AD/ROCK-114/14 Amdt 1 - Rudder Spar

The AD is structured around a few interlocking technical and regulatory concepts that determine operator obligations and the mechanics of compliance.

Applicability defines the population subject to the directive: Model 114 aircraft with serial numbers 14000-14499 inclusive (Applicability). This is a serial-number‑specific obligation rather than a whole-model blanket, so it limits the AD’s engineering scope to a discrete fleet subset.

Inspection scope and methods. Requirement 1 is a short, immediate visual inspection of the rudder spar near the upper hinge fitting, coupled with a manual movement test of the rudder tip to detect excessive play (Requirement 1). Requirement 2(a) prescribes a full removal of the rudder assembly and a dye penetrant inspection of specific structural areas (forward face of the spar web, bend radius, flanges, angle doublers P/N 44006-RE3 if installed) in accordance with Rockwell SL-114-17 and CAO 108.10 (Requirement 2(a)). The AD therefore layers a rapid screening check with a definitive non-destructive inspection technique when circumstances require.

Repair threshold and operational effect. The AD sets a concrete repair threshold: cracks, including stop-drilled cracks, that extend beyond installed angle doublers must be repaired by replacement of the rudder spar before further flight (Requirement 2(a)). The text uses the phrase "before further flight", attaching an operational constraint to certain inspection outcomes.

Modification as terminating action. Requirement 2(b) supplies a modification pathway,installing angle doublers P/N 44006-RE3 per Rockwell SL-114-17, Figure 1,as the end state that removes the need for the repeated 200-hour re-inspections. The spar, however, "must be free of cracks before modification". The AD therefore treats the modification as a mitigating measure but insists on a crack-free precondition.

Evidence burden and presumption. The AD contains an evidentiary rule: any spar with angle doublers installed shall be regarded as cracked unless there is positive confirmation that the spar was crack free when the angle doublers were installed (Requirement 2(b)). This allocates the burden of proof to the operator or maintainer to show the pre-existing spar condition at the moment of earlier modification. It also distinguishes prior compliance with cancelled AD/ROCK-114/10 from compliance under the present directive.

Timeframes and retroactivity. The Compliance section assigns inspection deadlines anchored to 25 May 1995: Requirement 1 within 10 hours TIS after 25 May 1995, Requirement 2(a) before 100 hours TIS after 25 May 1995, and repeated inspections at intervals not exceeding 200 hours TIS until modification (Compliance). The AD itself was amended and became effective in November 2008, but the compliance windows reference a 1995 anchor date. The Background confirms the amendment’s purpose to require repeat inspections until modification because of a report of substantial cracking approximately 1500 hours TIS after compliance with the cancelled AD/ROCK-114/10.

Technical references. The AD relies on external technical documents: Rockwell Service Letter SL-114-17 (including Figure 1) and CAO 108.10 for the dye penetrant inspection method, and the aircraft Maintenance Manual, Section VII, for the removal of the rudder assembly (Requirement 2(a), Requirement 2(b)). These references tie regulatory compliance to manufacturer and regulatory inspection standards rather than prescribing technical steps in the AD text itself.

Authority and provenance. The instrument is issued under the Civil Aviation Safety Authority (CASA) delegate, shown by the signature of David Villiers dated 7 October 2008 and the stated effective date of 20 November 2008. The Background explains the rationale , a report of substantial cracking discovered after earlier compliance with a cancelled directive , but is framed as the reason for the amended inspection and modification requirements rather than as evidence of causation beyond that report.

Collectively, the main concepts define a narrowly targeted, procedure-driven regulatory intervention that sequences screening, diagnosis, repair/replace, and a terminating structural modification, backed by specific service documents and a presumption rule about past modifications.

The AD affects owners and operators of Gulfstream (Rockwell) Model 114 aeroplanes bearing serial numbers 14000 through 14499 inclusive (Applicability). That is the explicitly identified universe of aircraft to which the requirements apply. Any operator responsible for the continuing airworthiness of an aircraft within that serial-number range must comply with the inspection and modification regimes set out in the AD.

Maintenance organisations, engineers and maintainers who perform the mandated inspections and modifications are also directly engaged by the AD, because Requirement 2(a) requires removal of the rudder assembly "as outlined in the Maintenance Manual, Section VII", and specifies the dye penetrant inspection method must follow Rockwell Service Letter SL-114-17 and CAO 108.10. Those references effectively require maintainers to follow manufacturer and regulator-prescribed procedures and standards when carrying out the work.

Part suppliers and parts managers are implicated because the modification requires installation of angle doublers P/N 44006-RE3 (Requirement 2(b)) and other work may require replacement rudder spars where cracks extend beyond doublers (Requirement 2(a)). The AD names the exact part number for the doublers, creating a parts specificity that affects procurement and inventory decisions.

Regulatory administrators at the Civil Aviation Safety Authority are engaged in issuance and post-issue oversight; the AD is signed by the CASA delegate (David Villiers) and carries an effective date (20 November 2008). The AD’s inclusion of references to a cancelled AD (AD/ROCK-114/10) and to service letter SL-114-17 creates a chain of compliance documentation that regulators may use to audit operator records.

Airworthiness inspectors and certificating staff who assess aircraft for continued operation are affected in the sense that inspection outcomes can impose restrictions: the AD requires that if cracks extend beyond installed angle doublers they "must be repaired by replacement of the rudder spar before further flight" (Requirement 2(a)). That phrase creates an operational bar for aircraft with specified crack outcomes pending repair.

Insurance underwriters and financiers have an interest insofar as the AD prescribes mandatory structural work and operational limitations on a defined fleet cohort; the AD may affect planned maintenance budgets, aircraft downtime, and perceived airworthiness risk, although the AD does not itself set financial terms.

Finally, the AD’s presumption rule , that any spar with angle doublers installed shall be regarded as cracked unless definite evidence exists that the spar was crack-free when those doublers were installed , creates evidentiary obligations for prior operators and maintainers who performed earlier modifications. Those entities may need to produce maintenance documentation to rebut the presumption, which affects record-keeping and traceability responsibilities for past work.

The AD does not extend beyond the specified serial-number cohort and does not make broader model-wide statements. The source contains no explicit list of approved organisations, no exemptions, and no alternative means of compliance, so affected parties are the operators, maintainers, parts suppliers and regulatory staff who service, certify, or finance aircraft within the serial-number range.

The AD establishes concrete duties on operators and maintainers within the Applicability range and some procedural conditions that affect rights to operate.

Primary duties

• Conduct a visual inspection of the rudder spar near the upper hinge fitting and a manual check for excessive movement by moving the rudder tip fore/aft and left/right (Requirement 1). This must be performed within 10 hours time in service after 25 May 1995 (Compliance).

• Remove the rudder assembly and the rudder tip assembly and upper hinge fitting in accordance with the Maintenance Manual, Section VII, and carry out dye penetrant inspections of the forward face of the rudder spar web, bend radius, flanges and any angle doublers P/N 44006-RE3, as specified by Rockwell Service Letter SL-114-17 and CAO 108.10 (Requirement 2(a)). This initial detailed inspection must occur before 100 hours TIS after 25 May 1995; re-inspection must occur at intervals not exceeding 200 hours TIS until the modification is completed (Compliance).

• If cracks (including stop drilled cracks) extend beyond installed angle doublers P/N 44006-RE3, repair by replacement of the rudder spar is mandatory "before further flight" (Requirement 2(a)). This creates a duty to effect replacement prior to continued operation in those cases.

• Modify the rudder spar upper hinge attachment area by installing angle doublers P/N 44006-RE3 according to Rockwell SL-114-17, Figure 1 (Requirement 2(b)). The rudder spar must be confirmed free of cracks before undertaking this modification.

Evidentiary and burden-of-proof duty

• Operators bear a burden of proof where angle doublers are already installed. The AD states that any spar with angle doublers installed shall be regarded as cracked unless it can be positively confirmed that the rudder spar was crack free when the angle doublers were installed (Requirement 2(b)). That is an affirmative evidentiary duty to produce maintenance records showing spar condition at the time of earlier installation.

Timing and continuity duties

• The AD’s Compliance section sets definitive time anchors: inspection within 10 hours and within 100 hours referenced to 25 May 1995, and recurrent inspections at not more than 200 hours TIS until the modification is performed. Those timings create an ongoing duty to repeat inspections at the specified frequency until the terminating modification is completed.

Rights and constraints

• The directive does not explicitly set out discretionary rights, exemptions or alternate means of compliance within its text. It requires adherence to the specified service documents (Rockwell SL-114-17, CAO 108.10) and to the aircraft Maintenance Manual for removal procedures, and prescribes replacement before further flight where specified cracks are found. The absence of an alternative means-of-compliance clause in the text means operators must follow the stated procedures unless otherwise authorised outside the text; the AD does not itself specify a process for approval of alternatives in its content.

• Operational constraint: the phrase "must be repaired by replacement of the rudder spar before further flight" functions as a conditional suspension of flight in instances where crack thresholds have been met. That is a rights-limiting operational instruction for affected aircraft.

Record and proof obligations are implicit from the presumption rule concerning previously installed angle doublers: the right to avoid treating a spar as cracked is contingent on positive confirmation (documentation) that the spar was crack-free at the time of installation.

Other duties implied by references. The AD requires maintainers to follow Rockwell SL-114-17 and CAO 108.10 for dye penetrant inspection and to use Maintenance Manual Section VII for rudder removal. These references effectively bind the technical method and procedures used during compliance.

The AD does not include language on who pays, civil penalties, or enforcement processes in its text. The duties above are the affirmative actions the AD prescribes; the AD sets no express rights such as compensation, exemptions, or timelines for administrative review within the text provided.

The AD text does not specify statutory penalties, fines, or a procedural enforcement regime within the printed instrument. It prescribes mandatory technical actions and timelines (Requirement 1; Requirement 2(a) and 2(b); Compliance), but it contains no stated civil or criminal sanction clause, no administrative penalty schedule, and no enforcement mechanism described in the document itself.

Operationally significant instructions in the AD function as enforceable airworthiness requirements by their nature (for example, "must be repaired by replacement of the rudder spar before further flight" in Requirement 2(a)). That phrase creates an operational bar for aircraft with specified crack outcomes pending repair. While the AD text itself does not label this as a 'grounding' order, the phrase imposes a non-optional remedial step before continued operation, which in practice is an enforceable compliance condition from an airworthiness perspective.

The AD names the regulatory issuer: the Civil Aviation Safety Authority, with the delegate signing the instrument (David Villiers, 7 October 2008), and records an effective date (20 November 2008). The presence of a CASA delegate signature indicates the directive is an official CASA instrument, and enforcement and oversight would ordinarily be administered by the relevant aviation regulator. However, the AD as presented does not enumerate the specific enforcement procedures, inspection or audit steps that CASA would use to verify compliance, nor does it set out civil sanctions, licence consequences, or penalties for non-compliance in the document content provided.

Because the AD ties compliance to manufacturer and regulatory technical references,Maintenance Manual Section VII, Rockwell SL-114-17 and CAO 108.10,inspectors verifying compliance would likely reference those documents when assessing whether required inspections and modifications have been carried out correctly. The AD’s presumption that spars with previously-installed angle doublers be treated as cracked unless positive confirmation exists introduces an evidentiary standard that may be used by an inspector to assess compliance in the absence of contemporaneous documentation.

The Lack of explicit penalty language in the AD means that any remedy for non-compliance would arise from the regulator’s usual enforcement powers outside the AD text, or from other statutory provisions that govern aircraft operation and airworthiness. The AD itself, however, remains the operative technical requirement that an operator must meet for the named serial-number cohort.

In short, the AD imposes mandatory technical duties and creates operational constraints but does not include in its text an explicit penalty regime or specific enforcement procedures. The document’s authority comes from CASA delegation and the standard regulatory process that issues such directives, but the instrument does not detail enforcement mechanisms or penalties within the provided content.

The AD cross-references other regulatory and manufacturer-issued documents rather than enacting standalone technical specifications. The AD requires inspections and modifications "in accordance with" Rockwell Service Letter SL-114-17 and CAO 108.10 (Requirement 2(a)), and removal procedures "as outlined in the Maintenance Manual, Section VII" (Requirement 2(a)). Those references create an operational interaction: compliance with the AD requires adherence to pre-existing manufacturer guidance and to the referenced CAO procedure. The AD therefore channels compliance through those documents rather than repeating technical instructions in full.

The AD explicitly addresses relationship with a cancelled prior AD. It states that "Previous compliance with cancelled AD/ROCK-114/10 does not necessarily constitute compliance with this AD" (Requirement 2(b); Background). This creates a legal distinction between a historical directive (AD/ROCK-114/10) and the current instrument, and signals that operators cannot assume earlier compliance absolves them under the present AD unless specific evidentiary conditions are met. That interaction imposes an evidentiary overlay: where angle doublers were installed under the earlier directive, the operator must be able to "positively confirm" that the spar was crack-free at the time of that earlier installation; otherwise the spar is to be regarded as cracked (Requirement 2(b)). This presumes an evidentiary relationship between past compliance records and current obligations.

By mandating inspection methods in accordance with CAO 108.10, the AD interacts with whatever regulatory standard CAO 108.10 sets for dye penetrant inspection. The AD does not restate CAO 108.10 but requires compliance with it, thereby incorporating that standard into the compliance obligation. Similarly, referencing the Maintenance Manual and Rockwell Service Letter integrates manufacturer instructions into the regulatory requirement.

The AD’s inscription of "must be repaired by replacement of the rudder spar before further flight" for certain crack outcomes imposes an operational limitation that interacts functionally with broader aviation safety rules governing airworthiness and allowable operations. The AD does not, however, recite other legislative provisions or provide a statutory cross-reference to enforcement powers; the interaction with enforcement authorities or civil aviation statute is implicit in the CASA delegate’s signature and the conventional regulatory architecture surrounding ADs.

There is no explicit mention in the AD text of exemptions, alternative means of compliance, or how conflicts with other maintenance obligations should be resolved. The AD’s specificity about parts (angle doublers P/N 44006-RE3) and inspection methods implies a prescriptive interaction with parts procurement and maintenance documentation regimes.

Finally, the AD’s effective date (20 November 2008) and its anchoring of compliance windows to 25 May 1995 create an unusual temporal interaction: operators are given compliance actions tied to time-in-service counters referenced to a date decades earlier. The AD does not explain in legal terms how that retroactive timing interacts with other statutory or regulatory deadlines; the text simply establishes the inspection deadlines as stated.

In sum, the AD interacts with other laws and norms mainly by incorporating manufacturer service letters, regulatory inspection standards (CAO 108.10), and prior AD history into its compliance structure, and by setting evidentiary and operational connections to previous directives (AD/ROCK-114/10). The AD itself does not provide an integrated legal enforcement clause; its normative force is exercised through the standard regulatory framework of CASA and the referenced technical documents.

The document is titled AD/ROCK-114/14 Amdt 1 and carries a date code of 12/2008 in the header. The AD records that it "becomes effective on 20 November 2008" and is signed by David Villiers, Delegate of the Civil Aviation Safety Authority, dated 7 October 2008. The Background section explains that this instrument is an amendment that includes a specific statement clarifying that "previous compliance with cancelled AD/ROCK-114/10 does not constitute compliance with this AD", despite the fact that the requirement document, Rockwell Service Letter SL-114-17, is the same for both directives.

The AD thus sits in a sequence: it supersedes or follows an earlier AD identified as AD/ROCK-114/10, which has been cancelled. The new element introduced by Amdt 1 is not a change in the technical inspection document (SL-114-17 remains the requirement document) but an added declaratory provision altering the legal effect of prior compliance. The Background notes a practical reason for that change: a prior report of substantial cracking on one aircraft approximately 1500 hours TIS after compliance with the now-cancelled AD/ROCK-114/10. That report motivated the inclusion of repeat inspections and the presumption rule about angle doublers.

The compliance timeframes referenced within the AD are anchored to 25 May 1995, which suggests the AD’s substantive inspection and modification requirements have roots extending back substantially prior to the amendment date. The AD’s text shows that the immediate inspection and the removal-and-dye-penetrant inspection originally had compliance deadlines in 1995 (Requirement 1 and Requirement 2(a), Compliance). The amendment in 2008 confirms the continuing need for repeat inspections until the modification is completed and adds the evidentiary clarification regarding prior compliance and angle doubler installations.

Beyond the labels in the text (Amdt 1), the AD does not provide a chronological log of earlier amendments, nor does it include dates for the cancelled AD/ROCK-114/10. The only explicit temporal markers present are the 25 May 1995 TIS anchor for compliance timeframes, the report of cracking "approximately 1500 hours TIS after compliance with now cancelled AD/ROCK-114/10" (Background), the delegate signature date 7 October 2008, and the stated effective date 20 November 2008.

The amendment history, to the extent it is recorded in the AD, therefore shows a practical evolution: an initial directive or action under AD/ROCK-114/10, subsequent discovery of cracking at substantive flight hours after compliance, cancellation of the earlier AD, and issuance of the amended AD/ROCK-114/14 Amdt 1 in 2008 which restores continuing inspections, a modification pathway, and an evidentiary presumption to address aircraft already modified. The AD does not record other amendments or rescissions, nor does it provide text from the cancelled AD for direct comparison.

The AD text contains no information about litigation, appeals, administrative proceedings, or judicial consideration. There are no case names, decisions, or references to legal challenges in the document provided.

Given that omission, the AD as presented has no litigation history recorded in its contents. The document is an administrative directive issued by the Civil Aviation Safety Authority (signed by a delegate) and is presented as an operational safety requirement; but the AD itself does not contain or record any dispute resolution outcomes, legal challenges, or court or tribunal determinations arising from its issuance or application.

To the extent that remedial or enforcement action would occur under broader aviation enforcement statutes or regulations, that material is not captured in this AD text. The Background describes a reported technical finding of substantial cracking after compliance with a prior directive, but it does not refer to any litigation about that event.

Therefore, within the limits of the source provided, there is no litigation history to summarise.

Several details in the AD are technically and administratively consequential and could trip up operators, maintainers and document managers if overlooked.

Serial-number specificity. The AD applies only to Model 114 aircraft with serial numbers 14000-14499 inclusive (Applicability). Operators must verify serial numbers precisely. Treating this as a model-wide obligation or failing to verify serial numbers may misapply the directive.

Backdated compliance anchors. The Compliance section anchors inspection windows to 25 May 1995 (Requirement 1 within 10 hours TIS after that date; Requirement 2(a) before 100 hours TIS after that date; continuing re-inspections at not more than 200 hours TIS until modification) despite the amendment being effective in 2008. Operators must take care to interpret these time anchors correctly in relation to their aircraft's time-in-service counters. The AD text does not provide explanation for the backdating; it should be read literally as the specified deadlines.

Evidentiary presumption about angle doublers. The AD states that "any spar with angle doublers installed shall be regarded as cracked unless it can be positively confirmed that the rudder spar was crack free when the angle doublers were installed" (Requirement 2(b)). That presumption shifts the evidentiary burden to operators and maintainers who installed or subsequently inherited aircraft with angle doublers. If documentation proving the pre-installation spar condition is absent or inconclusive, the operator must treat the spar as cracked and follow the AD’s requirements (including potential replacement before flight). This can be critical for aircraft that underwent modifications under the earlier AD/ROCK-114/10.

Replacement before further flight. The directive’s remedy for cracks that "extend beyond installed angle doublers" is "repair by replacement of the rudder spar before further flight" (Requirement 2(a)). That language creates an immediate operational constraint: certain inspection outcomes necessitate replacement prior to continuing to fly. Operators should be aware that replacement is the mandated fix in those circumstances, not a temporary repair.

Specific parts and documents named. The AD prescribes angle doublers P/N 44006-RE3 and references Rockwell Service Letter SL-114-17 (including Figure 1), CAO 108.10 for dye penetrant inspection, and Maintenance Manual Section VII for rudder removal (Requirement 2(a) and 2(b)). Compliance requires access to the specified parts and documents. Failing to follow the named documents could entail non-compliance.

Stop drilled cracks treated equally. The AD explicitly includes stop drilled cracks in the repair threshold language ("Cracks, including stop drilled cracks, which extend beyond installed angle doublers... must be repaired" (Requirement 2(a))). Operators must therefore not assume that stop-drilled crack mitigation suffices where the crack extends beyond the doublers.

Applicability of previous AD. The AD clarifies that prior compliance with a cancelled AD (AD/ROCK-114/10) does not automatically discharge obligations under this AD. Operators who relied on earlier compliance certificates should verify whether they can produce the positive confirmation required to avoid being treated as cracked.

Re-inspection cadence until modification. The AD mandates re-inspection at intervals not exceeding 200 hours TIS until the modification is completed (Compliance). That creates continuing maintenance scheduling and downtime implications until the terminating action (installation of angle doublers) is performed.

Ambiguity on enforcement and alternative compliance. The AD includes no explicit alternative means of compliance, no stated exemptions, and no penalties in the text. Operators should not infer that alternatives are permitted absent engagement with the competent authority. The AD’s silence requires operators to engage the regulator where a different technical approach is contemplated.

Record-keeping consequence. While the AD does not mandate record-keeping forms, the presumption rule effectively makes historical maintenance documentation decisive. Lack of record evidence that the spar was crack-free when angle doublers were installed will result in treating the spar as cracked and implementing the AD’s requirements.

In sum, the most actionable "gotchas" are: verifying serial numbers, handling the unusual 1995 compliance anchors, producing positive confirmation for prior doublers installations, understanding that certain crack findings mandate spar replacement before flight, and ensuring access to specific parts and service documents.

Follow the AD’s sequential actions exactly, referencing the named documents and part numbers. The AD sets out concrete technical tasks, timing windows, and terminating modifications. Operators and maintainers must read and execute the following steps as written in the AD.

1. Confirm applicability. Verify the aircraft’s serial number. The AD applies only to Gulfstream (Rockwell) Model 114 aircraft with serial numbers 14000 to 14499 inclusive (Applicability). If the serial number is outside that range, the AD does not apply as written.

2. Immediate visual screening (Requirement 1). Within the time window specified (within 10 hours time in service after 25 May 1995), perform a visual inspection of the rudder spar near the upper hinge fitting for signs of cracking. As part of this screening, attempt to move the rudder tip fore and aft and left to right to detect excessive movement. Record the inspection result in the aircraft’s maintenance documentation consistent with normal maintenance records practice. The AD specifies the inspection content in Requirement 1.

3. Detailed inspection on removal (Requirement 2(a)). Before 100 hours TIS after 25 May 1995, perform the initial detailed inspection described in Requirement 2(a). This requires removal of the rudder assembly from the aircraft "as outlined in the Maintenance Manual, Section VII". Remove the rudder tip assembly and the upper hinge fitting. Inspect the forward face of the rudder spar web, bend radius, flanges and any angle doublers P/N 44006-RE3 for cracks in the upper hinge fitting attachment area. Use the dye penetrant method for inspection, following Rockwell Service Letter SL-114-17 and CAO 108.10. If cracks are found, including stop drilled cracks, and they extend beyond installed angle doublers, the AD mandates repair by replacement of the rudder spar before further flight. Ensure compliance with the exact inspection scope in Requirement 2(a).

4. Re-inspections until modification. If the rudder spar has not been modified in accordance with Requirement 2(b), conduct re-inspections at intervals not to exceed 200 hours TIS until the modification is completed (Compliance). Maintain schedules to ensure adherence to the 200-hour maximum interval.

5. Modification (Requirement 2(b)). Modify the rudder spar upper hinge attachment area by installing angle doublers P/N 44006-RE3 in accordance with Rockwell SL-114-17, Figure 1. The rudder spar must be free of cracks before modification may be carried out. Use the exact part number and follow the figure and procedures in SL-114-17 as required by the AD.

6. Handling existing angle doublers. If angle doublers P/N 44006-RE3 are already installed on the spar, the AD instructs that the spar "shall be regarded as cracked unless it can be positively confirmed that the rudder spar was crack free when the angle doublers were installed". Operators must therefore produce positive confirmation,maintenance records or other firm evidence,showing the spar condition at the time of earlier installation to avoid treating the spar as cracked.

7. Remedy thresholds. If inspection identifies cracks that extend beyond installed angle doublers, replace the rudder spar before further flight (Requirement 2(a)). This is the required remedial action for that condition.

8. Use the referenced documents. Execute the removal, inspection and modification work in accordance with the Maintenance Manual Section VII, Rockwell Service Letter SL-114-17 (including Figure 1 for installation of angle doublers), and the dye penetrant inspection method per CAO 108.10. The AD binds compliance to those documents.

9. Record outcomes. The AD itself does not prescribe a specific form of record entry, but the presumption about angle doublers and the need to show whether the spar was crack-free at the time of prior doubler installation make maintaining and assembling continuous, dated maintenance records essential. Log inspection dates, findings, part numbers fitted, and serial-number confirmations for affected aircraft.

10. Engage qualified maintainers. Requirement 2(a) requires removal of the rudder assembly and dye penetrant inspections, which are specialist tasks. Ensure personnel performing the work are competent to follow Maintenance Manual Section VII, Rockwell SL-114-17 and CAO 108.10 procedures.

11. Plan for parts and downtime. The modification requires angle doublers P/N 44006-RE3 and, if replacement is needed, a replacement rudder spar. Plan procurement and aircraft downtime accordingly. The AD’s re-inspection cadence (every 200 hours TIS until modification) means the aircraft may undergo repeated maintenance intervals until the modification is completed.

12. Questions and alternatives. The AD text does not supply an alternative means of compliance or waiver process. If an operator wishes to pursue an alternative technical solution or a different schedule, that must be handled through the regulator’s usual channels outside the AD text; the AD itself prescribes the processes and documents above.

13. Observe the AD’s effective date and signature. The AD became effective 20 November 2008 and is signed by David Villiers, Delegate of the Civil Aviation Safety Authority (7 October 2008). Ensure that compliance is demonstrable against the AD’s stated requirements and dates.

In practice, the compliance path is: confirm applicability, perform the immediate visual check, undertake the removal-and-dye-penetrant inspection per the referenced documents within the specified time windows, replace the spar before flight if cracks extend beyond doublers, or install the specified angle doublers (after confirming the spar is free of cracks) as the terminating action, and continue re-inspections at intervals not exceeding 200 hours TIS until the modification is completed. Maintain documentary proof, especially where angle doublers are already present, because the AD treats previous installations as indicia of cracking unless affirmative evidence exists.