Section VII – Engines, APU

Question 1

What actions occur when an Engine Start Selector is moved into the GND position?

Answer 1

Opens the start valve to supply starter air and arms the selected ignitor(s).

Question 2

What actions occur when an Engine Start Selector is moved to the CONT position? (

Answer 2

The ‘selected’ ignitor will operate continuously.

Question 3

What actions occur when an Engine Start selector is moved to the FLT position?

Answer 3

Both ignitors operate continuously regardless of ignition selector.

Question 4

According to system logic, describe two scenarios in which an ignitor would operate continuously without the Engine Start Selector in the CONT position.

Answer 4

In the AUTO position, the selected ignitor(s) operate continuously with the Leading Edge Slats extended (flaps 1), or with engine anti ice selected on.

Question 5

When is maximum motoring speed achieved?

Answer 5

Maximum motoring sped is reached when acceleration is less than
approximately 1% in 5 seconds.

Question 6

During the engine start cycle, when will an Engine Start Selector automatically spring back to AUTO?

Answer 6

50% N2.

Question 7

Are there any starter operation limitations?

Answer 7

Normal Duty Cycle: Five (5) minutes ON, followed by one and a half minutes (1 1⁄2) OFF. Extended Duty Cycle: Two (2) consecutive (5) minute cycles require a ten (10) minute cooling period before additional (5) minute cycle

Question 8

What actions occur when a Fuel Control Switch is moved from CUT OFF to RUN?

Answer 8

Opens engine and spar fuel valve and activates selected ignitor(s).

Question 9

What is the normal power source for the ignitors?

Answer 9

Main AC power is the normal power source for ignition. Standby AC power provides a backup source.

Question 10

What is Electronic Engine Control (EEC)? What is its primary purpose?

Answer 10

Trims the fuel flow for limiting N1 RPM when engine is accelerating at or near any thrust mode limit. The EEC provides N1 and N2 red line overspeed protection. It does not provide EGT overtemperature protection.

Question 11

When will the In-Flight Start Envelope appear on the EICAS primary display?

Answer 11

Whenever an engine is not running in flight, the respective engine fire switch is not pulled, and both EICAS primary and secondary displays are selected.

Question 12

What would cause a FUEL SPAR VAL light to illuminate on the throttle quadrant?

Answer 12

The valves do not agree with the fuel control switch after allowing for normal operating time. The ENG VALVE and SPAR VALVE lights illuminate momentarily as the valves open or close (engine start).

Question 13

How are the Thrust Reversers actuated?

Answer 13

a. 767-200: Hydraulically actuated fan air thrust reverser.
b. 767-300: Pneumatically actuated fan air thrust reverser.

Question 14

Where can the engine vibration display be found? Are there any limitations?

Answer 14

The engine vibration display can be found on the lower EICAS page. Engine vibration display must not be blanked during takeoff.

Question 15

When would a Standby Engine Indicator placard automatically display engine indications with the indicator selector in AUTO?

Answer 15

Whenever AC power is lost, either CRT failed and STATUS selected on the ground, or EICAS failed.

Question 16

What actions occur when an APU selector is moved from OFF to ON?

Answer 16

a. FAULT light illuminates momentarily (disagreement between fuel valve and commanded position)
b. Opens the APU fuel valve and Inlet Door
c. Activates AC or DC fuel pump
d. Powers the APU controller
e. Permits the APU bleed valve to open if the APU bleed switch is on when APU reaches operating speed.

Question 17

What is an indication that the APU has successfully started and is ready to power the electrical system?

Answer 17

The RUN light is illuminated on the APU panel. This light indicates the APU is at operating speed.

Question 18

What are the altitude limitations with respect to APU operations for Electrical and Pneumatics?

Answer 18

Electrical power is available throughout the airplane operating envelope (43,100ft). APU bleed air is available up to approximately 17,000 feet.

Question 19

Where does the APU draw its fuel supply from? What would cause a DC pump to operate in place of an AC pump?

Answer 19

a. Fuel for the APU is supplied from the left manifold.
b. A dedicated DC fuel pump is energized when the APU selector in the ON position if no AC power is available (no EXT PWR plugged in). When AC power is available, the left forward AC fuel pump is signaled to operate regardless of switch position and the DC pump is signaled OFF.

Question 20

T/F: The APU will shut down immediately when the APU start selector is moved from the ON to OFF position.

Answer 20

a. False; to protect the unit from thermal shock the APU control system incorporates a time delay feature permitting APU cooling before shutdown.

Question 21

While on the ground with the APU running, what happens if the battery switch is selected to OFF? What happens to the APU if the battery switch is selected off while in flight?

Answer 21

a. This results in an APU shutdown (after a cooldown cycle). This is not recommended because APU fire detection may not be available.
b. In flight, battery switch position does not affect APU operation.

Question 22

How can an APU shutdown cycle be canceled?

Answer 22

If the selector is inadvertently moved to OFF, but the RUN light is still illuminated, momentarily moving the selector to START cancels the shutdown signal.

Question 23

What is the significance of an APU FAULT light when illuminated?

Answer 23

It means the APU has automatically shutdown and the APU fuel valve
disagrees with the commanded position.