# AD 72-10-01: Cracks in Control Pedal Reversal Lever

- Type: Airworthiness directive
- Status: Current
- Products: de Havilland Aircraft Co., Ltd., The D.H. 104 Dove Series 1A, D.H. 104 Dove Series 2A, D.H. 104 Dove Series 5A, D.H. 104 Dove Series 5BA, D.H. 104 Dove Series 6A, D.H. 104 Dove Series 6BA, D.H. 104 Dove Series 7A, D.H. 104 Dove Series 7AXC, D.H. 104 Dove Series 8A and D.H. 104 Dove Series 8AXC
- Effective: May 31, 1972
- Superseded by: Nothing supersedes this AD
- Product type: Aircraft, Small airplane
- Amendment: 39-1441
- Registered aircraft: 3 may be affected, by airframe or engine model (OpenAirDocs)
- FAA DRS: https://drs.faa.gov/browse/excelExternalWindow/5C06B3229533E95E86256A3400702346.0001
- DRS record last changed: May 30, 2024
- Page: https://openairdocs.org/ad/72-10-01

## The airworthiness directive

72-10-01 HAWKER SIDDELEY AVIATION: Amendment 39-1441. Applies to Hawker Siddeley de Havilland Model DH-104 "Dove" airplanes.

Compliance is required as indicated.

To detect cracks in the upper arm of the rudder control pedal reversal lever, P/N 4CF.767A, accomplish the following:

  (a) Within the next 200 hours' time in service after the effective date of this AD, 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 from the last inspection, inspect the upper arm of the rudder control pedal reversal lever, P/N 4CF.767A, for cracks, using a dye penetrant method, in accordance with Hawker Siddeley Technical News Sheet Series: CT(104) No. 219, Issue 1, dated October 19, 1970, or later ARB-approved issue or FAA-approved equivalent. If no cracks are found, visually inspect the upper radiused surface of the upper arm of the rudder control reversal lever for marks or other evidence of mechanical damage.

  (b) If a crack is found during an inspection required by paragraph (a), before further flight replace the rudder control pedal reversal lever, P/N 4CF.767A, with a new part of the same part number and continue to inspect in accordance with paragraph (a).

  (c) If marks or other evidence of mechanical damage are found during an inspection required by paragraph (a), before further flight smoothly blend out the marks and renew the protective treatment, using selenious acid treatment, or an FAA-approved equivalent, and repaint the part. After refitting the part, continue to inspect in accordance with paragraph (a).

This amendment is effective May 31, 1972.

## Affected data sheets (1) (OpenAirDocs)

The type certificate data sheets whose models the AD names.

- [TCDS A-807](https://openairdocs.org/tcds/A-807): Acro Aeronautical Services Ltd; names 10 of 10 models: D.H. 104 Dove Series 8A, D.H. 104 Dove Series 7A, D.H. 104 Dove Series 1A, D.H. 104 Dove Series 5A, D.H. 104 Dove Series 7AXC, D.H. 104 Dove Series 8AXC, D.H. 104 Dove Series 2A, D.H. 104 Dove Series 5BA…

## Registered aircraft it may apply to (OpenAirDocs)

Matched by airframe and engine model; the AD's applicability may narrow it by serial number, part number or equipment.

- Aircraft: 3 (3 by airframe model, 0 by engine model)
- Makers: Dehavilland 3

Models with the most aircraft:

- [Dehavilland DH104 DOVE 6A](https://openairdocs.org/model/dehavilland-dh104-dove-6a): 3 aircraft (airframe model)

All 1 models: https://openairdocs.org/ad/72-10-01/models.md
Every aircraft: https://openairdocs.org/ad/72-10-01/aircraft.md

Its text cites no advisory circulars or STCs.

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