AD 2021-10-11

The FAA is adopting a new airworthiness directive (AD) for all The Boeing Company Model 737-100, -200, -200C, -300, -400, and -500 series airplanes. This AD was prompted by a report indicating that a crack was found on the splice angle flange that is attached to the station (STA) 540 bulkhead in the area between certain stringers. This AD requires repetitive surface high frequency eddy current (HFEC) inspections at the radius of the left- and right-side of the STA 540 bulkhead splice angle for any cracking, and applicable on-condition actions. The FAA is issuing this AD to address the unsafe condition on these products.

Final rule.

The Amendment \n\n\n\tAccordingly, under the authority delegated to me by the Administrator, the FAA amends 14 CFR part 39 as follows: \n\nPART 39--AIRWORTHINESS DIRECTIVES \n\n0 1. The authority citation for part 39 continues to read as follows: \n\n\n\tAuthority: 49 U.S.C. 106(g), 40113, 44701. \n\n((Page 33103)) \n\nSec. 39.13 (Amended) \n\n0 2. The FAA amends Sec. 39.13 by adding the following new airworthiness directive: \n\n2021-10-11 The Boeing Company: Amendment 39-21544; Docket No. FAA- 2021-0026 Project Identifier AD-2020-01164-T. \n\n(a) Effective Date \n\n\n\tThis airworthiness directive (AD) is effective July 29, 2021. \n\n(b) Affected ADs \n\n\n\tNone. \n\n(c) Applicability \n\n\n\t(1) This AD applies to all The Boeing Company Model 737-100, - 200, -200C, -300, -400, and -500 series airplanes, certificated in any category. \n\t(2) Installation of Supplemental Type Certificate (STC) ST01219SE does not affect the ability to accomplish the actions required by this AD. Therefore, for airplanes on which STC ST01219SE is installed, a ''change in product'' alternative method of compliance (AMOC) approval request is not necessary to comply with the requirements of 14 CFR 39.17. \n\n(d) Subject \n\n\n\tAir Transport Association (ATA) of America Code 57, Wings. \n\n(e) Unsafe Condition \n\n\n\tThis AD was prompted by a report indicating that a crack was found on the splice angle flange that is attached to the station (STA) 540 bulkhead in the area between stringer 21 to stringer 22. The FAA is issuing this AD to address any cracking in the splice angle, which could result in the inability of a principal structural element to sustain limit load and could adversely affect the structural integrity of the airplane; in addition, such cracking could lead to adjoining parts cracking and a potential fuel leak and consequent fire. \n\n(f) Compliance \n\n\n\tComply with this AD within the compliance times specified, unless already done. \n\n(g) Required Actions \n\n\n\t(1) Forairplanes identified as Group 1 in Boeing Alert Requirements Bulletin 737-57A1347 RB, dated July 29, 2020: Within 120 days after the effective date of this AD, inspect the airplane and do all applicable on-condition actions using a method approved in accordance with the procedures specified in paragraph (i) of this AD. \n\t(2) For airplanes identified as Group 2 in Boeing Alert Requirements Bulletin 737-57A1347 RB, dated July 29, 2020: Except as specified by paragraph (h) of this AD, at the applicable times specified in the ''Compliance'' paragraph of Boeing Alert Requirements Bulletin 737-57A1347 RB, dated July 29, 2020, do all applicable actions identified in, and in accordance with, the Accomplishment Instructions of Boeing Alert Requirements Bulletin 737-57A1347 RB, dated July 29, 2020. \n\tNote 1 to paragraph (g): Guidance for accomplishing the actions required by this AD can be found in Boeing Alert Service Bulletin 737-57A1347, dated July 29, 2020, which is referred to in Boeing Alert Requirements Bulletin 737-57A1347 RB, dated July 29, 2020. \n\n(h) Exceptions to Service Information Specifications \n\n\n\t(1) Where Boeing Alert Requirements Bulletin 737-57A1347 RB, dated July 29, 2020, uses the phrase ''the original issue date of Requirements Bulletin 737-57A1347 RB,'' this AD requires using ''the effective date of this AD.'' \n\t(2) Where Boeing Alert Requirements Bulletin 737-57A1347 RB, dated July 29, 2020, specifies contacting Boeing for repair instructions: This AD requires doing the repair using a method approved in accordance with the procedures specified in paragraph (i) of this AD. \n\n(i) Alternative Methods of Compliance (AMOCs) \n\n\n\t(1) The Manager, Los Angeles ACO 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 tothe manager of the certification office, send it to the attention of the person identified in paragraph (j)(1) of this AD. Information may be emailed to: 9-ANM-LAACO-AMOC-Requests@faa.gov. \n\t(2) Before using any approved AMOC, notify your appropriate principal inspector, or lacking a principal inspector, the manager of the responsible Flight Standards Office. \n\t(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, Los Angeles ACO 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. \n\n(j) Related Information \n\n\n\t(1) For more information about this AD, contact Wayne Ha, Aerospace Engineer, Airframe Section, FAA,Los Angeles ACO Branch, 3960 Paramount Boulevard, Lakewood, CA 90712-4137; phone: 562-627- 5238; fax: 562-627-5210; email: Wayne.Ha@faa.gov. \n\t(2) Service information identified in this AD that is not incorporated by reference is available at the addresses specified in paragraphs (k)(3) and (4) of this AD. \n\n(k) Material Incorporated by Reference \n\n\n\t(1) The Director of the Federal Register approved the incorporation by reference (IBR) of the service information listed in this paragraph under 5 U.S.C. 552(a) and 1 CFR part 51. \n\t(2) You must use this service information as applicable to do the actions required by this AD, unless the AD specifies otherwise. \n\t(i) Boeing Alert Requirements Bulletin 737-57A1347 RB, dated July 29, 2020. \n\t(ii) (Reserved) \n\t(3) For service information identified in this AD, 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; internet https://www.myboeingfleet.com. \n\t(4) You may view this service information at the FAA, Airworthiness Products Section, Operational Safety Branch, 2200 South 216th St., Des Moines, WA. For information on the availability of this material at the FAA, call 206-231-3195. \n\t(5) You may view this service information that is incorporated by reference at the National Archives and Records Administration (NARA). For information on the availability of this material at NARA, email fedreg.legal@nara.gov, or go to: https://www.archives.gov/federal-register/cfr/ibr-locations.html. \n\n\n\tIssued on April 30, 2021. Lance T. Gant, Director, Compliance & Airworthiness Division, Aircraft Certification Service. (FR Doc. 2021-13122 Filed 6-23-21; 8:45 am) BILLING CODE 4910-13-P

Background \n\n\n\tThe FAA issued a notice of proposed rulemaking (NPRM) to amend 14 CFR part 39 by adding an AD that would apply to all The Boeing Company Model 737-100, -200, -200C, -300, -400, and -500 series airplanes. The NPRM published in the Federal Register on February 24, 2021 (86 FR 11186). The NPRM was prompted by a report indicating that a crack was found on the splice angle flange that is attached to the STA 540 bulkhead in the area between certain stringers. In the NPRM, the FAA proposed to require repetitive surface HFEC inspections at the radius of the left- and right-side of the STA 540 bulkhead splice angle for any cracking, and applicable on-condition actions. The FAA is issuing this AD to address any cracking in the splice angle, which could result in the inability of a principal structural element to sustain limit load and could adversely affect the structural integrity of the airplane; in addition, such cracking could lead to \n\n((Page 33102)) \n\nadjoining parts cracking and a potential fuel leak and consequent fire. \n\nDiscussion of Final Airworthiness Directive \n\nComments \n\n\n\tThe FAA received a comment from Boeing who supported the NPRM without change. \n\tThe FAA also received an additional comment from Aviation Partners Boeing. \n\nEffect of Winglets on Accomplishment of the Proposed Actions \n\n\n\tAviation Partners Boeing stated that accomplishing Supplemental Type Certificate (STC) ST01219SE does not affect the actions specified in the proposed AD. \n\tThe FAA concurs with the commenter. The FAA has redesignated paragraph (c) of the proposed AD as paragraph (c)(1) of this AD and added paragraph (c)(2) to this AD to state that installation of STC ST01219SE does not affect the ability to accomplish the actions required by this AD. Therefore, for airplanes on which STC ST01219SE is installed, a ''change in product'' alternative method of compliance (AMOC) approval request is not necessary to comply with the requirements of 14 CFR 39.17. \n\nConclusion \n\n\n\tThe FAA reviewed the relevant data, considered any comments received, and determined that air safety requires adopting this AD as proposed. Accordingly, the FAA is issuing this AD to address the unsafe condition on these products. Except for minor editorial changes, and any other changes described previously, this AD is adopted as proposed in the NPRM. None of the changes will increase the economic burden on any operator. \n\nRelated Service Information Under 1 CFR Part 51 \n\n\n\tThe FAA reviewed Boeing Alert Requirements Bulletin 737-57A1347 RB, dated July 29, 2020. The service information describes procedures for repetitive surface HFEC inspections at the radius of the left- and right-side of the STA 540 bulkhead splice angle for any cracking, and applicable on-condition actions. On-condition actions include repair or replacement. This service information is reasonably available because the interested parties have access to it through their normal course of business or by the means identified in ADDRESSES. \n\nCosts of Compliance \n\n\n\tThe FAA estimates that this AD affects 117 airplanes of U.S. registry. The FAA estimates the following costs to comply with this AD: \n\n\n\tEstimated Costs for Required Actions ---------------------------------------------------------------------------------------------------------------- \n\tCost on U.S. \n\tAction Labor cost Parts cost Cost per product operators ---------------------------------------------------------------------------------------------------------------- Repetitive surface HFEC 7 work-hour x $85 $0 $595 per inspection $69,615 per \n\tinspections. per hour = $595 cycle. inspection cycle. \n\tper inspection \n\tcycle. ---------------------------------------------------------------------------------------------------------------- \n\n\n\tThe FAAestimates the following costs to do any necessary on- condition actions that would be required. The FAA has no way of determining the number of aircraft that might need these on-condition actions: \n\n\n\tEstimated Costs of On-Condition Actions ------------------------------------------------------------------------ \n\tLabor cost Parts cost Cost per product ------------------------------------------------------------------------ Up to 53 work-hour x $85 per Up to $1,000........... Up to $5,505. \n\thour = Up to $4,505 \n\t(replacement). ------------------------------------------------------------------------ \n\n\n\tThe FAA has received no definitive data on which to base the cost estimates for the on-condition repair specified in this AD. \n\nAuthority for This Rulemaking \n\n\n\tTitle 49 of the United States Code specifies the FAA's authority to issue rules on aviation safety. Subtitle I, section 106, describes the authority of the FAA Administrator. Subtitle VII: Aviation Programs, describes in more detail the scope of the Agency's authority. \n\tThe FAA is issuing this rulemaking under the authority described in Subtitle VII, Part A, Subpart III, Section 44701: General requirements. Under that section, Congress charges the FAA with promoting safe flight of civil aircraft in air commerce by prescribing regulations for practices, methods, and procedures the Administrator finds necessary for safety in air commerce. This regulation is within the scope of that authority because it addresses an unsafe condition that is likely to exist or develop on products identified in this rulemaking action. \n\nRegulatory Findings \n\n\n\tThis AD will not have federalism implications under Executive Order 13132. This AD will not have a substantial direct effect on the States, on the relationship between the national government and the States, or on the distribution of power and responsibilities among the various levels of government. \n\tFor the reasons discussed above, I certify that this AD: \n\t(1) Is not a ''significant regulatory action'' under Executive Order 12866, \n\t(2) Will not affect intrastate aviation in Alaska, and \n\t(3) Will not have a significant economic impact, positive or negative, on a substantial number of small entities under the criteria of the Regulatory Flexibility Act. \n\nList of Subjects in 14 CFR Part 39 \n\n\n\tAir transportation, Aircraft, Aviation safety, Incorporation by reference, Safety.