Airworthiness Directives; The Boeing Company Airplanes, 92742-92745 [2016-30021]

Download as PDF 92742 Federal Register / Vol. 81, No. 244 / Tuesday, December 20, 2016 / Proposed Rules (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 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 (AD): ■ The Boeing Company; Docket No. FAA– 2016–9501; Directorate Identifier 2016– NM–137–AD. (a) Comments Due Date We must receive comments by February 3, 2017. (b) Affected ADs None. (c) Applicability This AD applies to The Boeing Company Model 777–200, –200LR, –300, –300ER, and 777F series airplanes, certificated in any category, identified in Boeing Special Attention Service Bulletin 777–22–0034, dated March 3, 2016. (d) Subject Air Transport Association (ATA) of America Code 22, Auto flight. mstockstill on DSK3G9T082PROD with PROPOSALS (e) Unsafe Condition This AD was prompted by reports of uncommanded altitude display changes in the mode control panel (MCP) altitude window. We are issuing this AD to prevent uncommanded changes to the MCP selected altitude; such uncommanded changes could result in incorrect spatial separation between airplanes, midair collision, or controlled flight into terrain. (f) Compliance Comply with this AD within the compliance times specified, unless already done. (g) Replacement of MCP Within 60 months after the effective date of this AD: Replace the existing MCP with a new MCP having a different part number, in accordance with the Accomplishment VerDate Sep<11>2014 18:20 Dec 19, 2016 Jkt 241001 Instructions of Boeing Special Attention Service Bulletin 777–22–0034, dated March 3, 2016. Directorate, 1601 Lind Avenue SW., Renton, WA. For information on the availability of this material at the FAA, call 425–227–1221. (h) Alternative Methods of Compliance (AMOCs) (1) The Manager, Seattle 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 (i)(1) of this AD. Information may be emailed to: 9-ANM-Seattle-ACO-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, Seattle 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) For service information that contains steps that are labeled as Required for Compliance (RC), the provisions of paragraphs (h)(4)(i) and (h)(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. Issued in Renton, Washington, on December 2, 2016. Michael Kaszycki, Acting Manager, Transport Airplane Directorate, Aircraft Certification Service. (i) Related Information (1) For more information about this AD, contact Frank Carreras, Aerospace Engineer, Systems and Equipment Branch, ANM–130S, FAA, Seattle ACO, 1601 Lind Avenue SW., Renton, WA 98057–3356; phone: 425–917– 6442; fax: 425–917–6590; email: frank.carreras@faa.gov. (2) For service information identified in this AD, contact Boeing Commercial Airplanes, Attention: Data & Services Management, P.O. Box 3707, MC 2H–65, Seattle, WA 98124–2207; telephone: 206– 544–5000, extension 1; fax: 206–766–5680; Internet: https://www.myboeingfleet.com. You may view this referenced service information at the FAA, Transport Airplane PO 00000 Frm 00040 Fmt 4702 Sfmt 4702 [FR Doc. 2016–30026 Filed 12–19–16; 8:45 am] BILLING CODE 4910–13–P DEPARTMENT OF TRANSPORTATION Federal Aviation Administration 14 CFR Part 39 [Docket No. FAA–2016–9502; Directorate Identifier 2016–NM–128–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 and –200PF series airplanes. This proposed AD was prompted by an evaluation by the design approval holder (DAH) indicating that certain areas of the frame webs are subject to widespread fatigue damage (WFD). This proposed AD would require high frequency eddy current (HFEC) inspections of the frame webs for any open coordinating holes, tooling holes, and insulation blanket attachment holes; repair if necessary; and modification of the frame webs at all open hole locations, which would terminate the repetitive inspections. We are proposing this AD to address the unsafe condition on these products. DATES: We must receive comments on this proposed AD by February 3, 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. SUMMARY: E:\FR\FM\20DEP1.SGM 20DEP1 Federal Register / Vol. 81, No. 244 / Tuesday, December 20, 2016 / Proposed Rules For service information identified in this NPRM, contact Boeing Commercial Airplanes, Attention: Data & Services Management, P.O. Box 3707, MC 2H–65, Seattle, WA 98124–2207; telephone: 206–544–5000, extension 1; fax: 206– 766–5680; 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. It is also available on the Internet at http:// www.regulations.gov by searching for and locating Docket No. FAA–2016– 9502. mstockstill on DSK3G9T082PROD with PROPOSALS 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–2016– 9502; 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 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: Muoi Vuong, Aerospace Engineer, Airframe Branch, ANM–120L, FAA, Los Angeles Aircraft Certification Office (ACO), 3960 Paramount Boulevard, Lakewood, CA 90712–4137; phone: 562–627–5205; fax: 562–627–5210; email: muoi.vuong@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– 2016–9502; Directorate Identifier 2016– NM–128–AD’’ at the beginning of your comments. We specifically invite comments on the overall regulatory, 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 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 proposed AD. VerDate Sep<11>2014 18:20 Dec 19, 2016 Jkt 241001 Discussion Fatigue damage can occur locally, in small areas or structural design details, or globally, in widespread areas. Multiple-site damage is widespread damage that occurs in a large structural element such as a single rivet line of a lap splice joining two large skin panels. Widespread damage can also occur in multiple elements such as adjacent frames or stringers. Multiple-site damage and multiple-element damage cracks are typically too small initially to be reliably detected with normal inspection methods. Without intervention, these cracks will grow, and eventually compromise the structural integrity of the airplane. This condition is known as widespread fatigue damage. It is associated with general degradation of large areas of structure with similar structural details and stress levels. As an airplane ages, WFD will likely occur, and will certainly occur if the airplane is operated long enough without any intervention. The FAA’s WFD final rule (75 FR 69746, November 15, 2010) became effective on January 14, 2011. The WFD rule requires certain actions to prevent structural failure due to WFD throughout the operational life of certain existing transport category airplanes and all of these airplanes that will be certificated in the future. For existing and future airplanes subject to the WFD rule, the rule requires that DAHs establish a limit of validity (LOV) of the engineering data that support the structural maintenance program. Operators affected by the WFD rule may not fly an airplane beyond its LOV, unless an extended LOV is approved. The WFD rule (75 FR 69746, November 15, 2010) does not require identifying and developing maintenance actions if the DAHs can show that such actions are not necessary to prevent WFD before the airplane reaches the LOV. Many LOVs, however, do depend on accomplishment of future maintenance actions. As stated in the WFD rule, any maintenance actions necessary to reach the LOV will be mandated by airworthiness directives through separate rulemaking actions. In the context of WFD, this action is necessary to enable DAHs to propose LOVs that allow operators the longest operational lives for their airplanes, and still ensure that WFD will not occur. This approach allows for an implementation strategy that provides flexibility to DAHs in determining the timing of service information development (with FAA approval), while providing operators with certainty PO 00000 Frm 00041 Fmt 4702 Sfmt 4702 92743 regarding the LOV applicable to their airplanes. We have received a report indicating that certain Model 757 airplanes have open coordinating holes, tooling holes, and insulation blanket attachment holes in the frame webs that were not filled during production. There have been no reports of frame web cracking at open hole locations. Cracking was found on a fatigue test article where WFD analysis identified the need for the inspection. Open attachment holes, if not corrected, could result in fatigue cracking that could adversely affect the structural integrity of the airplane. Related Service Information Under 1 CFR Part 51 We reviewed Boeing Alert Service Bulletin 757–53A0103, dated June 22, 2016. The service information describes procedures for performing repetitive HFEC inspections of the frame webs for any open coordinating holes, tooling holes, insulation blanket attachment holes; and modifying the frame webs between stringers S–20 and S–25. 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 accomplishing the actions specified in the service information described previously, except as discussed under ‘‘Differences Between this Proposed AD and the Service Information.’’ For information on the procedures and compliance times, see this service information at http:// www.regulations.gov by searching for and locating Docket No. FAA–2016– 9502. Differences Between This Proposed AD and the Service Information Boeing Alert Service Bulletin 757– 53A0103, dated June 22, 2016, specifies to contact the manufacturer for certain instructions, but this proposed AD would require accomplishment of repair methods, modification deviations, and alteration deviations in one of the following ways: • In accordance with a method that we approve; or E:\FR\FM\20DEP1.SGM 20DEP1 92744 Federal Register / Vol. 81, No. 244 / Tuesday, December 20, 2016 / Proposed Rules • Using data that meet the certification basis of the airplane, and that have been approved by the Boeing Commercial Airplanes Organization Designation Authorization (ODA) whom we have authorized to make those findings. Costs of Compliance We estimate that this proposed AD affects 74 airplanes of U.S. registry. We estimate the following costs to comply with this proposed AD: ESTIMATED COSTS Action Labor cost HFEC inspection .......... 68 work-hours × $85 per hour = $5,780 per inspection cycle. 1 work-hour × $85 per hour = $85 ..................... Modification .................. 1 Parts Parts cost Cost per product $0 1 $0 Cost on U.S. operators $5,780 per inspection cycle. 85 ................................. $427,720 per inspection cycle. 85. supplied by the operator. on a substantial number of small entities under the criteria of the Regulatory Flexibility Act. AD to prevent fatigue cracking that could adversely affect the reduced structural integrity of the airplane. List of Subjects in 14 CFR Part 39 (f) Compliance 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. 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. mstockstill on DSK3G9T082PROD with PROPOSALS We have received no definitive data that would enable us to provide cost estimates for the on-condition actions specified in this proposed AD. Air transportation, Aircraft, Aviation safety, Incorporation by reference, Safety. 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, VerDate Sep<11>2014 18:20 Dec 19, 2016 Jkt 241001 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 (AD): ■ The Boeing Company: Docket No. FAA– 2016–9502; Directorate Identifier 2016– NM–128–AD. (a) Comments Due Date We must receive comments by February 3, 2017. (b) Affected ADs None. (c) Applicability This AD applies to The Boeing Company Model 757–200 and –200PF series airplanes, certificated in any category, as identified in Boeing Alert Service Bulletin 757–53A0103, dated June 22, 2016. (d) Subject Air Transport Association (ATA) of America Code 53, Fuselage. (e) Unsafe Condition This AD was prompted by an evaluation by the design approval holder (DAH) indicating that the frame webs between stringers S–20 and S–25 on the left side and right side, from station (STA) 440 to STA 820 and from STA 1300 to STA 1701, are subject to widespread fatigue damage (WFD). We are issuing this PO 00000 Frm 00042 Fmt 4702 Sfmt 4702 Comply with this AD within the compliance times specified, unless already done. (g) Repetitive High Frequency Eddy Current (HFEC) Inspections of the Frame Webs At the applicable time specified in paragraph 1.E., ‘‘Compliance,’’ of Boeing Alert Service Bulletin 757–53A0103, dated June 22, 2016, do an HFEC inspection of the frame webs for any crack in any open coordinating holes, tooling holes, and insulation blanket attachment holes in accordance with the Accomplishment Instructions of Boeing Alert Service Bulletin 757–53A0103, dated June 22, 2016. If any cracking is found, repair before further flight using a method approved in accordance with the procedures specified in paragraph (i) of this AD. Repeat the inspection at the time specified in paragraph 1.E., ‘‘Compliance,’’ of Boeing Alert Service Bulletin 757–53A0103, dated June 22, 2016. (h) Modification of the Frame Webs Before the accumulation of 59,000 total flight cycles, modify the frame webs at all open hole locations, in accordance with the Accomplishment Instructions of Boeing Alert Service Bulletin 757–53A0103, dated June 22, 2016. Accomplishment of this modification terminates the repetitive inspection requirements of paragraph (g) of this AD at the modified locations only. (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 E:\FR\FM\20DEP1.SGM 20DEP1 Federal Register / Vol. 81, No. 244 / Tuesday, December 20, 2016 / Proposed Rules mstockstill on DSK3G9T082PROD with PROPOSALS 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 (g) of this AD: For service information that contains steps that are labeled as Required for Compliance (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. DEPARTMENT OF TRANSPORTATION Federal Aviation Administration 14 CFR Part 39 [Docket No. FAA–2016–9505; Directorate Identifier 2016–NM–155–AD] RIN 2120–AA64 Airworthiness Directives; Learjet, Inc. Airplanes Federal Aviation Administration (FAA), DOT. ACTION: Notice of proposed rulemaking (NPRM). AGENCY: We propose to adopt a new airworthiness directive (AD) for certain Learjet Inc. Model 60 airplanes. This proposed AD was prompted by an evaluation by the design approval holder (DAH) indicating that the upper fuselage skin under the aft oxygen line fairing is subject to multi-site damage (MSD). This proposed AD would require a one-time inspection of the fuselage skin for corrosion and related investigative and corrective actions if necessary. We are proposing this AD to address the unsafe condition on these products. SUMMARY: We must receive comments on this proposed AD by February 3, 2017. ADDRESSES: You may send comments, using the procedures found in 14 CFR 11.43 and 11.45, by any of the following (j) Related Information methods: (1) For more information about this AD, • Federal eRulemaking Portal: Go to contact Muoi Vuong, Aerospace Engineer, http://www.regulations.gov. Follow the Airframe Branch, ANM–120L, FAA, Los instructions for submitting comments. Angeles ACO, 3960 Paramount Boulevard, • Fax: 202–493–2251. Lakewood, CA 90712–4137; phone: 562–627– • Mail: U.S. Department of 5205; fax: 562–627–5210; email: Transportation, Docket Operations, M– muoi.vuong@faa.gov. 30, West Building Ground Floor, Room (2) For service information identified in W12–140, 1200 New Jersey Avenue SE., this AD, contact Boeing Commercial Washington, DC 20590. Airplanes, Attention: Data & Services • Hand Delivery: Deliver to Mail Management, P. O. Box 3707, MC 2H–65, address above between 9 a.m. and 5 Seattle, WA 98124–2207; telephone: 206– p.m., Monday through Friday, except 544–5000, extension 1; fax: 206–766–5680; Federal holidays. Internet: https://www.myboeingfleet.com. For service information identified in You may view this referenced service this NPRM, contact Learjet, Inc., One information at the FAA, Transport Airplane Learjet Way, Wichita, KS 67209–2942; Directorate, 1601 Lind Avenue SW., Renton, telephone: 316–946–2000; fax: 316– WA. For information on the availability of 946–2220; email: ac.ict@ this material at the FAA, call 425–227–1221. aero.bombardier.com; Internet: http:// Issued in Renton, Washington, on www.bombardier.com. You may view December 2, 2016. this referenced service information at Michael Kaszycki, the FAA, Transport Airplane Acting Manager, Transport Airplane Directorate, 1601 Lind Avenue SW., Directorate, Aircraft Certification Service. Renton, WA. For information on the availability of this material at the FAA, [FR Doc. 2016–30021 Filed 12–19–16; 8:45 am] call 425–227–1221. BILLING CODE 4910–13–P DATES: Examining the AD Docket You may examine the AD docket on the Internet at http:// VerDate Sep<11>2014 18:20 Dec 19, 2016 Jkt 241001 PO 00000 Frm 00043 Fmt 4702 Sfmt 4702 92745 www.regulations.gov by searching for and locating Docket No. FAA–2016– 9505; 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 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: Paul Chapman, Aerospace Engineer, Airframe Branch, ACE–118W, FAA, Wichita Aircraft Certification Office (ACO), 1801 Airport Road, Room 100, Dwight D. Eisenhower Airport, Wichita, KS 67209; phone: 316–946–4152; fax: 316–946–4107; email: Wichita-COS@ 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– 2016–9505; Directorate Identifier 2016– NM–155–AD’’ at the beginning of your comments. We specifically invite comments on the overall regulatory, 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 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 proposed AD. Discussion We have received a report indicating that the upper fuselage skin under the aft oxygen line fairing is subject to MSD (corrosion at multiple sites under the fairing). This condition, if not corrected, could result in reduced structural integrity of the airplane. Related Service Information Under 1 CFR Part 51 We reviewed Learjet 60 Service Bulletin 60–53–19, Revision 3, dated August 29, 2016. The service information describes procedures for inspections of the fuselage crown skin for corrosion and related investigative and corrective actions, if necessary. This service information is reasonably E:\FR\FM\20DEP1.SGM 20DEP1

Agencies

[Federal Register Volume 81, Number 244 (Tuesday, December 20, 2016)]
[Proposed Rules]
[Pages 92742-92745]
From the Federal Register Online via the Government Publishing Office [www.gpo.gov]
[FR Doc No: 2016-30021]


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

DEPARTMENT OF TRANSPORTATION

Federal Aviation Administration

14 CFR Part 39

[Docket No. FAA-2016-9502; Directorate Identifier 2016-NM-128-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 and -200PF series airplanes. 
This proposed AD was prompted by an evaluation by the design approval 
holder (DAH) indicating that certain areas of the frame webs are 
subject to widespread fatigue damage (WFD). This proposed AD would 
require high frequency eddy current (HFEC) inspections of the frame 
webs for any open coordinating holes, tooling holes, and insulation 
blanket attachment holes; repair if necessary; and modification of the 
frame webs at all open hole locations, which would terminate the 
repetitive inspections. We are proposing this AD to address the unsafe 
condition on these products.

DATES: We must receive comments on this proposed AD by February 3, 
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.

[[Page 92743]]

    For service information identified in this NPRM, contact Boeing 
Commercial Airplanes, Attention: Data & Services Management, P.O. Box 
3707, MC 2H-65, Seattle, WA 98124-2207; telephone: 206-544-5000, 
extension 1; fax: 206-766-5680; 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. It is also available on the Internet at http://www.regulations.gov by searching for and locating Docket No. FAA-2016-
9502.

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-2016-
9502; 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 
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: Muoi Vuong, Aerospace Engineer, 
Airframe Branch, ANM-120L, FAA, Los Angeles Aircraft Certification 
Office (ACO), 3960 Paramount Boulevard, Lakewood, CA 90712-4137; phone: 
562-627-5205; fax: 562-627-5210; email: muoi.vuong@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-2016-9502; 
Directorate Identifier 2016-NM-128-AD'' at the beginning of your 
comments. We specifically invite comments on the overall regulatory, 
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 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 proposed AD.

Discussion

    Fatigue damage can occur locally, in small areas or structural 
design details, or globally, in widespread areas. Multiple-site damage 
is widespread damage that occurs in a large structural element such as 
a single rivet line of a lap splice joining two large skin panels. 
Widespread damage can also occur in multiple elements such as adjacent 
frames or stringers. Multiple-site damage and multiple-element damage 
cracks are typically too small initially to be reliably detected with 
normal inspection methods. Without intervention, these cracks will 
grow, and eventually compromise the structural integrity of the 
airplane. This condition is known as widespread fatigue damage. It is 
associated with general degradation of large areas of structure with 
similar structural details and stress levels. As an airplane ages, WFD 
will likely occur, and will certainly occur if the airplane is operated 
long enough without any intervention.
    The FAA's WFD final rule (75 FR 69746, November 15, 2010) became 
effective on January 14, 2011. The WFD rule requires certain actions to 
prevent structural failure due to WFD throughout the operational life 
of certain existing transport category airplanes and all of these 
airplanes that will be certificated in the future. For existing and 
future airplanes subject to the WFD rule, the rule requires that DAHs 
establish a limit of validity (LOV) of the engineering data that 
support the structural maintenance program. Operators affected by the 
WFD rule may not fly an airplane beyond its LOV, unless an extended LOV 
is approved.
    The WFD rule (75 FR 69746, November 15, 2010) does not require 
identifying and developing maintenance actions if the DAHs can show 
that such actions are not necessary to prevent WFD before the airplane 
reaches the LOV. Many LOVs, however, do depend on accomplishment of 
future maintenance actions. As stated in the WFD rule, any maintenance 
actions necessary to reach the LOV will be mandated by airworthiness 
directives through separate rulemaking actions.
    In the context of WFD, this action is necessary to enable DAHs to 
propose LOVs that allow operators the longest operational lives for 
their airplanes, and still ensure that WFD will not occur. This 
approach allows for an implementation strategy that provides 
flexibility to DAHs in determining the timing of service information 
development (with FAA approval), while providing operators with 
certainty regarding the LOV applicable to their airplanes.
    We have received a report indicating that certain Model 757 
airplanes have open coordinating holes, tooling holes, and insulation 
blanket attachment holes in the frame webs that were not filled during 
production. There have been no reports of frame web cracking at open 
hole locations. Cracking was found on a fatigue test article where WFD 
analysis identified the need for the inspection. Open attachment holes, 
if not corrected, could result in fatigue cracking that could adversely 
affect the structural integrity of the airplane.

Related Service Information Under 1 CFR Part 51

    We reviewed Boeing Alert Service Bulletin 757-53A0103, dated June 
22, 2016. The service information describes procedures for performing 
repetitive HFEC inspections of the frame webs for any open coordinating 
holes, tooling holes, insulation blanket attachment holes; and 
modifying the frame webs between stringers S-20 and S-25. 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 accomplishing the actions specified 
in the service information described previously, except as discussed 
under ``Differences Between this Proposed AD and the Service 
Information.'' For information on the procedures and compliance times, 
see this service information at http://www.regulations.gov by searching 
for and locating Docket No. FAA-2016-9502.

Differences Between This Proposed AD and the Service Information

    Boeing Alert Service Bulletin 757-53A0103, dated June 22, 2016, 
specifies to contact the manufacturer for certain instructions, but 
this proposed AD would require accomplishment of repair methods, 
modification deviations, and alteration deviations in one of the 
following ways:
     In accordance with a method that we approve; or

[[Page 92744]]

     Using data that meet the certification basis of the 
airplane, and that have been approved by the Boeing Commercial 
Airplanes Organization Designation Authorization (ODA) whom we have 
authorized to make those findings.

Costs of Compliance

    We estimate that this proposed AD affects 74 airplanes of U.S. 
registry. We estimate the following costs to comply with this proposed 
AD:

                                                 Estimated Costs
----------------------------------------------------------------------------------------------------------------
                                                                                                 Cost on U.S.
              Action                    Labor cost        Parts cost      Cost per product        operators
----------------------------------------------------------------------------------------------------------------
HFEC inspection..................  68 work-hours x $85              $0  $5,780 per           $427,720 per
                                    per hour = $5,780                    inspection cycle.    inspection cycle.
                                    per inspection
                                    cycle.
Modification.....................  1 work-hour x $85            \1\ $0  85.................  85.
                                    per hour = $85.
----------------------------------------------------------------------------------------------------------------
\1\ Parts supplied by the operator.

    We have received no definitive data that would enable us to provide 
cost estimates for the on-condition actions 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.
    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-2016-9502; Directorate Identifier 
2016-NM-128-AD.

(a) Comments Due Date

    We must receive comments by February 3, 2017.

 (b) Affected ADs

    None.

 (c) Applicability

    This AD applies to The Boeing Company Model 757-200 and -200PF 
series airplanes, certificated in any category, as identified in 
Boeing Alert Service Bulletin 757-53A0103, dated June 22, 2016.

 (d) Subject

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

 (e) Unsafe Condition

    This AD was prompted by an evaluation by the design approval 
holder (DAH) indicating that the frame webs between stringers S-20 
and S-25 on the left side and right side, from station (STA) 440 to 
STA 820 and from STA 1300 to STA 1701, are subject to widespread 
fatigue damage (WFD). We are issuing this AD to prevent fatigue 
cracking that could adversely affect the reduced structural 
integrity of the airplane.

 (f) Compliance

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

 (g) Repetitive High Frequency Eddy Current (HFEC) Inspections of the 
Frame Webs

    At the applicable time specified in paragraph 1.E., 
``Compliance,'' of Boeing Alert Service Bulletin 757-53A0103, dated 
June 22, 2016, do an HFEC inspection of the frame webs for any crack 
in any open coordinating holes, tooling holes, and insulation 
blanket attachment holes in accordance with the Accomplishment 
Instructions of Boeing Alert Service Bulletin 757-53A0103, dated 
June 22, 2016. If any cracking is found, repair before further 
flight using a method approved in accordance with the procedures 
specified in paragraph (i) of this AD. Repeat the inspection at the 
time specified in paragraph 1.E., ``Compliance,'' of Boeing Alert 
Service Bulletin 757-53A0103, dated June 22, 2016.

 (h) Modification of the Frame Webs

    Before the accumulation of 59,000 total flight cycles, modify 
the frame webs at all open hole locations, in accordance with the 
Accomplishment Instructions of Boeing Alert Service Bulletin 757-
53A0103, dated June 22, 2016. Accomplishment of this modification 
terminates the repetitive inspection requirements of paragraph (g) 
of this AD at the modified locations only.

 (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

[[Page 92745]]

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 (g) of this AD: For service 
information that contains steps that are labeled as Required for 
Compliance (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 Muoi Vuong, 
Aerospace Engineer, Airframe Branch, ANM-120L, FAA, Los Angeles ACO, 
3960 Paramount Boulevard, Lakewood, CA 90712-4137; phone: 562-627-
5205; fax: 562-627-5210; email: muoi.vuong@faa.gov.
    (2) For service information identified in this AD, contact 
Boeing Commercial Airplanes, Attention: Data & Services Management, 
P. O. Box 3707, MC 2H-65, Seattle, WA 98124-2207; telephone: 206-
544-5000, extension 1; fax: 206-766-5680; 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 December 2, 2016.
Michael Kaszycki,
Acting Manager, Transport Airplane Directorate, Aircraft Certification 
Service.
[FR Doc. 2016-30021 Filed 12-19-16; 8:45 am]
 BILLING CODE 4910-13-P