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How long until FAA adopts this AD?Notification of a Proposal to issue an Airworthiness Directive PAD No.: 21-110 Issued: 28 July 2021 Note: This Proposed Airworthiness Directive (PAD) 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. In accordance with the EASA Continuing Airworthiness Procedures, the Executive Director is proposing the issuance of an EASA Airworthiness Directive (AD), applicable to the aeronautical product(s) identified below. All interested persons may send their comments, referencing the PAD Number above, to the e-mail address specified in the ‘Remarks’ section, prior to the consultation date indicated. Design Approval Holder’s Name: LEONARDO S.p.A. Type/Model designation(s): AW169 helicopters Effective Date: [TBD - standard: 14 days after AD issue date] TCDS Number(s): EASA.R.509 Foreign AD: Not applicable Supersedure: This AD supersedes EASA AD 2019-0252 issued on 10 October 2019. ATA 67 – Rotors Flight Control – Yaw Pedal Assemblies – Modification Manufacturer(s): Leonardo S.p.A. Helicopters, formerly Finmeccanica S.p.A., AgustaWestland S.p.A. Applicability: AW169 helicopters, all serial numbers (s/n). Definitions: For the purpose of this AD, the following definitions apply: Affected part: Pilot yaw pedal assemblies, having Part Number (P/N) 6F6720A06831 or P/N 6F6720A06832, including those marked with retromod 6F6720P01231; and co-pilot yaw pedal assemblies, having P/N 6F6720A06931 or P/N 6F6720A06932, including those marked with retromod P/N 6F6720P01331. Non-affected part: Pilot yaw pedal assemblies, having P/N 6F6720A06831 or P/N 6F6720A06832 and marked with retromod P/N 6F6720P01731, or pilot yaw pedal assembly P/N 6F6720A06833; and co-pilot yaw pedal assemblies, having P/N 6F6720A06931 or P/N 6F6720A06932 and marked with retromod P/N 6F6720P01831, or co-pilot yaw pedal assembly P/N 6F6720A06933. EASA PAD No.: 21-110 TE.CAP.00112-009 © 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 3 The SB: Leonardo Service Bulletin (SB) 169-181. Groups: Group 1 helicopters are those that have an affected part installed. Group 2 helicopters are those that do not have an affected part installed. A helicopter on which Leonardo modification (mod) 6F6720P01411 has been embodied in production is Group 2, provided the helicopter remains in that configuration. Reason: An occurrence was reported of finding a broken adjustable device, part of the pilot and co-pilot yaw pedal assembly. The results of the investigations determined that a modification of the pedal assembly was required to prevent the effect of this kind of failure. This condition, if not corrected, could possibly result in reduced yaw control of the helicopter. To initially address this unsafe condition, Leonardo developed a modification/rework of the pilot and co-pilot pedal assembly and published SB 169-147 to provide modification instructions. Consequently, EASA issued AD 2019-0252 to require rework of the pilot and co-pilot pedal assemblies. That AD was considered an interim action. Since that AD was issued, three additional events have been reported where the universal joint of the adjusting mechanism on the yaw pedals failed. Prompted by these findings, Leonardo developed mod 6F6720P01411, introducing upgraded pilot and co-pilot pedal assemblies of improved design which removes the failure modes. Leonardo also issued the SB to provide in-service modification instructions. For the reasons described above, this AD cancels the requirements of EASA AD 2019-0252, which is superseded, and requires modification and re-identification of the affected parts. Required Action(s) and Compliance Time(s): Required as indicated, unless accomplished previously: Modification: (1) For Group 1 helicopters: Within 400 flight hours or 12 months, whichever occurs first after the effective date of this AD, modify each installed affected part, as defined in this AD, and reidentify each modified pilot and co-pilot pedal assembly in accordance with the instructions of the SB. (2) Replacing each installed affected part on a helicopter with a non-affected part in accordance with the instructions of the SB is an acceptable method to comply with the modification requirements of paragraph (1) of this AD for that helicopter. Parts Installation: (3) Do not install on any helicopter an affected part, as defined in this AD, as required by paragraph (3.1) or (3.2) of this AD, as applicable.