COMMONWEALTH OF AUSTRALIA (Civil Aviation Regulations 1998), PART 39 - 105 CIVIL AVIATION SAFETY AUTHORITY SCHEDULE OF AIRWORTHINESS DIRECTIVES Bombardier (Boeing Canada/De Havilland) DHC-8 Series Aeroplanes AD/DHC-8/23 Amdt 3 NLG Upper Drag Strut Trunnion Fittings 11/95 Applicability: Model DHC-8, Series 100 and 300, serial numbers 003 through 395, except 011, 362, and 391, and which have accumulated more than 500 flight cycles. Requirement: Action in accordance with the Accomplishment Instructions contained in de Havilland ASB A8-53-40 Revision A: 1. Visually inspect, in-situ, the drag strut trunnion fittings for cracks, and torque check all the fasteners securing the fittings. If cracks are found on either fitting, replace both fittings with serviceable fittings prior to further flight. 2. (a) During the initial inspection, any fasteners found loose by the torque check must be replaced with new parts. (b) During subsequent inspections, any fastener found loose by the torque check must be tightened properly. 3. For aircraft already fitted with de Havilland Modification 8/1880, re-instate (or commence) the repetitive inspection required by parts 1 and 2 above in accordance with the schedule below: (a) If the aircraft has 900 or more flight cycles since the last inspection (or incorporation of Modification 8/1880), the next inspection (or the initial inspection) shall be performed within the subsequent 100 flight cycles. (b) If the aircraft has less than 900 flight cycles since the last inspection (or incorporation of Modification 8/1880), the next inspection (or the initial inspection) shall be performed at or before the due date of the actual 1000 flight cycle interval, determined from the last inspection (or incorporation of Modification 8/1880). Incorporation of de Havilland Modification 8/2139 (Introduction of New Trunnion Fittings and Fasteners for Drag Link of Nose Landing Gear) provides terminating action to the inspection requirements of this Directive. De Havilland Service Bulletin 8-53-49, dated 30 June 1995, provides approved instructions to incorporate Modification 8/2139 for aircraft not incorporating this modification during production. Note: Transport Canada AD CF-92-18R3 refers. Compliance: Initially, within 500 flight cycles after 12 November 1992, unless already accomplished during the last 500 flight cycles; and thereafter at intervals not to exceed 1000 flight cycles. COMMONWEALTH OF AUSTRALIA (Civil Aviation Regulations 1998), PART 39 - 105 CIVIL AVIATION SAFETY AUTHORITY SCHEDULE OF AIRWORTHINESS DIRECTIVES The compliance of the initial issue of this Directive remains unchanged. This Amendment is effective from 12 October 1995. Background: Cracks have been found in the two trunnion fittings that retain and support the nose landing gear upper drag strut. Investigations have indicated that this cracking problem is caused by ground handling loads that appear to be higher than originally predicted. This condition may be further aggravated by loose fasteners. Amendment 1 introduced optional terminating action. Amendment 2 rescinded the terminating action provided by an earlier issue of the AD. This action was prompted by reports that, due to bolt head gapping, installation difficulties have been encountered during incorporation of Modification 8/1880 on the aircraft, resulting in improper attachment of the fitting which, in turn, may cause the bolts to lose pre- tension. Amendment 3 is issued to introduce optional terminating action to the inspection requirements of this Directive.