SCHEDULE OF AIRWORTHINESS DIRECTIVES
CESSNA 550 Citation II · Airworthiness Directives
Overview
This document is an Airworthiness Directive (AD) issued by the Civil Aviation Safety Authority of Australia, specifically addressing the Cessna 550 (Citation II) series aeroplanes. It outlines mandatory inspection and modification requirements for the wing main spar of affected aircraft. The directive is crucial for maintaining the airworthiness of the aircraft and ensuring safety in operations. It includes specific compliance timelines and procedures that must be followed by operators and maintenance personnel to mitigate risks associated with fatigue cracks in the wing structure. The document serves as a regulatory requirement for the continued safe operation of the Cessna 550 series.
- Inspect the wing spar upper and lower cap at wing station 37 as per Cessna SL No. 550-57-1.
- Modify the wing spar in accordance with Cessna SB No. 550-57-3 Rev. 1.
- Conduct visual inspections for cracks at or prior to 1200 hours after modification, and thereafter at intervals not exceeding 1200 hours or 1200 landings.
- The modification can be performed at any time, exempting the aircraft from certain inspections.
- Fatigue cracks were found in 8 instances in the upper cap and in 1 instance in the lower cap during inspections.
Document
Source
Originally published by services.casa.gov.au. Sprinkle hosts a reference copy with an added summary, specifications and searchable full text.
Document details
- Type
- Airworthiness Directives
- Year
- 1982
- Pages
- 1
- File size
- 11 KB
- Publisher
- services.casa.gov.au
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In this document
Applicability
This Airworthiness Directive applies to the Cessna 550 series aeroplanes with specific serial numbers referenced in the associated Service Letter (SL) No. 550-57-1.
Requirement
The directive mandates a series of inspections and modifications to the wing main spar. This includes inspecting the upper and lower caps of the wing spar at wing station 37, following the guidelines set forth in Cessna SL No. 550-57-1 Rev. 1 and FAA AD 79-12-06. Additionally, modifications must be performed in accordance with Cessna SB No. 550-57-3 Rev. 1.
Compliance
Operators must comply with the inspection requirements as detailed in the directive. Inspections for cracks must be conducted at intervals not exceeding 1200 hours or 1200 landings, whichever comes first. Modifications can be performed at any time, which may exempt the aircraft from certain inspections.
Background
The directive is based on findings from fatigue testing and inspections of high-time Citation aircraft, which revealed fatigue cracks in the wing main spar. The document highlights the importance of these inspections to prevent potential structural failures.
Safety notes
- Failure to comply with the inspection and modification requirements may lead to structural failure of the wing spar.
Full document text
COMMONWEALTH OF AUSTRALIA (Civil Aviation Regulations 1998), PART 39 - 105 CIVIL AVIATION SAFETY AUTHORITY SCHEDULE OF AIRWORTHINESS DIRECTIVES Cessna 550 (Citation II) Series Aeroplanes AD/CESSNA 550/1 Wing Main Spar - Inspection and Modification 2/82 Applicability: Model 550 series aeroplanes with S/Nos. as referenced in SL No. 550-57-1. Requirement: 1. Inspect the wing spar upper and lower cap in the area of wing station 37 in accordance with Cessna SL No. 550-57-1 Rev. 1 dated 1 May 1979. FAA AD 79-12-06 also refers. 2. Inspect and modify in accordance with Cessna SB No. 550-57-3 Rev. 1 dated 28 March 1980. 3. Visually inspect for further cracks the wing main spar upper and lower caps of aircraft modified in accordance with SB No. 550-57-3 Rev. 1 in the area of the WS 37 modification. Compliance: For Para. 1 - As detailed in the requirement document. For Para. 2 - In accordance with the requirement document 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 1200 hours after modification and thereafter at intervals not exceeding 1200 hours or 1200 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 WS 37. In service cracks were found in 8 instances in the upper cap and in 1 instance in the lower cap.