2024-03-04: Flight controls

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: 2024-03-04 The Boeing Company: Amendment 39-22673; Docket No. FAA-2024-0224; Project Identifier AD-2024-00055-T. (a) Effective Date This airworthiness directive (AD) is effective February 12, 2024. (b) Affected ADs None. (c) Applicability This AD applies to The Boeing Company Model 737-8, 737-8200, and 737-9 airplanes, certificated in any category, with an original airworthiness certificate or original export certificate of airworthiness issued on or before December 20, 2023. (d) Subject Air Transport Association (ATA) of America Code 27, Flight controls. (e) Unsafe Condition This AD was prompted by a report of a missing washer and nut and consequent migrated bolt discovered by an operator during scheduled maintenance. The FAA is issuing this AD to address improper torque of the aft rudder quadrant output rod fasteners, which may cause a disconnect between the aft rudder quadrant and the output rod, which would result in loss of rudder control via the rudder pedals to counter an engine-out scenario during takeoff/climb out or to counter a high crosswind during landing. The unsafe condition, if not addressed, could result in loss of continued safe flight and landing. (f) Compliance Comply with this AD within the compliance times specified, unless already done. (g) Inspection Within 30 days after the effective date of this AD, perform a one-time detailed visual inspection or remote video inspection of the aft rudder quadrant for missing bolts, nuts, and washers; a gap between the bolt/nut/washer and quadrant; and insufficient thread protrusion. Note 1 to paragraph (g): Guidance for accomplishing the actions required by paragraph (g) of this AD can be found in Boeing Multi Operator Message MOM-MOM-23-0993-01B, dated December 27, 2023. (h) On-Condition Actions If any discrepancy is found during the inspection required by paragraph (g) of this AD, do the actions specified in paragraphs (h)(1) through (3) of this AD before further flight. (1) Do a detailed inspection of the bolt, washer, and nut for damage and, before further flight, replace any missing or damaged bolts, washers, and nuts. (2) Install each bolt, washer, and nut with a torque of 65 in-lb. (3) Perform a rudder travel test to ensure that the rudder is operating correctly. If the test fails, before further flight, do applicable corrective actions and repeat until the test is passed. Note 2 to paragraph (h) of this AD: Guidance for accomplishing the actions required by paragraph (h) of this AD can be found in Boeing Multi Operator Message MOM-MOM-23-0993-01B, dated December 27, 2023. (i) Credit for Previous Actions This paragraph provides credit for the actions specified in paragraphs (g) and (h) of this AD, if those actions were performed before the effective date of this AD using Boeing Multi Operator Message MOM-MOM-23-0993-01B, dated December 27, 2023. (j) Alternative Methods of Compliance (AMOCs) (1) The Manager, AIR-520, Continued 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 responsible Flight Standards Office, as appropriate. If sending information directly to the manager of the certification office, send it to the attention of the person identified in paragraph (k)(1) of this AD. Information may be emailed to: [email protected]. (2) Before using any approved AMOC, notify your appropriate principal inspector, or lacking a principal inspector, the manager of the responsible Flight Standards Office. (3) An AMOC that provides an acceptable level of safety may be used for any repair, modification, or alteration required by this AD if it is approved by The Boeing Company Organization Designation Authorization (ODA) that has been authorized by the Manager, AIR-520, Continued Operational Safety Branch, FAA, to make those findings. To be approved, the repair method, modification deviation, or alteration deviation must meet the certification basis of the airplane, and the approval must specifically refer to this AD. (k) Related Information (1) For more information about this AD, contact Anthony Caldejon, Aviation Safety Engineer, FAA, 2200 South 216th St., Des Moines, WA 98198; phone: 206-231-3534; email: [email protected]. (2) For service information identified in this AD that is not incorporated by reference, contact Boeing Commercial Airplanes, Attention: Contractual & Data Services (C&DS), 2600 Westminster Blvd., MC 110-SK57, Seal Beach, CA 90740-5600; telephone 562-797-1717; website myboeingfleet.com . (l) Material Incorporated by Reference None. Issued on February 2, 2024. Caitlin Locke, Director, Compliance & Airworthiness Division, Aircraft Certification Service. [FR Doc. 2024-02930 Filed 2-8-24; 2:00 pm]BILLING CODE 4910-13-P