737
Training Manual
THIS MANUAL IS FOR TRAINING PURPOSES ONLY.
NO MAINTENANCE ACTION SHOULD BE TAKEN AS A RESULT OF INFORMATION CONTAINED IN THIS MANUAL.
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UNPUBLISHED, ALL RIGHTS RESERVED UNDER COPYRIGHT LAWS (C) 2003 ALTEON TRAINING L.L.C
This manual has been prepared by Alteon Seattle, Washington for the
Boeing Commercial Airplane Group.
ALTEON.
737-600/700/800/900 AIRCRAFT MAINTENANCE MANUAL
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Page 1
Jun 10/2006
737-600/700/800/900 TRAINING MANUAL
IDC
Air India Express
YL461
Chapter
Section
Subject
Subject
737 GENERAL -- INTRODUCTION . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 00-00-00
RANGE . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .
STRUCTURE DIMENSIONS . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .
FUSELAGE DIMENSIONS . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .
ZONE DIAGRAM . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .
POWER PLANT INTRODUCTION . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .
POWER PLANT ENGINE HAZARDS . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .
FLIGHT CONTROL SURFACES . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .
DOORS INTRODUCTION . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .
ENTRY DOOR EXTERIOR OPERATION . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .
ENTRY DOOR INTERIOR OPERATION . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .
FLIGHT COMPARTMENT PANELS . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .
MAIN INSTRUMENT PANELS . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .
GLARESHIELD PANELS . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .
P2 CENTER INSTRUMENT PANEL AND P9 FORWARD ELECTRONICS PANEL . . . . . . . . . . . . . . . . . . . .
CONTROL STAND . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .
P8 AFT ELECTRONICS PANEL . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .
P5 AFT OVERHEAD PANEL . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .
P5 FORWARD OVERHEAD PANEL . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .
AFT FLIGHT COMPARTMENT PANELS . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .
ELECTRONIC EQUIPMENT RACK - LOCATION . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .
ELECTRONIC EQUIPMENT COMPARTMENT . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .
EE COMPARTMENT DOOR OPERATION . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .
ELECTRONIC EQUIPMENT RACK E1 . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .
ELECTRONIC EQUIPMENT RACKS E2, E3, AND E4 . . . . . . . . . . . . . . . . . . . . . . . . . . . . .
ELECTRONIC EQUIPMENT RACK E5 . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .
ELECTRONIC EQUIPMENT RACK - E6 . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .
PROGRAM SWITCH MODULE . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .
LOADABLE SOFTWARE . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .
ANTENNA LOCATIONS . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .
TABLE OF CONTENTS
Page
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. . 14
. . 16
. . 18
. . 20
. . 23
. . 26
. . 28
. . 30
. . 32
. . 34
. . 36
. . 38
. . 40
. . 42
. . 44
. . 46
. . 48
. . 50
. . 52
. . 54
. . 56
. . 58
. . 60
. . 63
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Page 1
ALTEON PROPRIETARY. Copyright.
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737-600/700/800/900 TRAINING MANUAL
IDC
Air India Express
YL461
Chapter
Section
Subject
Subject
EXTERNAL POWER APPLICATION . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .
ELECTRICAL POWER OPERATION . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .
ELECTRICAL POWER DISTRIBUTION . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .
APU FIRE PROTECTION . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .
APU OPERATION . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .
EQUIPMENT COOLING . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .
HYDRAULIC POWER OPERATION . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .
COMMUNICATION EQUIPMENT COMPONENT LOCATIONS - 1 . . . . . . . . . . . . . . . . . . . . . . . . . .
COMMUNICATION EQUIPMENT COMPONENT LOCATIONS - 2 . . . . . . . . . . . . . . . . . . . . . . . . . .
FLIGHT INTERPHONE SYSTEM OPERATION . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .
CREW CALL OPERATION . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .
SERVICE INTERPHONE SYSTEM . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .
VHF COMMUNICATION SYSTEM OPERATION . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .
MAIN LANDING GEAR DOWNLOCK PIN . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .
NOSE LANDING GEAR DOWNLOCK PIN . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .
TOWING LEVER . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .
PARKING BRAKE SYSTEM . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .
AIRPLANE TOWING . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .
TOWING OPERATION . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .
JACKING POINTS . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .
FMCS CONTROL DISPLAY UNIT . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .
Page
. . 69
. . 73
. . 76
. . 81
. . 85
. . 88
. . 91
. . 94
. . 96
. . 98
. 100
. 102
. 104
. 106
. 108
. 110
. 112
. 114
. 116
. 118
. 120
MAINTENANCE DOCUMENTS -- INTRODUCTION . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 01-00-00
MAINTENANCE PLANNING DATA DOCUMENT . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .
FAULT REPORTING MANUAL . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .
DISPATCH DEVIATION PROCEDURES GUIDE . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .
FIM - INTRODUCTION . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .
FIM - OBSERVED FAULT LISTS . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .
FIM - CABIN FAULT LIST . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .
FIM - CABIN FAULT CODE INDEX . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .
.
.
.
.
.
.
.
.
TABLE OF CONTENTS
122
126
128
131
134
136
138
140
Page 2
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737-600/700/800/900 TRAINING MANUAL
737 GENERAL -- INTRODUCTION
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737-600/700/800/900 TRAINING MANUAL
737 GENERAL -- INTRODUCTION
Introduction
This section introduces you to the 737-800 airplane.
You will see general information about these topics:
-
Range
Dimensions
Engines
Flight controls
Doors
Flight compartment panels
Electronic equipment rack configuration
Electrical.
This section also introduces you to these tasks:
-
Electrical power application
Hydraulic power application
Equipment cooling operation
Radio and intercommunication system operation
Towing
Control display unit (CDU) operation.
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Abbreviations and Acronyms
A/P
A/S
ac
ACARS
ACMS
ADF
- autopilot
- airspeed
- alternate current
- aircraft communications addressing and
reporting system
- airplane condition monitoring system
- automatic direction finder
ADIRS
AFCS
AGCU
altn
amp
APB
APU
ATC
att
auto
bat
bcn
BL
BPCU
BTB
C/W
capt
CDS
CDU
chgr
comm
comp
conn
cond
cntl
det
DEU
dist
DME
- air data inertial reference system
- automatic flight control system
- APU generator control unit
- alternate
- amplifier
- APU breaker
- auxiliary power unit
- air traffic control
- attendant
- automatic
- battery
- beacon
- buttock line
- bus power control unit
- bus tie breaker
- control wheel
- captain
- common display system
- control display unit
- charger
- communication
- computer
- connected
- condition
- control
- detector
- display electronic unit
- distribution
- distance measuring equipment
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737-600/700/800/900 TRAINING MANUAL
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737 GENERAL -- INTRODUCTION
DU
ECU
EE
EEC
elex
ELT
EMDP
ESDS
ext
F/O
FCC
FMC
FMCS
freq
fwd
GCU
gnd
GPS
HF
HUD
IDG
ILS
inv
L
LBL
LE
LRRA
LRU
mod
- display unit
- electronic control unit
- electronic equipment
- electronic engine control
- electronics
- emergency locator transmitter
- electric motor driven pump
- electrostatic discharge sensitive
- external
- first officer
- flight control computer
- flight management computer
- flight management computer system
- frequency
- forward
- generator control unit
- ground
- global positioning system
- high frequency
- heads up display
- integrated drive generator
- instrument landing system
- inverter
- left
- left buttock line
- leading edge
- low range radio altimeter
- line replaceable unit
- module
MLG
MCP
MPD
nav
NLG
ovht
PA
PCU
PDP
pnl
prox
PSU
pwr
R
RBL
REU
RLY
SATCOM
S/B
sec
sel
SCU
SPCU
SOV
stab
STA
stdby
sw
- main landing gear
- mode control panel
- maintenance planning document
- navigation
- nose landing gear
- overheat
- passenger address
- power control unit
- power distribution panel
- panel
- proximity
- passenger service unit
- power
- right
- right buttock line
- remote electronics unit
- relay
- satellite communication
- speedbrake
- section
- select
- start converter unit
- standby power control unit
- shutoff valve
- stabilizer
- station
- standby
- switch
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737-600/700/800/900 TRAINING MANUAL
737 GENERAL -- INTRODUCTION
TCAS
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TE
TRU
typ
VHF
vlv
VOR
WL
xfer
xfmr
- traffic alert and collision avoidance
system
- trailing edge
- transformer rectifier unit
- typical
- very high frequency
- valve
- VHF omni range
- water line
- transfer
- transformer
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737-600/700/800/900 TRAINING MANUAL
GENERAL INFORMATION
TASK INTRODUCTION
- RANGE
- ELECTRICAL POWER APPLICATION
- DIMENSIONS
- HYDRAULIC POWER APPLICATION
- ENGINES
- EQUIPMENT COOLING
- FLIGHT CONTROLS
- COMMUNICATION
- DOORS
- TOWING
- FLIGHT COMPARTMENT PANELS
- CDU OPERATION
- ELECTRONIC EQUIPMENT RACKS
- ELECTRICAL
737 GENERAL - INTRODUCTION
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737-600/700/800/900 TRAINING MANUAL
737 GENERAL -- RANGE
Introduction
The 737-800 is a two-engine airplane. It is for short
to medium range flights with a capacity of up to 189
passengers.
Features
There are many new features. These new features
increase the airplane payload, service ceiling, and
range.
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The airplane has a design range of 2,900 nautical
miles.
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737-600/700/800/900 TRAINING MANUAL
737-800 RANGE
(2,900 NM)
OSLO
LONDON
PARIS
KARACHI
BEIJING
MUMBAI
SEATTLE
SINGAPORE
NEW YORK
MEXICO CITY
PORT MORESBY
BOGOTA
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PERTH
737 GENERAL - RANGE
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737-600/700/800/900 TRAINING MANUAL
737 GENERAL -- STRUCTURE DIMENSIONS
General
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These are the general dimensions of the airplane.
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- 8 ALTEON PROPRIETARY. Copyright.
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737-600/700/800/900 TRAINING MANUAL
117 FEET 5 INCHES
34.3 METERS
47 FEET 1 INCH
14.4 METERS
129 FEET 6 INCHES
39.5 METERS
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41 FEET 2 INCHES
12.6 METERS
737-800 DIMENSIONS
737 GENERAL - STRUCTURE DIMENSIONS
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737-600/700/800/900 TRAINING MANUAL
737 GENERAL -- FUSELAGE DIMENSIONS
General
Dimensions give locations on the fuselage. The scale
for each dimension is inches. You use these dimensions
to find components on the fuselage:
-
Body station line
Body buttock line
Water line.
The body station line (STA) is a horizontal dimension.
It starts at station line zero. You measure the body
station line from a vertical reference plane that is
forward of the airplane.
The body buttock line (BL) is a lateral dimension. You
measure the buttock line to the left or right of the
airplane center line.
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The water line (WL) is a height dimension. You measure
the water line from a horizontal reference plane below
the airplane.
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130
178
196.5
211.8
224.8
243.7
259.5
277
294.5
312
328
344
360
380
400
420
440
460
480
500
522
544
566
588
610
632
654
676
698
718
738
757
776
795
814
837
861.75
883
904
925
945
965
985
1007
1029
1051
1073
1095
1117
1137
1157
1177
1197
1217
1237
1257
1277
1297
1317
1337
1357.5
1377
1396.5
1426
1450
1474
1498
1522
1539
1566
1627
130
178
196.5
211.8
224.8
243.7
259.5
277
294.5
312
328
344
360
380
400
420
440
460
480
500
500A
500B
500C
500D
500E
500F
500G
500H
500I
520
540
559
578
597
616
639
663.75
685
706
727
727A
727B
727C
727D
727E
727F
727G
727H
727I
727J
747
767
787
807
827
847
867
887
907
927
947.5
967
986.5
1016
1040
1064
1088
1112
1129
1156
1217
737-600/700/800/900 TRAINING MANUAL
198-IN STRETCH
STATION LINES
212-IN STRETCH
STA 500
LBL 73.75
WL 306.5
LBL 30
RBL 30
RBL 73.75
WL 232.5
WL AT TOP OF
FLOORBOARD
WL 208
FWD
WL 148.5
BBL 0
BODY BUTTOCK AND WATER LINES
737 GENERAL - FUSELAGE DIMENSIONS
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737-600/700/800/900 TRAINING MANUAL
737 GENERAL -- ZONE DIAGRAM
General
The airplane has eight major zones to help you find and
identify the airplane components and parts. The major
zones are divided into subzones and the subzones into
zones. These are the major zones:
100 - lower half of the fuselage
200 - upper half of the fuselage
300 - empennage
400 - powerplant and nacelle struts
500 - left wing
600 - right wing
700 - landing gear and landing gear doors
800 - doors.
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-
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737-600/700/800/900 TRAINING MANUAL
300
300
200
300
500
600
400
400
700
100
700
200 - UPPER FUSELAGE
800 - DOORS
500/600 - WINGS
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300 - EMPENNAGE
100 - LOWER FUSELAGE
400 - POWER PLANT/STRUT
700 - LANDING GEAR/LANDING
GEAR DOORS
737 GENERAL - ZONE DIAGRAM
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737-600/700/800/900 TRAINING MANUAL
737 GENERAL -- POWER PLANT INTRODUCTION
General
Two CFM56-7B engines supply thrust for the airplane.
The engines also supply power for these systems:
-
Electric
Hydraulic
Pneumatic.
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The CFM56-7B is a high bypass ratio, dual rotor, turbo
fan engine.
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737-600/700/800/900 TRAINING MANUAL
737 GENERAL - POWER PLANT INTRODUCTION
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737-600/700/800/900 TRAINING MANUAL
737 GENERAL -- POWER PLANT ENGINE HAZARDS
General
Exhaust Velocity
It is dangerous to work around engines. Use the
entry/exit corridor when the engine is in operation.
Stay out of the inlet and exhaust areas when the engine
is in operation.
Exhaust velocity is very high for a long distance
behind the engine. This can cause damage to personnel
and equipment.
Engine Noise
These are the hazards around an engine in operation:
-
Engine noise can cause temporary and permanent loss of
your ability to hear. You must wear ear protection when
near an engine in operation.
Inlet suction
Exhaust heat
Exhaust velocity
Engine noise.
Engine Entry/Exit Corridor
Inlet Suction
Engine inlet suction can pull people and large objects
into the engine. At idle power, the inlet hazard area
is a 10 ft (3.1 m) radius around the inlet.
Engine entry corridors are between the inlet hazard
areas and the exhaust hazard areas. You should go near
an engine in operation only when:
-
WARNING: IF THE WIND IS OVER 25 KNOTS, INCREASE THE
INLET HAZARD AREA BY 20%.
The engine is at idle
You can speak with people in the flight
compartment.
For additional safety, wear a safety harness when the
engine is in operation.
Exhaust Heat
Training Information Point
When the engine is in operation, the anti-collision
lights should be on.
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The engine exhaust is very hot for a long distance
behind the engine. This can cause damage to personnel
and equipment.
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737-600/700/800/900 TRAINING MANUAL
ANTI-COLLISION LIGHT
(TOP OF FUSELAGE)
ANTI-COLLISION LIGHT
(BOTTOM OF FUSELAGE)
INLET HAZARD AREA
- IDLE - 10 FT (3.1 M)
- TAKEOFF - 14 FT (4.2 M)
IDLE - 4 FT (1.2 M)
TAKEOFF - 5 FT (1.5 M)
45 DEG
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ENTRY/EXIT
CORRIDOR
IDLE POWER
HEAT AND EXHAUST
VELOCITY
HAZARD AREAS
ENTRY/EXIT
CORRIDOR
HEAT AND EXHAUST
VELOCITY
HAZARD AREAS
737 GENERAL - POWER PLANT ENGINE HAZARDS
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737-600/700/800/900 TRAINING MANUAL
737 GENERAL -- FLIGHT CONTROL SURFACES
General
Power Source
The flight controls keep the airplane at the necessary
attitude during flight. They have movable surfaces on
the wing and the empennage. These are the two types of
flight controls:
Hydraulic actuators or electric motors move the
surfaces. You must be very careful when you work near
flight control surfaces. When hydraulic power is on,
make sure that all the flight control surfaces are
clear of personnel and equipment.
-
Primary
Secondary.
Primary Flight Controls
The primary flight controls has these subsystems:
-
Aileron (2)
Elevator (2)
Rudder.
Secondary Flight Controls
The secondary flight control system has these
components:
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-
Leading edge flaps (4)
Leading edge slats (8)
Trailing edge flaps (4)
Spoilers (12)
Horizontal stabilizer.
The 12 spoilers consists of 4 ground and 8 flight
spoilers. The spoilers are numbered 1 to 12, left to
right.
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737-600/700/800/900 TRAINING MANUAL
RUDDER
ELEVATORS
(2)
FLIGHT
SPOILERS (8)
HORIZONTAL
STABILIZER
TE FLAPS (4)
GROUND
SPOILERS (4)
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AILERONS (2)
LE FLAPS (4)
LE SLATS (8)
737 GENERAL - FLIGHT CONTROL SURFACES
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- 19 ALTEON PROPRIETARY. Copyright.
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737-600/700/800/900 TRAINING MANUAL
737 GENERAL -- DOORS INTRODUCTION
General Description
Training Information Point
These are the types of doors on the airplane:
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.
-
Forward and aft entry doors
Forward and aft galley service doors
Overwing emergency exit doors (and pilot sliding
windows)
Cargo doors
Interior doors (crew door and lavatory doors)
Miscellaneous access doors.
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
The entry doors are on the left side of the airplane.
The galley service doors are on the right side of the
airplane.
The overwing emergency exit doors are above the wings
on both sides of the airplane. The pilot sliding
windows are in the flight compartment.
The crew door and lavatory doors are inside the
airplane.
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The cargo doors are on the right side of the airplane.
The miscellaneous access doors are near the systems
they serve.
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- 20 ALTEON PROPRIETARY. Copyright.
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737-600/700/800/900 TRAINING MANUAL
REFUELING STATION
ACCESS DOOR
AIR CONDITIONING
ACCESS DOOR
ENGINE OIL
TANK ACCESS DOOR
EXTERNAL POWER
RECEPTACLE DOOR
LOWER NOSE COMPARTMENT
ACCESS DOOR
RAM AIR
ACCESS PANEL
EE COMPARTMENT
ACCESS DOOR
FORWARD CARGO
COMPARTMENT DOOR
GROUND AIR CONDITIONING
ACCESS DOOR
AFT CARGO
COMPARTMENT
DOOR
TAIL CONE
ACCESS DOOR
APU
ACCESS
DOOR
WATER
SERVICE
DOOR
HYDRAULIC
ACCUMULATOR
ACCESS DOOR
TOILET
SERVICE
DOOR
CENTER FUEL TANK
SUMP ACCESS DOOR
AFT ENTRY
DOOR
AFT GALLEY
SERVICE DOOR
EMERGENCY
EXIT DOORS
SECTION 48
ACCESS AND
BLOWOUT DOOR
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FORWARD GALLEY
SERVICE DOOR
SLIDING
WINDOW
FORWARD
ENTRY DOOR
AIRSTAIR
DOOR
IDG OIL
RESERVOIR
ACCESS DOOR
737 GENERAL - DOORS INTRODUCTION
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- 21 ALTEON PROPRIETARY. Copyright.
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737-600/700/800/900 TRAINING MANUAL
737 GENERAL -- ENTRY DOOR EXTERIOR OPERATION
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- 22 ALTEON PROPRIETARY. Copyright.
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737-600/700/800/900 TRAINING MANUAL
737 GENERAL -- ENTRY DOOR EXTERIOR OPERATION
To complete the door opening operation, hold the aft
edge of the door and pull it open.
General
You open and close an entry door manually with the
control handle. While open, a hinge lock mechanism
holds the door in the open position.
The cabin crew puts the door slide warning pennant
across the door window if the slide is armed.
Open the Door - Exterior Operation
As you pull the door open, the door turns. This moves
the door parallel to the airplane fuselage when the
door is fully open.
An escape slide is on the inside, lower part of the
entry door. If the slide girt bar is in the armed
position, the slide will deploy automatically as the
door opens. Look to see if there is a door slide
warning pennant (orange) in the door window. The
pennant is across the window when the slide is armed.
Make sure that the escape slide is not armed before you
open the door.
Close the Door
The door swings out of the door frame when it opens.
Make sure that the area outside of the door is clear.
To close the door, first release the hinge lock. The
release mechanism is yellow. Operate the latch release
mechanism to unlock the hinge. This lets you to swing
the door back into the door frame.
You must pull the exterior door control handle from the
recess position to engage the door drive mechanisms.
Turn the handle 180 degrees in the clockwise direction.
The door moves to the cocked open position.
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As the door opens, winds may push it. This can push the
operator off balance. Keep a strong, secure stance to
prevent this.
At this point, any more effort on the door control
handle will not produce more door motion. The door
control handle has gone through its full motion.
Release the control handle and allow it to return to
its recess by spring force.
Before you close the door, examine the escape slide.
The escape slide girt strap and bar must be properly
stowed. An incorrectly folded strap or improperly
stowed bar will interfere with the door threshold
clearance. This will prevent the door from sealing and
latching, and may damage components.
Pull the door to the cocked position.
Pull the exterior control handle out of the recess, and
turn it slightly until it engages the door drive
mechanisms. Turn the door control handle
counterclockwise 180 degrees to complete the action.
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- 23 ALTEON PROPRIETARY. Copyright.
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737-600/700/800/900 TRAINING MANUAL
737 GENERAL -- ENTRY DOOR EXTERIOR OPERATION
When the control handle has gone through its full
motion, release it and allow it to return to the recess
by spring force.
Training Information Point
You can operate the forward entry door in winds up to
40 knots. You can let the door stay latched open in
winds up to 65 knots.
The force on the control handle to open and close the
door is not large. If a large force is required, there
is a fault with the door or the procedure.
If the door does not close and latch easily, there may
be a clearance problem. Make sure the door-to-frame
area is clear. An incorrectly stowed escape slide girt
strap may be caught between the door and the frame.
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If the airplane is pressurized, a properly rigged door
will not unlatch. This is because the door gates must
open against cabin pressure during door unlatch.
Pressure on the door gates prevents this.
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- 24 ALTEON PROPRIETARY. Copyright.
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737-600/700/800/900 TRAINING MANUAL
PENNANT
PENNANT NOT ACROSS WINDOW:
- SLIDE IS NOT ARMED
- IT IS OK TO OPEN
THE DOOR
PENNANT ACROSS WINDOW:
- SLIDE IS ARMED
- IF YOU OPEN THE DOOR,
THE SLIDE WILL DEPLOY
PULL DOOR HANDLE
FROM ITS RECESS
LOOK FOR DOOR SLIDE
WARNING PENNANT
DOOR SLIDE
WARNING
PENNANT
00-00-00-521.fm
HINGE LOCK
RELEASE
MECHANISM
TURN HANDLE
DOOR FULLY OPEN AND
UPPER HINGE LOCKED
PULL DOOR OPEN
737 GENERAL - ENTRY DOOR EXTERIOR OPERATION
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- 25 ALTEON PROPRIETARY. Copyright.
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737-600/700/800/900 TRAINING MANUAL
737 GENERAL -- ENTRY DOOR INTERIOR OPERATION
General
You use an interior control handle to open and close an
entry door. The hinge lock mechanism holds the door in
the open position. You release this mechanism to close
the door.
Interior Operation
The escape slide is on the inside lower part of the
door. If the slide girt bar is in the armed position,
the slide will deploy as the door opens. Make sure the
slide girt bar is not armed and then remove the door
slide warning pennant (orange) in the door window.
To open the door from the interior, unlatch the door
with the control handle and turn the handle in the OPEN
direction. This puts the door in the cocked position.
Push the door through the door frame until it is fully
open. Use the assist handles for this operation.
A hinge lock mechanism in the upper hinge keeps the
door in the fully open position.
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To close the door, first release the hinge lock. The
release mechanism is yellow. Operate the latch release
mechanism to unlock the hinge. This lets you swing the
door back into the door frame.
Pull the door to the cocked position and turn the
control handle in the close direction.
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- 26 ALTEON PROPRIETARY. Copyright.
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737-600/700/800/900 TRAINING MANUAL
DOOR SLIDE
WARNING
PENNANT
INTERIOR
CONTROL
HANDLE
HINGE LOCK
MECHANISM
ASSIST
HANDLES
EMERGENCY
ESCAPE
SLIDE
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SLIDE GIRT
BAR
SLIDE GIRT BAR
BRACKET (2)
FWD ENTRY DOOR
(INTERIOR VIEW - DOOR OPEN)
737 GENERAL - ENTRY DOOR INTERIOR OPERATION
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737-600/700/800/900 TRAINING MANUAL
737 GENERAL -- FLIGHT COMPARTMENT PANELS
Flight Compartment Panels
These are the major panels in the flight compartment:
P1 captain instrument panel
P2 center instrument panel
P5 forward overhead panel
P5 aft overhead panel
P7 glareshield panel
P3 first officer instrument panel
P9 forward electronic panel
Control stand
P8 aft electronic panel.
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- 28 ALTEON PROPRIETARY. Copyright.
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737-600/700/800/900 TRAINING MANUAL
P5 AFT
OVERHEAD PANEL
P5 FORWARD
OVERHEAD PANEL
P7 GLARESHIELD PANEL
P2 CENTER
INSTRUMENT PANEL
P3 FIRST OFFICER
INSTRUMENT PANEL
P1 CAPTAIN
INSTRUMENT
PANEL
P9 FORWARD
ELECTRONIC PANEL
CONTROL STAND
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P8 AFT ELECTRONIC
PANEL
737 GENERAL - FLIGHT COMPARTMENT PANELS
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- 29 ALTEON PROPRIETARY. Copyright.
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737-600/700/800/900 TRAINING MANUAL
737 GENERAL -- MAIN INSTRUMENT PANELS
General
The controls and displays on the main instrument panels
(P1 and P3) include these components:
Clock (2)
Display unit (4)
Display select panel (2)
Master dim and test switch
Brake pressure indicator
Autoflight status annunciator (2)
GPWS control panel
Lighting control (2)
Conditioned air outlet control (2).
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- 30 ALTEON PROPRIETARY. Copyright.
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737-600/700/800/900 TRAINING MANUAL
LIGHTS
MAIN PANEL DUs
OUTBD
PFD
P/RST
NORM
ENG
PRI
ENG
PRI
1
A/P A/T FMC
LOWER DU
NORM
P/RST
ND
P/RST
TEST
2
TEST
SPEED BRAKE
ARMED
MFD
BELOW G/S
P-INHIBIT
SPEED BRAKE
DO NOT ARM
4
BRAKE
DIM
PFD
INBD
LOWER DU
3
BRT
2
P/RST
STAB
OUT OF
TRIM
ND
P/RST
MAIN PANEL DUs
NORM
1
A/P A/T FMC
P/RST
1 PSIx1000PRESS
0
NORM
ENG
PRI
OUTBD
PFD
PFD
INBD
MFD
BELOW G/S
P-INHIBIT
SPEEDBRAKES
EXTENDED
ENG
PRI
2
TEST
DO NOT EXTEND THE SPEEDBRAKE LEVER
DO NOT EXTEND THE SPEEDBRAKE LEVER
BEYONE THE FLIGHT DETENT IN FLIGHT
BEYONE THE FLIGHT DETENT IN FLIGHT
CHR
50
40
TIME/DATE
CHR
TIME/DATE
60
60
UTC
MAN TIME
UTC
MAN TIME
DAY
MOYR
RUN ET
HLD
CHR
10
50
20
40
MOYR
CHR
30
30
ET HOLD TO RESET
ET HOLD TO RESET
PUSH TOSET
10
DAY
RUN ET
HLD
20
PUSH TOSET
NOSE WHEEL STEERING
A
L
T
N
O
R
M
REGISTRATION
SELCAL
REGISTRATION
SELCAL
PANEL
UPPER
BRT
BACKGROUND
PANEL
GROUND PROXIMITY
AFDS FLOOD
GPWS
FLAP
GEAR
TERR
INHIBIT INHIBIT INHIBIT
INOP
FOOT
AIR
WINDSHIELD
AIR
OFF
OUTBD
BRT
OFF
INBD
BRT
OFF
OFF
LOWER
BRT
INBD
BRT
SYS TEST
NORM
00-00-00-008.fm
P1 CAPT INSTRUMENT PANEL
NORM
OUTBD
BRT
WINDSHIELD
AIR
NORM
P3 F/O INSTRUMENT PANEL
(TYPICAL P1 AND P3 PANELS)
737 GENERAL - MAIN INSTRUMENT PANELS
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- 31 ALTEON PROPRIETARY. Copyright.
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FOOT
AIR
737-600/700/800/900 TRAINING MANUAL
737 GENERAL -- GLARESHIELD PANELS
General
The controls and displays on the P7 glareshield include
these components:
Master caution annunciator (2)
System caution annunciator (2)
Mode control panel (MCP)
EFIS control panel (2)
Fire warning light (2).
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737-600/700/800/900 TRAINING MANUAL
COURSE
00-00-00-009.fm
MINS
RADIO
BARO
FIRE
WARN
MASTER
CAUTION
BELL CUTOUT
PUSH TO RESET
FLT CONT
IRS
APU
OVHT/DET
MTRS
STD
ADF 1
40
VOR MAP
PLN 20
80
VOR 2
APP
160
10
320 OFF
5
TFC
CTR
640
ADF 2
WXR
STA
VOR 1
OFF
WPT
ARPT
DATA
A/T
ARM
HEADING
IAS/MACH
ALTITUDE
VNAV
A A/P
VERT SPEED
LNAV
CMD
BARO
IN
HPA
RST
ELEC
FUEL
FPV
POS
TERR
F/D
DN
VOR LOC
OFF
SPD
INTV
ON
N1
SPEED
LVL CHG
COURSE
CMD
MINS
RADIO
BARO
FPV
MTRS
BARO
IN
HPA
30
10
C/O
MA
ENGAGEB
CWS
ALT
INTV
HDG SEL
APP
ALT HLD
CWS
F/D
ADF 1
WXR
STA
OFF
DISENGAGE
UP
OFF
STD
40
VOR MAPPLN
20
80
VOR 2
APP
160
10
5
320 OFF
TFC
CTR
640
ADF 2
VOR 1
ON
V/S
OFF
RST
MA
WPT
ARPT
DATA
POS
(TYPICAL GLARESHIELD PANELS)
737 GENERAL - GLARESHIELD PANELS
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- 33 ALTEON PROPRIETARY. Copyright.
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TERR
ANTI-ICE
ENG
HYD
OVERHEAD
DOORS
AIR COND
MASTER
CAUTION
FIRE
WARN
PUSH TO RESET
BELL CUTOUT
737-600/700/800/900 TRAINING MANUAL
737 GENERAL -- P2 CENTER INSTRUMENT PANEL AND P9 FORWARD ELECTRONICS PANEL
General
The controls and displays on the P2 center instrument
panel include these components:
-
Yaw damper indicator
Standby instruments
Engine display control panel
Antiskid and autobrake switches and lights
Flap position indicator
Landing gear lever and position indicator
Upper center display unit.
The controls and displays on the P9 forward electronics
panel include these components:
Lower center display unit
Control display unit (CDU) (2).
00-00-00-010.fm
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- 34 ALTEON PROPRIETARY. Copyright.
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737-600/700/800/900 TRAINING MANUAL
YAW DAMPER
N1 SET
AUTO
1
AUTO BRAKE
SPD REF
AUTO
BOTH
SET
2
AUTO BRAKE
DISARM
V1
1
VREF
OFF
MFD
RTO
FUEL FLOW
RESET
RATE
10
20
30
ENG
USED
NOSE
GEAR
5
1
3
10
UP
WT
GYRO
30
20
10
2
2
VR
MAX
NOSE
GEAR
15
25
FLAPS
40
30
ANTISKID
SYS
ANTISKID
INOP
INOP
LE FLAPS
TRANSIT
LEFT
GEAR
RIGHT
GEAR
LEFT
GEAR
RIGHT
GEAR
LE FLAPS
EXT
APP
OFF
B/CRS
UP
L
A
N
D
I
N
G OFF
9 0 1
16 0 0 0 2
7
MB
6
1013
BARO
ALT
5
3
4
250
300
IAS
KNOTS
C
A
L
L
F
A
I
L
INIT
REF
RTE
CLB
CRZ
DES
MENU
LEGS
DEP
ARR
HOLD
PROG
N1
LIMIT
FIX
A
B
C
PREV
PAGE
NEXT
NEXT
PAGE
PAGE
1
2
3
INIT
REF
RTE
CLB
CRZ
DES
EXEC
MENU
LEGS
DEP
ARR
HOLD
PROG
E
N1
LIMIT
FIX
A
B
C
D
PREV
PAGE
NEXT
NEXT
PAGE
PAGE
F
G
H
I
J
BRT
D
F
G
H
I
J
K
L
M
N
O
1
2
3
K
L
M
N
O
4
5
6
P
Q
R
S
T
8
9
U
V
W
X
Y
7
8
9
U
V
W
X
Y
0
+/-
Z
SP
DEL
/
CLR
.
0
+/-
Z
SP
DEL
/
CLR
7
.
R
T
F
A
I
L
P
5
S
O
F
S
T
IN HG
G
E
A
R
2992
DN
P9 FORWARD ELECTRONIC PANEL
HDG
LANDING GEAR
LIMIT (IAS)
OPERATING
EXTEND 270-.82M
RETRACT 235K
EXTENDED 320K-.82M
V
O
R
V
O
R
FLAPS LIMIT (IAS)
ADF
ADF
INOP
INOP
15-185K
15-195K
1-250K
2-250K
25-175K
25-170K
5-250K
30-160K
30-165K
10-210K
40-155K
40-156K
230K ALT FLAP
EXTEND
P2 CENTER INSTRUMENT PANEL
APP
APP
HP/IN
29.92 IN
13200
240
220
13000
10
1
200
180
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E
6
4
Q
N
S
G
C
A
L
L
BRT
EXEC
40
12720
12600
10
160
ATT
RST
BARO
INT STANDBY FLIGHT DISPLAY (OPTIONAL)
(TYPICAL P2 AND P9 PANELS)
737 GENERAL - P2 CENTER INSTRUMENT PANEL AND P9 FORWARD ELECTRONICS PANEL
00-00-00
- 35 ALTEON PROPRIETARY. Copyright.
See title page for details
N
S
G
O
F
S
T
737-600/700/800/900 TRAINING MANUAL
737 GENERAL -- CONTROL STAND
General
The controls and indications on the control stand
include these components:
Forward thrust lever (2)
Reverse thrust lever (2)
Speedbrake handle
Horizontal stabilizer trim wheel and indicator(2)
Parking brake lever and light
Flap lever
Stabilizer trim cutout switch (2)
Start lever (2).
00-00-00-011.fm
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- 36 ALTEON PROPRIETARY. Copyright.
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737-600/700/800/900 TRAINING MANUAL
IDLE
STAB TRIM
MAIN
ELECT
CUTOFF
AUTO
NORMAL PILOT
CUT
OUT
2
1
2
PARKING
BRAKE
PULL
1
2
A/T
DISENGAGE
00-00-00-011.fm
A/T
DISENGAGE
737 GENERAL - CONTROL STAND
00-00-00
- 37 ALTEON PROPRIETARY. Copyright.
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737-600/700/800/900 TRAINING MANUAL
737 GENERAL -- P8 AFT ELECTRONICS PANEL
General
The P8 aft electronics panel has these components:
Weather radar control panel
Cargo fire control panel
Aileron/rudder trim panel
ATC/TCAS control panel
Audio control panel
Overheat/fire protection panel
Navigation control panel
Radio communication panel
ADF control panel
ACMS printer
Lighting control.
00-00-00-100.fm
-
00-00-00
- 38 ALTEON PROPRIETARY. Copyright.
See title page for details
737-600/700/800/900 TRAINING MANUAL
OVHT DET
ENG 1
OVERHEAT
L
APU DET
INOP
TEST
OF
VI
HR
TE
TFR
EXT
FWD AFT
C
O
M
M
V
H
F
COMM TEST
DISCH
C
A
R
G
O
N
A
V
STANDBY
TFR
DISCH
ENG 2
OVERHEAT
L
DET SELECT
NORM
NORM
B A
B
A
FWD
TEST
ARMED
ALT OFF ALT ON
STBY
TA
TEST
TA/RA
ET
XE 1
TS
T
ARMED
R
APU
ACTIVE
F
I
R
E
DISCH
2
L
AFT
C
O
M
M
V
H
F
COMM TEST
R
ATC
1
N
A
V
2
IDENT
2
STANDBY
TFR
ATC
1
P
N OFF
L
STANDBY
VHF1
VHF2
VHF3
HF1
AM
HF2
TEST
VHF
SEN
ACTIVE
ATC12
ACTIVE
STANDBY
TFR
DISCH
FAIL
TEST
R
DETECTOR
FAULT
AFT
ARM
FWD
ACTIVE
NORMAL
FIRE SWITCHES
(FUEL SHUTOFF)
PULL WHEN ILLUMINATED
LOCK OVERRIDE: PRESS
BUTTON UNDER HANDLE
APU BOTTLE
DISCHARGED
STANDBY
R BOTTLE
L BOTTLE
DISCHARGED DISCHARGED
B
ENGINES
NORMAL
FAULT
F
AI
UN
LO
TP
ACTIVE
A
DISCH
R
OVHT DET
BELL CUTOUT
WHEEL
WELL
B
A
OPTIONAL:
RADIO COMM PANEL
TEST
ALT
ATC
WX
MIC SELECTOR
WX RADAR
WX/TURB
MIC SELECTOR
MAP
TEST
VHF 1 VHF 2 VHF 3 HF 1
HF 2
INT
CABIN
C
C
C
PA
TILT
5
10
GAIN
1-VHF-2-VHF-3
SERV
INT
HF
FLT
INT
15
UP
PA
0
DN
1-NAV-2
1-ADF-2
MKR
1-VHF-2-VHF-3
HF
1-NAV-2
1-ADF-2
FLT
INT
C
PA
C
C
C
15
MAX
AUTO
SERV
INT
5
SPKR
10
MKR
SPKR
SAT 1 SAT 2
R/T
V
MASK
B
ALT
R
R/T
SLEW RESET TEST
I/C
BOOM
MSG
V
MASK
B
C
ALT
R
1-NAV-2
RADIO V
PAPER FAIL
I/C
NORM
BOOM
INT
ADF
ANT
ADF
ANT
A
D
F
ADF ANT
TFR
ADF
ANT
FULL
OFF ON
A
D
F
EMPTY
PAPER
ADF ANT
OFF ON
TONE
TONE
RF SENS
INOP
VHF2
VHF2
VHF2
C
O
M
M
HF2
H
F
PRESS TO RESET
15
10
RUDDER TRIM
5
0
5
10
OFF
USB
AM
15
OFF
LEFT
RIGHT
AILERON
00-00-00-100.fm
FLOOD
PANEL
NOSE
LEFT
LEFT
WING
DOWN
OFF
RIGHT
WING
DOWN
OFF
R
U
D
D
E
R
NOSE
RIGHT
STAB TRIM
FLT DK DOOR
AUTO
OVRD
NORM
LOCK
FAIL
UNLKD
DENY
AUTO
LOCK
UNLK
(TYPICAL P8 PANEL)
737 GENERAL - P8 AFT ELECTRONICS PANEL
00-00-00
- 39 ALTEON PROPRIETARY. Copyright.
R
C
MKR
SPKR
ALT
NORM SAT 1
CALL
CONTROL
SAT 2
OPTIONAL:
AUDIO CONTROL PANEL
W/CALL LIGHTS
ADF
ANT
SECAL
VHF2
1-ADF-2
NORM
DATA PRINTER
TFR
B
See title page for details
737-600/700/800/900 TRAINING MANUAL
737 GENERAL -- P5 AFT OVERHEAD PANEL
General
The controls and displays on the P5 aft overhead panel
include these components:
Inertial system display unit
Engine panel
Observer audio control panel
Captain flight interphone speaker
Oxygen panel
Landing gear indicator lights
White dome light switch
Service interphone switch
IRS mode select unit
Flight recorder and Mach airspeed warning module
Stall warning test module
Proximity switch electronics unit light
ELT control panel
Leading edge devices annunciator panel.
00-00-00-101.fm
-
00-00-00
- 40 ALTEON PROPRIETARY. Copyright.
See title page for details
737-600/700/800/900 TRAINING MANUAL
MIC SELECTOR
SERV
INT
HF
1-VHF-2-VHF-3
FLT
INT
PA
IRS DISPLAY
1-NAV-2
DSPL SEL
PPOS
WIND
TK/GS
HDG/STS
TEST
BRT
N
2
3
W
4
H
5
E
6
7
S
8
9
1
SYS DSPL
L
R
ENT
ELT
0
1-ADF-2
R/T
MASK
I/C
BOOM
V
NORM
OFF
EEC
ON
ON
ALTN
ALTN
FLAPS
3
ALIGN
ON DC
ALIGN
ON DC
CREW
OXYGEN
FAULT
DC FAIL
FAULT
DC FAIL
10
ALIGN
NAV
ALIGN
NAV
ON
LE DEVICES
2
4
TRANSIT
1
2
5
EXT
3
SLATS
4
FULL EXT
5
6
7
8
OFF
OFF
ATT
NO 1
TEST
NORMAL
NO 2
OFF
ENGINE
CONTROL
L
IRS
PASS OXYGEN
STALL WARNING TEST
NO. 1
NO. 2
NORMAL
ON
20
OXY PRESS
PSI X 100
R
DOME WHITE
DIM
00-00-00-101.fm
TEST
15
ATT
SLATS
TEST
T
I O
N
D L
E O
X C
K
MACH
AIRSPEED
WARNING
GPS
ON
1
FLIGHT RECORDER
REVERSER
EEC
ARM
ENGINE
CONTROL
ALT
2
REVERSER
SERVICE
INTERPHONE
SPKR
R
ENGINE
1
CLR
ELT
B
MKR
PSEU
OFF
PASS OXY
ON
RIGHT
GEAR
LEFT
GEAR
NOSE
GEAR
BRIGHT
(TYPICAL P5 AFT OVHD PANEL)
737 GENERAL - P5 AFT OVERHEAD PANEL
00-00-00
- 41 ALTEON PROPRIETARY. Copyright.
See title page for details
T
I O
N
D L
E O
X C
K
737-600/700/800/900 TRAINING MANUAL
737 GENERAL -- P5 FORWARD OVERHEAD PANEL
General
The controls and displays on the P5 forward overhead
panel include these components:
APU control switch
APU indicator panel
Fuel control panel
Ground power and bus switching panel
Equipment cooling panel
Generator drive and standby power panel
AC and dc meter panel
Flight control panel
Air-conditioning/bleed air controls panel
Hydraulic control panel
Cabin altitude panel
Cabin pressure control panel
Cockpit voice recorder panel
Engine start panel
Passenger signs panel
Source select panel
Window/pitot heat module
Instrument switching and VHF NAV and IRS panel
Door warning panel
Anti-ice panel
Temperature control panel
Light switches.
00-00-00-102.fm
-
00-00-00
- 42 ALTEON PROPRIETARY. Copyright.
See title page for details
737-600/700/800/900 TRAINING MANUAL
OFF
ZONE
TEMP
ZONE
TEMP
FWD CAB
AUTO
AFT CAB
AUTO
LOW
QUANTITY
ALTERNATE FLAPS
DC VOLTS
OFF
A
DUAL
BLEED
C
W
OFF
RAM DOOR
FULL OPEN
C
R RECIRC FAN
OFF
OFF
AUTO
AUTO
60
OFF
ON
ON
MACH TRIM
FAIL
AUTO SLAT
FAIL
OFF
AUTO
HIGH
WING
ANTI
ICE
AUTO
OPEN
TRIP
PACK
WING-BODY
OVERHEAT
BLEED
TRIP OFF
GEN1
TR3
GRD
PWR
STBY
PWR
TEST
STBY
PWR
APU GEN
COOL
INV
OFF
OFF
ON
CAB/UTIL
ON
IFE/PASS
SEAT
AC
COWL
ANTI-ICE
L VALVE
OPEN
R VALVE
OPEN
AUTO
WING-BODY
OVERHEAT
BLEED
TRIP OFF
BOTH
ON 2
BOTH
ON L
BOTH
ON R
RAM DOOR
FULL OPEN
RAM DOOR
FULL OPEN
RECIRC FAN
2
1
OFF
AUTO
EQUIP COOLING
ALL
ON 1
OFF
AUTO
OFF
ALL
ON 2
BOTH
ON 1
OFF
ALTN
-20
SPAR VALVE
CLOSED
MANUAL
GRD
PWR
OFF
SPAR VALVE
CLOSED
40
FILTER
BYPASS
ON
ON
SOURCE
OFF
LOW
LOW
PRESSURE PRESSURE
TEST
GRD
CALL
ATTEND
S
FPRES 0
DIF I
10 PS
0
50
9
CABIN
40
ALT
35
30
8
25
GEN OFF
BUS
OFF
OFF
OFF
GEN 1
R
L
ON
CTR
FWD
AFT
CALL
PARK
OFF
PARK
L
5
HIGH
TAXI
ALTN
MANUAL
MANUAL
FLT ALT
C
O
L
P
O
E
S
N
E
ALTN
AUTO
MAN
3
4
LAND ALT
V
A
L
V
E
2
3
GRD
OFF
CONT
FLT
GRD
BOTH
IGN
L
CAB ALT LAND ALT 2000
4
ENGINE START
ON
ON
R
FIXED
1
N CLIM
ABI
FLT ALT
0F
EET PER 3
.5
2
1
HIGH
APU
OFF
.5
UP
0
DN
LOW
OFF
ON
ON
L
R
RETRACTABLE
INT
LOW
2
RUNWAY
TURNOFF
L
R
OFF
15
6
2
OFF SCHED
DESCENT
AUTO
ALT
HORN
CUTOUT
2
5
10
20
100
LANDING
RETRACT
PRESS DIFF
LIMIT:TAKEOFF & LDG
.125 PSI
R WIPER
2
E
X
T
E
N
D
7
INT
0
4
ON
BLEED
B
6
ON
GEN 2
L WIPER
10
EGT
8
OFF
FUEL
PUMPS
OFF
OVER
SPEED
FAULT
LOW
LOW
PRESSURE PRESSURE
1
T
I O
N
D L
E O
X C
K
LOW OIL
PRESSURE
MAINT
FWD
ON
APU GEN
APU
ON
OVERHEAT
BLEED
TRIP OFF
APU
ERASE
HEADSET
600 OHMS
1
WING
ANTI
ICE
PACK
OPEN TRIP
OFF
TRIP WING-BODY
RESET
AUTO
FAIL
COCKPIT VOICE RECORDER
SOURCE
OFF
PACK
TRIP OFF
WING-BODY
OVERHEAT
BLEED
TRIP OFF
1
FASTEN
BELTS
FUEL PUMPS
ON
WING
ANTI
ICE
R PACK
OFF
AUTO
HIGH
OFF
ON
A
U TRANSFER
T BUS OFF
O
APU GEN
OFF BUS
GEN OFF
BUS
OFF
FWD
CARGO
AFT
CARGO
AUTO
O
F
F
TRANSFER
BUS OFF
FEED
CROSS
AFT
FWD
FWD
ENTRY
SERVICE
RIGHT
LEFT
OVERWING OVERWING
AFT
AFT
SERVICE
ENTRY
AUTO
ON
NO
SMOKING
BUS TRANSFER
FILTER
BYPASS
ISOLATION
VALVE
CLOSE
OFF
AUTO
HIGH
B
OFF
VALVE
OPEN
LOW
LOW
PRESSURE PRESSURE
L PACK
HYD PUMPS
OVHT
DUCT
PRESS
PSI
0
TEST
ON
EQUIP
ARMED
A
NR
OM
TE
D
GRD POWER
AVAILABLE
C
(-800/-900)
OFF
A
OFF
ENG VALVE
CLOSED
0
FUEL 20
TEMP
-40
ELEC 1 ENG 2
OFF
EMER EXIT LIGHTS
NORMAL
ENG VALVE
CLOSED
ENG 1 ELEC 2
80
20
OFF
BOTH
ON 2
2
40
LOW
LOW
PRESSURE PRESSURE
ON
ON
APU
OVERHEAT
LOW
LOW
PRESSURE PRESSURE
ALTERNATE
BAT
CONTROL PANEL
AUTO
OVERHEAT
NORMAL
DISPLAYS
SOURCE
60
EXHAUST
SUPPLY
DISCONNECT
NORMAL
WARM
OFF
MANUAL
ON
SMOKE
DRIVE
DISCONNECT
WARM
COOL
WARM
OFF
MANUAL
DUAL
BLEED
OFF
ON
COOL
WARM
COOL
ENG
ANTI-ICE
OFF
LAVATORY
COWL
ANTI-ICE
COWL VALVE COWL VALVE
OPEN
OPEN
WING ANTI-ICE
OFF
2
STANDBY POWER
IRS
NORMAL
WING
ANTI
ICE
BLEED
00-00-00-102.fm
DUCT
OVERHEAT
C
PANEL
TEST
STANDBY
PWR OFF
DRIVE
BOTH
ON 1
PACK
ON
OFF SCHED
DESCENT
80
20
AUTO
GEN2
BAT
NAVIGATION
D
60
40 TEMP
DUCT
OVERHEAT
0 o
OFF
1
VHF NAV
OFF
AUTO
HIGH
OFF
AUTO
FAIL
TR2
DC
RESET
1
ON
HEAT
AIR MIX
VALVE
H
ON
R PACK
ISOLATION
VALVE
CLOSE
F/O
PITOT
R ELEV
PITOT
R ALPHA
VANE
AUX
PITOT
B
100
BAT
BUS
0
TEST
L PACK
SPEED TRIM
FAIL
YAW
DAMPER
OFF
AIR MIX
VALVE
H
D
OFF
FEEL
DIFF PRESS
YAW DAMPER
ON
PASS CABIN
PASS
CABIN
SUPPLY
DUCT
MAINT
TR1
OFF
OVHT
DUCT
PRESS
PSI
20
OFF
ELEC
DOWN
ARM
ON
80
R L
40
B
BAT
RAM DOOR
FULL OPEN
R RECIRC FAN
BAT
DISCHARGE TR UNIT
OFF
W
OFF
CIRCUIT BREAKER
/ AC VOLTS
PROBE
A
AIR TEMP
CONT CABIN
R L
W
OFF
/ AC AMPS
UP
LOW
LOW
PRESSURE PRESSURE
SIDE
PWR TEST
CAPT
PITOT
L ELEV
PITOT
L ALPHA
VANE
TEMP
PROBE
STBY
RUD
B ON
FWD
OFF
ON
LOW
PRESSURE
ON
R
OVHT
FWD
OFF
SPOILER
C
SIDE
COL
STBY
RUD
OFF
CPS FREQ
OT
STBY
RUD
A ON
ZONE
TEMP
CONT CAB
AUTO
DC AMPS
STANDBY
HYD
B
OT
ON
A
ON
ON
WINDOW HEAT
L
FLT CONTROL
AUTO
VOICE
RECORDER
OVERHEAT OVERHEAT
ON
ON
COL
100
C
OVERHEAT OVERHEAT
C
20
PASS
AIR TEMP
CAB
FWD
S
AFT
AFT
U D
P U F
R
P C W
P
L T D
A
Y
L
CONT
C
CAB
TRIM AIR
K
OFF
80
MIN
60
40 TEMP.
OFF
CONT
LOGO
OFF
POSITION
STEADY
ON
STROBE &
STEADY
FLT
IGN
R
ON
2
(TYPICAL P5 FWD OVHD PANEL)
737 GENERAL - P5 FORWARD OVERHEAD PANEL
00-00-00
- 43 ALTEON PROPRIETARY. Copyright.
See title page for details
6000
FL260
ANTI
COLLISION
OFF
WING
OFF
WHEEL
WELL
OFF
ON
ON
ON
OFF
START
1
4000
<FL160 FL220
8000
FL320 FL410
T
I O
N
D L
E O
X C
K
737-600/700/800/900 TRAINING MANUAL
737 GENERAL -- AFT FLIGHT COMPARTMENT PANELS
General
The main circuit breaker panels are behind the first
officer and captain seats. The P6 and P18 have the
component load circuit breakers. Circuit breaker
organization is by airplane systems.
00-00-00-015.fm
The P61 panel has the data loader controls.
00-00-00
- 44 ALTEON PROPRIETARY. Copyright.
See title page for details
737-600/700/800/900 TRAINING MANUAL
P61
P6
00-00-00-015.fm
P18
FLIGHT COMPARTMENT
(LOOKING AFT)
737 GENERAL - AFT FLIGHT COMPARTMENT PANELS
00-00-00
- 45 ALTEON PROPRIETARY. Copyright.
See title page for details
737-600/700/800/900 TRAINING MANUAL
737 GENERAL -- ELECTRONIC EQUIPMENT RACK - LOCATION
General
The airplane has equipment racks in these parts of the
airplane:
Electronic equipment (EE) compartment
Aft cargo compartment
00-00-00-038.fm
-
00-00-00
- 46 ALTEON PROPRIETARY. Copyright.
See title page for details
737-600/700/800/900 TRAINING MANUAL
ELECTRONIC EQUIPMENT
(EE) COMPARTMENT
- E1 RACK
- E2 RACK
- E3 RACK
- E4 RACK
- E5 RACK
00-00-00-038.fm
AFT CARGO
COMPARTMENT
- E6 RACK
737 GENERAL - ELECTRONIC EQUIPMENT RACK - LOCATION
00-00-00
- 47 ALTEON PROPRIETARY. Copyright.
See title page for details
737-600/700/800/900 TRAINING MANUAL
737 GENERAL -- ELECTRONIC EQUIPMENT COMPARTMENT
General
Most electronic equipment is in a compartment below the
main cabin floor, aft of the nose wheel well. On the
ground, you enter this electronic equipment (EE)
compartment through a door in the bottom of the
fuselage. The door is aft of the nose landing gear.
The airplane has these equipment racks in the EE
compartment:
-
E1 - forward part of the compartment
E2 - left aft part of the compartment
E3 - center aft part of the compartment
E4 - right aft part of the compartment
E8 - forward part of the compartment above the E1
E5 - right side of the compartment.
Shelf assemblies have equipment mounts, interconnected
wiring, and accessory boxes. Most equipment rack
shelves are cooled with air. Air is blown through or
drawn through the equipment racks.
00-00-00-016.fm
There is a drip shield over the racks to protect the
equipment from moisture condensation.
The airplane has an E6 equipment rack (not shown) in
the aft cargo compartment on the right side, aft of the
cargo door. The rack does not have cooling air. The
equipment on this rack is passively cooled.
00-00-00
- 48 ALTEON PROPRIETARY. Copyright.
See title page for details
737-600/700/800/900 TRAINING MANUAL
E8, ABOVE THE E1
E5
E4
E1
E3
00-00-00-016.fm
E2
737 GENERAL - ELECTRONIC EQUIPMENT COMPARTMENT
00-00-00
- 49 ALTEON PROPRIETARY. Copyright.
See title page for details
737-600/700/800/900 TRAINING MANUAL
737 GENERAL -- EE COMPARTMENT DOOR OPERATION
Operation
You manually operate an external access door to the
electronic equipment (EE) compartment. You open and
close the door from outside the airplane.
Open Door
The handle on the door fairs in a recess. A push-button
trigger releases the handle, and it comes out of fair
by spring force.
Turn the handle counterclockwise to retract the latch
pins. If you do not do this, the door will not seat in
the door frame.
Pull the handle to the left and the door will come out
of the partially open detent. Then it slides down into
the door frame.
Turn the handle clockwise to latch the door. Then push
the door handle back into its recess.
Turn the handle counterclockwise to disengage the latch
pins. When the latch pins are free you can push the
door upward and slightly to the right to the first
detent. Then push the door to the right to the fully
open detent.
When the door is fully open, the roller tracks can be
folded to improve access to the equipment racks. A
spring catch on the end of each roller track holds the
track in the folded or unfolded position.
Close Door
00-00-00-523.fm
Before you close the door, release the spring catch and
extend the roller tracks. Make sure the door frame area
is clear.
Pull the door out of the fully open detent and then
restrain it as gravity causes it to slide down the
tracks. When the door reaches the lower detent you can
release it.
00-00-00
- 50 ALTEON PROPRIETARY. Copyright.
See title page for details
737-600/700/800/900 TRAINING MANUAL
DOOR
ROLLER TRACK
SPRING CATCH
ROLLER TRACK
(EXTENDED)
DOOR FRAME
LATCH
FITTING
HANDLE
00-00-00-523.fm
RELEASE
TRIGGER
FWD
FWD
EE COMPARTMENT EXTERNAL ACCESS DOOR
EE COMPARTMENT EXTERNAL ACCESS DOOR
(EXTERIOR VIEW - CLOSED)
737 GENERAL - EE COMPARTMENT DOOR OPERATION
00-00-00
- 51 ALTEON PROPRIETARY. Copyright.
See title page for details
737-600/700/800/900 TRAINING MANUAL
737 GENERAL -- ELECTRONIC EQUIPMENT RACK E1
The equipment on the E1-3 rack includes these line
replaceable units (LRUs):
General
The equipment on the E1 rack includes electronics for
these functions:
-
Autothrottle
Autopilot
Communication
Navigation
Flight control.
-
Anti-skid/autobrake controller
PA amplifier
VHF communication transceiver 1.
Blow through cooling cools the equipment on this rack.
The equipment on the E1-4 rack includes these line
replaceable units (LRUs):
Equipment
The equipment on the E1-1 rack includes these line
replaceable units (LRUs):
-
Ground proximity warning computer (GPWC)
Integrated flight systems accessory unit (IFSAU)
Flap/slat electronics unit (FSEU)
Flight control computer A (FCC A)
TCAS computer.
Blow through cooling cools the equipment on this rack.
The equipment on the E1-2 rack includes these line
replaceable units (LRUs):
-
VOR/marker beacon receiver 2
Multi-mode receiver 2
Flight control computer B
Compartment overheat detector controller.
Draw through cooling cools the equipment on this rack.
The equipment on the E1-5 rack includes these line
replaceable units (LRUs):
-
VHF communication transceiver 2
ATC transponder 2
DME interrogator 2.
00-00-00-017.fm
Draw through cooling cools the equipment on this rack.
-
DME interrogator 1
ATC transponder 1
VOR/marker beacon receiver 1
Multi-mode receiver (MMR)1.
Blow through cooling cools the equipment on this rack.
00-00-00
- 52 ALTEON PROPRIETARY. Copyright.
See title page for details
737-600/700/800/900 TRAINING MANUAL
G
P
W
C
CAB
PRES
CONT
2
IFSAU
ANTI
SKID
AUTO
BRAKE
CONT
PA
AMP
VHF
COM
2
ATC
2
FSEU
VHF
COM
1
TCAS
COMPUTER
FCC A
BTMU
(PROV)
DME1
DME
2
VOR
2
ATC
1
MMR
2
PROGRAM SWITCH
MODULE (TYP)
VOR/
MB 1
FCC
B
MMR
1
OVER
HEAT
CONT
MOD
00-00-00-017.fm
FWD
(TYPICAL E-1 RACK)
ACCESS DOOR
737 GENERAL - ELECTRONIC EQUIPMENT RACK E1
00-00-00
- 53 ALTEON PROPRIETARY. Copyright.
See title page for details
737-600/700/800/900 TRAINING MANUAL
737 GENERAL -- ELECTRONIC EQUIPMENT RACKS E2, E3, AND E4
General
The equipment in the E2, E3, and E4 racks include
electronics for these functions:
-
Window heat
Communications
Electrical power
Common display system (CDS)
Flight control
Fire detection
APU.
The EE compartment light switch is on a panel
immediately aft of the access door opening.
Blow-through and draw-through cooling removes heat from
the equipment on the racks. E2-1 uses blow-through
cooling. E3-2, E3-3, E4-1, and E4-2 use draw-through
cooling.
E3-1 uses draw-through and blow-through cooling.
00-00-00-018.fm
E2-2 does not have forced air cooling.
00-00-00
- 54 ALTEON PROPRIETARY. Copyright.
See title page for details
737-600/700/800/900 TRAINING MANUAL
E4 RACK
AIR
CON
RLYS
1
AIR
CON
RLYS
2
REU
SEL
CAL
AUDIO AUTO
SPD
ENT
BRK
MUX
(PROV) ACC
WIND
CONT
3
WIND
CONT
4
ISFD CMU
BAT NO. 1
(PROV)(PROV)
TRU
3
TRU
2
HUDHGS
COMP
(PROV)
ADF
2
(PROV)
GCU
2
LRRA
2
BPCU
POWER DIST
PANEL 2
E3 RACK
ZONE
TEMP
CONT
2
CDS DEU
2
DFDAU
ZONE
TEMP
CONT
1
CDS DEU
1
ENG
VIB
SIG
COND
ENG
ACC
ACARS
(PROV)
AUDIO
ENT
PLAYER
(PROV)
VHF
COMM
3
(PROV)
E2 RACK
ADF
1
LRRA
1
WIND
CONT
2
SMYD
2
SMYD
1
FIRE
DET
CONT
MOD
AUX BAT
CHARGER
(PROV)
WIND
CONT
1
AGCU
CAB
PRESS
CONT
1
GCU
1
APU
SCU
POWER DIST
PANEL 1
00-00-00-018.fm
BATTERY
EE COMPARTMENT
LIGHT SWITCH
AFT
ACCESS DOOR
(TYPICAL E2, E3, AND E4 RACKS)
737 GENERAL - ELECTRONIC EQUIPMENT RACKS E2, E3, AND E4
00-00-00
- 55 ALTEON PROPRIETARY. Copyright.
See title page for details
TRU
1
PRI
BAT
CHGRR
STATIC
INV
APU
SPU
737-600/700/800/900 TRAINING MANUAL
737 GENERAL -- ELECTRONIC EQUIPMENT RACK E5
General
The equipment in the E5 rack includes electronics for
these functions:
-
Air data inertial reference system (ADIRS)
Flight management computer system (FMCS).
Equipment
The E5-2 shelf has these line replaceable units:
-
Flight management computer 1 and 2
Air data inertial reference unit Left and Right.
Draw-through and blow-through cooling removes heat from
the equipment on the E5-2 shelf.
00-00-00-019.fm
An optional E5-1 shelf has electronics for HF and the
passenger entertainment systems.
00-00-00
- 56 ALTEON PROPRIETARY. Copyright.
See title page for details
737-600/700/800/900 TRAINING MANUAL
E5-1 SHELF
(OPTIONAL)
ADIRU
LEFT
FMC
1
FMC
ADIRU
2
RIGHT
(PROV)
E5-2 SHELF
00-00-00-019.fm
PORTABLE CDU
CONNECTOR
(OPTIONAL)
FWD
(TYPICAL E5-2 SHELF)
ACCESS DOOR
737 GENERAL - ELECTRONIC EQUIPMENT RACK E5
00-00-00
- 57 ALTEON PROPRIETARY. Copyright.
See title page for details
737-600/700/800/900 TRAINING MANUAL
737 GENERAL -- ELECTRONIC EQUIPMENT RACK - E6
Purpose
The E6 rack gives a place to mount electrical and
electronic equipment.
Location
The rack is in the aft cargo compartment on the right
side, aft of the cargo door.
Physical Description
00-00-00-039.fm
The E6 rack has three shelves. The rack is sealed from
the cargo compartment with two panels and cargo
sidewall liner material. The panels have quick release
fasteners.
00-00-00
- 58 ALTEON PROPRIETARY. Copyright.
See title page for details
737-600/700/800/900 TRAINING MANUAL
E6-1
E6 RACK
(SIDE ACCESS PANEL REMOVED)
00-00-00-039.fm
E6-2
E6-3
E6 RACK
(FWD ACCESS PANEL REMOVED)
737 GENERAL - ELECTRONIC EQUIPMENT RACK - E6
00-00-00
- 59 ALTEON PROPRIETARY. Copyright.
See title page for details
737-600/700/800/900 TRAINING MANUAL
737 GENERAL -- PROGRAM SWITCH MODULE
See the Standard Wiring Practices Manual for more
information on the program switch module.
General
Many of the line replaceable units (LRUs) are
controlled by internal digital computers. These
computers follow instructions (or programs) to do a
certain task.
The program switch module gives an external method to
customize a computer's program.
The program switch module has these components:
-
Switches
Pin contacts
Switch seal plug
Security cover.
An LRU's programming pin inputs come in on the pin
contacts. The switches set the programming pins.
The security cover goes over the switch seal plug. The
security cover and the switch seal plug keeps the
switches stationary.
00-00-00-036.fm
The program switch module gives this information to an
LRU:
-
Equipment physical orientation
Airplane type
Number of units installed
Customer specific options.
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737-600/700/800/900 TRAINING MANUAL
SWITCH
(24)
1 2 3 4 5 6 7 8 9 10 1112
SECURITY
COVER
1 2 3 4 5 6 7 8 9 1011 12
O
N
O
N
CTS
206-12
S1
T047
T047
S2
CTS
206-12
1
3
5
7
9
11
13
15
17
19
21
23
25
2
4
6
8
10
12
14
16
18
20
22
24
26
PIN CONTACTS
(INSIDE CAVITY)
(26)
WIRES TO LRU
(TYPICAL)
SWITCH SEAL
PLUG (2)
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PIN CONTACTS
(INSIDE CAVITY)
(26)
737 GENERAL - PROGRAM SWITCH MODULE
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737-600/700/800/900 TRAINING MANUAL
737 GENERAL -- LOADABLE SOFTWARE
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737-600/700/800/900 TRAINING MANUAL
737 GENERAL -- LOADABLE SOFTWARE
General
Some of the LRUs in the 737 need both hardware and
software. Without the software, the logic circuits in
the LRUs can not do their specified function. They must
have the proper software load.
You can load the software in the LRU at the shop or you
can load it at the airplane.
Except for the electronic engine control (EEC), you use
the airborne data loader on the P61 panel to load the
software.
The EEC software is loaded at the engine with a
portable data loader only.
Loadable Software Binder
A binder is in the book compartment at the bottom of
the P61. The binder has all the software necessary to
load software at the airplane.
Systems
These LRUs have loadable software features:
Installation Procedure
-
00-00-00-031.fm
-
Flight management computer (FMC)
Control display unit (CDU)
ARINC communications addressing and reporting
system (ACARS)/communication management unit (CMU)
Display electronic unit (DEU)
Satellite communication (SATCOM)
Flight control computer (FCC)
APU engine control unit (ECU)
Passenger flight information distribution system
(PFIDS) or AIRSHOW
Digital flight data acquisition unit (DFDAU)
Airplane condition monitoring system (ACMS).
NOTE: Some of the above units are for optional systems
on the airplane. When the airplane does not have
the LRU for the optional system, the switch
position for the optional system shows INOP.
The information below shows the steps to load an FMCS
navigation data base. The procedure to load the other
systems data is similar.
This is a summary of the steps to load data with an ADL:
-
-
Airplane must be on the ground
Apply electrical power to the airplane
Set the data loader 3-position switch to the FMC
you will load (the L position will load FMC 1 and
the R position will load FMC 2)
Set the data load selector to the FMC position
Open the data loader access door
Put the necessary diskette into the ADL.
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737-600/700/800/900 TRAINING MANUAL
737 GENERAL -- LOADABLE SOFTWARE
NOTE: The FMC source select switch on the P5 panel must
be set in the BOTH ON L or NORMAL positions to
see the load progress on the MCDUs if FMC 1 is
loaded. If the 3-position switch is in the R
position, the FMC source select switch must be
set to BOTH ON R to see the load progress on the
MCDUs.
The data load process is automatic. When the data
loader 3-position switch is set to the L position, the
data loads into FMC 1. You then do a crossload and load
the data into FMC 2 via the FMCS inter system bus.
Return the data loader control panel to the NORM
position after the transfer is complete.
00-00-00-031.fm
NOTE: Do not interrupt electrical power to the system
during software loading. If power is interrupted,
you will need to do the software load procedure
again.
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737-600/700/800/900 TRAINING MANUAL
P61 PANEL
AIRBORNE DATA LOADER
(TYPICAL)
L
CAPT
UPR
DATA LOAD SELECTOR
C
SINGLE SYS
R
F/O
LWR
FLIGHT COMPARTMENT
(LOOKING AFT)
SYSTEM SELECT
ACMS
DFDAU
PFIDS
00-00-00-031.fm
LOADABLE
SOFTWARE
BINDER
FMC
CDU
ACARS/CMU
INOP
INOP
INOP
INOP
APU
DEU
INOP
INOP
INOP
1
NORMAL
INOP
INOP
SATCOM
FCC
DATA LOADER CONTROL PANEL
OPTIONAL SYSTEMS NOT ACTIVE
ARE LABELED INOP.
737 GENERAL - LOADABLE SOFTWARE
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1
737-600/700/800/900 TRAINING MANUAL
737 GENERAL -- ANTENNA LOCATIONS
Antenna Location
These are the communication and navigation system
antennas:
-
00-00-00-006.004
-
Weather radar
Traffic alert and collision avoidance system
(TCAS)
Air traffic control (ATC)
Global positioning system (GPS)
Very high frequency (VHF) communication
Automatic direction finder (ADF)
High frequency (HF) communication
VHF omni range (VOR)/Localizer (LOC)
Marker beacon
Radio altimeter
Distance measuring equipment (DME)
Emergency locator transmitter (ELT)
Localizer
Glideslope.
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737-600/700/800/900 TRAINING MANUAL
VOR/LOC
TCAS
GPS 2
ATC
VHF 1
GPS 1
ELT
HF
ADF (2)
GLIDE SLOPE
WEATHER RADAR
LOCALIZER
VHF 3
TCAS
RADIO
ALTIMETER
(4)
DME (2)
VHF 2
MARKER BEACON
00-00-00-006.004
ATC
737 GENERAL - ANTENNA LOCATIONS
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737-600/700/800/900 TRAINING MANUAL
737 GENERAL -- EXTERNAL POWER APPLICATION
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737-600/700/800/900 TRAINING MANUAL
737 GENERAL -- EXTERNAL POWER APPLICATION
vGeneral
P19 External Power Receptacle Panel
You use these panels to apply external electrical
power:
The external power receptacle panel has these two
sections:
-
P5-13 electrical meters, battery and galley power
module
P5-4 ac systems, generator, and APU module
P19 external power receptacle panel.
P5-13 Electrical Meters, Battery, and Galley Power
Module
The BAT switch lets you energize these buses with
battery power:
-
Switched hot battery bus
Battery bus
AC and DC standby buses.
External power receptacle
Control and display section.
You connect the external power cable to the external
power receptacle.
The control and display section has the EXTERNAL POWER
CONN and the external power NOT IN USE indicators.
The amber EXTERNAL POWER CONN light comes on when the
ground power plug is connected and power is present.
The white NOT IN USE indicator comes on when external
power is present, but not in use.
The switch is guarded in the BAT ON position.
External Power Application
P5-4 AC Systems, Generator and APU Module
Before you supply external power to the airplane, make
sure that the external power supply operates correctly.
The ground power switch gives you manual control when
good quality ground power is available. The blue GRD
POWER AVAILABLE light above the switch shows if the
ground source is connected and quality is good.
00-00-00-026.fm
-
The ground power switch has three positions and is
spring loaded to the center (neutral) position. The ON
and OFF positions are momentary positions.
WARNING: IF THE EXTERNAL POWER SUPPLY HAS AN EARTH
GROUNDED NEUTRAL, THERE MUST NOT BE AN OPEN OR
FLOATING GROUND IN THE NEUTRAL CIRCUIT WIRING
OF THE SUPPLY OR THE AIRPLANE. IF AN OPEN OR
FLOATING GROUND IS PRESENT, THE AIRPLANE CAN
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737-600/700/800/900 TRAINING MANUAL
737 GENERAL -- EXTERNAL POWER APPLICATION
BE PUT AT AN ELECTRICAL POTENTIAL ABOVE EARTH
GROUND. THIS ELECTRICAL POTENTIAL CAN CAUSE
ELECTRIC SHOCK WITH POSSIBLE SEVERE INJURY TO
PERSONNEL WHO TOUCH THE AIRPLANE.
WARNING: REMOVE THE ELECTRICAL POWER FROM THE EXTERNAL
POWER CABLE BEFORE YOU CONNECT THE CABLE TO
THE AIRPLANE. INJURY TO PERSONS CAN BE CAUSED
BY AN ELECTRICAL SHOCK.
To apply power, open the external power receptacle door
and connect the power cable to the external power
receptacle.
Energize the external power cable.
-
1 TRANSFER BUS OFF
2 TRANSFER BUS OFF.
The NOT IN USE light on the P19 panel also goes off.
External Power Removal
To remove external power from the airplane, put the GRD
PWR switch momentarily to the OFF position. Then put
the BAT switch to the OFF position. This removes the ac
power from the ac transfer buses and the battery power
from the standby, switched hot battery and battery
buses.
The external power NOT IN USE light on the P19 panel
comes on.
These lights on the external power panel (P19) come on:
-
When you de-energize the external power cable, the
EXTERNAL POWER CONN and the NOT IN USE lights go off.
You can then safely remove the cable from the external
power receptacle.
EXTERNAL POWER CONN
NOT IN USE.
The GRD POWER AVAILABLE light on the P5-4 panel also
comes on.
00-00-00-026.fm
To let the ground power go to the ac transfer buses,
put the BAT switch on the P5-13 module to ON. Then put
the GRD PWR switch on the P5-4 panel to ON.
These lights on the P5-4 panel go off when ground power
goes to the ac transfer buses:
-
1 SOURCE OFF
2 SOURCE OFF
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737-600/700/800/900 TRAINING MANUAL
GROUND POWER
AVAILABLE LIGHT
BATTERY
SWITCH
GRD POWER
AVAILABLE
GRD
PWR
OFF
GROUND POWER
SWITCH
OFF
BAT
ON
ON
BUS TRANSFER
DC
TRANSFER
BUS OFF
P5-13 ELECTRICAL METERS
BATTERY AND GALLEY
POWER MODULE
O
F
F
SOURCE
OFF
A
U TRANSFER
T BUS OFF
O
SOURCE
OFF
GEN OFF
BUS
APU GEN
OFF BUS
OFF
GEN 1
GEN OFF
BUS
OFF
ON
APU GEN
APU
ON
GEN 2
P5-4 AC SYSTEMS, GENERATOR,
AND APU MODULE
EXTERNAL
POWER
EXTERNAL POWER
CONNECTED LIGHT
F
CONN
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PILO
NOT IN USE LIGHT
FWD
NOT
IN USE
CAL
P19 EXTERNAL POWER PANEL
737 GENERAL - EXTERNAL POWER APPLICATION
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737-600/700/800/900 TRAINING MANUAL
737 GENERAL -- ELECTRICAL POWER OPERATION
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737-600/700/800/900 TRAINING MANUAL
737 GENERAL -- ELECTRICAL POWER OPERATION
You use the IFE/PASS SEAT switch to control power to:
General
You use switches on the forward P5 overhead panel or
the forward flight attendant panel to operate the
electrical system. See the distribution general
description in this section for more information about
the operation effect on distribution.
Electrical Meters, Battery, And Galley Power Module
(P5-13)
You put the BAT switch to the ON position to energize
these buses and components with battery power:
-
Switched hot battery bus
Battery bus
Static inverter
AC standby bus
DC standby bus
P5-13 alphanumeric display.
00-00-00-247.fm
You use the CAB/UTIL switch to control power to:
-
Left and right recirculation fans
Forward and aft door area heaters
Drain mast heaters
Lavatory water heaters
ECS gasper fan
115v ac galley buses
115v ac shaver outlets
Logo lights
Potable water compressor.
-
115v ac audio entertainment equipment
115v ac video entertainment equipment
115v ac airphone equipment
Passenger seat electronic outlets.
You use the dc and ac selectors and the alphanumeric
display to monitor the electrical power system power
sources.
Generator Drive And Standby Power Module (P5-5)
The generator drive disconnect switch operates the
disconnect mechanism for its integrated drive generator
(IDG). This removes engine accessory gearbox power from
the IDG. The engine start lever must be in the idle
position for the disconnect function to operate.
The standby power switch gives you manual control of
the ac and dc standby power bus sources. In the auto
position, the ac standby bus receives power from ac
transfer bus 1, and the dc standby bus receives power
from dc bus 1 when these sources are available. If the
sources are not available, the ac standby bus receives
power from the static inverter, and the dc bus receives
power from the battery.
These are the effects of the standby power switch in
the other two positions:
-
Deenergize the ac standby bus and the dc standby
bus (OFF position)
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737-600/700/800/900 TRAINING MANUAL
737 GENERAL -- ELECTRICAL POWER OPERATION
-
Energize the ac standby bus with battery power
through the static inverter (BAT position)
Energize the dc standby bus with battery power
(BAT position).
AC Systems, Generator, And APU Module (P5-4)
You use the ground power switch to control external
power to the ac transfer buses. The blue GRD POWER
AVAILABLE light above the switch shows if the ground
source is connected and quality is good. The two ac
transfer buses receive power when you put the ground
power switch to the ON position. Initial power sources
are removed before the transfer buses receive external
power.
The bus transfer switch gives you manual control of the
BTBs and the dc bus tie relay. In the AUTO position,
the BTBs and the dc bus tie relay operate as necessary.
are two bus tie breakers (BTBs) that supply power to
the ac transfer buses. The two ac transfer buses
receive APU power with operation of one APU GEN switch
if the ac transfer buses do not have power initially.
If the ac transfer buses do have power, then only the
ac transfer bus on the same side as the APU GEN switch
you operate energizes with APU power.
The blue APU GEN OFF BUS light comes on when the APU is
ready to supply electrical power.
Forward Flight Attendant Panel
You use the ground service switch to supply external
power to ground service bus 1 and 2 with external power
connected. This makes it possible to supply electrical
power for cabin servicing without access to the flight
compartment.
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In the OFF position, the BTBs open and isolate the ac
transfer buses from each other. The dc bus tie relay
also opens. This isolates dc bus 1 and dc bus 2 from
each other. The position also resets the BTB trip
circuits.
You use the GEN 1 and GEN 2 switches to supply IDG power
to an ac transfer bus. The ac transfer bus on that side
goes to IDG power when you temporarily put the switch
to the ON position. Initial power sources are removed.
You use the APU GEN switches to supply power to the ac
transfer buses. There are two switches because there
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737-600/700/800/900 TRAINING MANUAL
DC AMPS
CPS FREQ
DC VOLTS / AC AMPS / AC VOLTS
BAT
DISCHARGE TR UNIT
ELEC
MAINT
AUX BAT
TR1
BAT
BAT
BUS
APU GEN
GEN2
GEN1
TR2
STBY
TR3
PWR TEST
OFF
GRD
PWR
INV
STBY
PWR
TEST
OFF
OFF
ON
CAB/UTIL
AC
ON
IFE/PASS
SEAT
BAT
ON
DC
STANDBY
PWR OFF
1
DRIVE
2
DRIVE
STANDBY POWER
DISCONNECT
DISCONNECT
FLIGHT COMPARTMENT
BAT
OFF
ELECTRICAL METERS
BATTERY AND GALLEY
POWER MODULE
(P5-13)
AUTO
GENERATOR DRIVE
AND STANDBY
POWER MODULE
(P5-5)
GRD POWER
AVAILABLE
GRD
PWR
OFF
ON
BUS TRANSFER
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TRANSFER
BUS OFF
O
F
F
SOURCE
OFF
FORWARD ATTENDANT PANEL
OFF
APU GEN
OFF BUS
GEN OFF
BUS
GROUND SERVICE
SWITCH
A
U TRANSFER
T BUS OFF
O SOURCE
OFF
GEN 1
ON
GEN OFF
BUS
AC SYSTEM
GENERATOR AND
APU MODULE
(P5-4)
OFF
APU GEN
APU
ON
GEN 2
737 GENERAL - ELECTRICAL POWER OPERATION
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737-600/700/800/900 TRAINING MANUAL
737 GENERAL -- ELECTRICAL POWER DISTRIBUTION
General
These AC buses receive power directly from an AC power
source:
-
AC transfer bus 1
AC transfer bus 2
Ground service bus 1
Ground service bus 2.
Each transfer bus supplies power to these components or
buses:
System logic removes loads (load shed) to prevent an
overload of an AC power source.
These DC buses receive power directly from the
transformer rectifier units (TRUs):
-
-
Galleys (as many as 2)
Main Bus
Ground service bus
Transformer rectifier unit (as many as 2).
Ground Service Buses
DC bus 1
DC bus 2
Battery bus
Each ground service bus receives power in one of these
two ways:
-
These buses receive power directly from the main
battery or the main battery charger:
-
The system design makes sure that two AC power sources
can not supply power to the same transfer bus at the
same time. However, one AC power source can supply
power to both transfer buses through the bus tie
breakers (BTBs).
Hot battery bus
Switched hot battery bus.
The AC transfer bus on that side has power
The ground service switch on the forward attendant
panel is in the ON position and external power is
connected to the airplane.
The two ground service transfer relays control the
selection of the power source.
AC Transfer Buses
Main Buses, Galley Buses and IFE/PASS SEAT Buses
00-00-00-242.fm
These AC sources supply power to the AC transfer buses:
-
External power
APU starter-generator
Integrated drive generators (IDGs).
The main buses, galley buses and IFE/PASS SEAT buses
receive power from their respective AC transfer bus.
Load shed relays remove the power to these buses when
their loads exceed operating limits. This protects the
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737-600/700/800/900 TRAINING MANUAL
737 GENERAL -- ELECTRICAL POWER DISTRIBUTION
AC power source from overload. The bus power control
unit (BPCU) controls the load shed function.
The battery bus normally receives power from TRU 3. The
battery bus receives power from the battery if TRU 3
has no output.
DC Buses
DC bus 1 normally receives power from TRU 1. The bus
can receive power from TRU 2 or TRU 3 through the bus
tie relay. This relay is normally energized.
The switched hot battery bus receives power from the
hot battery bus when the battery switch (P5 panel) is
in the ON position.
External Power
DC bus 2 normally receive power from TRU 2. TRU 3
supplies power if TRU 2 fails. DC bus 2 may also
receive power from TRU 1 through the bus tie relay.
External power can supply power to these buses:
-
Standby Buses
The AC standby bus normally receives power from AC
transfer bus 1. The static inverter may also supply
power to this bus. A remote control circuit breaker
(RCCB) controls power to the static inverter.
AC transfer buses
Ground service buses.
External power supplies power to each AC transfer bus
through the external power contactor (EPC) and the
necessary bus tie breaker (BTB).
APU Power
The DC standby bus normally receives power from DC bus
1. The hot battery bus may also supply power to the DC
standby bus.
00-00-00-242.fm
Battery Buses
The hot battery bus normally receives power from the
main battery or main battery charger. The auxiliary
battery and auxiliary battery charger connects in
parallel with the main battery during non-normal
conditions to help supply power. See the DC Generation
section for more information.(AMM PART I 24-30)
The APU starter-generator supplies power to each AC
transfer bus through the APU breaker (APB) and the
necessary BTB. The APU can supply power to both AC
transfer buses on the ground or in flight. See the AC
Generation section for more information.(AMM PART I 2420)
IDG Power
The IDGs are the normal power sources for the AC
transfer buses. An IDG supplies power to the transfer
bus through a generator control breaker (GCB).
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737-600/700/800/900 TRAINING MANUAL
737 GENERAL -- ELECTRICAL POWER DISTRIBUTION
Battery Charger
Each battery charger makes sure its battery stays at
maximum charge. Each battery charger also operates as a
TRU when not in the charge mode.
Remote Control Circuit Breaker (RCCB)
The standby power system uses a remote controlled
circuit breaker (RCCB) to control power input to the
static inverter. This RCCB is normally closed. See the
Standby Power section 24-34 for more information.(AMM
PART I 24-34)
00-00-00-242.fm
The dual battery RCCB closes to put the auxiliary
battery and the auxiliary battery charger output in
parallel with the output of the main battery and its
charger. This RCCB is normally open. See the DC
Generation section for more information.(AMM PART I 2430)
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737-600/700/800/900 TRAINING MANUAL
APU
GEN
IDG
1
GCB 1
GND SVC
XFR RLY 1
IDG
2
EXT
PWR
APB
EPC
GCB 2
AC XFR BUS 2
AC XFR BUS 1
BTB 2
BTB 1
GALLEY (S)
GALLEY (S)
MAIN BUS 1
MAIN BUS 2
GND SVC BUS 2
GND SVC BUS 1
IFE/PASS SEAT
AUX BAT
CHGR
TRU 1
GND SVC
XFR RLY 2
TR3 XFR
RLY
IFE/PASS SEAT
TRU 3
MAIN BAT
CHGR
TRU 2
RCCB
AUX
BAT
STATIC
INVERTER
RCCB
BAT BUS
ALT RLY
BUS TIE
RLY
DC BUS 1
DC BUS 2
STDBY
NORMAL RLY
AC STBY BUS
BAT BUS
NORM RLY
MAIN
BAT
DC STBY BUS
TO APU
START
CIRCUIT
STBY DC
ALTN RLY
BAT BUS
00-00-00-242.fm
FROM DC BUS 1
SW HOT BAT
BUS RLY
GND SVC
BUS RLY
SW HOT BAT BUS
GND SVC DC BUS
737 GENERAL - ELECTRICAL POWER DISTRIBUTION
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HOT BAT BUS
737-600/700/800/900 TRAINING MANUAL
737 GENERAL -- APU FIRE PROTECTION
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737-600/700/800/900 TRAINING MANUAL
737 GENERAL -- APU FIRE PROTECTION
General
You use the overheat/fire protection panel to do the
APU fire protection test and to extinguish an APU fire
from the flight compartment.
You use the APU ground control panel on the main wheel
well to turn off the APU and extinguish an APU fire
from outside the airplane.
Fire Protection System Test
To do a test of the APU squib, put the EXT TEST switch
to position 1 or 2. If the squib is good, the APU squib
light comes on.
Flight Compartment Operation
If the fire detection system detects an APU fire, these
are the results in the flight compartment:
Do a test of the APU fire protection system before you
start the APU. The controls to do the test are on the
overheat/fire protection panel.
Before you do the fire protection system test, alert
the ground crew. The APU fire warning horn comes on
during the test.
-
APU fire handle light on the overheat/fire
protection panel
APU fire handle unlocks
FIRE WARN lights on the glareshield
Fire bell from the aural warning unit
APU shuts down.
To start the test, momentarily put the TEST switch to
FAULT/INOP. The FAULT and APU DET INOP lights come on.
To stop the fire bell, use the bell cutout switch or
the master fire warning lights.
Momentarily put the TEST switch to OVHT/FIRE. Make sure
these indications come on:
To extinguish the fire, use the APU fire handle. Pull
up on the APU fire handle and then turn the handle to
discharge the APU fire bottle.
-
00-00-00-025.fm
Make sure the APU BOTTLE DISCHARGED light is off. This
light is normally off to show a charged APU fire
extinguishing bottle.
-
APU fire handle light on the overheat/fire
protection panel
FIRE WARN lights on the glareshield
Fire bell from the aural warning unit.
Main Wheel Well Operation
In the main wheel well, you hear an intermittent horn
if the fire protection system detects a fire. The APU
fire warning light on the APU ground control panel
flashes.
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737-600/700/800/900 TRAINING MANUAL
737 GENERAL -- APU FIRE PROTECTION
To stop the APU warning horn, use the HORN CUTOUT
switch.
00-00-00-025.fm
To extinguish the fire, pull down the APU ground
control panel fire control handle to arm the
extinguisher. Use the BOTTLE DISCHARGE switch to
discharge the extinguisher.
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737-600/700/800/900 TRAINING MANUAL
APU BOTTLE
DISCHARGE
SWITCH
HORN
CUTOUT
SWITCH
APU
FIRE
CONTROL
FIRE
WARN
MASTER
CAUTION
BELL CUTOUT
PUSH TO RESET
MASTER
FIRE
WARNING
LIGHT (2)
FIRE PROTECTION
TEST SWITCH
00-00-00-025.fm
NORMAL
DISCH
ENG 1
OVERHEAT
L
FI
AN
UO
LP
T
TEST
OF
VI
HR
TE
R
IRS
APU
1.PULL HANDLE DOWN
2.DISCHARGE BOTTLE
BOTTLE DISCHARGE
APU REMOTE FIRE
SWITCH HANDLE
FAULT
APU DET
INOP
APU BOTTLE
DISCHARGE
OVERHEAT/FIRE PROTECTION PANEL (P8)
BELL CUTOUT
OVHT DET
A
DISCH
BOTTLE
DISCHARGE
HORN
CUTOUT
APU FIRE
WARNING LIGHT
BELL CUTOUT
SWITCH
WHEEL
WELL
B
A
ELEC
FUEL
OVHT/DET
MASTER
CAUTION
SYSTEM CAUTION
LIGHT (2) ANNUNCIATOR
APU BOTTLE
DISCHARGE
INDICATOR
OVHT DET
FLT CONT
B
GROUND CONTROL
PANEL (P28)
L BOTTLE R BOTTLE
DISCHARGE DISCHARGE
NORMAL
DISCH
ENG 2
OVERHEAT
L
FIRE SWITCHES
(FUEL SHUTOFF)
PULL WHEN ILLUMINATED
LOCK OVERRIDE: PRESS
BUTTON UNDER HANDLE
R
ENGINES
ET
XE 1
TS
T
2
R
L
APU
EXT TEST
SWITCH
APU
SQUIB
LIGHT
APU FIRE HANDLE
737 GENERAL - APU FIRE PROTECTION
00-00-00
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737-600/700/800/900 TRAINING MANUAL
737 GENERAL -- APU OPERATION
00-00-00-496.fm
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737-600/700/800/900 TRAINING MANUAL
737 GENERAL -- APU OPERATION
The APU GEN OFF BUS light comes on when the APU is ready
to supply electrical power.
General
When you do maintenance, you start the APU to supply
electrical power and bleed air.
The APU switch lets you control the APU. The APU
electronic control unit (ECU) controls the system
operation.
The APU indicator panel shows system status.
Start
The battery switch must be ON before you can start and
operate the APU.
If AC power is available, turn the aft number 1 fuel
boost pump on. This gives pressurized fuel to the APU.
Pressurized fuel makes the APU start better.
The maintenance, fault, and overspeed lights normally
are off. If these lights come on, refer the problem to
a qualified APU technician.
Shutdown
The ECU also controls the APU shutdown. Normally, to
shutdown the APU, you put the APU switch to OFF. This
starts a cool down cycle. The cool down cycle time is
approximately 60 seconds. When the cool down cycle is
complete, the APU shuts down.
The ECU can also automatically shutdown the APU. If the
ECU finds a shutdown condition, the ECU does a
protective shutdown. A protective shutdown causes one
of these indications on the APU indicator panel to come
on:
The ECU controls the APU start sequence.
00-00-00-496.fm
When you move the APU switch to START and release it,
the switch moves back to the ON position. The ECU goes
through the start sequence. The time for the start
sequence is about 60 seconds.
The low oil pressure light comes on and stays on for
approximately 30 seconds. The APU exhaust gas
temperature (EGT) increases.
-
Fault light
Overspeed light
Low oil pressure light.
Training Information Point
The BAT DISCHARGE light on the electrical meters,
battery, and galley power module comes on when the APU
start uses DC power. The BAT DISCHARGE light does not
come on when the APU uses AC power to start.
See the APU chapter for more information on the
specific operating range of the APU. (AMM PART I 49)
00-00-00
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See title page for details
737-600/700/800/900 TRAINING MANUAL
737 GENERAL -- APU OPERATION
The APU fuel shutoff valve and air inlet door will
close for a normal or protective shutdown. Wait 40
seconds after the EGT goes below 300 C for the inlet
door and fuel shutoff valve to close before you move
the battery switch to the OFF position.
Do not use the battery switch or fire switches to begin
a normal APU shutdown. The 60-second cool down is
required to prevent coke in the turbine bearing and
fuel nozzles.
If the fuel shutoff valve does not close in the
required time, the APU FAULT light comes on and stays
on until you start the APU again or you put the battery
switch in the OFF position.
00-00-00-496.fm
See the engines controls section for more information
on APU faults.(AMM PART I 49-60)
00-00-00
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737-600/700/800/900 TRAINING MANUAL
LOW OIL
PRESSURE
MAINT
FAULT
OVER
SPEED
APU GEN OFF BUS
LIGHT (ON P5-4)
10
8 EGT
6
4
0
2
APU INDICATOR PANEL
STBY
PWR
TR3
TEST
APU GEN
OFF BUS
APU
OFF
ON
BAT
START
ON
DC
00-00-00-496.fm
BATTERY
SWITCH
APU
SWITCH
START OPERATION
- BATTERY SWITCH ON
- APU SWITCH TO THE START
POSITION & RELEASE TO ON
- LOW OIL PRESSURE LIGHT COMES
ON, THEN GOES OFF IN
APPROXIMATELY 30 SECONDS
- EGT INCREASES
- MAINT, FAULT AND OVERSPEED
LIGHTS OFF
- APU GEN OFF BUS LIGHT ON WHEN
APU IS READY TO SUPPLY POWER
NORMAL SHUTDOWN
- APU SWITCH TO THE OFF
POSITION
- 60-SECOND COOL DOWN
- APU SHUTS DOWN
PROTECTIVE SHUTDOWN
- ECU SHUTS DOWN APU IF
DETECTS SHUTDOWN
CONDITION
- LOW OIL PRESSURE, FAULT,
OR OVERSPEED LIGHT ON
737 GENERAL - APU OPERATION
00-00-00
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737-600/700/800/900 TRAINING MANUAL
737 GENERAL -- EQUIPMENT COOLING
General
To prevent damage to equipment, you must make sure that
cooling air is on while electrical power is on. The
controls and indications for the equipment cooling
system are on the equipment cooling panel.
Operation
The equipment cooling panel has an equipment cooling
SUPPLY switch and an equipment cooling EXHAUST switch.
Each switch has two positions:
-
NORMAL
ALTERNATE.
You put the switch in one of these positions to operate
the normal or the alternate fan.
Indication
The equipment cooling supply or exhaust OFF light and a
master caution light comes on when a failure occurs.
00-00-00-027.fm
The equipment cooling system has low flow detectors to
give a warning when there is not sufficient cooling
airflow. On the ground the ground crew call horn comes
on when low flow is found. This occurs to prevent an
overheat condition.
00-00-00
- 88 ALTEON PROPRIETARY. Copyright.
See title page for details
737-600/700/800/900 TRAINING MANUAL
ARM
ON
A ON
B ON
OFF
ON
BAT
TR UNIT
DISCHARGE
SPEED TRIM
FAIL
YAW DAMPER
MACH TRIM
FAIL
YAW
DAMPER
AUTO SLAT
FAIL
ON
STBY
PWR
NORMAL
ON
TEST
OFF
ON
CAB/UTIL
ON
IFE/PASS
SEAT
FMC
AC
STANDBY
PWR OFF
1
BOTH
ON L
BOTH
ON R
DRIVE
NORMAL
DISCONNECT
BOTH
ON 1
OFF
OFF
ARMED
NR
OM
TE
GRD POWER
AVAILABLE
OFF
OFF
VALVE
OPEN
O
F
F
TRANSFER
BUS OFF
SOURCE
OFF
LOW
LOW
PRESSURE PRESSURE
ERASE
A
U TRANSFER
T BUS OFF
O
OFF
GEN 1
R
ON
LOW
LOW
PRESSURE PRESSURE
AFT
CALL
8
FWD
PARK
10
EGT
4
EXHAUST
NORM
RUNWAY
TURNOFF
TAXI
L
R
OFF
OFF
LANDING
RETRACT
OFF
L
ON R
RETRACTABLE
L
ON
R
FIXED
INT
LOW
LOW
HIGH
HIGH
APU
OFF
ON
PARK
INT
0
2
ON
PRESS DIFF
LIMIT:TAKEOFF & LDG
.125 PSI
15
6
5
00-00-00-027.fm
OFF SCHED
DESCENT
ALT
HORN
CUTOUT
2
ALTN
MANUAL
GRD OFF CONT
GRD OFF CONT
BOTH
FLT IGN
FLT
IGN
R
L
LAND ALT
CAB ALT LAND ALT 2000
FLT ALT
ON
ON
STEADY
START
1
2
P5 FORWARD OVERHEAD PANEL
EMER EXIT LIGHTS
EQUIPMENT COOLING
PANEL
737 GENERAL - EQUIPMENT COOLING
00-00-00
- 89 See title page for details
ON
O
P
E
N
ALTN
AUTO
MAN
4000
6000
8000
<FL160 FL220 FL260 FL320 FL410
ANTI
POSITION
STERILE LOGO STROBE & COLLISION WING
OFF
OFF
OFF
OFF
STEADY
ON
V
A
L
V
E
C
L
O
S
E
1
2
.5
IN CLIM 3
UP AB
4
0
DN 0 F
EET PER 3
.5
2
1
ENGINE START
MANUAL
FLT ALT
4
OFF
ALTEON PROPRIETARY. Copyright.
ON
APU
3
10
20
ALTN
OFF
OFF
ON
1
AUTO
FAIL
2
5
100
SUPPLY
8
6
R WIPER
WING
ANTI
ICE
BLEED
1
B
EQUIP COOLING
AFT
ON
2
E
X
T
E
N
D
7
L WIPER
OFF
1
T
I O
N
D L
E O
X C
K
GEN 2
OVER
SPEED
FAULT
LOW
LOW
PRESSURE PRESSURE
FUEL
PUMPS
ON
LOW OIL
PRESSURE
MAINT
FWD
OFF
ON
APU GEN
APU
ON
RESET
OFF
AUTO
HIGH
PACK
TRIP OFF
WING-BODY
OVERHEAT
BLEED
TRIP OFF
HEADPHONE
PRESS0
DIFF I
10 PS
0
50
CABIN
40
ALT
35
30
25
OFF
CTR
OPEN
TRIP
AUTO
9
OFF
AUTO
PACK
TRIP OFF
WING-BODY
OVERHEAT
BLEED
TRIP OFF
OFF
TEST
STATUS
GRD
CALL
ATTEND
GEN OFF
BUS
APU GEN
OFF BUS
FUEL PUMPS
L
AFT
CARGO
OFF
AUTO
ON
SOURCE
OFF
GEN OFF
BUS
FWD
CARGO
LEFT AFT RIGHT AFT
OVERWING OVERWING
AFT
AFT
ENTRY
SERVICE
OVHT
R PACK
ISOLATION
VALVE
CLOSE
OFF
AUTO
HIGH
COCKPIT VOICE RECORDER MICROPHONE MONITOR
BUS TRANSFER
FILTER
BYPASS
FEED
L PACK
B
LEFT FWD RIGHT FWD
OVERWING OVERWING
FASTEN
BELTS
DUCT
PRESS
PSI
0
TEST
WING
ANTI
ICE
EQUIP
80
20
ON
HYD PUMPS
A
60
40
ELEC 1 ENG 2
ON
NO
SMOKING
ON
CROSS
OVERHEAT
LOW
LOW
PRESSURE PRESSURE
D
GRD
PWR
OFF
SPAR VALVE
CLOSED
40
C
FILTER
BYPASS
OVERHEAT
ENG 1 ELEC 2
OFF
ENG VALVE
CLOSED
0
-20 FUEL
TEMP 20
-40
RECIRC FAN
2
OFF
A
ENG VALVE
CLOSED
RAM DOOR
FULL OPEN
RAM DOOR
FULL OPEN
ON
LOW
LOW
PRESSURE PRESSURE
EMER EXIT LIGHTS
BOTH
ON 2
NORMAL
SPAR VALVE
CLOSED
WARM
COOL
WARM
OFF
MANUAL
OFF
NORMAL
AUTO
COOL
WARM
AUTO
EQUIP COOLING
EXHAUST
SUPPLY
ALTERNATE
DISCONNECT
BAT
AUTO
NORMAL
DUAL
BLEED
OFF
1
ON
CONTROL PANEL
ALL
ON 2
DUCT
OVERHEAT
C
COOL
WARM
OFF
MANUAL
ENG
ANTI-ICE
ON
D
100
0o
COWL VALVE COWL VALVE
OPEN
OPEN
SMOKE
2
DISPLAYS
SOURCE
ALL AUTO
ON 1
LAVATORY
DRIVE
STANDBY POWER
80
20
COOL
R VALVE
OPEN
OFF
OFF
DC
NORMAL
60
40 TEMP
COWL
COWL
ANTI-ICE ANTI-ICE
L VALVE
OPEN
WING ANTI-ICE
OFF
BAT
BOTH
ON R
AIR MIX
VALVE
H
DUCT
OVERHEAT
PANEL
OFF
BOTH
ON L
PASS CABIN
PASS
CABIN
AUTO
NORMAL
INV
STBY
PWR
TEST
IRS
BOTH
ON 2
ON
HEAT
APU GEN
GEN2
GEN1
GRD
PWR
TR3
B
SUPPLY
DUCT
AIR MIX
VALVE
H
D
OFF
ELEC
TR2
NAVIGATION
VHF NAV
BOTH
ON 1
F/O
PITOT
R ELEV
PITOT
R ALPHA
VANE
AUX
PITOT
OFF
AIR TEMP
CONT CABIN
TAT TEST
MAINT
TR1
BAT
BAT
BUS
OFF
PROBE
A
DC VOLTS / AC AMPS / AC VOLTS
FEEL
DIFF PRESS
ON
OT
CIRCUIT BREAKER
CAPT
PITOT
L ELEV
PITOT
L ALPHA
VANE
TEMP
PROBE
PWR TEST
OT
DOWN
ARM
OFF
SIDE
OFF
ON
OFF
B
ON
CPS FREQ
UP
SPOILER
A
DC AMPS
ON
R
FWD
OFF
HORN CUTOUT
LOW
LOW
PRESSURE PRESSURE
OVHT
FWD
AUTO
ON
ON
WINDOW HEAT
SIDE
VOICE
RECORDER
OVERHEAT OVERHEAT
ON
ON
L
ALTERNATE FLAPS
OFF
OVERHEAT OVERHEAT
OFF
STBY
RUD ON
COL
EVAC
LOW
PRESSURE
OFF
R L
EVACUATION
LOW
QUANTITY
STBY
RUD
COL
STANDBY HYD
B
C
A
OFF
MIN
FLT CONTROL
STBY
RUD
ON
WHEEL
WELL
OFF
ON
T
I O
N
D L
E O
X C
K
737-600/700/800/900 TRAINING MANUAL
737 GENERAL -- HYDRAULIC POWER OPERATION
00-00-00-294.fm
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00-00-00
- 90 ALTEON PROPRIETARY. Copyright.
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737-600/700/800/900 TRAINING MANUAL
737 GENERAL -- HYDRAULIC POWER OPERATION
General
You pressurize the hydraulic systems with a ground
service cart or with the hydraulic pumps.
The switches on the hydraulic panel lets you control
hydraulic system A and B hydraulic pumps.
Normally, the engine-driven pumps are on. When the
engines are on, the engine-driven pumps come on to also
pressurize systems A and B.
An overheat light lets you monitor the system
temperature.
Training Information Point
The flight control panel lets you control the standby
hydraulic system.
Ground Service Cart Pressurization
To pressurize hydraulic system A, connect a ground
service cart to the left ground service disconnect.
To pressurize hydraulic system B, connect a ground
service cart to the right ground service disconnect.
You can not pressurize the standby system from a ground
service cart.
Hydraulic Pump Pressurization
00-00-00-294.fm
You use the hydraulic panel to operate and to monitor
the hydraulic pumps for system A and B. The flight
control panel lets you operate the standby pump.
You pressurize system A and B with an engine-driven
pump (EDP) or an electric motor-driven pump (EMDP). The
ELEC 1 and ELEC 2 switches on the hydraulic panel let
you control the EMDPs. The hydraulic low pressure
lights go off when the hydraulic pressure is normal.
If you pressurize the hydraulic systems with the
hydraulic pumps, make sure there is sufficient fuel in
the main fuel tanks to remove heat from the heat
exchangers.
To pressurize a hydraulic system with a ground service
cart, first you must remove the pressure from the
hydraulic reservoir.
WARNING: KEEP PERSONS AND EQUIPMENT AWAY FROM ALL
CONTROL SURFACES AND THE NOSE GEAR WHEN
HYDRAULIC POWER IS SUPPLIED. THE AILERONS,
ELEVATORS, RUDDER, FLAPS, SLATS, SPOILERS,
AND THE NOSE GEAR ARE SUPPLIED WITH POWER BY
THE HYDRAULIC SYSTEMS. INJURIES TO PERSONS OR
DAMAGE TO EQUIPMENT CAN OCCUR WHEN HYDRAULIC
POWER IS SUPPLIED.
CAUTION: YOU MUST MONITOR THE INSTRUMENTS AND INDICATOR
LIGHTS FOR THE HYDRAULIC SYSTEMS WHEN
HYDRAULIC SYSTEMS ARE PRESSURIZED. THIS IS TO
MAKE SURE THE HYDRAULIC SYSTEMS OPERATE
CORRECTLY. IF THE OVERHEAT LIGHT OF A
00-00-00
- 91 ALTEON PROPRIETARY. Copyright.
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737-600/700/800/900 TRAINING MANUAL
737 GENERAL -- HYDRAULIC POWER OPERATION
HYDRAULIC SYSTEM COMES ON, YOU MUST STOP THE
OPERATION OF THAT HYDRAULIC SYSTEM
IMMEDIATELY. DAMAGE TO THE EQUIPMENT CAN OCCUR
IF YOU DO NOT DO THIS.
00-00-00-294.fm
CAUTION: DO NOT OPERATE THE EMDP FOR MORE THAN TWO
MINUTES IF A MAIN FUEL TANK CONTAINS LESS THAN
250 GALLONS (1675 POUNDS/761 KILOGRAMS) OF
FUEL. YOU MUST LET THE RESERVOIR TEMPERATURE
DECREASE TO AMBIENT TEMPERATURE BEFORE YOU
OPERATE THE PUMP AGAIN. DAMAGE TO EQUIPMENT
CAN OCCUR IF YOU DO NOT DO THIS.
00-00-00
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737-600/700/800/900 TRAINING MANUAL
FLT CONTROL
A
STANDBY HYD
B
LOW
QUANTITY
STBY
RUD
STBY
RUD
LOW
PRESSURE
OFF
OFF
A ON
B ON
STBY
RUD ON
ALTERNATE FLAPS
OFF
UP
LOW
LOW
PRESSURE PRESSURE
OFF
SPOILER
A
B
ARM
OFF
OFF
ON
ON
DOWN
FEEL
DIFF PRESS
SPEED TRIM
FAIL
YAW DAMPER
MACH TRIM
FAIL
YAW
DAMPER
AUTO SLAT
FAIL
OFF
ON
FLIGHT CONTROL PANEL
P5 OVERHEAD PANEL
RETURN
CONNECTION
00-00-00-294.fm
OVERHEAT
OVERHEAT
LOW
LOW
PRESSURE PRESSURE
LOW
LOW
PRESSURE PRESSURE
ENG 1 ELEC 2
ELEC 1 ENG 2
OFF
OFF
FWD
ON
ON
A
PRESSURE
CONNECTION
HYD PUMPS
B
LEFT GROUND SERVICE DISCONNECT (SYSTEM A)
(RIGHT GROUND SERVICE DISCONNECT SIMILAR)
HYDRAULIC PANEL
737 GENERAL - HYDRAULIC POWER OPERATION
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737-600/700/800/900 TRAINING MANUAL
737 GENERAL -- COMMUNICATION EQUIPMENT COMPONENT LOCATIONS - 1
Flight Compartment Component locations
These are the captain and first officer flight
interphone system components:
-
Remote mic switch
Boom mic jack
Headphone jack
Hand mic jack
Oxygen mask mic jack
Control column mic switch
Flight interphone speaker
Audio control panel.
The service interphone switch is on the P5 aft overhead
panel.
The passenger signs panel is on the P5 forward overhead
panel.
00-00-00-231.fm
The controls for the VHF radios are on the P8 aft
electronics panel.
00-00-00
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737-600/700/800/900 TRAINING MANUAL
SERVICE INTERPHONE SWITCH
OBSERVER AUDIO CONTROL PANEL
PASSENGER SIGNS PANEL
CAPT FLIGHT INTERPHONE SPEAKER
F/O FLIGHT INTERPHONE SPEAKER
CAPT JACKS (AFT OF
NO. 5 LEFT WINDOW)
- BOOM MICROPHONE
- HEADPHONE
F/O JACKS (AFT OF
NO. 5 RIGHT WINDOW)
- BOOM MICROPHONE
- HEADPHONE
CAPT REMOTE
MIC SWITCH
F/O REMOTE
MIC SWITCH
CAPT CONTROL
COLUMN MIC SWITCH
F/O CONTROL
COLUMN MIC SWITCH
CAPT JACKS
- MASK MICROPHONE
- HAND MICROPHONE
00-00-00-231.fm
F/O JACKS
- HAND MICROPHONE
- MASK MICROPHONE
P8 AFT ELECTRONIC PANEL
- CAPT AUDIO CONTROL PANEL
- F/O AUDIO CONTROL PANEL
- RADIO COMMUNICATION PANEL 1
- RADIO COMMUNICATION PANEL 2
- RADIO COMMUNICATION PANEL 3
737 GENERAL - COMMUNICATION EQUIPMENT COMPONENT LOCATIONS - 1
00-00-00
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737-600/700/800/900 TRAINING MANUAL
737 GENERAL -- COMMUNICATION EQUIPMENT COMPONENT LOCATIONS - 2
Jack Locations
These locations have service interphone jacks:
P19 external power panel (location A)
Electronic rack (location B)
Right wing refueling slat (loction C)
Right wheel well (location D)
Left wheel well (location E)
Aft entry light panel (location F)
APU (location G).
00-00-00-232.fm
-
00-00-00
- 96 ALTEON PROPRIETARY. Copyright.
See title page for details
737-600/700/800/900 TRAINING MANUAL
C
A
B
LOCATION
A
B
C
D
E
F
G
EXT PWR PNL
ELECTRONICS RACK
RT WING REFUELING SLAT
RIGHT WHEEL WELL
LEFT WHEEL WELL
AFT ENTRY LIGHT PNL
APU
F
G
E
00-00-00-232.fm
CODE
D
737 GENERAL - COMMUNICATION EQUIPMENT COMPONENT LOCATIONS - 2
00-00-00
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737-600/700/800/900 TRAINING MANUAL
737 GENERAL -- FLIGHT INTERPHONE SYSTEM OPERATION
General
-
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.
You hear audio on the headphones that are connected at
the other stations.
Flight Interphone Components
The ground crew can listen and talk to the flight crew
with a headset connected to the flight interphone jack
on the external power panel.
These are the captain and first officer flight
interphone system components:
-
-
Push down on the FLT INT receive volume switch and
turn the switch to adjust the volume
Push the FLT INT mic selector switch to select the
flight interphone system.
Key a mic switch. You use either the mic switch on
the control wheel or the radio-intercom (R/T-I/C)
switch on the audio control panel.
Talk on a microphone.
Control wheel microphone switch
Audio control panel (ACP)
Hand microphone
Oxygen mask
Headset
Hand microphone (mic)
Speaker.
The observer has the same components without a control
column microphone switch, boom mic jack, or speaker.
00-00-00-233.fm
The external power panel has a flight interphone jack
for the ground crew.
Operation
To talk between the pilot stations, do these on the
audio control panels:
00-00-00
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737-600/700/800/900 TRAINING MANUAL
FLT INT MIC
SELECTOR
FLT
FLT INT RECEIVE
VOLUME CONTROL
CONTROL WHEEL
MIC SWITCH
RADIOINTERCOM
SWITCH
FLIGHT INTERPHONE
SPEAKERS (2)
R/T
I/C
AUDIO CONTROL PANEL (3)
EXTERNAL
POWER
CONN
INTERPHONE
FLIGHT
PILOT
SERVICE
NOSE
WHEEL WELL
ON
00-00-00-233.fm
NORM
OXYGEN MASKS
HEADSETS
HEADPHONE
HAND MIC
MICROPHONES AND HEADSETS
NOT
IN USE
CALL
EXTERNAL POWER PANEL
737 GENERAL - FLIGHT INTERPHONE SYSTEM OPERATION
00-00-00
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LIGHT
737-600/700/800/900 TRAINING MANUAL
737 GENERAL -- CREW CALL OPERATION
signal to make the flight interphone call light on the
audio control panel come on.
General
The ground crew call system makes call signals between
the flight compartment and ground crew.
Aural signals from the system tells you to use the
service interphone.
Components
The ground crew call system has these components:
-
Ground call switch on the passenger signs panel
Pilot call switch on the external power panel
Ground crew call horn.
The system uses the aural warning module for alerts in
the flight compartment.
Operation
00-00-00-234.fm
A crew member pushes the GRD CALL switch in the flight
compartment to call the ground crew. The switch is on
the passenger signs panel on the P5 forward overhead
panel. A horn in the nose wheel well makes a sound when
the crew member uses the switch.
The ground crew pushes the PILOT CALL switch on the
external power panel to call the flight compartment.
This sends a signal to the remote electronics unit and
to the aural warning module. The aural warning module
makes a high chime. The remote electronics unit sends a
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737-600/700/800/900 TRAINING MANUAL
GRD
CALL
ATTEND
GROUND CREW
CALL HORN
PASSENGER SIGNS PANEL
FLT INTERPHONE
CALL LIGHT
EXTERNAL
POWER
CONN.
INTERPHONE
FLIGHT
PILOT CALL
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REMOTE
ELECTRONICS
UNIT
AUDIO CONTROL
PANEL
SERVICE
NWW LIGHT
ON
NOT
IN USE
NORMAL
AURAL WARNING MODULE
EXTERNAL POWER PANEL
737 GENERAL - CREW CALL OPERATION
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737-600/700/800/900 TRAINING MANUAL
737 GENERAL -- 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 ground crew hears audio when a headset connects to
a service interphone jack. For other stations to hear
the ground crew, the service interphone switch must be
ON.
The flight attendants use the service interphone system
to speak with each other and the pilots.
Components
The service interphone system has these components:
-
Service interphone jacks
Attendant handsets
Service interphone switch.
The pilots can use the flight interphone system to
interface with the service interphone system.
Operation
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From the flight compartment, you select the service
interphone function with the audio control panel (ACP).
Push the service interphone mic selector switch and
adjust the receiver volume control.
The attendant handset automatically connects into the
service interphone system when the handset is removed
from the cradle.
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737-600/700/800/900 TRAINING MANUAL
OFF
- FLIGHT INTERPHONE
- MICROPHONES
- HEADSETS
- SPEAKERS
ON
SERVICE INTERPHONE
SWITCH
SERVICE INTERPHONE
MIC SELECTOR
SERVICE INTERPHONE
RECEIVE VOLUME
CONTROL
CABIN
ATTENDANT
HANDSET (2)
C
C
C
C
C
C
C
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PASSENGER CABIN
SERVICE INTERPHONE
JACK (7)
AUDIO CONTROL PANEL (3)
FLIGHT COMPARTMENT
737 GENERAL - SERVICE INTERPHONE SYSTEM
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737-600/700/800/900 TRAINING MANUAL
737 GENERAL -- VHF COMMUNICATION SYSTEM OPERATION
General
You use these components to operate the VHF radio:
-
Use the frequency selectors to tune the radio to a new
frequency. The standby frequency display shows the new
frequency.
When you are sure the frequency is correct, push the
frequency transfer switch. The active frequency
indicator shows the new frequency. The VHF radio uses
the new frequency.
Microphone or headset
Radio communication panel (RCP)
Audio control panel.
Receive Operation
You use the radio communication panel and the audio
control panel to receive transmissions on the VHF
radio.
Listen to the audio from the VHF radio on the speaker
or headset. Adjust the volume control switches on the
audio control panel for a comfortable sound level.
Transmit Operation
On the audio control panel, push the receiver volume
control for the VHF radio. Turn the control to adjust
the volume from the VHF radio.
00-00-00-236.fm
You hear audio on the headset and the flight interphone
speakers. To hear sound from the flight interphone
speakers, push the speaker (SPKR) volume control to
turn on the speaker. Turn the control to adjust the
volume of sound from the speaker.
When you apply power to the airplane, the radio
communication panels (RCPs) are on. Initially, RCP 1
tunes VHF 1 and RCP 2 tunes VHF 2. Push the VHF switch
for the VHF radio you want to use. A light on the switch
comes on to show which radio the panel controls. The
frequency indicators show VHF radio frequencies
(118.000 to 136.975 kHz). The VHF transceiver tunes to
the frequency in the active frequency indicator.
Make sure the active frequency indicator shows the
frequency you want to transmit. Make sure the frequency
you select is a valid transmit frequency.
Push the microphone selector switch on the audio
control panel for the VHF radio.
Listen for transmissions on the frequency you selected.
When the frequency is clear and you want to transmit a
message, key the mic and speak into it. You hear
sidetone in the headphone and muted sidetone from the
speaker. The flight interphone system mutes the
sidetone to the speaker when you use the boom mic or
the hand mic.
You can continue to transmit and receive on the
frequency you selected.
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737-600/700/800/900 TRAINING MANUAL
MIC SWITCH
R/T
ACTIVE
V
H
F
/
H
F
STANDBY
PANEL
OFF
VHF1
VHF2
VHF3
HF1
AM
HF2
SEN
TEST
VHF
AUDIO CONTROL PANEL
HAND
MICROPHONE
CONTROL WHEEL
PTT SOURCE
C
O
M
M
RADIO COMMUNICATION PANEL
1
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1-VHF
1
INOP
INOP PLACARDS ARE OVER THE LEGEND
OF ANY RADIO SELECT SWITCH
THAT IS NOT CONNECTED.
AUDIO CONTROL PANEL
(VHF SELECT)
737 GENERAL - VHF COMMUNICATION SYSTEM OPERATION
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737-600/700/800/900 TRAINING MANUAL
737 GENERAL -- MAIN LANDING GEAR DOWNLOCK PIN
General
You install a downlock pin into the main landing gear
(MLG) to prevent an outside force from unlocking the
main landing gear.
There is one main landing gear downlock pin for each
main landing gear.
The downlock pin installs in the MLG downlock strut.
00-00-00-323.fm
WARNING: YOU MUST CAREFULLY INSTALL THE GROUND LOCKS IN
ALL LANDING GEAR. AN ACCIDENTAL RETRACTION OF
THE LANDING GEAR CAN CAUSE INJURY TO PERSONS
AND DAMAGE TO EQUIPMENT.
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737-600/700/800/900 TRAINING MANUAL
DOWNLOCK
SPRING (2)
DOWNLOCK
ACTUATOR
REACTION
LINK
DOWNLOCK
PIN HOLE
UPPER
SIDE
STRUT
DOWNLOCK
STRUT
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LEFT MAIN LANDING GEAR
(LOOKING FORWARD)
FWD
737 GENERAL - MAIN LANDING GEAR DOWNLOCK PIN
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737-600/700/800/900 TRAINING MANUAL
737 GENERAL -- NOSE LANDING GEAR DOWNLOCK PIN
General
You install a downlock pin into the nose landing gear
(NLG) to prevent an outside force from unlocking the
nose landing gear.
There is one nose landing gear downlock pin for the
nose landing gear.
The nose landing gear downlock pin installs in the NLG
downlock pin hole.
00-00-00-324.fm
WARNING: YOU MUST CAREFULLY INSTALL THE GROUND LOCKS IN
ALL LANDING GEAR. AN ACCIDENTAL RETRACTION OF
THE LANDING GEAR CAN CAUSE INJURY TO PERSONS
AND DAMAGE TO EQUIPMENT.
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737-600/700/800/900 TRAINING MANUAL
UPPER
DRAG
BRACE
FORWARD
LOCK LINK
AFT
LOCK LINK
FWD
00-00-00-324.fm
NLG
DOWNLOCK
PIN HOLE
FWD
NOSE LANDING GEAR
NOSE LANDING GEAR LOCKING MECHANISM
737 GENERAL - NOSE LANDING GEAR DOWNLOCK PIN
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LOWER
DRAG
BRACE
737-600/700/800/900 TRAINING MANUAL
737 GENERAL -- TOWING LEVER
General
A towing lever permits you to depressurize the nose
wheel steering system. Because of this, you do not have
to depressurize hydraulic system A to tow the airplane.
The towing lever is on the left side of the metering
valve module above the steering actuator.
WARNING: MAKE SURE ALL PERSONS AND EQUIPMENT ARE AWAY
FROM THE NOSE GEAR UNTIL THE NOSE GEAR IS
CENTERED. A FAST MOVEMENT OF NOSE GEAR CAN
OCCUR IF THE HYDRAULIC SYSTEM IS PRESSURIZED
WHEN THE LOCKOUT PIN IS REMOVED. THIS CAN
CAUSE INJURY TO PERSONS AND DAMAGE TO
EQUIPMENT.
Operation
The towing lever is spring-loaded to the off position.
Move the lever forward to the tow position. Insert a
pin in the pin hole in the lever to hold the lever in
the towing position. A placard on the protective cover
(not shown) shows the two positions of the towing
lever.
If you tow the airplane and turn the nose wheels more
than 78 degrees, you must disconnect the torsion links.
Support the lower torsion link from dragging on the
ground when it is disconnected.
00-00-00-329.fm
A red stripe on the outside of each nose landing gear
door shows when the wheels are at 78 degrees. When the
tow bar aligns with the red stripe, the wheels are at
78 degrees.
If you tow the airplane and turn the nose wheels more
than 90 degrees, you must disconnect the taxi light
wire bundle.
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737-600/700/800/900 TRAINING MANUAL
TOWING
LEVER
FWD
NOSE LANDING GEAR
TOWING
LEVER
00-00-00-329.fm
PIN HOLE
FWD
RED
STRIPE
NOSE WHEEL STEERING HYDRAULIC COMPONENTS
(PROTECTIVE COVER REMOVED)
TORSION
LINKS
737 GENERAL - TOWING LEVER
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737-600/700/800/900 TRAINING MANUAL
737 GENERAL -- PARKING BRAKE SYSTEM
THEREFORE, AFTER A HIGH ENERGY STOP, OR
FOLLOWING TOUCH AND GO STOPS, A COOLING PERIOD
OF 40 TO 60 MINUTES SHOULD BE ALLOWED BEFORE
THE PARKING BRAKE IS SET.
Purpose
The parking brake system uses the normal hydraulic
brake system to keep the main landing gear brakes
applied when you park the airplane.
Parking Brake System Indication
A red parking brake light next to the parking brake
lever shows the condition of the parking brake system.
A brake pressure indicator shows the available brake
pressure.
Operation
To set the parking brakes, push the brake pedals and
pull the parking brake lever. The linkage latches the
brake pedals in the brakes-applied position.
A fully charged brake accumulator shows 3000 PSI on the
brake pressure indicator. This keeps the brakes
pressurized for at least 8 hours.
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Training Information Point
CAUTION: PARKING BRAKES SHOULD NOT BE SET FOLLOWING A
HIGH ENERGY STOP. HIGH ENERGY STOPS ARE
DEFINED AS A REFUSED TAKE OFF OR ANY STOP
OTHER THAN NORMAL. UNDER STATIC PRESSURE, HOT
BRAKE SURFACES TEND TO FUSE TOGETHER.
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737-600/700/800/900 TRAINING MANUAL
3
2
4
1
BRAKE
PRESS
0
BRAKE PRESSURE INDICATOR
BRAKE
PEDALS (4)
PARKING
BRAKE LEVER
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PARKING
BRAKE LIGHT
CONTROL STAND
737 GENERAL - PARKING BRAKE SYSTEM
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737-600/700/800/900 TRAINING MANUAL
737 GENERAL -- AIRPLANE TOWING
General
You tow the airplane with a towbar that connects to the
nose gear tow fitting.
You install a special eyebolt on each main gear to move
the airplane in non-normal conditions or to moor the
airplane.
You can also tow the airplane with towbarless
equipment.
WARNING: WHEN YOU TOW THE AIRPLANE, ALL PERSONS MUST
STAY OUT OF THE DANGEROUS AREAS AROUND THE TOW
VEHICLE, TOW BAR, AND NOSE WHEELS. PERSONNEL
ON THE GROUND MUST BE AWARE OF THE POSSIBILITY
OF BEING RUN OVER BY THE NOSE WHEELS. THE TOW
VEHICLE, TOW BAR, AND AIRPLANE WILL CHANGE
POSITION DURING PUSHBACK AND TOWING. MAINTAIN
A MINIMUM OF 10 FEET SEPARATION BETWEEN
PERSONS ON THE GROUND AND THE EQUIPMENT THAT
MOVES. A FATAL INJURY COULD OCCUR.
00-00-00-029.fm
See part two of the maintenance manual for more
information about towing the airplane.
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00-00-00-029.fm
737-600/700/800/900 TRAINING MANUAL
NOSE GEAR TOW
FITTING
MAIN LANDING GEAR
TOW FITTING
737 GENERAL - AIRPLANE TOWING
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737-600/700/800/900 TRAINING MANUAL
737 GENERAL -- TOWING OPERATION
General
You push or pull the airplane with a suitable tow
vehicle. The design of the airplane lets you tow the
airplane from the nose or the main landing gear.
You normally tow the airplane by the nose gear. A tow
bar from a tow vehicle connects to a fitting on the
nose gear. The maximum turn angle is 78 degrees for
normal towing. Red stripes on the nose gear doors show
this towing limit. Disconnect the nose gear torsion
link for turn angles more than 78 degrees. Disconnect
the torsion link and the taxi light cable for turn
angles more than 90 degrees.
You use a towbarless equipment to move the airplane as
an alternate tow vehicle.
00-00-00-328.fm
You tow from the main gear for unusual towing
conditions such as towing on soft ground or on an
incline. This prevents loads more than the nose gear
structural limits. A tow fitting connects to an eye in
the jacking cone on each main gear. A locally
fabricated cable connects this cable to the tow
vehicle. The maximum turn angle is 30 degrees when you
tow from the main gear.
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737-600/700/800/900 TRAINING MANUAL
MAX STEERING
ANGLE
30 DEG
78 DEG
00-00-00-328.fm
SEE NOTES 1 AND 2
NOTES: 1. DISCONNECT NOSE GEAR TORSION
LINK WHEN TOWING AT ANGLES >78 DEG
2. DISCONNECT TORSION LINK AND
TAXI LIGHT CABLE WHEN TOWING
AT ANGLES >90 DEG
737 GENERAL - TOWING OPERATION
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737-600/700/800/900 TRAINING MANUAL
737 GENERAL -- JACKING POINTS
General
There are seven jacking points to lift and stabilize
the airplane. The jacking points consist of three main
and four auxiliary jack points.
The main jack points are the wing jack points A and B,
and the aft body jack point C. These jack points allow
you to connect jacks and lift the complete airplane.
The four auxiliary jack points are the forward body
jack point, the nose gear axle jack point, and the two
main gear axle jack points. The forward body jack point
at position D stabilizes the airplane. Jack points E
and F, underneath the landing gear axles, lets you
remove the wheel and tire or brake assembly without
jacking the complete airplane.
CAUTION: DO NOT PUT THE AIRPLANE ON THE JACKS IN WINDS
MORE THAN 35 KNOTS. IF YOU DO NOT OBEY THESE
INSTRUCTIONS, DAMAGE TO THE AIRPLANE CAN
OCCUR.
CAUTION: DURING WINDY CONDITIONS, YOU MUST USE THE
STABILIZING JACK (JACK POINT D). YOU MUST PUT
A PRE-LOAD ON THE STABILIZING JACK TO A
MAXIMUM OF 5000 POUNDS (2268 KILOGRAMS) AT
WINDS OF 35 MILES PER HOUR. IF YOU DO NOT OBEY
THESE INSTRUCTIONS, YOU CAN CAUSE DAMAGE TO
THE AIRPLANE.
Open the DRAIN MAST-AIR circuit breaker on the P18-3
circuit breaker panel and attach a DO-NOT-CLOSE tag.
This removes heat from the drain mast so it does not
burn persons around the airplane.
Before you jack the airplane, make sure that the
airplane gross weight and the center of gravity are
within the approved limits. For complete information
about jacking and leveling the airplane, refer to
Maintenance Manual Part II, Chapter 7 and 8.
00-00-00-322.fm
Training Information Point
WARNING: MAKE SURE THE DOWNLOCK PINS ARE INSTALLED ON
ALL THE LANDING GEARS. WITHOUT THE DOWNLOCK
PINS, THE LANDING GEAR COULD RETRACT AND CAUSE
INJURIES TO PERSONS AND DAMAGE TO EQUIPMENT.
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737-600/700/800/900 TRAINING MANUAL
JACK POINT C
(AFT BODY)
JACK POINT A
(WING)
JACK POINT E
(NOSE GEAR AXLE)
JACK POINT D
(FORWARD BODY)
JACK POINT B
(WING)
JACK POINT F
(MAIN GEAR AXLE)
00-00-00-322.fm
C
A
F
DB
E
F
737 GENERAL - JACKING POINTS
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737-600/700/800/900 TRAINING MANUAL
737 GENERAL -- FMCS CONTROL DISPLAY UNIT
General
Maintenance BITE Page
The flight crew uses the control display unit (CDU,
also called the MCDU) to put in flight data and to
select displays and modes of operation. They also use
the CDU to start ADIRU alignment. You use the CDU to
test the FMCS and other systems.
You use the MAINT BITE index page to select BITE for
these systems:
There are two CDUs in the airplane. They are
functionally and physically interchangeable.
Physical Description
-
Flight management computer system (FMCS)
Digital flight control system (DFCS)
Autothrottle system (A/T)
Air data inertial reference system (ADIRU)
Common display system (CDS)
Engines
Auxiliary power unit (APU)
Fuel quantity indication system (FQIS).
The CDU has a keyboard and a display.
Line select keys (LSK) are on the left and right of the
display.
This shows how to get to the MAINT BITE index page from
airplane electrical power up.
The keyboard has function and mode keys and alphanumeric keys.
The CDU has these annunciators:
00-00-00-341.fm
-
FAIL
CALL
MSG (message)
OFST (offset)
EXEC (execute).
The EXEC light is on the right of the CDU keyboard.
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737-600/700/800/900 TRAINING MANUAL
IDENT
MODEL
737-XXX
NAV
ENG
DATA
1/2
RATING
XX.XX
DISPLAY
ACTIVE
TBC6880401 MAR18APR17/97
MAINT BITE INDEX
APR18MAY17/97
OP
PROGRAM
549849-001
SUPP
DATA
APR17/97
<INDEX
LINE SELECT
KEYS (12)
<FMCS
ENGINES>
<DFCS
APU>
<A/T
FQIS>
<ADIRU
POS INIT>
<CDS
F MC DOWN LOAD>
<INDEX
FUNCTION AND
MODE KEYS
INIT/REF INDEX
<IDENT
1/1
NAV DATA>
ANNUNCIATORS
(4)
ALPHA-NUMERIC
KEYS
<TAKEOFF
00-00-00-341.fm
<APPROACH
<OFFSET
C
A
L
L
F
A
I
L
<POS
<PERF
1/1
SEL CONFIG>
MAINT>
INIT
REF
RTE
DEP
ARR
ATC
VNAV
FIX
LEGS
HOLD
FMC
COMM
PROG
MENU
N1
LIMIT
A
B
C
D
E
PREV
PAGE
NEXT
PAGE
F
G
H
I
J
EXEC
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
SP
DEL
/
CLR
CONTROL DISPLAY UNIT
737 GENERAL - FMCS CONTROL DISPLAY UNIT
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BRT
See title page for details
M
S
G
O
F
S
T