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/45 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.
Eurocopter AS 332 (Super Puma) Series Helicopters
AD/S-PUMA/45
Amdt 1
Main Rotor Blades - Vibration Absorbers 1/2003
TX
Applicability: Model AS 332 L2 helicopters.
Requirement: 1. For helicopters equipped with one or several main rotor blade vibration absorbers P/N 332A11-0460-02 that have logged more than 700 flight hours since new:
- On shafts that have not undergone a magnetic particle inspection within the last 200 flight hours, remove the vibration absorbers and check the tightening torque loads of the plugs and the condition of the shaft in accordance with the instructions described in paragraph 2.B.1 of EUROCOPTER AS 332 Alert Telex (AT) No. 05.00.60.
ii. On vibration absorber assemblies that have undergone a magnetic particle inspection within the last 200 flight hours, accomplish the inspection as described in paragraph 2.B.1 of EUROCOPTER AS 332 Alert Telex (AT) No. 05.00.60.
2. For helicopters equipped with one or several main rotor blade vibration absorbers P/N 332A11-0460-02 that have logged less than 700 flight hours since new, comply with the instructions described in paragraph 2.B.1 of EUROCOPTER AS 332 Alert Telex (AT) No. 05.00.60.
Following compliance with parts 1 or 2 above:
- If the fretting on the shaft is not removed after touching up, or a crack is found in the shaft, scrap the shaft and the spacer on the leading edge side.
3. Check the tightening torque of the two plugs in accordance with the instructions described in paragraph 2.B.2 of EUROCOPTER AS 332 Alert Telex (AT) No. 05.00.60.
4. Lubricate the vibration absorbers in accordance with the instructions described in paragraph 2.B.3 of EUROCOPTER AS 332 Alert Telex (AT) No. 05.00.60.
For vibration absorbers that were lubricated more than 100 hours or more than three months ago, comply with paragraph 2.B.3 of EUROCOPTER AS 332 Alert Telex (AT) No. 05.00.60 no later than the next check after the last flight of the day.
Eurocopter AS 332 (Super Puma) Series Helicopters
AD/S-PUMA/45 Amdt 1 (continued)
Note 1: Compliance with this amendment cancels the operational restrictions imposed by the original issue of this AD which became effective on 12th November 2002.
Note 2: DGAC AD T2002-582(A) refers.
Compliance: 1.i. Within 50 flight hours and before December 31, 2002 (whichever occurs first).
1.ii. Within 250 flight hours following the magnetic particle inspection and before December 31, 2002 (whichever occurs first).
2. No later than 750 flight hours (since new for the vibration absorber).
3. Within 300 flight hours, then at maximum intervals of 300 flight hours, after compliance with paragraph 2.B.1 of EUROCOPTER AS 332 Alert Telex.
4. Within 100 flight hours, then at maximum intervals of 100 flight hours (without exceeding 3 month intervals between inspections).
This Amendment becomes effective on the 26 November 2002.
Background: This Airworthiness Directive is issued after a helicopter lost a pendulous weight following the failure of the shaft that supports the pendulous flyweight assemblies on the main rotor vibration absorbers.
Loss of one or more weights will cause very high vibration in the rotor system and may cause rotor system damage.
This amendment specifies various inspections that need to be carried out on the vibration absorber assembly. The original issue of this AD only required an operational limitation as an interim measure, pending the issue of this amendment. Compliance with this amendment removes the operational limitation imposed by the original issue of this AD.
The original issue of this Airworthiness Directive became effective on 12 November 2002.
David Alan Villiers
Delega te of the Civil Aviation Safety Authority 25 November 2002
The above AD is notified in the Commonwealth of Australia Gazette on 26 November 2002.
Overview
The Civil Aviation Safety Authority Act 1998 was enacted to provide for the regulation of aviation safety in Australia, ensuring that civil aviation operations are conducted in a safe and orderly manner. This Act empowers the Civil Aviation Safety Authority (CASA) to issue airworthiness directives to address specific safety concerns within the aviation industry. The problem this legislation aimed to address was the need for effective and timely responses to safety issues that could potentially compromise the airworthiness of aircraft. The Civil Aviation Safety Authority Act 1998 was enacted by the Parliament of Australia, with the overarching policy objective being to enhance the safety and efficiency of civil aviation in Australia. The issuing of Airworthiness Directives under this Act is a means to ensure compliance with safety standards and to mitigate risks associated with identified unsafe conditions.
Scope and Application
The Airworthiness Directive AD/S-PUMA/45 Amdt 1 applies specifically to Eurocopter AS 332 L2 helicopters equipped with main rotor blade vibration absorbers P/N 332A11-0460-02. This AD targets aircraft operators and maintenance personnel who are responsible for ensuring that these helicopters meet specific airworthiness standards to mitigate safety risks associated with vibration absorbers. The directive mandates certain inspections and actions to be undertaken on the vibration absorber assemblies to prevent the failure of the shaft supporting these components, which could lead to catastrophic failures such as the loss of pendulous weights and subsequent high vibration in the rotor system. This AD operates under the jurisdiction of the Civil Aviation Safety Authority (CASA) and applies across the Commonwealth of Australia. The AD does not specify any exclusions, but compliance is mandatory for all helicopters falling within its scope. The directive extends its application through detailed instructions provided in the EUROCOPTER AS 332 Alert Telex, which must be followed to ensure the safety of the aircraft.
Key Provisions
The Airworthiness Directive (AD) AD/S-PUMA/45 Amdt 1 issued under the Civil Aviation Regulations 1998 (CAR 1998) mandates specific actions to be taken on Eurocopter AS 332 (Super Puma) Series helicopters to ensure their airworthiness. Section 1 of the AD applies to AS 332 L2 helicopters, while Section 2 details the requirements for action. For helicopters equipped with certain main rotor blade vibration absorbers, Section 2(1) requires that vibration absorbers be removed and checked if they have logged over 700 flight hours and have not undergone a magnetic particle inspection within the last 200 flight hours. For those that have undergone such an inspection, inspections as per specified instructions must be conducted (Section 2(2)). Helicopters with less than 700 flight hours must also comply with the same instructions (Section 2(3)). After compliance, if fretting is not removed or a crack is found, the shaft and spacer must be scrapped (Section 2(4)). Tightening torque of the plugs must be checked (Section 2(5)), and vibration absorbers must be lubricated (Section 2(6)), with specific attention to timing if the absorbers were lubricated more than 100 hours or three months prior.
The AD imposes several obligations on the operators and maintainers of the affected helicopters. They must ensure that the required inspections and maintenance actions are performed according to the specified timelines and instructions. Specifically, operators must ensure that vibration absorbers are removed, inspected, and checked for fretting and cracks within the stipulated flight hour limits (Section 2(1)-(4)). The tightening torque of the plugs must be verified (Section 2(5)), and the vibration absorbers must be lubricated at the specified intervals (Section 2(6)). Compliance with these requirements is crucial to maintaining the airworthiness of the aircraft.
Breach of the requirements set out in the AD can result in severe consequences. While the AD itself does not explicitly state penalties for non-compliance, failure to adhere to the AD may lead to the aircraft being deemed unairworthy by the Civil Aviation Safety Authority (CASA). This could result in the aircraft being grounded until the required actions are taken, potentially leading to significant operational disruptions. Furthermore, ongoing non-compliance may result in regulatory action, including fines or other enforcement measures, under the broader framework of the Civil Aviation Act 1988 and associated regulations. The exact penalties for non-compliance are not specified within the AD but would fall under the broader regulatory and enforcement powers of CASA.