A350-1000 Fcom [PDF]
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A350
FLIGHT CREW OPERATING MANUAL The content of this document is the property of Airbus. It is supplied in confidence and commercial security on its contents must be maintained. It must not be used for any purpose other than that for which it is supplied, nor may information contained in it be disclosed to unauthorized persons. It must not be reproduced in whole or in part without permission in writing from the owners of the copyright. © AIRBUS 2005. All rights reserved.
REFERENCE: VIR A350 FLEET FCOM
ISSUE DATE: 15 MAR 20
Intentionally left blank
TRANSMITTAL LETTER A350
FLIGHT CREW OPERATING MANUAL
Issue date: 15 MAR 20 This is the FLIGHT CREW OPERATING MANUAL at issue date 15 MAR 20 for the A350 and replacing last issue dated 03 FEB 20
VIR A350 FLEET FCOM
TRL P 1/2 15 MAR 20
TRANSMITTAL LETTER A350
FLIGHT CREW OPERATING MANUAL
Intentionally left blank
VIR A350 FLEET FCOM
TRL P 2/2 15 MAR 20
GENERAL SUMMARY OF HIGHLIGHTS AUTHORING MAJOR HIGHLIGHTS A350
FLIGHT CREW OPERATING MANUAL
AIRCRAFT SYSTEMS - 20 - AIRCRAFT GENERAL Localization Title
DSC-20-10 A350 FLEET SPECIFICS
Toc Index G
ID 1
RETO procedures now approved.
AIRCRAFT SYSTEMS - 46 - ONBOARD INFORMATION SYSTEM Localization Title
DSC-46-OIS-30 How To Start the Laptop DSC-46-OIS-30 How To Shutdown the Laptop DSC-46-OIS-30 Additional Controls of the Undocked Laptop
Toc Index
ID
C
1
Editorial change only.
D
2
H
3
Point 1. added and remainder renumbered. Editorial change only. Editorial change only.
PROCEDURES - NORMAL PROCEDURES Localization Title
PRO-NOR-SOP-40 OIS Initialization - Electronic Flight Bag (EFB) PRO-NOR-SOP-250 Parking - EFB PRO-NOR-SOP-260 Securing the Aircraft - Electronic Flight Bag (EFB) PRO-NOR-C-L Introduction PRO-NOR-C-L Reduced Engine Taxi Out PRO-NOR-C-L Reduced Engine Taxi In PRO-NOR-C-L Securing the Aircraft PRO-NOR-TSK Parking PRO-NOR-TSK Securing the Aircraft
VIR A350 FLEET FCOM
Reason
Reason
Toc Index
ID
Reason
G
1
Editorial change only.
A
1
A
2
Parking - EFB procedure updated in total. See separate highlights document for further information. Securing the Aircraft - EFB Procedure updated in total. See separate highlights document for further information.
A
1
C
2
J
3
L
4
T
1
U
2
Reduced Engine Taxi Out and In criteria added to Introduction table. New Reduced Engine Taxi Out Checklist added. See separate highlights document for further details. New Reduced Engine Taxi In Checklist added. See separate highlights document for further details. "ADIRS...AS RQRD" action reverted back to Airbus "ADIRS OFF". Last action added for CM1 and CM2 for shutting down the device. EFB SECURITY LOG action added to CM2 column. Securing the Aircraft procedures updated for when the OIS are blank. Continued on the following page
GSOH-MAJOR P 1/2 15 MAR 20
GENERAL SUMMARY OF HIGHLIGHTS AUTHORING MAJOR HIGHLIGHTS A350
FLIGHT CREW OPERATING MANUAL
Localization Title
PRO-NOR-SUP-SUP-SUP ENGINE PRO-NOR-SUP-SUP-ENG Crossbleed Engine Start - After Start PRO-NOR-SUP-SUP-ENG Reduced Engine Taxi - General PRO-NOR-SUP-SUP-ENG Reduced Engine - Taxi Out PRO-NOR-SUP-SUP-ENG Reduced Engine - Taxi In PRO-NOR-SUP-SUP-MISC General
VIR A350 FLEET FCOM
Continued from the previous page
Toc Index
ID
Reason
A
1
A
1
Menu updated to include Reduced Engine Taxi and All Engine Shutdown procedures. Timings revised from 1 MIN to 30 SECONDS.
H
3
Reduced Engine Taxi procedures added.
I
5
J
6
D
1
New procedure added for Reduced Engine Taxi Out. See separate Highlights document for further details. New procedure added for Reduced Engine Taxi In. See separate Highlights document for further details. Revised procedure title from TAXI OUT to TAXI GUIDANCE & CONSIDERATIONS.
GSOH-MAJOR P 2/2 15 MAR 20
GENERAL SUMMARY OF HIGHLIGHTS OTHER AUTHORING HIGHLIGHTS A350
FLIGHT CREW OPERATING MANUAL
GENERAL INFORMATION Localization Title
GEN-PLP-TOC Main FCOM Changes GEN-PLP-TOC FCOM Revision Management GEN FCOM Contents GEN Abbreviations GEN Abbreviations
Toc Index
ID 1 2
E
Reason Simplification of configuration management Information no longer available New DU to introduce TDU definition
8
L
Addition of the section that contains reference to Abnormal Temporary Behaviors. 11 Addition of REACT abbreviation.
L
12 Addition of the TAB abbreviation.
AIRCRAFT SYSTEMS - 22 - AFS - FLIGHT MANAGEMENT SYSTEM Localization Title
DSC-22-FMS-10-40-20 Purpose DSC-22-FMS-20-20-20 Fuel Planning Table
Toc Index
ID
Reason
G
1
V
1
Addition of a note in layer 2 in order to remind the flight crew to anticipate the insertion of an offset before a lateral turn. Addition of the hypothesis used by the system to compute the final reserve fuel.
AIRCRAFT SYSTEMS - 23 - COMMUNICATION Localization Title
DSC-23-20 Cockpit handset layout DSC-23-20 Soft Menu Selection Keys DSC-23-20 Soft Menu Selection Keys DSC-23-20 Function Keys DSC-23-20 Function Keys DSC-23-20 Area Selection Keys DSC-23-20 Area Selection Keys DSC-23-20
VIR A350 FLEET FCOM
Toc Index
ID
Reason
D
1
Update of the word "button" to "key" for standardization purposes.
D
2
Update of the word "button" to "key" for standardization purposes.
D
3
Update of the word "button" to "key" for standardization purposes.
D
4
Update of the word "button" to "key" for standardization purposes.
D
5
D
6
Update of the word "button" to "key" for standardization purposes. Change of the activation time of emergency call from 5 s to 1 s, in order to clarify the use of EMER BUTTON. Update of the word "button" to "key" for standardization purposes.
D
7
Update of the word "button" to "key" for standardization purposes.
D
8
Update of the word "button" to "key" for standardization purposes. Continued on the following page
GSOH-AUTH P 1/6 15 MAR 20
GENERAL SUMMARY OF HIGHLIGHTS OTHER AUTHORING HIGHLIGHTS A350
FLIGHT CREW OPERATING MANUAL
Localization Title
Interphone Transmission Control Keys DSC-23-20 Interphone Transmission Control Keys DSC-23-20 Push To Talk Key DSC-23-20 Push To Talk Key
Continued from the previous page
Toc Index
ID
Reason
D
9
Update of the word "button" to "key" for standardization purposes.
D
10 Update of the word "button" to "key" for standardization purposes.
D
11 Update of the word "button" to "key" for standardization purposes.
AIRCRAFT SYSTEMS - 24 - ELECTRICAL SYSTEM Localization Title
DSC-24-20 EXT 1(2) pb
Toc Index
ID
Reason
G
1
L
2
Addition of a recommendation to set the GND SVCE sw 1 to OFF before supplying the Aircraft to avoid the display of spurious dispatch messages. Update of the title from 'GND SVCE CTL SW' to GND SVCE CTL 1 SW' in order to differentiate the description of the "GND SVCE CTL 1 SW" from the "GND SVCE CTL 2 SW".
DSC-24-20 GND SVCE CTL 1 sw
AIRCRAFT SYSTEMS - 27 - FLIGHT CONTROLS Localization Title
DSC-27-10-40 Reconfiguration Control Laws
Toc Index
ID
Reason
A
1
Addition of the F/CTL INR FLAPS FAULT in the list of procedures that cause a reversion to alternate law.
Toc Index
ID
Reason
H
1
Addition of an hyperlink to the Abnormal Ops - Fuel Gauging Degradation in Layer 2.
H
2
Addition of an hyperlink to the Abnormal Ops - Fuel Gauging Degradation in Layer 2.
D
1
Addition of detailed accuracy values in order to help the flight crew to determine potential gauging error.
AIRCRAFT SYSTEMS - 28 - FUEL Localization Title
DSC-28-20 WING TANKS - FUEL QUANTITY Indication DSC-28-20 CENTER TANK - FUEL QUANTITY Indication DSC-28-40 Fuel Gauging Degradation
VIR A350 FLEET FCOM
GSOH-AUTH P 2/6 15 MAR 20
GENERAL SUMMARY OF HIGHLIGHTS OTHER AUTHORING HIGHLIGHTS A350
FLIGHT CREW OPERATING MANUAL
AIRCRAFT SYSTEMS - 32 - LANDING GEAR Localization Title
DSC-32-20-10-50 Disarming/Deactivation of the Basic Autobrake Mode DSC-32-20-10-50 Disarming/Deactivation of the Basic Autobrake Mode DSC-32-20-10-50 Disarming/Deactivation of the RTO Mode DSC-32-20-10-50 Disarming/Deactivation of the RTO Mode DSC-32-30-20 Steering Handwheel
Toc Index
ID
A
1
Addition of a new paragraph to clarify the conditions that lead to the autobrake deactivation.
A
2
Update of the paragraph to focus on the conditions that lead to the autobrake disarming.
A
3
Addition of a new paragraph to clarify the conditions that lead to the deactivation of the RTO mode.
A
4
Update of the paragraph to focus on the conditions that lead to the disarming of the RTO mode.
E
1
Addition of a table providing the nose wheel steering angle corresponding to the handwheel graduations.
AIRCRAFT SYSTEMS - 34 - NAVIGATION Localization Title
DSC-34-NAV-30-30 Roll Scale
Toc Index C
ID 1
AIRCRAFT SYSTEMS - 34 - SURVEILLANCE Localization Title
DSC-34-SURV-30-10 Overview DSC-34-SURV-30-10 Principle DSC-34-SURV-30-10 Turbulence Detection (TURB) Function DSC-34-SURV-30-20 WXR TURB OFF DSC-34-SURV-30-20 MFD DSC-34-SURV-30-20 WXR/PWS Button DSC-34-SURV-30-20
VIR A350 FLEET FCOM
Reason
Reason Addition of the description of the possible effect on the display of ISIS roll attitude in the case of a long turn at small bank angle.
Toc Index
ID
Reason
A
1
B
2
D
5
D
1
E
3
E
4
E
5
Update in order to take into account the optional weather hazard prediction function. Update in order to take into account the optional weather hazard prediction function. Update in order to take into account the optional weather hazard prediction function. Correction of the turbulence detection range from 40 NM to 60 NM in order to reflect the exact system design. Update in order to take into account the optional weather hazard prediction function. Update in order to take into account the optional weather hazard prediction function. Update in order to take into account the optional weather hazard prediction function. Correction of a typo. Continued on the following page
GSOH-AUTH P 3/6 15 MAR 20
GENERAL SUMMARY OF HIGHLIGHTS OTHER AUTHORING HIGHLIGHTS A350
FLIGHT CREW OPERATING MANUAL
Localization Title
TURB Button (If Installed)
DSC-34-SURV-30-20 DEFAULT SETTINGS Button DSC-34-SURV-30-20 ND DSC-34-SURV-30-20 Weather Colors DSC-34-SURV-30-20 WXR Messages DSC-34-SURV-70-50 DEFAULT SETTINGS Button
Toc Index E F F F B
Continued from the previous page
ID
Reason
Update in order to take into account the optional weather hazard prediction function. 8 Update in order to take into account the optional weather hazard prediction function. 9 Update in order to take into account the optional weather hazard prediction function. 10 Update in order to take into account the optional weather hazard prediction function. 11 Update in order to take into account the optional weather hazard prediction function. 1 Update in order to take into account the optional weather hazard prediction function.
AIRCRAFT SYSTEMS - 49 - AUXILIARY POWER UNIT Localization Title
DSC-49-30 Automatic APU Start and Bleed Supply
Toc Index A
ID 1
Correction: Replacement of "One of the MAIN L(R) TK fuel pump ..." by "Both Main L(R) TK fuel pumps ..."
PROCEDURES - ABNORMAL AND EMERGENCY PROCEDURES Localization Title
Reason
Toc Index
ID
A
1
Addition of KCCU reset procedure.
I
2
PRO-ABN-ABN-RESET OIS CAB&MAINT Reset
AA
5
PRO-ABN-ABN-RESET OIS CAB&MAINT Reset Procedure
AA
6
J
1
Addition of procedure in order to specify CAB COM CIDS reset procedure in case of DIR 1(2) inoperative under MMEL 44-10-01A. Update of the complete reset duration from 9 min to 12 min in order to provide the maximum time needed to recover applications. Relocation of the ECAM information lines associated with reset duration of applications in order to appropriately provide the information after the flight crew performs the reset of the OIS CAB&MAINT. Addition of a note to refer to the TAB "Erroneous BRAKES G(Y) SYS BRK LOST after landing gear retraction".
E
1
PRO-ABN-ABN-RESET CDS PRO-ABN-ABN-RESET CAB COM CIDS Reset Procedure
PRO-ABN-BRAKES BRAKES G(Y) SYS BRK LOST Alert PRO-ABN-CAB_PRESS
VIR A350 FLEET FCOM
Reason
Removal of procedure line "ATC COM EMER MSG..CONSIDER" in order to be in line with the FWS standard. Continued on the following page
GSOH-AUTH P 4/6 15 MAR 20
GENERAL SUMMARY OF HIGHLIGHTS OTHER AUTHORING HIGHLIGHTS A350
FLIGHT CREW OPERATING MANUAL
Localization Title
CAB PRESS EXCESS CAB ALT Alert PRO-ABN-ENG [ABN] ENG RELIGHT IN FLT - Alert PRO-ABN-F_CTL F/CTL INR FLAPS FAULT - Alert PRO-ABN-F_CTL F/CTL INR FLAPS FAULT - Fwspage
Toc Index
ID
A
2
X X
PRO-ABN-HYD HYD G(Y) SYS PRESS LO Fwspage
J
PRO-ABN-HYD HYD G(Y) SYS PRESS LO Fwspage
J
PRO-ABN-SURV [MEM] WINDSHEAR WARNING PREDICTIVE WINDSHEAR - Alert
E
Addition of procedure line "PACK 1+2...OFF" and "PACK 1+2...ON" to reflect actual condition of FWS S6. 1 Addition of the associated procedure F/CTL ALTN LAW (PROT LOST) 2 Addition of F/CTL PROT as INOP SYS and ALTN LAW : PROT LOST as STATUS information because the F/CTL INR FLAPS FAULT alert is associated with a reversion to alternate law. 11 Update of the indication in the INOP SYS "N/W STEER (If Y SYS PRESS LO) instead of "N/W+BKUP STEER (If Y SYS PRESS LO)". In case of failure of the yellow hydraulic system, only the N/W Steering is lost. 13 Update of the indication in the INOP SYS "N/W STEER (If Y SYS PRESS LO) instead of "N/W+BKUP STEER (If Y SYS PRESS LO)". In case of failure of the yellow hydraulic system, only the N/W Steering is lost. 1 Addition of a note to specify the pitch value to be targeted if the FD bars are not displayed.
PROCEDURES - NORMAL PROCEDURES Localization Title
PRO-NOR-SOP-50 Exterior Walkaround - Nose Section PRO-NOR-SOP-260 Securing the Aircraft - EXT Power PRO-NOR-SUP-SUP-ADVWXR Airframe Deicing/Anti-icing Procedure on Ground PRO-NOR-SUP-SUP-ENG Engine Start with An Air Start Unit After Start
Toc Index
ID
D
1
A
1
A
1
D
2
Addition of the procedure information to keep ENG idle for 1 minute in order to cover anti-ice faults of the engine stator section.
ID
Reason
PROCEDURES - SPECIAL OPERATIONS Localization Title
PRO-SPO-RVSM Flight Preparation
VIR A350 FLEET FCOM
Continued from the previous page
Reason
Toc Index B
1
Reason Correction from "ICE DETECTION VISUAL INDICATOR" to "WIPERS". Addition of a new information to indicate the recommended order to disconnect the EXT PWR. Addition of a waiting time of 1 minute to reduce the risk of contamination of the BLEED system after spraying operations.
Addition of the "GPS ALT" to the list of indications to check. Continued on the following page
GSOH-AUTH P 5/6 15 MAR 20
GENERAL SUMMARY OF HIGHLIGHTS OTHER AUTHORING HIGHLIGHTS A350
FLIGHT CREW OPERATING MANUAL
Localization Title
PRO-SPO-RVSM In Flight PRO-SPO-RVSM Abnormal and Emergency Procedures PRO-SPO-PRM Overview
ID
B
2
Addition of the "GPS ALT" to the list of indications to check.
B
3
Addition of the "GPS Alt" indication displayed in the event of the loss of the altimeter system redundancy.
A
1
Update of the Simultaneous Parallel Approach Operations procedure to cover the possibility of RNAV(GNSS)/RNAV(RNP)/GLS approaches and to provide an enhanced description.
LIMITATIONS - AIRCRAFT GENERAL Localization Title
LIM-AG-OPS Maximum Crosswind for Takeoff and Landing
Continued from the previous page
Toc Index
Toc Index B
Reason
ID 1
Reason Update of the landing maximum crosswind limit from 35kt up to 40kt for dry and damp conditions.
LIMITATIONS - TRANSMITTING PORTABLE ELECTRONIC DEVICE Localization Title
LIM-T-PED Transmitting Portable Electronic Device
PERFORMANCE - LANDING Localization Title
PER-LDG-30 Runway Condition Assessment Matrix for Landing
VIR A350 FLEET FCOM
Toc Index
ID
Reason
A
1
Addition of the Bluetooth or any low power technology that can be used in the flight deck because it is less restrictive than the WI-FI.
Toc Index
ID
Reason
D
1
Update of the landing maximum crosswind limit from 35kt up to 40kt for dry and damp conditions.
GSOH-AUTH P 6/6 15 MAR 20
GENERAL SUMMARY OF HIGHLIGHTS EFFECTIVITY HIGHLIGHTS A350
FLIGHT CREW OPERATING MANUAL
AIRCRAFT SYSTEMS - 29 - HYDRAULIC SYSTEM Localization Title
DSC-29-10 Fire Shut-off Valve DSC-29-10 Hydraulic Monitoring and Control (HMC) DSC-29-20 GREEN(YELLOW) ELEC PMP pb-sw DSC-29-20 GREEN(YELLOW) ENG 1(2) PUMP pb-sw DSC-29-20 GREEN(YELLOW) ENG 1(2) SUPPLY pb DSC-29-20 HYD SD page DSC-29-20 OVHT Indication DSC-29-20 Fire Shut-off Valve DSC-29-20 EDP DSC-29-30 Excessive Temperature in the Hydraulic System
Toc Index
ID
B
1
Effectivity update: The information no longer applies to all ACN.
B
3
Effectivity update: The information no longer applies to all ACN.
B
1
Effectivity update: The information no longer applies to all ACN.
C
3
Effectivity update: The information no longer applies to all ACN.
C
5
Effectivity update: The information no longer applies to all ACN.
D
7
Effectivity update: The information no longer applies to all ACN.
D
9
Effectivity update: The information no longer applies to all ACN.
D
11 Effectivity update: The information no longer applies to all ACN.
D
13 Effectivity update: The information no longer applies to all ACN.
A
1
Effectivity update: The information no longer applies to all ACN.
AIRCRAFT SYSTEMS - 34 - SURVEILLANCE Localization Title
DSC-34-SURV-30-10 Automatic Mode DSC-34-SURV-30-10 On Path Envelope Boundaries Definition
Toc Index
ID
Reason
B
3
Effectivity update: The information now applies to all ACN.
C
4
Effectivity update: The information now applies to all ACN.
PROCEDURES - ABNORMAL AND EMERGENCY PROCEDURES Localization Title
PRO-ABN-ENG [ABN] ENG RELIGHT IN FLT - Alert
VIR A350 FLEET FCOM
Reason
Toc Index A
ID 1
Reason
Effectivity update: The information now applies to all ACN. Continued on the following page
GSOH-EFF P 1/2 15 MAR 20
GENERAL SUMMARY OF HIGHLIGHTS EFFECTIVITY HIGHLIGHTS A350
FLIGHT CREW OPERATING MANUAL
Localization Title
PRO-ABN-ENG ENG 1(2) SHUTDOWN - Alert PRO-ABN-HYD HYD G(Y) SYS PRESS LO PRO-ABN-HYD HYD G(Y) SYS TEMP HI PRO-ABN-HYD HYD G(Y) SYS TEMP HI - Alert PRO-ABN-HYD HYD G(Y) SYS TEMP HI - Fwspage PRO-ABN-HYD HYD G(Y) SYS OVHT PRO-ABN-HYD HYD G(Y) SYS OVHT - Alert
Toc Index AU
ID 3
PRO-NOR-SOP-90 After Start - ENG Start Selector PRO-NOR-SUP-SUP-ENG Reduced Engine Taxi - General
LIMITATIONS - ENGINES Localization Title
LIM-ENG Shaft Speeds
VIR A350 FLEET FCOM
Effectivity update: The information now applies to all ACN.
J
10 Effectivity update: The information no longer applies to all ACN.
K
14 Effectivity update: The information no longer applies to all ACN.
K
15 Effectivity update: The information no longer applies to all ACN.
K
16 Effectivity update: The information no longer applies to all ACN.
L
17 Effectivity update: The information no longer applies to all ACN.
L
18 Effectivity update: The information no longer applies to all ACN.
PROCEDURES - NORMAL PROCEDURES Localization Title
Continued from the previous page
Reason
Toc Index
ID
A
1
Effectivity update: The information now applies to all ACN.
H
4
Effectivity update: The information now applies to all ACN.
Toc Index
ID
B
1
Reason
Reason Effectivity update: The information now applies to all ACN.
GSOH-EFF P 2/2 15 MAR 20
GENERAL SUMMARY OF HIGHLIGHTS AUTOMATIC HIGHLIGHTS A350
FLIGHT CREW OPERATING MANUAL
GENERAL INFORMATION Localization Title
GEN-PLP-TOC Main FCOM Changes
Toc Index
GEN-PLP-TOC FCOM Revision Management GEN TURB button GEN Weather Hazard Prediction Function GEN February 2020 GEN January 2020 GEN December 2019 GEN November 2019 GEN October 2019 GEN TDU General Description
VIR A350 FLEET FCOM
ID
Reason
1
Documentation update: Deletion of the "00025118 May 2019" table of content entry. Documentation update: Deletion of the "00025086 April 2019" table of content entry. Documentation update: Deletion of the "00025229.0001001 August 2019" documentary unit. Documentation update: Deletion of the "00025173.0001001 July 2019" documentary unit. Documentation update: Deletion of the "00025155.0001001 June 2019" documentary unit. Documentation update: Deletion of the "00025118.0001001 May 2019" documentary unit. Documentation update: Deletion of the "00025086.0001001 April 2019" documentary unit. Documentation update: Deletion of the "00025229 August 2019" table of content entry. Documentation update: Deletion of the "00025173 July 2019" table of content entry. Documentation update: Deletion of the "00025155 June 2019" table of content entry. Documentation update: Deletion of the "00020885 Temporary Information" table of content entry. Documentation update: Deletion of the "00020885.0001001 Temporary Information" documentary unit. Documentation update: Addition of "TURB button" documentary unit Documentation update: Addition of "Weather Hazard Prediction Function" documentary unit Documentation update: Addition of "February 2020" documentary unit Documentation update: Addition of "January 2020" documentary unit Documentation update: Addition of "December 2019" documentary unit Documentation update: Addition of "November 2019" documentary unit Documentation update: Addition of "October 2019" documentary unit Documentation update: Addition of "TDU General Description" documentary unit Continued on the following page
2
B
1
B
2
C
3
C
4
C
5
C
6
C
7
J
9
GSOH-AUTO P 1/8 15 MAR 20
GENERAL SUMMARY OF HIGHLIGHTS AUTOMATIC HIGHLIGHTS A350
FLIGHT CREW OPERATING MANUAL
Localization Title
GEN TAB General Description
Toc Index K
Continued from the previous page
ID
Reason
10 Documentation update: Addition of "TAB General Description" documentary unit
AIRCRAFT SYSTEMS - PRELIMINARY PAGES Localization Title
DSC-PLP-TOC 28 - Fuel
Toc Index
ID 1
Reason
Documentation update: Deletion of the "PP04719 Temporary Abnormal Behaviors" table of content entry. Documentation update: Deletion of the "00025074.0001001 Erroneous Variations of FQI and FOB" documentary unit.
AIRCRAFT SYSTEMS - 22 - AFS - FLIGHT MANAGEMENT SYSTEM Localization Title
Toc Index
ID
DSC-22-FMS-30 How To manage FMS Erroneous Predictions DSC-22-FMS-30 How To Change Departure T.O Data after Rejected Takeoff DSC-22-FMS-40 Display of ERRONEOUS Fix Info on the ND
A
1
B
2
Documentation update: Addition of "How To Change Departure T.O Data after Rejected Takeoff" documentary unit
H
1
Documentation update: Addition of "Display of ERRONEOUS Fix Info on the ND" documentary unit
DSC-22-FMS-PLP-TOC Temporary Abnormal Behaviors
1
Documentation update: Deletion of the "00024162 Display of Erroneous Fix Info on the ND" table of content entry. Documentation update: Deletion of the "00024162.0001001 Display of ERRONEOUS Fix Info on the ND" documentary unit. Documentation update: Addition of "How To manage FMS Erroneous Predictions" documentary unit
AIRCRAFT SYSTEMS - 23 - COMMUNICATION Localization Title
DSC-23-20 Cockpit handset layout
Toc Index D
ID 1
DSC-24-20
VIR A350 FLEET FCOM
Toc Index L
Reason
Documentation update: Deletion of information.
AIRCRAFT SYSTEMS - 24 - ELECTRICAL SYSTEM Localization Title
Reason
ID
Reason
3
Documentation update: Deletion of text. Continued on the following page
GSOH-AUTO P 2/8 15 MAR 20
GENERAL SUMMARY OF HIGHLIGHTS AUTOMATIC HIGHLIGHTS A350
FLIGHT CREW OPERATING MANUAL
Localization Title
GND SVCE CTL 1 sw DSC-24-20 GND SVCE CTL 2 sw
Toc Index
ID
L
4
Continued from the previous page
Reason
Documentation update: Addition of "GND SVCE CTL 2 sw" documentary unit
AIRCRAFT SYSTEMS - 27 - FLIGHT CONTROLS Localization Title
DSC-27-20-33 Inhibition of the flap retraction in the case of a spoiler failure
Toc Index
ID
Reason
A
1
Documentation update: Addition of "Inhibition of the flap retraction in the case of a spoiler failure" documentary unit
Toc Index
ID
Reason
D
1
AIRCRAFT SYSTEMS - 28 - FUEL Localization Title
DSC-28-PLP-TOC 28 - Fuel
DSC-28-40 Fuel Gauging Degradation
1
Documentation update: Deletion of the "PP04719 Temporary Abnormal Behaviors" table of content entry. Documentation update: Deletion of the "00025074.0001001 Erroneous Variations of FQI and FOB" documentary unit. Documentation update: Deletion of text.
AIRCRAFT SYSTEMS - 29 - HYDRAULIC SYSTEM Localization Title
DSC-29-10 Fire Shut-off Valve DSC-29-10 Hydraulic Monitoring and Control (HMC) DSC-29-20 GREEN(YELLOW) ELEC PMP pb-sw DSC-29-20 GREEN(YELLOW) ENG 1(2) PUMP pb-sw DSC-29-20 GREEN(YELLOW) ENG 1(2) SUPPLY pb DSC-29-20 HYD SD page
VIR A350 FLEET FCOM
Toc Index
ID
Reason
B
2
B
4
B
2
C
4
C
6
Documentation update: Addition of "GREEN(YELLOW) ENG 1(2) SUPPLY pb" documentary unit
D
8
Documentation update: Addition of "HYD SD page" documentary unit Continued on the following page
Documentation update: Addition of "Fire Shut-off Valve" documentary unit Documentation update: Addition of "Hydraulic Monitoring and Control (HMC)" documentary unit Documentation update: Addition of "GREEN(YELLOW) ELEC PMP pb-sw" documentary unit Documentation update: Addition of "GREEN(YELLOW) ENG 1(2) PUMP pb-sw" documentary unit
GSOH-AUTO P 3/8 15 MAR 20
GENERAL SUMMARY OF HIGHLIGHTS AUTOMATIC HIGHLIGHTS A350
FLIGHT CREW OPERATING MANUAL
Localization Title
DSC-29-20 RESERVOIR OVHT Indication DSC-29-20 Fire Shut-off Valve DSC-29-20 EDP DSC-29-20 EDP OVHT Indication DSC-29-30 Excessive Temperature in the Hydraulic System
Toc Index D D D D A
ID
10 Documentation update: Addition of "RESERVOIR OVHT Indication" documentary unit 12 Documentation update: Addition of "Fire Shut-off Valve" documentary unit 14 Documentation update: Addition of "EDP" documentary unit 15 Documentation update: Addition of "EDP OVHT Indication" documentary unit 2 Documentation update: Addition of "Excessive Temperature in the Hydraulic System" documentary unit
AIRCRAFT SYSTEMS - 32 - LANDING GEAR Localization Title
DSC-32-20-25 Erroneous BRAKES G(Y) SYS BRK LOST after landing gear retraction
Toc Index A
ID 1
AIRCRAFT SYSTEMS - 34 - SURVEILLANCE Localization Title
DSC-34-SURV-PLP-TOC WX Display Function DSC-34-SURV-30-10 Weather Hazard Prediction Function DSC-34-SURV-30-20 WXR HZD OFF (If Installed) DSC-34-SURV-30-20 MFD DSC-34-SURV-30-20 TURB TICK BOX (If Installed) DSC-34-SURV-30-20 HZD TICK BOX (If Installed) DSC-34-SURV-30-20 WXR Messages DSC-34-SURV-30-20 Weather Hazard Prediction Indications
VIR A350 FLEET FCOM
Toc Index
ID
E
6
D
2
E
3
E
6
E F F
Continued from the previous page
Reason
1
Reason Documentation update: Addition of "Erroneous BRAKES G(Y) SYS BRK LOST after landing gear retraction" documentary unit
Reason Documentation update: Deletion of the "00003427.0001001 Automatic Mode" documentary unit. Documentation update: Addition of "Weather Hazard Prediction Function (If Installed)" documentary unit Documentation update: Addition of "WXR HZD OFF (If Installed)" documentary unit Documentation update: Deletion of text.
Documentation update: Addition of "TURB TICK BOX (If Installed)" documentary unit 7 Documentation update: Addition of "HZD TICK BOX (If Installed)" documentary unit 11 Documentation update: Deletion of information. 12 Documentation update: Addition of "Weather Hazard Prediction Indications (If Installed)" documentary unit
GSOH-AUTO P 4/8 15 MAR 20
GENERAL SUMMARY OF HIGHLIGHTS AUTOMATIC HIGHLIGHTS A350
FLIGHT CREW OPERATING MANUAL
PROCEDURES - ABNORMAL AND EMERGENCY PROCEDURES Localization Title
PRO-ABN-PLP-TOC [ABN] ENG RELIGHT IN FLT PRO-ABN-PLP-TOC ENG 1(2) SHUTDOWN PRO-ABN-PLP-TOC [ABN] FUEL LEAK PRO-ABN-PLP-TOC FUEL LEAK SUSPECTED PRO-ABN-ABN-RESET CAB COM CIDS Reset Procedure
PRO-ABN-ABN-RESET CDS CAPT(F/O) KCCU Reset PRO-ABN-ABN-RESET CDS KCCU Reset Procedure PRO-ABN-ABN-RESET OIS CAB&MAINT Reset Procedure PRO-ABN-CAB_PRESS CAB PRESS EXCESS CAB ALT Alert PRO-ABN-FUEL [ABN] FUEL LEAK PRO-ABN-FUEL FUEL LEAK SUSPECTED - ALERT PRO-ABN-HYD HYD ENG 1(2) G(Y) PMP FAULT PRO-ABN-HYD HYD ENG 1(2) G(Y) PMP FAULT Procdesc PRO-ABN-HYD
VIR A350 FLEET FCOM
Toc Index
ID
Reason
1
I
2
M
3
M
4
AA
6
Documentation update: Deletion of the "00008659.0002001 [ABN] ENG RELIGHT IN FLT - Alert" documentary unit. Documentation update: Deletion of the "00008608.0008001 ENG 1(2) SHUTDOWN - Alert" documentary unit. Documentation update: Deletion of the "00014893.0002001 [ABN] FUEL LEAK" documentary unit. Documentation update: Deletion of the "00007957.0003001 FUEL LEAK SUSPECTED - Alert" documentary unit. Documentation update: Information "P.00022437.0001001.031" moved from "P.00022437.0001001.030" to "P.00022437.0001001.105" Documentation update: Information "P.00022437.0001001.032" moved from "P.00022437.0001001.030" to "P.00022437.0001001.105" Documentation update: Information "P.00022437.0001001.034" moved from "P.00022437.0001001.030" to "P.00022437.0001001.105" Documentation update: Information "P.00022437.0001001.037" moved from "P.00022437.0001001.030" to "P.00022437.0001001.105" Documentation update: Addition of "CDS CAPT(F/O) KCCU Reset" documentary unit Documentation update: Addition of "CDS KCCU Reset Procedure" documentary unit Documentation update: Deletion of information.
E
1
Documentation update: Deletion of information.
A
1
V
2
B
1
B
2
Documentation update: Addition of "[ABN] FUEL LEAK" documentary unit Documentation update: Addition of "FUEL LEAK SUSPECTED Alert" documentary unit Documentation update: Addition of "HYD ENG 1(2) G(Y) PMP FAULT" documentary unit Documentation update: Addition of "HYD ENG 1(2) G(Y) PMP FAULT - Procdesc" documentary unit
B
3
2 3 4
Documentation update: Addition of "HYD ENG 1(2) G(Y) PMP FAULT - Alert" documentary unit Continued on the following page
GSOH-AUTO P 5/8 15 MAR 20
GENERAL SUMMARY OF HIGHLIGHTS AUTOMATIC HIGHLIGHTS A350
FLIGHT CREW OPERATING MANUAL
Localization Title
HYD ENG 1(2) G(Y) PMP FAULT Alert PRO-ABN-HYD HYD ENG 1(2) G(Y) PMP FAULT Fwspage PRO-ABN-HYD HYD G(Y) RSVR OVHT PRO-ABN-HYD HYD G(Y) RSVR OVHT - Alert PRO-ABN-HYD HYD G(Y) RSVR TEMP HI PRO-ABN-HYD HYD G(Y) RSVR TEMP HI - Alert PRO-ABN-HYD HYD G(Y) RSVR TEMP HI Fwspage PRO-ABN-HYD HYD G(Y) SYS PRESS LO
ID
B
4
Documentation update: Addition of "HYD ENG 1(2) G(Y) PMP FAULT - Fwspage" documentary unit
F
5
F
6
H
7
H
8
H
9
Documentation update: Addition of "HYD G(Y) RSVR OVHT" documentary unit Documentation update: Addition of "HYD G(Y) RSVR OVHT Alert" documentary unit Documentation update: Addition of "HYD G(Y) RSVR TEMP HI" documentary unit Documentation update: Addition of "HYD G(Y) RSVR TEMP HI Alert" documentary unit Documentation update: Addition of "HYD G(Y) RSVR TEMP HI Fwspage" documentary unit
J
12 Documentation update: Addition of "HYD G(Y) SYS PRESS LO" documentary unit
PROCEDURES - NORMAL PROCEDURES Localization Title
PRO-NOR-PLP-TOC Fire Test/APU Start PRO-NOR-PLP-TOC After Start
PRO-NOR-PLP-TOC Engine
VIR A350 FLEET FCOM
Continued from the previous page
Toc Index
Toc Index
Reason
ID
Reason
1
Documentation update: Deletion of the "00005590.0002001 Fire Test/APU Start - APU Start" documentary unit. Documentation update: The "After Start - ENG Start Selector" table of content entry renamed in "After Start - ENG Start Selector - TDU" Documentation update: Deletion of the "00024673 After Start APU Bleed - TDU" table of content entry. Documentation update: Deletion of the "00024191.0001001 After Start - ENG Start Selector" documentary unit. Documentation update: Deletion of the "00024192 After Start Anti-Ice - TDU" table of content entry. Documentation update: The "One Engine Taxi - General" table of content entry renamed in "Reduced Engine Taxi - General" Documentation update: Deletion of the "00021974.0002001 Reduced Engine Taxi - Contingencies" documentary unit. Documentation update: Deletion of the "21400070 Reduced Engine Taxi Out MFD C/L" table of content entry. Continued on the following page
2
3
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GENERAL SUMMARY OF HIGHLIGHTS AUTOMATIC HIGHLIGHTS A350
FLIGHT CREW OPERATING MANUAL
Localization Title
Toc Index
ID
PRO-NOR-SOP-40 Fire Test/APU Start - APU Start PRO-NOR-SUP-SUP-ADVWXR Airframe Deicing/Anti-icing Procedure on Ground PRO-NOR-SUP-SUP-ENG Reduced Engine Taxi - General
I
2
A
1
H
3
PROCEDURES - SPECIAL OPERATIONS Localization Title
PRO-SPO-PLP-TOC Simultaneous Parallel Approach Operations
Toc Index
LIMITATIONS - PRELIMINARY PAGES Localization Title
LIM-PLP-TOC Engines
VIR A350 FLEET FCOM
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Continued from the previous page
Reason
Documentation update: The "Reduced Engine Taxi - Guidance" table of content entry renamed in "Reduced Engine Taxi General" Documentation update: The "Reduced Engine Taxi Considerations" table of content entry renamed in "Reduced Engine Taxi - General" Documentation update: Deletion of the "21400071 Reduced Engine Taxi In MFD C/L" table of content entry. Documentation update: The "Reduced Engine Taxi - General" table of content entry moved from "PG02386" to "PP04319" Documentation update: Deletion of the "PG02386 Reduced Engine Taxi" table of content entry. Documentation update: Deletion of the "00021974.9001002 Reduced Engine Taxi - General" documentary unit. Documentation update: The "Reduced Engine Taxi Contingencies" table of content entry renamed in "Reduced Engine Taxi - General" Documentation update: Addition of "Fire Test/APU Start - APU Start" documentary unit Documentation update: Deletion of information. Documentation update: Addition of "Reduced Engine Taxi General" documentary unit
ID
Reason
1
Documentation update: The "ILS Precision Runway Monitor" table of content entry renamed in "Simultaneous Parallel Approach Operations"
ID
Reason
1
Documentation update: Deletion of the "00016270.0003001 Shaft Speeds" documentary unit.
GSOH-AUTO P 7/8 15 MAR 20
GENERAL SUMMARY OF HIGHLIGHTS AUTOMATIC HIGHLIGHTS A350
FLIGHT CREW OPERATING MANUAL
LIMITATIONS - AIRCRAFT GENERAL Localization Title
LIM-AG-PLP-TOC Weights
LIMITATIONS - ENGINES Localization Title
LIM-ENG-PLP-TOC Engines
Toc Index
ID
Reason
1
Documentation update: Deletion of the "PG02589 Weight Limitations" table of content entry. Documentation update: The "Weight Limitations" table of content entry moved from "PG02589" to "PP04506" Documentation update: The "Takeoff Weight Limitations" table of content entry moved from "PG02589" to "PP04506" Documentation update: The "Landing Weight Limitations" table of content entry moved from "PG02589" to "PP04506"
Toc Index
ID
Reason
1
Documentation update: Deletion of the "00016270.0003001 Shaft Speeds" documentary unit.
Toc Index
ID
Reason
1
A
1
Documentation update: Deletion of the "00024163 AUTO FLT Display of Erroneous FIX INFO on the ND" table of content entry. Documentation update: Deletion of the "00025073 FUEL Erroneous Variations of FQI and FOB" table of content entry. Documentation update: Deletion of the "00024163.0001001 AUTO FLT - Display of Erroneous FIX INFO on the ND" documentary unit. Documentation update: Deletion of the "00025073.0001001 FUEL - Erroneous Variations of FQI and FOB" documentary unit. Documentation update: Addition of "Erroneous BRAKES G(Y) SYS BRK LOST after landing gear retraction" documentary unit
TEMPORARY ABNORMAL BEHAVIORS Localization Title
TAB-PLP-TOC Temporary Abnormal Behaviors Table
TAB Erroneous BRAKES G(Y) SYS BRK LOST after landing gear retraction
VIR A350 FLEET FCOM
GSOH-AUTO P 8/8 15 MAR 20
PRELIMINARY PAGES
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PLP-LESS GEN-PLP-LETDU GEN DSC-PLP-LETDU DSC-20-10 DSC-20-20-10 DSC-20-20-20 DSC-20-20-30 DSC-20-20-40 DSC-20-20-50 DSC-20-20-60 DSC-20-30 DSC-21-COND-10-10 DSC-21-COND-10-20 DSC-21-COND-10-30 DSC-21-COND-10-40 DSC-21-COND-20 DSC-21-COND-30 DSC-21-VENT-10-10 DSC-21-VENT-10-25 DSC-21-VENT-10-30 DSC-21-VENT-10-40 DSC-21-VENT-10-45 DSC-21-VENT-10-50 DSC-21-VENT-10-60-10 DSC-21-VENT-10-60-20 DSC-21-VENT-10-65 DSC-21-VENT-10-70 DSC-21-VENT-20 DSC-21-PRESS-10 DSC-21-PRESS-20 DSC-21-PRESS-30 DSC-21-PRESS-40 DSC-21-PRESS-45 DSC-22-27-10-10 DSC-22-27-10-20 DSC-22-27-20 DSC-22-INT DSC-22-FG-10 DSC-22-FG-30-10
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Subsection Title
Rev. Date
LIST OF EFFECTIVE SECTIONS/SUBSECTIONS 15 MAR 20 LIST OF EFFECTIVE TEMPORARY DOCUMENTARY UNITS 15 MAR 20 General Information 15 MAR 20 LIST OF EFFECTIVE TEMPORARY DOCUMENTARY UNITS 01 JUL 19 Overview 15 MAR 20 Main Dimensions 01 JUL 19 Antenna Locations 01 JUL 19 Unpressurized Areas 01 JUL 19 Ground Clearance Diagram 01 JUL 19 Landing Geometry 01 JUL 19 Visual Ground Geometry 01 JUL 19 Ground Handling 01 JUL 19 Overview 01 JUL 19 Air Conditioning Generation 01 JUL 19 Temperature and Flow Regulation 03 FEB 20 Supplemental Cooling System 01 JUL 19 Controls and Indicators 03 FEB 20 Abnormal Operations 01 JUL 19 Overview 01 JUL 19 Cockpit Ventilation 01 JUL 19 Cabin Ventilation 01 JUL 19 Aft Cargo Ventilation 01 JUL 19 Bulk Cargo Ventilation 01 JUL 19 FWD Cargo Ventilation 03 FEB 20 System Description 01 JUL 19 Abnormal Operations 01 JUL 19 Commercial Equipment Ventilation 01 JUL 19 Pack Bay Ventilation 01 JUL 19 Controls and Indicators 01 JUL 19 System Description 01 JUL 19 Controls and Indicators 01 JUL 19 Normal Operations 01 JUL 19 Abnormal Operations 01 JUL 19 Temporary Abnormal Behaviors 01 JUL 19 Reference Speeds 01 JUL 19 Operating Speeds 01 JUL 19 Protections 03 FEB 20 22 - AFS - Introduction 01 JUL 19 General 01 JUL 19 General 01 JUL 19 Continued on the following page
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DSC-22-FG-30-20 DSC-22-FG-30-30 DSC-22-FG-30-40 DSC-22-FG-30-50 DSC-22-FG-40-10 DSC-22-FG-40-20 DSC-22-FG-40-30 DSC-22-FG-40-40 DSC-22-FG-50-10 DSC-22-FG-50-20 DSC-22-FG-50-30 DSC-22-FG-50-40 DSC-22-FG-50-50 DSC-22-FG-50-60 DSC-22-FG-60-10 DSC-22-FG-60-20 DSC-22-FG-60-30 DSC-22-FG-60-40 DSC-22-FG-70-10 DSC-22-FG-70-20-10 DSC-22-FG-70-20-30 DSC-22-FG-70-20-40 DSC-22-FG-70-20-50 DSC-22-FG-70-30-10 DSC-22-FG-70-30-20 DSC-22-FG-70-30-30 DSC-22-FG-70-40-10 DSC-22-FG-70-40-20 DSC-22-FG-70-40-30 DSC-22-FG-70-50-10 DSC-22-FG-70-50-20 DSC-22-FG-70-50-30 DSC-22-FG-70-60-10 DSC-22-FG-70-60-20 DSC-22-FG-70-60-30 DSC-22-FG-70-60-40 DSC-22-FG-70-70 DSC-22-FG-70-80-00 DSC-22-FG-70-80-10
VIR A350 FLEET FCOM
Subsection Title
FD Display FD Engagement FD Disengagement FD Warnings General AP Engagement AP Disengagement AP in Protection General Thrust Levers A/THR Arming and Activation A/THR Disconnection A/THR Modes Scenario Examples General Managed Speed/Mach Selected Speed/Mach Speed/Mach Switching General General SRS TO Mode RWY Mode RWY TRK Mode General HDG/TRACK Mode NAV Mode General OP CLB Mode CLB Mode General Altitude Acquire Modes Altitude Hold Modes General OP DES DES EMER DES V/S / FPA Mode General LOC* Mode
Rev. Date
01 JUL 19 01 JUL 19 01 JUL 19 01 JUL 19 01 JUL 19 01 JUL 19 01 JUL 19 01 JUL 19 01 JUL 19 01 JUL 19 01 JUL 19 01 JUL 19 01 JUL 19 01 JUL 19 01 JUL 19 01 JUL 19 01 JUL 19 01 JUL 19 01 JUL 19 01 JUL 19 01 JUL 19 01 JUL 19 01 JUL 19 01 JUL 19 01 JUL 19 01 JUL 19 01 JUL 19 01 JUL 19 01 JUL 19 01 JUL 19 01 JUL 19 01 JUL 19 01 JUL 19 01 JUL 19 01 JUL 19 01 JUL 19 01 JUL 19 01 JUL 19 01 JUL 19 Continued on the following page
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DSC-22-FG-70-80-20 DSC-22-FG-70-80-30 DSC-22-FG-70-80-40 DSC-22-FG-70-80-50 DSC-22-FG-70-80-60 DSC-22-FG-70-80-70 DSC-22-FG-70-80-80 DSC-22-FG-70-80-90 DSC-22-FG-70-80-100 DSC-22-FG-70-80-110 DSC-22-FG-70-80-120 DSC-22-FG-70-80-130 DSC-22-FG-70-80-140 DSC-22-FG-70-90-10 DSC-22-FG-70-90-20 DSC-22-FG-70-90-30 DSC-22-FG-70-100-10 DSC-22-FG-70-100-20 DSC-22-FG-70-100-30 DSC-22-FG-70-100-40 DSC-22-FG-70-100-50 DSC-22-FG-70-110-20 DSC-22-FG-70-110-30 DSC-22-FG-70-110-40 DSC-22-FG-70-110-60 DSC-22-FG-70-110-90 DSC-22-FG-70-110-130 DSC-22-FG-80 DSC-22-FG-90-10 DSC-22-FG-90-20 DSC-22-FG-90-120 DSC-22-FG-90-100 DSC-22-FG-90-30 DSC-22-FG-90-40 DSC-22-FG-90-80 DSC-22-FG-90-110 DSC-22-FG-90-50 DSC-22-FG-90-90 DSC-22-FG-90-60
VIR A350 FLEET FCOM
Subsection Title
LOC Mode G/S* Mode G/S Mode LAND Mode FLARE Mode ROLL OUT Mode F-LOC* Mode F-LOC Mode F-G/S* Mode F-G/S Mode LOC B/C* Mode LOC B/C Mode APP-DES General SRS GA Mode GA TRK Mode General Arming and Disarming Conditions Engagement and Disengagement Conditions Normal Operations Inhibition Conditions Takeoff Climb with OP CLB Mode Climb with CLB Mode Altitude Acquire and Altitude Hold Approach and Landing AUTO EMER DESCENT Approach and Landing Capability Cockpit View AFS CP Audio Indicators AUTOLAND Light EFIS CP FCU Brightness Knobs FMA MEMO MFD - FCU Backup PFD Sidestick
Rev. Date
01 JUL 19 01 JUL 19 01 JUL 19 01 JUL 19 01 JUL 19 01 JUL 19 01 JUL 19 01 JUL 19 01 JUL 19 01 JUL 19 01 JUL 19 01 JUL 19 01 JUL 19 01 JUL 19 01 JUL 19 01 JUL 19 01 JUL 19 01 JUL 19 01 JUL 19 01 JUL 19 01 JUL 19 01 JUL 19 01 JUL 19 01 JUL 19 01 JUL 19 01 JUL 19 01 JUL 19 01 JUL 19 01 JUL 19 01 JUL 19 01 JUL 19 01 JUL 19 01 JUL 19 01 JUL 19 01 JUL 19 01 JUL 19 01 JUL 19 01 JUL 19 01 JUL 19 Continued on the following page
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DSC-22-FG-90-70 DSC-22-FG-90-130 DSC-22-FG-100-10 DSC-22-FG-100-20 DSC-22-FG-110 DSC-22-FMS-10-10 DSC-22-FMS-10-20 DSC-22-FMS-10-30-10 DSC-22-FMS-10-30-20 DSC-22-FMS-10-30-30 DSC-22-FMS-10-30-40 DSC-22-FMS-10-30-50 DSC-22-FMS-10-30-60 DSC-22-FMS-10-40-10 DSC-22-FMS-10-40-20 DSC-22-FMS-10-40-30 DSC-22-FMS-10-40-40 DSC-22-FMS-10-40-50 DSC-22-FMS-10-40-60 DSC-22-FMS-10-40-70 DSC-22-FMS-10-40-80 DSC-22-FMS-10-40-90 DSC-22-FMS-10-50-10 DSC-22-FMS-10-50-20 DSC-22-FMS-10-50-30 DSC-22-FMS-10-50-40 DSC-22-FMS-10-50-50 DSC-22-FMS-10-50-60 DSC-22-FMS-10-50-70 DSC-22-FMS-10-60 DSC-22-FMS-10-70-10 DSC-22-FMS-10-70-20 DSC-22-FMS-10-70-30 DSC-22-FMS-10-80 DSC-22-FMS-10-90 DSC-22-FMS-20-10 DSC-22-FMS-20-95 DSC-22-FMS-20-80
VIR A350 FLEET FCOM
Subsection Title
Rev. Date
Thrust Levers 01 JUL 19 SPEED BRAKE Panel 01 JUL 19 AFS CP Backup Function 01 JUL 19 Failure Indications During Approach 01 JUL 19 How to 01 JUL 19 Overview 01 JUL 19 Architecture 01 JUL 19 Aircraft Position 01 JUL 19 Radio Navigation Tuning 01 JUL 19 Polar Navigation 01 JUL 19 FLS Function within FMS 01 JUL 19 RNP AR Function 01 JUL 19 CDA function 01 JUL 19 General 01 JUL 19 Lateral Revisions 15 MAR 20 Vertical Revisions 01 JUL 19 Diversion 01 JUL 19 Temporary Flight Plan 01 JUL 19 Secondary Flight Plans 01 JUL 19 Flight Plan Predictions 01 JUL 19 Datalink with Company Ground Station 03 FEB 20 Datalink with ATC Center 01 JUL 19 Overview 01 JUL 19 FMS Speed Mode (ECON/LRC) 01 JUL 19 Flight Phases and Speed/Mach Profiles 01 JUL 19 Auto-Derated Thrust during Climb 01 JUL 19 Optimum Flight Level and Recommended Maximum Flight 01 JUL 19 Level NOISE Function 01 JUL 19 PERF Factor, IDLE Factor, and FUEL PENALTY Factor 01 JUL 19 Engine-Out (EO) Mode 01 JUL 19 Takeoff Monitoring Function 01 JUL 19 Takeoff Surveillance Function 01 JUL 19 Controls and Indicators 01 JUL 19 Time Function 01 JUL 19 Print Function 01 JUL 19 Cockpit View 01 JUL 19 Audio Indicators 01 JUL 19 Data Entry Format 01 JUL 19 Continued on the following page
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DSC-22-FMS-20-60 DSC-22-FMS-20-90 DSC-22-FMS-20-70 DSC-22-FMS-20-30 DSC-22-FMS-20-100 DSC-22-FMS-20-20-10 DSC-22-FMS-20-20-20 DSC-22-FMS-20-50 DSC-22-FMS-20-40 DSC-22-FMS-20-75 DSC-22-FMS-30 DSC-22-FMS-40 DSC-22-FMS-45 DSC-23-10-10 DSC-23-10-20 DSC-23-10-30-10 DSC-23-10-30-20 DSC-23-10-30-30 DSC-23-20 DSC-23-25 DSC-23-30-10 DSC-23-30-20 DSC-24-10-10 DSC-24-10-20 DSC-24-10-30 DSC-24-10-40 DSC-24-10-50 DSC-24-10-60 DSC-24-20 DSC-24-30 DSC-24-40 DSC-25-10 DSC-25-20 DSC-25-30-10 DSC-25-30-20 DSC-26-10 DSC-26-20 DSC-26-30-10 DSC-26-30-20
VIR A350 FLEET FCOM
Subsection Title
EFIS CP FMS Messages FMS Selector KCCU MEMO Overview FMS Pages ND PFD Printer How To Abnormal Operations Temporary Abnormal Behaviors Overview Internal Communication Radiocommunication SATCOM SELCAL Controls and Indicators Temporary Abnormal Behaviors RMP Failures RMP Connection Failures Overview AC Generation DC Generation Emergency Generation Electrical Networks and Supply Centers Electrical Network Management Controls and Indicators Normal Operations Abnormal Operations Cockpit Emergency Equipment Flight Crew Rest Compartment Cabin Crew Rest Compartment Overview Architecture System Description Controls and Indicators
Rev. Date
01 JUL 19 01 JUL 19 01 JUL 19 01 JUL 19 01 JUL 19 01 JUL 19 15 MAR 20 01 JUL 19 01 JUL 19 01 JUL 19 15 MAR 20 15 MAR 20 06 FEB 20 01 JUL 19 03 FEB 20 01 JUL 19 01 JUL 19 01 JUL 19 15 MAR 20 01 JUL 19 01 JUL 19 01 JUL 19 01 JUL 19 01 JUL 19 01 JUL 19 01 JUL 19 01 JUL 19 01 JUL 19 15 MAR 20 01 JUL 19 01 JUL 19 01 JUL 19 03 FEB 20 03 FEB 20 03 FEB 20 01 JUL 19 01 JUL 19 01 JUL 19 01 JUL 19 Continued on the following page
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DSC-26-40-10 DSC-26-40-20 DSC-26-50-10 DSC-26-50-20 DSC-26-60-10 DSC-26-60-20 DSC-26-70-10 DSC-26-70-20 DSC-26-80-10 DSC-26-80-20 DSC-26-90-10 DSC-26-90-20 DSC-27-10-10 DSC-27-10-20 DSC-27-10-30 DSC-27-10-40 DSC-27-20-10 DSC-27-20-20 DSC-27-20-30 DSC-27-20-33 DSC-28-10 DSC-28-20 DSC-28-30 DSC-28-40 DSC-28-50-30 DSC-29-10 DSC-29-20 DSC-29-30 DSC-29-40 DSC-30-20-10 DSC-30-20-20 DSC-30-30-10 DSC-30-30-20 DSC-31-CDS-10 DSC-31-CDS-20 DSC-31-CDS-30-10 DSC-31-CDS-30-20 DSC-31-CDS-30-30 DSC-31-CDS-30-40
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Subsection Title
System Description Controls and Indicators System Description Controls and Indicators System Description Controls and Indicators System Description Controls and Indicators Lavatory Crew Rest Compartments System Description Controls and Indicators System Description Controls and Indicators Normal Law Reconfiguration Control Laws System Description Configurations Controls and Indicators Abnormal Operations System Description Controls and Indicators Normal Operations Abnormal Operations Refuel/Defuel System Description Controls and Indicators Abnormal Operations Temporary Abnormal Behaviors System Description Controls and Indicators System Description Controls and Indicators Overview Architecture System Description Controls and Indicators Normal Operations Abnormal Operations
Rev. Date
01 JUL 19 01 JUL 19 01 JUL 19 01 JUL 19 01 JUL 19 01 JUL 19 03 FEB 20 03 FEB 20 01 JUL 19 01 JUL 19 01 JUL 19 01 JUL 19 03 FEB 20 03 FEB 20 01 JUL 19 15 MAR 20 01 JUL 19 03 FEB 20 03 FEB 20 15 MAR 20 03 FEB 20 15 MAR 20 01 JUL 19 15 MAR 20 03 FEB 20 15 MAR 20 15 MAR 20 15 MAR 20 01 JUL 19 01 JUL 19 01 JUL 19 01 JUL 19 01 JUL 19 03 FEB 20 01 JUL 19 03 FEB 20 01 JUL 19 03 FEB 20 03 FEB 20 Continued on the following page
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DSC-31-CDS-40-10 DSC-31-CDS-40-20-10 DSC-31-CDS-40-20-20 DSC-31-CDS-40-20-30 DSC-31-CDS-40-20-40 DSC-31-CDS-40-20-50 DSC-31-CDS-40-20-60 DSC-31-CDS-40-20-70 DSC-31-CDS-40-20-80 DSC-31-CDS-40-20-90 DSC-31-CDS-40-20-100 DSC-31-CDS-40-20-110 DSC-31-CDS-40-20-120 DSC-31-CDS-40-20-130 DSC-31-CDS-40-30 DSC-31-CDS-40-40-10 DSC-31-CDS-40-40-20 DSC-31-CDS-40-40-30 DSC-31-CDS-40-40-40 DSC-31-CDS-40-40-50 DSC-31-CDS-40-40-60 DSC-31-CDS-40-40-70 DSC-31-CDS-40-40-80 DSC-31-CDS-40-40-90 DSC-31-CDS-40-40-100 DSC-31-CDS-40-40-110 DSC-31-CDS-40-40-120 DSC-31-CDS-40-40-130 DSC-31-CDS-40-40-140 DSC-31-CDS-40-40-150 DSC-31-CDS-40-50 DSC-31-CDS-40-60 DSC-31-CDS-40-70 DSC-31-CDS-60-10-00 DSC-31-CDS-60-10-20 DSC-31-CDS-60-10-10 DSC-31-CDS-60-10-30 DSC-31-CDS-60-10-40 DSC-31-CDS-60-10-50
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Subsection Title
Overview Overview On Ground Indications Attitude Airspeed Altitude Altitude Alerts RA Height Vertical Speed Heading/Track Guidance Departure and Approach Guidance Flight Mode Annunciator (FMA) PFD Messages Lower Part of the PFD Overview ARC Mode PLAN Mode ROSE-NAV Mode ROSE-VOR Mode ROSE-LS Mode Common Data FMS Data BACKUP TRAJ Interactive ND Weather Terrain Traffic Airport Navigation ND Messages VD Controls and Indicators Abnormal Operations General Architecture ECAM Function MFD WD SD
Rev. Date
01 JUL 19 01 JUL 19 01 JUL 19 01 JUL 19 01 JUL 19 01 JUL 19 01 JUL 19 01 JUL 19 01 JUL 19 01 JUL 19 01 JUL 19 01 JUL 19 01 JUL 19 01 JUL 19 01 JUL 19 01 JUL 19 01 JUL 19 01 JUL 19 01 JUL 19 01 JUL 19 01 JUL 19 01 JUL 19 01 JUL 19 01 JUL 19 01 JUL 19 01 JUL 19 01 JUL 19 01 JUL 19 01 JUL 19 01 JUL 19 01 JUL 19 01 JUL 19 01 JUL 19 01 JUL 19 03 FEB 20 03 FEB 20 03 FEB 20 01 JUL 19 01 JUL 19 Continued on the following page
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DSC-31-CDS-60-10-80 DSC-31-CDS-60-20 DSC-31-CDS-60-30 DSC-31-CDS-60-40 DSC-31-CDS-70-10 DSC-31-CDS-70-20 DSC-31-CDS-80 DSC-31-CDS-90-10 DSC-31-CDS-100-10 DSC-31-CDS-100-20 DSC-31-CDS-100-30 DSC-31-CDS-110-10 DSC-31-CDS-110-20 DSC-31-REC-10 DSC-31-REC-20 DSC-31-REC-30 DSC-32-10-10-10 DSC-32-10-10-20 DSC-32-10-20 DSC-32-20-10-10 DSC-32-20-10-20 DSC-32-20-10-30 DSC-32-20-10-40 DSC-32-20-10-50 DSC-32-20-20 DSC-32-20-25 DSC-32-30-10 DSC-32-30-20 DSC-32-30-30 DSC-32-30-40 DSC-32-40-10 DSC-32-40-20 DSC-33-10 DSC-33-20-10 DSC-33-20-20 DSC-33-30-10 DSC-33-30-20 DSC-33-40-10 DSC-33-40-20
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Rev. Date
Permanent Data 01 JUL 19 Controls and Indicators 01 JUL 19 Normal Operations 01 JUL 19 Abnormal Operations 01 JUL 19 System Description 01 JUL 19 How to 01 JUL 19 OIS 01 JUL 19 System Description 01 JUL 19 System Description 01 JUL 19 Controls and Indicators 01 JUL 19 Abnormal Operations 01 JUL 19 System Description 01 JUL 19 Controls and Indicators 03 FEB 20 System Description 01 JUL 19 Controls and Indicators 01 JUL 19 Normal Operations 01 JUL 19 Overview 03 FEB 20 Landing Gear Extension Retraction System (LGERS) 03 FEB 20 Controls and Indicators 03 FEB 20 Overview 03 FEB 20 System Architecture 03 FEB 20 Braking System Hydraulic Architecture 03 FEB 20 Braking Modes 03 FEB 20 Braking Functions 15 MAR 20 Controls and Indicators 03 FEB 20 Temporary Abnormal Behaviors 15 MAR 20 System Description 03 FEB 20 Controls and Indicators 15 MAR 20 Normal Operations 01 JUL 19 Abnormal Operations 03 FEB 20 System Description 03 FEB 20 Controls and Indicators 03 FEB 20 Overview 01 JUL 19 System Description 01 JUL 19 Controls and Indicators 01 JUL 19 System Description 03 FEB 20 Controls and Indicators 01 JUL 19 System Description 01 JUL 19 Controls and Indicators 01 JUL 19 Continued on the following page
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DSC-33-40-30 DSC-33-50-10 DSC-33-50-20 DSC-34-NAV-10 DSC-34-NAV-20-10-10 DSC-34-NAV-20-10-20 DSC-34-NAV-20-10-30 DSC-34-NAV-20-10-40 DSC-34-NAV-20-10-50 DSC-34-NAV-20-10-60 DSC-34-NAV-20-10-70 DSC-34-NAV-20-20 DSC-34-NAV-20-30 DSC-34-NAV-30-10 DSC-34-NAV-30-20 DSC-34-NAV-30-30 DSC-34-NAV-30-40 DSC-34-NAV-30-50 DSC-34-NAV-30-60 DSC-34-NAV-30-70 DSC-34-NAV-30-80 DSC-34-NAV-40 DSC-34-NAV-50 DSC-34-NAV-60-10 DSC-34-NAV-60-20 DSC-34-NAV-70-10 DSC-34-NAV-70-20 DSC-34-NAV-70-30 DSC-34-NAV-80-10 DSC-34-NAV-80-20 DSC-34-NAV-90 DSC-34-SURV-10 DSC-34-SURV-20-10 DSC-34-SURV-20-20 DSC-34-SURV-30-10 DSC-34-SURV-30-20 DSC-34-SURV-40-10 DSC-34-SURV-40-20 DSC-34-SURV-50-10
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Subsection Title
Normal Operations System Description Controls and Indicators General Overview Architecture ADR IR ADIRS Monitoring Aircraft Position Time Function Controls and Indicators Abnormal Operations Overview Architecture SFD SND (if installed) Standby Compass Controls and Indicators Abnormal Operations How to GNSS Landing Systems System Description Controls and Indicators System Description Controls and Indicators How to System Description Controls and Indicators RNP AR Overview System Description Controls and Indicators System Description Controls and Indicators System Description Controls and Indicators System Description
Rev. Date
01 JUL 19 01 JUL 19 03 FEB 20 01 JUL 19 01 JUL 19 03 FEB 20 01 JUL 19 01 JUL 19 01 JUL 19 01 JUL 19 01 JUL 19 01 JUL 19 01 JUL 19 01 JUL 19 01 JUL 19 15 MAR 20 01 JUL 19 01 JUL 19 01 JUL 19 01 JUL 19 01 JUL 19 01 JUL 19 01 JUL 19 01 JUL 19 01 JUL 19 01 JUL 19 01 JUL 19 03 FEB 20 01 JUL 19 01 JUL 19 01 JUL 19 03 FEB 20 01 JUL 19 01 JUL 19 15 MAR 20 15 MAR 20 01 JUL 19 01 JUL 19 01 JUL 19 Continued on the following page
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DSC-34-SURV-50-20 DSC-34-SURV-60-10 DSC-34-SURV-60-20 DSC-34-SURV-60-30 DSC-34-SURV-70-10 DSC-34-SURV-70-30 DSC-34-SURV-70-40 DSC-34-SURV-70-50 DSC-34-SURV-70-90 DSC-34-SURV-70-110 DSC-34-SURV-70-120 DSC-34-SURV-70-20 DSC-34-SURV-70-100 DSC-34-SURV-80 DSC-34-SURV-90 DSC-34-32-10 DSC-34-32-20-10 DSC-34-32-20-20-10 DSC-34-32-20-20-20 DSC-34-32-20-20-30 DSC-34-32-20-20-35 DSC-34-32-20-20-40 DSC-34-32-20-20-50 DSC-34-32-20-20-60 DSC-34-32-20-20-70 DSC-34-32-20-20-80 DSC-34-32-20-20-90 DSC-34-32-30-10 DSC-34-32-30-20-10 DSC-34-32-30-20-20 DSC-34-32-30-20-30 DSC-34-32-30-20-40 DSC-34-32-30-20-50 DSC-34-32-30-20-60 DSC-34-32-35 DSC-35-10 DSC-35-20-10 DSC-35-20-20 DSC-35-20-40
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Controls and Indicators System Description Controls and Indicators How to Cockpit View EFIS Control Panel KCCU MFD ND PFD RMP SURV Panel VD Normal Operations Abnormal Operations General System Description Cockpit View Audio Indicators Brake Panel FMA MFD ND PFD RWY CONDITION/BRAKING ACTION Matrix SURV Panel on Overhead Panel (if installed) MEMO System Description Cockpit View Audio Indicators Brake Panel FMA MEMO ND Abnormal Operations Overview System Description Controls and Indicators How to
Rev. Date
01 JUL 19 01 JUL 19 01 JUL 19 01 JUL 19 01 JUL 19 01 JUL 19 01 JUL 19 15 MAR 20 01 JUL 19 01 JUL 19 01 JUL 19 01 JUL 19 01 JUL 19 03 FEB 20 01 JUL 19 01 JUL 19 01 JUL 19 01 JUL 19 01 JUL 19 01 JUL 19 01 JUL 19 01 JUL 19 01 JUL 19 01 JUL 19 01 JUL 19 01 JUL 19 01 JUL 19 01 JUL 19 01 JUL 19 01 JUL 19 01 JUL 19 01 JUL 19 01 JUL 19 01 JUL 19 01 JUL 19 01 JUL 19 01 JUL 19 01 JUL 19 01 JUL 19 Continued on the following page
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DSC-35-30-10 DSC-35-30-20 DSC-35-40-10 DSC-35-40-20 DSC-36-10-10 DSC-36-10-20 DSC-36-10-30 DSC-36-10-40 DSC-36-10-50 DSC-36-10-60 DSC-36-20 DSC-38-10 DSC-38-20 DSC-42-10 DSC-42-20 DSC-44-10-10 DSC-44-10-20 DSC-44-10-30 DSC-44-10-40 DSC-44-20 DSC-46-ATC-10-10 DSC-46-ATC-10-20 DSC-46-ATC-10-30 DSC-46-ATC-10-40 DSC-46-ATC-10-50 DSC-46-ATC-10-60 DSC-46-ATC-10-70 DSC-46-ATC-20-10 DSC-46-ATC-20-70 DSC-46-ATC-20-90 DSC-46-ATC-20-80 DSC-46-ATC-20-60 DSC-46-ATC-20-40 DSC-46-ATC-20-30-10 DSC-46-ATC-20-30-20 DSC-46-ATC-20-30-30 DSC-46-ATC-20-30-40 DSC-46-ATC-20-30-50 DSC-46-ATC-20-30-60
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Subsection Title
Rev. Date
System Description 01 JUL 19 Controls and Indicators 01 JUL 19 System Description 03 FEB 20 How to 01 JUL 19 Overview 01 JUL 19 Engine Bleed Air System 01 JUL 19 APU Bleed Air Supply 01 JUL 19 HP Ground Air Supply 01 JUL 19 Crossbleed 01 JUL 19 Leak Detection 01 JUL 19 Controls and Indicators 01 JUL 19 System Description 03 FEB 20 Controls and Indicators 03 FEB 20 System Description 03 FEB 20 Abnormal Operations 03 FEB 20 Overview 01 JUL 19 Cabin Communication and Signs 03 FEB 20 In-Flight Entertainment and Cabin Connectivity 03 FEB 20 Video Monitoring System 01 JUL 19 Controls and Indicators 03 FEB 20 General 01 JUL 19 Notification 01 JUL 19 Controller/Pilot Datalink Communication (CPDLC) 01 JUL 19 Message Record 01 JUL 19 A623 01 JUL 19 Automatic Dependent Surveillance - Contract (ADS-C) 01 JUL 19 Mailbox 01 JUL 19 Cockpit View 01 JUL 19 ATC MSG pb 01 JUL 19 Audio Indicators 01 JUL 19 KCCU 01 JUL 19 Mailbox 01 JUL 19 MFD - ATC COM Messages 01 JUL 19 Overview 01 JUL 19 CONNECT Page 01 JUL 19 REQUEST Page 01 JUL 19 REPORT & MODIFY Page 01 JUL 19 MSG RECORD Page 01 JUL 19 D-ATIS Page 01 JUL 19 Continued on the following page
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DSC-46-ATC-20-30-70 DSC-46-ATC-20-50 DSC-46-ATC-20-20 DSC-46-ATC-30 DSC-46-OIS-10-10 DSC-46-OIS-10-20 DSC-46-OIS-10-30 DSC-46-OIS-10-40 DSC-46-OIS-20-10 DSC-46-OIS-20-20 DSC-46-OIS-20-30 DSC-46-OIS-20-50 DSC-46-OIS-20-60 DSC-46-OIS-20-70 DSC-46-OIS-20-80-09 DSC-46-OIS-20-80-10 DSC-46-OIS-20-80-20 DSC-46-OIS-20-80-40 DSC-46-OIS-20-80-50 DSC-46-OIS-20-80-60 DSC-46-OIS-20-80-70 DSC-46-OIS-20-80-90 DSC-46-OIS-20-80-100 DSC-46-OIS-20-80-110 DSC-46-OIS-20-80-130 DSC-46-OIS-20-80-140 DSC-46-OIS-20-80-150 DSC-46-OIS-20-90 DSC-46-OIS-20-100 DSC-46-OIS-20-110 DSC-46-OIS-20-120 DSC-46-OIS-30 DSC-49-10 DSC-49-20 DSC-49-30 DSC-49-40 DSC-52-10 DSC-52-20-10 DSC-52-20-20
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Subsection Title
EMERGENCY Page MFD - Data Entry Format MFD - Overview Abnormal Operations Overview Architecture Applications on EFB Side Applications on AVNCS Side Cockpit View Audio Indicators COM GND CONNECTION pb-sw KCCU Laptop Package MEMO General Overview OIS MENU AVNCS - COMPANY COM EFB - FLT OPS MENU EFB - FLT OPS STS EFB - OPS LIBRARY EFB - T.O PERF EFB - IN-FLT PERF EFB - LDG PERF EFB - LOAD BOX EFB - EXPORT BOX OIS Messages OIS Controls on Main Instrument Panel OIS Keyboards OIS Panel on Overhead Panel Printer How To System Description Controls and Indicators Normal Operations Abnormal Operations Overview System Description Controls and Indicators
Rev. Date
01 JUL 19 01 JUL 19 01 JUL 19 01 JUL 19 01 JUL 19 03 FEB 20 03 FEB 20 01 JUL 19 01 JUL 19 01 JUL 19 01 JUL 19 01 JUL 19 03 FEB 20 01 JUL 19 03 FEB 20 03 FEB 20 01 JUL 19 01 JUL 19 01 JUL 19 01 JUL 19 03 FEB 20 03 FEB 20 03 FEB 20 03 FEB 20 01 JUL 19 03 FEB 20 01 JUL 19 01 JUL 19 01 JUL 19 03 FEB 20 01 JUL 19 15 MAR 20 01 JUL 19 01 JUL 19 15 MAR 20 01 JUL 19 01 JUL 19 01 JUL 19 01 JUL 19 Continued on the following page
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DSC-52-30-10 DSC-52-30-20 DSC-52-30-30 DSC-52-30-40 DSC-52-40-10 DSC-52-40-20 DSC-52-40-30 DSC-52-50-10 DSC-52-50-20 DSC-52-50-30 DSC-52-60-10 DSC-52-60-20 DSC-56-10 DSC-70-10-10 DSC-70-10-20 DSC-70-10-30-10 DSC-70-10-30-20 DSC-70-10-30-30 DSC-70-10-40 DSC-70-10-50 DSC-70-10-60 DSC-70-10-70-10 DSC-70-10-70-20 DSC-70-10-70-30 DSC-70-10-80-10 DSC-70-10-80-20 DSC-70-10-80-30 DSC-70-20 DSC-70-30 DSC-70-40 PRO-PLP-LETDU PRO-ABN-ABN-00 PRO-ABN-ABN-ABN PRO-ABN-ABN-ADV PRO-ABN-ABN-MEM PRO-ABN-ABN-QRH PRO-ABN-ABN-RESET PRO-ABN-A-ICE PRO-ABN-AIR
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Rev. Date
System Description 01 JUL 19 Controls and Indicators 01 JUL 19 How to 03 FEB 20 Temporary Abnormal Behavior 01 JUL 19 System Description 01 JUL 19 Controls and Indicators 01 JUL 19 How to 03 FEB 20 System Description 01 JUL 19 Controls and Indicators 01 JUL 19 How to 01 JUL 19 System Description 01 JUL 19 Controls and Indicators 01 JUL 19 System Description 01 JUL 19 Overview 03 FEB 20 Engine 01 JUL 19 General 01 JUL 19 Engine Protection 03 FEB 20 Power Management 03 FEB 20 Fuel System 01 JUL 19 Oil System 01 JUL 19 Air System 01 JUL 19 General 01 JUL 19 Protection of the Thrust Reverser System 01 JUL 19 Deployment and Stowage 01 JUL 19 General 01 JUL 19 Ignition System 01 JUL 19 Start System 01 JUL 19 Controls and Indicators 03 FEB 20 Normal Operations 01 JUL 19 Abnormal Operations 01 JUL 19 LIST OF EFFECTIVE TEMPORARY DOCUMENTARY UNITS 15 MAR 20 INTRODUCTION 03 FEB 20 [ABN] ECAM NOT-SENSED PROCEDURES 03 FEB 20 [ADV] ECAM ADVISORY 03 FEB 20 [MEM] MEMORY ITEMS 01 JUL 19 [QRH] PROCEDURES 01 JUL 19 [RESET] SYSTEM RESET 15 MAR 20 A-ICE 03 FEB 20 AIR 03 FEB 20 Continued on the following page
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PRO-ABN-APU PRO-ABN-APUF PRO-ABN-AUTO_FLT PRO-ABN-AVNCS PRO-ABN-BRAKES PRO-ABN-CAB_COM PRO-ABN-CAB_PRESS PRO-ABN-CDS PRO-ABN-CDS_AFLT PRO-ABN-COM PRO-ABN-COND PRO-ABN-CONFIG PRO-ABN-DISPATCH PRO-ABN-DOOR PRO-ABN-ELEC PRO-ABN-ENG PRO-ABN-ENGF PRO-ABN-EXT_LT PRO-ABN-F_CTL PRO-ABN-FIRE PRO-ABN-FUEL PRO-ABN-FWS PRO-ABN-HYD PRO-ABN-IMA PRO-ABN-LG PRO-ABN-MISC PRO-ABN-MLG_BAY PRO-ABN-MLG_BAYF PRO-ABN-NAV PRO-ABN-OIS PRO-ABN-OVERSPEED PRO-ABN-OXY PRO-ABN-SMOKE PRO-ABN-STEER PRO-ABN-SURV PRO-ABN-TAIL_STRK PRO-ABN-T-O PRO-ABN-VENT PRO-ABN-WHEEL
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APU APU FIRE AUTO FLT AVIONICS NETWORK BRAKES CAB COM CAB PRESS CDS CDS & AUTO FLT COM COND CONFIG DISPATCH DOOR ELEC ENG ENG FIRE EXT LT F/CTL FIRE FUEL FWS HYD IMA L/G MISC MLG BAY MLG BAY FIRE NAV OIS OVERSPEED OXY SMOKE STEER SURV TAIL STRIKE T.O VENT WHEEL
Subsection Title
Rev. Date
01 JUL 19 01 JUL 19 01 JUL 19 01 JUL 19 15 MAR 20 01 JUL 19 15 MAR 20 01 JUL 19 01 JUL 19 01 JUL 19 01 JUL 19 01 JUL 19 01 JUL 19 01 JUL 19 03 FEB 20 15 MAR 20 03 FEB 20 01 JUL 19 15 MAR 20 03 FEB 20 15 MAR 20 03 FEB 20 15 MAR 20 01 JUL 19 03 FEB 20 03 FEB 20 01 JUL 19 01 JUL 19 03 FEB 20 01 JUL 19 03 FEB 20 01 JUL 19 01 JUL 19 01 JUL 19 15 MAR 20 01 JUL 19 01 JUL 19 01 JUL 19 03 FEB 20 Continued on the following page
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PRO-NOR-SOP-10 PRO-NOR-SOP-20 PRO-NOR-SOP-30 PRO-NOR-SOP-40 PRO-NOR-SOP-50 PRO-NOR-SOP-60 PRO-NOR-SOP-70 PRO-NOR-SOP-80 PRO-NOR-SOP-90 PRO-NOR-SOP-100 PRO-NOR-SOP-110 PRO-NOR-SOP-120 PRO-NOR-SOP-130 PRO-NOR-SOP-140 PRO-NOR-SOP-150 PRO-NOR-SOP-160 PRO-NOR-SOP-170 PRO-NOR-SOP-180-A PRO-NOR-SOP-180-B PRO-NOR-SOP-180-C PRO-NOR-SOP-210 PRO-NOR-SOP-220 PRO-NOR-SOP-230 PRO-NOR-SOP-250 PRO-NOR-SOP-260 PRO-NOR-C-L PRO-NOR-SCO PRO-NOR-TSK PRO-NOR-SUP-SUP-SUP PRO-NOR-SUPSUP-ADVWXR PRO-NOR-SUP-SUP-ENG PRO-NOR-SUP-SUP-FUEL PRO-NOR-SUP-SUP-LG PRO-NOR-SUP-SUP-MISC PRO-SPO-AWOPS PRO-SPO-NAT HLA PRO-SPO-ETOPS PRO-SPO-FFWCCM
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Subsection Title
General Information Flight Preparation Safety Exterior Inspection Preliminary Cockpit Preparation Exterior Walkaround Cockpit Preparation Before Pushback or Start Engine Start After Start Taxi Before Takeoff Takeoff After Takeoff Climb Cruise Descent Preparation Descent Approach General Aircraft Configuration Management Aircraft Guidance Management Landing Go-Around After Landing Parking Securing the Aircraft Normal Checklists Standard Callouts Tasksharing [SUP] Supplementary Procedures Menu Adverse Weather Engine Fuel Landing Gear Miscellaneous AWOPS North Atlantic NAT HLA Extended Range Operations Ferry Flight without CCM
Rev. Date 01 JUL 19 03 FEB 20 03 FEB 20 15 MAR 20 15 MAR 20 03 FEB 20 03 FEB 20 03 FEB 20 15 MAR 20 03 FEB 20 03 FEB 20 03 FEB 20 01 JUL 19 01 JUL 19 03 FEB 20 03 FEB 20 03 FEB 20 03 FEB 20 03 FEB 20 03 FEB 20 03 FEB 20 03 FEB 20 03 FEB 20 15 MAR 20 15 MAR 20 15 MAR 20 03 FEB 20 15 MAR 20 15 MAR 20 15 MAR 20
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PRO-SPO-PBN PRO-SPO-RVSM PRO-SPO-PRM PRO-SPO-PBCS LIM-PLP-LETDU LIM-INT LIM-AG-F_CTL LIM-AG-OPS LIM-AG-SPD LIM-AG-WGHT LIM-AIR LIM-AFS-10 LIM-AFS-20
LIM-APU LIM-CAB LIM-CDS LIM-COM LIM-DOORS LIM-ENG LIM-F-CTL LIM-FUEL LIM-ICE_RAIN LIM-LG LIM-LT LIM-NAV LIM-OIS LIM-OXY LIM-ROW-ROP LIM-SURV LIM-T-PED PER-PLP-LETDU PER-PN1 PER-OPS PER-TOF-10 PER-TOF-20-10 PER-TOF-20-20-10 PER-TOF-20-20-20 PER-TOF-30-10
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Subsection Title
Rev. Date
PBN 03 FEB 20 RVSM 15 MAR 20 Simultaneous Parallel Approach Operations 15 MAR 20 Performance-Based Communication and Surveillance 01 JUL 19 LIST OF EFFECTIVE TEMPORARY DOCUMENTARY UNITS 03 FEB 20 Introduction 01 JUL 19 Flight Maneuvering Load Acceleration Limits 01 JUL 19 Operational Parameters 15 MAR 20 Speeds 03 FEB 20 Weights 06 FEB 20 Air BLEED/COND/PRESS/VENT 01 JUL 19 General 01 JUL 19 Automatic Approach, Automatic Landing and Automatic 03 FEB 20 Roll-Out Auxiliary Power Unit 01 JUL 19 Cabin Systems 01 JUL 19 Control and Display System 01 JUL 19 Communication 01 JUL 19 Doors 01 JUL 19 Engines 15 MAR 20 Flight Controls 01 JUL 19 Fuel 03 FEB 20 Ice and Rain Protection 01 JUL 19 Landing Gear 03 FEB 20 Lights 01 JUL 19 Navigation 01 JUL 19 Onboard Information System 01 JUL 19 Oxygen 01 JUL 19 ROW/ROP - BTV 01 JUL 19 Surveillance 01 JUL 19 Transmitting Portable Electronic Device 15 MAR 20 LIST OF EFFECTIVE TEMPORARY DOCUMENTARY UNITS 15 MAR 20 Pitch-N1 Tables 03 FEB 20 Operating Speeds 03 FEB 20 Takeoff Performance Optimization 03 FEB 20 Takeoff at Maximum Thrust 03 FEB 20 General 03 FEB 20 Flexible Takeoff 03 FEB 20 Takeoff on Dry Runway 03 FEB 20 Continued on the following page
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PER-TOF-30-20 PER-TOF-30-30 PER-TOF-40 PER-TOF-50 PER-IFT-10 PER-IFT-20-10-10 PER-IFT-20-10-20 PER-IFT-20-20-10 PER-IFT-20-20-20 PER-IFT-20-30 PER-IFT-20-40 PER-IFT-30 PER-IFT-FP PER-LDG-10 PER-LDG-20 PER-LDG-30 PER-LDG-40 PER-LDG-50 PER-PSD OEB-PLP-LETDU OEB-PLP-LEOEB TAB-PLP-LETDU TAB
Subsection Title
Takeoff on Damp and Wet Runways Takeoff on Contaminated Runway Takeoff with MEL or CDL Item Takeoff Recommendations In-Flight Performance Calculation General Climb Thrusts Speeds Altitude/Ceilings Descent Holding One Engine Inoperative Operations Fuel Penalty Tables - Fuel Consumption Increased Landing Performance Calculation Landing Speeds and Distances Definitions Runway Conditions Dispatch Requirements In-Flight Performance Assessment Supplementary Performance Information LIST OF EFFECTIVE TEMPORARY DOCUMENTARY UNITS LIST OF EFFECTIVE OPERATIONS ENGINEERING BULLETIN LIST OF EFFECTIVE TEMPORARY DOCUMENTARY UNITS Temporary Abnormal Behaviors
Rev. Date 03 FEB 20 03 FEB 20 01 JUL 19 01 JUL 19 01 JUL 19 01 JUL 19 01 JUL 19 01 JUL 19 01 JUL 19 01 JUL 19 01 JUL 19 03 FEB 20 03 FEB 20 01 JUL 19 01 JUL 19 15 MAR 20 01 JUL 19 03 FEB 20 03 FEB 20 15 MAR 20 03 FEB 20 15 MAR 20 15 MAR 20
(1) Evolution code : N=New, R=Revised, E=Effectivity, M=Moved
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This table gives, for each delivered aircraft, the cross reference between: -
The Manufacturing Serial Number (MSN). The Fleet Serial Number (FSN) of the aircraft as known by AIRBUS S.A.S. The registration number of the aircraft as known by AIRBUS S.A.S. The aircraft model. (1)
M
MSN 0071
FSN
Registration Number
Model
G-VDOT
350-1041
0274
G-VLUX
350-1041
0298
G-VPOP
350-1041
0319
G-VPRD
350-1041
0336
G-VJAM
350-1041
0415
G-VRNB
350-1041
0426
G-VTEA
350-1041
(1) Evolution code : N=New, R=Revised
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CRITERION L04011
Applicable to: ALL L04027
Linked SB
Incorp. Date
LANDING GEAR - LANDING GEAR MANAGEMENT SYSTEM - Introduce Remote Braking Control Unit (RBCU) Standard H4-3
21 OCT 19
LANDING GEAR - LANDING GEAR MANAGEMENT SYSTEM - Introduce BCS Software Standard S5B.
Applicable to: G-VDOT, G-VRNB, G-VTEA L06001 17 APR 19 Applicable to: ALL L06006
Title
08 AUG 19
17 APR 19
Applicable to: G-VDOT, G-VJAM, G-VRNB, G-VTEA L31464 08 FEB 18
FUEL - FUEL QUANTITY AND MANAGEMENT SYSTEM (FQMS) - Define and Install FQMS V5.1 Software Standard. FUEL - FUEL QUANTITY AND MANAGEMENT SYSTEM (FQMS) - Define and Install FQMS V5.1.1 Software Standard. AIR CONDITIONING - /1 Remove Cockpit Restrictor Valve in S.13/14
Applicable to: ALL L41114
08 FEB 18
Applicable to: ALL L41127
COMMUNICATIONS - HF SYSTEM - Define and install a second HF system
08 FEB 18
Applicable to: ALL L41135
COMMUNICATIONS - EXTERNAL VIDEO SYSTEM Install Taxiing Aid Camera System (TACS) ATA 23 part
08 FEB 18
Applicable to: ALL L41143
FUEL - REFUEL/DEFUEL SYSTEM - Define and Install refuel/defuel coupling on LH wing
08 FEB 18
Applicable to: ALL L41149
INDICATING/RECORDING SYSTEMS - CONTROL AND DISPLAY SYSTEM (CDS) - Change length units from metrics to US
08 FEB 18
Applicable to: ALL L41151
NAVIGATION - ATTITUDE AND HEADING STANDBY DATA: INSTALL A SECOND ISIS
08 FEB 18
Applicable to: ALL L41152
NAVIGATION - MULTI MODE RECEIVER (MMR) FUNCTIONS - Activate GLS function in the MMR.
08 FEB 18
NAVIGATION - MULTI MODE RECEIVER (MMR) FUNCTIONS - Activate Satellite Landing System (SLS) in the MMR
Applicable to: ALL
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CRITERION L41208
Applicable to: ALL L41387
Linked SB
Incorp. Date 08 FEB 18
Title
Air Conditioning - Commercial Equipment Ventilation Define And Install Isolation Valve ISO1 For IFE Center Rack Ventilation
LIGHTS - EXTERIOR - Define and Install Integrated Tail Cone Light and Single FWD Strobe Light Applicable to: G-VJAM, G-VLUX, G-VPOP, G-VPRD, G-VRNB, G-VTEA L41612 08 FEB 18 Miscellaneous - Additional certification items - Certify 15 Knots Tailwind operation at Take-Off (RR ENGINES) Applicable to: ALL L41629 08 FEB 18 INDICATING/RECORDING SYSTEMS CONCENTRATOR AND MULTIPLEXER FOR VIDEO (CMV)- Define and install two labelled P/B in the cockpit Applicable to: ALL L41830 08 FEB 18 INDICATING/RECORDING SYSTEMS - CONTROL AND DISPLAY SYSTEM (CDS) - Define and install CDS S4 standard Applicable to: ALL L41831 08 FEB 18 AUTO FLIGHT - FLIGHT MANAGEMENT (FM) - Define FMS S4 standard Applicable to: ALL L41838 08 FEB 18 AUTO FLIGHT - Define and install Automatic Emergency Descent function Applicable to: ALL L41839 08 FEB 18 INDICATING/RECORDING SYSTEMS - FWS ACQUISITION/INTERFACE - Define and install FWS S4/2.0 standard Applicable to: ALL L41953 08 FEB 18 FLIGHT CONTROLS - PFCS - CONTROL INPUTS Define new SBTU with EMER DESCENT push-button Applicable to: ALL L42048 08 FEB 18 ELECTRICAL POWER - BATTERY MAIN GENERATION - Define and install Li-Ion Batteries system with a single exhaust pipe per side Applicable to: ALL L42209 08 FEB 18 INDICATING/RECORDING SYSTEMS - INTEGRATED CONTROL PANELS (ICP) - Remove « No smoking » toggle switch from ICP LOWER CENTER Applicable to: ALL Continued on the following page
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CRITERION L42260
Linked SB
Incorp. Date
Title
08 FEB 18
Applicable to: ALL L42278
NAVIGATION - AIRCRAFT ENVIRONMENT SURVEILLANCE SYSTEM (AESS): Define & install ATSAW Step 2A activation based on AESS EIS standard
08 FEB 18
Applicable to: ALL L42280
LANDING GEAR - WHEELS AND BRAKES - Introduce S3B software Standard for BCS (Braking Control System)
08 FEB 18
Applicable to: ALL L42332
AUTO FLIGHT - FLIGHT MANAGEMENT (FM) - Activate CDA function on FMS
08 FEB 18
Applicable to: ALL L42425
LANDING GEAR - STEERING - Introduce Wheel Steering Control System (WSCS) Software (S4)
08 FEB 18
Applicable to: ALL L42430
INDICATING/RECORDING SYSTEMS - CENTRAL WARNING SYSTEMS ¿ Introduce ATQC V2 for EIS
08 FEB 18
Applicable to: ALL L42454
INDICATING/RECORDING SYSTEMS - FWS ACQUISITION/INTERFACE - Define and install FWS S3/5.0 standard
08 FEB 18
HYDRAULIC POWER - Increase robustness of HYDRAULICS architecture to improve ATA42 OR define wiring impacts for CRDC
08 FEB 18
HYDRAULIC POWER - Define new HMCA S4.0 software
08 FEB 18
Applicable to: ALL L42544
PLACARDS AND MARKINGS - INTERIOR PLACARDS AND MARKINGS - Define and install 511VU placards with optional VIDEO
08 FEB 18
Applicable to: ALL L42552
FLIGHT CONTROLS - PRIMARY FLIGHT CONTROL SYSTEM (PFCS) - INTRODUCE FCGS 6.1 SW STD
08 FEB 18
Applicable to: ALL L42571
ICE AND RAIN PROTECTION - ICE DETECTION Define and install AICF S3.1 standard
08 FEB 18
FUEL - FUEL QUANTITY AND MANAGEMENT SYSTEM (FQMS) - Define FQMS V4 Software Standard
Applicable to: ALL L42471 Applicable to: ALL L42493
Applicable to: ALL
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CRITERION L42596
Linked SB
Incorp. Date
Title
08 FEB 18
Applicable to: ALL L42665
MISCELLANEOUS - ADDITIONAL CERTIFICATION ITEMS - ENABLE WIFI IN COCKPIT
08 AUG 18
Applicable to: ALL L42666
FLIGHT CONTROLS - SPOILER - Introduce new std of Spoiler EBHA to solve undue active mode.
08 FEB 18
Applicable to: ALL L42669
ELECTRICAL POWER - AC MAIN GENERATION Define and install GCU S4
08 AUG 18
Applicable to: ALL L42746
INDICATING/RECORDING SYSTEMS - FWS ACQUISITION/INTERFACE - ACTIVATE ETC CODE N° 27SP ¿ UNDUE ACTIVE MODE ON SPOILER EBHA
08 FEB 18
Applicable to: ALL L42771
AUTO FLIGHT - GENERAL - Upgrade BTV-ROPS function to Step 3 with all runway states
08 FEB 18
Applicable to: ALL L42782
ICE AND RAIN PROTECTION - WINDSHIELD RAIN PROTECTION - Remove rain repellent system (Equipments only)
08 FEB 18
Applicable to: ALL L42820
NAVIGATION - VOR/MARKER - Define and install VOR2 receiver and uninstall 50 ohms load
08 FEB 18
Applicable to: ALL L42865
NAVIGATION - DISTANCE MEASURING EQUIPMENT (DME) - .Define and Install DME2 interrogator
17 APR 19
LIGHTS - EXTERIOR - Define and Install 3HID (Landing, Take-Off and RTO-Taxi lights) and 1HID (WES and Logo lights) in LED technology
Applicable to: G-VJAM, G-VPRD, G-VRNB, G-VTEA L42959 20 FEB 18
NAVIGATION - RADIO ALTIMETER - Define and install DLRA S3.2 standard
Applicable to: ALL L42973
08 AUG 18
Applicable to: ALL L42980
LANDING GEAR - PARKING BRAKING - INTRODUCE NEW PARK BRAKE SELECTOR VALVE (PBSELV) CHECK VALVES
08 FEB 18
ELECTRICAL POWER - BATTERY MAIN GENERATION - Define and Install Ni-Cad Batteries
Applicable to: ALL
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CRITERION L43001
Linked SB
Incorp. Date
Title
08 FEB 18
Applicable to: ALL L43080
INDICATING/RECORDING SYSTEMS - FWS ACQUISITION/INTERFACE - Activate ETC code 22TS Inhibit TOS Pack 2 alerts
08 FEB 18
Applicable to: ALL L43174
LANDING GEAR - WHEELS AND BRAKES /1 Introduce new A350-1000 Goodrich Wheel
08 AUG 19
NAVIGATION - SENSORS, POWER SUPPLY AND SWITCHING - Remove SSA probes and replace them by obturators Applicable to: G-VDOT, G-VJAM, G-VPRD, G-VRNB, G-VTEA L43207 08 AUG 18 LANDING GEAR - PARKING BRAKING - INTRODUCE MODIFIED PARK BRAKE SELECTOR VALVE (PBSELV) Applicable to: ALL L43234 08 AUG 18 FLIGHT CONTROLS - PRIMARY FLIGHT CONTROL SYSTEM (PFCS) - DEFINE AND INSTALL FCGS X10 STANDARD Applicable to: ALL L43237 08 AUG 18 NAVIGATION - AIR DATA/INERTIAL REFERENCE SYSTEM (ADIRS) - DEFINE AND INSTALL ADIRS S4.2 STANDARD Applicable to: ALL L43238 08 AUG 19 NAVIGATION - AIR DATA/INERTIAL REFERENCE SYSTEM (ADIRS) - DEFINE AND INSTALL ADIRS S6 STANDARD Applicable to: ALL L43246 08 AUG 18 FLIGHT CONTROLS - PRIMARY FLIGHT CONTROL SYSTEM (PFCS) - Define and install FCGS SW X9.1 standard Applicable to: ALL L43254 08 FEB 18 INDICATING/RECORDING SYSTEMS - FWS ACQUISITION/INTERFACE - DEACTIVATE ETC CODE 22TS - INHIBIT TOS PACK 2 ALERTS Applicable to: ALL L43257 08 FEB 18 EQUIPMENT/FURNISHINGS - LININGS AND FURNISHINGS - Remove of «DEACT » sticker for T.O SURV push button Applicable to: ALL Continued on the following page
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CRITERION L43292
Linked SB
Incorp. Date 21 OCT 19
Applicable to: G-VDOT, G-VRNB, G-VTEA L43407 08 AUG 18
Title
INDICATING/RECORDING SYSTEMS - CDS - DISPLAY UNITS (DU) AND INTERFACE - Activate SPP for touchscreen function on Display Unit INDICATING/RECORDING SYSTEMS - FWS ACQUISITION/INTERFACE - ACTIVATE ETC CODE 34AD - MODIFY DOUBLE IR FAULT PROCEDURES
Applicable to: ALL L43487
08 FEB 18
Applicable to: ALL L43488
INDICATING/RECORDING SYSTEMS - FWS ACQUISITION/INTERFACE - DEFINE AND INSTALL FWS S5/2.2 STANDARD
08 FEB 18
Applicable to: ALL L43494
INDICATING/RECORDING SYSTEMS - DISPLAY SYSTEMS - DEFINE AND INSTALL CDS S5.1 STANDARD
21 OCT 19
Applicable to: G-VRNB, G-VTEA L43510
INTEGRATED MODULAR AVIONICS - AFDX NETWORK - REMOVE 4 AFDX SWITCHES ON ONE NETWORK AND THE ASSOCIATED WIRING
08 AUG 18
Applicable to: ALL L43538
ICE AND RAIN PROTECTION - WING ICE PROTECTION - Add hole through WIPV butterfly to increase heating flow across the valve
08 AUG 18
Applicable to: ALL L43543
EQUIPMENT/FURNISHINGS - LININGS AND FURNISHINGS - REMOVE « DEACT » STICKER FOR ROPS PUSH BUTTON
08 FEB 18
Applicable to: ALL L43580
HYDRAULIC POWER - Define and install HMCA S/W upgrade to avoid excessive heat rejection
08 AUG 18
Applicable to: ALL L43587
ELECTRICAL POWER - BATTERY MAIN GENERATION - ADAPT NI-CAD BATTERIE INSTALLATION
21 OCT 19
NAVIGATION - AIRCRAFT ENVIRONMENT SURVEILLANCE SYSTEM (AESS) - Define and install AESS S4 standard
Applicable to: G-VDOT, G-VRNB, G-VTEA
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CRITERION L43597
Linked SB
Incorp. Date
Title
17 APR 19
Applicable to: ALL L43620
INDICATING/RECORDING SYSTEMS - FWS ACQUISITION/INTERFACE - Activate ETC code 36BV Open CBV in emergency electric configuration (EEC)
05 FEB 19
Applicable to: ALL L43634
INDICATING/RECORDING SYSTEMS - FWS ACQUISITION/INTERFACE - Activate ETC code 24GE EMER CONFIG & Deferred procedure GVTY EXTENSION
08 AUG 18
Applicable to: ALL L44214
FLIGHT CONTROLS - PRIMARY FLIGHT CONTROL SYSTEM (PFCS) - DEFINE AND INSTALL FCGS P9.1.3 STD
05 FEB 19
Applicable to: ALL L48016
FLIGHT CONTROLS - HIGH LIFT CONTROL AND MONITORING - Introduce new SFCC S/W standard 5.2
20 FEB 18
Applicable to: ALL L48065
NAVIGATION - RADIO ALTIMETER - REVERSE TO DLRA S3.1 STANDARD (ANTI-MOD)
08 AUG 18
Applicable to: ALL L48109
INDICATING/RECORDING SYSTEMS - FWS ACQUISITION/INTERFACE - Define and install ATQC V3 for FWS S5/2.2
05 FEB 19
Applicable to: ALL L48116
INDICATING/RECORDING SYSTEMS - CONTROL AND DISPLAY SYSTEM (CDS) - Define and install CDS S6 standard
05 FEB 19
Applicable to: ALL L48124
INDICATING/RECORDING SYSTEMS - FWS ACQUISITION/INTERFACE - Define and install FWS S6/2.0 standard
05 FEB 19
Applicable to: ALL L48136
FLIGHT CONTROLS - PRIMARY FLIGHT CONTROL SYSTEM (PFCS) - Define and Install FCGS SW X11 Standard
05 FEB 19
Applicable to: ALL L48209
ICE AND RAIN PROTECTION - WING ICE PROTECTION - Define and Install Wing Ice Protection System standard S5
05 FEB 19
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CRITERION
Linked SB
Incorp. Date
Title
- Modify procedures of alert F/CTL L(R) INR AILERON FAULT
Applicable to: ALL L48211
08 AUG 18
Applicable to: ALL L48350
INDICATING/RECORDING SYSTEMS - FWS ACQUISITION/INTERFACE - Define and install ATQC V4 for FWS S5/2.2
05 FEB 19
Applicable to: ALL L48369
INDICATING/RECORDING SYSTEMS - DISPLAY SYSTEMS Define and install CDS S6.1.1 standard
05 FEB 19
Applicable to: ALL L48397
INDICATING/RECORDING SYSTEMS - FWS ACQUISITION/INTERFACE - Define and install ATQC version 5 for FWS S5/2.2
21 OCT 19
Applicable to: G-VRNB, G-VTEA L48398
INDICATING/RECORDING SYSTEMS - FWS ACQUISITION/INTERFACE - Activate ETC 21AC Update CPCS procedure in AFDX 1.4 config
17 APR 19
Applicable to: ALL L60118
INDICATING/RECORDING SYSTEMS - FWS ACQUISITION/INTERFACE - Activate ETC code 29BF Remove FP9 inhibition for dual HYD alert
08 FEB 18
Applicable to: ALL L60189
CABIN SYSTEMS - INFLIGHT ENTERTAINMENT SYSTEM - Define IFE system
08 FEB 18
Applicable to: ALL L60206
CABIN SYSTEMS - IFE - HEAD END AND CABIN DISTRIBUTION - Define & install wiring for connection to external camera system
08 FEB 18
Applicable to: ALL L60271
CABIN SYSTEMS - CDSS - Define and install equipment and wiring for ADU1 and 3 cameras
08 FEB 18
Applicable to: ALL L60273
E/F - ADDITIONAL COMPARTMENTS Integrate FCRC in DMU and adapt secondary structure for FCRC at Z1
08 FEB 18
E/F - ADDITIONAL COMPARTMENTS Integrate CCRC in DMU and adapt secondary structure for CCRC 6 bunk at Z7
Applicable to: ALL
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CRITERION L60527
Linked SB
Incorp. Date
Title
08 FEB 18
Applicable to: ALL L62142
FIRE PROTECTION - LDCC FIRE EXTINGUISHING Define & Install extended cargo fire suppression capacity (300 min ETOPS, 290 min suppr. time)
08 FEB 18
Applicable to: ALL L62156
CABIN SYSTEMS - CIDS - Define "NO PED" sign on DBPS functionality
08 FEB 18
Applicable to: ALL L62914
CABIN SYSTEMS - IFE - HEAD END AND CABIN DISTRIBUTION - Define PAX INFO switch in cockpit
08 FEB 18
Applicable to: ALL L63047
OXYGEN - CREW OXYGEN DISTRIBUTION - DEFINE AND INSTALL CREW OXYGEN MASKS IN COCKPIT
08 AUG 18
Applicable to: ALL L64338
CABIN SYSTEMS - CIDS COCKPIT AND INTERCONNECTION - Define CIDS Software Release 5
08 AUG 19
Applicable to: ALL L64738
CABIN SYSTEMS - INFLIGHT ENTERTAINMENT (IFE) - HEAD END AND CABIN DISTRIBUTION - Define and Install nWAP2 Supplier Zodiac
08 AUG 18
Applicable to: ALL L80519
CABIN SYSTEMS - CIDS COCKPIT AND INTERCONNECTION - DEFINE CIDS SOFTWARE RELEASE 5.0.6
08 FEB 18
Applicable to: ALL L85311
FUSELAGE - CENTER FUSELAGE - Remove ventilation Grid for aerodynamic improvement in belly fairing
05 FEB 19
Applicable to: ALL L85312
ENGINE FUEL AND CONTROL - ENGINE CONTROL AND FAULT MONITORING - INTRODUCE EEC SOFTWARE STANDARD 5.3.3 FOR 97k
05 FEB 19
Applicable to: ALL L85350
OIL - OIL QUANTITY AND TEMPERATURE INDICATING SYSTEM - INTRODUCE UPGRADED COLTS REQUIRED TO INCREASE INDICATED ENGINE USEABLE OIL QUANTITY
21 OCT 19
ENGINE FUEL AND CONTROL - ENGINE CONTROL AND FAULT MONITORING - INTRODUCE EEC SOFTWARE STANDARD 7.0 for -1000
Applicable to: G-VDOT, G-VRNB, G-VTEA
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CRITERION L91040
Linked SB
Incorp. Date
Title
08 FEB 18
Applicable to: ALL L91102
AIRBORNE AUXILIARY POWER - CONTROL AND MONITORING - Introduce new APS ECB SW Standard 4.0
17 APR 19
Applicable to: ALL L92178
PNEUMATIC - ENGINE BLEED AIR SUPPLY SYSTEM Introduce SW STANDARD 5.0 for EBAS and OHDS
08 FEB 18
Applicable to: ALL L95014
AIR CONDITIONING - PRESSURIZATION CONTROL Introduce in-service needs for CPCS post-EIS SW S4
08 AUG 18
Applicable to: ALL L95116
MISCELLANEOUS - ADDITIONAL CERTIFICATION ITEMS - Implement capability for revenue flight with the landing gear extended
17 APR 19
MISCELLANEOUS - DESIGN WEIGHTS - CERTIFY THE AIRCRAFT A350-1000 WITH TRIPLE OPERATIONAL WEIGHTS: WV000, WV010 AND WV009
Applicable to: ALL (1) Evolution code : N=New, R=Revised, E=Effectivity
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TABLE OF CONTENTS
Aircraft Configuration Summary...............................................................................................................................A If Installed Table...................................................................................................................................................... B Main FCOM Changes..............................................................................................................................................C FCOM Purpose........................................................................................................................................................D FCOM Contents....................................................................................................................................................... E How can an Operator obtain an updated FCOM?.................................................................................................. F FCOM Use and Organization..................................................................................................................................G FCOM Revision Management................................................................................................................................. H Definitions.................................................................................................................................................................. I TDU General Description......................................................................................................................................... J TAB General Description.........................................................................................................................................K Abbreviations............................................................................................................................................................ L
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Localization Title
GEN-PLP-TOC Main FCOM Changes
Toc Index
GEN-PLP-TOC FCOM Revision Management
GEN TURB button GEN Weather Hazard Prediction Function GEN February 2020 GEN January 2020 GEN December 2019 GEN November 2019 GEN October 2019
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ID
Reason
1
Documentation update: Deletion of the "00025118 May 2019" table of content entry. Documentation update: Deletion of the "00025086 April 2019" table of content entry. Documentation update: Deletion of the "00025229.0001001 August 2019" documentary unit. Documentation update: Deletion of the "00025173.0001001 July 2019" documentary unit. Documentation update: Deletion of the "00025155.0001001 June 2019" documentary unit. Documentation update: Deletion of the "00025118.0001001 May 2019" documentary unit. Documentation update: Deletion of the "00025086.0001001 April 2019" documentary unit. Simplification of configuration management Information no longer available Documentation update: Deletion of the "00025229 August 2019" table of content entry. Documentation update: Deletion of the "00025173 July 2019" table of content entry. Documentation update: Deletion of the "00025155 June 2019" table of content entry. Documentation update: Deletion of the "00020885 Temporary Information" table of content entry. Documentation update: Deletion of the "00020885.0001001 Temporary Information" documentary unit. New DU to introduce TDU definition Documentation update: Addition of "TURB button" documentary unit Documentation update: Addition of "Weather Hazard Prediction Function" documentary unit Documentation update: Addition of "February 2020" documentary unit Documentation update: Addition of "January 2020" documentary unit Documentation update: Addition of "December 2019" documentary unit Documentation update: Addition of "November 2019" documentary unit Documentation update: Addition of "October 2019" documentary unit Continued on the following page
2
B
1
B
2
C
3
C
4
C
5
C
6
C
7
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Localization Title
GEN FCOM Contents GEN TDU General Description GEN TAB General Description GEN Abbreviations GEN Abbreviations
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ID
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Reason
L
Addition of the section that contains reference to Abnormal Temporary Behaviors. 9 Documentation update: Addition of "TDU General Description" documentary unit 10 Documentation update: Addition of "TAB General Description" documentary unit 11 Addition of REACT abbreviation.
L
12 Addition of the TAB abbreviation.
J K
8
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GENERAL INFORMATION A350
FLIGHT CREW OPERATING MANUAL
AIRCRAFT CONFIGURATION SUMMARY Applicable to: ALL Ident.: GEN-ACS-00022827.0001001 / 09 MAR 16
For awareness and for the specified aircraft, the following table provides the flight crew with a list of optional aircraft systems and functions related to flight and aircraft operations. Ident.: GEN-ACS-00022828.0001001 / 09 MAR 16
Name
Ident.: GEN-ACS-00022832.0001001 / 09 MAR 16
ADF
Ident.: GEN-ACS-00024231.0001001 / 27 JUN 17
Battery Type - Ni-Cad
Ident.: GEN-ACS-00023275.0001001 / 27 JUN 17
Battery Type - Li-Ion
Ident.: GEN-ACS-00022833.0002001 / 09 MAR 16
FMS - Continuous Descent Approach (CDA)
Ident.: GEN-ACS-00022834.0003001 / 09 MAR 16
GLS
Ident.: GEN-ACS-00024693.0001001 / 09 MAR 18
HPFD
Ident.: GEN-ACS-00022835.0001001 / 09 MAR 16
QFE Baro Setting
Ident.: GEN-ACS-00022839.0002001 / 22 MAR 16
SLS
System
Installed
NAV
No
ELEC
Yes
ELEC
No
AUTO FLT
Yes
NAV
Yes
CDS
No
CDS
No
NAV
Yes
IF INSTALLED TABLE Ident.: GEN-IFIT-00022829.0001001 / 09 MAR 16 Applicable to: ALL
The "If Installed" Table below provides a list of optional systems and functions of the aircraft. For most of the optional systems or functions associated with the "if installed" symbol in the FCOM, the table indicates if the optional systems or functions are installed, or not installed. Note:
Highly customized options such as cabin installations are not covered in the following table.
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FLIGHT CREW OPERATING MANUAL Ident.: GEN-IFIT-00022830.0001001 / 09 MAR 16 Applicable to: ALL
Item
System
Installed
NAV
No
Ident.: GEN-IFIT-00022973.0001001 / 09 MAR 16 Applicable to: ALL L13
ADF ADFs ADF1 ADF1 pb ADF 1 ADF 1(2) FREQ ENTRY FIELD ADF 1(2) IDENT ENTRY FIELD ADF2 ADF2 pb ADF 2 ADF BEARING DISPLAY ADF FREQ ADF FREQ ENTRY FIELD ADF IDENT ENTRY FIELD ADF Pointer ADF Pointers ADF TUNING Automatic Direction Finder (ADF) BFO Dual ADF system NDB NDB1 NDB2 NDBS NDB-DME Only one ADF Single Automatic Direction Finder (ADF) system SPECIF NDB NOT AVAIL
VIR A350 FLEET FCOM
←B→
GEN P 2/48 15 MAR 20
GENERAL INFORMATION A350
FLIGHT CREW OPERATING MANUAL Ident.: GEN-IFIT-00022947.0002001 / 17 NOV 17 Applicable to: ALL L13
ADS-B Traffic ADS-B TRAFFIC 1 ADS-B TRAFFIC 2 ADS-B TRAFFIC 1(2) ADS-B TRAFFIC 1+2 ADS-B TRAFFIC 1(2) FAULT ADS-B TRAFFIC 1+2 FAULT ADS-B TRAFFIC Button TRAFFIC Page
SURV
Yes
COND
No
VENT
No
Flight Envelope
No
BRAKES
No
Ident.: GEN-IFIT-00022958.0001001 / 09 MAR 16 Applicable to: ALL L13
Aft Cargo Compartment Ventilation Aft cargo compartment AFT CARGO ISOL AFT CARGO ISOL FAULT AFT CARGO VENT AFT CARGO VENT DEGRADED AFT CARGO VENT FAULT Aft Cargo Ventilation CARGO AFT ISOL VALVES
Ident.: GEN-IFIT-00022962.0001001 / 09 MAR 16 Applicable to: ALL
Avionics Ground Cooling Unit
Ident.: GEN-IFIT-00023283.0001001 / 09 MAR 16 Applicable to: ALL
Bank Angle Audio Indicator
Ident.: GEN-IFIT-00022886.0001001 / 09 MAR 16 Applicable to: ALL L13
Brake Fan Brake Fans BRAKE FAN pb
VIR A350 FLEET FCOM
←B→
GEN P 3/48 15 MAR 20
GENERAL INFORMATION A350
FLIGHT CREW OPERATING MANUAL Ident.: GEN-IFIT-00023264.0002001 / 08 NOV 18 Applicable to: ALL L13
Cabin Crew Rest Compartment CAB REST TEMP CTL CAB REST pb CAB REST FLT(CABIN) REST DET FAULT FLT(CABIN) REST SMOKE
Ident.: GEN-IFIT-00023414.0001001 / 07 JUL 16 Applicable to: ALL
Cabin crew WI-FI
N/A
Yes
CAB COM
No
CABIN
No
CAB COM
Yes
CDS-VIDEO
No
FIRE
Yes
FIRE
No
Ident.: GEN-IFIT-00023296.0001001 / 07 JUL 16 Applicable to: ALL L13
CABIN : READY Indication in T.O/LDG Memos and Checklists CABIN : READY CABIN : READY indication
Ident.: GEN-IFIT-00023271.0001001 / 09 MAR 16 Applicable to: ALL L13
CABIN READY memo CABIN READY
Ident.: GEN-IFIT-00022904.0001001 / 09 MAR 16 Applicable to: ALL L13
Cabin Video Cabin Video Monitoring System Cabin Video Monitoring System (CVMS) CVMS CVMS pb VIDEO pb
Ident.: GEN-IFIT-00024374.0002001 / 17 NOV 17 Applicable to: ALL L13
Cargo Fire Extinguishing System Suppression Time 290 min 290 min
Ident.: GEN-IFIT-00024375.0001001 / 17 NOV 17 Applicable to: ALL L13
Cargo Fire Extinguishing System Suppression Time 360 min 360 min
VIR A350 FLEET FCOM
←B→
GEN P 4/48 15 MAR 20
GENERAL INFORMATION A350
FLIGHT CREW OPERATING MANUAL Ident.: GEN-IFIT-00022905.0001001 / 09 MAR 16 Applicable to: ALL L13
Cargo Video Lower Deck Surveillance Function
CDS-VIDEO
No
OXY
No
CDS-VIDEO
Yes
COND
No
FMS
Yes
N/A
Yes
N/A
Yes
N/A
No
CAB COM
No
Ident.: GEN-IFIT-00024741.0001001 / 07 MAY 18 Applicable to: ALL L13
Chemical Oxygen System 15 min 15 min
Ident.: GEN-IFIT-00022906.0002001 / 09 MAR 16 Applicable to: ALL L13
Cockpit Door Video Cockpit Door Surveillance System Cockpit Door Surveillance System (CDSS) CDSS
Ident.: GEN-IFIT-00023399.0001001 / 09 MAR 16 Applicable to: ALL L13
Cockpit Humidifier HUMIDIFIER sw
Ident.: GEN-IFIT-00023555.0002001 / 14 JUN 16 Applicable to: ALL L13
Continuous Descent Approach CDA
Ident.: GEN-IFIT-00023602.0001001 / 14 JUN 16 Applicable to: ALL
Crash Axe
Ident.: GEN-IFIT-00023634.0002001 / 07 JUL 16 Applicable to: ALL
Crew rest compartments
Ident.: GEN-IFIT-00023603.0001001 / 14 JUN 16 Applicable to: ALL
Crow Bar
Ident.: GEN-IFIT-00023700.0001001 / 17 NOV 17 Applicable to: ALL L13
Emergency Crew Alerting System (ECAS) ECAS
VIR A350 FLEET FCOM
←B→
GEN P 5/48 15 MAR 20
GENERAL INFORMATION A350
FLIGHT CREW OPERATING MANUAL Ident.: GEN-IFIT-00023861.0001001 / 08 NOV 18 Applicable to: ALL L13
EVAC Panel COMMAND PB-SW Evacuation (EVAC) Panel Evacuation (EVAC) signaling EVAC HORN COMMAND EVAC EVAC COMMAND
CAB COM
Yes
N/A
Yes
COM
No
COND
No
Ident.: GEN-IFIT-00023265.0002001 / 08 NOV 18 Applicable to: ALL L13
Flight Crew Rest Compartment FLT REST pb FLT(CABIN) REST DET FAULT FLT(CABIN) REST SMOKE
Ident.: GEN-IFIT-00023425.0001001 / 17 NOV 17 Applicable to: ALL
Fourth occupant ACP
Ident.: GEN-IFIT-00022957.0001001 / 04 MAY 16 Applicable to: ALL L13
FWD Cargo Compartment Ventilation and Temperature Regulation CARGO FWD ISOL VALVES CARGO FWD TEMP REGUL CARGO FWD TEMP REGUL AVAIL IN FLT Forward cargo compartment FWD Cargo Compartment Temperature Regulation FWD Cargo Compartment Ventilation FWD CARGO ISOL FWD CARGO ISOL FAULT FWD CARGO TEMP FWD CARGO TEMP REGUL FWD CARGO TEMP REGUL DEGRADED FWD CARGO TEMP REGUL FAULT FWD CARGO VENT FWD CARGO VENT DEGRADED FWD CARGO VENT FAULT FWD Cargo Ventilation and Temperature Regulation Temperature regulation in the forward cargo compartment Temperature regulation of the forward cargo compartment
VIR A350 FLEET FCOM
←B→
GEN P 6/48 15 MAR 20
GENERAL INFORMATION A350
FLIGHT CREW OPERATING MANUAL Ident.: GEN-IFIT-00023266.0001001 / 09 MAR 16 Applicable to: ALL L13
Glareshield PTT pb PTT pb
COM
No
NAV
Yes
COM
Yes
COM
Yes
Ident.: GEN-IFIT-00022960.0002001 / 09 MAR 16 Applicable to: ALL L13
GLS channel GBAS Landing System (GLS) GLS 1(2) GLS 1(2) FAULT GLS 1+2 GLS 1+2 FAULT GLS Approach GLS AUTOLAND GLS CAT I GLS LIMITED TO APPR 1 NAV GLS 1(2) FAULT NAV GLS 1+2 FAULT
Ident.: GEN-IFIT-00022940.0002001 / 09 MAR 16 Applicable to: ALL
HF 2
Ident.: GEN-IFIT-00023491.0001001 / 08 NOV 18 Applicable to: ALL L13
HF Datalink HF Data mode Data mode GND HF DATALINK pb-sw DATALINK DATALINK FAULT GND HF DATALINK
VIR A350 FLEET FCOM
←B→
GEN P 7/48 15 MAR 20
GENERAL INFORMATION A350
FLIGHT CREW OPERATING MANUAL Ident.: GEN-IFIT-00022909.0001001 / 28 APR 17 Applicable to: ALL L13
HUD CAPT + F/O HUDs CAPT+F/O HUDs CAPT HUD F/O HUD HUD Control Panel Head Up Display Head Up Display (HUD) NAV CAPT(F/O) HUD FAULT NAV CAPT + F/O HUDs FAULT NAV CAPT(F/O) HUD NAV CAPT + F/O HUDs
CDS
No
FUEL
No
CDS-VIDEO
No
CDS-VIDEO
Yes
VENT
No
Ident.: GEN-IFIT-00022831.0001001 / 09 MAR 16 Applicable to: ALL L13
Jettison FUEL JETTISON PANEL JETTISON ACTIVE JETTISON ARM JETTISON ARM pb-sw JETTISON ACTIVE pb-sw JETTISON FAULT JETTISON COMPLETED JETTISON OUTLET JTSN GW JTSN GW ENTRY FIELD JETTISON IN PROGRESS JETTISON INDICATION JETTISON PROC
Ident.: GEN-IFIT-00022910.0001001 / 14 JUN 16 Applicable to: ALL
Landscape Camera
Ident.: GEN-IFIT-00023633.0002001 / 14 JUN 16 Applicable to: ALL
Landscape Camera pb-sw
Ident.: GEN-IFIT-00022961.0001001 / 09 MAR 16 Applicable to: ALL
LAV and Galleys Air Extraction Outlet
VIR A350 FLEET FCOM
←B→
GEN P 8/48 15 MAR 20
GENERAL INFORMATION A350
FLIGHT CREW OPERATING MANUAL Ident.: GEN-IFIT-00025096.0002001 / 15 APR 19 Applicable to: G-VJAM, G-VPRD, G-VRNB, G-VTEA L13
LED Landing Lights LED-based landing lights
LIGHTS
Yes
LIGHTS
No
LIGHTS
Yes
LIGHTS
No
LIGHTS
Yes
LIGHTS
No
ELEC
No
VENT
No
Ident.: GEN-IFIT-00025096.0001001 / 15 APR 19 Applicable to: G-VDOT, G-VLUX, G-VPOP L13
LED Landing Lights LED-based landing lights
Ident.: GEN-IFIT-00025097.0002001 / 15 APR 19 Applicable to: G-VJAM, G-VPRD, G-VRNB, G-VTEA L13
LED Takeoff Lights LED-based takeoff lights units
Ident.: GEN-IFIT-00025097.0001001 / 15 APR 19 Applicable to: G-VDOT, G-VLUX, G-VPOP L13
LED Takeoff Lights LED-based takeoff lights units
Ident.: GEN-IFIT-00025098.0002001 / 15 APR 19 Applicable to: G-VJAM, G-VPRD, G-VRNB, G-VTEA L13
LED Taxi and Runway Turn Off Lights LED-based taxi and runway turn off lights
Ident.: GEN-IFIT-00025098.0001001 / 15 APR 19 Applicable to: G-VDOT, G-VLUX, G-VPOP L13
LED Taxi and Runway Turn Off Lights LED-based taxi and runway turn off lights
Ident.: GEN-IFIT-00023398.0001001 / 09 MAR 16 Applicable to: ALL
Li-Ion Batteries
Ident.: GEN-IFIT-00023295.0002001 / 09 MAR 16 Applicable to: ALL
MLG Bay Ventilation Air Outlet
VIR A350 FLEET FCOM
←B→
GEN P 9/48 15 MAR 20
GENERAL INFORMATION A350
FLIGHT CREW OPERATING MANUAL Ident.: GEN-IFIT-00023411.0002001 / 19 MAY 16 Applicable to: ALL L13
MOBILE COM pb-sw PAX MOBILE COM DISC memo PAX MOBILE COM DISC
Ident.: GEN-IFIT-00023336.0002001 / 14 APR 16 Applicable to: ALL
NO PED sw
CAB COM
Yes
LIGHTS
Yes
LIGHTS
Yes
LIGHTS
No
LIGHTS
Yes
LIGHTS
No
CAB COM
No
VENT
No
Ident.: GEN-IFIT-00023471.0002001 / 07 JUL 16 Applicable to: ALL L13
NO PORTABLE DEVICES memo NO PORTABLE DEVICES No Portable Electronic Devices NO PED NO PED signs
Ident.: GEN-IFIT-00023337.0001001 / 14 APR 16 Applicable to: ALL
NO SMKG/NO PED sw
Ident.: GEN-IFIT-00023335.0001001 / 14 APR 16 Applicable to: ALL L13
NO SMOKING memo NO SMOKING
Ident.: GEN-IFIT-00023338.0002001 / 14 APR 16 Applicable to: ALL
NO SMOKING sw
Ident.: GEN-IFIT-00023267.0001001 / 08 NOV 18 Applicable to: ALL L13
On-board Mobile Telephony System On-board Mobile Telephony System (OMTS) OMTS NO MOBILE NO MOBILE sw NO MOBILE signs Mobile telephony
Ident.: GEN-IFIT-00023294.0002001 / 09 MAR 16 Applicable to: ALL
Pack Bay Ventilation Air Outlets
VIR A350 FLEET FCOM
←B→
GEN P 10/48 15 MAR 20
GENERAL INFORMATION A350
FLIGHT CREW OPERATING MANUAL Ident.: GEN-IFIT-00023415.0002001 / 07 JUL 16 Applicable to: ALL L13
Passenger WI-FI Internet
CAB COM
Yes
CAB COM
No
CAB COM
Yes
ELEC
No
ELEC
No
DOOR
No
CDS
No
Ident.: GEN-IFIT-00022968.0001001 / 08 NOV 18 Applicable to: ALL L13
PAX BBAND PAX BBAND bay PAX BBAND pb-sw PAX BBAND DET FAULT PAX BBAND SMK DET PAX BBAND SMOKE PAX BBAND VENT PAX BBAND VENT FAULT SMOKE PAX BBAND DET SMOKE PAX BBAND DET FAULT SMOKE PAX BBAND DET REDUNDANCY SMOKE PAX BBAND SMOKE
Ident.: GEN-IFIT-00023268.0002001 / 09 MAR 16 Applicable to: ALL
PAX INFO pb-sw
Ident.: GEN-IFIT-00023359.0001001 / 07 JUL 16 Applicable to: ALL L13
PAX PERS ELEC SPLY pb-sw PED power outlets
Ident.: GEN-IFIT-00023416.0001001 / 07 JUL 16 Applicable to: ALL
PED power outlets inhibition at slats extension
Ident.: GEN-IFIT-00023325.0001001 / 09 MAR 16 Applicable to: ALL L13
Privacy Door Privacy Area Privacy Door Keypad
Ident.: GEN-IFIT-00023224.0001001 / 09 MAR 16 Applicable to: ALL L13
QFE Baro Setting QFE
VIR A350 FLEET FCOM
←B→
GEN P 11/48 15 MAR 20
GENERAL INFORMATION A350
FLIGHT CREW OPERATING MANUAL Ident.: GEN-IFIT-00024130.0002001 / 30 JAN 18 Applicable to: ALL L12
Rain Repellent RAIN RPLNT LEVEL RAIN RPLNT PB Rain repellent system RAIN RPLNT LEVEL INDICATION
Ice and Rain Protection
No
FUEL
Yes
FUEL
No
ROW/ROP
Yes
Ident.: GEN-IFIT-00022868.0002001 / 09 MAR 16 Applicable to: ALL L13
Refuel Coupling (Left Wing) Left Wing Refuel Coupling Second Refuel Coupling Refuel Coupling Door
Ident.: GEN-IFIT-00022867.0001001 / 09 MAR 16 Applicable to: ALL L13
Refuel pb-sw Refuel Refuel Panel
Ident.: GEN-IFIT-00024731.0002001 / 08 NOV 18 Applicable to: ALL L13
ROW/ROP pb-sw ROW/ROP & BTV OFF ROW/ROP
VIR A350 FLEET FCOM
←B→
GEN P 12/48 15 MAR 20
GENERAL INFORMATION A350
FLIGHT CREW OPERATING MANUAL Ident.: GEN-IFIT-00022959.0002001 / 08 JUL 19 Applicable to: ALL L13
SLS DESELECT SLS BUTTON LP LPV LPV minima LPV-SLS NAV SLS 1(2) FAULT NAV SLS 1+2 FAULT NO SLS FOR THIS APPR FOR FLS: DESELECT SLS ON NAVAIDS Satellite Landing System (SLS) SBAS SLS 1 SLS 1(2) SLS 1(2) FAULT SLS 1+2 SLS 1+2 FAULT SLS function SLS MANUAL TUNING NOT ALLOWED SLS NOT AVAIL: SBAS DESELECTED FOR FLS: DESELECT SLS ON NAVAIDS
NAV
Yes
OIS
No
NAV
Yes
FMS
No
Ident.: GEN-IFIT-00022967.0001001 / 09 MAR 16 Applicable to: ALL L13
Spare EFB (EFB3) Spare EFB Spare EFB Button Spare Status Column
Ident.: GEN-IFIT-00023400.0002001 / 09 MAR 16 Applicable to: ALL L13
SND Standby Navigation Display Standby Navigation Display (SND)
Ident.: GEN-IFIT-00024961.0001001 / 03 JAN 19 Applicable to: ALL L13
Takeoff Monitoring TAKEOFF MONITORING FUNCTION T.O ACCELERATION DEGRADED
VIR A350 FLEET FCOM
←B→
GEN P 13/48 15 MAR 20
GENERAL INFORMATION A350
FLIGHT CREW OPERATING MANUAL Ident.: GEN-IFIT-00022945.0002001 / 14 APR 16 Applicable to: ALL L13
Taxi Video Taxi Camera Taxi Camera Light Taxi Camera Lights External and Taxiing Aid Camera System External and Taxiing Aid Camera System (ETACS) ETACS Belly Taxi Aid Camera Belly TAC Vertical Stabilizer Taxi Aid Camera Vertical Stabilizer TAC Taxi Aid Camera Taxi Aid Cameras TAC TAXI pb
Ident.: GEN-IFIT-00023468.0001001 / 07 JUL 16 Applicable to: ALL
Telemedicine
CDS-VIDEO
Yes
CAB COM
No
SURV
Yes
CDS
Yes
CDS
No
CDS
No
CDS-VIDEO
Yes
1 Ident.: GEN-IFIT-00025313.0001001 / 06 NOV 19
Applicable to: ALL
TURB Button
Ident.: GEN-IFIT-00023252.0002001 / 09 MAR 16 Applicable to: ALL
US Unit of Length
Ident.: GEN-IFIT-00023251.0001001 / 16 APR 19 Applicable to: ALL
US Unit of Temperature
Ident.: GEN-IFIT-00023250.0001001 / 09 MAR 16 Applicable to: ALL
US Unit of Weight
Ident.: GEN-IFIT-00023417.0002001 / 28 APR 17 Applicable to: ALL
Video monitoring system
VIR A350 FLEET FCOM
←B→
GEN P 14/48 15 MAR 20
GENERAL INFORMATION A350
FLIGHT CREW OPERATING MANUAL Ident.: GEN-IFIT-00023307.0002001 / 14 APR 16 Applicable to: ALL L13
VOR 2 DME 2 DME2 Dual DME system Dual VOR system VOR VOR2 VOR pb VORs
NAV
Yes
SURV
No
CAB COM
No
2 Ident.: GEN-IFIT-00025312.0001001 / 06 NOV 19
Applicable to: ALL
L13
Weather Hazard Prediction Function Weather Hazard Prediction Indications HZD tick box TURB tick box WXR HZD OFF WX+H WX+T+H
Ident.: GEN-IFIT-00023469.0001001 / 07 JUL 16 Applicable to: ALL
Wireless access to the Cabin Crew Mail Application
MAIN FCOM CHANGES Applicable to: ALL Ident.: GEN-GMAIN-00020946.0001001 / 28 APR 14
INTRODUCTION PURPOSE The purpose of the MAIN FCOM CHANGES section is to provide general information about the latest FCOM revisions, and to highlight the main changes. L12
Note:
In addition, each Documentary Unit (DU) highlights the reason(s) for change, and contains revision bars to indicate the revised sections. For more information, Refer to GEN FCOM Revision Management.
VIR A350 FLEET FCOM
← B to C →
GEN P 15/48 15 MAR 20
GENERAL INFORMATION A350
FLIGHT CREW OPERATING MANUAL
TIMEFRAME The MAIN FCOM CHANGES section is updated on a monthly basis, regardless of the revision cycle that is applicable to each Operator. The subjects in the MAIN FCOM CHANGES are categorized by month, but include revision information only from the previous 6 months. 3 Ident.: GEN-GMAIN-00025411.0001001 / 06 FEB 20
FEBRUARY 2020 AIRCRAFT SYSTEMS - LANDING GEAR - BRAKING SYSTEM - TEMPORARY ABNORMAL BEHAVIOR Introduction of two Temporary Abnormal Behaviors. In some failure modes of the landing gear lever, the Brake Control System (BCS) may consider the landing gear lever in an erroneous position. Each TAB provides a procedure to be applied in this situation to identify the failure mode. 4 Ident.: GEN-GMAIN-00025393.0001001 / 09 JAN 20
JANUARY 2020 GENERAL INFORMATION Introduction of the definition of Temporary Documentary Unit (TDU) and Temporary Abnormal Behaviors (TAB). As presented during 2019 Flight Operations Conferences, new TAB and TDU will comply with the new definitions. TAB and TDU that were published before January 2020 will be later adapted to the new definition in 2020. AIRCRAFT SYSTEMS - FLIGHT MANAGEMENT SYSTEM - ABNORMAL OPERATIONS Addition of a new description of the FIX INFO revision in the Abnormal Operations section to replace the TAB "Display of Erroneous FIX INFO on the ND" because the system design will not change. NORMAL PROCEDURES - STANDARD OPERATING PROCEDURES - AFTER START - ENG START SELECTOR Re-introduction of the TDU on ENG Start Selector recently removed. This is applicable to A350-900 and A350-1000. A thrust lever set above idle and stable during 1 min will lead to ENG STATOR A-ICE VLV CLOSED ECAM alert. This TDU, which requires no thrust lever movement, permits to avoid other events.
VIR A350 FLEET FCOM
←C→
GEN P 16/48 15 MAR 20
GENERAL INFORMATION A350
FLIGHT CREW OPERATING MANUAL
NORMAL PROCEDURES - SUPPLEMENTARY PROCEDURES - ENGINE START WITH AN AIR START UNIT Addition of the procedure information to keep engine thrust at idle for 1 min after engine start in order to avoid anti-ice faults of the engine stator section. 5 Ident.: GEN-GMAIN-00025359.0001001 / 09 JAN 20
DECEMBER 2019 No major change in this revision. 6 Ident.: GEN-GMAIN-00025342.0001001 / 09 JAN 20
NOVEMBER 2019 No major change in this revision. 7 Ident.: GEN-GMAIN-00025341.0001001 / 09 JAN 20
OCTOBER 2019 No major change in this revision. Ident.: GEN-GMAIN-00025282.0001001 / 05 SEP 19
SEPTEMBER 2019 OPERATIONS ENGINEERING BULLETINS - OEB 8 ISSUE 1 - AFS CP ALTITUDE KNOB USE Introduction of a new OEB 8 in order to limit to only 100 ft the possible not commanded altitude change due to AFS CP Alt knob sensitivity weakness. A new procedure is introduced, that requests the flight crew to set the outer knob of the AFS CP ALT knob to the 100 position after each use.
FCOM PURPOSE Applicable to: ALL Ident.: GEN-GPURP-00020640.0001001 / 28 APR 14
GENERAL The Flight Crew Operating Manual (FCOM) is a support documentation for flight crew.
VIR A350 FLEET FCOM
← C to D →
GEN P 17/48 15 MAR 20
GENERAL INFORMATION A350
FLIGHT CREW OPERATING MANUAL
The purpose of the FCOM is to: ‐ Provide all necessary operating limitations, procedures, techniques, performance and system information the flight crew needs to safely and efficiently operate the A350 during normal, abnormal and emergency situations. ‐ Serve directly as a Flight Crew Operating Manual, or as a basis for Operators to develop their own customized Airline Operations Manual, in accordance with applicable requirements ‐ Serve as a comprehensive reference guide during initial and refresher flight crew training. Note:
This manual is not designed: ‐ To teach basic piloting skills ‐ To provide basic piloting techniques applicable to jet aircraft , or information, that are considered as basic airmanship for trained flight crews who are familiar with that type of aircraft and its general handling characteristics.
The Flight Crew Operating Manual (FCOM) complements the Airplane Flight Manual (AFM). If the FCOM data differs from the AFM data, the AFM remains the reference. As a supplement to the FCOM, the FCTM may provide additional information that the flight crew should read in conjunction with the FCOM. For more information, Refer to FCTM/GI FCTM Purpose. Ident.: GEN-GPURP-00020800.0001001 / 07 JUL 16
QUESTIONS AND SUGGESTIONS For any questions or comments related to this manual, the Operator’s Flight Operations Management can contact the Airbus Flight Operations Support and Training Standard department.
VIR A350 FLEET FCOM
←D
GEN P 18/48 15 MAR 20
GENERAL INFORMATION A350
FLIGHT CREW OPERATING MANUAL
FCOM CONTENTS Ident.: GEN-00020808.0001001 / 03 JAN 20 Applicable to: ALL 8
The FCOM has four sections: ‐ Aircraft Systems : This section is divided into ATA chapters for each aircraft system. This section includes a specific description of each system and its associated cockpit interfaces. When several layouts are possible for the same cockpit interface (e.g. when the position of the ON/OFF label of a switch changes depending on the aircraft configuration), the FCOM may describe only one typical layout. ‐ Procedures : This section contains the following chapters: ‐ Normal Procedures that include the SOPs and Supplementary Procedures ‐ Abnormal and Emergency Procedures ‐ Special Operations. L12‐ Limitations : This section provides the aircraft and system limitations that the flight crew must know or refer to in operations. This section is divided into aircraft and system-related limitations in a similar way to the ABNORMAL And EMERGENCY PROCEDURES section. ‐ Performance : This section includes the aircraft performance for each flight phase. L12
Note:
The Operators are responsible for customizing the structure and the content of their documentation at their convenience, in accordance to their fleet configuration and applicable local requirements.
In addition, the FCOM has the following chapters, as required: ‐ List of Modifications : The LOM provides a list of aircraft modifications, also referred to as (LOM) criteria (Modification Proposals (MPs) and Service Bulletins (SBs), that affect the FCOM. For more information, Refer to GEN FCOM Revision Management. L12‐ General Summary of : The General SOH chapter provides a list of all changes and Highlights (SOH) associated reasons of the FCOM revision. For more information, Refer to GEN FCOM Revision Management. L12
VIR A350 FLEET FCOM
E→
GEN P 19/48 15 MAR 20
GENERAL INFORMATION A350
FLIGHT CREW OPERATING MANUAL
‐
L12
‐
L12
‐
L12
Operations Engineering : Bulletins (OEBs)
The OEB chapter provides a list and description of all applicable Operations Engineering Bulletins (OEBs). For more information, Refer to OEB-000 Introduction.
Temporary Abnormal Behaviors
:
This section provides the list of all abnormal behaviors of the FCOM with a link to access the appropriate FCOM section. For more information, Refer to GEN TAB General Description
:
The TDU chapter provides a list of all applicable Temporary Documentary Units (TDUs). For more information, Refer to GEN TDU General Description.
Temporary Documentary Units (TDUs)
HOW CAN AN OPERATOR OBTAIN AN UPDATED FCOM? Ident.: GEN-00020936.0001001 / 13 MAY 14 Applicable to: ALL
Airbus provides the Operator/aircraft owner with a FCOM that corresponds to the aircraft configuration at delivery, and the necessary revisions further to any configuration change associated to Airbus-approved modifications. The Operator/owner must inform Airbus without delay of the effective changes to the aircraft delivery configuration made through Airbus Service Bulletin (SB). This permits Airbus to provide the Operator/owner with the FCOM revisions/updates. The Operator/owner must timely report any SB installation to the following address: e-mail : [email protected] Airbus will not provide revisions, and will not take responsibility for any effect on the FCOM: ‐ Due to modifications installed by third parties without an Airbus SB, and/or ‐ Due to modifications installed through an Airbus SB, if Airbus is not informed of the SB installation.
FCOM USE AND ORGANIZATION Applicable to: ALL Ident.: GEN-GUSEO-00020932.0001001 / 28 APR 14
DOCUMENTARY UNIT (DU) The FCOM is made of Documentary Units (DU). The DU is the smallest part of information with a technical content.
VIR A350 FLEET FCOM
← E to G →
GEN P 20/48 15 MAR 20
GENERAL INFORMATION A350
FLIGHT CREW OPERATING MANUAL
DU IDENTIFICATION STRIP The information is available in the OPS LIBRARY consultation toolbar by selecting the “DOC REF” option in the INFO drop down list. Once "DOC REF" is selected, above the title of the DU, the gray identification strip indicates for each DU: ‐ The DU identification (Id.). Each DU is identified by its unique identification number. ‐ The DU date. This date corresponds to the date at which the DU has been revised. ‐ The “Criteria” field that indicates the aircraft configuration to which the DU applies. Note:
XW stands for Xtra Widebody meaning that this DU is applicable to the A350 family.
‐ The "Applicable to" field that provides the list of the aircraft to which the DU applies. Note:
This field may indicate either MSN or aircraft registration number, depending on customization. When MSN is used, the field may display a range of values, for e.g. 0012-0220 that indicates all MSNs from MSN 0012 up to and including MSN 0220.
Ident.: GEN-GUSEO-00020843.0001001 / 28 APR 14
INFORMATION TYPES AND LAYERS The FCOM has technical information that may be used for: ‐ Flight crew operations in flight, or on ground ‐ Refresher training. Therefore, the FCOM is organized in three layers as follows: ‐ Layer 1: "Need to know" Layer 1 presents information that is necessary in the cockpit. ‐ Layer 2: "Nice to know" Layer 2 presents information that is used as a reference, in order to fully understand the logic of the aircraft and pilot interfaces. ‐ Layer 3: Detailed information. Layer 3 provides more detailed explanations, that are not necessarily needed in flight. The text in each layer appears on a different colored background. When the flight crew selects a layer of information, it remains selected during the consultation of several documentary units. Ident.: GEN-GUSEO-00020849.0001001 / 02 MAY 14
HOW TO USE THE FCOM For more information on the EFB "OPS LIBRARY" application that hosts the FCOM manual, Refer to DSC-46-OIS-20-80-70 OPS LIBRARY.
VIR A350 FLEET FCOM
←G→
GEN P 21/48 15 MAR 20
GENERAL INFORMATION A350
FLIGHT CREW OPERATING MANUAL Ident.: GEN-GUSEO-00020852.0001001 / 09 MAR 16
OPTIONAL EQUIPMENT The legend (If Installed) indicates that a paragraph or an illustration is applicable only if the related optional equipment is installed.
FCOM REVISION MANAGEMENT Applicable to: ALL Ident.: GEN-GREVM-00020882.0001001 / 18 JUN 15
FCOM REVISION CYCLE The FCOM revision adds, updates, or deletes information. The Operator determines the revision cycle. When necessary (e.g. need for urgent update), Airbus issues an immediate revision regardless of the revision cycle. FCOM ISSUE DATE An issue date identifies each FCOM revision. The issue date appears at the top of the Navigation Tree of the EFB OPS LIBRARY application. HIGHLIGHTS AND REVISION MARKS
L2 L1 L2 L1
A vertical bar in the margin of the DU identifies the modified part. The vertical bar is available in the OPS LIBRARY consultation toolbar by ticking the “REV MARKS” option in the INFO drop down list. For more information, Refer to DSC-46-OIS-20-80-70 INFO List. The user can display the associated reason of the change by clicking on the bar. If the change is significant, the reason for the change is in bold. The General Summary Of Highlights (General SOH) provides a list of all changes and associated reasons of the FCOM revision. FCOM REVISION CONTENTS Each FCOM revision contains the following information that is useful to update the FCOM and to identify the changes that the revision has inserted: ‐ The General SOH ‐ The List of Modifications (LOM).
VIR A350 FLEET FCOM
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GENERAL SUMMARY OF HIGHLIGHTS (GENERAL SOH) The General SOH chapter provides the list of all the changes inserted by a FCOM revision. For each change, the General SOH provides: ‐ A link to the applicable part of the manual affected by the change ‐ The technical reason for each revision. LIST OF MODIFICATIONS (LOM) The LOM provides a list of aircraft modifications, also referred to as criteria (Modification Proposals (MPs) and Service Bulletins (SBs), that affect the FCOM. The LOM also indicates: ‐ The title of the criteria ‐ The date of incorporation of the criteria in the FCOM ‐ The list of aircraft that have the criteria ‐ The “M” field that may indicate the following Evolution Code: • The “E” letter indicates an aircraft effectivity change for the criteria: The list of aircraft to which the criteria applies has changed compared to the previous FCOM revision, by addition or deletion of one or several aircraft • The “N” letter indicates new criteria added by this FCOM revision • The “R” letter indicates a change in the criteria title or associated SB. Ident.: GEN-GREVM-00020886.0001001 / 28 APR 14
OPERATIONS ENGINEERING BULLETINS
L2
Operations Engineering Bulletins (OEB) are issued when it is necessary to rapidly transmit technical and procedural information. The OEB chapter provides a list of all applicable OEBs. For more information, Refer to OEB-000 Introduction. DEFINITIONS
Ident.: GEN-00020887.0001001 / 04 JUN 18 Applicable to: ALL
CAUTION
:
Daylight operations
:
Extended overwater flight
:
VIR A350 FLEET FCOM
An operating procedure, technique, or information that may result in damage to equipment if not followed. Period between the beginning of the morning civil twilight and the end of the evening civil twilight relevant to the local aeronautical airspace, or such other period, as may be prescribed by the appropriate Authority. A flight where the aeroplane is operated over water at a distance away from land greater than 400 NM.
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Icing conditions
:
LAND ANSA
:
Icing conditions exist when OAT on the ground and for takeoff, or TAT in flight is 10 °C (50 °F) or below and visible moisture in any form is present (such as clouds, fog with visibility of 1 sm/1 600 m or less, rain, snow, sleet or ice crystals). Icing conditions also exist when the OAT on the ground and for takeoff is 10 °C (50 °F) or below when operating on ramps, taxiways, or runways where surface snow, ice, standing water or slush may be ingested by the engines or freeze on engines, nacelles or engine sensor probes. Land At Next Suitable Airport. Consider landing at the nearest suitable airport. Note:
LAND ASAP
:
Land As Soon As Possible. Land as soon as possible at the nearest airport at which a safe landing can be made. Note:
Note
:
VMC
:
WARNING
:
The suitability criteria should be defined in accordance with the Operator's policy.
LAND ASAP information is applicable to a time-critical situation.
An operating procedure, technique, or information that is considered essential to emphasize. Information contained in notes may also be safety related. Under IFR or VFR, the crew must maintain Visual Meteorological Conditions (VMC). An operating procedure, technique, or information that may result in personal injury or loss of life if not followed. TDU GENERAL DESCRIPTION
9 Ident.: GEN-00025364.0001001 / 03 JAN 20
Applicable to: ALL
A TDU in the FCOM informs the flight crew about a temporary change in a normal Standard Operation Procedure, Advisory or Limitations. The TDU contains the reason for change in order to better understand and memorize this temporary change.
VIR A350 FLEET FCOM
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The TDU contains several indications: ‐ The date of application of the new or revised content ‐ The reason for change explains why the section is updated with a short general description of the malfunction ‐ The yellow dash line indicates the affected documentary unit ‐ When applicable, the arrow link provides a link to the previous content. TAB GENERAL DESCRIPTION
10 Ident.: GEN-00025365.0001001 / 03 JAN 20
Applicable to: ALL
A TAB is a description of a system behavior that temporarily deviates from the intended system design and that the flight crew can notice. The TAB enables the flight crew to better recognize, understand and if applicable, react to the abnormal system behavior in order to avoid any undue operational delay. When applicable, temporary abnormal behaviors are described in the related section of the Aircraft System in a dedicated product folder identified as "Temporary Abnormal Behaviors". Each TAB contains a description of the malfunction with an alternative instruction called "Operational recommendation" (if applicable). ABBREVIATIONS Ident.: GEN-00000085.0001001 / 15 MAR 20 Applicable to: ALL
A Abbreviation AAL AAP A.FLOOR A/BRK A/C A/THR A623 ABSELV ABV ABN AC ACARS ACC
VIR A350 FLEET FCOM
Term Above Aerodrome Level Additional Attendant Panel Alpha Floor Autobrake Aircraft Autothrust ARINC 623 format for FANS A+ Alternate Brake Selector Valve Above Abnormal Alternating Current Aircraft Communication Addressing and Reporting System Active Clearance Control, Acceleration
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Abbreviation ACCEL ACCU ACD ACFT ACM ACMS ACP ACQ ACR ACS ADF ADGB ADHF ADIRS ADIRU ADK ADR ADS ADS-B ADS-C ADV AECM AES AESS AESU AFM AFS AGL A-ICE AICF AIP AIR COND ALL ENG FF ALD ALT ALT CRZ ALT CRZ* ALT CST ALT CST* ALT*
VIR A350 FLEET FCOM
Term Acceleration Accumulator Airworthiness Compliance Document Aircraft Air Cycle Machine Aircraft Condition Monitoring System Area Control Panel Acquisition Avionics Communication Router Air Conditioning System Automatic Direction Finder Active Differential GearBox Adaptive Droop Hinge Function Air Data/Inertial Reference System Air Data/Inertial Reference Unit Activate/Dialing Key Air Data Reference Automatic Dependent Surveillance Automatic Dependent Surveillance - Broadcast Automatic Dependent Surveillance - Contract Advisory Alternate Extension Control Module Automatic Extension System Aircraft Environment Surveillance System Aircraft Environment Surveillance Unit Airplane Flight Manual Automatic Flight System Above Ground Level Anti-Ice Anti-Ice Control Function Attendant Indication Panel, Aeronautical Information Publication Air Conditioning All Engines Fuel Flow Actual Landing Distance Altitude Altitude Hold of the Cruise Flight Level Altitude Capture of the Cruise Flight Level Altitude Constraint Hold Mode Altitude Constraint Capture Mode Altitude capture Mode
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Abbreviation ALTN AM AMI AMSL AMU ANF AOA AOC AP APPR APU ARINC ARP ARPT ARS ARV ASCU ASD ASDA A-SKID ASPSU ASV ATA ATC ATIS ATM ATN ATQC ATS ATT ATU AUTO AUTO BRK AVAIL AVNCS AZIM
VIR A350 FLEET FCOM
Term Alternate Amplitude Modulation Airline Modifiable Information Above Mean Sea Level Audio Management Unit Airport Navigation Function Angle-Of-Attack Airline Operational Control Autopilot Approach Auxiliary Power Unit Aeronautical Radio Incorporated Airport Reference Point Airport Auto Retraction System Alternate Refill Valves Air System Control Unit Accelerate Stop Distance Accelerate Stop Distance Available Antiskid Autonomous Standby Power Supply Unit Alternate Servo Valve Air Transport Association Air Traffic Control Automatic Terminal Information Services Air Traffic Management Aeronautical Telecommunications Network Airbus Temporary Quick Change Air Traffic Service Attitude Auto Transformer Unit Automatic Autobrake Available Avionics Azimuth
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B Abbreviation B/C BAC BARO BAS BAT BBAND BCF BCM BCS BFO BKUP BLK BOMU BLW BPS BRG BRK BRAKES CTL BRT BSF BTMS BTV
Term Back Course Back Course Barometric Bleed Air System Battery Broadband Brake Cooling Fans Backup Control Module Brake Control System Beat Frequency Oscillator Backup Block Bleed and Overheat Monitoring Unit Below Backup Power Supply Bearing Brake Brakes Control Bright, Brightness Backup Steering Function Brake Temperature Monitoring System Brake to Vacate
C Abbreviation C/B C/L CAB CAPT CAS CAT CAUT CBMF CCD CCRC CDA CDL CDLS CDM
VIR A350 FLEET FCOM
Term Circuit Breaker Checklist Cabin Captain Calibrated Air Speed Category, Clear Air Turbulence Caution Circuit Breaker Monitoring Function Cursor Control Device Cabin Crew Rest Compartment Continuous Descent Approach Configuration Deviation List Cockpit Door Locking System Coolant Distribution Module
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Abbreviation CDO CDS CDSS CF CG CI CIDS CINS CKPT CL CLB CLR CM CM1 CM2 CMS CMV CNS COM COND CONF CONFIG CP CPA CPCS CPDLC CPIOM CPNY CRC CRDC CRS CRZ CST CSAS CSTR CT CTL CTR TK CVMS CVR CWY
VIR A350 FLEET FCOM
Term Continuous Descent Operations Control and Display System Cockpit Door Surveillance System Cost of Fuel Center of Gravity Cost Index Cabin Intercommunication Data System Cabin Information Network System Cockpit Coefficient of Lift, Climb Detent on Thrust Levers Climb Clear Conversion Module Crewmember 1 (Left Seat) Crewmember 2 (Right Seat) Constant Mach Segment, Central Maintenance System Concentrator and Multiplexer for Video Communication Navigation and Surveillance Communication Conditioning Configuration Configuration Control Panel Closest Point of Approach Cabin Pressure Control System Controller/Pilot Datalink Communication Core Processing Input/Output Module Company Continuous Repetitive Chime Common Remote Data Concentrator Course Cruise Cabin Service Trainer Conditioned Service Air System Constraint Cost of Time Control Center Tank Cabin Video Monitoring System Cockpit Voice Recorder Clearway
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D Abbreviation DA D-ATIS DC DCLB DCT DD DDD DECEL DES DEST DEU DEV DFDR DFS DGPS DH DIR DIR TO DISA DIST DLCS DME DOC DSCS DTO DU
Term Decision Altitude Digital Automatic Terminal Information Services Direct Current Derated Climb Direct Day (entry format) Decompression Deceleration Device Decelerate, Deceleration Point Descend, Descent Destination Decoder/Encoder Unit Deviation Digital Flight Data Recorder Differential Flap Setting Differential Global Positioning System Decision Height Direction, Direct, Director Direct To Deviation from ISA law Distance Data Loading and Configuration System Distance Measuring Equipment Direct Operating Cost Doors and Slides Control System Derated Takeoff Display Unit, Documentary Unit
E Abbreviation EASA EBAS EBHA ECAM ECAS ECB ECON ECP ED EDP
VIR A350 FLEET FCOM
Term European Aviation Safety Agency Engine Bleed Air System Electrical Backup Hydraulic Actuator Electronic Centralized Aircraft Monitoring Emergency Crew Alerting System Electronic Control Box Economy ECAM Control Panel Engine Display Engine Driven Pump
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Abbreviation EEC EFB EFF EFIS EFOB EGPWS EGT EHA EHS EIF EIM EIU ELCO ELEC ELEVN ELMF ELT ELS ENMF EMER EMU ENG ENT EO EOSID EP EPCU EPDC EPDS EPSU EPU ERAI ERP ESC ESS ESSAI ETA ETACS ETOPS ETP
VIR A350 FLEET FCOM
Term Engine Electronic Controller Electronic Flight Bag Electronic Flight Folder Electronic Flight Instrument System Estimated Fuel On Board Enhanced Ground Proximity Warning System Exhaust Gas Temperature Electro-Hydrostatic Actuator Enhanced Surveillance Engine Interface Function Engine Interface Management Engine Interface Unit Exterior Light Controller Electrical Elevation Electrical Load Management Function Emergency Locator Transmitter Elementary Surveillance Electrical Network Management Function Emergency Engine Monitoring Unit Engine Entry Engine-Out Engine-Out Standard Instrument Departure End Point External Power Control Unit Electrical Power Distribution Center Electrical Power Distribution System Emergency Power Supply Unit Estimated Position Uncertainty Emergency Ram Air Inlet External Refuel Panel Escape Essential Engine Stator Anti-Ice Estimated Time of Arrival External and Taxiing Aid Camera System Extended Twin Engine Operation Equi-Time Point
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Abbreviation ETT ETRAC ETRAS EVAC EXT
Term Estimated Takeoff Time Electrical Thrust Reverser Actuation Controller Electrical Thrust Reverser Actuation System Evacuate External
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F Abbreviation F F/CTL F/O FAA FADEC FAF FANS FAP FAR FCDC FCOM FCRC FCTM FCU FD FDP FDRS FE FEP FF FG F-G/S F-G/S* FIN FL FLD FLEX F-LOC F-LOC* FLRS FLS FLT
VIR A350 FLEET FCOM
Term Minimum Flap Retract Speed Flight Controls First Officer Federal Aviation Administration Full Authority Digital Engine Control Final Approach Fix Future Air Navigation System Final Approach Point, Flight Attendant Panel, Forward Attendant Panel Federal Aviation Regulations Flight Control Data Concentrator Flight Crew Operating Manual Flight Crew Rest Compartment Flight Crew Techniques Manual Flight Control Unit, Fuel Control Unit Flight Director Final Descent Point Flight Data Recording System Flight Envelope Final End Point Fuel Flow Flight Guidance FLS Glide Slope, FLS Glide Slope Track Mode FLS Glide Slope Capture Mode Functional Identification Number Flight Level Factored Landing Distance Flexible FLS Localizer, FLS Localizer Track Mode FLS Localizer Capture Mode Flap Load Relief System FMS Landing System Flight Continued on the following page
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Abbreviation FLX FM FMA FMC FMS FMV FO FOB FOD FOHE FPA FPD FPF FPMF F-PLN FPMU FPS FPV FQI FQMS FREQ FSM FSOV FTIS FTO FU FWC FWD FWS FZFG
Term Flexible Flight Management, Frequency Modulation Flight Mode Annunciator Flight Management Computer Flight Management System Fuel Metering Valve Fully Open Fuel On Board Foreign Object Damage Fuel/Oil Heat Exchanger Flight Path Angle Flight Path Director Fire Protection Function Fuel Penalty Monitoring Function Flight Plan Fuel Properties Measurement Unit Fire Protection System Flight Path Vector Fuel Quantity Indication Fuel Quantity and Management System Frequency Flight System Message Fire Shut Off Valve Fuel Tank Inerting System Flexible Takeoff Fuel Used Flight Warning Computer Forward Flight Warning System Freezing Fog
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G Abbreviation G/S G/S* GA GBAS GCU GD GDOT
VIR A350 FLEET FCOM
Term Glide Slope Glide Slope Capture Mode Go-Around Ground Based Augmentation System Ground Control Unit, Generator Control Unit Green Dot Green Dot
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Abbreviation GEN GES GLA GLS GND GNSS GPS GPIRS GPRS GPWS GRVTY GS GSM GW GWCG
Term Generator Ground Earth Station Gust Load Alleviation GBAS Landing System Ground Global Navigation Satellite System Global Positioning System Global Positioning and Inertial Reference System General Packet Radio Service Ground Proximity Warning System Gravity Ground Speed, Ground Servicing Global System for Mobile communications Gross Weight Gross Weight Center of Gravity
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H Abbreviation HA HCU HCF HDG HF HGA HH HHX HI HM HMC HMCA HMCRF HMU HP HPA hPFD HPU HUD HYD
VIR A350 FLEET FCOM
Term Holding pattern to an Altitude termination Head-up Combiner Unit Heading Control Function Heading High Frequency, Holding pattern to a Fixed waypoint High Gain Antenna Hours (entry format) Hydraulic Heat Exchanger High Holding pattern with a Manual termination Hydraulic Monitoring and Control Hydraulic Monitoring and Control Application Hydraulic Monitoring and Control Remote Function Hydromechanical Unit High Pressure High Power Amplifier harmonized Primary Flight Display Head-up Projection Unit Head-Up Display Hydraulic
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I Abbreviation IAF IAS IATA ICAO IDENT IFE IFEC IFR IGGS IGN IGS IGV ILS IMA IMC IN-BND IN-FLT INFO INIT INOP INT INTCPT INV IP IPCU IR IRS ISA ISIS ITP
Term Initial Approach Fix Indicated Airspeed International Air Transport Association International Civil Aviation Organization Identification In-Flight Entertainment In-Flight Entertainment Center Instrument Flight Rules Inert Gas Generation System Ignition Instrument Guidance System Inlet Guide Vane Instrument Landing System Integrated Modular Avionics Instrument Meteorological Conditions Inbound In Flight Information Initialization Inoperative Interphone Intercept Inverter Intermediate Pressure Ice Protection Control Unit Inertial Reference Inertial Reference System International Standard Atmosphere Integrated Standby Instrument System In-Trail Procedure
J Abbreviation JAA JTSN
VIR A350 FLEET FCOM
Term Joint Aviation Authorities Jettison
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FLIGHT CREW OPERATING MANUAL
K Abbreviation KBD KCCU KOZ
Term Keyboard Keyboard and Cursor Control Unit Keep Out Zone
L Abbreviation L L/G L/G CTL LAF LAND LAT LAV LCD LCTR LD LDA LDEV LDG LGCIS LGERS LGMS LH LIM LL LNAV LO LOC LOC B/C LOC B/C* LOC* LOM LONG LP LPV LRC LS LSK LT
VIR A350 FLEET FCOM
Term Left Landing Gear Landing Gear Control Load Alleviation Function Landing Latitude, Lateral Lavatory Liquid Crystal Display Locator Landing Distance Landing Distance Available, LOC type Directional Aid Lateral Deviation Landing Landing Gear Control Indication System Landing Gear Extension and Retraction System Landing Gear Monitoring System Left Hand Limit, Limitation Latitude/Longitude Lateral Navigation Low Localizer, Localizer Track Mode Localizer Back Course Track Mode Localizer Back Course Capture Mode Localizer Capture Mode List Of Modifications Longitude Localizer Performance, Low Pressure Localizer Performance with Vertical Guidance Long Range Cruise Landing System Line Selection Key Light
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Abbreviation LVR LW
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Term Lever Landing Weight
M Abbreviation MAG MAN MAINT MAP MAX MCL MCT MD MDA MDH MEA MEL MEM MFD MFP MIN MKR MLA MLE MLG MLO MLW MM MMEL MMM MMO MMR MP MORA MRA MRP MSA MSG MSL MSN
VIR A350 FLEET FCOM
Term Magnetic Manual Maintenance Missed Approach Point Maximum Maximum Climb Thrust Maximum Continuous Thrust Maximum Dive Speed Minimum Descent Altitude Minimum Descent Height Minimum En Route Altitude Minimum Equipment List Memory Items Multifunction Display Multifunction Probe Minimum Marker beacon Maneuver Load Alleviation Maximum Landing Gear Extended Mach Main Landing Gear Maximum Landing Gear Operating Mach Maximum Landing Weight Middle Marker, Minutes (entry format) Master Minimum Equipment List Month (entry format) Maximum Operating Mach Multi-Mode Receiver Modification Proposal Minimum Off Route Altitude Recommended Turbulence Penetration Mach Map Reference Point Minimum Safe Altitude Message Mean Sea Level Manufacturer Serial Number
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Abbreviation MTOW MTW MZFW
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Term Maximum Takeoff Weight Maximum Taxi Weight Maximum Zero Fuel Weight
N Abbreviation N N/A N1 N2 N3 NADP NAI NAV NAVAID NAVAIDS NBPT NBSELV ND NDB NEA NIV NLG NORM NOTAM NPA NSV NWS NWSSV
Term North, Rotor Speed Not Applicable Engine Low Pressure Rotor Speed Engine Intermediate Pressure Rotor Speed Engine High Pressure Rotor Speed Noise Abatement Departure Procedure Nacelle Anti-Ice Navigation Navigation Aid Navigation Aids No Break Power Transfer Normal Brake Selector Valve Navigation Display Non-Directional Beacon Nitrogen Enriched Air Nose Isolation Valve Nose Landing Gear Normal Notice To Airmen Non Precision Approach Normal Servo Valve Nose Wheel Steering Nose Wheel Steering Servo Valve
O Abbreviation OAT OCED OCU OEB OEI OFV OHDS OIS
VIR A350 FLEET FCOM
Term Outside Air Temperature Operator-Customized ECAM Database Outflow valve Control Unit Operations Engineering Bulletin One Engine Inoperative Outflow Valve OverHeat Detection System Onboard Information System
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Abbreviation OLB OMS OMTS OOOI OP OPC OP CLB OPS OPT OPU OSCM OUT-BND OVHT OVRD OXY
Term OPS Library Browser Onboard Maintenance System On-Board Mobile Telephony System Out-Off-On-In Open Operational Program Configuration Open Climb Operations Optimum Overvoltage Protection Unit Oxygen System Control and Monitoring Outbound Overheat Override Oxygen
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P Abbreviation P.POS PA PARK PAX pb PB PBCS PBD PBE PBN PBSELV PCS PD PDF PDHV PDLS PDMF PDT PED PERF PF PFC
VIR A350 FLEET FCOM
Term Present Position Passenger Address, Pressure Altitude Parking Passenger Pushbutton Place/Bearing, Pushbutton Performance-Based Communication and Surveillance Place/Bearing/Distance Protective Breathing Equipment Performance-Based Navigation Parking Brake Selector Valve Propulsion Control System Place/Distance Portable Document Format Pack Discharge Heating Valve Privacy Door Lock System Power Distribution Maintenance Function Probe Dual Temperature Portable Electronic Device Performance Pilot Flying Porous Friction Course
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Abbreviation PFD PFQ PFTU PLS PM PMG PMP POB POS PPOS PRED PRED W/S PRESS PREV PRIM PRM PROC PRSOV PSI PTT PURS PWR PWS
Term Primary Flight Display Preselected Fuel Quantity Pedal Feel and Trim Unit Primary Locking System Pilot Monitoring Permanent Magnet Generator Pump Power-Off Brake Position Present Position Prediction Predictive Windshear Pressurization Previous Primary Flight Control and Guidance Computer Precision Runway Monitor Procedure Pressure Regulating and Shut Off Valve Pound per Square Inch Push-To-Talk Purser Power Predictive Windshear
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Q Abbreviation QFE QFU QNH QRH QTY 11
Term Field Elevation Atmospheric Pressure Runway Heading Sea Level Atmospheric Pressure Quick Reference Handbook Quantity
R Abbreviation R RA RAD RAM RAT RCAM
VIR A350 FLEET FCOM
Term Right Radio Altimeter, Resolution Advisory Radio Random Access Memory Ram Air Turbine Runway Condition Assessment Matrix
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Abbreviation RBCU RCCB RCDR RCL RCO RCP REACT REC RED REF REG REGUL REV RF RFCF RGAU RH RLA RLD RMP RNAV RNG RNP RNP AR RNV ROC ROD ROP ROT ROW RPTG RSP RST RSV RSVR RTA RTE RTO RTU RVR
VIR A350 FLEET FCOM
Term Remote Braking Control Unit Remote Control Circuit Breaker Recorder Recall Remote Communications Outlet Required Communication Performance Rain Echo Attenuation Compensation Technique Recommended Reduction Reference Registration Regulation Revise, Revision, Reverse Radius to Fix Runway Field Clearance Floor Rate Gyrometer and Accelerometer Unit Right Hand Roll Load Alleviation Required Landing Distance Radio Management Panel Area Navigation Range Required Navigation Performance Required Navigation Performance with Authorization Required Area Navigation Rate of Climb Rate of Descent Runway Overrun Protection Runway Occupancy Time Runway end Overrun Warning Reporting Required Surveillance Performance Reset Reserve Reservoir Required Time of Arrival Route Rejected Takeoff Radar Transceiver Unit Runway Visual Range
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Abbreviation RVSM RWY RWY TRK
Term Reduced Vertical Separation Minimum Runway, Runway Mode Runway Track Mode
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S Abbreviation S S/C S/D S/G SACU SAOHE SAT SATCOM SB SBAS SC SCI SCS SD SDF SDU SDP SDS SEC SEL SELCAL SEP SFCC SFD SG SGCU SGS SHED SID SLS SMI SND SOH SOP
VIR A350 FLEET FCOM
Term Minimum Slat Retract Speed, South Step Climb Step Descent Starter Generator Semi-Automatic Control Unit Surface Air/Oil Heat Exchanger Static Air Temperature Satellite Communication Service Bulletin Satellite Based Augmentation System Single Chime Secure Communication Interface Supplemental Cooling System System Display Smoke Detection Function, Simplified Directional Facility Satellite Data Unit Steering Disconnect Panel Smoke Detection System Secondary Flight Control Computer, Secondary Flight Plan Select Selective Calling OM(B) SEP Manual Slat Flap Control Computer Standby Flight Display Starter Generator Starter Generator Control Unit Starter Generator System Shedding Standard Instrument Departure Satellite Landing System Stall Margin Indicator Standby Navigation Display Summary Of Highlights Standard Operating Procedure
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Abbreviation SP SPD SPDLIM SPLR SPU SQWK SR SRS SS SSA SSB SSPC STAR STAT STBY STD STEER STS SURV SVCE SWY SYS 12
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Term Space Speed Speed Limit Spoiler Starter Power Unit Squawk Specific Range Speed Reference System Seconds (entry format), Sky/Shading Sideslip Angle Single Side Band Solid State Power Controller Standard Terminal Arrival Route Static Standby Standard Steering Status Surveillance Service Stopway System
T Abbreviation T-P T.O T.WIND T/C T/D TA TAB TAC TACAN TAD TAS TASOV TAT TAU TAV
VIR A350 FLEET FCOM
Term Turning Point Takeoff True Wind Top of Climb Top of Descent, Touchdown Traffic Advisory Temporary Abnormal Behavior Taxiing Aid Camera Tactical Air Navigation Terrain Awareness and Display True Airspeed Trim Air Shut-Off Valves Total Air Temperature Estimated Time to Intercept Trim Air Valve
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Abbreviation TAWS TCAS TCF TCH TCV TDU TEL TEMP TERML TERR TFLEX THR THS TK TMAX TMPY TO TOC TOCG TOD TODA TOGA TOM TOR TORA TOS TOW TPIS TR TRAJ TRANS TREF TRK TROPO TRU TURB TWDC
VIR A350 FLEET FCOM
Term Terrain Awareness and Warning System Traffic Alert and Collision Avoidance System Terrain Clearance Floor Threshold Crossing Height Temperature Control Valve Temporary Documentary Unit Telephone Temperature Terminal Terrain Flex Temperature Thrust Trimmable Horizontal Stabilizer Tank Maximum Temperature Temporary Takeoff Top Of Climb TakeOff Center of Gravity Takeoff Distance, Top Of Descent Takeoff Distance Available Takeoff/Go-Around Takeoff Monitoring Takeoff Run Takeoff Run Available Takeoff Surveillance Takeoff Weight Tire Pressure Indicating System Transformer Rectifier Trajectory Transition Reference Temperature, Flat-Rating Temperature Track Tropopause Transformer Rectifier Unit Turbulence Tank Wall Data Concentrator
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U Abbreviation UERF USB UTC
Term Uncontained Engine Rotor Failure Universal Serial Bus Universal Time Coordinated
V Abbreviation V/S V1 V2 VA VAPP VBV VCRU VCS VD VDEV VENT VERT VERT REV VFE VFG VFR VHF VIGV VLE VLO VLOF VLS VLV VMAX VMC VMCA VMCG VMCL VMO VMU VNAV VOR VORTAC
VIR A350 FLEET FCOM
Term Vertical Speed Decision Speed, Critical Engine Failure Speed Takeoff Safety Speed Maximum Design Maneuvering Speed Approach Speed Variable Bleed Valve Vapor Cycle Refrigeration Unit Ventilation Control System Vertical Display, Maximum Dive Speed Vertical Deviation Ventilation Vertical Vertical Revisor Maximum Flap Extended Speed Variable Frequency Generator Visual Flight Rules Very High Frequency Variable Inlet Guide Valve Maximum Landing Gear Extended Speed Maximum Landing Gear Operating Speed Liftoff Speed Lowest Selectable Speed Valve Maximum Allowable Speed Visual Meteorological Conditions Minimum Control Airspeed in Flight / Minimum Control Airspeed in the Air Minimum Control Airspeed on Ground Minimum Control Airspeed for Landing Maximum Operating Speed Minimum Unstick Speed Vertical Navigation VHF Omnidirectional Range Co-Located VOR and TACAN Continued on the following page
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Abbreviation VR VRA VREF VSA VS1G VSMIN VSV VV VQAR
Term Rotation Speed Recommended Turbulence Penetration Speed Landing Reference Speed Visual Separation Approach Stall Speed with a Load Factor of 1 g Reference Stall Speed Variable Stator Vanes Velocity Vector Virtual Quick Access Recorder
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W Abbreviation WACS WADU WARN WBM WBBC WD WGS WHC Wi-Fi WIPS WPT WSCS WTB WX WXR WV
Term Wireless Airport Communication System Weather Antenna Drive Unit Warning Weight and Balance Manual Weight and Balance Backup Computer Warning Display World Geodetic System Window Heating Computer Wireless Fidelity Wing Ice Protection System Waypoint Wheel Steering Control System Wing Tip Brake Weather Mode Weather Radar Weight Variant
X Abbreviation XCHECK XFR XLS XPDR XTK
VIR A350 FLEET FCOM
Term Cross Check Transfer x Landing System (e.g. ILS, GLS, ...) Transponder Cross Track
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Y Abbreviation YYYY
Term Year (entry format)
Z Abbreviation ZFCG ZFW ZFWCG
VIR A350 FLEET FCOM
Term Zero Fuel Center of Gravity Zero Fuel Weight Zero Fuel Weight Center of Gravity
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TABLE OF CONTENTS
DSC-20 20 - Aircraft General DSC-21-COND 21 - Air Conditioning DSC-21-VENT 21 - Ventilation DSC-21-PRESS 21 - Pressurization DSC-22-27 22-27 - Flight Envelope DSC-22-INT 22 - AFS - Introduction DSC-22-FG 22 - AFS - Flight Guidance DSC-22-FMS 22 - AFS - Flight Management System DSC-23 23 - Communication DSC-24 24 - Electrical System DSC-25 25 - Equipment DSC-26 26 - Fire and Smoke Protection DSC-27 27 - Flight Controls 1
DSC-28 28 - Fuel DSC-29 29 - Hydraulic System DSC-30 30 - Ice and Rain Protection DSC-31-CDS 31 - Control and Display System DSC-31-REC 31 - Recorders DSC-32 32 - Landing Gear DSC-33 33 - Lights
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DSC-34-NAV 34 - Navigation
Continued from the previous page
DSC-34-SURV 34 - Surveillance DSC-34-32 34-32 - ROW/ROP - BTV DSC-35 35 - Oxygen DSC-36 36 - Bleed Air DSC-38 38 - Water/Waste DSC-42 42 - Avionics Network - IMA DSC-44 44 - Cabin Systems DSC-46-ATC 46 - Air Traffic Control Datalink System DSC-46-OIS 46 - Onboard Information System DSC-49 49 - Auxiliary Power Unit DSC-52 52 - Doors DSC-56 56 - Cockpit Windows DSC-70 70 - Engines
VIR A350 FLEET FCOM
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SUMMARY OF HIGHLIGHTS
FLIGHT CREW OPERATING MANUAL
Localization Title
DSC-PLP-TOC 28 - Fuel
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Toc Index
ID 1
Reason Documentation update: Deletion of the "PP04719 Temporary Abnormal Behaviors" table of content entry. Documentation update: Deletion of the "00025074.0001001 Erroneous Variations of FQI and FOB" documentary unit.
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Localization
LIST OF EFFECTIVE TEMPORARY DOCUMENTARY UNITS DU Title
DU identification
DU date
DSC-22-FMS-20-20- PERF Page PG00505 20 DSC-22-FMS-20-20- OPT 00024902.0001001 29 JAN 19 20 Criteria: XW Applicable to: ALL Impacted DU: 00004085 OPT Reason for issue: In certain conditions, the OPT FL is indicated as XXX. The next FMS standard S6 will correct this issue.
(1) Evolution code : N=New, R=Revised, E=Effectivity
VIR A350 FLEET FCOM
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DSC-20-10 Overview
Overview.................................................................................................................................................................. A Engines.................................................................................................................................................................... B Cockpit..................................................................................................................................................................... C Cabin........................................................................................................................................................................D Cargo........................................................................................................................................................................E Crew Rest Compartment......................................................................................................................................... F A350 FLEET SPECIFICS........................................................................................................................................G
DSC-20-20 Description DSC-20-20-10 Main Dimensions
Main Dimensions..................................................................................................................................................... A Fuselage...................................................................................................................................................................B Wing......................................................................................................................................................................... C Tail........................................................................................................................................................................... D
DSC-20-20-20 Antenna Locations
Antenna Locations................................................................................................................................................... A
DSC-20-20-30 Unpressurized Areas
Unpressurized Areas............................................................................................................................................... A
DSC-20-20-40 Ground Clearance Diagram
Ground Clearance Diagram.....................................................................................................................................A
DSC-20-20-50 Landing Geometry
Landing Geometry................................................................................................................................................... A
DSC-20-20-60 Visual Ground Geometry
Taxi - Visual Ground Geometry.............................................................................................................................. A
DSC-20-30 Ground Handling
Taxiing......................................................................................................................................................................A 180 degrees Turn on Runway.................................................................................................................................B
VIR A350 FLEET FCOM
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Localization Title
DSC-20-10 A350 FLEET SPECIFICS
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Toc Index G
ID 1
Reason RETO procedures now approved.
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AIRCRAFT SYSTEMS 20 - AIRCRAFT GENERAL A350
OVERVIEW
FLIGHT CREW OPERATING MANUAL
OVERVIEW Ident.: DSC-20-10-00000001.0001001 / 24 APR 14 Applicable to: ALL
The Airbus A350 is a subsonic, medium to long range aircraft designed for commercial transportation of passengers and cargo. ENGINES Ident.: DSC-20-10-00016612.0001001 / 24 APR 14 Applicable to: ALL
The aircraft has two high bypass turbofan engines, mounted under the wings. COCKPIT Ident.: DSC-20-10-00000088.0001001 / 24 APR 14 Applicable to: ALL
The cockpit has: ‐ One seat for the captain ‐ One seat for the first officer ‐ Two additional seats for the observers. CABIN Ident.: DSC-20-10-00000095.0001001 / 01 MAR 17 Applicable to: ALL
The passenger seating layout may vary, depending on Operator requirements. CARGO Ident.: DSC-20-10-00000096.0001001 / 24 APR 14 Applicable to: ALL
The aircraft has three cargo compartments: ‐ Forward cargo compartment ‐ Aft cargo compartment ‐ Bulk cargo compartment.
VIR A350 FLEET FCOM
A to E
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OVERVIEW
FLIGHT CREW OPERATING MANUAL
CREW REST COMPARTMENT Ident.: DSC-20-10-00000097.0002001 / 14 JUN 16 Applicable to: ALL
The aircraft can have two crew rest compartments: ‐ A Flight Crew Rest Compartment for the flight crew members ‐ A Cabin Crew Rest Compartment for the cabin crew members. Both types of crew rest compartments are installed in the overhead area with access from the main deck. Note:
These crew rest compartments may not correspond to the customized configuration of a specific aircraft. For more information on the installed equipment, refer to the relevant chapter's system description. A350 FLEET SPECIFICS
Ident.: DSC-20-10-21400149.9001001 / 15 MAR 20 Applicable to: ALL
LIMITATIONS For Weight, Refer to AFM/LIM-WGHT Weight Limitations AND the placard located on the Centre Pedestal. Note:
In the event of a discrepancy, contact OCC; the placard is the controlling data source.
For Usable Fuel, Refer to AFM/LIM-28 Usable Fuel For Take-Off Tailwind, Refer to AFM/LIM-OPS Tailwind for Takeoff For Landing Tailwind, Refer to AFM/LIM-OPS Tailwind for Landing For Crosswind, Refer to AFM/LIM-70 Crosswind 1
CONSIDERATIONS TAXI ‐ RETO procedure approved TAKE OFF ‐ Initial thrust setting: 25% ‐ Initial target pitch for normal and engine out: 12.5 deg/ 10 deg CRUISE/DESCENT/APPROACH/LANDING ‐ OXY duration 22 minutes; ‐ DEFAULT Autobrake - use BTV ‐ DEFAULT THRUST REVERSE VIR A350 FLEET FCOM
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AIRCRAFT SYSTEMS 20 - AIRCRAFT GENERAL A350
OVERVIEW
FLIGHT CREW OPERATING MANUAL
DRY WET
: :
CONTAM :
IDLE IDLE Subject to landing performance SOPs. (Refer to PRO-NOR-SOP-160 Descent Preparation - Landing Performance) MAX
AFTER LANDING ‐ RETI cooling time: 5 minutes ‐ Cooling time commences: ‐ IDLE REV used: Touchdown ‐ MAX REV used: After reverse has been cancelled
VIR A350 FLEET FCOM
←G
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OVERVIEW
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DESCRIPTION - MAIN DIMENSIONS
MAIN DIMENSIONS Ident.: DSC-20-20-10-00000098.0001001 / 03 NOV 16 Applicable to: ALL
Front View
VIR A350 FLEET FCOM
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FLIGHT CREW OPERATING MANUAL
DESCRIPTION - MAIN DIMENSIONS
Side View (Typical)
VIR A350 FLEET FCOM
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DESCRIPTION - MAIN DIMENSIONS
FLIGHT CREW OPERATING MANUAL
Top View
A B C D E F G H I
VIR A350 FLEET FCOM
A350-900 10.60 m (34 ft 9 in) 0.75 m (2 ft 5.5 in) 66.61 m (218 ft 6 in) 17.05 m (55 ft 11 in) 28.66 m (94 ft ) 65.26 m (214 ft 1 in)
←A
64.75 m (212 ft 5 in) 18.79 m (61 ft 8 in)
10.5 m (34 ft 5 in)
A350-1000 10.73 m (35 ft 2 in) 0.78 m (2 ft 6.7 in) 75.59 m (248 ft ) 17.08 m (56 ft ) 32.48 m (106 ft 7 in) 72.25 m (237 ft )
DSC-20-20-10 P 3/6 01 JUL 19
AIRCRAFT SYSTEMS 20 - AIRCRAFT GENERAL A350
FLIGHT CREW OPERATING MANUAL
DESCRIPTION - MAIN DIMENSIONS
FUSELAGE Ident.: DSC-20-20-10-00000099.0001001 / 24 APR 14 Applicable to: ALL
The aircraft fuselage has: ‐ In the cabin : 8 passengers doors ‐ In the cargo compartments: 3 cargo doors (forward, aft and bulk cargo doors). The cabin can have up to 10 seats abreast in each row. WING Ident.: DSC-20-20-10-00000513.0001001 / 24 APR 14 Applicable to: ALL L2
L1
The wing has two engine pylons. It has an area of 432.1 m² (4 652 ft²) and spans 64.75 m (212.44 ft) with winglet (59 m (194 ft) without winglet). Each half-wing has the following moving surfaces: ‐ Two ailerons ‐ Seven upper wing control surfaces that are used in various combinations as spoilers, air brakes, or lift dumpers ‐ Seven slat surfaces for high-lift configurations ‐ Two flap surfaces for high-lift configurations. The wing is also used as a fuel tank. TAIL
Ident.: DSC-20-20-10-00000515.0001001 / 04 DEC 14 Applicable to: ALL
VERTICAL STABILIZER The vertical stabilizer has one rudder.
VIR A350 FLEET FCOM
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AIRCRAFT SYSTEMS 20 - AIRCRAFT GENERAL A350
DESCRIPTION - MAIN DIMENSIONS
FLIGHT CREW OPERATING MANUAL
Vertical Stabilizer
HORIZONTAL STABILIZER The horizontal stabilizer has two elevators.
Horizontal Stabilizer
VIR A350 FLEET FCOM
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AIRCRAFT SYSTEMS 20 - AIRCRAFT GENERAL A350
FLIGHT CREW OPERATING MANUAL L2
DESCRIPTION - MAIN DIMENSIONS
DIMENSIONS Vertical Stabilizer Area 51.0 m² 548.9 ft²
VIR A350 FLEET FCOM
Horizontal Stabilizer Area 81.5 m² 877.2 ft²
←D
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AIRCRAFT SYSTEMS 20 - AIRCRAFT GENERAL A350
DESCRIPTION - ANTENNA LOCATIONS
FLIGHT CREW OPERATING MANUAL
ANTENNA LOCATIONS Ident.: DSC-20-20-20-00016209.0001001 / 24 APR 14 Applicable to: ALL
Antenna Locations
VIR A350 FLEET FCOM
A
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DESCRIPTION - ANTENNA LOCATIONS
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AIRCRAFT SYSTEMS 20 - AIRCRAFT GENERAL A350
DESCRIPTION - UNPRESSURIZED AREAS
FLIGHT CREW OPERATING MANUAL
UNPRESSURIZED AREAS Ident.: DSC-20-20-30-00016210.0001001 / 24 APR 14 Applicable to: ALL
Unpressurized Areas
VIR A350 FLEET FCOM
A
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DESCRIPTION - UNPRESSURIZED AREAS
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VIR A350 FLEET FCOM
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AIRCRAFT SYSTEMS 20 - AIRCRAFT GENERAL A350
DESCRIPTION - GROUND CLEARANCE DIAGRAM
FLIGHT CREW OPERATING MANUAL
GROUND CLEARANCE DIAGRAM Ident.: DSC-20-20-40-00020996.0001001 / 08 JUL 19 Applicable to: ALL
A350-900 Ground Clearance Diagram
VIR A350 FLEET FCOM
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FLIGHT CREW OPERATING MANUAL
DESCRIPTION - GROUND CLEARANCE DIAGRAM
A350-1000
VIR A350 FLEET FCOM
←A
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AIRCRAFT SYSTEMS 20 - AIRCRAFT GENERAL A350
DESCRIPTION - LANDING GEOMETRY
FLIGHT CREW OPERATING MANUAL
LANDING GEOMETRY Ident.: DSC-20-20-50-00023854.0001001 / 27 OCT 17 Applicable to: ALL
The table below is based on the following conditions: ‐ Glide path 3 ° ‐ CONF FULL ‐ MLW ‐ No wind ‐ The glide antenna crosses the runway threshold at 50 ft ‐ The Glide-to-Wheel Height is computed at the runway threshold ‐ The Eye-to-Wheel Height is computed during approach.
A350-900 A350-1000
VIR A350 FLEET FCOM
Glide-to-Wheel Height m ft 40 PSI ..................................................................................................... CHECK The recommended starter air supply pressure is 25 PSI, when the start valve is open. SOP — BEFORE START CLEARANCE............................................................................ RESUME
Ident.: PRO-NOR-SUP-SUP-ENG-B-00021220.0001001 / 04 APR 17
ENGINE START CAUTION
L2
L1
During engine start, if a bleed leak is detected, the air start unit must be disconnected only after the engine start sequence is completed or stopped.
Due to engine start on batteries, the engine vibrations indications are displayed XX on the ENG SD page. The Engine Monitoring Unit (EMU) is not electrically supplied on batteries, consequently the engines vibrations indications are not displayed on the ENG SD page. SOP — ENGINE START..................................................................................................PERFORM
Ident.: PRO-NOR-SUP-SUP-ENG-B-00021221.0001001 / 09 JUL 15
AFTER START AIR START UNIT DISC.................................................................................................... REQUEST XBLEED SEL............................................................................................................................ AUTO VIR A350 FLEET FCOM
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PROCEDURES NORMAL PROCEDURES A350
SUPPLEMENTARY PROCEDURES - ENGINE
FLIGHT CREW OPERATING MANUAL
ENG 1 BLEED...............................................................................................................................ON ENG 2 BLEED...............................................................................................................................ON PACK 1+2......................................................................................................................................ON SOP — AFTER START...................................................................................................... RESUME
ENGINE START WITH EXTERNAL ELECTRICAL POWER Applicable to: ALL Ident.: PRO-NOR-SUP-SUP-ENG-C-00021103.0001001 / 09 JUL 15
BEFORE START CLEARANCE EXTERNAL POWER : EXT 1 P/B................................................................................................................. CHECK ON EXT 2 P/B (IF USED) .............................................................................................. CHECK ON SOP — BEFORE START CLEARANCE......................................................................RESUME Ident.: PRO-NOR-SUP-SUP-ENG-C-00021326.0001001 / 28 APR 17
ENGINE START ENGINE 1 START............................................................................................................ PERFORM L2 L1
Note:
For any operational reason, engine 2 can be started first.
WARNING
Disconnection of the external power with the EXT PWR pb-sw ON may cause injury to the ground engineer. Request disconnection of the external power only with the EXT PWR pb-sw AVAIL.
EXT 1 P/B.................................................................................................................. CHECK AVAIL EXT 2 P/B (IF USED) ............................................................................................... CHECK AVAIL EXT PWR DISC................................................................................................................ REQUEST ENGINE 2 START............................................................................................................ PERFORM
ENGINE START WITH AN AIR START UNIT Applicable to: ALL Ident.: PRO-NOR-SUP-SUP-ENG-D-00006911.0001001 / 09 JUL 15
BEFORE START CLEARANCE L2
PACK 1+2.................................................................................................................................... OFF Packs are selected off to prevent any possible contamination of the packs by the air start unit.
VIR A350 FLEET FCOM
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PROCEDURES NORMAL PROCEDURES A350
FLIGHT CREW OPERATING MANUAL L1 L2
L1 L2
L1
L2
L1 L2 L1
SUPPLEMENTARY PROCEDURES - ENGINE
APU BLEED.................................................................................................................................OFF The APU BLEED pb-sw is set to OFF to prevent multiple bleed sources that may result in adverse effect on the bleed system. ENG 1 BLEED............................................................................................................................. OFF Simultaneous use of external pneumatic power and the engine bleed is prohibited to prevent any adverse effect on the bleed system. ENG 2 BLEED............................................................................................................................. OFF XBLEED SEL............................................................................................................................ OPEN AIR START UNIT CONNECTION..................................................................................... REQUEST Two ground air start units may be used in parallel, if the pressure/flow relation is expected to be marginal. BLEED PRESS > 40 PSI ..................................................................................................... CHECK The recommended starter air supply pressure is 25 PSI, when the start valve is open. EXT 1 P/B (IF USED) .....................................................................................................CHECK ON EXT 2 P/B (IF USED) .....................................................................................................CHECK ON SOP — BEFORE START CLEARANCE............................................................................ RESUME
Ident.: PRO-NOR-SUP-SUP-ENG-D-00021224.0001001 / 13 MAR 19
ENGINE START CAUTION
During engine start, if a bleed leak is detected, the air start unit must be disconnected only after the engine start sequence is completed or stopped.
ENGINE 1 START............................................................................................................ PERFORM L2
Note:
For any operational reason, engine 2 can be started first.
L1
If the XBLEED ENGINE START procedure is intended for the 2nd engine start: Before second engine start: CAUTION
L2
L1 L2
The simultaneous use of engine bleed supply and air start unit is prohibited.
AIR START UNIT DISC ...................................................................................... REQUEST Simultaneous use of air start unit and the engine bleed is prohibited to prevent any adverse effect on the bleed system. PACK 1+2.........................................................................................................................ON When both packs are set to ON, engine IDLE power is higher and appropriate for a crossbleed engine start.
VIR A350 FLEET FCOM
←D→
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PROCEDURES NORMAL PROCEDURES A350
FLIGHT CREW OPERATING MANUAL L1 L2
L1
SUPPLEMENTARY PROCEDURES - ENGINE
APU BLEED......................................................................................................CHECK OFF The APU BLEED pb-sw is set to OFF to prevent multiple bleed sources that may result in adverse effect on the bleed system. ENG BLEED (ENG STARTED)........................................................................................ON ENG BLEED (ENG NOT STARTED)...............................................................................ON XBLEED SEL................................................................................................. CHECK OPEN SECOND ENGINE START............................................................................................... PERFORM
Ident.: PRO-NOR-SUP-SUP-ENG-D-00021225.0001001 / 03 JAN 20 2
AFTER START ENG THRUST LEVER (LAST ENG STARTED) : KEEP IDLE FOR 1 MIN If an air start unit was used to start the second engine: AIR START UNIT DISC..............................................................................................REQUEST XBLEED SEL......................................................................................................................AUTO ENG 1 BLEED........................................................................................................................ ON ENG 2 BLEED........................................................................................................................ ON PACK 1+2............................................................................................................................... ON If the XBLEED ENGINE START procedure was used to start the second engine: XBLEED SEL......................................................................................................................AUTO WARNING
Disconnection of the external power with the EXT PWR pb-sw ON may cause injury to the ground engineer. Request disconnection of the external power only with the EXT PWR pb-sw AVAIL.
EXT 1 P/B (IF USED) ................................................................................................CHECK AVAIL EXT 2 P/B (IF USED) ............................................................................................... CHECK AVAIL EXT PWR DISC (IF USED) ............................................................................................. REQUEST SOP — AFTER START...................................................................................................... RESUME MANUAL ENGINE START Ident.: PRO-NOR-SUP-SUP-ENG-00016287.0001001 / 01 OCT 15 Applicable to: ALL
ENGINE START THR LEVERS........................................................................................................ IDLE CAUTION
VIR A350 FLEET FCOM
PF
The engines start regardless of the thrust lever position. If the thrust levers are not set to IDLE, the thrust rapidly increases to the corresponding thrust lever position, causing a hazardous situation.
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PROCEDURES NORMAL PROCEDURES A350
FLIGHT CREW OPERATING MANUAL
L2
L1
SUPPLEMENTARY PROCEDURES - ENGINE
ENG START SEL.....................................................................................NORM THEN IGN START The ENG SD page appears, and all pack valves close. Note:
The pack valves open again if the ENG MAN START pb-sw is not set to ON within 30 s.
Note:
During a manual engine start, the FADEC has limited control and does not aborts an abnormal manual start, except in the case of rotor overspeed. Therefore, if the flight crew suspects an engine start malfunction, or if an engine-related ECAM alert is triggered, the PF must interrupt the manual start sequence and perform one of the following: ‐ Before the PF sets the ENG MASTER lever to ON, the PF must set the ENG MAN START pb-sw to OFF, or ‐ After the PF sets the ENG MASTER lever to ON, the PF must set the ENG MASTER lever to OFF. Then, the PF must announce "ECAM actions", in accordance with the ECAM management philosophy. Before the flight crew performs another manual engine start, they should consider a dry cranking of the affected engine, if dry cranking is not part of the ECAM procedure (Refer to PRO-NOR-SUP-SUP-ENG Engine Ventilation (Dry Cranking)). In the case of ENG 1(2) START FAULT [EGT OVERLIMIT] alert, second manual engine start attempt on the affected engine is not permitted.
When all engines parameters are available on the ENG SD page: ENG 1 MAN START...............................................................................................................ON L2
Note:
L1
ENG PARAMETERS ..................................................................................................MONITOR In manual engine start mode, the FADEC does not automatically abort an abnormal manual start, except in the case of rotor overspeed. However, in the case of any engine malfunction, the FADEC still generates ECAM alerts, as necessary. As a result, the flight crew must closely monitor the manual start sequence, and the PF must be ready to immediately set the master lever of the affected engine to OFF when necessary. START VALVE...................................................................................................CHECK IN-LINE START VALVE PRESSURE..............................................................................CHECK GREEN OIL PRESSURE INCREASE...........................................................................................CHECK N3 INCREASE................................................................................................................. CHECK
L2
L1
For any operational reason, engine 2 can be started first.
When the maximum motoring speed is reached and the EGT< 150 °C: ‐ N2 (8 % minimum) ‐ N3 (25 % minimum) L2
The maximum motoring speed is reached when there is no significant increase of N3 and N2.
VIR A350 FLEET FCOM
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PROCEDURES NORMAL PROCEDURES A350
SUPPLEMENTARY PROCEDURES - ENGINE
FLIGHT CREW OPERATING MANUAL
In order to maximize stable compressor operation at light-off, the EGT should be < 150 °C. If the manual engine start is aborted, hot air may stagnate in the combustor chamber leading to no light up event. The flight crew has to perform a dry crank if the EGT > 150 °C. L1
L2 L1
ENG 1 MASTER..................................................................................................................... ON CHRONO.......................................................................................................................... START The PM starts timing in order to monitor the light-up delay. [ENG SD PAGE] IGNITORS A AND B INDICATIONS................................................... CHECK [ENG SD PAGE] FF INCREASE.....................................................................................CHECK 20 s maximum after the ENG 1 MASTER is set to ON: [ENG DISPLAY] N1 INCREASE............................................................................... CHECK [ENG DISPLAY] EGT INCREASE............................................................................ CHECK When N3 is at, or above 48 % : [ENG SD PAGE] IGNITORS INDICATIONS...........................................................CHECK OFF [ENG SD PAGE] START VALVE ............................................................ CHECK CROSS LINE
L2 L1
When idle is reached and AVAIL is displayed: MAIN ENG PARAMETERS.............................................................................CHECK NORMAL SECONDARY ENG PARAMETERS............................................................... CHECK NORMAL ENG 1 MAN START............................................................................................................. OFF ENG START SEL..............................................................................................................NORM After 30 s, the pack valves open again. If the second engine can be started manually: Apply the same procedure as indicated for engine 1. If the second engine can be started automatically: SOP - AUTOMATIC ENGINE START........................................................................PERFORM ENGINE START VALVE MANUAL OPERATION
Ident.: PRO-NOR-SUP-SUP-ENG-00021218.0001001 / 09 MAR 16 Applicable to: ALL
BEFORE ENGINE START Advise ground crew to prepare for manual engine start valve operation.
VIR A350 FLEET FCOM
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PROCEDURES NORMAL PROCEDURES A350
SUPPLEMENTARY PROCEDURES - ENGINE
FLIGHT CREW OPERATING MANUAL
ENGINE START RMP INT............................................................................................................................... SELECT The flight crew can establish communication with ground crew using service interphone at any service area next to the affected engine: ‐ Select RMP CAB ‐ Or use the cockpit handset.
L2
L1
GND CREW CLEARANCE....................................................................................................OBTAIN When ground crew is ready: ENG START SEL..................................................................................................... IGN START ENG (AFFECTED) MASTER..................................................................................................ON ENG START VALVE....................................................................................... REQUEST OPEN The ground crew must maintain the valve in the OPEN position until the engine is started. If not, the start valve closes. When N3 is at 48 % : ENG START VALVE...............................................................................REQUEST CLOSE SOP — ENGINE START....................................................................................... RESUME ENGINE VENTILATION (DRY CRANKING)
Ident.: PRO-NOR-SUP-SUP-ENG-00023013.0001001 / 30 JUL 15 Applicable to: ALL
On ground, after a manual engine start attempt that is not successful, the flight crew can perform a dry crank cycle on the affected engine to remove the fuel vapors and to reduce residual EGT to 150 °C. BEFORE MANUAL DRY CRANK CYCLE ENG MASTER............................................................................................................... CHECK OFF ENG START SEL.......................................................................................................CHECK NORM ENG MAN START P/B.................................................................................................. CHECK OFF MANUAL DRY CRANK CYCLE ENG START SEL...................................................................................................................CRANK ENG MAN START P/B..................................................................................................................ON When the EGT ≤ 150 °C: ENG MAN START P/B......................................................................................................... OFF ENG START SEL..............................................................................................................NORM Note: VIR A350 FLEET FCOM
For manual engine start Refer to PRO-NOR-SUP-SUP-ENG Manual Engine Start.
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PROCEDURES NORMAL PROCEDURES A350
SUPPLEMENTARY PROCEDURES - ENGINE
FLIGHT CREW OPERATING MANUAL
REDUCED ENGINE TAXI - GENERAL
3 Ident.: PRO-NOR-SUP-SUP-ENG-00021974.9001003 / 15 MAR 20 4 Applicable to: ALL
Prior to commencing Reduced Engine Taxi (RET) operations, crew shall review the following GUIDANCE and CONSIDERATIONS sections in full. GUIDANCE REDUCED ENGINE TAXI OUT (RETO) ‐ Procedures associated with the first engine start are announced by CM2 and actioned by CM1. ‐ Procedures associated with the second engine start are announced and actioned by the PM. Note:
This diversion of duties cannot be shown on the ECAM procedure due to formatting restrictions.
REDUCED ENGINE TAXI IN (RETI) ‐ All procedures are announced and actioned by the PM. Note:
This diversion of duties cannot be shown on the ECAM procedure due to formatting restrictions.
CONSIDERATIONS ALL RET OPERATIONS ‐ RET must NOT be used in LVO conditions. ‐ RET must NOT be used on slippery or contaminated taxiways or runways. ‐ RET must NOT be used if there are any system failures, MEL or DISPATCH page items affecting APU, Brakes, Nose Wheel Steering, Hydraulics or Electrical systems. ‐ RET may require more thrust than normal. Therefore, the flight crew must be careful in order to avoid excessive jet blast and the risk of Foreign Object Damage (FOD). ‐ RET is permitted in icing conditions, including freezing fog, however extra consideration must be given to taxi times with engine anti-ice selected. Taxi times must be recorded in the Tech Log as per SOP's. CAUTION
Do not increase the N1 above 64 % so that the N1 remains below the Keep Out Zone (KOZ). If the KOZ limit is reached, the N1 will automatically increase by 20 %, in order to exit the KOZ.
‐ Slow or tight turns in the direction of the operating engine may not be possible at high gross weights. VIR A350 FLEET FCOM
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PRO-NOR-SUP-SUP-ENG P 9/14 15 MAR 20
PROCEDURES NORMAL PROCEDURES A350
SUPPLEMENTARY PROCEDURES - ENGINE
FLIGHT CREW OPERATING MANUAL
‐ When RET is planned, pay particular attention to any fuel imbalance limitation for the next take-off. CAUTION
RET can be used when crossing an active runway only if the conditions below have been satisfied: ‐ The first engine start/stop sequence, including ECAM STATUS check for RETO, must be completed prior to crossing the active runway. ‐ The second engine start procedure must NOT begin until clear of an active runway. ‐ No checklist actions are allowed whilst crossing the active runway.
‐ Should any system failure occur consider bringing the aircraft to a halt and applying the parking brake. Consideration should also be given to starting the other engine or if unavailable, seeking external assistance. ‐ The Heading Control Function (HCF) is inoperative during all RET operations. Refer to DSC-32-30-10 SYSTEM DESCRIPTION HEADING CONTROL FUNCTION. RETO ‐ Reduced Engine Taxi Out (RETO) is NOT permitted once all engines have been started. CAUTION
RETO operations: After second engine start delay the selection of Cross Bleed to Auto for at least 30 seconds: ENG THRUST LEVER (LAST ENG STARTED) : KEEP IDLE FOR 30 SECONDS BEFORE XBLEED SEL ... AUTO
RETI CAUTION
RETI shall not be commenced until the minimum cooling time has passed and when taxiing straight. A350 minimum cooling time: 5 minutes Note:
Cooling time commences at:
‐ REV IDLE used: Touchdown ‐ MAX REV used: After reverse thrust has been cancelled
‐ Specifically for Reduced Engine Taxi In (RETI), a duration longer than approximately 5 min of taxi with one engine after landing will trigger the following ECAM alert: F/CTL DIRECT LAW (PROT LOST). This reversion to direct law has no effect on aircraft dispatch.
VIR A350 FLEET FCOM
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PRO-NOR-SUP-SUP-ENG P 10/14 15 MAR 20
PROCEDURES NORMAL PROCEDURES A350
FLIGHT CREW OPERATING MANUAL
SUPPLEMENTARY PROCEDURES - ENGINE
REDUCED ENGINE - TAXI OUT Ident.: PRO-NOR-SUP-SUP-ENG-21401126.9001001 / 15 MAR 20 Applicable to: ALL
FIRST ENGINE START GUIDANCE AND CONSIDERATIONS.......................................................REVIEWED PF-PM Refer to FCOM for guidance and considerations prior to using this procedure. (Refer to PRO-NOR-SUP-SUP-ENG Reduced Engine Taxi - General). ENGINE 1(2)...................................................................................................... START CM1 For any operational reason, engine 2 can be started instead of engine 1. ENG START SELECTOR...................................................................................NORM CM1 XBLEED............................................................................................................... OPEN CM1 Open the Crossbleed valve in order to supply both packs. APU BLEED............................................................................................................OFF CM1 APU.........................................................................................................................OFF CM1 ANTI ICE RUNNING ENG............................................................................ AS RQRD CM1 ECAM STATUS.................................................................................................CHECK BOTH Both pilots check there is no status reminder on the WD. If STS appears on the WD, CM2 presses the STS pb on the ECP to display the STATUS page allowing both pilots to review the status of the aircraft. TUG & GND CREW...............................................................................DISCONNECT CM1 Delay flight controls check and taxi flow until all engines are started.
L2
L1
L2 L1
L2 L1
L2
L1
L2 5 L1
SECOND ENGINE START ENG START SELECTOR...........................................................................IGN/START PM ENG 2(1)............................................................................................................ START PM ENG START SELECTOR...................................................................................NORM PM CHRONO............................................................................................................START PF-PM Accurate timing of the 5 minute warm up period is essential. XBLEED............................................................................................................... AUTO PM ANTI ICE RUNNING ENGS..........................................................................AS RQRD PM GND SPOILERS.................................................................................................... ARM PM RUDDER TRIM .....................................................................................CHECK ZERO PM FLAPS..................................................................................................................... SET PM Set the FLAPS for takeoff. Check the slats and flaps position on the slats/flaps display on the PFD. PITCH TRIM......................................................................................................CHECK PM Check that the pitch trim is set for takeoff on the pitch trim display on the PFD.
L2 L1
L2 L1
L2
VIR A350 FLEET FCOM
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PRO-NOR-SUP-SUP-ENG P 11/14 15 MAR 20
PROCEDURES NORMAL PROCEDURES A350
FLIGHT CREW OPERATING MANUAL
SUPPLEMENTARY PROCEDURES - ENGINE
ECAM STATUS.................................................................................................CHECK BOTH Both pilots check there is no status reminder on the WD. If STS appears on the WD, PM presses the STS pb on the ECP to display the STATUS page allowing both pilots to review the status of the aircraft.
L1
L2
REDUCED ENGINE - TAXI IN Ident.: PRO-NOR-SUP-SUP-ENG-21401127.9001001 / 15 MAR 20 Applicable to: ALL 6
GUIDANCE AND CONSIDERATIONS...........................................................REVIEWED PF-PM Refer to the FCOM for guidance and considerations prior to using this procedure. (Refer to PRO-NOR-SUP-SUP-ENG Reduced Engine Taxi - General). L1 ECAM STATUS.....................................................................................................CHECK BOTH L2 Both pilots check there is no status reminder on the WD. If STS appears on the WD, PM presses the STS pb on the ECP to display the STATUS page allowing both pilots to review the status of the aircraft. L1 APU..........................................................................................................................AVAIL PM ENG 1(2).......................................................................................................SHUTDOWN PM
L2
ALL ENGINE SHUT DOWN Ident.: PRO-NOR-SUP-SUP-ENG-21400072.9001002 / 03 FEB 20 Applicable to: ALL
This procedure can only be considered when the aircraft has left the gate and, prior to getting airborne, is required to hold at a remote location for an extended period for which it is not practical or desired to keep the engines running. Note:
The flight crew must operate the engines at or near idle thrust for a cooling period of 5 mins before engine shutdown, in order to thermally stabilize the engines. Normal thrust to manoeuvre during taxi (i.e. at or near idle) is acceptable and can be counted as this cooling period.
Additionally the following conditions must be satisfied: ‐ Serviceable APU ‐ NO MEL/CDL or system failures affecting NWS, Brakes, Hydraulics, Electrics or the APU. SHUT DOWN AFTER LANDING C/L.................................................................................................. COMPLETE C/L RESET............................................................................................................................ CLICK APU.......................................................................................................................................START ATC......................................................................................................................................ADVISE VIR A350 FLEET FCOM
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PRO-NOR-SUP-SUP-ENG P 12/14 15 MAR 20
PROCEDURES NORMAL PROCEDURES A350
FLIGHT CREW OPERATING MANUAL
SUPPLEMENTARY PROCEDURES - ENGINE
PARK BRAKE............................................................................................................................. ON APU BLEED pb ......................................................................................................................... ON ANTI ICE pb-sw .......................................................................................................................OFF BEACON sw .............................................................................................................................. ON EXTERIOR LIGHTS........................................................................................................ AS RQRD ENG 1, 2 MASTER LEVERS................................................................................................... OFF L2 L1
Note:
The ZFW, ZFWCG & BLOCK fields are emptied.
BEFORE START PREPARATION COCKPIT PREP.................................................................................................................REVIEW FMS PAGES................................................................................................... CHECK/COMPLETE
L2
Note:
The ZFW, ZFWCG & BLOCK values must be inserted.
L1
BEFORE START C/L TO THE LINE............................................................................COMPLETE STARTUP ATC......................................................................................................................................ADVISE BEFORE START C/L BELOW THE LINE....................................................................COMPLETE ENGINE 1, 2 START..................................................................................................AS NORMAL AFTER ALL ENGINES STARTED AFTER START C/L...................................................................................................... COMPLETE NORMAL TAXI PROCEDURES....................................................................................... RESUME
VIR A350 FLEET FCOM
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PRO-NOR-SUP-SUP-ENG P 13/14 15 MAR 20
PROCEDURES NORMAL PROCEDURES A350
FLIGHT CREW OPERATING MANUAL
SUPPLEMENTARY PROCEDURES - ENGINE
Intentionally left blank
VIR A350 FLEET FCOM
PRO-NOR-SUP-SUP-ENG P 14/14 15 MAR 20
PROCEDURES NORMAL PROCEDURES A350
FLIGHT CREW OPERATING MANUAL
SUPPLEMENTARY PROCEDURES - FUEL
SAFETY PRECAUTIONS FOR GROUND FUEL OPERATIONS Ident.: PRO-NOR-SUP-SUP-FUEL-00021161.0001001 / 17 NOV 17 Applicable to: ALL
WARNING
1. Prior initiation of any ground fuel operations, obey the below fuel safety precautions. This will prevent injury to people and/or damage to the aircraft. 2. Do not request or perform any ground fuel operations if a fire or engine overheat warning is displayed. 3. If the APU fails during any ground fuel operations, do not restart the APU.
SAFETY PRECAUTIONS............................................................................................................APPLY During any ground fuel operations, ensure that: ‐ The aircraft is properly bonded to the tanker ‐ The tanker and the aircraft grounding requirement is based on local regulations. Always connect the ground cable to the parking ground point (or to the tanker) before connecting it to the aircraft ‐ The external lighting is not operated except for • Navigation lights (NAV sw), • Logo lights (LOGO sw), • Wing and engine scan lights (WING sw). ACCESS PLATFORM.......................................................................................................IN POSITION CAUTION
Do not use the right wing refuel coupling and the left wing refuel coupling at the same time.
FUEL TANKER HOSES CONNECTION....................................................................................CHECK One or two fuel hoses can be used to perform a refuel operation. MAX REFUELING PRESSURE: 55 PSI (3.8 BAR) AUTOMATIC REFUELING Ident.: PRO-NOR-SUP-SUP-FUEL-00021924.0001001 / 05 NOV 18 Applicable to: ALL
[SUP] SAFETY PRECAUTIONS................................................................ REFER TO PROC APPLY If the aircraft is electrically powered with an EXT PWR or the APU: If the refueling is performed from the cockpit via the REFUEL pb-sw : FMS FUEL & LOAD PAGE......................................................................................... SELECT BLOCK........................................................................................................................... ENTER L2 Enter the desired FOB value in the BLOCK entry field and validate. L1 [OVERHEAD PANEL] REFUEL pb-sw ............................................................................... ON L2 Start the automatic refuel from the cockpit. VIR A350 FLEET FCOM
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PRO-NOR-SUP-SUP-FUEL P 1/6 01 JUL 19
PROCEDURES NORMAL PROCEDURES A350
FLIGHT CREW OPERATING MANUAL L1 L2
L1
L2 L1
L2
L1 L2 L1
L2
L1
L2
L1 L2
L1 L2
L1
L2
SUPPLEMENTARY PROCEDURES - FUEL
REFUEL IN PROGRESS The refueling automatically starts as soon as the tests are completed. The REFUEL IN PROGRESS memo appears on the WD. FUEL SD page ..........................................................................................................DISPLAY FUEL QUANTITY......................................................................................................MONITOR On the FUEL SD page, check that the fuel quantity increases. When the END light of the REFUEL pb-sw comes on : FUEL QUANTITY....................................................................................................CHECK On the FUEL SD page, check that the fuel quantity is within 200 kg (440 lb) of the preselected BLOCK value. [OVERHEAD PANEL] REFUEL pb-sw .......................................................................OFF The automatic refueling stops. If the refueling is performed from the External Refuel Panel (ERP): PRESELECT (PFQ)............................................................................................................SET Select the total fuel quantity that is required onboard the aircraft at the end of the refueling, with the PRESELECT sw. REFUEL/DEFUEL VALVES sw ........................................................................ CHECK SHUT MODE SELECT................................................................................................AUTO REFUEL Fuel system tests are automatically started, the SHUTOFF TEST label is displayed as long as the test is in progress (approximately 30 s). AUTO REFUEL The refueling automatically starts as soon as the tests are completed. The AUTO REFUEL indication appears on the STATUS displays of the ERP, and the REFUEL IN PROGRESS memo appears on the WD in the cockpit. FUEL QUANTITY......................................................................................................MONITOR On the ERP, check that the fuel quantities of the fuel tanks, and the ACTUAL (FOB) value increase. For aircraft equipped with REFUEL pb-sw , the PFQ is the last entered value between the ERP and the BLOCK value. As a consequence, the PFQ changes if the flight crew updates the BLOCK value of the FMS FUEL & LOAD Page during refueling. When the AUTO REFUEL END message appears on the ERP: FUEL QUANTITY....................................................................................................CHECK The fuel quantity on the ACTUAL (FOB) is within 200 kg (440 lb) of the PRESELECTED (PFQ) value.
VIR A350 FLEET FCOM
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PRO-NOR-SUP-SUP-FUEL P 2/6 01 JUL 19
PROCEDURES NORMAL PROCEDURES A350
FLIGHT CREW OPERATING MANUAL
SUPPLEMENTARY PROCEDURES - FUEL
MODE SELECT........................................................................................................... OFF The ERP STATUS displays the OFF MODE indication.
L1 L2 L1
If the refueling is performed on batteries: MAX REFUEL TIME ON BATTERY: 10 MIN [ELEC PANEL] ALL BAT pb-sw ................................................................................ CHECK OFF [ERP] POWER SUPPLY sw ...........................................................................................BATTERY PRESELECT (PFQ).................................................................................................................. SET L2 Select the total fuel quantity that is required onboard the aircraft at the end of the refueling, with the PRESELECT sw. L1 [ERP] REFUEL/DEFUEL VALVES sw .................................................................... CHECK SHUT [ERP] MODE SELECT............................................................................................AUTO REFUEL L2 Fuel system tests are automatically started, the SHUTOFF TEST label is displayed as long as the test is in progress (approximately 20 s). L1 L2
L1 L2
L1
L2
L1 L2 L1 L2
AUTO REFUEL The refueling automatically starts as soon as the tests are completed. The AUTO REFUEL indication appears on the STATUS displays of the ERP. [ERP] FUEL QUANTITY..................................................................................................MONITOR On the ERP, check that the fuel quantities of the fuel tanks and the ACTUAL (FOB) value increase. When the AUTO REFUEL END message appears on the ERP: [ERP] FUEL QUANTITY............................................................................................... CHECK The fuel quantity on the ACTUAL (FOB) is within 200 kg (440 lb) of the PRESELECTED (PFQ) value. [ERP] MODE SELECT....................................................................................................... OFF The ERP STATUS displays the OFF MODE indication. BATTERY VOLTAGE ............................................................................REGULARLY CHECK Check that the battery voltage is sufficient for current operations (engine start or APU start) GROUND FUEL TRANSFER
Ident.: PRO-NOR-SUP-SUP-FUEL-00021105.0001001 / 04 MAY 16 Applicable to: ALL L2
Note:
This supplementary procedure may be applied in case of abnormal fuel distribution on ground. For more information, Refer to PRO-ABN-FUEL FUEL ABNORM DISTRIBUTION.
L1
[SUP] SAFETY PRECAUTIONS................................................................ REFER TO PROC APPLY
VIR A350 FLEET FCOM
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PRO-NOR-SUP-SUP-FUEL P 3/6 01 JUL 19
PROCEDURES NORMAL PROCEDURES A350
FLIGHT CREW OPERATING MANUAL
WARNING
SUPPLEMENTARY PROCEDURES - FUEL
During the procedure, a flight crewmember must be in the cockpit to stop the pumps when the low pressure FAULT light comes on on the External Refuel Panel [ERP]. This is to prevent the operation of the pump without fuel.
In the cockpit: ALL IR MODE selector ....................................................................................... CHECK ON NAV L2 Ensure that all IRs are aligned. L1 FUEL SD page ................................................................................................................ DISPLAY FUEL QUANTITY (ALL TANKS)...................................................................................... RECORD L2 Record the fuel quantity in each tank. L1
On the ERP: Perform the FQMS high level shutoff test: [ERP] SHUTOFF TEST pb-sw ...................................PUSH IN AND MAINTAIN FOR 5 SEC. L2 All the ERP lamps and indicators comes on. L1 [ERP] SHUTOFF TEST pb-sw .................................................................................RELEASE L2 The ERP STATUS displays SHUTOFF TEST. L1
Note:
The release of the SHUTOFF TEST pb-sw starts the test. The test duration is approx. 30 s.
At the end of the test, ensure that: ‐ The ERP STATUS displays TEST OK for 2 seconds ‐ The FAULT light is not on. [ERP] REFUEL/DEFUEL VALVES sw (OF ALL TANKS).................................. CHECK SHUT [ERP] MODE SELECT..........................................................................................CHECK OFF [ERP] REFUEL/DEFUEL VALVES sw (OF TANKS TO BE FILLED)..............................OPEN In the cockpit: FUEL CROSSFEED A................................................................................................................ON FUEL CROSSFEED B................................................................................................................ON L2 Check that the ON and OPEN lights come on on the corresponding CROSSFEED pb. L1 L2 L1
FUEL PMPs (OF THE TANK(s) TO BE DEFUELED)................................................................ ON Check that the OFF light goes off on the corresponding PMP pb-sw. Note:
For fuel transfer from the center tank, use the Left and Right CTR TK pumps. For fuel transfer from the wing tanks, use the associated MAIN or the STBY pump.
VIR A350 FLEET FCOM
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PRO-NOR-SUP-SUP-FUEL P 4/6 01 JUL 19
PROCEDURES NORMAL PROCEDURES A350
FLIGHT CREW OPERATING MANUAL
SUPPLEMENTARY PROCEDURES - FUEL
On the ERP: [ERP] MODE SELECT........................................................................................... XFR POSITION L2 The fuel transfer starts. L1 L2 L1 L2
GND XFR IN PROGRESS The ECAM MEMO message appears on the WD. [ERP] or [ECAM] FUEL QUANTITY................................................................................MONITOR On the ERP or on the ECAM FUEL SD page, ensure that the fuel of the tank is transferred.
L1
When the fuel quantity have reached the necessary level, or have decreased to low level: On the ERP: [ERP] REFUEL/DEFUEL VALVES sw (OF ALL TANKS)................................................SHUT [ERP] MODE SELECT....................................................................................................... OFF L2 The ERP STATUS displays OFF MODE. L1
L2
L1
L2
In the cockpit: FUEL CORRESPONDING PMPs ............................................................................ AS RQRD If fuel pumps are set to OFF, check that the OFF light comes on on the corresponding PMPs pb-sw. FUEL CROSSFEED A........................................................................................................OFF FUEL CROSSFEED B........................................................................................................OFF Check that the ON light goes off on the corresponding CROSSFEED pb.
VIR A350 FLEET FCOM
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PRO-NOR-SUP-SUP-FUEL P 5/6 01 JUL 19
PROCEDURES NORMAL PROCEDURES A350
FLIGHT CREW OPERATING MANUAL
SUPPLEMENTARY PROCEDURES - FUEL
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VIR A350 FLEET FCOM
PRO-NOR-SUP-SUP-FUEL P 6/6 01 JUL 19
PROCEDURES NORMAL PROCEDURES A350
FLIGHT CREW OPERATING MANUAL
SUPPLEMENTARY PROCEDURES - LANDING GEAR
FLIGHT WITH GEAR DOWN Applicable to: ALL Ident.: PRO-NOR-SUP-SUP-LG-SUP-LG-00022736.0001001 / 09 MAR 16
This chapter applies to dispatch with L/G down. A revenue flight is permitted with the L/G down, and the L/G gear doors closed in the conditions stated below. Ident.: PRO-NOR-SUP-SUP-LG-SUP-LG-00022734.0002001 / 05 JUN 18
FLIGHT PREPARATION - LIMITATIONS
L2
L1
L2
L1
L2
L1 L2
L1 L2 L1 L2 L1 L2 L1
MAX FL : 350 MIN TAT : -38 °C This minimum TAT is required to maintain the minimum fluid temperature in the L/G shock absorbers. MIN SAT BELOW 21 000 FT : -45 °C MIN SAT AT OR ABOVE 21 000 FT : -52 °C Due to the lower cruise speed, the TAT is more likely to come close to the minimum limit. The minimum values of SAT (depending on the altitude) ensure the capability to maintain this minimum TAT, either by accelerating or descending to a lower altitude. MAX FLT TIME : 8 HR MAX T.O WEIGHT : 280 000 KG (617 200 LBS) The takeoff weight must be less than this maximum value in order to ensure a sufficient margin between VLS and VMO/MMO during the entire flight. MIN LDG WEIGHT : 185 000 KG (407 900 LBS) The aircraft weight must remain more than this minimum weight during the entire flight (that includes diversion to the alternate airport) for handling quality reasons (protection against possible high speed excursion). MAX SPEED : 255/.64 VMO/MMO for a flight with the L/G in the extended position and L/G doors closed is 255 kt/M 0.64. RECOMMENDED SPEED : 245/.55 245 kt/M 0.55 is the recommended speed for climb, cruise, and descent. FLT IN EXPECTED ICING CONDs : NOT PERMITTED Due to the possible ice accretion on the L/G, flight is not permitted in expected icing conditions. RVSM : NOT PERMITTED ETOPS : NOT PERMITTED DITCHING NOT DEMONSTRATED
VIR A350 FLEET FCOM
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PRO-NOR-SUP-SUP-LG P 1/10 03 FEB 20
PROCEDURES NORMAL PROCEDURES A350
FLIGHT CREW OPERATING MANUAL
SUPPLEMENTARY PROCEDURES - LANDING GEAR
DISPATCH NOT PERMITTED WITH MEL ITEMS AFFECTING RA, ADIRS, SLATS/FLAPS, F/CTL, BRAKE, TACHOMETER, LGERS COMPUTERS (L/G CTL 1 & 2, CPIOM H61, H62, H63 & H64), CRDC A02, A07, A10, A11, A12 & A13, ENG REVERSER, HYD ENG PMP, AND A/THR L2
L1 L2
L1 L2
L1 L2 L1
ACCU REINFLATE NOT AVAIL IN FLT : BRAKING ON ACCU DEGRADED Due to the fact that the L/G remains in the extended position, there is no automatic refill of the brake accumulators in flight. In addition, the hydraulic pressure in the brake accumulators is slightly reduced at landing. This pressure reduction is more significant if the L/G is exposed to outside air temperatures less than -20 °C (-4 °F). AUTO-DERATE CLB : DO NOT USE Because the AUTO-DERATE function is not designed to be used with the L/G in the extended position, the flight crew must select CLB (maximum climb) thrust for climb. GA THR : TOGA ONLY Because the soft go-around function is not designed to be used with the L/G in the extended position, the flight crew must select TOGA thrust for go-around. MANAGED VERTICAL MODES (CLB & DES) : DO NOT USE Due to the L/G in the extended position in flight, the FMS vertical guidance is not accurate. MANAGED SPEED (EXCEPT IN APPR) : DO NOT USE FMS PRED (ALT, SPD, TIME & PSEUDO-WPT) : DO NOT USE Note:
However, in level flight, time predictions at cruise waypoints are correct.
FUEL CONSUMPT INCRSD L2
L1 L2
L1 L2
L1 L2
FMS FUEL PRED UNRELIABLE WITHOUT ACCURATE FMS FUEL PENALTY INSERTION For more information about FMS fuel penalty value and insertion procedure, Refer to PRO-NOR-SUP-SUP-LG Flight With Gear Down - Cockpit Preparation. SIGNS AUTO MODE : DO NOT USE Because the L/G is in the extended position, the signs remain on during the whole flight if the AUTO mode is used. REDUCED DME RANGE The range of the DME antenna is reduced by approximately 75 NM at high altitude (at or above FL 265). CRUISE SD PAGE NOT AVAIL Because the L/G is in the extended position, the default SD page is the WHEEL SD page. The flight crew should check the other SD pages more frequently.
VIR A350 FLEET FCOM
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PRO-NOR-SUP-SUP-LG P 2/10 03 FEB 20
PROCEDURES NORMAL PROCEDURES A350
FLIGHT CREW OPERATING MANUAL L1
L2
SUPPLEMENTARY PROCEDURES - LANDING GEAR
In the case of HYD Y SYS PRESS LO ECAM alert in flight: MAX XWIND FOR LANDING : 20 KT As nose wheel steering is lost, and differential braking performance is slightly degraded due to lower accumulator pressure, the lateral control at low speed is ensured for a crosswind up to 20 kt only.
Ident.: PRO-NOR-SUP-SUP-LG-SUP-LG-00022740.0002001 / 05 JUN 18
DURING PRELIMINARY COCKPIT PREPARATION L/G LEVER L2 L1
L2
L1 L2
L1
L/G LEVER COVER.......................................................................................................IN PLACE Check that the appropriate cover is in place on the L/G lever. ECAM/LOGBOOK CHECK FLT L/G DOWN MEMO................................................................................ CHECK DISPLAYED The ground crew should set the VMO/MMO switch on the "L/G DOWN" position. The FLT L/G DOWN memo on the ECAM indicates this position. [LOGBOOK] L/G LOCKING DEVICES INSTALLATION (IF RQRD) : CHECK LOGGED Depending on the cause of the L/G retraction failure, the installation of L/G locking devices may be required or not. Check in the logbook whether maintenance crew has logged the installation of L/G locking devices instead of the safety pins. MEL/CDL ITEMS CHECK DISPATCH NOT PERMITTED WITH MEL ITEMS AFFECTING RA, ADIRS, SLATS/FLAPS, F/CTL, BRAKE, TACHOMETER, LGERS COMPUTERS (L/G CTL 1 & 2, CPIOM H61, H62, H63 & H64), CRDC A02, A07, A10, A11, A12 & A13, ENG REVERSER, HYD ENG PMP, AND A/THR TAKEOFF PERF
L2
L1 L2 L1
L2
MAX T.O WEIGHT : 280 000 KG (617 200 LBS) The takeoff weight must be less than this maximum value in order to ensure a sufficient margin between VLS and VMO/MMO during the entire flight. RECOMMENDED FLAPS : CONF 1+F CONF 1+F configuration gives the lower drag. AVOID TAILWIND T.O PERF WITH L/G DOWN........................................................................................COMPUTE Takeoff performance is affected, compute takeoff performance with the L/G in the extended position.
VIR A350 FLEET FCOM
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PRO-NOR-SUP-SUP-LG P 3/10 03 FEB 20
PROCEDURES NORMAL PROCEDURES A350
FLIGHT CREW OPERATING MANUAL L1
Note:
SUPPLEMENTARY PROCEDURES - LANDING GEAR
In the Airbus EFB T.O PERF application, select the "Landing gears position All extended" MEL item.
LANDING PERF (DISPATCH) L2
L1 L2
L1
MIN LDG WEIGHT : 185 000 KG (407 900 LBS) The aircraft weight must remain more than this minimum weight during the entire flight (that includes diversion to the alternate airport) for handling quality reasons (protection against possible high speed excursion). LDG PERF WITH L/G DOWN........................................................................................... CHECK Landing performance (go-around gradient and RLD) is affected, check landing performance with the L/G in the extended position. Note:
In the Airbus EFB LDG PERF application (DISPATCH computation mode), select the "Landing gears position All extended" MEL item.
Ident.: PRO-NOR-SUP-SUP-LG-SUP-LG-00023003.0001001 / 09 MAR 16
DURING EXTERIOR WALKAROUND L2
L/G LOCKING DEVICES.....................................................................................AS APPROPRIATE Depending on the cause of the L/G retraction failure, the installation of L/G locking devices may be required or not. Check that the L/G locking devices installation is in accordance with the logbook status.
Ident.: PRO-NOR-SUP-SUP-LG-SUP-LG-00023004.0001001 / 12 DEC 16
DURING COCKPIT PREPARATION OVERHEAD PANEL L2
L1
L2
L1
SIGNS AUTO MODE : DO NOT USE Because the L/G is in the extended position, the signs remain on during the whole flight if the AUTO mode is used. MFD FMS PREPARATION FMS FUEL PRED UNRELIABLE WITHOUT ACCURATE FMS FUEL PENALTY INSERTION The fuel consumption is increased. The FUEL PENALTY on the FMS DATA/STATUS page should be updated. Note:
A conservative value for the fuel penalty is provided in the Fuel Penalty INOP SYS TABLE for L/G - L/G RETRACTION - All L/G extended (Refer to PER-IFT-FP Fuel Penalty Tables - Fuel Consumption Increased).
[FMS-DATA/STATUS PAGE] FUEL PENALTY.................................................................INSERT VIR A350 FLEET FCOM
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PRO-NOR-SUP-SUP-LG P 4/10 03 FEB 20
PROCEDURES NORMAL PROCEDURES A350
FLIGHT CREW OPERATING MANUAL L2 L1
L2
SUPPLEMENTARY PROCEDURES - LANDING GEAR
RECOMMENDED SPEED : 245/.55 245 kt/M 0.55 is the recommended speed for climb, cruise, and descent. [FMS-ACTIVE/PERF PAGES] PRESEL SPDs ................................................................ INSERT [FMS-ACTIVE/PERF/CLB PAGE] THR — “CLB”..............................................................INSERT The auto-derate thrust is not designed to be used with the L/G in the extended position. The flight crew must select maximum climb thrust (CLB) for climb.
Ident.: PRO-NOR-SUP-SUP-LG-SUP-LG-00023005.0001001 / 09 MAR 16
TAKEOFF WHEN POSITIVE CLIMB L/G : KEEP DOWN AT S SPEED L2
A/BRK RTO.................................................................................................... CHECK DISARMED After standard actions, check that BRK RTO does not appear on the FMA.
Ident.: PRO-NOR-SUP-SUP-LG-SUP-LG-00023006.0002001 / 05 JUN 18
DURING CLIMB AND CRUISE L2
L1
L2
L1
L2
L1
L2 L1
AUTO-DERATE CLB : DO NOT USE Because the AUTO-DERATE function is not designed to be used with the L/G in the extended position, the flight crew must select CLB (maximum climb) thrust for climb. MAX FL : 350 MIN TAT : -38 °C This minimum TAT is required to maintain the minimum fluid temperature in the L/G shock absorbers. MIN SAT BELOW 21 000 FT : -45 °C MIN SAT AT OR ABOVE 21 000 FT : -52 °C TEMPERATURE (SAT & TAT).......................................................................................... MONITOR Due to the lower cruise speed, the TAT is more likely to come close to the minimum limit. The minimum values of SAT (depending on the altitude) ensure the capability to maintain this minimum TAT, either by accelerating or descending to a lower altitude. RVSM : NOT PERMITTED AVOID ICING CONDs RECOMMENDED SPEED : 245/.55 245 kt/M 0.55 is the recommended speed for climb and cruise. CRUISE SD PAGE NOT AVAIL
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PROCEDURES NORMAL PROCEDURES A350
FLIGHT CREW OPERATING MANUAL
SUPPLEMENTARY PROCEDURES - LANDING GEAR
L2
Because the L/G is in the extended position, the default SD page is the WHEEL SD page. The flight crew should check the other SD pages more frequently.
L1
REDUCED DME RANGE The range of the DME antenna is reduced by approximately 75 NM at high altitude (at or above FL 265).
L2
Ident.: PRO-NOR-SUP-SUP-LG-SUP-LG-00023007.0002001 / 05 JUN 18
ENGINE FAILURE L2
EO MAX ALT.................................................................................................................... COMPUTE The EO MAX ALT displayed by the FMS does not take into account the extended position of the L/G. The flight crew should use an alternate source to determine the EO maximum altitude.
L1
Note:
L2
GREEN DOT SPD : VLS + 13 KT The green dot speed displayed by the PFD does not take into account the extended position of the L/G.
In the Airbus EFB IN-FLT PERF application (DES (OEI) panel): ‐ Select the "L/G DISPATCH WITH GEAR DOWN" NON STD CONF item ‐ Select DES TYPE: OBSTACLE for a drift-down at Green Dot speed, or DES TYPE: EO STANDARD for a descent at fixed speed.
Ident.: PRO-NOR-SUP-SUP-LG-SUP-LG-00023009.0002001 / 05 JUN 18
LANDING PERFORMANCE L2 L1
LDG PERF WITH L/G DOWN........................................................................................... CONFIRM Go-around performance is affected. Note:
In the Airbus EFB LDG PERF application (IN-FLIGHT computation mode), select the "Landing gears position All extended" MEL item.
FOR DESCENT AND APPROACH L2 L1 L2
L1
L2
RECOMMENDED SPEED : 245/.55 245 kt/M 0.55 is the recommended speed for descent. DESCENT SELECTED V/S MODE................................................................................. CONSIDER To avoid a high rate of descent due to the L/G in the extended position, consider using selected vertical speed. AVOID ICING CONDs FOR HOLDING : CONF 1 RECOMMENDED Slats extended is the least penalizing configuration.
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PRO-NOR-SUP-SUP-LG P 6/10 03 FEB 20
PROCEDURES NORMAL PROCEDURES A350
FLIGHT CREW OPERATING MANUAL L1
L2
L1 L2
SUPPLEMENTARY PROCEDURES - LANDING GEAR
In the case of HYD Y SYS PRESS LO ECAM alert: MAX XWIND FOR LANDING : 20 KT As nose wheel steering is lost, and differential braking performance is slightly degraded due to lower accumulator pressure, the lateral control at low speed is ensured for a crosswind up to 20 kt only. GA THR : TOGA ONLY Because the soft go-around function is not designed to be used with the L/G in the extended position, the flight crew must select TOGA thrust for go-around.
Ident.: PRO-NOR-SUP-SUP-LG-SUP-LG-00023008.0001001 / 09 MAR 16
GO-AROUND GO-AROUND INITIATION ALL THR LEVERS................................................................................................................TOGA WHEN POSITIVE CLIMB L/G : KEEP DOWN
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PRO-NOR-SUP-SUP-LG P 7/10 03 FEB 20
PROCEDURES NORMAL PROCEDURES A350
SUPPLEMENTARY PROCEDURES - LANDING GEAR
FLIGHT CREW OPERATING MANUAL
TRAMPLING OF ARRESTOR CABLES Ident.: PRO-NOR-SUP-SUP-LG-21400047.9001001 / 29 OCT 18 Applicable to: ALL
INTRODUCTION Some military aerodromes and civil airports are equipped with aircraft cables at both ends of the main runway. Typically these systems consist of a raised (up and rigged) cable, under tension, with rubber spacers located equidistant along the cable, raising the cable off the runway surface. The crossing of raised (up and rigged) arrestor cables is an operational concern for operators due to potential damage to the landing gear. The following information is general operations information for airlines and airports regarding limit speed trampling of rigged (up and rigged) arrestor cables. INFORMATION AND GUIDELINES Information relating to specific types, location and precautionary measures should be provided in the AIP/NOTAM's. Arrestor cables are usually located approximatley 457m (1500') to 600m (2000') from the end of the runway. In most joint-use airports, civil and military operations combined, runways are equipped with two arresting cable systems. For ease of identification, yellow circles are painted across the runway along the cable. During operations at dusk or during CET, obstacles should be marked and illuminated in accordance with ICAO Annex 14 recommendations - usually a lighted circle on the edge of the runway marks the location during darkness. Pilots are advised to avoid crossing a raised arrestor cable, but, if this is not possible, to cross below the maximum speed of 60 knots. Control towers and flight operations departments should inform aircraft, landing or taking off, of the position and status of an arrestor cable that is in place across either end of the intended runway. In general, they will also issue a caution to aircraft taxiing over an arrestor cable. GENERAL INFORMATION BAK-14 system consists of a cable able to ride above the runway surface or retract below the runway surface. This system is controlled by the control tower and pilots may cross it at high speed if the cable status is known as below the runway surface. BAK-12 system consists of a cable across the runway, usually suspended on rubber circular spacers. If these rubber circular spacers are in place then the cable is known as up and rigged. If the spacers are moved to one side with the cable resting on the surface, but still tensioned, it is considered down and rigged.The take-off run should be started after any raised (up and rigged)
Continued on the following page
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PRO-NOR-SUP-SUP-LG P 8/10 03 FEB 20
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SUPPLEMENTARY PROCEDURES - LANDING GEAR
FLIGHT CREW OPERATING MANUAL
TRAMPLING OF ARRESTOR CABLES (Cont'd) cable or from a point such that the aircraft speed is below the maximum speed of the 60 knots as it crosses the cable. The cable must always be tense (rigged). In the event of crossing a raised (up and rigged) arrestor cable at a speed at or above 60 Knots, VAA Engineering must be informed to ensure inspections/ maintenance procedures to be performed. OPERATIONAL CAUTION NOTES Check with the local Airport Authorities that they have not published any specific operating restrictions. Landing beyond raised (up and rigged) cables reduces the possibility of damage. Unless necessary do not cross the cables at maximum reverse thrust. Take into account the above recommendations for the performance computation. Carefully monitor the tire pressure of your aircraft to avoid rolling over raised (up and rigged) cables with underinflated tires. Operations on airfields with raised (up and rigged) arrestor cables may lead to increase tire wears and/or damage. Regularly inspect the landing gear and tires to detect any damage caused by the arresting device.
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PRO-NOR-SUP-SUP-LG P 10/10 03 FEB 20
PROCEDURES NORMAL PROCEDURES A350
SUPPLEMENTARY PROCEDURES - MISCELLANEOUS
FLIGHT CREW OPERATING MANUAL
FLIGHT WITHOUT CABIN PRESSURIZATION Applicable to: ALL Ident.: PRO-NOR-SUP-SUP-MISC-SUP-MIS-01-00021507.0001001 / 06 NOV 14
DURING PRELIMINARY COCKPIT PREPARATION OXYGEN FOR FLIGHT CREW MEMBERS
L2
L1
L2
CAPT OXYGEN PRESSURE.............................................................................................CHECK F/O OXYGEN PRESSURE................................................................................................ CHECK To obtain the requirements in oxygen for flight crew members, refer to FAR 121.329 or EU-OPS 1.770, or any other applicable operational regulation. For more information on oxygen limitations for flight crew members, Refer to LIM-OXY Minimum Flight Crew Oxygen Pressure. OXYGEN FOR CABIN OCCUPANTS OXYGEN FOR CABIN OCCUPANTS................................................................................CHECK For flight at cabin pressure altitudes above 10 000 ft, up to and including 14 000 ft, there must be enough oxygen to supply 10 % of the cabin occupants for the flight at those altitudes that lasts more than 30 min. For flight at cabin pressure altitudes above 14 000 ft, up to and including 15 000 ft, there must be enough oxygen to supply 30 % of the cabin occupants. For flight at cabin pressure altitudes above 15 000 ft, there must be enough oxygen for all cabin occupants. Flight crew must refer to more stringent requirements (i.e. local regulations, operator's policies), if applicable.
Ident.: PRO-NOR-SUP-SUP-MISC-SUP-MIS-01-00021747.0001001 / 06 NOV 14
DURING COCKPIT PREPARATION FLIGHT PLAN INITIALIZATION MAX SPEED: 250 kt MAX CRZ FL: 100/MSA If the altitude of the aircraft cabin reaches 13 800 ft, the cabin oxygen masks will automatically drop. The flight crew must decide the aircraft altitude, depending on: ‐ The Minimum Safe Altitude (MSA) ‐ Oxygen requirements
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PRO-NOR-SUP-SUP-MISC P 1/6 15 MAR 20
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FLIGHT CREW OPERATING MANUAL
SUPPLEMENTARY PROCEDURES - MISCELLANEOUS
‐ Turbulence, that can be uncomfortable for passengers ‐ Possible low Outside Air Temperature (OAT), that can be uncomfortable for passengers, when the aircraft is ventilated by RAM air only. If aircraft cruise FL is above FL 95: EXPECT CAB PRESS EXCESS CAB ALT ALERT Ident.: PRO-NOR-SUP-SUP-MISC-SUP-MIS-01-00021760.0001001 / 14 FEB 17
AFTER TAKEOFF
L2
L1
FOR PAX AND CREW COMFORT: AVOID EXCESSIVE RATE OF CLIMB (MAX: +1 500 FT/MIN) AVOID EXCESSIVE RATE OF DESCENT (MAX: -1 000 FT/MIN) PACK 1..........................................................................................................................................ON PACK 2..........................................................................................................................................ON CABIN ALT MODE..................................................................................................................... MAN CABIN ALT TRGT.............................................................................................. CRUISE ACFT ALT CABIN V/S MODE...................................................................................................................... MAN CABIN V/S TRGT............................................................................................................ FULLY UP In the case of a door failure or a structural damage, the flight crew must ensure that the differential pressure remains equal to 0 PSI during the whole flight. ECAM ALERT If aircraft/cabin altitude is above 9 550 ft: EXPECT CAB PRESS EXCESS CAB ALT ALERT ECAM CLR............................................................................................................ CONSIDER
Ident.: PRO-NOR-SUP-SUP-MISC-SUP-MIS-01-00021754.0001001 / 06 NOV 14
DURING APPROACH FINAL APPROACH......................................................................................PERFORM NORMALLY
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PRO-NOR-SUP-SUP-MISC P 2/6 15 MAR 20
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FLIGHT CREW OPERATING MANUAL
SUPPLEMENTARY PROCEDURES - MISCELLANEOUS
OPERATIONS AT QNH ABOVE 1050 HPA (31.00 INHG) Applicable to: ALL Ident.: PRO-NOR-SUP-SUP-MISC-SUP-MIS-02-00023216.0001001 / 03 DEC 15
FLIGHT PREPARATION / LIMITATIONS L2
MIN PRESSURE ALT FOR XPDR ALT RPTG : -1 000 FT The transponder sends erroneous data if the aircraft standard altitude is below -1 000 ft pressure altitude.
L1
Note:
1. High QNH values may result in pressure altitudes below -1 000 ft during takeoff and landing at low altitude airports. Therefore, the crew should apply the following procedures when the QNH is more than 1 050 hPa (31.00 inHg), and the airport elevation is less than 1 000 ft. 2. TCAS and ADS-B OUT operations are affected if the above mentioned limitation is not complied with.
Ident.: PRO-NOR-SUP-SUP-MISC-SUP-MIS-02-00023217.0001001 / 03 DEC 15
BEFORE TAKEOFF L2
L1 L2
[MFD SURV] ALT RPTG.............................................................................................................OFF Due to the transponder limitation, the flight crew must disconnect the altitude reporting. After the flight crew turn off the altitude reporting, an ALT RPTG OFF memo and a TCAS STBY memo appear on the WD. Expect SURV TCAS STBY alert above 1 500 ft RA if the TCAS is not restored before. ATC........................................................................................................................................ NOTIFY Notify the ATC that the altitude reporting is not available.
Ident.: PRO-NOR-SUP-SUP-MISC-SUP-MIS-02-00023219.0001001 / 03 DEC 15
TAKEOFF
L2
ABOVE 1 000 FT QNH, WHEN TIME PERMITS: [MFD SURV] ALT RPTG........................................................................................................ ON As a result, the TCAS automatically reverts to its previous setting.
Ident.: PRO-NOR-SUP-SUP-MISC-SUP-MIS-02-00023220.0001001 / 03 DEC 15
INTERMEDIATE/FINAL APPROACH
L2
BEFORE FINAL APPROACH: ATC..................................................................................................................................NOTIFY Notify the ATC that the altitude reporting will be turned off.
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PRO-NOR-SUP-SUP-MISC P 3/6 15 MAR 20
PROCEDURES NORMAL PROCEDURES A350
SUPPLEMENTARY PROCEDURES - MISCELLANEOUS
FLIGHT CREW OPERATING MANUAL L1 L2 L1
[MFD SURV] ALT RPTG...................................................................................................... OFF Due to the transponder limitation, the flight crew must disconnect the altitude reporting. EXPECT SURV TCAS STBY ALERT
HIGH ALTITUDE AIRPORT OPERATIONS Applicable to: ALL Ident.: PRO-NOR-SUP-SUP-MISC-SUP-80-10-00020410.0001001 / 06 NOV 14
TAKEOFF AND/OR LANDING FROM/TO AIRPORT ELEVATION OF 9 000 FT OR ABOVE PRELIMINARY COCKPIT PREPARATION L2
CKPT OXYGEN QUANTITY.............................................................................................. CHECK The use of the mask increases the oxygen consumption. The minimum flight crew oxygen pressure must be increased: Refer to Minimum Flight Crew Oxygen Pressure
Ident.: PRO-NOR-SUP-SUP-MISC-SUP-80-10-00018746.0001001 / 06 NOV 14
TAKEOFF ON AIRPORTS WITH AN ELEVATION OF 9 000 FT OR ABOVE BEFORE TAKEOFF L2
L1
L2
ONE OXYGEN MASK (AT LEAST ONE PILOT)................................ DON / NORM SELECTION At least one pilot must use the oxygen mask from takeoff until the memo HI ALT ARPT disappears. CLIMB When the memo HI ALT ARPT disappears: OXYGEN MASK....................................................... REMOVE / 100% SELECTION / STOW For more information to stow the mask: Refer to How to Stow the Mask.
Ident.: PRO-NOR-SUP-SUP-MISC-SUP-80-10-00020411.0002001 / 05 JUL 19
LANDING ON AIRPORTS WITH AN ELEVATION OF 9 000 FT OR ABOVE DESCENT PREPARATION
L2
If airport elevation is at or above 9 200 ft: LANDING PERFORMANCE...................................................................................COMPUTE Perform an assessment of the in-flight landing performance to determine the flaps configuration for landing and go-around. In Airbus EFB LDG application, use the AUTO-CONF setting for the field LDG CONF.
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PRO-NOR-SUP-SUP-MISC P 4/6 15 MAR 20
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FLIGHT CREW OPERATING MANUAL
Note:
L1
SUPPLEMENTARY PROCEDURES - MISCELLANEOUS
To achieve go-around performance requirements, the flight crew can select CONF 3 for landing and CONF 1+F for go-around.
DESCENT Below FL 250 and when the memo HI ALT ARPT is triggered: ONE OXYGEN MASK (AT LEAST ONE PILOT)...........................USE / NORM SELECTION At least one pilot must use the oxygen mask continuously until landing.
L2
LANDING
L1
FLARE HEIGHT INCREASE....................................................................................... CONSIDER For more information: Refer to FCTM/Flare and Touchdown
L2
VA DATA Applicable to: ALL Ident.: PRO-NOR-SUP-SUP-MISC-X-21401025.9001001 / 15 MAR 20 1
Refer to the linked procedure for further details. REDUCED ENGINE TAXI GUIDANCE & CONSIDERATIONS Refer to PRO-NOR-SUP-SUP-ENG Reduced Engine Taxi - General ALL ENGINE SHUTDOWN Refer to PRO-NOR-SUP-SUP-ENG All Engine Shutdown SUPPLEMENTARY PERFORMANCE INFORMATION Refer to PER-PSD Supplementary Performance Information AWOPS / TAKEOFF Refer to PRO-SPO-AWOPS Takeoff NORTH ATLANTIC HLA Refer to PRO-SPO-NAT HLA North Atlantic NAT HLA AWOPS / AUTOLAND Refer to PRO-SPO-AWOPS Autoland
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PROCEDURES SPECIAL OPERATIONS
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PRELIMINARY PAGES - TABLE OF CONTENTS
PRO-SPO-AWOPS AWOPS
Takeoff..................................................................................................................................................................... A Autoland................................................................................................................................................................... B
PRO-SPO-NAT HLA North Atlantic NAT HLA
North Atlantic NAT HLA.......................................................................................................................................... A
PRO-SPO-ETOPS Extended Range Operations
Icing Consideration for ETOPS Critical Fuel Reserves...........................................................................................A Diversion Decision Making...................................................................................................................................... B Abnormal and Emergency Procedures................................................................................................................... C Maximum Diversion Distance..................................................................................................................................D
PRO-SPO-FFWCCM Ferry Flight without CCM
General.....................................................................................................................................................................A Limitations................................................................................................................................................................ B Procedures...............................................................................................................................................................C
PRO-SPO-PBN PBN
General.....................................................................................................................................................................A RNAV 10/RNP 10.................................................................................................................................................... B RNAV 5/B-RNAV..................................................................................................................................................... C RNAV 2/En-Route RNAV........................................................................................................................................ D RNAV 1/P-RNAV Terminal RNAV...........................................................................................................................E RNP 4.......................................................................................................................................................................F RNP 2 In Oceanic And Remote Continental Area..................................................................................................G RNP 2 In Domestic Area.........................................................................................................................................H RNP 1/Terminal RNP 1 Basic RNP 1...................................................................................................................... I RNP APCH/RNAV(GNSS)....................................................................................................................................... J RNP AR / RNAV(RNP)............................................................................................................................................K
PRO-SPO-RVSM RVSM
RVSM Requirements............................................................................................................................................... A RVSM Procedure..................................................................................................................................................... B
1
PRO-SPO-PRM Simultaneous Parallel Approach Operations
Overview.................................................................................................................................................................. A Break out Turn and Climb Procedure..................................................................................................................... B Break out Turn and Descent Procedure................................................................................................................. C Continued on the following page
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PRO-SPO-PLP-TOC P 1/2 15 MAR 20
PROCEDURES SPECIAL OPERATIONS A350
FLIGHT CREW OPERATING MANUAL
PRELIMINARY PAGES - TABLE OF CONTENTS Continued from the previous page
PRO-SPO-PBCS Performance-Based Communication and Surveillance
General.....................................................................................................................................................................A Requirements........................................................................................................................................................... B Procedure.................................................................................................................................................................C
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PRO-SPO-PLP-TOC P 2/2 15 MAR 20
PROCEDURES SPECIAL OPERATIONS A350
PRELIMINARY PAGES - SUMMARY OF HIGHLIGHTS
FLIGHT CREW OPERATING MANUAL
Localization Title
PRO-SPO-PLP-TOC Simultaneous Parallel Approach Operations PRO-SPO-RVSM Flight Preparation PRO-SPO-RVSM In Flight PRO-SPO-RVSM Abnormal and Emergency Procedures PRO-SPO-PRM Overview
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Toc Index
ID
Reason
1
B
1
Documentation update: The "ILS Precision Runway Monitor" table of content entry renamed in "Simultaneous Parallel Approach Operations" Addition of the "GPS ALT" to the list of indications to check.
B
2
Addition of the "GPS ALT" to the list of indications to check.
B
3
Addition of the "GPS Alt" indication displayed in the event of the loss of the altimeter system redundancy.
A
1
Update of the Simultaneous Parallel Approach Operations procedure to cover the possibility of RNAV(GNSS)/RNAV(RNP)/GLS approaches and to provide an enhanced description.
PRO-SPO-PLP-SOH P 1/2 15 MAR 20
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FLIGHT CREW OPERATING MANUAL
PRELIMINARY PAGES - SUMMARY OF HIGHLIGHTS
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PRO-SPO-PLP-SOH P 2/2 15 MAR 20
PROCEDURES SPECIAL OPERATIONS A350
AWOPS
FLIGHT CREW OPERATING MANUAL
TAKEOFF Ident.: PRO-SPO-AWOPS-21400066.9001001 / 03 FEB 20 Applicable to: ALL
SUMMARY The Commander must be satisfied that Low Visibility Procedures are in force when Low Visibility Operations are announced. For further information Refer to FCTM/PR-NP-SOP-100 Taxi in AWOPS, Refer to FCTM/PR-NP-SOP-120 Takeoff in AWOPS and OM(A) Ch 8.4, All Weather Operations. LOW VISIBILITY TAKE-OFF 1. Return Alternate required within 2 hours, Cat 1 or better. 2. Check H.I. edge and C/L lighting available. 3. Check threshold and R/W end lighting available. 4. All RVR's at or above minima. 5. Pilot assessment: check minimum of 8 lights visible light based on 15m/50ft spacing. 6. Maximum crosswind 10 kts 7. Verify LS tuned on POSITION/NAVAIDS - TUNED FOR DISPLAY page (LS p/b ON). 8. Brief FSM regarding PEDS policy. 9. Select NO PED s/w to ON RTO ‐ ‐ ‐ ‐ ‐
Max autobrake. Maintain C/L. Call ATC. 9 00 m to go : C/L lights to alternating red/white. 300 m to go : C/L lights on red. AUTOLAND
Ident.: PRO-SPO-AWOPS-21400067.9001001 / 03 FEB 20 Applicable to: ALL
SUMMARY The Commander must be satisfied that Low Visibility Procedures are in force when Low Visibility Operations are announced. For further information, refer to OM(A) Ch 8.4, All Weather Operations.
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PRO-SPO-AWOPS P 1/4 03 FEB 20
PROCEDURES SPECIAL OPERATIONS A350
AWOPS
FLIGHT CREW OPERATING MANUAL
LANDING IN CAT 2/3 1. A/C autoland operative. Refer to Tech Log and Refer to LIM-AFS-20 Required Equipment for ILS CAT II/III Approach with Autoland. 2. Confirm runway approved for autoland (No Cat 3B on L status runways). 3. Both pilots to hold LV rating endorsements Captain as PF. 4. Airfield equipment operative (FCOM + NOTAMS/ATIS). 5. For ground equipment failure or downgrade, refer to Ch 8.4, All Weather Operations; Table 8.8 Failed or Downgraded Equipment - Effect on Landing Minima. 6. Autoland wind limits 35 kt HWC, 10 kt TWC, 20 kt XWC (USA15 kt XWC). 7. For CAT 3 NO DH; insert NO in the PERF APP page. 8. Touchdown RVR is always controlling. If reported the Midpoint and Stopend RVR are also controlling. 9. RVR's are controlling up to the Approach Ban Point. Once passed the Approach Ban Point, they are advisory only. 10. FAA: ‐ Cat 2 - Touchdown RVR is required and controlling for all operations. Midpoint RVR if reported, is controlling. Rollout RVR is required. Midpoint RVR may be substituted if Rollout RVR is u/s. ‐ Cat 3 - Three RVR's are required and controlling. Rollout is advisory if the Touchdown & Midpoint RVR's are 600ft or greater. 11. Brief FSM regarding PEDS policy. 12. Select NO PED s/w to ON 13. Approach briefing to include: a. b. c. d. e. f. g.
PF/PM duties. R/W and approach lighting expected (see below). Procedures for Rollout, runway clearance and taxi. G/A procedure. Alternates and fuel state. Seat position. Aircraft external lighting.
MINIMUM VISUAL REFERENCE AT DH ‐ CAT 2: 3 consecutive lights (approach, touchdown, centreline or runway edge) including a lateral element. ‐ CAT 3A: 3 consecutive lights (approach, touchdown, centreline or runway edge). ‐ CAT 3B with DH: 1 centreline light. ‐ CAT 3B no DH: NO visual contact required. VIR A350 FLEET FCOM
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PRO-SPO-AWOPS P 2/4 03 FEB 20
PROCEDURES SPECIAL OPERATIONS A350
AWOPS
FLIGHT CREW OPERATING MANUAL
AFTER LANDING Crews shall complete an Autoland Report eForm for all attempted autolands. In the event of an autoland missed approach or unsatisfactory autoland, a Tech Log entry shall also be made. Refer to FCTM/PR-NP-SOP-230 AWOPS After Landing. NON-NORMAL PROCEDURES Refer to PRO-NOR-SOP-180-C Approach Using XLS - Management of Degraded Equipment.
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FLIGHT CREW OPERATING MANUAL
AWOPS
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PROCEDURES SPECIAL OPERATIONS A350
NORTH ATLANTIC NAT HLA
FLIGHT CREW OPERATING MANUAL
NORTH ATLANTIC NAT HLA Ident.: PRO-SPO-NAT HLA-21400068.9001001 / 03 FEB 20 Applicable to: ALL
Refer to OM(C), Refer to PRO-SPO-PBN RNAV/RNP Capability. APPROACHING PBCS AIRSPACE 1. Oceanic waypoint track/distances checked in accordance with VSOPs. 2. Re-route track/distances checked and plotted if applicable. 3. ADS/CPDLC logged on. 4. Enter cleared Mach as a CONSTANT MACH SEGMENT. 5. WPT selected on EFIS control panel. 6. Select NORTH REF: TRUE. 7. Navigation accuracy check. Confirm default RNP 2.00 NM and EPU < RNP. 8. PBCS. Confirm proximity of adjacent tracks and PBCS structure. 9. Altimeter check. Check agreement within 200ft and altitude recorded on the OFP. 10. Contingency brief. PBCS track proximity; Planned vs Unplanned; Weather; TCAS/ ATSAW 11. Secondary flight plan(s). ENTERING PBCS AIRSPACE 1. Strategic Lateral Offset (SLOP) of 0/1/2 right as applicable. 2. Select/monitor 121.5/123.45 Mhz. 3. HF frequencies confirmed and SELCAL checked. 4. Squawk 2000 30 minutes after entry. 5. Plot in accordance with VSOPs. LEAVING PBCS AIRSPACE 1. Select NORTH REF: MAG 2. Delete SLOP if applicable. 3. Managed speed as applicable. 4. NAV Accuracy check. 5. Log off ADS/CPDLC as required. 6. Step climb as applicable.
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PRO-SPO-NAT HLA P 1/2 03 FEB 20
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NORTH ATLANTIC NAT HLA
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FLIGHT CREW OPERATING MANUAL
ICING CONSIDERATION FOR ETOPS CRITICAL FUEL RESERVES Ident.: PRO-SPO-ETOPS-00021720.0001001 / 09 MAR 16 Applicable to: ALL
The most critical scenario must be compensated for the greater of: A. The effect of airframe icing during 10 % of the time during which icing is forecast, including ice accumulation on unprotected surfaces, and the fuel used by engine and wing anti-ice during this period. B. Fuel for engine and wing anti-ice for the entire time during which icing is forecast. Note:
The ETOPS icing fuel reserve is always limited by (B).
Unless a reliable icing forecast is available, icing may be presumed to occur when the Total Air Temperature (TAT) is less than +10 °C (50 °F), or if the outside air temperature is between 0 °C (32 °F) and -20 °C (-4 °F) with a relative humidity of 55 % or more. DIVERSION DECISION MAKING Ident.: PRO-SPO-ETOPS-00021456.0001001 / 03 SEP 14 Applicable to: ALL
Diversion is required in the case of only one generator (either one VFG, or APU GEN) remaining available following a multiple failure. ABNORMAL AND EMERGENCY PROCEDURES Ident.: PRO-SPO-ETOPS-00021510.0001001 / 03 SEP 14 Applicable to: ALL
In the case of failure of one engine or two VFG in ETOPS segment: APU GEN (if available).............................................................................................................USE
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EXTENDED RANGE OPERATIONS
FLIGHT CREW OPERATING MANUAL
MAXIMUM DIVERSION DISTANCE Ident.: PRO-SPO-ETOPS-00021464.0002001 / 04 OCT 17 Applicable to: ALL
The following computation takes into account the below conditions: ‐ ISA conditions ‐ No wind ‐ Optimum diversion level after engine failure ‐ Single engine diversion speed schedule. Note:
Obstacles have not to be considered to determine if a route is or is not an ETOPS route. MAXIMUM DIVERSION DISTANCE
A/C WEIGHT AT SPEED FL FOR CRITICAL SCHEDULE DIVERSION POINT (x1000 KG) 190 190 210 180 230 180 250 180 MCT/330KT 270 170 290 170 310 160 190 210 210 210 230 210 MCT/310KT 250 200 270 190 VIR A350 FLEET FCOM
DIVERSION TIME (MIN)
60
120
180
439 439 438 436 435 432 430 432 431 429 427 423
866 865 860 856 855 848 843 852 850 844 840 830
1293 1290 1284 1277 1274 1265 1257 1270 1269 1261 1253 1237
D→
300
370
2000 2000 2000 2000 2000 2000
2500 2500 2500 2500 2500 2500
2000 2000 2000 2000
2500 2500 2500 2500
Continued on the following page
PRO-SPO-ETOPS P 2/4 03 FEB 20
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EXTENDED RANGE OPERATIONS
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Continued from the previous page
MAXIMUM DIVERSION DISTANCE
A/C WEIGHT AT SPEED FL FOR CRITICAL SCHEDULE DIVERSION POINT (x1000 KG) 290 190 310 170
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DIVERSION TIME (MIN)
60
120
180
300
370
417 415
822 810
1228 1205
2000 1995
2500 2455
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PRO-SPO-ETOPS P 4/4 03 FEB 20
PROCEDURES SPECIAL OPERATIONS A350
FERRY FLIGHT WITHOUT CCM
FLIGHT CREW OPERATING MANUAL
GENERAL Ident.: PRO-SPO-FFWCCM-21400048.9001001 / 29 OCT 18 Applicable to: ALL
This chapter applies to dispatch for a ferry flight without Cabin Crew Member (CCM). LIMITATIONS Ident.: PRO-SPO-FFWCCM-21400049.9001001 / 29 OCT 18 Applicable to: ALL
‐ Planned flight time must not exceed 4 hours (block time may exceed 4 hours). ‐ Flight Crew must adhere to ferry flight without CCM Special Operations Procedures. PROCEDURES Ident.: PRO-SPO-FFWCCM-21400050.9001001 / 03 FEB 20 Applicable to: ALL
The standard operating procedures given in PRO-NOR-SOP remain applicable for ferry flight without CCM. In addition the following actions must be performed. PREFLIGHT A cabin walk around shall be performed ensuring ‐ ‐ ‐ ‐ ‐ ‐ ‐
All loose items secured The toilets are checked and doors latched open All doors disarmed The CC be checked secure FDCR checked secure The flight deck door latched open Confirm location of Fire Containment Bag (FCB). Door R1; centre unit of A zone & Door R4; outboard stowage.
BEFORE START Before completing the before start check list ‐ Arm doors L1 and R1 ‐ Select PAX SYSTEMS and GALLEY p/b's on the overhead Electrical panel to OFF CRUISE Time permitting, a cabin walk around shall be performed. PARKING On completion of the parking check list VIR A350 FLEET FCOM
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PROCEDURES SPECIAL OPERATIONS A350
FLIGHT CREW OPERATING MANUAL
FERRY FLIGHT WITHOUT CCM
‐ Select PAX SYSTEMS and GALLEY p/b's on the overhead Electrical panel to AUTO. ‐ Disarm doors L1 and R1 (where applicable give a thumbs up signal to ground staff through the door window to confirm the doors are disarmed).
VIR A350 FLEET FCOM
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PRO-SPO-FFWCCM P 2/2 03 FEB 20
PROCEDURES SPECIAL OPERATIONS A350
PBN
FLIGHT CREW OPERATING MANUAL
GENERAL Applicable to: ALL Ident.: PRO-SPO-PBN-A-00021688.0001001 / 09 JAN 18
GENERAL The Performance-Based Navigation (PBN) concept implies that the aircraft follows the defined track with a requested navigation performance. PBN includes several types of operations named RNAV and RNP that apply to all flight phases. An operational approval from the Operators national authorities is sometimes required for some RNAV or RNP operations. The AFM provides regulatory compliances associated with PBN operations. Ident.: PRO-SPO-PBN-A-00021689.0001001 / 01 JUL 19
RNAV/RNP CAPABILITY Before the aircraft enters a RNAV/RNP airspace, RNAV/RNP capability is based on: ‐ The required RNAV/RNP equipment that is described in each RNAV/RNP section of the FCOM ‐ Navigation Accuracy HIGH displayed on the FMS POSITION/MONITOR page for RNAV operations ‐ NAV PRIMARY displayed on the FMS POSITION/MONITOR page for RNP operations ‐ RNP AR capability indicated on the ECAM for RNP AR operations ‐ Any specific local requirements published in the procedure chart or within the OM(C).
RNAV 10/RNP 10 Applicable to: ALL Ident.: PRO-SPO-PBN-B-00021698.0001001 / 09 JAN 18
GENERAL RNAV 10 operations correspond to RNP 10 operations. In RNAV 10 airspace, the aircraft is expected to fly for a long period of time outside radio navaid coverage. Required equipment and procedures for RNAV 10, described in this section, cover the navigation requirements of the Minimum Navigation Performance Specification (MNPS) operations.
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PRO-SPO-PBN P 1/14 03 FEB 20
PROCEDURES SPECIAL OPERATIONS A350
PBN
FLIGHT CREW OPERATING MANUAL Ident.: PRO-SPO-PBN-B-00006863.0001001 / 09 JAN 18
REQUIRED RNAV 10 EQUIPMENT The following is a list of the minimum navigation equipment that is required to enter RNAV 10 airspace: ‐ Two FMS ‐ Two IRS ‐ One GPS if the flight time outside radio navaid coverage is longer than either : • 6.2 h from the time of IRS ground alignment, or • 5.7 h from the time of the last radio position update. Ident.: PRO-SPO-PBN-B-00021699.0001001 / 09 JAN 18
PROCEDURE MANAGEMENT OF DEGRADED NAVIGATION • If one of the following messages appears: ‐ NAV PRIMARY LOST on only one ND/MFD ‐ NAV ACCURACY DOWNGRADED on only one ND/MFD, the flight crew can continue navigation with the side that provides the best position. • If NAV PRIMARY LOST appears on both NDs/MFDs, RNAV 10 operations can be continued: ‐ if radio navaids update is available, there is no time restriction ‐ if radio navaids update is not available, then RNAV 10 operations can be continued for 5.7 h from the time of the last position. Note:
VIR A350 FLEET FCOM
As per regulation, after 5.7 h, the navigation accuracy shall be considered as downgraded regardless of the current navigation accuracy that is displayed on the FMS POSITION/MONITOR page.
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• If the NAV GNSS/ACFT POS DISAGREE ECAM alert appears, the flight crew should check the position data using the FMS POSITION/MONITOR page. This action permits to identify the side that provides the best position. The flight crew can then continue navigation with the side that provides the best position. • If NAV ACCURACY DOWNGRADED appears on both NDs/MFDs, all the following is applicable: ‐ As per design, the FMS uses the default RNP value. This default value (2 NM in cruise, 1 NM in terminal area) is more restrictive than airspace required navigation performance. ‐ The flight crew can modify, on the FMS, the RNP default value and manually select a specific navigation accuracy in accordance with airspace requirement. When the aircraft leaves the airspace, the flight crew should set back the default value. • If NAV ACCURACY DOWNGRADED remains displayed, the flight crew should inform the ATC that RNAV 10 capability is lost.
RNAV 5/B-RNAV Applicable to: ALL Ident.: PRO-SPO-PBN-C-00021700.0001001 / 09 JAN 18
GENERAL RNAV 5 operations correspond to European B-RNAV operations. Ident.: PRO-SPO-PBN-C-00021701.0001001 / 08 NOV 18
REQUIRED RNAV 5 EQUIPMENT The following is a list of the minimum navigation equipment that is required to enter RNAV 5 airspace: ‐ One FMS ‐ One GPS, or one VOR/DME, or two DME for aircraft position update ‐ One IRS.
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PRO-SPO-PBN P 3/14 03 FEB 20
PROCEDURES SPECIAL OPERATIONS A350
PBN
FLIGHT CREW OPERATING MANUAL Ident.: PRO-SPO-PBN-C-00006868.0001001 / 09 JAN 18
PROCEDURE MANAGEMENT OF DEGRADED NAVIGATION • If one of the following messages appears: ‐ NAV PRIMARY LOST on only one ND/MFD ‐ NAV ACCURACY DOWNGRADED on only one ND/MFD, the flight crew can continue navigation with the side that provides the best position. • If one of the following messages appears: ‐ NAV PRIMARY LOST on both NDs/MFDs ‐ NAV GNSS/ACFT POS DISAGREE on the ECAM, the flight crew should check the position data with navaid raw data using the FMS POSITION/MONITOR page. This action permits to identify the side that provides the best position. The flight crew can then continue navigation with the side that provides the best position. • If NAV ACCURACY DOWNGRADED appears on both NDs/MFDs, all the following is applicable: ‐ As per design, the FMS uses the default RNP value. This default value (2 NM in cruise, 1 NM in terminal area) is more restrictive than airspace required navigation performance. ‐ The flight crew can modify, on the FMS, the RNP default value and manually select a specific navigation accuracy in accordance with airspace requirement. When the aircraft leaves the airspace, the flight crew should set back the default value. • If NAV ACCURACY DOWNGRADED remains displayed, the flight crew should inform the ATC that RNAV 5 capability is lost.
RNAV 2/EN-ROUTE RNAV Applicable to: ALL Ident.: PRO-SPO-PBN-K-00024578.0001001 / 09 JAN 18
GENERAL RNAV 2 operations correspond to En-Route RNAV operations. The AIP may specify that GPS equipment is required.
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PBN
FLIGHT CREW OPERATING MANUAL Ident.: PRO-SPO-PBN-K-00024579.0001001 / 09 JAN 18
REQUIRED RNAV 2 / EN-ROUTE RNAV EQUIPMENT The following is a list of the minimum navigation equipment that is required to enter RNAV 2 airspace: ‐ One FMS ‐ One GPS, or one VOR/DME, or two DME for aircraft navigation update ‐ Two IRS ‐ One FD in NAV mode. Ident.: PRO-SPO-PBN-K-00024580.0001001 / 09 JAN 18
PROCEDURE MANAGEMENT OF DEGRADED NAVIGATION • If one of the following messages appears: ‐ NAV PRIMARY LOST on only one ND/MFD ‐ NAV ACCURACY DOWNGRADED on only one ND/MFD, the flight crew can continue navigation with the side that provides the best position. • If one of the following messages appears: ‐ NAV PRIMARY LOST on both NDs/MFDs ‐ NAV GNSS/ACFT POS DISAGREE on the ECAM, the flight crew should check the position data with navaid raw data using the FMS POSITION/MONITOR page. This action permits to identify the side that provides the best position. The flight crew can then continue navigation with the side that provides the best position. • If NAV ACCURACY DOWNGRADED appears on both NDs/MFDs, the flight crew should inform the ATC that RNAV 2 capability is lost.
RNAV 1/P-RNAV TERMINAL RNAV Applicable to: ALL Ident.: PRO-SPO-PBN-D-00021702.0001001 / 31 OCT 18
GENERAL RNAV 1 operations correspond to P-RNAV - Terminal RNAV operations. The procedure chart may specify that GPS equipment is required.
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PRO-SPO-PBN P 5/14 03 FEB 20
PROCEDURES SPECIAL OPERATIONS A350
PBN
FLIGHT CREW OPERATING MANUAL Ident.: PRO-SPO-PBN-D-00006864.0001001 / 09 JAN 18
REQUIRED RNAV 1 EQUIPMENT The following is a list of the minimum navigation equipment that is required to enter RNAV 1 airspace: ‐ One FMS ‐ One GPS, or one VOR/DME, or two DME for aircraft navigation update ‐ Two IRS ‐ One FD in NAV mode. Ident.: PRO-SPO-PBN-D-00021703.0001001 / 20 FEB 19
PROCEDURE BEFORE THE AIRCRAFT ENTERS RNAV 1 AIRSPACE The flight crew must crosscheck the terminal procedure from the published charts with the FMS navigation database on the F-PLN page. IN RNAV 1 AIRSPACE The flight crew can only modify this terminal procedure if required by the ATC (e.g. DIR TO, radar vectoring, and insertion of waypoints from the navigation database).. At a published waypoint where no database constraint is shown, enter speed and altitude constraints from Jeppesen chart. Where chart shows a range of options dependant on the runway in use, enter speed and altitude constraints for the planned runway. MANAGEMENT OF DEGRADED NAVIGATION • If one of the following messages appears: ‐ NAV PRIMARY LOST on only one ND/MFD ‐ NAV ACCURACY DOWNGRADED on only one ND/MFD, the flight crew can continue navigation with the side that provides the best position. • If one of the following messages appears ‐ NAV PRIMARY LOST on both NDs/MFDs ‐ NAV GNSS/ACFT POS DISAGREE on the ECAM. the flight crew should check the position data with navaid raw data using the FMS POSITION/MONITOR page. This action permits to identify the side that provides the best position. The flight crew can then continue navigation with the side that provides the best position. • If NAV ACCURACY DOWNGRADED appears on both NDs/MFDs, the flight crew should inform the ATC that RNAV 1 capability is lost.
VIR A350 FLEET FCOM
←E
PRO-SPO-PBN P 6/14 03 FEB 20
PROCEDURES SPECIAL OPERATIONS A350
PBN
FLIGHT CREW OPERATING MANUAL
RNP 4 Applicable to: ALL Ident.: PRO-SPO-PBN-E-00021706.0001001 / 03 SEP 14
GENERAL In this airspace, the aircraft is expected to fly for a long period of time outside radio navaid coverage. Ident.: PRO-SPO-PBN-E-00006869.0001001 / 09 JAN 18
REQUIRED RNP 4 EQUIPMENT The following is a list of the minimum navigation equipment that is required to enter RNP 4 airspace: ‐ Two FMS ‐ One GPS ‐ Two IRS. Ident.: PRO-SPO-PBN-E-00021707.0001001 / 09 JAN 18
PROCEDURE MANAGEMENT OF DEGRADED NAVIGATION • If one of the following messages appears: ‐ NAV PRIMARY LOST on only one ND/MFD ‐ NAV ACCURACY DOWNGRADED on only one ND/MFD, the flight crew can continue navigation with the side that provides the best position. • If NAV GNSS/ACFT POS DISAGREE ECAM alert appears, the flight crew should check the position data using the FMS POSITION/MONITOR page. This action permits to identify the side that provides the best position. The flight crew can then continue navigation with the side that provides the best position. • If NAV ACCURACY DOWNGRADED appears on both NDs/MFDs, all the following is applicable: ‐ As per design, the FMS uses the default RNP value. This default value (2 NM in cruise, 1 NM in terminal area) is more restrictive than airspace required navigation performance. ‐ The flight crew can modify, on the FMS, the RNP default value and manually select a specific navigation accuracy in accordance with airspace requirement. When the aircraft leaves the airspace, the flight crew should set back the default value. • If NAV ACCURACY DOWNGRADED remains displayed, the flight crew should inform the ATC that RNP 4 capability is lost.
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F
PRO-SPO-PBN P 7/14 03 FEB 20
PROCEDURES SPECIAL OPERATIONS A350
PBN
FLIGHT CREW OPERATING MANUAL
RNP 2 IN OCEANIC AND REMOTE CONTINENTAL AREA Applicable to: ALL Ident.: PRO-SPO-PBN-I-00024575.0001001 / 09 JAN 18
In this airspace, the aircraft is expected to fly for a long period of time outside radio navaid coverage. Ident.: PRO-SPO-PBN-I-00024576.0001001 / 09 JAN 18
REQUIRED RNP 2 IN OCEANIC AND REMOTE CONTINENTAL AREA EQUIPMENT The following is a list of the minimum navigation equipment that is required to enter RNP 2 oceanic and remote continental airspace: ‐ Two FMS ‐ One GPS ‐ Two IRS. Ident.: PRO-SPO-PBN-I-00024577.0001001 / 09 JAN 18
PROCEDURE MANAGEMENT OF DEGRADED NAVIGATION • If one of the following messages appears: ‐ NAV PRIMARY LOST on only one ND/MFD ‐ NAV ACCURACY DOWNGRADED on only one ND/MFD, the flight crew can continue navigation with the side that provides the best position. • If NAV GNSS/ACFT POS DISAGREE ECAM alert appears, the flight crew should check the position data with navaid raw data using the FMS POSITION/MONITOR page. This action permits to identify the side that provides the best position. The flight crew can then continue navigation with the side that provides the best position. • If NAV ACCURACY DOWNGRADED appears on both NDs/MFDs, the flight crew should inform the ATC that RNP 2 capability is lost.
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G
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PBN
FLIGHT CREW OPERATING MANUAL
RNP 2 IN DOMESTIC AREA Applicable to: ALL Ident.: PRO-SPO-PBN-J-00024573.0001001 / 09 JAN 18
REQUIRED RNP 2 IN DOMESTIC AREA EQUIPMENT The following is a list of the minimum navigation equipment that is required to enter RNP 2 domestic airspace: ‐ One FMS ‐ One GPS ‐ Two IRS. Ident.: PRO-SPO-PBN-J-00024574.0001001 / 09 JAN 18
PROCEDURE • If one of the following messages appears: ‐ NAV PRIMARY LOST on only one ND/MFD ‐ NAV ACCURACY DOWNGRADED on only one ND/MFD, the flight crew can continue navigation with the side that provides the best position. • If one of the following messages appears: ‐ NAV PRIMARY LOST on both NDs/MFDs ‐ NAV GNSS/ACFT POS DISAGREE on the ECAM, the flight crew should check the position data with navaid raw data using the FMS POSITION/MONITOR page. This action permits to identify the side that provides the best position. The flight crew can then continue navigation with the side that provides the best position. • If NAV ACCURACY DOWNGRADED appears on both NDs/MFDs, the flight crew should inform the ATC that RNP 2 capability is lost.
RNP 1/TERMINAL RNP 1 BASIC RNP 1 Applicable to: ALL Ident.: PRO-SPO-PBN-F-00021708.0001001 / 09 JAN 18
GENERAL RNP 1 operations correspond to Terminal RNP 1 and Basic RNP 1.
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PRO-SPO-PBN P 9/14 03 FEB 20
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PBN
FLIGHT CREW OPERATING MANUAL Ident.: PRO-SPO-PBN-F-00021338.0001001 / 09 JAN 18
REQUIRED RNP 1 EQUIPMENT The following is a list of the minimum navigation equipment that is required to enter RNP 1 airspace: ‐ One FMS ‐ One GPS ‐ Two IRS ‐ One FD in NAV mode. Ident.: PRO-SPO-PBN-F-00021709.0001001 / 20 FEB 19
PROCEDURE BEFORE THE AIRCRAFT ENTERS RNP 1 AIRSPACE The flight crew must crosscheck the terminal procedure from the published charts with the FMS navigation database on the F-PLN page. IN RNP 1 AIRSPACE The flight crew can only modify the procedure if required by the ATC (e.g. DIR TO, radar vectoring, and insertion of waypoints from the navigation database). At a published waypoint where no database constraint is shown, enter speed and altitude constraints from Jeppesen chart. Where chart shows a range of options dependant on the runway in use, enter speed and altitude constraints for the planned runway. MANAGEMENT OF DEGRADED NAVIGATION • If one of the following messages appears: ‐ NAV PRIMARY LOST on only one ND/MFD ‐ NAV ACCURACY DOWNGRADED on only one ND/MFD, the flight crew can continue navigation with the side that provides the best position. • If NAV GNSS/ACFT POS DISAGREE ECAM alert appears, the flight crew should check the position data with navaid raw data using the FMS POSITION/MONITOR page. This action permits to identify the side that provides the best position. The flight crew can then continue navigation with the side that provides the best position. • If NAV ACCURACY DOWNGRADED appears on both NDs/MFDs, the flight crew should inform the ATC that RNP 1 capability is lost.
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PRO-SPO-PBN P 10/14 03 FEB 20
PROCEDURES SPECIAL OPERATIONS A350
PBN
FLIGHT CREW OPERATING MANUAL
RNP APCH/RNAV(GNSS) Applicable to: ALL Ident.: PRO-SPO-PBN-G-00021710.0001001 / 09 JAN 18
GENERAL RNP APCH operations correspond to approaches named RNAV(GNSS), or RNAV(GPS), or RNP. These approaches are also identified by LNAV, LNAV/VNAV, or LPV. Ident.: PRO-SPO-PBN-G-00006865.0001001 / 09 JAN 18
REQUIRED RNP APCH EQUIPMENT The minimum navigation equipment that is required to enter RNP APCH airspace is one FMS in NAV PRIMARY. Ident.: PRO-SPO-PBN-G-00021711.0001001 / 03 SEP 14
PROCEDURE Refer to PRO-NOR-SOP-180-C Approach Using XLS - General.
RNP AR / RNAV(RNP) Applicable to: ALL Ident.: PRO-SPO-PBN-H-00021712.0001001 / 04 SEP 14
GENERAL RNP AR operations correspond to RNAV(RNP) operations. For RNP AR operations, the flight crew should refer to the specific procedures published by the airline. The airline must obtain an operational approval and the flight crew must be qualified for this type of operations. To obtain this operational approval, the airline should refer to the AFM. The main procedure steps for RNP AR have been introduced in the Procedures of this FCOM and in the paragraph below. This does not relieve the airline from the need to provide the flight crew with tailored procedures when required. Ident.: PRO-SPO-PBN-H-00021349.0001001 / 08 NOV 18
REQUIRED RNP AR EQUIPMENT The following table presents the equipment, not monitored by the PRIMs, required to perform RNP AR operations:
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PRO-SPO-PBN P 11/14 03 FEB 20
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Required Equipment Not Monitored by the PRIMs MFDs TAWS KCCU (1)
RNP AR down to RNP 0.1 NM
RNP AR limited to RNP 0.3 NM
1 1 1 (1)
1 1 1 (1)
It is sufficient that KCCU has either an operative Cursor Control Device (CCD), or an operative keyboard. In addition, the following table presents equipment, as monitored by the PRIMs, to compute RNP AR capability:
Required Equipment Monitored by the PRIMs FMC PRIM with AP ((1)), FD and A/THR available EFIS ADIRS MMR FWC FCDC CP (1) L2
RNP AR down to RNP 0.1 NM
RNP AR limited to RNP 0.3 NM
3 2
2 1
2 3 2 1 1 1 EFIS/AFS CP and 1 MFD FCU backup
1 2 1 1 1 1 EFIS/AFS CP or 2 MFD FCU backup
For RNP AR operations strictly below RNP 0.3 NM, 1 AP must be engaged in NAV mode. Note:
The PRIMs also monitor navigation performance.
If the PRIMs detect a RNP AR capability lost or downgraded, the ECAM and/or the ND display dedicated indications. For more information, Refer to DSC-22-FMS-10-30-50 RNP AR Capability. Ident.: PRO-SPO-PBN-H-00021713.0001001 / 03 OCT 17
PROCEDURE Prior starting a RNP AR instrument procedure, check that: ‐ A complete alignment of the IRS has been performed before takeoff ‐ OAT and wind, as applicable, are within limits ‐ The FMS lateral and vertical F-PLN extracted from the navigation database is in agreement with the instrument procedure chart, particularly check that the correct RNP values displayed on F-PLN page ‐ The RNP AR capability is in accordance with the intended RNP AR procedure.
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PBN
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Airbus recommends the use of a Ground Based Prediction Program in order to check NAV PRIMARY availability at the estimated time of operation in either of the following cases: ‐ For RNP AR operations strictly below 0.15 NM and with less than 24 satellites available ‐ Within constrained environment areas. An environment area is considered constrained in the case of GPS masking in mountainous area (GPS mask angle > 5 °). L2 L1
Out of the two previous cases, NAV PRIMARY is available 100 % of the time worldwide. If obstacles, TERR must be selected on both NDs unless weather monitoring is required on one side. Airspeed and configuration must be adapted for the radius of turns in the procedure. DEPARTURE Before takeoff, check that: ‐ LDEV appears on PFDs,
L2 L1 L2
L1
L2 L1
Note:
When the aircraft is aligned on the runway, the LDEV indication is centered.
‐ XTK with two precision digits appears on NDs. Note:
When the aircraft is aligned on the runway, the XTK value is equal to zero. As a result, the XTK does not appear on the NDs.
When NAV is indicated armed on FMA and, 5 s after liftoff, select AP ON. Monitor lateral deviation on PFD or XTK on ND. Callout "CROSS TRACK" must be performed when XTK or LDEV is at or above 1/2 RNP or 0.1 NM (whichever occurs first). If XTK or LDEV increases toward the current RNP value, take over manually to fly back on the intended flight path and reengage AP as applicable. XTK pulses if its value is above the current RNP value. APPROACH Refer to PRO-NOR-SOP-180-C Approach Using APP-DES Guidance for RNP AR - General. GO-AROUND Refer to PRO-NOR-SOP-220 Go-Around - Go-Around Initiation.
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RVSM
FLIGHT CREW OPERATING MANUAL
RVSM REQUIREMENTS Applicable to: ALL Ident.: PRO-SPO-RVSM-GRVSMR-00021171.0001001 / 02 OCT 14
A350 aircraft systems are designed to comply with the design criteria of the JAA Temporary Guidance Leaflet No. 6 (JAA TGL 6 - EASA Regulations), and the FAA Guidance Material for RVSM operations No. 91 - RVSM. The AFM provides the statement of RVSM capability. Ident.: PRO-SPO-RVSM-GRVSMR-00021173.0001001 / 02 OCT 14
In addition to the RVSM capability statement provided in the AFM, Operators must obtain operational approval from their national airworthiness authorities, in order to operate within the RVSM airspace. The above-mentioned EASA and FAA documents also indicate the requirements for obtaining operational approval. Ident.: PRO-SPO-RVSM-GRVSMR-00021174.0001001 / 02 OCT 14
The RVSM regulation requires that the following equipment or functions be operative: ‐ Two ADRs (for altitude indication) ‐ One transponder For associated MEL dispatch conditions, Refer to MEL/MI-34-71 Transponder. ‐ One autopilot function For associated MEL dispatch conditions: ‐ Refer to MEL/MI-22-10 AP ‐ Refer to MEL/MI-22-10 Sidesticks and Rudder Pedal Locking Devices in AP Mode. ‐ Two PFDs (for altitude indication) ‐ One AFS CP channel or AFS CP backup (for the altitude target selection and the OP CLB or OP DES mode engagement) ‐ One FWS (for the altitude alert function). Ident.: PRO-SPO-RVSM-GRVSMR-00021175.0001001 / 02 OCT 14
MAXIMUM DIFFERENCES BETWEEN ALTITUDE INDICATIONS Flight Level FL 50 FL 100 FL 200 FL 290
VIR A350 FLEET FCOM
Speed or Mach Number 250 kt 250 kt 320 kt M 0.85
Comparison of Altitude Indications (ft) Difference between ADRs Difference between ISIS and (on the PFDs) ADRs (on the PFDs) 50 100 50 100 100 250 150 400 Continued on the following page
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PRO-SPO-RVSM P 1/4 15 MAR 20
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RVSM
FLIGHT CREW OPERATING MANUAL
FL 350 FL 430
Continued from the previous page Comparison of Altitude Indications (ft) 150 400 150 400
M 0.85 M 0.85
RVSM PROCEDURE Applicable to: ALL Ident.: PRO-SPO-RVSM-GRVSMP-00021172.0001001 / 02 OCT 14
For flights in RVSM airspace, the flight crew must apply the standard or abnormal and emergency procedures, in addition to the following RVSM procedures: Ident.: PRO-SPO-RVSM-GRVSMP-00021176.0001001 / 03 JAN 20
FLIGHT PREPARATION
1
The flight crew must take into account the conditions that may affect operations in RVSM airspace, including: L2 L1 L2
L1 L2
L1 L2
RVSM APPROVAL.................................................................................................................CHECK Verify that the aircraft is approved for RVSM operations. WEATHER.............................................................................................................................. CHECK Review the weather forecasted for the flight route. If severe turbulence is expected, this may affect the ability to maintain aircraft altitude. REQUIRED EQUIPMENT FOR RVSM..................................................................................CHECK Check that all the required equipment is operative (MEL). The flight crew should review the maintenance logs and forms, in order to ensure that the equipment required for RVSM is satisfactory. ALTITUDES............................................................................................................................ CHECK Check that the difference between each altitude indication (in the QNH reference) displayed on PFDs and the airport elevation is less than 75 ft. Check on PFDs that the indication ADR 1(2)(3) ALT, ISIS ALT, BKUP ALT or GPS ALT is not displayed. For more information, Refer to DSC-31-CDS-40-20-50 Altitude.
Ident.: PRO-SPO-RVSM-GRVSMP-00021177.0001001 / 03 JAN 20
IN FLIGHT
2
BEFORE ENTERING RVSM AIRSPACE L2
REQUIRED EQUIPMENT FOR RVSM...................................................................... OPERATIVE If any of the required equipment fails before the aircraft enters RVSM airspace, the flight crew must request new clearance, to avoid this airspace.
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PRO-SPO-RVSM P 2/4 15 MAR 20
PROCEDURES SPECIAL OPERATIONS A350
RVSM
FLIGHT CREW OPERATING MANUAL L1 L2
L1
L2 L1 L2
L1
L2
ALTITUDES........................................................................................................................ CHECK Check that the difference between the altitude indications on PFDs (in the standard baro setting) is less than the specified tolerance. For more information, Refer to PRO-SPO-RVSM Maximum Differences between Altitude Indications. Check on PFDs that the indication ADR 1(2)(3) ALT, ISIS ALT, BKUP ALT or GPS ALT is not displayed. For more information,Refer to DSC-31-CDS-40-20-50 Altitude. IN RVSM AIRSPACE AP.......................................................................................................................KEEP ENGAGED Ensure that autopilot is engaged for cruise, and for flight level changes. AP GUIDANCE.............................................................................................................. MONITOR During flight level transitions, do not exceed or go below the assigned flight level by more than 150 ft. Approximately every hour: ALTITUDES..................................................................................................................CHECK Check that the difference between the altitude indications on PFDs is less than the specified tolerance. For more information, Refer to PRO-SPO-RVSM Maximum Differences between Altitude Indications. Regular checks of the flight deck instruments should be sufficient. Check on PFDs that the indication ADR 1(2)(3) ALT, ISIS ALT, BKUP ALT or GPS ALT is not displayed. For more information, Refer to DSC-31-CDS-40-20-50 Altitude.
Ident.: PRO-SPO-RVSM-GRVSMP-00021178.0001001 / 02 OCT 14
AT THE END OF THE FLIGHT ANY MALFUNCTIONS or DEVIATIONS............................................................................. REPORT L2
Report any malfunction of the systems that enable the aircraft to maintain altitude, including: ‐ Any malfunction or loss of required equipment ‐ Any deviation involving the functions that enable the aircraft to maintain altitude.
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PROCEDURES SPECIAL OPERATIONS A350
RVSM
FLIGHT CREW OPERATING MANUAL Ident.: PRO-SPO-RVSM-GRVSMP-00021179.0001001 / 03 JAN 20
ABNORMAL AND EMERGENCY PROCEDURES
3
ATC........................................................................................................................................ NOTIFY When the aircraft is in RVSM airspace, the flight crew must notify the ATC of the following situations, because they may affect the aircraft's ability to maintain the flight level: ‐ The failure of both autopilots ‐ The loss of altimeter system redundancy: ‐ The same ADR altitude is displayed on both PFDs. This is indicated with ADR 1(2)(3) ALT indication on PFDs. ‐ The ISIS altitude is displayed on both PFDs. This is indicated with ISIS ALT indication on PFDs. ‐ The backup altitude is displayed on both PFDs. This is indicated with BKUP ALT indication on PFDs. ‐ The backup GPS altitude is displayed on both PFDs. This is indicated with GPS ALT indication on PFDs. ‐ An excessive discrepancy in altitude indications, and no way to identify the valid indication ‐ The failure of any other equipment, that affects the aircraft's ability to maintain the flight level ‐ The encounter of greater than moderate turbulence. If the flight crew cannot notify the ATC, or obtain ATC clearance, before deviating from the assigned flight level, they should follow the established contingency procedure and obtain ATC clearance as soon as possible. L2
Note:
Appendix 4 of the JAA TGL 6 (EASA Regulations), and Appendix 5 of the FAA 91-RVSM (FAA Regulations), provide detailed Operator guidelines, on the content and development of contingency procedures.
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PRO-SPO-RVSM P 4/4 15 MAR 20
PROCEDURES SPECIAL OPERATIONS A350
FLIGHT CREW OPERATING MANUAL
SIMULTANEOUS PARALLEL APPROACH OPERATIONS
OVERVIEW Ident.: PRO-SPO-PRM-00022173.0001001 / 03 JAN 20 Applicable to: ALL 1
Simultaneous Parallel Approach operations permit ILS/RNAV(GNSS)/RNAV(RNP)/GLS instrument approaches to be performed to dual or triple parallel runway configurations. Two types of simultaneous approaches to parallel or near-parallel instrument runways exist: ‐ Independent Approaches, where radar separation minima between aircraft on adjacent extended runway center lines are not prescribed and approaches are monitored to ensure aircraft do not enter a No Transgression Zone (NTZ). A Precision Runway Monitor (PRM) system which enables simultaneous close parallel approaches may also be employed. The air traffic controllers use the PRM system to monitor the aircraft position. ‐ Dependent Approaches, where radar separation minima between aircraft on adjacent extended runway center lines are prescribed and aircraft are staggered to provide separation from the adjacent final course. To perform Simultaneous Parallel Approach operations: ‐ The ATC and flight crew must satisfy specific training requirements. ‐ The ATC and the aircraft equipment must also comply with specific requirements.
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PRO-SPO-PRM P 1/4 15 MAR 20
PROCEDURES SPECIAL OPERATIONS A350
FLIGHT CREW OPERATING MANUAL
SIMULTANEOUS PARALLEL APPROACH OPERATIONS
BREAK OUT TURN AND CLIMB PROCEDURE Ident.: PRO-SPO-PRM-00022174.0001001 / 30 JAN 17 Applicable to: ALL
Simultaneously: AP............................................................................................................................... OFF BREAK OUT LEFT(RIGHT), HDG___, ALT___........................................... ANNOUNCE THR LEVERS...............................................................................TOGA, and back to CL L2 The SRS GA and the GA TRK modes engage. The THR CLB mode engages. The speed is managed. The speed target is the aircraft speed at SRS GA engagement. The FMS GO-AROUND phase becomes active. Thus, the FMS reinserts the approach. L1 TURN LEFT(RIGHT) AND CLIMB L2 As the situation is urgent, the flight crew should temporarily disregard the FD orders. L1 HDG___................................................................................................ TURN AND PULL L2 The GA TRK mode disengages, and the HDG mode engages. L1 ALT___................................................................................................. TURN AND PULL L2 The SRS GA mode disengages, and the OP CLB mode engages. The speed target becomes the FMS speed target of the CLIMB phase. L1 SPEED..............................................................................................PULL AND ADJUST L2 For the initial break out procedure, adjust the speed (e.g.160 kt), in order to avoid a significant acceleration, and an increase in workload.
PF PF PF
PM PM PM
L1
When established on the break out path: AP...........................................................................................................................ON PM L2 Before engaging the AP, ensure that the FD bar orders approximately correspond to the aircraft current path. L1 SPEED.........................................................................................SELECT AS RQRD PF FLAPS.........................................................................................................AS RQRD PM GEAR..........................................................................................................AS RQRD PM TCAS MODE SEL.......................................................................... TA/RA AS RQRD PM
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PRO-SPO-PRM P 2/4 15 MAR 20
PROCEDURES SPECIAL OPERATIONS A350
FLIGHT CREW OPERATING MANUAL
SIMULTANEOUS PARALLEL APPROACH OPERATIONS
BREAK OUT TURN AND DESCENT PROCEDURE Ident.: PRO-SPO-PRM-00022176.0001001 / 01 SEP 19 Applicable to: ALL
Simultaneously: AP............................................................................................................................... OFF PF TURN LEFT(RIGHT) AND MAINTAIN RATE OF DESCENT BREAK OUT LEFT(RIGHT), HDG___, ALT___........................................... ANNOUNCE PF L2 As the situation is urgent, the flight crew should temporarily disregard the FD orders. L1 HDG___................................................................................................ TURN AND PULL PM L2 The HDG mode engages. The vertical mode reverts to the V/S mode. The vertical speed target is the aircraft vertical speed at V/S engagement. L1 ALT___................................................................................................. TURN AND PULL PM L2 This action defines an altitude target. The OP DES mode and the THR IDLE mode engage. The speed target does not change. L1 V/S.....................................................................................................................MONITOR PM CAUTION
Depending on the speed target, the vertical speed may become excessive. If the rate of descent exceeds 1 000 ft/min, engage the V/S mode and limit the rate of descent to 1 000 ft/min.
When established on the break out path: AP...........................................................................................................................ON PM L2 Before engaging the AP, ensure that the FD bar orders approximately correspond to the aircraft current path. L1
When cleared by ATC: ALT___.............................................................................................................. TURN L2 Select an altitude target for go-around, in accordance with the ATC clearance. L1 THR LEVERS........................................................................ TOGA, and back to CL L2 The SRS GA and the GA TRK modes engage. The THR CLB mode engages. The speed is managed. The speed target is the aircraft speed at SRS GA engagement. The FMS GO-AROUND phase becomes active. L1 HDG___..............................................................................................................PULL L2 The GA TRK mode disengages, and the HDG mode engages. The SRS GA mode remains engaged, until ALT* engagement. L1 SPEED.........................................................................................SELECT AS RQRD FLAPS.........................................................................................................AS RQRD GEAR..........................................................................................................AS RQRD VIR A350 FLEET FCOM
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PF PF
PF PF PM PM
PRO-SPO-PRM P 3/4 15 MAR 20
PROCEDURES SPECIAL OPERATIONS A350
FLIGHT CREW OPERATING MANUAL
SIMULTANEOUS PARALLEL APPROACH OPERATIONS
TCAS MODE SEL.......................................................................... TA/RA AS RQRD
PM
CONSIDERATIONS CAUTION
‐ Do not over bank: the necessity to immediately respond is addressed by disconnecting A/P then smoothly applying bank, looking through F/D. ‐ Beware of high ROD beyond 1000 fpm in event of descending breakout. Consider that ROD will already be approx. 800 fpm if on G/S. ‐ Do not descend below cleared altitude.
Subsequent Actions When appropriate, re-engage A/P and clean up as required. e.g. a standard G/A procedure can be initiated by PF selecting TOGA then back to CL, then calling G/A Flaps. Ensure TCAS mode TA/RA selected. Note:
‐ It is recommended to initially target the following pitch altitudes. Pitch attitude Climbing +12 deg. Descending +2 deg (or current attitude if stabilised on G/S). Then adjust as required. ‐ A/THR will maintain SPEED mode. Brief accordingly if A/THR unserviceable.
TCAS Events ‐ Pilots should always immediately follow a TCAS RA whenever it is received. Should a TCAS RA be received before, during, or after an ATC breakout instructions is issued, the pilot should follow the RA, even if it conflicts with the climb/ descent portion of the breakout manoeuvre. ‐ Whilst following an RA, it is extremely important that the pilot also complies with the turn portion of the ATC breakout instruction unless safety is determined to be a factor.
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PROCEDURES SPECIAL OPERATIONS A350
FLIGHT CREW OPERATING MANUAL
PERFORMANCE-BASED COMMUNICATION AND SURVEILLANCE
GENERAL Ident.: PRO-SPO-PBCS-00024647.0001001 / 08 JUL 19 Applicable to: ALL
GENERAL The Performance-Based Communication and Surveillance (PBCS) concept provides performance requirements for communication and surveillance operations. PBCS supports the required performance for Air Traffic Management (ATM). The PBCS concept sets the following performance parameters: ‐ The Required Communication Performance (RCP) specification that defines performance requirements associated to a communication transaction. A communication transaction is performed between the ATC controller and the flight crew (clearance, flight information, or request). Performance requirements are specified for each part of the communication chain (aircraft, air/ground network, and ATC). The RCP specification impacts CPDLC and SATCOM voice communications on the aircraft. ‐ RCP specification is identified by a designator (e.g. RCP 240, RCP 400) where the value refers to the maximum time (in seconds) for the ATC controller to initiate an ATC clearance and receive the response from the flight crew. ‐ The Required Surveillance Performance (RSP) specification that defines performance requirements associated to the delivery of surveillance data. Performance requirements are specified for each part of the communication chain (aircraft, air/ground network, and ATC). The RSP specification impacts ADS-C and SATCOM voice communications on the aircraft. RSP specification is identified by a designator (e.g. RSP 180, RSP 400) where the value refers to a maximum time (in seconds) to deliver the surveillance data (e.g. aircraft position) to the ATC. The RCP and/or RSP specifications apply to a defined airspace, route, or procedure with optimized operations (e.g. reduced separations). REQUIREMENTS Ident.: PRO-SPO-PBCS-00024648.0001001 / 08 NOV 18 Applicable to: ALL
REQUIREMENTS Aircraft Performance Capability for Communication and Surveillance RCP 240 RCP 400
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Required Onboard Configuration to Maintain Aircraft Performance Capability Applications that Support Aircraft Communication Means that Support Performance Capability Applications CPDLC VHF datalink or SATCOM datalink CPDLC HF datalink Continued on the following page
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PRO-SPO-PBCS P 1/2 01 JUL 19
PROCEDURES SPECIAL OPERATIONS A350
FLIGHT CREW OPERATING MANUAL
Aircraft Performance Capability for Communication and Surveillance RSP 180 RSP 400
PERFORMANCE-BASED COMMUNICATION AND SURVEILLANCE Continued from the previous page Required Onboard Configuration to Maintain Aircraft Performance Capability Applications that Support Aircraft Communication Means that Support Performance Capability Applications ADS-C VHF datalink or SATCOM datalink ADS-C HF datalink
PROCEDURE Ident.: PRO-SPO-PBCS-00024649.0001001 / 02 MAR 18 Applicable to: ALL
MANAGEMENT OF DEGRADED DATALINK COMMUNICATION AND SURVEILLANCE In PBCS airspace with RCP/RSP requirements, if the ATC datalink application or the communication means associated to a required RCP/RSP level are lost, the flight crew should notify ATC that RCP and/or RSP capability are lost.
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PRO-SPO-PBCS P 2/2 01 JUL 19
LIMITATIONS
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LIMITATIONS PRELIMINARY PAGES A350
FLIGHT CREW OPERATING MANUAL
TABLE OF CONTENTS
LIM-INT Introduction LIM-AG Aircraft General LIM-AIR Air BLEED/COND/PRESS/VENT LIM-AFS Auto Flight System LIM-APU Auxiliary Power Unit LIM-CAB Cabin Systems LIM-CDS Control and Display System LIM-COM Communication LIM-DOORS Doors 1
LIM-ENG Engines LIM-F-CTL Flight Controls LIM-FUEL Fuel LIM-ICE_RAIN Ice and Rain Protection LIM-LG Landing Gear LIM-LT Lights LIM-NAV Navigation LIM-OIS Onboard Information System LIM-OXY Oxygen LIM-ROW-ROP ROW/ROP - BTV LIM-SURV Surveillance
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LIM-PLP-TOC P 1/2 03 FEB 20
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FLIGHT CREW OPERATING MANUAL
TABLE OF CONTENTS
LIM-T-PED Transmitting Portable Electronic Device
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SUMMARY OF HIGHLIGHTS
FLIGHT CREW OPERATING MANUAL
Localization Title
LIM-PLP-TOC Engines
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Toc Index
ID
Reason
1
Documentation update: Deletion of the "00016270.0003001 Shaft Speeds" documentary unit.
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SUMMARY OF HIGHLIGHTS
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M
(1)
Localization
LIST OF EFFECTIVE TEMPORARY DOCUMENTARY UNITS DU Title
LIM-ENG Oil Criteria: RR, TRENTXWB-97, L48350, L85312, L85350 Applicable to: G-VDOT, G-VRNB, G-VTEA Impacted DU: 00016269 Oil LIM-ENG Oil Criteria: RR, TRENTXWB-97, L48350, L85312 Applicable to: G-VJAM, G-VLUX, G-VPOP, G-VPRD Impacted DU: 00016269 Oil
DU identification
DU date
00025130.0007001
27 SEP 19
00025130.0006001
01 JUL 19
(1) Evolution code : N=New, R=Revised, E=Effectivity
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FLIGHT CREW OPERATING MANUAL
LIST OF EFFECTIVE TEMPORARY DOCUMENTARY UNITS
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LIMITATIONS INTRODUCTION
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FLIGHT CREW OPERATING MANUAL
PRELIMINARY PAGES - TABLE OF CONTENTS
Introduction...............................................................................................................................................................A
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FLIGHT CREW OPERATING MANUAL
PRELIMINARY PAGES - TABLE OF CONTENTS
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LIMITATIONS INTRODUCTION A350
FLIGHT CREW OPERATING MANUAL
INTRODUCTION Ident.: LIM-INT-00022265.0001001 / 17 AUG 17 Applicable to: ALL
This FCOM chapter contains operational limitations, related to the aircraft and associated systems. All references to airspeed, Mach and altitude relate to indicated airspeed, indicated Mach, and pressure altitude, unless otherwise noted.
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LIM-INT P 1/2 01 JUL 19
LIMITATIONS INTRODUCTION A350
FLIGHT CREW OPERATING MANUAL
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LIMITATIONS AIRCRAFT GENERAL
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FLIGHT CREW OPERATING MANUAL
PRELIMINARY PAGES - TABLE OF CONTENTS
LIM-AG-F_CTL Flight Maneuvering Load Acceleration Limits
Flight Maneuvering Load Acceleration Limits......................................................................................................... A
LIM-AG-OPS Operational Parameters
Environmental Envelope.......................................................................................................................................... A Airport Operations and Wind Limitations.................................................................................................................B Final Approach Slope on Airports with an Elevation of 8 000ft or Above...............................................................C
LIM-AG-SPD Speeds
Maximum Flaps/Slats Speeds................................................................................................................................. A Maximum Operating Speed VMO/MMO..................................................................................................................B Maximum Speeds with the Landing Gear Extended.............................................................................................. C Maximum Tire Speed.............................................................................................................................................. D Minimum Control Speeds........................................................................................................................................ E Wipers Maximum Operating Speed.........................................................................................................................F
1
LIM-AG-WGHT Weights
Weight Limitations....................................................................................................................................................A Takeoff Weight Limitations...................................................................................................................................... B Landing Weight Limitations..................................................................................................................................... C
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FLIGHT CREW OPERATING MANUAL
PRELIMINARY PAGES - TABLE OF CONTENTS
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PRELIMINARY PAGES - SUMMARY OF HIGHLIGHTS
FLIGHT CREW OPERATING MANUAL
Localization Title
Toc Index
ID
Reason
1
LIM-AG-OPS Maximum Crosswind for Takeoff and Landing
B
1
Documentation update: Deletion of the "PG02589 Weight Limitations" table of content entry. Documentation update: The "Weight Limitations" table of content entry moved from "PG02589" to "PP04506" Documentation update: The "Takeoff Weight Limitations" table of content entry moved from "PG02589" to "PP04506" Documentation update: The "Landing Weight Limitations" table of content entry moved from "PG02589" to "PP04506" Update of the landing maximum crosswind limit from 35kt up to 40kt for dry and damp conditions.
LIM-AG-PLP-TOC Weights
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PRELIMINARY PAGES - SUMMARY OF HIGHLIGHTS
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FLIGHT CREW OPERATING MANUAL
FLIGHT MANEUVERING LOAD ACCELERATION LIMITS
FLIGHT MANEUVERING LOAD ACCELERATION LIMITS Ident.: LIM-AG-F_CTL-00022150.0001001 / 06 NOV 14 Applicable to: ALL
Clean configuration...........................................................................................................-1 g to +2.5 g Other configurations.......................................................................................................... 0 g to +2.0 g
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LIMITATIONS AIRCRAFT GENERAL A350
FLIGHT CREW OPERATING MANUAL
FLIGHT MANEUVERING LOAD ACCELERATION LIMITS
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LIMITATIONS AIRCRAFT GENERAL A350
OPERATIONAL PARAMETERS
FLIGHT CREW OPERATING MANUAL
ENVIRONMENTAL ENVELOPE Applicable to: ALL Ident.: LIM-AG-OPS-ENV-00016262.0002001 / 24 MAR 17
Environmental Envelope
Ident.: LIM-AG-OPS-ENV-00022282.0001001 / 06 NOV 14
Minimum TAT............................................................................................................................... -52 °C
AIRPORT OPERATIONS AND WIND LIMITATIONS Applicable to: ALL Ident.: LIM-AG-OPS-ARPT_WIND-00022298.0001001 / 06 NOV 14
RUNWAY SLOPE Runway slope (mean) ..............................................................................................................± 2 %
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LIM-AG-OPS P 1/4 15 MAR 20
LIMITATIONS AIRCRAFT GENERAL A350
OPERATIONAL PARAMETERS
FLIGHT CREW OPERATING MANUAL Ident.: LIM-AG-OPS-ARPT_WIND-00022323.0002001 / 06 NOV 19 1
MAXIMUM CROSSWIND FOR TAKEOFF AND LANDING Runway Surface Conditions Runway State or / and Runway Contaminant Dry Damp Wet: Up to 3 mm (1/8”) of water Slush: Up to 3 mm (1/8”) Dry Snow: Up to 3 mm (1/8”) Wet Snow: Up to 3 mm (1/8”) Frost Compacted Snow: OAT at or below -15 °C Dry Snow: More than 3 mm (1/8”), up to 100 mm (4”) Wet Snow: More than 3 mm (1/8”), up to 30 mm (6/5”) Compacted Snow: OAT above -15 °C Dry Snow over Compacted Snow Wet Snow over Compacted Snow Slippery Wet
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PiRep(3) or ESF(4) -
Maximum Crosswind for Takeoff (Gust included) 35 kt (1)
35 kt
GOOD
(1)
27 kt
GOOD TO MEDIUM
(2)
20 kt
MEDIUM
(2)
Braking Performance Level FOR LANDING 6 - DRY
5 - GOOD
4 - GOOD TO MEDIUM
3 - MEDIUM
Maximum Crosswind for Landing (Gust included) 40 kt (1)
40 kt (1)
27 kt (2)
20 kt (2)
Continued on the following page
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LIMITATIONS AIRCRAFT GENERAL A350
OPERATIONAL PARAMETERS
FLIGHT CREW OPERATING MANUAL
Runway Surface Conditions Runway State or / and Runway Contaminant
PiRep(3) or ESF(4)
Water: More than 3 mm (1/8”), up to 15 mm (3/5”) Slush: More than 3 mm (1/8”), up to 15 mm (3/5”) Ice (cold and dry)
Maximum Crosswind for Takeoff (Gust included) 20 kt
MEDIUM TO POOR
(2)
15 kt
POOR
(2)
Continued from the previous page Braking Maximum Performance Crosswind Level for Landing FOR LANDING (Gust included)
20 kt
2 - MEDIUM TO POOR
(2)
15 kt
1 - POOR
(2)
(1)
Maximum certified crosswind values. For maximum wind limitations for automatic approach, landing and roll-out, Refer to LIM-AFS-20 General.
(2)
For contaminated runways, the maximum crosswind values given in the above table are recommended values based on computations.
(3)
PiRep: Pilot Report of Braking Action
(4)
ESF: Estimated Surface Friction
Ident.: LIM-AG-OPS-ARPT_WIND-21400059.9001001 / 31 OCT 18
TAKEOFF LIMITATIONS ON CONTAMINATED RUNWAYS Maximum Thrust (TOGA) must be used for all takeoffs. Takeoff is not recommended on the following runway conditions: ‐ Wet ice, ‐ Water on top of Compacted Snow, ‐ Dry Snow or Wet Snow over Ice. Ident.: LIM-AG-OPS-ARPT_WIND-00022286.0002001 / 04 DEC 14
MAXIMUM TAILWIND FOR TAKEOFF Maximum tailwind for takeoff......................................................................................................15 kt Ident.: LIM-AG-OPS-ARPT_WIND-00022294.0001001 / 06 NOV 14
MAXIMUM TAILWIND FOR LANDING Maximum tailwind for landing..................................................................................................... 10 kt
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LIMITATIONS AIRCRAFT GENERAL A350
OPERATIONAL PARAMETERS
FLIGHT CREW OPERATING MANUAL Ident.: LIM-AG-OPS-ARPT_WIND-00022287.0001001 / 06 NOV 14
MAXIMUM WIND FOR CABIN AND CARGO DOORS OPERATION Maximum wind for cabin and cargo doors operation ................................................................ 40 kt The cabin and cargo doors must be closed before the wind reaches 60 kt. FINAL APPROACH SLOPE ON AIRPORTS WITH AN ELEVATION OF 8 000FT OR ABOVE Ident.: LIM-AG-OPS-00024250.0002001 / 24 MAY 17 Applicable to: ALL
On airports with an elevation of 8 000 ft or above: Maximum final approach slope: 4 °.
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LIMITATIONS AIRCRAFT GENERAL A350
SPEEDS
FLIGHT CREW OPERATING MANUAL
MAXIMUM FLAPS/SLATS SPEEDS Ident.: LIM-AG-SPD-00005762.0002001 / 30 MAY 17 Applicable to: ALL
FLAPS Lever Position
Configuration on Slat/Flap display
2 3 FULL
1 1+F 2 3 FULL
0 1
(1)
Max Speed
Flight Phase
VMO/MMO 260 kt 231 kt (1) 219 kt 206 kt 192 kt
CRUISE HOLDING TAKEOFF / APPROACH TAKEOFF / APPROACH TAKEOFF / APPROACH / LANDING LANDING
In CONF 1+F, when the aircraft reaches a speed of 221 kt, the Automatic Retraction System (ARS) automatically retracts the flaps to CONF 1. MAXIMUM OPERATING SPEED VMO/MMO
Ident.: LIM-AG-SPD-00005760.0001001 / 06 NOV 14 Applicable to: ALL
VMO.............................................................................................................................................. 340 kt MMO.................................................................................................................................................0.89
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LIM-AG-SPD P 1/4 03 FEB 20
LIMITATIONS AIRCRAFT GENERAL A350
SPEEDS
FLIGHT CREW OPERATING MANUAL
VMO/MMO
The maximum operating limit speed VMO/MMO must not be intentionally exceeded in any regime of flight. MAXIMUM SPEEDS WITH THE LANDING GEAR EXTENDED Ident.: LIM-AG-SPD-00005764.0002001 / 17 NOV 17 Applicable to: ALL
Maximum speed with the landing gear extended (VLE/MLE).........................................250 kt / M 0.55 Maximum speed with the landing gear operating (VLO/MLO)........................................250 kt / M 0.55 Maximum speed for landing gear gravity extension (VLO/MLO=VLE/MLE)................... 250 kt / M 0.55 MAXIMUM TIRE SPEED Ident.: LIM-AG-SPD-00022117.0002001 / 30 OCT 18 Applicable to: ALL
Maximum ground speed.............................................................................................................. 213 kt Maximum ground speed if trampling arrestor cables.................................................................... 60 kt
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LIMITATIONS AIRCRAFT GENERAL A350
SPEEDS
FLIGHT CREW OPERATING MANUAL
MINIMUM CONTROL SPEEDS Ident.: LIM-AG-SPD-00005763.0002001 / 06 SEP 17 Applicable to: ALL
MINIMUM CONTROL SPEED FOR LANDING (VMCL) VMCL........................................................................................................................................ 123 kt MINIMUM CONTROL SPEEDS IN THE AIR (VMCA) AND ON THE GROUND (VMCG) Altitude (ft)
VMCA (kt IAS)
-2 000 0 2 000 4 000 6 000 8 000 10 000 12 000 14 000
134 134 130 125 121 116 112 107 103
CONF 1+F 132 131 128 123 120 116 112 109 105
VMCG (kt IAS) CONF 2 132 131 128 123 120 116 112 109 105
CONF 3 131 131 127 123 119 115 112 108 105
WIPERS MAXIMUM OPERATING SPEED Ident.: LIM-AG-SPD-00022119.0001001 / 06 NOV 14 Applicable to: ALL
Maximum speed............................................................................................................................230 kt
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WEIGHTS
FLIGHT CREW OPERATING MANUAL
WEIGHT LIMITATIONS Ident.: LIM-AG-WGHT-00016264.0036001 / 08 APR 19 Applicable to: ALL
Multiple Weight Variants are certified. A placard installed in the cockpit must indicate the current MTOW. Maximum Taxi Weight Maximum Takeoff Weight (MTOW) Maximum Landing Weight (MLW) Maximum Zero Fuel Weight (MZFW) Minimum Weight for Takeoff Minimum Weight for Landing and in Flight Note:
308 900 kg
681 007 lb
233 000 kg
513 677 lb
308 000 kg 220 000 kg 155 000 kg 138 000 kg
679 023 lb 485 017 lb 341 717 lb 304 238 lb
‐ MTOW, MLW, and MZFW vary with the center of gravity. ‐ In exceptional conditions (in-flight turnback or diversion), an immediate landing at a weight above maximum landing weight is permitted, provided that the flight crew follows the overweight landing procedure.
Maximum Taxi Weight Maximum Takeoff Weight (MTOW) Maximum Landing Weight (MLW) Maximum Zero Fuel Weight (MZFW) Minimum Weight for Takeoff Minimum Weight for Landing and in Flight Note:
Weight Variant: WV 000
Weight Variant: WV 010 300 900 kg
663 371 lb
233 000 kg
513 677 lb
300 000 kg 220 000 kg 155 000 kg 138 000 kg
661 386 lb 485 017 lb 341 717 lb 304 238 lb
‐ MTOW, MLW, and MZFW vary with the center of gravity. ‐ In exceptional conditions (in-flight turnback or diversion), an immediate landing at a weight above maximum landing weight is permitted, provided that the flight crew follows the overweight landing procedure.
Maximum Taxi Weight Maximum Takeoff Weight (MTOW) Maximum Landing Weight (MLW) Maximum Zero Fuel Weight (MZFW)
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Weight Variant: WV 009 290 900 kg
641 324 lb
233 000 kg
513 677 lb
290 000 kg 220 000 kg
A→
639 340 lb 485 017 lb Continued on the following page
LIM-AG-WGHT P 1/2 06 FEB 20
LIMITATIONS AIRCRAFT GENERAL A350
WEIGHTS
FLIGHT CREW OPERATING MANUAL
Continued from the previous page
Minimum Weight for Takeoff Minimum Weight for Landing and in Flight Note:
155 000 kg
341 717 lb
138 000 kg
304 238 lb
‐ MTOW, MLW, and MZFW vary with the center of gravity. ‐ In exceptional conditions (in-flight turnback or diversion), an immediate landing at a weight above maximum landing weight is permitted, provided that the flight crew follows the overweight landing procedure. TAKEOFF WEIGHT LIMITATIONS
Ident.: LIM-AG-WGHT-00024408.0004001 / 28 SEP 17 Applicable to: ALL
TAKEOFF WEIGHT LIMITATIONS Condition TOW below 170 t (374 786 lb) and crosswind above 20 kt TOW below 175 t (385 809 lb) and takeoff performed in CONF 3
Limitation D12 or D16 derated takeoff is mandatory FLEX takeoff is not permitted
LANDING WEIGHT LIMITATIONS Ident.: LIM-AG-WGHT-00024471.0001001 / 28 SEP 17 Applicable to: ALL
LANDING WEIGHT LIMITATIONS Condition Landing weight below 150 t (330 694 lb)
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Limitation CONF 3 landing is mandatory
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PRELIMINARY PAGES - TABLE OF CONTENTS
APU Bleed Use with HP Air Start Unit................................................................................................................... A Differential Pressure................................................................................................................................................ B Packs Use with LP Air Conditioning Unit................................................................................................................C Ram Air Inlet............................................................................................................................................................D
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PRELIMINARY PAGES - TABLE OF CONTENTS
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APU BLEED USE WITH HP AIR START UNIT Ident.: LIM-AIR-00022007.0001001 / 06 NOV 14 Applicable to: ALL
Do not use bleed air from the APU BLEED and from the HP Air Start Unit at the same time, to prevent any adverse effect on the Bleed Air System (BAS). DIFFERENTIAL PRESSURE Ident.: LIM-AIR-00017979.0001001 / 06 NOV 14 Applicable to: ALL
Maximum positive differential pressure.................................................................................. 10.29 PSI Maximum negative differential pressure..................................................................................-0.72 PSI L2 These two operating limitations correspond to the settings of the Negative Relief Valve and the Overpressure Relief Valve. PACKS USE WITH LP AIR CONDITIONING UNIT Ident.: LIM-AIR-00018078.0001001 / 06 NOV 14 Applicable to: ALL
Do not use conditioned air from the packs and from the LP Air Conditioning Unit at the same time, to prevent any adverse effect on the Air Conditioning system. RAM AIR INLET Ident.: LIM-AIR-00018064.0001001 / 06 NOV 14 Applicable to: ALL
The ram air inlet opens, only if the differential pressure is below 2 PSI.
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LIM-AFS-10 General
General.....................................................................................................................................................................A Use of FLS and FLS Capability.............................................................................................................................. B Use of APP-DES Mode...........................................................................................................................................C Use of NAV mode................................................................................................................................................... D
LIM-AFS-20 Automatic Approach, Automatic Landing and Automatic Roll-Out
General.....................................................................................................................................................................A Special Authorization CAT I (SA CAT I)................................................................................................................. B Lower Than Standard CAT I (LTS CAT I).............................................................................................................. C ILS CAT I and ILS CAT II/III with no LVP.............................................................................................................. D GLS CAT I............................................................................................................................................................... E Special Authorization CAT II (SA CAT II)............................................................................................................... F Other Than Standard CAT II (OTS CAT II)............................................................................................................ G ILS CAT II/III............................................................................................................................................................H Required Equipment for GLS CAT I Approach with Autoland.........................................................................I Required Equipment for ILS CAT II/III Approach with Autoland..............................................................................J
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PRELIMINARY PAGES - TABLE OF CONTENTS
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LIMITATIONS AUTO FLIGHT SYSTEM A350
GENERAL
FLIGHT CREW OPERATING MANUAL
GENERAL Applicable to: ALL Ident.: LIM-AFS-10-G10-00013044.0001001 / 06 NOV 14
AUTOPILOT The autopilot can be used with the following minimum values: At takeoff After manual go-around In approach with F-G/S mode In approach with V/S or FPA mode In approach with APP-DES mode In approach with G/S mode and APPR1 on FMA In approach with G/S mode and one of the following on FMA: ‐ LAND1 ‐ LAND2 ‐ LAND3 SINGLE ‐ LAND3 DUAL. In all other flight phases (1)
At least 5 s after lift-off 100 ft AGL 200 ft AGL 200 ft AGL 200 ft AGL 160 ft AGL 0 ft AGL if autoland 80 ft AGL if manual landing (1)
500 ft AGL
This value is an operating limitation recommended by Airbus (not an AFM limitation). The use of AP or FD in OP DES or DES is not permitted, if the AFS CP selected altitude is set below MDA(H)/DA(H), or 500 ft AGL, whichever is higher.
Ident.: LIM-AFS-10-G10-00005745.0001001 / 06 NOV 14
AUTOTHRUST All AP/FD modes may be used with or without autothrust, except if specified. Autothrust may be used with, or without AP/FD, in selected or managed speed/Mach. Ident.: LIM-AFS-10-G10-00022271.0002001 / 06 NOV 14
FLIGHT MANAGEMENT ‐ The FMS lateral and vertical navigation is approved for after takeoff, en route and terminal area operations and for instrument approach procedures and missed approach procedures. ‐ The FLS (FMS Landing System) function is certified for instrument approach procedures using FMS navigation alone or FMS navigation associated with LOC, or ILS (G/S out), or LOC-BC. The FLS function is not certified for ILS, GLS, IGS, LDA, and SDF approaches or for RNAV(GNSS) final approaches with LP/LPV Minimum. ‐ The SLS function is certified for RNAV(GNSS) final approaches with LP/LPV Minimum.
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LIM-AFS-10 P 1/6 01 JUL 19
LIMITATIONS AUTO FLIGHT SYSTEM A350
GENERAL
FLIGHT CREW OPERATING MANUAL
‐ The FMS lateral navigation (NAV mode) is certified for instrument approach procedures except ILS, GLS, IGS, ILS (G/S out), LOC, LOC-BC, LDA, SDF final approaches and RNAV(GNSS) final approaches with LNAV/VNAV Minimum or LP/LPV Minimum. ‐ Approval of the FMS is based on the assumption that the navigation database is validated for intended use. The airworthiness approval does not account for database accuracy or compatibility. Obstacle clearance and adherence to airspace constraints remains a flight crew responsibility. Fuel, time predictions/performance information is provided for advisory purpose only. For instrument procedures not coded in the WGS 84 coordinate system, the GPS must be deselected, unless the shift between the local coordinate system and the WGS 84 is found acceptable for the intended operation. Note:
1. The assessment of this shift can be done: ‐ In flight, monitoring the navaid raw data in non RNAV procedures ‐ On ground performing a GNSS survey of the procedure waypoints. 2. The navigation performance for RNAV(GNSS) procedures is demonstrated based on WGS 84 coordinates.
Ident.: LIM-AFS-10-G10-00021668.0001001 / 06 NOV 14
NAVIGATION PERFORMANCE For Advanced RNP operations with RF leg capability requiring RNP strictly below 1 NM, the FD and/or AP must be engaged and the numerical cross track deviations must be monitored on navigation display. The above limitation does not concern RNP AR operations. With NAV PRIMARY: The RNP accuracy is: With AP ON ‐ In NAV (all phases) ‐ In F-LOC (approach phase)
En route Terminal area In approach
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With AP OFF and FD ON
With AP OFF and FD OFF
‐ In NAV (all phases) ‐ In F-LOC (approach phase)
1 NM
1 NM
1 NM
0.3 NM
0.3 NM
0.5 NM with F-LOC deviation. Not authorized without F-LOC deviation.
0.5 NM
0.5 NM
←A→
0.5 NM
LIM-AFS-10 P 2/6 01 JUL 19
LIMITATIONS AUTO FLIGHT SYSTEM A350
GENERAL
FLIGHT CREW OPERATING MANUAL
For RNP AR: The minimum approved/certified RNP AR level is 0.10 NM. RNP AR performance requires AP ON and the following modes: ‐ Departure in NAV mode ‐ Initial / Intermediate approach in NAV mode ‐ Final approach in NAV and APP-DES modes ‐ Missed approach in NAV mode. Note:
1. For RNP AR operations limited to RNP 0.3 NM only, the flight crew may consider AP OFF and FD ON. However, Airbus recommends the use of AP for all RNP AR operations. 2. The transition from a RNP AR VIA to an approach which is not RNP AR is submitted to operational approval.
Without NAV PRIMARY The navigation accuracy is demonstrated provided that the appropriate RNP value is checked or entered on the MFD and HIGH accuracy is displayed.
USE OF FLS AND FLS CAPABILITY Applicable to: ALL Ident.: LIM-AFS-10-20-00022273.0001001 / 06 NOV 14
APPROACH BASED ON RADIO NAVAIDS A navaids approach (e.g. VOR/DME) may be flown with the FLS provided that: ‐ F-APP capability is displayed on FMA. In this case, the reference navaids may be unserviceable, or the airborne radio equipment may be inoperative, or not installed, provided an operational approval is obtained. ‐ F-APP + RAW capability is displayed on FMA. In this case, the reference navaids and the corresponding airborne radio equipment must be serviceable, tuned and monitored during the approach. An ILS (G/S out), ILS-BC (G/S out), LOC, LOC-BC approach may be flown with the lateral LOC (LOC-BC) mode and with the F-G/S mode of FLS function provided that: ‐ F-APP capability is displayed on FMA. In this case, the reference navaids used for the vertical path validation must be tuned and checked at final descent point. ‐ F-APP + RAW capability is displayed on FMA. In this case, the reference navaids used for the vertical path validation must be tuned and checked at final descent point and monitored during the approach.
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LIM-AFS-10 P 3/6 01 JUL 19
LIMITATIONS AUTO FLIGHT SYSTEM A350
GENERAL
FLIGHT CREW OPERATING MANUAL
RNAV(GNSS) APPROACH An RNAV(GNSS) approach with LNAV minimum may be flown with the FLS provided that the F-APP capability is displayed on FMA. An RNAV(GNSS) approach with LNAV/VNAV minimum must be flown with the FLS provided that the F-APP capability is displayed on FMA. Note:
The RNAV(GNSS) approach limitations and procedures must be used to perform an RNAV approach for which the GNSS is not required.
Ident.: LIM-AFS-10-20-00022275.0001001 / 06 NOV 14
FLS CAPABILITY The following table presents the FLS capability, as monitored by the FG, in accordance with required conditions: Required Conditions FMC Navigation Accuracy MMR With FLS function MMR With GNSS reception ADIRU FMS and GNSS position consistency
1
FLS Capability F-APP + RAW 1 ACCURACY HIGH in one FMS 1
F-APP 1 NAV PRIMARY in one FMS 1
0
0
1
1 No requirement
1 Yes
2 Yes
RAW ONLY 1 No requirement
USE OF APP-DES MODE Ident.: LIM-AFS-10-00022277.0001001 / 06 NOV 14 Applicable to: ALL
The use of APP-DES vertical mode is certified for RNAV(RNP) final approaches, provided that the RNP AR capability is compliant with the selected procedure. The use of APP-DES vertical mode is not permitted for RNAV(GNSS) with LNAV or LNAV/VNAV or LP/LPV minima, or for approaches based on navaids.
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LIM-AFS-10 P 4/6 01 JUL 19
LIMITATIONS AUTO FLIGHT SYSTEM A350
GENERAL
FLIGHT CREW OPERATING MANUAL
USE OF NAV MODE Ident.: LIM-AFS-10-00022272.0001001 / 06 NOV 14 Applicable to: ALL
AFTER TAKEOFF NAV mode may be used after takeoff provided that: ‐ NAV PRIMARY is available, or ‐ The flight crew check of FMS runway position update. IN TERMINAL AREA NAV mode may be used in terminal area provided that: ‐ NAV PRIMARY is available, or ‐ HIGH accuracy is displayed and the appropriate RNP is checked or entered on the MFD, or ‐ Aircraft navigation is crosschecked with navaids. APPROACH BASED ON RADIO NAVAIDS A navaids approach (e.g. VOR/DME) may be flown in NAV mode provided that: ‐ NAV PRIMARY is available. In this case, the reference navaids may be unserviceable, or the airborne radio equipment may be inoperative, or not installed, provided that an operational approval is obtained ‐ NAV PRIMARY is not available. In this case, the reference navaids and the corresponding airborne radio equipment must be serviceable, tuned and monitored during the approach. RNAV(GNSS) APPROACH An RNAV(GNSS) approach with LNAV minimum may be flown in NAV mode provided that NAV PRIMARY is available.
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LIMITATIONS AUTO FLIGHT SYSTEM A350
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GENERAL
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LIMITATIONS AUTO FLIGHT SYSTEM A350
FLIGHT CREW OPERATING MANUAL
AUTOMATIC APPROACH, AUTOMATIC LANDING AND AUTOMATIC ROLL-OUT
GENERAL Ident.: LIM-AFS-20-00021666.0005001 / 08 APR 19 Applicable to: ALL
For automatic landing, one autopilot at least must be engaged in APPR mode, LAND1, LAND2 or LAND3 SINGLE or LAND3 DUAL capability must be displayed on the FMA and the configuration must be CONF 3 or CONF FULL. Note:
Automatic approach and automatic landing have been demonstrated with one engine inoperative in CONF 3 and CONF FULL, if engine out procedures are completed before reaching 1 000 ft in approach.
Minimum aircraft weight: 165 000 kg (363 763 lb). Note:
Depending on the situation (e.g. emergency or other) and provided that the runway is approved for automatic landing, the flight crew can decide to perform an autoland up to the maximum takeoff weight.
AIRPORT CONDITIONS Automatic landing is demonstrated, as follows: ‐ With an airport elevation up to 9 200 ft ‐ With a glide slope angle between -2.5 ° and -3.5 °. RUNWAY CONDITIONS CAT IIIB operation is not authorized on contaminated runways. The performance of the ROLL OUT mode is demonstrated on dry and wet runways (up to 3 mm of water). The roll out performance on contaminated runways has not been demonstrated and cannot be assured.
L2 L1
Therefore, if the flight crew aims to keep AP engaged during rollout on a contaminated runway, they must apply all of the following: ‐ Consider the maximum crosswind value that is the most restrictive (associated either with the runway condition, or with autoland) For more information on the maximum crosswind value for landing associated with the runway condition, Refer toRefer to FCOM/Maximum Crosswind for Takeoff and Landing. ‐ Be prepared to disengage the AP and take over manually should ROLL OUT directional control become inadequate.
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LIM-AFS-20 P 1/10 03 FEB 20
LIMITATIONS AUTO FLIGHT SYSTEM A350
AUTOMATIC APPROACH, AUTOMATIC LANDING AND AUTOMATIC ROLL-OUT
FLIGHT CREW OPERATING MANUAL
WEATHER CONDITIONS Maximum wind conditions: ‐ Maximum tailwind: Refer to LIM-AG-OPS Maximum Tailwind for Landing ‐ Maximum headwind: 30 kt ‐ Maximum crosswind: 30 kt Note:
Wind limitation is based on the surface wind reported by the tower. If the ND indicates a current wind speed that exceeds the above-noted autoland limitations, but the tower reports a surface wind speed within the limitations, then the flight crew can perform an automatic landing. If the tower reports a surface wind speed beyond the limits, the flight crew can only perform a CAT I or CAT II automatic approach without autoland. SPECIAL AUTHORIZATION CAT I (SA CAT I)
Ident.: LIM-AFS-20-00022924.0001001 / 06 NOV 18 Applicable to: ALL
APPLICABLE TO AIRCRAFT EQUIPPED WITH HUD Minimum decision height........................................................................................................... 150 ft At least one autopilot must be engaged down to DH in APPR mode and LAND2, LAND3 SINGLE or LAND3 DUAL must be displayed on the FMA. The flight crew must use the HUD to monitor the approach. The flight crew should perform a manual landing. LOWER THAN STANDARD CAT I (LTS CAT I) Ident.: LIM-AFS-20-00022925.0001001 / 06 NOV 18 Applicable to: ALL
APPLICABLE TO AIRCRAFT EQUIPPED WITH HUD Minimum decision height........................................................................................................... 200 ft The flight crew must use the HUD to monitor the approach. The flight crew should perform a manual landing. ILS CAT I AND ILS CAT II/III WITH NO LVP Ident.: LIM-AFS-20-00022354.0001001 / 06 NOV 14 Applicable to: ALL
Automatic landing system performance is demonstrated with CAT II and CAT III ILS airport installation. However, ILS CAT I automatic landing can be performed on ILS CAT I airport installation,
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LIM-AFS-20 P 2/10 03 FEB 20
LIMITATIONS AUTO FLIGHT SYSTEM A350
AUTOMATIC APPROACH, AUTOMATIC LANDING AND AUTOMATIC ROLL-OUT
FLIGHT CREW OPERATING MANUAL
or on CAT II/III airport installation when Low Visibility Procedure (LVP) are not applicable, provided that the following precautions are taken: ‐ The airline checked that the ILS beam quality, and the effect of the terrain profile before the runway have no adverse effect on autopilot guidance. Particularly, the effect of terrain profile within 300 m before the runway threshold must be evaluated ‐ The flight crew is aware that LOC or G/S beam fluctuations, independent of the aircraft system, may occur. The PF is prepared to immediately disconnect the autopilot, and to take the appropriate action, should not satisfactory guidance occur ‐ At least LAND2 capability is displayed on the FMA and the flight crew use CAT II/III procedures ‐ Visual references are obtained at a DH appropriate for the ILS CAT I approach. If not, a go-around must be performed. GLS CAT I Ident.: LIM-AFS-20-00021664.0001001 / 06 NOV 18 Applicable to: ALL
GLS CATEGORY I APPROACH Minimum decision height ..........................................................................................................200 ft Without automatic landing One AP and/or FD must be engaged in APPR mode and APPR1 or LAND1 approach and landing capability must be displayed on FMA. With automatic landing One AP at least must be engaged in APPR mode and LAND1 approach and landing capability must be displayed on FMA. SPECIAL AUTHORIZATION CAT II (SA CAT II) Ident.: LIM-AFS-20-00022926.0001001 / 06 NOV 18 Applicable to: ALL
Minimum decision height...............................................................................................................100 ft At least one autopilot must be engaged in APPR mode and LAND2, LAND3 SINGLE or LAND3 DUAL must be displayed on the FMA. With HUD , the flight crew must use the HUD to monitor the approach and perform an automatic landing or a manual landing. If the flight crew performs an automatic approach without automatic landing, the autopilot must be disengaged no later than at 80 ft AGL. Without HUD, the flight crew must perform an automatic landing.
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LIM-AFS-20 P 3/10 03 FEB 20
LIMITATIONS AUTO FLIGHT SYSTEM A350
AUTOMATIC APPROACH, AUTOMATIC LANDING AND AUTOMATIC ROLL-OUT
FLIGHT CREW OPERATING MANUAL
OTHER THAN STANDARD CAT II (OTS CAT II) Ident.: LIM-AFS-20-00022927.0001001 / 06 NOV 18 Applicable to: ALL
Minimum decision height...............................................................................................................100 ft At least one autopilot must be engaged in APPR mode and LAND2, LAND3 SINGLE or LAND3 DUAL must be displayed on the FMA. With HUD , the flight crew must use the HUD to monitor the approach and perform an automatic landing or a manual landing. If the flight crew performs an automatic approach without automatic landing, the autopilot must be disengaged no later than at 80 ft AGL. Without HUD, the flight crew must perform an automatic landing. ILS CAT II/III Ident.: LIM-AFS-20-00021665.0001001 / 06 NOV 18 Applicable to: ALL
CATEGORY II AUTOMATIC APPROACH WITH OR WITHOUT AUTOMATIC LANDING Minimum decision height ..........................................................................................................100 ft One AP at least must be engaged in APPR mode and LAND2, LAND3 SINGLE or LAND3 DUAL approach and landing capability must be displayed on FMA. CATEGORY III WITH DH AT OR ABOVE 50 FT AUTOMATIC APPROACH WITH AUTOMATIC LANDING Minimum decision height............................................................................................................. 50 ft One AP at least must be engaged in APPR mode and LAND3 SINGLE or LAND3 DUAL approach and landing capability must be displayed on FMA. CATEGORY III WITH DH BELOW 50 FT OR NO DH AUTOMATIC APPROACH WITH AUTOMATIC LANDING Decision height................................................................................................. Below 50 ft or no DH Alert height........................................................................................................................ 200 ft AGL Two AP must be engaged in APPR mode and LAND3 DUAL approach and landing capability must be displayed on FMA. REQUIRED EQUIPMENT FOR GLS CAT I APPROACH WITH AUTOLAND Ident.: LIM-AFS-20-00021785.0001001 / 30 JAN 18 Applicable to: ALL
Prior to initiating a CAT I GLS approach with autoland, the flight crew should check that the equipment or functions below-listed are available:
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LIM-AFS-20 P 4/10 03 FEB 20
LIMITATIONS AUTO FLIGHT SYSTEM A350
FLIGHT CREW OPERATING MANUAL
AUTOMATIC APPROACH, AUTOMATIC LANDING AND AUTOMATIC ROLL-OUT
Required Equipment Not Monitored by FG
GLS With Autoland 2
AP pb, or CAPT sidestick pushbutton, or F/O sidestick pushbutton Autoland light AP OFF alert DA/DH Indication Attitude indication on PFD Attitude indication on standby instrument Windshield wiper, or rain repellent Windshield heating
1 Available 1 for PM 2 1 1 for PF 1 for PF
In addition, the Flight Guidance (FG) monitors other required equipment, and computes the approach capability. The loss of a required equipment, monitored by the FG, is announced by an assigned alert (e.g. NAV RA SYS A+B+C FAULT), or by the AUTO FLT APPROACH CAPABILITY DOWNGRADED alert. L2 The following table presents equipment, monitored by the FG, required to perform a GLS CAT I approach with autoland: Required Equipment Monitored by FG AP PRIM Normal law for yaw, pitch, and roll Rudder trim and rudder position AFS CP, or CAPT AFS CP backup, or F/O AFS CP backup PFD display RA and MMR display on PFD FWS, including the audio function Ground spoilers Radio Altimeter MMR tuned with GLS channel ADR IRS in NAV mode
GLS LAND1 1 AP engaged 1 Available Available 1 2 Available 1 Available 1 2 2 2
REQUIRED EQUIPMENT FOR ILS CAT II/III APPROACH WITH AUTOLAND Ident.: LIM-AFS-20-00005757.0005001 / 07 JUN 19 Applicable to: G-VDOT, G-VJAM, G-VPRD, G-VRNB, G-VTEA
Prior to initiating an ILS CAT II/III approach with autoland, the crew should check that the equipment or functions listed in the following table are available:
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LIM-AFS-20 P 5/10 03 FEB 20
LIMITATIONS AUTO FLIGHT SYSTEM A350
AUTOMATIC APPROACH, AUTOMATIC LANDING AND AUTOMATIC ROLL-OUT
FLIGHT CREW OPERATING MANUAL
Required Equipment Not Monitored by FG AP pb, or CAPT sidestick pushbutton, or F/O sidestick pushbutton Autoland light AP OFF alert DH Indication Attitude indication on PFD Attitude indication on standby instrument Windshield wiper, or rain repellent Windshield heating
LAND2
LAND3 SINGLE
LAND3 DUAL
2
2
2
1 Available 1 for PM 2 1
1 Available 1 for PM 2 1
1 Available 1 for PM 2 1
1 for PF
1 for PF
1 for PF
1 for PF
1 for PF
1 for PF
In addition, the FG monitors other required equipment, and computes the approach capability. The loss of a required equipment, monitored by the FG, is announced by an assigned alert (e.g. NAV RA SYS A+B+C FAULT), or by the AUTO FLT APPROACH CAPABILITY DOWNGRADED alert. L2 The following table presents equipment, monitored by the FG, required to perform an ILS CAT II or CAT III approach with autoland:
L23
Required Equipment Monitored by FG AP A/THR PRIM SEC North reference Slat and Flap Systems
LAND2 1 AP engaged Not required 1 SEC 2 or SEC 3 MAG (SLAT SYS 1 and FLAP SYS 1) or (SLAT SYS 2 and FLAP SYS 2)
LAND3 SINGLE 1 AP engaged Active 1 SEC 2 or SEC 3 MAG (SLAT SYS 1 and FLAP SYS 1) or (SLAT SYS 2 and FLAP SYS 2)
LAND3 DUAL 2 APs engaged Active 2 SEC 2 or SEC 3 MAG (SLAT SYS 1 and FLAP SYS 2) or (SLAT SYS 2 and FLAP SYS 1)
1 Available
1 Available
1 Available
Available 1 1
Available 1 1
Available 2 1
2
2
2 Continued on the following page
(4)
Elevator Rudder actuation, rudder position and rudder trim Normal or Alternate law Hydraulic circuit AFS CP, or CAPT AFS CP backup, or F/O AFS CP backup PFD display
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(4)
←J→
(4)
LIM-AFS-20 P 6/10 03 FEB 20
LIMITATIONS AUTO FLIGHT SYSTEM A350
AUTOMATIC APPROACH, AUTOMATIC LANDING AND AUTOMATIC ROLL-OUT
FLIGHT CREW OPERATING MANUAL
1
LAND3 SINGLE 1
1 Not required Not required Not required
1 Not required Not required Not required
Nosewheel Steering
Not required
Not required
2 1 Available Available and ON Available
Ground spoilers Radio Altimeter MMR tuned with ILS frequency
Available 1 2
Available 2 2
Available 2 2
ADR IRS in NAV mode Angle of Attack Engine AC busbar Supply of AC busbars Supply of DC busbars
2 2 2 1
2 2 2 1
(3)
(3)
(3)
(3)
(3)
(3)
2 3 3 1 4 2 independent AC busbars 2 independent DC emergency busbars
(1)
LAND2
Continued from the previous page LAND3 DUAL 2
Required Equipment Monitored by FG FWS, including the audio function FCDC Braking Systems (BCS) Symetrical braking Antiskid
(2)
(1)
In LAND3 DUAL , the nosewheel steering must be able to receive AP guidance orders.
(2)
In addition, the tuning of both ILS must be consistent. If the tuning of both ILS in MMR is not consistent, the NAV LS TUNING DISAGREE alert triggers.
(3)
In accordance with the failure, and the associated equipment loss, capability downgrade may occur.
(4)
The approach and landing capability downgrades to APPR1 if all of the following are applicable: ‐ A failure leads to the loss of the Slat system (i.e. F/CTL SLAT SYS 1+2 FAULT) or to the loss of the Flap system (i.e. F/CTL FLAP SYS 1+2 FAULT) ‐ The configuration is not set to CONF 3 or CONF FULL.
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LIM-AFS-20 P 7/10 03 FEB 20
LIMITATIONS AUTO FLIGHT SYSTEM A350
AUTOMATIC APPROACH, AUTOMATIC LANDING AND AUTOMATIC ROLL-OUT
FLIGHT CREW OPERATING MANUAL
REQUIRED EQUIPMENT FOR ILS CAT II/III APPROACH WITH AUTOLAND Ident.: LIM-AFS-20-00005757.0002001 / 31 MAY 18 Applicable to: G-VLUX, G-VPOP
Prior to initiating an ILS CAT II/III approach with autoland, the crew should check that the equipment or functions listed in the following table are available: Required Equipment Not Monitored by FG AP pb, or CAPT sidestick pushbutton, or F/O sidestick pushbutton Autoland light AP OFF alert DH Indication Attitude indication on PFD Attitude indication on standby instrument Windshield wiper, or rain repellent Windshield heating
LAND2
LAND3 SINGLE
LAND3 DUAL
2
2
2
1 Available 1 for PM 2 1
1 Available 1 for PM 2 1
1 Available 1 for PM 2 1
1 for PF
1 for PF
1 for PF
1 for PF
1 for PF
1 for PF
In addition, the FG monitors other required equipment, and computes the approach capability. The loss of a required equipment, monitored by the FG, is announced by an assigned alert (e.g. NAV RA SYS A+B+C FAULT), or by the AUTO FLT APPROACH CAPABILITY DOWNGRADED alert. L2 The following table presents equipment, monitored by the FG, required to perform an ILS CAT II or CAT III approach with autoland:
L23
Required Equipment Monitored by FG AP A/THR PRIM SEC North reference Slat and Flap Systems
LAND2 1 AP engaged Not required 1 SEC 2 or SEC 3 MAG (SLAT SYS 1 and FLAP SYS 1) or (SLAT SYS 2 and FLAP SYS 2)
LAND3 SINGLE 1 AP engaged Active 1 SEC 2 or SEC 3 MAG (SLAT SYS 1 and FLAP SYS 1) or (SLAT SYS 2 and FLAP SYS 2)
LAND3 DUAL 2 APs engaged Active 2 SEC 2 or SEC 3 MAG (SLAT SYS 1 and FLAP SYS 2) or (SLAT SYS 2 and FLAP SYS 1)
1
1
1 Continued on the following page
(4)
Elevator
VIR A350 FLEET FCOM
(4)
←J→
(4)
LIM-AFS-20 P 8/10 03 FEB 20
LIMITATIONS AUTO FLIGHT SYSTEM A350
AUTOMATIC APPROACH, AUTOMATIC LANDING AND AUTOMATIC ROLL-OUT
FLIGHT CREW OPERATING MANUAL
Required Equipment Monitored by FG Rudder actuation, rudder position and rudder trim Normal or Alternate law Hydraulic circuit AFS CP, or CAPT AFS CP backup, or F/O AFS CP backup PFD display FWS, including the audio function FCDC Braking Systems (BCS) Symetrical braking Antiskid
Continued from the previous page LAND3 DUAL Available
Available
LAND3 SINGLE Available
Available 1 1
Available 1 1
Available 2 1
2 1
2 1
2 2
1 Not required Not required Not required
1 Not required Not required Not required
Nosewheel Steering
Not required
Not required
2 1 Available Available and ON Available
Ground spoilers Radio Altimeter MMR tuned with ILS frequency
Available 1 2
Available 2 2
Available 2 2
2 2 2 2 1
2 2 2 2 1
(3)
(3)
2 3 3 2 1 4 Continued on the following page
(1)
LAND2
(2)
ADR IRS in NAV mode Angle of Attack Sideslip angle Engine AC busbar
VIR A350 FLEET FCOM
←J→
LIM-AFS-20 P 9/10 03 FEB 20
LIMITATIONS AUTO FLIGHT SYSTEM A350
AUTOMATIC APPROACH, AUTOMATIC LANDING AND AUTOMATIC ROLL-OUT
FLIGHT CREW OPERATING MANUAL
Required Equipment Monitored by FG Supply of AC busbars Supply of DC busbars
LAND2
LAND3 SINGLE
(3)
(3)
(3)
(3)
Continued from the previous page LAND3 DUAL 2 independent AC busbars 2 independent DC emergency busbars
(1)
In LAND3 DUAL , the nosewheel steering must be able to receive AP guidance orders.
(2)
In addition, the tuning of both ILS must be consistent. If the tuning of both ILS in MMR is not consistent, the NAV LS TUNING DISAGREE alert triggers.
(3)
In accordance with the failure, and the associated equipment loss, capability downgrade may occur.
(4)
The approach and landing capability downgrades to APPR1 if all of the following are applicable: ‐ A failure leads to the loss of the Slat system (i.e. F/CTL SLAT SYS 1+2 FAULT) or to the loss of the Flap system (i.e. F/CTL FLAP SYS 1+2 FAULT) ‐ The configuration is not set to CONF 3 or CONF FULL.
VIR A350 FLEET FCOM
←J
LIM-AFS-20 P 10/10 03 FEB 20
LIMITATIONS AUXILIARY POWER UNIT
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LIMITATIONS AUXILIARY POWER UNIT A350
FLIGHT CREW OPERATING MANUAL
PRELIMINARY PAGES - TABLE OF CONTENTS
General.....................................................................................................................................................................A APU Start/Shutdown During Refueling/Defueling....................................................................................................B Operational Envelope.............................................................................................................................................. C
VIR A350 FLEET FCOM
LIM-APU-PLP-TOC P 1/2 02 APR 19
LIMITATIONS AUXILIARY POWER UNIT A350
FLIGHT CREW OPERATING MANUAL
PRELIMINARY PAGES - TABLE OF CONTENTS
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LIM-APU-PLP-TOC P 2/2 02 APR 19
LIMITATIONS AUXILIARY POWER UNIT A350
FLIGHT CREW OPERATING MANUAL
GENERAL Applicable to: ALL Ident.: LIM-APU-10-00022309.0001001 / 13 JAN 15
OIL QUANTITY The APU may be started and operated even if the OIL LEVEL LO ECAM advisory is displayed. Maintenance action is required within 20 h of APU operation. Ident.: LIM-APU-10-00022308.0001001 / 06 NOV 14
APU START After three consecutive APU start attempts, the flight crew must wait 60 min before a new start attempt. Ident.: LIM-APU-10-00022310.0001001 / 06 NOV 14
ROTOR SPEED Maximum N speed................................................................................................................... 106 % Ident.: LIM-APU-10-00022311.0001001 / 06 NOV 14
EGT Maximum EGT for APU start............................................................................................... 1 260 °C Maximum EGT for APU running..............................................................................................680 °C APU START/SHUTDOWN DURING REFUELING/DEFUELING Ident.: LIM-APU-00021937.0001001 / 06 NOV 14 Applicable to: ALL
An APU start is not permitted during a refuel/defuel procedure if the APU has failed to start or an automatic shutdown has occurred. A normal APU shutdown must be completed if a fuel spill has occurred during the refuel/defuel procedure. OPERATIONAL ENVELOPE Ident.: LIM-APU-00013182.0001001 / 06 NOV 14 Applicable to: ALL
APU ELECTRIC GENERATOR The electric generator of the APU can operate in the entire flight envelope. APU BLEED Max altitude to assist engine start....................................................................................... 25 000 ft VIR A350 FLEET FCOM
A to C →
LIM-APU P 1/2 01 JUL 19
LIMITATIONS AUXILIARY POWER UNIT A350
FLIGHT CREW OPERATING MANUAL
Max altitude for air conditioning and pressurization (single pack operation)........................ 25 000 ft Max altitude for air conditioning and pressurization (dual pack operation)...........................22 500 ft Use of APU bleed air for wing anti-ice is not permitted.
VIR A350 FLEET FCOM
←C
LIM-APU P 2/2 01 JUL 19
LIMITATIONS CABIN SYSTEMS
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FLIGHT CREW OPERATING MANUAL
PRELIMINARY PAGES - TABLE OF CONTENTS
POWER SUPPLY FOR PORTABLE ELECTRONIC DEVICE (PED)..................................................................... A
VIR A350 FLEET FCOM
LIM-CAB-PLP-TOC P 1/2 03 FEB 20
LIMITATIONS CABIN SYSTEMS A350
FLIGHT CREW OPERATING MANUAL
PRELIMINARY PAGES - TABLE OF CONTENTS
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VIR A350 FLEET FCOM
LIM-CAB-PLP-TOC P 2/2 03 FEB 20
LIMITATIONS CABIN SYSTEMS A350
FLIGHT CREW OPERATING MANUAL
POWER SUPPLY FOR PORTABLE ELECTRONIC DEVICE (PED) Ident.: LIM-CAB-00022295.0002001 / 03 AUG 16 Applicable to: ALL
The power supply for the Portable Electronic Device (PED carried by the passengers) must be turned off during takeoff and landing.
VIR A350 FLEET FCOM
A
LIM-CAB P 1/2 01 JUL 19
LIMITATIONS CABIN SYSTEMS A350
FLIGHT CREW OPERATING MANUAL
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LIM-CAB P 2/2 01 JUL 19
LIMITATIONS CONTROL AND DISPLAY SYSTEM
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FLIGHT CREW OPERATING MANUAL
PRELIMINARY PAGES - TABLE OF CONTENTS
Vertical Display (VD)............................................................................................................................................... A
VIR A350 FLEET FCOM
LIM-CDS-PLP-TOC P 1/2 02 APR 19
LIMITATIONS CONTROL AND DISPLAY SYSTEM A350
FLIGHT CREW OPERATING MANUAL
PRELIMINARY PAGES - TABLE OF CONTENTS
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VIR A350 FLEET FCOM
LIM-CDS-PLP-TOC P 2/2 02 APR 19
LIMITATIONS CONTROL AND DISPLAY SYSTEM A350
FLIGHT CREW OPERATING MANUAL
VERTICAL DISPLAY (VD) Ident.: LIM-CDS-00022279.0001001 / 06 NOV 14 Applicable to: ALL
The Vertical Display (VD) is provided for advisory purpose only. It is not a primary means of vertical navigation.
VIR A350 FLEET FCOM
A
LIM-CDS P 1/2 01 JUL 19
LIMITATIONS CONTROL AND DISPLAY SYSTEM A350
FLIGHT CREW OPERATING MANUAL
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LIM-CDS P 2/2 01 JUL 19
LIMITATIONS COMMUNICATION
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FLIGHT CREW OPERATING MANUAL
PRELIMINARY PAGES - TABLE OF CONTENTS
HF Communication.................................................................................................................................................. A
VIR A350 FLEET FCOM
LIM-COM-PLP-TOC P 1/2 02 APR 19
LIMITATIONS COMMUNICATION A350
FLIGHT CREW OPERATING MANUAL
PRELIMINARY PAGES - TABLE OF CONTENTS
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VIR A350 FLEET FCOM
LIM-COM-PLP-TOC P 2/2 02 APR 19
LIMITATIONS COMMUNICATION A350
FLIGHT CREW OPERATING MANUAL
HF COMMUNICATION Ident.: LIM-COM-00008842.0001001 / 06 NOV 14 Applicable to: ALL
During ground fuel operations (i.e. refueling, defueling, fuel transfer), do not use HF communication.
VIR A350 FLEET FCOM
A
LIM-COM P 1/2 01 JUL 19
LIMITATIONS COMMUNICATION A350
FLIGHT CREW OPERATING MANUAL
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VIR A350 FLEET FCOM
LIM-COM P 2/2 01 JUL 19
LIMITATIONS DOORS
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LIMITATIONS DOORS A350
FLIGHT CREW OPERATING MANUAL
PRELIMINARY PAGES - TABLE OF CONTENTS
Maximum Wind for Cabin and Cargo Doors Operation.......................................................................................... A
VIR A350 FLEET FCOM
LIM-DOORS-PLP-TOC P 1/2 02 APR 19
LIMITATIONS DOORS A350
FLIGHT CREW OPERATING MANUAL
PRELIMINARY PAGES - TABLE OF CONTENTS
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VIR A350 FLEET FCOM
LIM-DOORS-PLP-TOC P 2/2 02 APR 19
LIMITATIONS DOORS A350
FLIGHT CREW OPERATING MANUAL
MAXIMUM WIND FOR CABIN AND CARGO DOORS OPERATION Ident.: LIM-DOORS-00022288.0001001 / 06 NOV 14 Applicable to: ALL
Refer to LIM-AG-OPS Maximum Wind for Cabin and Cargo Doors Operation.
VIR A350 FLEET FCOM
A
LIM-DOORS P 1/2 01 JUL 19
LIMITATIONS DOORS A350
FLIGHT CREW OPERATING MANUAL
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VIR A350 FLEET FCOM
LIM-DOORS P 2/2 01 JUL 19
LIMITATIONS ENGINES
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FLIGHT CREW OPERATING MANUAL
PRELIMINARY PAGES - TABLE OF CONTENTS
1
Thrust Setting/EGT LIMITS..................................................................................................................................... A Shaft Speeds........................................................................................................................................................... B Oil.............................................................................................................................................................................C OIL........................................................................................................................................................................... D Starter.......................................................................................................................................................................E Reverse Thrust.........................................................................................................................................................F Reduced Thrust Takeoff..........................................................................................................................................G Derated Takeoff....................................................................................................................................................... H Soft Go-Around......................................................................................................................................................... I Maximum Taxi Time in FZFG conditions.................................................................................................................J Engine Warm-up Before Takeoff.............................................................................................................................K
VIR A350 FLEET FCOM
LIM-ENG-PLP-TOC P 1/2 15 MAR 20
LIMITATIONS ENGINES A350
FLIGHT CREW OPERATING MANUAL
PRELIMINARY PAGES - TABLE OF CONTENTS
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VIR A350 FLEET FCOM
LIM-ENG-PLP-TOC P 2/2 15 MAR 20
LIMITATIONS ENGINES A350
PRELIMINARY PAGES - SUMMARY OF HIGHLIGHTS
FLIGHT CREW OPERATING MANUAL
Localization Title
LIM-ENG-PLP-TOC Engines LIM-ENG Shaft Speeds
VIR A350 FLEET FCOM
Toc Index
ID
Reason
1
Documentation update: Deletion of the "00016270.0003001 Shaft Speeds" documentary unit.
B
1
Effectivity update: The information now applies to all ACN.
LIM-ENG-PLP-SOH P 1/2 15 MAR 20
LIMITATIONS ENGINES A350
FLIGHT CREW OPERATING MANUAL
PRELIMINARY PAGES - SUMMARY OF HIGHLIGHTS
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LIM-ENG-PLP-SOH P 2/2 15 MAR 20
LIMITATIONS ENGINES A350
FLIGHT CREW OPERATING MANUAL
THRUST SETTING/EGT LIMITS Ident.: LIM-ENG-00016268.0001001 / 04 DEC 14 Applicable to: ALL
Operating Conditions All engines operative Takeoff and Go-around One engine inoperative Maximum Continuous Thrust (MCT) (1) On ground Starting In flight (1)
Time Limit 5 min 10 min Not limited
EGT Limit 900 °C 850 °C 700 °C 850 °C
Applicable to engine failure. SHAFT SPEEDS
Ident.: LIM-ENG-00016270.0005001 / 27 SEP 19 1 Applicable to: ALL
Maximum N1............................................................................................................................. 104.3 % Maximum N2............................................................................................................................. 102.6 % Maximum N3............................................................................................................................... 99.9 % OIL Ident.: TDU / LIM-ENG-00025130.0007001 / 27 SEP 19 Applicable to: G-VDOT, G-VRNB, G-VTEA Impacted DU: 00016269 Oil
OIL TEMPERATURE Maximum continuous temperature.......................................................................................... 188 °C Minimum starting temperature..................................................................................................-40 °C Minimum temperature before takeoff........................................................................................ 50 °C OIL PRESSURE Minimum oil pressure...............................................................................................................25 PSI OIL QUANTITY Flight Time (FT) FT below 5 h FT at or above 5 h and below 7 h FT at or above 7 h
VIR A350 FLEET FCOM
Minimum Oil Quantity 13 qts 15 qts 23.6 qts
A to C →
LIM-ENG P 1/8 15 MAR 20
LIMITATIONS ENGINES A350
FLIGHT CREW OPERATING MANUAL
Note:
One of the following actions or oil system characteristics can cause indications of reduced oil quantity on the ENG SD page: ‐ If oil drains from the oil tank to the engine after oil servicing, or ‐ If engine crank or engine run are performed on the engine before the flight. As a result, if the oil quantity indicated on the ENG SD page is less than the FCOM minimum oil quantity, perform one of the following: ‐ Check that the oil tank level, that was reported in the technical logbook, is above the FCOM minimum oil quantity, or ‐ Check in the technical log book that the oil tank was fully filled. OIL
Ident.: TDU / LIM-ENG-00025130.0006001 / 01 JUL 19 Applicable to: G-VJAM, G-VLUX, G-VPOP, G-VPRD Impacted DU: 00016269 Oil
OIL TEMPERATURE Maximum continuous temperature.......................................................................................... 186 °C Minimum starting temperature..................................................................................................-40 °C Minimum temperature before takeoff........................................................................................ 50 °C OIL PRESSURE Minimum oil pressure...............................................................................................................25 PSI OIL QUANTITY Flight Time (FT) FT below 5 h FT at or above 5 h and below 7 h FT at or above 7 h
Note:
Minimum Oil Quantity 13 qts 15 qts 23.6 qts
One of the following actions or oil system characteristics can cause indications of reduced oil quantity on the ENG SD page: ‐ If oil drains from the oil tank to the engine after oil servicing, or ‐ If engine crank or engine run are performed on the engine before the flight. As a result, if the oil quantity indicated on the ENG SD page is less than the FCOM minimum oil quantity, perform one of the following: ‐ Check that the oil tank level, that was reported in the technical logbook, is above the FCOM minimum oil quantity, or ‐ Check in the technical log book that the oil tank was fully filled.
VIR A350 FLEET FCOM
←C
LIM-ENG P 2/8 15 MAR 20
LIMITATIONS ENGINES A350
FLIGHT CREW OPERATING MANUAL
OIL Ident.: LIM-ENG-00016269.0005001 / 27 SEP 19 Applicable to: G-VDOT, G-VRNB, G-VTEA Impacted by TDU: 00025130 Oil - TDU
OIL TEMPERATURE Maximum continuous temperature.......................................................................................... 188 °C Minimum starting temperature..................................................................................................-40 °C Minimum temperature before takeoff........................................................................................ 50 °C OIL PRESSURE Minimum oil pressure...............................................................................................................25 PSI OIL QUANTITY Flight Time (FT) FT below 7 h FT at or above 7 h (1)
Minimum Oil Quantity 13 qts 9.7 qts + 0.5 qt/h (1)
0.5 qt/h corresponds to the maximum oil consumption in normal operations. Note:
One of the following actions or oil system characteristics can cause indications of reduced oil quantity on the ENG SD page: ‐ If oil drains from the oil tank to the engine after oil servicing, or ‐ If an engine crank or an engine run is performed on the engine before the flight. As a result, if the oil quantity indicated on the ENG SD page is less than the minimum oil quantity defined in the above table, perform one of the following: ‐ Check that the oil tank level, that is reported in the technical logbook, is above the minimum oil quantity, or ‐ Check in the technical log book that the oil tank was fully filled. OIL
Ident.: LIM-ENG-00016269.0004001 / 09 JUL 19 Applicable to: G-VJAM, G-VLUX, G-VPOP, G-VPRD Impacted by TDU: 00025130 Oil - TDU
OIL TEMPERATURE Maximum continuous temperature.......................................................................................... 186 °C Minimum starting temperature..................................................................................................-40 °C Minimum temperature before takeoff........................................................................................ 50 °C OIL PRESSURE Minimum oil pressure...............................................................................................................25 PSI VIR A350 FLEET FCOM
D→
LIM-ENG P 3/8 15 MAR 20
LIMITATIONS ENGINES A350
FLIGHT CREW OPERATING MANUAL
OIL QUANTITY Flight Time (FT) FT below 7 h FT at or above 7 h (1)
Minimum Oil Quantity 13 qts 9.7 qts + 0.5 qt/h (1)
0.5 qt/h corresponds to the maximum oil consumption in normal operations. Note:
One of the following actions or oil system characteristics can cause indications of reduced oil quantity on the ENG SD page: ‐ If oil drains from the oil tank to the engine after oil servicing, or ‐ If an engine crank or an engine run is performed on the engine before the flight. As a result, if the oil quantity indicated on the ENG SD page is less than the minimum oil quantity defined in the above table, perform one of the following: ‐ Check that the oil tank level, that is reported in the technical logbook, is above the minimum oil quantity, or ‐ Check in the technical log book that the oil tank was fully filled. STARTER
Ident.: LIM-ENG-00016271.0001001 / 31 JUL 18 Applicable to: ALL
Maximum continuous starter operation is 5 min: ‐ Two consecutive cycles of 3 min maximum, plus one additional cycle of 1 min, with a run down to zero N3 and wait 30 s between each cycle, or ‐ One 5 min cycle. Wait 30 min after the last cycle to allow the starter to cool. No running engagement of the starter when the N3 is above 10 % on ground, or 30 % in flight. REVERSE THRUST Ident.: LIM-ENG-00008852.0001001 / 06 NOV 14 Applicable to: ALL
‐ Selection of the reverse thrust is prohibited in flight ‐ Backing the aircraft with reverse thrust is not permitted ‐ Maximum reverse should not be used below 70 kt (or when the indication starts to fluctuate). Idle reverse is allowed down to aircraft stop.
VIR A350 FLEET FCOM
← D to F
LIM-ENG P 4/8 15 MAR 20
LIMITATIONS ENGINES A350
FLIGHT CREW OPERATING MANUAL
REDUCED THRUST TAKEOFF Ident.: LIM-ENG-00008853.0001001 / 04 MAY 16 Applicable to: ALL
Takeoff at reduced thrust, so-called as FLEX takeoff, is allowed only if the airplane meets all performance requirements at the takeoff weight, with the operating engines at the thrust available for the flexible temperature (TFLEX). Takeoff at reduced thrust is allowed with any inoperative item affecting the performance only if the associated performance shortfall has been applied to meet the above requirements. FLEX takeoff is not permitted on contaminated runways. TFLEX cannot be: ‐ Higher than TMAXFLEX, equal to ISA + 60. TMAXFLEX corresponds to a reduction of 40 % from the full rated takeoff thrust. ‐ Lower than the flat rating temperature (TREF), equal to: • • • •
ISA + 15, for pressure altitudes below 2 000 ft ISA + 10, for pressure altitudes between 4 000 ft and 8 000 ft ISA + 15, for pressure altitudes above 10 000 ft For pressure altitudes between 2 000 ft and 4 000 ft, and for pressure altitudes between 8 000 ft and 10 000 ft, TREF is determined by linear interpolation between ISA + 10 and ISA + 15.
‐ Lower than the actual OAT.
VIR A350 FLEET FCOM
G→
LIM-ENG P 5/8 15 MAR 20
LIMITATIONS ENGINES A350
FLIGHT CREW OPERATING MANUAL
TFLEX Limitations
DERATED TAKEOFF Ident.: LIM-ENG-00019848.0002001 / 24 MAY 17 Applicable to: ALL
Selection of TOGA thrust is not permitted when a derated takeoff is performed, except when requested in any abnormal or emergency procedures. The use of reduced thrust takeoff (FLEX takeoff) is not permitted in conjunction with derated takeoff. The use of derated takeoff is permitted regardless of the runway condition (dry, wet or contaminated). VIR A350 FLEET FCOM
← G to H
LIM-ENG P 6/8 15 MAR 20
LIMITATIONS ENGINES A350
FLIGHT CREW OPERATING MANUAL
SOFT GO-AROUND Ident.: LIM-ENG-00019849.0001001 / 06 NOV 14 Applicable to: ALL
The use of GA SOFT mode is prohibited with one engine inoperative. MAXIMUM TAXI TIME IN FZFG CONDITIONS Ident.: LIM-ENG-00024239.0005001 / 29 JAN 19 Applicable to: ALL
Outside Air Temperature (OAT) Engine Stator A-ICE Valve Operative or Failed Open 120 min + 40 min (1) -9 °C (16 °F) ≤ OAT < 1 °C (34 °F) 80 min + 40 min (2) -15 °C (5 °F) ≤ OAT < -9 °C (16 °F) 40 min + 40 min (1) OAT below -15 °C (5 °F)
Engine Stator A-ICE Valve Failed Closed 40 min + 40 min (2)
(1)
Case "A" of the ENGINE OPERATION ON GROUND IN FZFG supplementary procedure must be performed in order to extend the maximum taxi-time with additional 40 min running time. For more information, Refer to PRO-NOR-SUP-SUP-ADVWXR Engine Operation on Ground in FZFG
(2)
Case "B" of the ENGINE OPERATION ON GROUND IN FZFG supplementary procedure must be performed in order to extend the maximum taxi-time with additional 40 min running time. For more information, Refer to PRO-NOR-SUP-SUP-ADVWXR Engine Operation on Ground in FZFG ENGINE WARM-UP BEFORE TAKEOFF
Ident.: LIM-ENG-00024061.0001001 / 13 DEC 16 Applicable to: ALL
The engines must warm up at idle or taxi thrust before takeoff. IF ENGINES WERE SHUT DOWN 90 MIN OR LESS: Warm-up Time........................................................................................................................... 2 min IF ENGINES WERE SHUT DOWN MORE THAN 90 MIN: Warm-up Time........................................................................................................................... 5 min
VIR A350 FLEET FCOM
I to K
LIM-ENG P 7/8 15 MAR 20
LIMITATIONS ENGINES A350
FLIGHT CREW OPERATING MANUAL
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LIM-ENG P 8/8 15 MAR 20
LIMITATIONS FLIGHT CONTROLS
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FLIGHT CREW OPERATING MANUAL
PRELIMINARY PAGES - TABLE OF CONTENTS
Flight Maneuvering Load Acceleration Limits......................................................................................................... A Maximum Altitude Flaps/Slats Extended.................................................................................................................B Maximum Flaps/Slats Speeds.................................................................................................................................C Use of Flight Controls............................................................................................................................................. D
VIR A350 FLEET FCOM
LIM-F-CTL-PLP-TOC P 1/2 02 APR 19
LIMITATIONS FLIGHT CONTROLS A350
FLIGHT CREW OPERATING MANUAL
PRELIMINARY PAGES - TABLE OF CONTENTS
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VIR A350 FLEET FCOM
LIM-F-CTL-PLP-TOC P 2/2 02 APR 19
LIMITATIONS FLIGHT CONTROLS A350
FLIGHT CREW OPERATING MANUAL
FLIGHT MANEUVERING LOAD ACCELERATION LIMITS Ident.: LIM-F-CTL-00005772.0001001 / 06 NOV 14 Applicable to: ALL
Refer to LIM-AG-F_CTL Flight Maneuvering Load Acceleration Limits. MAXIMUM ALTITUDE FLAPS/SLATS EXTENDED Ident.: LIM-F-CTL-00022289.0001001 / 06 NOV 14 Applicable to: ALL
Maximum operating altitude with slats and/or flaps extended..................................................20 000 ft MAXIMUM FLAPS/SLATS SPEEDS Ident.: LIM-F-CTL-00022227.0001001 / 06 NOV 14 Applicable to: ALL
Refer to LIM-AG-SPD Maximum Flaps/Slats Speeds. USE OF FLIGHT CONTROLS Ident.: LIM-F-CTL-00022229.0001001 / 06 NOV 14 Applicable to: ALL
CAUTION
VIR A350 FLEET FCOM
Rapid and large alternating control inputs, especially in combination with large changes in pitch, roll and yaw (e.g. large sideslip angles) may result in structural failures at any speed.
A to D
LIM-F-CTL P 1/2 01 JUL 19
LIMITATIONS FLIGHT CONTROLS A350
FLIGHT CREW OPERATING MANUAL
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LIM-F-CTL P 2/2 01 JUL 19
LIMITATIONS FUEL
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LIMITATIONS FUEL A350
FLIGHT CREW OPERATING MANUAL
PRELIMINARY PAGES - TABLE OF CONTENTS
Certified Fuel............................................................................................................................................................A Fuel Temperature.................................................................................................................................................... B Maximum Allowed Fuel Imbalance......................................................................................................................... C
VIR A350 FLEET FCOM
LIM-FUEL-PLP-TOC P 1/2 03 FEB 20
LIMITATIONS FUEL A350
FLIGHT CREW OPERATING MANUAL
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LIM-FUEL-PLP-TOC P 2/2 03 FEB 20
LIMITATIONS FUEL A350
FLIGHT CREW OPERATING MANUAL
CERTIFIED FUEL Ident.: LIM-FUEL-00021938.0001001 / 06 NOV 14 Applicable to: ALL
The fuel system has been certified with: JET A, JET A1, JP5, JP8, N°3 Jet Fuel, RT and TS-1, in accordance with engine manufacturers and fuel specifications. FUEL TEMPERATURE Ident.: LIM-FUEL-00021477.0001001 / 30 OCT 18 Applicable to: ALL
MAXIMUM FUEL TEMPERATURE Maximum fuel temperature
:
JET A, JET A1, JP 5, JP 8, N°3 JET, RT and TS-1 : +55 °C.
MINIMUM FUEL TEMPERATURE Minimum fuel : Freezing point temperature If the actual fuel freezing point of the fuel being used for the flight is unknown, the fuel specification freezing point provided hereafter must be used : JET A -40 °C
JET A1 -47 °C
JP 5 -46 °C
JP 8 -47 °C
N°3 JET -47 °C
TS-1 -50 °C
RT -50 °C
FUEL MIXABILITY Note:
The various types of fuel can be mixed in all proportions. However, in the case of fuel mixture, the minimum fuel specification values provided in the table above are no longer applicable. Refer to OM(B) Ch 2. MAXIMUM ALLOWED FUEL IMBALANCE
Ident.: LIM-FUEL-00021939.0001001 / 06 NOV 14 Applicable to: ALL
The table indicates the maximum allowed wing imbalance at takeoff, in flight and at landing. Tanks
Left Tank / Right Tank
Note:
3 000 kg
Maximum Asymmetry
6 613 lb
In abnormal conditions (i.e. fuel system failures) the above-mentioned maximum fuel imbalance values may be exceeded without significantly affecting the aircraft handling qualities. The aircraft remains fully controllable in all phases of the flight.
VIR A350 FLEET FCOM
A to C
LIM-FUEL P 1/2 03 FEB 20
LIMITATIONS FUEL A350
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LIM-FUEL P 2/2 03 FEB 20
LIMITATIONS ICE AND RAIN PROTECTION
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FLIGHT CREW OPERATING MANUAL
PRELIMINARY PAGES - TABLE OF CONTENTS
Rain Repellent ................................................................................................................................................A Wipers Maximum Operating Speed........................................................................................................................ B
VIR A350 FLEET FCOM
LIM-ICE_RAIN-PLP-TOC P 1/2 02 APR 19
LIMITATIONS ICE AND RAIN PROTECTION A350
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LIM-ICE_RAIN-PLP-TOC P 2/2 02 APR 19
LIMITATIONS ICE AND RAIN PROTECTION A350
FLIGHT CREW OPERATING MANUAL
RAIN REPELLENT Ident.: LIM-ICE_RAIN-00022324.0001001 / 30 JAN 18 Applicable to: ALL
Use the rain repellent in the case of heavy rain only. CAUTION
Rain repellent must not be used as a windshield washer, and never be applied on a dry windshield. WIPERS MAXIMUM OPERATING SPEED
Ident.: LIM-ICE_RAIN-00022113.0001001 / 06 NOV 14 Applicable to: ALL
Refer to LIM-AG-SPD Wipers Maximum Operating Speed.
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Braking System........................................................................................................................................................A Brake Temperature.................................................................................................................................................. B Landing Gear Gravity Extension Reset...................................................................................................................C Maximum Speeds with the Landing Gear Extended.............................................................................................. D Maximum Tire Speed.............................................................................................................................................. E Trampling Arrestor Cables.......................................................................................................................................F Parking Brake.......................................................................................................................................................... G Taxi with Deflated or Damaged Tires..................................................................................................................... H Backup Steering Function.........................................................................................................................................I
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BRAKING SYSTEM Ident.: LIM-LG-00022002.0001001 / 06 NOV 14 Applicable to: ALL
The braking system is not designed to hold the aircraft in a stationary position when a high thrust level is applied on at least one engine. During ground procedures that require a thrust increase with braking, the flight crew must ensure that the aircraft remains stationary. BRAKE TEMPERATURE Ident.: LIM-LG-00022001.0001001 / 06 NOV 14 Applicable to: ALL
Maximum brake temperature for takeoff..................................................................................... 300 °C LANDING GEAR GRAVITY EXTENSION RESET Ident.: LIM-LG-00022356.0001001 / 06 NOV 14 Applicable to: ALL
The landing gear gravity extension reset function must not be used in flight. CAUTION
The landing gear gravity extension must be reset only on ground by maintenance personnel. MAXIMUM SPEEDS WITH THE LANDING GEAR EXTENDED
Ident.: LIM-LG-00022098.0001001 / 06 NOV 14 Applicable to: ALL
Refer to LIM-AG-SPD Maximum Speeds with the Landing Gear Extended. MAXIMUM TIRE SPEED Ident.: LIM-LG-00022112.0001001 / 06 NOV 14 Applicable to: ALL
Refer to LIM-AG-SPD Maximum Tire Speed. TRAMPLING ARRESTOR CABLES Ident.: LIM-LG-21400051.9001001 / 03 FEB 20 Applicable to: ALL
Refer to LIM-AG-SPD Maximum Tire Speed.
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PARKING BRAKE Ident.: LIM-LG-00022332.0001001 / 06 NOV 14 Applicable to: ALL
Use of parking brake while aircraft is moving is prohibited unless in emergency. TAXI WITH DEFLATED OR DAMAGED TIRES Ident.: LIM-LG-00023092.0001001 / 07 JAN 16 Applicable to: ALL
To vacate the runway or taxi with one or more deflated or damaged tires all of the following limitations apply: ‐ Maximum taxi speed: 3 kt ‐ Maximum nosewheel steering angle: 30 ° ‐ No more than one affected tire on the nose landing gear ‐ No more than two affected tires on each main landing gear provided that the affected tires are not on the same axle. In addition, if tire damage is suspected, the flight crew must ask for an aircraft inspection prior to vacate the runway or taxi. If the ground crew suspects that a tire burst may damage the landing gear, maintenance action is due. For more information, Refer to FCTM/PR-AEP-LDG Taxi with Deflated Tires. BACKUP STEERING FUNCTION Ident.: LIM-LG-00022548.0001001 / 03 OCT 17 Applicable to: ALL
The Backup Steering Function (BSF) must not be used: ‐ On contaminated runways, ‐ For more than 90 ° turns, ‐ To perform more than 2 turns. When the BSF activates, do not use manual differential braking or differential thrust to steer the aircraft unless required for controllability at the end of the rollout.
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Exterior Lights.......................................................................................................................................................... A
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EXTERIOR LIGHTS Ident.: LIM-LT-00022304.0001001 / 06 NOV 14 Applicable to: ALL
During any ground fuel operations, do not use the exterior lights, except for: ‐ Navigation lights (NAV sw), ‐ Logo lights (LOGO sw), ‐ Wing and engine scan lights (WING sw).
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Airport Navigation Function (ANF).......................................................................................................................... A Inertial Reference System (IRS)..............................................................................................................................B
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AIRPORT NAVIGATION FUNCTION (ANF) Ident.: LIM-NAV-00022281.0001001 / 06 NOV 14 Applicable to: ALL
GENERAL The use of the airport moving map is approved for certain flight phases only. Note:
Direct visual observation out of the cockpit windows remains the primary means of taxiing. The flight crew must always use external reference indications during aircraft taxi. They must never use the ANF instead of these external reference indications.
TAXI The use of the airport moving map is authorized on both PF and PM displays. TAKEOFF The use of the airport moving map is not authorized on PF display. GO-AROUND, CRUISE, DESCENT AND APPROACH UNTIL TOUCHDOWN The use of the airport moving map is authorized on either PF or PM display for BTV. ROLL OUT AFTER TOUCHDOWN The use of the airport moving map is authorized on both PF and PM displays. INERTIAL REFERENCE SYSTEM (IRS) Ident.: LIM-NAV-00022305.0001001 / 06 NOV 14 Applicable to: ALL
IR GROUND ALIGNMENT Ground alignment of the IRS is possible in latitudes between 82 ° North and 78.25 ° South. MAGNETIC (MAG) / TRUE REFERENCE In NAV mode, the IR will not provide valid magnetic heading and magnetic track angle: ‐ North of 82 ° North ‐ North of 73 ° North between 90 ° and 120 ° West (magnetic polar region) ‐ South of 60 ° South. When flying at latitudes beyond these limits, TRUE reference must be selected.
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Printers..................................................................................................................................................................... A
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PRINTERS Ident.: LIM-OIS-00018028.0001001 / 06 NOV 14 Applicable to: ALL
The reference information is the information that appears on the different display units. In the case of a discrepancy between the printed and displayed information, the flight crew should use the displayed information for flight and fuel planning, ATC communication, etc.
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Minimum Flight Crew Oxygen Pressure..................................................................................................................A
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MINIMUM FLIGHT CREW OXYGEN PRESSURE Ident.: LIM-OXY-00019742.0003001 / 09 JUL 15 Applicable to: ALL
The following table provides the minimum oxygen pressure. It is the responsibility of the Operator to ensure that the minimum oxygen pressure complies with the intended aircraft operations. Flight Crewmembers CAPT + F/O CAPT + F/O + 3rd Occupant CAPT + F/O + 4th Occupant CAPT + F/O + 3rd Occupant + 4th Occupant
Minimum Oxygen Pressure displayed on DOOR SD page (PSI) CAPT Indication F/O Indication 750 750 750 1050 1050 750 1050 1050
For more information on the third and fourth occupant seats, Refer to Cockpit Seats. FLIGHT ABOVE FL 410 For FAA-certified aircraft, and in accordance with FAR 121.333, if flight above FL 410 is expected: ‐ Before departure, the flight crew must increase the minimum oxygen bottle pressure. The amount of the increase is based on the amount of time that the aircraft will be above FL 410. For calculation purposes, the minimum oxygen pressure must be increased by 150 PSI per hour ‐ When the aircraft goes above FL 410, one flight crewmember must don the oxygen mask, and set the regulator to normal position (diluted oxygen).
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BTV.......................................................................................................................................................................... A ROW/ROP................................................................................................................................................................B
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BTV Ident.: LIM-ROW-ROP-00020512.0002001 / 03 APR 17 Applicable to: ALL
For landing on a contaminated runway, the flight crew must set the LDG PERF CODE at or below 4 (COMP SNOW - GOOD TO MEDIUM), regardless of the available airport reports (e.g. Pilot Report of Braking Action = Good or Estimated Surface Friction = Good). Note: L2
The flight crew must pay attention to the validity of the reported depth of contamination at the time of landing.
For more information about: ‐ The definition of the landing performance equivalent to wet, Refer to PER-LDG-30 Contaminated Runway ‐ The runway condition assessment matrix, Refer to PER-LDG-30 Runway Condition Assessment Matrix for Landing ‐ The selection of a runway condition, Refer to DSC-34-32-20-20-70 RWY CONDITION/BRAKING ACTION Matrix.
ROW/ROP Applicable to: ALL Ident.: LIM-ROW-ROP-10-00020511.0002001 / 03 APR 17
The ROW/ROP is certified : ‐ On dry, wet and contaminated runways, ‐ With thrust reversers available, ‐ Without failure affecting landing performance. Note:
In the case of a failure affecting landing performance, the ROW/ROP alerts are available. The ROW/ROP alerts are based on landing performance that does not take into account the performance penalties linked to the alert that impacts the landing performance. The flight crew must always follow the ROW/ROP alerts.
Ident.: LIM-ROW-ROP-10-00022329.0001001 / 05 JUN 18
Operations where the ROW landing distance is above the LDA ("TOO SHORT" indication displayed on the ND) must not be conducted unless a specific authorization is obtained from the appropriate authority to deactivate the ROW/ROP for these operations.
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In this case, the flight crew must deactivate the ROW/ROP via either: ‐ The ROW/ROP pb-sw on the SURV overhead panel , or ‐ The TERR SYS button on the MFD SURV page, if the ROW/ROP pb-sw is not installed. In this case, the flight crew must deactivate the ROW/ROP when the aircraft position is less than 15 NM from the airfield. Ident.: LIM-ROW-ROP-10-00024128.0002001 / 05 JUN 18
CONTAMINATED RUNWAY LDG PERF CODE SELECTION For landing on a contaminated runway, the flight crew must set the LDG PERF CODE at or below 4 (COMP SNOW - GOOD TO MEDIUM), regardless of the available airport reports (e.g. Pilot Report of Braking Action = Good or Estimated Surface Friction = Good). Note:
The flight crew must pay attention to the validity of the reported depth of contamination at the time of landing.
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Terrain Awareness and Warning System (TAWS)..................................................................................................A Transponder............................................................................................................................................................. B
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TERRAIN AWARENESS AND WARNING SYSTEM (TAWS) Ident.: LIM-SURV-00022107.0001001 / 06 NOV 14 Applicable to: ALL
Aircraft navigation is not to be predicated upon the use of the terrain display. The terrain display is intended to serve as a situation awareness tool only, and may not provide the accuracy on which to solely base terrain avoidance maneuvering. The TAWS function should be inhibited (TERR SYS button set to OFF on the MFD SURV/CONTROLS page): ‐ For operations from/to runways not incorporated into the TAWS database ‐ For specific approach procedures, which have previously been identified as potentially producing false terrain alerts. The TAWS should be inhibited when the aircraft position is less than 15 NM from the airfield. TRANSPONDER Ident.: LIM-SURV-00023221.0001001 / 03 DEC 15 Applicable to: ALL
Minimum pressure altitude for transponder altitude reporting...................................................-1 000 ft
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Transmitting Portable Electronic Device................................................................................................................. A
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Localization Title
LIM-T-PED Transmitting Portable Electronic Device
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Toc Index A
ID
Reason
1
Addition of the Bluetooth or any low power technology that can be used in the flight deck because it is less restrictive than the WI-FI.
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TRANSMITTING PORTABLE ELECTRONIC DEVICE Ident.: LIM-T-PED-00024157.0002001 / 03 JAN 20 Applicable to: ALL 1
The Transmitting Portable Electronic Device (T-PED) can be used in the flight deck, the cabin and the cargo area. Note:
In the flight deck and in the corridor of the flight deck privacy area, T-PED use is only restricted to Wi-Fi, Bluetooth or any low power technology. Use of GSM, 3G, 4G, and other standards is not permitted in this area when the aircraft is moving.
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PER-PN1 Pitch-N1 Tables PER-OPS Operating Speeds PER-TOF Takeoff PER-IFT In-Flight PER-LDG Landing PER-PSD Supplementary Performance Information
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Localization
LIST OF EFFECTIVE TEMPORARY DOCUMENTARY UNITS DU Title
DU identification
DU date
No Temporary Documentary Unit
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INTRODUCTION......................................................................................................................................................A CLIMB IN CLEAN CONF........................................................................................................................................ B LEVEL FLIGHT IN CLEAN CONF.......................................................................................................................... C DESCENT IN CLEAN CONF.................................................................................................................................. D LEVEL FLIGHT WITH CONF.................................................................................................................................. E APPROACH ON A SLOPE OF MINUS 3 DEGREES.............................................................................................F
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INTRODUCTION Ident.: PER-PN1-00024296.0002001 / 06 FEB 18 Applicable to: ALL
The main goal of the Pitch/N1 tables is to reinforce flight crew awareness about the pitch/N1 thrust value. This is in order to safely fly in the complete domain of flight in normal and abnormal situations. All tables are computed for a CG of 30 %. For extreme CG values, expect maximum variations in terms of both of the following: ‐ For forward CG: +3 % N1 and +5 kt. ‐ For aft CG: -3 % N1 and -5 kt. CLIMB IN CLEAN CONF Ident.: PER-PN1-00023760.0002001 / 06 FEB 18 Applicable to: ALL
The resultant speed is between VLS+10 and VMAX. FL
Above FL 300 FL 300 FL 200 FL 100 FL 050
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THRUST LEVERS
CLB position
180 t (397 klb)
320 t (705 klb)
5°
250 t (551 klb) PITCH 4°
7°
6°
5°
10 °
8°
7°
A to B
4°
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LEVEL FLIGHT IN CLEAN CONF Ident.: PER-PN1-00023761.0002001 / 06 FEB 18 Applicable to: ALL
CLEAN CONF - GEAR UP FL
FL 400 FL 350 FL 300 FL 250 FL 200 FL 150 FL 100 Note:
180 t (397 klb)
PITCH 3°
320 t (705 klb)
82 % (235 kt)
250 t (551 klb) N1 % (Resultant speed) MCL
70 % (218 kt)
79 % (260 kt)
86 % (290 kt)
71 % (259 kt)
77 % (297 kt)
76 % (240 kt)
4°
84 % (276 kt)
67 % (217 kt)
75 % (259 kt)
64 % (218 kt) 58 % (203 kt)
5°
67 % (239 kt)
54 % (203 kt)
63 % (240 kt)
MCL MCL
82 % (296 kt) 73 % (272 kt) 69 % (272 kt)
A deviation of 0.5 ° pitch may result in a speed variation of 13 kt. DESCENT IN CLEAN CONF
Ident.: PER-PN1-00023768.0002001 / 06 FEB 18 Applicable to: ALL
The resultant speed is below VMAX. THRUST LEVERS Idle position
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180 t (397 klb)
250 t (551 klb) PITCH 1°
0°
C to D
320 t (705 klb) 2°
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LEVEL FLIGHT WITH CONF Applicable to: ALL Ident.: PER-PN1-002-00023763.0002001 / 06 FEB 18
CONF 1 - GEAR UP 180 t (397 klb) 9°
PITCH FL
FL 150 FL 125 FL 100 FL 075 FL 050 FL 025 Note:
320 t (705 klb) 10 °
58 % (162 kt)
250 t (551 klb) 9° N1 % (Resultant speed) 67 % (191 kt)
54 % (161 kt)
63 % (192 kt)
70 % (207 kt)
56 % (161 kt)
65 % (191 kt)
52 % (161 kt)
61 % (191 kt)
51 % (161 kt)
59 % (191 kt)
49 % (161 kt)
57 % (191 kt)
74 % (206 kt) 72 % (206 kt) 68 % (207 kt) 66 % (207 kt) 64 % (207 kt)
For landing gear down (average correction), apply both of the following: ‐ N1: Add 9 % ‐ Speed: Subtract 6 kt
Ident.: PER-PN1-002-00023764.0002001 / 06 FEB 18
CONF 1+F - GEAR UP FL
FL 150 FL 125 FL 100 FL 075 FL 050 FL 025 Note:
PITCH
180 t (397 klb)
310 t (683 klb)
59 % (156 kt)
250 t (551 klb) N1 % (Resultant speed) 68 % (185 kt)
55 % (155 kt)
63 % (185 kt)
70 % (210 kt)
57 % (156 kt) 5°
53 % (155 kt) 51 % (155 kt) 50 % (155 kt)
66 % (185 kt) 61 % (185 kt) 60 % (185 kt) 58 % (185 kt)
74 % (209 kt) 72 % (210 kt) 68 % (210 kt) 66 % (211 kt) 64 % (211 kt)
For landing gear down (average correction), apply both of the following: ‐ N1: Add 9 % ‐ Speed: Subtract 1 kt
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FLIGHT CREW OPERATING MANUAL Ident.: PER-PN1-002-00023765.0002001 / 06 FEB 18
CONF 2 - GEAR UP PITCH FL
FL 150 FL 125 FL 100 FL 075 FL 050 FL 025 Note:
180 t (397 klb) 4°
320 t (705 klb) 5°
60 % (150 kt)
250 t (551 klb) 4° N1 % (Resultant speed) 69 % (178 kt)
56 % (150 kt)
65 % (178 kt)
72 % (194 kt)
58 % (150 kt)
67 % (178 kt)
54 % (150 kt)
63 % (178 kt)
52 % (150 kt)
61 % (178 kt)
50 % (150 kt)
59 % (178 kt)
76 % (193 kt) 74 % (193 kt) 70 % (194 kt) 68 % (194 kt) 66 % (194 kt)
For landing gear down (average correction), apply both of the following: ‐ N1: Add 7 % ‐ Speed: Add 1 kt
Ident.: PER-PN1-002-00024297.0002001 / 06 FEB 18
CONF 3- GEAR UP PITCH FL
FL 150 FL 125 FL 100 FL 075 FL 050 FL 025 Note:
180 t (397 klb) 4°
320 t (705 klb) 5°
63 % (143 kt)
250 t (551 klb) 4° N1 % (Resultant speed) 72 % (169 kt)
59 % (143 kt)
68 % (169 kt)
75 % (185 kt)
61 % (143 kt)
70 % (169 kt)
57 % (143 kt)
66 % (169 kt)
55 % (143 kt)
64 % (169 kt)
53 % (143 kt)
62 % (169 kt)
80 % (185 kt) 78 % (185 kt) 73 % (185 kt) 71 % (185 kt) 69 % (185 kt)
For landing gear down (average correction), apply both of the following: ‐ N1: Add 6 % ‐ Speed: Add 2 kt
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APPROACH ON A SLOPE OF MINUS 3 DEGREES Applicable to: ALL Ident.: PER-PN1-003-00023769.0002001 / 06 FEB 18
CONF 3 - GEAR DOWN ALTITUDE
9 000 ft 6 000 ft 3 000 ft 1 000 ft
PITCH 2°
160 t (353 klb)
180 t 200 t 220 t 236 t (397 klb) (441 klb) (485 klb) (520 klb) N1 % (Resultant speed) 43 % (131 kt) 45 % (139 kt) 48 % (147 kt) 50 % (155 kt) 51 % (160 kt) 42 % (131 kt) 44 % (139 kt) 46 % (147 kt) 48 % (154 kt) 50 % (160 kt) 40 % (131 kt) 43 % (139 kt) 45 % (147 kt) 47 % (154 kt) 48 % (160 kt) 40 % (131 kt) 45 % (139 kt) 44 % (147 kt) 46 % (154 kt) 47 % (160 kt)
Ident.: PER-PN1-003-00023770.0002001 / 06 FEB 18
CONF FULL - GEAR DOWN PITCH ALTITUDE
9 000 ft 6 000 ft 3 000 ft 1 000 ft
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160 t (353 klb) 180 t (397 klb) 200 t (441 klb) 220 t (485 klb) 236 t (520 klb) 0° 2° N1 % (Resultant speed) 49 % (131 kt) 51 % (131 kt) 53 % (138 kt) 56 % (145 kt) 57 % (150 kt) 47 % (131 kt)
49 % (131 kt)
51 % (138 kt)
54 % (145 kt)
55 % (150 kt)
45 % (131 kt)
47 % (131 kt)
49 % (138 kt)
51 % (145 kt)
52 % (150 kt)
45 % (131 kt)
47 % (131 kt)
F
50 % (138 kt)
52 % (145 kt)
53 % (150 kt)
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OPERATING SPEEDS DURING APPROACH....................................................................................................... A VLS DURING APPROACH..................................................................................................................................... B GREEN DOT SPEEDS........................................................................................................................................... C VLS CONF 0........................................................................................................................................................... D
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OPERATING SPEEDS DURING APPROACH Ident.: PER-OPS-00018568.0003001 / 06 SEP 17 Applicable to: ALL
Weight (1 000 kg)
140 160 180 200 220 240 260 280 300 320
OPERATING SPEEDS DURING APPROACH (KT) S (CONF 1) F (CONF 2) 146 138 157
142
175
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166
F (CONF 3) 133 133
151
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141 149
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192
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175
200
163
182
208
170
189
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187
VLS DURING APPROACH Ident.: PER-OPS-00021584.0003001 / 06 SEP 17 Applicable to: ALL
Weight (1 000 kg)
140 160 180 200 220 240 260 280 300 320
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CONF 1 131 140 148 157 164 172 179 185 192 199
VLS DURING APPROACH (KT) CONF 1+F CONF 2 125 123 134
131
149
147
142
139
157
154
164
161
170
167
177
174
184
180
190
186
A to B
CONF 3 123
CONF FULL 123
132
128
124 139 145 152 158 164 170 176
123 135 142 148 154 160 166 171
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GREEN DOT SPEEDS Ident.: PER-OPS-00021585.0003001 / 06 SEP 17 Applicable to: ALL
GREEN DOT - ALL ENGINES OPERATIVE Weight (1 000 kg)
140 160 180 200 220 240 260 280 300 320
GREEN DOT (KT) ALL ENGINES OPERATIVE At or below FL 100 FL 200 FL 300 167 168 176 177
181
191
196
203
227
186 206 216 225 234 244 253
192 216 226 238 251 262 273
206 249 269 277
FL 400 195 222 243 246 246 246
287 294 302
GREEN DOT - ONE ENGINE INOPERATIVE Weight (1 000 kg)
140 160 180 200 220 240 260 280 300 320
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GREEN DOT (KT) ONE ENGINE INOPERATIVE FL 100 FL 200 FL 300 163 171 182 178
189
198
201
210
229
189 212 222 232 244 255 256
202 218 223 233 249 265 273
C
216 243 259 271
FL 400 197 217 236 241 245 246
283 290 294
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VLS CONF 0 Ident.: PER-OPS-00021588.0003001 / 03 OCT 17 Applicable to: ALL
Weight (1 000 kg)
140 160 180 200 220 240 260 280 300 320
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FL 0 149 159 169 178 187 195 203 211 219 227
VLS CONF 0 (KT) FL 100 FL 200 149 150 159
163
179
186
169
175
189
198
199
209
209
221
218
234
227
246
237
257
D
FL 300 158
FL 400 174
188
206
172 203 216 230 243
191 224 232 240
255 266 281
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PERFORMANCE TAKEOFF
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PER-TOF-10 Takeoff Performance Optimization
General.....................................................................................................................................................................A Takeoff Parameters................................................................................................................................................. B
PER-TOF-20 Thrust Options PER-TOF-20-10 Takeoff at Maximum Thrust
TOGA Thrust............................................................................................................................................................A
PER-TOF-20-20 Flexible Takeoff PER-TOF-20-20-10 General
General.....................................................................................................................................................................A
PER-TOF-20-20-20 Flexible Takeoff
Flexible Takeoff Definition....................................................................................................................................... A Flexible Takeoff Principle........................................................................................................................................ B Flexible Takeoff Limitations.....................................................................................................................................C
PER-TOF-30 Runway Conditions PER-TOF-30-10 Takeoff on Dry Runway
Description............................................................................................................................................................... A Performance Calculation..........................................................................................................................................B
PER-TOF-30-20 Takeoff on Damp and Wet Runways
Descriptions..............................................................................................................................................................A Performance Calculation..........................................................................................................................................B
PER-TOF-30-30 Takeoff on Contaminated Runway
Descriptions..............................................................................................................................................................A Performance Calculation..........................................................................................................................................B Restrictions.............................................................................................................................................................. C
PER-TOF-40 Takeoff with MEL or CDL Item
Takeoff with MEL or CDL Item............................................................................................................................... A
PER-TOF-50 Takeoff Recommendations
Takeoff Recommendations...................................................................................................................................... A
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TAKEOFF PERFORMANCE OPTIMIZATION
GENERAL Ident.: PER-TOF-10-00017742.0001001 / 06 AUG 14 Applicable to: ALL
The takeoff performance optimization is the process which aims at obtaining: ‐ The maximum performance limited takeoff weight (MTOW (perf)) ‐ The optimum takeoff thrust for a given weight. The takeoff performance is optimized for a given runway, the associated obstacles, the flaps setting, the prevailing outside conditions (temperature, wind, and QNH) and the aircraft status. The takeoff performance optimization process: ‐ Takes into account the parameters that affect takeoff performance ‐ Optimizes the parameters for which there is a possible range of values or settings L2
The takeoff performance optimization process is made with the takeoff performance (T.O PERF) application. For more information on the T.O PERF application, Refer to DSC-46-OIS-20-80-90 T.O PERF.
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A
PER-TOF-10 P 1/4 03 FEB 20
PERFORMANCE TAKEOFF A350
TAKEOFF PERFORMANCE OPTIMIZATION
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TAKEOFF PARAMETERS Ident.: PER-TOF-10-00021524.0001001 / 01 JUL 19 Applicable to: ALL
The takeoff performance parameters are: ‐ The characteristics of the runway L2
L1
L2 L3
L2
L1 L2
L1 L2
• • • •
Declared lengths (TORA, TODA, ASDA) Elevation Slope Obstacles.
‐ The regulatory requirements ‐ The line up distances as applicable ‐ The outside conditions • Outside Air Temperature (OAT) • Wind Maximum tailwind is limited to a certified value. There is no maximum certified value for headwind, however a headwind higher than 40 kt brings no additional performance credit. As per regulation, the computation is based on 150 % of the entered tailwind, and 50 % of the entered headwind. A maximum crosswind component is associated with each runway condition. For more information on crosswind limitations, Refer to LIM-AG-OPS Maximum Crosswind for Takeoff and Landing. In addition, the flight crew applies a different thrust setting technique during the takeoff procedure when the crosswind component exceeds a threshold value, which affects the calculation of the takeoff distance. For more information on the takeoff procedure, Refer to PRO-NOR-SOP-120 Takeoff - Thrust Setting. • QNH • Runway condition. ‐ The aircraft configuration • • • •
Aerodynamic configuration Air conditioning setting Anti-ice selection Thrust setting.
‐ The aircraft status • MEL items • CDL items.
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TAKEOFF PERFORMANCE OPTIMIZATION
‐ The takeoff speeds. • V1 • VR • V2. The following parameters can be optimized: ‐ Aerodynamics configuration ‐ Air conditioning ‐ Thrust setting • TOGA • FLEX ‐ Takeoff speeds. Among the takeoff performance parameters that can be optimized, the takeoff speeds optimization has the largest potential for gain of takeoff weight. The range for optimization varies from 0.84 to 1.0 for V1/VR ratio and from 1.13 to 1.4 for V2/VS1G ratio.
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PER-TOF-10 P 4/4 03 FEB 20
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THRUST OPTIONS - TAKEOFF AT MAXIMUM THRUST
TOGA THRUST Ident.: PER-TOF-20-10-00017759.0001001 / 29 JAN 19 Applicable to: ALL
TOGA is the maximum thrust certified for takeoff. When all engines are operative, the TOGA thrust rating must not be used more than 5 min. In the case of one engine out, the TOGA thrust rating may be used for a maximum of 10 min. The flight crew must use TOGA thrust for takeoff if at least one of the following conditions applies: ‐ Maximum power is required ‐ Performance reasons ‐ Flexible takeoff are not permitted.
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PER-TOF-20-10 P 2/2 03 FEB 20
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THRUST OPTIONS - FLEXIBLE TAKEOFF
General GENERAL Ident.: PER-TOF-20-20-10-00017760.0001001 / 29 JAN 19 Applicable to: ALL
The actual takeoff weight of the aircraft is often lower than the maximum regulatory takeoff weight. In this case, it may be possible to takeoff at a thrust less than the maximum takeoff thrust. This allows to increase the engine life, improve the engine reliability and reduce the maintenance costs. Two categories of takeoff at reduced thrust exist: ‐ The use of flexible temperature concept referred to as flexible takeoff ‐ The use of a fixed derated thrust level referred to as derated takeoff. NB this is not used in Virgin Atlantic operations.
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Flexible Takeoff FLEXIBLE TAKEOFF DEFINITION Ident.: PER-TOF-20-20-20-00017761.0001001 / 06 AUG 14 Applicable to: ALL
When the actual takeoff weight is lower than the maximum performance limited takeoff weight, the aircraft may comply with the regulatory requirements with a reduced thrust, called flexible takeoff thrust. This takeoff operation is the FLEX takeoff.
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A
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THRUST OPTIONS - FLEXIBLE TAKEOFF
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FLEXIBLE TAKEOFF PRINCIPLE Ident.: PER-TOF-20-20-20-00021543.0001001 / 06 AUG 14 Applicable to: ALL
The FLEX takeoff principle is based on the change in maximum available thrust with OAT. The maximum performance limited takeoff weight depends on the maximum available takeoff thrust, therefore it is possible to determine a temperature at which the actual takeoff weight would be limited by performance. This temperature is referred to as TFLEX (Flex Temperature). Flexible Takeoff Principle
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THRUST OPTIONS - FLEXIBLE TAKEOFF
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FLEXIBLE TAKEOFF LIMITATIONS Ident.: PER-TOF-20-20-20-00017762.0002001 / 06 SEP 17 Applicable to: ALL
Takeoff at reduced thrust, so-called as FLEX takeoff, is allowed only if the airplane meets all performance requirements at the takeoff weight, with the operating engines at the thrust available for the flexible temperature (TFLEX). TFLEX cannot be: ‐ Higher than TMAXFLEX, equal to ISA + 60. TMAXFLEX corresponds to a reduction of 40 % from the full rated takeoff thrust. ‐ Lower than the flat rating temperature (TREF), equal to ISA + 15. ‐ Lower than the actual OAT.
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THRUST OPTIONS - FLEXIBLE TAKEOFF
TFLEX Limitations
FLEX takeoff is not permitted on contaminated runways. Some items listed in the MEL and CDL do not permit a flexible takeoff. L2
The operator should check the maximum thrust (TOGA) by: ‐ Performing full-rated takeoffs at regular intervals, in order to detect a reduced EGT margin, or ‐ Maintaining an adequate engine monitoring program, in order to follow-up on the engine parameters.
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PERFORMANCE TAKEOFF A350
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RUNWAY CONDITIONS - TAKEOFF ON DRY RUNWAY
DESCRIPTION Ident.: PER-TOF-30-10-00021528.0001001 / 06 AUG 14 Applicable to: ALL
A runway is dry when its surface is not: ‐ Damp ‐ Wet ‐ Contaminated. PERFORMANCE CALCULATION Ident.: PER-TOF-30-10-00015893.0001001 / 29 JAN 19 Applicable to: ALL
Takeoff performance is calculated without the benefit of thrust reversers, as per regulation. Flexible takeoff is allowed for a takeoff from a dry runway.
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RUNWAY CONDITIONS - TAKEOFF ON DAMP AND WET RUNWAYS
DESCRIPTIONS Ident.: PER-TOF-30-20-00011356.0001001 / 06 AUG 14 Applicable to: ALL
DAMP RUNWAY A runway is considered as damp, when the surface of the runway is not dry, but the water on the surface does not cause a shiny appearance. Note:
In line with the recommendations from the FAA Takeoff And Landing Performance Assessment Aviation Rulemaking Group, the applicable performance for this runway condition is WET and not DRY. This is not communicated via the definitions but via the RCAM.
WET RUNWAY A runway is considered as wet, when the surface of the runway has a shiny appearance due to a thin film of water. When this film does not exceed 3 mm (1/8"), there is no significant danger of hydroplaning. PERFORMANCE CALCULATION Ident.: PER-TOF-30-20-00014338.0001001 / 29 JAN 19 Applicable to: ALL
Takeoff performance on a damp or wet runway can be calculated with the benefit of thrust reversers. However, it is not allowed to take off at a weight higher than the weight on dry runway. Flexible takeoff is allowed for a takeoff from a damp or wet runway. L2 For information on contaminants equivalent to wet runway, Refer to PER-TOF-30-30 Performance Calculation.
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RUNWAY CONDITIONS - TAKEOFF ON CONTAMINATED RUNWAY
DESCRIPTIONS Ident.: PER-TOF-30-30-00014339.0001001 / 07 NOV 16 Applicable to: ALL
A runway is contaminated when more than 25 % of its surface is covered with: ‐ A layer of fluid contaminant not considered as thin ‐ A hard contaminant. FLUID CONTAMINANT In terms of performance, a contaminated runway is a runway covered by a fluid contaminant with a depth of more than 3 mm (1/8"). The fluid contaminant can be either: ‐ Dry snow ‐ Wet snow ‐ Standing water ‐ Slush. Fluid Contaminants reduce friction forces, and cause: ‐ Precipitation drag ‐ Hydroplaning. L2
L1
Fluid contaminants descriptions: ‐ Dry snow is snow that, if compacted by hand, does not stay compressed when released. The wind can blow dry snow. The density of dry snow is approximately 0.2 kg/l (1.7 lb/US Gal). ‐ Wet snow is snow that, if compacted by hand, stays compressed when released, and with which snowballs can be created. The density of wet snow is approximately 0.4 kg/l (3.35 lb/US Gal). ‐ Standing water occurs due to heavy rain and/or not sufficient runway drainage. Standing water has a depth of more than 3 mm. ‐ Slush is snow soaked with water, which spatters when stepped on firmly. Slush occurs at temperatures of approximately 5 °C, and has a density of approximately 0.85 kg/l (7.1 lb/US Gal). HARD CONTAMINANT In terms of performance, a contaminated runway is a runway covered by a hard contaminant that can be either: ‐ Compacted snow, ‐ Ice (Cold and Dry) ‐ Wet ice. Hard contaminants only reduce friction forces.
L2
Hard contaminants descriptions: ‐ Compacted snow: the maintenance personnel use a snow groomer to compress the snow on a runway in order to obtain a hard surface
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RUNWAY CONDITIONS - TAKEOFF ON CONTAMINATED RUNWAY
‐ Ice (Cold and Dry): situation in which ice occurs on the runway in cold and dry conditions ‐ Wet ice: when the ice on a runway melts, or there are loose/fluid contaminants on top of the ice, the ice is referred to as "wet ice". When there is wet ice on a runway, braking and directional control are difficult or not possible, because the runway surface is very slippery. PERFORMANCE CALCULATION Ident.: PER-TOF-30-30-00015894.0001001 / 03 FEB 20 Applicable to: ALL
Takeoff performance on contaminated runways can be calculated with the benefit of thrust reversers. However, it is not allowed to take off at a weight higher than the weight on a dry runway. For fluid contaminants, takeoff performance data are provided up to the following depths: ‐ Dry snow: 100 mm (4") ‐ Wet snow: 20 mm (4/5") ‐ Standing water: 15 mm (3/5") ‐ Slush: 15 mm (3/5"). L2
The following assumptions are considered for the calculation: ‐ The contaminant covers the entire length of the runway in a layer that has a uniform depth and density. ‐ The friction coefficient is based on studies, and verified by tests ‐ The screen height at the end of the takeoff segment is 15 ft, instead of 35 ft.
L1
EQUIVALENCES In terms of performance: ‐ A fluid contamination is equivalent to wet, up to a maximum depth of 3 mm (1/8") of: • dry snow • wet snow • standing water • slush. ‐ "Frost" is equivalent to wet, unless a lower runway performance code is reported. RESTRICTIONS
Ident.: PER-TOF-30-30-00021544.0001001 / 20 FEB 19 Applicable to: ALL
TOGA thrust must be used in all cases. FLEX takeoff is not permitted on contaminated runways. Dispatch from and to a runway covered with wet ice is not permitted, unless an effective friction coefficient at or higher than 0.07 is demonstrated.
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TAKEOFF WITH MEL OR CDL ITEM
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TAKEOFF WITH MEL OR CDL ITEM Ident.: PER-TOF-40-00014680.0001001 / 06 MAR 15 Applicable to: ALL
The aircraft can be dispatched with deferred MEL or CDL items. MEL or CDL items that affect takeoff performance are: ‐ MEL items that reduce braking capabilities (brakes, spoilers, thrust reversers) ‐ MEL items that have an effect on thrust available (engine anti-ice valve stuck open) ‐ MEL items that may lead to a reduced systems efficiency (rudder actuator, DFS, EDP) ‐ CDL items that increase aircraft drag (seals, fairings). L2
CDL items are divided in two categories: negligible and non-negligible items. If the number of negligible CDL items is less or equal to three, no penalty applies. If the number of negligible CDL items is more than three, a drag increase for each item is applied.
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TAKEOFF RECOMMENDATIONS Ident.: PER-TOF-50-00017758.0001001 / 06 AUG 14 Applicable to: ALL
TAKEOFF CONFIGURATION As a general rule, CONF 1+F gives better performance on long runways (better climb gradient), whereas CONF 3 gives better performance on short runways (shorter takeoff distances). Sometimes, other parameters, such as obstacles can interfere. In this case, a compromise between climb and runway performance is requested, making CONF 2 the optimum configuration for takeoff. Environmental takeoff conditions may also impact the choice of the takeoff configuration. The following takeoff configuration is then recommended: OUTSIDE CONDITIONS Dry or wet, well-paved runway
FLAPS SETTINGS OBJECTIVE Use the flaps setting that provides the To extend engine life and save optimum performance. maintenance costs If takeoff weight is not limited by performance, consider using the higher flaps setting. Note:
Corresponds to OPT CONF selection in T.O PERF
High altitude takeoff Use CONF 2 or CONF 3 Badly-paved runway, or accelerate stop Use CONF 2 or CONF 3 distance limited runway
To improve comfort To improve comfort and stopping distance
FLEXIBLE TAKEOFF Flexible takeoff is the recommended method for takeoff at reduced thrust on dry and wet runways. The highest flexible temperature (TFLEX) extends engine life and saves maintenance costs. However, if a high TFLEX is reduced by a few degrees only, the engines are not significantly affected. The highest TFLEX will usually be obtained at the lowest flap setting. However, a higher flaps setting provides a lower decision speed (V1) and more comfort. To extend engine life and to save maintenance costs, the use of flaps setting that provides the highest TFLEX is recommended. However, when the difference (in terms of TFLEX) between two configurations is low, the highest of both takeoff configurations is preferable.
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PERFORMANCE IN-FLIGHT
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PER-IFT-10 In-Flight Performance Calculation
In-Flight Performance Calculation........................................................................................................................... A
PER-IFT-20 All Engines Operative Operations PER-IFT-20-10 Climb PER-IFT-20-10-10 General
General.....................................................................................................................................................................A
PER-IFT-20-10-20 Climb Thrusts
Auto-Derated Climb Thrust......................................................................................................................................A Maximum Climb Thrust............................................................................................................................................B
PER-IFT-20-20 Cruise PER-IFT-20-20-10 Speeds
Economic Mach Number (ECON Mach)................................................................................................................. A Long Range Cruise Speed (LRC)........................................................................................................................... B Fixed Speed.............................................................................................................................................................C Turbulence Speed................................................................................................................................................... D Maximum Speed...................................................................................................................................................... E
PER-IFT-20-20-20 Altitude/Ceilings
Definitions.................................................................................................................................................................A Altitude Optimization................................................................................................................................................ B
PER-IFT-20-30 Descent
General.....................................................................................................................................................................A
PER-IFT-20-40 Holding
General.....................................................................................................................................................................A
PER-IFT-30 One Engine Inoperative Operations
One Engine Inoperative Strategies......................................................................................................................... A Long Range Cruise Speed......................................................................................................................................B EO MAX Altitude..................................................................................................................................................... C Holding..................................................................................................................................................................... D Severe Icing............................................................................................................................................................. E
PER-IFT-FP Fuel Penalty Tables - Fuel Consumption Increased
Fuel Penalty Tables - Fuel Consumption Increased...............................................................................................A
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PERFORMANCE IN-FLIGHT A350
IN-FLIGHT PERFORMANCE CALCULATION
FLIGHT CREW OPERATING MANUAL
IN-FLIGHT PERFORMANCE CALCULATION Ident.: PER-IFT-10-00020638.0001001 / 03 SEP 14 Applicable to: ALL
Performance data are split by flight phases: climb, cruise, descent, and holding. In-flight performance calculation is made with the in-flight performance application (IN-FLT PERF). For more information on IN-FLT PERF application, Refer to DSC-46-OIS-20-80-100 IN-FLT PERF.
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ALL ENGINES OPERATIVE OPERATIONS - CLIMB
General GENERAL Ident.: PER-IFT-20-10-10-00020641.0001001 / 03 SEP 14 Applicable to: ALL
The climb phase starts at the end of takeoff and ends at the initial cruise level. The available thrust options are: ‐ AUTO-DERATE: the FMS automatically computes the appropriate reduced level of climb thrust, ‐ CLB: maximum climb thrust.
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ALL ENGINES OPERATIVE OPERATIONS - CLIMB
Climb Thrusts AUTO-DERATED CLIMB THRUST Ident.: PER-IFT-20-10-20-00020642.0001001 / 05 NOV 18 Applicable to: ALL
The AUTO-DERATE function automatically reduces the thrust during the climb phase. The reduced thrust level is computed by the FMS to have similar performance level as a reference case, corresponding to the climb to REC MAX ALT at MTOW with MCL thrust. The function reduces as much as possible the thrust to give the same time to climb to the cruise altitude as the reference case. It guarantees also a minimum climb capability and a limited impact on the fuel consumption. The level of thrust is optimized by the FMS as a function of the aircraft weight (TOW or GW), the target cruise altitude (CRZ FL) and the ISA deviation at cruise altitude (CRZ TEMP). The AUTO-DERATE function is selected by default in the FMS. It corresponds to the option AUTO-DERATE in the CLB THR list of the FMS ACTIVE/PERF page. The auto-derated climb thrust mode is engaged when it is selected in the FMS ACTIVE/PERF page and the thrust levers are set to CL detent position. If necessary, the flight crew can disengage the auto-derated climb thrust mode during PREFLIGHT, T.O or CLB FMS flight phases by one of the following actions: ‐ To move the thrust levers from CL to MCT detent and back to CL, or ‐ To select CLB in the CLB THR list of the FMS ACTIVE/PERF page. The AUTO-DERATE option does not affect the climb ceiling as the Maximum Climb thrust (MCL) is automatically recovered before reaching the REC MAX ALT. The AUTO-DERATE function allows to systematically reduce the thrust during the climb phase and has the following economical advantages: ‐ Increased engine life ‐ Improved engine reliability ‐ Reduced direct maintenance costs. MAXIMUM CLIMB THRUST Ident.: PER-IFT-20-10-20-00021743.0001001 / 03 SEP 14 Applicable to: ALL
The “Maximum Climb” thrust rating is the maximum thrust approved for normal climb. The FADEC commands this rating when the thrust lever is on the CL detent and the flight crew has selected CLB in the CLB THR list of the FMS ACTIVE/PERF page.
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PER-IFT-20-10-20 P 1/2 01 JUL 19
PERFORMANCE IN-FLIGHT A350
FLIGHT CREW OPERATING MANUAL
ALL ENGINES OPERATIVE OPERATIONS - CLIMB
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PER-IFT-20-10-20 P 2/2 01 JUL 19
PERFORMANCE IN-FLIGHT A350
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ALL ENGINES OPERATIVE OPERATIONS - CRUISE
Speeds ECONOMIC MACH NUMBER (ECON MACH) Ident.: PER-IFT-20-20-10-00019551.0001001 / 01 OCT 15 Applicable to: ALL
COST INDEX The Cost index (CI) is defined as the ratio between Cost of Time per time unit (CT) and Cost of Fuel per mass unit (CF). The CI value is expressed in kilograms per minute (kg/min), or hundreds of pounds per hour (100 lbs/hr). The purpose of the CI concept is to reduce Direct Operating Costs (DOC). ECON MACH For a given CI, ECON Mach is defined as the Mach for which DOC are minimum. LONG RANGE CRUISE SPEED (LRC) Ident.: PER-IFT-20-20-10-00019552.0001001 / 03 SEP 14 Applicable to: ALL
The Long Range Cruise speed (LRC) is defined as the Mach number for which the specific range is equal to 99 % of the maximum specific range. L2 For more information, Refer to DSC-22-FMS-10-50-20 FMS Speed Mode (ECON/LRC). FIXED SPEED Ident.: PER-IFT-20-20-10-00019553.0001001 / 03 SEP 14 Applicable to: ALL
The fixed speed is either a Mach or a CAS. TURBULENCE SPEED Ident.: PER-IFT-20-20-10-00019555.0001001 / 03 SEP 14 Applicable to: ALL
Turbulence speeds are recommended when the aircraft flies in a turbulent atmosphere. The recommended turbulence speed is between Green Dot and 300 kt/M 0.85. The MAX TURB function indicated on the MFD PERF CRZ page displays the maximal speed/Mach not to exceed according to this recommendation.
VIR A350 FLEET FCOM
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PER-IFT-20-20-10 P 1/2 01 JUL 19
PERFORMANCE IN-FLIGHT A350
FLIGHT CREW OPERATING MANUAL
ALL ENGINES OPERATIVE OPERATIONS - CRUISE
MAXIMUM SPEED Ident.: PER-IFT-20-20-10-00019556.0001001 / 03 SEP 14 Applicable to: ALL
Maximum speed is either: ‐ The Maximum Operating Mach (MMO), or ‐ The Maximum Operating speed (VMO), or ‐ The speed limited by the available thrust. L2
For more information on Maximum Speed, Refer to LIM-AG-SPD Maximum Operating Speed VMO/MMO.
VIR A350 FLEET FCOM
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PER-IFT-20-20-10 P 2/2 01 JUL 19
PERFORMANCE IN-FLIGHT A350
FLIGHT CREW OPERATING MANUAL
ALL ENGINES OPERATIVE OPERATIONS - CRUISE
Altitude/Ceilings DEFINITIONS Ident.: PER-IFT-20-20-20-00019557.0001001 / 03 SEP 14 Applicable to: ALL
OPTIMUM ALTITUDE The optimum altitude (OPT ALT) is the altitude at which the SR is maximum. REC MAX Maximum altitude is defined as the lower of: ‐ Maximum altitude at maximum cruise thrust in level flight ‐ Maximum altitude at maximum climb thrust with 300 ft/min vertical speed ‐ Maximum certified altitude ‐ 1.3 g buffet limited altitude. ALTITUDE OPTIMIZATION Ident.: PER-IFT-20-20-20-00019558.0001001 / 05 NOV 18 Applicable to: ALL
The optimum altitude definition depends on the cruise type. The optimum altitude (OPT) displayed on the FMS-PERF page and the optimum altitude (OPTIMUM ALT) determined by the OIS IN-FLT PERF Cruise computation for a given Cost Index (CI) are the result of a minimum cost analysis. To determine these optimum altitudes, both the FMS and IN-FLT PERF calculate the value of the Cost Function (CF) based on the CI at 500 ft increment altitudes. The altitude that provides the lowest value for the CF is displayed as OPT on the FMS-PERF page and as OPTIMUM ALT on the OIS IN-FLT PERF. These optimum altitude computations take into account a large number of parameters. The FMS and the OIS consider some of these parameters in a different manner. Therefore, OPT on the FMS and OPTIMUM ALT on the OIS may differ. L2 The main contributor to any difference between OPT on the FMS and OPTIMUM ALT on the OIS is the wind.
VIR A350 FLEET FCOM
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PER-IFT-20-20-20 P 1/2 01 JUL 19
PERFORMANCE IN-FLIGHT A350
FLIGHT CREW OPERATING MANUAL
ALL ENGINES OPERATIVE OPERATIONS - CRUISE
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ALL ENGINES OPERATIVE OPERATIONS - DESCENT
GENERAL Ident.: PER-IFT-20-30-00020649.0001001 / 03 SEP 14 Applicable to: ALL
The descent phase starts at the top of descent and ends at landing or level off. In the case of an emergency descent, MMO/VMO is the best speed profile as it gives high rate of descent, which can be increased by extending the speed brakes, if needed.
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PER-IFT-20-30 P 1/2 01 JUL 19
PERFORMANCE IN-FLIGHT A350
FLIGHT CREW OPERATING MANUAL
ALL ENGINES OPERATIVE OPERATIONS - DESCENT
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ALL ENGINES OPERATIVE OPERATIONS - HOLDING
GENERAL Ident.: PER-IFT-20-40-00020650.0001001 / 03 SEP 14 Applicable to: ALL
The holding phase, when required, starts before the landing phase above the destination or alternate airport. In CONF CLEAN, the standard holding speed is the green dot speed + 20 kt, as it is a good approximation of the maximum endurance speed.
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PER-IFT-20-40 P 1/2 01 JUL 19
PERFORMANCE IN-FLIGHT A350
FLIGHT CREW OPERATING MANUAL
ALL ENGINES OPERATIVE OPERATIONS - HOLDING
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PER-IFT-20-40 P 2/2 01 JUL 19
PERFORMANCE IN-FLIGHT A350
ONE ENGINE INOPERATIVE OPERATIONS
FLIGHT CREW OPERATING MANUAL
ONE ENGINE INOPERATIVE STRATEGIES Ident.: PER-IFT-30-00019545.0001001 / 03 SEP 14 Applicable to: ALL
For more information about One Engine Inoperative Strategies, Refer to FCTM/PR-AEP-ENG Engine Failure During Cruise. LONG RANGE CRUISE SPEED Ident.: PER-IFT-30-00019546.0001001 / 03 SEP 14 Applicable to: ALL
If the EO mode of the FMS is active, the FMS takes the engine failure into account to compute the EO-LRC speed/ Mach. EO MAX ALTITUDE Ident.: PER-IFT-30-00019547.0001001 / 04 MAY 16 Applicable to: ALL
The FMS Engine Out Maximum (EO MAX) altitude is a precomputed value, function of the aircraft gross weight and DISA, displayed on all the PERF pages if one engine is inoperative. L2
EO MAX altitude respects the following criteria: ‐ It can be flown with LRC speed ‐ It can be held in level flight with: • The operating engine at "Maximum Continuous Thrust" rating • The failed engine in windmilling • Anti-ice OFF ‐ It can be reached before buffeting with a margin of 0.3 g ‐ It is less than the maximum certified altitude. HOLDING
Ident.: PER-IFT-30-00020652.0001001 / 03 SEP 14 Applicable to: ALL
In CONF CLEAN, the standard EO holding speed is the green dot speed + 20 kt.
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PER-IFT-30 P 1/2 03 FEB 20
PERFORMANCE IN-FLIGHT A350
FLIGHT CREW OPERATING MANUAL
ONE ENGINE INOPERATIVE OPERATIONS
SEVERE ICING Ident.: PER-IFT-30-00021742.0003001 / 06 SEP 17 Applicable to: ALL
If severe icing conditions are encountered, ice may build up on non heated structure. In these conditions: ‐ The minimum speed is Green Dot in clean configuration ‐ The nominal gross OEI Level off is reduced by: • 5 800 ft for weights less than 300 t (661 400 lb) • 6 800 ft for weights more than 320 t (705 500 lb) • linear interpolation between 5 800 ft and 6 800 ft for intermediate values of weights. L2 The nominal gross Level off is calculated at Green Dot speed, engines at MCT, and Anti-ice Off. The reduction in altitude takes into account the effect of activation of Engine and Wing Anti-ice, in addition to ice accretion.
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PER-IFT-30 P 2/2 03 FEB 20
PERFORMANCE IN-FLIGHT A350
FLIGHT CREW OPERATING MANUAL
FUEL PENALTY TABLES - FUEL CONSUMPTION INCREASED
FUEL PENALTY TABLES - FUEL CONSUMPTION INCREASED Applicable to: ALL Ident.: PER-IFT-FP-FPF-00019614.0001001 / 27 FEB 17 Applicable to: ALL
USE OF THE FUEL PENALTY TABLES L2
For more information, Refer to FCTM/PR-AEP-FUEL Fuel Penalty.
L1
If an ECAM procedure displays FUEL CONSUMPT INCRSD : ECAM STATUS PAGE...................................................................................................SELECT INOP SYS........................................................................................................................ CHECK FCOM FUEL PENALTY TABLE...................................................................................... CHECK TOTAL FUEL PENALTY............................................................................................ COMPUTE Add together all the applicable fuel penalties determined with the fuel penalty table. FMS DATA/STATUS PAGE........................................................................................... SELECT FMS FUEL PENALTY UPDATE............................................................................... CONSIDER If the fuel penalty value is determined from the FCOM FUEL PENALTY TABLE, this value must be added to the existing value (if any) on the FMS DATA/STATUS page.
L2 L1
L2
L1
L2
FOR BETTER RANGE : REDUCE CRZ MACH/SPD MIN CRZ SPD : GREEN DOT FUEL CONSUMPTION................................................................................................MONITOR The flight crew must still monitor and assess the real fuel consumption. Consider the FMS fuel penalty adjustment, if required.
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PER-IFT-FP P 1/4 03 FEB 20
PERFORMANCE IN-FLIGHT A350
FLIGHT CREW OPERATING MANUAL
FUEL PENALTY TABLES - FUEL CONSUMPTION INCREASED
Ident.: PER-IFT-FP-FPF-00023881.0002001 / 04 JUN 18 Applicable to: ALL
FUEL PENALTY TABLE L2
The fuel penalty values of the FCOM table are conservative, and provided as a guideline for both of the following: ‐ Increase flight crew awareness, particularly when the fuel penalty associated with the failure may change during the flight ‐ Help the decision making.
L1
Fuel penalties less than 3 % are neither leading to the FUEL CONSUMPT INCRSD display on the ECAM nor included in the table. The list of INOP SYS appears in the same order of priority as it appears on the STATUS page on the ECAM. TOTAL FUEL PENALTY : ADD TOGETHER ALL APPLICABLE LINES INOP SYS or ECAM Alert REASON FOR FUEL CONSUMPT INCRSD
STABILIZER
Stabilizer locked
PRIM 1+2+3
Outer ailerons slightly extended
RUDDER
Rudder jammed
L(R) ELEVATOR
Left or right elevator partly extended 1 inner aileron partly extended 1 inner aileron fully extended 2 inner ailerons partly extended 1 outer aileron partly extended 1 outer aileron fully extended 2 outer ailerons partly extended 1 spoiler inoperative as per MEL item 27-64-01 to 27-64-06. For more information, Refer to FCTM/FCTM/Fuel Penalty
L(R) INR AILERON L(R) OUTR AILERON
PART SPLRs
1 spoiler in runaway position (fully extended) 1 spoiler or 1 pair of spoilers inoperative and suspected extended 2 spoilers or 2 pairs of spoilers inoperative and suspected extended
FUEL PENALTY Up to 65 % (Not Variable) (3)
10 % Up to 25 % (Not Variable) (3)
3% 25 % 40 % 40 % 15 % 35 % 25 % Refer to MEL 30 % (2)
Variable Max 8 % (1)
Variable Max 20% (1)
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PER-IFT-FP P 2/4 03 FEB 20
PERFORMANCE IN-FLIGHT A350
FLIGHT CREW OPERATING MANUAL
FUEL PENALTY TABLES - FUEL CONSUMPTION INCREASED
FUEL PENALTY TABLE (Cont'd) TOTAL FUEL PENALTY : ADD TOGETHER ALL APPLICABLE LINES INOP SYS or ECAM Alert REASON FOR FUEL CONSUMPT INCRSD 3 spoilers or 3 pairs of spoilers inoperative and suspected extended
(1)
Variable Max 25 %
4 spoilers or 4 pairs of spoilers inoperative and suspected extended
MOST SPLRs
(1)
Variable Max 25 %
5 spoilers or 5 pairs of spoilers inoperative and suspected extended
(1)
Variable Max 30 %
6 spoilers or 6 pairs of spoilers inoperative and suspected extended
(1)
Variable Max 30 %
7 spoilers or 7 pairs of spoilers inoperative and suspected extended DIFF FLAP SETTING L/G RETRACTION L/G DOORS FUEL WINGS NOT BALANCED F/CTL RUDDER PEDAL JAMMED F/CTL RUDDER TRIM RUNAWAY
Abnormal Configuration
FUEL PENALTY Variable Max 25 %
(1)
Up to 6 % (Not Variable)
Flaps slightly extended and locked after flap deployment in cruise
(3)
All L/G extended One main L/G extended Nose L/G extended All L/G doors open One main L/G door open Nose L/G door open F/CTL surfaces partly extended to compensate the lateral imbalance
130 % 60 % 30 % 25 % 9% 3% Above 4 t (8.8 klb), Refer to Graph.
If the AP is not available: See RUDDER CONF 1 CONF 1+F CONF 2 CONF 3 (Takeoff) CONF 3 (Landing) CONF FULL RAT Extended
15 % 40 % 50 % 60 % 105 % 175 % 4%
(1)
In the case of spoiler(s) failure, the affected spoiler(s) may gradually extend during the flight up to the balanced position. The fuel penalty may therefore increase during the flight.
(2)
A visual inspection from the cabin, if time permits, can confirm the extension of the spoiler.
Continued on the following page
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PER-IFT-FP P 3/4 03 FEB 20
PERFORMANCE IN-FLIGHT A350
FUEL PENALTY TABLES - FUEL CONSUMPTION INCREASED
FLIGHT CREW OPERATING MANUAL
FUEL PENALTY TABLE (Cont'd) (3)
Depending of the flight control surface position at the time of the failure, the flight crew must determine the fuel penalty within the specified range.
Ident.: PER-IFT-FP-FPF-00022530.0002001 / 24 JUL 17 Applicable to: ALL
FUEL PENALTY - IMBALANCE The following graph provides the fuel penalty factor that depends on both the fuel imbalance, and the fuel quantity in the heaviest wing tank. When the fuel imbalance is below 4 000 kg (8.8 klb), the associated fuel penalty is below 3 %.
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PER-IFT-FP P 4/4 03 FEB 20
PERFORMANCE LANDING
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PERFORMANCE LANDING A350
FLIGHT CREW OPERATING MANUAL
PRELIMINARY PAGES - TABLE OF CONTENTS
PER-LDG-10 Landing Performance Calculation
General.....................................................................................................................................................................A Landing Parameters.................................................................................................................................................B
PER-LDG-20 Landing Speeds and Distances Definitions
Landing Speeds....................................................................................................................................................... A Landing Distances Definitions................................................................................................................................. B
PER-LDG-30 Runway Conditions
Dry Runway............................................................................................................................................................. A Damp and Wet Runway.......................................................................................................................................... B Contaminated Runway............................................................................................................................................ C Runway Condition Assessment Matrix for Landing................................................................................................ D
PER-LDG-40 Dispatch Requirements
General.....................................................................................................................................................................A Dispatch on Dry Runway.........................................................................................................................................B Dispatch on Wet Runway........................................................................................................................................C Dispatch on Contaminated Runway........................................................................................................................D Dispatch with MEL or CDL Item............................................................................................................................. E In-Flight Landing Distance Crosscheck................................................................................................................... F ROW Landing Distance Crosscheck.......................................................................................................................G
PER-LDG-50 In-Flight Performance Assessment
General.....................................................................................................................................................................A Landing Performance without In-Flight Failure....................................................................................................... B Landing Performance following In-Flight Failure.....................................................................................................C ROW Landing Distance Crosscheck.......................................................................................................................D
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PER-LDG-PLP-TOC P 1/2 15 MAR 20
PERFORMANCE LANDING A350
FLIGHT CREW OPERATING MANUAL
PRELIMINARY PAGES - TABLE OF CONTENTS
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PERFORMANCE LANDING A350
PRELIMINARY PAGES - SUMMARY OF HIGHLIGHTS
FLIGHT CREW OPERATING MANUAL
Localization Title
PER-LDG-30 Runway Condition Assessment Matrix for Landing
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Toc Index D
ID 1
Reason Update of the landing maximum crosswind limit from 35kt up to 40kt for dry and damp conditions.
PER-LDG-PLP-SOH P 1/2 15 MAR 20
PERFORMANCE LANDING A350
FLIGHT CREW OPERATING MANUAL
PRELIMINARY PAGES - SUMMARY OF HIGHLIGHTS
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PER-LDG-PLP-SOH P 2/2 15 MAR 20
PERFORMANCE LANDING A350
FLIGHT CREW OPERATING MANUAL
LANDING PERFORMANCE CALCULATION
GENERAL Ident.: PER-LDG-10-00021541.0001001 / 03 SEP 14 Applicable to: ALL
The landing performance calculation enables: ‐ At dispatch, to check that the aircraft can land at destination for the predicted conditions, in compliance with the regulatory requirements ‐ During flight, to check that the aircraft can land at destination for the actual conditions. L2 The calculation is made in compliance with the recommendations coming from the FAA Takeoff And Landing Performance Assessment Aviation Rulemaking Group (called TALPA ARC). The landing performance calculation is made with the landing performance (LDG PERF) application. For more information on the LDG PERF application, Refer to DSC-46-OIS-20-80-110 LDG PERF.
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PER-LDG-10 P 1/4 01 JUL 19
PERFORMANCE LANDING A350
LANDING PERFORMANCE CALCULATION
FLIGHT CREW OPERATING MANUAL
LANDING PARAMETERS Ident.: PER-LDG-10-00016750.0001001 / 05 NOV 18 Applicable to: ALL
The landing performance parameters are: ‐ The characteristics of the runway L2
L1
L2 L3
L2
L1 L2
L1 L2
L1
• • • •
Landing Distance Available (LDA) Elevation Slope Missed approach gradient.
‐ The regulatory requirements ‐ The outside conditions • Wind As per regulation, the computation is based on 150 % of the entered tailwind, and 50 % of the entered headwind. The crosswind component does not affect the calculation of the landing distance. However, a maximum crosswind component is associated with each runway condition. For more information about crosswind limitation, Refer to LIM-AG-OPS Maximum Crosswind for Takeoff and Landing. • Outside Air Temperature (OAT) • Sea level atmospheric pressure (QNH) • Icing conditions (anti-ice selection) • Runway condition, or landing performance level. ‐ The aircraft configuration • • • • •
Landing Weight (LW) Aerodynamic configuration Air conditioning setting Aircraft CG position Approach speed and go-around speed.
‐ The aircraft status. • MEL items • CDL items • Abnormal and emergency configuration (ABN EMER) for in-flight computation only. The following parameters can be optimized: ‐ Aerodynamics configuration ‐ Go-around speed.
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PER-LDG-10 P 2/4 01 JUL 19
PERFORMANCE LANDING A350
FLIGHT CREW OPERATING MANUAL L2
LANDING PERFORMANCE CALCULATION
For more information about the go-around speed, Refer to PER-LDG-20 Landing Speeds.
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PER-LDG-10 P 3/4 01 JUL 19
PERFORMANCE LANDING A350
FLIGHT CREW OPERATING MANUAL
LANDING PERFORMANCE CALCULATION
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PERFORMANCE LANDING A350
FLIGHT CREW OPERATING MANUAL
LANDING SPEEDS AND DISTANCES DEFINITIONS
LANDING SPEEDS Ident.: PER-LDG-20-00016524.0001001 / 03 SEP 14 Applicable to: ALL
LOWEST SELECTABLE SPEED (VLS) VLS is the lowest selectable speed. VLS is used to determine the Final Approach Speed (VAPP) in normal conditions. For more information about VLS, Refer to DSC-22-27-10-20 VLS. REFERENCE SPEED (VREF) VREF is equal to the VLS of CONF FULL. VREF is used to determine the Final Approach Speed (VAPP) when a system failure affects the landing performance. For more information about VREF, Refer to DSC-22-27-10-10 VREF. FINAL APPROACH SPEED (VAPP) VAPP is the speed of the aircraft when crossing the runway threshold. The flaps/slats are in the landing configuration, and the landing gears are extended. For more information about VAPP, Refer to DSC-22-27-10-20 VAPP. GO-AROUND SPEED In the case of a missed approach, the go-around climb gradient is calculated at the go-around speed. The standard go-around speed is 1.23 VS1G of the go-around configuration. For approaches with a decision height at or above 200 ft, where approach climb performance is found restrictive, the go-around speed can be increased up to 1.3 VS1G of the go-around configuration.
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PER-LDG-20 P 1/4 01 JUL 19
PERFORMANCE LANDING A350
LANDING SPEEDS AND DISTANCES DEFINITIONS
FLIGHT CREW OPERATING MANUAL
LANDING DISTANCES DEFINITIONS Ident.: PER-LDG-20-00021576.0001001 / 03 APR 17 Applicable to: ALL
REQUIRED LANDING DISTANCE (RLD) The RLD is the regulatory reference to be used for dispatch landing performance computation. The RLD is the factored certified landing distance based on: ‐ Maximum manual braking initiated immediately after main gear touchdown ‐ Prompt selection of max reverse thrust, maintained to 70 kt, and idle thrust to full stop (when credit is used) ‐ Antiskid system and all ground spoilers operative ‐ The regulatory dispatch factor. Note:
The Required Landing Distance calculation considers the effect of the MEL/CDL items that affects the landing performance.
IN-FLIGHT LANDING DISTANCE (LD) The In-Flight Landing Distance reflects the performance achievable in a typical operational landing without margin. The In-Flight Landing Distance calculation assumes: ‐ An airborne phase of 7 s from threshold to touchdown ‐ In the case of manual braking: maximum manual braking initiated immediately after main gear touchdown ‐ In the case of autobrake: normal system delays in braking activation ‐ Antiskid system and all ground spoilers operative ‐ Prompt selection of max reverse thrust, maintained to 70 kt, and idle thrust to full stop (when credit is used). Note:
The In-Flight Landing Distance calculation considers the effect of the inoperative system(s) following: ‐ An MEL/CDL dispatch that affects the landing performance ‐ An in-flight failure (ECAM alert) that affects the landing performance.
FACTORED IN-FLIGHT LANDING DISTANCE (FLD) The definition of the In-Flight Landing Distance does not include any margin. The In-Flight Landing Distance is a realistic distance achievable in nominal conditions, i.e. the actual conditions during the landing are those used for the computation.
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PER-LDG-20 P 2/4 01 JUL 19
PERFORMANCE LANDING A350
FLIGHT CREW OPERATING MANUAL
LANDING SPEEDS AND DISTANCES DEFINITIONS
it is recommended to apply an appropriate margin to the In-Flight Landing Distance (either determined with or without failure) in order to cover: ‐ The variability in flying techniques (e.g. flare execution, delay in application of the deceleration means) ‐ Unexpected conditions at landing (e.g. real runway friction vs. reporting, turbulence, crosswind). L2
The Factored In-Flight Landing Distance is defined as: ‐ The In-Flight Landing Distance multiplied by a Factor, or ‐ The In-Flight Landing Distance plus an Increment.
L1
It is the Airlines responsibility to define the margins (and their applicability) to apply on top of the In-Flight Landing Distance. The recommended margin is a Factor of 1.15 on the In-Flight Landing Distance. Under exceptional circumstances, the flight crew may decide to disregard this margin. ROW LANDING DISTANCE The ROW landing distance is calculated by the PRIMs and displayed on the ANF. For more information about the ROW system, Refer to DSC-34-32-20-10 ROW.
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PER-LDG-20 P 3/4 01 JUL 19
PERFORMANCE LANDING A350
FLIGHT CREW OPERATING MANUAL
LANDING SPEEDS AND DISTANCES DEFINITIONS
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PER-LDG-20 P 4/4 01 JUL 19
PERFORMANCE LANDING A350
RUNWAY CONDITIONS
FLIGHT CREW OPERATING MANUAL
DRY RUNWAY Ident.: PER-LDG-30-00021599.0001001 / 03 SEP 14 Applicable to: ALL
A runway is dry when its surface is not: ‐ Damp ‐ Wet ‐ Contaminated. DAMP AND WET RUNWAY Ident.: PER-LDG-30-00021600.0001001 / 03 SEP 14 Applicable to: ALL
DAMP RUNWAY A runway is considered as damp, when the surface of the runway is not dry, but the water on the surface does not cause a shiny appearance. Note:
In line with the recommendations from the FAA Takeoff And Landing Performance Assessment Aviation Rulemaking Group, the applicable performance for this runway condition is GOOD and not DRY. This is not communicated via the definitions but via the RCAM.
WET RUNWAY A runway is considered as wet, when the surface of the runway has a shiny appearance due to a thin film of water. When this film does not exceed 3 mm (1/8"), there is no significant danger of hydroplaning.
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PER-LDG-30 P 1/6 15 MAR 20
PERFORMANCE LANDING A350
RUNWAY CONDITIONS
FLIGHT CREW OPERATING MANUAL
CONTAMINATED RUNWAY Ident.: PER-LDG-30-00021602.0001001 / 08 JUL 19 Applicable to: ALL
A runway is contaminated when more than 25 % of its surface is covered with: ‐ A layer of fluid contaminant not considered as thin ‐ A hard contaminant. DESCRIPTION OF FLUID CONTAMINANTS In terms of performance, a contaminated runway is a runway covered by a fluid contaminant with a depth of more than 3 mm (1/8"). The fluid contaminant can be either: ‐ Dry snow ‐ Wet snow ‐ Standing water ‐ Slush. Fluid Contaminants reduce friction forces, and cause: ‐ Precipitation drag ‐ Hydroplaning. L2
L1
Fluid contaminants descriptions: ‐ Dry snow is snow that, if compacted by hand, does not stay compressed when released. The wind can blow dry snow. The density of dry snow is approximately 0.2 kg/l (1.7 lb/US Gal). ‐ Wet snow is snow that, if compacted by hand, stays compressed when released, and with which snowballs can be created. The density of wet snow is approximately 0.4 kg/l (3.35 lb/US Gal). ‐ Standing water occurs due to heavy rain and/or not sufficient runway drainage. Standing water has a depth of more than 3 mm. ‐ Slush is snow soaked with water, which spatters when stepped on firmly. Slush occurs at temperatures of approximately 5 °C, and has a density of approximately 0.85 kg/l (7.1 lb/US Gal). DESCRIPTION OF HARD CONTAMINANTS In terms of performance, a contaminated runway is a runway covered by a hard contaminant that can be either: ‐ Compacted snow, ‐ Ice (Cold and Dry) ‐ Wet ice. Hard contaminants only reduce friction forces.
L2
Hard contaminants descriptions: ‐ Compacted snow: the maintenance personnel use a snow groomer to compress the snow on a runway in order to obtain a hard surface
VIR A350 FLEET FCOM
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PER-LDG-30 P 2/6 15 MAR 20
PERFORMANCE LANDING A350
RUNWAY CONDITIONS
FLIGHT CREW OPERATING MANUAL
‐ Ice (Cold and Dry): situation in which ice occurs on the runway in cold and dry conditions ‐ Wet ice: when the ice on a runway melts, or there are loose/fluid contaminants on top of the ice, the ice is referred to as "wet ice". When there is wet ice on a runway, braking and directional control are difficult or not possible, because the runway surface is very slippery. L1 L2
LANDING PERFORMANCE CALCULATION COMPUTATION ASSUMPTIONS The following assumptions are considered for the calculation: ‐ The contaminant covers the entire length of the runway ‐ For fluid contaminants, the landing distance calculation does not take credit of the precipitation drag.
L1
EQUIVALENCES In terms of performance: ‐ A fluid contamination is equivalent to wet, up to a maximum depth of 3 mm (1/8") of: • dry snow • wet snow • standing water • slush. ‐ "Frost" is equivalent to wet, unless a lower runway performance code is reported ‐ "Slippery Wet" is equivalent to 10 mm (2/5") of dry snow. RESTRICTIONS For maximum depth of fluid contaminants, Refer to PER-LDG-30 Runway Condition Assessment Matrix for Landing. Dispatch from and to a runway covered with wet ice is not permitted, unless an effective friction coefficient at or higher than 0.07 is demonstrated.
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PER-LDG-30 P 3/6 15 MAR 20
PERFORMANCE LANDING A350
RUNWAY CONDITIONS
FLIGHT CREW OPERATING MANUAL
RUNWAY CONDITION ASSESSMENT MATRIX FOR LANDING Ident.: PER-LDG-30-00018439.0002001 / 06 NOV 19 Applicable to: ALL 1
RUNWAY SURFACE CONDITIONS Runway State or / and Runway Contaminant Dry Damp Wet: Up to 3 mm (1/8”) of water Slush: (3) Up to 3 mm (1/8”) Dry Snow: (3) Up to 3 mm (1/8”) Wet Snow: (3) Up to 3 mm (1/8”) Frost Compacted Snow: OAT at or below -15 °C
ESF(1) or PiRep(2)
Related Observations Maximum Landing on Deceleration Crosswind Performance and Directional (Gust Control Code Level included)
-
-
6
DRY
40 kt
Good
Braking deceleration is normal for the wheel braking effort applied. Directional control is normal.
5
GOOD
40 kt
Good to Medium
Braking deceleration and controllability is between Good and Medium.
4
GOOD TO MEDIUM
Braking deceleration is noticeably reduced for the wheel braking Medium effort applied. Directional control may be reduced.
3
MEDIUM
Braking deceleration and controllability is between Medium and Poor. Potential for Hydroplaning exists.
2
MEDIUM TO POOR
27 kt (4)
Dry Snow: (3)
More than 3 mm (1/8”), up to 100 mm (4”) Wet Snow: (3) More than 3 mm (1/8”), up to 30 mm (6/5”) Dry Snow over Compacted Snow(3) Wet Snow over Compacted Snow(3) Compacted Snow: OAT above -15 °C Slippery Wet Water: More than 3 mm (1/8”), up to 15 mm (3/5”) Slush: (3) More than 3 mm (1/8”), up to 15 mm (3/5”)
VIR A350 FLEET FCOM
Medium to Poor
D→
20 kt (4)
20 kt (4)
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PER-LDG-30 P 4/6 15 MAR 20
PERFORMANCE LANDING A350
RUNWAY CONDITIONS
FLIGHT CREW OPERATING MANUAL
Ice (cold and dry)
Wet Ice Water on top of Compacted Snow Dry Snow(3) or Wet Snow(3) over Ice
Braking deceleration is significantly reduced for the Poor wheel braking effort applied. Directional control may be significantly reduced. Braking deceleration is minimal to non-existent for Less the wheel braking than Poor effort applied. Directional control may be uncertain.
Continued from the previous page
1
POOR
-
-
15 kt (4)
-
(1)
ESF: Estimated Surface Friction
(2)
PiRep: Pilot Report of Braking Action
(3)
For loose contaminants (Dry Snow, Wet Snow or Slush), the friction measurements are unreliable and should not be considered for the landing performance assessment.
(4)
Maximum recommended value based on computations
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PER-LDG-30 P 5/6 15 MAR 20
PERFORMANCE LANDING A350
FLIGHT CREW OPERATING MANUAL
RUNWAY CONDITIONS
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PER-LDG-30 P 6/6 15 MAR 20
PERFORMANCE LANDING A350
DISPATCH REQUIREMENTS
FLIGHT CREW OPERATING MANUAL
GENERAL Ident.: PER-LDG-40-00018372.0001001 / 13 JAN 15 Applicable to: ALL
LANDING PERFORMANCE CALCULATION
L2 L1
The landing performance calculation is made with the landing performance (LDG PERF) application, with the computation type set to DISPATCH. For more information on the LDG PERF application, Refer to DSC-46-OIS-20-80-110 LDG PERF. REQUIREMENT ON THE LANDING DISTANCE The Landing Distance Available (LDA) at destination must be at least equal to the Required Landing Distance (RLD) for the planned landing weight. REQUIREMENT ON THE GO-AROUND PERFORMANCE The go-around climb gradient must be at least equal to: ‐ 2.1 % ‐ The gradient published in the airport approach chart. Note:
EU-OPS requires a minimum go-around climb gradient of 2.5 % for instrument approaches with decision heights below 200 ft. DISPATCH ON DRY RUNWAY
Ident.: PER-LDG-40-00016506.0001001 / 03 SEP 14 Applicable to: ALL L2
Landing performance is calculated without the benefit of thrust reversers, as per regulation. For information, the AFM publishes the autoland landing distance increments on dry runways. DISPATCH ON WET RUNWAY
Ident.: PER-LDG-40-00016509.0001001 / 03 SEP 14 Applicable to: ALL
Landing performance is calculated without the benefit of thrust reversers, as per regulation. The RLD for a wet runway is the RLD for the dry runway multiplied by 1.15.
VIR A350 FLEET FCOM
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PER-LDG-40 P 1/4 01 JUL 19
PERFORMANCE LANDING A350
DISPATCH REQUIREMENTS
FLIGHT CREW OPERATING MANUAL
DISPATCH ON CONTAMINATED RUNWAY Ident.: PER-LDG-40-00016511.0001001 / 03 SEP 14 Applicable to: ALL
Landing performance can be calculated with the benefit of the thrust reversers. For operators complying with EU-OPS regulation, the landing weight on a contaminated runway cannot exceed the landing weight on a wet runway. DISPATCH WITH MEL OR CDL ITEM Ident.: PER-LDG-40-00016512.0001001 / 06 MAR 15 Applicable to: ALL
The aircraft can be dispatched with deferred MEL or CDL items. In this case, the LDA must be at least equal to the RLD calculated with the applicable MEL or CDL item selected. MEL or CDL items that affect landing performance are: ‐ MEL items that reduce braking capabilities (brakes, spoilers, thrust reversers if applicable) ‐ MEL items that have an impact on thrust available for go-around (engine anti-ice valve stuck open) ‐ CDL items that increase aircraft drag (seals, fairings). L2
CDL items are divided in two categories: negligible and non-negligible items. If the number of negligible CDL items is less or equal to three, no penalty applies. If the number of negligible CDL items is more than three, a drag increase for each item is applied. IN-FLIGHT LANDING DISTANCE CROSSCHECK
Ident.: PER-LDG-40-00019134.0001001 / 03 SEP 14 Applicable to: ALL
The Factored In-Flight Landing Distance may, in some cases, and in particular on contaminated runway, exceed the RLD considered at dispatch. The requirements for dispatch remain unchanged and are based on the RLD. However, when arrival conditions are expected to be marginal it is recommended to make a preliminary calculation of In-Flight Landing Distance or Factored In-Flight Landing Distance at dispatch in order to nominate suitable destination alternates. The landing performance calculation may also check that the aircraft can land at destination in compliance with In-Flight Landing Distance. In this case, the landing distance considered for dispatch is the maximum of the RLD and the Factored In-Flight Landing Distance.
VIR A350 FLEET FCOM
D to F
PER-LDG-40 P 2/4 01 JUL 19
PERFORMANCE LANDING A350
DISPATCH REQUIREMENTS
FLIGHT CREW OPERATING MANUAL
ROW LANDING DISTANCE CROSSCHECK Ident.: PER-LDG-40-00021304.0001001 / 04 DEC 14 Applicable to: ALL
The ROW landing distance may, in some cases, exceed the RLD considered at dispatch. The requirements for dispatch remains unchanged and are based on the RLD. However, if the conditions remain unchanged, the flight crew will not be authorized to initiate an approach (unless a specific authorization is obtained from the appropriate authority to deactivate the ROW/ROP). As a consequence, the dispatch conditions should be adapted in order to prevent a ROW alert to be triggered.
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PER-LDG-40 P 3/4 01 JUL 19
PERFORMANCE LANDING A350
FLIGHT CREW OPERATING MANUAL
DISPATCH REQUIREMENTS
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PER-LDG-40 P 4/4 01 JUL 19
PERFORMANCE LANDING A350
FLIGHT CREW OPERATING MANUAL
IN-FLIGHT PERFORMANCE ASSESSMENT
GENERAL Ident.: PER-LDG-50-00018097.0001001 / 28 JAN 19 Applicable to: ALL
During flight, the flight crew must perform a landing performance computation in all cases. The landing performance calculation is made with the landing performance (LDG PERF) application, with the computation type set to IN-FLIGHT. L2 For more information on the LDG PERF application, Refer to DSC-46-OIS-20-80-110 LDG PERF. L1 The landing distance used for this computation is the Factored In-Flight Landing Distance (FLD). The flight crew uses the RCAM to determine the runway landing performance and code. If the aircraft has been dispatched with deferred MEL or CDL items, the In-Flight Landing Distance and Factored In-Flight Landing Distance must be calculated with the applicable MEL or CDL items selected. Under exceptional circumstances, the flight crew may decide to disregard the Factored In-Flight Landing Distance. In this case the flight crew must check that the In-Flight Landing Distance is shorter than the LDA at the destination or diversion airport. L2 For more information on In-Flight Landing Distances, Refer to PER-LDG-20 Landing Distances Definitions. LANDING PERFORMANCE WITHOUT IN-FLIGHT FAILURE Ident.: PER-LDG-50-00019790.0001001 / 13 JAN 15 Applicable to: ALL
LANDING PERFORMANCE CALCULATION L2 L1
The flight crew enters the expected landing conditions and calculates the landing performance. For more information on the LDG PERF application, Refer to DSC-46-OIS-20-80-110 LDG PERF. FLAPS LEVER POSITION The FLAPS lever position for landing is at flight crew's discretion. VAPP DETERMINATION VAPP is calculated by the FMS and is displayed on the APPR panel of the FMS PERF page.
L2
The VAPP is calculated by the FMS as the maximum of: ‐ VMCL + 5 kt ‐ 1.23*VS1G + (5 ≤ headwind/3 ≤ 15)
VIR A350 FLEET FCOM
A to B
PER-LDG-50 P 1/4 03 FEB 20
PERFORMANCE LANDING A350
FLIGHT CREW OPERATING MANUAL
IN-FLIGHT PERFORMANCE ASSESSMENT
LANDING PERFORMANCE FOLLOWING IN-FLIGHT FAILURE Ident.: PER-LDG-50-00018101.0001001 / 13 JAN 15 Applicable to: ALL
LANDING PERFORMANCE ECAM INDICATIONS
L2
L1
L2 L1
After an aircraft system failure that occurs in flight, the flight crew follows the associated ECAM procedure. When required, the ECAM displays landing performance indications in the applicable procedure. The ECAM alert items are displayed on the ECAM STATUS page. The ECAM displays LDG DIST AFFECTED or LDG PERF AFFECTED if an ECAM alert item affects landing performance. LDG DIST AFFECTED means that only the landing distance is affected. LDG PERF AFFECTED means that both approach speed and landing distance are affected. LANDING PERFORMANCE CALCULATION The ECAM alert items that affect landing performance are automatically sent to the LDG PERF application. The LDG PERF application displays these items in the ACFT STATUS panel. The flight crew enters the expected landing conditions and calculates the landing performance. For more information on the LDG PERF application, Refer to DSC-46-OIS-20-80-110 LDG PERF. FLAPS LEVER POSITION The flight crew selects the FLAPS lever position requested by the ECAM. Note:
If there are no ECAM instructions, the FLAPS lever position for landing is at flight crew's discretion.
VAPP DETERMINATION If the ECAM displays LDG DIST AFFECTED: The flight crew uses the VAPP calculated by the FMS. If the ECAM displays LDG PERF AFFECTED: The flight crew enters into the FMS - PERF - APPR page the VAPP value computed by the LDG PERF application.
VIR A350 FLEET FCOM
C
PER-LDG-50 P 2/4 03 FEB 20
PERFORMANCE LANDING A350
IN-FLIGHT PERFORMANCE ASSESSMENT
FLIGHT CREW OPERATING MANUAL
ROW LANDING DISTANCE CROSSCHECK Ident.: PER-LDG-50-00021305.0001001 / 04 DEC 14 Applicable to: ALL
The ROW landing distance may, in some cases, exceed the factored in-flight landing distance (FLD). The flight crew will not be authorized to initiate an approach if a ROW alert is expected (unless a specific authorization is obtained from the appropriate authority to deactivate the ROW/ROP). If a ROW alert is expected, and the flight crew is not authorized to deactivate the ROW/ROP, the flight crew should request to change the runway, or initiate a diversion.
VIR A350 FLEET FCOM
D
PER-LDG-50 P 3/4 03 FEB 20
PERFORMANCE LANDING A350
FLIGHT CREW OPERATING MANUAL
IN-FLIGHT PERFORMANCE ASSESSMENT
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PER-LDG-50 P 4/4 03 FEB 20
PERFORMANCE SUPPLEMENTARY PERFORMANCE INFORMATION
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PERFORMANCE SUPPLEMENTARY PERFORMANCE INFORMATION A350
FLIGHT CREW OPERATING MANUAL
PRELIMINARY PAGES - TABLE OF CONTENTS
Supplementary Performance Information................................................................................................................ A
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PER-PSD-PLP-TOC P 1/2 03 FEB 20
PERFORMANCE SUPPLEMENTARY PERFORMANCE INFORMATION A350
FLIGHT CREW OPERATING MANUAL
PRELIMINARY PAGES - TABLE OF CONTENTS
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PER-PSD-PLP-TOC P 2/2 03 FEB 20
PERFORMANCE SUPPLEMENTARY PERFORMANCE INFORMATION A350
FLIGHT CREW OPERATING MANUAL
SUPPLEMENTARY PERFORMANCE INFORMATION Ident.: PER-PSD-21400074.9001002 / 03 FEB 20 Applicable to: ALL
EQUIVALENCES Refer to PER-TOF-30-30 Performance Calculation MAXIMUM RECOMMENDED CROSSWIND ON DRY, WET AND CONTAMINATED RUNWAYS Refer to LIM-AG-OPS Maximum Crosswind for Takeoff and Landing. REVISED TAKE-OFF PERFORMANCE CALCULATIONS WHILST TAXI-OUT Refer to OM(B) 2.3, FMS FlySmart Data Insertion During Taxi-Out. SECONDARY FLYSMART & EFB PROCEDURES Refer to OM(B) Ch 2.3, FlySmart Alternative Procedures.
VIR A350 FLEET FCOM
A
PER-PSD P 1/2 03 FEB 20
PERFORMANCE SUPPLEMENTARY PERFORMANCE INFORMATION A350
FLIGHT CREW OPERATING MANUAL
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PER-PSD P 2/2 03 FEB 20
OPERATIONS ENGINEERING BULLETINS
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OPERATIONS ENGINEERING BULLETINS PRELIMINARY PAGES A350
LIST OF EFFECTIVE OPERATIONS ENGINEERING BULLETIN
FLIGHT CREW OPERATING MANUAL (1)
M
Identification OEB9 issue 2
(2)
T
R
(3)
E
N
Criteria: XW Applicable to: ALL OEB1 issue 3 W N Criteria: L42959, L48016, XW Applicable to: ALL OEB8 issue 1 W N Criteria: XW Applicable to: ALL
Rev. Date
Title
06 FEB 20
Not commanded engine shutdown due to liquid spillage on the center pedestal - Updated Procedure v2
17 OCT 19
RA Height Disturbance when Overflying Another Aircraft
04 SEP 19
AFS CP Altitude Knob Use
(1) Evolution code : N=New, R=Revised, E=Effectivity (2) Type of OEB: R=Red, W=White (3) Affects ECAM: Y=Yes, N=No
VIR A350 FLEET FCOM
OEB-PLP-LEOEB P 1/2 03 FEB 20
OPERATIONS ENGINEERING BULLETINS PRELIMINARY PAGES A350
FLIGHT CREW OPERATING MANUAL
LIST OF EFFECTIVE OPERATIONS ENGINEERING BULLETIN
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OEB-PLP-LEOEB P 2/2 03 FEB 20
OPERATIONS ENGINEERING BULLETINS PRELIMINARY PAGES A350
FLIGHT CREW OPERATING MANUAL
M
Localization
LIST OF EFFECTIVE TEMPORARY DOCUMENTARY UNITS DU Title
DU identification
DU date
No Temporary Documentary Unit
VIR A350 FLEET FCOM
OEB-PLP-LETDU P 1/2 15 MAR 20
OPERATIONS ENGINEERING BULLETINS PRELIMINARY PAGES A350
FLIGHT CREW OPERATING MANUAL
LIST OF EFFECTIVE TEMPORARY DOCUMENTARY UNITS
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OEB-PLP-LETDU P 2/2 15 MAR 20
OPERATIONS ENGINEERING BULLETINS INTRODUCTION
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OPERATIONS ENGINEERING BULLETINS INTRODUCTION A350
FLIGHT CREW OPERATING MANUAL
PRELIMINARY PAGES - TABLE OF CONTENTS
Introduction...............................................................................................................................................................A
VIR A350 FLEET FCOM
OEB-000-PLP-TOC P 1/2 02 APR 19
OPERATIONS ENGINEERING BULLETINS INTRODUCTION A350
FLIGHT CREW OPERATING MANUAL
PRELIMINARY PAGES - TABLE OF CONTENTS
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OEB-000-PLP-TOC P 2/2 02 APR 19
OPERATIONS ENGINEERING BULLETINS INTRODUCTION A350
FLIGHT CREW OPERATING MANUAL
INTRODUCTION Ident.: OEB-000-00020937.0001001 / 29 MAR 17 Applicable to: ALL
DEFINITION Airbus issues an Operations Engineering Bulletin (OEB) to rapidly inform Operators of any deviations from initial design objectives that have a significant operational effect. An OEB provides Operators with technical information and temporary operational procedures that address these deviations. TYPES OF OEB OEBs can be either red or white, depending on their level of priority. Red OEBs : Are issued to indicate that non-compliance with the recommended procedures may have a significant impact on the safe operation of the aircraft . White OEBs : Are issued to indicate that non-compliance with the recommended procedures may have a significant impact on aircraft operation. Airbus strongly recommends that all Operators rapidly apply the OEB corrective actions as soon as they become available, particularly for red OEBs. The information in OEBs is recommended by Airbus, but may not be approved by Airworthiness Authorities. However, in case of red OEB, Airbus also issues a Temporary Revision (TR) of the Airplane Flight Manual (AFM). If the procedures contained in the red OEB differ from the procedures in the AFM TR, the approved AFM TR remains the reference. OEB CONTENT AND MANAGEMENT An OEB: ‐ Is a part of the Flight Crew Operating Manual (FCOM) ‐ Is temporary, and usually focuses on one operational subject only ‐ Remains applicable, until the appropriate corrective actions are applied ‐ Is filed in increasing order. The content of each OEB includes: ‐ The reason for issue ‐ Technical explanations of the deviation from the initial design objectives ‐ The operational effect, if the flight crew does not apply the OEB procedure ‐ The conditions to apply the OEB procedures: • Cockpit effect • Flight phases • Specific events. VIR A350 FLEET FCOM
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OEB-000 P 1/2 01 JUL 19
OPERATIONS ENGINEERING BULLETINS INTRODUCTION A350
FLIGHT CREW OPERATING MANUAL
‐ The OEB operational procedure(s) the flight crew must apply ‐ The corrective actions (i.e. the SB(s) modification) that cancel the OEB, as soon as these corrective actions become available. If necessary, there are links to the FCOM sections for which the OEB is applicable, and these sections are usually in the format of a Temporary Documentary Unit (TDU). OEB AND ECAM ABNORMAL & EMERGENCY PROCEDURES
L2 L1
L2
L1
OEBs do not normally apply to ECAM abnormal/emergency procedures. The Airbus Temporary Quick Change (ATQC) database is used to urgently make any required updates or changes to an ECAM abnormal and emergency procedures. For more information on the ATQC database, Refer to DSC-31-CDS-60-10-20 FWS. REVIEW OF THE OEB In accordance with the Standard Operating Procedures (SOPs), and before each flight, the flight crew must review all OEBs that are applicable to their aircraft. If the OEB conditions are applicable, the flight crew must apply the operational procedure(s) that is in the OEB. For more information on OEB review in the SOPs, (Refer to PRO-NOR-SOP-40 OIS Preparation Operations Engineering Bulletins (OEB) ) . DISTRIBUTION OEB are distributed to all affected Operators. It is the Operators responsibility to ensure the distribution of the OEB to all their applicable flight crews.
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OEB-000 P 2/2 01 JUL 19
OPERATIONS ENGINEERING BULLETINS RA HEIGHT DISTURBANCE WHEN OVERFLYING ANOTHER AIRCRAFT
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PRELIMINARY PAGES - TABLE OF CONTENTS
RA Height Disturbance when Overflying Another Aircraft.......................................................................................A
VIR A350 FLEET FCOM
OEB-OEB1-PLP-TOC P 1/2 03 FEB 20
OPERATIONS ENGINEERING BULLETINS RA HEIGHT DISTURBANCE WHEN OVERFLYING ANOTHER AIRCRAFT A350
FLIGHT CREW OPERATING MANUAL
PRELIMINARY PAGES - TABLE OF CONTENTS
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OEB-OEB1-PLP-TOC P 2/2 03 FEB 20
OPERATIONS ENGINEERING BULLETINS RA HEIGHT DISTURBANCE WHEN OVERFLYING ANOTHER AIRCRAFT A350
FLIGHT CREW OPERATING MANUAL
RA HEIGHT DISTURBANCE WHEN OVERFLYING ANOTHER AIRCRAFT Applicable to: ALL
OEB1 Issue 3 RA HEIGHT DISTURBANCE WHEN OVERFLYING ANOTHER AIRCRAFT Ident.: OEB-OEB1-OEB1-00021420.0001001 / 17 OCT 19
APPROVAL REFERENCE APPROVED BY: Head of Airbus Flight Operations and Training Support Approval date: 17 OCT 19 Approval reference: 20191017 - This OEB covers a significant operational issue. Non-compliance with this OEB may have a significant impact on the operations of the aircraft. Airbus recommends that the operators apply this OEB within 30 days from the date of issue of this OEB. - Airbus recommends that all operators rapidly incorporate the corrective Service Bulletins that cancel this OEB when they become available.
Reason for issue: Applicable to:
This OEB is issued to provide operational recommendations in the case of an erroneous RA height during an aircraft overfly. All A350 aircraft.
Note: The interchangeability code, given in the Illustrated Part Catalog (IPC), indicates the conditions for interchangeability of equipment. After installation of corrective modification(s)/SB(s), if an Operator reinstalls any equipment affected by this OEB, it is the Operator's responsibility to ensure that the recommendations given in this OEB are applied again for the applicable aircraft.
Operations Engineering Bulletins are issued by Airbus, as the need arises, to quickly transmit technical and procedural information. They are distributed to all FCOM holders and to others who need advice of changes to operational information. The information in the OEB is recommended by Airbus, but may not be approved by Airworthiness Authorities. If the procedures contained in this OEB differ from the procedures in the AFM, the AFM remains the reference. Continued on the following page
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OEB-OEB1 P 1/8 01 JUL 19
OPERATIONS ENGINEERING BULLETINS RA HEIGHT DISTURBANCE WHEN OVERFLYING ANOTHER AIRCRAFT A350
FLIGHT CREW OPERATING MANUAL
RA HEIGHT DISTURBANCE WHEN OVERFLYING ANOTHER AIRCRAFT (Cont'd) M
Localization
T
DU Title
RA Height Disturbance when Overflying Another Aircraft OEB-OEB1 RA Height Disturbance when Overflying Another Aircraft Criteria: L42959, L48016, XW Applicable to: ALL OEB-OEB1 RA Height disturbance when Overflying Another Aircraft - Bulletin Criteria: L42959, L48016, XW Applicable to: ALL OEB-OEB1
DU identification
DU date
00021420.0001001
17 OCT 19
00021421.0001001
17 OCT 19
PG02419
Continued on the following page
VIR A350 FLEET FCOM
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OEB-OEB1 P 2/8 01 JUL 19
OPERATIONS ENGINEERING BULLETINS RA HEIGHT DISTURBANCE WHEN OVERFLYING ANOTHER AIRCRAFT A350
FLIGHT CREW OPERATING MANUAL
RA HEIGHT DISTURBANCE WHEN OVERFLYING ANOTHER AIRCRAFT (Cont'd) Ident.: OEB-OEB1-OEB1-00021421.0001001 / 17 OCT 19
DESCRIPTION Above 7 000 ft AGL, when an A350 overflies another aircraft that is less than 5 500 ft below, the A350 RA (Radio Altimeter) signals may be disturbed due to the returns of the RA signals from the overflown aircraft. Overfly Phase
During the overfly: The RA indication fluctuates within its operational range.
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OEB-OEB1 P 3/8 01 JUL 19
OPERATIONS ENGINEERING BULLETINS RA HEIGHT DISTURBANCE WHEN OVERFLYING ANOTHER AIRCRAFT A350
FLIGHT CREW OPERATING MANUAL
RA HEIGHT DISTURBANCE WHEN OVERFLYING ANOTHER AIRCRAFT (Cont'd) As a consequence, depending on the RA height indication, some of the following cockpit effects may be triggered: ‐ Spurious L/G GEAR NOT DOWN ECAM alert ‐ Spurious altitude auto callouts ‐ Spurious TAWS aural alerts ‐ Reversion of the TCAS mode to TA ONLY mode associated with the inhibition of "TRAFFIC TRAFFIC" aural alert ‐ Inhibition of the AP/FD TCAS function with AUTO FLT TCAS MODE FAULT ECAM alert ‐ Temporary loss of the BTV function associated with the BRAKES BTV FAULT ECAM alert ‐ Temporary loss of the ROW/ROP function associated with the SURV ROW / ROP LOST ECAM alert ‐ Temporary loss the Autoland capability associated with the AUTO FLT APPROACH CAPABILITY DOWNGRADED ECAM alert ‐ Temporary loss of the reactive windshear detection associated with the SURV REACTIVE W/S DET FAULT ECAM alert. After the overfly and above 5 500 ft AGL : When the RA antenna of the overflown aircraft is out of the A350 RA antenna range, the RA indication disappears. Normal behaviors of the ECAM alerts, auto callouts and TCAS Traffic Advisory / Resolution Advisory mode is recovered.
Continued on the following page
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OEB-OEB1 P 4/8 01 JUL 19
OPERATIONS ENGINEERING BULLETINS RA HEIGHT DISTURBANCE WHEN OVERFLYING ANOTHER AIRCRAFT A350
FLIGHT CREW OPERATING MANUAL
RA HEIGHT DISTURBANCE WHEN OVERFLYING ANOTHER AIRCRAFT (Cont'd) After Overfly Phase
However, after such event, RA are rejected by the PRIMs. As a consequence, the following cockpit effects are triggered until the A350 descends below 5 500 ft AGL: ‐ Inhibition of the AP/FD TCAS function with AUTO FLT TCAS MODE FAULT ECAM alert ‐ Temporary loss of the ROW/ROP function associated with the SURV ROW / ROP LOST ECAM alert
Continued on the following page
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OEB-OEB1 P 5/8 01 JUL 19
OPERATIONS ENGINEERING BULLETINS RA HEIGHT DISTURBANCE WHEN OVERFLYING ANOTHER AIRCRAFT A350
FLIGHT CREW OPERATING MANUAL
RA HEIGHT DISTURBANCE WHEN OVERFLYING ANOTHER AIRCRAFT (Cont'd) ‐ Temporary loss the Autoland capability associated with the AUTO FLT APPROACH CAPABILITY DOWNGRADED ECAM alert ‐ Temporary loss of the reactive windshear detection associated with the SURV REACTIVE W/S DET FAULT ECAM alert. Below 5 500 ft AGL: Normal operation of the RA is recovered. Normal behavior of the all ECAM alerts, landing capability and guidance mode is recovered. PROCEDURE During the overfly: Above 7 000 ft AGL, if the flight crew observes some of the above behaviors when overflying an aircraft with fluctuations of the RA height indication, the flight crew may suspect that the alerts and auto callouts are spurious. Therefore, the flight crew may disregard the aural alerts and auto callouts, and clear or cancel the ECAM alerts. In addition, the flight crew must carefully monitor traffics on the ND for possible threats, since TCAS may revert to TA ONLY without aural alert, until the Traffic Advisory / Resolution Advisory mode is recovered (TA ONLY message disappears on ND). After the overfly: The following cockpit effects remain triggered until the aircraft descends below 5 500 ft AGL: ‐ Inhibition of the AP/FD TCAS function with AUTO FLT TCAS MODE FAULT ECAM alert ‐ Temporary loss of the ROW/ROP function associated with the SURV ROW / ROP LOST ECAM alert ‐ Temporary loss the Autoland capability associated with the AUTO FLT APPROACH CAPABILITY DOWNGRADED ECAM alert ‐ Temporary loss of the reactive windshear detection associated with the SURV REACTIVE W/S DET FAULT ECAM alert. For approach: Unless other failure that affects the approach capability occurred during the flight, the aircraft will retrieve its normal approach capability below 5 500 ft AGL. In order to retrieve the correct approach capability, the flight crew should wait below 5 500 ft AGL to press the AFS CP APPR pushbutton to arm the approach.
Continued on the following page
VIR A350 FLEET FCOM
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OEB-OEB1 P 6/8 01 JUL 19
OPERATIONS ENGINEERING BULLETINS RA HEIGHT DISTURBANCE WHEN OVERFLYING ANOTHER AIRCRAFT A350
FLIGHT CREW OPERATING MANUAL
RA HEIGHT DISTURBANCE WHEN OVERFLYING ANOTHER AIRCRAFT (Cont'd) Note:
1. Above 5 500 ft AGL, If the flight crew press the APPR pushbutton to arm the approach, the approach capability displayed on the FMA will remain APPR1 with no update. In order to retrieve the correct approach capability, the flight crew should pull the V/S knob to disengage the approach and wait below 5 500 ft AGL to press the APPR pushbutton to arm the approach again. 2. Above 5 500 ft AGL, the flight crew could press the LOC pushbutton to arm lateral guidance. END OF OEB1
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OEB-OEB1 P 7/8 01 JUL 19
OPERATIONS ENGINEERING BULLETINS RA HEIGHT DISTURBANCE WHEN OVERFLYING ANOTHER AIRCRAFT A350
FLIGHT CREW OPERATING MANUAL
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VIR A350 FLEET FCOM
OEB-OEB1 P 8/8 01 JUL 19
OPERATIONS ENGINEERING BULLETINS AFS CP ALTITUDE KNOB USE
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OPERATIONS ENGINEERING BULLETINS AFS CP ALTITUDE KNOB USE A350
FLIGHT CREW OPERATING MANUAL
PRELIMINARY PAGES - TABLE OF CONTENTS
AFS CP Altitude Knob Use..................................................................................................................................... A
VIR A350 FLEET FCOM
OEB-OEB8-PLP-TOC P 1/2 03 FEB 20
OPERATIONS ENGINEERING BULLETINS AFS CP ALTITUDE KNOB USE A350
FLIGHT CREW OPERATING MANUAL
PRELIMINARY PAGES - TABLE OF CONTENTS
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VIR A350 FLEET FCOM
OEB-OEB8-PLP-TOC P 2/2 03 FEB 20
OPERATIONS ENGINEERING BULLETINS AFS CP ALTITUDE KNOB USE A350
FLIGHT CREW OPERATING MANUAL
AFS CP ALTITUDE KNOB USE Applicable to: ALL
OEB8 Issue 1 AFS CP ALTITUDE KNOB USE Ident.: OEB-OEB8-OEB8-00025231.0001001 / 04 SEP 19
- This OEB covers a significant operational issue. Non-compliance with this OEB may have a significant impact on the operations of the aircraft. Airbus recommends that the operators apply this OEB within 30 days from the date of issue of this OEB. - Airbus recommends that all operators rapidly incorporate the corrective Service Bulletins that cancel this OEB when they become available.
Reason for issue: Applicable to:
This OEB is issued to provide operational recommendations on the use of the AFS CP Altitude Knob. A350 aircraft.
Note: The interchangeability code, given in the Illustrated Part Catalog (IPC), indicates the conditions for interchangeability of equipment. After installation of corrective modification(s)/SB(s), if an Operator reinstalls any equipment affected by this OEB, it is the Operator's responsibility to ensure that the recommendations given in this OEB are applied again for the applicable aircraft.
Operations Engineering Bulletins are issued by Airbus, as the need arises, to quickly transmit technical and procedural information. They are distributed to all FCOM holders and to others who need advice of changes to operational information. The information in the OEB is recommended by Airbus, but may not be approved by Airworthiness Authorities. If the procedures contained in this OEB differ from the procedures in the AFM, the AFM remains the reference. Continued on the following page
VIR A350 FLEET FCOM
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OEB-OEB8 P 1/4 03 FEB 20
OPERATIONS ENGINEERING BULLETINS AFS CP ALTITUDE KNOB USE A350
FLIGHT CREW OPERATING MANUAL
AFS CP ALTITUDE KNOB USE (Cont'd) M
Localization
OEB-OEB8 OEB-OEB8 Criteria: XW Applicable to: ALL OEB-OEB8 Criteria: XW Applicable to: ALL OEB-OEB8 Criteria: XW Applicable to: ALL
T
DU Title
AFS CP Altitude Knob Use AFS CP Altitude Knob Use
DU identification
DU date
PG02616 00025231.0001001
04 SEP 19
AFS CP Altitude Knob Use - Desc Bulletin
00025232.0001001
04 SEP 19
AFS CP Altitude Knob Use- Proc Bulletin
00025233.0001001
04 SEP 19
Continued on the following page
VIR A350 FLEET FCOM
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OEB-OEB8 P 2/4 03 FEB 20
OPERATIONS ENGINEERING BULLETINS AFS CP ALTITUDE KNOB USE A350
FLIGHT CREW OPERATING MANUAL
AFS CP ALTITUDE KNOB USE (Cont'd) Ident.: OEB-OEB8-OEB8-00025232.0001001 / 04 SEP 19
EXPLANATION Operators reported some events of not commanded AFS CP altitude change. Investigations indicates that internal mechanical components of the AFS CP ALT Knob might have sensitivity weakness.
The ALT Knob is made of: ‐ An outer knob that has two positions: 100 and 1000, to set the target altitude in increments of 100 ft or 1 000 ft. ‐ A button that the flight crew can turn, push and pull to define a new target altitude, and use the managed or selected mode. The possible sensitivity weakness could lead to an offset of only one increment of not commanded altitude change, i.e.(100 ft or 1 000 ft depending on the outer knob setting. As a result, in order to limit the possible not commanded altitude change, a new procedure is introduced. Flight crew should set the outer knob of the AFS CP ALT knob to the 100 position after each use. AFS CP ALTITUDE KNOB USE- PROC - BULLETIN Ident.: OEB-OEB8-OEB8-00025233.0001001 / 04 SEP 19
PROCEDURE
L2
After each use of the AFS CP ALT knob: ALT outer knob..............................................................................................................SET 100 The 1000 position of the ALT outer knob can be used for altitude target selection. However, the flight crew should ensure that the ALT outer knob is set to the 100 position after each use. END OF OEB8
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OEB-OEB8 P 3/4 03 FEB 20
OPERATIONS ENGINEERING BULLETINS AFS CP ALTITUDE KNOB USE A350
FLIGHT CREW OPERATING MANUAL
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VIR A350 FLEET FCOM
OEB-OEB8 P 4/4 03 FEB 20
OPERATIONS ENGINEERING BULLETINS NOT COMMANDED ENGINE SHUTDOWN DUE TO LIQUID SPILLAGE ON THE CENTER PEDESTAL - UPDATED PROCEDURE V2
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OPERATIONS ENGINEERING BULLETINS
A350
FLIGHT CREW OPERATING MANUAL
NOT COMMANDED ENGINE SHUTDOWN DUE TO LIQUID SPILLAGE ON THE CENTER PEDESTAL - UPDATED PROCEDURE V2 PRELIMINARY PAGES - TABLE OF CONTENTS
Not commanded engine shutdown due to liquid spillage on the center pedestal - Updated Procedure V2.............A
VIR A350 FLEET FCOM
OEB-OEB9-PLP-TOC P 1/2 03 FEB 20
OPERATIONS ENGINEERING BULLETINS
A350
FLIGHT CREW OPERATING MANUAL
NOT COMMANDED ENGINE SHUTDOWN DUE TO LIQUID SPILLAGE ON THE CENTER PEDESTAL - UPDATED PROCEDURE V2 PRELIMINARY PAGES - TABLE OF CONTENTS
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VIR A350 FLEET FCOM
OEB-OEB9-PLP-TOC P 2/2 03 FEB 20
OPERATIONS ENGINEERING BULLETINS
A350
NOT COMMANDED ENGINE SHUTDOWN DUE TO LIQUID SPILLAGE ON THE CENTER PEDESTAL - UPDATED PROCEDURE V2
FLIGHT CREW OPERATING MANUAL
RED OEB – RED OEB – RED OEB – RED OEB – RED OEB – RED OEB
NOT COMMANDED ENGINE SHUTDOWN DUE TO LIQUID SPILLAGE ON THE CENTER PEDESTAL - UPDATED PROCEDURE V2 Applicable to: ALL
OEB9 Issue 2 NOT COMMANDED ENGINE SHUTDOWN DUE TO LIQUID SPILLAGE ON THE CENTER PEDESTAL - UPDATED PROCEDURE V2 Ident.: OEB-OEB9-OEB9-00025399.0001001 / 06 FEB 20
- This OEB covers a significant operational issue. Non-compliance with this OEB may have a significant impact on the safe operations of the aircraft. The operators shall distribute its content to all flight crews without delay. - Airbus recommends that all operators rapidly incorporate the corrective Service Bulletins that cancel this OEB when they become available.
Reason for revision:
Update to clarify the OEB procedure to: 1. Specify that the flight crew should: ‐ Consider landing at the next suitable airport (LAND ANSA), in the case of inadvertent liquid spillage on ENG START panel or on ECAM Control Panel ‐ Land as soon as possible at the nearest suitable airport at which a safe landing can be made (LAND ASAP), in the case of inadvertent liquid spillage on ENG START panel or on ECAM Control Panel and one engine shutdown. 2. Clarify the condition that triggers the flight crew report in the technical logbook at the parking.
Reason for issue: Applicable to:
Update of the OEB explanation to include the liquid prohibited zone. This OEB provides operational recommendations in the case of inadvertent liquid spillage on the pedestal in the cockpit. All A350 aircraft.
Continued on the following page
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OEB-OEB9 P 1/6 03 FEB 20
OPERATIONS ENGINEERING BULLETINS
A350
NOT COMMANDED ENGINE SHUTDOWN DUE TO LIQUID SPILLAGE ON THE CENTER PEDESTAL - UPDATED PROCEDURE V2
FLIGHT CREW OPERATING MANUAL
RED OEB – RED OEB – RED OEB – RED OEB – RED OEB – RED OEB
NOT COMMANDED ENGINE SHUTDOWN DUE TO LIQUID SPILLAGE ON THE CENTER PEDESTAL - UPDATED PROCEDURE V2 (Cont'd) Note: The interchangeability code, given in the Illustrated Part Catalog (IPC), indicates the conditions for interchangeability of equipment. After installation of corrective modification(s)/SB(s), if an Operator reinstalls any equipment affected by this OEB, it is the Operator's responsibility to ensure that the recommendations given in this OEB are applied again for the applicable aircraft.
Operations Engineering Bulletins are issued by Airbus, as the need arises, to quickly transmit technical and procedural information. They are distributed to all FCOM holders and to others who need advice of changes to operational information. The information in the OEB is recommended by Airbus, but may not be approved by Airworthiness Authorities. If the procedures contained in this OEB differ from the procedures in the AFM, the AFM remains the reference. Continued on the following page
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OEB-OEB9 P 2/6 03 FEB 20
OPERATIONS ENGINEERING BULLETINS
NOT COMMANDED ENGINE SHUTDOWN DUE TO LIQUID SPILLAGE ON THE CENTER PEDESTAL - UPDATED PROCEDURE V2
A350
FLIGHT CREW OPERATING MANUAL
RED OEB – RED OEB – RED OEB – RED OEB – RED OEB – RED OEB
NOT COMMANDED ENGINE SHUTDOWN DUE TO LIQUID SPILLAGE ON THE CENTER PEDESTAL - UPDATED PROCEDURE V2 (Cont'd) M
Localization
OEB-OEB9 OEB-OEB9
Criteria: XW Applicable to: ALL OEB-OEB9 Criteria: XW Applicable to: ALL OEB-OEB9 Criteria: XW Applicable to: ALL
T
DU Title
DU identification
DU date
00025399.0001001
06 FEB 20
Not commanded engine shutdown due to liquid spillage on the center pedestal
00025401.0001001
06 FEB 20
Not commanded engine shutdown due to liquid spillage on the center pedestal
00025403.0001001
06 FEB 20
Not commanded engine shutdown due to liquid spillage on the center pedestal - Updated Procedure V2 Not commanded engine shutdown due to liquid spillage on the center pedestal - Updated Procedure v2
PG02626
Continued on the following page
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OEB-OEB9 P 3/6 03 FEB 20
OPERATIONS ENGINEERING BULLETINS
A350
NOT COMMANDED ENGINE SHUTDOWN DUE TO LIQUID SPILLAGE ON THE CENTER PEDESTAL - UPDATED PROCEDURE V2
FLIGHT CREW OPERATING MANUAL
RED OEB – RED OEB – RED OEB – RED OEB – RED OEB – RED OEB
NOT COMMANDED ENGINE SHUTDOWN DUE TO LIQUID SPILLAGE ON THE CENTER PEDESTAL - UPDATED PROCEDURE V2 (Cont'd) Ident.: OEB-OEB9-OEB9-00025401.0001001 / 06 FEB 20
EXPLANATION Operators reported few events of not commanded In Flight Shut Down (IFSD) a few minutes after inadvertent liquid spillage on the ENG START panel or ECAM Control Panel (ECP) of the pedestal. Several engine relight attempts were not successful. Investigations indicate an abnormal operation of the components of the ENG START panel. As a result, a precautionary procedure is introduced in addition to standard practices for the handling of liquids in the cockpit as commonly applied by Operators. During the preliminary cockpit preparation, the flight crew must advise the cabin crew about the standard practices for the handling of liquids in the cockpit. Flight and cabin crews must respect the following liquid prohibited zone: ‐ ‐ ‐ ‐
Center pedestal Sliding tables of captain and first officer Inboard sides of captain and first officer seats Third occupant seat. Continued on the following page
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OEB-OEB9 P 4/6 03 FEB 20
OPERATIONS ENGINEERING BULLETINS
A350
NOT COMMANDED ENGINE SHUTDOWN DUE TO LIQUID SPILLAGE ON THE CENTER PEDESTAL - UPDATED PROCEDURE V2
FLIGHT CREW OPERATING MANUAL
RED OEB – RED OEB – RED OEB – RED OEB – RED OEB – RED OEB
NOT COMMANDED ENGINE SHUTDOWN DUE TO LIQUID SPILLAGE ON THE CENTER PEDESTAL - UPDATED PROCEDURE V2 (Cont'd)
In flight, the flight crew should: ‐ Consider landing at the next suitable airport (LAND ANSA), in the case of inadvertent liquid spillage on ENG START panel or on ECAM Control Panel ‐ Land as soon as possible (LAND ASAP) at the nearest suitable airport at which a safe landing can be made, in the case of inadvertent liquid spillage on ENG START panel or on ECAM Control Panel, and one engine shutdown. Continued on the following page
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OEB-OEB9 P 5/6 03 FEB 20
OPERATIONS ENGINEERING BULLETINS
A350
NOT COMMANDED ENGINE SHUTDOWN DUE TO LIQUID SPILLAGE ON THE CENTER PEDESTAL - UPDATED PROCEDURE V2
FLIGHT CREW OPERATING MANUAL
RED OEB – RED OEB – RED OEB – RED OEB – RED OEB – RED OEB
NOT COMMANDED ENGINE SHUTDOWN DUE TO LIQUID SPILLAGE ON THE CENTER PEDESTAL - UPDATED PROCEDURE V2 (Cont'd) In the case of liquid spillage on the pedestal, the flight crew must report the event in the logbook after landing. A maintenance action is required. NOT COMMANDED ENGINE SHUTDOWN DUE TO LIQUID SPILLAGE ON THE CENTER PEDESTAL Ident.: OEB-OEB9-OEB9-00025403.0001001 / 06 FEB 20
PROCEDURE PRELIMINARY COCKPIT PREPARATION CABIN CREW................................................................................................................ADVISE The flight crew must advise the cabin crew about the standard practices for the handling of liquids in the cockpit. IN FLIGHT In the case of inadvertent liquid spillage on ENG START panel or on ECAM Control Panel (ECP): LAND ANSA DIVERSION.......................................................................................................CONSIDER In the case of inadvertent liquid spillage on ENG START panel or on ECAM Control Panel (ECP), and one engine shutdown: LAND ASAP DIVERSION........................................................................................................... INITIATE PARKING In the case of inadvertent liquid spillage on the pedestal: LOGBOOK.................................................. REPORT LIQUID SPILLAGE ON PEDESTAL Maintenance action is due. END OF OEB9
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OEB-OEB9 P 6/6 03 FEB 20
TEMPORARY ABNORMAL BEHAVIORS
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TEMPORARY ABNORMAL BEHAVIORS PRELIMINARY PAGES A350
FLIGHT CREW OPERATING MANUAL 1
TABLE OF CONTENTS
Temporary Abnormal Behaviors Table....................................................................................................................A
VIR A350 FLEET FCOM
TAB-PLP-TOC P 1/2 15 MAR 20
TEMPORARY ABNORMAL BEHAVIORS PRELIMINARY PAGES A350
FLIGHT CREW OPERATING MANUAL
TABLE OF CONTENTS
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VIR A350 FLEET FCOM
TAB-PLP-TOC P 2/2 15 MAR 20
TEMPORARY ABNORMAL BEHAVIORS PRELIMINARY PAGES A350
SUMMARY OF HIGHLIGHTS
FLIGHT CREW OPERATING MANUAL
Localization Title
TAB-PLP-TOC Temporary Abnormal Behaviors Table
TAB Erroneous BRAKES G(Y) SYS BRK LOST after landing gear retraction
VIR A350 FLEET FCOM
Toc Index
ID
Reason
1
A
1
Documentation update: Deletion of the "00024163 AUTO FLT Display of Erroneous FIX INFO on the ND" table of content entry. Documentation update: Deletion of the "00025073 FUEL Erroneous Variations of FQI and FOB" table of content entry. Documentation update: Deletion of the "00024163.0001001 AUTO FLT - Display of Erroneous FIX INFO on the ND" documentary unit. Documentation update: Deletion of the "00025073.0001001 FUEL - Erroneous Variations of FQI and FOB" documentary unit. Documentation update: Addition of "Erroneous BRAKES G(Y) SYS BRK LOST after landing gear retraction" documentary unit
TAB-PLP-SOH P 1/2 15 MAR 20
TEMPORARY ABNORMAL BEHAVIORS PRELIMINARY PAGES A350
FLIGHT CREW OPERATING MANUAL
SUMMARY OF HIGHLIGHTS
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TAB-PLP-SOH P 2/2 15 MAR 20
TEMPORARY ABNORMAL BEHAVIORS A350
FLIGHT CREW OPERATING MANUAL
TEMPORARY ABNORMAL BEHAVIORS TABLE Applicable to: ALL Ident.: TAB-TABT-00023159.0001001 / 07 JUL 16
The table below provides a list of all Temporary Abnormal Behaviors. Ident.: TAB-TABT-00023121.0001001 / 07 JUL 16
System
Temporary Abnormal Behavior
Link
Erroneous Altitude Constraint after SID or STAR Selection Change
Refer to link
Ident.: TAB-TABT-00023726.0001001 / 07 JUL 16
AUTO FLT
Ident.: TAB-TABT-00024161.0001001 / 27 FEB 17
AUTO FLT
Erroneous Fuel & Load Values Following RECEIVED CPNY F-PLN
Refer to link
Ident.: TAB-TABT-00023834.0001001 / 01 SEP 16
AUTO FLT
Erroneous Trajectory while in HDG(TRK) Mode during Procedures with a Turn Direction on a Leg with an Altitude Termination
Refer to link
Ident.: TAB-TABT-00024991.0001001 / 08 JUL 19
AUTO FLT
Erroneous Vertical Guidance in Approach Subsequent to a DIR TO Performed when near the Top of Descent
Refer to link
1 Ident.: TAB-TABT-00025348.0002001 / 04 FEB 20
BRAKES
Erroneous BRAKES G(Y) SYS BRK LOST after landing gear retraction
Refer to link
Ident.: TAB-TABT-00024305.0001001 / 29 MAY 17
BRAKES
Discrepancy Between WHEEL SD page and ECAM alerts Released Indication.
Refer to link
Ident.: TAB-TABT-00024455.0001001 / 26 OCT 17
BRAKES
Low Level of Residual Braking Pressure after Parking Brake Release.
Refer to link
Ident.: TAB-TABT-00024951.0001001 / 03 JAN 19
CAB PRESS
Abnormal Cabin Altitude Increase in Climb due to Erroneously Open OFV
Ident.: TAB-TABT-00023791.0001001 / 08 JUL 19
COM
VIR A350 FLEET FCOM
Loss of HF voice or HF datalink
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Refer to link
Refer to link
TAB P 1/2 15 MAR 20
TEMPORARY ABNORMAL BEHAVIORS A350
FLIGHT CREW OPERATING MANUAL Ident.: TAB-TABT-00024740.0001001 / 04 MAY 18
DOORS
Erroneous Activation of the CABIN PRESSURE WARNING Lights without Real Residual Differential Pressure
Refer to Link
Ident.: TAB-TABT-00023145.0001001 / 07 JUL 16
HYD
VIR A350 FLEET FCOM
Discrepancy Between WHEEL SD page and ECAM Alerts in the case of Hydraulic Failure - NORM Indication
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Refer to link
TAB P 2/2 15 MAR 20