AD 72-08-06

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AD Number:
72-08-06
Document Type:
AD Final Rules
Docket Number:
Unknown
Subject Heading:
Airworthiness Directives; Piper Models PA 28-140, PA 28-150, PA-28-160, PA-28-180, PA-28-235, PA 32-...Show more
Subject:
Main Landing Gear Torque Links
Status:
Current
Citation:
This information is not available.
Citation Publish Date:
04/12/1972
Effective Date:
04/14/1972
Make:
Piper Aircraft Inc.
Model:
PA-28-140 | PA-28-150 | PA-28-160 | PA-28-180 | PA-28-235 | PA-32-260 | PA-32-300
Product Type:
Aircraft
Product Subtype:
Small Airplane
Affected AD:
Superseded AD:
Affected By:
Superseded By:
Service/Office:
AIR-700: Compliance & Airworthiness Division
Office of Primary Responsibility:
AIR-720: Operational Safety Branch
CFR Part Reference:
Part 39
Comments:
AIRWORTHINESS DIRECTIVES FINAL RULES: 72-08-06
CITATION:   This information is not available.

PAGE NUMBER:  

DOCKET NUMBER:   Unknown

AMENDMENT:   39-1433

AD NUMBER:   72-08-06

SUBJECT HEADING:   Airworthiness Directives; Piper Models PA 28-140, PA 28-150, PA-28-160, PA-28-180, PA-28-235, PA 32-260, and PA-32-300 Airplanes

ACTION:  

SUMMARY:  

DATES:   Effective April 14, 1972.

ADDRESSES:  

FOR FURTHER INFORMATION CONTACT:  

SUPPLEMENTARY INFORMATION:  

REGULATORY TEXT:  
72-08-06 PIPER: Amendment 39-1433. Applies to Model PA 28-140 airplanes, Serial Numbers 28-20000 and up; Model PA 28-150/-160/-180 airplanes, Serial Numbers 28-01 and up; Model PA 28-235 airplanes, Serial Numbers 28-10000 and up; Model PA 32-260 airplanes, Serial Numbers 32-01 and up; and Model PA 32-300 airplanes, Serial Numbers 32-40000 and up. Serial Numbers prefixed by model year, such as 28-7120000 are included in effectivity.

For airplanes having main landing gear torque links, P/N 65691-00 or P/N 65691-00V, compliance required within the next 50 hours of torque link time in service from the effective date of this AD, or before the accumulation of 750 hours of torque link time in service, whichever occurs later, unless already accomplished in the last 450 hours of torque link time in service. Repetitive inspections are required at intervals not to exceed 500 hours of torque link time in service from last inspection.

To detect cracks adjacent to the 2 1/2" diameter machined boss in any of the four main landing gear torque links (Piper Part No. 65691-00 or 65691-00V) accomplish the following:

(a) Remove paint at least one inch away from the large boss by any suitable means which does not leave a wax residue.

(b) Clean this area for inspection and allow to dry if necessary.

(c) Inspect for cracks by any of the following methods:

(1) Visually with the aid of at least a 10 power magnifying glass.

(2) Fluorescent or dye penetrant inspection.

(3) FAA approved equivalent inspection.

(d) If cracks are present, replace the torque links with serviceable torque links of the same part number before further flight, except that the airplane may be flown in accordance with FAR 21.197 to a base where installation can be performed.

Piper Service Letter No. 600 pertains to this same subject; however, compliance times must be in accordance with the provisions of this AD.

Operators who have not kept records of hours time in service on individual torque links shall substitute airplane hours time in service in lieu thereof.

Previous AD's 67-20-04 and 70-18-05, concerning main landing gear torque links are still applicable. Piper Kit No. 757-123 as mentioned in these AD's contains appropriate hardware for torque link installation and may be reused.

This amendment becomes effective April 14, 1972.

FOOTER: