- Effective
- March 29, 1976
- Model
- SF-26A Standard
- Data sheet
- TCDSG4IN
- Registered aircraft
- 1 matched by model
- Product
- Aircraft · Glider
- Amendment
- 39-2552
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 | 20 KB | 89b04465…dff6e8e | FAA DRS (API key needed) |
On this page
The airworthiness directive
76-06-03 SCHEIBE FLUGZEUGBAU GmbH: Amendment 39-2552. Applies to SF 26A gliders, certificated in all categories.
Compliance is required as indicated.
To prevent the possible loss of lateral control, accomplish the following:
(a) Within the next 10 hours time in service after the effective date of this AD, and thereafter at intervals not to exceed 50 hours time in service from the last inspection, visually inspect the aileron bellcranks near the weld of the middle bearing bushing for cracks with a magnifying glass of at least 5 power, in accordance with Scheibe Technical Note No. 232-1/75 dated October 7, 1975, or an FAA-approved equivalent.
(b) If a crack is found during an inspection required by paragraph (a) of this AD, before further flight, repair the cracked aileron bellcrank, in accordance with FAR 43.13.
This amendment becomes effective March 29, 1976.
Affected TCDS · 1
The type certificate data sheets for the models this AD names, matched by model and maker.
Registered aircraft · 1
Registered aircraft whose airframe or engine model this AD names. Matched by model only, so check each against the AD’s applicability.