{"id":"F2006B06147","name":"AD/PC-6/43 - Aileron Attachment Bracket","slug":"ad-pc-6-43-aileron-attachment-bracket","collection":"legislative_instrument","jurisdiction":"commonwealth","status":"in_force","isInForce":true,"actNumber":null,"makingDate":null,"administeringDepartment":null,"currentVersion":{"id":46944,"registerId":"commonwealth-F2006B06147-current","compilationNumber":null,"startDate":"2026-04-02","status":"InForce","reasons":null,"registeredAt":null},"sections":[{"sectionNumber":"1","sectionType":"section","heading":"AD/PC-6/43 - Aileron Attachment Bracket","content":"---\nmeta-content-style-type: text/css\nmeta-content-type: application/xhtml+xml; charset=utf-8\nmeta-generator: Aspose.Words for .NET 22.10.0\n---\n\n?xml version=\"1.0\" encoding=\"utf-8\" standalone=\"no\"?>\n\nCOMMONWEALTH OF AUSTRALIA (Civil Aviation Regulations 1998), PART 39 - 105 CIVIL AVIATION SAFETY AUTHORITY\n\nSCHEDULE OF AIRWORTHINESS DIRECTIVES\n\n \n\n![](image.001.png)  Pilatus Porter PC-6 Series Aeroplanes\n\n \n\nAD/PC-6/43 Aileron Attachment Bracket 4/97\n\nApplicability: Pilatus PC-6 Porter / Turbo Porter up to Serial No. 815\n\n \n\nRequirement: Modify aileron/ flap mountings in accordance with Pilatus Service Bulletin (SB) No.\n\n138, Rev. 2.\n\n \n\nNote: Swiss FOA AD HB 84-023 refers.\n\n \n\nCompliance: Unless already accomplished, within 100 hours time in service from 27 March 1997.\n\n \n\nThis Airworthiness Directive becomes effective on 27 March 1997.\n\n \n\nBackground: Cracks have been found in the angle brackets forming the attachment of the aileron flap mountings. The cracks have been attributed to fatigue caused by the aircraft being subjected to overspeeding and harsh manoeuvring of the aircraft at high speed.\n\n \n\n \n\n \n\n \n\n \n\n \n\n \n\n \n\n \n\n \n\n \n\n \n\n \n\n \n\n \n\n \n\n \n\n \n\n \n\n \n\n \n\n \n\n \n\n \n\n \n\n \n\n \n\n \n\n \n\n \n\n \n","sortOrder":0}],"analysis":{"kimi_summary":{"content_quality":"ok","complexity_score":2,"scope_assessment":{"changed":false,"description":"This is a discrete, targeted safety directive addressing a specific structural defect in a specific aircraft model. It has not expanded beyond its original purpose of mandating a safety modification."},"complexity_factors":["Single, specific aircraft type and serial number range","One clear compliance action (modify per specific service bulletin)","Simple time-based compliance condition (100 hours time in service)","No defined terms section","No cross-references to other legislation beyond a single note referencing the Swiss authority directive","Straightforward background explanation without technical engineering specifications"],"plain_english_summary":"**What this is:** This is an Airworthiness Directive (AD) — essentially a mandatory safety order issued by Australia's Civil Aviation Safety Authority (CASA) for specific aircraft.\n\n**What it does:** It requires owners and operators of Pilatus PC-6 Porter and Turbo Porter aeroplanes (serial numbers up to 815) to modify the aileron and flap mountings following a specific manufacturer's service bulletin (SB 138, Revision 2).\n\n**Why it matters:** Cracks have been discovered in the angle brackets that attach the ailerons (the hinged surfaces on the wings that control roll) and flaps (the surfaces that extend to increase lift at low speeds) to the aircraft structure. These cracks are caused by metal fatigue from flying too fast and making harsh manoeuvres at high speed. If left unaddressed, these cracks could lead to structural failure and loss of control of the aircraft.\n\n**Who must comply:** Anyone operating affected Pilatus PC-6 aircraft must complete this modification within 100 hours of flight time after 27 March 1997, unless already done.\n\n**Key details:**\n- **Effective date:** 27 March 1997\n- **Compliance deadline:** Within 100 hours 'time in service' from the effective date\n- **Reference:** Follows Swiss aviation authority directive FOA AD HB 84-023"},"flash_summary":{"complexity_score":2,"scope_assessment":{"changed":false,"description":"The directive sets a targeted mandatory modification for specified PC-6 serial numbers; the source document contains no indication that the scope was expanded or narrowed from an earlier intent or instrument."},"complexity_factors":["Narrow applicability: single aircraft type and serial range (Applicability).","Single, prescriptive corrective action by reference to Pilatus Service Bulletin No. 138 Rev. 2 (Requirement).","Short, explicit compliance window: within 100 hours time in service from 27 March 1997 (Compliance).","Technical work requires maintenance resources and access to the manufacturer service bulletin (Requirement).","No discretionary exemptions, alternatives, or phased implementation described in the text.","Cross-reference to foreign directive noted (Swiss FOA AD HB 84-023) but no further harmonisation detail provided (Note)."],"plain_english_summary":"This Airworthiness Directive requires owners/operators of Pilatus PC-6 Porter/Turbo Porter aeroplanes (serial numbers up to 815) to modify the aileron/flap attachment brackets in line with Pilatus Service Bulletin No. 138 Rev. 2. The work must be done within 100 hours time in service from 27 March 1997. The directive responds to discovered fatigue cracks in the angle brackets attributed to overspeeding and harsh high‑speed manoeuvring."}},"importantCases":[],"_links":{"self":"/api/acts/ad-pc-6-43-aileron-attachment-bracket","history":"/api/acts/ad-pc-6-43-aileron-attachment-bracket/history","analysis":"/api/acts/ad-pc-6-43-aileron-attachment-bracket/analysis","conflicts":"/api/acts/ad-pc-6-43-aileron-attachment-bracket/conflicts","importantCases":"/api/acts/ad-pc-6-43-aileron-attachment-bracket/important-cases","documents":"/api/acts/ad-pc-6-43-aileron-attachment-bracket/documents"}}