AIRCRAFT FITTING (KEY)

In a hovering helicopter equipped with a tail rotor, directional control is maintained by

• Varying the pitch of the tail rotor blades.

• Changing the tail rotor RPM.

• Tilting the main rotor disk in the desired direction.

• Varying the pitch of the tail rotor blades.

What physical factors are involved in the aspect ratio of airplane wings?

• Thickness and chord

• Dihedral and angle of attack

• Span and chord

• Span and chord

If the control stick of an aircraft with properly rigged flight controls is moved forward and to the right, the left aileron will move

• Down and the elevator will move up

• Up and the elevator will move down

• Down and the elevator will move down

• Down and the elevator will move down

Other than the manufacturer maintenance manual, what other document could be used to determine the primary flight control surface deflection for an imported aircraft that is reassembled after shipment?

• Import manual for the aircraft.

• Aircraft type certificate data sheet.

• The certificate of airworthiness issued by the importing country.

• Aircraft type certificate data sheet.

The acute angle formed by the chord line of a wing and the relative wind is known as the

• Angle of Attack

• Longitudinal Dihedral Angle

• Angle of Incidence

• Angle of Attack

The primary purpose of stall strips is to

• Stall the inboard portion of the wings first.

• Provide added lift at slow speeds.

• Provide added lift at high angles of attack.

• Stall the inboard portion of the wings first.

What is the purpose of the free-wheeling unit in a helicopter drive system?

• It allows the engines to be started without any load from the transmission.

• It allows the rotors to turn slowly as the engine RPM increases.

• It disengages the engine from the main rotor when engine RPM is less than rotor RPM.

• It disengages the engine from the main rotor when engine RPM is less than rotor RPM.

The correct dihedral angle can be determined by

• Using a dihedral board and bubble level along the front spar of each wing.

• Measuring the angular setting of each wing at the rear spar with a bubble protractor.

• Placing a straightedge and bubble protractor across the spars while the airplane is in flying position.

• Using a dihedral board and bubble level along the front spar of each wing.

Which statement is correct concerning the torque effect on helicopters?

• Torque direction is the same as rotor blade rotation.

• Torque direction is the opposite of rotor blade rotation.

• As horsepower decreases, torque increases.

• Torque direction is the opposite of rotor blade rotation.

Where would you find precise information to perform a symmetry alignment check for a particular aircraft?

• Aircraft service or maintenance manual

• Aircraft Specification or Type Certificate Data Sheet

• Manufacturer's service bulletins

• Aircraft service or maintenance manual

Aircraft flight control trim systems must be designed and installed so that the

• Operating control and the trim tab will always move in the same direction.

• Trim system will disengage or become inoperative if the primary flight control system fails.

• Pilots can determine the relative position of the trim tab from the cockpit.

• Pilots can determine the relative position of the trim tab from the cockpit.

If control cables are adjusted properly and the control surfaces tend to vibrate, the probable cause is

• Worn attachment fittings.

• Oil can effects on the control surfaces.

• Excessive cable tension.

• Worn attachment fittings

The angle of incidence is that acute angle formed by

• The angular difference between the setting of the main airfoil and the auxiliary airfoil (horizontal stabilizer) in reference to the longitudinal axis of the aircraft.

• A line parallel to the wing chord and a line parallel to the longitudinal axis of the aircraft.

• A line parallel to the wing from root to tip and a line parallel to the lateral axis of the aircraft.

• A line parallel to the wing chord and a line parallel to the longitudinal axis of the aircraft.

When the lift of an airfoil increases, the drag will

• Increase while the lift is changing but will return to its original value.

• Also increase.

• Decrease.

• Also increase

If the vertical fin of a single-engine, propeller-driven airplane is rigged properly, it will generally be parallel to

• The vertical axis but not the longitudinal axis.

• Both the longitudinal and vertical axes.

• The longitudinal axis but not the vertical axis.

• The vertical axis but not the longitudinal axis.

A universal propeller protractor used to measure the degrees of aileron travel should be zeroed

• With the aileron in the NEUTRAL position.

• With the aileron in the DOWN position.

• When the aircraft is in a level flight attitude.

• With the aileron in the NEUTRAL position.

Stability about the axis which runs parallel to the line of flight is referred to as

• Longitudinal stability

• Lateral stability

• Directional stability

• Lateral stability

Fairleads should never deflect the alignment of a cable more than

• 12 degrees

• 8 degrees

• 3 degrees

• 3 degrees

What nondestructive checking method is normally used to ensure that the correct amount of swaging has taken place when installing swaged-type terminals on aircraft control cables?

• Use a terminal gauge to check the diameter of the swaged portion of the terminal.

• Measure the finished length of the terminal barrel and compare it with the beginning length.

• Check the surface of the swaged portion of the terminal for small cracks which indicate incomplete swaging.

• Use a terminal gauge to check the diameter of the swaged portion of the terminal.

Excessive wear on both of the sides of a control cable pulley groove is evidence of

• Cable misalignment

• Excessive cable tension

• Pulley misalignment

• Pulley misalignment

A reduction in anti-torque thrust will cause the

• Tail to pivot in the opposite direction of torque rotation around the main rotor axis.

• Anti-torque system to become more efficient in the hover mode.

• Tail to pivot in the direction of torque rotation around the main rotor axis.

• Tail to pivot in the direction of torque rotation around the main rotor axis.

The angle of incidence of an airplane at rest

• Does not change when in flight.

• Affects the dihedral of the wings in flight.

• Is the same as the angle between the relative wind and the chord of the wing.

• Does not change when in flight.

An airplane's center of lift is usually located aft of its center of gravity

• So that the airplane will have a nose-heavy tendency.

• To improve stability about the longitudinal axis.

• So that the airplane will have a tail-heavy tendency.

• So that the airplane will have a nose-heavy tendency.

The purpose of checking main rotor blade tracking is to determine the

• Flight path of the blades during rotation.

• Relative position of the blades during rotation.

• Extent of an out of balance condition during rotation.

• Relative position of the blades during rotation.

The vertical flight of a helicopter is controlled by

• Increasing or decreasing the RPM of the main rotor

• Cyclic pitch changes

• Collective pitch changes

• Collective pitch changes

After repairing or re-covering a rudder, the surface should be rebalanced

• To manufacturer's specifications.

• To its spanwise axis.

• In its normal flight position.

• To manufacturer's specifications.

When used in close proximity to magnetic compasses, cotter pins are made of what material?

• Cadmium-plated low carbon steel

• Corrosion resisting steel

• Anodized aluminum alloy

• Corrosion resisting steel

Which is an acceptable safety device for a castle nut when installed on secondary structures?

• Star washer

• Cotter pin

• Lockwasher

• Cotter pin

Washing-in the left wing of a monoplane, for purposes of rigging corrections after flight test, will have what effect on the lift and drag of that wing?

• Both drag and lift will increase due to increased angle of attack.

• Both drag and lift will decrease due to decreased angle of attack.

• The drag will decrease due to the effect of the lift increase.

• Both drag and lift will increase due to increased angle of attack.

An airplane which has good longitudinal stability should have a minimum tendency to

• Yaw

• Roll

• Pitch

• Pitch

A helicopter in forward flight, cruise configuration, changes direction by

• Varying the pitch of the main rotor blades.

• Tilting the main rotor disk in the desired direction.

• Changing rotor RPM.

• Tilting the main rotor disk in the desired direction.

One purpose of the freewheeling unit required between the engine and the helicopter transmission is to

• Permit practice of autorotation landings.

• Disconnect the rotor from the engine to relieve the starter load.

• Automatically disengage the rotor from the engine in case of an engine failure.

• Automatically disengage the rotor from the engine in case of an engine failure.

How are changes in direction of a control cable accomplished?

• Pulleys

• Bell cranks

• Fairleads

• Pulleys

If a single-rotor helicopter is in forward horizontal flight, the angle of attack of the advancing blade is

• Less than the retreating blade.

• Equal to the retreating blade.

• More than the retreating blade.

• Less than the retreating blade.

Rigging and alignment checks should not be undertaken in the open. However, if this cannot be avoided, the aircraft should be positioned with the

• Nose into the wind

• Tail into the wind

• Left wing into the wind

• Nose into the wind

The universal propeller protractor can be used to measure

• Propeller track

• Aspect ratio of a wing

• Degrees of flap travel

• Degrees of flap travel

The cable-operated control system of an all-metal aircraft, not incorporating a temperature compensating device, has been rigged to the correct tension in a heated hangar. If the aircraft is operated in very cold weather, the cable tension will 

• Be unaffected if stainless steel cable is installed. 

• Decrease when the aircraft structure and cables become cold. 

• Increase when the aircraft structure and cables become cold.

• Decrease when the aircraft structure and cables become cold. 

Movement about the lateral axis (pitch) in a helicopter is affected by the movement of the

• Tail rotor pitch control

• Collective pitch control

• Cyclic pitch control

• Cyclic pitch control

Very often, repairs to a control surface require a static rebalancing of the control surface. Generally, flight control balance condition may be determined by

• The behavior of the trailing edge when the surface is suspended from its hinge points.

• Suspending the control surface from its leading edge in the stream line position and checking weight distribution.

• Checking for equal distribution of weight throughout the control surface.

• The behavior of the trailing edge when the surface is suspended from its hinge points.

Differential control on an aileron system means that

• The down travel is more than the up travel.

• The up travel is more than the down travel.

• One aileron on one wing travels further up than the aileron on the opposite wing to adjust for wash-in and wash-out.

• The up travel is more than the down travel.

If all instructions issued by the swaging tool manufacturer are followed when swaging a cable terminal, the resultant swaged terminal strength should be

• The full rated strength of the cable.

• 80 percent of the full rated strength of the cable.

• 70 percent of the full rated strength of the cable.

• The full rated strength of the cable.

Which statement concerning the 100-hour inspection of an airplane equipped with a push-pull tube-type control system is true? 

• The threaded rod ends should be checked for the amount of thread engagement by means of the inspection hole provided.

• The threaded rod ends should not be adjusted in length for rigging purposes because the rod ends have been properly positioned and staked during the manufacture.

• The terminal end threads of the turnbuckles should be visible through the safety hole in the barrel.

• The threaded rod ends should be checked for the amount of thread engagement by means of the inspection hole provided.

Proper wing twist in a sheet metal constructed wing can usually be checked by utilizing a

• Plum bob, string, and straightedge.

• Bubble level and special fixtures described by the manufacturer.

• Straightedge, tape measure, and carpenter’s square.

• Bubble level and special fixtures described by the manufacturer.

With which system is differential control associated?

• Aileron

• Trim

• Elevator

• Aileron

Where is the buttock line or buttline of an aircraft?

• A height measurement left or right of, and perpendicular to, the horizontal centerline.

• A width measurement left of, and perpendicular to, the vertical centerline.

• A width measurement left or right of, and parallel to, the vertical centerline.

• A width measurement left or right of, and parallel to, the vertical centerline.

What is the smallest size cable that may be used in aircraft primary control systems?

• 5/16 inch

• 1/8 inch

• 1/4 inch

• 1/8 inch

Movement about the longitudinal axis (roll) in a helicopter is affected by the movement of the

• Tail rotor pitch control

• Cyclic pitch control

• Collective pitch control

• Cyclic pitch control

An airplane that has a tendency to gradually increase a pitching moment that has been set into motion has

• Poor longitudinal stability

• Good lateral stability

• Poor lateral stability

• Poor longitudinal stability

The purpose of spring tabs or servo tabs is to

• Contribute to the static balance of the control surface.

• Assist the pilot in moving the control surfaces.

• Make in-flight trim adjustments possible.

• Assist the pilot in moving the control surfaces.

In rotorcraft external-loading, the ideal location of the cargo release is where the line of action passes

• Forward of the center of gravity at all times.

• Aft of the center of gravity at all times.

• Through the center of gravity at all times

• Through the center of gravity at all times

Movement of the cockpit control toward the nose down position during a ground operational check of the elevator trim tab system will cause the trailing edge of the trim tab to move in which direction?

• Downward regardless of elevator position.

• Downward if the elevator is in the UP position and upward if the elevator is in the DOWN position.

• Upward regardless of elevator position.

• Upward regardless of elevator position.

If a pilot reports that an airplane flies left wing heavy, this condition may be corrected by

• Increasing the angle of incidence of the left wing, or decreasing the angle of incidence of the right wing, or both.

• Increasing the dihedral angle of the left wing, or decreasing the dihedral angle, adjusting the dihedral of the right wing, or both.

• Adjusting the dihedral angle of the left wing so that differential pressure between the upper and lower wing surfaces is increased.

• Increasing the angle of incidence of the left wing, or decreasing the angle of incidence of the right wing, or both.

The purpose of wing slats is to

• Reduce lift.

• Decrease drag.

• Reduce stalling speed.

• Reduce stalling speed.

Which should be accomplished before jacking an aircraft?

• Make sure the aircraft is leveled laterally.

• Determine that the fuel tanks are empty.

• Install critical stress panels or plates.

• Install critical stress panels or plates.

The movement of an airplane along its lateral axis (roll) is also movement

• Around or about the longitudinal axis controlled by the ailerons.

• Around or about the longitudinal axis controlled by the elevator.

• Around or about the lateral axis controlled by the ailerons.

• Around or about the longitudinal axis controlled by the ailerons.

The elevators of a conventional airplane are used to provide rotation about the

• Lateral axis

• Longitudinal axis

• Vertical axis

• Lateral axis

Wing dihedral, a rigging consideration on most airplanes of conventional design, contributes most to the stability of the airplane about its

• Vertical axis

• Longitudinal axis

• Lateral axis

• Longitudinal axis

The purpose of the vertical fin is to provide

• Directional stability

• Lateral stability

• Longitudinal stability

• Directional stability

A tension regulator in the flight control cable system of a large all-metal aircraft is used primarily to

• Provide a means of changing cable tension in flight.

• Increase the cable tension in cold weather.

• Retain a set tension.

• Retain a set tension.

If the travel of an airplane's controls is correct but the cables are rigged exceptionally tight, what probable effect will this have when flying the airplane?

• The airplane will be heavy on the controls.

• The airplane will tend to fall off on one wing.

• The pilot will be unable to fly the airplane hands-off.

• The airplane will be heavy on the controls.

During inspection of the flight control system of an airplane equipped with differential-type aeron control, side-to-side movement of the control stick will cause

• Each aileron to have a greater down travel (from the streamlined position) than up travel.

• The left aileron to move through a greater number of degrees (from full up to full down) than the right aileron.

• Each aileron to have a greater up travel (from the streamlined position) than down travel.

• Each aileron to have a greater up travel (from the streamlined position) than down trave

Main rotor blades that do not cone by the same amount during rotation are said to be out of

• Track

• Collective pitch

• Balance

• Track

Where is fuselage Station No. 137 located?

• Aft of the engine.

• 137 inches aft of the zero or fixed reference line.

• 137 centimeters aft of the nose or fixed reference line.

• 137 inches aft of the zero or fixed reference line.

When a fiber or nylon insert-type, the self-locking nut can be threaded on a bolt or stud through the insert with only the fingers, it should be

• Rejected.

• Re-torqued frequently.

• Reused only in a different location.

• Rejected.

Improper rigging of the elevator trim tab system will affect the balance of the airplane about its

• Vertical axis

• Longitudinal axis

• Lateral axis

• Lateral axis

The auxiliary (tail) rotor of a helicopter permits the pilot to compensate for and/or accomplish which of the following?

• Attitude and airspeed

• Lateral and yaw position

• Torque and directional control

• Torque and directional control

As the angle of attack of an airfoil increases, the center of pressure will

• Move toward the leading edge.

• Move toward the trailing edge.

• Remain stationary because both lift and drag components increase proportionally to increased angle of attack.

• Move toward the leading edge.

When inspecting a control cable turnbuckle for proper installation, determine that

• The terminal end threads are visible through the safety hole in the barrel.

• No more than four threads are exposed on either side of the turnbuckle barrel.

• The safety wire ends are wrapped a minimum of four turns around the terminal end shanks

• The safety wire ends are wrapped a minimum of four turns around the terminal end shanks

When installing a castle nut, start alignment with the cotter pin hole at the

• Minimum recommended torque without friction drag torque.

• Maximum recommended torque minus friction drag torque.

• Minimum recommended torque plus friction drag torque.

• Minimum recommended torque plus friction drag torque.

If the right wing of a monoplane is improperly rigged to a greater angle of incidence than designated in the manufacturer's specifications, it will cause the

• Airplane to be off balance both laterally and directionally.

• Right wing to have both an increased lift and a decreased drag.

• Airplane to pitch and roll about the lateral axis.

• Airplane to be off balance both laterally and directionally.

An airplane is controlled directionally about its vertical axis by the

• Rudder

• Elevators

• Ailerons

• Rudder

The chord of a wing is measured from

• Leading edge to trailing edge

• Wing root to the wingtip

• Wingtip to wingtip

• Leading edge to trailing edge

What type of flap system increases the wing area and changes the wing camber?

• Fowler flaps

• Split flaps

• Slotted flaps

• Fowler flaps

Where does the breakage of control cable wires occur most frequently?

• Breakage usually occurs where cables pass over pulleys and through fairleads.

• Breakage usually occurs where cables are swaged to turnbuckle and ball terminals.

• Breakage sites are unpredictable and usually occur randomly anywhere along the length of a cable.

• Breakage usually occurs where cables pass over pulleys and through fairleads.

If the control stick of an aircraft with properly rigged flight controls is moved rearward and to the left, the right aileron will move

• Down and the elevator will move up.

• Down and the elevator will move down.

• Up and the elevator will move down.

• Down and the elevator will move up.

The dihedral angle of a wing may be measured by placing a straightedge and level protractor on the

• Wing chord

• Front spar

• Wing root

• Front spar

The vast majority of aircraft control cables are terminated with swaged terminals, that must be

A. Corrosion treated to show compliance with the manufacturer’s requirements after the swaging operation.

B. Pull tested to show compliance with the manufacturer’s requirements after the swaging operation.

C. Checked with a go-no-go gauge before and after, to show compliance with manufacturer’s requirements after the swaging operation.

C. Checked with a go-no-go gauge before and after, to show compliance with manufacturer’s requirements after the swaging operation.

Buffeting is the intermittent application of forces to a part of an airplane. It is caused by

• Incorrect rigging of flaps.

• Incorrect rigging of ailerons.

• An unsteady flow from turbulence.

• An unsteady flow from turbulence.

Placing a piece of cloth around a stainless steel control cable and running it back and forth over the length of the cable is generally a satisfactory method for

• Corrosion

• Broken strands

• Excessive wear

• Broken strands

Why is it generally necessary to jack an aircraft indoors for weighing?

• So aircraft may be placed in a level position.

• So weighing scales may be calibrated to 0 pounds.

• So that air currents do not destabilize the scales.

• So that air currents do not destabilize the scales.