C-12C/D Pilot/WSO Closed Feb 2022 Flashcards
1 A red annunciator will extinguish:
A. when the indicated fault is corrected.
B. when the Master Warning flasher is pressed.
C. when the RESET button is depressed.
D. when the TEST button is depressed.
Reference: T.O. 1C-12A-1 [1-14A]
when the indicated fault is corrected.
2 The red ALT WARN annunciator will illuminate when the cabin altitude exceeds:
A.10,000 feet.
B.11,500 feet.
C.12,500 feet.
D.13,000 feet.
Reference: T.O. 1C-12A-1 [1-15 (F), 1-64, 3-6 (F)]
12,500 feet
3 The yellow #1/#2 NAC LOW annunciators illuminate when:
A. the corresponding engine has 20 minutes (30 minutes for C-12D) fuel remaining at sea level, normal cruise power consumption rate.
B. the corresponding engine nacelle tank has less than 265 pounds of fuel.
C. the primary boost pump fails.
D. the stand-by boost pump is in operation.
Reference: T.O. 1C-12A-1 [1-15 (F)]
the corresponding engine has 20 minutes (30 minutes for C-12D) fuel remaining at sea level, normal cruise power consumption rate.
4 When the #1 propeller is selected to FEATHER during an Engines Running On/Offload (ERO), if the propeller RPM cannot be maintained below 450:
A. on/offload time with the propeller feathered is limited to two minutes.
B. the engine must be shut down during on/offload.
C. an entry will be made in the AFTO 781 noting the length of time in feather.
D. advance power on the #1 engine to 70% N1.
Reference: T.O. 1C-12A-1 [2-36 (C)]
the engine must be shut down during on/offload.
5 Moving the power levers into reverse without the engines running will damage the reversing linkage mechanisms.
A.TRUE
B.FALSE
Reference: T.O. 1C-12A-1 [1-28 (C)]
TRUE
6 Which of the following is a function of the electric standby boost pump?
A.It functions as a backup pump for use in the event of primary boost pump failure.
B.It is used with aviation gas in flights above 20,000 feet.
C.It is used in crossfeed operation.
D.all of the above
Reference: T.O. 1C-12A-1 [1-31]
all of the above
7 The hot battery bus check tests electrical continuity to which fuel system items?
A.firewall valves only
B.standby boost pumps only
C.standby boost pumps and firewall valves
D.firewall valves, standby boost pumps, and crossfeed valve
Reference: T.O. 1C-12A-1 [1-31/32, 2-4 (N)]
standby boost pumps and firewall valves
8 If the #2 NO FUEL XFR annunciator illuminates in flight when there is fuel in the right auxiliary tank, and the pilot places the right AUX transfer switch to override:
A. the #2 NO FUEL XFR annunciator will extinguish if the motive flow valve has opened and no other fault exists.
B. the #2 NO FUEL XFR annunciator should always extinguish within 30 to 60 seconds.
C. the #2 NO FUEL XFR annunciator should extinguish, but illuminate again when the right Aux tank becomes empty.
D. the question is wrong - The #2 NO FUEL XFR annunciator will not illuminate if the RIGHT AUX tank contains fuel.
Reference: T.O. 1C-12A-1 [1-32, 3-7 (F)]
the #2 NO FUEL XFR annunciator will extinguish if the motive flow valve has opened and no other fault exists.
9 Which of the following items are on the Hot Battery Bus?
A. firewall shut-off valves, standby boost pumps, cabin lights, & fire extinguishers (squibs)
B. firewall shut-off valves, standby boost pumps, cabin lights, & fire detectors
C. firewall shut-off valves, standby boost pumps, & emergency lighting system
D. firewall shut-off valves, high pressure pump, cabin lights, & fire extinguishers (squibs)
Reference: T.O. 1C-12A-1 [1-40, 1-42 (F)]
firewall shut-off valves, standby boost pumps, cabin lights, & fire extinguishers (squibs)
10 Illumination of the BATTERY CHARGE annunciator indicates:
A. the battery is charging at an excessive rate.
B. a normal condition after a battery start.
C. that the battery has received a charge of 6 volts for over 7 seconds.
D. b and c above are correct
Reference: T.O. 1C-12A-1 [1-40]
a normal condition after a battery start.
11 The battery switch must be ___ to close the external power relay to allow external power into the aircraft.
A. OFF
B. ON
C. in either the OFF or ON position
D. EXT PWR
Reference: T.O. 1C-12A-1 [1-41, 1-208]
ON
12 The landing gear warning horn will sound under the following conditions:
A. either or both power levers are retarded to a position corresponding to 79-81% N1 with the gear not down and locked.
B. moving the landing gear warning horn test switch on the copilot’s subpanel to the momentary LANDING GEAR WARN TEST position.
C. with flaps set beyond approach and the gear retracted, regardless of the power lever(s) position.
D. all of the above
Reference: T.O. 1C-12A-1 [1-52]
all of the above
13 An alternate static air source is provided for:
A. the pilot’s instruments only.
B. the copilot’s instruments only.
C. both the pilot and copilot’s instruments.
D. ground operation only.
Reference: T.O. 1C-12A-1 [1-53, 3-41]
the pilot’s instruments only.
14 Should an engine fail on takeoff below 117 KIAS accompanied by a failure of the autofeather system, it may be necessary to:
A. add power on the good engine to cause the autofeather system to activate.
B. reduce power on the operating engine to maintain directional control and reduce pitch as required to maintain airspeed.
C. use stall recovery procedures.
D. immediately lower the landing gear and select landing flaps.
Reference: T.O. 1C-12A-1 [3-14 (W)]
reduce power on the operating engine to maintain directional control and reduce pitch as required to maintain airspeed.
15 Moving the pressure switch up to the dump position in flight:
A. shuts off bleed air input and dumps cabin pressure.
B. opens the safety valve, de-energizes the electromagnet holding the ambient air flapper closed, but does not affect bleed air input.
C. should be done before landing.
D. opens the outflow and safety valves to dump cabin pressure.
Reference: T.O. 1C-12A-1 [1-61, 1-64, 1-65]
opens the safety valve, de-energizes the electromagnet holding the ambient air flapper closed, but does not affect bleed air input.
16 Severe yaw may be encountered if an engine fails in flight. If this occurs outside the takeoff phase, the pilot should:
A. place the inoperative engine power lever to IDLE.
B. immediately manually feather the propeller on the inoperative engine.
C. advance both power levers above 90% N1 position to activate an armed autofeather system.
D. either B or C.
Reference: T.O. 1C-12A-1 [3-15(W, N)]
either B or C.
17 When the propeller deice system is operated manually, the prop ammeter reads:
A. 18 - 24 amperes.
B. 14 - 18 amperes.
C. 6 amperes, alternating every 30 seconds
D. 0 amperes.
Reference: T.O. 1C-12A-1 [1-77]
0 amperes.
18 The PED OVERTEMP annunciator indicates temperature within the center pedestal is ____ degrees Celsius or greater. Center pedestal temperatures in excess of____ degrees Celsius may cause failure and irreparable damage to the Flight Management System.
A. 40, 35
B. 50, 51
C. 51, 50
D. +37 ISA, 50
Reference: T.O. 1C-12A-1 [1-84 (C)]
51, 50
19 The V/UHF transceiver provides which of the following features:
A. 8.33 kHz channel spacing in the VHF band.
B. AM or FM modulation in plain mode.
C. simultaneous reception of 121.5 (VHF) or 243.0 (UHF) emergency frequency in addition to the selected frequency.
D. all of the above
Reference: T.O. 1C-12A-1 [1-98A]
all of the above
20 When aircraft pitch angle exceeds______degrees, an unusual attitude display on the PFD appears as red chevrons pointing to the horizon line. Zenith or nadirsymbols appear at the______degree pitch markings.
A. 40, 90
B. 40, 100
C. 35, 90
D. 45, 100
Reference: T.O. 1C-12A-1 [1-118]
40, 90
21 If a bus feeder circuit breaker opens in flight:
A. it is essential and may be reset once.
B. a short is indicated.
C. do not reset in flight.
D. both B and C
Reference: T.O. 1C-12A-1 [3-23]
both B and C
22 Information received from other aircraft enables the TCAS to determine range, relative bearing and relative altitude to the host aircraft. Using this information, TCAS predicts flight paths and:
A. issues visual and aural warnings if aircraft will pass within 500 feet.
B. sends duplicate TA or RA warning to both aircraft and ATC.
C. estimates the separation at the Closest Point of Approach (CPA) to determine if a conflict exists.
D. all of the above
Reference: T.O. 1C-12A-1 [1-144G]
estimates the separation at the Closest Point of Approach (CPA) to determine if a conflict exists.
23 The T2CAS terrain database includes man-made obstacles.
A. True
B. False
Reference: T.O. 1C-12A-1 [1-146A (W)]
False
24 During an approach to an airfield not in the terrain database, in order to avoid continuous terrain warnings, the crew must:
A. select FLAP OVRD on the TAWS Control Panel.
B. select TERR INHIBIT on the TAWS Control Panel.
C. pull the TAWS circuit breaker.
D. pull the LDN GEAR Control circuit breaker.
Reference: T.O. 1C-12A-1 [1-147]
select TERR INHIBIT on the TAWS Control Panel.