Commonwealth legislation

AD/CESSNA 500/15 - Wing Main Spar - Inspection and Modification

In ForceCTH

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Commonwealth

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legislative instrument

Plain English Summary

5/10 complexity

Requires owners/operators of Cessna 500/501 aeroplanes (unit nos. 0001–0520) to inspect and, where necessary, modify the wing main spar upper and lower caps near wing station 37 using specified Cessna service documents and a referenced FAA AD. Inspections are mandatory as detailed in the AD; modification is required when monitored cracks reach 0.30 inches and, after modification, recurring visual inspections are required every 1,200 hours or 1,200 landings (modification may be done earlier to avoid the inspection schedule).

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AD/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

View image in the official source 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.

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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.

Source text

Sourced from the Federal Register of Legislation (legislation.gov.au), CC BY 4.0.