{"id":"F2006B02060","name":"AD/AA-5/27 Amdt 1 - Wing Attach Shoulder Bolts","slug":"ad-aa-5-27-amdt-1-wing-attach-shoulder-bolts","collection":"legislative_instrument","jurisdiction":"commonwealth","status":"in_force","isInForce":true,"actNumber":null,"makingDate":null,"administeringDepartment":null,"currentVersion":{"id":41282,"registerId":"commonwealth-F2006B02060-current","compilationNumber":null,"startDate":"2026-04-01","status":"InForce","reasons":null,"registeredAt":null},"sections":[{"sectionNumber":"1","sectionType":"section","heading":"AD/AA-5/27 Amdt 1 - Wing Attach Shoulder Bolts","content":"COMMONWEALTH OF AUSTRALIA (Civil Aviation Regulations 1998), PART 39 \\- 105 CIVIL AVIATION SAFETY AUTHORITY\n\nSCHEDULE OF AIRWORTHINESS DIRECTIVES\n\n![](image.001.png)  \nGulfstream (Grumman American/ American Aviation) AA-5 Series Aeroplanes\n\nAD/AA-5/27\n\nAmdt 1\n\n  \nWing Attach Shoulder Bolts 10/95 DM\n\nApplicability: AA-5, AA-5A, AA-5B, and AG-5B aircraft.\n\nRequirement: 1. Remove the subject bolts or other approved replacement bolts, in accordance with American General Aviation SB-185.\n\n    2. Inspect the bolts for cracking at the bolt shoulder using either the Magnaflux or Fluorescent Dye NDI technique and discard any bolts with indications of cracking.\n\n    3. Install bolts in accordance with the requirements of American General Aviation SB-185.\n\nCompliance: Unless already accomplished, prior to attaining 1000 hours bolt time in service, or within 10 hours’ time in service after 23 August 1995, whichever occurs last; thereafter at intervals not exceeding 500 hours’ time in service.\n\nBackground: A MDR was received stating that a bolt had been found cracked when inspected using magnaflux, instead of visually, in accordance with the Requirement document. The defect was highlighted in the AAC Major Defect Summary. However, subsequent laboratory examination of the bolt has revealed that the fatigue cracking could be attributable to the rapid change in section at the shoulder and the sharp edge revealed at X230 magnification.\n\nFailure of a shoulder bolt may compromise the structural integrity of an aircraft and could result in a loss of flight control.\n\nAmendment 1 is raised as the result of a random inspection of a second aircraft where one of the bolts was found to be fully fractured.","sortOrder":0}],"analysis":{"flash_summary_failed":{"failed":true,"reason":"A positive credit balance is required for all requests, including BYOK, so fallback providers remain available. Add credits at https://vercel.com/d?to=%2F%5Bteam%5D%2F%7E%2Fai%3Fmodal%3Dtop-up to continue.","source":"analysis-cron"},"flash_summary":{"complexity_score":3,"scope_assessment":{"changed":false,"description":"The amendment does not alter the aircraft applicability or the core requirements (remove, inspect, discard cracked bolts, reinstall per SB-185 and recurring 500‑hour inspections). Amendment 1 is recorded as issued because a random inspection found a fully fractured bolt (Background), but the directive's scope and mandated actions remain the same in the source text."},"complexity_factors":["Technical NDI requirement: specifies Magnaflux or Fluorescent Dye inspection techniques (Requirement 2) — requires trained/qualified inspection capability.","Manufacturer procedural dependence: mandates compliance with American General Aviation SB-185 for removal/installation (Requirement 1,3) — requires access to and adherence to the service bulletin.","Time-tracking burden: compliance tied to 'bolt time in service' with an initial deadline and recurring 500‑hour intervals (Compliance) — requires component-level logging.","Operational disruption and cost: removal and reinstallation of wing-attach bolts involve maintenance downtime and replacement parts (Requirements 1,3).","Evidence/interpretation risk: Background notes laboratory findings and differing detection by magnaflux versus visual inspection — potential for differing inspection outcomes and discard rates.","Limited administrative discretion: the AD prescribes methods, intervals and discard action (Requirements/Compliance), leaving little room for alternative approaches without approved replacements."],"plain_english_summary":"This airworthiness directive requires owners/operators of Gulfstream (Grumman American/American Aviation) AA-5, AA-5A, AA-5B and AG-5B aeroplanes to remove, non-destructively inspect (Magnaflux or fluorescent dye) and replace wing-attach shoulder bolts in line with American General Aviation SB-185, then repeat inspections at 500‑hour intervals. Compliance deadlines are measured by bolt time in service. It matters because a cracked or fractured shoulder bolt can undermine structural integrity and flight control."},"kimi_summary":{"content_quality":"ok","complexity_score":3,"scope_assessment":{"changed":false,"description":"This amendment maintains the original scope of the directive. Amendment 1 was triggered by new safety evidence (a second aircraft with a fractured bolt) but does not expand the applicability to new aircraft models or introduce new categories of requirements. It reinforces the existing inspection regime rather than broadening it."},"complexity_factors":["Short, single-purpose directive with clear applicability and requirement sections","Only 4 aircraft models affected, listed explicitly","Straightforward three-step compliance requirement (remove, inspect, install)","Single cross-reference to external technical document (American General Aviation SB-185)","Simple compliance timeline with 'whichever occurs last' conditional logic","No defined terms section — common aviation terminology used without legal definitions","Background narrative explains rationale but doesn't create additional legal obligations","No nested exceptions or conditional sub-clauses within requirements"],"plain_english_summary":"Owners and operators of Gulfstream (AA-5, AA-5A, AA-5B, AG-5B) light aircraft must remove, non‑destructively inspect (Magnaflux or dye penetrant), discard cracked wing \"shoulder\" bolts and reinstall per the service bulletin. Inspections recur every 500 flight hours. CASA issued this mandatory AD because fatigue cracks in these bolts can lead to catastrophic wing failure; the rule was tightened after a second complete bolt fracture showed earlier checks were insufficient."}},"importantCases":[],"_links":{"self":"/api/acts/ad-aa-5-27-amdt-1-wing-attach-shoulder-bolts","history":"/api/acts/ad-aa-5-27-amdt-1-wing-attach-shoulder-bolts/history","analysis":"/api/acts/ad-aa-5-27-amdt-1-wing-attach-shoulder-bolts/analysis","conflicts":"/api/acts/ad-aa-5-27-amdt-1-wing-attach-shoulder-bolts/conflicts","importantCases":"/api/acts/ad-aa-5-27-amdt-1-wing-attach-shoulder-bolts/important-cases","documents":"/api/acts/ad-aa-5-27-amdt-1-wing-attach-shoulder-bolts/documents"}}