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command study > 15 - Powerplant > Flashcards

15 - Powerplant Flashcards

1
Q
  1. (DSC-70-80) On ground the start sequence is automatically aborted :
    (a) There is no automatic abort sequence.
    (b) Only in the case of hot start or hung start.
    (c) Only in the case of no light up.
    (d) In case of hot start, hung start, stall or no light up.
A

(d) In case of hot start, hung start, stall or no light up.

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2
Q
  1. (DSC-70-80) During an automatic start on ground, the sequence is :
    (a) Ignition by N2>16%, HP fuel valve opening by 22%, start valve closure by N2>50%.
    (b) Ignition and HP fuel valve opening by N2>16 % - Start valve closure by N2>50%.
    (c) Ignition and HP fuel valve opening by N2 22%, Start valve closure by N2>50%
    (d) Ignition by N2>16%, - HP fuel valve opening by N2>22%, - Start valve closure by setting mode selector to norm.
A

(a) Ignition by N2>16%, HP fuel valve opening by 22%, start valve closure by N2>50%.

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3
Q
  1. (DSC-70-70) Thrust reversers are actuated by :
    (a) Hydraulic actuators ; Green for engine one - Yellow for engine two.
    (b) Hydraulic actuator ; Green for both engines.
    (c) Hydraulic actuators ; Blue for engine 1, Yellow for engine 2.
    (d) Pneumatic actuators.
A

(a) Hydraulic actuators ; Green for engine one - Yellow for engine two.

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4
Q
  1. (DSC-70-20) The FADEC is electrically supplied by ;
    (a) Aircraft electrical system only.
    (b) Batteries if A/C electrical power fails.
    (c) Self powered above 15% N2.
    (d) Aircraft electrical system or self powered in an emergency.
A

(c) Self powered above 15% N2.

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5
Q
  1. (DSC-70-30) In manual mode, when the thrust levers are between the climb detent and idle :
    (a) Each position of the levers correspond to an N1.
    (b) N1 is climb N1.
    (c) N1 is idle N1.
    (d) N1 is frozen.
A

(a) Each position of the levers correspond to an N1.

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6
Q
  1. (LIM-70) What is the EGT limit at TOGA power setting.
    (a) 850 deg.c
    (b) 725 deg.c.
    (c) 950 deg.c.
    (d) 915 deg.c.
A

(c) 950 deg.c.

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7
Q
  1. (LIM-70) What is the maximum continuous oil temperature ;
    (a) 150 deg.c.
    (b) 140 deg.c.
    (c) 155 deg.c.
    (d) 105 deg.c.
A

(b) 140 deg.c.

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8
Q
  1. (LIM-70) The max continuous oil temp limit may be exceeded, What is the limit and under what conditions ;
    (a) 155 deg.c for less than 15 mins.
    (b) 155 deg.c for 20 mins.
    (c) The max continuous oil temp must not be exceeded.
    (d) 195 deg.c for 20 mins.
A

(a) 155 deg.c for less than 15 mins.

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9
Q
  1. (LIM-70) What is the minimum starting oil temperature ;
    (a) -40 deg.c.
    (b) -10 deg.c.
    (c) 0 deg.c.
    (d) -56 deg.c.
A

(a) -40 deg.c.

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10
Q
  1. (PRO-NOR-SOP-04) What is the minimum oil quantity for dispatch ;
    (a) 5 quarts + estimated consumption (0.5 Qts/hr).
    (b) 9.5 quarts + estimated consumption (0.5 Qts/hr).
    (c) 16 Quarts from Irish stations or or 14 Quarts from outstations
    (d) 10 quarts.
A

(c) 16 Quarts from Irish stations or or 14 Quarts from outstations

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11
Q
  1. (LIM-70) What is the minimum oil pressure at ground idle :
    (a) 13 psi.
    (b) 10 psi.
    (c) Variable with oil temperature.
    (d) 11 psi.
A

(a) 13 psi.

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12
Q
  1. (LIM-70) What is the maximum N1 :
    (a) 105 %
    (b) 104 %
    (c) 100 %
    (d) 120 %
A

(b) 104 %

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13
Q
  1. (LIM-70) What is the maximum N2 :
    (a) 105 %
    (b) 102 %
    (c) 100 %
    (d) 120 %
A

(a) 105 %

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14
Q
  1. (LIM-70) What is the maximum N2 for starter engagement :
    (a) 0 %
    (b) 25 %
    (c) 20%
    (d) 50 %
A

(c) 20%

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15
Q
  1. (LIM-70) What is the maximum starter operating time ;
    (a) 8 min followed by 15 min of no operation.
    (b) 5 min followed by 20 sec of no operation.
    (c) 2 min followed by 20 sec of no operation.
    (d) 1 min followed by 20 sec of no operation.
A

(c) 2 min followed by 20 sec of no operation.

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16
Q
  1. (LIM-70) Starter cooling time requirements are ;
    (a) 15 min cooling time after 4 cycles of 2 min.
    (b) 5 min cooling time after 4 cycles of 2 min.
    (c) 2 min cooling time after 4 cycles of 8 min.
    (d) 5 min cooling time after 2 cycles of 1 min.
A

(a) 15 min cooling time after 4 cycles of 2 min.

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17
Q
  1. (LIM-70) The MAXIMUM Reverse Thrust may be used down to ;
    (a) A/C Stop according to EGT limit.
    (b) 70 kts. ( idle reverse down to A/C stop)
    (c) 40 kts. ( idle reverse down to A/C stop)
    (d) 20 kts.
A

(b) 70 kts. ( idle reverse down to A/C stop)

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18
Q
  1. (PER-TOF-TOC-14) What is the (A321) maximum allowable flex temperature ;
    (a) ISA + 29c
    (b) ISA + 15c
    (c) ISA + 43c
    (d) ISA + 13c
A

(c) ISA + 43c

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19
Q
  1. (PER-TOF-TOC-14) Reduced thrust is not permitted :
    (a) If outside air temp is lower than corrected temp.
    (b) On a contaminated runway or with one or more reverser inop.
    (c) If outside air temp is higher than T Ref (ISA +15).
    (d) If outside air temp is less than 15 c.
A

(b) On a contaminated runway or with one or more reverser inop.

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20
Q
  1. (PER-THR) In manual thrust, in cruise, the pilot should limit the N1, What is this limit;
    (a) Displayed max climb N1, minus 2.4 %
    (b) Displayed max climb N1
    (c) Displayed MCT N1
    (d) Idle N1 + 24%.
A

(a) Displayed max climb N1, minus 2.4 %

21
Q
  1. (PER-THR) Is the maximum cruise N1 displayed on the upper ECAM ;
    (a) No.
    (b) Yes.
    (c) Sometimes.
    (d) Always.
A

(a) No.

22
Q
  1. (PER-TOF-TOC-14) At Toulouse (500 ft) ; TREF is 29c, outside air temp is 36c, and you found a corrected Flex TEMP of 33c, is it possible to use flex thrust for
    take off ;

(a) Yes, flex temp of 33c is OK.
(b) No, flex temp 33c is not allowed because it is less than OAT.
(c) Yes, because flex temp 33c is greater than TREF.
(d) Yes, because OAT is greater than TREF.

A

(b) No, flex temp 33c is not allowed because it is less than OAT.

23
Q
  1. (DSC-70-90) EGT indication becomes red on E/W display when EGT is higher than :
    (a) 855 deg.c
    (b) 950 deg.c.
    (c) 910 deg.c.
    (d) 700 deg.c.
A

(b) 950 deg.c.

24
Q
  1. (DSC-70-20) What is the FADEC ;
    (a) An engine control box.
    (b) A thrust control unit.
    (c) A digital control system that performs complete engine management consisting of the electronic control unit and its peripheral sensors and components.
    (d) A bleed control computer.
A

(c) A digital control system that performs complete engine management consisting of the electronic control unit and its peripheral sensors and components.

25
Q
  1. (DSC-70-20) The FADEC system is ;
    (a) Always powered by A/C electrical circuit.
    (b) Always self powered.
    (c) Self powered above 15 % N2 with A/C power when N2 is below 15 %.
    (d) Powered by the RAT.
A

(c) Self powered above 15 % N2 with A/C power when N2 is below 15 %.

26
Q
  1. (DSC-70-80) What device provides direct closure of the HP Shut Off Valve ;
    (a) The master switch at off position.
    (b) The ECU.
    (c) The HMU.
    (d) The eng. Man Start push button.
A

(a) The master switch at off position

27
Q
  1. (DSC-70-40) Which valve ensures an adequate fuel flow ;
    (a) The HP fuel SOV.
    (b) The BSV (burner staging valve)
    (c) The fuel metering valve of the HMU.
    (d) The start valve.
A

(c) The fuel metering valve of the HMU.

28
Q
  1. (DSC-70-40 + PRO-ABN-70) Is the engine still supplied in case of fuel filter clog;
    (a) Yes, by using the fuel coming from the idg cooling tank line.
    (b) Yes, by by-passing the fuel filter (by-pass valve).
    (c) No, the engine stops.
    (d) No fuel will be supplied to the engines if the filter is clogged.
A

(b) Yes, by by-passing the fuel filter (by-pass valve).

29
Q
  1. (DSC-70-80) Cranking may be manually selected by setting;
    (a) The mode selector to crank and the master switch to on.
    (b) With master switch to off the mode selector to crank and the man start PB to on.
    (c) With the master switch to on the mode selector to crank and the man start PB to on.
    (d) By selecting the mode selector to crank.
A

(b) With master switch to off the mode selector to crank and the man start PB to on.

30
Q
  1. (DSC-70-80) During an automatic starting sequence, the pack valves close when ;
    (a) The master switch is selected to on and ignition start is selected.
    (b) Ign start is selected
    (c) Packs are on and ign start is selected.
    (d) The master switch is selected to on.
A

(c) Packs are on and ign start is selected.

31
Q
  1. (DSC-70-80) During an automatic starting sequence;
    (a) Start valve closes at N2 > 43%
    (b) Start valve closes at N2 > 45%
    (c) Start valve closes at N2 > 50 %
    (d) Start valve closes at N2 > 22%
A

(c) Start valve closes at N2 > 50 %

32
Q
  1. (LIM-70) Maximum EGT during engine start is ;
    (a) 855 c.
    (b) 890 c.
    (c) 725 c.
    (d) 950 c.
A

(c) 725 c.

33
Q
  1. (DSC-70-80) The FADEC automatically selects continuous ignition in the following cases ;
    (a) Wing ant-ice on or engine flame out.
    (b) In flight restart or engine failure or EIU failure.
    (c) In flight automatic restart or engine flame out or EIU failure or engine ant-ice on.
    (d) Only when wing ant-ice is on.
A

(c) In flight automatic restart or engine flame out or EIU failure or engine ant-ice on.

34
Q
  1. (DSC-70-50) How is the oil cooled ;
    (a) By the engine fuel /oil heat exchanger and the servo fuel heater.
    (b) By oil recirculation.
    (c) By the air / oil heat exchanger.
    (d) By the precooler.
A

(a) By the engine fuel /oil heat exchanger and the servo fuel heater.

35
Q
  1. (DSC-70-90) The oil pressure indicator becomes red when pressure is lower than
    (a) 16 psi.
    (b) 200 psi.
    (c) 13 psi.
    (d) 85 psi.
A

(c) 13 psi.

36
Q
  1. (DSC-70-30) In autothrust mode the thrust computed by the fmgc is limited ;
    (a) To the value corresponding to the thrust lever position(unless the alphafloor mode is activated)
    (b) By the mode engaged on the FCU.
    (c) By the FMGC itself.
    (d) To the TOGA detent.
A

(a) To the value corresponding to the thrust lever position(unless the alphafloor mode is activated)

37
Q
  1. (DSC-70-70) The thrust reverser activation conditions are ;
    (a) Aircraft on the ground and thrust lever between reverse idle detent and max reverse.
    (b) Spoilers armed and thrust levers on the reverse sector.
    (c) Thrust levers in full reverse sector.
    (d) Aircraft in flight and thrust levers on the reverse sector.
A

(a) Aircraft on the ground and thrust lever between reverse idle detent and max reverse.

38
Q
  1. (DSC-70-90) REV green appears on the N1 indicator when ;
    (a) The thrust levers are selected to full reverse sector.
    (b) The reverse doors are fully deployed.
    (c) The thrust lever position is in the idle reverse sector.
    (d) Any one reverse door is deployed.
A

(b) The reverse doors are fully deployed.

39
Q
  1. (DSC-70-70) Reverse deployment requires TLA. signal from the SECs, one reverse will be lost if;
    (a) SEC 2 fails.
    (b) SEC 3 fails.
    (c) SECs 1+2 fail or SECs 1+3 fail.
    (d) SEC 1 fails.
A

(c) SECs 1+2 fail or SECs 1+3 fail.

40
Q
  1. (DSC-70-10) The low pressure rotor (N1) consists of ;
    (a) A front fan - 2 stage booster - 5 stage Lp turbine.
    (b) A front fan - 4 stage booster - 4 stage Lp turbine.
    (c) A front fan - 3 stage booster - 3 stage Lp turbine.
    (d) A front fan - 5 stage booster - 5 stage Lp turbine.
A

(b) A front fan - 4 stage booster - 4 stage Lp turbine.

41
Q
  1. (DSC-22-30) A/thr can be engaged ;
    (a) Manually on ground (eng running), automatically after take-off.
    (b) In flight, manually or automatically if there is an alpha floor detection.
    (c) Automatically when the pilot initiates a take off or a go-around or if there is an alpha floor detection after take off and down to 100 ft radio on landing.
    (d) In flight, only if it has been armed on the ground first.
A

(c) Automatically when the pilot initiates a take off or a go-around or if there is an alpha floor detection after take off and down to 100 ft radio on landing.

42
Q
  1. (DSC-22-30) In flight, if the instinctive disconnect pushbutton is pressed for more than 15 secs, the A/thr including alpha floor is:
    (a) Lost
    (b) Available.
    (c) Armed
    (d) Active
A

(a) Lost

43
Q
  1. (DSC-22-30) At takeoff as soon as the power is set (flex or toga) ;
    (a) A/THR function is engaged provided A/THR PB on FCU is pressed in.
    (b) A/THR function is active.
    (c) A/THR function is armed but not active
    (d) A/THR function is not engaged.
A

(c) A/THR function is armed but not active

44
Q
  1. (DSC-70-30) After a flex take off, you have an engine failure and you want to select MCT ;
    (a) You have the thrust lever in flex; MCT selection is automatic.
    (b) You set the thrust levers out of the flex/MCT detent then back to flex/MCT position.
    (c) You must disconnect the ATHR
    (d) You must disconnect the ATHR and the A/P
A

(b) You set the thrust levers out of the flex/MCT detent then back to flex/MCT position.

45
Q
  1. (DSC-26-20) Pressing the engine fire Pb switch on the eng. fire panel causes the closure of ;
    (a) Fuel Lp valve.
    (b) Fuel Lp valve and Hp valve (due to LP valve closure)
    (c) Fuel Hp valve.
    (d) Only the hydraulic isolation valve.
A

(a) Fuel Lp valve.

46
Q
  1. (DSC-22-30) ASYM amber message (FMA) means ;
    (a) One thrust lever is set out of climb detent (both engines running).
    (b) Asymmetric power is established due to fadec malfunction.
    (c) Asymmetric power is established due to TLA resolver fault.
    (d) One engine has failed.
A

(a) One thrust lever is set out of climb detent (both engines running).

47
Q
  1. (DSC-70-30) LVR MCT flashing white message ( in the left part of theFMA) means ;
    (a) Thrust Levers are not in MCT position after engine failure in flight.
    (b) Thrust Levers are not in MCT position after engine failure when speed is greater than green dot.
    (c) MCT should not be set for this phase of flight.
    (d) MCT is not available.
A

(b) Thrust Levers are not in MCT position after engine failure when speed is greater than green dot.

48
Q
  1. (DSC-70-30) LVR CLB flashes white on the FMA if the throttles are not in the climb position when ;
    (a) The a/c is above the altitude of thrust reduction.
    (b) The a/c is at lift off.
    (c) The landing gear is retracted.
    (d) The a/c is below the altitude of thrust reduction.
A

(a) The a/c is above the altitude of thrust reduction.

49
Q
  1. (DSC-70-30) The thrust rating limit is computed by ;
    (a) The fmgc according to the AP/FD mode.
    (b) The FADEC (ECU) according to the thrust lever position.
    (c) The ECU according to the AP/FD mode.
    (d) The FMGC according to the ECU order.
A

(b) The FADEC (ECU) according to the thrust lever position.

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