Sai B742 Upgrade/recurrent Systems Review

Front 1

What do you lose when INS fails?

Back 1

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)

Front 2

Other than the HSI and ADI, what other systems get their attitude data information from the INS?

Back 2

•Upper/Lower Rudder TURN COORDINATOR

•RADAR stabilization

•AUTOTHROTTLE ANTICIPATION

•AP/FD computers


(AOM 216-31)

Front 3

CADC-1* supples AP/FD computer A with what information?

Back 3

•Calibrated airspeed

•True airspeed

•Altitude

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



(AOM 204-4)

Front 4

On a normal ILS, what does it mean if you have a TCH of less than 42 feet?

Back 4

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)

Front 5

What will cause the Autopilot to disengage?

Back 5

•Pressing Autopilot Disengage switch on yoke

•Using MANUAL STAB TRIM switches

•Major loss of information to associated AP

Front 6

What causes Takeoff Warning horn?

Back 6

Thrust lever 3 advanced beyond takeoff warning horn range,
OR
Thrust lever 1 to T.O. HORN decal range,

AND

•STAB TRIM not in GREEN BAND
•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)

Front 7

Name 4 functions of the PYLON BLEED AIR VALVE

Back 7

•Shutoff valve

•Pressure regulator to 45psi

•Temperature regulator

•Reverse flow check valve


(AOM 217-4)

Front 8

What does the G/S Antenna light mean?

Back 8

•Associated glideslope antenna did not transfer from radome to nose gear doors.

•Could reduce threshold clearance by approx 8 feet.


(AOM 216-14)

Front 9

Do TAT and Pitot HEAT work while on the ground?

Back 9

TAT heat= NO

Pitot heat= YES


(AOM 214-11)

Front 10

What does pressing the "MAX IND RESET" button accomplish?

Back 10

Use to reset maximum indications pointer on N1 and N2 tachometers and EGT indicators.


(AOM 218-5)

Front 11

What do the amber lights on the EGT gauges mean?

Back 11

Amber light illuminates to indicate the EGT has REACHED or is APPROACHING a critical OVERTEMP condition.


(AOM 218-5)

Front 12

You just lost Hydraulic System 4. What won't work?

Back 12

•WING GEAR

•SPOILERS 5,6,7,8

•Outboard TE Flaps

•Right outboard elevator


(AOM 213-7)

Front 13

What is INS Battery Paralleling?

Back 13

•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)

Front 14

What valves open/close in SMOKE mode?

What valves close in DITCH mode?

Back 14

SMOKE MODE:
•Closes FORWARD CARGO HEAT VALVE and opens two OVERBOARD VALVES.

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

DITCH MODE:
•Closes FLOW CONTROL VALVE.


(AOM 203-11)

Front 15

What causes an APU to auto-shutdown?

Back 15

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)


also,

•Battery switch to "OFF" (AOM 207-16)

Front 16

Describe the APU SHUTDOWN SEQUENCE

Back 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)

Front 17

What happens when you pull the APU FIRE HANDLE?

Back 17

•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)

Front 18

What happens when you pull the ENGINE FIRE HANDLE?

Back 18

•Arms the bottle

•Closes FUEL SHUTOFF valve

•Closes HYDRAULIC SUPPLY

•Energizes the DEPRESSURIZING SOLENOID on the EDP

•Trips the GENERATOR FIELD and GB in 10 seconds

•Closes BLEED AIR valve


(AOM 209-6)

Front 19

What does an illuminated STANDBY POWER ON light mean?

Back 19

The green STANDBY POWER ON light, when illuminated, indicates that the STATIC INVERTER is working.


(AOM 207-17)

Front 20

STANDBY POWER powers what instruments?

Back 20

HAINES1

Captains:

•HSI
•ADI
•IGNITION, Standby
•N1 indicators
•EGT indicators
•STBY ATTITUDE indicator
•# 1 COM/NAV systems

Front 21

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?

Back 21

The "RES FUEL" (as installed) switch will ONLY issue an aural warning if there is fuel in reserve tanks 2 & 3.


(AOM 211-9)

Front 22

When illuminated, what does the "ESS BUSS OFF" light indicate?

Back 22

When illuminated, indicates the Essential AC Bus is not powered.


(AOM 207-15)

Front 23

GE CF6-50

Takeoff Thrust rating

Back 23

51,805 pounds

•sea level
•temps up to 86ºF


(AOM 218-3)

Front 24

What does the "GND IDLE" light mean?

What is a consideration for landing?

Back 24

•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)

Front 25

INS Battery time?

What is the difference between the CDU and the MSU light?

Back 25

•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.

•MSU BAT LIGHT on indicates INS has AUTOMATICALLY SHUT DOWN.


(AOM 216-29, 32, 34)

Front 26

Where does Essential Power come from?

Back 26

•Essential AC bus, normally powered from AC Bus 4

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


(AOM 207-9)

Front 27

Hydraulic power is required for what systems?

Back 27

•All flight controls, including stabilizer trim.

•Trailing edge flaps

•Landing gear and brakes.

•Nose and body gear steering.


(AOM 213-3)

Front 28

What does the Reserve Brake Open light indicate?

Back 28

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)

Front 29

Describe your level of happiness since Norwalk Declined.

Back 29

•Giddy

•Steady, constant increase in euphoria and satisfaction.

Front 30

The HYDRAULIC QUANTITY LOW lights illuminate at what quantities?

Back 30

1.5 to 2.5 gallons


(AOM 101-12)

Front 31

What temperature does the ZONE OVERHEAT light come on?

What happens next?

Back 31

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

When in AUTO, excessive temperature will:

•close ZONE TRIM AIR VALVE
•illuminate OVERHEAT LIGHT
•lock out affected zone


(AOM 203-5)

Front 32

What will cause a Pack to trip?

Back 32

•COMP DISC over 218ºC (425ºF)

•ACM OUTLET over 85ºC (185ºF)

•System OUT OF SEQUENCE


(AOM 203-5)

Front 33

What causes a pressurization autofail?

Back 33

•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)

Front 34

What do the PRESS RELIEF lights indicate?

Back 34

•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)

Front 35

What protection does pressurization AUTOCONTROLLER provide?

Back 35

•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)

Front 36

When does the ALTITUDE WARNING HORN sound at?

Back 36

CABIN ALTITUDES of 10,000 feet or more.


(AOM 203-12)

Front 37

The OUTFLOW VALVES close automatically at what altitude?

Back 37

10,500 to 13,000 feet CABIN ALTITUDE.


(AOM 203-12)

Front 38

What is the electrical source for the outflow valves?

Back 38

•AC for automatic operation

•DC for manual operation and AUTO RATE limiting


(AOM 203-13)

Front 39

When does the ADP come on, and how long does it run for?

Back 39

•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)

Front 40

How does the Brake Temperature Monitor work?

Back 40

•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)

Front 41

Explain the difference between the "BRAKE OVHT" light on the Pilots panel vs the "OVER HEAT" light on the FE's panel.

Back 41

Pilots panel-
•illuminates when any wheel is APPROACHING an overheated condition.

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


(AOM 215-17)

Front 42

What will cause the Autobrakes to disarm?

Back 42

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)

Front 43

What are the three deceleration levels for the Autobrakes?

Back 43

MIN:
• 4 ft/sec2

MED:
• 6 ft/sec2

MAX:
• 3000 psi is applied to all brakes


(AOM 215-8)

Front 44

How are the brakes powered if all engines are off?

Back 44

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)

Front 45

What is the normal and what is the backup (reserve) system for the brakes?

Back 45

NORMAL:
•Systems 4 (primary) or 1 (secondary)

RESERVE:
•System 2


(AOM 215-15)

Front 46

What does the LOW SPEED BK REL light mean?

Back 46

•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)

Front 47

Explain the Anti-skid differences between NORMAL (Systems 4 or 1) vs. RESERVE (System 2).

Back 47

Indicates fuel filter is approaching a bypass condition due to ice or foreign material.


(AOM 212-11)

Front 48

Where does the fuel temperature indicator get its reading?

Back 48

•Number 1 main tank


(AOM 212-11)

Front 49

What does the oil "FILTER BYPASS" light indicate?

Back 49

•At excessive differential pressure, the FILTER BYPASS light illuminates for the affected engine indicating an IMPENDING oil filter bypass.


(QRH 107.8-17)

Front 50

What is the weight limitation for fuel transfer from reserve tanks, and why?

Back 50

•Transfer below 703,000 pounds

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


(AOM 101-5)

Front 51

What must be done prior to takeoff, if using CWT fuel?

Back 51

•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)

Front 52

What is the rate of the SCAVENGE PUMPS?

Back 52

Scavenge pumping rate is about 1600 pph.


(AOM 212-5)

Front 53

Fuel jettison system- how many pumps, what rate, and total jettisoning rate?

Back 53

•6 pumps

•Approximate 1000 lb/min rate PER PUMP

•Total jettison rate limited to 5000 lb/min


(AOM 212-6)

Front 54

If you forget to shut off the jettison pumps, will they pump out all of your fuel?

Back 54

•No. Standpipes in each main tank assures a minimum reserve.


(AOM 212-6)

Front 55

Which pumps are the Jettison pumps?

Back 55

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)

Front 56

How does fuel from tanks 1 and 4 get jettisoned?

Back 56

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)

Front 57

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

Where does it get its input from?

Back 57

• 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)

Front 58

What does the Bus Power Control Unit(s) do?

Back 58

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)

Front 59

Which fire handle has a delay item, and why?

Back 59

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)

Front 60

Are the engines equipped with an "AND" or an "OR" fire detection logic system?

How about the APU?

Back 60

Engines:
•"AND" logic, with the switch set to "BOTH"

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


APU:
•"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)

Front 61

Describe the aural warnings for:

•Engine fire
•APU fire
•Wheel well fire

Back 61

Engine fire:
• Bell in cockpit

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

Wheel well fire:
•No aural warning


(AOM 219-3)

Front 62

When using STANDBY IGNITION, what happens to the flight instruments?

Back 62

The use of STANDBY IGNITION renders the COMPASS CARD in the Captians HSI and the FO's RMI inoperative.


(QRH 107.8-3)

Front 63

Describe the function of the TE "ALT FLAPS" switch, and how it differs from the LE "ALT FLAPS" switch.

Back 63

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)

Front 64

Can wing thermal anti-ice (TAI) be used on the ground?

How about with flaps extended?

Back 64

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)

Front 65

How many fire bottles does a GE powered aircraft have? How about a P&W powered aircraft?

Back 65

GE:

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


P&W:

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


(AOM 209-6)
(AOM220C-229)

Front 66

Is the RAM AIR valve modulated?

When can you use the Ram Air vent?

Back 66

•The Ram Ir vent is UNMODULATING. It's either OPEN (emergency mode) or CLOSED (normal).

•Use Ram Air in UNPRESSURIZED FLIGHT only.

(AOM 203-14)

Front 67

General dimensions:

LENGTH

Back 67

225 ft. 2 in.


(AOM 202-3)

Front 68

General dimensions:

WINGSPAN

Back 68

195 ft. 8 in.


(AOM 202-3)

Front 69

General dimensions:

HEIGHT

Back 69

63 ft. 5 in.


(AOM 202-3)

Front 70

Minimum pavement width for 180º turn,

•WITH Body Gear Steering

•WITHOUT Body Gear Steering

Back 70

With BGS: 153'

Without BGS: 170'

Front 71

Including takeoff roll, the tires should not be subjected to a continuous roll of more than:

Back 71

35,000'


(AOM 201-10)

Front 72

What is the minimum clearance from any forward obstacle before initiating a turn?

Why?

Back 72

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


(AOM 201-9)

Front 73

What pitch angle will you get a tailstrike?

How about a podstrike?

Back 73

Tailstrike at 11º

Podstrike at 7º

(Remember 7-11)


(AOM 201-28)

Front 74

How does the gear drop when using the alternate extension?

Back 74

•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)

Front 75

Body Gear Steering- when does it actuate and how does it react?

What happens if you lose steering pressure?

Back 75

•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)

Front 76

What hydraulic system powers the nose and body gear steering?

Back 76

Nose and body gear steering is pressurized from the No. 1 hydraulic system gear extend line.


(AOM 215-15)

Front 77

The pneumatic system provides compressed air for:

Back 77

•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)

Front 78

Forward Caution Panel:

ENG OIL PRESS 1 (2,3,4)

Back 78

Indicates engine oil pressure AT or BELOW 10psi.


(AOM 218-5)

Front 79

Forward Caution Panel:

HYD SYS PRESS 1 (2,3,4)

Back 79

On:
System pressure is below limits. BOTH EDP and ADP PRESS lights must be on.

Off:
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)

Front 80

Forward Caution Panel:

LOW N1

Back 80

Inhibited on the ground or when landing flaps selected.

Flashing:
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)

Front 81

Forward Caution Panel:

YAW DAMPER UPPER
YAW DAMPER LOWER

Back 81

Turn coordination out of sequence with flap position


(AOM 210-23)

Front 82

Forward Caution Panel:

GEAR NOT CENTERED

Back 82

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

On:
Body gear steering unlocked

Out:
Body gear steering locked.


(AOM 215-12)

Front 83

Forward Caution Panel:

ESS BUS OFF

Back 83

Illuminated:
indicates that the essential AC bus is NOT POWERED


(AOM 207-15)

Front 84

Forward Caution Panel:

AUTO STAB TRIM A(B)

Back 84

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)

Front 85

Forward Caution Panel:

ELEV FEEL

Back 85

•Indicates loss of one of two feel computers.

•Control forces not changed if failure occurs.


(AOM 210-21)

Front 86

Forward Caution Panel:

STAB TRIM GREEN BAND

Back 86

ILLUMINATED:

•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)

Front 87

Forward Caution Panel:

FLAP LD RELIEF

Back 87

•KIAS exceeds 169 with Flaps 30º

or

•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)

Front 88

Forward Caution Panel:

RUDDER RATIO

Back 88

Monitors the two rudder ratio changers.

On:
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)

Front 89

Forward Caution Panel:

AUTO SPOILERS

Back 89

Indicates status of autospoiler system.

On:
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)

Front 90

Forward Caution Panel:

ANTI SKID

Back 90

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


(AOM 215-8)

Front 91

Forward Caution Panel:

BRAKE OVHT

Back 91

Illuminates when any brake is APPROACHING an overheat condition.


(AOM 215-17)

Front 92

Forward Caution Panel:

AUTO BRAKE

Back 92

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
•Auto-brake FAULT or LOSS OF ELECTRICS
•Landing Gear Tilt not in agreement


(AOM 215-17)
(AOM 215-17)

Front 93

Forward Caution Panel:

OXYGEN

Back 93

Illuminated- System ACTIVATED.

NOTE: Also turns on "NO SMOKING FASTEN SEAT BELTS" sign.


(AOM 208-6)
(AOM 208-8)

Front 94

Forward Caution Panel:

PROBE HEAT

Back 94

On:
An overhead probe heater's light is on

Out:
All overhead probe heaters annunciator lights are out.


(AOM 214-15)

Front 95

Forward Caution Panel:

FIRE DETECTION

Back 95

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


(AOM 209-13)

Front 96

Forward Caution Panel:

DUCT PRESS

Back 96

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


(AOM 217-6)

Front 97

Forward Caution Panel:

G/S - 1(2,3) ANT

Back 97

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)

Front 98

Forward Caution Panel:

LE FLAPS
(Some aircraft)

Back 98

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)

Front 99

The Central Instrument Warning System (CIWS) monitors what instruments?

Back 99

•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)

Front 100

What will cause the CIWS "MON" light to illuminate?

Back 100

•Illuminates when power is lost to CIWS computer.

•INST WARN light will not illuminate.

•CIWS monitoring ability is lost.


(AOM 211-25)

Front 101

JT9D:

Thrust Rating

Back 101

53,580 pounds

•Sea level
•Temperatures up to 30ºC


(AOM 220C-236)

Front 102

What systems are powered by:

External Power/ APU Generator 1?
External Power/ APU Generator 2?

Back 102

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)

Front 103

The engine and APU use the same generator. The engine generators are rated at 60kVa, but the APU is rated at 90 kVa. Why?

Back 103

The APU generator is rated at 90 kVa due to more efficient cooling.


(AOM 207-3)

Front 104

What electrical bus powers the Anti-Skid system?

Back 104

The ESSENTIAL DC bus.


(QRH 107.7-4)