AD/BELL 212/67 - Emergency Floatation Reservoir Adapter

The AD explicitly identifies the category of aircraft affected (Applicability). It applies to Bell Helicopter Textron Model 212 helicopters that either have been modified under AAI STC SH2820SO, or that have installed AAI PMA reservoir assemblies P/N 212-372-050, or installed adapter P/N 212-371-002. That language confines the AD to those airframes with that modification or those parts fitted; Bell 212 helicopters without those modifications or parts are not within the stated applicability on the face of this text.

The text does not name a particular person or corporate role as the party required to perform the mandated steps. The AD prescribes maintenance actions that must be accomplished on the listed aircraft (Requirement and Compliance). Practically, those actions will be undertaken by whoever is responsible for the airworthiness maintenance of the affected helicopter , for example the aircraft owner, operator, or approved maintenance organisation , but the AD itself does not allocate cost or expressly specify the responsible legal entity in this document. The AD was issued by the Civil Aviation Safety Authority (CASA), signed by Delegate James Coyne, and becomes effective on 9 November 2005; it therefore places a regulatory obligation attached to the aircraft and its continuing fitness to fly from that date (effective date statement).

Parts suppliers and maintenance facilities are implicated because the AD requires either recharging the existing floatation system (if dimension D is acceptable) or replacing the reservoir assembly and adapter with serviceable parts if the dimension exceeds .860 inch (Requirement 2 and 2(b)). That creates a demand for replacement parts (AAI reservoir assembly and adapter) and for access to the AAI ASB as the procedural authority for discharging and charging the system. The note cross-referencing FAA AD 2005-20-38 implies that US oversight and documentation may be relevant to operators and maintainers working with these components.

Finally, the AD’s safety rationale,risk of rupture and uncontrolled jetting of pressurised gas causing injury or damage,affects occupants, maintenance personnel who will vent the system during the inspection, and any third parties exposed if a rupture were to occur. The AD’s immediate deadlines therefore impose operational disruption risk for affected aircraft until the required inspection/repair is completed.

The AD sets discrete duties and references the procedural authority to accomplish them. The duty elements in the text are:

• Vent the nitrogen from the reservoir assembly by following the Accomplishment Instructions, Part II - Floatation System Discharging, of AAI ASB No. AA-05005, Revision A dated 27 June 2005 or later FAA Approved revision (Requirement 1). The AD directs that discharging be done in accordance with that specified portion of the ASB; the ASB is the procedural document for safe discharge.

• Remove the valve assembly and air line from the adapter and inspect the counter bore depth (dimension D) as shown in Figure 1 of the ASB (Requirement 2). The AD makes that inspection step mandatory prior to recharging or replacement decisions.

• Conditional corrective action tied to the inspection metric:

  • If dimension D does not exceed .860 inch, recharge the floatation system by following the Accomplishment Instructions, Part III - Floatation System Charging, and referring to Figures 2 and 3 of the ASB (Requirement 2(a)). The AD therefore prescribes a prescribed recharging procedure where the measurement is within tolerance.
  • If dimension D exceeds .860 inch, replace the reservoir assembly and the adapter with serviceable parts (Requirement 2(b)). Replacement is mandatory where the dimensional tolerance is exceeded.

• The AD reiterates that discharging and recharging the floatation system and inspecting the counter bore depth shall be done in accordance with the specified portions of the ASB (Requirement 3). The AD therefore delegates the exact steps and safety precautions to the named portions of the ASB.

Rights are not enumerated in this instrument. The AD does not specify appeal rights, waivers or exemptions in its text. It does, however, incorporate the ASB and an FAA AD reference, which may provide procedural detail or options external to this text (Note referencing FAA AD 2005-20-38). The AD also contains explicit compliance timing provisions (Compliance), which set the regulatory deadlines that must be met. The AD becomes effective on a stated date (9 November 2005), which determines when the duties take legal effect.

In short, the key duties are the three required maintenance actions and the conditional repair/replace decision driven by the .860 inch measurement, all to be performed in conformity with the relevant parts of AAI ASB No. AA-05005 Revision A or any later FAA-approved revision. The AD text itself does not specify rights, cost allocation, or administrative review mechanisms.

The AD text provided does not specify penalties, fines, or enforcement mechanisms within its body. It records that the Airworthiness Directive becomes effective on 9 November 2005 and is issued under the authority of the Civil Aviation Safety Authority, with James Coyne identified as the delegate who signed the instrument on 4 November 2005. The document’s scope and compliance deadlines create an enforceable airworthiness requirement by operation of the AD mechanism; however, this particular text contains no express provisions about sanctions for non-compliance or the procedural steps CASA would take to enforce the AD.

Operationally, the compliance deadlines are strict: most required work must be completed within 24 hours TIS or before the next emergency floatation supply bottle nitrogen charging after the effective date, and replacement is required before further flight if the critical measurement exceeds .860 inch (Compliance; Requirement 2(b)). Those deadlines effectively constrain flight operations of affected aircraft until compliance is demonstrated.

The AD also cross-references AAI ASB No. AA-05005 Revision A for the detailed method of discharging, inspecting, charging and replacing parts; following those instructions will be the evidentiary basis for demonstrating compliance with the AD’s requirements (Requirement 1, 2, 3). The AD’s Note references FAA AD 2005-20-38 Amendment 39-14335, which may indicate that similar enforcement expectations exist under FAA oversight. The AD text does not list an enforcement agency beyond CASA or specify the regulatory procedure for documenting compliance in maintenance records, reporting to CASA, or seeking relief from the AD.

Because the text does not state penalties, readers should not infer specific sanctioning provisions from this AD alone. Any penalty or administrative enforcement action would derive from the broader statutory regime that empowers CASA to issue and enforce ADs, but such statutory provisions are not included in the supplied text and thus are not a basis for statements here. The AD itself functions as a mandatory maintenance instruction with precise timing and technical thresholds, and non-compliance would reasonably be expected to affect the aircraft’s airworthiness status; the AD document here does not further elaborate enforcement steps or penalties.

The AD text makes two explicit cross-document references, which define its primary interactions with other regulatory or technical materials in this document:

• AAI Alert Service Bulletin No. AA-05005, Revision A dated 27 June 2005, or a later FAA-approved revision, is incorporated by reference for procedural detail. The AD requires that venting (Part II - Floatation System Discharging) and charging (Part III - Floatation System Charging) actions be executed according to those ASB sections and figures. Thus, the AD’s technical compliance regime depends on the ASB’s procedural content; the AD does not duplicate procedural steps and instead points to the ASB as the operational authority for accomplishing the specified tasks (Requirement 1; Requirement 2(a); Requirement 3).

• FAA AD 2005-20-38 Amendment 39-14335 is referenced in a note. That indicates the Australian AD is aligned with or cognisant of a contemporaneous FAA directive addressing the same technical issue. The AD’s note does not spell out the legal effect of the FAA AD within Australian law, but it makes a documentary connection that may be relevant to operators with transnational maintenance chains or with documentation that references FAA action (Note).

The supplied AD does not reference other Australian statutes, regulations, or CASA policy instruments by section number, nor does it include a transposition clause or any express statement about how conflicts between the AD and other laws should be resolved. The AD’s incorporation by reference of the ASB means that the requirements of the ASB (and any FAA-approved revisions) are necessary for compliance; this is an interaction where a technical manufacturer document becomes part of the regulatory compliance regime by reference.

Because the AD specifies compliance timing and that replacement must be carried out "before further flight" when the dimension exceeds .860 inch, the AD interacts functionally with operational safety rules: affected aircraft cannot lawfully continue flight if they have not met the AD’s replacement requirement in that scenario. The AD does not, however, provide the administrative mechanisms for recording compliance, notifying CASA, or seeking an exemption; those mechanisms would be governed by broader aviation safety law and CASA procedures that are not contained in the supplied text.

No other statutes, regulations, or international agreements are named in the supplied text. The document therefore single-lines its interactions to the ASB and the FAA AD it explicitly references.

The AD text itself provides only limited amendment-history information. It identifies the AAI Alert Service Bulletin required for accomplishing the actions as "AAI Alert Service Bulletin (ASB) No. AA-05005, Revision A dated 27 June 27 2005 or later FAA Approved revision" (Requirement 1). That language acknowledges that later revisions of the ASB may exist and that FAA approval of any revision is the controlling milestone for acceptability; however, the AD text does not list earlier revisions or subsequent amendments to the AD itself.

The AD includes a Note referencing FAA AD 2005-20-38 Amendment 39-14335. This cross-reference serves as documentary context; it does not, within this text, constitute an amendment to the AD nor does the AD state whether it was amended to align with that FAA AD. The AD is signed on 4 November 2005 and is stated to become effective on 9 November 2005, which indicates its initial issuance and effective date. No subsequent amendments to AD/BELL 212/67 are recorded in the supplied text.

Consequently, based solely on the supplied instrument, the amendment history consists of:

• The incorporation of AAI ASB No. AA-05005 Revision A (dated 27 June 2005) as the procedural authority; the AD allows for "later FAA Approved revision" as acceptable, which leaves open incorporation by reference of any future FAA-approved ASB revisions post-dating the AD.
• The contemporaneous FAA AD reference (FAA AD 2005-20-38 Amendment 39-14335) recorded in the note.
• The issuance signature and dates: signed 4 November 2005 by James Coyne (Delegate of CASA) and effective 9 November 2005.

No further modifications, revocations, or updates to AD/BELL 212/67 are contained in the provided text. If an operator needs the current amendment status beyond what is in this instrument, they must consult CASA’s official AD registry or the AAI/FAA documents that are referenced; such external consultation is not reflected in the instrument itself.

The AD text supplied contains no litigation history. It does not cite any court decisions, judicial interpretations, administrative appeals, or challenges to this AD. The document does not indicate whether any parties contested the AD, sought review, obtained temporary relief, or otherwise engaged in litigation related to AD/BELL 212/67. The only external reference is to FAA AD 2005-20-38 Amendment 39-14335 and to AAI ASB No. AA-05005 Revision A; neither of those references in the supplied text is accompanied by litigation or case citations.

Therefore, based exclusively on the supplied material, there is no recorded litigation history for AD/BELL 212/67 in this document. Any judicial or administrative challenges, if they occurred, are not reflected in the text provided and would need to be located in external records, case reports, or administrative registries outside the scope of this instrument.

The AD includes a number of specific technical and timing details that create practical risk points and potential pitfalls for operators, maintainers and supply chains. These are stated in the AD and stem directly from its language.

• Narrow applicability but precise dependency on modifications and part numbers: Only Bell Model 212 helicopters modified with AAI STC SH2820SO, or fitted with AAI PMA reservoir assembly P/N 212-372-050 or adapter P/N 212-371-002, are subject to the AD (Applicability). Operators must check aircraft records carefully; incorrectly assuming the AD applies or does not apply could lead to unnecessary work or regulatory non-compliance.

• Dependency on an external ASB for method: The AD requires that tasks be completed "by following the Accomplishment Instructions, Part II - Floatation System Discharging, of AAI ASB No. AA-05005, Revision A dated 27 June 2005 or later FAA Approved revision" and, for recharging, Part III and relevant figures (Requirement 1 and 2(a)). The AD therefore makes procedural compliance conditional on access to that ASB. If maintainers do not possess the correct revision or an FAA-approved later revision, they lack the step-by-step instructions mandated by the AD. The AD does not itself set out the procedural steps.

• Critical measurement threshold: The inspection depends on a single dimensional limit, .860 inch, as depicted in Figure 1 of the ASB (Requirement 2 and 2(a)/(b)). The AD does not provide alternate tolerances or measurement methods; performing the measurement incorrectly, or misreading the ASB figure, will yield incorrect compliance outcomes. The AD’s accept/reject decision is binary and hinges on this measurement.

• Order of operations: The AD requires that the reservoir be vented first by following the ASB Part II discharging instructions (Requirement 1). Then the valve assembly and air line must be removed and the measurement taken (Requirement 2). Recharging is only permitted if the measured D does not exceed .860 inch; otherwise replacement is mandatory (Requirement 2(a)/(b)). Failure to vent before disassembly could create a hazard during inspection. The AD imposes an order that must be followed.

• Rapid compliance window: The AD requires action "within the next 24 hours time-in-service (TIS) or before the next emergency floatation supply bottle nitrogen charging after the effective date of this AD" (Compliance). That short window creates scheduling pressure for operators and maintenance providers. The AD also requires replacement "before further flight" when the D measurement exceeds .860 inch. Those deadlines may effectively ground affected helicopters pending inspection and possible parts replacement.

• Parts and "serviceable" requirement: If D exceeds the tolerance, the AD mandates replacement with "serviceable parts" (Requirement 2(b)). The AD does not define in this text how to demonstrate a part’s serviceability or where to source AAI parts. Availability of replacement reservoir assemblies and adapters may thus be a practical constraint; the AD does not provide transitional relief or temporary measures.

• Recordkeeping and proof: The AD instructs actions but does not specify how compliance must be documented in maintenance logs or notified to CASA. Operators must ensure their own records adequately demonstrate the AD tasks were followed per the ASB to show compliance, but the AD text does not prescribe the form of that evidence.

• Cross-reference to FAA AD and later ASB revisions: The AD allows later FAA-approved ASB revisions to govern the procedures. If a later revision exists that changes figures, measurement techniques, or thresholds, operators must ensure they are using the FAA-approved revision that the AD accepts. Misapplication of an incorrect ASB revision could lead to non-compliance.

• Personnel safety during venting: The AD cites the hazard (rupture, uncontrolled jetting) and requires venting as the first step. Maintenance personnel must follow the ASB’s discharge procedures to manage that hazard; the AD does not include the procedural detail that addresses personnel safety, leaving that to the ASB.

These are operational and compliance "gotchas" directly visible in the AD text: precise applicability, reliance on an external ASB, a single dimensional pass/fail metric, rapid compliance deadlines, and replacement with unspecified "serviceable parts" if the threshold is exceeded.

The AD prescribes a concise, sequenced set of steps and timing rules. To comply with the AD as written, an operator or maintainer should do the following, working only from the language of the AD and the incorporated ASB:

1. Confirm applicability: Verify that the helicopter is a Bell Helicopter Textron Model 212 that is modified under AAI STC SH2820SO, or that it has AAI PMA reservoir assembly P/N 212-372-050, or adapter P/N 212-371-002 installed (Applicability). If the helicopter does not meet any of these criteria, this AD’s requirements do not apply as drafted.

2. Obtain the referenced ASB: Secure AAI Alert Service Bulletin No. AA-05005, Revision A dated 27 June 2005, or a later FAA-approved revision. The AD requires following the ASB’s Accomplishment Instructions Part II for discharging and Part III for charging, and refers to Figures 1-3 for inspection and recharge guidance (Requirement 1 and 2(a)). Ensure the ASB revision in hand is acceptable under the AD: either Revision A or a later FAA-approved revision.

3. Meet the time window: Schedule the work within the regulatory time frame. The AD requires the specified actions "within the next 24 hours time-in-service (TIS) or before the next emergency floatation supply bottle nitrogen charging after the effective date of this AD" for the primary steps, and imposes "before further flight" for mandatory replacements where the measurement exceeds the limit (Compliance). Plan maintenance slots and, if necessary, ground the aircraft until the inspection and any required remedial work are complete.

4. Discharge the system first: Vent the nitrogen from the reservoir assembly by following the Accomplishment Instructions, Part II - Floatation System Discharging, of the ASB (Requirement 1). The AD makes venting the first required action, so do not proceed to remove the valve assembly or conduct measurements until the system has been discharged per the ASB instructions.

5. Remove and inspect the adapter: Remove the valve assembly and air line from the adapter, then inspect the counter bore depth, dimension D, as depicted in Figure 1 of the ASB (Requirement 2). Use the ASB figure and any measurement tolerances or techniques it prescribes to determine the true depth.

6. Compare to the .860 inch threshold and act accordingly:

   • If the measured D does not exceed .860 inch, recharge the floatation system by following the Accomplishment Instructions, Part III - Floatation System Charging, and refer to Figures 2 and 3 of the ASB for the charging procedure (Requirement 2(a)). After recharging, document the steps per usual maintenance record practice.
   • If the measured D exceeds .860 inch, replace the reservoir assembly and the adapter with serviceable parts before further flight (Requirement 2(b)). Do not return the helicopter to service until the replacement has been completed. The AD does not define "serviceable" within this text; follow the ASB, manufacturer guidance, and approved parts lists to obtain and install compliant replacement components.

7. Ensure all discharging, recharging and inspection steps are carried out exactly per the specified portions of the ASB (Requirement 3). The AD requires that these tasks be done "in accordance with the specified portions of the ASB", so procedural fidelity to the ASB is essential to satisfy the AD.

8. Maintain records: Although the AD does not specify a particular form of documentation, maintain clear maintenance records that show the date, TIS at which the inspection and actions were done, the measured value for dimension D, the ASB revision used, any parts replaced (including part numbers and serial numbers if applicable), and the identity of the persons or organisation performing the work. Such records will be the operational proof of compliance.

9. Consider supply chain implications: If replacement is required, make arrangements to obtain AAI reservoir assemblies and adapters identified by the AD. The AD demands replacement with "serviceable parts" where D exceeds .860 inch (Requirement 2(b)); ensure sourced parts meet the serviceability and approvals standard that the ASB and local aviation regulations require.

10. Liaise with CASA or follow organisational procedures if clarification or relief is needed: The AD text itself does not set out processes for requesting alternative inspections, extensions, or exemptions. If such relief is needed, seek the appropriate CASA channels or follow established maintenance organisation procedures, noting the AD’s effective date and urgent deadlines.

Following these steps will implement the AD requirements as they appear in the supplied text: vent the system per Part II of the ASB, inspect the counter bore depth per Figure 1, recharge per Part III and Figures 2-3 if D ≤ .860 inch, and replace the reservoir assembly and adapter with serviceable parts before further flight if D > .860 inch, all within the AD’s tight compliance windows.