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.
CFM International Turbine Engines - CFM56 Series
AD/CFM56/22 EGT Harnesses and EGT Couplings 3/2003
Applicability: CFM56-5 and -5B series turbofan engines that have an exhaust gas temperature (EGT) upper harness part number (P/N) CA170-00, with a serial number (S/N) of YC021674 or lower, or an EGT lower harness P/N CA171-00, with a S/N of YC026641 or lower, or an EGT coupling P/N CA172-02 with a S/N of YC166736 or lower.
Note 1: These engines are installed on, but not limited to, Airbus Industrie A318, A319, A320 and A321 aeroplanes.
Note 2: Harnesses or couplings having a serial number that is followed by the letter "W" are not affected by this Directive.
Requirement: 1. If EGT harnesses and EGT couplings have accumulated less than 3,000 engine flight hours since installation, carry out either of the following actions:
- Replace affected EGT harnesses and EGT couplings, not being trend monitored, with serviceable parts in accordance with CFM International Service Bulletins CFM56-5 S/B 77-0020 or CFM56-5B S/B 77-0008, both dated 4 March 2002, as applicable, or
b. Review the smooth data EGT trend via the System for Analysis of Gas Turbine Engines (SAGE), or equivalent, since the affected components were first installed on the current engine. This trend monitoring must continue for the affected EGT harnesses and couplings to ensure that the system does not show a minimum of 30oC downward (i.e. cooler) indication, or more, without a corresponding change in other associated engine parameters such as N1 (LPT rotor speed), N2 (HPT rotor speed), and fuel flow.
2. If the Requirement 1b. SAGE monitoring shows a minimum of 30oC downward indication, or more, without a corresponding change in other associated engine parameters such as N1, N2 and fuel flow, provided that there is sufficient actual EGT margin to do so, replace the EGT harnesses and couplings.
Note 3: FAA AD 2003-02-04 Amdt 39-13020 and DGAC AD 2003-001(B) refer.
CFM International Turbine Engines - CFM56 Series
AD/CFM56/22 (Continued)
Compliance: For Requirement 1a. - Within 500 hours time in service (TIS) after the effective date of this Directive.
For Requirement 1b. - As of the effective date of this Directive until 3,000 engine flight hours have been accumulated since the first installation on the current engine or until the harness and coupling have either been replaced with a serviceable part or a part that has a letter “W” following the S/N.
For Requirement 2 - Within 100 hours TIS after the harness and coupling have been determined to be defective.
This Airworthiness Directive becomes effective on 20 March 2003.
Background: This Directive requires the establishment of an EGT baseline and trend monitoring using SAGE, or equivalent, as an option to EGT harness replacement, and if necessary, replacement of certain EGT harnesses and EGT couplings as soon as a slow and continuous EGT drift downward is noticed.
Both the United States Federal Aviation Administration and the Direction Générale de l’Aviation Civile of France have received reports of erroneous EGT readings. The actions specified by this Directive are intended to prevent unexpected deterioration of critical rotating engine parts due to higher than desired engine operating EGTs.
James Coyne
Delegate of the Civil Aviation Safety Authority 30 January 2003
The above AD is notified in the Commonwealth of Australia Gazette on 26 February 2003.
Overview
The Airworthiness Directive (AD) issued by the Civil Aviation Safety Authority (CASA) under subregulation 39.1(1) of the Civil Aviation Regulations 1998 addresses safety concerns related to certain CFM56 Series turbine engines. The AD was enacted in 2003 to mitigate risks associated with erroneous exhaust gas temperature (EGT) readings, which could potentially lead to engine failures. This directive applies to specific CFM56-5 and -5B series turbofan engines installed in Airbus A318, A319, A320, and A321 aircraft, specifically those with particular EGT harness and coupling serial numbers. The directive mandates either the replacement of affected components or the implementation of a trend monitoring system to ensure the engines do not exhibit significant EGT discrepancies. The overarching policy objective is to maintain and enhance air safety by preventing unexpected engine deterioration due to higher than desired EGTs.
Scope and Application
The Airworthiness Directive (AD) issued by the Civil Aviation Safety Authority (CASA) pertains specifically to the CFM International Turbine Engines of the CFM56 Series, specifically those equipped with Exhaust Gas Temperature (EGT) harnesses and EGT couplings with certain serial numbers. This AD applies to the EGT upper harness part number CA170-00 with serial numbers up to YC021674, the EGT lower harness part number CA171-00 with serial numbers up to YC026641, and the EGT coupling part number CA172-02 with serial numbers up to YC166736. The directive is particularly relevant to turbofan engines installed in Airbus Industrie A318, A319, A320, and A321 aeroplanes, although it is not exclusive to these aircraft models. It is important to note that harnesses or couplings with serial numbers followed by the letter "W" are exempt from this directive. The directive applies at the national level within Australia, overseen by CASA, and mandates compliance with the specified requirements for ensuring the airworthiness of affected aircraft engines. The AD outlines specific actions that must be taken depending on the accumulated flight hours of the affected components, either replacing them with serviceable parts or conducting trend monitoring through systems like the System for Analysis of Gas Turbine Engines (SAGE). Compliance with this directive is mandatory and must be achieved within specified timeframes post the directive's effective date.
Key Provisions
The main operative sections of this Airworthiness Directive (AD) pertain to the applicability, requirement, and compliance timelines of the AD concerning specific CFM56 series turbofan engines. According to the applicability section (AD/CFM56/22), this directive is pertinent to engines with specific serial numbers and part numbers (CA170-00, CA171-00, and CA172-02). These engines are primarily installed on Airbus A318, A319, A320, and A321 aircraft, but are not limited to these models (Applicability). The requirement section outlines two actions: first, if the engines have accumulated less than 3,000 flight hours, then either the affected parts must be replaced or trend monitoring must be initiated (Requirement 1). Second, if the trend monitoring shows a significant EGT drift, the parts must be replaced if feasible (Requirement 2). Compliance with these requirements must occur within specific timeframes (Compliance).
This Act imposes several obligations on the entities it governs. First, it mandates that affected engines undergo either replacement of certain components or initiation of trend monitoring (Requirement 1). If the trend monitoring indicates an EGT drift, the parts must be replaced within a certain timeframe (Requirement 2). Additionally, compliance with these requirements must be achieved within specified time frames, which are contingent on the engine's flight hours and the results of any trend monitoring (Compliance).
Failure to comply with this Airworthiness Directive may result in severe consequences. While the AD does not explicitly state penalties, non-compliance with civil aviation regulations can result in significant civil and criminal penalties under Australian law. These may include fines and imprisonment, depending on the severity of the breach and its impact on air safety. The maximum penalties are not specified in the AD itself but can be substantial under relevant aviation and safety legislation.