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104 Cards in this Set

  • Front
  • Back
What do you lose when INS fails?
INS 1 powers the Capt's side, INS 2 the FO's. So loss of an INS loses the respective side's:

•Associated AP/FD computer

•DME display on associated HSI

•GS Display on associated HSI

Note: HSI-1 and HSI-2 can display INS-3 information with the use of the transfer switch.

(AOM 216-31)
Other than the HSI and ADI, what other systems get their attitude data information from the INS?
•Upper/Lower Rudder TURN COORDINATOR

•RADAR stabilization


•AP/FD computers

(AOM 216-31)
CADC-1* supples AP/FD computer A with what information?
•Calibrated airspeed

•True airspeed


(Note: CADC-2 supplies the same information to AP/FD computer B and C.)

(AOM 204-4)
On a normal ILS, what does it mean if you have a TCH of less than 42 feet?
The glide slope (localizer, if offset) should be abandoned at no less than 200 feet above ground level and visual cues used for the remainder of the approach with extra care exercised to cross the threshold with a gear height of a least 20 feet.

(AOM 201-24)
What will cause the Autopilot to disengage?
•Pressing Autopilot Disengage switch on yoke

•Using MANUAL STAB TRIM switches

•Major loss of information to associated AP
What causes Takeoff Warning horn?
Thrust lever 3 advanced beyond takeoff warning horn range,
Thrust lever 1 to T.O. HORN decal range,


•LE FLAPS not extended
•TE FLAPS not at 10º or 20º
•SPEED BRAKE not in DOWN detent
•BODY GEAR STEERING not centered
•PARKING BRAKE not released

(AOM 219-3)
Name 4 functions of the PYLON BLEED AIR VALVE
•Shutoff valve

•Pressure regulator to 45psi

•Temperature regulator

•Reverse flow check valve

(AOM 217-4)
What does the G/S Antenna light mean?
•Associated glideslope antenna did not transfer from radome to nose gear doors.

•Could reduce threshold clearance by approx 8 feet.

(AOM 216-14)
Do TAT and Pitot HEAT work while on the ground?
TAT heat= NO

Pitot heat= YES

(AOM 214-11)
What does pressing the "MAX IND RESET" button accomplish?
Use to reset maximum indications pointer on N1 and N2 tachometers and EGT indicators.

(AOM 218-5)
What do the amber lights on the EGT gauges mean?
Amber light illuminates to indicate the EGT has REACHED or is APPROACHING a critical OVERTEMP condition.

(AOM 218-5)
You just lost Hydraulic System 4. What won't work?

•SPOILERS 5,6,7,8

•Outboard TE Flaps

•Right outboard elevator

(AOM 213-7)
What is INS Battery Paralleling?
•Increases battery life of INS 1 by connecting INS 3 battery

(Note: STBY POWER must be ON for paralleling to work)

•Disconnects INS 3 from electrical power; cannot be reconnected in flight.

(AOM 216-37)
What valves open/close in SMOKE mode?

What valves close in DITCH mode?

On ground, blowers continue to run; in flight, flighdeck blower shuts down.


(AOM 203-11)
What causes an APU to auto-shutdown?
The ETC automatically shuts down the APU if

•the air inlet screen ices over,
•an APU fire is detected,
•the fuselage portion of the APU duct ruptures.
•oil pressure is low,
•oil temperature is high,
•EGT, RPM, or TT2 sensor fails,
•EGT is excessive (730 ° steady state, or 90° over schedule during acceleration),
•RPM exceeds 110%,
•cooling fan air valve not open.

(AOM 205-5)


•Battery switch to "OFF" (AOM 207-16)
When the APU master switch is positioned to STOP:
•The fuel valve is closed,

•The AC and DC fuel pumps are disarmed,

•A simulated 110% over speed signal is sent to the ETC to test the auto-shutdown circuit and shut down the APU.

•The amber FAULT light illuminates.

•The APU door begins to close at 50%.

•When the door is fully closed, the FAULT light goes out.

(AOM 205-5)
What happens when you pull the APU FIRE HANDLE?
•APU shuts down

•DISCHARGE switch is armed

•Wheel well warning horn silenced

•Main fuel valve and APU doors close

•BOTH DC and AC pumps turned off

•All circuits locked out to prevent APU restart.

(AOM 209-7)
What happens when you pull the ENGINE FIRE HANDLE?
•Arms the bottle

•Closes FUEL SHUTOFF valve



•Trips the GENERATOR FIELD and GB in 10 seconds

•Closes BLEED AIR valve

(AOM 209-6)
What does an illuminated STANDBY POWER ON light mean?
The green STANDBY POWER ON light, when illuminated, indicates that the STATIC INVERTER is working.

(AOM 207-17)
STANDBY POWER powers what instruments?


•IGNITION, Standby
•N1 indicators
•EGT indicators
•STBY ATTITUDE indicator
•# 1 COM/NAV systems
The "MACH A/S WARN TEST" checks good when the switch is pushed up to "NORM", but silent when pressed down to "RES FUEL". Why?
The "RES FUEL" (as installed) switch will ONLY issue an aural warning if there is fuel in reserve tanks 2 & 3.

(AOM 211-9)
When illuminated, what does the "ESS BUSS OFF" light indicate?
When illuminated, indicates the Essential AC Bus is not powered.

(AOM 207-15)
GE CF6-50

Takeoff Thrust rating
51,805 pounds

•sea level
•temps up to 86ºF

(AOM 218-3)
What does the "GND IDLE" light mean?

What is a consideration for landing?
•Except for the approach and landing phase, with flaps at 25º or 30º, Ground Idle is used for all regimes of flight, including taxi.

•Once flaps 25º or 30º are selected, engines shift to HIGH IDLE to facilitate QUICKER RESPONSE for a GO-AROUND, then maintained for 5 seconds after touchdown, illuminating "GND IDLE" light.

•LIGHT ON IN FLIGHT means engines have not shifted; engines will have LONGER ENGINE SPOOL TIME.

•Must maintain 55% N1 on ALL ENGINES to assure sufficient response in event of a go-around.

(AOM 218-3)
(QRH 107.8-26)
INS Battery time?

What is the difference between the CDU and the MSU light?
•INS has a battery time of 15 minutes. Horn sounds on the ground after 30 seconds.

•CDU BAT LIGHT comes on when INS is opersting on battery power.


(AOM 216-29, 32, 34)
Where does Essential Power come from?
•Essential AC bus, normally powered from AC Bus 4

•Can also be powered directly from generators 3,2 & 1

(AOM 207-9)
Hydraulic power is required for what systems?
•All flight controls, including stabilizer trim.

•Trailing edge flaps

•Landing gear and brakes.

•Nose and body gear steering.

(AOM 213-3)
What does the Reserve Brake Open light indicate?
A RESERVE BRAKE switch on the captain's instrument panel, when placed to OPEN, permits the No. 2 hydraulic system to pressurize the reserve brake system.

(AOM 215-6)
Describe your level of happiness since Norwalk Declined.

•Steady, constant increase in euphoria and satisfaction.
The HYDRAULIC QUANTITY LOW lights illuminate at what quantities?
1.5 to 2.5 gallons

(AOM 101-12)
What temperature does the ZONE OVERHEAT light come on?

What happens next?
Comes on if temperature in ANY zone distribution duct exceeds 185ºF (85ºC).

When in AUTO, excessive temperature will:

•illuminate OVERHEAT LIGHT
•lock out affected zone

(AOM 203-5)
What will cause a Pack to trip?
•COMP DISC over 218ºC (425ºF)

•ACM OUTLET over 85ºC (185ºF)


(AOM 203-5)
What causes a pressurization autofail?
•Autofails when cabin rate of change exceeds 2000 fpm descent or 3100 fpm climb.

•Rate limit system and light deactivated above 10,000 foot cabin altitude.

(AOM 203-21)
What do the PRESS RELIEF lights indicate?
•Cabin pressure exceeded 9.25 psi (lower) or 9.75 psi (upper) and pneumatic relief valve is open.

•Upper light for upper valve, lower light for lower valve.

(AOM 203-21)
What protection does pressurization AUTOCONTROLLER provide?
•Maintains 8.9 psi maximum

•Closes both outflow valves if cabin altitude exceeds 10,500 to 13,000 feet

•A rate limit system, in AUTO mode, takes control of both outflow valves whenever the cabin rate of change exceeds approximately 2000 fpm rate of descent or 3100 fpm rate of climb. The rate limit system is deactivated above 10,000 ft cabin altitude.

•On the ground in AUTO mode, commands cabin altitude of 17,000 feet. Outflow valves open to 90%.

(AOM 203-12)
When does the ALTITUDE WARNING HORN sound at?
CABIN ALTITUDES of 10,000 feet or more.

(AOM 203-12)
The OUTFLOW VALVES close automatically at what altitude?
10,500 to 13,000 feet CABIN ALTITUDE.

(AOM 203-12)
What is the electrical source for the outflow valves?
•AC for automatic operation

•DC for manual operation and AUTO RATE limiting

(AOM 203-13)
When does the ADP come on, and how long does it run for?
•The ADP starts automatically if EDP pressure drops below approximately 2600 psi.

•To minimize cycling, the ADP will run 10 to 15 seconds after pressure returns to normal.

(AOM 213-4)
How does the Brake Temperature Monitor work?
•If no wheels switches are depressed, overheat light monitors ALL brakes.

•If any wheels switch is depressed, overheat light ONLY MONITORS WHEELS SELECTED.

(AOM 215-17)
Explain the difference between the "BRAKE OVHT" light on the Pilots panel vs the "OVER HEAT" light on the FE's panel.
Pilots panel-
•illuminates when any wheel is APPROACHING an overheated condition.

FE's panel-
•Illuminates if brake temperatures are high.

(AOM 215-17)
What will cause the Autobrakes to disarm?
The autobrake switch will automatically move to the DISARM position and the AUTO BRAKE light will illuminate if:

•Brake pedal(s) are depressed.

•Airplane on the ground and #1 or #3 thrust levers advanced to TO range.

•Anti-skid system is not ON or fault exists.

•Autobrake system fault or loss of electrical power.

•Landing gear tilt functions not in agreement.

(AOM 215-17)
What are the three deceleration levels for the Autobrakes?
• 4 ft/sec2

• 6 ft/sec2

• 3000 psi is applied to all brakes

(AOM 215-8)
How are the brakes powered if all engines are off?
The ELECTRICALLY OPERATED hydraulic pump in the No. 4 hydraulic system is normally used to provide brake pressure prior to engine starting and while the airplane is being towed.

(AOM 215-6)
What is the normal and what is the backup (reserve) system for the brakes?
•Systems 4 (primary) or 1 (secondary)

•System 2

(AOM 215-15)
What does the LOW SPEED BK REL light mean?
•Illuminates on ground when either PRIM or ALT tilt input to anti-skid system is in the air (tilted) mode.

• Releases all the brakes below 20 kts.

(AOM 215-6)
(AOM 215-16)
Explain the Anti-skid differences between NORMAL (Systems 4 or 1) vs. RESERVE (System 2).
Indicates fuel filter is approaching a bypass condition due to ice or foreign material.

(AOM 212-11)
Where does the fuel temperature indicator get its reading?
•Number 1 main tank

(AOM 212-11)
What does the oil "FILTER BYPASS" light indicate?
•At excessive differential pressure, the FILTER BYPASS light illuminates for the affected engine indicating an IMPENDING oil filter bypass.

(QRH 107.8-17)
What is the weight limitation for fuel transfer from reserve tanks, and why?
•Transfer below 703,000 pounds

•Fuel in reserve tanks minimizes wing flex at high weights.

(AOM 101-5)
What must be done prior to takeoff, if using CWT fuel?
•CWT fuel must be sampled after engine start and prior to takeoff.

•Minimum of 600 pounds (4 minutes at idle thrust) must be used, by the Number 1 & 4 engines.

(AOM 106-56)
What is the rate of the SCAVENGE PUMPS?
Scavenge pumping rate is about 1600 pph.

(AOM 212-5)
Fuel jettison system- how many pumps, what rate, and total jettisoning rate?
•6 pumps

•Approximate 1000 lb/min rate PER PUMP

•Total jettison rate limited to 5000 lb/min

(AOM 212-6)
If you forget to shut off the jettison pumps, will they pump out all of your fuel?
•No. Standpipes in each main tank assures a minimum reserve.

(AOM 212-6)
Which pumps are the Jettison pumps?
A total of six pumps are used:

•OUTBD and INBD jettison pumps in each of the No. 2 and No. 3 main tanks,

•LEFT and RIGHT OVRD/JETT pumps in the center wing tank.

(AOM 212-6)
How does fuel from tanks 1 and 4 get jettisoned?
Fuel in No. 1 and No. 4 main tanks (and their respective reserve tanks) is transferred into No. 2 and No. 3 main tanks by GRAVITY and from there pumped overboard.

(AOM 212-6)
What does the split-system breaker (SSB) do?

Where does it get its input from?
• The SSB allows the sync bus to function as a single bus or two independent buses.

•The Bus Power Control Unit 2 (BPCU 2) controls the operation of the SSB.

(AOM 207-3)
(AOM 207-4)
What does the Bus Power Control Unit(s) do?
The auxiliary power system contains two bus power control units (BPCUs) which:

•prevent connecting external power unless frequency and voltage are within limits

•control the APU generator voltage

•provide automatic fault protection for external power, APU generator power, and the respective side of the sync bus

•BPCU logic prevents different power sources from being put on the sync bus at the same time.

•BCPU 2 controls the operation of the SSB.

(AOM 207-4)
Which fire handle has a delay item, and why?
Engine fire handle:

•The generator field and generator breaker (GB) trip after 10 seconds to allow the engine bleed air valve time to close.

(AOM 209-6)
Are the engines equipped with an "AND" or an "OR" fire detection logic system?

How about the APU?
•"AND" logic, with the switch set to "BOTH"

•BOTH loops "A" AND "B" need to detect a fault for an alarm to sound.

•"OR" logic

•EITHER loops "A" or "B" need to detect a fault for alarm to sound. APU will autoshutdown.

(AOM 209-4)
(AOM 209-7)
Describe the aural warnings for:

•Engine fire
•APU fire
•Wheel well fire
Engine fire:
• Bell in cockpit

APU fire:
•Bell in cockpit
•Horn in wheel well

Wheel well fire:
•No aural warning

(AOM 219-3)
When using STANDBY IGNITION, what happens to the flight instruments?
The use of STANDBY IGNITION renders the COMPASS CARD in the Captians HSI and the FO's RMI inoperative.

(QRH 107.8-3)
Describe the function of the TE "ALT FLAPS" switch, and how it differs from the LE "ALT FLAPS" switch.
TE Flaps switch to ARM:
•actuates a bypass valve in each trailing edge flap hydraulic system

•arms the two directional switches, allowing for electric motor operation

LE flaps switch to ARM:

•arms the directional switches

•pneumatic valves remain open until directional switch placed to UP or DOWN position.

•valves then close, allowing for electric motor operation.

(AOM 210-13)
(AOM 210-15)
Can wing thermal anti-ice (TAI) be used on the ground?

How about with flaps extended?
On ground:

•Except for ground test, the wing TAI system is designed for INFLIGHT USE ONLY.

With flaps extended:

•Do not use wing anti-ice with flaps extended, as the leading edge flaps are too far forward of the heated air to benefit and the forward wing section is susceptible to damage from the heat.

(AOM 214-4)
(AOM 201-49)
How many fire bottles does a GE powered aircraft have? How about a P&W powered aircraft?

•5 bottles- 2 in EACH WING and 1 for APU


•9 bottles- 2 for EACH ENGINE and 1 for APU.

(AOM 209-6)
Is the RAM AIR valve modulated?

When can you use the Ram Air vent?
•The Ram Ir vent is UNMODULATING. It's either OPEN (emergency mode) or CLOSED (normal).


(AOM 203-14)
General dimensions:

225 ft. 2 in.

(AOM 202-3)
General dimensions:

195 ft. 8 in.

(AOM 202-3)
General dimensions:

63 ft. 5 in.

(AOM 202-3)
Minimum pavement width for 180º turn,

•WITH Body Gear Steering

•WITHOUT Body Gear Steering
With BGS: 153'

Without BGS: 170'
Including takeoff roll, the tires should not be subjected to a continuous roll of more than:

(AOM 201-10)
What is the minimum clearance from any forward obstacle before initiating a turn?

The cockpit must have a minimum of 50 FEET clearance from any forward obstacle to prevent wing tip damage during turn.

(AOM 201-9)
What pitch angle will you get a tailstrike?

How about a podstrike?
Tailstrike at 11º

Podstrike at 7º

(Remember 7-11)

(AOM 201-28)
How does the gear drop when using the alternate extension?
•Nose & main gears, once unlocked via electric motor, landing gear weight (GRAVITY) and AIR LOADING will extend each gear to the down and locked position.

•The nose gear also has an available hand crank.

(AOM 215-4)
Body Gear Steering- when does it actuate and how does it react?

What happens if you lose steering pressure?
•Tiller movement of 45 degrees (20 degrees of nose wheel steering) unlocks the body gear steering system.

•The body gear then turns in the OPPOSITE direction to nose wheel movement to a maximum angle of 13 degrees.

•If steering pressure is lost, mechanical locks in the actuators hold the gear straight ahead.

(AOM 215-15)
What hydraulic system powers the nose and body gear steering?
Nose and body gear steering is pressurized from the No. 1 hydraulic system gear extend line.

(AOM 215-15)
The pneumatic system provides compressed air for:
•Engine starting
•Air conditioning pack operation
•Pressurizing fuselage compartments, hydraulic reservoirs, and potable water tanks
•Leading edge flap positioning
•Wing anti-icing
•Aft cargo compartment heat.

(AOM 217-3)
Forward Caution Panel:

ENG OIL PRESS 1 (2,3,4)
Indicates engine oil pressure AT or BELOW 10psi.

(AOM 218-5)
Forward Caution Panel:

HYD SYS PRESS 1 (2,3,4)
System pressure is below limits. BOTH EDP and ADP PRESS lights must be on.

System pressure is normal. Either EDP and/or ADP PRESS lights must be out.

NOTE: HYD SYS PRESS 4 light will be on if system 4 is pressurized by ELECTRIC pump only.

(AOM 213-11)
Forward Caution Panel:

Inhibited on the ground or when landing flaps selected.

With associated nacelle anti-ice switch on, engine(s) N1 is less than;
•50% N1 above 10,000 feel
•45% N1 below 10,000 feet

(AOM 214-12)
Forward Caution Panel:

Turn coordination out of sequence with flap position

(AOM 210-23)
Forward Caution Panel:

Illuminates for EITHER a PRIM or ALT body gear unlocked indication.

Body gear steering unlocked

Body gear steering locked.

(AOM 215-12)
Forward Caution Panel:

indicates that the essential AC bus is NOT POWERED

(AOM 207-15)
Forward Caution Panel:

Functions only when autopilot engaged. Illuminates when:

•Corresponding automatic stabilizer trim unit fails, or

•an out-of-trim condition is sustained for about 12 seconds

(AOM 210-21)
Forward Caution Panel:

•Indicates loss of one of two feel computers.

•Control forces not changed if failure occurs.

(AOM 210-21)
Forward Caution Panel:


•Selected green band range is in disagreement with the existing airplane C.G. and gross weight.

•WILL NOT illuminate Stab Trim Green Band Select Switch is in MID position with flaps 25º or 30º, or when airplane is in flight.

NOTE: The Green Band lights are independent of the takeoff warning horn.

(AOM 210-27)
Forward Caution Panel:

•KIAS exceeds 169 with Flaps 30º


•KIAS exceeds 191-203 with flaps 25º

NOTE: Flaps will retract to position 25º or 20º as long as airspeed remains high.

(AOM 210-25)
Forward Caution Panel:

Monitors the two rudder ratio changers.

Indicates SIGNIFICANT DIFFERENCE between ratio changer inputs to rudders.

Illuminates when RUDDER RATIO TEST switch is pressed.

NOTE: Crosswind limited to 20 knots.

(AOM 201-23)
(QRH 107.10-10)
Forward Caution Panel:

Indicates status of autospoiler system.

System Inoperative

NOTE: Automatic spoiler function is unreliable and speed brake lever should not be placed to ARMED position.

(AOM 210-20)
QRH 107.10-10)
Forward Caution Panel:

Parking brake valve is not fully open. Anti-Skid is inoperative.

(AOM 215-8)
Forward Caution Panel:

Illuminates when any brake is APPROACHING an overheat condition.

(AOM 215-17)
Forward Caution Panel:

Illuminates (flashing) to indicate system is disarmed and autobrake system is inoperative.

Disarmed by:
•Pressing brake pedals
•#1 or #3 thrust lever to TO position
•Anti-skid OFF or FAULT
•Landing Gear Tilt not in agreement

(AOM 215-17)
(AOM 215-17)
Forward Caution Panel:

Illuminated- System ACTIVATED.


(AOM 208-6)
(AOM 208-8)
Forward Caution Panel:

An overhead probe heater's light is on

All overhead probe heaters annunciator lights are out.

(AOM 214-15)
Forward Caution Panel:

Repeats indication of the engine fire detection loop FAULT light on the FE's panel.

(AOM 209-13)
Forward Caution Panel:

Illuminates when pressure in either pneumatic duct is below minimum required to operate leading edge flaps.

(AOM 217-6)
Forward Caution Panel:

G/S - 1(2,3) ANT
Light illuminates when associated glideslope receiver fails to transfer from upper antenna in radome to the lower antenna in nose gear door.

NOTE: reduces threshold clearance by approx 8 feet.

(AOM 216-14)
Forward Caution Panel:

(Some aircraft)
This light illuminates only if the amber LE FLAPS indicator light below the flap gages remains illuminated in excess of 7 to 10 seconds, which is the normal time for extension or retraction of the leading edge flaps.

(AOM 210-16)
The Central Instrument Warning System (CIWS) monitors what instruments?
•Both pilot's ATT lights will flash with a difference of 4º or more exists between two ADI's.

•ADI differences must be corrected to extinguish light.

(AOM 211-25)
What will cause the CIWS "MON" light to illuminate?
•Illuminates when power is lost to CIWS computer.

•INST WARN light will not illuminate.

•CIWS monitoring ability is lost.

(AOM 211-25)

Thrust Rating
53,580 pounds

•Sea level
•Temperatures up to 30ºC

(AOM 220C-236)
What systems are powered by:

External Power/ APU Generator 1?
External Power/ APU Generator 2?
External Power 1:
•Ground Handling Bus- Towing and cargo loading
•Ground Service Bus- servicing capability without powering total electrical system

External Power 2:
•Main Deck cargo loading

NOTE: The MAIN DECK CARGO HANDLING BUS is powered from EXT PWR 2 (or APU GEN 2) only. The LOWER CARGO HANDLING busses are powered from EXT PWR 1 (or APU GEN 1) only.

(AOM 207-9)
(AOM 207-13)
The engine and APU use the same generator. The engine generators are rated at 60kVa, but the APU is rated at 90 kVa. Why?
The APU generator is rated at 90 kVa due to more efficient cooling.

(AOM 207-3)
What electrical bus powers the Anti-Skid system?

(QRH 107.7-4)