all Flashcards
1
Q
Center of Gravity Calculated as:
A
Total Moment divided by Total Weight
- Total Weight Divided by Total Moment
- Total Moment Divided by Total Height
2
Q
Empty Weight of the aircraft includes:
A
All the Above
- Residual Fuel and Oil
- Weight of the airframe, powerplant and optional or special equipment
- Hydraulic fluid
3
Q
Electronically operated scale called:
A
Load Cell
- Spring Type
- Beam Scale
4
Q
Find the moment, if a 5 lb radio located 80” from the datum?
A
400 in-lb
- 400 lb
- 200 in-lb
5
Q
Find the New Center of Gravity?
Airplane Empty Weight - 2,350 lb, Airplane Empty Weight CG - +24.7”, Airplane Datum - Leading edge of the wing, Radio Installed - 5.8 lb at an arm of (-28)”, Global Positioning System Installed - 7.3 lb at an arm of (-26)”, Emergency Locater Transmitter Installed - 2.8 lb at an arm of (+105)”, Strobe Light Removed - 1.4 lb at an arm of (+75)”, Automatic Direction Finder (ADF) removed - 3 lb at an arm of (-28)”, Seat removed - 34 lb at an arm of (+60)”.
A
24.03”
6
Q
How to determine Useful load?
A
(Subtract the empty weight from the maximum allowable gross weight)
- Add the empty weight from the maximum allowable gross weight
- Multiply the empty weight from the maximum allowable gross weight
7
Q
How weight and balance extreme condition check done?
A
By pencil and paper only
- None of the above.
- Weighing aircraft on scale
8
Q
Maximum Zero Fuel Weight means:
A
The heaviest weight an aircraft can be loaded to without having any usable fuel in the fuel tank.
- The heaviest weight of the aircraft without oil and fuel
- The heaviest weight an aircraft can be loaded with full fuel in the fuel tank
9
Q
Payload Includes:
A
Useful weight minus Fuel
- Without the weight of Passengers.
- Useful weight minus Fuel
10
Q
The heaviest weight an aircraft can have when it land.
A
Maximum Landing Weight
-Maximum Zero Fuel Weight
-Maximum Ramp Weight
11
Q
The heaviest weight an aircraft can have when it starts the takeoff roll.
A
Maximum Takeoff Weight
-Maximum Zero Fuel Weight
-Maximum Landing Weight
12
Q
The heaviest weight to which an aircraft can be loaded while it is sitting on the ground know as:
A
Maximum Ramp Weight
- Maximum Zero Fuel Weight
- Maximum Landing Weight
13
Q
The horizontal distance that a part of the aircraft or a piece of equipment is located form the datum is called:
A
Arm
- Moment
- None of the above
14
Q
The total arm is the airplane center of gravity and is found by dividing the total moment by the total weight.
A
True
15
Q
Useful load consists of:
A
All the above
- Passengers, Baggage and flight crew
- Fuel, any other fluids that are not part of empty weight
16
Q
What are the information found in a Type Certificate Data Sheet:
A
All of the above
- Center of Gravity Range & Maximum Weight
- Number of Seats and location, Fuel Capacity
- Datum Location and Baggage Capacity
17
Q
What are the proper position of flight control during weighing an aircraft?
A
Refer to the manufacturers instruction
-Flaps down and Elevator up
-Flaps UP and Elevator down
18
Q
What are the weight and balance equipment:
A
All of the above
-Plump Bob
-Scales
-Spirit level
19
Q
What is Center of Gravity (CG)?
A
A point about which the nose heavy and tail heavy moments are exactly equal in magnitude.
- A point about which the nose heavy and tail heavy moments are not equal in magnitude.
- Tendency to rotate in nose up attitude.
20
Q
What is CG Envelop:
A
Graphically Plotted CG limits form
-None of the above
-Pie chart of CG limit
21
Q
What is an imaginary vertical plane from which all horizontal measurements are taken for balance purpose, with the aircraft in level flight attitude?
A
Datum
- Moment
- Arm
22
Q
What is the algebraic sign if an item is located aft of the datum?
A
Positive (+)
- Negative (-)
- Any sign can be used as you decide
23
Q
What is the algebraic sign if an item is located forward of the datum?
A
Negative (-)
- Positive (+)
- Any sign can be used as you decide
24
Q
What is the primary reason for concern about an aircraft’s weight and balance?
A
Safety
-Efficiency
-To Save Fuel
25
# 1.
What is the unit of Moment?
Inch-Pounds (in-lb)
## Footnote
1. Pounds (lb)
2. Inch (in)
26
What should be done if the weight and balance report for an aircraft is lost?
Aircraft must be weighed, and a new report must be created
## Footnote
1. Wight and balance report only for manufactures record
2. No need to create a new report
27
When aircraft are places on scale and weighed, it is sometimes necessary to use support equipment to aid in the weighing process. This extra weight is known as:
Tare Weight
## Footnote
-Zero Fuel Weight
-Payload
28
Where I can find the maximum authorized weight of the aircraft.
Type certificate data sheet
## Footnote
-Service Bulletin
-Airworthiness Directives
29
Where you can find Datum of an aircraft?
Aircraft Type Certificate Data Sheet
## Footnote
1. Service Bulletin
2. Flight Operation Manual
30
Who is responsible for weight and balance of the loaded airplane, and makes the final decision on whether airplane is safe to fly or not?
Pilot in Command
31
Choose the correct statement:
Most helicopters have much more restricted Center of Gravity range than do airplane
## Footnote
* CG is not necessary for helicopters
* All helicopters have wide Center of Gravity range than do airplane.
32
Loading Graph and CG envelope system, is an excellent and rapid method for determining the CG location for various loading arrangements.
True
33
On large airplanes, the CG is identified as being at a location that is a specific percent of the _____________________________.
Mean Aerodynamic chord (%MAC)
## Footnote
* Aspect Ratio
* Mean Aerodynamic Characteristics
34
What is the use of Ballast in aircraft?
To attain the desired CG balance when CG is not within the limits
## Footnote
* None of the above
* To reduce the weight of the aircraft
35
The installation of permanent ballast results in an increase in the aircraft empty weight, and it reduces the useful load.
True
36
Identify the below true statement:
Weight-shift control aircraft, commonly known by the name "trikes" have few options for loading because they have few places to put useful load items.
## Footnote
* Weigh shift control aircraft has large places to put useful load items.
*
* Weight-shift control aircraft commonly know by the name "trikes" have wide options for loading because they have large places to put useful load items.
37
Find the the Center of Gravity, if Weight is 1250 lb and Moment is 80,750 in-lb
64.6"
## Footnote
* 60"
* 55.7"
38
Identify the formula to calculate how much ballast is needed to bring the center of gravity within the limits?
Loaded weight of aircraft x (Distance CG is out of limits) / Arm from ballast location to affected limit.
## Footnote
* Loaded weight of aircraft / Arm from ballast location to affected limit
* Loaded Weight of aircraft x Distance CG is out of limits
39
Find the Center of Gravity and the Empty Weight?
Empty Weight - 1502.5 lb, Center of Gravity - 55.2"
## Footnote
* Empty Weight - 2000 lb, Center of Gravity - 55.2"
* Empty Weight - 1502.5 lb, Center of Gravity - 65"
40
The width of the wing on an airplane is known as:
Chord
## Footnote
* Swept back Wing
* Tapered Wing
41
If an aircraft CG is found to be at 24 percent of MAC, that 24 percent is an expression of the
distance from the LEMAC.
## Footnote
* distance from the TEMAC.
* average distance from the LEMAC to the wing center of lift.
42
Maximum zero fuel weight is the
maximum permissible weight of a loaded aircraft (passengers, crew, and cargo) without fuel.
## Footnote
* basic operating weight without crew, fuel, and cargo.
* dry weight plus the weight of full crew, passengers, and cargo.
43
If the empty weight CG of an airplane lies within the empty weight CG limits,
it is not necessary to calculate CG extremes.
## Footnote
* it is necessary to calculate CG extremes.
* minimum fuel should be used in both forward and rearward CG checks.
44
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.
## Footnote
* It will be at maximum taxi or ramp weight.
* It will be at maximum basic operating weight (BOW).
45
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
60.31 inches.
## Footnote
* 62.92 inches.
* 58.54 inches.
46
In the theory of weight and balance, what is the name of the distance from the fulcrum to an object?
Lever arm.
## Footnote
* Balance arm.
* Fulcrum arm.
47
In a balance computation of an aircraft from which an item located aft of the datum was removed, use
(-)weight X (+)arm (-)moment.
## Footnote
* (-)weight X (-)arm (+)moment.
* (+)weight X (-)arm (-)moment.
48
What is meant by the term "residual fuel"?
The fuel remaining in the tanks, lines, and engine after draining.
## Footnote
* The fuel remaining in the tank, lines, and engine before draining.
* A known amount of fuel left in the tanks, lines, and engine.
49
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.
## Footnote
* +31.35.
* +23.51.
50
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.
## Footnote
* by adding the weight of full fuel, pilot, passengers, and maximum allowable baggage to the empty weight.
* by adding the empty weight and payload.
51
If it is necessary to weigh an aircraft with full fuel tanks, all fuel weight must be subtracted from the scale reading(s)
except unusable fuel.
## Footnote
* including unusable fuel.
* except minimum fuel.
52
When an aircraft is positioned for weighing on scales located under each landing gear wheel, which of the following may cause erroneous scale readings?
Parking brakes set.
## Footnote
* Gear downlocks installed.
* Parking brakes not set.
53
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.
## Footnote
* 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.
54
If a 40-pound generator applies +1400 inch-pounds to a reference axis, the generator is located
+35 from the axis.
## Footnote
* -35 from the axis.
* +25 from the axis.
55
The major source of weight change for most aircraft as they age is caused by
repairs and alterations.
## Footnote
* accumulation of grime and debris in hard-to-reach areas of the structure, and moisture absorption in cabin insulation.
* installation of hardware and safety wire, and added layers of primer and paint on the structure.
55
The useful load of an aircraft consists of the
crew, usable fuel, passengers, and cargo.
## Footnote
* crew, usable fuel, oil, and fixed equipment.
* crew, passengers, usable fuel, oil, cargo, and fixed equipment.
56
The useful load of an aircraft is the difference between
the maximum takeoff weight and basic empty weight.
## Footnote
* maximum ramp or takeoff weight as applicable, and zero fuel weight.
* 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.
57
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 fill hydraulic reservoir.
## Footnote
* 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.
58
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.
## Footnote
* a part of the useful load.
* the same as the fluid contained in the water injection reservoir.
59
The CG range in single-rotor helicopters is
more restricted than for airplanes.
## Footnote
* approximately the same as the CG range for airplanes.
* much greater than for airplanes.
60
The empty weight of an airplane is determined by
subtracting the tare weight from the scale reading and adding the weight of each weighing point.
## Footnote
* adding the net weight of each weighing point and multiplying the measured distance to the datum.
* multiplying the measured distance from each weighing point to the datum times the sum of scale reading less the tare weight.
60
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
forward in proportion to the weight of the item and its location in the aircraft.
## Footnote
* orward in proportion to the weight of the item, regardless of its location in the aircraft.
* ft in proportion to the weight of the item and its location in the aircraft.
61
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.
## Footnote
* 150.700.
* 151.700.
62
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
forward CG limit.
## Footnote
* rearward CG limit.
* datum.
63
What FAA-approved document gives the leveling means to be used when weighing an aircraft?
Type Certificate Data Sheet.
## Footnote
* AC 43.13-1B.
* Manufacturer's maintenance manual.
64
An aircraft's LEMAC and TEMAC are defined in terms of distance
from the datum.
## Footnote
* from each other.
* ahead of and behind the wing center of lift, respectively.
64
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.
## Footnote
* +32.69.
* +30.61.
65
Which would have an effect on aircraft CG results when conducting a weight and balance check?
Leaving the downlocks installed.
## Footnote
* Leaving the parking brake off.
* Leaving the parking brake on.
66
What type of measurement is used to designate the arm in weight and balance computation?
Distance.
## Footnote
* Weight
* Weight x distance.
67
What determines whether the value of a moment is preceded by a plus (+) or a minus (-) sign in aircraft weight and balance?
The result of a weight being added or removed and its location relative to the datum.
## Footnote
* The location of the weight in reference to the datum.
* The location of the datum in reference to the aircraft CG.
68
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.
## Footnote
* all measurement arms will be in negative numbers.
* measurement arms can be either positive or negative numbers depending on the manufacturer's preference.
69
Where do you look to determine the operating CG range when calculating a new aircraft weight and balance document?
It is found in the type certificate data sheet.
## Footnote
* It is found on the airframe data plate.
* It is found in the pilot's aircraft information manual.
70
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
rearward CG limit.
## Footnote
* datum.
* forward CG limit.
71
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.
57.16 pounds.
## Footnote
* 30.58 pounds.
* 61.98 pounds.
72
Which statement is true regarding helicopter weight and balance?
Weight and balance procedures for airplanes generally also apply to helicopters.
## Footnote
* The moment of tail-mounted components is subject to constant change.
* Regardless of internal or external loading, lateral axis cg control is ordinarily not a factor in maintaining helicopter weight and balance.
72
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.
## Footnote
* 155.2.
* 146.5.
73
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.
## Footnote
* straight forward from each of the landing gear.
* directly from each weighing point to the others.
74
To obtain useful weight data for purposes of determining the CG, it is necessary that an aircraft be weighed
in a level flight attitude.
## Footnote
* with all items of useful load installed.
* with no more than minimum fuel (1/12-gallon per METO horsepower) in all fuel tanks.
75
When, or under what condition(s) are adverse loading checks conducted?
Anytime a repair or alteration causes EWCG to fall outside the CG range.
## Footnote
* At specified flight hour or calendar time intervals.
* At or below the maximum gross weight of the aircraft.
76
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.
## Footnote
* weight and location of permanent ballast.
* unusable fuel weight and distance from datum.
76
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.
## Footnote
* Coriolis effect being translated to the fuselage.
* reduction or loss of effective collective pitch control.
76
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.
## Footnote
* The applicable Aircraft Specification or Type Certificate Data Sheet.
* The applicable flight manual or pilot's operating handbook.
77
Use of which of the following generally yields the highest degree of aircraft leveling accuracy?
Spirit level(s).
## Footnote
* Plumb bob and chalk line.
* Electronic load cell(s).
78
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.
## Footnote
* 2.03 inches forward of the original empty weight CG.
* 2.03 inches aft of the original empty weight CG.
79
What should be clearly indicated on the aircraft weighing form?
Weighing points.
## Footnote
* Weight of unusable fuel.
* Minimum allowable gross weight.
80
The maximum weight of an aircraft is the
empty weight plus useful load.
## Footnote
* empty weight plus crew, passengers, and fixed equipment.
* empty weight plus crew, maximum fuel, cargo, and baggage.
81
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?
2.5 feet.
## Footnote
* 3 feet.
* 8 feet.
82
The amount of fuel used for computing empty weight and corresponding CG is
unusable fuel.
## Footnote
* empty fuel tanks.
* the amount of fuel necessary for 1/2 hour of operation.
83
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?
+33.68.
## Footnote
* +34.01.
* +34.65.
84
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?
12.73 inches.
## Footnote
* 14.25 inches.
* 13.96 inches.
85
When dealing with weight and balance of an aircraft, the term 'maximum weight' is interpreted to mean the maximum
authorized weight of the aircraft and its contents.
## Footnote
* weight of the useful load.
* weight of the empty aircraft.
86
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.
+96.11 inches.
## Footnote
* +95.61 inches.
* +97.375 inches.
91
(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 is true.
## Footnote
* only No. 1 is true.
* only No. 2 is true.
