AD/BR700/9 - Fan Disc Retirement Lives

The AD builds around a small set of precise technical and administrative concepts drawn from engine management and airworthiness recordkeeping. These are:

• Life Limited Part (LLP): The discs in question are treated as life-limited components. The AD identifies two specific part numbers, BRH10048 and BRH19253, and requires operators to treat the maximum approved life for those parts as 25,000 flight cycles when installed in BR700-715A1-30 engines operated on the Hawaiian Flight Mission (Requirement 1; Requirement 2; Background).

• Declared Safe Cyclic Life (DSCL): The AD states that the Post Certification Life Statement for the LP Compressor (Fan) Disc Assembly has revised the DSCL, reducing it from 33,000 to 25,000 flight cycles for the stated engine/mission combination (Background). The DSCL is the technical quantity on which retirement and tracking rely.

• Time Limits Manual (TLM): The AD mandates a specific amendment to TLM SUBTASK 05-10-01-860-016 to change the “GIVEN LIFE A1-30 RATING (FLIGHT CYCLES)” to the new value. It also requires changes to any other reference that quotes the previous maximum when applicable (Requirement 1; Requirement 2). The AD directs operators to TLM TASK 05-00-01-800-001 for recording and control of LLP lives (Requirement 3).

• Pro rata calculations and tracking: The AD requires operators to check LLP Tracking Sheets and, where relevant, update pro rata calculations to reflect the new maximum life. If consumed life (as updated) exceeds 25,000 flight cycles, the disc must be rejected (Requirement 3).

• Applicability and mission profile: The AD’s applicability clause lists BR700-715A1-30, BR700-715B1-30 and BR700-715C1-30 engines as the subject matter, and notes these engines are known to be installed on, but not limited to, Boeing 717 aircraft. However, the life reduction requirement is explicitly limited to parts when “installed in the BR700-715A1-30 engine model and operated under the Hawaiian Flight Mission” (Applicability; Requirement 1; Background). That limitation means the reduced DSCL is mission- and engine-variant-specific.

• Compliance timing: The AD imposes a clear short-term mandatory compliance period (no later than 100 flight cycles after the effective date) and records the effective date as 11 May 2007 (Compliance).

• Regulatory cross-reference: The AD explicitly references EASA Emergency AD 2007-0116-E dated 4 May 2007 (Requirement Note 2), signalling alignment with or adoption of an emergency action issued by the European authority.

These concepts together change both operational practice and recordkeeping. The technical change (shorter disc life for a particular engine/mission combination) produces administrative duties (amend manuals, update tracking sheets, recalculate pro rata values), conditional operational actions (reject discs if updated consumed life exceeds the new limit), and a time-bound obligation to complete the changes within 100 flight cycles.

The AD identifies specific parties and roles affected by its requirements, and places precise obligations on those parties:

• Engine owner/operators and aircraft operators that use BR700-715A1-30 engines on the Hawaiian Flight Mission. The Requirement text repeatedly limits the life reduction to discs “when installed in the BR700-715A1-30 engine model and operated under the Hawaiian Flight Mission” (Requirement 1; Requirement 2; Requirement 3). Operators running that engine/mission combination are directly affected because they must change manuals, check LLP records, update pro rata calculations and reject discs if they exceed the revised DSCL.

• Maintenance organisations and engineers responsible for Time Limits Manual (TLM) content and life tracking. The AD mandates an amendment to TLM SUBTASK 05-10-01-860-016 and refers to TLM TASK 05-00-01-800-001 for recording and control of the lives of parts (Requirement 1; Requirement 3). Those maintaining the TLM and the LLP Tracking Sheet must implement the documented changes and ensure record continuity.

• Part custodians and airworthiness recordkeepers. The AD requires a check of the LLP Tracking Sheet for the two specified part numbers (Requirement 3). Those responsible for maintaining life-limited part records are required to update entries, complete pro rata calculations and effect rejections where necessary.

• Manufacturers and technical authorities insofar as they provide technical data and Post Certification Life Statements. The Background states that recent 3D FEM modelling revisions and a Post Certification Life Statement changed the DSCL (Background). While the AD itself imposes obligations on operators, the underlying technical data providers are implicated because the AD’s action is triggered by their analysis.

• Regulatory administrators. The AD is issued by the Civil Aviation Safety Authority (CASA) delegate (Charles Lenarcic) and cites an EASA Emergency AD (Requirement Note 2; signature block). CASA staff and their delegates will administer and monitor compliance; similarly, where records must be checked and discs rejected, the regulator will be the point of oversight, as demonstrated by the signature and formal issuance.

• Broader fleet operators who have the affected parts in inventory or previously installed on BR700-715A1-30 engines operated under the Hawaiian Flight Mission. The AD requires checking if the parts are “currently or has previously been installed in the BR700-715A1-30 engine model and operated under the Hawaiian Flight Mission” (Requirement 3). That language captures historical installations, so operators with parts moved between engines or stored spares must examine historical records.

Parties not affected, or only potentially affected in limited circumstances, include operators of BR700-715B1-30 and BR700-715C1-30 engines. Although the Applicability block lists those engine models, the life reduction and the subsequent mandatory steps are expressly limited to the BR700-715A1-30 model when paired with the Hawaiian Flight Mission (Applicability; Requirement 1). The AD’s Note 1 further clarifies that these engines are known to be installed on Boeing 717 aircraft, but does not extend the revised DSCL beyond the stated engine/mission combination.

The AD sets out concrete duties and conditional rights that flow from the life reduction. The duties are explicit and procedural; the “rights” are primarily procedural exemptions where certain checks show no relevant installation history.

Duties (explicit in the Requirement block)

• Amend the TLM: Operators or their authorised TLM custodians must amend the Time Limits Manual SUBTASK 05-10-01-860-016 to change the “GIVEN LIFE A1-30 RATING (FLIGHT CYCLES)” for BRH10048 and BRH19253 from 33,000 to 25,000 flight cycles (Requirement 1). This is a specific editorial and technical change to a named TLM subtask.

• Amend other references: Operators must amend any other reference that quotes the maximum approved life for those parts when installed in BR700-715A1-30 engines operating under the Hawaiian Flight Mission to reflect the new 25,000 flight cycle limit (Requirement 2). That creates a duty to search for and correct other documents, manuals or records that may still quote the higher number.

• Check LLP Tracking Sheet: Operators must check the LLP Tracking Sheet for the two part numbers if the relevant disc is currently or previously installed in the BR700-715A1-30 engine and operated under the Hawaiian Flight Mission, using TLM TASK 05-00-01-800-001 as the recording and control reference (Requirement 3).

• Update pro rata calculations and complete LLP Tracking Sheet entries: If the relevant discs have been installed in the specified engine/mission combination, operators must update all pro rata calculations and complete the LLP Tracking Sheet entries for the discs using the revised 25,000 flight cycle limit (Requirement 3.a). This duty is to recalculate consumed life and to bring records into conformity with the new DSCL.

• Reject discs where consumed life exceeds the revised DSCL: If, after updating records, the consumed life exceeds 25,000 flight cycles, operators must reject the disc (Requirement 3.b(ii)). The AD provides a clear operational consequence tied to the tracking check and recalculation duties.

Conditional rights or exemptions (explicit)

• No further action where not applicable: If the LLP Tracking Sheet check shows that the disc has not been and is not currently installed in a BR700-715A1-30 engine operating under the Hawaiian Flight Mission, the AD states “no further action in accordance with this AD is required” (Requirement 3.a(i)). That language functions as a conditional exemption, limiting the scope of mandatory action to discs with the specified installation history.

Administrative bounds and timing

• Use of prescribed TLM tasks for recording and control: The AD directs operators to TLM TASK 05-00-01-800-001 for recording and control of the lives of parts. That creates a duty to use the identified procedural framework for updating and controlling LLP records (Requirement 3).

• Timing: All required actions must be completed no later than 100 flight cycles after the AD’s effective date (Compliance). This timing is a duty to act within a short window; it imposes an operational scheduling requirement on affected operators and recordkeepers.

Rights not expressed

• The AD does not specify a process for appeal, variation, or alternative means of compliance within the provided text. The AD does not set out any approvals or waivers for operators seeking different mitigations within its body. The only procedural flexibility the AD itself contains is the “If NO, no further action” conditional.

Documentary duties and evidentiary effect

• Record amendments and calculations: The AD’s instructions to amend the TLM and the LLP Tracking Sheet mean affected parties must create documentary evidence of the change and the steps taken, consistent with the referenced TLM tasks. The AD thus creates documentary duties that will support any oversight or audit activity.

In sum, the AD places clear, time-bound duties on operators and maintenance/recordkeeping personnel to alter manuals and records, recompute life consumption, and remove discs that exceed the revised DSCL, while giving a small, explicitly stated exemption where no relevant installation history exists.

The AD text supplied does not specify penalties, enforcement mechanisms, or sanctions within its own wording. The document sets out requirements, an effective date, and a compliance timeframe, but it does not contain language describing civil penalties, criminal sanctions, enforcement procedures, or the identity of enforcement authorities beyond the issuer’s signature. Relevant textual points are:

• The AD requires actions (amend TLM, amend other references, check and update LLP Tracking Sheets, reject parts where overconsumed) and sets a compliance deadline “No later than 100 flight cycles after the effective date of this AD” (Compliance). The AD becomes effective on 11 May 2007 (Compliance).

• The AD is issued under the authority of the Civil Aviation Safety Authority, evidenced by the signature block naming Charles Lenarcic as “Delegate of the Civil Aviation Safety Authority” (signature block). The presence of a CASA delegate name indicates the issuing authority, but the AD itself does not state enforcement steps.

• The AD references an EASA Emergency AD 2007-0116-E dated 4 May 2007 (Requirement Note 2). That cross-reference demonstrates regulatory alignment, but the AD text does not incorporate EASA’s enforcement text nor any specific enforcement sanctions.

What the supplied text does not specify

• No statutory penalty clauses: The supplied AD does not include penalties for non-compliance, nor does it set out the regulatory or administrative process by which non-compliance would be detected, adjudicated, or sanctioned.

• No inspection or audit process described: The AD does not include procedures for how CASA (or any other body) will verify compliance, such as mandatory reporting, submission of amended TLM pages, or mandatory certification of completed checks.

• No variation or alternative compliance route included: The supplied text contains no provision for alternative means of compliance, waivers, or extensions.

Practical consequences of these absences (as described in the source)

• The AD’s duties (amend manuals, check records, reject components) are clear and time-limited; the absence of specified penalties in the AD itself does not negate the practical necessity to comply. The AD’s authority derives from its status as an airworthiness directive issued by CASA (signature block). Operators relying on the AD will need to assume that aviation safety oversight will assess compliance against the AD through ordinary regulatory oversight channels even though the AD text does not itself specify penalties.

• The AD’s cross-reference to an EASA Emergency AD may imply that similar obligations and enforcement approaches exist under EASA’s regime; however, the supplied text does not transcribe or adopt EASA’s enforcement measures.

In short, the AD establishes mandatory technical and recordkeeping obligations within a short compliance window, but the supplied AD text does not set out the sanctions or the enforcement process for failure to meet these obligations. The AD should therefore be read in conjunction with the broader statutory and regulatory framework governing CASA’s enforcement powers, which is not contained in the provided text.

The supplied AD text contains limited, explicit references to other regulatory documents and procedural materials; these define the principal interactions:

• EASA Emergency AD 2007-0116-E: The AD expressly states “Note 2: EASA Emergency AD 2007-0116-E dated 4 May 2007 refers” (Requirement Note 2). This is an explicit cross-reference to a European Aviation Safety Agency emergency directive that pre-dates the CASA AD by a week. The reference signals regulatory alignment or reliance on EASA’s emergency finding as the underlying technical trigger. The supplied AD does not reproduce EASA’s text, but it uses EASA’s AD as a supporting or referenced instrument.

• Time Limits Manual (TLM) tasks: The AD mandates amendments to a specific TLM subtask, SUBTASK 05-10-01-860-016, and directs operators to use TLM TASK 05-00-01-800-001 for recording and control of the lives of parts (Requirement 1; Requirement 3). These TLM tasks are internal regulatory/maintenance instruments that interact with the AD by serving as the procedural mechanism for implementing the AD’s requirements. The AD’s instruction to amend and to use particular TLM tasks binds operators to a defined documentary and procedural framework.

• Post Certification Life Statement and 3D FEM modelling: The Background states that “The most recent 3D FEM modelling has resulted in the need to reconsider the disc lives ... The current Post Certification Life Statement for the Low Pressure (LP) Compressor (Fan) Disc Assembly revises the Declared Safe Cyclic Life (DSCL) from 33000 flight cycles to 25000 flight cycles” (Background). This interaction is technical rather than legal, but it indicates that the AD adopts a change in manufacturer or certification documentation (the Post Certification Life Statement) that resulted from engineering analysis (3D FEM). The AD thus interacts with manufacturer certification statements and engineering analyses which underpin approved life limits.

• Applicability to documented aircraft and engines: The Applicability block lists Rolls-Royce Deutschland BR700-715A1-30, BR700-715B1-30 and BR700-715C1-30 engines, and notes these engines are known to be installed on Boeing 717 aircraft (Applicability). This situates the AD within the broader airworthiness requirements that tie engine and airframe approvals together; however, the AD’s operative reduction in life is explicitly limited to the BR700-715A1-30 model under the Hawaiian Flight Mission (Requirement 1; Requirement 2). The AD thereby interacts with aircraft operator obligations dependent on the engine/airframe combination and the mission profile.

• Time-limited compliance: The AD sets a compliance deadline of “No later than 100 flight cycles after the effective date of this AD” and an effective date of 11 May 2007 (Compliance). That timing interacts with operational scheduling and maintenance planning obligations incumbent on operators under general airworthiness rules.

Limits of the text’s interaction statements

• The AD does not explicitly incorporate or amend primary legislation or state statutory instruments in the supplied text. It does not identify specific statutory sections or broader regulatory instruments beyond the named TLM tasks and the EASA AD. The AD’s legal force is implicit from its status as a CASA-issued AD (signature block), but the supplied text does not elaborate the statutory basis or conflict resolution mechanisms if other documents differ.

• The AD does not specify how it should be reconciled with other operators’ manuals, continuing airworthiness management instructions, or alternative certified practices; instead it instructs operators to amend any other references quoting the previous maximum where relevant (Requirement 2).

In practice, the AD interacts with manufacturer certification documentation, TLM procedures, the EASA emergency measure, and an operator’s maintenance and life-tracking systems. The supplied text does not set out the broader legal regime for enforcement or dispute resolution; it limits itself to the cross-references quoted above.

The supplied AD text itself records a specific, one-off change to component life limits, but contains no prior amendment trail within the document. What the text provides relevant to amendment history is:

• The AD’s own effective date and issuance: The AD “becomes effective on 11 May 2007” and is dated with a delegate’s signature recorded as 8 May 2007 (Compliance; signature block). This establishes the AD’s date of effect and issuance.

• The technical origin of the change: The Background explains that “The most recent 3D FEM modelling has resulted in the need to reconsider the disc lives as currently show[n] in the Time Limits Manual” and that the “current Post Certification Life Statement ... revises the Declared Safe Cyclic Life (DSCL) from 33000 flight cycles to 25000 flight cycles” for the specified part numbers when installed in the BR700-715A1-30 engine model and operated against the Hawaiian Flight Mission (Background). That language confirms that the AD’s substantive amendment is the operationalisation of a Post Certification Life Statement driven by new engineering analysis.

• The AD’s explicit amendment instruction: The Requirement block requires amending the TLM SUBTASK 05-10-01-860-016 and any other references quoting the previous maximum approved life (Requirement 1; Requirement 2). The AD thus functions as an administrative direction to amend existing operator and maintenance documentation.

What the supplied text does not contain

• No record of prior ADs altering these specific life limits is provided in the text. The AD refers to a prior DSCL (33,000 flight cycles) and states the new DSCL (25,000), but it does not include a history of when the 33,000 number was adopted or any prior amendments to that value within the TLM or certification records.

• No subsequent amendments to this AD are recorded in the text. The AD itself is the issuing instrument without recorded later changes or variations.

Implications that follow from what is recorded

• The AD formalises a change arising from manufacturer or certification documentation (Post Certification Life Statement) updated after 3D FEM analysis. It is an implementing instrument that requires document-level amendments across the TLM and any other relevant references.

• Operators will need to treat the AD as the effective amendment direction as of 11 May 2007 and must make the specified textual changes in their TLM and related materials within the 100 flight-cycle compliance window.

• The procedural references (SUBTASK 05-10-01-860-016 and TASK 05-00-01-800-001) indicate the precise administrative locations where the amendments must be recorded; the AD thus creates a traceable record of amendment to the TLM and to LLP tracking records that can be evidenced by updated task pages and tracking sheet entries.

In short, the AD is the operative amendment instrument. The supplied text documents the technical basis (3D FEM and Post Certification Life Statement) and prescribes the exact TLM tasks and tracking sheets to amend, but it does not include a longer amendment or revision history beyond the DSCL change it implements and the date it becomes effective.

The AD text itself does not mention any litigation, challenges, appeals, or disputes. There is no litigation history recorded within the supplied document. Relevant textual points are:

• The AD contains a technical mandate, a compliance timeline and a cross-reference to an EASA Emergency AD, but it does not record any legal challenges or proceedings in respect of the AD’s issuance (full text).

• The signature block identifies the issuing delegate (“Charles Lenarcic, Delegate of the Civil Aviation Safety Authority”) and the date of signature (8 May 2007), but includes no references to judicial or administrative reviews, stays, or injunctions.

What the absence of litigation statements in the text implies within the scope of the supplied source

• The AD is presented as an authoritative regulatory instrument without recorded dispute within the text. The document does not purport to be subject to litigation nor does it include contested findings.

• Because the supplied text contains no litigation references, there is no source-grounded basis in this document to report on any judicial or administrative outcomes, interim relief, or jurisdictional disputes. Any commentary about litigation risk, potential challenges to the technical basis, or enforcement proceedings would be outside the document’s explicit content.

Operational relevance for affected parties

• Affected operators must proceed on the basis of the AD’s mandates and compliance deadline. The absence of litigation in the text does not provide a legal basis to withhold compliance or to assume that a challenge exists; the AD is effective on its stated date and contains mandatory instructions.

• If operators or their legal counsel seek to contest an AD in jurisdictional proceedings, that process is not recorded in this text and would need to be pursued and documented outside the AD itself. The supplied text does not provide procedural directions for such contestation.

In summary, the document records no litigation history. It stands as an implementing regulatory order dated and signed by a CASA delegate, and affected parties should treat it as an operative directive in the absence of any recorded judicial or administrative stay or variation in this text.

The AD’s brevity and technical focus create several practical pitfalls that operators and maintainers should note precisely as stated in the source:

• Narrow but consequential applicability: The life reduction applies only to BR715 LP Compressor (Fan) Disc Assembly Part Nos BRH10048 and BRH19253 “when installed in the BR700-715A1-30 engine model and operated under the Hawaiian Flight Mission” (Requirement 1; Requirement 2; Background). Operators who read the Applicability block (which lists BR700-715A1-30, -B1-30 and -C1-30 engines and notes installation on Boeing 717 aircraft) without closely reading the Requirement and Background could misapply the life change to other engine variants or missions. The AD’s operative limitation is both engine-variant and mission-profile specific, and that specificity is essential.

• Historical installations matter: The Requirement instructs a check of the LLP Tracking Sheet “if the relevant BR715 LP Compressor (Fan) Disc Assembly is currently or has previously been installed in the BR700-715A1-30 engine model and operated under the Hawaiian Flight Mission” (Requirement 3). This captures past installations as well as current ones. A disc removed from an engine but later re-established into inventory may still be subject to the revised life if it has the relevant service history. Operators who only check current installations, and not historical records, risk missing affected parts.

• Short compliance window: The AD requires completion “No later than 100 flight cycles after the effective date of this AD” (Compliance), with the AD effective on 11 May 2007 (Compliance). A 100 flight-cycle window is short in operational terms; parts already close to the older DSCL could, after pro rata recalculation, immediately exceed the new DSCL and require removal. Operators must prioritise the mandated checks and calculations quickly to avoid inadvertent operation beyond 25,000 cycles.

• Pro rata calculation complexity: The AD requires operators to “up-date all pro rata calculations” and complete LLP Tracking Sheet entries “using the revised Hawaiian Flight Mission maximum approved life of 25000 flight cycles” (Requirement 3). Pro rata calculations may involve combining multiple mission profiles, partial lives or transfers between engines; operators must ensure the calculations are performed consistently with applicable TLM TASK 05-00-01-800-001 procedures, which the AD references for recording and control.

• Documentation consistency risk: Requirement 2 obliges operators to “Amend any other Reference, where the maximum approved life is quoted for” the parts when installed in the BR700-715A1-30 and operated under the Hawaiian Flight Mission. This requires a thorough search for all manuals, service bulletins, inventory records, and other documents that might still quote the 33,000 cycle figure. Failure to amend all references could produce inconsistent records and compliance confusion.

• Immediate operational consequences if overconsumed: The AD requires rejection of the relevant BR715 LP Compressor (Fan) Disc Assembly if, after updating tracking using 25,000 cycles, “their consumed life has exceeded the maximum approved life of the Flight Mission currently installed” (Requirement 3.b(ii)). Operators whose tracking records are close to the limit risk immediate asset rejection and operational disruption if they do not plan for timely replacements.

• Implicit reliance on Post Certification Life Statement and 3D FEM results: The Background links the DSCL change to recent 3D FEM modelling and a Post Certification Life Statement (Background). The AD depends on those technical statements but does not include detailed modelling results or the Post Certification Life Statement in the text. Operators may need to obtain those underlying documents to understand the technical basis for the change and to inform maintenance planning.

• Cross-jurisdictional reference: The AD cites an EASA Emergency AD (Requirement Note 2). Operators who maintain fleets or parts across jurisdictions should ensure they handle the differing regulatory references correctly and record that CASA’s AD mirrors or references an EASA emergency action.

• No stated alternatives or waivers in the AD: The text offers no explicit alternative compliance pathway or waiver process. The only conditional relief the AD provides is where a check shows no applicable installation history (Requirement 3.a(i)). Entities seeking alternative mitigations or extensions cannot find a process for such relief in the text.

These “gotchas” are concrete, document-grounded traps. Each flows from the AD’s precise language, the mission-specific scope, and the AD’s process-oriented instructions for TLM and LLP tracking amendments within a short compliance horizon.

The AD prescribes a concise, document-centred compliance procedure. Below is a practical, source-grounded checklist that reproduces the AD’s mandatory steps in operational order, with references to the specific tasks named in the AD.

1. Determine applicability to your inventory and operations

   • Identify all BR715 LP Compressor (Fan) Disc Assembly Part Nos BRH10048 and BRH19253 in your fleet or stores (Applicability).
   • For each such disc, determine whether it is currently installed in, or has previously been installed in, a BR700-715A1-30 engine model and whether it was operated under the Hawaiian Flight Mission (Requirement 3). Historical installation must be considered.

2. Prioritise timing

   • Note the AD’s effective date (11 May 2007) and the compliance deadline: all required actions must be completed no later than 100 flight cycles after the effective date (Compliance).
   • Prioritise checks and documentation updates immediately to meet this short window.

3. Amend the Time Limits Manual (TLM)

   • Update TLM SUBTASK 05-10-01-860-016 to revise the “GIVEN LIFE A1-30 RATING (FLIGHT CYCLES)” for BRH10048 and BRH19253 from 33,000 to 25,000 flight cycles (Requirement 1).
   • Ensure the amended TLM page is controlled and recorded according to your document control procedures, and reference the AD in the amendment record to provide an audit trail.

4. Amend any other references quoting the old DSCL

   • Search and amend any other manuals, service documents, maintenance schedules, inventory records or references where the maximum approved life for the two part numbers is quoted for the BR700-715A1-30 engine model under the Hawaiian Flight Mission (Requirement 2).
   • Update electronic and hard-copy records to ensure consistency.

5. Check LLP Tracking Sheets using the prescribed task

   • For any disc currently or previously installed in BR700-715A1-30 engines operated under the Hawaiian Flight Mission, check the LLP Tracking Sheet. The AD directs you to TLM TASK 05-00-01-800-001 for recording and control of part lives (Requirement 3).
   • If the LLP Tracking Sheet or historical records show no installation under the specified engine/mission combination, the AD states no further action is required for that disc (Requirement 3.a(i)).

6. Update pro rata calculations and LLP records

   • Where relevant (i.e., the disc has been or is installed in the specified engine/mission), update all pro rata calculations and complete the LLP Tracking Sheet entries using the revised maximum approved life of 25,000 flight cycles (Requirement 3.a(ii)).
   • Ensure that the recalculation and the method used are transparent and recorded in compliance files.

7. Determine consumed life and act if necessary

   • After updating pro rata calculations, determine whether the consumed life of the disc has exceeded the revised 25,000 flight cycles (Requirement 3.b).
   • If consumed life exceeds 25,000 flight cycles, reject the relevant BR715 LP Compressor (Fan) Disc Assembly (Requirement 3.b(ii)). Record the rejection and subsequent parts disposition in accordance with your LLP control procedures.

8. Recordkeeping and audit trail

   • Keep documentary evidence of the TLM amendment, the search and amendment of other references, the LLP Tracking Sheet checks, the pro rata recalculations, and the rejection(s) where applicable. The AD directs use of TLM TASK 05-00-01-800-001 for recording and control (Requirement 3).
   • Where the AD returns an “If NO, no further action” result, keep a record demonstrating the check outcome and why no further action was required (Requirement 3.a(i)).

9. Coordinate with regulators and technical authorities

   • The AD was issued by a CASA delegate (signature block). While the AD text does not set out an explicit reporting requirement, best practice is to make the amended TLM pages and LLP Tracking Sheet updates available for regulatory inspection to demonstrate compliance.
   • The AD references an EASA Emergency AD (Requirement Note 2). For operators with cross-border operations, ensure you also review the EASA AD text (not contained in the supplied AD) to align with any parallel obligations.

10. Technical follow-up

• The Background notes that the DSCL change follows 3D FEM modelling and a Post Certification Life Statement (Background). Obtain and retain copies of the Post Certification Life Statement and any supporting manufacturer data if available, to support maintenance planning and to document the technical basis for the TLM changes.

11. Operational planning

• Anticipate that discs recalculated as over the revised DSCL will need replacement and plan spare parts procurement and maintenance slots accordingly within your operational timetable.
• Consider the logistical effect of any immediate rejections on aircraft dispatch reliability and maintenance scheduling.

12. Internal review and training

• Brief maintenance, planning and records staff on the changes to TLM SUBTASK 05-10-01-860-016, the need to search other references, and the process for pro rata recalculation and rejection.
• Ensure that those performing the checks are competent in using TLM TASK 05-00-01-800-001 procedures.

Following these steps, which map directly onto the AD’s Requirement paragraphs and TLM task references, will align an operator’s documentation and parts control with the AD’s mandatory instructions. The AD’s explicit conditional outcome (“If NO, no further action is required”) must be recorded where applicable to demonstrate proper execution of the required checks (Requirement 3.a(i)).