B737 Training [PDF]

Zitiervorschau

B737--600/700/800/900

General Familiarization

One Stop Airline MRO Support Pvt. Ltd

Training Manual

One Stop Airline MRO Support Pvt. Ltd

Boeing B737--600/700/800/900 ATA DIVERSE

General Familiarization

Level 1 OSA B737--6_DIVERSE_L1

Issue: Jul 2007 Author: OSA For Training Purposes Only E OSA 2007

Training Manual

One Stop Airline MRO Support Pvt. Ltd

For training purposes and internal use only. E Copyright by One Stop Airline MRO Support Pvt. Ltd (OSA). OSA is the owner of all rights to training documents and training software. Any use outside the training measures, especially reproduction and/or copying of training documents and software -- also extracts there of -- in any format all (photocopying, using electronic systems or with the aid of other methods) is prohibited. Passing on training material and training software to third parties for the purpose of reproduction and/or copying is prohibited without the express written consent of OSA. Copyright endorsements, trademarks or brands may not be removed. A tape or video recording of training courses or similar services is only permissible with the written consent of OSA. In other respects, legal requirements, especially under copyright and criminal law, apply.

B737-- 600/700/800/900

GENERAL FAMILIARIZATION

FOR TRAINING PURPOSES ONLY!

OSA MRO Support Pvt. Ltd

One Stop Airline MRO Support Pvt. Ltd

ATA DOC

Page 1

OSA MRO Support Pvt. Ltd FOR TRAINING PURPOSES ONLY!

INTRODUCTION GENERAL AIRCRAFT

One Stop Airline MRO Support Pvt. Ltd

B737-- 600/700/800/900

GENERAL DESCRIPTION The design of the B737 NG (Next Generation) is based on the B737 Classic family: B737--300/-400/-500. The Boeing B737 NG is a twin engine airplane. It is designed for short to medium range operation and consists of four models: S B737--600 S B737--700 S B737--800 S B737--900 In this document, the use of the designator B737 NG without a reference to a specific model indicates that this information applies to all four models. Evaluation The Boeing 737 NG programme was launched in June 1993, starting with the B737--700 (22cm (9in) longer than the original B737--300 and a seating up to 149). The B737--800 project was launched in September 1994 and is based on the B737--400 but is significantly longer at 39.4m (129ft 6in) and seats up to 189. The --800 has been available with winglets since May 2001. These reduce aerodynamic drag thereby reducing fuel consumption by up to 7%. The B737--600 was the third of the NG’s to be built and started in March 1995 and originated as the B737--500 with a similar length fuselage, seating between 108--132. Boeing began work on the stretched B737--900 in April 1997 and opted to use the same (-800) emergency exit layout, with 4 main exit doors and 4 overwing exits, thereby still restricting the maximum passenger load to 189.

FRA US/E GiM

Mai 10, 2006

INTRO

Page 2

OSA MRO Support Pvt. Ltd

INTRODUCTION GENERAL AIRCRAFT

One Stop Airline MRO Support Pvt. Ltd

B737-- 600/700/800/900

35,80 mtr

12,60 mtr

FOR TRAINING PURPOSES ONLY!

14,30 mtr

B737--600 B737--700 B737--800 B737--900

31,20 mtr 33,60 mtr 39,50 mtr 42,10 mtr

Figure 1 FRA US/E GiM

Mai 10, 2006

Dimension

INTRO

Page 3

OSA MRO Support Pvt. Ltd

INTRODUCTION GENERAL AIRCRAFT

B737-- 600/700/800/900

One Stop Airline MRO Support Pvt. Ltd B737--600

B737--700

B737--800

B737--900

Taxi

56530

60550

78460

79243

Take-off

56250

60330

78220

79016

Landing

54650

58060

65310

66360

Zero-fuel

51480

54660

61690

62730

Maximum weight (kg):

Powerplant: Model

CFM56--7

CFM56--7

CFM56--7

CFM56--7

Type

B18

B20 / B22 / B24

B24 / B26 / B27

B24 / B26 / B27

Static Thrust (lb)

19500

20600 / 22700 / 24200

24200 / 26400 / 27300

24200 / 26400 / 27300

Bypass Ratio

5.5 : 1

5.4 : 1

5.3 : 1

5.1 : 1

Accomodation: Max. Seating (single class) Hold Volume (m3)

132

149

189

189

23.30

30.20

47.10

52.40

20536

20536

20536

20536

2926

2726

Fuel (kg): Standard FOR TRAINING PURPOSES ONLY!

Optional (BBJ)

30170

Long Range Cruise: Range with max. payload (nm)

3153

3299

Figure 2 FRA US/E GiM

Mai 10, 2006

Aircraft Data INTRO

Page 4

OSA MRO Support Pvt. Ltd

INTRODUCTION GENERAL AIRCRAFT

B737-- 600/700/800/900

One Stop Airline MRO Support Pvt. Ltd P7 P1

P2

P3

P8 P9

P7 (GLARESHIELD)

1

FOR TRAINING PURPOSES ONLY!

1

P1 Figure 3 FRA US/E GiM

Mai 10, 2006

P2 FLIGHT DECK PANEL - FRONT VIEW INTRO

P3 Page 5

OSA MRO Support Pvt. Ltd

INTRODUCTION GENERAL AIRCRAFT

One Stop Airline MRO Support Pvt. Ltd

B737-- 600/700/800/900

P8

FOR TRAINING PURPOSES ONLY!

P8

P9

PILOTS’ CONTROL STAND P9

Figure 4 FRA US/E GiM

Mai 10, 2006

FLIGHT DECK PANEL - PEDESTAL INTRO

Page 6

OSA MRO Support Pvt. Ltd

INTRODUCTION GENERAL AIRCRAFT

B737-- 600/700/800/900

One Stop Airline MRO Support Pvt. Ltd

1

P 5 AFT

P 5 AFT

FOR TRAINING PURPOSES ONLY!

P 5 FWD

P 5 FWD

Figure 5 FRA US/E GiM

Mai 10, 2006

FLIGHT DECK PANEL - OVERHEAD INTRO

Page 7

OSA MRO Support Pvt. Ltd

INTRODUCTION GENERAL AIRCRAFT

One Stop Airline MRO Support Pvt. Ltd

B737-- 600/700/800/900

GROUND OPERATIONS The doors, service connections and access panels on the B737 NG are located to facilitate simultaneous ground operations and minimum ground operations and turn around times.

FOR TRAINING PURPOSES ONLY!

Self--Sufficiency The 737 can operate from modern and non--modern airports. These are the Systems that make the airplane self sufficient: S The APU supplies on--ground or in--flight electrical power S The APU supplies air for engine starting S The APU maintains an air--conditioned cabin during ground operations S The APU is started from the airplane battery S The airplane has large fuel and water capacity S Alternative Systems allow dispatch with inoperative Systems S Two or more Systems which have equal function but one System operates at a time which allows more rapid fault dispatching S Self--contained airstairs (Option)

FRA US/E GiM

Mai 10, 2006

INTRO

Page 8

OSA MRO Support Pvt. Ltd

INTRODUCTION GENERAL AIRCRAFT

B737-- 600/700/800/900

One Stop Airline MRO Support Pvt. Ltd FUELING

GALLEY SERVICE

BAGGAGE HANDLING

BAGGAGE HANDLING

POTABLE WATER SERVICE

ELECTRICAL POWER APU 2

1

FOR TRAINING PURPOSES ONLY!

FORWARD AIRSTAIRS

STARTING AIR 1 1 2

NOT REQUIRED IF APU IS IN USE. AUXILIARY POWER UNIT CAN PROVIDE: w ELECTRICAL POWER w ENGINE START w AIR CONDITIONING

AIR CONDITIONING 1

Figure 6 FRA US/E GiM

Mai 10, 2006

VACUUM GALLEY LAVATORY SERVICE SERVICE (SECOND POSITION)

Servicing

INTRO

Page 9

OSA MRO Support Pvt. Ltd

MAINTENANCE DOCUMENTS

One Stop Airline MRO Support Pvt. Ltd

MAINTENANCE DOCUMENTS - INTRODUCTION General The maintenance documents will help you to do scheduled and unscheduled maintenance work.

B737-- 600/700/800/900

Dispatch Deviation Guide The Dispatch Deviation Guide (DDG) supplies Boeing’s recommended minimum equipment required for dispatch in the Master Minimum Equipment List (MMEL). It also supplies the procedures for dispatch with a fault if permitted. Training Information Point Each maintenance document has an introduction to show you how to use that document.

System Schematics Manual The System Schematic Manual (SSM) gives the user an understanding of system operation and helps in the fault isolation process. It supplies the interconnection of all LRUs of a system or subsystem. It also supplies a general know-ledge about system operation. Standard Wiring Practices Manual The Standard Wiring Practices Manual has instructions for maintenance and repair of the wiring of all Boeing airplanes. It is not customized.

FOR TRAINING PURPOSES ONLY!

Fault Reporting Manual The flight crew uses the Fault Reporting Manual (FRM) to improve communication with maintenance personnel and for future automatized fault reporting. The flight crew uses the FRM to get fault codes for airplane faults. These faults can be flight deck effects or other faults. The FRM has standard log book write-ups for each fault code. FRM fault codes refer you to the FIM - Task. Structural Repair Manual The Structural Repair Manual (SRM) supplies descriptive information and specific instructions to help in field repair of airplane structure. The SRM is not customized. It has data relative to these areas: S Allowable damage evaluation S Typical repairs S Material identification S Material substitution S Fastener installation S Alignment check S Planning. FRA US/E GiM

Mai 10, 2006

Documentation

Page 10

One Stop Airline MRO Support Pvt. Ltd

B737-- 600/700/800/900

NOTE:

FOR TRAINING PURPOSES ONLY!

OSA MRO Support Pvt. Ltd

MAINTENANCE DOCUMENTS

THE SHADOWED DOCUMENTS CAN BE FOUND IN THE BOEING PORTABLE MAINTENANCE AID (PMA)

PMA

Figure 7 FRA US/E GiM

Mai 10, 2006

MAINT. DOCUMENTS - INTRODUCTION Documentation

Page 11

OSA MRO Support Pvt. Ltd

MAINTENANCE DOCUMENTS

One Stop Airline MRO Support Pvt. Ltd

B737-- 600/700/800/900

Scheduled Maintenance These are examples of scheduled maintenance work: S Through stop checks S Airplane turn around S Daily checks S Planned checks.

Unscheduled Maintenance These are examples of unscheduled maintenance work: S Flight faults S Ground faults S Service problems S Structural damage.

You use these documents to do scheduled maintenance: S Maintenance Planning Document (MPD) S Airplane Maintenance Manual (AMM).

You use these documents to do unscheduled maintenance: S Fault Reporting Manual (FRM) S Fault Isolation Manual (FIM) (PMA)! S Structural Repair Manual (SRM) S Dispatch Deviations Guide (DDG) S Airplane Maintenance Manual (AMM) (PMA)!

These documents supply supporting data to do scheduled maintenance: S System Schematics Manual (SSM) S Wiring Diagram Manual (WDM) S Structural Repair Manual (SRM) S Illustrated Parts Catalog (IPC). S Maintenance Planning Document

NOTE:

NOTE: SOME OF THIS DOCUMENTS CAN BE FOUND IN THE DIGITAL BOEING PORTABLE MAINTENANCE AID (PMA)!

FOR TRAINING PURPOSES ONLY!

The Maintenance Planning Document (MPD) defines the tasks for each type of scheduled maintenance check. Airlines use the MPD to make task cards that the technician uses during the maintenance checks.

FRA US/E GiM

Mai 10, 2006

Documentation

Page 12

One Stop Airline MRO Support Pvt. Ltd

SCHEDULED MAINTENANCE

FOR TRAINING PURPOSES ONLY!

OSA MRO Support Pvt. Ltd

MAINTENANCE DOCUMENTS

B737-- 600/700/800/900

UNSCHEDULED MAINTENTANCE

NOTE: THE SHADOWED DOCUMENTS CAN BE FOUND IN THE BOEING PORTABLE MAINTENANCE AID (PMA)

Figure 8 FRA US/E GiM

Mai 10, 2006

PMA

MAINT. DOCUMENTS - MAINTENANCE Documentation

Page 13

OSA MRO Support Pvt. Ltd FOR TRAINING PURPOSES ONLY!

ELECTRICAL POWER

ATA 24

One Stop Airline MRO Support Pvt. Ltd

ELECTRICAL POWER

POWER AND CONTROL The electrical power system makes and supplies AC and DC power to airplane. The system has automatic and manual controls and protection. A standby AC and DC system gives normal and emergency power. AC Power The electrical power system has four main AC power sources and one standby power source. These are the main AC power sources and their supply capacity: S Left integrated drive generator (IDG 1) (90 KVA) S Right integrated drive generator (IDG 2) (90 KVA) S APU starter-generator (90 KVA below 32,000 feet/9,753 meters, and goes down to 66 KVA at 41,000 feet/12,496 meters) S External power (90 KVA). The IDGs and APU starter-generator supply a 3 phase,115/200 volts (nominal) at 400 Hz. The AC power system design prevents two sources to the same load at the same time. The static inverter supplies a one phase, 115v ac output to the AC standby bus. DC Power Three transformer rectifier units (TRUs) change 115v ac to 28v dc. The airplane also has these DC power sources: S Main battery S Main battery charger S Auxiliary battery S Auxiliary battery charger. The batteries are the backup DC source if other sources do not operate. The standby power control unit (SPCU) controls the distribution of dc power. Standby Power With the loss of norma power, the standby power system supplies a minimum of 60 minutes of AC and DC power to systems necessary to maintain safe flight. The batteries supply DC power. The static inverter uses battery power to

FRA US/E GiM

Mai 10, 2006

B737-- 600/700/800/900 24-- 00

make AC power. The SPCU controls the distribution of AC and DC standby power. Protection The electrical power system uses automatic control to protect the system from source failure or load failure. These line replaceable units (LRUs) supply the system with protection and control logic: S Left generator control unit (GCU 1) S Right generator control unit (GCU 2) S APU generator control unit (AGCU) S Bus power control unit (BPCU) S Standby power control unit (SPCU) S Start converter unit (SCU). The GCUs monitor the system to control and protect the IDGs. The APU GCU and the starter converter unit (SCU) work together to control and protect the APU starter-generator. The bus power control unit (BPCU) controls and monitors the use of external power. The BPCU protects the airplane from external power whose quality is out of limits. Control These modules on the P5 panel give manual control of the electrical power system: S Electrical meters, battery and galley power module (P5-13) S Generator drive and standby power module (P5-5) S AC systems, generator and APU module (P5-4). The switches on these modules send signals to the LRUs that control portions of the system. The LRUs then energize or de-energize relays or breakers to control electrical power. Breakers allow power to the buses. A breaker closes to let power through it. The breakers close when you command the GCU to close it. The GCU closes the breaker only when power is good and no other power source is on the bus. These are the main breakers: S External power contactor (EPC) S APU power breaker (APB) S Generator control breaker (GCB) S Bus tie breakers (BTBs).

ATA 24 Electric

Page 14

OSA MRO Support Pvt. Ltd

ELECTRICAL POWER

DC AMP

B737-- 600/700/800/900

One Stop Airline MRO Support Pvt. Ltd

24-- 00

CPS FREQ

A

SYS DATA

EPC DC VOLTS / AC AMPS / AC VOLTS

BPCU BAT

TR1

GEN1

TR2

BAT BUS

GRD PWR

TR3 TEST

STBY PWR

INV TEST

STBY PWR

OFF

OFF

BAT

GALLEY ON

ON

A

EXTERNAL POWER

APU GEN GEN2

STATIC INV

TRU 1

TO SYS

GCB 2

AC

DC P5--13

2

1 STANDBY POWER

DISCONNECT

DISCONNECT BAT

OFF

GCU 2 SYS STATUS

IDG 2

AUTO

TO SYS

A SCU

P5--5

APB

ON

BUS TRANSFER A O U F T F O

OFF ON GEN 1

SYS STATUS

AGCU

APU STARTER--GENERATOR

CHARGER

A

DC BUSES

SPCU

OFF

APU GEN APU

ON GEN 2

GCB 1

P5--4

GCU 1

Figure 9 FRA US/E GiM

DC STDBY

TRU 3

GRD PWR OFF

FOR TRAINING PURPOSES ONLY!

AC STDBY

TRU 2

Mai 10, 2006

IDG 1

AC BUSES

BATTERY

POWER / CONTROL - GEN. DESCRIPTION ATA 24 Electric

Page 15

OSA MRO Support Pvt. Ltd FOR TRAINING PURPOSES ONLY!

ELECTRICAL POWER

One Stop Airline MRO Support Pvt. Ltd

EL. METERS, BATTERY & GALLEY POWER MODULE General You use the electrical meters, battery and galley power module (P5-13) for these functions: S See electrical power parameters for AC and DC components or buses S Connect battery power to electrical buses with the battery switch S Supply and remove power to the galleys with the galley switch. The module also has these BITE functions: S Supplies DC and standby power system failure indication S Monitors the dc and standby power and saves fault messages in memory. S Shows fault messages on the LED alphanumeric display. See the training information point page in this section for more information on BITE. AC Meter Selector The AC meter selector is a rotary selector with seven positions. Each position, except the TEST position, is related to an AC power source or AC bus. The alphanumeric display shows these parameters for the three generators: S Voltage (AC VOLTS) S Load (AC AMPS) S Output frequency (CPS FREQ). The alphanumeric, display shows only voltage and frequency when you select one of these: S STBY PWR S GRD PWR S INV. The selector must be in the TEST position to use the P5-13 BITE.

FRA US/E GiM

Mai 10, 2006

B737-- 600/700/800/900 24-- 00

DC Meter Selector The DC meter selector is a rotary selector with seven positions. Each position, except the TEST position, is related to a DC power source or DC bus. Voltage (DC VOLTS) and load (DC AMPS) show on the alphanumeric display when you put the selector in any of the TR positions or any of the BAT positions. Only voltage shows when you put the selector to the BAT BUS or STBY PWR positions. The selector must be in the TEST position to use the P5-l3 BITE. BAT DISCHARGE Light The amber BAT DISCHARGE light gives indication of main battery discharge or auxiliary battery discharge. The BAT DISCHARGE light temporarily comes on during an APU start with battery power. See the APU chapter for more information on APU starting.(AMM PART I 49) TR UNIT Light The amber TR UNIT light gives indication of transformer rectifier unit (TRU) failure. The TR UNIT light comes on for any one of these reasons: S Any TRU fails on the ground, or S TRU 1 fails in flight, or S TRU 2 and TRU 3 fail in flight. ELEC Light The ELEC light gives indication that the DC system or standby power system has a failure. You use BITE to find the failure. The amber ELEC light comes on only when the airplane is on the ground. MAINT Switch You use the maintenance switch during BITE. The BITE operates only on the ground. The maintenance switch is a momentary push-button switch.

ATA 24 Electric

Page 16

OSA MRO Support Pvt. Ltd

ELECTRICAL POWER

B737-- 600/700/800/900

One Stop Airline MRO Support Pvt. Ltd

ELECTRICAL METERS, BATTERY, AND GALLEY POWER MODULE (P5)

DC AMP

24-- 00

CPS FREQ

LED ALPHANUMERIC DISPLAY

DC VOLTS / AC AMPS / AC VOLTS BAT DISCHARGE

a

FLIGHT COMPARTMENT DC METER SELECTOR

TR UNIT a

FOR TRAINING PURPOSES ONLY!

OFF

OFF

ON

ON

BATTERY SWITCH (BEHIND COVER)

TR1 TR2

STBY PWR TEST

TR3

GEN1

MAINT APU GEN GEN2

GRD PWR

DC

AC METER SELECTOR

INV

STBY PWR

TEST

OFF

ON

IFE/PASS SEAT

a

OFF BAT

CAB/UTIL

ELEC

AUX BAT BAT BAT BUS

2

MAINTENANCE SWITCH

GALLEY ON

GALLEY POWER SWITCH

1 AC

ELECTRICAL METERS, BATTERY, AND GALLEY POWER MODULE (P5) 1

AIRPLANES WITH GALLEY SWITCH

2

AIRPLANES WITH CABIN UTILITY AND IFE SWITCHES

Figure 10 FRA US/E GiM

Mai 10, 2006

EL. METERS / BATTERY / GALLEY PWR MODULE ATA 24 Electric

Page 17

OSA MRO Support Pvt. Ltd

ELECTRICAL POWER

One Stop Airline MRO Support Pvt. Ltd

B737-- 600/700/800/900 24-- 00

LED Alphanumeric Display The LED alphanumeric display shows this type of information: S DC parameters (amps, volts) S AC parameters (amps, volts, frequency) S As many as two lines of maintenance fault messages. The selectors and the maintenance switch control what shows on the alphanumeric display. Battery Switch The main battery energizes these buses and components when you put the battery switch to the ON position: S Switched hot battery bus S Battery bus S Static inverter S AC standby bus S DC standby bus S P5-13 alphanumeric display. The battery switch is a two-position switch. The cover, when down, is a guard for the switch in the ON position. You must lift the cover before you move the switch to the OFF position.

FOR TRAINING PURPOSES ONLY!

Galley Switch The galley switch controls galley electrical power. The switch is a two-position switch. Cab/Util Switch and IFE / Pass Seat Switches Airplanes with CAB/UTIL and IFE/PASS SEAT switches; the CAB/UTIL switch controls galley and some utility’s electrical power. A second switch, the IFE/PASS SEAT switch, controls electrical power to passenger in--flight entertainment, cabin phones and passenger seat outlets. The two cabin power control switches are two--position switches

FRA US/E GiM

Mai 10, 2006

ATA 24 Electric

Page 18

OSA MRO Support Pvt. Ltd

ELECTRICAL POWER

B737-- 600/700/800/900

One Stop Airline MRO Support Pvt. Ltd

ELECTRICAL METERS, BATTERY, AND GALLEY POWER MODULE (P5)

DC AMP

24-- 00

CPS FREQ

LED ALPHANUMERIC DISPLAY

DC VOLTS / AC AMPS / AC VOLTS BAT DISCHARGE

a

FLIGHT COMPARTMENT DC METER SELECTOR

TR UNIT a

FOR TRAINING PURPOSES ONLY!

OFF

OFF

ON

ON

BATTERY SWITCH (BEHIND COVER)

TR1 TR2

STBY PWR TEST

TR3

GEN1

MAINT APU GEN GEN2

GRD PWR

DC

AC METER SELECTOR

INV

STBY PWR

TEST

OFF

ON

IFE/PASS SEAT

a

OFF BAT

CAB/UTIL

ELEC

AUX BAT BAT BAT BUS

2

MAINTENANCE SWITCH

GALLEY ON

GALLEY POWER SWITCH

1 AC

ELECTRICAL METERS, BATTERY, AND GALLEY POWER MODULE (P5) 1

AIRPLANES WITH GALLEY SWITCH

2

AIRPLANES WITH CABIN UTILITY AND IFE SWITCHES

Figure 11 FRA US/E GiM

Mai 10, 2006

EL. METERS / BATTERY / GALLEY PWR MODULE ATA 24 Electric

Page 19

OSA MRO Support Pvt. Ltd

ELECTRICAL POWER

One Stop Airline MRO Support Pvt. Ltd

GENERATOR DRIVE AND STBY POWER MODULE General The generator drive and standby power module (P5-5) has these indications and manual controls: S IDG low oil pressure indication (DRIVE lights) S Indication that the battery bus or either standby bus do not have power (STANDBY PWR OFF light) S Generator drive disconnect switches S Standby power switch.

B737-- 600/700/800/900 24-- 00

Standby Power Switch The standby power switch gives you manual control of the AC and DC standby power bus sources. The switch is a three-position switch. The switch is usually in the AUTO position. The cover is a guard for the switch in the AUTO position.

DRIVE Light The amber DRIVE light comes on when the IDG oil pressure is less than the operation limit.

FOR TRAINING PURPOSES ONLY!

Generator Drive Disconnect Switch The generator drive disconnect switch operates the disconnect mechanism for its (IDG) when the respective engine start lever is in the idle position. This removes engine accessory gearbox power from the IDG. There is one witch for each IDG. Each switch is spring-loaded to the NORMAL position. The DISCONNECT position is a momentary position. The cover is a guard for the switch in the NORMAL position. Break-away wire usually keeps the cover down. You must lift the cover and break the wire to move the switch. STANDBY PWR OFF Light The amber STANDBY PWR OFF light comes on when any of these buses do not have power: S AC standby bus S DC standby bus S Battery bus.

FRA US/E GiM

Mai 10, 2006

ATA 24 Electric

Page 20

OSA MRO Support Pvt. Ltd

ELECTRICAL POWER

B737-- 600/700/800/900

One Stop Airline MRO Support Pvt. Ltd

24-- 00

STANDBY POWER SWITCH (BEHIND GUARD)

STANDBY PWR OFF A

1 DRIVE

A

FOR TRAINING PURPOSES ONLY!

DRIVE A

STANDBY POWER

DISCONNECT

DISCONNECT

GENERATOR DRIVE DISCONNECT SWITCH (BEHIND GUARD)

2

BAT OFF AUTO

R

R

GENERATOR DRIVE AND STANDBY POWER MODULE (P5)

Figure 12 FRA US/E GiM

Mai 10, 2006

GEN. DRIVE / STBY POWER MODULE ATA 24 Electric

Page 21

OSA MRO Support Pvt. Ltd

ELECTRICAL POWER

One Stop Airline MRO Support Pvt. Ltd

General The upper part of the AC systems, generator and APU module (P5-4) has these lights: S GRD POWER AVAILABLE S TRANSFER BUS OFF S SOURCE OFF S GEN OFF BUS S APU GEN OFF BUS. The upper part of the module also has these manual controls: S Ground power switch S Engine generator switches S APU generator switches S Bus transfer switch.

FOR TRAINING PURPOSES ONLY!

GROUND POWER AVAILABLE Light The GRD POWER AVAILABLE light is on when external AC power is connected and the quality is good. The light is bright blue when on. Ground Power Switch You use the ground power switch to control external power to the AC transfer buses. See Electrical Power - Operation - General Description in this section for more information. TRANSFER BUS OFF Light The amber TRANSFER BUS OFF light comes on when the AC transfer bus does not have power. There is one light for each AC transfer bus.

Mai 10, 2006

24-- 00

SOURCE OFF Light The amber SOURCE OFF light supplies indication that an AC transfer bus is not energized by the selected source. The left SOURCE OFF light is related to these sources: S IDG 1 (GEN 1 switch) S APU (left APU GEN switch) S External power (ground power switch). The right SOURCE OFF light is related to these sources: S IDG 2 (GEN 2 switch) S APU (right APU GEN switch) S External power (ground power switch). The SOURCE OFF light does not indicate that the AC transfer bus is de-energized. For example, in flight the left SOURCE OFF light comes on when GCB 1 trips. However, the bus transfer function lets IDG 2 power AC transfer bus 1 S IDG1 fails S The bus transfer function closes the BTBs, and S Both AC transfer buses receive power from IDG2.

AC SYSTEMS, GENERATOR AND APU MODULE

FRA US/E GiM

B737-- 600/700/800/900

GEN OFF BUS Light The blue GEN OFF BUS light comes on when the engine generator control breaker (GCB) is open. This shows that the IDG is not a power source in use. The light goes off when the GCB closes. APU GEN OFF BUS Light The blue APU GEN OFF BUS light shows that the APU is running, but its generator is not a power source in use. The light is on when the APU is running and the auxiliary power breakers (APBs) is open. The light goes off when the APB closes or you shut down the APU.

ATA 24 Electric

Page 22

OSA MRO Support Pvt. Ltd

ELECTRICAL POWER

B737-- 600/700/800/900

One Stop Airline MRO Support Pvt. Ltd

24-- 00

GRD POWER AVAILABLE

GRD PWR OFF

GROUND POWER SWITCH

ON BUS TRANSFER TRANSFER BUS OFF A

O F F

SOURCE OFF A

FOR TRAINING PURPOSES ONLY!

GEN OFF BUS B

TRANSFER BUS OFF A

BUS TRANSFER SWITCH (BEHIND COVER)

SOURCE OFF A GEN OFF BUS B

APU GEN OFF BUS B

OFF

OFF

ON

ON

GEN 1

APU GENERATOR SWITCH (2)

A U T O

APU GEN

ENGINE GENERATOR SWITCH (2)

GEN 2

APU B MAINT

LOW OIL A PRESSURE

FAULT

A

OVER SPEED A

AC SYSTEMS, GENERATOR, AND APU MODULE (P5--4)

Figure 13 FRA US/E GiM

Mai 10, 2006

AC SYSTEMS / GENERATOR / APU MODULE ATA 24 Electric

Page 23

OSA MRO Support Pvt. Ltd

ELECTRICAL POWER

One Stop Airline MRO Support Pvt. Ltd

B737-- 600/700/800/900 24-- 00

Engine Generator Switches The engine generator switches give manual control for IDG power source selection. Each switch is a three-position switch and is spring-loaded to the center (neutral) position. The ON and OFF positions are momentary positions. You put a generator switch momentarily to the ON position to make that IDG the power source for its AC transfer bus. If IDG power quality is good, the electrical power system will first remove the present power source (open its generator breaker). Then, the generator breaker for the IDG will close and the IDG will now supply power. See Electrical Power - Operation - General Description in this section for more information.

FOR TRAINING PURPOSES ONLY!

APU Generator Switches The APU engine generator switches give manual control for APU generator power source selection. There are two switches because there are two bus tie breakers (BTBs). The switches operate like the engine generator switches. See Electrical Power - Operation - General Description in this section for more information. Bus Transfer Switch The bus transfer switch gives you manual control of the BTBs and the DC bus tie relay. The switch has two positions. The switch is usually in the AUTO position. A cover is a guard for the switch in the AUTO position. In the AUTO position, the BTBs and the DC bus tie relay work automatically as necessary. The BTBs and the DC bus tie relay open when the switch is put to the OFF position. See Electrical Power - Operation - General Description in this section for more information.

FRA US/E GiM

Mai 10, 2006

ATA 24 Electric

Page 24

OSA MRO Support Pvt. Ltd

ELECTRICAL POWER

B737-- 600/700/800/900

One Stop Airline MRO Support Pvt. Ltd

24-- 00

GRD POWER AVAILABLE

GRD PWR OFF

GROUND POWER SWITCH

ON BUS TRANSFER TRANSFER BUS OFF A

O F F

SOURCE OFF A

FOR TRAINING PURPOSES ONLY!

GEN OFF BUS B

TRANSFER BUS OFF A

BUS TRANSFER SWITCH (BEHIND COVER)

SOURCE OFF A GEN OFF BUS B

APU GEN OFF BUS B

OFF

OFF

ON

ON

GEN 1

APU GENERATOR SWITCH (2)

A U T O

APU GEN

ENGINE GENERATOR SWITCH (2)

GEN 2

APU B MAINT

LOW OIL A PRESSURE

FAULT

A

OVER SPEED A

AC SYSTEMS, GENERATOR, AND APU MODULE (P5--4)

Figure 14 FRA US/E GiM

Mai 10, 2006

AC SYSTEMS / GENERATOR / APU MODULE ATA 24 Electric

Page 25

OSA MRO Support Pvt. Ltd FOR TRAINING PURPOSES ONLY!

ELECTRICAL POWER

One Stop Airline MRO Support Pvt. Ltd

GENERATOR DRIVE - GENERAL DESCRIPTION Purpose The generator drive makes the normal source of AC power in flight. There are two IDGs on the airplane. Each supplies 115/200v ac, 400 Hz power. Each IDG can supply up to 90 KVA. General Description The engine accessory gearbox turns the IDG. Because engine speed changes, the gearbox speed also changes. The IDG takes the variable input speed and changes it into a constant speed (24,000 rpm) for its internal AC generator. The IDG uses a combination of internal mechanical and hydraulic components to supply the constant speed to the generator. The IDG uses oil for these purposes: S Hydromechanical S Lubrication S Cooling. The IDG has an oil cooling system. The cooling system has two external cooling components: S Air/oil cooler S Fuel/oil heat exchanger. The generator drive and standby power module gives indication and control of the AC generator drive system. The amber DRIVE light comes on when the IDG oil pressure is less than the minimum operating limit. You use the generator drive switch to manually operate the disconnect mechanism of the IDG. The IDG stops turning after the disconnect. You can reconnect the IDG on the ground only while then engine is not turning. The IDG also has an automatic thermal disconnect which occurs when the oil temperature gets too hot. You must remove the IDG to reset this type of disconnect.

FRA US/E GiM

Mai 10, 2006

B737-- 600/700/800/900 24-- 00

IDG The IDG is an assembly that has a hydromechanical constant speed drive (CSD) section and an oil-cooled brushless AC generator section. The IDG also includes a permanent magnet generator (PMG) for control and excitation power to the main generator section. The generator control unit (GCU) rectifies the PMG AC output to DC. See the AC generation section for more information on the generator.(AMM PART I 24-20) The GCU monitors IDG output power quality at two places: S A neutral current transformer (NCT) on the IDG, between the generator and ground S A line current transformer (LCT) between the generator and generator control breaker. The GCU uses DC power to excite the generator. The GCU controls the excitation power to control the output power of the IDG main generator. The GCU controls the generator control breaker (GCB) as a function of power quality or manual control input. IDG Oil System Pumps inside the IDG move the oil through the IDG and out through two external coolers. The air/oil cooler first uses engine fan air to decrease the temperature of the IDG oil. The air/oil cooler has an internal bypass which opens if the cooler becomes clogged. The oil leaves the air/oil cooler and goes to the fuel/oil heat exchanger. This cooler uses fuel to decrease the temperature of the IDG oil. See the fuel distribution system section for more information on the fuel/oil heat exchanger.(AMM PART I 73-11) The oil returns to the IDG from the air/oil cooer. The high pressure bypass valve opens if the fuel/oil heat exchanger becomes clogged. The amber DRIVE light comes on if the IDG oil pressure decreases below the minimum operating limit. The GCU receives a low oil pressure input from the IDG to control this light.

ATA 24 Electric

Page 26

OSA MRO Support Pvt. Ltd

ELECTRICAL POWER

1 DRIVE

B737-- 600/700/800/900

One Stop Airline MRO Support Pvt. Ltd

STANDBY PWR OFF

24-- 00

2

STANDBY POWER DRIVE

DISCONNECT

DISCONNECT BAT OFF AUTO GCU ENG START LEVER RELAY

GENERATOR DRIVE AND STANDBY POWER MODULE (P5) TO AC TRANSFER BUS OIL OUT

DPCT

GCB

IDG FOR TRAINING PURPOSES ONLY!

OIL IN HIGH PRESSURE BYPASS VALVE

ENGINE FAN AIR

IDG OIL COOLER

AIR/OIL COOLER

Figure 15 FRA US/E GiM

Mai 10, 2006

GENERATOR DRIVE - GENERAL ATA 24 Electric

Page 27

OSA MRO Support Pvt. Ltd

FIRE WARNING

ATA 26

One Stop Airline MRO Support Pvt. Ltd

B737-- 600/700/800/900 26-- 00

FIRE PROTECTION - GENERAL

FIRE PROTECTION - INTRODUCTION Purpose The fire protection systems monitor the airplane for these conditions: S Fire S Smoke S Overheat S Pneumatic duct leaks.

FOR TRAINING PURPOSES ONLY!

Fire/Overheat Detection The airplane has these fire/overheat detection systems: S Lavatory smoke detection S Engine fire/overheat detection S APU fire detection S Wheel well fire detection S Wing/Body overheat detection. S Cargo compartment smoke detection Extinguishing The airplane has these fire extinguishing systems: S Lavatory fire extinguishing bottles S Engine fire extinguishing bottles S APU fire extinguishing bottle S Portable fire extinguishers. S Cargo compartment fire extinguishing bottle.

FRA US/E GiM

Mai 10, 2006

ATA 26 Fire Warning

Page 28

OSA MRO Support Pvt. Ltd

FIRE WARNING

B737-- 600/700/800/900

One Stop Airline MRO Support Pvt. Ltd

26-- 00

WHEEL WELL FIRE DETECTION

APU -- APU FIRE DETECTION -- APU FIRE EXTINGUISHING

ENGINES -- ENGINE OVERHEAT AND FIRE DETECTION -- ENGINE FIRE EXTINGUISHING

CARGO COMPARTMENT -- CARGO COMPARTMENT SMOKE DETECTION -- CARGO COMPARTMENT FIRE EXTINGUISHING

FOR TRAINING PURPOSES ONLY!

LAVATORIES -- LAVATORY SMOKE DETECTION -- LAVATORY FIRE EXTINGUISHING

PORTABLE FIRE EXTINGUISHERS

WING/BODY OVERHEAT DETECTION CARGO COMPARTMENT -- CARGO COMPARTMENT SMOKE DETECTION -- CARGO COMPARTMENT FIRE EXTINGUISHING

Figure 16 FRA US/E GiM

Mai 10, 2006

ENGINES -- ENGINE OVERHEAT AND FIRE DETECTION -- ENGINE FIRE EXTINGUISHING

FIRE PROTECTION - INTRODUCTION ATA 26 Fire Warning

Page 29

OSA MRO Support Pvt. Ltd

FIRE WARNING

One Stop Airline MRO Support Pvt. Ltd

B737-- 600/700/800/900 26-- 00

FIRE PROTECTION - FIRE ALARMS

Description

Purpose The fire alarms provide visual and aural indication to the flight crew about a fire in any of these systems: S Engine 1 S Engine 2 S APU S Forward cargo compartment S Aft cargo compartment S Main wheel well.

When there is a fire in the engine, the engine and APU fire detection module provides a ground for the two red FIRE WARN lights and the bell. When there is a fire in the APU, the engine and APU fire detection module provides a ground for the two red FIRE WARN lights and the bell. The same module provides power for the red light and horn on the P28 panel. When there is a fire in the main wheel well, the compartment overheat detection controller provides a ground for the two red FIRE WARN lights and the bell. When there is smoke in the forward or aft cargo compartment, the cargo electronic unit provides a ground for the two red FIRE WARN lights and the bell. The two red FIRE WARN lights, bell, and horn are reset by removal of the ground. The reset is done by a momentary push on one of these: S Left FIRE WARN light S Right FIRE WARN light S Bell cutout switch on P8 S Horn cutout switch on the P28 panel

FOR TRAINING PURPOSES ONLY!

Visual and Aural Indications When there is a fire, these are the visual and aural indications: S Two red FIRE WARN lights on the P7 panel come on S Bell in the aural warning unit comes on S Red light and horn on alternatly in the right main wheel well come on (APU fire only). (The horn does not come on in flight.)

FRA US/E GiM

Mai 10, 2006

ATA 26 Fire Warning

Page 30

OSA MRO Support Pvt. Ltd

FIRE WARNING

B737-- 600/700/800/900

One Stop Airline MRO Support Pvt. Ltd

26-- 00

FWD

P7 PANEL APU FIRE DETECTORS

ENGINE FIRE DETECTORS

FIRE & OVERHEAT DETECTION FAULT AREA A

ENGINE 1 B LOOP

A

ENGINE 2 B LOOP

APU

FAULT

APU FIRE SHUTDOWN

SEE F.I.M. FOR MULTIPLE FAULTS OR FAULT CODE INFO.

FAULT DISPLAY FAULT CODES

OVHT DET A

WHEEL WELL

A DISCH

NORMAL

L

FOR TRAINING PURPOSES ONLY!

ENG 1 OVERHEAT F A U L T

I N O P

TEST

O V H T

OVHT DET

BELL CUTOUT

B

F I R E

L BOTTLE DISCHARGED

B

DISCH

FAULT

ENG 2 OVERHEAT

APU DET INOP APU BOTTLE DISCHARGED

R BOTTLE DISCHARGED ENGINES

DISCH

NORMAL

R

WIRING OPEN OR DETECTOR(S) FAULT WIRING SHORT TO GND LOOP POWER LOW DET. RESISTANCE CLEAN CONNECTIONS DETECTOR FAULT FOR 737--600/700/800 ONLY ENGINE APU CORE LEFT UPPER CORE RIGHT LOWER FAN LOWER TAILPIPE FAN UPPER

L

R

FIRE SWITCHES (FUEL SHUTOFF) PULL WHEN ILLUMINATED LOCK OVERRIDE: PRESS BUTTON UNDER HANDLE

ENGINE AND APU FIRE CONTROL PANEL (P8)

T E E1 X S T T

2

L

R

APU

FIRE

FAULT/INOP TEST PRESS AND HOLD 5 SEC TEST PASSES IF ALL 8 LIGHTS ON

APU ELECTRONIC CONTROL UNIT

A.P.U. FIRE CONTROL

TEST ENGINE AND APU FIRE DETECTION MODULE AURAL WARNING UNIT P28 APU GROUND CONTROL PANEL

Figure 17 FRA US/E GiM

Mai 10, 2006

Engine and APU Fire Warning ATA 26 Fire Warning

Page 31

OSA MRO Support Pvt. Ltd

FIRE WARNING

One Stop Airline MRO Support Pvt. Ltd

B737-- 600/700/800/900 26-- 00

ENGINE FIRE EXTINGUISHING Purpose The engine fire extinguishing system extinguishes fires in the engine compartment. General Description The engine fire extinguishing system floods the engine compartments with halon gas to extinguish the fire. Two fire extinguisher bottles supply the agent to either engine.

FOR TRAINING PURPOSES ONLY!

Physical Description These are the components of the engine fire extinguishing system: S Engine and APU fire controt module S Two fire extinguisher bottles S Engine fire extinguishing ports.

FRA US/E GiM

Mai 10, 2006

ATA 26 Fire Warning

Page 32

OSA MRO Support Pvt. Ltd

FIRE WARNING

OVHT DET

BELL CUTOUT

FAULT

DISCH

NORMAL ENG 1 A

L

R

O V H T

A

F I R E

A

R

A

R

A

R BOTTLE DISCHARGED

B DISCH L

R

OVERHEAT

APU BOTTLE DISCHARGED

26-- 00

L BOTTLE DISCHARGED

NORMAL ENG 2 A

APU DET INOP A

OVERHEAT I TEST N O P

OVHT DET A

DISCH

F A U L T

WHEEL WELL R B

A

B737-- 600/700/800/900

One Stop Airline MRO Support Pvt. Ltd

FIRE SWITCHES (FUEL SHUTOFF) PULL WHEN ILLUMINATED LOCK OVERRIDE: PRESS BUTTON UNDER HANDLE

ENGINES T E E 1 X S T T L

R

2

G APU

G

R

G

ENGINE AND APU FIRE CONTROL PANEL (P8) ENGINE AND APU FIRE CONTROL PANEL (P8) ENGINE FIREEXTINGUISHER BOTTLES

FOR TRAINING PURPOSES ONLY!

ENGINE FIRE EXTINGUISHING PORTS

MAIN WHEEL WELL

Figure 18 FRA US/E GiM

Mai 10, 2006

ENGINE FIRE EXTINGUISHING - INTRODUCTION ATA 26 Fire Warning

Page 33

OSA MRO Support Pvt. Ltd

FIRE WARNING

One Stop Airline MRO Support Pvt. Ltd

B737-- 600/700/800/900 26-- 00

APU FIRE EXTINGUISHING Purpose The APU fire extinguishing system extinguishes fires in the APU compartment. General Description When you operate the APU fire extinguishing system, it fills the APU compartment with halon gas to extinguish the fire. Physical Description The APU fire extinguishing system has these components: S Fire extinguisher bottle S Overheat/fire protection panel S APU ground control panel.

FOR TRAINING PURPOSES ONLY!

Location The APU fire extinguisher bottle is in the section 48 horizontal stabilizer accessory compartment. The overheat/fire protection panel is in the flight compartment on the PS panel. The APU ground control panel is in the right main wheel well, on the aft bulkhead. Operation When there is a fire condition, the APU fire warning switch unlocks. You can also use the warning switch override under the handle to unlock the switch. When you pull the APU fire warning switch up, the APU systems are shutdown and isolated. Turn the APU fire warning switch clockwise or counter-clockwise. This causes the APU fire extinguisher bottle to discharge halon gas. You can also use the APU ground control panel to operate the APU fire extinguisher bottle. When the APU fire extinguisher bottle is empty, the APU BOTTLE DISCHARGED light on the overheat/fire protection panel panel comes on. The APU DET INOP light and MASTER CAUTION lights come on if the APU fire detection circuits do not operate.

FRA US/E GiM

Mai 10, 2006

ATA 26 Fire Warning

Page 34

OSA MRO Support Pvt. Ltd

FIRE WARNING

OVHT DET

WHEEL WELL R

A DISCH

NORMAL ENG 1 A

L

R

I N O P

TEST

O V H T

FAULT

A

F I R E

R

APU BOTTLE DISCHARGED A

A R BOTTLE DISCHARGED

B DISCH NORMAL ENG 2 A OVERHEAT

R

26-- 00

A L BOTTLE DISCHARGED

DISCH

APU DET INOP A

OVERHEAT F A U L T

OVHT DET

BELL CUTOUT

B

A

B737-- 600/700/800/900

One Stop Airline MRO Support Pvt. Ltd

FIRE SWITCHES (FUEL SHUTOFF) PULL WHEN ILLUMINATED LOCK OVERRIDE: PRESS BUTTON UNDER HANDLE

L

ENGINES T R E E 1 X S T T L

R

2

G

APU

G

R

G

PRESSURE SWITCH WARNING SWITCH OVERRIDE

APU FIRE CONTROL 1.PULL HANDLE DOWN 2.DISCHARGE BOTTLE

FOR TRAINING PURPOSES ONLY!

BOTTLE DISCHARGE

FWD BOTTLE DISCHARGE

HORN CUTOUT

EXTINGUISHING BOTTLE SQUIB

FIRE WARNING SWITCH (TYPICAL)

APU FIRE CONTROL PANEL (P28)

Figure 19 FRA US/E GiM

Mai 10, 2006

APU FIRE EXT. - GEN. DESCR. ATA 26 Fire Warning

Page 35

OSA MRO Support Pvt. Ltd

FIRE WARNING

One Stop Airline MRO Support Pvt. Ltd

26-- 14 LAVATORY SMOKE DETECTION Purpose The Lavatory smoke detection system aterts the flight crew to smoke conditions in the lavatories. General Description — Smoke Detector A green indicator light comes on when a smoke detector has power. When there is smoke in the lavatory, the detector red alarm indicator light comes on and the detector horn sounds.

B737-- 600/700/800/900 26-- 00

Physical Description The smoke detector assembly has these components: S Alarm horn S Electrical connector S Power indicator S Power/reset switch S Sensor unit. The sensor unit has a red alarm indicator. It supplies a visual indication when the unit detects smoke.

FOR TRAINING PURPOSES ONLY!

Control Panel A green indicator light comes on when a smoke detector has power. When there is smoke in the lavatory, the detector sends a signal to cause these indications on the controt panet: S Red alarm indicator light comes on S Control panel horn sounds S Location indicator shows the location of the smoke detector under warning condition. Purpose The lavatory smoke detection system monitors for smoke in the lavatories. General Description A green indicator light comes on when a smoke detector has power. When there is smoke in a lavatory, the detector gives these alarm indications: S Detector alarm indicator light comes on. S Detector gives a horn sound. S Optional P5 panel SMOKE light comes on.

FRA US/E GiM

Mai 10, 2006

ATA 26 Fire Warning

Page 36

OSA MRO Support Pvt. Ltd

FIRE WARNING

B737-- 600/700/800/900

One Stop Airline MRO Support Pvt. Ltd

26-- 00

LAVATORY SMOKE DETECTOR (TYPICAL) LOCK RELEASE LEVER

POCKET SCALE

MOUNTING BRACKET

FOR TRAINING PURPOSES ONLY!

ELECTRICAL CONNECTOR

CASE COVER COVER SCREW SMOKE SENSOR

LAVATORY (TYPICAL)

FILTER (INTERNAL)

PLUGGED HOLES ALARM LED (RED)

Figure 20 FRA US/E GiM

Mai 10, 2006

LAV. SMOKE DET. - INTRO ATA 26 Fire Warning

Page 37

OSA MRO Support Pvt. Ltd

FIRE WARNING

One Stop Airline MRO Support Pvt. Ltd

LAVATORY SMOKE DETECTION - GENERAL DESCRIPTION General The smoke detection system gives aural and visual alarm indications when smoke is detected in a lavatory. Interfaces The lavatory smoke detector has these interfaces: S Lavatory call circuitry S Flight data recorder system S Lavatory smoke detection control panel S Electrical power.

B737-- 600/700/800/900 26-- 00

Control Panel Interface The control panel lets you test the smoke detectors and gives indications when a detector finds smoke. These indications show on the control panel when a smoke detector finds smoke: S SMOKE DETECT indicator (red) S Location indicator (red) S Internal horn turns on. S Electrical Power The smoke detection system uses 28v dc from bus 1.

FOR TRAINING PURPOSES ONLY!

Lavatory Call Circuitry The lavatory call light/reset switch (amber) on the outside of the lavatory and above the door flashes when the detector inside of that lavatory finds smoke. The smoke condition overrides the usual lavatory call indications. See the passenger and lavatory call lights section in the lights chapter for more information about the usual lavatory call indications (SECTION 33--27). The master lavatory call light (amber) on the forward exit locator sign flashes when a detector finds smoke in a forward lavatory. The master lavatory call light (amber) on the aft exit locator sign flashes when a detector finds smoke in an aft lavatory. The passenger address system turns on a chime that cycles on/off when a smoke detector finds smoke in a lavatory. Flight Data Recorder System The smoke detection system gives data to the flight data recorder system when any lavatory smoke detector finds smoke.

FRA US/E GiM

Mai 10, 2006

ATA 26 Fire Warning

Page 38

OSA MRO Support Pvt. Ltd

FIRE WARNING

B737-- 600/700/800/900

One Stop Airline MRO Support Pvt. Ltd

26-- 00

28V DC BUS 1

FLIGHT DATA RECORDER SYSTEM

SMOKE DETECTR

LAVATORY CALL LIGHT/RESET SW G POWER

MASTER LAVATORY CALL LIGHTS HORN INTERRUPT

PA SYS -- HIGH TONE CHIME LAVATORY CALL CIRCUITRY

FAULT R

FOR TRAINING PURPOSES ONLY!

TEST

RESET

LAVATORY SMOKE DETECTOR CONTROL PANEL

LAVATORY SMOKE DETECTOR (ONE IN EACH LAVATORY)

Figure 21 FRA US/E GiM

Mai 10, 2006

LAV. SMOKE DET. - GEN. DESCRIPTION ATA 26 Fire Warning

Page 39

One Stop Airline MRO Support Pvt. Ltd

B737-- 600/700/800/900 26-- 00

WHEEL WELL OVERHEAT DETECTION - INTRO Purpose The wheel well fire detection system uses overheat sensing elements in the main wheel well. It monitors the wheel well for fire condition. When the system senses a fire condition, alarm indications operate in the flight compartment. The indications are on the glareshield panel P7 and on the engine and APU fire control panel P8. A bell also operates in the flight compartment.

FOR TRAINING PURPOSES ONLY!

OSA MRO Support Pvt. Ltd

FIRE WARNING

FRA US/E GiM

Mai 10, 2006

ATA 26 Fire Warning

Page 40

OSA MRO Support Pvt. Ltd

FIRE WARNING

B737-- 600/700/800/900

One Stop Airline MRO Support Pvt. Ltd

26-- 00

FIRE WARN LIGHTS (P7) OVERHEAT SENSING ELEMENT

FOR TRAINING PURPOSES ONLY!

ENGINE AND APU FIRE CONTROL PANEL (P8) BELL

FWD MAIN WHEEL WELL

Figure 22 FRA US/E GiM

Mai 10, 2006

WHEEL WELL OVERHEAT DET. - INTRO ATA 26 Fire Warning

Page 41

OSA MRO Support Pvt. Ltd FOR TRAINING PURPOSES ONLY!

FIRE WARNING

One Stop Airline MRO Support Pvt. Ltd NOTE:

GENERAL DESCRIPTION Physical Description These are the major components of the wheel well fire detection system: S Wheel well fire detector elements S Compartment overheat detection control module S Overheat/fire protection panel.

B737-- 600/700/800/900 26-- 00

DURING THE WHEEL WELL FIRE TEST, THE ENGINE OVERHEAT-, THE ENGINE FIRE- AND THE APU FIRE SYSTEMS DO A TEST ALSO.

General Description These are the components for the wheel well fire detection: S Main wheel well fire (overheat) sensing element S Compartment overheat detection controller S P7 glareshield panel S Engine and APU fire control panel S Aural warning unit. Fire (overheat) sensing element in the main wheel well supplies the wheel well fire detection signal. The signal goes to the compartment overheat detection controller. This unit supplies the fire alarms. These are the flight compartment indications of a wheel well fire: S Two red FIRE WARN lights on P7 panel come on S Bell sounds in the aural warning unit S Red WHEEL WELL light on engine and APU fire control panel comes on. If the wheel well fire alarms come on due to a real fire or a fault, the MAINT ADV light on the compartment overheat detection controller comes on. Use the module to do a check for real alarm or a fault condition. You use the test switch on engine and APU fire control module panel to the OVHT/FIRE position to do a test of the wheel well sensing element. If the test passes, the indications in the flight compartment are the same as for a real fire condition. If the test fails, use the compartment overheat detection controller to isolate the fault.

FRA US/E GiM

Mai 10, 2006

ATA 26 Fire Warning

Page 42

OSA MRO Support Pvt. Ltd

FIRE WARNING

B737-- 600/700/800/900

One Stop Airline MRO Support Pvt. Ltd

26-- 00

WHEEL WELL FIRE, WING & BODY OVERHEAT DETECTION FIRE MASTER FLT CONT WARN CAUTION BELL CUTOUT PUSH TO RESET IRS FUEL

ELEC

ANTI--ICE

APU

HYD

OVHT/DET

DOORS

MASTER FIRE ENG WARN CAUTION OVERHEAD BELL CUTOUT PUSH TO RESET AIR COND

REFER TO MAINT. MANUAL FOR COMPLETE EXPLANATION OF SYSTEM CHARACTERISTICS

MAIN WHEEL WELL

WHEEL WELL FIRE ALARM

TEST DEPRESS AND HOLD ”DISP TEST” SWITCH UNTIL DISPLAY DISPLAY SHOWS ”88”. THEN RELEASE AND DISPLAY WILL BLANK. DEPRESS AND RELEASE ”MEM READ” SWITCH TO DISPLAY READ FIRST FAULT. REPEAT FOR ADDITIONAL FAULTS UNTIL CODE MEMORY ”97” IS DISPLAYED. DEPRESS ”MEM READ” TO BLANK. DEPRESS AND RELEASE ”LOC TEST” CODE. ”90” WILL BE PERFORM DISPLAYED WHILE TEST IS IN PROGRESS. IF NO FAULTS EXIST, SYSTEM ”99” WILL BE DISPLAYED. IF FAULTS ARE DISPLAYED, THEN DEPRESS AND RELEASE ”LOC TEST” SWITCH UNTIL ALL FAULTS TEST HAVE BEEN DISPLAYED OR UNTIL DISPLAY IS BLANK. (1) DEPRESS AND RELEASE ”LOC TEST” SWITCH UNTIL ”99” IS ERASE DISPLAYED. WHILE ”99” IS DISPLAYED, DEPRESS AND RELEASE ”MEM READ” SWITCH THEN DEPRESS AND RELEASE ”MEM CLEAR” MEMORY SWITCH FOR EACH FAULT UNTIL CODE ”97” IS BLANKED. (2) ABORT

OVHT DET A

WHEEL WELL R

B

A DISCH

FOR TRAINING PURPOSES ONLY!

NORMAL ENG 1 A OVERHEAT F A U L T

I TEST N O P

O V H T

OVHT DET

BELL CUTOUT

L

FAULT

R

A

DISCH

DISCH NORMAL ENG 2 A OVERHEAT

APU DET INOP A F I R E

R

APU BOTTLE DISCHARGED A

B

A L BOTTLE DISCHARGED

R

L

FIRE SWITCHES (FUEL SHUTOFF) PULL WHEN ILLUMINATED LOCK OVERRIDE: PRESS BUTTON UNDER HANDLE

R

A R BOTTLE DISCHARGED ENGINES T E 1 E X S T T L

R

2 R

G

APU

DEPRESS AND RELEASE ”DISP TEST” SWITCH.

MEM READ

MEM CLEAR

G G

MAINT. ADV.

FAULT & ALARM CODE MAINT. ADV. LIGHT WILL BE ON DURING FAULTS AND ALARMS--OFF AFTER ERASURE 00 FAILURE IN CONTROL OR POWER SUPPLY CARDS 01.02 115VAC FAILURE OR CONTROL CARD FAILURE 03.04.05 FAILED CONTROL CARD

FWD

P7 PANEL

A

LOC TEST

NOTES: 1. ALARMS BECOME ALARM HISTORY AFTER ERASURE. 2. EXISTING FAULTS CAN NOT BE ERASED UNTIL CORRECTED. LOCAL TEST ZONE/ SITUATION ALARM OPEN SHORT LEFT WING LE 14 12 10 LEFT AC PACK BAY 24 22 20 KEELBEAM 32 34 30 AFT CARGO SECT 44 40 42 RIGHT WING LE AND 64 62 60 AC PACK BAY WHEEL WELL FIRE 84 --IN NOT LOCAL PROGRESS COMPLETE COMPLETE TEST 90 98 99

ENGINE AND APU FIRE CONTROL PANEL (P8) DISP TEST

AURAL WARNING UNIT

Figure 23 FRA US/E GiM

Mai 10, 2006

COMPARTMENT OVERHEAT DETECTION CONTROLLER

WW-FIRE WARNING - GENERAL. DESCR. ATA 26 Fire Warning

Page 43

One Stop Airline MRO Support Pvt. Ltd

B737-- 600/700/800/900 26-- 00

WING AND BODY OVERHEAT DET.- INTRO Purpose The wing and body overheat detection system monitors for overheat conditions caused by pneumatic duct leaks. When it’s detectors sense this condition, they are shown in the flight compartment on the P5 and P7 panels.

FOR TRAINING PURPOSES ONLY!

OSA MRO Support Pvt. Ltd

FIRE WARNING

FRA US/E GiM

Mai 10, 2006

ATA 26 Fire Warning

Page 44

OSA MRO Support Pvt. Ltd

FIRE WARNING

B737-- 600/700/800/900

One Stop Airline MRO Support Pvt. Ltd

26-- 00

AIR CONDITIONING/ BLEED AIR CONTROLS PANEL (P5)

WHEEL WELL FIRE, WING & BODY OVERHEAT DETECTION RAM DOOR FULL OPEN

DUAL BLEED

RAM DOOR FULL OPEN RECIRC FAN OFF

L RECIRC FAN OFF

60 40 20

FAULT & ALARM CODE MAINT. ADV. LIGHT WILL BE ON DURING FAULTS AND ALARMS--OFF AFTER ERASURE 00 FAILURE IN CONTROL OR POWER SUPPLY CARDS 01.02 115VAC FAILURE OR CONTROL CARD FAILURE 03.04.05 FAILED CONTROL CARD

80 DUCT PRESS PSI 0

OVHT

TEST DISPLAY

TEST L PACK

MASTER CAUTION LIGHTS (P7)

OFF AUTO HIGH WING ANTI ICE

FOR TRAINING PURPOSES ONLY!

R PACK

ISOLATION VALVE

OFF AUTO HIGH AUTO

PACK A WING--BODY OVERHEATA BLEED TRIP OFFA

1

EXPLANATION OF SYSTEM CHARACTERISTICS

AUTO

AUTO

OPEN TRIP

RESET

WING ANTI ICE

A WING--BODY OVERHEATA BLEED TRIP OFFA

DEPRESS AND RELEASE ”MEM READ” SWITCH TO DISPLAY READ FIRST FAULT. REPEAT FOR ADDITIONAL FAULTS UNTIL CODE MEMORY ”97” IS DISPLAYED. DEPRESS ”MEM READ” TO BLANK.

DEPRESS AND RELEASE ”LOC TEST” SWITCH UNTIL ”99” IS (1) DISPLAYED. WHILE ”99” IS DISPLAYED, DEPRESS AND RELEASE ERASE ”MEM READ” SWITCH THEN DEPRESS AND RELEASE ”MEM CLEAR” MEMORY SWITCH FOR EACH FAULT UNTIL CODE ”97” IS BLANKED. (2) ABORT

DEPRESS AND RELEASE ”DISP TEST” SWITCH.

MEM READ

NOTES: 1. ALARMS BECOME ALARM HISTORY AFTER ERASURE. 2. EXISTING FAULTS CAN NOT BE ERASED UNTIL CORRECTED. ZONE/ SITUATION

OFF

ON

ON APU

DEPRESS AND HOLD ”DISP TEST” SWITCH UNTIL DISPLAY SHOWS ”88”. THEN RELEASE AND DISPLAY WILL BLANK.

DEPRESS AND RELEASE ”LOC TEST” CODE. ”90” WILL BE PERFORM DISPLAYED WHILE TEST IS IN PROGRESS. IF NO FAULTS EXIST, SYSTEM ”99” WILL BE DISPLAYED. IF FAULTS ARE DISPLAYED, THEN TEST DEPRESS AND RELEASE ”LOC TEST” SWITCH UNTIL ALL FAULTS HAVE BEEN DISPLAYED OR UNTIL DISPLAY IS BLANK.

PACK

OFF

MAINT. ADV.

A

REFER TO MAINT. MANUAL FOR COMPLETE

2

MEM CLEAR

BLEED

AIR CONDITIONING PANEL (P5)

WING AND BODY OVERHEAT SENSING ELEMENTS (TYP)

LOC TEST

LEFT WING LE LEFT AC PACK BAY KEELBEAM AFT CARGO SECT RIGHT WING LE AND AC PACK BAY WHEEL WELL FIRE LOCAL TEST

IN PROGRESS 90

ALARM 14 24 34 44

LOCAL TEST OPEN SHORT 12 10 22 20 32 30 40 42

64

62

84

--

NOT COMPLETE 98

60 -COMPLETE 99

DISP TEST

COMPARTMENT OVERHEAT DETECTION CONTROLLER

Figure 24 FRA US/E GiM

Mai 10, 2006

WING & BODY OVERHEAT DET.- INTRO ATA 26 Fire Warning

Page 45

OSA MRO Support Pvt. Ltd

FIRE WARNING

One Stop Airline MRO Support Pvt. Ltd

B737-- 600/700/800/900 26-- 00

CARGO COMP. SMOKE DETECTION - INTRO Purpose The lower cargo compartment smoke detection system gives warnings in the flight deck if there is smoke in a lower cargo compartment. The warnings are for the forward and aft lower cargo compartments.

FOR TRAINING PURPOSES ONLY!

Abbreviations and Acronyms CEU ---- cargo electronics unit

FRA US/E GiM

Mai 10, 2006

ATA 26 Fire Warning

Page 46

B737-- 600/700/800/900

One Stop Airline MRO Support Pvt. Ltd

26-- 00

AFT CARGO COMPARTMENT

FOR TRAINING PURPOSES ONLY!

OSA MRO Support Pvt. Ltd

FIRE WARNING

FORWARD CARGO COMPARTMENT

Figure 25 FRA US/E GiM

Mai 10, 2006

CARGO SMOKE DET. - INTRO ATA 26 Fire Warning

Page 47

OSA MRO Support Pvt. Ltd FOR TRAINING PURPOSES ONLY!

FIRE WARNING

One Stop Airline MRO Support Pvt. Ltd

B737-- 600/700/800/900 26-- 00

GENERAL DESCRIPTION Component Location These are the components in the flight deck that have an interface with the lower cargo compartment smoke detection system: S Aural warning unit S Cargo smoke detection and fire suppression module, P8--75 S Fire warning lights on P7. General Description These are the functions of the lower cargo compartment smoke detection components on the cargo smoke detection and fire suppression module: S DETECTOR FAULT amber light is on if one or more of the detectors has a power failure. S A three--position (A, NORM, B) DET SELECT SWITCH, one for each cargo compartment. S NORM position lets both detectors or with one detector failed sense smoke and give fire alarm. S A or B lets the selected detector sense smoke and give fire alarm. S TEST push button switch, does a test of cargo smoke detectors and extinguishing system. S FWD, AFT red cargo fire warning switchlight is on if smoke is detected in the related cargo compartment. S Smoke detection in the forward or aft cargo compartment puts on the two fire lights on the P7 panel and operates the fire bell in the aural warning unit.

FRA US/E GiM

Mai 10, 2006

ATA 26 Fire Warning

Page 48

OSA MRO Support Pvt. Ltd

FIRE WARNING

B737-- 600/700/800/900

One Stop Airline MRO Support Pvt. Ltd

26-- 00

FIRE LIGHT (2)

EXT FWD AFT G

C A R G O

DET SELECT NORM A

NORM B

B

A

DETECTOR FAULT A

G FWD

TEST

ARM

ARMED W FWD

R

F I R E

DISCH

AFT

ARMED W AFT

R

DISCH

A

FOR TRAINING PURPOSES ONLY!

CARGO SMOKE DETECTION AND FIRE SUPPRESSION MODULE (P8)

AURAL WARNING UNIT Figure 26 FRA US/E GiM

Mai 10, 2006

CARGO SMOKE DET. - GENERAL DESCR. ATA 26 Fire Warning

Page 49

OSA MRO Support Pvt. Ltd

FIRE WARNING

One Stop Airline MRO Support Pvt. Ltd

B737-- 600/700/800/900 26-- 00

LAV FIRE EXTING BOTTLE AND TEMP INDICATOR Purpose The lavatory fire extinguishing system extinguishes fires under the wash basin and trash bin area. Physical Description The lavatory extinguishing system has these components: S Fire extinguisher bottle S Temperature indicators. Location The lavatory fire extinguishing systems are in the lavatories under the wash basin. Operation The extinguisher bottle has two discharge ports. The ports have eutectic plugs. These plugs melt at high temperatures. When there is an overheat or fire condition, this occurs: -- Temperature indicators change color (white to black) -- Eutectic plug melts -- Extinguisher releases halon to stop the fire.

FOR TRAINING PURPOSES ONLY!

Training Information Point You must weigh the lavatory extinguisher bottle at regular intervals.

FRA US/E GiM

Mai 10, 2006

ATA 26 Fire Warning

Page 50

OSA MRO Support Pvt. Ltd

FIRE WARNING

B737-- 600/700/800/900

One Stop Airline MRO Support Pvt. Ltd

26-- 00

LAVATORY FIRE EXTINGUISHER BOTTLE

FOR TRAINING PURPOSES ONLY!

DISCHARGE NOZZLES

TEMPERATURE INDICATOR STRIP BLACK WHEN EXPOSED TO TEMPERATURE IS EXCEEDED LAVATORY (TYPICAL)

180

F

200

F

230

F

250

F

TEMPERATURE INDICATORS

Figure 27 FRA US/E GiM

Mai 10, 2006

LAVATORY FIRE EXT. - BOTTLE AND TEMP-INDIC. ATA 26 Fire Warning

Page 51

OSA MRO Support Pvt. Ltd

FIRE WARNING

One Stop Airline MRO Support Pvt. Ltd

PORTABLE FIRE EXTINGUISHING Purpose There are portable fire extinguishers to extinguish fires inside the airplane. There are two types of extinguishers, water-type and halon. The Halon extinguishers are for electrical and flammable liquid fires. The water-type extinguishers are for solid combustible fires.

FOR TRAINING PURPOSES ONLY!

Location There are extinguishers in these areas: S Flight compartment S Galley S Passenger compartment. Placards identify all of the extinguisher locations.

B737-- 600/700/800/900 26-- 00

Operation To operate the water-type extinguisher, turn the handle and push the trigger. To operate the Halon extinguisher, remove the handle lock pin and push the handle. Training Information Point After you use the water-type extinguisher, you must fill it again and replace the cartridge. If the handle lock pin on the Halon extinguisher is not there, you must weight the extinguisher to find out if it is not full. The pressure gage is not a satisfactory check of the extinguisher.

Physical Description The water—type extinguishers contain a water and anti-freeze mixture. Each water extinguisher has these parts: S Trigger (discharge valve) S Water cylinder S Handle with internal gas cartridge S Discharge nozzle S Quick—release mounting strap. Each Halon extinguisher has these parts: S Pressure gage S Halon cylinder S Trigger S Discharge nozzle S Handle lock pin S Handle.

FRA US/E GiM

Mai 10, 2006

ATA 26 Fire Warning

Page 52

OSA MRO Support Pvt. Ltd

FIRE WARNING

One Stop Airline MRO Support Pvt. Ltd

DISCHARGE NOZZLE

TRIGGER

B737-- 600/700/800/900 26-- 00

HANDLE

HANDLE PRESSURE INDICATOR

DISCHARGE NOZZLE

QUICK RELEASE STRAP

HANDLE LOCK PIN

TRIGGER (DISCHARGE VALVE)

FOR TRAINING PURPOSES ONLY!

WATER CYLINDER

HALON CYLINDER

WATER--TYPE FIRE EXTINGUISHER

HALON FIRE EXTINGUISHER

Figure 28 FRA US/E GiM

Mai 10, 2006

PORTABLE FIRE EXT.

ATA 26 Fire Warning

Page 53

OSA MRO Support Pvt. Ltd

ANTI ICE

ATA 30

One Stop Airline MRO Support Pvt. Ltd

B737-- 600/700/800/900 30-- 00

ICE AND RAIN PROTECTION

ICE AND RAIN PROTECTION - GEN. DESCRIPTION Control Panel The controls and indications for the ice and rain protection system are on the P-5 panel. Wing and Engine Thermal Anti-ice Systems The wing thermal anti—ice and the engine inlet cowl thermal anti—ice systems use hot engine bleed air to prevent ice formation. Probe Heat The air data probes use electric heat to prevent ice. Flight Deck Windows Flight deck windows use electric heat to do these things: S Prevent ice formation on the windows S Prevent fog on the windows S Improve windshield impact strength.

PITOT AND STATIC - INTRODUCTION The pitot and static anti—icing system keeps ice off the air data probes. This prevents false air data signals that ice causes. General The air data probes use electric power for heat. The probes have integral heaters. The pitot and static anti—icing system supplies heat to these probes: — Alpha vanes(2) — Total air temperature probe (1) — Pitot probes (5). The static system sense ports are not part of the probe heat system. These ports are flush with the fuselage and heat is not necessary. You control the air data probe heat from the control module on the P—5 panel.

FOR TRAINING PURPOSES ONLY!

The windshields have these features to improve forward vision in heavy rain: -- Windshield wipers -- Hydrophobic (rain repellent) coatings. Drain and Water line Heating Electric heaters prevent freezing in the water and waste systems components.

FRA US/E GiM

Mai 10, 2006

ATA 30 Anti Ice

Page 54

OSA MRO Support Pvt. Ltd

ANTI ICE

B737-- 600/700/800/900

One Stop Airline MRO Support Pvt. Ltd

30-- 00

FOR TRAINING PURPOSES ONLY!

ELEVATOR PROBE HEAT

WATER AND WASTE LINES AND DRAINS HEAT

ICE AND RAIN CONTROLS AND INDICATIONS FLIGHT COMPARTMENT WINDOWS

PITOT PROBE (3)

ANGLE OF ATTACK SENSOR (2)

TOTAL AIR TEMPERATURE PROBE

Figure 29 FRA US/E GiM

Mai 10, 2006

INLET COWL THERMAL ANTI--ICE

WING THERMAL ANTI--ICE

ICE & RAIN - GENERAL DESCRIPTION ATA 30 Anti Ice

Page 55

OSA MRO Support Pvt. Ltd

ANTI ICE

One Stop Airline MRO Support Pvt. Ltd

B737-- 600/700/800/900 30-- 00

PITOT AND STATIC - CONTROL PANEL Purpose The pitot and static control panel (P5—9) does these things: S Controls the electric power to the pitot and static anti—icing systems S Gives the flight crew indication of the pitot and static anti—icing system status. Location The panel is on the P5 overhead panel.

FOR TRAINING PURPOSES ONLY!

General Description The panel has control and indication circuitry for the pitot and static anti—icing system. The air data probe heaters are divided into two systems, A and B. Two toggle switches let the crew turn on the heat systems: — PITOT HEAT A — PITOT HEAT B. The system indication lights are divided into two banks, one for A system and one for B system. The lights come on when the probe heaters do not draw electrical current. TAT test switch This is a customer option: This switch is only installed in airplanes with aspirated TAT-probe. On airplanes with aspirated TAT-probe installed, the flight management computer uses even on ground the ambient airtemperature for performance calculations. Probe heating on ground would result wrong performance calculations. So on ground, even with left heater switch in ON, the TAT-probe is not heated. Nevertheless, the amber OFF-light extinguishes. With airplane air, the probe automatically is heated.

FRA US/E GiM

Mai 10, 2006

ATA 30 Anti Ice

Page 56

OSA MRO Support Pvt. Ltd

ANTI ICE

B737-- 600/700/800/900

One Stop Airline MRO Support Pvt. Ltd

CAPT PITOT L ELEV PITOT

PROBE A A

B OFF

A

L ALPHA VANE A

FOR TRAINING PURPOSES ONLY!

30-- 00

TEMP PROBE A

ON

F/O PITOT

A

AUX PITOT

A

HEAT

R ELEV PITOT A

TAT TEST

R ALPHA VANE A

WINDOW/PITOT HEAT MODULE (P5)

Figure 30 FRA US/E GiM

Mai 10, 2006

PITOT AND STATIC - CONTROL PNL ATA 30 Anti Ice

Page 57

OSA MRO Support Pvt. Ltd FOR TRAINING PURPOSES ONLY!

ANTI ICE

One Stop Airline MRO Support Pvt. Ltd

B737-- 600/700/800/900 30-- 00

CABIN WINDOW ANTI-ICING (CWAI) INTRO Purpose The control cabin window anti-icing system improves window impact strength and prevents ice formation on the flight compartment windows. General Description The control cabin anti-icing system uses electrical power to heat the flight compartment windows. The controls and indications for the control cabin window anti-icing system are on the P5—9 panel. Window heat control units (WHCUs) are part of the control cabin window anti-icing system. The WHCUs do these things: S Monitor window temperatures S Supply ON and OVERHEAT system indication S Test the system S Program power output to the windows. The WHCUs control power to these windows: -- No. 1 Left and right -- No. 2 left and right. Thermal switches monitor window temperature and control power to these windows: -- No. 3 left and right -- No. 4 left and right -- No. 5 left and right. Windows in the thermal switch control systems are not part of the P5—9 indication and test functions.

FRA US/E GiM

Mai 10, 2006

ATA 30 Anti Ice

Page 58

OSA MRO Support Pvt. Ltd

ANTI ICE

B737-- 600/700/800/900

One Stop Airline MRO Support Pvt. Ltd

OVERHEAT

A

OVERHEAT

A

OFF A

OVERHEAT

OFF A

A

5L

OFF A

FWD

FWD

SIDE

OFF

OFF ON

A

R

OVHT

SIDE

OVERHEAT

OFF A

WINDOW HEAT

L

30-- 00

PWR TEST

ON

4R

4L

1L

5R

1R 2R

2L 3L

FLIGHT COMPARTMENT

3R

FOR TRAINING PURPOSES ONLY!

WINDOWS

WHCU

WHCU

WHCU

WHCU

WINDOW HEAT CONTROL UNITS

Figure 31 FRA US/E GiM

Mai 10, 2006

CWAI SYSTEM - INTRODUCTION ATA 30 Anti Ice

Page 59

OSA MRO Support Pvt. Ltd

ANTI ICE

One Stop Airline MRO Support Pvt. Ltd

B737-- 600/700/800/900 30-- 00

WINDSHIELD WIPER SYSTEM Purpose The windshield wiper system removes rain, sleet and snow from the No. 1 and No. 2 flight compartment windows. This improves the pilots’ forward vision. General Two WIPER control switches on the P5 forward overhead panel give the flight crew control of the system. The system has two windshield wiper and drive assemblies.

FOR TRAINING PURPOSES ONLY!

Location The WIPER control switches are on the P5 forward overhead panel. The two windshield wiper assemblies are on the No. 1R and No. 1L flight compartment windows. The two windshield wiper drive assemblies are on the No. 1R and No. 1L window sills. You get access to the windshield wiper drive assemblies from panels under the P7 glareshield.

FRA US/E GiM

Mai 10, 2006

ATA 30 Anti Ice

Page 60

OSA MRO Support Pvt. Ltd

ANTI ICE

B737-- 600/700/800/900

One Stop Airline MRO Support Pvt. Ltd

30-- 00

WIPER PARK

INT LOW HIGH

CONTROL SWITCH

FOR TRAINING PURPOSES ONLY!

WINDSHIELD WIPER ASSEMBLY

WINDSHIELD WIPER DRIVE ASSEMBLY

Figure 32 FRA US/E GiM

Mai 10, 2006

WINDSHIELD WIPER - INTRO ATA 30 Anti Ice

Page 61

OSA MRO Support Pvt. Ltd

ANTI ICE

One Stop Airline MRO Support Pvt. Ltd

B737-- 600/700/800/900 30-- 00

30--43 RAIN REPELLENT SYSTEM HYDROPHOBIC WINDSHIELD COATING Purpose The hydrophobic windshield coating improves visibility in heavy rain. Location Hydrophobic windshield coatings are on the outside surface of the left and right number 1 flight compartment windows.

FOR TRAINING PURPOSES ONLY!

General Description Hydrophobic (water repellent) windshield coatings are transparent films. The coatings repel water. This causes water drops to bead up and roll off the windshields. The coatings do not affect windshield strength or optical clarity. The hydrophobic coatings wear down over time. Wear depends on these things: -- Wiper use -- Route structure -- Windshield maintenance practices. As the coatings wear, they do not repel water droplets as satisfactorily. When this happens, apply a new hydrophobic coating on the windshield. It is not necessary to remove the windshield to do this.

Training Information Point For maintenance of the hydrophobic coatings, regularly clean the windshields. Use a 50 percent solution of isopropanol in distilled water and a soft cloth to clean the windshields. Do not use abrasive cleaning pads or cleaners. Do not use cleaning solutions with fluorides. Make sure the force of the blades on the window is proper. Worn or incorrectly set--up windshield wipers wear the coatings.

FRA US/E GiM

Mai 10, 2006

ATA 30 Anti Ice

Page 62

OSA MRO Support Pvt. Ltd

ANTI ICE

One Stop Airline MRO Support Pvt. Ltd

B737-- 600/700/800/900 30-- 00

WINDOW NO. 1

FOR TRAINING PURPOSES ONLY!

HYDROPHOBIC (RAIN REPELLENT) WINDSHIELD COATING

Figure 33 FRA US/E GiM

Mai 10, 2006

HYDROPHOBIC WINDSHIELD COATING ATA 30 Anti Ice

Page 63

30--10

One Stop Airline MRO Support Pvt. Ltd

B737-- 600/700/800/900 30-- 00

WING THERMAL ANTI-ICING SYSTEM

The wing anti-ice system (WTAI) keeps ice from forming on the Leading edge of the wing. General Description The WTAI system uses hot air from the pneumatic system to heat the 3 inboard leading edge slats of the wing. Switches in the flight deck control the operation of the WTAI system. The WTAI system may operate in flight or on the ground. The controls and indicators are on the P-5 panel. When the system is ON, the valves open, hot air from the pneumatic ducts goes to the leading edge of the wing. The heated air flows to the three inboard leading edge slat spray tubes. The air sprays into the slat cavities and exhausts overboard through holes in the bottom of the slats. Overheat switches in each wing leading edge, protect the slats from overheat. This overheat protection works only when the airplane is on the ground. Switches on the autothrottle switchpacks automatically close the WTAI valves when you advance the engine thrust levers. This conserves engine thrust for takeoff. This thrust conservation protection only works when the airplane is on the ground. The proximity sensor electronic unit (PSEU) gives the wing anti-ice control module (P5-11) air ground sense feedback. The engine and wing anti-ice module uses this feedback to enable overheat and thrust conservation protection for the wing anti-ice system. It also resets (switches off) the WTAI system during takeoff.

FOR TRAINING PURPOSES ONLY!

OSA MRO Support Pvt. Ltd

ANTI ICE

FRA US/E GiM

Mai 10, 2006

ATA 30 Anti Ice

Page 64

One Stop Airline MRO Support Pvt. Ltd

B737-- 600/700/800/900 30-- 00

FOR TRAINING PURPOSES ONLY!

OSA MRO Support Pvt. Ltd

ANTI ICE

Figure 34 FRA US/E GiM

Mai 10, 2006

Wing Anti Ice System Schematic ATA 30 Anti Ice

Page 65

30--20

One Stop Airline MRO Support Pvt. Ltd

B737-- 600/700/800/900 30-- 00

INLET COWL ANTI-ICING SYSTEM

The inlet cowl anti-icing system keeps ice from forming on the engine inlet cowl. Each engine has an inlet cowl anti-icing system. The sytems operate in flight and on the ground. The inlet cowl anti-icing system controls and indications are on the P5—11 panel. The system uses 28v dc power. When the system is ON, the inlet cowl thermal anti-ice (TAI) valve opens. Hot air from the engine bleed air manifold flows through the valve into the hollow inlet cowl. The warm air increases the temperature in the inlet cowl. The warm air then flows overboard through a vent at the bottom of the cowl. Each engine is the source of its inlet cowl thermal anti-icing air. Thermal anti-icing air is from the engine bleed air manifold, upstream of the pressure regulator and shutoff valve. An inlet cowl TAI pressure switch monitors the pressure in the duct downstream of the inlet cowl anti-icing valve. It causes the COWL ANTI-ICE (P5) light to come ON if pressures in the duct are greater than 65 psi.

FOR TRAINING PURPOSES ONLY!

OSA MRO Support Pvt. Ltd

ANTI ICE

FRA US/E GiM

Mai 10, 2006

ATA 30 Anti Ice

Page 66

OSA MRO Support Pvt. Ltd

ANTI ICE

One Stop Airline MRO Support Pvt. Ltd

B737-- 600/700/800/900 30-- 00

FOR TRAINING PURPOSES ONLY!

65 PSI

Figure 35 FRA US/E GiM

Mai 10, 2006

ICAI System Schematic ATA 30 Anti Ice

Page 67

OSA MRO Support Pvt. Ltd

INSTRUMENTS

ATA 31

One Stop Airline MRO Support Pvt. Ltd

B737-- 600/700/800/900 31-- 00

INSTRUMENTS

CLOCKS - GENERAL DESCRIPTION Purpose The clocks give time reference to the flight crew and other airplane systems. General This is the data that the clock shows: S Time and date set manually from the clock S Global positioning system (GPS) time and date from the multi--mode receiver (MMR) S Elapsed time S Chronograph time. The captain clock sends time and date to these components: S Flight management computer (FMC) S Flight data acquisition unit (FDAU) S Voice recorder. These units use the clock time and date for internal timing functions. The flight management computer (FMC) does not use the clock data if the FMC is programmed to use the global positioning system (GPS).

FOR TRAINING PURPOSES ONLY!

NOTE:

FRA US/E GiM

Mai 10, 2006

ATA 31 Instruments

Page 68

OSA MRO Support Pvt. Ltd

INSTRUMENTS

B737-- 600/700/800/900

One Stop Airline MRO Support Pvt. Ltd CHR

31-- 00

TIME/DATE MAN

GPS-TIME 60 TIME MMR 2

50

SET TIME-DATE

10

FMC 2 P3 F/O INSTRUMENT PANEL -- F/0 CLOCK

20

40 ET 30 RESET

FIRST OFFICER CLOCK

FMC 1

TIME/DATE

CHR

MAN

FOR TRAINING PURPOSES ONLY!

60 TIME

FDAU

SET

50

10

40

20

P1 CAPT INSTRUMENT PANEL -- CAPT CLOCK TIME-DATE

ET 30 GPS-TIME

VOICE RECORDER RESET

MMR 1

CAPTAIN CLOCK

Figure 36 FRA US/E GiM

Mai 10, 2006

Clocks - General, Location ATA 31 Instruments

Page 69

One Stop Airline MRO Support Pvt. Ltd

B737-- 600/700/800/900 31-- 00

INTRODUCTION Purpose The flight data recorder system (FDRS) stores airplane parameters and system data for the last 25 hours of operation (minimum memorize-time). The flight data recorder (FDR) protects the parameters and the system data. If there is an airplane accident, these parameters supply data on flight conditions and ai rp lane systems operat ion. Airline personneI can also use the data to make an analysis of system performance during airplane maintenance.

FOR TRAINING PURPOSES ONLY!

OSA MRO Support Pvt. Ltd

INSTRUMENTS

FRA US/E GiM

Mai 10, 2006

ATA 31 Instruments

Page 70

One Stop Airline MRO Support Pvt. Ltd

B737-- 600/700/800/900 31-- 00

FOR TRAINING PURPOSES ONLY!

OSA MRO Support Pvt. Ltd

INSTRUMENTS

Figure 37 FRA US/E GiM

Mai 10, 2006

FDRS - INTRODUCTION ATA 31 Instruments

Page 71

OSA MRO Support Pvt. Ltd FOR TRAINING PURPOSES ONLY!

INSTRUMENTS

One Stop Airline MRO Support Pvt. Ltd

General The FDRS receives and stores aip[ane parameters from airplane systems and sensors. The flight data recorder (FDR) keeps this data and protects it if the airplane has an accident. It records parameters that are necessary for regulatory agencies. The airlines can also set additional parameters to record. According to shop maintenance information, in 2004, there are 1275 parameters recorded on the flight data recorder of a 737--NG. Each parameter is appr. 50hrs memorized in the FDR. In the following training manual, you will not find all the components and their location which provide data to be recorded on the FDR! Each airline may request additional parameters to be recorded for customized purposes like system-trendmornitoring! The FDRS has these components: S Flight data recorder (FDR) S Flight data acquisition unit (FDAU) S FDAU status relay S Flight recorder test module S Printer S System test plug/connector S Program switch module. The FDRS operates automatically when one of the engines is in operation or the airplane is in the air. It also operates while you do tests on the ground.

Aircraft Identification A program switch module gives the aircraft identification number to the flight data acquisition unit. FDAU The FDAU collects mandatory and recommended flight data for the flight data recorder. The FDAU also collects aircraft condition monitoring system (ACMS) data for airline use. The FDAU changes the mandatory and the recommended flight parameters into the Harvard biphase format. This data goes to the flight data recorder. The FDAU has ACMS software in its memory. This software selects input data to monitor. The data is changed to a digital format. The FDAU keeps it in memory. Data can go to the data loader control panel and then move to a disk in a data loader. FDR The FDR gets formatted data from the FDAU and keeps it in solid state non--volatile memory. The flight recorder has the capacity to keep the last 25 hours of flight data. The FDR records the data in a fire and crash resistant LRU. An underwater locator beacon is on the front of the FDR. System Test Plug/Connector Connect ground support equipment to the system test plug to test the FDRS. Data Loader Control Panel ACMS data from the FDAU goes through the data loader control panel to a data loader. The data loader can store data from the FDAU on a disk. The data loader control panel switch lets you select the transfer of ACMS data. You can transfer software from a disk in the data loader to the FDAU through the data loader control panel.

Flight Recorder/Mach Airspeed Warning Test Module The flight recorder test module shows the condition of the flight recorder system. If there is a system fault, an amber OFF light comes on. The OFF light also comes on if the system is off. The flight recorder test module also has a TEST/NORMAL switch. When this switch is in the TEST position, the FDR gets power. Input Signals The fliqht data acquisition unit (FDAU) processes arralog, digital, ard discrete signals from many sensors and systems. Mai 10, 2006

31-- 00

A three axis accelerometer gives acceleration data along the vertical, lateral, and longitudinal axis.

FDRS - GENERAL DESCRIPTION

FRA US/E GiM

B737-- 600/700/800/900

Printer A printer gives printed ACMS reports. The FDAU sends report data to the printer. The printer sends status and bus control signals to the FDAU.

ATA 31 Instruments

Page 72

OSA MRO Support Pvt. Ltd

INSTRUMENTS

B737-- 600/700/800/900

One Stop Airline MRO Support Pvt. Ltd

FLIGHT RECORDER TEST NORMAL

31-- 00

FLIGHT DATA RECORDER

MACH AIRSPEED WARNING TEST NO 1 NO 2

OFF A

FLIGHT RECORDER/MACH AIRSPEED WARNING TEST MODULE

115V AC

FDAU STATUS RELAY

SYSTEM TEST PLUG/CONNECTOR CAGE CODE: 97895 PN: 967--0212

FOR TRAINING PURPOSES ONLY!

ACCELEROMETER

ACMS WEIGHT 19.0 LBS (8.63 KGS) MAX DFDR POWER: 35W MAX, 115V. 400HZ DFDAU SERIAL NO. MFR DATE MOD STATUS

CONTROL DISPLAY UNITS DISCRETE DATA

ACMS

ANALOG DATA

DFDAU

1 2 3 4 5 6 7 8 9 10 11121314151617181920

DIGITAL DATA

Figure 38 Mai 10, 2006

DATA LOAD SELECTOR SINGLE SYS C L R CAPT F/O UPR LWR SYSTEM SELECT NORMAL DFDAU ACMS

DATA LOADER CONTROL PANEL

FLIGHT DATA ACQUISITION UNIT FRA US/E GiM

OPTICAL FDR: (CUSTO MER OPTION)

PRINTER

FDRS - GENERAL DESCRIPTION ATA 31 Instruments

Page 73

One Stop Airline MRO Support Pvt. Ltd

B737-- 600/700/800/900 31-- 00

FDRS - COMPONENT LOCATION FLT. COMPT Flight Compartment The flight recorder/mach airspeed warning test module is on the P5 aft overhead panel. The system test plug/connector is on the P l8 panel. The data loader control panel is on the P 6l pare I. The printer is on the aft electronic panel P 8.

FOR TRAINING PURPOSES ONLY!

OSA MRO Support Pvt. Ltd

INSTRUMENTS

FRA US/E GiM

Mai 10, 2006

ATA 31 Instruments

Page 74

OSA MRO Support Pvt. Ltd

INSTRUMENTS

B737-- 600/700/800/900

One Stop Airline MRO Support Pvt. Ltd

31-- 00

P5 AFT OVERHEAD PANEL -- FLIGHT RECORDER/MACH AIRSPEED WARNING TEST MODULE P7 GLARESHIELD PANEL -- MASTER CAUTION LIGHTS -- OVERHEAD ANNUNCIATOR P9 FORWARD ELECTRONICS PANEL -- CONTROL DISPLAY UNITS

FOR TRAINING PURPOSES ONLY!

P8 PANEL -- PRINTER

P61 PANEL -- DATA LOADER CONTROL PANEL

FLIGHT COMPARTMENT (LOOKING FORWARD)

BEHIND P18 PANEL -- SYSTEM TEST PLUG/CONNECTOR

FLIGHT COMPARTMENT (LOOKING AFT)

Figure 39 FRA US/E GiM

Mai 10, 2006

FLIGHT COMP. - LOCATION ATA 31 Instruments

Page 75

OSA MRO Support Pvt. Ltd

INSTRUMENTS

One Stop Airline MRO Support Pvt. Ltd

B737-- 600/700/800/900 31-- 00

AURAL WARNING SYSTEM - GENERAL DESCRIPTION General The aural warning module is the only component in the aural warning system. System monitor circuits detect incorrect system conditions and flight crew alerts. The monitor circuits supply discrete signals to the aural warning module.

FOR TRAINING PURPOSES ONLY!

Inputs These are the discrete inputs to the aural warning system: S Unsafe landing warning S Unsafe takeoff warning S Cabin pressure warning S Autopilot disengage S Overspeed warning S Fire warning S Crew call. Sounds The aural warning module gives these sounds in the flight compartment: S Fire bells S Chimes S Overspeed clackers S Wailer S Continuous horn S Intermittent horn. NOTE:

This section only describes in general the types of warnings available in the 737NG. more detailed descriptions and functions are described in the particular system-description. (example: fire bell is described in chapter 26--fire warning system).

FRA US/E GiM

Mai 10, 2006

ATA 31 Instruments

Page 76

OSA MRO Support Pvt. Ltd

INSTRUMENTS

B737-- 600/700/800/900

One Stop Airline MRO Support Pvt. Ltd

31-- 00

P5 OVERHEAD PANEL -- ALTITUDE HORN CUTOUT SWITCH P7 GLARESHIELD PANEL -- MASTER FIRE WARNING LIGHTS

P9 FORWARD ELECTRONIC PANEL -- AURAL WARNING MODULE P10 CONTROL STAND -- LANDING GEAR WARNING HORN CUTOUT SWITCH

AURAL WARNING MODULE TAKEOFF WARNING

FOR TRAINING PURPOSES ONLY!

P8 AFT ELECTRONIC PANEL -- FIRE WARNING BELL CUTOUT SWITCH

CONTINUOUS HORN

LANDING WARNING

INTERMITTENT HORN

FIRE WARNING

FIRE BELL

AUTOPILOT DISENGAGE

WAILER

OVERSPEED WARNING

OVERSPEED CLACKERS

CABIN PRESSURE WARNING

CHIMES

CREW CALL

AURAL WARNING MODULE

Figure 40 FRA US/E GiM

Mai 10, 2006

AURAL WARNING - GENERAL ATA 31 Instruments

Page 77

One Stop Airline MRO Support Pvt. Ltd

B737-- 600/700/800/900 31-- 00

MASTER CAUTION SYSTEM - INTRODUCTION General The purpose of the master caution system is to inform the flight crew that system warnlights, located behind pilots or out of view of the captain and copilot, are illuminated. Example: With a hydraulic low-pressure light illuminated, (which is located on the aft overhead panel and therefor out of view of the pilots), on the glareshield the system annunciator HYDR and both MASTER CAUTION lights will illuminate. Reset of master caution lights: S Press captains or copilots master caution light. Master caution lights and master caution system annunciator lights will extinguish. Recall of the master caution lights: S Press any master caution six--pack. If pilots want to know if there is still a system warn-light out of their illuminated and pilots don’t want to turn their heads to see it, they simply press one of the master caution system annunciators. Six pack lights whose system warn light is still on will illuminate again. Six--pack system lights will illuminate.

FOR TRAINING PURPOSES ONLY!

OSA MRO Support Pvt. Ltd

INSTRUMENTS

FRA US/E GiM

Mai 10, 2006

ATA 31 Instruments

Page 78

OSA MRO Support Pvt. Ltd

INSTRUMENTS

B737-- 600/700/800/900

One Stop Airline MRO Support Pvt. Ltd

31-- 00

SYSTEM ANNUNCIATOR LIGHT (EXAMPLE: HYDRAULIC LOW PRESSURE

FOR TRAINING PURPOSES ONLY!

MASTER CAUTION LIGHT

FIRE WARN

MASTER CAUTION

BELL CUTOUT PUSH TO RESET

MASTER CAUTION LIGHT

ANTI--ICE

FLT CONT

ELEC

IRS

APU

HYD

FUEL

OVHT/DET

DOORS

ENG OVERHEAD

MASTER CAUTION

FIRE WARN

PUSH TO RESET BELL CUTOUT

AIR COND

MASTER CAUTION SYSTEM ANNUNCIATOR (COMMONLY CALLED: SIX-PACK)

Figure 41 FRA US/E GiM

Mai 10, 2006

MASTER CAUTION - GENERAL ATA 31 Instruments

Page 79

OSA MRO Support Pvt. Ltd FOR TRAINING PURPOSES ONLY!

INSTRUMENTS

One Stop Airline MRO Support Pvt. Ltd

B737-- 600/700/800/900 31-- 00

MASTER CAUTION SYSTEM - GENERAL DESCRIPTION The following should give a very general about the master caution system only! What we want to point out is: S Master Caution is not a centralized system with a „big black box“ downstairs. S Master Caution is individually integrated in the individual system module or -panel. S The panel triggers the master caution lights and the system lights in the master caution annunciator (commonly called „six-pack“). S So according to which system light illuminates together with the master lights, the crew knows from the beginning, which system malfunctions. S The master caution reset, by pressing a master caution light, is achieved in the system module (flight control module, fuel module, elec. module and so on). S The master caution recall, by pressing a master caution system six-pack, is also done in the system module. S To operate a system, for example a fuel pump including its warning, there are at least 4 circuit breaker necessary. Power reduncy not included. The circuit breakers are (example fuel pump): -- Fuel pump CB -- MASTER CAUTION ANNUNCIATOR CONT 1 CB (for the Fuel Module) -- SECT (for the system module annunciator lights) -- At least one MASTER CAUTION ANNUNCIATOR CB Please keep in mind, that each individual system controls its master caution by its module.

FRA US/E GiM

Mai 10, 2006

ATA 31 Instruments

Page 80

OSA MRO Support Pvt. Ltd

INSTRUMENTS

B737-- 600/700/800/900

One Stop Airline MRO Support Pvt. Ltd MODULE POWER

MASTER CAUTION ANNUNCIATOR CONT 1

31-- 00

FUEL MODULE P5 (TYPICAL)

SECT 1 LOW PRESSURE FUEL PUMP MASTER CAUTION LOGIC

P

RECALL RESET

PRESS. SWITCH (TYPICAL)

FUEL PUMP (TYPICAL)

FOR TRAINING PURPOSES ONLY!

SET

TO ALL OTHER SYSTEM MODULES WHO HAVE INTERFACE TO MASTER CAUTION

FIRE WARN

MASTER CAUTION

MASTER CAUTION

FLT CONT

ELEC

IRS

APU

HYD

FUEL

OVHT/DET

DOORS

BELL CUTOUT PUSH TO RESET

ANTI--ICE

ENG OVERHEAD

MASTER CAUTION

FIRE WARN BELL CUTOUT PUSH TO RESET

AIR COND

ALTERNATE POWER SOURCE

MASTER CAUTION ANNUNCIATOR

Figure 42 FRA US/E GiM

Mai 10, 2006

MASTER CAUTION - BASIC INTRODUCTION ATA 31 Instruments

Page 81

OSA MRO Support Pvt. Ltd

INSTRUMENTS

One Stop Airline MRO Support Pvt. Ltd

B737-- 600/700/800/900 31-- 00

TAKEOFF WARNING General The takeoff warning function gives an aural warning sound if the airplane is in an unsafe condition during takeoff or if the ground spoiler interlock valve remains open after takeoff. Abbreviations and Acronyms S asym -- asymmetry S FSEU -- flap/slat electronics unit S gnd -- ground S LE -- leading edge S PSEU -- proximity switch electronic unit S SMYD -- stall management yaw damper S spdbk -- speedbrake S sw -- switch S TE -- trailing edge S TO -- takeoff S UCM -- uncommanded motion S warn -- warning

FOR TRAINING PURPOSES ONLY!

NOTE:

in this document the take-off and landing warning is only shown in a very brief form. for more details see type-rating courses.

FRA US/E GiM

Mai 10, 2006

ATA 31 Instruments

Page 82

OSA MRO Support Pvt. Ltd

INSTRUMENTS

B737-- 600/700/800/900

One Stop Airline MRO Support Pvt. Ltd

31-- 00

SPDBK LEVER NOT DOWN PARKING BRAKE SET AIRPLANE ON GROUND PRESSURE TO GROUND SPOILERS

THRUST LEVERS AT TAKEOFF

LE FLAPS AND SLATS NOT EXTENDED, OR UCM

TE FLAPS NOT AT TAKEOFF, OR SKEW, ASYM, UCM STAB TRIM

FOR TRAINING PURPOSES ONLY!

STABILIZER OUT OF GREEN BAND

GROUND SPOILER INTERLOCK VALVE NOT CLOSED

INTERMITTENT HORN

LANDING GEAR

TAKEOFF WARNING CUTOFF

16

LE FLAPS AND SLATS NOT EXTENDED

Figure 43 FRA US/E GiM

Mai 10, 2006

17

18

LANDING GEAR TAKEOFF WARNING CUTOFF CIRCUIT BREAKER NOT OPEN

AIRPLANE IN AIR

LANDG. WARNING - GENERAL ATA 31 Instruments

Page 83

OSA MRO Support Pvt. Ltd

INSTRUMENTS

One Stop Airline MRO Support Pvt. Ltd

B737-- 600/700/800/900 31-- 00

COMMON DISPLAY SYSTEM General Introduction The common display system (CDS) shows performance, navigation and engine information in many different formats on six display units in the flight compartment. In the following description is only a very brief introduction to the common display system CDS. For more details see the training manual „31--62 CDS“ in type-rating courses.

FOR TRAINING PURPOSES ONLY!

NOTE:

FRA US/E GiM

Mai 10, 2006

ATA 31 Instruments

Page 84

One Stop Airline MRO Support Pvt. Ltd

B737-- 600/700/800/900 31-- 00

FOR TRAINING PURPOSES ONLY!

OSA MRO Support Pvt. Ltd

INSTRUMENTS

Figure 44 FRA US/E GiM

Mai 10, 2006

COMMON DISPL. SYSTEM - GENERAL ATA 31 Instruments

Page 85

OSA MRO Support Pvt. Ltd

INSTRUMENTS

One Stop Airline MRO Support Pvt. Ltd

CDS - GENERAL DESCRIPTION Purpose The purpose of the common display system (CDS) is to supply navigation and engine information to the flight crew. External Interfaces The computer for the CDS is the display electronics unit (DEU). Many avionic and airframe systems interface with the DEUs. These systems send ARINC 429, analog, and discrete data to the DEUs. The DEUs send ARINC 429, analog, and discrete data to these systems.

B737-- 600/700/800/900 31-- 00

Functional Description The DEUs collect data from many avionic and airframe systems. The DEU changes this data into a video signal and sends the data out on a coax cable. A coax coupler splits the video signal and sends the data to all six display units. Both DEUs send data to all six display units. The DEUs also are the interface between some avionic and airframe systems. For example, the DEUs receive BITE data from the electronic engine controller (EEC) and auxiliary power unit (APU). The DEUs send this data to the flight management computer. The DEUs also send EEC data to other avionic systems.

FOR TRAINING PURPOSES ONLY!

Components These are the components of the common display system: -- Two display select panels -- An engine display control panel -- Two EFIS control panels -- Two display source selectors -- Two display electronics units (DEUs) -- Four coax couplers -- Six identical display units (DUs) -- Two brightness control panels -- Two remote light sensors (RLSs). Operation These are the things that determine the information that shows on the displays units: S Display unit status S Display unit location S Selections made on the control panels and modules. S These are the formats that show on the display units: S Primary flight display (PFD) S Navigation display (ND) S Engine display.

FRA US/E GiM

Mai 10, 2006

ATA 31 Instruments

Page 86

OSA MRO Support Pvt. Ltd

INSTRUMENTS

MAIN PANEL DUS NORM ENG PRI

B737-- 600/700/800/900

One Stop Airline MRO Support Pvt. Ltd

31-- 00

LOWER DU NORM ND ENG PRI

OUTBD PFD

MAIN PANEL

UPPER DU BRT

PFD INBD MFD

OFF OUTBD DU INBD DU LOWER DU BRT BRT BRT

DISPLAY SELECT PANEL (2)

MINS FPV BARO RADIO

MTRS

IN

BARO HPA

BRIGHTNESS CONTROL PANEL (2)

STD

RST

MAP 20 40 80 VOR 2 VOR PLN APP 10 160 OFF CTR 5 TFC 320 OFF 640 ADF 1 ADF 2

VOR 1

WXR STA

WPT ARPT DATA

POS

TERR

RLS (2)

EFIS CONTROL PANEL (2)

1

SPD REF N1 SET AUTO AUTO BOTH V1

2 FUEL FLOW RESET RATE

VREF

FOR TRAINING PURPOSES ONLY!

VR

1

WT

OFF

MFD ENG SYS

USED

AUTO BRAKE AUTO BRAKE DISARM 2

3

DISPLAYS MAX

RTO ANTI SKID ANTI SKID INOP

CONTROL PANEL SOURCE AUTO BOTH BOTH ALL ALL ON 2 ON 1 ON 2 ON 1 NORMAL

DU (6) DISPLAY SOURCE SELECTORS

ENGINE DISPLAY CONTROL PANEL

AIRPLANE SYSTEMS

ARINC 429 OUTPUT BUSES

AIRPLANE SYSTEMS

DISCRETES

COAXIAL COUPLER (4)

DISPLAY ELECTRONICS UNIT (2)

Figure 45 FRA US/E GiM

Mai 10, 2006

COMMON DISPL. SYSTEM - GEN. DESCR. ATA 31 Instruments

Page 87

OSA MRO Support Pvt. Ltd FOR TRAINING PURPOSES ONLY!

LIGHTS

ATA 33

One Stop Airline MRO Support Pvt. Ltd

33-- 00

LIGHTS

FLIGHT COMPARTMENT LIGHTING - INTRO Purpose These are the four types of flight compartment lights: S Instrument and panel lights S Miscellaneous lights S Flight crew lights S Master dim and test. The instrument and panel lights are for the flight compartment controls and panel indications. The miscellaneous lights supply general lighting to the flight compartment. These are the miscellaneous lights: S Panel and control stand flood lights S Circuit breaker panel lights S Standby compass S Dome lights. The flight crew lights supply light for specific tasks. These are the flight crew lights: S Reading lights S Map lights S Flight kit lights S Chart lights. The master dim and test system controls the light for the system annunciator and indicator lights.

FRA US/E GiM

B737-- 600/700/800/900

Mai 10, 2006

General Description The dome lights supply general lighting for the cabin. The glareshield supplies background lighting for the pi lots. Each instrument and instrument panel has lighting. The control stand gets light from an overhead floodlight. The circuit breaker panels get light from floodlights. There are lights for the standby compass and map lighting. The master dim and test switch can do these functions: S Test the indicator and panel lights S Cause the indicator and panel lights to come on in the bright or dim mode. The replacement lamps for the lights in the flight compartment are above the right number three window.

ATA 33 Lights

Page 88

OSA MRO Support Pvt. Ltd

LIGHTS

One Stop Airline MRO Support Pvt. Ltd

B737-- 600/700/800/900 33-- 00

MISCELLANEOUS LIGHT (TYP) INSTRUMENT AND PANEL LIGHTS FLIGHT CREW LIGHT (TYP) (TYP) MASTER DIM AND TEST STANDBY COMPASS SWITCH

SPARE LAMPS

FOR TRAINING PURPOSES ONLY!

GLARESHIELD

Figure 46 FRA US/E GiM

Mai 10, 2006

FLIGHT COMP. LIGHTING - INTRO ATA 33 Lights

Page 89

OSA MRO Support Pvt. Ltd

LIGHTS

One Stop Airline MRO Support Pvt. Ltd

B737-- 600/700/800/900 33-- 00

CARGO AND SERVICE COMPARTMENT - INTRO Purpose The cargo and service compartment lights supply light to aid maintenance personnel and ground crews.

FOR TRAINING PURPOSES ONLY!

Location There are cargo compartments lights in the forward and aft cargo compartments. There are service lights in these areas: S Forward equipment compartment S Electronic equipment compartment S Right air conditioning compartment S Left air conditioning compartment S Aft accessory compartment (section 48 interior) S APU compartment S Tail cone compartment. There are wheel well lights in the nose and main wheel wells.

FRA US/E GiM

Mai 10, 2006

ATA 33 Lights

Page 90

OSA MRO Support Pvt. Ltd

LIGHTS

B737-- 600/700/800/900

One Stop Airline MRO Support Pvt. Ltd

33-- 00

AFT ACCESSORY COMPARTMENT LIGHT

TAILCONE SERVICE LIGHTS

MAIN WHEEL WELL LIGHTS FWD CARGO COMPARTMENT LIGHTS

APU COMPARTMENT SERVICE LIGHTS

FOR TRAINING PURPOSES ONLY!

ELECTRONIC EQUIPMENT COMPARTMENT LIGHTS

AFT CARGO COMPARTMENT LIGHTS

NOSE WHEEL WELL LIGHTS

AIR CONDITIONING COMPARTMENT LIGHTS FORWARD EQUIPMENT COMPARTMENT LIGHTS

Figure 47 FRA US/E GiM

Mai 10, 2006

CARGO & SERVICE COMP. LIGHTING - INTRO ATA 33 Lights

Page 91

OSA MRO Support Pvt. Ltd

LIGHTS

One Stop Airline MRO Support Pvt. Ltd

B737-- 600/700/800/900 33-- 00

EXTERIOR LIGHTING - INTRODUCTION Purpose The exterior lights supply light for airplane identification, direction, and to aid in the safe operation of the airplane. These are the exterior lights on the airplane: S Wing illumination S Landing lights (not shown) S White anti—collision lights S Red anti—collision lights S Position lights S Taxi and runway turnoff lights S Logo lights. EXTERIOR lights - CONTROL SWITCHES Purpose The exterior lighting control switches control the airplane external lights.

FOR TRAINING PURPOSES ONLY!

Location The exterior lighting control switches are in the flight compartment on the lower edge of the P5 forward overhead panel. General Description These are the switches on the P5 that control the external lights: S Landing (retractable and fixed) S Runway turnoff S Logo S Position S Anti--collision S Wing S Wheel Well S Taxi.

FRA US/E GiM

Mai 10, 2006

ATA 33 Lights

Page 92

OSA MRO Support Pvt. Ltd

LIGHTS

B737-- 600/700/800/900

One Stop Airline MRO Support Pvt. Ltd

ANTI--COLLISION LIGHT (WHITE)

33-- 00

ANTI--COLLISION LIGHT (WHITE)

POSITION LIGHTS (WHITE AND GREEN)

ANTI--COLLISION LIGHT (RED) LOGO LIGHTS POSITION LIGHTS (WHITE AND RED)

WING ILLUMINATION LIGHT

FOR TRAINING PURPOSES ONLY!

TAXI LIGHT

E X T E N D

LANDING RETRACT

OFF

RUNWAY TURNOFF L R OFF

OFF

ON

ON

RUNWAY TURNOFF LIGHT

LOGO OFF

TAXI

ANTI--COLLISION LIGHT (WHITE)

FIXED LANDING LIGHT

ANTI POSITION STROBE & COLLISION WING OFF OFF STEADY

WHEEL WELL OFF

OFF L ON R RETRACTABLE

L

ON R FIXED

ON

STEADY

ON

ON

ON

EXTERIOR LIGHTING SWITCHES

Figure 48 FRA US/E GiM

Mai 10, 2006

EXTERIOR LIGHTING - INTRO ATA 33 Lights

Page 93

OSA MRO Support Pvt. Ltd

LIGHTS

One Stop Airline MRO Support Pvt. Ltd

EMERGENCY LIGHTING - INTRODUCTION Purpose The emergency lighting system puts lights on areas inside and outside of the airplane. The emergency lights also identify the exit paths. The emergency lights operate at these times: S When emergency light system is on S When there is a loss of airplane DC power and the P5 panel emergency light switch is in the ARMED position.

33-- 00

General Description The emergency lighting system has these components: S Exit signs S Aisle lights S Slide lights S Floor proximity lights S Power supplies (battery packs) S Control switches. The emergency lights use rechargeable battery packs as a power source. There are seven battery packs on the airplane. The battery pack assemblies have logic and charging circuits. The logic controls circuits control light operation and charges the battery packs during normal airplane operations.

FOR TRAINING PURPOSES ONLY!

Location Control switches are at these locations: S The P5 panel in the flight compartment. S The P14 aft attendant panel. The battery packs are at these locations: S Behind the sidewall carpet risers S In the ceiling panels near the fwd and aft entry doors. The emergency lights supply lights for these areas: S Aisles S Exit areas (inside and outside of airplane) S Floor paths to exits.

B737-- 600/700/800/900

FRA US/E GiM

Mai 10, 2006

ATA 33 Lights

Page 94

One Stop Airline MRO Support Pvt. Ltd

B737-- 600/700/800/900 33-- 00

FOR TRAINING PURPOSES ONLY!

OSA MRO Support Pvt. Ltd

LIGHTS

Figure 49 FRA US/E GiM

Mai 10, 2006

EMERGENCY LIGHTING - INTRO ATA 33 Lights

Page 95

ATA 23

One Stop Airline MRO Support Pvt. Ltd

B737-- 600/700/800/900 23-- 00

COMMUNICATION

FLIGHT INTERPHONE SYSTEM Purpose The flight crew uses the flight interphone system to speak with each other and the ground crew. Flight and maintenance crews use the flight interphone system to get access to the communication systems. You can also use the flight interphone system to monitor the navigation receivers.

FOR TRAINING PURPOSES ONLY!

OSA MRO Support Pvt. Ltd

COMMUNICATION

FRA US/E GiM

Mai 10, 2006

ATA 23 Communication

Page 96

One Stop Airline MRO Support Pvt. Ltd

B737-- 600/700/800/900 23-- 00

FOR TRAINING PURPOSES ONLY!

OSA MRO Support Pvt. Ltd

COMMUNICATION

Figure 50 FRA US/E GiM

Mai 10, 2006

FLIGHT INTERPHONE - INTRODUCTION ATA 23 Communication

Page 97

OSA MRO Support Pvt. Ltd FOR TRAINING PURPOSES ONLY!

COMMUNICATION

One Stop Airline MRO Support Pvt. Ltd

FLIGHT INTERPHONE - GENERAL DESCRIPTION General The remote electronics unit (REU) and the audio control panel (ACP) control the audio signals to and from the flight crew. The REU also controls the communication with the service interphone and related electronics equipment. During a system failure, emergency operation bypasses all active system circuitry and maintains airplane to ground station communication. Flight Crew Interfaces This system description shows the captain’s system. Interfaces and components for other flight crew stations are similar. The flight crew uses microphone (mic) switches on these components to send audio to the REU: S Control wheel S ACP S Hand microphone. A microphone on these components lets the flight crew speak on the flight interphone system: S Oxygen mask S Headset S Hand mic. The flight crew uses the audio control panels for these functions: S Listen to the communication and navigation receivers S Adjust the volume of the received audio S Select a transmitter and microphone S Key the microphone. The remote electronic unit (REU) sends audio signals to the headsets and to the flight interphone speakers. Other Component and System Interfaces The REU connects to these other components: S Communications radios

FRA US/E GiM

Mai 10, 2006

B737-- 600/700/800/900 23-- 00

-- the REU sends push-to-talk (PTT) and microphone audio to the transceivers and receives audio back from them S Navigation receivers -- the REU receives voice and Morse code identification tones. The flight interphone system also has an interface with these other systems: S Passenger address system: Lets the flight crew make announcements to passengers -S Service interphone system: Lets the flight crew speak with attendants and service personnel S Voice recorder: Records the flight crew microphone and receive audio S Ground proximity warning computer (GPWC): Lets flight crew monitor warning signals S Traffic alert and collision avoidance system (TCAS): Lets the flight crew monitor TCAS signals S Flight control computer (FCC): Gives discrete signals to the REU. This signal activates an altitude alert tone generator. S Weather radar (WXR): Lets the flight crew monitor WXR windshear warnings Flight Interphone - Control Wheel PTT switch The control wheel PTT switch gives push--to--talk input for the boom or oxygen mask microphones. The control wheel PTT switch is a three position switch. It is on the outboard horn of the captain’s and the first officer ’s control wheel. These are the switch positions: S MIC - spring loaded to OFF position: -- microphone audio and PTT signals go to the communication system you select. S OFF - fixed position: -- The ACP PTT switch can key the microphone. S INT - fixed position (hot-mike function): -- microphone audio goes to the flight interphone system (ACP selection is not changed).

ATA 23 Communication

Page 98

OSA MRO Support Pvt. Ltd

COMMUNICATION

B737-- 600/700/800/900

One Stop Airline MRO Support Pvt. Ltd

23-- 00

MIC SELECTOR

AAU

R/T

CONTROL WHEEL MIC SWITCH

I/C

MASK V BOOM

B

R

SVR INT SVR INT FLT INT ONE 2

ALT NORM

AUDIO CONTROL PANEL (3)

MOD

OBS EXT ATT

F/O

CAPT

HDPH FLT SVR

HDPH FLT SVR

FLIGHT INTERPHONE SPEAKERS

ADJ DME 1 ADJ PA SENS PA GAIN ATTENTION PA ST FOR HANDLING AUDIO POT 1 ELECTROSTATIC AUDIO POT 2 SENSITIVE DEVICES

COMMUNICATION RADIOS

A[]

NAVIGATION RECEIVERS

B[]

C[]

D[]

OXYGEN MASKS

PASSENGER ADDRESS REMOTE ELEC

ONICS UNIT

SERVICE INTERPHONE

RVTECH P/N BOEING P/N

HEADSETS

TSO C50C RTCA 00--16

FOR TRAINING PURPOSES ONLY!

B2AKXXXXFX

ENV CAT AAZ

VOICE RECORDER

HEADPHONE GPWC TCAS COMPUTER HAND MIC

SERIAL NO.

FCC

DATE MFD

WXR

WEIGHT 7.75 LBS

EXTERNAL POWERPANEL

Figure 51 FRA US/E GiM

Mai 10, 2006

REMOTE ELECTRONICS UNIT

FLIGHT INTERPHONE - GEN. DESCRIPTION ATA 23 Communication

Page 99

OSA MRO Support Pvt. Ltd FOR TRAINING PURPOSES ONLY!

COMMUNICATION

One Stop Airline MRO Support Pvt. Ltd

FLIGHT INTERPHONE - AUDIO CONTROL PANEL Purpose The flight crew uses the audio control panels (ACPs) to control audio for the communication and navigation systems. Each ACP controls one station. Controls These are the controls on the ACP: S Transmitter selectors S Receiver switches S Radio--Intercom PTT switch S BOOM--MASK switch S Filter switch S ALT--NORM switch. Microphone Selector Switches The flight interphone system gets audio from these microphones: S Boom S Oxygen mask S Hand--held. You push a transmitter selector to select a communication transmitter or system. You can select only one system at a time. When you push a transmitter selector, this happens: S The selector switch light comes on S The received audio comes on at the volume set by the receiver volume control S The microphone audio and PTT signals are enabled for that system. When you push a PTT switch, the microphone audio and PTT signals go to the system set by the selector switches. When the ACP initially gets power, the flight interphone system is active. Receiver Switches Push the receiver switch (push--on, push--off) to listen to communication or navigation system audio. Turn it to adjust the volume. Radio--Intercom PTT Switch The radio--intercom PTT switch is a three--position switch with momentary contacts in the R/T and I/C positions. FRA US/E GiM

Mai 10, 2006

B737-- 600/700/800/900 23-- 00

In the R/T position, the microphone audio and PTT signals go to the communication system set by the transmitter selectors. In the I/C position, the boom or mask microphone jacks connect to the flight interphone system. BOOM--MASK Switch The BOOM--MASK switch allows selection of the boom microphone jack or the oxygen mask microphone as an audio source. Filter Switch The filter switch controls the filter that processes the navigation audio you receive. This switch has these positions: S V (voice) position passes only voice frequencies through the filter and blocks the 1020 hz range frequency. S B (both) position passes voice and range (coded station identification) frequencies through the filter to the audio output. S R (range) position passes only range frequencies through the filter and blocks voice frequencies. ALT--NORM Switch You use the ALT--NORM switch to select either normal or emergency operation of the flight interphone system. Each station operates independently. When you select NORM, the flight interphone system operates as usual. When you select ALT, the flight interphone system operates in the emergency mode. The only ACP controls that operate are the BOOM--MASK switch and the R/T position of the PTT switch. The hand--mic does not operate. When you select ALT on the captain or observer ACP, you hear receiver audio from the VHF--1 transceiver at the headphone and headset jacks. When you key the MIC, the audio and PTT signals go to the VHF--1 transceiver. When you select ALT on the first officer ACP, you hear receiver audio from the VHF--2 transceiver at the headphone and headset jacks. When you key the MIC, the audio and PTT signals go to the VHF--2 transceiver.

ATA 23 Communication

Page 100

OSA MRO Support Pvt. Ltd

COMMUNICATION

23-- 00

MIC SELECTOR

W

W

W

1--VHF--2--VHF--3

R/T

MASK

I/C

BOOM

W HF

1--NAV--2

FOR TRAINING PURPOSES ONLY!

B737-- 600/700/800/900

One Stop Airline MRO Support Pvt. Ltd

B

SERV INT

W FLT INT

MKR

W PA

SPKR

RECEIVER SWITCHES

ALT

R

NORM

RADIO--INTERCOM MASK--BOOM FILTER SWITCH PTT SWITCH SWITCH

1

W

1--ADF--2

V

TRANSMITTER SELECTOR (7)

ALT--NORM SWITCH

INOP INOP PLACARDS ARE OVER THE LEGEND OF ANY TRANSMITTER SELECTOR OR RECEIVE SWITCH THAT IS NOT CONNECTED.

Figure 52 FRA US/E GiM

Mai 10, 2006

FLIGHT INTERPHONE - ACP ATA 23 Communication

Page 101

One Stop Airline MRO Support Pvt. Ltd

B737-- 600/700/800/900 23-- 00

FLIGHT INTERPHONE FLIGHT COMP. LOCATIONS Flight Compartment Component Locations These are the captain’s and first officer’s flight interphone system components: S Control wheel mic switch S Flight interphone speaker S Hand mic jack S Oxygen mask mic jack S Boom mic jack S Headphone jack S Audio control panel. The observer has these flight interphone components: S Hand mic jack S Oxygen mask mic jack S Headphone jack S Audio control panel.

FOR TRAINING PURPOSES ONLY!

OSA MRO Support Pvt. Ltd

COMMUNICATION

FRA US/E GiM

Mai 10, 2006

ATA 23 Communication

Page 102

OSA MRO Support Pvt. Ltd

COMMUNICATION

B737-- 600/700/800/900

One Stop Airline MRO Support Pvt. Ltd

ALTERNATE LOCATION FOR CAPT. INTERPHONE SPEAKER

23-- 00

P5 AFT OVERHEAD PANEL -- OBSERVER AUDIO CONTROL PANEL

CAPT FLIGHT INTERPHONE SPEAKER

F/O FLIGHT INTERPHONE SPEAKER

F/O JACKS -- BOOM MICROPHONE -- HEADPHONE CAPT JACKS -- BOOM MICROPHONE -- HEADPHONE CAPT CONTROL WHEEL MIC SWITCH

F/O CONTROL WHEEL MIC SWITCH

FOR TRAINING PURPOSES ONLY!

CAPT JACKS -- HAND MICROPHONE -- MASK MICROPHONE

F/O JACKS -- HAND MICROPHONE -- MASK MICROPHONE

P8 AFT ELECTRONIC PANEL -- CAPT AUDIO CONTROL PANEL -- F/O AUDIO CONTROL PANEL

Figure 53 FRA US/E GiM

Mai 10, 2006

FLIGHT INTERPHONE - COMP. LOC. ATA 23 Communication

Page 103

One Stop Airline MRO Support Pvt. Ltd

B737-- 600/700/800/900 23-- 00

SERVICE INTERPHONE SYSTEM General The ground crew uses the service interphone system to talk to each other and to the flight crew. Service interphone jacks are at different locations on the airplane. The flight attendants use the service interphone system to speak with each other and the pilots.

FOR TRAINING PURPOSES ONLY!

OSA MRO Support Pvt. Ltd

COMMUNICATION

FRA US/E GiM

Mai 10, 2006

ATA 23 Communication

Page 104

OSA MRO Support Pvt. Ltd

COMMUNICATION

One Stop Airline MRO Support Pvt. Ltd

B737-- 600/700/800/900 23-- 00

FOR TRAINING PURPOSES ONLY!

GROUND CREW

CABIN CREW

Figure 54 FRA US/E GiM

Mai 10, 2006

SERVICE INTERPHONE - INTRODUCTION ATA 23 Communication

Page 105

OSA MRO Support Pvt. Ltd FOR TRAINING PURPOSES ONLY!

COMMUNICATION

One Stop Airline MRO Support Pvt. Ltd

B737-- 600/700/800/900 23-- 00

SERVICE INTERPHONE - GEN. DESCRIPTION General The service interphone system is for the: S Flight crew S Attendants S Ground crew. The flight crew selects the service interphone function from the audio control panel (ACP). Flight interphone microphones send audio to the remote electronics unit (REU). Flight interphone headsets and speakers get audio from the REU. The flight crew can also use a handset to talk on the service interphone system. The handset jack connects to the system without ACP control. The attendants operate a handset to connect into the system. An attendant panel connects the handset to the REU. The ground crew microphones connect into the system through the service interphone switch. You must turn on the service interphone switch to operate the system from the service station jacks. The headset gets audio from the REU. The REU does these functions: S Combines audio from the microphones S Amplifies the audio signal S Sends audio to handsets, headsets, and speakers.

FRA US/E GiM

Mai 10, 2006

ATA 23 Communication

Page 106

OSA MRO Support Pvt. Ltd

COMMUNICATION

B737-- 600/700/800/900

One Stop Airline MRO Support Pvt. Ltd

23-- 00

MIC SELECTOR

SERV INT

AAU SVR INT SVR INT FLT INT ONE 2

AUDIO CONTROL PANEL (3)

MOD

OBS EXT ATT

F/O HDPH FLT SVR

ADJ DME 1 ADJ PA SENS PA GAIN PA ST AUDIO POT 1 AUDIO POT 2

A[]

CAPT HDPH FLT SVR

FWD ATTENDANT PANEL FWD ATTENDANT HANDSET

ATTENTION FOR HANDLING ELECTROSTATIC SENSITIVE DEVICES

B[]

C[]

D[]

FLIGHT INTERPHONE AFT ATTENDANT PANEL

FOR TRAINING PURPOSES ONLY!

-- MICROPHONES -- HEADPHONES -- SPEAKERS

REMOTE ELEC RVTECH P/N BOEING P/N TSO C50C RTCA 00--16 B2AKXXXXFX

ENV CAT AAZ

AFT ATTENDANT HANDSET

INSIDE AIRPLANE OUTSIDE AIRPLANE

SERVICE INTERPHONE SWITCH

SERVICE INTERPHONE JACKS

REMOTE ELECTRONICS UNIT

FLIGHT CREW OPERATION Figure 55 Mai 10, 2006

ATTENDANT OPERATION

SERIAL NO. DATE MFD WEIGHT 7.75 LBS

INTERPHONE JACK

FRA US/E GiM

ONICS UNIT

GROUND CREW OPERATION SERVICE INTERPHONE - GEN. DESCRIPTION ATA 23 Communication

HEADSET

Page 107

OSA MRO Support Pvt. Ltd

COMMUNICATION

One Stop Airline MRO Support Pvt. Ltd

B737-- 600/700/800/900 23-- 00

FLIGHT CREW CALL / CABIN INTERPHONE Purpose The flight crew call system tells: S Flight compartment personnel that there is a call from the cabin attendants S Attendants there is a call from the flight compartment or another attendant panel. FLIGHT CREW CALL / CABIN INTERPHONE -- DESCR. The flight crew call system lets the flight crew and attendants call each other. These are the calls that can be made: S Flight compartment to attendant stations S Attendant station to flight compartment S Attendant station to attendant station. Aural and visual indications from the system tell the flight and cabin crew to use the cabin interphone.

FOR TRAINING PURPOSES ONLY!

Flight Compartment to Attendant Stations You push the ATTEND switch on the passenger signs panel to call the attendant stations from the flight compartment. When you make this call, these are the indications in the passenger cabin: S The pink light on the forward and the aft exit locator signs comes on S The passenger address system sends a HI/LO chime to the cabin speakers. Attendant Station to Flight Compartment You use the handset to call the flight compartment from an attendant station. When you make this call, these are the indications in the flight compartment: S The CALL light on the passenger signs panel comes on S The aural warning module makes a HI chime. Attendant Station to Attendant Station You use the handset to call one attendant station from another attendant station. When you make this call, these are the indications in the passenger cabin: S The green light on the exit locator sign comes on at the other attendant station S The passenger address system sends a HI/LO chime to the cabin speakers. FRA US/E GiM

Mai 10, 2006

ATA 23 Communication

Page 108

OSA MRO Support Pvt. Ltd

COMMUNICATION

One Stop Airline MRO Support Pvt. Ltd

B737-- 600/700/800/900 23-- 00

EXIT LOCATOR SIGN (2) ATTENTAND CALL LIGHTS

ATTENDANT PANEL (2)

ATTENDANT HANDSET (2) CABIN

FOR TRAINING PURPOSES ONLY!

P5 FORWARD OVERHEAD PANEL -- PASSENGER SIGNS PANEL

ATTEND

GRD CALL

CALL

PASSENGER SIGNS PANEL

AURAL WARNING MODULE

P9 FORWARD ELECTRONIC PANEL -- AURAL WARNING MODULE

PASSENGER ADDRESS AMPLIFIER

FLIGHT COMPARTMENT

Figure 56 FRA US/E GiM

Mai 10, 2006

FLIGHT CREW CALL - GEN. DESCRIPTION ATA 23 Communication

Page 109

OSA MRO Support Pvt. Ltd FOR TRAINING PURPOSES ONLY!

COMMUNICATION

One Stop Airline MRO Support Pvt. Ltd

B737-- 600/700/800/900 23-- 00

PASSENGER ADDRESS - INTRODUCTION Purpose The passenger address (PA) system supplies these to the passenger cabin: S Passenger address announcements S Pre--recorded announcements S Boarding music S Chimes. PASSENGER ADDRESS -- GENERAL DESCRIPTION The passenger address (PA) amplifier puts a priority on the audio inputs from these places: S Pilots S Attendants S Pre--recorded announcement and boarding music reproducer (PRAM). The PA amplifier amplifies the audio input that has the highest priority and sends the signal to these places: S Passenger cabin speakers S Attendant speakers S Passenger entertainment system S Remote electronics unit (REU). The amplified audio to the REU goes through muting circuits for the forward and aft attendant speakers. When an attendant makes an announcement, the muting circuits stop the audio for that attendants speaker. The PA amplifier supplies chimes with other PA audio.

FRA US/E GiM

Mai 10, 2006

ATA 23 Communication

Page 110

OSA MRO Support Pvt. Ltd

COMMUNICATION

AAU SVR INT SVR INT FLT INT ONE 2

PILOT

MOD

OBS EXT ATT

F/O HDPH FLT SVR

ADJ DME 1 ADJ PA SENS PA GAIN PA ST AUDIO POT 1 AUDIO POT 2

A[]

B[]

23-- 00

CAPT HDPH FLT SVR

ATT SPEAKERS

ATTENTION ELECTROSTATIC SENSITIVE DEVICES C[]

D[]

DISPLAY REMOTE ELEC RVTECH P/N BOEING P/N TSO C50C RTCA 00--16 B2AKXXXXFX

CABIN AND LAV SPEAKERS

ONICS UNIT

TONE

ENV CAT AAZ

LOAD (OHMS)

SERIAL NO. DATE MFD WEIGHT 7.75 LBS

REMOTE ELECTRONICS UNIT

ATTENDANT

FOR TRAINING PURPOSES ONLY!

B737-- 600/700/800/900

One Stop Airline MRO Support Pvt. Ltd

OPERATE

LEVEL (VRMS)

MASTER GAIN

PA PTT PASSENGER ENTERTAINMENT SYSTEM

NO FASTEN SMOKING BELTS OFF AUTO ON

ATTEND

PRE--RECORDED ANNOUNCEMENT/ MUSIC REPRODUCER

LAVATORIES AND PASS SERVICE UNITS

Figure 57 FRA US/E GiM

Mai 10, 2006

PASSENGER ADDRESS AMPLIFIER

GRD CALL

PASSENGER SIGNS PANEL

PA - DESCRIPTION

ATA 23 Communication

Page 111

One Stop Airline MRO Support Pvt. Ltd

B737-- 600/700/800/900 23-- 00

VERY HIGH FREQUENCY SYSTEM - INTRO General The very high frequency (VHF) communication system supplies voice and data communication over line--of--sight distances. It gives communication between airplanes or between ground stations and airplanes. The VHF system operates in the aeronautical frequency range of 118.000 MHz to 136.975 MHz.

FOR TRAINING PURPOSES ONLY!

OSA MRO Support Pvt. Ltd

COMMUNICATION

FRA US/E GiM

Mai 10, 2006

ATA 23 Communication

Page 112

OSA MRO Support Pvt. Ltd

One Stop Airline MRO Support Pvt. Ltd

B737-- 600/700/800/900 23-- 00

FOR TRAINING PURPOSES ONLY!

COMMUNICATION

Figure 58 FRA US/E GiM

Mai 10, 2006

VHF - INTRODUCTION

ATA 23 Communication

Page 113

OSA MRO Support Pvt. Ltd

COMMUNICATION

One Stop Airline MRO Support Pvt. Ltd

VHF - GENERAL DESCRIPTION General The VHF communication system supplies the flight crew with voice and data line-of-sight communication. The VHF communication system can be used to communicate between airplanes and between airplanes and ground stations. The VHF communication radio is tunable in the frequency range of 118.000 MHz to 136.975 MHz. The VHF radio is used to transmit and receive voise and data communication. The 8.33 kHz spacing is only available for these frequency ranges: S 118.000 to 121.400 S 121.600 to 123.050 S 123.150 to 136.475

23-- 00

External Interface The VHF communication system connects with these components/systems: S The remote electronics unit (REU) S The proximity switch electronic unit (PSEU) S The flight data acquisition unit (FDAU). Microphone audio and microphone discretes go to the VHF transceiver through the remote electronics unit. Receiver audio goes from the VHF transceiver to the flight interphone speakers and headsets through the remote electronics unit. The flight data acquisition unit receives transceiver key data to record the event. The VHF transceiver receives an air/ground discrete from the proximity switch electronic unit. The VHF transceivers use the discrete to calculate flight legs and for internal fault memory.

FOR TRAINING PURPOSES ONLY!

System Components Each VHF communication radio has these components: S VHF control panel S VHF transceiver S VHF antenna. The aircraft communication and reporting system (ACARS) uses one of the VHF transceivers to transmit data.

B737-- 600/700/800/900

FRA US/E GiM

Mai 10, 2006

ATA 23 Communication

Page 114

OSA MRO Support Pvt. Ltd

COMMUNICATION

One Stop Airline MRO Support Pvt. Ltd

ACTIVE V H F

TFR

COMM TEST

B737-- 600/700/800/900 23-- 00

STANDBY C O M M VHF ANTENNA GROUND

VHF CONTROL PANEL AIR

AAU SVR INT SVR INT FLT INT ONE 2

OBS

EXT ATT

F/O

HDPH FLT SVR

HDPH FLT SVR

ADJ DME 1 ADJ PA SENS PA GAIN PA ST AUDIO POT 1 AUDIO POT 2

MOD A[]

B[]

CAPT

PROXIMITY SWITCH ELECTRONICS UNIT

ATTENTION FOR HANDLING ELECTROSTATIC SENSITIVE DEVICES

C[]

D[]

FOR TRAINING PURPOSES ONLY!

1 -- VHF REMOTE ELEC RVTECH P/N BOEING P/N TSO C50C RTCA 00--16 B2AKXXXXFX

ONICS UNIT

AUDIO CONTROL PANEL

VHF TRANSCEIVER

FLIGHT DATA ACQUISITION UNIT

ENV CAT AAZ

FLIGHT INTERPHONE

SERIAL NO. DATE MFD WEIGHT 7.75 LBS

MICROPHONES HEADPHONES OXYGEN MASKS SPEAKERS

REMOTE ELECTRONICS UNIT

Figure 59 FRA US/E GiM

Mai 10, 2006

VHF - GENERAL DESCRIPTION ATA 23 Communication

Page 115

One Stop Airline MRO Support Pvt. Ltd

B737-- 600/700/800/900 23-- 00

ACARS - INTRODUCTION Purpose The aircraft communications addressing and reporting system (ACARS) is a datalink communication system. It lets you transmit messages and data between an airplane and an airline ground base. A message from the airplane to the airline ground base is called a downlink. A message from the airline ground base to the airplane is called an uplink. To reduce crew workload, ACARS sends reports when necessary and at scheduled times of the flight. These are typical ACARS reports: S Crew identification S Out, Off, On, In (000I) times S Engine performance S Flight status S Maintenance items.

FOR TRAINING PURPOSES ONLY!

OSA MRO Support Pvt. Ltd

COMMUNICATION

FRA US/E GiM

Mai 10, 2006

ATA 23 Communication

Page 116

OSA MRO Support Pvt. Ltd

COMMUNICATION

One Stop Airline MRO Support Pvt. Ltd

B737-- 600/700/800/900 23-- 00

DREAM-AIRLINE

ACARS DATA LINK CONTROL

AIRLINE OPERATIONS

FOR TRAINING PURPOSES ONLY!

ACARS DATA/ VOICE STATION

Figure 60 FRA US/E GiM

Mai 10, 2006

ACARS - INTRODUCTION ATA 23 Communication

Page 117

OSA MRO Support Pvt. Ltd FOR TRAINING PURPOSES ONLY!

COMMUNICATION

One Stop Airline MRO Support Pvt. Ltd

B737-- 600/700/800/900 23-- 00

ACARS - GENERAL DESCRIPTION General The ACARS is a voice and data communication system to manage flight plan data and maintenance data between the airplane and the airline. These are the components of the ACARS: S Control display unit (CDU) S ACARS program switch modules S Management unit (MU). You use the control display unit (CDU) to control the operation of the ACARS and display ACARS messages. The ACARS program switch modules contain dual inline package (DIP) switches. These switches identify the airplane. The ACARS MU receives the ground--to--air digital messages (uplink) and controls the transmission of the air--to--ground digital messages (downlink). ACARS connects to these components of other systems: S VHF transceiver to transmit to and receive data from the ground S Printer to print ACARS reports and messages S Proximity switch electronics unit which sends discrete signals for out, off, on and in (000I) S Remote electronics unit to distribute the chime and light annunciation for an incoming ACARS message. ACARS also connects to these systems to upload information from the airline operations or download information to the airline operations: S Flight management computers S Flight data acquisition unit S Data loader control panel. The ACARS MU is on the E3--3 shelf. The ACARS program switch modules are on the E3--3 shelf behind the ACARS MU.

FRA US/E GiM

Mai 10, 2006

ATA 23 Communication

Page 118

OSA MRO Support Pvt. Ltd

COMMUNICATION

B737-- 600/700/800/900

One Stop Airline MRO Support Pvt. Ltd

23-- 00 UPLINK/ DOWNLINK DATA

MK 2 CMU

VHF TRANSCEIVER

MU PASS HW FAIL LOAD SW XFER BUSY XFER COMP

CONTROL DISPLAY UNIT

XFER FAIL

CHIME

APM FAIL

REMOTE ELECTRONICS UNIT

PRINTER

AURAL WARNING MODULE

FOR TRAINING PURPOSES ONLY!

PROXIMITY SWITCH ELECTRONICS UNIT PROGRAM PINS

UPLOAD/ DOWNLOAD DATA

PROGRAM SWITCH MODULES

FLIGHT MANAGEMENT COMPUTER SYSTEM FLIGHT DATA ACQUISITION UNIT DATA LOADER CONTROL PANEL

ACARS MANAGEMENT UNIT

Figure 61 FRA US/E GiM

Mai 10, 2006

ACARS - DESCRIPTION

ATA 23 Communication

Page 119

OSA MRO Support Pvt. Ltd

COMMUNICATION

ACARS - OPERATION Purpose The flight management computer system control display unit (CDU) gives you an interface with the ACARS system. It lets you enter, send, and review downlink/uplink data. The CDU shows ACARS messages in the scratch pad. These are the ACARS messages: S ACARS UPLINK -- ACARS has received an uplink message S ACARS NO COMM -- no ACARS link available S ACARS VOICE -- ACARS VHF radio set to voice S ACARS CALL -- ground station requests voice--go--ahead S ACARS VOICE BUSY -- ACARS VHF radio voice circuits are busy S ACARS MU FAIL -- ACARS management unit failure S PRINTER UPLINK -- uplink message for printer S PRINTER FAIL -- ACARS reports printer failure S ACARS ALERT -- ACARS requires flight crew action. CAUTION:

FOR TRAINING PURPOSES ONLY!

One Stop Airline MRO Support Pvt. Ltd

THE ACARS IS A DATA-LINK SYSTEM, WHICH IS HIGHLY CUSTOMIZED THE MCDU-PAGES ON THE FOLLOWING PAGE MAY DIFFER FROM AIRLINE TO AIRLINE!! CHECK YOUR AIRLINE DEDICATED DOCUMENTS FOR DETAILS, SHOWN ON THIS PAGES11

B737-- 600/700/800/900 23-- 00

ACARS PREFLT MENU The ACARS PREFLT (preflight) menu shows when you push the ACARS LSK on the MENU page. You use this to get access to other ACARS pages. The flight crew uses these selections and the control indexes to transmit and receive information from ACARS: S PREFLIGHT -- to put preflight information into ACARS S FUEL INIT -- to put in starting airplane fuel S CREW REPORT -- to make refuel and ground service reports S ATC -- to send reports to air traffic control S TELEX -- to make, address, and send telexes to the ground station S MISC -- to find frequencies, check ACARS parameters and select the maintenance menu for test-puposes. S WEATHER REQUEST -- to get weather information S VOICE/DATA CONTROL -- to change the ACARS radio from voice to data or data to voice S VOICE CONTACT -- to tell operations, engineering, or maintenance to contact the airplane on a voice frequency S RECEIVED MESSAGES -- to view or to print received messages from ground stations. NOTE:

THERE ARE MULTIPLE ACARS MENUS AVAILABLE: ONLY TWO ARE SHOWN IN THE FOLLOWING DESCRIPTIONS.

MAIN MENU The menus on the CDU screen are airline specific. Push the line select key (LSK) next to ACARS to connect the CDU to ACARS. These pages are available for maintenance: S ACARS PREFLT MENU S ACARS MISC S ACARS MAINTENANCE. To exit from ACARS, push the CDU MENU key.

FRA US/E GiM

Mai 10, 2006

ATA 23 Communication

Page 120

OSA MRO Support Pvt. Ltd

COMMUNICATION

B737-- 600/700/800/900

One Stop Airline MRO Support Pvt. Ltd

23-- 00

MENU

ACARS PRE F L T MENU < FMC

< P R E F L I GH T < F UE L

WE A T H E R R E QU E S T >

I NI T

< C R E W R E P OR T < AT C < T EL EX

< MISC

OR

< ACARS < DFDAU

V OI C E / D A T A C O N T R OL > V OI C E C ON T A C T > RE C E I V E D ME S S A GE S >

SCRATCH PAD MENU

MESSAGE ANNUNCIATION

ACARS PREFLIGHT MENU # 1

M S G

OR ALTERNATE ACCESS TO PROMPT „MISC“

FOR TRAINING PURPOSES ONLY!

CONTROL DISPLAY UNIT LOG NR: ACARS TECHLOG DATE D-AHFI TAH TAC 13 APR 05

00112 : 51 / 00042

< FLIGHT LOG

ACTION >

PUSHBACK > REQUEST

TAXI >

< WX - REQUEST < TELEX / MSG

OIL REFILL > PAR UPDATE >

< REC MSG

MAIN SCREEN >

< SENT MSG

PREV LOG > INITIALIZE > PRE - FLT DATA >

ACARS PREFLIGHT MENU # 2

Figure 62 Mai 10, 2006

PDC / DCL >

< TECHLOG

ACARS TECHLOG FRA US/E GiM

1/3

REQUEST

REPORT >

WEEKLY ( ) P - CHECK ( ) C - CHECK ( )

< MISC

ACARS PREF L T MENU

ACARS - OPERATION – MCDU ATA 23 Communication

Page 121

One Stop Airline MRO Support Pvt. Ltd

B737-- 600/700/800/900 23-- 00

EMERGENCY LOCATOR TRANSMITTER - INTRO Purpose The emergency Locator transmitter (ELT) system automatically sends emergency signals when it senses a large change in the airplane’s velocity. The ELT sends homing signals to search and rescue crews on the VHF and UHF emergency channels. The ELT also sends emergency signals to satellite receivers. The satellite receivers send this information to ground stations to calculate the location of the distress signals.

FOR TRAINING PURPOSES ONLY!

OSA MRO Support Pvt. Ltd

COMMUNICATION

FRA US/E GiM

Mai 10, 2006

ATA 23 Communication

Page 122

OSA MRO Support Pvt. Ltd

COMMUNICATION

One Stop Airline MRO Support Pvt. Ltd

B737-- 600/700/800/900 23-- 00

HELP

FOR TRAINING PURPOSES ONLY!

HELP HELP HELP HELP HELP

HELP HELP

Figure 63 FRA US/E GiM

Mai 10, 2006

ELT - INTRODUCTION

ATA 23 Communication

Page 123

One Stop Airline MRO Support Pvt. Ltd

B737-- 600/700/800/900 23-- 00

ELT - GENERAL DESCRIPTION General The emergency locator transmitter (ELT) system has these components: S Control panel S Programming and position interface unit S Transmitter S Antenna. The control panel has a switch that you use to start the ELT manually. It also has a Iight to show you that the ELT is in operation. The ELT transmitter has two transmitter sections. One transmitter sends a swept tone on the VHF and UHF emergency channels (121 .5 and 243.0 MHz). The other transmitter sends digital data every 50 seconds on the 406 MHz channel. The antenna sends the 121.5/243.0 MHz and 406 MHz transmit signals. The antenna is a dual element antenna with two coax connectors. The 121 .5 MHz and 243.0 MHz ELT transmissions come in on the BNC series connector. The 406 MHz transmissions come in on the TNC series connector.

FOR TRAINING PURPOSES ONLY!

OSA MRO Support Pvt. Ltd

COMMUNICATION

FRA US/E GiM

Mai 10, 2006

ATA 23 Communication

Page 124

OSA MRO Support Pvt. Ltd

COMMUNICATION

B737-- 600/700/800/900

One Stop Airline MRO Support Pvt. Ltd

23-- 00

ELT TRANSMITTER ELT ANTENNA

FOR TRAINING PURPOSES ONLY!

ELT ARM

ELT 0N

ELT CONTROL PANEL

Figure 64 FRA US/E GiM

Mai 10, 2006

ELT - DESCRIPTION

ATA 23 Communication

Page 125

One Stop Airline MRO Support Pvt. Ltd

B737-- 600/700/800/900 23-- 00

HIGH FREQUENCY COMMUNICATION - INTRO General The high frequency (HF) communication system supplies voice communication over long distances. It gives communication between airplanes or between ground stations and airplanes. The HF system operates in the aeronautical frequency range of 2 MHz to 29.999 MHz. The system uses the earth’s surface and an ionized layer to cause a reflection (skip) of the communication signal. The distance between skips changes due to the time of day, radio frequency, and airplane altitude.

FOR TRAINING PURPOSES ONLY!

OSA MRO Support Pvt. Ltd

COMMUNICATION

FRA US/E GiM

Mai 10, 2006

ATA 23 Communication

Page 126

OSA MRO Support Pvt. Ltd

One Stop Airline MRO Support Pvt. Ltd

B737-- 600/700/800/900 23-- 00

FOR TRAINING PURPOSES ONLY!

COMMUNICATION

Figure 65 FRA US/E GiM

Mai 10, 2006

HF - INTRODUCTION

ATA 23 Communication

Page 127

OSA MRO Support Pvt. Ltd

COMMUNICATION

One Stop Airline MRO Support Pvt. Ltd

B737-- 600/700/800/900 23-- 00

HF - GENERAL DESCRIPTION General The HF communication system has these components: S HF control panel S HF transceiver S HF antenna coupler S HF antenna.

FOR TRAINING PURPOSES ONLY!

General Description The HF communication system interfaces with these components: S Audio control panel (ACP) S Remote electronics unit (REU) S Flight data acquisition unit. The REU receives HF radio selection and volume control from the ACP. The HF transceiver receives microphone (mic) audio from the REU. Receiver audio goes from the HF transceiver, through the REU, to the flight interphone speakers and headsets. The HF transceiver supplies the received audio to the SELCAL decoder. The SELCAL decoder monitors the audio for SELCAL calls that come from the airline ground operations. The HF transceiver supplies a key event to the flight data acquisition unit for key event marking.

FRA US/E GiM

Mai 10, 2006

ATA 23 Communication

Page 128

OSA MRO Support Pvt. Ltd

COMMUNICATION

ACTIVE V H F / H F

PANEL OFF

23-- 00

STANDBY C O M M

TEST VHF 1 VHF 2 VHF 3 HF 1

SEN

B737-- 600/700/800/900

One Stop Airline MRO Support Pvt. Ltd

AM

VHF

HF 2

RADIO COMMUNICATION PANEL HF ANTENNA

HF ANTENNA COUPLER COLLINS

FOR TRAINING PURPOSES ONLY!

AAU OBS F/O SVR INT EXT HDPH SVR INT ATT FLT FLT INT SVR ADJ ONE 2 DME 1 ADJ PA SENS PA GAIN PA ST AUDIO POT 1 AUDIO POT 2

MOD

A[]

B[]

REMOTE ELEC RVTECH P/N BOEING P/N TSO C50C RTCA 00--16 B2AKXXXXFX

LRU FAIL

CAPT HDPH FLT SVR

ATTENTION SENSITIVE DEVICES

C[]

FLIGHT DATA ACQUISITION UNIT

KEY INTERLOCK

GROUND AIR

D[]

HF

ONICS UNIT

CONTROL INPUT FAIL SQL/LAMP TEST

PROXIMITY SWITCH ELECTRONICS UNIT

PHONE

MIC

SELCAL DECODER

ENV CAT AAZ

AUDIO CONTROL PANEL SERIAL NO. DATE MFD WEIGHT 7.75 LBS

FLIGHT INTERPHONE

MICROPHONES HEADPHONES OXYGEN MASKS SPEAKERS

HF TRANSCEIVER

REU

Figure 66 FRA US/E GiM

Mai 10, 2006

HF - GEN. DESCRIPTION

ATA 23 Communication

Page 129

OSA MRO Support Pvt. Ltd

COMMUNICATION

One Stop Airline MRO Support Pvt. Ltd

B737-- 600/700/800/900 23-- 00

SELECTIVE CALLING SYSTEM - INTRODUCTION Purpose The selective calling (SELCAL) system supplies the flight crew with indications of calls that come in from the airline’s ground stations. It is not necessary for the pilots to continuously monitor company communications channels. Airline radio networks supply communication between ground stations and airplanes. For SELCAL operation, each airplane has a different four--letter code. Each letter in the code equals a different audio tone. The ground stations send the applicable tones to call an airplane.

FOR TRAINING PURPOSES ONLY!

Abbreviations and Acronyms ACP . . . . audio control panel comm . . . . . communication HF . . . . high frequency REU . . . . remote electronics unit SELCAL . . selective calling VHF . . . . very high frequency

FRA US/E GiM

Mai 10, 2006

ATA 23 Communication

Page 130

OSA MRO Support Pvt. Ltd

One Stop Airline MRO Support Pvt. Ltd

B737-- 600/700/800/900 23-- 00

FOR TRAINING PURPOSES ONLY!

COMMUNICATION

Figure 67 FRA US/E GiM

Mai 10, 2006

SELCAL - INTRODUCTION ATA 23 Communication

Page 131

OSA MRO Support Pvt. Ltd

COMMUNICATION

One Stop Airline MRO Support Pvt. Ltd

B737-- 600/700/800/900 23-- 00

SELCAL - GENERAL DESCRIPTION General Each airplane has a different SELCAL code. A ground station transmits this code to communicate with an airplane. when the airplane receives its SELCAL code, flight compartment indications come on to tell the flight crew. HF and VHF Transceivers The HF and VHF transceivers receive the SELCAL signal and send it to the SELCAL decoder. SELCAL Coding Switch A SELCAL coding switch gives the airplane its SELCAL code. It supplies the code to the SELCAL decoder. The SELCAL coding switch is behind the SELCAL decoder on the E-4 rack.

FOR TRAINING PURPOSES ONLY!

SELCAL Decoder Unit The SELCAL decoder unit monitors for audio tones. If the tones are the same as the code, the decoder sends a signal to the control panel. The decoder also sends a ground to the SELCAL aural warning relay. This relay gives power to the REU to send a signal to the aural warning unit. The SELCAL decoder is on the E-4 rack in the electronic equipment compartment. SELCAL Control Panel The SELCAL control panel receives the signals that come from the SELCAL decoder unit. The alert light comes on for the transceiver that receives the call. Push the alert light switch to reset the decoder channel. Remote Electronics Unit (REU) The REU sends a signal to the aural warning unit. The aural warning unit makes a high / low chime signal.

FRA US/E GiM

Mai 10, 2006

ATA 23 Communication

Page 132

OSA MRO Support Pvt. Ltd

COMMUNICATION

One Stop Airline MRO Support Pvt. Ltd

B737-- 600/700/800/900 23-- 00

SELCAL AURAL WARNING RELAY HF TRANSCEIVER

AURAL WARNING MODULE REMOTE ELECTRONICS UNIT

AUDIO TO REU

C

W

FOR TRAINING PURPOSES ONLY!

1--VHF

C

W

2–VHF

AUDIO CONTROL PANEL

VHF TRANSCEIVER

SELCAL DECODER UNIT

SELCAL PROGRAM SWITCH MODULE

Figure 68 FRA US/E GiM

Mai 10, 2006

SELCAL - GENERAL DESCR. ATA 23 Communication

Page 133

OSA MRO Support Pvt. Ltd

COMMUNICATION

One Stop Airline MRO Support Pvt. Ltd

VOICE RECORDER SYSTEM - INTRODUCTION General The voice recorder continuously records these: S Flight crew communications S Flight compartment sounds. The voice recorder keeps the last 120 minutes of audio.

VOICE RECORDER - GENERAL DESCRIPTION

FOR TRAINING PURPOSES ONLY!

General The voice recorder unit makes a continuous record of flight crew communication and flight compartment sounds. It erases the communication data automatically so that the memory stores only recent audio. The voice recorder unit keeps the last 120 minutes of communication data in memory. The voice recorder unit receives audio from the remote electronics unit (REU) and the area microphone. The area microphone is in the cockpit voice recorder panel.

B737-- 600/700/800/900 23-- 00

Description The pilot uses the voice recorder switch to control voice recorder power. the AUTO swirch position provides automatic control. In this position, the voice recorder receives power through the time delay relay. When an engine is at or above idle, an engine running relay energizes the time delay relay. The energized relay keeps voice recorder power on from engine start to engine shutdown. The time delay relay also keeps power for an additional five minutes after engine shutdown to let pilots complete postflight checks. The ON position lets you apply power to the voice recorder for maintenance or for preflight tests. In this position, the voice recorder switch latches while it supplies the power. It gives the power until an engine starts or until you put the switch back to AUTO. The switch automatically goes to AUTO when an engine is at or above idle.

Components The voice recorder system has these components: S Cockpit voice recorder panel S Voice recorder unit. S Voice recorder switch

FRA US/E GiM

Mai 10, 2006

ATA 23 Communication

Page 134

OSA MRO Support Pvt. Ltd

COMMUNICATION

B737-- 600/700/800/900

One Stop Airline MRO Support Pvt. Ltd

COCKPIT VOICE RECORDER MICROPHONE MONITOR

23-- 00

ERASE VOLTAGE

PARKING BRAKE SET AND GROUND SENSING RELAY

ERASE TEST

ERASE

UNDERWATER LOCATOR BEACON

TEST AUDIO

HEADPHONE

STATUS

TIME DELAY RELAY

COCKPIT VOICE RECORDER PANEL AUTO ENG 1 AND 2 RUN RELAYS ON VOICE RECORDER SWITCH

CLOCK

MICROPHONE AND HEADPHONE AUDIO (3) CAPTAIN MICROPHONE

FOR TRAINING PURPOSES ONLY!

VOICE RECORDER AUDIO

MOD A[]

FIRST OFFICER MICROPHONE

FIRST OBSERVER MICROPHONE

Figure 69 FRA US/E GiM

Mai 10, 2006

AAU OBS F/O CAPT SVR INT EXT HDPH HDPH SVR INT ATT FLT FLT FLT INT SVR SVR ONE 2 ADJ DME 1 ADJ PA SENS PA GAIN ATTENTION PA ST AUDIO POT 1 SENSITIVE AUDIO POT 2 DEVICES B[]

REMOTE ELEC RVTECH P/N BOEING P/N TSO C50C RTCA 00--16 B2AKXXXXFX

C[]

VOICE RECORDER UNIT

D[]

ONICS UNIT

ENV CAT AAZ

SERIAL NO. DATE MFD WEIGHT 7.75 LBS

REMOTE ELECTRONICSUNIT

VOICE RECORDER - DESCRIPTION ATA 23 Communication

Page 135

One Stop Airline MRO Support Pvt. Ltd

B737-- 600/700/800/900 23-- 00

PES / AUDIO - INTRODUCTION Introduction The passenger entertainment system -- audio (PES--audio) sends recorded entertainment audio and passenger address audio to each passenger seat. Each passenger can make a selection to hear one of many available audio channels.

FOR TRAINING PURPOSES ONLY!

OSA MRO Support Pvt. Ltd

COMMUNICATION

FRA US/E GiM

Mai 10, 2006

ATA 23 Communication

Page 136

OSA MRO Support Pvt. Ltd

One Stop Airline MRO Support Pvt. Ltd

B737-- 600/700/800/900 23-- 00

FOR TRAINING PURPOSES ONLY!

COMMUNICATION

Figure 70 FRA US/E GiM

Mai 10, 2006

PES-AUDIO - INTRODUCTION ATA 23 Communication

Page 137

OSA MRO Support Pvt. Ltd

COMMUNICATION

One Stop Airline MRO Support Pvt. Ltd

PES-- AUDIO / GENERAL DESCRIPTION General Audio signals from the audio entertainment player (AEP) and the passenger entertainment system--video (PES -- video) go through passenger entertainment system--audio (PES--audio) components to the passengers. Attendants use the forward attendant panel to control the PES--audio. Passengers use the passenger control units (PCUs) to make audio selections and control the volume.

FOR TRAINING PURPOSES ONLY!

Components These are the components of the PES--audio: -- Audio entertainment player (AEP) -- Audio multiplexer (AMUX) -- Seat electronics boxes (SEB) -- Passenger control units (PCU). There are two columns of seat electronics boxes. There is one seat electronics box for each seat group on the airplane. A seat group has one, two, or three seats. Each seat has one passenger control unit. These systems connect with the PES--audio: -- Passenger entertainment system--video (PES--video) -- Passenger address system (PAS).

B737-- 600/700/800/900 23-- 00

Audio Entertainment Signals The PES--audio gets audio inputs from these sources and sends them to each passenger seat: -- Entertainment audio from the audio entertainment player -- Video audio from the passenger entertainment system--video -- Announcements from the passenger address system. The audio multiplexer sends signals directly to the first seat electronics box in each column. The signals go through the seat electronics box to the next seat electronics box in the column. The seat electronics boxes send signals to the passenger control units in the seat group. Passenger Address Override The passenger address system stops the entertainment audio during an announcement. Passengers cannot change channels on the passenger control unit during a passenger address announcement.

Attendant Control Attendants use the forward attendant panel to control power to the audio entertainment player and the audio multiplexer. Passenger Control Passengers use the passenger control units to select audio programs. They hear entertainment audio from the audio entertainment player or the video tape reproducer.

FRA US/E GiM

Mai 10, 2006

ATA 23 Communication

Page 138

OSA MRO Support Pvt. Ltd

COMMUNICATION

B737-- 600/700/800/900

One Stop Airline MRO Support Pvt. Ltd

23-- 00

IFE

FORWARD ATTENDANT PANEL

PASSENGER CONTROL UNITS

PASSENGER CONTROL UNITS

OTHER SEBS

LEFT COLUMN

FOR TRAINING PURPOSES ONLY!

SEAT ELECTRONICS BOX

PASSENGER ADDRESS SYSTEM

SEAT ELECTRONICS BOX

AUDIO ENTERTAINMENT PLAYER TO PCUs

TO PCUs OTHER SEBS

RIGHT COLUMN PES--VIDEO

AUDIO MULTIPLEXER

Figure 71 FRA US/E GiM

Mai 10, 2006

SEAT ELECTRONICS BOX

SEAT ELECTRONICS BOX

PES / AUDIO - DESCRIPTION ATA 23 Communication

Page 139

One Stop Airline MRO Support Pvt. Ltd

B737-- 600/700/800/900 23-- 00

PES - VIDEO - INTRODUCTION General The passenger entertainment system -- video (PES--video) provides video programs for the passengers. The video programs have video and audio. The video goes to monitors throughout the cabin. The audio goes through the passenger entertainment system -- audio (PES--audio). Passengers receive this audio through headsets attached to the passenger service units in the seats. The audio can go through the passenger address system. Passengers receive this audio through speakers in the passenger service units.

FOR TRAINING PURPOSES ONLY!

OSA MRO Support Pvt. Ltd

COMMUNICATION

FRA US/E GiM

Mai 10, 2006

ATA 23 Communication

Page 140

OSA MRO Support Pvt. Ltd

COMMUNICATION

One Stop Airline MRO Support Pvt. Ltd

B737-- 600/700/800/900 23-- 00

LCD-SCREEN: EXTENDED (WHEN VIDEO OFF; DISPLAY IS STOWED IN THE HATRACK)

FOR TRAINING PURPOSES ONLY!

WALL MOUNTED VIDEO-MONITOR (OPTIONAL)

Figure 72 FRA US/E GiM

Mai 10, 2006

PES / VIDEO - INTRODUCTION ATA 23 Communication

Page 141

OSA MRO Support Pvt. Ltd FOR TRAINING PURPOSES ONLY!

COMMUNICATION

One Stop Airline MRO Support Pvt. Ltd

PES - VIDEO - GENERAL DESCRIPTION General The passenger entertainment system -- video (PES--video) provides video programs for the passengers. These are the major components of the PES--video: -- Video tape reproducer (VTR) -- Video system control unit (VSCU) -- Video distribution unit (VDU) -- Video monitor. The PES--video also provides data about the flight to the passengers. The DIU provides flight information to the passengers. Video Sources Video tapes provide programs for the passengers. You put the video tapes into the video tape reproducers (VTR). The VTRs send the video and audio signals to the video system control unit. The digital interface unit provides flight data for the passengers. The DIU sends video signals to the video system control unit. The digital interface unit receives signals from these systems: -- Air data inertial reference system -- flight management computer system. The DIU gets images from the random access video entertainment player. The DIU uses the images to create displays for the passengers. The digital interface unit is in the electronic equipment compartment on the E3--2 shelf. The video transformer is on the rack behind the digital interface unit.

FRA US/E GiM

Mai 10, 2006

B737-- 600/700/800/900 23-- 00

Control You use the video system control unit to control the operation of the PES--video. The video system control unit sends signals to the VTRs. These signals turn on the VTRs and control the video tape. A signal from the passenger oxygen system stops the video program when passenger oxygen masks deploy. A signal from the PSEU is used for flight leg switching in the video system. It shows the video system when the airplane is in air to start automatic passenger entertainment. Distribution The video system control unit sends control signals and three video signals to the video distribution units. The video system control unit tells each video distribution unit when to turn on the monitors and which video signal to send to the monitors. One video distribution unit controls two monitors. The video system control unit sends the audio from the video program to the passenger entertainment system -- audio (PES--audio). The PES--audio distributes the audio to the passenger control units in the passenger seats. Passengers connect headsets to the passenger control units and set the control for the video channel when they want to listen to the video program. When you want the audio to play on the speakers in the cabin, the video system control unit sends the audio to the passenger address system. The passenger address system distributes the audio to the speakers in the cabin. When a video program plays, the VSCU turns on the VIDEO ON light in the flight compartment ( P5 Overhead Panel ).

ATA 23 Communication

Page 142

OSA MRO Support Pvt. Ltd

COMMUNICATION

B737-- 600/700/800/900

One Stop Airline MRO Support Pvt. Ltd

VIDEO TAPE REPRODUCER(S)

23-- 00

VIDEO DISTRIBUTION UNITS

FLIGHT MANAGEMENT COMPUTER

VIDEO MONITORS

VIDEO ON W

P5 OVERHEAD PANEL

FOR TRAINING PURPOSES ONLY!

AIR DATA INERTIAL REFERENCE UNIT

DIGITAL INTERFACE UNIT PASSENGER OXYGEN SYSTEM

DATA LOADER CONTROL PANEL

AUDIO MULTIPLEXER

PROXIMITY SWITCH ELECTRONICS UNIT

Figure 73 FRA US/E GiM

Mai 10, 2006

VIDEO SYSTEM CONTROL UNIT

PASSENGER ADDRESS AMPLIFIER

PES / VIDEO - DESCRIPTION ATA 23 Communication

Page 143

OSA MRO Support Pvt. Ltd FOR TRAINING PURPOSES ONLY!

COMMUNICATION

One Stop Airline MRO Support Pvt. Ltd

B737-- 600/700/800/900 23-- 00

OPERATION OF THE VSCU Video System Control Unit Operation The master power switch lets you apply power to VSCU. The VSCU does a self--test when you first apply power. After a short delay, the system test PASS light comes on. You use the VSCU screen, the menu key, and the keypad keys to control music and message announcement playback. The menu key lets you see the main menu on the screen. You use the key pad up and down arrows to move the cursor up and down the menu list. The cursor shows as a reverse--highlighted video. You scroll through the menu selection to select the system function. The keypad SEL key lets you enter your selection. The menu screen and the SEL key let you select the passenger address function. EXAMPLE: When you select announcement, an announcement entry page shows. You enter the announcement number with the keypad numeric and enter keys. You can select announcements individually or in groups. The AUTO PROGRAM START and STOP keys let you start or stop the message announcements. The mode select key and the PA ON/OFF manual control switch lets you manually send video audio to the PA system. Automatic Messages The pre--recorded announcement and boarding music reproducer has a solid state stored message that comes on automatically. The announcement starts automatically when the airplane has a decompression.

FRA US/E GiM

Mai 10, 2006

ATA 23 Communication

Page 144

OSA MRO Support Pvt. Ltd

COMMUNICATION

B737-- 600/700/800/900

One Stop Airline MRO Support Pvt. Ltd

23-- 00

MASTER POWER SWITCH

START/STOP KEYS

MODE SELECT KEY

SYSTEM TEST LIGHTS

KEYPAD

ALL -- ZONE

MENU MODE SELECT

< SEL >

MASTER POWER PASS

VTR 1 PRI

AUTO MANUAL ALL ZONES

1 – PLAY VIDEO 2 – ANNOUNCEMENTS 3 – BG MUSIC

FAIL

AUTO PROGRAM

4 – AIRSHOW

SYSTEM TEST

PA VOL ( 0 – 77 )

ETI

OFF

START

FOR TRAINING PURPOSES ONLY!

2

3

4

5

6

7

8

9

STOP

0

PREVIEW SELECT MENU VTR AUX

1

CLEAR

PRI SEC

VTR AUX

ON/OFF

PRI SEC

ENTER

MANUAL CONTROL VTR CONTROL

ALL ZONES PWR

SEL

SEL

PA

SOURCE SELECT ON/OFF

SEL STOP REW PLAY

FF

SELECT

VSCU (VIDEO SYSTEM CONTROL UNIT) MENU KEY

Figure 74 FRA US/E GiM

Mai 10, 2006

PA ON/OFF MANUAL CONTROL

VSCU - OPERATION

ATA 23 Communication

Page 145

ATA 34

One Stop Airline MRO Support Pvt. Ltd

B737-- 600/700/800/900 34-- 00

NAVIGATION

STATIC AND TOTAL AIR PRESSURE SYSTEM General The purpose of the static and total air pressure system is to measure pilot and static air pressure. These pressures are used to calculate flight parameters such as airspeed and altitude.

FOR TRAINING PURPOSES ONLY!

OSA MRO Support Pvt. Ltd

NAVIGATION

FRA US/E GiM

Mai 10, 2006

ATA 34 Navigation

Page 146

One Stop Airline MRO Support Pvt. Ltd

B737-- 600/700/800/900 34-- 00

FOR TRAINING PURPOSES ONLY!

OSA MRO Support Pvt. Ltd

NAVIGATION

Figure 75 FRA US/E GiM

Mai 10, 2006

PITOT, STATIC INTRODUCTION ATA 34 Navigation

Page 147

OSA MRO Support Pvt. Ltd FOR TRAINING PURPOSES ONLY!

NAVIGATION

One Stop Airline MRO Support Pvt. Ltd

B737-- 600/700/800/900 34-- 00

AIR DATA - INERTIAL REFERENCE SYSTEM The static and total air pressure system gets air pressure inputs from three pitot probes and six static ports on the airplane fuselage. These are the two types of air pressure: S Static air pressure is the ambient air pressure around the airplane S Pitot air pressure is the air pressure on the pitot probe tube as a result of the forward motion of the airplane. The static and total air pressure system has these components: S 3 pitot probes S 6 static ports S 5 drain fittings. Flexible and hard pneumatic tubing are used to connect the pitot—static components. The system drains act as sumps to remove condensation in the pitot—static lines. General The air data inertial reference system (ADIRS) supplies these type of data to the aircrew and to the airplanesystems: S Altitude S Airspeed S Temperature S Heading S Attitude S Present position. The ADIRS has these components: S Air data modules (ADMs) (4) S Total air temperature (TAT) probe S Angle of attack (AOA) sensors (2) S Inertial system display unit (ISDU) S Mode select unit (MSU) S Air data inertial reference unit (ADIRU) (2) S IRS master caution unit.

FRA US/E GiM

Mai 10, 2006

ATA 34 Navigation

Page 148

OSA MRO Support Pvt. Ltd

NAVIGATION

B737-- 600/700/800/900

One Stop Airline MRO Support Pvt. Ltd

34-- 00

PITOT PRESSURE ADR DATA STATIC PRESSURE

AIR DATA MODULE (2) AIR DATA REFERENCE CDS

AIR DATA MODULE (2)

TOTAL AIR TEMPERATURE PROBE

FMCS IR DATA

FOR TRAINING PURPOSES ONLY!

INERTIAL REFERENCE ISDU

IRS MASTER CAUTION UNIT

GPS A

ALIGN

ANGLE OF ATTACK SENSOR (2)

FAULT

W A

ALIGN OFF

ON DC DC FAIL

ALIGN

A

FAULT

A

NAV ATT

L

IRS

Figure 76 Mai 10, 2006

A

ALIGN OFF

ON DC DC FAIL

LOCATED IN THE P61 (RH OF THE COCKPIT DOOR FRAME)

A A

NAV ATT

R

MSU

FRA US/E GiM

W

ADIRU (2) E5--2

ADIRS GENERAL DESCRIPTION ATA 34 Navigation

Page 149

One Stop Airline MRO Support Pvt. Ltd

B737-- 600/700/800/900 34-- 00

ADIRS - ALIGNMENT PROCEDURE 1

ADIRS - LAST PRESENT POSITION ENTRY ON CDU

General The ADIRU calculates these values during the alignment procedure: S Local vertical S True north S Present position latitude. The ADIRS alignment time will change between a minimum of 5 minutes at the equator to 17 minutes maximum at 78.25 degrees, north or south latitudes. The alignment time will not be more than 10 minutes if the present position latitude is between 60.0 degrees north or south. The alignment time is fixed at 10 minutes between latitudes of 60.0 and 70.2 degrees north or south. The alignment time is fixed at 17 minutes between latitudes of 70.2 and 78.25 degrees north or south. The ADIRU will not align at a latitude more than 78.25 north or south.

CDU Present Position Entry ADIRS present position can be set using the FMC CDU. Push the INIT/REF key on the CDU to show the position initialization (POS INIT) page. From this page, there are these three procedures that you can use to enter present position for the ADIRUs: S Transfer position data from LAST POS line S Transfer position data trom REF AIRPORT line S Enter position data using CDU keyboard. LAST POS Transfer Do this to transfer position data from the LAST POS line on the CDU to the ADIRUs: S Push line select key (LSK) 1R. The position data moves to the scratchpad S Push LSK 4R. Position data moves from scratchpad to the SET IRS POS boxes.

FOR TRAINING PURPOSES ONLY!

OSA MRO Support Pvt. Ltd

NAVIGATION

FRA US/E GiM

Mai 10, 2006

ATA 34 Navigation

Page 150

OSA MRO Support Pvt. Ltd

NAVIGATION

34-- 00

GPS P OS

RE -- -- -GA -- -- --

F -T E -- --

I NI T

N4 0 3 8 . 0 A I RP ORT

1 / 3 L A ST P OS W0 7 3 4 6 . 4

SET

I RS

GMT 1 4 3 -- -- -< I N

-2 -D

ALIGN OFF

P OS .

L

CLB

CRZ

DES

DIR INTC

LEGS

DEP ARR

HOLD

PROG

N1 LIMIT

FIX

PREV PAGE

NEXT PAGE

W F A I LA

ALIGN

NAV

OFF IRS

ATT

R

IRS- MODE SELECT UNIT (MSU) P OS I N I T

RTE

1

NAV

ATT

MON / D Y . 2 Z 1 1 / 2 9 -- -- -- -- -- -- -- -- -- -- -- -- -- -- -- -- -- -- -- -EX ROUT E >

INIT REF

ALIGN

ALIGN

2

.

FOR TRAINING PURPOSES ONLY!

B737-- 600/700/800/900

One Stop Airline MRO Support Pvt. Ltd

BRT EXEC

A

B

C

D

E

F

G

H

I

J

1

2

3

K

L

M

N

O

4

5

6

P

Q

R

S

T

7

8

9

U

V

W

X

Y

0

+/ --

Z

DEL

/

M S G W O F S TW

3

1/ 3 L A S T P OS W0 7 3 4 6 . 4

N4 0 3 8 . 0 R E F A I R P OR T -- -- -- -GA T E -- -- -- -- -S E T I R S P OS . . G MT -- MO N / D Y 1432. 2Z 11/ 29 -- -- -- -- -- -- -- -- -- -- -- -- -- -- -- -- -- -- -- -- -- -- -- -< I ND E X R OU T E > N 4 0 3 8 0 W0 7 3 4 6 4

4

P OS

I NI T

1/ 3 L A S T P OS W0 7 3 4 6 . 4

N4 0 3 8 . 0 R E F A I R P OR T -- -- -- -GA T E -- -- -- -- -S E T I R S P OS N 4 0 3 8 . 0 W0 7 3 4 6 . 4 G MT -- MO N / D Y 1432. 2Z 11/ 29 -- -- -- -- -- -- -- -- -- -- -- -- -- -- -- -- -- -- -- -- -- -- -- -< I NDE X R OU T E >

5

CLR

FMCS CDU Figure 77 FRA US/E GiM

Mai 10, 2006

IRS ALIGN - MCDU POS. ENTRY ATA 34 Navigation

Page 151

One Stop Airline MRO Support Pvt. Ltd

B737-- 600/700/800/900 34-- 00

CDS - PFD - OVERVIEW (AIR DATA - IRS DATA) General The primary flight display (PFD) shows these indications: S Airspeed S Attitude S Altitude S Heading S Vertical speed S Flight modes S Flight director commands S Landing indications S Radio altitude S Time critical annunciations.

FOR TRAINING PURPOSES ONLY!

OSA MRO Support Pvt. Ltd

NAVIGATION

FRA US/E GiM

Mai 10, 2006

ATA 34 Navigation

Page 152

OSA MRO Support Pvt. Ltd

NAVIGATION

B737-- 600/700/800/900

One Stop Airline MRO Support Pvt. Ltd

LNAV VOR/LOC

FMC SPD

138

34-- 00

VNAV PTH G/S

2 500 IBFI/130 DME 8.1

200

3 200

CMD 180

ATTITUDE

6

OM

3 000

(IRS) 160

3

AIRSPEED

14

2 1

10

(IRS/AIR DATA)

20

BARO ALTITUDE

2 800

(AIR DATA)

2

(AIR DATA)

VERTICAL SPEED

REF

1 120

2 600

2 6

100 FOR TRAINING PURPOSES ONLY!

1000

2 400 1011

186

Figure 78 FRA US/E GiM

Mai 10, 2006

H

HPA

MAG

PFD - OVERVIEW (IRS / AIR DATA) ATA 34 Navigation

Page 153

One Stop Airline MRO Support Pvt. Ltd

B737-- 600/700/800/900 34-- 00

INSTRUMENT LANDING SYSTEM (ILS) Purpose The multi mode receiver (MMR) contains these functions: S Instrument landing system (ILS) function S Global positioning system (GPS) function S Microwave landing system (MLS) function. The ILS function provides lateral and vertical position data neccessary to put the airplane on the runway for approach. The system uses signals from a glideslope ground station and a localizer ground station. The glideslope ground station transmits signals to give the airplane a descent path to the touchdown point on the runway. The localizer ground station transmits signals to give the airplane lateral guidance to the runway centerline.

FOR TRAINING PURPOSES ONLY!

OSA MRO Support Pvt. Ltd

NAVIGATION

FRA US/E GiM

Mai 10, 2006

ATA 34 Navigation

Page 154

One Stop Airline MRO Support Pvt. Ltd

B737-- 600/700/800/900 34-- 00

FOR TRAINING PURPOSES ONLY!

OSA MRO Support Pvt. Ltd

NAVIGATION

Figure 79 FRA US/E GiM

Mai 10, 2006

ILS INTRODUCTION

ATA 34 Navigation

Page 155

OSA MRO Support Pvt. Ltd

NAVIGATION

One Stop Airline MRO Support Pvt. Ltd

B737-- 600/700/800/900 34-- 00

ILS - GENERAL DESCRIPTION General The instrument landing system (ILS) has two multi mode receivers that contain the ILS functions. The ILS function in the MMRs use inputs from these antennas: S VOR/LOC antenna S Localizer antenna S Glideslope antenna. Description The receivers get manual tune inputs from the navigation (NAV) control panels. The VOR/LOC antenna and the localizer antenna send localizer signals to the ILS receivers. The glideslope antenna sends glideslope signals to the ILS receivers.

FOR TRAINING PURPOSES ONLY!

The ILS receivers send ILS deviation data to these LRUs: S DEUs S REU S GPWC S FCC S FDAU S FMC S Standby attitude indicator.

FRA US/E GiM

Mai 10, 2006

ATA 34 Navigation

Page 156

OSA MRO Support Pvt. Ltd

NAVIGATION

B737-- 600/700/800/900

One Stop Airline MRO Support Pvt. Ltd

34-- 00

NAVIGATION ACTIVE N A V

TFR

I08.I0

STANDBY

COLLINS

111.90

TEST

LRU STATUS

DEU (2)

VHF NAV SELECT SWITCH

CONTROL FAIL NAVIGATION CONTROL PANEL (2)

VHF NAV BOTH BOTH ON 2 ON 1 NORMAL

ANT FAIL

TO VOR/MB RECEIVER

REU DUAL VOR/LOC ANTENNA

GPWC

BOTH PILOTS SELECTED ILS-FREQ

TEST

FCC (2)

FOR TRAINING PURPOSES ONLY!

GLU--920

DUAL LOCALIZER ANTENNA

LOC ANT SWITCH (2)

FDAU

FMC

DUAL GLIDESLOPE ANTENNA

MULTI--MODE RECEIVER NOTE: OPTIONAL - ALLIED SIGNAL

Figure 80 FRA US/E GiM

Mai 10, 2006

STDBY ATT IND

GEN. DESCRIPTION

ATA 34 Navigation

Page 157

One Stop Airline MRO Support Pvt. Ltd

B737-- 600/700/800/900 34-- 00

CDS - PFD - OVERVIEW General The primary flight display (PFD) shows these indications: S Airspeed S Attitude S Altitude S Heading S Vertical speed S Flight modes S Flight director commands S Landing indications S Radio altitude S Time critical annunciations.

FOR TRAINING PURPOSES ONLY!

OSA MRO Support Pvt. Ltd

NAVIGATION

FRA US/E GiM

Mai 10, 2006

ATA 34 Navigation

Page 158

OSA MRO Support Pvt. Ltd

NAVIGATION

B737-- 600/700/800/900

One Stop Airline MRO Support Pvt. Ltd

LNAV VOR/LOC

FMC SPD

138

34-- 00

VNAV PTH G/S

2 500 IBFI/130 DME 8.1

200

3 200

CMD 180

6

OM

3 000 160

10

3

20

14

2 1

GLIDESLOPE DEVIATION SCALE AND POINTER

2 800

2 REF

1 120

2 600

6

100 FOR TRAINING PURPOSES ONLY!

2

1000

2 400 1011

186

H

HPA

MAG

LOCALIZER DEVIATION SCALE AND INDICATOR

Figure 81 FRA US/E GiM

Mai 10, 2006

PFD - OVERVIEW

ATA 34 Navigation

Page 159

One Stop Airline MRO Support Pvt. Ltd

B737-- 600/700/800/900 34-- 00

ND - CENTERED APPROACH Centered Approach To show the centered approach display, select the APP position on the EFIS control panel and push the CTR switch. If you do not tune an ILS frequency on the navigation control panel, the message EFIS MODE/NAV FREQ DISAGREE shows. The approach display shows localizer and glideslope deviation to the tuned ILS station.

FOR TRAINING PURPOSES ONLY!

OSA MRO Support Pvt. Ltd

NAVIGATION

FRA US/E GiM

Mai 10, 2006

ATA 34 Navigation

Page 160

OSA MRO Support Pvt. Ltd

NAVIGATION

B737-- 600/700/800/900

One Stop Airline MRO Support Pvt. Ltd

34-- 00

ILS SOURCE

GS313

TAS 305

ILS 1 110.10 CRS055 DME13.5

350 ‘/15 HDG

090

ILS FREQUENCY SELECTED COURSE

MAG VOR POINTER

SELECTED COURSE POINTER

GLIDESLOPE DEVIATION SCALE AND POINTER

LOC DEVIATION POINTER LOC

FOR TRAINING PURPOSES ONLY!

DEVIATION SCLALE

VOR POINTER VOR 2 ELN DME28.5

Figure 82 FRA US/E GiM

Mai 10, 2006

VOR 2 IDENTIFIER/ DME DISTANCE

ND - CENTERED APPROACH ATA 34 Navigation

Page 161

One Stop Airline MRO Support Pvt. Ltd

B737-- 600/700/800/900 34-- 00

VHF OMNIDIRECTIONAL RANGING (VOR) SYSTEM

VOR SYSTEM - GENERAL DESCRIPTION

Purpose The VHF omnidirectional ranging (VOR) system is a navigation aid that gives magnetic bearing data from a VOR ground station to the airplane. The VOR ground stations transmit signals that give magnetic radial information from 000 degrees to 359 degrees. All VOR stations reference the 000 degree to magnetic north.

General The VOR system has two VOR/marker beacon (VOR/MB) receivers. The receivers have VOR and marker beacon functions. This section covers only the VOR operation of the VOR/MB receivers. Description The navigation (NAV) control panels give manual tune inputs to the VOR/MB receivers. There are two NAV control panels, one for the captain and one for the first officer. RF signals from the VOR/ILS antenna go through power dividers, then to the VOR/MB receivers. The VOR/MB receivers use the RF signals to calculate station bearing and decode the morse code station identifier signal and process station audio. The receivers send VOR bearing data to the display electronic units (DEU) for display. The NAV select switch permits the crew to select the VOR/MB receiver l or the VOR/MB receiver 2 as the source for the captain’ s and first officer’s displays. The receivers send station audio and morse code station identifier signals to the remote electronic unit (REU).

FOR TRAINING PURPOSES ONLY!

OSA MRO Support Pvt. Ltd

NAVIGATION

FRA US/E GiM

Mai 10, 2006

ATA 34 Navigation

Page 162

OSA MRO Support Pvt. Ltd

NAVIGATION

B737-- 600/700/800/900

One Stop Airline MRO Support Pvt. Ltd

34-- 00

VOR STATION 1

VOR STATION 2

RMI ACTIVE N A V

TFR

STANDBY

NAVIGA VHF NAV BOTH ON 1

DEU (2)

BOTH ON 2 NORMAL DISPL

TEST

NAV SELECT SWITCH (P5)

FOR TRAINING PURPOSES ONLY!

NAVIGATION CONTROL PANEL (2) TO MMR

REU

FCC (2)

VOR/LOC ANTENNA

POWER DIVIDER (2)

Figure 83 FRA US/E GiM

Mai 10, 2006

VOR/MB RECEIVER (2)

FMCS

VOR GENERAL DESCRIPTION ATA 34 Navigation

Page 163

One Stop Airline MRO Support Pvt. Ltd

B737-- 600/700/800/900 34-- 00

ND - CENTERED VOR Centered VOR To show the centered VOR display, select the VOR position on the EFIS control panel and push the CTR switch. If you do not tune a VOR frequency on the navigation control panel, the message EFIS MODE/NAV FREQ DISAGREE shows. The VOR display shows VOR deviation from the selected course for the tuned VOR station and TO/FROM displays

FOR TRAINING PURPOSES ONLY!

OSA MRO Support Pvt. Ltd

NAVIGATION

FRA US/E GiM

Mai 10, 2006

ATA 34 Navigation

Page 164

OSA MRO Support Pvt. Ltd

NAVIGATION

B737-- 600/700/800/900

One Stop Airline MRO Support Pvt. Ltd

34-- 00 VOR SOURCE

VOR FREQUENCY/ IDENTIFIER GS315 TAS312 350‘/15

VOR 2

HDG

090

116.80 CRS055 DME28.5

SELECTED COURSE

MAG

VOR POINTERS

VOR COURSE DEVIATION SCALE AND INDICATOR

SELECTED COURSE POINTER

FOR TRAINING PURPOSES ONLY!

SELECTED COURSE POINTER

VOR POINTERS TO VOR 1 FREQUENCY/ DME DISTANCE

VOR 1 116.00 DME121

VOR 2 116.80 DME28.5

VOR 2 FREQUENCY/ DME DISTANCE

TO/FROM INDICATION/ ANNUNCIATION

Figure 84 FRA US/E GiM

Mai 10, 2006

ND - CENTERED VOR ATA 34 Navigation

Page 165

OSA MRO Support Pvt. Ltd

NAVIGATION

One Stop Airline MRO Support Pvt. Ltd

B737-- 600/700/800/900 34-- 00

MARKER BEACON SYSTEM - INTRODUCTION

MARKER SYSTEM - GENERAL DESCRIPTION

General The marker beacon system supplies visual and aural indications when the airplane flies over airport runway marker beacon transmitters.

General The marker beacon system has an antenna and a VOR/marker beacon (VOR/MB) receiver. The marker beacon function only operates in the VOR/MB receiver 1 position.

FOR TRAINING PURPOSES ONLY!

Operation The marker beacon antenna receives the marker beacon signals. The signals go to the VOR/MB receiver 1. The VOR/MB receiver 1 supplies this data: S Marker beacon audio to the remote electronics unit (REU) S Marker beacon data to the common display system (CDS) display electronics unit (DEU) S Marker beacon data to the flight data acquisition unit (FDAU). The displays show marker beacon data.

FRA US/E GiM

Mai 10, 2006

ATA 34 Navigation

Page 166

OSA MRO Support Pvt. Ltd

NAVIGATION

One Stop Airline MRO Support Pvt. Ltd

B737-- 600/700/800/900 34-- 00

DISPLAY ELECTRONICS UNIT (2)

FOR TRAINING PURPOSES ONLY!

FDAU

REMOTE ELECTRONICS UNIT MARKER BEACON ANTENNA

Figure 85 FRA US/E GiM

Mai 10, 2006

VOR/MB RECEIVER 1

MARKER GENERAL DESCRIPTION ATA 34 Navigation

Page 167

One Stop Airline MRO Support Pvt. Ltd

B737-- 600/700/800/900 34-- 00

PFD - OVERVIEW - MARKER BEACON INDICATIONS

FOR TRAINING PURPOSES ONLY!

OSA MRO Support Pvt. Ltd

NAVIGATION

FRA US/E GiM

Mai 10, 2006

ATA 34 Navigation

Page 168

OSA MRO Support Pvt. Ltd

NAVIGATION

B737-- 600/700/800/900

One Stop Airline MRO Support Pvt. Ltd

LNAV VOR/LOC

FMC SPD

138

VNAV PTH G/S

IBFI/130 DME 8.1

200

34-- 00

2 500 3 200

CMD 180

6

OM 3 000

160

10

3

20

14

2

2

MARKER BEACON INDICATION - OM - MM - AW

1

2 800

REF 1

120 2 600

2 6

100 FOR TRAINING PURPOSES ONLY!

1000 2 400 1011 186 H

MAG

Figure 86 FRA US/E GiM

Mai 10, 2006

HPA

PFD - OVERVIEW

ATA 34 Navigation

Page 169

OSA MRO Support Pvt. Ltd

NAVIGATION

One Stop Airline MRO Support Pvt. Ltd

B737-- 600/700/800/900 34-- 00

DISTANCE MEASURING EQUIPMENT

DME SYSTEM - GENERAL DESCRIPTION

Purpose The distance measuring equipment (DME) system supplies slant range (line of sight) distance measurement between the airplane and the ground station. The DME system supplies station audio and identifier signals to the interphone speakers and headsets.

General The DME system has two DME interrogators and two antennas. The DME interrogator transmits a signal to the DME ground stations. The ground stations send a reply signal back to the interrogator. The interrogator measures the time between the transmit signal and the reply signal and calculates the distance to the station.

FOR TRAINING PURPOSES ONLY!

These are the components in the flight compartment that have an interface with the DME system: S FMC source select switch S Left inboard and outboard display units S Left and right EFIS control panels S Right inboard and outboard display units S Captain’s and first officer’s NAV control panel S Captain’s and first officer’s audio control panel.

FRA US/E GiM

Mai 10, 2006

ATA 34 Navigation

Page 170

OSA MRO Support Pvt. Ltd

NAVIGATION

One Stop Airline MRO Support Pvt. Ltd

B737-- 600/700/800/900 34-- 00

DME DEU (2)

FMC

ACTIVE N A V

TFR

STANDBY

FCC (2) TEST

FOR TRAINING PURPOSES ONLY!

NAVIGATION CONTROL PANEL (2)

FDAU

ATC 1 ATC 2 TCAS COAX TEE

DME ANTENNA (2)

DME INTERROGATOR (2)

Figure 87 FRA US/E GiM

Mai 10, 2006

REU

DME GENERAL

ATA 34 Navigation

Page 171

One Stop Airline MRO Support Pvt. Ltd

B737-- 600/700/800/900 34-- 00

ND - CENTERED APPROACH - DME INDICATION

FOR TRAINING PURPOSES ONLY!

OSA MRO Support Pvt. Ltd

NAVIGATION

FRA US/E GiM

Mai 10, 2006

ATA 34 Navigation

Page 172

OSA MRO Support Pvt. Ltd

NAVIGATION

GS313 TAS 305 350 ‘/15

ILS 1

090

Figure 88 Mai 10, 2006

34-- 00

110.10 CRS 055 DME 13.5

DME 1 DISTANCE

VOR 2 ELN DME 28.5

DME 2 DISTANCE

MAG

FOR TRAINING PURPOSES ONLY!

HDG

FRA US/E GiM

B737-- 600/700/800/900

One Stop Airline MRO Support Pvt. Ltd

ND - CENTERED APPROACH ATA 34 Navigation

Page 173

One Stop Airline MRO Support Pvt. Ltd

B737-- 600/700/800/900 34-- 00

AUTOMATIC DIRECTION FINDER SYSTEM - INTRODUCTION

ADF SYSTEM - GENERAL DESCRIPTION

Purpose The automatic direction finder (ADF) system is a navigation aid. The ADF receiver uses AM signals from ground stations to calculate the bearing to the ADF station from the airplane longitudinal axis. The ADF system also receives standard AM radio broadcasts.‘

Description The ADF receiver calculates the bearing to the ADF ground stations and sends it to the DEUs for display. The ADF bearing also goes to the radio magnetic indicator (RMI). The ADF receiver processes audio from the ground stations and sends it to the remote electronics unit (REU).

FOR TRAINING PURPOSES ONLY!

OSA MRO Support Pvt. Ltd

NAVIGATION

FRA US/E GiM

Mai 10, 2006

ATA 34 Navigation

Page 174

OSA MRO Support Pvt. Ltd

NAVIGATION

One Stop Airline MRO Support Pvt. Ltd

B737-- 600/700/800/900 34-- 00

ADF

DEU (2)

TFR ADF ANT A D F

ADF ANT

ADF ANT

OFF ON

FOR TRAINING PURPOSES ONLY!

RMI TONE ADF CONTROL PANEL

ADF RECEIVER

ADF ANTENNA

Figure 89 FRA US/E GiM

Mai 10, 2006

REU

ADF GENERAL DESCRIPTION ATA 34 Navigation

Page 175

One Stop Airline MRO Support Pvt. Ltd

B737-- 600/700/800/900 34-- 00

RADIO ALTIMETER SYSTEM — INTRODUCTION

RA SYSTEM - GENERAL DESCRIPTION

General The radio altimeter (RA) system measures the vertical distance from the airplane to the ground. The radio altitude shows in the flight compartment. The system has a range of —20 to 2500 feet. The flight crew and other airplane systems use the altitude during low altitude flight, approach, and landing.

General The radio altimeter system has two receiver/transmitters. Each receiver/transmitter has a transmit and a receive antenna. The receiver/transmitters gets discrete inputs from the air ground relays. Radio altitude data goes on ARINC 429 data buses to these components: S Flight control computers (FCC) S Autothrottle computer S Ground proximity warning computer (GPWC) S Flight data acquisition unit (FDAU) S Traffic alert and collision avoidance system (TCAS) computer S Common display system (CDS) display electronic units (DEU).

FOR TRAINING PURPOSES ONLY!

OSA MRO Support Pvt. Ltd

NAVIGATION

FRA US/E GiM

Mai 10, 2006

ATA 34 Navigation

Page 176

OSA MRO Support Pvt. Ltd

NAVIGATION

B737-- 600/700/800/900

One Stop Airline MRO Support Pvt. Ltd

34-- 00

RA

RECEIVE ANTENNA

TRANSMIT ANTENNA

FCC (2)

AUTOTHROTTLE COMPUTER GPWC

FOR TRAINING PURPOSES ONLY!

TCAS COMPUTER

RA RECEIVER/ TRANSMITTER (2)

FDAU

DEU (2) PROXIMITY SWITCH ELECTRONICS UNIT

WEATHER RADAR

Figure 90 FRA US/E GiM

Mai 10, 2006

GEN. SCHEMATIC

ATA 34 Navigation

Page 177

One Stop Airline MRO Support Pvt. Ltd

B737-- 600/700/800/900 34-- 00

PFD - INDICATION - RADIO ALTITUDE

FOR TRAINING PURPOSES ONLY!

OSA MRO Support Pvt. Ltd

NAVIGATION

FRA US/E GiM

Mai 10, 2006

ATA 34 Navigation

Page 178

OSA MRO Support Pvt. Ltd

NAVIGATION

B737-- 600/700/800/900

One Stop Airline MRO Support Pvt. Ltd

LNAV VOR/LOC

FMC SPD

138

34-- 00

VNAV PTH G/S

2 500 IBFI/130 DME 8.1

200

3 200

CMD 180

6

OM

3 000 160

10

3

20

14

2 1

2 800

2 REF

1 120

2 600

-3

6

100 FOR TRAINING PURPOSES ONLY!

2

1000

2 400 1011

RADIO ALTITUDE

186

H

MAG

Figure 91 FRA US/E GiM

Mai 10, 2006

HPA

PFD - OVERVIEW

ATA 34 Navigation

Page 179

One Stop Airline MRO Support Pvt. Ltd

B737-- 600/700/800/900 34-- 00

AIR TRAFFIC CONTROL SYSTEM - INTRODUCTION General The air traffic control (ATC) ground stations interrogate the airborne ATC system. The ATC transponder replies to the interrogations in the form of coded information that the ground station uses. The ATC transponder also replies to mode S interrogations from the traffic alert and collision avoidance systems (TCAS) of other airplanes. When a ground station or a TCAS computer from another airplane interrogates the ATC system, the transponder transmits a pulse—coded reply signal. The reply signal identifies and shows the altitude of the airplane.

FOR TRAINING PURPOSES ONLY!

OSA MRO Support Pvt. Ltd

NAVIGATION

FRA US/E GiM

Mai 10, 2006

ATA 34 Navigation

Page 180

One Stop Airline MRO Support Pvt. Ltd

B737-- 600/700/800/900 34-- 00

FOR TRAINING PURPOSES ONLY!

OSA MRO Support Pvt. Ltd

NAVIGATION

Figure 92 FRA US/E GiM

Mai 10, 2006

ATC INTRODUCTION

ATA 34 Navigation

Page 181

One Stop Airline MRO Support Pvt. Ltd

B737-- 600/700/800/900 34-- 00

ATC SYSTEM - GENERAL DESCRIPTION General Description These are the components of the ATC system: S Top antenna S Bottom antenna S ATC coaxial switch (2) S ATC/TCAS control panel S ATC transponder (2). The two antennas transmit signals from the ATc transponder and send receive signals to the ATC transponder. The signals go through the ATC coax switches. The ATC/TCAS control panel sends identification and control data to the transponders. The ATC/TCAS control panel also controls the ATC coax switches. The air data inertial reference units (ADIRU) supply altitude data to the the ATC transponders. The ATC transponders have interface with the TCAS computer. The ATC transponders send and receives suppression pulses to prevent interference with DME and TCAS components.

FOR TRAINING PURPOSES ONLY!

OSA MRO Support Pvt. Ltd

NAVIGATION

FRA US/E GiM

Mai 10, 2006

ATA 34 Navigation

Page 182

OSA MRO Support Pvt. Ltd

NAVIGATION

B737-- 600/700/800/900

One Stop Airline MRO Support Pvt. Ltd

34-- 00

ATC TPR/ MODE S BENDIX/KING TPR

ANTENNA (TOP)

ALT DATA IN TOP BOT TCAS MAINTENANCE RESERVED RESERVED

ATC COAX SWITCH (TOP)

ADIRU (2)

TEST

TCAS COMPUTER

FOR TRAINING PURPOSES ONLY!

ANTENNA (BOTTOM)

ATC COAX SWITCH (BOTTOM)

ATC TRANSPONDER (2)

DME/ATC/TCAS SUPPRESSION COAX TEE

TA/RA TA

T OFF C A S

ABV

1

2

ATC 1

3

TST IDNT A

BLW

4

5

1 XPDR

7

0

T C

6

CLR

AUTO

2 STBY

ON

DME INTERROGATOR (2)

A FAULT

ATC/TCAS CONTROL PANEL

Figure 93 FRA US/E GiM

Mai 10, 2006

ATC GENERAL DESCRIPTION ATA 34 Navigation

Page 183

One Stop Airline MRO Support Pvt. Ltd

B737-- 600/700/800/900 34-- 00

TRAFFIC ALERT AND COLLISION AVOIDANCE SYSTEM (TCAS) General The traffic alert and collision avoidance system (TCAS) helps the flight crew and air traffic control maintain safe air traffic separation. TCAS is an airborne system. TCAS uses signals from an air traffic control radar beacon system (ATCRBS) transponder or an air traffic control (ATC) mode S transponder to track other airplanes. TCAS also communicates with other airplanes that have TCAS to agree on the flight movement to prevent a collision. TCAS supplies a traffic display and visual and aural vertical commands to the flight crew.

FOR TRAINING PURPOSES ONLY!

OSA MRO Support Pvt. Ltd

NAVIGATION

FRA US/E GiM

Mai 10, 2006

ATA 34 Navigation

Page 184

One Stop Airline MRO Support Pvt. Ltd

B737-- 600/700/800/900 34-- 00

FOR TRAINING PURPOSES ONLY!

OSA MRO Support Pvt. Ltd

NAVIGATION

Figure 94 FRA US/E GiM

Mai 10, 2006

TCAS INTRODUCTION ATA 34 Navigation

Page 185

OSA MRO Support Pvt. Ltd

NAVIGATION

One Stop Airline MRO Support Pvt. Ltd

B737-- 600/700/800/900 34-- 00

TCAS - GENERAL DESCRIPTION General The TCAS transmits to and receives signals from other airplanes to get altitude, range, and bearing data. TCAS uses this data and inputs from other onboard airplanes systems to calculate traffic avoidance data.

FOR TRAINING PURPOSES ONLY!

General Description These are the TCAS components: S TCAS directional antennas (2) S TCAS computer S ATC control panel. TCAS interfaces with these other system components: S ATC transponders (2) S Landing gear lever S Ground sensing relay S common display system (CDS) display electronic units (DEUs) (2) S Remote electronics unit (REU) S Radio altimeters (2) S Ground proximity warning computer (GPWC) S Left air data inertial reference unit (ADIRU) S Suppression coax tees. S Flight data acquisition unit (FDAU).

FRA US/E GiM

Mai 10, 2006

ATA 34 Navigation

Page 186

OSA MRO Support Pvt. Ltd

NAVIGATION

TOP ATC ANTENNA

TOP TCAS DIRECTIONAL ANTENNA

BOTTOM ATC ANTENNA

DEU (2)

ATC TRANSPONDER (2)

OFF

T C A S

1

2

3

4

5

6

ATC1

BLW

0

RADIO ALTIMETER (2)

TEST

CLR

A

AUTO STBY ON

GPWC

A T C

FAULT

L ADIRU

ATC/TCAS CONTROL PANEL FOR TRAINING PURPOSES ONLY!

TO COCKPIT SPKRS REMOTE ELECTRONICS UNIT

IDENT XPNDR1 2

7

34-- 00

TO DISPLAYS

BENDIX/KING

TA/RA TA ABV

B737-- 600/700/800/900

One Stop Airline MRO Support Pvt. Ltd

TCAS COMPUTER

LANDING GEAR LEVER

GROUND SENSING RELAY

FDAU BOTTOM TCAS DIRECTIONAL ANTENNA

Figure 95 FRA US/E GiM

Mai 10, 2006

SUPPRESSION COAX TEES

WEATHER RADAR

TCAS GERERAL DESCRIPTION ATA 34 Navigation

Page 187

One Stop Airline MRO Support Pvt. Ltd

B737-- 600/700/800/900 34-- 00

TCAS - NAVIGATION DISPLAY General The TCAS computer puts traffic into these four groups: S Other traffic shows as a white open diamond, and the altitude readout is white text S Proximate traffic shows as a solid white diamond, and the altitude readout is white text S Traffic advisory (TA) shows as a solid amber circle, and the altitude readout is amber text S Resolution advisory (RA) shows as a solid red square and the altitude readout is red text.

FOR TRAINING PURPOSES ONLY!

OSA MRO Support Pvt. Ltd

NAVIGATION

FRA US/E GiM

Mai 10, 2006

ATA 34 Navigation

Page 188

OSA MRO Support Pvt. Ltd

NAVIGATION

B737-- 600/700/800/900

One Stop Airline MRO Support Pvt. Ltd

GS 0 TAS -----------/------

HDG

131

MAG

34-- 00

VOR 1 115.10 CRS 131 DME -----OFFSCALE TRAFFIC (RED FOR RA AMBER FOR TA)

TRAFFIC ADVISORY (SOLID AMBER CIRCLE) --02

OFFSCALE TRAFFIC RA 5.3 +03 TA 12.7 --12

20

+14 --10

PROXIMATE TRAFFIC (WHITE SOLID)

NO--BEARING RA TRAFFIC (RED) NO--BEARING TA TRAFFIC (AMBER) OTHER TRAFFIC (WHITE)

--09 FOR TRAINING PURPOSES ONLY!

TA OR RA TRAFFIC (RED FOR RA AMBER FOR TA)

RESOLUTION ADVISORY (SOLID RED SQUARE)

TO VOR 2 114.20 DME ------

VOR 1 115.10 DME ------

NAVIGATION DISPLAY Figure 96 FRA US/E GiM

Mai 10, 2006

TCAS - NAVIGATION DISPLAY ATA 34 Navigation

Page 189

OSA MRO Support Pvt. Ltd

NAVIGATION

One Stop Airline MRO Support Pvt. Ltd

B737-- 600/700/800/900 34-- 00

TCAS - ATTITUDE INDICATOR DISPLAY General These are the two types of TCAS vertical resolution advisories that can show on the attitude indicator (AI): S TCAS RA-- down advisory S TCAS RA- up advisory. These symbols only show for an RA when: S The function selector on the ATC control panel is in the TA/RA position S The TCAS communicates with threat airplanes that give their altitude.

FOR TRAINING PURPOSES ONLY!

Description The red advisories show on the attitude display. They tell the flight crew to avoid some pitch movements. The flight crew uses the advisories to avoid a possible collision with threat airplanes.

FRA US/E GiM

Mai 10, 2006

ATA 34 Navigation

Page 190

OSA MRO Support Pvt. Ltd

NAVIGATION

B737-- 600/700/800/900

One Stop Airline MRO Support Pvt. Ltd

34-- 00

TCAS RA DOWN ADVISORY

1

1

TCAS RA UP ADVISORY FOR TRAINING PURPOSES ONLY!

2

2

ALTERNATE FLIGHT DIRECTOR DISPLAY

NOTE: THE AIRPLANE / FLIGHT DIRECTOR QUE-SYMBOL IS AN OPTION !

Figure 97 FRA US/E GiM

Mai 10, 2006

TCAS - ATTITUDE INDICATOR DISPLAY ATA 34 Navigation

Page 191

OSA MRO Support Pvt. Ltd

NAVIGATION

One Stop Airline MRO Support Pvt. Ltd

B737-- 600/700/800/900 34-- 00

WEATHER RADAR SYSTEM Purpose The weather radar (WXR) system supplies these visual indications: S Weather conditions S Land contours. Description The WXR system transmits radio frequency (RF) pulses in a 180 degree area forward of the airplane path. Rain or terrain contours reflect the pulses back to the airplane.

FOR TRAINING PURPOSES ONLY!

Display The WXR returns show in four different colors on the navigation displays (ND). Colors of the indications give the crew information about the intensity of the returns.

FRA US/E GiM

Mai 10, 2006

ATA 34 Navigation

Page 192

OSA MRO Support Pvt. Ltd

NAVIGATION

One Stop Airline MRO Support Pvt. Ltd

GS 305 TAS 319

HDG090 TRU

B737-- 600/700/800/900 34-- 00

VOR R 116.80 CRS 055 DME 13.5

40

FROM

FOR TRAINING PURPOSES ONLY!

WXR +5 VAR

Figure 98 FRA US/E GiM

Mai 10, 2006

WXR - GENERAL

ATA 34 Navigation

Page 193

OSA MRO Support Pvt. Ltd

NAVIGATION

One Stop Airline MRO Support Pvt. Ltd

WXR SYSTEM - GENERAL DESCRIPTION Control These components supply weather radar (WXR) system control: S Left and right EFIS control panels S Weather radar control panel. System Inputs These components supply signals to the WXR transceiver for predictive windshear: S Air data inertial reference system sends air data for the PWS function S Radio altimeters send altitude to enable or disable PWS during takeoff and approach S Autothrottle switch packs enable PWS during takeoff S Landing gear lever switch sends a landing gear down discrete to enable PWS during approach S An air/ground relay sends an air/ground discrete for flight leg counting.

FOR TRAINING PURPOSES ONLY!

System Outputs The weather radar transceiver sends these signals out for predictive windshear: S PWS video to the WXR/TERR relays S PWS warnings or cautions to the GPWS to prioritize any callouts S Audio inhibit to TCAS when there is a PWS warning S Audio to the REU for PWS.

FRA US/E GiM

Mai 10, 2006

B737-- 600/700/800/900 34-- 00

Display WXR data shows on the navigation displays (NDs). The weather data from the WXR receiver/transmitter (R/T) goes to the display electronics units (DEUs) for display. WXR data shows on the navigation displays (NDs). The weather data from the WXR receiver/transmitter (R/T) goes to the weather radar/terrain (WXR/TERR) relays. The ground proximity warning computer (GPWC) controls and switches the relays. If TERR is selected on the EFIS control panel or there is a Terrain Awareness/Terrain Clearance Floor warning from the GPWC, then the EGPWS terrain data shows on the navigation display (ND). If TERR is not selected and there are no EGPWS warnings, WXR data shows on the ND. Antenna The WXR antenna sends the RF pulses and receives the RF returns. The R/T gets air data inertial reference unit (ADIRU) pitch and roll data for antenna stabilization. Receiver/Transmitter (R/T) The primary component of the WXR system is the weather radar R/T. The WXR R/T does these functions: S Transmits RF pulses S Processes the RF returns S Detects windshear events and sends warnings and cautions to the flight crew S Supplies the WXR display data.

ATA 34 Navigation

Page 194

OSA MRO Support Pvt. Ltd

NAVIGATION

MINS

RADIO

FPV

BARO

MTRS

IN

BARO

34-- 00

HPA

STD

RST VOR MAPPLN VOR 1 APP OFF CTR

20 10 5

40 80 160 TFC

320

STA

WPT

ARPT

DATA

WXR ANTENNA

VOR 2 OFF

640

ADF 1 WXR

B737-- 600/700/800/900

One Stop Airline MRO Support Pvt. Ltd

WX RADAR

ADF 2

POS

AIR TRANSPORT AVIONICS BENDIX

TO DEU(S)

TERR

EFIS CP (2)

FOR TRAINING PURPOSES ONLY!

ADIRS RADIO ALTIMETERS AUTOTHROTTLE SWITCH PACKS LANDING GEAR LEVER SWITCH AIR/GROUND RELAY

SYSTEM CHECKER RTA--4B SWXX VERXX TEST MENU

WXR/TERR RELAYS

GPWS WX TEST

WX/TURB MAP

WX RADAR

TILT 5 10 GAIN

AUTO

TCAS

UP

15

0 DN

15

REU WEATHER RADAR RECEIVER/TRANSMITTER

MAX 5

10

WEATHER RADAR CONTROL PANEL

Figure 99 FRA US/E GiM

Mai 10, 2006

WXR - GENERAL DESCRIPTION ATA 34 Navigation

Page 195

OSA MRO Support Pvt. Ltd

NAVIGATION

One Stop Airline MRO Support Pvt. Ltd

B737-- 600/700/800/900 34-- 00

EGPWS INTRODUCTION Purpose The purpose of the ground proximity warning system (GPWS) is to alert the flight crew of an unsafe condition when near the terrain The GPWS also alerts the flight crew for to early descent on approach or to terrain threats ahead of the airplane. It also supplies a warning for windshear conditions and radio-altitude voice call-outs.

FOR TRAINING PURPOSES ONLY!

Description The GPWS uses aural messages, lights, and displays to give alerts and warnings in the flight compartment. GPWS Modes These are the GPWS modes: S Mode 1; Large descent rates S Mode 2; Too much of a closure rate when approaching terrain that is rising S Mode 3; Too much altitude loss during climbout (at takeoff or in go around) when the airplane is not in the landing configuration S Mode 4; Not enough terrain clearance S Mode 5; Too much deviation below the glideslope S Mode 6; Aural callouts when the airplane descends through radio altitudes and selected radio altitudes S Mode 7; Warning for windshear conditions. In addition to the GPWS modes 1 through 7, these two additional functions are used: Terrain clearance floor -- early descent on approach Terrain awareness -- display of terrain around the airplane.

FRA US/E GiM

Mai 10, 2006

ATA 34 Navigation

Page 196

OSA MRO Support Pvt. Ltd

NAVIGATION

B737-- 600/700/800/900

One Stop Airline MRO Support Pvt. Ltd

34-- 00

CAUTION TERRAINAHEAD WHOOP WHOOP PULL UP

GS 315 TAS 312 190/15

CHN 0134.5 Z 82.5 NM

HDG 131 MAG 12

15

9 18

TERRAIN WARNING: 100% RED CAUTION: 100% YELLOW

20

FOR TRAINING PURPOSES ONLY!

50% RED 50% YELLOW 25% YELLOW

+ 2000 FT

TERR

+ 1000 FT 0 FT

25% GRN 12.5% GRN BLACK

-- 2000 FT -- 2000 FT

E GPWS -- TERRAIN AWARENESS DISPLAYE

Figure 100 FRA US/E GiM

Mai 10, 2006

EGPWS INTRODUCTION ATA 34 Navigation

Page 197

One Stop Airline MRO Support Pvt. Ltd

B737-- 600/700/800/900 34-- 00

EGPWS GENERAL DESCRIPTION General Description The main component of the GPWS is the ground proximity warning computer (GPWC). It uses inputs from other systems to calculate unsafe conditions and gives the applicable alert or warning. Visual indications show on these: S Captain and first officer primary EFIS displays S Captain and first officer glideslope inhibit switch The system operates when the airplane is less than 2450 feet above the ground. The GPWS uses inputs from these units to calculate warning conditions: S Landing gear lever switch S Ground proximity warning (GPW) module S Radio altimeter (RA) S Flight management computer (FMC) S Air data inertial reference unit (ADIRU) S Stall management yaw damper (SMYD) S Multi mode receiver (MMR) S Weather radar (WXR) S Display Electronics Unit (DEU). Aural messages go to the Remote Electronics Unit (REU).

FOR TRAINING PURPOSES ONLY!

OSA MRO Support Pvt. Ltd

NAVIGATION

FRA US/E GiM

Mai 10, 2006

ATA 34 Navigation

Page 198

OSA MRO Support Pvt. Ltd

NAVIGATION

B737-- 600/700/800/900

One Stop Airline MRO Support Pvt. Ltd

34-- 00

GROUND PROXIMITY GPWS FLAP GEAR TERR INOP INHIBIT INHIBIT INHIBIT

SYS TEST

LAND GEAR LEVER SW MOD

NORMNORM NORM

GPWM

EN HAN C ED

EXTERNAL FAULT COMPUTER OK COMPUTER

FAIL

TERRAIN/WEATHER RELAY (2) TO DISPLAYS CDS DISPLAY ELECTRONICS UNIT (2)

RADIO ALTIMETER(2)

BELOW G/S P--INHIBIT A BELOW G/S LIGHT (2)

ADIRU (2) FDAU

OBS F/O CAPT AAU

FOR TRAINING PURPOSES ONLY!

SMYD (2) WEATHER RADAR PWR FMC ON VALID

MOD A B C D

MMR (2)

REU FMCS DFCS MCP

GROUND PROXIMITY WARNING COMPUTER

Figure 101 FRA US/E GiM

Mai 10, 2006

TCAS COMPUTER

EGPWS - GENERAL DESCRIPTION ATA 34 Navigation

Page 199

One Stop Airline MRO Support Pvt. Ltd

B737-- 600/700/800/900 34-- 00

GLOBAL POSITIONING SYSTEM (GPS)

GPS - GENERAL DESCRIPTION

Purpose The global positioning system (GPS) uses navigation satellites to supply airplane position to airplane systems and to the flight crew.

General The global positioning system (GPS) calcutates this data: S Latitude S Longitude S Altitude S Accurate time S Ground speed. There are two GPS systems. Antenna 1 receives satellite signals and sends them to multi mode receiver (MMR) 1. Antenna 2 connects to MMR 2. The MMRs calculate the airplane position and accurate time. This data goes to the flight management computer system (FMCS) and the IRS master caution unit. The FMCS uses GPS or navigation radio position with inertial reference data to calculate the airpiane position. The ADIRU sends position data to the MMRs. The IRS master caution unit gets GPS data from both MMRs. It causes the GPS fail light on the IRS mode select unit to come on when the two units have a failure.

FOR TRAINING PURPOSES ONLY!

OSA MRO Support Pvt. Ltd

NAVIGATION

FRA US/E GiM

Mai 10, 2006

ATA 34 Navigation

Page 200

OSA MRO Support Pvt. Ltd

NAVIGATION

One Stop Airline MRO Support Pvt. Ltd

B737-- 600/700/800/900 34-- 00

MMR

IRS MASTER CAUTION UNIT

Pres. Pos.

FLIGHT MANAGEMENT COMPUTER

LEFT ADIRU

FOR TRAINING PURPOSES ONLY!

ANTENNA POWER RECEIVE

GROUND PROXIMITY WARNING COMPUTER ANTENNA Pres. Pos.

MMR (2) RIGHT ADIRU

NOTE: THERE ARE VARIOUS MMRs AVAILABLE

CLOCK

Figure 102 FRA US/E GiM

Mai 10, 2006

GPS GENERAL DESCRIPTION ATA 34 Navigation

Page 201

OSA MRO Support Pvt. Ltd FOR TRAINING PURPOSES ONLY!

AUTOFLIGHT

ATA 22

One Stop Airline MRO Support Pvt. Ltd

22-- 00

AUTOFLIGHT

DIGITAL FLIGHT CONTROL SYSTEM - INTRODUCTION General The digital flight control system (DFCS) does these functions: S Autopilot S Flight director S Altitude alert S Speed trim S Mach trim. The DFCS has a mode control panel (MCP), two flight control computers (FCC), and actuator inputs to the flight control system. Each FCC can do all of the five functions. Autopilot The FCCs get inputs from several systems such as the air data inertial reference system (ADIRS) and the flight management computer (FMC) and sends commands to the aileron and elevator actuators. These actuators control the movement of the ailerons and elevators, which control the flight path of the airplane. There are two autopilots, autopilot A from FCC A and autopilot B from FCC B. When you engage an autopilot from the MCP, the autopilot controls the airplane attitude through these phases of flight: S Climb S Cruise S Descent S Approach S Go--around S Flare.

FRA US/T

B737-600/700/800/900

NeA

Oct 2001

Flight Director The FCCs get inputs from several systems and send flight director commands to the common display system (CDS) to provide guidance for the pilots. When the MCP flight director switches are on, the flight director display shows on the common display system (CDS). The flight crew can use the flight director commands to control the attitude of the airplane. The flight director commands do not show at flare. Altitude Alert As the airplane gets near or flies away from the MCP selected altitude, an alert occurs. This alert warns the pilots that they are getting near or leaving the MCP selected altitude. This warning occurs with or without the autopilots engaged or the flight directors on. Speed Trim When the engine thrust is high and the airspeed is low, the speed trim function keeps the speed set by the pilots with commands to the horizontal stabilizer. This function primarily occurs during takeoff and only operates when the autopilots are not engaged. The flight directors may be on or off. Mach Trim As the speed of the airplane increases, the nose starts to drop. This is called mach tuck. When the airplane airspeed is more than mach 0.615, the mach trim function gives an up elevator to keep the nose of the airplane level. This function operates with or without the autopilot engaged or the flight director on.

ATA 22 Autoflight

Page 202

OSA MRO Support Pvt. Ltd

AUTOFLIGHT

B737-600/700/800/900

One Stop Airline MRO Support Pvt. Ltd

22-- 00

CRUISE A/T

COURSE

IAS/MACH

V NAV

HEADING

L NAV

A/P ENGAGE CMD B CMD A

VERT SPEED

ALTITUDE

ARM

C/O MA

F/D

CLIMB

10

10

30

SPEED

LVL CHG

DN

VOR LOC

SPD INTV

OFF

N1

30

HDG SEL

APP

ALT HLD

CWS A

CWS B

ALT INTV

SEL

MA

DISENGAGE

V/S UP

OFF

COURSE

F/D

DESCENT

OFF

MODE CONTROL PANEL

AUTOFLIGHT SYSTEM MODE-ANNUNCIATION

FMC SPD

LNAV VOR/LOC

VNAV PTH G/S

AUTOFLIGHT SYSTEM STATUS

FLIGHT DIRECTOR BARS

FOR TRAINING PURPOSES ONLY!

CMD

GO--AROUND APPROACH

TAKEOFF

FLARE PRIMARY FLIGHT DISPLAY

Figure 103 FRA US/T

NeA

Oct 2001

DFCS - INTRODUCTION ATA 22 Autoflight

Page 203

One Stop Airline MRO Support Pvt. Ltd

DFCS - MCP DESCRIPTION Purpose The mode control panel (MCP) supplies the interface between the flight crew and the digital flight control system (DFCS). The MCP does these functions: S Engages the autopilot S Turns on the flight directors S Selects the operation mode S Arms the autothrottle S Controls parameter selection S Displays data.

B737-600/700/800/900 22-- 00

Physical Description The MCP weighs approximately 15 lbs. The MCP installs in the glareshield with four screws on the front of the panel. There are two screws on the bottom of the MCP that also attach to the glareshield. Three electrical receptacles on the rear of the MCP connect to the airplane wiring. Each mode selector switch on the MCP contains six light emitting diodes (LED). The switches and the LEDs are not line replaceable units (LRUs). There are six liquid crystal displays (LCDs). They show these selected parameter values: S Course 1 and 2 S IAS/MACH S Heading S Altitude S Vertical speed. Three lamps give backlight to the five position LCD display. Two lamps give backlight to the three position LCD display. These lamps and the LCDs are not LRUs. There are 52 incandescent lamps for the light plate. These lamps are also not LRUs.

FOR TRAINING PURPOSES ONLY!

OSA MRO Support Pvt. Ltd

AUTOFLIGHT

FRA US/T

NeA

Oct 2001

ATA 22 Autoflight

Page 204

OSA MRO Support Pvt. Ltd

AUTOFLIGHT

B737-600/700/800/900

One Stop Airline MRO Support Pvt. Ltd

22-- 00

SELECTED PARAMETER LCD (TYP)

A/T ARM

COURSE

IAS/MACH

V NAV

C/O MA F/D

30

SPEED

LVL CHG

ALTITUDE

VERT SPEED

10 VOR LOC

SPD INTV

OFF N1

L NAV

HEADING

ALT INTV

SEL 10

30 HDG SEL

APP

ALT HLD

DN

A/P ENGAGE CMD B CMD A

CWS A

CWS B MA

DISENGAGE

V/S UP

OFF

COURSE

F/D

OFF

FOR TRAINING PURPOSES ONLY!

MCP

MODE SELECTOR SWITCH (TYP)

Figure 104 FRA US/T

NeA

Oct 2001

DFCS MCP - GENERAL DESCRIPTION ATA 22 Autoflight

Page 205

OSA MRO Support Pvt. Ltd FOR TRAINING PURPOSES ONLY!

AUTOFLIGHT

One Stop Airline MRO Support Pvt. Ltd

DFCS - GENERAL DESCRIPTION Mode Control Panel The crew uses the MCP to do these functions: S Engage the autopilots S Turn on the flight directors S Select the mode of operation S Select course and heading S Select target speeds and altitude. Other crew inputs to the FCCs are from these components: S Autopilot (A/P) disengage switches S Takeoff/Go--around (TO/GA) switches S Control wheel steering (CWS) force transducers S Autoflight status annunciators (ASAs). S FCC A and B The FCCs use data from the MCP, sensors, and these systems to calculate the autopilot and flight director commands: S Radio navigation systems S Air data inertial reference system (ADIRS) S Flight management computer system (FMCS) S Autothrottle (A/T) system S Control surface position sensors S Autopilot actuator position sensors. The FCCs also use the data to calculate these commands and alerts: S Speed trim commands S Mach trim commands S Altitude alerts S Autopilot disengage warnings.

FRA US/T

NeA

Oct 2001

B737-600/700/800/900 22-- 00

Autopilot Commands The autopilot can be in the command (CMD) or the control wheel steering (CWS) mode. In the CMD mode, the FCC calculates the commands which go to the autopilot actuators. The actuators cause the inputs to the power control units (PCU) to move which control the ailerons and elevator. In the CWS mode, force transducers under the control columns sense control wheel and control column forces from the pilots and send these signals to the FCC. The FCC sends the commands to the autopilot actuators to control the ailerons and elevator. The FCC also sends commands to the stabilizer trim electric actuator to trim the stabilizer. The autopilot mode shows on the common display system (CDS) above the attitude indicator. To disengage the autopilot, the pilot pushes the disengage switches on the control wheel. When the autopilot disengages, an aural warning is heard from the aural warning module and the red A/P light on the autoflight status annunciator (ASA) flashes. The ASA warning and aural alert can be reset if the pilot pushes the red A/P annunciator on the ASA or pushes the A/P disconnect switch. Flight Director Commands When the flight directors are on, the FCC calculates the guidance commands that show on the CDS. There is no movement of the control surfaces and no alert if the flight directors are turned off. When you set the flight director mode on the MCP, the mode and its status also show on the CDS display.

ATA 22 Autoflight

Page 206

OSA MRO Support Pvt. Ltd

AUTOFLIGHT

B737-600/700/800/900

One Stop Airline MRO Support Pvt. Ltd A/T

COURSE

IAS/MACH

V NAV

HEADING

L NAV

ALTITUDE

A/P ENGAGE

VERT SPEED

ARM

DN

VOR LOC

F/D

SPD INTV

SPEED

LVL CHG

CWS A

CWS B

ALT INTV

SEL

10 N1

CMD B

COURSE

10

30

C/O

OFF

MA

CMD A

22-- 00

30

HDG SEL

APP

ALT HLD

MA

DISENGAGE

V/S UP

OFF

F/D

OFF

MODE CONTROL PANEL

AUTOTHROTTLE FMCS ADIRU NAV SENSORS POSITION SENSORS SWITCHES

REU

CONTROL COLUMN AND CWS FORCE TRANSDUCERS

AUTOPILOT AILERON AND ELEVATOR ACTUATORS

FOR TRAINING PURPOSES ONLY!

AUTOFLIGHT STATUS ANNUNCIATOR (2)

FCC (2)

STAB TRIM ELECTRIC ACTUATOR CMD

MACH TRIM ACTUATOR

AURAL WARNING MODULE

COMMON DISPLAY SYSTEM

Figure 105 FRA US/T

NeA

Oct 2001

DFCS - GENERAL DESCRIPRION ATA 22 Autoflight

Page 207

OSA MRO Support Pvt. Ltd

AUTOFLIGHT

One Stop Airline MRO Support Pvt. Ltd

B737-600/700/800/900 22-- 00

Altitude Alert The altitude alert function uses the altitude that is set on the MCP. The FCCs tells the flight crew when the airplane approaches or departs the set altitude. The autopilot or flight directors do not have to be on for this alert to operate. There is an aural indication from the remote electronic unit (REU) and a visual indication on the CDS displays.

FOR TRAINING PURPOSES ONLY!

Speed Trim The FCCs send speed trim signals to the stabilizer trim primary electric actuator to control the horizontal stabilizer movements. This control increases the airplane stability at low air speeds. As the airplane speed slows, the stabilizer is moved to a more nose down position to increase the speed. As the speed increases, the stabilizer is moved to a more nose up position to decrease the speed. This function only operates if the autopilot is not engaged. Mach Trim The FCCs send mach trim signals to a mach trim actuator to control the elevator movements. As the mach trim actuator output shaft moves, it turns the feel and centering unit which moves the input to the elevator PCUs. This moves the elevator. The mach trim signal keeps the nose up at high air speeds. The mach trim actuator also causes the elevator to be in a more nose down position during takeoff which allows the pilots to move the stabilizer to a more nose up position. This allows a more nose up attitude if there is an engine failure during takeoff and is called the FCC controlled neutral shift enable (FCNSE) region. Built--In--Test--Equipment (BITE) The DFCS has interfaces with the FMCS to show the BITE condition on the control display units (CDU). The BITE function helps to find failures.

FRA US/T

NeA

Oct 2001

ATA 22 Autoflight

Page 208

OSA MRO Support Pvt. Ltd

AUTOFLIGHT

B737-600/700/800/900

One Stop Airline MRO Support Pvt. Ltd A/T

COURSE

IAS/MACH

V NAV

HEADING

L NAV

ALTITUDE

A/P ENGAGE

VERT SPEED

ARM

DN

VOR LOC

F/D

SPD INTV

SPEED

LVL CHG

CWS A

CWS B

ALT INTV

SEL

10 N1

CMD B

COURSE

10

30

C/O

OFF

MA

CMD A

22-- 00

30

HDG SEL

APP

ALT HLD

MA

DISENGAGE

V/S UP

OFF

F/D

OFF

MODE CONTROL PANEL

AUTOTHROTTLE FMCS ADIRU NAV SENSORS POSITION SENSORS SWITCHES

REU

CONTROL COLUMN AND CWS FORCE TRANSDUCERS

AUTOPILOT AILERON AND ELEVATOR ACTUATORS

FOR TRAINING PURPOSES ONLY!

AUTOFLIGHT STATUS ANNUNCIATOR (2)

FCC (2)

STAB TRIM ELECTRIC ACTUATOR CMD

MACH TRIM ACTUATOR

AURAL WARNING MODULE

COMMON DISPLAY SYSTEM

Figure 106 FRA US/T

NeA

Oct 2001

DFCS - GENERAL DESCRIPRION ATA 22 Autoflight

Page 209

One Stop Airline MRO Support Pvt. Ltd

B737-600/700/800/900 22-- 00

AUTOTHROTTLE SYSTEM - INTODUCTION General The autothrottle (A/T) system is part of the flight management system (FMS). The A/T system controls engine thrust in response to mode requests from these components: S Mode control panel (MCP) S Flight deck switches. The A/T system operates from takeoff to touchdown. The pilot uses the digital flight control system (DFCS) and the A/T system to automatically fly the airplane.

FOR TRAINING PURPOSES ONLY!

OSA MRO Support Pvt. Ltd

AUTOFLIGHT

FRA US/T

NeA

Oct 2001

ATA 22 Autoflight

Page 210

One Stop Airline MRO Support Pvt. Ltd

B737-600/700/800/900 22-- 00

FOR TRAINING PURPOSES ONLY!

OSA MRO Support Pvt. Ltd

AUTOFLIGHT

Figure 107 FRA US/T

NeA

Oct 2001

AT INTRODUCTION

ATA 22 Autoflight

Page 211

One Stop Airline MRO Support Pvt. Ltd

B737-600/700/800/900 22-- 00

A/T SYSTEM - OPERATION, OVERVIEW General The A/T operates on the ground for takeoff and in flight. The A/T system controls engine thrust for these flight sequences: S Takeoff S Climb S Cruise S Descent S Approach S Flare S Go—around. For each flight phase, the DFCS selects the A/T mode. The MCP mode selector switch light comes on to show the active mode. The pilot uses the TO/GA switches to start the takeoff and go—around modes.

FOR TRAINING PURPOSES ONLY!

OSA MRO Support Pvt. Ltd

AUTOFLIGHT

FRA US/T

NeA

Oct 2001

ATA 22 Autoflight

Page 212

One Stop Airline MRO Support Pvt. Ltd

B737-600/700/800/900 22-- 00

FOR TRAINING PURPOSES ONLY!

OSA MRO Support Pvt. Ltd

AUTOFLIGHT

Figure 108 FRA US/T

NeA

Oct 2001

AT OPERATION OVERVIEW ATA 22 Autoflight

Page 213

OSA MRO Support Pvt. Ltd

STRUCTURE

ATA 51--57

One Stop Airline MRO Support Pvt. Ltd

B737-- 600/700/800/900 51-- 57

STRUCTURE

BASIC STRUCTURAL DESCRIPTION The B737 is a low wing twin engine airplane. The engines are below the wings on Struts. It has full cantilever wings and tail surfaces. The fuselage is a semi--monocoque design. High--fatigue Design Life The design service objective for the B737 is 75,000 flight cycles. For typical operations the aircraft reaches this objective after 25 years of Service.

FOR TRAINING PURPOSES ONLY!

Corrosion Prevention Years of extensive in--service experience lead to an optimum airframe design. This knowledge along with new material technology gives the operator an airframe that results in: S Minimal corrosion S Longer in service periods S Less maintenance costs. Composite Material Some airplane structure and parts are composite materials. These are some advantages of composite materials: S High strength S Corrosion resistant S Increased fatigue life S Light weight.

FRA US/E GiM

Mai 10, 2006

Structure

Page 214

OSA MRO Support Pvt. Ltd

STRUCTURE

B737-- 600/700/800/900

One Stop Airline MRO Support Pvt. Ltd

51-- 57

INBOARD & OUTBOARD UPPER COVE SKIN PANELS (FIBERGLASS) TRAILING EDGE PANELS (FIBERGLASS/GRAPHITE)

FOR TRAINING PURPOSES ONLY!

FLAP SUPPORT FAIRINGS (FIBERGLASS/GRAPHITE)

GRAPHITE FIBERGLASS

INBOARD FIXED LEADING EDGE LOWER SKIN PANEL (FIBERGLASS)

OUTBOARD FIXED LEADING EDGE UPPER & LOWER SKIN PANELS (FIBERGLASS)

NOSE LANDING GEAR DOORS (GRAPHITE)

FIBERGLASS/GRAPHITE

Figure 109 FRA US/E GiM

Mai 10, 2006

Composite Materials Structure

Page 215

OSA MRO Support Pvt. Ltd

STRUCTURE

ATA 52

One Stop Airline MRO Support Pvt. Ltd

51-- 57

DOORS

DOOR LOCATION Purpose The doors are removable units that give access to the airplane compartments. General Description These are the types of doors on the airplane: S Forward and aft entry doors S Forward and aft galley service doors S Emergency exit hatches (and pilots’ sliding windows) S Cargo doors A door warning system shows the crew that pressure bearing doors are closed and properly latched before flight. All doors have silicon rubber seals. The seals do these things: S Seal air and light leaks S Act as acoustic and thermal barriers S Supply aerodynamic smoothness.

FOR TRAINING PURPOSES ONLY!

B737-- 600/700/800/900

Training Information Point You can open and close entry, galley service, and cargo doors in winds up to 40 knots without structural damage. You can let these doors stay latched open in winds up to 65 knots without structural damage. If a door is left open for a long time, a protective cover should be put over the door frame. This prevents bad weather damage to the airplane.

Location S The entry doors are on the left side of the airplane. S The galley service doors are on the right side of the airplane. S The emergency exit hatches are above the wings on both sides of the airplane. S The crew door and lavatory doors are inside the ai rplane. S The cargo doors are on the right side of the airplane. S The miscellaneous access doors are near the systems they serve.

FRA US/E GiM

Mai 10, 2006

Structure

Page 216

OSA MRO Support Pvt. Ltd

STRUCTURE

B737-- 600/700/800/900

One Stop Airline MRO Support Pvt. Ltd

51-- 57

AFT GALLEY SERVICE DOOR AFT CARGO COMPARTMENT DOOR (R/H SIDE)

AFT ENTRY DOOR

EMERGENCY EXIT DOORS

FOR TRAINING PURPOSES ONLY!

FWD CARGO COMPARTMENT DOOR (R/H SIDE) FORWARD GALLEY SERVICE DOOR

ELEC EQUIP COMP ACCESS DOOR

FORWARD ENTRY DOOR LOWER NOSE COMP ACCESS DOOR

Figure 110 FRA US/E GiM

Mai 10, 2006

Introduction

Structure

Page 217

OSA MRO Support Pvt. Ltd

STRUCTURE

ATA 25

One Stop Airline MRO Support Pvt. Ltd

51-- 57

EQUIPMENT AND FURNISHINGS

DOOR MOUNTED ESCAPE SLIDES Purpose The escape slides provide a means of emergency egress from the airplane. The slides can also be separated from the airplane and used as flotation devices. Location An escape slide is mounted on each entry and service door. Physical Description/Features Each escape slide assembly consists of an escape slide package, an escape slide compartment, and two floor brackets. The escape slide package is stowed in the escape slide compartment which is fastened to the lower inboard face of each entry and service door. The floor brackets are located at the forward and aft ends of the doorways, inboard of the door sill. The escape slide package consists of an escape slide, a detachable girt, girt bar, gas cylinder, and valise. The gas cylinder contains high pressure gas for inflating the slide. The valise holds the slide in the stowed position, and opens to deploy the slide.

FOR TRAINING PURPOSES ONLY!

B737-- 600/700/800/900

Maintenance Practices To ensure that the slide is ready for use, check the pressure gage reading at regular intervals as required by each airline’s operating procedures. The temperature compensating pressure gage needle should be within, or not more than one needle width above, the green band. Although the slide will be usable following inflation with the bottle pressure at the minimum safe level, it is recommended that the pressure should be no less than 3000 psig (at 21_C, 70_F) for initial installation of the slide on the airplane, and that the bottle be recharged before the pressure drops below the minimum safe level.

Operation For automatic escape slide deployment, the slide must be placed in the operation readiness mode by securing the girt bar in the floor brackets. When the door is opened, tension on the girt and latch cable will cause the cover latch to separate, allowing the escape slide compartment to open and the slide to deploy. Inflation by the gas cylinder and aspirator is triggered by tension on the inflation cable secured to the girt bar and the gas cylinder discharge valve. One end of a detachable fabric girt is attached to the slide with the opposite end attached to the girt bar. Removing the parachute--type pin causes the slide to separate from the airplane. The slide can be used as a flotation device.

FRA US/E GiM

Mai 10, 2006

Structure

Page 218

OSA MRO Support Pvt. Ltd

STRUCTURE

B737-- 600/700/800/900

One Stop Airline MRO Support Pvt. Ltd

51-- 57 GAGE NEEDLE GREEN BAND (GO) RED BAND (NO GO)

PRESSURE GAGE

DOOR STOWAGE HOOKS

FLOOR BRACKET (2 LOCATIONS)

GIRT BAR

OPEN DOOR

SLIDE LATCH SLIDE COVER

LATCH CABLE

FOR TRAINING PURPOSES ONLY!

LATCH CLOSED

FULL INFLATED SLIDE READY FOR USE

DETACHABLE GIRT DETAILS

Figure 111 FRA US/E GiM

Mai 10, 2006

Door Mounted Escape Slide Structure

Page 219

OSA MRO Support Pvt. Ltd

STRUCTURE

One Stop Airline MRO Support Pvt. Ltd

B737-- 600/700/800/900 51-- 57

INTRODUCTION Purpose Equipment and furnishings provide for the comfort and convenience of passengers and crew members, for handling and stowing cargo, and for ensuring passenger and crew safety in an emergency.

FOR TRAINING PURPOSES ONLY!

General Component Locations Equipment and furnishings are located in the flight compartment and the passenger compartment. Cargo nets are around the door opening in each cargo compartment to prevent cargo from blocking the doors. Emergency equipment is throughout the airplane including slides on each door and escape straps.

FRA US/E GiM

Mai 10, 2006

Structure

Page 220

OSA MRO Support Pvt. Ltd

STRUCTURE

One Stop Airline MRO Support Pvt. Ltd

B737-- 600/700/800/900 51-- 57

AFT RIGHT LAVATORY

GALLEY

FWD LAVATORY

AFT LEFT LAVATORY

CLASS DIVIDER

GALLEY

FOR TRAINING PURPOSES ONLY!

STOWAGE UNIT

Figure 112 FRA US/E GiM

Mai 10, 2006

Equipment and Furnishing Structure

Page 221

OSA MRO Support Pvt. Ltd FOR TRAINING PURPOSES ONLY!

STRUCTURE

One Stop Airline MRO Support Pvt. Ltd

Purpose Passenger compartment equipment/furnishings provide for the comfort, convenience, and safety of the passengers and cabin attendants. General Description Sidewall panels line the sidewalls of the passenger compartment. Lowered ceiling panels, moveable ceiling panels, and sculptured ceiling panels line the ceiling. Service units are at all seats, attendant panels, and in all lavatories. Closets store coats during flight. There are seats for passengers and attendants. Full height stowage partitions store miscellaneous equipment. Overhead stowage bins store luggage and miscellaneous equipment. Service outlets provide 115v ac and 28v dc power. The passenger compartment equipment/furnishings includes these items: S Lining and insulation S Inner windows S Air return grilles S Passenger seats S Passenger service units S Attendant/lavatory service units S Windscreens S Class dividers S Overhead stowage bins S Cabin attendant stations S Floor covering.

Sidewall Panels Sidewall panels extend from the air return grilles to the overhead stowage bins. The panels are crushed—core composite. The inboard surface has a decorative stain—resistant covering. Sidewall panels have one or two window cutouts. The window mounts near the middle of each panel. The inner window is removable with the panel in place. Sidewall panels mount to the airplane structure by support brackets on the vertical edges. A trim strip fits between each panel to cover the fasteners. The upper edge slides into the air outlet extrusion. Passenger Service Units Passenger service units (PSU) are above each passenger seat row. The speaker, information signs (NO SMOKING, FASTEN SEAT BELT), life vest stowage, gasper air and reading light assemblies are all on one panel. PSUs have inboard and outboard support rails. They have hinges on the outboard side and latches on the inboard side. Small holes in the PSU face panels give access to the release latches. A lanyard limits movement as the unit swings open. Individual reading lights are controlled by switches on the PSU. An attendant call light and switch is located between the reading lights.

Passenger Seats The passenger seats attach to the seat tracks in the floor. You may move the seats forward or aft for different cabin configurations. Each seat has a lap belt. The back of each seat reclines. To recline the seatback, push the button on the armrest and apply pressure to the seatback. Most seats have trays which fold down. Seats adjacent to windscreens have trays under their armrests.

Mai 10, 2006

51-- 57

For seats adjacent to escape hatches, the armrest attaches to the escape hatch (rather than the seat). This makes sure that the escape hatches can open quickly in an emergency. The seats are two or three passenger assemblies. Seat placement allows four, five, or six abreast confi gurations. You can use the seat cushions as flotation devices. You can stow life vests in the space under the seats.

PASSENGER COMPARTMENT

FRA US/E GiM

B737-- 600/700/800/900

Training Information Point You can use the same PSU for either the left or right side of the airplane. To do this, you must move the panel hinges and latches to opposite sides of the panel. NOTE:

Structure

To open passenger service units, insert a small allen wrench or other applicable tool into the latch release hole. Then lower the service unit.

Page 222

OSA MRO Support Pvt. Ltd

STRUCTURE

B737-- 600/700/800/900

One Stop Airline MRO Support Pvt. Ltd

PASSENGER SERVICE UNIT

BULL NOSE

OVERHEAD STOWAGE BIN

51-- 57

CEILING PANEL

SHADE/REVEAL

ARMREST

SEAT BACK

FOR TRAINING PURPOSES ONLY!

SIDEWALL LINER

SEAT TRAY

SEAT CUSHION

AIR RETURN FLOOR GRILLE COVERING

SEAT

SEAT TRACK

Figure 113 FRA US/E GiM

Mai 10, 2006

SEAT TRAY

Passenger Compartment - Introduction Structure

Page 223

OSA MRO Support Pvt. Ltd FOR TRAINING PURPOSES ONLY!

STRUCTURE

One Stop Airline MRO Support Pvt. Ltd

B737-- 600/700/800/900 51-- 57

CABIN ATTENDANT STATIONS Purpose Cabin attendant stations provide workstations and seats for the cabin attendants. Physical Description/Location Cabin attendant stations are near the forward and aft entry doors. Each station has accommodations for two attendants and include these items: S Double seats S Stowage provisions S Attendant panel S Service unit. Each seat is spring—loaded to move to the stowed position when not in use. The seat cushions attach to the seat assembly with hook—and—loop tape. The cushions are removable for use as flotation devices when necessary. Each seat has a shoulder harness and seat belt restraint system. The attendant seat cushion, backrest, and headrest assemblies have fire retardant material to provide fire blocking protection. A stowage box above the forward attendant panel contains the music announce panel and provides additional stowage space for miscellaneous equipment and emergency equipment. Compartments below the seat bottom provide stowage for life vests and flashlights. The attendant handset is between the headrests. The attendant panels are above the headrests. A boarding light is above each entry door. Attendant service units are in the ceiling above each cabin attendant station. Each attendant service unit has two oxygen masks and an oxygen generator. On some airplanes, additional cabin attendant stations are in the passenger compartment. Attendant Service Units Attendant service units (ASUs) provide emergency oxygen for attendants or passengers. ASUs are in lowered ceiling panels at entryways. ASUs have oxygen masks and oxygen generators.

FRA US/E GiM

Mai 10, 2006

Structure

Page 224

OSA MRO Support Pvt. Ltd

STRUCTURE

One Stop Airline MRO Support Pvt. Ltd

B737-- 600/700/800/900 51-- 57

SERVICE UNIT ATTENDANT PANEL

HEAD REST

FOR TRAINING PURPOSES ONLY!

BACK RESTS

STOWAGE FLASHLIGHT & LIFE VEST STOWAGE FORWARD ATTENDANT STATION

SEAT CUSHIONS STOWAGE PROVISIONS FOR EMERGENCY EQUIPMENT AFT ATTENDANT STATION

Figure 114 FRA US/E GiM

Mai 10, 2006

Attendant Station Structure

Page 225

OSA MRO Support Pvt. Ltd FOR TRAINING PURPOSES ONLY!

STRUCTURE

ATA 35

One Stop Airline MRO Support Pvt. Ltd

B737-- 600/700/800/900 51-- 57

OXYGEN

OXYGEN SYSTEM INTRODUCTION Purpose The purpose of the oxygen systems is to provide oxygen for the crew and passengers, when required. General Subsystem Features Three independent oxygen systems are installed: S Crew System: The flight crew oxygen system has a supply of high pressure gaseous oxygen and distributes and delivers it at low pressure to the crew. High pressure oxygen is kept in an oxygen cylinder assembly. The oxygen cylinder assembly includes a safety discharge device to protect against too much pressure. Oxygen cylinder pressure is reduced through a pressure regulator. Low pressure oxygen is distributed through individual control panels and mask stowage boxes. S Passenger System: The passenger oxygen system automatically releases oxygen masks to the passengers and attendants whenever the cabin pressure falls to a value equivalent to an altitude of 14,000 feet. Oxygen is kept in chemical oxygen generators and oxygen flow is started by the action of the passenger or attendant pulling the oxygen mask down to the face. Mask deployment also can be operated by a switch on the P5 aft overhead panel. S Portable System: The portable oxygen equipment includes portable oxygen cylinder assemblies and protective breathing equipment. The portable cylinders supply oxygen for emergency, first aid or sustaining oxygen for the passengers and/or crew. General Components Location The crew oxygen components are in the forward cargo compartment and the flight compartment. The passenger oxygen components are located in the PSU’s. Portable oxygen cylinders are located in the flight compartment and passenger cabin. FRA US/E GiM

Mai 10, 2006

Structure

Page 226

OSA MRO Support Pvt. Ltd

STRUCTURE

B737-- 600/700/800/900

One Stop Airline MRO Support Pvt. Ltd O G 2

51-- 57

= CHEMICAL OXYGEN GENERATOR = MASK

M

MASK REGULATOR AND STOWAGE BOX

DEMAND REGULATOR TO OTHER MASKS

OXYGEN PRESS IND (P5 PANEL)

PRESSURE REDUCING REGULATOR

O G 2

M

M

M

M

M

M

PASSENGER SERVICE UNITS (PSU) M

PRESSURE TRANSDUCER

FOR TRAINING PURPOSES ONLY!

CYLINDER SOV CYLINDER PRESS GAGE

O G 2

M

M

REGULATOR

ATTENDANT

M

CYLINDER SOV

O G 2

M

CYLINDER PRESS GAGE

LAVATORY PASSENGER OXYGEN SYSTEM

FLIGHT CREW OXYGEN SYSTEM

PORTABLE OXYGEN SYSTEM

Figure 115 FRA US/E GiM

Mai 10, 2006

Introduction

Structure

Page 227

OSA MRO Support Pvt. Ltd FOR TRAINING PURPOSES ONLY!

STRUCTURE

One Stop Airline MRO Support Pvt. Ltd

PASSENGER OXYGEN SYSTEM General Description The passenger oxygen system uses chemical generators to make oxygen. Oxygen from the generators flows through flexible supply hoses to the passenger oxygen masks. Passenger oxygen masks are deployed electrically one of two ways: S Manually by the crew using a guarded toggle switch on the aft P5 panel S Automatically by activation of an aneroid switch (cabin altitude 14000 ft.). Passenger oxygen generation is initiated mechanically when the oxygen mask is pulled to the user s face. Pulling the mask releases a spring loaded firing pin on the generator. The firing pin strikes a percussion cap, which starts the reaction. Once started, the reaction goes to completion, and cannot be stopped. Location Passenger oxygen generators, masks, firing pin mechanisms, and deployment door latch actuators are located in: S The passenger service units (PSUs) S The lavatory service units S The attendant service units. A guarded toggle switch for manual deployment of the passenger oxygen masks is located on the aft P5 panel. An aneroid switch for automatic deployment, and system electrical relays are located in the EE compartment in the J23 junction box. A PASS OXY ON light on the P5 panel indicates deployment of the passenger oxygen masks. Operational Displays The PASS OXY ON light on the P5 panel comes on when the passenger oxygen masks are deployed. The chemical oxygen generators have a band of heat sensitive tape around them. The tape turns black when heated. A chemical oxygen generator with black tape is expended and must be replaced.

FRA US/E GiM

Mai 10, 2006

B737-- 600/700/800/900 51-- 57

OXYGEN MASK The passenger oxygen masks supply breathing oxygen to aircraft passengers and flight attendants during emergency decompression of the aircraft. The passenger oxygen masks have the following parts: S A bright yellow silicon rubber facepiece with breathing valves, elastic headstrap, and generator release lanyard S Flexible supply tubing and reservoir bag. Functional Description When stowed, the masks are packed in the service unit. When deployed, the masks hang by a mask lanyard. When the mask is pulled to the user’s face, the mask lanyard pulls on the oxygen generator firing pin release cable. This starts the oxygen generator. Oxygen from the generator manifold flows through the mask tubing to the reservoir bag. The reservoir bag stores oxygen from the constant outflow of the generator when the user is not inhaling. During inhalation, the oxygen flows through the reservoir bag and the mask inhalation valve. When the oxygen in the bag is used, the mask ambient air valve opens to allow ambient air to enter the facepiece. When the user exhales, the inhalation and ambient air valves close, and the exhalation valve opens. The exhalation valve lets the used air flow out of the mask. Operational Controls The user places the yellow facepiece over the mouth and nose. The soft silicon rubber of the mask contours to the facial features to give a good seal. The mask can be held in place by hand or by pulling the mask’s elastic headstrap over the user1s head. The headstrap can be adjusted by pulling on either of its ends. Instructions for mask use are diagrammed on the reservoir bag.In some models the reservoir bag has a built-in flow indicator which inflates when oxygen flows into the bag. The indicator area is shaded green for easy recognition. Other configurations include an in-line flow indicator which changes color to green in the presence of oxygen.

Structure

Page 228

OSA MRO Support Pvt. Ltd

STRUCTURE

B737-- 600/700/800/900

One Stop Airline MRO Support Pvt. Ltd

51-- 57

PASSENGER SERVICE UNIT MASKS (DEPLOYED)

OXYGEN GENERATOR

OXYGEN TUBING FLOW INDICATORS OXY MOD DOOR

PASSENGER CABIN

RELEASE CABLE INSTRUCTIONS OXYGEN TUBING

RESERVOIR BAG

14,000 FT

FOR TRAINING PURPOSES ONLY!

S 813 ALT PRESS SW J23 BOX (E&E COMP)

EXHALATION VALVE CREW OXYGEN

PASS OXYGEN INHALATION VALVE ORONASAL CUP

NORMAL 10 5

15

0

20

ON OXY PRESS PSI X 100

PASS OXY ON

HEADSTRAP

a

OXYGEN MASK

P5 PANEL

Figure 116 FRA US/E GiM

Mai 10, 2006

Passenger Oxygen System Introduction Structure

Page 229

OSA MRO Support Pvt. Ltd

STRUCTURE

ATA 38

One Stop Airline MRO Support Pvt. Ltd

B737-- 600/700/800/900 51-- 57

WATER AND WASTE

POTABLE WATER - INTRODUCTION The potable water system supplies water to the lavatories and galleys. General Description The potable water system has these subsystems: S Passenger water S Water heating S Water quantity indication. The passenger water system supplies water to the lavatories and galleys. The water heating system heats the water supplied to the lavatory hot water faucets. The water quantity indication system measures and displays the quantity of water in the potable water system.

FOR TRAINING PURPOSES ONLY!

l

Pneumatic System The water tank pressurization system pressurizes the potable water tank. Pressure for the water tank comes from the pneumatic system or the air compressor. The water tank pressurization system has these functions: S Controls the air pressure that goes into the water tank S Selects the source of the pressurized air S Prevents contamination from unwanted material in the air. The pneumatic system supplies pressurized air to the water tank when the pneumatic system is on. An in--line air filter cleans the air in the pneumatic system supply line. A pressure regulator controls the pneumatic system supply line pressure to a maximum of 35 psig.

FRA US/E GiM

Mai 10, 2006

Structure

Page 230

OSA MRO Support Pvt. Ltd

STRUCTURE

B737-- 600/700/800/900

One Stop Airline MRO Support Pvt. Ltd

51-- 57

WATER QTY INDICATOR FWD LAV

FWD GALLEY

AFT LAV

WATER SUPPLY SOV TOILET RINSE VALVE

AFT GALLEY WATER FILTER

WATER HEATER TOILET RINSE VALVE

H

H

WATER SUPPLY SOV FWD LAVATORY DRAIN VALVE

CABIN FLOOR RELIEF VALVE > 60 PSI

FILL/OVERFLOW VALVE T WATER QTY TRANSMITTER

PRESS REG 35 PSI

PRESS SW < 30 PSI ON > 40 PSI OFF

RELIEF VALVE > 90 PSI

AIR FILTER

AIR COMPR AIR FILTER

FOR TRAINING PURPOSES ONLY!

WATER TANK

WATER TANK LEVEL SENSOR WATER TANK DRAIN VALVE

FWD DRAIN MAST FWD POTABLE WATER DRAIN PORT

AFT DRAIN MAST WATER SEVICE PANEL POTABLE WATER FILL FITTING

Figure 117 FRA US/E GiM

Mai 10, 2006

FROM PNEUMATIC MANIFOLD

AFT POTABLE WATER DRAIN PORT

AIR SUPPLY

Functional Description Structure

Page 231

OSA MRO Support Pvt. Ltd

STRUCTURE

One Stop Airline MRO Support Pvt. Ltd

VACUUM WASTE SYSTEM The vacuum toilet collects human waste. A flush cycle puts the waste material into the vacuum waste tubing. There are two sources that cause low pressure (vacuum) in the tank: S The vacuum blower S Cabin--to--ambient pressure differential. Vacuum Toilet Assemblies Operation of the flush switch sends a signal to the flush control unit (FCU). The FCU opens the rinse valve to supply potable water to flush the toilet bowl. After 0.7 seconds, the FCU closes the rinse valve. Each rinse cycle uses eight ounces of potable water. The FCU then opens the flush valve for four seconds to let the toilet waste drain out of the toilet. The flush valve then closes. The anti--siphon valve prevents the vacuum waste system from siphoning water from the potable water system. The manual shutoff handle closes the flush valve.

FOR TRAINING PURPOSES ONLY!

Waste Tank Assembly The waste tank collects the waste from the lavatory toilets. Differential pressure causes the toilet bowl contents to flow from the toilet to the waste tank. The vacuum blower or cabin differential pressure supplies the differential pressure for the waste tank. The vacuum check valve prevents the pull of ambient air in from the waste tank vent port by the vacuum blower. Waste System Servicing You service the waste tank from the waste service panel. Attach the waste drain hose to the waste drain valve and open the waste drain ball valve. When the tank is empty, attach the rinse hose to the waste tank rinse fitting. Then pressurize the rinse water supply. Rinse water flows through the waste tank rinse filter and two rinse nozzles. The waste tank rinse nozzles spray water on the inside of the tank to clean the point level sensors and waste tank. Add chemical precharge after the waste tank is fully drained and flushed. The waste drain ball valve proximity switch stops the operation of the vacuum blower when the waste drain ball valve is open. FRA US/E GiM

Mai 10, 2006

B737-- 600/700/800/900 51-- 57

You use the drain line blockage removal valve to remove a blockage in the waste tank drain line. Rinse water flows to the drain line elbow and pushes the blockage out of the drain line. Interfaces The FCU must receive an enable signal from the logic control module (LCM) to operate the toilet components. The LCM disables the FCU if the waste tank is full. The LCM monitors the two point level sensors to find if the waste tank is full. If the FCU is enabled, a flush cycle starts with the operation of the flush switch. The flush switch sends a signal to the FCU. The FCU then sends a signal to operate the vacuum blower for 15 seconds. The signal goes through the waste drain ball valve proximity switch and the vacuum blower barometric switch. The waste drain ball valve proximity switch and vacuum blower barometric switch must be closed for the vacuum blower to operate. The waste drain ball valve proximity switch is closed when the waste drain ball valve is closed. The barometric switch is closed when the airplane is below 16,000 feet. Training Information Point The waste tank must be flushed at each servicing interval. If the waste tank is not serviced correctly, unwanted waste material can collect on the point level sensors. The waste material on the point level sensors can cause a tank full signal and stop operation of the lavatory toilets. You should flush crushed ice down the toilets at regular intervals. The crushed ice will help to prevent unwanted material from collecting in the vacuum waste lines. CAUTION: DO NOT USE ICE CUBES AS AN ALTERNATIVE TO THE CRUSHED ICE. ICE CUBES CAN CAUSE DAMAGE TO THE POINT LEVEL SENSORS IN THE WASTE TANK. There is a clean--out fitting in the forward vacuum waste line. You can use the clean--out fitting to clean a blockage between the waste tank and the forward lavatory.

Structure

Page 232

OSA MRO Support Pvt. Ltd

STRUCTURE

B737-- 600/700/800/900

One Stop Airline MRO Support Pvt. Ltd

51-- 57 RINSE VALVE

FLUSH SWITCH

ANTI--SIPHON VALVE

WASTE QTY IND

AFT TOILET

S

S

FCU

FWD TOILET

MANUAL SOV

FCU

CABIN FLOOR

FLUSH VALVE

FLUSH VALVE

BLOWER BARO SW 25 000 FT

APU FUEL SHUTOFF VALVE

FLOW DIVIDER AND FLOW DIVIDER SOLENOID FUEL CONTROL UNIT

FWD

FOR TRAINING PURPOSES ONLY!

APU FUEL FEED

APU FUEL FEED METERED FUEL PRIMARY FUEL ELECTRONIC CONTROL UNIT (AFT CARGO)

SECONDARY FUEL

Figure 157 FRA US/T4GiM

Mai 12, 2006

FUEL MANIFOLDS AND NOZZLES (10)

Fuel System General ATA 49 APU

Page 309

OSA MRO Support Pvt. Ltd

APU AUXILIARY POWER SYSTEM

One Stop Airline MRO Support Pvt. Ltd

B737-- 600/700/800/900 49-- 00

APU PNEUMATIC SYSTEM The APU supplies pneumatic power for the environmental control System and for main engine start. The air inlet door directs air into the inlet plenum. The APU takes inlet Plenum air for use in two APU sections. The APU has two separate compressors: S a power compressor supplies compressed air to the combustor. S a load compressor supplies pressurized air to the airplane’s pneumatic system. Load Compressor Inlet guide vanes control the amount of air that enters the load compressor. The ECU controls the inlet guide vanes with the inlet guide vane actuator. The inlet guide vane actuator uses fuel pressure to operate the inlet guide vanes.

FOR TRAINING PURPOSES ONLY!

Surge Control Valve A surge control valve sends excess pressurized air to the APU exhaust. This protects the load compressor from a surge. The ECU controls the surge control valve. Regulated fuel pressure, from the fuel control unit, operates the surge control valve.

FRA US/T4GiM

Mai 12, 2006

ATA 49 APU

Page 310

OSA MRO Support Pvt. Ltd

APU AUXILIARY POWER SYSTEM

B737-- 600/700/800/900

One Stop Airline MRO Support Pvt. Ltd

FUEL IN

49-- 00

FUEL RETURN INLET GUIDE VANE ACTUATOR

LOAD COMPRESSOR

ENGINE COMPRESSOR

CDU INLET GUIDE VANES ELECTRONIC CONTROL UNIT

FOR TRAINING PURPOSES ONLY!

BLEED AIR VALVE

INLET AIR FLOW

SURGE BLEED AIR AIR FLOW

TO APU EXHAUST FUEL RETURN FUEL IN

LVDT T/M

Figure 158 FRA US/T4GiM

Mai 12, 2006

SURGE CONTROL VALVE

APU Pneumatic System ATA 49 APU

Page 311

OSA MRO Support Pvt. Ltd

APU AUXILIARY POWER SYSTEM

One Stop Airline MRO Support Pvt. Ltd

B737-- 600/700/800/900 49-- 00

IGNITION AND START SYSTEM General The APU ignition and start system consists of these components: S Ignition unit S Igniter plug S Start power unit (SPU) S Start converter unit (SCU) S Starter--generator. The APU electronic control unit (ECU) controls the APU start sequence. Ignition System The ignition system supplies sparks to start APU combustion during the APU start. The ignition unit supplies spark to the igniter plug. The ECU energizes the ignition unit at 0% speed and deenergizes the ignition unit at 60% speed. The ECU energizes the ignition system again, if the APU engine speed goes below 95% speed during APU operation (speed droop).

FOR TRAINING PURPOSES ONLY!

Start System The starter--generator, SPU, and SCU together supply initial rotation of the APU. The start power sources are 28v dc from the battery or 115v ac transfer bus number 1. The starter--generator is also a source of electrical power for the airplane systems. It supplies 90 kva of ac electrical power on ground and in flight. The starter--generator is on the upper right side of the APU gearbox. The APU oil system cools the starter--generator.

FRA US/T4GiM

Mai 12, 2006

ATA 49 APU

Page 312

OSA MRO Support Pvt. Ltd

APU AUXILIARY POWER SYSTEM

One Stop Airline MRO Support Pvt. Ltd

B737-- 600/700/800/900 49-- 00

ENERGIZED 0% SPEED DE-ENERGIZED >60% SPEED

IGNITION UNIT AND IGNITER PLUG LEAD

FWD

115V AC TRANSFER BUS 1 OR BATTERY

STARTER--GENERATOR

FOR TRAINING PURPOSES ONLY!

IGNITER PLUG

270V DC

START POWER UNIT

START CONVERTER UNIT

Figure 159 FRA US/T4GiM

Mai 12, 2006

270V AC

ELECTRONIC CONTROL UNIT

Ignition and Start System Components ATA 49 APU

Page 313

OSA MRO Support Pvt. Ltd

POWER PLANT

ATA 71

One Stop Airline MRO Support Pvt. Ltd

B737-- 600/700/800/900 71-- 80

POWER PLANT Bump Option for the --7B22 B1, --7B24 B1, --7B26 B1. Bump is an Option provided to achieve power levels greater than the normal take--off levels within specific limitations. The bump rating does not influence power levels which are at, or below Max. Continuous Thrust. For any available bump, the redline values (N1, N2, EGT) remain identical to the baseline rating.

ENGINE — INTRODUCTION General Two CFM56—7B engines supply thrust for the airplane. The engines also supply power for these systems: S Electric S Hydraulic S Pneumatic. The CFM56—7B is a high bypass ratio, dual rotor, turbo fan engine. Engine Thrust Ratings and Aircraft Model Application A limited number of the six engine thrust rating configurations are applicable to a 737 model. The different engine thrust ratings are based upon airplane weight and elevator/rudder control limits. The longer--body 737--800 and 737--900 models can operate at the maximum thrust capability of the CFM56--7B engine. Also, the lowest thrust rating is not sufficient for the 737--700, 737--800, 737--900.

FOR TRAINING PURPOSES ONLY!

Aircraft Models The normal models are 737--600, 700, 800 and 900. Some other variations will be 737--700 IGW (increased gross weight), and 737--700 BBJ (Boeing business jet). Engine Thrust Rating By design, all 7B engines can produce a take--off thrust of 27,300 Ibs. Specific contacts within the identification plug enable various thrust ratings, which are : -- B18 : 19,500 Ibs 737--600. -- B20 : 20,600 Ibs 737--600 & --700. -- B22 : 22,700 Ibs 737--600 & --700. -- B24 : 24,200 Ibs 737--700 & --800 & --900. -- B26 : 26,300 Ibs 737--800 & --900 & --BBJ & COMBI & C40A. -- B27 : 27,300 Ibs 737--800 & --900. FRA US/E GiM

Mai 10, 2006

ATA 71--80 Engine

Page 314

One Stop Airline MRO Support Pvt. Ltd

FOR TRAINING PURPOSES ONLY!

OSA MRO Support Pvt. Ltd

POWER PLANT

B737-- 600/700/800/900 71-- 80

30_C

Figure 160 FRA US/E GiM

Mai 10, 2006

Thrust Rating

ATA 71--80 Engine

Page 315

OSA MRO Support Pvt. Ltd

POWER PLANT

ATA 72

One Stop Airline MRO Support Pvt. Ltd

The CFM56-7 is a high bypass, dual rotor, axial flow turbofan engine. The engine has these sections: S Fan and booster The fan and booster rotor and the LPC rotor are on the same low pressure shaft (N1). The fan and booster is a four-stage compressor. The fan increases the speed of the air. A splitter fairing divides the air into these two air flows: -- Primary The primary air flow goes into the core of the engine. The booster increases the pressure of this air and sends it to the HPC. -- Secondary.

FOR TRAINING PURPOSES ONLY!

S

S

S

The secondary air flow goes in the fan duct. It supplies approximately 80% of the thrust during take-off. High pressure compressor (HPC) The HPC rotor and the HPT rotor are on the same high pressure shaft (N2). The HPC is a nine-stage compressor. It increases the pressure of the air from the LPC and sends it to the combustor. The HPC also supplies bleed air for the aircraft pneumatic system and the engine air system. Combustor The combustor mixes air from the compressors and fuel from the fuel nozzles. This mixture of air and fuel burns in the combustion chamber to make hot gases. The hot gases go to the HPT. High pressure turbine (HPT) The HPT is a single-stage turbine. It changes the energy of the hot gases into a mechanical energy. The HPT uses this mechanical energy to turn the HPC rotor and the accessory drive. Low pressure turbine (LPT) The LPT is a four-stage turbine. It changes the energy of the hot gases into a mechanical energy. The LPT uses this mechanical energy to turn the fan and booster rotor.

FRA US/E GiM

71-- 80

ENGINE

GENERAL DESCRIPTION

S

B737-- 600/700/800/900

Mai 10, 2006

S Accessory drive. The accessory drive has these components: -- Inlet gear box (IGB) -- Radial drive shaft (RDS) -- Transfer gear box (TGB) -- Horizontal drive shaft (HDS) -- Accessory gear box (AGB). The N2 shaft turns the AGB through these shafts and gearboxes: -- IGB -- RDS -- TGB -- HDS. The AGB holds and operates the airplane accessories and the engine accessories.

ATA 71--80 Engine

Page 316

One Stop Airline MRO Support Pvt. Ltd

B737-- 600/700/800/900 71-- 80

FOR TRAINING PURPOSES ONLY!

OSA MRO Support Pvt. Ltd

POWER PLANT

FRA US/E GiM

Mai 10, 2006

ATA 71--80 Engine

Page 317

One Stop Airline MRO Support Pvt. Ltd

B737-- 600/700/800/900 71-- 80

FADEC SYSTEM INTRODUCTION FADEC Purpose. The CFM56--7B operates through a system known as FADEC (Full Authority Digital Engine Control). It takes complete control of engine systems in response to command inputs from the aircraft. It also provides information to the aircraft for flight deck indications, engine condition monitoring, maintenance reporting and troubleshooting. S It performs fuel control and provides limit protections for N1 and N2. S It controls the engine parameters during the starting sequence and prevents the engine from exceeding starting EGT limits (aircraft on ground). S It manages the thrust according to 2 modes: -- manual and -- autothrust. S It provides optimal engine operation by controlling compressor airflow and turbine clearances. S Finally, it controls the 2 thrust lever interlock solenoids.

FOR TRAINING PURPOSES ONLY!

OSA MRO Support Pvt. Ltd

POWER PLANT

FRA US/E GiM

Mai 10, 2006

ATA 71--80 Engine

Page 318

OSA MRO Support Pvt. Ltd

POWER PLANT

B737-- 600/700/800/900

One Stop Airline MRO Support Pvt. Ltd

71-- 80

FOR TRAINING PURPOSES ONLY!

FADEC

Figure 161 FRA US/E GiM

Mai 10, 2006

Fadec Purpose

ATA 71--80 Engine

Page 319

OSA MRO Support Pvt. Ltd

POWER PLANT

ATA 79

One Stop Airline MRO Support Pvt. Ltd

B737-- 600/700/800/900 71-- 80

OIL

ENGINE OIL SYSTEM General The engine oil system is a self--contained, centervented and recirculating type system. Each engine has an independant oil system to provide lubrication and cooling for the engine main bearings, radial driveshaft bearings and gears and bearings in the transfer gearbox (TGB) and accessory gearbox (AGB). The oil system consist of: S oil storage system, S oil distribution system and S oil indicating system Storage The oil storage system keeps sufficient oil for a continuous supply to the oil distribution circuit. The oil storage system lets you do an oil level check and to fill the oil system. The oil storage system holds oil in the oil tank.

Distribution The oil distribution system has these circuits: S Supply The supply circuit sends oil to lubricate the engine bearings and gears. Oil from the tank goes to the lubrication unit through an anti--leakage valve. The lubrication unit pressurizes and filters the oil. The oil then goes to the engine. S Scavenge The scavenge circuit takes the oil from the engine. Oil first flows through the lubrication unit. The lubrication unit also scavenges the oil. The oil goes to the scavenge oil filter and then to the servo fuel heater. The oil goes from the servo fuel heater to the main oil/fuel heat exchanger and then back to the servo fuel heater. Then the oil flows back to the oil tank. S Vent. The vent circuit balances the internal air pressures in the oil system. Externally, a vent line connects the engine to the oil tank. Unwanted air pressure goes out of the oil tank through the vent line.

FOR TRAINING PURPOSES ONLY!

Indication The oil quantity indicating system sends this data to the display electronic units (DEUs): S Scavenge oil filter bypass indication S Low oil pressure indication S Oil pressure S Oil temperature S Oil quantity.

FRA US/E GiM

Mai 10, 2006

ATA 71--80 Engine

Page 320

OSA MRO Support Pvt. Ltd

POWER PLANT

B737-- 600/700/800/900

One Stop Airline MRO Support Pvt. Ltd

71-- 80

EEC

DEU

SERVO FUEL HEATER

OIL FILTER BYPASS

OIL FILTER BYPASS

LOW OIL PRESSURE

LOW OIL PRESSURE

T/P SENSOR 100

50

100

50

0

0 OIL P

OIL TANK

200

200

100

100 0

0 OIL T

75

OIL Q %

75

UPPER CENTER DISPLAY UNIT (P2 PANEL) CONFIG. 1

ANTI--LEAKAGE VALVE MAIN OIL/FUEL HEAT EXCHANGER

FOR TRAINING PURPOSES ONLY!

12

165

20 LUBRICATION UNIT

SCAVENGE OIL FILTER

SUPPLY SCAVENGE VENT

Figure 162 FRA US/E GiM

Mai 10, 2006

OIL PRESS

36

OIL TEMP

130

OIL QTY

20

SECONDARY ENGINE DISPLAY UNIT (P2) CONFIG. 2

Oil System Schematic

ATA 71--80 Engine

Page 321

OSA MRO Support Pvt. Ltd

POWER PLANT

ATA 73

One Stop Airline MRO Support Pvt. Ltd

B737-- 600/700/800/900 71-- 80

ENGINE CONTROLS

The engine control system supplies manual and automatic control inputs to control the engine thrust. It also supplies signals to other airplane systems that require engine control status. The engine control system has these components: S Thrust levers (forward and reverse) S Engine start levers and switches S Thrust lever interlock solenoids. Thrust Levers You use the thrust levers to supply the manual inputs to the engine control system. There are two thrust lever assemblies, one for each engine. For each engine, there is a forward thrust lever and a reverse thrust lever. The reverse thrust lever is on the forward thrust lever. For each engine, the thrust levers supply a thrust command signal to the electronic engine control (EEC) through a resolver. Each thrust lever assembly connects mechanically to a resolver through an adjustable rod. An interlock latch prevents the operation of the forward thrust lever and the reverse thrust lever at the same time.

FOR TRAINING PURPOSES ONLY!

Start Levers There are two start levers, one for each engine. You use the engine start lever during an engine start. You also use it to shutdown the engine. The start levers operate switches which supply signals to different aircraft and engine systems and components. Reverse Thrust Interlock Solenoids There are two reverse thrust interlock solenoids, one for each engine. Each reverse thrust interlock solenoid limits the range of motion of a reverse thrust lever. You can make the thrust reverser deploy, but you can not increase the reverse thrust until the thrust reverser sleeves are near the full deployed position. The EEC operates the solenoids. The thrust lever interlock solenoids are in the autothrottle assembly. You must remove the autothrottle assembly to access the thrust lever interlock solenoids. See the thrust reverser section for more information. (AMM PART I 78—31) See the autoflight chapter for more information on the autothrottle system. (AMM PART I 22) FRA US/E GiM

Mai 10, 2006

ATA 71--80 Engine

Page 322

OSA MRO Support Pvt. Ltd

POWER PLANT

B737-- 600/700/800/900

One Stop Airline MRO Support Pvt. Ltd

71-- 80

RODS

INTERLOCK LATCH THRUST LEVERS

FOR TRAINING PURPOSES ONLY!

THRUST LEVER CRANK

START LEVERS START LEVER SWITCHES

RODS REVERSE THRUST INTERLOCK SOLENOIDS

FWD

FWD

THRUST LEVER RESOLVER ASSEMBLIES

Figure 163 FRA US/E GiM

Mai 10, 2006

Engine Controls Components ATA 71--80 Engine

Page 323

One Stop Airline MRO Support Pvt. Ltd

B737-- 600/700/800/900 71-- 80

ENGINE FUEL AND CONTROL - DISTRIBUTION The engine fuel pump assembly receives fuel from the airplane fuel system. The fuel pump assembly supplies pressurized fuel to the servo and metering sections of the HMU. The fuel filter in the pump cleans the fuel that goes to the HMU. These units heat the fuel before it goes to the HMU: S IDG oil cooler S Oil/fuel heat exchanger S Servo fuel heater. Fuel goes from the fuel pump to the IDG oil cooler, then to the oil/fuel heat exchanger. From the oil/fuel heat exchanger, the fuel goes back to the fuel pump assembly. This fuel becomes high pressure fuel. This high pressure fuel goes to the HMU. Part of the high pressure fuel goes through the servo fuel heater before it goes to the HMU. The other part of the high pressure fuel becomes metered fuel in the HMU. The fuel pump always supplies more fuel to the HMU than the HMU can use. The fuel that the HMU does not use (bypass fuel) goes back to the outlet of the integrated drive generator (IDG) oil cooler. This fuel returns to the fuel pump. Metered fuel goes through the fuel flow transmitter. From the fuel flow transmitter, metered fuel goes through the fuel nozzle filter. Fuel goes from the fuel nozzle filter to the fuel nozzles. The fuel nozzles supply atomized fuel to the engine combustion chamber.

FOR TRAINING PURPOSES ONLY!

OSA MRO Support Pvt. Ltd

POWER PLANT

FRA US/E GiM

Mai 10, 2006

ATA 71--80 Engine

Page 324

OSA MRO Support Pvt. Ltd

POWER PLANT

B737-- 600/700/800/900

One Stop Airline MRO Support Pvt. Ltd

71-- 80

SERVO FUEL HEATER AIRPLANE FUEL SYSTEM HYDROMECHANICAL UNIT

FUEL MANIFOLD FUEL FLOW TRANSMITTER

OIL/FUEL HEAT EXCHANGER

FUEL NOZZLE FILTER FUEL NOZZLES (20)

FOR TRAINING PURPOSES ONLY!

FUEL PUMP ASSEMBLY

IDG OIL COOLER FUEL SUPPLY (LOW PRESSURE) UNMETERED (HIGH PRESSURE) METERED (HIGH PRESSURE) BYPASS (LOW PRESSURE)

Figure 164 FRA US/E GiM

Mai 10, 2006

Fuel Distribution

ATA 71--80 Engine

Page 325

OSA MRO Support Pvt. Ltd

POWER PLANT

One Stop Airline MRO Support Pvt. Ltd

ENGINE THRUST CONTROL The engine fuel and control system controls the power for engine operation. The electronic engine control (EEC) uses the fuel metering valve (FMV) in the hydro mechanical unit (HMU) schedule fuel flow. The metered fuel supplies correct engine power at all thrust lever positions. This is for both forward and reverse thrust. Percent N1 speed indication is the measure of engine thrust. The EEC controls these engine forward and reverse thrust conditions: S Idle forward thrust S Maximum forward thrust S Idle reverse thrust S Maximum reverse thrust.

FOR TRAINING PURPOSES ONLY!

Idle Thrust Control The EEC/HMU controls ground and in--flight idle speed and thrust. There are no mechanical adjustments for idle speeds. On the ground, the EEC uses a selected total temperature to control minimum N2 speed. In flight, the EEC uses static air pressure, total air pressure and total air temperature to calculate and control the fuel metering valve for idle speed. The EEC/HMU prevents engine flameout and adjust idle speed for high pressure compressor (HPC) bleed air supply to airplane pneumatic or thermal anti--ice (TAI) systems. The EEC does not let the in--flight N2 idle speed to decrease less than approximately 59%. The fuel flow will not go below 300 lb/h (136 kg/h). Other inputs that have an effect on idle speed are pressure altitude and mach airspeed number.

B737-- 600/700/800/900 71-- 80

Thrust Reverser LVDT The T/R s leeve linear variable differential transformer (LVDT) supplies position data to the EEC. There is one dual channel on each T/R half locking actuator. The EEC uses the thrust reverser position data to operate these functions: S Reverse thrust lever interlock solenoid control S Fuel metering valve (FMV) control for reverse thrust power S The two color REV message control signals to the common display system (CDS) display electronic units (DEUs), which show on some display units (DUs). Make sure to supply airplane electrical power to the EEC during thrust reverser operation with the engines not on. Put the engine start switch to the CONT position, making sure the start lever is in CUTOFF. With power to the EEC, the REV message signal will go to the DEUs.

Forward Thrust Control The EEC uses thrust resolver angle (TRA) inputs to control forward thrust and reverse thrust. The EEC calculates and controls forward and reverse thrust conditions from changes in thrust lever angle inputs from the thrust lever angle resolvers (TLRs). Reverse Thrust Control and Indication The EEC controls engine speed for thrust reverser (T/R) operation. The EEC also supplies T/R translating sleeve data to the DEUs. When the T/R sleeves get to the 90 % deploy position, full reverse thrust from the engine can occur.

FRA US/E GiM

Mai 10, 2006

ATA 71--80 Engine

Page 326

OSA MRO Support Pvt. Ltd

POWER PLANT

One Stop Airline MRO Support Pvt. Ltd

B737-- 600/700/800/900 71-- 80

FORWARD THRUST REVERSE THRUST

FOR TRAINING PURPOSES ONLY!

IDLE THRUST

HMU

Figure 165 FRA US/E GiM

Mai 10, 2006

Engine Thrust Control System Schematic ATA 71--80 Engine

Page 327

OSA MRO Support Pvt. Ltd FOR TRAINING PURPOSES ONLY!

POWER PLANT

ATA 75

One Stop Airline MRO Support Pvt. Ltd

71-- 80

ENGINE AIR

During engine operation, the electronic engine control (EEC) receives airplane system data through the display electronic units (DEUs). The EEC uses this data to control the engine air system. The EEC adjusts the bleed airflows to adjust the turbine blade tips clearances. The EEC also controls the compressor airflows to prevent stall. The EEC operates the air valves and the actuators through the hydromechanical unit (HMU). HMU servo fuel pressure moves the valves and the actuators. The engine air system has these subsystems: S Turbine clearance control The engine air system adjusts the clearances between the high pressure turbine (HPT) blades and shroud, and the low pressure turbine (LPT) blades and shroud. Usually, the engine air system decreases the clearance between the rotors and the turbine case. This helps the engine use less fuel. The engine air system also increases the clearance between the high pressure turbine blades and shroud during some power conditions. This makes sure the HPT blades tips do not rub against the case. S Compressor airflow control. The engine air system adjusts the low pressure compressor (LPC) and the high pressure compressor (HPC) airflows for all power conditions. These adjustments prevent an engine stall. Turbine Clearance Control The engine air system uses air to control the engine internal clearances. When the air flows onto a case, it heats or cools the case. This increases or decreases the clearance between the rotor blade tips and the case. These are the turbine clearance control sub--systems: S High pressure turbine active clearance control (HPTACC) S Low pressure turbine active clearance control (LPTACC). The HPATCC system controls the 4th--stage air and the 9th--stage air to the high pressure turbine (HPT) shroud support. The air flows through an HPTACC valve. The EEC uses the HMU to control the position of the HPTCC valve. The HMU sends servo fuel pressure to move the HPTACC valve actuator. The HPTACC actuator sends electrical position data to the EEc for closed--loop control.

FRA US/E GiM

B737-- 600/700/800/900

Mai 10, 2006

The LPTACC system controls the amount of fan discharge air that goes to the low pressure turbine (LPT) case. The air flows through the LPTACC valve. The EEC uses the HMU to control the position of the LPTACC valve. The HMU sends servo fuel pressure to move the LPTACC valve actuator. The LPTACC actuator sends electrical position data to the EEC for closed-loop control. Compressor Airflow Control These are the compressor airflow control subsystems: S Variable stator vanes (VSV) S Variable bleed valve (VBV) S Transient bleed valve (TBV). The VSV system controls the high pressure compressor (HPC) inlet airflow. The VSV system gives the correct quantity of air to the HPC. The EEC uses the HMU to control the VSV system. The HMU sends servo fuel pressure to move two VSV actuators. The two actuators move the variable stator vanes. Each actuator sends electrical position data to the EEC for closed-loop control. The VBV system controls the low pressure compressor (LPC) discharge airflow. The VBV system bleeds the LPC air out into the secondary airflow. The EEC uses the HMU to control the VBV system. The HMU sends servo fuel pressure to move two VBV actuators. The actuators cause the HPC discharge air bleed to the secondary airflow. Each actuator sends an electrical position data to the EEC for closed--loop control. The TBV sends HPC 9th--stage air to the low pressure turbine stage 1 nozzles for these two conditions: S Engine start S Engine acceleration. The EEC uses the HMU to control the TBV system. The HMU sends a servo fuel pressure to move the TBV actuator. The transient bleed valve sends an electrical position data to the EEC for closed-loop control.

ATA 71--80 Engine

Page 328

OSA MRO Support Pvt. Ltd

POWER PLANT

B737-- 600/700/800/900

One Stop Airline MRO Support Pvt. Ltd

FAN AIR

9TH STAGE HPC AIR

4TH STAGE HPC AIR

71-- 80

LPTACC VALVE

TBV

HPTACC VALVE

VBV

FOR TRAINING PURPOSES ONLY!

VSV STAGES (4)

FAN AND LPC (BOOSTER)

HPC

Figure 166 FRA US/E GiM

Mai 10, 2006

COMBUSTOR

HPT

LPT

Engine Air General

ATA 71--80 Engine

Page 329

OSA MRO Support Pvt. Ltd FOR TRAINING PURPOSES ONLY!

POWER PLANT

ATA 74

One Stop Airline MRO Support Pvt. Ltd

B737-- 600/700/800/900 71-- 80

IGNITION

The ignition systems supply electrical sparks in the combustion chamber for combustion. Each engine has two ignition systems that operate independently. The ignition system usually operates manually. However, the ignition systems operate automatically when the electronic engine control (EEC) sees a possible engine flameout condition. You use ignition during these times: S Ground start S Takeoff and Landings S In--flight (during heavy turbulence or bad weather) S In--flight start. These components control ignition: S Start levers S Start switches S Ignition selector switch S Electronic engine control (EEC). The start lever controls ignition system power to the EEC. The start switch and the ignition selector switch supply inputs to the EEC. The EEC uses these inputs to supply power to the ignition exciters. The ignition exciters supply power to the spark igniters.

WARNING:

MAKE SURE THE IGNITION EXITERS ARE DEENERGIZED BEFORE YOU START ON THE IGNITION SYSTEM. THE IGNITION SYSTEM VOLTAGE IS DANGEROUSLY HIGH. DO NOT TOUCH THE IGNITION SYSTEM COMPONENTS UNTIL YOU DO THE PROCE DURE THAT FOLLOWS. THIS PROCEDURE WILL RELEASE THE HIGH VOLTAGE FROM THE IGNITION EXITER. IF YOU DO NOT OBEY THIS PROCEDURE, INJURY TO PERSONS CAN OCCUR.

Electrical Power The engine 1 ignition systems receive 115 v ac from ac transfer bus 1 and the ac standby bus. The EEC has internal switches that control the 115v ac to the ignition exciters. The ignition exciters change the 115 v ac input to a dc voltage of approximately 15 000 to 20 000 v dc and 14.5 to 16 joules, for the spark igniters. The spark igniters give a spark for combustion. Usually, only one ignition exiter per engine operates at a time. The ignition systems of engine 2 receive ac power from ac transfer bus 2 and the ac standby bus.

FRA US/E GiM

Mai 10, 2006

ATA 71--80 Engine

Page 330

OSA MRO Support Pvt. Ltd

POWER PLANT

B737-- 600/700/800/900

One Stop Airline MRO Support Pvt. Ltd

71-- 80

GRD

START SWITCH

OFFCONT FLT

ENGINE START BOTH IGN

L

OFF CONT

IGN

FLT

R

1 115V AC TRANSFER BUS 1

GRD

2

P5

IGNITION SELECTOR SWITCH

115V AC STANDBY BUS CDS/DEU (2)

ENGINE 1 START LEVERS

FOR TRAINING PURPOSES ONLY!

CONTROL STAND

R SPARK IGNITER

L SPARK IGNITER

IGNITION EXCITERS

Figure 167 FRA US/E GiM

Mai 10, 2006

EEC 1

Ignition System Schematic ATA 71--80 Engine

Page 331

ATA 78

One Stop Airline MRO Support Pvt. Ltd

B737-- 600/700/800/900 71-- 80

THRUST REVERSER SYSTEM

The thrust reverser (T/R) system changes the direction of the fan air exhaust to help create reverse thrust. The fight crew uses reverse thrust to slow the airplane after landing or during a rejected takeoff (RTO). The turbine exhaust airflow direction does not change during reverse thrust. The T/R system has a eectrohydraulic control system and an indicating system. The T/R system has two thrust reversers. T/R 1 is the thrust reverser for engine 1 (left). T/R 2 is the thrust reverser for engine 2 (right).

FOR TRAINING PURPOSES ONLY!

OSA MRO Support Pvt. Ltd

POWER PLANT

FRA US/E GiM

Mai 10, 2006

ATA 71--80 Engine

Page 332

OSA MRO Support Pvt. Ltd

POWER PLANT

LEFT TRANSLATING SLEEVE

STRUT (REF)

71-- 80

FAN AIR EXHAUST

FAN COWL (REF)

INLET AIR

EXHAUST AIR

EXHAUST NOZZLE

EXHAUST AIR

EXHAUST PLUG

EXHAUST NOZZLE

BLOCKER DOOR (CLOSED) CASCADE

OUTER SKIN

OUTER SKIN

INNER SKIN

FAN AIR EXHAUST

FAN AIR EXHAUST

BLOCKER DOOR DRAG LINK FWD

FWD

FAN DUCT

Figure 168 Mai 10, 2006

INNER SKIN BLOCKER DOOR DRAG LINK FAN DUCT REVERSE THRUST (DEPLOY POSITION)

FORWARD THRUST (STOW POSITION)

FRA US/E GiM

EXHAUST PLUG

T/R DEPLOY POSITION

CASCADE

BLOCKER DOOR (OPEN)

LEFT TRANSLATING SLEEVE

INLET AIR

T/R STOW POSITION

FOR TRAINING PURPOSES ONLY!

B737-- 600/700/800/900

One Stop Airline MRO Support Pvt. Ltd

Translating Sleeves

ATA 71--80 Engine

Page 333

OSA MRO Support Pvt. Ltd

POWER PLANT

One Stop Airline MRO Support Pvt. Ltd

Thrust Reverser System The T/R system changes the direction of the fan air exhaust to help decrease the speed of the airplane after landing or during a rejected takeoff (RTO). The T/R system has two thrust reversers. T/R 1 is the thrust reverser for engine 1 (Left). T/R 2 is the thrust reverser for engine 2 (right). Each T/R has a left and right half. Each half has a translating sleeve which moves aft for reverse thrust. The sleeves work at the same time, but are independent from each other. Three hydraulic actuators move each sleeve. Rotary flex shafts make sure that the hydraulic actuators extend and retract at the same rate.

71-- 80

The T/R indicating system supplies these indications in the flight compartment: S REV message on common display system (CDS) S REVERSER light on the P5 aft overhead panel S Linear variable differential transformer (LVDT) data on the control display unit (CDU). The common display system (CDS) shows the REV message. This message refers to the positions of a T/R’s translating sleeves. Each T/R has LVDTs which supply translating sleeve position data to the electronic engine control (EEC). When on, the REVERSER light shows that there is a failure in one of these areas: S T/R control system S Mechanical failure which prevents the control system from correct operation. The REVERSER light comes on for 10 seconds during a T/R stow operation. The light will stay on if the T/R does not stow in l0 seconds. The EAU controls this light.

FOR TRAINING PURPOSES ONLY!

T/R Control System The T/R control system lets you deploy the T/R when the airplane is less than 10 feet (3 meters) from the ground. You give a deploy signal to the control system when you raise a reverse thrust Lever. You supply a stow signal when you return the reverse thrust lever to the stow position. The T/R control valve module controls hydraulic power to the hydraulic actuators. The reverse thrust lever operates the switches necessary to send a deploy or stow signal to the T/R control valve module. The sync locks prevent the operation of the hydraulic actuators when there is no deploy signal. The primary purpose of the engine accessory unit (EAU) is to control the T/R stow operation. The EAU supplies front panel built-in-test equipment (BITE) to help you do trouble shooting of the control system. The EAU uses two T/R proximity sensors for each translating sleeve for control. The EAU also interfaces with the T/R indicating system to control the REVERSER light.

B737-- 600/700/800/900

FRA US/E GiM

Mai 10, 2006

ATA 71--80 Engine

Page 334

OSA MRO Support Pvt. Ltd

POWER PLANT

B737-- 600/700/800/900

One Stop Airline MRO Support Pvt. Ltd

71-- 80

DEPLOY SYSTEM A OR STANDBY HYDRAULIC POWER

TO RIGHT T/R HALF STOW

PROXIMITY SENSORS (2)

REVERSE THRUST LEVER DEPLOY

LVDT

DEPLOY

T/R 1 CTRL SW

P18

SYNC LOCK

STOW

28 VDC STANDBY BUS

ARM

ARM

T/R 1 CONTROL VALVE MODULE

ENG 1 FIRE SW

EAU

EEC

ARM (STOW) STOW

STOW

DEU FOR TRAINING PURPOSES ONLY!

ARM (DEPLOY)

SYNC LOCK

SYNC LOCK

CDU

DEPLOY

FCC (2) REV

SYNC LOCK (POWER) L AUTOTHROTTLE SWITCH PACK

67.7

10

0 8

SYNC LOCK (POWER)

REVERSER A

NOTE: T/R 1 IS SHOWN. T/R 2 IS ALMOST THE SAME.

MISC EQUIP PANEL (J22)

Figure 169 FRA US/E GiM

Mai 10, 2006

AFT P5

6

2 4

N

1

CDS DISPLAY UNIT

System Schematic

ATA 71--80 Engine

Page 335

OSA MRO Support Pvt. Ltd

POWER PLANT

ATA 77

One Stop Airline MRO Support Pvt. Ltd

B737-- 600/700/800/900 71-- 80

ENGINE INDICATING

The engine indicating system shows these parameters for each engine: S Low pressure rotor speed (N1) S High pressure rotor speed (N2) S Exhaust gas temperature (EGT) S Engine vibration.

FOR TRAINING PURPOSES ONLY!

Electronic Engine Control The electronic engine control (EEC) receives an analog input from these engine sensors: S N1 speed sensor S N2 speed sensor S EGT probes (T49.5). The EEC changes the analog signals to digital signals. The EEC sends the digital signals on an ARINC 429 data bus to the common display system (CDS) display electronics units (DEU)s. Airborne Vibration Monitoring Signal Conditioner The airborne vibration monitoring (AVM) signal conditioner calculates and monitors vibration levels of each engine. The AVM signal conditioner receives analog input from these engine sensors: S N1 speed sensor S N2 speed sensor S Number 1 bearing vibration sensor, or S Fan frame compressor case vertical vibration (FFCCV) sensor. The DEUs and the flight data acquisition unit (FDAU) receive AVM information through an ARINC 429 data bus. DEUs The DEUs use input from the engine indicating system to show engine parameters on the CDS.

FRA US/E GiM

Mai 10, 2006

ATA 71--80 Engine

Page 336

OSA MRO Support Pvt. Ltd

POWER PLANT

One Stop Airline MRO Support Pvt. Ltd

B737-- 600/700/800/900 71-- 80

EEC

NO. 1 BEARING VIB SENSOR N2 SPEED SENSOR

FOR TRAINING PURPOSES ONLY!

N1 SPEED SENSOR

DEU 1

Mai 10, 2006

FFCCV SENSOR

DEU 2

AVM SIGNAL CONDITIONER

Figure 170 FRA US/E GiM

T49.5 (EGT)

FDAU

General Schematic

ATA 71--80 Engine

Page 337

OSA MRO Support Pvt. Ltd FOR TRAINING PURPOSES ONLY!

POWER PLANT

One Stop Airline MRO Support Pvt. Ltd

B737-- 600/700/800/900 71-- 80

ENGINE DISPLAY CONFIG 1 The upper center display unit usually shows these indications: S N1 rotor speed S EGT S N2 rotor speed S Engine vibration The display unit can also show these indications: S Thrust reverser message S Engine inlet cowl thermal anti-ice on S Autothrottle limit S Autothrottle mode S N1 reference S Engine fail message S Cross bleed start message S Start control valve open S Engine oil filter bypass S Engine low oil pressure. S Fuel flow or fuel used S Fuel quantity S Total air temperature S Engine oil pressure S Engine oil temperature S Engine oil quantity S Hydraulic pressure S Hydraulic quantity. Refer to the applicable chapters for more information about these indications. The lower center and inboard display units can also show this information.

FRA US/E GiM

Mai 10, 2006

ATA 71--80 Engine

Page 338

OSA MRO Support Pvt. Ltd

POWER PLANT

B737-- 600/700/800/900

One Stop Airline MRO Support Pvt. Ltd

90.0

N1 ROTOR SPEED

90.0

20.0

10

20.0

10 0

8 6 EXHAUST GAS TEMPERATURE (EGT)

0 8

2 4

71-- 80

6 N1

2 4

100

50

100

50

0

0

583

583

OIL P 200

EGT

200

100

100

N2 ROTOR SPEED 60.0

0

60.0

0 OIL T

96 N2

2

0.87

6

0.87

6

0 4

2

4

0

FF/FU LB X 1000

A 3

CTR 1 8 500

1

AIRBORNE VIBRATION MONITORING (AVM)

5

B 3

4

2

2 2 800

4

0

VIB

2

3

1

5

4 2

FOR TRAINING PURPOSES ONLY!

3

1

0

96

OIL Q %

2

0 HYD P

4

1

0

8 500 100

FUEL LB

HYD Q %

100

COMMON DISPLAY SYSTEM DISPLAY UNIT

Figure 171 FRA US/E GiM

Mai 10, 2006

Engine Display

ATA 71--80 Engine

Page 339

One Stop Airline MRO Support Pvt. Ltd

B737-- 600/700/800/900 71-- 80

ENGINE DISPLAY CONFIG 2 The CDS usually shows engine data on two display units. One display unit shows the primary engine display and the other shows the secondary engine display. The primary engine display usually shows on the upper center display unit (DU). The secondary engine display usually shows on the lower center DU. Engine data can also show on the inboard display units

FOR TRAINING PURPOSES ONLY!

OSA MRO Support Pvt. Ltd

POWER PLANT

FRA US/E GiM

Mai 10, 2006

ATA 71--80 Engine

Page 340

OSA MRO Support Pvt. Ltd

POWER PLANT

B737-- 600/700/800/900

One Stop Airline MRO Support Pvt. Ltd

71-- 80

N1 ROTOR SPEED

TAT +19c

10

ENG 1 75.0

75.0

21.0

21.0

10

0 8 6

N2 ROTOR SPEED

ENG 2

61.0

0 8

2

6

4

N2

2 4

N1

500

61.0

5.90 500

EXHAUST GAS TEMPERATURE (EGT)

36

EGT

FF OIL PRESS

129

OIL TEMP

20

OIL QTY

1.6

VIB

5.99

36

130

20

CTR

14 1

FOR TRAINING PURPOSES ONLY!

8 760

AIRBORNE VIBRATION MONITORING (AVM)

890

FUEL LB

8 760

COMMON DISPLAY SYSTEM UPPER CENTER DISPLAY UNIT (PRIMARY ENGINE DISPLAY)

COMMON DISPLAY SYSTEM LOWER CENTER DISPLAY UNIT (SECONDARY ENGINE DISPLAY)

Figure 172 FRA US/E GiM

Mai 10, 2006

1.6 4.5

2

Engine Indication Config. 2 ATA 71--80 Engine

Page 341

OSA MRO Support Pvt. Ltd

POWER PLANT

One Stop Airline MRO Support Pvt. Ltd

B737-- 600/700/800/900 71-- 80

EEC-BITE General The EEC built--in test equipment (BITE) stores engine information in non--volatile memory and lets the mechanic do ground tests. You get the information from the EEC BITE memory and do the ground tests with the flight management computer (FMC) control display unit (CDU). You select the data or test with the CDU. The FMC CDU sends a signal to the EEC through the display electronic unit (DEU) on a ARINC 429 data bus. The EEC returns the requested data or test results to the FMC CDU through the DEU. These are the types of data that the EEC stores: S RECENT FAULTS (faults that occurred during the last 3 flight legs) S FAULT HISTORY (faults that occurred during the last 10 flight legs) S IDENT/CONFIG (engine identification and configuration data) S INPUT MONITORING (data sent to the EEC by engine and airplane sensors). EEC BITE can do several ground tests. The ground test let the mechanic find engine system problems and make sure maintenance action corrected the problem.

FOR TRAINING PURPOSES ONLY!

Training Information Point You use the fault isolation manual (FIM) to interpret engine faults that show on the CDU. You use part II of the maintenance manual to do the engine ground tests.

FRA US/E GiM

Mai 10, 2006

ATA 71--80 Engine

Page 342

OSA MRO Support Pvt. Ltd

POWER PLANT

B737-- 600/700/800/900

One Stop Airline MRO Support Pvt. Ltd

71-- 80

ENGINE 1 BITE TEST MAIN MENU

1/1

< RECENT FAULTS < FAULT HISTORY < INDENT/CONFIG < GROUND TESTS < INPUT MONITORING < INDEX

FOR TRAINING PURPOSES ONLY!

DEU

INIT REF

RTE

CLB

CRZ

DIR INTC

LEGS

DEP ARR

HOLD PROG EXEC

N1 LIMIT

FIX

BRT

DES

A

B

C

D

E

PREV NEXT PAGE PAGE

F

G

H

I

J

1

2

3

K

L

M

N

O

4

5

6

P

Q

R

S

T

7

8

9

U

V

W

X

Y

0

+/ --

Z

DEL

/

CLR

EEC

CDU

Figure 173 FRA US/E GiM

Mai 10, 2006

EEC BITE General

ATA 71--80 Engine

Page 343

One Stop Airline MRO Support Pvt. Ltd

OSA B737--6 GEN FAM

TABLE OF CONTENTS GENERAL FAMILIARIZATION . . . . . . . . . . . . . . .

1

GENERAL DESCRIPTION . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . GROUND OPERATIONS . . . . . . . . . . . . . . . . . . . . . . . . . . MAINTENANCE DOCUMENTS - INTRODUCTION . . . .

2 8 10

ATA 24 ELECTRICAL POWER . . . . . . . . . . . . . . POWER AND CONTROL . . . . . . . . . . . . . . . . . . . . . . . . . . EL. METERS, BATTERY & GALLEY POWER MODULE GENERATOR DRIVE AND STBY POWER MODULE . . AC SYSTEMS, GENERATOR AND APU MODULE . . . . GENERATOR DRIVE - GENERAL DESCRIPTION . . . .

14 14 16 20 22 26

ATA 26 FIRE PROTECTION - GENERAL . . . . .

28

FIRE PROTECTION - INTRODUCTION . . . . . . . . . . . . . FIRE PROTECTION - FIRE ALARMS . . . . . . . . . . . . . . . ENGINE FIRE EXTINGUISHING . . . . . . . . . . . . . . . . . . . . APU FIRE EXTINGUISHING . . . . . . . . . . . . . . . . . . . . . . . 26--14 LAVATORY SMOKE DETECTION . . . . . . . . . . . . . LAVATORY SMOKE DETECTION - GENERAL DESCRIPTION . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . WHEEL WELL OVERHEAT DETECTION - INTRO . . . . GENERAL DESCRIPTION . . . . . . . . . . . . . . . . . . . . . . . . . WING AND BODY OVERHEAT DET.- INTRO . . . . . . . . CARGO COMP. SMOKE DETECTION - INTRO . . . . . . . GENERAL DESCRIPTION . . . . . . . . . . . . . . . . . . . . . . . . . LAV FIRE EXTING BOTTLE AND TEMP INDICATOR . PORTABLE FIRE EXTINGUISHING . . . . . . . . . . . . . . . . .

28 30 32 34 36 38 40 42 44 46 48 50 52

ATA 30 ICE AND RAIN PROTECTION . . . . . . . .

54

ICE AND RAIN PROTECTION - GEN. DESCRIPTION .

54

OSA

NN

Jul 3, 2007

PITOT AND STATIC - CONTROL PANEL . . . . . . . . . . . . CABIN WINDOW ANTI-ICING (CWAI) INTRO . . . . . . . WINDSHIELD WIPER SYSTEM . . . . . . . . . . . . . . . . . . . .

56 58 60

30--43 RAIN REPELLENT SYSTEM . . . . . . . . . . . . . . . . . . . . . . . . . . . . HYDROPHOBIC WINDSHIELD COATING . . . . . . . . . . .

62 62

30--10

WING THERMAL ANTI-ICING SYSTEM . . . . . . . . . . . . .

64

30--20

INLET COWL ANTI-ICING SYSTEM . . . . . . . . . . . . . . . .

66

ATA 31 INSTRUMENTS . . . . . . . . . . . . . . . . . . . .

68

CLOCKS - GENERAL DESCRIPTION . . . . . . . . . . . . . . . INTRODUCTION . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . FDRS - GENERAL DESCRIPTION . . . . . . . . . . . . . . . . . . FDRS - COMPONENT LOCATION FLT. COMPT . . . . . . AURAL WARNING SYSTEM - GENERAL DESCRIPTION . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . MASTER CAUTION SYSTEM - INTRODUCTION . . . . . MASTER CAUTION SYSTEM - GENERAL DESCRIPTION . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . TAKEOFF WARNING . . . . . . . . . . . . . . . . . . . . . . . . . . . . . COMMON DISPLAY SYSTEM . . . . . . . . . . . . . . . . . . . . . . CDS - GENERAL DESCRIPTION . . . . . . . . . . . . . . . . . . .

68 70 72 74

ATA 33 LIGHTS . . . . . . . . . . . . . . . . . . . . . . . . . . . .

88

FLIGHT COMPARTMENT LIGHTING - INTRO . . . . . . . CARGO AND SERVICE COMPARTMENT - INTRO . . . EMERGENCY LIGHTING - INTRODUCTION . . . . . . . . .

88 90 94

ATA 23 COMMUNICATION . . . . . . . . . . . . . . . . . .

96

FLIGHT INTERPHONE SYSTEM . . . . . . . . . . . . . . . . . . . FLIGHT INTERPHONE - GENERAL DESCRIPTION . . FLIGHT INTERPHONE - AUDIO CONTROL PANEL . . .

96 98 100

76 78 80 82 84 86

Page i

One Stop Airline MRO Support Pvt. Ltd

OSA B737--6 GEN FAM

TABLE OF CONTENTS FLIGHT INTERPHONE FLIGHT COMP. LOCATIONS . SERVICE INTERPHONE SYSTEM . . . . . . . . . . . . . . . . . . SERVICE INTERPHONE - GEN. DESCRIPTION . . . . . FLIGHT CREW CALL / CABIN INTERPHONE . . . . . . . . PASSENGER ADDRESS - INTRODUCTION . . . . . . . . . VERY HIGH FREQUENCY SYSTEM -- INTRO . . . . . . . VHF - GENERAL DESCRIPTION . . . . . . . . . . . . . . . . . . . ACARS -- INTRODUCTION . . . . . . . . . . . . . . . . . . . . . . . . ACARS - GENERAL DESCRIPTION . . . . . . . . . . . . . . . . ACARS - OPERATION . . . . . . . . . . . . . . . . . . . . . . . . . . . . EMERGENCY LOCATOR TRANSMITTER - INTRO . . . ELT - GENERAL DESCRIPTION . . . . . . . . . . . . . . . . . . . . HIGH FREQUENCY COMMUNICATION -- INTRO . . . . HF -- GENERAL DESCRIPTION . . . . . . . . . . . . . . . . . . . . SELECTIVE CALLING SYSTEM -- INTRODUCTION . . SELCAL - GENERAL DESCRIPTION . . . . . . . . . . . . . . . . VOICE RECORDER SYSTEM -- INTRODUCTION . . . . VOICE RECORDER - GENERAL DESCRIPTION . . . . . PES / AUDIO -- INTRODUCTION . . . . . . . . . . . . . . . . . . . PES--AUDIO / GENERAL DESCRIPTION . . . . . . . . . . . . PES - VIDEO -- INTRODUCTION . . . . . . . . . . . . . . . . . . . PES - VIDEO - GENERAL DESCRIPTION . . . . . . . . . . . OPERATION OF THE VSCU . . . . . . . . . . . . . . . . . . . . . .

102 104 106 108 110 112 114 116 118 120 122 124 126 128 130 132 134 134 136 138 140 142 144

ATA 34 NAVIGATION . . . . . . . . . . . . . . . . . . . . . . .

146

STATIC AND TOTAL AIR PRESSURE SYSTEM . . . . . . AIR DATA - INERTIAL REFERENCE SYSTEM . . . . . . . ADIRS - ALIGNMENT PROCEDURE 1 . . . . . . . . . . . . . . ADIRS - LAST PRESENT POSITION ENTRY ON CDU CDS - PFD - OVERVIEW (AIR DATA - IRS DATA) . . . . . INSTRUMENT LANDING SYSTEM (ILS) . . . . . . . . . . . . . ILS - GENERAL DESCRIPTION . . . . . . . . . . . . . . . . . . . . CDS - PFD - OVERVIEW . . . . . . . . . . . . . . . . . . . . . . . . . .

146 148 150 150 152 154 156 158

OSA

NN

Jul 3, 2007

ND - CENTERED APPROACH . . . . . . . . . . . . . . . . . . . . . VHF OMNIDIRECTIONAL RANGING (VOR) SYSTEM . VOR SYSTEM - GENERAL DESCRIPTION . . . . . . . . . . ND - CENTERED VOR . . . . . . . . . . . . . . . . . . . . . . . . . . . . MARKER BEACON SYSTEM - INTRODUCTION . . . . . MARKER SYSTEM - GENERAL DESCRIPTION . . . . . . PFD - OVERVIEW - MARKER BEACON INDICATIONS DISTANCE MEASURING EQUIPMENT . . . . . . . . . . . . . . DME SYSTEM - GENERAL DESCRIPTION . . . . . . . . . . ND - CENTERED APPROACH - DME INDICATION . . . AUTOMATIC DIRECTION FINDER SYSTEM INTRODUCTION . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . ADF SYSTEM - GENERAL DESCRIPTION . . . . . . . . . . RADIO ALTIMETER SYSTEM — INTRODUCTION . . . RA SYSTEM - GENERAL DESCRIPTION . . . . . . . . . . . . PFD - INDICATION - RADIO ALTITUDE . . . . . . . . . . . . . AIR TRAFFIC CONTROL SYSTEM - INTRODUCTION ATC SYSTEM - GENERAL DESCRIPTION . . . . . . . . . . . TRAFFIC ALERT AND COLLISION AVOIDANCE SYSTEM (TCAS) . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . TCAS - GENERAL DESCRIPTION . . . . . . . . . . . . . . . . . . TCAS - NAVIGATION DISPLAY . . . . . . . . . . . . . . . . . . . . . TCAS - ATTITUDE INDICATOR DISPLAY . . . . . . . . . . . . WEATHER RADAR SYSTEM . . . . . . . . . . . . . . . . . . . . . . . WXR SYSTEM - GENERAL DESCRIPTION . . . . . . . . . . EGPWS INTRODUCTION . . . . . . . . . . . . . . . . . . . . . . . . . EGPWS GENERAL DESCRIPTION . . . . . . . . . . . . . . . . . GLOBAL POSITIONING SYSTEM (GPS) . . . . . . . . . . . . GPS - GENERAL DESCRIPTION . . . . . . . . . . . . . . . . . . .

160 162 162 164 166 166 168 170 170 172

ATA 22 AUTOFLIGHT . . . . . . . . . . . . . . . . . . . . . .

202

DIGITAL FLIGHT CONTROL SYSTEM INTRODUCTION . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . DFCS - MCP DESCRIPTION . . . . . . . . . . . . . . . . . . . . . . .

202 204

174 174 176 176 178 180 182 184 186 188 190 192 194 196 198 200 200

Page ii

One Stop Airline MRO Support Pvt. Ltd

OSA B737--6 GEN FAM

TABLE OF CONTENTS DFCS - GENERAL DESCRIPTION . . . . . . . . . . . . . . . . . . AUTOTHROTTLE SYSTEM - INTODUCTION . . . . . . . . A/T SYSTEM - OPERATION, OVERVIEW . . . . . . . . . . .

206 210 212

ATA 51--57 STRU CTURE . . . . . . . . . . . . . . . . . . . . . . . . . . . . 214 BASIC STRUCTURAL DESCRIPTION . . . . . . . . . . . . . . .

214

ATA 52 DOORS . . . . . . . . . . . . . . . . . . . . . . . . . . . .

216

DOOR LOCATION . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .

216

ATA 25 EQUIPMENT AND FURNISHINGS . . . .

218

DOOR MOUNTED ESCAPE SLIDES . . . . . . . . . . . . . . . . INTRODUCTION . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . PASSENGER COMPARTMENT . . . . . . . . . . . . . . . . . . . . CABIN ATTENDANT STATIONS . . . . . . . . . . . . . . . . . . . .

218 220 222 224

ATA 35 OXYGEN . . . . . . . . . . . . . . . . . . . . . . . . . .

226

OXYGEN SYSTEM INTRODUCTION . . . . . . . . . . . . . . . PASSENGER OXYGEN SYSTEM . . . . . . . . . . . . . . . . . . .

226 228

ATA 38 WATER AND WASTE . . . . . . . . . . . . . . .

230

POTABLE WATER -- INTRODUCTION . . . . . . . . . . . . . . . VACUUM WASTE SYSTEM . . . . . . . . . . . . . . . . . . . . . . . .

230 232

ATA 28 FUEL . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .

234

FUEL STORAGE . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .

234

OSA

NN

Jul 3, 2007

PRESSURE REFUEL SYSTEM . . . . . . . . . . . . . . . . . . . . . FUEL VENT SYSTEM . . . . . . . . . . . . . . . . . . . . . . . . . . . . DEFUEL -- SYSTEM . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . FUEL SYSTEM CONTROL . . . . . . . . . . . . . . . . . . . . . . . . . ENGINE FUEL FEED SYSTEM . . . . . . . . . . . . . . . . . . . . . FUEL INDICATING SYSTEM . . . . . . . . . . . . . . . . . . . . . . .

236 238 240 242 244 246

ATA 29 HYDRAULIC . . . . . . . . . . . . . . . . . . . . . . .

248

HYD INDICATING SYSTEM . . . . . . . . . . . . . . . . . . . . . . . .

250

ATA 27 FLIGHT CONTROL . . . . . . . . . . . . . . . . .

252

GENERAL . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . AILERON SYSTEM FUNCTIONAL . . . . . . . . . . . . . . . . . . SPOILER SYSTEM AND SPEEDBRAKES . . . . . . . . . . . PITCH CONTROL . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . ELEVATOR CONTROL . . . . . . . . . . . . . . . . . . . . . . . . . . . . RUDDER (YAW) CONTROL . . . . . . . . . . . . . . . . . . . . . . . . HIGH LIFT DEVICES . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . FLIGHT CONTROL PANEL . . . . . . . . . . . . . . . . . . . . . . . . CENTER PANEL . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . CENTER CONTROL STAND . . . . . . . . . . . . . . . . . . . . . . .

252 254 256 258 260 262 264 268 270 272

ATA 32 LANDING GEAR . . . . . . . . . . . . . . . . . . .

274

MAIN GEAR . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . BRAKE SYSTEM . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . INDICATION . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .

274 276 278

ATA 36 PNEUMATIC . . . . . . . . . . . . . . . . . . . . . . .

280

GENERAL . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . PNEUMATIC SYSTEM DESCRIPTION . . . . . . . . . . . . . .

280 282 Page iii

One Stop Airline MRO Support Pvt. Ltd

OSA B737--6 GEN FAM

TABLE OF CONTENTS PNEUMATIC PANEL DESCRIPTION . . . . . . . . . . . . . . . .

284

ATA 73 ENGINE CONTROLS . . . . . . . . . . . . . . .

322

ATA 21 AIR CONDITIONING . . . . . . . . . . . . . . . .

286

ENGINE FUEL AND CONTROL - DISTRIBUTION . . . . ENGINE THRUST CONTROL . . . . . . . . . . . . . . . . . . . . . .

324 326

AIR COND SYSTEM DESCRIPTION . . . . . . . . . . . . . . . OVERHEAD PANEL DESCRIPTION . . . . . . . . . . . . . . . . EQUIPMENT COOLING SYSTEM . . . . . . . . . . . . . . . . . . COOLING - FUNCTIONAL DESCRIPTION . . . . . . . . . . . PNEUMATIC CONTROL PANEL . . . . . . . . . . . . . . . . . . . . PRESSURIZATION CONTROL . . . . . . . . . . . . . . . . . . . . . PRESSURIZATION CONTROL - GENERAL DESCRIPTION . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . PRESSURIZATION CONTROL MODULE . . . . . . . . . . . . GENERAL DESCRIPTION . . . . . . . . . . . . . . . . . . . . . . . . . INDICATION & CONTROLS . . . . . . . . . . . . . . . . . . . . . . . . APU LUBRICATION SYSTEM . . . . . . . . . . . . . . . . . . . . . . APU FUEL SYSTEM . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . APU PNEUMATIC SYSTEM . . . . . . . . . . . . . . . . . . . . . . . . IGNITION AND START SYSTEM . . . . . . . . . . . . . . . . . . .

286 288 290 292 294 296

ATA 75 ENGINE AIR . . . . . . . . . . . . . . . . . . . . . . .

328

ATA 74 IGNITION . . . . . . . . . . . . . . . . . . . . . . . . . .

330

ATA 78 THRUST REVERSER SYSTEM . . . . . .

332

ATA 77 ENGINE INDICATING . . . . . . . . . . . . . . .

336

ENGINE DISPLAY CONFIG 1 . . . . . . . . . . . . . . . . . . . . . . ENGINE DISPLAY CONFIG 2 . . . . . . . . . . . . . . . . . . . . . . EEC-BITE . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .

338 340 342

ATA 71 POWER PLANT . . . . . . . . . . . . . . . . . . . .

314

ENGINE — INTRODUCTION . . . . . . . . . . . . . . . . . . . . . . .

314

ATA 72 ENGINE . . . . . . . . . . . . . . . . . . . . . . . . . . .

316

GENERAL DESCRIPTION . . . . . . . . . . . . . . . . . . . . . . . . . FADEC SYSTEM INTRODUCTION . . . . . . . . . . . . . . . . .

316 318

ATA 79 OIL . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .

320

ENGINE OIL SYSTEM . . . . . . . . . . . . . . . . . . . . . . . . . . . .

320

OSA

NN

Jul 3, 2007

298 300 302 304 306 308 310 312

Page iv

One Stop Airline MRO Support Pvt. Ltd

OSA B737--6 GEN FAM

TABLE OF FIGURES Figure Figure Figure Figure Figure Figure Figure Figure Figure Figure Figure Figure Figure Figure Figure Figure Figure Figure Figure Figure Figure Figure Figure Figure Figure Figure Figure Figure Figure Figure Figure Figure Figure Figure Figure OSA

1 2 3 4 5 6 7 8 9 10 11 12 13 14 15 16 17 18 19 20 21 22 23 24 25 26 27 28 29 30 31 32 33 34 35

Dimension . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . Aircraft Data . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . FLIGHT DECK PANEL - FRONT VIEW . . . . . . . . . . . . . . . . . . . FLIGHT DECK PANEL - PEDESTAL . . . . . . . . . . . . . . . . . . . . . FLIGHT DECK PANEL - OVERHEAD . . . . . . . . . . . . . . . . . . . . Servicing . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . MAINT. DOCUMENTS - INTRODUCTION . . . . . . . . . . . . . . . . MAINT. DOCUMENTS - MAINTENANCE . . . . . . . . . . . . . . . . . POWER / CONTROL - GEN. DESCRIPTION . . . . . . . . . . . . . EL. METERS / BATTERY / GALLEY PWR MODULE . . . . . . EL. METERS / BATTERY / GALLEY PWR MODULE . . . . . . GEN. DRIVE / STBY POWER MODULE . . . . . . . . . . . . . . . . AC SYSTEMS / GENERATOR / APU MODULE . . . . . . . . . . AC SYSTEMS / GENERATOR / APU MODULE . . . . . . . . . . GENERATOR DRIVE - GENERAL . . . . . . . . . . . . . . . . . . . . . . FIRE PROTECTION - INTRODUCTION . . . . . . . . . . . . . . . . . Engine and APU Fire Warning . . . . . . . . . . . . . . . . . . . . . . . . . . ENGINE FIRE EXTINGUISHING - INTRODUCTION . . . . . . APU FIRE EXT. - GEN. DESCR. . . . . . . . . . . . . . . . . . . . . . . . LAV. SMOKE DET. - INTRO . . . . . . . . . . . . . . . . . . . . . . . . . . . LAV. SMOKE DET. - GEN. DESCRIPTION . . . . . . . . . . . . . . . WHEEL WELL OVERHEAT DET. - INTRO . . . . . . . . . . . . . . . WW-FIRE WARNING - GENERAL. DESCR. . . . . . . . . . . . . . WING & BODY OVERHEAT DET.- INTRO . . . . . . . . . . . . . . . CARGO SMOKE DET. - INTRO . . . . . . . . . . . . . . . . . . . . . . . . CARGO SMOKE DET. - GENERAL DESCR. . . . . . . . . . . . . . LAVATORY FIRE EXT. - BOTTLE AND TEMP-INDIC. . . . . . PORTABLE FIRE EXT. . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . ICE & RAIN - GENERAL DESCRIPTION . . . . . . . . . . . . . . . . PITOT AND STATIC - CONTROL PNL . . . . . . . . . . . . . . . . . . CWAI SYSTEM - INTRODUCTION . . . . . . . . . . . . . . . . . . . . . WINDSHIELD WIPER - INTRO . . . . . . . . . . . . . . . . . . . . . . . . HYDROPHOBIC WINDSHIELD COATING . . . . . . . . . . . . . . . Wing Anti Ice System Schematic . . . . . . . . . . . . . . . . . . . . . . . ICAI System Schematic . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . NN

Jul 3, 2007

3 4 5 6 7 9 11 13 15 17 19 21 23 25 27 29 31 33 35 37 39 41 43 45 47 49 51 53 55 57 59 61 63 65 67

Figure Figure Figure Figure Figure Figure Figure Figure Figure Figure Figure Figure Figure Figure Figure Figure Figure Figure Figure Figure Figure Figure Figure Figure Figure Figure Figure Figure Figure Figure Figure Figure Figure Figure Figure

36 37 38 39 40 41 42 43 44 45 46 47 48 49 50 51 52 53 54 55 56 57 58 59 60 61 62 63 64 65 66 67 68 69 70

Clocks - General, Location . . . . . . . . . . . . . . . . . . . . . . . . . . . . . FDRS - INTRODUCTION . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . FDRS - GENERAL DESCRIPTION . . . . . . . . . . . . . . . . . . . . . FLIGHT COMP. - LOCATION . . . . . . . . . . . . . . . . . . . . . . . . . . AURAL WARNING - GENERAL . . . . . . . . . . . . . . . . . . . . . . . . MASTER CAUTION - GENERAL . . . . . . . . . . . . . . . . . . . . . . . MASTER CAUTION - BASIC INTRODUCTION . . . . . . . . . . . LANDG. WARNING - GENERAL . . . . . . . . . . . . . . . . . . . . . . . COMMON DISPL. SYSTEM - GENERAL . . . . . . . . . . . . . . . . COMMON DISPL. SYSTEM - GEN. DESCR. . . . . . . . . . . . . FLIGHT COMP. LIGHTING - INTRO . . . . . . . . . . . . . . . . . . . . CARGO & SERVICE COMP. LIGHTING - INTRO . . . . . . . . . EXTERIOR LIGHTING - INTRO . . . . . . . . . . . . . . . . . . . . . . . . EMERGENCY LIGHTING - INTRO . . . . . . . . . . . . . . . . . . . . . FLIGHT INTERPHONE - INTRODUCTION . . . . . . . . . . . . . . FLIGHT INTERPHONE - GEN. DESCRIPTION . . . . . . . . . . FLIGHT INTERPHONE - ACP . . . . . . . . . . . . . . . . . . . . . . . . . FLIGHT INTERPHONE - COMP. LOC. . . . . . . . . . . . . . . . . . . SERVICE INTERPHONE - INTRODUCTION . . . . . . . . . . . . . SERVICE INTERPHONE - GEN. DESCRIPTION . . . . . . . . . FLIGHT CREW CALL - GEN. DESCRIPTION . . . . . . . . . . . . PA - DESCRIPTION . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . VHF - INTRODUCTION . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . VHF - GENERAL DESCRIPTION . . . . . . . . . . . . . . . . . . . . . . . ACARS - INTRODUCTION . . . . . . . . . . . . . . . . . . . . . . . . . . . . ACARS - DESCRIPTION . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . ACARS - OPERATION – MCDU . . . . . . . . . . . . . . . . . . . . . . . . ELT - INTRODUCTION . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . ELT - DESCRIPTION . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . HF - INTRODUCTION . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . HF - GEN. DESCRIPTION . . . . . . . . . . . . . . . . . . . . . . . . . . . . . SELCAL - INTRODUCTION . . . . . . . . . . . . . . . . . . . . . . . . . . . SELCAL - GENERAL DESCR. . . . . . . . . . . . . . . . . . . . . . . . . . VOICE RECORDER - DESCRIPTION . . . . . . . . . . . . . . . . . . . PES-AUDIO - INTRODUCTION . . . . . . . . . . . . . . . . . . . . . . . .

69 71 73 75 77 79 81 83 85 87 89 91 93 95 97 99 101 103 105 107 109 111 113 115 117 119 121 123 125 127 129 131 133 135 137

Page v

One Stop Airline MRO Support Pvt. Ltd

OSA B737--6 GEN FAM

TABLE OF FIGURES Figure Figure Figure Figure Figure Figure Figure Figure Figure Figure Figure Figure Figure Figure Figure Figure Figure Figure Figure Figure Figure Figure Figure Figure Figure Figure Figure Figure Figure Figure Figure Figure Figure Figure Figure OSA

71 72 73 74 75 76 77 78 79 80 81 82 83 84 85 86 87 88 89 90 91 92 93 94 95 96 97 98 99 100 101 102 103 104 105

PES / AUDIO - DESCRIPTION . . . . . . . . . . . . . . . . . . . . . . . . . PES / VIDEO - INTRODUCTION . . . . . . . . . . . . . . . . . . . . . . . PES / VIDEO - DESCRIPTION . . . . . . . . . . . . . . . . . . . . . . . . . VSCU - OPERATION . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . PITOT, STATIC INTRODUCTION . . . . . . . . . . . . . . . . . . . . . . . ADIRS GENERAL DESCRIPTION . . . . . . . . . . . . . . . . . . . . . . IRS ALIGN - MCDU POS. ENTRY . . . . . . . . . . . . . . . . . . . . . . PFD - OVERVIEW (IRS / AIR DATA) . . . . . . . . . . . . . . . . . . . . ILS INTRODUCTION . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . GEN. DESCRIPTION . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . PFD - OVERVIEW . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . ND - CENTERED APPROACH . . . . . . . . . . . . . . . . . . . . . . . . . VOR GENERAL DESCRIPTION . . . . . . . . . . . . . . . . . . . . . . . . ND - CENTERED VOR . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . MARKER GENERAL DESCRIPTION . . . . . . . . . . . . . . . . . . . PFD - OVERVIEW . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . DME GENERAL . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . ND - CENTERED APPROACH . . . . . . . . . . . . . . . . . . . . . . . . . ADF GENERAL DESCRIPTION . . . . . . . . . . . . . . . . . . . . . . . . GEN. SCHEMATIC . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . PFD - OVERVIEW . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . ATC INTRODUCTION . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . ATC GENERAL DESCRIPTION . . . . . . . . . . . . . . . . . . . . . . . . TCAS INTRODUCTION . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . TCAS GERERAL DESCRIPTION . . . . . . . . . . . . . . . . . . . . . . . TCAS - NAVIGATION DISPLAY . . . . . . . . . . . . . . . . . . . . . . . . TCAS - ATTITUDE INDICATOR DISPLAY . . . . . . . . . . . . . . . WXR - GENERAL . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . WXR - GENERAL DESCRIPTION . . . . . . . . . . . . . . . . . . . . . . EGPWS INTRODUCTION . . . . . . . . . . . . . . . . . . . . . . . . . . . . EGPWS - GENERAL DESCRIPTION . . . . . . . . . . . . . . . . . . GPS GENERAL DESCRIPTION . . . . . . . . . . . . . . . . . . . . . . . DFCS - INTRODUCTION . . . . . . . . . . . . . . . . . . . . . . . . . . . . . DFCS MCP - GENERAL DESCRIPTION . . . . . . . . . . . . . . . DFCS - GENERAL DESCRIPRION . . . . . . . . . . . . . . . . . . . . NN

Jul 3, 2007

139 141 143 145 147 149 151 153 155 157 159 161 163 165 167 169 171 173 175 177 179 181 183 185 187 189 191 193 195 197 199 201 203 205 207

Figure Figure Figure Figure Figure Figure Figure Figure Figure Figure Figure Figure Figure Figure Figure Figure Figure Figure Figure Figure Figure Figure Figure Figure Figure Figure Figure Figure Figure Figure Figure Figure Figure Figure Figure

106 107 108 109 110 111 112 113 114 115 116 117 118 119 120 121 122 123 124 125 126 127 128 129 130 131 132 133 134 135 136 137 138 139 140

DFCS - GENERAL DESCRIPRION . . . . . . . . . . . . . . . . . . . . AT INTRODUCTION . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . AT OPERATION OVERVIEW . . . . . . . . . . . . . . . . . . . . . . . . . Composite Materials . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . Introduction . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . Door Mounted Escape Slide . . . . . . . . . . . . . . . . . . . . . . . . . . . Equipment and Furnishing . . . . . . . . . . . . . . . . . . . . . . . . . . . . Passenger Compartment - Introduction . . . . . . . . . . . . . . . . . Attendant Station . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . Introduction . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . Passenger Oxygen System Introduction . . . . . . . . . . . . . . . . Functional Description . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . Vacuum Waste System - Introduction . . . . . . . . . . . . . . . . . . . Fuel Storage - General Description . . . . . . . . . . . . . . . . . . . . . Refueling System . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . Fuel Vent System . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . Defueling System . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . Fuel Panel . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . Engine and APU Fuel Feed System . . . . . . . . . . . . . . . . . . . . Fuel Indicating . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . Hydraulic Basic Schematic . . . . . . . . . . . . . . . . . . . . . . . . . . . . Hydraulic Indicating System . . . . . . . . . . . . . . . . . . . . . . . . . . . Roll Control . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . Aileron System Schematic . . . . . . . . . . . . . . . . . . . . . . . . . . . . Flight Spoiler System . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . Stabilizer . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . Stabilizer and Elevator Schematic . . . . . . . . . . . . . . . . . . . . . Rudder . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . High Lift Device . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . Flap Drive System . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . Flap positions . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . Flight Control Panel . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . Flight Control Panel . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . Center Control Stand . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . Landing Gear Schematic . . . . . . . . . . . . . . . . . . . . . . . . . . . . .

209 211 213 215 217 219 221 223 225 227 229 231 233 235 237 239 241 243 245 247 249 251 253 255 257 259 261 263 265 266 267 269 271 273 275

Page vi

One Stop Airline MRO Support Pvt. Ltd

OSA B737--6 GEN FAM

TABLE OF FIGURES Figure Figure Figure Figure Figure Figure Figure Figure Figure Figure Figure Figure Figure Figure Figure Figure Figure Figure Figure Figure Figure Figure Figure Figure Figure Figure Figure Figure Figure Figure Figure Figure Figure

OSA

141 142 143 144 145 146 147 148 149 150 151 152 153 154 155 156 157 158 159 160 161 162 163 164 165 166 167 168 169 170 171 172 173

Brake and Anti Skid Systems . . . . . . . . . . . . . . . . . . . . . . . . . Indication . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . Pneumatic System . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . Pneumatic System Schematic . . . . . . . . . . . . . . . . . . . . . . . . . Pneumatic Control Panel . . . . . . . . . . . . . . . . . . . . . . . . . . . . . Air Conditioning System Schematic . . . . . . . . . . . . . . . . . . . . Overhead Control Panel . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . Equipment Cooling General . . . . . . . . . . . . . . . . . . . . . . . . . . . Air Conditioning System Schematic . . . . . . . . . . . . . . . . . . . . Overhead Control Panel . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . Pressurization Control . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . Pressurization Control Interface . . . . . . . . . . . . . . . . . . . . . . . Pressurization Control Module . . . . . . . . . . . . . . . . . . . . . . . . . Allied Signal 131--9 B . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . Indication & Controls . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . Oil System . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . Fuel System General . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . APU Pneumatic System . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . Ignition and Start System Components . . . . . . . . . . . . . . . . . Thrust Rating . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . Fadec Purpose . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . Oil System Schematic . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . Engine Controls Components . . . . . . . . . . . . . . . . . . . . . . . . . Fuel Distribution . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . Engine Thrust Control System Schematic . . . . . . . . . . . . . . . Engine Air General . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . Ignition System Schematic . . . . . . . . . . . . . . . . . . . . . . . . . . . . Translating Sleeves . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . System Schematic . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . General Schematic . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . Engine Display . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . Engine Indication Config. 2 . . . . . . . . . . . . . . . . . . . . . . . . . . . EEC BITE General . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .

NN

Jul 3, 2007

277 279 281 283 285 287 289 291 293 295 297 299 301 303 305 307 309 311 313 315 319 321 323 325 327 329 331 333 335 337 339 341 343

Page vii