{"id":"F2008L01638","name":"AD/ROBIN/28 Amdt 2 - Wing Attachment Bolts","slug":"ad-robin-28-amdt-2-wing-attachment-bolts","collection":"legislative_instrument","jurisdiction":"commonwealth","status":"in_force","isInForce":true,"actNumber":null,"makingDate":null,"administeringDepartment":null,"currentVersion":{"id":73726,"registerId":"commonwealth-F2008L01638-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/28 Amdt 2 | Wing Attachment Bolts | 6/2008 |\n| ------------------ | --------------------- | ------ |\n\n| Applicability: | Model HR 200/100, HR 200/100S, HR 200/120, HR 200/120B, and HR 200/160 aircraft, serial numbers 001 through 378.Model R 2100, R 2100 A, R 2112, R 2120 U, and R 2160 D aircraft, serial numbers 001 through 378.Model R 2160 aircraft, serial numbers 001 through 378, and serial number160A-06001 and subsequent.Model R 2160i aircraft, serial numbers 001 through 378, and serial numbers160Ai-07007 and subsequent.                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                 |\n| -------------- | --------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------- |\n| Requirement:   | 1. For Model HR 200 aircraft, check the torque of the front, main, and rear wing attachment bolts, in accordance with Avions Pierre Robin Service Bulletin (SB) No. 145 Revision 2.If the torque values are not as specified in SB No. 145 Revision 2, before further flight, contact the aircraft manufacturer for corrective action.If the torque values are correct, the previous flight limitation +3.8g and -1.52g in the “N” category is cancelled.2. For Model R 2000 aircraft, serial numbers 001 through 298, replace the main spar attachment bolts in accordance with SB No. 145 Revision 2 and NAV 96-3.3. For all Model R 2000 aircraft, check the torque values of the wing attachments in accordance with SB No. 145 Revision 2.If the torque values are not as specified in SB No. 145 Revision 2, before further flight, contact the aircraft manufacturer for corrective action.Note: NZ CAA AD DCA/R2000/24A refers. |\n| Compliance:    | 1. Unless the initial check is already accomplished, within 100 hours time in service after 5 June 2008. Thereafter at intervals not to exceed 1,000 hours time in service.                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                             |\n\n|             | 2. Unless already accomplished, before further flight after 5 June 2008.3. Unless the initial check is already accomplished, within 50 hours time in service after 5 June 2008. Thereafter at intervals not to exceed 100 hours time in service.                                                                                                                                                                                                                                                                                                                                                                                                                                                            |\n| ----------- | ----------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------- |\n|             | This Amendment becomes effective on 5 June 2008.                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                            |\n| Background: | The initial issue of this directive followed a report by the French airworthiness authority, the DGAC, of the in-flight failure of the wing attachments of a Robin R2160 aircraft. The flight restrictions of Requirement 2 were imposed while the DGAC investigated the incident.Amendment 1 provided for removal of the flight restriction once the wing attachment hardware is replaced. The torque check and inspection requirements subsequent to replacement are to ensure the continuing airworthiness of the wing attachment hardware.Amendment 2 is issued to align this Directive with NZ CAA AD DCA/R2000/24A. Alpha Aviation manufactured Model R 2160i aircraft are included in applicability. |\n\n![](image.001.png)  \nDavid Villiers  \nDelegate of the Civil Aviation Safety Authority\n\n16 April 2008","sortOrder":0},{"sectionNumber":"AD/ROBIN/28 Amdt 2","sectionType":"part","heading":"AD/ROBIN/28 Amdt 2","content":"## AD/ROBIN/28 Amdt 2","sortOrder":1},{"sectionNumber":"Wing Attachment Bolts","sectionType":"part","heading":"Wing Attachment Bolts","content":"## Wing Attachment Bolts","sortOrder":2},{"sectionNumber":"6/2008","sectionType":"part","heading":"6/2008","content":"## 6/2008","sortOrder":3}],"analysis":{"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":5,"scope_assessment":{"changed":true,"description":"Amendment 2 expands the AD’s applicability to include Alpha Aviation–manufactured Model R2160i aircraft and aligns the directive with NZ CAA AD DCA/R2000/24A. It also formalises torque-check and replacement requirements (and their compliance intervals) and provides for cancellation of a prior g-load flight restriction once torque is verified (Background; Applicability; Requirement)."},"complexity_factors":["Multiple models and detailed serial-number ranges in applicability, requiring operators to verify exact serial inclusion (Applicability).","Different mandatory actions by model: HR 200s require torque checks and potential cancellation of a g-load restriction; certain R 2000s require bolt replacement plus torque checks (Requirement).","Varied compliance timing and recurring intervals: initial checks within 50–100 hours and recurring intervals of 100–1,000 hours depending on model and action (Compliance).","Dependence on external technical documents (Avions Pierre Robin SB No.145 Revision 2; NAV 96-3) for specification of torque values and replacement procedures (Requirement).","Conditional grounding and manufacturer involvement: if torque values are outside SB limits, operators must contact the manufacturer before further flight, creating procedural and potential downtime implications (Requirement).","Cross-jurisdictional alignment: Amendment 2 explicitly aligns this AD with NZ CAA AD DCA/R2000/24A and adds Alpha Aviation R2160i aircraft to applicability, expanding scope (Background).","Operational effect: verification of correct torque mechanically removes a prior +3.8g/-1.52g ‘N’ category limit for HR 200s, so maintenance actions directly change permitted flight envelope (Requirement).","Enforcement and interpretation require reading both the AD and the referenced SBs; ambiguity could arise if SBs or NAV documents are updated separately (Requirement/Background)."],"plain_english_summary":"This airworthiness directive requires owners/operators of specified Robin HR 200 and R 2000/R 2160-series aeroplanes (particular serial ranges, including Alpha-manufactured R2160i) to inspect and torque-check wing attachment bolts and, for some R2000 aircraft, replace main spar attachment bolts using Avions Pierre Robin Service Bulletin No.145 Rev 2 (and NAV 96-3). Operators pay for inspections/repairs, must ground aircraft until corrective action if torque is outside SB limits, and may have a previous g-load flight restriction cancelled once torque is verified."},"kimi_summary":{"content_quality":"ok","complexity_score":4,"scope_assessment":{"changed":true,"description":"The original directive (initial issue) was emergency-focused, imposing flight restrictions after a reported wing attachment failure. Amendment 1 allowed removal of flight restrictions upon hardware replacement. Amendment 2 expands applicability to include Alpha Aviation manufactured Model R 2160i aircraft and aligns the directive with New Zealand aviation safety requirements, broadening scope beyond the original French incident response."},"complexity_factors":["Multiple aircraft models and serial number ranges with different requirements (HR 200 vs R 2000 series)","Three distinct compliance actions with different deadlines (100 hours, 50 hours, and 'before further flight')","Cross-reference to external technical documents (Service Bulletin No. 145 Revision 2, NAV 96-3, and NZ CAA AD DCA/R2000/24A)","Conditional logic: different actions depending on whether torque values are correct or incorrect","Amendment history referenced (Amendment 1 and 2) explaining evolution of requirements","Removal of previous flight restrictions contingent on compliance"],"plain_english_summary":"Owners and operators of specified Robin HR 200 and R 2000 series aeroplanes must inspect—and for some R 2000s, replace—wing attachment bolts per the manufacturer’s service bulletin. Required torque checks and bolt replacements are mandated within short flight-hour windows and may lift prior flight G‑limits if passed; incorrect torque or missing bolts requires contacting the manufacturer before further flight. The AD responds to a reported in‑flight wing attachment failure and addresses a potential wing separation hazard."}},"importantCases":[],"_links":{"self":"/api/acts/ad-robin-28-amdt-2-wing-attachment-bolts","history":"/api/acts/ad-robin-28-amdt-2-wing-attachment-bolts/history","analysis":"/api/acts/ad-robin-28-amdt-2-wing-attachment-bolts/analysis","conflicts":"/api/acts/ad-robin-28-amdt-2-wing-attachment-bolts/conflicts","importantCases":"/api/acts/ad-robin-28-amdt-2-wing-attachment-bolts/important-cases","documents":"/api/acts/ad-robin-28-amdt-2-wing-attachment-bolts/documents"}}