Engine System Review Questions Flashcards
The T-56-A-14 engine is rated at ____ SHP.
4600
NATOPS 2.9
The 6 uses of 14th stage bleed air include: engine starting, engine anti-icing, wing deicing, oil cooling augmentation, bomb bay heating, and:
closing the 5th and 10th stage bleeds.
WEEBOC
NATOPS 2.9.2
Fourteenth stage bleed air is tapped off the ____ section.
compressor
NATOPS 2.9.2
The ignitors are in:
cans 2 and 5
NATOPS 2.9.3
Of all the airflow entering the combustion section, approximately percent is used for combustion.
25%
NATOPS 2.9.3
The 18 thermocouples mounted in each engine turbine inlet casing send a signal to the ____.
TIT indicator and temperature datum control
NATOPS 2.9.12.2
The turbine section consists of ____ stages.
Four
NATOPS 2.9.4
The engine accessory section is mounted on and driven by gearing from the ____ section.
compressor
NATOPS 2.9.5
The equipment mounted on the compressor accessory section are the engine fuel pump, the main oil pump, the speed sense control, the scavenge oil pump, the:
fuel control unit, the oil filter, and the speed sense valve.
NATOPS 2.9.5
The reduction gearbox reduces ____ of the power section to ____ for use by the propeller.
high RPM, low torque; low rpm, high torque
NATOPS 2.9.6
The torquemeter assembly transmits torque from the power section to the reduction gear assembly, provides the primary support structure between the power unit and the RGB, and:
displays SHP on the indicators in the flight station.
NATOPS 2.9.7
Shaft horsepower gauges are powered by ____.
MEAC
NATOPS Fig. 2-5
The TIT gauges are powered by ____.
SEAC
NATOPS Fig. 2-5
The fuel flow gauges are powered by ____.
Bus A
NATOPS Fig. 2-5
Each engine oil system take has a useable capacity of ____ U.S. gallons.
8.65
NATOPS 2.9.14.1
Engine oil cooling augmentation requires the oil cooler door be fully opened, the power lever below flight idle, and
the start selector off.
NATOPS 2.9.14.3
The electrical functions of the emergency shutdown handle are controlled by electrical wiper switches, activated by the E-Handle, and powered by:
MEDC
NATOPS 2.9.10
If a fire warning sensing element is broken, the system will:
still sense a fire up to both sides of the break, but will not test.
NATOPS 2.9.13.1
Each engine fire extinguishing bottle simultaneously receives power from two independent sources. They are:
EMDC and MEDC
NATOPS 2.9.13.2
The ignitors operate:
between 16% and 65% engine rpm.
NATOPS 2.9.9.3
The purpose of the 5th and 10th stage bleed valves is to:
unload the compressor during engine acceleration
NATOPS 2.9.9.6
The 16% switch on the speed sense control opens the fuel shutoff valve, energizes the igniters, energizes the fuel drain manifold solenoid, and:
energizes the paralleling valve solenoid to put the fuel pumps into parallel.
NATOPS 2.9.9.3
The 94% switch on the speed sense control:
changes the TD system from start limiting to temperature limiting.
NATOPS 2.9.9.5
The speed sensitive valve:
closes the 5th and 10th stage bleed air ports at 94%
NATOPS 2.9.9.6
The starting system requires a stabilized air source that must maintain a minimum of ___ psi at 16% RPM
25
NATOPS 2.9.9.1, 8.5
The engine starter uses ____ from the ____ to provide engine rotation during a normal start.
compressed air; APU, an operating engine, or an external gas turbine compressor
NATOPS 2.9.9.1
The paralleling valve solenoid in the engine fuel system is energized by:
the ignition relay at 16%
NATOPS 2.9.9.3
The fuel manifold drain valve is closed:
electrically at 16% and is held closed by fuel pressure above 65% RPM
NATOPS 2.9.9.3
A CHIPS light indicates metal particles on a plug in the:
engine power section and/or the reduction gearbox
NATOPS 2.9.12.9
Maximum allowable oil pressure fluctuation in the power section at 100% RPM is ____ psi, provided pressure remains within limits.
+-5
NATOPS Fig 4-2
The maximum time for operation of the T56-14 engine at 1077 TIT is ___ minutes.
5
NATOPS Fig 4-2
Maximum TIT in normal rpm at ground start is
645 C
NATOPS Fig 4-2
In normal rpm, normal gearbox oil pressure is __ to 250 psi.
150
NATOPS Fig 4-2
Maximum allowable oil pressure fluctuation in the reduction gearbox at 100% rpm is psi, provided pressure remains within limits.
+-20
NATOPS Fig 4-2
Reduction gearbox oil pressure limits are 150-250 psi. Operation:
below 150 psi when below 100% rpm is permitted
NATOPS Fig 4-2
After returning to a positive g condition, following negative g flight, shut down the engine if oil pressure fluctuates for more than ___ seconds.
15
NATOPS Fig 4-2
In flight, oil pressure limits in the power section are ____ psi.
50-60
NATOPS Fig 4-2
Under extremely cold weather conditions, you may operate an engine with oil temperatures between 50-60C provided:
all oil pressure limitations are maintained.
NATOPS Fig 4-2
With an engine oil temperature of +25C, the maximum allowable SHP is:
1000
NATOPS Fig 4-2
With LOW rpm slected, a properly adjusted fuel control will maintain engine rpm between:
71.0-73.8
NATOPS Fig 4-2
After being shifted to NORMAL rpm and the power lever at 15 degrees coordinator, the engine rpm should be ___
96.3-99.1
NATOPS Fig 4-2
Torquemeter “flop over” can occur with too rapid an application of power. This means that at least ___ SHP has been momentarily exceeded and the engine shall be ____.
5300; inspected as soon as possible
NATOPS 4.3
Maximum power may be applied for takeoff provided:
oil temperature is 40C and rising with no fluctuations in the gearbox oil pressure
NATOPS Fig 4-2
After executing a max power takeoff (1077 TIT), you must retard the power lever within ___ mins.
5
NATOPS Fig 4-2
