Differences Training 747-400

12/22/2011

Preamble

12/22/2011

The purpose of this presentation is to familiarize the crew with the

various differences in procedures and systems among the 747-400

Fleet. The presentation highlights differences in the FCOM Volume 1,

FCOM Vol II and the QRH.

*All FCOM Volume 1 and 2 differences are highlighted in RED

Where a particular system/component or procedure only applies to a

particular aircraft, the effectivity will be highlighted in red.

*All QRH differences are highlighted in Yellow

Where there are differences which apply to both aircraft every attempt

has been made show them side by side in order to draw out the

distinctions.

Preface Model Identification

12/22/2011

Airplane Number Registry Number Serial Number Tabulation Number

400 N400SA 27068 RT 521

469 N469AC 27602 RM 082

NOTE:. The overriding difference on N469AC is that it is equipped with GE engines.

Normal Procedures Preflight procedures – First Officer

N400SA N469AC

N400SA AUTO IGNITION selector - 1 or 2

N469AC

AUTO IGNITION selector - SINGLE

AUTO START switch (if installed) - ON

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Engine Start Procedure

N400SA

Select the secondary engine indications. F/O

Pack control selectors ............................................................... SET F/O

Set two or three packs off..

Start sequence .................................................................. Announce C

Call “START ___ ENGINE.” C

Engine START switch .................................................................. Pull F/O

Verify that the N2 RPM increases. F/O

Verify that the oil pressure increases. C, F/O

At maximum motoring (N2 greater than or equal to the fuel-on indicator

and no increase for five to ten seconds) and a minimum of the fuel-on indicator:

FUEL CONTROL switch..........................................................RUN C

Verify that the EGT increases and stays below the EGT limit…… C, F/O

After the engine is stabilized at idle, start the other engines. Do the ABORTED

ENGINE START checklist for one or more of the following abort start conditions:

• the EGT does not increase by 20 seconds after the fuel control

switch is moved to RUN

• there is no N1 rotation by 40% N2

• the EGT quickly nears or exceeds the start limit

• the N2 is not at idle by 2 minutes after the fuel control switch is

moved to RUN

• the oil pressure indication is not normal by the time the engine is

stabilized at idle

Normal Procedures

Engine Start Procedure

Normal Procedures Engine Start Procedure (Auto Start)

N469AC

Select the secondary engine indications. F/O

Pack control selectors .................................................................. SET F/O

Set two or three packs off. To start two engines at the same time,

it may be necessary to set three packs off.

Start sequence ..................................................................... Announce C

Call “START ___ ENGINE.” C

Engine START switch .................................................................. Pull F/O

FUEL CONTROL switch.............................................................RUN C

Verify that the oil pressure increases. C, F/O

Verify that there is N1 rotation and an oil pressure indication by idle N2. ………C, F/O

After the engine is stabilized at idle, start the other engines.

Autostart does corrective steps for:

• no EGT rise

• a hot start

• a hung start

Do the ABORTED ENGINE START checklist for one or more of the

following abort start conditions:

• there is no N1 rotation by idle N2

• the fuel control switch is in RUN, the engine RPM is low, and the

Autostart switch is off

• the oil pressure indication is not normal by the time the engine is stabilized at idle

N469AC – Auto Start Procedure

Normal Procedures Before Takeoff Procedure

Before Takeoff Procedure

When responding to the “FLAPS” challenge in the BEFORE TAKEOFF CHECKLIST, the

PF is verifying that the CDU and EICAS flap selections agree with the takeoff

performance calculated.

Engine warm up requirements:

• engine oil temperature must be above the

lower amber band before takeoff Engine warm

up recommendations (there is no need to delay

the takeoff for these recommendations):

• when the engines have been shut down more

than 2 hours:

• run the engines for 5 minutes

• when the taxi time is expected to be less than

5 minutes, start the engines as early as feasible

• use a thrust setting normally used for taxi

operations

N400SA

Engine warm up requirements:

• engine oil temperature must be above the

bottom of the temperature scale

Engine warm up recommendations:

• run the engines for at least 3 minutes

• use a thrust setting normally used for taxi

operations

N469AC

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Normal Procedures Takeoff Procedure

Advance the thrust levers to

approximately 1.10 EPR.

Allow the engines to stabilize.

Advance the thrust levers to

approximately 70% N1.

Allow the engines to stabilize.

N400SA N469AC

Procedure also applies to Supplemental Procedure – Low Gross Wt, Aft CG Takeoff

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Normal Procedures After Landing Procedure

Engine cool down requirement:

• run the engines for at least 90 seconds

• use a thrust setting no higher than that

normally used for taxi operations

Engine cool down recommendations:

• run the engines for at least 5 minutes

• use a thrust setting no higher than that

normally used for taxi operations

Engine cool down recommendations:

• run the engines for at least 3 minutes

• use a thrust setting normally used for taxi

operations

N400SA N469AC

12/22/2011

Supplementary Procedures Weather Radar Test

Weather Radar Mode selector..............................non-TEST mode

ND Mode selector.................................................MAP

EFIS WXR switch.................................................Push

Note: In the short time the weather radar is on and not in the TEST position, it will radiate.

Weather Radar Mode selector..............................TEST

Observe the following sequence (approximately 20 seconds).

The amber WINDSHEAR annunciation shows on the NDs and the aural message “monitor radar

display” sounds.

Then the amber WINDSHEAR annunciation blanks, the Master

Warning lights illuminate, and the WINDSHEAR SYS and WINDSHEAR PRED EICAS

messages show.

Then the red WINDSHEAR annunciation shows on the NDs, the WINDSHEAR SYS and

WINDSHEAR PRED EICAS messages blank, the Master Warning lights extinguish, and the

aural messages “go around, windshear ahead”, and then “windshear ahead, windshear ahead”

sound.

During this time, the “rainbow” test pattern (with embedded PWS symbol) is shown.

N400SA

Continue 12/22/2011

Supplementary Procedures Weather Radar Test

Weather Radar Mode selector.............................................................TEST

ND Mode selector ............................................................................... MAP

EFIS WXR switch ............................................................................... Push

Verify radar test pattern displays on ND.

EFIS WXR switch ............................................................................... Push

Select Captain’s and First Officer’s weather radar displays off.

Weather Radar Mode selector ................................................... As desired

N469AC

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Supplementary Procedures Electrical Power up

Electrical Power Up The following procedure is accomplished to permit safe application of electrical power.

If APU power desired:

APU Start Source switch (if installed) - TR

APU selector – START, then ON

Position APU selector back to ON position. Do

not allow APU selector to spring back to ON

position.

APU generator 1 and APU generator 2 AVAIL

lights - Illuminated

APU GENERATOR 1 switch - Push

Verify ON light illuminated.

APU GENERATOR 2 switch - Push 12/22/2011

Supplementary Procedures Engine Start Procedure – Manual Start

Engine Start Procedure - Manual Start

N469AC

Select the secondary engine indications. F/O

Pack control selectors.....................................................................SET F/O

All packs may be off or one pack may be on for engine start.

Start sequence..........................................................................Announce C

AUTOSTART switch..........................................................................Off F/O

Call “START ___ ENGINE” C

Engine START switch.......................................................................Pull F/O

Verify that the N2 RPM increases. F/O

Verify that the oil pressure increases. C, F/O

At the fuel-on indicator:

FUEL CONTROL switch......................................................................RUN C

Verify that the EGT increases and stays below EGT limit. C, F/O

After the engine is stable at idle:

If autostart is operative:

AUTOSTART switch.......................................................................... ON F/O The autostart switch may stay OFF between manual starts when more than one engine is to be started manually.

After the engine is stabilized at idle, start the other engines.

Do the ABORTED ENGINE START checklist for one or more of the following abort start conditions:

• the EGT does not increase by 25 seconds after the fuel control switch is moved to RUN

• there is no N1 rotation by idle N2

• the EGT quickly nears or exceeds the start limit

• N2 does not stabilize at idle

• the oil pressure indication is not normal by the time the engine is stabilized at idle

Supplementary Procedures Cold Weather Operations

Taxi - Out

CAUTION: Taxi at a reduced speed. Use smaller tiller and rudder inputs, and apply

minimum thrust evenly and smoothly. Taxiing on slippery taxiways or runways at

excessive speed or with high crosswinds may start a skid.

When nacelle anti-ice is required and the OAT is 3°C or below, do an engine run up, as

needed, to minimize ice build-up.

Use the following procedure: …………………………….C

Check that the area behind the airplane is clear.

N400SA

Run-up to a minimum of 50% N1 for

approximately 1 second duration at

intervals no greater than 15 minutes.

N469AC

Run-up to a minimum of 60% N1 for

approximately 30 seconds duration at

intervals no greater than 30 minutes.

This procedure and parameters also apply to SP - “After Landing Procedure”

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Supplementary Procedures Cold Weather Operations

Takeoff Procedure

Do the normal Takeoff Procedure with the following modifications.

When nacelle anti-ice is required and the OAT is 3°C or below, the takeoff must be preceded

by a static engine run-up. Use the following procedure:

N400SA

Run-up to a minimum of 50% N1

and confirm stable engine

operation before the start of the

takeoff roll.

N469AC

Run-up to a minimum of 60% N1 for

approximately 30 seconds

duration and confirm stable engine

operation before the start of the takeoff roll.

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Supplementary Procedures Cold Weather Operations

Nacelle Anti-ice Operation – In flight

N400SA Nacelle anti-ice must be ON during all flight operations when icing conditions exist or are anticipated, except when the temperature is below –40°C SAT.

N469AC Prior to reducing thrust for descent in visible moisture and TAT less than 10 °C, including SAT less than -40 °C, nacelle anti-ice switch must be in the ON position. At or below 22,000 ft, wing anti-ice selector must be in the ON position. When these icing conditions (visible moisture and TAT less than 10 °C, including SAT less than -40 °C) are no longer present or anticipated, place the nacelle and wing anti-ice selectors in the OFF (or AUTO) position.

Supplementary Procedures Cold Weather Operations

Fan Ice Removal

Fan Ice Removal

CAUTION: Avoid prolonged operation in moderate to severe icing conditions.

If moderate to severe icing conditions are encountered:

During flight in moderate to severe icing conditions for prolonged periods with N1

settings at or below 70%, or when fan icing is suspected due to high engine vibration,

the fan blades must be cleared of any ice. Do the following procedure every 10 minutes

on all engines, one engine at a time: increase thrust to a minimum of 70% N1 for 10 to

30 seconds.

N469AC

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Limitations

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Weight Limitations

Additional weight limitations have been added to the above table. These limitations apply to N469AC and N400SA

Weights Pounds

Maximum Taxi Weight 878,000

Maximum Takeoff Weight 875,000

Maximum Fuel Transfer Weight 740,000

Maximum Landing Weight 652,000

Maximum Zero Fuel Weight 610,000

Minimum Flight Weight 377,400

Note: Maximum Fuel Transfer Weight is the weight above which Reserve Tanks 2

and 3 must be full.

Note: In order to be above the a/c minimum flight weight, a minimum payload or

fuel ballast of 20,000 lbs should be loaded.

Airplane General, Emergency Equipment, Doors, Windows

Oxygen Mask Panel

N400SA - Test and Reset switch is a push button type

O2 flow indicator located in the top left corner of panel

N469AC – Test and Reset switch is a slide type

O2 flow indicator located in the top right corner of panel

N400SA N469AC

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Air Systems

Shoulder Air Selector

1. Rotate – Sets air flow to side window shoulder air outlet

N469AC

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Anti-Ice, Rain Nacelle and Wing Anti-Ice Panel

•Push Button Switches installed

• Off – Valve Closed

• On – remains the same

• 3 Position Toggle switches installed

• Off - nacelle anti-ice valves commanded closed

• On – remains the same

• Auto -

• In flight, nacelle anti-ice operates in

response to inputs from the ice detection

system. Requirements for valve operation

are the same as ON position.

• On the ground, system off. When nacelle

anti-ice valve is open at touchdown, valve

remains open until engine shutdown.

N400SA N469AC

continue 12/22/2011

Anti-Ice, Rain Automatic Ice Detection System

N400SA Automatic Ice Detection System

The automatic ice detection system detects

airplane icing in flight. The system consists of

two ice detector probes on the forward fuselage.

The system provides signals to control the

nacelle and wing anti–ice systems when those

systems are in automatic mode.

N469AC

Nacelle Anti–Ice System

Nacelle Anti–Ice System Automatic Operation

In flight, when the NACELLEANTI-ICE switch is

in AUTO, nacelle anti–ice system operation is

automatic. When ice is detected, bleed air opens

the nacelle anti–ice valve and bleed air is

supplied to the engine cowl inlet. When ice is no

longer detected, the nacelle anti–ice valve closes

and bleed air is no longer supplied to the engine

inlet cowl.

Nacelle Anti–Ice System Manual Operation

On the ground and in flight, when the

NACELLEANTI-ICE switch is ON, bleed air

opens the nacelle anti-ice valve and bleed air is

supplied to the engine inlet cowl.

Ice Detection System

The automatic ice detection system detects

airplane icing in flight.

An ice detection system probe on the forward

fuselage detects airplane icing in

flight. The system provides data for displaying

EICAS alert messages.

Nacelle Anti-Ice System

The nacelle anti-ice system uses engine

bleed air to provide engine cowl inlet ice

protection. Nacelle anti-ice can be operated in

flight or on the ground. The nacelle

anti-ice indication NAI is displayed beside the

EICAS N1 indication when the

nacelle anti-ice valve is open.

When the Nacelle Anti-Ice switch is ON the

selected engine igniters operate

continuously.

Nacelle Anti-Ice System Operation

When the Nacelle Anti-Ice switch is ON, bleed

air opens the nacelle anti-ice valve

and bleed air is supplied to the engine inlet

cowl.

Communications Glareshield Microphone Switch

N469SA

1. Push – allows oxygen mask or boom microphone transmission on selected transmitter.

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Communications Captain Audio System Switch

N469AC

1. CAPT AUDIO SYSTEM Switch Normal (NORM) - all communication systems operate normally. VHF-L DIRECT - bypasses audio system by connecting Captain’s boom/mic

headset and control wheel push-to-talk switches directly to VHF-L transceiver. Allows Captain to communicate on VHF-L transceiver if audio system failure causes loss of communication. Volume control is not available.

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Communications Printer Controls

N400SA 1. FAIL Light

Illuminated (amber) –

• printer failure, or

• test in progress

2.PAPER Light

Illuminated (amber) –

• test in progress, or

• paper jam

3. RESET Switch

Push –

• aborts current print job

• deletes pending print job(s)

• resets printer

Illuminated (white) –

• reset in progress, or\

• test in progress

4. TEST Switch

Push –

• tests printer

• prints test pattern

Illuminated (white) - test in progress.

5. SLEW Switch

Push and hold – advances paper. Continue

Appearance and switch functions 12/22/2011

Communications Printer Controls

1. SLEW Switch

Push and hold - advances paper.

2. RESET Switch

Push - resets Message (MSG) light.

3. TEST Switch

Push –

• tests printer

• when pushed with RESET switch, prints

test pattern.

4. PAPER Indicator

Indicates amount of paper in printer.

5. FAIL Light

Illuminated (amber) - indicates printer

failure.

6. PAPER Light

Illuminated (amber) - indicates printer out

of paper.

7. Message (MSG) Light

Illuminated (blue) - indicates message

sent to printer.

N469AC

Appearance and switch functions

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Communications Stuck Mic Protection

Stuck Mic Protection

On the ground, any VHF radio transmitting for longer than 35 seconds is disabled

following annunciation of a warning beep. The radio is enabled when the

microphone switch for that radio is released.

N469AC

On the ground or in flight, an EICAS advisory message RADIO TRANSMIT will

display if any VHF or HF transceiver has been keyed for more than 30 seconds.

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Electrical Alternate EFIS Selector

N400SA

ALTERNATE EFIS Selector

CAPT - left FMC, and left PFD and ND powered by APU alternate power if

captain transfer bus unpowered. right PFD and ND unpowered if both transfer

busses unpowered.

F/O - left FMC and first officer PFD and ND powered by APU alternate power if

first officer transfer bus is unpowered. Left PFD and ND unpowered if both

transfer busses unpowered.

Note: Selector not functional during normal electrical system operation, or with

failure of only captain transfer bus. 12/22/2011

Electrical Electrical Power System Schematic

N400SA N469AC

Note: N469AC does not have the alternate EFIS switch

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Engines, APU Primary Engine Display

N400SA N469AC

1. Primary Engine Indications

Displayed full time on EICAS display:

• N1

• EGT

The N1 indication does not change color

when the maximum N1 is reached

Primary Engine Indications

Displayed full time on EICAS display:

• EPR

• N1

• EGT

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Engines, APU EPR/N1 Indications N400SA N469AC

Primary Engine Indications

Displayed full time on EICAS

display:

• N1

• EGT

Thrust Reverser Indication

Displayed REV (amber) - reverser in transit.

Displayed REV (green) - reverser fully deployed.

EPR

Digital EPR displayed (white).

Maximum EPR Line

Displayed (amber) - maximum allowable thrust.

Displayed (white) - maximum EPR is invalid.

EPR Indication

EPR, displayed:

• (white) - normal operating range

• (red) - operating limit reached

Reference EPR

Displayed (digital, green) - reference thrust selected by

FMC.

PW - The EEC selects an unannunciated alternate mode when reverse thrust is used due to

EPR sensing inaccuracies during reverser operation.

Engines, APU N2 Indication

At maximum motoring (N2 greater than or equal

to the fuel-on indicator and no increase for five

to ten seconds) and a minimum of the fuel-on

indicator:

FUEL CONTROL

switch..........................................................RUN

At the fuel-on indicator:

FUEL CONTROL

switch..............................................RUN

N400SA N469SA

12/22/2011

Engines, APU Oil Pressure Indications

4. Oil Pressure Amber Band - GE only Displayed (amber) – oil pressure caution range.

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Engines, APU Engine Vibration Indications

Engine Vibration Source

Identifies the vibration source being displayed.

Displayed (white) – vibration source with the

highest vibration:

• FAN - fan vibration

• LPT - N1 Low Pressure Turbine vibration

• N2 - N2 rotor vibration

Engine Vibration Source Identifies the vibration source being displayed. Displayed (white) - vibration source with the highest vibration: • N1 - N1 rotor vibration • N2 - N2 rotor vibration

N400SA N469AC

12/22/2011

Engines, APU Compact Engine Display

N400SA N469AC

Compact Engine Indications

Displayed continuously:

• EPR (Only for P&W Engines)

• N1

• EGT

Compact Engine Indications Displayed continuously: • N1 • EGT

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Engines, APU Engine Start Panel

N400SA N469AC

AUTO IGNITION Selector

1, BOTH, or 2 - selects respective

igniters. AUTO IGNITION Selector

SINGLE -

• EEC alternates igniter 1 and igniter 2

after every second ground start

• EEC selects both igniters for in-flight

start or flameout

Selected igniters operate when any of

the following occur:

• engine flameout

Engine START Switches

Pull (Autostart switch ON) –

• arms start valve

• opens engine bleed air valve

Pull (Autostart switch OFF)–Same as P&W

AUTOSTART Switch

ON – arms the autostart system.

OFF – • autostart system is disabled

• start is manually controlled

Selected igniters operate when any of the

following occur:

• during start when N2 RPM less than 50%

• trailing edge flaps out of up position

• nacelle anti-ice ON

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Engines, APU Engine Fuel System Schematic

N400SA N469AC

PW-

The first stage engine fuel pump adds

additional pressure to the fuel.

GE-

The first and second stage engine fuel pumps

add additional pressure to the fuel.

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Engines, APU Engine Oil system

N400SA N469AC

GE -

The oil is cooled by fuel as it flows

through the fuel/oil heat exchanger.

P&W

The oil is cooled first by fan air as it flows

through the air/oil heat exchanger

and then by fuel as it flows through the

fuel/oil heat exchanger.

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Engines, APU Thrust Reverser System

PW-

Each engine has a hydraulically actuated

fan air thrust reverser.

N400SA

GE-

Each engine has a pneumatically actuated fan

air thrust reverser.

N469AC

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Engines, APU APU Operation

APU Start

N400SA

An APU start requires both the main and APU batteries. The APU battery

supplies power to the starter, air inlet door, APU controller, DC fuel pump, and

APU fire detection system. The main battery supplies power for the APU fire

extinguisher, APU fuel valve, and standby power for the APU controller. All

APU components except the starter are powered by the main battery while

the APU starter is engaged during a start sequence. Rotating the APU

selector momentarily to START begins the start sequence. The APU fuel

valve and inlet door open simultaneously. Starter engagement occurs

when the inlet door is fully open. The start sequence continues with ignition,

lightoff, and engine acceleration to rated speed.

APU Start limitations are not the same for P&W and GE Engines.

continue 12/22/2011

Between starts Battery wait:

1 and 2 1 minute

2 and 3 5 minutes

3 and 4 1 minute

4 and 5 20 minutes

5 and 6 1 minute

For additional starts, wait 20 minutes then

alternate between one and 20 minutes for

further starts.

Engines, APU APU Operation Cont.

APU Start

N469AC

The APU DC electric starter is powered by an APU start transformer rectifier (TR) whenever

galley bus 2 is powered. Galley bus 2 may be powered from either an external or internal AC

power source through the synchronous bus. If galley bus 2 is not powered, starter power is

supplied by the 24 volt APU battery. The battery has a charger which disconnects during APU

starter engagement. The APU battery powers the inlet door, APU controller, DC fuel pump, and

APU fire detection system. The main battery supplies power for the APU fire extinguisher, APU

fuel valve, and standby power for the APU controller. During a battery start sequence, the APU

starter is powered by the APU battery and all APU components except the starter are powered

by the main battery while the APU starter is engaged. Rotating the APU selector momentarily to

START begins the start sequence. The APU fuel valve and inlet door open simultaneously.

Starter engagement occurs when the inlet door is fully open. The start sequence continues with

ignition, lightoff, and engine acceleration to rated speed.

APU Start limitations are not the same for P&W and GE Engines.

Between starts TR wait: Battery wait:

1 and 2 1 minute 1 minute

2 and 3 10 minutes 5 minutes

3 and 4 20 minutes 1 minute

4 and 5 20 minutes 20 minutes

5 and 6 20 minutes 1 minute

For additional starts with TR power, wait 20 minutes between each start. For additional starts with battery power, wait 20 minutes then alternate between one and 20 minutes for further starts.

Flight Instrument, Displays Instrument Source Select Panels

PVD is only installed on N400SA and is Deactivated

N400SA

Continued

12/22/2011

Flight Instrument, Displays Para-Visual Display

N400SA

1. Para-Visual Display (PVD) - Deactivated

2. PVD Switch - Deactivated

The PVD will be Deactivated

Flight Instruments, Displays Radio Magnetic Indicator

N400SA

Radio magnetic indicator displays heading and VOR and ADF bearing to the selected station. Heading information is provided by the right or center IRU as selected by the F/O IRS source selector. Only installed on N400SA

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Flight Management, Navigation Transponder Panel

N400SA N469AC

Appearance and functionality

12/22/2011

Above/Below switch (N400SA)

Flight Management, Navigation Weather Radar Panel

N400SA

Appearance and functionality –

(N469AC)

* has a left and right “tilt map and gain” knob

* Push button selections for “TFR, WX, WS+T, MAP, and GCS”, “LR/T RR/T”

N469AC

12/22/2011

Flight Management, Navigation Thrust Management

N400SA N469AC

N400SA

Thrust limits are expressed as EPR

limits. Thrust equalization references

EPR.

N469AC Thrust limits are expressed as N1 limits. Thrust equalization references N1.

12/22/2011

Landing Gear Gear Synoptic Display

N469AC N400SA

Disabled System Messages

TILT (amber) - main gear truck not in full tilt positions.

ANTISKID (white or amber) - loss of antiskid protection

to related wheels.

LIMITER (white or amber) - torque limiting control fault

detected.

Warning Systems GPWS and PWS Alerts on PFD

N400SA N469AC

Alert on PFD

PULL UP (red) - PULL UP alert is occurring.

WINDSHEAR (red) -

• predictive WINDSHEAR AHEAD alert or

immediate WINDSHEAR alert is occurring

• all other GPWS alerts inhibited

Alert on PFD

PULL UP (red) – GPWS PULL UP alert is

occurring.

WINDSHEAR (red) –

• WINDSHEAR alert is occurring

• all other GPWS alerts inhibited

Continue 12/22/2011

Warning Systems Predictive Windshear (PWS) Display and Annunciations

N400SA

PWS Symbol

Displayed (red and black) -

• PWS alert is occurring

• displays windshear location and

approximate geometric size (width and

depth) Symbol, radials, and weather radar

returns displayed automatically when:

• PWS alert occurs, and

• WXR is not selected on either ND, and

• respective ND is in MAP, MAP CTR,

VOR, or APP mode

When terrain display is selected and PWS alert

occurs, weather radar display replaces terrain

display.

PWS Radials

Displayed (amber) -

• PWS alert is occurring

• Extend from PWS symbol to help locate windshear

event

WINDSHEAR Annunciation

WINDSHEAR (amber) - PWS caution is occurring.

WINDSHEAR (red) - PWS warning is occurring.

Displayed in all navigation display modes.

Only installed on N400SA

Warning Systems Master WARNING/CAUTION Reset Switches and Lights

Master WARNING/CAUTION Reset Switch

Push –

• extinguishes master WARNING lights

• extinguishes master CAUTION lights

• silences the aural alert that accompany the EICAS warning messages:

• CABIN ALTITUDE

• CONFIG GEAR, if displayed because landing gear not down and

locked, any thrust lever at idle, and radio altitude less than 800 feet

• FIRE

N400SA

• PILOT RESPONSE

• OVERSPEED 12/22/2011

Warning Systems Transponder Mode Selector

N400SA N469AC

TCAS Airspace Switch ABOVE - displays altitude reporting traffic from 2,700 feet below to 9,000 feet above current altitude. Normal (NORM) - displays altitude reporting traffic from 2,700 feet below to 2,700 feet above current altitude. BELOW - displays altitude reporting traffic 9,000 feet below to 2,700 feet above current altitude.

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Warning Systems Radio Altitude/Barometric Altitude Control

N400SA N469SA

The airplanes listed in the table below

are covered in this manual. The numbers

distinguish data peculiar to one or more,

but not all of the airplanes. Where data

applies to all airplanes listed, no

reference is made to individual airplane

numbers.

Altitude Voice Annunciations During

Approach

GPWS provides the following altitude voice

annunciations during approach:

• 2,500 feet - TWENTY-FIVE HUNDRED

• 1,000 feet - ONE THOUSAND N469AC

• 500 feet - FIVE HUNDRED

• 100 feet - ONE HUNDRED

• 50 feet - FIFTY

• 40 feet - FORTY N400SA

• 30 feet - THIRTY

• 20 feet - TWENTY N400SA

• 10 feet - TEN

• 5 feet - FIVE N469AC

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N469AC GPWS provides the voice annunciations PLUS HUNDRED at 100 feet above the altitude set by the Captain’s RADIO/BARO Altitude control on the EFIS control panel, and MINIMUMS at the altitude set.

N400SA Minimums Voice Annunciation GPWS provides the voice annunciation MINIMUMS at the altitude set by the captain RADIO/BARO Altitude control on the EFIS control panel.

QUICK REFERENCE HANDBOOK Differences

12/22/2011

Preface Airplane Effectivities

Effectivities will be displayed below associated checklist title

When airplane effectivities are stated immediately below a checklist title, the

entire checklist applies to the listed airplanes only. In the following example,

the ENG 1, 2, 3, 4 FAIL checklist is applicable to N400SA only:

DOOR F/D OVHD..................................................1.6

N400SA

12/22/2011

ALL QRH DIFFERENCES ARE

HIGHLIGHTED IN YELLOW

DOOR F/D OVHD..........................................................................1.6

N400SA

Condition: The flight deck overhead door is not closed

and secure.

12/22/2011

>ELT ON............................................................................................1.15 N400SA

Condition: The emergency locator transmitter is on.

12/22/2011

BLD 1, 2, 3, 4 OVHT/PRV.................... 2.6

N400SA

BLD 1, 2, 3, 4 OVHT/PRV................ 2.7

N469AC

Condition:

One or more of these occur:

•An engine bleed air overheat

•A PRV is failed closed Objective: To turn the engine bleed switch off

while at a high power setting.

Condition: One or more of these occur:

•An engine bleed air overheat

•A PRV is failed closed

>ANTI-ICE................................ 3.1

N400SA

>ANTI-ICE............................. 3.1

N469AC

Condition: All of these occur:

•A nacelle or wing anti-ice system is on

•TAT above 12°C

•Ice is not detected

Condition: All of these occur:

•A nacelle or wing anti-ice system is on

•TAT above 12°C

12/22/2011

>ANTI-ICE NAC...................................................... 3.1

N469AC

Condition: All of these occur: •A nacelle anti-ice system is on •TAT above 12°C •Ice is not detected

12/22/2011

>ANTI-ICE WING...................................... 3.1

N469AC

Condition: All of these occur:

•A wing anti-ice system is on

•TAT above 12°C

•Ice is not detected

12/22/2011

HEAT P/S CAPT, F/O............................. 3.3

N400SA HEAT P/S CAPT, F/O............................. 3.4

N469AC

Condition:

A pitot static probe heat is failed.

Objective:

To isolate the failed probe to prevent

erroneous flight instrument indications.

Condition:

A pitot static probe heat is failed.

HEAT P/S L, R AUX......................... 3.5

N400SA

HEAT P/S L, R AUX............................ 3.6

N469AC

Condition:

A pitot static probe heat is failed.

Objective:

To isolate the failed probe to prevent

erroneous flight instrument indications.

Condition:

A pitot static probe heat is failed.

12/22/2011

>ICING.................................................... 3.7

N400SA

Condition: Ice detector detects ice. 1 Message can be cancelled but cannot be recalled.

12/22/2011

>ICE DETECTORS...................................... 3.7

N469AC

Condition: The ice detectors are failed.

12/22/2011

>ICING NAC............................................. 3.7

N469AC

Condition: Ice is detected and a nacelle anti-ice

system is off.

12/22/2011

>ICING WING........................................... 3.7

N469AC

Condition: Ice is detected and the wing anti-ice

system is off.

12/22/2011

>NO ICING............................................... 3.8

N400SA

Condition: Ice no longer detected. 1 Message can be cancelled but cannot be recalled. If ice detected, message no longer shown.

12/22/2011

>RADIO TRANSMIT................................... 5.1

N469AC

Condition: A VHF or HF radio transmits for 30 seconds or more.

12/22/2011

RADIO TRANSMIT...................................... 5.2

N469AC

1 Transmitter select switches

(all audio select panels)............... Flight Interphone

This deselects the radios and stops radio transmissions.

2 The microphone or interphone with the stuck switch continuously

transmits on flight interphone.

3 The associated audio select panel should stay on flight interphone. All

other audio select panels may be used normally.

Condition: A radio transmits continuously without crew input. Objective: To identify and isolate the stuck microphone.

12/22/2011

Radio Transmit Continuous (Stuck

Microphone Switch)................................... 5.3

N400SA

Condition: A radio transmits continuously without crew input.

Objective: To identify and isolate the stuck microphone.

1 Transmitter select switches

(all audio select panels)............... Flight Interphone

This deselects the radios and stops radio transmissions.

2 The microphone or interphone with the stuck

switch continuously transmits on flight interphone.

3 The associated audio select panel should stay on flight

interphone. All other audio select panels may be used

normally.

12/22/2011

ELEC AC BUS 1, 2, 3, 4....................... 6.2

N400SA

ELEC AC BUS 1, 2, 3, 4.............................. 6.6

N469AC

12/22/2011

>STBY BUS APU.......................................6.12

N469AC

Condition: The APU standby bus is not powered.

12/22/2011

>STBY BUS MAIN.....................................6.12

N469AC

Condition: The main standby bus is not powered.

12/22/2011

>STBY POWER OFF...................................6.12

N400SA

Condition: The standby bus is not powered.

12/22/2011

Aborted Engine Start.............................. 7.1

N400SA

Aborted Engine Start.............................. 7.2

N469AC

3 When N2 decreases below 20%:

AUTOSTART switch................................... Off

This allows engine motoring.

Engine START switch (affected engine)....... Pull

Motor the engine for 30 seconds.

Engine START switch (affected engine)......Push

3 When N2 decreases below 20%:

Engine START switch

(affected engine).................................... Pull

Motor the engine for 30 seconds.

Engine START switch

(affected engine)...................................Push

12/22/2011

ENG 1, 2, 3, 4 AUTOSTART...................... 7.3

N469AC

12/22/2011

ENG 1, 2, 3, 4 FAIL (multiple) or Multiple

Engine Flameout or Stall…................. 7.4

N400SA

ENG 1, 2, 3, 4 FAIL (multiple) or Multiple

Engine Flameout or Stall................... 7.6

N469AC

12/22/2011

Engine Limit or Surge or Stall................. 7.8

N400SA

Engine Limit or Surge or Stall............... 7.10

N469AC

12/22/2011

>AUTOSTART OFF....................................7.14

N469AC

Condition: The engine autostart switch is off.

12/22/2011

>EEC 1, 2, 3, 4 TEST PWR.........................7.15

N400SA

Condition: EEC maintenance power switch in TEST.

12/22/2011

ENG 1, 2, 3, 4 EEC MODE..........................7.15

N400SA

ENG 1, 2, 3, 4 EEC MODE..........................7.16

N469AC

Condition: An EEC is in the alternate control

mode.

Objective: To place all the EECs in alternate.

1 Do these steps on all operating engines, one

engine at a time:

Thrust lever..................Retard to mid position

ELEC ENG CONTROL switch................. ALTN

2 Maximum thrust limiting is not available.

3 Autothrottle is not available.

Condition: An EEC is in the alternate control

mode.

Objective: To place all the EECs in alternate.

1 Do these steps on all operating engines, one

engine at a time:

Thrust lever..................Retard to mid position

ELEC ENG CONTROL switch................. ALTN

2 Maximum thrust limiting is not available.

3 Autothrottle is available.

ENG 1, 2, 3, 4 FAIL................................7.17

N400SA

ENG 1, 2, 3, 4 FAIL...................................7.20

N469AC

12/22/2011

>ENG 1, 2, 3, 4 LIM PROT......................7.24

N400SA

>ENG 1, 2, 3, 4 LIM PROT.........................7.25

N469AC

Condition: The EEC is in the alternate control

mode and thrust is approaching

maximum rating.

Condition: The EEC is in the alternate mode

and command N1 is more than the

limit.

12/22/2011

ENG 1, 2, 3, 4 OIL FILT.............................7.25

N400SA

ENG 1, 2, 3, 4 OIL FILT.............................7.26

N469AC

Condition: Oil filter contamination can cause

oil to bypass the oil filter.

1 Primary engine oil filter approaching bypass

condition. Oil flow to the engine will be

filtered through the secondary filter element.

Condition: Oil filter contamination can cause oil

to bypass the oil filter.

12/22/2011

ENG 1, 2, 3, 4 OIL TEMP............................7.28

N400SA

ENG 1, 2, 3, 4 OIL TEMP............................7.29

N469AC

12/22/2011

>ENG 1, 2, 3, 4 RPM LIM.......................7.30

N400SA

>ENG 1, 2, 3, 4 RPM LIM...........................7.30

N469AC

Condition: The N2 red line limit restricts the

engine’s thrust.

Condition: The N1 or N2 red line limit

restricts the engine’s thrust.

Engine In-flight Start................................7.32

N400SA

Engine In-flight Start................................7.34

N469AC

12/22/2011

STARTER CUTOUT 1, 2, 3, 4.......................7.38

N400SA

STARTER CUTOUT 1, 2, 3, 4.......................7.39

N469AC

12/22/2011

Volcanic Ash............................................7.42

N400SA

Volcanic Ash............................................7.45

N469AC

12/22/2011

Fire Engine Tailpipe................................ 8.4

N400SA

Fire Engine Tailpipe................................ 8.6

N469AC

12/22/2011

IAS DISAGREE or Airspeed Unreliable 10.1

N400SA

IAS DISAGREE or Airspeed Unreliable 10.5

N469AC

12/22/2011

ALT DISAGREE.........................................10.9

N400SA

ALT DISAGREE.......................................10.11

N469AC

Entire Procedure differs from

N469AC. Consult QRH

Entire Procedure differs from

N400SA. Consult QRH

12/22/2011

>FMC RUNWAY DIS..................................11.4

N400SA

Condition: Airplane is not on the FMC origin

runway when takeoff is attempted.

GEAR DOOR...........................................14.15

N400SA

GEAR DOOR...........................................14.16

N469AC

12/22/2011

>PILOT RESPONSE...................................15.3

N400SA

Condition: Pilot action is not detected during a specified time.