AD/BELL 205/70 Amdt 1 - Tail Rotor Blade Fwd Tip Weight Retention Block and Aft Tip Closure

The instrument centres on the structural integrity and fitment of two tail rotor blade components: the forward tip weight retention block and the aft tip closure. These components are implicated in bond integrity and mechanical retention of the tail rotor blade tip assembly. The AD addresses three failure modes or defects: adhesive bond voids in the retention block or aft closure, recessed or filled countersink screws for the retention-block attachment, and missing aft tip closure rivets.

Applicability is narrowly drawn by model, part number range, and serial-number exceptions. The AD applies only to Bell 205A, 205A-1, and 205B helicopters fitted with tail rotor blade part numbers 212-010-750-009 through -129, all serial numbers, except serial numbers with a prefix of "A" or "AFS" and the number 11926, 13351, 13367, 13393, 13400, 13402, 13515, 13540, 13568, 13595 through 13602, 13619, and subsequent assigned numbers, installed ("Applicability"). That language both limits the regulated population and creates an identification task for operators to match blade part and serial numbers precisely.

The AD links compliance to manufacturer's Alert Service Bulletins: ASB 205-00-80 Revision D or 205B-00-34 Revision D, or later FAA approved revisions. These ASBs contain the locations for the four countersink screws (depicted in Figure 1) and the step-by-step Accomplishment Instructions for shear pin installation (Part A) and aft tip closure rivet installation and dynamic balancing (Part B) ("Requirement"). The AD thereby delegates the detailed technical steps to the ASBs and requires use of FAA approved later revisions if applicable.

One administrative identification change is mandated: after the aft tip closure rivets are installed, the modified blade must be re-identified by adding "FM" to the part number, and the tail rotor hub assembly must be dynamically balanced in accordance with the ASB ("Requirement"). Dynamic balancing is an operational step that requires appropriate tooling and balancing procedures. The AD further requires removal of blades where adhesive bond voids exceed the limitations specified in the Component Repair and Overhaul Manual; the AD does not itself give the numerical void limits, instead pointing operators to the overhaul manual.

Timing is strict: the whole sequence must be completed within 100 hours time-in-service after 20 December 2007 unless already done ("Compliance"). The background recites operational incidents leading to the AD: five occurrences of missing forward tip weight retention blocks or aft tip closures that produced damage and could lead to loss of a tail rotor blade and helicopter control ("Background"). Amendment 1 is explicitly said to respond to a new FAA AD that expands applicability and clarifies re-identification and balancing requirements ("Background").

The AD therefore implements a targeted airworthiness action: inspect for bond integrity and countersink screw condition, install shear pins and aft tip closure rivets where required, re-identify blades, and perform dynamic balancing, using ASB-specified procedures within a set compliance hours. The AD references and relies on FAA rulemaking and the manufacturer’s ASBs for technical content and for later FAA-approved revisions.

This AD affects operators, owners, maintenance organisations, and maintainers of Bell Helicopter Textron 205 series aircraft that have the specified tail rotor blades installed. The "Applicability" clause identifies the precise cohort: Model 205A, 205A-1 and 205B helicopters with tail rotor blade part numbers 212-010-750-009 through -129, subject to the serial-number carve-outs listed in the instrument ("Applicability"). Maintenance planners and records personnel are particularly implicated because compliance requires identification of the blade part and serial number and a re-identification marking change where work is done.

The immediate financial and operational burden falls on the registered owners and operators of the affected helicopters because they must arrange and fund the inspections, removals, repairs, shear pin installations, aft-tip rivet installations, re-identification, and dynamic balancing within the 100 hours time-in-service window after 20 December 2007 ("Requirement", "Compliance"). Maintenance organisations will provide the labour, tooling, and in some cases replacement parts. If a blade is removed because its adhesive bond void exceeds limits in the Component Repair and Overhaul Manual, the operator will incur additional costs for a repair or replacement blade, and may face aircraft downtime while a suitable blade or repair capability is sourced.

Regulatory actors are also affected. The AD is issued by CASA and signed by a delegate (David Villiers, dated 7 November 2007). It references FAA AD 2007-22-02 Amdt 39-15238, and the ASBs identified are Bell Helicopter Textron Inc. ASB 205-00-80 Revision D and 205B-00-34 Revision D, or later FAA approved revisions. Maintenance organisations must therefore use the specified ASB revisions or later FAA approved revisions where applicable. This creates a dependency on manufacturer documentation and FAA approval of later revisions.

Record-keeping stakeholders are implicated by the re-identification requirement: when aft tip closure rivets are installed the modified blade must be re-identified by adding "FM" to the part number. That change must be reflected in the aircraft and component records, logbooks, and any continuing airworthiness records used to demonstrate AD compliance. The source text does not provide the method or authority for recording the re-identification beyond the instruction to add "FM".

Pilots and operators indirectly affected include those involved in flight scheduling, because compliance actions may remove aircraft from service temporarily. The AD’s 100-hour compliance horizon sets an operational deadline; aircraft that exceed that window without the required inspection and repairs will be non-compliant with the AD as written.

The AD’s exclusions (serial numbers with "A" or "AFS" prefixes and specific listed numbers and subsequent assigned numbers) mean some blades and therefore some aircraft are not captured. That creates a discrete population that is out-of-scope, and an identification task for operators to confirm whether their blades fall into that excluded sub-set.

Finally, component suppliers and overhaul shops that maintain or supply tail rotor blades are implicated because the AD references Component Repair and Overhaul Manual limits for adhesive bond voids; those manuals determine when a blade must be removed rather than repaired on-wing.

Duties

• Identify applicability: Operators must determine whether any installed tail rotor blades fall within the part-number range and serial-number criteria specified in the AD ("Applicability"). This is a precondition to performing the AD work.

• Inspect for adhesive bond voids: Within the compliance window, inspect the tail rotor blade forward tip weight retention block and aft tip closure for adhesive bond voids, and remove any blade with a void exceeding the Component Repair and Overhaul Manual limitations ("Requirement"). The AD does not list the numerical void criteria; it defers to the Component Repair and Overhaul Manual for limits.

• Inspect countersink screws: Inspect the forward tip weight retention block attachment countersink screws in four locations, as depicted in Figure 1 of the referenced ASB, to determine whether the head of each screw is flush with the abrasion strip surface. If any screw is recessed or covered with filler, the operator must install shear pins in accordance with the ASB Part A instructions ("Requirement").

• Install aft tip closure rivets: Where necessary, install aft tip closure rivets per the ASB Part B instructions ("Requirement").

• Re-identify modified blade: After modification, re-identify the blade by adding "FM" to the part number as specified ("Requirement").

• Dynamically balance tail rotor hub: After the rivet installation and re-identification, dynamically balance the tail rotor hub assembly in accordance with the ASB Part B instructions ("Requirement").

• Time limit: All required actions must be completed within 100 hours time in service after 20 December 2007 unless already accomplished ("Compliance").

These duties are expressed as mandatory within the AD. The AD prescribes the use of specific ASB revisions or later FAA approved revisions for the technical steps, so implementing persons must have access to and follow those documents. The AD also delegates to the Component Repair and Overhaul Manual judgment on when a blade must be removed for excessive adhesive voids.

Rights

• Right to use later FAA-approved ASB revisions: The AD explicitly allows the use of ASB 205-00-80 Revision D or 205B-00-34 Revision D, "or later FAA approved revisions, as applicable" for the detailed procedures ("Requirement"). That gives operators latitude to follow later ASB revisions if those revisions have FAA approval.

• Right to consult Component Repair and Overhaul Manual: For the adhesive bond void acceptance criteria, operators rely on the Component Repair and Overhaul Manual. The AD does not amend or override those limits; it instructs removal where limits are exceeded ("Requirement").

• Right to have work performed by qualified maintenance organizations: The AD does not specify the qualifications required to perform the inspections and repairs, but the use of ASB instructions and dynamic balancing implies work should be performed by appropriately approved maintenance personnel or organisations with the necessary equipment.

• Right to rely on the stated compliance window: The AD sets the compliance deadline, giving operators a clear timeframe in which to plan and perform actions. It also notes that if actions were already accomplished prior to the effective date, they are compliant ("Compliance").

What the AD does not state

• The AD text does not specify penalties, fees, approval requirements for minor deviations, or a process for requesting alternative methods of compliance in the text provided. The instrument references FAA ADs and ASBs for technical content but does not include a procedure in the published text for seeking an alternative compliance method.

• The AD does not list the specific adhesive bond void numerical thresholds; it defers that technical limit to the Component Repair and Overhaul Manual.

In practical terms the AD imposes clear, time-limited physical inspection, repair and recordation duties on operators and maintenance organisations tied to specific manufacturer and FAA materials.

The AD text supplied does not set out any express penalty provisions, fines, or criminal sanctions. The instrument states the mandatory actions, the applicable aircraft and component identifiers, the timeframe for compliance, and the effective date ("Requirement", "Applicability", "Compliance"). It is silent in the published text on the specific enforcement mechanisms, administrative penalties, or the process for demonstrating compliance beyond performing the required inspections and corrective actions.

From the text itself: the AD becomes effective on 20 December 2007 ("Compliance"), and it is issued by a CASA delegate (David Villiers) dated 7 November 2007. The document therefore represents a regulatory direction. However, the supplied source does not specify the procedural or legal steps CASA will take to enforce non-compliance, nor does it reference infringement or penalty sections under aviation law within the text. The document does not include an Alternative Methods of Compliance (AMOC) procedure, nor does it include a provision for seeking exemptions, waivers, or extensions, at least not within the material provided.

Consequences that can be inferred only to the extent they are recorded in the source are limited to non-compliance with the AD itself. The AD prescribes an effective date and a compliance horizon (100 hours time in service after 20 December 2007). The source explicitly ties compliance action to specified ASBs and the Component Repair and Overhaul Manual. Operators are thereby required to follow those instructions. The AD does not enumerate what constitutes acceptable evidence of compliance, but the re-identification requirement (adding "FM") and the need to follow ASB procedures create documentary traces that an operator can present to show actions were taken.

Users should not assume additional penalty regimes from this document alone; the source does not state them. If a reader needs to know the specific statutory enforcement or penalty consequences for failing to comply with a CASA AD, they must consult the relevant aviation safety legislation, CASA enforcement policies, or regulatory guidance outside the provided text. The AD itself provides neither punishment details nor an enforcement process in the material supplied.

The AD explicitly interacts with two categories of external instruments: manufacturer Alert Service Bulletins and a related FAA Airworthiness Directive. The AD requires operators to carry out the actions in accordance with Bell Helicopter Textron Inc. ASB 205-00-80 Revision D or ASB 205B-00-34 Revision D, or later FAA approved revisions, as applicable, for the detailed inspection locations, shear pin installation procedures, and aft tip closure rivet installation and dynamic balancing instructions ("Requirement"). This means that the AD delegates the technical method of compliance to manufacturer documentation, but it requires that such documentation be the FAA-approved revision or a later FAA-approved revision.

The AD also notes FAA AD 2007-22-02 Amdt 39-15238 as a referenced instrument ("Requirement", "Note"). Amendment 1 is said to be issued in response to a new FAA AD which expands the applicability to include other part and serial-numbered blades, and which clarifies the requirement to re-identify the modified blade by adding "FM" and requires dynamically balancing the tail rotor ("Background"). Thus the CASA AD operates in parallel with FAA rulemaking and aligns Australia’s regulatory action with the FAA’s findings and technical directions.

The AD also defers to the Component Repair and Overhaul Manual for the acceptance criteria of adhesive bond voids ("Requirement"). That manual will be part of the continuing airworthiness documentation for the component and is the defined source for limits determining whether removal is required. Therefore compliance requires cross-referencing and applying limits contained in that manual, whose authority derives from maintenance and overhaul standards rather than from this AD text.

The supplied AD does not reference Australian statutes, regulations, or specific CASA enforcement provisions, nor does it provide an AMOC process or cite Civil Aviation Safety Regulations. The AD is therefore not self-contained on enforcement or alternative compliance mechanisms; it simply prescribes a mandatory action tied to manufacturer and FAA documents. Practitioners wishing to understand the AD’s interaction with statutory enforcement powers, certification, or approval processes will need to consult the relevant Australian aviation safety legislation and CASA policy instruments beyond this AD text.

Because the AD requires re-identification of modified parts by adding "FM", it affects component identification records and therefore interacts with record-keeping obligations under airworthiness regulations. The AD’s requirements for inspection, removal, repair and balancing will also intersect with regulatory requirements for approved maintenance organisations and certified personnel to perform such work; the AD does not specify personnel qualifications, but adherence to the ASB and balancing procedures presumes qualified maintenance.

In summary, within the supplied text the AD interacts with and depends upon: (1) Bell Helicopter ASBs (specified revisions or later FAA-approved revisions), (2) the FAA AD 2007-22-02 Amdt 39-15238 (as a related foreign regulatory action and technical reference), and (3) the Component Repair and Overhaul Manual (for adhesive bond void limits). It does not, in the supplied text, articulate interactions with domestic statute or CASA enforcement mechanisms; those relationships must be inferred and confirmed against the wider regulatory framework outside this AD.

The document presented is Amendment 1 to AD/BELL 205/70, issued as AD/BELL 205/70 Amdt 1 and identified as 13/2007. The AD is dated 7 November 2007 (signed by David Villiers, Delegate of the Civil Aviation Safety Authority) and becomes effective on 20 December 2007 ("This Amendment becomes effective on 20 December 2007", signature block). The AD text under "Background" states that Amendment 1 is issued in response to a new FAA AD which expands the applicability to include other part and serial-numbered blades, and that Amendment 1 clarifies the requirement to re-identify the modified blade by adding "FM" after the part number and that it requires dynamically balancing the tail rotor ("Background").

The supplied material suggests a predecessor AD existed (AD/BELL 205/70) to which this document is an amendment, but the text of the prior AD is not included. The background paragraph is the source’s explicit statement of what Amendment 1 changes relative to that prior instrument: expanded applicability and clarified procedural requirements (re-identification and dynamic balancing). The AD also incorporates by reference Bell ASBs Revision D (205-00-80 Revision D or 205B-00-34 Revision D) and allows use of later FAA-approved revisions, hence future ASB revisions could be used if FAA-approved ("Requirement").

The document contains repeating header lines and table entries that re-state the AD identifier (AD/BELL 205/70 Amdt 1), the subject (Tail Rotor Blade Fwd Tip Weight Retention Block and Aft Tip Closure), and the instrument number/date (13/2007). Those repeated elements are administrative formatting rather than substantive changes.

No later amendments, revocations, or superseding CASA actions are included in the supplied text. The AD refers to FAA AD 2007-22-02 Amdt 39-15238 as the FAA action prompting Amendment 1 ("Note"). The signature date and effective date are explicit: signed 7 November 2007, effective 20 December 2007.

The AD also includes a procedural allowance: compliance may be met using ASB Revision D or "later FAA approved revisions, as applicable." That phrase is an open-ended mechanism permitting later FAA-approved ASB revisions to be used for compliance without needing immediate further amendment to the CASA AD.

Practitioners needing a full amendment history beyond what is printed here (for example the original AD/BELL 205/70 text, any superseding ADs, or subsequent CASA amendments) must consult CASA records or the official AD database; the supplied instrument gives only Amendment 1 and its relationship to a contemporaneous FAA AD.

The text supplied contains no litigation history. It does not reference any court proceedings, administrative appeals, or legal disputes arising from the AD, nor does it mention challenges, stays, injunctions, or precedent decisions. The background section recounts safety incidents reported by the FAA (five occurrences of missing forward tip weight retention blocks or aft tip closures that resulted in minor to substantial damage and could lead to loss of a tail rotor blade and control) and states that Amendment 1 was issued in response to the FAA AD which expanded applicability and clarified requirements ("Background"). Those items are operational and regulatory facts, not litigation.

Because the supplied AD does not record any disputes, and does not cite appeals processes, practitioners seeking litigation or dispute history must look beyond this document to CASA enforcement records, administrative tribunal decisions, or court archives. The AD’s silence on litigation in the source document should not be taken as evidence that none exists; it simply means none is documented here.

If a practitioner needs to assess precedent for challenges to ADs generally or to this AD in particular, they will need to conduct external legal research in Australian administrative law and aviation law databases. The supplied text does not supply details that would permit a grounded discussion of cases, remedies, or appeals related to this AD.

• Applicability nuance: The serial-number exclusion language is precise and potentially confusing. The AD applies to blades with part numbers 212-010-750-009 through -129, but excludes "serial numbers with a prefix of 'A' or 'AFS' and the number 11926, 13351, 13367, 13393, 13400, 13402, 13515, 13540, 13568, 13595 through 13602, 13619, and subsequent assigned numbers, installed" ("Applicability"). Operators must carefully check part-number and serial-number formats against their records, noting prefix characters and specific listed numbers and any subsequently assigned numbers. Mis-reading this list could lead to unnecessary inspections or missed compliance obligations.

• Reliance on other documents for technical limits: The AD requires removal of blades with adhesive bond voids "in excess of that allowed by the Component Repair and Overhaul Manual limitations" ("Requirement"). The AD does not state the numeric void tolerance. Operators must consult the Component Repair and Overhaul Manual; failure to do so risks inconsistent decision-making about when to remove a blade.

• Delegation to ASBs and FAA approval: The AD mandates following ASB 205-00-80 Revision D or 205B-00-34 Revision D, or later FAA approved revisions. If an operator uses a later ASB revision that is not FAA approved, the AD’s language does not confirm that action as compliant. Practitioners should verify FAA approval status of any ASB revision they plan to use.

• Re-identification requirement: The AD requires re-identifying modified blades by adding "FM" to the part number ("Requirement"). This is a physical marking and a record-keeping action. Omitting or incorrectly applying the "FM" marking can cause inspection confusion down the line and may complicate later maintenance or resale. Clarify how the "FM" is to be recorded in component and aircraft records.

• Dynamic balance after modification: The AD requires dynamic balancing of the tail rotor hub assembly after installing aft tip closure rivets and re-identifying the blade ("Requirement"). Dynamic balancing requires appropriate equipment and skill. Some operators may not have on-site capability and may need to subcontract, leading to scheduling and cost implications.

• Figure 1 dependence: The four countersink screw locations are "depicted on Figure 1 of Bell Helicopter Textron Inc. Alert Service Bulletin (ASB) 205-00-80 Revision D or 205B-00-34 Revision D" ("Requirement"). The AD text does not reproduce Figure 1. Operators must obtain the ASB to know exactly where to inspect.

• Potential for aircraft downtime: If adhesive bond voids exceed overhaul manual limits and blades must be removed, this may require replacement blades or depot-level repair, which can ground an aircraft for longer than the 100-hour compliance window permits if logistic support is not pre-arranged.

• Record evidence: The AD does not specify the exact form of compliance documentation. The re-identification ("FM") creates physical evidence, and following ASB procedures will produce paperwork, but operators should establish and retain clear maintenance records that show the inspections, findings, and any parts changed.

• Timing edge cases: The AD applies "within 100 hours time in service after 20 December 2007, unless already accomplished" ("Compliance"). Operators must calculate time-in-service accurately. Aircraft close to their next scheduled flights must plan inspections to avoid inadvertently exceeding the deadline.

• No AMOC or variance text included: The published excerpt contains no procedure for requesting an alternate method of compliance (AMOC) or extension. If an operator contemplates an alternative approach to inspection or repair, the AD text does not provide the administrative route to secure approval in this document; external CASA guidance would need to be consulted.

• Multiple document cross-references: Complying requires consulting at least three documents: the AD text, the relevant ASB Revision D (or later FAA-approved revision), and the Component Repair and Overhaul Manual. Failure to reconcile differences among those documents may cause non-compliance.

• International interplay: Because the AD is aligned with an FAA AD and requires FAA-approved ASB revisions, operators with international maintenance providers or parts sourced from outside Australia should ensure those revisions and approvals are current and accepted under Australian regulatory practice.

Follow these steps, all drawn from the AD text and its referenced materials:

1. Confirm applicability

   • Check helicopter model and the installed tail rotor blade part number. The AD applies to Model 205A, 205A-1 and 205B helicopters fitted with tail rotor blade part numbers 212-010-750-009 through -129 ("Applicability").
   • Confirm the blade serial number is not one of the excluded items: serial numbers with a prefix "A" or "AFS" and the numbers 11926, 13351, 13367, 13393, 13400, 13402, 13515, 13540, 13568, 13595 through 13602, 13619, and subsequent assigned numbers ("Applicability"). If the blade falls into the excluded list, the AD’s requirements do not apply.

2. Obtain required reference documents

   • Acquire Bell Helicopter Textron Inc. Alert Service Bulletin 205-00-80 Revision D or 205B-00-34 Revision D, or any later FAA approved revision as applicable. The ASB contains Figure 1 (showing the four countersink screw locations) and the Accomplishment Instructions for Part A (Shear Pin Installation) and Part B (Aft Tip Closure Rivet Installation and dynamic balancing) ("Requirement").
   • Have the Component Repair and Overhaul Manual available to determine the allowable adhesive bond void limits that govern blade removal ("Requirement").

3. Schedule work within the compliance window

   • The AD requires completion within 100 hours time in service after 20 December 2007 unless already done ("Compliance"). Plan inspections and any necessary repairs within that timeframe.

4. Inspect adhesive bonds

   • Inspect the forward tip weight retention block and aft tip closure for adhesive bond voids per the Component Repair and Overhaul Manual and the ASB instructions where applicable ("Requirement").
   • If a void exceeds the Component Repair and Overhaul Manual’s limit, remove the tail rotor blade as directed by the manual and the ASB ("Requirement").

5. Inspect countersink screws

   • Using Figure 1 of the ASB, locate the four countersink screws attaching the forward tip weight retention block. Inspect each to determine whether the screw head is flush with the abrasion strip surface ("Requirement").
   • If any screw is set below surface or covered with filler, proceed to install shear pins.

6. Install shear pins when required

   • Where screws are recessed or covered with filler, install shear pins in accordance with the Accomplishment Instructions, Part A, Shear Pin Installation paragraphs of the applicable ASB revision ("Requirement").
   • Ensure the installation follows the ASB steps exactly and document the work.

7. Install aft tip closure rivets and re-identify

   • Install aft tip closure rivets in accordance with the Accomplishment Instructions, Part B, Aft Tip Closure Rivet Installation paragraphs of the applicable ASB revision ("Requirement").
   • Once the aft tip closure rivets are installed and the work is complete, re-identify the modified blade by adding the letters "FM" after the part number on the blade and in the component records as directed ("Requirement").

8. Dynamically balance the tail rotor hub assembly

   • After modifications, dynamically balance the tail rotor hub assembly in accordance with the ASB Part B Accomplishment Instructions ("Requirement").
   • Ensure balancing is performed using the appropriate tooling and documented balancing procedures. Retain balancing reports.

9. Record and retain evidence

   • Record the inspections, findings, any removals, parts installed (including rivet and shear-pin details), the re-identification marking ("FM"), and dynamic balancing outcomes in the aircraft and component maintenance records. Although the AD does not prescribe a particular record format, the physical marking and ASB-based procedure produce documentary evidence for compliance.

10. Verify FAA approval for any later ASB revisions

• If using an ASB revision later than Revision D, ensure it is FAA approved, as the AD allows "later FAA approved revisions" ("Requirement"). Document the revision used and its FAA approval.

11. If in doubt, consult CASA and Bell

• The AD text does not provide an AMOC procedure or instructions for variance within the supplied text. If an operator needs an alternative method or extension, they should consult CASA and the manufacturer for the formal administrative route outside the provided AD text.

12. Operational planning

• Anticipate possible blade removal and replacement needs that could extend aircraft downtime beyond routine maintenance windows. Plan parts procurement and qualified maintenance support in advance.

By following the AD’s steps and the referenced ASB and Component Repair and Overhaul Manual, operators will fulfil the specific obligations spelled out in the instrument: inspect for adhesive voids, inspect and remedy countersink screw issues via shear pins where necessary, install aft tip closure rivets, re-identify modified blades with "FM", and dynamically balance the tail rotor hub assembly, all within the stated compliance window.