AIRWORTHINESS DIRECTIVE
For the reasons set out in the background section, the CASA delegate whose signature appears below revokes Airworthiness Directive (AD) AD/CESSNA 210/66 Amdt 2 and issues the following AD under subregulation 39.1 (1) of CAR 1998. The AD requires that the action set out in the requirement section (being action that the delegate considers necessary to correct the unsafe condition) be taken in relation to the aircraft or aeronautical product mentioned in the applicability section: (a) in the circumstances mentioned in the requirement section; and (b) in accordance with the instructions set out in the requirement section; and (c) at the time mentioned in the compliance section.
Cessna 210 Series Aeroplanes
AD/CESSNA 210/66
Amdt 3
Forward Door Post Bulkhead 6/2002
Applicability: All models with wing struts that do not have Cessna Service Kit part no. SK210-156 incorporated as per Cessna SEB95-19.
Requirement: 1. Visually inspect the wing strut lower attachment structure to determine the type of strut attachment used. Aircraft with the earlier embedded type strut attachment are not subject to any further action. Aircraft with strut attachment fittings of the type with the protruding lug, similar to that shown in the diagram below, must comply with Requirement paragraphs 2 and 3.
Note: This inspection may be easily accomplished by removing the strut attachment fairing at the lower end of one of the wing struts. Structure requiring further inspection is characterised by the strut attachment lug protruding beyond the fuselage skin.
2. Visually inspect for cracks at the inside edge of the left hand and right hand bend relief notches of the forward door post bulkhead.
3. Visually inspect for loose or working fasteners securing the lower strut end pick- up fitting to the forward door post bulkhead. The inspection areas and typical crack location are shown in the diagram below.
Note 1: Inspection in accordance with Requirement 2 will initially require removal of certain floor panels. Incorporation of inspection holes in accordance with an approved modification will allow further inspection of the relief notch without requiring repeated removal of the floor panels.
Note 2: Inspection in accordance with Requirement 3 may be accomplished from outside the aircraft via the hole exposed by removing the lower wing strut fairing.
Compliance: Inspect before exceeding 2000 hours aircraft time in service, or before 100 hours time in service after 20 July 1995, or before 500 hours time in service since last inspected in accordance with this Directive, whichever occurs last. Thereafter inspect affected aircraft in accordance with Requirements 2 and 3, at intervals not to exceed 500 hours time in service.
Note: Repaired or modified structure must continue to be inspected unless a variation to the requirements of this AD has been approved.
This Amendment becomes effective on 13 June 2002.
Background: Numerous reports have been received of cracking in this area on Cessna models 206 and 182. The structure on the strutted 210 model is similar. The bend relief notch in the bulkhead serves as a stress concentration notch, causing fatigue cracks to promulgate across the bulkhead web. The strut attachment area forms part of the wing’s primary load path, and loss of strength in this area could be catastrophic.
Although the majority of this area is covered by the strut attach fitting and a bulkhead reinforcement doubler, the inside edge of the bulkhead, where the cracks have been initiating, is visible without removing the lower strut attachment fitting.
Amendment 1 reduced the initial threshold time for inspection as several model 206 and 182 aircraft have been found cracked at less than 4000 hours. Cessna Single Engine Service Bulletin SEB 93-5, for the model 206, provides background information.
Amendment 3 of this Airworthiness Directive is issued to correct a typographical error in the effective date of Amendment 2 and the effective date quoted for the original issue. Compliance with Amendment 2 constitutes compliance with this Amendment and no further action is required.
Amendment 2 of this Airworthiness Directive was issued to allow the installation if the Cessna Service kit P/N Sk210-156 as terminating action for the repetitive inspection requirement.
Amendment 2 of this Airworthiness Directive became effective on 24 January 2002. Amendment 1 of this Airworthiness Directive became effective on 20 July 1995.
The original issue of this Airworthiness Directive became effective on 25 April 1995.
David Alan Villiers
Delegate of the Civil Aviation Safety Authority 15 April 2002
The above AD is notified in the Commonwealth of Australia Gazette on 22 May 2002.