{"id":"F2017L00556","name":"AD/A320/65 Amdt 3 - Fuselage Reinforcement Section 18","slug":"ad-a320-65-amdt-3-fuselage-reinforcement-section-18","collection":"legislative_instrument","jurisdiction":"commonwealth","status":"in_force","isInForce":true,"actNumber":null,"makingDate":null,"administeringDepartment":null,"currentVersion":{"id":96331,"registerId":"commonwealth-F2017L00556-current","compilationNumber":null,"startDate":"2026-04-02","status":"InForce","reasons":null,"registeredAt":null},"sections":[{"sectionNumber":"Airbus A319, A320 and A321 Series Aeropl","sectionType":"part","heading":"Airbus A319, A320 and A321 Series Aeroplanes","content":"# Airbus A319, A320 and A321 Series Aeroplanes\n\n| AD/A320/65 Amdt 3 | Fuselage Reinforcement Section 18 | 10/2017 |\n| ----------------- | --------------------------------- | ------- |\n\n| Applicability: | All Airbus A320 models without Airbus modification 22764 embodied, or Airbus Service Bulletins (SBs) A320-53-1110 and A320-53-1131 as in force from time to time incorporated.                                                                                                                                                                                                                                            |\n| -------------- | ------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------- |\n| Requirement:   | Reinforce the fuselage at section 18 in accordance with the instructions of:Airbus SB A320-53-1110 as in force from time to time for frames 68 and 69; and,Airbus SB A320-53-1131 as in force from time to time for frames 65, 66, and 67.Note 1: This AD is based on DGAC AD 97-315-109(B).Note 2: The words “as in force from time to time” require compliance with the most recent version of the referenced document. |\n| Compliance:    | Before 13 January 2002.Note 3: Previous compliance with any requirement in AD/A320/65 Amdt 2 constitutes compliance with the same requirement in this AD.                                                                                                                                                                                                                                                                 |\n|                | This AD commences on 26 May 2017.                                                                                                                                                                                                                                                                                                                                                                                         |\n| Background:    | This directive was issued to increase the marginal strength of the rear fuselage to enable it to cope with an undetected tail scrape.Amendment 1 reflected the amended compliance of the related DGAC AD.Amendment 2 was issued in response to a new DGAC AD which introduced additional frames for reinforcement.Amendment 3 is issued to clarify the AD applicability.                                                  |\n\n![](image.001.jpeg)\n\nPieter van Dijk  \nDelegate of the Civil Aviation Safety Authority\n\n17 May 2017","sortOrder":0},{"sectionNumber":"AD/A320/65 Amdt 3","sectionType":"part","heading":"AD/A320/65 Amdt 3","content":"## AD/A320/65 Amdt 3","sortOrder":1},{"sectionNumber":"Fuselage Reinforcement Section 18","sectionType":"part","heading":"Fuselage Reinforcement Section 18","content":"## Fuselage Reinforcement Section 18","sortOrder":2},{"sectionNumber":"10/2017","sectionType":"part","heading":"10/2017","content":"## 10/2017","sortOrder":3}],"analysis":{"flash_summary":{"complexity_score":4,"scope_assessment":{"changed":true,"description":"The AD's original safety objective (increase rear fuselage marginal strength against tail scrape) remains, but scope was expanded and then clarified: Amendment 2 introduced additional frames for reinforcement (Background) which broadened the set of affected structure, and Amendment 3 clarified which aeroplanes are within applicability (Background; Applicability). Previous compliance with AD/A320/65 Amdt 2 is treated as compliance with this AD (Compliance Note 3)."},"complexity_factors":["Conditional applicability depending on absence of Airbus mod 22764 or incorporation of two specific SBs (Applicability).","Mandated compliance with the latest version of referenced service bulletins — 'as in force from time to time' — requiring ongoing reference updates (Requirement; Note 2).","Multiple frame locations requiring different SBs (frames 65–69 covered across two SBs) increasing coordination for maintenance (Requirement).","Temporal inconsistency: specific compliance-by date (before 13 January 2002) vs AD commencement date (26 May 2017) creates potential record-tracing complexity (Compliance).","Amendment history: prior amendments added frames and Amendment 3 clarifies applicability; operators must track amendment effects and prior compliance credits (Background; Compliance Note 3).","Technical implementation imposes physical work, parts and downtime costs on operators and must be performed to SB instructions (Requirement)."],"plain_english_summary":"**What it does:** Requires reinforcement of the fuselage at section 18 on Airbus A319/A320/A321 aeroplanes that have not had Airbus modification 22764 or the specified service bulletins applied. Affected parties are aircraft owners/operators and maintenance organisations; the work must follow the most recent Airbus service bulletin versions.  \n\n**Why it matters:** The reinforcement is intended to raise rear‑fuselage strength to cope with an undetected tail scrape. Operators pay for and schedule the work; the Civil Aviation Safety Authority (Delegate) enforces the airworthiness directive and its compliance deadlines."},"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":false,"description":"This amendment remains tightly scoped to its original purpose. Amendment 3 explicitly states it is issued only 'to clarify the AD applicability' — it does not expand the technical requirements, add new aircraft models, or extend the reinforcement work beyond the original frames (65-69). The original intent was to address rear fuselage strength following tail scrape incidents, and this version maintains that narrow safety focus."},"complexity_factors":["Multiple cross-references to external technical documents (Airbus Service Bulletins) that are 'living documents' (as in force from time to time)","Nested applicability conditions: applies to all models EXCEPT those with specific modification OR those that have already incorporated specific service bulletins","Amendment history creates layered compliance logic (Amendment 3 references compliance with Amendment 2)","Technical aviation terminology requires domain knowledge (frames, section 18, fuselage, tail scrape, DGAC AD references)","Dual effective dates: compliance deadline (2002) versus directive commencement date (2017)"],"plain_english_summary":"This AD requires reinforcement of the rear fuselage on certain Airbus A319/A320/A321 aircraft that haven’t received factory mod 22764 or the specified Airbus service bulletins, using the latest versions of those bulletins. It was to be completed before 13 January 2002 and prevents progressive weakening from an undetected tail scrape.\n\nAmendment 3 only clarifies which aircraft are affected; it does not introduce new work."}},"importantCases":[],"_links":{"self":"/api/acts/ad-a320-65-amdt-3-fuselage-reinforcement-section-18","history":"/api/acts/ad-a320-65-amdt-3-fuselage-reinforcement-section-18/history","analysis":"/api/acts/ad-a320-65-amdt-3-fuselage-reinforcement-section-18/analysis","conflicts":"/api/acts/ad-a320-65-amdt-3-fuselage-reinforcement-section-18/conflicts","importantCases":"/api/acts/ad-a320-65-amdt-3-fuselage-reinforcement-section-18/important-cases","documents":"/api/acts/ad-a320-65-amdt-3-fuselage-reinforcement-section-18/documents"}}