{"id":"F2006B10214","name":"AD/GAF-N22/65 Amdt 3 - Rear Fuselage Frame","slug":"ad-gaf-n22-65-amdt-3-rear-fuselage-frame","collection":"legislative_instrument","jurisdiction":"commonwealth","status":"in_force","isInForce":true,"actNumber":null,"makingDate":null,"administeringDepartment":null,"currentVersion":{"id":55872,"registerId":"commonwealth-F2006B10214-current","compilationNumber":null,"startDate":"2026-04-02","status":"InForce","reasons":null,"registeredAt":null},"sections":[{"sectionNumber":"1","sectionType":"section","heading":"AD/GAF-N22/65 Amdt 3 - Rear Fuselage Frame","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)  \n![](image.002.png)  \nGAF N22 and N24 Series Aeroplanes\n\nAIRWORTHINESS DIRECTIVE\n\n![](image.002.png)\n\n![](image.002.png)  \nFor the reasons set out in the background section, the CASA delegate whose signature appears below revokes Airworthiness Directive (AD) AD/GAF-N22/65 Amdt 2 and issues the following AD under subregulation 39.1 (1) of CAR 1998. The AD requires that the action set out in the requirement section (being action that the delegate considers necessary to correct the unsafe condition) be taken in relation to the aircraft or aeronautical product mentioned in the applicability section: (a) in the circumstances mentioned in the requirement section; and (b) in accordance with the instructions set out in the requirement section; and (c) at the time mentioned in the compliance section.\n\nAD/GAF-N22/65\n\nAmdt 3\n\n  \nRear Fuselage Frame 6/2000\n\nApplicability: All model N22 and N24 aircraft which have NOT been modified in accordance with ASTA Modification N806.\n\nRequirement: 1. Inspect the forward face of the rear fuselage frame for cracks in accordance with ASTA Nomad Alert Service Bulletin ANMD-53-15 Revision 3, Section 2.A, (Part 1 - Inspection).\n\n2. Modify the aircraft by installing ASTA Modification N806 in accordance with ASTA Nomad Alert Service Bulletin ANMD-53-15 Revision 3, Section 2.C, (Part 3 - Mod N806 Incorporation).\n\nNote: ANMD-53-15 Revision 3 describes the same inspection as that required by previous amendments to this AD.\n\nCompliance: For Requirement Para 1: As detailed in the Requirement Document Para 1.D.(2).\n\nFor Requirement Para 2: As detailed in the Requirement Document Para 1.D.(4). Aircraft which have already exceeded the applicable compliance time must be modified within 12 months time in service after 15 June 2000.\n\nThis Amendment becomes effective on 15 June 2000.\n\nBackground: The initial issue of this directive was issued following receipt of a number of reports of aircraft with cracks around the rivet heads on the rear bulkhead frame. Frame failure may lead to loss of structural integrity and possible subsequent loss of aircraft control. This amendment adopts the inspection procedures and compliance times specified by the manufacturer, and requires installation of the preventive modification which is terminating action for the inspections.\n\nAmendment 2 of this Airworthiness Directive became effective on 30 September 1993.\n\nCOMMONWEALTH OF AUSTRALIA (Civil Aviation Regulations 1998), PART 39 \\- 105 CIVIL AVIATION SAFETY AUTHORITY\n\nSCHEDULE OF AIRWORTHINESS DIRECTIVES\n\n![](image.003.png)  \nAmendment 1 of this Airworthiness Directive became effective on 25 May 1993. The original issue of this Airworthiness Directive became effective on 25 May 1993.\n\nBernard Malcolm Hole\n\nDelegate of the Civil Aviation Safety Authority 5 May 2000\n\n![](image.002.png)  \n\nThe above AD is notified in the Commonwealth of Australia Gazette on 17 May 2000.","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":true,"description":"Yes. Earlier iterations required inspections; this Amendment 3 adopts the manufacturer's inspection procedures and adds a mandatory preventive modification (ASTA Modification N806) as terminating action for the inspections. That shifts the AD from recurring inspection-only obligations toward a required one-off modification (still limited to affected N22/N24 aircraft not already modified), increasing the AD's scope from inspection enforcement to compulsory modification."},"complexity_factors":["2 substantive mandatory actions (inspection per service bulletin; installation of Modification N806)","Applicability limited to aircraft NOT modified per ASTA Modification N806 (single conditional applicability)","Cross-reference to an external document: ASTA Nomad Alert Service Bulletin ANMD-53-15 Revision 3 (Section 2.A and 2.C) for procedural details","Compliance times are specified in the referenced Requirement Document (Para 1.D.(2) and Para 1.D.(4)) rather than spelled out in full in the AD","A retroactive compliance clause for aircraft already past the applicable time (must be modified within 12 months after 15 June 2000)","Terminology and effect inherited from previous amendments (AD has a short amendment history but the inspection described is unchanged)","Relatively short text with limited cross-references within the instrument itself"],"plain_english_summary":"**What this instrument changes (mechanics)\n\n- Applicability: The directive applies to all GAF Nomad model N22 and N24 aeroplanes that have NOT already been modified under ASTA Modification N806 (\"Applicability\").\n\n- Two mandatory actions for affected aircraft (\"Requirement\"):\n  - Inspect the forward face of the rear fuselage frame for cracks, following ASTA Nomad Alert Service Bulletin ANMD-53-15 Revision 3, Section 2.A (Part 1 - Inspection) (\"Requirement Para 1\").\n  - Modify the aircraft by installing ASTA Modification N806, following ANMD-53-15 Revision 3, Section 2.C (Part 3 - Mod N806 Incorporation) (\"Requirement Para 2\").\n\n- Timing rules (\"Compliance\"): The exact inspection and modification times are set out in the referenced service bulletin (specifically Requirement Document Para 1.D.(2) for inspection and Para 1.D.(4) for modification). Aircraft already past those compliance times on 15 June 2000 must be modified within 12 months of that date.\n\n- Termination: Installing Modification N806 is the terminating action for the repetitive inspections required by this AD (stated in the Background).\n\n- Legal force: The Civil Aviation Safety Authority (CASA) delegate issued the AD under the Civil Aviation Regulations; compliance is mandatory for affected aircraft.\n\nWhy the AD was issued (official rationale and effect)\n\n- The AD follows reports of cracks around rivet heads on the rear bulkhead frame. The stated safety concern is that frame failure could compromise structural integrity and possibly lead to loss of aircraft control (\"Background\").\n\n- This amendment adopts the manufacturer’s inspection procedures and compliance times (ANMD-53-15 Rev 3) and requires the preventive modification (N806) which removes the need for continuing inspections once installed.\n\nWho this affects and who pays\n\n- Aircraft owners/operators of N22 and N24 aeroplanes that have not had Modification N806 installed are directly affected.\n\n- Those owners/operators (or their maintenance providers) must perform the inspections and pay for, schedule and install Modification N806. Costs include labour, parts, aircraft downtime and any associated certification/maintenance paperwork.\n\nPractical effects, incentives and trade-offs\n\n- Behaviour change: Operators must inspect until they install Mod N806. Because Mod N806 is a stated terminating action, there is a clear incentive to install it to avoid recurring inspections.\n\n- Concentrated vs diffuse effects: The safety benefit (reduced risk of frame failure) accrues to aircraft occupants and operators (concentrated), while the compliance cost (inspection and modification expense, downtime) is paid by the individual owners/operators (concentrated cost as well). There is no broad change to other markets or aircraft types.\n\n- Compliance burden and implementation risk: The AD cross-references an external service bulletin (ANMD-53-15 Rev 3). Operators need access to that document and suitable maintenance facilities and parts to carry out the modification. Availability of parts, qualified technicians, or workshop time can create practical delays or additional costs. The AD includes a fixed remedial deadline for aircraft already overdue (12 months after 15 June 2000).\n\n- Regulatory clarity: The AD is short and prescriptive (inspect per the service bulletin, then install Mod N806). However it delegates detailed technical steps and timing to the manufacturer’s service bulletin; that external dependence can create interpretive or logistical issues if the bulletin is unclear or parts are scarce.\n\nNet procedural effect\n\n- Mechanically, the AD replaces ongoing inspection-only requirements with a two-step rule: inspect (per the manufacturer) and then install a mandated modification that stops the inspection requirement. The CASA delegate enforces the requirement under civil aviation regulation. (See Applicability; Requirement Para 1 and Para 2; Compliance Para 1.D.(2) and Para 1.D.(4); Background.)"},"kimi_summary":{"content_quality":"ok","complexity_score":3,"scope_assessment":{"changed":false,"description":"The legislation maintains its original scope as a targeted airworthiness directive for specific GAF aircraft models. While this is Amendment 3, it remains focused on the same safety issue (rear fuselage frame cracks) and the same aircraft types as the original 1993 directive. The amendment updates technical references and compliance times but does not expand beyond the original safety purpose."},"complexity_factors":["Multiple cross-references to external technical documents (ASTA Nomad Alert Service Bulletin ANMD-53-15 Revision 3, specific sections)","Conditional applicability (excludes aircraft already modified per ASTA Modification N806)","Dual compliance pathways (ongoing inspections vs one-time terminating modification)","Nested compliance timing (references to paragraphs within the external requirement document rather than stating dates directly)","Amendment history tracking (references to previous amendments and their effective dates)"],"plain_english_summary":"This CASA safety order for GAF N22/N24 Nomad aircraft replaces the prior amendment and requires owners/operators to address cracking found in the rear fuselage bulkhead: either follow the manufacturer’s inspection schedule or install ASTA Modification N806 as a permanent repair. It affects all affected Nomads to prevent possible structural failure and loss of the aircraft. The order took effect 15 June 2000; a 12‑month installation allowance applies if prior deadlines lapsed."}},"importantCases":[],"_links":{"self":"/api/acts/ad-gaf-n22-65-amdt-3-rear-fuselage-frame","history":"/api/acts/ad-gaf-n22-65-amdt-3-rear-fuselage-frame/history","analysis":"/api/acts/ad-gaf-n22-65-amdt-3-rear-fuselage-frame/analysis","conflicts":"/api/acts/ad-gaf-n22-65-amdt-3-rear-fuselage-frame/conflicts","importantCases":"/api/acts/ad-gaf-n22-65-amdt-3-rear-fuselage-frame/important-cases","documents":"/api/acts/ad-gaf-n22-65-amdt-3-rear-fuselage-frame/documents"}}