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-112/14
Amdt 1
Vertical Stabiliser Forward Spar Attachment Structure
3/88
Applicability: Models 112 and 112B, serial numbers 3 to 544 and 13000. Models 112TC and 112TCA, serial numbers 13001 to 13309.
Requirement: 1. Inspect for cracks in the fuselage frame and the vertical fin attachment fitting as shown in Part I of Gulfstream Aerospace SB 112-72A.
Note: This inspection requirement is unchanged from the previous issue of this Directive.
2. Modify the vertical fin attachment in accordance with Part II of Gulfstream Aerospace SB 112-72A.
Note: Simple AC 43.13 type repairs are not equivalent.
Compliance: For Requirement Para 1: Within 10 hours’ time in service after 7 May 1987.
For Requirement Para 2: Before further flight if cracks are found. Otherwise not later than 24 March 1989.
Background: Numerous reports have now been received of cracking in the vertical stabiliser forward spar attachment structure. The manufacturer has analysed the load paths through this critical area and determined that substantial reinforcement is required to prevent further cracking.
Overview
The Civil Aviation Regulations 1998, specifically Part 39 - 105, address the need for ensuring the airworthiness of aircraft in Australian airspace. The legislative instrument F2006B02184, issued by the Civil Aviation Safety Authority, was enacted to fill a critical gap identified in the safety of the Gulfstream (Rockwell) 112 Series Aeroplanes. This directive, AD/AC-112/14, focuses on the vertical stabiliser forward spar attachment structure, aiming to prevent and rectify cracking issues that have been reported in certain models and serial numbers of the Gulfstream 112 Series. The objective is to mandate specific inspections and modifications to ensure the continued safety and airworthiness of these aircraft. Compliance with the directive is mandatory, with inspection requirements to be fulfilled within a specified timeframe and modifications to be carried out if cracks are found or before a set date if no cracks are detected.
Scope and Application
The Civil Aviation Regulations 1998, specifically Part 39 - 105, pertains to the Civil Aviation Safety Authority's Schedule of Airworthiness Directives concerning the Gulfstream (Rockwell) 112 Series Aeroplanes. This legislative instrument applies to specific models and serial numbers of the Gulfstream 112 Series, including models 112 and 112B with serial numbers ranging from 3 to 544 and 13000, as well as models 112TC and 112TCA with serial numbers from 13001 to 13309. The directive mandates an inspection for cracks in the fuselage frame and the vertical fin attachment fitting, with a compliance requirement of within 10 hours’ time in service after the directive was issued on 7 May 1987. Additionally, if cracks are detected, modifications to the vertical fin attachment must be made before further flight, otherwise by a specified deadline of 24 March 1989. The directive also notes that simple AC 43.13 type repairs are not considered equivalent to the required modifications. This regulatory measure is aimed at addressing the issue of cracking in the vertical stabiliser forward spar attachment structure, as identified through numerous reports and analysis by the manufacturer.
Key Provisions
The Civil Aviation Regulations 1998, particularly Part 39, contain several operative sections which pertain to airworthiness directives for specific aircraft models. One such directive, AD/AC-112/14 Amendment 1, applies to the Gulfstream (Rockwell) 112 Series Aeroplanes. This directive mandates specific inspections and modifications to the vertical stabiliser forward spar attachment structure (Section 105). The directive covers models 112 and 112B with serial numbers ranging from 3 to 544 and 13000, as well as models 112TC and 112TCA with serial numbers from 13001 to 13309. The directive requires inspections for cracks in the fuselage frame and vertical fin attachment fitting, as specified in Part I of Gulfstream Aerospace Service Bulletin 112-72A (Section 1). Additionally, it necessitates modifications to the vertical fin attachment according to Part II of the same service bulletin, explicitly noting that simple AC 43.13 type repairs are not acceptable (Section 2).
The obligations under this directive are clear and time-sensitive. For Requirement 1, operators must inspect for cracks within 10 hours’ time in service after 7 May 1987. For Requirement 2, if cracks are found during the inspection, modifications must be made before further flight. If no cracks are detected, the modifications must be completed by 24 March 1989. These requirements are designed to ensure that any identified structural weaknesses are addressed promptly to maintain the safety of the aircraft.
Failure to comply with the airworthiness directive could result in serious safety risks. The legislation does not explicitly state the penalties for non-compliance, but non-compliance with airworthiness directives can lead to severe consequences, including the grounding of the aircraft, which can have significant operational and financial implications for the operator. Additionally, the Civil Aviation Safety Authority (CASA) has the authority to take enforcement actions, which could include fines or other regulatory penalties. The severity of the consequences underscores the importance of adhering to the mandated inspection and modification schedules.