AD 93-13-08

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AD Number:
93-13-08
Document Type:
AD Final Rules
Docket Number:
92-CE-51-AD
Subject Heading:
Airworthiness Directives; AEROSTAR AIRCRAFT CORPORATION Models PA-60-600, PA-60-601, PA-60-601P, PA-...Show more
Subject:
Torque Links
Status:
Current
Citation:
This information is not available.
Citation Publish Date:
Effective Date:
08/20/1993
Make:
Aerostar Aircraft Corporation
Model:
PA-60-600 (Aerostar 600) | PA-60-601 (Aerostar 601) | PA-60-601P (Aerostar 601P) | PA-60-602P (Aeros...Show more
Product Type:
Aircraft
Product Subtype:
Small Airplane
Affected AD:
Superseded AD:
Affected By:
Superseded By:
Service/Office:
Office of Primary Responsibility:
CFR Part Reference:
Part 39
Comments:
AIRWORTHINESS DIRECTIVES FINAL RULES: 93-13-08
CITATION:   This information is not available.

PAGE NUMBER:  

DOCKET NUMBER:   92-CE-51-AD

AMENDMENT:   39-8621

AD NUMBER:   93-13-08

SUBJECT HEADING:   Airworthiness Directives; AEROSTAR AIRCRAFT CORPORATION Models PA-60-600, PA-60-601, PA-60-601P, PA-60-602P and PA-60-700P

ACTION:  

SUMMARY:  

DATES:   Effective August 20, 1993.

ADDRESSES:  

FOR FURTHER INFORMATION CONTACT:  

SUPPLEMENTARY INFORMATION:  

REGULATORY TEXT:  
93-13-08 AEROSTAR AIRCRAFT CORPORATION: Amendment 39-8621. Docket No. 92-CE-51-AD. Supersedes AD 92-11-08, Amendment 39-8258 which superseded AD 80-02-09, Amendments 39-3665 and 39-3991.

Applicability: The following model and serial number airplanes, certificated in any category:

Models	Serial Numbers
PA-60-600 Aerostar 600	60-0001-003 through 60-0933-8161262
PA-60-601 Aerostar 601	61-0001-004 through 61-0880-8162157
PA-60-601P Aerostar 601P	61P-0157-001 through 61P-0860-8163455
PA-60-602P Aerostar 602P	62P-0750-8165001 through 60-8365021
PA-60-700P Aerostar 700P	60-8223001 through 60-8423025

NOTE 1: The manufacturing and ownership rights of the affected model airplanes were previously owned by the Piper Aircraft Corporation, but these rights were recently transferred to the Aerostar Aircraft Corporation.

Compliance: Required as indicated, unless already accomplished.

To prevent loss of directional control of the airplane during ground operation caused by torque link failure, accomplish the following:

(a) Within the next 100 hours time-in-service (TIS) after the effective date of this AD, accomplish either (1) or (2) below:

(1) Replace the existing main landing gear torque links with improved design torque links, part number (P/N) 400126-501 and 400126-503 (left main landing gear) and P/N 400126-502 and 400126-504 (right main landing gear), in accordance with the INSTRUCTIONS section of Aerostar Service Bulletin (SB) No. 746C, dated September 15, 1992.

NOTE 2: Aerostar SB No. 746C, dated September 15, 1992, references the availability of Main Landing Gear Torque Link Replacement Kit No. 765-155 revision G. This kit contains the improved torque links and all hardware necessary to install these links. This kit may be obtained from the manufacturer at the address specified in paragraph (d) of this AD.

(2) Dye penetrant inspect (using FAA-approved methods) the main landing gear torque links for cracks.

(i) If cracks are found, prior to further flight, replace the cracked torque links with improved designed torque links part number (P/N) 400126-501 and 400126-503 (left main landing gear) and P/N 400126-502 and 400126-504 (right main landing gear), in accordance with the INSTRUCTIONS section of Aerostar SB No. 746C, dated September 15, 1992.

(ii) If no cracks are found, reinspect at intervals not to exceed 100 hours TIS.

(iii) The repetitive inspection requirement is no longer required when both the left and right main landing gear torque links are replaced with improved design torque links, part number (P/N) 400126-501 and 400126-503 (left main landing gear) and P/N 400126-502 and 400126-504 (right main landing gear), in accordance with the INSTRUCTIONS section of Aerostar SB No. 746C, dated September 15, 1992. This installation may be accomplished at any time regardless of whether cracks are found during the inspection.

NOTE 3: Operators should ensure that proper strut inflation is maintained as improper strut inflation could put extreme impact upon the torque links. In addition, improper use of the hydraulic nose gear steering mechanism at high speeds could also lead to overstressed torque links.

(b) Special flight permits may be issued in accordance with FAR 21.197 and 21.199 to operate the airplane to a location where the requirements of this AD can be accomplished.

(c) An alternative method of compliance or adjustment of the compliance time that provides an equivalent level of safety may be approved by the Manager, Seattle Aircraft Certification Office, 1601 Lind Avenue, S.W., Renton, Washington 98055-4056. The request shall be forwarded through an appropriate FAA Maintenance Inspector, who may add comments and then send it to the Manager, Seattle Aircraft Certification Office.

NOTE 4: Information concerning the existence of approved alternative methods of compliance with this AD, if any, may be obtained from the Seattle Aircraft Certification Office.

(d) The replacement required by this AD shall be done in accordance with Aerostar Service Bulletin No. 746C, dated September 15, 1992. This incorporation by reference was approved by the Director of the Federal Register in accordance with 5 U.S.C. 552(a) and 1 CFR Part 51. Copies may be obtained from the Aerostar Aircraft Corporation, Customer Service Department, South 3608 Davison Boulevard, Spokane, Washington 99204. Copies may be inspected at the FAA, Central Region, Office of the Assistant Chief Counsel, Room 1558, 601 E. 12th Street, Kansas City, Missouri, or at the Office of the Federal Register, 800 North Capitol Street, NW., suite 700, Washington, DC.

(e) This amendment (39-8621) supersedes AD 92-11-08, Amendment 39-8258 which superseded AD 80-02-09, Amendments 39-3665 and 39-3991.

(f) This amendment becomes effective on August 20, 1993.

FOOTER: