{"id":"F2007L01346","name":"AD/B737/277 Amdt 1 - Splice Fitting between Windows 1 and 2","slug":"ad-b737-277-amdt-1-splice-fitting-between-windows-1-and-2","collection":"legislative_instrument","jurisdiction":"commonwealth","status":"in_force","isInForce":true,"actNumber":null,"makingDate":null,"administeringDepartment":null,"currentVersion":{"id":65580,"registerId":"commonwealth-F2007L01346-current","compilationNumber":null,"startDate":"2026-04-02","status":"InForce","reasons":null,"registeredAt":null},"sections":[{"sectionNumber":"Boeing 737 Series Aeroplanes","sectionType":"division","heading":"Boeing 737 Series Aeroplanes","content":"### Boeing 737 Series Aeroplanes\n\n| AD/B737/277 Amdt 1 | Splice Fitting between Windows 1 and 2 | 6/2007 |\n| ------------------ | -------------------------------------- | ------ |\n\n| Applicability: | Model 737-600, -700, -700C, and -800 series aircraft, as identified in Boeing Alert Service Bulletin 737-53A1222 Revision 3, or later FAA approved revision.                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                               |\n| -------------- | ------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------ |\n| Requirement:   | Action in accordance with the technical requirements of FAA AD 2007-06-09 Amdt 39-14990.                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                   |\n| Compliance:    | As specified in the Requirement document, with a revised effective date of7 June 2007.                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                     |\n|                | This Amendment becomes effective on 7 June 2007.                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                           |\n| Background:    | The FAA received a report indicating that during the Model 737-800 series aircraft full-scale fuselage fatigue test, the splice fitting failed prior to the design service objective. Additionally, the FAA received a report of a cracked splice fitting on an aircraft with less than 13,500 total flight cycles. This condition, if not corrected, could result in cracking of the existing fitting that may cause cracking through the skin and consequent depressurisation of the fuselage.Amendment 1 is issued in response to a new FAA AD, which adds repetitive inspections for cracking of the skin just below each splice fitting, and related corrective actions if necessary. |\n\n![](image.001.png)  \nDavid Villiers  \nDelegate of the Civil Aviation Safety Authority\n\n24 April 2007","sortOrder":0},{"sectionNumber":"AD/B737/277 Amdt 1","sectionType":"part","heading":"AD/B737/277 Amdt 1","content":"## AD/B737/277 Amdt 1","sortOrder":1},{"sectionNumber":"Splice Fitting between Windows 1 and 2","sectionType":"part","heading":"Splice Fitting between Windows 1 and 2","content":"## Splice Fitting between Windows 1 and 2","sortOrder":2},{"sectionNumber":"6/2007","sectionType":"part","heading":"6/2007","content":"## 6/2007","sortOrder":3}],"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"},"kimi_summary":{"content_quality":"ok","complexity_score":3,"scope_assessment":{"changed":true,"description":"The original AD (presumably AD/B737/277) appears to have required one-time corrective action on the splice fittings. Amendment 1 expands the scope significantly by adding 'repetitive inspections' — meaning ongoing, periodic checks rather than a single fix — and 'related corrective actions if necessary.' This transforms the directive from a finite compliance task into a continuing airworthiness obligation."},"complexity_factors":["Very short document (approximately 250 words of substantive content)","Only 1 defined term implicitly referenced (the FAA AD number)","Single cross-reference to external technical document (FAA AD 2007-06-09) — actual detailed requirements are 'incorporated by reference' rather than spelled out in the text","No nested conditional logic or exceptions within the document itself","Simple two-part structure: applicability statement + compliance requirement","Technical complexity is offloaded to the referenced Boeing Service Bulletin and FAA AD"],"plain_english_summary":"This CASA Airworthiness Directive mandates repeated inspections and any necessary repairs of a fuselage splice fitting (between the first and second windows) on certain Boeing 737-600/700/700C/800 aircraft, requiring compliance with FAA AD 2007-06-09 and Boeing Alert Service Bulletin 737-53A1222 Rev 3.  \n\nIt responds to early fatigue failure and an in-service cracked fitting that could lead to skin cracks and cabin depressurisation; Amendment 1 adds ongoing inspection requirements."},"flash_summary":{"complexity_score":3,"scope_assessment":{"changed":true,"description":"Amendment 1 expands the prior directive by adding repetitive inspections for skin cracking just below each splice fitting between windows 1 and 2 and related corrective actions. The change broadens the measure from addressing specific failure reports to imposing an ongoing inspection regime (see Background and Requirement)."},"complexity_factors":["Cross-reference to an external FAA AD (2007-06-09) — requires users to consult another instrument for technical detail","Reliance on Boeing Alert Service Bulletin 737-53A1222 Rev 3 to identify affected airframes","Technical nature of required repetitive inspections and potential corrective repairs","Operational impacts: scheduling inspections, potential grounding and repair time","Amendment mechanism (revised effective date and added inspection requirements) increasing procedural steps for compliance"],"plain_english_summary":"This amendment requires operators of certain Boeing 737-600/-700/-700C/-800 aircraft (as listed in Boeing Alert Service Bulletin 737-53A1222 Rev 3) to follow FAA AD 2007-06-09 procedures, effective 7 June 2007. It adds repetitive inspections for cracking of the fuselage skin beneath the splice fitting between windows 1 and 2 and any necessary repairs. Aircraft operators bear the cost and downtime; the regulator (CASA) enforces compliance by mandating FAA-prescribed inspections and corrective actions."}},"importantCases":[],"_links":{"self":"/api/acts/ad-b737-277-amdt-1-splice-fitting-between-windows-1-and-2","history":"/api/acts/ad-b737-277-amdt-1-splice-fitting-between-windows-1-and-2/history","analysis":"/api/acts/ad-b737-277-amdt-1-splice-fitting-between-windows-1-and-2/analysis","conflicts":"/api/acts/ad-b737-277-amdt-1-splice-fitting-between-windows-1-and-2/conflicts","importantCases":"/api/acts/ad-b737-277-amdt-1-splice-fitting-between-windows-1-and-2/important-cases","documents":"/api/acts/ad-b737-277-amdt-1-splice-fitting-between-windows-1-and-2/documents"}}