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The TFE731-2-2B engine provides 3,500 pounds of thrust at:

  1. Sea level up to 72°F(22°C)

  2. All altitudes and temperatures

  3. Sea level at any temperature

  4. All altitudes up to 72°F(22°C)

LJ30 PTM V2R01 p7-1


A. Sea level up to 72°F(22°C)
The engine LP rotor (N1) consists of:

  1. A four-stage, axial -flow compressor and a single-stage centrifugal compressor

  2. A single-stage fan and a three-stage axial-flow compressor

  3. A single-stage fan, a four-stage, axial-flow compressor, and a three-stage, axial-flow turbine.

  4. A four-stage, axial-flow compressor and a four-stage, axial flow turbine

LJ30 PTM V2R01 p7-2,7-3

C. A single-stage fan, a four-stage, axial-flow compressor, and a three-stage, axial-flow turbine.
During a normal ground start, the ignition light should come on when:

  1. N2 reaches 10%

  2. The START-GEN switch is moved to START

  3. The thrust lever is moved to IDLE

  4. N1 reaches 10%

LJ30 PTM V2r01 p7-18

C. The thrust lever is moved to IDLE
the engine HP spool (N2) consists of a:

  1. Three-stage axial compressor and a four-stage radial turbine

  2. Single-stage centrifugal compressor and a two-stage axial turbine

  3. Two-stage axial compressor and a single-stage axial turbine

  4. Single-stage centrifugal compressor and a single-stage axial turbine

LJ30 PTM V2r01 p7-2,7-3

D. Single-stage centrifugal compressor and a single-stage axial turbine
The engine instruments (N1 N2, and ITT) are powered by:

  1. Self-generating tachometers

  2. The 26 VAC buses

  3. The essential buses

  4. The DC main and essential buses

LJ30 PTM V2r01 p7-18

D. the DC main and essential buses
Electrical power for engine oil pressure indication is provided by the:

  1. Left and right essential buses

  2. Inverters through the 26 VAC bus

  3. Battery charging bus

  4. Pilot's and Co-Pilot's 115 VAC buses

LJ30 PTM V2r01 p7-6

B. Inverters through the 26 VAC bus
The primary engine thrust indicating instrument is the:

  1. Turbine (N2)

  2. ITT

  3. Fan (N1)

  4. Fuel Flow

LJ30 PTM V2r01 p7-19

C. Fan speed (N1)
The maximum ITT during engine start is:
  1. 832°C
  2. 870°C for ten seconds
  3. 795°C
  4. 860°C
The maximum transient ITT during takeoff is:
  1. 860°C for five minutes
  2. 870°C for ten seconds
  3. 880°C for five seconds
  4. 865°C fro five minutes
What is the maximum acceptable engine oil temperature?

  1. 140°C

  2. 70°C

  3. 130°C

  4. 127°C



A. 140°C
During computer-on operation, the surge bleed valve:

  1. Is controlled by the fuel computer

  2. Remains closed

  3. Remains at 1/3 OPEN position

  4. Has no function

LJ30 PTM V2r01 p7-9

A. Is controlled by the fuel comptuer
During computer-on operatinon, what engine overspeed protection is provided?
  1. Only 109% N1 abd 110% N2 ultimate overspeed shutoff
  2. Only 105% N2 mechanical governor
  3. Only 109% N1 ultimate overspeed shutoff
  4. Only 105% N2 mechanical governor and 109% N1/110% N2 ultimate overspeed shutoff
LJ30 PTM V2r01 p7-10

D. Only 105% N2 mechanical governor and 109% N1/110% N2 ultimate overspeed shutoff
Which of the following statements regarding fuel control is true in the event of airplane electrical failure:

  1. Fuel control remains in the NORMAL mode, but overspeed protection is lost.

  2. Fuel control reverts to the MANUAL mode, and ultimate overspeed protection is lost

  3. Fuel control reverts to the MANUAL mode, but 109% N1 overspeed protection is still available if the computer switch is on.

  4. Fuel control remains in the NORMAL mode with no loss of overspeed protection.



B. Fuel control reverts to the MANUAL mode, and ultimate overspeed protection is lost
If the SPR switch is used during engine start, it should be released to OFF when:

  1. ITT begins to rise

  2. ITT reaches 200°C

  3. ITT reaches 300°C to 400°C

  4. Engine idle rpm stabilizes

LJ30 PTM V2r01 p7-11

C. ITT reaches 300°C to 400°C
the ENG SYNCH light indicates:

  1. Engine sync is not turned on or has failed

  2. Engine synch is operating properly.

  3. Engine synch is turned on, and the nose landing gear is locked in the DOWN position

  4. The engines are sychronized.

LJ30 PTM V2r01 p7-19

C. Engine synch is turned on, and the nose landing gear is lockede in the DOWN position.
When performing a fuel control governor check, N2 rpm increases rapidly, The pilot must:

  1. Turn on the fuel computer switch immediately, allow rpm to stabilize at idle, shut down the engine, and have the system checked

  2. Pull the associated fire T-handle, set the fuel computer switch to manual, and restart the engine

  3. Wait until N2 rpm stabilizes at 105%, then turn on the fuel computer switch, and, when N2 drops to idle, shut the engine down

  4. Turn on the fuel computer swithc, and, if the rpm drops to idle, no further action is necessary.



A. Turn on the fuel computer switch immediately, allow rpm to stabilize at idle, shut down the engine, and have the system checked.
The major portion of total thrust at low altitudes is developed by the:

  1. Fan

  2. LP turbine

  3. Core engine

  4. HP turbine

LJ30 PTM V2r01 p7-4

A. Fan
The maximum allowable N1 under all operating conditions is:

  1. 101% to 103% maximum continuous

  2. 105% for one minute

  3. 103% to 105% for five seconds

  4. 101.5% for five minutes



C. 103% to 105% for five seconds
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