AD/HU 269/111 - Lateral Control Trim Actuator Assembly

The Directive is organised around a small set of technical and procedural concepts. Applicability: the AD applies to narrow serial-number ranges and particular model/configuration variants (Models 269C, 269C-1, and 269D Configuration A) only where the lateral control trim actuator assembly P/N 269A7316-13 is installed, with one explicit exclusion for those assemblies containing a number 30 twist drill hole through the lateral trim control housing wall into the inner spring tube socket (Applicability). The substantive interventions are inspection, modification and test-running of the actuator assembly (Requirement). The inspections include visual checks for scuffmarks, indentations or outer spring guide tube deformation, a security check of the inner spring tube achieved by rotating and pulling on it, and examination of the resin bead around the base of the inner spring tube and housing socket, where a translucent dark pink resin bead is indicated in the AD as a sign of a good bond (Requirement 1(a)).

Two operational distinctions govern timing and sequence. For Models 269C and 269C-1 the AD imposes an immediate inspection requirement before further flight; if defects are found the assembly must be removed, modified and tested before further flight; if no defects are found the assembly still must be modified within 25 hours TIS after the inspection (Requirement 1(a)-(c); Compliance). For Model 269D Configuration A the AD prescribes modification within 50 hours TIS after the AD’s effective date (Requirement 2; Compliance). The procedures to be followed are not printed into the AD text but are incorporated by reference: the specific parts of Schweizer Service Bulletins B-283.1, C1B-017.1 (Parts I and II) and DB-012 are mandated (Requirement).

The safety rationale stated in the Background ties the technical defect to plausible failure modes: separation of the inner spring tube from the lateral trim control housing produced lateral cyclic control restriction in three incidents, and the AD frames the inspection and modification actions as intended to prevent that separation and associated outcomes including emergency landings or loss of control. The inclusion of an FAA AD reference (Note) signals that the same or similar corrective measures were addressed by the United States Federal Aviation Administration, which the AD explicitly cites (Note). The AD’s effective date and signature are in the Compliance and closing lines: it is signed by a CASA delegate (James Coyne) and dated 30 May 2005, with an effective date of 2 June 2005.

Mechanically centred concepts therefore are: identification of affected serial numbers and part number; immediate and short-term mitigation sequencing (inspect then modify/test or modify within fixed TIS windows); reliance on manufacturer service bulletin procedures for the detailed work; and an explicit safety purpose grounded in three reported separation incidents. The AD also establishes an exclusion criterion via a physical modification already present (number 30 twist drill hole), which functions as an alternative compliance marker for assemblies that already incorporate a particular modification.

The AD affects a narrowly defined set of individuals and entities by model, serial number, and installed component. Specifically, the directive applies to owners, operators, maintenance organisations and maintenance personnel responsible for Schweizer (Hughes) 269-series helicopters falling within the serial-number ranges listed: Model 269C S/N 1865 through 1874 with a prefix of S; Model 269C-1 S/N 0169 through 0191; and Model 269D Configuration A S/N 0044 through 0050 with an A suffix, where the lateral control trim actuator assembly P/N 269A7316-13 is installed (Applicability). Where the assembly contains the specified number 30 twist drill hole through the lateral trim control housing into the inner spring tube socket, the AD explicitly excludes that assembly from applicability (Applicability).

Workforces affected include maintenance technicians authorised to carry out inspections, modifications and test runs in accordance with the Schweizer service bulletins. The AD mandates inspecting "by following the Procedures in Part I of Schweizer Service Bulletin B-283.1 or C1B-017.1" and modifying and test-running "by following the Procedures in Part II of Schweizer Service Bulletin B-283.1 or C1B-017.1" for the 269C and 269C-1 series (Requirement 1(a)-(b)). For 269D Configuration A helicopters the AD requires modification "by following the Procedures in Schweizer Service Bulletin DB-012, paragraphs a through i" (Requirement 2). Those procedural references allocate technical responsibility to the operator and the technician to execute the specified manufacturer's steps.

Operational stakeholders include flight crew and operators who may face aircraft downtime because the AD requires inspections before further flight and modifications within short TIS windows. For affected 269C/269C-1 helicopters the inspection must be done before further flight following the AD’s effective date (Requirement 1(a); Compliance). If defects are found, removal, modification and testing must also be completed before further flight (Requirement 1(b); Compliance). Even if no defect is found, modification must be carried out within 25 hours TIS after inspection (Requirement 1(c); Compliance). For the small group of 269D Configuration A helicopters the modification window is 50 hours TIS after the effective date (Requirement 2; Compliance). Those timeframes directly affect scheduling of flights, maintenance slots and parts procurement.

The AD is issued by CASA, signed by a delegate (James Coyne), and thus becomes a regulatory requirement imposed by the national aviation safety authority (Compliance; signature). CASA is therefore the issuing authority; the AD does not itself name a separate enforcement body or penalties in its text. The AD also references FAA AD 2005-10-12, indicating that US operators and authorities dealing with the same type/design may be affected or have already acted in parallel (Note). Owners or operators of the affected helicopters must therefore interact with service providers and apply the specified Schweizer procedures to remain compliant with the Directive.

Duties mandated by the AD are specific, prescriptive and time-bound. The core duties are: (1) to inspect lateral control trim actuator assemblies on specified 269C and 269C-1 helicopters for scuffmarks, indentations, deformation of the outer spring guide tube, looseness of the inner spring tube in the housing socket (via rotation and pull), and to examine the resin bead for translucent dark pink colour indicative of a good bond, following the Procedures in Part I of Schweizer Service Bulletin B-283.1 or C1B-017.1 (Requirement 1(a)); (2) where inspection reveals scuffmarks, deformation, looseness, or bond separation, to remove the affected actuator assembly, modify the trim control housing and inner spring tube, and test run the assembly by following Part II of the same service bulletins (Requirement 1(b)); and (3) where the inspection finds no defect, to still modify the lateral control trim actuator assembly as required by Requirement 1(b) within 25 hours TIS after the inspection (Requirement 1(c)). For Model 269D Configuration A helicopters (S/N 0044 through 0050 with suffix A), the duty is to modify the actuator assembly by following Schweizer Service Bulletin DB-012 paragraphs a through i within 50 hours TIS after the AD’s effective date (Requirement 2; Compliance).

The AD sets immediate duties by using "before further flight" as the compliance trigger for inspections and, if defects are found, for removal/modification/testing (Requirement 1(a)-(b); Compliance). That phrasing imposes an operational constraint: the aircraft must not be flown until the inspection and, where required, corrective action has been completed. For non-defective assemblies the AD still imposes a short-term duty to perform the mandated modification within 25 hours TIS (Requirement 1(c)). These are mandatory duties in the text; the AD does not phrase them as recommendations or options.

The AD also effectively grants procedural rights to rely on the specified Schweizer Service Bulletins to satisfy the substantive inspection and modification requirements because it identifies those documents as the Procedures to follow (Requirement). That is, compliance is measured against execution of the steps contained in the named service bulletin parts. The AD supplies objective markers for inspection outcomes: scuffmark, indentation, outer spring tube deformation, inner spring tube motion/looseness, and separation of bonding; it also provides a specific resin bead appearance (translucent dark pink) as an indicator of a good bond (Requirement 1(a)). These markers narrow interpretive discretion for maintenance staff.

What the AD does not do in its text is prescribe penalties, a process for disputing the AD, or alternative means of compliance other than the one explicit exclusion (the drilled number 30 twist drill hole). The Directive references the FAA AD but does not, in its text, articulate a compliance equivalency mechanism or delegation of enforcement to another agency (Note). The AD thereby sets duties, specifies the accepted procedural instruments (the Schweizer Service Bulletins), and leaves the path to compliance defined by those documents and the stated timeframes.

The Directive itself contains no explicit penalty provisions or enforcement mechanics in the text supplied. It specifies compliance actions and timeframes, and it states an effective date, but it does not set out sanctions, fines, or administrative penalties for non-compliance within its printed sections (Compliance; Requirement). It is signed by a CASA delegate (James Coyne), which identifies the issuing authority, but the AD does not describe in-text how CASA will enforce compliance or what the consequences of failing to comply are.

Because the AD requires inspections "before further flight" and sets short windows for modification (25 hours TIS or 50 hours TIS depending on model), failure to comply will create operational non-conformity with the Directive as drafted. The AD frames the actions as intended to prevent specific hazardous outcomes, namely inner spring tube separation leading to lateral cyclic control restriction and potential emergency landings or loss of control (Background). The AD therefore creates a compliance obligation with an implied safety consequence, but the instrument does not itself list penalty mechanisms or an enforcement process.

The absence of explicit penalties in the AD text means that, based solely on the document provided, interested parties cannot point to specified fines or a prosecution path contained within this AD. The Directive does, however, incorporate by reference manufacturer service bulletin procedures (Requirement), which form the technical standard for compliance. Practical enforcement in operations typically follows from an aviation authority’s oversight posture and certification framework. The AD does not describe those oversight mechanisms or how CASA will monitor compliance, nor does it describe an appeals process or an alternative method of compliance. The only procedural note is a cross-reference to FAA AD 2005-10-12 Amdt 39-14089 (Note).

Accordingly, a reader relying solely on this AD should note that the text imposes mandatory action and timeframes but does not itself enumerate penalties or enforcement steps. To understand enforcement consequences a party would need to consult CASA directly or other regulatory instruments not included in this AD text. The AD itself provides no litigation, sanction, or enforcement history in its body.

The AD makes one explicit external reference: it notes that "FAA AD 2005-10-12 Amdt 39-14089 refers" (Note). That linkage indicates there is an equivalent or related Federal Aviation Administration requirement in the United States addressing the same technical issue. Within the text supplied there is no further statutory cross-reference to other Australian aviation statutes, regulatory instruments, or legislative provisions. The AD is issued by CASA, signed by a delegate, and therefore functions as an administrative directive within the authority of that office; however the AD document itself does not narrate its legal basis nor does it identify enabling legislation or other domestic instruments by name.

Operationally the AD instructs compliance with procedures set out in Schweizer Service Bulletins B-283.1, C1B-017.1 (Parts I and II) and DB-012 (Requirement). Those manufacturer service bulletins are incorporated as the procedural means to meet the AD’s technical requirements. Thus this Directive interacts with private technical documents issued by the helicopter manufacturer by making them the required method of performance for inspection and modification steps. The AD thereby creates a locus where regulatory compliance and manufacturer guidance converge: following the specified parts of the named service bulletins constitutes compliance within the AD’s terms (Requirement).

The AD’s explicit exclusion for actuator assemblies "containing a number 30 twist drill drilled hole in the lateral trim control housing through the wall of the inner spring tube socket" creates an internal interaction between an identified physical alteration and the Directive’s applicability (Applicability). Where that physical alteration is present, the assembly is excluded from the AD’s requirements, and the AD thereby recognises prior corrective or equivalent action as a condition that removes the operator from the AD’s duties.

Beyond the FAA cross-reference and incorporation of manufacturer service bulletins, the AD text does not discuss interactions with other Australian regulatory obligations, maintenance recordkeeping rules, aircraft certification requirements, insurance requirements, or airworthiness certificate status. Those interactions may exist in the broader regulatory system, but they are not documented in the AD text supplied. The AD does, however, set concrete operational windows and mandatory steps that would interact in practice with flight scheduling, maintenance planning, parts procurement and maintenance personnel authorisations.

The AD text supplies a limited, specific amendment record. It lists the effective date of the Directive as 2 June 2005 (Compliance) and bears a signature block showing James Coyne, Delegate of the Civil Aviation Safety Authority, dated 30 May 2005. The AD carries the identifier AD/HU 269/111 and a date-code "8/2005 TX" in the heading. The AD contains a note referencing FAA AD 2005-10-12 Amdt 39-14089, which is itself a distinct instrument from another jurisdiction (Note). The service bulletins it mandates are dated: Schweizer Service Bulletins B-283.1 and C1B-017.1 are both dated 4 March 2005, and Schweizer Service Bulletin DB-012 is dated 8 February 2005 (Requirement). Those dates are the only documentary timestamps for source procedures and the AD in the supplied text.

No further amendments, superseding ADs, or historical revisions are provided in the AD text. There is no indication in this document of prior AD/HU 269/111 versions, no amendment log within the instrument, and no later effective dates or corrigenda in the supplied text. The AD’s internal note that the FAA AD "refers" suggests parallel action by the FAA but does not by itself constitute an amendment history for this CASA AD. The text therefore presents this instrument as a single-issue Directive with a single effective date and with referenced service bulletins dated earlier in 2005.

If a reader needs to know whether subsequent amendments, extensions, or cancellations occurred after the effective date, that information is not contained in the AD text provided. The supplied AD only records the original effective date, the signing delegate and the dates of the referenced service bulletins and FAA AD. No change history or later revisions are recorded within this document.

The AD contains no litigation history, case citations or mention of legal proceedings in the text provided. The only external instrument it references by identifier is the FAA AD 2005-10-12 Amdt 39-14089 (Note). There are no named appeals, judicial reviews, administrative disputes, or court decisions noted in the AD. The directive’s Background references "three reported incidents" as the operational rationale for the measures, but those incident reports are not linked to litigation or to judicial pronouncements within this document.

Therefore, based solely on the AD text, there is no litigation history to report. There are no cases named, no contested enforcement actions documented, and no mention of disputes regarding the content or validity of this Directive in the material provided. Any litigation or appeals related to the AD, the referenced service bulletins, or the FAA action would need to be sought in other records; they are not part of this AD’s text.

The AD contains several precise technical and procedural features that can produce compliance traps if overlooked.

1. Narrow applicability by serial number and suffix: The Directive is limited to specific serial number blocks and, for the 269C series, requires attention to a prefix "S" for S/N 1865-1874 and a suffix "A" for the 269D Configuration A S/N 0044-0050 (Applicability). Operators must carefully match serial numbers and suffix/prefix conventions to determine applicability. Misreading serial number formats or overlooking prefixes/suffixes could lead to incorrect assumption of applicability.

2. Part-number specificity and an explicit exclusion: Applicability is tied to P/N 269A7316-13. Assemblies with that part number are subject to the AD unless they contain a number 30 twist drill hole in the lateral trim control housing through the wall of the inner spring tube socket, in which case they are excluded (Applicability). The presence or absence of that drilled hole is a physical fact that determines compliance obligation. Maintenance staff must check for that feature rather than assume presence or absence.

3. Dual-stage requirements (inspect then modify) with tight timeframes: For 269C/269C-1 helicopters an inspection must be performed before further flight (Requirement 1(a); Compliance). If defects are found, removal/modification/test-run must be completed before further flight (Requirement 1(b); Compliance). Even if no defect is found, the assembly must be modified within 25 hours TIS after the inspection (Requirement 1(c); Compliance). That means inspection may only postpone modification for a very short operational interval; operators must plan parts procurement and maintenance slots accordingly.

4. Procedure-by-reference: The AD mandates following parts of specific Schweizer Service Bulletins (B-283.1 or C1B-017.1 Parts I and II; DB-012 paragraphs a-i) rather than reproducing those procedures in full (Requirement). Compliance therefore requires access to the correct service bulletin edition. Using an incorrect bulletin version, or incomplete adherence to the named parts, could create ambiguity about whether the AD’s procedural requirements were met.

5. Objective but technical inspection criteria: The AD requires checking for scuffmarks, indentation, outer spring guide tube deformation, inner spring tube motion (by rotation and pull), and for the resin bead to be "translucent dark pink" as an indicator of a good bond (Requirement 1(a)). Those criteria are somewhat technical and require trained personnel to interpret consistently. Dispute about whether a particular resin bead colour or a scuff constitutes a defect could create practical disagreement between operator and regulator.

6. Immediate grounding potential: Because inspections are required "before further flight" and removals/modifications/test-runs likewise required "before further flight" if defects are found (Requirement 1(a)-(b); Compliance), the AD can effectively ground an affected helicopter at short notice. Operators operating under tight flight schedules may encounter sudden availability constraints.

7. Small covered fleet and substitution risks: The AD applies to a small subset of serial-numbered aircraft. An operator managing mixed fleets must track compliance only for the affected tail numbers; confusion with similarly numbered but non-affected aircraft could lead to inadvertent non-compliance.

8. Lack of penalties in text and enforcement silence: The AD does not specify penalties or enforcement processes (Penalties and enforcement). That may create uncertainty about the immediate regulatory consequence of non-compliance, even though the AD sets mandatory actions and deadlines. Users cannot rely on this document alone to determine sanctioning mechanisms.

9. Cross-reference to FAA AD: The AD references FAA AD 2005-10-12 Amdt 39-14089 (Note). Operators should be careful to review both documents where relevant because procedural detail or alternative compliance paths may appear in the FAA instrument or the manufacturer’s service bulletins; the AD does not reconcile differences that might exist between documents.

10. Signature and effective date proximity: The AD is signed on 30 May 2005 and becomes effective 2 June 2005 (Compliance). That short lead time leaves little runway for operators to locate parts, secure maintenance windows, or obtain and review the referenced service bulletins before the "before further flight" inspection requirement applies.

Failure to note any one of these items can create operational, scheduling, or interpretive difficulties. The AD’s narrow technical scope and tight deadlines mean attention to serial-number identification, part-number confirmation, checking for the drilled-hole exclusion, and immediate access to the correct service bulletin parts are practical necessities.

The AD prescribes a concrete sequence for compliance that must be followed as written and in the timeframes stated.

1. Determine applicability. Check the helicopter’s model and serial number against the ranges listed for Model 269C (S/N 1865-1874 with a prefix of S), Model 269C-1 (S/N 0169-0191), and Model 269D Configuration A (S/N 0044-0050 with suffix A). Confirm if the lateral control trim actuator assembly installed is P/N 269A7316-13 (Applicability). If the assembly contains a number 30 twist drill hole through the lateral trim control housing into the inner spring tube socket, the assembly is excluded and the AD’s requirements do not apply to that assembly (Applicability).

2. For affected 269C and 269C-1 helicopters, perform the inspection required by Requirement 1(a) before further flight after the AD’s effective date. The inspection must be conducted "by following the Procedures in Part I of Schweizer Service Bulletin B-283.1 or C1B-017.1, both dated 4 March 2005" as applicable. The inspection must check for scuffmarks, indentations, outer spring guide tube deformation; security of the inner spring tube in the socket by rotating and pulling on the inner spring tube; and examine the resin bead around the base of the inner spring tube and housing socket, noting that a translucent dark pink resin bead is identified in the AD as indicating a good bond (Requirement 1(a)).

3. If the inspection identifies a scuffmark, indentation, deformation, inner spring tube looseness or motion, or bond separation, remove the lateral control trim actuator assembly, modify the trim control housing and inner spring tube, and test run the actuator assembly "by following the Procedures in Part II of Schweizer Service Bulletin B-283.1 or C1B-017.1, as applicable." These corrective actions and the test run must be completed before further flight (Requirement 1(b); Compliance).

4. If the inspection finds no scuffmark, indentation, deformation, looseness, or bond separation, the AD still requires modification of the lateral control trim actuator assembly "as required by Requirement 1(b) of this Directive" within the next 25 hours TIS following the inspection. In other words, the Part II modification and test-run procedures must be completed within 25 hours TIS even in the absence of detected defects (Requirement 1(c); Compliance).

5. For affected 269D Configuration A helicopters, modify the lateral control trim actuator assembly "by following the Procedures in Schweizer Service Bulletin DB-012, paragraphs a through i, dated 8 February 2005" within the next 50 hours TIS after the AD’s effective date (Requirement 2; Compliance).

6. Use the specified service bulletins. The AD makes adherence to the stated parts of the named service bulletins the required procedural method for inspections, modifications and test runs. Ensure you have the correct edition and parts: B-283.1 or C1B-017.1 (Parts I and II, both dated 4 March 2005) for the 269C/269C-1 items; DB-012 (paragraphs a-i dated 8 February 2005) for the 269D Configuration A items (Requirement). Do not substitute alternative procedures unless and until an authorised alternative is issued by CASA or the manufacturer and explicitly accepted by the relevant authority.

7. Plan maintenance scheduling and parts. Because the AD requires inspections before further flight and short windows for modifications (before further flight if defects found; within 25 hours TIS otherwise; within 50 hours TIS for the 269D Configuration A helicopters), operators should schedule maintenance capacity and source any required parts or tools to avoid excessive grounding. The AD’s “before further flight” trigger has immediate operational effect on scheduling (Compliance).

8. Recordkeeping and evidence. While the AD text does not specify recordkeeping requirements, maintenance personnel should document the inspection findings, photographs of any defects or the resin bead, removed parts, modification steps undertaken following the service bulletin, and results of the test-run. Because the AD incorporates the service bulletins by reference as the procedures to be followed, contemporaneous records demonstrating adherence to the specific parts of the named service bulletins will be the straightforward evidentiary proof of compliance in case of subsequent inquiries.

9. Coordinate with CASA as required. The AD is issued by CASA and signed by a delegate (James Coyne). If there is any uncertainty about interpretation of the AD, alternative means of compliance, or whether a particular physical alteration (for example the presence of the number 30 twist drill hole) meets the exclusion, consult CASA for formal guidance. The AD text itself does not describe a formal alternative means of compliance process or enforcement steps (Penalties and enforcement); CASA is the issuing authority and the appropriate point of contact.

10. Check for related documents. The AD refers to FAA AD 2005-10-12 Amdt 39-14089 (Note). While the AD incorporates Schweizer service bulletins for the detailed technical steps, operators should review the FAA AD and any other manufacturer technical notes for harmonised instructions, clarifications, or additional test criteria that might affect the work scope or provide alternative compliance options. The AD itself does not reconcile differences; you must ensure the steps you perform align with the parts of the service bulletins referenced in this Directive (Requirement).

In summary, compliance requires confirming applicability, obtaining and following the named service bulletin parts, performing the inspection before further flight, executing required removals/modifications/test runs immediately when defects are found or within 25/50 hours TIS as applicable, and maintaining objective records evidencing the procedures followed.