BOEING 737-400 QUICK REFERENCE HANDBOOK

BOEING 737-400
QUICK REFERENCE HANDBOOK AND NON NORMAL CHECKLIST
Issue No.4 March 2014
Q-Pulse Ref No: PTR-TRM-37
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 BOEING 737-400 QRH

CONTENTS

PREFACE

ENGINES 1

Engine Fire, Severe Damage, or Separation 1.1

Engine Failure and Shutdown 1.3
Engine High Oil Temperature 1.4
Engine Low Oil Pressure 1.5
Engine Overtemperature - High EGT Indicated 1.5
Engine Overheat - Engine Overheat Light Illuminated 1.6
Engine Vibration 1.7
One Engine Inoperative 1.8
In Flight Engine Start 1.10
After Engine Flight Start Checks 1.12

ELECTRIC / FUEL / ANTI-ICING 2

Electrical Smoke or Fire 2.1
Bus Off Light Illuminated 2.2
Drive Low Oil Pressure or High Oil Temperature 2.3
Inadvertent Transfer Into Centre Tank 2.4
Operation With Fuel Contents Below 1500 Kgs 2.5
Temp Probe Illuminated 2.5

HYDRAULIC 3

Loss of System A 3.1
Landing Gear Gravity Extension 3.2
Loss of System B 3.3
Hydraulic Pump Low Pressure or Overheat 3.5

PRESSURISATION 4

Rapid Depressurisation 4.1
Emergency Descent 4.2
Off Scheduled Descent Light Illuminated 4.3
Unscheduled Pressurisation Change 4.4

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GENERAL 5

Landing Gear Lever Cannot Be Moved to Up Position 5.1
Gear Down Fuel Burn 5.2
Speeds and Altitudes 5.3
Passenger Evacuation 5.6

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 BOEING 737-400 QRH

PREFACE

The procedures in this QRH assume that certain actions are completed by the
crew, namely that:

• Normal procedures have been done properly.

• Aural warnings are silenced.

• Circuit breakers have been checked.

• Oxygen masks and goggles are donned when required.

Liaison with the cabin crew and all other relevant agencies is maintained via
PAs, radios, and normal conversation.

The crew divert to the nearest suitable airfield in the event of:

• An engine failure or fire.

• Cabin smoke or a fire whose location cannot be determined.

• Only one hydraulic system remaining.

• Only one AC source remaining.

• Any other situation that has a significant flight safety implication.

All the checks in this QRH are read and do by the Pilot Monitoring.
The Pilot Flying will observe these actions and operate the radios, but their
prime responsibility is to fly the aircraft.

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ENGINES
ENGINES 1

ENGINE FIRE, SEVERE DAMAGE, OR SEPARATION 1.1

ENGINE FAILURE AND SHUTDOWN 1.3

ENGINE HIGH OIL TEMPERATURE 1.4

ENGINE LOW OIL PRESSURE 1.5

ENGINE OVERTEMPERATURE - HIGH EGT INDICATED 1.5

ENGINE OVERHEAT - ENGINE OVERHEAT LIGHT ILLUMINATED 1.6

ENGINE VIBRATION 1.7

ONE ENGINE INOPERATIVE LANDING 1.8

IN FLIGHT ENGINE START 1.10

AFTER ENGINE FLIGHT START CHECKS 1.12

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1.1
ENGINE FIRE, SEVERE DAMAGE, OR SEPARATION

AUTO THRUST........................………………….............…DISENGAGE

THRUST LEVER ………………......……..…….................….......CLOSE

START LEVER………………………..….……..........................CUT OFF

ENGINE FIRE WARNING SWITCH ……......................................PULL

To manually unlock the Engine Fire Warning Switch, press the override
and pull.

If the Engine Fire Warning Switch remains illuminated

ENGINE FIRE WARNING SWITCH…….................ROTATE L or R

Rotate to stop and hold for one second.

If after 30 seconds the Engine Fire warning Switch remains

illuminated:

ENGINE FIRE WARNING SWITCH….....................ROTATE TO

REMAINING BOTTLE

If high vibration is felt:

Check buffet boundary - Reduce Airspeed - Descend

FUEL CROSSFEED VALVE ……..............………........................OPEN

APU …………………………...................………..........................START

ISOLATION VALVE SWITCH ……........……..............................CLOSE

APU BLEED AIR SWITCH ……………............................................OFF

START SWITCH (FAILED ENGINE) ...............................................OFF

APU ……………………………………....................ON RELEVANT BUS

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1.2

If wing anti-ice is required:

If the fire has not been extinguished, wing anti ice is not available.

However, if the Engine Fire Warning Switch is not illuminated:

PACK SWITCH (FAILED SIDE)...............................................OFF

ISOLATION VALVE SWITCH ..........................….................AUTO

Accomplish the ONE ENGINE INOPERATIVE LANDING checklist, page 1.8

END OF PROCEDURE

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1.3
ENGINE FAILURE AND SHUTDOWN

Accomplish an engine shutdown only when flight conditions permit

FUEL CROSSFEED VALVE.…......................................................OPEN

APU……………….…....................................................................START

AUTO THRUST……………….…........................................DISENGAGE

THRUST LEVER………………………..........................…................IDLE

Conditions permitting operate at idle for three minutes

APU …………………………………….....................ON RELEVANT BUS

START LEVER ……………………....................….............…....CUT OFF

START SWITCH (Failed Engine) ....................................................OFF

If wing anti-ice is required:

PACK SWITCH FAILED SIDE.............…....................................OFF

ISOLATION VALVE SWITCH...................................................AUTO

Accomplish the ONE ENGINE INOPERATIVE LANDING checklist, page 1.8

END OF PROCEDURE

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1.4
ENGINE HIGH OIL TEMPERATURE

If temperature rises to yellow band and flight conditions permit:

AUTO THRUST.......……..........….................................DISENGAGE

THRUST LEVER …….............................…...............................IDLE

If engine temperature remains below the yellow band maintain idle power

FUEL CROSSFEED VALVE ……........………....................OPEN

Accomplish the ONE ENGINE INOPERATIVE LANDING checklist, page

1.8

If engine oil temperature remains in the yellow band for 15 minutes:

Accomplish the ENGINE FAILURE AND SHUTDOWN checklist, page 1.3

If engine oil temperature rises into the red band:

Accomplish the ENGINE FAILURE AND SHUTDOWN checklist, page 1.3

END OF PROCEDURE

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1.5
ENGINE LOW OIL PRESSURE

OIL PRESSURE AND QUANTITY…….....................................CHECK

If engine oil pressure is at or below the red line:

AUTOTHRUST.......……….........…….......................DISENGAGE

THRUST LEVER…………….......………....…........…............IDLE

Accomplish the ONE ENGINE INOPERATIVE LANDING checklist,page 1.8

END OF PROCEDURE

ENGINE OVERTEMPERATURE - HIGH EGT INDICATED

AUTOTHRUST.......………......….......................................DISENGAGE

THRUST LEVER ……………..............……..............................RETARD

Retard the thrust lever until the EGT is within limits

If temperature stabilises within limits, maintain the N1 at that setting

FUEL CROSSFEED VALVE ……..….....….........................OPEN

Consider actioning the ONE ENGINE INOPERATIVE LANDING checklist,

page 1.8

If unable to maintain EGT within limits:

Accomplish the ENGINE FAILURE AND SHUTDOWN checklist, page 1.3

END OF PROCEDURE

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1.6
ENGINE OVERHEAT - ENGINE OVERHEAT LIGHT ILLUMINATED

AUTO THRUST...............................................................DISENGAGE

THRUST LEVER .....................................................................CLOSE

If engine overheat light remains illuminated:

Action the ENGINE FIRE, SEVERE DAMAGE OR SEPARATION
checklist, page 1.1

If engine overheat light extinguishes:

Operate the engine at reduced thrust to keep the light extinguished.

Consider actioning THE ONE ENGINE INOPERATIVE LANDING

checklist, page 1.8

END OF PROCEDURE

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1.7
ENGINE VIBRATION

Abnormal engine vibration or gauge above 4 units

AUTOTHRUST......………….……........................................DISENGAGE

THRUST LEVER ………………..….….......................................RETARD

Flight conditions permitting, reduce N1 until vibration ceases, or the gauge

is below 4.0 units.

FUEL CROSSFEED VALVE ……......…….....................................OPEN

Do not shut down an engine for high vibration indications alone.

Do not use full reverse on a suspect engine

Consider actioning the ONE ENGINE INOPERATIVE LANDING checklist

page 1.8

END OF PROCEDURE

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1.8
ONE ENGINE INOPERATIVE LANDING

Plan and brief for a Flaps 15 landing

DESCENT CHECKS

MSA……………..……..……...….................................………..STATED

PRESSURISATION ………………….....................LANDING ALT SET

START SWITCH…………................... CONT (OPERATING ENGINE)

IAS BUGS…………………………….SET FOR FLAP 15 APPROACH

ALTIMETERS BUGS………………..…..........................................SET

STANDBY ALTIMETER ……………………….…..................QNH SET

AUTOBRAKE.................................................................LEVEL _ SET

GROUND PROX SWITCH …………....……..................FLAP INHIBIT

GO AROUND PROCEDURE ………………...........................REVIEW

“DECIDE” “Go Around Flap 1”

PF must press TOGA button and advance the thrust lever
Pitch to 12.5 degrees. Do not follow the FD in pitch
Apply positive rudder to keep slip ball central
PM must manually set GA thrust
“Positive climb” “Gear Up”
“400 ft” “Heading Select”
“Acceleration Altitude” “Level Change Set Speed 210”
At 190 kts “190 kts” “Flaps Up”
“Flaps Up No Lights”
Maintain 210 kts to safety altitude or Missed Approach Altitude

The PF must manually reduce the thrust at the level off altitude to control
the speed.

BRIEFING………………………...……….………...............COMPLETE

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1.9
APPROACH CHECKS

RECALL ……………………………….......................………...CHECKED

ALTIMETERS ……………..............................QNH SET & X CHECKED

APPROACH AIDS…………........................COURSE SET: IDENTIFIED

If additional go-around thrust is required:

Additional thrust is not available if the Engine Fire Warning switch
is illuminated.
However, if the Engine Fire Warning switch is not illuminated:

ISOLATION VALVE ……………….…...…..…...................CLOSE

No1 ENGINE
BLEED AIR SWITCH…………………….…............................OFF

APU BLEED AIR SWITCH …..………….….............................ON

No2 ENGINE
BLEED AIR SWITCH ………………..……….….....................OFF

LANDING CHECKS

SPEEDBRAKE ………………..........................ARMED, GREEN LIGHT

LANDING GEAR ……………….......................….....DOWN, 3 GREENS

CABIN ……………………….....….........................SECURE & WARNED

FLAPS …………….......................15 REQUIRED 15/15 GREEN LIGHT

END OF PROCEDURE

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1.10
IN FLIGHT ENGINE START

IN FLIGHT ENVELOPE .............................................................CHECK

Caution: Use starter assist if the N2 is below 15%.

THRUST LEVER......................................................................CLOSED

START LEVER ......................................................................CUT OFF

ENGINE FIRE WARNING SWITCH .......................................STOWED

Then either:

STARTER ASSISTED START

PACK SWITCH ( AFFECTED SIDE )...............................................OFF

ISOLATION VALVE SWITCH .......................................................AUTO

DUCT PRESSURE ...............................................................MIN 30 PSI

If required advance the operating thrust lever to achieve 30 psi

IGNITION SELECT SWITCH .......................................................BOTH

START SWITCH .............................................................................GRD

At min 15% N2:

START LEVER ................................................................IDLE DETENT

Maximum EGT 725

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1.11
If engine starts

Accomplish the After Engine Flight Start Checks below:

If no EGT increase within 30 secs

START LEVER ...................................................................CUT OFF

START SWITCH .........................................................................OFF

Action the ENGINE FAILURE AND SHUTDOWN checklist page 1.3

or

WINDMILL START

START SWITCH .........................................................................FLIGHT

START LEVER ................................................................IDLE DETENT

If engine starts

Accomplish the After Engine Flight Start Checks below:

If no EGT increase within 30 secs

START LEVER ...................................................................CUT OFF

START SWITCH .........................................................................OFF

Action the ENGINE FAILURE AND SHUTDOWN checklist page 1.3

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1.12
AFTER ENGINE FLIGHT START CHECKS

Establish symmetric power and establish the engine performs safely.

Pay particular attention the EGT and any vibration indications

If the engine is performing safely:

FUEL ................................................................PUMPS AS REQUIRED

FUEL CROSSFEED ......................................................AS REQUIRED

ELECTRICAL ...........................................GENERATOR ON BUS BAR

AIR COND & PRESS...........................................PACKS BLEEDS SET

START SWITCHES .......................................................AS REQUIRED

APU................................................................................AS REQUIRED

AUTO THRUST .............................................................AS REQUIRED

END OF PROCEDURE

If the engine is not performing safely:

Action the ENGINE FAILURE AND SHUTDOWN checklist page 1.3

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2
ELECTRIC/FUEL/ANTI-ICING

ELECTRICAL SMOKE OR FIRE 2.1

BUS OFF LIGHT ILLUMINATED 2.2

ELEC/FUEL/ICE
DRIVE LOW OIL PRESSURE OR HIGH OIL TEMPERATURE 2.3

INADVERTENT TRANSFER INTO CENTRE TANK 2.4

OPERATION WITH FUEL CONTENTS BELOW 1500 KGS 2.5

TEMP PROBE ILLUMINATED 2.5

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ELEC/FUEL/ICE

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2.1
ELECTRICAL SMOKE OR FIRE

OXYGEN MASKS AND REGULATORS……...........................ON 100%

CREW COMMUNICATION ……………...............................ESTABLISH

If smoke source can be determined:

ELECTRICAL POWER ………………......….......................REMOVE

If smoke source cannot be determined:

GALLEY POWER ……………….......…………...........................OFF

Land at the nearest suitable airfield.

END OF PROCEDURE

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2.2
BUS OFF LIGHT ILLUMINATED

GENERATOR SWITCH …………………....………............................ON

If BUS OFF light remains illuminated

APU ……………………………….................................................START

When blue APU GEN OFF BUS light illuminated

APU GENERATOR……………….….....................ON RELEVANT BUS

If only one source of AC power remains:

Land at nearest suitable airport.

END OF PROCEDURE

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2.3
DRIVE LOW OIL PRESSURE OR HIGH OIL TEMPERATURE

APU...................……………….........................………….………..START

When blue APU GEN OFF BUS illuminates

APU…………………………………........................ON RELEVANT BUS

GENERATOR DRIVE DISCONNECT SWITCH..............DISCONNECT

END OF PROCEDURE

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2.4
INADVERTENT TRANSFER INTO CENTRE TANK

Before actioning this drill, descend below 30,000 feet to avoid engine
flame out.

PUMPS ON DECREASING WING TANK........................................OFF

CENTRE TANK FUEL PUMP SWITCH (affected side)……............ON

When the centre tank fuel pump low pressure light is out

WING TANK PUMPS.................................................................ALL ON

Leave the affected centre tank Fuel Pump Switch ON and the crossfeed
selector closed for the remainder of the flight.

END OF PROCEDURE

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2.5
OPERATION WITH FUEL CONTENTS BELOW 1500 KGS

Wing tank fuel

PUMP SWITCHES......................................................................ALL ON

CROSSFEED SELECTOR ...........................................................OPEN

START SWITCHES ......................................................................CONT

Apply thrust slowly to avoid rapid acceleration.

END OF PROCEDURE

TEMP PROBE LIGHT ILLUMINATED

CAPTAINs PITOT STATIC HEAT switch..........................OFF then ON

If light extinguishes:

No further action necessary

END OF PROCEDURE

If light remains on:

Do not rely on TAT indications

END OF PROCEDURE

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3
HYDRAULICS

LOSS OF SYSTEM A 3.1

LANDING GEAR GRAVITY EXTENSION 3.2

LOSS OF SYSTEM B 3.3

HYDRAULIC PUMP LOW PRESSURE OR OVERHEAT 3.5

HYDRAULICS

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HYDRAULICS

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3.1
LOSS OF SYSTEM A

FLIGHT CONTROL A Switch ……...............................STBY RUDDER

SYSTEM A PUMPS…………………….........…….......................…..OFF

The following systems are inoperative:

Ground Spoilers

Inboard flight spoilers

Auto pilot A

Nosewheel steering

Alternate brakes

No 1 engine thrust reverse has standby pressure

Plan for a manual gear extension.

DESCENT CHECKS (SYSTEM A)

MSA………………...………………….....................................CHECKED

PRESSURISATION…………………..............................LAND ALT SET

START SWITCHES....................................…...............................CONT

IAS BUGS…………………...............................................................SET

ALTIMETER BUGS..……….............................................................SET

STANDBY ALTIMETER..........................................................QNH SET

AUTOBRAKE...................................................................LEVEL _ SET

DESCENT BRIEF……………………...................................COMPLETE

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3.2
APPROACH CHECKS (SYSTEM A)

RECALL …………………………………….......................…...CHECKED

ALTIMETERS…….......…......................…QNH SET AND X CHECKED

APPROACH AIDS ………..........................COURSE SET; IDENTIFIED

For Gravity Extension see below.

LANDING GEAR GRAVITY EXTENSION PROCEDURE

LANDING GEAR LEVER.....................LEAVE IN THE OFF POSITION

MANUAL L/G EXTENSION HANDLES.…….............………….....PULL

Wait 15 seconds after the last MANUAL EXTENSION HANDLE is

pulled, then:

LANDING GEAR LEVER…………………...................................DOWN

LANDING CHECKS (SYSTEM A)

SPEEDBRAKE …………….….........................ARMED GREEN LIGHT

LANDING GEAR ………………..…...............….......DOWN 3 GREENS

CABIN ………………………..…......................SECURE AND WARNED

FLAPS……………………….......……..................._____ GREEN LIGHT

END OF PROCEDURE

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3.3
LOSS OF SYSTEM B

FLIGHT CONTROL B Switch….……......................…..STBY RUDDER

SYSTEM B PUMPS …………………....…….......................………..OFF

The following systems are inoperative:

Outboard flight spoilers

Autopilot B

Yaw damper

Normal brakes

No 2 engine thrust reverse has standby pressure

When selected out, all leading edges devices go to full extension and cannot
be retracted.

Trailing edge flaps have alternate electrical power.

Plan and brief for a Flap 15 landing and set VREF Flap 15.

When configuring, extend flaps on manoeuvring speed schedule using the

alternate flaps position switch, and then select flap lever to that position. Do not
set the speed until the flaps are at the desired position.

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3.4
DESCENT CHECKS (SYSTEM B)

MSA………………………………………........................……..CHECKED

PRESSURISATION………………......................…..LANDING ALT SET

START SWITCHES......................................................................CONT

IAS BUGS……………………..............SET FOR FLAP 15 APPROACH

ALTIMETER BUGS ..……............……............................................SET

STANDBY ALTIMETER..........................................................QNH SET

GROUND PROX SWITCH…………..…......................….FLAP INHIBIT

DESCENT BRIEF……………………...........................…....COMPLETE

APPROACH CHECKS (SYSTEM B)

RECALL …………………………………………......................CHECKED

ALTIMETERS……………..…....................QNH SET AND X CHECKED

ALTERNATE FLAPS MASTER SWITCH……................................ARM

AUTOBRAKE ………………………….………..…................….........OFF

APPROACH AIDS ……...….......................COURSE SET: IDENTIFIED

When configuring, extend flaps on manoeuvring speed schedule using the

alternate flaps position switch, and then select flap lever to that position.

Do not set the speed until the flaps are at the desired position.

When selected out, all leading edges devices go to full extension and
cannot be retracted.

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3.5
LANDING CHECKS (SYSTEM B)

SPEEDBRAKE ……..…...................................ARMED GREEN LIGHT

LANDING GEAR …...………....................................DOWN 3 GREENS

CABIN …………...….…..................................SECURE AND WARNED

FLAPS……..................................15 REQUIRED 15 15 GREEN LIGHT

END OF PROCEDURE

HYDRAULIC PUMP LOW PRESSURE OR OVERHEAT

PUMP SWITCH ...............................................................................OFF

END OF PROCEDURE

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4
PRESSURISATION

RAPID DEPRESSURISATION 4.1

EMERGENCY DESCENT 4.2

OFF SCHEDULED DESCENT LIGHT ILLUMINATED 4.3

UNSCHEDULED PRESSURISATION CHANGE 4.4

PRESSURISATION

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PRESSURISATION

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4.1
RAPID DEPRESSURISATION

OXYGEN MASKS AND REGULATORS…….......................…ON 100%

CREW COMMUNICATIONS .…..........................................ESTABLISH

PRESSURISATION MODE SELECTOR ….......................….........MAN

OUTFLOW VALVE SWITCH .....................................................CLOSE

If pressurisation is restored continue manual operation

NO SMOKING - FASTEN BELTS SIGNS........................……..........ON

PASSENGER OXYGEN (If required)…………….….....................…ON

If required:

EMERGENCY DESCENT ………….....................................…INITIATE

END OF PROCEDURE

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4.2
EMERGENCY DESCENT

EMERGENCY DESCENT…………...……...................……ANNOUNCE

EMERGENCY DESCENT………………...……..…...................INITIATE

THRUST LEVERS …………………….....…..……....................CLOSED

SPEED BRAKE ………….........……..….....................FLIGHT DETENT

Limit the speed and avoid high manoeuvring loads if the structural
integrity is in doubt.

TARGET SPEED ……………….………………..................…VMO /MMO

START SWITCHES ……………….........………................…...…..CONT

LEVEL OFF ALTITUDE............................................HIGHEST of MSA

or 10,000 FEET

When levelling off:

SPEEDBRAKE ………….........……...……................…DOWN DETENT

OXYGEN …………………..……........…....…..................AS REQUIRED

START SWITCHES .......................................................AS REQUIRED

PA......................................................................................COMPLETED

END OF PROCEDURE

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4.3
OFF SCHEDULED DESCENT LIGHT ILLUMINATED

If not landing at airport of departure:

FLIGHT ALTITUDE (ON PRESSURE CONTROLLER)…...........RESET

END OF PROCEDURE

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4.4
UNSCHEDULED PRESSURISATION CHANGE

Consider increasing thrust to ensure adequate air supply.

PRESSURISATION MODE SELECTOR........………...............….STBY

If standby mode cannot maintain the cabin pressure

PRESSURISATION MODE SELECTOR.................................MANUAL

OUTFLOW VALVE SWITCH.............................OPERATE MANUALLY

END OF PROCEDURE

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5
GENERAL

LANDING GEAR LEVER CANNOT BE MOVED TO UP POSITION 5.1

GEAR DOWN FUEL BURN 5.2

SPEEDS AND ALTITUDES 5.3

PASSENGER EVACUATION 5.6

GENERAL

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GENERAL

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5.1
LANDING GEAR LEVER CANNOT BE MOVED TO UP POSITION

LANDING GEAR LEVER .............................................SELECT DOWN

CAUTION:
Do not operate the trigger over-ride switch unless it is essential to raise the
undercarriage to ensure terrain clearance. Such operation can cause structural
damage to the aircraft and landing gear.

GEAR LEVER SOLENOID CB ..................................................CHECK

If circuit breaker has popped:

Do not reset

Leave gear down

Restrict airspeed to 220 kts and restrict altitude as shown on page 5.2

Consult gear down fuel burn graph page 5.2

END OF PROCEDURE

If circuit breaker has not popped:

Make one further attempt to move the gear lever

If lever moves and gear retracts:

Continue with trip

If lever still cannot be moved:

LANDING GEAR LEVER .............................................SELECT DOWN

Leave gear down

Restrict airspeed to 220 kts and restrict altitude as shown on page 5.2

Consult gear down fuel burn graph page 5.2

END OF PROCEDURE

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5.2 GEAR DOWN FUEL BURN

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 QRH - GENERAL

SPEEDS AND ALTITUDES 5.3

V Ref Speeds

Weight Flap Setting

X 1000 kgs 40 30 15

70 155 Kts 159 Kts 182 Kts

65 149 Kts 154 Kts 176 Kts
60 143 Kts 147 Kts 169 Kts
55 137 Kts 141 Kts 161 Kts
50 130 Kts 134 Kts 155 Kts
45 124 Kts 127 Kts 147 Kts
40 116 Kts 119 Kts 137 Kts
35 109 Kts 111 Kts 128 Kts

Minimum Speeds In Turbulence And Maximum Cruise Altitudes

1.35 G Margin To Buffet Hence Turbulence Acceptable

Mass 50 Tonnes 53 Tonnes 56 Tonnes

FL 370 240 kts Too High Too High
FL 350 240 kts 250 kts Too High
FL 330 240 kts 245 kts 250 kts
FL 310 235 kts 240 kts 245 kts

FL 300 – FL 210 ALL MASSES MINIMUM SPEED 235 KTS

FL 200 – FL 100 ALL MASSES MINIMUM SPEED 220 KTS
BELOW FL 100 ALL MASSES MINIMUM SPEED 210 KTS

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March 2014
QRH - GENERAL

5.4
Single Engine Drift Down Level Off Altitudes

Mass And Drift Stabilising Altitudes And N1

Down Ias Settings At Various
Isa Deviations

MASS IAS ISA +10 ISA +15 ISA+20

56 Tonnes 250 kts 20600 / 90.4 19100 / 90.8 18500 / 90.9
54 Tonnes 245 kts 21500 / 90.4 20300 / 90.8 19600 / 90.9
52 Tonnes 245 kts 22500 / 90.4 21400 / 90.8 20600 / 90.9
50 Tonnes 240 kts 23500 / 90.4 22500 / 90.8 21500 / 90.9

Published by CAE Oxford Aviation Academy

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March 2014
 QRH - GENERAL

INTENTIONALLY BLANK

Published by CAE Oxford Aviation Academy

© CAE Oxford Aviation Academy All Rights Reserved
March 2014
QRH - GENERAL

5.6
PASSENGER EVACUATION

CAPTAIN

1. PARKING BRAKE ...............................................................SET

2. FLAPS.....................................................................................40

3. SPEEDBRAKES...............................................DOWN DETENT

4. START LEVERS..........................................................CUT OFF

5. EVACUATION ALERT................................................ACTIVATE

FIRST OFFICER

1. STANDBY POWER SWITCH...............................................BAT

2. PRESSURISATION......................................................MANUAL

3. OUTFLOW VALVE............................................................OPEN

4. ENGINE & APU FIRE HANDLES......................................PULL

10. ATC.................................................................................NOTIFY

Published by CAE Oxford Aviation Academy

© CAE Oxford Aviation Academy All Rights Reserved
March 2014