AP GN Maintenance Publications

Airworthiness Directives are issued primarily to

(1) A Supplemental Type Certificate (STC) 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 (TSO) system requires no further approval for installation in a particular aircraft.

Regarding the above statements,

What does the acronym TSO mean regarding a type certificated aircraft part, material, component or process?

Primary responsibility for compliance with Airworthiness Directives lies with the

An aircraft Type Certificate Data Sheet contains

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

When an aircraft is sold domestically, the Airworthiness Certificate

The insurance of an Airworthiness Certificate is governed by

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

Where are technical descriptions of certificated propellers found?

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

Placards required on an aircraft are specified in

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

Which of the following are sometimes used as authorization to deviate from an aircraft’s original type design?

(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 Center system requires no further approval for installation in a particular aircraft.

Regarding the above statements,

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

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

What regulations are covered by 14 CFR Part 1?

(1) Propellers are NOT included in the Airworthiness Directive system.

(2) A certificated powerplant mechanic may take a minor repair on an aluminum propeller and approve for return to service.

Regarding the above statements,

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?

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

(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,

A Technical Standard Order (TSO) is insured by whom?

The Air Transport Association of America (ATAA) 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,

Aviation Maintenance Alerts (formerly General Aviation Airworthiness Alerts)

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

AREA 2

GENERAL NOTES – 100

1. ALL BENDS +/- .5 deg.
2. All holes +/- .003.
3. Apply Alodine 1,000.
4. Prime with MIL-P-23377 or equivalent.
5. Trim S-1 C just aft of the clip at STA. 355.750 and forward of the front face of the STA. 370.25 frame and remove from the airplane.
6. Position the -101 doubler as shown. Install wet with NAS1097AD-4-4 and -4-5 rivets and a fraying surface seal of PR 1,422. Pick up the rivet row that was in S-1 C and the aft rivets in sta. 370.25. Tie doubler into front frame with clips as shown using MS20470AD-4-4 nutplates with NAS1097-3-4 rivets through the skin and doubler to retain the antenna.
7. Install 4 NAS1473-3A nutplates with NAS1097-3-4 rivets through the skin and doubler to retain the antenna.
8. Strip paint and primer from under the antenna footprint.
9. Treat skin with Alodine 1,000.
10. Install antenna and apply weather seal fillet around antenna base

AREA 3

GENERAL NOTES – 200                    NOTE:  P.S. = Process Specification
                                                                                    IAW = In Accordance with

1. ALL BENDS IAW P.S. 1,000.
2. All holes IAW P.S. 1,015.
3. Heat treat – 102 to – T6 IAW P.S. 5,602.
4. Alodine IAW P.S. 10,000.
5. Prime IAW P.S. 10,125.
6. Trim S-1 C just aft of the clip at STA. 355.750 and forward of the front face of the STA. 370.25 frame and remove from airplane.
7. Position the -102 doubler as shown. Install wet with NAS1097AD-4-4 and -4-5 rivets, and a faying surface seal IAW P.S. 41,255. Pick up the rivet row that was S-1 C and the aft rivets in STA> 370.25. Add two edge rows as shown. Tie doubler into front frame with clips as shown along MS20470AD-4-4 rivets through the clips and the frame.
8. Install 4 NAS1473-3A nutplates with NAS 1097-3-4 rivets through the skin and doubler to retain the antenna.
9. Strip paint and primer from under the antenna footprint.
10. Treat skin IAW P.S. 10,000.
11. Install antenna and apply weather seal fillet around antenna base.

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

AREA 2

GENERAL NOTES – 100

1. ALL BENDS +/- .5 deg.
2. All holes +/- .003.
3. Apply Alodine 1,000.
4. Prime with MIL-P-23377 or equivalent.
5. Trim S-1 C just aft of the clip at STA. 355.750 and forward of the front face of the STA. 370.25 frame and remove from the airplane.
6. Position the -101 doubler as shown. Install wet with NAS1097AD-4-4 and -4-5 rivets and a fraying surface seal of PR 1,422. Pick up the rivet row that was in S-1 C and the aft rivets in sta. 370.25. Tie doubler into front frame with clips as shown using MS20470AD-4-4 nutplates with NAS1097-3-4 rivets through the skin and doubler to retain the antenna.
7. Install 4 NAS1473-3A nutplates with NAS1097-3-4 rivets through the skin and doubler to retain the antenna.
8. Strip paint and primer from under the antenna footprint.
9. Treat skin with Alodine 1,000.
10. Install antenna and apply weather seal fillet around antenna base

AREA 3

GENERAL NOTES – 200                    NOTE:  P.S. = Process Specification
                                                                                    IAW = In Accordance with

1. ALL BENDS IAW P.S. 1,000.
2. All holes IAW P.S. 1,015.
3. Heat treat – 102 to – T6 IAW P.S. 5,602.
4. Alodine IAW P.S. 10,000.
5. Prime IAW P.S. 10,125.
6. Trim S-1 C just aft of the clip at STA. 355.750 and forward of the front face of the STA. 370.25 frame and remove from airplane.
7. Position the -102 doubler as shown. Install wet with NAS1097AD-4-4 and -4-5 rivets, and a faying surface seal IAW P.S. 41,255. Pick up the rivet row that was S-1 C and the aft rivets in STA> 370.25. Add two edge rows as shown. Tie doubler into front frame with clips as shown along MS20470AD-4-4 rivets through the clips and the frame.
8. Install 4 NAS1473-3A nutplates with NAS 1097-3-4 rivets through the skin and doubler to retain the antenna.
9. Strip paint and primer from under the antenna footprint.
10. Treat skin IAW P.S. 10,000.
11. Install antenna and apply weather seal fillet around antenna base.

Refer to Figures 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?

AREA 2

GENERAL NOTES – 100

1. ALL BENDS +/- .5 deg.
2. All holes +/- .003.
3. Apply Alodine 1,000.
4. Prime with MIL-P-23377 or equivalent.
5. Trim S-1 C just aft of the clip at STA. 355.750 and forward of the front face of the STA. 370.25 frame and remove from the airplane.
6. Position the -101 doubler as shown. Install wet with NAS1097AD-4-4 and -4-5 rivets and a fraying surface seal of PR 1,422. Pick up the rivet row that was in S-1 C and the aft rivets in sta. 370.25. Tie doubler into front frame with clips as shown using MS20470AD-4-4 nutplates with NAS1097-3-4 rivets through the skin and doubler to retain the antenna.
7. Install 4 NAS1473-3A nutplates with NAS1097-3-4 rivets through the skin and doubler to retain the antenna.
8. Strip paint and primer from under the antenna footprint.
9. Treat skin with Alodine 1,000.
10. Install antenna and apply weather seal fillet around antenna base

AREA 3

GENERAL NOTES – 200                    NOTE:  P.S. = Process Specification
                                                                                    IAW = In Accordance with

1. ALL BENDS IAW P.S. 1,000.
2. All holes IAW P.S. 1,015.
3. Heat treat – 102 to – T6 IAW P.S. 5,602.
4. Alodine IAW P.S. 10,000.
5. Prime IAW P.S. 10,125.
6. Trim S-1 C just aft of the clip at STA. 355.750 and forward of the front face of the STA. 370.25 frame and remove from airplane.
7. Position the -102 doubler as shown. Install wet with NAS1097AD-4-4 and -4-5 rivets, and a faying surface seal IAW P.S. 41,255. Pick up the rivet row that was S-1 C and the aft rivets in STA> 370.25. Add two edge rows as shown. Tie doubler into front frame with clips as shown along MS20470AD-4-4 rivets through the clips and the frame.
8. Install 4 NAS1473-3A nutplates with NAS 1097-3-4 rivets through the skin and doubler to retain the antenna.
9. Strip paint and primer from under the antenna footprint.
10. Treat skin IAW P.S. 10,000.
11. Install antenna and apply weather seal fillet around antenna base

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

Refer to Figure 63. 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 gain be complied with?

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.”

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.

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

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

When is a mechanic responsible for checking AD compliance?

How long are AD compliance records required to be kept?

What does the Type Certificate Data Sheet designation code “2 PCSM” mean? (K01)

Which of the following includes all the regulatory definitions of “maintenance?”

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

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?

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 be check the thrust bearing nut for tightness?