AD/ROBIN/32 Amdt 2 - Wing Spars

The directive sets out a narrow technical regulatory concept: targeted structural inspections for corrosion on wing spars and a compliance regime tied to aircraft age and recent maintenance history. Core concepts in the text are:

• Applicability: the directive applies only to explicitly listed Robin models and serial numbers (Applicability). The list enumerates HR 100 series, HR200 variants, R2100/R2112/R2120/R2160 variants and specific serial number ranges and exceptions. Applicability is the primary scope control in the instrument.

• Inspection protocol references: inspectors must follow Avions Pierre Robin Service Letter No. 19 and Service Bulletin No. 99 for how to inspect, treat and repair corrosion; the AD does not reproduce inspection thresholds but relies on those supplier documents (Requirement).

• Access procedures and invasive inspections: the AD anticipates that corrosion may be hidden and allows for invasive access. It requires removal of main landing gear legs and wing inspection panels, and where rear-face corrosion is found, inspection of the front face that may require cutting inspection holes or wing removal; inspection holes must be prepared to an approved repair scheme (Requirement). That makes the inspection potentially intrusive and structural.

• Repair threshold rule: the AD distinguishes between corrosion that must be "treated" in accordance with SL No. 19 and SB No. 99 before further flight, and corrosion that "exceeds the limits specified in SL No. 19", which must be repaired in accordance with an approved repair scheme before further flight (Requirement). Thus the supplier documents contain the quantitative or qualitative limits that trigger repair rather than treatment.

• Timing and recurrence: a staged compliance timetable is specified. Initial compliance occurs within 60 months of manufacture, or within six months for aircraft older than 60 months at the effective date, unless the required actions were completed within the prior 24 months. Thereafter, inspections are required at intervals not exceeding 24 months (Compliance). Additionally, if spars are replaced, the 24-month inspection cadence must be resumed within 60 months from date of replacement (Requirement).

• Exemptions conditioned on maintenance programme: aircraft inspected within the last 72 months, or aircraft less than 72 months old, are not subject to the directive provided they "are maintained and continued to be maintained to an approved Alpha Aviation Design Ltd maintenance programme" (Requirement). The AD therefore ties an exemption to a maintenance approval.

• Regulatory alignment: Amendment 2 aligns the directive with certain overseas ADs and national CAA directives. The text references NZ CAA AD DCA/R2000/37B, NZ CAA AD DCA/R2000/24A and EASA AD 2005-0028, and indicates Amendment 1 was issued in response to a new EASA AD (Background). Those references indicate cross-jurisdictional coordination but the technical obligations in this AD are the controlling instrument for affected aircraft within the issuing authority.

These concepts structure the directive around a supplier-based inspection standard, invasive access where necessary, strict timing, a limited exemption based on approved maintenance programmes, and cross-reference to other authorities' directives.

The directive imposes obligations and practical effects on a specific set of parties tied to the affected aircraft. Primary affected parties are:

• Aircraft owners and operators of the listed Robin models and serial numbers. The Applicability table precisely identifies models HR 100 series; HR200 variants (HR200/100, HR200/100S, HR200/120, HR200/120B, HR200/160 with serials 001-378); R2100, R2100A, R2112, R2120U and R2160D aircraft (serials 001-378); R2160 aircraft (serials 001-378 and serial number 160A-06001 and subsequent); and R2160i aircraft (serials 001-378 and serial numbers 160Ai-07007 and subsequent). Compliance obligations attach to persons responsible for the continuing airworthiness of those aircraft.

• Maintenance organisations and licensed aircraft maintenance engineers who execute the inspections and repairs. The Requirement instructs removal of main landing gear legs and wing inspection panels "in accordance with the instructions in the aircraft maintenance manual" and directs compliance with Avions Pierre Robin SL No. 19 and SB No. 99. Those tasks will be carried out by maintenance providers authorised to work on the type.

• Certifying authorities or delegations within an operator or maintenance organisation who decide whether corrosion constitutes a condition to "treat" or "repair" and who approve any "approved repair scheme" for inspection holes or spar repairs. The AD repeatedly references actions that must be performed "in accordance with" or "prepared to an approved repair scheme", which assigns decision and approval responsibilities to the holder of maintenance approvals or to the approving authority named by the maintenance approvals regime.

• Owners or operators seeking to rely on the 72‑month exemption must be operating under "an approved Alpha Aviation Design Ltd maintenance programme" and continue to be maintained to that programme. That creates an administrative effect: operators must ensure their maintenance programme approvals are in place and documented if they intend to avoid the directive on the basis of the exemption.

• Potentially, entities responsible for spare spar replacement and structural repair approvals: where spars are replaced, the AD instructs that the inspection interval regime resumes and specifies time limits relative to the replacement date (Requirement). This affects parts suppliers, repair stations and the administrative processes surrounding parts replacement.

Financially and operationally, the primary economic burden will fall on the owners/operators and the maintenance organisations that undertake the inspections, treatments and repairs. The directive requires removal of landing gear legs and possibly wing removal and cutting inspection holes, all of which create direct labour, parts and aircraft downtime costs. The AD places inspection and remedy responsibility squarely on the persons responsible for continuing airworthiness of the affected aircraft.

Key duties imposed by the AD are explicit and procedural. They are:

• To perform specified inspections: "Remove the main landing gear legs and all the wing inspection panels ... and inspect the visible parts of the spar web and the upper and lower boom angles (top and bottom spar caps), in accordance with Avions Pierre Robin Service Letter (SL) No. 19 and Service Bulletin (SB) No. 99" (Requirement). This is a direct duty to carry out invasive inspection tasks per the supplier service documents.

• To expand inspection where rear-face corrosion is found: if corrosion is discovered on the rear face of the spar web or boom angles, the operator must "inspect the front face of the spar for corrosion in accordance with SL No. 19 and SB No. 99" and the AD anticipates that "It may be necessary to cut inspection holes or remove the wings to inspect the front face of the spar." Inspection holes must be prepared to an approved repair scheme (Requirement). This duty can require aircraft disassembly or structural intervention.

• To treat or repair found corrosion before further flight: "Treat corrosion in accordance with SL No. 19 and SB No. 99, before further flight." Where corrosion "exceeds the limits specified in SL No. 19, before further flight, repair in accordance with an approved repair scheme." The AD therefore imposes the duty to remediate to a supplier-guided or approved repair standard prior to returning the aeroplane to service (Requirement).

• To maintain inspection intervals: the AD specifies the timing obligations , initial compliance within 60 months of manufacture, within 6 months where aircraft are older than 60 months unless accomplished within the last 24 months, and thereafter at intervals not to exceed 24 months. If spars are replaced inspections "at intervals of 24 months must be resumed within 60 months from the date of replacement" (Compliance; Requirement).

• To satisfy the exemption conditions if relying on them: aircraft are exempted if they "have been inspected within the last 72 months or are less than 72 months old, provided that these aircraft are maintained and continued to be maintained to an approved Alpha Aviation Design Ltd maintenance programme." Operators claiming the exemption bear the duty to have and continue the approved maintenance programme in effect (Requirement).

Key "rights" or procedural allowances built into the AD:

• Use of supplier technical material: the AD explicitly references Avions Pierre Robin SL No. 19 and SB No. 99 as the inspection and treatment standards. Operators have the right to follow those documents and the AD does not set out alternate technical standards within its text. Where the AD requires an "approved repair scheme" for certain repairs or inspection holes, the operator may obtain approval from the approving authority for an alternative repair scheme, but the AD conditions any departure on approval. The right to use an approved repair scheme is conditioned on approval.

• Exemption by maintenance programme: the AD provides a conditional exemption for aircraft inspected within 72 months or less than 72 months old if maintained to an "approved Alpha Aviation Design Ltd maintenance programme." That is a limited right to defer the AD requirements provided the named maintenance programme approval is in place and maintained.

• Restart of inspection cycle on spar replacement: on spar replacement the requirement to "resume" the 24-month inspection interval within 60 months allows operators some temporal flexibility, but it also imposes a clear time cap tied to the replacement date.

The AD frames duties as prerequisites to "further flight", thereby creating a strict temporal duty: treatment or repair must be completed before flight is resumed if corrosion is found. The duties impose operational constraints on maintenance scheduling and may require approval processes for repair schemes and maintenance programme validation.

The AD text contains no explicit penalty clauses, fines or criminal sanctions. The document is an Airworthiness Directive issued by the Civil Aviation Safety Authority (CASA), evidenced by the signature block: "David Villiers, Delegate of the Civil Aviation Safety Authority, 16 April 2008" and the statement "This Amendment becomes effective on 5 June 2008" (Background; Compliance). The AD sets out mandatory compliance timelines and technical requirements but does not specify in its text the enforcement procedures, penalty amounts or administrative processes to be applied in the event of non‑compliance.

Where the AD requires actions to be performed "in accordance with" the aircraft maintenance manual and Avions Pierre Robin SL No. 19 and SB No. 99, and where it requires use of "an approved repair scheme", enforcement necessarily implicates the same mechanisms that enforce continuing airworthiness requirements in the regulatory regime, but those mechanisms are not described in the AD text provided. The AD itself does not identify which administrative or judicial remedies will be pursued for breaches, nor does it set out demerit, licence suspension or civil penalty schedules.

Practically, the directive's operation relies on CASA's status as the issuing authority and the AD's mandatory language and specified compliance dates. The effective date is stated. Beyond that, the AD does not state who will confirm compliance, how evidence of compliance is to be recorded or what follow-up inspections CASA will perform. The AD also cross-references other authorities' ADs (NZ CAA and EASA) but does not incorporate their enforcement provisions (Background). Therefore, the instrument imposes obligations and deadlines but leaves enforcement mechanics and sanctions outside the text. Any enforcement steps, penalty regimes or administrative actions that follow non‑compliance would need to be identified from CASA's wider regulatory framework or from other legal instruments, which are not included in the AD text provided.

The directive explicitly references other airworthiness directives and maintenance approvals, establishing a cross‑jurisdictional and supplier‑standard interaction rather than creating standalone, novel obligations:

• It refers to New Zealand Civil Aviation Authority ADs and an EASA AD. The "Requirement" section includes the Note: "NZ CAA AD DCA/R2000/37B and EASA AD 2005-0028, refer." The Background adds that "Amendment 1 was issued in response to a new EASA AD" and that "Amendment 2 is issued to align this Directive with NZ CAA AD DCA/R2000/24A for all models except the Model HR 100, which is aligned with EASA AD2005-0028." These statements indicate that the AD has been drafted to align obligations and timing with related directives issued by other aviation safety authorities. The AD therefore functions as the domestic instrument implementing compatible or equivalent technical requirements alongside those foreign ADs.

• Maintenance programme approvals: the AD conditions an exemption on being "maintained and continued to be maintained to an approved Alpha Aviation Design Ltd maintenance programme." That ties the AD to the domestic legal regime governing approved maintenance programmes. The exemption therefore interacts with the approval process and regulatory recognition of Alpha Aviation Design Ltd's maintenance programme; whether an operator qualifies depends on external approval status, which the AD treats as dispositive.

• Supplier technical material: the AD incorporates Avions Pierre Robin SL No. 19 and SB No. 99 by reference as the operative inspection, treatment and repair standards. By doing so, the AD defers technical threshold definitions and remediation standards to those supplier documents. That creates a normative interaction: compliance with the AD requires compliance with the supplier documents and, where an "approved repair scheme" is required, with an authorised repair approval process. The AD does not itself specify alternative technical standards.

• Replacement and inspection scheduling: the AD sets rules that might interact with parts approval, airworthiness approvals for replaced spars, and continuing airworthiness record-keeping obligations. It requires that, if spars are replaced, the 24-month inspection interval requirements "must be resumed within 60 months from the date of replacement." This interacts with the airworthiness record regime and part installation approval processes.

• Absence of expressed enforcement provisions: because the AD contains no in-text penalty or enforcement schedule, interaction with enforcement law is implicit. Any enforcement, sanctions, or administrative actions for non‑compliance will be governed by CASA's wider statutory powers and enforcement instruments, which are not reproduced here.

In short, the AD interacts with foreign ADs (NZ CAA, EASA), supplier technical documentation, maintenance programme approval processes, and the broader continuing airworthiness regulatory regime. The AD relies on external approvals and supplier documents to define inspection thresholds, repair schemes and exemptions.

The instrument presented is AD/ROBIN/32 Amendment 2, and the text includes a brief amendment chronology and rationale. The document identifies an earlier Amendment 1 and the reasons for both amendments:

• Original AD label: The header shows "AD/ROBIN/32 Amdt 2", indicating this is the second amendment to AD/ROBIN/32.

• Amendment 1: The Background states "Amendment 1 was issued in response to a new EASA AD, which was issued because the existing state of design AD did not address all affected types of a similar design." This indicates Amendment 1 modified the original AD to reflect a new EASA directive and to expand or clarify affected types that had previously been omitted.

• Amendment 2: The Background further states "Amendment 2 is issued to align this Directive with NZ CAA AD DCA/R2000/24A for all models except the Model HR 100, which is aligned with EASA AD2005-0028." Therefore Amendment 2 changes the AD to achieve alignment with specific New Zealand CAA and EASA ADs. The effect is cross‑reference harmonisation rather than a free-standing technical change within the AD itself. The AD also notes in the Requirement that "Note: NZ CAA AD DCA/R2000/37B and EASA AD 2005-0028, refer."

• Effective date of Amendment 2: The AD states "This Amendment becomes effective on 5 June 2008" (Compliance). The signature block records the delegate and date of signature: "David Villiers, Delegate of the Civil Aviation Safety Authority, 16 April 2008" (Background).

• Practical consequence: The AD does not list other prior amendment dates or the full text of prior versions; it records that the second amendment aligns domestic obligations with the new foreign ADs and that the AD has been adjusted to bring the affected models and serial ranges into synch with those external documents. The text makes clear that Amendment 2 is an alignment exercise intended to ensure the domestic AD mirrors comparable foreign directives for similar designs, while maintaining an explicit exception (HR 100 alignment with EASA AD2005-0028).

No further amendment steps, transitional provisions beyond the compliance dates, or sunset clauses are included in the AD text provided.

The AD text contains no litigation history, judicial decisions, or references to legal disputes. There are no cases named in the document. The Background recounts operational occurrences (safety incidents) that motivated the AD , "Several occurrences have shown that the Robin series of aircraft are highly susceptible to corrosion of wing spar web and boom angles" , but this is programmatic background information and not a record of litigation (Background). The AD does not report any legal challenges to the directive, appeals, or adjudicative outcomes.

Because the AD itself is an administrative instrument produced by the Civil Aviation Safety Authority and the document includes no mention of legal proceedings, there is no litigation record in the source to summarise. Any litigation brought in relation to the AD, compliance requirements, or enforcement would need to be located in court or tribunal records outside the text supplied.

The AD contains several provisions that create practical pitfalls or sources of confusion if read incompletely. Key points to watch for are:

• Applicability precision: the directive applies only to specific models and serial number ranges. Missing or misreading serial ranges may result in non‑compliance or unnecessary work. The Applicability table lists multiple model variants and serial number ranges; operators must check serial numbers precisely against the table.

• Multiple timing windows and overlapping exemptions: the Compliance and Requirement paragraphs use several different time thresholds. Initial compliance is "within 60 months after aircraft date of manufacture" but for aircraft "older than 60 months" at the effective date the initial compliance window is "within 6 months", unless the inspection was "accomplished within the last 24 months." Separately, the Requirement contains an exemption for aircraft inspected within the last 72 months or less than 72 months old, provided they are on an approved Alpha Aviation maintenance programme. Operators may find these multiple windows confusing: the exemption uses 72 months; initial compliance uses 60 months and 6 months; the "accomplished within the last 24 months" bracket also affects whether immediate work is required. Clear record-keeping is therefore essential to show which timing bracket applies.

• Invasive inspection likely and structural work implications: the AD anticipates that the front face inspection may require cutting inspection holes or wing removal. It also requires that inspection holes "must be prepared to an approved repair scheme." Constructing inspection holes and then restoring the structure in accordance with an approved repair scheme is a structural modification requiring approval and may incur substantial cost, parts lead time and aircraft downtime. Operators must plan for potential removal of wings and the approval processes for repair schemes.

• Reliance on external technical documents and approvals: the AD does not provide quantitative corrosion limits or technical detail; instead it requires operators to follow "SL No. 19 and SB No. 99" for inspection criteria and treatment thresholds. If those documents are unavailable, ambiguous, or difficult to interpret, operators will need to obtain them and ensure qualified engineers apply them correctly. Where corrosion exceeds the limits set in SL No. 19, repair must be "in accordance with an approved repair scheme." That approval process can be a gating item.

• Exemption conditional on a specific maintenance programme approval: the AD states the exemption depends on being "maintained and continued to be maintained to an approved Alpha Aviation Design Ltd maintenance programme." Operators not on that exact approved programme cannot rely on the exemption,even if they maintain to an equivalent standard,unless they obtain the named approval.

• Post‑replacement inspection timing nuance: if spars are replaced, inspections "at intervals of 24 months must be resumed within 60 months from the date of replacement." This phrasing can be read to mean that replacement does not indefinitely reset the inspection schedule; there is a maximum 60‑month window within which the 24‑month recurrence schedule must be reinstated. Operators replacing spars should ensure they understand and record the replacement date and resume inspections accordingly.

• Cross‑references do not themselves alter domestic obligations: the AD references NZ CAA and EASA ADs for alignment, but the domestic AD text is the controlling instrument for the obligations described here. Do not assume identical wording or enforcement across jurisdictions based solely on the cross‑references.

• No penalty schedule in the text: the AD sets mandatory obligations and compliance dates but includes no penalty provisions or enforcement steps in the document itself. Operators reliant on knowledge of enforcement mechanisms must consult CASA's broader regulatory instruments.

Being alert to these specific textual features will reduce the risk of misinterpretation and unexpected maintenance costs or grounding time.

The AD prescribes a concrete sequence of inspection and remediation steps and explicit timing. The steps below restate the AD's requirements and translate them into an operational checklist:

1. Confirm applicability. Verify the aircraft model and serial number against the Applicability table in the AD. Only the listed models and serial numbers are subject to these requirements.

2. Establish whether the exemption applies. Determine whether the aircraft has been inspected within the last 72 months or is less than 72 months old and is "maintained and continued to be maintained to an approved Alpha Aviation Design Ltd maintenance programme." If both conditions hold, the directive's requirements are not applicable. Maintain documentary evidence of the approved maintenance programme and the date and content of the relevant inspection.

3. Schedule the inspection within the specified compliance window. If the exemption does not apply, ensure initial compliance:

   • For aircraft within 60 months of manufacture, carry out the inspection within 60 months after the date of manufacture.
   • For aircraft older than 60 months at the effective date, carry out the inspection within 6 months unless the inspection has been accomplished within the last 24 months.
   • After the initial inspection, schedule subsequent inspections at intervals "not to exceed 24 months."

4. Execute the inspection exactly as required. The AD requires that you "Remove the main landing gear legs and all the wing inspection panels in accordance with the instructions in the aircraft maintenance manual, and inspect the visible parts of the spar web and the upper and lower boom angles ... in accordance with Avions Pierre Robin SL No. 19 and SB No. 99." Therefore:

   • Use the aircraft maintenance manual for gear and panel removal procedures.
   • Apply SL No. 19 and SB No. 99 criteria and inspection techniques for corrosion detection and assessment.

5. Expand inspection if rear-face corrosion is identified. If corrosion is found on the rear face of the spar web or boom angles, inspect the front face for corrosion "in accordance with SL No. 19 and SB No. 99." Be prepared to perform invasive access:

   • Cutting inspection holes or removing the wings may be necessary to access the front face.
   • Any inspection holes must be "prepared to an approved repair scheme." Obtain approval prior to creating inspection holes where required, or ensure the maintenance organisation has an approved repair scheme.

6. Remediation before further flight. If corrosion is found:

   • "Treat corrosion in accordance with SL No. 19 and SB No. 99, before further flight."
   • If corrosion "exceeds the limits specified in SL No. 19," then "before further flight, repair in accordance with an approved repair scheme." This requires following supplier treatment procedures for minor corrosion and obtaining an approved structural repair scheme for significant corrosion repairs.

7. Record-keeping and approvals. Keep maintenance records documenting:

   • Dates and scope of inspections, findings, treatment actions and any repairs performed.
   • Evidence that the inspection and repairs were completed in accordance with SL No. 19 and SB No. 99, and that any repairs were carried out to an approved repair scheme.
   • For operators relying on the 72‑month exemption, retain documentation of the approved Alpha Aviation maintenance programme and records verifying continuous compliance.

8. When spars are replaced. If the spars are replaced, resume inspections at 24‑month intervals and ensure the 24‑month inspection regime is reinstated "within 60 months from the date of replacement." Record the replacement date and the schedule for resuming inspections.

9. Liaise with CASA and approvals holders where necessary. Where an approved repair scheme is required, or where there is uncertainty about interpretation of SL No. 19 and SB No. 99, seek approval from the appropriate authority or the holder of the maintenance approval. The AD anticipates use of "approved repair scheme" and adherence to supplier documents; ensure the repair scheme approval is in hand before significant structural work is commenced.

10. Plan for operational disruption. Because the AD contemplates gear removal, cutting holes or wing removal, plan for the associated aircraft downtime, labour and parts lead times. Coordinate with maintenance providers to schedule work and secure any necessary approvals.

Following these steps, documenting compliance and maintaining supplier and approval records will align maintenance activity with the AD's mandatory requirements. The AD becomes effective on 5 June 2008; ensure all applicable compliance windows are met relative to that date and the aircraft manufacture dates.