Airworthiness Directives; The Boeing Company Airplanes, 43642-43645 [2015-17955]

Download as PDF 43642 Federal Register / Vol. 80, No. 141 / Thursday, July 23, 2015 / Proposed Rules (2) The analysis will include an assessment of the projected losses, net income, and pro forma capital levels and regulatory capital ratios and other capital ratios for the covered company and use such analytical techniques that the Board determines are appropriate to identify, measure, and monitor risks of the covered company that may affect the financial stability of the United States. * * * * * ■ 10. Section 252.45 is amended by revising paragraph (b)(2) to read as follows: § 252.45 Data and information required to be submitted in support of the Board’s analyses. * * * * * (b) * * * (2) Project a company’s pre-provision net revenue, losses, provision for loan and lease losses, and net income; and, pro forma capital levels, regulatory capital ratios, and any other capital ratio specified by the Board under the scenarios described in § 252.44(b). * * * * * ■ 11. Section 252.52 is amended by: ■ a. Revising paragraph (n); and ■ b. removing paragraph (t). The revision to read as follows: § 252.52 Definitions. * * * * * (n) Regulatory capital ratio means a capital ratio for which the Board established minimum requirements for the company by regulation or order, including the company’s tier 1 and supplementary leverage ratios as calculated under 12 CFR part 217, including the deductions required under 12 CFR 248.12, as applicable, and the company’s common equity tier 1, tier 1, and total risk-based capital ratios as calculated under 12 CFR part 217, including the deductions required under 12 CFR 248.12 and the transition provisions at 12 CFR 217.1(f)(4) and 12 CFR 217.300, or any successor regulation; except that, the company shall not use the advanced approaches to calculate its regulatory capital ratios. * * * * * ■ 12. Section 252.53 is amended by revising paragraph (b)(3) to read as follows: mstockstill on DSK4VPTVN1PROD with PROPOSALS § 252.53 Applicability. * * * * * (b) * * * (3) Transition periods for covered companies subject to the supplementary leverage ratio. Notwithstanding § 252.52(n) of this subpart, only for purposes of the stress test cycle beginning on January 1, 2016, a bank holding company shall not include an VerDate Sep<11>2014 19:18 Jul 22, 2015 Jkt 235001 estimate of its supplementary leverage ratio. * * * * * ■ 13. Section 252.56 is amended by revising paragraphs (a)(2), (b)(2)(i), and (b)(2)(iv) to read as follows: § 252.56 Disclosure of stress test results. * * * * * (b) * * * (3) * * * (v) Pro forma regulatory capital ratios and any other capital ratios specified by the Board; (4) An explanation of the most significant causes for the changes in regulatory capital ratios; and * * * * * (c) * * * (2) The disclosure of pro forma regulatory capital ratios and any other capital ratios specified by the Board that is required under paragraph (b) of this section must include the beginning value, ending value, and minimum value of each ratio over the planning horizon. * * * * * PO 00000 [FR Doc. 2015–18038 Filed 7–22–15; 8:45 am] BILLING CODE P Methodologies and practices. (a) * * * (2) The potential impact on pro forma regulatory capital levels and pro forma capital ratios (including regulatory capital ratios and any other capital ratios specified by the Board), incorporating the effects of any capital actions over the planning horizon and maintenance of an allowance for loan losses appropriate for credit exposures throughout the planning horizon. (b) * * * (2) * * * (i) Common stock dividends equal to the quarterly average dollar amount of common stock dividends that the company paid in the previous year (that is, the first quarter of the planning horizon and the preceding three calendar quarters) plus common stock dividends attributable to issuances related to expensed employee compensation; * * * * * (iv) An assumption of no issuances of common stock or preferred stock, except for issuances related to expensed employee compensation or in connection with a planned merger or acquisition to the extent that the merger or acquisition is reflected in the covered company’s pro forma balance sheet estimates. * * * * * ■ 14. Section 252.58 is amended by revising paragraphs (b)(3)(v), (b)(4), and (c)(2) to read as follows: § 252.58 By order of the Board of Governors of the Federal Reserve System, July 17, 2015. Margaret McCloskey Shanks, Deputy Secretary of the Board. Frm 00006 Fmt 4702 Sfmt 4702 DEPARTMENT OF TRANSPORTATION Federal Aviation Administration 14 CFR Part 39 [Docket No. FAA–2015–2958; Directorate Identifier 2014–NM–248–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 all The Boeing Company Model 787 airplanes. This proposed AD was prompted by the disclosure that the inner diameters of some batches of landing gear pins were not shot peened in accordance with design specifications and need to be replaced. This proposed AD would require inspection for improperly manufactured landing gear pins, and replacement if necessary. We are proposing this AD to detect and correct insufficient shot peening that could lead to stress corrosion cracking and failure of the landing gear pin, and cause landing gear collapse and inability to control the airplane at high speeds on the ground. DATES: We must receive comments on this proposed AD by September 8, 2015. ADDRESSES: You may send comments, using the procedures found in 14 CFR 11.43 and 11.45, by any of the following methods: • Federal eRulemaking Portal: Go to https://www.regulations.gov. Follow the instructions for submitting comments. • Fax: 202–493–2251. • Mail: U.S. Department of Transportation, Docket Operations, M– 30, West Building Ground Floor, Room W12–140, 1200 New Jersey Avenue SE., Washington, DC 20590. • Hand Delivery: Deliver to Mail address above between 9 a.m. and 5 p.m., Monday through Friday, except Federal holidays. For service information identified in this proposed AD, contact Boeing Commercial Airplanes, Attention: Data & Services Management, P. O. Box 3707, MC 2H–65, Seattle, WA 98124–2207; SUMMARY: E:\FR\FM\23JYP1.SGM 23JYP1 43643 Federal Register / Vol. 80, No. 141 / Thursday, July 23, 2015 / Proposed Rules 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 https:// www.regulations.gov by searching for and locating Docket No. FAA–2015– 2958. Examining the AD Docket You may examine the AD docket on the Internet at https:// www.regulations.gov by searching for and locating Docket No. FAA–2015– 2958; 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: Melanie Violette, Senior Aerospace Engineer, Airframe Branch, ANM–120S, FAA, Seattle Aircraft Certification Office (ACO), 1601 Lind Avenue SW., Renton, WA 98057–3356; phone: 425– 917–6422; fax: 425–917–6590; email: melanie.violette@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– 2015–2958; Directorate Identifier 2014– NM–248–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 https:// 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 inner diameters of some batches of landing gear pins were not shot peened and need to be replaced. On high strength steel parts, shot peening increases fatigue life and reduces the likelihood of stress corrosion cracking. Stress corrosion cracking, if not corrected, could result in failure of the landing gear pin, and consequent landing gear collapse and the inability to control the airplane at high speeds on the ground. Related Service Information Under 1 CFR Part 51 We reviewed Boeing Alert Service Bulletin B787–81205–SB320022–00, Issue 001, dated November 14, 2014. The service information describes procedures for the inspection for improperly manufactured landing gear pins (parts that were not shot peened), and replacement if necessary. 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 of this NPRM. 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.’’ Refer to this service information for details on the procedures and compliance times. Differences Between This Proposed AD and the Service Information Boeing Alert Service Bulletin B787– 81205–SB320022–00, Issue 001, dated November 14, 2014, limits the effectivity in Group 2 to airplanes delivered prior to the publication of Boeing Alert Service Bulletin B787– 81205–SB320022–00, Issue 001, dated November 14, 2014. However, this NPRM does not propose to include that limitation. The applicability of this proposed AD includes all The Boeing Company Model 787 airplanes. Because the affected landing gear pins are rotable parts, we have determined that these parts could later be installed on production airplanes, thereby subjecting those airplanes to the unsafe condition. This difference has been coordinated with Boeing. Costs of Compliance We estimate that this proposed AD affects 13 airplanes of U.S. registry. We estimate the following costs to comply with this proposed AD: ESTIMATED COSTS Action Labor cost Inspection ........................................................ 3 work-hours × $85 per hour = $255 ............. mstockstill on DSK4VPTVN1PROD with PROPOSALS We estimate the following costs to do any necessary replacements that would Cost per product Parts cost $0 be required based on the results of the proposed inspection. We have no way of Cost on U.S. operators $255 determining the number of aircraft that might need these replacements: ON-CONDITION COSTS Action Labor cost Replacement ............................................ Up to 19 work-hours × $85 per hour = $1,615. VerDate Sep<11>2014 19:18 Jul 22, 2015 Jkt 235001 PO 00000 Frm 00007 Fmt 4702 Parts cost Sfmt 4702 $3,315 $35,569 E:\FR\FM\23JYP1.SGM Cost per product Up to $37,184 23JYP1 43644 Federal Register / Vol. 80, No. 141 / Thursday, July 23, 2015 / Proposed Rules Explanation of ‘‘RC’’ Steps in Service Information The FAA worked in conjunction with industry, under the Airworthiness Directive Implementation Aviation Rulemaking Committee (ARC), to enhance the AD system. One enhancement was a new process for annotating which steps in the service information are required for compliance with an AD. Differentiating these steps from other tasks in the service information is expected to improve an owner’s/operator’s understanding of crucial AD requirements and help provide consistent judgment in AD compliance. The steps identified as RC (required for compliance) in any service information identified previously have a direct effect on detecting, preventing, resolving, or eliminating an identified unsafe condition. For service information that contains steps that are labeled as Required for Compliance (RC), the following provisions apply: (1) 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, and an AMOC is required for any deviations to RC steps, including substeps and identified figures; and (2) 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. mstockstill on DSK4VPTVN1PROD with PROPOSALS Authority for This Rulemaking 19:18 Jul 22, 2015 Jkt 235001 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 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. VerDate Sep<11>2014 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. [Amended] 2. The FAA amends § 39.13 by adding the following new airworthiness directive (AD): ■ The Boeing Company: Docket No. FAA– 2015–2958; Directorate Identifier 2014– NM–248–AD. (a) Comments Due Date We must receive comments by September 8, 2015. (b) Affected ADs None. (c) Applicability This AD applies to all The Boeing Company Model 787 airplanes, certificated in any category. (d) Subject Air Transport Association (ATA) of America Code 32, Landing Gear. (e) Unsafe Condition This AD was prompted by the disclosure that the inner diameters of some batches of PO 00000 Frm 00008 Fmt 4702 Sfmt 4702 landing gear pins were not shot peened in accordance with design specifications and need to be replaced. We are issuing this AD to detect and correct insufficient shot peening that could lead to stress corrosion cracking and failure of the landing gear pin, and cause landing gear collapse and inability to control the airplane at high speeds on the ground. (f) Compliance Comply with this AD within the compliance times specified, unless already done. (g) Inspection and Replacement At the applicable time specified in paragraph 5, ‘‘Compliance,’’ of Boeing Alert Service Bulletin B787–81205–SB320022–00, Issue 001, dated November 14, 2014, do a landing gear pin part number and serial number inspection, in accordance with the Accomplishment Instructions of Boeing Alert Service Bulletin B787–81205–SB320022–00, dated November 14, 2014. A review of airplane maintenance or delivery records is acceptable in lieu of this inspection if the part number and serial number of the installed landing gear pins can be conclusively determined from that review. (1) If no part number or serial number is found that matches the list of affected pin numbers: No further action is required by this paragraph at that pin location. (2) If any part number or serial number is found that matches the list of affected pin numbers: At the applicable time specified in paragraph 5, ‘‘Compliance,’’ of Boeing Alert Service Bulletin B787–81205–SB320022–00, Issue 001, dated November 14, 2014, replace the affected pin with a pin that does not have an affected part number and serial number, in accordance with the Accomplishment Instructions of Boeing Alert Service Bulletin B787–81205–SB320022–00, Issue 001, dated November 14, 2014. (h) Parts Installation Prohibition As of the effective date of this AD, no person may install on any airplane a landing gear pin having an affected part or serial number identified in Boeing Alert Service Bulletin B787–81205–SB320022–00, Issue 001, dated November 14, 2014. (i) 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 (j)(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 E:\FR\FM\23JYP1.SGM 23JYP1 Federal Register / Vol. 80, No. 141 / Thursday, July 23, 2015 / Proposed Rules 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. For a repair method to be approved, the repair 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 (i)(4)(i) and (i)(4)(ii) 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. 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 Melanie Violette, Senior Aerospace Engineer, Airframe Branch, ANM–120S, FAA, Seattle Aircraft Certification Office (ACO), 1601 Lind Avenue SW., Renton, WA 98057–3356; phone: 425–917–6422; fax: 425– 917–6590; email: melanie.violette@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 July 14, 2015. Suzanne Masterson, Acting Manager, Transport Airplane Directorate, Aircraft Certification Service. [FR Doc. 2015–17955 Filed 7–22–15; 8:45 am] BILLING CODE 4910–13–P DEPARTMENT OF TRANSPORTATION 14 CFR Part 39 [Docket No. FAA–2015–2568; Directorate Identifier 2014–SW–026–AD] mstockstill on DSK4VPTVN1PROD with PROPOSALS RIN 2120–AA64 Airworthiness Directives; Airbus Helicopters (Previously Eurocopter France) Helicopters Federal Aviation Administration (FAA), DOT. ACTION: Notice of proposed rulemaking (NPRM). VerDate Sep<11>2014 19:18 Jul 22, 2015 Jkt 235001 You may send comments by any of the following methods: • Federal eRulemaking Docket: Go to https://www.regulations.gov. Follow the online instructions for sending your comments electronically. • Fax: 202–493–2251. • Mail: Send comments to the U.S. Department of Transportation, Docket Operations, M–30, West Building Ground Floor, Room W12–140, 1200 New Jersey Avenue SE., Washington, DC 20590–0001. • Hand Delivery: Deliver to the ‘‘Mail’’ address between 9 a.m. and 5 p.m., Monday through Friday, except Federal holidays. ADDRESSES: Examining the AD Docket Federal Aviation Administration AGENCY: We propose to supersede airworthiness directive (AD) 2014–07– 52 for certain Airbus Helicopters (previously Eurocopter France) Model AS350B, AS350BA, AS350B1, AS350B2, AS350B3, AS350C, AS350D, AS350D1, AS355E, AS355F, AS355F1, AS355F2, AS355N, and AS355NP helicopters. AD 2014–07–52 currently requires repetitively inspecting certain reinforcement angles of the rear structure to tailboom junction frame (reinforcement angles) for a crack at 10 hour time-in-service (TIS) intervals, repairing any cracked reinforcement angle, and allows an optional repetitive inspection with a 165 hour TIS inspection interval as a terminating action for the 10 hour TIS inspections. This proposed AD would retain the inspection requirements of AD 2014– 07–52 and require the inspection of the area around each reinforcement angle screw hole as terminating action to the 10 hour TIS inspections. These proposed actions are intended to detect a crack in the reinforcement angle, which if not corrected, could result in loss of the tailboom and subsequent loss of control of the helicopter. DATES: We must receive comments on this proposed AD by September 21, 2015. SUMMARY: You may examine the AD docket on the Internet at https:// www.regulations.gov or in person at the Docket Operations Office between 9 a.m. and 5 p.m., Monday through Friday, except Federal holidays. The AD docket contains this proposed AD, the European Aviation Safety Agency (EASA) AD, the economic 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. PO 00000 Frm 00009 Fmt 4702 Sfmt 4702 43645 For service information identified in this proposed AD, contact Airbus Helicopters, Inc., 2701 N. Forum Drive, Grand Prairie, TX 75052; telephone (972) 641–0000 or (800) 232–0323; fax (972) 641–3775; or at https:// www.airbushelicopters.com/techpub. You may review service information at the FAA, Office of the Regional Counsel, Southwest Region, 10101 Hillwood Pkwy., Room 6N–321, Fort Worth, TX 76177. FOR FURTHER INFORMATION CONTACT: Robert Grant, Aviation Safety Engineer, Safety Management Group, FAA, 10101 Hillwood Pkwy., Fort Worth, TX 76177; telephone (817) 222–5110; email robert.grant@faa.gov. SUPPLEMENTARY INFORMATION: Comments Invited We invite you to participate in this rulemaking by submitting written comments, data, or views. We also invite comments relating to the economic, environmental, energy, or federalism impacts that might result from adopting the proposals in this document. The most helpful comments reference a specific portion of the proposal, explain the reason for any recommended change, and include supporting data. To ensure the docket does not contain duplicate comments, commenters should send only one copy of written comments, or if comments are filed electronically, commenters should submit only one time. We will file in the docket all comments that we receive, as well as a report summarizing each substantive public contact with FAA personnel concerning this proposed rulemaking. Before acting on this proposal, we will consider all comments we receive on or before the closing date for comments. We will consider comments filed after the comment period has closed if it is possible to do so without incurring expense or delay. We may change this proposal in light of the comments we receive. Discussion On May 21, 2014, we issued AD 2014–07–52, Amendment 39–17858, 79 FR 33054, June 10, 2014) for Airbus Helicopters Model AS350B, AS350BA, AS350B1, AS350B2, AS350B3, AS350C, AS350D, AS350D1, AS355E, AS355F, AS355F1, AS355F2, AS355N, and AS355NP helicopters with Modification (MOD) 07 3215 installed or with a reinforcement angle, part-number (P/N) 350A08.2493.21 or 350A08.2493.23, installed. AD 2014–07–52 requires, for helicopters with 640 or more hours TIS, within 10 hours TIS and thereafter at E:\FR\FM\23JYP1.SGM 23JYP1

Agencies

[Federal Register Volume 80, Number 141 (Thursday, July 23, 2015)]
[Proposed Rules]
[Pages 43642-43645]
From the Federal Register Online via the Government Publishing Office [www.gpo.gov]
[FR Doc No: 2015-17955]


=======================================================================
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DEPARTMENT OF TRANSPORTATION

Federal Aviation Administration

14 CFR Part 39

[Docket No. FAA-2015-2958; Directorate Identifier 2014-NM-248-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 all 
The Boeing Company Model 787 airplanes. This proposed AD was prompted 
by the disclosure that the inner diameters of some batches of landing 
gear pins were not shot peened in accordance with design specifications 
and need to be replaced. This proposed AD would require inspection for 
improperly manufactured landing gear pins, and replacement if 
necessary. We are proposing this AD to detect and correct insufficient 
shot peening that could lead to stress corrosion cracking and failure 
of the landing gear pin, and cause landing gear collapse and inability 
to control the airplane at high speeds on the ground.

DATES: We must receive comments on this proposed AD by September 8, 
2015.

ADDRESSES: You may send comments, using the procedures found in 14 CFR 
11.43 and 11.45, by any of the following methods:
     Federal eRulemaking Portal: Go to https://www.regulations.gov. Follow the instructions for submitting comments.
     Fax: 202-493-2251.
     Mail: U.S. Department of Transportation, Docket 
Operations, M-30, West Building Ground Floor, Room W12-140, 1200 New 
Jersey Avenue SE., Washington, DC 20590.
     Hand Delivery: Deliver to Mail address above between 9 
a.m. and 5 p.m., Monday through Friday, except Federal holidays.
    For service information identified in this proposed AD, contact 
Boeing Commercial Airplanes, Attention: Data & Services Management, P. 
O. Box 3707, MC 2H-65, Seattle, WA 98124-2207;

[[Page 43643]]

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 https://www.regulations.gov by searching for and locating 
Docket No. FAA-2015-2958.

Examining the AD Docket

    You may examine the AD docket on the Internet at https://www.regulations.gov by searching for and locating Docket No. FAA-2015-
2958; 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: Melanie Violette, Senior Aerospace 
Engineer, Airframe Branch, ANM-120S, FAA, Seattle Aircraft 
Certification Office (ACO), 1601 Lind Avenue SW., Renton, WA 98057-
3356; phone: 425-917-6422; fax: 425-917-6590; email: 
melanie.violette@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-2015-2958; 
Directorate Identifier 2014-NM-248-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 https://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 inner diameters of 
some batches of landing gear pins were not shot peened and need to be 
replaced. On high strength steel parts, shot peening increases fatigue 
life and reduces the likelihood of stress corrosion cracking. Stress 
corrosion cracking, if not corrected, could result in failure of the 
landing gear pin, and consequent landing gear collapse and the 
inability to control the airplane at high speeds on the ground.

Related Service Information Under 1 CFR Part 51

    We reviewed Boeing Alert Service Bulletin B787-81205-SB320022-00, 
Issue 001, dated November 14, 2014. The service information describes 
procedures for the inspection for improperly manufactured landing gear 
pins (parts that were not shot peened), and replacement if necessary. 
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 of this NPRM.

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.'' Refer to this service information for details on the 
procedures and compliance times.

Differences Between This Proposed AD and the Service Information

    Boeing Alert Service Bulletin B787-81205-SB320022-00, Issue 001, 
dated November 14, 2014, limits the effectivity in Group 2 to airplanes 
delivered prior to the publication of Boeing Alert Service Bulletin 
B787-81205-SB320022-00, Issue 001, dated November 14, 2014. However, 
this NPRM does not propose to include that limitation. The 
applicability of this proposed AD includes all The Boeing Company Model 
787 airplanes. Because the affected landing gear pins are rotable 
parts, we have determined that these parts could later be installed on 
production airplanes, thereby subjecting those airplanes to the unsafe 
condition. This difference has been coordinated with Boeing.

Costs of Compliance

    We estimate that this proposed AD affects 13 airplanes of U.S. 
registry. We estimate the following costs to comply with this proposed 
AD:

                                                 Estimated Costs
----------------------------------------------------------------------------------------------------------------
                                                                                     Cost per      Cost on U.S.
                Action                         Labor cost           Parts cost        product        operators
----------------------------------------------------------------------------------------------------------------
Inspection............................  3 work-hours x $85 per                $0            $255          $3,315
                                         hour = $255.
----------------------------------------------------------------------------------------------------------------

    We estimate the following costs to do any necessary replacements 
that would be required based on the results of the proposed inspection. 
We have no way of determining the number of aircraft that might need 
these replacements:

                                               On-Condition Costs
----------------------------------------------------------------------------------------------------------------
                 Action                           Labor cost            Parts cost         Cost per product
----------------------------------------------------------------------------------------------------------------
Replacement.............................  Up to 19 work-hours x $85          $35,569  Up to $37,184
                                           per hour = $1,615.
----------------------------------------------------------------------------------------------------------------


[[Page 43644]]

Explanation of ``RC'' Steps in Service Information

    The FAA worked in conjunction with industry, under the 
Airworthiness Directive Implementation Aviation Rulemaking Committee 
(ARC), to enhance the AD system. One enhancement was a new process for 
annotating which steps in the service information are required for 
compliance with an AD. Differentiating these steps from other tasks in 
the service information is expected to improve an owner's/operator's 
understanding of crucial AD requirements and help provide consistent 
judgment in AD compliance. The steps identified as RC (required for 
compliance) in any service information identified previously have a 
direct effect on detecting, preventing, resolving, or eliminating an 
identified unsafe condition.
    For service information that contains steps that are labeled as 
Required for Compliance (RC), the following provisions apply: (1) 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, 
and an AMOC is required for any deviations to RC steps, including 
substeps and identified figures; and (2) 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.

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-2015-2958; Directorate Identifier 
2014-NM-248-AD.

(a) Comments Due Date

    We must receive comments by September 8, 2015.

(b) Affected ADs

    None.

(c) Applicability

    This AD applies to all The Boeing Company Model 787 airplanes, 
certificated in any category.

(d) Subject

    Air Transport Association (ATA) of America Code 32, Landing 
Gear.

(e) Unsafe Condition

    This AD was prompted by the disclosure that the inner diameters 
of some batches of landing gear pins were not shot peened in 
accordance with design specifications and need to be replaced. We 
are issuing this AD to detect and correct insufficient shot peening 
that could lead to stress corrosion cracking and failure of the 
landing gear pin, and cause landing gear collapse and inability to 
control the airplane at high speeds on the ground.

(f) Compliance

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

(g) Inspection and Replacement

    At the applicable time specified in paragraph 5, ``Compliance,'' 
of Boeing Alert Service Bulletin B787-81205-SB320022-00, Issue 001, 
dated November 14, 2014, do a landing gear pin part number and 
serial number inspection, in accordance with the Accomplishment 
Instructions of Boeing Alert Service Bulletin B787-81205-SB320022-
00, dated November 14, 2014. A review of airplane maintenance or 
delivery records is acceptable in lieu of this inspection if the 
part number and serial number of the installed landing gear pins can 
be conclusively determined from that review.
    (1) If no part number or serial number is found that matches the 
list of affected pin numbers: No further action is required by this 
paragraph at that pin location.
    (2) If any part number or serial number is found that matches 
the list of affected pin numbers: At the applicable time specified 
in paragraph 5, ``Compliance,'' of Boeing Alert Service Bulletin 
B787-81205-SB320022-00, Issue 001, dated November 14, 2014, replace 
the affected pin with a pin that does not have an affected part 
number and serial number, in accordance with the Accomplishment 
Instructions of Boeing Alert Service Bulletin B787-81205-SB320022-
00, Issue 001, dated November 14, 2014.

(h) Parts Installation Prohibition

    As of the effective date of this AD, no person may install on 
any airplane a landing gear pin having an affected part or serial 
number identified in Boeing Alert Service Bulletin B787-81205-
SB320022-00, Issue 001, dated November 14, 2014.

(i) 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 (j)(1) 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

[[Page 43645]]

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. For 
a repair method to be approved, the repair 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 
(i)(4)(i) and (i)(4)(ii) 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. 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 Melanie 
Violette, Senior Aerospace Engineer, Airframe Branch, ANM-120S, FAA, 
Seattle Aircraft Certification Office (ACO), 1601 Lind Avenue SW., 
Renton, WA 98057-3356; phone: 425-917-6422; fax: 425-917-6590; 
email: melanie.violette@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 July 14, 2015.
Suzanne Masterson,
Acting Manager, Transport Airplane Directorate, Aircraft Certification 
Service.
[FR Doc. 2015-17955 Filed 7-22-15; 8:45 am]
 BILLING CODE 4910-13-P
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