{"id":"F2008L04110","name":"AD/ROCK-114/14 Amdt 1 - Rudder Spar","slug":"ad-rock-114-14-amdt-1-rudder-spar","collection":"legislative_instrument","jurisdiction":"commonwealth","status":"in_force","isInForce":true,"actNumber":null,"makingDate":null,"administeringDepartment":null,"currentVersion":{"id":76018,"registerId":"commonwealth-F2008L04110-current","compilationNumber":null,"startDate":"2026-04-02","status":"InForce","reasons":null,"registeredAt":null},"sections":[{"sectionNumber":"Gulfstream (Rockwell) 114 Series Aeropla","sectionType":"division","heading":"Gulfstream (Rockwell) 114 Series Aeroplanes","content":"### Gulfstream (Rockwell) 114 Series Aeroplanes\n\n| AD/ROCK-114/14 Amdt 1 | Rudder Spar | 12/2008 |\n| --------------------- | ----------- | ------- |\n\n| Applicability: | Applicability: Model 114 aircraft with serial numbers 14000 to 14499, inclusive |\n| -------------- | -------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------- |\n| Requirement: | 1. Visually inspect the rudder spar near the upper hinge fitting for signs of cracking. Check for excessive movement by attempting to move the rudder tip fore and aft and left to right.2. (a) Remove 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 angle doublers P/N 44006-RE3, if installed, for cracks in the area of the upper hinge fitting attachment. Inspect using the dye penetrant method in accordance with Rockwell Service Letter SL-114-17 and CAO 108.10. Cracks, including stop drilled cracks, which extend beyond installed angle doublers, P/N 44006-RE3, must be repaired by replacement of the rudder spar before further flight.(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.Previous compliance with cancelled AD/ROCK-114/10 does not necessarily constitute compliance with this AD. 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. |\n| Compliance: | 1. Inspect in accordance with Requirement 1 within 10 hours time in service after 25 May 1995.2. Initially inspect in accordance with Requirement 2(a) before 100 hours time in service after 25 May 1995. Re-inspect at intervals not to exceed 200 hours time in service until modified in accordance with Requirement 2(b). |\n| | This Amendment becomes effective on 20 November 2008. |\n\n| Background: | This Directive requires repeat inspections of the hinge fitting area until the rudder spar is modified.This amendment includes a statement to the effect that previous compliance with cancelled AD/ROCK-114/10 does not constitute compliance with this AD, even though the requirement document, Rockwell International Service Letter (SL) No. SL-114-17 is the same for both Airworthiness Directives. A previous report of cracking of the rudder spar, in the region of the upper hinge fitting, had been received indicating substantial cracking found on one aircraft approximately 1500 hours TIS after compliance with now cancelled AD/ROCK-114/10. |\n| ----------- | --------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------- |\n\n![](image.001.png) \nDavid Villiers \nDelegate of the Civil Aviation Safety Authority\n\n7 October 2008","sortOrder":0},{"sectionNumber":"AD/ROCK-114/14 Amdt 1","sectionType":"part","heading":"AD/ROCK-114/14 Amdt 1","content":"## AD/ROCK-114/14 Amdt 1","sortOrder":1},{"sectionNumber":"Rudder Spar","sectionType":"part","heading":"Rudder Spar","content":"## Rudder Spar","sortOrder":2},{"sectionNumber":"12/2008","sectionType":"part","heading":"12/2008","content":"## 12/2008","sortOrder":3}],"analysis":{"flash_summary":{"complexity_score":6,"scope_assessment":{"changed":true,"description":"The amendment clarifies scope by stating that previous compliance with the cancelled AD/ROCK‑114/10 does not necessarily satisfy this AD, even though both reference the same Service Letter. It therefore increases verification burden on operators (they must demonstrate the spar was crack‑free when angle doublers were fitted) and mandates repeat inspections until the specified modification is completed (Background; Requirement 2(b); Compliance)."},"complexity_factors":["Technical inspection methods: dye‑penetrant inspections and assessment of stop‑drilled cracks (Requirement 2(a); Service Letter SL‑114‑17; CAO 108.10).","Removal and disassembly work: requires removing the rudder assembly and upper hinge fitting for some inspections (Requirement 2(a); Maintenance Manual, Section VII).","Structural modification or replacement: must either repair by replacing the rudder spar if cracks found, or install angle doublers P/N 44006‑RE3 (Requirement 2(a)–2(b)).","Timing and recurrent checks: short mandatory deadlines (inspect within 10 hours TIS; initial detailed inspection before 100 hours TIS; re‑inspect every 200 hours until modified) (Compliance).","Burden of proof on operators: angle doublers already installed are to be treated as indicating a crack unless positive evidence shows the spar was crack‑free when installed (Requirement 2(b)).","Operational impact: potential aircraft downtime and parts/labour costs if spar replacement or modification is required (Requirement 2(a)–2(b); Compliance).","Regulatory linkage and document dependence: compliance requires following an external Service Letter (SL‑114‑17) and CAO standard, adding procedural dependency (Requirement 2(a); Service Letter reference).","Enforcement and administration: issued by the CASA delegate with effective dates and retrospection on prior AD compliance (Background; signature block)."],"plain_english_summary":"This Airworthiness Directive applies to Gulfstream (Rockwell) 114 aircraft, serials 14000–14499. It requires operators to inspect the rudder spar near the upper hinge for cracks, perform dye‑penetrant inspections, remove and replace the spar if cracked, and install angle doublers per Rockwell SL‑114‑17. Inspections must be done promptly and repeated at set intervals until the modification is fitted. The amendment also states that compliance with the earlier cancelled AD does not automatically meet this AD’s requirements."},"flash_summary_failed":{"failed":true,"reason":"Unauthenticated. Configure AI_GATEWAY_API_KEY or use a provider module. Learn more: https://ai-sdk.dev/unauthenticated-ai-gateway","source":"analysis-cron"},"kimi_summary":{"content_quality":"ok","complexity_score":4,"scope_assessment":{"changed":true,"description":"The original AD/ROCK-114/10 apparently required less stringent measures. This amendment expands scope significantly by: (1) explicitly cancelling and superseding the predecessor directive rather than merely updating it; (2) adding a presumption that any aircraft with angle doublers already installed is cracked unless proven otherwise; (3) imposing recurring inspection obligations (every 200 hours) where the previous regime may have been one-off; and (4) responding to new evidence of failure (the crack found at 1,500 hours TIS) that revealed the original safety margin was inadequate. The directive has evolved from a single-point inspection to a sustained airworthiness monitoring regime."},"complexity_factors":["Multiple compliance deadlines with cascading conditions (10 hours, 100 hours, then recurring 200-hour intervals)","Cross-reference to external technical documents (Rockwell Service Letter SL-114-17, CAO 108.10, Maintenance Manual Section VII) without reproducing their content","Conditional logic: modification only permitted if spar confirmed crack-free; angle doublers presumed evidence of cracking unless proven otherwise","Retroactive negation clause explicitly voiding compliance with predecessor directive AD/ROCK-114/10","Specific part numbers (P/N 44006-RE3) and serial number ranges requiring precise technical matching","Dual inspection methods (visual vs. dye penetrant) with different thresholds for action"],"plain_english_summary":"This mandatory CASA Airworthiness Directive affects Gulfstream (Rockwell) 114 series aircraft (S/N 14000–14499) and requires owners/operators to inspect and repair the rudder spar after cracks were found near the upper hinge. It mandates immediate visual checks, a dye-penetrant removal inspection, recurring checks until a permanent reinforcement is fitted, and installation of angle doublers only if the spar is crack-free.\n\nIt overrides prior AD compliance and is required to prevent in‑flight rudder failure."}},"importantCases":[],"_links":{"self":"/api/acts/ad-rock-114-14-amdt-1-rudder-spar","history":"/api/acts/ad-rock-114-14-amdt-1-rudder-spar/history","analysis":"/api/acts/ad-rock-114-14-amdt-1-rudder-spar/analysis","conflicts":"/api/acts/ad-rock-114-14-amdt-1-rudder-spar/conflicts","importantCases":"/api/acts/ad-rock-114-14-amdt-1-rudder-spar/important-cases","documents":"/api/acts/ad-rock-114-14-amdt-1-rudder-spar/documents"}}