General FAA question bank

1. 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.

2. 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.

3. The useful load of an aircraft consists of the

crew, usable fuel, passengers, and cargo.

4. 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.

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

Lever arm.

6. 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.

7. Which would have an effect on aircraft CG results when conducting a weight and balance check?

Leaving the downlocks installed.

8. 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.

9. (1) Private aircraft are required by regulations to be weighed periodically. 9. (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.

10. What FAA-approved document gives the leveling means to be used when weighing an aircraft?

Type Certificate Data Sheet.

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

Spirit level(s).

12. To obtain useful weight data for purposes of determining the CG, it is necessary that an aircraft be weighed

in a level flight attitude.

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

Distance.

14. 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.

15. The maximum weight of an aircraft is the

empty weight plus useful load.

16. Which statement is true regarding helicopter weight and balance?

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

17. What should be clearly indicated on the aircraft weighing form?

Weighing points.

18. 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.

19. Zero fuel weight is the

maximum permissible weight of a loaded aircraft (passengers, crew, and cargo) without fuel.

20. 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.

21. 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.

22. 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.

23. 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.

24. The major source of weight change for most aircraft as they age is caused by

repairs and alterations.

25. The useful load of an aircraft is the difference between

the maximum takeoff weight and basic empty weight.

26. 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.

27. 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.

28. 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.

29. An aircraft with an empty weight of 2,100 pounds and an empty weight CG +32.5 was altered as follows: 29. 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.

30. The CG range in single-rotor helicopters is

more restricted than for airplanes.

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

unusable fuel.

32. 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.

33. 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.

34. 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.

35. An aircraft with an empty weight of 1,800 pounds and an empty weight CG of +31.5 was altered as follows: 35. 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.

36. 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: 36. 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.

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

+35 from the axis.

38. In a balance computation of an aircraft from which an item located aft of the datum was removed, use

(-)weight X (+)arm (-)moment.

39. 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.

40. Datum is forward of the 40. 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?

60.31 inches.

41. 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.

42. When, or under what condition(s) are adverse loading checks conducted?

Anytime a repair or alteration causes EWCG to fall within the EWCG range.

43. 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.

44. 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.

45. An aircraft with an empty weight of 1,500 pounds and an empty weight CG of +28.4 was altered as follows: 45. 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.

46. 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.

47. If the empty weight CG of an airplane lies within the empty weight CG limits,

it is not necessary to calculate CG extremes.

48. 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.

49. 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.

50. An aircraft's LEMAC and TEMAC are defined in terms of distance

from the datum.

51. 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.

1. Airworthiness Directives are issued primarily to

correct an unsafe condition.

2. (1) A Supplemental Type Certificate may be issued to more than one applicant for the same design change, providing each applicant shows compliance with the applicable airworthiness requirement. 2. (1) A Supplemental Type Certificate may be issued to more than one applicant for the same design change, providing each applicant shows compliance with the applicable airworthiness requirement. (2) An installation of an item manufactured in accordance with the Technical Standard Order system requires no further approval for installation in a particular aircraft. Regarding the above statements,

only No. 1 is true.

3. Primary responsibility for compliance with Airworthiness Directives lies with the

aircraft owner or operator.

4. An aircraft Type Certificate Data Sheet contains

location of the datum.

5. Suitability for use of a specific propeller with a particular engine-airplane combination can be determined by reference to what informational source?

Aircraft Specifications or Aircraft Type Certificate Data Sheet.

6. When an airworthy (at the time of sale) aircraft is sold, the Airworthiness Certificate

is transferred with the aircraft.

7. The issuance of an Airworthiness Certificate is governed by

14 CFR Part 21.

8. Specifications pertaining to an aircraft model manufactured under a type certificate, of which less than 50 are shown on the FAA Aircraft Registry, can be found in the

Aircraft Listing.

9. Where are technical descriptions of certificated propellers found?

Propeller Type Certificate Data Sheets.

10. What information is generally contained in Aircraft Specifications or Type Certificate Data Sheets?

Control surface movements.

11. Placards required on an aircraft are specified in

Aircraft Specifications or Type Certificate Data Sheets.

12. Technical information about older aircraft models, of which no more than 50 remain in service, can be found in the

Aircraft Listing.

13. Which of the following are sometimes used as authorization to deviate from an aircraft's original type design? 13. Which of the following are sometimes used as authorization to deviate from an aircraft's original type design? 1. FAA Form 337. 2. Supplemental Type Certificate. 3. Airworthiness Directive. 4. Technical Standard Order

1, 2, and 3.

14. (1) The Federal Aviation Regulations require approval after compliance with the data of a Supplemental Type Certificate. 14. (1) The Federal Aviation Regulations require approval after compliance with the data of a Supplemental Type Certificate. (2) An installation of an item manufactured in accordance with the Technical Standard Order system requires no further approval for installation in a particular aircraft. Regarding the above statements,

only No. 1 is true.

15. Which regulation provides information regarding instrument range markings for an airplane certificated in the normal category?

14 CFR Part 23.

16. Which regulation provides the airworthiness standards for an airplane certificated in the normal category?

14 CFR Part 23.

17. (1) Propellers are NOT included in the Airworthiness Directive system. 17. (1) Propellers are NOT included in the Airworthiness Directive system. (2) A certificated powerplant mechanic may make a minor repair on an aluminum propeller and approve for return to service. Regarding the above statements,

only No. 2 is true.

18. An aircraft mechanic is privileged to perform major alterations on U.S. certificated aircraft; however, the work must be done in accordance with FAA-approved technical data before the aircraft can be returned to service. Which is NOT approved data?

AC 43.13-2A.

19. What is the maintenance recording responsibility of the person who complies with an Airworthiness Directive?

Make an entry in the maintenance record of that equipment.

20. (1) Manufacturer's data and FAA publications such as Airworthiness Directives, Type Certificate Data Sheets, and advisory circulars are all approved data. 20. (1) Manufacturer's data and FAA publications such as Airworthiness Directives, Type Certificate Data Sheets, and advisory circulars are all approved data. (2) FAA publications such as Technical Standard Orders, Airworthiness Directives, Type Certificate Data Sheets, and Aircraft Specifications and Supplemental Type Certificates are all approved data. Regarding the above statements,

only No. 2 is true.

21. The Air Transport Association of America (ATA) Specification No. 100 21. The Air Transport Association of America (ATA) Specification No. 100 (1) establishes a standard for the presentation of technical data in maintenance manuals. (2) divides the aircraft into numbered systems and subsystems in order to simplify locating maintenance instructions. Regarding the above statements,

both No. 1 and No. 2 are true.

22. Aviation Maintenance Alerts (formerly General Aviation Airworthiness Alerts)

provide information about aircraft problems and suggested corrective actions.

23. (Refer to Figure 62, 62A, and 62B as necessary.) Which doubler(s) require(s) heat treatment before installation?

-102

24. (Refer to Figure 62, 62A, & 62B as necessary.) How many parts will need to be fabricated by the mechanic in the construction and installation of one doubler?

3

25. (Refer to Figure 62, 62A, and 62B as necessary.) Using only the information given (when bend allowance, set back, etc. have been calculated) which doubler is it possible to construct and install?

-101

26. (Refer to Figure 62.) The -100 in the title block (Area 1) is applicable to which doubler part number(s)?

-101

27. An aircraft has a total time in service of 468 hours. The Airworthiness Directive given was initially complied with at 454 hours in service. How many additional hours in service may be accumulated before the Airworthiness Directive must again be complied with? 27. An aircraft has a total time in service of 468 hours. The Airworthiness Directive given was initially complied with at 454 hours in service. How many additional hours in service may be accumulated before the Airworthiness Directive must again be complied with? The following is the compliance portion of an Airworthiness Directive. 'Compliance required as indicated, unless already accomplished. I. Aircraft with less that 500-hours' total time in service: Inspect in accordance with instructions below at 500-hours' total time, or within the next 50-hours' time in service after the effective date of this AD, and repeat after each subsequent 200 hours in service. II. Aircraft with 500-hours' through 1,000-hours' total time in service: Inspect in accordance with instructions below within the next 50-hours' time in service after the effective date of this AD, and repeat after each subsequent 200 hours in service. III. Aircraft with more than 1,000-hours' time in service: Inspect in accordance with instructions below within the next 25-hours' time in service after the effective date of this AD, and repeat after each subsequent 200 hours in service.'

186

28. The following words are an example of what kind of statement in an AD? 'Required within the next 25 hours time-in-service after the effective date of this AD, unless already accomplished.

Compliance.

29. The action required by an AD may take what form? 29. The action required by an AD may take what form? 1. Inspection. 2. Part(s) replacement. 3. Design modification. 4. Change in operating procedure(s). 5. Overall change in the content, form and disposition of aircraft maintenance records.

1, 2, 3, and/or 4.

30. Type Certificate Data Sheets are issued for which of the following products?

Aircraft, engines, and propellers.

31. The following is a table of airspeed limits as given in an FAA-issued aircraft specification: 31. The following is a table of airspeed limits as given in an FAA-issued aircraft specification: Normal operating speed 260 knots Never-exceed speed 293 knots Maximum landing gear operation speed 174 knots Maximum flap extended speed 139 knots The high end of the white arc on the airspeed instrument would be at

139 knots.

32. When is a mechanic responsible for checking AD compliance?

When performing an inspection required under part 91, 125, or 135.

33. How long are AD compliance records required to be kept?

They shall be retained, and then transferred with the aircraft when it is sold.

34. What does the Type Certificate Data Sheet designation code '2 PCSM' mean?

Two place (number of seats), closed, sea, monoplane.

35. Which of the following includes all the regulatory definitions of 'maintenance'?

Overhaul, repair, parts replacement, inspection, and preservation.

36. What is the maximum penalty for cheating or other unauthorized conduct when taking an FAA mechanic test?

Ineligibility to receive any certificate or rating for one year, and suspension or revocation of any certificate held.

37. A complete detailed inspection and adjustment of the valve mechanism will be made at the first 25 hours after the engine has been placed in service. Subsequent inspections of the valve mechanism will be made each second 50-hour period. 37. A complete detailed inspection and adjustment of the valve mechanism will be made at the first 25 hours after the engine has been placed in service. Subsequent inspections of the valve mechanism will be made each second 50-hour period. From the above statement, at what intervals will valve mechanism inspections be performed?

100 hours.

38. Check thrust bearing nuts for tightness on new or newly overhauled engines at the first 50-hour inspection following installation. Subsequent inspections on thrust bearing nuts will be made at each third 50-hour inspection. 38. Check thrust bearing nuts for tightness on new or newly overhauled engines at the first 50-hour inspection following installation. Subsequent inspections on thrust bearing nuts will be made at each third 50-hour inspection. From the above statement, at what intervals should you check the thrust bearing nut for tightness?

150 hours.

39. Under the Federal Aviation Regulations, an aviation maintenance technician is required to perform maintenance on an aircraft so that it

is at least equal to its original or properly altered condition.

1. If a double-acting actuating cylinder in a 3,000 psi system has a piston with a surface area of three square inches on the extension side, and a rod with a cross-section area of one square inch attached to the piston on the other side, approximately how much force will the actuator be able to produce when retracting?

6,000 pounds.

2. The boiling point of a given liquid varies

directly with pressure.

3. Which of the following is NOT considered a method of heat transfer?

Diffusion.

4. An engine that weighs 350 pounds is removed from an aircraft by means of a mobile hoist. The engine is raised 3 feet above its attachment mount, and the entire assembly is then moved forward 12 feet. A constant force of 70 pounds is required to move the loaded hoist. What is the total work input required to move the hoist?

840 foot-pounds.

5. Which condition is the actual amount of water vapor in a mixture of air and water?

Absolute humidity.

6. Under which conditions will the rate of flow of a liquid through a metering orifice (or jet) be the greatest (all other factors being equal)?

Unmetered pressure, 17 PSI; metered pressure, 5 PSI; atmospheric pressure, 14.7 PSI.

7. (Refer to Figure 61.) The amount of force applied to rope A to lift the weight is

15 pounds.

8. Which will weigh the least?

35 parts of dry air and 65 parts of water vapor.

9. Which is the ratio of the water vapor actually present in the atmosphere to the amount that would be present if the air were saturated at the prevailing temperature and pressure?

Relative humidity.

10. The speed of sound in the atmosphere

changes with a change in temperature.