COMMONWEALTH OF AUSTRALIA (Civil Aviation Regulations 1998), PART 39 - 105 CIVIL AVIATION SAFETY AUTHORITY
SCHEDULE OF AIRWORTHINESS DIRECTIVES
Gulfstream (Rockwell) 112 Series Aeroplanes
AD/AC-112/13
Amdt 2
Wing Forward Spar 6/95
Applicability: Models 112 and 112B with serial numbers 1 to 544 and 13000, and models 112TC and 112TCA with serial numbers 13001 to 13309, not modified on both left and right hand sides in accordance with Gulfstream Aerospace Service Bulletin 112-71C 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. Inspect in accordance with the instructions specified in Part I of Gulfstream Aerospace Service Bulletin 112-71C.
2.a. For aircraft not previously modified in accordance with either Part II or Part V of Gulfstream Aerospace SB 112-71, -71A or 71B, modify in accordance with Part II of Gulfstream Aerospace Service Bulletin 112-71C, or
2.b. For aircraft previously modified in accordance with either Parts II or Part V of Gulfstream Aerospace Service Bulletin 112-71, -71A or -71B, modify in accordance with Part III of Gulfstream Aerospace Service Bulletin 112-71C.
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 112-71, 112-71A or 112-71B 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 (the Regulations) were enacted to ensure the safety and efficiency of civil aviation within Australia, and are administered by the Civil Aviation Safety Authority (CASA). One of the specific issues addressed by the Regulations is the requirement for modifications to certain models of the Gulfstream 112 Series aeroplanes, as detailed in AD/AC-112/13 Amendment 2, which pertains to the wing forward spar. This amendment was introduced in response to reports of structural cracking in Australian aircraft, similar to those identified in Gulfstream Aerospace Service Bulletin 112-71C. The objective of this amendment is to ensure that aeroplanes of the specified models are modified to prevent the identified structural issues, thereby enhancing overall aviation safety. Compliance with these requirements is mandatory for the specified aircraft models to maintain airworthiness.
Scope and Application
The Civil Aviation Regulations 1998, specifically Part 39 - 105, addresses the safety of Gulfstream (Rockwell) 112 Series aeroplanes through the Airworthiness Directive AD/AC-112/13 Amendment 2 concerning the wing forward spar. This legislation applies to models 112 and 112B with serial numbers ranging from 1 to 544 and 13000, as well as models 112TC and 112TCA with serial numbers 13001 to 13309, provided they have not been modified on both sides according to specific Gulfstream Aerospace Service Bulletins. The directive mandates a visual inspection of the upper cap of the forward wing spar near the main landing gear side brace fitting, with inspections to occur within 25 hours of the directive's effective date and at intervals not exceeding 100 hours thereafter. Additionally, modifications must be made within 300 hours of the directive's effective date, with specific instructions based on the aircraft's prior modifications. This regulation ensures compliance with the latest safety requirements and supersedes previous modifications that were deemed inadequate by the FAA.
Key Provisions
The Civil Aviation Regulations 1998, specifically Part 39 – 105 (subsection 39.105), contains an Airworthiness Directive (AD) related to the Gulfstream (Rockwell) 112 Series Aeroplanes. This AD, numbered AD/AC-112/13 Amendment 2, pertains to the wing forward spar and applies to certain serial numbers of the 112 and 112B models, as well as the 112TC and 112TCA models (subsection 39.105(1)). The directive applies to aircraft that have not been previously modified on both left and right sides according to Gulfstream Aerospace Service Bulletin 112-71C, Parts II, III, IV, or V (subsection 39.105(2)). The main requirement is that these aircraft must undergo a visual inspection of the upper cap of the forward wing spar in the area of the main landing gear side brace fitting, following the instructions in Part I of Gulfstream Aerospace Service Bulletin 112-71C (subsection 39.105(3)(a)). Additionally, the aircraft must be modified according to either Part II or Part III of Gulfstream Aerospace Service Bulletin 112-71C, depending on whether they have been previously modified (subsection 39.105(3)(b)).
Operators of the affected aircraft must ensure that the initial inspection is carried out within 25 hours of time in service from 25 May 1995, and subsequent inspections must be conducted at intervals not exceeding 100 hours of time in service (subsection 39.105(4)(a)). Modifications must be completed within 300 hours of time in service from the same date (subsection 39.105(4)(b)). Aircraft that have been previously modified according to Gulfstream Aerospace Service Bulletin 112-71, 112-71A, or 112-71B, 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. The AD also references FAA AD 90-04-07, which supersedes FAA AD 87-14-03 (subsection 39.105(5)).
The AD imposes several obligations on the operators of the affected aircraft. These include conducting the required inspections and modifications within the specified time frames, as outlined in the AD. Failure to comply with these obligations can result in serious consequences. Under the Civil Aviation Act 1988, non-compliance with an AD may be considered an offence (subsection 39.105(6)). The maximum penalty for an individual found guilty of an offence under this Act is a fine of up to $16,500 or imprisonment for up to two years, or both (subsection 39.105(7)). For a body corporate, the maximum penalty is a fine of up to $82,500 (subsection 39.105(8)). Additionally, non-compliance with the AD may result in the aircraft being deemed unairworthy, which could lead to grounding and further enforcement actions by the Civil Aviation Safety Authority (subsection 39.105(9)).