{"id":"F2008L01639","name":"AD/ROBIN/32 Amdt 2 - Wing Spars","slug":"ad-robin-32-amdt-2-wing-spars","collection":"legislative_instrument","jurisdiction":"commonwealth","status":"in_force","isInForce":true,"actNumber":null,"makingDate":null,"administeringDepartment":null,"currentVersion":{"id":73727,"registerId":"commonwealth-F2008L01639-current","compilationNumber":null,"startDate":"2026-04-02","status":"InForce","reasons":null,"registeredAt":null},"sections":[{"sectionNumber":"Robin Aviation Series Aeroplanes","sectionType":"division","heading":"Robin Aviation Series Aeroplanes","content":"### Robin Aviation Series Aeroplanes\n\n| AD/ROBIN/32 Amdt 2 | Wing Spars | 6/2008 |\n| ------------------ | ---------- | ------ |\n\n| Applicability: | All Model HR 100 series aircraft.Model HR200/100, HR200/100S, HR200/120, HR200/120B, and HR200/160 aircraft, serial numbers 001 through 378.Model R2100, R2100A, R2112, R2120U, and R2160D aircraft, serial numbers 001 through 378.Model R2160 aircraft, serial numbers 001 through 378, and serial number160A-06001 and subsequent.Model R2160i aircraft, serial numbers 001 through 378, and serial numbers160Ai-07007 and subsequent.                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                |\n| -------------- | -------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------- |\n| Requirement:   | Remove the main landing gear legs and all the wing inspection panels in accordance with the instructions in the aircraft maintenance manual, and inspect the visible parts of the spar web and the upper and lower boom angles (top and bottom spar caps), in accordance with Avions Pierre Robin Service Letter (SL) No. 19 and Service Bulletin (SB) No. 99.If corrosion is found on the rear face of the spar web or the upper and lower boom angles, then inspect the front face of the spar for corrosion in accordance with SL No. 19 and SB No. 99. It may be necessary to cut inspection holes or remove the wings to inspect the front face of the spar. Inspection holes must be prepared to an approved repair scheme.Treat corrosion in accordance with SL No. 19 and SB No. 99, before further flight.If corrosion is found which exceeds the limits specified in SL No. 19, before further flight, repair in accordance with an approved repair scheme.If the spars are replaced, the inspections at intervals of 24 months must be resumed within 60 months from the date of replacement. |\n\n|             | The requirements of this Directive are not applicable to aircraft that have been inspected within the last 72 months or are less than 72 months old, provided that these aircraft are maintained and continued to be maintained to an approved Alpha Aviation Design Ltd maintenance programme.Note: NZ CAA AD DCA/R2000/37B and EASA AD 2005-0028, refer.                                                                                                                                                                                                                                                                                                                                                                                        |\n| ----------- | ------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------- |\n| Compliance: | Within 60 months after aircraft date of manufacture and within 6 months for aircraft which are older than 60 months, unless accomplished within the last 24 months, and thereafter at intervals not to exceed 24 months.                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                          |\n|             | This Amendment becomes effective on 5 June 2008.                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                  |\n| Background: | Several occurrences have shown that the Robin series of aircraft are highly susceptible to corrosion of wing spar web and boom angles.Corrosion of the wing spars may not be detected by normal maintenance practices on these aircraft due to access for inspection being difficult. Corrosion may therefore develop unchecked, leading to an unsafe condition and ultimately a catastrophic failure of the wing.Amendment 1 was issued in response to a new EASA AD, which was issued because the existing state of design AD did not address all affected types of a similar design.Amendment 2 is issued to align this Directive with NZ CAA AD DCA/R2000/24A for all models except the Model HR 100, which is aligned with EASA AD2005-0028. |\n\n![](image.001.png)  \nDavid Villiers  \nDelegate of the Civil Aviation Safety Authority\n\n16 April 2008","sortOrder":0},{"sectionNumber":"AD/ROBIN/32 Amdt 2","sectionType":"part","heading":"AD/ROBIN/32 Amdt 2","content":"## AD/ROBIN/32 Amdt 2","sortOrder":1},{"sectionNumber":"Wing Spars","sectionType":"part","heading":"Wing Spars","content":"## Wing Spars","sortOrder":2},{"sectionNumber":"6/2008","sectionType":"part","heading":"6/2008","content":"## 6/2008","sortOrder":3}],"analysis":{"kimi_summary":{"content_quality":"ok","complexity_score":4,"scope_assessment":{"changed":true,"description":"The original directive appears to have covered fewer aircraft models. Amendment 1 expanded coverage to address additional aircraft types of 'similar design' following a new EASA AD. Amendment 2 further expanded alignment with New Zealand CAA directives for most models, while maintaining separate EASA alignment for the HR 100 series. The directive has grown from addressing a specific corrosion issue in a limited fleet to harmonising with multiple international aviation safety regulators (EASA and NZ CAA) across an expanded range of serial numbers and model variants."},"complexity_factors":["Multiple overlapping applicability categories with serial number ranges and exceptions (5 distinct model groups with varying serial number cutoffs)","Conditional inspection logic: initial inspection triggers, followed by conditional secondary inspections if corrosion found on rear face","Cross-references to external documents (Avions Pierre Robin Service Letter No. 19, Service Bulletin No. 99, NZ CAA AD DCA/R2000/37B, EASA AD 2005-0028)","Nested compliance timeline: 60 months from manufacture OR 6 months for older aircraft OR 24 months if recently done, then 24-month recurring intervals","Exception to the exception: 72-month exemption only applies if maintained to specific Alpha Aviation Design Ltd programme","Procedural conditionality: repair schemes must be 'approved', inspection holes must meet 'approved repair scheme'"],"plain_english_summary":"This mandatory CASA Airworthiness Directive requires owners/operators of specified Robin Aviation models to inspect wing spars for corrosion, remove gear/inspection panels (and if needed cut access or remove wings), and treat or repair any corrosion before flight. Inspections are first within set age limits and repeat every 24 months. It targets hidden spar corrosion that can cause catastrophic wing failure."},"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"},"flash_summary":{"complexity_score":6,"scope_assessment":{"changed":true,"description":"Amendment 2 alters the directive's scope to align with overseas directives: it aligns with NZ CAA AD DCA/R2000/24A for most models while the HR100 is aligned with EASA AD 2005‑0028. The Background notes prior Amendment 1 was issued because the earlier AD did not address all affected types, so Amendment 2 updates applicability and compliance alignment with foreign ADs (Background)."},"complexity_factors":["Detailed model- and serial-number applicability across multiple series (Applicability table).","Prescriptive physical work required: removal of main landing gear and all wing inspection panels (Requirement).","Conditional escalation: if corrosion found, inspect opposite spar face, potentially cutting inspection holes or removing wings (Requirement).","Repairs and inspection-hole preparation must follow an approved repair scheme, creating regulatory oversight and approval steps (Requirement).","Multiple external normative references: Avions Pierre Robin SL No.19 and SB No.99, Alpha Aviation maintenance programme, NZ CAA AD and EASA AD (Requirement/Notes/Background).","Layered compliance timings (initial 60 months or 6 months for older aircraft, exemption if inspected within last 72 months, then recurring 24‑monthly intervals) increasing scheduling complexity (Compliance/Requirement).","Operational disruption and cost risk from invasive inspections or wing removal (implied by Requirement: may be necessary to cut holes or remove wings).","Alignment edits across previous amendments and foreign ADs requiring administrators/operators to track evolving scope and equivalence (Background)."],"plain_english_summary":"This airworthiness directive requires owners/operators of specified Robin HR100/HR200 and R21/R2160 series aeroplanes (listed by model and serial number) to remove main landing gear and inspection panels and inspect wing spar webs and upper/lower boom angles for corrosion, following Avions Pierre Robin Service Letter No.19 and Service Bulletin No.99. Any corrosion must be treated or repaired under an approved repair scheme before further flight; inspections are initially required within specified months after manufacture and then every 24 months."}},"importantCases":[],"_links":{"self":"/api/acts/ad-robin-32-amdt-2-wing-spars","history":"/api/acts/ad-robin-32-amdt-2-wing-spars/history","analysis":"/api/acts/ad-robin-32-amdt-2-wing-spars/analysis","conflicts":"/api/acts/ad-robin-32-amdt-2-wing-spars/conflicts","importantCases":"/api/acts/ad-robin-32-amdt-2-wing-spars/important-cases","documents":"/api/acts/ad-robin-32-amdt-2-wing-spars/documents"}}