70-23-02 de HAVILLAND: Amendment 39-1106 as amended by Amendment 39-1124 is further amended by Amendment 39-1680. DeHavilland Aircraft Company, Ltd. Applies to all DeHavilland Model D.H. 104 Dove Series 7A, 8A, 7AXC, 8AXC airplanes modified per STC SA1554WE or SA1747WE.
(a) Within the next 10 hours time in service after receipt of telegram dated October 23, 1970, unless already accomplished within the last ten hours time in service, and thereafter at intervals not to exceed twenty hours time in service from the last inspection, accomplish the following:
(1) With wing weight relieved, visually inspect lower main spar cap in region of rib 4 using a 4 power glass and/or dye penetrant methods.
If cracks are found, repair prior to further flight in a manner approved by the Chief, Aircraft Engineering Division, FAA Western Region.
(2) Determine that all tank door attachment bolts (Wing Sta. 0-40) are tight. If any bolts are found to have loosened, remove the door, check for hole elongation in the door and supporting structure, and replace the nut plates for the loose bolts. If any hole elongation is found, repair in accordance with Section (b)(2) below.
(b) Within the next 200 hours time in service after receipt of this telegram, unless already accomplished within the last 800 hours time in service, and thereafter at intervals not to exceed 1000 hours time in service from the last inspection, accomplish the following:
(1) With wing weight relieved, remove all tank doors (Wing Sta. 0-40) and accomplish inspections of lower spar cap, the attachment bolt holes in doors and the door supporting structure in accordance with Paragraphs 3.2 through 3.5 of Strato Engineering Company, Inc. Service Bulletin No. APA-3, Revision A, dated October 23, 1970, or later FAA approved revision, or an equivalent inspection procedure approved by the Chief, Aircraft Engineering Division, FAA Western Region. Wings should continue to be supported until doors have been reinstalled.
(2) Accomplish modification to all out-of-tolerance holes and nutplates in accordance with Section 4.0 of Strato Engineering Company, Inc. Service Bulletin No. APA-3, Revision A, dated October 23, 1970, or later FAA approved revision, or an equivalent procedure approved by the Chief, Aircraft Engineering Division, FAA Western Region.
(c) After accomplishing (b), repeat inspections outlined in (a)(1) and (a)(2) above at intervals not to exceed 200 hours time in service from the last inspection.
(d) After the effective date of this amendment 39-1680 to AD 70-23-02, on those aircraft which have incorporated STC SA2438WE and the inspection access hole design provided therein, or an equivalent modification approved by the Chief, Aircraft Engineering Division, FAA Western Region, the visual inspections of paragraph (a)(1) and the determination of paragraph (a)(2), above, must be performed at intervals not to exceed 500 and 250 hours time in service, respectively. These actions must be accomplished with the wing fuel tanks empty and the aircraft in the static condition. The use of a 4 power glass and/or dye penetrant method is not required. The inspection of (a)(1) must be performed both inboard and outboard of rib 4.
This supersedes the telegraphic AD dated October 14, 1970, concerning this problem.
Amendment 39-1106 became effective November 16, 1970 for all persons except those to whom it was made effective by telegram dated October 23, 1970, which contained this amendment.
Amendment 39-1124 became effective December 11, 1970.
This amendment 39-1680 is made effective July 3, 1973.