Airworthiness Directives; The Boeing Company Airplanes, 29206-29209 [2016-10915]

Download as PDF 29206 Federal Register / Vol. 81, No. 91 / Wednesday, May 11, 2016 / Proposed Rules 1065, Revision 3, dated June 30, 2015: Do an external low frequency eddy current (LFEC) inspection for cracking of the skin at the critical fastener row of the repair doubler; and do all applicable corrective actions; in accordance the Accomplishment Instructions of Boeing Special Attention Service Bulletin 737–53–1065, Revision 3, dated June 30, 2015, except as required by paragraph (i)(3) of this AD. Do all applicable corrective actions before further flight. Repeat the LFEC inspection thereafter at the applicable intervals specified in Boeing Special Attention Service Bulletin 737–53–1065, Revision 3, dated June 30, 2015. (m) Skin Panel Replacement Except for Group 1 airplanes identified in Boeing Special Attention Service Bulletin 737–53–1065, Revision 3, dated June 30, 2015: At the later of the times specified in paragraphs (m)(1) and (m)(2) of this AD: Replace the applicable skin panels, and do all applicable related investigative and corrective actions, in accordance with the Accomplishment Instructions of Boeing Special Attention Service Bulletin 737–53– 1065, Revision 3, dated June 30, 2015. Do all applicable related investigative and corrective actions before further flight. Doing the skin panel replacement required by this paragraph terminates the inspection requirements of paragraph (h) of this AD for that skin panel only, provided the skin panel was replaced with a production skin panel after 59,000 total flight cycles. (1) Before 60,000 total flight cycles, but not at or before 59,000 total flight cycles. (2) Within 6,000 flight cycles after the effective date of this AD, but not at or before 59,000 total flight cycles. mstockstill on DSK3G9T082PROD with PROPOSALS (n) Credit for Previous Actions This paragraph provides credit for the actions required by paragraph (h) of this AD, if those actions were performed before the effective date of this AD using Boeing Special Attention Service Bulletin 737–53–1065, Revision 2, dated April 19, 2001, which was incorporated by reference in AD 2005–13–30. (o) 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 (p)(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 VerDate Sep<11>2014 16:58 May 10, 2016 Jkt 238001 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) AMOCs approved previously for AD 2005–13–30, are approved as AMOCs for the corresponding provisions of paragraph (h) of this AD. (p) Related Information (1) For more information about this AD, contact Wade Sullivan, Aerospace Engineer, Airframe Branch, ANM–120S, FAA, Seattle ACO, 1601 Lind Avenue SW., Renton, WA 98057–3356; phone: 425–917–6430; fax: 425– 917–6590; email: wade.sullivan@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, 1601 Lind Avenue SW., Renton, Washington. For information on the availability of this material at the FAA, call 425–227–1221. Issued in Renton, Washington, on May 4, 2016. Michael Kaszycki, Acting Manager, Transport Airplane Directorate, Aircraft Certification Service. [FR Doc. 2016–11095 Filed 5–10–16; 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] 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 787–8 airplanes. This proposed AD was prompted by reports indicating that certain wing side-of-body stringer fittings have been installed with faying surface mismatch beyond the allowed machining tolerance. This proposed AD would 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 SUMMARY: PO 00000 Frm 00038 Fmt 4702 Sfmt 4702 fittings and upper side-of-body rib chord with tapered sleeve bolts. We are proposing 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 to a point where it cannot sustain limit load, which could adversely affect the structural integrity of the airplane. DATES: We must receive comments on this proposed AD by June 27, 2016. ADDRESSES: You may send comments, using the procedures found in 14 CFR 11.43 and 11.45, by any of the following methods: • Federal eRulemaking Portal: Go to https://www.regulations.gov. Follow the instructions for submitting comments. • Fax: 202–493–2251. • Mail: U.S. Department of Transportation, Docket Operations, M– 30, West Building Ground Floor, Room W12–140, 1200 New Jersey Avenue SE., Washington, DC 20590. • Hand Delivery: Deliver to Mail address above between 9 a.m. and 5 p.m., Monday through Friday, except Federal holidays. For service information identified in this NPRM, contact Boeing Commercial Airplanes, Attention: 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 https:// www.regulations.gov by searching for and locating Docket No. FAA–2016– 6428. 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–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 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: Allen Rauschendorfer, Aerospace Engineer, Airframe Branch, ANM–120S, E:\FR\FM\11MYP1.SGM 11MYP1 Federal Register / Vol. 81, No. 91 / Wednesday, May 11, 2016 / Proposed Rules 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: 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– 2016–6428; Directorate Identifier 2015– NM–119–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 reports indicating that certain wing side-of-body stringer fittings have been installed with faying surface mismatch beyond the allowed machining tolerance. The fittings are assembled to the mating side-of-body rib chord. The faying surface mismatch 29207 produces a gouge in the mating surface which reduces the fatigue life, and could grow into a widespread fatigue condition on the upper side-of-body rib chord. We are proposing 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 to a point where it cannot sustain limit load, which could adversely affect the structural integrity of the airplane. and determined the unsafe condition described previously is likely to exist or develop in other products of the same type design. Related Service Information Under 1 CFR Part 51 We reviewed Boeing Alert Service Bulletin B787–81205–SB570018–00, Issue 001, dated July 1, 2015. The service information describes procedures for inspection of the left and right hand side stringer 1 fittings for faying surface mismatch common to the side-of-body rib chord. If faying surface mismatch is found, instructions are also given to replace the stringer 1 fitting, and removal and replacement of the clearance fit fasteners common to the side-of-body fittings and upper side-ofbody rib chord with tapered sleeve bolts from stringer 5 to stringer 11. 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. Differences Between This Proposed AD and the Service Information FAA’s Determination We are proposing this AD because we evaluated all the relevant information Proposed AD Requirements This proposed AD would require accomplishing the actions specified in the service information described previously, except as described in ‘‘Differences Between this Proposed AD and the Service Information.’’ Boeing Alert Service Bulletin B787– 81205–SB570018–00, Issue 001, dated July 1, 2015, specifies to contact the manufacturer for instructions on how to repair certain conditions, but this proposed AD would require repairing those conditions in one of the following ways: • In accordance with a method that we approve; or • 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 5 airplanes of U.S. registry. We estimate the following costs to comply with this proposed AD: ESTIMATED COSTS Labor cost Parts cost Cost per product Cost on U.S. operators 144 work-hours × $85 per hour = $12,240 ................................................ $100,079 $112,319 $561,595 Action Modification and inspection. We estimate the following costs to do any necessary corrective action for fretting damage or cutter mismatch 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 corrective actions: ON-CONDITION COSTS Labor cost Parts cost Cost per product Repair for fretting damage or cutter mismatch. mstockstill on DSK3G9T082PROD with PROPOSALS Action 9 work-hours × $85 per hour = $765 ............................................... $0 $765 We have received no definitive data that would enable us to provide cost estimates for the crack repair specified in this proposed AD. Authority for This Rulemaking Title 49 of the United States Code specifies the FAA’s authority to issue VerDate Sep<11>2014 16:58 May 10, 2016 Jkt 238001 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. PO 00000 Frm 00039 Fmt 4702 Sfmt 4702 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 E:\FR\FM\11MYP1.SGM 11MYP1 29208 Federal Register / Vol. 81, No. 91 / Wednesday, May 11, 2016 / Proposed Rules 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: 1. The authority citation for part 39 continues to read as follows: ■ Authority: 49 U.S.C. 106(g), 40113, 44701. [Amended] 2. The FAA amends § 39.13 by adding the following new airworthiness directive (AD): mstockstill on DSK3G9T082PROD with PROPOSALS ■ The Boeing Company: Docket No. FAA– 2016–6428; Directorate Identifier 2015– NM–119–AD. (a) Comments Due Date We must receive comments by June 27, 2016. (b) Affected ADs None. VerDate Sep<11>2014 16:58 May 10, 2016 Jkt 238001 This AD applies to The Boeing Company Model 787–8 airplanes, certificated in any category, as identified in Boeing Alert Service Bulletin B787–81205–SB570018–00, Issue 001, dated July 1, 2015. (d) Subject Air Transport Association (ATA) of America Code 57, Wings. (e) Unsafe Condition This AD was prompted by reports indicating that certain wing side-of-body stringer fittings have been installed with faying surface mismatch beyond the allowed machining tolerance. We are 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 to a point where it cannot sustain limit load, which could adversely affect the structural integrity of the airplane. (f) Compliance Comply with this AD within the compliance times specified, unless already done. (g) Inspection Before the accumulation of 18,000 total flight cycles, or within 13 years after the effective date of this AD, whichever occurs first, do the inspections specified in paragraphs (g)(1), (g)(2), and (g)(3) of this AD, and all applicable corrective actions, in accordance with the Accomplishment Instructions of Boeing Alert Service Bulletin B787–81205–SB570018–00, Issue 001, dated July 1, 2015, except as required by paragraph (i) of this AD. Do all applicable corrective actions before further flight. (1) Do a detailed inspection for fretting damage of the faying surface of the aluminum T-chord. (2) Do an eddy current inspection for cracking of the fastener holes. (3) Do a detailed inspection for a machine mismatch condition of the stringer 1 fitting faying surface. (h) Modifications PART 39—AIRWORTHINESS DIRECTIVES § 39.13 (c) Applicability Concurrently with accomplishment of the requirements of paragraph (g) of this AD: Modify the stringer fitting fasteners, and do an eddy current inspection for cracking of the fastener holes, in accordance with the Accomplishment Instructions of Boeing Alert Service Bulletin B787–81205–SB570018–00, Issue 001, dated July 1, 2015. If any crack is found, before further flight, repair using a method approved in accordance with the procedures specified in paragraph (j) of this AD. (i) Exception to Service Information Specifications Where Boeing Alert Service Bulletin B787– 81205–SB570018–00, Issue 001, dated July 1, 2015, specifies to contact Boeing for repair of cracking: Before further flight, repair the cracking using a method approved in accordance with the procedures specified in paragraph (j) of this AD. PO 00000 Frm 00040 Fmt 4702 Sfmt 4702 (j) 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 (k)(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) Except as required by paragraph (i) of this AD: For service information that contains steps that are labeled as Required for Compliance (RC), the provisions of paragraphs (j)(4)(i) and (j)(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. (k) Related Information (1) For more information about this AD, 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. (2) For service information identified in this AD, 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. E:\FR\FM\11MYP1.SGM 11MYP1 Federal Register / Vol. 81, No. 91 / Wednesday, May 11, 2016 / Proposed Rules Issued in Renton, Washington, on May 3, 2016. Michael Kaszycki, Acting Manager, Transport Airplane Directorate, Aircraft Certification Service. [FR Doc. 2016–10915 Filed 5–10–16; 8:45 am] BILLING CODE 4910–13–P DEPARTMENT OF TRANSPORTATION Federal Aviation Administration 14 CFR Part 39 [Docket No. FAA–2016–6431; Directorate Identifier 2015–NM–182–AD] RIN 2120–AA64 Airworthiness Directives; Airbus Airplanes Federal Aviation Administration (FAA), DOT. ACTION: Notice of proposed rulemaking (NPRM). AGENCY: We propose to adopt a new airworthiness directive (AD) for certain Airbus Model A318–112 airplanes, A319–111, –112, –115, –132, and –133 airplanes, A320–214, –232, and –233 airplanes, and A321–211, –212, –213, –231, and –232 airplanes. This proposed AD was prompted by a quality control review on the final assembly line, which determined that aluminum alloy with inadequate heat treatment had been delivered and used on several structural parts. This proposed AD would require a one-time eddy current conductivity measurement of certain cabin, cargo compartment, and frame structural parts to determine if aluminum alloy with inadequate heat treatment was used, and replacement if necessary. We are proposing this AD to detect and replace structural parts made of aluminum alloy with inadequate heat treatment. This condition could result in reduced structural integrity of the airplane. DATES: We must receive comments on this proposed AD by June 27, 2016. 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. mstockstill on DSK3G9T082PROD with PROPOSALS SUMMARY: VerDate Sep<11>2014 16:58 May 10, 2016 Jkt 238001 For service information identified in this NPRM, contact Airbus, Airworthiness Office—EIAS, 1 Rond Point Maurice Bellonte, 31707 Blagnac Cedex, France; telephone: +33 5 61 93 36 96; fax: +33 5 61 93 44 51; email: account.airworth-eas@airbus.com; Internet: https://www.airbus.com. You may view this referenced service information at the FAA, Transport Airplane Directorate, 1601 Lind Avenue SW., Renton, WA. For information on the availability of this material at the FAA, call 425–227–1221. 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–2016– 6431; or in person at the Docket Management Facility between 9 a.m. and 5 p.m., Monday through Friday, except Federal holidays. The AD docket contains this proposed AD, the regulatory evaluation, any comments received, and other information. The street address for the Docket Operations office (telephone: 800–647–5527) is in the ADDRESSES section. Comments will be available in the AD docket shortly after receipt. FOR FURTHER INFORMATION CONTACT: Sanjay Ralhan, Aerospace Engineer, International Branch, ANM–116, Transport Airplane Directorate, FAA, 1601 Lind Avenue SW., Renton, WA 98057–3356; telephone: 425–227–1405; fax: 425–227–1149. SUPPLEMENTARY INFORMATION: Comments Invited We invite you to send any written relevant data, views, or arguments about this proposed AD. Send your comments to an address listed under the ADDRESSES section. Include ‘‘Docket No. FAA–2016–6431; Directorate Identifier 2015–NM–182–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 based on 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 The European Aviation Safety Agency (EASA), which is the Technical Agent for the Member States of the European Union, has issued EASA Airworthiness PO 00000 Frm 00041 Fmt 4702 Sfmt 4702 29209 Directive 2015–0219, dated November 3, 2015 (referred to after this as the Mandatory Continuing Airworthiness Information, or ‘‘the MCAI’’), to correct an unsafe condition for certain Airbus Model A318–112 airplanes, A319–111, –112, –115, –132, and –133 airplanes, A320–214, –232, and –233 airplanes, and A321–211, –212, –213, –231, and –232 airplanes. The MCAI states: Following an Airbus quality control review on the final assembly line, it was discovered that aluminum alloy with inadequate heat treatment were delivered by a supplier for several structural parts. The results of the investigations highlighted that 1% of the stock could be impacted by this wrong material. Structural investigations demonstrated the capability to sustain the static limits loads, and sufficient fatigue life up to a certain inspection threshold. This condition, if not detected and corrected, could reduce the aeroplane structural integrity following fatigue load. To address this potential unsafe condition, Airbus issued Service Bulletin (SB) A320– 53–1292, SB A320–53–1293, and SB A320– 53–1294 to provide inspection instructions. For the reasons described above, this [EASA] AD requires a one-time Special Detailed Inspection (SDI) [i.e., eddy current conductivity measurement] of certain cabin, cargo compartment and frame parts [for material identification] and, depending on findings, replacement with serviceable parts. You may examine the MCAI in the AD docket on the Internet at https:// www.regulations.gov by searching for and locating Docket No. FAA–2016– 6431. Related Service Information Under 1 CFR Part 51 Airbus has issued the following service information: • Airbus Service Bulletin A320–53– 1292, dated July 23, 2015; including Appendices 01 and 02, dated July 23, 2015. • Airbus Service Bulletin A320–53– 1293, dated July 30, 2015; including Appendices 01 and 02, dated July 30, 2015. • Airbus Service Bulletin A320–53– 1294, dated July 23, 2015; including Appendices 01 and 02, dated July 23, 2015. The service information describes procedures for a one-time eddy current conductivity measurement of certain cabin, cargo compartment, and frame structural parts to determine if aluminum alloy with inadequate heat treatment was used, and replacement of any affected part with a serviceable part. 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. E:\FR\FM\11MYP1.SGM 11MYP1

Agencies

[Federal Register Volume 81, Number 91 (Wednesday, May 11, 2016)]
[Proposed Rules]
[Pages 29206-29209]
From the Federal Register Online via the Government Publishing Office [www.gpo.gov]
[FR Doc No: 2016-10915]


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

DEPARTMENT OF TRANSPORTATION

Federal Aviation Administration

14 CFR Part 39

[Docket No. FAA-2016-6428; Directorate Identifier 2015-NM-119-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 787-8 airplanes. This proposed AD was 
prompted by reports indicating that certain wing side-of-body stringer 
fittings have been installed with faying surface mismatch beyond the 
allowed machining tolerance. This proposed AD would 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 
proposing 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 to a point where it cannot sustain 
limit load, which could adversely affect the structural integrity of 
the airplane.

DATES: We must receive comments on this proposed AD by June 27, 2016.

ADDRESSES: You may send comments, using the procedures found in 14 CFR 
11.43 and 11.45, by any of the following methods:
     Federal eRulemaking Portal: Go to https://www.regulations.gov. Follow the instructions for submitting comments.
     Fax: 202-493-2251.
     Mail: U.S. Department of Transportation, Docket 
Operations, M-30, West Building Ground Floor, Room W12-140, 1200 New 
Jersey Avenue SE., Washington, DC 20590.
     Hand Delivery: Deliver to Mail address above between 9 
a.m. and 5 p.m., Monday through Friday, except Federal holidays.
    For service information identified in this NPRM, contact Boeing 
Commercial Airplanes, Attention: 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 https://www.regulations.gov by 
searching for and locating Docket No. FAA-2016-6428.

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-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 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: Allen Rauschendorfer, Aerospace 
Engineer, Airframe Branch, ANM-120S,

[[Page 29207]]

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:

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-2016-6428; 
Directorate Identifier 2015-NM-119-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 reports indicating that certain wing side-of-body 
stringer fittings have been installed with faying surface mismatch 
beyond the allowed machining tolerance. The fittings are assembled to 
the mating side-of-body rib chord. The faying surface mismatch produces 
a gouge in the mating surface which reduces the fatigue life, and could 
grow into a widespread fatigue condition on the upper side-of-body rib 
chord. We are proposing 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 to a point where it 
cannot sustain limit load, which could adversely affect the structural 
integrity of the airplane.

Related Service Information Under 1 CFR Part 51

    We reviewed Boeing Alert Service Bulletin B787-81205-SB570018-00, 
Issue 001, dated July 1, 2015. The service information describes 
procedures for inspection of the left and right hand side stringer 1 
fittings for faying surface mismatch common to the side-of-body rib 
chord. If faying surface mismatch is found, instructions are also given 
to replace the stringer 1 fitting, and removal 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 from stringer 5 to 
stringer 11. 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 described in 
``Differences Between this Proposed AD and the Service Information.''

Differences Between This Proposed AD and the Service Information

    Boeing Alert Service Bulletin B787-81205-SB570018-00, Issue 001, 
dated July 1, 2015, specifies to contact the manufacturer for 
instructions on how to repair certain conditions, but this proposed AD 
would require repairing those conditions in one of the following ways:
     In accordance with a method that we approve; or
     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 5 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
-----------------------------------------------------------------------------------------------------------------------------------------
Modification and inspection...................  144 work-hours x $85 per hour =               $100,079         $112,319         $561,595
                                                 $12,240.
--------------------------------------------------------------------------------------------------------------------------------------------------------

    We estimate the following costs to do any necessary corrective 
action for fretting damage or cutter mismatch 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 corrective 
actions:

                                               On-condition Costs
----------------------------------------------------------------------------------------------------------------
                                                                                                     Cost per
                 Action                                Labor cost                  Parts cost        product
----------------------------------------------------------------------------------------------------------------
Repair for fretting damage or cutter      9 work-hours x $85 per hour = $765..              $0             $765
 mismatch.
----------------------------------------------------------------------------------------------------------------

    We have received no definitive data that would enable us to provide 
cost estimates for the crack repair 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

[[Page 29208]]

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-2016-6428; Directorate Identifier 
2015-NM-119-AD.

(a) Comments Due Date

    We must receive comments by June 27, 2016.

(b) Affected ADs

    None.

(c) Applicability

    This AD applies to The Boeing Company Model 787-8 airplanes, 
certificated in any category, as identified in Boeing Alert Service 
Bulletin B787-81205-SB570018-00, Issue 001, dated July 1, 2015.

(d) Subject

    Air Transport Association (ATA) of America Code 57, Wings.

(e) Unsafe Condition

    This AD was prompted by reports indicating that certain wing 
side-of-body stringer fittings have been installed with faying 
surface mismatch beyond the allowed machining tolerance. We are 
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 to a point where it cannot 
sustain limit load, which could adversely affect the structural 
integrity of the airplane.

(f) Compliance

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

(g) Inspection

    Before the accumulation of 18,000 total flight cycles, or within 
13 years after the effective date of this AD, whichever occurs 
first, do the inspections specified in paragraphs (g)(1), (g)(2), 
and (g)(3) of this AD, and all applicable corrective actions, in 
accordance with the Accomplishment Instructions of Boeing Alert 
Service Bulletin B787-81205-SB570018-00, Issue 001, dated July 1, 
2015, except as required by paragraph (i) of this AD. Do all 
applicable corrective actions before further flight.
    (1) Do a detailed inspection for fretting damage of the faying 
surface of the aluminum T-chord.
    (2) Do an eddy current inspection for cracking of the fastener 
holes.
    (3) Do a detailed inspection for a machine mismatch condition of 
the stringer 1 fitting faying surface.

(h) Modifications

    Concurrently with accomplishment of the requirements of 
paragraph (g) of this AD: Modify the stringer fitting fasteners, and 
do an eddy current inspection for cracking of the fastener holes, in 
accordance with the Accomplishment Instructions of Boeing Alert 
Service Bulletin B787-81205-SB570018-00, Issue 001, dated July 1, 
2015. If any crack is found, before further flight, repair using a 
method approved in accordance with the procedures specified in 
paragraph (j) of this AD.

(i) Exception to Service Information Specifications

    Where Boeing Alert Service Bulletin B787-81205-SB570018-00, 
Issue 001, dated July 1, 2015, specifies to contact Boeing for 
repair of cracking: Before further flight, repair the cracking using 
a method approved in accordance with the procedures specified in 
paragraph (j) of this AD.

(j) 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 (k)(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, 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 (i) of this AD: For service 
information that contains steps that are labeled as Required for 
Compliance (RC), the provisions of paragraphs (j)(4)(i) and 
(j)(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.

(k) Related Information

    (1) For more information about this AD, 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.
    (2) For service information identified in this AD, 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.


[[Page 29209]]


    Issued in Renton, Washington, on May 3, 2016.
Michael Kaszycki,
Acting Manager, Transport Airplane Directorate, Aircraft Certification 
Service.
[FR Doc. 2016-10915 Filed 5-10-16; 8:45 am]
 BILLING CODE 4910-13-P
This site is protected by reCAPTCHA and the Google Privacy Policy and Terms of Service apply.