AD/CF6/64 - Fuel Shroud Retaining Snap Ring

Applicability. The AD defines applicability by three cumulative criteria: model, prior incorporation of a specified GE SB or factory drainless manifold configuration, and presence of the older retaining ring P/N. Specifically, for CF6-80C2 series it applies where GE SB No. CF6-80C2 S/B 73-0253 has been incorporated, or the engine was built with the drainless manifold configuration, and "have one or more fuel shroud retaining rings, P/N J204P0084, installed." The AD expands scope to certain CF6-80E1 models on analogous terms, stating the engines must have incorporated GE SB No. CF6-80E1 S/B 73-0026 or been built drainless, and have P/N J204P0084 installed.

Part-number specificity. The AD is strictly part-number driven. The old/affected part is identified as P/N J204P0084. The mandated replacement part is P/N 2186M12P01. The AD quantifies exposure by stating "Each engine has a total of 30 rings installed." Operators therefore know the per-engine count for parts logistics and records.

Method of compliance. The AD specifically directs operators to use particular paragraphs of GE service bulletins. For CF6-80C2 series engines use GE SB No. CF6-80C2 S/B 73-0337, Revision 3, (paragraphs 3.A through 3.C.(1)(b)2). For CF6-80E1 series engines use GE SB No. CF6-80E1 S/B 73-0075, Revision 1, (same paragraphs). Those SBs provide the procedural steps to make the replacement. The AD also states that no further action is required where the snap rings were installed before the AD effective date using GE SB No. CF6-80C2 S/B 73-0337 in Revision 2, Revision 1, or the original.

Timing of compliance. The AD requires the replacement "At the next engine shop visit for any reason after the effective date of this AD, unless the actions have already been done." This gives operators a deferred but mandatory window: the replacement can be carried out during the next scheduled shop visit rather than immediately, subject to the engine being in scope.

Supporting references and cross-jurisdictional linkage. The AD references several GE SBs by number and revision, and notes that "FAA AD 2007-11-20 Amdt 39-15077 dated 24 May 2007 refers." Those references show the AD links manufacturer instructions and the FAA action as points of coordination.

Safety rationale. The Background section links the AD to two events of external engine fuel leakage and a subsequent under-cowl engine fire. The AD's stated intent is to "prevent an under-cowl engine fire and damage to the aeroplane during an engine high vibration event." The AD therefore frames the part replacement as a remedy targeted at a mechanical failure mode observed in service.

Documentation and traceability. The AD includes an explicit table (Table 1) listing fuel manifold production P/Ns to help determine whether an engine has a drained or drainless manifold and thereby whether the engine falls within the AD's applicability. Note 1 lists aircraft types on which these engines are installed, "but not limited to" Airbus A300, A310, A330, Boeing 747, 767, and MD-11.

Scope exception. The AD contains a narrowly defined exception for engines where the replacement snap rings were already installed using earlier revisions of the GE SB. The AD therefore recognises that earlier voluntary or recommended work performed with the correct SB revisions extinguishes the AD requirement for those specific engines.

Regulatory instrument. The AD is issued by the Civil Aviation Safety Authority, signed by a delegate, and carries an effective date. It is an instrument that sets a mandatory maintenance action for aircraft continuing airworthiness, framed with manufacturer-specified methods.

Operators and airframe/engine owners. The primary burden falls on owners and operators of aircraft equipped with the specified GE CF6-80C2 and CF6-80E1 series engines that meet the AD's applicability criteria. The AD lists specific engine models and clarifies the common types of aeroplanes on which those engines are installed, noting Airbus A300, A310, A330, Boeing 747, 767, and McDonnell Douglas MD-11 as examples. Because the AD is model- and part-number-specific, it affects those owners who have engines with the older retaining rings P/N J204P0084 or who have incorporated the specified SBs or produced with drainless manifolds.

Maintenance organisations and MRO providers. Maintenance providers who perform engine shop visits, overhauls and component replacements will be directly involved. The AD requires the replacement work to follow specified GE SB procedures. Repair stations, approved maintenance organisations and engine shops must have access to the applicable GE SBs (CF6-80C2 S/B 73-0337 Rev 3; CF6-80E1 S/B 73-0075 Rev 1) and be capable of replacing up to 30 rings per engine to the specified P/N 2186M12P01.

Parts suppliers and the aftermarket. Suppliers of GE parts and aftermarket distributors will be asked to supply P/N 2186M12P01 snap rings in the volume required. The AD also implicates inventory of the older P/N J204P0084 rings: operators must identify and replace those items as they appear in their engines. The AD’s part-number specificity imposes sourcing and stock management tasks for parts procurement.

Fleet planners and operators’ maintenance departments. Because compliance is at the next engine shop visit, fleet managers must track applicable engines and schedule the replacement work to coincide with the next shop visit. For operators that operate long on-wing intervals, the AD creates a deferred risk window until the next scheduled shop visit.

Regulators and certificating authorities. The Civil Aviation Safety Authority (CASA) issued the AD, and the document references a related FAA AD. Regulators will monitor compliance through continuing airworthiness processes; operators interact with CASA and possibly other national authorities to confirm compliance status during inspections and audits.

Training and documentation. Engineers and mechanics will need to access and apply the specified GE SB procedures. Quality and records personnel must capture the replacement actions in maintenance logs and records to show the AD has been complied with, or to demonstrate that earlier SB revisions were used to install snap rings before the AD effective date.

Insurance and safety oversight stakeholders. Aviation insurers and safety auditors will be interested in evidence of compliance because the AD is expressly framed to prevent fuel leakage and under-cowl engine fire risk. Evidence of non-compliance could affect airworthiness determinations or insurance positions, although the AD itself does not specify insurance consequences.

Passengers and airlines. Airlines operating affected aircraft will incur the direct cost of parts and labour for the replacements, and may need to schedule additional shop-time. The AD’s deferral to the next shop visit mitigates the need for immediate AOG actions, but for engines scheduled for immediate shop visits the airline will carry the cost and downtime of the replacements.

Mandatory duty to replace specified parts. The core duty established by the AD is clear and prescriptive: for affected engines, replace any fuel shroud retaining rings with P/N J204P0084 with fuel shroud retaining snap rings P/N 2186M12P01, using the method prescribed in the relevant GE SB paragraphs. The AD identifies the exact P/Ns and the GE SB paragraphs to be used, thereby limiting discretion over replacement method for compliance purposes.

Timing duty. The AD sets the compliance timing as "At the next engine shop visit for any reason after the effective date of this AD, unless the actions have already been done." That creates an obligation that is tied to operational maintenance scheduling rather than an immediate grounding, but it is mandatory when the condition (an engine shop visit) next occurs.

Procedural duty to use specified SB paragraphs. The AD does not simply state 'replace the part'; it requires following explicit parts of manufacturer service bulletins: paragraphs 3.A through 3.C.(1)(b)2 of GE SB No. CF6-80C2 S/B 73-0337 Revision 3 for CF6-80C2 engines, and the equivalent paragraphs of GE SB No. CF6-80E1 S/B 73-0075 Revision 1 for CF6-80E1 engines. This channels the technique, tooling and inspection steps to the manufacturer-prescribed method.

Record-based exception and proof. The AD grants an exception where "the fuel shroud retaining snap rings were installed in the CF6-80C2 series engines before the effective date of this AD using GE SB No. CF6-80C2 S/B 73-0337, Revision 2; Revision 1; or the Original." That creates a right to claim no further action where an operator can demonstrate via maintenance records that the earlier SB revisions were used to perform the work before the effective date. The burden is on the operator to produce the record demonstrating prior compliant work.

Obligation to determine applicability. Operators must determine whether an engine is within scope. The AD sets out the applicability criteria and includes Table 1 listing fuel manifold production P/Ns to assist with that determination. The duty to correctly identify affected engines rests with the operator.

Right to rely on specified methods and parts. The AD prescribes particular replacement parts and SB procedures; operators who comply with those specified parts and paragraphs should be deemed to have complied with the AD’s technical prescription as to the ring replacement. Where prior work used the SB revisions explicitly listed in the AD, the operator has a right to rely on that work as satisfying the AD.

No additional actions stated. The AD contains a limited and specific requirement. It does not require broader inspections or replacement of other components. It also does not require immediate grounding or removal unless an engine shop visit occurs; the duty is triggered by the next scheduled shop visit unless prior compliant work exists.

Documentation duty. Although the AD does not state a separate recordkeeping section, the AD’s exception for previously installed snap rings necessarily implies a documentation obligation: operators must retain or present maintenance records showing the method and revision of SB used prior to the AD effective date when asserting they have no further action to take.

Coordination duty with maintenance providers. Since the AD requires use of GE SB paragraphs, operators must ensure that maintenance providers have the correct SB revisions and apply the required paragraphs. This assigns a coordination and oversight duty to operators who outsource maintenance.

Ambit of discretion. The AD limits discretion on what is acceptable as compliance by specifying P/Ns and SB paragraphs. It does not explicitly grant alternative methods of compliance within the text. Operators seeking an alternative method would need to consult CASA processes for alternative means of compliance, but the AD text itself makes no provision for that.

What the AD says. The AD text itself does not set out express monetary penalties, criminal sanctions or a specific enforcement procedure. It states the directive becomes effective on 2 August 2007 and identifies the required action and timing. The AD is issued by the Civil Aviation Safety Authority and signed by a delegate, which signals it is a regulatory instrument carrying the authority of CASA.

Regulatory enforcement context, as implied by the instrument. Because this AD is an instrument issued by CASA, it sits within Australian civil aviation continuing airworthiness regulation. The AD requires specified work to be carried out. The AD text does not expressly specify the enforcement mechanisms or penalties for non-compliance in the document, nor does it set out a remedial enforcement schedule.

Practical enforcement mechanisms operators should expect. Although the AD does not list enforcement steps, operators should anticipate that compliance will be monitored through routine continuing airworthiness oversight, airworthiness inspections, and audits. Failure to comply with an applicable AD could be identified in maintenance records review, routine inspections, or safety oversight, which may lead regulators to take administrative enforcement action under the Civil Aviation legislation. The AD itself remains silent on the specific enforcement penalties.

Evidence and records as enforcement tools. The AD’s exception for engines where snap rings were installed before the effective date using specified SB revisions highlights that documentary evidence is central to proving compliance. Operators will need to retain maintenance records, SB compliance documentation and parts traceability to demonstrate to CASA or auditors that the AD has been complied with, or that no action is required because prior work used the specified SB revisions.

Cross-reference to FAA AD. The AD notes that FAA AD 2007-11-20 refers. Where aircraft are operated under multiple jurisdictions or where operators must satisfy foreign regulators, the FAA AD reference can be a point of comparative enforcement; however the AD text does not describe how CASA enforcement will be coordinated with FAA actions.

Absence of penalties in text. Because the AD does not set out explicit penalties or enforcement steps, users seeking precise enforcement consequences will need to consult CASA enforcement policy and the Civil Aviation legislation, or request clarification from CASA. The AD document itself does not attempt to catalogue or restate CASA’s enforcement powers.

Relation to manufacturer service bulletins. The AD directly incorporates manufacturer service bulletin procedures by reference. It prescribes specific paragraphs of GE SB No. CF6-80C2 S/B 73-0337 Revision 3 for CF6-80C2 engines and GE SB No. CF6-80E1 S/B 73-0075 Revision 1 for CF6-80E1 engines. The AD therefore requires operators to follow manufacturer technical instructions as the method of compliance, tying an enforced regulatory requirement to industry technical guidance.

Cross-jurisdictional alignment. The AD explicitly notes that FAA AD 2007-11-20 refers. This shows the CASA action is coordinated with an existing FAA AD and suggests alignment with a foreign regulator. For operators and maintainers who must show compliance to both CASA and FAA or other authorities, the AD provides a reference point to the FAA equivalent action, which may assist in audit and recordkeeping across jurisdictions.

Continuing airworthiness and maintenance obligations. The AD is a continuing airworthiness directive. Although the AD text does not cite the Civil Aviation Act or Civil Aviation Safety Regulations, in practice such ADs are instruments used to impose continuing airworthiness obligations. Operators must reconcile their obligations under general aviation safety laws and maintenance regulations with the AD’s specific requirement. The AD does not itself amend primary legislation.

Interaction with operator maintenance programmes and approvals. The AD requires use of GE SB procedures. For operators whose maintenance programmes or maintenance organisation approvals specify different procedures, there will be an operational need to adopt the SB method for these AD-compliance tasks. The AD does not address how to reconcile any discrepancies between an operator’s approved maintenance data and the GE SB paragraphs; operators should align their approved maintenance data with the AD’s mandated methods.

Recordkeeping and certification of maintenance releases. The AD’s compliance requirement will be recorded in maintenance logs and releases to show the engine meets the AD requirement. Where maintenance release processes are governed by other regulatory instruments, the AD’s requirements must be incorporated into the operator’s maintenance control and recordkeeping systems to demonstrate legal compliance.

Parts provenance and airworthiness directives. The AD establishes part-number requirements. The use of specified parts ties into laws and regulations concerning replacement parts, parts conformity, and parts traceability. Operators must ensure procurement and installation of P/N 2186M12P01 snap rings comply with parts management rules and any applicable approvals for parts.

No explicit conflict resolution mechanism stated. The AD itself does not contain provisions for requesting alternative means of compliance or for resolving conflicts between the AD and other regulatory instruments. In practice, operators would need to engage CASA processes for alternative compliance methods, but the AD text does not provide or describe those processes.

Document provenance and dates. The AD is dated 12 June 2007 and signed by David Punshon, Delegate of the Civil Aviation Safety Authority. It states that the AD "becomes effective on 2 August 2007." The AD references GE SB revisions, including the versions that the AD requires (for example, CF6-80C2 S/B 73-0337 Revision 3 dated 5 February 2007, and CF6-80E1 S/B 73-0075 Revision 1 dated 27 November 2006) and earlier revisions that, if used prior to the AD effective date, render the AD unnecessary for that engine.

Service Bulletin revision milestones cited. The AD cites that "This AD requires no further action if the fuel shroud retaining snap rings were installed ... before the effective date of this AD using GE SB No. CF6-80C2 S/B 73-0337, Revision 2, dated 11 January 2007; Revision 1, dated 19 April 2005; or the Original, dated 30 November 2004." That identifies a sequence of SB revisions and acknowledges work done under those earlier revisions as valid.

Reference to FAA AD. The AD records that "FAA AD 2007-11-20 Amdt 39-15077 dated 24 May 2007 refers." This indicates that the FAA had already issued a related AD shortly before CASA’s AD. The CASA AD does not provide an amendment history for itself beyond the issuance and effective date, and it does not record any subsequent amendments.

Absence of further amendments in the text. The AD as provided contains the initial issuance material and references to SB revision history and the FAA AD. The text does not include any later amendments, supersessions, cancellations, or revisions to the AD itself. To determine whether this AD was later amended, superseded or cancelled would require consulting CASA’s subsequent AD publications or the CASA AD register; the document here does not record such follow-up action.

Revision specificity for compliance. The AD’s reliance on specific SB revisions to determine whether prior work satisfies the AD suggests that the AD’s obligational content is sensitive to the revision history of manufacturer documentation. That means operators need to check revision numbers on any prior SB compliance entries before claiming compliance with this AD.

No change log in the AD. Unlike some instruments that include a brief amendment log, this AD contains only the issuance date, effective date, and references to the SB revision history. There is no in-document log of amendments following issuance.

No litigation recorded in the AD. The AD text does not reference any court decisions, appeals, or litigation concerning the directive. It refers to FAA AD 2007-11-20 and to GE service bulletins, but it does not identify any legal challenges, disputes or judicial review actions.

Implication for researchers and litigators. Because the AD itself does not include litigation history, anyone seeking whether this AD was subsequently the subject of legal proceedings must search external sources: CASA enforcement records, administrative appeals, judicial reviews, or industry litigation databases. The AD document as provided contains no entries that would allow a reader to infer that litigation occurred.

Precedent and cases not named. The AD does not name any cases or provide a legal precedent history. The developer instructions for this analysis caution not to invent case law; accordingly, this section records only the absence of litigation material within the AD text.

Disputes about compliance or costs. The AD does not mention disputes over who bears costs or about the technical remedy. Such disputes, if they arose, would be dealt with outside the AD text in contractual, administrative or judicial fora. The AD itself contains no record of such proceedings.

Applicability can be non-obvious and record-sensitive. The AD ties applicability to engine models that have either incorporated specific GE SBs or were built with the "drainless manifold configuration", and that have P/N J204P0084 rings installed. Operators must check maintenance history and parts records carefully to establish whether an engine meets all elements of applicability. If records do not clearly show which SBs were incorporated or the manifold configuration, an engine might be treated as affected when it is not, or vice versa.

Table 1 complexity and partially missing imagery. The AD includes a Table 1 listing drained and drainless manifold production P/Ns for left and right sides across CF6-80C2 and CF6-80E1 series. The HTML rendering in the provided source includes missing or blank image cells (image.001.png placeholders) in places where the PDF or original AD may have had P/Ns. Practically, operators must consult the authoritative Table 1 in the CASA AD or the GE SBs rather than relying on an incomplete electronic copy. Misreading Table 1 could lead to incorrect applicability determinations.

Part-number exactness. The AD is precise about P/Ns: the old ring is J204P0084, the replacement snap ring is 2186M12P01. A single-digit error in ordering or recording could result in installing an incorrect part. Because the AD itself ties compliance to those P/Ns, incorrect parts could leave an operator non-compliant.

Counting requirement per engine. The AD states "Each engine has a total of 30 rings installed." Operators must ensure they order and install the correct number per engine. Failure to replace all 30 rings would not conform to the AD’s stated replacement requirement.

Deferred compliance window may be operationally risky. The AD defers compliance until the next engine shop visit for any reason after the effective date. For engines with long on-wing intervals, that permits a period during which the older rings remain installed. If an operator misinterprets or delays the next shop visit, the engine may remain exposed to the failure mode described in the AD. Operators must therefore track affected engines and not lose sight of the next shop visit as the compliance trigger.

Proof required for exception. The AD provides an exception for engines where snap rings were already installed prior to the effective date using specific SB revisions. To claim the exception, operators must demonstrate that the installation used Revision 2, Revision 1, or the Original of GE SB No. CF6-80C2 S/B 73-0337. If maintenance records do not specify which SB revision was used, the operator cannot reliably claim the exception.

Dependency on service bulletin availability. The mandated procedure refers to SB paragraphs; operators must have access to the exact SB revision cited. If a maintenance organisation only has a different revision or lacks the specific paragraph references, additional administrative work to obtain and confirm the right SB revision will be required. Using a different SB revision without CASA confirmation could create compliance uncertainty.

Interpreting "drainless manifold configuration". The AD refers to engines "built with the drainless manifold configuration at the factory during production assembly." Determining whether an engine is a factory drainless build versus a drained manifold that later had SB work could be non-trivial in the absence of clear build records.

No alternative means of compliance in the AD text. The AD does not describe an alternative means of compliance or how to apply for one. Operators who believe an equivalent method exists must engage with CASA processes outside the AD text, which may take time and add administrative burden.

Cross-jurisdictional recordkeeping. For operators who must demonstrate compliance to multiple regulators, aligning records with the AD’s requirements and with FAA AD 2007-11-20 may require extra documentation and evidence management.

Step 1 , Determine applicability. For each CF6-80C2 and CF6-80E1 engine in your fleet, check the engine serial number and maintenance history to confirm whether the engine has incorporated GE SB No. CF6-80C2 S/B 73-0253 (CF6-80C2) or GE SB No. CF6-80E1 S/B 73-0026 (CF6-80E1), or whether it was built with the factory drainless manifold configuration. Also confirm whether the engine currently has fuel shroud retaining rings P/N J204P0084 installed. Use the AD’s Table 1 of fuel manifold production P/Ns to help determine drained versus drainless manifolds; if the source copy is incomplete, obtain the definitive Table 1 from CASA or the original AD publication. Record the determination in the engine log.

Step 2 , Check prior compliance records for the exception. If snap rings P/N 2186M12P01 were already installed before 2 August 2007, confirm the work was completed using GE SB No. CF6-80C2 S/B 73-0337 Revision 2, Revision 1, or the Original (for CF6-80C2 engines), and retain the documentation showing the SB revision used and the work scope. If the earlier SB revision was used and records are available, no further action under this AD is required for that engine.

Step 3 , Plan for the next engine shop visit. The AD permits compliance at the next engine shop visit for any reason after the effective date. Incorporate the ring replacement into the job card and scope of work for the next shop visit. Ensure scheduling lets you replace all rings on the engine during that shop visit to meet the AD’s instruction that each engine has a total of 30 rings.

Step 4 , Obtain parts and SB procedures. Order sufficient P/N 2186M12P01 snap rings, quantity 30 per engine. Confirm parts provenance and ensure the supplier provides correct P/N identification. Obtain the required GE service bulletins: for CF6-80C2 series engines, GE SB No. CF6-80C2 S/B 73-0337 Revision 3 dated 5 February 2007; for CF6-80E1 series engines, GE SB No. CF6-80E1 S/B 73-0075 Revision 1 dated 27 November 2006. Confirm you have the exact revision cited in the AD and that the maintenance organisation's approved data allows performance of the specific SB paragraphs named.

Step 5 , Perform the work per the SB paragraphs required. Execute the replacement in accordance with paragraphs 3.A through 3.C.(1)(b)2 of the applicable GE SB. Ensure technicians follow the procedures, inspection steps and acceptance criteria found in those paragraphs. Replace all P/N J204P0084 rings with P/N 2186M12P01 snap rings, verifying torque, clearances and any functional checks the SB requires. Conduct any associated inspections that the SB specifies.

Step 6 , Quality control and sign-off. Have the work inspected by the appropriate certifying staff within the maintenance organisation and endorse the maintenance release in accordance with the organisation’s procedures and regulatory obligations. Ensure that the certifying release references the GE SB paragraph compliance as the method required by the AD.

Step 7 , Recordkeeping. Enter the AD compliance action into the maintenance records, specifying the AD number (AD/CF6/64), the engine serial number, the part numbers replaced (J204P0084 out; 2186M12P01 in), the number of rings replaced (30), the GE SB number and revision and the SB paragraphs used. Retain invoices and parts delivery documentation to demonstrate procurement of the correct P/Ns. Keep records of the shop visit date, personnel performing the work, and certifying signatures. If prior SB revisions were used before the AD effective date, preserve the records that establish that fact to invoke the AD exception.

Step 8 , Communicate with regulators and auditors. Ensure that the operator’s continuing airworthiness records reflect AD compliance. Where necessary for interstate operations or leased aircraft, provide evidence of AD compliance to other national authorities or lessors as required.

Step 9 , Supply chain and spare parts planning. For fleet-wide compliance, determine total parts needs (30 snap rings per affected engine) and place orders in sufficient time to avoid delaying scheduled shop visits. Coordinate with parts suppliers to confirm availability of P/N 2186M12P01.

Step 10 , Consider verification and traceability of manifolds and parts. Use Table 1 and parts tags to verify drained versus drainless manifold P/Ns. Ensure traceability of installed snap rings by including P/Ns in the parts installed section of maintenance records and, if your organisation uses electronic records, ensure the part number fields are accurately recorded and searchable.

Step 11 , If in doubt, contact CASA. The AD text supplies the directive but does not describe alternative means of compliance or dispute resolution within the document; if an operator believes an alternative compliance method is technically equivalent, or if there is doubt about interpretation of the SB paragraph requirements or Table 1, contact CASA for guidance or to seek an accepted alternative method of compliance.

Step 12 , Cross-reference to FAA AD if necessary. For operations that interface with FAA oversight or where the aircraft are registered in multiple jurisdictions, consult FAA AD 2007-11-20 (Amdt 39-15077) for the FAA perspective and ensure documentary evidence satisfies both CASA and FAA expectations where applicable.

By following these steps, operators will implement the AD-mandated part-number replacement using the manufacturer-prescribed methods, and will create and retain the records needed to demonstrate compliance or to claim the exception for prior compliant installations.