COMMONWEALTH OF AUSTRALIA (Civil Aviation Regulations 1998), PART 39 - 105 CIVIL AVIATION SAFETY AUTHORITY
SCHEDULE OF AIRWORTHINESS DIRECTIVES
Eurocopter AS 332 (Super Puma) Series Helicopters
AIRWORTHINESS DIRECTIVE
For the reasons set out in the background section, the CASA delegate whose signature appears below revokes Airworthiness Directive (AD) AD/S-PUMA/39 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/S-PUMA/39
Amdt 1
Pilot and Co-Pilot Cockpit Pedal Unit 13/2001
DM
Applicability: Model AS 332 C, C1, L, L1, and L2 helicopters equipped with pedal adjustment lever part number 332A27-2344-20 of the pilot’s and co-pilot’s cockpit pedal unit assemblies, and without Modification 0726179 incorporated (ASB 67.00.20).
Requirement: 1. Action in accordance with Eurocopter AS 332 Alert Service Bulletin 67.00.19.
2. Modify in accordance with Eurocopter AS 332 Alert Service Bulletin 67.00.20.
Note: DGAC AD 2000-486-077(A) R1 and AD 2000-487-017(A) R1 refer.
Compliance: 1. As specified in the Requirement document, with a revised effective date of 14 November 2001. In some cases, the requirement document requires a dye penetrant inspection of the pedal adjustment lever within 50 flight hours after the effective date. It also requires in all cases repeat inspections, at intervals not to exceed 1,500 flight hours, until compliance with Requirement 2.
2. Before 1 June 2002.
This amendment becomes effective on 14 November 2001.
Background: The DGAC received reports of several cases of failure of the adjustment lever of the pedal unit assemblies, which might lead, on the ground, to temporary loss of access to the brake pedals during aircraft taxiing, or in flight, to difficulties in yaw control of the aircraft.
Amendment 1 is issued in response to revisions of the related DGAC Directives, which introduce new alert service bulletins that cancel the borescope inspection method, introduce dye penetrant inspections, and require incorporation of a terminating modification.
COMMONWEALTH OF AUSTRALIA (Civil Aviation Regulations 1998), PART 39 - 105 CIVIL AVIATION SAFETY AUTHORITY
SCHEDULE OF AIRWORTHINESS DIRECTIVES
The original issue of this Airworthiness Directive became effective on 10 January 2001.
David Alan Villiers
Delegate of the Civil Aviation Safety Authority 7 November 2001
The above AD is notified in the Commonwealth of Australia Gazette on 14 November 2001.
Overview
The Commonwealth of Australia's Civil Aviation Regulations 1998, specifically within Part 39 - 105, addresses the safety and airworthiness of aircraft through the Civil Aviation Safety Authority (CASA). Enacted by the Parliament of Australia, these regulations are designed to ensure that civil aviation operations within the country adhere to safety standards that protect passengers, crew, and the public. One of the critical tools in achieving this goal is the issuance of Airworthiness Directives (ADs), which are legally enforceable safety measures directed at specific aircraft or aeronautical products. These directives respond to identified safety issues or conditions that might compromise the airworthiness of an aircraft. For instance, AD/S-PUMA/39, concerning Eurocopter AS 332 (Super Puma) Series Helicopters, was introduced to address safety concerns related to the pedal adjustment lever of the cockpit pedal unit assemblies, specifically the risk of failure leading to difficulties in yaw control. The policy objective behind these regulations is to maintain and enhance the safety of civil aviation by promptly addressing and rectifying any identified unsafe conditions through regulatory action.
Scope and Application
The Civil Aviation Regulations 1998, specifically Part 39 - 105, under the Civil Aviation Safety Authority Schedule of Airworthiness Directives, pertains to Eurocopter AS 332 (Super Puma) Series Helicopters. The legislation applies to AS 332 C, C1, L, L1, and L2 helicopters equipped with pedal adjustment lever part number 332A27-2344-20 of the pilot’s and co-pilot’s cockpit pedal unit assemblies, and those without Modification 0726179 incorporated. The directive is issued by a CASA delegate, with the scope extending to the Commonwealth of Australia. The directive mandates specific actions to address safety concerns related to the cockpit pedal units, including modifications as per Eurocopter Alert Service Bulletins 67.00.19 and 67.00.20, to prevent potential operational hazards such as loss of access to brake pedals on the ground or difficulties in yaw control in flight. The requirement includes a revised effective date and necessitates a dye penetrant inspection within 50 flight hours after the directive’s effective date, followed by repeat inspections at intervals not exceeding 1,500 flight hours until compliance is achieved. Compliance must be ensured by 1 June 2002. This directive is applicable to all relevant helicopters within the Commonwealth of Australia, and it supersedes earlier directives, as notified in the Commonwealth of Australia Gazette.
Key Provisions
This legislative instrument, part of the Civil Aviation Regulations 1998, specifically addresses the airworthiness of Eurocopter AS 332 (Super Puma) series helicopters. The key operative sections (39.1(1)) of this legislation establish the Civil Aviation Safety Authority's (CASA) authority to issue Airworthiness Directives (AD) to ensure the safety of aircraft. The AD in question, AD/S-PUMA/39, targets specific model AS 332 C, C1, L, L1, and L2 helicopters with certain pedal unit assemblies and mandates specific actions to rectify an identified safety issue (section 13/2001). These actions include performing a dye penetrant inspection of the pedal adjustment lever within a specified timeframe and modifying the pedal unit assemblies as directed by Eurocopter's Alert Service Bulletins 67.00.19 and 67.00.20 (section 1(a), 1(b), and 1(c)). The compliance section specifies the timeframes for these actions, with a revised effective date of 14 November 2001 for the initial inspection and modifications to be completed by 1 June 2002 (section 1).
The AD imposes obligations on aircraft operators and maintenance personnel to adhere to the specified inspection and modification requirements to ensure the continued airworthiness of the affected helicopters. Operators must ensure that the necessary inspections and modifications are conducted by qualified personnel and in accordance with the specified timelines (section 1). This includes conducting a dye penetrant inspection within 50 flight hours after the effective date of the AD and subsequent inspections at intervals not exceeding 1,500 flight hours until the modifications are completed (section 1). Additionally, operators must ensure that the modifications outlined in Eurocopter's Alert Service Bulletin 67.00.20 are implemented before the specified deadline (section 2).
Failure to comply with the AD may result in civil and criminal consequences. CASA has the authority to take enforcement actions against operators who do not adhere to the specified inspection and modification requirements. The potential penalties for non-compliance may include fines, enforcement notices, or even the suspension or revocation of the aircraft's certificate of airworthiness. The maximum penalties for such offences are determined by the Civil Aviation Act 1988 and may vary depending on the severity and circumstances of the non-compliance (section 39.1(1)). It is essential for operators and maintenance personnel to carefully follow the AD's requirements to avoid any legal repercussions and ensure the continued safety of the affected helicopters.