COMMONWEALTH OF AUSTRALIA (Civil Aviation Regulations 1998), PART 39 - 105 CIVIL AVIATION SAFETY AUTHORITY
SCHEDULE OF AIRWORTHINESS DIRECTIVES
Bombardier (Canadair) CL-600 (Challenger) Series Aeroplanes
AIRWORTHINESS DIRECTIVE
For the reasons set out in the background section, the CASA delegate whose signature appears below revokes Airworthiness Directive (AD) AD/CL-600/35 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.
AD/CL-600/35
Amdt 1
Main Landing Gear Main Fitting 3/2001
Applicability: Model CL-600-2B19 “Regional Jet” aircraft, serial numbers 7003 through 7999.
Requirement: 1. Perform an eddy current inspection of the main landing gear main fittings in accordance with Part B of the Accomplishment Instructions of Bombardier Alert Service Bulletin (ASB) A601R-32-079. Replace any cracked main landing gear main fitting before further flight.
2. Service both the left and right main landing gear shock struts in accordance with the applicable Part C or D of the Accomplishment Instructions of Bombardier ASB A601R-32-079, Revision C.
3. Inspect both the left and right main landing gear shock struts for nitrogen pressure, visible chrome dimension and oil leakage in accordance with Part E of the Accomplishment Instructions of Bombardier ASB A610R-32-079, Revision C.
If the shock strut nitrogen pressure and visible chrome dimensions are outside the limits and/or oil leakage is found, before further flight, service the affected main landing gear shock strut in accordance with the applicable Part C or D of the Accomplishment Instructions of ASB A601R-32-079 Revision C.
Note: Transport Canada AD CF-1999-32R1 refers.
Compliance: 1. Initially upon accumulating a total of 1,500 flight cycles since new, or within 150 flight cycles after 22 March 2001, whichever occurs later. Thereafter at intervals not to exceed 500 flight cycles.
The eddy current inspection interval of 500 flight cycles may be increased to 1,000 flight cycles provided that:
- following the shock strut servicing required by Requirement 2 of this Directive, the next four consecutive shock strut inspections accomplished in accordance with Requirement 3 of this Directive yield inspection parameters within the limits; and,
COMMONWEALTH OF AUSTRALIA (Civil Aviation Regulations 1998), PART 39 - 105 CIVIL AVIATION SAFETY AUTHORITY
SCHEDULE OF AIRWORTHINESS DIRECTIVES
b. no cracks are found on the affected main landing gear main fittings during the five consecutive eddy current inspections accomplished in accordance with Requirement 1 of this Directive and concurrent with the shock strut inspections of paragraph (a) above.
2. Upon accumulating a total of 1,500 flight cycles since new, or within 500 flight cycles after 22 March 2001, whichever occurs later.
3. Initially within the next 500 flight cycles after completing the servicing specified in Requirement 2 of this Directive, and thereafter at intervals not to exceed 500 flight cycles.
This amendment becomes effective on 22 March 2001.
Background: There have been three reported cases of premature failure of the main landing gear main fitting. The reports indicated that a circumferential crack was found on the fitting at the radius between the fitting cylinder area and the upper attachment lug for the shock strut.
Amendment 1 is issued is response to a revision of the related Transport Canada AD which adds servicing of the main landing gear shock struts, and repetitive inspection of the shock strut for nitrogen pressure and visible chrome dimensions. Further investigation revealed that, under certain conditions, a mis-serviced shock strut could lead to premature failure of the fitting. This amendment also allows the eddy current inspection interval to be increased under certain conditions.
The original issue of this Airworthiness Directive became effective on 24 February 2000.
David Alan Villiers
Delegate of the Civil Aviation Safety Authority 9 February 2001
The above AD is notified in the Commonwealth of Australia Gazette on 21 February 2001.
Overview
The Civil Aviation Regulations 1998 (CAR 1998), enacted by the Parliament of Australia, serve as a comprehensive regulatory framework governing civil aviation safety within the country. Among its provisions, Part 39 - 105, specifically the Civil Aviation Safety Authority (CASA) Schedule of Airworthiness Directives, addresses critical safety mandates for various aircraft types. One such directive concerns Bombardier (Canadair) CL-600 (Challenger) Series Aeroplanes, targeting the identified problem of premature failure of the main landing gear main fittings. This directive, issued under subregulation 39.1 (1) of CAR 1998, mandates specific actions to rectify unsafe conditions, ensuring compliance with stringent safety standards. The policy objective behind this directive is to mitigate the risk of aircraft accidents due to structural failures by enforcing regular inspections and necessary repairs on specified aircraft components.
Scope and Application
The Civil Aviation Regulations 1998, specifically under PART 39 - 105, govern the safety standards for civil aviation in Australia, with the Civil Aviation Safety Authority (CASA) as the regulatory body. This particular Airworthiness Directive (AD) pertains to Bombardier (Canadair) CL-600 (Challenger) Series Aeroplanes, more specifically model CL-600-2B19 “Regional Jet” aircraft with serial numbers 7003 through 7999. The AD mandates specific maintenance actions for the main landing gear main fittings and the associated shock struts to ensure airworthiness. The directive requires the performance of an eddy current inspection of the main landing gear main fittings, the servicing of the main landing gear shock struts, and the inspection of the shock struts for nitrogen pressure, visible chrome dimension, and oil leakage. These requirements must be followed at specified intervals based on flight cycles. The AD extends to aircraft within the specified serial number range and must be adhered to by the aircraft operators and maintenance personnel. There are no exclusions mentioned in the text, and the AD becomes effective as of 22 March 2001. The scope of the AD is further defined by its compliance sections, which set out the specific timing for inspections and servicing based on flight cycles.
Key Provisions
The Civil Aviation Regulations 1998 (CAR 1998) Part 39, specifically Airworthiness Directive (AD) AD/CL-600/35 Amendment 1, pertains to Bombardier (Canadair) CL-600 (Challenger) Series aeroplanes, particularly the CL-600-2B19 “Regional Jet” aircraft with serial numbers 7003 through 7999. The AD outlines mandatory actions and inspections to ensure the continued airworthiness of these aircraft (AD/CL-600/35). The applicability section (Applicability) specifies the aircraft models and serial numbers that the directive applies to. The requirement section (Requirement) details the specific actions and inspections that must be performed. These include an eddy current inspection of the main landing gear main fittings (Requirement 1), servicing of both the left and right main landing gear shock struts (Requirement 2), and inspecting both the left and right main landing gear shock struts for nitrogen pressure, visible chrome dimensions, and oil leakage (Requirement 3). The compliance section (Compliance) provides the intervals at which these inspections and servicing must occur.
The AD imposes several obligations on the parties or entities it governs. Aircraft operators and maintenance providers must adhere to the specified inspection and servicing intervals, ensuring that the inspections and servicing are performed according to the instructions set out in the Accomplishment Instructions of Bombardier Alert Service Bulletins (ASB). Specifically, operators must conduct an eddy current inspection of the main landing gear main fittings at the specified intervals and replace any cracked fittings before further flight. Additionally, operators must service the left and right main landing gear shock struts and inspect them for nitrogen pressure, visible chrome dimensions, and oil leakage. If any parameters are found to be outside the specified limits, the affected shock strut must be serviced before further flight.
Failure to comply with the provisions of this AD may result in various civil and criminal consequences. Civil Aviation Safety Authority (CASA) can take enforcement action against non-compliance, which may include fines, suspension or revocation of certificates of airworthiness, or other regulatory actions. The maximum penalties for non-compliance with CAR 1998 are set out in section 48 of the Civil Aviation Act 1988, which includes fines of up to $105,000 for individuals and $525,000 for bodies corporate, as well as potential imprisonment for serious offences. Additionally, non-compliance can lead to the grounding of affected aircraft, which can have significant operational and financial implications for operators.