Engines, APU

If engine oil pressure is in the amber band with takeoff thrust set: DO NOT TAKE OFF. reduce thrust after takeoff to maintain acceptable oil temperature. continuously monitor oil temperature. no action is necessary.

What is the position of the engine BLEED air switches during the shutdown procedure?. High. On. Auto. Off.

What are the indications that the engine starter has disengaged?. the ENGINE START switch rotates to FLT, N1 goes to 17-20%, and N2 RPM stabilizes. The ENGINE START switch returns to OFF (or AUTO with automatic ignition) at 36% N2'. The ENGINE START switch returns to OFF (or AUTO with automatic ignition) approximately 56% N2, and the start valve closes. The fuel LOW PRESSURE lights extinguish at 56% N1'.

The amber DUAL BLEED light is illuminated after engine start. What should the pilot do?. Limit engine thrust to idle and/or place the APU BLEED air switch to OFF. Limit engine thrust to 56% N2 while the light is illuminated. Place the APU BLEED air switch to ON. Pull the engine fire handles.

During normal operations, which hydraulic system powers the thrust reversers?. System B powers both reversers. System A powers both reversers. The Standby System powers both reversers. System A powers engine No.1 reverser and System B powers engine No.2 reverser.

The thrust reverser can be deployed: when either radio altimeter senses less than 10 feet altitude or when the air/ground safety sensor is in the ground mode. during cruise when the thrust lever is at idle. when either radio altimeter senses less than 27 feet altitude. when the air/ground safety sensor is in the air mode.

Which APU annunciator light is not associated with an automatic shutdown of the APU?. OVERSPEED. Fult. Maint. Low oil press.

An APU shutdown in flight occurs: when the MAINT annunciator light illuminates. automatically by moving the battery switch to OFF. only by an exceedance. with a LOW fuel alert in main tank No. 1.

The APU may be used in flight as an electrical and bleed air source simultaneously up to: 17.000. 10.000. 30.000. 25.000.

Electronic engine control abnormal start protection: is provided for EGT start limit exceedances and wet start protection both in flight and on the ground. requires that hydraulic System B must be pressurized prior to start. is provided for EGT start limit exceedances and wet start protection on the ground only. is inoperative; there is no abnormal start protection.

If the upper DU fails. engine indications automatically shift to the lower DU. engine indications automatically shift to either inboard DU. N1 and N2 indications are not displayed; manually select either inboard DU. display of all engine indications are lost.

When the EEC is not powered, the following indications are displayed directly from the engine sensors: oil temperature,pressure,and quantity. fuel flow and oil pressure. oil temperature and engine vibration. N1,N2,oilquantity,andenginevibration.

During a normal start, prior to placing the engine start switch to GRD, the EEC is not being powered: and only digital readouts are visible for engine indications. until the engine accelerates to a speed greater than 15% N2'. and only N1, N2, oil quantity, and engine vibration are available and are displayed directly from the engine sensors. and only oil quantity and engine vibration are available.

The EEC hard alternate mode thrust is: used only for assumed temperature reduction takeoffs and go-arounds. always less than normal mode thrust for the same lever position. not approved for use. always equal to or greater than normal mode thrust for the same lever position. (7.20.5).

The EEC provides redline overspeed protection for: N1 and N2, in both the normal and alternate modes. N1 and N2, in the normal mode only. N2 only, in both the normal and alternate modes. N1 only, in both the normal and alternate modes.

What position must the forward thrust levers be in before reverse thrust can be selected?. Any for ward thrust position. Take off thrust position. Continuous thrust position. Idle thrust position.

The EEC automatically selects approach idle in flight anytime: the flaps are in the landing configuration or engine anti-ice is ON for either engine. the flaps are in the landing configuration and thrust lever angle is above 34 degrees on either engine. the flaps are in the landing configuration or ENGINE START switches are placed to CONT or FLT. the airplane descends below 15,000 feet MSL.

The APU starts and operates up to: 41.000 ft. 17.000 ft. 35.000 ft. 37.000 ft.

Regarding the APU, both Transfer Busses can be powered: in flight only. on the ground only. only by the IDGs; the APU can power only one transfer bus at a time. on the ground or in flight.

The APU supplies bleed air for both air conditioning packs: on the ground only. only in an emergency; the APU should not routinely be used as a bleed air source for both air conditioning packs. in flight only. on the ground and in flight.

APU cooling air: enters through the ram air doors on both sides of the fuselage. enters through the air inlet door on the right side of the fuselage. is supplied by the air conditioning packs. enters through a cooling air inlet above the APU exhaust outlet.

Electrical power to start the APU comes from: AC Transfer Bus 1 or airplane Battery. the DC ground power receptacle. either AC Transfer Bus. GalleybusC&D.

With AC power available, the starter generator uses AC power to start the APU. Without AC power available, the starter generator uses Battery power to start the APU. T. F.

The APU start cycle may take as long as: 60seconds. 120 seconds. 90 seconds. 135 seconds.

The APU electronic control unit provides: automatic shutdown protection for APU fire, Fuel Control Unit failure, and EGT exceedance. manual control of APU speed through the Electronic Fuel Control. manual shutdown protection for overspeed conditions, low oil pressure, and low oil temperature. automatic shutdown protection for underspeed conditions, high oil pressure, and high oil temperature.

If the APU is the only source of electrical power: on the ground, the Main Busses are shed first if an overload condition is sensed. in flight, the galley busses are automatically shed. in flight,the APU attempts to carry the full electrical load. on the ground,the Galley Busses are automatically shed.

If a wet start is detected, the electronic engine control turns off the ignition and shuts of fuel to the engine: 15 seconds after the startlever is moved to IDLE during ground starts. 10 seconds on the ground or 30 seconds in flight after the start lever is moved to IDLE. immediately upon EGT exceedance. 15 seconds after the start valve opens during ground starts.

Regarding the APU, moving the BAT switch to OFF: shuts down the APU after a delay of three minutes. does not affect the APU; it has its own power source. automatically shuts down the APU because of power loss to the electric control unit. shuts down the APU after two minutes.

Moving the APU switch to OFF: causes automatic shutdown after 120 seconds. causes the fuel valve and inlet doors to remain open. bypasses the recommended one minute time delay for no bleed air load prior to shutdown. trips the APU Generator and closes the APU bleed air valve.

Starter cutout speed is: approximately 56%. N2. 25%N2. 46% N2. approximately 50% N1.