COMMONWEALTH OF AUSTRALIA (Civil Aviation Regulations 1998), PART 39 - 106 CIVIL AVIATION SAFETY AUTHORITY
SCHEDULE OF AIRWORTHINESS DIRECTIVES
General Electric Turbine Engines - CF6 Series
AD/CF6/38 Stage 1 Fan Disk Inspection 1/99 DM
Applicability: General Electric Company CF6-6, -45, -50, -80A and 80C2 series turbofan engines with Stage 1 fan disks installed, identified by serial numbers (S/N) in the following GE Alert Service Bulletins (ASBs):
- CF6-6 ASB 72-A996 Revision 4 dated 9 June 1998.
2. CF6-50 ASB 72-A988 Revision 6 dated 25 August 1998.
3. CF6-80A ASB 72-A565 Revision 5 dated 9 June 1998.
4. CF6-80C2 ASB 72-A478 Revision 4 dated 9 June 1998.
These engines are installed on, but not limited to, Boeing 747 and 767, Airbus 300 and 310, McDonnell Douglas DC-10 and MD-11 Series aircraft.
Requirement: On fan disks affected by this Directive, perform an ultrasonic immersion inspection for cracks in accordance with the applicable alert service bulletin (as identified in the applicability section above), remove from service any disks found to be cracked and replace with serviceable components.
Compliance: Before next flight after the effective date of this Directive.
This Airworthiness Directive becomes effective on 25 November 1998.
Note: US FAA AD 98-22-06 Amendment 39-10853 refers.
Background: Stage 1 fan disks manufactured between late 1984 and early 1985 have been found to be cracked during routine shop inspections. The actions in this Directive are intended to prevent fan disk failures, due to cracks, which could result in an uncontained engine failure and damage to the aircraft. This Directive reflects a country of origin AD.
Overview
The Civil Aviation Regulations 1998, administered by the Civil Aviation Safety Authority (CASA) and enacted by the Australian Parliament, aim to ensure the safety and efficiency of civil aviation operations within Australia. One particular legislative instrument under these regulations, F2006B08480, addresses the critical issue of airworthiness for specific turbine engines, specifically targeting the General Electric CF6 Series engines. This legislative instrument was introduced to tackle the problem of potential fan disk failures in these engines, which could lead to uncontained engine failure and significant damage to aircraft. The policy objective, as outlined in the legislation, is to mandate rigorous inspection and compliance measures to ensure the continued safety of these engines in operation. CASA’s directive, effective from 25 November 1998, requires an ultrasonic immersion inspection for cracks on affected fan disks and mandates the removal and replacement of any cracked components to prevent potential catastrophic failures.
Scope and Application
The Civil Aviation Regulations 1998, specifically Part 39 - 106, applies to General Electric CF6 series turbofan engines, including those of the CF6-6, -45, -50, -80A, and 80C2 variants, installed on certain aircraft such as Boeing 747 and 767, Airbus 300 and 310, and McDonnell Douglas DC-10 and MD-11. This regulation mandates that an ultrasonic immersion inspection for cracks be conducted on the Stage 1 fan disks of these engines as identified by specific serial numbers listed in the applicable General Electric Alert Service Bulletins. The requirement to perform these inspections and replace any cracked disks with serviceable components must be fulfilled before the next flight following the directive’s effective date of 25 November 1998. This directive aims to ensure the airworthiness and safety of these aircraft by preventing potential fan disk failures, which could lead to uncontained engine failure and subsequent damage to the aircraft. The directive aligns with a similar directive issued by the US Federal Aviation Administration, reflecting a country of origin approach to maintaining civil aviation safety standards.
Key Provisions
The main operative sections of this Airworthiness Directive (AD/CF6/38) focus on the inspection, maintenance, and replacement of Stage 1 fan disks for specific General Electric CF6 series engines (sections 1 and 2). The directive applies to certain CF6-6, -45, -50, -80A, and 80C2 series turbofan engines installed on various aircraft models (section 1). It mandates an ultrasonic immersion inspection for cracks on fan disks identified by specific GE Alert Service Bulletins, and requires the removal and replacement of any cracked disks before the next flight following the directive's effective date, which is 25 November 1998 (section 3). This directive is a reflection of a US Federal Aviation Administration (FAA) Airworthiness Directive (AD 98-22-06 Amendment 39-10853).
The obligations imposed by this Act on the relevant parties include conducting the specified inspections and ensuring that any cracked Stage 1 fan disks are removed from service and replaced with serviceable components before the next flight (section 3). This requirement applies to the identified engine models and aircraft, and compliance must be achieved before the next flight following the effective date of the directive (section 3). The directive aims to mitigate the risk of fan disk failures due to cracks, which could lead to uncontained engine failure and potential damage to the aircraft (section 4).
Breaches of this directive could result in significant civil or criminal consequences, depending on the severity of the non-compliance and the potential impact on flight safety. The maximum penalties for such breaches are not explicitly stated in this directive but could include fines and other regulatory actions under the Civil Aviation Act 1988 and the Civil Aviation Regulations 1998. Failure to comply with airworthiness directives can lead to serious safety risks, and thus, it is imperative for operators and maintenance personnel to adhere strictly to the requirements outlined in this directive to ensure the continued airworthiness of the affected aircraft.