AD 87-03-11

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AD Number:
87-03-11
Document Type:
AD Final Rules
Docket Number:
Unknown
Subject Heading:
Airworthiness Directives; Socata Model TB 10, TB 20, and TB 21 Series Airplanes
Subject:
Stabilator Rod Ends
Status:
Current
Citation:
This information is not available.
Citation Publish Date:
Effective Date:
03/11/1987
Make:
SOCATA
Model:
TB 10 | TB 20 | TB 21
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Superseded AD: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Superseded By: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: 87-03-11
CITATION:   This information is not available.

PAGE NUMBER:  

DOCKET NUMBER:   Unknown

AMENDMENT:   39-5575

AD NUMBER:   87-03-11

SUBJECT HEADING:   Airworthiness Directives; Socata Model TB 10, TB 20, and TB 21 Series Airplanes

ACTION:  

SUMMARY:  

DATES:   Effective March 11, 1987.

ADDRESSES:  

FOR FURTHER INFORMATION CONTACT:  

SUPPLEMENTARY INFORMATION:  

REGULATORY TEXT:   87-03-11 SOCATA Groupe AEROSPATIALE: Amendment 39-5575. Applies to Models TB 10, TB 20, and TB 21 (Serial Numbers (S/N) 1 through 709) airplanes certificated in any category.

Compliance: Required as indicated in the body of the AD, unless already accomplished.

To prevent loose stabilator rod ends that may result in loss of pitch control, accomplish the following:
(a) Prior to further flight, and each 100 hours time-in-service (TIS) thereafter until repaired or replaced with a modified stabilator actuator rod assembly, inspect the stabilator actuator rod ends and rivets for relative motion as described in paragraph A of SOCATA TB Aircraft S/B No. 29 dated October 1986. If there is any detectable play in any axis, loose or working rivets, prior to further flight, accomplish the actions in paragraphs (i) or (ii) below:
(i) Repair the stabilator actuator rod assembly Part Number (P/N) TB 10.27.000.024 and replace the rivets with threaded fasteners as described in paragraph B of SOCATA TB Aircraft S/B No. 29 dated October 1986; or
(ii) Replace the existing riveted stabilator actuator rod assembly P/N TB 10.27.000.024 with actuator rod assembly P/N TB 10.27.000.026, modified with the threaded fasteners as described in paragraph B of SOCATA TB Aircraft S/B No. 29 dated October 1986.

(b) Airplanes may be flown in accordance with FAR 21.197 to a location where this AD may be accomplished.

(c) An equivalent means of compliance with this AD may be used if approved by the Manager, Brussels Aircraft Certification Office, FAA, AEU-100, Europe, Africa, and Middle East Office, c/o American Embassy, B-1000 Brussels, Belgium; Telephone 513.38.30.

All persons affected by this directive may obtain copies of the document(s) referred to herein upon request to SOCATA Groupe AEROSPATIALE, B.P. 38, 65001-Tarbes, France; Telephone 62.93.97.30; or Product Support Deputy Manager, U.S., Mr. Bernard M. Veyssiere, 12605 Woodygrove Drive, St. Louis, Missouri 63146; Telephone (314) 469-7490; or may examine the document(s) referred to herein at the FAA, Office of the Regional Counsel, Room 1558, 601 East 12th Street, Kansas City, Missouri 64106.

This amendment becomes effective on March 11, 1987, to all persons except those to whom it has already been made effective by priority letter from the FAA dated February 2, 1987, and is identified as AD 87-03-11.

FOOTER: