Section 3

Question 1

Maximum Decceleration Can Be Obtained by Maximum Braking Below ___kts

Answer 1

130kts

Question 2

Optimum Braking Should Not be Attempted Above ___kts

Answer 2

100kts

Question 3

Any time the aircraft departs a hard surface (taxiway or runway), immediately

Answer 3

Shutdown both engines

Question 4

During heavy gross weight aborts, the nose will lower at approximately

Answer 4

120 Knots

Question 5

Aerodynamic braking is more effective than cautious wheel braking above

Answer 5

100 Knots

Question 6

If the abort was made as a result of an engine fire, place the throttle of the affected engine to OFF once

Answer 6

A/C is under control followed by emergency ground egress

Question 7

Aerodynamic Braking Pitch Attitude

Answer 7

12 NH

Question 8

SETOS Ensures ___fpm Climb Gradient

Answer 8

100fpm

Question 9

SETOS and SETOS +10 KCAS, single-climb performance increases at the rate _____ of for each knot of airspeed above SETOS

Answer 9

8 to 50 fpm

Question 10

SETOS climb should be restricted to only that required to avoid obstacles until the airspeed reaches

Answer 10

200 Knots

Question 11

Fuel consumption with gear, gear/flaps 60 and gear/flaps full in lbs/min and lbs/NM

Answer 11

• Gear: 40lbs/min, 10 lbs/NM
• Gear/Flaps 60: 50lbs/min, 12lbs/NM
• Gear/Flaps Full: 60lbs/min, 15lbs/NM

Question 12

Gear retraction, when initiated between SETOS +10 KCAS and 200 KCAS, may require up to _____ minutes with a left engine failure

Answer 12

1 minute

Question 13

level flight/climb capability is obtained at ____ KCAS with 60% flaps or at ____ KCAS with the flaps up during SETOS

Answer 13

• 200 Knots

- 220 Knots (if high gross weight flap retraction after 220K)

Question 14

Tire Failure Effects Most Pronounced Below ___kts

Answer 14

100kts

Question 15

If Engine is Shutdown in Flight, Wait ___ Seconds Before Attempting a Restart

Answer 15

10 Seconds

Question 16

During SE Operations, Turn Both Boost Pumps On and Crossfeed On When Below ___lbs in Either Fuel System

Answer 16

250lbs

Question 17

Zoom Maneuver Should Be ___ Degrees Nose High

Answer 17

20 Degrees

Question 18

Minimum RPM For Restart During Flight (To Provide Fuel Flow Through PVC Valves)

Answer 18

12-14%

Question 19

Leave Throttle at Idle for ___ Seconds Before Aborting an air restart

Answer 19

30 Seconds

Question 20

If Loss of Canopy May Occur or Has Occur, Slow Below ___kts

Answer 20

300kts

Question 21

Minimum Drag Airspeed

Answer 21

225kts

Question 22

The UTILITY HYDRAULIC or FLIGHT HYDRAULIC caution light will illuminate for either a

Answer 22

fluid overtemperature or a low pressure condition but not a high pressure condition

Question 23

If the right engine is to be shut down, check _____?

Why?

Answer 23

• check right crossover
• If crossover is bad, consider lowering 60% flaps to reduce landing distance and trim the aircraft to final approach airspeed (fuel permitting). If crossover is good, leave generator OFF

Question 24

Hydraulic pressure provided solely by a windmilling engine is _______ to control the aircraft for landing.

Answer 24

insufficient

Question 25

If one system reads zero, hydraulic system transfer may occur. In this case, flight time could be limited to only ____ minutes.

Answer 25

35 minutes

Question 26

The EED fuel flow indicator(s) on the inoperative engine may read as high as ____ PPH.

Answer 26

60 PPH

Question 27

Left Generator No Cross INDICATIONS

Answer 27

-All AOA indexer lights on. -Utility hydraulic gauge freezes. Left oil pressure and left fuel flow EED indications display OFF. -Master Caution with Left Gen light and Left Fuel Px lights -At night, all interior and exterior lights except caution, warning, and indicator lights, flood lights, and utility lights lost.

Question 28

Right Generator No Cross INDICATIONS

Answer 28

* Flight hydraulic gauge freezes, right fuel flow, and both fuel quantity EED indications display OFF. Oil pressure indications freeze. * MASTER CAUTION, RIGHT GENERATOR, RIGHT FUEL PRESS, and ENG ANTI-ICE ON lights illuminate. * At night, when Caution and Warning lights are set to DIM, Caution, Warning, and Indicator lights go to bright.

Question 29

GENERATOR FAILURE - PARTIAL

Answer 29

• Boost pump (LEFT/RIGHT FUEL PRESS light may be on) • Transformer-rectifier (XMFR RECT OUT light on) • Flaps (slow flap actuation) • HUD (two or more phase failures required to affect HUD operations)

Question 30

RIGHT ESSENTIAL 28-VDC BUS FAILURE ELECTRONICS LOST

Answer 30

Loss of TACAN and UHF radio indicates right essential 28-VDC bus failure.

Question 31

LEFT ESSENTIAL 28-VDC BUS FAILURE ELECTRONICS LOST

Answer 31

- loss of VHF radio communications - VOR/ILS is lost and DME limited to the last channel that was tuned. - TACAN range and bearing is operational and steering information is accurate but limited to the last selected EGI destination. - Flap control and speed brake are not operative. - Landing gear operates normally, but position/warning lights function only in dim mode, if dim mode is selected. - Attitude information is limited to a minimum of 9 minutes based on standby attitude indicator inertia.

Question 32

Turning crossfeed on should cause the LEFT/RIGHT FUEL PRESSURE light(s) to go out. If not,

Answer 32

possibly fuel leak

Question 33

If the FIRE light goes out, check the light by positioning the WARNING TEST switch to TEST. If one or both bulbs of the affected FIRE light does not illuminate, it indicates a possible burn-through of one or both fire sensors. Do what?

Answer 33

shutdown engine

Question 34

When a FIRE light is preceded or accompanied by a pop, bang or thump

Answer 34

shutdown engine

Question 35

Simultaneous failure of the engine RPM indications and oil pump (oil pressure indi- cates zero) may be an indication of

Answer 35

sheared oil pump shaft

Question 36

T/F Under single-engine low fuel conditions (approximately 250 pounds in either system) with two operating boost pumps, placing the CROSSFEED ON and both BOOST PUMPS ON will provide the maximum usable fuel.

Answer 36

True

Question 37

Heart of engine restart RPM range`

Answer 37

18-20%

Question 38

T/F If dual engine flameout occurs, the right engine should be attempted first as right engine instruments will operate normally as soon as engine start button is pushed.

Answer 38

True

Question 39

For a compressor stall do what

Answer 39

Rapidly retarding the throttle to IDLE and immediately pushing the engine start button may permit the engine to recover and prevent complete flameout.

Question 40

If interconnect cable failure occurs after flaps are down 60% or more, a sudden pitch-up will occur and the aircraft will stall instantaneously. Full forward stick will be necessary to arrest the rate of pitch-up and the pilot must take corrective action within _____ seconds to ensure recovery without a loss of altitude.

Answer 40

3 seconds

Question 41

The stability augmentor yaw system can fail with a result- ing rudder deflection of _____. This deflection will cause a yaw and resulting moderate rudder roll.

Answer 41

2 degrees

Question 42

If a touchdown speed greater than ____ KCAS is computed, another controllability check at a lower fuel weight should be considered. Touchdowns greater than ___ KCAS should not be attempted

Answer 42

200 KCAS | 200 KCAS

Question 43

After controllability check Maintain at least ___ KCAS above minimum controllable airspeed during descent and landing approach.

Answer 43

20 KCAS

Question 44

After controllability check fly a power-on straight-in approach requiring minimum flare. Plan to touch down at ____knots above either normal touchdown speed or minimum control speed, whichever is higher.

Answer 44

10 Knots

Question 45

First 5 steps of Alternate gear extension

Answer 45

1. Airspeed - 240 KCAS OR LESS 2. FLAPS - AS REQUIRED 3. Gear door switch - OPEN 4. Landing gear lever - LG DN 5. Landing gear alternate release handle - PULL APPROXIMATELY 10 INCHES AND HOLD UNTIL GEAR UNLOCKS; THEN STOW HANDLE

Question 46

Non-landable configurations

Answer 46

- one main down only - only nose down - nose and one main down

Question 47

As a guide, the no flap landing distance is approximately

Answer 47

2X (2500 + fuel weight) + 1000' (touchdown point)