AD 87-12-09 R1

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AD Number:
87-12-09 R1
Document Type:
AD Final Rules
Docket Number:
Unknown
Subject Heading:
Airworthiness Directives; Socata Model TB 20 and TB 21 Series Airplanes
Subject:
Aileron Weight Attach Rivets
Status:
Current
Citation:
This information is not available.
Citation Publish Date:
Effective Date:
06/25/1989
Make:
SOCATA
Model:
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Superseded AD: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Superseded By: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: 87-12-09 R1
CITATION:   This information is not available.

PAGE NUMBER:  

DOCKET NUMBER:   Unknown

AMENDMENT:   39-6224

AD NUMBER:   87-12-09 R1

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

ACTION:  

SUMMARY:  

DATES:   Effective June 25, 1989.

ADDRESSES:  

FOR FURTHER INFORMATION CONTACT:  

SUPPLEMENTARY INFORMATION:  

REGULATORY TEXT:   87-12-09 R1 SOCATA GROUPE AEROSPATIALE: Amendment 39-5650 as revised by Amendment 39-6224.
Applicability: Models TB 20 and TB 21 (Serial Numbers 275 through 700) airplanes certificated in any category.

Compliance: Required within the next 50 hours time-in-service (TIS) after the effective date of this AD, and each 100 hours TIS thereafter, unless already accomplished in accordance with the original issuance of AD 87-12-09.

To prevent structural failure of the aileron, possible flutter, and loss of control, accomplish the following:
(a) Visually inspect the five aileron balance weight attachment rivets for any detectable looseness, and the aileron skin for cracks using the procedures described in paragraph A, SOCATA TB Service Bulletin (S/B) No. 28, dated December 1986.
(1) If one or more loose rivets, or cracks extending less than 9/16 inch (15 mm) from the center of the rivet is found, prior to further flight, repair as described in paragraph B of SOCATA TB Aircraft S/B No. 28, dated December 1986.
(2) If a crack 9/16 inch or longer from the center of the rivet is found, prior to further flight, replace the P/N TB 20.15.001.000 aileron with P/N TB 20.15.001.001 or P/N TB 20.15.001.002 aileron as applicable.

(b) The repetitive inspections specified in this AD are no longer required when the ailerons have been repaired or replaced per the actions specified in either paragraph (a)(1), or (a)(2) above.

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

(d) 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 (322) 513.38.30.

All persons affected by this directive may obtain copies of document(s) referred to herein upon request to SOCATA Groupe AEROSPATIALE, B.P. 38, 65001 Tarbes, France; Telephone 62.51.73.00 or 62.93.99.45 (for recorder); or the Product Support Manager, U.S., AEROSPATIALE, 2701 Forum Drive, Grand Prairie, Texas, 75053; Telephone (214) 641-3614; or may examine these documents referred to herein at the FAA, Office of the Assistant Chief Counsel, Room 1558, 601 East 12th Street, Kansas City, Missouri 64106.

This AD revises AD 87-12-09, Amendment 39-5650, which became effective on June 26, 1987.
This amendment (39-6224, AD 87-12-09 R1) becomes effective on June 25, 1989.

FOOTER: