AD/IAI-W/9 Amdt 3 - Horizontal Stabiliser Rear Spar Splice Fitting

The AD is structured around a small set of core regulatory concepts: applicability, mandated inspections, corrective action, compliance timing, terminating modification, and reference to external technical documents.

Applicability: the instrument applies to "All Model 1124 and 1124A aircraft, all serial numbers" (Applicability). That means the directive covers the entire population of those two models without serial-number carve-outs in this text.

Mandated inspection procedure: the AD does not describe the inspection technique in detail within the Directive itself. Instead it mandates inspection "in accordance with Israel Aircraft Industries Service Bulletin (SB)1124-55-020 Revision 2, or later Israel CAA approved revision" (Requirement). The SB is therefore incorporated by reference as the technical method to locate and assess cracking in the splice fitting.

Repeat inspections and interval: if no cracking is found, operators must "repeat the inspection" (Requirement). The compliance clause defines the repeat interval as "at intervals not to exceed 300 flight hours; until a titanium splice fitting (MOD AFC2081) is installed" (Compliance). The AD also imposes an initial compliance window of 75 flight hours after 10 April 2008, with an exception tied to prior inspections: "unless inspected within the last 225 flight hours since compliance with the previous issue of this Directive" (Compliance). Those numeric thresholds are the primary timing controls embedded in the AD.

Corrective action: where cracking is detected, the AD requires replacement before further flight, "replace the splice fitting with a serviceable fitting in accordance with SB 1124-55-021 Revision 3, or later Israel CAA approved revision" (Requirement). The AD specifies the replacement part procedure by SB reference.

Terminating action by modification: the AD recognises a discrete modification (MOD AFC2081) that fits a titanium splice fitting P/N WW4453005-509; installing that part in accordance with the AMM "constitutes terminating action for the requirements of this Directive" (Note 1). The AD also notes that the modified aircraft will have a "considerably longer inspection interval" documented in AMM Chapter 5 (Note 1). The Directive therefore creates two compliance pathways: ongoing cyclic inspections or install a terminating modification to reduce inspection burden.

Cross-reference to foreign regulator: the AD explicitly tracks the Israel Civil Aviation Authority (CAA) directives: it requires SBs or revisions that are "Israel CAA approved" and references Israel CAA AD 85-001 R3 (Note 2 and Background). Amendment 3 is issued "in response to a revision of the related CAA AD," and the AD records that the Israeli AD introduces the titanium fitting (Background).

Effective date and administrative authority: the AD states an effective date of 10 April 2008 and is signed by "David Villiers, Delegate of the Civil Aviation Safety Authority" on 28 February 2008 (Compliance; signature block). The AD is an instrument of CASA in the Australian regulatory system and functions by requiring adherence to specified SBs and AMM procedures.

Together these concepts define a targeted technical safety intervention: regular inspections to detect cracks in a known susceptible fitting, mandatory replacement pre-flight if cracking is present, and an option to end repetitive inspections by installing a specified titanium part per approved maintenance procedures.

The AD text identifies the directly affected parties in narrow technical terms and thereby indicates who bears operational responsibilities.

Aircraft operators and owners of IAI Westwind Model 1124 and 1124A: the applicability clause is explicit, applying to "All Model 1124 and 1124A aircraft, all serial numbers" (Applicability). Any entity that operates, owns, or is responsible for maintenance of those aircraft must comply with the AD’s inspection and corrective-action requirements. This includes commercial operators, corporate operators, aircraft lessors while the lessor’s maintenance obligations attach, and private owners of the affected models.

Maintenance organisations and licensed engineers: the Directive requires inspections "in accordance with Israel Aircraft Industries Service Bulletin SB1124-55-020 Revision 2" and replacement "in accordance with SB 1124-55-021 Revision 3" (Requirement). Those service bulletins and the Aircraft Maintenance Manual (AMM) set out technical maintenance procedures, so organisations performing maintenance (Part 145 organisations or equivalent approved maintenance providers) and licensed aircraft maintenance engineers are directly implicated. The AD therefore shapes which maintenance tasks are to be performed, how they are to be performed, and when.

Part suppliers and modification providers: the AD identifies a specific titanium part number P/N WW4453005-509 and identifies MOD AFC2081 as a terminating modification (Note 1). Suppliers of that part, and organisations authorised to perform MOD AFC2081 in accordance with the AMM, are a narrow but concrete group whose products and services enable operators to remove the ongoing inspection obligation.

Civil Aviation Safety Authority and certifying authorities: the AD is issued by CASA (Delegate David Villiers); it references Israel CAA approvals and related Israel CAA AD 85-001 R3 (Note 2; Background). CASA, through its continuing airworthiness oversight, and the Israel CAA through its approved revisions and related ADs, are implicated administratively. The AD makes explicit that only Israel CAA approved revisions of the SBs or AMM are acceptable under the Directive, so regulatory approval processes for revisions matter to compliance.

Flight operations: while the AD addresses a structural component, its requirement that replacement must be performed "before further flight" when cracks are detected (Requirement) directly affects flight scheduling decisions. Operators must ground aircraft where cracking is found until the part is replaced.

Insurance and lessors (indirect): while not named in the text, parties with financial or contractual interests,insurers and lessors,will be affected through operational disruption, but the AD itself does not address contractual remedies or insurance obligations. The text does not create contractual rights for these parties; it imposes safety obligations on operators and maintenance providers.

Geographic and fleet scope: the AD applies irrespective of serial number and is silent on geographic carve-outs; it is an Australian AD but explicitly relies on Israel CAA technical materials. That combination means Australian-registered IAI Westwind 1124/1124A aircraft must comply with CASA’s AD while following Israel CAA-approved SBs and the AMM.

In short, the directive binds operators and maintenance providers of all IAI Model 1124/1124A aircraft to perform specified inspections at the stated intervals, to replace cracked fittings before further flight, and to either continue inspections until a titanium part is installed or install the titanium splice fitting as terminating action.

The AD creates a compact set of duties for operators and maintenance organisations, and implicitly defines limited rights through alternative compliance paths. All duties and options in this section derive from the Directive text.

Primary duties:

• Inspect: Operators must "Inspect in accordance with Israel Aircraft Industries Service Bulletin (SB)1124-55-020 Revision 2, or later Israel CAA approved revision" (Requirement). The inspection technique itself is not described in the AD but is mandated to be performed as detailed in the referenced SB.

• Repeat inspection: If no cracking is evident the operator must "repeat the inspection" (Requirement). The AD specifies repeat intervals in the Compliance clause: at intervals not to exceed 300 flight hours until the titanium splice fitting is installed.

• Replace cracked fittings prior to flight: If cracks are detected the operator must, "before further flight, replace the splice fitting with a serviceable fitting in accordance with SB 1124-55-021 Revision 3, or later Israel CAA approved revision" (Requirement). This imposes a pre-flight grounding obligation for aircraft with detected cracking until a replacement is fitted.

• Time-limited initial compliance: The Directive imposes an immediate compliance window: "Within 75 flight hours after 10 April 2008, unless inspected within the last 225 flight hours since compliance with the previous issue of this Directive" (Compliance). Operators therefore must assess their inspection history against the previous issue of the Directive to determine applicability of the 75 FH window.

• Repeat interval until modification: Inspect at intervals "not to exceed 300 flight hours; until a titanium splice fitting (MOD AFC2081) is installed" (Compliance). That creates an ongoing inspection duty that continues until the terminating modification is performed.

Terminating action and rights:

• Installation of the titanium splice fitting P/N WW4453005-509 (MOD AFC2081) "in accordance with the Aircraft Maintenance Manual (AMM) constitutes terminating action for the requirements of this Directive" (Note 1). Installing the specified part via the AMM gives the operator the right to cease compliance with the AD’s inspection regime; the AD records that the AMM provides a "considerably longer inspection interval" for modified aircraft in Chapter 5 (Note 1). Thus the AD defines a clear trade-off: continue periodic inspections, or carry out a modification that relieves the operator of those inspection obligations under the AD.

• Use of approved revisions: Wherever the AD refers to SBs or AMM procedures it qualifies the reference with "or later Israel CAA approved revision" (Requirement). That gives operators the right to rely on later revisions of the SB or AMM, provided those revisions are approved by the Israel CAA.

Implied duties and limits in the AD:

• No technical deviation authorised in the AD text: the Directive mandates compliance with the specific SBs and AMM procedures or later Israel CAA approved revisions. The AD does not itself grant alternative technical methods of compliance; any alternate procedure would need to be accepted by the relevant authority but is not contained in the AD text.

• No contractual or administrative rights specified: the AD does not create or specify rights of reimbursement, nor does it set out appeal procedures against the AD’s requirements; the Directive focuses solely on technical compliance duties.

• Cross-reference duty: Note 2 and Background reference Israel CAA AD 85-001 R3 and the related Israel CAA actions. The AD requires use of Israel CAA approved revisions, so ensuring the SB/AMM revisions used are Israel CAA approved is a compliance obligation.

Who decides: the AD does not specify a delegated waiver or variation process within its text. It is signed by the CASA delegate (David Villiers), showing the instrument’s administrative source, but any discretion to vary requirements or accept alternatives is not set out in the AD itself.

In sum, the AD imposes clear, binding duties to inspect, to replace cracked fittings prior to flight, and to either continue inspections at stated intervals or complete a specified modifying installation that terminates the inspection requirement. Rights in the AD are limited to reliance on later Israel CAA-approved revisions of the referenced SBs and AMM and to take the terminating action described.

The Directive text itself contains no express penalty provisions or enforcement mechanisms. The AD sets out technical requirements, inspection intervals and corrective actions, and an effective date, but it does not specify sanctions, fines, or enforcement procedures within the text provided.

What the AD does include that is relevant to enforcement:

• Effective date and signature: The AD "becomes effective on 10 April 2008" and is signed by David Villiers, "Delegate of the Civil Aviation Safety Authority" (Compliance; signature block). The instrument is therefore a formal CASA direction, which implies that CASA will be the enforcing authority for compliance, but the AD text does not spell out enforcement steps or penalties.

• Mandatory pre-flight replacement: The Directive mandates that if cracks are detected the splice fitting must be replaced "before further flight" (Requirement). That operationally means aircraft with detected cracking are not compliant for flight until the specified corrective action is taken. The AD places operational limits (grounding until replacement if cracking exists) but does not describe enforcement consequences for failing to ground the aircraft.

• Reference to approved documentation: The AD requires compliance with Israel CAA approved revisions of SBs and the AMM. Use of unapproved documents would, by definition, put an operator outside the AD’s specified compliance route; however the AD does not specify how CASA will determine compliance or what sanctions would follow.

Because the Directive text contains no penalty regime, readers must note that:

• Any civil, administrative or criminal enforcement for non-compliance would be governed by the broader statutory and regulatory framework under which CASA operates, but those statutory mechanisms are not described in this document.

• The AD’s operational prescriptions (inspection timing; replacement before flight) create immediate practical consequences for safe operation; non-observance would leave the operator non-compliant with the AD and, depending on the broader aviation safety law and CASA practice (not described in the AD), could give rise to regulatory action. Those external enforcement mechanisms are not stated in the AD text and are therefore beyond what can be asserted from the supplied instrument.

In short, the AD imposes mandatory technical duties but does not itself set out penalties or enforcement steps in the text provided. Any enforcement action would be taken under CASA’s broader statutory powers or other applicable rules not contained within this AD.

The AD interacts with other technical and regulatory instruments through explicit references and implied reliance on external approvals. The Directive itself is narrowly technical and therefore draws on other documents rather than restating those materials.

References to Israel CAA requirements: Multiple parts of the AD require that the Service Bulletins and Aircraft Maintenance Manual revisions be "Israel CAA approved" (Requirement; Note 2). The AD also explicitly references "Israel CAA AD 85-001 R3" (Note 2) and states that Amendment 3 responds to a revision of the related Israel CAA AD (Background). Therefore, the AD functions in coordination with the Israel CAA’s airworthiness directives and approved revisions to the SBs and AMM.

Incorporation by reference of technical documents: The AD requires compliance "in accordance with" SB1124-55-020 Revision 2 for inspections and SB1124-55-021 Revision 3 for replacement, or "later Israel CAA approved revision" (Requirement). The AMM is also incorporated for the terminating modification MOD AFC2081 (Note 1). This AD does not itself set technical inspection procedures; it depends on the SBs and the AMM to set the detailed technical requirements. That reliance means the AD’s practical content is dependent on the content and approval status of those external documents.

Cross-jurisdictional technical harmonisation: The AD is an Australian CASA instrument that explicitly aligns with, and reacts to, an Israel CAA AD. Amendment 3 was issued "in response to a revision of the related CAA AD, which introduces a strengthened aft spar splice fitting made of titanium" (Background). The AD thus demonstrates cross-jurisdictional regulatory alignment for this aircraft type: CASA’s Directive requires compliance with Israel CAA-approved revisions of the SBs/AMM and tracks the Israel CAA’s technical solution (installation of the titanium fitting).

Operational rules and maintenance manuals: The AD requires actions "in accordance with" the AMM for MOD AFC2081 and notes that the AMM contains a "considerably longer inspection interval" for modified aircraft in Chapter 5 (Note 1). That shows how the AD delegates ongoing inspection policy for modified aircraft to the AMM rather than prescribing a specific interval within the AD.

Absence of explicit legal harmonisation language beyond technical documents: The AD does not state how it interacts with other Australian aviation regulations (for example, civil penalties, airworthiness directive appeal mechanisms, or continuing airworthiness obligations under Australian aviation law). The AD’s text is limited to technical mandates and references to the Israel CAA as the approving authority for the SBs and AMM revisions mentioned.

Therefore, in the limited scope of the AD text, interaction occurs primarily through incorporation and reliance on the Israel CAA-approved SBs and AMM, and through explicit cross-reference to Israel CAA AD 85-001 R3. Broader legal interactions with Australian aviation statutes and enforcement mechanisms are not described in this Directive.

The AD text contains an internal amendment trail and explanatory notes identifying earlier changes. The information in the Directive allows a chronology of relevant changes as follows.

Current instrument: AD/IAI-W/9 Amendment 3 is the instrument presented, dated 28 February 2008 and stated to "become effective on 10 April 2008" (signature block; Compliance). The heading identifies it as "AD/IAI-W/9 Amdt 3" and repeats that multiple times in the document.

Earlier amendment reference: The Background section records that "Amendment 2 reduced the inspection interval from 600 to 300 flight hours" (Background). That identifies the substantive change implemented in Amendment 2 , a shortening of the repeat inspection interval , and allows a reader to infer that Amendment 1 or the original AD had a 600 flight-hour inspection interval.

Reason for Amendment 3: The AD states that "Amendment 3 is issued in response to a revision of the related CAA AD, which introduces a strengthened aft spar splice fitting made of titanium. There is no additional work required by this issue of the Directive" (further Background). That shows Amendment 3’s purpose was to align CASA’s Directive with the Israel CAA’s technical solution (the titanium fitting). The AD thereby documents that Amendment 3 does not impose new inspection or replacement tasks on top of previous requirements; instead it recognises the titanium splice fitting introduced by the Israel CAA AD and notes the terminating action consequence.

Notes indicating linked materials and revisions: The Requirement clauses repeatedly allow the use of "later Israel CAA approved revision" of the SBs and the AMM for the terminating modification (Requirement; Note 1). That provides a mechanism by which future revisions approved by Israel CAA would be acceptable for compliance purposes without further amendment to the CASA AD, subject to CASA’s acceptance procedures implied by the phrasing.

Administration dates: The signature block is dated 28 February 2008 and the AD "becomes effective on 10 April 2008" (signature block; Compliance). These dates provide the administrative timeline for the issuance and the operational start of the Directive.

In sum, the amendment history recorded in the AD shows an initial AD with a 600 flight-hour inspection interval, Amendment 2 reducing that interval to 300 flight hours, and Amendment 3 aligning CASA’s Directive with an Israel CAA revision that introduced the titanium splice fitting and provided a terminating modification option. The AD text does not provide full historical texts of prior amendments, but it documents the key substantive changes relevant to inspection intervals and the terminating modification.

The supplied Directive contains no litigation record, court citations, or references to judicial proceedings. There are no cases named in the AD, no references to litigation outcomes, nor any mention of legal challenges to this instrument in the text provided.

What is present in the document is administrative provenance: the AD is issued by the Civil Aviation Safety Authority as shown by the signature block, which records "David Villiers, Delegate of the Civil Aviation Safety Authority" and the issuance date 28 February 2008. The AD does not describe any disputes, appeals, or legal proceedings arising from its issuance.

Because the AD text does not contain litigation history, there is no source-grounded material within this instrument from which to draw concrete statements about judicial interpretation, compliance disputes, or enforcement litigation. Any external litigation or appeal routes that may exist under broader aviation law or administrative law are not described in this Directive. Therefore readers must rely on other sources beyond this document to determine whether any litigation or legal challenges occurred in relation to AD/IAI-W/9 or its amendments.

In short, the AD provides no litigation history; the text is silent on judicial or administrative challenge outcomes, and makes no reference to case law or proceedings.

The Directive contains several specific technical and procedural features that may pose compliance pitfalls if overlooked. Each of these points is grounded in the AD text.

Applicability covers all serial numbers: the AD applies to "All Model 1124 and 1124A aircraft, all serial numbers" (Applicability). Operators cannot assume the AD only targets a subset of their fleet; the applicability is broad for these types.

Requirement references external SBs and AMM revisions: inspections and replacements must be performed "in accordance with" specified Service Bulletins and the AMM, "or later Israel CAA approved revision" (Requirement; Note 1). A common pitfall is to perform inspections using unapproved or non-current documents; the AD requires Israel CAA approved revisions. Operators should confirm the approval status of any SB/AMM revision used for compliance.

Timing interplay with previous Directive: the AD’s initial compliance window is "Within 75 flight hours after 10 April 2008, unless inspected within the last 225 flight hours since compliance with the previous issue of this Directive" (Compliance). That conditional creates a potential confusion point: whether an operator who performed an inspection under the previous issue within the last 225 flight hours meets the initial requirement. Operators must reconcile their maintenance records against the "previous issue" compliance history to determine whether the 75 FH window applies.

Repeat inspection interval applies until modification: the AD requires inspection "at intervals not to exceed 300 flight hours; until a titanium splice fitting (MOD AFC2081) is installed" (Compliance). Operators must therefore not treat the 300 FH interval as permanent if the modification has not been performed. Some might incorrectly assume MOD AFC2081 is optional; it is optional insofar as it is a terminating action, but until installed the inspection cadence at or below 300 FH remains mandatory.

Replacement pre-flight obligation: If cracks are detected, the AD requires replacement "before further flight" (Requirement). That creates an immediate grounding obligation where cracking is found. Failure to ground and replace prior to flight would put the operator outside the AD’s explicit compliance requirement.

Terminating modification scope and scheduling: Note 1 states that incorporation of the titanium splice fitting P/N WW4453005-509 (MOD AFC2081) "in accordance with the Aircraft Maintenance Manual (AMM) constitutes terminating action for the requirements of this Directive" and that the AMM contains a "considerably longer inspection interval for modified aircraft" in Chapter 5. The AD does not state the longer interval numerically; operators must consult the AMM Chapter 5 to determine the new inspection schedule. A gotcha is assuming a particular interval without checking the AMM.

"Serviceable fitting" meaning: The AD requires replacement with a "serviceable fitting in accordance with SB1124-55-021 Revision 3, or later Israel CAA approved revision" (Requirement). The AD does not define "serviceable" beyond that SB, so operators must ensure that any replacement part and the procedures used are those specified in the SB or an Israel CAA approved revision.

Cross-jurisdictional approvals: The AD is an Australian instrument that mandates compliance with "Israel CAA approved revision[s]" of SBs and AMM documents. If an operator uses a revision that is approved in another jurisdiction but not Israel CAA approved, the AD’s condition may not be satisfied. Operators should verify Israel CAA approval status, not merely the existence of a revision.

No enforcement details within AD: The AD provides no explicit enforcement or penalty text. Operators should not assume that absence of penalties in the AD means non-compliance carries no consequences; the AD’s operational prescriptions are mandatory even if enforcement details are not included here.

Documentation and record implications: While the AD does not state specific recordkeeping requirements, the conditional compliance window tied to inspections "since compliance with the previous issue of this Directive" requires operators to have accessible, accurate maintenance records demonstrating inspection dates and flight hours. Failure to document could lead to disputes about whether the 75 FH window applied.

In summary, the principal gotchas derive from the AD’s reliance on externally approved SBs/AMM revisions, conditional timing linked to prior compliance history, a mandatory pre-flight replacement requirement where cracking is found, and the need to confirm Israel CAA approval status for referenced documents. Operators should consult the named SBs and the AMM Chapter 5 for the technical detail necessary to avoid these pitfalls.

The AD’s compliance path is prescriptive and narrowly defined. The following step-by-step approach is directly grounded in the AD text.

1. Confirm applicability: Verify whether each aircraft is an IAI Model 1124 or 1124A. The AD applies to "All Model 1124 and 1124A aircraft, all serial numbers" (Applicability). If the aircraft is an affected type, proceed.

2. Identify relevant documents and approvals: Obtain Israel Aircraft Industries Service Bulletin SB1124-55-020 Revision 2 and SB1124-55-021 Revision 3, and the Aircraft Maintenance Manual (AMM). Ensure the specific revisions you intend to use are "Israel CAA approved revision[s]" as required by the AD (Requirement; Note 1). If later Israel CAA-approved revisions exist, those may be used.

3. Schedule initial inspection within the AD’s initial window: The Directive mandates inspection "within 75 flight hours after 10 April 2008, unless inspected within the last 225 flight hours since compliance with the previous issue of this Directive" (Compliance). Determine whether an inspection satisfying the previous issue of the AD was performed within the last 225 flight hours; if so, the 75 FH requirement may not apply. Maintain records demonstrating that prior inspection if relying on the exception.

4. Perform the inspection per SB1124-55-020 Rev 2: Conduct the inspection "in accordance with" the SB to detect cracking of the horizontal stabiliser rear spar splice fitting P/N 453005-501 (Requirement). Because the AD does not contain the inspection technique, follow the SB’s procedures precisely and ensure all steps and acceptance criteria are met.

5. If no cracking is evident, schedule recurring inspections: The AD requires inspection "at intervals not to exceed 300 flight hours; until a titanium splice fitting (MOD AFC2081) is installed" (Compliance). Establish maintenance planning tasks to ensure inspections occur within this interval and document each inspection.

6. If cracking is detected, ground the aircraft until replacement: The AD requires that where cracks are detected the operator must, "before further flight, replace the splice fitting with a serviceable fitting in accordance with SB 1124-55-021 Revision 3, or later Israel CAA approved revision" (Requirement). Follow the replacement SB for removal and installation procedures, torque, checks and any associated non-destructive testing or inspections.

7. Consider the terminating modification: The AD notes that installing the titanium splice fitting P/N WW4453005-509 (MOD AFC2081) per the AMM "constitutes terminating action for the requirements of this Directive" (Note 1). If an operator prefers to reduce inspection frequency and remove the ongoing 300 FH cycle, plan and perform MOD AFC2081 in accordance with the AMM, ensuring the modification work and parts are installed per the AMM and that the AMM revision used is Israel CAA approved. After modification, consult AMM Chapter 5 for the "considerably longer inspection interval" applicable to modified aircraft.

8. Confirm part numbers and traceability: When ordering replacement fittings or the titanium part, ensure the exact part number P/N WW4453005-509 is procured for the terminating modification, and that any replacement fitting used when cracking is detected is "serviceable" and procured/installed per SB1124-55-021 Rev 3 or later Israel CAA approved revision (Requirement; Note 1).

9. Maintain maintenance records that support compliance: While the AD does not specify recordkeeping, compliance depends on demonstrating inspection history relative to specified flight-hour intervals and the previous issue of the AD (Compliance). Keep dated inspection reports, flight-hour tallies, SB/AMM revision numbers used, and work packages showing part numbers and MOD AFC2081 incorporation where performed. These records will show whether the initial 75 FH window applied and whether inspections were performed within the required 300 FH cycles.

10. Use only Israel CAA approved revisions for compliance: Wherever the AD permits "later Israel CAA approved revision" for SBs or AMM, confirm Israel CAA approval of any revision you rely on. Do not treat approvals by other jurisdictions as automatically satisfying the AD’s Israel CAA approval requirement (Requirement; Note 1).

11. Coordinate with CASA where necessary: The AD is issued by CASA (signed by the delegate). If an operator has questions about acceptance of alternative procedures, subtleties in the AD text, or coordination of the terminating modification’s certification under the Australian registry, those matters should be raised with CASA. The AD itself does not set out appeal or waiver procedures.

By following these steps closely and using the specified SBs and AMM revisions that are Israel CAA approved, operators will implement the AD’s inspection and corrective-action regime or will incorporate the terminating modification to remove the inspection obligation under this Directive.