AS 411 Exam #2
Advancing engine start lever to idle prematurely can cause a _____ start
"HOT"
Engine ignition must be on for:
- takeoff - landing - operation in heavy rain - anti-ice operation
Limit each engine start attempt to a maximum of _____ minutes
2 minutes
The fuel LOW amber alert will occur when the tank quantity is less than
2,000 lbs
Re-engagement of starter with N2 in excess of ______ will result in serious damage to starter and engine.
20%
Total usable fuel for the B-737
46063 lbs
Maximum tank fuel temperature
49°C
When should the starter cutout?
56% N2
Which of the following is an indication of an engine fire: - the related engine fire switch illuminates - All related engine overheat alert indications illuminate - the fire warning bell - All answers are correct
All answers are correct
The fuel crossfeed valve is operated by a
DC motor powered by the battery bus
During an INFLIGHT engine start, the EEC automatically protects against ______ starts
EEC provides no protection for inflight starts
What redundancy is built in to the Electronic Engine Control (EEC)?
Each EEC has two independent control channels with automatic transfer
An ENG FAIL alert will be displayed under which circumstances?
Engine is operating below 50% with the start lever at IDLE
The B-737 has a fuel jettison system installed
False
The main gear wheel well has fire detection and extinguishing systems. T/F
False
The Electronic Engine Control (EEC) compares commanded N1 to actual N1 and adjusts ____________ to achieve the commanded N1?
Fuel Flow
If one of the engine overheat/fire detection loops fails with the OVHT DET switch in the NORMAL position which of the following will occur?
That loop is automatically deselected and the system will continue to function with a single loop detector.
At the same airspeed and altitude, N1 and N2% RPM will be higher for approach idle than for flight minimum idle for which of the following reasons?
To improve engine acceleration time in the event of a go-around.
Indications of an engine overheat are both MASTER CAUTION lights illuminate, the OVHT/DET system annunciator light illuminates and the related ENG OVERHEAT light illuminates. T/F
True
Operation with reduced takeoff thrust is not permitted with the EECs in alternate (ALTN) mode. T/F
True
Single engine taxi using the number 2 engine is the normal procedure. T/F
True
The lavatory fire extinguisher system is located beneath the sink area and operates automatically when fire is detected T/F
True
The main wheel fire detection system uses a single loop detector. T/F
True
If the EEC detects a wet start on the ground. What action does it automatically take?
Turns off the ignition and shuts off fuel to the engine 15 seconds after the start lever is moved to IDLE
APU fire detection is powered by the
battery bus
The nitrogen generation system converts bleed air to nitrogen-enriched air
during all phases of flight
The B-737 had fire detection and extinguishing systems for the
engines, APU, lavatories and cargo compartments
The fuel pumps are cooled by
fuel passing through the pump
The engine fuel shutoff valves are powered by the battery bus and are actuated by
fuel pressure
The B 737 NG is powered by two CFM 56-7 engines that are
high bypass, dual rotor, axial flow turbo fan
Engine fire extinguishing is powered by the
hot battery bus
Which of the following do not cause the secondary engine indications to be displayed? - in flight when an engine start lever is moved to CUTOFF - in flight when an engine N1 RPM is below idle - when the displays initially receive electrical power - when a secondary engine parameter is exceeded
in flight when an engine N1 RPM is below idle
The APU fire extinguishing system consists of
one APU fire extinguisher bottle, an APU fire switch, an APU BOTTLE DISCHARGE light and an EXT TEST switch.
In normal operations, with fuel in all tanks, both engines are initially fed from
the center tank
The nitrogen generation system operates in
the center tank only
When the AC fuel pumps are operating the APU draws fuel from the _______ fuel manifold
the left
In the event of a detector failure in the cargo compartment smoke detection system
the system can be manually converted to single loop detection using the DETECT SELECT switch on the cargo fire control panel
Once the loop detects a fire the WHEEL WELL fire warning light will remain illuminated until
the temperature of the detector has decreased below the onset temperature.
The purpose of the center tank scavenge pump is to
transfer any remaining center tank fuel to main tank 1
