{"id":"F2008L02959","name":"AD/DO 328/35 Amdt 1 - Rudder Spring Tab Lever Assembly","slug":"ad-do-328-35-amdt-1-rudder-spring-tab-lever-assembly","collection":"legislative_instrument","jurisdiction":"commonwealth","status":"in_force","isInForce":true,"actNumber":null,"makingDate":null,"administeringDepartment":null,"currentVersion":{"id":74923,"registerId":"commonwealth-F2008L02959-current","compilationNumber":null,"startDate":"2026-04-02","status":"InForce","reasons":null,"registeredAt":null},"sections":[{"sectionNumber":"Dornier 328 Series Aeroplanes","sectionType":"division","heading":"Dornier 328 Series Aeroplanes","content":"### Dornier 328 Series Aeroplanes\n\n| AD/DO 328/35 Amdt 1 | Rudder Spring Tab Lever Assembly | 9/2008 |\n| ------------------- | -------------------------------- | ------ |\n\n| Applicability: | Model 328-100 aircraft, all serial numbers, with part number 001A272A4020-002 rudder spring tab lever assembly installed.                                                                                                                                                                                                                                                                                                                                                                   |\n| -------------- | ------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------- |\n| Requirement:   | Action in accordance with the requirements of EASA AD 2008-0107.Note: AvCraft Aerospace GmbH ASB-328-27-036 dated 12 February 2003 andASB-328-27-036 Revision 1 dated 7 May 2004, and 328 Support Services GmbH ASB-328-27-036 Revision 2 dated 24 January 2008, or later EASA approved revisions, refer; and, AvCraft Aerospace GmbH SB-328-27-459 dated 3 May 2004 and 328 Support Services GmbH SB-328-27-459 Revision 1 dated 24 January 2008, or later EASA approved revisions, refer. |\n| Compliance:    | As specified in the Requirement document, with Compliance (1) effective date to be read as the date specified in the original issue of this Directive (19 January 2006).                                                                                                                                                                                                                                                                                                                    |\n|                | This Amendment becomes effective on 28 August 2008.                                                                                                                                                                                                                                                                                                                                                                                                                                         |\n| Background:    | The manufacturer has determined that the possibility of failure exists in the rudder flight control system due to cracks in the spring tab lever assembly bearing lugs.Amendment 1 is issued in response to a new EASA AD, which expands applicability, reduces the inspection interval to 400 flight hours, and requires replacement of the rudder spring tab lever assembly with an improved unit as mandatory terminating action to the inspection requirement.                          |\n\n![](image.001.png)  \nDavid Villiers  \nDelegate of the Civil Aviation Safety Authority\n\n14 July 2008","sortOrder":0},{"sectionNumber":"AD/DO 328/35 Amdt 1","sectionType":"part","heading":"AD/DO 328/35 Amdt 1","content":"## AD/DO 328/35 Amdt 1","sortOrder":1},{"sectionNumber":"Rudder Spring Tab Lever Assembly","sectionType":"part","heading":"Rudder Spring Tab Lever Assembly","content":"## Rudder Spring Tab Lever Assembly","sortOrder":2},{"sectionNumber":"9/2008","sectionType":"part","heading":"9/2008","content":"## 9/2008","sortOrder":3}],"analysis":{"kimi_summary":{"content_quality":"ok","complexity_score":3,"scope_assessment":{"changed":true,"description":"The original 2006 directive has expanded in scope through this Amendment 1. The Background explicitly states three expansions: (1) broader aircraft applicability ('expands applicability'), (2) more stringent ongoing obligations (inspection interval reduced from previous standard to 400 flight hours), and (3) conversion from open-ended inspection regime to mandatory replacement as terminating action. This represents a significant tightening of safety requirements beyond the original directive's intent."},"complexity_factors":["Short, single-purpose instrument (approximately 250 words of substantive content)","Only one defined applicability criterion (specific aircraft model and part number)","Heavy reliance on external documents — the actual technical requirements are contained in referenced EASA AD 2008-0107 and manufacturer service bulletins (ASB-328-27-036 and SB-328-27-459), which are not reproduced in the text","Simple conditional structure: if aircraft has part X, then do Y","No nested exceptions or complex legislative cross-references — references are purely to technical aviation documents","Clear compliance date structure with only one interpretive note about effective date reading"],"plain_english_summary":"This CASA Airworthiness Directive requires owners/operators of Dornier 328-100s with rudder spring tab lever assembly 001A272A4020-002 to inspect it every 400 flight hours and to replace it with a redesigned unit. Cracks in the bearing lugs can lead to rudder control failure, so the amendment tightens applicability, shortens inspection intervals and mandates permanent replacement (ending repetitive inspections). The amendment takes effect 28 August 2008."},"flash_summary":{"complexity_score":5,"scope_assessment":{"changed":true,"description":"Yes. The Amendment expands applicability and tightens requirements compared with the original directive by widening the affected population (all serial numbers with the specified P/N), reducing the inspection interval to 400 flight hours, and mandating replacement with an improved unit as the terminating action (Background; Applicability; Requirement). Compliance timing was also adjusted/clarified by treating Compliance (1) as effective from 19 January 2006 while the Amendment itself becomes effective 28 August 2008 (Compliance)."},"complexity_factors":["Cross-reference to external mandated document (EASA AD 2008-0107) and multiple service documents (ASBs/SBs) requiring cross‑checking for full compliance (Requirement; Note).","Technical specificity: applicability limited to a single part number (001A272A4020-002) but across all serial numbers, implying fleet‑wide checks (Applicability).","Regulatory change elements: reduced inspection interval (to 400 flight hours) plus a mandatory terminating modification, creating staged compliance steps (Background).","Multiple dates and retrodating: Compliance (1) is to be read as 19 January 2006 while the Amendment is effective 28 August 2008, raising recordkeeping and retrospective compliance questions (Compliance).","Operational burden: inspections and replacement require maintenance capability, parts availability and scheduling across operators, implicating cost and downtime (Requirement; Background).","Enforcement and interpretation risk: reliance on later EASA‑approved revisions of referenced ASBs/SBs introduces discretion about which revision applies (Requirement Note)."],"plain_english_summary":"This airworthiness directive requires operators of Dornier 328‑100 aircraft that have rudder spring tab lever assembly P/N 001A272A4020-002 fitted to follow the actions set out in EASA AD 2008‑0107: inspect the part more often and replace it with an improved unit. It shortens the inspection interval to 400 flight hours and makes replacement the mandatory terminating action; compliance dates are specified so earlier compliance from 19 January 2006 is recognised and this Amendment is effective 28 August 2008."},"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"}},"importantCases":[],"_links":{"self":"/api/acts/ad-do-328-35-amdt-1-rudder-spring-tab-lever-assembly","history":"/api/acts/ad-do-328-35-amdt-1-rudder-spring-tab-lever-assembly/history","analysis":"/api/acts/ad-do-328-35-amdt-1-rudder-spring-tab-lever-assembly/analysis","conflicts":"/api/acts/ad-do-328-35-amdt-1-rudder-spring-tab-lever-assembly/conflicts","importantCases":"/api/acts/ad-do-328-35-amdt-1-rudder-spring-tab-lever-assembly/important-cases","documents":"/api/acts/ad-do-328-35-amdt-1-rudder-spring-tab-lever-assembly/documents"}}