COMMONWEALTH OF AUSTRALIA (Civil Aviation Regulations 1998), PART 39 - 105 CIVIL AVIATION SAFETY AUTHORITY
SCHEDULE OF AIRWORTHINESS DIRECTIVES
Fairchild (Swearingen) SA226 and SA227 Series Aeroplanes
AD/SWSA226/84 Cargo Door Lower Belt Frames 7/98
Applicability: Models Serial Numbers
SA226-AT AT001 through AT074
SA226-TC TC201 through TC419
SA227-AC AC406, AC415, AC416, AC420 through AC456, AC458
through AC469, and AC471 through AC478
SA227-AT AT423 through AT469
Requirement: 1. Inspect the cargo door lower belt frames at the cargo latch receptacles for cracks in accordance with Part A of the Accomplishment Instructions section in Fairchild Aircraft SA226 Series Service Bulletin 226-53-007, issued 7 May 1981, revised 17 February 1992; or SA227 Series Service Bulletin 227-53-003, issued 29 January 1986, revised 13 February 1986; as applicable.
2. If cracks are found, accomplish the following:
- For belt frames located at Fuselage Station (FS) 438.060 and FS 491.060, repair the belt frame by installing angle part number (P/N) 27-22206-009 or 27-22206- 010, in accordance with the Fairchild Aircraft SA226 / 227 Structural Repair Manual (SRM), Section 53-90-20, initial issue 1 March 1983, Revision 24, dated 27 August 1997; or Fairchild Aircraft Approved Repair Procedure (ARP) 53-30- 9701, dated 28 July 1997. The reinforcement doublers (P/N 27-22206-007 and - 008) are also needed together with this repair.
- For belt frames located at FS 454.501, FS 455.726, FS 473.392, and FS 474.657, replace all four belt frames with new design frames, P/N 27-22207-008, 27-22208- 005, and 27-22207-007, respectively, in accordance with the SA226 / 227 SRM, Section 53-90-20; or, ARP 53-30-9701. No reinforcement doublers are needed for these four new design belt frames.
3. If no cracks are found in all six belt frames during the inspection, install reinforcement doublers in all six belt frames in accordance with Part B of the Accomplishment Instructions of SB 226-53-007 or SB 227-53-003, as applicable.
Note: FAA AD 98-06-25 Amdt 39-10403 refers.
Compliance: 1. Within 500 hours time in service after 18 June 1998.
2. Before further flight.
3. Within 500 hours time in service after accomplishment of the Requirement 1 inspection.
This Airworthiness Directive becomes effective on 18 June 1998.
COMMONWEALTH OF AUSTRALIA (Civil Aviation Regulations 1998), PART 39 - 105 CIVIL AVIATION SAFETY AUTHORITY
SCHEDULE OF AIRWORTHINESS DIRECTIVES
Background: The FAA requires certain actions as a result of a decompression incident during flight caused by fatigue at the bottom of the cargo door on a Model SA226-TC. Failure of the cargo door in flight could cause decompression injury to passengers and substantial structural damage to the aircraft.
Overview
The Civil Aviation Regulations 1998, enacted by the Australian Parliament, serve to regulate civil aviation safety across the nation. One such regulation is the Airworthiness Directive (AD) for the Fairchild (Swearingen) SA226 and SA227 series aeroplanes, specifically concerning the cargo door lower belt frames, issued in 1998. This AD was introduced in response to a critical safety issue identified by the Federal Aviation Administration (FAA) regarding fatigue-related failures at the cargo door bottom on a Model SA226-TC, which could lead to severe in-flight decompression incidents with potential passenger injury and significant aircraft damage. The policy objective of this AD is to mandate inspections and necessary repairs or replacements to ensure the structural integrity of the cargo door lower belt frames, thereby enhancing overall flight safety. Compliance with this directive is mandatory within specific time frames following the issuance of the AD.
Scope and Application
The Civil Aviation Safety Authority Schedule of Airworthiness Directives under the Civil Aviation Regulations 1998 specifically applies to certain models of Fairchild (Swearingen) SA226 and SA227 series aeroplanes, namely those with specified serial numbers. The directive mandates the inspection and necessary repair of cargo door lower belt frames to ensure airworthiness and safety, particularly in light of a reported decompression incident. The requirement is to inspect these belt frames for cracks and, if cracks are found, either repair or replace the affected belt frames according to detailed instructions provided in relevant service bulletins and structural repair manuals. If no cracks are detected, reinforcement doublers must be installed. The directive applies across the Commonwealth of Australia, reflecting the national scope of civil aviation safety regulation. This directive does not specify any exclusions or exemptions but requires compliance within certain timeframes to ensure safety and operational readiness. Subordinate instruments may further detail the compliance process and enforcement mechanisms.
Key Provisions
The Civil Aviation Regulations 1998, under Part 39 - 105, mandate specific actions regarding the inspection and repair of the cargo door lower belt frames on Fairchild (Swearingen) SA226 and SA227 Series aeroplanes. According to the Airworthiness Directive (AD) SA226/84, the inspections and repairs are required for specific models and serial numbers of these aircraft. The AD outlines the requirement to inspect the cargo door lower belt frames for cracks at designated fuselage stations (section 1). If cracks are found, the AD specifies the necessary repairs or replacements (section 2). In the absence of cracks, reinforcement doublers must be installed in all six belt frames (section 3).
The obligations imposed by this legislation require the aircraft operators or owners to conduct the inspections and make the necessary repairs or replacements within specified timeframes. Compliance with the AD is mandatory and must be achieved within 500 hours of time in service after 18 June 1998 and before further flight. The AD also stipulates that if an inspection is performed under Requirement 1, the subsequent repairs or installations must be completed within 500 hours of time in service after the inspection.
Failure to comply with the AD can result in serious consequences. The legislation does not explicitly state the penalties for non-compliance but does imply that the aircraft will not be considered airworthy if the requirements are not met. This non-compliance could lead to the grounding of the aircraft, preventing it from operating until the required actions are taken. Given the potential safety implications of non-compliance, such as the risk of in-flight decompression, the consequences of breaching these regulations can be severe, both in terms of safety and legal repercussions.