A&P - General

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 arms to fall outside the CG range.

What tasks are completed prior to weighing an aircraft to determine its 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.

The useful load of an aircraft consists of the. crew, usable fuel, passengers, and cargo. crew, usable fuel, oil, and fixed equipment. crew, passengers, usable fuel, oil, cargo, and fixed equipment.

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?. Reweighing the aircraft. The applicable Aircraft Specification or Type Certificate Data Sheet. The applicable flight manual or pilot's operating handbook.

In the theory of weight and balance, what is the name of the distance from the fulcrum to an object?. Lever arm. Balance arm. Fulcrum arm.

In the process of weighing an airplane toward obtaining 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.

Which would have an effect on aircraft CG results when conducting a weight and balance check?. Leaving the parking brake on. Leaving the parking brake off. Leaving the downlocks installed.

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.

(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 No. 1 nor No. 2 is true. only No. 1 is true. only No. 2 is true.

What FAA-approved document gives the leveling means to be used when weighing an aircraft?. Type Certificate Data Sheet. AC 43.13-1B. Manufacturer's maintenance manual.

Use of which of the following generally yields the highest degree of aircraft leveling accuracy?. Plumb bob and chalk line. Spirit level(s). Electronic load cell(s).

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 no more than minimum fuel (1/12-gallon per METO horsepower) in all fuel tanks.

What type of measurement is used to designate the arm in weight and balance computation?. Distance. Weight. Weight x distance.

What determines whether the value of a moment is preceded by a plus (+) or a 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.

The maximum weight of an aircraft is the. empty weight plus crew, maximum fuel, cargo, and baggage. empty weight plus crew, passengers, and fixed equipment. empty weight plus useful load.

Which statement is true regarding helicopter weight and balance?. Regardless of internal or external loading, lateral axis 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.

What should be clearly indicated on the aircraft weighing form?. Minimum allowable gross weight. Weight of unusable fuel. Weighing points.

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,. all measurement arms will be in negative numbers. all measurement arms will be in positive numbers. measurement arms can be either positive or negative numbers depending on the manufacturer's preference.

Maximum 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, and cargo) without fuel.

If it is necessary to weigh an aircraft with full fuel tanks, all fuel weight must be subtracted from the scale reading(s). except minimum fuel. including unusable fuel. except unusable fuel.

The empty weight of an airplane is determined by. adding the net weight of each weighing point and multiplying the measured distance to the datum. subtracting the tare weight from the scale reading and adding the weight of each weighing point. multiplying the measured distance from each weighing point to the datum times the sum of scale reading less the tare weight.

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.

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?. It will be in excess of maximum takeoff weight. It will be at maximum basic operating weight (BOW). It will be at maximum taxi or ramp weight.

The major source of weight change for most aircraft as they age is caused by. accumulation of grime and debris in hard-to-reach areas of the structure, and moisture absorption in cabin insulation. repairs and alterations. installation of hardware and safety wire, and added layers of primer and paint on the structure.

The useful load of an aircraft is the difference between. the maximum takeoff weight and basic empty weight. maximum ramp or takeoff weight as applicable, and zero fuel weight. (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.

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

Improper loading of a helicopter which results in exceeding either the fore or 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.

The maximum weight as used in weight and balance control of a given aircraft can normally be found. by adding the weight of full fuel, pilot, passengers, and maximum allowable baggage to the empty weight. in the Aircraft Specification or Type Certificate Data Sheet. by adding the empty weight and payload.

An aircraft with an empty weight of 2,100 pounds and an empty weight CG +32.5 was altered as follows: 1. two 18-pound passenger seats located at +73 were removed; 2. structural modifications were made at +77 increasing weight by 17 pounds; 3. a seat and safety belt weighing 25 pounds were installed at +74.5; and 4. radio equipment weighing 35 pounds was installed at +95. What is the new empty weight CG?. +34.01. +33.68. +34.65.

The CG range in single-rotor helicopters is. much greater than for airplanes. approximately the same as the CG range for airplanes. more restricted than for airplanes.

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.

An aircraft as loaded weighs 4,954 pounds at a CG of +30.5 inches. The CG range is +32.0 inches to +42.1 inches. 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.

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 a tank located at +101. What is the empty weight CG of the aircraft?. 150.700. 151.700. 151.365.

Two boxes which weigh 10 pounds and 5 pounds are placed in an airplane so that 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.

An aircraft with an empty weight of 1,800 pounds and an empty weight CG of +31.5 was altered as follows: 1. two 15-pound passenger seats located at +72 were removed; 2. structural modifications increasing the weight 14 pounds were made at +76; 3. a seat and safety belt weighing 20 pounds were installed at +73.5; and 4. radio equipment weighing 30 pounds was installed at +30. What is the new empty weight CG?. +30.61. +31.61. +32.69.

An aircraft had an empty weight of 2,886 pounds with a moment of 101,673.78 before several alterations were made. The alterations included: 1. removing two passenger seats (15 pounds each) at +71; 2. installing a cabinet (97 pounds) at +71; 3. installing a seat and safety belt (20 pounds) at +71; and 4. installing radio equipment (30 pounds) at +94. The alterations caused the new empty weight CG to move. 1.62 inches aft of the original empty weight CG. 2.03 inches forward of the original empty weight CG. 2.03 inches aft of the original empty weight CG.

If a 40-pound generator applies +1400 inch-pounds to a reference axis, the generator is located. -35 from the axis. +35 from the axis. +25 from the axis.

In a balance computation of an aircraft from which an item located aft of the datum was removed, use. (-)weight X (+)arm (-)moment. (-)weight X (-)arm (+)moment. (+)weight X (-)arm (-)moment.

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. 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.

Datum is forward of the main gear center point 30.24 inches Actual distance between tail gear and main gear center points 360.26 inches Net weight at right main gear 9,980 pounds Net weight at left main gear 9,770 pounds Net weight at tail gear 1,970 pounds These items were in the aircraft when weighed: 1. Lavatory water tank full (34 pounds at +352). 2. Hydraulic fluid (22 pounds at -8). 3. Removable ballast (146 pounds at +380). What is the empty weight CG of the aircraft described above?. 62.92 inches. 60.31 inches. 58.54 inches.

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. forward CG limit. datum. rearward CG limit.

When, or under what condition(s) are adverse loading checks conducted?. At or below the maximum gross weight of the aircraft. Anytime a repair or alteration causes EWCG to fall outside the CG range. At specified flight hour or calendar time intervals.

When accomplishing loading computations 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.

When an empty aircraft is weighed, the combined net weight at the main gears is 3,540 pounds with an arm of 195.5 inches. At the nose gear, the net weight is 2,322 pounds with an arm of 83.5 inches. 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.

An aircraft with an empty weight of 1,500 pounds and an empty weight CG of +28.4 was altered as follows: 1. two 12-pound seats located at +68.5 were removed; 2. structural modifications weighing +28 pounds were made at +73; 3. a seat and safety belt weighing 30 pounds were installed at +70.5; and 4. radio equipment weighing 25 pounds was installed at +85. What is the new empty weight CG?. +23.51. +31.35. +30.30.

The following alteration was performed on an aircraft: A model B engine weighing 175 pounds was replaced by a model D engine weighing 185 pounds at a -62.00-inch station. The aircraft weight and balance records show the previous empty weight to be 998 pounds and an empty weight CG of 13.48 inches. What is the new empty weight CG?. 13.96 inches. 14.25 inches. 12.73 inches.

If the empty weight CG of an airplane lies within the empty weight CG limits,. it is necessary to calculate CG extremes. it is not necessary to calculate CG extremes. minimum fuel should be used in both forward and rearward CG checks.

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.

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

An aircraft's LEMAC and TEMAC are defined in terms of distance. from the datum. from each other. ahead of and behind the wing center of lift, respectively.

If an aircraft CG is found to be at 24 percent of MAC, that 24 percent is an expression of the. distance from the TEMAC. distance from the LEMAC. average distance from the LEMAC to the wing center of lift.

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 tank, lines, and engine before draining.

Where do you look to determine the operating CG range when calculating a new aircraft weight and balance document?. It is found on the airframe data plate. It is found in the type certificate data sheet. It is found in the pilot's aircraft information manual.