AD/S-PUMA/69 - Engine Controls - Fuel Shut off Lever

The AD is organised around a small set of operational and technical concepts found in the source text: applicability, inspection functional checks, identification of a “hard point,” remedial action (gearbox reconditioning and grease‑lubrication), recurring intervals, termination of repetitive checks, and linkage to Eurocopter ASB and EASA material.

• Applicability: The AD applies only to specified models , Eurocopter AS 332 C, C1, L, L1 and L2 (Applicability). That defines the scope of units subject to the directive.

• Functional inspection: Requirement 1 directs a functional check of the fuel shut‑off controls “for correct operation” in accordance with Para 2.B.1 of the Eurocopter ASB No. 76.00.04 (Requirement 1). The ASB paragraph is prescribed as the procedural standard; the AD requires operators to follow that specific ASB text or later EASA‑approved revisions, thereby outsourcing the precise test procedure and acceptance criteria to the manufacturer’s ASB as approved by EASA.

• Hard point: The AD distinguishes between two inspection outcomes. If a “hard point” is found in any fuel shut‑off control (a binding/jamming condition), Requirement 3 requires compliance with Requirement 4 (inspect and grease‑lubricate the tangential gearboxes) (Requirement 3). If no hard point is found, Requirement 2 requires repeating the functional inspection until Requirement 4 is done (Requirement 2; Note 1). The AD therefore uses the “hard point” finding to determine urgency of remedial action and whether repetitive inspections remain necessary.

• Gearbox reconditioning/grease‑lubrication: Requirement 4 prescribes inspection and grease‑lubrication of the tangential gearboxes following Para 2.B.2 of the ASB (Requirement 4). Note 1 explicitly states that compliance with Requirement 4 is the terminating action for the repetitive inspections mandated by Requirement 2, so the AD contemplates a discrete maintenance action that ends the need for frequent functional checks.

• Timing and recurrence: The AD sets concrete scheduling rules by reference to helicopter age at the AD effective date. For helicopters ≥4 years old at the effective date, initial inspection within 15 flight hours, recurrence at intervals not exceeding 50 flight hours, and gearbox work within six months after the initial inspection (Compliance). For helicopters <4 years old at effective date, initial inspection by the time the helicopter reaches 4 years, recurrence at intervals not exceeding 50 flight hours, and gearbox work by 4.5 years of calendar life (Compliance). The AD also imposes “before further flight” requirements in connection with some items (Compliance).

• Cross‑reference to EASA and ASB: The AD requires operators to use Eurocopter ASB No. 76.00.04 original issue dated 21 March 2007 or later EASA‑approved revisions for procedural detail, and it expressly refers to EASA Emergency Airworthiness Directive AD No. 2007‑0082‑E dated 27 March 2007 (Requirement 1; Note 2). The AD thus links Australian regulatory action to EASA guidance and to the manufacturer’s ASB.

These concepts combine to produce a compliance regime that is prescriptive on what inspections and remedial actions must happen, when they must happen (age or flight‑hour triggered), and what procedural documents must be followed.

The AD identifies a particular set of operator/machine combinations and thereby allocates obligations and risk mitigation responsibilities.

• Affected aircraft: The AD applies to Eurocopter AS 332 model helicopters C, C1, L, L1 and L2 (Applicability). Only these model types are listed in the applicability field of the AD; helicopters of other models are not covered by the AD as published.

• Affected parties: The direct addressees are operators and maintenance organisations responsible for the airworthiness and maintenance of the listed helicopters. The AD’s requirements are operational and maintenance tasks that must be carried out on the listed helicopters (Requirement 1; Requirement 4). The AD does not identify specific named operators, owners, lessees, or third parties, but the practical duty rests with whoever is accountable for maintenance and airworthiness of the subject helicopter under prevailing operational arrangements.

• Maintenance personnel and approvers: The AD mandates procedures set out in Eurocopter ASB No. 76.00.04 or later EASA‑approved revisions (Requirement 1; Requirement 4). That requires maintenance staff to follow manufacturer ASB procedures, and, by cross‑reference to EASA approval, to ensure they implement the revision version that is EASA‑approved. Inspectors and maintenance certifiers will be tasked with performing and documenting the functional checks and gearbox reconditioning/grease‑lubrication mandated.

• Timing‑sensitive cohorts: The AD divides the affected fleet by calendar age at the AD effective date. Helicopters that were four years or older on the effective date must comply within 15 flight hours, initiate a sequence of inspections every 50 flight hours, and carry out gearbox work within six months of the initial inspection (Compliance). Helicopters younger than four years must complete the initial inspection by the time the helicopter reaches four years and the gearbox work by 4.5 years of calendar life (Compliance). Those different schedules affect operators depending on their helicopter fleet age profile.

• Safety and operational stakeholders: While not directly named, the safety rationale (Background) identifies potential broader operational consequences , inability to close the fuel cock, failure of ventilation flaps to close, or inability to engage the general electrical cut‑off control , which would concern flight crews, emergency response procedures, insurers and operators’ risk managers. The AD therefore has implications for operational safety protocols, training and fleet dispatch decisions when inspections or gearbox work are required.

• Regulatory interface: The AD is issued by a delegate of the Civil Aviation Safety Authority and references EASA material. As such, operators using Australian‑registered helicopters must reconcile this AD with their maintenance programmes and with any other regulatory requirements binding their operations.

In sum, the AD assigns immediate, documented maintenance obligations to operators and their maintenance organisations for a defined set of Eurocopter AS 332 variants, with schedules that depend on calendar age at the AD’s effective date.

The AD imposes prescriptive duties and identifies procedural standards; it does not enumerate rights such as appeals or alternative compliance within the text provided.

• Mandatory duties imposed by the AD:

  • Functional check duty: Operators must inspect the fuel shut‑off controls for correct operation in accordance with Para 2.B.1 of Eurocopter ASB No. 76.00.04 original issue dated 21 March 2007 or later EASA‑approved revisions (Requirement 1).
  • Repetition duty when no hard point: If no hard point is found in the fuel shut‑off controls, operators must repeat the functional inspection per Requirement 1 until Requirement 4 is complied with (Requirement 2).
  • Immediate remedial duty when a hard point is found: If a hard point is found in one of the fuel shut‑off controls, operators must comply with Requirement 4 (Requirement 3).
  • Gearbox reconditioning/grease‑lubrication duty: Operators must inspect and grease‑lubricate the tangential gearboxes in accordance with Para 2.B.2 of ASB No. 76.00.04 or later EASA‑approved revisions (Requirement 4).

• Timing and recurrence duties:

  • For helicopters four years or older on the AD effective date: initial inspection within 15 flight hours after the AD’s effective date; subsequent inspections at intervals not exceeding 50 flight hours; certain actions required “before further flight”; gearbox reconditioning within six months after the initial inspection (Compliance).
  • For helicopters under four years on the AD effective date: initial inspection by the time the helicopter reaches four years of calendar life; subsequent inspections at intervals not exceeding 50 flight hours; certain actions required “before further flight”; gearbox reconditioning by 4.5 years calendar life (Compliance).

• Procedural standard duty:

  • The AD prescribes that the inspection and gearbox procedures are to be carried out in accordance with specified paragraphs of Eurocopter ASB No. 76.00.04 (Requirement 1; Requirement 4). The AD also permits the use of later ASB revisions only if they are EASA‑approved (Requirement 1; Requirement 4).

• Termination of repetitive duty:

  • Note 1 makes clear that completion of Requirement 4 (i.e., gearbox reconditioning/grease‑lubrication) is the terminating action for the repetitive inspections required by Requirement 2. Accordingly, after Requirement 4 is carried out, the repetitive inspection obligation created by Requirement 2 ceases (Note 1).

• Rights and procedural absence:

  • The AD text does not specify a right of appeal, alternative means of compliance, or a formal deferral mechanism in the body of the AD as presented. It likewise does not set out compensation, cost recovery, or discretionary waivers. The AD does not itself articulate any rights to deviate from the prescribed ASB procedure except to permit “later EASA approved revisions” of the specified ASB paragraphs (Requirement 1; Requirement 4).

• Reference to external mandatory material:

  • The AD references EASA Emergency AD No. 2007‑0082‑E (Note 2), indicating an alignment or cross‑reference with EASA’s emergency directive; the AD thereby places reliance on external, referenced regulatory/technical materials as the operative technical standard.

In practical terms the operator’s duty is to follow the AD’s inspection/remedial steps and schedules, using the specified ASB text as the technical method. The AD does not itself specify procedural remedies for non‑compliance or rights to seek alternative compliance within its own text.

The AD text supplied does not set out specific penalties, fines, or enforcement procedures. Instead, it imposes mandatory maintenance and inspection requirements and records an effective date and issuing authority; those elements are the operative mechanism for forcing compliance.

• Absence of penalties in the AD: The published AD does not include a sanctions matrix, monetary penalty schedule, or criminal/civil penalty clauses within the text provided. There is no wording in the AD specifying fines, licence suspensions, or remedial enforcement steps in the event of non‑compliance.

• Enforcement signals present in the AD: The AD is issued by a delegate of the Civil Aviation Safety Authority (Charles Lenarcic) and contains an effective date of 30 March 2007 (signature block, 29 March 2007). That shows the AD is an instrument of regulatory authority and thereby carries the regulatory force typical of an AD: it prescribes required actions within defined time frames (Applicable Requirements; Compliance). The practical enforcement of these requirements would typically occur through the regulator’s compliance oversight, maintenance audits, airworthiness inspections or air operator certificate surveillance. However, those enforcement mechanisms and any associated sanctions are not set out in this AD text.

• Actionable compliance items that facilitate enforcement: The AD requires specific actions to be performed in accordance with the Eurocopter ASB paragraphs referenced, and sets distinct timing triggers (flight hours and calendar age). Those concrete checkpoints create observable, documentable steps that a regulator can verify in a maintenance log, thereby enabling standard regulatory oversight. For example, the initial inspection within 15 flight hours, the 50 flight‑hour recurrence interval, and the gearbox work within six months are specific metrics that permit checking whether an operator acted as required (Compliance sections).

• Interaction with other enforcement authorities: The AD expressly references an EASA Emergency AD (AD No. 2007‑0082‑E dated 27 March 2007) (Note 2) and refers operators to ASB procedures that are subject to EASA approval for revisions. Those cross‑references suggest that other aviation safety authorities and European regulator guidance are in play, but the AD itself does not assign enforcement roles or penalties to those bodies.

• Practical implications: Because the AD does not enumerate penalties within its text, any enforcement or penalty mechanisms will be applied pursuant to the broader legal framework governing aviation safety enforcement (not contained in this document). The AD creates obligatory, verifiable maintenance actions; the AD’s value to enforcement lies in those objective requirements rather than in any in‑text sanction provisions.

In short, the AD prescribes mandatory safety actions with precise timing and procedural references; it does not itself specify penalties or the enforcement process in the text provided.

The AD references and incorporates external technical and regulatory material but does not explicitly describe broader statutory interactions. The source text identifies two specific links to external instruments and leaves implicit any other statutory interaction.

• Link to Eurocopter ASB No. 76.00.04: The AD makes the manufacturer’s Alert Service Bulletin the procedural standard for the required inspections and tangential gearbox reconditioning/grease‑lubrication (Requirement 1; Requirement 4). The AD specifies the ASB original issue dated 21 March 2007 or “later EASA approved revisions,” thereby making the ASB paragraphs the operative technical procedure, subject to EASA approval for any later revisions. This creates a dependency whereby the AD’s technical compliance is achieved by following a manufacturer document approved by EASA.

• Link to EASA Emergency Airworthiness Directive: The AD explicitly references EASA Emergency Airworthiness Directive AD No. 2007‑0082‑E dated 27 March 2007 (Note 2). That reference indicates that the Australian AD is aligned with or follows an EASA emergency AD on the same issue. The AD thereby incorporates or echoes EASA’s emergency findings and remedies as part of its technical and regulatory basis.

• Implicit interaction with national airworthiness requirements: The AD was issued by a delegate of the Civil Aviation Safety Authority and contains an effective date. While this AD text does not recite its statutory authority (for example, the particular Act or regulation empowering CASA to issue ADs) or how it integrates with national maintenance regulations, the AD’s existence and its mandates imply it operates within the domestic airworthiness regulatory framework. Those broader statutory provisions and regulatory enforcement mechanisms are not reproduced in the AD text.

• Dependency on approved revisions: Because the AD accepts “later EASA approved revisions” of the cited ASB paragraphs, the AD’s operational effect depends on the process by which EASA approves revisions to the manufacturer’s ASB. That creates an interaction between the AD and EASA’s approval process: operators may need to monitor EASA approvals to confirm whether a later ASB revision is acceptable for compliance with this AD.

• No explicit conflicts noted: The AD does not identify any inconsistency with, nor does it set out rules for resolving conflicts with, other normative documents, regulations or operating rules. The AD presents its requirements and points to the ASB and EASA AD; any conflict resolution would be handled by broader regulatory practice or by subsequent regulatory instruments, neither of which is contained in the AD text.

• No substitute or alternative compliance provisions: The AD does not provide an explicit alternative compliance pathway (for example, an approved alternative method of compliance) within the text provided. The only flexibility noted is limited to accepting later ASB revisions that have EASA approval.

Therefore, the AD’s immediate interaction is with Eurocopter’s ASB and with the referenced EASA emergency AD; other statutory interactions are implicit and would be governed by the broader regulatory framework under which the AD was issued, but that framework is not specified within the source text.

The AD text supplied contains a single issuance record and does not include a history of amendments, revocations or supersessions in the document.

• Single issuance and effective date: The AD states that it “becomes effective on 30 March 2007” and bears the delegate’s signature block dated 29 March 2007 (Effective date; signature). There is no separate chronological list of prior versions or later amendments contained in the document.

• References to other documents rather than internal amendments: The AD refers to Eurocopter ASB No. 76.00.04 original issue dated 21 March 2007 or later EASA‑approved revisions for procedural content (Requirement 1; Requirement 4). That phrasing permits the technical procedures to be updated through EASA‑approved ASB revisions, but it does not itself represent an amendment to the AD text; rather it allows updated technical methodology as those ASB revisions obtain EASA approval.

• Reference to EASA AD: Note 2 refers operators to EASA Emergency Airworthiness Directive AD No. 2007‑0082‑E dated 27 March 2007. That EASA AD is external to this Australian AD and may contain its own amendment history; however, the Australian AD as supplied does not recite any changes to its own content arising from later events.

• No recorded supersessions or cancellations: The text contains no statement that this AD supersedes or replaces earlier Australian ADs nor any statement of subsequent ADs that would modify or cancel this AD. The document appears to be the initial and sole text of AD/S‑PUMA/69 as of the effective date presented.

• Practical consequence: Operators should treat the AD as active from 30 March 2007 and monitor Eurocopter ASB revisions and EASA ADs for any technical updates; any formal amendment of the AD itself would be documented separately and is not present in this source text.

In summary, the supplied AD shows a one‑time issuance, effective 30 March 2007, with no amendment history recorded in the text provided. It does allow technical procedure updates via EASA‑approved ASB revisions, but does not itself show any subsequent amendment or revocation.

The AD as supplied does not record any litigation history. There are no references to court decisions, disputes, legal challenges, or judicial reviews in the text.

• No cases or judicial references: The AD contains no citations to litigation or administrative appeals. It documents factual background (two maintenance findings of jamming and causes) and prescribes remedial measures, but it does not mention any legal proceedings initiated by affected parties or others.

• No recorded disputes over scope, authority or content: The AD does not narrate any history of disagreement with operators, manufacturers, or other regulators. It does not indicate that the AD’s issuance was stayed, modified or challenged.

• Practical inference: Because the AD contains only prescriptive maintenance requirements and technical cross‑references, any litigation arising from it would be external to this document. The AD as supplied furnishes no information of litigation outcomes, pending actions, or legal arguments.

Therefore, based solely on the provided material, there is no litigation history documented in the AD.

This AD contains a number of practical pitfalls and implementation details that operators and maintenance organisations should note carefully, as revealed by the AD text.

• The ASB is the required procedural source and only EASA‑approved revisions are acceptable: The AD mandates specific paragraphs of Eurocopter ASB No. 76.00.04 (Para 2.B.1 and Para 2.B.2) “original issue dated 21 March 2007 or later EASA approved revisions” (Requirement 1; Requirement 4). Operators must ensure they use the original ASB or wait for a later ASB revision only if it is EASA‑approved. Using a non‑EASA‑approved ASB revision would not meet the AD’s stated standard.

• Termination logic is tied to Requirement 4: Note 1 states that “Compliance with Requirement 4 of this AD is the terminating action for repetitive inspections in accordance with Requirement 2 of this AD.” That means operators who repeatedly pass the functional check still must carry out the gearbox reconditioning/grease‑lubrication to end the repetitive inspection cycle. Passing inspections alone does not terminate the repeated checks.

• “Hard point” triggers immediate gearbox action: If any inspection reveals a “hard point” in a fuel shut‑off control, Requirement 3 requires immediate compliance with Requirement 4. Operators must be prepared to escalate from an inspection to gearbox reconditioning without delay.

• Timing can be tight for older helicopters: For helicopters that were four years or older on 30 March 2007, the initial inspection window is within 15 flight hours after the AD’s effective date (Compliance). For high utilisation aircraft, 15 flight hours can occur in a very short calendar window; operators must schedule inspections promptly to avoid being out of compliance.

• Multiple timing metrics: The AD mixes flight‑hour and calendar‑age triggers. For some actions the standard is “within X flight hours,” for others it is “by the time the helicopter is calendar‑age 4 or 4.5 years.” Operators must track both flight hours and the helicopter’s calendar life relative to the AD effective date to ensure compliance.

• “Before further flight” obligations: The Compliance table includes “Before further flight” entries. The AD does not elaborate within its own text what specific triggers move an action into a “before further flight” category for each Requirement, so maintenance organisations should interpret these phrases conservatively: if an inspection discovers a condition that falls within a “before further flight” item, the helicopter must not depart until the required action is complete.

• The AD refers to an EASA Emergency AD: Note 2 states that EASA Emergency AD No. 2007‑0082‑E dated 27 March 2007 is referenced. Operators should verify the content of that EASA AD where relevant; the Australian AD does not reproduce the EASA AD’s text, but the EASA AD may contain additional technical detail or context.

• Documentation and proof of compliance: The AD prescribes specific actions (inspection/grease‑lubrication) and precise timing windows; operators should be mindful to document the inspection results, the presence or absence of a hard point, the dates/flight hours at which actions were carried out, and the ASB revision used to demonstrate compliance. The AD itself does not set out the acceptable documentation format.

• Scope limited to certain models: The AD applies only to AS 332 C, C1, L, L1 and L2 models. Owners/operators of other Super Puma variants should not assume they are covered; conversely, operators of the listed models must not assume any other variants are covered under this AD.

• No text on alternative compliance: The AD does not provide an explicit alternative method of compliance within its text. If an operator wishes to use a different procedure or timing, the AD itself does not offer an in‑text approval path; any alternative would need to be pursued through the appropriate regulatory process outside this AD text.

• Maintenance capacity and parts: The AD requires grease‑lubrication and inspection of tangential gearboxes, work that may require downtime and specific parts or consumables. The AD does not provide logistical allowances, so operators should plan maintenance slots and ensure they have the required supplies and technical capability.

These are operationally significant details that can lead to non‑compliance if overlooked, and each is directly traceable to the AD text (Requirements, Notes, Compliance).

The AD prescribes concrete inspection and maintenance steps, with precise timing rules tied to either flight hours or calendar age. The following sequence is the compliance pathway as required by the AD text.

1. Confirm applicability:

   • Verify that the helicopter is one of the listed models: Eurocopter AS 332 C, C1, L, L1 or L2 (Applicability).

2. Identify the technical procedure to use:

   • Obtain Eurocopter AS 332 Alert Service Bulletin No. 76.00.04, original issue dated 21 March 2007, and use Para 2.B.1 to perform the functional check of the fuel shut‑off controls and Para 2.B.2 to perform inspection and grease‑lubrication of the tangential gearboxes (Requirement 1; Requirement 4).
   • If a later ASB revision is available, confirm it is EASA‑approved before relying on it for compliance (Requirement 1; Requirement 4).

3. Schedule the initial inspection according to helicopter age at the AD’s effective date:

   • If the helicopter was four years old or older on 30 March 2007 (the AD effective date), schedule the functional inspection within 15 flight hours after 30 March 2007 (Compliance).
   • If the helicopter was less than four years old on 30 March 2007, schedule the functional inspection by the time the helicopter reaches four years of calendar life (Compliance).

4. Perform the functional inspection:

   • Conduct the functional check of the fuel shut‑off controls per Para 2.B.1 of the ASB. Record the inspection, including whether a “hard point” (binding/jamming) was found (Requirement 1).

5. Follow the branching logic in the AD:

   • If a hard point is found in any fuel shut‑off control during the functional inspection, immediately comply with Requirement 4: inspect and grease‑lubricate the tangential gearboxes in accordance with Para 2.B.2 of the ASB (Requirement 3; Requirement 4).
   • If no hard point is found, repeat the functional inspection per Requirement 1 at the intervals required under Requirement 2 until Requirement 4 is completed (Requirement 2; Note 1).

6. Comply with gearbox reconditioning/grease‑lubrication timing:

   • For helicopters ≥4 years at effective date: complete inspection and grease‑lubrication required by Requirement 4 within six months after the initial inspection per Requirement 1 (Compliance).
   • For helicopters <4 years at effective date: complete the gearbox work required by Requirement 4 at the latest when the helicopter reaches 4.5 years of calendar life (Compliance).

7. Observe recurring inspection intervals:

   • After the initial inspection, perform functional inspections at intervals not to exceed 50 flight hours as specified for both age cohorts (Compliance). Repetitive inspections continue until Requirement 4 has been carried out (Note 1).

8. “Before further flight” actions:

   • Note the AD’s “before further flight” entries in the Compliance table. If an item is designated “before further flight” in the AD’s compliance sequencing (for example where a discovered condition necessitates immediate action), do not return the helicopter to service until the required action is complete (Compliance).

9. Documentation and records:

   • Record the date, flight hours, inspection results (including presence or absence of hard point), the ASB paragraph and revision used, and the details of any gearbox reconditioning/grease‑lubrication performed. The AD does not specify the required documentation format; retain records sufficient to demonstrate compliance with the AD’s timing and procedural requirements (Requirements; Compliance).

10. Cross‑reference to EASA AD:

    • Review EASA Emergency Airworthiness Directive AD No. 2007‑0082‑E dated 27 March 2007 as referenced in Note 2, to ensure there is no additional technical or procedural detail relevant to the inspections or remedial actions.

11. Plan maintenance capacity:

    • Because the AD requires initial inspections on a short timetable for older helicopters (within 15 flight hours) and recurring checks every 50 flight hours thereafter, ensure maintenance scheduling, qualified personnel and spare parts/consumables (grease, seals, parts as per ASB) are available to avoid groundings or non‑compliance. The AD itself does not allocate time or parts, so these operational matters must be addressed by the operator.

12. Consider regulatory reporting and confirmation:

    • While the AD text does not prescribe an administrative submission or approval step within its own body, operators should ensure that any required regulatory notifications or logbook entries required under their national maintenance rules are completed in order to document compliance with the AD.

Following the AD requires adherence to the ASB paragraphs cited, strict observance of the timing triggers (flight hours and calendar age), and precise documentation of findings and corrective actions so that compliance can be demonstrated. Completion of Requirement 4 ends the repetitive inspection obligation from Requirement 2 (Note 1). The AD became effective on 30 March 2007 and was issued by a CASA delegate on 29 March 2007 (Effective date; signature).