69-20-04 FAIRCHILD-HILLER: Amdt. 39-849. Applies to F-27 and FH-227 type airplanes certificated in all categories and incorporating rear passenger door spindle, P/N 27-313006-3, -5, -7, or -9.
Compliance required within the next 100 hours' time in service after the effective date of this AD, unless already accomplished.
To provide a more positive retention of the passenger door locking mechanism accomplish the following:
(a) For F-27 type airplanes with spindle, P/N 27-313006-3, installed in the door lock mechanism, comply with Section D(1) through D(8) of Revision 1 of Fairchild Hiller Service Bulletin No. F-27-52-27 dated June 17, 1969. In place of Step "D(5)", rig the door mechanism in accordance with Fairchild Hiller Service Bulletin No. F-27-52-19, dated June 17, 1969.
(b) For F-27 type airplanes with spindle, P/N 27-313006-5, 27-313006-7, or 27-313006-9, installed in the door lock mechanism, comply with Section E(1) through E(8) of Revision 1- of Fairchild Hiller Service Bulletin No. F-27-52-27, dated June 17, 1969. Rig the door mechanism in accordance with Fairchild Hiller Service Bulletin No. F-27-52-19, dated June 17, 1969.
(c) For FH-227 type airplanes with spindle, P/N 27-313006-5, 27-313006-7, or 27-313006-9, installed in the door lock mechanism, comply with the "Accomplishment Instructions" of Fairchild Hiller Service Bulletin No. FH-227-52-13, dated June 17, 1969.
(d) An equivalent alteration approved by the Chief, Engineering and Manufacturing Branch, FAA, Eastern Region may be used in lieu of the foregoing methods.
(e) Upon request with substantiating data submitted through an FAA maintenance inspector, the compliance time specified in this AD may be increased by the Chief, Engineering and Manufacturing Branch, FAA, Eastern Region.
This amendment effective November 3, 1969.