AD 70-02-08
Applicability
| Type | Manufacturer | Model | Details |
|---|---|---|---|
| aircraft | Vickers-Armstrongs (Aircraft Limited) | Viscount 744 | Airworthiness Directives; BRITISH AIRCRAFT CORP. Models 744, 745D, and 810 Series Airplanes |
| aircraft | Vickers-Armstrongs (Aircraft Limited) | Viscount 745D | Airworthiness Directives; BRITISH AIRCRAFT CORP. Models 744, 745D, and 810 Series Airplanes |
| aircraft | Vickers-Armstrongs (Aircraft Limited) | Viscount 810 | Airworthiness Directives; BRITISH AIRCRAFT CORP. Models 744, 745D, and 810 Series Airplanes |
Unsafe Condition
Failure of the fuselage leading edge frame structure due to cracks in reinforcing plates P/N 70152-2787/8 or P/N 70152-3311/12.
AI-generated summary from the source AD text. Verify against the official source before acting.
Required Actions
Visually inspect reinforcing plates for cracks at specified intervals. Replace cracked plates with new P/N 70152-3311/12 and incorporate specified modifications if cracks are found.
AI-generated summary from the source AD text. Verify against the official source before acting.
Compliance Time
Within the next 500 landings after the effective date (for P/N 70152-2787/8) or within the next 1,500 landings after the effective date (for P/N 70152-3311/12), unless already accomplished within the last interval. Thereafter, inspections at intervals not exceeding 1,000 or 3,000 landings respectively. Repairs must be done within next 500 landings if cracks are found.
AI-generated summary from the source AD text. Verify against the official source before acting.
Affected Aircraft
Vickers-Armstrongs (Aircraft Limited) Viscount Models 744, 745D, and 810 series airplanes with fuselage leading edge frame reinforcing plates P/N 70152-2787/8 or P/N 70152-3311/12 installed.
AI-generated summary from the source AD text. Verify against the official source before acting.
Source: Official FAA Source ↗
Retrieved: Apr 8, 2026
Rights: U.S. Government Public Domain
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