Section 3

Front 1

If engine shutdown or failure occurs in flight, consider the use of crossfeed to balance the fuel load, unless fuel system contamination is suspected.
T/F

Back 1

True

Front 2

The base of the emergency escape hatch is 4.5 (1 Nolta) above the ground with the landing gear extended, use caution when using the exit.
T/F

Back 2

True

Front 3

With dual remote tuning unit (RTU) failure, how can VHF guard (121.5) be tuned?

Back 3

Pulling and resetting the VHF circuit breaker

Front 4

NAV auto-tuning is disabled when the RMT TUNE switch is in the DSABL position.
T/F

Back 4

True

Front 5

How will you know if you have an AIR Data Computer (ADC) failure?

Back 5

Boxed ADC on the altitude and MACH/speed indicators
Audible warning "ADC failure"

Front 6

If a tire failure occurs after S1, ___

Back 6

Do not retract the gear and burn down fuel
Do not change the flap configuration

Front 7

Securing an engine after a failure/fire on takeoff should not be accomplished prior to ___

Back 7

400ft AGL (1500 optional)
Clear of obstructions

Front 8

If an engine fire occurs immediately after takeoff when using the ACM OFF procedure, the bleed air selector may be turned to NORM at any time.
T/F

Back 8

False

Front 9

If a spin is entered (how do you recover): ___

Back 9

Simultaneously reduce power to idle, apply full rudder opposite spin direction, forward elevator control and neutral roll control

Front 10

During a windmilling airstart, should the temperature rise indicate a hot start, place the throttle to CUTOFF and windmill the engine for ___ second before attempting another start.

Back 10

30

Front 11

When both generator master switches are placed to EMER and the battery selected OFF, all electrical power except ___ is lost.

Back 11

DC standby power

Front 12

If the AIR COND FAIL annunciator illuminates, the system will switch from normal to emergency pressure mode automatically.
T/F

Back 12

True

Front 13

The emergency descent procedures are intended to be used for a maximum rate descent to quickly escape the high altitude environment.
T/F

Back 13

True

Front 14

Initiate the level-off after an emergency descent only when pressurization is no longer required.
T/F

Back 14

False

Front 15

During a controllability check, the aircraft speed should be decreased to a point where full control deflection is required to maintain controlled flight.
T/F

Back 15

False

Front 16

Do not attempt an actual single engine go-around after selecting flaps to 30.
T/F

Back 16

True

Front 17

To execute a forced landing with no power ___

Back 17

High Key 4000ft AGL over landing area
Low Key 2000ft AGL abeam landing area
Gear should be lowered at high key or delayed if altitude is low to make low key on alt

Front 18

When accomplishing a side window landing, landing distance will increase approximately ___

Back 18

20%

Front 19

If the landing gear cannot be extended, secure all loose equipment and make a normal approach with a 10 flap setting
T/F

Back 19

False

Front 20

Prior to contacting the water during a ditching maneuver, all crew members except the pilot should unstrap in order to provide the quickest escape.
T/F

Back 20

False

Front 21

Electrical loads up to ___ amps are permissible for single generator operation above 32,500ft

Back 21

280

Front 22

If cruising below 32,500ft, single generator operation load capacity is ___ amps.

Back 22

400

Front 23

When both generator master switches are placed to EMER, ___

Back 23

Both the battery feed emergency bus and DC standby bus are powered

Front 24

When both generator master switches and the battery switch are placed in EMER, the engine anti-ice valves will ___

Back 24

Open

Front 25

During a dual generator failure situation, if the generators fail to reset and flight conditions permit, attempt to reset by turning both generator switches OFF, and reset them one at a time.
T/F

Back 25

True

Front 26

Illumination of the AC BUS SHED annunciator is advisory only and indicates a combination inverter/load bus malfunction that will result in the loss of flap position indicator and both oil pressure indicators.
T/F

Back 26

True

Front 27

Which of the following will cause the BATTERY FDR FAIL light on the over(nugget) panel to illuminate?

Back 27

Failure of the emergency bus feeder

Front 28

When the BATT CUT-OFF annunciator is illuminated, it means the battery ___

Back 28

relay is open

Front 29

The following hydraulic powered systems will not be functional when electrical power is lost___

Back 29

Normal landing gear extension
Flaps
Speed brakes
Anti-skid system

Front 30

If one hydraulic pump fails, ___

Back 30

All hydraulic systems will operate normally

Front 31

Flight in visible moisture without pitot heat may result in erratic operation of the airspeed/mach indicator.
T/F

Back 31

True

Front 32

When using the horizontal stabilizer deice backup switch, activate the system every ___

Back 32

2 minutes

Front 33

The AIR COND FAIL annunciator will illuminate when the air conditioning system ___

Back 33

Temp exceeds 400F
Pressure exceeds 53psi

Front 34

Land as soon as possible:

Back 34

An emergency will be declared

Front 35

During a Tailpipe Fire (on the ground), typically, there will be ___ to the aircrew

Back 35

No indication visible

Front 36

During a Tailpipe Fire (on the ground), if the LH/RH ENG FIRE PUSH annunciator illuminates, the fire ___.

Back 36

Has spread beyond the tailpipe. Accomplish the Engine Fire During Ground Operations checklist

Front 37

Emergency braking is accomplished with ___

Back 37

stored nitrogen pressure

Front 38

The emergency brake cylinder provides pressure for ___

Back 38

At leaset 7 applications

Front 39

The parking brake may not be functional when hydraulic pressure is lost.
T/F

Back 39

True

Front 40

___ protection is not available during emergency braking

Back 40

Anti-skid

Front 41

Emergency ground egress
Do not endanger crew and passengers in an attempt to accomplish all items of this checklist. ___

Back 41

Primary consideration should be given to safely evacuating the aircraft

Front 42

If a malfunction occurs with an associated loss of brakes, immediately ___

Back 42

place the anti skid switch to the off position

Front 43

To maximum brake properly, immediately ___

Back 43

depress the toe brakes fully in one smooth continuous application

Front 44

If gear is retracted with a blown tire, possible damage to the wheel well area could occur.
T/F

Back 44

True

Front 45

Passing Vco + ___ retract the flaps. At Vco + ___ set MCT power and continue climb at Vco + ___ to 2200 feet above airfield elevation.

Back 45

10
15
15

Front 46

Single engine best rate of climb speed:

Back 46

170

Front 47

The ACM must remain OFF until ___ or ___ which ever is ___, to assure aircraft performance.

Back 47

2200ft AGL
Clear of obstacles
Higher

Front 48

Securing the engine should not be accomplished prior to reaching ___ and ___.

Back 48

400ft AGL
Clear of obstructions

Front 49

If fuel crossfeed is required, the ___ must be turned ___ to ensure crossfeed capability

Back 49

Boost pump
On

Front 50

If the engine is being shutdown with no mechanical difficulty, ___

Back 50

stabilize ITT at IDLE thrust for 1 minute

Front 51

What is used for all inflight starter assisted air starts? (regardless of the position of the GEN Reset)

Back 51

Battery Power

Front 52

A relight should normally be obtained within ___ seconds after the ___ is positioned to ___ and will be confirmed by fuel flow indication and increase in rpm and ITT

Back 52

10
Throttle
IDLE

Front 53

Windmilling Airstart
In the event of a hot start, ___

Back 53

Windmill engine for 30 seconds before attempting another start

Front 54

Do not reset a popped circuit breaker in the fuel system

Back 54

Do not reset a popped circuit breaker in the fuel system

Front 55

With the EFC off, the throttle ___

Back 55

angle to achieve similar thrust settings will be different

Front 56

If the L OR R F FLTR BYPASS annunciator illuminates:

Back 56

Land as soon as posible
Unfiltered fuel is being supplied to the engine

Front 57

While operating on emergency and/or standby power, what hydraulic powered systems will not be functional?

Back 57

Normal landing gear extension
Flaps
Speed brakes
Anti-skid systems

Front 58

Do not reset popped BUS FDR circuit breakers

Back 58

Do not reset popped BUS FDR circuit breakers

Front 59

BATTERY FDR FAIL

Back 59

Battery feeder protection circuit has lost power

Front 60

BATTERY FDR FAIL + EMER BUS FDR FAIL

Back 60

Emergency bus feeder circuit has failed
Emergency bus is powered by the Left Load bus only

Front 61

BATTERY FDR FAIL + EMER BUS FDR FAIL + BATT CUT OFF

Back 61

Battery Relay is open
Battery cutoff from system

Front 62

Electrical Fire
If it has not or cannot be visibly verified that the fire is extinguished,

Back 62

land as soon as possible

Front 63

The extinguishing agent and its combustion products can produce toxic effects if inhaled.
T/F

Back 63

True

Front 64

When the trim interrupt switch is engaged, all trim systems except the emergency pitch trim are ___

Back 64

interrupted and the autopilot and yaw damper are diesngaged.

Front 65

Can you engage the autopilot with the pitch trim selector switch in EMER?

Back 65

No

Front 66

If aircrew suspects a binding control surface, visually ___

Back 66

ensure that the autopilot switch is disengaged.

Front 67

Observe maximum speed limits appropriate to flap position of the ___. The flap position indicator shows position of ___.

Back 67

most extended flaps
right flap only

Front 68

With speed brakes extened, do not ___

Back 68

extend flaps beyond 10 degrees

Front 69

Controllability Check
The aircraft must never be decreased to the point at which ___

Back 69

full control deflection is required

Front 70

With all occupants breathing oxygen, attempt to keep the cabin at or below ___ft, but in no case allow it to exceed ___ft.

Back 70

18k
25k

Front 71

Prolonged use of emergency pressurization can result in the __

Back 71

melting of aircraft trim panels near the rear bulkhead and potential smoke and fumes in the cockpit

Front 72

If the AIR COND FAIL annunciator illuminates, the system will ___

Back 72

switch from normal to emergency pressure mode automatically

Front 73

Cracking of the thin outer glass ply layer presents ___ but can significantly ___

Back 73

no structural integrity problems
impede vision through the windshield

Front 74

If aircraft structural failure is suspected, limit the ___

Back 74

maximum airspeed to the current airspeed or as appropriate

Front 75

Normally, single-engine landings will be made with flaps set at ___ degrees with an approach speed of ___ KIAS

Back 75

10
Vref+10

Front 76

Side window landing
Landing will increase

Back 76

Approximately 20%

Front 77

After prolonged flight in cold temperaures, followed by rapid descent, ___ when gear down is selected.

Back 77

one or both H PMP PRESS LO annunciators may illuminate momentarily

Front 78

Without hydraulic pressure, the following systems will be inoperative:

Back 78

Flaps, Landing gear normal extension, Anti-skid, Power brakes, and Speed brakes

Front 79

For 0 hydraulic pressure, increase computed 30 flap landing distance by ___ due to ___

Back 79

90%
the increased threshold speed of a flaps up landing

Front 80

Landing with Nose Gear Up and both Main Gear Down

Back 80

Gently fly the nose down to the runway
Do not drop the nose down to the runway
Do not drop the nose abruptly to the landing surface

Front 81

If any ice accumulation is visible on the leading edges, use ___

Back 81

10 flaps for landing

Front 82

Approach airspeed of ___ is required for ice accumulation of approximately 1.5 inches. Accumulation of less than 1.5 inches may allow approach airspeeds slower than ___ if no aerodynamic buffet is observed.

Back 82

Vapp+35
Vapp+35

Front 83

When landing with a flat nose tire, ___

Back 83

Move weight to rear
Hold nose of aircraft off of runway as long as possible

Front 84

AIR COND FAIL

Back 84

Temp >400F
PSI >53

Front 85

BL AIR DCT FAIL

Back 85

PSI 3.5+-0.5
Temp > 350F

Front 86

DEFOG AIR OV HT

Back 86

Defog air Temp >200F

Front 87

CABIN AIR OV HT

Back 87

Cabin area high temp in excess of 235F