ACM-115 W & B FAA QUESTIONS

Question 1

8155
The useful load of an aircraft consists of the:

1. Crew, usable fuel, passengers, and cargo
2. Crew, usable fuel, oil and fixed equipment
3. Crew, passengers, usable fuel, oil, cargo, and fixed equipment

Answer 1

1

The useful load of an aircraft is the difference between its empty weight and the maximum allowable gross weight. It does not include any of the fixed or required equipment as these are part of the empty weight.

(AM.I.C.K1) - FAA-H-8083-30

Question 2

8158
(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,

A. Neither 1 nor 2 is true.
B. Only 1 is true.
C. Only 2 is true

Answer 2

A

Statement 1 is not true. No Federal Aviation Regulation requires that private aircraft be weighed periodically.
Statement 2 is not true. When a private aircraft is altered, the weight and balance records must be updated to show any change that has been made in the weight or in the empty weight CG location.
These changes are normally found mathematically rather than by actually weighing the aircraft.

(AM.I.C.K3) - FAA-H-8083-30

Question 3

8163
The maximum weight of an aircraft is the:

1. Empty weight plus crew, maximum fuel, cargo, and baggage
2. Empty weight plus crew, passengers, and fixed equipment
3. Empty weight plus useful load

Answer 3

3

The useful load of an aircraft is found by subtracting the empty weight of the aircraft from the maximum weight. Therefore, the maximum weight is the sum of the empty weight and the useful load.

(AM.I.C.K5)- FAA-H-8083-30

Question 4

8167
Zero fuel weight is the:

1. Dry weight plus the weight of fuel crew, passengers, and cargo
2. Basic operating weight without crew, fuel, and cargo
3. Maximum permissible weight of a loaded aircraft (passengers, crew, and cargo) without fuel.

Answer 4

3

The zero fuel weight of an aircraft is the maximum allowable weight of the loaded aircraft without fuel. The weight of the cargo, passengers, and crew are included in the zero fuel weight.

(AM.I.C.K1)-FAA-H-8083-30

Question 5

8169-1
When dealing with weight and balance of an aircraft, the term “maximum weight” is interpreted to mean the maximum:

1. Weight of the empty aircraft
2. Weight of the useful load
3. Authorized weight of the aircraft and its contents

Answer 5

3

Maximum weight, when considering the weight and balance of an aircraft, is the maximum certificated weight of the aircraft as specified on the Type Certificate Data Sheet or in the Aircraft Specification.

(AM.I.C.K1) - FAAH - 8083-30

Question 6

8170. The useful load of an aircraft is the difference between:

A. The maximum takeoff weight and basic empty weight.
B. Maximum ramp or takeoff weight as applicable, and zero fuel weight.
C. (1) the weight of an aircraft with all seats filled, full baggage/cargo, and full fuel, and (2) aircraft weight with all seats empty, no baggage/cargo, and minimum operating fuel.

Answer 6

A

The useful load of an aircraft is the difference between the maximum takeoff weight and the basic empty weight of the aircraft.

(AM.J.C.K1) - FAA-H-8083-30

Question 7

8171
When determining the empty weight of an aircraft, certificated under current airworthiness standards (14 CFR Part 23), the oil contained in the supply tank is considered:

1. Part of the empty weight
2. Part of the useful load
3. Same as the fluid contained in the water injection reservoir

Answer 7

1

The empty weight of an aircraft certificated under Part 23 includes a full supply tank of engine oil.

(AM.I.C.K1) - 14 CFR §23.29

Question 8

8173
The maximum weight as used in weight and balance control of a given aircraft can normally be found:

1. By adding the weight of full fuel, pilot, passengers, and maximum allowable baggage to the empty weight.
2. In the Aircraft specification or Type Certificate Data Sheet
3. By adding the empty weight and payload

Answer 8

2

Type Certificate Data Sheets or Aircraft Specifications include the maximum certificated gross weight of an aircraft.

(AM.I.C.K5) - FAA-H-8083-30

Question 9

8176
The amount of fuel used for computing empty weight and corresponding CG is:

1. Empty fuel tanks
2. Unusable fuel
3. Amount of fuel necessary for 1/2 hour of operation

Answer 9

2

The amount of fuel to be in the aircraft when it is weighed for purposes of finding its empty weight is only the unusable fuel. If the aircraft is weighed with full fuel tanks, the weight of the fuel must be subtracted from the weight found by the scales. The weight of the unusable fuel and its CG can be found in the Type Certificate Data Sheet for the aircraft.

(AM.I.C.K3) - 14 CFR §23.29

Question 10

8169-2
Most modern aircraft are designed so that if all seats are occupied, full baggage weight is carried, and all fuel tanks are full, what will be the weight condition of the aircraft?

1. It will be in excess of maximum takeoff weight
2. Will be at maximum basic operating weight (BOW).
3. Will be at maximum taxi or ramp rate.

Answer 10

1

Most modern aircraft are designed so that if all seats are occupied, full baggage weight is carried, and all fuel tanks are full, the aircraft will be grossly overloaded. It will be in excess of maximum takeoff weight.

(AM.I.C.K5) - FAAH - 8083-30

Question 11

8169-3
The major source of weight change for most aircraft as they age is caused by:

1. Accumulation of grime and debris in hard-to-reach areas of the structure, & moisture absorption in cabin insulation.
2. Repairs and alterations
3. Installation of hardware & safety wire, and added layers of primer and paint on structure.

Answer 11

2

Changes of fixed equipment may have a major effect upon the weight of an aircraft. Many aircraft are overloaded by the installation of extra radios or instruments.

(AM.I.C.K5) - FAA-H-8083-30

Question 12

8107
A specific measured distance from the datum or some other point identified by the manufacturer, to a point in or on the aircraft is called a:

1. Zone number
2. Reference number
3. Station number

Answer 12

3

A station number is a number used to identify the number of inches from the datum or other point identified by the manufacturer to a point in or on the aircraft.

(AM.I.B.K4) - FAA-H-8083-30

Question 13

8161
What type of measurement is used to designate the arm in weight and balance computation?

1. Distance
2. Weight
3. Weight / distance

Answer 13

1

The arm used in weight and balance computation is the distance, in inches, between the center of gravity of an object and the aircraft datum.

(AM.I.C.K1) - FAA-H - 8083-30

Question 14

8166
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:

1. All measurement arms will be in negative numbers
2. All measurement arms will be in positive numbers
3. Measurement arms can be either positive or negative numbers depending on the manufacturer’s preference.

Answer 14

2

The reference datum used for weight and balance purposes can be located anywhere the aircraft manufacturer chooses. Current practice is to locate it on or near the nose or out ahead of the aircraft. The reason for this is that all of the arms will be positive (they will all be behind the datum).
If all of the arms are positive, the moment of all added weight will be positive, and the moment of all removed weight will be negative. This will simplify weight and balance computations and will give less chance for error.

(AM.I.C.K4) - FAA-H-8083-30

Question 15

8182
If a 40 lb. generator applies +1400 inch lbs. to a reference axis, the generator is located:

1. -35 from the axis
2. +35 from the axis
3. +25 from the axis

Answer 15

2

The distance from the axis is found by dividing the moment
by the weight.
1,400 + 40 = 35
Since the moment is positive, the arm will also be positive. The generator is located +35 inches from the axis.

(AM.I.C.K4) - FAA-H-8083-30

Question 16

8153
When computing weight and balance, an airplane is considered to be in balance when:

1. The average moment arm of the loaded airplane falls within its CG range.
2. All moment arms of the plane fall within CG range
3. The movement of the passengers will not cause the moment arms to fall outside the CG range.

Answer 16

1

An airplane is considered to be in balance when the average moment arm of the loaded aircraft falls within its CG range.

(AM.I.C.K6) - FAA-H-8083-30

Question 17

8191-1
An aircraft’s LEMAC and TEMAC are defined in terms of distance:

1. From the datum
2. From each other
3. Ahead of and behind the wing center of lift, respectively

Answer 17

1

LEMAC is the leading edge of the mean aerodynamic chord, TEMAC is the trailing edge of the mean aerodynamic chord. These are locations measured from the datum and expressed in station numbers.

(AM.I.C.K1) - FAA-H-8083-30

Question 18

8191-2
If an aircraft CG is found to be at 24% of MAC, that 24% is an expression of the:

1. Distance from the TEMAC
2. Distance from the LEMAC
3. Average distance from the LEMAC to the wing center of lift.

Answer 18

2

When the CG of an aircraft is expressed as a percentage of MAC, its location is determined by finding that percent of MAC (the distance between the LEMAC and the TEMAC).
The CG is located at this distance measured from the LEMAC.

(AM.J.C.K1) - FAA-H-8083-30

Question 19

8183-1
All other things being equal, if an item of useful load located aft of an aircraft’s CG is removed, the aircraft’s CG change will be:

1. Aft in proportion to the weight of the item and its location in the aircraft.
2. Forward in proportion to the weight of the item and its location in the aircraft.
3. Forward in proportion to the weight of the item, regardless of its location in the aircraft.

Answer 19

2

An item located aft of an aircraft’s CG has a positive arm, and when it is removed, it has a negative weight. A positive arm and a negative weight produce a negative moment (+arm x -weight= -moment). A negative moment moves the CG forward by an amount that is proportional to the weight of the item and its location in the aircraft.

(AM.I.C.K6) - FAA-H-8083-30

Question 20

8156
Which 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?

1. Reweighing the aircraft
2. The applicable Aircraft Specification or Type Certificate Data Sheet
3. The applicable flight manual or pilot’s operating handbook

Answer 20

1

If the aircraft weight and balance records are lost, destroyed, or otherwise inaccurate, the aircraft must be re-weighed. The Aircraft Specification Sheet, Type Certificate Data Sheet, flight manual, and pilot’s operating handbook do not list the empty weight of the specific aircraft.

(AM.I.C.K3) - FAA-H-8083-30

Question 21

8160
To obtain useful weight data for purposes of determine the CG, it is necessary that an aircraft be weighed:

1. In a level flight attitude
2. With all items of useful load installed
3. With at least minimum fuel (1/12 gallon per METO horsepower) in the fuel tanks

Answer 21

1

When an aircraft is being weighed, it must be placed in a level-flight attitude. When the aircraft is in its level-flight attitude, the centers of gravity of all of the items are in their correct locations relative to the datum.

(AM.I.C.K2) - FAA-H-8083-30

Question 22

8159-1
Which device(s) is/are used to obtain the greatest accuracy of aircraft leveling?

A. Plumb bob and chalk line.
B. Spirit level.
C. Electronic load cells.

Answer 22

B

The leveling means for determining weight and balance is specified by the aircraft manufacturer and is listed in the Type Certificate Data Sheets. Proper level may be determined with spirit levels placed across leveling lugs or along the door sill.

(AM.I.C.K3) - FAA-H-8083-30

Question 23

8154
What tasks are completed prior to weighing an aircraft to determine its empty weight?

1. Remove all items except those on the aircraft equipment list, drain fuel & hyd fluid.
2. Remove all items on aircraft equipment list, drain fuel, compute oil & hyd fluid weight.
3. Remove all items except those on aircraft equipment list, drain fuel & fill hyd reservoir.

Answer 23

3

Part 23, which applies to most general aviation aircraft, defines empty weight of an aircraft. Empty weight includes fixed ballast, unusable fuel, full operating fluids including oil, hydraulic fluid and other fluids required for normal operation of airplane systems except potable water, lavatory precharge water, and water intended for injection in the engines. When preparing an airplane for weighing, remove all items except those on the equipment list, drain the fuel, and fill the hydraulic reservoir.

(AM.I.C.K1) - FAA-H-8083-30

Question 24

8165
What should be clearly indicated on the aircraft weighing form?

1. Minimum allowable gross weight
2. Weight of unusable fuel
3. Weighing points

Answer 24

3

Since the weight and balance computations are based on the scale weights of an aircraft, the weighing form used with a specific aircraft should specify not only the leveling means, but also the location of the weighing points.

(AM.I.C.K5) - FAA-H-8083-30

Question 25

8168 The empty weight of an airplane is determined by: 1. Adding net weight of each weighing point & multiplying measured distance to datum. 2. Subtracting tare weight from the scale reading & adding weight of each weighing point 3. Multiplying the measured distance from each weighing point to the datum times the sum of scale reading less the tare weight.

Answer 25

2 When an aircraft is to be weighed, it is placed on the scales and chocked to prevent its rolling. The weight of the chocks is called tare weight. The empty weight of the aircraft is found by subtracting the tare weight from the scale readings, to get the net weight. The net weight from each weighing point is added to get the total net weight which is the total empty weight of the aircraft. (AM.I.C.K5) - FAA-H-8083-30

Question 26

8157-1 In the process of weighing an airplane toward obtaining the CG, the arms from the weighing points always extend: 1. Parallel to the center line of the airplane 2. Straight forward from each of the landing gear 3. Directly from each weighing point to the others

Answer 26

1 An arm, used in determining the CG of an airplane, is the horizontal distance from the datum to the center of gravity of the item. An arm is always measured parallel to the center line of the airplane. (AM.I.C.K3)- FAA-H-8083-30

Question 27

8157-3 Which of the following may cause erroneous scale readings? A. Wheel chocks in place. B. Parking brakes set. C. Parking brakes not set.

Answer 27

B When positioning an aircraft on platform-type scales for weighing, the parking brakes must be released so there will be no side load applied to the scale platform. Any side load will cause an erroneous scale reading. (AM.I.C.K3) - FAA-H-8083-30

Question 28

8167-1 If it is necessary to weigh an aircraft with full fuel tanks, all fuel weight must be subtracted from the scale reading (s). 1. Except minimum fuel 2. Including unusable fuel 3. Except unusable fuel

Answer 28

3 The empty weight of an aircraft includes the weight of the unusable fuel. The weight and location of the unusable fuel are found in Note 1 in the section of the Type Certificate Data Sheets, "Data Pertinent to All Models." (AM.I.C.K5) - FAA-H-8083-1

Question 29

8154-1 What is meant by the term "residual fuel"? 1. A known amount of fuel left in the tanks, lines, and engine 2. The fuel remaining in the tanks, lines, and engine after draining 3. The fuel remaining in the tank, lines, and engine before draining

Answer 29

2 When weighing an aircraft to determine its empty weight, only the weight of residual (unusable) fuel should be included. Residual fuel is the fluid that will not normally drain out because it is trapped in the fuel lines and tanks. (AM.I.C.K1) - FAA-H-8083-30

Question 30

8186 When an empty aircraft is weighed, the combined net weight at the main gears is 3,540 lbs. with an arm of 195.5". At the nose gear, the net weight is 2,322 lbs. with an arm of 83.5". The datum line is forward of the nose of the aircraft. What is the CG of the aircraft? 1. 151.1 2. 155.2 3. 146.5

Answer 30

1 The empty weight of this aircraft is 5,862 pounds, and its empty weight CG is located at fuselage station 151.14. (AM.J.C.KB-A) C 43.13-1B

Question 31

8162 What determines whether the value of the moment is preceded by a plus (+) or a minus (-) sign in aircraft weight & balance? 1. The location of the weight in reference to the datum. 2. The result of a weight being added or removed and its location relative to the datum. 3. The location of the datum in reference to the aircraft CG.

Answer 31

2 A moment is a force that causes rotation about a point, and in order to specify the direction of the rotation, (+) and (-) signs are assigned to the moment. A positive moment is one that causes the aircraft nose to go up, and a negative moment is one that causes the nose to go down. Since a moment is the product of weight and the distance from the datum, and both of these are signed values, we have four choices for the sign of the moment: 1. A positive weight (weight added) and a positive arm (arm behind the datum) give a positive moment. 2. A positive weight and a negative arm (arm ahead of the datum) give a negative moment. 3. A negative weight (weight removed) and a positive arm give a negative moment. 4. A negative weight and a negative arm gives a positive moment. (AM.I.C.K4) - FAA-H-8083-30

Question 32

8174 An aircraft with an empty weight of 2100 lbs. and an empty weight CG of +32.5 was altered as follows: 1. 2 18 lb. passenger seats located at +73 were removed. 2. Structural modifications were made at +77 increasing weight by 17 lbs. 3. A seat and safety belt weighing 25 lbs. were installed at +74.5. 4. Radio equipment weighing 35 lbs. was installed at +95. What is the new empty weight CG? 1. 34.01 2. 33.68 3. 34.65

Answer 32

2 The new empty weight is 2,141 pounds, and the CG is located at fuselage station 33.68. (AM.I.C.KB) - FAAH-8083-30

Question 33

8178 As weighed, the total empty weight of an aircraft is 5,862 lbs. with a moment of 885,957. When the aircraft was weighed 20 lbs. of potable water were on board at +84 and 23 lbs. of hydraulic fluid were in a tank located at +101. What is the empty weight CG of the aircraft? 1. 150.700 2. 151.700 2. 151.365

Answer 33

3 When weighing an aircraft to find its empty weight, a full reservoir of hydraulic fluid is included, but the potable water is not part of the required equipment. When the water is computed out of the empty weight, we find the new empty weight to be 5,842 pounds and the new empty weight CG is located at fuselage station 151.365. (AM.I.C.KB) - FAA-H-8083-30

Question 34

8180 An aircraft with an empty weight of 1800 lbs. and an empty weight CG of +31.5 was altered as follows: 1. Two 15 lb. passenger seats located at +72 were removed. 2. Structural modifications increasing the weight 14 lbs. were made at +76. 3. A seat and safety belt weighing 20 lbs. were installed at +73.5. 4. Radio equipment weighing 30 lbs. was installed at +30. What is the new empty weight CG? 1. +30.61 2. +31.61 3. +32.69

Answer 34

2 The alterations shown here will change the empty weight to 1,834 pounds and the empty weight CG will move to fuselage station 31.61. (AM.I.C.KB)-FAA-H-8083-30

Question 35

8181 An aircraft had an empty weight of 2886 lbs. with a moment of 101,673.78 before several alterations were made. The alterations included: 1. Removing 2 passenger seats (15 lbs. each) at +71. 2. Installing a cabinet (97 lbs.) at +71. 3. Installing a seat and safety belt (20 lbs.) at +71. 4. Installing radio equipment (30 lbs.) at +94. The alterations caused the new empty weight CG to move: 1. 1.62" AFT of the original empty weight CG. 2. 2.03" FWD of the original empty weight CG. 3. 2.03" AFT of the original empty weight CG.

Answer 35

1 The alterations shown here will change the empty weight to 3,003 pounds and the empty weight CG will move to fuselage station 36.85. Before the alteration, the empty weight CG was at +35.23. The new empty weight CG of +36.85 is 1.62 inches aft of the original. (AM.I.C.KB) - FAA-H-8083-30

Question 36

8183 In a balance computation of an aircraft from which an item located AFT of the datum was removed, use: 1. (-) weight x (+ARM) (-) moment 2. (-) weight x (-) ARM (+) moment 3. (+) weight x (-) ARM (-) moment

Answer 36

1 A moment is a force that causes rotation about a point, and in order to specify the direction of the rotation, signs (+) and (-) are assigned to the moment. In aircraft weight and balance, a positive moment is a moment that causes the aircraft nose to go up, and a negative moment is one that causes the nose to go down. Since a moment is the product of weight and the distance from the datum and both of these are signed values, we have four choices for the sign of the moment: 1. A positive weight (weight added) and a positive arm (arm behind the datum) give a positive moment. 2. A positive weight and a negative arm (arm ahead of the datum) give a negative moment. 3. A negative weight (weight removed} and a positive arm give a negative moment. 4. A negative weight and a negative arm give a positive moment. (AM.I.C.K1) - FAA-H-8083-30

Question 37

8184 Datum is forward of the main gear center point. 30.24" Actual distance between tail gear and main gear center points. 360.26 Net weight at RH main gear. 9,980 lbs Net weight at LH main gear. 9,770 lbs Net weight at Tail Gear. 1,970 lbs These items were in the aircraft when weighed: 1. LAV water tank full (34 lbs. at +352) 2. Hydraulic Fluid (22 lbs at -8) 3. Removable ballast (146 lbs at +380) What is the empty weight CG of the aircraft? 1. 62.92" 2. 60.31 3. 58.54"

Answer 37

2 We must first find the empty weight CG of the aircraft as it is weighed. Remove, by computation, the weight of the water and the removable ballast. Leave the hydraulic fluid in, as it is part of the empty weight. The new empty weight, as corrected for the water and the ballast, is 21,540 pounds and the new empty weight CG is at fuselage station 60.31. (AM.I.C.KB)- FAA-H-8083-30

Question 38

8187 An aircraft with an empty weight of 1500 lbs. and an empty weight CG of +28.4 was altered as follows: 1. 2 12 lb. seats located at 68.5 were removed. 2. Structural modifications weighing 28 lbs. were made at +73. 3. A seat and safety belt weighing 30 lbs. were installed at +70.5. 4. Radio equipment weighing 25 lbs. was installed at +85. What is the new empty weight CG? 1. +23.51 2. +31.35 3. +30.30

Answer 38

3 The empty weight of this aircraft is 1,559 pounds, and its empty weight CG is located at fuselage station 30.30. (AM.I.C.KB) - FAA-H-8083-30

Question 39

8188 The following alterations were performed on an aircraft: 1. A model B engine weighing 175 lbs. was replaced by a model D engine weighing 185 lbs at -62.00 station. 2. The aircraft weight and balance records show the previous empty weight to be 998 lbs. and an empty weight CG of 13.48". What is the new empty weight CG? 1. 13.96" 2. 14.25" 3. 12.73"

Answer 39

3 The new empty weight is 1,008 pounds, and the new empty weight CG is at fuselage station 12.73. (AM.I.C.KB) - FAA-H-8083-30

Question 40

8156-1 Where do you look to determine the operating CG range when calculating a new aircraft weight and balance document? 1. Airframe Data Plate 2. Type Certificate Data Sheet 3. Pilot's Aircraft Information Manual

Answer 40

2 Some of the important weight and balance information found in a Type Certificate Data Sheet is as follows: center of gravity range, maximum weight, leveling means, number of seats and location, baggage capacity, fuel capacity, datum location, engine horsepower, oil capacity, amount of fuel in empty weight, and amount of oil in empty weight. (AM.I.C.K3) - FAA-H-8083-30

Question 41

8157 In the theory of weight and balance, what is the name of the distance from the fulcrum to an object? 1. Lever Arm 2. Balance Arm 3. Fulcrum Arm

Answer 41

1 In the theory of weight and balance, the distance of any object from the fulcrum is called the lever arm. (AM.I.C.K1) - FAA-H-8083-30

Question 42

8179 Two boxes which weigh 10 lbs. and 5lbs. are placed in an aircraft so that their distance AFT from the CG are 4 ft. and 2 ft. respectively. How far forward of the CG should a third box weighing 20 lbs. be placed so that the CG will not be changed. A. 3 feet B. 2.5 feet C. 8 feet

Answer 42

2 In order to not change the CG of the aircraft, it is necessary that the moment of the 20-pound weight be the same but have the opposite sign as the combined moments of the 10-pound box and the 5-pound box. The moment of the 10-pound box is 40 pound/feet. The moment of the 5-pound box is 10 pound/feet. The total positive moment is 50 pound/feet, and this must be balanced by a 50-pound/ foot negative moment. By dividing the required moment by the weight, we find that the 20-pound box will have to be placed 2.5 feet ahead of the CG. (AM.I.C.K4) - FAAH - 8083-30

Question 43

8177 An aircraft loaded weight 4954 lbs. at a CG of +30.5". The CG range is +32.0" - 42.1". Find the minimum weight of the ballast necessary to bring the CG within the CG range. The ballast arm is +162" 1. 61.98 lbs. 2. 30.58 lbs. 3. 57.16 lbs.

Answer 43

3 The CG of this aircraft is out of allowable range by 1.5 inches. Its CG is at fuselage station 30.5 and the forward CG limit is at station 32.0. To find the amount of ballast needed to be attached at fuselage station 162, multiply the empty weight of the aircraft by the distance the CG is to be moved and divide this by the distance between the ballast location and the desired CG location. Attaching a 57.16-pound ballast at fuselage station 162 will move the empty weight CG to fuselage station 32.0. (AM.I.C.K9)- FAA-H-8083-30

Question 44

8185 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 computed at their minimum weights are those located forward of the: 1. Forward CG limit 2. Datum 3. Rearward CG limit

Answer 44

3 When making a rearward weight and balance check to determine that the loaded CG cannot fall behind the rearward CG limit, you should use the maximum weight of all items of the useful load whose CG is behind the rear limit and the minimum weight for all items that are ahead of the rearward CG limit. (AM.I.C.Kl)-AC 43.13-1B

Question 45

8189 If the empty weight CG of an airplane lies within the empty weight CG limits,: 1. It is necessary to calculate CG extremes 2. It is not necessary to calculate CG extremes 3. Minimum fuel should be used in both forward and rearward CG checks.

Answer 45

2 If the empty weight CG of an airplane lies within the empty weight CG limits, it is not necessary to calculate the CG extremes. The airplane cannot be legally loaded in such a way that either its forward or aft CG limits can be exceeded. (AM.I.C.KB) - FAA-H-8083-1

Question 46

8190 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: 1. Rearward CG limit 2. Forward CG limit 3. Datum

Answer 46

2 When computing a maximum forward-loaded CG of an aircraft, you should use maximum weight for all items of the useful load located ahead of the forward CG limit, and the minimum weight for all items of the useful load located behind the forward CG limit. (AM.I.C.K5) -AC 43.13-1B

Question 47

8185-1 When, or under what conditions are adverse loading checks conducted? 1. At or below the maximum gross weight of the aircraft 2. Any time a repair or alteration causes EWCG to fall within the EWCG range. 3. At specified flight hour or calendar time intervals.

Answer 47

1 When a repair or alteration of an aircraft has been made that causes the empty weight-center of gravity to fall outside the empty weight CG range, an adverse-loaded CG check should be conducted to determine whether or not it is possible to load the aircraft in such a way that its operational CG will fall outside of its allowable limits. (AM.I.C.Kl) - FAA-H-8083-1

Question 48

8185-2 When accomplishing loading computations for a small aircraft, necessary information obtained from the weight and balance records would include: 1. Unusable fuel weight and distance from datum. 2. Weight and location of permanent ballast. 3. Current empty weight and empty weight CG

Answer 48

3 When accomplishing loading computations for a small aircraft, you must know the current empty weight and the empty weight CG of the aircraft. This information is essential to determine the loaded weight and loaded CG. (AM.J.C.K1-) FAA-H-8083-30

Question 49

8164 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 & balance. 2. The moment of tail-mounted components is subject to constant change. 3. Weight and balance procedures for airplanes generally also apply to helicopters.

Answer 49

3 When computing the weight and balance of an aircraft, it makes no difference whether the aircraft has a fixed wing or a rotary wing. The procedures are the same, but the actual effect of weight and balance is more critical for a helicopter than for a fixed-wing aircraft. (AM.I.C.K3) - FAA-H-8083-30

Question 50

8172 Improper loading of a helicopter which results in exceeding either the fore or aft CG limits is hazardous due to the: 1. Reduction or loss of effective cyclic pitch control. 2. Coriolis effect being translated to the fuselage. 3. Reduction or loss of effective collective pitch control

Answer 50

1 If a helicopter is loaded in such a way that its CG is either too far forward or too far aft, flight will be hazardous. The cyclic pitch control will likely not be effective enough to control the helicopter against its out-of-balance condition. (AM.I.C.Kl) - FAA-H-8083-30

Question 51

8175 The CG range in single-rotor helicopters is: 1. Much greater than for airplanes 2. Approximately the same as the CG range for airplanes 3. More restricted than for airplanes

Answer 51

3 Most helicopters have a much more restricted CG range than do airplanes. In some cases, this range is less than three inches. (AM.I.C.K6) - FAA-H-8083-30

Question 52

10021 Which statement is true regarding weight and balance? 1. The flight crew is solely responsible for ensuring proper weight and balance. 2. If the CG is out of the manufacturer's CG limits, the aircraft will not display the stability characteristics it was designed for which could cause the aircraft to stall or spin. 3. Weight and balance will impact the performance of the aircraft, such as range, but it will not impact the stability characteristics of the aircraft.

Answer 52

2

Question 53

10022 Which of the following will not be a result of overloading an aircraft? 1. Shortened cruising range 2. Shorter landing roll 3. Excessive loads imposed on the structure and especially the landing gear.

Answer 53

2

Question 54

8159. What FAA-approved document gives the leveling means to be used when weighing an aircraft? A. Type Certificate Data Sheet. B. AC 43.13-18. C. Manufacturer's maintenance manual.

Answer 54

A The FAA-approved document that gives the leveling means to be used when weighing a specific aircraft is the Type Certificate Data Sheet for that aircraft. (AM.I.C.K3) - FAA-H-8083-30

Question 55

8157-2. Which of the following have an effect on aircraft CG results when conducting a weight and balance check? A. Leaving the parking brake on. B. Leaving the parking brake off. C. Leaving the down locks installed.

Answer 55

C All of the required equipment must be properly installed, and there should be no equipment installed that is not included in the equipment list. (AM.I.C.K3) - FAA-H- 8083-30

Question 56

8169-3 The major source of weight change for most aircraft as they age is caused by A. Accumulation of grime and debris in hard-to-reach areas of the structure, and moisture absorption in cabin insulation. B. Repairs and alterations. C. Installation of hardware and safety wire, and added layers of primer and paint on the structure.

Answer 56

B Changes of fixed equipment may have a major effect upon the weight of an aircraft. Many aircraft are overloaded by the installation of extra radios or instruments. (AM.I.C.K5) - FAA-H-8083-30

Question 57

8191 Find the empty weight CG location for the following tricycle-gear aircraft. Each main wheel weighs 753 pounds, nose wheel weighs 22 pounds, distance between nose wheel and main wheels is 87.5 inches, nose wheel location is +9.875 inches from datum, with 1 gallon of hydraulic fluid at -21.0 inches included in the weight scale. A. +97.375 inches. B. +95.61 inches. C. +96.11 inches.

Answer 57

C The empty weight of this aircraft is 1,528 pounds, and its empty weight CG is located at fuselage station 96.115. (AM.I.C.KB) - FAA-H-8083-30

Question 58

8191-3. Which should be accomplished before jacking an aircraft? A. Install critical stress panels or plates. B. Determine that the fuel tanks are empty. C. Make sure the aircraft is leveled laterally.

Answer 58

A Before some aircraft are jacked, stress panels or plates must be installed to distribute the weight of the aircraft over the jack pad. When any aircraft is jacked, the recommendations of the aircraft manufacturer must be followed in detail. (AM.I.C.K10) - FAA-H-8083-30

Question 59

8291-1 Why is it generally necessary to jack an aircraft indoors for weighing? A. So aircraft may be placed in a level position. B. So that air currents do not destabilize the scales. C. So weighing scales may be calibrated to 0 pounds.

Answer 59

B An aircraft should be weighed indoors to prevent the possibility of air currents moving the aircraft and knocking it off the jacks or causing the scales to give an inaccurate reading. (AM.I.C.K10) - FAA-H-8083-30