AD/BEECH 200/35 Amdt 6 - Wing Fatigue Life Limitation
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COMMONWEALTH OF AUSTRALIA (Civil Aviation Regulations 1998), PART 39 - 105 CIVIL AVIATION SAFETY AUTHORITY
SCHEDULE OF AIRWORTHINESS DIRECTIVES
View image in the official source Beechcraft 200 (Super King Air) Series Aeroplanes
AD/BEECH 200/35
Amdt 6
Applicability: All models.
Wing Fatigue Life Limitation 3/98
Requirement: 1. For aircraft serial numbers BB-2 through BB-161:-
Retire from service the outer wing lower spar cap assembly in accordance with Beech Service Bulletin No 2240.
Note: FAA AD 89-02-03 refers.
- (a). For aircraft serial numbers BB-1158, BB-1167, BB-1193 through BB-1203, BB-1207 through BB-1312, BB1314 through BB-1334, BL-124 through BL- 132, and BT-33:
Modify the lower forward wing spar attachment fittings by installing Beech Kit No 101-4050, and,
2. (b). For aircraft serial numbers BB-1158, BB-1167, BB-1193 and on, BL-73 and on, BN-5 and on, and BT-31 and on:
Remove the wings and inspect the wing spar shear attach fittings for cracks using a fluorescent dye penetrant method in accordance with CAO 108.10.
Note: FAA AD 91-12-10 refers.
3. For all aircraft, retire from service the wing centre and outer section main spar lower cap assemblies.
Note 1: The lower cap assemblies includes the lower wing attachment fittings.
Note 2: Section 4-00-00 of the Beech 200 Maintenance Manual contains related information.
Compliance: 1. Retire in accordance with Beech Service Bulletin No 2240.
- (a). Modify prior to exceeding 9 500 hours component time in service.
2. (b). Initially inspect prior to 15000 hours time in service. Re-inspect at intervals not to exceed 6000 hours component time in service until 30000 flight cycles. Thereafter inspect at intervals of 1500 hours time in service, or 1200 flight cycles, whichever occurs sooner.
3. Retire prior to exceeding 30 000 hours component time in service. This amendment becomes effective on 26 February 1998.
COMMONWEALTH OF AUSTRALIA (Civil Aviation Regulations 1998), PART 39 - 105 CIVIL AVIATION SAFETY AUTHORITY
SCHEDULE OF AIRWORTHINESS DIRECTIVES
Background: Amendment 3 introduced a reduced spar-cap life for aircraft listed in Requirement 1. Early spar cap assemblies were manufactured with a smaller critical radius in the spar cap fitting which reduced the spar cap fatigue life. Beech SB No. 2240 refers.
Amendment 4 introduced the attachment fitting requirements of FAA AD 91-12-10 and the interim lives applicable to Requirement 2 aircraft. The lower life limits for the unmodified attachment fittings result from a fatigue test in which the shear fitting failed well short of the interim 15 000 hour life. The Beech modification kit introduces cold worked bushes to the attachment fitting lug holes, reducing their susceptibility to fatigue failure.
Amendment 5 makes a correction to the applicability of Requirement 2.
Amendment 6 incorporates revised wing spar shear attachment fitting fatigue lives of 30000 hours time in service with an associated inspection schedule. These extensions to the aircraft fatigue lives have been accepted by CASA for Australian operators, based on a critical review of the manufacturer’s fatigue test results.
Amendment 5 of this airworthiness directive became effective on 14 September 1995. Amendment 4 of this airworthiness directive became effective on 5 September 1991. The original issue of this airworthiness directive became effective on
30 September 1981.