Engine

Question 1

A ‘dry motoring’ starter engagement is limited to:
60
90
45
2 min

Answer 1

90 seconds

Question 2

If an engine failure occurs while the thrust levers are in the TOGA detent:
(A). Thrust will increase on the operative engine to APR power

(B). Thrust will increase proportionately

(C). Thrust will remain at climb power

(D). None of the above

Answer 2

Thrust will increase on the operative engine to APR power

Question 3

Logic within the FADEC alternates between both ignitions ___ and ____on each successive start

Answer 3

A and B

Question 4

The ATS disengages at approximately ____N2 during an engine start.
20
45
50
55

Answer 4

50%

Question 5

After ‘dry motoring’ the engine for 90 seconds, a cooling time of __ must be observed before a start attempt can be made.
1min
5min
30sec
2 min

Answer 5

5 minutes

Question 6

The engine fuel/oil heat exchanger is used to warm the engine fuel and cool the engine oil.
t
f

Answer 6

True

Question 7

The CF34-8C5 is a dual assembly engine comprised of a fan rotor (N1), and a compressor rotor (N2). The N1 rotor is a:
Single stage fan connected through a shaft to a four stage low-pressure turbine.

10 stage axial flow compressor connected through a shaft to a two stage high pressure turbine

10 stage axial flow compressor connected through a shaft to a two stage low pressure turbine

Single stage fan connected through a shaft to a single stage low pressure turbine

Answer 7

Single stage fan connected through a shaft to a four stage low-pressure turbine.

Question 8

Each aircraft engine FADEC (Full Authority Digital Electronic Control) is powered by the aircraft electrical system until N2 reaches:
20
50
55
79

Answer 8

50%

Question 9

What is used to position the actuators for the VG inlet guide vanes and stators?
A). High pressure fuel from the engine’s fuel metering unit

B). Hydraulic fluid from the associated engine driven hydraulic pumps

C). 10th stage high pressure air

D). Manually via throttle linkage

Answer 9

High pressure fuel from the engine’s fuel metering unit

Question 10

There are _______ different N2 idle settings
3
4
5
6

Answer 10

5

Question 11

Approach idle is activated when:
A). Gear is up

B). Gear is down

C). Flap>20

D). Flaps<20

E). Both A and D

F). Both B and C

Answer 11

Gear is down
Flap>20

Question 12

If thrust reversers are not activated after weight on wheels or wheel spin up, FADEC will maintain landing idle for only:
3 sec
5 sec
8 sec
10 sec

Answer 12

5 seconds

Question 13

FADEC will automatically increase the thrust on the operations engine when the other engine fails. This occurs when there is a mismatch of:
A). N2 turbine speed of 15%

B). N2 turbine speed of 25%

C). N1 fan speed of 15%

D). N1 fan speed of 13%

Answer 13

N1 fan speed of 15%

Question 14

If the throttles are in the TOGA detent and an engine is lost, FADEC will automatically increase thrust:

A). To MCT

B). To APR

C). By 15% or MCT whichever is lower

D). By 15% or APR whichever is lower

Answer 14

To APR

Question 15

The note concerning the High Power Schedule Switch indicates that there is no procedure that permits the use of the switch.
t
f

Answer 15

True

Question 16

FADEC can synchronize engine fan or core speed. The right engine is designated as the master and the left the slave.
t
f

Answer 16

False

Question 17

Oil reservoir quantities can be found on the EICAS ______ page.

A). MENU

B). STATUS

C). PRIMARY

D). ECS

Answer 17

MENU

Question 18

If you see magenta indications on the N1 gauges, that means you are looking at:
A). Normal-Rated Takeoff N1 Thrust

B). Go-Around Thrust

C). Climb Thrust

D). Flex Thrust

Answer 18

Flex Thrust

Question 19

Bleed air is extracted from the _____ stage of the engine compressor. Under times of high demand, it is augmented with ______ stage air.
A). 5th/10th

B). 6th/10th

C). 6th/9th

D). 5th/9th

Answer 19

6th/10th

Question 20

Bleed air is used for:
Correct answer:

A). Wing anti ice

B). Tail anti ice

C). Engine cowl anti ice

D). Air conditioning and pressurization

E). Tire inflation

F). The flight attendants to make fizzy first class beverages

G). Cross bleed engine starts

Answer 20

Wing anti ice
Engine cowl anti ice
Air conditioning and pressurization
Cross bleed engine starts

Question 21

When N2 rpm reaches approximately ______, the FADEC removes power from the solenoid, the start valve closes and the air turbine starter disengages.
50
60
40
65

Answer 21

50%

Question 22

For subsequent engine starts, the air turbine starter can be reengaged at any amp up to ______ N2 rpm.
50
55
40
45

Answer 22

45%

Question 23

Ignition A’s power source is the
A). AC ESS BUS

B). ADG BUS

C). AC BUS 1

D). DC ESS BUS

Answer 23

AC ESS BUS

Question 24

Ignition B’s power source is:
A). ESS AC BUS

B). ESS DC BUS

C). ADG BUS

D). BATT BUS

Answer 24

BATT BUS

Question 25

Continuous ignition must be used for the following flight conditions:
Correct answer:

A). Takeoffs and landings on contaminated runways

B). Flight through light or heavier icing

C). Flight through moderate or heavier rain

D). Flight through moderate or heavier turbulence

E). Flight in the vicinity of thunderstorms

Answer 25

Takeoffs and landings on contaminated runways
Flight through moderate or heavier rain
Flight through moderate or heavier turbulence
Flight in the vicinity of thunderstorms

Question 26

The “soft” detents on the throttle quadrant are which power settings?

A). SHUTOFF

B). IDLE

C). CRUISE

D). CLIMB

E). TOGA

F). MAX POWER

Answer 26

CLIMB
TOGO
MAX POWER

Question 27

When N1 vibration level is above a target value, the green digital read out and pointer turn to amber and a FAN VIBE EICAS message is displayed
t
f

Answer 27

False

Question 28

The CF34-8C5 is a dual assembly engine comprised of a fan rotor (N1), and a compressor rotor (N2). The N1 rotor is a:
Single stage fan connected through a shaft to a four stage low-pressure turbine.

10 stage axial flow compressor connected through a shaft to a two stage high pressure turbine

10 stage axial flow compressor connected through a shaft to a two stage low pressure turbine

Single stage fan connected through a shaft to a single stage low pressure turbine

Answer 28

Single stage fan connected through a shaft to a four stage low-pressure turbine.