Airworthiness Directives; The Boeing Company Airplanes, 70799-70802 [2014-28124]

Download as PDF tkelley on DSK3SPTVN1PROD with PROPOSALS Federal Register / Vol. 79, No. 229 / Friday, November 28, 2014 / Proposed Rules 6311–6317), which was subsequently redesignated as Part A–1 for editorial reasons, established an energy conservation program for certain industrial equipment, including compressors, the subject of today’s notice. (42 U.S.C. 6311(2)(B)(i)) Unlike some other types of equipment included in EPCA, the term ‘‘compressors’’ is undefined. Section 341 of EPCA, 42 U.S.C. 6312, provides a general statement of purpose to improve the efficiency of a variety of industrial equipment to conserve the energy resources of the Nation and permits the Secretary of Energy to classify certain equipment as covered equipment if a determination is made by rulemaking that doing so is necessary to carry out the purposes of Part A–1 of EPCA. Consistent with this process, DOE is currently considering whether to regulate the efficiency of a specific group of compressors—commercial and industrial compressors. 77 FR 76972 (December 31, 2012). DOE received comments from interested parties, which are available in docket number EERE–2013–BT–STD–0040. The comments were considered in developing a Framework Document to explain the relevant issues, analyses, and processes it anticipates using when considering new energy conservation standards for commercial and industrial compressors. DOE issued that document and conducted a public meeting to discuss its contents earlier this year. 79 FR 6839 (February 5, 2014). For more information, see http:// www1.eere.energy.gov/buildings/ appliance_standards/rulemaking.aspx/ ruleid/58. Because the term ‘‘compressors’’ is undefined by EPCA, DOE considered a variety of definitions for this term to help ensure a reasonable level of clarity with respect to the type of equipment that might be regulated. In its ongoing proceeding, DOE offered for comment the following definition for ‘‘commercial and industrial compressors’’ to clarify the coverage of any potential test procedure or energy conservation standard: Compressor: ‘‘A compressor is an electric-powered device that takes in air or gas at atmospheric pressure and delivers the air or gas at a higher pressure. Compressors typically have a specific ratio, the ratio of delivery pressure to supply pressure, greater than 1.20.’’ After further evaluating this definition and considering the comments it received, DOE revisited this definition and offered a revised version. That version, which is based on International Organization for Standardization (ISO) VerDate Sep<11>2014 16:38 Nov 26, 2014 Jkt 235001 Technical Report (TR) 12942, provides a different definition of the term ‘‘compressor’’ from DOE’s initial approach. (ISO TR 12942 provides a means to classify modern compressor types along with definitions and related terms that can be utilized in technical and contractual specifications such as a manufacturer’s literature and industrial statistics.) DOE offered the following revised definition for public comment: Compressor: a machine or apparatus converting different types of energy into the potential energy of gas pressure for displacement and compression of gaseous media to any higher pressure values above atmospheric pressure with pressure-increase ratios exceeding 1.1.1 DOE is continuing to consider revisions to this definition, however, due at least in part to submitted comments in which some parties commented that the specified ratio should be different to avoid overlapping with what the compressor industry generally treats as ‘‘blowers,’’ equipment for which DOE may also establish standards. See 78 FR 7306 (February 1, 2013) (announcing DOE’s issuance of a framework document related to the potential setting of energy conservation standards for industrial fans and blowers). Also see http:// www1.eere.energy.gov/buildings/ appliance_standards/rulemaking.aspx/ ruleid/25. While DOE’s focus has centered primarily on those compressors that are intended to compress air, compressors are used in a wide variety of applications and may be used to compress different types of gases. DOE is aware that compressors intended to compress other gases such as natural gas (i.e., gas compressors) may, both collectively and individually, use a substantial amount of energy, as such compressors are often very large. An important application of gas compressors is the pipeline transport of natural gas. The drivers for such compressors can be natural gas turbines (particularly since gas is an easily accessible fuel out in the field), steam turbines, internal combustion engines, or electric motors. Recent data provided by the Energy Information Administration (EIA) indicate that the annual amount of natural gas used to transport natural gas through the pipeline system was about 0.7 quadrillion Btu. In addition to the pipeline transport of natural gas, compressors are used in the production 1 International Organization for Standardization (ISO), ISO 12942, Compressors—Classification— Complementary information to ISO 5390, International Organization for Standardization (ISO), 2012. PO 00000 Frm 00003 Fmt 4702 Sfmt 4702 70799 and processing of natural gas, which is accounted for in the 1.4 quadrillion Btus of natural gas reported by EIA as ‘‘lease and plant fuel.’’ 2 As such, DOE is now considering the possibility of setting energy efficiency standards for natural gas compressors, in addition to efficiency standards for commercial and industrial air compressors. To inform its decision making regarding natural gas compressors DOE will hold a public meeting to discuss and receive further comments and supporting data about the characteristics and energy use of this equipment as described in the RFI. (79 FR 45377) Issued in Washington, DC, on November 20, 2014. Kathleen B. Hogan, Deputy Assistant Secretary, Energy Efficiency and Renewable Energy. [FR Doc. 2014–28126 Filed 11–26–14; 8:45 am] BILLING CODE 6450–01–P DEPARTMENT OF TRANSPORTATION Federal Aviation Administration 14 CFR Part 39 [Docket No. FAA–2014–0778; Directorate Identifier 2014–NM–095–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 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 proposed AD was prompted by reports of corrosion found on the mating surfaces between certain skin and stringers at circumferential skin splices. This proposed AD would require general visual inspections of the fuselage skin at certain lower circumferential splices for the presence of existing external doublers, repetitive inspections of the fuselage skin, and related investigative and corrective actions if necessary. We are proposing this AD to detect and correct compromised fillet seals, which can result in corrosion and skin cracking and consequent loss of capability to support limit loads. SUMMARY: 2 Energy Information Administration, Annual Energy Outlook 2014, Table 2. E:\FR\FM\28NOP1.SGM 28NOP1 70800 Federal Register / Vol. 79, No. 229 / Friday, November 28, 2014 / Proposed Rules We must receive comments on this proposed AD by January 12, 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 http://www.regulations.gov. Follow the instructions for submitting comments. • Fax: 202–493–2251. • Mail: U.S. Department of Transportation, Docket Operations, M– 30, West Building Ground Floor, Room W12–140, 1200 New Jersey Avenue SE., Washington, DC 20590. • Hand Delivery: Deliver to Mail address above between 9 a.m. and 5 p.m., Monday through Friday, except Federal holidays. For service information identified in this proposed 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. DATES: Examining the AD Docket tkelley on DSK3SPTVN1PROD with PROPOSALS You may examine the AD docket on the Internet at http:// www.regulations.gov by searching for and locating Docket No. FAA–2014– 0778; 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: Bill Ashforth, Aerospace Engineer, Airframe Branch, ANM–120S, FAA, Seattle Aircraft Certification Office (ACO), 1601 Lind Avenue SW., Renton, WA 98057– 3356; phone: 425–917–6432; fax: 425– 917–6590; email: bill.ashforth@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– 2014–0778; Directorate Identifier 2014– NM–095–AD’’ at the beginning of your VerDate Sep<11>2014 16:38 Nov 26, 2014 Jkt 235001 comments. We specifically invite comments on the overall regulatory, economic, environmental, and energy aspects of this proposed AD. We will consider all comments received by the closing date and may amend this proposed AD because of those comments. We will post all comments we receive, without change, to http:// www.regulations.gov, including any personal information you provide. We will also post a report summarizing each substantive verbal contact we receive about this proposed AD. Discussion We received reports of corrosion found on the mating surfaces between the skin and stringers in Section 42 and Section 46 at circumferential skin splices. A review of the applicable drawings shows that the stringers in these circumferential splice locations were not installed with faying surface sealant. Fillet seals were applied on both the upper and lower sides of the stringer, so if a fillet seal is compromised, moisture can enter the area and result in corrosion in the area between the skin and the stringer. This condition, if not corrected, could result in skin cracking, which could result in a loss of capability to support limit loads. Relevant Service Information We reviewed Boeing Alert Service Bulletin 747–53A2861, dated April 1, 2014. For information on the procedures and compliance times, see this service information at http:// www.regulations.gov by searching for and locating Docket No. FAA–2014– 0778. 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 identified previously, except as discussed under ‘‘Difference Between the Proposed AD and the Service Information.’’ The phrase ‘‘related investigative actions’’ is used in this proposed AD. ‘‘Related investigative actions’’ are follow-on actions that (1) are related to the primary actions, and (2) further investigate the nature of any condition found. Related investigative actions in PO 00000 Frm 00004 Fmt 4702 Sfmt 4702 an AD could include, for example, inspections. The phrase ‘‘corrective actions’’ is used in this proposed AD. ‘‘Corrective actions’’ are actions that correct or address any condition found. Corrective actions in an AD could include, for example, repairs. Explanation of ‘‘RC’’ Steps in Service Information The FAA worked in conjunction with industry, under the Airworthiness Directives Implementation Aviation Rulemaking Committee (AD 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 actions specified in the service information described previously include steps that are labeled as RC (required for compliance) because these steps have a direct effect on detecting, preventing, resolving, or eliminating an identified unsafe condition. As noted in the specified service information, steps labeled as RC must be done to comply with the proposed AD. However, steps that are not labeled as RC are recommended. Those steps that are not labeled as RC may be deviated from, done as part of other actions, or done using accepted methods different from those identified in the service information without obtaining approval of an alternative method of compliance (AMOC), provided the steps labeled as RC can be done and the airplane can be put back in a serviceable condition. Any substitutions or changes to steps labeled as RC will require approval of an AMOC. Difference Between Proposed Rule and Service Bulletin Boeing Alert Service Bulletin 747– 53A2861, dated April 1, 2014, 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. E:\FR\FM\28NOP1.SGM 28NOP1 Federal Register / Vol. 79, No. 229 / Friday, November 28, 2014 / Proposed Rules Costs of Compliance 70801 We estimate the following costs to comply with this proposed AD: We estimate that this proposed AD affects 165 airplanes of U.S. registry. ESTIMATED COSTS Action Labor cost Parts cost Cost per product Inspection ............... Up to 121 work-hours × $85 per hour = $10,370 ............. $0 Up to $10,285 ............ We have received no definitive data that would enable us to provide cost estimates for the on-condition actions specified in this proposed AD. List of Subjects in 14 CFR Part 39 Authority for This Rulemaking The Proposed Amendment 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 proposed 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. Accordingly, under the authority delegated to me by the Administrator, the FAA proposes to amend 14 CFR part 39 as follows: Air transportation, Aircraft, Aviation safety, Incorporation by reference, Safety. tkelley on DSK3SPTVN1PROD with PROPOSALS 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. VerDate Sep<11>2014 16:38 Nov 26, 2014 Jkt 235001 PART 39—AIRWORTHINESS DIRECTIVES 1. The authority citation for part 39 continues to read as follows: ■ Authority: 49 U.S.C. 106(g), 40113, 44701. § 39.13 [Amended] 2. The FAA amends § 39.13 by adding the following new airworthiness directive (AD): ■ The Boeing Company: Docket No. FAA– 2014–0778; Directorate Identifier 2014– NM–095–AD. (a) Comments Due Date We must receive comments by January 12, 2015. (b) Affected ADs None. (c) Applicability This AD applies to The Boeing Company Model 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 747–53A2861, dated April 1, 2014. (d) Subject Air Transport Association (ATA) of America Code 53, Fuselage. (e) Unsafe Condition This AD was prompted by reports of corrosion found on the mating surfaces between certain skin and stringers at circumferential skin splices. We are issuing this AD to detect and correct compromised fillet seals, which can result in corrosion and skin cracking and consequent loss of capability to support limit loads. (f) Compliance Comply with this AD within the compliance times specified, unless already done. PO 00000 Frm 00005 Fmt 4702 Sfmt 4702 Cost on U.S. operators Up to $1,697,025. (g) Inspections and Repair for Group 1 Airplanes For airplanes identified as Group 1 in Boeing Alert Service Bulletin 747–53A2861, dated April 1, 2014: At the applicable times specified in paragraph 1.E., ‘‘Compliance,’’ of Boeing Alert Service Bulletin 747–53A2861, dated April 1, 2014, except as provided by paragraph (i)(1) of this AD, do external general visual inspections for the presence of external doublers on the fuselage skin, and do the applicable actions specified in paragraphs (g)(1) and (g)(2) of this AD, in accordance with the Accomplishment Instructions of Boeing Alert Service Bulletin 747–53A2861, dated April 1, 2014, except as required by paragraph (i)(2) of this AD. (1) Before further flight, do an external lower lobe doubler surface low frequency eddy current (LFEC) inspection for skin cracks or do an external lower lobe skin surface LFEC inspection for corrosion, as applicable, and do all applicable related investigative and corrective actions. Do all applicable related investigative and corrective actions before further flight. (2) Do all applicable repetitive inspections of the fuselage skin thereafter at the applicable times specified in paragraph 1.E., ‘‘Compliance,’’ of Boeing Alert Service Bulletin 747–53A2861, dated April 1, 2014. (h) Inspections and Repair for Group 2 Airplanes For airplanes identified as Group 2 in Boeing Alert Service Bulletin 747–53A2861, dated April 1, 2014: At the applicable times specified in paragraph 1.E., ‘‘Compliance,’’ of Boeing Alert Service Bulletin 747–53A2861, dated April 1, 2014, except as provided by paragraph (i)(1) of this AD, do external general visual inspections for the presence of external doublers on the fuselage skin, and do the applicable actions specified in paragraphs (h)(1) and (h)(2) of this AD, in accordance with the Accomplishment Instructions of Boeing Alert Service Bulletin 747–53A2861, dated April 1, 2014, except as required by paragraph (i)(2) of this AD. (1) For affected areas with any existing repair doubler: Before further flight, do inspections and applicable repairs using a method approved in accordance with the procedures specified by paragraph (j) of this AD. (2) For affected areas with no existing repair doubler, do the applicable actions specified in paragraph (h)(2)(i) and (h)(2)(ii) of this AD. (i) Before further flight, do an external lower lobe skin surface LFEC for corrosion, an external lower lobe doubler surface LFEC inspection for skin cracks, and an external E:\FR\FM\28NOP1.SGM 28NOP1 70802 Federal Register / Vol. 79, No. 229 / Friday, November 28, 2014 / Proposed Rules lower lobe skin detailed inspection for cracks and do all applicable related investigative and corrective actions. Do all applicable related investigative and corrective actions before further flight. (ii) Do all applicable repetitive inspections of the fuselage skin thereafter at the applicable times specified in paragraph 1.E., ‘‘Compliance,’’ of Boeing Alert Service Bulletin 747–53A2861, dated April 1, 2014. (i) Exceptions to Service Information Specifications (1) Where Boeing Alert Service Bulletin 747–53A2861, dated April 1, 2014, 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) Although Boeing Alert Service Bulletin 747–53A2861, dated April 1, 2014, specifies to contact Boeing for repair data, and specifies that action as ‘‘RC’’ (Required for Compliance), this AD requires repair before further flight using a method approved in accordance with the procedures specified in paragraph (j) of this AD. tkelley on DSK3SPTVN1PROD with PROPOSALS (j) Alternative Methods of Compliance (AMOCs) 16:38 Nov 26, 2014 Jkt 235001 Issued in Renton, Washington, on November 19, 2014. Suzanne Masterson, Acting Manager, Transport Airplane Directorate, Aircraft Certification Service. [FR Doc. 2014–28124 Filed 11–26–14; 8:45 am] BILLING CODE 4910–13–P DEPARTMENT OF TRANSPORTATION (1) The Manager, 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) Except as required by paragraph (i) of this AD: If the service information contains steps that are labeled as RC (Required for Compliance), those steps must be done to comply with this AD; any steps that are not labeled as RC are recommended. Those steps that are not labeled as RC may be deviated from, done as part of other actions, or done using accepted methods different from those identified in the specified service information without obtaining approval of an AMOC, provided the steps labeled as RC can be done and the airplane can be put back in a serviceable condition. Any substitutions or changes to steps labeled as RC require approval of an AMOC. (4) An AMOC that provides an acceptable level of safety may be used for any repair 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. VerDate Sep<11>2014 (k) Related Information (1) For more information about this AD, contact Bill Ashforth, Aerospace Engineer, Airframe Branch, ANM–120S, FAA, Seattle Aircraft Certification Office (ACO), 1601 Lind Avenue SW., Renton, WA 98057–3356; phone: 425–917–6432; fax: 425–917–6590; email: bill.ashforth@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. Federal Aviation Administration You may send comments, using the procedures found in 14 CFR 11.43 and 11.45, by any of the following methods: • Federal eRulemaking Portal: Go to http://www.regulations.gov. Follow the instructions for submitting comments. • Fax: 202–493–2251. • Mail: U.S. Department of Transportation, Docket Operations, M– 30, West Building Ground Floor, Room W12–140, 1200 New Jersey Avenue SE., Washington, DC 20590. • Hand Delivery: Deliver to Mail address above between 9 a.m. and 5 p.m., Monday through Friday, except Federal holidays. For service information identified in this proposed 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. ADDRESSES: 14 CFR Part 39 Examining the AD Docket [Docket No. FAA–2014–0777; Directorate Identifier 2014–NM–088–AD] You may examine the AD docket on the Internet at http:// www.regulations.gov by searching for and locating Docket No. FAA–2014– 0777; 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: Douglas Tsuji, Senior Aerospace Engineer, Systems and Equipment Branch, ANM–130S, FAA, Seattle Aircraft Certification Office, 1601 Lind Avenue SW., Renton, WA 98057–3356; telephone: 425–917–6546; fax: 425– 917–6590; email: douglas.tsuji@faa.gov. SUPPLEMENTARY INFORMATION: 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 numerous reports of failures of the proximity sensor within the slat skew detection mechanism assembly (DMA) leading to slats up landing events. This proposed AD would require replacing the slat skew DMAs with new slat skew DMAs, and marking the existing identification plates on the slat with the new part number. We are proposing this AD to prevent failure of the proximity sensor, which could result in the slats being shut down and a slats up high speed landing. This condition, in combination with abnormal landing conditions such as a short runway or adverse weather conditions, could result in a runway excursion. DATES: We must receive comments on this proposed AD by January 12, 2015. SUMMARY: PO 00000 Frm 00006 Fmt 4702 Sfmt 4702 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– 2014–0777; Directorate Identifier 2014– NM–088–AD’’ at the beginning of your comments. We specifically invite E:\FR\FM\28NOP1.SGM 28NOP1

Agencies

[Federal Register Volume 79, Number 229 (Friday, November 28, 2014)]
[Proposed Rules]
[Pages 70799-70802]
From the Federal Register Online via the Government Printing Office [www.gpo.gov]
[FR Doc No: 2014-28124]


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

Federal Aviation Administration

14 CFR Part 39

[Docket No. FAA-2014-0778; Directorate Identifier 2014-NM-095-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 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 proposed AD was prompted by reports of corrosion 
found on the mating surfaces between certain skin and stringers at 
circumferential skin splices. This proposed AD would require general 
visual inspections of the fuselage skin at certain lower 
circumferential splices for the presence of existing external doublers, 
repetitive inspections of the fuselage skin, and related investigative 
and corrective actions if necessary. We are proposing this AD to detect 
and correct compromised fillet seals, which can result in corrosion and 
skin cracking and consequent loss of capability to support limit loads.

[[Page 70800]]


DATES: We must receive comments on this proposed AD by January 12, 
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 http://www.regulations.gov. Follow the instructions for submitting comments.
     Fax: 202-493-2251.
     Mail: U.S. Department of Transportation, Docket 
Operations, M-30, West Building Ground Floor, Room W12-140, 1200 New 
Jersey Avenue SE., Washington, DC 20590.
     Hand Delivery: Deliver to Mail address above between 9 
a.m. and 5 p.m., Monday through Friday, except Federal holidays.
    For service information identified in this proposed 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.

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-2014-
0778; 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: Bill Ashforth, Aerospace Engineer, 
Airframe Branch, ANM-120S, FAA, Seattle Aircraft Certification Office 
(ACO), 1601 Lind Avenue SW., Renton, WA 98057-3356; phone: 425-917-
6432; fax: 425-917-6590; email: bill.ashforth@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-2014-0778; 
Directorate Identifier 2014-NM-095-AD'' at the beginning of your 
comments. We specifically invite comments on the overall regulatory, 
economic, environmental, and energy aspects of this proposed AD. We 
will consider all comments received by the closing date and may amend 
this proposed AD because of those comments.
    We will post all comments we receive, without change, to http://www.regulations.gov, including any personal information you provide. We 
will also post a report summarizing each substantive verbal contact we 
receive about this proposed AD.

Discussion

    We received reports of corrosion found on the mating surfaces 
between the skin and stringers in Section 42 and Section 46 at 
circumferential skin splices. A review of the applicable drawings shows 
that the stringers in these circumferential splice locations were not 
installed with faying surface sealant. Fillet seals were applied on 
both the upper and lower sides of the stringer, so if a fillet seal is 
compromised, moisture can enter the area and result in corrosion in the 
area between the skin and the stringer. This condition, if not 
corrected, could result in skin cracking, which could result in a loss 
of capability to support limit loads.

Relevant Service Information

    We reviewed Boeing Alert Service Bulletin 747-53A2861, dated April 
1, 2014. For information on the procedures and compliance times, see 
this service information at http://www.regulations.gov by searching for 
and locating Docket No. FAA-2014-0778.

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 identified previously, except as discussed 
under ``Difference Between the Proposed AD and the Service 
Information.''
    The phrase ``related investigative actions'' is used in this 
proposed AD. ``Related investigative actions'' are follow-on actions 
that (1) are related to the primary actions, and (2) further 
investigate the nature of any condition found. Related investigative 
actions in an AD could include, for example, inspections.
    The phrase ``corrective actions'' is used in this proposed AD. 
``Corrective actions'' are actions that correct or address any 
condition found. Corrective actions in an AD could include, for 
example, repairs.

Explanation of ``RC'' Steps in Service Information

    The FAA worked in conjunction with industry, under the 
Airworthiness Directives Implementation Aviation Rulemaking Committee 
(AD 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 actions specified in the service 
information described previously include steps that are labeled as RC 
(required for compliance) because these steps have a direct effect on 
detecting, preventing, resolving, or eliminating an identified unsafe 
condition.
    As noted in the specified service information, steps labeled as RC 
must be done to comply with the proposed AD. However, steps that are 
not labeled as RC are recommended. Those steps that are not labeled as 
RC may be deviated from, done as part of other actions, or done using 
accepted methods different from those identified in the service 
information without obtaining approval of an alternative method of 
compliance (AMOC), provided the steps labeled as RC can be done and the 
airplane can be put back in a serviceable condition. Any substitutions 
or changes to steps labeled as RC will require approval of an AMOC.

Difference Between Proposed Rule and Service Bulletin

    Boeing Alert Service Bulletin 747-53A2861, dated April 1, 2014, 
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.

[[Page 70801]]

Costs of Compliance

    We estimate that this proposed AD affects 165 airplanes of U.S. 
registry.
    We estimate the following costs to comply with this proposed AD:

                                                                     Estimated Costs
--------------------------------------------------------------------------------------------------------------------------------------------------------
               Action                               Labor cost                   Parts cost        Cost per product          Cost on U.S.  operators
--------------------------------------------------------------------------------------------------------------------------------------------------------
Inspection..........................  Up to 121 work-hours x $85 per hour =               $0   Up to $10,285..........  Up to $1,697,025.
                                       $10,370.
--------------------------------------------------------------------------------------------------------------------------------------------------------

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

Authority for This Rulemaking

    Title 49 of the United States Code specifies the FAA's authority to 
issue rules on aviation safety. Subtitle I, section 106, describes the 
authority of the FAA Administrator. Subtitle VII: Aviation Programs, 
describes in more detail the scope of the Agency's authority.
    We are issuing this rulemaking under the authority described in 
Subtitle VII, Part A, Subpart III, Section 44701: ``General 
requirements.'' Under that section, Congress charges the FAA with 
promoting safe flight of civil aircraft in air commerce by prescribing 
regulations for practices, methods, and procedures the Administrator 
finds necessary for safety in air commerce. This proposed 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-2014-0778; Directorate Identifier 
2014-NM-095-AD.

(a) Comments Due Date

    We must receive comments by January 12, 2015.

(b) Affected ADs

    None.

(c) Applicability

    This AD applies to The Boeing Company Model 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-
53A2861, dated April 1, 2014.

(d) Subject

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

(e) Unsafe Condition

    This AD was prompted by reports of corrosion found on the mating 
surfaces between certain skin and stringers at circumferential skin 
splices. We are issuing this AD to detect and correct compromised 
fillet seals, which can result in corrosion and skin cracking and 
consequent loss of capability to support limit loads.

(f) Compliance

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

(g) Inspections and Repair for Group 1 Airplanes

    For airplanes identified as Group 1 in Boeing Alert Service 
Bulletin 747-53A2861, dated April 1, 2014: At the applicable times 
specified in paragraph 1.E., ``Compliance,'' of Boeing Alert Service 
Bulletin 747-53A2861, dated April 1, 2014, except as provided by 
paragraph (i)(1) of this AD, do external general visual inspections 
for the presence of external doublers on the fuselage skin, and do 
the applicable actions specified in paragraphs (g)(1) and (g)(2) of 
this AD, in accordance with the Accomplishment Instructions of 
Boeing Alert Service Bulletin 747-53A2861, dated April 1, 2014, 
except as required by paragraph (i)(2) of this AD.
    (1) Before further flight, do an external lower lobe doubler 
surface low frequency eddy current (LFEC) inspection for skin cracks 
or do an external lower lobe skin surface LFEC inspection for 
corrosion, as applicable, and do all applicable related 
investigative and corrective actions. Do all applicable related 
investigative and corrective actions before further flight.
    (2) Do all applicable repetitive inspections of the fuselage 
skin thereafter at the applicable times specified in paragraph 1.E., 
``Compliance,'' of Boeing Alert Service Bulletin 747-53A2861, dated 
April 1, 2014.

(h) Inspections and Repair for Group 2 Airplanes

    For airplanes identified as Group 2 in Boeing Alert Service 
Bulletin 747-53A2861, dated April 1, 2014: At the applicable times 
specified in paragraph 1.E., ``Compliance,'' of Boeing Alert Service 
Bulletin 747-53A2861, dated April 1, 2014, except as provided by 
paragraph (i)(1) of this AD, do external general visual inspections 
for the presence of external doublers on the fuselage skin, and do 
the applicable actions specified in paragraphs (h)(1) and (h)(2) of 
this AD, in accordance with the Accomplishment Instructions of 
Boeing Alert Service Bulletin 747-53A2861, dated April 1, 2014, 
except as required by paragraph (i)(2) of this AD.
    (1) For affected areas with any existing repair doubler: Before 
further flight, do inspections and applicable repairs using a method 
approved in accordance with the procedures specified by paragraph 
(j) of this AD.
    (2) For affected areas with no existing repair doubler, do the 
applicable actions specified in paragraph (h)(2)(i) and (h)(2)(ii) 
of this AD.
    (i) Before further flight, do an external lower lobe skin 
surface LFEC for corrosion, an external lower lobe doubler surface 
LFEC inspection for skin cracks, and an external

[[Page 70802]]

lower lobe skin detailed inspection for cracks and do all applicable 
related investigative and corrective actions. Do all applicable 
related investigative and corrective actions before further flight.
    (ii) Do all applicable repetitive inspections of the fuselage 
skin thereafter at the applicable times specified in paragraph 1.E., 
``Compliance,'' of Boeing Alert Service Bulletin 747-53A2861, dated 
April 1, 2014.

(i) Exceptions to Service Information Specifications

    (1) Where Boeing Alert Service Bulletin 747-53A2861, dated April 
1, 2014, 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) Although Boeing Alert Service Bulletin 747-53A2861, dated 
April 1, 2014, specifies to contact Boeing for repair data, and 
specifies that action as ``RC'' (Required for Compliance), this AD 
requires repair before further flight 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, 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) Except as required by paragraph (i) of this AD: If the 
service information contains steps that are labeled as RC (Required 
for Compliance), those steps must be done to comply with this AD; 
any steps that are not labeled as RC are recommended. Those steps 
that are not labeled as RC may be deviated from, done as part of 
other actions, or done using accepted methods different from those 
identified in the specified service information without obtaining 
approval of an AMOC, provided the steps labeled as RC can be done 
and the airplane can be put back in a serviceable condition. Any 
substitutions or changes to steps labeled as RC require approval of 
an AMOC.
    (4) An AMOC that provides an acceptable level of safety may be 
used for any repair 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.

(k) Related Information

    (1) For more information about this AD, contact Bill Ashforth, 
Aerospace Engineer, Airframe Branch, ANM-120S, FAA, Seattle Aircraft 
Certification Office (ACO), 1601 Lind Avenue SW., Renton, WA 98057-
3356; phone: 425-917-6432; fax: 425-917-6590; email: 
bill.ashforth@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 November 19, 2014.
Suzanne Masterson,
Acting Manager, Transport Airplane Directorate, Aircraft Certification 
Service.
[FR Doc. 2014-28124 Filed 11-26-14; 8:45 am]
BILLING CODE 4910-13-P