AIRWORTHINESS DIRECTIVE
For the reasons set out in the background section, the CASA delegate whose signature appears below issues the following Airworthiness Directive (AD) under subregulation 39.1 (1) of CAR 1998. The AD requires that the action set out in the requirement section (being action that the delegate considers necessary to correct the unsafe condition) be taken in relation to the aircraft or aeronautical product mentioned in the applicability section: (a) in the circumstances mentioned in the requirement section; and (b) in accordance with the instructions set out in the requirement section; and (c) at the time mentioned in the compliance section.
General Electric Turbine Engines - CT58 Series
AD/CT58/16 Fuel Flow Divider Assemblies - Replacement 5/2002
Applicability: Models CT58-140-1, -140-2, and former military T58-GE-5, -8F, -10, -100, and -402 turboshaft engines, with fuel flow divider assemblies Part Numbers (P/N) 4050T82G02, or 5040T77G02.
Requirement: 1. Locate the temperature control assembly, which is mounted on the fuel flow divider assembly and carry out the following:
(a) Read the temperature control assembly Serial Number(S/N), located on the temperature control assembly end cap. The end cap can be identified by a one- inch hex flange and by being threaded into the fuel flow divider body.
(b) If the first two digits of the S/N are 95, 96, 97, 98, or 99, or if the S/N cannot be determined, replace the entire fuel flow divider assembly.
2. Do not install any fuel flow divider assembly with P/N 4050T82G02 or 5040T77G02, that have the first two digits of the temperature control assembly S/N of 95, 96, 97, 98, or 99.
Note: Further information regarding S/N location on the temperature control assembly may be found in GE Alert Service Bulletin CT58 73-A0080, dated 13 February, 2001.
Note: FAA AD 2001-12-07 refers.
Compliance: For Requirements 1 and 2: As from the effective date of this Airworthiness Directive.
This Airworthiness Directive becomes effective on 16 May 2002.
General Electric Turbine Engines - CT58 Series
AD/CT58/16 (Continued)
Background: Reports have been received by the FAA of substantial fuel leakage from the end caps of fuel flow divider assemblies. Investigation by the manufacturer revealed that the manufacturer of the temperature control valve assembly end caps did not accomplish the required manufacturing process steps following heat treatment. This caused the end caps to be susceptible to intergranular corrosion, which can result in cracking.
This Airworthiness Directive is therefore raised to correct a condition that could cause an engine fire, leading to an in-flight engine shutdown and forced landing.
Eugene Paul Holzapfel
Delegate of the Civil Aviation Safety Authority 25 March 2002
The above AD is notified in the Commonwealth of Australia Gazette on 24 April 2002.
Overview
The Airworthiness Directive (AD) AD/CT58/16, issued in 2002 by the Civil Aviation Safety Authority (CASA) under the Civil Aviation Regulations 1998, targets specific General Electric CT58 Series turbine engines to address a safety concern involving fuel leakage. The directive was enacted to correct a potentially unsafe condition identified with certain fuel flow divider assemblies, which were found to be susceptible to intergranular corrosion due to manufacturing process failures. This corrosion could lead to end cap cracking, substantial fuel leakage, engine fire, and consequently, an in-flight engine shutdown and forced landing. The AD specifies that if the serial number of the temperature control assembly starts with 95, 96, 97, 98, or 99, or if the serial number cannot be determined, the entire fuel flow divider assembly must be replaced and no assemblies with the specified part numbers should be installed if their serial numbers start with the aforementioned digits. The directive became effective on 16 May 2002, aiming to enhance aviation safety by mitigating the identified risk.
Scope and Application
The Airworthiness Directive (AD) AD/CT58/16 applies specifically to certain models of General Electric CT58 series turboshaft engines, including the CT58-140-1, -140-2, and the former military T58-GE-5, -8F, -10, -100, and -402 engines. These engines must have fuel flow divider assemblies with part numbers 4050T82G02 or 5040T77G02 to be subject to the directive. The AD mandates certain actions to be taken to address a condition that could lead to engine failure due to fuel leakage caused by intergranular corrosion of the fuel flow divider assembly end caps. The directive applies nationally across the Commonwealth of Australia and was issued by the delegate of the Civil Aviation Safety Authority (CASA) under subregulation 39.1 (1) of the Civil Aviation Regulations 1998. The directive requires the inspection and, if necessary, replacement of specific fuel flow divider assemblies and prohibits the installation of certain assemblies identified by serial number ranges. Failure to comply with this directive could result in serious safety hazards, including engine fires and in-flight shutdowns.
Key Provisions
The Airworthiness Directive (AD) in question, specifically AD/CT58/16, pertains to General Electric Turbine Engines of the CT58 Series. The main requirement of this directive, detailed in section 1, mandates the replacement of the fuel flow divider assembly in certain models of CT58-140-1, -140-2, and former military T58-GE-5, -8F, -10, -100, and -402 turboshaft engines. This action is necessary if the temperature control assembly's serial number (S/N) starts with 95, 96, 97, 98, or 99, or if the S/N is undeterminable. It is also prohibited to install any fuel flow divider assembly with the specified part numbers (4050T82G02 or 5040T77G02) if the temperature control assembly's S/N begins with 95, 96, 97, 98, or 99. The compliance section stipulates that these requirements must be met as from the effective date of the AD, which is 16 May 2002.
The AD imposes specific obligations on the parties involved. These include the identification of the temperature control assembly and reading its serial number, which can be found on the end cap of the assembly, identifiable by its one-inch hex flange and threaded into the fuel flow divider body. If the S/N starts with the digits 95 to 99, or if the S/N is unreadable, the entire fuel flow divider assembly must be replaced. Additionally, any new fuel flow divider assemblies with the specified part numbers must be checked to ensure their temperature control assembly's S/N does not start with 95 to 99 before installation. Non-compliance with these requirements could lead to unsafe conditions that might result in engine fire, in-flight shutdown, and forced landing.
In terms of consequences, while the AD does not explicitly detail offences or penalties, non-compliance could lead to severe repercussions. The directive's purpose is to address a condition that could cause substantial fuel leakage, leading to potentially catastrophic outcomes. Therefore, failing to comply with the AD could result in the aircraft being deemed unairworthy, which could lead to enforcement actions by the Civil Aviation Safety Authority (CASA). This might include grounding the aircraft, imposing fines, or other regulatory actions as stipulated under the Civil Aviation Regulations 1998. The specific penalties would be determined based on the nature and severity of the non-compliance, but the overarching aim is to ensure aviation safety by enforcing adherence to the AD.