Weight and Balance Flashcards
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
What tasks are completed prior to weighing an aircraft to determine is empty 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
Which of the following can you provide the empty weight of an aircraft if the aircraft weight and balance records become lost, destroyed or otherwise inaccurate?
Reweighing the aircraft
When calculating the new weight and balance for an aircraft, what is used to determine the operating CG range?
The Type Certificate Data Sheets
In the theory of weight, what is the name of the distance from the fulcrum to an object?
Lever arm
In the process of weighing an airplane toward obtaining the CG, the arms from the weighing points always extend
Parallel to the centreline of the airplane
Which would have an effect on the aircraft CG results when conducting a weight and balance check?
Leaving the downlocks installed
Which of the following may cause erroneous scale readings?
Parking brakes set
Which of the following is an example of a second class (class B) lever?
Wheelbarrow
What FAA-approved documents give the leveling means to be used when weighing an aircraft?
Type Certificate Data Sheet
Which device(s) is/are used to obtain the greatest accuracy of aircraft leveling?
Spirit level
To obtain useful weight data for purposes of determining the CG, it is necessary that an aircraft be weighed
in a level flight altitude
What type of measurement is used to designate the arm in weight and balance computation?
Distance
What determines whether value of the moment is preceded by a plus (+) or a minus (-) sign in an aircraft weight and balance?
The location weight to the datum and if it is being removed or added
The maximum weight of an aircraft is the
empty weight plus useful load
Which statement is true regarding helicopter weight and balance?
Weight and balance procedure for airplanes also apply to helicopters
What should be clearly indicated on the aircraft weighing form?
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 positive numbers
Maximum zero fuel weight is the
Maximum permissible weight of a loaded aircraft (passenger, crew and cargo) without fuel
If it is necessary to weigh an aircraft with full fuel tank, all fuel weight must be subtracted from the scale reading
excet unusable fuel
The empty weight of an airplane is determined by
subtracting the tare weight from the scale reading and adding the weight of weighing point
When dealing with weight and balance of an aircraft, maximum weight is interpreted to mean the maximum
authorized weight of the aircraft and its contents
Most modern aircraft are designed so that if all seats are occupied full baggage is carried, and all fuel tanks are full, what will be the weight condition of the aircraft?
It will be in excess of max takeoff weight
The major source of weight change for most aircraft as they age is caused by
repairs and alterations
The useful load of an aircraft is the difference between
The maximum takeoff weight and basic empty weight
When determining the empty weight of an aircraft, certificated under current airworthiness standards (14 CFR/FAR Part 23), the oil contained in the supply tank is considered
part of the empty weight
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
The maximum weight as used in weight and balance control of a given aircraft can normally be found
in the Aircraft Specification or Type Certificate Data Sheet
The CG range in single rotor helicopters is
more restricted than for airplanes
The amount of fuel used for computing empty weight and corresponding CG is
unusable fuel
An aircraft as loaded weighs 4,954 pounds at a CG of +30.5 inches. The CG range is +32 inches to +42.1 inches. Find the max weight of all ballast necessary to bring the CG within the CG range. The ballast arm is +162 inches
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?
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 retrospectively. How far forward of the CG should a third box, weighing 20 pounds be placed so that the CG will not be changed?
2.5 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?
+31.61
An aircraft had an empty weight of 2,886 with a moment of 101,673.78 before several alterations were made. The alterations included:
1. Removing two passengers 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
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 weight CG
If a 40-pound generator applies +1400-inch pounds to a reference axis, the generator is located
+35 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
All other things being equal if an item of useful load located aft of an aircraft’s CG is removed, the aircrafts CG change will be
forward in proportion to the weight of the item and its location in the aircraft
When making a rearward weight and balance check to determine that the CG will not exceed the rearward limit during extreme conditions, the item of useful load which should be computed at their minimum weights are located forward of the
Rearward CG limit
When, or under what conditions are adverse loading checks conducted?
Anytime a repair or alteration causes EWCG to fall within the CG range
When accomplishing loading computations for a small aircraft, necessary information obtained from the weight and balance records would include
current empty weight and empty weight CG
When an empty weight 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 is forward of the nose of the aircraft. What is the empty weight CG of the aircraft?
151.1
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?
+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 -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?
12.73 inches
If the empty weight CG of an airplane lies within the empty weight CG limits,
it is not necessary to calculate CG extremes
When computing the maximum forward loaded of CG of an aircraft, minimum weights, arms, and moments should be used for items of useful loads that are located aft of the
forward CG limit
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 wheel is 87.5 inches, nosewheel location is +9.875 from the datum, with 1 gallon of hydraulic fluid at -21.0 inches included in the weight scale.
+96.11 inches
An aircraft LEMAC and TEMAC are defined in terms of distance
from the datum
If an aircraft CF is found to be at 24 percent of MAC, that 24 percent is an expression of the
distance of the LEMAC
