AIRWORTHINESS DIRECTIVE
On the effective date specified below, and for the reasons set out in the background section, the CASA delegate whose signature appears below revokes Airworthiness Directive (AD) AD/SD3-60/36 and issues the following AD under subregulation 39.1 (1) of CASR 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.
Short SD3-60 Series Aeroplanes
AD/SD3-60/36
Amdt 1
MLG Rear Pintle Pin Bush 12/2004
Applicability: Model SD3-60 aircraft.
Requirement: 1. Inspect the main landing gear rear pintle pin assemblies for correctly applied sealant in accordance with Shorts Service Bulletin SD360-32-37 original issue, or later EASA approved revision (refer to Accomplishment Instructions, paragraph 2A of Messier-Dowty Service Bulletin 32-70SD Revision 1).
2. If the sealant is incorrectly applied, perform a magnetic flaw detection inspection of the rear pintle pin fork ends in accordance with Shorts Service Bulletin SD360-32-37 original issue, or later EASA approved revision (refer to Accomplishment Instructions, paragraph 2B of Messier-Dowty Service Bulletin 32-70SD Revision 1).
If pintle pin fork ends are found cracked, before further flight, replace with a serviceable part that has been inspected in accordance with this Directive.
Note: UK CAA AD G-2004-0022 refers.
Compliance: 1. At the next “B” check after 25 November 2004, but no later than 3 months after the effective date of this Directive.
2. At the next “C” check after 25 November 2004, but no later than 12 months after the effective date of this Directive.
This Amendment becomes effective on 25 November 2004.
Background: A report was received of the failure of a main landing gear rear pintle pin fork end on a SD3 aircraft. The failure was attributed to stress corrosion cracking. Absence of a fillet of sealant around the flange of the bronze bush was determined to be cause for the moisture ingress that initiated the corrosion.
Short SD3-60 Series Aeroplanes
AD/SD3-60/36 Amdt 1 (continued)
Amendment 1 is issued in response to a new CAA AD, which was prompted by another incident on a SD3 aircraft where the pintle pin fork end cracked. This Directive requires further inspections to identify damaged pintle pin fork ends.
David Villiers
Delegate of the Civil Aviation Safety Authority 14 October 2004
The above AD is notified in the Commonwealth of Australia Gazette on 3 November 2004.