TH-67 Systems

TH-67 Systems

TH-67 SystemsStudy Guide

(Power Train, Electrical, Fuel Systems, and Weight and Balance)

11. State the purpose of the power train system?Provides drive for the tail rotor

Supports the rotor head

Provides a means of transmitting engine power to the main and tail rotor systems

All of the above22. State the purpose of the freewheeling unit/sprag clutch assembly?It prevents main drive shaft failure by acting as a freewheeling unit when the rotor is subject to high Gs

The sprag clutch, in the freewheeling unit, provides a disconnect from the engine enabling autorotational forces to drive the transmission, tail rotor, and all transmission mounted accessories in the event of an engine failure

The sprag clutch transfers transmission RPM (inflow of air through the rotor system) to the freewheeling unit to drive the tail rotor

B and C33. What is the lubrication source for the freewheeling unit?The freewheeling unit is lubricated by the engine

The freewheeling unit is lubricated by the hydraulic to oil heat exchanger behind the transmission

The freewheeling unit is a dry system thus it uses ambient air to cool down

The freewheeling unit is lubricated by transmission oil44. Does the freewheeling unit have a chip detection capability?No, the chip detector is not electrically wired for a Caution Light indication in the cockpit, thus is not consider a chip detection system

Yes, but the chip detector is not electrically wired for a Caution Light indication in the cockpit

There is no chip detector installed in the freewheeling unit (no gears)

Yes, the chip detector is electrically wire to the cockpit for a Caution Light indication to alert the pilot55. What does the main drive shaft connect ?It is a flexible coupling that connects the freewheeling unit to the transmission input drive

It connects the transmission to the rotor head

It connects the #5 drive shaft to the tail rotor gear box

None of the above66. Why is the main drive shaft a flexible coupling?Flexible is better

The engine is going to provide the transmission with different kinds of power settings, thus the need for a flexible and adaptable coupling is required

The movement between the transmission (a floating pylon mount) and the freewheeling unit mounted on the engine (a rigid mount) requires a flexible coupling

It must be flexible because of the high vibration from the tail rotor that are transmitted back to the main rotor during autorotation77. In the event of an engine failure, what drives the tail rotor in autorotation?The main drive shaft transfers transmission RPM (inflow of air through the rotor system) to the freewheeling unit and crosswinds provide drive to the tail rotor

The main drive shaft transfers transmission RPM (inflow of air through the rotor system) to the freewheeling unit to drive the tail rotor

The only thing that drives the tail rotor is the engine and if engine failure occurs the helicopter will enter an uncontrolled spin to the right

Autorotate when over a safe landing area

88. What mounting technique is used to secure the transmission to the airframe?A rigid mounting technique

An isolation mounting technique (it is not rigidly mounted)

Rubber mount technique

By the drag pylon technique (spike knock)99. What is the purpose of the pylon support links?To mount the transmission to the airframe and bear the aircrafts weight

To support the flight control pylon and all related equipment

To absorb negative Gs during descents grater than 2,000 FPM

All of the above1010. What effects does a focused pylon mount have on the transmission?It rises the CG of the transmission. This reduces the transmissions movement

It moves the CG of the transmission 5 inches forward. This reduces the transmissions movement

It moves the CG of the transmission 5 inches aft. This reduces the transmissions movement

It lowers the CG of the transmission. This reduces the transmissions movement1111. Why is the transmission mounted with a 5 forward tilt?To provide a more desirable attitude during a hover

To provide a more comfortable attitude in forward flight

To provide a forward tilt of the main rotor to assist the pilot on forward flight at airspeeds above 100 KIAS

The tilt is 5 aft rather than forward and is to maintain a more comfortable attitude in forward flight1212. Why is the transmission mounted with a 1.25 tilt to the left?Because of the position of the cyclic no matter if the pilot is right or left handed, it is designed for a right handed person. The tilt is built for those left handed pilot to reduced their constant cyclic input

There is no left or right tilt on the main transmission system

To help compensate for translating tendency

To help compensate for dissymmetry of lift

1313. What does a rubber isolation mount provide?It provides for lateral centering and shock absorption

It provides for longitudinal centering and shock absorption

There is no rubber on the transmission system due to high temperatures

A and B1414. What does the drag links round pin and the pylon stops square hole provide?Centering of the transmission during installation

It provides for fore/aft/side to side movement to the desired limits

Stops high vibration frequency coming down the cabin

Positive travel limits for the pylon1515. Where does the TRANS OIL TEMP caution light get its information?From the thermostat installed on the return line going to the oil cooler

From the switch located on the transmission oil filters housing

From the sump of the transmission

From a thermo bulb/transducer on the oil filters housing1616. Where does the transmission oil temperature gauge get its information?From the switch located on the transmission oil filters housing

From the transmission oil sump

From a thermo bulb/transducer on the oil filters housing

From the thermal difference of the transmission oil cooler in and out lines1717. Does the transmission oil cooler have a bypass capability?The transmission oil cooler has a thermal bypass at temperatures below 61 C. Above 81 C the bypass valve closes and the oil must be cooled.

The transmission oil cooler has a thermal bypass at temperatures below 81 C. Above 71 C the bypass valve closes and the oil must be cooled.



1818. How is the transmission oil cooled?There is and outer case of the transmission that is filled with water and serves as heat exchange, from there goes back to the oil cooler

A flexible duct/hose assembly transports cooling air from the engine oil cooler housing to the transmission oil cooler where some air about to cool the transmission oil is scavenged to cool the hydraulic reservoir

It is cooled by ambient air

The transmission is splash lubricated and the oil heat is dissipated as it splashes reducing the heat on the oil1919. How many chip detectors are there on the transmission oil system?There are 2 transmission chip detectors (sump and pump) on the oil system

There are 3 transmission chip detectors (sump, pump, chip pan) on the oil system

There are 4 transmission chip detectors (sump, pump, chip pan, and freewheeling unit) on the oil system

There are 5 transmission chip detectors (sump, pump, chip pan, freewheeling unit, and the floating gear) on the oil system2020. How many chip detectors are there on the transmission that can activate the TRANS CHIP caution light?There are 5 transmission chip detectors (sump, pump, chip pan, freewheeling unit, and the floating gear) that can activate the TRANS CHIP caution light

There are 4 transmission chip detectors (sump, pump, chip pan, and freewheeling unit) that can activate the TRANS CHIP caution light

There are 3 transmission chip detectors (sump, pump, chip pan) that can activate the TRANS CHIP caution light

There are 2 transmission chip detectors (sump and pump) that can activate the TRANS CHIP caution light

2121. Where is the transmission oil level sight glass located?The sight glass is located on the back side of the transmission

The sight glass is located on the front side of the transmission

The sight glass is located on the left side of the transmission

The sight glass is located on the right side of the transmission

2222. What are the three splined areas on the mast?The mast is splined to the planetary gear case, the floating gear, and the yoke

The mast is splined to the planetary gear case, the collar set, and the trunnion

The mast is splined to the planetary gear case and the trunnion

The mast is splined to the trunnion yoke2323. Why is the mast hallow?It is cheaper than a solid mast

High frequency vibrations are less because the vibration travels less through the air inside the hallow mast

A hallow mast is stronger, flexible, and lighter weight

The mast is solid for maximum strength and durability2424. How many tail rotor drive shaft segments are there?There are five tail rotor drive shaft segments. Two are made of steel, and three are aluminum alloy.

There are eight tail rotor drive shaft segments. Two are made of iron, and six are titanium alloy.

There are six tail rotor drive shaft segments. Two are made of steel, and six are aluminum alloy.

There are eight tail rotor drive shaft segments. Two are made of steel, and six are aluminum alloy.2525. How many tail rotor drive shaft segments are on top of the tail boom section of the aircraft?Four of the eight tail rotor drive shaft segments are on top of the tail boom

Five of the eight tail rotor drive shaft segments are on top of the tail boom

Six of the eight tail rotor drive shaft segments are on top of the tail boom

Seven of the eight tail rotor drive shaft segments are on top of the tail boom

2626. What are the hanger bearing assemblies used for?Hanger-bearing assemblies are used to support the tail rotor to the tail boom

Hanger-bearing assemblies are used in Army helicopter hangar doors to assist maintainers when opening and closing the doors

Hanger-bearing assemblies are used to support the drive shaft and maintain drive train alignment in its position over the tail boom

B and C2727. What is used to connect a drive shaft segment to another component?Disc couplings are used at every drive shaft connection to provide a strong yet flexible connection requiring no lubrication

Flexible couplings are used at every drive shaft connection to provide a strong yet flexible connection requiring no lubrication

Thompson couplings are used at every drive shaft connection to provide a strong yet flexible connection requiring no lubrication

Thomas couplings are used at every drive shaft connection to provide a strong yet flexible connection requiring no lubrication2828. Why are the indexing flats in Thomas couplings alternated?Alternating indexing flats helps with balancing of the drive shaft

Alternating indexing flats increases the tensile strength on the flexible couplings

A and B

There are no flats on the Thomas couplings

2929. What is used to prevent slipping when the last tail rotor drive shaft segment is attached to the tail rotor gearbox?A splined adapter is used to prevent slipping

A splined trunnion is used to prevent slipping

A splined yoke is used to prevent slipping

The delta hinge is used to prevent slipping

3030. Why are breather type filler caps used on the tail rotor gearbox?Breather type filler caps are used to let high pressure buildup in the tail gearbox escape

Breather type filler caps are used to prevent pooling and cavitation

Breather type filler caps are used to provide a mean to service the tail gearbox without removing the cap, thus preventing foreign object damage (FOD) to enter the system

All of the above3131. What caution light illuminates when ferrous metal particles complete the circuit on the tail rotor gearbox chip detector?The T/R particle caution light

The T/R complete circuit light

The T/R ship caution light

The T/R chip caution light3232. What is the rating of the SLAB battery?The SLAB battery voltage is 21 VDC 19 amps

The SLAB battery voltage is 24 VDC 17 amps



3333. Where is the battery switch (BATT/OFF) located?On the lower console

On the upper panel

On the battery panel

On the overhead console

3434. What recharges the battery?The standby generator recharges the battery in flight

The N2 tachometer generator recharges the battery in flight

The N1 tachometer generator recharges the battery in flight

The generator recharges the battery in flight3535. Can the batteries level of charge be checked during flight?No, there is no selection on the voltmeter selector switch that gives you this option

Only on the IFR version aircraft

Yes, the generator must be on as the battery switch is turned off. The drop observed on the load meter indicates how much of the generators load was devoted to recharging the battery

None of the above3636. What indicates a fully charged battery?During pre-flight the SLAB dip stick should be on the full line

During pre-flight you should see acid fluid through the sight glass in front of the SLAB (top line)

A drop of less that 1% indicates a fully charge battery

A rise of 1% or more indicates a fully charge battery3737. What a drop of 1% or more on the load meter indicates?It indicates that the battery is still charging

Indicates a fully charged battery

Indicates the thickness of the gauge

Battery life less than 30 minutes3838. What measuring gauge is used to measure 1%?The thickness of a nickel is the measuring gauge for 1%

The thickness of a dime is the measuring gauge for 1%

The thickness of a primary line is the measuring gauge for 1%

The thickness of a secondary line is the measuring gauge for 1%

3939. What does the starter component of the starter/generator do during the starting sequence?The starter component turns the N2 gear train to drive the accessories necessary for basic engine operation

The starter component turns the N1 gear train to drive the accessories necessary for basic engine operation

The starter component turns the power turbine train to drive the accessories necessary for basic engine operation

The starter component turns the Ng gear train to drive the accessories necessary for basic engine operation40 40. What does the generator component of the starter generator do after the engine is running?The generator provides 24 VDC to the aircrafts electrical circuits, plus it maintains charge of the main battery that is in the nose of the helicopter

The generator provides 22 VDC to the aircrafts electrical circuits, plus it maintains charge of the main battery that is in the nose of the helicopter



4141. How many buss bars are there in the VFR and A+ configuration?There are three main buss bars in the VFR and A+ configuration

There is one main buss bar in the VFR and A+ configuration

There are two main buss bars in the VFR and A+ configuration

There are four main buss bars in the VFR and A+ configuration4242. What is the purpose of a bus bar?A buss bar distributes electrical power

A buss bar protects circuits from over and under frequencies

A buss bar is a device which converts AC current to DC current

A buss bar connects to moving parts electrically 4343. What is the starter/generator rated at?The starter/generator is rated at 28 VAC and 105 amperes

The starter/generator is rated at 28 VDC and 150 amperes

The starter/generator is rated at 28 VDC and 105 ohms

The starter/generator is rated at 28 VDC and 105 amperes

4444. What are the power sources for starting the VFR and A+ configured aircraft?The 12 volts battery and the CPU

The battery in the nose of the aircraft and the auxiliary power unit

The starter/generator and the main battery

The main battery and standby battery4545. During normal operations, what are the power sources for the VFR and A+ configuration?The main generator is the primary source with the standby generator as a backup power source

The battery is the primary source with the standby battery as a backup power source

The main generator is the primary source with the battery as a backup power source

The ground power unit (GPU) and the main generator

4646. How long will the battery power the electrical systems after the generator has failed?30 minutes during the day and 10 minutes during the night

There are too many variables to predict battery life in terms of time after generator failure

With all essential electrical equipment on, about 25 minutes

With all nonessential electrical equipment off, about 45 minutes4747. How many direct current power sources are available for normal operations in the IFR configuration?Two (main generator and standby generator)

Two (main battery and standby battery)

Three (main generator, standby generator, and the standby battery)

Three (main generator, standby generator, and the main battery)4848. What is the rating of the standby generator? 24 VDC and 17 amperes

28 VAC and 15 amperes

28 VDC and 17 amperes

28 VDC and 15 amperes4949. What is the rating of the main battery in the nose of the helicopter?28 VDC and 15 amperes

24 VDC and 17 amperes

24 VAC and 17 amperes

28 VAC and 15 amperes5050. What does the Voltage Monitoring System allow the pilot to monitor?Allows the pilot to monitor generators, batteries, and buss bar voltage

Allows the pilot to switch from DC to AC current and to monitor generators, batteries, and buss bar voltage

A and B

None of the above5151. What does an inverter do?Sends a signal to the cockpit just before the helicopter reaching an inverted attitude

Converts DC voltage to 115 volts AC to run two elements of the avionics package

Following a Main Generator failure it will keep the battery charge for 30 minutes

None of the above5252. What is the rating of the standby battery?12 VDC

28 VDC

24 VDC

22 VDC5353. How many buss bars are there in the IFR configuration?There are two buss bars (ESS 1 and ESS 2)

There are four buss bars (ESS 1, ESS 2, NON-ESS, and SEMI-ESS)

There are three bus bars (ESS 1, ESS 2, and NON-ESS)

Only one buss bar (ESS 1)5454. Which buss bar is the most protected?The pilots buss bar (ESS 4)

The pilots buss bar (ESS 3)

The pilots buss bar (ESS 1)

The pilots buss bar (ESS 2)5555. Following the main generators failure (MAIN GEN FAIL) what powers the ESS 2 buss bar?The standby battery

The main battery

A and B

None of the above5656. Following a main generator failure (MAIN GEN FAIL) what powers the NON ESS buss bar?The main battery powers the NON ESS buss bar provided the NON ESS switch is placed in the NORMAL position; otherwise the NON ESS circuits are shed from the batterys load

The main battery powers the NON ESS buss bar provided the NON ESS switch is placed in the MANUAL position; otherwise the NON ESS circuits are shed from the batterys load

A or B

None of the above. In the event of main generator failure the only thing that is protected is the ESS 1

5757. In the IFR configuration, how many power sources are there for starting?There are three power sources (the main generator, main battery, and the standby generator) for starting

There are two power sources (the main battery, and the auxiliary power unit) for starting

There is one power source (the auxiliary power unit) for starting

There is one power source (the main battery) for starting

5858. In the event of dual generator failure (MAIN GEN FAIL and STBY GEN FAIL) and main battery power becomes depleted, what powers the standby attitude indicator?The main battery for at least 30 min

The back up battery for at least 30 min

The standby battery for at least 30 min

The secondary battery for at least 30 min5959. What airspeed should be avoided when the standby generator is powering the ESS 1 buss bar?Airspeeds above 122 KIAS

Airspeeds below 40 KIAS

Airspeeds above 50 KIAS

Airspeeds below 50 KIAS

6060. How many layers are there in the TH-67 fuel cell?The TH-67 fuel cell is a triple layer, crashworthy, bladder based on civilian aviation standards

The TH-67 fuel cell is a double layer, crashworthy, bladder based on civilian aviation standards

The TH-67 fuel cell is single layer, crashworthy, bladder based on civilian aviation standards

. The TH-67 fuel cell is a zero layer, crashworthy, bladder based on civilian aviation standards6161. What is the fuel cell capacity and how much of that capacity is consumable?The fuel cell capacity is 90.1 U.S. gallons of which 86.6 gallons are consumable

The fuel cell capacity is 84.1 U.S. gallons of which 72.6 gallons are consumable

The fuel cell capacity is 82.1 U.S. gallons of which 80.6 gallons are consumable

The fuel cell capacity is 84.1 U.S. gallons of which 82.6 gallons are consumable6262. What is the burn rate of the Allison C20J turbine engine?The burn rate is 22-26 gallons per hour

The burn rate is 20-29 gallons per hour



6363. How many boost pumps are there in the TH-67?3

1

2

46464. How many fuel quantity-sending units are there in the fuel cell?1

2

3

46565. What caution light illuminates with approximately 12 gallons of fuel remaining?12 GALLON light

Land ASAP light

FUEL LOW light

All of the above6666. What is the purpose of the fuel sump drain valve?Provides for the tacking of a fuel sample or defueling the aircraft

This valve prevents the grow of micro bacterial organisms in the fuel cell by venting the tank

This valve maintains the fuel cell at the correct fuel level when fueling the aircraft to prevent a rupture fuel cell during pressure fueling

A and C6767. Where is the fuel pressure transducer located and what does it do?It is located left side of the aircraft above the fuel filer cap. It converts a pressure head signal of the two boost pumps pressure and sends the higher reading to the fuel pressure gauge

It is located right side of the aircraft above the fuel filer cap. It converts a pressure head signal of the two boost pumps pressure and sends the higher reading to the fuel pressure gauge

It is located bottom of the aircraft fuel cell. It converts a pressure head signal of the two boost pumps pressure and sends the higher reading to the fuel pressure gauge

None of the above

6868. Where is the fuel shut-off valve located and what does it do?It is located in the cockpit on the pilot side right below the flight instruments and it will stop the flow of fuel when placed on the off position guard down

It is located at the extreme top-right portion of the fuel cell above the fuel filler cap. It stops the flow of fuel when the FUEL VALVE ON/OFF switch is turned off

It is located on the fuel cell and it will shutoff fuel to the engine in the event of a crash

It is located right side of the aircraft above the fuel filer cap. It converts a pressure head signal of the two boost pumps pressure and sends the higher reading to the fuel pressure gauge 6969. Where is the airframe fuel filter located and what does it advise the pilot of?It is located right side of the aircraft above the fuel filer cap. It converts a pressure head signal of the two boost pumps pressure and sends the higher reading to the fuel pressure gauge

It is located at the extreme top-right portion of the fuel cell above the fuel filler cap. It stops the flow of fuel when the FUEL VALVE ON/OFF switch is turned off

It is located on the right side of the engine compartment on the forward firewall. It advises the pilot of an impending airframe fuel filter bypass and that the fuel will continue to be delivered to the engine driven fuel pump

There is no airframe filters on the TH-67

7070. How is the fuel sump drain valve operated?Hydraulically

Electrically

Pneumatically

Mechanically7171. Where is the fuel sump drain valve located?Forward of the forward cross tube and centered laterally

Forward of the aft cross tube and centered laterally

Right below the #4 tail drive shaft section

On the bottom right below the filler cap7272. The fuel valve switch must be in which position for the fuel drain valve to operate?OFF

ON

STANDBY

ALTERNATE7373. When taking a fuel sample from the fuel cell, the fuel boost pump circuit breakers should be in which position?ALTERNATE to prevent water and sediment from circulating through the fuel system

STANDBY to prevent water and sediment from circulating through the fuel system

IN to prevent water and sediment from circulating through the fuel system

OUT to prevent water and sediment from circulating through the fuel system7474. Where will sediment and water be found in the fuel sample jar?Bottom of the jar

Top of the jar

Middle of the jar

Water in the bottom and sediment about the middle of the jar7575. Where is the fuel flow transducer located on the aircraft?It is located right side of the aircraft above the fuel filer cap. It converts a pressure head signal of the two boost pumps pressure and sends the higher reading to the fuel pressure gauge

It is located on the right side of the engine compartment near the aft firewall

It is located on the right side of the engine compartment on the forward firewall. It advises the pilot of an impending airframe fuel filter bypass and that the fuel will continue to be delivered to the engine driven fuel pump

Forward of the aft cross tube and centered laterally

7676. When is the fuel low warning indicating system activated?The fuel low warning system is activated when 35 minutes of fuel remains at the present consumption rate

The fuel low warning system is activated when 40 minutes of fuel remains at the present consumption rate



7777. The A/F FUEL FILTER caution light illuminates at ____ PSID and bypasses the filter at ___ PSID.2, 4

2, 4.5

1, 4.5

1, 47878. How many times is the fuel filtered before it is ignited?The fuel is filtered three times (A/F fuel filter, engine driven fuel pump, gas producer fuel control)

The fuel is filtered four times (A/F fuel filter, engine driven fuel pump, gas producer fuel control, and fuel nozzle)

The fuel is filtered two times (A/F fuel filter, engine driven fuel pump)

The fuel is filtered one time (A/F fuel filter)7979. A dual boost pump failure is indicated by ___________.A FUEL PUMP caution light and a little or no change in fuel pressure

A FUEL PUMP caution light and a fuel pressure drop to zero

FWD and AFT BOOST PUMP caution lights illuminated

Decreased fuel flow on the fuel management control box8080. A single boost pump failure is indicated by _________.A FUEL PUMP caution light and a fuel pressure drop to zero

FWD and AFT BOOST PUMP caution lights illuminated

A FUEL PUMP caution light and a little or no change in fuel pressure

Decreased fuel flow on the fuel management control box

8181. The ____________ responsibilities are to have a DD Form 365-4 F on board the aircraft when flying; ensure computations are accurate and correct; and to ensure the center of gravity remains between the allowable limits for the entire flight The student pilot

Your stick buddy

Pilot in command

Weight and balance technician8282. Class __ aircraft are those aircraft whose weight and center of gravity limits can readily be exceeded; therefore, a high degree of loading control is needed.1

2

3

48383. Is used to record any permanent changes in basic weight or center of gravity when the aircraft is modified.DA Form 2408-13-1

DD Form 365-3 Chart C

DD Form 365-4 Form F

TM 55-1500-342-238484. Can electronic data sheets be used in lieu of any of the DD Form 365 series forms?No, only paper copy allowed

Yes, provided the information is identical to that required on the DD Form 365 series forms

There are no electronic forms of DD Form 365 series forms

None of the above8585. Can the aircraft be flown if the aircrafts basic weight has been modified?Yes, provided the change in weight is less than 200 pounds

Yes, provided the change in weight is less than 100 pounds

The aircraft cannot be flown unless the change in basic weight is accounted for by the proper method

The aircraft can be flown but it must be weight and all forms updated prior to next day flight8686. How are permanent changes in basic weight accounted for?The pilot in command accounts for permanent changes by making an entry on DD Form 365-3 Chart C and creating new forms to replace the old forms

The weight and balance technician accounts for permanent changes by making an entry on DD Form 365-3 Chart C and creating new forms to replace the old forms

Manufacturer will come and weight the aircraft for any permanent changes in basic weight

Basic weight SHALL not be change under any circumstances

8787. How are temporary changes in basic weight accounted for?The pilot in command accounts for temporary changes in basic weight by using the data recorded on DA Form 2408-13-1 or 2408-14-1 to account for the temporary changes on the forms in the back of the logbook and flight planning area



Basic weight SHALL not be change under any circumstances

8888. Is define as 90 days or less.Permanent

Temporary

Basic

Tri-monthly8989. What should be done if the aircraft is not returned to its original condition within the 90 day period?Basic weight SHALL not be change under any circumstances


The DD Form 365-3 Chart C should be updated to reflect the temporary change and new DD Forms 365-4 Form F should be created for every typical mission with two sets of copies to replace the expired copies in the logbook and the flight planning area


9090. How often must all DD Forms 365-4 Form F be reviewed?They must be reviewed every 45 days (365 days, Ft. Rucker policy)

They must be reviewed every 30 days (365 days, Ft. Rucker policy)



9191. How often must all other forms, besides DD Form 365-4 F, in the file folder be reviewed for currency?18 months

12 months

9 months

3 months9292. Can a new date and initials in the date block extend the currency of DD Form 365-4 F?No, only the manufacturer can approve date changes in accordance with FAA regulations

If no changes are required the DD Form 365-4 Form F will be re-dated and initialed in the date block to certify their currency

If the date expires you must create new forms and replace the old forms

None of the above9393. When extending the currency of DD Form 365-4 and changes are required one must __________?Nothing given that the date is good for one year (Ft. Rucker policy)

No extension permitted

Complete a new DD Form 365-4

Complete a new DD Form 365-3 Chart C9494. How often should class 2 aircraft be weighed?When last weighing exceeds 3 months

When last weighing exceeds 6 months

When last weighing exceeds 12 months

When last weighing exceeds 24 months9595. How often should class 1 aircraft be weighed?When the last weighing exceeds 36 days

When the last weighing exceeds 32 months

When the last weighing exceeds 36 months

When the last weighing exceeds 36 years9696. What is the definition for basic weight?Basic weight is the weight that is determine by the manufacturer when the helicopter comes out of the assembly line

Is that weight that includes all filled hydraulic and oil systems, trapped and unusable fuel, and all fixed equipment (this includes the first aid kit and fire extinguisher)

Is the weight of the aircraft minus the weight of the pilot, copilot, and observer

None of the above9797. Is that weight that includes basic weight plus crew weight, crew baggage, stewards equipment, emergency equipment, and other equipment that may be required.Basic weight

Standard weight

Operating weight

Total aircraft weight9898. Is the operating weight plus the weight of take-off fuel and water injection fluid if applicable.Zero fuel weight

Complete aircraft weight

Total aircraft weight

B or C9999. Is the operating weight (ref. 9) plus Distribution of Allowable Load, payload (ref. 13).Allowable weight

Zero fuel weight

Operating weight

Full fuel weight100100. Is operating weight plus fuel, cargo, passengers, ammunitions, bombs, auxiliary fuel tanks, etc.OGE hover take-off

IGE hover take-off

Take-off gross weight

Aircraft weight101101. Take-off weight minus items expended in flight.Expended weight

Landing gross weight

Zero fuel weight

Operating weight102102. Is defined as the tendency to cause motion about a point or axis.Spectrum

Arm

Moment

Center of gravity103103. Weight times the arm (WxA=M)Formula for Fulcrum

Formula for Center of Gravity

Formula for the reference Datum

Formula for moment104104. Is the distance from the reference datum plane to the center of gravity of an item placed in the aircraft.Arm

Moment

Fulcrum

CG105105. Is an imaginary plane perpendicular to the longitudinal axis at the nose of the aircraft from which all measurements of arm are taken.Arm

Center of gravity

Moment

Reference Datum106106. What is the formula for CG?TW/TM=CG

WxA=M

TM/TW=CG

FxM=A

107

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TH-67 Systems