Airworthiness Directives; The Boeing Company Airplanes, 3246-3250 [2022-01014]

Download as PDF 3246 Federal Register / Vol. 87, No. 14 / Friday, January 21, 2022 / Proposed Rules 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. Regulatory Findings The FAA determined that this proposed AD would not have federalism implications under Executive Order 13132. This proposed AD would 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. For the reasons discussed above, I certify this proposed regulation: (1) Is not a ‘‘significant regulatory action’’ under Executive Order 12866, (2) Would not affect intrastate aviation in Alaska, and (3) Would not have a significant economic impact, positive or negative, on a substantial number of small entities under the criteria of the Regulatory Flexibility Act. List of Subjects in 14 CFR Part 39 Air transportation, Aircraft, Aviation safety, Incorporation by reference, Safety. The Proposed Amendment Accordingly, under the authority delegated to me by the Administrator, the FAA proposes to amend 14 CFR part 39 as follows: PART 39—AIRWORTHINESS DIRECTIVES 1. The authority citation for part 39 continues to read as follows: ■ Authority: 49 U.S.C. 106(g), 40113, 44701. § 39.13 [Amended] 2. The FAA amends § 39.13 by adding the following new airworthiness directive: ■ jspears on DSK121TN23PROD with PROPOSALS1 Bell Textron Inc.: Docket No. FAA–2022– 0006; Project Identifier AD–2021–01298– R. (a) Comments Due Date The FAA must receive comments on this airworthiness directive (AD) by March 7, 2022. (b) Affected ADs None. (c) Applicability This AD applies to the following Bell Textron Inc. helicopters certificated in any VerDate Sep<11>2014 17:13 Jan 20, 2022 Jkt 256001 category, with a tailboom left hand fin spar cap (spar cap) part number 212–030–447–117 installed. (1) Model 205A and 205A–1 helicopters, serial number (S/N) 30001 through 30065 inclusive, 30067 through 30165 inclusive, 30167 through 30187 inclusive, 30189 through 30296 inclusive, and 30298 through 30332 inclusive; (2) Model 205B helicopters, S/N 30066, 30166, 30188, and 30297; (3) Model 210 helicopters, all S/Ns; (4) Model 212 helicopters, S/N 30502 through 30603 inclusive, 30611 through 30999 inclusive, 31101 through 31311 inclusive, 32101 through 32142 inclusive, and 35001 through 35103 inclusive; (5) Model 412 and 412EP helicopters, S/N 33001 through 33213 inclusive, 34001 through 34036 inclusive, 36001 through 36999 inclusive, 37002 through 37999 inclusive, 38001 through 38999 inclusive, and 39101 through 39999 inclusive; and (6) Model 412CF helicopters, S/N 46400 through 46499 inclusive. (d) Subject Joint Aircraft System Component (JASC) Code 5302, Rotorcraft Tail Boom. (e) Unsafe Condition This AD was prompted by the discovery of fatigue cracking in the spar cap. A crack in the spar cap, if not detected and corrected, could create stress concentrations at the edge of the rivet holes, resulting in reduced structural integrity of the helicopter and subsequent loss of control of the helicopter. The FAA is issuing this AD to detect and prevent this unsafe condition. (f) Compliance Comply with this AD within the compliance times specified, unless already done. (g) Required Actions Within 100 hours time-in-service (TIS) after the effective date of this AD, and thereafter at intervals not to exceed 100 hours TIS: (1) Using a 10x or higher power magnifying glass and a flashlight, inspect both flanges of the spar cap between fin station (F.S.) 50 and F.S. 71 for any crack, loose rivet, and other damage such as a scratch, dent, spalling, or corrosion, as depicted in Figure 1 of Bell Alert Service Bulletin (ASB) 205–20–116, ASB 205B–20–69, ASB 210–20–13, ASB 212– 20–162, ASB 412–20–180, or ASB 412CF– 20–67, each dated April 15, 2020, as applicable to your helicopter. If either spar cap flange is cracked, has a loose rivet, or has other damage, remove the spar cap from service before further flight. (2) Inspect the exterior of the fin skin in the area that contacts the spar cap for any crack, loose rivets, and distortion. If there is any crack, loose rivet, or distortion in the fin skin in the area that contacts the spar cap, remove the spar cap from service before further flight. (h) Alternative Methods of Compliance (AMOCs) (1) The Manager, DSCO Branch, FAA, has the authority to approve AMOCs for this AD, PO 00000 Frm 00018 Fmt 4702 Sfmt 4702 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 certification office, send it to the attention of the person identified in Related Information. (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. (i) Related Information (1) For more information about this AD, contact Ameet Shrotriya, Aviation Safety Engineer, DSCO Branch, Compliance & Airworthiness Division, FAA, 10101 Hillwood Pkwy., Fort Worth, TX 76177– 1524; phone: (817) 222–5525; email: Ameet.Shrotriya@faa.gov. (2) For service information identified in this AD, contact Bell Textron, Inc., P.O. Box 482, Fort Worth, TX 76101; telephone 1–450– 437–2862 or 1–800–363–8023; fax 1–450– 433–0272; email productsupport@ bellflight.com; or at https:// www.bellflight.com/support/contact-support. You may view this referenced service information at the FAA, Office of the Regional Counsel, Southwest Region, 10101 Hillwood Pkwy., Room 6N–321, Fort Worth, TX 76177. For information on the availability of this material at the FAA, call (817) 222– 5110. Issued on January 11, 2022. Gaetano A. Sciortino, Deputy Director for Strategic Initiatives, Compliance & Airworthiness Division, Aircraft Certification Service. [FR Doc. 2022–00886 Filed 1–20–22; 8:45 am] BILLING CODE 4910–13–P DEPARTMENT OF TRANSPORTATION Federal Aviation Administration 14 CFR Part 39 [Docket No. FAA–2021–1073; Project Identifier AD–2021–01252–T] RIN 2120–AA64 Airworthiness Directives; The Boeing Company Airplanes Federal Aviation Administration (FAA), DOT. ACTION: Notice of proposed rulemaking (NPRM). AGENCY: The FAA proposes to supersede Airworthiness Directive (AD) 2017–24–10, which applies to certain The Boeing Company Model 757–200, –200PF, and –300 series airplanes. AD 2017–24–10 requires repetitive inspections for any cracking of a certain fuselage frame inner chord; identification of the material of a certain fuselage frame inner chord for certain SUMMARY: E:\FR\FM\21JAP1.SGM 21JAP1 Federal Register / Vol. 87, No. 14 / Friday, January 21, 2022 / Proposed Rules airplanes; and applicable corrective actions. Since the FAA issued AD 2017– 24–10, the FAA has received reports of new crack findings outside of the AD 2017–24–10 inspection area, which the existing inspections will not detect. This proposed AD would continue to require the actions in AD 2017–24–10, would add new airplanes and would require new inspection types in certain areas, an expanded inspection area, additional inspections, and applicable corrective actions. The FAA is proposing this AD to address the unsafe condition on these products. DATES: The FAA must receive comments on this proposed AD by March 7, 2022. ADDRESSES: You may send comments, using the procedures found in 14 CFR 11.43 and 11.45, by any of the following methods: • Federal eRulemaking Portal: Go to https://www.regulations.gov. Follow the instructions for submitting comments. • Fax: 202–493–2251. • Mail: U.S. Department of Transportation, Docket Operations, M– 30, West Building Ground Floor, Room W12–140, 1200 New Jersey Avenue SE, Washington, DC 20590. • Hand Delivery: Deliver to Mail address above between 9 a.m. and 5 p.m., Monday through Friday, except Federal holidays. For service information identified in this NPRM, 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. 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. It is also available at https:// www.regulations.gov by searching for and locating Docket No. FAA–2021– 1073. jspears on DSK121TN23PROD with PROPOSALS1 Examining the AD Docket You may examine the AD docket at https://www.regulations.gov by searching for and locating Docket No. FAA–2021–1073; or in person at Docket Operations between 9 a.m. and 5 p.m., Monday through Friday, except Federal holidays. The AD docket contains this NPRM, any comments received, and other information. The street address for Docket Operations is listed above. FOR FURTHER INFORMATION CONTACT: Peter Jarzomb, Aerospace Engineer, Airframe Section, FAA, Los Angeles ACO Branch, 3960 Paramount VerDate Sep<11>2014 17:13 Jan 20, 2022 Jkt 256001 Boulevard, Lakewood, CA 90712–4137; phone: 562–627–5234; email: peter.jarzomb@faa.gov. SUPPLEMENTARY INFORMATION: Comments Invited The FAA invites you to send any written relevant data, views, or arguments about this proposal. Send your comments to an address listed under ADDRESSES. Include ‘‘Docket No. FAA–2021–1073; Project Identifier AD– 2021–01252–T’’ at the beginning of your comments. The most helpful comments reference a specific portion of the proposal, explain the reason for any recommended change, and include supporting data. The FAA will consider all comments received by the closing date and may amend the proposal because of those comments. Except for Confidential Business Information (CBI) as described in the following paragraph, and other information as described in 14 CFR 11.35, the FAA will post all comments received, without change, to https:// www.regulations.gov, including any personal information you provide. The agency will also post a report summarizing each substantive verbal contact received about this proposed AD. Confidential Business Information CBI is commercial or financial information that is both customarily and actually treated as private by its owner. Under the Freedom of Information Act (FOIA) (5 U.S.C. 552), CBI is exempt from public disclosure. If your comments responsive to this NPRM contain commercial or financial information that is customarily treated as private, that you actually treat as private, and that is relevant or responsive to this NPRM, it is important that you clearly designate the submitted comments as CBI. Please mark each page of your submission containing CBI as ‘‘PROPIN.’’ The FAA will treat such marked submissions as confidential under the FOIA, and they will not be placed in the public docket of this NPRM. Submissions containing CBI should be sent to Peter Jarzomb, Aerospace Engineer, Airframe Section, FAA, Los Angeles ACO Branch, 3960 Paramount Boulevard, Lakewood, CA 90712–4137; phone: 562–627–5234; email: peter.jarzomb@faa.gov. Any commentary that the FAA receives which is not specifically designated as CBI will be placed in the public docket for this rulemaking. Background The FAA issued AD 2017–24–10, Amendment 39–19114 (82 FR 57343, PO 00000 Frm 00019 Fmt 4702 Sfmt 4702 3247 December 5, 2017) (AD 2017–24–10), for certain The Boeing Company Model 757–200, –200PF, and –300 series airplanes. AD 2017–24–10 was prompted by reports of cracking found at a certain fuselage frame inner chord. AD 2017–24–10 requires repetitive inspections for any cracking of a certain fuselage frame inner chord; identification of the material of a certain fuselage frame inner chord for certain airplanes; and applicable corrective actions. The agency issued AD 2017– 24–10 to detect and correct such cracks, which could result in the cargo door opening during flight, and result in rapid decompression of the airplane and the inability to sustain loads required for continued safe flight and landing. Actions Since AD 2017–24–10 Was Issued Since the FAA issued AD 2017–24– 10, the FAA has received reports of new crack findings outside of the AD 2017– 24–10 inspection area, which the existing inspections will not detect. An operator was accomplishing Boeing Alert Service Bulletin 757–53A0101, dated November 8, 2016, which is the service information required by AD 2017–24–10) on a certain The Boeing Company Model 757–200 airplane and found four cracks ranging from 0.10 to 2.00 inches in length in the station (STA) 1380 frame web and two cracks ranging from 1.00 to 2.12 inches in length in the frame inner chord. The airplane had 23,005 total flight cycles at the time of the crack findings. The frame web was made from 0.09 inch thick 2024–T3 aluminum, and the inner chord was made from 7075–T73 aluminum. Based on the length of the crack in the web at the time of discovery, the cracks in the frame may have initiated in the 2024–T3 web, and would have been hidden behind the guide track fitting. If the cracks start in the frame web, existing Maintenance Planning Data (MPD) and Boeing Alert Service Bulletin 757–53A0101, dated November 8, 2016, inspections do not provide sufficient opportunities to find cracks in the STA 1380 frame before the critical crack length is reached, resulting in an airplane-level safety issue. In addition, the FAA has received five reports of crack findings in airplanes with production line numbers 1–57, which are made with 7075 material for the inner and outer chord and the frame web. Those airplanes may also have a thinner web gauge than that in airplanes with line numbers 58 and subsequent. Existing inspections for these airplanes do not remove the guide track fitting at STA 1380, and therefore do not provide sufficient opportunity to detect cracks E:\FR\FM\21JAP1.SGM 21JAP1 3248 Federal Register / Vol. 87, No. 14 / Friday, January 21, 2022 / Proposed Rules before the critical crack length is reached. The root cause for the cracking in the STA 1380 frame inner chord and web under the roller guide track fitting is attributed to the out-of-plane bending stress induced from a mis-rigging condition of the No. 2 cargo door, which allows the roller pin on the lower cargo door to contact the roller guide track fitting. The new proposed repetitive inspections include removing the guide track fitting to inspect for any crack. The FAA is issuing this AD to detect and correct such cracks, which could result in rapid decompression of the airplane and the inability to sustain loads required for continued safe flight and landing. FAA’s Determination The FAA is issuing this NPRM after determining that the unsafe condition described previously is likely to exist or develop on other products of the same type design. Related Service Information Under 1 CFR Part 51 The FAA reviewed Boeing Alert Requirements Bulletin 757–53A0118 RB, dated October 22, 2021. This service information specifies procedures for a general visual inspection or a maintenance records check of the STA 1380 frame for any repair, and repetitive surface high frequency eddy current (HFEC) inspections of the STA 1380 frame inner chord and frame web for any cracking, repetitive sub-surface low frequency eddy current (LFEC) inspections of the STA 1380 frame inner chord for any cracking, and applicable corrective actions. Corrective actions include repair. This AD would also require Boeing Alert Service Bulletin 757–53A0101, dated November 8, 2016, which the Director of the Federal Register approved for incorporation by reference as of January 9, 2018 (82 FR 57343, December 5, 2017). 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 the ADDRESSES section. Proposed AD Requirements in This NPRM area, additional inspections, and applicable corrective actions. This proposed AD would require accomplishment of the actions identified in Boeing Alert Requirements Bulletin 757–53A0118 RB, dated October 22, 2021, described previously, except for any differences identified as exceptions in the regulatory text of this proposed AD. Accomplishment of the applicable initial inspections and corrective actions specified in the Accomplishment Instructions of Boeing Alert Requirements Bulletin 757– 53A0118 RB, dated October 22, 2021, terminates the inspections required by paragraphs (g) and (h) of this proposed AD. For information on the procedures and compliance times, see this service information at https:// www.regulations.gov by searching for and locating Docket No. FAA–2021– 1073. Costs of Compliance This proposed AD would retain all requirements of AD 2017–24–10. This proposed AD would add new airplanes and would require new inspection types in certain areas, an expanded inspection The FAA estimates that this AD, if adopted as proposed, would affect 477 airplanes of U.S. registry. The FAA estimates the following costs to comply with this proposed AD: ESTIMATED COSTS Cost on U.S. operators 0 $425 per inspection cycle. Up to $170 .................... $202,725 per inspection cycle. Up to $81,090. 0 $510 .............................. $243,270. 0 Up to $850 per inspection cycle. Up to $510 per inspection cycle. Up to $405,450 per inspection cycle. Up to $243,270 per inspection cycle. Up to $510 per inspection cycle. Up to $243,270 per inspection cycle. Labor cost Surface HFEC inspection (retained actions from AD 2017–24–10). Identify the material (retained actions from AD 2017–24–10). General visual inspection (new proposed action). Surface frame inner chord HFEC inspection (new proposed action). Sub-surface frame inner chord LFEC inspection (new proposed action). Surface HFEC frame web inspection (new proposed action). 5 work-hours × $85 per hour = $425 per inspection cycle. Up to 2 work-hours × $85 per hour = $170. 6 work-hours × $85 per hour = $510. Up to 10 work-hours × $85 per hour = $850 per inspection cycle. Up to 6 work-hours × $85 per hour = $510 per inspection cycle. $0 Up to 6 work-hours × $85 per hour = $510 per inspection cycle. 0 The FAA has received no definitive data on which to base the cost estimates for the on-condition repairs specified in this proposed AD. Authority for This Rulemaking jspears on DSK121TN23PROD with PROPOSALS1 Cost per product Action Title 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. The FAA is issuing this rulemaking under the authority described in VerDate Sep<11>2014 17:13 Jan 20, 2022 Jkt 256001 Parts cost 0 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. PO 00000 Frm 00020 Fmt 4702 Sfmt 4702 Regulatory Findings The FAA has determined that this proposed AD would not have federalism implications under Executive Order 13132. This proposed AD would 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. For the reasons discussed above, I certify that the proposed regulation: (1) Is not a ‘‘significant regulatory action’’ under Executive Order 12866, E:\FR\FM\21JAP1.SGM 21JAP1 Federal Register / Vol. 87, No. 14 / Friday, January 21, 2022 / Proposed Rules (2) Would not affect intrastate aviation in Alaska, and (3) Would not have a significant economic impact, positive or negative, on a substantial number of small entities under the criteria of the Regulatory Flexibility Act. List of Subjects in 14 CFR Part 39 Air transportation, Aircraft, Aviation safety, Incorporation by reference, Safety. The Proposed Amendment Accordingly, under the authority delegated to me by the Administrator, the FAA proposes to amend 14 CFR part 39 as follows: PART 39—AIRWORTHINESS DIRECTIVES 1. The authority citation for part 39 continues to read as follows: ■ Authority: 49 U.S.C. 106(g), 40113, 44701. § 39.13 [Amended] 2. The FAA amends § 39.13 by: a. Removing Airworthiness Directive (AD) 2017–24–10, Amendment 39– 19114 (82 FR 57343, December 5, 2017), and ■ b. Adding the following new AD: ■ ■ The Boeing Company: Docket No. FAA– 2021–1073; Project Identifier AD–2021– 01252–T. (a) Comments Due Date The FAA must receive comments on this airworthiness directive (AD) action by March 7, 2022. (b) Affected ADs This AD replaces AD 2017–24–10, Amendment 39–19114 (82 FR 57343, December 5, 2017) (AD 2017–24–10). (c) Applicability This AD applies to all The Boeing Company Model 757–200, –200PF, –200CB, and –300 series airplanes, certificated in any category. jspears on DSK121TN23PROD with PROPOSALS1 (d) Subject Air Transport Association (ATA) of America Code 53, Fuselage. (e) Unsafe Condition This AD was prompted by reports of cracking found at the fuselage station (STA) 1380 frame inner chord and by reports of new crack findings outside of the AD 2017– 24–10 inspection area, which the existing inspections will not detect. The FAA is issuing this AD to detect and correct such cracks, which could result in rapid decompression of the airplane and the inability to sustain loads required for continued safe flight and landing. (f) Compliance Comply with this AD within the compliance times specified, unless already done. VerDate Sep<11>2014 17:13 Jan 20, 2022 Jkt 256001 (g) Retained Inspection for Group 1 Airplanes, With No Changes This paragraph restates the requirements of paragraph (g) of AD 2017–24–10, with no changes. For Group 1 airplanes as identified in Boeing Alert Service Bulletin 757– 53A0101, dated November 8, 2016: At the applicable time specified in paragraph 1.E., ‘‘Compliance,’’ of Boeing Alert Service Bulletin 757–53A0101, dated November 8, 2016; except as specified in paragraph (i)(1) of this AD, do a surface high frequency eddy current (HFEC) inspection for any cracking of the fuselage STA 1380 frame inner chord, and do all applicable corrective actions, in accordance with the Accomplishment Instructions of Boeing Alert Service Bulletin 757–53A0101, dated November 8, 2016; except as specified in paragraph (i)(2) of this AD. Do all applicable corrective actions before further flight. Repeat the surface HFEC inspection, thereafter, at the times specified in paragraph 1.E., ‘‘Compliance,’’ of Boeing Alert Service Bulletin 757–53A0101, dated November 8, 2016. (h) Retained Inspection for Group 2 Airplanes, With No Changes This paragraph restates the requirements of paragraph (h) of AD 2017–24–10, with no changes. For Group 2 airplanes as identified in Boeing Alert Service Bulletin 757– 53A0101, dated November 8, 2016: At the applicable time specified in paragraph 1.E., ‘‘Compliance,’’ of Boeing Alert Service Bulletin 757–53A0101, dated November 8, 2016, except as specified in paragraph (i)(1) of this AD, identify the material of the fuselage STA 1380 frame inner chord, in accordance with the Accomplishment Instructions of Boeing Alert Service Bulletin 757–53A0101, dated November 8, 2016. (1) If the fuselage STA 1380 frame inner chord material 2024–T42 aluminum alloy is found during any identification required by paragraph (h) of this AD: No further action is required by this paragraph for that airplane. (2) If the fuselage STA 1380 frame inner chord material 7075–T73 aluminum alloy is found during any identification required by the introductory text of paragraph (h) of this AD: Before further flight, do a surface HFEC inspection for any cracking of the fuselage STA 1380 frame inner chord, and do all applicable corrective actions, in accordance with the Accomplishment Instructions of Boeing Alert Service Bulletin 757–53A0101, dated November 8, 2016; except as specified in paragraph (i)(2) of this AD. Do all applicable corrective actions before further flight. Repeat the surface HFEC inspection thereafter at the times specified in paragraph 1.E., ‘‘Compliance,’’ of Boeing Alert Service Bulletin 757–53A0101, dated November 8, 2016. (i) Retained Exceptions to the Service Information, With No Changes This paragraph restates the requirements of paragraph (i) of AD 2017–24–10, with no changes. (1) Where Boeing Alert Service Bulletin 757–53A0101, dated November 8, 2016, specifies a compliance time ‘‘after the original issue date of this service bulletin,’’ PO 00000 Frm 00021 Fmt 4702 Sfmt 4702 3249 this AD requires compliance within the specified compliance time after January 9, 2018 (the effective date of AD 2017–24–10). (2) Where Boeing Alert Service Bulletin 757–53A0101, dated November 8, 2016, specifies to contact Boeing for appropriate action and identifies that action as ‘‘RC’’ (Required for Compliance): Before further flight, repair the crack using a method approved in accordance with the procedures specified in paragraph (m) of this AD. (j) New Required Actions Except as specified by paragraph (k) of this AD: At the applicable times specified in the ‘‘Compliance’’ paragraph of Boeing Alert Requirements Bulletin 757–53A0118 RB, dated October 22, 2021, do all applicable actions identified in, and in accordance with, the Accomplishment Instructions of Boeing Alert Requirements Bulletin 757–53A0118 RB, dated October 22, 2021. Note 1 to paragraph (j): Guidance for accomplishing the actions required by this AD can be found in Boeing Alert Service Bulletin 757–53A0118, dated October 22, 2021, which is referred to in Boeing Alert Requirements Bulletin 757–53A0118 RB, dated October 22, 2021. (k) New Exceptions to Service Information Specifications (1) Where the Compliance Time column of the tables in the ‘‘Compliance’’ paragraph of Boeing Alert Requirements Bulletin 757– 53A0118 RB, dated October 22, 2021, uses the phrase ‘‘the original issue date of the Requirements Bulletin 757–53A0118 RB,’’ this AD requires using ‘‘the effective date of this AD.’’ (2) Where Boeing Alert Requirements Bulletin 757–53A0118 RB, dated October 22, 2021, specifies contacting Boeing for repair instructions or for alternative inspections: This AD requires doing the repair, or doing the alternative inspections and applicable oncondition actions using a method approved in accordance with the procedures specified in paragraph (m) of this AD. (l) Terminating Action for Certain Inspections Accomplishment of the applicable initial inspections and corrective actions specified in the Accomplishment Instructions of Boeing Alert Requirements Bulletin 757– 53A0118 RB, dated October 22, 2021, terminates the inspections required by paragraphs (g) and (h) of this AD. (m) Alternative Methods of Compliance (AMOCs) (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 to the manager of the certification office, send it to the attention of the person identified in paragraph (n)(1) of this AD. Information may be emailed to: 9ANM-LAACO-AMOC-Requests@faa.gov. (2) Before using any approved AMOC, notify your appropriate principal inspector, E:\FR\FM\21JAP1.SGM 21JAP1 3250 Federal Register / Vol. 87, No. 14 / Friday, January 21, 2022 / Proposed Rules jspears on DSK121TN23PROD with PROPOSALS1 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, 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. (4) AMOCs approved previously for AD 2017–24–10 are not approved as AMOCs with this AD. (5) Except as specified by paragraph (i) of this AD: For service information that contains steps that are labeled as Required for Compliance (RC), the provisions of paragraphs (m)(5)(i) and (ii) of this AD apply. (i) The steps labeled as RC, including substeps under an RC step and any figures identified in an RC step, must be done to comply with the AD. If a step or substep is labeled ‘‘RC Exempt,’’ then the RC requirement is removed from that step or substep. An AMOC is required for any deviations to RC steps, including substeps and identified figures. (ii) Steps not labeled as RC may be deviated from using accepted methods in accordance with the operator’s maintenance or inspection program without obtaining approval of an AMOC, provided the RC steps, including substeps and identified figures, can still be done as specified, and the airplane can be put back in an airworthy condition. DEPARTMENT OF HEALTH AND HUMAN SERVICES Food and Drug Administration 21 CFR Part 866 [Docket No. FDA–2021–N–0851] Medical Devices; Immunology and Microbiology Devices; Classification of Human Leukocyte, Neutrophil and Platelet Antigen and Antibody Tests AGENCY: Food and Drug Administration, HHS. ACTION: Proposed rule. The Food and Drug Administration (FDA, the Agency, or we) is proposing to classify Human Leukocyte Antigen (HLA), Human Platelet Antigen (HPA), and Human Neutrophil Antigen (HNA) devices, a generic type of device, into class II (special controls). FDA is identifying proposed special controls for HLA, HPA, and HNA devices that are necessary to provide a reasonable assurance of safety and effectiveness. FDA is also giving notice that we do not intend to exempt these device types from premarket notification requirements of the Federal Food, Drug, and Cosmetic Act (FD&C Act). FDA is publishing in this document the recommendations of the Blood Products Advisory Committee, serving as a device classification panel, regarding the classification of these devices. After considering public comments on the (n) Related Information proposed classification, FDA will (1) For more information about this AD, publish a final regulation classifying contact Peter Jarzomb, Aerospace Engineer, these device types. Airframe Section, FAA, Los Angeles ACO DATES: Submit either electronic or Branch, 3960 Paramount Boulevard, written comments on the proposed rule Lakewood, CA 90712–4137; phone: 562–627– by April 21, 2022. 5234; email: peter.jarzomb@faa.gov. ADDRESSES : You may submit comments (2) For service information identified in as follows. Please note that late, this AD, contact Boeing Commercial untimely filed comments will not be Airplanes, Attention: Contractual & Data considered. Electronic comments must Services (C&DS), 2600 Westminster Blvd., be submitted on or before April 21, MC 110–SK57, Seal Beach, CA 90740–5600; 2022. The https://www.regulations.gov telephone 562–797–1717; internet https:// electronic filing system will accept www.myboeingfleet.com. You may view this comments until 11:59 p.m. Eastern Time referenced service information at the FAA, at the end of April 21, 2022. Comments Airworthiness Products Section, Operational received by mail/hand delivery/courier Safety Branch, 2200 South 216th St., Des (for written/paper submissions) will be Moines, WA. For information on the considered timely if they are availability of this material at the FAA, call postmarked or the delivery service 206–231–3195. acceptance receipt is on or before that Issued on December 10, 2021. date. Lance T. Gant, Director, Compliance & Airworthiness Division, Aircraft Certification Service. [FR Doc. 2022–01014 Filed 1–20–22; 8:45 am] BILLING CODE 4910–13–P VerDate Sep<11>2014 17:13 Jan 20, 2022 Jkt 256001 SUMMARY: Electronic Submissions Submit electronic comments in the following way: • Federal eRulemaking Portal: https://www.regulations.gov. Follow the instructions for submitting comments. Comments submitted electronically, PO 00000 Frm 00022 Fmt 4702 Sfmt 4702 including attachments, to https:// www.regulations.gov will be posted to the docket unchanged. Because your comment will be made public, you are solely responsible for ensuring that your comment does not include any confidential information that you or a third party may not wish to be posted, such as medical information, your or anyone else’s Social Security number, or confidential business information, such as a manufacturing process. Please note that if you include your name, contact information, or other information that identifies you in the body of your comments, that information will be posted on https://www.regulations.gov. • If you want to submit a comment with confidential information that you do not wish to be made available to the public, submit the comment as a written/paper submission and in the manner detailed (see ‘‘Written/Paper Submissions’’ and ‘‘Instructions’’). Written/Paper Submissions Submit written/paper submissions as follows: • Mail/Hand Delivery/Courier (for written/paper submissions): Dockets Management Staff (HFA–305), Food and Drug Administration, 5630 Fishers Lane, Rm. 1061, Rockville, MD 20852. • For written/paper comments submitted to the Dockets Management Staff, FDA will post your comment, as well as any attachments, except for information submitted, marked and identified, as confidential, if submitted as detailed in ‘‘Instructions.’’ Instructions: All submissions received must include the Docket No. FDA– 2021–N–0851 for ‘‘Medical Devices; Immunology and Microbiology Classification of Human Leukocyte, Neutrophil and Platelet Antigen and Antibody Tests.’’ Received comments, those filed in a timely manner (see ADDRESSES), will be placed in the docket and, except for those submitted as ‘‘Confidential Submissions,’’ publicly viewable at https://www.regulations.gov or at the Dockets Management Staff between 9 a.m. and 4 p.m., Monday through Friday, 240–402–7500. • Confidential Submissions—To submit a comment with confidential information that you do not wish to be made publicly available, submit your comments only as a written/paper submission. You should submit two copies total. One copy will include the information you claim to be confidential with a heading or cover note that states ‘‘THIS DOCUMENT CONTAINS CONFIDENTIAL INFORMATION.’’ The Agency will review this copy, including the claimed confidential information, in its consideration of comments. The E:\FR\FM\21JAP1.SGM 21JAP1

Agencies

[Federal Register Volume 87, Number 14 (Friday, January 21, 2022)]
[Proposed Rules]
[Pages 3246-3250]
From the Federal Register Online via the Government Publishing Office [www.gpo.gov]
[FR Doc No: 2022-01014]


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DEPARTMENT OF TRANSPORTATION

Federal Aviation Administration

14 CFR Part 39

[Docket No. FAA-2021-1073; Project Identifier AD-2021-01252-T]
RIN 2120-AA64


Airworthiness Directives; The Boeing Company Airplanes

AGENCY: Federal Aviation Administration (FAA), DOT.

ACTION: Notice of proposed rulemaking (NPRM).

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SUMMARY: The FAA proposes to supersede Airworthiness Directive (AD) 
2017-24-10, which applies to certain The Boeing Company Model 757-200, 
-200PF, and -300 series airplanes. AD 2017-24-10 requires repetitive 
inspections for any cracking of a certain fuselage frame inner chord; 
identification of the material of a certain fuselage frame inner chord 
for certain

[[Page 3247]]

airplanes; and applicable corrective actions. Since the FAA issued AD 
2017-24-10, the FAA has received reports of new crack findings outside 
of the AD 2017-24-10 inspection area, which the existing inspections 
will not detect. This proposed AD would continue to require the actions 
in AD 2017-24-10, would add new airplanes and would require new 
inspection types in certain areas, an expanded inspection area, 
additional inspections, and applicable corrective actions. The FAA is 
proposing this AD to address the unsafe condition on these products.

DATES: The FAA must receive comments on this proposed AD by March 7, 
2022.

ADDRESSES: You may send comments, using the procedures found in 14 CFR 
11.43 and 11.45, by any of the following methods:
     Federal eRulemaking Portal: Go to https://www.regulations.gov. Follow the instructions for submitting comments.
     Fax: 202-493-2251.
     Mail: U.S. Department of Transportation, Docket 
Operations, M-30, West Building Ground Floor, Room W12-140, 1200 New 
Jersey Avenue SE, Washington, DC 20590.
     Hand Delivery: Deliver to Mail address above between 9 
a.m. and 5 p.m., Monday through Friday, except Federal holidays.
    For service information identified in this NPRM, 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. 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. It is also available at https://www.regulations.gov 
by searching for and locating Docket No. FAA-2021-1073.

Examining the AD Docket

    You may examine the AD docket at https://www.regulations.gov by 
searching for and locating Docket No. FAA-2021-1073; or in person at 
Docket Operations between 9 a.m. and 5 p.m., Monday through Friday, 
except Federal holidays. The AD docket contains this NPRM, any comments 
received, and other information. The street address for Docket 
Operations is listed above.

FOR FURTHER INFORMATION CONTACT: Peter Jarzomb, Aerospace Engineer, 
Airframe Section, FAA, Los Angeles ACO Branch, 3960 Paramount 
Boulevard, Lakewood, CA 90712-4137; phone: 562-627-5234; email: 
[email protected].

SUPPLEMENTARY INFORMATION:

Comments Invited

    The FAA invites you to send any written relevant data, views, or 
arguments about this proposal. Send your comments to an address listed 
under ADDRESSES. Include ``Docket No. FAA-2021-1073; Project Identifier 
AD-2021-01252-T'' at the beginning of your comments. The most helpful 
comments reference a specific portion of the proposal, explain the 
reason for any recommended change, and include supporting data. The FAA 
will consider all comments received by the closing date and may amend 
the proposal because of those comments.
    Except for Confidential Business Information (CBI) as described in 
the following paragraph, and other information as described in 14 CFR 
11.35, the FAA will post all comments received, without change, to 
https://www.regulations.gov, including any personal information you 
provide. The agency will also post a report summarizing each 
substantive verbal contact received about this proposed AD.

Confidential Business Information

    CBI is commercial or financial information that is both customarily 
and actually treated as private by its owner. Under the Freedom of 
Information Act (FOIA) (5 U.S.C. 552), CBI is exempt from public 
disclosure. If your comments responsive to this NPRM contain commercial 
or financial information that is customarily treated as private, that 
you actually treat as private, and that is relevant or responsive to 
this NPRM, it is important that you clearly designate the submitted 
comments as CBI. Please mark each page of your submission containing 
CBI as ``PROPIN.'' The FAA will treat such marked submissions as 
confidential under the FOIA, and they will not be placed in the public 
docket of this NPRM. Submissions containing CBI should be sent to Peter 
Jarzomb, Aerospace Engineer, Airframe Section, FAA, Los Angeles ACO 
Branch, 3960 Paramount Boulevard, Lakewood, CA 90712-4137; phone: 562-
627-5234; email: [email protected]. Any commentary that the FAA 
receives which is not specifically designated as CBI will be placed in 
the public docket for this rulemaking.

Background

    The FAA issued AD 2017-24-10, Amendment 39-19114 (82 FR 57343, 
December 5, 2017) (AD 2017-24-10), for certain The Boeing Company Model 
757-200, -200PF, and -300 series airplanes. AD 2017-24-10 was prompted 
by reports of cracking found at a certain fuselage frame inner chord. 
AD 2017-24-10 requires repetitive inspections for any cracking of a 
certain fuselage frame inner chord; identification of the material of a 
certain fuselage frame inner chord for certain airplanes; and 
applicable corrective actions. The agency issued AD 2017-24-10 to 
detect and correct such cracks, which could result in the cargo door 
opening during flight, and result in rapid decompression of the 
airplane and the inability to sustain loads required for continued safe 
flight and landing.

Actions Since AD 2017-24-10 Was Issued

    Since the FAA issued AD 2017-24-10, the FAA has received reports of 
new crack findings outside of the AD 2017-24-10 inspection area, which 
the existing inspections will not detect. An operator was accomplishing 
Boeing Alert Service Bulletin 757-53A0101, dated November 8, 2016, 
which is the service information required by AD 2017-24-10) on a 
certain The Boeing Company Model 757-200 airplane and found four cracks 
ranging from 0.10 to 2.00 inches in length in the station (STA) 1380 
frame web and two cracks ranging from 1.00 to 2.12 inches in length in 
the frame inner chord. The airplane had 23,005 total flight cycles at 
the time of the crack findings. The frame web was made from 0.09 inch 
thick 2024-T3 aluminum, and the inner chord was made from 7075-T73 
aluminum. Based on the length of the crack in the web at the time of 
discovery, the cracks in the frame may have initiated in the 2024-T3 
web, and would have been hidden behind the guide track fitting. If the 
cracks start in the frame web, existing Maintenance Planning Data (MPD) 
and Boeing Alert Service Bulletin 757-53A0101, dated November 8, 2016, 
inspections do not provide sufficient opportunities to find cracks in 
the STA 1380 frame before the critical crack length is reached, 
resulting in an airplane-level safety issue.
    In addition, the FAA has received five reports of crack findings in 
airplanes with production line numbers 1-57, which are made with 7075 
material for the inner and outer chord and the frame web. Those 
airplanes may also have a thinner web gauge than that in airplanes with 
line numbers 58 and subsequent. Existing inspections for these 
airplanes do not remove the guide track fitting at STA 1380, and 
therefore do not provide sufficient opportunity to detect cracks

[[Page 3248]]

before the critical crack length is reached.
    The root cause for the cracking in the STA 1380 frame inner chord 
and web under the roller guide track fitting is attributed to the out-
of-plane bending stress induced from a mis-rigging condition of the No. 
2 cargo door, which allows the roller pin on the lower cargo door to 
contact the roller guide track fitting. The new proposed repetitive 
inspections include removing the guide track fitting to inspect for any 
crack. The FAA is issuing this AD to detect and correct such cracks, 
which could result in rapid decompression of the airplane and the 
inability to sustain loads required for continued safe flight and 
landing.

FAA's Determination

    The FAA is issuing this NPRM after determining that the unsafe 
condition described previously is likely to exist or develop on other 
products of the same type design.

Related Service Information Under 1 CFR Part 51

    The FAA reviewed Boeing Alert Requirements Bulletin 757-53A0118 RB, 
dated October 22, 2021. This service information specifies procedures 
for a general visual inspection or a maintenance records check of the 
STA 1380 frame for any repair, and repetitive surface high frequency 
eddy current (HFEC) inspections of the STA 1380 frame inner chord and 
frame web for any cracking, repetitive sub-surface low frequency eddy 
current (LFEC) inspections of the STA 1380 frame inner chord for any 
cracking, and applicable corrective actions. Corrective actions include 
repair.
    This AD would also require Boeing Alert Service Bulletin 757-
53A0101, dated November 8, 2016, which the Director of the Federal 
Register approved for incorporation by reference as of January 9, 2018 
(82 FR 57343, December 5, 2017).
    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 the ADDRESSES section.

Proposed AD Requirements in This NPRM

    This proposed AD would retain all requirements of AD 2017-24-10. 
This proposed AD would add new airplanes and would require new 
inspection types in certain areas, an expanded inspection area, 
additional inspections, and applicable corrective actions. This 
proposed AD would require accomplishment of the actions identified in 
Boeing Alert Requirements Bulletin 757-53A0118 RB, dated October 22, 
2021, described previously, except for any differences identified as 
exceptions in the regulatory text of this proposed AD.
    Accomplishment of the applicable initial inspections and corrective 
actions specified in the Accomplishment Instructions of Boeing Alert 
Requirements Bulletin 757-53A0118 RB, dated October 22, 2021, 
terminates the inspections required by paragraphs (g) and (h) of this 
proposed AD.
    For information on the procedures and compliance times, see this 
service information at https://www.regulations.gov by searching for and 
locating Docket No. FAA-2021-1073.

Costs of Compliance

    The FAA estimates that this AD, if adopted as proposed, would 
affect 477 airplanes of U.S. registry. The FAA estimates the following 
costs to comply with this proposed AD:

                                                 Estimated Costs
----------------------------------------------------------------------------------------------------------------
                                                                                                 Cost on U.S.
              Action                    Labor cost        Parts cost      Cost per product        operators
----------------------------------------------------------------------------------------------------------------
Surface HFEC inspection (retained  5 work-hours x $85               $0  $425 per inspection  $202,725 per
 actions from AD 2017-24-10).       per hour = $425                      cycle.               inspection cycle.
                                    per inspection
                                    cycle.
Identify the material (retained    Up to 2 work-hours                0  Up to $170.........  Up to $81,090.
 actions from AD 2017-24-10).       x $85 per hour =
                                    $170.
General visual inspection (new     6 work-hours x $85                0  $510...............  $243,270.
 proposed action).                  per hour = $510.
Surface frame inner chord HFEC     Up to 10 work-hours               0  Up to $850 per       Up to $405,450 per
 inspection (new proposed action).  x $85 per hour =                     inspection cycle.    inspection cycle.
                                    $850 per
                                    inspection cycle.
Sub-surface frame inner chord      Up to 6 work-hours                0  Up to $510 per       Up to $243,270 per
 LFEC inspection (new proposed      x $85 per hour =                     inspection cycle.    inspection cycle.
 action).                           $510 per
                                    inspection cycle.
Surface HFEC frame web inspection  Up to 6 work-hours                0  Up to $510 per       Up to $243,270 per
 (new proposed action).             x $85 per hour =                     inspection cycle.    inspection cycle.
                                    $510 per
                                    inspection cycle.
----------------------------------------------------------------------------------------------------------------

    The FAA has received no definitive data on which to base the cost 
estimates for the on-condition repairs specified in this proposed AD.

Authority for This Rulemaking

    Title 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.
    The 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.

Regulatory Findings

    The FAA has determined that this proposed AD would not have 
federalism implications under Executive Order 13132. This proposed AD 
would 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.
    For the reasons discussed above, I certify that the proposed 
regulation:
    (1) Is not a ``significant regulatory action'' under Executive 
Order 12866,

[[Page 3249]]

    (2) Would not affect intrastate aviation in Alaska, and
    (3) Would not have a significant economic impact, positive or 
negative, on a substantial number of small entities under the criteria 
of the Regulatory Flexibility Act.

List of Subjects in 14 CFR Part 39

    Air transportation, Aircraft, Aviation safety, Incorporation by 
reference, Safety.

The Proposed Amendment

    Accordingly, under the authority delegated to me by the 
Administrator, the FAA proposes to amend 14 CFR part 39 as follows:

PART 39--AIRWORTHINESS DIRECTIVES

0
1. The authority citation for part 39 continues to read as follows:

    Authority:  49 U.S.C. 106(g), 40113, 44701.


Sec.  39.13  [Amended]

0
2. The FAA amends Sec.  39.13 by:
0
a. Removing Airworthiness Directive (AD) 2017-24-10, Amendment 39-19114 
(82 FR 57343, December 5, 2017), and
0
b. Adding the following new AD:

The Boeing Company: Docket No. FAA-2021-1073; Project Identifier AD-
2021-01252-T.

(a) Comments Due Date

    The FAA must receive comments on this airworthiness directive 
(AD) action by March 7, 2022.

(b) Affected ADs

    This AD replaces AD 2017-24-10, Amendment 39-19114 (82 FR 57343, 
December 5, 2017) (AD 2017-24-10).

(c) Applicability

    This AD applies to all The Boeing Company Model 757-200, -200PF, 
-200CB, and -300 series airplanes, certificated in any category.

(d) Subject

    Air Transport Association (ATA) of America Code 53, Fuselage.

(e) Unsafe Condition

    This AD was prompted by reports of cracking found at the 
fuselage station (STA) 1380 frame inner chord and by reports of new 
crack findings outside of the AD 2017-24-10 inspection area, which 
the existing inspections will not detect. The FAA is issuing this AD 
to detect and correct such cracks, which could result in rapid 
decompression of the airplane and the inability to sustain loads 
required for continued safe flight and landing.

(f) Compliance

    Comply with this AD within the compliance times specified, 
unless already done.

(g) Retained Inspection for Group 1 Airplanes, With No Changes

    This paragraph restates the requirements of paragraph (g) of AD 
2017-24-10, with no changes. For Group 1 airplanes as identified in 
Boeing Alert Service Bulletin 757-53A0101, dated November 8, 2016: 
At the applicable time specified in paragraph 1.E., ``Compliance,'' 
of Boeing Alert Service Bulletin 757-53A0101, dated November 8, 
2016; except as specified in paragraph (i)(1) of this AD, do a 
surface high frequency eddy current (HFEC) inspection for any 
cracking of the fuselage STA 1380 frame inner chord, and do all 
applicable corrective actions, in accordance with the Accomplishment 
Instructions of Boeing Alert Service Bulletin 757-53A0101, dated 
November 8, 2016; except as specified in paragraph (i)(2) of this 
AD. Do all applicable corrective actions before further flight. 
Repeat the surface HFEC inspection, thereafter, at the times 
specified in paragraph 1.E., ``Compliance,'' of Boeing Alert Service 
Bulletin 757-53A0101, dated November 8, 2016.

(h) Retained Inspection for Group 2 Airplanes, With No Changes

    This paragraph restates the requirements of paragraph (h) of AD 
2017-24-10, with no changes. For Group 2 airplanes as identified in 
Boeing Alert Service Bulletin 757-53A0101, dated November 8, 2016: 
At the applicable time specified in paragraph 1.E., ``Compliance,'' 
of Boeing Alert Service Bulletin 757-53A0101, dated November 8, 
2016, except as specified in paragraph (i)(1) of this AD, identify 
the material of the fuselage STA 1380 frame inner chord, in 
accordance with the Accomplishment Instructions of Boeing Alert 
Service Bulletin 757-53A0101, dated November 8, 2016.
    (1) If the fuselage STA 1380 frame inner chord material 2024-T42 
aluminum alloy is found during any identification required by 
paragraph (h) of this AD: No further action is required by this 
paragraph for that airplane.
    (2) If the fuselage STA 1380 frame inner chord material 7075-T73 
aluminum alloy is found during any identification required by the 
introductory text of paragraph (h) of this AD: Before further 
flight, do a surface HFEC inspection for any cracking of the 
fuselage STA 1380 frame inner chord, and do all applicable 
corrective actions, in accordance with the Accomplishment 
Instructions of Boeing Alert Service Bulletin 757-53A0101, dated 
November 8, 2016; except as specified in paragraph (i)(2) of this 
AD. Do all applicable corrective actions before further flight. 
Repeat the surface HFEC inspection thereafter at the times specified 
in paragraph 1.E., ``Compliance,'' of Boeing Alert Service Bulletin 
757-53A0101, dated November 8, 2016.

(i) Retained Exceptions to the Service Information, With No Changes

    This paragraph restates the requirements of paragraph (i) of AD 
2017-24-10, with no changes.
    (1) Where Boeing Alert Service Bulletin 757-53A0101, dated 
November 8, 2016, specifies a compliance time ``after the original 
issue date of this service bulletin,'' this AD requires compliance 
within the specified compliance time after January 9, 2018 (the 
effective date of AD 2017-24-10).
    (2) Where Boeing Alert Service Bulletin 757-53A0101, dated 
November 8, 2016, specifies to contact Boeing for appropriate action 
and identifies that action as ``RC'' (Required for Compliance): 
Before further flight, repair the crack using a method approved in 
accordance with the procedures specified in paragraph (m) of this 
AD.

(j) New Required Actions

    Except as specified by paragraph (k) of this AD: At the 
applicable times specified in the ``Compliance'' paragraph of Boeing 
Alert Requirements Bulletin 757-53A0118 RB, dated October 22, 2021, 
do all applicable actions identified in, and in accordance with, the 
Accomplishment Instructions of Boeing Alert Requirements Bulletin 
757-53A0118 RB, dated October 22, 2021.
    Note 1 to paragraph (j): Guidance for accomplishing the actions 
required by this AD can be found in Boeing Alert Service Bulletin 
757-53A0118, dated October 22, 2021, which is referred to in Boeing 
Alert Requirements Bulletin 757-53A0118 RB, dated October 22, 2021.

(k) New Exceptions to Service Information Specifications

    (1) Where the Compliance Time column of the tables in the 
``Compliance'' paragraph of Boeing Alert Requirements Bulletin 757-
53A0118 RB, dated October 22, 2021, uses the phrase ``the original 
issue date of the Requirements Bulletin 757-53A0118 RB,'' this AD 
requires using ``the effective date of this AD.''
    (2) Where Boeing Alert Requirements Bulletin 757-53A0118 RB, 
dated October 22, 2021, specifies contacting Boeing for repair 
instructions or for alternative inspections: This AD requires doing 
the repair, or doing the alternative inspections and applicable on-
condition actions using a method approved in accordance with the 
procedures specified in paragraph (m) of this AD.

(l) Terminating Action for Certain Inspections

    Accomplishment of the applicable initial inspections and 
corrective actions specified in the Accomplishment Instructions of 
Boeing Alert Requirements Bulletin 757-53A0118 RB, dated October 22, 
2021, terminates the inspections required by paragraphs (g) and (h) 
of this AD.

(m) Alternative Methods of Compliance (AMOCs)

    (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 to the 
manager of the certification office, send it to the attention of the 
person identified in paragraph (n)(1) of this AD. Information may be 
emailed to: [email protected].
    (2) Before using any approved AMOC, notify your appropriate 
principal inspector,

[[Page 3250]]

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, 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.
    (4) AMOCs approved previously for AD 2017-24-10 are not approved 
as AMOCs with this AD.
    (5) Except as specified by paragraph (i) of this AD: For service 
information that contains steps that are labeled as Required for 
Compliance (RC), the provisions of paragraphs (m)(5)(i) and (ii) of 
this AD apply.
    (i) The steps labeled as RC, including substeps under an RC step 
and any figures identified in an RC step, must be done to comply 
with the AD. If a step or substep is labeled ``RC Exempt,'' then the 
RC requirement is removed from that step or substep. An AMOC is 
required for any deviations to RC steps, including substeps and 
identified figures.
    (ii) Steps not labeled as RC may be deviated from using accepted 
methods in accordance with the operator's maintenance or inspection 
program without obtaining approval of an AMOC, provided the RC 
steps, including substeps and identified figures, can still be done 
as specified, and the airplane can be put back in an airworthy 
condition.

(n) Related Information

    (1) For more information about this AD, contact Peter Jarzomb, 
Aerospace Engineer, Airframe Section, FAA, Los Angeles ACO Branch, 
3960 Paramount Boulevard, Lakewood, CA 90712-4137; phone: 562-627-
5234; email: [email protected].
    (2) 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. You may view this referenced 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.

    Issued on December 10, 2021.
Lance T. Gant,
Director, Compliance & Airworthiness Division, Aircraft Certification 
Service.
[FR Doc. 2022-01014 Filed 1-20-22; 8:45 am]
BILLING CODE 4910-13-P