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.
Overview
The Civil Aviation Safety Authority Amendment Instrument 2004 (F2006B06881) was enacted to address safety concerns arising from incidents involving the main landing gear rear pintle pin fork ends of SD3-60 Series Aeroplanes. This instrument was issued by the Civil Aviation Safety Authority (CASA) under subregulation 39.1 (1) of the Civil Aviation Safety Regulations 1998 (CASR 1998), following reports of failures due to stress corrosion cracking, which were traced to the absence of a fillet of sealant around the flange of the bronze bush. The policy objective of this legislation is to ensure that the identified unsafe condition is rectified through mandatory inspections and, if necessary, the replacement of affected components to maintain the airworthiness of the aircraft. Compliance with this directive must be achieved during the next "B" and "C" checks, within specified timeframes after the directive's effective date.
Scope and Application
The Airworthiness Directive (AD) AD/SD3-60/36 Amdt 1 pertains specifically to Short SD3-60 Series Aeroplanes, mandating particular safety inspections and corrective actions to address the unsafe condition identified in the main landing gear rear pintle pin assemblies. This directive applies to aircraft owners, operators, and maintenance personnel who are responsible for ensuring compliance with airworthiness standards for the specified aircraft model. The AD was issued by the Civil Aviation Safety Authority (CASA) under the Civil Aviation Safety Regulations 1998, reflecting the Commonwealth’s jurisdictional reach. The directive outlines specific inspection and corrective actions to be undertaken by authorised personnel in accordance with detailed service bulletins and instructions, ensuring that any incorrectly applied sealant is corrected and any cracked pintle pin fork ends are replaced. The AD specifies compliance timelines, requiring inspections at the next “B” check no later than three months from the effective date, and at the next “C” check no later than twelve months from the effective date. The AD does not explicitly mention any exclusions or exemptions, implying that all applicable aircraft must comply with the outlined requirements.
Key Provisions
The Airworthiness Directive (AD) AD/SD3-60/36 Amendment 1 specifies requirements for the inspection and maintenance of SD3-60 series aircraft to address a safety issue identified with the main landing gear rear pintle pin assemblies. Section 1 of the AD mandates that inspections be carried out to ensure that the sealant around the flange of the bronze bush is correctly applied. If the sealant is found to be incorrectly applied, further inspections must be conducted using magnetic flaw detection to identify any cracks in the rear pintle pin fork ends (Section 2). Any cracked fork ends identified must be replaced with a serviceable part that has been inspected in accordance with the directive before the aircraft can be flown again.
Operators of SD3-60 series aircraft must comply with the AD by conducting the required inspections and taking necessary actions. Specifically, inspections must be carried out at the next scheduled “B” check following the effective date of the AD (Section 1). Additionally, further inspections are required at the next “C” check within 12 months of the effective date (Section 2). Failure to adhere to these inspection and maintenance requirements can result in the aircraft being deemed unairworthy, which could lead to operational restrictions or grounding.
Breach of the AD may result in regulatory actions against the aircraft operator. Under the Civil Aviation Safety Regulations 1998, non-compliance with an Airworthiness Directive can lead to civil penalties, including fines up to the maximum statutory limits. Additionally, continued operation of an aircraft that does not comply with an AD may result in criminal charges, with penalties including fines and imprisonment, depending on the severity of the non-compliance and its impact on aviation safety.