AD/BEECH 65/61 Amdt 5 - Nose Gear Lower Shock Absorber Assembly

The Directive is structured around a narrow set of technical concepts tied to a single component and a single MSB. The core concepts are:

• Applicability by model and serial number: The AD applies to specific airframes. Models and serial number ranges are listed in the Applicability block (for example Model A65 and A65‑8200, serial numbers LC‑240 through LC‑335; Model 70, serial numbers LB‑1 through LB‑35; Model 65‑A80, 65‑A80‑8800, 65‑B80, serial numbers LD‑151 through LD‑511; Model 65‑88, serial numbers LP‑1 through LP‑26, LP‑28, and LP‑30 through LP‑47). The Directive communicates that only aircraft within these model/serial ranges are subject to its requirements.

• Prescribed inspection methods and reference documentation: The AD requires inspection by fluorescent liquid penetrant or magnetic particle methods, explicitly directing compliance "in accordance with Part II of Raytheon Aircraft Company Mandatory Service Bulletin (MSB) SB 32‑2102 Revision 7, Revised: July 2003." The MSB (manufacturer's document) is the normative technical reference for how the inspection is to be carried out.

• Corrective modification kits as mandatory remedial action: Two kit numbers are named as the required corrective modification where cracks are found , Kit No. 101‑8030‑1S and Kit No. 114‑8015‑1S , and incorporation must follow the procedures in the MSB. The AD states that incorporation of either kit, as applicable, is terminating action for the inspection requirements of this Directive.

• Compliance timing and intervals: The compliance block sets the initial inspection deadline relative to either the last inspection under the previous issue of the Directive or relative to the AD effective date (5 July 2007), and establishes a repetitive inspection interval not to exceed 200 hours TIS. It also imposes a "before further flight" requirement where cracks are discovered (that is, remedial modification after a positive finding must be done before the aircraft next flies).

• Relationship to previous amendments and FAA AD: The background traces the Directive’s amendment history: Amendment 3 introduced a modification kit that removed the repetitive inspection if fitted; Amendment 4 changed the inspection method and imposed kit incorporation on detection of a crack and expanded applicability; Amendment 5 corrects an internal reference error (Part III should have been Part II). The Directive also notes FAA Corrected AD 2004‑23‑02 as a related document.

Together, these concepts frame the Directive as a targeted safety measure requiring periodic non‑destructive inspection of a structural assembly, with mandatory fitment of defined modification kits where cracking is discovered, and with termination of repetitive inspections upon kit incorporation. The MSB is the procedural standard, and the serial number lists define the population of affected aircraft.

The Directive affects operators, owners, maintainers, and possibly lessors of the specified Beechcraft 65 and 70 (Queen Air) series aeroplanes identified by the exact model and serial number ranges in the Applicability block. Any person responsible for continuing airworthiness of a listed airframe must ensure the inspection and corrective actions set out in the Directive are completed in the specified timeframes.

Specifically identified aircraft in the Applicability block include:

• Model A65 and A65‑8200, serial numbers LC‑240 through LC‑335;
• Model 70, serial numbers LB‑1 through LB‑35;
• Model 65‑A80, 65‑A80‑8800, and 65‑B80, serial numbers LD‑151 through LD‑511;
• Model 65‑88, serial numbers LP‑1 through LP‑26, LP‑28, and LP‑30 through LP‑47.

Because the Directive prescribes inspection methods, the people carrying out the inspections must have access to and competence in the specified non‑destructive testing methods (fluorescent liquid penetrant or magnetic particle inspection) and must be able to work in accordance with Part II of the Raytheon MSB SB 32‑2102 Rev 7 (Revised: July 2003). This implies maintenance organisations with appropriate NDT capability or suitably qualified individuals will perform the work. The Directive does not itself name the category of person (for example licensed maintenance engineer or approved maintenance organisation), but it prescribes the method and the MSB standard that must be followed.

When cracks are found, the Directive requires incorporation of Kit No. 101‑8030‑1S or Kit No. 114‑8015‑1S "as applicable", per the MSB. That work requires procurement of the specified kit and installation in accordance with the MSB; the owner/operator or their maintenance provider is responsible for acquiring and fitting the kit. Incorporation of the kit is explicitly stated as terminating action for the inspection requirements of the AD, so operators who fit the kit will cease the repetitive 200‑hour inspection regime described in the Directive.

The Directive also has implications for fleet managers and compliance officers: aircraft within the serial ranges must be tracked for initial inspection deadlines (either within 200 hours TIS after the last inspection required by the previous issue of the Directive, or within 200 hours TIS after 5 July 2007 for aircraft not covered by the previous issue), and for repeat inspection scheduling every 200 hours TIS until a kit is incorporated or other relief is documented. Finally, the Directive cross‑refers FAA Corrected AD 2004‑23‑02, so operators who operate in multiple jurisdictions or who follow FAA directives should note the relationship.

The Directive imposes specific duties; it does not enumerate rights, but the text of the AD and its notes imply certain choices within the mandatory framework.

Duties imposed by the Directive:

• Inspection duty: Operators must inspect the nose landing gear fork assembly for cracks "using fluorescent liquid penetrant or magnetic particle method" and must do so "in accordance with Part II of Raytheon Aircraft Company Mandatory Service Bulletin (MSB) SB 32‑2102 Revision 7, Revised: July 2003." This is the foundational duty (Requirement 1 in the Requirement block).

• Corrective action duty on detection: If cracks are found during the Requirement 1 inspection, operators must "incorporate Kit No. 101‑8030‑1S or Kit No. 114‑8015‑1S, as applicable; as specified in MSB SB32‑2102 Revision 7, Revised: July 2003." The Compliance block clarifies that if cracks are found, the kit must be incorporated "before further flight" (Compliance item 2). This makes the corrective action a pre‑flight mandatory corrective step.

• Repetitive inspection duty: If no cracks are found during the inspection, the operator must repeat the inspection "in accordance with Part II of MSB SB 32‑2102 Revision 7, Revised: July 2003" at intervals not to exceed 200 hours TIS (Requirement 3; Compliance item 3). The Directive sets the repeat interval at 200 hours TIS.

• Initial timing duty: Operators must conduct the initial inspection within 200 hours TIS after the last inspection required by the previous issue of the Directive (Compliance 1.a) for aircraft affected by the previous issue, or within 200 hours TIS after 5 July 2007 for aircraft not affected by the previous issue (Compliance 1.b).

• Termination of inspection duty upon modification: Note 1 states incorporation of Kit No. 101‑8030‑1S or Kit No. 114‑8015‑1S is "terminating action for the inspection requirements of this Directive." That creates an operative pathway: once a kit is fitted per the MSB, the repetitive inspection duty ceases.

Implied operational constraints and rights:

• Right to select corrective pathway when cracks are found is limited: the AD specifies which kits must be fitted "as applicable" per the MSB; alternative corrective measures are not described in the Directive text. Operators therefore have little latitude when cracks are found other than to follow the specified kit incorporation procedures in the MSB.

• The Directive grants a narrow choice to operators without detected cracks: they may either continue the periodic inspections every 200 hours TIS, or choose to incorporate a terminating kit voluntarily (the Directive makes clear that kit incorporation terminates the inspection obligation; this incentivises kit fitment). The AD does not state that proactive kit incorporation is prohibited; rather Note 1 identifies kit incorporation as terminating action.

• Duty timing creates an enforcement trigger: a positive finding requires kit incorporation before further flight, which is a strict operational constraint that will typically ground the aircraft until remedial action is complete.

• Relationship to MSB: The Directive's duties are to be performed "in accordance with Part II" of the MSB; this makes the MSB the technical baseline and implies adherence to the MSB's specified procedures and conditions.

The AD does not explicitly state recordkeeping, certification procedures, or approval routes for alternative methods of compliance. It does not specify penalties in its main text; those topics are handled under enforcement/penalty law outside the scope of this Directive as presented. The Directive does, however, clearly shift costs and operational decisions to the aircraft owner/operator: they must schedule and perform or commission NDT inspections, procure applicable kits where cracking is detected, and ensure compliance within the specified time windows.

The text provided for AD/BEECH 65/61 Amdt 5 does not set out specific monetary penalties, fines, or administrative sanctions within its own wording. The Directive states the mandatory inspection and corrective actions and provides timing and procedural requirements, but it does not include a penalty schedule in the content supplied. The document is an instrument that creates continuing airworthiness obligations; enforcement mechanisms and penalties for non‑compliance are not enumerated in the excerpt provided.

Practically, the Directive creates enforceable obligations by prescribing mandatory actions: identification of applicability by serial number; inspection using specified non‑destructive testing methods in accordance with Part II of the Raytheon MSB SB 32‑2102 Rev 7; mandatory incorporation of specified kits where cracks are found; and specified compliance timings (initial inspection within 200 hours TIS after a defined baseline, repeat inspections every 200 hours TIS if no crack, and incorporation of kit before further flight when cracks are found). Where an aircraft subject to the Directive does not have the required inspections or remedial kit incorporation, that aircraft would, under the usual regulatory framework for airworthiness directives, be non‑compliant with continuing airworthiness requirements. The Directive’s "before further flight" stipulation for corrective action creates an operational enforcement point: aircraft found to have cracking but not fitted with a kit as required should not be flown, according to the Directive’s terms.

The Directive also cross‑refers FAA Corrected AD 2004‑23‑02 Amdt 39‑13857 (Note 2). That indicates a parallel regulatory expectation in the FAA domain. The presence of the MSB as the technical standard and of FAA AD reference suggests coordinated regulatory oversight, but the supplied text does not say how CASA will enforce compliance, nor does it state what sanctions apply if the Directive is ignored.

Because the Directive is a prescriptive safety regulation, the enforcement consequences (for example grounding, removal from service, administrative penalties) are determined by the broader civil aviation regulatory regime rather than by the AD text alone. The AD does, however, create clear compliance checkpoints, including a mandatory "before further flight" obligation where cracks are found, and the cessation of repetitive inspections upon correct kit incorporation, which is an operationally enforceable condition.

Within the text provided, the Directive explicitly interacts with two types of external documents: the manufacturer's Mandatory Service Bulletin (MSB) and a related FAA Airworthiness Directive. These interactions are described in the Requirement and Notes:

• Interaction with the manufacturer's MSB: The AD requires inspections and corrective action "in accordance with Part II of Raytheon Aircraft Company Mandatory Service Bulletin (MSB) SB 32‑2102 Revision 7, Revised: July 2003." That makes the MSB the procedural and technical standard for carrying out the inspection, determining whether cracks exist, and implementing the corrective kit installation. The AD thus delegates the detailed inspection and modification procedures to the manufacturer’s MSB; compliance with the AD requires adherence to that MSB Part II content. The AD also corrects an earlier misreference from Part III to Part II, indicating the precise MSB part is legally relevant for satisfying the Directive’s obligations.

• Interaction with FAA AD: Note 2 states "FAA Corrected AD 2004‑23‑02 Amdt 39‑13857 refers." This indicates the CASA Directive is related to, and probably harmonised with, an FAA action addressing the same technical issue. The text does not elaborate on the FAA AD's content within this document, but the cross‑reference signals that operators should be aware of the FAA AD when considering the global regulatory context for affected aircraft.

The Directive does not, within the supplied text, reference or modify other Australian statutes, regulations, or administrative rules. It does not specify recordkeeping, alternative means of compliance, or penalty provisions; those matters are typically governed by the broader civil aviation regulatory framework, but are not detailed here. The AD’s reliance on the MSB means that the MSB, while a manufacturer’s document, operates as a de facto regulatory instrument when the AD mandates compliance with it. That creates an interaction between CASA's regulatory authority and the manufacturer’s technical instructions; the MSB supplies the substantive technical method and the AD supplies the legal force.

The Directive also situates itself in a sequence of earlier amendments (Amendment 3, Amendment 4, and now Amendment 5) and notes that Amendment 5 corrects an internal error that flowed from related FAA AD 2004‑23‑02. This historical connection suggests an ongoing cross‑jurisdictional dialogue, but the instrument as provided does not purport to change any other legislation or AD beyond correcting an internal reference.

In short, the Directive interacts directly with the Raytheon MSB SB 32‑2102 Rev 7 (Part II) by making that document the method for compliance, and it cross‑refers an FAA Corrected AD, thereby positioning the CASA AD in a wider regulatory conversation. The AD as supplied does not set out procedural interactions with other Australian laws, but enforcement and sanctions for non‑compliance would be administered under the broader civil aviation regulatory system.

The Directive’s Background section summarises prior changes and explains the purpose of Amendment 5. The text records the following amendment milestones and their mechanical effects:

• Original Issue and Manufacturer Action: The manufacturer initially required a mandatory inspection of the nose gear lower shock absorber for evidence of slippage at the intersection of the tube and fork assembly, and a dye check of the weld area on the fork assembly. This created the initial subject matter for the Directive’s inspections.

• Amendment 3: Amendment 3 introduced a modification kit which, if fitted, removed the repetitive inspection requirement. That is a structural change: operators who installed the kit were relieved from continuing with the periodic inspection regime. The exact kit or kits introduced by Amendment 3 are not specified in the Background paragraph in the supplied text, but Amendment 3’s effect is described , it provided a terminating modification.

• Amendment 4: Amendment 4 required the same inspection requirements but by a different inspection method, and it required incorporation of an improved nose landing gear fork kit any time a crack was found. Amendment 4 also expanded the applicability by adding additional aircraft to the applicability list. Mechanically, Amendment 4 both changed the inspection technique and tightened the remedial response (mandatory kit incorporation on any crack finding), as well as increasing the population of affected aircraft.

• Amendment 5: The present amendment (Amendment 5) was issued to correct an error in Requirement 3 in the previous issue of the Directive: Requirement 3 should have referred to Part II of the referenced Beechcraft MSB SB 32‑2102 Revision 7, but the earlier text mistakenly referred to Part III. The Background states that this error flowed from related FAA AD 2004‑23‑02. Amendment 5 thus makes a correction of reference, realigning Requirement 3 with the correct part of the MSB (Part II).

The supply text also contains an explicit effective date for this issue of the Directive: "This Airworthiness Directive becomes effective on 5 July 2007." The Directive is signed and dated by David Punshon, Delegate of the Civil Aviation Safety Authority, on 16 May 2007.

The cumulative amendment history, as reported, shows an evolving regulatory response: initial inspection requirement, the availability of a terminating modification kit (Amendment 3), a change in inspection method and mandatory kit incorporation on crack detection (Amendment 4), and a technical correction to the MSB part reference (Amendment 5). The present amendment is corrective and clarificatory rather than substantive in the sense of adding new procedural obligations beyond correcting the MSB part reference and preserving the compliance times for Requirements 2 and 3 as unchanged by this issue.

The text provided for AD/BEECH 65/61 Amdt 5 does not contain any litigation history. There are no references within the supplied document to judicial proceedings, administrative appeals, or enforcement litigation related to this Directive. The Background recounts the sequence of amendments and the correction of an internal reference error that flowed from the FAA AD but does not mention any court cases or legal disputes.

Because the document is an airworthiness directive issued by a regulator, it is normally an administrative instrument that may be subject to compliance enforcement rather than to private litigation; however, the supplied text provides neither examples nor instances of litigation or appeals. It does not indicate whether affected parties challenged the Directive, sought alternative means of compliance, or engaged in administrative review. The only related external reference is to FAA Corrected AD 2004‑23‑02 Amdt 39‑13857, which the Directive notes for informational context (Note 2), but the text does not say whether that FAA AD produced any litigation.

In the absence of litigation history in the text, a reader should note only that the Directive itself contains no litigation narrative. The omission of litigation history in this instrument is not itself evidence about whether litigation has occurred; it simply means that this particular document does not record or report any legal proceedings. Any references to disputes, appeals, or court decisions would need to come from other documents or records beyond the supplied AD.

The Directive has several points where a literal or inattentive reading could produce compliance risk or operational missteps. The supplied text highlights the following practical "gotchas" that operators, maintainers, and compliance officers should note carefully:

• Exact MSB part reference matters: Amendment 5 corrects an earlier internal error that had Requirement 3 referring to Part III of Raytheon MSB SB 32‑2102 Revision 7. The correct reference is Part II. The Directive therefore requires inspections "in accordance with Part II of Raytheon Aircraft Company Mandatory Service Bulletin (MSB) SB 32‑2102 Revision 7, Revised: July 2003." Using the wrong part of the MSB could lead to performing the wrong inspection procedure or failing to meet the Directive’s requirements.

• Tight "before further flight" obligation after crack detection: The Compliance block sets a strict operational constraint: if a crack is found during the Requirement 1 inspection, incorporation of the applicable kit is required "before further flight" (Compliance item 2). That means a positive inspection finding is an immediate grounding event until the specified kit is installed in accordance with the MSB.

• Terminating action only by specified kits: The Directive states incorporation of Kit No. 101‑8030‑1S or Kit No. 114‑8015‑1S, "as applicable", is terminating action for the inspection requirements of the Directive (Note 1). Operators cannot substitute other modifications as terminating action unless another approved pathway is provided; the AD itself does not provide alternate terminating actions. The kits must be installed per the MSB.

• Serial number specificity: Applicability is given in detailed serial number ranges across multiple model variants. It is necessary to check an aircraft’s exact serial number against the list in the Applicability block. Mistaking model designation for applicability or overlooking listed serial number gaps (for example LP‑27 is not listed in the Model 65‑88 sequence) could lead to incorrectly assuming compliance obligations.

• Initial inspection timing depends on previous issue coverage: Compliance 1.a and 1.b differ. For aircraft affected by the previous issue of the Directive, the initial inspection timing is within 200 hours TIS after the last inspection required by that previous issue. For aircraft not affected by the previous issue, the initial inspection is within 200 hours TIS after 5 July 2007. Understanding whether an airframe was covered by the previous issue is therefore necessary to apply the correct initial inspection deadline.

• Repeat interval and its continuity: The repeat inspection interval is "not to exceed 200 hours time in service." Operators must schedule and track inspections closely. If a kit is incorporated, the inspection requirement terminates , monitoring whether and when the terminating kit was fitted is therefore essential to maintain correct scheduling.

• Cross‑reference to FAA Corrected AD: Note 2 refers to FAA Corrected AD 2004‑23‑02 Amdt 39‑13857. Practitioners operating internationally or cross‑referencing FAA records should track that FAA AD for its content and any differences in method, deadlines, or compliance pathways that might affect multi‑registry operations.

• The AD corrects rather than creates new obligations in this issue: Amendment 5 is corrective , it fixes a misreferenced MSB part. The Compliance note says "The compliance times for Requirements 2 and 3 remain unchanged by this issue of the Directive." That can be misread as implying other compliance times changed; care should be taken to treat this issue as a correction of a reference rather than as a substantive deadline change.

• Procurement and installation logistics: While not numerically specified in the AD, the Directive requires operators to obtain and install specified kits when cracks are found. If a kit is not readily available, the "before further flight" requirement could create operational disruption. Planning for parts availability and maintenance capacity is therefore essential.

• Record‑keeping and proof of compliance: The AD itself does not set out recordkeeping formalities in the provided text. Nonetheless, because kit incorporation is terminating action, operators must be able to demonstrate that the applicable kit was fitted per the MSB when requested by the regulator. Failure to keep demonstrable evidence of compliance could create enforcement exposure even where the physical work was carried out.

These are practical compliance pitfalls rooted in the AD’s textual terms: the precise MSB part, the before‑flight requirement on crack detection, the specified kit numbers as the only terminating action, serial number lists, and the distinct initial inspection timing rules.

To comply with AD/BEECH 65/61 Amdt 5 as set out in the supplied text, follow these concrete steps tied directly to the Directive’s Requirement and Compliance blocks and the referenced MSB.

1. Confirm applicability:

   • Check the aircraft model and serial number against the Applicability block. Affected aircraft include Model A65 and A65‑8200 (serials LC‑240 through LC‑335); Model 70 (serials LB‑1 through LB‑35); Model 65‑A80, 65‑A80‑8800, 65‑B80 (serials LD‑151 through LD‑511); and Model 65‑88 (serials LP‑1 through LP‑26, LP‑28, and LP‑30 through LP‑47). Only aircraft within these serial ranges are subject to the Directive.

2. Obtain the referenced technical procedure:

   • Acquire Raytheon Aircraft Company Mandatory Service Bulletin SB 32‑2102 Revision 7, Revised: July 2003, and locate Part II. The AD mandates inspections be carried out "in accordance with Part II" of that MSB. Ensure you are working from the correct revision and part , Amendment 5 corrects a prior erroneous reference to Part III.

3. Schedule and perform the initial inspection within the correct interval:

   • If the aircraft was affected by the previous issue of this Directive, perform the initial inspection within 200 hours time in service after the last inspection required by the previous issue (Compliance 1.a).
   • If the aircraft was not affected by the previous issue, perform the initial inspection within 200 hours TIS after 5 July 2007 (Compliance 1.b).
   • The inspection method required is fluorescent liquid penetrant or magnetic particle inspection, performed per Part II of the MSB.

4. If cracks are found:

   • Follow the MSB’s instructions regarding identification and reporting of a crack.
   • Incorporate the applicable modification kit: either Kit No. 101‑8030‑1S or Kit No. 114‑8015‑1S, as applicable, "as specified in MSB SB32‑2102 Revision 7, Revised: July 2003" (Requirement).
   • Do not return the aircraft to service until the kit is installed in accordance with the MSB; the Compliance block states incorporation is required "before further flight" (Compliance 2).
   • Note that incorporation of the applicable kit is terminating action for the inspection requirements of this Directive (Note 1). Once the kit is incorporated per the MSB, the repetitive inspections mandated by Requirement 3 are no longer required.

5. If no cracks are found:

   • Repeat the inspection "in accordance with Part II of MSB SB 32‑2102 Revision 7, Revised: July 2003" at intervals not to exceed 200 hours time in service (Requirement 3; Compliance 3).
   • Maintain inspection scheduling to ensure the 200‑hour TIS maximum interval is not exceeded.

6. Document the work:

   • While the AD text does not prescribe recordkeeping procedures in this excerpt, operators should document the inspection results, dates, times in service, methods used, and any kit procurement and installation records. Because kit installation is terminating action, retain records demonstrating the kit was installed in accordance with the MSB.

7. Coordinate logistics in advance:

   • Because a positive inspection requires kit incorporation before further flight, ensure that either the operator or maintenance provider has access to the relevant kit and to the technical capability to install it promptly. Failure to have parts and maintenance capacity available risks aircraft grounding.

8. Cross‑reference related material:

   • Note 2 references FAA Corrected AD 2004‑23‑02 Amdt 39‑13857. For operators subject to multiple jurisdictions or who operate internationally, review the FAA AD for any additional or differing procedures or timelines.

9. Monitor for any further regulatory updates:

   • This AD is Amendment 5 and corrects a procedural reference. Check for any subsequent amendments, safety bulletins, or alternative means of compliance that may affect obligations.

10. Ensure maintenance personnel competence and equipment:

• The required inspection methods , fluorescent liquid penetrant and magnetic particle inspection , require appropriate NDT equipment and qualified personnel. Ensure the maintenance organisation or technician performing the inspection is competent and follows the MSB’s Part II procedures.

Follow the Directive’s exact procedural references and the specified compliance windows: initial inspection within the stated 200 hours TIS threshold; repeat inspections every 200 hours TIS if no crack; kit incorporation before further flight when a crack is found; and recognition that kit installation is terminating action for the inspection requirement. Adherence to Part II of SB 32‑2102 Revision 7 (Revised: July 2003) is the procedural touchstone for compliance.