Airworthiness Directives; The Boeing Company Airplanes, 34103-34106 [2015-14231]

Download as PDF Federal Register / Vol. 80, No. 114 / Monday, June 15, 2015 / Proposed Rules conclusively determined from that review. For any engine replaced as specified in the Airbus A318/A319/A320/A321 Aircraft Maintenance Manual (AMM), Task 71–00– 00–400–040–A01, ‘‘Installation of the Power Plant with Engine Positioner TWW 75E,’’ dated May 2013: Within 6 months or 1,500 flight cycles, whichever occurs first after the effective date of this AD, re-torque the 4 aft mount pylon bolts using a method approved by the Manager, International Branch, ANM– 116, Transport Airplane Directorate, FAA; or the European Aviation Safety Agency (EASA); or Airbus’ EASA Design Organization Approval (DOA). Note 1 to paragraph (g) of this AD: Additional guidance for the re-torque can be found in Airbus A318/A319/A320/A321 AMM Temporary Revision 71–030, dated March 14, 2014, or Airbus A318/A319/A320/ A321 AMM Task 71–00–00–400–040–A01, ‘‘Installation of the Power Plant with Engine Positioner TWW 75E,’’ dated May 2014. asabaliauskas on DSK5VPTVN1PROD with PROPOSALS (h) Parts Installation Limitation As of the effective date of this AD, no person may install a CFM56–5 engine, on any airplane, unless the engine is installed in accordance with the Accomplishment Instructions of Airbus Service Bulletin A320– 71–1063, including Appendix 01, dated August 13, 2014. (i) 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: Sanjay Ralhan, Aerospace Engineer, International Branch, ANM–116, Transport Airplane Directorate, FAA, 1601 Lind Avenue SW., Renton, WA 98057–3356; telephone: 425–227–1405; fax: 425–227– 1149. Information may be emailed to: 9ANM-116-AMOC-REQUESTS@faa.gov. 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. (2) Contacting the Manufacturer: 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 EASA; or Airbus’s EASA DOA. If approved by the DOA, the approval must include the DOA-authorized signature. (j) Related Information (1) Refer to Mandatory Continuing Airworthiness Information (MCAI) EASA Airworthiness Directive 2014–0258, dated November 28, 2014, for related information. This MCAI may be found in the AD docket VerDate Sep<11>2014 16:22 Jun 12, 2015 Jkt 235001 on the Internet at http://www.regulations.gov by searching for and locating Docket No. FAA–2015–1429. (2) For service information identified in this AD, contact Airbus SAS, Airworthiness Office—EAW, 1 Rond Point Maurice Bellonte, 31707 Blagnac Cedex, France; telephone: +33 5 61 93 36 96; fax: +33 5 61 93 44 51; email account.airworth-eas@ airbus.com; Internet 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 June 3, 2015. Michael Kaszycki, Acting Manager, Transport Airplane Directorate, Aircraft Certification Service. [FR Doc. 2015–14228 Filed 6–12–15; 8:45 am] BILLING CODE 4910–13–P DEPARTMENT OF TRANSPORTATION Federal Aviation Administration 14 CFR Part 39 [Docket No. FAA–2015–1428; Directorate Identifier 2015–NM–026–AD] RIN 2120–AA64 34103 • 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; phone: 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– 1428. Examining the AD Docket 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 777–200 and –300 series airplanes. This proposed AD was prompted by reports of fatigue cracking of a certain chord of the pivot bulkhead. This proposed AD would require repetitive inspections for cracking of the left side and right side forward outer chords of the pivot bulkhead, and related investigative and corrective actions if necessary. This proposed AD provides a modification of the pivot bulkhead, which would terminate the repetitive inspections. We are proposing this AD to detect and correct fatigue cracking of the outer flanges of the left and right side forward outer chords of the pivot bulkhead, which could result in a severed forward outer chord and consequent loss of horizontal stabilizer control. DATES: We must receive comments on this proposed AD by July 30, 2015. ADDRESSES: You may send comments, using the procedures found in 14 CFR 11.43 and 11.45, by any of the following methods: SUMMARY: PO 00000 Frm 00024 Fmt 4702 Sfmt 4702 You may examine the AD docket on the Internet at http:// www.regulations.gov by searching for and locating Docket No. FAA–2015– 1428; 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: Narinder Luthra, Aerospace Engineer, Airframe Branch, ANM–120S, FAA, Seattle Aircraft Certification Office (ACO), 1601 Lind Avenue SW., Renton, WA 98057–3356; phone: 425–917–6513; fax: 425–917–6590; email: narinder.luthra@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– 2015–1428; Directorate Identifier 2015– NM–026–AD’’ at the beginning of your comments. We specifically invite E:\FR\FM\15JNP1.SGM 15JNP1 34104 Federal Register / Vol. 80, No. 114 / Monday, June 15, 2015 / Proposed Rules 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 fatigue cracking of the forward outer chord of the STA 2370 pivot bulkhead. Cracks in the forward outer chords of the STA 2370 pivot bulkhead that are not found and repaired can become large and result in a severed forward outer chord. The cracks were caused by a stress concentration, which is generated at the transition radius of the forward outer flange of the chord prior to the chord splice at the upper longeron. Since the horizontal stabilizer is attached to the STA 2370 bulkhead at two pivot locations, fatigue cracking of the outer flanges of the left and right side forward outer chords of the STA 2370 pivot bulkhead, if not corrected, could result in a severed forward outer chord and consequent loss of horizontal stabilizer control. Related Service Information Under 1 CFR Part 51 We reviewed the following Boeing service information. • Boeing Alert Service Bulletin 777– 53A0075, dated January 14, 2015, describes procedures for repetitive detailed and high frequency eddy current (HFEC) inspections for cracking of the outer flanges of the left and right side forward outer chords of the STA 2370 pivot bulkhead, repetitive postrepair inspections for certain airplanes, and related investigative and corrective actions. • Boeing Service Bulletin 777–53– 0076, dated January 14, 2015, describes procedures for a modification of the STA 2370 pivot bulkhead by replacing the left and right side forward outer chords and upper splice angles, and 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 these same type designs. Proposed AD Requirements This proposed AD would require accomplishing the actions specified in the service information described previously, except as discussed under ‘‘Differences Between this Proposed AD and the Service Information.’’ Refer to this service information for details on the procedures and compliance times. 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 Directive Implementation Aviation Rulemaking Committee (ARC), to enhance the AD system. One enhancement was a new process for annotating which steps in the service information are required for compliance with an AD. Differentiating these steps from other tasks in the service information is expected to improve an owner’s/operator’s understanding of crucial AD requirements and help provide consistent judgment in AD compliance. The steps identified as RC (required for compliance) in any service information identified previously have a direct effect on detecting, preventing, resolving, or eliminating an identified unsafe condition. For service information that contains steps that are labeled as Required for Compliance (RC), the following provisions apply: (1) The steps labeled as RC, including substeps under an RC step and any figures identified in an RC step, must be done to comply with the AD, and an AMOC is required for any deviations to RC steps, including substeps and identified figures; and (2) steps not labeled as RC may be deviated from using accepted methods in accordance with the operator’s maintenance or inspection program without obtaining approval of an AMOC, provided the RC steps, including substeps and identified figures, can still be done as specified, and the airplane can be put back in an airworthy condition. Differences Between This Proposed AD and the Service Information The service bulletin specifies to contact the manufacturer for instructions on how to repair certain conditions, but this proposed AD would require repairing those conditions in one of the following ways: • In accordance with a method that we approve; or • Using data that meet the certification basis of the airplane, and that have been approved by the Boeing Commercial Airplanes Organization Designation Authorization (ODA) whom we have authorized to make those findings. Costs of Compliance We estimate that this proposed AD affects 60 airplanes of U.S. registry. We estimate the following costs to comply with this proposed AD: asabaliauskas on DSK5VPTVN1PROD with PROPOSALS ESTIMATED COSTS Action Labor cost Inspections of left and right side pivot bulkhead forward chord. Post-Repair Inspections .......... Up to 15 work-hours × $85 per hour = $1,275 per inspection cycle. Up to 11 work-hours × $85 per hour = $935 per inspection cycle. VerDate Sep<11>2014 16:22 Jun 12, 2015 Jkt 235001 PO 00000 Frm 00025 Parts cost Cost per product $0 Cost on U.S. operators Up to $76,500 per inspection cycle. 0 Fmt 4702 Up to $1,275 per inspection cycle. Up to $935 per inspection cycle. Up to $56,100 per inspection cycle. Sfmt 4702 E:\FR\FM\15JNP1.SGM 15JNP1 34105 Federal Register / Vol. 80, No. 114 / Monday, June 15, 2015 / Proposed Rules We estimate the following costs to do any necessary repairs and modifications 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 Action Labor cost Small crack repair .......................................................... Up to 45 work-hours × $85 per hour = $3,825 per side. Up to 137 work-hours × $85 per hour = $11,645 ........ Modification of the STA 2370 Pivot Bulkhead (forward outer chord replacement). Parts cost (1) $34,086 Cost per product Up to $7,650. Up to $45,731. 1 We have received no definitive data that would enable us to provide parts cost estimates for the on-condition repair 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. asabaliauskas on DSK5VPTVN1PROD 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. 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 VerDate Sep<11>2014 16:22 Jun 12, 2015 Jkt 235001 (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 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– 2015–1428; Directorate Identifier 2015– NM–026–AD. (a) Comments Due Date We must receive comments by July 30, 2015. (b) Affected ADs None. (c) Applicability This AD applies to The Boeing Company Model 777–200 and –300 series airplanes, certificated in any category, as identified in Boeing Alert Service Bulletin 777–53A0075, dated January 14, 2015. (d) Subject Air Transport Association (ATA) of America Code 53, Fuselage. (e) Unsafe Condition This AD was prompted by reports of fatigue cracking of the forward outer chord of the station (STA) 2370 pivot bulkhead. We are issuing this AD to detect and correct fatigue cracking of the outer flanges of the left and right side forward outer chords of the STA 2370 pivot bulkhead, which could result PO 00000 Frm 00026 Fmt 4702 Sfmt 4702 in a severed forward outer chord and consequent loss of horizontal stabilizer control. (f) Compliance Comply with this AD within the compliance times specified, unless already done. (g) Inspections and Corrective Actions At the times specified in table 1 of paragraph 1.E., ‘‘Compliance,’’ of Boeing Alert Service Bulletin 777–53A0075, dated January 14, 2015, except as provided in paragraph (j)(1) of this AD: Do a detailed inspection and high frequency eddy current (HFEC) inspections for cracking of the left and right side forward outer chords of the STA 2370 pivot bulkhead, and do all applicable related investigative and corrective actions, in accordance with the Accomplishment Instructions of Boeing Alert Service Bulletin 777–53A0075, dated January 14, 2015, except as provided in paragraph (j)(2) of this AD. Do all applicable related investigative and corrective actions before further flight. Repeat the inspections thereafter at the applicable intervals specified in table 1 of paragraph 1.E., ‘‘Compliance,’’ of Boeing Alert Service Bulletin 777– 53A0075, dated January 14, 2015, until the modification specified in paragraph (i) of this AD is done. (h) Post-Repair Inspections For airplanes on which a repair specified in Part 2 of the Accomplishment Instructions of Boeing Alert Service Bulletin 777– 53A0075 has been done: At the times specified in table 2 of paragraph 1.E., ‘‘Compliance,’’ of Boeing Alert Service Bulletin 777–53A0075, dated January 14, 2015, do a surface HFEC inspection, an openhole HFEC inspection, and a detailed inspection for cracking of the left side and right side forward outer chords of the STA 2370 pivot bulkhead, and do all applicable related investigative and corrective actions, in accordance with Part 3 of the Accomplishment Instructions of Boeing Alert Service Bulletin 777–53A0075, dated January 14, 2015, except as required by paragraph (j)(2) of this AD. Do all applicable related investigative and corrective actions before further flight. Repeat the inspections thereafter at the applicable times specified in table 2 of paragraph 1.E., ‘‘Compliance,’’ of Boeing Alert Service Bulletin 777–53A0075, dated January 14, 2015, until the modification specified in paragraph (i) of this AD is done. E:\FR\FM\15JNP1.SGM 15JNP1 34106 Federal Register / Vol. 80, No. 114 / Monday, June 15, 2015 / Proposed Rules (i) Terminating Action Modifying the STA 2370 pivot bulkhead by replacing the left and right side forward outer chords and upper splice angles, and doing all applicable related investigative and corrective actions, terminates the repetitive inspections required by paragraphs (g) and (h) of this AD for the modified location only. The modification must be done in accordance with the Accomplishment Instructions of Boeing Service Bulletin 777– 53–0076, dated January 14, 2015, except as required by paragraph (j)(2) of this AD. asabaliauskas on DSK5VPTVN1PROD with PROPOSALS (j) Exceptions to Service Bulletin Specifications (1) Where Boeing Alert Service Bulletin 777–53A0075, dated January 14, 2015, specifies a compliance time ‘‘after the Original Issue date of this Service Bulletin,’’ this AD requires compliance within the specified compliance time after the effective date of this AD. (2) Although Boeing Alert Service Bulletin 777–53A0075, dated January 14, 2015; and Boeing Service Bulletin 777–530076, dated January 14, 2015; specify to contact Boeing for appropriate action, and Boeing Alert Service Bulletin 777–53A0075, dated January 14, 2015, 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 (k) of this AD. (k) Alternative Methods of Compliance (AMOCs) (1) The Manager, Seattle Aircraft Certification Office (ACO), FAA, has the authority to approve AMOCs for this AD, if requested using the procedures found in 14 CFR 39.19. In accordance with 14 CFR 39.19, send your request to your principal inspector or local Flight Standards District Office, as appropriate. If sending information directly to the manager of the ACO, send it to the attention of the person identified in paragraph (l)(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 required by this AD if it is approved by the Boeing Commercial Airplanes Organization Designation Authorization (ODA) that has been authorized by the Manager, Seattle ACO, to make those findings. For a repair method to be approved, the repair must meet the certification basis of the airplane, and the approval must specifically refer to this AD. (4) Except as required by paragraph (j)(2) of this AD: For service information that contains steps that are labeled as Required for Compliance (RC), the provisions of paragraphs (k)(4)(i) and (k)(4)(ii) 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. VerDate Sep<11>2014 16:22 Jun 12, 2015 Jkt 235001 (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. prevent an ignition source in the fuel tank vapor space, which could result in a fuel tank explosion and consequent loss of the airplane. We must receive comments on this proposed AD by July 30, 2015. DATES: [Docket No. FAA–2015–1982; Directorate Identifier 2014–NM–108–AD] 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: U.S. Department of Transportation, Docket Operations, M– 30, West Building Ground Floor, Room W12–140, 1200 New Jersey Avenue SE., Washington, DC, between 9 a.m. and 5 p.m., Monday through Friday, except Federal holidays. For service information identified in this proposed AD, contact Fokker Services B.V., Technical Services Dept., P.O. Box 1357, 2130 EL Hoofddorp, the Netherlands; telephone +31 (0)88–6280– 350; fax +31 (0)88–6280–111; email technicalservices@fokker.com; Internet http://www.myfokkerfleet.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. RIN 2120–AA64 Examining the AD Docket Airworthiness Directives; Fokker Services B.V. Airplanes You may examine the AD docket on the Internet at http:// www.regulations.gov by searching for and locating Docket No. FAA–2015– 1982; or in person at the Docket Operations office between 9 a.m. and 5 p.m., Monday through Friday, except Federal holidays. The AD docket contains this proposed AD, the regulatory evaluation, any comments received, and other information. The street address for the Docket Operations office (telephone 800–647–5527) is in the ADDRESSES section. Comments will be available in the AD docket shortly after receipt. (l) Related Information (1) For more information about this AD, contact Narinder Luthra, Aerospace Engineer, Airframe Branch, ANM–120S, FAA, Seattle ACO, 1601 Lind Avenue SW., Renton, WA 98057–3356; phone: 425–917–6513; fax: 425– 917–6590; email: narinder.luthra@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; phone: 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 June 2, 2015. Jeffrey E. Duven, Manager, Transport Airplane Directorate, Aircraft Certification Service. [FR Doc. 2015–14231 Filed 6–12–15; 8:45 am] BILLING CODE 4910–13–P DEPARTMENT OF TRANSPORTATION Federal Aviation Administration 14 CFR Part 39 Federal Aviation Administration (FAA), DOT. ACTION: Notice of proposed rulemaking (NPRM). AGENCY: We propose to adopt a new airworthiness directive (AD) for all Fokker Services B.V. Model F.28 Mark 1000, 2000, 3000, and 4000 airplanes. This proposed AD was prompted by a design review, which revealed that no controlled bonding provisions are present on a number of critical locations outside the fuel tank. This proposed AD would require installing additional and improved fuel system bonding provisions, and revising the airplane maintenance or inspection program, as applicable, by incorporating fuel airworthiness limitation items and critical design configuration control limitations. We are proposing this AD to SUMMARY: PO 00000 Frm 00027 Fmt 4702 Sfmt 4702 ADDRESSES: Tom Rodriguez, Aerospace Engineer, International Branch, ANM–116, Transport Airplane Directorate, FAA, 1601 Lind Avenue SW., Renton, WA 98057–3356; telephone 425–227–1137; fax 425–227–1149. FOR FURTHER INFORMATION CONTACT: SUPPLEMENTARY INFORMATION: E:\FR\FM\15JNP1.SGM 15JNP1

Agencies

[Federal Register Volume 80, Number 114 (Monday, June 15, 2015)]
[Proposed Rules]
[Pages 34103-34106]
From the Federal Register Online via the Government Publishing Office [www.gpo.gov]
[FR Doc No: 2015-14231]


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

DEPARTMENT OF TRANSPORTATION

Federal Aviation Administration

14 CFR Part 39

[Docket No. FAA-2015-1428; Directorate Identifier 2015-NM-026-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 777-200 and -300 series airplanes. 
This proposed AD was prompted by reports of fatigue cracking of a 
certain chord of the pivot bulkhead. This proposed AD would require 
repetitive inspections for cracking of the left side and right side 
forward outer chords of the pivot bulkhead, and related investigative 
and corrective actions if necessary. This proposed AD provides a 
modification of the pivot bulkhead, which would terminate the 
repetitive inspections. We are proposing this AD to detect and correct 
fatigue cracking of the outer flanges of the left and right side 
forward outer chords of the pivot bulkhead, which could result in a 
severed forward outer chord and consequent loss of horizontal 
stabilizer control.

DATES: We must receive comments on this proposed AD by July 30, 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; phone: 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-2015-1428.

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-
1428; 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: Narinder Luthra, Aerospace Engineer, 
Airframe Branch, ANM-120S, FAA, Seattle Aircraft Certification Office 
(ACO), 1601 Lind Avenue SW., Renton, WA 98057-3356; phone: 425-917-
6513; fax: 425-917-6590; email: narinder.luthra@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-2015-1428; 
Directorate Identifier 2015-NM-026-AD'' at the beginning of your 
comments. We specifically invite

[[Page 34104]]

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 fatigue cracking of the forward outer chord 
of the STA 2370 pivot bulkhead. Cracks in the forward outer chords of 
the STA 2370 pivot bulkhead that are not found and repaired can become 
large and result in a severed forward outer chord. The cracks were 
caused by a stress concentration, which is generated at the transition 
radius of the forward outer flange of the chord prior to the chord 
splice at the upper longeron. Since the horizontal stabilizer is 
attached to the STA 2370 bulkhead at two pivot locations, fatigue 
cracking of the outer flanges of the left and right side forward outer 
chords of the STA 2370 pivot bulkhead, if not corrected, could result 
in a severed forward outer chord and consequent loss of horizontal 
stabilizer control.

Related Service Information Under 1 CFR Part 51

    We reviewed the following Boeing service information.
     Boeing Alert Service Bulletin 777-53A0075, dated January 
14, 2015, describes procedures for repetitive detailed and high 
frequency eddy current (HFEC) inspections for cracking of the outer 
flanges of the left and right side forward outer chords of the STA 2370 
pivot bulkhead, repetitive post-repair inspections for certain 
airplanes, and related investigative and corrective actions.
     Boeing Service Bulletin 777-53-0076, dated January 14, 
2015, describes procedures for a modification of the STA 2370 pivot 
bulkhead by replacing the left and right side forward outer chords and 
upper splice angles, and 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 these same type 
designs.

Proposed AD Requirements

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

Differences Between This Proposed AD and the Service Information

    The service bulletin specifies to contact the manufacturer for 
instructions on how to repair certain conditions, but this proposed AD 
would require repairing those conditions in one of the following ways:
     In accordance with a method that we approve; or
     Using data that meet the certification basis of the 
airplane, and that have been approved by the Boeing Commercial 
Airplanes Organization Designation Authorization (ODA) whom we have 
authorized to make those findings.

Costs of Compliance

    We estimate that this proposed AD affects 60 airplanes of U.S. 
registry.
    We estimate the following costs to comply with this proposed AD:

                                                 Estimated Costs
----------------------------------------------------------------------------------------------------------------
                                                                                                Cost on U.S.
              Action                    Labor cost        Parts cost    Cost per product          operators
----------------------------------------------------------------------------------------------------------------
Inspections of left and right      Up to 15 work-hours            $0  Up to $1,275 per      Up to $76,500 per
 side pivot bulkhead forward        x $85 per hour =                   inspection cycle.     inspection cycle.
 chord.                             $1,275 per
                                    inspection cycle.
Post-Repair Inspections..........  Up to 11 work-hours             0  Up to $935 per        Up to $56,100 per
                                    x $85 per hour =                   inspection cycle.     inspection cycle.
                                    $935 per inspection
                                    cycle.
----------------------------------------------------------------------------------------------------------------


[[Page 34105]]

    We estimate the following costs to do any necessary repairs and 
modifications 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
----------------------------------------------------------------------------------------------------------------
                Action                           Labor cost            Parts cost         Cost per product
----------------------------------------------------------------------------------------------------------------
Small crack repair...................  Up to 45 work[dash]hours x           (\1\)  Up to $7,650.
                                        $85 per hour = $3,825 per
                                        side.
Modification of the STA 2370 Pivot     Up to 137 work[dash]hours x        $34,086  Up to $45,731.
 Bulkhead (forward outer chord          $85 per hour = $11,645.
 replacement).
----------------------------------------------------------------------------------------------------------------
\1\ We have received no definitive data that would enable us to provide parts cost estimates for the on-
  condition repair 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.

The Proposed Amendment

    Accordingly, under the authority delegated to me by the 
Administrator, the FAA proposes to amend 14 CFR part 39 as follows:

PART 39--AIRWORTHINESS DIRECTIVES

0
1. The authority citation for part 39 continues to read as follows:

    Authority:  49 U.S.C. 106(g), 40113, 44701.


Sec.  39.13  [Amended]

0
2. The FAA amends Sec.  39.13 by adding the following new airworthiness 
directive (AD):

The Boeing Company: Docket No. FAA-2015-1428; Directorate Identifier 
2015-NM-026-AD.

(a) Comments Due Date

    We must receive comments by July 30, 2015.

(b) Affected ADs

    None.

(c) Applicability

    This AD applies to The Boeing Company Model 777-200 and -300 
series airplanes, certificated in any category, as identified in 
Boeing Alert Service Bulletin 777-53A0075, dated January 14, 2015.

(d) Subject

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

(e) Unsafe Condition

    This AD was prompted by reports of fatigue cracking of the 
forward outer chord of the station (STA) 2370 pivot bulkhead. We are 
issuing this AD to detect and correct fatigue cracking of the outer 
flanges of the left and right side forward outer chords of the STA 
2370 pivot bulkhead, which could result in a severed forward outer 
chord and consequent loss of horizontal stabilizer control.

(f) Compliance

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

(g) Inspections and Corrective Actions

    At the times specified in table 1 of paragraph 1.E., 
``Compliance,'' of Boeing Alert Service Bulletin 777-53A0075, dated 
January 14, 2015, except as provided in paragraph (j)(1) of this AD: 
Do a detailed inspection and high frequency eddy current (HFEC) 
inspections for cracking of the left and right side forward outer 
chords of the STA 2370 pivot bulkhead, and do all applicable related 
investigative and corrective actions, in accordance with the 
Accomplishment Instructions of Boeing Alert Service Bulletin 777-
53A0075, dated January 14, 2015, except as provided in paragraph 
(j)(2) of this AD. Do all applicable related investigative and 
corrective actions before further flight. Repeat the inspections 
thereafter at the applicable intervals specified in table 1 of 
paragraph 1.E., ``Compliance,'' of Boeing Alert Service Bulletin 
777-53A0075, dated January 14, 2015, until the modification 
specified in paragraph (i) of this AD is done.

(h) Post-Repair Inspections

    For airplanes on which a repair specified in Part 2 of the 
Accomplishment Instructions of Boeing Alert Service Bulletin 777-
53A0075 has been done: At the times specified in table 2 of 
paragraph 1.E., ``Compliance,'' of Boeing Alert Service Bulletin 
777-53A0075, dated January 14, 2015, do a surface HFEC inspection, 
an open-hole HFEC inspection, and a detailed inspection for cracking 
of the left side and right side forward outer chords of the STA 2370 
pivot bulkhead, and do all applicable related investigative and 
corrective actions, in accordance with Part 3 of the Accomplishment 
Instructions of Boeing Alert Service Bulletin 777-53A0075, dated 
January 14, 2015, except as required by paragraph (j)(2) of this AD. 
Do all applicable related investigative and corrective actions 
before further flight. Repeat the inspections thereafter at the 
applicable times specified in table 2 of paragraph 1.E., 
``Compliance,'' of Boeing Alert Service Bulletin 777-53A0075, dated 
January 14, 2015, until the modification specified in paragraph (i) 
of this AD is done.

[[Page 34106]]

(i) Terminating Action

    Modifying the STA 2370 pivot bulkhead by replacing the left and 
right side forward outer chords and upper splice angles, and doing 
all applicable related investigative and corrective actions, 
terminates the repetitive inspections required by paragraphs (g) and 
(h) of this AD for the modified location only. The modification must 
be done in accordance with the Accomplishment Instructions of Boeing 
Service Bulletin 777-53-0076, dated January 14, 2015, except as 
required by paragraph (j)(2) of this AD.

(j) Exceptions to Service Bulletin Specifications

    (1) Where Boeing Alert Service Bulletin 777-53A0075, dated 
January 14, 2015, specifies a compliance time ``after the Original 
Issue date of this Service Bulletin,'' this AD requires compliance 
within the specified compliance time after the effective date of 
this AD.
    (2) Although Boeing Alert Service Bulletin 777-53A0075, dated 
January 14, 2015; and Boeing Service Bulletin 777-530076, dated 
January 14, 2015; specify to contact Boeing for appropriate action, 
and Boeing Alert Service Bulletin 777-53A0075, dated January 14, 
2015, 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 
(k) of this AD.

(k) Alternative Methods of Compliance (AMOCs)

    (1) The Manager, Seattle Aircraft Certification Office (ACO), 
FAA, has the authority to approve AMOCs for this AD, if requested 
using the procedures found in 14 CFR 39.19. In accordance with 14 
CFR 39.19, send your request to your principal inspector or local 
Flight Standards District Office, as appropriate. If sending 
information directly to the manager of the ACO, send it to the 
attention of the person identified in paragraph (l)(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 required by this AD if it is approved by the 
Boeing Commercial Airplanes Organization Designation Authorization 
(ODA) that has been authorized by the Manager, Seattle ACO, to make 
those findings. For a repair method to be approved, the repair must 
meet the certification basis of the airplane, and the approval must 
specifically refer to this AD.
    (4) Except as required by paragraph (j)(2) of this AD: For 
service information that contains steps that are labeled as Required 
for Compliance (RC), the provisions of paragraphs (k)(4)(i) and 
(k)(4)(ii) 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.

(l) Related Information

    (1) For more information about this AD, contact Narinder Luthra, 
Aerospace Engineer, Airframe Branch, ANM-120S, FAA, Seattle ACO, 
1601 Lind Avenue SW., Renton, WA 98057-3356; phone: 425-917-6513; 
fax: 425-917-6590; email: narinder.luthra@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; phone: 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 June 2, 2015.
Jeffrey E. Duven,
Manager, Transport Airplane Directorate, Aircraft Certification 
Service.
[FR Doc. 2015-14231 Filed 6-12-15; 8:45 am]
 BILLING CODE 4910-13-P