AD/CONVAIR/17 - Pilot and Co-Pilot Direct Vision Window Frame Casting

The directive is constructed around a simple inspection-replace compliance mechanism triggered by measured time-in-service metrics and discovery of cracks. Key concepts and mechanical elements in the text are:

• Applicability: The AD applies to Model 340 and 440 aeroplanes, including all such models converted to turbopropeller power (Applicability line). The instrument lists the affected parts by part number: P/N 340-3110314-9, -10, -13, and -14 (Requirement 1).

• Inspection methods: The AD authorises three specific inspection techniques: a visual inspection using an 8x magnifying glass, a dye penetrant method, or an eddy current method (Requirement 1). The instruction requires special attention to the lower left and right corners of the Casting.

• Definition of inspected area: The AD narrows the meaning of "main body" of the Casting for inspection to the portion outlining the Direct View Window only, explicitly excluding attach flanges (Note 1). This reduces ambiguity about which surfaces must be examined.

• Time-based triggers and recurring inspections: The compliance schedule distinguishes Castings with 4,500 or more hours time in service and those with less than 4,500 hours. For Castings ≥ 4,500 hours, an initial inspection is required within 250 hours time in service after 11 May 2006 and then at intervals not exceeding 250 hours. For Castings < 4,500 hours, inspection is required before accumulation of 4,750 hours and thereafter at intervals not exceeding 250 hours (Compliance: For Requirement 1). Operators without individual casting hours records may substitute aircraft hours time in service (Compliance Note).

• Action on finding cracks: If cracking is detected, the AD prescribes two potential courses depending on severity. If the Casting is completely severed, it must be replaced with specified P/Ns and the aircraft may be flown to a base for replacement only at cabin pressure differential zero p.s.i. (Requirement 2). If the Casting is cracked but not completely severed, it must nonetheless be replaced, but until replacement the aircraft must be limited to cabin pressure differential zero p.s.i. and must carry in clear view of the pilots a placard stating “Operation Limitation. Pressurised Flight Prohibited.” (Requirement 3 and 3.b).

• Replacement parts and deadlines: Replacement must be with specified new parts: left-hand P/Ns 340-3110314-9 or -13; right-hand P/Ns 340-3110314-10 or -14 (Requirements 2 and 3). For non-severed cracks, replacement must occur within 250 hours time in service after detection, with the operating restrictions in force until replacement (Compliance 3).

• Ferry provisioning: The AD permits an exception allowing the aircraft to be flown at a cabin pressure differential of zero p.s.i. to a base where replacement can be accomplished (Requirement 2 and Compliance entries). That exception applies both where a Casting is completely severed (Requirement 2) and, for replacement before further flight, the same exception is noted for Requirement 2 “Before further flight; except that the aircraft may be flown at a cabin pressure differential of zero p.s.i. to a base where the replacement can be accomplished” (Compliance wording).

• Cross-reference to FAA AD: The AD refers to FAA AD 68-07-01 Amdt 39-568 (Note 2), indicating reliance on earlier FAA findings for context.

• Effective date and signatory: The AD becomes effective 11 May 2006 and is signed by David Villiers, Delegate of the Civil Aviation Safety Authority, dated 31 March 2006 (bottom of the document).

These are the mechanical building blocks. The directive couples periodic inspection with mandatory replacement when cracks are found, and it limits interim operational use to unpressurised flight with a required placard to inform flight crew.

The document identifies several categories of affected parties through its applicability statement and operational prescriptions. The list below follows the AD text and identifies the specific responsibilities implied:

• Aircraft operators and owners of Convair Model 340 and Model 440 aeroplanes, and all such model aircraft converted to turbopropeller power. The Applicability line explicitly limits the AD to these models and their conversions.

• Maintenance organisations and licensed maintenance personnel who must carry out inspections and replacements using one of the three approved techniques (8x magnifying glass visual inspection, dye penetrant, eddy current). Requirement 1 sets out the authorised inspection methods and the focus areas.

• Pilots and flight crews operating affected aircraft. The AD requires installation of a placard in clear view of the pilots reading “Operation Limitation. Pressurised Flight Prohibited” before initial takeoff after detection of a crack that is not completely severed (Requirement 3.b). Pilots must therefore comply with and observe operating limitations, and they will be constrained to unpressurised flight for affected aircraft until replacement is completed.

• Persons responsible for record-keeping of hours time in service. The Compliance section notes operators without records of hours time in service of individual Castings shall substitute aircraft hours time in service in lieu. This assigns to operators the responsibility to maintain or substitute appropriate time-in-service data to determine inspection timing.

• Procurement/logistics personnel responsible for sourcing replacement parts. The AD specifies exact replacement part numbers for left and right hand castings (P/N 340-3110314-9 or -13 for left, P/N 340-3110314-10 or -14 for right). Those procuring parts must obtain these P/Ns if replacement is required.

• Airworthiness authorities and inspectors. The AD is issued by CASA and becomes an airworthiness requirement on the effective date (11 May 2006). While the AD text does not state enforcement procedures or penalties, CASA as the issuing authority is the responsible body for the directive.

• Operators scheduling flights and maintenance. The AD’s time-in-service inspection intervals (every 250 hours time in service after the initial trigger) and the possibility of required replacement with the attendant limitation on pressurised flight will affect scheduling decisions and operational planning.

The AD does not identify other specific third parties, such as original equipment manufacturers, lessors, or insurers, within its text. It does refer to a cross-reference to an FAA AD (Note 2), which may affect operators that also must comply with FAA directives, but the directive itself applies under CASA’s authority and the listed aircraft types.

The AD sets out specific duties for operators and maintenance personnel, and a small set of limited operational rights. The following list is drawn verbatim or paraphrased closely from the AD text:

Duties (mandatory actions)

• Inspect: Operators must “inspect all visible areas of the main body of each Pilot and Co-pilot Direct Vision Window Frame Casting” P/Ns 340-3110314-9, -10, -13, and -14 for cracks by using either an 8x magnifying glass visual inspection, a dye penetrant method, or an eddy current method (Requirement 1). The inspection must pay special attention to the lower left and right hand corner of the Casting.

• Replace cracked castings: If cracking is detected, the AD requires replacement of the affected Casting with specified new parts: left hand P/N 340-3110314-9 or -13; right hand P/N 340-3110314-10 or -14 (Requirement 2 and 3).

• Install placard when cracked but not severed: If a Casting is cracked but not completely severed, the operator must install an operating limitation placard in clear view of pilots before the initial takeoff after detection. The required wording is exact: “Operation Limitation. Pressurised Flight Prohibited.” (Requirement 3.b).

• Operate at zero cabin pressure differential while awaiting replacement: If the Casting is cracked but not completely severed, the affected aircraft must be operated at a cabin pressure differential of zero p.s.i. until replacement occurs (Requirement 3.a). If a Casting is completely severed, the aircraft may be flown at zero p.s.i. to the base where replacement can be accomplished (Requirement 2).

• Adhere to inspection intervals: For Castings with 4,500 or more hours time in service, the initial inspection must occur within 250 hours time in service after 11 May 2006 and then at intervals not to exceed 250 hours. For Castings with less than 4,500 hours time in service, inspection must occur before reaching 4,750 hours and thereafter at intervals not exceeding 250 hours (Compliance: For Requirement 1).

• Replace within 250 hours after detection where cracked but not severed: Where cracking is detected but not completely severed, replacement must be completed within 250 hours time in service after detection, with the operating restrictions in place until replacement (Compliance 3).

• Substitute aircraft hours when casting hours unknown: Operators “who do not have records of hours time in service of individual Castings, shall substitute aircraft hours time in service in lieu” (Compliance Note).

Rights or limited permissions

• Ferry flight to replacement base: The AD gives the operator the right to ferry the aircraft to a base for replacement while maintaining a cabin pressure differential of zero p.s.i. This applies both where the Casting is completely severed (Requirement 2) and in certain compliance entries which permit a flight to a base for replacement at zero p.s.i.

• Use of specified inspection methods: Operators have a choice of three inspection methods; the AD does not require a specific non-destructive testing lab method beyond those listed (Requirement 1).

• Replacement with specified part numbers: The AD prescribes which new parts may be used for replacement, providing clarity for procurement (Requirements 2 and 3).

The AD phrases the placard requirement and pressurisation prohibition as operating restrictions tied to non-severed cracking, and it gives the explicit placard text to be installed before the next flight. The AD does not provide any alternative wording, temporary patching allowances, or conditional relief other than the zero p.s.i. ferry option. The AD does not specify recordkeeping formats or additional administrative filings as part of its text beyond the substitution rule for hours records.

The AD text supplied does not specify penalties, enforcement procedures, or administrative sanctions within its own wording. The document is styled and presented as an Airworthiness Directive, becomes effective on 11 May 2006, and is signed by David Villiers, Delegate of the Civil Aviation Safety Authority (signature date 31 March 2006). Beyond stating the effective date and setting out mandatory technical and operational requirements (inspection intervals, replacement obligations, operating limitations, and required placard wording), the AD does not by its text include express provisions on:

• Administrative penalties, fines, or other sanctions for non-compliance.
• Procedures for CASA audits, notice and remedy cycles, or show-cause processes.
• Appeals, variations, exemptions, or mechanisms by which an operator may seek temporary relief or deferment from the stated obligations.

Because the AD itself contains no enforcement clauses, the directive operates as a regulatory requirement set out by CASA and its effect as an airworthiness mandate is implied by its format and the signature of a CASA delegate. The AD does, however, include explicit compliance timings and operational prescriptions (for example, inspections within 250 hours, replacement deadlines, and the placard installation prior to initial takeoff after detection). Failure to comply with those explicit technical requirements would place an aircraft outside the conditions described in this AD.

Readers relying on the AD for operational planning should note that this document itself records the technical and operational demands; any enforcement processes, civil or administrative penalties, or criminal liability arising from non-compliance are not stated in the AD text supplied. The AD also cross-references FAA AD 68-07-01 Amdt 39-568 (Note 2), but the text does not set out enforcement consequences tied to that FAA AD within the supplied material. Absent further material in this document, the AD does not record enforcement steps, nor does it provide appeal or exemption procedures.

The AD itself references one external regulatory instrument directly: FAA AD 68-07-01 Amdt 39-568 (Note 2). This cross-reference indicates that the FAA previously addressed the same or similar cracking issues in the Pilot and Co-pilot Direct Vision Window Frame Castings. The supplied text does not elaborate on the legal consequences of that cross-reference nor does it incorporate other laws by reference. The interaction is therefore limited, in the AD text, to an acknowledgement that the FAA AD exists and is relevant.

Operationally and legally, the AD imposes technical and operational commands on operators of the specified Convair models. The directive sets inspection intervals, replacement obligations, operational limitations (including a mandatory placard stating “Operation Limitation. Pressurised Flight Prohibited”), and specific part numbers for replacement. Those obligations will intersect in practice with other regulatory requirements concerning:

• Airworthiness certification and continuing airworthiness obligations for the operator and aircraft.

• Maintenance and record-keeping obligations under airworthiness regulations and air operator certificates, insofar as the AD requires substitution of aircraft hours if individual casting hour records do not exist (Compliance Note). The AD’s substitution rule interacts with recordkeeping obligations by placing a burden on operators to use aircraft hours in the absence of component-level records.

• Operational approvals: The AD’s requirement that affected aircraft be operated at zero cabin pressure differential until replacement will interact with operational planning, route approvals, and passenger carriage obligations where pressurisation is normally required.

However, the AD does not itself restate or modify any general airworthiness regulation, nor does it cite an amending Act or other law. It is presented as a CASA Airworthiness Directive that becomes effective on 11 May 2006. The AD contains no express provision on how it fits with other CASA instruments , for instance, whether compliance with this AD satisfies some other specific statutory requirement. The only explicit external legal link in the text is the FAA AD reference.

In sum, within the supplied material, the only explicit legal interaction is a cross-reference to the FAA AD; other interactions with airworthiness regulation, civil aviation operational rules, maintenance rules, or safety management obligations are left implicit and would require reference to the broader regulatory framework outside this AD to describe fully.

The supplied document records the following historical facts that are internal to the AD:

• Signature and date: The AD text is signed by David Villiers, Delegate of the Civil Aviation Safety Authority, dated 31 March 2006 (signature block at the document end).

• Effective date: The AD “becomes effective on 11 May 2006” (Compliance block and closing line).

• AD designation and issuance date: The header identifies the directive as AD/CONVAIR/17 and gives the issuance notation “5/2006” (top lines and table header). The title block is repeated multiple times in the document, which appears to be formatting duplication.

No subsequent amendments, revisions, supersessions, or corrigenda are provided within the supplied material. The AD does not include an explicit list of prior versions of AD/CONVAIR/17 nor any later amendment notices. The only temporal markers in the text are the signing date (31 March 2006), the effective date (11 May 2006), and the compliance scheduling references tied to that effective date (e.g., initial inspections for Castings with ≥ 4,500 hours “within 250 hours time in service after 11 May 2006”).

The AD also cross-references FAA AD 68-07-01 Amdt 39-568 (Note 2), but the supplied material does not indicate whether this CASA AD amends, replaces, or is supplementary to any existing CASA ADs. The document does not include an amendment log, history of prior CASA AD numbers for the same subject, or references to later CASA instruments.

If an operator or compliance professional needs a full amendment history (for example, to determine whether later CASA ADs have superseded AD/CONVAIR/17), that information is not present in this AD text and would need to be sourced from CASA records or a consolidated AD list outside the supplied document.

The supplied AD text does not include any litigation history, case citations, or references to judicial or administrative determinations concerning AD/CONVAIR/17 or the subject Castings. The Background paragraph records that the FAA received numerous reports of cracks and that such cracking “affects the structural integrity of the Casting, and in some cases has caused loss of cabin pressurisation.” That is a factual background rather than a legal finding or litigation record.

The AD itself does not recount any disputes, enforcement actions, or appeals relating to its issuance. It does not cite cases, decisions, or prior administrative adjudications. The cross-reference to FAA AD 68-07-01 Amdt 39-568 indicates prior FAA action on the technical problem, but the AD text does not state any litigation or contested proceedings in relation to that FAA AD.

Therefore, based solely on the supplied document, there is no litigation history to report. Any litigation or administrative challenge arising before or after this AD’s effective date is not documented in the AD text and would therefore require external research beyond this instrument to identify.

The AD contains several textually explicit details and narrow formulations that create operational pitfalls and compliance traps. The following points are drawn directly from the AD text and are likely to cause confusion or inadvertent breaches if not carefully observed:

• Narrow definition of the inspected area: Note 1 clarifies that “the main body of the Casting includes only that part of the Casting which outlines the Direct View Window and does not include the attach flanges.” Inspectors who examine attach flanges believing them part of the required inspection could either over-inspect or misapply the AD. Conversely, failing to inspect the specified “main body” area, especially the lower corners, risks non-compliance.

• Exact inspection methods permitted: The AD authorises only three methods , visual with an 8x magnifying glass, dye penetrant, or eddy current , and requires “special attention” to the lower left and right corners. Using any other method, or a visual inspection without at least 8x magnification, would fall outside the AD’s permitted techniques.

• Precise replacement part numbers: Replacement parts are prescribed exactly (left-hand P/Ns 340-3110314-9 or -13; right-hand P/Ns 340-3110314-10 or -14). Substituting alternate part numbers, using overhauled or non-new parts, or fitting parts without those P/Ns would not satisfy the AD’s specific replacement language.

• Timing thresholds and intervals tied to hours: The inspection schedule is sensitive to hours thresholds (4,500 and 4,750 hours) and recurring 250-hour inspection intervals. Miscalculating hours or applying calendar-based intervals instead of hours could lead to missed inspections. The AD allows substitution of aircraft hours where individual casting hours are not recorded, but that substitution must be actively applied by the operator and may shift inspection timing.

• Immediate placard installation requirement: For a cracked but not severed Casting, the AD requires that “Before the initial takeoff after detection of the initial crack, an operating limitation in the form of a placard must be installed” with exact wording. Failing to install the placard before the next takeoff would breach the AD even if the operator intended to replace the Casting soon thereafter.

• Operational restriction scope: The required placard text is categorical: “Operation Limitation. Pressurised Flight Prohibited.” The AD also states “The affected aircraft must be operated at a cabin pressure differential of zero p.s.i.” It is important to note that the AD does not provide alternative interim mitigations or conditional allowances for short climbs or descent profiles; it requires zero differential at all times until replacement.

• Ferry flight limited to zero p.s.i.: Although the AD allows the aircraft to be flown to a base for replacement, it is constrained to zero cabin differential. Operators must ensure the planned ferry flight can be conducted safely without pressurisation and within the aircraft’s performance limitations.

• Record substitution only explicitly permitted for hours: The AD permits substitution of aircraft hours time in service only “for the purposes of complying with this Directive” where individual casting hours are not known. Operators should not assume the AD relaxes other component tracking or maintenance record obligations.

• Background note regarding pressurisation loss: The Background records that cracking “in some cases has caused loss of cabin pressurisation.” That language signals the safety rationale for the zero p.s.i. limitation and the placard. Operators should not treat the placard as a mere administrative step; it reflects an identified structural and safety risk.

• Repetition and formatting noise: The document contains repeated headings and duplicated labels (AD/CONVAIR/17 appears multiple times); readers should rely on the substantive Requirement and Compliance sections rather than header duplication.

Each of these items is grounded in the AD text. Overlooking any one could produce inadvertent non-compliance, operational disruptions, or safety exposures. The AD leaves little discretion in the technical prescriptions; adherence requires attention to the precise language on methods, part numbers, hours thresholds, placard wording, and pressurisation limitations.

The AD gives a clear step-by-step compliance path which operators and maintenance organisations should follow. The following steps track the AD’s Requirements and Compliance sections closely:

1. Confirm applicability: Verify that the aircraft is a Convair Model 340 or Model 440, or such a model converted to turbopropeller power. This is the applicability line of the AD; only aircraft meeting this description fall under the AD.

2. Identify affected components by part number: Locate the Pilot and Co-pilot Direct Vision Window Frame Castings on the aeroplane and confirm their part numbers are among P/N 340-3110314-9, -10, -13, -14. The AD’s Requirement 1 specifies these P/Ns.

3. Determine time-in-service status: Establish hours time in service for each Casting. If individual casting hours are not recorded, substitute aircraft hours time in service in line with the AD’s compliance note.

   • If a Casting has 4,500 or more hours time in service, schedule an inspection within 250 hours time in service after 11 May 2006 and thereafter at intervals not to exceed 250 hours.
   • If a Casting has less than 4,500 hours time in service, schedule an inspection before it accumulates 4,750 hours and thereafter at intervals not exceeding 250 hours.

4. Perform the inspection using an authorised method: Inspect all visible areas of the main body (defined by Note 1 as only the part outlining the Direct View Window, excluding attach flanges) for cracks by one of the approved techniques: visual inspection with an 8x magnifying glass, dye penetrant, or eddy current. Give special attention to the lower left and right hand corners of the Casting (Requirement 1).

5. If inspection finds no cracking: Continue with the recurring inspection schedule dictated by the AD (every 250 hours after the initial inspection trigger). Maintain records of the hours used to time the next required inspection; the AD permits substitution of aircraft hours where component hours are unavailable.

6. If inspection detects cracking, determine severity:

   • If the Casting is completely severed at any point: a. Replace the affected Casting with a new part: left hand P/N 340-3110314-9 or -13, right hand P/N 340-3110314-10 or -14 (Requirement 2). b. The aircraft “may be flown at a cabin pressure differential of zero p.s.i. to a base where the replacement can be accomplished.” Do not operate the aircraft pressurised until replacement is completed. c. Replace before further flight except for the single permitted ferry condition indicated.

   • If the Casting is cracked but not completely severed: a. Replace the affected Casting with the specified new parts (same P/Ns as above) (Requirement 3). b. Until replacement is accomplished, operate the affected aircraft at a cabin pressure differential of zero p.s.i. (Requirement 3.a). c. Before the initial takeoff after detection, install an operating limitation placard in clear view of the pilots with exact wording: “Operation Limitation. Pressurised Flight Prohibited.” (Requirement 3.b). d. Complete replacement within 250 hours time in service after detection (Compliance 3).

7. Procurement of replacement parts: Ensure the replacement parts are the new parts with the specified P/Ns. The AD does not authorise alternative P/Ns or refurbished parts; the text requires replacement with “a new part, P/N …” (Requirements 2 and 3).

8. Record actions and time stamps: While the AD does not prescribe a specific record format, operators must be able to demonstrate the timing of inspections, detections, placard installation, ferry flights (if used), and replacement within the AD’s deadlines. The AD permits substitution of aircraft hours where component hours are unknown.

9. Ensure placard compliance and visibility: If a placard is required, it must be installed “in clear view of the pilots.” The AD gives the exact wording and makes the installation a precondition to the initial takeoff after detection.

10. Plan for operational impact: Scheduling must accommodate inspection intervals (every 250 hours) and potential replacement downtime, together with the operational constraint that affected aircraft cannot fly pressurised until replacement. Ferry flights to replacement bases are permitted only at zero cabin pressure differential.

11. Follow the AD from effective date: The AD “becomes effective on 11 May 2006.” Initial inspection deadlines for Castings with ≥4,500 hours are measured relative to that effective date (Compliance language).

Compliance requires strict adherence to the AD’s methods, part numbers, intervals, placard wording, and pressurisation limits. There is no allowance in the AD text for temporary or alternative mitigations other than the expressly permitted zero p.s.i. ferry to a base for replacement.