Boeing 737 - 600/700/800/900. Operations Manual (1997 year)

Boeing 737 Operations Manual

Supplementary Procedures

Chapter SP

Electrical

Section 6

Standby Power Test

[Option - Single battery]

Battery switch

AC-DC meter selectors

STBY PWR

If APU generator is on-line:

BUS TRANSFER switch

OFF

APU GEN No. 2 switch or GRD PWR switch

OFF

Turn OFF appropriate switch depending on power source in use. Removes

power from TR 3.

STANDBY POWER switch

OFF

Check STANDBY PWR OFF light illuminated.

AC-DC voltmeters

Zero

STANDBY POWER switch

BAT

Check STANDBY PWR OFF Light extinguished

AC-DC voltmeters

Check

AC voltmeter 115 +/-5 volts

DC voltmeter 24 +/-2 volts

Frequency meter

Check

Check frequency meter for normal indication: 400 +/- 10 CPS.

STANDBY POWER switch

AUTO

BUS TRANS switch

AUTO

APU GEN No. 2 switch or GRD PWR switch

Note: It may take up to 3 minutes for CDS displays to recover when

power is interrupted for more than 2 seconds on the ground.

SP.6.1

Supplementary Procedures -

Electrical

Boeing 737 Operations Manual

Standby Power Test

[Option - Dual battery]

Battery switch

AC-DC meter selectors

STBY PWR

If APU generator is on-line:

APU GEN No. 1 switch

OFF

APU GEN No. 2 switch

OFF

If ground power is on-line:

GRD PWR switch

OFF

STANDBY POWER switch

OFF

Check STANDBY PWR OFF light illuminated.

AC-DC voltmeters

Zero

STANDBY POWER switch

BAT

Check STANDBY PWR OFF Light extinguished.

AC-DC voltmeters

Check

AC voltmeter 115 +/-5 volts

DC voltmeter 24 +/-2 volts

Frequency meter

Check

Check frequency meter for normal indication: 400 +/- 10 CPS.

DC meter selector

BAT

Check DC voltmeter for normal indication: 24 +/- 2 volts.

Check DC ammeter for discharge indication: a negative value.

DC meter selector

AUX BAT

Check DC voltmeter for normal indication: 24 +/- 2 volts.

Check DC ammeter for discharge indication: a negative value.

STANDBY POWER switch

AUTO

SP.6.2

October 15, 2001

Boeing 737 Operations Manual

Supplementary Procedures

Chapter SP

Engines, APU

Section 7

Battery Start

(With APU bleed or ground air available)

Prior to a battery start, accomplish the exterior safety inspection and the

flight deck safety inspection. Accomplish interior/exterior inspections

if required except for items requiring electrical or hydraulic power.

Accomplish the following preliminary flight deck preparation items:

Fault/Inop detection

Check

Fire/Overheat warning

Check

EXT TEST switch

Check

APU (bleed air source if available)

Start

Flap Lever

Set

Position the FLAP lever to agree with the FLAPS position indicator.

Emergency equipment

Check

Circuit breakers

Check

Flight recorder

Set

Crash axe

Stowed

On the captain's command, the first officer reads and the captain

accomplishes the following items:

Oxygen & interphone

Check

CAB/UTIL power switch

IFE/PASS seat power switch

EMER EXIT LIGHTS switch

ARMED

Passenger signs

Set

HYD PUMP switches

Air conditioning & pressurization

_____ Pack(s), bleeds ON, set

SP.7.1

Supplementary Procedures -

Engines, APU

Boeing 737 Operations Manual

Parking brake

Set

Note: The wheels should be chocked in case the brake pressure

has bled down.

Papers

Aboard

Cleared for Start

PACK switches

OFF

ANTICOLLISION light switch

Ignition select switch

IGN-R

Engine Start

Engine No. 1 start

Accomplish

Only N1, N2, and oil quantity are displayed until the EECs are

powered.

Generator No. 1 switch

IRS mode selectors

NAV

FMC/CDU

Set IRS position

WARNING: If engine No. 1 was started using a ground air

source, to minimize the hazard to ground

personnel, the external air should be disconnected

and engine No. 2 started using the Engine

Crossbleed Start procedure.

Engine No. 2 start

Accomplish

Generator No. 2 switch

After Start

Complete the preliminary flight deck preparation by checking the

following items:

MACH AIRSPEED WARNING test switches

Push

STALL WARNING TEST switches

Push

REVERSER lights

Check

EEC switches

ALTN then ON

SP.7.2

Supplementary Procedures -

Engines, APU

Boeing 737 Operations Manual

Passenger oxygen switch

NORMAL

Crew oxygen

Check

Accomplish panel scan to insure that the flight deck preparation

procedure is complete.

AFTER START checklist

Accomplish

IRS alignment

Complete & no flags

The airplane is ready for taxi. Refer to the normal checklists for

subsequent checks.

Starting with Ground Air Source

(AC electrical power available)

Engine No. 1 must be started first.

When cleared to start:

APU BLEED air switch

OFF

Engine No. 1 start

Accomplish

Use normal start procedures.

WARNING: To minimize the hazard to ground personnel, the

external air should be disconnected, and engine No. 2

started using the Engine Crossbleed Start procedure.

Engine Crossbleed Start

Prior to using this procedure, ensure that the area to the rear is clear.

Engine BLEED air switches

APU BLEED air switch

OFF

PACK switches

OFF

ISOLATION VALVE switch

AUTO

Ensures bleed air supply for engine start.

Engine thrust lever

(operating engine)

Advance thrust lever until bleed

duct pressure indicates 30 PSI

SP.7.3

Supplementary Procedures -

Engines, APU

Boeing 737 Operations Manual

Non-operating engine

Start

Use normal start procedures with crossbleed air.

After starter cutout, adjust thrust on both engines, as required.

Setting N1 Bugs with an Inoperative FMC

Reference the Performance - Inflight section to determine N1 setting

for desired phase of flight.

N1 SET outer knob

BOTH

The last FMC computed value is displayed by reference N1 bugs and

readouts. If the FMC has not calculated an input since power up, a default

value of 104% is displayed.

N1 SET inner knob

Set N1

Note: If the N1 SET outer knob is returned to the AUTO position, the

bugs and readouts will revert to the last FMC computed value or

104% if the FMC has not calculated an input since power up.

APU Start

Note: With at least one generator operating, subsequent start attempts

should be made at succeedingly lower altitudes until a

satisfactory start is accomplished.

Note: During the APU start cycle, the APU EGT indication may

fluctuate from 0° to 1100° C prior to normal EGT rise and the

LOW OIL PRESSURE light may cycle on and off several

times.These indications have no adverse effect on starting the

APU. It is not necessary to monitor EGT during start. Automatic

shutdown occurs in the event of EGT exceedance. If the LOW

OIL PRESSURE light illuminates after the start cycle is

complete, accomplish the APU LOW OIL PRESSURE

non-normal checklist.

APU Switch

START

Momentarily position APU switch to START and release to ON.

Check LOW OIL PRESSURE light illuminates, then extinguishes.

SP.7.4

Supplementary Procedures -

Engines, APU

Boeing 737 Operations Manual

Check APU GEN OFF BUS light illuminates.

Note: The start cycle may take as long as 120 seconds.

Note: If extended APU operation is required on the ground and fuel is

loaded in the center tank, place the left center tank fuel pump

switch ON to prevent a fuel imbalance before takeoff.

CAUTION: Do not operate the center tank fuel pumps with the

flight deck unattended.

[Option - Without DC Operated APU Fuel Pump]

Note: Whenever the APU is operating and AC electrical power is on

the airplane busses, extended service life of the APU fuel

control unit can be realized by operating at least one fuel boost

pump to supply fuel under pressure to the APU.

SP.7.5

Boeing 737 Operations Manual

Supplementary Procedures

Chapter SP

Fire Protection

Section 8

Fire and Overheat System Test with an Inoperative Loop

To determine the specific inoperative loop:

OVHT DET switches

Test switch

OVHT/FIRE

If the FAULT light remains extinguished and both ENG OVERHEAT

lights and engine fire warning switches illuminate, loop A is good.

If the FAULT light illuminates and one of the ENG OVERHEAT lights

and corresponding engine fire warning switch remain extinguished,

there is a fault in loop A of the detection system of that engine.

OVHT DET switches

Test switch

OVHT/FIRE

If the FAULT light remains extinguished and both ENG OVERHEAT

lights and engine fire warning switches illuminate, loop B is good.

If the FAULT light illuminates and one of the ENG OVERHEAT lights

and corresponding engine fire warning switch remain extinguished,

there is a fault in loop B of the detection system of that engine.

OVHT DET switches

As required

Select the good loop for each engine (NORMAL if both loops tested

good).

Test switch

OVHT/FIRE

If the test is successful leave the fire panel in this configuration for

flight.

SP.8.1

Boeing 737 Operations Manual

Supplementary Procedures

Chapter SP

Flight Controls

Section 9

Flight Controls Check

This is a check of normal flight control functions and is not a complete check of

the flight control system. Two people are required; both on interphone.

FLIGHT DECK ACTION

GROUND RESPONSE

Electrical power (APU or external)

- On bus

System A and B electric hydraulic

pump switches - OFF

Control wheel - Left

“LEFT AILERON UP, TAB

DOWN; RIGHT AILERON

DOWN, TAB UP”

Control wheel - Right

“LEFT AILERON DOWN, TAB

UP; RIGHT AILERON UP, TAB

DOWN”

Control wheel - Neutral

Control column - Forward

“ELEVATOR DOWN, TABS UP”

Control column - Aft

“ELEVATOR UP, TABS DOWN”

Control column - Neutral

Request hydraulic clearance

“CLEAR FOR HYDRAULIC

PRESSURE, WING AND

CONTROL AREAS CLEAR”

System A and B electric hydraulic

pump switches - ON

Verify System A & B pressure

indicators and brake pressure

indicator read 2800 psi minimum

Parking brake - Set

Rudder trim - Turn left

Verify left rudder pedals move

forward

SP.9.1

Supplementary Procedures -

Flight Controls

Boeing 737 Operations Manual

FLIGHT DECK ACTION

GROUND RESPONSE

Rudder trim - Turn right

Verify right rudder pedals move

forward

Rudder trim

- Zero, pedals

centered

Aileron trim - Turn left

Verify control wheel turns to left

Aileron trim - Turn right

Verify control wheel turns to right

Aileron trim - Zero, control wheels

centered

Flap lever - UP

Verify flap position indicator reads

zero

Nose gear steering wheel - Hold

“LEFT

AILERON

UP,

TAB

DOWN; LEFT

FLIGHT

Control wheel - Left

SPOILERS

UP;

RIGHT

Control column - Forward

AILERON DOWN,

TAB UP;

Rudder pedal - Left

RUDDER LEFT; ELEVATORS

DOWN, TABS UP”

Nose gear steering wheel - Hold

“LEFT AILERON DOWN, TAB

UP; RIGHT FLIGHT SPOILERS

Control wheel - Right

UP; RIGHT AILERON UP, TAB

Control column - Aft

DOWN; RUDDER RIGHT;

Rudder pedal - Right

ELEVATORS UP, TABS DOWN”

Flight controls - Neutral

Alternate flaps master switch

ARM

Flap lever - Position 1

Verify no flap movement

SP.9.2

Supplementary Procedures -

Flight Controls

Boeing 737 Operations Manual

FLIGHT DECK ACTION

GROUND RESPONSE

Alternate flaps position switch -

“FLAPS MOVING DOWN”

hold DOWN until flap position

indicator indicates 1

Flap position indicator - flaps 1

“ALL

LEADING

EDGE

DEVICES FULLY EXTENDED”

Verify aft overhead leading edge

devices annunciator panel indicates

all green (FULL EXTEND) with

no amber lights illuminated.

Verify LE FLAPS TRANSIT light

remains illuminated

Alternate flaps master switch

“LEADING EDGE FLAPS

OFF

FULLY EXTENDED, ALL

LEADING EDGE SLATS

Verify Aft overhead leading edge

RETRACTED TO EXTEND

devices annunciator panel indicates

POSITION”

all leading edge flaps full extended

and all leading edge slats in extend

position

Verify LE FLAPS EXT light

illuminated

Speed brake lever - UP

“ALL SPOILERS UP”

Speed brake lever - DOWN

“ALL SPOILERS DOWN”

Stabilizer trim switches - NOSE

“STABILIZER LEADING EDGE

DOWN

MOVING UP”

Stabilizer trim switches - NOSE

“STABILIZER LEADING EDGE

MOVING DOWN”

With stabilizer still moving:

Stabilizer trim cutout switches

CUTOUT

Verify trim motor stops

SP.9.3

Supplementary Procedures -

Flight Controls

Boeing 737 Operations Manual

FLIGHT DECK ACTION

GROUND RESPONSE

Stabilizer trim cutout switches

NORMAL

Verify Trim motor resumes

Control column - Forward

Verify Trim motor stops

Column actuated stab trim override

- OVERRIDE

Verify Trim motor resumes

Stabilizer trim switches - Trim into

green band

Column actuated stab trim override

- NORMAL

Switch guard - Close

Request clearance to flaps 30

“FLAPS CLEAR”

Flap lever - Position 30

“FLAPS MOVING DOWN”

Control column - Forward

“ELEVATOR DOWN, TABS

DOWN”

Control column - Aft

“ELEVATOR UP, TABS UP”

Control column - Neutral

Flap lever - UP

“FLAPS MOVING UP”

Parking Brake - As desired

Electrical power - As desired

SP.9.4

Boeing 737 Operations Manual

Supplementary Procedures

Chapter SP

Flight Instruments, Displays

Section 10

Altimeter Difference

Note: If flight in RVSM airspace is planned use the RVSM table in the

limitations section.

This procedure is accomplished when there is a noticeable difference between the

altimeters. Accomplish this procedure in stabilized level flight or on the ground.

Altimeter barometric settings

Check

Check all altimeters set to proper barometric setting for phase of flight.

Standby altimeter baro set control

Rotate and reset

Rotate to a different setting, then reset proper barometric setting.

Altimeters

Crosscheck

Maximum differences between the altimeter readings:

Altitude

CDS/CDS

CDS/Standby

Sea Level

50 feet

5,000 feet

50 feet

80 feet

10,000 feet

60 feet

120 feet

15,000 feet

70 feet

(see note)

20,000 feet

80 feet

(see note)

25,000 feet

100 feet

(see note)

30,000 feet

120 feet

(see note)

35,000 feet

140 feet

(see note)

40,000 feet

160 feet

(see note)

41,000 feet

170 feet

(see note)

Note: Above 10,000 feet and 0.4 Mach, position error causes the

tolerance to diverge rapidly and direct crosscheck becomes

inconclusive. Differences greater than 400 feet should be

suspect and verified by ground maintenance checks.

If it is not possible to identify which altimeter is indicating the correct

altitude:

ATC

Notify

SP.10.1

Supplementary Procedures -

Flight Instruments, Displays

Boeing 737 Operations Manual

QFE Operation

This procedure is accomplished when ATC altitude assignments are referenced to

QFE altimeter settings.

Note: Do not use LNAV or VNAV below transition altitude/level.

Altitudes in the navigation data base are not referenced to QFE.

Use only raw data for navigation.

[Option - Altimeter with QFE]

FMC/CDU APPROACH REFERENCE page

or TAKEOFF REFERENCE page 2/2

Select

LANDING REF line select key

Push

Verify QFE selected.

[This sets the landing altitude to zero.]

Altimeters

Set

Set altimeters to QFE when below transition altitude/level.

Note: If QFE altimeter setting is beyond the range of the altimeters,

QNH procedures must be used with QNH set in the altimeters.

Landing altitude indicator

Set at zero

SP.10.2

October 15, 2001

Supplementary Procedures -

Flight Instruments, Displays

Boeing 737 Operations Manual

Setting Airspeed Bugs with an Inoperative FMC

To set reference airspeed bugs for takeoff:

Speed reference selector (outer)

Default speed of 80 knots is displayed.

Speed reference selector (inner)

Set V1 speed

V1 bug is displayed when a speed greater than 80 knots is set. The NO

VSPD flag is displayed until both V1 and VR are set.

Speed reference selector (outer)

Default speed of 80 knots is displayed.

Speed reference selector (inner)

Set VR speed

VR bug is displayed when a speed greater than 80 knots is set. The NO

VSPD flag is removed after both V1 and VR are set.

MCP speed selector

Set V2

Airspeed cursor and V2+15 bug move to the correct speeds.

Speed reference selector (outer)

Default weight of 32,000 kgs / 70,000 lbs is displayed.

Speed reference selector (inner)

Set takeoff gross weight

Flaps up maneuver speed bug is displayed.

Note: If VREF is selected on the ground, INVALID ENTRY is

displayed.

To set the spare bug, if desired:

Speed Reference selector (outer)

Spare bug

Default speed of 60 knots is displayed.

Speed reference selector (inner)

Set

Set speed as desired.

Speed reference selector (outer)

SET

Digital readout is removed.

Note: When the flap lever is set to any takeoff flap setting above

flaps 1, a bug comes into view for the next smaller flap

maneuvering speed, between takeoff flaps and flaps up. For

SP.10.3

Boeing 737 - 600/700/800/900. Operations Manual (1997 year) - page 12