COMMONWEALTH OF AUSTRALIA (Civil Aviation Regulations 1998), PART 39 - 105 CIVIL AVIATION SAFETY AUTHORITY
SCHEDULE OF AIRWORTHINESS DIRECTIVES
Robin Aviation Series Aeroplanes
AD/ROBIN/8
Amdt 2
Wing Assembly 1/97
Applicability: Avions Pierre Robin model R2160, all serial numbers, with a time in service of 3400 hours or greater.
Requirement: 1. Inspect both wings in accordance with Avions Pierre Robin Service Bulletin (SB) 123.
Note: The inspection of the wing attachment fittings, using the method specified in SB 123, is not required as it is superseded by Requirement 2 of this Directive.
2. Remove both wings from the fuselage. Remove all paint from the wing-to- fuselage attachment fittings, using a solvent paint remover, including fittings on the fuselage. If the use of other paint strippers is unavoidable, remove all residue before inspection. Use of heavy mechanical or abrasive means of paint removal is not permitted.
Inspect all wing attachment fitting components for cracking, paying particular attention to the lower bolt hole areas. Check bolt holes for any eccentricity or signs of wear. Any cracks found during inspection must be repaired before further flight.
Note: It is recommended that some form of protective treatment, such as a standard Zinc Chromate Primer, be applied between inspections to surfaces from which the paint has been removed.
2A. Replace the wing attachment hardware in accordance with sections 2 and 3 of Avions Pierre Robin NOTE NAV 96-3, dated 2 May 1996.
2B. Check the torque of the front and rear wing attachment bolts is in accordance with section 3.3 of Avions Pierre Robin NOTE NAV 96-3, dated 2 May 1996. If the torque of the nut is incorrect, inspect in accordance with requirement 2C.
2C. Inspect the wing attachment hardware in accordance with sections 2 and 3 of Avions Pierre Robin NOTE NAV 96-3, dated 2 May 1996.
Note: DGAC AD 96-051(a)R1 refers to requirements 2A to 2C.
3. Retire wing assembly from service.
Compliance: 1. Initially inspect in accordance with Requirement 1 before exceeding 3 500 hours total time in service or before 375 hours time in service after 14 September 1995, whichever occurs later. Re-inspect at intervals not to exceed 750 hours time in service.
2. Unless already accomplished, inspect in accordance with Requirement 2 before exceeding 3500 hours total time in service. Re-inspect at intervals not to exceed 750 hours time in service.
COMMONWEALTH OF AUSTRALIA (Civil Aviation Regulations 1998), PART 39 - 105 CIVIL AVIATION SAFETY AUTHORITY
SCHEDULE OF AIRWORTHINESS DIRECTIVES
2A. Unless already accomplished, replace the wing attachment hardware before 3500 hours time in service, or at the next inspection in accordance with Requirement 2 of this Directive after 2 January 1997, whichever occurs later.
2B. Unless already accomplished, check the torque in accordance with Requirement 2B before 100 hours time in service after replacement in accordance with Requirement 2A. Thereafter, check the torque at intervals not to exceed 100 hours time in service.
2C. Inspect the wing attachment hardware in accordance with Requirement 2C at each inspection in accordance with Requirement 2 after 2 January 1997.
3. Retire the wing assembly before exceeding 12000 hours time in service. This amendment becomes effective on 2 January 1997.
Background: The inspection of the wing attachment fittings superseded the retirement life requirement of AD/ROBIN/6, which was cancelled. Amendment 1 extended the existing inspection threshold and interval for the wing attachment fitting, mandated the manufacturers wing general inspection and specified a wing service life limit.
This Amendment adds requirements for replacement and inspection of the wing attachment hardware, as a result of the in-flight separation of a wing on a French R2160 aircraft. AD/ROBIN/28 Amdt 1 has similar requirements for R2160 aircraft with less than 3400 hours time in service.
Amendment 1 of this Airworthiness Directive became effective on 14 September 1995.
The initial issue of this Airworthiness Directive became effective on 28 February 1985.
Overview
The Civil Aviation Regulations 1998, enacted by the Parliament of Australia, provide a comprehensive framework for ensuring aviation safety across the country. A particular focus of these regulations is the issue of airworthiness directives, which are legally binding instructions issued by the Civil Aviation Safety Authority (CASA) to ensure the safe operation of aircraft. One such airworthiness directive, AD/ROBIN/8, pertains specifically to the Robin Aviation Series Aeroplanes, particularly the Avions Pierre Robin model R2160. This directive was introduced to address safety concerns related to the wing assembly of these aircraft, particularly after instances of in-flight wing separation. The policy objective of AD/ROBIN/8 is to mandate regular inspections, maintenance, and, where necessary, replacement of critical wing components to prevent structural failures and ensure the continued airworthiness of the affected aircraft. The directive outlines specific requirements for inspecting and maintaining the wing attachment fittings and hardware, aiming to mitigate the risk of in-flight separation and enhance overall flight safety.
Scope and Application
The Civil Aviation Regulations 1998, specifically Part 39 - 105 and the Civil Aviation Safety Authority Schedule of Airworthiness Directives for Robin Aviation Series Aeroplanes, applies to all Avions Pierre Robin model R2160 aircraft with a time in service of 3400 hours or greater. This legislation mandates that the wing assembly of these aircraft must be inspected and maintained according to the outlined procedures to ensure airworthiness. The Act applies nationally across Australia and is enforced by the Civil Aviation Safety Authority (CASA). The regulations detail requirements for the inspection and replacement of wing attachment fittings, as well as the removal and replacement of wing assemblies to maintain safety standards. There are no specific exclusions or exemptions mentioned in the text, implying that all applicable aircraft must comply with the directives. The requirements are extended and detailed through subordinate instruments such as service bulletins and notes from Avions Pierre Robin, ensuring specific and actionable guidelines for maintenance personnel.
Key Provisions
The Civil Aviation Regulations 1998, specifically Part 39 - 105 under the Civil Aviation Safety Authority, mandate stringent safety measures for certain aircraft models. This includes an amendment concerning the wing assembly of Avions Pierre Robin model R2160 aeroplanes (section 1). These regulations apply to all serial numbers of this model that have accumulated 3400 or more hours of service (section 1). The key requirements outlined in this directive include a comprehensive inspection of the wings and wing attachment fittings, as specified in the Avions Pierre Robin Service Bulletin 123, excluding the inspection of wing attachment fittings by the method specified in the service bulletin (section 1). Additionally, it mandates the removal of wings and the subsequent inspection and repair of wing attachment fittings (section 2). The directive also includes specific procedures for replacing wing attachment hardware and checking bolt torque, as outlined in sections 2A, 2B, and 2C of the Avions Pierre Robin NOTE NAV 96-3 (sections 2A-2C).
The obligations under this legislation impose a series of actions on aircraft operators and maintenance personnel. Operators must ensure that their aircraft meet the specified inspection and maintenance criteria. This includes conducting the initial inspection before the aircraft reaches 3500 hours of total time in service or 375 hours after 14 September 1995, and subsequent inspections at intervals not exceeding 750 hours (section 3.1). Maintenance personnel must replace the wing attachment hardware before the aircraft accumulates 3500 hours of service, or at the next inspection after 2 January 1997, and check the torque of the wing attachment bolts within 100 hours after replacement and then at intervals not exceeding 100 hours (sections 2A-2B). Furthermore, the wing attachment hardware must be inspected at each inspection in accordance with Requirement 2, following 2 January 1997 (section 2C). The wing assembly must be retired from service before the aircraft accumulates 12000 hours of total time in service (section 3).
Failure to comply with the provisions of this directive can result in significant consequences. Non-compliance may lead to the grounding of the affected aircraft, as the regulations impose strict safety measures designed to prevent in-flight separation of the wings. The potential civil and criminal penalties for non-compliance are severe, although specific maximum penalties are not detailed in the provided text. However, it is understood that breaches of civil aviation safety regulations can result in substantial fines and legal action against the aircraft operator and maintenance personnel. The implications of such non-compliance extend beyond financial penalties, as they can also impact the safety and reliability of the aircraft, potentially endangering passengers and crew.