AD/BEECH 33/46 - Grimes Strobe Lights

The Directive is built around a narrow technical-hazard correction model. The primary concepts are (1) strict applicability, (2) temporary mitigation pending a modification, (3) a specified modification standard, (4) record-based acceptance of alternative compliance where the manufacturer has implemented equivalent FAA-referenced actions, and (5) time-limited compliance windows.

Applicability is tightly constrained: only Beech Model F33A aeroplanes, serial numbers CE-436 through CE-537 inclusive, fitted with Grimes strobe assemblies P/N 30-0467-1 or P/N 30-0467-3 fall within scope (Applicability). This is not a blanket fleet-wide rule; it targets a set of serial numbers and particular parts. The instrument specifies the exact part numbers, which is the mechanism that ties the hazard to a concrete component rather than a general equipment class.

Temporary mitigation is mandated prior to modification. The Directive requires immediate deactivation of the strobe system in a specified manner and adds a mandatory placard with an exact phrase, "STROBE LIGHT SYSTEM DEACTIVATED" (Requirement 1). The placard is prescriptive: the wording is specified in the Directive. The deactivation requirement is explicitly temporary and only applies until the permanent modification is installed (Note 1). The compliance window for the temporary measure is the next 25 hours time in service after the effective date (Compliance). That mechanism forces near-term operator action while allowing breathing room until modification.

Permanent correction is required by a specified service instruction. Requirement 2 mandates modification per Beech SI 0655-362, Rev I, or later approved revisions. The Directive therefore uses the manufacturer’s service instruction as the technical standard for the fix and ties relevance to the Rev I level (Requirement 2). The modification must be completed by a fixed calendar date, prior to 10 October 2008 (Compliance), which is the mechanism to ensure operators effect the permanent remedy within a bounded period.

Record-based acceptance provides a pathway for compliance where the aircraft manufacturer has performed the modification and noted it in the permanent maintenance record in defined terms. If the manufacturer’s entry states that the modification was "in accordance with either AD 74-20-11 or 74-24-03, as amended", then that entry is acceptable evidence that Requirement 2 has been met (Requirement 2 paragraph). This is a cross-reference mechanism to FAA directives that allows Australian compliance recognition based on manufacturer practice and record entries.

Finally, the Directive cross-references FAA AD 74-24-03 Amdt 39-2016 (Note 2) as relevant and explains its issuance was prompted by an internal review and receipt of the FAA AD (Background). The safety objective is stated in the text: eliminate a possible ignition source in an area where fuel or fuel vapour may exist (Background; final paragraph). The document is an operational, technical correction rather than a policy-setting instrument; it prescribes specific technical steps and a short-term operational change.

The Directive places obligations on holders and operators of the specified Beech Model F33A aeroplanes, serial numbers CE-436 through CE-537 inclusive, fitted with Grimes strobe assemblies P/N 30-0467-1 or P/N 30-0467-3 (Applicability). In practice that means owners, operators, maintenance organisations and any maintenance personnel responsible for continuing airworthiness of those aircraft are the parties that will implement the deactivation, placarding and modification required by the AD.

Decision authority for issuing the instrument is the Civil Aviation Safety Authority, represented in the document by its delegate, David Punshon, who signed the Directive on 13 February 2008 (signature block). The Directive specifies technical compliance with a Beech Service Instruction, and therefore the aircraft manufacturer (Beech) and its approved maintenance providers are the institutions whose procedures will be used to perform and verify the modification and deactivation (Requirement 1; Requirement 2).

Maintenance shops and engineers will make the record entries necessary to demonstrate compliance. The Directive explicitly recognises that an aircraft manufacturer’s entry in the aircraft permanent maintenance record stating that the modification was performed "in accordance with either AD 74-20-11 or 74-24-03, as amended", is acceptable for Requirement 2 (Requirement 2 paragraph). That allocates evidentiary function to maintenance records and to the manufacturer’s written entry.

Supply-side actors are affected indirectly. The Modification requires use of Beech SI 0655-362, Rev I, or later approved revisions. That creates demand for authorised copies of that SI and possibly parts or labour authorised by the manufacturer. The Directive does not state any government subsidy or funding for the works; the document’s requirements are framed as obligations, so financial responsibility for compliance rests with the owners/operators and their maintenance providers (the Directive contains no cost or funding provision).

Regulatory timing affects operational planning. The temporary deactivation must occur within 25 hours time in service after the AD’s effective date (Compliance). The permanent modification must be completed prior to 10 October 2008 (Compliance). Operators therefore must schedule maintenance and potentially ground aircraft pending modification or manage the aircraft’s utilisation to meet the 25-hour window and the modification deadline.

The Directive does not identify other classes of persons, such as passengers or third-party suppliers, as direct duty-holders. It does not assign responsibilities to regulators beyond issuing the AD, nor does it specify criminal penalties or enforcement actions within its text; it is focused on prescriptive technical steps and timelines (the instrument text contains no penalty clauses).

Duties are express and technical. Duty 1 is immediate deactivation: the operator must deactivate the strobe light system in accordance with Beech Service Instruction 0655-362, Rev I, or later approved revisions, and fit a temporary placard near the strobe light switch with the exact wording "STROBE LIGHT SYSTEM DEACTIVATED" (Requirement 1). The Directive specifies the method standard (the Beech SI) and the placard wording; it does not leave placard language to discretion (Requirement 1).

Duty 2 is modification: the operator must modify the strobe light system in accordance with the same Beech SI (Requirement 2). The SI is the required technical standard, not a suggestion. Both duties are subject to the defined compliance windows: deactivation within 25 hours time in service after the AD’s effective date and modification prior to 10 October 2008 (Compliance).

Rights are limited and procedural. The Directive allows an operator to rely on a prior manufacturer-performed modification if the aircraft permanent maintenance record contains an appropriate entry. Specifically, if the manufacturer recorded that the modification was "in accordance with either AD 74-20-11 or 74-24-03, as amended", that record is acceptable for compliance with Requirement 2 (Requirement 2 paragraph). That provides a right to acceptance of prior work that mirrors the AD’s technical expectation, and it recognises cross-jurisdictional equivalence with specified FAA ADs.

The Directive also allows the use of "later approved revisions" of SI 0655-362, which grants a limited flexibility: operators may comply with a later revision of the service instruction, but that later revision must be approved (Requirement 1 and Requirement 2). The document does not specify who grants that approval; it refers to "approved revisions", implying regulatory or manufacturer approval mechanisms external to the AD itself.

The Directive prescribes the effective date (10 April 2008), which establishes the start of compliance obligations (Compliance). It does not enumerate exceptions, waivers or remediation processes within the text. It does not expressly set out processes for seeking extensions or alternative means of compliance. The only alternative compliance mechanism provided is the record-based acceptance referenced above, and the only scope for technical variation is the use of later approved SI revisions.

The Directive also defines temporal limits on the temporary duty: Requirement 1 is explicitly applicable only until the strobe system is modified per Requirement 2 (Note 1). That creates a sequential duty structure: temporary deactivation plus placard followed by the permanent modification. The instrument therefore imposes a short-term operational duty and a longer-term technical duty, each with specified standards and timelines.

The text of this Directive does not contain an explicit penalties section, criminal sanctions, or a specific enforcement process. The instrument sets mandatory technical requirements and compliance times, but it does not itself articulate fines, licence consequences, or administrative enforcement mechanisms within the printed text. The Directive is framed as an airworthiness requirement with prescriptive technical steps and dates (Requirements and Compliance), yet any enforcement consequences must be inferred from the regulatory context rather than stated in the document itself.

Because the Directive mandates actions to maintain airworthiness,deactivation, placarding, and modification using a specified service instruction,failure to comply would reasonably affect an aircraft’s airworthiness status. The Directive, however, does not set out the administrative procedures or penalties that apply for non-compliance, nor does it set out a notice-to-airmen or operator-specific enforcement timetable in the text. The absence of an explicit penalties clause in the instrument means readers should not assume particular sanctions from this text alone; any enforcement or penalty regime would derive from the broader regulatory framework under which such Directives are issued, not from provisions within this AD.

The document’s compliance windows create an implicit enforcement trigger: if an affected aircraft remains unmodified after 25 hours time in service post-effective date but has not been placarded/deactivated, or if it has not been modified before the 10 October 2008 deadline, the aircraft would be non-compliant with the prescriptive measures in the Directive (Compliance). The Directive’s text does not, however, prescribe what actions CASA or other regulatory bodies will take in response to noncompliance, nor does it state the process for validating compliance beyond the record-based acceptance provision that recognises specific manufacturer entries (Requirement 2).

The recorded acceptance of manufacturer-performed modifications, when entered as specified, establishes an evidentiary basis for showing compliance, which operators should rely upon when demonstrating adherence to the Directive. The Directive specifies the acceptable record wording for that purpose (Requirement 2). Absent such entries, operators must demonstrate that the SI-based modification and placarding/deactivation steps were performed in accordance with the SI and within the stated timeframes.

Practically, because the AD relates to a possible ignition source near fuel or fuel vapour, regulators and operators will view compliance as material to continuing airworthiness. The instrument itself does not provide an appeals, waiver, or alternative means of compliance process in its text; parties seeking such relief will need to refer to broader CASA procedures or other regulatory instruments outside the AD text.

The Directive directly cross-references two United States Federal Aviation Administration airworthiness directives: AD 74-20-11 and AD 74-24-03, and specifically notes FAA AD 74-24-03 Amdt 39-2016 (Note 2; Requirement 2 paragraph). It therefore creates an interaction by recognising equivalence between the Beech SI-based modification and compliance with those FAA ADs for the purposes of Australian compliance recognition. If the aircraft manufacturer’s permanent maintenance record states the modification was "in accordance with either AD 74-20-11 or 74-24-03, as amended", then that is considered acceptable for meeting Requirement 2.

The Directive mandates compliance with a manufacturer’s Service Instruction, Beech SI 0655-362, Rev I, or later approved revisions. That links the AD’s operative requirements to technical material produced by the aircraft manufacturer. The AD therefore functions as a regulatory demand that manufacturer technical material be used as the compliance standard. The interaction here is procedural: the AD elevates the SI into a regulatory standard for the specified modification and deactivation actions.

The AD does not expressly reference Australian aviation legislation, such as the Civil Aviation Act or Civil Aviation Safety Regulations, within its text. It is a standalone directive produced by CASA, evidenced by the signature block of the CASA delegate. The Directive therefore operates as an administrative regulatory instrument issued under the authority of CASA, but the text does not set out the statutory delegation or specific legislative powers. The signing delegate is David Punshon of CASA, dated 13 February 2008.

Because the AD speaks to the aircraft permanent maintenance record and accepts specific wording as evidence of compliance (Requirement 2), it interacts with maintenance record-keeping obligations. The Directive effectively makes a record-entry standard a trigger for acceptance of compliance. That creates an interface with record-keeping rules in the wider regulatory regime; however, this AD does not specify the form, retention, or audit mechanisms for those records.

Finally, the Directive’s cross-reference to FAA ADs implies a cross-jurisdictional recognition mechanism. Where the manufacturer has already implemented modification work in line with specified FAA ADs, Australian compliance may be met without additional local action, provided the record contains the precise phrasing. The AD therefore permits duplication avoidance by accepting work consistent with named foreign directives, but the Directive does not itself modify other laws or harmonise regulatory registries; it simply recognises work conforming to the named FAA ADs as acceptable for the Australian requirement.

The text of the Directive references substantive revision levels and other directives but contains no amendment history for itself beyond the effective and signature dates. The AD becomes effective on 10 April 2008 (Compliance). It bears the date 4/2008 and is signed on 13 February 2008 by the CASA delegate, David Punshon, which establishes the issuance timeline that leads to the stated effective date.

Internally, the Directive specifies that compliance must be in accordance with Beech Service Instruction 0655-362, Revision I, or later approved revisions (Requirement 1; Requirement 2). That language anticipates that the SI may be amended, and it permits later approved revisions to satisfy the AD. The AD does not list any later SI revisions itself; it simply sets Rev I as the baseline and leaves later approval processes outside the AD’s text.

The Directive also refers to FAA AD 74-24-03 and notes "Amdt 39-2016 refers" (Note 2). That is an external reference to an amendment number of the FAA AD; within this instrument that reference serves as an acknowledgment that the FAA AD has its own amendment history and that the Australian AD takes that into account when setting record-based acceptance criteria for compliance. The AD additionally mentions AD 74-20-11 in the context of acceptable manufacturer entries (Requirement 2). Those references are the only indications of amendment interaction in the text.

No revisions to AD/BEECH 33/46 are listed in the document itself, and there is no explicit mechanism described in the text for how amendments to the AD would be promulgated, nor any history of amendments prior to its effective date. The instrument’s statement that it becomes effective on 10 April 2008 and its signature date of 13 February 2008 imply an issuance process, but the AD does not include an explicit prior-version log or later amendment notes inside the printed text. Any amendment history subsequent to 10 April 2008 is not reflected in the supplied text.

Because the Directive allows later approved revisions of the Beech SI as means of compliance, the practical amendment pathway for technical detail lies primarily in manufacturer SI revisions and their approvals, rather than in repeated formal amendments of the AD’s text. The AD itself thus remains a standing administrative instrument tied to evolving manufacturer technical material.

The supplied Directive text contains no litigation history. It does not cite any court decisions, nor does it reference any administrative appeals, disputes or challenges arising from the issuance of the Directive. The document makes no mention of judicial review, precedent, or prior adjudications in relation to the subject matter.

Because the AD cross-references FAA ADs and allows manufacturer-recorded conformity with those FAA ADs to satisfy Requirement 2, the text suggests a reliance on technical standards rather than litigation to resolve disputes. However, the AD does not set out procedures for dispute resolution, judicial review, or how contested compliance claims would be handled. The absence of litigation references in the instrument means readers should treat the AD as a technical regulatory requirement and, if contesting it or seeking relief, refer to the broader CASA regulatory framework and administrative law procedures outside the AD text.

If compliance or enforcement were to be contested in court or through administrative channels, those processes would be governed by external statutes and procedures that are not described within this Directive. The instrument itself contains no record of any past litigation related to the Grimes strobe lights issue or to the AD’s issuance. Users seeking litigation history must therefore consult external sources or CASA records beyond the scope of this text.

The Directive contains several details that are easy to miss but significant for compliance and practical effect.

1. Narrow applicability by serial number and part number. Applicability is limited to Beech Model F33A aeroplanes, serial numbers CE-436 through CE-537 inclusive, and only when equipped with Grimes strobe light assemblies P/N 30-0467-1 or P/N 30-0467-3 (Applicability). Aircraft outside that serial range, or those with different strobe assemblies, are not within the AD’s scope. Operators must confirm both serial number and part number before assuming applicability.

2. Exact placard wording required. Requirement 1 mandates the addition of a temporary placard near the strobe light switch stating "STROBE LIGHT SYSTEM DEACTIVATED". The Directive specifies the text; alternative phrasing may not meet the Directive’s explicit requirement (Requirement 1). The placard is not advisory but prescriptive.

3. Sequence and temporality. Requirement 1 is explicitly applicable only until the strobe system is modified per Requirement 2 (Note 1). The temporary deactivation therefore expires once the permanent modification is installed. The deactivation must be completed within 25 hours time in service after the Directive became effective, while the modification must be done before 10 October 2008 (Compliance). Operators must manage scheduling to satisfy both short-term and medium-term timing.

4. Reliance on an SI revision baseline. The technical standard is Beech SI 0655-362, Rev I, or later approved revisions (Requirement 1; Requirement 2). Operators must ensure they use Rev I or a later revision that is formally approved. The Directive does not define the approval channel for later revisions within its text.

5. Record-based compliance wording is precise. The AD accepts manufacturer entries in the permanent maintenance record that state the modification was "in accordance with either AD 74-20-11 or 74-24-03, as amended" as evidence of compliance with Requirement 2 (Requirement 2 paragraph). The prescribed phrase is specific; deviation in wording may jeopardise the operator’s ability to rely on that record as acceptable proof within the exact terms of the Directive.

6. Cross-reference to FAA ADs. Note 2 mentions FAA AD 74-24-03 Amdt 39-2016, which the Directive references; operators should not assume that any FAA AD work automatically satisfies the Australian AD unless it matches the record criteria set out in this Directive (Note 2; Requirement 2 paragraph).

7. No penalties specified. The AD does not contain an express penalties or enforcement clause in its text. Operators should not assume the AD defines enforcement consequences; those will derive from broader regulatory authorities outside the AD itself (Penalties and enforcement).

8. Issuance despite zero Australian-registered aircraft at time of receipt. The Background describes that when FAA AD 74-24-03 was received there were no Beech Model F33A aeroplanes on the Australian register, yet the Directive was still issued (Background). This means the AD applies prospectively if affected aircraft later enter the register.

9. Effective date and signature mismatch. The Directive is signed on 13 February 2008, but becomes effective on 10 April 2008 (signature block; Compliance). Operators must use the effective date to calculate compliance windows.

10. Limited textual scope. The AD is technical and prescriptive but silent on broader compliance logistics such as approved maintenance organisations, costs, supply of parts or approvals for later SI revisions. Those practicalities must be resolved against the wider regulatory and industry framework; the AD itself does not supply procedural details.

Follow these concrete steps based on the Directive’s requirements and timeframes.

1. Confirm applicability. Verify the aircraft is a Beech Model F33A with serial number within CE-436 to CE-537 inclusive, and that the installed strobe assemblies are Grimes P/N 30-0467-1 or P/N 30-0467-3 (Applicability). Do not proceed with deactivation or modification planning unless both serial number and part number match the AD’s applicability.

2. Obtain the specified Service Instruction. Secure Beech Service Instruction (SI) 0655-362, Revision I, and check whether any later revision exists and is formally approved for use. The AD requires compliance with Rev I or a later approved revision (Requirement 1; Requirement 2). Ensure maintenance personnel authorised to work on the type are familiar with and follow the SI’s procedures.

3. Implement the temporary measure within the 25-hour window. Within the next 25 hours time in service after the AD’s effective date (10 April 2008), deactivate the strobe light system in accordance with SI 0655-362, Rev I, or later approved revisions (Requirement 1; Compliance). Fit the temporary placard adjacent to the strobe light switch that reads exactly: "STROBE LIGHT SYSTEM DEACTIVATED" (Requirement 1). Record the deactivation action in the aircraft maintenance logs with date, time, and reference to the SI and this AD.

4. Plan and execute the permanent modification. Schedule and complete the modification specified by SI 0655-362, Rev I, or later approved revisions, prior to 10 October 2008 (Requirement 2; Compliance). Use appropriately authorised personnel or an approved maintenance organisation to perform the work in accordance with the SI.

5. Record the modification correctly. If the manufacturer performs the modification, the aircraft permanent maintenance record should include the entry that the modification was "in accordance with either AD 74-20-11 or 74-24-03, as amended", or words to that effect, to ensure the modification is accepted as compliance with Requirement 2 (Requirement 2 paragraph). If the modification is performed by an operator or third-party maintenance organisation, make a clear record referencing SI 0655-362, Rev I (or later approved revision), including dates, part numbers changed if any, and signatures of certifying personnel.

6. Remove the temporary placard once modified. Note 1 makes Requirement 1 applicable only until the permanent modification required by Requirement 2 is performed. After the modification is installed and appropriate records entered, remove the temporary placard and update the aircraft’s maintenance status accordingly.

7. Maintain documentation for audit. While the AD does not specify enforcement procedures in-text, maintain comprehensive maintenance records that show compliance with the AD’s dates and technical standards. Include copies of the SI used, logbook entries showing deactivation and later modification, and, if applicable, the manufacturer’s maintenance record entry with the exact phrase set out in the Directive.

8. Verify parts. Ensure that any replacement or modified strobe assemblies conform to the requirements of the SI and that part numbers and configuration post-modification are documented. The AD’s applicability is tied to specific Grimes P/Ns; confirmation that the aircraft no longer contains those parts post-modification will be relevant for demonstrating compliance.

9. Cross-reference FAA AD compliance where applicable. If the manufacturer’s work references FAA ADs 74-20-11 or 74-24-03 and that is recorded as indicated, the Directive will accept that as meeting Requirement 2 (Requirement 2 paragraph). Confirm that the record wording aligns with the Directive’s phrasing.

10. Keep aware of SI revision approvals. If relying on a later revision of SI 0655-362, ensure that the revision is formally approved for use. The AD allows later approved revisions, but the AD text does not define the approval authority or process; confirm approval status with the manufacturer or relevant regulatory authority prior to performing the work.

These steps implement the Directive’s two-pronged approach: immediate mitigation by deactivation and placarding, followed by a manufacturer-prescribed modification to eliminate the ignition-source hazard. The effective date to calculate the compliance windows is 10 April 2008; the AD is signed by David Punshon, Delegate of the Civil Aviation Safety Authority, dated 13 February 2008.