AIRWORTHINESS DIRECTIVE
For the reasons set out in the background section, the CASA delegate whose signature appears below revokes Airworthiness Directive (AD) AD/CL-600/32 Amdt 1 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.
Bombardier (Canadair) CL-600 (Challenger) Series Aeroplanes
AD/CL-600/32
Amdt 2
Underfloor Pressure Bulkhead at FS409.00 7/2002
Applicability: | Models | Serial Numbers |
| CL-600-1A11 (CL-600) CL-600-2A12 (CL-601) | 1004 through 1085 3001 through 3066 |
| CL-600-2B16 (CL-601-3A/-3R) CL-600-2B16 (CL-604) | 5001 through 5194 5301 through 5352 |
Requirement: Perform a detailed visual inspection of both the fuselage frame FS409 bulkhead web (P/N 600-32014-71/-95/-105/-137, as applicable) from the corner radius at WL 49.00, LBL 6.00 and RBL 6.00, and the angles (P/Ns 600-32014-13 and -15, or -113 and - 115, as applicable) between LBL 9.0 and RBL 9.0. The inspection is to be carried out in accordance with Part 2, Accomplishment Instructions, of Bombardier Service Bulletins 600-0679, 601-0501, or 604-53-007, as applicable.
Note: Transport Canada AD CF-1997-16R2 refers.
Compliance: 1. Unless the initial inspection is already accomplished:
- CL-600-1A11 aircraft.
(i) For aircraft with 1900 or more flight cycles, initially within 100 flight cycles after 5 November 1997; and,
(ii) For aircraft with less than 1900 flight cycles, not later than 2000 flight cycles since new.
b. CL-600-2A12 and CL-600-2B16 aircraft.
(i) For aircraft with 1100 or more flight cycles, initially within 100 flight cycles after 5 November 1997; and.
(ii) For aircraft with less than 1100 flight cycles, not later than 1200 flight cycles since new.
Bombardier (Canadair) CL-600 (Challenger) Series Aeroplanes
AD/CL-600/32 Amdt 2 (Continued)
Aircraft that are visually determined to be crack free are to be re-inspected at intervals not to exceed 600 flight cycles; until modified in accordance with Bombardier Service Bulletins 600-0680, 601-0503, or 604-53-006, as applicable.
2. Aircraft that are visually determined to have cracks that do not extend up to the angles as specified in the Requirement, may only be returned to service under the following conditions:
- No more than one crack exists at each corner; and,
b. Angles on the aft side of the web are visually confirmed to be crack free; and,
c. No crack extends under the angles; and,
d. Aircraft shall be re- inspected at intervals not exceeding 100 flight cycles; and,
e. The cracked bulkhead is to be repaired before the aircraft accumulates 600 flight cycles or within 12 months, whichever occurs first, after the date of initial detection of the crack.
The compliance times remain unchanged by this issue. This amendment becomes effective on 11 July 2002.
Background: A check of 105 Challenger aircraft has revealed 13 aircraft with fatigue cracks in the pressure bulkhead frame at the forward end of the wing box cutout.
Bombardier (Canadair) CL-600 (Challenger) Series Aeroplanes
AD/CL-600/32 Amdt 2 (Continued)
Amendment 1 deleted a specific repair date.
Amendment 2 is issued in response to a revision of the related Transport Canada AD, which introduces a modification that provides terminating action for the repeat inspection requirements for those aircraft that have never developed cracks.
Amendment 1 of this Airworthiness Directive became effective on 3 December 1998. The original issue of this Airworthiness Directive became effective on
5 November 1997.
David Alan Villiers
Delegate of the Civil Aviation Safety Authority 30 May 2002
The above AD is notified in the Commonwealth of Australia Gazette on 19 June 2002.
Overview
The Civil Aviation Safety Authority (CASA) issued the Airworthiness Directive (AD) AD/CL-600/32 Amdt 2 for Bombardier (Canadair) CL-600 (Challenger) Series Aeroplanes on 11 July 2002. This directive responds to the discovery of fatigue cracks in the pressure bulkhead frame at the forward end of the wing box cutout in 13 out of 105 Challenger aircraft. The AD was enacted under subregulation 39.1 (1) of the Civil Aviation Regulations 1998 (CAR 1998) to address safety concerns and ensure the airworthiness of affected aircraft models. The policy objective is to mandate detailed visual inspections and establish specific repair timelines to prevent the propagation of cracks that could compromise the structural integrity of the aircraft. CASA’s delegate, David Alan Villiers, issued this amendment to align with a revised Transport Canada AD, which introduced modifications to terminate repeat inspection requirements for aircraft that have not developed cracks. This amendment ensures compliance with international safety standards and enhances the safety of aircraft operations in Australia.
Scope and Application
The Airworthiness Directive (AD) AD/CL-600/32 Amdt 2 issued under the Civil Aviation Regulations 1998 applies specifically to Bombardier (Canadair) CL-600 (Challenger) Series aeroplanes, including models CL-600-1A11, CL-600-2A12, and CL-600-2B16, within the specified serial number ranges. The directive mandates detailed visual inspections of the fuselage frame FS409 bulkhead web and the angles between LBL 9.0 and RBL 9.0, in accordance with Bombardier Service Bulletins 600-0679, 601-0501, or 604-53-007, as applicable. The directive outlines specific inspection timelines based on the number of flight cycles the aircraft has accumulated since new or since the directive's issuance on 5 November 1997. Aircraft found to be crack-free must undergo re-inspection at intervals not exceeding 600 flight cycles until modified according to the specified service bulletins. Aircraft with detected cracks must meet specific conditions before returning to service, including limitations on the number of cracks, the condition of the angles, and a requirement for repair within 600 flight cycles or 12 months from the initial detection of the crack, whichever comes first. This AD is applicable across the Commonwealth of Australia and is effective as of 11 July 2002.
Key Provisions
The main operative sections of this Airworthiness Directive (AD) require a detailed visual inspection of certain parts of the Challenger aircraft's fuselage. Specifically, the AD mandates an inspection of the fuselage frame FS409 bulkhead web and the angles between LBL 9.0 and RBL 9.0 (sections 1(a) and 1(b)). This inspection must be carried out in accordance with the instructions in Bombardier Service Bulletins 600-0679, 601-0501, or 604-53-007, as applicable (section 1(a)). The AD applies to specific models and serial numbers of the Challenger aircraft, including the CL-600-1A11, CL-600-2A12, and CL-600-2B16 (section 2).
The AD imposes obligations on aircraft operators and maintenance personnel to conduct the required inspections within specified flight cycle intervals. For aircraft with 1900 or more flight cycles, the initial inspection must be completed within 100 flight cycles after 5 November 1997 (section 3(a)(i)). For aircraft with fewer than 1900 flight cycles, the inspection must occur not later than 2000 flight cycles since new (section 3(a)(ii)). Similarly, for aircraft with 1100 or more flight cycles, the initial inspection must be completed within 100 flight cycles after 5 November 1997 (section 3(b)(i)). For aircraft with fewer than 1100 flight cycles, the inspection must occur not later than 1200 flight cycles since new (section 3(b)(ii)). If an aircraft is visually determined to be crack-free, it must be re-inspected at intervals not exceeding 600 flight cycles (section 3(a)). Aircraft found to have cracks must meet specific conditions before being returned to service, including restrictions on the number of cracks, confirmation of crack-free angles, and a repair deadline (section 3(b)).
Failure to comply with the requirements of this AD can result in severe consequences. The AD does not explicitly mention specific penalties, but non-compliance with airworthiness directives generally can lead to enforcement actions under the Civil Aviation Act 1988 and the Civil Aviation Regulations 1988. These actions can include fines, imprisonment, or both. The specific penalties can vary, but they are designed to ensure that aircraft remain airworthy and safe for operation.