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General A&P 2024 > Ch. 6 - Aircraft Weight & Balance > Flashcards

Ch. 6 - Aircraft Weight & Balance Flashcards

1
Q

Which one of the following can provide the empty weight of an aircraft if the aircraft’s weight and balance records become lost, destroyed, or otherwise inaccurate?

  • Reweighing the aircraft with the proper configuration for determining weight.
  • The applicable Aircraft Specification or Type Certificate Data Sheets.
  • The applicable flight manual or pilot’s operating handbook.
A

Reweighing the aircraft with the proper configuration for determining weight.

Ref: General Handbook H-8083-30B-ATB, Chapter 6 Page 1

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2
Q
  1. Private aircraft are required by regulations to be weighed periodically.
  2. Private aircraft are required to be weighed after making any alteration.
    Regarding the above statements:

  • Neither #1 nor #2 are true
  • Only # 1 is true
  • Only #2 is true
A

Neither #1 nor #2 are true

Ref: General Handbook H-8083-30B-ATB, Chapter 6 Page 1

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3
Q

In the theory of weight and balance, what is the name of the distance from the fulcrum to an object?

  • Arm
  • Datum
  • Moment
A

Arm

Ref: General Handbook H-8083-30B-ATB, Chapter 6 Page 2

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4
Q

What type of measurement is used to designate arm in a weight and balance computation?

  • Distance
  • Weight
  • Weight/distance
A

Distance

Ref: General Handbook H-8083-30B-ATB, Chapter 6 Page 2

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5
Q

A 7 pound component located at an arm of +146 is replaced with a 4 pound component at the same location, how does this effect the overall CG of the aircraft?

  • The center of gravity moves rearward.
  • The center of gravity moves forward.
  • Not enough information is given to determine.
A

Not enough information is given to determine.

Ref: General Handbook H-8083-30B-ATB, Chapter 6 Page 2

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6
Q

The major source of weight change for most aircraft as they age is caused by?

  • Accumulation of grime and debris and moisture absorption in cabin insulation.
  • Repairs and alterations made to the aircraft over time.
  • Installation of hardware and safety wire and added layers of paint to the structure.
A

Repairs and alterations made to the aircraft over time.

Ref: General Handbook H-8083-30B-ATB, Chapter 6 Page 1

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7
Q

What determines whether the value of a moment is preceded by a plus (+) or minus (-) sign in aircraft weight and balance?

  • The location of the weight in reference to the datum.
  • The result of a weight being added or removed and its location relative to the datum.
  • The location of the datum in reference to the aircraft CG.
A

The result of a weight being added or removed and its location relative to the datum.

Ref: General Handbook H-8083-30B-ATB, Chapter 6 Page 3

Prepware book incorrectly marks answer A as correct answer.

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8
Q

In the process of weighing an airplane to obtain the CG, the arms from the weighing points always extend

  • parallel to the centerline of the airplane.
  • straight forward from each of the landing gear.
  • directly from each weighing point to the others.
A

parallel to the centerline of the airplane.

Ref: General Handbook H-8083-30B-ATB, Chapter 6 Page 2

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9
Q

When dealing with weight and balance of an aircraft, the term “maximum weight” is interpreted to mean the maximum

  • weight of the empty aircraft.
  • weight of the useful load.
  • authorized weight of the aircraft and its contents.
A

authorized weight of the aircraft and its contents.

Ref: General Handbook H-8083-30B-ATB, Chapter 6 Page 3

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10
Q

The useful load of an aircraft consists of the

  • crew, usable fuel, passengers, and cargo.
  • crew, usable fuel, oil, cargo, and fixed equipment.
  • crew, passengers, usable fuel, oil, cargo, and fixed equipment.
A

crew, usable fuel, passengers, and cargo.

Ref: General Handbook H-8083-30B-ATB, Chapter 6 Page 4

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11
Q

The useful load of an aircraft is the difference between

  • The maximum takeoff weight and the basic empty weight.
  • Maximum ramp or takeoff weight as applicable and zero fuel weight.
  • The weight of an aircraft filled, and full fuel, and weight empty with minimum fuel.
A

The maximum takeoff weight and the basic empty weight.

Ref: General Handbook H-8083-30B-ATB, Chapter 6 Page 4

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12
Q

The amount of fuel used for computing empty weight and corresponding CG is?

  • Empty fuel tanks.
  • Unusable fuel.
  • The amount of fuel necessary for 1/2 hour of operation.
A

Unusable fuel.

Ref: General Handbook H-8083-30B-ATB, Chapter 6 Page 4-5

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13
Q

When determining the empty weight of an aircraft certificated under current airworthiness standards (FAR 23), the oil contained in the supply tank is considered

  • a part of the empty weight.
  • a part of the useful load.
  • the same as the fluid contained in the water injection reservoir.
A

a part of the empty weight.

Ref: General Handbook H-8083-30B-ATB, Chapter 6 Page 4

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14
Q

What is meant by the term “residual fuel”?

  • A known amount of fuel left in the tanks, lines, and engine.
  • The fuel remaining in the tanks, lines, and engine after draining.
  • The fuel remaining in the tanks, lines, and engine before draining.
A

The fuel remaining in the tanks, lines, and engine after draining.

Ref: General Handbook H-8083-30B-ATB, Chapter 6 Page 4

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15
Q

Zero fuel weight is the

  • dry weight plus the weight of full crew, passengers, and cargo.
  • basic operating weight without crew, fuel, and cargo.
  • maximum permissible weight of a loaded aircraft (passengers, crew, cargo) without fuel.
A

maximum permissible weight of a loaded aircraft (passengers, crew, cargo) without fuel.

Ref: General Handbook H-8083-30B-ATB, Chapter 6 Page 3

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16
Q

To determine center of gravity, which of the following formulas is used?

  • total arm × total weight
  • total moment / total weight
  • total moment × total weight
A

total moment / total weight

Ref: General Handbook H-8083-30B-ATB, Chapter 6 Page 6

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17
Q

The maximum weight as used in the weight and balance control of a given aircraft can normally be found

  • by adding the fuel, passengers and baggage to the empty weight.
  • in the Aircraft Specification or Type Data Sheets.
  • by adding the empty weight and payload.
A

in the Aircraft Specification or Type Data Sheets.

Ref: General Handbook H-8083-30B-ATB, Chapter 6 Page 6

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18
Q

When leveling an airplane for a weight and balance calculation, if a spirit level is used to level the aircraft, how is it determined where the spirit level is placed?

  • Level position is parallel to the chord of the wing as stated in the TCDS.
  • Level position is parallel to aircraft thrust line as stated in the TCDS.
  • Leveling points are stated in the aircraft type certificate data sheet.
A

Leveling points are stated in the aircraft type certificate data sheet.

Ref: General Handbook H-8083-30B-ATB, Chapter 6 Page 11

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19
Q

Use of which of the following generally yields the highest degree of aircraft leveling accuracy?

  • electronic load cell(s)
  • spirit level(s)
  • plumb bob and chalk line
A

spirit level(s)

Ref: General Handbook H-8083-30B-ATB, Chapter 6 Page 14-15

20
Q

When an aircraft is weighed with full fuel tanks, which device is used to determine the weight of the fuel?

  • A calculator
  • A thermometer
  • A hydrometer
A

A hydrometer

Ref: General Handbook H-8083-30B-ATB, Chapter 6 Page 12

21
Q

What tasks are completed prior to weighing an aircraft to determine empty weight?

  • Remove all items except those on the aircraft equipment list; drain fuel and hydraulic fluid.
  • Remove all items on the aircraft equipment list; drain fuel, compute oil and hydraulic fluid weight.
  • Remove all items except those on the aircraft equipment list; drain fuel and fill hydraulic reservoir.
A

Remove all items except those on the aircraft equipment list; drain fuel and fill hydraulic reservoir.

Ref: General Handbook H-8083-30B-ATB, Chapter 6 Page 4, 12

22
Q

To obtain useful weight data for purposes of determining the CG, it is necessary that an aircraft be weighed

  • in a level flight attitude.
  • with all items of useful load installed.
  • with at least minimum fuel (1/2 gallon per METO horsepower) in the fuel tanks.
A

in a level flight attitude.

Ref: General Handbook H-8083-30B-ATB, Chapter 6 Page 14

23
Q

When an aircraft is positioned for weighing on scales located under each landing gear wheel, which of the following may cause erroneous scale readings?

  • gear downlocks installed
  • parking brakes set
  • parking brakes not set
A

parking brakes set

Ref: General Handbook H-8083-30B-ATB, Chapter 6 Page 14

24
Q

The standard weight of a person, for the purposes of weight and balance calculations, is

  • 180 pounds.
  • 170 pounds.
  • 75 kilos.
A

170 pounds.

Ref: General Handbook H-8083-30B-ATB, Chapter 6 Page 16

25
Q

As weighed, the total empty weight of an aircraft is 5,862 pounds with a moment of 885,957. However, when the aircraft was weighed, 20 pounds of potable water were on board at +84, and 23 pounds of hydraulic fluid were in the tank located at +101. What is the empty weight CG of the aircraft?

  • 152.25
  • 151.56
  • 151.48
A

151.48

Ref: General Handbook H-8083-30B-ATB, Chapter 6 Page 16, 19

26
Q

Two boxes which weigh 10 pounds and 5 pounds are placed in an airplane so their distance aft from the CG are 4 feet and 2 feet respectively. How far forward of the CG should a third box weighing 20 pounds be placed so that the CG will not be changed?

  • 3 feet
  • 2.5 feet
  • 8 feet
A

2.5 feet

Ref: General Handbook H-8083-30B-ATB, Chapter 6 Page 16, 19

27
Q

In a balance computation of an aircraft from which an item located aft of the datum was removed, use

  • (-) weight × (+) arm (-) moment.
  • (-) weight × (-) arm (+) moment.
  • (+) weight × (-) arm (-) moment.
A

(-) weight × (+) arm (-) moment.

Ref: General Handbook H-8083-30B-ATB, Chapter 6 Page 16, 19

28
Q

Consider the specifications of the following aircraft:
The datum is 30.24” forward of the main gear
The distance from the main gear to the tail gear is 360.26”
The weight measured on the right main gear is 9,980 lbs
The weight measured on the left main gear is 9,770 lbs
The weight measured on the tail wheel is 1,970 lbs
The following items were in the aircraft when weighed:
Lavatory water weighing 34 lbs at an arm of +352
Ballast weighing 146 lbs at an arm of +380
Hydraulic fluid weighing 22 lbs at an arm of +8
What is the empty weight CG of the aircraft described?

  • 62.92”
  • 60.31”
  • 58.54”
A

60.31”

Ref: General Handbook H-8083-30B-ATB, Chapter 6 Page 16, 19

29
Q

When an aircraft is weighed, the combined net weight at the main gear is 3540 pounds with an arm of 195.5”. At the nose gear, the net weight is 2322 pounds with an arm of 83.5”. The datum line is forward of the nose of the aircraft. What is the empty CG of the aircraft?

  • 151.1
  • 155.2
  • 146.5
A

151.1

Ref: General Handbook H-8083-30B-ATB, Chapter 6 Page 16, 19

30
Q

Find the empty weight CG location for the following aircraft. Each main wheel weighs 753 pounds, nose wheel weighs 22 pounds, distance between nose wheel and main wheels is 87.5”, nose wheel location is +9.875” from datum, with 1 gallon of hydraulic fluid at -2.10” included in the weight.

  • +97.375”
  • +95.61”
  • +96.11”
A

+96.11”

Ref: General Handbook H-8083-30B-ATB, Chapter 6 Page 16, 19

31
Q

An aircraft with an empty weight of 2100 pounds and an empty weight CG of +32.5 was altered as follows:
* Two 18 pound seats located at +73 were removed;
* Structural modifications were made at +77 increasing weight by 17 pounds;
* A seat and safety belt weighing 25 pounds were installed at +74.5;
* Radio equipment weighing 35 pounds was installed at +95
What is the new CG of the aircraft?

  • +34.01
  • +33.68
  • +34.65
A

+33.68

Ref: General Handbook H-8083-30B-ATB, Chapter 6 Page 16, 19

32
Q

You must weigh an aircraft with full fuel tanks in order to document its current CG point. After the total weight has been determined, what must be done?

  • Subtract the weight of unusable fuel.
  • Subtract the weight of usable fuel.
  • Nothing. The weight you have determine is correct.
A

Subtract the weight of usable fuel.

Ref: General Handbook H-8083-30B-ATB, Chapter 6 Page 13, 19

33
Q

When accomplishing loading computation for a small aircraft, necessary information obtained from the weight and balance records would include

  • unusable fuel weight and distance from datum.
  • weight and location of permanent ballast.
  • current empty weight and empty weight CG.
A

current empty weight and empty weight CG.

Ref: General Handbook H-8083-30B-ATB, Chapter 6 Page 19

34
Q

All other things being equal, if an item of useful load located aft of an aircraft’s CG is removed, the aircraft’s CG will be

  • aft in proportion to the weight of the item and its location in the aircraft.
  • forward in proportion to the weight of the item and its location in the aircraft.
  • forward in proportion to the weight of the item, regardless of its location in the aircraft.
A

forward in proportion to the weight of the item and its location in the aircraft.

Ref: General Handbook H-8083-30B-ATB, Chapter 6 Page 19

35
Q

When conducting a rearward adverse condition CG check, all load items (such as cargo, usable fuel, and passengers) located forward of the _____________ should be left empty.

  • forward CG limit
  • rearward CG limit
  • datum
A

rearward CG limit

Ref: General Handbook H-8083-30B-ATB, Chapter 6 Page 20

36
Q

When computing the maximum forward loaded CG of an aircraft, minimum weights, arms, and moments should be used for items of useful load that are located aft of the

  • rearward CG limit.
  • forward CG limit.
  • datum.
A

forward CG limit.

Ref: General Handbook H-8083-30B-ATB, Chapter 6 Page 20

37
Q

An aircraft as loaded weighs 4,954 pounds at a CG of +30.5 inches. The CG range is +32.0 to +42.1. Find the minimum weight of the ballast necessary to bring the CG within the CG range. The ballast arm is +162 inches.

  • 61.98 pounds
  • 30.58 pounds
  • 57.16 pounds
A

57.16 pounds

Ref: General Handbook H-8083-30B-ATB, Chapter 6 Page 22

38
Q

When computing weight and balance, an airplane is considered to be in balance when?

  • the average moment arm of the loaded airplane falls within its cg range.
  • all moment arms of the plane fall within CG range.
  • the movement of the passengers will not cause the moment arm to fall outside the CG range.
A

all moment arms of the plane fall within CG range.

Ref: General Handbook H-8083-30B-ATB, Chapter 6 Page 15, 16

39
Q

Which statement is true regarding helicopter weight and balance?

  • Regardless of internal or external loading, lateral CG control is ordinarily not a factor in maintaining helicopter weight and balance.
  • The moment of tail-mounted components is subject to constant change.
  • Weight and balance procedures for airplanes generally also apply to helicopters.
A

Weight and balance procedures for airplanes generally also apply to helicopters.

Ref: General Handbook H-8083-30B-ATB, Chapter 6 Page 25

40
Q

Improper loading of a helicopter which results in exceeding either the fore and aft CG limits is hazardous due to the

  • reduction or loss of effective cyclic pitch control.
  • coriolis effect being translated to the fuselage.
  • reduction or loss of effective collective pitch control.
A

reduction or loss of effective cyclic pitch control.

Ref: General Handbook H-8083-30B-ATB, Chapter 6 Page 25

41
Q

When jacking an aircraft for the purpose of weighing it, how do you determine the correct leveling position?

  • Manufacturer’s maintenance manual.
  • Type Certificate Data Sheets.
  • Aircraft are always weighed in its level flight attitude.
A

Type Certificate Data Sheets.

Ref: General Handbook H-8083-30B-ATB, Chapter 6 Page 14

42
Q

The FAA mandates the same weight and balance requirements for weight-shift control aircraft and powered parachutes as it does for certified airplanes and helicopters.

  • True, the regulations are the same.
  • False, the regulations are not the same.
  • False, the regulations are the same for weight-shift control aircraft but not for powered parachutes.
A

False, the regulations are not the same.

Ref: General Handbook H-8083-30B-ATB, Chapter 6 Page 26

43
Q

If an aircraft CG is found to be at 24% of MAC, that 24% is an expression of the

  • distance from the TEMAC.
  • distance from the LEMAC.
  • average distance from the LEMAC to the wing center of lift.
A

distance from the LEMAC.

Ref: General Handbook H-8083-30B-ATB, Chapter 6 Page 28

44
Q

An aircraft’s LEMAC and TEMAC are defined in terms of their distance from

  • the datum.
  • the wing root leading edge.
  • the indicated center of lift.
A

the datum.

Ref: General Handbook H-8083-30B-ATB, Chapter 6 Page 28

45
Q

Consider the following on a large aircraft, and convert the CG location from inches to percent of MAC.
* The CG is located at 283 inches behind the datum.
* LEMAC is located at 270 inches behind the datum.
* TEMAC is located at 324 inches behind the datum.

  • 24%
  • 17%
  • 21%
A

24%

Ref: General Handbook H-8083-30B-ATB, Chapter 6 Page 30, 31

Incorrectly marked in Prepware book as answer B

General A&P 2024 (1 decks)

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