72-16-07 HAWKER SIDDELEY AVIATION LTD: Amendment 39-1492. Applies to de Havilland "Dove" Model DH-104 airplanes which have not been modified to incorporate Supplemental Type Certificate SA 1747WE.
To prevent a possible failure of the wing fuselage attachment, accomplish the following:
(a) Within the next 25 hours' time in service after the effective date of this AD, unless already accomplished in accordance with one of the AD's specified in subparagraph (a)(4), comply with subparagraph (a)(1), (a)(2), and (a)(3), and thereafter comply with subparagraph (a)(2) at intervals not to exceed six years from the last inspection and comply with subparagraph (a)(3) at intervals not to exceed 4,500 hours' time in service from the last inspection.
(1) Inspect the bore of the wing main spar lower pick-up fittings for chrome plating in accordance with de Havilland Service Technical News Sheet, Series: CT(104), No. 178, Issue 1, dated July 10, 1961, or an FAA-approved equivalent. If a bore is found to be chrome plated, before further flight, replace the affected fitting with a serviceable fitting that does not have a chrome plated bore.
(2) Inspect the wing main spar lower pick up fittings, the fuselage center section spar boom lugs, and the main wing to fuselage lower attachment bolts for corrosion, surface roughness, and signs of fretting in accordance with Appendix 1 of Hawker Siddeley Aviation Limited, Technical News Sheet, Series: CT(104), No. 168, Issue 4, dated July 12, 1971, or an FAA-approved equivalent.
(3) Inspect the total length of the bore of the wing main spar lower pick-up fittings for cracks in accordance with Appendix 2 of Hawker Siddeley Aviation Limited, Technical News Sheet, Series: CT(104), No. 168, Issue 4, dated July 12, 1971, or an FAA- approved equivalent. Eddy current equipment, of a manufacture not specified in the referenced service bulletin, may be used to comply with this subparagraph, if the equipment meets thesensitivity requirement contained in the referenced service bulletin, the equipment is suitable for inspection of ferrous materials, and the procedure used to operate the equipment complies with the equipment manufacturer's recommended operating instructions.
(4) Previous AD's on this same subject which may be used in establishing compliance with the initial inspection specified in paragraph (a) are: AD 70-15-06, Amendment 39-1033 issued on July 8, 1970; AD 70-12-08, Amendment 39-1009 dated June 8, 1970; AD 67- 32-03, Amendment 39-513 issued November 9, 1967; AD 61-18-03, Amendment 329 to Part 507 issued August 25, 1961; and the telegraphic AD's dated May 28, 1970, and June 11, 1970.
(b) Each time the wing to fuselage lower joint is reassembled after any inspection required by this AD or for any other reason, apply corrosion protection in accordance with Appendix 1 of Hawker Siddeley Aviation Limited, Technical News Sheet, Series: CT(104), No. 108, Issue 4, dated July 12, 1971, or an FAA-approved equivalent, and incorporate Modification 686 bolts and shims upon reassembly of the wing to fuselage lower joint on those airplanes having Modification 538 installed.
(c) If during the inspections required by subparagraphs (a)(2) or (a)(3), corrosion, pitting, fretting, or corrosion discoloration is found which cannot be removed using the procedures in Appendix 1 of Hawker Siddeley Aviation Limited, Technical News Sheets, Series: CT(104), No. 168, Issue 4, dated July 12, 1971, or an FAA-approved equivalent, or if cracks are found in the wing main spar pick-up fitting bore, before further flight, replace the affected part with a serviceable part of the same part number.
This amendment supersedes Amendment 39-1033 (35 F.R. 11385), AD 70-15-06.
This amendment becomes effective July 31, 1972.