AD/PREMIER/7 - Hydraulic Pump Fitting

The AD operationalises a small set of mechanical and compliance concepts. Applicability is tightly defined: it applies to Hawker Beechcraft (Raytheon) Model 390 aeroplanes with serial numbers RB‑4 through RB‑224. The requirement element comprises two specified retrofit tasks, each mapped to a Hawker Beechcraft Mandatory Service Bulletin (SB 29‑3869 and SB 29‑3851). The parts and kit are identified by part numbers: MS28778‑6 (preformed packing), MS21908J6 (elbow fitting, to be removed), AN924‑6J (jam nut, to be removed), MS21902J6 (union, to be installed), NAS1762J0606 (swivel fitting, to be installed) and Kit No. 390‑5803‑0001 (hydraulic pump case drain check valve kit). The AD requires compliance using the specified SBs “dated January 2008 or later FAA approved revision”; this conditions the legally acceptable method on the use of an FAA‑approved revision of the manufacturer’s SBs.

The compliance measure is time‑bounded and capacity‑sensitive: it requires completion within 200 hours TIS or within six months after the effective date of the AD, whichever occurs first. That structure converts two different resource dimensions, operating hours and calendar time, into a single binding deadline so units with low utilisation must still complete the work within six months while high‑utilisation units must do so within 200 flight hours.

The document states the causal safety rationale: nine occurrences of hydraulic fluid leaking from the engine hydraulic pump output fitting due to improperly installed elbows. The stated downstream failure modes are loss of hydraulic pressure leading to loss of systems (gear, spoilers, anti‑skid braking) and the possible presence of flammable hydraulic fluid in the engine compartment, with resulting fire risk. The AD therefore implements a hardware and routing change to prevent leak paths and to add a case drain check valve.

Formally the AD functions as a regulatory instrument that prescribes both method and materials; acceptable compliance is constrained to the manufacturer service bulletins as approved by the FAA. It also references an FAA AD (2008‑23‑13) as related material, signalling cross‑jurisdictional regulatory coordination for the same technical issue.

The primary legal addressees are persons who operate, maintain, or certify Hawker Beechcraft Model 390 aeroplanes bearing serial numbers RB‑4 through RB‑224. That includes aircraft owners, commercial or private operators, maintenance organisations, and certificated maintenance engineers or certifying staff responsible for structural and system airworthiness tasks on those aeroplanes. The AD’s applicability table specifies the serial number range , RB‑4 through RB‑224 , so an operator’s first compliance task is identification of aircraft in their fleet by serial number to determine whether the AD applies.

Secondary affected parties include parts suppliers, logistics and procurement personnel who must source the specified replacement parts and check valve kit, and the manufacturer or authorised service centres responsible for producing, distributing or installing the Hawker Beechcraft Service Bulletins SB 29‑3869 and SB 29‑3851 and the kit 390‑5803‑0001. Because the AD conditions acceptable work on “dated January 2008 or later FAA approved revision” of those SBs, the FAA’s approval status of later revisions affects which workpacks are legally acceptable; this will engage engineering and certification staff who manage SB revision control and regulatory approvals.

Operators’ scheduling and planning functions are affected by the compliance window: the AD requires completion within either the next 200 hours TIS or within six months after the effective date, whichever occurs first. This produces operational choices: aircraft with heavy utilisation may need to schedule the work promptly within hours-based limits; low‑utilisation aircraft still must undergo the work within six months, producing potential calendar‑time groundings or planned maintenance events.

Regulatory and oversight staff in the Civil Aviation Safety Authority (CASA) or their delegates will be responsible for monitoring, auditing and enforcing compliance, though the AD text does not specify enforcement mechanisms or penalties. Because the AD references an FAA AD, operators who fly across jurisdictions or who operate under FAA-related maintenance approvals will also need to reconcile obligations under both the CASA AD and the FAA AD referred to in the note.

Finally, designers of maintenance programmes and continuing airworthiness records are affected; the AD imposes a mandatory modification that needs to be recorded in maintenance logs, refresh maintenance schedules and may be a precondition for subsequent airworthiness certifications, export or sale of the aircraft, or insurance. The AD text itself does not state recordkeeping procedures, but the nature of ADs and the requirement to perform specified modifications make record documentation a practical necessity for operators and maintainers.

Duties:

• Identification duty: Determine whether an aeroplane falls within the applicability range , HBC Model 390, serial numbers RB‑4 through RB‑224 , because the AD explicitly applies to that set. The AD’s applicability block is definitive; no other aircraft are covered by the text provided.

• Modification duty: Carry out two specific physical modifications. First, remove the existing components at both left and right hydraulic pump pressure output ports , preformed packing P/N MS28778‑6, elbow fitting P/N MS21908J6, and jam nut P/N AN924‑6 , and install preformed packing P/N MS28778‑6, union P/N MS21902J6, and swivel fitting P/N NAS1762J0606 at those output ports, in accordance with Hawker Beechcraft Mandatory Service Bulletin SB 29‑3869 dated January 2008 or a later FAA‑approved revision. Second, install hydraulic pump case drain check valve Kit No. 390‑5803‑0001 in accordance with Hawker Beechcraft Mandatory Service Bulletin SB 29‑3851 dated January 2008 or a later FAA‑approved revision. The AD specifies both parts and the controlling SBs.

• Timing duty: Complete the required modifications within either the next 200 hours TIS after the effective date or within six months after the effective date, whichever occurs first. The effective date is stated as 15 January 2009, so both an hours-limited and a calendar-limited deadline are imposed.

• Method duty: Use the specified Hawker Beechcraft Mandatory Service Bulletins SB 29‑3869 and SB 29‑3851, but only the versions dated January 2008 or later FAA‑approved revisions. The AD conditions acceptable compliance on the SBs being FAA approved.

Rights and absence of rights as stated in the text:

• The AD grants no explicit exemptions, deferrals, or alternative method authorisations within the text provided. The AD ties compliance to specific SBs and FAA approval status; it does not set out a procedure for alternative methods of compliance, waivers, or extension requests within the text provided.

• The AD includes a note referencing FAA AD 2008‑23‑13 Amdt 39‑15734 dated 5 November 2008. This is an informational cross‑reference rather than a right or duty conferred on addressees by the AD text itself.

• The AD does not specify recordkeeping obligations, continuing airworthiness credits, maintenance release standards or post‑modification testing protocols beyond the requirement to accomplish the SBs “in accordance with” their instructions. The performance of the SBs will typically include instructions on torque, sealant, and test runs; those are not reproduced in the AD text, so the SBs are the controlling documents for details of the work.

Who decides compliance is adequate: the text makes acceptable compliance conditional on following the Hawker Beechcraft SBs dated January 2008 or later FAA‑approved revisions. This places operational control over method selection with whoever holds or applies the FAA‑approved SB revision: typically the manufacturer, FAA, or an authorised engineering authority. Certifying engineers performing the work must ensure the SB revision used is FAA‑approved to meet the AD wording.

The AD text itself does not set out specific penalties, fines, or enforcement procedures. It is an airworthiness directive issued by a delegate of the Civil Aviation Safety Authority, signed and dated 28 November 2008, and made effective 15 January 2009. As issued, it prescribes mandatory corrective actions and a compliance window. The text references the FAA AD 2008‑23‑13, but contains no text describing enforcement mechanisms, inspector powers, sanctions, or remedial enforcement processes.

Because the instrument is labelled and presented as an Airworthiness Directive, compliance is mandatory given the instrument’s form and issuance by the Civil Aviation Safety Authority’s delegate; however, the AD as provided does not include explicit enforcement provisions, such as civil penalty provisions, suspension/cancellation triggers, or criminal sanctions. The AD also does not state administrative processes for evidence of compliance, notifications, or required filings once the modifications are completed.

Where the AD is silent about penalties and enforcement, the relevant enforcement mechanisms will be the general statutory and regulatory enforcement framework that governs airworthiness directives and aviation safety in the issuing jurisdiction. The AD itself does not describe or limit those general powers, nor does it set out any interaction with insurance or commercial liabilities stemming from non‑compliance. The AD also does not specify who is authorised to certify the work or the form of certification required; it only requires that the modifications be performed “in accordance with” specified manufacturer service bulletins that are FAA‑approved revisions.

Practically, the absence of explicit penalties in the AD text does not mean there are none available under the aviation safety framework; it simply means this document does not enumerate them. The AD does provide mandatory technical obligations (part replacements and kit installation) and an explicit compliance deadline, which are the operative requirements; operators should therefore treat them as binding obligations and consult the wider regulatory regime for enforcement details and certification procedures not contained in this AD.

The AD expressly references an external regulatory instrument: FAA AD 2008‑23‑13 Amdt 39‑15734 dated 5 November 2008. That reference signals coordination between the Civil Aviation Safety Authority’s AD and a corresponding FAA AD addressing the same technical safety concern. The AD also conditions the acceptable methods of compliance on Hawker Beechcraft Mandatory Service Bulletins SB 29‑3869 and SB 29‑3851 “dated January 2008 or later FAA approved revision”; this creates an operational dependency on the FAA’s approval status of later revisions to the manufacturer’s service bulletins.

The AD does not itself state any relationship to other domestic statutes or regulations within its text. It does not specify interaction with registration, certification of maintenance organisations, maintenance release standards, export or sale conditions, or insurance conditions. It also does not state whether compliance with this AD satisfies any parallel domestic obligations, or whether the AD imposes any additional continuing airworthiness requirements beyond the two specified modifications.

Because the AD requires compliance with FAA‑approved revisions of the manufacturer’s SBs, operators who must comply with other jurisdictions’ ADs or approvals will need to ensure they use SB revisions that are FAA‑approved. That creates a cross‑jurisdictional compliance dependency where a later manufacturer bulletin revision that is not FAA‑approved may not be acceptable under this AD.

The AD’s method duty effectively elevates manufacturer service bulletins (as FAA‑approved) to the status of the required compliance method, thereby linking manufacturing engineering documents with statutory compliance. The AD does not, however, specify whether other AMOCs (alternative methods of compliance) are permissible under domestic rules; the AD text contains no procedure for seeking or approving alternatives. Similarly, the AD does not state whether compliance with the referenced FAA AD alone is sufficient for domestic compliance; the note points to FAA AD 2008‑23‑13, but does not convert that FAA AD into an operative domestic obligation within the AD text. Users must therefore reconcile the two ADs operationally and rely on regulatory practice or other domestic guidance to determine whether compliance with the FAA AD satisfies the CASA AD requirements.

In sum, the AD interacts with other laws and regulatory instruments by: (1) mandating FAA‑approved revisions of manufacturer SBs as the compliance method; and (2) noting a related FAA AD. The AD does not explicitly set out how it dovetails with domestic maintenance certification law, penalties, or alternative compliance procedures; those aspects will be governed by the broader aviation safety regulatory framework beyond the AD’s text.

The document supplied contains a single dated instrument and does not list prior domestic amendments or successive versions of the AD. The AD is signed and dated by the CASA delegate on 28 November 2008 and states an effective date of 15 January 2009. The requirement paragraphs reference Hawker Beechcraft Mandatory Service Bulletins SB 29‑3869 and SB 29‑3851, both dated January 2008, and permit later FAA‑approved revisions of those SBs to be used for compliance. The AD includes an explicit cross‑reference note to FAA AD 2008‑23‑13 Amdt 39‑15734 dated 5 November 2008.

No subsequent amendments, variations, superseding ADs, or revocations appear in the text provided. The AD text does not record any amendment history entries such as revocation dates, change notes, or serial updates. It also does not record changes to the applicability serial number range or to part numbers after issuance. The only instrument history visible in the document is the issuance signature and dates: issued 28 November 2008 and effective 15 January 2009, and the referenced manufacturer SB dates of January 2008.

Because the AD permits compliance using “dated January 2008 or later FAA approved revision” of the specified service bulletins, the AD allows future SB revisions that are FAA‑approved to be used as the operative method for compliance; that is the only explicit forward‑looking amendment mechanism embedded in the text. The AD does not set out how later ADs would amend or supersede this document, nor does it reference any domestic amendment processes that would produce updated versions. Users who require a formal amendment history or confirmation of current status would therefore need to consult CASA’s records or a consolidated AD database to see whether this AD has since been amended, superseded, or revoked; that information is not contained in the text provided.

The AD text provided contains no litigation history. There are no cases, proceedings, appeals, or judicial reviews cited in the document. The AD does not record any disputes, stays, injunctions, or compliance litigation, nor does it include references to tribunal decisions, administrative appeals, or enforcement proceedings.

Because the document supplied is a single issuing instrument (signed on 28 November 2008 and effective 15 January 2009) and does not append legal process or litigation materials, it supplies no basis to describe legal disputes or judicial interpretations of this AD. Any litigation history, if it exists, would have to be located outside the text provided, for example in court records, administrative appeal logs or subsequent CASA publications; that information is not present in the supplied document.

In the absence of litigation materials in the text, practitioners should treat the AD as a primary regulatory requirement in force as of the effective date, and if knowledge of litigation is required for risk assessment or compliance strategy, obtain judicial or administrative records from the relevant courts, tribunals or CASA’s public registers. The AD itself contains no entries to report.

Several practical and drafting features in the AD may create confusion or operational pitfalls for implementers.

• Identical preformed packing part number: The Requirement text states removal of the current preformed packing (P/N MS28778‑6) and then installation of new preformed packing (P/N MS28778‑6). The same part number appears as both removed and installed. That might reflect the need to replace an existing packing that is fitted incorrectly, even if the part number remains the same, or it could reflect a drafting repetition. Operators should not assume this means no change; the SB will contain the correct installation orientation, torque and sealing practice. The AD conditions acceptance on accomplishing SB 29‑3869, so implementers must follow the SB’s specific instructions rather than rely purely on P/N parity.

• Serial number scope: Applicability is RB‑4 through RB‑224. Careful identity checking is required. Operators with aircraft close to these serial numbers must verify the exact serial to determine applicability. The AD does not state whether the range is inclusive; standard reading is that it applies to that entire range. Misidentifying serials can lead to incorrect application or omission of the mandated work.

• Dual compliance deadline: The compliance window is “within the next 200 hours TIS after the effective date of this AD or within the next 6 months after the effective date of this AD, whichever occurs first”. This creates a “whichever occurs first” rule that shortens the calendar window for high‑utilisation aircraft. Operators must track both flight hours and calendar time carefully to avoid missing the earlier deadline.

• FAA‑approved revision condition: The AD requires doing the work “in accordance with” SB 29‑3869 and SB 29‑3851 dated January 2008 or later “FAA approved revision”. That condition means an SB revision that is not FAA‑approved may not be acceptable for compliance purposes even if produced by the manufacturer. Practitioners must confirm FAA approval status of any SB revision used for compliance and keep documentary evidence of the exact SB revision and its approval status.

• Cross‑referenced FAA AD: The AD includes a note referring to FAA AD 2008‑23‑13. Operators should not treat that reference as optional background; it signals there may be parallel FAA obligations or clarifications. The AD does not state whether compliance with the FAA AD satisfies this AD, so operators must check both instruments and follow the stricter or otherwise applicable requirements.

• Lack of enforcement/AMOC text: The AD does not state alternative methods of compliance (AMOCs), waiver routes, certification requirements for the work, or recordkeeping formats. Where an operator seeks an alternative fix, or to rely on equivalent parts, the AD provides no in‑text path for approval. That silence means the implementer must consult CASA for an AMOC or follow the SBs strictly.

• Parts procurement and installation details: The AD specifies part numbers and a kit number but does not provide lead times, compatibility matrices, stock status, or approved suppliers. Operators should account for procurement lead times in scheduling, especially given the six‑month calendar limit.

• Workscope at both sides: The tasks must be performed on both left and right hydraulic pump pressure output ports. Omitting one side would leave the aircraft non‑compliant.

• Potential for misreading “left and right” as symmetrical: The AD requires installation on both left and right pressure pump output ports; while the parts lists are symmetrical, installation orientations and routing may differ; follow the SBs.

• The AD does not prescribe any test flights, functional checks or sign‑off form beyond requiring that the SBs be followed. The SBs themselves will contain test and sign‑off procedures; ensure they are completed and documented.

Compliance requires a sequence of identification, procurement, scheduling, execution, certification and recordation steps derived directly from the AD text.

1. Applicability check: Confirm each aeroplane’s serial number. The AD applies only to Hawker Beechcraft (Raytheon) Model 390 aeroplanes, serial numbers RB‑4 through RB‑224. If the aircraft is not in that serial number range, the AD’s requirements, as stated, do not apply.

2. Plan timing: The AD’s effective date is 15 January 2009. The compliance window is within the next 200 hours TIS after that date or within the next six months after that date, whichever occurs first. Calculate both the hours‑based and calendar deadlines for each affected aircraft and prioritise work to meet the earlier deadline.

3. Obtain the correct service bulletins: Acquire Hawker Beechcraft Mandatory Service Bulletin SB 29‑3869 and SB 29‑3851 dated January 2008 or a later FAA‑approved revision. Confirm the revision used is FAA‑approved. Record the SB revision number, date and FAA approval evidence as part of the compliance documentation.

4. Source specified parts and kit: Secure the necessary components by P/N: preformed packing MS28778‑6 (for replacement), union MS21902J6, swivel fitting NAS1762J0606, and the hydraulic pump case drain check valve Kit No. 390‑5803‑0001. Also identify and make available any original parts to be removed (MS21908J6 elbow fitting, AN924‑6J jam nut) for proper disposal or retention as directed in the SB.

5. Schedule a certified maintainer: Engage a certificated maintenance organisation or appropriately licensed certifying staff to accomplish the SB instructions. The AD requires the work be performed “in accordance with” the SBs; the SBs typically contain step‑by‑step instructions, torque values and functional test sequences required to validate the installation.

6. Perform the work on both left and right pump output ports: Remove the current elbow, jam nut and packing and install the union and swivel fitting as required by SB 29‑3869. Install the Kit No. 390‑5803‑0001 in accordance with SB 29‑3851. Ensure the work is performed on both the left and right hydraulic pump output ports as stated.

7. Conduct required functional tests and inspections: Follow the SBs’ specified functional tests and leak checks. The AD’s safety rationale emphasises preventing hydraulic leaks and preventing hydraulic fluid from entering engine compartments, therefore pressure and leak tests specified in the SBs must be completed and documented.

8. Certification and recordkeeping: Although the AD text does not prescribe a specific form for certification, standard aviation practice requires signature and release to service by the authorised certifying staff, inclusion of the AD compliance entry in the aircraft maintenance logbooks, and retention of records for the required period under domestic maintenance regulations. Record the SB revision used and any FAA approval evidence, the parts installed (including serial numbers if relevant), the hours TIS at which the work was accomplished, and the dates.

9. Cross‑check related ADs: Review FAA AD 2008‑23‑13 Amdt 39‑15734 dated 5 November 2008 as referenced in the AD note to determine parallel obligations, differences in acceptable methods or potential duplication. Where discrepancies exist, seek regulatory clarification to ensure both instruments’ obligations are satisfied.

10. Manage supply and scheduling risks: Because the AD imposes a finite compliance window and specific component part numbers, plan procurement and maintenance slots with lead times in mind. If parts are unavailable locally, secure them early to avoid forced grounding beyond the AD’s calendar/time limits.

11. Seek clarification from CASA for alternatives: If an operator wishes to propose an alternative method of compliance, a different part that achieves an equivalent safety outcome, or a deferral, the AD provides no in‑text AMOC procedure. Therefore approach CASA or the relevant delegated authority with a technical proposal, including engineering substantiation and reference to any FAA counterparts, for approval.

12. Document post‑modification inspection and operations checks: Given the AD’s safety rationale concerning loss of hydraulic pressure and potential fire, include in the documentation the leakage checks, system pressure readings and any ground/run checks as specified by the SBs. Maintain that documentation for future airworthiness reviews, sales or export inspections.

Following these steps while ensuring adherence to SB 29‑3869 and SB 29‑3851 (FAA‑approved revisions where applicable), completing work on both left and right pump output ports, and meeting the earlier of 200 hours TIS or six months after 15 January 2009, will align operations with the AD’s explicit requirements.