AD/CESSNA 500/15 - Wing Main Spar - Inspection and Modification
1AD/CESSNA 500/15 - Wing Main Spar - Inspection and Modification
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COMMONWEALTH OF AUSTRALIA (Civil Aviation Regulations 1998), PART 39 - 105 CIVIL AVIATION SAFETY AUTHORITY
SCHEDULE OF AIRWORTHINESS DIRECTIVES
Image unavailable in extracted text Cessna 500 (Citation) Series Aeroplanes
AD/CESSNA 500/15 Wing Main Spar - Inspection
and Modification
Applicability: All models 500 and 501 with unit numbers 0001 to 0520.
4/81
Requirement: 1. Inspect the wing spar upper and lower cap in the area of wing section 37 in accordance with Cessna SL No. 57-2 Rev. 3 dated 15 May 1980. FAA AD 79-12-06 also refers.
2. Inspect and modify in accordance with :
(a) Cessna SB No. 57-10 Rev. 1 dated 28 March 1980 for aircraft unit Nos. 0001 to 0349.
(b) Cessna SB No. 57-11 rev. 1 dated 28 March 1980 for aircraft unit Nos. 0350 to 0520.
3. Visually inspect for further cracks the wing main spar upper and lower caps of aircraft modified in accordance with SB No. 57-10 Rev. 1 or SB No. 57-11 Rev. 1, in the area of the W.S. 37 modification.
Compliance: For Para. 1 - As detailed in the requirement document.
For Para. 2 - In accordance with the requirement documents when any crack monitored under the provisions of Para. 1 reaches or exceeds 0.30 inches in length.
Note: The modification may be carried out at any time (i.e. not necessarily at crack detection) and thus exempt the aircraft from the inspections under Para.1.
For Para. 3 - At or prior to exceeding 1,200 hours after modification and thereafter at intervals not exceeding 1,200 hours or 1,200 landings whichever occurs first.
Background: The results of full-scale fatigue testing and the inspection of several high time Citation aircraft have revealed small fatigue cracks in the main spar upper and lower caps at W.S. 37. In service cracks were found in 8 instances in the upper cap and in 1 instance in the lower cap.