test Flashcards
(247 cards)
1
Q
The main gearbox has a built-in forward tilt of________.
A
5 degrees
2
Q
The helicopter normally has seats for ______ passengers, but has provisions for the installation of centerline seating giving it a seating capacity of_________.
A
32, 50
3
Q
Maximum allowable gross weight is _______________.
A
73,500 lbs
4
Q
The design gross weight is ____________, and the maximum weight-on-wheels is ______________
A
46,500 lbs, 69,750 lbs
5
Q
The helicopter is powered by three _______________ or _________________ or ________________
engines producing individually ________________ at a power turbine output speed of_____________
A
T64-GE-416, T64-GE-416A, T64-GE-419, 4,380/4,750 shp, 14,280rpm
6
Q
The length of the refueling probe is ___________ when extended and ___________ when retracted
A
21.96 ft, 10.52 ft
7
Q
The main rotor diameter is ___________
A
79 ft
8
Q
The overall length of the helicopter with blades and pylon spread is _______________
A
99 ft 0.5 inches
9
Q
In order to select continuous ignition, the_________________ must be turned on.
A
respective engine anti-ice
10
Q
The ignition system consists of an ignition unit, a control circuit, and _______ igniter plugs per engine.
a. 1.
b. 2.
c. 6.
d. 12
A
b. 2
11
Q
When the start valve is energized by depressing the engine starter button, the engine start pump provides
_______ psi hydraulic pressure for engine starting
A
4000
12
Q
The starter will not operate if any of the interlocks are in this configuration:
a.
b.
c.
d.
e.
f.
A
- 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.
13
Q
The start abort switches (do/do not) shut off fuel to the engines
A
Do not
14
Q
The _____________________ switch positions the head for engine start so that hot engine exhaust gases
do not damage the main rotor blades
A
ENG ST HEAD POS
15
Q
When icing conditions are anticipated, engine ice ingestion can be prevented by manually closing the
______________ and keeping them closed until after engine shutdown.
A
EAPS
16
Q
The automatic control circuit, in conjunction with two pressure switches, functions to open the EAPS doors
automatically above ______ to ______ KIAS.
A
78 to 88
17
Q
The scavenge blowers operate whenever the EAPS door is closed and the main transmission oil pressure is
above_____
A
14 psi
18
Q
The engine overspeed system actuates at about ________Nf to protect against actual overspeed
A
110 +/-2
19
Q
The engine fuel control unit functions to prevent _________, _________, _________, govern _______, and
schedule ______.
A
compressor stall, turbine overtemperature, rich or lean blowouts, gas generator idle and maximum speeds, inlet guide and stator vane positions
20
Q
The engine fuel control unit senses, ___________, ___________, ___________, ___________,
__________, and ___________.
A
- 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
21
Q
The engine oil pressure lights on the caution panel (will/will not) indicate whether the oil pressure is too
high or too low.
A
Will
22
Q
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
_____________________.
A
25 percent, auxiliary oil system
23
Q
Ground idle Ng is variable with ____________ and its range is ___________ to ___________.
A
OAT, 60.5% to 70%
24
Q
The ________________ provides anticipation of load changes for reduction of transient droop by resetting
the fuel control governor proportional to the power required.
A
Load signal shaft (collective bias)
25
The helicopter has a single, articulated main rotor and an antitorque tail rotor.
a. True.
b. False.
TRUE
26
The main rotor blades have a(n) _______spar.
a. Aluminum.
b. Fiberglass.
c. Titanium.
d. Stainless steel
Titanium
27
The hollow main rotor blade spar is pressurized with _____________ to about ______________ at an
ambient temperature of _________to _______
nitrogen, 10 psi, 18, 24
28
The IBIS spar pressure indicator test button is always pressed with a ____________________ to prevent
radiation escape.
clear plastic shield over the indicator
29
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
30
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
31
The input drive to the main gearbox from the No. 2 engine is through a ________________.
gimbal assembly
32
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
33
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
34
The main gearbox auxiliary oil system has no associated warning system.
a. True.
b. False
FALSE
35
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
36
The tail rotor gearbox and the intermediate gearbox have combination chip and temperature detectors.
a. True.
b. False
A. True
37
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
38
The pilot can, from the cockpit, identify which chip detector in the main gearbox has picked up chips.
a. True.
b. False.
B. False
39
Nose gearbox oil temperature caution lights will activate when the oil temperature reaches ___________.
121° ± 5.5°C
40
The accessory gearbox has two chip detectors, one for ____________________ and the other for ____________________
Gearbox ;Returning oil from the APP clutch
41
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
42
Holding the low-pressure rotor brake switch at __________________ for about ____ seconds engages the
rotor brake with __________ psi hydraulic pressure.
ON; 5 ; 350 psi
43
The ROTOR BRAKE PRESS caution light will go on whenever the manifold pressure is above
___________.
10 psi
44
The ROTOR BRAKE ON advisory light visually indicates that the system pressure is ________.
975 psi
45
There must be electrical power on the helicopter in order to release the rotor brake.
a. True.
b. False
b. False
46
The helicopter is equipped with _________________ type fuel systems
three independent suction/pressure
47
Fuel for the APP is supplied from the _________________ fuel tank
No. 2 (right) tank
48
The fuel boost pump failure caution lights go on any time fuel boost pump pressure has decreased to _______
psi
8.5 ±0.5 psi
49
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
50
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
51
Each fuel filter will bypass when the pressure drop across it is over _____ psi
2.8
52
Fuel is transferred from the auxiliary fuel tanks to the main fuel tanks at a rate of about _________ gallons
per minute.
45
53
The main and auxiliary tanks may be refueled through the ground pressure refueling system without
electrical power.
a. True.
b. False
FALSE
54
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
55
Each sponson can dump fuel at a rate of _________ gallons per minute.
75
56
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
57
The fuel dump system is capable of dumping all fuel from the main fuel cells.
a. True.
b. False
FALSE
58
The fuel dump system has two dump pumps in each sponson.
a. True.
b. False.
b. False
59
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
60
The APP is set for operation up to ________ feet pressure altitude
10,000
feet
61
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
62
Fuel consumption for the APP is approximately ___________ pph, depending on OAT and the accessory
loads being used.
80 to 180
63
The APP control lever should be held at _______________ until clutch engagement, and then allowed to
return to _________.
START; RUN
64
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
65
The helicopter has ______ brushless generators, each rated at _____________ for operation up to
___________ feet.
3; 40 kVA; 10,000
66
Underfrequency protection is provided when Nr drops below __________.
91 to 96 percent
67
The ___________ and ___________ generators are driven by the accessory gearbox.
No. 1; No. 3
68
Underfrequency protection (is/is not) available when the weight of the helicopter is removed from the
landing gear.
is not
69
The three generators in the helicopter provide____________ volts, ____________ Hz, ____________ phase
power.
115/200; 400; 3
70
Each generator is routed through its supervisory panel that provides control and protection of the
electrical system from _________________, __________________, _________________, and
_________________.
underfrequency;
overvoltage; undervoltage; feeder fault
71
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
72
Relay chatter can be eliminated by ___________________________________.
recycling the generator switches
73
The purpose of the three autotransformers is to reduce 115 VAC to 26 VAC.
a. True.
b. False
a. True
74
External power for the CH-53E should be ________ volts AC, _______ Hz.
115/200; 400
75
The failure of either rectifier will cause the ______________________ to be dropped from the system.
monitor DC bus
76
The emergency AC and DC circuit breakers are located in the _______________________
cockpit overhead control panel
77
The second stage and utility hydraulic systems are equipped with a finned tube heat exchanger:
a. True.
b. False.
b. False
78
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
79
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
80
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.
81
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
82
The UTILITY OIL HOT caution light will go on when utility hydraulic fluid temperature is over _______°C
107
83
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
84
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
85
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
86
To smooth out pilot roll inputs, a ____________ is incorporated in the roll linkage between the cyclic and
the AFCS roll.
a viscous damper
87
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
88
The __________ loop is primarily a stability augmentation system that employs rate damping to improve
helicopter stability.
inner
89
The longitudinal bias actuator provides the pilot with a positive longitudinal cyclic gradient.
a. True.
b. False.
a. True
90
The _________ loop maintains the flight regime selected by the pilot when he trims the flight controls.
outer
91
The ____________________ provides pitch force feel to the cyclic
force augmentation system (FAS)
92
The second stage of the AFCS servo, when selected, is pressurized by the ______________ hydraulic
system.
utility
93
When the AFCS servos are not pressurized, their only function is to provide a mechanical link between
___________ and ___________
the pilot input; the mixing unit.
94
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
95
The first stage of the AFCS servo, when selected, is pressurized by the ______________ hydraulic system.
2nd stage
96
With RAD ALT hold engaged, if a failure occurs, RAD ALT will automatically switch to BAR ALT hold.
a. True.
b. False.
a. True
97
Each AFCS computer will store, indefinitely, up to ______ Flight Bite Codes (FBC) until cleared by
maintenance personnel.
five
98
The ____________________ is used to remove hydraulic pressure from the FAS actuator in case of a
hydraulic leak in the FAS actuator.
FAS pressure switch
99
The longitudinal bias actuator is fully retracted from ________to ________ knots and is fully extended at
___________ knots.
0; 60; 180
100
During normal operations, each AFCS computer furnishes ________________ of the correction signal to
the AFCS servos and the longitudinal bias actuator
half
101
The nose landing gear ___________________ prevents nose gear vibration during forward motion on the
ground
shimmy damper
102
If the pin is extended on the top of the landing gear strut, this is an indication that _________ servicing is
necessary.
a. Hydraulic.
b. Nitrogen.
a. Hydraulic
103
The attitude warning system will function if the helicopter has experienced a single computer failure.
a. True.
b. False.
a. True
104
During forward flight, with an airload on the nose gear door, emergency extension may take from _______to
______ minutes
1; 2
105
With the utility hydraulic system not pressurized, the wheel brakes are capable of holding the helicopter,
loaded to 46,500 pounds, on a ______________ slope.
10 degree
106
The copilot vertical gyro indicator normally receives inputs from the ______________, and the pilot vertical
gyro indicator receives inputs from the __________________.
vertical gyro; AHRS
107
The circuit breaker controlling the copilot vertical gyro is located on the ___________
No. 3 primary AC bus
108
The heater uses about _____ pounds of fuel per hour.
54
109
The heater is rated at _______________ BTUs and receives its fuel from the ______________
600,000; No. 2 left tank
110
An overheat switch in the heater will shut off if for any reason the heat in the plenum chamber rises to
______________
204 degrees C
111
The vent fan and combustion air fan will continue to operate after the heater is shut off until the temperature
in the plenum chamber drops to __________
49 degrees C
112
The heater should be turned off __________ minutes before removing electrical power from the system
10
113
With EAPS installed, engine anti-icing capabilities are available with the exception of the _________ and
________ nose gearbox fairing anti-ice.
No. 1; No. 3
114
If the respective ENG ANTI-ICE caution light goes on after the engine anti-ice switches are turned
on, they will remain on until the temperature increases above the low temperature sensor setting of
_________________
35 degrees C
115
A loss of about ____________ of each engine horsepower will result at maximum power when the engine
air anti-icing system is on
3 percent
116
The single-point hook opens automatically when the weight on the hook is reduced to ______________
pounds when in the automatic mode
525 +/- 225
117
Jettisoning of airborne cargo of over _____________ pounds with the pilot cargo release buttons or
aircrewman pendant may cause the cargo hook to recoil and strike the fuselage.
20,000
118
The two-point cargo hooks are on the longitudinal axis of the helicopter and are _____ feet apart.
10
119
Two ____________ pound limit cargo hooks, limited to a combined capacity of ___________ pounds, are
mounted on attachments under the cabin deck
21,600; 36,000
120
With TWO PT MODE switch at ____________, the loss of the load from one hook, for any reason,
automatically opens both hooks electrically for load release
TWO PT FLIGHT
121
The hoist winch motor receives hydraulic power from the _______________ hydraulic system and is
controlled by an electrohydraulic hoist control valve.
utility
122
The utility hoist has a capacity for _________ pounds with about _________ feet of usable cable length.
600; 245
123
The cabin section has provision for the installation of___________ pole type litters
24
124
The tail skid circuit is routed through the down side of the ramp control switch so that the tail skid
will automatically __________________ when the cargo ramp is lowered, and the helicopter is ________________.
Retract; on the ground
125
Each engine has _____ photocell flame detectors mounted through the fuselage fairing into the engine
section
3
126
Each flame detector provides _______ degrees of scan.
90°
127
A crash-generated force of _____ G’s automatically discharges the fire extinguishers into the engine
compartments
10
128
If more than one emergency T-handle is moved full aft, the fire-extinguishing agent will be directed to the
engine compartment of the ___________ emergency T-handle actuated
last
129
The loss of any single generator will result in the loss of which buses?
a. No. 1 Primary DC Bus.
b. No. 2B Primary AC Bus.
c. No. 1 Monitor AC Bus.
d. No. 2 Monitor AC Bus.
C. No.1 Monitor AC Bus
130
The UTILITY PRESS and UTILITY T/R PRESS caution lights illuminate when system pressure drops
below ______ psi. The 1 STG PRESS M/R T/R and 2 STG PRESS M/R caution lights illuminate when
system pressure drops below _____ psi
1500; 2000
131
The capacities of the main fuel tanks are as follows:
No. 1 tank _______ gallons.
No. 2 tank _______ gallons.
No. 3 tank _______ gallons.
300; 377; 300
132
The helicopter is equipped with two _____________ -gallon auxiliary fuel tanks
650
133
When pressure refueling, fuel tank quantities should be monitored closely, as the
_______________________ may not secure refueling.
high-level shutoff valves
134
When pressure refueling, make sure that pressure from the fueling source is not over _______ psi before
beginning fueling
55
135
The normal setting of the fuel control density selector is ________ for JP-4, JP-5, and JP-8
No. 4
136
Towing speeds shall not exceed _______ mph, and sudden stops or starts will be avoided.
5
137
The parking brakes are not to be set during cold-weather operations, because of ________________
Freezing due to condensation
138
When tied down properly, the helicopter can withstand winds of up to _____ knots.
60
139
The NATO CODE for JP-4 is ___________
F-40
140
Rotors should not be engaged or disengaged in winds from any direction over_____ knots
45
141
The tail skid/oil shock strut will withstand inadvertent ground contact up to a sink rate of _________ feet
per minute
672
142
The two-point suspension hooks shall never be used independently or in conjunction with the single-point
system.
a. True.
b. False.
TRUE
143
The lateral cg limits of this helicopter are _____ inches right and ____ inches left regardless of the helicopter
configuration.
8.5; 13.5
144
The helicopter is designed to permit emergency water landings with the ability to stay afloat for at least
______ hours in 1- to 3-foot waves with a wind of 7 to 16 knots.
2
145
Density altitude varies with ________________, ____________________, and
____________________
atmospheric pressure; temperature; humidity
146
An increase in OAT, at a constant pressure altitude, causes _________________ engine performance
decreased
147
The __________ weight of a transport helicopter is the weight of the helicopter including the crew and all
equipment required for the mission, but not including fuel or payload
operating
148
Restarting of APP before a _____-minute wait may cause a hot start.
2
149
The engine oil high pressure light may stay on for as long as _____ minutes until oil has warmed.
3
150
When approaching power and telephone lines, it is advisable to fly over the poles or towers rather than over
the wire.
a. True.
b. False.
TRUE
151
A single-point performance check is done to determine if the engine is producing ___________ acceptable
torque, at a specific T5, OAT, and pressure altitude
Minimum
152
An emergency brake application can be made at any Nr with all engines shut off and high-pressure rotor
brake switch at EMER.
a. True.
b. False.
TRUE
153
Total time to extend the air-refueling probe should not be over _______________
1 minute
154
Receiver crews __________________ attempt probe-to-drogue contact while in a turn at night.
Should not
155
Land as soon as possible means:
a. Landing site and duration of flight are at the discretion of the pilot in command.
b. Land at the first site at which a safe landing can be made.
c. Land immediately
B. Land at the first site at which a safe landing can be made
156
A precautionary landing is described as a landing when further flight is possible but inadvisable.
a. True.
b. False.
TRUE
157
WARNING: A fire hazard exists during emergency brake application due to the ______________________
and the presence of ______________________ in the rotor brake area.
heat generated; debris and oil
158
Tail rotor drive system failure is always accompanied by loss of directional control and a sharp
_______________ yaw.
Right
159
Accessory gearbox failure will result in the loss of the _______, ________, and _______ pumps, and the
_______ and _______ generators.
the second stage; utility; engine start; No. 1; No. 3
160
The primary visual indications of loss of utility hydraulic fluid to the utility system are:
a. _________________________________.
b. _________________________________.
A. The utility hydraulic quantity indicator; B Caution lights
161
The master switch on the hoist control panel has to be at _____________ or _____________ before the
hoist shear switch, on the cockpit console, can shear the cable.
Crew; Pilot
162
A(n) _________________ in torque for a given flight condition is an indication of main gearbox impending
failure.
Increase
163
Compressor stall is normally accompanied by unusual engine ___________________ and a
____________________.
Sounds; Slight yaw kick
164
During desert operations, prior to engine start with the EAPS door closed, the ____________ (14 psi) circuit
breaker (Emergency DC Bus) should be pulled and left out for __________ seconds once the APP is on line.
MAIN TR INT GB PRESS; 30
165
The engine overspeed test circuit will function after the engine has attained ___________ Nf.
95 percent ±2 percent
166
Placing a respective engine overspeed switch to TEST will energize the fuel control solenoid at any Nf.
a. True.
b. False.
b. False
167
With only two engines operating, a total torque indication of 70 percent would mean that:
a. The total (sum) of the torques of the two operating engines equals 70 percent.
b. The average torque of the two operating engines is 70 percent.
c. The average torque of all three engines is 70 percent.
d. Each operating engine is producing 70 percent torque.
c. The average torque of all three engines is 70 percent.
168
The T5 gauges are powered by thermocouples and do not require any additional power source.
a. True.
b. False.
b. False
169
The helicopter fuel system cannot be purged while pressure refueling or fuel transfer is taking place.
a. True.
b. False.
a. True
170
6. What six things will fail with the loss of the No. 2 and 3 generators?
a.
b.
c.
d.
e.
f.
All 3 BDHI's
AHRS
RADALT
VOR
AFCS #2
TACAN
171
Because two generators are driven by the APP, it is possible to operate the copilot spotlight on the ground without the rotor head turning.
a. True.
b. False.
a. True
172
Current limiters restrict the maximum flow of current regardless of the voltage applied to the system.
a. True.
b. False.
a. True
173
The ________ coupling provides increased tail rotor thrust for collective increases.
collective to yaw
174
The ___________ provides longitudinal cyclic inputs proportional to pedal inputs to compensate for the pitching moment produced by the vertical thrust component of the canted tail rotor.
yaw to pitch
175
. The _________ function applies a force at the cyclic pitch position, providing feedback cuing that is directly proportional to gravity forces.
FAS
176
The AFCS servos provide three separate functions:
a.
b.
c.
a.Provide power boost in all four axes for pilot initiated control inputs
b.Converting electrical inner loop signals from the computers into mechanical motion of the main and tail rotor servos, without moving the cockpit controls, to improve short term dynamic stability
c.Converting electrical outer loop signals from the computers into mechanical movement of the cockpit flight controls to improve long-term dynamic stability (autopilot) and providing cockpit flight control trim.
177
Pitch attitude hold, airspeed hold, and pitch trim are done by the _________________ actuator from computer inputs.
FAS
178
_____________________ provides damping to improve short-term dynamic stability in pitch, roll, and yaw inner loop.
Stability Augmentation System (SAS)
179
Turn coordination provides yaw channel inputs to coordinate turns above _______ knots.
60
180
Above 60 knots, beeping the cyclic stick trim beep button FWD and AFT re-references pitch trim at a rate of _____ knots per second to hold selected airspeed.
6
181
Airspeed hold is not available below _____ knots.
60
182
Auto bank automatically disengages and engages with attitude retention during a maneuver above_______ knots.
60
183
The output of the AFCS pitch servo is linked through the __________ to the mixing unit, providing mechanical outputs to the forward and aft primary servos.
longitudinal bias actuator (LBA)
184
The output of the AFCS roll servo is linked directly to the mixing unit, which furnishes a single input to the _________________ primary servo.
lateral
185
The ______________ loop stability signals are applied to the servo output and do not move the cockpit flight controls.
inner
186
With AFCS off, pressing and lighting the TRIM pushbutton to read TRIM turns on ________________, ________________, and ________________.
cyclic; collective; pedal trim
187
Servo 1 or Servo 2, CMPTR POWER and AFCS have to be turned on before the TRIM pushbutton provides ______________ functions.
autopilot
188
The mechanical gust lock engaged interlock is automatically bypassed, when airborne, by a microswitch on the main landing gear scissors switch.
a. True.
b. False
a. True
189
With the radar altimeter off, the landing gear up warning system will be activated any time the gear is up and airspeed is less than ______ knots.
60
190
The airspeed indicators in the cockpit are unreliable below ______ KIAS.
40
191
When the PUSH-TO-TEST control knob on the radar altimeter indicator is pressed, a visual indication of _________________ on the indicator indicates satisfactory system operation.
100 ±15
192
When the HOIST CONTROL panel is placed to PILOT, placing the control switch to either UP or DOWN will cause the hoist cable to travel in the mode selected at a maximum cable speed of __________ feet per minute.
50
193
An autorotative descent speed of ____________ will produce a minimum sink rate, and _________________ will provide the greatest distance.
85 KIAS; 110 KIAS
194
At gross weights below ____________ pounds, average torque is limited to ___________ in a climb.
60,000; 110 percent
195
At gross weights above __________ pounds, 121 percent average torque may be used in a climb.
60,000;
196
The tail skid/oil shock strut will withstand inadvertent ground contact up to a sink rate of ________ feet per minute.
672
197
The maximum gross weight at which hover or level flight can be maintained ______________ as density altitude increases.
decreases
198
A rise in T5 to __________ before the engine reaches ground idle is an indication of a hot start:
a. 627 °C.
b. 638 °C.
c. 650 °C.
d. 790 °C.
c. 650 °C.
199
A _________________ will be indicated by a failure of the gas generator to accelerate to proper idle speed, accompanied by a low T5 indication.
cold hang-up (hung start)
200
During transition to forward flight, as airspeed increases above approximately _______ knots, translational lift will become effective and tend to cause the helicopter to climb.
15 knots
201
Fuel shall not be dumped below _____KIAS or above 130 KIAS.
90
202
For heavy lift operations and landings, set rotor speed to ______ percent Nr.
105
203
Landing on slopes up to approximately _______ differ very little from normal, level landings, and any direction of landing may be accomplished.
4 degrees
204
Practice autorotations should not be attempted in conditions of high gross weight and critical ___________ loadings
center of gravity
205
To provide engine cooling before engine shutdown, one of the following conditions must occur before moving the speed control levers to SHUT-OFF:
a.
b.
c.
(a)one minute of taxiing
(b) one minute of operation at or above the minimum governing range and with minimum collective pitch
(c) one minute at GRD IDLE.
206
With all engines shut down, the rotor brake will stop the rotor within ________ seconds after high-pressure brake.
30
207
Main rotor-to-drogue/probe clearance can be as little as ________ feet during _________-inch longitudinal cyclic inputs.
4.0; 1.0
208
Refueling directly behind the refueling pod __________________ recommended.
is not
209
WARNING: If an operating engine and a failed or secured engine have the same tank selected, the operating engine may __________________ if the failed or secured engine _____________________ was not placed in ___________________.
flame out; fuel selector lever; shutoff
210
Note: Flare effectiveness at airspeed for ____________________ will be marginal in arresting ______________.
minimum rate of descent; descent rate
211
WARNING: Delay in shutting down the helicopter may give the fire time to burn through a flight control component, causing _________________________________.
the helicopter to roll over
212
WARNING: Loss of a control desensitizer will, under certain circumstances, allow the pilot to interact with the ________________________ to create a _________________________.
fuselage bending modes; pilot-induced oscillation (PIO)
213
When the 1 STG M/R SERVO BYPASS caution light is observed after a utility hydraulic system failure, securing first stage flight control system will result in __________________.
loss of tail rotor control
214
Maximum continuous power turbine inlet temperature for the T64-GE-416/416A is __________ °C, and for the T64-GE-419 is __________ °C. Military power turbine inlet temperature for the T64-GE-416/416A is __________ °C, and for the T64-GE-419 is __________ °C. This temperature is allowable for __________ minutes. Maximum temperature for the T64-GE-416 is __________, for the T64-GE-416A is __________ °C and for the T64-GE-419 is __________ °C. This temperature is allowable for __________ minutes.
713; 769; 753; 810; 30; 773; 792; 829; 10
215
A T5 increase of 40 °C at a constant torque is equal to a power loss of about _______ percent.
10%
216
. Compressor Stall:
1.
2.
3.
4.
5.
1. Collective — Maintain Nr.
*2. Airspeed — As required.
*3. Pickle — External load as required.
*4. Tanks — Jettison as required.
*5. Speed control levers — As required. (If
compressor stall of No. 2 eng is indicated,
immediately secure SCL and continue with
Engine Shutdown in Flight procedures. If No. 1
or No. 3 engs, affected SCL below MIN GOV.)
217
Symptoms of affected engine experiencing an Nf Flex Shaft Failure:
All engine parameters decreasing. As long as the
affected engine is producing any usable torque, Nf
will remain matched with the normal Nf/Nr. If torque
drops to zero, Nf will likely split off and decay.
218
Symptoms of affected engine experiencing Power Train Failure are:
a.
b.
c.
a. Sudden decrease to zero on Nf and torque indicators.
b. Ng and T5 increasing until overspeed system actuation,
then T5 decreasing and Ng decreasing to flight idle.
c. Grinding/howling noise may be heard.
219
Why will high engine oil temperatures occur when the helicopter engines are operating and the rotor is not engaged?
because the engine oil cooler blowers are not operating.
220
If, after closing a precheck valve on the pressure refueling panel, fuel continues to flow into that fuel tank, a malfunction exists in the respective ____________.
Shutoff valve
221
At the completion of pressure refueling, the precheck valves must be left in the __________ position to allow for fuel transfer
open
222
The APP high exhaust temperature circuit breaker will automatically pop out at _________ degrees Celsius.
621
223
The 28 VDC external power receptacle is colocated with the 115/200 VAC external power receptacle.
a. True.
b. False.
FALSE
224
The first stage of the AFCS servo, when selected, is pressurized by the ________________ hydraulic system.
second stage flight control
225
The blades and pylon may be folded separately; however, the blades cannot be folded if the pylon has already been folded.
a. True.
b. False
TRUE
226
The cabin compartment floor is capable of sustaining loads of ________ pounds per square foot.
300
227
The cargo tiedown rings installed in the cabin floor are rated at ________ pounds.
5000
228
The pilot master ramp control switch must be in the ________ position before the crew ramp control panel will function.
CREW
229
When starting the APP with no external power applied to the helicopter, fire detection is available at ________ percent.
92
230
A fire in the APP or heater compartment will be indicated by ____________ and ____________. It can be extinguished by pulling the ____________.
master fire warning lights;
APP emergency T-handle fire warning light
APP emergency T-handle
231
In case of an in-flight fire in either of the electronics compartments, there is an emergency access panel between the cabin and the electronics compartments through which the fire extinguisher can be discharged.
a. True.
b. False
TRUE
232
The fuel control unit uses the same density setting for both JP-4 and JP-5.
a. True.
b. False
TRUE
233
When checking engine oil level after engine has been at idle for some time, or the engine is cold, the engine should be ___________ for ____________ seconds before checking the oil level.
motored; 30
234
When replenishing the oil tanks using the auxiliary oil system, add oil until the ____________ light goes on.
TANK FULL
235
The M32A-10 power cart is accepted for use on the CH-53E.
a. True.
b. False
TRUE
236
When using other than chain tiedowns to secure the helicopter or the rotor blades, enough slack should be provided in all ropes to prevent ______________ due to moisture absorption.
overtightening
237
The NATOPS Aircrew Pocket Checklist is a required item of equipment for aircrewmen on all flights.
a. True.
b. False
TRUE
238
For the procedure to be followed for internal transport of selected cargo, passengers, including cg limits, floor loading, and tiedown requirements, aircrew should refer to the ___________.
A1-H53BE-CLG-000
239
Before lowering ramp, be sure that area under ramp is clear of _______, _______, ________, etc. and that ground is of equal ________ ability:
a.
b.
c.
d.
equipment; rocks; stumps;
load-carrying
240
During the cargo hook system functional check, the emergency cargo hook release handle is not tested.
a. True.
b. False.
FALSE
241
What are the aircrewman actions if the helicopter develops an APP fire during ground operation?
a.
b.
a. Notify pilot of location and extent of fire.
B. Discharge fire extinguisher into compartment access.
242
The cargo conveyor system is limited to ________ pounds for a ________ inch pallet.
2,200 lbs; 48
243
MIL-PRF-23699 oil is used in the engines, gearboxes, and rotor system.
a. True.
b. False
FALSE
244
While in flight or away from home base maintenance facilities, malfunction information and troubleshooting and adjustment procedures can be found in the A1-H53BE-NFM-900, which is also known as the __________________.
NATOPS Aircrew Pocket Checklist
245
A passenger briefing guide is included in the Aircrew Pocket Checklist.
a. True.
b. False
TRUE
246
During pressure refueling, line pressure should be _________ to _________ psi.
35 to 55 psi
247
The fuel nozzle grounding cable should always be attached after the fuel nozzle is attached to the fuel panel adapter.
a. True.
b. False
b. False
