{"id":"F2006B02033","name":"AD/AA-1/20 - Wing Attach Shoulder Bolts","slug":"ad-aa-1-20-wing-attach-shoulder-bolts","collection":"legislative_instrument","jurisdiction":"commonwealth","status":"in_force","isInForce":true,"actNumber":null,"makingDate":null,"administeringDepartment":null,"currentVersion":{"id":41255,"registerId":"commonwealth-F2006B02033-current","compilationNumber":null,"startDate":"2026-04-01","status":"InForce","reasons":null,"registeredAt":null},"sections":[{"sectionNumber":"1","sectionType":"section","heading":"AD/AA-1/20 - 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-1 Series Aeroplanes\n\nAD/AA-1/20 Wing Attach Shoulder Bolts 11/95 DM\n\nApplicability: All models AA-1.\n\nRequirement: 1. Remove the subject bolts, or other approved replacement bolts in accordance with American General Aviation AA-5 (repeat, AA-5) 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. Until further notice, install bolts in accordance with the requirements of American General Aviation AA-5 SB-185.\n\nCompliance: Unless already accomplished, prior to attaining 1000 hours bolt time in service, or within 10 hours time in service after the effective date, whichever occurs last; thereafter at intervals not exceeding 500 hours’ time in service.\n\nThe effective date of this Directive is 06 September 1995.\n\nBackground: The intent of this Directive was initially aimed at AA-5 Series aircraft. However, a report has been received of an AA-1 found with both attach bolts in both wings cracked, when randomly inspected as a result of the AD/AA-5/27 Amdt 1.\n\nThe AA-5 AD was raised as the result of a MDR received stating that a bolt had been found cracked when inspected using Magnaflux, instead of visually, in accordance with the SB 185. The defect was highlighted in the AAC Major Defect Summary.\n\nHowever, subsequent laboratory examination of the bolt 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\nUntil further notice, the bolt inspection and reinstallation will be carried out in accordance with the AA-5 instructions.","sortOrder":0}],"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"},"kimi_summary":{"content_quality":"ok","complexity_score":3,"scope_assessment":{"changed":true,"description":"The directive explicitly states it was 'initially aimed at AA-5 Series aircraft' but was expanded to cover AA-1 series after a report of cracked bolts in an AA-1. The scope grew from the original AA-5 AD to include AA-1 aircraft, effectively creating a parallel safety requirement for a different but related aircraft model based on shared component design."},"complexity_factors":["Single, specific mechanical defect addressed with clear procedural steps","Only 3 defined compliance actions (remove, inspect, reinstall)","Straightforward compliance timeline with simple 'whichever occurs last' condition","References external technical document (SB-185) but does not reproduce its contents","No nested exceptions or conditional logic beyond the initial applicability and compliance timing","Limited to single aircraft series (AA-1) with universal applicability within that series"],"plain_english_summary":"This CASA Airworthiness Directive mandates owners/operators of Gulfstream AA-1 aircraft inspect and replace the wing \"shoulder\" attachment bolts because fatigue cracks have been found where the bolt diameter changes, risking bolt failure and loss of a wing or control. Inspections must use magnetic-particle or fluorescent dye methods (not visual only), with initial and recurring intervals tied to flight hours.\n\nCompliance is mandatory and follows procedures in Service Bulletin SB-185 for removal, inspection, disposal, and reinstallation."},"flash_summary":{"complexity_score":3,"scope_assessment":{"changed":true,"description":"The directive was originally aimed at AA‑5 series aircraft but was applied to AA‑1 after a report of cracked wing attach bolts on an AA‑1. The Background explains the scope expansion from AA‑5 to include all AA‑1 models."},"complexity_factors":["Cross-reference to external manufacturer service bulletin (American General Aviation AA‑5 SB‑185) for removal/installation instructions increases reliance on another document (Requirement).","Technical inspection methods mandated (Magnaflux or Fluorescent Dye NDI) require specialist equipment and skills (Requirement).","Timing rules combine an initial compliance trigger (1,000 hours bolt time or 10 hours after effective date, whichever is later) with ongoing 500‑hour intervals, creating scheduling and recordkeeping needs (Compliance).","Mandate to discard any bolts with indications of cracking creates direct replacement cost and logistics for owners/operators (Requirement).","Applicability to all AA‑1 models broadens operational impact compared with the original AA‑5 focus (Applicability, Background)."],"plain_english_summary":"Requires owners/operators of Gulfstream (Grumman American/American Aviation) AA‑1 aeroplanes to remove and inspect wing‑attach shoulder bolts using Magnaflux or fluorescent‑dye non‑destructive inspection, discard any bolts showing cracking, and reinstall bolts per American General Aviation AA‑5 Service Bulletin 185 (Requirement). Inspections must occur before 1,000 hours bolt time (or within 10 hours after the effective date) and then every 500 hours (Compliance). The AD responds to reports of fatigue cracking that could compromise flight control (Background)."}},"importantCases":[],"_links":{"self":"/api/acts/ad-aa-1-20-wing-attach-shoulder-bolts","history":"/api/acts/ad-aa-1-20-wing-attach-shoulder-bolts/history","analysis":"/api/acts/ad-aa-1-20-wing-attach-shoulder-bolts/analysis","conflicts":"/api/acts/ad-aa-1-20-wing-attach-shoulder-bolts/conflicts","importantCases":"/api/acts/ad-aa-1-20-wing-attach-shoulder-bolts/important-cases","documents":"/api/acts/ad-aa-1-20-wing-attach-shoulder-bolts/documents"}}