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NCR 744 > 7 - Engine, APU > Flashcards

7 - Engine, APU Flashcards

1
Q

APU Selector - ON (4)

A
  • opens APU fuel valve and inlet door
  • arms APU bleed air isolation valve
  • activates DC or AC fuel pump
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2
Q

The APU drives ___ generator(s) capable of supplying the entire electrical load of the airplane for normal ground operations. Electrical power __(is/is not)__ available in flight.

A

2

is NOT

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3
Q

An APU start requires both the ______ and _____

A

main and APU batteries

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4
Q

Rotating the APU selector momentarily to START begins the start sequence. The ____ and _____ open simultaneously. Starter engagement occurs when _______ is fully open. The start sequence continues with ignition, lightoff, and engine acceleration to rated speed

A

fuel valve

inlet door

inlet door

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5
Q

The EICAS memo message ______ is displayed when the APU selector is ON and APU N1 RPM exceeds ____ N1

A

APU RUNNING

95% N1

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6
Q

Rotating the APU selector to OFF begins the shutdown cycle by closing the ______. The APU continues running unloaded for a ______ cooldown period. When the cooldown period finishes, the APU shuts down.

A

APU bleed air valve

60 sec

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7
Q

If the Battery switch is positioned OFF prior to _____, the APU will shut down immediately

A

completion of the cooldown period

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8
Q

A complete shutdown sequence with fire detection capability can be assured by waiting at least _______ after the APU selector is rotated to OFF before placing the battery switch OFF.

If a limit is exceeded or a fire detected, the APU
_____

A

2 mins

shuts down immediately

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9
Q

TO 1

D-TO 2

A

derate one takeoff thrust

derate two assumed temperature derated takeoff thrust

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10
Q

Thrust Reverser Indication:

REV (amber) -

REV (green) -

A

in transit

fully deployed

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11
Q

EGT indication:

  • (white) -
  • (amber) -
  • (red) -
A

normal operating range

continuous limit reached

start or takeoff limit reached

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12
Q

During TO or GA, EGT indication remains white for ______, or for ______ if one engine fails or is shut down, when continuous EGT limit is reached or exceeded

A

5 min

10 min

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13
Q

EGT Red Line: displayed (red) - ______ or _____

A

takeoff EGT limit

multiple engine in-flight start limit

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14
Q

EGT Start Limit Line

displayed (red): ________ until _________

A

with Fuel Control switch in CUTOFF

N2 reaches a predetermined RPM

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15
Q

Secondary Engine Exceedance Cue on Primary EICAS displayed (cyan) - VVVVVV
• ____________
• ____________
• ____________

A
  • secondary engine parameter exceedance is occurring
  • no longer displayed when exceeding parameter returns to normal operating range
  • replaces status cue if displayed
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16
Q

The In-Flight Start Envelope displays on Primary EICAS (magenta) showing _______ when ______

A

airspeed range for an in-flight start at the current flight level or maximum flight level, whichever is lower

the respective Engine Fire switch is in and a Fuel Control switch is in CUTOFF

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17
Q

When the Fuel Control Switch is in CUTOFF, Fuel-on Indicator on Secondary EICAS (magenta) indicates _______

A

minimum N2 RPM to move Fuel Control switch to RUN during engine manual start

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18
Q

Engine Vibration Source with the highest vibration displays on Secondary EICAS:

FAN -
LPT -
N2 -
BB -

A

Fan

Low Pressure Turbine

N2 rotor

broad band (source is unknown and 
average vibration displayed)
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19
Q

Crossbleed (X-BLD) Start Indication on Secondary EICAS indicates crossbleed air is recommended for in-flight start (magenta) if: ______ and _____

A

in-flight start envelope displayed

airspeed lower than required for a windmilling start

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20
Q

Partial secondary engine indications will be displayed when the secondary engine
display is not selected and _______

A

a limit or operating parameter has been reached

an oil quantity differential is exceeded

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21
Q

What happens; FUEL CONTROL Switch RUN

Autostart switch ON) - (2/3

A
  • opens spar fuel valve
  • opens engine fuel valve
  • EEC sequences start valve, fuel metering valve, and igniter operation
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22
Q

What happens; FUEL CONTROL Switches RUN

Autostart switch OFF) - (3

A
  • opens spar and engine fuel valves
  • opens fuel metering valve
  • energizes igniters
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23
Q

What happens; FUEL CONTROL Switches - Cutoff (4)

A
  • closes fuel valves
  • removes igniter power
  • commands respective hydraulic demand pump to operate when Demand Pump selector in AUTO
  • unlocks Engine Fire switch
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24
Q

Engine START Switches (bleed/start valves):

Pull (Autostart switch ON) - (2)

Pull (Autostart switch OFF)- (2)

Releases at ___ N2 RPM - (2)

A

(ON) -
• arms start valve
• opens engine bleed air valve

(OFF)-
• opens start valve
• opens engine bleed air valve

50%
• closes start valve
• closes engine bleed air valve

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25
Q

Engine START Switches release at ______

A

50% N2 RPM

  • start valve closes
  • engine bleed air valve closes
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26
Q

Standby (STBY) IGNITION Selector NORM -

What is the power source?

What is the backup source?

1/2 -

A
  • AC power system supplies power to selected igniters
  • standby power system supplies power continuously to all igniters if AC power system is not powered

1 or 2 - standby power system supplies power continuously to respective igniters

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27
Q

What happens; Continuous (CON) IGNITION Switch - ON (2)

A
  • selected igniters operate continuously

* commands approach idle minimum

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28
Q

AUTO IGNITION Selector - SINGLE, which igniter(s) is used for start?

Ground -

Inflight -

A
  • EEC alternates igniter 1 and igniter 2 after every second ground start
  • EEC selects both igniters for in-flight start or flameout
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29
Q

AUTO IGNITION - Selected igniters operate when any of the following occur: (4)

A
  • during start when N2 RPM less than 50%
  • trailing edge flaps out of up position
  • nacelle anti-ice ON
  • engine flameout
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30
Q

Engine Start Lights : Illuminated -

A

start valve is open

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31
Q

What primary engine indications always display on primary EICAS ?

A

N1 and EGT

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32
Q

EGT indications are inhibited from changing color to amber during takeoff or go-around for ______ after the TO/GA switch is pushed, even though EGT reaches the continuous limit.

The amber color change is inhibited for ______ if one engine fails or is shutdown

A

5 min

10 min

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33
Q

The EGT indicator has a ______ displayed by a red line. The indication changes color to red if EGT reaches the ______

A

takeoff limit

takeoff limit

34
Q

An engine indication changes color back to white when the parameter returns to the normal operating range. The box enclosing the digital indicator remains red as a reminder of the exceedance. The red box color can be selectively canceled to white or recalled to red by _______

A

pushing the cancel or recall switch on the EICAS Display Select panel

35
Q

The oil quantity indication changes color to amber if _____ or if _____

A

low oil quantity is detected

the oil quantity differential is exceeded

36
Q 
N1 Operating Limit Line -
Maximum N1 Line -
Reference N1 -
Target N1 -
Command N1 Indicator -
A 
Red
Amber 
Green - (thrust ref selected by FMC)
Magenta - (commanded by FMC)
White - (commanded by thrust lever position)
37
Q

Secondary engine indications display in partial format if _______ when the secondary engine display is not selected

A

a secondary engine parameter exceeds the normal operating range

38
Q

The EEC has two control modes: ____ and ____

In both modes, the EEC uses _____
as the controlling parameter for setting thrust.

A

normal and alternate

N1 RPM

39
Q

Electrical power for each EEC is provided by ______ mounted on the engine accessory gearbox

A

an alternator

40
Q

What corrections must the pilot make for OAT and pressure in order to maintain constant thrust?

What corrections must the pilot make when using NAI and or WAI?

A

When the engine is stabilized, the EEC keeps thrust constant independent of outside air temperature and pressure.

The EEC adjusts thrust for changes in nacelle and wing anti-ice and airplane pressurization bleed requirements.

41
Q

The EEC continuously computes maximum N1. Maximum thrust is available during ____ phase of flight by moving the Thrust lever to _____

A

any

the full forward position

42
Q

Alternate mode __(does/does not)__ provide thrust limiting at maximum N1. Maximum N1 is reached at a Thrust lever position ______

A

does not

less than full forward

43
Q

Do thrust levers need to be adjusted to maintain desired thrust as environmental conditions and bleed requirements change?

EEC normal mode -

EEC alternate mode -

A

No

Yes

44
Q

Does thrust change when EEC automatically transfers control from normal mode to alternate mode?

Does thrust change when alternate mode is selected
manually?

A

no change

thrust increases

(When thrust is greater than idle, the Thrust lever should be moved aft prior to manually selecting alternate mode so thrust does not exceed maximum
N1)

45
Q

If the EECs are in the alternate mode, advancing the Thrust levers full forward
______

A

provides some overboost and should be considered only during emergency situations when all other actions have been taken and terrain contact is imminent

46
Q

If control for any EEC transfers from normal to alternate, the autothrottle ______

Can autothrottle be activated after all EECs are manually transferred to alternate mode?

A

disconnects

Yes

47
Q

Approach idle is selected in flight when: (3)

A
  • nacelle anti-ice is ON
  • flaps are in landing position
  • Continuous Ignition switch is ON

Approach idle decreases acceleration time for go-around

48
Q

The start limit remains displayed until _____

A

N2 reaches a predetermined RPM (idle)

49
Q

An in-flight start envelope displays (where) when a Fuel Control switch is moved to CUTOFF in flight.

The in-flight start envelope displays (what)
to ensure an in-flight start at the current flight level.

A

on primary EICAS

the airspeed range

50
Q

If the current flight level is greater than the maximum start altitude on the in-flight start envelope, ______ display

X-BLD displays next to _____ if crossbleed air is necessary for start

A

the maximum start altitude and related airspeed range

the N2 indication

51
Q

During Auto Start the EEC opens the start valve and the Start light illuminates. At a predetermined N2, the EEC _____.

\_\_\_ igniter(s) is/are normally selected for ground start, while \_\_\_ igniter(s) is/are selected for 
in-flight start.
A

opens the fuel metering valve and energizes the selected igniter

one

two

52
Q

Starter cutout occurs at ______

A

50% N2

53
Q

During autostart, the EEC monitors _____ and ______ until the engine stabilizes at idle

A

EGT

N2 RPM

54
Q

During ground start, the autostart system monitors engine parameters and aborts
the start for any of the following malfunctions: (3)

A
  • hot start
  • hung start
  • no EGT rise
55
Q

The autostart system does not monitor ______ or _______

A

oil pressure

N1 rotation

56
Q

If the EEC detects no EGT rise, it _______

The engine motors for ______ and then _______

A

cuts off fuel and ignition

30 seconds

applies fuel and ignition to both igniters for another attempt

57
Q

If the EEC detects no EGT rise, it makes ___ attempts before aborting the autostart sequence.

The engine motors for ______ before the start and engine bleed air valves close

A

3

30 sec

58
Q

If there is an EGT rise, but the EEC detects an impending hot start or a hung start before starter cutout, it ______

The EEC makes ___ attempts before aborting the autostart sequence

The engine motors for ____ before the start and engine bleed air valves close

A

cuts off fuel, adjusts the fuel schedule, then reapplies fuel for another attempt

3

30 secs

59
Q

If the EEC detects an impending hot start or a hung start AFTER starter cutout, _______

A

the autostart sequence is aborted immediately

The engine does not motor

60
Q

During IN-FLIGHT flameout and/or start, the EEC ________

The EEC allows the EGT to _______ before cutting off fuel

A

cuts off and then reapplies fuel.

increase past the start limit to the takeoff limit

61
Q

During in-flight flameout and/or start the autostart sequence is not automatically aborted. The EEC continues making start attempts until ________

A

the engine stabilizes at idle or the Fuel Control switch is moved to CUTOFF

62
Q

Auto relight is provided if _______

A

a flameout is detected

A rapid decrease in N2 occurs, or N2 is less than idle RPM. Both igniters are used

63
Q

Manual Start: Pulling the Start switch out (2) ______

When N2 RPM reaches ______, the Fuel Control switch is moved to RUN

A

opens the start and engine bleed air valves

the fuel-on indicator

64
Q

During a manual start what happens when the Fuel Control switch is moved to RUN? (4)

A

the fuel metering, spar and engine fuel valves open and the selected igniter(s) energizes

(one igniter is normally selected for ground start while two igniters are selected for in-flight start)

65
Q

Ignition is selected for each engine when _______, _______, or _______

A

related Start switch is OUT

nacelle anti-ice is on

flameout is detected

66
Q

Ignition is selected for all engines when

_______ or ______

A

trailing edge flaps are out of the up position

Continuous Ignition switch is ON

67
Q

The ______ is the normal power source for ignition

The ______ provides a backup source

A

AC power system

standby power

68
Q

When the Standby Ignition selector is in 1 or 2, the _______ system supplies power continuously to the related igniter regardless of Auto Ignition selector position or EEC selection

A

standby power system

69
Q

Fuel is supplied under pressure from pumps located in the fuel tanks. The ______ add additional pressure to the fuel when _____

A

first and second stage engine fuel pumps

the N2 rotor is turning

70
Q

_______ heats the fuel as it flows through the _______ heat exchanger

A

Engine oil

fuel/oil

71
Q

The oil is cooled by _____ as it flows through the ______

A

fuel

fuel/oil heat exchanger

72
Q

An oil filter removes contaminants. If the

filter becomes saturated with contaminants, _______

A

oil bypasses the filter

73
Q

During cruise, oil quantity displays on EICAS whenever _______

A

oil quantity on one engine differs from any other engine by a predetermined amount

(when this occurs, the lowest oil quantity is shown in magenta)

74
Q

During cruise if there is an increase in oil

quantity during cruise caused by ________ or ________ the EICAS oil partial engine indications display may appear.

A

indicator malfunction

leaking fuel/oil heat exchanger

(however, for this condition the low quantity displays in magenta, even though that oil quantity may
be normal

75
Q

Each thrust reverser is powered by ______ from _____

A

bleed air

the related engine

(only on the ground)

76
Q

What unlocks and extends the reversers aft to the deployed position?

A

bleed air from the related engine

77
Q

Is thrust reverse available when associated Engine Bleed Switch is OFF?

A

Yes

HP bleed valve and PRV open for thrust reverse, unless PRV closed by:
• prior or present bleed air overheat, or
• start valve not closed

78
Q

N 1 lines:

Red -
Amber -
Green -
Magenta -
White -
A 
operating limit
max limit
reference
target (FMC)
thrust lever position
79
Q

EGT lines:

Red -
Amber -
Red -

A

takeoff/multiple engine inflight start
continuous
start limit (fuel control switch in cutoff)

80
Q

At what speed does the A/T engage in HOLD?

When does it return to THR REF?

A

65 kts

400 ft

81
Q

APU Battery supplies power to ____ (5)

MAIN Battery supplies power to ____ (3)

A
  • Starting
  • Controller
  • DC Fuel pump
  • Air inlet door
  • Fire detection
  • Controller back up power
  • Fuel valve
  • Fire extinguishing
82
Q

Maximum altitude for APU Bleed for one pack ____ ?

Maximum altitude for APU usage ____ ?

A

15,000 ft

20,000 ft

NCR 744 (23 decks)

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