2024-19-09: Nose/Tail Landing Gear

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: a. Removing Airworthiness Directive 2016-08-08, Amendment 39-18484 (81 FR 21711, April 13, 2016); and b. Adding the following new airworthiness directive: 2024-19-09 DAHER (Type Certificate previously held by SOCATA): Amendment 39-22851; Docket No. FAA-2024-1480; Project Identifier MCAI-2023-00930-A. (a) Effective Date This airworthiness directive (AD) is effective November 26, 2024. (b) Affected ADs This AD replaces AD 2016-08-08, Amendment 39-18484 (81 FR 21711, April 13, 2016). (c) Applicability This AD applies to DAHER (type certificate previously held by SOCATA) Model MS 880B, MS 885, MS 892A-150, MS 892E-150, MS 893A, MS 893E, MS 894A, MS 894E, Rallye 100S, Rallye 150ST, Rallye 150T, Rallye 235C, and Rallye 235E airplanes, all serial numbers, certificated in any category. (d) Subject Joint Aircraft System Component (JASC) Code 3220, Nose/Tail Landing Gear. (e) Unsafe Condition This AD was prompted by a report of a nose landing gear (NLG) wheel axle failure in service. The FAA is issuing this AD to address chafing and cracking of the NLG wheel axle. The unsafe condition, if not addressed, could lead to failure of the NLG with consequent damage to the airplane and injury to occupants. (f) Compliance Comply with this AD within the compliance times specified, unless already done. (g) Definitions For the purpose of this AD the following definitions apply: (1) Group 1 Airplanes: Airplanes having any affected parts installed as of the effective date of this AD. (2) Group 2 Airplanes: Airplanes that do not have any affected parts installed as of the effective date of this AD. (3) Affected Parts: NLG wheel axles having part number (P/N) 8954200270 and NLG wheel spacer having P/N 8954200260. (4) Serviceable Parts: NLG wheel axles having P/N AV-RAL-001-01 and NLG wheel spacer having P/N AV-RAL-002-01. (5) New Part: Any part that has zero hours time-in-service (TIS). (h) Inspections and Axle Replacement For Group 1 Airplanes (1) Within 200 hours TIS after the effective date of this AD, and thereafter at intervals not to exceed 200 hours TIS, perform a detailed visual inspection for chafing and cracking between the NLG wheel bearing and axle surface in accordance with paragraphs B.1 and B.2 of Daher Service Bulletin SB 150, Revision 4, dated January 2023 (Daher SB 150, Revision 4). (2) If any chafing or cracking is found during any inspection required by paragraph (h)(1) of this AD, before further flight, replace the NLG wheel axle with one of the following: (i) An NLG wheel axle that is found to be free of chafing and cracking per the inspection required by paragraph (h)(1) of this AD and free of damage per the inspection required by paragraph (h)(3) of this AD. (ii) Serviceable parts, as defined in this AD, in accordance with paragraphs C.2 through C.4 of Daher SB 150, Revision 4. This part installation makes the airplane a Group 2 airplane and terminates the inspection requirements in this AD. (3) If no chafing or cracking is found during any inspection required by paragraph (h)(1) of this AD, before further flight, do a magnetic particle inspection of the NLG wheel axle for damage (distortion, nicks, wear, and cracking). (4) If any damage is found during any magnetic particle inspection required by paragraph (h)(3) of this AD, before further flight, replace the NLG wheel axle with one of the following: (i) An NLG wheel axle that is found to be free of chafing and cracking per the inspection required by paragraph (h)(1) of this AD and free of damage per the inspection required by paragraph (h)(3) of this AD. (ii) Serviceable parts, as defined in this AD, in accordance with paragraphs C.2 through C.4 of Daher SB 150, Revision 4. This part installation makes the airplane a Group 2 airplane and terminates the inspection requirements in this AD. (i) NLG Wheel Axle Attachment Screw Replacement For Group 1 and Group 2 Airplanes Replace the NLG wheel axle attachment screws in accordance with paragraph C.2 of Daher SB 150, Revision 4, as follows: (1) If no screw is found to be distorted, scratched, nicked, or worn during any repetitive inspection required by paragraph (h)(1) of this AD, replace all of the NLG wheel axle attachment screws as follows: (i) Initially before exceeding 2,000 hours TIS total on the airplane; before exceeding 2,000 hours TIS since the last time the attachment screws were replaced; or within 50 hours TIS after the effective date of this AD, whichever occurs later; and (ii) Repetitively thereafter at intervals not to exceed 2,000 hours TIS after the last replacement. (2) If any screw is found to be distorted, scratched, nicked, or worn during any repetitive inspection required by paragraph (h)(1) of this AD, replace that screw before further flight. (j) Installation Prohibition For Group 1 and Group 2 Airplanes As of the effective date of this AD, do not install an affected NLG wheel axle, as defined in this AD, on any airplane, unless the criteria in paragraphs (j)(1) and (2) of this AD are met: (1) The affected NLG wheel axle is found to be free of chafing and cracking per the inspection required by paragraph (h)(1) of this AD and free of damage per the inspection required by paragraph (h)(3) of this AD. (2) The NLG wheel axle attachment screws are replaced with new screws. (k) Credit for Previous Actions You may take credit for the initial actions required by paragraphs (h) and (i) of this AD if you performed those actions before the effective date of this AD using SOCATA SB 150, Revision 2; or Daher-SOCATA SB 150, Revision 3. (l) Alternative Methods of Compliance (AMOCs) The Manager, International Validation 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 International Validation Branch, mail it to the address identified in paragraph (m)(1) of this AD or email to: AMOC@faa.gov. If mailing information, also submit information by email. Before using any approved AMOC, notify your appropriate principal inspector, or lacking a principal inspector, the manager of the local Flight Standards Office. (m) Additional Information (1) For more information about this AD, contact Fred Guerin, Aviation Safety Engineer, FAA, 1600 Stewart Avenue, Suite 410, Westbury, NY 11590; phone: (206) 231-2346; email: fred.guerin@faa.gov. (2) Material identified in this AD that is not incorporated by reference is available at the address specified in paragraph (n)(3) of this AD. (n) Material Incorporated by Reference (1) The Director of the Federal Register approved the incorporation by reference (IBR) of the material listed in this paragraph under 5 U.S.C. 552(a) and 1 CFR part 51. (2) You must use this material as applicable to do the actions required by this AD, unless the AD specifies otherwise. (i) Daher Service Bulletin SB 150, Revision 4, dated January 2023. (ii) [Reserved] (3) For Daher Aerospace material identified in this AD, contact Daher Aerospace, Customer Support, Airplane Division, 65921 Tarbes Cedex 9, France; phone: 33 (0)5 62.41.73.00; email: tbmcare@daher.com; website: daher.com. (4) You may view this material at the FAA, Airworthiness Products Section, Operational Safety Branch, 901 Locust, Kansas City, MO 64106. For information on the availability of this material at the FAA, call (817) 222-5110. (5) You may view this material at the National Archives and Records Administration (NARA). For information on the availability of this material at NARA, visit www.archives.gov/federal-register/cfr/ibr-locations or email fr.inspection@nara.gov . Issued on October 10, 2024. Steven W. Thompson, Acting Deputy Director, Compliance & Airworthiness Division, Aircraft Certification Service. [FR Doc. 2024-24368 Filed 10-21-24; 8:45 am]BILLING CODE 4910-13-P