AD 81-24-01

AD Final Rules - DRS_81-24-01.html
Copy URL
Print/Save as PDF
Document Versions
 Feedback
Details
AD Number:
81-24-01
Document Type:
AD Final Rules
Docket Number:
Unknown
Subject Heading:
Airworthiness Directives; Piper Model PA-36-285, PA-36-300, and PA-36-375 Airplanes
Subject:
Rudder Control And Harness Cable Assemblies
Status:
Current
Citation:
This information is not available.
Citation Publish Date:
11/16/1981
Effective Date:
11/19/1981
Make:
Piper Aircraft Inc.
Model:
PA-36-285 | PA-36-300 | PA-36-375
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Superseded AD: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Superseded By: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: 81-24-01
CITATION:   This information is not available.

PAGE NUMBER:  

DOCKET NUMBER:   Unknown

AMENDMENT:   39-4262

AD NUMBER:   81-24-01

SUBJECT HEADING:   Airworthiness Directives; Piper Model PA-36-285, PA-36-300, and PA-36-375 Airplanes

ACTION:  

SUMMARY:  

DATES:   Effective November 19, 1981.

ADDRESSES:  

FOR FURTHER INFORMATION CONTACT:  

SUPPLEMENTARY INFORMATION:  

REGULATORY TEXT:  
81-24-01 PIPER: Amendment 39-4262. Applies to Piper airplane Models PA-36-285 and PA-36-300, S/N 36-7360001 thru 36-8160001, 36-8160003, 36-8160004 and 36-8160009 and PA-36-375, S/N 36-7802001 thru 36-8102004, certificated in all categories.

To prevent failure of the rudder control system, and seat and harness cable assemblies, accomplish the following inspection or an approved equivalent.

(a) Within the next 15 hours in service after the effective date of this AD, inspect for cracks, using a dye penetrant method,

(1) Two Rudder Control Shackles, Piper P/N 486 566 (MS 20115-5), and

(2) Two MS 20115-5 shackles on seat and harness cable assemblies, Piper P/N 98193-10 and 98193-9, respectively.

(b) Replace all shackles found cracked prior to further flight with new shackles Piper P/N 486 566 or equivalent which have been previously inspected for cracks in accordance with paragraph (a).

(c) Equivalent inspections or parts must be approved by the Chief, Engineering and Manufacturing Branch, FAA, Eastern Region.

(d) Compliance times may be increased by the Chief, Engineering and Manufacturing Branch, FAA, Eastern Region upon receipt of substantiating data submitted through an FAA Maintenance Inspector.

This amendment is effective November 19, 1981.

FOOTER: