2A656 Vol 3 Ure (2013)
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- 1.(401) The constant speed drive (CSD) that is used to drive a 60/80 kilovolts amperes (kVA) generator has an output of approximately
- A.
4,000 revolutions per minute (rpm).
- B.
6,000 rpm.
- C.
8,000 rpm.
- D.
10,000 rpm.
- 2.(401) In an alternating current (AC) power supply system, which component controls load division during parallel generator operation?Type question here
- A.
Load controller.
- B.
Underspeed switch.
- C.
Constant speed drive.
- D.
Generator control unit.
- 3.(401) The undervoltage activation point for the main generator in a volts alternating current (VAC) power supply system is
- A.
93 [±3] VAC.
- B.
103 [±3] VAC.
- C.
115 [±2] VAC.
- D.
125 [±2] VAC.
- 4.(401) At what volts alternating current (VAC) range does the generator control unit (GCU) in an AC power supply system maintain generator output?
- A.
135 [±3] VAC.
- B.
125 [±3] VAC.
- C.
115 [±2] VAC.
- D.
105 [±2] VAC.
- 5.(401) In an alternating current (AC) power supply system, what component connects the 115/200 volts alternating current (VAC) main generator output to the main power buses?
- A.
Bus tie lockout (BTL).
- B.
Bus tie contactor (BTC).
- C.
Generator control unit (GCU).
- D.
Generator line contactor (GLC).
- 6.(402) Which emergency alternating current (AC) power system component connects the output of the emergency generator to the essential bus?
- A.
Emergency power disconnect relay (EPDR).
- B.
Emergency power interlock relay (EPIR).
- C.
Emergency generator test switch (EGTS).
- D.
Power fail relay (PFR).
- 7.(402) Which emergency alternating current (AC) power system component prevents the emergency generator from dropping off-line when the aircraft lands?
- A.
Emergency power disconnect relay (EPDR).
- B.
Emergency power interlock relay (EPIR).
- C.
Emergency generator test switch (EGTS).
- D.
Power fail relay (PFR).
- 8.(402) What is the minimum volts alternating current (VAC) requirement to energize the emergency power disconnect relay (EPDR)?
- A.
90 VAC from A phase.
- B.
90 VAC from C phase.
- C.
93 VAC from A phase.
- D.
93 VAC from C phase.
- 9.(403) What external power system component disconnects external power from the aircraft?
- A.
Bus protection panel (BPP).
- B.
Auxiliary power unit (APU).
- C.
APU/external power contactor (AEPC).
- D.
APU/external power disconnect contactor (AEDC).
- 10.(403) The auxiliary source selected to power the tie bus in the auxiliary power unit (APU) is determined by the
- A.
Lockout relay (LOR).
- B.
Bus protection panel (BPP).
- C.
APU/external power contactor (AEPC).
- D.
APU external power disconnect contactor (AEDC).
- 11.(403) What relays connect the auxiliary power source to the aircraft buses?
- A.
Bus tie connector (BTC).
- B.
Bus protection panel (BPP).
- C.
APU/external power contactor (AEPC).
- D.
APU/external power disconnect contactor (AEDC).
- 12.(404) During which troubleshooting step do you review the Air Force Technical Order (AFTO) Form 781A?
- A.
Learn normal system operation.
- B.
Define the discrepancy.
- C.
Limit the malfunction.
- D.
Take meter readings.
- 13.(405) The transformer rectifier units in a volts direct current (VDC) power system convert three-phase 115 volts alternating current (VAC) into
- A.
10 to 12 VDC.
- B.
26 to 31 VDC.
- C.
32 to 36 VDC.
- D.
52 to 56 VDC.
- 14.(405) In the direct current (DC) power supply system, the delta-wound secondaries of the internal transformer in the transformer rectifier (TR) unit are used to provide a more stable
- A.
Current input.
- B.
Voltage input.
- C.
Current output.
- D.
Voltage output.
- 15.(405) In the direct current (DC) power supply system, the reverse current relays (RCR) deenergize when the potential at the
- A.
GEN terminal is greater than the indicator terminal.
- B.
GEN terminal is less than the battery terminal.
- C.
GEN terminal is greater than the SW terminal.
- D.
BAT terminal is less than the SW terminal.
- 16.(406) If the normal battery is supplying direct current (DC) to the battery bus and emergency DC bus, your first step in troubleshooting is to
- A.
Define the problem.
- B.
Take meter readings.
- C.
Know system operation.
- D.
Perform an operational check.
- 17.(406) If the normal battery will not charge but the standby battery is OK, then you start taking meter readings at the
- A.
No. 1 transformer rectifier (TR).
- B.
No. 2 TR.
- C.
Standby battery relay.
- D.
Normal battery relay.
- 18.(407) Which flight control system operates the disconnect clutch in the stabilizer trim actuator assembly?
- A.
Manual system.
- B.
Autopilot system.
- C.
Hydraulic system.
- D.
Electric power system.
- 19.(408) The aircraft write-up states that the leading edge of the stabilizer does not move down when either horizontal stabilizer trim control switch is put to the NOSE UP position. Where is the best place to start taking meter readings?
- A.
Check for 28 VDC between pins A and H, B and H, and G and H of the actuator connector plug.
- B.
Check for 115 VAC between pins A and H, B and H, and G and H of the actuator connector plug.
- C.
Check for 28 VDC at the up-limit switch with either of the horizontal stabilizer trim control switches actuated.
- D.
Check for 28 VDC at pin F of the actuator connector plug with either of the horizontal stabilizer trim control switches actuated.
- 20.(409) Which component is used as an emergency means of controlling the aileron trim control circuit?
- A.
Control stick grip trim switch.
- B.
Aileron trim control switch.
- C.
Trim selector switch.
- D.
Auxiliary trim switch.
- 21.(409) When the stick grip trim selector switch is moved to the left, the position of the aircraft left aileron is
- A.
Up (left wing up).
- B.
Up (left wing down).
- C.
Down (right wing up).
- D.
Down (right wing down).
- 22.(410) After you release the stick grip trim selector switch, the trim indicator light
- A.
Extinguishes.
- B.
Remains illuminated.
- C.
Flashes on and off briefly.
- D.
Remains on throughout the full cycle of the ailerons.
- 23.(410) Before operating the aileron trim system, you must supply power to
- A.
Both the electrical and hydraulic systems.
- B.
The electrical system.
- C.
The hydraulic system.
- D.
The bleed air system.
- 24.(410) When you achieve maximum aileron travel, you should see the aileron takeoff trim indicator lights
- A.
Change from red to green.
- B.
Turn on.
- C.
Go out.
- D.
Flash.
- 25.(411) The slotted wing flaps are used on heavy aircraft and
- A.
Extended forward and downward.
- B.
Form a slot between the flap and the wing.
- C.
Increases the chamber or curvature of the wing.
- D.
Lowers the trailing edge to about 40° below its retracted (UP) position.
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