AD/BEECH 65/22 Amdt 4 - Wing Spar and Lower Attachment Fittings

The AD is structured around a fault-correction and recurring-inspection regulatory model. The key concepts are:

• Unsafe condition identification and mandatory corrective action: The AD identifies fatigue cracking in the “bathtub” fittings of Beechcraft Queen Air/65/70/80/88 main spar lower attachments as the unsafe condition. The corrective actions are removal of bolts, paint stripping of the bathtub area, and NDT inspection; the remedial action on detection of fatigue is mandatory replacement of the complete outer wing main spar lower cap assembly before further flight.

• Prescriptive inspection methodology but limited flexibility: The primary inspection method mandated is fluorescent liquid penetrant inspection in alignment with specific SIRM chapters and chart indices. An alternative is explicitly permitted, an eddy current pencil-probe procedure found in the SIRM Chapter 20-00-00. The AD thereby prescribes a specific technical standard (the manufacturer SIRM P/N 98-39006B3, revised 28 May 1999) rather than leaving inspection technique to operator discretion.

• Time-based, component-hours triggers: Compliance is driven by component hours’ time in service. The Inspection Schedule in the AD lists initial inspection thresholds (column (3)) and repeat inspection intervals (column (4)) by model and serial-range designator as used in the Type Certificate Data Sheet. The AD requires initial inspection prior to exceeding the listed component hours, and recurring inspections at or below the repeat interval. The eddy current alternative allows doubling of the repetitive interval, changing the inspection cadence in exchange for a different technique.

• Hierarchy and cross-reference: The AD refers to the manufacturer SIRM for procedural details and to a related AD (AD/BEECH 65/57) for bolt and nut inspection. It instructs operators to disregard an SIRM “Warning” about not removing paint when inspecting the bathtub portion, but replaces that SIRM warning with its own note to apply protective treatment (for corrosion prevention) between inspections.

• Delegated regulatory instrument: CASA issues the AD via a delegate under CAR 1998 subregulation 39.1(1). The AD revokes a previous AD amendment and substitutes a new set of requirements, showing the instrument operates as an iterative, regulatory-enforcement mechanism responding to service history and manufacturer guidance.

• Safety-critical grounding trigger: The AD contains an absolute grounding trigger , if a fitting fatigue crack is found, the aircraft cannot be flown further until the complete outer wing main spar lower cap assembly is replaced. That produces immediate operational and cost consequences for an operator where cracks are found.

These concepts combine a technical NDT regime with strict timing and enumerated model applicability, and they position the manufacturer SIRM as the operative technical reference. The AD balances prescriptiveness with a single explicit alternative (eddy current), with a compensatory relaxation of inspection frequency if that alternative is adopted.

The AD explicitly applies to “All models” of the Beechcraft 65 and 70 (Queen Air) series aeroplanes as stated in the Applicability line. Practically, the following actors are affected:

• Aircraft owners and operators of the listed Beechcraft models. They are the legal addressees of the AD because the directive requires actions to be taken “in relation to the aircraft” in specified circumstances and at specified times. Owners and operators carry the immediate cost of inspections, consumables, technician labour, paint stripping, and any mandated replacements.

• Maintenance organisations and certificated engineers. The AD requires removal of attachment bolts and NDT inspections in accordance with the SIRM. That work will typically be performed by maintenance organisations authorised to work on these airframes and by NDT practitioners skilled in penetrant and eddy current inspections. The AD’s procedural notes (for example, brush application of penetrant to bolt counterbores) impose specific technical steps that affect how maintenance work is executed.

• Suppliers of spare parts and assemblies. If a fatigue crack is found, the AD requires replacement of the complete outer wing main spar lower cap assembly before further flight. This creates demand for those replacement assemblies and any associated fasteners and corrosion-protection materials.

• Regulators and CASA delegates. The AD is issued under CASA’s delegated power and requires operators to contact the Authority for models not listed in the Schedule. CASA will be the decision-maker where model coverage or alternative compliance approaches are in question.

• Insurers and lessors. The AD imposes mandatory inspections and replacement obligations that will affect aircraft availability and potentially influence underwriting and lease obligations. While the AD does not itself address insurance or leasing, the practical effect is that operators must comply to maintain airworthiness.

• Airworthiness auditors, safety investigators and compliance professionals. The AD becomes part of the airworthiness compliance landscape that auditors or investigators will check against maintenance logs and aircraft status.

The AD also affects the distribution of costs and timing: there is a concentration of decision authority with CASA and the SIRM. Costs are concentrated on aircraft operators and owners, who must carry out the inspections and fund replacement parts and labour. Benefits , the reduction of the risk of in-flight fatigue failure associated with cracked fittings , are diffuse across operators, passengers, and the public. The AD also creates a compliance market: NDT providers, painters, and part suppliers will be engaged to satisfy the AD.

Duties imposed by the AD are concrete and prescriptive. The AD sets out operator obligations and limited procedural choices:

• Duty to perform paint removal and bolt removal prior to inspection. Requirement 1 mandates removing the wing main spar lower attachment bolts “in accordance with the manufacturer’s instructions” and stripping all paint from the bathtub portion of the four outer wing to centre section main spar lower attachment fittings. The SIRM is explicitly referenced as the technical standard for inspection procedures (Requirement 2).

• Duty to inspect using specified methods. Requirement 2 mandates a fluorescent liquid penetrant inspection in accordance with SIRM P/N 98-39006B3, Chapter 57-11-00 (models 65, 70, 80) and Chapter 57-12-00 (model 88), Chart 201, Index Nos. 1 and 10. As an alternative, the eddy current pencil-probe procedure in Chapter 20-00-00 of the SIRM may be used. Where eddy current is used the repetitive inspection interval may be doubled. The AD therefore grants a narrow right to choose the eddy current alternative, but couples that right to a modification of the repetitive interval.

• Duty to replace cracked fittings before further flight. The AD specifies that “if a fitting fatigue crack is found, the complete outer wing main spar lower cap assembly must be replaced in before further flight.” This is a non-derogable remedial requirement.

• Duty to follow the Inspection Schedule. Compliance is required “prior to exceeding the component hours’ time in service listed in column (3) ... and thereafter at intervals not to exceed the component hours’ time in service listed in column (4).” For models not listed in the Schedule, a duty to contact the Authority is imposed.

• Duty to follow specified preparation and inspection practices. Notes 1 to 5 provide operational instructions: disregard the SIRM “Warning” about not removing paint for the bathtub area (Note 1), apply protective treatment such as a standard zinc chromate primer to prevent corrosion between inspections, use solvent paint removers wherever possible and avoid mechanical or abrasive means of paint removal (Note 2), apply penetrant into the counterbore radius using a fine artist’s paint brush to simplify removal and minimise false indications (Note 3), and do not attempt to polish out suspect indications , seek specialist NDT advice where needed (Note 4). Inspection of bolts and nuts is detailed in AD/BEECH 65/57 (Note 5).

Rights and procedural flexibilities are limited and technical:

• Right to use an alternative approved technique within the SIRM. The AD allows the eddy current pencil probe as an alternative to penetrant, but links that choice to a compensating change in repeat interval and requires the eddy current procedure to be performed per the SIRM Chapter 20-00-00.

• Right to consult the Authority for models not listed. Where a model is not in the Schedule, operators have the procedural right and duty to contact CASA.

What the AD does not do in the text: it does not set out penalties, appeal routes, or administrative processes for relief or alternative methods of compliance beyond the single eddy current alternative. It also does not in the body of the AD prescribe recordkeeping steps, although recordkeeping would be implicated in proof of compliance. The AD vests the CASA delegate with authority to revoke earlier ADs and to issue amended ADs; here, the delegate revoked Amdt 3 and issued Amdt 4.

The AD is issued under subregulation 39.1(1) of the Civil Aviation Regulations 1998, with the cover statement explaining that the delegate “revokes Airworthiness Directive (AD) AD/BEECH 65/22 Amdt 3 and issues the following AD under subregulation 39.1(1) of CAR 1998.” The instrument therefore operates as a regulatory requirement in the framework of the CAR 1998. However, the AD text itself does not specify particular penalties or sanctions for non-compliance.

Enforcement mechanics implicit in the document are as follows:

• Mandatory compliance timing. The AD imposes timing obligations: inspections must be completed prior to exceeding the component hours listed in the initial threshold column and repeated at intervals not exceeding the specified hours in the repeat column. The document therefore creates discrete, dated obligations tied to component hours. Compliance is binary: either the inspection/replacement has been completed in accordance with the AD, or it has not.

• Grounding on detection of fatigue cracks. The AD creates a direct operational enforcement-like mechanism in that a detected fatigue crack triggers an immediate no-fly requirement until the complete outer wing main spar lower cap assembly is replaced. That effectively grounds the aircraft until a prescribed remedial action is taken.

• CASA oversight and amendment power. The AD was issued by a CASA delegate and it instructs operators to contact the Authority for models not listed. CASA has authority to issue, amend and revoke ADs. While the AD does not spell out the enforcement tools, issuance under CAR 1998 implies that CASA has statutory enforcement mechanisms available under those Regulations.

Absent from the AD are explicit descriptions of penalties, infringement notices, or the process for seeking an alternative method of compliance or relief. The AD references other documents for technical compliance (SIRM and related ADs) but not for sanctions. For an operator, the practical enforcement risk is operational rather than criminal: failure to comply risks having an aircraft not legally maintained as airworthy, and risks regulatory action under CAR 1998. The AD itself should be read alongside CAR 1998 and CASA enforcement policy to determine precise sanctioning routes and possible appeal or variation processes; the AD text does not reproduce those provisions.

The AD is linked directly to the Civil Aviation Regulations 1998 through subregulation 39.1(1), which is cited as the statutory power under which the AD is issued. The AD therefore sits within the regulatory framework of the CAR 1998 and the broader airworthiness regulatory regime administered by CASA.

The AD cross-references and interacts with several technical and regulatory instruments:

• Beechcraft Structural Inspection and Repair Manual (SIRM) P/N 98-39006B3 (revised 28 May 1999). The AD makes the SIRM the operative technical standard for the inspections, specifying Chapters 57-11-00 and 57-12-00 for fluorescent penetrant inspection, and Chapter 20-00-00 for the eddy current alternative. By doing so, the AD imports manufacturer technical content into the mandatory regulatory requirement. The AD also instructs operators to disregard a specific SIRM “Warning” about not removing paint with respect to the bathtub , replacing that SIRM warning with AD instructions on paint removal and corrosion protection.

• AD/BEECH 65/57. Note 5 refers operators to the current issue of AD/BEECH 65/57 for inspection of bolts and nuts. That creates an interaction between ADs: compliance with one AD may require reference to and compliance with another AD.

• Type Certificate Data Sheet model designations. The Inspection Schedule uses the model designations used in the Type Certificate Data Sheet. The AD explains that the SIRM’s model designations are the manufacturer’s popular or marketing designations. This creates a cross-reference step: operators must map their aircraft serial numbers and model identifiers to the Schedule entries and the Type Certificate Data Sheet designations.

• Prior ADs and amendments. The AD revokes a prior amendment and consolidates prior ADs. Note 6 confirms that inspections carried out under earlier issues of this or related ADs satisfy the initial inspection requirements of this amendment. That makes the AD interact temporally with prior regulatory instruments, providing continuity for earlier-completed inspections.

The AD does not reproduce other CAR 1998 provisions, enforcement mechanisms, or administrative appeal pathways, but it implies that these exist in the overarching regulatory framework. The AD’s requirement that “for models not listed in the Schedule, the Authority must be contacted” embeds a procedural interaction between operators and CASA where model coverage is unclear, signalling CASA’s discretionary role in resolving gaps.

Finally, the AD modifies the SIRM’s instructions by expressly disapplying one SIRM warning and by adding protective treatment advice. Therefore, operators must harmonise manufacturer guidance with the AD; when the AD contradicts a SIRM warning, the AD controls for regulatory compliance.

AD/BEECH 65/22 has an explicit amendment history documented in the background section of the text. The timeline and key changes recorded in the instrument are:

• Original issue: The AD’s original issue became effective on 30 June 1980. At that time, “a number of similar ADs were issued to cover the different Queen Air models.” The original inspection requirement was grounded on the “known fatigue history of the ‘bathtub’ fittings.”

• Amendment 2: Became effective on 22 March 1990. Amendment 2 consolidated the Beech 65 and 70 series Airworthiness Directives without changing the substantive technical requirements.

• Amendment 3: Became effective on 12 January 1992. Amendment 3 consolidated AD/BEECH 65/22, 23, 24, 25 and 26 and aligned the requirements with the Beech SIRM “to the extent possible.” It also changed intervals: the repeat inspection interval was reduced for Model 65-B80 and extended for most other models. These interval adjustments were based on “a review of the fitting stress levels and service experience.”

• Amendment 4 (this instrument): The AD text explains that this Amendment results from a review of the AD which confirmed the need for the requirement and the appropriateness of the inspection intervals. Practical changes in Amdt 4 include updating the SIRM reference to the SIRM P/N 98-39006B3 as revised 28 May 1999; clarifying the requirement because two sections of the SIRM (Index Nos. 1 and 10) referred to the same fluorescent penetrant inspection but at different compliance times; correcting some minor errors; and permitting the use of eddy current inspection of the bathtub as an optional alternative to fluorescent dye penetrant, with a corresponding increase in the repetitive inspection interval.

Administrative dates associated with Amdt 4 are: delegate signature dated 20 September 2000; the Amendment becomes effective on 2 November 2000; it was notified in the Commonwealth of Australia Gazette on 4 October 2000. Note 6 clarifies that inspections carried out in accordance with previous issues of this or related ADs satisfy the initial inspection requirements of Amdt 4, providing continuity for operators who already complied with earlier AD iterations.

The amendment history shows an iterative calibration between manufacturer guidance, service experience, and regulatory prescription. The changes over time include consolidation of multiple model-specific ADs into a single directive, alignment with manufacturer SIRM content, differentiation of repeat intervals by model based on stress analysis and service data, and the technical accommodation of an eddy current alternative inspection methodology with compensatory interval adjustments.

The AD text does not include any litigation history, case names, or references to court decisions. There are no judicial or administrative appeals recited in the instrument. The background, amendment notes and scheduling material focus exclusively on technical, procedural and administrative changes across iterations of the AD.

Because the AD is a regulatory instrument issued under subregulation 39.1(1) of CAR 1998, any litigation or enforcement proceedings arising from it would be recorded elsewhere: in CASA enforcement records, administrative appeal records, or judicial decisions interpreting CAR 1998 and related airworthiness requirements. None of those materials are reproduced in, or referenced by, this AD.

Practically, the absence of litigation history in the AD means that the AD document itself is the primary source of the technical and compliance obligations. Parties seeking to understand any past enforcement actions, disputes over interpretation, or precedential rulings would need to consult CASA records, tribunal or court decisions, or legal databases that are outside the content of this AD. The AD does cross-reference other ADs and the SIRM for technical detail, but it does not reference any adjudicated resolution of compliance disputes.

Readers should therefore treat the document as a technical regulatory instrument rather than a statement of legal adjudication. Any question about the legal enforceability, penalties, appeals or disputed interpretations must be addressed by reference to statutory CAR 1998 provisions and to records external to this AD; none of those external materials are included in the AD text.

The AD contains several practical traps and specific procedural nuances that can materially affect compliance, inspection quality, aircraft availability and corrosion risk:

• Paint removal instruction conflicts with SIRM Warning: The AD explicitly instructs operators to “strip all paint from the ‘bath tub’ portion” of the fittings but also instructs to disregard the SIRM Chapter 20-00-00 “Warning” which advises against paint removal. Note 1 replaces that SIRM warning by prescribing the application of protective treatment, such as a standard zinc chromate primer, between inspections to prevent corrosion. Operators must therefore follow the AD instruction even though it contradicts a SIRM warning.

• Method of paint removal: Note 2 directs the use of solvent removers “wherever possible” and states that if other paint strippers are unavoidable, complete removal of residue must be ensured before inspection. It also states mechanical or abrasive means of paint removal must be avoided. Operators who use mechanical removal risk introducing surface damage that can obscure or induce defects. Ensuring residue-free surfaces may require additional cleaning steps and verification.

• Penetrant technique detail: Note 3 recommends applying penetrant to the counterbore radius using a fine artist’s paint brush to minimise false indications and to get coverage into the fillet radius and at least 5 mm into the cylindrical portion of the counterbore, particularly on the side adjacent to the “bottom of the bathtub.” This is a specific technique detail; skipping it increases the risk of false negatives or positives. NDT practitioners unfamiliar with the geometry may under-cover critical areas.

• False indication handling: Note 4 warns that polishing suspect indications has previously obscured large cracks. The AD instructs operators to avoid polishing and to seek specialist NDT advice where suspect indications need confirmation. Polishing to “clear” an apparent defect risks destroying evidence of a significant crack and may lead to continued operation of an unsafe aircraft.

• Bolt and nut inspection linkage: Note 5 points to AD/BEECH 65/57 for inspection of the bolts and nuts. Operators who focus only on the bathtub fittings risk missing related bolt/nut inspection requirements captured in that separate AD.

• Repetitive interval doubling if eddy current used: The AD permits an eddy current alternative but explicitly states the repetitive inspection interval in column (4) “may be doubled” when that procedure is used. Adopting the eddy current method therefore changes inspection cadence. Operators must ensure their maintenance planning accounts for the altered timeline.

• Model and serial-number mapping: The Inspection Schedule uses model designators and serial ranges (for example LC-1 to -180, LD-151 to -244) that correspond to Type Certificate Data Sheet designations. Mis-mapping an aircraft to the wrong Schedule row could cause incorrect initial thresholds or repeat intervals. The AD also requires contacting the Authority for models not listed, creating a procedural step where gaps exist.

• Immediate replacement requirement: If a fitting fatigue crack is found, the AD mandates replacement of the complete outer wing main spar lower cap assembly before further flight. This can lead to immediate aircraft grounding and significant operational disruption, supply dependency for assemblies, and potentially long ferry or downtime periods.

• Record continuity: Note 6 provides relief by acknowledging that earlier inspections done in accordance with prior ADs satisfy the initial inspection requirement. However, operators must be able to demonstrate that earlier inspections were performed to prior AD standards. Incomplete records could lead to uncertainty over whether the initial threshold is already satisfied or overdue.

• No penalties spelled out in AD text: The AD itself does not list fines, infringement procedures or appeal mechanisms; those reside in the CAR framework. Operators should not assume absence of penalties based on the AD text alone.

These “gotchas” emphasise that compliance is technical and procedural: it requires attention to SIRM cross-references, careful NDT practice, correct paint removal and protection, mapping to correct model/serial ranges, and readiness to replace major structural assemblies if cracks are found.

Compliance with AD/BEECH 65/22 Amdt 4 requires a programme of actions tied to component hours and the SIRM procedures. Below is a stepwise compliance checklist that tracks the AD text and Notes. Each step is grounded in the AD’s provisions:

1. Confirm applicability and model/serial mapping. The AD lists model designators and serial ranges in its Inspection Schedule. Identify your aircraft’s model designator and serial number and map it to the Schedule row (column (1) Model; column (2) Serial Numbers). If your model is not listed in the Schedule, contact the Authority as required by the AD.

2. Determine initial inspection threshold timing. Using the Schedule, identify the Initial Inspection Threshold in hours (column (3)). Perform the initial inspection prior to exceeding the component hours specified.

3. Plan for removal of wing main spar lower attachment bolts. Requirement 1 mandates removal of the wing main spar lower attachment bolts “in accordance with the manufacturer’s instructions.” Obtain and follow the manufacturer’s instructions for bolt removal to avoid damaging fittings or alignment features.

4. Strip paint from the bathtub portion. Requirement 1 requires stripping all paint from the bathtub portion of the four outer wing to centre section main spar lower attachment fittings. Follow Note 2: use solvent removers wherever possible; if other paint strippers are used ensure complete removal of residue before inspection; avoid mechanical or abrasive paint removal.

5. Apply protective treatment between inspections. Note 1 instructs operators to apply some form of protective treatment, such as a standard zinc chromate primer, to surfaces from which paint has been removed to prevent corrosion between inspections. Plan to have suitable primer materials and curing times available, and document when protective treatment is applied.

6. Perform the required NDT. Requirement 2 prescribes a fluorescent liquid penetrant inspection in accordance with SIRM P/N 98-39006B3 (rev 28 May 1999), Chapter 57-11-00 (models 65, 70, 80) and Chapter 57-12-00 (model 88), Chart 201, Index Nos. 1 and 10. Alternatively, the eddy current pencil-probe procedure in SIRM Chapter 20-00-00 may be used. If using penetrant, follow Note 3 regarding applying penetrant into the counterbore radius with a fine artist’s paint brush to ensure full coverage of fillet radii and at least 5 mm into the cylindrical portion adjacent to the bottom of the bathtub.

7. Adhere to inspection intervals. After the initial inspection, carry out repeat inspections at intervals not to exceed the hours in column (4) of the Schedule. If the eddy current procedure is used, the repetitive inspection interval in column (4) may be doubled, per the AD.

8. Respond to suspect indications properly. Note 4 instructs operators not to attempt to polish out suspect indications and recommends seeking specialist NDT advice where suspect indications need confirmation. Arrange access to skilled NDT specialists to review any ambiguous findings.

9. Replace cracked fittings before further flight. If a fitting fatigue crack is found during any inspection, replace the complete outer wing main spar lower cap assembly before further flight, as stated in Requirement 2.

10. Coordinate bolt and nut inspections. See Note 5 and refer to the current issue of AD/BEECH 65/57 for inspection requirements for bolts and nuts associated with these attachments. Incorporate those inspections into the maintenance workflow.

11. Record evidence of compliance. Although the AD does not in its text define recordkeeping requirements, maintain contemporaneous records showing compliance with the AD’s steps (dates, technician names, method used, SIRM references, results, parts replaced). Note 6 allows that prior inspections carried out in accordance with previous issues of this or related ADs satisfy the initial inspection requirement; be prepared to demonstrate that earlier inspections were performed per prior ADs if applying Note 6.

12. Contact CASA where required. For models not listed, contact the Authority as the AD requires. Also contact CASA for clarifications if the SIRM references or serial ranges create ambiguity.

13. Plan for operational disruption. Because a cracked fitting requires replacement of the entire outer wing main spar lower cap assembly before further flight, prepare contingency plans for aircraft grounding, parts procurement and maintenance scheduling.

14. Maintain alignment with the SIRM revision named. The AD specifies SIRM P/N 98-39006B3 as revised 28 May 1999. Ensure the SIRM revision cited is used for inspection procedures; if a later SIRM revision is used, document the authority under which that change is accepted, noting the AD’s explicit reference.

Following these steps will align day-to-day maintenance operations with the prescriptive content of the AD. The AD provides limited procedural flexibility (adel alternative inspection method and contact point for unlisted models) but otherwise mandates specific actions and timings that must be satisfied prior to exceeding component hours and for ongoing repeated inspections.