- Effective
- September 22, 1986
- Model
- TB 20
- Data sheet
- TCDSA51EU
- Registered aircraft
- 200 matched by model
- Product
- Aircraft · Small airplane
- Amendment
- 39-5392
Unofficial copy of the text in the FAA’s Dynamic Regulatory System. The FAA’s own copy is the authoritative one. DRS record last changed May 30, 2024.
Copies of the files this page was built from, with their SHA-256. Retrieved October 18, 2026.
| File | Size | SHA-256 | Original |
|---|---|---|---|
| FAA DRS HTML | 25 KB | c7bbb58b…2a133e1 | FAA DRS (API key needed) |
On this page
The airworthiness directive
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.
Affected TCDS · 1
The type certificate data sheets for the models this AD names, matched by model and maker.
Registered aircraft · 200
Registered aircraft whose airframe or engine model this AD names. Matched by model only, so check each against the AD’s applicability.
| 1983 | 1 |
|---|---|
| 1984 | 11 |
| 1985 | 8 |
| 1986 | 4 |
| 1987 | 3 |
| 1989 | 10 |
| 1990 | 8 |
| 1991 | 5 |
| 1992 | 1 |
| 1993 | 1 |
| 1994 | 6 |
| 1995 | 4 |
| 1996 | 3 |
| 1997 | 1 |
| 1998 | 10 |
| 1999 | 7 |
| 2000 | 9 |
| 2001 | 8 |
| 2002 | 3 |
| 2003 | 4 |
93 with no year recorded