AD/TBM 700/45 Amdt 1 - Nose Landing Gear Actuator Hinge Pin

This AD is structured around a small set of concrete regulatory levers and references. First, the instrument establishes precise applicability by aircraft type, NLG part number and NLG serial number ranges. Applicability is essential because all subsequent obligations attach only if an operator’s aircraft fall within those S/N ranges and are fitted with NLG P/N 21130-001-02 (Applicability). Second, the AD delegates detailed procedural steps to an external document, EADS SOCATA Service Bulletin (SB) No. 70-147 or later EASA approved revision, and repeatedly instructs that accomplishment instructions in that SB must be followed (Requirement 1-7). The SB is therefore incorporated by reference as the source of the operational and inspection procedures.

Third, the directive uses both preventative and reactive measures. Preventative measures include adding an operational procedure to the Aircraft Flight Manual (AFM) as set out in paragraph A of the SB and instituting a prohibition on installing pins from three specific batches (Requirement 2 and 7). Reactive measures include immediate batch number identification, dimensional checks, and mandatory replacement of out-of-tolerance or defective-batch hinge pins (Requirement 3-5; Requirement 6). The AD also permits a narrowly defined remedial movement, namely special flight permits, but only to allow aircraft to reach an approved maintenance centre to conduct the required checks or replacements (Requirement 2).

Fourth, the AD embeds time-critical compliance points. The compliance table sets the majority of actions to be completed "Before further flight after the effective date of this AD" (Compliance 1-5), requires dimensional checks after certain abnormal landings (pancake or three-point) (Compliance 6), and instructs that the installation ban is effective immediately from the AD’s effective date (Compliance 7). There is a specific date reference in the compliance block that reads, in part, "Any pin from the defective batches, with satisfactory dimensional check, before3 October 2006", which imposes an explicit deadline for replacement where a pin from a defective batch initially passes the dimensional check, although the formatting in the source text is compacted and will require precise reading to interpret (Compliance 5).

Fifth, the AD connects to prior regulatory actions. It supersedes an earlier EASA AD and notes an EASA Emergency AD, signalling that the issue was the subject of prior regulatory intervention and that this amendment extends landing gear applicability relative to the original AD (Requirement note; Background). Finally, authority and signatory detail are included: the AD is issued by the CASA delegate, James Coyne, dated 6 September 2006, and recorded as effective 8 September 2006 (signature block; Compliance effective date). These elements clarify the issuing authority and effective timing of the directive.

The AD directly affects owners and operators of Aérospatiale (SOCATA) TBM 700 A and B aeroplanes that have Nose Landing Gear part number 21130-001-02 installed, where the NLG serial number is within the specified ranges B155 to B173 inclusive, and EUR 174 to EUR 240 inclusive (Applicability). For aircraft outside that NLG serial number range, the AD states explicitly that "no further action is required" following the NLG serial number verification step (Requirement 1). Therefore the universe of affected parties is tightly defined by aircraft type, the installed part number, and the NLG serial number.

Maintenance organisations and approved maintenance centres are also affected functionally. The AD allows special flight permits "to reach an approved Maintenance Centre to check the batch number and to do the pin check" (Requirement 2). That implies that maintenance centres must be prepared to receive affected aircraft, perform the SB-specified inspections and dimensional checks, identify hinge pin batch numbers, and carry out replacements in accordance with the EADS SOCATA Service Bulletin No. 70-147 or later EASA approved revision (Requirement 3-5). The AD therefore shifts obligations to operators to deliver aircraft to maintenance providers and to maintenance providers to execute the steps found in the referenced SB.

Manufacturers and suppliers of hinge pins are indirectly affected because the AD specifically bans the installation of pins from three identified defective batches on NLG P/N 21130-001-02 (Requirement 7). The three batches are listed by batch numbers EUR BC 21344-000-01, EUR BD 21344-000-01 and EUR SF 21344-000-01. Anyone supplying or installing hinge pins for these NLGs must ensure pins are not from these batches.

Regulatory bodies that coordinate ADs, notably EASA as referenced in the AD, are implicated by the cross-reference and supersession language. The AD references EASA Emergency AD 2006-0271-E and states it supersedes EASA AD 2006-0226-E (Requirement note). This indicates interplay between CASA and EASA on the same technical unsafe condition; however the document is a CASA AD, so Australian operators must comply per CASA’s directive.

Aeroplane flight crews and their operators will incur operational impacts. The AD requires incorporation of an operational procedure into the AFM where the NLG S/N is applicable, as detailed in paragraph A of the SB (Requirement 2). That compels changes to operating documentation and procedures for affected aircraft.

Financially, the AD places the immediate costs of inspection, dimensional checks, part identification, potential replacement of hinge pins, and any consequential maintenance or downtime on aircraft owners and operators and, where relevant, maintenance organisations. The text does not specify cost-sharing or compensation, nor does it specify penalties for non-compliance; it sets out required technical and procedural actions. Finally, insurers may be indirectly affected by clauses addressing airworthiness and mandatory rectification, but the AD itself does not address insurance matters.

The AD sets out a discrete set of mandatory duties for affected operators and maintenance organisations, and qualifies one specific operational right, namely limited special flight permits.

Duties

• Verify applicability: Operators must verify the NLG serial number to determine whether the AD applies. The AD instructs, "If the NLG S/N is not listed in the applicability section of this AD no further action is required" (Requirement 1). This creates an initial verification duty.
• Incorporate an AFM procedure: For aircraft with an applicable NLG S/N, the operator must "incorporate the operational procedure as detailed in paragraph A of the accomplishment instructions of EADS SOCATA Service Bulletin No. 70-147 or later EASA approved revision into the AFM" (Requirement 2). This is an explicit documentation and operational duty.
• Identify pin batch number: Operators or maintenance providers must identify hinge pin batch numbers as instructed in paragraph B of the SB (Requirement 3). This is a traceability and inspection duty.
• Perform dimensional checks: The AD requires a dimensional check on any hinge pin listed in the SB (Requirement 6). The AD also requires dimensional checks after specified abnormal landings (Compliance 6).
• Replace defective or out-of-tolerance pins: The AD mandates replacement of pins according to the SB, and specifically mandates replacement for any out-of-tolerance pin before further flight (Requirement 5; Compliance 5).
• Prohibition on installation: From the effective date of the AD, installing hinge pins from the three named defective batches on NLG P/N 21130-001-02 is forbidden (Requirement 7; Compliance 7).

Rights and permitted actions

• Special flight permits: The AD provides that special flight permits may be issued for aircraft fitted with the applicable NLG S/N to reach an approved maintenance centre "to check the batch number and to do the pin check" (Requirement 2). This is a limited operational right that allows movement of aircraft that might otherwise be grounded, but only for the specific purpose of obtaining the mandated inspections and repairs.

Procedural delegation and cross-reference

• Use of EADS SOCATA SB: The AD repeatedly refers to the EADS SOCATA Service Bulletin No. 70-147 or later EASA approved revision for the detailed steps (Requirement 1-6). That delegates the procedural content of inspections, checks, and replacements to the SB document. Compliance requires following the SB paragraphs cited (for example paragraph A for AFM procedure, paragraph B for batch identification, and paragraphs B5, C & D for actions where the batch is defective or unreadable).

Timing duties

• Immediate compliance windows are specified: The AD lists most required actions to be completed "Before further flight after the effective date of this AD" (Compliance items 1-5), reflecting an immediate safety imperative. There is also a direction to perform dimensional checks after any "Pancake" or "three-point" landing (Compliance 6).

Record-keeping and evidence

• While the AD does not explicitly prescribe record-keeping formats in the text provided, compliance necessarily requires evidence: verification of NLG S/N, batch number identification, dimensional check results, any replacements performed, and AFM amendments. These evidentiary items will be necessary to demonstrate compliance should an inspector or regulator request substantiation.

Limits and omissions

• The AD does not specify civil penalties, enforcement mechanisms, or appeal processes in the text provided. It also does not set out who is responsible for costs. Therefore, where rights, penalties or appeal routes might otherwise be expected, the AD is silent and operators must treat the AD’s technical prescriptions as mandatory operational duties under CASA’s regulatory authority.

The AD text supplied does not specify civil or criminal penalties, nor does it detail enforcement procedures, administrative review or appeal mechanisms. The document sets out technical requirements and compliance timelines but does not attach explicit sanctions within the text for non-compliance (Compliance; Requirement). As a CASA Airworthiness Directive, the instrument functions as a mandatory safety measure; the AD itself therefore expresses required actions and timing, but the text provided contains no separate penalties or enforcement clauses.

Enforcement implications that follow from the AD’s structure and issuer

• Issuing authority: The AD is issued under CASA authority, and is signed by a CASA delegate, James Coyne, dated 6 September 2006, with the AD effective date 8 September 2006 (signature block; Compliance effective date). That establishes the AD as an official CASA instrument, which in practice means CASA may take regulatory enforcement action for non-compliance, though the text does not set out those powers.
• Compliance evidence: The AD requires operators to carry out specific inspections, dimensional checks and replacements. To demonstrate compliance to CASA, operators and maintenance organisations will need to retain records showing that the serial number verification, batch identification, AFM amendment, dimensional checks and replacements were completed in accordance with the referenced SB and within the stated timeframes. The AD does not specify the form, retention period, or particular record-keeping requirements.

Operational enforcement levers

• Grounding and permission to fly: The AD ties many of its actions to pre-flight status, repeatedly directing that certain steps must be completed "Before further flight after the effective date" (Compliance 1-5). This creates a practical enforcement lever: an aircraft that has not complied would be considered non-conforming for the purposes of airworthiness and should not be flown, except under the narrowly defined special flight permit purpose described in the AD (Requirement 2). The AD does not provide the mechanics for how a permitted non-compliant flight is authorised beyond the statement that special flight permits may be issued to reach a maintenance centre.

Third-party obligations and market enforcement

• Maintenance centre obligations are implicit: the AD requires certain maintenance actions to be performed according to the SB. If maintenance organisations perform these tasks, they will produce documentary evidence of compliance. The AD does not specify reporting obligations back to CASA or to the manufacturer in the text provided.

Absence of monetary penalties or criminal sanctions in text

• The instrument includes no clause specifying fines, penalties, suspension of certificates, or criminal liability for failure to comply. Any such consequences must be inferred from the broader statutory framework under which CASA operates; they are not enumerated in this AD text.

In short, the AD prescribes mandatory technical measures and deadlines, references industry-standard accomplishment instructions, and provides a narrow right to special flight permits. It does not itself spell out enforcement procedures, monetary penalties or appeal pathways in the text provided; CASA’s broader enforcement powers and practice would determine how non-compliance is addressed in practice, but those powers are not described here.

The AD explicitly references European Aviation Safety Agency (EASA) actions and the EADS SOCATA Service Bulletin, creating a regulatory and technical cross-linking structure. The AD states that EASA Emergency AD 2006-0271-E is referred to, and that this AD supersedes EASA AD 2006-0226-E (Requirement note). Therefore the CASA instrument is operating in parallel with, and in response to, corresponding EASA directives addressing the same unsafe condition. The AD also relies on an EADS SOCATA Service Bulletin No. 70-147 or later EASA approved revision for the detailed consequences and technical procedures (Requirement 1-6), effectively importing the SB into the AD as the procedural standard.

Interplay with airworthiness and maintenance regulatory regimes

• The AD prescribes specific technical actions that must be completed and ties many of them to pre-flight status. That aligns with standard airworthiness regulatory practice where ADs require corrective action to maintain the aircraft’s airworthiness. The AD does not, in the text provided, explicitly state how compliance is to be recorded against airworthiness certificates or maintenance release processes, but operators will need to ensure that maintenance records, AFM amendments, and release-to-service documentation reflect compliance with the AD and the referenced SB.

Incorporation by reference and standards harmonisation

• The AD’s repeated reference to EADS SOCATA Service Bulletin No. 70-147 or a later EASA approved revision means that the technical standard to be followed is the SB, possibly as updated by future EASA-approved revisions. This creates a mechanism by which procedural detail is harmonised with the manufacturer’s guidance and with EASA’s approvals, supporting consistency across jurisdictions. The AD also ties into EASA corrective actions by referencing the EASA Emergency AD and superseded EASA AD. That indicates coordination or harmonisation rather than conflicting directives.

Absence of explicit interaction with non-aviation laws

• The AD text does not reference or interact with workplace health and safety statutes, contract law, consumer protection law, tariff or import/export restrictions, or insurance law. While those laws may be indirectly implicated in practice (for example, maintenance work may trigger workplace health and safety obligations), no such cross-references appear in the AD itself.

No explicit mention of civil aviation enforcement or appeals

• The AD does not set out enforcement actions, fines, or administrative appeal rights, nor does it detail how CASA will monitor compliance. Accordingly, specific procedural interactions with administrative law, like review or merits appeal of CASA decisions, are not addressed in this text.

Operational and supply-chain interactions

• By banning installation of hinge pins from specified batches, the AD affects procurement and supply chain decisions. Suppliers and maintenance organisations must ensure that replacements are not from the banned batches. This creates an interaction with commercial contracts, parts traceability and supplier verification, although such commercial law interactions are implied rather than described.

In summary, the AD interacts directly with EASA instruments and with the manufacturer’s service bulletin. It implicitly interacts with the domestic airworthiness and maintenance compliance framework administered by CASA, but it does not explicitly lay out cross-references to other statutes, enforcement mechanisms, or administrative review pathways in the provided text.

The document provided is an amendment to an existing Airworthiness Directive. Key points in the amendment history that appear in the text are:

• Original AD effective date: The original issue of this AD "became effective on 26 July 2006" (Background). That original AD preceded this amendment and established an earlier scope of action.
• This amendment effective date: The amendment described in the supplied document is effective 8 September 2006. The Compliance block explicitly states "This Amendment becomes effective on 8 September 2006" and the signatory block is dated 6 September 2006 (Compliance; signature block).
• Supersession and reference to EASA ADs: The AD text notes that it "supersedes EASA AD 2006-0226-E" and refers to "EASA Emergency AD 2006-0271-E dated 4 September 2006" (Requirement note). That indicates the CASA AD was adjusted to reflect subsequent EASA emergency actions and to replace an earlier EASA AD cited in the original issue.
• Scope extension in amendment: The Background expressly states that "This amendment is issued to extend the landing gear applicability as listed in the original issue of this AD" (Background). That means the amendment broadens the set of NLG serial numbers or landing gear items to which the AD applies, relative to the original July 26, 2006 issue. The exact extension is signalled by the updated Applicability block which lists NLG S/N ranges B155 to B173 inclusive and EUR 174 to EUR 240 inclusive.
• Reason for amendment: The reason underlying the AD and its amendment remains the same safety concern: a reported NLG hinge pin rupture caused an uncommanded NLG retraction, and investigations found incomplete thermal treatment in three hinge pin batches that reduced mechanical properties and increased the risk of deformation under load (Background). The amendment preserves the core corrective measures while extending applicability.
• Procedural continuity: The AD continues to require adherence to EADS SOCATA Service Bulletin No. 70-147 or later EASA-approved revisions; the amendment does not replace the SB reference with another document, but it may rely upon updated SB revisions as they become EASA approved (multiple Requirement references).

No other amendment iterations are listed in the source provided. The AD therefore shows a short initial history: an original AD effective 26 July 2006, followed by Amendment 1 effective 8 September 2006 that expands applicability and references subsequent EASA emergency action, all in response to an identified hinge pin manufacturing/process defect.

The text of the AD supplied contains no litigation history. There are no references to court challenges, administrative appeals, or judicial review of the AD in the document. It names no judicial decisions and cites no cases. The only legal or regulatory cross-references in the AD are to EASA Emergency AD 2006-0271-E and EASA AD 2006-0226-E, which are regulatory instruments rather than judicial rulings (Requirement note). The AD itself is an administrative instrument issued by CASA, signed by a delegate, James Coyne, but the text includes no record of litigation, disputes, or challenges to its validity.

Given the absence of litigation material in the source, there is nothing in the AD to summarise about court findings, stays, injunctions, or settlements. Any legal contests arising from this AD, whether pertaining to compliance costs, grounding of aircraft, or the propriety of the amendment, are not referenced in the provided text.

The AD contains a number of technical, timing and textual details that create operational pitfalls if read or applied hurriedly. These are practical "gotchas" directly grounded in the text.

1. Applicability is narrow, but initial verification is mandatory

• The AD applies only to TBM 700 A and B aircraft fitted with NLG P/N 21130-001-02 with NLG S/N in very specific ranges (B155-B173 and EUR 174-EUR 240). However, the AD places the initial duty on operators to "Verify the NLG serial number to determine its applicability to this AD" (Requirement 1). Failure to perform that serial number check could mean accidentally overlooking applicability and therefore failing to comply with mandatory actions.

2. Procedural detail is in the Service Bulletin

• The AD repeatedly defers technical steps to EADS SOCATA SB No. 70-147 or later EASA approved revision (Requirement 1-6). If an operator does not have immediate access to the correct SB revision or misunderstands which "later EASA approved revision" is applicable, they might execute incorrect procedures. The AD’s compliance depends on following the paragraph references in the SB (for example paragraph A, B, B5, C & D), so not possessing or misapplying the SB is a practical risk.

3. Special flight permits are narrowly justified and limited

• The AD allows special flight permits only "to reach an approved Maintenance Centre to check the batch number and to do the pin check" (Requirement 2). Using a special flight permit for other purposes would not be authorised by the AD and could expose operators to regulatory action.

4. Ambiguity / formatting on the temporal requirement for pins that pass dimensional check

• The Compliance block contains a compacted sentence fragment that reads: "Any out of tolerance pin, before further flight after the effective date of this AD.Any pin from the defective batches, with satisfactory dimensional check, before3 October 2006." The lack of spacing ("before3") and the compressed punctuation introduces an interpretive glitch. The likely reading is that any pin from the defective batches that is apparently within dimensional tolerance still required replacement by 3 October 2006, but the text as presented requires careful reading and cross-checking with the SB and any EASA guidance to confirm. Operators should treat the deadline as strict and seek clarification if necessary.

5. After abnormal landings, immediate action required

• The AD commands a dimensional check after any "Pancake" or "three-point" landing (Compliance 6). Failure to do so immediately could mean continuing to operate an aircraft with a potentially compromised pin. Operators must have a process to trigger and complete that dimensional check after such landings.

6. Installation ban from effective date

• From the effective date, the AD forbids installation of pins from the three defective batches on NLG P/N 21130-001-02 (Requirement 7; Compliance 7). This is an absolute prohibition in the text, and a parts procurement or maintenance team must ensure traceability and inventory segregation to avoid accidentally installing banned batch parts.

7. Responsibility allocation not spelled out for costs and records

• The AD is silent on who pays for inspections, parts, or maintenance downtime, and it does not specify the required form or retention period for records. Practitioners should not assume cost-sharing or the absence of record-keeping obligations; CASA expects compliance and evidence of compliance even if the AD does not detail documentation formats.

8. Supersession and cross-jurisdictional referencing

• The AD supersedes an earlier EASA AD and refers to an EASA Emergency AD. This interconnection could create administrative complexity for operators operating internationally, particularly if the EASA documents differ in timing or detail. Operators should compare the SB, the CASA AD and the referenced EASA ADs to ensure consistent compliance.

9. The AD’s direct language may require reading the SB for crucial definitions

• Terms like "operational procedure" (to be incorporated into the AFM) and exact dimensional tolerances are not in the AD text and are instead in the SB. Misunderstanding those SB definitions or failing to correctly incorporate the AFM change could lead to non-compliance.

10. Narrow technical focus, broad operational consequences

• Although the AD is narrowly targeted at one hinge-pin issue, its requirements can ground aircraft until inspections and replacements are completed. The AD’s multiple "Before further flight" requirements create the risk of unexpected aircraft downtime if operators do not have inventory of permitted replacement parts or ready access to maintenance centres capable of performing the SB tasks.

In short, precise serial number verification, strict adherence to the referenced SB, attention to the unusual deadline formatting, strict prohibition on use of specified batches, and readiness to react to abnormal landings are the main operational pitfalls that the AD itself creates or highlights.

This AD prescribes a step-by-step compliance pathway; the following checklist is grounded in the AD text and identifies the actions needed, the documents to consult, timing constraints and practical notes for execution.

1. Immediate serial number verification

• Action: Verify the NLG serial number on each TBM 700 A or B to determine whether it is within the AD’s applicability ranges: B155 to B173 inclusive and EUR 174 to EUR 240 inclusive, and confirm the installed NLG part number is P/N 21130-001-02 (Applicability; Requirement 1).
• Timing: Before further flight after the effective date the AD, for each affected aircraft (Compliance 1).
• Note: If the NLG S/N is not listed, the AD states "no further action is required" for that aircraft (Requirement 1).

2. Acquire the correct Service Bulletin revision

• Action: Obtain EADS SOCATA Service Bulletin No. 70-147 or the later EASA approved revision that applies at the time of compliance. Identify paragraph A (AFM procedure), paragraph B (batch identification), paragraph B5 and paragraphs C & D (actions for defective or unreadable batch numbers), and the detailed dimensional criteria and replacement instructions (multiple Requirement references).
• Timing: Prior to commencing the inspections or AFM changes, and kept on file as the procedural basis for work.

3. Incorporate AFM operational procedure

• Action: For aircraft with an applicable NLG S/N, incorporate the AFM operational procedure as detailed in paragraph A of the SB into the AFM (Requirement 2).
• Timing: Before further flight after the effective date (Compliance 2).
• Documentation: Record the AFM amendment and the date of incorporation in maintenance records; maintain the SB reference as the authority.

4. Obtain or authorise a special flight permit where necessary

• Action: If the aircraft cannot reach an approved maintenance centre by other means, seek and obtain a special flight permit specifically to reach an approved maintenance centre to check batch numbers and perform pin checks, as the AD permits special flight permits for that limited purpose (Requirement 2).
• Note: Special flight permits are only authorised to reach maintenance for compliance actions, not for normal operations.

5. Identify hinge pin batch numbers

• Action: As instructed in paragraph B of the SB, identify the hinge pin batch numbers on the NLG hinge pins (Requirement 3).
• Timing: Before further flight after the effective date, for aircraft with applicable NLG S/N (Compliance 3).
• If batch number is legible and not among listed defective batches, follow SB return-to-service instructions (Requirement 3).

6. Deal with defective or unreadable batch numbers per SB

• Action: For pins from the defective batches, or where the batch number is unreadable, follow the specific actions in paragraph B5 and paragraphs C & D of the SB, which will include replacement and any additional checks (Requirement 4).
• Timing: These actions are required "Before further flight after the effective date" (Compliance 4).
• Practical note: If the batch number is unreadable, do not assume the pin is satisfactory; follow SB-prescribed procedures for unreadable batch identification and rectification.

7. Dimensional checks and post-landing checks

• Action: Perform dimensional checks on hinge pins listed in the SB as required (Requirement 6). Additionally, perform a dimensional check after any "Pancake" or "three-point" landing (Compliance 6).
• Timing: Dimensional checks after abnormal landings must be done immediately after those events and before further flight. General dimensional checks are required before further flight after the AD’s effective date.

8. Replace any out-of-tolerance or defective pins

• Action: Replace any out-of-tolerance pins and any pin from defective batches as instructed in the accomplishment instructions of the SB (Requirement 5).
• Timing: Any out-of-tolerance pin must be replaced "before further flight after the effective date" (Compliance 5). In the case where a pin from a defective batch is within dimensional tolerance, the AD includes an explicit deadline of "before 3 October 2006" for replacement, per the Compliance text fragment; treat that as a firm deadline where applicable and consult the SB and CASA/EASA clarifications as necessary.

9. Do not install pins from the three defective batches

• Action: Ensure that no NLG actuator hinge pins from the three defective batches (EUR BC 21344-000-01; EUR BD 21344-000-01; EUR SF 21344-000-01) are installed on NLG P/N 21130-001-02 (Requirement 7). Remove such parts from inventory and quarantines stock to prevent inadvertent installation.
• Timing: Prohibition applies from the effective date of the AD (Compliance 7).

10. Record-keeping and evidence

• Action: Document the serial number verification, SB revision used, AFM amendment, batch identification results, dimensional check numbers and outcomes, any pin replacements (including new batch numbers), and special flight permit documentation if used.
• Timing: Maintain contemporaneous records to demonstrate compliance upon regulatory inspection. The AD does not spell out record retention periods, therefore store records in line with standard maintenance record practices and organisational requirements.

11. Liaise with maintenance providers and parts suppliers

• Action: Coordinate with approved maintenance centres to ensure they understand SB paragraph references and have suitable replacement parts available that are not from the defective batches. Confirm supplier traceability for replacement hinge pins.
• Note: Limited authorised movement to maintenance facilities via special flight permit can reduce logistical obstacles, but planning is required to avoid aircraft on-ground time.

12. Seek clarification where the AD text is ambiguous

• Action: The Compliance block contains a formatting ambiguity around the replacement deadline for defective-batch pins that pass the dimensional check. Operators should, where ambiguity exists, consult the SB, CASA guidance, or EASA documentation referenced in the AD to confirm precise required timing and compliance interpretation (Compliance 5).
• Practical step: If time-critical work is impeded by uncertainty, contact CASA or the manufacturer to confirm the intended compliance window in writing prior to proceeding.

Following this checklist, and ensuring all actions are performed in accordance with the referenced EADS SOCATA Service Bulletin No. 70-147 or a later EASA approved revision, will align operations with the AD’s requirements. Maintain documentary evidence of compliance and ensure that maintenance and procurement processes prevent reinstallation of banned batch parts.