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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
12/22/2011
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
12/22/2011
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
12/22/2011
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
12/22/2011
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”
12/22/2011
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.
12/22/2011
12/22/2011
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
12/22/2011
Limitations
12/22/2011
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
12/22/2011
Air Systems
Shoulder Air Selector
1. Rotate – Sets air flow to side window shoulder air outlet
N469AC
12/22/2011
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.
12/22/2011
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.
12/22/2011
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
12/22/2011
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.
12/22/2011
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
12/22/2011
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
12/22/2011
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.
12/22/2011
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
12/22/2011
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
12/22/2011
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.
12/22/2011
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.
12/22/2011
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
12/22/2011
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
12/22/2011
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.
12/22/2011
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
12/22/2011
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.
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>ELT ON............................................................................................1.15 N400SA
Condition: The emergency locator transmitter is on.
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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
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>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
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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.
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>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
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>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
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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
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>PILOT RESPONSE...................................15.3
N400SA
Condition: Pilot action is not detected during a specified time.
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