Airworthiness Directive AD No.: 2023-0013R1
Diamond DA42 NG · Airworthiness Directives
Overview
This document is an Airworthiness Directive (AD) issued by the European Union Aviation Safety Agency (EASA) concerning the Diamond DA42 series aircraft, specifically addressing issues related to the rudder steering bracket. The directive outlines mandatory inspections and modifications to ensure the continued airworthiness of the aircraft. It is applicable to all DA 42 models, including the DA 42 NG, and requires compliance within specified timeframes to mitigate risks associated with potential rudder control loss. The AD emphasizes the importance of following the outlined procedures to maintain safety standards in aviation operations.
- AD No.: 2023-0013R1 effective from 02 May 2024.
- Initial inspections for Group 1 aeroplanes must be completed within 200 flight hours or 9 months after 01 February 2023.
- If the measured distance at the rudder steering bracket is less than 11 mm, contact DAI for repair instructions before the next flight.
- Group 2 aeroplanes must replace affected parts during the initial inspection.
- Repetitive inspections are required at intervals not exceeding 200 flight hours.
Document
Source
Originally published by services.casa.gov.au. Sprinkle hosts a reference copy with an added summary, specifications and searchable full text.
Document details
- Type
- Airworthiness Directives
- Year
- 2024
- Pages
- 5
- File size
- 213 KB
- Publisher
- services.casa.gov.au
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In this document
Applicability
The AD applies to all DA 42, DA 42 M, DA 42 NG, and DA 42 M-NG aeroplanes, covering all manufacturer serial numbers (MSN).
Reason for the AD
The directive was issued due to reports of loose rudder T-yoke bolt nuts, excessive wear, and insufficient hole edge margins at the rudder steering bracket, which could lead to loss of rudder control. The AD mandates inspections and corrective actions to address these issues.
Required Actions and Compliance Times
Inspections must be conducted within specified timeframes: Group 1 aeroplanes must be inspected within 200 flight hours or 9 months after the original issue date. If certain conditions are found during inspections, corrective actions must be taken before the next flight.
Modification Requirements
For Group 2 aeroplanes, a modification is required concurrently with the initial inspection, which involves replacing affected parts with serviceable ones.
Repetitive Inspections
All aeroplanes must undergo repetitive inspections at intervals not exceeding 200 flight hours to ensure proper installation of the T-yoke bolt and self-locking nut.
Safety notes
- Failure to comply with this AD could lead to loss of rudder control.
- Affected parts must not be installed on any aeroplane unless specified by the AD.
Full document text
EASA AD No.: 2023-0013R1 TE.CAP.00110-012 © European Union Aviation Safety Agency. All rights reserved. ISO9001 Certified. Proprietary document. Copies are not controlled. Confirm revision status through the EASA-Internet/Intranet. An agency of the European Union Page 1 of 5 Airworthiness Directive AD No.: 2023-0013R1 Issued: 25 April 2024 Note: This Airworthiness Directive (AD) is issued by EASA, acting in accordance with Regulation (EU) 2018/1139 on behalf of the European Union, its Member States and of the European third countries that participate in the activities of EASA under Article 129 of that Regulation. This AD is issued in accordance with Regulation (EU) 748/2012, Part 21.A.3B. In accordance with Regulation (EU) 1321/2014 Annex I Part M.A.301, or Annex Vb Part ML.A.301, as applicable, the continuing airworthiness of an aircraft shall be ensured by accomplishing any applicable ADs. Consequently, no person may operate an aircraft to which an AD applies, except in accordance with the requirements of that AD, unless otherwise specified by the Agency [Regulation (EU) 1321/2014 Annex I Part M.A.303, or Annex Vb Part ML.A.303, as applicable] or agreed with the Authority of the State of Registry [Regulation (EU) 2018/1139, Article 71 exemption]. Design Approval Holder’s Name: DIAMOND AIRCRAFT INDUSTRIES GmbH Type/Model designation(s): DA 42 aeroplanes Effective Date: 02 May 2024 Original issue: 01 February 2023 TCDS Number(s): EASA.A.005 and EASA.A.513 Foreign AD: Not applicable Revision: This AD revises EASA AD 2023-0013 dated 18 January 2023, which superseded EASA AD 2019-0302 dated 13 December 2019. ATA 27 – Flight Controls – Rudder Steering Bracket – Inspections / Modification Manufacturer(s): Diamond Aircraft Industries GmbH (Austria), Diamond Aircraft Industries Inc. (Canada), CETC Wuhu Diamond Aircraft Manufacture Co. (China) Applicability: DA 42, DA 42 M, DA 42 NG and DA 42 M-NG aeroplanes (including those certified in the Restricted category), all manufacturer serial numbers (MSN). Definitions: For the purpose of this AD, the following definitions apply: The inspection MSB: Diamond Aircraft Industries (DAI) Mandatory Service Bulletins (MSB) 42-143/1 and MSB 42NG-086/1 (published as a single document), which include Work Instructions WI-MSB 42-143 and WI-MSB 42NG-086. The modification MSB: DAI Mandatory Service Bulletins (MSB) 42-146 and MSB 42NG-087 (published as a single document). EASA AD No.: 2023-0013R1 TE.CAP.00110-012 © European Union Aviation Safety Agency. All rights reserved. ISO9001 Certified. Proprietary document. Copies are not controlled. Confirm revision status through the EASA-Internet/Intranet. An agency of the European Union Page 2 of 5 The AMM TR: DAI Aircraft Maintenance Manual (AMM) Temporary Revision (TR) AMM-TR-MÄM- 42-1213. Affected part: Rudder T-yoke bolt, standard bolt LN 9037 with dimensions M6x90. Serviceable part: Rudder T-yoke bolt, Part Number (P/N) D60-5320-00-32. Note 1: The affected and serviceable parts, identified as ‘bolt’ in this AD, may be referred to as ‘axle’ in certain Diamond documents. Groups: Group 1 aeroplanes are those having MSN as listed in the inspection MSB. Group 2 aeroplanes are those having MSN as listed in the modification MSB. Group 2 is a subgroup of Group 1 aeroplanes. Group 3 aeroplanes are those which are not Group 1. Reason: Occurrences were reported of finding a loose rudder T-yoke bolt nut, excessive wear of the hole and insufficient hole edge margin at the rudder steering bracket for DA 42 aeroplanes. It has been determined that the root cause may be either a production deficiency or insufficient torque applied to the self-locking nut. This condition, if not detected and corrected, could lead to blockage or loss of rudder control. To address this potential unsafe condition, DAI issued MSB 42-137 and MSB 42NG-079 (published as a single document), which includes Work Instruction WI-MSB 42-137 and WI-MSB 42NG-079, and EASA issued AD 2019-0302 to require repetitive inspections and, depending on findings, accomplishment of corrective action(s). After that AD was issued, DAI published the inspection MSB and modification MSB, as defined in this AD, to provide further inspection and modification instructions. Consequently, EASA issued AD 2023-0013, superseding AD 2019-0302, which required a one-time inspection of the rudder steering bracket for insufficient edge distance or wear, replacement of the affected part with a serviceable part and repetitive inspections of the serviceable part for correct installation, and also prohibited installation of affected parts. Since that AD was issued, it was identified the need to improve definitions of Groups, description of Compliance Time for the initial torque seal mark inspection, and description of Parts Installation paragraph(s). Therefore, this AD is revised to include the above changes and to update the Referenced Publications chapter. Required Action(s) and Compliance Time(s): Required as indicated by this AD, unless the action(s) required by this AD have been already accomplished: EASA AD No.: 2023-0013R1 TE.CAP.00110-012 © European Union Aviation Safety Agency. All rights reserved. ISO9001 Certified. Proprietary document. Copies are not controlled. Confirm revision status through the EASA-Internet/Intranet. An agency of the European Union Page 3 of 5 Inspections: (1) For Group 1 aeroplanes: Within 200 flight hours (FH) or 9 months after 01 February 2023 [the effective date of the original issue of this AD], whichever occurs first, measure the distance between the edge of the rudder steering bracket hole and rear edge of the rudder steering bracket in accordance with the instructions of the inspection MSB. (2) If, during the inspection as required by paragraph (1) of this AD, the measured distance is equal to or more than 11 mm, before next flight, examine the hole in the rudder steering bracket for
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wear and play in accordance with the instructions of the inspection MSB (see Note A of this AD). Note A: The inspection as required by paragraph (2) of this AD includes marking the head of the T- yoke bolt and the self-locking nut in accordance with the instructions of the inspection MSB. Corrective Actions: (3) If, during the inspection as required by paragraph (1) of this AD, the measured distance is less than 11 mm, before next flight, contact DAI for approved repair instructions and, within the compliance time specified therein, accomplish those instructions accordingly. (4) If, during the inspection as required by paragraph (2) of this AD, a worn or enlarged hole is found on the rudder steering bracket, or if the T-yoke bolt is found to have play, before next flight, contact DAI for approved repair instructions and, within the compliance time specified therein, accomplish those instructions accordingly. Modification: (5) For Group 2 aeroplanes: Concurrently with the inspection as required by paragraph (1) of this AD, replace the affected part with a serviceable part and mark the head of the T-yoke bolt and the self-locking nut in accordance with the instructions of the modification MSB. Repetitive Inspections: (6) For all aeroplanes: Within the compliance time as specified in Table 1 of this AD and, thereafter, at intervals not to exceed 200 FH (see Note 2 of this AD), perform general visual inspection of the torque seal marks on the T-yoke bolt head and the self-locking nut at the rudder steering bracket for proper installation. This can be accomplished in accordance with the instructions of the AMM-TR, or of a later AMM revision which includes the AMM-TR. Table 1 – Initial Inspection Group Compliance Time Group 1 (except Group 2) Within 200 FH after the inspection as required by paragraph (1) of this AD. Group 2 Within 200 FH after the modification as required by paragraph (5) of this AD. Group 3 Within 200 FH after 01 February 2023 [the effective date of the original issue of this AD], or after first flight of the aeroplane, whichever occurs later. EASA AD No.: 2023-0013R1 TE.CAP.00110-012 © European Union Aviation Safety Agency. All rights reserved. ISO9001 Certified. Proprietary document. Copies are not controlled. Confirm revision status through the EASA-Internet/Intranet. An agency of the European Union Page 4 of 5 Note 2: A non-cumulative tolerance of 10 FH may be applied to the compliance times specified in paragraph (6) of this AD to allow synchronization of the required inspections with other maintenance tasks, for which a non-cumulative tolerance is already granted in the applicable Maintenance Manual. Corrective Actions: (7) If, during any inspection as required by paragraph (6) of this AD, any discrepancy is found, before next flight, contact DAI for approved instructions and, within the compliance time specified therein, accomplish those instructions accordingly. Credit: (8) Inspections accomplished on an aeroplane before 01 February 2023 [the effective date of the original issue of this AD] in accordance with WI-MSB 42-143 or WI-MSB 42NG-086 at original issue, or Revision 1, or Revision 2 are acceptable to comply with the requirements of paragraphs (1) and (2) of this AD, as applicable, for that aeroplane. (9) Modification of an aeroplane accomplished before 01 February 2023 [the effective date of the original issue of this AD] in accordance with the instructions of Recommended Service Bulletin (RSB) 42-139 or RSB 42NG-081 is acceptable to comply with the requirements of paragraph (5) of this AD for that aeroplane. Terminating Action: (10) None. Parts Installation: (11) Do not install on any aeroplane an affected part, as required by paragraph (11.1) or (11.2) of this AD, as applicable. (11.1) For Group 2 aeroplanes: After modification of an aeroplane as specified in paragraph (5) of this AD. (11.2) For all other aeroplanes: From 01 February 2023 [the effective date of the original issue of this AD]. Ref. Publications: Diamond Aircraft Industries MSB 42-143 and MSB 42NG-086 (published as a single document), dated 23 December 2021, which includes WI-MSB 42-143 and WI-MSB 42NG-086 original issue dated 23 December 2021; or MSB 42-143/1 and MSB 42NG-086/1 (published as a single document), dated 25 January 2022, which includes WI-MSB 42-143 and WI-MSB 42NG-086 Revision 1 dated 25 January 2022, or Revision 2 dated 10 March 2022, or Revision 3 dated 15 November 2022. Diamond Aircraft Industries MSB 42-146 and MSB 42NG-087 (published as a single document), original issue dated 15 November 2022. Diamond Aircraft Industries Recommended Service Bulletin (RSB) 42-139 or RSB 42NG-081 (published as a single document), original issue dated 21 October 2019, which includes WI-RSB 42- 139 and WI-RSB 42NG-081 Revision 2 dated 15 November 2022. EASA AD No.: 2023-0013R1 TE.CAP.00110-012 © European Union Aviation Safety Agency. All rights reserved. ISO9001 Certified. Proprietary document. Copies are not controlled. Confirm revision status through the EASA-Internet/Intranet. An agency of the European Union Page 5 of 5 Diamond Aircraft Industries AMM-TR-MÄM-42-1213 original issue dated 28 September 2021. The use of later approved revisions of the above-mentioned documents is acceptable for compliance with the requirements of this AD. Remarks: 1. If requested and appropriately substantiated, EASA can approve Alternative Methods of Compliance for this AD. 2. The original issue of this AD was posted on 19 December 2022 as PAD 22-177 for consultation until 16 January 2023. No comments were received during the consultation period. 3. Enquiries regarding this AD should be referred to the EASA Safety Information Section, Certification Directorate. E-mail: ADs@easa.europa.eu. 4. Information about any failures, malfunctions, defects or other occurrences, which may be similar to the unsafe condition addressed by this AD, and which may occur, or have occurred on a product, part or appliance not affected by this AD, can be reported to the EU aviation safety reporting system. This may include reporting on the same or similar components, other than those covered by the design to which this AD applies, if the same unsafe condition can exist or may develop on an aircraft with those components installed. Such components may be installed under an FAA Parts Manufacturer Approval (PMA), Supplemental Type Certificate (STC) or other modification. 5. For any question concerning the technical content of the requirements in this AD, please contact: Diamond Aircraft Industries GmbH, Austria, Telephone: +43 2622 26700, E‐mail: airworthiness-austria@diamondaircraft.com.