- Effective
- November 19, 1966
- Models
- Viscount 744, Viscount 745D, Viscount 810
- Data sheet
- TCDSA-814
- Product
- Aircraft · Large airplane
- Amendment
- 39-304
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 | 61d385ee…79436d9 | FAA DRS (API key needed) |
On this page
The airworthiness directive
66-29-04 VICKERS: Amdt. 39-304 Part 39 Federal Register November 9, 1966. Applies to Viscount Models 744, 745D, and 810 Series Airplanes.
Compliance required within the next 100 hours' time in service after the effective date of this AD, unless already accomplished.
To prevent fouling between the trailing edge of the elevator hinge beam shroud and the elevator skin lap joint, accomplish the following:
(a) Visually inspect top and bottom shrouds on elevator hinge beam assemblies to unsure that clearance between trailing edge of shroud and forward edge of elevator skin lap joints or rivet heads is not less than 0.20 inch throughout full range of elevator movement.
(b) If clearance is less than 0.20 inch, cut back trailing edge of hinge beam shroud to provide clearance of at least 0.20 inch but less than 0.25 inch throughout full range of elevator movement.
(British Aircraft Corporation (B.A.C.) Ltd. Preliminary Technical Leaflet (PTL) No. 263, Issue 1, (700 Series) and No. 126, Issue 1) (800/810 Series) pertain to this subject.)
This directive effective November 19, 1966.
Affected TCDS · 1
The type certificate data sheets for the models this AD names, matched by model and maker.