Airworthiness Directives; The Boeing Company Airplanes, 34888-34891 [2017-15554]

Download as PDF 34888 Federal Register / Vol. 82, No. 143 / Thursday, July 27, 2017 / Proposed Rules inspection for damage (including cracking) of the upper wing skin and top stringer joints at rib 18 on both wings, do all applicable corrective actions, and do the applicable modification, including related investigative and corrective actions, in accordance with the Accomplishment Instructions of Airbus Service Bulletin A300–57–6118, Revision 01, dated January 31, 2017, except as required by paragraph (i) of this AD. Do all applicable modifications, related investigative actions, and corrective actions before further flight. (1) For Group 1, LR airplanes: Inspect at the time specified in paragraph (h)(1)(i) or (h)(1)(ii) of this AD, whichever occurs later. (i) Before exceeding 32,500 flight cycles or 70,300 flight hours, whichever occurs first since first flight of the airplane. (ii) Within 700 flight cycles, 1,500 flight hours, or 12 months, whichever occurs first after the effective date of this AD. (2) For Group 1, SR airplanes: Inspect at the time specified in paragraphs (h)(2)(i) or (h)(2)(ii) of this AD, whichever occurs later. (i) Before exceeding 35,100 flight cycles or 52,600 flight hours, whichever occurs first since the first flight of the airplane. (ii) Within 700 flight cycles or 1,000 flight hours, or 12 months, whichever occurs first after the effective date of this AD. (3) For Group 2, LR airplanes: Inspect before exceeding 35,000 flight cycles or 75,700 flight hours, whichever occurs first since the first flight of the airplane. (4) For Group 2, SR airplanes: Inspect before exceeding 37,800 flight cycles or 56,700 flight hours, whichever occurs first since the first flight of the airplane. TABLE 1 TO PARAGRAPH (h) OF THIS AD—COMPLIANCE TIME LOWER THRESHOLDS Applicable airplanes Group 1, LR Group 1, SR Group 2, LR Group 2, SR Compliance time flight cycles (FC) or flight hours (FH), whichever occurs first since first flight of the airplane Not before exceeding 66,700 FH. Not before exceeding 43,000 FH. Not before exceeding 61,700 FH. Not before exceeding 51,600 FH. 30,900 FC or 28,700 FC or 28,600 FC or 34,400 FC or (i) Service Information Exception mstockstill on DSK30JT082PROD with PROPOSALS Where Airbus Service Bulletin A300–57– 6118, Revision 01, dated January 31, 2017, specifies to contact Airbus for appropriate action, and specifies that action as ‘‘RC’’ (Required for Compliance): Before further flight, accomplish corrective actions in accordance with the procedures specified in paragraph (k)(2) of this AD. (j) Credit for Previous Actions This paragraph provides credit for actions required by paragraph (h) of this AD, if those actions were performed before the effective date of this AD using Airbus Service Bulletin A300–57–6118, dated June 30, 2015. (k) Other FAA AD Provisions The following provisions also apply to this AD: VerDate Sep<11>2014 17:09 Jul 26, 2017 Jkt 241001 (1) Alternative Methods of Compliance (AMOCs): The Manager, International Branch, ANM–116, 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 Branch, send it to the attention of the person identified in paragraph (l)(2) of this AD. Information may be emailed to: 9-ANM-116AMOC-REQUESTS@faa.gov. 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. (2) Contacting the Manufacturer: For any requirement in this AD to obtain corrective actions from a manufacturer, the action must be accomplished using a method approved by the Manager, International Branch, ANM– 116, Transport Airplane Directorate, FAA; or the European Aviation Safety Agency (EASA); or Airbus’s EASA Design Organization Approval (DOA). If approved by the DOA, the approval must include the DOA-authorized signature. (3) Required for Compliance (RC): If any service information contains procedures or tests that are identified as RC, those procedures and tests must be done to comply with this AD; any procedures or tests that are not identified as RC are recommended. Those procedures and tests that are not identified 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 procedures and tests identified as RC can be done and the airplane can be put back in an airworthy condition. Any substitutions or changes to procedures or tests identified as RC require approval of an AMOC. (l) Related Information (1) Refer to Mandatory Continuing Airworthiness Information (MCAI) EASA Airworthiness Directive 2017–0023, dated February 10, 2017, for related information. This MCAI may be found in the AD docket on the Internet at http://www.regulations.gov by searching for and locating Docket No. FAA–2017–0710. (2) For more information about this AD, contact Dan Rodina, Aerospace Engineer, International Branch, ANM–116, Transport Airplane Directorate, FAA, 1601 Lind Avenue SW., Renton, WA 98057–3356; telephone 425–227–2125; fax 425–227–1149. (3) For service information identified in this AD, contact Airbus SAS, Airworthiness Office—EAW, 1 Rond Point Maurice Bellonte, 31707 Blagnac Cedex, France; telephone +33 5 61 93 36 96; fax +33 5 61 93 44 51; email account.airworth-eas@ airbus.com; Internet http://www.airbus.com. You may view this service information at the FAA, Transport Airplane Directorate, 1601 Lind Avenue SW., Renton, WA. For information on the availability of this material at the FAA, call 425–227–1221. PO 00000 Frm 00005 Fmt 4702 Sfmt 4702 Issued in Renton, Washington, on July 18, 2017. Victor Wicklund, Acting Manager, Transport Airplane Directorate, Aircraft Certification Service. [FR Doc. 2017–15558 Filed 7–26–17; 8:45 am] BILLING CODE 4910–13–P DEPARTMENT OF TRANSPORTATION Federal Aviation Administration 14 CFR Part 39 [Docket No. FAA–2017–0711; Directorate Identifier 2017–NM–003–AD] RIN 2120–AA64 Airworthiness Directives; The Boeing Company Airplanes Federal Aviation Administration (FAA), DOT. ACTION: Notice of proposed rulemaking (NPRM). AGENCY: We propose to adopt a new airworthiness directive (AD) for certain The Boeing Company Model 757–200, –200CB, and –300 series airplanes. This proposed AD was prompted by a report of fatigue cracking found in a certain fuselage frame, which severed the inner chord and web. This proposed AD would require inspecting the fuselage frame for existing repairs, repetitive inspections, and applicable repairs. We are proposing this AD to address the unsafe condition on these products. DATES: We must receive comments on this proposed AD by September 11, 2017. SUMMARY: 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 http://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; telephone: 562–797–1717; Internet: https:// www.myboeingfleet.com. You may view this referenced service information at ADDRESSES: E:\FR\FM\27JYP1.SGM 27JYP1 34889 Federal Register / Vol. 82, No. 143 / Thursday, July 27, 2017 / Proposed Rules the FAA, Transport Airplane Directorate, 1601 Lind Avenue SW., Renton, WA. For information on the availability of this material at the FAA, call 425–227–1221. It is also available on the Internet at http:// www.regulations.gov by searching for and locating Docket No. FAA–2017– 0711. We will post all comments we receive, without change, to http:// www.regulations.gov, including any personal information you provide. We will also post a report summarizing each substantive verbal contact we receive about this NPRM. Examining the AD Docket You may examine the AD docket on the Internet at http:// www.regulations.gov by searching for and locating Docket No. FAA–2017– 0711; or in person at the Docket Management Facility between 9 a.m. and 5 p.m., Monday through Friday, except Federal holidays. The AD docket contains this NPRM, the regulatory evaluation, any comments received, and other information. The street address for the Docket Office (phone: 800–647– 5527) is in the ADDRESSES section. Comments will be available in the AD docket shortly after receipt. FOR FURTHER INFORMATION CONTACT: Chandra Ramdoss, Aerospace Engineer, Airframe Branch, ANM–120L, FAA, Los Angeles Aircraft Certification Office (ACO), 3960 Paramount Boulevard, Lakewood, CA 90712–4137; phone: 562–627–5239; fax: 562–627–5210; email: chandraduth.ramdoss@faa.gov. SUPPLEMENTARY INFORMATION: We have received a report of a crack in the fuselage frame at station (STA) 1640, at stringer (S) 14–R, adjacent to door stop number 5. The inner chord and web of the STA 1640 fuselage frame had been severed after developing a crack. Analysis revealed that the crack was caused by fatigue due to flight loads and pressurization of the fuselage. Cracking of the fuselage frame, if not detected and corrected, could result in reduced structural integrity of the airplane. Discussion Comments Invited We invite you to send any written relevant data, views, or arguments about this proposal. Send your comments to an address listed under the ADDRESSES section. Include ‘‘Docket No. FAA– 2017–0711; Directorate Identifier 2017– NM–001–AD’’ at the beginning of your comments. We specifically invite comments on the overall regulatory, economic, environmental, and energy aspects of this NPRM. We will consider all comments received by the closing date and may amend this NPRM because of those comments. Related Service Information Under 1 CFR Part 51 We reviewed Boeing Alert Service Bulletin 757–53A0108, dated November 14, 2016. The service information describes procedures for an inspection of the fuselage frame for existing frame repairs, repetitive high frequency eddy current and low frequency eddy current inspections for cracking in specified areas with no existing frame repair, and repair of any cracking. We also reviewed Aviation Partners Boeing (APB) Alert Service Bulletin AP757–53–001, Revision 1, dated June 21, 2017. The service information provides compliance times for accomplishing the procedures identified in Boeing Alert Service Bulletin 757– 53A0108, dated November 14, 2016; for airplanes on which APB blended or scimitar blended winglets are installed. 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. FAA’s Determination We are proposing this AD because we evaluated all the relevant information and determined the unsafe condition described previously is likely to exist or develop in other products of the same type design. Proposed AD Requirements This proposed AD would require accomplishment of the actions identified as ‘‘RC’’ (required for compliance) in the Accomplishment Instructions of Boeing Alert Service Bulletin 757–53A0108, dated November 14, 2016, described previously, except for differences between this proposed AD and the service information that are identified in the regulatory text of this proposed AD. For information on the procedures and compliance times, see this Boeing service information at http:// www.regulations.gov by searching for and locating Docket No. FAA–2017– 0711, except for airplanes on which blended or scimitar blended winglets are installed in accordance with Supplemental Type Certificate ST01518SE, which have different repetitive compliance times as specified in APB Alert Service Bulletin AP757– 53–001, Revision 1, dated June 21, 2017. For airplanes on which blended or scimitar blended winglets are installed in accordance with Supplemental Type Certificate ST01518SE, the repetitive compliance times have a range, depending on airplane configuration. The earliest repetitive interval is 1,950 flight cycles; the latest repetitive interval is 8,600 flight cycles. Costs of Compliance We estimate that this proposed AD affects 606 airplanes of U.S. registry. We estimate the following costs to comply with this proposed AD: ESTIMATED COSTS Cost per product mstockstill on DSK30JT082PROD with PROPOSALS Labor cost Inspect for existing frame repairs ............... Repetitive high and low frequency inspections for Groups 1 through 3 airplanes (598 airplanes). Repetitive high and low frequency inspections for Groups 4 and 5 airplanes (8 airplanes). 1 work-hour × $85 per hour = $85 ............. 48 work-hours × $85 per hour = $4,080 per inspection cycle. $0 0 $85 4,080 $51,510. $2,439,840 per inspection cycle. 26 work-hours × $85 per hour = $2,210 per inspection cycle. 0 2,210 $17,680 per inspection cycle. We have received no definitive data that would enable us to provide cost VerDate Sep<11>2014 17:09 Jul 26, 2017 Jkt 241001 Parts cost Cost on U.S. operators Action estimates for the on-condition repair specified in this proposed AD. PO 00000 Frm 00006 Fmt 4702 Sfmt 4702 Authority for This Rulemaking Title 49 of the United States Code specifies the FAA’s authority to issue E:\FR\FM\27JYP1.SGM 27JYP1 34890 Federal Register / Vol. 82, No. 143 / Thursday, July 27, 2017 / Proposed Rules 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. We are 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 We 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) Is not a ‘‘significant rule’’ under the DOT Regulatory Policies and Procedures (44 FR 11034, February 26, 1979), (3) Will not affect intrastate aviation in Alaska, and (4) 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. List of Subjects in 14 CFR Part 39 Air transportation, Aircraft, Aviation safety, Incorporation by reference, Safety. mstockstill on DSK30JT082PROD with PROPOSALS 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. VerDate Sep<11>2014 17:09 Jul 26, 2017 Jkt 241001 § 39.13 [Amended] 2. The FAA amends § 39.13 by adding the following new airworthiness directive (AD): ■ The Boeing Company: Docket No. FAA– 2017–0711; Directorate Identifier 2017– NM–003–AD. (a) Comments Due Date We must receive comments by September 11, 2017. (b) Affected ADs None. (c) Applicability This AD applies to The Boeing Company Model 757–200, –200CB, and –300 series airplanes, certificated in any category, as identified in Boeing Alert Service Bulletin 757–53A0108, dated November 14, 2016. (d) Subject Air Transport Association (ATA) of America Code 53; Fuselage. (e) Unsafe Condition This AD was prompted by a report of fatigue cracking found in the fuselage frame at station (STA) 1640, which severed the inner chord and web. We are issuing this AD to detect and correct cracking of the fuselage frame at STA 1640, which could result in reduced structural integrity of the airplane. (f) Compliance Comply with this AD within the compliance times specified, unless already done. (g) Actions Required for Compliance (1) For all airplanes except those identified in paragraph (g)(2) of this AD: Do all applicable actions identified as ‘‘RC’’ (required for compliance) in, and in accordance with, the Accomplishment Instructions of Boeing Alert Service Bulletin 757–53A0108, dated November 14, 2016; except as provided by paragraph (h)(1) of this AD. Do the actions at the applicable times specified in paragraph 1.E., ‘‘Compliance,’’ of Boeing Alert Service 757–53A0108, dated November 14, 2016, except as provided by paragraph (h)(2) of this AD. (2) For airplanes on which blended or scimitar blended winglets are installed in accordance with Supplemental Type Certificate ST01518SE: Do all applicable actions identified as ‘‘RC’’ (required for compliance) in, and in accordance with, the Accomplishment Instructions of APB Alert Service Bulletin AP757–53–001, Revision 1, dated June 21, 2017; and Boeing Alert Service Bulletin 757–53A0108, dated November 14, 2016; except as provided by paragraph (h)(1) of this AD. Do the actions at the applicable times specified in paragraph 1.E., ‘‘Compliance,’’ of Aviation Partners Boeing (APB) Alert Service Bulletin AP757– 53–001, Revision 1, dated June 21, 2017, except as provided by paragraph (h)(2) of this AD. (h) Exceptions to Service Information Specifications (1) Where Boeing Alert Service Bulletin 757–53A0108, dated November 14, 2016, PO 00000 Frm 00007 Fmt 4702 Sfmt 4702 specifies contacting Boeing for instructions, and specifies that action as RC: This AD requires using a method approved in accordance with the procedures specified in paragraph (i) of this AD. (2) Where Boeing Alert Service Bulletin 757–53A0108, dated November 14, 2016, and APB Alert Service Bulletin AP757–53–001, Revision 1, dated June 21, 2017, use the phrase ‘‘after the original issue of this service bulletin’’ for determining compliance, this AD requires compliance within the specified compliance time after the effective date of this AD. (i) Alternative Methods of Compliance (AMOCs) (1) The Manager, Los Angeles Aircraft Certification Office (ACO), 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 ACO, send it to the attention of the person identified in paragraph (j)(1) of this AD. Information may be emailed to 9-ANM-LAACO-AMOCRequests@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. (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 Commercial Airplanes Organization Designation Authorization (ODA) that has been authorized by the Manager, Los Angeles ACO, 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) Except as required by paragraph (h)(1) of this AD: For service information that contains steps that are labeled as RC, the provisions of paragraphs (i)(4)(i) and (i)(4)(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. (j) Related Information (1) For more information about this AD, contact Chandra Ramdoss, Aerospace Engineer, Airframe Branch, ANM–120L, FAA, Los Angeles ACO, 3960 Paramount Boulevard, Lakewood, CA 90712–4137; E:\FR\FM\27JYP1.SGM 27JYP1 Federal Register / Vol. 82, No. 143 / Thursday, July 27, 2017 / Proposed Rules phone: 562–627–5239; fax: 562–627–5210; email: chandraduth.ramdoss@faa.gov. (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; telephone: 562–797–1717; Internet: https:// www.myboeingfleet.com. You may view this referenced service information at the FAA, Transport Airplane Directorate, 1601 Lind Avenue SW., Renton, WA. For information on the availability of this material at the FAA, call 425–227–1221. Issued in Renton, Washington, on July 18, 2017. Victor Wicklund, Acting Manager, Transport Airplane Directorate, Aircraft Certification Service. [FR Doc. 2017–15554 Filed 7–26–17; 8:45 am] BILLING CODE 4910–13–P DEPARTMENT OF TRANSPORTATION Federal Aviation Administration 14 CFR Part 39 [Docket No. FAA–2017–0708; Directorate Identifier 2017–NM–035–AD] RIN 2120–AA64 Airworthiness Directives; Airbus Airplanes Examining the AD Docket Federal Aviation Administration (FAA), DOT. ACTION: Notice of proposed rulemaking (NPRM). AGENCY: We propose to supersede Airworthiness Directive (AD) AD 2016– 20–11, for certain Airbus Model A300 B4–600, B4–600R, and F4–600R series airplanes, and Model A300 C4–605R Variant F airplanes (collectively called Model A300–600 series airplanes); and Airbus Model A310 series airplanes. AD 2016–20–11 requires repetitive inspections of the external area of the aft cargo door sill beam for cracking, repetitive inspections for fatigue cracking of the cargo door sill beam, lock fitting, and torsion box plate, and repair if necessary. Since we issued AD 2016–20–11, we have determined that reinforcement of the aft cargo door sill beam area is necessary to address the unsafe condition, which constitutes terminating action for the repetitive inspections. This proposed AD would retain the inspections for cracking, and repair if necessary; and require reinforcement of the aft cargo door sill beam area. We are proposing this AD to address the unsafe condition on these products. DATES: We must receive comments on this proposed AD by September 11, 2017. mstockstill on DSK30JT082PROD with PROPOSALS SUMMARY: VerDate Sep<11>2014 17:09 Jul 26, 2017 Jkt 241001 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 http://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 Airbus SAS, Airworthiness Office—EAW, 1 Rond Point Maurice Bellonte, 31707 Blagnac Cedex, France; telephone +33 5 61 93 36 96; fax +33 5 61 93 44 51; email account.airworth-eas@airbus.com; Internet http://www.airbus.com. You may view this referenced service information at the FAA, Transport Airplane Directorate, 1601 Lind Avenue SW., Renton, WA. For information on the availability of this material at the FAA, call 425–227–1221. ADDRESSES: You may examine the AD docket on the Internet at http:// www.regulations.gov by searching for and locating Docket No. FAA–2017– 0708; or in person at the Docket Management Facility between 9 a.m. and 5 p.m., Monday through Friday, except Federal holidays. The AD docket contains this proposed AD, the regulatory evaluation, any comments received, and other information. The street address for the Docket Operations office (telephone 800–647–5527) is in the ADDRESSES section. Comments will be available in the AD docket shortly after receipt. FOR FURTHER INFORMATION CONTACT: Dan Rodina, Aerospace Engineer, International Branch, ANM–116, Transport Airplane Directorate, FAA, 1601 Lind Avenue SW., Renton, WA 98057–3356; telephone 425–227–2125; fax 425–227–1149. SUPPLEMENTARY INFORMATION: Comments Invited We invite you to send any written relevant data, views, or arguments about this proposal. Send your comments to an address listed under the ADDRESSES section. Include ‘‘Docket No. FAA– 2017–0708; Directorate Identifier 2017– NM–035–AD’’ at the beginning of your comments. We specifically invite comments on the overall regulatory, PO 00000 Frm 00008 Fmt 4702 Sfmt 4702 34891 economic, environmental, and energy aspects of this proposed AD. We will consider all comments received by the closing date and may amend this proposed AD based on those comments. We will post all comments we receive, without change, to http:// www.regulations.gov, including any personal information you provide. We will also post a report summarizing each substantive verbal contact we receive about this proposed AD. Discussion On September 28, 2016, we issued AD 2016–20–11, Amendment 39–18677 (81 FR 85837, November 29, 2016) (‘‘AD 2016–20–11’’), for certain Airbus Model A300–600 series airplanes; and Airbus Model A310 series airplanes. AD 2016– 20–11 was prompted by reports of fatigue cracks on the cargo door sill beam, lock fitting, and torsion box plate. AD 2016–20–11 requires repetitive ultrasonic and detailed inspections of the external area of the aft cargo door sill beam for cracking, repetitive high frequency eddy current (HFEC) inspections for fatigue cracking of the cargo door sill beam, lock fitting, and torsion box plate, and repair if necessary. We issued AD 2016–20–11 to detect and correct fatigue cracking of the cargo door sill beam, lock fitting, and torsion box plate, which could result in the loss of the door locking function and subsequently, loss of the cargo door in flight and rapid decompression. Since we issued AD 2016–20–11, Airbus has developed a reinforcement modification of the aft cargo door sill beam area, which constitutes terminating action for the repetitive inspections. We have determined the reinforcement of the aft cargo door sill beam area is necessary to address the unsafe condition. The European Aviation Safety Agency (EASA), which is the Technical Agent for the Member States of the European Union, has issued EASA AD 2017–0048, dated March 15, 2017; corrected April 20, 2017 (referred to after this as the Mandatory Continuing Airworthiness Information, or ‘‘the MCAI’’), to correct an unsafe condition for certain Airbus Model A300–600 series airplanes; and Airbus Model A310 series airplanes. The MCAI states: In the frame of the widespread fatigue damage (WFD) compliance study and after an in-service occurrence, the area of the aft cargo door sill beam and adjacent structure was identified as sensitive to the fatigue loads. This condition, if not detected and corrected, could lead to failure of multiple lock fittings, possibly resulting in loss of the cargo door in flight and consequent explosive decompression of the aeroplane. E:\FR\FM\27JYP1.SGM 27JYP1

Agencies

[Federal Register Volume 82, Number 143 (Thursday, July 27, 2017)]
[Proposed Rules]
[Pages 34888-34891]
From the Federal Register Online via the Government Publishing Office [www.gpo.gov]
[FR Doc No: 2017-15554]


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DEPARTMENT OF TRANSPORTATION

Federal Aviation Administration

14 CFR Part 39

[Docket No. FAA-2017-0711; Directorate Identifier 2017-NM-003-AD]
RIN 2120-AA64


Airworthiness Directives; The Boeing Company Airplanes

AGENCY: Federal Aviation Administration (FAA), DOT.

ACTION: Notice of proposed rulemaking (NPRM).

-----------------------------------------------------------------------

SUMMARY: We propose to adopt a new airworthiness directive (AD) for 
certain The Boeing Company Model 757-200, -200CB, and -300 series 
airplanes. This proposed AD was prompted by a report of fatigue 
cracking found in a certain fuselage frame, which severed the inner 
chord and web. This proposed AD would require inspecting the fuselage 
frame for existing repairs, repetitive inspections, and applicable 
repairs. We are proposing this AD to address the unsafe condition on 
these products.

DATES: We must receive comments on this proposed AD by September 11, 
2017.

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 http://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; telephone: 
562-797-1717; Internet: https://www.myboeingfleet.com. You may view 
this referenced service information at

[[Page 34889]]

the FAA, Transport Airplane Directorate, 1601 Lind Avenue SW., Renton, 
WA. For information on the availability of this material at the FAA, 
call 425-227-1221. It is also available on the Internet at http://www.regulations.gov by searching for and locating Docket No. FAA-2017-
0711.

Examining the AD Docket

    You may examine the AD docket on the Internet at http://www.regulations.gov by searching for and locating Docket No. FAA-2017-
0711; or in person at the Docket Management Facility between 9 a.m. and 
5 p.m., Monday through Friday, except Federal holidays. The AD docket 
contains this NPRM, the regulatory evaluation, any comments received, 
and other information. The street address for the Docket Office (phone: 
800-647-5527) is in the ADDRESSES section. Comments will be available 
in the AD docket shortly after receipt.

FOR FURTHER INFORMATION CONTACT: Chandra Ramdoss, Aerospace Engineer, 
Airframe Branch, ANM-120L, FAA, Los Angeles Aircraft Certification 
Office (ACO), 3960 Paramount Boulevard, Lakewood, CA 90712-4137; phone: 
562-627-5239; fax: 562-627-5210; email: chandraduth.ramdoss@faa.gov.

SUPPLEMENTARY INFORMATION: 

Comments Invited

    We invite you to send any written relevant data, views, or 
arguments about this proposal. Send your comments to an address listed 
under the ADDRESSES section. Include ``Docket No. FAA-2017-0711; 
Directorate Identifier 2017-NM-001-AD'' at the beginning of your 
comments. We specifically invite comments on the overall regulatory, 
economic, environmental, and energy aspects of this NPRM. We will 
consider all comments received by the closing date and may amend this 
NPRM because of those comments.
    We will post all comments we receive, without change, to http://www.regulations.gov, including any personal information you provide. We 
will also post a report summarizing each substantive verbal contact we 
receive about this NPRM.

Discussion

    We have received a report of a crack in the fuselage frame at 
station (STA) 1640, at stringer (S) 14-R, adjacent to door stop number 
5. The inner chord and web of the STA 1640 fuselage frame had been 
severed after developing a crack. Analysis revealed that the crack was 
caused by fatigue due to flight loads and pressurization of the 
fuselage. Cracking of the fuselage frame, if not detected and 
corrected, could result in reduced structural integrity of the 
airplane.

Related Service Information Under 1 CFR Part 51

    We reviewed Boeing Alert Service Bulletin 757-53A0108, dated 
November 14, 2016. The service information describes procedures for an 
inspection of the fuselage frame for existing frame repairs, repetitive 
high frequency eddy current and low frequency eddy current inspections 
for cracking in specified areas with no existing frame repair, and 
repair of any cracking.
    We also reviewed Aviation Partners Boeing (APB) Alert Service 
Bulletin AP757-53-001, Revision 1, dated June 21, 2017. The service 
information provides compliance times for accomplishing the procedures 
identified in Boeing Alert Service Bulletin 757-53A0108, dated November 
14, 2016; for airplanes on which APB blended or scimitar blended 
winglets are installed.
    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.

FAA's Determination

    We are proposing this AD because we evaluated all the relevant 
information and determined the unsafe condition described previously is 
likely to exist or develop in other products of the same type design.

Proposed AD Requirements

    This proposed AD would require accomplishment of the actions 
identified as ``RC'' (required for compliance) in the Accomplishment 
Instructions of Boeing Alert Service Bulletin 757-53A0108, dated 
November 14, 2016, described previously, except for differences between 
this proposed AD and the service information that are identified in the 
regulatory text of this proposed AD.
    For information on the procedures and compliance times, see this 
Boeing service information at http://www.regulations.gov by searching 
for and locating Docket No. FAA-2017-0711, except for airplanes on 
which blended or scimitar blended winglets are installed in accordance 
with Supplemental Type Certificate ST01518SE, which have different 
repetitive compliance times as specified in APB Alert Service Bulletin 
AP757-53-001, Revision 1, dated June 21, 2017.
    For airplanes on which blended or scimitar blended winglets are 
installed in accordance with Supplemental Type Certificate ST01518SE, 
the repetitive compliance times have a range, depending on airplane 
configuration. The earliest repetitive interval is 1,950 flight cycles; 
the latest repetitive interval is 8,600 flight cycles.

Costs of Compliance

    We estimate that this proposed AD affects 606 airplanes of U.S. 
registry. We estimate the following costs to comply with this proposed 
AD:

                                                 Estimated Costs
----------------------------------------------------------------------------------------------------------------
                                                                           Cost per
            Action                    Labor cost          Parts cost        product      Cost on U.S. operators
----------------------------------------------------------------------------------------------------------------
Inspect for existing frame      1 work-hour x $85 per               $0             $85  $51,510.
 repairs.                        hour = $85.
Repetitive high and low         48 work-hours x $85                  0           4,080  $2,439,840 per
 frequency inspections for       per hour = $4,080 per                                   inspection cycle.
 Groups 1 through 3 airplanes    inspection cycle.
 (598 airplanes).
Repetitive high and low         26 work-hours x $85                  0           2,210  $17,680 per inspection
 frequency inspections for       per hour = $2,210 per                                   cycle.
 Groups 4 and 5 airplanes (8     inspection cycle.
 airplanes).
----------------------------------------------------------------------------------------------------------------

    We have received no definitive data that would enable us to provide 
cost estimates for the on-condition repair specified in this proposed 
AD.

Authority for This Rulemaking

    Title 49 of the United States Code specifies the FAA's authority to 
issue

[[Page 34890]]

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.
    We are 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

    We 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) Is not a ``significant rule'' under the DOT Regulatory Policies 
and Procedures (44 FR 11034, February 26, 1979),
    (3) Will not affect intrastate aviation in Alaska, and
    (4) 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.

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 adding the following new airworthiness 
directive (AD):

The Boeing Company: Docket No. FAA-2017-0711; Directorate Identifier 
2017-NM-003-AD.

(a) Comments Due Date

    We must receive comments by September 11, 2017.

(b) Affected ADs

    None.

(c) Applicability

    This AD applies to The Boeing Company Model 757-200, -200CB, and 
-300 series airplanes, certificated in any category, as identified 
in Boeing Alert Service Bulletin 757-53A0108, dated November 14, 
2016.

(d) Subject

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

(e) Unsafe Condition

    This AD was prompted by a report of fatigue cracking found in 
the fuselage frame at station (STA) 1640, which severed the inner 
chord and web. We are issuing this AD to detect and correct cracking 
of the fuselage frame at STA 1640, which could result in reduced 
structural integrity of the airplane.

(f) Compliance

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

(g) Actions Required for Compliance

    (1) For all airplanes except those identified in paragraph 
(g)(2) of this AD: Do all applicable actions identified as ``RC'' 
(required for compliance) in, and in accordance with, the 
Accomplishment Instructions of Boeing Alert Service Bulletin 757-
53A0108, dated November 14, 2016; except as provided by paragraph 
(h)(1) of this AD. Do the actions at the applicable times specified 
in paragraph 1.E., ``Compliance,'' of Boeing Alert Service 757-
53A0108, dated November 14, 2016, except as provided by paragraph 
(h)(2) of this AD.
    (2) For airplanes on which blended or scimitar blended winglets 
are installed in accordance with Supplemental Type Certificate 
ST01518SE: Do all applicable actions identified as ``RC'' (required 
for compliance) in, and in accordance with, the Accomplishment 
Instructions of APB Alert Service Bulletin AP757-53-001, Revision 1, 
dated June 21, 2017; and Boeing Alert Service Bulletin 757-53A0108, 
dated November 14, 2016; except as provided by paragraph (h)(1) of 
this AD. Do the actions at the applicable times specified in 
paragraph 1.E., ``Compliance,'' of Aviation Partners Boeing (APB) 
Alert Service Bulletin AP757-53-001, Revision 1, dated June 21, 
2017, except as provided by paragraph (h)(2) of this AD.

(h) Exceptions to Service Information Specifications

    (1) Where Boeing Alert Service Bulletin 757-53A0108, dated 
November 14, 2016, specifies contacting Boeing for instructions, and 
specifies that action as RC: This AD requires using a method 
approved in accordance with the procedures specified in paragraph 
(i) of this AD.
    (2) Where Boeing Alert Service Bulletin 757-53A0108, dated 
November 14, 2016, and APB Alert Service Bulletin AP757-53-001, 
Revision 1, dated June 21, 2017, use the phrase ``after the original 
issue of this service bulletin'' for determining compliance, this AD 
requires compliance within the specified compliance time after the 
effective date of this AD.

(i) Alternative Methods of Compliance (AMOCs)

    (1) The Manager, Los Angeles Aircraft Certification Office 
(ACO), 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 ACO, 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.
    (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.
    (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 Commercial Airplanes Organization 
Designation Authorization (ODA) that has been authorized by the 
Manager, Los Angeles ACO, 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) Except as required by paragraph (h)(1) of this AD: For 
service information that contains steps that are labeled as RC, the 
provisions of paragraphs (i)(4)(i) and (i)(4)(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.

(j) Related Information

    (1) For more information about this AD, contact Chandra Ramdoss, 
Aerospace Engineer, Airframe Branch, ANM-120L, FAA, Los Angeles ACO, 
3960 Paramount Boulevard, Lakewood, CA 90712-4137;

[[Page 34891]]

phone: 562-627-5239; fax: 562-627-5210; email: 
chandraduth.ramdoss@faa.gov.
    (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; 
telephone: 562-797-1717; Internet: https://www.myboeingfleet.com. 
You may view this referenced service information at the FAA, 
Transport Airplane Directorate, 1601 Lind Avenue SW., Renton, WA. 
For information on the availability of this material at the FAA, 
call 425-227-1221.

    Issued in Renton, Washington, on July 18, 2017.
Victor Wicklund,
Acting Manager, Transport Airplane Directorate, Aircraft Certification 
Service.
[FR Doc. 2017-15554 Filed 7-26-17; 8:45 am]
BILLING CODE 4910-13-P