CAGE Code 81205
737 Classic
Post Delivery
Flight Profile
DOCUMENT NUMBER:
RELEASE/REVISION:
RELEASE/REVISION DATE:
D6-22134-2
NEW
SEPTEMBER 26 2011
CONTENT OWNER:
Flight Crew Operations (9R-TE-TGXX)
All revisions to this document must be approved by the content owner before release.
The information contained herein is the property of The Boeing Company and shall not be reproduced or disclosed in
whole or in part or used for any purpose except when the user possesses direct, written authorization from
The Boeing Company.
Table of Contents
TITLE PAGE
TABLE OF CONTENTS
2
1 PURPOSE AND SCOPE
3
2 GLOSSARY
4
CHAPTER 1
PREFLIGHT
6
CHAPTER 2
ENGINE START
30
CHAPTER 3
AFTER ENGINE START
31
CHAPTER 4
TAXI
32
CHAPTER 5
TAKEOFF
33
CHAPTER 6
CLIMB
34
CHAPTER 7
CRUISE
35
CHAPTER 8
DESCENT
36
CHAPTER 9
LOW ALTITUDE
37
CHAPTER 10
APPROACH
38
CHAPTER 11
LANDING AND SHUTDOWN
39
ACTIVE PAGE RECORD
40
REVISION RECORD
41
NEW
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1. PURPOSE AND SCOPE
This is a Boeing 737 Classic post delivery flight profile that outlines information on what to
check to assess airplane operation following heavy maintenance, modification, or long term
storage. It is intended to provide information to flight crews already trained in proper flight
testing procedures and techniques. This information may help evaluate proper airplane
systems function, airworthiness, and conformity to type design. This document is intended to
be used only as a guide and is not designed to satisfy regulatory requirements. Any use of this
document outside this intended function and/or by crews that are not highly experienced in
performing these types of tests is strongly discouraged. Boeing does not endorse or
recommend using this document to conduct any flight test.
Because this document is only a guideline based on representative Boeing Production Flight
Test Procedures, it is not specific to any model or configuration. Tests identified in this
document may not apply to all model airplanes. Conversely, this profile may not accommodate
all possible airplane configurations or modifications. As such, the information in this document
will not specifically address airplanes that have undergone modification, repair, and/or
maintenance due to service bulletin incorporation or compliance with airworthiness directives, or
any other changes or modifications due to installation of additional equipment, such as by STC.
Therefore, tolerances, limitations, and specific procedures for performing each test or maneuver
are not provided. All flight and maintenance personnel should refer to operations manuals and
maintenance manuals specific to the airplane for this information and it is the responsibility of
the operator to prepare a detailed plan of test prior to flight.
An in-depth understanding of airplane systems operation and the ability to recognize the
appropriate outcome of tests or checks is critical to proper use of this document and are keys to
a safe and efficient flight test. For certain checks, the inability to recognize system malfunctions
may result in structural failure and/or loss of airplane control; conditions which may be beyond
the capability of inexperienced and untrained flight crews and/or test pilots.
The pilot in command is responsible for the safe operation and control of the airplane. If an
abnormal or emergency situation occurs, all testing should be discontinued and the appropriate
non-normal checklist accomplished. The pilot in command may then determine if further testing
is possible or appropriate.
Any time the cabin altitude is raised above 10,000 feet, all personnel should be seated.
Supplemental oxygen shall be made available and readily accessible. It is recommended that
operators limit participation to minimum crew. It will be the responsibility of individual operators
to determine the environmental conditions and requirements necessary for testing. In general,
all checks should be conducted in day, VMC.
CAUTION: The checks outlined in this document are in addition to the normal operating
procedures contained in the approved FAA Flight Manual and the appropriate Boeing
Operations Manual. System failures during certain maneuvers may place the airplane
outside its approved operating envelope. ONLY HIGHLY EXPERIENCED, PROPERLY
TRAINED CREWS SHOULD BE AT THE CONTROLS WHILE PERFORMING THE
MANEUVERS OUTLINED IN THIS DOCUMENT.
This document is not kept up to date and notification of revision is not provided.
NEW
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2. GLOSSARY
FAA
Federal Aviation Administration
(USA)
FLT
Flight
F/O
First Officer
FMS
Flt Management System
FPM
Feet Per Minute
Alternate Navigation Control
GPWS
Ground Proximity Warning System
Display Unit
GS
Glideslope
A/P
Auto Pilot
GW
Gross Weight
APU
Auxiliary Power Unit
HF
High Frequency
A/T
Auto Throttle
HSI
Horizontal Situation Indicator
CAA
Civil Aviation Authority
HYD
Hydraulics
C/B
Circuit Breaker
Hz
Hertz
CCW
Counterclockwise
IAS
Indicated Airspeed
CDU
Control Display Unit
ILS
Instrument Landing System
CMD
Command
IRS
Inertial Reference System
CPCS
Cabin Pressure Control System
COMM
Communication
KIAS
Knots Indicated Airspeed
CW
Clockwise
LAT
Latitude
CWS
Control Wheel Steering
LE
Leading Edge
DC
Direct Current
LNAV
Lateral Navigation
DCPCS
Digital Cabin Pressure Control
System
LONG
Longitude
LVL CH
Level Change
M
Mach Number
MAN
Manual
MAX
Maximum
MCP
Mode Control Panel
AC
Alternating Current
ADF
Automatic Direction Finder
ADI
Attitude Direction Indicator
AGL
Above Ground Level
ALT
Altitude, Altimeter
ALTN
Alternate
ANCDU
DH
Decision Height
DFDR
Digital Flt Data Recorder
DIFF
Differential
DME
Distance Measuring Equipment
EFIS
Electronic Flight Instrument
MDA
Minimum Decision Altitude
System
MIN
Minimum
Electric Horizontal Situation
MSL
Mean Sea Level
NM
Nautical Miles
EHSI
Indicator
EIS
Engine Indication System
EWA
Engineering Work Authorization
NEW
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2. GLOSSARY (Cont’d)
PLA
Power Level Angle
PRESS
Pressure
PSI
Pounds Per Square Inch
PSID
Pounds Per Square Inch Gage
PSU
Passenger Service Unit
PTU
Power Transfer Unit
RECIRC
Recirculation
REF
Reference
RMI
Radio Magnetic Indicator
RPM
Revolutions Per Minute
RTO
Rejected Take-Off
SAT
Static Air Temperature
SLFPM
Sea Level Feet Per Minute
STBY
Standby
SYS
System
TAI
Thermal Anti-Ice
TAT
Total Air Temperature
TE
Trailing Edge
TEMP
Temperature
TOL
Tolerance
VHF
Very High Frequency
VNAV
Vertical Navigation
VOR
VHF Omni-Directional Range
NEW
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CHAPTER 1
PREFLIGHT
________________________________________________________________________
CONTENTS
FLIGHT TEST PROFILE
FLIGHT DECK LIGHTING
STANDBY POWER
ENG / APU OVERHEAT & FIRE WARNING
APU START
NORMAL ELECTRICAL POWER
WHEEL WELL FIRE WARNING
FUEL, CENTER FUEL BOOST PUMP AUTO SHUTOFF (AS INSTALLED)
FUEL
BRAKE ACCUMULATOR / HYDRAULICS
ASPIRATED PROBE (AS INSTALLED)
PNEUMATICS
AIR CONDITIONING -300/-500
RECIRC & GASPER FAN -300/-500 (AS INSTALLED)
AIR CONDITIONING -400
RECIRC FANS -400
PACK HIGH FLOW
PACK HIGH FLOW INHIBIT
EQUIPMENT COOLING
PRESSURIZATION (DCPCS)
PRESSURIZATION (WITHOUT DCPCS)
WINDOW HEAT
WING ANTI-ICE
WING ANTI-ICE (GRD TEST FEATURE) (AS INSTALLED)
FLIGHT CONTROLS
OXYGEN, INTERPHONE, PA
COMMUNICATION
INERTIAL REFERENCE SYSTEM (IRS)
AUTOPILOT DISCONNECTS
EXTERIOR LIGHTS
INSTRUMENT AND FURNISHINGS
COCKPIT VOICE RECORDER (CVR)
FLIGHT MANAGEMENT SYSTEM (FMS)
STALL WARNING TEST
MACH AIRSPEED WARNING TEST
CHARTS
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CHAPTER 1
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FLIGHT PROFILE
7--CRUISE
Fuel
Com/Nav
Cruise Manual
Accel High
Headings Trim Reversion Decels Stage AVM Crossfeed Checks APU
Max Cruise Leak Pack High Recirc
Alt Oxygen Cabin Trim Air
Delta P Data Rate
Flow
Fans Limiting Drop Pressure
FL350
Window Heat
AVM
Alt Alerts
SELCAL
Transponders
Radar
Mmo
Engine
Cooling
8--DESCENT
9--LOW ALTITUDE
Cabin Climb Rates
Windshield &
Foot Air Vents
Eng/Wing TAI
TCAS
6--CLIMB
6--CLIMB
10,000 ft
(For Safety, Limit Testing Below 10,000 ft)
APU Shutdown
Duct Press
Outflow Valve
4--TAXI
5--TAKEOFF
1--PREFLIGHT
2--ENGINE START
3--AFTER START
#1 Engine Shutdown/Relight
#2 Engine Shutdown/Relight
Cabin
Descent Rates
17,000 ft
APU Bleed
8--DESCENT
9--LOW ALTITUDE
Spoiler Pickup (Gear Up) (Gear Up)
Spoiler Float F5 SS
F40
250 Trim F15 Trim
< FL200
F40 SS
F40
Trim
Load
Relief
F0 SS Alt Flaps LE Lockout
F1 Trim
(15,000 ft Preferred)
Hyd Stdby Pump
Flight Controls
Autoslats
Alt Gear
Vmo/SpeedBrakes
11--TAXI AND
SHUTDOWN
Max Reverse, RTO, Suction
Feed,CSD Disconnect,
Fire Handle S/D
Testing & Altitude as Required
F40 Autoland, Gnd Prox
Speedbrakes, F15 G/A
Off Schedule Descent
on Second Approach
Full Stop Landing
NEW
APU Bleed
& Generator
10,000 ft
10--APPROACH
AND LANDING
2 Coupled Approaches
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FLIGHT DECK LIGHTING
Check instrument and panel lighting with
windshield blackout panels installed.
Verify even illumination and the absence of
light leaks.
STANDBY POWER
BAT switch ′ON′
STANDBY POWER switch ′AUTO′
EMER EXIT LIGHTS switch ′ARMED′
GRD PWR switch ′OFF′
DC METERS selector ′BAT′
DC & AC METERS selector ′STBY PWR′
STANDBY POWER switch ′OFF′
EMER EXIT LIGHTS switch ′OFF′
BAT switch ′OFF′
DC METERS selector ′BAT BUS′
DC METERS selector ′BAT′
Engine 1 & 2 Start Levers ′IDLE′
Engine 1 & 2 Fire Warning switches ′PULL′
Engine 1 & 2 Fire Warning switches
′RESET′
Engine 1 & 2 Start Levers ′CUTOFF′
Ground Service switch ′ON′
BAT switch ′ON′
Remove the ground power cord
Left IRS switch ′ALIGN′
AIR/GND RELAY & LTS circuit breaker
(P6-2 panel) ′OPEN′
STANDBY POWER switch ′AUTO′
NEW
Emergency exit lights illuminate.
GRD POWER AVAILABLE light remains
illuminated.
Battery is 20-28 VDC.
Standby power is 0 VDC and 0 VAC
STANDBY PWR OFF, MASTER
CAUTION(s) & ELEC lights illuminate.
STANDBY PWR OFF light remains
illuminated
Emergency Exit lights extinguish.
Battery Bus is 0 VDC
Observe small negative amperage
indications, confirming fuel shutoff valves
operate using the engine start levers and
engine fire switches.
Normal equipment cooling blower runs.
Battery is 25-31 VDC and charging.
Passenger cabin lights are illuminated.
Ground Service switch trips ′OFF′
Battery is 20-28 VDC and discharging
Fuel crossfeed valve operates
Landing gear green lights are illuminated
ON DC, MASTER CAUTION(s) & IRS
lights illuminate
ECS warning horn sounds (20 second
delay)
STANDBY PWR OFF light extinguishes
Left IRS ON DC light extinguishes
ECS warning horn stops
Standby power is 20-28 VDC, 110-120
VAC, 390-410 Hz
Instrument panel floodlights illuminate
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STANDBY POWER, cont′d
L IRS MODE selector ′ATT′
Enter a heading on the IRS Control Panel
AIR/GND RELAY & LTS circuit breaker
(P6-2 panel) ′CLOSE′
STANDBY POWER switch ′BAT′
Left IRS switch ′OFF′
STANDBY POWER switch ′AUTO′
Verify the following items operate on
Standby Power: (As installed)
ADI #1
VHF #1
HSI #1
NAV #1
RMI #1
Standby ADI
ADF #1
Standby Altimeter Vibrator
Standby Altimeter Lighting
Capt′s Standby Airspeed
Fuel Quantity
Interphone and PA
EIS Primary Display
Standby powered equipment is
inoperative.
Standby powered equipment is operative
ON DC light extinguishes
ECS warning horn stops (20 second delay)
STANDBY PWR OFF light illuminates
ENG/APU OVERHEAT & FIRE WARNING
ENG 1 & 2 OVHT DET switches LOOP ′A′
FAULT/INOP and OVHT/FIRE TEST
switch hold at ′FAULT/INOP′ until
responses are verified
FAULT/INOP and OVHT/FIRE TEST
switch hold at ′OVHT/FIRE′ until responses
are verified
Capt′s Master FIRE WARN switch ′PUSH′
FAULT, APU DET INOP, MASTER
CAUTION(s) & OVHT/DET lights
illuminate.
Master FIRE WARN, MASTER
CAUTION(s) & OVHT/DET lights
illuminate.
ENGINE 1, ENGINE 2 & APU FIRE
WARNING switches illuminate.
ENG 1 OVERHEAT & ENG 2 OVERHEAT
lights illuminate.
The fire warning bell sounds in the flight
deck.
The APU fire warning horn sounds in the
wheel well.
The APU FIRE warning light flashes in the
wheel well.
Verify that the FIRE WARN lights and bell
cancel. The APU fire warning horn
cancels and the APU FIRE warning light
illuminates steady in the wheel well.
FAULT/INOP and OVHT/FIRE TEST
switch ′release′
ENG 1 & 2 OVHT DET switches LOOP ′B′
NEW
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ENG/APU OVERHEAT & FIRE WARNING, cont′d
FAULT/INOP and OVHT/FIRE TEST
switch hold at ′FAULT/INOP′
FAULT/INOP and OVHT/FIRE TEST
switch hold at ′OVHT/FIRE′
F/O′s Master FIRE WARN switch PUSH
FAULT/INOP and OVHT/FIRE TEST
switch release
ENG 1 & 2 OVHT DET switches LOOP
′NORMAL′
FAULT/INOP and OVHT/FIRE TEST
switch hold at ′FAULT/INOP′
FAULT/INOP and OVHT/FIRE TEST
switch hold at ′OVHT/FIRE′
BELL CUTOUT switch PUSH
Engine 1 & 2 and APU Fire Warning
switches PULL
FAULT/INOP and OVHT/FIRE TEST
switch release
Engine 1 & 2 and APU Fire Warning
switches RESET
ENGINES EXT TEST switch hold at ′1′
ENGINES EXT TEST switch hold at ′2′
Same indications as above
Same indications as above
Same indications as above
Same indications as above
Same indications as above
Same indications as above
Verify locks are released
L, R, & APU extinguisher test lights
illuminate.
L, R, & APU extinguisher test lights
illuminate.
APU START
All FUEL PUMP switches ′ON′
DC METERS selector ′BAT′
AC METERS selector ′APU GEN′
BUS TRANSFER switch ′OFF′
GEN 1, GEN 2, APU GEN switches ′ON′
All WINDOW HEAT & PITOT STATIC
HEAT switches ′ON′
All HYD PUMP switches ′ON′
APU switch ′START′ and release to ′ON′
NEW
APU initiates a start sequence.
Monitor starter engage and cutout on DC
ammeter.
APU generator output is 110-120 VAC,
405-410 Hz ( Old Garrett),
400 + 5 Hz ( New Garrett and Sundstrand).
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NORMAL ELECTRICAL POWER
Left APU GEN switch ′ON′
BUS TRANS switch ′AUTO′
Right APU GEN switch ′ON′
BUS TRANS switch ′OFF′
Left APU GEN switch ′OFF′
TR 2 circuit breaker ′PULL′
TR 2 circuit breaker ′CLOSED′
NEW
APU GEN OFF BUS light is extinguished.
No. 1 & 2 GEN OFF BUS lights are
illuminated.
No. 1 BUS OFF lights are extinguished.
No. 1 TRANSFER BUS OFF light is
extinguished.
No. 2 TRANSFER BUS OFF light is
illuminated.
No. 2 BUS OFF light is illuminated.
Battery is 25-31 VDC and charging.
TR 1 is 20-28 VDC, positive amps.
TR 2 & 3 are 0 VDC, 0 amps.
B ELEC 1 HYD PUMP LOW PRESSURE
light is extinguished.
No. 2 TRANSFER BUS OFF light
extinguishes.
TR 1 is 20-28 VDC, decreased amps.
TR 2 is 20-28 VDC, positive amps.
TR 3 is approximately 3 VDC, 0 amps.
CAUTION
If TR 3 reads more than 1 VDC, push
indicator on M238 power panel, verify 1
VDC max.
No. 2 BUS OFF light extinguishes.
Battery ammeter indicates high charging or
pulsing.
TR 3 is 20-28 VDC, positive amps.
All busses and equipment are powered.
No change should occur.
No. 1 TRANSFER BUS OFF light is
illuminated.
No. 1 BUS OFF light is illuminated.
STANDBY PWR OFF light illuminates.
TR 1 is 0 VDC, 0 amps.
TR 2 is 20-28 VDC, positive amps.
TR 3 is 20-28 VDC, positive amps (note
amps).
A ELEC 2 HYD PUMP LOW PRESSURE
light is extinguished.
TR 3 is 20-28 VDC, increased amps
TR 2 is 0 VDC, 0 amps.
TR 3 is 20-28 VDC, decreased amps.
TR 2 is 20-28 VDC, positive amps.
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NORMAL ELECTRICAL POWER, cont′d
STANDBY POWER switch ′BAT′
BUS TRANS switch ′AUTO′
STANDBY POWER switch ′AUTO′
Left APU GEN switch ′ON′
GALLEY Power switch ′OFF′
A&B PITOT STATIC HEAT switches ′OFF′
L and R IRS MODE selectors ′ALIGN′
STANDBY PWR OFF light is extinguished.
Standby equipment is powered.
Battery is not charging
No. 1 TRANSFER BUS OFF light is
extinguished.
Battery ammeter indicates charging.
TR 1 is 24-31 VDC, positive amps.
STANDBY PWR OFF light is extinguished.
No. 1 BUS OFF light is extinguished.
Verify galley power busses shed.
WHEEL WELL FIRE WARNING
FAULT/INOP & OVHT/FIRE TEST switch
′OVHT/FIRE′
Capt′s master FIRE WARN switch ′PUSH′
Verify WHEEL WELL fire warning lights
illuminate.
Master FIRE WARN lights illuminate.
Fire warning bell sounds.
Verify that the FIRE WARN lights and bell
cancel.
FUEL, CENTER FUEL BOOST PUMP AUTO SHUTOFF
POST SB 737-28A1210 or POST SB 28A1216
Ensure all Fuel Boost Pump Switches ′ON′
Press the MASTER CAUTION(s)
′RECALL′
Press the MASTER CAUTION(s) ′RESET′
Push and Hold the LEFT FUEL TEST
AUTO SHUTOFF switch to the ′AUTO
OFF′ position
Release the LEFT FUEL TEST AUTO
SHUTOFF switch
Position the Left Center Fuel Tank Boost
Pump to ′OFF′ and back ′ON′ (resets the
AUTO SHUTOFF function)
Press the MASTER CAUTION(s)
′RECALL′
NEW
All LOW PRESSURE lights extinguished.
Master Caution FUEL annunciation
extinguished.
Master Caution annunciations extinguish.
Left pump shuts off and LOW PRESSURE
light illuminates after 15 + 2 seconds.
MASTER CAUTION(s) and FUEL
annunciation illuminate 10 + 2 seconds
after the LOW PRESSURE light
illuminates.
LOW PRESSURE light illuminates briefly
and remains extinguished when pump is
cycled on.
Master Caution FUEL annunciation
extinguished.
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FUEL, CENTER FUEL BOOST PUMP AUTO SHUTOFF, cont′d
Press the MASTER CAUTION(s) ′RESET′
Push and Hold the RIGHT FUEL TEST
AUTO SHUTOFF switch to the ′AUTO
OFF′ position
Release the RIGHT FUEL TEST AUTO
SHUTOFF switch
Position the Right Center Fuel Tank Boost
Pump to ′OFF′ and back ′ON′ (resets the
AUTO SHUTOFF function)
Press the MASTER CAUTION(s) ′RESET′
Main Tank 1 AFT FUEL PUMP switch
′OFF′
Press the MASTER CAUTION(s)
′RECALL′
Press the MASTER CAUTION(s) ′RESET′
Main Tank 1 FWD FUEL PUMP switch
′OFF′
Main Tank 1 FWD and 1 AFT FUEL PUMP
switches ′ON′
Main Tank 2 AFT FUEL PUMP switch
′OFF′
Press the MASTER CAUTION(s)
′RECALL′
Press the MASTER CAUTION(s) ′RESET′
Main Tank 2 FWD FUEL PUMP switch
′OFF′
Main Tank 2 FWD and 2 AFT FUEL PUMP
switches ′ON′
NEW
Master Caution annunciations extinguish.
Right pump shuts off and LOW
PRESSURE light illuminates after 15 + 2
seconds.
MASTER CAUTION(s) and FUEL
annunciation illuminate 10 + 2 seconds
after the LOW PRESSURE light
illuminates.
LOW PRESSURE light illuminates briefly
and remains extinguished when pump is
cycled on.
Master Caution annunciations extinguish.
1 AFT LOW PRESSURE light illuminates.
MASTER CAUTION(s) and FUEL
annunciation illuminates.
Master Caution annunciations extinguish.
1 FWD LOW PRESSURE, MASTER
CAUTION(s) and FUEL lights illuminate.
1 FWD and 1 AFT LOW PRESSURE,
MASTER CAUTION(s) and FUEL lights
extinguish.
2 AFT LOW PRESSURE light illuminates.
MASTER CAUTION(s) and FUEL
annunciation illuminates.
Master Caution annunciations extinguish.
2 FWD LOW PRESSURE, MASTER
CAUTION(s) and FUEL lights illuminate.
2 FWD and 2 AFT LOW PRESSURE,
MASTER CAUTION(s) and FUEL lights
extinguish.
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FUEL
Ensure all Fuel Boost Pump Switches ′ON′
Press the MASTER CAUTION(s)
′RECALL′
Press the MASTER CAUTION(s) ′RESET′
Main Tank 1 AFT FUEL PUMP switch
′OFF′
Press the MASTER CAUTION(s)
′RECALL′
Press the MASTER CAUTION(s) ′RESET′
Main Tank 1 FWD FUEL PUMP switch
′OFF′
Main Tank 1 FWD and 1 AFT FUEL PUMP
switches ′ON′
Main Tank 2 AFT FUEL PUMP switch
′OFF′
Press the MASTER CAUTION(s)
′RECALL′
Press the MASTER CAUTION(s) ′RESET′
Main Tank 2 FWD FUEL PUMP switch
′OFF′
Main Tank 2 FWD and 2 AFT FUEL PUMP
switches ′ON′
L & R CTR FUEL PUMP switches ′OFF′ for
5 seconds, then ′ON′
All LOW PRESSURE lights extinguished.
Master Caution FUEL annunciation
extinguished.
Master Caution annunciations extinguish.
1 AFT LOW PRESSURE light illuminates.
MASTER CAUTION(s) and FUEL
annunciation illuminates.
Master Caution annunciations extinguish.
1 FWD LOW PRESSURE, MASTER
CAUTION(s) and FUEL lights illuminate.
1 FWD and 1 AFT LOW PRESSURE,
MASTER CAUTION(s) and FUEL lights
extinguish.
2 AFT LOW PRESSURE light illuminates.
MASTER CAUTION(s) and FUEL
annunciation illuminates.
Master Caution annunciations extinguish.
2 FWD LOW PRESSURE, MASTER
CAUTION(s) and FUEL lights illuminate.
2 FWD and 2 AFT LOW PRESSURE,
MASTER CAUTION(s) and FUEL lights
extinguish.
L & R Center LOW PRESSURE lights
illuminate briefly, then extinguish.
BRAKE ACCUMULATOR / HYDRAULICS
Ensure airplane is properly chocked
ELEC 2 & ELEC 1 HYD PUMP switches
′OFF′
Hydraulic BRAKE PRESSURE checked
PARKING BRAKE release
Pump the brake pedals until the brake
accumulator pressure no longer decreases
ELEC 2 HYD PUMP switch ′ON′
NEW
Electric 2 & 1 hydraulic pump LOW
PRESSURE, MASTER CAUTION(s), HYD
and FLT CONT lights illuminate.
Pressure is 2800 PSI or greater.
PARK BRAKE light extinguishes.
Verify brake pressure does not drop below
accumulator precharge limit.
TOLERANCE: 1000 PSI at 25ºC
Verify “A” system hydraulic pressure
increases to nominal, but brake
accumulator pressure remains as above.
TOLERANCE: 2925 to 3125 PSI
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BRAKE ACCUMULATOR / HYDRAULICS, cont′d
ELEC 1 HYD PUMP switch ′ON′
PARKING BRAKE ′SET′
PARKING BRAKE ′RELEASE′ and ′SET′
from opposite side
Verify “B” system hydraulic pressure
increases to nominal and brake
accumulator pressure rises with “B”
system.
TOLERANCE: 2925 to 3125 PSI
PARK BRAKE light illuminates
PARK BRAKE light extinguishes and
illuminates.
ASPIRATED TAT (As Installed)
PITOT STATIC A & B switches ′OFF′
APU BLEED switch ′OFF′
TAT TEST switch PUSH
Verify Total Air Temperature (TAT)
indication increases and TEMP PROBE
light extinguishes.
TEMP PROBE light illuminates
Verify TAT indication decreases.
TAT TEST switch released
APU BLEED switch ′ON′
APU BLEED switch as required.
PNEUMATICS
L & R PACK switches ′OFF′
Engine 1, 2 & APU BLEED switches ′OFF′
ISOLATION VALVE switch ′AUTO′
APU BLEED switch ′ON′
APU BLEED switch ′OFF′
Engine 1 & APU BLEED switches ′ON′
Engine 1 BLEED switch ′OFF′
Engine 2 BLEED switch ′ON′
Engine 1 BLEED switch ′ON′
R PACK switch ′AUTO′
ISOLATION VALVE switch ′CLOSE′
ISOLATION VALVE switch ′AUTO′
NEW
L & R duct pressure is zero.
L & R duct pressure are as follows:
Old Garrett: approximately 42 PSI
New Garrett: approximately 30 PSI
New Sunstrand: approximately 50 PSI
L & R duct pressures bleed off slowly
DUAL BLEED, MASTER CAUTION(s)
and AIR COND lights illuminate.
DUAL BLEED, MASTER CAUTION(s) and
AIR COND lights extinguish.
DUAL BLEED, MASTER CAUTION(s)
and AIR COND lights illuminate.
Right pack operates and L & R duct
pressures are within 3 PSI of each other.
Right pack shuts down and R duct
pressure decreases to approximately 0
PSI.
Right pack operates and L & R duct
pressures are within 3 PSI of each other.
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PROPERTY OF THE BOEING COMPANY
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CHAPTER 1
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________________________________________________________________________
PNEUMATICS, cont′d
L PACK switch ′AUTO′
Left pack operates, right pack shuts down
and R duct pressure decreases to
approximately 0 PSI.
ISOLATION VALVE switch ′OPEN′
Both packs operate, L & R duct pressures
are normal and approximately equal
APU generator frequency within 10Hz of
no load frequency.
L & R WING-BODY OVERHEAT,
MASTER CAUTION(s) and AIR COND
lights illuminate.
OVHT TEST switch ′PUSH and HOLD′
AIR CONDITIONING -300/500
CAUTION: During right pack operation only, under cold conditions, the LEFT PACK
TRIP OFF light may illuminate. Position the RECIRC FAN OFF until the cabin
temperature stabilizes.
CAUTION: For SWA aircraft only, 737-300/500, ensure the recirculation and gaspers
fans are OFF and a minimum of 50% of the left and right side passenger gaspers are
CLOSED before testing the 190 or 250 duct overheat switches.
NOTE: If compartment temperature is heat-soaked at or near 85ºF, you may not be able
to get the mix valves to move toward HOT with the temp selectors at MAX
AUTO WARM. Cool down the airplane or accomplish this check after the cabin
temperature stabilizes near the normal temperature of 75ºF.
AIR TEMP source selector ′SUPPLY
DUCT′
RECIRC FAN switch ′OFF′
GASPER FAN switch ′OFF′ (As installed)
L & R PACK switches ′AUTO′
CONT CABIN temperature selector to full
AUTO ′WARM′
CONT CABIN temperature selector to full
AUTO ′COOL′
PASS CABIN temperature selector to full
AUTO ′WARM′
NEW
Left and Right RAM DOOR FULL OPEN
lights are illuminated.
CONT CABIN AIR MIX VALVE moves
toward HOT.
SUPPLY DUCT temperature increases.
DUCT OVERHEAT light does not
illuminate.
CONT CABIN AIR MIX VALVE moves
toward COLD.
SUPPLY DUCT temperature decreases.
PASS CABIN AIR MIX VALVE moves
toward HOT.
SUPPLY DUCT temperature increases to
approximately 70ºC (158ºF).
DUCT OVERHEAT light does not
illuminate.
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CHAPTER 1
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________________________________________________________________________
AIR CONDITIONING -300/500, cont′d
PASS CABIN temperature selector to full
AUTO ′COOL′
L PACK switch ′OFF′
PASS CABIN temperature selector toggle
MANUAL ′WARM′ until the PASS CABIN
AIR MIX VALVE is at the
12 o′clock position.
PASS CABIN temperature selector ′AUTO′
TRIP RESET switch PUSH
R PACK switch ′OFF′
L PACK switch ′AUTO′
CONT CABIN temperature selector toggle
MANUAL ′WARM until an overheat
condition occurs
CONT CABIN temperature selector ′AUTO′
TRIP RESET switch PUSH
RECIRC FAN switch ′AUTO′
GASPER FAN switch ′ON′ (As installed)
PASS CABIN AIR MIX VALVE moves
toward COLD.
SUPPLY DUCT temperature decreases.
SUPPLY DUCT temperature increases
slowly until the right DUCT OVERHEAT
light illuminates between 78ºC and 95ºC
(172ºF and 205ºF).
MASTER CAUTION(s) and AIR COND
lights illuminate.
PASS CABIN AIR MIX VALVE moves
COLD.
Right DUCT OVERHEAT light
extinguishes.
Left DUCT OVERHEAT, MASTER
CAUTION(s) and AIR COND lights
illuminate.
CONT CABIN AIR MIX VALVE moves
COLD.
Left DUCT OVERHEAT light extinguishes.
RECIRC & GASPER FANS -300/500 (As installed)
AC meters selector switch ′APU GEN′
RECIRC FAN switch ′OFF′
RECIRC FAN switch ′AUTO′
GASPER FAN switch ′OFF′ (As installed)
GASPER FAN switch ′ON′ (As installed)
NEW
AC AMMETER indicates a decrease in
amps.
AC AMMETER indicates an increase in
amps.
AC AMMETER indicates a decrease in
amps.
AC AMMETER indicates an increase in
amps.
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PROPERTY OF THE BOEING COMPANY
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CHAPTER 1
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________________________________________________________________________
AIR CONDITIONING -400
NOTE: If compartment temperature is heat-soaked at or near 85ºF, the Trim Air system
will not provide additional hot air to the compartments. In this case, it may be
necessary to cool down the airplane before accomplishing the Trim Air checks
below.
NOTE: Press Master Caution Recall and verify there are no ZONE TEMPERATURE or
PACK lights illuminated on the Overhead Panel.
AIR TEMP source selector SUPPLY DUCT
′CONT CAB′
TRIM AIR switch ′ON′
L & R RECIRC FAN switches ′OFF′
L PACK switch ′HIGH′
R PACK switch ′OFF′
CONT CAB temperature selector to full
AUTO ′W′
FWD CAB & AFT CAB temperature
selectors to full AUTO ′C′
CONT CAB temperature selector to full
AUTO ′C′
FWD CAB temperature selector to full
AUTO ′W′
FWD CAB temperature selector to full
AUTO ′C′
AFT CAB temperature selector to full
AUTO ′W′
AFT CAB temperature selector to full
AUTO ′C′
L PACK switch ′OFF′
R PACK switch ′HIGH′
CONT CAB temperature selector to full
AUTO ′W′
CONT CAB temperature selector to full
AUTO ′C′
L & R PACK switches ′AUTO′
ISOLATION VALVE switch ′OPEN′
L & R RECIRC FAN switches ′AUTO′
AIR TEMP source selector ′L & R PACK′
TRIM AIR switch ′OFF′
CONT CAB temperature selector full
AUTO ′W′
NEW
Left & Right RAM DOOR FULL OPEN
lights are illuminated.
SUPPLY DUCT CONT CAB temperature
increases, not to exceed 85ºC (185ºF).
ZONE TEMP light does not illuminate.
SUPPLY DUCT CONT CAB temperature
decreases.
SUPPLY DUCT FWD CAB temperature
increases, not to exceed 85ºC (185ºF).
ZONE TEMP light does not illuminate.
SUPPLY DUCT FWD CAB temperature
decreases.
SUPPLY DUCT AFT CAB temperature
increases, not to exceed 85ºC (185ºF).
ZONE TEMP light does not illuminate.
SUPPLY DUCT AFT CAB temperature
decreases.
SUPPLY DUCT CONT CAB temperature
increases, not to exceed 85ºC (185ºF).
ZONE TEMP light does not illuminate.
SUPPLY DUCT CONT CAB temperature
decreases.
Verify both pack temperatures stabilize no
lower than 0ºC (32ºF) and are
approximately equal.
SUPPLY DUCT CONT CAB and L PACK
temperatures increase.
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CHAPTER 1
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________________________________________________________________________
AIR CONDITIONING -400, cont′d
CONT CAB temperature selector full
AUTO ′C′
FWD & AFT CAB temperature selectors
full AUTO ′W′
FWD & AFT CAB temperature selectors
full AUTO ′C′
ISOLATION VALVE switch ′AUTO′
TRIM AIR switch ′ON′
Temperature Selectors ′As Desired′
MASTER CAUTION ′RECALL′
SUPPLY DUCT CONT CAB and L PACK
temperatures decrease.
SUPPLY DUCT FWD & AFT CAB and R
PACK temperatures increase.
SUPPLY DUCT FWD & AFT CAB and R
PACK temperatures decrease.
ZONE TEMP and PACK lights should not
illuminate. Illumination of any of these
lights indicates equipment failure.
RECIRC FANS -400
L RECIRC FAN switch ′OFF′
L RECIRC FAN switch ′AUTO′
R RECIRC FAN switch ′OFF′
R RECIRC FAN switch ′AUTO′
ISLOATION VALVE switch ′OPEN′
L & R PACK switch ′HIGH′
AC AMMETER indicates a decrease in
amps.
AC AMMETER indicates a increase in
amps.
AC AMMETER indicates a decrease in
amps.
AC AMMETER indicates a increase in
amps.
AC AMMETER indicates a decrease in
amps. (L RECIRC FAN stops)
L & R PACK switch ′AUTO′
PACK HIGH FLOW
ISOLATION VALVE switch ′OPEN′
R PACK switch ′AUTO′
L PACK switch ′HIGH′
FLAPS ′UP′
L PACK switch ′AUTO′
R PACK switch ′HIGH′
NEW
Verify the L PACK has regulated to high
flow by:
An increase in APU EGT.
Left and right duct pressure decreases
approximately 2 PSI.
Verify the L PACK has regulated to low
flow by:
A decrease in APU EGT.
Left and right duct pressure increases
approximately 2 PSI.
Verify the R PACK has regulated to high
flow by:
An increase in APU EGT.
Left and right duct pressure decreases
approximately 2 PSI.
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PROPERTY OF THE BOEING COMPANY
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CHAPTER 1
PREFLIGHT
________________________________________________________________________
PACK HIGH FLOW, cont′d
R PACK switch ′AUTO′
Verify the R PACK has regulated to low
flow by:
A decrease in APU EGT.
Left and right duct pressure increases
approximately 2 PSI.
1 & 2 BLEED switches ′OFF′
APU BLEED switch ′ON′
ISOLATION VALVE switch ′AUTO′
L PACK switch ′AUTO′
R PACK switch ′OFF′
1 BLEED switch ′ON′
1 BLEED switch ′OFF′
L PACK switch ′OFF′
R PACK switch ′AUTO′
2 BLEED switch ′ON′
Verify the L PACK has regulated to low
flow by:
A decrease in APU EGT.
Left and right duct pressure increases
approximately 2 PSI.
Verify the L PACK has regulated to high
flow by:
An increase in APU EGT.
Left and right duct pressure decreases
approximately 2 PSI.
Verify the R PACK has regulated to low
flow by:
A decrease in APU EGT.
Left and right duct pressure increases
approximately 2 PSI.
Verify the R PACK has regulated to high
flow by:
An increase in APU EGT.
Left and right duct pressure decreases
approximately 2 PSI.
2 BLEED switch ′OFF′
1 & 2 BLEED switches ′ON′
APU BLEED switch ′ON′
ISOLATION VALVE switch ′OPEN′
L & R PACK switches ′AUTO′
NEW
D6-22134-2
PROPERTY OF THE BOEING COMPANY
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CHAPTER 1
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________________________________________________________________________
PACK HIGH FLOW INHIBIT
1 & 2 BLEED switches ′ON′
APU BLEED switch ′ON′
ISOLATION VALVE switch ′AUTO′
L PACK switch ′AUTO′
R PACK switch ′OFF′
AIR/GND RELAY & LTS circuit breaker
(P6-2 panel) ′OPEN′
FLAPS ′2′
Verify the L PACK has regulated to high
flow by:
An increase in APU EGT.
Left and right duct pressure decreases
approximately 2 PSI.
Verify the L PACK has regulated to low
flow by:
A decrease in APU EGT.
Left and right duct pressure increases
approximately 2 PSI.
AIR/GND RELAY & LTS circuit breaker
(P6-2 panel) ′CLOSE′
Reconfigure pack controls and flaps as
desired.
EQUIPMENT COOLING
EQUIP COOLING SUPPLY & EXHAUST
switches ′NORM′
EQUIP COOLING SUPPLY & EXHAUST
switches ′ALTN′
Verify proper equipment cooling with the
normal supply and exhaust fans.
Verify proper equipment cooling with the
alternate supply and exhaust fans for
several minutes.
EQUIP COOLING SUPPLY & EXHAUST
switches ′NORM′
PRESSURIZATION (DCPCS)
NOTE: A cabin exterior door must be open for test, if AC PACK is operating
Pressurization Mode selector ′MAN′
Outflow VAVLE switch hold ′CLOSE′
AUTO 2 c/b OPEN/CLOSE (P6-4)
Pressurization Mode selector ′AUTO′
NEW
MANUAL light illuminates.
Verify valve closes.
Resets Auto 1 as the controlling system.
MANUAL light extinguishes.
The outflow valve moves toward open.
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PROPERTY OF THE BOEING COMPANY
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________________________________________________________________________
PRESSURIZATION (DCPCS), cont′d
AUTO 1 c/b ′OPEN′ (P6-4)
The outflow stops.
AUTO FAIL, ALTN, MASTER
CAUTION(s) and AIR COND lights
illuminate.
After a few seconds the outflow valve
continues toward open.
AUTO FAIL, MASTER CAUTION (s) and
AIR COND lights extinguish.
MANUAL light illuminates.
ALTN light extinguishes.
Pressurization Mode selector ′ALTN′
Pressurization Mode selector ′MAN′
AUTO 2 c/b ′OPEN′
AUTO 1 c/b ′CLOSE′
AUTO 2 c/b ′CLOSE′
Outflow VALVE switch hold ′CLOSE′
Pressurization Mode selector ′ALTN′
AUTO 2 c/b ′OPEN′
Pressurization Mode selector ′MAN′
Outflow VALVE switch ′CLOSE/OPEN′
AUTO 2 c/b ′CLOSE′
Pressurization Mode selector ′AUTO′
Set FLT ALT window to cruise altitude
Verify valve closes.
The outflow valve moves toward open.
MANUAL light extinguishes.
ALTN light illuminates.
The outflow valve stops momentarily, then
continues toward open.
MANUAL light illuminates.
ALTN light extinguishes.
Verify that the outflow valve moves through
the full range of full closed to full open.
All pressurization lights are extinguished.
PRESSURIZATION (Without DCPCS)
NOTE: A cabin exterior door must be open for test, if AC PACK is operating
Pressurization Mode selector ′AUTO′
FLT/GRD switch ′GRD′
CAB ALT selector ′200 Feet above field
elevation′
Capt and F/O′s altimeters set to current
airport ′BARO′
FLT/GRD switch ′FLT′
Pressurization Mode selector ′CHECK′
CAB ALT selector ′200 Feet below field
elevation′.
NEW
After a 10 second delay, the outflow valve
indicator moves to CLOSE.
AUTO FAIL and STANDBY lights
illuminate. ( Simulates excessive
pressurization rates)
Outflow valve indicator moves to OPEN.
Outflow valve indicator moves to CLOSE.
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PROPERTY OF THE BOEING COMPANY
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CHAPTER 1
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________________________________________________________________________
PRESSURIZATION (Without DCPCS), cont′d
FLT/GRD switch ′GRD′`
FLT/GRD switch ′FLT′
FLT/GRD switch ′GRD′`
Pressurization Mode selector ′MAN AC′
Pressurization Mode selector ′MAN DC′
AUTO FAIL and STANDBY lights
extinguish.
Outflow valve indicator moves to OPEN.
(System is now in the Auto Mode)
Outflow valve indicator moves to CLOSE.
NOTE: System will stay in Auto Mode if
FLT was selected more than 20 seconds
after mode selector was moved to CHECK.
Outflow valve indicator moves to OPEN.
Cycle outflow valve full CLOSED to full
OPEN.
Cycle outflow valve full CLOSED to full
OPEN.
Pressurization Mode selector ′AUTO′
FLT ALT selector ′27000′
WINDOW HEAT
NOTE: 1. Do not select PWR TEST when all green ON lights are illuminated.
2. ON lights for windows in direct sunlight may not be illuminated.
3. ON lights illuminating may be replaced by OFF lights extinguishing, as
installed.
All WINDOW HEAT switches ′ON′
If any window heat ON lights are
extinguished:
WINDOW HEAT TEST switch ′PWR TEST′
WINDOW HEAT TEST switch ′OVHT′
All WINDOW HEAT switches ′OFF′
Verify all window heat ON lights illuminate.
All window heat ON lights are illuminated.
All window heat OVERHEAT lights
illuminate.
All window heat ON lights extinguish within
70 seconds.
All window heat OVERHEAT lights
extinguish.
All WINDOW HEAT switches ′ON′
NEW
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PROPERTY OF THE BOEING COMPANY
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CHAPTER 1
PREFLIGHT
________________________________________________________________________
WING ANTI-ICE
One PACK switch ′AUTO′
WING ANTI-ICE switch ′ON′
Wing anti-ice L & R VALVE OPEN lights
illuminate bright then dim. Duct pressure
decreases.
NOTE: A DUCT OVERTEMPERATURE condition may occur if there is a delay
between the next two steps.
No. 1 FORWARD THRUST lever advance At approximately 30 degrees above idle:
towards ′INCREASE THRUST′
Wing anti-ice L & R VALVE OPEN lights
illuminate bright.
No. 1 FORWARD THRUST lever retard
No. 2 FORWARD THRUST lever advance
towards ′INCREASE THRUST′
Duct pressure increases.
Wing anti-ice L & R VALVE OPEN lights
illuminate dim.
Duct pressure decreases.
At approximately 30 degrees above idle:
Wing anti-ice L & R VALVE OPEN lights
illuminate bright.
No. 2 FORWARD THRUST lever retard
Duct pressure increases.
Wing anti-ice L & R VALVE OPEN lights
illuminate dim.
Duct pressure decreases.
WING ANTI-ICE switch returns to OFF
AIR/GND RELAY & LTS C/B ′OPEN′
Wing anti-ice L & R VALVE OPEN lights
extinguish.
AIR/GND RELAY & LTS C/B ′RESET′
WING ANTI-ICE (Grd Test Feature)
One PACK switch ′AUTO′
WING ANTI-ICE switch ′GRD TEST′ and
hold
Wing anti-ice L & R VALVE OPEN lights
illuminate bright, then dim.
Duct pressure decreases.
WING ANTI-ICE switch ′OFF′
NEW
After several seconds, the L & R VALVE
OPEN lights illuminate bright and duct
pressure increases as the valves close for
overheat trip.
Wing anti-ice L & R VALVE OPEN lights
extinguish.
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PROPERTY OF THE BOEING COMPANY
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CHAPTER 1
PREFLIGHT
________________________________________________________________________
FLIGHT CONTROLS
A & B HYD PUMP switches ′ON′
AILERON TRIM ′ZERO′
CONTROL WHEEL to 6 units then 2 units
and ′release′
Repeat check in the opposite direction.
Check the following systems:
Control wheel centers within limits
Control wheel centers within limits
Compare to CHART 1
Manual reversion
System is evaluated for proper operation.
Standby Rudder
Correct responses reported by ground
person.
Hydraulic System A
Hydraulic System B
Hydraulic System A & B
Speedbrakes Check
Trim Systems
Takeoff Warnings
Alternate Flaps
Thrust Reversers
OXYGEN, INTERPHONE, PA
Check all O2 masks (as installed)
Functions properly in Normal and
Alternate.
Mask Mic functions properly in I/C and PA.
The mask can be extracted and donned
with one hand and in one smooth motion.
Transmission and reception are clear.
Check all boom mics (as installed)
COMMUNICATION
Use 1, 2 & 3(L, R & C) VHF and HF radios
(as installed) for ground communication
Tuning functions operate normally.
Transmission and reception are clear.
NEW
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CHAPTER 1
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________________________________________________________________________
INERTIAL REFERENCE SYSTEM (IRS)
Perform normal preflight
Confirm all IRS functions are operative
using normal preflight items.
NAVIGATION
Capt′s & F/O′s EFIS Control Panels
DH & LRRA display
Verify for proper operation.
Verify the selected DH is annunciated and
the radio altimeter reads -8 to 0 feet.
Perform appropriate self-test (as installed)
Verify proper operation
Verify test pattern
VOR/ILS/DME/ATC TRANSPONDER
ADF
WX RADAR
AUTOPILOT DISCONNECTS
NOTE: For all disconnect conditions, check the autopilot disconnects, A/P DISC red
lights illuminate and siren sounds.
A & B HYD PUMP switches ′ON′
DISENGAGE bar PUSH
A/P ENGAGE switches CMD A, CMD B,
CWS A & CWS A ′PUSH′ in turn
DISENGAGE bar reset
A/P ENGAGE switches CMD A, CMD B,
CWS A & CWS A ′PUSH′ in turn,
disengaging each with the Capt′s & F/O′s
control column disengage switches
Repeat using Capt′s & F/O′s control
column electric trim switches to
′DISCONNECT′
Repeat using STAB TRIM AUTOPILOT
CUTOUT switch to ′CUTOUT′
FCCs will no engage
Check that all FCCs disconnect with single
push from both pilot′s columns.
Double push silences aural WARNING &
DISENGAGE lights extinguish.
Check that FCCs disconnect and visual
and aural warnings occur as above.
Check that FCCs disconnect and visual
and aural warnings occur as above.
EXTERIOR LIGHTS
Select all exterior lights ′ON′
EMER EXIT, LANDING, L & R RUNWAY
TURNOFF, TAXI, LOGO, STROBE,
POSTION,ANTI-COLLISION, WING,
WHEEL WELL
Following ground report of a light ON, turn
respective switch ′OFF′
NEW
Ground observer responds by reporting
that a light is illuminated.
(NOTE: Attempt to limit LANDING light
illumination time to less than 5 minutes)
Ground observer reports that light
extinguished.
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CHAPTER 1
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________________________________________________________________________
INSTRUMENTS & FURNISHINGS
Instruments
Verify all instruments, indicators,
annunciators, switches and placards for
compliance and readability.
Instruments and indicators which have
mechanical failure flags are evaluated for
appropriate response.
Verify all cockpit seats, harnesses,
windows, roller sun shades, clocks, gasper
outlets, Grimes lights, rudder pedals
adjustment, etc, operate freely and perform
their intended function.
Furnishings
COCKPIT VOICE RECORDER (CVR)
CVR TEST switch ′PUSH′
CVR self tests.
Verify area mic audio pickup.
FLIGHT MANAGEMENT SYSTEM (FMS)
Perform normal preflight
Confirm all FMC functions are operative
using normal preflight items.
STALL WARNING TEST
STALL WARNING TEST switches PUSH
Verify control column vibration when each
switch is pushed.
MACH AIRSPEED WARNING TEST
MACH AIRSPEED WARNING TEST
switch PUSH
NEW
Verify clacker sounds
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PREFLIGHT
________________________________________________________________________
NEW
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CHAPTER 1
PREFLIGHT
________________________________________________________________________
NEW
D6-22134-2
PROPERTY OF THE BOEING COMPANY
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CHAPTER 2
ENGINE START
_______________________________________________________
CONTENTS
STARTER OPERATION
ENGINE GENERATORS
NEW
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PROPERTY OF THE BOEING COMPANY
30
CHAPTER 3
AFTER ENGINE START
_____________________________________________________________
CONTENTS
ENGINE TAI
FUEL SYSTEM
HYDRAULIC SYSTEM
ENGINE OPERATIONS
INSTRUMENT SWITCHING
PNEUMATICS
ELECTRICAL SYSTEM
PRESSURIZATION
NEW
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CHAPTER 4
TAXI
_____________________________________________________________
CONTENTS
BRAKES & ANTI-SKID
STEERING
FLIGHT INSTRUMENTS
FMS
NEW
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PROPERTY OF THE BOEING COMPANY
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CHAPTER 5
TAKEOFF
_____________________________________________________________
CONTENTS
LANDING GEAR
TRAILING EDGE AND LEADING EDGE FLAPS
AUTOTHROTTLE
PRESSURIZATION
NEW
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PROPERTY OF THE BOEING COMPANY
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CHAPTER 6
CLIMB
_______________________________________________________
CONTENTS
ENGINE OPERATIONS
PRESSURIZATION
TAI SYSTEMS
YAW DAMPER
FMS
FLIGHT CONTROLS
AUTOPILOT
APU FIRE HANDLE SHUTDOWN
NEW
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PROPERTY OF THE BOEING COMPANY
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CHAPTER 7
CRUISE
_______________________________________________________
CONTENTS
FMS
APU START
ELECTRICAL SYSTEMS
PRESSURIZATION
CABIN PRESSURE MAX DIFFERENTIAL
CABIN LEAKAGE
AIR CONDITIONING
CABIN ALTITIUDE WARNING
CABIN ALTITIUDE LIMITING
CABIN OXYGEN MASK DROP
CRUISE PERFORMANCE
FLIGHT INSTRUMENTS
FLIGHT CONTROLS
AIRPLANE TRIM
COMPASS HEADINGS
WINDOW HEAT
COMMUNICATION
NAVIGATION
AUTOPILOT / FLIGHT DIRECTOR
PNEUMATICS
FUEL SYSTEM
ENGINE OPERATIONS
CABIN SYSTEMS
NEW
D6-22134-2
PROPERTY OF THE BOEING COMPANY
35
CHAPTER 8
DESCENT
_____________________________________________________________
CONTENTS
AIRSPEED WARNINGS
ENGINE RELIGHTS
FMS
SPEEDBRAKES
CABIN PRESSURE
NEW
D6-22134-2
PROPERTY OF THE BOEING COMPANY
36
CHAPTER 9
LOW ALTITUDE
_____________________________________________________________
CONTENTS
ALTERNATE LANDING GEAR
ALTERNATE FLAPS
FLAP LOAD RELIEF
AUTO-SLAT / PTU
STALL WARNING
PNEUMATICS
AIRPLANE TRIM
AUTOPILOT / AUTOTHROTTLE ALPHA LIMITS
AIR CONDITIONING
CONFIGURATION WARNING
SPOILER FLOAT
APU BLEED / GENERATOR
NEW
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PROPERTY OF THE BOEING COMPANY
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CHAPTER 10
APPROACH
_____________________________________________________________
CONTENTS
AUTO FLIGHT / FMS
GROUND PROXIMITY WARNING
RAIN PROTECTION
NAVIGATION
NEW
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PROPERTY OF THE BOEING COMPANY
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CHAPTER 11
LANDING & SHUTDOWN
_____________________________________________________________
CONTENTS
AUTO SPEEDBRAKES
AUTOBRAKES
THRUST REVERSERS
PRESSURIZATION
RTO
APU START
SUCTION FEED
GENERATOR DISCONNECTS
FMS
FIRE HANDLE SHUTDOWN
NEW
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PROPERTY OF THE BOEING COMPANY
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Revision Record
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NEW
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41