AD 72-15-01 ACTIVE

72-15-01 HAWKER SIDDELEY AVIATION LTD.: Amendment 39-1483. Applies to deHavilland "Heron" Model DH-114 airplanes.

To prevent a possible failure of the wing to 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 subparagraphs (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 with (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 Appendix 1 of Hawker Siddeley Aviation Limited Technical News Sheet, Series: Heron (114) No. W. 17, Issue 1, dated July, 7, 1970, 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: Heron (114), No. W. 9, Issue 5, 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: Heron (114), No. W.9 (referred to above), or on 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 the sensitivity 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 70-15-11, Amendment 39-1041 issued July 13, 1970, as amended by Amendment 39-1186 issued March 31, 1971; AD 70-12-09, Amendment 39-1010, dated June 8, 1970; AD 70-05-04, Amendment 39-948, dated May 28, 1970; 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: Heron (114) No. W. 9 (referred to above), or an FAA-approved equivalent.

(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: Heron (114), No. W. 9 (referred to above), 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 except as provided in paragraphs (d), (e) and (f) of this AD.

(d) If during the inspections required by paragraph (a), the following obsolete main wing to fuselage lower attachment bolts are found, before further flight, replace the obsolete bolts with the appropriate replacement bolts listed below:

Obsolete Bolt P/Ns
Replacement Bolt P/Ns
14.FS.15
14FS.6669
14.FS.3985
14FS.6669
14.FS.6399
14FS.6669
14.2FS.1555
14.2FS.575
RD.14W.173ND
RD.14FS.274
RD.14W.175ND
RD.14FS.275
RD.14FS.262
RD.14FS.271
RD.14FS.259
RD.14FS.272
RD.14FS.260
RD.14FS.273
RD.14FS.165
RD.14FS.273

(e) If during the inspections required by paragraph (a), the following obsolete main wing to fuselage lower attachment bolts are found, before further flight, ream the wing center section spar boom lugs and main spar lower pick-up fittings in accordance with Hawker Siddeley Repair Drawings RD.14FS.263 and RD.14FS.270 or FAA-approved equivalents and replace the obsolete bolts with the appropriate replacement bolts listed below:

ObsoleteBolt P/Ns
Replacement Bolt P/Ns
RD.14FS.254
RD.14FS.271
RD.14FS.232
RD.14FS.272
RD.14FS.223
RD.14FS.273

(f) If during the inspections required by paragraph (a), main wing to fuselage lower attachment bolts are found which are other than those listed as either obsolete or replacement bolts in paragraphs (c) and (d), before further flight, report the part number for the installed bolts to the Chief, Aircraft Certification Staff, FAA, Europe, Africa, and Middle East Region to obtain the identification of the required replacement bolts (reporting approved by the Bureau of the Budget under BOB No. 04.R 0174). Upon receipt of notice giving the part number of the required replacement bolts, install the replacement bolts specified in the notification.

This amendment supersedes Amendment 39-1041 (35 F. R. 11554), AD 70-15-11 as amended by Amendment 39-1186 (36 F.R. 5967).

This amendment becomes effective July 11, 1972.