AD 72-08-03
Applicability
| Type | Manufacturer | Model | Details |
|---|---|---|---|
| aircraft | de Havilland Aircraft Co., Ltd., The | D.H.114 Heron Series 2A | Airworthiness Directives; Hawker Siddeley Model DH-114 "Heron" Airplanes |
| aircraft | de Havilland Aircraft Co., Ltd., The | D.H.114 Heron Series 2DA | Airworthiness Directives; Hawker Siddeley Model DH-114 "Heron" Airplanes |
| aircraft | de Havilland Aircraft Co., Ltd., The | D.H.114 Heron Series 2X | Airworthiness Directives; Hawker Siddeley Model DH-114 "Heron" Airplanes |
Unsafe Condition
Cracks in the upper arm of the rudder control pedal reversal lever, P/N 4CF.767A, could lead to failure of the rudder control system.
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Required Actions
Inspect the upper area of the rudder control pedal reversal lever (P/N 4CF.767A) using dye penetrant method per Hawker Siddeley Technical News Sheet 'Heron' 114, No. C.F.15. If cracks are found, replace the part before further flight. If marks or damage are found, blend out marks, apply selenious acid treatment, repaint, and continue inspections.
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Compliance Time
Within the next 200 hours' time in service after May 1, 1972, unless already accomplished within the last 2,200 hours' time in service, and thereafter at intervals not to exceed 2,400 hours' time in service.
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Affected Aircraft
Hawker Siddeley Model DH-114 'Heron' airplanes: Series 2A, 2DA, 2X
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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