Airworthiness Directives; The Boeing Company Airplanes, 76878-76881 [2015-31218]

Download as PDF 76878 Federal Register / Vol. 80, No. 238 / Friday, December 11, 2015 / Proposed Rules on which the modification described in Airbus Service Bulletin A330–36–3032 has not been incorporated, and for Model A340 series airplanes: Doing the bleed leak detection loop modification of the APU, in accordance with the Accomplishment Instructions of the applicable Airbus service bulletin specified in paragraphs (i)(1) and (i)(2) of this AD, is an acceptable alternative to the actions required by paragraph (h) of this AD, provided the modification is accomplished within 26 months after March 26, 2014 (the effective date of AD 2014–03– 14). (1) Airbus Service Bulletin A330–36–3037, Revision 02, dated April 7, 2014. (2) Airbus Service Bulletin A340–36–4033, Revision 02, dated May 19, 2014. (j) Retained Drain Mast Installation, With No Changes This paragraph restates the requirements of paragraph (j) of AD 2014–03–14, Amendment 39–17752 (79 FR 9382, February 19, 2014), with no changes. For Model A340–500 and –600 series airplanes, except those on which Airbus Modification 54636 or 54637 has been incorporated in production: Within 26 months after March 26, 2014 (the effective date of AD 2014–03–14), install a drain mast between frame (FR) 80 and FR 83, in accordance with the Accomplishment Instructions of Airbus Mandatory Service Bulletin A340–53–5031, Revision 02, dated August 3, 2011. jstallworth on DSK7TPTVN1PROD with PROPOSALS (k) New Requirement of This AD: Replacement of Certain Insulation Sleeves For Model A340 series airplanes in configurations 002, 003, and 005, as described in Airbus Service Bulletin A340– 36–4035, dated September 18, 2012, that have been modified before the effective date of this AD in accordance with the Accomplishment Instructions of Airbus Service Bulletin A340–36–4035, dated September 18, 2012: Within 14 months after the effective date of this AD, replace the insulation sleeves between frames 83 and 84 with new insulation sleeves, in accordance with the Accomplishment Instructions of Airbus Service Bulletin A340–36–4035, Revision 01, dated September 24, 2013. (l) Credit for Previous Actions (1) This paragraph provides credit for actions required by paragraph (g) of this AD, if those actions were performed before March 26, 2014 (the effective date of AD 2014–03– 14, Amendment 39–17752 (79 FR 9382, February 19, 2014)), using Airbus Service Bulletin A330–33–3041, dated January 3, 2012; or Airbus Service Bulletin A340–33– 4026, dated January 3, 2012; as applicable; which are not incorporated by reference in this AD. (2) This paragraph provides credit for actions required by paragraph (h) of this AD, if those actions were performed before March 26, 2014 (the effective date of AD 2014–03– 14, Amendment 39–17752 (79 FR 9382, February 19, 2014)), using Airbus Service Bulletin A330–36–3040, dated September 18, 2012, which is not incorporated by reference in this AD. (3) For Model A340 series airplanes in configurations 001 and 004, as described in VerDate Sep<11>2014 14:54 Dec 10, 2015 Jkt 238001 Airbus Service Bulletin A340–36–4035, dated September 18, 2012: This paragraph provides credit for actions required by paragraph (h) of this AD, if those actions were performed before the effective date of this AD using Airbus Service Bulletin A340– 36–4035, dated September 18, 2012, which is not incorporated by reference in this AD. (4) This paragraph provides credit for actions required by paragraph (j) of this AD, if those actions were performed before March 26, 2014 (the effective date of AD 2014–03– 14, Amendment 39–17752 (79 FR 9382, February 19, 2014)), using Airbus Service Bulletin A340–53–5031, dated July 31, 2006; or Airbus Service Bulletin A340–53–5031, Revision 01, dated January 10, 2008; as applicable; which are not incorporated by reference in this AD. (m) Other FAA AD Provisions The following provisions also apply to this AD: (1) Alternative Methods of Compliance (AMOCs): The Manager, International Branch, ANM–116, Transport Airplane Directorate, 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 International Branch, send it to ATTN: Vladimir Ulyanov, Aerospace Engineer, International Branch, ANM–116, Transport Airplane Directorate, FAA, 1601 Lind Avenue SW., Renton, WA 98057–3356; telephone 425–227–1138; fax 425–227–1149. Information may be emailed to: 9-ANM-116AMOC-REQUESTS@faa.gov. (i) 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. The AMOC approval letter must specifically reference this AD. (ii) AMOCs approved previously for paragraphs (g) and (h) of AD 2014–03–14, Amendment 39–17752 (79 FR 9382, February 19, 2014), are approved as AMOCs for the corresponding provisions of paragraphs (g) and (h) of this AD. (2) Contacting the Manufacturer: As of the effective date of this AD, for any requirement in this AD to obtain corrective actions from a manufacturer, the action must be accomplished using a method approved by the Manager, International Branch, ANM– 116, Transport Airplane Directorate, FAA; or the European Aviation Safety Agency (EASA); or Airbus’s EASA Design Organization Approval (DOA). If approved by the DOA, the approval must include the DOA-authorized signature. (3) Required for Compliance (RC): If any service information contains procedures or tests that are identified as RC, those procedures and tests must be done to comply with this AD; any procedures or tests that are not identified as RC are recommended. Those procedures and tests that are not identified as RC may be deviated from using accepted methods in accordance with the operator’s maintenance or inspection program without PO 00000 Frm 00006 Fmt 4702 Sfmt 4702 obtaining approval of an AMOC, provided the procedures and tests identified as RC can be done and the airplane can be put back in an airworthy condition. Any substitutions or changes to procedures or tests identified as RC require approval of an AMOC. (n) Related Information (1) Refer to Mandatory Continuing Airworthiness Information (MCAI) EASA Airworthiness Directive 2014–0148, dated June 13, 2014, for related information. This MCAI may be found in the AD docket on the Internet at http://www.regulations.gov by searching for and locating Docket No. FAA– 2015–6547. (2) For service information identified in this AD, contact Airbus SAS, Airworthiness Office—EAL, 1 Rond Point Maurice Bellonte, 31707 Blagnac Cedex, France; telephone +33 5 61 93 36 96; fax +33 5 61 93 45 80; email airworthiness.A330–A340@airbus.com; Internet http://www.airbus.com. You may view this service information at the FAA, Transport Airplane Directorate, 1601 Lind Avenue SW., Renton, WA. For information on the availability of this material at the FAA, call 425–227–1221. Issued in Renton, Washington, on December 4, 2015. Michael Kaszycki, Acting Manager, Transport Airplane Directorate, Aircraft Certification Service. [FR Doc. 2015–31210 Filed 12–10–15; 8:45 am] BILLING CODE 4910–13–P DEPARTMENT OF TRANSPORTATION Federal Aviation Administration 14 CFR Part 39 [Docket No. FAA–2015–6548; Directorate Identifier 2015–NM–114–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 and 787–9 airplanes equipped with General Electric engines. This proposed AD was prompted by reports of cracking in barrel nuts on a forward engine mount of Model 747–8 airplanes, which shares a similar design to the forward engine mount of Model 787–8 and 787–9 airplanes. This proposed AD would require, for certain airplanes, replacement of the four barrel nuts of the forward engine mount on each engine. For certain other airplanes, this proposed AD would require an inspection to determine if any forward SUMMARY: E:\FR\FM\11DEP1.SGM 11DEP1 Federal Register / Vol. 80, No. 238 / Friday, December 11, 2015 / Proposed Rules engine mount barrel nut having a certain part number is installed, and related investigative and corrective actions if necessary. We are proposing this AD to detect and correct cracking of the forward engine mount barrel nuts; such cracking could result in reduced load capacity of the forward engine mount and could result in separation of an engine from the airplane, and consequent loss of control of the airplane. We must receive comments on this proposed AD by January 25, 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 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. It is also available on the Internet at http:// www.regulations.gov by searching for and locating Docket No. FAA–2015– 6548. DATES: jstallworth on DSK7TPTVN1PROD with PROPOSALS Examining the AD Docket You may examine the AD docket on the Internet at http:// www.regulations.gov by searching for and locating Docket No. FAA–2015– 6548; 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. VerDate Sep<11>2014 14:54 Dec 10, 2015 Jkt 238001 FOR FURTHER INFORMATION CONTACT: Allen Rauschendorfer, Aerospace Engineer, Airframe Branch, ANM–120S, Seattle Aircraft Certification Office, FAA, 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– 2015–6548; Directorate Identifier 2015– NM–114–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 a report indicating that during the replacement of the No. 2 engine on a Model 747–8 airplane, an operator conducted a non-destructive test (NDT) inspection of the barrel nuts on the forward engine mount and found cracks on two of the four barrel nuts. The same operator also discovered one cracked barrel nut on the No. 1 engine of the same Model 747–8 airplane. Boeing did an NDT inspection on the barrel nuts of the No. 2 engine of a Model 747–8 flight test airplane and discovered two barrel nuts with cracks. Since these initial findings, two additional barrel nuts were found cracked on two additional Model 747– 8 airplanes. The barrel nuts are located at the forward end of the strut box and are used to fasten the forward engine mount to the strut. A barrel nut with a crack on one side is still able to carry ultimate load. A crack on both sides of a barrel nut will cause complete failure of the barrel nut. Complete failure of two or more barrel nuts on the same forward engine mount reduces the load capacity of the forward engine mount and could result in separation of an engine from the airplane, and consequent loss of control of the airplane. Model 787–8 and 787–9 airplanes with General Electric engines have a PO 00000 Frm 00007 Fmt 4702 Sfmt 4702 76879 similar forward engine mount bolt and barrel nut configuration to that on Model 747–8 series airplanes. Therefore, Model 787–8 and 787–9 airplanes are subject to the same unsafe condition revealed on Model 747–8 series airplanes. We issued AD 2013–24–12, Amendment 39–17686 (78 FR 71989, December 2, 2013), to address this unsafe condition on Model 747–8 series airplanes. Relevant Service Information Under 1 CFR Part 51 We reviewed Boeing Service Bulletin B787–81205–SB710026–00, Issue 001, dated June 10, 2015. The service information describes procedures for replacing the forward engine mount barrel nuts with new, improved barrel nuts; doing an inspection to determine if barrel nuts having a certain part number are installed on the forward engine mount; and doing related investigative and corrective actions. This service information is reasonably available because the interested parties have access to it through their normal course of business or by the means identified in the ADDRESSES section of this NPRM. FAA’s Determination We are proposing this AD because we evaluated all the relevant information and determined the unsafe condition described previously is likely to exist or develop in other products of the same type design. Proposed AD Requirements This proposed AD would require accomplishing the actions specified in the service information described previously, except as discussed under ‘‘Differences Between this Proposed AD and the Service Information.’’ For information on the procedures and compliance times, see this service information at http:// www.regulations.gov by searching for Docket No. FAA–2015–6548. 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. E:\FR\FM\11DEP1.SGM 11DEP1 76880 Federal Register / Vol. 80, No. 238 / Friday, December 11, 2015 / Proposed Rules Differences Between This Proposed AD and the Service Information The service 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. Explanation of ‘‘RC’’ Steps in Service Information The FAA worked in conjunction with industry, under the Airworthiness Directive Implementation Aviation Rulemaking Committee (ARC), to enhance the AD system. One enhancement was a new process for annotating which steps in the service information are required for compliance with an AD. Differentiating these steps from other tasks in the service information is expected to improve an owner’s/operator’s understanding of crucial AD requirements and help provide consistent judgment in AD compliance. The steps identified as Required for Compliance (RC) in any service information identified previously have a direct effect on detecting, preventing, resolving, or eliminating an identified unsafe condition. For service information that contains steps that are labeled as RC, the following provisions apply: (1) The steps labeled as RC, including substeps under an RC step and any figures identified in an RC step, must be done to comply with the AD, and an AMOC is required for any deviations to RC steps, including substeps and identified figures; and (2) steps not labeled as RC may be deviated from using accepted methods in accordance with the operator’s maintenance or inspection program without obtaining approval of an AMOC, provided the RC steps, including substeps and identified figures, can still be done as specified, and the airplane can be put back in an airworthy condition. Costs of Compliance We estimate that this proposed AD affects 36 airplanes of U.S. registry. We estimate the following costs to comply with this proposed AD: ESTIMATED COSTS Cost per product Action Labor cost Parts cost Replacement (2 engines). Inspection for part number using maintenance records (2 engines). 29 work-hours × $85 per hour = $2,465 for 2 engines. 1 work-hour × $85 per hour = $85 for 2 engines. $1,988 per engine × 2 engines = $3,976. $0 ..................................................... We estimate the following costs to do any related investigative actions that would be required based on the results of the proposed inspection. We have no Cost on U.S. operators $6,441 85 $64,410 (10 airplanes). $2,210 (26 airplanes). way of determining the number of aircraft that might need these actions: ON-CONDITION COSTS Action Labor cost Parts cost Cost per product Inspection (2 engines) ................................. 9 work-hours × $85 per hour = $765 for 2 engines ...................... $0 $765 We have received no definitive data that would enable us to provide cost estimates for the on-condition corrective actions specified in this proposed AD. According to the manufacturer, some of the costs of this proposed AD may be covered under warranty, thereby reducing the cost impact on affected individuals. We do not control warranty coverage for affected individuals. As a result, we have included all costs in our cost estimate. jstallworth on DSK7TPTVN1PROD with PROPOSALS 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. VerDate Sep<11>2014 14:54 Dec 10, 2015 Jkt 238001 We are issuing this rulemaking under the authority described in Subtitle VII, Part A, Subpart III, Section 44701: ‘‘General requirements.’’ Under that section, Congress charges the FAA with promoting safe flight of civil aircraft in air commerce by prescribing regulations for practices, methods, and procedures the Administrator finds necessary for safety in air commerce. This regulation is within the scope of that authority because it addresses an unsafe condition that is likely to exist or develop on products identified in this rulemaking action. Regulatory Findings We determined that this proposed AD would not have federalism implications under Executive Order 13132. This proposed AD would not have a substantial direct effect on the States, on the relationship between the national PO 00000 Frm 00008 Fmt 4702 Sfmt 4702 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. E:\FR\FM\11DEP1.SGM 11DEP1 Federal Register / Vol. 80, No. 238 / Friday, December 11, 2015 / Proposed Rules The Proposed Amendment Accordingly, under the authority delegated to me by the Administrator, the FAA proposes to amend 14 CFR part 39 as follows: PART 39—AIRWORTHINESS DIRECTIVES 1. The authority citation for part 39 continues to read as follows: ■ Authority: 49 U.S.C. 106(g), 40113, 44701. § 39.13 [Amended] 2. The FAA amends § 39.13 by adding the following new airworthiness directive (AD): ■ No. FAA–2015–6548; Directorate Identifier 2015–NM–114–AD. (a) Comments Due Date We must receive comments by January 25, 2016. (b) Affected ADs None. (c) Applicability This AD applies to The Boeing Company Model 787–8 and 787–9 airplanes, certificated in any category, equipped with General Electric GEnx–1B engines, as identified in Boeing Service Bulletin B787– 81205–SB710026–00, Issue 001, dated June 10, 2015. (d) Subject Air Transport Association (ATA) of America Code 71, Powerplant. (e) Unsafe Condition This AD was prompted by reports of cracking in barrel nuts on a forward engine mount of Model 747–8 airplanes, which shares a similar design to the forward engine mount of Model 787–8 and 787–9 airplanes. We are issuing this AD to detect and correct cracking of the forward engine mount barrel nuts; such cracking could result in reduced load capacity of the forward engine mount, and could result in separation of an engine from the airplane, and consequent loss of control of the airplane. jstallworth on DSK7TPTVN1PROD with PROPOSALS (f) Compliance Comply with this AD within the compliance times specified, unless already done. (g) Replacement Barrel Nuts For Group 1 airplanes as identified in Boeing Service Bulletin B787–81205– SB710026–00, Issue 001, dated June 10, 2015: Except as provided by paragraph (i)(1) of this AD, at the time specified in paragraph 5., ‘‘Compliance,’’ of Boeing Service Bulletin B787–81205–SB710026–00, Issue 001, dated June 10, 2015, replace the existing forward engine mount barrel nuts on each engine, in accordance with the Accomplishment Instructions of Boeing Service Bulletin B787– 81205–SB710026–00, Issue 001, dated June 10, 2015. VerDate Sep<11>2014 14:54 Dec 10, 2015 Jkt 238001 (h) Part Number Inspection for Installed Barrel Nuts For Group 2 airplanes as identified in Boeing Service Bulletin B787–81205– SB710026–00, Issue 001, dated June 10, 2015: Except as provided by paragraph (i)(1) of this AD, at the time specified in paragraph 5. ‘‘Compliance,’’ of Boeing Service Bulletin B787–81205–SB710026–00, Issue 001, dated June 10, 2015, review the aircraft maintenance records to determine if the airplane engine has been removed, installed, or replaced, in accordance with the Accomplishment Instructions of Boeing Service Bulletin B787–81205–SB710026–00, Issue 001, dated June 10, 2015. If the maintenance records indicate that a barrel nut having part number SL4081C14SP1 is installed, or if the part number of an installed barrel nut cannot be determined, before further flight, do the related investigative and applicable corrective actions, in accordance with the Accomplishment Instructions of Boeing Service Bulletin B787–81205– SB710026–00, Issue 001, dated June 10, 2015. (i) Exception to Service information (1) Where Boeing Service Bulletin B787– 81205–SB710026–00, Issue 001, dated June 10, 2015, specifies a compliance time ‘‘after the Issue 001 date on this service bulletin,’’ this AD requires compliance within the specified compliance time after the effective date of this AD. (2) Where Boeing Service Bulletin B787– 81205–SB710026–00, Issue 001, dated June 10, 2015, specifies to contact Boeing for repair instructions: Before further flight, repair 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-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)(2) of this AD: For service information that PO 00000 Frm 00009 Fmt 4702 Sfmt 4702 76881 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, Seattle Aircraft Certification Office, FAA, 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, contact Boeing Commercial Airplanes, Attention: Data & Services Management, P.O. Box 3707, MC 2H–65, Seattle, WA 98124–2207; telephone: 206– 544–5000, extension 1; fax: 206–766–5680; Internet https://www.myboeingfleet.com. You may view this referenced service information at the FAA, Transport Airplane Directorate, 1601 Lind Avenue SW., Renton, WA. For information on the availability of this material at the FAA, call 425–227–1221. Issued in Renton, Washington, on December 4, 2015. Michael Kaszycki, Acting Manager, Transport Airplane Directorate, Aircraft Certification Service. [FR Doc. 2015–31218 Filed 12–10–15; 8:45 am] BILLING CODE 4910–13–P DEPARTMENT OF DEFENSE Office of the Secretary 32 CFR Part 75 RIN 0790–AI82 [Docket ID: DOD–2011–OS–0127] Exceptional Family Member Program (EFMP) Office of the Under Secretary of Defense for Personnel and Readiness, DoD. ACTION: Proposed rule. AGENCY: This proposed rule establishes the Exceptional Family Member Program (EFMP) and provides guidance, assigns responsibilities, and prescribes procedures for identifying a family member with special needs, and coordinating travel at government expense for family members of active duty Service members who meet the SUMMARY: E:\FR\FM\11DEP1.SGM 11DEP1

Agencies

[Federal Register Volume 80, Number 238 (Friday, December 11, 2015)]
[Proposed Rules]
[Pages 76878-76881]
From the Federal Register Online via the Government Publishing Office [www.gpo.gov]
[FR Doc No: 2015-31218]


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DEPARTMENT OF TRANSPORTATION

Federal Aviation Administration

14 CFR Part 39

[Docket No. FAA-2015-6548; Directorate Identifier 2015-NM-114-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 and 787-9 airplanes equipped 
with General Electric engines. This proposed AD was prompted by reports 
of cracking in barrel nuts on a forward engine mount of Model 747-8 
airplanes, which shares a similar design to the forward engine mount of 
Model 787-8 and 787-9 airplanes. This proposed AD would require, for 
certain airplanes, replacement of the four barrel nuts of the forward 
engine mount on each engine. For certain other airplanes, this proposed 
AD would require an inspection to determine if any forward

[[Page 76879]]

engine mount barrel nut having a certain part number is installed, and 
related investigative and corrective actions if necessary. We are 
proposing this AD to detect and correct cracking of the forward engine 
mount barrel nuts; such cracking could result in reduced load capacity 
of the forward engine mount and could result in separation of an engine 
from the airplane, and consequent loss of control of the airplane.

DATES: We must receive comments on this proposed AD by January 25, 
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 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. It is also available on the Internet at http://www.regulations.gov by searching for and locating Docket No. FAA-2015-
6548.

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-2015-
6548; 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, Seattle Aircraft Certification 
Office, FAA, 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-2015-6548; 
Directorate Identifier 2015-NM-114-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 a report indicating that during the replacement of the 
No. 2 engine on a Model 747-8 airplane, an operator conducted a non-
destructive test (NDT) inspection of the barrel nuts on the forward 
engine mount and found cracks on two of the four barrel nuts. The same 
operator also discovered one cracked barrel nut on the No. 1 engine of 
the same Model 747-8 airplane. Boeing did an NDT inspection on the 
barrel nuts of the No. 2 engine of a Model 747-8 flight test airplane 
and discovered two barrel nuts with cracks. Since these initial 
findings, two additional barrel nuts were found cracked on two 
additional Model 747-8 airplanes.
    The barrel nuts are located at the forward end of the strut box and 
are used to fasten the forward engine mount to the strut. A barrel nut 
with a crack on one side is still able to carry ultimate load. A crack 
on both sides of a barrel nut will cause complete failure of the barrel 
nut. Complete failure of two or more barrel nuts on the same forward 
engine mount reduces the load capacity of the forward engine mount and 
could result in separation of an engine from the airplane, and 
consequent loss of control of the airplane.
    Model 787-8 and 787-9 airplanes with General Electric engines have 
a similar forward engine mount bolt and barrel nut configuration to 
that on Model 747-8 series airplanes. Therefore, Model 787-8 and 787-9 
airplanes are subject to the same unsafe condition revealed on Model 
747-8 series airplanes. We issued AD 2013-24-12, Amendment 39-17686 (78 
FR 71989, December 2, 2013), to address this unsafe condition on Model 
747-8 series airplanes.

Relevant Service Information Under 1 CFR Part 51

    We reviewed Boeing Service Bulletin B787-81205-SB710026-00, Issue 
001, dated June 10, 2015. The service information describes procedures 
for replacing the forward engine mount barrel nuts with new, improved 
barrel nuts; doing an inspection to determine if barrel nuts having a 
certain part number are installed on the forward engine mount; and 
doing related investigative and corrective actions. This service 
information is reasonably available because the interested parties have 
access to it through their normal course of business or by the means 
identified in the ADDRESSES section of this NPRM.

FAA's Determination

    We are proposing this AD because we evaluated all the relevant 
information and determined the unsafe condition described previously is 
likely to exist or develop in other products of the same type design.

Proposed AD Requirements

    This proposed AD would require accomplishing the actions specified 
in the service information described previously, except as discussed 
under ``Differences Between this Proposed AD and the Service 
Information.'' For information on the procedures and compliance times, 
see this service information at http://www.regulations.gov by searching 
for Docket No. FAA-2015-6548.
    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.

[[Page 76880]]

Differences Between This Proposed AD and the Service Information

    The service 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.

Explanation of ``RC'' Steps in Service Information

    The FAA worked in conjunction with industry, under the 
Airworthiness Directive Implementation Aviation Rulemaking Committee 
(ARC), to enhance the AD system. One enhancement was a new process for 
annotating which steps in the service information are required for 
compliance with an AD. Differentiating these steps from other tasks in 
the service information is expected to improve an owner's/operator's 
understanding of crucial AD requirements and help provide consistent 
judgment in AD compliance. The steps identified as Required for 
Compliance (RC) in any service information identified previously have a 
direct effect on detecting, preventing, resolving, or eliminating an 
identified unsafe condition.
    For service information that contains steps that are labeled as RC, 
the following provisions apply: (1) The steps labeled as RC, including 
substeps under an RC step and any figures identified in an RC step, 
must be done to comply with the AD, and an AMOC is required for any 
deviations to RC steps, including substeps and identified figures; and 
(2) steps not labeled as RC may be deviated from using accepted methods 
in accordance with the operator's maintenance or inspection program 
without obtaining approval of an AMOC, provided the RC steps, including 
substeps and identified figures, can still be done as specified, and 
the airplane can be put back in an airworthy condition.

Costs of Compliance

    We estimate that this proposed AD affects 36 airplanes of U.S. 
registry.
    We estimate the following costs to comply with this proposed AD:

                                                 Estimated Costs
----------------------------------------------------------------------------------------------------------------
                                                                      Cost per
            Action                Labor cost        Parts cost         product        Cost on  U.S. operators
----------------------------------------------------------------------------------------------------------------
Replacement (2 engines)......  29 work-hours x   $1,988 per                $6,441  $64,410 (10 airplanes).
                                $85 per hour =    engine x 2
                                $2,465 for 2      engines =
                                engines.          $3,976.
Inspection for part number     1 work-hour x     $0..............              85  $2,210 (26 airplanes).
 using maintenance records (2   $85 per hour =
 engines).                      $85 for 2
                                engines.
----------------------------------------------------------------------------------------------------------------

    We estimate the following costs to do any related investigative 
actions 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 actions:

                                               On-Condition Costs
----------------------------------------------------------------------------------------------------------------
                                                                                                     Cost per
                    Action                                Labor cost               Parts cost        product
----------------------------------------------------------------------------------------------------------------
Inspection (2 engines).......................  9 work-hours x $85 per hour =                $0             $765
                                                $765 for 2 engines.
----------------------------------------------------------------------------------------------------------------

    We have received no definitive data that would enable us to provide 
cost estimates for the on-condition corrective actions specified in 
this proposed AD.
    According to the manufacturer, some of the costs of this proposed 
AD may be covered under warranty, thereby reducing the cost impact on 
affected individuals. We do not control warranty coverage for affected 
individuals. As a result, we have included all costs in our cost 
estimate.

Authority for This Rulemaking

    Title 49 of the United States Code specifies the FAA's authority to 
issue rules on aviation safety. Subtitle I, section 106, describes the 
authority of the FAA Administrator. Subtitle VII: Aviation Programs, 
describes in more detail the scope of the Agency's authority.
    We are issuing this rulemaking under the authority described in 
Subtitle VII, Part A, Subpart III, Section 44701: ``General 
requirements.'' Under that section, Congress charges the FAA with 
promoting safe flight of civil aircraft in air commerce by prescribing 
regulations for practices, methods, and procedures the Administrator 
finds necessary for safety in air commerce. This regulation is within 
the scope of that authority because it addresses an unsafe condition 
that is likely to exist or develop on products identified in this 
rulemaking action.

Regulatory Findings

    We determined that this proposed AD would not have federalism 
implications under Executive Order 13132. This proposed AD would not 
have a substantial direct effect on the States, on the relationship 
between the national Government and the States, or on the distribution 
of power and responsibilities among the various levels of government.
    For the reasons discussed above, I certify this proposed 
regulation:
    (1) Is not a ``significant regulatory action'' under Executive 
Order 12866,
    (2) Is not a ``significant rule'' under the DOT Regulatory Policies 
and Procedures (44 FR 11034, February 26, 1979),
    (3) Will not affect intrastate aviation in Alaska, and
    (4) Will not have a significant economic impact, positive or 
negative, on a substantial number of small entities under the criteria 
of the Regulatory Flexibility Act.

List of Subjects in 14 CFR Part 39

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

[[Page 76881]]

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):

No. FAA-2015-6548; Directorate Identifier 2015-NM-114-AD.

(a) Comments Due Date

    We must receive comments by January 25, 2016.

(b) Affected ADs

    None.

(c) Applicability

    This AD applies to The Boeing Company Model 787-8 and 787-9 
airplanes, certificated in any category, equipped with General 
Electric GEnx-1B engines, as identified in Boeing Service Bulletin 
B787-81205-SB710026-00, Issue 001, dated June 10, 2015.

(d) Subject

    Air Transport Association (ATA) of America Code 71, Powerplant.

(e) Unsafe Condition

    This AD was prompted by reports of cracking in barrel nuts on a 
forward engine mount of Model 747-8 airplanes, which shares a 
similar design to the forward engine mount of Model 787-8 and 787-9 
airplanes. We are issuing this AD to detect and correct cracking of 
the forward engine mount barrel nuts; such cracking could result in 
reduced load capacity of the forward engine mount, and could result 
in separation of an engine from the airplane, and consequent loss of 
control of the airplane.

(f) Compliance

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

(g) Replacement Barrel Nuts

    For Group 1 airplanes as identified in Boeing Service Bulletin 
B787-81205-SB710026-00, Issue 001, dated June 10, 2015: Except as 
provided by paragraph (i)(1) of this AD, at the time specified in 
paragraph 5., ``Compliance,'' of Boeing Service Bulletin B787-81205-
SB710026-00, Issue 001, dated June 10, 2015, replace the existing 
forward engine mount barrel nuts on each engine, in accordance with 
the Accomplishment Instructions of Boeing Service Bulletin B787-
81205-SB710026-00, Issue 001, dated June 10, 2015.

(h) Part Number Inspection for Installed Barrel Nuts

    For Group 2 airplanes as identified in Boeing Service Bulletin 
B787-81205-SB710026-00, Issue 001, dated June 10, 2015: Except as 
provided by paragraph (i)(1) of this AD, at the time specified in 
paragraph 5. ``Compliance,'' of Boeing Service Bulletin B787-81205-
SB710026-00, Issue 001, dated June 10, 2015, review the aircraft 
maintenance records to determine if the airplane engine has been 
removed, installed, or replaced, in accordance with the 
Accomplishment Instructions of Boeing Service Bulletin B787-81205-
SB710026-00, Issue 001, dated June 10, 2015. If the maintenance 
records indicate that a barrel nut having part number SL4081C14SP1 
is installed, or if the part number of an installed barrel nut 
cannot be determined, before further flight, do the related 
investigative and applicable corrective actions, in accordance with 
the Accomplishment Instructions of Boeing Service Bulletin B787-
81205-SB710026-00, Issue 001, dated June 10, 2015.

(i) Exception to Service information

    (1) Where Boeing Service Bulletin B787-81205-SB710026-00, Issue 
001, dated June 10, 2015, specifies a compliance time ``after the 
Issue 001 date on this service bulletin,'' this AD requires 
compliance within the specified compliance time after the effective 
date of this AD.
    (2) Where Boeing Service Bulletin B787-81205-SB710026-00, Issue 
001, dated June 10, 2015, specifies to contact Boeing for repair 
instructions: Before further flight, repair 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)(2) 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, 
Seattle Aircraft Certification Office, FAA, 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, contact 
Boeing Commercial Airplanes, Attention: Data & Services Management, 
P.O. Box 3707, MC 2H-65, Seattle, WA 98124-2207; telephone: 206-544-
5000, extension 1; fax: 206-766-5680; Internet https://www.myboeingfleet.com. You may view this referenced service 
information at the FAA, Transport Airplane Directorate, 1601 Lind 
Avenue SW., Renton, WA. For information on the availability of this 
material at the FAA, call 425-227-1221.

    Issued in Renton, Washington, on December 4, 2015.
Michael Kaszycki,
Acting Manager, Transport Airplane Directorate, Aircraft Certification 
Service.
[FR Doc. 2015-31218 Filed 12-10-15; 8:45 am]
 BILLING CODE 4910-13-P