th-67 systems

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


An optional procedure

Recommended or preferred, not mandatory55. Define the term SHOULDRecommended or preferred, not mandatory

An optional procedure


An operating procedure, condition, etc., which is essential to highlight66. Define the terms MAY or NEED NOTIndicated futurity


A condition that you may do or not

An optional procedure77. Define the term WILLAn optional procedure

Indicates futurity


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



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


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



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



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%



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 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


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

th-67 systems

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