th-67 systems
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TH-67 Systems. Study Guide (General Description, Flight Controls and Hydraulics, Rotors, and Power Plant). 1. Define the term WARNING. An operating procedure, practice, etc., which if not strictly observed could result in damage to or destruction of equipment. A mandatory procedure - PowerPoint PPT PresentationTRANSCRIPT
TH-67 Systems
TH-67 SystemsStudy Guide
(General Description, Flight Controls and Hydraulics, Rotors, and Power Plant)11. Define the term WARNINGAn operating procedure, practice, etc., which if not strictly observed could result in damage to or destruction of equipment.
A mandatory procedure
An operating procedure, practice, etc., which if not correctly followed could result in personal injury or loss of life.
Indicated futurity22. Define the term CAUTIONAn operating procedure, condition, etc., which is essential to highlight.
An operating procedure, practice, etc., which if not strictly observed could result in damage to or destruction of equipment.
An operating procedure, practice, etc., which if not correctly followed could result in personal injury or loss of life.
Indicates futurity33. Define NOTEA mandatory procedure
Recommended or preferred, not mandatory.
Indicates futurity
An operating procedure, condition, etc., which is essential to highlight.44. Define the term SHALLIndicated futurity
A mandatory procedure
An optional procedure
Recommended or preferred, not mandatory55. Define the term SHOULDRecommended or preferred, not mandatory
An optional procedure
A mandatory procedure
An operating procedure, condition, etc., which is essential to highlight66. Define the terms MAY or NEED NOTIndicated futurity
A mandatory procedure
A condition that you may do or not
An optional procedure77. Define the term WILLAn optional procedure
Indicates futurity
A mandatory procedure
A procedure that will be done88. The three sections of the TH-67 fuselage are the _____, _______, and the _______ section.cockpit, cabin, and aft boom
front, intermediate, and back tail
forward, intermediate, and tail boom
cockpit, cabin, and tail99. The VFR & A+ configuration have one pitot that provides _______ air to the airspeed indicator and two vents that provide _____ air to the static instruments. direct, indirect
pressure, kinetic
impact (ram), static
direct, static
1010. The IFR configuration has __ ______ pitot/static systems.4 separate
3 individual
2 independent
2 individual1111. The TH-67 ____ light, located on the aircraft nose provides a 450 watt lamp in an extendable and slewable mount.landing
position
collision
search1212. The TH-67 ____ light, located on the aircraft nose provides a 250 watt lamp in a fixed mount.landing
search
position
collision 1313. How many switches are used to control the search light in the NVG mode on the A+ configuration?2, one for selecting IR light, and one to turn it on.
4, one to turn it on, one to select white light, one to select IR light, and one to slew the search light to extended and retracted position.
3, one to select the IR light, one to turn the light on, and one to slew the search light to the desired position.
2, one on/off switch, and one to select IR.1414. What does the term semi-monocoque mean?The skin of the aircraft provides all of the structural strength
The aircraft skin provides none of the structural strength
The aircraft skin provides some of the structural strength
None of the above
1515. The TH-67 intermediate section uses a ____ type of construction.semi-rigid
semi-flex
semi-monocoque
monocoque1616. Which section of the aircraft contains the engine?A. The forward section
B. The cabin section
C. The engine/transmission section
D. The intermediate section1717. The TH-67 tail boom section uses ___ ______ type of construction.semi monocoque
partial monocoque
fully monocoque
semi rigid1818. State the purpose of the vertical fin.Provides vertical stability on the x-axis
The vertical fin, being displaced (canted) 5 degrees to the right thus reducing the tail rotor thrust requirements in forward flight
Off-loads the tail rotor between 80 and 100 knots
Provides vertical stability on the yaw axis19State the purpose of the horizontal stabilizer.A. Maintains a desirable aircraft attitude through the high end of the airspeed range. The metal strip at its leading edge provides for autorotational stability.
B. Provides pitch (up and down) about the lateral axis
C. Provides horizontal control of the aircraft during low G maneuvers.
D. None of the above2019. At what airspeed is the tail rotor fully off-loaded in forward flight?Between 110 and 130 knots
Between 90 and 120 knots
At 100 knots
Between 100 and 110 knots2120. The nomenclature of the TH-67 power plant is the model _______.T700-GE-401C
JP-WD40
PW-123-J
250-C20J2221. State the maximum torque available (MAX TQ AVAIL).107% TQ for 15 seconds max
100% TQ for 5 minutes max
>85% to 100% for 5 minutes max
100% TQ for 5 seconds max2322. State the maximum continuous power (TQ AVAIL CONT) of the TH-67 power plant.85% TQ (270 SHP) no time limit
85% TQ (270 SHP) take-off power range 5 minute limit
>85% to 100% TQ maximum
100% TQ no time limit2423. Can the maximum transient power setting (110% TQ) be used intentionally?Yes, 5 minutes limit
Yes, 5 seconds limit
No, only when executing high G maneuvers
No, intentional use is prohibited2524. State the diameter of the TH-67 main rotor.52 4
42 4
33 4
44 32625. What type of airfoil is the main rotor blade?A honey comb airfoil
A symmetrical airfoil
An asymmetrical airfoil
None of the above
2726. How many degrees of twist are there in the main rotor blade?A positive 10 degrees
A negative 5 degrees
A positive 5 degrees
A negative 10 degrees2827. State the tail rotor diameter.5 10
4 5
5 5
8 52928. How many degrees of pitch are in the tail rotor with full left pedals applied?25 degrees
23 degrees
17 degrees
21 degrees
3029. State the TH-67 Vne122 knots
78 knots
130 knots
100 knots
3129. State the maximum airspeed limitation with >85 to 100% TQ applied.78 knots
110 knots
80 knots
122 knots3231. State the minimum rate of descent airspeed in autorotation.A. 50 knots @ 394 RPM (100% rotor RPM)
B. 69 knots @ 394 RPM (100% rotor RPM)
C. 52 knots @ 394 RPM (100% rotor RPM)
D. 60 knots @ 394 RPM (100% rotor RPM)3332. State the maximum glide distance airspeed in autorotation.69 knots @ 394 RPM (100% rotor RPM)
79 knots @ 394 RPM (100% rotor RPM)
52 knots @ 394 RPM (100% rotor RPM)
60 knots @ 394 RPM (100% rotor RPM)3433. State the minimum crew restriction VFR and IFR.VFR minimum 1 pilot, IFR minimum 1 pilot and 1 observer
VFR minimum 2 pilots, IFR minimum 1 pilot
VFR minimum 1 pilot, IFR minimum 2 pilots
VFR minimum 1 student, IFR minimum 1 student and 1 pilot
3534. State the fuel capacity of the TH-67 fuel cell.69.4 U.S. gallons total; 64.2 U.S. gallons useable; 2.3 U.S. gallons unusable
81.4 U.S. gallons total; 64.2 U.S. gallons useable; 1.5 U.S. gallons unusable
69.4 U.S. gallons total; 68.2 U.S. gallons useable; 1.3 U.S. gallons unusable
84.1 U.S. gallons total; 82.6 U.S. gallons useable; 1.5 U.S. gallons unusable
3635. Why must the engine oil system be drained and refilled if transmission and engine oils are intermixed?To prevent chemical reaction
To prevent damage to the engine oil seals
If the two are mixed they become very flammable
To prevent damage to the transmission3736. In a conventional helicopter, what are the three basic flight controls that are used to maneuver the aircraft?Throttle, stick, rudder
Cyclic, stick, collective
Cyclic, collective, tail rotor (anti-torque) pedals
Stick, elevator, vertical fin3837. In a conventional helicopter, which flight control directs the total lift/thrust of the main rotor system?The collective
The stick
The pedals
The cyclic 3938. Which conventional helicopter flight control will input a pitch change to all main rotor blades simultaneously regardless of the blades position?Cyclic
Rudder
Collective
Stick4039. In a conventional helicopter, the rotation of the main rotor induces a force known as torque. Describe the effects this force has on the fuselage.The torque force will cause the fuselage of the aircraft to rotate in the same direction of the main rotor
The torque force will cause the fuselage of the aircraft to rotate in the opposite direction of the main rotor
No effect is observed since rotor torque and fuselage torque will be equalized
None of the above
4140. State the primary purpose of the tail rotor system in a conventional helicopter.Provides directional control
Yaws the aircraft
To counter-act the torque effects of the main rotor
Provides right and left inputs on a hover4241. The ___ ____ controls will provide directional control (heading) of the aircraft during hovering, as well as trimming the fuselage of the helicopter at higher speeds.Cyclic pedals
Stick pedals
Tail rotor
A and B4342. Cyclic control inputs (fore/aft and lateral) are considered independent up to the _____ ______ from there on up to the non-rotating swash plate they are considered ______.intermixing bellcrank, coordinated
self adjusting controls, manual
intermixing push rods, coordinated
self input controls, manual
4443. In the VFR configuration, what happens to the pilots cyclic stick if left unattended when the copilots cyclic stick is removed?Nothing, there is no difference with both or just one cyclic stick installed/removed
The reduced load on the balance spring will cause the pilots cyclic stick to creep aft slightly
If this situation is encountered you must not go flying do to lack of controls on the aircraft
You must maintain right cyclic input to counteract for the missing copilots cyclic stick4544. Where is the cyclic friction knob located?Right on the base of the copilots cyclic stick
There is not such thing installed in the TH-67 helicopter
In between the pilot and copilot seat
Left of the base on the pilots cyclic stick4645. How much preload is on the cyclic system with the aircraft running and the hydraulics on?2 to 3 pounds preload
1 to 1 pounds preload
2 to 4 pounds preload
to 1 pound preload
4746. Which aircraft configuration has the force trim system?VFR only
IFR only
A+ only
All of the above4847. What switches are located on the pilots collective stick control head?On/off switch, landing light, fuel start
Search light switches, landing light, governor RPM increase/decrease, and the starter button
There is no switches on the pilots collective stick; all switches are located on the copilots collective stick
Fuel valve switch, landing light, starter button, and hover button
4948. Where is the collective friction located?It is located on the right of the copilots collective stick base
Right behind the pilots anti-torque pedals
It is located on the left of the pilots collective stick base
No such thing installed in the TH-67 helicopter5049. What switches are located on the co-pilots collective control head?The search light switch, landing light, governor RPM increase/decrease, and the starter button
Fuel valve switch, throttle switch, landing light, and hover switch
There is no c0-pilot collective control head
Eject switch, landing light, fuel valve switch, and avionics5150. What amount of collective control preload is built into the collective flight control system?2 to 4 pound preload
1 to 3 pound preload
4 to 6 pound preload
3 to 5 pound preload5251. Which collective control stick is removable and why?The co-pilots collective stick is removable in case a non-rated passenger is flown in the co-pilots seat
The pilots collective for egress purposes
Neither the pilot or co-pilots collective stick can be removed unless is for maintenance reasons only
None of the above5352. Which direction can the tail rotor pedals be adjusted?Forward only
Aft only
Pedals are fixed and can not be re-adjusted
The pedals can be adjusted fore and aft5453. What changes the pitch (angle-of-attack) in the tail rotor through the lever assembly?The pitch horn
The tail rotor bell cranks
The pitch change links
The anti-torque pedals
5554. What is the preload on the tail rotor system?1 to 3 pounds preload
3 to 5 pounds preload
2 to 5 pounds preload
4 to 5 pounds preload5655. Does the tail rotor system have hydraulic assist?The tail rotor system does not have hydraulics
Yes
Yes, but only in the retreating blade to prevent tail vibrations
None of the above
5756. The TH-67 flight control system can best be described as ____ ____ ____ with hydraulic assist.fully articulated links
hydro mechanical linkages
direct mechanical linkages
articulated mechanical links
5857. The purpose of the hydraulic servo actuator installed to the cyclic and collective controls is to convert ____ ____ under pressure into ____ ____ work.JP-8 fuel, carbon monoxide
hydraulic fluid, useful mechanical
servo fluid, useful mechanical
Hydraulic fluid, control movement
5958. The TH-67 hydraulic pump is a constant ____, _____ delivery system component providing 600 +/- 25 psi, and _____ GPM flow rate.pressure, variable, 1.9
flow, direct, 2.3
pressure, flow, 1.2
flow, pressure, 1.9
6059. The purpose of the differential release valve is to reduce ____ ____ ____ when rotor loads are increased due to high G maneuvers or flight into turbulence.rotor centrifugal forces
transmission high speeds
engine high speeds
pressure build up
6160. With regard to cyclic input, does the blades position in the plane of rotation matter?No
Only during forward flight
Yes, the desired input does not occur until the blade is positioned exactly 90 earlier in the plane of rotation (phase lag)
Only during right side flight above 20 knots6261. What drives the rotating swash plate?The transmission
The power turbine
The connection of the collar set and idler lever/link assembly to the rotating swash plate
The rotating scissors 6362. What is another name for the collar set and idler lever/link assembly?The drag link assembly
The rotating link assembly
The rotating swash plate link
None of the above6463. What connects the rotating swash plate to the pitch change horn?The pitch control rods (PCR)
The pitch change tubes
The swash plate tubes
The pitch horn tubes6564. What type of rotor system is used on the TH-67 helicopter?Fully articulated rotor system
Fully aerobatic rotor system
Rigid, semi-articulated rotor system
Semi-rigid, under slung rotor system6665. How is the rotor system attached to the mast?It is attached to the mast by 4 grade 1172 steel bolts
The rotor system is attached to the mast by means of bolts, washer, and nuts
The rotor system is attached to the mast by a splined trunnion
None of the above
6766. What is the definition of a trunnion?A component that holds things together
The act of bringing two objects of dissimilar shapes to form one
A component that allows rotation and tilt
To turn or to be turned 6867. What is the purpose of the yoke?Attaches the main rotor and main transmission to the hub
To support the main rotor system and serves as the pitch change axis
Sends a signal to the cockpit to let the pilot know of exact angle of pitch in the main rotor blades
A and C6968. How is the trunnion attached to the yoke?The trunnion is attached to the yoke by pillow blocks
The trunnion is attached to the yoke by 2 high impact type 117 grade steel bolts
The trunnion is attached to the yoke by the go/no-go fly wheel assembly
The trunnion does not attached to the yoke by any means. They are two separate systems independent of one another7069. What kind of balancing requires lead weights to be added to the blade retention bolt?Trailing edge balancing requires lead weights to be added to the blade retention bolts
Sprout rigging balancing requires lead weights to be added to the blade retention bolts
WARNING. Never add weights to the blade retention bolts
Spanwise (root to tip) balancing requires lead weights to be added to the blade retention bolts7170. What distributes the centrifugal load from the blade grip to the yoke?The under-slung design of the TH-67 rotor system
The yoke centrifugal bearings
Tension torsion straps
The is no centrifugal force load from the blade grip to the yoke7271. What structural members make up the main rotor blade?The titanium spar, the chamber, and the trailing edge
The aluminum spar, the spar closure, and the trailing edge
The titanium spar, the spar closure, and the trailing edge
Aluminum, honey comb, and titanium7372. Weights are added at the factory at the time of manufacturing to control the undesirable twisting associated with asymmetrical airfoils and to preserve favorable aerodynamic characteristics.True
False7473. Why does the main rotor blades have a negative 10 twist?The negative twist is designed to equalize lift during autorotation
The negative twist is designed to prevent turbulence during high power/high G maneuvers
There is no negative twist on the main rotor blades
The negative twist is designed to equalize lift along the blade span (length)7574. The droop snoot is known for what aerodynamic characteristics? The droop snoot design is noted for a wide thrust margin for maneuverability and high efficiency during forward flight
The droop snoot design is noted for a wide thrust margin for maneuverability and high efficiency during hovering
The droop snoot design is noted for a wide thrust margin for maneuverability and high efficiency during turns
The droop snoot design is noted for a wide thrust margin for maneuverability and high efficiency during autorotation7675. How many trim tabs are there on the main rotor blade?Two trim-tabs, one for adjusting A+ vibrations and the other one to adjust B+ vibrations
Just one trim-tab
Three trim-tabs, one for adjusting the inner blade track, a second for the middle blade track, and a third for the outer blade track
Two trim-tabs, one for adjusting the inner blade track, and a second trim-tab is used to adjust the outer portion of the blades track7776. What are doublers used for on the main rotor blade?They are applied at the blades root to sustain the shearing force caused by the centrifugal force occurring at the blade retention bolt
Used to equalize lift along the blade span (length)
They are designed to stop excessive droop (lower motion of the blade) and conning (upper movement of the blade)
Doublers are used on the main rotor to reduce main rotor vibrations during slow autorotations
7877. What is the purpose of the flap restraint kit?Its purpose is to limit flapping during autorotations
Its purpose is to limit flapping during high power maneuvers
Its purpose is to limit flapping during startup and shutdown
The is no flap restraint system installed on any under-slung rotor system7978. At what RPM is flapping limited to 6 maximum?At 90% N2 and below
At 97% N2 and below
At 25% N2 and below
At 31% N2 and below8079. At what RPM is the flapping angle no longer limited?Above 31% N2 RPM
Above 85% N2 RPM
Above 90% N2 RPM
Above 25% N2 RPM8180. How is the tail rotor assembly mounted to the tail rotor output shaft?It is mounted to the tail rotor output shaft by a quick disconnect fitting
It is mounted to the tail rotor output shaft by a splined trunnion
It is mounted to the tail rotor output shaft by two crossheads bolts
It is mounted to the tail rotor output shaft by a spherical bearing8281. How does the tail rotor system compensates for dissymmetry of lift?The tail rotor assembly compensates for dissymmetry of lift through the chordwise hinge by allowing the blade to feather as it flaps
The tail rotor assembly compensates for dissymmetry of lift through the trunnion hinge by allowing the blade to feather as it flaps
The tail rotor assembly compensates for dissymmetry of lift through the crosshead hinge by allowing the blade to feather as it flaps
The tail rotor assembly compensates for dissymmetry of lift through the delta hinge by allowing the blade to feather as it flaps8382. What are the washers on the blade bolts used for?They are used for preventing corrosion from dissimilar metals
They are used for counter weight
They are used for spanwise balancing
None of the above8483. What are the rectangular weights and washers on one end of the trunnion used for?They are used for chordwise balance
They are used for spanwise balance
They are used for trailing edge balance
They are used for leading edge balance8584. What are the nut, bolt, and washer(s) used for on the dynamic balance wheel?They are used to eliminate high frequency vibrations and to assist in spherical and chordwise balance
They are used to eliminate high frequency vibrations and to assist in spanwise and trailing edge balance
They are used to eliminate high frequency vibrations and to assist in spanwise and chordwise balance
None of the above8685. Where are the weights that are added at the factory located?They are located on the outboard trailing edge and the blade tip
They are located on the inboard trailing edge and the leading edge
They are located on the inboard trailing edge and at the blade tip
None of the above
8786. What are the washers on the pitch horns used for?They are used as aerodynamic balance during steep turns/high G maneuvers
There are no washers installed on the pitch horn
They are used as aerodynamic balance to eliminate pedal creep
They are used for spanwise balancing 8887. The TH-67 engines rated shaft horsepower is de-rated for _____ ______. 100% TQ
85% TQ
Transmission compatibility
Turbine comapatibility
8988. The statement that best describes the TH-67 engine is Internal combustion gas turbine featuring a ______ ______ ______.free gas turbine
free power turbine
reverse combustion chamber
compressor discharge tube9089. What are two advantages of a free turbine?Reduces cost throughout the Army, and since is free it does not require calibration every 1,000 hours of flight
Provides reduced load for starting , and each turbine operates at optimum RPM capacity
No mechanical connection between the gas turbine thus reducing friction and loss of power, and they can be operated independently of each other
No cost to the Army, and they are light weight9190. The purpose of the Air Barrier Filter is to provide clean ______ air to the engine.particle-free
fresh
cool
All of the above9291. Will the engine air be filtered if the ENG ALT AIR switch is placed in the open position?Yes, but only 39% of the air passing through will be filtered
No such switch installed in the TH-67 helicopter
Yes, when the air filtered is bypass, filtered air will still be going into the engine through the secondary filtration system
No, when the air barrier filter is bypass, unfiltered air will be going into the engine9392. What indication will the pilot receive when the air barrier filter is blocked/clogged?The FILTER CLOGGED caution light will illuminate
The HIGH INLET PRESSURE caution light will illuminate
The LOW INLET PRESSURE caution light will illuminate
There is no indication sent to the cockpit for this condition9493. What are the four sections of the model 250-C20J turbine engine?Intake, compressor, combustion, and exhaust section
Power turbine, combustion chamber, exhaust, and ignition section
The compressor, power and accessory gearbox, turbine, and combustion section
The stator vanes, the rotating vanes, the centrifugal stage, and the impeller section9594. What does the bleed air control valve do?It aids in rapid engine acceleration and helps prevent compressor stalls
It controls the amount of bleed air needed for cabin/cockpit heating
It controls bleed air for de-icing of the compressor inlet vane
Both B and C9695. What are the five customer bleed air ports on the diffuser scroll?Anti-icing, vent and cap, discharge air, exhaust holes, and PC filter
The engine anti-ice valve, bleed air control valve, two cabin heat ports, and PC air filter
Two cabin heat ports, cockpit heat port, and the PC air filter
None of the above9796. What is the purpose of the cap on the rear diffuser vent and cap?To increase air pressure on one side of two labyrinth seals as the compressor experiences wear.
To equalize the high pressure between the diffuser and the compressor section
To prevent Foreign Object Damage (FOD) from entering the diffuser
Vents out high pressure from the diffuser and redirects it to the compressor9897. The compressor consists of how many and what kind of compressor stages?It consists of four axial stages and one centrifugal stage
It consists of five axial stages and two centrifugal stage
It consists of five axial stages and one centrifugal stage
It consists of six axial stages and one centrifugal stage
9998. On a standard day the airs temperature increases to approximately ___ F by the time it goes through the seventh stage of compression.1270
456
502
52010099. What are the only items provided with anti-icing capability?The engine inlet, and the windshield
The windshield, and the main rotor blade leading edge
Both, main and tail rotor blades leading edges
The front support hub and the seven inlet guide vanes101100. Should the bleed-air control valve be opened or closed on preflight?The bleed-air control valve SHALL be closed on preflight or maintenance action is required
This valve can not be seen unless parts from the engine are removed during major overhaul to the engine
The bleed-air valve SHOULD be closed on preflight or maintenance action is required
The bleed-air valve SHALL be open on preflight or maintenance action is required
102101. When does the spark cease to exist in the combustion section of the engine?When N1 reaches 90% RPM
When N2 reaches 90%
When the starter button is released
The spark never ceases unless there is a failure of the exciter box or engine tachometer generator103102. What is the temperature of the flame in the combustion section of the engine?Approximately 4500 F
Approximately 5500 F
Approximately 3500 F
Approximately 2500 F
104103. What is the melting point of titanium?3200 F
220 F
320 F
2200 F105104. How much of the compressed air is used for combustion?Approximately 20 to 25%
Approximately 50 to 60%
Approximately 70 to 80%
Approximately 80 to 95%
106105. T or F Approximately 75 to 80% of the air is used to cool and center the combustion flame plus drive the five customer bleed-air accessories.False
True107106. What principle takes advantage of impact and reaction forces?Newtons third law of action and reaction
Newtons first law of inertia
The gas turbine principle
The action reaction principle108107. Changes in ____ ______ cause changes in fuel flow.power settings
wind conditions
pressure altitude
high temperature 109108. Changes in fuel flow will cause changes in _______ of the gases entering the turbine rotors.flow
cooling
temperature
expansion
110109. Combustion gases impact the gas producer and the turbine rotors inducing _____________________.rotation of the compressor
rotation of the accessory gearbox
rotation of the free wheeling unit
rotation of the turbine shaft111110. An increase in expansion rate/velocity induces an increase in _____ that is transmitted through the N2 gear train as measurable _______.air, RPM
torque, horsepower
fuel, shaft torque
fuel, horsepower112111. Which section of the engine is the primary structural member of the engine?The power and accessory gearbox section
The compressor section
The combustion section
The power turbine section113112. What is designed to reduce the high RPM required for horsepower development to more practical RPM at the accessory output pads?The reverse flow combustion chamber
Electrical motors dedicated just to the accessory output pads
Two separate gear trains (N1 and N2)
The N1 tachometer and the N2 tachometer114113. Which section of the engine is driven by the gas producer gear train?The oil cooler section is the only section driven by the N1 gear train
The combustion section is the only section driven by the N1 gear train
The turbine section is the only section driven by the N1 gear train
The compressor section is the only section driven by the N1 gear train115114. The fuel pump, gas producer fuel control, starter/generator, oil pump, tachometer generator, and the standby generator (only on the IFR configuration) are driven by what gear train?N2 gear train
N1 gear train
Both, N1 and N2 gear trains
None of the above116115. The freewheeling unit, the torque meter, the governor, and the tachometer generator are driven by what gear train?N1 gear train
N2 gear train
Both, N1 and N2 gear trains
None of the above117116. The N1 and N2 tachometer generators produce what kind of voltage?Direct Current (DC) voltage
Alternate Current (AC) voltage
The N1 DC voltage, and the N2 AC voltage
The N1 AC voltage, and the N2 DC voltage
118117. The starter portion of the starter/generator is used to crank the ____ _____ _____ during the start sequence.N2 gear train
engine combustion section
N1 gear train
accessory gear box 119118. The generator portion of the starter/generator provides ____ ____ voltage to all of the helicopters electrical systems plus it re-charges the ___ _____.alternate current, main battery
direct current, standby battery
direct current, main battery
alternate current, standby battery120119. How are the gas producer fuel control and the governor integrated?They are integrated by pneumatic connections
They are integrated by mechanical connection
They are integrated by hydro mechanical connections
They are integrated electrically121120. What is the purpose of the burner drain valve?To burn fuel that remains on the outer combustion case
To drain unburned fuel from the combustion chamber back to the fuel tank
To allow unburned fuel to drain from the outer combustion case
None of the above
122121. The purpose of the dual accumulator-double check valve is to ____ _____ ______ from the main rotor system.reduce the vibrations
dampen torsional vibrations
maintain CG balance
None of the above123122. Where is the combustions gas temperature measured on the C20-J turbine engine?Right before the N1 rotor
Right after the gas passes by the N2 rotor
Right in between the N1 and the N2 rotors
A and B124123. Where is the engine oil temperature measured? At the combustion chamber #7 bearing solenoid
It is measured as the oil leaves the bottom of the engine oil reservoir
It is measured by a wet line (direct oil pressure)
By a wet line (direct pressure reading)
125124. How is the engine oil pressure measured?It is measured in PSI by a dry line
It is measured in PSI by the transmission pressure gauge
It is measured by a wet line (direct oil pressure)
It is measured as it passes through the #2 and #7 bearing126125. How is the engine torque measured?By a wet line (direct pressure reading)
By the difference in pressure from the sump and the pump
It is measured by a wet line (direct oil pressure)
None of the above127126. Which engine bearings are externally lubricated?Bearings 1, 2, 5, and 8
Bearings 5, 6, 7, and 8
Bearings 2, 2 , 6, 7, and 8
Bearings 1, 6, 7, and 8128127. How many engine oil chip detectors will activate the ENG Chip caution light?One (the accessory section chip detector)
One (the temp/chip detector)
Two ( the #1 and #2 chip detectors)
Two (the sump and the pump chip detectors)129128. The auxiliary oil filter has a pop-up feature that activates at __ PSID.17
10
7
40130129. After completing lubrication, oil is scavenged into a sump below the number __ and __ bearings and at the bottom of the gear case.2, 2
3, 4
5, 6
6, 7131130. How many engine oil bypasses are there?There are 4 bypasses. Auxiliary oil filter (10 PSID), oil cooler (thermal bypass below 81 C or 178 F), oil cooler (40 PSI clogged oil cooler), and internal oil filter (150 PSID)
There are 4 bypasses. Auxiliary oil filter (7 PSID), oil cooler (thermal bypass below 81 C or 178 F), oil cooler (40 PSI clogged oil cooler), and internal oil filter (105 PSID)
There are 4 bypasses. Auxiliary oil filter (10 PSID), oil cooler (thermal bypass below 81 C or 178 F), oil cooler (40 PSI clogged oil cooler), and internal oil filter (105 PSID)
There are 4 bypasses. Auxiliary oil filter (10 PSID), oil cooler (thermal bypass below 81 F), oil cooler (40 PSI clogged oil cooler), and internal oil filter (105 PSID)132131. How many wet lines are there associated with the engine oil system?Three (the engine oil pressure, and torque meter gauges, and the transmission oil pressure gauge)
Two (the engine oil pressure, and the transmission oil pressure gauge)
Two (the engine oil pressure, and the torque meter gauges)
Three ( transmission oil and pressure gauges, and the torque meter gauge)133132. Is defined as a decrease in N2 RPM that exists between the time a demand for power is made and the time that power is delivered?Spike knock
Mast bumping
Droop
Flapping stop134133. Is droop allowed to exist?No, INTENTIONAL USE IS PROHIBITED
Yes, 5 minute limit
Only momentarily, otherwise rotor RPM may become critically low
Yes, but rotor RPM must be at 107% RPM to compensate for droop
135134. How is droop compensated for?By lowering the collective, and turning the engine anti-ice and heater switches off
Once droop is encounter you must wait until the aircraft recovers from it
Through mechanical linkages (collective stick to governor lever), electrical connections (governor increase/decrease switch and linear actuator motor), and a pneumatic signal between the N2 governor and the gas producer fuel control passing through the dual accumulators and double check valve
By lowering the collective and maintaining 107% max RPM
136135. Why is the engine mounted horizontally behind the transmissionTo simplify the drive system, improve the air intake/exhaust arrangement, and to reduce cabin noise
All helicopter must have the engine horizontally mounted for weight and balance purposes
By the engine being mounted horizontally it will improve the autorotational capability by 40%
For no particular reason, its just the way the engineers wanted it mounted137136. How are three bipod mounts used to secure the engine?Semi-rigid
Flexible for vibration reduction
Rigidly
None of the above138