Airworthiness Directives; The Boeing Company Airplanes, 3137-3140 [2016-31187]

Download as PDF Federal Register / Vol. 82, No. 7 / Wednesday, January 11, 2017 / Rules and Regulations (9) Purchase of equipment and equipment-related modifications or renovations of a facility, but only to the extent that such equipment and any related modifications or renovations are used to support another eligible activity as described in this section (the recipient may be required to secure and record the Federal interest in the equipment); and (10) Any other activity determined appropriate by the Assistant Secretary and consistent with section 27(b) of Stevenson-Wydler. (b) An ineligible activity includes, but is not limited to: (1) Use of Federal funds or matching share for equity investments; (2) Acquisition or improvement of real property; (3) Construction except to the extent provided in paragraph (a)(9) of this section; and (4) Lending programs, such as a direct loan program or capitalizing a revolving loan fund. § 312.8 Investment rates. (a) Minimum investment rate. There is no minimum investment rate for a project. (b) Maximum investment rate. The maximum investment rate for a project shall not exceed 50 percent. § 312.9 Matching share requirements. The required matching share of a project’s eligible costs may consist of cash or in-kind contribution(s) whose value can be readily determined, verified, and justified. Applicants must show at the time of application that the matching share is committed to the project, will be available as needed, and is not or will not be conditioned or encumbered in any way that would preclude its use consistent with the requirements of the investment assistance. EDA shall determine at its sole discretion whether the matching share documentation adequately addresses the requirements of this section. sradovich on DSK3GMQ082PROD with RULES § 312.10 Application components. In addition to the criteria set forth in the FFO, to be considered for a RIS Program grant, eligible applicants must provide the following information: (a) A description of the regional innovation cluster supported by the proposed activity; (b) The extent to which the regional innovation cluster is supported by the private sector, State and local units of government, and other relevant stakeholders; (c) The methods that participants in the regional innovation cluster will use VerDate Sep<11>2014 15:58 Jan 10, 2017 Jkt 241001 to encourage and solicit participation by all types of entities that might benefit from participation, including newly formed entities and rival existing participants; (d) The extent to which the regional innovation cluster is likely to stimulate innovation and have a positive effect on regional economic growth and development; (e) The capacity of participants in the regional innovation cluster to access, or contribute to, a well-trained workforce; (f) The ability of participants in the regional innovation cluster to attract additional funds to support the cluster with non-Federal funds; and (g) The likelihood that participants in the regional innovation cluster will be able to sustain activities after the grant expires. § 312.11 Application evaluation and selection criteria. (a) EDA will evaluate and select complete applications in accordance with the evaluation criteria, funding priority considerations, availability of funding, competitiveness of the application, and requirements set forth in section 27(b) of Stevenson-Wydler, the FFO, and other applicable Federal statutes and regulations. All awards are subject to the availability of funds. (b) EDA will endeavor to notify applicants as soon as practicable regarding whether their applications are selected for funding. (c) Stevenson-Wydler does not require nor does EDA provide an appeal process for denial of applications for EDA investment assistance. § 312.12 General terms and conditions for investment assistance. RIS Program grants are subject to all requirements contained in part 302 of this chapter, except §§ 302.2, 302.3, 302.9, 302.10, and 302.17. Subpart C—Regional Innovation Research and Information Program [Reserved] §§ 312.13–312.17 [Reserved] [FR Doc. 2017–00116 Filed 1–10–17; 8:45 am] PO 00000 Frm 00007 Fmt 4700 Sfmt 4700 DEPARTMENT OF TRANSPORTATION Federal Aviation Administration 14 CFR Part 39 [Docket No. FAA–2016–8181; Directorate Identifier 2016–NM–002–AD; Amendment 39–18765; AD 2016–26–07] RIN 2120–AA64 Airworthiness Directives; The Boeing Company Airplanes Federal Aviation Administration (FAA), DOT. ACTION: Final rule. AGENCY: We are adopting a new airworthiness directive (AD) for certain The Boeing Company Model 747–100, 747–100B, 747–100B SUD, 747–200B, 747–200C, 747–200F, 747–300, 747– 400, 747–400D, 747–400F, 747SR, and 747SP series airplanes. This AD was prompted by an evaluation by the design approval holder (DAH) indicating that the nose wheel well is subject to widespread fatigue damage (WFD). This AD requires modification, inspections, and corrective actions of the nose wheel body structure. We are issuing this AD to address the unsafe condition on these products. DATES: This AD is effective February 15, 2017. The Director of the Federal Register approved the incorporation by reference of a certain publication listed in this AD as of February 15, 2017. ADDRESSES: For service information identified in this final rule, 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, 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– 8181. SUMMARY: Examining the AD Docket Dated: January 3, 2017. Roy K.J. Williams, Assistant Secretary for Economic Development. BILLING CODE 3510–24–P 3137 You may examine the AD docket on the Internet at http:// www.regulations.gov by searching for and locating Docket No. FAA–2016– 8181; 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 AD, the regulatory E:\FR\FM\11JAR1.SGM 11JAR1 3138 Federal Register / Vol. 82, No. 7 / Wednesday, January 11, 2017 / Rules and Regulations evaluation, any comments received, and other information. The address for the Docket Office (phone: 800–647–5527) is Docket Management Facility, U.S. Department of Transportation, Docket Operations, M–30, West Building Ground Floor, Room W12–140, 1200 New Jersey Avenue SE., Washington, DC 20590. FOR FURTHER INFORMATION CONTACT: Nathan Weigand, Aerospace Engineer, Airframe Branch, ANM–120S, FAA, Seattle Aircraft Certification Office (ACO), 1601 Lind Avenue SW., Renton, WA 98057–3356; phone: 425–917–6428; fax: 425–917–6590; email: Nathan.P.Weigand@faa.gov. SUPPLEMENTARY INFORMATION: Discussion We issued a notice of proposed rulemaking (NPRM) to amend 14 CFR part 39 by adding an AD that would apply to certain The Boeing Company Model 747–100, 747–100B, 747–100B SUD, 747–200B, 747–200C, 747–200F, 747–300, 747–400, 747–400D, 747– 400F, 747SR, and 747SP series airplanes. The NPRM published in the Federal Register on July 28, 2016 (81 FR 49572) (‘‘the NPRM’’). The NPRM was prompted by an evaluation by the DAH indicating that the nose wheel well is subject to WFD. The NPRM proposed to require modification of the nose wheel body structure; a detailed inspection of the nose wheel body structure for any cracking; a surface HFEC or an open hole HFEC inspection of the vertical beam outer chord and web for any cracking; and all applicable related investigative actions including repetitive inspections, and other specified and corrective actions. We are issuing this AD to detect and correct fatigue cracking in the nose wheel well structure; such cracking could adversely affect the structural integrity of the airplane. Comments We gave the public the opportunity to participate in developing this AD. We have considered the comments received. Boeing and United Airlines supported the NPRM. Conclusion We reviewed the relevant data, considered the comments received, and determined that air safety and the public interest require adopting this AD as proposed, except for minor editorial changes. We have determined that these minor changes: • Are consistent with the intent that was proposed in the NPRM for correcting the unsafe condition; and • Do not add any additional burden upon the public than was already proposed in the NPRM. Since the NPRM was Issued Since the NPRM was issued, we have updated the AD with Boeing’s new contact information. Related Service Information Under 1 CFR Part 51 We reviewed Boeing Alert Service Bulletin 747–53A2887, dated December 2, 2015. The service information describes procedures for modification of the nose wheel body structure; a detailed inspection of the nose wheel body structure for any cracking; a web surface HFEC and an open hole HFEC inspection of the vertical beam outer chord for any cracking; and repair. 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. Costs of Compliance We estimate that this AD affects 107 airplanes of U.S. registry. We estimate the following costs to comply with this AD: ESTIMATED COSTS Action Labor cost Modification ....... Part 2 detailed inspection. Surface HFEC inspection. Open hole HFEC inspection. 408 work-hours × $85 per hour $34,680. 140 work-hours × $85 per hour $11,900 per inspection cycle. 4 work-hours × $85 per hour $340 per inspection cycle. 4 work-hours × $85 per hour $340 per inspection cycle. sradovich on DSK3GMQ082PROD with RULES We have received no definitive data that would enable us to provide cost estimates for the on-condition actions specified in this 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 VerDate Sep<11>2014 15:58 Jan 10, 2017 Jkt 241001 Cost per product Parts cost = $15,743 $50,423 .................................... $5,395,261. = $0 $11,900 per inspection cycle ... $1,273,300 per inspection cycle. = $0 $340 per inspection cycle ........ Up to $36,380 per inspection cycle. = $0 $340 per inspection cycle ........ Up to $36,380 per inspection cycle. 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 This AD will not have federalism implications under Executive Order 13132. This AD will not have a substantial direct effect on the States, on the relationship between the national government and the States, or on the distribution of power and PO 00000 Cost on U.S. operators Frm 00008 Fmt 4700 Sfmt 4700 responsibilities among the various levels of government. For the reasons discussed above, I certify that this AD: (1) Is not a ‘‘significant regulatory action’’ under Executive Order 12866, (2) Is not a ‘‘significant rule’’ under 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. E:\FR\FM\11JAR1.SGM 11JAR1 Federal Register / Vol. 82, No. 7 / Wednesday, January 11, 2017 / Rules and Regulations List of Subjects in 14 CFR Part 39 Air transportation, Aircraft, Aviation safety, Incorporation by reference, Safety. (h) Inspection for Groups 1 and 4 Airplanes (a) Effective Date This AD is effective February 15, 2017. For groups 1 and 4 airplanes on which the actions of paragraph (g) have been done: Except as required by paragraph (j)(1) of this AD, at the applicable time specified in paragraph 1.E., ‘‘Compliance,’’ of Boeing Alert Service Bulletin 747–53A2887, dated December 2, 2015, do a detailed inspection of the nose wheel body structure for any cracking; do a surface high frequency eddy current inspection (HFEC) or an open hole HFEC inspection of the vertical beam outer chord and web for any cracking; and do all applicable related investigative, other specified actions, and corrective actions, in accordance with the Accomplishment Instructions of Boeing Alert Service Bulletin 747–53A2887, dated December 2, 2015; except as required by paragraph (j)(2) of this AD. Do all applicable related investigative actions, other specified actions, and corrective actions before further flight. Repeat the detailed inspection of the nose wheel body structure, and either the surface HFEC or the open hole HFEC inspection of the vertical beam outer chord, thereafter, at the applicable interval specified in paragraph 1.E., ‘‘Compliance,’’ of Boeing Alert Service Bulletin 747–53A2887, dated December 2, 2015. (b) Affected ADs None. (i) Inspection for Groups 2, 3, 5 and 6 Airplanes (c) Applicability This AD applies to The Boeing Company Model 747–100, 747–100B, 747–100B SUD, 747–200B, 747–200C, 747–200F, 747–300, 747–400, 747–400D, 747–400F, 747SR, and 747SP series airplanes, certificated in any category, as identified in Boeing Alert Service Bulletin 747–53A2887, dated December 2, 2015. For groups 2, 3, 5 and 6 airplanes identified in Boeing Alert Service Bulletin 747–53A2887, dated December 2, 2015: Except as required by paragraph (j)(1) of this AD, at the applicable time specified in paragraph 1.E., ‘‘Compliance,’’ of Boeing Alert Service Bulletin 747–53A2887, dated December 2, 2015, do a detailed inspection of the nose wheel well body structure for any cracking, and do all applicable related investigative and corrective actions, in accordance with the Accomplishment Instructions of Boeing Alert Service Bulletin 747–53A2887, dated December 2, 2015; except as required by paragraph (j)(2) of this AD. Do all related investigative and corrective actions before further flight. Repeat the detailed inspection thereafter at the applicable intervals specified in paragraph 1.E., ‘‘Compliance,’’ of Boeing Alert Service Bulletin 747–53A2887, dated December 2, 2015. Adoption of the Amendment Accordingly, under the authority delegated to me by the Administrator, the FAA amends 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): ■ 2016–26–07 The Boeing Company: Amendment 39–18765; Docket No. FAA–2016–8181; Directorate Identifier 2016–NM–002–AD. (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 indicating that the nose wheel well is subject to widespread fatigue damage. We are issuing this AD to detect and correct fatigue cracking in the nose wheel well structure; such cracking could adversely affect the structural integrity of the airplane. sradovich on DSK3GMQ082PROD with RULES (f) Compliance Comply with this AD within the compliance times specified, unless already done. (g) Modification for Groups 1 and 4 Airplanes For groups 1 and 4 airplanes as identified in Boeing Alert Service Bulletin 747– 53A2887, dated December 2, 2015: Except as required by paragraph (j)(1) of this AD, at the applicable time specified in paragraph 1.E., ‘‘Compliance,’’ of Boeing Alert Service Bulletin 747–53A2887, dated December 2, 2015, modify the nose wheel body structure, in accordance with the Accomplishment Instructions of Boeing Alert Service Bulletin 747–53A2887, dated December 2, 2015. VerDate Sep<11>2014 15:58 Jan 10, 2017 Jkt 241001 (j) Exceptions to the Service Information (1) Where Boeing Alert Service Bulletin 747–53A2887, dated December 2, 2015, specifies a compliance time ‘‘after the original issue date of this service bulletin,’’ this AD requires compliance within the specified compliance time after the effective date of this AD. (2) If any crack is found during any inspection required by this AD, and Boeing Alert Service Bulletin 747–53A2887, dated December 2, 2015, specifies to contact Boeing for appropriate action, and specifies that action as ‘‘RC’’ (Required for Compliance): Before further flight, repair using a method approved in accordance with the procedures specified in paragraph (k) of this AD. PO 00000 Frm 00009 Fmt 4700 Sfmt 4700 3139 (k) 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 (l) 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) Except as required by paragraph (j)(2) of this AD: For service information that contains steps that are labeled as Required for Compliance (RC), the provisions of paragraphs (k)(4)(i) and (k)(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 sub-step is labeled ‘‘RC Exempt,’’ then the RC requirement is removed from that step or sub-step. 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. (l) Related Information For more information about this AD, contact Nathan Weigand, Aerospace Engineer, Airframe Branch, ANM–120S, FAA, Seattle ACO, 1601 Lind Avenue SW., Renton, WA 98057–3356; phone: 425–917– 6428; fax: 425–917–6590; email: Nathan.P.Weigand@faa.gov. (m) Material Incorporated by Reference (1) The Director of the Federal Register approved the incorporation by reference (IBR) of the service information listed in this paragraph under 5 U.S.C. 552(a) and 1 CFR part 51. (2) You must use this service information as applicable to do the actions required by this AD, unless the AD specifies otherwise. (i) Boeing Alert Service Bulletin 747– 53A2887, dated December 2, 2015. E:\FR\FM\11JAR1.SGM 11JAR1 3140 Federal Register / Vol. 82, No. 7 / Wednesday, January 11, 2017 / Rules and Regulations (ii) Reserved. (3) For Boeing 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. (4) 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. (5) You may view this service information that is incorporated by reference at the National Archives and Records Administration (NARA). For information on the availability of this material at NARA, call 202–741–6030, or go to: http:// www.archives.gov/federal-register/cfr/ibrlocations.html. Issued in Renton, Washington, on December 15, 2016. Victor Wicklund, Acting Manager, Transport Airplane Directorate, Aircraft Certification Service. [FR Doc. 2016–31187 Filed 1–10–17; 8:45 am] BILLING CODE 4910–13–P DEPARTMENT OF TRANSPORTATION Federal Aviation Administration 14 CFR Part 39 [Docket No. FAA–2016–6428; Directorate Identifier 2015–NM–119–AD; Amendment 39–18764; AD 2016–26–06] RIN 2120–AA64 Airworthiness Directives; The Boeing Company Airplanes Federal Aviation Administration (FAA), DOT. ACTION: Final rule. AGENCY: We are adopting a new airworthiness directive (AD) for certain The Boeing Company Model 787–8 airplanes. This AD was prompted by reports indicating that certain wing side-of-body upper stringer fittings have been installed with faying surface mismatch beyond the allowed machining tolerance. This AD requires inspections of certain stringer fittings, replacement if necessary, and replacement of certain fasteners. We are issuing this AD to address the unsafe condition on these products. DATES: This AD is effective February 15, 2017. The Director of the Federal Register approved the incorporation by reference of a certain publication listed in this AD as of February 15, 2017. ADDRESSES: For service information identified in this final rule, contact sradovich on DSK3GMQ082PROD with RULES SUMMARY: VerDate Sep<11>2014 15:58 Jan 10, 2017 Jkt 241001 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. It is also available on the Internet at http:// www.regulations.gov by searching for and locating Docket No. FAA–2016– 6428. issuing this AD to prevent an unacceptable reduction of the fatigue life in the upper side-of-body rib chord. Associated fatigue cracks can reduce the structural capability of the upper sideof-body t-chord to a point where it cannot sustain limit load, which could adversely affect the structural integrity of the airplane. Examining the AD Docket Request To Reference Revised Service Information You may examine the AD docket on the Internet at http:// www.regulations.gov by searching for and locating Docket No. FAA–2016– 6428; 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 AD, the regulatory evaluation, any comments received, and other information. The address for the Docket Office (phone: 800–647–5527) is Docket Management Facility, U.S. Department of Transportation, Docket Operations, M–30, West Building Ground Floor, Room W12–140, 1200 New Jersey Avenue SE., Washington, DC 20590. FOR FURTHER INFORMATION CONTACT: Allen Rauschendorfer, Aerospace Engineer, Airframe Branch, ANM–120S, FAA, Seattle Aircraft Certification Office (ACO), 1601 Lind Avenue SW., Renton, WA 98057–3356; phone: 425– 917–6487; fax: 425–917–6590; email: allen.rauschendorfer@faa.gov. SUPPLEMENTARY INFORMATION: Discussion We issued a notice of proposed rulemaking (NPRM) to amend 14 CFR part 39 by adding an AD that would apply to certain The Boeing Company Model 787–8 airplanes. The NPRM published in the Federal Register on May 11, 2016 (81 FR 29206) (‘‘the NPRM’’). The NPRM was prompted by reports indicating that certain wing side-of-body upper stringer fittings have been installed with faying surface mismatch beyond the allowed machining tolerance. The NPRM proposed to require inspection of certain stringer fittings for faying surface mismatch common to the side-of-body rib chord, replacement if necessary, and replacement of the clearance fit fasteners common to the side-of-body fittings and upper side-of-body rib chord with tapered sleeve bolts. We are PO 00000 Frm 00010 Fmt 4700 Sfmt 4700 Comments We gave the public the opportunity to participate in developing this AD. The following presents the comments received on the NPRM and the FAA’s response to each comment. United Airlines (UA) and All Nippon Airways (ANA) asked that we revise the NPRM to reference Boeing Alert Service Bulletin B787–81205–SB570018–00, Issue 002, because Boeing Alert Service Bulletin B787–81205–SB570018–00, Issue 001, dated July 1, 2015, is currently being revised by Boeing. UA and ANA added that by including the revised service information for accomplishing the specified actions, requests for alternative methods of compliance (AMOCs) will be reduced. We do not agree because the revised service information is not yet released. In an AD, we cannot refer to service information that does not exist because doing so violates Office of the Federal Register (OFR) regulations for approval of materials incorporated by reference in rules. To allow operators to use service information issued after publication of an AD, either we must supersede the AD to reference specific service information, or operators must request approval to use the new service information as an AMOC for the AD under the provisions of paragraph (j) of this AD. We consider addressing the unsafe condition as soon as possible a necessity. We might consider issuing a global AMOC if revised service information is approved. We have not changed this AD in this regard. Request for Clarification of the Reason for the AD Boeing asked that we clarify that the proposed AD was prompted by reports indicating that the wing side-of-body stringer fittings that were installed with a faying surface mismatch beyond allowed tolerances were the upper stringer fittings. We agree that clarification of the language describing what prompted the AD is necessary. We have changed the SUMMARY section of this final rule, as well as paragraph (e) of this AD, to E:\FR\FM\11JAR1.SGM 11JAR1

Agencies

[Federal Register Volume 82, Number 7 (Wednesday, January 11, 2017)]
[Rules and Regulations]
[Pages 3137-3140]
From the Federal Register Online via the Government Publishing Office [www.gpo.gov]
[FR Doc No: 2016-31187]


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DEPARTMENT OF TRANSPORTATION

Federal Aviation Administration

14 CFR Part 39

[Docket No. FAA-2016-8181; Directorate Identifier 2016-NM-002-AD; 
Amendment 39-18765; AD 2016-26-07]
RIN 2120-AA64


Airworthiness Directives; The Boeing Company Airplanes

AGENCY: Federal Aviation Administration (FAA), DOT.

ACTION: Final rule.

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

SUMMARY: We are adopting a new airworthiness directive (AD) for certain 
The Boeing Company Model 747-100, 747-100B, 747-100B SUD, 747-200B, 
747-200C, 747-200F, 747-300, 747-400, 747-400D, 747-400F, 747SR, and 
747SP series airplanes. This AD was prompted by an evaluation by the 
design approval holder (DAH) indicating that the nose wheel well is 
subject to widespread fatigue damage (WFD). This AD requires 
modification, inspections, and corrective actions of the nose wheel 
body structure. We are issuing this AD to address the unsafe condition 
on these products.

DATES: This AD is effective February 15, 2017.
    The Director of the Federal Register approved the incorporation by 
reference of a certain publication listed in this AD as of February 15, 
2017.

ADDRESSES: For service information identified in this final rule, 
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, 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-
8181.

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-
8181; 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 AD, the regulatory

[[Page 3138]]

evaluation, any comments received, and other information. The address 
for the Docket Office (phone: 800-647-5527) is Docket Management 
Facility, U.S. Department of Transportation, Docket Operations, M-30, 
West Building Ground Floor, Room W12-140, 1200 New Jersey Avenue SE., 
Washington, DC 20590.

FOR FURTHER INFORMATION CONTACT: Nathan Weigand, Aerospace Engineer, 
Airframe Branch, ANM-120S, FAA, Seattle Aircraft Certification Office 
(ACO), 1601 Lind Avenue SW., Renton, WA 98057-3356; phone: 425-917-
6428; fax: 425-917-6590; email: Nathan.P.Weigand@faa.gov.

SUPPLEMENTARY INFORMATION: 

Discussion

    We issued a notice of proposed rulemaking (NPRM) to amend 14 CFR 
part 39 by adding an AD that would apply to certain The Boeing Company 
Model 747-100, 747-100B, 747-100B SUD, 747-200B, 747-200C, 747-200F, 
747-300, 747-400, 747-400D, 747-400F, 747SR, and 747SP series 
airplanes. The NPRM published in the Federal Register on July 28, 2016 
(81 FR 49572) (``the NPRM''). The NPRM was prompted by an evaluation by 
the DAH indicating that the nose wheel well is subject to WFD. The NPRM 
proposed to require modification of the nose wheel body structure; a 
detailed inspection of the nose wheel body structure for any cracking; 
a surface HFEC or an open hole HFEC inspection of the vertical beam 
outer chord and web for any cracking; and all applicable related 
investigative actions including repetitive inspections, and other 
specified and corrective actions. We are issuing this AD to detect and 
correct fatigue cracking in the nose wheel well structure; such 
cracking could adversely affect the structural integrity of the 
airplane.

Comments

    We gave the public the opportunity to participate in developing 
this AD. We have considered the comments received. Boeing and United 
Airlines supported the NPRM.

Conclusion

    We reviewed the relevant data, considered the comments received, 
and determined that air safety and the public interest require adopting 
this AD as proposed, except for minor editorial changes. We have 
determined that these minor changes:
     Are consistent with the intent that was proposed in the 
NPRM for correcting the unsafe condition; and
     Do not add any additional burden upon the public than was 
already proposed in the NPRM.

Since the NPRM was Issued

    Since the NPRM was issued, we have updated the AD with Boeing's new 
contact information.

Related Service Information Under 1 CFR Part 51

    We reviewed Boeing Alert Service Bulletin 747-53A2887, dated 
December 2, 2015. The service information describes procedures for 
modification of the nose wheel body structure; a detailed inspection of 
the nose wheel body structure for any cracking; a web surface HFEC and 
an open hole HFEC inspection of the vertical beam outer chord for any 
cracking; and repair. 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.

Costs of Compliance

    We estimate that this AD affects 107 airplanes of U.S. registry.
    We estimate the following costs to comply with this AD:

                                                                     Estimated Costs
--------------------------------------------------------------------------------------------------------------------------------------------------------
           Action                  Labor cost         Parts cost               Cost per product                        Cost on U.S. operators
--------------------------------------------------------------------------------------------------------------------------------------------------------
Modification................  408 work-hours x $85         $15,743  $50,423..............................  $5,395,261.
                               per hour = $34,680.
Part 2 detailed inspection..  140 work-hours x $85              $0  $11,900 per inspection cycle.........  $1,273,300 per inspection cycle.
                               per hour = $11,900
                               per inspection
                               cycle.
Surface HFEC inspection.....  4 work[dash]hours x               $0  $340 per inspection cycle............  Up to $36,380 per inspection cycle.
                               $85 per hour = $340
                               per inspection
                               cycle.
Open hole HFEC inspection...  4 work-hours x $85                $0  $340 per inspection cycle............  Up to $36,380 per inspection cycle.
                               per hour = $340 per
                               inspection cycle.
--------------------------------------------------------------------------------------------------------------------------------------------------------

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

    This AD will not have federalism implications under Executive Order 
13132. This AD will not have a substantial direct effect on the States, 
on the relationship between the national government and the States, or 
on the distribution of power and responsibilities among the various 
levels of government.
    For the reasons discussed above, I certify that this AD:
    (1) Is not a ``significant regulatory action'' under Executive 
Order 12866,
    (2) Is not a ``significant rule'' under 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.

[[Page 3139]]

List of Subjects in 14 CFR Part 39

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

Adoption of the Amendment

    Accordingly, under the authority delegated to me by the 
Administrator, the FAA amends 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):

2016-26-07 The Boeing Company: Amendment 39-18765; Docket No. FAA-
2016-8181; Directorate Identifier 2016-NM-002-AD.

(a) Effective Date

    This AD is effective February 15, 2017.

(b) Affected ADs

    None.

(c) Applicability

    This AD applies to The Boeing Company Model 747-100, 747-100B, 
747-100B SUD, 747-200B, 747-200C, 747-200F, 747-300, 747-400, 747-
400D, 747-400F, 747SR, and 747SP series airplanes, certificated in 
any category, as identified in Boeing Alert Service Bulletin 747-
53A2887, dated December 2, 2015.

(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 indicating that the nose wheel well is subject to widespread 
fatigue damage. We are issuing this AD to detect and correct fatigue 
cracking in the nose wheel well structure; such cracking could 
adversely affect the structural integrity of the airplane.

(f) Compliance

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

(g) Modification for Groups 1 and 4 Airplanes

    For groups 1 and 4 airplanes as identified in Boeing Alert 
Service Bulletin 747-53A2887, dated December 2, 2015: Except as 
required by paragraph (j)(1) of this AD, at the applicable time 
specified in paragraph 1.E., ``Compliance,'' of Boeing Alert Service 
Bulletin 747-53A2887, dated December 2, 2015, modify the nose wheel 
body structure, in accordance with the Accomplishment Instructions 
of Boeing Alert Service Bulletin 747-53A2887, dated December 2, 
2015.

(h) Inspection for Groups 1 and 4 Airplanes

    For groups 1 and 4 airplanes on which the actions of paragraph 
(g) have been done: Except as required by paragraph (j)(1) of this 
AD, at the applicable time specified in paragraph 1.E., 
``Compliance,'' of Boeing Alert Service Bulletin 747-53A2887, dated 
December 2, 2015, do a detailed inspection of the nose wheel body 
structure for any cracking; do a surface high frequency eddy current 
inspection (HFEC) or an open hole HFEC inspection of the vertical 
beam outer chord and web for any cracking; and do all applicable 
related investigative, other specified actions, and corrective 
actions, in accordance with the Accomplishment Instructions of 
Boeing Alert Service Bulletin 747-53A2887, dated December 2, 2015; 
except as required by paragraph (j)(2) of this AD. Do all applicable 
related investigative actions, other specified actions, and 
corrective actions before further flight. Repeat the detailed 
inspection of the nose wheel body structure, and either the surface 
HFEC or the open hole HFEC inspection of the vertical beam outer 
chord, thereafter, at the applicable interval specified in paragraph 
1.E., ``Compliance,'' of Boeing Alert Service Bulletin 747-53A2887, 
dated December 2, 2015.

(i) Inspection for Groups 2, 3, 5 and 6 Airplanes

    For groups 2, 3, 5 and 6 airplanes identified in Boeing Alert 
Service Bulletin 747-53A2887, dated December 2, 2015: Except as 
required by paragraph (j)(1) of this AD, at the applicable time 
specified in paragraph 1.E., ``Compliance,'' of Boeing Alert Service 
Bulletin 747-53A2887, dated December 2, 2015, do a detailed 
inspection of the nose wheel well body structure for any cracking, 
and do all applicable related investigative and corrective actions, 
in accordance with the Accomplishment Instructions of Boeing Alert 
Service Bulletin 747-53A2887, dated December 2, 2015; except as 
required by paragraph (j)(2) of this AD. Do all related 
investigative and corrective actions before further flight. Repeat 
the detailed inspection thereafter at the applicable intervals 
specified in paragraph 1.E., ``Compliance,'' of Boeing Alert Service 
Bulletin 747-53A2887, dated December 2, 2015.

(j) Exceptions to the Service Information

    (1) Where Boeing Alert Service Bulletin 747-53A2887, dated 
December 2, 2015, specifies a compliance time ``after the original 
issue date of this service bulletin,'' this AD requires compliance 
within the specified compliance time after the effective date of 
this AD.
    (2) If any crack is found during any inspection required by this 
AD, and Boeing Alert Service Bulletin 747-53A2887, dated December 2, 
2015, specifies to contact Boeing for appropriate action, and 
specifies that action as ``RC'' (Required for Compliance): Before 
further flight, repair using a method approved in accordance with 
the procedures specified in paragraph (k) of this AD.

(k) 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 (l) of this AD. 
Information may be emailed to: 9-ANM-Seattle-ACO-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, 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) Except as required by paragraph (j)(2) of this AD: For 
service information that contains steps that are labeled as Required 
for Compliance (RC), the provisions of paragraphs (k)(4)(i) and 
(k)(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 sub-step is labeled ``RC Exempt,'' then 
the RC requirement is removed from that step or sub-step. 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.

(l) Related Information

    For more information about this AD, contact Nathan Weigand, 
Aerospace Engineer, Airframe Branch, ANM-120S, FAA, Seattle ACO, 
1601 Lind Avenue SW., Renton, WA 98057-3356; phone: 425-917-6428; 
fax: 425-917-6590; email: Nathan.P.Weigand@faa.gov.

(m) Material Incorporated by Reference

    (1) The Director of the Federal Register approved the 
incorporation by reference (IBR) of the service information listed 
in this paragraph under 5 U.S.C. 552(a) and 1 CFR part 51.
    (2) You must use this service information as applicable to do 
the actions required by this AD, unless the AD specifies otherwise.
    (i) Boeing Alert Service Bulletin 747-53A2887, dated December 2, 
2015.

[[Page 3140]]

    (ii) Reserved.
    (3) For Boeing 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.
    (4) 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.
    (5) You may view this service information that is incorporated 
by reference at the National Archives and Records Administration 
(NARA). For information on the availability of this material at 
NARA, call 202-741-6030, or go to: http://www.archives.gov/federal-register/cfr/ibr-locations.html.

    Issued in Renton, Washington, on December 15, 2016.
Victor Wicklund,
Acting Manager, Transport Airplane Directorate, Aircraft Certification 
Service.
[FR Doc. 2016-31187 Filed 1-10-17; 8:45 am]
 BILLING CODE 4910-13-P