AD/BEECH 200/67 Amdt 6 - Fuselage Rear Pressure Bulkhead

The central concept in this AD is the rear pressure bulkhead, a structural component that seals the aft end of the pressurised fuselage. On Beechcraft 200 series aeroplanes, the bulkhead separates the pressurised cabin from the unpressurised tail cone. A crack or other damage in this bulkhead can cause loss of pressurisation, which may be inconvenient or hazardous at altitude. More critically, a large undetected crack could lead to catastrophic structural failure, because the bulkhead is a primary load-bearing element of the fuselage. The AD mandates a special inspection of both the forward side (visible from inside the pressure cabin) and the aft side (visible from the tail cone area, after removing insulation). The inspection must follow the procedure described in the Beech Super King Air 200 series maintenance manual, under Section 5-20-05, Inspection item 51, “Aft fuselage area and rear pressure bulkhead”. The AD also requires inspecting the area around the outflow valve and safety valve box, which was added in an earlier amendment based on damage found on an Australian-registered aircraft. The inspection looks for cracks, loose or missing rivets, and other damage such as sharp dents or punctures. These are stress concentration points that may later develop into cracks. The term cycles is used as the compliance metric: one cycle equals one pressurisation event. For most pressurised aircraft, a cycle is one take-off and landing. The AD sets an initial inspection at 10,000 cycles, then a recurrent inspection every 500 cycles, with a permitted tolerance of plus or minus 10 per cent. This tolerance, allowed by the manufacturer’s manual, gives operators a modest scheduling window but does not reduce the total number of inspections over the aircraft’s life. The AD also introduces the concept of damage causation: operators must not only repair damage but also identify and rectify the cause so it does not recur. For example, a sharp dent caused by a loose cargo restraint would require not just an engineering repair but also a procedural fix to prevent future impacts. The AD does not prescribe a specific engineering standard for repairs; it requires the repair to be “assessed” and “if necessary” performed, leaving the technical method to the maintenance manual and the judgment of an appropriately authorised person. The concept of special inspection is distinct from routine pre-flight or A-check inspections; it is a deeper, more methodical check that may require removing insulation and gaining access to hidden areas. This imposes additional labour and downtimes, which are direct compliance costs on the operator.

The AD applies to all registered operators of Beechcraft 200 series aeroplanes in Australia, including models 200, B200, 200C, B200C, 200T, and B200T, regardless of serial number. This covers a significant fleet of light twin-turboprop aircraft used in charter operations, air taxi services, regional transport, medevac, and private or corporate flying. The compliance burden falls most heavily on operators who fly frequent short sectors, because cycles accumulate quickly, triggering the 500-cycle inspection interval more often. An aircraft that flies four sectors per day will hit the interval every 125 days, while a low-utilisation aircraft flown once per week might take years to reach 500 cycles. The cost of each inspection (labour to remove and refit insulation, visual access, possibly borescope use, record-keeping) is identical for both high- and low-cycle aircraft, so the per-cycle cost is higher for low-use operators. This creates a regressive compliance burden: smaller operators with older aircraft may face proportionally larger costs relative to aircraft value. The AD also affects maintenance organisations (MROs) that hold approvals to perform airframe work on King Airs. They must ensure their technicians have up-to-date access to the maintenance manual, latest revision, and are trained on inspection item 51. The AD places no new obligations on manufacturers or parts suppliers; the burden is entirely on the operational side. CASA itself is affected in a process sense: its delegates must manage the AD filing system and ensure the instrument is properly promulgated. However, CASA bears no direct financial cost from the inspections. The AD also implicitly affects insurers, who may require proof of AD compliance as a condition of hull and liability coverage. A failure to perform the inspections could void coverage in the event of a pressurisation incident. Finally, the AD indirectly affects passengers and the flying public: compliance reduces the risk of in-flight depressurisation or structural failure, but the cost of compliance (labour, downtime) is ultimately passed through to ticket prices or charter rates.

The primary duty under this AD is to inspect the entire forward and aft side of the rear pressure bulkhead and the outflow and safety valve box for cracks, loose or missing rivets, and other damage. The inspection must be conducted in accordance with the Beech Super King Air 200 series maintenance manual, latest revision, Special Inspections, Section 5-20-05, Inspection item 51. This is a positive obligation: the operator must ensure the inspection is performed, not merely that a plan exists. The duty includes checking for sharp dents or punctures, which are stress raisers. If damage is found, the operator must have it “assessed, repaired if necessary and its cause rectified so it does not reoccur”. This implies a multi-step obligation: (1) assess the damage to determine if it is within allowable limits per the maintenance manual or if a repair is needed; (2) if a repair is needed, carry it out to an approved standard; (3) investigate and correct the underlying cause to prevent recurrence. The AD does not specify who must perform the assessment or repair, but in practice this must be done by an appropriately licensed aircraft maintenance engineer (LAME) or an approved maintenance organisation under CASR Part 145. The operator also has a duty to schedule the inspection at the correct intervals: initial at 10,000 cycles then every 500 cycles. However, the AD grants a right to apply a 10 per cent tolerance to the compliance time, as permitted in the Beech maintenance manual. This tolerance is an entitlement, not an automatic extension; the operator may choose to schedule inspections at 450-cycle intervals or as far out as 550-cycle intervals, but cannot exceed the tolerance consistently without exposing the aircraft to non-compliance risk. The amendment also lifted the transitional provision, meaning operators no longer have a grace period for special cases; they must be fully compliant from the effective date. The AD does not confer any new rights on third parties or create a private right of action. It is a safety directive that creates duties enforceable by CASA. Operators retain the right to seek an alternative means of compliance or an exemption under CASR Part 11, but that would require a separate application demonstrating equivalent safety. The AD does not explicitly mention record-keeping, but standard maintenance practice under CASR Part 42 requires that all mandatory inspections be recorded in the aircraft’s maintenance release or logbook, with details of findings and corrective actions. Failure to keep adequate records would also breach the airworthiness regulations, separately from the AD itself.

The AD itself does not prescribe monetary penalties or prison terms. However, it is made under the Civil Aviation Safety Regulations 1998, and non-compliance with an airworthiness directive is an offence under regulation 42.450 or related provisions. The maximum penalty for an individual can be up to 50 penalty units (currently AUD 9,650) per offence, with higher penalties for corporations. Additionally, operating an aircraft that is not in compliance with its AD schedule renders the aircraft unairworthy. Flying an unairworthy aircraft is a separate, more serious offence under the Civil Aviation Act 1988, with potential fines in the hundreds of thousands of dollars and, in extreme cases, imprisonment for reckless endangerment. CASA may also take administrative action: suspending or cancelling the aircraft’s certificate of airworthiness, issuing a grounding order, or requiring the aircraft to be flown to a place for inspection. For aircraft used in commercial operations, a grounding can cause significant economic loss through cancelled flights, reputation damage, and downstream contractual penalties. CASA enforcement is typically complaint-driven or triggered by routine surveillance. An operator who knowingly fails to perform the rear pressure bulkhead inspection at the correct interval could face escalated enforcement action. The AD’s requirement to rectify the cause of any damage adds another layer: if an operator merely patches a crack without fixing the underlying cause (e.g., a misaligned valve box), and the damage reappears, that could be viewed as ongoing non-compliance. The practical risk for operators is not just a fine but the loss of flying hours during downtime for rectification and the potential for CASA to audit the entire maintenance system. The AD does not impose a specific record-keeping requirement, but regulators will typically expect written evidence of each inspection, with photographs or engineering reports if damage is found. Without records, the operator bears the burden of proving compliance. Enforcement costs to the regulator are relatively low because the AD is well-established and the inspection interval is straightforward. CASA may use its Airworthiness Assurance section to audit selected operators. There is no provision in the AD for an internal review or appeal; an operator who disputes a notice of non-compliance must pursue it through the AAT or the Federal Court. The cost of contesting enforcement action almost always outweighs the cost of just doing the inspection, creating a powerful incentive for compliance regardless of the underlying safety merit.

This AD operates within a web of airworthiness regulations, other ADs, and manufacturer’s service information. Most directly, it is issued under CASR Part 39, which empowers CASA to mandate mandatory continuing airworthiness information. Non-compliance with Part 39 is an offence. The AD itself references the Beech Super King Air 200 series maintenance manual; that manual is a regulatory document approved by the US FAA and accepted by CASA, so following it is implicitly required for continued certification. The AD also interacts with FAA AD 2003-13-16, which is mentioned in the Background: Amendment 3 of the Australian AD removed a requirement that duplicated the FAA AD, specifying that the separate inspection for score marks is now mandated by the FAA AD alone. Operators must therefore track both the Australian AD and the FAA AD (if the aircraft is also on the US register, or if CASA has adopted it). The AD does not specify priority, but the more restrictive requirement applies. The AD’s compliance tolerance (10%) is aligned with the manufacturer’s manual. However, other CASA regulations may impose stricter record-keeping or repair standards; for instance, a repair to a primary structure like the rear pressure bulkhead would be a major repair under CASR Part 145 and may require approval from a design organisation. The AD does not exempt those requirements; it merely adds inspection duties on top. Additionally, the AD does not replace any existing airworthiness limitations. The maintenance manual may contain other life limits or scheduled inspections for the same area; the AD supplements them. The AD also interacts with the Civil Aviation Safety Regulations Part 42 (continuing airworthiness) and Part 91 (aircraft operations). An operator who discovers damage must decide whether the aircraft is safe to fly to a repair facility; that decision is governed by regulation 42.260 (defect reporting) and the operator’s own maintenance control manual. The AD does not provide an explicit ferry flight permission. The amendment history notes that a transitional provision was removed, meaning there is no longer any grace period for operators who are building up cycles slowly. This interacts with the general CASR requirement to maintain the aircraft in a condition for safe operation at all times. Finally, the AD’s requirement to work to the “latest revision” of the manual creates an ongoing interaction with the manufacturer’s revision process. If Beech revises Section 5-20-05 to change the inspection method or the allowed damage limits, the AD automatically incorporates that change, without needing a further amendment. This saves CASA administrative work but forces operators to monitor manual revisions continuously, a hidden compliance burden.

The original AD became effective on 7 March 2000, establishing the core requirement to inspect the rear pressure bulkhead. Amendment 1 (effective 20 March 2003) added a requirement to inspect and repair the aft pressure bulkhead in accordance with a mandatory service bulletin issued by Raytheon (the then manufacturer) and added a visual inspection of the area around the cabin outflow valve cutouts for damage. This was prompted by damage observed on an Australian-registered aircraft that was not covered by the manufacturer’s bulletin. Amendment 2 (effective 11 February 2004) clarified the applicability to include aircraft that had had post-production removal and reinstallation of insulation material covering the rear pressure bulkhead. It also brought forward the compliance time for Requirement 2 to align with the shorter interval in the FAA version. Amendment 3 (effective 15 April 2004) removed Requirement 2 entirely because the mandated inspection for score marks was now covered by a separate, dedicated AD (based on FAA AD 2003-13-16). This rationalised the AD suite. Amendment 4 (effective 24 November 2005) removed the specific revision date and page number from the requirement section, replacing them with “latest revision”. This change was forward-looking, intended to avoid needing a new amendment every time Beech updated the manual. Amendment 5 (effective 12 March 2009) introduced the 10% tolerance on the compliance interval, aligning the AD with the manufacturer’s own allowance for special inspections. This gave operators scheduling flexibility but did not change the fundamental inspection interval. Amendment 6 (the current instrument, effective 18 January 2012) corrected the maintenance manual reference in the requirement section to use the current manual number and removed the now-obsolete transitional provision. Each amendment was explicitly stated to make no change to the technical requirement or compliance interval (except where noted). The cumulative effect is a maturing regulatory instrument that has become simpler and more durable over time, while the underlying safety concern (cracking in the rear pressure bulkhead) remains the same. The history shows CASA reacting to field experience, manufacturer service bulletins, and FAA activity, gradually delegating more of the technical detail to the manufacturer’s manual rather than freezing it in the AD text. This reduces the frequency of amendments but shifts the compliance burden onto operators to track manual changes.

The source document makes no mention of any litigation, court cases, or tribunal decisions related to this AD or its predecessors. That does not guarantee none exists; a search of Australian administrative law databases might reveal applications to the AAT for review of CASA decisions (e.g., to grant an extension, or to contest a grounding). However, because the AD involves a routine repetitive inspection with no novel policy and minimal discretion, it is unlikely to have generated significant litigation. The costs of challenging a CASA airworthiness directive would be high, and the scope for a successful challenge narrow: the AD must be reasonably necessary for safety, but the courts give CASA wide deference on technical matters. The AD does not, on its face, contain any arbitrary or capricious elements; it tracks manufacturer recommendations and FAA actions. If litigation has occurred, it is probably at the enforcement level: an operator prosecuted for failing to perform the inspection might argue the AD was not properly promulgated, or that the inspection interval was impossible to meet. But no such case is cited in the instrument. The absence of litigation history is itself informative: it suggests that the regulated community accepts the AD as conventional and non-controversial, and that compliance costs, while real, are not so high as to provoke legal resistance. However, the lack of case law also means there is no judicial guidance on borderline issues such as what constitutes a “rectified cause” of damage, or whether the 10% tolerance may be applied cumulative across multiple intervals. Operators and MROs must rely solely on the text and the maintenance manual for interpretation. In the event of a dispute, a tribunal would likely give significant weight to the manufacturer’s documentation and CASA’s public guidance materials.

Several traps in this AD can lead to inadvertent non-compliance. First, the requirement to use the “latest revision” of the maintenance manual. If an operator’s maintenance library is outdated, or if the manual revision is not recorded in the maintenance records, a CASA inspector could find the aircraft non-compliant even though the actual work performed was correct. The AD does not provide a grace period for manual updates. Second, the 10% tolerance on compliance intervals is available only if the maintenance manual permits it for special inspections and only for those that are flight-cycle or hourly limited. An operator cannot apply the tolerance just because the AD says “500 cycles” without confirming the manual authorises it. Misapplication would render the interval non-compliant. Third, the AD requires inspecting both sides of the bulkhead. The aft side often requires removing insulation, which may be time-consuming and easy to skip if the aircraft is under pressure to return to service. A superficial visual check from the forward side only does not satisfy the AD. Fourth, damage assessment is not a one-time event; if damage is found and repaired, the operator must also rectify the cause so it does not reoccur. This is a less familiar obligation for many operators. If a sharp dent is caused by a fastener protruding through a panel, simply replacing the panel without inspecting the rest of the area for similar issues might be considered incomplete rectification. Fifth, the AD does not specify a failure reporting threshold. Even hairline cracks that are within allowable limits must be noted and assessed. If the operator decides no repair is needed, that decision must be documented. Without a written record, the operator cannot prove compliance. Sixth, the 500-cycle interval may be easy to exceed if an aircraft is used intensively over a short period, especially if the operator relies on calendar-based tracking and forgets to monitor cycles. The AD has no calendar alternative; it is cycles only. Seventh, the amendment removed the transitional provision. Any operator who was relying on a previous grace period (e.g., for aircraft that had already passed 10,000 cycles before Amendment 5) must now be compliant with the current interval. Eighth, the outflow and safety valve box area must be inspected as part of the same task. That area may be partially hidden by ducting; failing to access it fully is a common omission. Ninth, the AD applies to “all serial numbers”, including aircraft that may have been modified with a non-standard bulkhead or a supplemental type certificate. No exclusion exists. Tenth, if the aircraft is operated under a contracted maintenance provider, the operator remains legally responsible for compliance, not the MRO. The fines and grounding risk stay with the registered operator. The cost of each inspection is not trivial: labour to remove and refit insulation, possibly borescope, and the need for a LAME to sign off means compliance is a measurable expense that must be budgeted.

Compliance with AD/BEECH 200/67 Amdt 6 requires a systematic approach embedded in the operator’s continuing airworthiness management system. First, the operator must ensure they hold or have access to the current (latest revision) Beech Super King Air 200 series maintenance manual, specifically Section 5-20-05, Inspection item 51. The manual should be checked for any revisions at least annually or whenever CASA issues a bulletin. Second, the operator must determine the aircraft’s cycle count. This means having a reliable cycle counter or flight hours conversion, recognising that one cycle equals one take-off and landing (pressurisation event). The initial compliance point is 10,000 cycles, but for aircraft that have already exceeded that, the next recurring interval is 500 cycles from the last inspection. Third, the operator should schedule the inspection at the calculated cycle number, applying the 10% tolerance if beneficial and if the manual permits it. The tolerance should not be used to permanently shift the baseline; it is a scheduling window. Fourth, the inspection must be performed by an appropriately authorised person (a LAME or an approved maintenance organisation). The inspector must access both the forward and aft sides of the bulkhead, including the outflow and safety valve box area. This may require removing soundproofing insulation, which must be done carefully to avoid damage and to allow replacement. The scope includes checking for cracks (visual, possibly with magnification or dye penetrant if the manual requires), loose or missing rivets, sharp dents, and punctures. If any damage or anomaly is found, it must be assessed against the manual’s allowable limits. If repair is required, the operator must arrange for a repair approved by the design authority (typically via a repair design approval or a manufacturer’s repair scheme). After the repair, the root cause of the damage must be investigated and corrected. For example, if a punctured bulkhead was caused by a loose object in the tail cone, the operator must implement a procedure to secure cargo or prevent object movement. Fifth, all findings, assessments, and corrective actions must be documented. The entry in the aircraft maintenance record should include the date, the cycle count at inspection, the manual revision used, a description of findings, any repairs performed, and the signature of the certifying person. A photo of the bulkhead (especially if damage found) can be helpful for future reference and for CASA audits. Sixth, the operator must monitor the cycle count after the inspection to ensure the next inspection is performed within 500 cycles (plus tolerance). This requires an effective airworthiness tracking system, whether spreadsheet-based or commercial. Seventh, if the aircraft is leased or chartered, the operator must ensure that any maintenance provider used is aware of this specific AD and its details. Because this AD has been in effect since 2000, it is well known, but a change of ownership or maintenance provider may cause a gap. Eighth, the operator should periodically review the CASA AD list to confirm that no further amendments have been issued. Amendment 6 is current, but subsequent amendments might alter the interval or scope. Ninth, for operators with multiple King Airs, a fleet-wide schedule can reduce administrative overhead and allow pooling of access to the manual. The cost of compliance will be dominated by labour hours for insulation removal and replacement, plus the direct cost of any repairs. A typical inspection might take 2-4 man-hours plus downtime. The cost of non-compliance (grounding, fines, accident risk) far exceeds this, making the inspection an easy compliance decision. However, the ongoing administrative burden of tracking cycles and manual revisions should not be underestimated; it is a real but manageable cost of operating pressurised turbine aircraft in Australia.