2023-09-09: Exhaust Turbine System (Recip)

1. The authority citation for part 39 continues to read as follows: Authority: 49 U.S.C. 106(g), 40113, 44701. 2. The FAA amends § 39.13 by adding the following new airworthiness directive: 2023-09-09 Various Airplanes, Helicopters, and Engines: Amendment 39 22432; Docket No. FAA-2022-0891; Project Identifier AD-2022-00585-A,E,R. (a) Effective Date This airworthiness directive (AD) is effective July 17, 2023. (b) Affected ADs None. (c) Definitions (1) For purposes of this AD, a "v-band coupling" means a spot-welded, multi-segment v-band coupling installed at the tailpipe to turbocharger exhaust housing flange. (2) For purposes of this AD, "new" means zero hours time-in-service (TIS). (d) Applicability This AD applies to all turbocharged, reciprocating engine-powered airplanes and helicopters and turbocharged, reciprocating engines, certificated in any category, with a spot-welded, multi-segment v-band coupling installed at the tailpipe to turbocharger exhaust housing flange, except for airplanes that are in compliance with an AD listed in paragraphs (d)(1) through (10) of this AD, or have the supplemental type certificate (STC) listed in paragraph (d)(11) of this AD installed. These v-band couplings are installed on, but not limited to, the products listed in Table 1 to paragraph (d) of this AD. (1) AD 2018-06-11, Amendment 39-19231 (83 FR 13383, March 29, 2018). (2) AD 2014-23-03, Amendment 39-18019 (79 FR 67340, November 13, 2014). (3) AD 2013-10-04, Amendment 39-17457 (78 FR 35110, June 12, 2013; corrected September 5, 2013 (78 FR 54561)). (4) AD 2010-13-07, Amendment 39-16338 (75 FR 35619, June 23, 2010; corrected July 26, 2010 (75 FR 43397)). (5) AD 2004-23-17, Amendment 39-13872 (69 FR 67809, November 22, 2004). (6) AD 2001-08-08, Amendment 39-12185 (66 FR 20192, April 20, 2001). (7) AD 2000-11-04, Amendment 39-11752 (65 FR 34941, June 1, 2000). (8) AD 2000-01-16, Amendment 39-11514 (65 FR 2844, January 19, 2000). (9) AD 91-21-01 R1, Amendment 39-9470 (61 FR 29003, June 7, 1996; corrected September 6, 1996 (61 FR 47051)). (10) AD 81-23-03 R2, Amendment 39-4491 (47 FR 51101, November 12, 1982). (11) STC Number SA4976NM for Type Certificate Number: A17WE, Make: Aerostar, Model: PA-60-600, -601, -601P, -602P, and -700P. Table 1 to Paragraph ( d )-Applicability Includes, But Is Not Limited to, the Following Airplanes, Helicopters, and Engines When Turbocharged Type certificate holder Model Aerostar Aircraft Corporation PA-60-600 (Aerostar 600), PA-60-601 (Aerostar 601), PA-60-601P (Aerostar 601P), PA-60-602P (Aerostar 602P), and PA-60-700P (Aerostar 700P). B-N Group Ltd. (formerly Pilatus Britten-Norman Limited) BN-2, BN-2A, BN-2A-6, BN-2A-8, and BN-2A-9. Cirrus Design Corporation SR22, SR22T. Commander Aircraft Corporation (formerly CPAC, Inc.; Commander Aircraft Company; Gulfstream Aerospace Corporation; Gulfstream American Corporation; and Rockwell International, Commander Aircraft Division) 112TC, 112TCA, and 114TC. Continental Aerospace Technologies, Inc. (formerly Continental Motors, Inc., and Teledyne Continental Motors) LTSIO-360-E, LTSIO-360-EB, LTSIO-360-KB, LTSIO-360-RB; TSIO-360-E, TSIO-360-EB, TSIO-360-F, TSIO-360-FB, TSIO-360-KB, TSIO-360-LB, TSIO-360-MB, TSIO-360-RB, TSIO-360-SB; TSIO-520-BE, TSIO-520-L, TSIO-520-LB, TSIO-520-T, TSIO-520-WB; TSIO-550-A, TSIO-550-B, TSIO-550-C, TSIO-550-E, TSIO-550-G, TSIO-550-J, TSIO-550-K, TSIO-550-N; TSIOF-550-D, TSIOF-550-J, IO-520-B, IO-520-BA, IO-520-BB, IO-520-D, IO-550-B, IO-550-E, and IO-550-N. Costruzioni Aeronautiche Tecnam S.P.A P2012 Traveller. Daher Aerospace (formerly SOCATA and SOCATA-Groupe AEROSPATIALE) TB 21. Diamond Aircraft Industries Inc. (formerly Diamond Aircraft Industries GmbH) DA 40. The Enstrom Helicopter Corporation F-28C, F-28C-2, F-28C-2R, F-28F, F-28F-R, 280C, 280F, and 280FX. Helio Aircraft LLC 500. Helio Alaska, Inc H-295 (USAF U-10D) and H-395 (USAF L-28A or U-10B). The King's Engineering Fellowship (formerly Evangel-Air) 4500-300 and 4500-300 Series II. Lycoming Engines (formerly Textron Lycoming) IO-540-AA1A5, IO-540-AG1A5, IO-540-S1A5, TIO-540-AE2A, TIO-540-AH1A, TIO-540-J2BD, TO-360-C1A6D, TO-360-E1A6D, LTO-360-A1A6D, LTO-360-E1A6D, and LTIO-540-J2BD. Maule Aerospace Technology, Inc. (formerly Maule Aircraft Corporation) M-5-210TC. Merlyn Products, Inc IO-540-MX1. Mooney International Corporation (formerly Mooney Aviation Company, Inc.; Mooney Airplane Company, Inc.; Mooney Aircraft Corporation; Aerostar Aircraft Corporation of Texas; and Mooney Aircraft Inc.) M20J, M20K, M20M, M20TN, and M20V. Piper Aircraft, Inc. (formerly The New Piper Aircraft, Inc.) PA-23, PA-23-160, PA-23-235, PA-23-250, PA-23-250 (Navy UO-1), PA-E23-250, PA-24-250, PA-24-260, PA-24-400, PA-28-201T, PA-28R-201T, PA-28RT-201T, PA-30, PA-31, PA-31-325, PA-31-350, PA-31P, PA-31P-350, PA-32-260, PA-32R-300, PA-32RT-300T, PA-32R-301(SP), PA-32-301T, PA-32R-301T, PA-34-200, PA-34-200T, PA-34-220T, PA-39, PA-44-180T, PA-46-310P, and PA-46-350P. Revo, Incorporated (formerly Global Amphibians, LLC; Consolidated Aeronautics, Inc.; Lake Aircraft Corporation; and Colonial Aircraft Company) Lake Model LA-4, Lake Model LA-4A, Lake Model LA-4-200, and Lake Model 250. Scott's-Bell 47, Inc. (formerly Bell Helicopter Textron Inc.) 47G-3B, 47G-3B-1, 47G-3B-2, and 47G-3B-2A. Siam Hiller Holdings, Inc. (formerly Rogerson Hiller Corporation; Hiller Helicopters; Rogerson Aircraft Corporation; Hiller Aviation; Heli-Parts, Inc.; Fairchild Industries, Inc.; and Hiller Aircraft Corporation) UH-12L and UH-12L4. SST FLUGTECHNIK GmbH (formerly Extra Flugzeugproduktions-und Vertriebs-GmbH and Extra Flugzeugbau GmbH Flugplatz) EA 400. Textron Aviation Inc. (formerly Beechcraft Corporation, Hawker Beechcraft Corporation, Raytheon Aircraft Company, and Beech Aircraft Corporation) 35-33, 35-A33, 35-B33, 35-C33, 35-C33A, E33, E33A, E33C, F33, F33A, F33C, H35, J35, K35, M35, N35, P35, S35, V35, V35A, V35B, 36, A36, A36TC, B36TC, D55, E55, 56TC (Turbo Baron), A56TC (Turbo Baron), 58, G58, 60 (Duke), A60 (Duke), B60 (Duke), 95, 95-C55, B95, B95A, D95A, and E95. Textron Aviation Inc. (formerly Cessna Aircraft Company) 185, 185A, 185B, 185C, 185D, 185E, A185E, A185F, A188, A188A, A188B, A188C, T182, T182T, TR182, T188C, 206, P206, P206A, P206B, P206C, P206D, P206E, T206H, TP206A, TP206B, TP206C, TP206D, TP206E, TU206A, TU206B, TU206C, TU206D, TU206E, TU206F, TU206G, U206, U206A, U206B, U206C, U206D, U206E, U206F, U206G, T207, T207A, 210, 210A, 210B, 210C, 210-5 (205), 210-5A (205A), P210N, T210G, T210H, T210J, T210K, T210L, T210M, T210N, T240, T303, 310, 310B, 310C, 310D, 310E (USAF U-3B), 310F, 310G, 310H, 310I, 310J, T310P, T310Q, T310R, 320, 320A, 320B, 320C, 320D, 320E, 320F, 320-1, 321, 335, 340, 340A, LC40-550FG, LC41-550FG, LC42-550FG, FT337E, FT337F, FT337GP, FT337HP, P337H, T337B, T337C, T337D, T337E, T337F, T337G, T337H, T337H-SP, 401, 401A, 401B, 402, 402A, 402B, 402C, 404, 411, 411A, 414, 414A, 421, 421A, 421B, 421C. Triton Aerospace LLC (formerly Triton America LLC; AAI Acquisition, Inc.; and Adam Aircraft) A500. 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. Vulcanair S.p.A. (formerly Partenavia Costruzioni Aeronautiche S.p.A.) P.68C-TC, and P.68TC "Observer". (e) Subject Joint Aircraft System Component (JASC) Code 8100, Exhaust Turbine System (Recip). (f) Unsafe Condition This AD was prompted by multiple failures of spot-welded, multi-segment v-band couplings installed at the tailpipe to turbocharger exhaust housing flange. The FAA is issuing this AD to prevent failure of the spot-welded, multi-segment exhaust tailpipe v-band coupling. The unsafe condition, if not addressed, could lead to detachment of the exhaust tailpipe from the turbocharger and allow high-temperature exhaust gases to enter the engine compartment. This could result in smoke in the cockpit, in-flight fire, and loss of control of the aircraft. (g) Compliance Comply with this AD within the compliance times specified, unless already done. (h) Review of the Maintenance Records Within 50 hours TIS after the effective date of this AD, review the aircraft maintenance records to determine the number of hours TIS accumulated on each v-band coupling. (i) V-Band Coupling Life Limit (1) Within the compliance times specified in paragraph (i)(1)(i) or (ii) or (i)(2) of this AD, remove the v-band coupling from service and install a new v-band coupling. Apply correct torque as necessary to the v-band coupling nut. (i) If the v-band coupling has accumulated less than 500 hours TIS: Initially remove the v-band coupling from service before it accumulates 500 hours TIS or within 50 hours TIS after the effective date of this AD, whichever occurs later. Thereafter, remove the v-band coupling from service before it accumulates 500 hours TIS. (ii) If the v-band coupling has accumulated 500 or more hours TIS or if the hours TIS of the v-band coupling cannot be determined: Initially remove the v-band coupling from service within 50 hours TIS after the effective date of this AD. Thereafter, remove the v-band coupling from service before it accumulates 500 hours TIS. (2) As an alternative to initially removing the v-band coupling from service as required by paragraph (i)(1) of this AD, you may perform the inspections required by paragraphs (k)(1) through (7) or (l) of this AD. Do the initial inspections at the time the v-band coupling would have been removed from service and thereafter at intervals not to exceed 6 months or 100 hours TIS, whichever occurs first, for a period not to exceed 2 years after the effective date of this AD. If the v-band coupling fails to meet any inspection criteria in paragraphs (k)(1) through (7) or (l) of this AD, it must be removed from service before further flight. Removing the v-band coupling from service and installing a new v-band coupling does not terminate the requirement to do these repetitive inspections. Note 1 to paragraph (i): Instructions for installing a v-band coupling can be found in Appendix B: Best Practices Guide, paragraph 3.1, of the "Exhaust System Turbocharger to Tailpipe V-band Coupling/Clamp Working Group Final Report," dated January 2018. (j) V-Band Coupling Inspections At the next annual inspection after the effective date of this AD or within the next 12 months after the effective date of this AD, whichever occurs first, and repetitively thereafter at intervals not to exceed 12 months, visually inspect the v-band coupling as required by paragraphs (k)(1) through (7) of this AD. Removing the v-band coupling from service and installing a new v-band coupling does not terminate the requirement to do these repetitive inspections. (k) Inspections Without Removal of the V-Band Coupling (1) Inspect the v-band coupling and area around the v-band coupling for exhaust stains, sooting, and discoloration. If any of those conditions are found, remove the coupling and, instead of the inspections in paragraphs (k)(2) through (7) of this AD, do the inspections in paragraph (l) of this AD. (2) Inspect the v-band coupling outer band for cracks, paying particular attention to the spot weld areas. If there is a crack, before further flight, remove the v-band coupling from service and install a new v-band coupling. (3) Inspect the v-band coupling 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 further flight, remove the v-band coupling from service and install a new v-band coupling. (4) Inspect the v-band coupling outer band for cupping, bowing, and crowning as depicted in figure 1 to paragraph (l)(1)(iii) of this AD. If there is any cupping, bowing, or crowning, before further flight, remove the coupling and, instead of the inspections in paragraphs (k)(5) through (7) of this AD, do the inspections in paragraph (l) of this AD. (5) Inspect the area of the v-band coupling, including the outer band, opposite the t-bolt for damage and distortion. If there is any damage or distortion, before further flight, remove the v-band coupling from service and install a new v-band coupling. (6) Using a mirror, inspect the v-band coupling 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 further flight, remove the v-band coupling from service and install a new v-band coupling. (7) Determine whether the v-band coupling nut is properly torqued and apply correct torque as necessary. (l) Inspections With the Spot-Welded, Multi-Segment Exhaust Tailpipe V-Band Coupling Removed (1) Remove the v-band coupling and do the inspections in paragraphs (l)(1) and (2) of this AD if required by paragraph (k)(1) or (4) of this AD or as an alternative to the inspections required by paragraph (k) of this AD. Removing the v-band coupling from service and installing a new v-band coupling does not terminate the requirement to repeat the inspections in paragraph (k) or (l) of this AD. (i) Using crocus cloth or fine abrasive cloth and mineral spirits or Stoddard solvent, clean the outer band of the v-band coupling. Pay particular attention to the spot weld areas on the v-band coupling. If there is corrosion that cannot be removed by cleaning or if there is pitting, before further flight, remove the v-band coupling from service and install a new v-band coupling. (ii) 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 further flight, remove the v-band coupling from service and install a new v-band coupling. (iii) 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 1 to paragraph (l)(1)(iii) of this AD. If the gap between the outer band and the straight edge exceeds 0.062 inch, before further flight, remove the v-band coupling from service and install a new v-band coupling. ER12JN23.077 (iv) 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 further flight, remove the v-band coupling from service and install a new v-band coupling. Note 2 to paragraph (l)(1)(iv): You may use backlighting to see gaps. (v) Visually inspect the bend radii of the v-retainer coupling segments, throughout the length of the segment, as depicted in figure 1 to paragraph (l)(1)(iii) of this AD, for cracks. If there are any cracks, before further flight, remove the v-band coupling from service and install a new v-band coupling. (vi) 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 further flight, remove the v-band coupling from service and install a new v-band coupling. (2) If the v-band coupling passes all of the inspections in paragraphs (l)(1)(i) through (vi) of this AD, it may be re-installed. (i) Apply correct torque as necessary to the v-band coupling nut. (ii) Inspect the v-band coupling 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 further flight, remove the v-band coupling from service and install a new v-band coupling. (m) Installation Prohibitions (1) From the effective date of this AD until two years after the effective date of this AD, do not install a v-band coupling that has accumulated more than zero hours TIS on any turbocharged airplane, helicopter, or engine, unless it has passed all inspections required by paragraph (k) or (l) of this AD. (2) As of two years after the effective date of this AD, do not install a v-band coupling that has accumulated more than zero and less than 500 hours TIS on any turbocharged airplane, helicopter, or engine, unless it has passed all inspections required by paragraph (k) or (l) of this AD. (3) As of two years after the effective date of this AD, do not install a v-band coupling that has accumulated 500 or more hours TIS on any turbocharged airplane, helicopter, or engine. (n) Alternative Methods of Compliance (AMOCs) (1) The Manager, Operational Safety Branch, FAA, has the authority to approve AMOCs for this AD, if requested using the procedures found in 14 CFR 39.19. In accordance with 14 CFR 39.19, send your request to your principal inspector or local Flight Standards District Office, as appropriate. If sending information directly to the manager of the Operational Safety Branch, send it to the attention of Tom Teplik, add this AD number AD 2023-09-09 to the subject line, and email to: AMOC@faa.gov. (2) Before using any approved AMOC, notify your appropriate principal inspector, or lacking a principal inspector, the manager of the local flight standards district office/certificate holding district office. (o) Related Information (1) For more information about this AD, contact Thomas Teplik, Aviation Safety Engineer, Central Certification Branch, FAA, 1801 S Airport Road, Wichita, KS 67209; phone: (316) 946-4196; email: thomas.teplik@faa.gov or Wichita-COS@faa.gov. (2) The "Exhaust System Turbocharger to Tailpipe V-band Coupling/Clamp Working Group Final Report," dated January 2018, may be found in the AD docket at regulations.gov by searching for and locating Docket No. FAA-2022-0891. (p) Material Incorporated by Reference None. Issued on May 9, 2023. Gaetano A. Sciortino, Acting Director, Compliance & Airworthiness Division, Aircraft Certification Service. [FR Doc. 2023-12417 Filed 6-9-23; 8:45 am]BILLING CODE 4910-13-P