- Effective
- November 24, 1971
- Models
- 1100, FH-1100
- Data sheet
- TCDSH2WE
- Registered aircraft
- 8 matched by model
- Product
- Aircraft · Rotorcraft
- Amendment
- 39-1334
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 | 70e3dec5…45d7f27 | FAA DRS (API key needed) |
On this page
The airworthiness directive
71-24-02 FAIRCHILD HILLER ROTORCRAFT: Amdt. 39-1334. Applies to Model 1100 and FH-1100 Type Helicopters certificated in all categories.
Compliance required as indicated.
To preclude fatigue failure of the transmission mount strut, P/N 24-28031, due to internal corrosion, accomplish the following:
Within the next 30 days after the effective date of this AD, unless already accomplished replace P/N 24-28031 left side, lateral, adjustable transmission strut with P/N 24-28031-11 strut in accordance with Section 28 of the FH-1100 Service Manual or an alternate method approved by the Chief, Engineering & Manufacturing Branch, FAA, Eastern Region. Upon installation of MS-21252 fork fitting apply RTV-102 sealant or equivalent to the threads of fitting and under AN316-5R retaining nut.
This amendment is effective November 24, 1971.
Affected TCDS · 1
The type certificate data sheets for the models this AD names, matched by model and maker.
Registered aircraft · 8
Registered aircraft whose airframe or engine model this AD names. Matched by model only, so check each against the AD’s applicability.
| 1968 | 1 |
|---|---|
| 1970 | 1 |
| 1972 | 1 |
5 with no year recorded