AD 69-25-07
Applicability
| Type | Manufacturer | Model | Details |
|---|---|---|---|
| aircraft | de Havilland Aircraft Co., Ltd., The | D.H.114 Heron Series 2A | Airworthiness Directives; Hawker Siddeley Aviation Ltd Model DH-114 Heron Airplanes |
| aircraft | de Havilland Aircraft Co., Ltd., The | D.H.114 Heron Series 2DA | Airworthiness Directives; Hawker Siddeley Aviation Ltd Model DH-114 Heron Airplanes |
| aircraft | de Havilland Aircraft Co., Ltd., The | D.H.114 Heron Series 2X | Airworthiness Directives; Hawker Siddeley Aviation Ltd Model DH-114 Heron Airplanes |
Unsafe Condition
Fatigue failure of the aileron lever, P/N 14 WA.199, due to cracks at the lugs for connecting rod attachment and in the counterbored portion receiving the mass balance arm.
AI-generated summary from the source AD text. Verify against the official source before acting.
Required Actions
Visually inspect the aileron lever P/N 14 WA.199 for cracks at specified locations every 50 hours' time in service. If cracks found, use dye penetrant or approved method to verify and install new forged lever P/N 14 WA.245. If no cracks, install new lever within 1,000 hours' time in service after AD effective date.
AI-generated summary from the source AD text. Verify against the official source before acting.
Compliance Time
within the next 50 hours' time in service after the effective date of this AD unless already accomplished within the last 50 hours' time in service, and thereafter at intervals not to exceed 50 hours' time in service from the last inspection
AI-generated summary from the source AD text. Verify against the official source before acting.
Affected Aircraft
Hawker Siddeley Aviation Ltd Model DH-114 Heron Airplanes with aileron lever P/N 14 WA.199 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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