AD 76-16-03 ACTIVE

76-16-03 HAWKER SIDDELEY AVIATION LIMITED: Amendment 39-2689 as amended by Amendment 39-3405. Applies to DH-114 "Heron" airplanes, all series and approved variants, certificated in all categories.

Compliance required as indicated.

To prevent possible failure of the wing to fuselage attachment and loss of the wing in flight, accomplish the following:

(a) Within the next 10 hours time in service after the effective date of this AD, unless already accomplished, inspect the upper lugs of the left and right hand side of the upper carry through boom, P/N 14FS345, for cracks using an ultrasonic method of inspection, in accordance with Appendix 1 of Hawker Siddeley Aviation Ltd., Technical News Sheet TNS F.19, Issue 1, dated July 26, 1976, or an FAA approved equivalent.

Note: This inspection can be conducted with the wing installed.

(b) If no cracks are found during the inspection required by paragraph (a) of this AD, repeat the inspection at intervals not to exceed 1200 flight hours or 2 calendar years, whichever occurs sooner, until the wings are removed for compliance with AD 72-15-01 at which time the area must be further inspected using the ultrasonic and dye penetrant methods in accordance with Appendix 2 of Hawker Siddeley Aviation, Limited, Technical News Sheet TNS F.19, Issue 1, dated July 26, 1976, (hereinafter referred to as the Technical News Sheet) or an FAA-approved equivalent. Thereafter, if no cracking is found, continue to inspect the area as follows:

(1) In accordance with the method specified in paragraph (a) of this AD at an interval not to exceed 3 calendar years from each time the area is inspected in conjunction with the wing removal required by AD 72-15-01; and

(2) In accordance with the ultrasonic and dye penetrant methods specified in Appendix 2 of the Technical News Sheet or an FAA-approved equivalent at each time the wings are removed for compliance with AD 72-15-01.

(c) If any cracks are found during any inspection required by this AD to be performed in accordance with the method specified in paragraph (a) of this AD, further inspect by ultrasonic and dye penetrant methods in accordance with Appendix 2 of the Technical News Sheet or an FAA-approved equivalent with the wing removed.

(d) If, during any inspection required by this AD, cracking of the lugs is found which is confined to only one of the lugs per side of the aircraft and exists only from the bolt hole towards the outboard end of the lug, the center section carry through boom may remain on the aircraft and continued flight is permitted provided the wing is removed at intervals not to exceed 300 flight hours or 3 months, whichever is sooner, and the cracked lug is inspected for crack propagation and the remaining two lugs are inspected for cracking, all in accordance with Appendix 2 of the Technical News Sheet or an FAA-approved equivalent, until the boom is replaced with a new boom of the same part number or a usedboom of the same part number determined after inspection in accordance with Appendix 2 of the Technical News Sheet to be crack-free.

(e) If, during any inspection required by this AD, cracking is found in more than one lug per side of the aircraft or the cracking of any one lug extends to both sides (inboard and outboard) of the bolt hole or runs from the bolt hole in an inboard direction only, before further flight, replace the carry through boom with a new boom of the same part number or a used boom of the same part number determined after inspection in accordance with Appendix 2 of the Technical News Sheet to be crack-free. Replacement booms must continue to be inspected in accordance with the following schedule:

(1) For used replacement booms, within 3 years from replacement, inspect the lug area in accordance with Appendix 1 of the Technical News Sheet or an FAA-approved equivalent except if any wing removal is required by AD 72-15-01 during that period, inspect in accordance with Appendix 2 of the Technical News Sheet or an FAA-approved equivalent concurrently with that wing removal. Thereafter inspect in accordance with the schedule and inspection methods specified in paragraphs (b)(1) and (b)(2) of this AD.

(2) For new replacement booms, inspect the lug area in accordance with Appendix 2 of the Technical News Sheet or an FAA-approved equivalent with the wing removed prior to accumulating 6 years in service and thereafter in accordance with the schedule and inspection methods specified in paragraphs (b)(1) and (b)(2) of this AD. However, if the first inspection required after replacement is not performed in conjunction with a wing removal required by AD 72-15-01, within the next 3 years after that inspection, inspect in accordance with Appendix 1 of the Technical News Sheet or an FAA-approved equivalent except if any wing removal is required by AD 72-15-01 during that period, inspect in accordance with Appendix 2 of the Technical News Sheetor an FAA-approved equivalent concurrently with that wing removal and thereafter inspect in accordance with the schedule and inspection methods specified in paragraphs (b)(1) and (b)(2) of this AD.

(f) Report the findings of the inspection specified in paragraph (a) of this AD to Chief, Aircraft Certification Staff, FAA, c/o American Embassy, APO New York, N.Y. 09667.

(Reporting approved by OMB No. 04-R-0174.)

Amendment 39-2689 became effective August 16, 1976.

This amendment 39-3405 becomes effective February 8, 1979.