG2 COMM A/B message?
-Yes
07 Do the troubleshooting for the maintenance message (Ref. 77-40-00-810-807).
| No 03 Operate both engines, select AT/O thrust mode and move the thrust levers above 45 degrees TLA (access the FADEC analog label on the CMC to view TLA position). Access FADEC discrete label 147 for the FADEC-in-control on both engines (Ref. Introduction). Does ATTCSC (bit 18) = 0 for either FADEC?
08 Replace the FADEC with ATTCSC (bit 18) = 0 (Ref. 73-25-10-000-801/73-25-10-400-801 MM). -Yes
| No 04 Go to Block 05
EICAS Message: ATTCS FAIL EFFECTIVITY:ALL
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05 With both thrust levers above 45 degrees TLA, does ATTCSA (bit 19) = 0 for either FADEC?
09 Replace the FADEC with ATTCSA (bit 19) -Yes = 0 (Ref. 73-25-10-000-801/73-25-10-400-801 MM).
| No |
10 Do the troubleshooting on the aircraft avionics system (data acquisition unit, IC-600) (Ref. 31-42-00/201 EMB FIM).
EICAS Message: ATTCS FAIL EFFECTIVITY:ALL
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EICAS Message: FADEC ID NO DISP DESCRIPTION: This message occurs when the FADECs detect that the engine model application number assigned to the FADECs for this engine do not match or, the engine model application number assigned to ENG1 and ENG2 FADECs do not match. The FADEC power up test compares engine model application number between FADECs on each engine separately. The EICAS computer will compare the assigned engine model application number between ENG1 and ENG2. Any detected application number mismatches are annunciated using this message.
POSSIBLE CAUSES: 1. Incorrect FADEC application (part number) installed in aircraft 2. FADEC 3. Cross-channel data link (CCDL), W4 harness
01 Get access to the FADECs in the rear electronics compartment. Do all four (4) of the FADEC part numbers match?
03 Replace the FADECs that are not assigned -No to this engine model (Ref. 73-25-10-000-801/73-25-10-400-801 MM).
| Yes R
02 Supply electrical power to the aircraft. Access FADEC discrete label 352 from the central maintenance computer (CMC) for both FADECs on each engine (Ref. Introduction). Does AIDNOK (bit 12) = 1 ?
-Yes
04 Do the troubleshooting for AIDNOK (bit 12) (Ref. 73-25-00-810-868-A01).
| No | 05 De-energize and energize the FADECs for each engine and do this task again.
EICAS Message: FADEC ID NO DISP R EFFECTIVITY:FADEC SOFTWARE VER. B5.1.1
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EICAS Message: FADEC ID NO DISP DESCRIPTION: This message occurs when the FADECs detect that the engine model application number assigned to the FADECs for this engine do not match or, the engine model application number assigned to ENG1 and ENG2 FADECs do not match. The FADEC power up test compares engine model application number between FADECs on each engine separately. The EICAS computer will compare the assigned engine model application number between ENG1 and ENG2. Any detected application number mismatches are annunciated using this message.
POSSIBLE CAUSES: 1. Incorrect FADEC application (part number) installed in aircraft 2. FADEC 3. Cross-channel data link (CCDL), W4 harness
01 Get access to the FADECs in the rear electronics compartment. Do all four (4) of the FADEC part numbers match?
03 Replace the FADECs that are not assigned -No to this engine model (Ref. 73-25-10-000-801/73-25-10-400-801 MM).
| Yes 02 Supply electrical power to the aircraft. Access FADEC discrete label 352 from the central maintenance computer (CMC) for both FADECs on each engine (Ref. Introduction). Does AFINOK (bit 12) = 1 ?
-Yes
04 Do the troubleshooting for AFINOK (bit 12) (Ref. 73-25-00-810-868-B01).
| No | 05 De-energize and energize the FADECs for each engine and do this task again.
EICAS Message: FADEC ID NO DISP R EFFECTIVITY:FADEC SOFTWARE VER. B7.5 OR R LATER
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Maintenance Message: ND - ENG1/ENG2 DUAL PMA SYS (set by FADEC Discrete: PMABLF (bit 25) / (354 / CFPLRU) = 1) DESCRIPTION: This message occurs when the FADEC finds that while the engine is operating, the PMA is not providing sufficient electrical power to both FADECs (N2 greater than 54%) or when the PMA is not providing sufficient electrical power to a FADEC and the CCDL has failed. The FADEC will operate on 28 VDC provided by the aircraft electrical system when the engine is not operating or when the PMA power source has failed.
POSSIBLE CAUSES: 1. PMA stator 2. Harness 3. FADEC 4. PMA rotor CAUTION: DO NOT INSTALL A REPLACEMENT FADEC IN THE POSITION OF THE AFFECTED FADEC UNTIL THE PMA STATOR AND THE W11/14 AND W7 HARNESS HAVE BEEN TESTED. DAMAGE TO THE FADEC COULD RESULT.
01 Access the central maintenance computer (CMC) Maintenance Messages (Ref. Introduction). Did an ND - ENG1/ENG2 COMM A/B message occur prior to or at the same time as the ND - ENG1/ENG2 DUAL PMA SYS message?
03 Do the troubleshooting for maintenance message ND - ENG1/ENG2 COMM A/B (Ref. 77-40-00-810-807) and ST - ENG1/ENG2 PMA -Yes SYS (Ref. 73-25-00-810-817, block 02).
| No 02 Remove the PMA stator from the engine (Ref. 74-11-15-000-801 MM) and examine the stator (Ref. 74-11-15-200-801 MM) for foreign objects or damage. Are foreign objects or damage found?
-Yes
04 Replace the PMA stator (Ref. 74-11-15-000-801/74-11-15-400-801 MM).
| No |
05 Replace the PMA rotor (Ref. 74-11-10-000-801/74-11-10-400-801 MM).
Maintenance Message: ND - ENG1/ENG2 DUAL PMA SYS EFFECTIVITY:ALL
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Maintenance Message: ND-ENG1 / ENG2 FADEC A/B DESCRIPTION: This message occurs when either an application identity fault has been detected or the FADEC temperature limit has been exceeded.
POSSIBLE CAUSES: 1. FADEC application (part number) incorrectly installed in aircraft 2. FADEC 3. Cross-channel data link (CCDL) harness (W4) 4. Airframe rear electronics compartment cooling failure
R
01 Supply electrical power to the aircraft. Access FADEC discrete label 352 from the central maintenance computer (CMC) for both FADECs (Ref. Introduction). Does AIDNOK (bit 12) = 1?
-Yes
03 Do the troubleshooting for AIDNOK (bit 12) (Ref. 73-25-00-810-868-A01).
| No 02 Access FADEC discrete label 360 from the 04 Do the troubleshooting for FADTMF (bit CMC (Ref. Introduction). Does FADTMF (bit -Yes 18) (Ref. 73-25-00-810-820). 18) = 1 ? | No |
05 Operate the engine (Ref. AMM) and do the procedure again.
Maintenance Message: ND-ENG1 / ENG2 FADEC A/B EFFECTIVITY:ALL
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Maintenance Message: ST-ENG1/ENG2 CTL A/B SYS DESCRIPTION: This message is displayed when a FADEC control-system fault has occurred.
POSSIBLE CAUSES: 1. Engine/FADEC interface fault 2. Aircraft/FADEC interface fault 3. FADEC/FADEC interface fault 4. FADEC internal fault
01 Did the aircraft experience an uncommanded thrust mode increase or the loss of ECS packs during the takeoff prior to the maintenance message?
12 This maintenance message can be incorrectly set by a reduced bleed request output driver difference fault during takeoff, if -Yes an uncommanded thrust mode increase occurs or the ECS packs close during takeoff. Return the aircraft to service.
| No 02 Supply electrical power to the aircraft. Access FADEC discrete label 265 from the central maintenance computer (CMC) for both FADECs (Ref. Introduction). Does RBRQDF (bit 26) = 1?
-Yes
13 Do the troubleshooting for RBRQDF (bit 26) = 1 (Ref. 73-25-00-810-833).
| No 03 Access FADEC discrete label 355 from the 14 Do the troubleshooting for CHNFLT (bit CMC (Ref. Introduction). Does CHNFLT (bit -Yes 15) = 1 (Ref. 73-25-00-810-855). 15) = 1? | No 04 Does STFAIL (bit 21) = 1?
-Yes
15 Do the troubleshooting for STFAIL (bit 21) = 1 (Ref. 73-25-00-810-818).
| No 05 Go to Block 06
Maintenance Message: ST-ENG1/ENG2 CTL A/B SYS R EFFECTIVITY:FADEC SOFTWARE VER. B5.1.1
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06 Access FADEC discrete label 356 from the 16 Do the troubleshooting for INHFLB (bit 20) CMC (Ref. Introduction). Does INHFLB (bit 20) -Yes = 1 (Ref. 73-25-00-810-834). = 1? | No 07 Access FADEC discrete label 354 from the 17 Do the troubleshooting for AIDPFT (bit 20) CMC (Ref. Introduction). Does AIDPFT (bit 20) -Yes = 1 (Ref. 73-25-00-810-869). = 1? | No 08 Access FADEC discrete label 360 from the 18 Do the troubleshooting for V5RFLT (bit CMC (Ref. Introduction). Does V5RFLT (bit 19) -Yes 19) = 1 (Ref. 73-25-00-810-824). = 1? | No 09 Does V15RFT (bit 20) = 1?
-Yes
19 Do the troubleshooting for V15RFT (bit 20) (Ref. 73-25-00-810-825).
-Yes
20 Do the troubleshooting for IDTFL (bit 24) = 1 (Ref. 73-25-00-810-848).
-Yes
21 Do the troubleshooting for FADFLT (bit 27) = 1 (Ref. 73-25-00-810-831).
| No 10 Does IDTFL (bit 24) = 1? | No 11 Does FADFLT (bit 27) = 1? | No | 22 Examine the harness connectors at the FADEC J4 receptacle and the W11/W14 harnesses for looseness, corrosion, contamination, or damage. Tighten, clean, or repair the harness(es) as necessary (Ref. 20-50-00 WM) (Ref. 70-00-00-910-804 MM).
Maintenance Message: ST-ENG1/ENG2 CTL A/B SYS R EFFECTIVITY:FADEC SOFTWARE VER. B5.1.1
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Maintenance Message: ST-ENG1/ENG2 CTL A/B SYS DESCRIPTION: This message is displayed when a FADEC control-system fault has occurred.
POSSIBLE CAUSES: 1. Engine/FADEC interface fault 2. Aircraft/FADEC interface fault 3. FADEC/FADEC interface fault 4. FADEC internal fault
01 Did the aircraft experience an uncommanded thrust mode increase or the loss of ECS packs during the takeoff prior to the maintenance message?
11 This maintenance message can be incorrectly set by a reduced bleed request output driver difference fault during takeoff, if -Yes an uncommanded thrust mode increase occurs or the ECS packs close during takeoff. Return the aircraft to service.
| No 02 Supply electrical power to the aircraft. Access FADEC discrete label 355 from the CMC (Ref. Introduction). Does CHNFLT (bit 15) = 1?
-Yes
12 Do the troubleshooting for CHNFLT (bit 15) = 1 (Ref. 73-25-00-810-855).
| No 03 Does STFAIL (bit 21) = 1?
-Yes
13 Do the troubleshooting for STFAIL (bit 21) = 1 (Ref. 73-25-00-810-818).
| No 04 Access FADEC discrete label 356 from the 14 Do the troubleshooting for INHFLB (bit 20) CMC (Ref. Introduction). Does INHFLB (bit 20) -Yes = 1 (Ref. 73-25-00-810-834). = 1? | No 05 Go to Block 06.
Maintenance Message: ST-ENG1/ENG2 CTL A/B SYS EFFECTIVITY:FADEC SOFTWARE VER. B7.5 OR LATER & AIRCRAFT CMC SOFTWARE VERSION 15 OR EARLIER
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06 Access FADEC discrete label 354 from the 15 Do the troubleshooting for AIDPFT (bit 20) CMC (Ref. Introduction). Does AIDPFT (bit 20) -Yes = 1 (Ref. 73-25-00-810-869). = 1? | No 07 Access FADEC discrete label 360 from the 16 Do the troubleshooting for V5RFLT (bit 19) CMC (Ref. Introduction). Does V5RFLT (bit 19) -Yes = 1 (Ref. 73-25-00-810-824). = 1? | No 08 Does V15RFT (bit 20) = 1?
-Yes
17 Do the troubleshooting for V15RFT (bit 20) (Ref. 73-25-00-810-825).
-Yes
18 Do the troubleshooting for IDTFL (bit 24) = 1 (Ref. 73-25-00-810-848).
-Yes
19 Do the troubleshooting for FADFLT (bit 27) = 1 (Ref. 73-25-00-810-831).
| No 09 Does IDTFL (bit 24) = 1? | No 10 Does FADFLT (bit 27) = 1? | No | 20 Examine the harness connectors at the FADEC J4 receptacle and the W11/W14 harnesses for looseness, corrosion, contamination, or damage. Tighten, clean, or repair the harness(es) as necessary (Ref. 20-50-00 WM) (Ref. 70-00-00-910-804 MM).
Maintenance Message: ST-ENG1/ENG2 CTL A/B SYS EFFECTIVITY:FADEC SOFTWARE VER. B7.5 OR LATER & AIRCRAFT CMC SOFTWARE VERSION 15 OR EARLIER
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Maintenance Message: ND-ENG1/ENG2 FADEC A/B DESCRIPTION: This message is displayed when a FADEC control-system fault has occurred.
POSSIBLE CAUSES: 1. Engine/FADEC interface fault 2. Aircraft/FADEC interface fault 3. FADEC/FADEC interface fault 4. FADEC internal fault
01 Did the aircraft experience an uncommanded thrust mode increase or the loss of ECS packs during the takeoff prior to the maintenance message?
11 This maintenance message can be incorrectly set by a reduced bleed request output driver difference fault during takeoff, if -Yes an uncommanded thrust mode increase occurs or the ECS packs close during takeoff. Return the aircraft to service.
| No 02 Supply electrical power to the aircraft. Access FADEC discrete label 355 from the CMC (Ref. Introduction). Does CHNFLT (bit 15) = 1?
-Yes
12 Do the troubleshooting for CHNFLT (bit 15) = 1 (Ref. 73-25-00-810-855).
| No 03 Does STFAIL (bit 21) = 1?
-Yes
13 Do the troubleshooting for STFAIL (bit 21) = 1 (Ref. 73-25-00-810-818).
| No 04 Access FADEC discrete label 356 from the 14 Do the troubleshooting for INHFLB (bit 20) CMC (Ref. Introduction). Does INHFLB (bit 20) -Yes = 1 (Ref. 73-25-00-810-834). = 1? | No 05 Go to Block 06.
Maintenance Message: ND-ENG1/ENG2 FADEC A/B EFFECTIVITY:AIRCRAFT CMC SOFTWARE VERSION 16 OR LATER
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06 Access FADEC discrete label 354 from the 15 Do the troubleshooting for AIDPFT (bit 20) CMC (Ref. Introduction). Does AIDPFT (bit 20) -Yes = 1 (Ref. 73-25-00-810-869). = 1? | No 07 Access FADEC discrete label 360 from the 16 Do the troubleshooting for V5RFLT (bit 19) CMC (Ref. Introduction). Does V5RFLT (bit 19) -Yes = 1 (Ref. 73-25-00-810-824). = 1? | No 08 Does V15RFT (bit 20) = 1?
-Yes
17 Do the troubleshooting for V15RFT (bit 20) (Ref. 73-25-00-810-825).
-Yes
18 Do the troubleshooting for IDTFL (bit 24) = 1 (Ref. 73-25-00-810-848).
-Yes
19 Do the troubleshooting for FADFLT (bit 27) = 1 (Ref. 73-25-00-810-831).
| No 09 Does IDTFL (bit 24) = 1? | No 10 Does FADFLT (bit 27) = 1? | No | 20 Examine the harness connectors at the FADEC J4 receptacle and the W11/W14 harnesses for looseness, corrosion, contamination, or damage. Tighten, clean, or repair the harness(es) as necessary (Ref. 20-50-00 WM) (Ref. 70-00-00-910-804 MM).
Maintenance Message: ND-ENG1/ENG2 FADEC A/B EFFECTIVITY:AIRCRAFT CMC SOFTWARE VERSION 16 OR LATER
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Maintenance Message: LT-ENG MODE SYS DIFF DESCRIPTION: This message occurs when the condition of either the two maximum-continuous-mode, cruise-mode, or climb-mode switch circuits (Active/Not Active) sensed by FADEC A and B is not the same.
POSSIBLE CAUSES: 1. Maximum-continuous-mode switch circuit 2. Cruise-mode switch circuit 3. Climb-mode switch circuit 4. FADEC
01 Supply electrical power to the aircraft. Access FADEC discrete label 264 from the central maintenance computer (CMC) (Ref. Introduction). Does MXCDIF (bit 28) = 1?
-Yes
04 Do the troubleshooting for MXCDIF (bit 28) = 1 (Ref. 73-25-00-810-842).
| No 02 Does CRZDIF (bit 27) = 1?
-Yes
05 Do the troubleshooting for CRZDIF (bit 27) = 1 (Ref. 73-25-00-810-843).
-Yes
06 Do the troubleshooting for CLBDIF (bit 26) = 1 (Ref. 73-25-00-810-844).
| No 03 Does CLBDIF (bit 26) = 1? | No |
07 Examine all of the electrical connectors and harness connectors between the mode switches, the W1 harness, and the FADEC J2 receptacle for looseness, corrosion, contamination, or damage. Tighten, clean or repair the harness as necessary (Ref. 76-12-57/76-12-58 WM) (Ref. 70-00-00-910-804 MM).
Maintenance Message: LT-ENG MODE SYS DIFF EFFECTIVITY:ALL
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Maintenance Message: LT-ENG A/I SYS DIFF DESCRIPTION: This message occurs when the FADEC finds the channel A and B anti-ice system indication switch circuit conditions are not the same (ON/OFF).
POSSIBLE CAUSES: 1. Aircraft circuit fault 2. FADEC
01 Supply electrical power to the aircraft. 03 Do the troubleshooting for FADEC discrete Access FADEC discrete label 264 from the AISIDF (bit 21) = 1 (Ref. 73-25-00-810-803). central maintenance computer (CMC) for both -Yes FADECs (Ref. Introduction). Does AISIDF (bit 21) = 1? | No 02 Turn the engine anti-ice on for a minimum of two (2) seconds. Does AISIDF (bit 21) = 1?
-Yes
04 Do the troubleshooting for FADEC discrete AISIDF (bit 21) = 1 (Ref. 73-25-00-810-803).
| No |
05 Examine all of the harness connectors between the anti-ice switch and the FADEC. Clean or repair them as necessary (Ref. 30-20-50/30-20-51 WM) (Ref. 70-00-00-910-804 MM).
Maintenance Message: LT-ENG A/I SYS DIFF EFFECTIVITY:ALL
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Maintenance Message: LT-ENG1/ENG2 CTL I/O SYS DESCRIPTION: R R
This message occurs when the FADEC self-test finds an engine-control system fault, or a fault bit is set for one of the following hardwired discretes: shutoff-interlock output drive, FADEC-capable output drive, or this FADEC-in-control output drive (Ref. FIG. 301/TASK 73-25-00-990-801).
POSSIBLE CAUSES: 1. Loose FADEC connectors 2. FADEC 3. N1 speed sensor (primary) 4. N2 speed sensor (primary) 5. Inter-FADEC harness (CCDL)
01 Examine the FADEC J3 connectors for looseness on both FADECs. Are the connectors tight?
11 Tighten the connectors (Ref. -No 70-00-00-910-804 MM).
| Yes 02 Supply electrical power to the aircraft. Access FADEC discrete label 360 from the central maintenance computer (CMC) for both FADECs (Ref. Introduction). Does SOIFLT (bit 11) = 1?
-Yes
12 Do the troubleshooting for FADEC discrete SOIFLT (bit 11) = 1 (Ref. 77-40-00-810-804).
| No 03 Does CAPOFT (bit 12) = 1?
-Yes
13 Do the troubleshooting for FADEC discrete CAPOFT (bit 12)= 1 (Ref. 77-40-00-810-805).
-Yes
14 Do the troubleshooting for FADEC discrete TLICFT (bit 13) = 1 (Ref. 77-40-00-810-806).
| No 04 Does TLICFT (bit 13) = 1? | No 05 Go to Block 06
Maintenance Message: LT-ENG1/ENG2 CTL I/O SYS EFFECTIVITY:ALL
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06 Does N1OSF (bit 14) = 1?
15 Do the troubleshooting for FADEC discrete -Yes N1OSF (bit 14) = 1 (Ref. 73-25-00-810-822-B01).
| No 07 Does N2OSF (bit 15) = 1?
16 Do the troubleshooting for FADEC discrete -Yes N2OSF (bit 15) = 1 (Ref. 73-25-00-810-823-B01).
| No 08 Does MMVDLF (bit 28) = 1?
-Yes
17 Do the troubleshooting for FADEC discrete MMVDLF (bit 28) = 1 (Ref. 73-21-00-810-813).
-Yes
18 Do the troubleshooting for FADEC discrete CVGDLF (bit 29) = 1 (Ref. 73-21-00-810-814).
| No 09 Does CVGDLF (bit 29) = 1? | No 10 Operate the engine to the maximum thrust practical and do a normal shutdown (Ref. AMM). Do not remove electrical power from the FADECs. Repeat the procedures starting from block 01. Do any of the FADEC discrete(s) = 1?
19 Do the troubleshooting for the FADEC discrete(s). -Yes
| No |
20 Access the CMC after subsequent flights. Do not remove electrical power from the FADECs. Repeat the procedure.
Maintenance Message: LT-ENG1/ENG2 CTL I/O SYS EFFECTIVITY:ALL
TASK 73−25−00−810−865 Page 202 Aug 15/04
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Maintenance Message: LT-ENG1/ENG2 STOP SYS DESCRIPTION: This message occurs when the FADEC finds an open or shorted circuit condition.
POSSIBLE CAUSES: 1. Aircraft circuit fault 2. FADEC
01 Supply electrical power to the aircraft. Access FADEC discrete label 351 from the central maintenance computer (CMC) for both FADECs (Ref. Introduction). Does STPFLT (bit 12) = 1?
-Yes
02 Do the troubleshooting for FADEC discrete STPFLT (bit 12) = 1 (Ref. 73-25-00-810-853).
| No |
03 Examine all of the harness connectors between the start/stop switch and the FADEC. Clean or repair them as necessary (Ref. 80-10-50/80-10-51 WM) (Ref. 70-00-00-910-804 MM).
Maintenance Message: LT-ENG1/ENG2 STOP SYS EFFECTIVITY:ALL
TASK 73−25−00−810−866 Page 201/202 Feb 15/03
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Maintenance Message: ND-ENG1/ENG2 STOP SYS DIFF DESCRIPTION: This message occurs when the FADEC finds channel A and B circuit conditions are not the same (STOP/ not STOP).
POSSIBLE CAUSES: 1. Aircraft circuit fault 2. FADEC
01 Supply electrical power to the aircraft. Put 03 Do the troubleshooting for FADEC discrete the STOP/RUN/START switch in the STOP STPDIF (bit 12) = 1 (Ref. 73-25-00-810-854). position. Access FADEC discrete label 264 -Yes from the central maintenance computer (CMC) for both FADECs (Ref. Introduction). Does STPDIF (bit 12) = 1? | No 02 Put the STOP/RUN/START switch in the RUN position (do not move to START) for at least 2.0 seconds. Does STPDIF (bit 12) = 1?
04 Do the troubleshooting for FADEC discrete -Yes STPDIF (bit 12) = 1 (Ref. 73-25-00-810-854).
| No |
05 Examine all of the harness connectors between the START/STOP switch and the FADEC. Clean or repair them as necessary (Ref. 80-10-50/80-10-51 WM).
Maintenance Message: ND-ENG1/ENG2 STOP SYS DIFF EFFECTIVITY:ALL
TASK 73−25−00−810−867 Page 201/202 Feb 15/03
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FADEC Discrete: AIDNOK (bit 12) / (352 / AILRU2) = 1 DESCRIPTION: This discrete is set = 1 when, during FADEC power up, and the engine is not running, any of the following occur: (1)
There is an engine model application number mismatch between the controlling and standby FADECs on the engine
(2)
Either FADEC has failed its application ID parity test and:
(3)
-
The cross-channel data link (CCDL) information is not available or
-
The other FADEC on this engine has also failed its application ID parity test.
The N2 overspeed shutdown trip point does not match the requirement for the engine application
POSSIBLE CAUSES: 1. Incorrect FADEC part number installed in aircraft 2. FADEC 3. Cross-channel data link (CCDL) harness (W4)
01 Compare the FADEC part numbers for this engine installed in the aircraft's rear electronics compartment. Do all four (4) of the FADEC part numbers match?
06 Replace the FADEC(s) that are not assigned to this engine model (Ref. -No 73-25-10-000-801/73-25-10-400-801 MM).
| Yes 02 Supply electrical power to the aircraft. Access FADEC discrete label 354 from the central maintenance computer (CMC) for both FADECs and both engines (Ref. Introduction). Does XTLKFT (bit 11) = 1?
07 Disconnect the CCDL harness (W4) from the J3 receptacles on both FADECs (Ref. FIG. 307/TASK 73-25-00-990-807). Examine the -Yes harness connectors for looseness, damage, corrosion, or contamination. Tighten, clean, or repair the harness as necessary (Ref. 70-00-00-910-804 MM).
| No 03 Does AIDPFT (bit 20) = 1 on any of the four 08 Replace the FADEC that has the fault (Ref. -Yes (4) FADECs? 73-25-10-000-801/73-25-10-400-801 MM). | No 04 Go to Block 05
FADEC Discrete: AIDNOK (bit 12) / (352 / AILRU2) = 1 R EFFECTIVITY:FADEC SOFTWARE VER. B7.5 OR R LATER
TASK 73−25−00−810−868−A01 Page 201 Oct 15/05
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05 De-energize and energize all four (4) FADECs. Do the procedure above one more time. If either of the other engine's FADECs show AIDNOK (bit 12) = 1, interchange the position of one FADEC from this engine to the other engine and do this task starting at block 02 again for each FADEC until the fault is found. Does the fault follow the FADEC?
09 Replace the FADEC that has the fault (Ref. 73-25-10-000-801/73-25-10-400-801 MM). -Yes
| No |
10 Do the troubleshooting on the aircraft's avionics system (data acquisition unit (DAU), IC-600) (Ref. 31-42-00/201 EMB FIM).
FADEC Discrete: AIDNOK (bit 12) / (352 / AILRU2) = 1 R EFFECTIVITY:FADEC SOFTWARE VER. B7.5 OR R LATER
TASK 73−25−00−810−868−A01 Page 202 Oct 15/05
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FADEC Discrete: AFINOK (bit 12) / (352 / AILRU2) = 1 DESCRIPTION: This discrete is set = 1 when, during FADEC power up, and the engine is not running, any of the following occur: (1)
There is an engine model application number mismatch between the controlling and standby FADECs on the engine
(2)
Either FADEC has failed its application ID parity test and:
(3)
-
The cross-channel data link (CCDL) information is not available or
-
The other FADEC on this engine has also failed its application ID parity test.
The N2 overspeed shutdown trip point does not match the requirement for the engine application
POSSIBLE CAUSES: 1. Incorrect FADEC part number installed in aircraft 2. FADEC 3. Cross-channel data link (CCDL) harness (W4)
R
01 Compare the FADEC part numbers for this engine installed in the aircraft's rear electronics compartment. Do all four (4) of the FADEC part numbers match?
07 Replace the FADEC(s) that are not assigned to this engine model (Ref. -No 73-25-10-000-801/73-25-10-400-801 MM).
| Yes R
02 Supply electrical power to the aircraft. Access FADEC discrete label 354 from the central maintenance computer (CMC) for both FADECs and both engines (Ref. Introduction). Does XTLKFT (bit 11) = 1?
08 Disconnect the CCDL harness (W4) from the J3 receptacles on both FADECs (Ref. FIG. 307/TASK 73-25-00-990-807). Examine the -Yes harness connectors for looseness, damage, corrosion, or contamination. Tighten, clean, or repair the harness as necessary (Ref. 70-00-00-910-804 MM).
| No R
03 Does AIDPFT (bit 20) = 1 on any of the four 09 Replace the FADEC that has the fault (Ref. -Yes (4) FADECs? 73-25-10-000-801/73-25-10-400-801 MM). | No 04 Go to Block 05
FADEC Discrete: AFINOK (bit 12) / (352 / AILRU2) = 1 EFFECTIVITY:FADEC SOFTWARE VER. B7.5 OR LATER
TASK 73−25−00−810−868−B01 Page 201 Jul 20/14
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R R R R
05 Has SB AE3007A-73-090 been embodied to install high speed FADECs and trim plugs?
R
06 De-energize and energize all four (4) FADECs. Do the procedure above one more time. If either of the other engine's FADECs show AFINOK (bit 12) = 1, interchange the position of one FADEC from this engine to the other engine and do this task starting at block 02 again for each FADEC until the fault is found. Does the fault follow the FADEC?
10 Verify that E1 and E2 trim plugs are correct, (Ref. 77-21-25-400-801, MM) Table 404. If yes, -Yes to to Block 06. If no, replace the FADECs and trim plugs (Ref. SB AE3007A-73-090). 11 Replace the FADEC that has the fault (Ref. 73-25-10-000-801/73-25-10-400-801 MM). -Yes
| No | R R R
12 Do the troubleshooting on the aircraft's avionics system (data acquisition unit (DAU), IC-600) (Ref. 31-42-00/201 EMB FIM).
FADEC Discrete: AFINOK (bit 12) / (352 / AILRU2) = 1 EFFECTIVITY:FADEC SOFTWARE VER. B7.5 OR LATER
TASK 73−25−00−810−868−B01 Page 202 Jul 20/14
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FADEC Discrete: AIDPFT (bit 20) / (354/CFPLRU) = 1 DESCRIPTION: During FADEC power up, this discrete is set = 1 when this FADEC fails the application ID parity test or the engine application ID number stored in EEPROM does not correspond to a defined engine application. This discrete bit sets the FADEC fault bit FADFLT (bit 27) of label 360 annuciated on the ARINC 429 data bus.
POSSIBLE CAUSES: 1. FADEC
01 Replace the FADEC that has the fault (Ref. 73-25-10-000-801/73-25-10-400-801 MM).
FADEC Discrete: AIDPFT (bit 20) / (354/CFPLRU) = 1 EFFECTIVITY:ALL
TASK 73−25−00−810−869 Page 201/202 Feb 15/03
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Observed fault: FADEC Does Not Change Lanes On Start DESCRIPTION: The pilot has no control over which FADEC channel controls the start. The channel that controlled the previous start was recorded to memory. When a start is initiated, the other channel controls the start, and then records the start to memory. Control of the engine start changes back and forth between channels A and B.
POSSIBLE CAUSES: 1. FADEC
01 Do the engine runs and flights for the FADEC lane change pro forma data (Ref. 71-00-00-900-804 MM). | Yes 02 Does the FADEC change lanes when commanded?
-No
04 Download the CMC and check for fault codes. Troubleshoot for the fault codes found.
| Yes 03 Did the FADEC in control alternate lanes between consecutive start? Example: A-B-A-B or B-A-B-A
05 Download the CMC and check for fault -No codes. Contact Roll-Royce with this data and the data from block 01.
| Yes
06 Return the engine to service.
Observed fault: FADEC Does Not Change Lanes On Start EFFECTIVITY:ALL
TASK 73−25−00−810−870 Page 201/202 Jul 20/11
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Anti-ice System Indicator Switch / FADEC Interface Diagram FIG. 301/TASK 73-25-00-990-801 EFFECTIVITY:ALL
73−25−TASK SUPPORT Page 301 Aug 15/06
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Landing Gear Down and Locked Position Relay / FADEC Interface Diagram FIG. 302/TASK 73-25-00-990-802 EFFECTIVITY:ALL
73−25−TASK SUPPORT Page 302 Aug 15/06
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FADEC Reset/Select Switch / FADEC Interface Diagram FIG. 303/TASK 73-25-00-990-803 EFFECTIVITY:ALL
73−25−TASK SUPPORT Page 303 Aug 15/06
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Takeoff Data Increment/Decrement Switch / FADEC Interface Diagram FIG. 304/TASK 73-25-00-990-804 EFFECTIVITY:ALL
73−25−TASK SUPPORT Page 304 Aug 15/06
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Takoff Data Store Switch / FADEC Interface Diagram FIG. 305/TASK 73-25-00-990-805 EFFECTIVITY:ALL
73−25−TASK SUPPORT Page 305 Aug 15/06
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FADEC Power Source Diagram FIG. 306/TASK 73-25-00-990-806 EFFECTIVITY:ALL
73−25−TASK SUPPORT Page 306 Aug 15/06
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Engine Wiring Diagram FIG. 307/TASK 73-25-00-990-807 EFFECTIVITY:ALL
73−25−TASK SUPPORT Page 307 Aug 15/06
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Maximum Takeoff Mode Switch / FADEC Interface Diagram FIG. 308/TASK 73-25-00-990-808 EFFECTIVITY:ALL
73−25−TASK SUPPORT Page 308 Aug 15/06
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Climb Mode Switch / FADEC Interface Diagram FIG. 309/TASK 73-25-00-990-809 EFFECTIVITY:ALL
73−25−TASK SUPPORT Page 309 Aug 15/06
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Cruise Mode Switch / FADEC Interface Diagram FIG. 310/TASK 73-25-00-990-810 EFFECTIVITY:ALL
73−25−TASK SUPPORT Page 310 Aug 15/06
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Maximum Continuous Mode Switch / FADEC Interface Diagram FIG. 311/TASK 73-25-00-990-811 EFFECTIVITY:ALL
73−25−TASK SUPPORT Page 311 Aug 15/06
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FADEC Identification Jumper Diagram FIG. 312/TASK 73-25-00-990-812 EFFECTIVITY:ALL
73−25−TASK SUPPORT Page 312 Aug 15/06
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Start/Stop Switch / FADEC Interface Diagram FIG. 313/TASK 73-25-00-990-813 EFFECTIVITY:ALL
73−25−TASK SUPPORT Page 313 Aug 15/06
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R
R R
CVG Position Sensor (LVDT) / FADEC Interface Diagram FIG. 314/TASK 73-25-00-990-814 EFFECTIVITY:ALL
73−25−TASK SUPPORT Page 314 Aug 15/06
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R
R R
T2.5 Sensor / FADEC Interface Diagram FIG. 315/TASK 73-25-00-990-815 EFFECTIVITY:ALL
73−25−TASK SUPPORT Page 315 Aug 15/06
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R
R R
P2.5 Sensor / FADEC Interface Diagram FIG. 316/TASK 73-25-00-990-816 EFFECTIVITY:ALL
73−25−TASK SUPPORT Page 316 Aug 15/06
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Maintenance Message: ENG1/ENG2 FUEL HIGH TEMP DESCRIPTION: This message occurs when the temperature of the fuel discharged from the fuel-cooled oil cooler (FCOC) is above 113 °C.
POSSIBLE CAUSES: R R
R R R R
1. External engine-indicating harness (W9) 2. Fuel temperature sensor 3. Fuel cooled oil cooler (FCOC) 4. Aircraft system, signal conditioning fault
01 Do the inspection of the external harness 07 Clean the connector (Ref. (W9) connector at the fuel temperature sensor 70-00-00-910-804 MM) or replace the harness -Yes for corrosion, contamination, or damage. Is the (Ref. 76-00-00 MM) (Ref. AMM). connector dirty or damaged? | No 02 Replace the fuel temperature sensor (Ref. 73-31-10-000-801/73-31-10-400-801 MM). Is the fault removed?
08 Remove the fuel temperature sensor from -Yes service.
| No R
03 Do a test for continuity/resistance (1 ohm max./harness), internal shorts, and shorts to ground (1,000 ohms min.) on the external engine-indicating harness (W9) (Ref. FIG. 301/TASK 73-31-00-990-801/FIG. 302/TASK 73-31-00-990-802) (Ref. 73-30-50/ 73-30-51 WM). Does the harness test satisfactorily?
09 Go to block 06. -Yes
| No R R R
04 Replace the external engine-indicating harness (W9) (Ref. 76-00-00 MM). Is the fault removed?
R R R R
10 Remove the external engine-indicating -Yes harness from service.
| No 05 Go to block 06.
Maintenance Message: ENG1/ENG2 FUEL HIGH TEMP EFFECTIVITY:ALL
TASK 73−31−00−810−801 Page 201 Jul 20/12
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R R R
06 Replace the FCOC (Ref. 79-25-15-000-801/79-25-15-400-801 MM). Is the fault removed?
R R R
| No |
R R R
-Yes
11 Remove the FCOC from service.
12 Do the troubleshooting on the aircraft systems (harness, signal conditioning unit) (Ref. 73-30-50/73-30-51 WM).
Maintenance Message: ENG1/ENG2 FUEL HIGH TEMP EFFECTIVITY:ALL
TASK 73−31−00−810−801 Page 202 Jul 20/12
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EICAS Message: E1/E2 FUEL LOW TEMP DESCRIPTION: This message occurs when the temperature of the fuel discharged from the fuel-cooled oil cooler (FCOC) is below 5 °C and N2 RPM is above 53%.
POSSIBLE CAUSES: 1. Oil temperature low 2. FCOC 3. Fuel temperature sensor 4. Harness (W9) 5. Aircraft system, signal conditioning fault
01 Is the oil temperature low?
06 Low fuel temperature is a normal indication -Yes when the oil temperature is low, at low ambient temperatures.
| No 02 Replace the FCOC (Ref. 79-25-15-000-801/ 79-25-15-400-801 MM). Is the fault removed?
-Yes
07 Remove the FCOC from service.
| No 03 Replace the fuel temperature sensor (Ref. 73-31-10-000-801/73-31-10-400-801 MM). Is the fault removed?
08 Remove the fuel temperature sensor from -Yes service.
| No 04 Go to Block 05
EICAS Message: E1/E2 FUEL LOW TEMP EFFECTIVITY:ALL
TASK 73−31−00−810−802 Page 201 Aug 15/04
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R R
05 Do a test for continuity/resistance (1 ohm max./harness), internal shorts, and shorts to ground (1,000 ohms min.) on the external engine-indicating harness (W9) (Ref. FIG. 301/TASK 73-31-00-990-801) (Ref. 73-30-50/ 73-30-51 WM). Does the harness test satisfactorily?
-Yes
09 Do the troubleshooting on the aircraft systems (harness, signal conditioning unit) (Ref. 73-30-50/73-30-51 WM).
| No |
10 Replace the external engine-indicating harness (Ref. 76-00-00 MM).
EICAS Message: E1/E2 FUEL LOW TEMP EFFECTIVITY:ALL
TASK 73−31−00−810−802 Page 202 Aug 15/04
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Fuel Temperature Sensor Installation FIG. 3012/TASK 73-31-00-990-801
R EFFECTIVITY:ALL
73−31−TASK SUPPORT Page 301 Aug 15/04
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Engine Wiring Diagram FIG. 302/TASK 73-31-00-990-802
R EFFECTIVITY:ALL
73−31−TASK SUPPORT Page 302 Aug 15/04
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EICAS Message: E1/E2 FUEL IMP BYP DESCRIPTION: This message occurs when there is an impending bypass of the fuel filter.
POSSIBLE CAUSES: 1. Fuel filter blocked 2. Electrical fuel-filter impending-bypass indicator 3. Harness (W9)
01 Is the electrical fuel-filter impending-bypass indicator red pop-up indicator extended?
07 Replace the FPMU impending bypass indicator and send the part to the supplier for -No investigation (Ref. 73-37-10-000-801/73-37-10-400-801 MM).
| Yes 02 Remove the glass cap on the electrical 08 Discard the FPMU fuel filter. fuel-filter impending-bypass indicator and push in the pop-up indicator. Install the glass cap and torque the nut to the value marked on the -Yes glass cap. Replace the FPMU fuel filter (Ref. 73-21-10-000-802/73-21-10-400-802 MM). Is the fault removed? | No 03 Do a test for continuity between pins B and C on the electrical fuel-filter impending-bypass indicator (Ref. 73-30-50/73-30-51 WM). Is there continuity?
09 Replace the electrical fuel-filter impending-bypass indicator (Ref. -No 73-37-10-000-801/ 73-37-10-400-801 MM).
| Yes 04 Do a test for continuity between pins B and 10 Replace the electrical fuel-filter C on the electrical fuel-filter impending-bypass impending-bypass indicator (Ref. -Yes indicator and the indicator shell (Ref. 73-37-10-000-801/ 73-37-10-400-801 MM). 73-30-50/73-30-51 WM). Is there continuity? | No 05 Go to block 06.
EICAS Message: E1/E2 FUEL IMP BYP EFFECTIVITY:ALL
TASK 73−37−00−810−801 Page 201 Aug 15/04
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R R R
06 Do a test for continuity/resistance (1 ohm max./harness), internal shorts, and shorts to ground (1,000 ohms min.) on the external engine-indicating harness (W9) (Ref. FIG. 301/TASK 73-37-00-990-801/FIG. 302/TASK 73-37-00-990-802) (Ref. 73-30-50/ 73-30-51 WM). Does the harness test satisfactorily?
-Yes
11 Do the troubleshooting on the aircraft systems (harness, signal conditioning unit) (Ref. 73-30-50/73-30-51 WM).
| No |
12 Replace the external engine-indicating harness (Ref. 76-00-00 MM).
EICAS Message: E1/E2 FUEL IMP BYP EFFECTIVITY:ALL
TASK 73−37−00−810−801 Page 202 Aug 15/04
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Electrical Fuel-filter Impending-bypass Indicator Installation FIG. 301/TASK 73-37-00-990-801
R EFFECTIVITY:ALL
73−37−TASK SUPPORT Page 301 Aug 15/04
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Engine Wiring Diagram FIG. 302/TASK 73-37-00-990-802
R EFFECTIVITY:ALL
73−37−TASK SUPPORT Page 302 Aug 15/04
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CHAPTER 74 LIST OF EFFECTIVE PAGES
CHAPTER SECTION OTHER SUBJECT PAGE IDENT DATE 74 R Contents 1/ Apr.20/08 2 R 00-00 101/ Apr.20/08 102 13-00 201 Aug.15/04 13-00 202 Aug.15/04 13-00 301 Aug.15/04 13-00 302 Aug.15/04 30-00 201/ Feb.15/03 202 30-00 201 Aug.15/04 30-00 202 Aug.15/04 30-00 201 Aug.15/04 30-00 202 Aug.15/04 30-00 201/ Aug.15/04 202 30-00 201/ Aug.15/04 202 30-00 201/ Oct.15/05 202 R 30-00 201 Apr.20/08 30-00 301/ Aug.15/04 302 --------------- END ---------------
CHAPTER SECTION SUBJECT PAGE 74
OTHER IDENT
DATE
C=CONFIG B=BREAKOUT
CHAPTER SECTION SUBJECT PAGE 74
OTHER IDENT
DATE
LIST OF EFFECTIVE PAGES-74 Page 1/2 Oct 20/16
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CHAPTER 74 TABLE OF CONTENTS
SUBJECT
CH-SE-SUB
IGNITION FAULT CODE INDEX
74-00-00
IGNITION EXCITER Maintenance Message: ENG1/ENG2 IGNITION SYSTEM FAIL or LT-ENG1/ENG2 IGN SYS Task Support
74-13-00
IGNITION CONTROL Maintenance Message: ENG1/ENG2 IGNITION SWITCH FAIL or LT-ENG1/ENG2 IGN OFF FADEC Discrete: IGONFT (bit 13) / (351 / AILRU1) = 1 FADEC Discrete: IGOFFT (bit 14) / (351 / AILRU1) = 1 FADEC Discrete: IGONDF (bit 13) / (264 / AIDIF1) = 1 FADEC Discrete: IGOFDF (bit 14) / (264 / AIDIF1) = 1 Maintenance Message: ST-ENG1/ENG2 IGN ON SYS DIFF Observed Fault: ENG1/ENG2 IGN A/B (active ignition system after deceleration to ground idle) Task Support
74-30-00
PAGE
EFFECTIVITY
101
201 301
201 201 201 201 201 201 201 301
74−CONTENTS Page 1/2 Jan 20/16
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FAULT CODE INDEX FAULT CODE R 7430O1 00 R R R
EFFECTIVITY:ALL
FAULT DESCRIPTION
MAINT. MESSAGE
ENG1/ENG2 IGN A/B None (Observed Fault: active ignition system after RPM slows to ground idle)
GO TO FIM TASK 74-30-00-810-807
74−FAULT CODE INDEX Page 101/102 Apr 20/08
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Maintenance Message: ENG1/ENG2 IGNITION SYSTEM FAIL or LT-ENG1/ENG2 IGN SYS (set by FADEC Discrete: IGNFLT (bit 23) / (353/EILRU) = 1 DESCRIPTION: This message occurs when the FADEC finds an open or shorted ignition-relay circuit, or the driver (FADEC internal) is not in its commanded condition. This message can be incorrectly set if aircraft power to the FADEC is momentarily lost or if a FADEC circuit breaker is opened while the engine is running.
POSSIBLE CAUSES: 1. FADEC power supply interruption 2. Ignition exciter 3. Harness 4. FADEC
01 Operate the engine and shutdown (Ref. AMM). Do not remove electrical power from the FADECs. Access FADEC discrete labels 353 from the central maintenance computer (CMC) for both FADECs (Ref. Introduction). Does IGNFLT (bit 23) = 1?
07 Examine all the harness connectors between the FADEC J4 and the ignition exciter (control) receptacles for looseness, damage, -No corrosion, or contamination. Tighten, clean or repair as necessary (Ref. 70-00-00-910-804 MM).
| Yes
R R R
02 Remove and install the harness (W7, W11/14) connectors at the FADEC J4 and ignition exciter (control) receptacles (Ref. FIG. 301/TASK 74-13-00-990-801/FIG. 302/TASK 74-13-00-990-802) (Ref. 74-10-50/74-10-51 WM). Remove power from the FADECs and then supply power again. Does IGNFLT (bit 23) = 0?
08 Examine the harness connectors at the FADEC J4 and the ignition exciter (control) receptacles for damage, corrosion or contamination (Ref. FIG. 302/TASK -Yes 74-13-00-990-802 ). Repair or clean as necessary (Ref. 70-00-00-910-804 MM).
| No 03 Interchange the position of the ignition 09 Replace the ignition exciter that has the exciters (Ref. 74-13-10-000-801/ fault (Ref. 74-13-10-000-801/ 74-13-10-400-801 MM). Remove electrical 74-13-10-400-801 MM). -Yes power from the FADEC and then supply power again. Does IGNFLT (bit 23) = 1 occur on the opposite channel? | No 04 Go to block 05. Maintenance Message: ENG1/ENG2 IGNITION SYSTEM FAIL or LT-ENG1/ENG2 IGN SYS EFFECTIVITY:ALL
TASK 74−13−00−810−801 Page 201 Aug 15/04
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05 Interchange the position of the FADECs (Ref. 73-25-10-000-801/73-25-10-400-801 MM). Remove electrical power from the FADEC and then supply power again. Does IGNFLT (bit 23) = 1 occur on the opposite channel?
-Yes
10 Replace the FADEC that has the fault (Ref. 73-25-10-000-801/73-25-10-400-801 MM).
| No
R R R
06 Examine the FADEC/engine interconnect and FADEC harness (W7 and W11/14) connectors at the FADEC J4 and the ignition exciter (control) receptacles for corrosion, contamination, or damage (Ref. FIG. 301/TASK 74-13-00-990-801/FIG. 302/TASK 74-13-00-990-802) (Ref. 76-12-50/76-12-51 WM). Are the connectors dirty or damaged?
11 Clean or repair the connectors as necessary (Ref. 70-00-00-910-804 MM). -Yes
| No |
R R R
12 Do a test for continuity/resistance (1 ohm max./harness), internal shorts, and shorts to ground (1,000 ohms min.) on the W7 and the W11/14 harnesses (Ref. FIG. 301/TASK 74-13-00-990-801/FIG. 302/TASK 74-13-00-990-802) (Ref. 74-10-50/74-10-51 WM).
Maintenance Message: ENG1/ENG2 IGNITION SYSTEM FAIL or LT-ENG1/ENG2 IGN SYS EFFECTIVITY:ALL
TASK 74−13−00−810−801 Page 202 Aug 15/04
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Ignition Relay / FADEC Interface Diagram FIG. 301/TASK 74-13-00-990-801
R EFFECTIVITY:ALL
74−13−TASK SUPPORT Page 301 Aug 15/04
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Engine Wiring Diagram FIG. 302/TASK 74-13-00-990-802
R EFFECTIVITY:ALL
74−13−TASK SUPPORT Page 302 Aug 15/04
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Maintenance Message: ENG1/ENG2 IGNITION SWITCH FAIL or LT-ENG1/ENG2 IGN OFF DESCRIPTION: This message occurs when the FADEC finds an open or shorted ignition-switch OFF circuit, or when channel A and B circuit ON conditions are not the same.
POSSIBLE CAUSES: 1. Aircraft circuit fault 2. FADEC
01 Supply electrical power to the aircraft. 04 Do the troubleshooting for FADEC discrete Access FADEC discrete label 351 from the IGOFFT (bit 14) (Ref. 74-30-00-810-803). central maintenance computer (CMC) for both -Yes FADECs (Ref. Introduction). Does IGOFFT (bit 14) = 1? | No 02 Put the ignition switch in the ON position. Access FADEC discrete label 264 from the CMC (Ref. Introduction). Does IGONDF (bit 13) = 1?
-Yes
05 Do the troubleshooting for FADEC discrete IGONDF (bit 13) (Ref. 74-30-00-810-804).
| No 03 Put the ignition switch in the AUTO position. Does IGONDF (bit 13) = 1?
-Yes
06 Do the troubleshooting for FADEC discrete IGONDF (bit 13) (Ref. 74-30-00-810-804).
| No |
07 Examine all of the harness connectors between the ignition switch and the FADEC. Clean or repair them as necessary (Ref. 74-10-50/74-10-51 WM) (Ref. 20-50-00 WM).
Maintenance Message: ENG1/ENG2 IGNITION SWITCH FAIL or LT-ENG1/ENG2 IGN OFF EFFECTIVITY:ALL
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FADEC Discrete: IGONFT (bit 13) / (351 / AILRU1) = 1 DESCRIPTION: The FADEC does a test of the ignition switch ON circuit. This discrete is set to 1 (fault sensed) when an open or shorted circuit is detected.
POSSIBLE CAUSES: 1. Aircraft circuit fault 2. FADEC
01 Disconnect the harness (W1) from the 07 Clean or repair the connector (Ref. FADEC J2 receptacle. Examine the harness 20-50-00 WM). Rotate the FADEC reset/select connector for damage, corrosion, or -Yes switch to the RESET position to remove the contamination. Is the connector contaminated fault (IGONFT (bit 13) = 0). or damaged? | No
R R
02 Supply electrical power to the aircraft and do a test for voltage at pin P of the FADEC J2 receptacle (Ref. FIG. 301/TASK 74-30-00-990-801) (Ref. 74-10-50/ 74-10-51 WM). Is there 12-15 VDC measured?
08 Replace the FADEC that has the fault (Ref. 73-25-10-000-801/73-25-10-400-801 -No MM).
| Yes
R R
03 Put the ignition switch in the ON position and do a test for continuity between pins P and q at the W1 harness connector (Ref. FIG. 301/TASK 74-30-00-990-801) (Ref. 74-10-50/74-10-51 WM). Is there continuity, with resistance less than 10 ohms?
09 Repair the aircraft circuit fault (Ref. 74-10-50/74-10-51 WM). Rotate the FADEC reset/select switch to the RESET position to -No remove the fault (IGONFT (bit 13) = 0).
| Yes 04 Go to Block 05
FADEC Discrete: IGONFT (bit 13) / (351 / AILRU1) = 1 EFFECTIVITY:ALL
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R R
05 With the ignition switch in the ON position, 10 Repair the aircraft circuit fault (Ref. do a test for continuity between ground and pin 74-10-50/74-10-51 WM). Rotate the FADEC P at the W1 harness connector (Ref. FIG. -Yes reset/select switch to the RESET position to 301/TASK 74-30-00-990-801) (Ref. remove the fault (IGONFT (bit 13) = 0). 74-10-50/74-10-51 WM). Is there continuity? | No
R R
06 Put the ignition switch in the AUTO position and do a test for continuity between pins P and q at the W1 harness connector (Ref. FIG. 301/TASK 74-30-00-990-801) (Ref. -No 74-10-50/74-10-51 WM). Is there continuity, with resistance between 9.5K and 10.5K ohms?
11 Repair the aircraft circuit fault (Ref. 74-10-50/74-10-51 WM). Rotate the FADEC reset/select switch to the RESET position to remove the fault (IGONFT (bit 13) = 0).
| Yes |
12 Replace the FADEC that has the fault (Ref. 73-25-10-000-801/73-25-10-400-801 MM).
FADEC Discrete: IGONFT (bit 13) / (351 / AILRU1) = 1 EFFECTIVITY:ALL
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FADEC Discrete: IGOFFT (bit 14) / (351 / AILRU1) = 1 DESCRIPTION: The FADEC does a test of the ignition switch OFF circuit. This discrete is set to 1 (fault sensed) when an open or shorted circuit is detected.
POSSIBLE CAUSES: 1. Aircraft circuit fault 2. FADEC
01 Disconnect the harness (W1) from the 07 Clean or repair the connector (Ref. FADEC J2 receptacle. Examine the harness 20-50-00 WM). Rotate the FADEC reset/select connector for damage, corrosion, or -Yes switch to the RESET position to remove the contamination. Is the connector contaminated fault (IGOFFT (bit 14) = 0). or damaged? | No
R R
02 Supply electrical power to the aircraft and do a test for voltage at pin P of the FADEC J2 receptacle (Ref. FIG. 301/TASK 74-30-00-990-801) (Ref. 74-10-50/ 74-10-51 WM). Is there 12-15 VDC measured?
08 Replace the FADEC that has the fault (Ref. 73-25-10-000-801/73-25-10-400-801 -No MM).
| Yes
R R
03 Put the ignition switch in the OFF position and do a test for continuity between pins P and r at the W1 harness connector (Ref. FIG. 301/TASK 74-30-00-990-801) (Ref. 74-10-50/74-10-51 WM). Is there continuity, with resistance less than 10 ohms?
09 Repair the aircraft circuit fault (Ref. 74-10-50/74-10-51 WM). Rotate the FADEC reset/select switch to the RESET position to -No remove the fault (IGOFFT (bit 14) = 0).
| Yes 04 Go to Block 05
FADEC Discrete: IGOFFT (bit 14) / (351 / AILRU1) = 1 EFFECTIVITY:ALL
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R R
05 With the ignition switch in the OFF position, 10 Repair the aircraft circuit fault (Ref. do a test for continuity between ground and pin 74-10-50/74-10-51 WM). Rotate the FADEC P at the W1 harness connector (Ref. FIG. -Yes reset/select switch to the RESET position to 301/TASK 74-30-00-990-801) (Ref. remove the fault (IGOFFT (bit 14) = 0). 74-10-50/74-10-51 WM). Is there continuity? | No
R R
06 Put the ignition switch in the AUTO position and do a test for continuity between pins P and r at the W1 harness connector (Ref. FIG. 301/TASK 74-30-00-990-801) (Ref. -No 74-10-50/74-10-51 WM). Is there continuity, with resistance between 9.5K and 10.5K ohms?
11 Repair the aircraft circuit fault (Ref. 74-10-50/74-10-51 WM). Rotate the FADEC reset/select switch to the RESET position to remove the fault (IGOFFT (bit 14) = 0).
| Yes |
12 Replace the FADEC that has the fault (Ref. 73-25-10-000-801/73-25-10-400-801 MM).
FADEC Discrete: IGOFFT (bit 14) / (351 / AILRU1) = 1 EFFECTIVITY:ALL
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FADEC Discrete: IGONDF (bit 13) / (264 / AIDIF1) = 1 DESCRIPTION: The FADECs do a lane difference test of the two ignition-switch ON circuits. This fault occurs when the condition of the circuits (ON/OFF/AUTO) sensed by FADEC A and B is not the same. The FADECs will not do this test if one of the two ON circuits has a fault.
POSSIBLE CAUSES: 1. Aircraft circuit fault 2. FADEC
01 Disconnect the harness (W1) from the J2 receptacles on both FADECs. Examine the harness connectors for damage, corrosion, or contamination. Are the connectors contaminated or damaged?
04 Clean or repair the connector (Ref. 20-50-00 WM). Rotate the FADEC reset/select -Yes switch to the RESET position to remove the fault (IGONDF (bit 13) = 0).
| No
R R
02 Disconnect the harness from the switch 05 Replace the W1 harness. Rotate the and do a test for continuity between pins P and FADEC reset/select switch to the RESET q at both W1 harness connectors (Ref. FIG. -Yes position to remove the fault (IGONDF (bit 13) = 301/TASK 74-30-00-990-801) (Ref. 0). 74-10-50/74-10-51 WM). Is there continuity? | No 03 Supply electrical power to the aircraft. Access FADEC discrete label 264, for FADEC A and B, from the central maintenance computer (CMC) (Ref. Introduction). Does IGONDF (bit 13) = 1 for both FADECs?
06 Replace the ignition switch (Ref. 20-13-03/401 AMM). Rotate the FADEC -Yes reset/select switch to the RESET position to remove the fault (IGONDF (bit 13) = 0).
| No |
07 Replace the FADEC that shows IGONDF (bit 13) = 1) (Ref. 73-25-10-000-801/73-25-10-400-801 MM).
FADEC Discrete: IGONDF (bit 13) / (264 / AIDIF1) = 1 EFFECTIVITY:ALL
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FADEC Discrete: IGOFDF (bit 14) / (264 / AIDIF1) = 1 DESCRIPTION: The FADECs do a lane difference test of the two ignition-switch OFF circuits. This fault occurs when the condition of the circuits (ON/OFF/AUTO) sensed by FADEC A and B is not the same. The FADECs will not do this test if one of the two OFF circuits has a fault.
POSSIBLE CAUSES: 1. Aircraft circuit fault 2. FADEC
01 Disconnect the harness (W1) from the J2 receptacles on both FADECs. Examine the harness connectors for damage, corrosion, or contamination. Are the connectors contaminated or damaged?
04 Clean or repair the connector (Ref. 20-50-00 WM). Rotate the FADEC reset/select -Yes switch to the RESET position to remove the fault (IGOFDF (bit 14) = 0).
| No
R R
02 Disconnect the harness from the switch 05 Replace the W1 harness. Rotate the and do a test for continuity between pins P and FADEC reset/select switch to the RESET r at both W1 harness connectors (Ref. FIG. -Yes position to remove the fault (IGOFDF (bit 14) = 301/TASK 74-30-00-990-801) (Ref. 0). 74-10-50/74-10-51 WM). Is there continuity? | No 03 Supply electrical power to the aircraft. Access FADEC discrete label 264, for FADEC A and B, from the central maintenance computer (CMC) (Ref. Introduction). Does IGOFDF (bit 14) = 1 for both FADECs?
06 Replace the ignition switch (Ref. 20-13-03/401 AMM). Rotate the FADEC -Yes reset/select switch to the RESET position to remove the fault (IGOFDF (bit 14) = 0).
| No |
07 Replace the FADEC that shows IGOFDF (bit 14) = 1) (Ref. 73-25-10-000-801/73-25-10-400-801 MM).
FADEC Discrete: IGOFDF (bit 14) / (264 / AIDIF1) = 1 EFFECTIVITY:ALL
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R Maintenance Message: ST-ENG1/ENG2 IGN ON SYS DIFF DESCRIPTION: This message occurs when the FADEC finds that the channel A and B circuit ON conditions are not the same.
POSSIBLE CAUSES: 1. Aircraft circuit fault 2. FADEC
01 Supply electrical power to the aircraft. Access FADEC discrete label 264 from the central maintenance computer (CMC) for both FADECs (Ref. Introduction). Does IGONDF (bit 13) = 1?
-Yes
03 Do the troubleshooting for FADEC discrete IGONDF (bit 13) = 1 (Ref. 74-30-00-810-804).
| No 02 Operate the engine and shutdown. Do not remove electrical power from the FADECs. Does IGONDF (bit 13) = 1?
04 Do the troubleshooting for FADEC discrete -Yes IGONDF (bit 13) = 1 (Ref. 74-30-00-810-804).
| No |
05 Examine all of the harness connectors between the ignition switch and the FADEC (Ref. 74-10-50/74-10-51 WM) (Ref. FIG. 301/TASK 74-30-00-990-801). Clean or repair them as necessary (Ref. 20-50-00 WM) (Ref. 70-00-00-910-804 MM).
Maintenance Message: ST-ENG1/ENG2 IGN ON SYS DIFF EFFECTIVITY:ALL
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Observed Fault: ENG1/ENG2 IGN A/B (active ignition system after deceleration to ground idle) DESCRIPTION: This fault occurs on engines with the post-B8.0 version FADEC software upgrade (SB AE 3007A-73-075/076/077/078/079). During taxi after the engine RPM decreases to ground idle, an ENG1/ENG2 IGN A/B indication shows that the igniters continue to be energized.
POSSIBLE CAUSES: 1. AE 3007A-series engines with post-B8.0 FADEC software
01 Read the engine logbook. Was the engine 04 Engine operation is normal. Return the upgraded to FADEC software version 8.0 (Ref. -Yes engine to service. SB AE 3007A-73-075/076/077/078/079)? | No 02 Supply electrical power to the aircraft. Access the maintenance messages from the Central Maintenance Computer (CMC). Are there engine-related faults or maintenance messages displayed?
05 Do the troubleshooting for the faults or maintenance messages displayed. Go to block -Yes 03.
| No | 03 Were all the faults or maintenance messages corrected?
06 Return the engine to service. -Yes 07 Return the engine to service.
| No |
08 Contact Rolls-Royce.
Observed Fault: ENG1/ENG2 IGN A/B (active ignition system after deceleration to ground idle) EFFECTIVITY:ALL
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Ignition Switch / FADEC Interface Diagram FIG. 301/TASK 74-30-00-990-801
R EFFECTIVITY:ALL
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CHAPTER 75 LIST OF EFFECTIVE PAGES
R R R R R R R R R R R R R R
CHAPTER SECTION SUBJECT PAGE 75 Contents 1 Contents 2 00-00 101/ 102 31-00 201 31-00 202 31-00 203 31-00 204 31-00 205/ 206 31-00 201/ 202 31-00 201 31-00 202 31-00 203/ 204 31-00 201 31-00 202 31-00 203/ 204 33-00 201 33-00 202 33-00 201 33-00 202 33-00 201/ 202 33-00 201/ 202 33-00 201/ 202 33-00 301 33-00 302 41-00 201 41-00 202 41-00 201 41-00 202 41-00 201 41-00 202 41-00 201/ 202 41-00 201/ 202 41-00 201/ 202 41-00 201/ 202 41-00 301 41-00 302 43-00 201 43-00 202 43-00 201 43-00 202 43-00 201 43-00 202 43-00 201 43-00 202 43-00 201 43-00 202 43-00 201 43-00 202
OTHER IDENT
DATE Jul.20/15 Jul.20/15 Jul.20/15 Jul.20/15 Jul.20/15 Jul.20/15 Jul.20/15 Jul.20/15 Apr.20/10 Jul.20/15 Jul.20/15 Jul.20/15 Jul.20/15 Jul.20/15 Jul.20/15
CHAPTER SECTION OTHER SUBJECT PAGE IDENT DATE 75 43-00 201 Oct.15/05 43-00 202 Oct.15/05 43-00 203/ Oct.15/05 204 43-00 201 Oct.15/05 43-00 202 Oct.15/05 43-00 201 Apr.20/09 43-00 202 Apr.20/09 43-00 201/ Oct.15/05 202 43-00 201/ Oct.15/05 202 43-00 301 Aug.15/04 43-00 302 Aug.15/04 43-00 303/ Aug.15/04 304 --------------- END ---------------
CHAPTER SECTION SUBJECT PAGE 75
OTHER IDENT
DATE
Apr.20/12 Apr.20/12 Apr.20/12 Apr.20/12 Jul.20/08 Apr.20/12 Apr.20/12 Aug.15/04 Aug.15/04 Oct.15/05 Oct.15/05 Oct.15/05 Oct.15/05 Oct.15/05 Oct.15/05 Oct.15/05 Oct.15/05 Oct.15/05 Oct.15/05 Aug.15/04 Aug.15/04 Oct.15/05 Oct.15/05 Oct.15/05 Oct.15/05 Oct.15/05 Oct.15/05 Apr.20/09 Apr.20/09 Aug.15/04 Aug.15/04 Aug.15/04 Aug.15/04
C=CONFIG B=BREAKOUT
LIST OF EFFECTIVE PAGES-75 Page 1/2 Oct 20/16
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CHAPTER 75 TABLE OF CONTENTS
SUBJECT
CH-SE-SUB
AIR FAULT CODE INDEX
75-00-00
COMPRESSOR BLEED SYSTEM Bleed Leak Alert Bleed Valve Alert Low ITT Margin Alert Bleed Leak Alert and Low ITT Margin
75-31-00
COMPRESSOR-VARIABLE-GEOMETRY ACTUATOR FADEC Discrete: CVGFBF (bit 18) / (353 / EILRU) = 1 FADEC Discrete: CVGFBD (bit 22) / (357 / EIDIF) = 1 Observed Fault: CVG Hydraulic-Actuator Seal-Drain Accumulation Maintenance Message: ND-ENG1/ENG2 CVG SYS DIFF Maintenance Message: ST-ENG1/ENG2 CVG SYS Task Support
75-33-00
COMPRESSOR-INLET-TEMPERATURE SENSOR INDICATIONS FADEC Discrete: T25FLT (bit 16) / (353 / EILRU) = 1 FADEC Discrete: T25NOK (bit 16) / (353 / EILRU) = 1 FADEC Discrete: T25DIF (bit 20) / (357 / EIDIF) = 1 Maintenance Message: ND - ENG1 / ENG2 HPC SYS Maintenance Message: ND - ENG1 / ENG2 HPC SYS FADEC Discrete: T25BLF (bit 22) / (352 /AILRU2) = 1 FADEC Discrete: T25DCF (bit 22) / (352 /AILRU2) = 1 Task Support COMPRESSOR -INLET-PRESSURE SENSOR
PAGE
EFFECTIVITY
101
201 201 201 201
201 201 201 201 201 301
75-41-00 201 201 201 201 201 201 201 301 75-43-00
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SUBJECT FADEC Discrete: P25FLT (bit 17) / (353 / EILRU) = 1 FADEC Discrete: P25NOK (bit 17) / (353 / EILRU) = 1 FADEC Discrete: P25DIF (bit 21) / (357 / EIDIF) = 1 FADEC Discrete: P0SFT (bit 28) / (353 / EILRU) = 1 FADEC Discrete: P0SDIF (bit 27) / (357 / EIDIF) = 1 Maintenance Message: ENG1/ENG2 PALT x P0 DIFF FAULT Maintenance Message: LT-ENG1/ENG2 PR/TMP DATA SYS Maintenance Message: LT-ENG1/ENG2 PR/TMP DATA SYS Maintenance Message: ND-ENG1/ENG2 P0 SYS FADEC Discrete: P25BLF (bit 23) / (352/AILRU2) = 1 FADEC Discrete: P25DCF (bit 23) / (352/AILRU2) = 1 Task Support
CH-SE-SUB
PAGE
EFFECTIVITY
201 201 201 201 201 201 201 201 201 201 201 301
75−CONTENTS Page 2
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FAULT CODE INDEX FAULT CODE
FAULT DESCRIPTION
75300100
Bleed Leak Alert
75-31-00-810-801
753101 00
ITT Margin Decreases Quickly or in Steps with a Fuel Flow Increase of 1% or More and a Flat or Decreasing N2 Margin
75-31-00-810-801
753102 00
Low ITT Margin Alert
75-31-00-810-803
ITT Margin Decreases Quickly or in Steps with a Fuel Flow Increase of 1% or More and a Flat or Decreasing N2 Margin
75-31-00-810-804
CVG Hydraulic Actuator Seal Drain Accumulation
75-33-00-810-804
R 753103 00 R R R R 753301 00
EFFECTIVITY:ALL
MAINT. MESSAGE
GO TO FIM TASK
75−FAULT CODE INDEX Page 101/102 Jul 20/15
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Bleed Leak Alert Observed Fault: ITT margin decreases quickly or in steps with a fuel flow increase of 1% or more and a flat or decreasing N2 margin. DESCRIPTION: This fault occurs when the ITT trend data shows the ITT margin has decreased quickly by 15°C (27°F)/1000 hours or in steps more than 10°C (18°F) with a fuel flow increase of 1% or more and a flat or decreased N2 margin.
POSSIBLE CAUSES: 1. Customer-service outer-manifold, the outer-bypass duct gasket, the customer-bleed-air offtake tubes, the left-hand compressor-discharge-air tube, or the right-hand compressor-discharge-air tube 2. Upper or lower compressor-air bleed-valve, the lower compressor-acceleration bleed-control valve (PRE-SB AE 3007A-75-019), the lower compressor-acceleration air-bleed valve (POST-SB AE 3007A-75-019) 3. Upper bleed-air-valve bleed-air control tube (PRE-SB AE 3007A-75-019), the CABCV-to-line-tee tube (PRE-SB AE 3007A-75-019), the line tee-to-service manifold tube (PRE-SB AE 3007A-75-019), the diffuser-to-CABCV air tube (PRE-SB AE 3007A-75-020) or the flexible metal tube (POST-SB AE 3007A-75-020), or the bleed-control transfer-tube (PRE-SB AE 3007A-72-276) 4. Fuel nozzle gaskets 5. Aircraft bleed ducts (from customer service outer manifold to pylon connection) 6. Aircraft bleed system 7. Aircraft/engine anti-ice system 8. Combustion liner distress 9. High-pressure turbine 10.One or more piloted and pure air blast fuel nozzles installed are mixed
CAUTION: MAKE SURE THAT YOU DO NOT MIX PILOTED FUEL NOZZLES WITH NON-PILOTED FUEL NOZZLES. DAMAGE TO THE ENGINE CAN OCCUR.
01 Read the engine logbook. Was there a fuel nozzle change done before the ITT margin change?
-No
23 Go to block 04.
| Yes 02 Make sure that piloted fuel nozzles were not mixed with pure air blast fuel nozzles. Were the correct fuel nozzles installed? -No
24 Replace the incorrect fuel nozzles (Ref. 73-11-10-000-801, MM/73-11-10-400-801, MM). Continue to monitor the ITT trend through the subsequent trend period and fault isolate as necessary.
| Yes 03 Go to block 04. Bleed Leak Alert EFFECTIVITY:ALL
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04 Read the engine logbook. Was other maintenance done before the ITT margin change (for example, thermocouple change or compressor wash)?
25 Continue to monitor ITT trend through the subsequent trend period and fault isolate as -Yes necessary.
| No 05 Examine the fuel nozzle mount pads for missing or damaged gaskets. Were there missing or damaged gaskets?
26 Remove the fuel nozzle (Ref. 73-11-10-000-801, MM). Replace the fuel nozzle gasket. Install the fuel nozzle (Ref. -Yes 73-11-10-400-801, MM). Continue to monitor the ITT trend through the subsequent trend period and fault isolate as necessary.
| No 06 Examine the customer-service 27 Do the inspection of the customer-service outer-manifold and the outer-bypass duct outer-manifold (Ref. 75-31-30-200-801, MM). gasket for loose or missing bolts and gasket -Yes Continue to monitor the ITT trend through the damage. Was one of the two conditions found? subsequent trend period and fault isolate as necessary (Ref. SB AE 3007A-75-033). | No 07 Examine the aircraft bleed-air system (Ref. 28 Replace the damaged or defective bleed-air AMM) from OCSM to pylon for valve(s) system components as necessary, and operation, missing or loose clamps, and broken -Yes continue to monitor the ITT trend through the fittings/damaged insulation. Was one of these subsequent trend period and fault isolate as conditions found? necessary. | No 08 Examine the customer-bleed-air offtake tubes for lateral movement or the piston rings that can be seen, and the OCSM and the core manifolds for wear sleeve movement (Ref. SB AE 3007A-75-033). Was one of these conditions found?
29 Remove the defective customer-bleed-air offtake tube (Ref. 75-31-35-000-801, MM). Install the replacement customer-bleed-air offtake tube (Ref. 75-31-35-400-801, MM), the -Yes core manifold (Ref. 75-31-20-200-801, MM), and the OCSM (Ref. 75-31-30-200-801, MM). Continue to monitor the ITT trend through the subsequent trend period and fault isolate as necessary.
| No 09 Go to block 10. Bleed Leak Alert EFFECTIVITY:ALL
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10 Examine the left-hand-compressor-discharge-air tube for damage or separation. If (POST-SB AE 3007A-75-021), examine the V-band clamp and braided bellows for wear or damage. Was one of these conditions found?
30 Remove the defective left-hand compressor-discharge-air tube (Ref. 75-00-00-000-801, MM). Install the replacement left-hand -Yes compressor-discharge-air tube (Ref. 75-00-00-400-801, MM). Continue to monitor the ITT trend through the subsequent trend period and fault isolate as necessary.
| No 11 If (PRE-SB AE 3007A-75-021), examine the 31 Remove the defective right-hand right-hand compressor-discharge-air tube for compressor-discharge-air tube (Ref. damage or separation. On the upper flange, 75-00-00-000-801, MM). Install the remove the three nuts and pull the flange back replacement right-hand -Yes from the mounting pad to examine the flared compressor-discharge-air tube (Ref. end. If (POST SB AE 3007A-75-021), examine 75-00-00-400-801, MM). Continue to monitor the v-band clamp and braided bellows for the ITT trend through the subsequent trend damage. Was one of these conditions found? period and fault isolate as necessary. | No 12 Have you done SB AE 3007A-75-019 or SB 32 Go to block 17. -Yes AE 3007A-75-021? | No 13 Examine all 1/4 inch tubing in the bleed system, and the tubing for the diffuser to CABCV and CABCV to upper and lower bleed valves for cracks near fittings and breakage. Was one of these conditions found?
33 Remove the defective tube(s) (Ref. 75-00-00-000-801, MM). Install a replacement -Yes tube (Ref. 75-00-00-400-801, MM). Continue to monitor the ITT trend through the subsequent trend period and fault isolate as necessary.
| No 14 Remove and replace the upper and lower bleed valves, or remove and clean the valves (Ref. TASK 75-31-10-100-801, MM). Do the test of the engine (Ref. TASK 72-00-00-700-801, MM). Is the ITT margin corrected?
-Yes
34 Put the engine back in service. Continue to monitor the ITT trend through the subsequent trend period and fault isolate as necessary.
| No 15 Go to block 16. Bleed Leak Alert EFFECTIVITY:ALL
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16 Remove and replace the compressor-acceleration bleed-control valve. Do the test of the engine (Ref. 72-00-00-700-801, MM). Was the ITT margin corrected?
35 Put the engine back in service. Continue to monitor the ITT trend through the subsequent -Yes trend period and fault isolate as necessary.
| No 17 Remove and replace the lower compressor-acceleration air-bleed valve (Ref. 75-31-10-000-802, MM). Do the test of the engine (Ref. 72-00-00-700-801, MM). Was the ITT margin corrected?
36 Put the engine back in service. Continue to monitor the ITT trend through the subsequent -Yes trend period and fault isolate as necessary.
| No 18 Continue to monitor the ITT trend through the subsequent trending period and fault isolate as necessary. Was the ITT margin corrected?
37 Put the engine back in service. Continue to monitor the ITT trend through the subsequent -Yes trend period and fault isolate as necessary.
| No R R R R
19 Is the bleed system POST-AE 3007A-75-019?
R R R
38 Replace the start control bleed line. Continue to monitor the ITT trend through the -No subsequent trend period and fault isolate as necessary.
| Yes 20 Is the high-pressure turbine Pre-AE 3007A-72-260 configuration?
39 Borescope the combustion liner (Ref. -Yes 72-40-00-200-801 MM) and the high-pressure turbine (Ref. 72-50-00-200-805, MM).
| No 21 Go to block 22.
Bleed Leak Alert EFFECTIVITY:ALL
TASK 75−31−00−810−801 Page 204 Jul 20/15
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22 Is the ITT margin acceptable to continue operation (contact Rolls-Royce for recommendation)?
40 Put the engine back in service. Continue to -Yes monitor the ITT trend through the subsequent trend period and fault isolate as necessary.
| No |
41 Remove the engine (Ref. 71-00-00-000-801, AMM) and install the replacement engine (Ref. 71-00-00-400-801, AMM). Make sure the engine logbook shows why the engine was removed.
Bleed Leak Alert EFFECTIVITY:ALL
TASK 75−31−00−810−801 Page 205/206 Jul 20/15
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Bleed Valve Alert Observed Fault: ITT margin and N2 margin decrease suddenly. R This TASK has been deleted.
Bleed Valve Alert EFFECTIVITY:ALL
TASK 75−31−00−810−802 Page 201/202 Apr 20/10
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Low ITT Margin Alert Observed Fault: This fault occurs when the engine ITT trend data shows low ITT margin. DESCRIPTION: An Engine Health Monitoring (EHM) ITT alert is issued if an engine has low ITT margin. Low ITT margin can put an engine at risk for an aborted takeoff due to an Automatic Takeoff Trust Control System (ATTCS) No Margin EICAS message.
POSSIBLE CAUSES: 1. Bleed leak 2. Aircraft bleed system 3. Aircraft bleed ducts (from customer service outer manifold to pylon connection) 4. Upper or lower compressor-air bleed-valve, the lower compressor-acceleration bleed-control valve (PRE-SB AE 3007A-75-019), the lower compressor-acceleration air-bleed valve (POST-SB AE 3007A-75-019) 5. Upper bleed-air-valve bleed-air control tube (PRE-SB AE 3007A-75-019), the CABCV-to-line-tee tube (PRE-SB AE 3007A-75-019), the line tee-to-service manifold tube (PRE-SB AE 3007A-75-019), the diffuser-to-CABCV air tube (PRE-SB AE 3007A-75-020) or the flexible metal tube (POST-SB AE 3007A-75-020), or the bleed-control transfer-tube (PRE-SB AE 3007A-72-276) 6. Engine deterioration
01 Examine the aircraft bleed-air system (Ref. 09 Replace the damaged or defective bleed-air AMM) from OCSM to pylon for valve(s) system components. Go to block 02. operation, missing or loose clamps, and broken -Yes fittings/damaged insulation. Was one of these conditions found? | No 02 Examine the 10 Remove the defective left-hand left-hand-compressor-discharge-air tube for compressor-discharge-air tube (Ref. damage or separation. If POST-SB AE 75-00-00-000-801, MM). Install the -Yes 3007A-75-021, examine the V-band clamp and replacement left-hand braided bellows for wear or damage. Was one compressor-discharge-air tube (Ref. of these conditions found? 75-00-00-400-801, MM). Go to block 04. | No 03 Go to block 04
Low ITT Margin Alert EFFECTIVITY:ALL
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04 If PRE-SB AE 3007A-75-021, examine the right-hand compressor-discharge-air tube for damage or separation. On the upper flange, remove the three nuts and pull the flange back from the mounting pad to examine the flared end. If POST SB AE 3007A-75-021, examine the V-band clamp and braided bellows for damage. Was one of these conditions found?
11 Remove the defective right-hand compressor-discharge-air tube (Ref. 75-00-00-000-801, MM). Install the replacement right-hand -Yes compressor-discharge-air tube (Ref. 75-00-00-400-801, MM). Go to block 05.
| No R
05 Have you done SB AE 3007A-75-019 or SB -Yes 12 Go to block 08. AE 3007A-75-021? | No
R
06 Examine all 1/4 inch tubing in the bleed system, and the tubing for the diffuser to CABCV and CABCV to upper and lower bleed valves for cracks near fittings and breakage. Was a defective tube(s) found?
13 Remove the defective tube(s) (Ref. 75-00-00-000-801, MM). Install a replacement -Yes tube (Ref. 75-00-00-400-801, MM). Go to block 14.
| No R
R R R R
07 Remove and replace the upper and lower 14 Put the engine back in service. Continue to bleed valves (Ref. monitor the ITT trend. 75-31-10-000-801/75-31-10-400-801, MM), or remove and clean the valves (Ref. 75-31-10-000-801, MM). Remove and replace the compressor-acceleration bleed-control -Yes valve (Ref. 75-31-15-000-801/75-31-15-400-801, MM). Put the engine back in service. Download and provide data to Rolls-Royce within 2 days or within 10 flight hours. Was the ITT margin corrected? | No
15 Go to Block 17.
Low ITT Margin Alert EFFECTIVITY:ALL
TASK 75−31−00−810−803 Page 202 Jul 20/15
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R R R R
08 Remove and replace the lower bleed valve 16 Put the engine back in service. Continue to (Ref. 75-31-10-000-801/75-31-10-400-801, monitor the ITT trend. MM). Put the engine back in service. Download -Yes and provide data to Rolls-Royce within 2 days or within 10 flight hours. Was the ITT margin corrected? | No
17 Schedule the engine to be removed within 50 hours. Download and provide data to Rolls-Royce within 2 days or within 10 flight hours. Remove the engine (Ref. 71-00-00-000-801, AMM) and install a replacement engine (Ref. 71-00-00-400-801, AMM). Make sure that the engine logbook describes why the engine was removed.
Low ITT Margin Alert EFFECTIVITY:ALL
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Bleed Leak Alert and Low ITT Margin Observed Fault: ITT margin decreases quickly or in steps with a fuel flow increase of 1% or more and a flat or decreasing N2 margin. DESCRIPTION: Engine Health Monitoring (EHM) alerts an engine with sudden loss of ITT margin accompanied by a fuel flow increase of 1% or more. An alert would be issued to check for bleed leaks throughout the engine and aircraft bleed air systems.
POSSIBLE CAUSES: 1. Bleed leak 2. Aircraft bleed system 3. Aircraft bleed ducts (from customer service outer manifold to pylon connection) 4. Upper or lower compressor-air bleed-valve, the lower compressor-acceleration bleed-control valve (PRE-SB AE 3007A-75-019), the lower compressor-acceleration air-bleed valve (POST-SB AE 3007A-75-019) 5. Upper bleed-air-valve bleed-air control tube (PRE-SB AE 3007A-75-019), the CABCV-to-line-tee tube (PRE-SB AE 3007A-75-019), the line tee-to-service manifold tube (PRE-SB AE 3007A-75-019), the diffuser-to-CABCV air tube (PRE-SB AE 3007A-75-020) or the flexible metal tube (POST-SB AE 3007A-75-020), or the bleed-control transfer-tube (PRE-SB AE 3007A-72-276) 6. Engine deterioration
01 Examine the aircraft bleed-air system (Ref. 10 Replace the damaged or defective bleed-air AMM) from OCSM to pylon for valve(s) system components. Go to block 02. operation, missing or loose clamps, and broken -Yes fittings/damaged insulation. Was one of these conditions found? | No 02 Examine the 11 Remove the defective left-hand left-hand-compressor-discharge-air tube for compressor-discharge-air tube (Ref. damage or separation. If POST-SB AE 75-00-00-000-801, MM). Install the 3007A-75-021, examine the V-band clamp and -Yes replacement left-hand braided bellows for wear or damage. Was one compressor-discharge-air tube (Ref. of these conditions found? 75-00-00-400-801, MM). Put the engine back in service. Continue to monitor the ITT trend. | No 03 Go to block 04
Bleed Leak Alert and Low ITT Margin EFFECTIVITY:ALL
TASK 75−31−00−810−804 Page 201 Jul 20/15
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04 If PRE-SB AE 3007A-75-021, examine the right-hand compressor-discharge-air tube for damage or separation. On the upper flange, remove the three nuts and pull the flange back from the mounting pad to examine the flared end. If POST SB AE 3007A-75-021, examine the V-band clamp and braided bellows for damage. Was one of these conditions found?
12 Remove the defective right-hand compressor-discharge-air tube (Ref. 75-00-00-000-801, MM). Install the replacement right-hand -Yes compressor-discharge-air tube (Ref. 75-00-00-400-801, MM). Put the engine back in service. Continue to monitor the ITT trend.
| No 05 Have you done SB AE 3007A-75-019 or SB -No AE 3007A-75-021?
13 Go to block 08.
| Yes 06 Examine all 1/4 inch tubing in the bleed system, and the tubing for the diffuser to CABCV and CABCV to upper and lower bleed valves for cracks near fittings and breakage. Was a defective tube(s) found?
14 Remove the defective tube(s) (Ref. 75-00-00-000-801, MM). Install a replacement -Yes tube (Ref. 75-00-00-400-801, MM). Go to block 15.
| No 07 Remove and replace the upper and lower bleed valves (Ref. 75-31-10-000-801/75-31-10-400-801, MM), or remove and clean the valves (Ref. 75-31-10-000-801, MM). Remove and replace the compressor-acceleration bleed-control valve (Ref. 75-31-15-000-801/75-31-15-400-801, MM). Was the ITT margin corrected?
15 Put the engine back in service. Continue to monitor the ITT trend through the subsequent trend period and fault isolate as necessary. Download and provide data to Rolls-Royce -Yes within 2 days or within 10 flight hours.
| No
16 Go to Block 19.
Bleed Leak Alert and Low ITT Margin EFFECTIVITY:ALL
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08 Remove and replace the lower bleed valve (Ref. 75-31-10-000-801/75-31-10-400-801, MM). Was the ITT margin corrected?
17 Put the engine back in service. Continue to monitor the ITT trend through the subsequent -Yes trend period and fault isolate as necessary. Download and provide data to Rolls-Royce within 2 days or within 10 flight hours.
| No 09 Is the ITT margin acceptable to continue operation (contact Rolls-Royce for recommendation)?
18 Put the engine back in service. Continue to -Yes monitor the ITT trends.
| No
19 Schedule the engine to be removed within 50 hours. Download and provide data to Rolls-Royce within 2 days or within 10 flight hours. Remove the engine (Ref. 71-00-00-000-801, AMM) and install a replacement engine (Ref. 71-00-00-400-801, AMM). Make sure that the engine logbook describes why the engine was removed.
Bleed Leak Alert and Low ITT Margin EFFECTIVITY:ALL
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FADEC Discrete: CVGFBF (bit 18) / (353 / EILRU) = 1 DESCRIPTION: The FADEC monitors the signal received from the position sensor for the compressor variable-geometry (CVG) actuator. This discrete is set to 1 (fault sensed) when the position of the actuator sensed is not within the limits.
POSSIBLE CAUSES: R R R
1. Harness 2. FADEC 3. CVG actuator
01 Remove and install all of the harness connectors between the FADEC J4 receptacle and the INTA(B) connector (Ref. FIG. 301/TASK 75-33-00-990-801/FIG. 302/TASK 75-33-00-990-802). Rotate the FADEC reset/select switch to the RESET position. Access label 353 from the CMC (Ref. Introduction). Does CVGFBF (bit 18) = 1?
06 Examine all the harness connectors between the FADEC J4 receptacle and the INTA(B) connector for damage, corrosion, or contamination (Ref. FIG. 301/TASK 75-33-00-990-801/FIG. 302/TASK -No 75-33-00-990-802) (Ref. 70-00-00-910-804 MM). Repair or clean the connectors as necessary. Make sure there is not another occurrence of the maintenance message after engine operation.
| Yes 02 Interchange the position of the FADECs 07 Replace the FADEC that has the fault (Ref. (Ref. 73-25-10-000-801/73-25-10-400-801 73-25-10-000-801/73-25-10-400-801 MM). MM). Rotate the FADEC reset/select switch to -Yes the RESET position. Does the fault move to the opposite channel? | No 03 Interchange the position of harness connectors CVGA and CVGB at the CVG actuator. Rotate the FADEC reset/select switch to the RESET position. Does the fault move to the opposite channel?
-Yes
08 Replace the CVG actuator (Ref. 75-33-10-000-801/75-33-10-400-801 MM).
| No | 04 Go to block 05
FADEC Discrete: CVGFBF (bit 18) / (353 / EILRU) = 1 EFFECTIVITY:ALL
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05 Interchange the position of harness connectors CVGA and CVGB at the CVG actuator. Rotate the FADEC reset/select switch to the RESET position. Does the fault move to the opposite channel?
-Yes
09 Replace the CVG actuator (Ref. 75-33-10-000-801/75-33-10-400-801 MM).
| No |
10 Do a test for continuity/resistance (1 ohm max./harness), internal shorts, and shorts to ground (1,000 ohms min.) on the W11/14, W12/13, and the W7 harnesses (Ref. FIG. 301/TASK 75-33-00-990-801/FIG. 302/TASK 75-33-00-990-802) (Ref. 75-31-50 WM). Replace the harness that has the fault (Ref. 76-00-00 MM) (Ref. AMM).
FADEC Discrete: CVGFBF (bit 18) / (353 / EILRU) = 1 EFFECTIVITY:ALL
TASK 75−33−00−810−802 Page 202 Apr 20/12
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FADEC Discrete: CVGFBD (bit 22) / (357 / EIDIF) = 1 DESCRIPTION: This discrete is set to 1 (fault sensed) when the signal received from the position sensor (LVDT) for the compressor variable-geometry (CVG) actuator, for this FADEC, is different (more than 0.1 inches) from that received by the other FADEC. This test is not done if either channel's CVG position sensor or the cross-channel data link fault discretes are set to 1.
POSSIBLE CAUSES: R R R
1. Harness 2. FADEC 3. CVG actuator
01 Remove and install all of the harness connectors between the FADEC J4 receptacle and the INTA(B) connector (Ref. FIG. 301/TASK 75-33-00-990-801/FIG. 302/TASK 75-33-00-990-802). Rotate the FADEC reset/select switch to the RESET position. Access label 357 from the CMC (Ref. Introduction). Does CVGFBD (bit 22) = 1?
06 Examine all the harness connectors between the FADEC J4 receptacle and the INTA(B) connector for damage, corrosion, or contamination (Ref. FIG. 301/TASK 75-33-00-990-801/FIG. 302/TASK -No 75-33-00-990-802) (Ref. 70-00-00-910-804 MM). Repair or clean the connectors as necessary. Make sure there is not another occurrence of the maintenance message after engine operation.
| Yes 02 Access the FADEC analog label from the central maintenance computer (CMC) for both FADECs (Ref. Introduction). Is CVGPOS different, by more than 0.1 in.?
07 Replace the FADEC showing CVGFBD (bit 22) = 1 (Ref. -No 73-25-10-000-801/73-25-10-400-801 MM).
| Yes 03 Interchange the position of the FADECs 08 Replace the FADEC that has the fault (Ref. (Ref. 73-25-10-000-801/73-25-10-400-801 73-25-10-000-801/73-25-10-400-801 MM). MM). Rotate the FADEC reset/select switch to -Yes the RESET position. Do the CVGPOS values move to the opposite channel? | No 04 Go to Block 05
FADEC Discrete: CVGFBD (bit 22) / (357 / EIDIF) = 1 EFFECTIVITY:ALL
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05 Interchange the position of harness connectors CVGA and CVGB on the CVG actuator. Rotate the FADEC reset/select switch to the RESET position. Do the CVGPOS values move to the opposite channel?
09 Replace the CVG actuator (Ref. 75-33-10-000-801/75-33-10-400-801 MM). -Yes
| No |
10 Do a test for continuity/resistance (1 ohm max./harness), internal shorts, and shorts to ground (1,000 ohms min.) on the W11, W14, W12, W13 and both W7 harnesses (Ref. FIG. 301/TASK 75-33-00-990-801/FIG. 302/TASK 75-33-00-990-802) (Ref. 75-31-50 WM). Replace the harness that has the fault (Ref. 76-00-00 MM) (Ref. AMM).
FADEC Discrete: CVGFBD (bit 22) / (357 / EIDIF) = 1 EFFECTIVITY:ALL
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Observed Fault: CVG Hydraulic-Actuator Seal-Drain Accumulation DESCRIPTION: The CVG hydraulic actuator has an integral drain cavity to allow the fuel leakage past the actuator rod seal to accumulate, and be drained. A tube connects the actuator drain cavity to a drain sight-glass, located below the accessory-drive gearbox.
POSSIBLE CAUSES: 1. CVG actuator
R R R R R R R
01 Operate the engine at ground idle for a minimum of five minutes before you do the leakage inspection or you will get an incorrect leakage indication (Ref. TASK 72-00-00-700-801). Does the fuel accumulate in the sight-glass at a rate of more than 0.5 cc or 10 drops in three minutes?
02 Replace the CVG hydraulic actuator (Ref. 75-33-10-000-801/75-33-10-400-801 MM). -Yes
| No | R
03 Up to 0.5 cc or 10 drops in three minutes is an allowable leakage rate. Continue to monitor the sight-glass for an increase in the leakage rate.
Observed Fault: CVG Hydraulic-Actuator Seal-Drain Accumulation EFFECTIVITY:ALL
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Maintenance Message: ND-ENG1/ENG2 CVG SYS DIFF DESCRIPTION: This message occurs when the FADEC finds that the signal from the position sensor for the compressor variable-geometry (CVG) actuator, for this channel, is not within limits.
POSSIBLE CAUSES: R R R
1. Harness 2. FADEC 3. CVG actuator
01 Supply electrical power to the aircraft. Access FADEC discrete label 357 from the central maintenance computer (CMC) for both FADECs (Ref. Introduction). Is CVGFBD (bit 22) = 1?
-Yes
03 Do the troubleshooting for FADEC discrete CVGFBD (bit 22) = 1 (Ref. 75-33-00-810-803).
| No 02 Operate the engine to the maximum thrust practical and do a normal shutdown (Ref. AMM). Do not remove electrical power from the FADECs. Does CVGFB (bit 22) = 1?
-Yes
04 Do the troubleshooting for FADEC discrete CVGFBD (bit 22) = 1 (Ref. 75-33-00-810-803).
| No |
05 Examine all of the harness connectors between the FADEC J4 receptacle and the CVG actuator for looseness, damage, corrosion or contamination. Tighten, repair, or clean the connectors as necessary (Ref. FIG. 301/TASK 75-33-00-990-801/FIG. 302/TASK 75-33-00-990-802) (Ref. 70-00-00-910-804 MM).
Maintenance Message: ND-ENG1/ENG2 CVG SYS DIFF EFFECTIVITY:ALL
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Maintenance Message: ST-ENG1/ENG2 CVG SYS DESCRIPTION: This message occurs when the FADEC finds that the signal from the position sensor for the compressor variable-geometry (CVG) actuator, for this channel, is different than the signal from the other channel.
POSSIBLE CAUSES: R R R
1. Harness 2. FADEC 3. CVG actuator
01 Supply electrical power to the aircraft. Access FADEC discrete label 353 from the central maintenance computer (CMC) for both FADECs (Ref. Introduction). Does CVGFBF (bit 18) = 1?
-Yes
03 Do the troubleshooting for FADEC discrete CVGFBF (bit 18) = 1 (Ref. 75-33-00-810-802).
| No 02 Operate the engine to the maximum thrust practical and do a normal shutdown (Ref. AMM). Do not remove electrical power from the FADECs. Does CVGFBF (bit 18) = 1?
-Yes
04 Do the troubleshooting for FADEC discrete CVGFBF (bit 18) = 1 (Ref. 75-33-00-810-802).
| No |
05 Examine all of the harness connectors between the FADEC J4 receptacle and the CVG actuator for looseness, damage, corrosion or contamination. Tighten, repair, or clean the connectors as necessary (Ref. FIG. 301/TASK 75-33-00-990-801/FIG. 302/TASK 75-33-00-990-802) (Ref. 70-00-00-910-804 MM).
Maintenance Message: ST-ENG1/ENG2 CVG SYS EFFECTIVITY:ALL
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CVG Position Sensor (LVDT) / FADEC Interface Diagram FIG. 301/TASK 75-33-00-990-801
R EFFECTIVITY:ALL
75−33−TASK SUPPORT Page 301 Aug 15/04
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Engine Wiring Diagram FIG. 3021/TASK 75-33-00-990-802
R EFFECTIVITY:ALL
75−33−TASK SUPPORT Page 302 Aug 15/04
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FADEC Discrete: T25FLT (bit 16) / (353 / EILRU) = 1 DESCRIPTION: The FADEC monitors the signal received from the T2.5 sensor for this channel. This discrete is set to 1 (fault sensed) when the T2.5 value sensed is not within the limits.
POSSIBLE CAUSES: 1. T2.5 sensor 2. Harness 3. FADEC
01 Remove and install all of the harness connectors between the FADEC J4 receptacle and the INTA(B) connector (Ref. FIG. 301/TASK 75-41-00-990-801/FIG. 302/TASK 75-41-00-990-802). Rotate the FADEC reset/select switch to the RESET position. Access label 353 from the CMC (Ref. Introduction). Does T25FLT (bit 16) = 1?
06 Examine all the harness connectors between the FADEC J4 receptacle and the INTA(B) connector for damage, corrosion, or contamination (Ref. FIG. 301/TASK 75-41-00-990-801/FIG. 302/TASK -No 75-41-00-990-802) (Ref. 70-00-00-910-804 MM). Repair or clean the connectors as necessary. Make sure there is not another occurrence of the maintenance message after engine operation.
| Yes 02 Access FADEC discrete label 360 from the 07 Do the troubleshooting for SEXFLT (bit 21) -Yes CMC. Does SEXFLT (bit 21) = 1? = 1 (Ref. 73-25-00-810-826). | No 03 Interchange the position of the FADECs 08 Replace the FADEC that has the fault (Ref. (Ref. 73-25-10-000-801/73-25-10-400-801 73-25-10-000-801/73-25-10-400-801 MM). MM). Rotate the FADEC reset/select switch to -Yes the RESET position. Does the fault move to the opposite channel? | No 04 Go to Block 05
FADEC Discrete: T25FLT (bit 16) / (353 / EILRU) = 1 R EFFECTIVITY:FADEC SOFTWARE VER. B5.1.1
TASK 75−41−00−810−801−A01 Page 201 Oct 15/05
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05 Interchange the position of harness 09 Replace the T2.5 sensor (Ref. connectors T2.5A and T2.5B at the T2.5 75-41-10-000-801/75-41-10-400-801 MM). sensor. Rotate the FADEC reset/select switch -Yes to the RESET position. Does the fault move to the opposite channel? | No | 10 Do a test for continuity/resistance (1 ohm max./harness), internal shorts and shorts to ground (1,000 ohms min.) on the W11/14, W12/13 and the W7 harnesses (Ref. FIG. 301/TASK 75-41-00-990-801/FIG. 302/TASK 75-41-00-990-802) (Ref. 75-31-51 WM). Replace the harness that has the fault (Ref. 76-00-00 MM) (Ref. AMM).
FADEC Discrete: T25FLT (bit 16) / (353 / EILRU) = 1 R EFFECTIVITY:FADEC SOFTWARE VER. B5.1.1
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FADEC Discrete: T25NOK (bit 16) / (353 / EILRU) = 1 DESCRIPTION: The FADEC monitors the signal received from the T2.5 sensor for this channel. This discrete is set to 1 (fault sensed) when the T2.5 value sensed is not within the limits.
POSSIBLE CAUSES: 1. T2.5 sensor 2. Harness 3. FADEC
01 Remove and install all of the harness connectors between the FADEC J4 receptacle and the INTA(B) connector (Ref. FIG. 301/TASK 75-41-00-990-801/FIG. 302/TASK 75-41-00-990-802). Rotate the FADEC reset/select switch to the RESET position. Access label 353 from the CMC (Ref. Introduction). Does T25NOK (bit 16) = 1?
06 Examine all the harness connectors between the FADEC J4 receptacle and the INTA(B) connector for damage, corrosion, or contamination (Ref. FIG. 301/TASK 75-41-00-990-801/FIG. 302/TASK -No 75-41-00-990-802) (Ref. 70-00-00-910-804 MM). Repair or clean the connectors as necessary. Make sure there is not another occurrence of the maintenance message after engine operation.
| Yes 02 Access FADEC discrete label 360 from the CMC. Does SEXFLT (bit 21) = 1?
-Yes
07 Do the troubleshooting for SEXFLT (bit 21) = 1 (Ref. 73-25-00-810-826).
| No 03 Interchange the position of the FADECs 08 Replace the FADEC that has the fault (Ref. (Ref. 73-25-10-000-801/73-25-10-400-801 73-25-10-000-801/73-25-10-400-801 MM). MM). Rotate the FADEC reset/select switch to -Yes the RESET position. Does the fault move to the opposite channel? | No 04 Go to Block 05.
FADEC Discrete: T25NOK (bit 16) / (353 / EILRU) = 1 EFFECTIVITY:FADEC SOFTWARE VER. B7.5 OR LATER
TASK 75−41−00−810−801−B01 Page 201 Oct 15/05
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05 Interchange the position of harness connectors T2.5A and T2.5B at the T2.5 sensor. Rotate the FADEC reset/select switch to the RESET position. Does the fault move to the opposite channel?
-Yes
09 Replace the T2.5 sensor (Ref. 75-41-10-000-801/75-41-10-400-801 MM).
| No | 10 Do a test for continuity/resistance (1 ohm max./harness), internal shorts and shorts to ground (1,000 ohms min.) on the W11/14, W12/13 and the W7 harnesses (Ref. FIG. 301/TASK 75-41-00-990-801/FIG. 302/TASK 75-41-00-990-802) (Ref. 75-31-51 WM). Replace the harness that has the fault (Ref. 76-00-00 MM) (Ref. AMM).
FADEC Discrete: T25NOK (bit 16) / (353 / EILRU) = 1 EFFECTIVITY:FADEC SOFTWARE VER. B7.5 OR LATER
TASK 75−41−00−810−801−B01 Page 202 Oct 15/05
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FADEC Discrete: T25DIF (bit 20) / (357 / EIDIF) = 1 DESCRIPTION: This discrete is set to 1 (fault sensed) when the signal received from the T2.5 sensor for this FADEC is different (more than 25 °F) from that received by the other FADEC. This test is not done if either channel's T2.5 sensor or the cross-channel data link fault discretes are set to 1.
POSSIBLE CAUSES: 1. T2.5 sensor 2. Harness 3. FADEC
01 Remove and install all of the harness 06 Examine all the harness connectors connectors between the FADEC J4 receptacles between the FADEC J4 receptacle and the and the INTA(B) connectors (Ref. FIG. INTA(B) connector for damage, corrosion, or 301/TASK 75-41-00-990-801/FIG. 302/TASK contamination (Ref. FIG. 301/TASK 75-41-00-990-802). Rotate the FADEC 75-41-00-990-801/FIG. 302/TASK -No reset/select switch to the RESET position. 75-41-00-990-802) (Ref. 70-00-00-910-804 Access label 357 from the CMC, for both MM). Repair or clean the connectors as FADECs. Does T25DIF (bit 20) = 1? necessary. Make sure there is not another occurrence of the maintenance message after engine operation. | Yes 02 Access the FADEC analog label from the central maintenance computer (CMC) for both FADECs. Is T2.5 different, by more than 25 °F?
07 Replace the FADEC showing T25DIF (bit 20) = 1 (Ref. 73-25-10-000-801/ -Yes 73-25-10-400-801 MM).
| No 03 Interchange the position of the FADECs 08 Replace the FADEC that has the fault (Ref. (Ref. 73-25-10-000-801/73-25-10-400-801 73-25-10-000-801/73-25-10-400-801 MM). MM). Rotate the FADEC reset/select switch to -Yes the RESET position. Do the T2.5 values move to the opposite channel? | No 04 Go to Block 05
FADEC Discrete: T25DIF (bit 20) / (357 / EIDIF) = 1 R EFFECTIVITY:FADEC SOFTWARE VER. B5.1.1
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05 Interchange the position of harness connectors T2.5A and T2.5B at the T2.5 sensor. Rotate the FADEC reset/select switch to the RESET position. Do the T2.5 values move to the opposite channel?
-Yes
09 Replace the T2.5 sensor (Ref. 75-41-10-000-801/75-41-10-400-801 MM).
| No | 10 Do a test for continuity/resistance (1 ohm max./harness), internal shorts, and shorts to ground (1,000 ohms min.) on the W11, W14, W12, W13 and both W7 harnesses (Ref. FIG. 301/TASK 75-41-00-990-801/FIG. 302/TASK 75-41-00-990-802). Replace the harness that has the fault (Ref. 76-00-00 MM) (Ref. AMM).
FADEC Discrete: T25DIF (bit 20) / (357 / EIDIF) = 1 R EFFECTIVITY:FADEC SOFTWARE VER. B5.1.1
TASK 75−41−00−810−802 Page 202 Oct 15/05
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Maintenance Message: ND - ENG1 / ENG2 HPC SYS DESCRIPTION: This message occurs when a dual T2.5 or P2.5 failure occurs, or when a single T2.5 or P2.5 failure occurs and the cross-channel data link (CCDL) failure is detected.
POSSIBLE CAUSES: 1. T2.5 Sensor 2. P2.5 Sensor 3. Harness 4. FADEC
01 Supply electrical power to the aircraft. Access FADEC discrete label 354 from the central maintenance computer (CMC) for both FADECs (Ref. Introduction). Does XTLKFT (bit 11) = 1 for either FADEC?
-Yes
04 Do the troubleshooting for XTLKFT (bit 11) (Ref. 77-40-00-810-803, go to block 02).
| No R
02 Access FADEC discrete label 352 from the 05 Do the troubleshooting for FADEC discrete central maintenance computer (CMC) for both T25BLF (bit 22) (Ref. 75-41-00-810-804-A01). -Yes FADECs (Ref. Introduction). Does T25BLF (bit 22) = 1? | No
R
03 Does P25BLF (bit 23) = 1?
-Yes
06 Do the troubleshooting for FADEC discrete P25BLF (bit 23) (Ref. 75-43-00-810-809-A01).
| No | 07 Examine all of the harness connectors between the FADEC J4 receptacle and the T2.5 and P2.5 sensors for looseness, corrosion, contamination, or damage (Ref. FIG. 302/TASK 75-41-00-990-802). Tighten, clean, or repair the harness(es) as necessary (Ref. 70-00-00-910-804 MM).
Maintenance Message: ND - ENG1 / ENG2 HPC SYS R EFFECTIVITY:FADEC SOFTWARE VER. B5.1.1
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Maintenance Message: ND - ENG1 / ENG2 HPC SYS DESCRIPTION: This message occurs when a dual T2.5 or P2.5 failure occurs.
POSSIBLE CAUSES: 1. T2.5 Sensor 2. P2.5 Sensor 3. Harness 4. FADEC
01 Supply electrical power to the aircraft. Access FADEC discrete label 352 from the central maintenance computer (CMC) for both FADECs (Ref. Introduction). Does T25DCF (bit 22) = 1?
-Yes
03 Do the troubleshooting for FADEC discrete T25DCF (bit 22) (Ref. 75-41-00-810-804-B01).
| No 02 Does P25DCF (bit 23) = 1?
-Yes
04 Do the troubleshooting for FADEC discrete P25DCF (bit 23) (Ref. 75-43-00-810-809-B01).
| No | 05 Examine all of the harness connectors between the FADEC J4 receptacle and the T2.5 and P2.5 sensors for looseness, corrosion, contamination, or damage (Ref. FIG. 302/TASK 75-41-00-990-802). Tighten, clean, or repair the harness(es) as necessary (Ref. 70-00-00-910-804 MM).
Maintenance Message: ND - ENG1 / ENG2 HPC SYS EFFECTIVITY:FADEC SOFTWARE VER. B7.5 OR LATER
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FADEC Discrete: T25BLF (bit 22) / (352 /AILRU2) = 1 DESCRIPTION: This message occurs when this FADEC has detected a T2.5 sensor fault (label 353, bit 16) and, either a T2.5 sensor fault has been detected in the other FADEC or a cross-channel data link (CCDL) fault has been detected.
POSSIBLE CAUSES: 1. T2.5 Sensor 2. Harness 3. FADEC
01 Supply electrical power to the aircraft. Access FADEC discrete label 354 from the central maintenance computer (CMC) for both FADECs (Ref. Introduction). Does XTLKFT (bit 11) = 1 for either FADEC?
-Yes
03 Do the troubleshooting for XTLKFT (bit 11) (Ref. 77-40-00-810-803, go to block 02).
| No 02 Access FADEC discrete label 353 from the 04 Do the troubleshooting for FADEC discrete CMC for both FADECs (Ref. Introduction). -Yes T25FLT (bit 16) (Ref. 75-41-00-810-801). Does T25FLT (bit 16) = 1 for either FADEC? | No | 05 Examine all of the harness connectors between the FADEC J4 receptacle and the T2.5 sensor for looseness, corrosion, contamination, or damage (Ref. FIG. 302/TASK 75-41-00-990-802). Tighten, clean, or repair the harness(es) as necessary (Ref. 70-00-00-910-804 MM).
FADEC Discrete: T25BLF (bit 22) / (352 /AILRU2) = 1 R EFFECTIVITY:FADEC SOFTWARE VER. B5.1.1
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FADEC Discrete: T25DCF (bit 22) / (352 /AILRU2) = 1 DESCRIPTION: This message occurs when this FADEC has detected a T2.5 sensor fault (label 353, bit 16).
POSSIBLE CAUSES: 1. T2.5 Sensor 2. Harness 3. FADEC
01 Supply electrical power to the aircraft. Access FADEC discrete label 353 from the CMC for both FADECs (Ref. Introduction). Does T25NOK (bit 16) = 1 for either FADEC?
-Yes
02 Do the troubleshooting for FADEC discrete T25NOK (bit 16) (Ref. 75-41-00-810-801-B01).
| No | 03 Examine all of the harness connectors between the FADEC J4 receptacle and the T2.5 sensor for looseness, corrosion, contamination, or damage (Ref. FIG. 302/TASK 75-41-00-990-802). Tighten, clean, or repair the harness(es) as necessary (Ref. 70-00-00-910-804 MM).
FADEC Discrete: T25DCF (bit 22) / (352 /AILRU2) = 1 EFFECTIVITY:FADEC SOFTWARE VER. B7.5 OR LATER
TASK 75−41−00−810−804−B01 Page 201/202 Oct 15/05
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T2.5 Sensor / FADEC Interface Diagram FIG. 301/TASK 75-41-00-990-801
R EFFECTIVITY:ALL
75−41−TASK SUPPORT Page 301 Aug 15/04
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Engine Wiring Diagram FIG. 302/TASK 75-41-00-990-802
R EFFECTIVITY:ALL
75−41−TASK SUPPORT Page 302 Aug 15/04
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R FADEC Discrete: P25FLT (bit 17) / (353 / EILRU) = 1 DESCRIPTION: The FADEC monitors the signal received from the P2.5 sensor for this channel. This discrete is set to 1 (fault sensed) when the P2.5 value sensed is not within the limits.
POSSIBLE CAUSES: 1. P2.5 sensor 2. Harness 3. FADEC
01 Remove and install the harness connectors 06 Examine all the harness connectors at the FADEC J4 receptacle, the firewall, and between the FADEC J4 receptacle and the the P2.5 sensor (Ref. FIG. 301/TASK P2.5 sensor for damage, corrosion, or 75-43-00-990-801/FIG. 302/TASK contamination (Ref. FIG. 301/TASK -No 75-43-00-990-802). Rotate the FADEC 75-43-00-990-801/FIG. 302/TASK reset/select switch to the RESET position. 75-43-00-990-802). Repair or clean the Access label 353 from the CMC (Ref. connectors as necessary (Ref. Introduction). Does P25FLT (bit 17) = 1? 70-00-00-910-804 MM). | Yes 02 Access FADEC discrete label 360 from the 07 Do the troubleshooting for SEXFLT (bit 21) CMC (Ref. Introduction). Does SEXFLT (bit -Yes = 1 (Ref. 73-25-00-810-826). 21) = 1? | No 03 Interchange the position of the P2.5 sensors (Ref. 75-43-10-000-801/75-43-10-400-801 MM). Rotate the FADEC reset/select switch to the RESET position. Does the fault move to the opposite channel?
-Yes
08 Replace the P2.5 sensor that has the fault (Ref. 75-43-10-000-801/75-43-10-400-801 MM).
| No 04 Go to Block 05
FADEC Discrete: P25FLT (bit 17) / (353 / EILRU) = 1 R EFFECTIVITY:FADEC SOFTWARE VER. B5.1.1
TASK 75−43−00−810−801−A01 Page 201 Oct 15/05
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05 Interchange the position of the FADECs 09 Replace the FADEC that has the fault (Ref. 73-25-10-000-801/73-25-10-400-801 (Ref. 73-25-10-000-801/73-25-10-400-801 MM). Rotate the FADEC reset/select switch to -Yes MM). the RESET position. Does the fault move to the opposite channel? | No | 10 Do a test for continuity/resistance (1 ohm max./harness), internal shorts, and shorts to ground (1,000 ohms min.) on the W7 and the W11/14 harnesses (Ref. FIG. 301/TASK 75-43-00-990-801/FIG. 302/TASK 75-43-00-990-802) (Ref. 75-31-51 WM). Replace the harness that has the fault (Ref. 76-00-00 MM) (Ref. AMM).
FADEC Discrete: P25FLT (bit 17) / (353 / EILRU) = 1 R EFFECTIVITY:FADEC SOFTWARE VER. B5.1.1
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FADEC Discrete: P25NOK (bit 17) / (353 / EILRU) = 1 DESCRIPTION: The FADEC monitors the signal received from the P2.5 sensor for this channel. This discrete is set to 1 (fault sensed) when the P2.5 value sensed is not within the limits.
POSSIBLE CAUSES: 1. P2.5 sensor 2. Harness 3. FADEC
01 Remove and install the harness connectors at the FADEC J4 receptacle, the firewall, and the P2.5 sensor (Ref. FIG. 301/TASK 75-43-00-990-801/FIG. 302/TASK 75-43-00-990-802). Rotate the FADEC reset/select switch to the RESET position. Access label 353 from the CMC (Ref. Introduction). Does P25NOK (bit 17) = 1?
06 Examine all the harness connectors between the FADEC J4 receptacle and the P2.5 sensor for damage, corrosion, or contamination (Ref. FIG. 301/TASK -No 75-43-00-990-801/FIG. 302/TASK 75-43-00-990-802). Repair or clean the connectors as necessary (Ref. 70-00-00-910-804 MM).
| Yes 02 Access FADEC discrete label 360 from the 07 Do the troubleshooting for SEXFLT (bit 21) CMC (Ref. Introduction). Does SEXFLT (bit 21) -Yes = 1 (Ref. 73-25-00-810-826). = 1? | No 03 Interchange the position of the P2.5 sensors (Ref. 75-43-10-000-801/75-43-10-400-801 MM). Rotate the FADEC reset/select switch to the RESET position. Does the fault move to the opposite channel?
-Yes
08 Replace the P2.5 sensor that has the fault (Ref. 75-43-10-000-801/75-43-10-400-801 MM).
| No 04 Go to Block 05.
FADEC Discrete: P25NOK (bit 17) / (353 / EILRU) = 1 EFFECTIVITY:FADEC SOFTWARE VER. B7.5 OR LATER
TASK 75−43−00−810−801−B01 Page 201 Oct 15/05
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05 Interchange the position of the FADECs (Ref. 73-25-10-000-801/73-25-10-400-801 MM). Rotate the FADEC reset/select switch to the RESET position. Does the fault move to the opposite channel?
-Yes
09 Replace the FADEC that has the fault (Ref. 73-25-10-000-801/73-25-10-400-801 MM).
| No | 10 Do a test for continuity/resistance (1 ohm max./harness), internal shorts, and shorts to ground (1,000 ohms min.) on the W7 and the W11/14 harnesses (Ref. FIG. 301/TASK 75-43-00-990-801/FIG. 302/TASK 75-43-00-990-802) (Ref. 75-31-51 WM). Replace the harness that has the fault (Ref. 76-00-00 MM) (Ref. AMM).
FADEC Discrete: P25NOK (bit 17) / (353 / EILRU) = 1 EFFECTIVITY:FADEC SOFTWARE VER. B7.5 OR LATER
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FADEC Discrete: P25DIF (bit 21) / (357 / EIDIF) = 1 DESCRIPTION: This discrete is set to 1 (fault sensed) when the signal received from the P2.5 sensor for this FADEC is different (more than 2 psia) from that received by the other FADEC. This test is not done if either channel's P2.5 sensor or the cross-channel data link fault discretes are set to 1.
POSSIBLE CAUSES: 1. P2.5 sensor 2. Harness 3. FADEC
01 Remove and install the harness connectors 06 Examine all the harness connectors at the FADEC J4 receptacles, the firewall, and between the FADEC J4 receptacle and the the P2.5 sensors (Ref. FIG. 301/TASK P2.5 sensor for damage, corrosion, or 75-43-00-990-801/FIG. 302/TASK contamination (Ref. FIG. 301/TASK 75-43-00-990-802). Rotate the FADEC -No 75-43-00-990-801/FIG. 302/TASK reset/select switch to the RESET position. 75-43-00-990-802). Repair or clean the Access label 357 from the CMC, for both connectors as necessary (Ref. FADECs (Ref. Introduction). Does P25DIF (bit 70-00-00-910-804 MM). 21) = 1? | Yes 02 Access the FADEC analog label from the central maintenance computer (CMC) for both FADECs (Ref. Introduction). Is P2.5 different, by more than 2 psia?
07 Replace the FADEC showing P25DIF (bit 21) = 1 (Ref. 73-25-10-000-801/ -No 73-25-10-400-801 MM).
| Yes 03 Interchange the position of the P2.5 sensors (Ref. 75-43-10-000-801/75-43-10-400-801 MM). Rotate the FADEC reset/select switch to the RESET position. Do the P2.5 values move to the opposite channel?
08 Download the FADEC analog label from the CMC (Ref. Introduction), for both FADECs on the opposite engine. Replace the P2.5 -Yes sensor on this engine with the greatest difference, compared to the pressure values of the other 3 sensors (Ref. 75-43-10-000-801/ 75-43-10-400-801 MM).
| No 04 Go to Block 05
FADEC Discrete: P25DIF (bit 21) / (357 / EIDIF) = 1 R EFFECTIVITY:FADEC SOFTWARE VER. B5.1.1
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05 Interchange the position of the FADECs 09 Replace the FADEC that has the fault (Ref. 73-25-10-000-801/73-25-10-400-801 (Ref. 73-25-10-000-801/73-25-10-400-801 MM). Rotate the FADEC reset/select switch to -Yes MM). the RESET position. Do the P2.5 values move to the opposite channel? | No | 10 Do a test for continuity/resistance (1 ohm max./harness), internal shorts, and shorts to ground (1,000 ohms min.) on the W7 and the W11/14 harnesses (Ref. FIG. 301/TASK 75-43-00-990-801/FIG. 302/TASK 75-43-00-990-802) (Ref. 75-31-51 WM). Replace the harness that has the fault (Ref. 76-00-00 MM) (Ref. AMM).
FADEC Discrete: P25DIF (bit 21) / (357 / EIDIF) = 1 R EFFECTIVITY:FADEC SOFTWARE VER. B5.1.1
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FADEC Discrete: P0SFT (bit 28) / (353 / EILRU) = 1 DESCRIPTION: The FADEC monitors the signal received from the P0 sensor for this channel. This discrete is set to 1 (fault sensed) when the P0 value sensed is not within the limits.
POSSIBLE CAUSES: 1. Foreign material in the aircraft P0 sensor line 2. P0 sensor 3. Harness 4. FADEC
01 Examine the aircraft P0 static line for blockage or water contamination. Is foreign material present?
06 Remove the foreign material or drain the -Yes water from the static line (Ref. 34-13-00/201 AMM).
| No 02 Remove and install the harness connectors 07 Examine the harness connnectors at the at the FADEC J4 receptacle and the P0 sensor FADEC J4 recptacle and the P0 sensor for (Ref. FIG. 302/TASK 75-43-00-990-802/FIG. damage, corrosion, or contamination (Ref. 303/TASK 75-43-00-990-803). Rotate the -No 20-50-00 WM). Repair or clean the connectors FADEC reset/select switch to the RESET as necessary. position. Access label 353 from the CMC (Ref. Introduction). Does P0SFT (bit 28) = 1? | Yes R R
03 Interchange the position of the P0 sensors. 08 Replace the P0 sensor that has the fault Rotate the FADEC reset/select switch to the (Ref. 73-25-01-000-801/73-25-01-400-801, -Yes RESET position. Does the fault move to the AMM). opposite channel? | No 04 Go to Block 05
FADEC Discrete: P0SFT (bit 28) / (353 / EILRU) = 1 EFFECTIVITY:ALL
TASK 75−43−00−810−803 Page 201 Apr 20/09
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05 Interchange the position of the FADECs (Ref. 73-25-10-000-801/73-25-10-400-801 MM). Rotate the FADEC reset/select switch to the RESET position. Does the fault move to the opposite channel?
09 Replace the FADEC that has the fault (Ref. 73-25-10-000-801/73-25-10-400-801 -Yes MM).
| No |
10 Do the troubleshooting on the aircraft W7 harness (Ref. 75-31-51 WM).
FADEC Discrete: P0SFT (bit 28) / (353 / EILRU) = 1 EFFECTIVITY:ALL
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FADEC Discrete: P0SDIF (bit 27) / (357 / EIDIF) = 1 DESCRIPTION: This discrete is set to 1 (fault sensed) when the signal received from the P0 sensor for this FADEC is different (more than 0.5 psia) from that received by the other FADEC. This test is not done if either channel's P0 sensor or the cross-channel data link fault discretes are set to 1.
POSSIBLE CAUSES: 1. Foreign material in the aircraft P0 sensor line 2. P0 sensor 3. Harness 4. FADEC
01 Examine the aircraft P0 static line for blockage or water contamination. Is foreign material present?
07 Remove the foreign material or drain the -Yes water from the static line (Ref. 34-13-00/201 AMM).
| No
R R R
02 Remove and install the harness connectors at the FADEC J4 receptacle and the P0 sensors (Ref. FIG. 302/TASK 75-43-00-990-802/FIG. 303/TASK 75-43-00-990-803) (Ref. 73-22-01/401 AMM). -No Rotate the FADEC reset/select switch to the RESET position. Access label 357 from the central maintenance computer (CMC), for both FADECs (Ref. Introduction). Does P0SDIF (bit 27) = 1?
08 Examine the harness connnectors at the FADEC J4 recptacle and the P0 sensor for damage, corrosion, or contamination (Ref. 20-50-00 WM). Repair or clean the connectors as necessary.
| Yes 03 Access the FADEC analog label from the CMC for both FADECs (Ref. Introduction). Is P0 different, by more than 0.5 psia?
09 Replace the FADEC showing P0SDIF (bit -No 27) = 1 (Ref. 73-25-10-000-801/ 73-25-10-400-801 MM).
| Yes 04 Go to Block 05
FADEC Discrete: P0SDIF (bit 27) / (357 / EIDIF) = 1 EFFECTIVITY:ALL
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05 Interchange the position of the FADECs 10 Download the FADEC analog label from (Ref. 73-25-10-000-801/73-25-10-400-801 the CMC, for both FADECs on the opposite MM). Rotate the FADEC reset/select switch to engine (Ref. Introduction). Replace the P0 -Yes the RESET position. Do the P0 values move to sensor on this engine with the greatest the opposite channel? difference, compared to the pressure values of the other 3 sensors. | No 06 Interchange the position of the FADECs 11 Replace the FADEC that has the fault (Ref. 73-25-10-000-801/73-25-10-400-801 (Ref. 73-25-10-000-801/73-25-10-400-801 MM). Rotate the FADEC reset/select switch to -Yes MM). the RESET position. Do the P0 values move to the opposite channel? | No |
12 Do the troubleshooting on the aircraft W7 harnesses (Ref. 75-31-51 WM).
FADEC Discrete: P0SDIF (bit 27) / (357 / EIDIF) = 1 EFFECTIVITY:ALL
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Maintenance Message: ENG1/ENG2 PALT x P0 DIFF FAULT (set by FADEC Discrete: P0ADCF (bit 29) / (357/EIDIF) = 1) DESCRIPTION: This message is set when the ambient pressure signal received from the P0 sensor for this FADEC is different from the ambient pressure value (calculated from pressure altitude (PALT) received from the air data computer (ADC) for this channel, by more than 0.5 psia.
POSSIBLE CAUSES: 1. Foreign material in the aircraft P0/Pamb sensor lines 2. P0 sensor 3. Harness 4. FADEC 5. Air data computer/circuit fault
01 Examine the aircraft P0 and Pamb static lines for blockage or water contamination. Is foreign material present?
08 Remove the foreign material or drain the -Yes water from the static line(s) (Ref. 34-13-00/201 AMM).
| No 02 Supply electrical power to the aircraft. Access FADEC discrete label 353 from the central maintenance computer (CMC) for both FADECs (Ref. Introduction). Does P0SFT (bit 28) = 1?
-Yes
09 Do the troubleshooting for FADEC discrete P0SFT (bit 28) = 1 (Ref. 75-43-00-810-803).
| No 03 Access the FADEC discrete label 357 CMC for both FADECs (Ref. Introduction). Does P0ADCF (bit 29) = 1?
10 Examine the J4 harness connector at the FADEC, and the aircraft harness connector at the P0 sensor, for damage, corrosion, or -No contamination (Ref. 20-50-00 WM). (Ref. 70-00-00-910-804 MM). Repair or clean the connectors as necessary.
| Yes 04 Go to Block 05
Maintenance Message: ENG1/ENG2 PALT x P0 DIFF FAULT EFFECTIVITY:ALL
TASK 75−43−00−810−805 Page 201 Aug 15/04
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R R
05 Remove and install the harness connectors at the FADEC J4 receptacle and the P0 sensor (Ref. FIG. 302/TASK 75-43-00-990-802/FIG. 303/TASK 75-43-00-990-803). Rotate the FADEC reset/select switch to the RESET position. Does P0ADCF (bit 29) = 1?
11 Examine the harness connectors at the FADEC J4 receptacles and the P0 sensors for damage, corrosion, or contamination (Ref. -No 20-50-00 WM) (Ref. 70-00-00-910-804 MM). Repair or clean the connectors as necessary.
| Yes 06 Interchange the positions of the P0 sensor 12 Replace the P0 sensor that has the fault connectors. Rotate the FADEC reset/select (Ref. 73-22-00/401 AMM). -Yes switch to the RESET position. Does fault move to the opposite channel? | No 07 Interchange the position of the FADECs 13 Replace the FADEC that has the fault (Ref. 73-25-10-000-801/73-25-10-400-801 (Ref. 73-25-10-000-801/73-25-10-400-801 MM). Rotate the FADEC reset/select switch to -Yes MM). the RESET position. Does the fault move to the opposite channel? | No |
14 Do the troubleshooting on the aircraft system (W7 harness and air data computer) (Ref. 75-31-51 WM) (Ref. 34-22-00 EMB FIM).
Maintenance Message: ENG1/ENG2 PALT x P0 DIFF FAULT EFFECTIVITY:ALL
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Maintenance Message: LT-ENG1/ENG2 PR/TMP DATA SYS DESCRIPTION: This message occurs when either of the following conditions occur: the signal received by the FADEC from either the T2.5, P2.5, or P0 sensor is not within limits, or any one of the T2.5, P2.5, or P0 sensor signals received by this FADEC is different from that received by the other FADEC, or the ambient pressure signal received from the P0 sensor for this FADEC is different from the ambient pressure value received from the air data computer (ADC) for this channel. NOTE: If this message continues to occur without a fault found, look at the maintenance page of the central maintenance computer (CMC) for the maintenance message "ENG1/ENG2 LT FAULT" and "LT-ENG1/ENG2 PR/TMP DATA SYS" after subsequent flights.
POSSIBLE CAUSES: 1. Loose connectors 2. Foreign material in the aircraft P0/Pamb sensor lines 3. P0 Sensor System failure 4. T2.5 Sensor System failure 5. P2.5 Sensor System failure 6. Harness 7. ADC 8. FADEC
01 Examine the J4 connectors on both FADECs and the J0820/J0820 connectors between the W7 and W11/14 harnesses (located in the pylon). Are the connectors tight?
13 Tighten the connectors (Ref. 70-00-00-910-804 MM).
-No
| Yes 02 Examine the aircraft P0 and Pamb static lines for blockage or water contamination. Is foreign material present?
14 Remove the foreign material or drain the -Yes water from the static line(s) (Ref. 34-13-00/201 AMM).
| No 03 Supply electrical power to the aircraft. Access FADEC discrete label 357 from the CMC for both FADECs (Ref. Introduction). Does P0ADCF (bit 29) = 1?
-Yes
15 Do the troubleshooting for P0ADCF (bit 29) = 1 (Ref. 75-43-00-810-805).
| No 04 Go to Block 05
Maintenance Message: LT-ENG1/ENG2 PR/TMP DATA SYS R EFFECTIVITY:FADEC SOFTWARE VER. B5.1.1
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05 Does T25DIF (bit 20) = 1?
-Yes
16 Do the troubleshooting for T25DIF (bit 20) = 1 (Ref. 75-41-00-810-802).
-Yes
17 Do the troubleshooting for P25DIF (bit 27) =1 (Ref. 75-43-00-810-802).
-Yes
18 Do the troubleshooting for P0SDIF (bit 21) = 1 (Ref. 75-43-00-810-804).
| No 06 Does P25DIF (bit 21) = 1? | No 07 Does P0SDIF (bit 27) = 1? | No R
08 Access FADEC descrete label 353 from the 19 Do the troubleshooting for T25FLT (bit 16) CMC for both FADECs. Does T25FLT (bit 16) = -Yes = 1 (Ref. 75-41-00-810-801-A01). 1? | No
R
09 Does P25FLT (bit 17) = 1?
-Yes
20 Do the troubleshooting for P25FLT (bit 17) = 1 (Ref. 75-43-00-810-801-A01).
-Yes
21 Do the troubleshooting for P0SFT (bit 28) = 1 (Ref. 75-43-00-810-803).
| No 10 Does P0SFT (bit 28) = 1? | No 11 Go to Block 12
Maintenance Message: LT-ENG1/ENG2 PR/TMP DATA SYS R EFFECTIVITY:FADEC SOFTWARE VER. B5.1.1
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12 Operate the engine to the maximum thrust practical and do a normal shutdown (Ref. AMM). Do not remove electrical power from FADECs. Do this procedure again starting at block 01. Did any FADEC discrete label = 1?
-Yes
22 Do the troubleshooting for the FADEC discrete that = 1.
| No |
23 Examine the harness connectors at the FADEC J4 receptacle and the W11/14 harness at the P0, P2.5, and T2.5 sensors for looseness, corrosion, or damage. Tighten, clean, or repair the harness/connector as necessary (Ref. 70-00-00-910-804 MM) (Ref. 20-50-00 WM).
Maintenance Message: LT-ENG1/ENG2 PR/TMP DATA SYS R EFFECTIVITY:FADEC SOFTWARE VER. B5.1.1
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Maintenance Message: LT-ENG1/ENG2 PR/TMP DATA SYS DESCRIPTION: This message occurs when either of the following conditions occur: the signal received by the FADEC from either the T2.5, P2.5, or P0 sensor is not within limits, or if the P0 sensor signal received by this FADEC is different from that received by the other FADEC, or the ambient pressure signal received from the P0 sensor for this FADEC is different from the ambient pressure value received from the air data computer (ADC) for this channel. NOTE: If this message continues to occur without a fault found, look at the maintenance page of the central maintenance computer (CMC) for the maintenance message "ENG1/ENG2 LT FAULT" and "LT-ENG1/ENG2 PR/TMP DATA SYS" after subsequent flights.
POSSIBLE CAUSES: 1. Loose connectors 2. Foreign material in the aircraft P0/Pamb sensor lines 3. P0 Sensor System failure 4. T2.5 Sensor System failure 5. P2.5 Sensor System failure 6. Harness 7. ADC 8. FADEC
01 Examine the J4 connectors on both FADECs and the J0820/J0820 connectors between the W7 and W11/14 harnesses (located in the pylon). Are the connectors tight?
10 Tighten the connectors (Ref. 70-00-00-910-804 MM).
-No
| Yes 02 Examine the aircraft P0 and Pamb static lines for blockage or water contamination. Is foreign material present?
11 Remove the foreign material or drain the -Yes water from the static line(s) (Ref. 34-13-00/201 AMM).
| No 03 Supply electrical power to the aircraft. Access FADEC discrete label 357 from the CMC for both FADECs (Ref. Introduction). Does P0ADCF (bit 29) = 1?
-Yes
12 Do the troubleshooting for P0ADCF (bit 29) = 1 (Ref. 75-43-00-810-805).
| No 04 Go to Block 05.
Maintenance Message: LT-ENG1/ENG2 PR/TMP DATA SYS EFFECTIVITY:FADEC SOFTWARE VER. B7.5 OR LATER
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05 Does P0SDIF (bit 27) = 1?
-Yes
13 Do the troubleshooting for P0SDIF (bit 21) = 1 (Ref. 75-43-00-810-804).
| No 06 Access FADEC descrete label 353 from the 14 Do the troubleshooting for T25NOK (bit 16) CMC for both FADECs. Does T25NOK (bit 16) -Yes = 1 (Ref. 75-41-00-810-801-B01). = 1? | No 07 Does P25NOK (bit 17) = 1?
-Yes
15 Do the troubleshooting for P25NOK (bit 17) = 1 (Ref. 75-43-00-810-801-B01).
-Yes
16 Do the troubleshooting for P0SFT (bit 28) = 1 (Ref. 75-43-00-810-803).
| No 08 Does P0SFT (bit 28) = 1? | No 09 Operate the engine to the maximum thrust practical and do a normal shutdown (Ref. AMM). Do not remove electrical power from FADECs. Do this procedure again starting at block 01. Did any FADEC discrete label = 1?
-Yes
17 Do the troubleshooting for the FADEC discrete that = 1.
| No |
18 Examine the harness connectors at the FADEC J4 receptacle and the W11/14 harness at the P0, P2.5, and T2.5 sensors for looseness, corrosion, or damage. Tighten, clean, or repair the harness/connector as necessary (Ref. 70-00-00-910-804 MM) (Ref. 20-50-00 WM).
Maintenance Message: LT-ENG1/ENG2 PR/TMP DATA SYS EFFECTIVITY:FADEC SOFTWARE VER. B7.5 OR LATER
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Maintenance Message: ND-ENG1/ENG2 P0 SYS (set by FADEC Discrete: P0BLF (bit 24) / (352/AILRUZ) = 1) DESCRIPTION: This message occurs when this FADEC has detected a P0 sensor fault (label 353, bit 28) and, either a P0 sensor fault has been detected in the other FADEC or a cross-channel data link fault has been detected.
POSSIBLE CAUSES: 1. Foreign material in the aircraft P0 sensor line 2. Leakage in the P0 sensor line / aircraft cabin outflow valves 3. P0 sensor 4. Harness 5. FADEC
R R R R
01 Examine the aircraft P0 static line for blockage or water contamination (Ref. 75-43-00-810-801 EMB FIM). Is foreign material present?
06 Remove the foreign material or drain the water from the static line (Ref. 34-13-00/201 -Yes AMM).
| No R R R
02 Carry out a leak check of the aircraft P0 static line (Ref. 21-31-00-700-806 AMM or 75-43-00-810-801 EMB FIM). Is any leakage found?
07 Repair any P0 line leaks. -Yes
| No 03 Supply electrical power to the aircraft. Access FADEC discrete label 354 from the central maintenance computer (CMC) for both FADECs (Ref. Introduction). Does XTLKFT (bit 11) = 1 for either FADEC?
-Yes
08 Do the troubleshooting for XTLKFT (bit 11) (Ref. 77-40-00-810-803) and do block 05.
| No 04 Go to block 05
Maintenance Message: ND-ENG1/ENG2 P0 SYS EFFECTIVITY:ALL
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05 Access FADEC discrete label 353 from the 09 Do the troubleshooting for FADEC discrete (CMC) for both FADECs (Ref. Introduction). -Yes P0SFT (bit 28) (Ref. 75-43-00-810-803). Does P0SFT (bit 28) = 1 for either FADEC? | No |
10 Examine all the harness connectors between the P0 sensor and the FADEC J4 receptacle (W7 harness) for looseness, corrosion, contamination or damage. Tighten, clean or repair the harness as necessary (Ref. 70-00-00-910-804 MM).
Maintenance Message: ND-ENG1/ENG2 P0 SYS EFFECTIVITY:ALL
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FADEC Discrete: P25BLF (bit 23) / (352/AILRU2) = 1 DESCRIPTION: This discrete is set when this FADEC has detected a P2.5 sensor fault (label 353, bit 17) and, either a P2.5 sensor fault has been detected in the other FADEC or a cross-channel data link fault has been detected.
POSSIBLE CAUSES: 1. P2.5 sensor port blockage 2. P2.5 sensor 3. Harness 4. FADEC
01 Supply electrical power to the aircraft. 04 Do the troubleshooting for XTLKFT (bit 11). Access FADEC discrete label 354 from the Go to block 02 (Ref. 77-40-00-810-803). central maintenance computer (CMC) for both -Yes FADECs (Ref. Introduction). Does XTLKFT (bit 11) = 1 for either FADEC? | No 02 Access FADEC discrete label 353 from the from the CMC for both FADECs (Ref. Introduction). Does P25FLT (bit 17) = 1 for either FADEC?
05 Examine all the harness connectors between the P2.5 sensor and the FADEC J4 receptacle (W7 harness) for looseness, corrosion, contamination, or damage (Ref. -No FIG. 301/TASK 75-43-00-990-801/FIG. 302/TASK 75-43-00-990-802). Tighten, clean, or repair the harness as necessary (Ref. 70-00-00-910-804 MM).
| Yes 03 Using a borescope, examine the P2.5 air sensing tip, located at the 12 o'clock position on the fan frame for obstructions and damage. Is the P2.5 air sensing tip or passage obstructed or damaged?
06 Clean the P2.5 air sensing tip and passage or replace the damaged air sensing tip as -Yes necessary.
| No |
R
07 Do the troubleshooting for FADEC discrete P25FLT (bit 17) = 1 (Ref. 75-43-00-810-801-A01).
FADEC Discrete: P25BLF (bit 23) / (352/AILRU2) = 1 R EFFECTIVITY:FADEC SOFTWARE VER. B5.1.1
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FADEC Discrete: P25DCF (bit 23) / (352/AILRU2) = 1 DESCRIPTION: This discrete is set when this FADEC has detected a confirmed dual P2.5 sensor fault (label 353, bit 17).
POSSIBLE CAUSES: 1. P2.5 sensor port blockage 2. P2.5 sensor 3. Harness 4. FADEC
01 Supply electrical power to the aircraft. Access FADEC discrete label 353 from the from the CMC for both FADECs (Ref. Introduction). Does P25NOK (bit 17) = 1 for either FADEC?
03 Examine all the harness connectors between the P2.5 sensor and the FADEC J4 receptacle (W7 harness) for looseness, corrosion, contamination, or damage (Ref. FIG. -No 301/TASK 75-43-00-990-801/FIG. 302/TASK 75-43-00-990-802). Tighten, clean, or repair the harness as necessary (Ref. 70-00-00-910-804 MM).
| Yes 02 Using a borescope, examine the P2.5 air sensing tip, located at the 12 o'clock position on the fan frame for obstructions and damage. Is the P2.5 air sensing tip or passage obstructed or damaged?
04 Clean the P2.5 air sensing tip and passage or replace the damaged air sensing tip as -Yes necessary.
| No | 05 Do the troubleshooting for FADEC discrete P25NOK (bit 17) = 1 (Ref. 75-43-00-810-801-B01).
FADEC Discrete: P25DCF (bit 23) / (352/AILRU2) = 1 EFFECTIVITY:FADEC SOFTWARE VER. B7.5 OR LATER
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P2.5 Sensor / FADEC Interface Diagram FIG. 301/TASK 75-43-00-990-801
R EFFECTIVITY:ALL
75−43−TASK SUPPORT Page 301 Aug 15/04
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Engine Wiring Diagram FIG. 302/TASK 75-43-00-990-802
R EFFECTIVITY:ALL
75−43−TASK SUPPORT Page 302 Aug 15/04
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P0 Sensor / FADEC Interface Diagram FIG. 303/TASK 75-43-00-990-803
R EFFECTIVITY:ALL
75−43−TASK SUPPORT Page 303/304 Aug 15/04
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CHAPTER 76 LIST OF EFFECTIVE PAGES
CHAPTER SECTION OTHER SUBJECT PAGE IDENT DATE 76 R Contents 1/ Jul.20/15 2 00-00 101/ Feb.15/03 102 11-00 201 Aug.15/04 11-00 202 Aug.15/04 11-00 201 Aug.15/04 11-00 202 Aug.15/04 11-00 201/ Aug.15/04 202 11-00 201/ Feb.15/03 202 11-00 201/ Aug.15/04 202 11-00 201/ Feb.15/03 202 11-00 201/ Feb.15/03 202 R 11-00 201/ Jul.20/15 202 R 11-00 201/ Jul.20/15 202 11-00 201/ Feb.15/03 202 11-00 301 Aug.15/04 11-00 302 Aug.15/04 --------------- END ---------------
CHAPTER SECTION SUBJECT PAGE 76
OTHER IDENT
DATE
C=CONFIG B=BREAKOUT
CHAPTER SECTION SUBJECT PAGE 76
OTHER IDENT
DATE
LIST OF EFFECTIVE PAGES-76 Page 1/2 Oct 20/16
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CHAPTER 76 TABLE OF CONTENTS
R R R R
SUBJECT
CH-SE-SUB
ENGINE CONTROLS FAULT CODE INDEX
76-00-00
ENGINE CONTROL FADEC Discrete: TLADIF (bit 16) / (265 / AIDIF 2) = 1 FADEC Discrete: WOWFT (bit 19) / (351 / AILRU1) = 1 FADEC Discrete: WOWDF (bit 19) / (264 / AIDIF1) = 1 EICAS Message: E1/E2 TLA FAIL FADEC Discrete: TLAFIX (bit 16) / (355 / SFLTS1) = 1 FADEC Discrete: TLAFLT (bit 16) / (352 / AILRU2) = 1 Maintenance Message: LT-ENG A/G LGDAL SYS Maintenance Message: ND-ENG1/ENG2 A/G SYS DIFF Maintenance Message: LT-ENG1/ENG2 TLA SYS Maintenance Message: ST-ENG1/ENG2 TLA SYS Maintenance Message: ND-ENG1/ENG2 TLA SYS DIFF Task Support
76-11-00
PAGE
EFFECTIVITY
101
201 201 201 201 201 201 201 201 201 201 301
76−CONTENTS Page 1/2 Jul 20/15
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FAULT CODE INDEX FAULT CODE
FAULT DESCRIPTION
761M93 00
E1 TLA FAIL (Caution)
76-11-00-810-806
761M94 00
E2 TLA FAIL (Caution)
76-11-00-810-806
EFFECTIVITY:ALL
MAINT. MESSAGE
GO TO FIM TASK
76−FAULT CODE INDEX Page 101/102 Feb 15/03
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FADEC Discrete: TLADIF (bit 16) / (265 / AIDIF 2) = 1 DESCRIPTION: This discrete is set to 1 (fault sensed) when the signal received from the thrust lever resolver by this FADEC is different (more than 2.5 degrees) from that received by the other FADEC.
POSSIBLE CAUSES: 1. Resolver 2. Harness 3. FADEC
01 Examine all of the harness connectors between the thrust lever resolver and the FADEC J2 receptacles for damage, corrosion, or contamination. Are the connectors contaminated or damaged?
-Yes
06 Clean or repair the harness connectors (Ref. 20-50-00 WM).
| No 02 Supply electrical power to the aircraft. Access the FADEC analog label (Ref. Introduction) from the central maintenance computer (CMC) for both FADECs and record -Yes the TLA values. Interchange the position of the harness connectors at the thrust lever resolver (Ref. 76-12-01/501 AMM). Do the TLA values recorded move to the opposite FADEC?
07 Replace the thrust lever resolver. Rotate the FADEC reset/select switch to the RESET position to remove the fault (TLADIF (bit 16) = 0).
| No
R R
03 Do a test for continuity/resistance, internal shorts, and shorts to ground on the aircraft harnesses between the FADECs and the resolver (Ref. FIG. 301/TASK 76-11-00-990-801) (Ref. 76-12-55/76-12-56 WM). Do the harnesses test satisfactorily?
08 Replace the harness that has the fault (Ref. 76-12-55/76-12-56 WM). Rotate the FADEC reset/select switch to the RESET -No position to remove the fault (TLADIF(bit 16) = 0).
| Yes 04 Go to Block 05
FADEC Discrete: TLADIF (bit 16) / (265 / AIDIF 2) = 1 EFFECTIVITY:ALL
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05 Replace FADEC A (Ref. 73-25-10-000-801/ 09 Remove the FADEC with the fault from 73-25-10-400-801 MM). Does TLADIF (bit 16) -Yes service. = 0? | No |
10 Replace FADEC B (Ref. 73-25-10-000-801/ 73-25-10-400-801 MM).
FADEC Discrete: TLADIF (bit 16) / (265 / AIDIF 2) = 1 EFFECTIVITY:ALL
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FADEC Discrete: WOWFT (bit 19) / (351 / AILRU1) = 1 DESCRIPTION: The FADEC does a test of the air/ground circuit. This discrete is set to 1 (fault sensed) when an open or shorted circuit is detected.
POSSIBLE CAUSES: 1. Aircraft circuit fault 2. FADEC
01 Disconnect the harness from the FADEC 07 Clean or repair the connector (Ref. J2 receptacle. Examine the harness connector 20-50-00 WM). Rotate the FADEC reset/select -Yes for damage, corrosion, or contamination. Is the switch to the RESET position to remove the connector contaminated or damaged? fault (WOWFT (bit 19) = 0). | No
R R
02 Supply electrical power to the aircraft and do a test for voltage at pin S of the FADEC J2 receptacle (Ref. FIG. 302/TASK 76-11-00-990-802) (Ref. 76-12-52/76-12-53 WM). Is there 12-15 VDC measured?
-No
08 Replace the FADEC that has the fault (Ref. 73-25-10-000-801/73-25-10-400-801 MM).
| Yes
R R
03 Make sure the air/ground switch is in the GROUND position and do a test for continuity between pins S and n at the W1 harness connector (Ref. FIG. 302/TASK 76-11-00-990-802) (Ref. 76-12-52/76-12-53 WM). Is there continuity, with resistance less than 10 ohms?
09 Repair the aircraft circuit fault (Ref. 76-12-52/76-12-53 WM). Rotate the FADEC reset/select switch to the RESET position to -No remove the fault (WOWFT (bit 19) = 0).
| Yes 04 Go to Block 05
FADEC Discrete: WOWFT (bit 19) / (351 / AILRU1) = 1 EFFECTIVITY:ALL
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R
05 With the air/ground switch in the GROUND 10 Repair the aircraft circuit fault (Ref. position, do a test for continuity between 76-12-52/76-12-53 WM). Rotate the FADEC ground and pin S at the W1 harness connector -Yes reset/select switch to the RESET position to (Ref. FIG. 302/TASK 76-11-00-990-802) (Ref. remove the fault (WOWFT (bit 19) = 0). 76-12-52/76-12-53 WM). Is there continuity? | No
R R
06 Make sure the air/ground switch is in the AIR position and do a test for continuity between pins n and S at the W1 harness connector (Ref. FIG. 302/TASK 76-11-00-990-802) (Ref. 76-12-52/76-12-53 WM). Is there continuity, with resistance between 9.5K and 10.5K ohms?
11 Repair the aircraft circuit fault (Ref. 76-12-52/76-12-53 WM). Rotate the FADEC reset/select switch to the RESET position to -No remove the fault (WOWFT (bit 19) = 0).
| Yes |
12 Replace the FADEC that has the fault (Ref. 73-25-10-000-801/73-25-10-400-801 MM).
FADEC Discrete: WOWFT (bit 19) / (351 / AILRU1) = 1 EFFECTIVITY:ALL
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FADEC Discrete: WOWDF (bit 19) / (264 / AIDIF1) = 1 DESCRIPTION: The FADECs do a lane difference test of the two air/ground relay circuits. This fault occurs when the condition of the circuits (AIR/GROUND) sensed by FADEC A and B is not the same. The FADECs will not do this test if one of the two circuits has a fault.
POSSIBLE CAUSES: 1. Aircraft circuit fault 2. FADEC
01 Disconnect the harness from the J2 receptacles on both FADECs. Examine the harness connectors for damage, corrosion, or contamination. Are the connectors contaminated or damaged?
04 Clean or repair the connector (Ref. 20-50-00 WM). Rotate the FADEC reset/select -Yes switch to the RESET position to remove the fault (WOWDIF (bit 19) = 0).
| No
R R
02 Disconnect the harness from the switch 05 Repair the aircraft harness fault (Ref. and do a test for continuity between pins S and 76-12-52/76-12-53 WM). Rotate the FADEC n at both W1 harness connectors (Ref. FIG. -Yes reset/ select switch to the RESET position to 302/TASK 76-11-00-990-802) (Ref. remove the fault (WOWDIF (bit 19) = 0). 76-12-52/76-12-53 WM). Is there continuity? | No 03 Supply electrical power to the aircraft. Access FADEC discrete label 264 from the central maintenance computer (CMC) for both FADECs (Ref. Introduction). Does WOWDIF (bit 19) = 1) for both FADECs?
06 Repair the aircraft circuit fault (Ref. 76-12-52/76-12-53 WM). Rotate the FADEC -Yes reset/select switch to the RESET position to remove the fault (WOWDIF (bit 19) = 0).
| No |
07 Replace the FADEC that shows WOWDIF (bit 19) = 1 (Ref. 73-25-10-000-801/73-25-10-400-801 MM).
FADEC Discrete: WOWDF (bit 19) / (264 / AIDIF1) = 1 EFFECTIVITY:ALL
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EICAS Message: E1/E2 TLA FAIL FADEC Discrete: TLAFIX (bit 16) / (355 / SFLTS1) = 1 DESCRIPTION: This discrete is set to 1 (fault sensed) when there is not a valid thrust-lever-angle (TLA) signal to this FADEC from either of the two thrust lever resolvers for this engine (one per FADEC). The FADEC will set the engine thrust at a level equal to the last valid TLA signal.
POSSIBLE CAUSES: 1. Thrust lever resolver / quadrant fault 2. Aircraft harness 3. FADEC
01 Supply electrical power to the aircraft. Access FADEC discrete label 352 from the CMC for both FADECs (Ref. Introduction). Is TLAFLT (bit 16) = 1 for both FADECs?
-Yes
03 Do the troubleshooting for FADEC discrete TLAFLT (bit 16) = 1 (Ref. 76-11-00-810-807).
| No 02 Access FADEC discrete label 354 from the 04 Do the troubleshooting for FADEC CMC for this FADEC. Is XTLKFT (bit 11) = 1 discretes XTLKFT (bit 11) = 1 (Ref. -Yes and does TLAFLT (bit 16) of label 352 = 1? 77-40-00-810-803) and TLAFLT (bit 16) = 1 (Ref. 76-11-00-810-807). | No |
05 Replace the FADEC (Ref. 73-25-10-000-801/73-25-10-400-801 MM) that shows TLAFIX (bit 18) of label 355 = 1.
EICAS Message: E1/E2 TLA FAIL FADEC Discrete: TLAFIX (bit 16) / (355 / SFLTS1) = 1 EFFECTIVITY:ALL
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FADEC Discrete: TLAFLT (bit 16) / (352 / AILRU2) = 1 DESCRIPTION: This message occurs when the signal received from the thrust lever resolver by this FADEC is not within the limits, or the excitation voltage provided to the resolver by the FADEC has failed.
POSSIBLE CAUSES: 1. Resolver 2. Harness 3. FADEC
01 Access FADEC discrete label 360 from the 04 Do the troubleshooting for TLAEXF (bit 22) CMC (Ref. Introduction). Does TLAEXF (bit -Yes = 1 (Ref. 73-25-00-810-827). 22) = 1? | No 02 Interchange the position of the FADECs 05 Replace the FADEC that has the fault (Ref. (Ref. 73-25-10-000-801/73-25-10-400-801 73-25-10-000-801/73-25-10-400-801 MM). MM). Rotate the FADEC reset/select switch to -Yes the RESET position. Does TLAFLT (bit 16) = 1 occur on the opposite channel? | No 03 Interchange the position of the harness connectors at the thrust lever resolver. Rotate the FADEC reset/select switch to the RESET position. Does TLAFLT (bit 16) = 1 occur on the opposite channel?
06 Replace the defective thrust lever resolver (Ref. 76-12-01/401 AMM). Rotate the FADEC -Yes reset/select switch to the RESET position to remove the fault (TLAFLT (bit 16) = 0).
| No |
R
07 Do a test for continuity/resistance, internal shorts, and shorts to ground on the aircraft harness between the FADEC and the resolver (Ref. FIG. 301/TASK 76-11-00-990-801) (Ref. 76-12-55/76-12-56 WM). Replace the harness that has the fault. Rotate the FADEC reset/select switch to the RESET position to remove the fault (TLAFLT (bit 16) = 0).
FADEC Discrete: TLAFLT (bit 16) / (352 / AILRU2) = 1 EFFECTIVITY:ALL
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Maintenance Message: LT-ENG A/G LGDAL SYS DESCRIPTION: This message occurs when the condition of the landing gear circuits (Down & Locked/Not Down & Locked) sensed by FADEC A and B is not the same, or when an open or shorted circuit in the air/ground switch circuit is detected.
POSSIBLE CAUSES: 1. Aircraft circuit fault 2. FADEC
01 Supply electrical power to the aircraft. Access FADEC discrete label 264 from the central maintenance computer (CMC) for both FADECs (Ref. Introduction). Does LGDLDF (bit 20) = 1?
-Yes
04 Do the troubleshooting for LGDLDF (bit 20) = 1 (Ref. 73-25-00-810-806).
| No 02 Access FADEC discrete label 351 from the 05 Do the troubleshooting for WOWFT (bit -Yes CMC. Does WOWFT (bit 19) = 1? 19) = 1 (Ref. 76-11-00-810-804). | No 03 Examine all of the harness connectors between the air/ground position relay, the landing gear down and locked position switch, and the FADEC for looseness, corrosion, contamination, or damage. Does an unsatisfactory condition exist?
-Yes
06 Tighten, clean, or repair the harness as necessary (Ref. 76-12-52/ 76-12-53 WM) (Ref. 70-00-00-910-804 MM).
| No |
07 Access the CMC for this message after subsequent flights. Do not remove electrical power from the FADECs. Repeat the procedure again.
Maintenance Message: LT-ENG A/G LGDAL SYS EFFECTIVITY:ALL
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Maintenance Message: ND-ENG1/ENG2 A/G SYS DIFF DESCRIPTION: This message occurs when the FADEC finds channel A and B air/ground switch circuit conditions are not the same (AIR/GROUND).
POSSIBLE CAUSES: 1. Aircraft circuit fault 2. Harness 3. FADEC
01 Supply electrical power to the aircraft. Access FADEC discrete label 264 from the central maintenance computer (CMC) for both FADECs (Ref. Introduction). Does WOWDF (bit 19) = 1?
-Yes
03 Do the troubleshooting for FADEC discrete WOWDF (bit 19) = 1 (Ref. 76-11-00-810-805).
| No 02 Examine all of the harness connectors between the air/ground position relay and the FADEC. Is a fault found ?
04 Tighten, clean, or repair them as necessary -Yes (Ref. 76-12-52/76-12-53 WM) (Ref. 70-00-00-910-804 MM).
| No |
05 Access the CMC after the next flight. Do not remove electrical power. Do the procedure again.
Maintenance Message: ND-ENG1/ENG2 A/G SYS DIFF EFFECTIVITY:ALL
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Maintenance Message: LT-ENG1/ENG2 TLA SYS DESCRIPTION: This message occurs when the signal received from the thrust lever resolver by this FADEC is not within limits.
POSSIBLE CAUSES: 1. Resolver 2. Harness 3. FADEC
01 Supply electrical power to the aircraft. Access FADEC discrete label 352 from the central maintenance computer (CMC) (Ref. Introduction). Does TLAFLT (bit 16) = 1?
-Yes
03 Do the troubleshooting for FADEC discrete TLAFLT (bit 16) = 1 (Ref. 76-11-00-810-807).
| No 02 Put the thrust lever in the MAX position for at least 4.0 seconds, and then put the thrust lever in the MAX REV position for at least 4.0 seconds. Return the thrust lever to the IDLE position. Does TLAFLT (bit 16) = 1?
-Yes
04 Do the troubleshooting for FADEC discrete TLAFLT (bit 16) = 1 (Ref. 76-11-00-810-807).
| No | 05 Examine all of the harness connectors between the thrust lever resolver and the FADEC J2 receptacle. Tighten, clean, or repair them as necessary (Ref. 20-50-00 WM) (Ref. 76-12-55/76-12-56 WM) (Ref. 70-00-00-910-804 MM).
Maintenance Message: LT-ENG1/ENG2 TLA SYS EFFECTIVITY:AIRCRAFT CMC SOFTWARE VERSION 15 OR EARLIER
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Maintenance Message: ST-ENG1/ENG2 TLA SYS DESCRIPTION: This message occurs when the signal received from the thrust lever resolver by this FADEC is not within limits.
POSSIBLE CAUSES: 1. Resolver 2. Harness 3. FADEC
01 Supply electrical power to the aircraft. Access FADEC discrete label 352 from the central maintenance computer (CMC) (Ref. Introduction). Does TLAFLT (bit 16) = 1?
-Yes
03 Do the troubleshooting for FADEC discrete TLAFLT (bit 16) = 1 (Ref. 76-11-00-810-807).
| No 02 Put the thrust lever in the MAX position for at least 4.0 seconds, and then put the thrust lever in the MAX REV position for at least 4.0 seconds. Return the thrust lever to the IDLE position. Does TLAFLT (bit 16) = 1?
-Yes
04 Do the troubleshooting for FADEC discrete TLAFLT (bit 16) = 1 (Ref. 76-11-00-810-807).
| No | 05 Examine all of the harness connectors between the thrust lever resolver and the FADEC J2 receptacle. Tighten, clean, or repair them as necessary (Ref. 20-50-00 WM) (Ref. 76-12-55/76-12-56 WM) (Ref. 70-00-00-910-804 MM).
Maintenance Message: ST-ENG1/ENG2 TLA SYS EFFECTIVITY:AIRCRAFT CMC SOFTWARE VERSION 16 OR LATER
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Maintenance Message: ND-ENG1/ENG2 TLA SYS DIFF DESCRIPTION: This message occurs when the signal received from the thrust lever resolver by this FADEC is different from the signal received by the other FADEC.
POSSIBLE CAUSES: 1. Resolver 2. Harness 3. FADEC
01 Supply electrical power to the aircraft. Access FADEC discrete label 265 from the central maintenance computer (CMC) (Ref. Introduction). Does TLADIF (bit 16) = 1?
-Yes
03 Do the troubleshooting for FADEC discrete TLADIF (bit 16) = 1 (Ref. 76-11-00-810-802).
| No 02 Put the thrust lever in the MAX position for at least 4.0 seconds, and then put the thrust lever in the MAX REV position for at least 4.0 seconds. Return the thrust lever to the IDLE position. Does TLADIF (bit 16) = 1?
-Yes
04 Do the troubleshooting for FADEC discrete TLADIF (bit 16) = 1 (Ref. 76-11-00-810-802).
| No |
05 Examine all of the harness connectors between the thrust lever resolver and the FADEC J2 receptacle. Tighten, clean, or repair them as necessary (Ref. 20-50-00 WM) (Ref. 76-12-55/76-12-56 WM) (Ref. 70-00-00-910-804 MM).
Maintenance Message: ND-ENG1/ENG2 TLA SYS DIFF EFFECTIVITY:ALL
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Thrust Level Resolver / FADEC Interface Diagram FIG. 301/TASK 76-11-00-990-801
R EFFECTIVITY:ALL
76−11−TASK SUPPORT Page 301 Aug 15/04
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Air/Ground Position Relay / FADEC Interface Diagram FIG. 302/TASK 76-11-00-990-802
R EFFECTIVITY:ALL
76−11−TASK SUPPORT Page 302 Aug 15/04
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CHAPTER 77 LIST OF EFFECTIVE PAGES
CHAPTER SECTION SUBJECT PAGE 77 Contents 1 Contents 2 Contents 3/ 4 00-00 101/ 102 11-00 201/ 202 11-00 201/ 202 11-00 201 11-00 202 11-00 201 11-00 202 11-00 201/ 202 11-00 201/ 202 11-00 201 11-00 202 11-00 201 11-00 202 11-00 201 11-00 202 11-00 201 11-00 202 11-00 201 11-00 202 11-00 201 11-00 202 11-00 201 11-00 202 11-00 203/ 204 11-00 201 11-00 202 11-00 201 11-00 202 11-00 201 11-00 202 11-00 203/ 204 11-00 201/ 202 11-00 201/ 202 11-00 201 11-00 202 11-00 201 11-00 202 11-00 201 11-00 202 11-00 201 11-00 202 11-00 201 11-00 202 11-00 203/ 204 11-00 301 11-00 302
OTHER IDENT
DATE Jul.20/11 Jul.20/11 Jul.20/11 Apr.15/06 Oct.20/15 Oct.20/15 Oct.20/15 Oct.20/15 Oct.20/15 Oct.20/15 Oct.20/15 Oct.20/15 Aug.15/04 Aug.15/04 Aug.15/04 Aug.15/04 Oct.20/15 Oct.20/15 Oct.20/15 Oct.20/15 Oct.20/15 Oct.20/15 Oct.20/15 Oct.20/15 Oct.20/15 Oct.20/15 Oct.20/15 Oct.20/15 Oct.20/15 Oct.20/15 Oct.20/15 Oct.20/15 Oct.20/15 Oct.20/15 Feb.15/03 Feb.15/03 Aug.15/04 Aug.15/04 Aug.15/04 Aug.15/04 Mar.15/03 Mar.15/03 Mar.15/03 Mar.15/03 Oct.20/15 R Oct.20/15 R Oct.20/15 R R Aug.15/04 Aug.15/04
CHAPTER SECTION SUBJECT PAGE 77 11-00 303 11-00 304 21-00 201/ 202 21-00 201/ 202 21-00 201/ 202 21-00 201 21-00 202 21-00 203/ 204 21-00 201 21-00 202 21-00 201 21-00 202 21-00 201 21-00 202 21-00 203 21-00 204 21-00 205/ 206 21-00 201/ 202 21-00 201 21-00 202 21-00 203/ 204 21-00 201 21-00 202 21-00 203/ 204 21-00 301 21-00 302 21-00 303/ 304 40-00 201/ 202 40-00 201/ 202 40-00 201/ 202 40-00 201/ 202 40-00 201/ 202 40-00 201 40-00 202 40-00 301 40-00 302 41-00 201 41-00 202 41-00 203/ 204 41-00 201 41-00 202 41-00 203 41-00 204 41-00 201 41-00 202
OTHER IDENT
DATE Aug.15/04 Aug.15/04 Aug.15/04 Oct.20/15
CHAPTER SECTION OTHER SUBJECT PAGE IDENT DATE 77 41-00 203/ Jul.20/11 204 41-00 301/ Aug.15/04 302 --------------- END ---------------
Oct.20/15 Oct.20/15 Oct.20/15 Oct.20/15 Oct.20/15 Oct.20/15 Oct.20/15 Oct.20/15 Jul.20/11 Jul.20/11 Jul.20/11 Jul.20/11 Jul.20/11 Aug.15/04 Oct.20/15 Oct.20/15 Oct.20/15 Oct.20/15 Oct.20/15 Oct.20/15 Aug.15/04 Aug.15/04 Aug.15/04 Aug.15/04 Aug.15/04 Aug.15/04 Feb.15/03 Feb.15/03 Jul.20/10 Jul.20/10 Aug.15/04 Aug.15/04 Jul.20/13 Jul.20/13 Jul.20/13 Apr.20/16 Apr.20/16 Apr.20/16 Apr.20/16 Jul.20/11 Jul.20/11
C=CONFIG B=BREAKOUT
LIST OF EFFECTIVE PAGES-77 Page 1/2 Oct 20/16
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CHAPTER 77 TABLE OF CONTENTS
SUBJECT
CH-SE-SUB
ENGINE INDICATING FAULT CODE INDEX
77-00-00
ENGINE INDICATING - SPEED 77-11-00 FADEC Discrete: N1PSFT (bit 11) / (353 / EILRU) = 1 FADEC Discrete: N1SSFT (bit 12) / (353 / EILRU) = 1 FADEC Discrete: N1PDIF (bit 11) and N1PSTD (bit 13) (357 / EIDIF) = 1 FADEC Discrete: N1SDIF (bit 12) and N1PSOD (bit 18) (357 / EIDIF) = 1 FADEC Discrete: N2PSFT (bit 13) / (353 / EILRU) = 1 FADEC Discrete: N2PDIF (bit 15) and N2PSTD (bit 17) / (357 / EIDIF) = 1 Observed Fault: Overspeed (N1) (displayed on EICAS and/or CMC Exceedance) Observed Fault: Overspeed (N2) (displayed on EICAS and/or CMC Exceedance) FADEC Discrete: N1PDIF (bit 11) / (357 / EIDIF) = 1 FADEC Discrete: N1PSTD (bit 13) / (357 / EIDIF) = 1 FADEC Discrete: N1SDIF (bit 12) / (357 / EIDIF) = 1 FADEC Discrete: N1PSOD (bit 14) / (357 / EIDIF) = 1 FADEC Discrete: N2PDIF (bit 15) / (357 / EIDIF) = 1 FADEC Discrete: N2PSTD (bit 17) / (357 / EIDIF) = 1 FADEC Discrete: N2SDIF (bit 16) / (357 / EIDIF) = 1 FADEC Discrete: N2PSOD (bit 18) / (357 / EIDIF) = 1 FADEC Discrete: N1LRMD (bit 26) / (355 / SFLTS1) = 1 Maintenance Message: ND - ENG1 / ENG2 OVSPD PROT SYS Maintenance Message: LT-ENG1/ENG2 N1 SYS Maintenance Message: LT-ENG1/ENG2 N2 SYS
PAGE
EFFECTIVITY
101
201 201 201 201 201 201 201 201 201 201 201 201 201 201 201 201 201 201 201 201
77−CONTENTS Page 1 Jul 20/11
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SUBJECT
CH-SE-SUB
FADEC Discrete: LN1OSP (bit 21) / (356 / SFLTS2) = 1 FADEC Discrete: LN2OSP (bit 22) / (356 / SFLTS2) = 1 FADEC Discrete: N2SSFT (bit 14) / (353 / EILRU) = 1 Task Support
(354 /
201 201 301
201 201 201 201 201 201 201 201 201 201 301
77-40-00 201
(354 /
201
(360 /
201
(360 /
201
(360 /
201 201 301
COMM A/B
ENGINE INDCIATING - VIBRATION SENSORS
EFFECTIVITY
201
ENGINE INDICATING - TEMPERATURE 77-21-00 Maintenance Message: ENG1/ENG2 ITT SENSOR FAIL or ST-ENG1/ENG2 ITT SYS FADEC Discrete: ITTFLT (bit 15) / (353 / EILRU) = 1 FADEC Discrete: TRMFMD (bit 27) / (353 / EILRU) = 1 FADEC Discrete: ITTDIF (bit 19) / (357 / EIDIF) = 1 FADEC Discrete: TRMDMX (bit 25) / (357 / EIDIF) = 1 FADEC Discrete: TRMEDF (bit 26) / (357 / EIDIF) = 1 Observed Fault: Sudden Increase in ITT Maintenance Message: LT-ENG1/ENG2 ITT TRIM SYS Observed Fault: ITT indication difference (split) between left and right engines (static) Observed Fault: ITT Fluctuations Task Support ENGINE INDICATING - VIBRATION FADEC Discrete: NCNCFT (bit 12) / CFPLRU) = 1 FADEC Discrete: XTLKFT (bit 11) / CFPLRU) = 1 FADEC Discrete: SOIFLT (bit 11) / FADLRU) = 1 FADEC Discrete: CAPOFT (bit 12) / FADLRU) = 1 FADEC Discrete: TLICFT (bit 13) / FADLRU) = 1 Maintenance Message: ND-ENG1/ENG2 Task Support
PAGE
77-41-00
77−CONTENTS Page 2 Jul 20/11
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SUBJECT
R R R R
Observed Fault: LP Rotor Vibration High (displayed on EICAS and/or CMC Exceedance or Aircrew felt) Observed Fault: HP Rotor Vibration High (displayed on EICAS and/or CMC Exceedance) Observed Fault: LP or HP Rotor Vibration Level of 0.00/unreadable (displayed on EICAS or CMC download) Task Support
CH-SE-SUB
PAGE
EFFECTIVITY
201 201 201 301
77−CONTENTS Page 3/4 Jul 20/11
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FAULT CODE INDEX FAULT CODE
FAULT DESCRIPTION
7710O1 00
Overspeed (N1)
77-11-00-810-809
7710O2 00
Overspeed (N2)
77-11-00-810-810
Sudden Increase in ITT
77-21-00-810-807
772M01 00
E1 ITT LIMIT FAIL (Caution)
77-21-00-810-808
772M02 00
E2 ITT LIMIT FAIL (Caution)
77-21-00-810-808
7721O1 00
ITT indication difference (split) between left and right engines (static)
77-21-00-810-810
7721O2 00
ITT Fluctuations
77-21-00-810-811
7740O1 00
Vibration High (LP Rotor)
77-41-00-810-801
7740O2 00
Vibration High (HP Rotor)
77-41-00-810-802
R 7720O1 00
EFFECTIVITY:ALL
MAINT. MESSAGE
GO TO FIM TASK
77−FAULT CODE INDEX Page 101/102 Apr 15/06
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FADEC Discrete: N1PSFT (bit 11) / (353 / EILRU) = 1 DESCRIPTION:
R R
The FADEC monitors the signal received from its primary fan speed (N1) sensor and does a test for circuit continuity. This discrete is set to 1 (fault sensed) when the signal is not within the limits, or an open circuit is found (removing electrical power from the FADEC is necessary to remove a fault set by failure of the continuity test) (Ref. FIG. 301/TASK 77-11-00-990-801/FIG. 303/TASK 77-11-00-990-803). If available, the AE 3007 Engine Signal Test Set and Cable (CDS P/N 86690158) (Ref. TASK 73-25-10-700-801, MM) can be used for continuity/resistance testing of a suspected faulty FADEC/engine interconnect (W7) harness.
POSSIBLE CAUSES: 1. Fan speed (N1) sensor 2. Harness 3. FADEC
01 Do a test for continuity/resistance (1 ohm max./harness), internal shorts, and shorts to ground (1,000 ohms min.) on the FADEC A/B (W11/14) and FADEC/engine interconnect (W7) harnesses (Ref. FIG. 301/TASK 77-11-00-990-801/FIG. 303/TASK 77-11-00-990-803) (Ref. 77-11-51 WM). Do the harnesses test satisfactorily?
04 Replace the harness that has the fault (Ref. 76-00-00 MM) (Ref. AMM). -No
| Yes 02 Do a test for continuity/resistance, internal shorts, and shorts to ground on the fan speed (N1) sensor (Ref. 77-11-51 WM). Maximum resistance between pins A and B is 500 ohms. Does the sensor test satisfactorily?
-No
05 Replace the fan speed (N1) sensor (Ref. 77-11-15-000-801/77-11-15-400-801 MM).
| Yes 03 Interchange the position of the FADECs (Ref. 73-25-10-000-801/73-25-10-400-801 MM). Turn electrical power to the FADEC OFF, and then ON. Operate the engine as necessary (Ref. AMM). Does the fault move to the opposite channel?
06 Replace the fan speed (N1) sensor (Ref. 77-11-15-000-801/77-11-15-400-801 MM). -No
| Yes |
07 Replace the FADEC that has the fault (Ref. 73-25-10-000-801/73-25-10-400-801 MM). FADEC Discrete: N1PSFT (bit 11) / (353 / EILRU) = 1
EFFECTIVITY:ALL
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FADEC Discrete: N1SSFT (bit 12) / (353 / EILRU) = 1 DESCRIPTION:
R R
The FADEC monitors the signal received from its primary fan speed (N1) sensor and does a test for circuit continuity. This discrete is set to 1 (fault sensed) when the signal is not within the limits, or an open circuit is found (removing electrical power from the FADEC is necessary to remove a fault set by failure of the continuity test) (Ref. FIG. 301/TASK 77-11-00-990-801/FIG. 303/TASK 77-11-00-990-803). If available, the AE 3007 Engine Signal Test Set and Cable (CDS P/N 86690158) (Ref. TASK 73-25-10-700-801, MM) can be used for continuity/resistance testing of a suspected faulty FADEC/engine interconnect (W7) harness.
POSSIBLE CAUSES: 1. Fan speed (N1) sensor 2. Harness 3. FADEC
01 Do a test for continuity/resistance (1 ohm max./harness), internal shorts, and shorts to ground (1,000 ohms min.) on the FADEC A/B (W11/14) and FADEC/engine interconnect (W7) harnesses (Ref. FIG. 301/TASK 77-11-00-990-801/FIG. 303/TASK 77-11-00-990-803) (Ref. 77-11-51 WM). Do the harnesses test satisfactorily?
04 Replace the harness that has the fault (Ref. 76-00-00 MM) (Ref. AMM). -No
| Yes 02 Do a test for continuity/resistance, internal shorts, and shorts to ground on the fan speed (N1) sensor (Ref. 77-11-15-700-801 MM). Maximum resistance between pins A and B is 500 ohms. Does the sensor test satisfactorily?
-No
05 Replace the fan speed (N1) sensor (Ref. 77-11-15-000-801/77-11-15-400-801 MM).
| Yes 03 Interchange the position of the FADECs (Ref. 73-25-10-000-801/73-25-10-400-801 MM). Turn electrical power to the FADEC OFF, and then ON. Operate the engine as necessary (Ref. AMM). Does the fault move to the opposite channel?
06 Replace the fan speed (N1) sensor (Ref. 77-11-15-000-801/77-11-15-400-801 MM). -No
| Yes |
07 Replace the FADEC that has the fault (Ref. 73-25-10-000-801/73-25-10-400-801 MM). FADEC Discrete: N1SSFT (bit 12) / (353 / EILRU) = 1
EFFECTIVITY:ALL
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FADEC Discrete: N1PDIF (bit 11) and N1PSTD (bit 13) (357 / EIDIF) = 1 DESCRIPTION:
R R
The FADECs compare the signals received from their primary fan speed (N1) sensors (N1 primary sensors). The FADECs also compare their N1 primary and N1 secondary signals. These two discretes are set to 1 (fault sensed) when the N1 signals being compared are different, by more than 35 RPM. This is an indication of a fault with the N1 primary circuit for this FADEC. The lane difference tests are not done when either a sensor or the cross-channel data link (W4 harness) have failed. If available, the AE 3007 Engine Signal Test Set and Cable (CDS P/N 86690158) (Ref. TASK 73-25-10-700-801, MM) can be used for continuity/resistance testing of a suspected faulty FADEC/engine interconnect (W7) harness.
POSSIBLE CAUSES: 1. Harness 2. Fan speed (N1) sensor 3. FADEC
01 Examine the harness connectors between this FADEC and the fan speed (N1) sensor for this channel, for corrosion, contamination, or damage. Are the connectors dirty or damaged?
06 Clean the connectors (Ref. 70-00-00-910-804 MM) or replace the harness -Yes (Ref. 76-00-00 MM) (Ref. AMM).
| No 02 Do a test for continuity/resistance (1 ohm max./harness), internal shorts, and shorts to ground (1,000 ohms min.) on the FADEC A/B (W11/14) and FADEC/engine interconnect (W7) harnesses (N1 primary circuit) (Ref. FIG. 301/TASK 77-11-00-990-801/FIG. 303/TASK 77-11-00-990-803) (Ref. 77-11-51 WM). Do the harnesses test satisfactorily?
07 Replace the harness that has the fault (Ref. 76-00-00 MM) (Ref. AMM). -No
| Yes 03 Do a test for continuity/resistance, internal shorts, and shorts to ground on the fan speed (N1) sensor (primary circuit) (Ref. 77-11-15-700-801 MM). Maximum resistance between pins A and B is 500 ohms. Does the sensor test satisfactorily?
08 Replace the fan speed (N1) sensor (Ref. 77-11-15-000-801/77-11-15-400-801 MM). -No
| Yes 04 Go to Block 05 FADEC Discrete: N1PDIF (bit 11) and N1PSTD (bit 13) (357 / EIDIF) = 1 EFFECTIVITY:ALL
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05 Interchange the position of the FADECs (Ref. 73-25-10-000-801/73-25-10-400-801 MM). Turn electrical power to the FADEC OFF, and then ON. Operate the engine as necessary (Ref. AMM). Does the fault move to the opposite channel?
09 Replace the fan speed (N1) sensor (Ref. 77-11-15-000-801/77-11-15-400-801 MM). -No
| Yes |
10 Replace the FADEC that has the fault (Ref. 73-25-10-000-801/73-25-10-400-801 MM).
FADEC Discrete: N1PDIF (bit 11) and N1PSTD (bit 13) (357 / EIDIF) = 1 EFFECTIVITY:ALL
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FADEC Discrete: N1SDIF (bit 12) and N1PSOD (bit 18) (357 / EIDIF) = 1 DESCRIPTION:
R R
The FADECs compare the signals received from their secondary fan speed (N1) sensors. The FADECs also compare their N1 primary and N1 secondary signals. These two discretes are set to 1 (fault sensed) when the N1 signals being compared are different, by more than 35 RPM. This is an indication of a fault with the N1 secondary circuit (this channel's sensor, other FADEC). The lane difference tests are not done when either a sensor or the cross-channel data link (W4 harness) have failed. If available, the AE 3007 Engine Signal Test Set and Cable (CDS P/N 86690158) (Ref. TASK 73-25-10-700-801, MM) can be used for continuity/resistance testing of a suspected faulty FADEC/engine interconnect (W7) harness.
POSSIBLE CAUSES: 1. Harness 2. Fan speed (N1) sensor 3. FADEC
01 Examine the harness connectors between this FADEC and the fan speed (N1) sensor for this channel, for corrosion, contamination, or damage. Are the connectors dirty or damaged?
06 Clean the connectors (Ref. 70-00-00-910-804 MM) or replace the harness -Yes (Ref. 76-00-00 MM) (Ref. AMM).
| No 02 Do a test for continuity/resistance (1 ohm 07 Replace the harness that has the fault max./harness), internal shorts, and shorts to (Ref. 76-00-00 MM) (Ref. AMM). ground (1,000 ohms min.) on the FADEC A/B (W11/14) and FADEC/engine interconnect (W7) harnesses (secondary circuit; this -No channel's sensor, other FADEC) (Ref. 77-11-51 WM) (Ref. FIG. 301/TASK 77-11-00-990-801/FIG. 303/TASK 77-11-00-990-803). Do the harnesses test satisfactorily? | Yes 03 Do a test for continuity/resistance, internal 08 Replace the fan speed (N1) sensor (Ref. shorts, and shorts to ground on the fan speed 77-11-15-000-801/77-11-15-400-801 MM). (N1) sensor (secondary circuit; this channel's sensor, other FADEC) (Ref. 77-11-15-700-801 -No MM). Maximum resistance between pins C and D is 500 ohms. Does the sensor test satisfactorily? | Yes FADEC Discrete: N1SDIF (bit 12) and N1PSOD (bit 18) (357 / EIDIF) = 1 04 Go to Block 05 EFFECTIVITY:ALL
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05 Interchange the position of the FADECs (Ref. 73-25-10-000-801/73-25-10-400-801 MM). Turn electrical power to the FADEC OFF, and then ON. Operate the engine as necessary (Ref. AMM). Does the fault move to the opposite channel?
09 Replace the fan speed (N1) sensor (Ref. 77-11-15-000-801/77-11-15-400-801 MM). -No
| Yes |
10 Replace the FADEC that has the fault (Ref. 73-25-10-000-801/73-25-10-400-801 MM).
FADEC Discrete: N1SDIF (bit 12) and N1PSOD (bit 18) (357 / EIDIF) = 1 EFFECTIVITY:ALL
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FADEC Discrete: N2PSFT (bit 13) / (353 / EILRU) = 1 DESCRIPTION:
R R
The FADEC monitors the signal received from its primary N2 speed sensor and does a test for circuit continuity. This discrete is set to 1 (fault sensed) when the signal is not within the limits, or an open circuit is found (removing electrical power from the FADEC is necessary to remove a fault set by failure of the continuity test) (Ref. FIG. 302/TASK 77-11-00-990-802/FIG. 303/TASK 77-11-00-990-803). If available, the AE 3007 Engine Signal Test Set and Cable (CDS P/N 86690158) (Ref. TASK 73-25-10-700-801, MM) can be used for continuity/resistance testing of a suspected faulty FADEC/engine interconnect (W7) harness.
POSSIBLE CAUSES: 1. N2 speed sensor 2. Harness 3. FADEC
01 Interchange the position of the N2A and 03 Replace the N2 speed sensor that has the N2B harness connectors on the N2 speed fault (Ref. 77-11-10-000-801/ sensors. Turn electrical power to the FADEC 77-11-10-400-801 MM). -Yes OFF, and then ON. Operate the engine as necessary (Ref. AMM). Does the fault move to the opposite channel? | No 02 Interchange the position of the FADECs 04 Replace the FADEC that has the fault (Ref. (Ref. 73-25-10-000-801/73-25-10-400-801 73-25-10-000-801/73-25-10-400-801 MM). MM). Turn electrical power to the FADEC -Yes OFF, and then ON. Operate the engine as necessary (Ref. AMM). Does the fault move to the opposite channel? | No |
05 Do a test for continuity / resistance (1 ohm max./harness), internal shorts, and shorts to ground 1,000 ohms min.) on the FADEC A/B (W11/14) and FADEC/engine interconnect (W7) harnesses (Ref. FIG. 302/TASK 77-11-00-990-802/FIG. 303/TASK 77-11-00-990-803) (Ref. 77-11-51 WM). Replace the harness that has the fault (Ref. 76-00-00 MM) (Ref. AMM).
FADEC Discrete: N2PSFT (bit 13) / (353 / EILRU) = 1 EFFECTIVITY:ALL
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FADEC Discrete: N2PDIF (bit 15) and N2PSTD (bit 17) / (357 / EIDIF) = 1 DESCRIPTION:
R R
The FADECs compare the signals received from their primary N2 speed sensors. The FADECs also compare their N2 primary and N2 secondary signals. These two discretes are set to 1 (fault sensed) when the N2 signals being compared are different, by more than 50 RPM. This is an indication of a fault with the N2 primary circuit for this FADEC. The lane difference tests are not done when either a sensor or the cross-channel data link (W4 harness) have failed. If available, the AE 3007 Engine Signal Test Set and Cable (CDS P/N 86690158) (Ref. TASK 73-25-10-700-801, MM) can be used for continuity/resistance testing of a suspected faulty FADEC/engine interconnect (W7) harness.
POSSIBLE CAUSES: 1. Harness 2. N2 speed sensor 3. FADEC
01 Interchange the position of the N2A and 03 Replace the N2 speed sensor that has the N2B harness connectors on the N2 speed fault (Ref. 77-11-10-000-801/ sensors. Turn electrical power to the FADEC 77-11-10-400-801 MM). -Yes OFF, and then ON. Operate the engine as necessary (Ref. AMM). Does the fault move to the opposite channel? | No 02 Interchange the position of the FADECs 04 Replace the FADEC that has the fault (Ref. (Ref. 73-25-10-000-801/73-25-10-400-801 73-25-10-000-801/73-25-10-400-801 MM). MM). Rotate the FADEC reset/select switch to -Yes the RESET position. Operate the engine as necessary (Ref. AMM). Does the fault move to the opposite channel? | No |
05 Do a test for continuity / resistance (1 ohm max./harness), internal shorts, and shorts to ground 1,000 ohms min.) on the FADEC A/B (W11/14) and FADEC/engine interconnect (W7) harnesses (Ref. FIG. 302/TASK 77-11-00-990-802/FIG. 303/TASK 77-11-00-990-803) (Ref. 77-11-51 WM). Replace the harness that has the fault (Ref. 76-00-00 MM) (Ref. AMM).
FADEC Discrete: N2PDIF (bit 15) and N2PSTD (bit 17) / (357 / EIDIF) = 1 EFFECTIVITY:ALL
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Observed Fault: Overspeed (N1) (displayed on EICAS and/or CMC Exceedance) (associated with software detected FADEC Discrete: N1OSTR (bit 19) / (355/SFLTS1) = 1) DESCRIPTION: The FADEC controls N1 rotor speed by controlling fuel flow through the fuel pump and metering unit (FPMU). If N1 rotor speed is above 100%, an exceedance event is recorded in the central maintenance computer (CMC), and the EICAS display will become red.
POSSIBLE CAUSES: 1. FADEC 2. FPMU 3. Aircraft signal-conditioning failure
01 Supply electrical power to the aircraft. Access the engine exceedance data from the CMC (Ref. Introduction). Did an exceedance event occur at the same time as the overspeed indication on the EICAS?
07 Do the troubleshooting on the aircraft signal-conditioning system (Ref. 31-41-00/201 -No EMB FIM).
| Yes 02 Do the inspection of the engine for N1 overspeed (Ref. 72-50-00-200-803 MM). Can the engine be returned to service?
-No
08 Remove the engine (Ref. AMM).
| Yes 03 Access the maintenance messages and the 09 Do the troubleshooting for the FADEC FADEC discrete labels from the CMC (Ref. discrete(s) that = 1 and/or the maintenance Introduction). Does a FADEC discrete label = message(s) with a fault. -Yes 1 or did a maintenance message fault occur prior to or at the same time as the overspeed indication? | No 04 Go to Block 05
Observed Fault: Overspeed (N1) (displayed on EICAS and/or CMC Exceedance) EFFECTIVITY:ALL
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R R
05 Examine all the connectors on the W11/14 10 Tighten or clean the connectors (Ref. and W7 harnesses (Ref. FIG. 303/TASK 70-00-00-910-804 MM) or replace the harness 77-11-00-990-803) for looseness, corrosion, -Yes (Ref. 76-00-00 MM) (Ref. AMM). contamination, or damage. Are the connectors loose, dirty, or damaged? | No 06 Was the N1 rotor speed above 103.3%?
11 Replace both FADECs (Ref. 73-25-10-000-801/73-25-10-400-801 MM) and -Yes the FPMU (Ref. 73-21-10-000-801/ 73-21-10-400-801 MM). Send the parts to Rolls-Royce.
| No |
12 Return the engine to service.
Observed Fault: Overspeed (N1) (displayed on EICAS and/or CMC Exceedance) EFFECTIVITY:ALL
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Observed Fault: Overspeed (N2) (displayed on EICAS and/or CMC Exceedance) (associated with software detected FADEC Discrete: N2OSTR (bit 20) / (355/SFLTS1) = 1) DESCRIPTION: R R
The FADEC controls N2 rotor speed by controlling fuel flow through the fuel pump and metering unit (FPMU). If N2 rotor speed is above 102.5% (for 3007A, A1, A1/1, A1/3, A1P, and A3), or 103.8% (for 3007A1E), an exceedance event is recorded in the central maintenance computer (CMC), and the EICAS display will become red.
POSSIBLE CAUSES: 1. FADEC 2. FPMU 3. Aircraft signal-conditioning failure 4. CVG actuator
01 Supply electrical power to the aircraft. Access the engine exceedance data from the CMC (Ref. Introduction). Did an exceedance event occur at the same time as the overspeed indication on the EICAS?
07 Do the troubleshooting on the aircraft signal-conditioning system (Ref. 31-41-00/201 -No EMB FIM).
| Yes 02 Do the inspection of the engine for N2 overspeed (Ref. 72-50-00-200-802 MM). Can the engine be returned to service?
-No
08 Remove the engine (Ref. AMM).
| Yes 03 Access the maintenance messages and the 09 Do the troubleshooting for the FADEC FADEC discrete labels from the CMC (Ref. discrete(s) that = 1 and/or the maintenance Introduction). Does a FADEC discrete label = message(s) with a fault. -Yes 1 or did a maintenance message fault occur prior to or at the same time as the overspeed indication? | No 04 Go to Block 05
Observed Fault: Overspeed (N2) (displayed on EICAS and/or CMC Exceedance) EFFECTIVITY:ALL
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05 Examine all the connectors on the W11/14 and W7 harnesses (Ref. Fig. 303) for looseness, corrosion, contamination, or damage. Are the connectors loose, dirty, or damaged?
10 Tighten or clean the connectors (Ref. 70-00-00-910-804 MM) or replace the harness -Yes (Ref. 76-00-00 MM) (Ref. AMM).
| No 06 Was the N2 rotor speed above 104.6%?
11 Replace both FADECs (Ref. 73-25-10-000-801/73-25-10-400-801 MM) and the CVG actuator (Ref. -Yes 75-33-10-000-801/75-33-10-400-810 MM), and the FPMU (Ref. 73-21-10-000-810/73-21-10-400-810 MM). Send the parts to Rolls-Royce.
| No |
12 Return the engine to service.
Observed Fault: Overspeed (N2) (displayed on EICAS and/or CMC Exceedance) EFFECTIVITY:ALL
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FADEC Discrete: N1PDIF (bit 11) / (357 / EIDIF) = 1 DESCRIPTION:
R R
The FADECs compare the signals received from the primary circuits of their fan speed (N1) sensors. This discrete is set to 1 (fault sensed) when the N1 signals being compared are different, by more than 35 RPM. This is an indication of a fault with the N1 primary circuit. The lane difference test is not done when either a sensor or the cross-channel data link (W4 harness) have failed. If available, the AE 3007 Engine Signal Test Set and Cable (CDS P/N 86690158) (Ref. TASK 73-25-10-700-801, MM) can be used for continuity/resistance testing of a suspected faulty FADEC/engine interconnect (W7) harness.
POSSIBLE CAUSES: 1. Harness 2. Fan speed (N1) sensor 3. FADEC
01 Examine the harness connectors between 08 Clean the connectors (Ref. the FADECs and the fan speed (N1) sensors 70-00-00-910-804 MM) or replace the harness for both channels, for corrosion, contamination, -Yes (Ref. 76-00-00 MM). or damage. Are the connectors dirty or damaged? | No 02 Do a test for continuity/resistance (1 ohm max./harness), internal shorts, and shorts to ground (1,000 ohms min.) on the FADEC A/B (W11/14) and FADEC/engine interconnect (W7) harnesses (N1 primary circuit) for both channels (Ref. FIG. 301/TASK 77-11-00-990-801/FIG. 303/TASK 77-11-00-990-803) (Ref. 77-11-51 WM). Do the harnesses test satisfactorily?
09 Replace the harness that has the fault (Ref. 76-00-00 MM). -No
| Yes 03 Do a test for continuity/resistance, internal 10 Replace the fan speed (N1) sensor that has shorts, and shorts to ground on the fan speed the fault (Ref. 77-11-15-000-801/ (N1) sensor (primary circuit) (Ref. 77-11-15-400-801 MM). -No 77-11-15-700-801 MM) (Ref. 77-11-51 WM). Maximum resistance between pins A and B is 500 ohms. Does the sensor test satisfactorily? | Yes 04 Go to Block 05 FADEC Discrete: N1PDIF (bit 11) / (357 / EIDIF) = 1 EFFECTIVITY:ALL
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05 Replace FADEC A with a FADEC from the 11 Replace the FADEC that has the fault (Ref. opposite engine (Ref. 73-25-10-000-801/ 73-25-10-000-801/73-25-10-400-801 MM). -Yes 73-25-10-400-801 MM). Operate the engine as necessary (Ref. AMM). Is the fault removed? | No 06 Replace FADEC B with a FADEC from the 12 Replace the FADEC that has the fault (Ref. opposite engine (Ref. 73-25-10-000-801/ 73-25-10-000-801/73-25-10-400-801 MM). -Yes 73-25-10-400-801 MM). Operate the engine as necessary (Ref. AMM). Is the fault removed? | No 07 Replace the fan speed (N1) sensor for 13 Remove the fan speed (N1) sensor from channel A (Ref. 77-11-15-000-801/ service. -Yes 77-11-15-400-801 MM). Operate the engine as necessary (Ref. AMM). Is the fault removed? | No |
14 Replace the fan speed (N1) sensor for channel B (Ref. 77-11-15-000-801/ 77-11-15-400-801 MM).
FADEC Discrete: N1PDIF (bit 11) / (357 / EIDIF) = 1 EFFECTIVITY:ALL
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FADEC Discrete: N1PSTD (bit 13) / (357 / EIDIF) = 1 DESCRIPTION:
R R
The FADECs compare the signals received from the primary circuits of their fan speed (N1) sensors, to those received from their secondary circuits. This discrete is set to 1 (fault sensed) when the N1 signals being compared are different, by more than 35 RPM. This is an indication of a fault with the N1 primary/secondary circuit. The lane difference test is not done when either a sensor or the cross-channel data link (W4 harness) have failed. If available, the AE 3007 Engine Signal Test Set and Cable (CDS P/N 86690158) (Ref. TASK 73-25-10-700-801, MM) can be used for continuity/resistance testing of a suspected faulty FADEC/engine interconnect (W7) harness.
POSSIBLE CAUSES: 1. Harness 2. Fan speed (N1) sensor 3. FADEC
01 Examine the harness connectors between 08 Clean the connectors (Ref. the FADEC and the fan speed (N1) sensors for 70-00-00-910-804 MM) or replace the harness this channel, for corrosion, contamination, or -Yes (Ref. 76-00-00 MM). damage. Are the connectors dirty or damaged? | No 02 Do a test for continuity/resistance (1 ohm max./harness), internal shorts, and shorts to ground (1,000 ohms min.) on the FADEC A/B (W11/14) and FADEC/engine interconnect (W7) harnesses (N1 primary and secondary circuit) for both channels (Ref. FIG. 301/TASK 77-11-00-990-801 /FIG. 303/TASK 77-11-00-990-803) (Ref. 77-11-51 WM). Do the harnesses test satisfactorily?
09 Replace the harness that has the fault (Ref. 76-00-00 MM). -No
| Yes 03 Do a test for continuity/resistance, internal shorts, and shorts to ground on both fan speed (N1) sensors (all circuits) (Ref. 77-11-51 WM) (Ref. 77-11-15-700-801 MM). Maximum resistance between pins A/B and C/D is 500 ohms. Does the sensor test satisfactorily?
-No
10 Replace the fan speed (N1) sensor that has the fault (Ref. 77-11-15-000-801/ 77-11-15-400-801 MM).
| Yes 04 Go to Block 05 FADEC Discrete: N1PSTD (bit 13) / (357 / EIDIF) = 1 EFFECTIVITY:ALL
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05 Replace FADEC A with a FADEC from the 11 Replace the FADEC that has the fault (Ref. opposite engine (Ref. 73-25-10-000-801/ 73-25-10-000-801/73-25-10-400-801 MM). -Yes 73-25-10-400-801 MM). Operate the engine as necessary (Ref. AMM). Is the fault removed? | No 06 Replace FADEC B with a FADEC from the 12 Replace the FADEC that has the fault (Ref. opposite engine (Ref. 73-25-10-000-801/ 73-25-10-000-801/73-25-10-400-801 MM). -Yes 73-25-10-400-801 MM). Operate the engine as necessary (Ref. AMM). Is the fault removed? | No 07 Replace the fan speed (N1) sensor for 13 Remove the fan speed (N1) sensor from channel A (Ref. 77-11-15-000-801/ service. -Yes 77-11-15-400-801 MM). Operate the engine as necessary Ref. AMM). Is the fault removed? | No |
14 Replace the fan speed (N1) sensor for channel B (Ref. 77-11-15-000-801/ 77-11-15-400-801 MM).
FADEC Discrete: N1PSTD (bit 13) / (357 / EIDIF) = 1 EFFECTIVITY:ALL
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FADEC Discrete: N1SDIF (bit 12) / (357 / EIDIF) = 1 DESCRIPTION:
R R
The FADECs compare the signals received from the secondary circuits of their fan speed (N1) sensors. This discrete is set to 1 (fault sensed) when the N1 signals being compared are different, by more than 35 RPM. This is an indication of a fault with the N1 secondary circuit. The lane difference test is not done when either a sensor or the cross-channel data link (W4 harness) have failed. If available, the AE 3007 Engine Signal Test Set and Cable (CDS P/N 86690158) (Ref. TASK 73-25-10-700-801, MM) can be used for continuity/resistance testing of a suspected faulty FADEC/engine interconnect (W7) harness.
POSSIBLE CAUSES: 1. Harness 2. Fan speed (N1) sensor 3. FADEC
01 Examine the harness connectors between 08 Clean the connectors (Ref. the FADEC and the fan speed (N1) sensors for 70-00-00-910-804 MM) or replace the harness both channels, for corrosion, contamination, or -Yes (Ref. 76-00-00 MM). damage. Are the connectors dirty or damaged? | No 02 Do a test for continuity/resistance (1 ohm max./harness), internal shorts, and shorts to ground (1,000 ohms min.) on the FADEC A/B (W11/14) and FADEC/engine interconnect (W7) harnesses (N1 secondary circuit) for both channels (Ref. FIG. 301/TASK 77-11-00-990-801/FIG. 303/TASK 77-11-00-990-803) (Ref. 77-11-51 WM). Do the harnesses test satisfactorily?
09 Replace the harness that has the fault (Ref. 76-00-00 MM) -No
| Yes 03 Do a test for continuity/resistance, internal 10 Replace the fan speed (N1) sensor that has shorts, and shorts to ground on the fan speed the fault (Ref. 77-11-15-000-801/ (N1) sensor (secondary circuit) (Ref. 77-11-15-400-801 MM). -No 77-11-15-700-801 MM) (Ref. 77-11-51 WM). Maximum resistance between pins C and D is 500 ohms. Does the sensor test satisfactorily? | Yes 04 Go to Block 05 FADEC Discrete: N1SDIF (bit 12) / (357 / EIDIF) = 1 EFFECTIVITY:ALL
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05 Replace FADEC A with a FADEC from the 11 Replace the FADEC that has the fault (Ref. opposite engine (Ref. 73-25-10-000-801/ 73-25-10-000-801/73-25-10-400-801 MM). -Yes 73-25-10-400-801 MM). Operate the engine as necessary (Ref. AMM). Is the fault removed? | No 06 Replace FADEC B with a FADEC from the 12 Replace the FADEC that has the fault (Ref. opposite engine (Ref. 73-25-10-000-801/ 73-25-10-000-801/73-25-10-400-801 MM). -Yes 73-25-10-400-801 MM). Operate the engine as necessary (Ref. AMM). Is the fault removed? | No 07 Replace the fan speed (N1) sensor for 13 Remove the fan speed (N1) sensor from channel A (Ref. 77-11-15-000-801/ service. -Yes 77-11-15-400-801 MM). Operate the engine as necessary Ref. AMM). Is the fault removed? | No |
14 Replace the fan speed (N1) sensor for channel B (Ref. 77-11-15-000-801/ 77-11-15-400-801 MM).
FADEC Discrete: N1SDIF (bit 12) / (357 / EIDIF) = 1 EFFECTIVITY:ALL
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FADEC Discrete: N1PSOD (bit 14) / (357 / EIDIF) = 1 DESCRIPTION:
R R
The FADECs compare the signals received from the primary circuits of their fan speed (N1) sensors, to those received from their secondary circuits. This discrete is set to 1 (fault sensed) when the N1 signals being compared are different, by more than 35 RPM. This is an indication of a fault with the N1 primary/secondary circuit. The lane difference test is not done when either a sensor or the cross-channel data link (W4 harness) have failed. If available, the AE 3007 Engine Signal Test Set and Cable (CDS P/N 86690158) (Ref. TASK 73-25-10-700-801, MM) can be used for continuity/resistance testing of a suspected faulty FADEC/engine interconnect (W7) harness.
POSSIBLE CAUSES: 1. Harness 2. Fan speed (N1) sensor 3. FADEC
01 Examine the harness connectors between the other FADEC and the fan speed (N1) sensors for the other channels, for corrosion, contamination, or damage. Are the connectors dirty or damaged?
08 Clean the connectors (Ref. 70-00-00-910-804 MM) or replace the harness -Yes (Ref. 76-00-00 MM).
| No 02 Do a test for continuity/resistance (1 ohm max./harness), internal shorts, and shorts to ground (1,000 ohms min.) on the FADEC A/B (W11/14) and FADEC/engine interconnect (W7) harnesses (N1 secondary circuit) for the other channels (Ref. FIG. 301/TASK 77-11-00-990-801/FIG. 303/TASK 77-11-00-990-803) (Ref. 77-11-51 WM). Do the harnesses test satisfactorily?
09 Replace the harness that has the fault (Ref. 76-00-00 MM). -No
| Yes 03 Do a test for continuity/resistance, internal shorts, and shorts to ground on both fan speed (N1) sensors (all circuits) (Ref. 77-11-51 WM) (Ref. 77-11-15-700-801 MM). Maximum resistance between pins A/B and C/D is 500 ohms. Does the sensor test satisfactorily?
-No
10 Replace the fan speed (N1) sensor that has the fault (Ref. 77-11-15-000-801/ 77-11-15-400-801 MM).
| Yes 04 Go to Block 05 FADEC Discrete: N1PSOD (bit 14) / (357 / EIDIF) = 1 EFFECTIVITY:ALL
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05 Replace FADEC A with a FADEC from the 11 Replace the FADEC that has the fault (Ref. opposite engine (Ref. 73-25-10-000-801/ 73-25-10-000-801/73-25-10-400-801 MM). -Yes 73-25-10-400-801 MM). Operate the engine as necessary (Ref. AMM). Is the fault removed? | No 06 Replace FADEC B with a FADEC from the 12 Replace the FADEC that has the fault (Ref. opposite engine (Ref. 73-25-10-000-801/ 73-25-10-000-801/73-25-10-400-801 MM). -Yes 73-25-10-400-801 MM). Operate the engine as necessary (Ref. AMM). Is the fault removed? | No 07 Replace the fan speed (N1) sensor for 13 Remove the fan speed (N1) sensor from channel A (Ref. 77-11-15-000-801/ service. -Yes 77-11-15-400-801 MM). Operate the engine as necessary Ref. AMM). Is the fault removed? | No |
14 Replace the fan speed (N1) sensor for channel B (Ref. 77-11-15-000-801/ 77-11-15-400-801 MM).
FADEC Discrete: N1PSOD (bit 14) / (357 / EIDIF) = 1 EFFECTIVITY:ALL
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FADEC Discrete: N2PDIF (bit 15) / (357 / EIDIF) = 1 DESCRIPTION:
R R
The FADECs compare the signals received from the N2 speed sensors. This discrete is set to 1 (fault sensed) when the N2 signals being compared are different, by more than 35 RPM. This is an indication of a fault with the N2 speed sensor circuit. The lane difference test is not done when either a sensor or the cross-channel data link (W4 harness) have failed. If available, the AE 3007 Engine Signal Test Set and Cable (CDS P/N 86690158) (Ref. TASK 73-25-10-700-801, MM) can be used for continuity/resistance testing of a suspected faulty FADEC/engine interconnect (W7) harness.
POSSIBLE CAUSES: 1. Harness 2. N2 speed sensor 3. FADEC
01 Cycle electrical power to the FADECs. Operate the engine at ground idle. Access FADEC discrete label 357 from the central maintenance computer (CMC) for both FADECs (Ref. Introduction). Does N2PDIF (bit 15) = 1?
10 Go to block 03. -Yes
| No 02 Use the FADEC ALTN switch to select the other FADEC for engine control. Access FADEC discrete label 357 from the central maintenance computer (CMC) for both FADECs (Ref. Introduction). Does N2PDIF (bit 15) = 1?
11 Go to block 03. -Yes
| No |
12 Return the engine to service.
FADEC Discrete: N2PDIF (bit 15) / (357 / EIDIF) = 1 EFFECTIVITY:ALL
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03 Examine the harness connectors between the FADECs and the N2 speed sensors for both channels, for corrosion, contamination, or damage. Are the connectors dirty or damaged?
13 Clean the connectors (Ref. 70-00-00-910-804 MM) or replace the harness -Yes (Ref. 76-00-00 MM).
| No 04 Do a test for continuity/resistance (1 ohm max./harness), internal shorts, and shorts to ground (1,000 ohms min.) on the FADEC A/B (W11/14) and FADEC/engine interconnect (W7) harnesses (N2 sensor circuit) for both channels (Ref. FIG. 301/TASK 77-11-00-990-801/FIG. 303/TASK 77-11-00-990-803) (Ref. 77-11-51 WM). Do the harnesses test satisfactorily?
14 Replace the harness that has the fault (Ref. 76-00-00 MM). -No
| Yes 05 Do a test for continuity/resistance, internal shorts, and shorts to ground on both N2 speed sensors (Ref. 77-11-10-700-801 MM) (Ref. 77-11-51 WM). Maximum resistance between pins A and C is 500 ohms. Does the sensor test satisfactorily?
-No
15 Replace the N2 speed sensor that has the fault (Ref. 77-11-10-000-801/ 77-11-10-400-801 MM).
| Yes 06 Replace the N2 speed sensor for channel A 16 Remove the N2 speed sensor from service. (Ref. 77-11-10-000-801/77-11-10-400-801 -Yes MM). Operate the engine as necessary (Ref. AMM). Is the fault removed? | No 07 Go to Block 08.
FADEC Discrete: N2PDIF (bit 15) / (357 / EIDIF) = 1 EFFECTIVITY:ALL
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08 Replace the N2 speed sensor for channel B 17 Remove the N2 speed sensor from service. (Ref. 77-11-10-000-801/77-11-10-400-801 -Yes MM). Operate the engine as necessary Ref. AMM). Is the fault removed? | No 09 Replace FADEC A with a FADEC from the 18 Replace the FADEC that has the fault (Ref. opposite engine (Ref. 73-25-10-000-801/ 73-25-10-000-801/73-25-10-400-801 MM). -Yes 73-25-10-400-801 MM). Operate the engine as necessary (Ref. AMM). Is the fault removed? | No |
19 Replace the FADEC B (Ref. 73-25-10-000-801/73-25-10-400-801 MM).
FADEC Discrete: N2PDIF (bit 15) / (357 / EIDIF) = 1 EFFECTIVITY:ALL
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FADEC Discrete: N2PSTD (bit 17) / (357 / EIDIF) = 1 DESCRIPTION:
R R
This FADEC compares the signals received from its primary and secondary N2 speed sensors. One phase of the permanent magnet alternator (PMA) provides the N2 secondary signal to the FADEC. This discrete is set to 1 (fault sensed) when the N2 signals being compared are different, by more than 35 RPM. The lane difference test is not done when either a sensor or the cross-channel data link (W4) have failed. If available, the AE 3007 Engine Signal Test Set and Cable (CDS P/N 86690158) (Ref. TASK 73-25-10-700-801, MM) can be used for continuity/resistance testing of a suspected faulty FADEC/engine interconnect (W7) harness.
POSSIBLE CAUSES: 1. Harness 2. 2 speed sensor 3. Permanent magnet alternator (PMA) 4. FADEC
01 Interchange the position of the N2A and N2B harness connectors on the N2 speed sensors. Rotate the FADEC reset/select switch to the RESET position. Operate the engine as necessary. Does the fault move to the opposite channel?
-Yes
06 Replace the N2 speed sensor that has the fault (Ref. 77-11-10-000-801/ 77-11-10-400-801 MM).
| No 02 Interchange the position of the PMAA and PMAB harness connectors on the PMA. Rotate the FADEC reset/select switch to the RESET position. Operate the engine as necessary. Does the fault move to the opposite channel?
07 Replace the alternator stator (Ref. 74-11-10-000-801/74-11-10-400-801 MM). -Yes
| No 03 Interchange the position of the FADECs 08 Replace the FADEC that has the fault (Ref. (Ref. 73-25-10-000-801/73-25-10-400-801 73-25-10-000-801/73-25-10-400-801 MM). MM). Rotate the FADEC reset/select switch to -Yes the RESET position. Operate the engine as necessary. Does the fault move to the opposite channel? | No 04 Go to Block 05 FADEC Discrete: N2PSTD (bit 17) / (357 / EIDIF) = 1 EFFECTIVITY:ALL
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05 Do a test for continuity/resistance (1 ohm max./harness), internal shorts, and shorts to ground (1,000 ohms min.) on the FADEC A/B (W11/14) and FADEC/engine interconnect (W7) harnesses (PMA/FADEC circuits) (Ref. FIG. 303/TASK 77-11-00-990-803/FIG. 304/TASK 77-11-00-990-804) (Ref. 76-12-50/76-12-51 WM). Do the harnesses test satisfactorily?
09 Do a test for continuity/resistance (1 ohm max./harness), internal shorts, and shorts to ground (1,000 ohms min.) on the FADEC A/B (W11/14) and FADEC/engine interconnect -Yes (W7) harnesses (N2 sensor circuit) (Ref. 77-11-51 WM) (Ref. FIG. 302/TASK 77-11-00-990-802/FIG. 303/TASK 77-11-00-990-803). Replace the harness that has the fault (Ref. 76-00-00 MM) (Ref. AMM).
| No |
10 Replace the harness that has the fault (Ref. 76-00-00 MM) (Ref. AMM).
FADEC Discrete: N2PSTD (bit 17) / (357 / EIDIF) = 1 EFFECTIVITY:ALL
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FADEC Discrete: N2SDIF (bit 16) / (357 / EIDIF) = 1 DESCRIPTION:
R R
The FADECs compare the secondary N2 speed signals received from the permanent magnet alternator (PMA). This discrete is set to 1 (fault sensed) when the N2 signals being compared are different, by more than 35 RPM. This is an indication of a fault with the PMA circuit. The lane difference test is not done when either a sensor or the cross-channel data link (W4 harness) have failed. If available, the AE 3007 Engine Signal Test Set and Cable (CDS P/N 86690158) (Ref. TASK 73-25-10-700-801, MM) can be used for continuity/resistance testing of a suspected faulty FADEC/engine interconnect (W7) harness.
POSSIBLE CAUSES: 1. Harness 2. Permanent magnet alternator (PMA) 3. FADEC
01 Cycle electrical power to the FADECs. Operate the engine at ground idle. Access FADEC discrete label 357 from the central maintenance computer (CMC) for both FADECs (Ref. Introduction). Does N2SDIF (bit 16) = 1?
07 Go to block 03. -Yes
| No 02 Use the FADEC ALTN switch to select the other FADEC for engine control. Access FADEC discrete label 357 from the central maintenance computer (CMC) for both FADECs (Ref. Introduction). Does N2SDIF (bit 16) = 1?
08 Go to block 03. -Yes
| No |
09 Return the engine to service.
FADEC Discrete: N2SDIF (bit 16) / (357 / EIDIF) = 1 EFFECTIVITY:ALL
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03 Examine the harness connectors between 10 Clean the connectors (Ref. the FADEC and the PMA for both channels, for 70-00-00-910-804 MM) or replace the harness -Yes corrosion contamination or damage. Are the (Ref. 76-00-00 MM). connectors dirty or damaged? | No 04 Do a test for continuity/resistance (1 ohm max./harness), internal shorts, and shorts to ground (1,000 ohms min.) on the FADEC A/B (W11/14) and FADEC/interconnect (W7) harnesses (PMA/FADEC circuits) for both channels (Ref. FIG. 303/TASK 77-11-00-990-803/FIG. 304/TASK 77-11-00-990-804) (Ref. 76-12-50/76-12-51 WM). Do the harnesses test satisfactorily?
11 Replace the harness that has the fault (Ref. 76-00-00 MM). -No
| Yes 05 Replace the alternator stator (Ref. 74-11-10-000-801/74-11-10-411-801 MM). Operate the engine as necessary. Is the fault removed?
12 Remove the alternator stator from service. -Yes
| No 06 Replace FADEC A with a FADEC from the 13 Replace the FADEC that has the fault opposite engine (Ref. 73-25-10-000-801/ (Ref. 73-25-10-000-801/73-25-10-400-801 -Yes 73-25-10-400-801 MM). Operate the engine as MM). necessary. Is the fault removed? | No |
14 Replace FADEC B (Ref. 73-25-10-000-801/73-25-10-400-801 MM).
FADEC Discrete: N2SDIF (bit 16) / (357 / EIDIF) = 1 EFFECTIVITY:ALL
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FADEC Discrete: N2PSOD (bit 18) / (357 / EIDIF) = 1 DESCRIPTION:
R R
The other FADEC compares the signals received from its primary and secondary N2 speed sensors. One phase of the permanent magnet alternator (PMA) provides the N2 secondary signal to the FADEC. This discrete is set to 1 (fault sensed) when the N2 signals being compared are different, by more than 35 RPM. The lane difference test is not done when either a sensor or the cross-channel data link (W4 harness) have failed. If available, the AE 3007 Engine Signal Test Set and Cable (CDS P/N 86690158) (Ref. TASK 73-25-10-700-801, MM) can be used for continuity/resistance testing of a suspected faulty FADEC/engine interconnect (W7) harness.
POSSIBLE CAUSES: 1. Harness 2. N2 speed sensor 3. Permanent magnet alternator (PMA) 4. FADEC
01 Cycle electrical power to the FADECs. Operate the engine at ground idle. Access FADEC discrete label 357 from the central maintenance computer (CMC) for both FADECs (Ref. Introduction). Does N2PSOD (bit 18) = 1?
10 Go to block 03. -Yes
| No 02 Use the FADEC ALTN switch to select the other FADEC for engine control. Access FADEC discrete label 357 from the central maintenance computer (CMC) for both FADECs (Ref. Introduction). Does N2PSOD (bit 18) = 1?
11 Go to block 03. -Yes
| No |
12 Return the engine to service.
FADEC Discrete: N2PSOD (bit 18) / (357 / EIDIF) = 1 EFFECTIVITY:ALL
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03 Interchange the position of the N2A and N2B harness connectors on the N2 speed sensors. Rotate the FADEC reset/select switch to the RESET position. Operate the engine as necessary. Does the fault move to the opposite channel?
-Yes
13 Replace the N2 speed sensor that has the fault (Ref. 77-11-10-000-801/ 77-11-10-400-801 MM).
| No 04 Interchange the position of the PMAA and PMAB harness connectors on the PMA. Rotate the FADEC reset/select switch to the RESET position. Operate the engine as necessary. Does the fault move to the opposite channel?
14 Replace the alternator stator (Ref. 74-11-10-000-801/74-11-10-400-801 MM). -Yes
| No 05 Interchange the position of the N2A and N2B harness connectors on the N2 speed sensors. Rotate the FADEC reset/select switch to the RESET position. Operate the engine as necessary. Does the fault move to the opposite channel?
-Yes
15 Replace the N2 speed sensor that has the fault (Ref. 77-11-10-000-801/ 77-11-10-400-801 MM).
| No 06 Interchange the position of the PMAA and PMAB harness connectors on the PMA. Rotate the FADEC reset/select switch to the RESET position. Operate the engine as necessary. Does the fault move to the opposite channel?
16 Replace the alternator stator (Ref. 74-11-10-000-801/74-11-10-400-801 MM). -Yes
| No 07 Go to Block 08.
FADEC Discrete: N2PSOD (bit 18) / (357 / EIDIF) = 1 EFFECTIVITY:ALL
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08 Interchange the position of the FADECs 17 Replace the FADEC that has the fault (Ref. (Ref. 73-25-10-000-801/73-25-10-400-801 73-25-10-000-801/73-25-10-400-801 MM). MM). Rotate the FADEC reset/select switch to -Yes the RESET position. Operate the engine as necessary. Does the fault move to the opposite channel? | No 09 Do a test for continuity/resistance (1 ohm max./harness), internal shorts, and shorts to ground (1,000 ohms min.) on the FADEC A/B (W11/14) and FADEC/engine interconnect (W7) harnesses (PMA/FADEC circuits) (Ref. FIG. 303/TASK 77-11-00-990-803/FIG. 304/TASK 77-11-00-990-804) (Ref. 76-12-50/76-12-51 WM). Do the harnesses test satisfactorily?
18 Do a test for continuity/resistance (1 ohm max./harness), internal shorts, and shorts to ground (1,000 ohms min.) on the FADEC A/B (W11/14) and FADEC/engine interconnect -Yes (W7) harnesses (N2 sensor circuit) (Ref. FIG. 302/TASK 77-11-00-990-802/FIG. 303/TASK 77-11-00-990-803) (Ref. 77-11-51 WM). Replace the harness that has the fault (Ref. 76-00-00 MM) (Ref. AMM).
| No |
19 Replace the harness that has the fault (Ref. 76-00-00 MM) (Ref. AMM).
FADEC Discrete: N2PSOD (bit 18) / (357 / EIDIF) = 1 EFFECTIVITY:ALL
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FADEC Discrete: N1LRMD (bit 26) / (355 / SFLTS1) = 1 DESCRIPTION: This discrete is set to 1 (fault sensed) when there is not a valid N1 signal available to this FADEC. The FADEC uses an N1 value synthesized from a valid N1 for thrust control in this reversionary control mode.
POSSIBLE CAUSES: 1. Harness 2. Fan speed (N1) sensor 3. FADEC
01 Supply electrical power to the aircraft. 03 Do the troubleshooting for the FADEC Access FADEC discrete label 353 from the discretes = 1. central maintenance computer (CMC) for both -Yes FADECs (Ref. Introduction). Is N1PSFT (bit 11) and N1SSFT (bit 12) = 1 for both FADECs? | No 02 Access FADEC discrete label 354 from the 04 Do the troubleshooting for the FADEC CMC. Is XTLKFT (bit 11) = 1 and does discretes = 1. -Yes N1PSFT (bit 11) and N2SSFT label 353 (bit 14) =1, for this engine? | No |
05 Replace the FADEC that shows N1LRMD (bit 26) = 1 (Ref. 73-25-10-000-801/ 73-25-10-400-801 MM).
FADEC Discrete: N1LRMD (bit 26) / (355 / SFLTS1) = 1 EFFECTIVITY:ALL
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Maintenance Message: ND - ENG1 / ENG2 OVSPD PROT SYS DESCRIPTION: This message occurs when there is a complete loss of N1 or N2 overspeed protection on this engine or this FADEC has lost N1 or N2 overspeed protection and cannot tell whether or not the other FADEC still has N1 or N2 overspeed protection.
POSSIBLE CAUSES: 1. N1 or N2 speed sensor (primary) circuit fault 2. FADEC 3. Cross-channel datalink (CCDL) harness (W4)
01 Supply electrical power to the aircraft. Access FADEC discrete label 354 from the central maintenance computer (CMC) for both FADECs (Ref. Introduction). Does XTLKFT (bit 11) = 1 for either FADEC ?
-Yes
06 Do the troubleshooting for XTLKFT (bit 11) (Ref. 77-40-00-810-803, block 02).
| No 02 Access FADEC discrete label 356 from the 07 Do the troubleshooting for LN1OSP (bit 21) CMC for both FADECs. Does LN1OSP (bit -Yes (Ref. 77-11-00-810-825). 21) = 1 for either FADEC? | No 03 Does LN2OSP (bit 22) = 1 for either FADEC?
-Yes
08 Do the troubleshooting for LN2OSP (bit 22) (Ref. 77-11-00-810-826).
| No 05 Operate the engine at maximum thrust and 09 Do the troubleshooting for that fault (Ref. shutdown. Do not remove electrical power 77-11-00-810-825) or (Ref. 77-11-00-810-826). -Yes from the FADECs. Does LN1OSP (bit 21) or LN2OSP (bit 22) = 1 for either FADEC? | No |
10 Examine all of the harness connectors between the N1 and N2 primary sensors and the J4 receptacle of the FADEC for looseness, corrosion, contamination, or damage. Tighten, clean, or repair the harness as necessary (Ref. 70-00-00-910-804 MM).
Maintenance Message: ND - ENG1 / ENG2 OVSPD PROT SYS EFFECTIVITY:ALL
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Maintenance Message: LT-ENG1/ENG2 N1 SYS DESCRIPTION: R R
This message occurs when the signals received from the fan speed (N1) sensors by this FADEC are either different from the signals received by the other FADEC, or are not within the limits, or an open circuit condition is sensed (Ref. FIG. 301/TASK 77-11-00-990-801/FIG. 303/TASK 77-11-00-990-803).
POSSIBLE CAUSES: 1. Fan speed (N1) sensor 2. Harness 3. FADEC
01 Supply electrical power to the aircraft. Access FADEC discrete label 357 from the central maintenance computer (CMC) for both FADECs (Ref. Introduction). Does N1PDIF (bit 11) = 1?
-Yes
09 Do the troubleshooting for N1PDIF (bit 11) = 1 (Ref. 77-11-00-810-812).
| No 02 Does N1PSTD (bit 13) = 1?
-Yes
10 Do the troubleshooting for N1PSTD (bit 13) = 1 (Ref. 77-11-00-810-813).
-Yes
11 Do the troubleshooting for N1SDIF (bit 12) = 1 (Ref. 77-11-00-810-814).
-Yes
12 Do the troubleshooting for N1PSOD (bit 14) = 1 (Ref. 77-11-00-810-815).
| No 03 Does N1SDIF (bit 12) = 1? | No 04 Does N1PSOD (bit 14) = 1? | No 05 Access FADEC discrete label 353 from the 13 Do the troubleshooting for N1PSFT (bit 11) CMC for both FADECs. Does N1PSFT (bit -Yes = 1 (Ref. 77-11-00-810-802). 11) = 1? | No 06 Go to Block 07 Maintenance Message: LT-ENG1/ENG2 N1 SYS EFFECTIVITY:ALL
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07 Does N1SSFT (bit 12) = 1?
-Yes
14 Do the troubleshooting for N1SSFT (bit 12) = 1 (Ref. 77-11-00-810-803).
| No 08 Operate the engine to the maximum thrust 15 Do the troubleshooting for the fault found. practical and do a normal shutdown. Do not -Yes remove electrical power from the FADECs. Do the procedure again. Are any faults found? | No |
16 Examine all of the harness connectors for the fan speed (N1) sensor circuit, for looseness, corrosion, contamination or damage. Tighten, clean, or replace as necessary (Ref. 70-00-00-910-804 MM).
Maintenance Message: LT-ENG1/ENG2 N1 SYS EFFECTIVITY:ALL
TASK 77−11−00−810−823 Page 202 Aug 15/04
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Maintenance Message: LT-ENG1/ENG2 N2 SYS DESCRIPTION:
R R
This message occurs when either the N2 speed signals received by this FADEC are different from the signals received by the other FADEC, or the signal received from the N2 speed sensor (primary and secondary) by this FADEC is not within the limits, the signals from the N2 primary and N2 secondary are different, or an open circuit condition is sensed (Ref. FIG. 301/TASK 77-11-00-990-801/FIG. 302/TASK 77-11-00-990-802/FIG. 303/TASK 77-11-00-990-803).
POSSIBLE CAUSES: 1. N2 speed sensor 2. Harness 3. Permanent magnet alternator (PMA) 4. FADEC
01 Supply electrical power to the aircraft. Access FADEC discrete label 357 from the central maintenance computer (CMC) for both FADECs (Ref. Introduction). Does N2PDIF (bit 15) = 1?
-Yes
09 Do the troubleshooting for N2PDIF (bit 15) = 1 (Ref. 77-11-00-810-817).
| No 02 Does N2PSTD (bit 17) = 1?
-Yes
10 Do the troubleshooting for N2PSTD (bit 17) = 1 (Ref. 77-11-00-810-818).
-Yes
11 Do the troubleshooting for N2SDIF (bit 16) = 1 (Ref. 77-11-00-810-819).
-Yes
12 Do the troubleshooting for N2PSOD (bit 18) = 1 (Ref. 77-11-00-810-820).
-Yes
13 Do the troubleshooting for N2PSFT (bit 13) = 1 (Ref. 77-11-00-810-807).
| No 03 Does N2SDIF (bit 16) = 1? | No 04 Does N2PSOD (bit 18) = 1? | No 05 Access label 353 from the CMC. Does N2PSFT (bit 13) = 1? | No 06 Go to Block 07 Maintenance Message: LT-ENG1/ENG2 N2 SYS EFFECTIVITY:ALL
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07 Does N2SSFT (bit 14) = 1?
-Yes
14 Do the troubleshooting for N2SSFT (bit 14) = 1 (Ref. 77-11-00-810-827).
| No 08 Operate the engine to the maximum thrust practical and do a normal shutdown. Do not remove electrical power from the FADECs. Do the procedure above again. Are any faults found?
15 Do the troubleshooting for the fault found. -Yes
| No |
16 Examine all of the harness connectors for the N2 speed-sensor and PMA circuits, for looseness, corrosion, contamination, or damage. Tighten, clean, or replace as necessary (Ref. 70-00-00-910-804 MM).
Maintenance Message: LT-ENG1/ENG2 N2 SYS EFFECTIVITY:ALL
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FADEC Discrete: LN1OSP (bit 21) / (356 / SFLTS2) = 1 DESCRIPTION: This discrete is set = 1 when this FADEC has detected a loss of software independent N1 overspeed protection in this FADEC and either a loss of software independent N1 overspeed protection in the other FADEC or a cross-channel data link (CCDL) fault.
POSSIBLE CAUSES: 1. Fan speed (N1) sensor (primary) circuit fault 2. FADEC 3. Cross-channel data link (CCDL) harness (W4)
01 Supply electrical power to the aircraft. Access FADEC discrete label 354 from the central maintenance computer (CMC) for both FADECs (Ref. Introduction). Does XTLKFT (bit 11) = 1?
-Yes
06 Do the troubleshooting for XTLKFT (bit 11) (Ref. 77-40-00-810-803, block 02).
| No R
02 Access FADEC discrete label 360 from the 07 Do the troubleshooting for N1OSF (bit 14) CMC for both FADECs. Does N1OSF (bit 14) -Yes (Ref. 73-25-00-810-822-B01). = 1 for either FADEC? | No
R R
03 Operate the engine at maximum thrust and 08 Do the troubleshooting for N1OSF (bit 14) shutdown (Ref. AMM). Do not remove (Ref. 73-25-00-810-822-B01). electrical power from the FADECs. Access -Yes FADEC discrete label 360 from the CMC for both FADECs. Does N1OSF (bit 14) = 1 for either FADEC? | No 04 Go to Block 05
FADEC Discrete: LN1OSP (bit 21) / (356 / SFLTS2) = 1 EFFECTIVITY:ALL
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05 Access FADEC discrete label 353 from the 09 Do the troubleshooting for N1PSFT (bit 11) CMC for both FADECs. Does N1PSFT (bit 11) -Yes (Ref. 77-11-00-810-802). = 1 for either FADEC? | No |
10 Examine all of the harness connectors between the N1 sensor and the J4 receptacle of the FADEC for looseness, corrosion, contamination, or damage. Tighten, clean, or repair as necessary (Ref. 70-00-00-910-804 MM).
FADEC Discrete: LN1OSP (bit 21) / (356 / SFLTS2) = 1 EFFECTIVITY:ALL
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FADEC Discrete: LN2OSP (bit 22) / (356 / SFLTS2) = 1 DESCRIPTION: This FADEC has detected a loss of software independent N2 overspeed protection (LN2OSP) from both FADECs. This discrete is set = 1 when this FADEC has detected a loss of software independent N2 overspeed protection in this FADEC and either a loss of software independent N2 overspeed protection in the other FADEC or a cross-channel data link (CCDL) fault.
POSSIBLE CAUSES: 1. N2 speed sensor (primary) circuit fault 2. FADEC 3. Cross-channel data link (CCDL) harness (W4)
01 Supply electrical power to the aircraft. Access FADEC discrete label 354 from the central maintenance computer (CMC) for both FADECs (Ref. Introduction). Does XTLKFT (bit 11) = 1?
-Yes
05 Do the troubleshooting for XTLKFT (bit 11) (Ref. 77-40-00-810-803, block 02).
| No R
02 Access FADEC discrete label 360 from the 06 Do the troubleshooting for N2OSF (bit 15) CMC for both FADECs. Does N2OSF (bit 15) -Yes (Ref. 73-25-00-810-823-B01). = 1? | No
R R
03 Operate the engine at maximum thrust and 07 Do the troubleshooting for N2OSF (bit 15) shutdown (Ref. AMM). Do not remove (Ref. 73-25-00-810-823-B01). electrical power from the FADECs. Access -Yes FADEC discrete label 360 from the CMC for both FADECs. Does N2OSF (bit 15) = 1 for either FADEC? | No 04 Go to Block 05
FADEC Discrete: LN2OSP (bit 22) / (356 / SFLTS2) = 1 EFFECTIVITY:ALL
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04 Access FADEC discrete label 353 from the 08 Do the troubleshooting for N2PSFT (bit 13) CMC for both FADECs. Does N2PSFT (bit 13) -Yes (Ref. 77-11-00-810-807). = 1? | No |
09 Examine all of the harness connectors between the N2 sensor and the J4 receptacle of the FADEC for looseness, corrosion, contamination, or damage. Tighten, clean, or repair as necessary (Ref. 70-00-00-910-804 MM).
FADEC Discrete: LN2OSP (bit 22) / (356 / SFLTS2) = 1 EFFECTIVITY:ALL
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FADEC Discrete: N2SSFT (bit 14) / (353 / EILRU) = 1 DESCRIPTION:
R R
The FADEC monitors the signal received from its secondary N2 speed sensor for circuit continuity and range limits. This discrete is set to 1 (fault sensed) when the FADEC finds that the N2 secondary signal from the permanent magnet alternator (PMA) for this channel is not within the limits or an open circuit is detected. If available, the AE 3007 Engine Signal Test Set and Cable (CDS P/N 86690158) (Ref. TASK 73-25-10-700-801, MM) can be used for continuity/resistance testing of a suspected faulty FADEC/engine interconnect (W7) harness.
POSSIBLE CAUSES: 1. PMA 2. Harness 3. FADEC
01 Operate the engine, and do not remove electrical power from the FADECs. Access FADEC discrete labels 353 from the central maintenance computer (CMC) for both FADECs (Ref. Introduction). Does N2SSFT (bit 14)= 1?
10 Examine all the harness connectors between the FADEC J4 and the PMA receptacles for damage, corrosion, or -No contamination. Repair or clean as necessary (Ref. 70-00-00-910-804 MM).
| Yes 02 Remove and install the harness connectors 11 Examine the harness connectors at the at the FADEC J4 and PMA receptacles (Ref. FADEC J4 and the PMA receptacles for FIG. 304/TASK 77-11-00-990-804) (Ref. damage, corrosion, or contamination. Repair 76-12-50/76-12-51 WM). Rotate the FADEC -Yes or clean as necessary (Ref. 70-00-00-910-804 reset/select switch to the RESET position. MM). Operate the engine. Does N2SSFT (bit 14) = 0? | No 03 Examine the stator (Ref. 74-11-15-200-801 12 Replace the damaged alternator stator MM) and rotor (Ref. 74-11-10-200-801 MM) for (Ref. 74-11-15-000-801/74-11-15-400-801 MM) -Yes foreign objects or damage. Are foreign objects or rotor (Ref. 74-11-10-000-801/ or damage to the stator or rotor found? 74-11-10-400-801 MM). | No 04 Go to Block 05
FADEC Discrete: N2SSFT (bit 14) / (353 / EILRU) = 1 EFFECTIVITY:ALL
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05 Install the PMA stator from the other engine 13 Remove the stator from service (Ref. (Ref. 74-11-15-000-801/74-11-15-400-801 74-11-15-000-801/74-11-15-400-801 MM). MM). (Do not install the PMA from this engine -Yes on the other engine or damage to the FADECs can occur.) Is the fault removed? | No 06 Examine the harness connectors between the FADEC (J4) and the PMA receptacle for corrosion, contamination, or damage (Ref. FIG. 304/TASK 77-11-00-990-804) (Ref. 76-12-50/76-12-51 WM). Are the connectors dirty or damaged?
-Yes
14 Clean the connectors (Ref. 70-00-00-910-804 MM) or replace the harness (Ref. 76-00-00 MM) (Ref. AMM).
| No 07 Do a test for continuity/resistance (1 ohm max./harness), internal shorts, and shorts to ground (1,000 ohms min.) on the FADEC A/B (W11/14) and the FADEC/engine interconnect (W7) harnesses (PMA/FADEC circuits) (Ref. FIG. 304/TASK 77-11-00-990-804) (Ref. 76-12-50/ 76-12-51 WM). Do the harnesses test satisfactorily?
15 Replace the harness that has the fault (Ref. 76-00-00 MM) (Ref. AMM). -No
| Yes 08 Go to block 09
FADEC Discrete: N2SSFT (bit 14) / (353 / EILRU) = 1 EFFECTIVITY:ALL
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09 Interchange the position of the FADECs 16 Replace the FADEC that has the fault (Ref. (Ref. 73-25-10-000-801/73-25-10-400-801 73-25-10-000-801/73-25-10-400-801 MM). MM). Rotate the FADEC reset/select switch to -Yes the RESET position. Operate the engine. Do not remove electrical power from the FADECs. Does the fault move to the opposite channel? | No |
17 Do a test for continuity/resistance (1 ohm max./harness), internal shorts, and shorts to ground (1,000 ohms min.) on the FADEC A/B (W11/14) and the FADEC/engine interconnect (W7) harnesses (Ref. FIG. 303/TASK 77-11-00-990-803) (Ref. 76-12-50/76-12-51 WM). Replace the harness that has the fault (Ref. 76-00-00 MM) (Ref. AMM). .
FADEC Discrete: N2SSFT (bit 14) / (353 / EILRU) = 1 EFFECTIVITY:ALL
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N1 Sensor / FADEC Interface Diagram FIG. 301/TASK 77-11-00-990-801
R EFFECTIVITY:ALL
77−11−TASK SUPPORT Page 301 Aug 15/04
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N2 Sensor / FADEC Interface Diagram FIG. 302/TASK 77-11-00-990-802
R EFFECTIVITY:ALL
77−11−TASK SUPPORT Page 302 Aug 15/04
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Engine Wiring Diagram FIG. 303/TASK 77-11-00-990-803
R EFFECTIVITY:ALL
77−11−TASK SUPPORT Page 303 Aug 15/04
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Permanent Magnet Alternator / FADEC Interface Diagram FIG. 304/TASK 77-11-00-990-804
R EFFECTIVITY:ALL
77−11−TASK SUPPORT Page 304 Aug 15/04
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Maintenance Message: ENG1/ENG2 ITT SENSOR FAIL or ST-ENG1/ENG2 ITT SYS DESCRIPTION: R
This message occurs when the signal received from the turbine interstage thermocouples by this FADEC is not within the limits, or is different from the signal received from the other FADEC (Ref. FIG. 301/TASK 77-21-00-990-801).
POSSIBLE CAUSES: 1. Harness 2. Turbine interstage thermocouples 3. FADEC
01 Supply electrical power to the aircraft. 04 Do the troubleshooting for ITTFLT (bit 15) Access FADEC discrete label 353 from the = 1 (Ref. 77-21-00-810-802). central maintenance computer (CMC) for both -Yes FADECs (Ref. Introduction). Does ITTFLT (bit 15) = 1? | No 02 Access FADEC discrete label 357 from the 05 Do the troubleshooting for ITTDIF (bit 19) CMC (Ref. Introduction). Does ITTDIF (bit 19) -Yes = 1 (Ref. 77-21-00-810-804). = 1? | No 03 Operate the engine to the maximum thrust practical and do a normal shutdown. Do not remove electrical power from the FADECs. Do the procedures again. Is a fault found?
06 Examine all of the harness connectors for the ITT circuit, for corrosion, contamination, or -No damage. Clean or replace as necessary. Apply Stabilant 22 to harness connector pins (Ref. 70-00-00-910-804 MM).
| Yes |
07 Perform the troubleshooting for that fault.
Maintenance Message: ENG1/ENG2 ITT SENSOR FAIL or ST-ENG1/ENG2 ITT SYS EFFECTIVITY:ALL
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FADEC Discrete: ITTFLT (bit 15) / (353 / EILRU) = 1 DESCRIPTION:
R R
The FADEC monitors the signal received from the turbine interstage thermocouples (set of eight per channel). This discrete is set to 1 (fault sensed) when the signal is not within the limits (38-1093 °C with the engine running). If available, the AE 3007 Engine Signal Test Set and Cable (CDS P/N 86690158) (Ref. TASK 73-25-10-700-801, MM) can be used for continuity/resistance testing of a suspected faulty FADEC/engine interconnect (W7) harness.
POSSIBLE CAUSES: 1. Harness 2. Turbine interstage thermocouples 3. FADEC
01 Examine all of the harness connectors between the FADEC J4 receptacle and the INTA(B) connector, on the outer bypass duct, for corrosion, contamination, damage and correct installation (Ref. FIG. 301/TASK 77-21-00-990-801/FIG. 303/TASK 77-21-00-990-803) (Ref. 77-11-52 WM). Are the connectors dirty, damaged or loose?
04 Clean the connectors (Ref. 70-00-00-910-804 MM) or replace the harness (Ref. 76-00-00 MM) (Ref. AMM) as necessary. -Yes
| No 02 Interchange the position of the FADECs 05 Replace the FADEC that has the fault (Ref. (Ref. 73-25-10-000-801/73-25-10-400-801 73-25-10-000-801/73-25-10-400-801 MM). MM). Rotate the FADEC reset/select switch to -Yes the RESET position. Does the fault move to the opposite channel? | No 03 Do a test for continuity/resistance, internal shorts, and shorts to ground on the W11/14, W12/13, W7 and thermocouple wiring harnesses (Ref. FIG. 301/TASK 77-21-00-990-801). Do the harnesses test satisfactorily?
06 Do the test of the turbine interstage thermocouples (Ref. 77-21-10-700-801 MM). Replace the thermocouples as necessary -Yes (Ref. 77-21-10-000-801/77-21-10-400-801 MM).
| No |
07 Replace the harness that has the fault (Ref. 76-00-00 MM) (Ref. AMM).
FADEC Discrete: ITTFLT (bit 15) / (353 / EILRU) = 1 EFFECTIVITY:ALL
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FADEC Discrete: TRMFMD (bit 27) / (353 / EILRU) = 1 DESCRIPTION:
R R
The FADEC monitors the signal received from the ITT trim plug. This discrete is set to 1 (fault sensed) when the signal sensed is not within the limits. If available, the AE 3007 Engine Signal Test Set and Cable (CDS P/N 86690158) (Ref. TASK 73-25-10-700-801, MM) can be used for continuity/resistance testing of a suspected faulty FADEC/engine interconnect (W7) harness.
POSSIBLE CAUSES: 1. Harness 2. ITT trim plug 3. FADEC
01 Interchange the position of the TRIMA(B) harness connectors at the ITT trim plug. Rotate the FADEC reset/select switch to the RESET position. Does the fault move to the opposite channel?
-Yes
03 Replace the ITT trim plug (Ref. 77-21-25-000-801/77-21-25-400-801 MM).
| No 02 Interchange the position of the FADECs 04 Replace the FADEC that has the fault (Ref. (Ref. 73-25-10-000-801/73-25-10-400-801 73-25-10-000-801/73-25-10-400-801 MM). MM). Rotate the FADEC reset/select switch to -Yes the RESET position. Does the fault move to the opposite channel? | No |
05 Do a test for continuity/resistance, internal shorts, and shorts to ground on the W11/14 and the W7 harnesses. 1 ohm maximum resistance, pin-to-pin (Ref. FIG. 302/TASK 77-21-00-990-802) (Ref. 77-11-52 WM). Replace the harness that has the fault (Ref. 76-00-00 MM) (Ref. AMM).
FADEC Discrete: TRMFMD (bit 27) / (353 / EILRU) = 1 EFFECTIVITY:ALL
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FADEC Discrete: ITTDIF (bit 19) / (357 / EIDIF) = 1 DESCRIPTION:
R R
This discrete is set to 1 (fault sensed) when the signal received from the turbine interstage thermocouples (set of eight per channel) by this FADEC is different (more than 111 °C) from that received by the other FADEC. If available, the AE 3007 Engine Signal Test Set and Cable (CDS P/N 86690158) (Ref. TASK 73-25-10-700-801, MM) can be used for continuity/resistance testing of a suspected faulty FADEC/engine interconnect (W7) harness.
POSSIBLE CAUSES: 1. Harness 2. Thermocouples 3. FADEC
01 Operate both engines at the same thrust 11 Replace the FADEC showing ITTDIF (bit level. Access the FADEC analog label from 19) = 1 (Ref. the CMC for both FADECs on both engines. 73-25-10-000-801/73-25-10-400-801 MM). Record the values for ITT. (Note: The value that has the greatest difference compared to -No the other three indicates a fault with the circuit.) Are the ITT values for the engine showing ITTDIF (bit 19) = 1 different by more than 111 °C? | Yes 02 Examine all of the harness connectors 12 Go to block 06. between the FADEC J4 receptacle and the INTA(B) connector for corrosion, contamination, damage, and correct installation -Yes (Ref. FIG. 303/TASK 77-21-00-990-803) (Ref. 77-11-52 WM). Are the connectors dirty, damaged, or loose? | No 03 Do a test for continuity/resistance, internal 13 Replace the harness that has the fault (Ref. shorts, and shorts to ground on the W11/14, 76-00-00 MM) (Ref. AMM). W12/13, W7, and thermocouple wiring -No harnesses (Ref. FIG. 301/TASK 77-21-00-990-801) (Ref. 77-11-52 WM). Do the harnesses test satisfactorily? | Yes 04 Go to Block 05 FADEC Discrete: ITTDIF (bit 19) / (357 / EIDIF) = 1 EFFECTIVITY:ALL
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05 Do the test of the turbine interstage thermocouples (Ref. 77-21-10-700-801 MM). Do the thermocouples test satisfactorily?
14 Replace the FADEC (Ref. -Yes 73-25-10-000-801/73-25-10-400-801 MM).
| No |
15 Replace the turbine interstage thermocouple(s) that has the fault (Ref. 77-21-10-000-801/77-21-10-400-801 MM).
FADEC Discrete: ITTDIF (bit 19) / (357 / EIDIF) = 1 EFFECTIVITY:ALL
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06 Clean, replace, or tighten the harness as necessary. Apply Stabilant 22 to the harness connector pins (Ref. 70-00-00-910-804 MM). 07 Operate both engines at the same thrust level. Access the FADEC discrete label from the CMC. Does ITTDIF (bit19)=1?
-No
16 Return the engine to service.
| Yes 08 With the engines still operating, access the 17 Replace the FADEC showing ITTDIF (bit FADEC analog label from the CMC for both 19) = 1 (Ref. FADECs on both engines. Record the values 73-25-10-000-801/73-25-10-400-801 MM). for ITT. (Note: The value that has the greatest -No difference compared to the other three indicates a fault with the circuit.) Are the ITT values for the engine showing ITTDIF (bit 19) = 1 different by more than 111 °C? | Yes 09 Do a test for continuity/resistance, internal 18 Replace the harness that has the fault (Ref. shorts, and shorts to ground on the W11/14, 76-00-00 MM) (Ref. AMM). W12/13, W7, and thermocouple wiring -No harnesses (Ref. FIG. 301/TASK 77-21-00-990-801) (Ref. 77-11-52 WM). Do the harnesses test satisfactorily? | Yes 10 Do the test of the turbine interstage thermocouples (Ref. 77-21-10-700-801 MM). Do the thermocouples test satisfactorily?
19 Replace the FADEC (Ref. -Yes 73-25-10-000-801/73-25-10-400-801 MM).
| No |
20 Replace the turbine interstage thermocouple(s) that has the fault (Ref. 77-21-10-000-801/77-21-10-400-801 MM).
FADEC Discrete: ITTDIF (bit 19) / (357 / EIDIF) = 1 EFFECTIVITY:ALL
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FADEC Discrete: TRMDMX (bit 25) / (357 / EIDIF) = 1 DESCRIPTION:
R R
This discrete is set to 1 (fault sensed) when the signal received from the ITT trim plug by this FADEC is different from that received by the other FADEC or the ITT trim plug signal is not being received from the other FADEC. If available, the AE 3007 Engine Signal Test Set and Cable (CDS P/N 86690158) (Ref. TASK 73-25-10-700-801, MM) can be used for continuity/resistance testing of a suspected faulty FADEC/engine interconnect (W7) harness.
POSSIBLE CAUSES: 1. Harness 2. ITT trim plug 3. FADEC
01 Supply electrical power to the aircraft. Access FADEC discrete label 354 from the central maintenance computer (CMC) for both FADECs (Ref. Introduction). Does XTLKFT (bit 11) = 1 for either FADEC?
-Yes
06 Do the troubleshooting for XTLKFT (bit 11) (Ref. 77-40-00-810-803, block 02).
| No 02 Access the FADEC analog label from the CMC for both FADECs (Ref. Introduction). Are the values for TRMMDR different ?
07 Replace the FADEC showing TRMDMX (bit -No 25) = 1 (Ref. 73-25-10-000-801/73-25-10-400-801 MM).
| Yes 03 Interchange the harness connectors TRIMA 08 Replace the ITT trim plug (Ref. and TRIMB on the ITT trim plug (Ref. FIG. 77-21-25-000-801/77-21-25-400-801 MM). 302/TASK 77-21-00-990-802) (Ref. 77-11-52 WM). Access the FADEC analog label from -Yes the CMC, for both FADECs (Ref. Introduction). Do the values for TRMMDR move to the opposite channel? | No 04 Go to Block 05
FADEC Discrete: TRMDMX (bit 25) / (357 / EIDIF) = 1 EFFECTIVITY:ALL
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05 Interchange the position of the FADECs 09 Replace the FADEC with the TRMMDR (Ref. 73-25-10-000-801/73-25-10-400-801 value that has the greatest difference, MM). Access the FADEC analog label from the compared to the resistance value of the ITT -Yes CMC, for both FADECs. Do the values for trim plug. (Ref. FIG. 302/TASK TRMMDR move to the opposite channel? 77-21-00-990-802) (Ref. 73-25-10-000-801/ 73-25-10-400-801 MM). | No |
10 Find which channel has the greatest difference between TRMMDR and the resistance value of the ITT trim plug. Do a test for continuity/resistance, internal shorts, and shorts to ground on the harness, between the FADEC and the ITT trim plug, for the channel with the greatest difference. Maximum resistance of 1 ohm, pin-to-pin (Ref. FIG. 302/TASK 77-21-00-990-802) (Ref. 77-11-52 WM).
FADEC Discrete: TRMDMX (bit 25) / (357 / EIDIF) = 1 EFFECTIVITY:ALL
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FADEC Discrete: TRMEDF (bit 26) / (357 / EIDIF) = 1 DESCRIPTION:
R R
This discrete is set to 1 (fault sensed) when the signal received from the ITT trim plug by this FADEC is different from the trim value in this FADEC's memory (EEPROM). If available, the AE 3007 Engine Signal Test Set and Cable (CDS P/N 86690158) (Ref. TASK 73-25-10-700-801, MM) can be used for continuity/resistance testing of a suspected faulty FADEC/engine interconnect (W7) harness.
POSSIBLE CAUSES: 1. Harness 2. ITT trim plug 3. FADEC
01 Rotate the FADEC reset/select switch to the RESET position. Access FADEC discrete label 357 from the central maintenance computer (CMC) (Ref. Introduction). Does TRMEDF (bit 26) = 1?
05 Examine the harness connectors between the FADEC and the ITT trim plug for corrosion, contamination, or damage (Ref. -Yes 70-00-00-910-804 MM). Clean or replace the harness as necessary (Ref. 76-00-00 MM) (Ref. AMM).
| No 02 Access the FADEC analog label from the CMC (Ref. Introduction). Is TRMMDR the same as the resistance value indicated by the part number of the ITT trim plug (Ref. FIG. 302/TASK 77-21-00-990-802) (Ref. 77-11-52 WM)?
06 Replace the FADEC that has the fault (Ref. 73-25-10-000-801/73-25-10-400-801 MM). -Yes
| No 03 Go to block 04
FADEC Discrete: TRMEDF (bit 26) / (357 / EIDIF) = 1 EFFECTIVITY:ALL
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04 Interchange the harness connectors TRIMA 07 Replace the ITT trim plug (Ref. and TRIMB on the ITT trim plug. Rotate the 77-21-25-000-801/77-21-25-400-801 MM). FADEC reset/select switch to the RESET position. Access FADEC discrete label 357 -Yes from the CMC, for both FADECs. Does TRMEDF (bit 26) = 1 move to the opposite channel? | No |
08 Do a test for continuity/resistance, internal shorts, and shorts to ground on the harness between the FADEC and the ITT trim plug (Ref. FIG. 302/TASK 77-21-00-990-802) (Ref. 77-11-52 WM). Maximum resistance of 1 ohm, pin-to-pin. Replace the harness that has the fault (Ref. 76-00-00 MM) (Ref. AMM).
FADEC Discrete: TRMEDF (bit 26) / (357 / EIDIF) = 1 EFFECTIVITY:ALL
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Observed Fault: Sudden Increase in ITT DESCRIPTION: This fault occurs when the ITT during steady-state condition is above the value usually seen, for the same operating conditions, or the ITT is above the limit, in any mode of operation not found in ITT trend data.
POSSIBLE CAUSES: 1. Compressor bleed-air leakage 2. Engine internal surfaces dirty 3. ITT-sensor circuit fault 4. Aircraft pneumatic-system fault 5. Compressor/turbine damaged/eroded 6. FADEC 7. 9th stage compressor-air-bleed check valve 8. Cracked or broken fuel nozzle gaskets
01 Download central maintenance computer (CMC) exceedance data (Ref. Introduction). For AE 3007A, A1/1: was ITT over 921 °C? For AE 3007A1, A1/3, A3, A1P: was ITT over 948 °C? For AE 3007A1E: was ITT over 992 °C on takeoff, or over 970°C in flight?
18 Go to block 13. -Yes
| No 02 Supply electrical power to the aircraft. Access the maintenance messages from the central maintenance computer (CMC) (Ref. Introduction). Is their a message for the ITT circuit?
-Yes
19 Do the troubleshooting for the maintenance message (Ref. 77-21-00-810-801).
| No 03 Access the maintenance messages from the CMC. Is there an aircraft pneumatic-systems message?
20 Do the troubleshooting for the maintenance -Yes message (Ref. 36-11-00/201 EMB FIM).
| No 04 Go to Block 05
Observed Fault: Sudden Increase in ITT EFFECTIVITY:ALL
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05 Examine the fan for foreign object damage (Ref. 05-00-200-804 MM). Is there damage?
21 Do the borescope inspection of the compressor section (Ref. 72-30-00-200-801 -Yes MM). Repair/replace the damaged fan blades. Remove the engine if there is any damage or wear that is more than the serviceable limits.
| No 06 Examine all of the aircraft mounted 22 Replace the parts that have a fault (Ref. compressor bleed-air tubes, valves, and 36-11-09/401 AMM). -Yes manifolds attached to the engine for damage or leaks. Is a fault found? | No 07 Examine the customer-services outer 23 Replace the damaged customer-services manifold and gasket for damage or leaks (Ref. -Yes outer manifold and/or gasket (Ref. 75-31-30-200-801 MM). Is fault found? 75-31-30-000-801/ 75-31-30-400-801 MM). | No 08 Do the test of the upper (if applicable) and lower compressor air-bleed valves (CABV) (Ref. 75-31-10-700-801 MM). Are the CABVs and tubes serviceable?
24 Clean (Ref. 75-31-10-100-801 MM), repair (Ref. 75-31-10-300-801 MM), or replace (Ref. -No 75-31-10-000-801/ 75-31-10-400-801 MM) the CABV(s) or replace the tube(s) (Ref. 75-00-00-000-801 / 75-00-00-400-801 MM).
| Yes 09 Examine the compressor-acceleration bleed-control valve (CABCV) (Ref. 75-31-00-100-801 MM). Is the CABCV dirty?
25 Clean the compressor bleed system (Ref. -Yes 75-31-00-100-801 MM).
| No 10 Examine all 16 fuel nozzle gaskets for cracks or missing pieces. Is there damage found?
26 Replace the damaged gasket(s) (Ref. -Yes 73-11-10-000-801/73-11-10-400-801 MM).
| No 11 Go to block 12.
Observed Fault: Sudden Increase in ITT EFFECTIVITY:ALL
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R R R R R
12 Do the test of the compressor-bleed system 27 Troubleshoot the aircraft bleed-air system (Ref. 75-31-00-700-802, MM). Was the ITT (Ref. AMM). difference more than 5° C (9° F) between the -No performance runs with and without the compressor-bleed cover plates? | Yes |
28 Go to block 15.
Observed Fault: Sudden Increase in ITT EFFECTIVITY:ALL
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13 Do the inspection for ITT over the limit (Ref. 77-00-00-200-801 MM). Can the engine be returned to service?
-Yes
29 Return the engine to service.
| No | 14 Download the Flight Data Recorder data (Ref. 31-31-00-700-803A AMM) and do the inspection for ITT over the limit (Ref. 77-00-00-200-801 MM). Can the engine be returned to service?
30 Return the engine to service. -Yes
| No |
31 Replace the engine (Ref. 71-00-00/401 AMM).
Observed Fault: Sudden Increase in ITT EFFECTIVITY:ALL
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15 Examine the 9th-stage air-bleed check valve (check valve) (Ref. 36-11-01/601 AMM). Is the check valve serviceable?
32 Replace the check valve (Ref. -No 36-11-01/401 AMM).
| Yes 16 Clean and flush the internal surfaces of the engine (Ref. 72-00-00-100-801/ 72-00-00-100-802 MM). Do the performance run of the engine (Ref. 72-00-00-700-801 MM). Is the ITT high?
-No
33 Decrease the interval for cleaning and flushing the internal surfaces of engine.
| Yes | 17 Do the borescope inspection of the compressor section (Ref. 72-30-00-200-801 MM). Is the engine serviceable?
34 Replace the engine (Ref. 71-00-00/401 -No AMM).
| Yes |
35 Do the borescope inspection of the turbine section (Ref. 72-50-00-200-801 MM). Replace the engine if there is damage or wear that is more than the serviceable limits.
Observed Fault: Sudden Increase in ITT EFFECTIVITY:ALL
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Maintenance Message: LT-ENG1/ENG2 ITT TRIM SYS DESCRIPTION: This message occurs when the signal received from the ITT trim plug is not within the limits, the signal from the ITT plug by this FADEC is different from that received by the other FACEC, the signal is different from the value in this FADECs memory, or the FADEC is not receiving data correctly from the opposite FADEC on the same engine.
POSSIBLE CAUSES: 1. Harness 2. ITT trim plug 3. FADEC
01 Access the central maintenance computer (CMC) Maintenance Messages (Ref. Introduction). Did a ND-ENG1/ENG2 COMM A/B SYS message occur at the same time as the LT-ENG1/ENG2 ITT TRIM SYS message?
05 Do the troubleshooting for maintenance ND-ENG1/ENG2 COMM A/B SYS (Ref. -Yes 77-40-00-810-807).
| No 02 Access FADEC discrete label 357 from the 06 Do the troubleshooting for TRMDMX (bit -Yes CMC. Does TRMDMX (bit 25) = 1? 25) = 1 (Ref. 77-21-00-810-805). | No 03 Does TRMEDF (bit 26) = 1?
-Yes
07 Do the troubleshooting for TRMEDF (bit 26) = 1 (Ref. 77-21-00-810-806).
| No 04 Access FADEC discrete label 353 from the 08 Do the troubleshooting for TRMFMD (bit -Yes CMC. Does TRMFMD (bit 27) = 1? 27) = 1 (Ref. 77-21-00-810-803). | No |
R R
09 Examine all of the harness connectors for the ITT trim resistor circuit for looseness, corrosion, contamination or damage (Ref. FIG. 303/TASK 77-21-00-990-803). Tighten, clean, or replace as necessary (Ref. 70-00-00-910-804 MM).
Maintenance Message: LT-ENG1/ENG2 ITT TRIM SYS EFFECTIVITY:ALL
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Observed Fault: ITT indication difference (split) between left and right engines (static) DESCRIPTION:
R R
This fault is observed when the EICAS displayed ITT indication between the left and right engines differ by more than 5 °C when the engines are static (not running) and the engine is cooled to ambient temperature. This condition is best discovered prior to the first flight of the day. If available, the AE 3007 Engine Signal Test Set and Cable (CDS P/N 86690158) (Ref. TASK 73-25-10-700-801, MM) can be used for continuity/resistance testing of a suspected faulty FADEC/engine interconnect (W7) harness.
POSSIBLE CAUSES: 1. ITT sensor 2. Thermocouple harness 3. FADEC 4. External engine control harness 5. Internal engine control harness 6. ITT trim plug fault/improperly installed
01 Examine all of the harness connectors between the FADEC J4 receptacle and the ITTA(B) connector for looseness, damage, or corrosion (Ref. FIG. 301/TASK 77-21-00-990-801/FIG. 303/TASK 77-21-00-990-803). Is a fault found?
-Yes
09 Clean or tighten the connector (Ref. 70-00-00-910-804 MM) or replace the harness (Ref. 76-00-00 MM).
| No 02 Supply electrical power to the aircraft. Access FADEC discrete label 353 from the central maintenance computer (CMC) (Ref. Introduction). Does ITTFLT (bit 15) or TRMFMD (bit 27) = 1?
10 Do the troubleshooting for the message(s) shown (Ref. 77-21-00-810-802) or (Ref. -Yes 77-21-00-810-803).
| No 03 Access FADEC discrete label 357 from the 11 Do the troubleshooting for the message(s) CMC. Does ITTDIF (bit 19), TRMDMX (bit 25), shown (Ref. 77-21-00-810-804), (Ref. -Yes or TRMEDF (bit 26) = 1? 77-21-00-810-805), or (Ref. 77-21-00-810-806). | No 04 Go to Block 05
Observed Fault: ITT indication difference (split) between left and right engines (static) EFFECTIVITY:ALL
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05 For the engine indicating the highest temperature, pull the circuit breaker (CB) for FADEC A and record the ITT value indicated by FADEC B. Push in the CB for FADEC A and pull the CB for FADEC B. Record the ITT value indicated by FADEC A. Record the outside ambient air temperature. Compare the recorded ITT values for FADECs A and B with the recorded ambient air temperature. Is there a difference in temperature values?
12 Make sure that the appropriate CBs are fully pushed in, or pulled out, and that the correct FADEC is being isolated and recorded. -No
| Yes 06 For the FADEC that indicates the highest 13 Replace the thermocouple(s) that has a temperature, do the ITT thermocouple test -Yes fault (Ref. 77-21-10-000-801/77-21-10-400-801 (Ref. 77-21-10-700-801 MM). Is a fault found? MM). | No 07 Do the test and fault isolation of the 14 Replace the harness (Ref. thermocouple wiring harness. Is a fault found? -Yes 77-21-15-000-801/77-21-15-400-801 MM) (Ref. 77-21-20-000-801/77-21-20-400-801 MM). | No 08 Interchange the position of this FADEC with 15 Replace the FADEC that has the fault (Ref. a FADEC from the other engine (Ref. 73-25-10-000-801/73-25-10-400-801 MM). 73-25-10-000-801/73-25-10-400-801 MM). Move the FADEC reset/select switch to the -Yes RESET position. Does the ITT indication for this FADEC match the ITT indication for the other FADEC (on this engine) within -5 °C? | No | 16 Do a test for continuity/resistance (1 ohm max./harness), internal shorts to ground (1,000 ohms min.) on the harnesses between the FADEC J4 receptacle, the ITT trim plug and the ITT harness (Ref. FIG. 301/TASK 77-21-00-990-801/FIG. 302/TASK 77-21-00-990-802/FIG. 303/TASK 77-21-00-990-803). Replace the harness that has the fault. Observed Fault: ITT indication difference (split) between left and right engines (static) EFFECTIVITY:ALL
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Observed Fault: ITT indication difference (split) between left and right engines (static) EFFECTIVITY:ALL
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Observed Fault: ITT Fluctuations DESCRIPTION:
R R
This fault is observed when the EICAS ITT indication appears to fluctuate by at least 25°C when the engine is running at a steady TLA position. This fault can cause the thrust to increase or decrease for the N1 and/or N2. If available, the AE 3007 Engine Signal Test Set and Cable (CDS P/N 86690158) (Ref. TASK 73-25-10-700-801, MM) can be used for continuity/resistance testing of a suspected faulty FADEC/engine interconnect (W7) harness.
POSSIBLE CAUSES: 1. Thermocouple harness connections 2. Thermocouple 3. Thermocouple harness 4. External engine control harness
01 Are the ITT fluctuations associated with noticeable N1, N2 or thrust oscillations?
-Yes
12 Do the FIM task for thrust oscillations (Ref. 72-00-00-810-804).
-Yes
13 Do the FIM task for CMC message ST-ENG1(2) ITTSYS (Ref. 77-21-00-810-801).
| No 02 Access CMC data. Is the maintenance message ST-ENG1(2) ITTSYS Displayed? | No 03 Is there a split of EICAS indicated ITT of 14 Do the troubleshooting for split ITT more than 5°C when the engines are static and -Yes readings (Ref. 77-21-00-810-810). at ambient temperature? | No 04 Examine all of the harness connectors between the FADEC J4 receptacle and the INTA(B) connector for corrosion, contamination, damage, and correct installation -Yes (Ref. FIG. 303/TASK 77-21-00-990-803) (Ref. 77-11-52 WM). Are the connectors dirty, damaged, or loose?
15 Clean, replace, or tighten the harness as necessary. Apply stabilant 22 to the harness connector pins (Ref. 70-00-00-910-804 MM) then go to block 08.
| No 05 Go to block 06
Observed Fault: ITT Fluctuations EFFECTIVITY:ALL
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06 Do a test for continuity/resistance, internal 16 Replace the harness that has the fault (Ref. shorts, and shorts to ground on the W11/14, 76-00-00 MM) (Ref. AMM). W12/13, W7, and thermocouple wiring -No harnesses (Ref. FIG. 301/TASK 77-21-00-990-801) (Ref. 77-11-52 WM). Do the harnesses test satisfactorily? | Yes 07 Do the test of the turbine interstage thermocouples (Ref. 77-21-10-700-801 MM). Do the thermocouples test satisfactorily?
17 Replace the FADEC (Ref. -Yes 73-25-10-000-801/73-25-10-400-801 MM).
| No |
18 Replace the turbine interstage thermocouple(s) that has the fault (Ref. 77-21-10-000-801/77-21-10-400-801 MM).
Observed Fault: ITT Fluctuations EFFECTIVITY:ALL
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08 Operate engines to power seting where ITT fluctuations occured. Cycle FADECs. Are ITT fluctuations still present?
-No
19 Return the engine to service.
| Yes 09 With the engines still operating, access the 20 Replace the FADEC showing ITTDIF (bit FADEC analog label from the CMC for both 19) = 1 (Ref. FADECs on both engines. Record the values 73-25-10-000-801/73-25-10-400-801 MM). for ITT. (Note: The value that has the greatest -No difference compared to the other three indicates a fault with the circuit.) Are the ITT values for the engine showing ITTDIF (bit 19) = 1 different by more than 55 °C? | Yes 10 Do a test for continuity/resistance, internal shorts, and shorts to ground on the W11/14, W12/13, W7, and thermocouple wiring harnesses (Ref. FIG. 301/TASK 77-21-00-990-801) (Ref. TASK 77-21-10-700-802 MM) (Ref. 77-11-52 WM). Do the harnesses test satisfactorily?
21 Replace the harness that has the fault (Ref. 76-00-00 MM) (Ref. AMM). -No
| Yes 11 Do the test of the turbine interstage thermocouples (Ref. 77-21-10-700-801/77-21-10-700-802 MM). Do the thermocouples test satisfactorily?
-Yes
22 Replace the FADEC (Ref. 73-25-10-000-801/73-25-10-400-801 MM).
| No |
23 Replace the turbine interstage thermocouple(s) that has the fault (Ref. 77-21-10-000-801/77-21-10-400-801 MM).
Observed Fault: ITT Fluctuations EFFECTIVITY:ALL
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Turbine Interstage Thermocouples / FADEC Interface Diagram FIG. 301/TASK 77-21-00-990-801
R EFFECTIVITY:ALL
77−21−TASK SUPPORT Page 301 Aug 15/04
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ITT Trim Plug / FADEC Interface Diagram FIG. 302/TASK 77-21-00-990-802
R EFFECTIVITY:ALL
77−21−TASK SUPPORT Page 302 Aug 15/04
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Engine Wiring Diagram FIG. 303/TASK 77-21-00-990-803
R EFFECTIVITY:ALL
77−21−TASK SUPPORT Page 303/304 Aug 15/04
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FADEC Discrete: NCNCFT (bit 12) / (354 / CFPLRU) = 1 DESCRIPTION: R
This message occurs when this FADEC is not receiving data correctly from the same channel FADEC, on the opposite engine. The FADEC monitors the validity and the rate of the data received (Ref. FIG. 302/TASK 77-40-00-990-802).
POSSIBLE CAUSES: 1. Internacelle data bus/harness 2. FADEC
01 Supply electrical power to the aircraft. Access FADEC discrete label 354 from the central maintenance computer (CMC) for both FADECs (Ref. Introduction). Does NCNCFT (bit 12) = 1?
04 Examine both harness connectors at the FADEC J2 receptacles (this engine and the other engine) for damage, corrosion or -No contamination. Clean or repair them as necessary (Ref. 20-50-00 WM) (Ref. 76-12-54 WM).
| Yes 02 Replace the FADEC showing NCNCFT (bit 05 Remove the FADEC that has the fault from 12) = 1 with the other FADEC from this engine service (Ref. -Yes (Ref. 73-25-10-000-801/73-25-10-400-801 73-25-10-000-801/73-25-10-400-801 MM). MM). Is the fault removed? | No 03 Replace the FADEC for the other engine, same channel as the one showing NCNCFT (bit 12) = 1 (Ref. 73-25-10-000-801/ 73-25-10-400-801 MM). Is the fault removed?
06 Remove the FADEC that has the fault from service (Ref. -Yes 73-25-10-000-801/73-25-10-400-801 MM).
| No |
07 Do the troubleshooting on the data bus/harness (Ref. 76-12-54 WM). Replace the harness that has the fault.
FADEC Discrete: NCNCFT (bit 12) / (354 / CFPLRU) = 1 EFFECTIVITY:ALL
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FADEC Discrete: XTLKFT (bit 11) / (354 / CFPLRU) = 1 DESCRIPTION: R
This discrete is set to 1 (fault sensed) when this FADEC is not receiving data correctly from the opposite FADEC. The FADEC monitors the validity and the rate of the data received (Ref. FIG. 301/TASK 77-40-00-990-801).
POSSIBLE CAUSES: 1. Inter-FADEC harness 2. FADEC
01 Supply electrical power to the aircraft. Access FADEC discrete label 354 from the central maintenance computer (CMC) for both FADECs (Ref. Introduction). Does XTLKFT (bit 11) = 1?
04 Replace the W4 harness (Ref. 76-12-54 WM). Rotate the FADEC reset/select switch to -Yes the RESET position to remove the fault (XTLKFT (bit 11) = 0).
| No 02 Install the W4 harness from the FADEC set 05 Replace the W4 harness (Ref. 76-12-54 for the other engine. Is the fault removed WM). Rotate the FADEC reset/select switch to -Yes (XTLKFT (bit 11) = 0)? the RESET position to remove the fault (XTLKFT (bit 11) = 0). | No 03 Replace the FADEC showing XTLKFT (bit 11) = 1 with a FADEC from the other engine (Ref. 73-25-10-000-801/73-25-10-400-801 MM). Is the fault removed?
06 Remove the FADEC that has the fault from service (Ref. -Yes 73-25-10-000-801/73-25-10-400-801 MM).
| No |
07 Replace the other FADEC and return good FADEC to service (Ref. 73-25-10-000-801/73-25-10-400-801 MM).
FADEC Discrete: XTLKFT (bit 11) / (354 / CFPLRU) = 1 EFFECTIVITY:ALL
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FADEC Discrete: SOIFLT (bit 11) / (360 / FADLRU) = 1 DESCRIPTION: R R
This FADEC discrete is set to 1 (fault sensed) when the shutoff interlock bit is active (cross-channel data link, data bus) and no signal is received by this FADEC through the shutoff-interlock-in discrete (cross-channel data link, hardwired circuit) (Ref. FIG. 301/TASK 77-40-00-990-801).
POSSIBLE CAUSES: 1. FADEC 2. Cross-channel data link
01 Supply electrical power to the aircraft. Access FADEC discrete label 354 from the central maintenance computer (CMC) for both FADECs (Ref. Introduction). Does SOIFLT (bit 11) = 1?
04 Replace the W4 harness (Ref. 76-12-54 WM). Rotate the FADEC reset/select switch to -Yes the RESET position to remove the fault (SOIFLT (bit 11) = 0).
| No 02 Install the W4 harness from the FADEC set 05 Replace the W4 harness (Ref. 76-12-54 for the other engine. Is the fault removed WM). Rotate the FADEC reset/select switch to -Yes (SOIFLT (bit 11) = 0)? the RESET position to remove the fault (SOIFLT (bit 11) = 0). | No 03 Replace the FADEC showing SOIFLT (bit 11) = 1 with a FADEC from the other engine (Ref. 73-25-10-000-801/73-25-10-400-801 MM). Is the fault removed?
06 Remove the FADEC that has the fault from service (Ref. -Yes 73-25-10-000-801/73-25-10-400-801 MM).
| No |
07 Replace the other FADEC and return good FADEC to service (Ref. 73-25-10-000-801/73-25-10-400-801 MM).
FADEC Discrete: SOIFLT (bit 11) / (360 / FADLRU) = 1 EFFECTIVITY:ALL
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FADEC Discrete: CAPOFT (bit 12) / (360 / FADLRU) = 1 DESCRIPTION: This FADEC discrete is set to 1 (fault sensed) when the This-FADEC-Capable output-driver circuit is not in its commanded condition.
POSSIBLE CAUSES: 1. FADEC
01 Replace the FADEC that has the fault (Ref. 73-25-10-000-801/73-25-10-400-801 MM).
FADEC Discrete: CAPOFT (bit 12) / (360 / FADLRU) = 1 EFFECTIVITY:ALL
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FADEC Discrete: TLICFT (bit 13) / (360 / FADLRU) = 1 DESCRIPTION: This FADEC discrete is set to 1 (fault sensed) when the This-FADEC-In-Control output-driver circuit is not in its commanded condition.
POSSIBLE CAUSES: 1. FADEC
01 Replace the FADEC that has the fault (Ref. 73-25-10-000-801/73-25-10-400-801 MM).
FADEC Discrete: TLICFT (bit 13) / (360 / FADLRU) = 1 EFFECTIVITY:ALL
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Maintenance Message: ND-ENG1/ENG2 COMM A/B DESCRIPTION:
R R
This message occurs when the FADEC is not receiving data correctly either from the opposite FADEC channel on the same engine, or the same channel FADEC (via the internacelle data bus, W1 harness) on the opposite engine. The FADEC monitors the validity and rate of data received (Ref. FIG. 301/TASK 77-40-00-990-801/FIG. 302/TASK 77-40-00-990-802). The engine shutdown can be done with the fire handle when this fault occurs.
POSSIBLE CAUSES: 1. Loose FADEC connectors 2. Internacelle data bus/ harness 3. Cross-channel data link (Inter-FADEC harness) 4. FADEC
01 Examine the J2 and J3 connectors for looseness on all four FADECs. Are the connectors tight?
07 Tighten the connectors (Ref. -No 70-00-00-910-804 MM).
| Yes 02 Supply electrical power to the aircraft. 08 Do the troubleshooting for FADEC discrete Access FADEC discrete label 354 from the XTLKFT (bit 11) = 1 (Ref. 77-40-00-810-803). central maintenance computer (CMC) for both -Yes FADECs (Ref. Introduction). Does XTLKFT (bit 11) = 1? | No 03 Does NCNCFT (bit 12) = 1?
09 Examine both harness connectors at the FADEC J2 receptacles (this engine and the other engine) for damage, corrosion or -No contamination. Clean or repair them as necessary (Ref. 20-50-00 WM) (Ref. 76-12-54 WM).
| Yes 04 Go to Block 05
Maintenance Message: ND-ENG1/ENG2 COMM A/B EFFECTIVITY:ALL
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05 Interchange the FADEC showing NCNCFT 10 Replace the FADEC that has the fault (bit 12) = 1 with the other FADEC from this (Ref. 73-25-10-000-801/73-25-10-400-801 engine (Ref. -Yes MM). 73-25-10-000-801/73-25-10-400-801 MM). Is the fault removed? | No 06 Interchange the FADEC for the other engine, same channel as the one showing NCNCFT (bit 12) = 1 (Ref. 73-25-10-000-801/73-25-10-400-801 MM). Is the fault removed?
11 Replace the FADEC that has the fault (Ref. 73-25-10-000-801/73-25-10-400-801 -Yes MM).
| No |
12 Do the troubleshooting on the data bus/harness. Replace the harness that has the fault (Ref. 76-12-54 WM).
Maintenance Message: ND-ENG1/ENG2 COMM A/B EFFECTIVITY:ALL
TASK 77−40−00−810−807 Page 202 Jul 20/10
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FADEC / FADEC Interface Diagram FIG. 301/TASK 77-40-00-990-801
R EFFECTIVITY:ALL
77−40−TASK SUPPORT Page 301 Aug 15/04
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FADEC / FADEC (this engine/other engine) Interface Diagram FIG. 302/TASK 77-40-00-990-802
R EFFECTIVITY:ALL
77−40−TASK SUPPORT Page 302 Aug 15/04
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Observed Fault: LP Rotor Vibration High (displayed on EICAS and/or CMC Exceedance or Aircrew felt) DESCRIPTION: Vibration of the low pressure (fan) rotor, greater than 1.8 IPS in magnitude, will cause an exceedance event to be recorded on the central maintenance computer (CMC) and the EICAS display for LP vibration to become amber. Vibrations felt by aircrew members can be isolated using this procedure. If available, use the vibration equipment such as an ACES analyzer to aid in troubleshooting engine vibrations (Ref. 72-21-00-820-801, MM).
POSSIBLE CAUSES: 1. Fan blade damage 2. Ice accumulation on fan blades 3. Front-frame vibration sensor 4. Fan imbalance 5. Fan bearing cage movement 6. Compressor blade damage 7. Turbine-blade damage 8. Engine mounts loose or damaged 9. Aircraft signal-conditioning failure 10.Missing LPT1 or LPT2 coverplates (aircrew felt vibration)
01 Supply electrical power to the aircraft. 16 Ice can accumulate on the fan blades at an Access the engine exceedance data from the N1 rpm below 50%, and cause a vibration in -Yes CMC (Ref. Introduction). Did the high vibration the LP rotor. occur at an N1 rpm of less than 50% only? | No 02 Does the engine have low oil pressure at idle?
17 Download trend data (Ref. Introduction) and -Yes send to Rolls-Royce for analysis. Go to Block 08.
| No 03 Go to Block 04.
Observed Fault: LP Rotor Vibration High (displayed on EICAS and/or CMC Exceedance or Aircrew felt) EFFECTIVITY:ALL
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04 Do the general visual inspection of the 18 Do the maintenance action required by the engine fan case, exhaust, harnesses, examine MM. the fan blades for damage (Ref. 72-00-00-200-801, MM) (Ref. -Yes 72-21-15-200-801, MM) and visually inspect the low pressure turbine. Is any damage found? | No 05 Do the inspection and the test of the front-frame vibration sensor (Ref. FIG. 301/TASK 77-41-00-990-801) (Ref. 77-41-10-200-801, MM) (Ref. 77-41-10-700-801, MM). Is the sensor serviceable?
19 Replace the sensor (Ref. 77-41-10-000-801/77-41-10-400-801, MM). -No
| Yes 06 Download trend data (Ref. Introduction) and 20 Replace the sensor that has the fault (Ref. send to Rolls-Royce for analysis. Replace the 77-41-10-000-801/77-41-10-400-801, MM). sensor with the sensor from the other engine -No (Ref. 77-41-10-000-801/ 77-41-10-400-801, MM). Is the N1 vibration high? | Yes 07 Remove the fan spinner and look for loose hardware inside the spinner and the fan wheel hub (Ref. 72-21-20-000-801/ 72-21-20-400-801, MM). Is any hardware found?
21 Remove the loose hardware. Examine the spinner and fan wheel hub for damage. -Yes Repair if necessary.
| No 08 Contact Rolls-Royce to get the results of the 22 Rolls-Royce will supply instructions. trend data analysis. Did Rolls-Royce find -Yes unusual or incorrect trends? | No 09 Go to Block 10.
Observed Fault: LP Rotor Vibration High (displayed on EICAS and/or CMC Exceedance or Aircrew felt) EFFECTIVITY:ALL
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10 Do the fan balance procedure (Ref. 72-21-00-820-801, MM). Does the fan require balancing?
23 Balance the fan (Ref. 72-21-00-820-801, -Yes MM).
| No 11 Do the borescope inspection for fan bearing 24 Contact Rolls-Royce. cage movement (Ref. 72-20-00-200-802, MM). -Yes Did the fan bearing cage move from its initial position? | No R R R R R R R
12 Do the inspection of the forced core-to-bypass mixer assembly. (Ref. 78-11-15-200-801, MM). Is there a crack on the lobes? -Yes
R R R
25 Replace the forced core-to-bypass mixer assembly and do the borescope inspection of the 1st- and 2nd-stage low-pressure turbine blades to see if there are missing coverplates. (Ref. 72-50-00-200-801, SUBTASK 72-50-00-290-018, and SUBTASK 72-50-00-290-025, MM).
| No 13 Do the borescope inspection of the low pressure (LP) turbine section (Ref. 72-50-00-200-801, MM). Is there damage, beyond serviceable limits?
-Yes
26 Remove the engine (Ref. 71-00-00/401, AMM).
| No 14 Examine the engine mounts (Ref. 72-20-00/601, AMM). Are they loose or damaged?
27 Repair or replace the engine mounts (Ref. -Yes 71-20-00/401, AMM).
| No 15 Do the troubleshooting on the aircraft signal 28 Remove the engine (Ref. 71-00-00/401, conditioning system (Ref. AMM). -Yes FIM-1133_77-41-00-02, EMB FIM). Is the vibration high? | No |
29 Return the engine to service.
Observed Fault: LP Rotor Vibration High (displayed on EICAS and/or CMC Exceedance or Aircrew felt) EFFECTIVITY:ALL
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Observed Fault: HP Rotor Vibration High (displayed on EICAS and/or CMC Exceedance) DESCRIPTION: R
Vibration of the high-pressure rotor, greater than or equal to 1.1 inches per second (IPS) in magnitude, will cause an exceedance event to be recorded on the central maintenance computer (CMC) and the EICAS display for HP vibration to become amber.
POSSIBLE CAUSES:
R R
R
1. Compressor blade damage 2. HP turbine-blade damage 3. Vibration sensor incorrectly attached 4. Engine mounts loose or damaged 5. Harness damage 6. Connector corrosion 7. Aircraft signal-conditioning failure
01 Do the general visual inspection of the 22 Repair or replace the damaged component. engine inlet, exhaust, and harnesses for -Yes damage (Ref. 72-00-00-200-801 MM). Is there damage, beyond serviceable limits? | No
R R R
02 Is there a high vibration indication on the EICAS display, without a physical indication of vibration?
23 Do the troubleshooting on the aircraft signal -Yes conditioning system (Ref. 77-41-00-810-803, FIM).
| No R
03 Do the inspection and the test of the 24 Replace the sensor that has the fault (Ref. compressor vibration sensor (Ref. FIG. 77-41-10-000-802/77-41-10-400-802 MM). 301/TASK 77-41-00-990-801) (Ref. -No 77-41-10-200-802 MM) (Ref. 77-41-10-700-802 MM). Is the sensor serviceable? | Yes
R R R
04 Has SB AE 3007A-72-273 (relocation of the diffuser vibration sensor from the 6 o'clock -No position to the 9 o'clock position, ALF) been done?
25 Do SB AE 3007A-72-273. Go to Block 06.
| Yes 05 Go to Block 06. Observed Fault: HP Rotor Vibration High (displayed on EICAS and/or CMC Exceedance) EFFECTIVITY:ALL
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R
06 Replace the compressor vibration sensor with the sensor from the other engine (Ref. 77-41-10-000-802/77-41-10-400-802 MM). Is the N2 vibration high?
-No
26 Replace the sensor that has the fault (Ref. 77-41-10-000-802/77-41-10-400-802 MM).
| Yes R R
07 Do a detailed inspection of the engine mounts (Ref. 71-20-00-200-801-A, AMM). Are they loose or damaged?
27 Repair or replace the engine mounts (Ref. -Yes 71-20-00/401 AMM).
| No R R
08 Has the engine had an exceedance of more 28 Remove the engine (Ref. 71-00-00/401, -Yes than 1.5 IPS for more than 30 seconds? AMM). | No
R R
09 Has the engine had an exceedance of more than 1.5 IPS for less than 30 seconds?
-No
29 Go to block 12.
| Yes R R
10 Do the inspection of the engine for high pressure rotor vibration (Ref. 72-30-00-200-802, MM). Is an engine removal or scheduled removal required?
R R R R R
-Yes
30 Remove the engine, or schedule the engine for removal (Ref. 71-00-00/401, AMM).
| No 11 Contact Rolls-Royce for further trend analysis.
Observed Fault: HP Rotor Vibration High (displayed on EICAS and/or CMC Exceedance) EFFECTIVITY:ALL
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R R
12 Has the engine had an exceedance of 1.1-1.5 IPS for more than 30 seconds?
R R R
13 No action is necessary.
R R R R
14 Has the aircraft flown for two subsequent flights since the initial exceedance?
R R R
15 On subsequent flights, has the engine had an exceedance of more than 1.5 IPS for more than 30 seconds?
16 On the subsequent flights, has the engine had an exceedance of more than 1.5 IPS for less than 30 seconds?
-No
34 Go to block 19.
| Yes 17 Do the inspection of the engine for high pressure rotor vibration (Ref. 72-30-00-200-802, MM). Is an engine removal or scheduled removal required?
R R R R
33 Remove the engine (Ref. 71-00-00/401, -Yes AMM).
| No
R R R R R R R
32 Monitor the engine for two flights. If the engine did not have an exceedance, then no -No action is necessary. If the engine had an exceedance, then go to block 15.
| Yes
R R R R R R
31 Go to block 14.
| No
R
R R R
-Yes
-Yes
35 Remove the engine, or schedule the engine for removal (Ref. 71-00-00/401, AMM).
| No 18 Go to block 19.
Observed Fault: HP Rotor Vibration High (displayed on EICAS and/or CMC Exceedance) EFFECTIVITY:ALL
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R R R R
19 On the subsequent flights, has the engine had an exceedance of 1.1-1.5 IPS for more than 30 seconds?
R R R R R R
| No 20 On the subsequent flights, has the engine had an exceedance of 1.1-1.5 IPS for less than -No 30 seconds?
R R R R R
36 Remove the engine, or schedule the engine for removal (Ref. 71-00-00/401, AMM). A fly-on -Yes limit of 50 hours is permitted before the engine must be removed.
37 No action is necessary.
| Yes 21 Contact Rolls-Royce for further trend analysis.
Observed Fault: HP Rotor Vibration High (displayed on EICAS and/or CMC Exceedance) EFFECTIVITY:ALL
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R Observed Fault: LP or HP Rotor Vibration Level of 0.00/unreadable (displayed on EICAS or CMC download) R DESCRIPTION: R R
Vibration indication of the LP (fan) rotor or HP (compressor) rotor with zero IPS RMS in magnitude. This can cause a maintenance message on the CMC.
R POSSIBLE CAUSES: R R R
1. Engine Vibration Module 2. Vibration Sensors 3. Electrical Harness
R R R R R R R R R
01 Do the general visual inspection of the internal engine-indicating harness (Ref. 76-13-10-200-801 MM) and external engine-indicating harnesses (Ref. 76-13-15-200-801 MM) for damage. Is the damage more than the serviceable limits?
R R R
| No
R R R R R
02 Do a check of the CMC for the maintenance message “EVM E1/E2 vibration input fail”. Is the maintenance message “EVM E1/E2 vibration input fail” on the CMC display?
R R R R R R R R
03 Do a check of the CMC for the 10 Do the troubleshooting (Ref. maintenance message “EVM degraded”. Is 77-41-00-810-803-A EMB FIM). -Yes the maintenance message “EVM degraded” on the CMC display? | No 04 Is the “zero” vibration indicator on LP?
R R R R
-Yes
09 Do the troubleshooting (Ref. 77-41-00-810-804-A EMB FIM).
| No
R R R R
08 Repair or replace the internal engine-indicating harness (Ref. 76-13-10-000-801/76-13-10-400-801 MM), the LH engine external engine-indicating harness -Yes (Ref. 76-13-15-000-801/76-13-15-400-801 MM), or the RH engine external engine-indicating harness (Ref. 76-13-15-000-802/76-13-15-400-802 MM) that has the fault.
-Yes 11 Go to block 07.
| No 05 Go to block 06. Observed Fault: LP or HP Rotor Vibration Level of 0.00/unreadable (displayed on EICAS or CMC download)
R EFFECTIVITY:ALL
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R R R R R
06 Do the inspection and the test of the compressor vibration sensor (sensor) (Ref. FIG. 301/TASK 77-41-00-990-801) (Ref. -No 77-41-10-200-802/77-41-10-700-802 MM). Is the sensor serviceable?
R R R
| Yes
R R R
12 Replace the sensor (Ref. 77-41-10-000-802/77-41-10-400-802 MM).
13 Continue to monitor the vibration trend through the subsequent trending period and fault isolate as necessary.
Observed Fault: LP or HP Rotor Vibration Level of 0.00/unreadable (displayed on EICAS or CMC download) R EFFECTIVITY:ALL
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R R R R R
07 Do the inspection and the test of the front-frame vibration sensor (sensor) (Ref. FIG. 301/TASK 77-41-00-990-801) (Ref. -No 77-41-10-200-801/77-41-10-700-801 MM). Is the sensor serviceable?
R R R
| Yes
R R R
14 Replace the sensor (Ref. 77-41-10-000-801/77-41-10-400-801 MM).
15 Continue to monitor the vibration trend through the subsequent trending period and fault isolate as necessary.
Observed Fault: LP or HP Rotor Vibration Level of 0.00/unreadable (displayed on EICAS or CMC download) R EFFECTIVITY:ALL
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R
R R R EFFECTIVITY:ALL
N1 and N2 Vibration Sensor FIG. 301/TASK 77-41-00-990-801
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CHAPTER 78 LIST OF EFFECTIVE PAGES
R
R R R R R R R R
CHAPTER SECTION OTHER SUBJECT PAGE IDENT DATE 78 Contents 1/ Aug.15/04 2 00-00 101/ Feb.15/03 102 30-00 201 Feb.15/03 30-00 202 Feb.15/03 30-00 201 Aug.15/04 30-00 202 Aug.15/04 30-00 201 Aug.15/04 30-00 202 Aug.15/04 30-00 201/ Aug.15/04 202 30-00 201/ Aug.15/04 202 30-00 301 Aug.15/04 30-00 302 Aug.15/04 --------------- END ---------------
CHAPTER SECTION SUBJECT PAGE 78
OTHER IDENT
DATE
C=CONFIG B=BREAKOUT
CHAPTER SECTION SUBJECT PAGE 78
OTHER IDENT
DATE
LIST OF EFFECTIVE PAGES-78 Page 1/2 Oct 20/16
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CHAPTER 78 TABLE OF CONTENTS
SUBJECT
CH-SE-SUB
EXAUST FAULT CODE INDEX
78-00-00
ENGINE EXHAUST - THRUST REVERSER 78-30-00 Maintenance Message: ENG1/ENG2 TR/DEPL/STOW SIGNAL or LT - ENG1/ENG2 T/R POS SYS FADEC Discrete: TRDPFT (BIT 17) / (351 / AILRU1) = 1 FADEC Discrete: TRSTFT (bit 18) / (351 / AILRU1) = 1 FADEC Discrete: TRDPDF (bit 17) / (264/ AIDIF1) = 1 FADEC Discrete: TRSTDF (bit 18) / (264/ AIDIF1) = 1 Task Support
PAGE
EFFECTIVITY
101
201 201 201 201 201 301
78−CONTENTS Page 1/2 Oct 20/13
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FAULT CODE INDEX FAULT CODE
EFFECTIVITY:ALL
FAULT DESCRIPTION
MAINT. MESSAGE
GO TO FIM TASK
78−FAULT CODE INDEX Page 101/102 Feb 15/03
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Maintenance Message: ENG1/ENG2 TR/DEPL/STOW SIGNAL or LT - ENG1/ENG2 T/R POS SYS DESCRIPTION: This message occurs when the FADEC finds an open or shorted condition of the thrust-reverser deployed or thrust-reverser stowed position-switch circuits, or when channel A and B circuit conditions are not the same (DEPLOYED/NOT DEPLOYED, OR STOWED/NOT STOWED).
POSSIBLE CAUSES: 1. Aircraft circuit fault 2. FADEC
01 Supply electrical power to the aircraft. Access FADEC discrete label 351 from the central maintenance computer (CMC) for both FADECs (Ref. Introduction). Does TRDPFT (bit 17) = 1?
-Yes
08 Do the troubleshooting for FADEC discrete TRDPFT (bit 17) (Ref. 78-30-00-810-802).
| No 02 Does TRSTFT (bit 18) = 1?
-Yes
09 Do the troubleshooting for FADEC discrete TRSTFT (bit 18) (Ref. 78-30-00-810-803).
| No 03 Access FADEC discrete label 264 from the 10 Do the troubleshooting for FADEC discrete -Yes CMC. Does TRDPDF (bit 17) = 1? TRDPDF (bit 17) (Ref. 78-30-00-810-804). | No 04 Does TRSTDF (bit 18) = 1?
-Yes
11 Do the troubleshooting for FADEC discrete TRSTDF (bit 18) (Ref. 78-30-00-810-805).
| No 05 Deploy the thrust reversers. Does TRDPDF 12 Do the troubleshooting for FADEC discrete -Yes (bit 17) = 1? TRDPDF (bit 17) (Ref. 78-30-00-810-804). | No 06 Go to Block 07
Maintenance Message: ENG1/ENG2 TR/DEPL/STOW SIGNAL or LT - ENG1/ENG2 T/R POS SYS EFFECTIVITY:ALL
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07 Does TRSTDF (bit 18) = 1?
-Yes
13 Do the troubleshooting for FADEC discrete TRSTDF (bit 18) (Ref. 78-30-00-810-805).
| No |
14 Examine all of the harness connectors between the thrust-reverser position switches and the FADEC (Ref. 78-31-54/78-31-55 WM). Clean or repair them as necessary.
Maintenance Message: ENG1/ENG2 TR/DEPL/STOW SIGNAL or LT - ENG1/ENG2 T/R POS SYS EFFECTIVITY:ALL
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FADEC Discrete: TRDPFT (BIT 17) / (351 / AILRU1) = 1 DESCRIPTION: The FADEC does a test of the circuits for the thrust-reverser (T/R) fully-deployed position switch. This discrete is set to 1 (fault sensed) when an open or shorted circuit is detected.
POSSIBLE CAUSES: 1. Aircraft circuit fault 2. FADEC
01 Disconnect the harness from the FADEC 07 Clean or repair the connector (Ref. J2 receptacle. Examine the harness connector 20-50-00 WM). Rotate the FADEC reset/select -Yes for damage, corrosion, or contamination. Is the switch to the RESET position to remove the connector contaminated or damaged? fault (TRDPFT (bit 17) = 0). | No 02 Supply electrical power to the aircraft and do a test for voltage at pin S of the FADEC J2 receptacle (Ref. 76-12-52/76-12-53 WM) (Ref. Fig. 301). Is there 12-15 VDC measured?
-No
08 Replace th FADEC that has the fault (Ref. 73-25-10-000-801/73-25-10-400-801 MM).
| Yes
R R
03 Make sure the T/R deployed switch is in the 09 Repair the aircraft circuit fault (Ref. DEPLOYED position and do a test for 76-12-52/76-12-53 WM). Rotate the FADEC continuity between pins S and m at the W1 reset/select switch to the RESET position to -No harness connector (Ref. FIG. 301/TASK remove the fault (TRDPFT (bit 17) = 0). 78-30-00-990-801). Is there continuity, with resistance less than 10 ohms? | Yes 04 Go to Block 05
FADEC Discrete: TRDPFT (BIT 17) / (351 / AILRU1) = 1 EFFECTIVITY:ALL
TASK 78−30−00−810−802 Page 201 Aug 15/04
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R
05 With the T/R deployed switch in the DEPLOYED position, do a test for continuity between ground and pin S at the W1 harness connector (Ref. 76-12-52/76-12-53 WM) (Ref. FIG. 301/TASK 78-30-00-990-801). Is there continuity?
10 Repair the aircraft circuit fault (Ref. 76-12-52/76-12-53 WM). Rotate the FADEC reset/select switch to the RESET position to -Yes remove the fault (TRDPFT (bit 17) = 0).
| No
R R
06 Make sure the T/R deployed switch is in the NOT DEPLOYED position and do a test for continuity between pins m and S at the W1 harness connector (Ref FIG. 301/TASK -No 78-30-00-990-801) (Ref. 76-12-52/76-12-53 WM). Is there continuity, with resistance between 9.5K and 10.5K ohms?
11 Repair the aircraft circuit fault (Ref. 76-12-52/76-12-53 WM). Rotate the FADEC reset/select switch to the RESET position to remove the fault (TRDPFT (bit 17) = 0).
| Yes |
12 Replace th FADEC that has the fault (Ref. 73-25-10-000-801/73-25-10-400-801 MM).
FADEC Discrete: TRDPFT (BIT 17) / (351 / AILRU1) = 1 EFFECTIVITY:ALL
TASK 78−30−00−810−802 Page 202 Aug 15/04
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FADEC Discrete: TRSTFT (bit 18) / (351 / AILRU1) = 1 DESCRIPTION: The FADEC does a test of the circuits for the thrust-reverser (T/R) fully-stowed position switch. This discrete is set to 1 (fault sensed) when an open or shorted circuit is detected.
POSSIBLE CAUSES: 1. Aircraft circuit fault 2. FADEC
01 Disconnect the harness (W1) from the FADEC J2 receptacle. Examine the harness connector for damage, corrosion, or contamination. Is the connector contaminated or damaged?
07 Clean or repair the connector (Ref. 20-50-00 WM). Rotate the FADEC reset/select -Yes switch to the RESET position to remove the fault (TRSTFT (bit 18) = 0).
| No
R
02 Supply electrical power to the aircraft and do a test for voltage at pin S of the FADEC J2 receptacle (Ref. 76-12-52/76-12-53 WM) (Ref. FIG. 302/TASK 78-30-00-990-802). Is there 12-15 VDC measured?
-No
08 Replace th FADEC that has the fault (Ref. 73-25-10-000-801/73-25-10-400-801 MM).
| Yes
R R
03 Make sure the T/R stowed switch is in the STOWED position and do a test for continuity between pins S and k at the W1 harness connector (Ref. FIG. 302/TASK 78-30-00-990-802). Is there continuity, with resistance less than 10 ohms?
09 Repair the aircraft circuit fault (Ref. 76-12-52/76-12-53 WM). Rotate the FADEC reset/select switch to the RESET position to -No remove the fault (TRSTFT (bit 18) = 0).
| Yes 04 Go to Block 05
FADEC Discrete: TRSTFT (bit 18) / (351 / AILRU1) = 1 EFFECTIVITY:ALL
TASK 78−30−00−810−803 Page 201 Aug 15/04
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R
05 With the T/R stowed switch in the 10 Repair the aircraft circuit fault (Ref. STOWED position, do a test for continuity 76-12-52/76-12-53 WM). Rotate the FADEC between ground and pin S at the W1 harness reset/select switch to the RESET position to -Yes connector (Ref. 76-12-52/76-12-53 WM) (Ref. remove the fault (TRSTFT (bit 18) = 0). FIG. 302/TASK 78-30-00-990-802). Is there continuity? | No
R R
06 Make sure the T/R stowed switch is in the NOT STOWED position and do a test for continuity between pins k and S at the W1 harness connector (Ref FIG. 302/TASK 78-30-00-990-802) (Ref. 76-12-52/76-12-53 WM). Is there continuity, with resistance between 9.5K and 10.5K ohms?
11 Repair the aircraft circuit fault (Ref. 76-12-52/76-12-53 WM). Rotate the FADEC reset/select switch to the RESET position to -No remove the fault (TRDPFT (bit 17) = 0).
| Yes |
12 Replace th FADEC that has the fault (Ref. 73-25-10-000-801/73-25-10-400-801 MM).
FADEC Discrete: TRSTFT (bit 18) / (351 / AILRU1) = 1 EFFECTIVITY:ALL
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FADEC Discrete: TRDPDF (bit 17) / (264/ AIDIF1) = 1 DESCRIPTION: The FADECs do a lane difference test of the two thrust-reverser (TR) fully-deployed circuits. This fault occurs when the condition of the circuits (DEPLOYED/NOT DEPLOYED) sensed by FADEC A and B is not the same. The FADECs will not do this test if one of the two circuits has a fault.
POSSIBLE CAUSES: 1. Aircraft circuit fault 2. FADEC
01 Disconnect the harness (W1) from the J2 receptacles on both FADECs. Examine the harness connectors for damage, corrosion, or contamination. Are the connectors contaminated or damaged?
04 Clean or repair the connector (Ref. 20-50-00 WM). Rotate the FADEC reset/select -Yes switch to the RESET position to remove the fault (TRDPDF (bit 17) = 0).
| No
R R
02 Disconnect the harness from the switch 05 Repair the aircraft harness fault (Ref. and do a test for continuity between pins S and 76-12-52/76-12-53 WM). Rotate the FADEC m at both W1 harness connectors (Ref. FIG. -Yes reset/select switch to the RESET position to 301/TASK 78-30-00-990-801) (Ref. remove the fault (TRDPDF (bit 17) = 0). 76-12-52/76-12-53 WM). Is there continuity? | No 03 Supply electrical power to the aircraft. Access FADEC discrete label 264, for FADEC A and B, from the central maintenance computer (CMC) (Ref. Introduction). Does TRDPDF (bit 17) = 1 for both FADECs?
06 Repair the aircraft circuit fault (Ref. 76-12-52/76-12-53 WM). Rotate the FADEC -Yes reset/select switch to the RESET position to remove the fault (TRDPDF (bit 17) = 0).
| No |
07 Replace th FADEC that shows TRDPDF (bit 17) = 1 (Ref. 73-25-10-000-801/73-25-10-400-801 MM).
FADEC Discrete: TRDPDF (bit 17) / (264/ AIDIF1) = 1 EFFECTIVITY:ALL
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FADEC Discrete: TRSTDF (bit 18) / (264/ AIDIF1) = 1 DESCRIPTION: The FADECs do a lane difference test of the two thrust-reverser (TR) fully-stowed circuits. This fault occurs when the condition of the circuits (STOWED/NOT STOWED) sensed by FADEC A and B is not the same. The FADECs will not do this test if one of the two circuits has a fault.
POSSIBLE CAUSES: 1. Aircraft circuit fault 2. FADEC
01 Disconnect the harness (W1) from the J2 receptacles on both FADECs. Examine the harness connectors for damage, corrosion, or contamination. Are the connectors contaminated or damaged?
04 Clean or repair the connector (Ref. 20-50-00 WM). Rotate the FADEC reset/select -Yes switch to the RESET position to remove the fault (TRSTDF (bit 18) = 0).
| No
R R
02 Disconnect the harness from the switch 05 Repair the aircraft harness fault (Ref. and do a test for continuity between pins S and 76-12-52/76-12-53 WM). Rotate the FADEC k at both W1 harness connectors (Ref. FIG. -Yes reset/select switch to the RESET position to 302/TASK 78-30-00-990-802) (Ref. remove the fault (TRSTDF (bit 18) = 0). 76-12-52/76-12-53 WM). Is there continuity? | No 03 Supply electrical power to the aircraft. Access FADEC discrete label 264, for FADEC A and B, from the central maintenance computer (CMC) (Ref. Introduction). Does TRSTDF (bit 18) = 1 for both FADECs?
06 Repair the aircraft circuit fault (Ref. 76-12-52/76-12-53 WM). Rotate the FADEC -Yes reset/select switch to the RESET position to remove the fault (TRSTDF (bit 18) = 0).
| No |
07 Replace th FADEC that shows TRSTDF (bit 18) = 1 (Ref. 73-25-10-000-801/73-25-10-400-801 MM).
FADEC Discrete: TRSTDF (bit 18) / (264/ AIDIF1) = 1 EFFECTIVITY:ALL
TASK 78−30−00−810−805 Page 201/202 Aug 15/04
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Thurst Reverser Fully-deployed Switch / FADEC Interface Diagram FIG. 301/TASK 78-30-00-990-801
R EFFECTIVITY:ALL
78−30−TASK SUPPORT Page 301 Aug 15/04
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Thurst Reverser Stowed / FADEC Interface Diagram FIG. 302/TASK 78-30-00-990-802
R EFFECTIVITY:ALL
78−30−TASK SUPPORT Page 302 Aug 15/04
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CHAPTER 79 LIST OF EFFECTIVE PAGES
R R R R R R R R R
CHAPTER SECTION OTHER SUBJECT PAGE IDENT DATE 79 Contents 1/ Jul.20/08 2 00-00 101/ Jan.20/10 102 37-00 201 Aug.15/04 37-00 202 Aug.15/04 37-00 201 Apr.20/13 37-00 202 Apr.20/13 37-00 201 Apr.20/16 37-00 202 Apr.20/16 37-00 203 Apr.20/16 37-00 204 Apr.20/16 37-00 201 Apr.20/16 37-00 202 Apr.20/16 37-00 203 Apr.20/16 37-00 204 Apr.20/16 37-00 205 Apr.20/16 37-00 206 Apr.20/16 37-00 201 Oct.20/09 37-00 202 Oct.20/09 37-00 203 Oct.20/09 37-00 204 Oct.20/09 37-00 201 Apr.20/09 37-00 202 Apr.20/09 37-00 203/ Apr.20/09 204 37-00 201 Oct.20/16 37-00 202 Oct.20/16 37-00 203 Oct.20/16 37-00 204 Oct.20/16 37-00 205 Oct.20/16 37-00 206 Oct.20/16 37-00 207 Oct.20/16 37-00 208 Oct.20/16 37-00 209/ Oct.20/16 210 37-00 201/ Feb.15/03 202 37-00 201/ Oct.20/13 202 37-00 301 Aug.15/04 37-00 302 Aug.15/04 37-00 303 Aug.15/04 37-00 304 Aug.15/04 37-00 305 Aug.15/04 37-00 306 Aug.15/04 37-00 307/ Aug.15/04 308 --------------- END ---------------
CHAPTER SECTION SUBJECT PAGE 79
OTHER IDENT
DATE
C=CONFIG B=BREAKOUT
CHAPTER SECTION SUBJECT PAGE 79
OTHER IDENT
DATE
LIST OF EFFECTIVE PAGES-79 Page 1/2 Oct 20/16
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CHAPTER 79 TABLE OF CONTENTS
SUBJECT
CH-SE-SUB
OIL FAULT CODE INDEX
79-00-00
ENGINE OIL - INDICATING Maintenance Message: ENG1/ENG2 OIL DEBRIS EICAS Message: E1/E2 OIL IMP BYP EICAS Message: E1/E2 OIL LOW PRESS WARNING Observed Fault: Oil Pressure Low (displayed on EICAS and/or a CMC exceedance) Observed Fault: Oil Pressure High (displayed on EICAS) Observed Fault: Oil Temperature High (displayed on EICAS and/or a CMC exceedance) Observed Fault: Oil Consumption High / Oil Leakage Observed Fault: Oil or Fuel Smell/Haze in the Cabin Observed Fault: Oil Pressure Display Shows Dashes Task Support
79-37-00
PAGE
EFFECTIVITY
101
201 201 201 201 201 201 201 201 201 301
79−CONTENTS Page 1/2 Jul 20/08
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FAULT CODE INDEX FAULT CODE
FAULT DESCRIPTION
793M01 00
E1 OIL LOW PRESS (Warning)
79-37-00-810-803
793M02 00
E2 OIL LOW PRESS (Warning)
79-37-00-810-803
793M73 00 (POST SB EMB 145-79-0001)
E1 OIL IMP BYP (Advisory)
79-37-00-810-802-A02
793M74 00 (POST SB EMB 145-79-0001)
E2 OIL IMP BYP (Advisory)
79-37-00-810-802-A02
7930O1 00
Oil Consumption High / Oil Leakage
79-37-00-810-807
793002 00
Oil Pressure High (displayed on EICAS)
79-37-00-810-805
7930O3 00
Oil Pressure Low (display)
79-37-00-810-804
7930O4 00
Oil Temperature High
79-37-00-810-806
7930O5 00
Oil Pressure Display Shows Dashes
79-37-00-810-809
MAINT. MESSAGE
GO TO FIM TASK
NOTE: Fault code 793005 00 (Task 79-37-00-810-808, Oil or Fuel Smell / Haze in the Cabin) has been changed to 7200O8 00 (Task 72-00-00-810-814, Oil or Fuel Smell / Haze in the Cabin)
EFFECTIVITY:ALL
79−FAULT CODE INDEX Page 101/102 Jan 20/10
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Maintenance Message: ENG1/ENG2 OIL DEBRIS DESCRIPTION: This message occurs when conductive debris bridges the gap across the two electrodes of the magnetic indicating plug (mounted in the oil tank).
POSSIBLE CAUSES: 1. Debris from internal engine wear or failure 2. Magnetic indicating plug 3. Harness (W9) 4. Aircraft system, signal conditioning fault
01 Remove the magnetic indicating plug from the oil tank and examine it (Ref. 79-37-10-000-801/79-37-10-400-801 MM). Is there conductive debris across the gap?
06 Do the inspection for particles on the magnetic indicating plug (Ref. -Yes 79-30-00-200-801 MM).
| No 02 Connect the harness to the plug. Supply electrical power to the aircraft. Record the number of occurrences of this message on the CMC. Put a conductive material across the electrode gap. Is there a new occurrence of the message?
07 Examine the 4 chip collectors on the on the lube and scavenge pump (Ref. 79-21-10 MM), and the chip collector plugs on the oil tank -Yes (Ref. 79-11-10 MM) and accessory drive gearbox (Ref. 72-63-10 MM). If any conductive debris is found, do the inspection for the particles (Ref. 79-30-00-200-801 MM).
| No 03 Do a test for continuity between pins A and 08 Replace the magnetic indicating plug (Ref. B of the magnetic indicating plug. Is there -Yes 79-37-10-000-801/79-37-10-400-801 MM). continuity? | No 04 Go to Block 05
Maintenance Message: ENG1/ENG2 OIL DEBRIS EFFECTIVITY:ALL
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R R R
05 Disconnect the EIS harness (W9) from the 09 Replace the EIS harness (Ref. 76-00-00 firewall and the magnetic indicating plug. Do a MM). test for continuity between pins A and B on the harness connector (Ref. FIG. 301/TASK -Yes 79-37-00-990-801/FIG. 304/TASK 79-37-00-990-804) (Ref. 79-30-50/79-30-51 WM). Is there continuity? | No |
10 Do the troubleshooting on the aircraft systems (harness, signal conditioning unit) (Ref. 79-30-50/79-30-51 WM).
Maintenance Message: ENG1/ENG2 OIL DEBRIS EFFECTIVITY:ALL
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EICAS Message: E1/E2 OIL IMP BYP DESCRIPTION: This message occurs when the circuit for the electrical impending-bypass indicator is open or the circuit for the magnetic indicating plug (oil tank) is completed. This is an indication of an impending bypass of the oil filter, or the presence of metallic debris on the magnetic indicating plug.
POSSIBLE CAUSES: 1. Oil filter element blocked 2. Metallic debris on oil tank magnetic indicating plug 3. Electrical impending-bypass indicator/circuit 4. Magnetic indicating plug/circuit fault 5. Aircraft system, signal conditioning fault
01 Gain access to the maintenance messages 08 Do the fault isolation procedure for an on the multi-function display. Is ENG1/ENG2 ENG1/ENG2 OIL DEBRIS message (Ref. -Yes OIL DEBRIS message shown? 79-37-00-810-801). Do the inspection of the bypass indicators (Ref. 79-30-00-200-802 MM). | No 02 Does the fault occur only when the oil temperature is below 4 °C?
09 Replace the electrical impending-bypass -Yes indicator (Ref. 79-37-15-000-801/ 79-37-15-400-801 MM).
| No R R
03 Does the engine have less than 500 hours since last shop visit?
-Yes
10 Remove the engine from service (Ref. AMM).
| No 04 Do the inspection of the by-pass indicators 11 Return the aircraft to service. (Ref. 79-30-00-200-802 MM). Is the message -Yes removed after the oil filter element is replaced? | No R
05 Go to Block 06
EICAS Message: E1/E2 OIL IMP BYP EFFECTIVITY:ALL
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06 Replace the electrical impending-bypass indicator (Ref. 79-37-15-000-801/ 79-37-15-400-801 MM). Is the fault removed?
12 Remove the electrical impending-bypass -Yes indicator from service.
| No 07 Do a test for continuity/resistance (1 ohm max./harness), internal shorts, and shorts to ground (1,000 ohms min.) on the EIS harness (W9) (Ref. FIG. 302/TASK 79-37-00-990-802/FIG. 304/TASK 79-37-00-990-804) (Ref. 79-30-50/ 79-30-51 WM). Does the harness test satisfactorily?
-Yes
13 Do the troubleshooting on the aircraft systems (harness, signal conditioning unit) (Ref. 79-30-50/79-30-51 WM).
| No |
14 Replace the EIS harness (Ref. 76-00-00 MM).
EICAS Message: E1/E2 OIL IMP BYP EFFECTIVITY:ALL
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EICAS Message: E1/E2 OIL LOW PRESS WARNING DESCRIPTION: This message occurs when the low-oil-pressure sensor (switch) circuit opens at 34 psig (234 kPag), or less, with decreasing oil pressure, and N2 RPM is above 53%, or when the sensor circuit is closed and N2 RPM is below 10%.
POSSIBLE CAUSES: 1. Lube and scavenge pump 2. Tank pressurizing valve 3. Low-oil-pressure sensor circuit 4. Low oil level 5. Aircraft system, signal conditioning fault 6. Blockage in the center-sump scavenge path
01 Supply electrical power to the aircraft. 15 Go to block 04. Access the exceedance information from the central maintenance computer (CMC) (Ref. -Yes Introduction). Did an exceedance event for low oil pressure occur at the same time as the message? | No 02 Replace the low oil-pressure switch (Ref. 79-33-10-000-801/79-33-10-400-801, MM). Is the fault removed?
16 Remove the low oil-pressure switch from -Yes service.
| No 03 Do a test for continuity/resistance (1 ohm max./harness), internal shorts, and shorts to ground (1,000 ohms min.) on the EIS harness (W9) (Ref. FIG. 303/TASK 79-37-00-990-803/FIG. 304/TASK 79-37-00-990-804) (Ref. 79-30-50/79-30-51, WM). Does the harness test satisfactorily?
-Yes
17 Do the troubleshooting on the aircraft systems (harness, signal conditioning unit) (Ref. 79-30-50/79-30-51, WM).
| No |
18 Replace the EIS harness on the left-hand engine (Ref. 76-13-15-000-801/76-13-15-400-801, MM) or on the right-hand engine (Ref. 76-13-15-000-802/76-13-15-400-802, MM). EICAS Message: E1/E2 OIL LOW PRESS WARNING
EFFECTIVITY:ALL
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04 Did the engine operate with the main oil pressure below 10 psig (69 kPag)?
R R R R R R
| No 05 Did the engine operate for more than 30 seconds with the main oil pressure below 34 psig (234 kPag)?
R R R R R R R
-Yes 20 Send the CMC and DFDR data to Rolls-Royce for evaluation.
| No 06 Is the oil level in the oil tank 2 qts (2.2 L) or less?
R R R R R R
-Yes 19 Replace the engine.
-Yes 21 Identify the source of the oil leakage (Ref. 79-37-00-810-807, FIM). If acceptable for continued operation, then service the oil tank (Ref. 12-10-79-600-801, MM). Go to Block 14.
| No 07 Access the exceedance information from the CMC. Did the exceedance occur during operation at altitude only?
22 Replace the oil tank pressurizing valve (Ref. -Yes 79-27-35-000-801/79-27-35-400-801, MM). Go to Block 14.
| No R
08 Is the oil pressure below 34 psig (234 kPag) 23 Do SB AE 3007A-79-039 or AE but above 32 psig (221 kPag)? -Yes 3007A-72-303. Go to Block 09 if SB is incorporated. | No
R
09 Is the engine POST-SB AE3007A-72-416?
R R R R
-Yes 24 Go to Block 12.
| No 10PRE-SB AE3007A-72-416: Do the borescope inspection for fan bearing cage movement (Ref. 72-20-00-200-802, MM). Did the fan bearing cage move from its initial position?
25 Contact Rolls-Royce. -Yes
| No R
11 Go to Block 12. EICAS Message: E1/E2 OIL LOW PRESS WARNING EFFECTIVITY:ALL
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12 Replace the lube-and-scavenge pump (Ref. 26 Remove the lube-and-scavenge pump from 79-21-10-000-801/79-21-10-400-801, MM). Is -Yes service. the fault removed? | No 13 Examine the scavenge oil path from the center sump to the lube-and-scavenge pump for blockage (Ref. FIG. 305/TASK 79-37-00-990-805) (Ref. 79-27-30-200-801, MM). Is blockage found?
27 Correct the blockage in the scavenge oil path from the center sump to the -Yes lube-and-scavenge pump (Ref. 79-27-30-200-801, MM).
| No |
28 Contact Rolls-Royce.
EICAS Message: E1/E2 OIL LOW PRESS WARNING EFFECTIVITY:ALL
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R R
14 Do the test of the engine (Ref. 71-00-00-810-806, MM). Is the fault removed?
R R R
| No |
R
-Yes 29 Return the engine to service.
30 Contact Rolls-Royce.
EICAS Message: E1/E2 OIL LOW PRESS WARNING EFFECTIVITY:ALL
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Observed Fault: Oil Pressure Low (displayed on EICAS and/or a CMC exceedance) DESCRIPTION: This condition occurs when the oil pressure value measured by the oil-pressure/temperature-transducer sensor is below 50 psig (with N2 88% RPM or greater) or is below 34 psig (with N2 below 88% RPM).
POSSIBLE CAUSES: 1. Oil-pressure/temperature-transducer sensor / circuit 2. Aircraft system, signal conditioning fault 3. Low oil level 4. Tank pressurizing valve 5. Fan bearing cage movement 6. No. 3 bearing damper oil rings
R
01 Supply electrical power on the aircraft. Access the exceedance information from the central maintenance computer (CMC) (Ref. Introduction). Was the lowest value of oil pressure 0.0 psig (0.0 kPag)?
20 Go to Block 19. -Yes
| No 02 Was the MOP below 34 psig (234 kPag) and N2 less than 88%?
-Yes
21 Go to Block 09.
| No 03 Was the oil pressure below 50 psig (345 kPag) and N2 more than 88%?
-Yes
22 Go to Block 09.
| No 04 Was there an OIL LOW PRESS warning message on the EICAS?
-Yes
23 Replace the low-oil-pressure switch (Ref. 79-33-10-000-801/ 79-33-10-400-801, MM).
| No 05 Go to Block 06.
Observed Fault: Oil Pressure Low (displayed on EICAS and/or a CMC exceedance) EFFECTIVITY:ALL
TASK 79−37−00−810−804 Page 201 Apr 20/16
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06 Examine the W8/W9 harness connector at the engine pylon for damage, corrosion, or contamination (Ref. FIG. 304/TASK 79-37-00-990-804/FIG. 307/TASK 79-37-00-990-807) (Ref. 79-30-50/79-30-51, WM). Is damage, corrosion, or contamination present?
-Yes
24 Repair or clean the connectors as necessary (Ref. 20-50-00, WM) (Ref. 70-00-00-910-804, MM).
| No
R
07 Replace the oil-pressure/temperature-transducer sensor (sensor) with the sensor from the other engine (Ref. 79-31-10-000-801/ 79-31-10-400-801, MM). Is the LOW OIL PRESS warning message removed from EICAS?
25 Replace the sensor that has the fault (Ref. 79-31-10-000-801/ 79-31-10-400-801, MM). -Yes
| No 08 Do a test for continuity/resistance (1 ohm max./harness), internal shorts and shorts to ground (1,000 ohms min.) on the EIS harness (W9) (Ref. FIG. 304/TASK 79-37-00-990-804/FIG. 306/TASK 79-37-00-990-806) (Ref. 79-30-50/79-30-51, WM). Does the harness test satisfactorily?
26 Do the troubleshooting on the aircraft systems (harness, signal conditioning unit) (Ref. 31-41-00/201, EMB FIM) (Ref. -Yes 79-30-50/79-30-51, WM).
| No |
27 Replace the EIS harness on the left-hand engine (Ref. 76-13-10-000/400-801, MM) or on the right-hand engine (Ref. 76-13-10-000/400-802, MM).
Observed Fault: Oil Pressure Low (displayed on EICAS and/or a CMC exceedance) EFFECTIVITY:ALL
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R R
09 Did the engine operate with the main oil pressure below 10 psig (69 kPag)?
R R R R R R
10 Did the engine operate for more than 30 seconds with the main oil pressure below 34 psig (234 kPag)?
29 Send the CMC and DFDR data to -Yes Rolls-Royce for evaluation.
| No 11 Is the oil level in the oil tank 2 qts (2.2 L) or less?
R R R
R
28 Replace the engine.
| No
R R R R R R R
-Yes
30 Identiify the source of the oil leakage (Ref. 79-37-00-810-807, FIM). If acceptable for -Yes continued operation, then service the oil tank (Ref. 12-10-79-600-801, MM). Go to Block 18.
| No 12 Access the exceedance information from the CMC. Did the exceedance occur during operation at altitude only?
31 Replace the oil tank pressurizing valve (Ref. -Yes 79-27-35-000-801/ 79-27-35-400-801, MM). Go to Block 18.
| No R
13 Is the engine POST-SB AE3007A-72-416?
R R R R
-Yes 32 Go to Block 18.
| No 14 PRE-SB AE3007A-72-416: Do the borescope inspection for fan bearing cage movement (Ref. 72-20-00-200-802, MM). Did the fan bearing cage move from its initial position?
-Yes
33 Replace the fan bearing support housing assembly (Ref. SB AE 3007A-72-416).
| No R
15 Go to Block 16.
Observed Fault: Oil Pressure Low (displayed on EICAS and/or a CMC exceedance) EFFECTIVITY:ALL
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R
16 Was the main oil pressure below 34 psig (234 kPag) but above 32 psig (221 kPag)?
R
34 Verify that SB AE 3007A-79-039 or AE 3007A-72-303 is completed. Go to Block 17 if -Yes SB is completed. If SB is not incorporated, then do SB AE 3007A-79-039 and AE 3007A-72-303.
| No 17 Remove the engine.
Observed Fault: Oil Pressure Low (displayed on EICAS and/or a CMC exceedance) EFFECTIVITY:ALL
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18 Do the test of the engine (Ref. 71-00-00-810-806, MM). Is the fault removed?
-Yes
35 Return the engine to service.
| No |
36 Contact Rolls-Royce.
Observed Fault: Oil Pressure Low (displayed on EICAS and/or a CMC exceedance) EFFECTIVITY:ALL
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19 Was there an OIL LOW PRESS warning message on the EICAS?
-Yes 37 Go to Block 09.
| No |
38 Put the engine back in service.
Observed Fault: Oil Pressure Low (displayed on EICAS and/or a CMC exceedance) EFFECTIVITY:ALL
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Observed Fault: Oil Pressure High (displayed on EICAS) DESCRIPTION: This condition occurs when the oil pressure value measured by the oil pressure/temperature sensor is above 115 psig (793 kPag)for more than 2 minutes or above 110 psig (758 kPag)for more than 5 minutes.
POSSIBLE CAUSES: 1. Oil temperature low 2. Aircraft engine pylon connector fault 3. Oil pressure/temperature sensor/circuit damaged 4. Lube-and-scavenge pump damaged/blockage of scavenge system full-flow chip-collector debris monitor 5. Blockage in the center-sump vent-air path 6. Aircraft system, signal conditioning fault 7. Engine internal fault
01 Was the oil pressure high during engine start and the oil temperature low (below 70°F (21°C))?
15 Oil pressure above the limit can be a correct -Yes indicationwith low oil temperature during engine start.
| No 02 Do the test of the engine (Ref. TASK 16 Go to block 08. 71-00-00-810-804).Is the oil pressure indication -Yes irregular (more than ±3 psig (±21 kPag)in less than 3 seconds)? | No 03 Is the oil pressure more than 68 psig (469 kPag)at idle?
-Yes
17 Go to block 08.
| No 04 Is the 2 minute oil pressure more than 115 psig (793 kPag)or is the 5 minute steady-state oil pressure more than 110 psig (758 kPag)?
-Yes
18 Go to block 14.
| No 05 Go to block 06.
Observed Fault: Oil Pressure High (displayed on EICAS) EFFECTIVITY:ALL
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06 Is FADEC software version B7.6 (or higher) installed?
-No
19 Install version B7.6 (or higher) FADEC software.
| Yes 07 Is the oil pressure compared to the oil temperature in Region A on Fig. 201 (Ref. TASK 71-00-00-810-804)?
-Yes
20 Return the engine to service.
| No |
21 Remove the engine from service (Ref. AMM).
Observed Fault: Oil Pressure High (displayed on EICAS) EFFECTIVITY:ALL
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08 Remove the oil pressure/temperature sensor and leave it connected to the W9 harness (Ref. 79-31-10-000-801, MM). Is the oil pressure reading on the EICAS display more than 4 psig (28 kPag)?
-No
22 Install the oil pressure/temperature sensor (Ref. 79-31-10-400-801, MM). Go to block 10.
| Yes 09Replace the oil pressure/temperature sensor 23 Go to block 02. with a serviceable sensor (Ref. -Yes 79-31-10-000-801/79-31-10-400-801, MM). Is the fault corrected? | No 10Examine the W8/W9 harness connector at the engine pylon for damage, corrosion, or contamination (Ref. FIG. 304/TASK 79-37-00-990-804/FIG. 306/TASK 79-37-00-990-806/FIG. 307/TASK 79-37-00-990-807) (Ref. 79-30-50/79-30-51, WM).Is a fault found?
-Yes
24Clean or repair the connector (Ref. 70-00-00-910-804, MM) (Ref. 20-50-00, WM).Go to block 02.
| No
R R
11Do a test for continuity/resistance (1 ohm Max./harness), internal shorts, and shorts to ground (1,000 ohms Min.) on the EIS harness (W9) (Ref. FIG. 304/TASK 79-37-00-990-804/FIG. 306/TASK 79-37-00-990-806/FIG. 307/TASK 79-37-00-990-807) (Ref. 79-30-50/79-30-51, WM).Is the harness damaged?
25 Replace the EIS harness (for left-hand engine Ref. 76-13-15-000-801/76-13-15-400-801, MM or for right-hand engine Ref. -Yes 76-13-15-000-802/76-13-15-400-802, MM).Go to block 02.
| No 12Do a check on the aircraft systems (harness, 26 Repair the fault (Ref. 31-41-00/201 EMB signal conditioning unit) (Ref. 31-41-00/501, FIM) (Ref. 79-30-50/79-30-51, WM).Go to -Yes AMM). (Ref. 79-30-50/ 79-30-51, WM).Is a fault block 02. found? | No 13 Go to block 14. Observed Fault: Oil Pressure High (displayed on EICAS) EFFECTIVITY:ALL
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14 Remove and examine each of the four full-flow chip-collector debris monitors on the lube-and-scavenge pump (Ref. 79-21-10-000-803/79-21-10-400-803, MM). Is unwanted material or elastomer found?
27 Do the inspection of the oil filter bypass indicators (Ref. 79-30-00-200-802, MM). Go to -Yes block 02.
| No |
28 Remove the engine from service (Ref. AMM).
Observed Fault: Oil Pressure High (displayed on EICAS) EFFECTIVITY:ALL
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Observed Fault: Oil Temperature High (displayed on EICAS and/or a CMC exceedance) DESCRIPTION: This condition occurs when the oil temperature value measured by the oil-pressure/temperature-transducer sensor is above 126 °C. There are two resistance temperature devices (RTD) in the sensor; RTD 1 supplies a temperature value to the EICAS display, and RTD 2 supplies a temperature value to the central maintenance computer (for detection of exceedance events).
POSSIBLE CAUSES: 1. Blockage in the center-sump scavenge-oil path 2. Air-cooled oil cooler thermal-bypass valve (in the FCOC) 3. Oil-pressure/temperature-transducer sensor / circuit 4. Lube and scavenge pump 5. Low oil level 6. Internal engine failure
R
01 Supply electrical power to the aircraft. 13 Go to block 11. Access the exceedance information from the central maintenance computer (CMC) (Ref. -No 72-00-00/201 AMM). Did an exceedance event for high oil temperature occur at the same time? | Yes 02 Is the oil level in the tank 2 qts., or below?
-Yes
14 Service the oil tank (Ref. 12-10-79-600-801 MM).
| No 03 Remove the four full-flow chip-collector debris monitors on the lube-and-scavenge pump (Ref. 79-21-10-000-803/79-21-10-400-803 MM). Examine the webbing on the four full-flow chip-collector debris monitors for blockage. -Yes Remove the lube-and-scavenge pump (Ref. 79-21-10-000-801/79-21-10-400-801 MM). Examine the filter screen in the AGB port for blockage. Is there blockage on the four full-flow chip-collector debris monitors or the filter screen in the AGB port?
15 Clean the filter screen in the AGB port and the webbing on the four full-flow chip-collector debris monitors to remove all blockage. Go to Block 05.
| No 04 Go to Block 05. Observed Fault: Oil Temperature High (displayed on EICAS and/or a CMC exceedance) EFFECTIVITY:ALL
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05 Examine the scavenge-oil path from the center sump to the lube-and-scavenge pump for blockage (Ref. FIG. 305/TASK 79-37-00-990-805) (Ref. 79-27-30-200-801 MM). Is there blockage found?
-Yes
16 Correct the blockage in the scavenge-oil path (Ref. 79-27-30-200-801 MM).
| No R R R
06 Download trend data (Ref. Introduction) and 17 Rolls-Royce will give the corrective action. send to Rolls-Royce for analysis. Did -Yes Rolls-Royce find problems with the trend data? | No 07 Replace the fuel-cooled oil cooler (FCOC) (Ref. 79-25-15-000-801/79-25-15-400-801 MM). Is the fault removed?
-Yes
18 Remove the FCOC from service.
| No 08 Replace the lube and scavenge pump (Ref. 79-21-10-000-801/79-21-10-400-801 MM). Is the fault removed?
19 Remove the lube and scavenge pump from -Yes service.
| No 09 Replace the air-cooled oil cooler (ACOC) (Ref. 79-25-10-000-801/79-25-10-400-801 MM). Is the fault removed?
-Yes
20 Remove the ACOC from service.
| No 10 Replace the accessory drive gearbox (AGB) (Ref. 72-63-10-000-801/72-63-10-400-801 MM). Is the fault removed?
21 Remove the AGB from service. -Yes
| No |
22 Remove the engine (Ref. 71-00-00/401 AMM).
Observed Fault: Oil Temperature High (displayed on EICAS and/or a CMC exceedance) EFFECTIVITY:ALL
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11 Replace the oil-pressure/temperature transducer sensor (Ref. 79-31-10-000-801/ 79-31-10-400-801 MM). Is the fault removed?
-Yes
23 Remove the sensor from service.
| No 12 Do a test for continuity/resistance (1 ohm max./harness), internal shorts, and shorts to ground (1,000 ohms min.) on the EIS harness (W9) (Ref. FIG. 304/TASK 79-37-00-990-804/FIG. 304/TASK 79-37-00-990-804). Does the harness test satsfactorily?
24 Do the troubleshooting on the aircraft systems (harness, signal conditioning unit) (Ref. 31-41-00/201 EMB FIM) (Ref. -Yes 79-30-50/79-30-51 EMB FIM).
| No |
25 Replace the EIS harness (Ref. 76-00-00 MM).
Observed Fault: Oil Temperature High (displayed on EICAS and/or a CMC exceedance) EFFECTIVITY:ALL
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Observed Fault: Oil Consumption High / Oil Leakage DESCRIPTION: Oil consumption rate is high when it is equal to or more than 0.08 gal/hr (0.32 qts/hr or 10.2 oz/hr or 303 cc/hr). Engine oil consumption rates can increase with engine hours/cycles. A possible sign of oil leakage is if oil consumption is higher than the typical consumption rate for that engine. NOTE: Indications of soot/coking from the breather tube between the 9 and 10 o'clock position on the rear turbine bearing support is normal. NOTE: Spraying the area with a non-aqueous aerosol developer can help find the source of the leak. When finished, make sure that the developer is removed from the engine.
POSSIBLE CAUSES: 1. External leakage 2. Internal leakage
01 Monitor engine oil consumption (Ref. 30 Correct the leakage. 12-10-79-600-801, MM). Examine all of the external -Yes oil tubes and service manifolds for leakage. Is there leakage? | No 02 Examine the FCOC, the ACOC, the oil tank, and the oil filter unit for leakage. Is there leakage?
31 Correct the leakage. If the oil tank is cracked and must be replaced, then replace -Yes the oil-tank pressure relief valve with a new valve (Ref. 79-27-40-000-801/79-27-40-400-801, MM).
| No R 03 Is there oil in the drains mast (Ref. Ch. 54 AMM IPC)?
-No
32 Go to Block 08.
| Yes 04 Go to block 05.
Observed Fault: Oil Consumption High / Oil Leakage
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05 Do TASK 71-00-00-810-803. Was the leakage 33 Replace the O-ring on the aircraft more than the limits (Ref. 72-00-00-700-801, MM) accessory shaft and magnetic carbon seal for from the hydraulic pump, generators, starter pad, or -Yes the applicable accessory on the AGB (Ref. the FPMU seal drain tubes at ground idle or takeoff 72-63-10-000-802/72-63-10-400-802, MM). power? | No R 06 Was there leakage from the pressure relief valve R drain tube?
-No
34 Go to Block 17.
| Yes
R
R 07 Do the pressure test of the accessory gearbox R (Ref. 72-00-00-700-802, MM). Is the pressure more R than 18 psig (124 kPa)? R R R
| Yes
R
-No
35 Go to Block 19.
36 Go to Block 18.
Observed Fault: Oil Consumption High / Oil Leakage
TASK 79−37−00−810−807
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08 Examine the lube and scavenge pump attachment to the AGB. Is there leakage?
-Yes
37 Replace the seals and/or packings (Ref. 79-21-10-000-801/79-21-10-400-801, MM).
| No 09 Remove the outer bypass duct access covers at 38 emove the engine (Ref. AMM). the 8 o'clock and 4 o'clock positions (aft looking forward) (Ref. 72-73-10-000-801, MM). Examine the inner surface of the outer bypass duct for signs of oil. Do the inspection of the rear-turbine bearing -Yes support (RTBS) oil supply and scavenge tubes for signs of leakage because of wear against the RTBS strut. Is there an indication of leakage because of wear? | No 10 Do the inspection of the six o'clock position of the 39 Go to TABLE 601 (Ref. 05-50-00-200-808, inner RTBS at the ends of the 3rd-stage MM) to find the action necessary. low-pressure turbine blades, and at the RTBS and -Yes low-pressure turbine case assembly outer mating splitline. (Note: This is typically accompanied by smoke on shutdown.) Is there an indication of oil? | No 11 Examine the lobes of the mixer between the 7 thru 10 o'clock positions and examine the breather tube located at the 9 o'clock position of the RTBS. Is there an indication of oil (wetting)?
40 Replace the magnetic carbon seal and O-ring behind the AGB breather adapter (Ref. -Yes 72-63-10-000-802/72-63-10-400-802, MM).
| No 12 Examine the air turbine starter (ATS) for external leakage. Is there leakage?
41 Replace the carbon seal on the AGB starter shaft (Ref. -Yes 72-63-10-000-802/72-63-10-400-802, MM), replace the ATS and the O-ring on the ATS output shaft (Ref. 80-10-01, AMM).
| No R 13 Go to Block 14. Observed Fault: Oil Consumption High / Oil Leakage
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R 14 Do the inspection of the engine for oil leakage from the No. 0 carbon seal (Ref. 72-00-00-200-802, -No MM). Is there leakage that extends to the fan case/front frame splitline?
42 Go to Block 21.
| Yes 15 Remove the No. 0 fan carbon seal (Ref. 72-25-25-000-801, MM) and carbon seal runner (Ref. 72-25-40-000-801, MM). Is a fault or damage found with the seal or runner?
43 Replace the No. 0 fan carbon seal (Ref. 72-25-25-400-801, MM) or carbon seal -Yes runner (Ref. 72-25-40-400-801, MM).
| No 16 Is the oil consumption high?
-No
44 Return the engine to service and monitor the oil consumption.
| Yes | 45 Schedule the engine for removal (Ref. AMM).
Observed Fault: Oil Consumption High / Oil Leakage
TASK 79−37−00−810−807
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17 Was the oil pressure 110 psi (758 kPa) or above 46 Remove the engine (Ref. AMM). -Yes at maximum takeoff power (steady state)? | No 18 Does the leakage occur on the oil tank relief valve drain only when the change from ground idle to maximum takeoff power occurs (transient state)?
47 Remove the engine (Ref. AMM) in less -Yes than 200 flight hours.
| No | 48 Schedule the engine for removal (Ref. AMM).
Observed Fault: Oil Consumption High / Oil Leakage
TASK 79−37−00−810−807
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19 Test the oil-tank pressure relief valve (Ref. 79-27-40-700-801, MM). Do TASK 71-00-00-810-803. Was there leakage from the pressure relief valve drain tube?
49 Return the engine to service. -No
| Yes 20 Test the oil-tank pressurization valve (Ref. 79-27-35-700-801, MM). Do TASK 71-00-00-810-803. Was there leakage from the pressure relief valve drain tube?
50 Return the engine to service. -No
| Yes | 51 Schedule the engine for removal (Ref. AMM).
Observed Fault: Oil Consumption High / Oil Leakage
TASK 79−37−00−810−807
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21 Remove the cap from the water wash port. Is there evidence of oil in the water wash port?
52 Schedule the engine for removal (Ref. AMM). Monitor the engine oil consumption -Yes rate (Ref. 12-10-79-600-801, MM) daily until the engine is removed.
| No 22 Install the cap on the water wash port, torque the 53 Schedule the engine for removal (Ref. cap on the water wash port to 80-120 in-lb (9.0-13.6 AMM). Nm) (Ref. 70-00-00-910-801, MM). (NOTE: If necessary, you can remove the inner core bypass -Yes ducts.) Examine the front frame struts. Make sure you examine the front frame struts at the 4 o'clock position (Strut #3) and the 6 o'clock position (Strut #4). Is there leakage? | No 23 Examine the fan speed (N1) sensor, the fan speed (N1) sensor plug, the mid-span bearing housing, and the oil tubes on the inner area of the outer bypass duct. Is there leakage?
54 Correct the leakage. -Yes
| No R 24 Was SB AE 3007A-72-241 done?
-No
55 Go to Block 29.
| Yes R 25 Remove the outer bypass duct access cover at 56 Do SB AE 3007A-75-044. Go to Block 27. the 8 o'clock position (ALF) (Ref. 72-73-10-000-801, MM) Examine the outer surface of the diffuser near -Yes the center sump pressure/vent tube (approximately 4 o'clock) and the inner surface of the outer bypass duct for oil leakage. Is there leakage? | No R 26 Go to Block 27.
Observed Fault: Oil Consumption High / Oil Leakage
TASK 79−37−00−810−807
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27 Examine the outer surface of the diffuser near the center sump scavenge tube (approximately 6 o'clock) and the inner surface of the outer bypass duct for oil leakage. Is there leakage?
-No
57 If oil consumption is not high, return the engine to service and monitor. If oil consumption is high, then schedule the engine for removal (Ref. AMM).
| Yes 28 Replace the center sump vent tube check valve (Ref. 79-27-42-000-801/79-27-42-400-801, MM). Is there leakage?
58 If oil consumption is not high, return the engine to service and monitor. If oil -No consumption is high, then schedule the engine for removal (Ref. AMM).
| Yes 59 Remove the engine (Ref. AMM).
Observed Fault: Oil Consumption High / Oil Leakage
TASK 79−37−00−810−807
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29 Remove the outer bypass duct access cover at the 8 o'clock position (ALF) (Ref. 72-73-10-000-801, MM). Examine the outer surface of the diffuser near -No the oil pressure tube (approximately 6 o'clock) and the oil scavenge tube for oil leakage. Is there leakage?
60 If oil consumption is not high, return the engine to service and monitor. If oil consumption is more than 0.32 qts/hr (0.30 ltr/hr), then schedule the engine for removal (Ref. AMM).
| Yes 61 Do the inspection of the oil tubes (Ref. 79-00-00-200-803, MM).
Observed Fault: Oil Consumption High / Oil Leakage
TASK 79−37−00−810−807
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Observed Fault: Oil or Fuel Smell/Haze in the Cabin
Go to task 72-00-00-810-814.
Observed Fault: Oil or Fuel Smell/Haze in the Cabin EFFECTIVITY:ALL
TASK 79−37−00−810−808 Page 201/202 Feb 15/03
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Observed Fault: Oil Pressure Display Shows Dashes DESCRIPTION: This condition occurs when the oil pressure display on the MFD shows dashes, as compared to a usual oil pressure indication. The engine display can show dashes with the engine stopped. This is not an unusual condition.
POSSIBLE CAUSES:
R
1. Engine is not running 2. Oil pressure/temperature sensor failure 3. EIS harness (W9) 4. Aircraft DAU 5. Aircraft system, signal conditioning fault
01 With the engine running, is the oil pressure display showing dashes?
-No
05 Return the engine to service.
| Yes 02 Do the test of the oil pressure/temperature sensor (Ref. 79-31-10-700-801 MM). Does the sensor test good?
06 Replace the sensor (Ref. -No 79-31-10-000-801/79-31-10-400-801 MM).
| Yes 03 Do a test for continuity/resistance (1 ohm Max./harness), internal shorts, and shorts to ground (1,000 ohms min.) on the EIS harness (W9) (Ref. FIG. 304/TASK 79-37-00-990-804) (Ref. 79-30-50/79-30-51 WM). Does the harness test good?
07 Replace the EIS harness (Ref. 76-00-00 MM). -No
| Yes | R R
04 Replace the aircraft DAU (Ref. Embraer manual) Does the display still show dashes?
-No
08 Return the aircraft to service.
| Yes |
09 Do the troubleshooting on the aircraft systems (harness, signal conditioning unit) (Ref. 79-30-50/79-30-51 WM).
Observed Fault: Oil Pressure Display Shows Dashes EFFECTIVITY:ALL
TASK 79−37−00−810−809 Page 201/202 Oct 20/13
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Magnetic Indicating Plug Installation FIG. 301/TASK 79-37-00-990-801
R EFFECTIVITY:ALL
79−37−TASK SUPPORT Page 301 Aug 15/04
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Electrical Impending-bypass Indicator Installation FIG. 302/TASK 79-37-00-990-802
R EFFECTIVITY:ALL
79−37−TASK SUPPORT Page 302 Aug 15/04
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Low Oil-pressure Sensor Installation FIG. 303/TASK 79-37-00-990-803
R EFFECTIVITY:ALL
79−37−TASK SUPPORT Page 303 Aug 15/04
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Engine Wiring Diagram FIG. 304/TASK 79-37-00-990-804
R EFFECTIVITY:ALL
79−37−TASK SUPPORT Page 304 Aug 15/04
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Oil System Diagram FIG. 305/TASK 79-37-00-990-805
R EFFECTIVITY:ALL
79−37−TASK SUPPORT Page 305 Aug 15/04
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Oil Pressure/Temperature-transducer Sensor Installation FIG. 306/TASK 79-37-00-990-806
R EFFECTIVITY:ALL
79−37−TASK SUPPORT Page 306 Aug 15/04
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Oil Pressure/Temperature-transducer Sensor Installation FIG. 307/TASK 79-37-00-990-807
R EFFECTIVITY:ALL
79−37−TASK SUPPORT Page 307/308 Aug 15/04
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CHAPTER 80 LIST OF EFFECTIVE PAGES
R R R R R R
CHAPTER SECTION OTHER SUBJECT PAGE IDENT DATE 80 Contents 1/ Aug.15/04 2 00-00 101/ Feb.15/03 102 10-00 201 Aug.15/04 10-00 202 Aug.15/04 10-00 201 Aug.15/04 10-00 202 Aug.15/04 10-00 301/ Aug.15/04 302 --------------- END ---------------
CHAPTER SECTION SUBJECT PAGE 80
OTHER IDENT
DATE
C=CONFIG B=BREAKOUT
CHAPTER SECTION SUBJECT PAGE 80
OTHER IDENT
DATE
LIST OF EFFECTIVE PAGES-80 Page 1/2 Oct 20/16
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CHAPTER 80 TABLE OF CONTENTS
SUBJECT
CH-SE-SUB
STARTING FAULT CODE INDEX
80-00-00
ENGINE STARTING FADEC Discrete: STRTFT (bit 11) / (351 / AILRU1) = 1 FADEC Discrete: STRTDF (bit 11) / (264 / AIDIF1) = 1 Task Support
80-10-00
PAGE
EFFECTIVITY
101
201 201 301
80−CONTENTS Page 1/2 Apr 20/16
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FAULT CODE INDEX FAULT CODE
EFFECTIVITY:ALL
FAULT DESCRIPTION
MAINT. MESSAGE
GO TO FIM TASK
80−FAULT CODE INDEX Page 101/102 Feb 15/03
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FADEC Discrete: STRTFT (bit 11) / (351 / AILRU1) = 1 DESCRIPTION: The FADEC does a test of the start/stop switch START circuit. This discrete is set to 1 (fault sensed) when an open or shorted circuit is detected, or if the circuit is in a closed condition for more than 3 seconds.
POSSIBLE CAUSES: 1. Aircraft circuit fault 2. FADEC
01 Disconnect the harness (W1) from the 07 Clean or repair the connector (Ref. FADEC J2 receptacle. Examine the harness 20-50-00 WM). Rotate the FADEC reset/select connector for damage, corrosion, or -Yes switch to the RESET position to remove the contamination. Is the connector contaminated fault (STRTFT (bit 11) = 0). or damaged? | No
R R
02 Supply electrical power to the aircraft and do a test for voltage at pin N of the FADEC J2 receptacle (Ref. FIG. 301/TASK 80-10-00-990-801) (Ref. 80-10-50/80-10-51 WM). Is there 12-15 VDC measured?
-No
08 Replace the FADEC that has the fault (Ref. 73-25-10-000-801/73-25-10-400-801 MM).
| Yes
R R
03 Remove electrical power from all of the FADECs. Put the start/stop switch in the START position and do a test for continuity between pins V and N at the W1 harness connector (Ref. FIG. 301/TASK 80-10-00-990-801) (Ref. 80-10-50/80-10-51 WM). Is there continuity, with resistance less than 10 ohms?
-No
09 Repair the aircraft circuit fault (Ref. 80-10-50/80-10-51 WM). Rotate the FADEC reset/select switch to the RESET position to remove the fault (STRTFT (bit11) = 0).
| Yes 04 Go to Block 05
FADEC Discrete: STRTFT (bit 11) / (351 / AILRU1) = 1 EFFECTIVITY:ALL
TASK 80−10−00−810−802 Page 201 Aug 15/04
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R R
05 With the start/stop switch held in the START position, do a test for continuity between ground and pin N at the W1 harness connector (Ref. FIG. 301/TASK 80-10-00-990-801) (Ref. 80-10-50/80-10-51 WM). Is there continuity?
10 Repair the aircraft circuit fault (Ref. 80-10-50/80-10-51 WM). Rotate the FADEC reset/select switch to the RESET position to -Yes remove the fault (STRTFT (bit 11) = 0).
| No
R
06 Put the start/stop switch in the RUN position and do a test for continuity between pins V and N at the W1 harness connector (Ref. FIG. 301/TASK 80-10-00-990-801) (Ref. 80-10-50/80-10-51 WM). Is there continuity, with resistance between 9.5K and 10.5K ohms?
11 Repair the aircraft circuit fault (Ref. 80-10-50/80-10-51 WM). Rotate the FADEC reset/select switch to the RESET position to -No remove the fault (STRTFT (bit 11) = 0).
| Yes |
12 Replace the FADEC that has the fault (Ref. 73-25-10-000-801/73-25-10-400-801 MM).
FADEC Discrete: STRTFT (bit 11) / (351 / AILRU1) = 1 EFFECTIVITY:ALL
TASK 80−10−00−810−802 Page 202 Aug 15/04
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FADEC Discrete: STRTDF (bit 11) / (264 / AIDIF1) = 1 DESCRIPTION: The FADECs do a lane difference test of the two START circuits for the start/stop switch. This fault occurs when the condition of the circuits (START/STOP/RUN) sensed by FADEC A and B is not the same. The FADECs will not do this test if one of the two START circuits has a fault.
POSSIBLE CAUSES: 1. Aircraft circuit fault 2. FADEC
01 Disconnect the harness (W1) from the J2 receptacles on both FADECs. Examine the harness connectors for damage, corrosion, or contamination. Are the connectors contaminated or damaged?
06 Clean or repair the connector (Ref. 20-50-00 WM). Rotate the FADEC reset/select -Yes switch to the RESET position to remove the fault (STRTDF (bit 11) = 0).
| No
R R
02 Disconnect the harness from the switch 07 Repair the aircraft harness fault (Ref. and do a test for continuity between pins N and 80-10-50/80-10-51 WM). Rotate the FADEC V at both W1 harness connectors (Ref. FIG. -Yes reset/select switch to the RESET position to 301/TASK 80-10-00-990-801) (Ref. remove the fault (STRTDF (bit 11) = 0). 80-10-50/80-10-51 WM). Is there continuity? | No 03 Supply electrical power to the aircraft. Access FADEC discrete label 264, for FADEC A and B, from the central maintenance computer (CMC) (Ref. Introduction). Does STRTDF (bit 11) = 1 for both FADECs?
08 Repair the aircraft circuit fault (Ref. 80-10-50/80-10-51 WM). Rotate the FADEC -Yes reset/select switch to the RESET position to remove the fault (STRTDF (bit 11) = 0).
| No 04 Go to Block 05
FADEC Discrete: STRTDF (bit 11) / (264 / AIDIF1) = 1 EFFECTIVITY:ALL
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05 Record the number of occurrences for this maintenance message. Make sure that CMC INHIBIT is not selected. Rotate the start/stop switch to the START position (no more than 2 seconds) and release. Access the maintenance messages from CMC, for both FADECs. Is there a new occurrence of the message for both FADECs?
-Yes
09 Repair the aircraft circuit fault (Ref. 80-10-50/80-10-51 WM). Rotate the FADEC reset/select switch to the RESET position to remove the fault (STRTDF (bit 11) = 0).
| No |
10 Replace the FADEC that has the fault (Ref. 73-25-10-000-801/73-25-10-400-801 MM).
FADEC Discrete: STRTDF (bit 11) / (264 / AIDIF1) = 1 EFFECTIVITY:ALL
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Start/Stop Switch / FADEC Interface Diagram FIG. 301/TASK 80-10-00-990-801
R EFFECTIVITY:ALL
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