SCHEDULE OF AIRWORTHINESS DIRECTIVES
Cessna Citation 500 · Airworthiness Directives
Overview
This document is an Airworthiness Directive (AD) issued by the Civil Aviation Safety Authority of Australia, specifically addressing the Cessna 500 (Citation) series aeroplanes. It outlines mandatory inspection and modification requirements for the wing main spar of all models 500 and 501 with unit numbers ranging from 0001 to 0520. The directive emphasizes the importance of inspecting the wing spar for fatigue cracks and provides detailed compliance instructions to ensure the safety and airworthiness of the aircraft. The document is intended for aircraft operators and maintenance personnel responsible for ensuring compliance with airworthiness standards.
- Inspect the wing spar upper and lower cap at wing section 37 as per Cessna SL No. 57-2 Rev. 3.
- Follow specific service bulletins for modifications based on aircraft unit numbers.
- Visual inspections for cracks must occur at or before 1,200 hours after modification.
- The modification can be done at any time, exempting the aircraft from certain inspections.
- Fatigue cracks were found in 8 upper cap instances and 1 lower cap instance 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 ·
- 1981
- Pages ·
- 1
- File size ·
- 11 KB
- Publisher ·
- services.casa.gov.au
What is the SCHEDULE OF AIRWORTHINESS DIRECTIVES?
The SCHEDULE OF AIRWORTHINESS DIRECTIVES is a airworthiness directives for the Cessna Citation 500, dated 1981.
How many pages is the SCHEDULE OF AIRWORTHINESS DIRECTIVES?
The copy of the SCHEDULE OF AIRWORTHINESS DIRECTIVES on file runs 1 pages.
Where does the SCHEDULE OF AIRWORTHINESS DIRECTIVES come from?
This copy of the SCHEDULE OF AIRWORTHINESS DIRECTIVES was originally published by services.casa.gov.au and is hosted on Sprinkle as a free, searchable reference copy.
What year was the SCHEDULE OF AIRWORTHINESS DIRECTIVES published?
The SCHEDULE OF AIRWORTHINESS DIRECTIVES — the Cessna Citation 500 airworthiness directives on file — is dated 1981.
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- Pilot's Operating Handbook / AFM
- Checklist
- Maintenance Manual
- Parts Catalog (IPC)
- Systems & Wiring
- Service Bulletins on file
- Type Certificate (TCDS)
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In this document
Applicability
The directive applies to all Cessna 500 and 501 models with unit numbers from 0001 to 0520.
Requirement
Operators must inspect the wing spar's upper and lower caps at wing section 37 as per Cessna SL No. 57-2 Rev. 3 dated 15 May 1980 and FAA AD 79-12-06. Modifications must follow Cessna SB No. 57-10 Rev. 1 for unit Nos. 0001 to 0349 and SB No. 57-11 Rev. 1 for unit Nos. 0350 to 0520. Additionally, a visual inspection for cracks is required for modified aircraft.
Compliance
Inspections must be conducted as specified in the requirement document. Modifications can be performed at any time, exempting the aircraft from inspections if no cracks are detected. For visual inspections, they must occur at or before 1,200 hours post-modification and at intervals not exceeding 1,200 hours or 1,200 landings.
Background
The directive is based on findings from fatigue testing and inspections revealing small fatigue cracks in the main spar caps at W.S. 37. Instances of cracks were documented in both the upper and lower caps.
Safety notes
- Mandatory inspections are critical for maintaining airworthiness.
- Failure to comply with the directive may lead to safety risks.
Full document text
COMMONWEALTH OF AUSTRALIA (Civil Aviation Regulations 1998), PART 39 - 105 CIVIL AVIATION SAFETY AUTHORITY SCHEDULE OF AIRWORTHINESS DIRECTIVES Cessna 500 (Citation) Series Aeroplanes AD/CESSNA 500/15 Wing Main Spar - Inspection and Modification 4/81 Applicability: All models 500 and 501 with unit numbers 0001 to 0520. 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.