AD 86-17-03

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AD Number:
86-17-03
Document Type:
AD Final Rules
Docket Number:
Unknown
Subject Heading:
Airworthiness Directives; Socata Model TB20 Series Airplanes
Subject:
Elevator Attachments
Status:
Current
Citation:
This information is not available.
Citation Publish Date:
Effective Date:
09/22/1986
Make:
SOCATA
Model:
TB 20
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Superseded AD: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Superseded By: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: 86-17-03
CITATION:   This information is not available.

PAGE NUMBER:  

DOCKET NUMBER:   Unknown

AMENDMENT:   39-5392

AD NUMBER:   86-17-03

SUBJECT HEADING:   Airworthiness Directives; Socata Model TB20 Series Airplanes

ACTION:  

SUMMARY:  

DATES:   Effective September 22, 1986.

ADDRESSES:  

FOR FURTHER INFORMATION CONTACT:  

SUPPLEMENTARY INFORMATION:  

REGULATORY TEXT:   86-17-03 SOCATA: Amendment 39-5392. Applies to Model TB20 (Serial Numbers up to and including No. 479) airplanes certificated in any category.

Compliance: Required within 100 hours time-in-service after the effective date of this AD, unless already accomplished.

To assure the integrity of the trim control system, accomplish the following:
(a) Replace the attachment of the elevator tab control to the elevator tab levers in accordance with Operation II of the Description paragraph of SOCATA Service Bulletin (S/B) No. 24, dated January 1985, as follows:
(1) Remove and discard the bolt, washers, spacer, nut and pin attaching the elevator trim tab rod eye-end-fitting to the trim tab levers. (Ref. Detail A of the figure in SOCATA Service Bulletin No. 24)
(2) Measure the rod length in order to reposition the eye-end-fitting.
(3) Remove the eye-end-fitting.
(4) Bore the eye-end-fitting at dia. 10 mm (.3937 inches + .0009, - .0000).
(5) Bore the two tab levers at dia. 6 mm (.2363 inches + .0007, - .0000).
(6) Grease the new bolt of dia. 6 mm (nominal 0.24 in.).
(7) Install the eye-end-fitting at the rod length measured using a new lock plate (Z00.5544.1.10.000).
(8) Install the dia. 6 mm bolt, the spacer and washers according to Detail A of the figure shown in SOCATA S/B No. 24.
(9) Tighten the castellated nut (apply a tightening torque of 0.42 m.daN-37 inch.Pound), if necessary loosen to the lower notch.
(10) Install pin and grease.
(11) Bore the tab levers according to Detail B of the figure shown in SOCATA S/B No. 24 to 5 mm (.1969 inches + .0003, -.0000) diameter.
(12) Grease the bolt.
(13) Install the spacer, the dia. 5 mm (nominal 0.20 in.) bolt, the washer and nut according to Detail B of the figure in SOCATA S/B No. 24.
(14) Tighten the nut (apply a tightening torque of 0.25 m.daN - 23 inch.Pound).
(15) Check the tab deflection angles (SOCATA TB20 Maintenance Manual Section V.5).

(b) Aircraft may be flown in accordance with Federal Aviation Regulation 21.197 to a location where this AD can be accomplished.

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

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; or FAA, Office of the Regional Counsel, Room 1558, 601 East 12th Street, Kansas City, Missouri 64106.

This amendment becomes effective on September 22, 1986.

FOOTER: