{"id":"F2005L01302","name":"AD/JETSTREAM/96 Amdt 1 - Landing Gear Rod Spherical Bearing","slug":"ad-jetstream-96-amdt-1-landing-gear-rod-spherical-bearing","collection":"legislative_instrument","jurisdiction":"commonwealth","status":"in_force","isInForce":true,"actNumber":null,"makingDate":null,"administeringDepartment":null,"currentVersion":{"id":35037,"registerId":"commonwealth-F2005L01302-current","compilationNumber":null,"startDate":"2026-04-01","status":"InForce","reasons":null,"registeredAt":null},"sections":[{"sectionNumber":"British Aerospace BAe 3100 (Jetstream) S","sectionType":"division","heading":"British Aerospace BAe 3100 (Jetstream) Series Aeroplanes","content":"### British Aerospace BAe 3100 (Jetstream) Series Aeroplanes\n\n| AD/JETSTREAM/96 Amdt 1 | Landing Gear Rod Spherical Bearing | 7/2005 |\n| ---------------------- | ---------------------------------- | ------ |\n\n| Applicability: | British Aerospace Aircraft Models HP 137 Jetstream Mk 1, Jetstream Series 200, 3100 and 3200.                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                             |\n| -------------- | --------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------- |\n| Requirement:   | 1. Install the redesigned radius rod retention washer as per provisions of BAE Systems Service Bulletin (SB) 32-JM5413 Original Issue, or later EASA approved revision.2. For aircraft not modified per SB 32-JM5413 Original Issue, or later EASA approved revision, per Requirement 1 of this Directive: Inspect the main landing gear (MLG) radius rod spherical bearing for evidence of migration from the radius rod cylinder in accordance with SB 32-JA030340 Revision 1, or later EASA approved revision.3. For aircraft modified per SB 32-JM5413 Original Issue, or later EASA approved revision, per Requirement 1 of this Directive: Carry out a visual inspection of the radius rod cylinder and the retention washer for evidence of spherical bearing migration towards contact, or contact damage with the retention washer.4. Replace the radius rod and / or retention washer, if bearing migration or retention washer damage is observed on inspection per Requirement 3 of this AD.Note: UK CAA Airworthiness Directive G-2005-0012 dated 20 April 2005 approved by EASA under approval number 2005-3462 dated 15 April 2005 refers. |\n| Compliance:    | 1. Within 2000 flight hours or one year after the effective date of this AD, whichever occurs later.2. Within 50 flight cycles since the last inspection in accordance with the original issue of this AD and then repetitively, at intervals not to exceed 50 flight cycles.3. Prior to the accumulation of 5,000 flight cycles since installation of the redesigned radius rod retention washer in accordance with Requirement 1 of this AD and then repetitively, at intervals not to exceed 5000 flight cycles.4. Before further flight.                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                              |\n\n|             | This Amendment becomes effective on 7 July 2005.                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                        |\n| ----------- | ----------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------- |\n| Background: | A potential unsafe condition has been identified from an incidence of migration of the MLG radius rod housing from the spherical bearing attachment at the wing root, which could lead to detachment and sudden collapse of the MLG leg. This has been classified as a Hazardous condition.The cause of this migration has been established as incorrect swaging of the bearing sleeve, which cannot be detected with the radius rod actuator installed on the aircraft.Original issue of this AD required frequent repetitive inspection of the effected area to detect migration within the radius rod cylinder spherical joint. Current amendment maintains the inspection requirements and mandates the installation of a modified retention washer to prevent detachment of the MLG radius rod should migration from the spherical bearing occur.The original issue of this AD became effective on 13 August 2003. |\n\n![](image.001.png)  \nJames Coyne  \nDelegate of the Civil Aviation Safety Authority\n\n19 May 2005","sortOrder":0},{"sectionNumber":"AD/JETSTREAM/96 Amdt 1","sectionType":"part","heading":"AD/JETSTREAM/96 Amdt 1","content":"## AD/JETSTREAM/96 Amdt 1","sortOrder":1},{"sectionNumber":"Landing Gear Rod Spherical Bearing","sectionType":"part","heading":"Landing Gear Rod Spherical Bearing","content":"## Landing Gear Rod Spherical Bearing","sortOrder":2},{"sectionNumber":"7/2005","sectionType":"part","heading":"7/2005","content":"## 7/2005","sortOrder":3}],"analysis":{"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 maintains the original safety purpose of preventing landing gear collapse. It adds a mandatory physical modification (the redesigned retention washer) while preserving the inspection regime from the original directive. The scope remains tightly focused on the specific spherical bearing defect in the main landing gear radius rod assembly."},"complexity_factors":["Multiple conditional requirements based on modification status (modified vs unmodified aircraft)","Four distinct compliance deadlines with different measurement units (flight hours, years, flight cycles)","Cross-references to external technical documents (BAE Systems Service Bulletins SB 32-JM5413 and SB 32-JA030340)","Nested logic: Requirement 3 only applies if Requirement 1 is completed; Requirement 2 only applies if Requirement 1 is NOT completed","Repetitive inspection intervals (50 cycles and 5,000 cycles) creating ongoing obligations"],"plain_english_summary":"This is an **Airworthiness Directive (AD)** — a mandatory safety order issued by Australia's Civil Aviation Safety Authority (CASA) for specific British Aerospace Jetstream aircraft.\n\n**What it does:**\nThis directive addresses a serious safety flaw in the main landing gear (the wheels that support the aircraft during takeoff and landing). A part called the \"radius rod spherical bearing\" can slip out of position due to a manufacturing defect. If this happens, the landing gear leg could suddenly collapse — a \"hazardous condition\" in aviation terms.\n\n**Who it affects:**\nOwners and operators of British Aerospace Jetstream aircraft models: HP 137 Mk 1, Series 200, 3100, and 3200.\n\n**What must be done:**\n1. **Install a redesigned washer** (a modified retention device) to prevent the bearing from slipping out — this must be done within 2,000 flight hours or one year.\n2. **For unmodified aircraft:** Inspect the landing gear every 50 flight cycles (takeoff-landing pairs) to check if the bearing is moving out of place.\n3. **For modified aircraft:** Visually inspect every 5,000 flight cycles to ensure the new washer isn't being damaged by bearing movement.\n4. **If damage is found:** Replace the damaged parts before flying again.\n\n**Why it matters:**\nLanding gear collapse during landing or takeoff could cause a serious accident. This directive prevents that by requiring both a physical fix (the new washer) and ongoing inspections to catch problems early."},"flash_summary":{"complexity_score":4,"scope_assessment":{"changed":true,"description":"The amendment expands the original AD’s scope. The original AD (effective 13 Aug 2003) required frequent inspections to detect bearing migration. This amendment retains those inspection requirements but adds a mandatory engineered modification: installation of a redesigned radius-rod retention washer (Requirement 1). It also formalises different inspection intervals depending on whether the modification has been installed (50 flight cycles for unmodified, 5,000 flight cycles for modified), and makes replacement mandatory when migration or washer damage is observed (Requirements 2–4; Compliance 2–3). In short, the AD moved from inspection-only mitigation toward a combination of retrofit modification plus inspections, changing both required actions and the inspection cadence."},"complexity_factors":["Four substantive mandatory actions (Requirements 1–4)","Multiple distinct compliance timing rules (Compliance 1–4) with different units (flight hours, flight cycles, calendar time, before further flight)","Cross-references to multiple manufacturer service bulletins (SB 32-JM5413 and SB 32-JA030340) and to later EASA-approved revisions","Conditional logic based on whether the aircraft is modified per the SB (different inspection regimes for modified vs unmodified aircraft)","Reference to an external UK CAA AD and EASA approval numbers (regulatory cross-recognition)","Replacement action triggered by inspection findings (condition -> mandatory corrective action)"],"plain_english_summary":"**What this instrument does (mechanically)**\n\n- Applies to British Aerospace Jetstream aeroplanes: HP 137 Jetstream Mk 1, Jetstream Series 200, 3100 and 3200 (Applicability).\n- Requires operators to install a redesigned radius-rod retention washer (a small metal part that helps keep the landing-gear link in place) in accordance with the manufacturer service bulletin (BAE Systems SB 32-JM5413) or an EASA-approved later revision (Requirement 1).\n- If an aircraft has not been modified with that redesigned washer, the operator must inspect the main landing-gear (MLG) radius-rod spherical bearing (the ball-and-socket style joint) for signs that the bearing has migrated out of its cylinder, using BAE Systems SB 32-JA030340 Rev 1 or later (Requirement 2).\n- If the aircraft has been modified with the redesigned washer, the operator must carry out a visual inspection of the radius-rod cylinder and the retention washer to look for migration or contact damage (Requirement 3).\n- If migration of the bearing or damage to the retention washer is found, the radius rod and/or the retention washer must be replaced before the aircraft flies again (Requirement 4). \n\n**Timing and intervals (how quickly and how often)**\n\n- Install the redesigned washer within 2,000 flight hours or one year from the AD’s effective date, whichever is later (Compliance 1).\n- For aircraft not yet modified: initial inspection within 50 flight cycles since the last inspection called for by the original AD, then repeat inspections at intervals no greater than 50 flight cycles (Compliance 2).\n- For aircraft modified with the redesigned washer: carry out the first visual inspection before the component reaches 5,000 flight cycles since installation, then repeat at intervals not to exceed 5,000 flight cycles (Compliance 3).\n- Where migration or damage is detected, replacement must occur before further flight (Compliance 4).\n\n**Why the regulator issued this (official stated purpose)**\n\n- The Background section says there was an incident in which the MLG radius rod housing migrated away from its spherical bearing attachment at the wing root. That migration can lead to detachment and sudden collapse of the MLG leg (a hazardous condition).\n- The cause was traced to incorrect swaging (a metal-forming process) of the bearing sleeve, which cannot be detected when the rod actuator is installed. The original AD required frequent inspections to detect migration; the current amendment keeps inspection requirements and adds a redesigned retention washer intended to prevent detachment if migration occurs.\n\n**Who this affects and who pays**\n\n- Primary cost-bearers are aircraft owners/operators of affected Jetstream models: they must schedule inspections, purchase parts (the redesigned retention washer and possibly replacement radius rods), and pay labour and downtime costs for installation and any replacements (Requirements 1–4; Compliance 1–4).\n- Maintenance organisations and parts suppliers will perform the work and supply the approved parts; they bear the cost of inventory, compliance documentation and any certification steps required by EASA/CASA.\n- The regulator (Civil Aviation Safety Authority) enforces compliance; the AD cites an earlier UK CAA AD and EASA approvals (Background; Note).\n\n**Behavioural and economic effects, trade-offs and implementation issues**\n\n- Incentives: Operators have a clear incentive to install the redesigned washer promptly because that modification extends inspection intervals from 50 flight cycles to 5,000 flight cycles, reducing recurrent inspection cost and aircraft downtime (Requirements 1, 2, Compliance 2–3).\n- Immediate cost vs. recurring cost: Up-front cost of parts and installation (within 2,000 flight hours or one year) is balanced against reduced long-term inspection frequency if the modification is done.\n- Safety vs. detection limits: The redesigned washer is presented as a physical mitigation to prevent separation if bearing migration occurs. The Background notes that incorrect swaging cannot be detected with the actuator installed, which explains reliance on both an engineered fix (washer) and inspections.\n- Implementation risks: availability of EASA-approved parts or later revisions of the service bulletins may affect how quickly operators can comply; repair facilities need access to the appropriate SB revision and may need to document EASA approvals.\n- Compliance burden and operational impact: For unmodified aircraft, the very frequent inspection interval (every 50 flight cycles) is operationally burdensome and may lead operators to prioritise installing the washer to move to the much longer interval (5000 cycles). Where migration or damage is found, the aircraft is grounded until replacement is done (Compliance 4).\n- Concentrated benefits, diffuse costs: The safety benefit is concentrated (prevents catastrophic landing-gear failure on affected aircraft), while the costs (parts, labour, downtime) fall directly and unevenly on the relatively small group of affected operators.\n- Regulatory discretion: The AD ties required actions to manufacturer service bulletins and to EASA-approved revisions, so the regulator and the certification process (EASA approvals) determine which technical documents and part designs meet the AD’s requirements.\n\n**Concrete mechanics: who decides and what changes**\n\n- The operator decides whether to immediately modify an aircraft (install washer) or continue operating under the short-inspection regime until modification; if migration/damage is observed, the operator must replace parts before further flight (Requirements 1–4; Compliance 1–4).\n- Maintenance organisations perform inspections and replacements to the specified service bulletins; EASA (and referenced UK CAA AD) approvals govern which revisions qualify.\n\n(Referenced provisions: Requirement 1–4; Compliance 1–4; Background and Note.)"}},"importantCases":[],"_links":{"self":"/api/acts/ad-jetstream-96-amdt-1-landing-gear-rod-spherical-bearing","history":"/api/acts/ad-jetstream-96-amdt-1-landing-gear-rod-spherical-bearing/history","analysis":"/api/acts/ad-jetstream-96-amdt-1-landing-gear-rod-spherical-bearing/analysis","conflicts":"/api/acts/ad-jetstream-96-amdt-1-landing-gear-rod-spherical-bearing/conflicts","importantCases":"/api/acts/ad-jetstream-96-amdt-1-landing-gear-rod-spherical-bearing/important-cases","documents":"/api/acts/ad-jetstream-96-amdt-1-landing-gear-rod-spherical-bearing/documents"}}