EASA AD No.: 2024-0221

Proprietary document. Copies are not controlled. Confirm revision status through the EASA-Internet/Intranet. An agency of the European Union Page 3 of 11 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: Review of the Maintenance Records: (1) For Group 1 aircraft: Within 50 FH after the effective date of this AD, review the aircraft maintenance records to determine the FH accumulated by each affected part since its first installation on an aircraft or engine. Affected Part Life Limit: (2) For Group 1 aircraft: Within the compliance times specified in Table 1 of this AD, and, thereafter, at intervals not to exceed 500 FH, remove each affected part from service and install a serviceable part, as defined in this AD, and apply correct torque, as applicable, to the affected part nut. Figure 1 – Spot-Welded, Multi-Segment Exhaust Tailpipe V-Band Coupling EASA AD No.: 2024-0221 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 11 Table 1 – Affected Part Initial Replacement (see Note 1 of this AD) FH Accumulated Compliance Time Less than 500 FH Before exceeding 500 FH, or within 50 FH after the effective date of this AD, whichever occurs later. 500 FH or more Within 50 FH after the effective date of this AD FH not determined Note 1: Unless specified otherwise, the FH indicated in Table 1 of this AD are those accumulated by the affected part since its first installation on an aircraft or engine. Alternative Method of Compliance: (3) As an alternative to the initial removal of this affected part from service as required by paragraph (2) of this AD, inspect the affected part as specified in Appendix 3 of this AD. The initial inspection must be accomplished not later than at the time the affected part would have been removed from service (see Table 1 of this AD) and, thereafter, inspect at intervals not to exceed 6 months or 100 FH, whichever occurs first, for a period not to exceed 2 years after the effective date of this AD. Note 2: Instructions for installing an affected part can be found in Appendix B of Best Practices Guide, paragraph 3.1, of the “Exhaust System Turbocharger to Tailpipe Affected part/Clamp Working Group Final Report” dated January 2018 (see link in Section Ref. Publications of this AD). Inspection(s): (4) For Group 1 aircraft: At the next annual inspection, or within 12 months, whichever occurs first after the effective date of this AD, and, thereafter, at intervals not to exceed 12 months, inspect the affected part as specified in Appendix 3 of this AD. Terminating Action: (5) None. Parts Installation: (6) For Group 1 and Group 2 aircraft: From the effective date of this AD, it is allowed to install on any aircraft an affected part, provided it is a serviceable part, as defined in this AD, and that, following installation, the affected part is replaced as required by this AD. Ref. Publications: FAA Best Practice Guide for Maintaining Exhaust System Turbocharger to Tailpipe Affected parts/Clamps. FAA SAIB CE-03-46 dated 21 July 2003. FAA SAIB CE-04-22 dated 17 December 2003. FAA SAIB CE-05-13 dated 09 November 2004. EASA AD No.: 2024-0221 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 11 FAA SAIB CE-09-11 dated 09 February 2009. FAA SAIB CE-10-33R1 dated 16 August 2010. FAA SAIB CE-13-07R1 dated 01 May 2013. FAA SAIB CE-13-45 dated 05 September 2013. FAA SAIB CE-18-07 dated 14 December 2017. FAA SAIB CE-18-21 dated 13 July 2018. FAA SAIB CE-18-22 dated 13 July 2018. Remarks: 1. If requested and appropriately substantiated, EASA can approve Alternative Methods of Compliance for this AD. 2. This AD was posted on 17 August 2023 as PAD 23-096 for consultation until 14 September 2023. The Comment Response Document can be found in the EASA Safety Publications Tool, in the compressed (‘zipped’) file, attached to the record for this AD. 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 the aircraft design approval holder, or modification/STC approval holder, as applicable. EASA AD No.: 2024-0221 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 6 of 11 Appendix 1 – Affected Aircraft and Engines The affected parts are known to be installed on, but not limited to, the following aircraft and engine types, models: Type Certificate Holder Type(s) and Model(s) Aerostar Aircraft Corporation (formerly Piper Aircraft Inc., Ted Smith Aerostar) PA-60 (Aerostar) series aeroplanes, except those modified by FAA STC SA4976NM Britten-Norman Aircraft Ltd, (formerly B-N Group Ltd., Britten-Norman Ltd., Pilatus Britten Norman Ltd., Fairey Britten-Norman Ltd, Britten-Norman (Bembridge) Ltd) BN2, BN2A, BN2A-6, BN2A-8, and BN2A-9 aeroplanes Cirrus Design Corporation SR22 and SR22T aeroplanes Commander Aircraft Corporation (formerly CPAC Inc., Commander Aircraft Corporation, Gulfstream Aerospace Corporation, Gulfstream American Corporation, and Rockwell International - Commander Aircraft Division) 112TC, 112TCA and 114TC aeroplanes Continental Aerospace Technologies Inc. (formerly Continental Motors Inc., Teledyne Continental Motors) (L)TSIO-360, (TS)IO-520 and (TS)IO-550 series engines Costruzioni Aeronautiche TECNAM S.p.A. P2012 Traveller aeroplanes DAHER Aerospace (formerly SOCATA, SOCATA - Groupe Aerospatiale) TB21 aeroplanes Diamond Aircraft Industries Inc (formerly Diamond Aircraft Industries GmbH) DA 40 aeroplanes Enstrom Helicopter Corporation F-28 and 280 series helicopters Lycoming Engines (formerly Textron Lycoming, Lycoming - AVCO Division) (L)TO-360 and (T)IO-540 series, and LTIO-540-J2BD engines Merlyn Products, Inc. Twin Commander 500B, 500S and 500U aeroplanes, modified by STC SA01212SE and STC SE01211SE (Lycoming IO-540-MX1 engines) Mooney International Corporation M20J, M20K, M20M and M20V aeroplanes Piper Aircraft, Inc. (formerly The New Piper Aircraft Inc., Piper Aircraft Corporation) PA-23, PA-24, PA-28, PA-30, PA-31, PA-31P, PA-32, PA-32R, PA-34, PA-39, PA-44 and PA-46 series aeroplanes Revo, Inc. LA-4A, LA-4-200 and Model 250 aeroplanes SST FLUGTECHNIK GmbH (formerly Extra Flugzeugproduktions- und Vertriebs- GmbH and Extra Flugzeugbau GmbH Flugplatz) EA 400 aeroplanes EASA AD No.: 2024-0221 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 7 of 11 Type Certificate Holder Type(s) and Model(s) Textron Aviation, Inc. (formerly Hawker Beechcraft, Raytheon Aircraft Company, Beech Aircraft Corporation) 33, 35, 36 and 55 series, 56TC and A56TC (Turbo Baron), 58 and G58, 60, A60 and B60 (Duke), and 95 series aeroplanes Textron Aviation, Inc. (formerly Cessna Aircraft Company) 182, T182, TR182, 185, A185, A188, T188, 206, P206, TP206, TU206, U206, T207, 210, P210, T210, T240, T303, 310, T310, 320, 321, 335, P337, T337, 340, 401, 402, 404, 411, 414 and 421 series aeroplanes Textron Aviation, Inc. (formerly Reims Aviation) FT337 aeroplanes Twin Commander Aircraft LLC (formerly Twin Commander Aircraft Corporation, Gulfstream Aerospace Corporation, Gulfstream American Corporation, Rockwell-Standard & Associates, and Aero Design and Engineering Company, also known as Aero Commander Aircraft) 500, 500A, 500B, 500S, 500U, 560A, 560E and 685 aeroplanes Vulcanair S.p.A. (formerly Partenavia Costruzioni Aeronautica S.p.A.) P.68C-TC and P.68TC ‘Observer’ aeroplanes EASA AD No.: 2024-0221 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 8 of 11 Appendix 2 – Existing Related ADs FAA AD 81-23-03 R2 – Textron Aviation (Cessna) P210N aeroplanes FAA AD 91-21-01 R1 – Lycoming TIO-540-S1AD engines FAA AD 2000-01-16 – Textron Aviation (Cessna) 310, 320, 321, 340, 401, 402, 404, 411, 414 and 421 aeroplanes FAA AD 2000-11-04 – Commander 114TC aeroplanes FAA AD 2001-08-08 – Textron Aviation (Raytheon, Beechcraft) 33, 35 and 36 aeroplanes, if modified by STC SA5223NM and STC SE5222NM FAA AD 2004-23-17 – Mooney M20M aeroplanes FAA AD 2010-13-07 – Piper PA-32R-301T and PA-46-350P aeroplanes FAA AD 2013-10-04 – Piper PA-31, PA-31-325 and PA-31-350 aeroplanes FAA AD 2014-23-03 – Piper PA-31P aeroplanes FAA AD 2018-06-11 – Textron Aviation (Raytheon, Beechcraft) A36TC and B36TC; and S35, V35, V35A and V35B aeroplanes if equipped with optional Continental TSIO-520-D engine with AiResearch turbocharger or modified by STC SA1035WE EASA AD No.: 2024-0221 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 9 of 11 Appendix 3 – Affected Part Inspections (a) Inspections without Removal of the Affected Part: Note A3.1 to paragraph (a): as an alternative to the inspections specified in this paragraph (a), it is acceptable to inspect the affected part as specified in paragraph (b) of this Appendix. (a.1) Visually inspect the affected part and area around the affected part for exhaust stains, soot, and discolouration. If any of those conditions are found, remove the affected part and, instead of the inspections in paragraphs (a.2) through (a.7) of this Appendix, do the inspections in paragraph (b) of this Appendix. (a.2) Visually inspect the affected part outer band for cracks, paying particular attention to the spot weld areas. If there is a crack, before next flight, remove the affected part from service and install a serviceable part, as defined in this AD. (a.3) Visually inspect the affected part for looseness and for separation of the outer band from the v-retainer segments at all spot welds. If there is any looseness or separation of the outer band from any retainer segment, before next flight, remove the affected part from service and install a serviceable part, as defined in this AD. (a.4) Visually inspect the affected part outer band for cupping, bowing, and crowning as depicted in Figure A3.1 of paragraph (b.4) of this Appendix. If there is any cupping, bowing, or crowning, before next flight, remove the affected part and, instead of the inspections in paragraphs (a.5) through (a.7) of this Appendix, do the inspections in paragraph (b) of this Appendix. (a.5) Visually inspect the area of the affected part, including the outer band, opposite the t-bolt for damage and distortion. If there is any damage or distortion, before next flight, remove the affected part from service and install a serviceable part, as defined in this AD. (a.6) Using a mirror, visually inspect the affected part to determine whether there is a space between the two v-retainer coupling segments next to the t-bolt. If there is no space between the two v-retainer coupling segments next to the t-bolt, before next flight, remove the affected part from service and install a serviceable part, as defined in this AD. (a.7) Determine whether the affected part nut is properly torqued and apply correct torque as necessary. (b) Inspections with the Affected Part Removed: (b.1) Remove the affected part and inspect it as specified in paragraphs (b.2) through (b.7) of this Appendix. (b.2) Using fine abrasive cloth and mineral spirits, clean the outer band of the affected part. Pay particular attention to the spot weld areas on the affected part. If there is corrosion that cannot be removed by cleaning or if there is pitting, before next flight, remove the affected part from service and install a serviceable part, as defined in this AD. EASA AD No.: 2024-0221 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 10 of 11 (b.3) Using a 10X magnifying glass, visually inspect the outer band for cracks, paying particular attention to the spot weld areas. If there is a crack, before next flight, remove the affected part from service and install a serviceable part, as defined in this AD. (b.4) Visually inspect the flatness of the outer band using a straight edge. Lay the straight edge across the width of the outer band as depicted in Figure A3.1 of this paragraph. If the gap between the outer band and the straight edge exceeds 0.062 inch (1,575 mm) before next flight, remove the affected part from service and install a serviceable part, as defined in this AD. Figure A3.1 (b.5) With the t-bolt in the 12 o’clock position, visually inspect the attachment of the outer band to the v-retainer coupling segments for gaps between the outer band and the v-retainer coupling segments from the 1 o’clock through 11 o’clock positions. If there are any gaps between the outer band and the v-retainer coupling segments, before next flight, remove the affected part from service and install a serviceable part, as defined in this AD. Note A3.2 to paragraph (b.4): Backlighting may be used to see gaps. (b.6) Visually inspect the bend radii of the v-retainer coupling segments, throughout the length of the segment, as depicted in Figure A3.1 of paragraph (b.4) of this Appendix, for cracks. If there are any cracks, before next flight, remove the affected part from service and install a serviceable part, as defined in this AD. (b.7) Visually inspect the outer band opposite the t-bolt for damage (distortion, creases, bulging, or cracks) caused by excessive spreading of the coupling during installation or removal. If there is any damage, before next flight, remove the affected part from service and install a serviceable part, as defined in this AD. (b.8) If any affected part passes all inspections specified in paragraphs (b.2) through (b.7) of this Appendix, it may be re-installed. EASA AD No.: 2024-0221 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 11 of 11 (b.8.1) Apply correct torque as necessary to the affected part nut. (b.8.2) Inspect the affected part to determine whether there is space between the two v-retainer coupling segments next to the t-bolt. If there is no space between the two v-retainer coupling segments next to the t-bolt, before next flight, remove the affected part from service and install a serviceable part, as defined in this AD.