AD 69-26-02
Applicability
| Type | Manufacturer | Model | Details |
|---|---|---|---|
| aircraft | de Havilland Aircraft Co., Ltd., The | D.H.114 Heron Series 2A | Airworthiness Directives; Hawker Siddeley Aviation, Limited Model D.H. 114 Airplanes |
| aircraft | de Havilland Aircraft Co., Ltd., The | D.H.114 Heron Series 2DA | Airworthiness Directives; Hawker Siddeley Aviation, Limited Model D.H. 114 Airplanes |
| aircraft | de Havilland Aircraft Co., Ltd., The | D.H.114 Heron Series 2X | Airworthiness Directives; Hawker Siddeley Aviation, Limited Model D.H. 114 Airplanes |
Unsafe Condition
Fatigue cracks developing in the engine mount pick-up wing straps located at the top outboard position of the left and right inboard engine-to-wing attachment structure.
AI-generated summary from the source AD text. Verify against the official source before acting.
Required Actions
Within 50 hours' time in service after the effective date, inspect the upper outboard engine mounting pick-up wing straps for fatigue cracks using dye penetrant method. Within 300 hours' time in service after inspection, remove and discard specific bolts and nuts, re-inspect, and replace with new bolts (P/N A.25/4E) and nuts (P/N A.16Y/ET). Thereafter, inspect every 600 hours' time in service and replace cracked straps.
AI-generated summary from the source AD text. Verify against the official source before acting.
Compliance Time
Within 50 hours' time in service after the effective date of this AD, unless already accomplished within the last 250 hours' time in service
AI-generated summary from the source AD text. Verify against the official source before acting.
Affected Aircraft
Hawker Siddeley Aviation, Limited Model D.H. 114 Heron Series 2A, 2DA, 2X airplanes
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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