test Flashcards
The main gearbox has a built-in forward tilt of________.
5 degrees
The helicopter normally has seats for ______ passengers, but has provisions for the installation of centerline seating giving it a seating capacity of_________.
32, 50
Maximum allowable gross weight is _______________.
73,500 lbs
The design gross weight is ____________, and the maximum weight-on-wheels is ______________
46,500 lbs, 69,750 lbs
The helicopter is powered by three _______________ or _________________ or ________________
engines producing individually ________________ at a power turbine output speed of_____________
T64-GE-416, T64-GE-416A, T64-GE-419, 4,380/4,750 shp, 14,280rpm
The length of the refueling probe is ___________ when extended and ___________ when retracted
21.96 ft, 10.52 ft
The main rotor diameter is ___________
79 ft
The overall length of the helicopter with blades and pylon spread is _______________
99 ft 0.5 inches
In order to select continuous ignition, the_________________ must be turned on.
respective engine anti-ice
The ignition system consists of an ignition unit, a control circuit, and _______ igniter plugs per engine.
a. 1.
b. 2.
c. 6.
d. 12
b. 2
When the start valve is energized by depressing the engine starter button, the engine start pump provides
_______ psi hydraulic pressure for engine starting
4000
The starter will not operate if any of the interlocks are in this configuration:
a.
b.
c.
d.
e.
f.
- Pylon is unsafe for flight.
- Blade fold safety valve is open.
- Pitch locks are advanced.
- Rotor brake is not fully pressurized (975 psi).
- Mechanical gust lock is engaged.
- Head is not in start position.
The start abort switches (do/do not) shut off fuel to the engines
Do not
The _____________________ switch positions the head for engine start so that hot engine exhaust gases
do not damage the main rotor blades
ENG ST HEAD POS
When icing conditions are anticipated, engine ice ingestion can be prevented by manually closing the
______________ and keeping them closed until after engine shutdown.
EAPS
The automatic control circuit, in conjunction with two pressure switches, functions to open the EAPS doors
automatically above ______ to ______ KIAS.
78 to 88
The scavenge blowers operate whenever the EAPS door is closed and the main transmission oil pressure is
above_____
14 psi
The engine overspeed system actuates at about ________Nf to protect against actual overspeed
110 +/-2
The engine fuel control unit functions to prevent _________, _________, _________, govern _______, and
schedule ______.
compressor stall, turbine overtemperature, rich or lean blowouts, gas generator idle and maximum speeds, inlet guide and stator vane positions
The engine fuel control unit senses, ___________, ___________, ___________, ___________,
__________, and ___________.
- Gas generator speed (Ng)
- Free power turbine speed (Nf)
- Compressor discharge pressure (P3)
- Compressor inlet temperature (T2)
- Overspeed voltage from the overspeed switch mounted on the engine front frame section
- Pilot input through the positioning of the engine speed control lever (SCL)
- Pilot input through the positioning of the collective pitch lever
The engine oil pressure lights on the caution panel (will/will not) indicate whether the oil pressure is too
high or too low.
Will
Illumination of the NO. 1, NO. 2, or NO. 3 ENG OIL QTY LOW caution light indicates the associated
tank has been depleted by ________________ of its usable capacity and shall be replenished by
_____________________.
25 percent, auxiliary oil system
Ground idle Ng is variable with ____________ and its range is ___________ to ___________.
OAT, 60.5% to 70%
The ________________ provides anticipation of load changes for reduction of transient droop by resetting
the fuel control governor proportional to the power required.
Load signal shaft (collective bias)
The helicopter has a single, articulated main rotor and an antitorque tail rotor.
a. True.
b. False.
TRUE
The main rotor blades have a(n) _______spar.
a. Aluminum.
b. Fiberglass.
c. Titanium.
d. Stainless steel
Titanium
The hollow main rotor blade spar is pressurized with _____________ to about ______________ at an
ambient temperature of _________to _______
nitrogen, 10 psi, 18, 24
The IBIS spar pressure indicator test button is always pressed with a ____________________ to prevent
radiation escape.
clear plastic shield over the indicator
If main rotor blade spar pressure drops to ___________ or less, the pressure indicator will show two black
stripes, indicating pressure is escaping through a crack in the spar or through a malfunctioning seal.
5 +/- 0.5 psi
The IBIS detector continually senses its own radiation and sends a signal to the signal processor, which energizes a relay that ______________ the BIM® caution light.
extinguishes
The input drive to the main gearbox from the No. 2 engine is through a ________________.
gimbal assembly
The main transmission gearbox has _______chip detectors, the accessory gearbox has _______, and the intermediate, tail rotor, and both engine nose gearboxes each have_______.
5, 2, 1
The accessory gearbox drives _______________, _________________, __________________, _________________, __________________, and ________________.
No. 1 and No.3 generators, second-stage servo hydaulic pump, engine start hydraulic pump, utility hydraulic system pump, accessory gearbox oil pump
The main gearbox auxiliary oil system has no associated warning system.
a. True.
b. False
FALSE
The intermediate and tail rotor pressure caution lights receive their power through an emergency DC bus
circuit breaker labeled:
a. AIT.
b. MAIN/TR INT GB.
c. INT-TAlL GB
B. MAIN/TR INT GB
The tail rotor gearbox and the intermediate gearbox have combination chip and temperature detectors.
a. True.
b. False
A. True
Under what three conditions will the automatic fuzz-burn feature be disabled in the main gearbox?
a.
b.
c.
A. MGB OIL HOT caution light illuminates; MGB OIL PRESS; MGB AUX LUBE
The pilot can, from the cockpit, identify which chip detector in the main gearbox has picked up chips.
a. True.
b. False.
B. False
Nose gearbox oil temperature caution lights will activate when the oil temperature reaches ___________.
121° ± 5.5°C
The accessory gearbox has two chip detectors, one for ____________________ and the other for ____________________
Gearbox ;Returning oil from the APP clutch
A green rotor brake light on the lower portion of the tachometer goes on whenever Nr is between _______
and _______.
50 ±4 percent ; 25 ±4 percent
Holding the low-pressure rotor brake switch at __________________ for about ____ seconds engages the
rotor brake with __________ psi hydraulic pressure.
ON; 5 ; 350 psi
The ROTOR BRAKE PRESS caution light will go on whenever the manifold pressure is above
___________.
10 psi
The ROTOR BRAKE ON advisory light visually indicates that the system pressure is ________.
975 psi
There must be electrical power on the helicopter in order to release the rotor brake.
a. True.
b. False
b. False
The helicopter is equipped with _________________ type fuel systems
three independent suction/pressure
Fuel for the APP is supplied from the _________________ fuel tank
No. 2 (right) tank
The fuel boost pump failure caution lights go on any time fuel boost pump pressure has decreased to _______
psi
8.5 ±0.5 psi
The fuel low caution light will go on when there are approximately ______ pounds of fuel remaining in either the No 1 or No 3 tank, or ________ pounds of fuel in either the No 2 left or right tank.
a. 340 ±20, 170 ±10
b. 390 ±60, 195 ±15
c. 666 ±30, 333 ±15
d. 610 ±30, 305 ±15
c. 666 ±30, 333 ±15
The ENG FLTR BY-PASS caution light will go on when the pressure drop across any one of the filters is
over _____ psi.
1.37 ±0.5
Each fuel filter will bypass when the pressure drop across it is over _____ psi
2.8
Fuel is transferred from the auxiliary fuel tanks to the main fuel tanks at a rate of about _________ gallons
per minute.
45
The main and auxiliary tanks may be refueled through the ground pressure refueling system without
electrical power.
a. True.
b. False
FALSE
There are ______ fuel flow sensors that will sense a fuel flow above ________ gpm and cause the appropriate fuel flow indicator light to go on.
4; 2 ±1
Each sponson can dump fuel at a rate of _________ gallons per minute.
75
The fuel dumping system permits dumping of fuel from each main tank and each auxiliary tank to reduce
the gross weight of the helicopter.
a. True.
b. False
FALSE
The fuel dump system is capable of dumping all fuel from the main fuel cells.
a. True.
b. False
FALSE
The fuel dump system has two dump pumps in each sponson.
a. True.
b. False.
b. False
Pressing and lighting the PURGE pushbutton causes the pressure refueling and fuel transfer system to start
purging. The purge cycle lasts for _______ minutes and shuts down automatically.
8.5
The APP is set for operation up to ________ feet pressure altitude
10,000
feet
A longer APP start interval may be obtained by using both accumulators _____________. The No. 2
accumulator is brought into the system by _______________________________ that is overhead on the
right side of the cabin.
simultaneously;pulling a T-handle
Fuel consumption for the APP is approximately ___________ pph, depending on OAT and the accessory
loads being used.
80 to 180
The APP control lever should be held at _______________ until clutch engagement, and then allowed to
return to _________.
START; RUN
Which of the following APP protective circuits is not bypassed during the engine start cycle?
a. Low oil pressure.
b. High exhaust gas temperature.
c. Overspeed.
c. Overspeed
The helicopter has ______ brushless generators, each rated at _____________ for operation up to
___________ feet.
3; 40 kVA; 10,000
Underfrequency protection is provided when Nr drops below __________.
91 to 96 percent
The ___________ and ___________ generators are driven by the accessory gearbox.
No. 1; No. 3
Underfrequency protection (is/is not) available when the weight of the helicopter is removed from the
landing gear.
is not
The three generators in the helicopter provide____________ volts, ____________ Hz, ____________ phase
power.
115/200; 400; 3
Each generator is routed through its supervisory panel that provides control and protection of the
electrical system from _________________, __________________, _________________, and
_________________.
underfrequency;
overvoltage; undervoltage; feeder fault
If the generators have not been turned off when external power is connected and the APP and/or main rotor
head is to be shut down, ___________ may be encountered on the next turnup.
relay chatter
Relay chatter can be eliminated by ___________________________________.
recycling the generator switches
The purpose of the three autotransformers is to reduce 115 VAC to 26 VAC.
a. True.
b. False
a. True
External power for the CH-53E should be ________ volts AC, _______ Hz.
115/200; 400
The failure of either rectifier will cause the ______________________ to be dropped from the system.
monitor DC bus
The emergency AC and DC circuit breakers are located in the _______________________
cockpit overhead control panel
The second stage and utility hydraulic systems are equipped with a finned tube heat exchanger:
a. True.
b. False.
b. False
The first stage hydraulic system is cooled by heat exchangers (finned tubes) located
_____________________ and _______________________.
at the inlet of the main transmission oil cooler; uses the air flow of this blower
The hydraulic fluid from the second stage and utility hydraulic systems is cooled as it returns to its respective
hydraulic system reservoir.
a. True.
b. False
a. True
The utility hydraulic system provides subsystem pressure for the following:
a.
b.
c.
d.
e.
f.
g.
h.
i.
j.
k.
a. utility hoist
b. APP and engine starting
c. landing gear extension and retraction
d. cargo door and ramp operation e. cargo winch operation
f. main wheel power brakes
g. main rotor and pylon folding
h. second stage of the tail rotor tandem servo
i. AFCS SERVO 2
j. the Force Augmentation System
(FAS) actuator if AFCS SERVO 2 is selected
k. main rotor head positioning for engine start.
The engine start hydraulic system draws its fluid from which hydraulic reservoir?
a. 1st stage reservoir.
b. 2nd stage reservoir.
c. Utility reservoir.
d. Engine start reservoir
c. Utility Reservoir
The UTILITY OIL HOT caution light will go on when utility hydraulic fluid temperature is over _______°C
107
The 1st stage of the primary tandem servos is powered by the _____________________, and the 2nd stage
is powered by the _____________.
the first stage hydraulic system; Second stage hydraulic system
The interlock that prevents either side of the tandem servos from being turned off if there is not at least
2,000 psi to the other side also prevents securing first stage if utility pressure is less than 2,000 psi.
a. True.
b. False
b. False
The 1 STG M/R SERVO BYPASS or 2 STG M/R SERVO BYPASS caution light will go on to indicate:
a. __________________________________.
b. _________________________________.
a. one or more cylinder sections on one side of the main rotor tandem servos may be jammed and is bypassing hydraulic pressure
b. any time the electrical system is energized and the first or second stage systems are not pressurized
To smooth out pilot roll inputs, a ____________ is incorporated in the roll linkage between the cyclic and
the AFCS roll.
a viscous damper
There are five couplings providing automatic proportional transfer between the axes when the appropriate
flight control is moved. They are __________________, _________________, __________________,
_________________, and _______________
The mixing unit makes these couplings: collective to yaw, collective to pitch, collective to roll, yaw to pitch, and yaw to roll
The __________ loop is primarily a stability augmentation system that employs rate damping to improve
helicopter stability.
inner
The longitudinal bias actuator provides the pilot with a positive longitudinal cyclic gradient.
a. True.
b. False.
a. True
The _________ loop maintains the flight regime selected by the pilot when he trims the flight controls.
outer
The ____________________ provides pitch force feel to the cyclic
force augmentation system (FAS)
The second stage of the AFCS servo, when selected, is pressurized by the ______________ hydraulic
system.
utility
When the AFCS servos are not pressurized, their only function is to provide a mechanical link between
___________ and ___________
the pilot input; the mixing unit.
The output of the AFCS ______________ and ______________ servos are linked directly to the mixing
unit, which furnishes output to the tail rotor servo plus the forward, aft, and lateral primary servos.
yaw; collective
The first stage of the AFCS servo, when selected, is pressurized by the ______________ hydraulic system.
2nd stage
With RAD ALT hold engaged, if a failure occurs, RAD ALT will automatically switch to BAR ALT hold.
a. True.
b. False.
a. True
Each AFCS computer will store, indefinitely, up to ______ Flight Bite Codes (FBC) until cleared by
maintenance personnel.
five
The ____________________ is used to remove hydraulic pressure from the FAS actuator in case of a
hydraulic leak in the FAS actuator.
FAS pressure switch
