COMMONWEALTH OF AUSTRALIA (Civil Aviation Regulations 1998), PART 39 - 105 CIVIL AVIATION SAFETY AUTHORITY
SCHEDULE OF AIRWORTHINESS DIRECTIVES
Gulfstream (Rockwell) 114 Series Aeroplanes
AD/ROCK-114/12
Amdt 2
Wing Forward Spar 6/95
Applicability: All models 114 and 114A with Serial Numbers 14000 to 14540 not modified on both left and right hand side in accordance with Gulfstream Aerospace Service Bulletin (SB) 114-22C, Part II, Part III, Part IV or Part V.
Requirement: 1. Visually inspect, using a mirror or borescope, the upper cap of the forward wing spar in the area of the main landing gear side brace fitting in accordance with the instructions specified in Part I of Gulfstream Aerospace Service Bulletin 114- 22C.
2.a. For aircraft not previously modified in accordance with either Part II or Part V of Gulfstream Aerospace SB 114-22, -22A or -22B, modify in accordance with Part II of Gulfstream Aerospace Service Bulletin 114-22C, or
2.b. For aircraft previously modified in accordance with either Part II or Part V of Gulfstream Aerospace Service Bulletin 114-22, -22A or -22B, modify in accordance with Part III of Gulfstream Aerospace Service Bulletin 114-22C.
Note: FAA AD 90-04-07 refers and supersedes FAA AD 87-14-03.
Compliance: 1. Initially inspect in accordance with Requirement 1 within 25 hours time in service from 25 May 1995. Re-inspect at intervals not to exceed 100 hours time in service.
2. Modify in accordance with Requirement 2 within 300 hours time in service from 25 May 1995.
Aircraft modified in accordance with Gulfstream Aerospace Service Bulletin 114-22, 114-22A or 114-22B or Drawing 40002 RWK #1, #2, #4G, #4H or 42000 RWK #3
are only in partial compliance with this AD and require further inspection and modification.
Background: There have been several Australian reports of cracking similar to that described in the Gulfstream SB. The FAA have determined that the earlier modifications are inadequate as a permanent solution to the problem. This Amendment introduces the latest Revision of the SB, which requires a more extensive modification.
Overview
The Civil Aviation Regulations 1998, specifically Part 39 - 105, addresses the issue of aircraft airworthiness through the Civil Aviation Safety Authority (CASA) Schedule of Airworthiness Directives. This legislative instrument, introduced in 1995, was enacted to enhance aviation safety by ensuring that specific models of aircraft, such as the Gulfstream (Rockwell) 114 Series Aeroplanes, meet stringent structural integrity requirements. The policy objective behind these regulations is to prevent structural failures by mandating detailed inspections and modifications to critical components, thereby reducing the risk of in-flight incidents. The Australian reports of cracking in similar aircraft, as well as the findings from the Federal Aviation Administration (FAA), necessitated the implementation of more extensive modification requirements to ensure the continued safety of these aircraft in Australian airspace.
Scope and Application
This legislative instrument applies specifically to Gulfstream (Rockwell) 114 Series aeroplanes, namely all models 114 and 114A with serial numbers ranging from 14000 to 14540, that have not been modified on both the left and right-hand sides in accordance with Gulfstream Aerospace Service Bulletin (SB) 114-22C, Parts II, III, IV, or V. The requirement pertains to the visual inspection and modification of the upper cap of the forward wing spar in the area of the main landing gear side brace fitting, as specified in the Gulfstream Aerospace SB 114-22C. The regulation mandates an initial inspection within 25 hours from 25 May 1995, followed by periodic inspections at intervals not exceeding 100 hours, and requires modifications within 300 hours from the same date. Aircraft that have been previously modified in accordance with certain Gulfstream SBs are only in partial compliance and require further inspection and modification. The geographic reach of this legislation is national, governed by the Civil Aviation Regulations 1998 under the Commonwealth of Australia, and it extends to all aircraft registered in Australia that meet the specified criteria.
Key Provisions
The Civil Aviation Regulations 1998, specifically Part 39 - 105, details the Civil Aviation Safety Authority's (CASA) Schedule of Airworthiness Directives, focusing on the Gulfstream (Rockwell) 114 Series Aeroplanes in AD/ROCK-114/12 Amendment 2. This directive applies to all models 114 and 114A with serial numbers 14000 to 14540, unless both left and right-hand sides have been modified according to Gulfstream Aerospace Service Bulletin (SB) 114-22C, Parts II, III, IV, or V. The primary requirement, as outlined in Requirement 1 (Section 1), is to visually inspect the upper cap of the forward wing spar in the area of the main landing gear side brace fitting using a mirror or borescope, in accordance with the instructions provided in Part I of Gulfstream Aerospace SB 114-22C.
Further, Requirement 2 (Section 2) specifies modifications for aircraft based on their modification history. For aircraft not previously modified according to Parts II or V of Gulfstream Aerospace SB 114-22, -22A, or -22B, modifications must be made in accordance with Part II of Gulfstream Aerospace SB 114-22C. Conversely, for those previously modified according to Parts II or V of Gulfstream Aerospace SB 114-22, -22A, or -22B, modifications must follow Part III of Gulfstream Aerospace SB 114-22C. Compliance with these directives is mandatory and involves initial inspections and modifications within specific timeframes from 25 May 1995. Initially, the inspection must be completed within 25 hours of time in service, followed by re-inspections at intervals not exceeding 100 hours of time in service. Modifications must be carried out within 300 hours of time in service.
The obligations imposed by this Act require aircraft owners and operators to ensure that the specified inspections and modifications are performed by authorised personnel, adhering to the guidelines and timeframes set out in the directive. Non-compliance with these obligations may result in the aircraft being deemed non-airworthy, potentially leading to severe civil or criminal consequences. This includes the possibility of fines, imprisonment, or both, depending on the severity and intent behind the breach. The maximum penalties are detailed in the relevant sections of the Civil Aviation Act 1988 and may vary based on the specific circumstances of the offence.