Amt General Study Guide Ch6

Front 1

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

Back 1

The average moment arm of the loaded airplane falls within its CG range

Hint 1

The CG can be thought of as the average moment arm for the aircraft. this value must fall within an allowable range to be considered safe for flight.

Front 2

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

Back 2

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

Hint 2

According to FAR part 23, the empty weight of an aircraft includes all items on the aircraft's minimum equipment list, permanent ballast, unusable fuel, full hydraulics, and full oil (aircraft certified prior to March 1, 1978, are weighed with only the undrainable oil).

Front 3

The useful load of an aircraft consists of the

Back 3

Crew, usable fuel, passengers, and cargo

Hint 3

The useful load of an aircraft is the difference between the maximum gross weight and the empty weight. it includes itself such as passengers and crew, usable fuel, and cargo.

Front 4

Which of the following can provide the empty weight of an aircraft if the aircraft weight and balance record becomes lost, destroyed or otherwise inaccurate?

Back 4

Reweighing the aircraft.

Hint 4

If an aircraft's weight and balance records become lost or destroyed, the actual empty weight can only be established by reweighing the aircraft. The aircraft specification or type certificate data sheet is wrong because an aircraft's type certificate data sheet only lists maximum weight and not an empty weight, and the flight manual or pilots operating handbook is wrong because an aircraft's flight manual contains an average empty wait for that model aircraft.

Front 5

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

Back 5

Lever arm

Hint 5

In the theory of weight and balance, the name given to the distance from the fulcrum to an object is a lever arm. The lever arm is multiplied by the weight of the object to find the moment. In actual aircraft weight and balance problems, the arm is a distance from the datum to an item.

Front 6

(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,

Back 6

Neither number 1 nor number 2 is true

Hint 6

Both of these statements are false. There is no regulation that requires private aircraft to be reweighed. Generally, after alterations, the weight changes are calculated and recorded in the aircraft record. However, it's good operating practice to reweigh an aircraft whenever alterations in a substantially affect an aircraft weight and balance.

Front 7

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

Back 7

In a level flight altitude

Hint 7

When an aircraft is weighed, it must be in a level flight altitude for the scale readings to be accurate. Weigh points, level points, and proper procedures for weighing are usually contained in the type certificate datasheet and are provided by the manufacturer's maintenance manual.

Front 8

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

Back 8

Distance

Hint 8

Arm is the horizontal distance in inches or feet from the reference datum to an item of equipment.

Front 9

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

Back 9

The location of the weight is reference to the datum

Hint 9

The location of items in an aircraft are given as positive or negative values according to their location relative to the reference datum. Items foward of the datum have a negative arm and items aft the datum have a positive arm.

Front 10

What should be clearly indicated on the aircraft weighing form?

Back 10

Weighing points

Hint 10

The weighing points should be clearly indicated on the aircraft weighing forms because the arm values used for the scale readings are based on these locations.

Front 11

If the reference datum line is placed at the nose of an airplane rather than at the firewall or some other location aft of the nose,

Back 11

All measurement arms will be in the positive numbers

Hint 11

All measurement arms aft of the datum carry a positive value and arms in the front of the datum carry a negative value. When the datum is located in front of the aircraft, all measurement arms are positive.

Front 12

Zero fuel weight is the

Back 12

Maximum permissible weight of a loaded aircraft (passenger, crew, and cargo) without fuel

Hint 12

Zero fuel weight is the maximum permissible weight of a loaded aircraft, including the payload (passengers, crew, and cargo), but excluding the fuel load.

Front 13

The empty weight of an airplane is determined by

Back 13

Subtracting the tare weight from the scale reading and adding the weight of each weighing point

Hint 13

Tare weight includes the weight of extra items on the weighing scale that are not part of the aircraft. To determine the empty weight of an aircraft being weighed, add the weight of each scale reading and subtract out the tare weight.

Front 14

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

Back 14

Authorized the weight of the aircraft and its contents

Hint 14

Maximum weight is the maximum authorized weight of the aircraft and its contents. This value may be found in the aircraft specifications or types certificate data sheet.

Front 15

Most modern aircraft are designed so that if all seats are occupied for baggage weight is carried, and all fuel tanks are full, what will be the weight condition of the aircraft?

Back 15

It will be in excess of maximum takeoff weight

Hint 15

If all seats are occupied, all baggage allowed, and all fuel tanks full, most modern aircraft will be grossly over loaded. Excessive weight reduces the efficiency of an aircraft in the safety margin available if an emergency condition should arise

Front 16

A major source of weight change for most aircraft as the age is caused by

Back 16

Repairs and alterations

Hint 16

Repairs and alterations are the major sources of weight changes. the growth due to trash and dirt in hard to reach places is normally small

Front 17

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

Back 17

Spirit level(s)

Hint 17

The most accurate method of leveling an aircraft is a plumb bob and a group plate and not a plumb bob and chalk line. of the choices given, spirit levels are the most accurate method of leveling an aircraft.

Front 18

In the process of weighing an airplane for obtaining the CG, the arms of the weighing points always extend

Back 18

Parallel to the center line of the airplane

Hint 18

And airplanes CG is determined from the distribution of weight along the center line. Lateral distribution is not considered and in determining an airplane CG

Front 19

The useful load of an aircraft is a difference between

Back 19

The maximum takeoff weight and basic empty weight

Hint 19

The useful load of an aircraft is the difference between the maximum gross weight maximum takeoff weight and the empty weight. It includes items such as passengers and crew, usable fuel, and cargo.

Front 20

When determining the empty weight of an aircraft, certificated undercurrent airworthiness standard FAR part 23, the oil contained in the supply tank is considered

Back 20

A part of the empty weight

Hint 20

Undercurrent airworthiness standard FAR part 23, for oil is considered part of the empty weight of an aircraft. Until March one, not 1978, empty weight included only undrainable oil.

Front 21

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

Back 21

In the aircraft specification or type certificate data sheet

Hint 21

The maximum weight of a particular model or aircraft is found in the aircraft specification or type certificate data sheet. Empty weights and useful loads very with the equipment installed on in particular aircraft. These values must be located in the permanent records for the aircraft

Front 22

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

Back 22

Unusable fuel

Hint 22

The empty weight of an aircraft includes only the weight of the fuel which remains in the sumps and plumbing of the aircraft and is termed unusable fuel

Front 23

The useful load of an aircraft is the difference between

Back 23

Maximum takeoff weight and basic empty weight

Hint 23

The useful load of an aircraft is the difference between the maximum gross weight maximum takeoff weight and the empty way. It includes items such as passengers and crew, usable fuel, and cargo.

Front 24

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

Back 24

Distance from the LEMAC

Hint 24

The mean aerodynamic chord (MAC) is determined from the leading edge to the trailing edge of the airfoil. The leading edge MAC (LEMAC) is the start or 0% MAC. The trailing edge MAC (TEMAC) is 100% MAC. A CG that is 24% MAC is 24% of the distance from LEMAC to TEMAC.

Front 25

An aircraft LEMAC and TEMAC are defined in terms of

Back 25

From the datum

Hint 25

An aircrafts leading edge mean aerodynamic chord (LEMAC) and trailing edge mean aerodynamic chord (TEMAC) are assigned fuselage or body station number representative of the distance from the datum. The actual MAC is the difference between the TEMAC and the LEMAC.

Front 26

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

Back 26

Parking brakes set

Hint 26

When an aircraft is weighed, chocks should be used to prevent the aircraft from rolling and the weight of the chocks subtracted from the scale weight readings as tare weight. Setting the brakes may cause adverse side load to be applied to the scale, causing an accurate readings

Front 27

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

Back 27

Current empty weight and empty weight CG

Hint 27

When accomplishing loading computations on a small aircraft, if necessary to locate the empty weight and empty weight center of gravity in the weight and balance records to have a starting point from which to calculate the effect of added weight of useful load items.

Front 28

If it is necessary to wait an aircraft with full fuel tanks all fuel tanks must be subtracted from the scale readings

Back 28

Except unusable fuel

Hint 28

When weighing an aircraft, only unusable fuel should be considered part of the aircraft empty weight. If an aircraft is Wade with full fuel, off your weight must be subtracted from the scale weight ratings accept unusable fuel, as specified in the aircraft type certificate data sheet or specifications

Front 29

When making a rearward weight and balance check to determine that the CG will not exceed the rearward limit during extreme conditions, the items of useful load which should be complicated at their minimum weights are those located forward of the

Back 29

Rearward CG limit

Hint 29

When making a rearward extreme loading check, you must love the items of useful load behind the rearward CG limit to their maximum, and the items are used for load ahead of the rearward CG limit to the minimum.

Front 30

If the empty weight CG of an airplane flies within the empty weight CG limits

Back 30

It is not necessary to calculate CG extremes

Hint 30

Adverse loading trucks are a deliberate attempt to load an aircraft any manner that will create the most critical about his condition and still remain within the aircraft design city limits. If the empty weight CG Falls within the empty weight CG range it is unnecessary to perform this check

Front 31

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

Back 31

Forward CG limit

Hint 31

Afford adverse loading check is performed to determine if it is possible to load an airplane so that it said you will fall ahead of the forward CG limit. To perform this type of check, use maximum values for items of beautiful loads that are forward of the Ford limit, and minimum values for those adams located after of the Forward CG limit

Front 32

All other things being equal, if an item of useful are located at of an aircraft's CG is removed the, the aircraft's CG

Back 32

Forward is proportion to the weight of the item and its location in the aircraft

Hint 32

When weighing is added or removed to an aircraft, the CG is affected depending on an amount of weight and its location relative to the CG. When weight is added, it moves the CG toward that I did wait. When weight is removed, the CG moved away from the location of the remove the wait. Only when weight is added or removed at the CG does the CG remain constant

Front 33

Which statement is true regarding helicopter weight and balance?

1. Regardless of internal or external loading, lateral axis CG control is ordinarily not a factor in maintaining helicopter weight and balance.

2. The moment of tail mounted components is subjected to constant change.

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

Back 33

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

Hint 33

The same theory and methodology for calculating weight and balance applies to both helicopters and airplanes. The formula weight × Arm = moment applies in both cases

Front 34

Improper loading of a helicopter with the results and exceeding other fore or aft CG limits is hazardous due to the

Back 34

Reduction or loss of effective cyclic pitch control

Hint 34

Helicopters generally have a smaller CG enveloped then airplanes, so extra caution must be observing during loading. Trimming of a helicopter which has less than ideal balance is done with the cyclic pitch control. And extreme out of balance conditions for four or a cyclic control maybe insufficient to maintain control.

Front 35

The CG range in single rotor helicopters is

Back 35

More restricted than for airplanes

Hint 35

Most helicopters have a restricted CG range as compared to airplanes. In some cases, is strange is less than 3 inches.