Dash 1 Flashcards
- If it appears that a boost pump has failed and flight below 25,000 feet is impractical: (T.O. 1T-
38C-1)
A. flight can be continued above 25,000 feet at reduced power settings.
B. crossfeed may be used to ensure boost pump pressure if a reduced power setting is
impractical.
C. flight at lowest practical altitude and reduced power minimizes probability of fuel flow
interruptions.
->D. All of the above
- With dual engine failure, the battery switch is not required to be ON to provide ignition if
windmilling rpm is available. (T.O. 1T-38C-1)
True
->False
- If you suspect engine damage during a compressor stall, you should: (T.O. 1T-38C-1)
->A. advance the throttle above idle only if required.
B. never advance the throttle above idle.
C. advance the throttle cautiously above 80% to determine the maximum usable engine
speed.
1
- A compressor stall may be recovered prior to complete flameout by: (T.O. 1T-38C-1)
A. selecting MAX power.
B. rapidly retarding the throttle to idle.
C. pressing the affected engine’s start button.
D. A and C
->E. B and C
- When a fire light is preceded or accompanied by a pop, bang or thump, it usually indicates a
serious engine malfunction and (or) fire. Consideration should be given to: (T.O. 1T-38C-1)
A. increasing airspeed.
->B. shutting down the engine.
C. ejecting.
D. retarding the throttle to idle and checking the fire sensors.
- If the engine cannot be shut down with the throttle, the _____ switch (affected engine) should be
closed. (T.O. 1T-38C-1)
A. boost pump
->B. fuel shutoff
C. crossfeed
D. generator
- With boost pumps inoperative, engine flameout may occur if above 25,000 feet. (T.O. 1T-38C-1)
->True
False
- Vibrations accompanied by fumes and/or odors from the air conditioning system may indicate air
conditioner turbine failure. You should: (T.O. 1T-38C-1
A. select oxygen - 100% B. descend below FL250 C. select RAM DUMP ->D. all of the above E. B and C
- After losing a canopy, the minimum drag airspeed is approximately _____ KIAS. (T.O. 1T-38C-1)
A. 200
->B. 225
C. 250
D. 275
- Simultaneous failure of the engine RPM and oil pump (oil pressure zero) may be an indication of:
(T.O. 1T-38C-1
A. Airframe mounted gearbox failure.
B. Left generator failure without crossover.
C. Right generator failure without crossover.
->D. Oil pump shaft shear.
- If the operating engine requires shutdown, the previously shutdown engine for an oil system
malfunction may be restarted. (T.O. 1T-38C-1)
->True
False
- Under controlled flight, do not delay ejection below _____ feet in futile attempts to start the
engines or for other reasons that may commit you to an unsafe ejection. (T.O. 1T-38C-1)
A. 1,000
->B. 2,000
C. 5,000
D. 15,000
- If the yaw damper switch is found OFF during flight: (T.O. 1T-38C-1)
->A. attempt to reset it to YAW one time.
B. the mission must be terminated.
C. do not attempt to reengage the yaw damper switch.
D. check the stability augmenter circuit breaker in, reengage the yaw damper switch, and
continue the mission
- Simultaneous illumination of the generator and hydraulic caution lights for the same engine may
indicate a gearbox failure. This can be confirmed by checking the appropriate _____ indicator.
(T.O. 1T-38C-1)
A. oil pressure
->B. hydraulic pressure
C. nozzle
- Hydraulic pressure provided solely by a windmilling engine will allow control of the aircraft for
landing. (T.O. 1T-38C-1)
True
->False
- If utility hydraulic pressure is depleted: (T.O. 1T-38C-1)
A. land with all gear up.
->B. stop straight ahead and have the gear pins installed prior to clearing the runway.
C. the flight control hydraulic system backs up all the utility driven systems.
D. the flaps will not extend
- With dual hydraulic system failure: (T.O. 1T-38C-1)
->A. eject. B. hydraulic pressure provided solely by a windmilling engine is sufficient to control the aircraft for C. land as soon as conditions permit. D. B and C
- Touchdowns as high as _____ KCAS are possible. (T.O. 1T-38C-1)
A. 180
->B. 200
C. 220
D. 240
- If takeoff is made with flab-slab interconnect system failure (non-locking): (T.O. 1T-38C-1)
A. a lighter than normal stick force will be required for rotation.
B. a reduced amount of stick travel will be required for rotation.
C. until the flaps are retracted, significant forward stick pressure will be required to keep the
pitch from increasing.
->D. all of the above
- During an abrupt pitch-up due to interconnect system failure (nonlocking), the pilot must take
corrective action within _____ second(s) to ensure recovery without loss of altitude. (T.O. 1T-
A. 1
B. 2
->C. 3
D. 4
- During single-engine landing, at high density altitude or high gross weights, selecting full flaps in
the flare, an immediate touchdown and premature landing may occur. (T.O. 1T-38C-1)
->True
False
- If you have your nose gear up and one main gear extended, this is a landable configuration. (T.O
True
->False
- After landing with all gear up, the speedbrake may grind down beyond the actuator attach point
and cause the nose to suddenly . (T.O. 1T-38C-1)
A. pitch up
B. yaw
->C. drop
D. collapse
- Vibrations accompanied by fumes and/or odors from the air-conditioning system may indicate
failure of the: (T.O. 1T-38C-1)
->A. air conditioner turbine
B. right/left airframe mounted gearbox
C. right/left generator
D. right/left oil pump shaft
- Normal load capacity of the WSSP is approximately _____ pounds. (T.O. 1T-38C-1)
A. 130
->B. 140
C. 150
D. 160
- An overstress failure of the main landing gear sidebrace trunnion may occur if the gear is: (T.O.
1T-38C-1
A. extended with greater than 30 degrees of bank.
B. extended/retracted with greater than 45 degrees of bank.
C. extended at greater than 1.5 Gs.
->D. B or C.
- The nosewheel tire is rated to knots groundspeed. (T.O. 1T-38C-1)
->A. 174
B. 195
C. 204
D. SETOS + 10
- Spins may be intentionally entered when flying dual with a qualified T-38 spin pilot. (T.O. 1T-38C-
True
->False
- Total fluctuations in EGT of _____ degrees are acceptable if the average EGT is between _____
and _____ degrees C. (T.O. 1T-38C-1)
A. 10 (+/-5), 620, 645
B. 10 (+/-5), 630, 650
C. 15 (+/-7.5), 630, 645
->D. 15 (+/-7.5), 630, 650
- Nozzle position at MIL is _____ %. (T.O. 1T-38C-1)
->A. 0 - 20
B. 20 - 55
C. 50 - 85
D. 50 - 100
- Following rapid throttle movements, nozzles should stabilize within _____ seconds. (T.O. 1T-
38C-1)
A. 2
B. 5
->C. 10
D. 15
- Aircraft fuel flow limits in MIL power on the ground are _____ pph at sea level. (T.O. 1T-38C-1)
A. 2100-2500
B. 400-600
->C. 2100-2700
D. 360 (MAX)
- If full aileron deflection in the direction of the spin is not maintained, spin recovery may be
prolonged or prevented. (T.O. 1T-38C-1)
->True
False
