AD 69-25-07

69-25-07 HAWKER SIDDELEY AVIATION, LTD.: Amdt. 39-888. Applies to Model DH-114 Heron Airplanes which have aileron lever, P/N 14 WA.199 installed.

Compliance is required as indicated unless already accomplished.

To prevent fatigue failure of the aileron lever, accomplish the following:

(a) Visually inspect the aileron lever, P/N 14 WA.199 for cracks at the lugs for the attachment of the connecting rod and in the counterbored portion which receives the mass balance arm 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. If evidence of cracks is found, verify using dye penetrant or other FAA-approved equivalent inspection methods.

(b) If cracks are found during the inspection required by paragraph (a), before further flight, install a new forged aileron lever, P/N 14 WA.245 in accordance with Hawker Siddeley Aviation, Ltd. Heron Modification No. 662, or an equivalent approved by the Chief, Aircraft Certification Staff, Europe, Africa, and Middle East Region.

(c) If no cracks are found during the inspections required by paragraph (a), within the next 1,000 hours' time in service after the effective date of this AD, install a new forged aileron lever P/N 14 WA.245 in accordance with Hawker Siddeley Aviation, Ltd. Heron Modification No. 662, or an equivalent approved by the Chief, Aircraft Certification Staff, Europe, Africa, and Middle East Region.

(d) The inspections required in paragraph (a) may be discontinued after the new aileron lever, P/N WA.245 or an equivalent approved by the Chief, Aircraft Certification Staff, Europe, Africa, and Middle East Region is installed.

(Hawker Siddeley Aviation, Ltd. Technical News Sheet Heron No. W.3, Issue 3, dated 14 July 1969 covers this subject.)

This supersedes Amendment 453, Part 507 (27 F.R. 5793), AD 62-14-01. This amendment becomes effective January 3, 1970.