Airworthiness Directives; Airbus Airplanes, 56405-56407 [2015-23409]

Download as PDF Federal Register / Vol. 80, No. 181 / Friday, September 18, 2015 / Proposed Rules PART 327—IMPORTED PRODUCTS 1. The authority citation for part 327 continues to read as follows: ■ Authority: 21 U.S.C. 601–695; 7 CFR 2.18, 2.53. § 327.2 [Amended] 2. Amend § 327.2 by adding Namibia in alphabetical order to the list of countries in paragraph (b). ■ Done at Washington, DC, on September 14, 2015. Alfred V. Almanza, Acting Administrator. [FR Doc. 2015–23455 Filed 9–17–15; 8:45 am] BILLING CODE 3410–DM–P DEPARTMENT OF TRANSPORTATION Federal Aviation Administration 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 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 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. 14 CFR Part 39 Examining the AD Docket [Docket No. FAA–2015–3631; Directorate Identifier 2015–NM–060–AD] You may examine the AD docket on the Internet at http:// www.regulations.gov by searching for and locating Docket No. FAA–2015– 3631; or in person at the Docket Management Facility between 9 a.m. and 5 p.m., Monday through Friday, except Federal holidays. The AD docket contains this proposed AD, the regulatory evaluation, any comments received, and other information. The street address for the Docket Operations office (telephone 800–647–5527) is in the ADDRESSES section. Comments will be available in the AD docket shortly after receipt. FOR FURTHER INFORMATION CONTACT: 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. SUPPLEMENTARY INFORMATION: RIN 2120–AA64 Airworthiness Directives; Airbus Airplanes Federal Aviation Administration (FAA), DOT. ACTION: Notice of proposed rulemaking (NPRM). AGENCY: We propose to adopt a new airworthiness directive (AD) for certain Airbus Model A330–200 and –300 series airplanes; Model A330–200 Freighter series airplanes; and Model A340–200, –300, –500, and –600 series airplanes. This proposed AD was prompted by reports of chafed wiring at the upper left corner of the cockpit door. The affected wire bundle was not grounded on the cockpit door frame. This proposed AD would require modifying the cockpit door frame structure, installing bondingleads to the upper cockpit door frame, and modifying the upper cockpit door plate cover. We are proposing this AD to prevent electrical shock injury to persons contacting the cockpit door. DATES: We must receive comments on this proposed AD by November 2, 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, tkelley on DSK3SPTVN1PROD with PROPOSALS SUMMARY: VerDate Sep<11>2014 17:14 Sep 17, 2015 Jkt 235001 Comments Invited We invite you to send any written relevant data, views, or arguments about this proposed AD. Send your comments to an address listed under the ADDRESSES section. Include ‘‘Docket No. FAA–2015–3631; Directorate Identifier 2015–NM–060–AD’’ at the beginning of your comments. We specifically invite comments on the overall regulatory, economic, environmental, and energy aspects of this proposed AD. We will consider all comments received by the closing date and may amend this proposed AD based on those comments. We will post all comments we receive, without change, to http:// www.regulations.gov, including any PO 00000 Frm 00007 Fmt 4702 Sfmt 4702 56405 personal information you provide. We will also post a report summarizing each substantive verbal contact we receive about this proposed AD. Discussion The European Aviation Safety Agency (EASA), which is the Technical Agent for the Member States of the European Union, has issued EASA Airworthiness Directive 2015–0037, dated March 2, 2015 (referred to after this as the Mandatory Continuing Airworthiness Information, or ‘‘the MCAI’’), to correct an unsafe condition for certain Airbus Model A330–200 and –300 series airplanes; Model A330–200 Freighter series airplanes; and Model A340–200, –300, –500, and –600 series airplanes. The MCAI states: An operator has reported chafed wiring at the upper left corner of the cockpit door. The investigation concluded that the affected wire bundle, which supplies a voltage of 115V [volt] AC [alternating current], was not grounded on the cockpit door frame as part of the design of A330 and A340 aeroplanes. This condition, if not corrected, could result in injury [electrical shock], in case any person gets in contact with the door frame. Prompted by these findings, Airbus issued SB [service bulletin] A330–25–3534, SB A340–25–4349 and SB A340–25–5212 to provide instructions to modify the electrical bonding of the cockpit door. For the reasons described above, this [EASA] AD requires modification of the cockpit door frame structure, installation of bonding-leads to the upper cockpit door frame and modification of the upper cockpit door plate cover. You may examine the MCAI in the AD docket on the Internet at http:// www.regulations.gov by searching for and locating Docket No. FAA–2015– 3631. Related Service Information Under 1 CFR Part 51 Airbus has issued the following service information. • Service Bulletin A330–25–3534, Revision 01, dated October 23, 2014. This service information describes procedures for modifying the cockpit door frame structure and installing bonding-leads to the upper cockpit door frame. • Service Bulletin A340–25–4349, Revision 01, dated October 27, 2014. This service information describes procedures for modifying the cockpit door frame structure and installing bonding-leads to the upper cockpit door frame. • Service Bulletin A340–25–5212, Revision 01, dated October 27, 2014. This service information describes procedures for modifying the cockpit door frame structure and installing E:\FR\FM\18SEP1.SGM 18SEP1 56406 Federal Register / Vol. 80, No. 181 / Friday, September 18, 2015 / Proposed Rules bonding-leads to the upper cockpit door frame. 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. tkelley on DSK3SPTVN1PROD with PROPOSALS FAA’s Determination and Requirements of This Proposed AD This product has been approved by the aviation authority of another country, and is approved for operation in the United States. Pursuant to our bilateral agreement with the State of Design Authority, we have been notified of the unsafe condition described in the MCAI and service information referenced above. We are proposing this AD because we evaluated all pertinent information and determined an unsafe condition exists and is likely to exist or develop on other products of these same type designs. Explanation of ‘‘RC’’ Procedures and Tests 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 procedures and tests in the service information are required for compliance with an AD. Differentiating these procedures and tests 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 procedures and tests identified as Required for Compliance (RC) in any service information have a direct effect on detecting, preventing, resolving, or eliminating an identified unsafe condition. As specified in a NOTE under the Accomplishment Instructions of the specified service information, procedures and tests that are identified as RC in any service information must be done to comply with the proposed AD. However, procedures and 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 obtaining approval of an alternative method of compliance (AMOC), provided the procedures and tests identified as RC can be done and the airplane can be put back in a serviceable condition. Any substitutions or changes to procedures or tests VerDate Sep<11>2014 17:14 Sep 17, 2015 Jkt 235001 identified as RC will require approval of an AMOC. Costs of Compliance We estimate that this proposed AD affects 70 airplanes of U.S. registry. We also estimate that it would take about 27 work-hours per product to comply with the basic requirements of this proposed AD. The average labor rate is $85 per work-hour. Required parts would cost about $2,620 per product. Based on these figures, we estimate the cost of this proposed AD on U.S. operators to be $344,050, or $4,915 per product. 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. 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 1. The authority citation for part 39 continues to read as follows: ■ Authority: 49 U.S.C. 106(g), 40113, 44701. 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); PO 00000 Frm 00008 Fmt 4702 Sfmt 4702 § 39.13 [Amended] 2. The FAA amends § 39.13 by adding the following new airworthiness directive (AD): ■ Airbus: Docket No. FAA–2015–3631; Directorate Identifier 2015–NM–060–AD. (a) Comments Due Date We must receive comments by November 2, 2015. (b) Affected ADs None. (c) Applicability This AD applies to all the Airbus airplanes identified in paragraphs (c)(1), (c)(2), and (c)(3) of this AD, certificated in any category, except airplanes on which Airbus Modification 203066, Modification 203074, or Modification 203372 has been embodied in production. (1) Model A330–201, –202, –203, –223, –223F, –243, –243F, –301, –302, –303, –321, –322, –323, –341, –342, and –343 airplanes; all manufacturer serial numbers (MSNs); if modified in-service as specified in Airbus Service Bulletin A330–25–3161, or in production with Airbus Modification 50014. (2) Model A340–211, –212, –213, –311, –312, and –313 airplanes; all MSNs, if modified in-service as specified in Airbus Service Bulletin A340–25–4181, or in production with Airbus Modification 50014. (3) Model A340–541 airplanes; and Model A340–642 airplanes; all MSNs. (d) Subject Air Transport Association (ATA) of America Code 25, Equipment/Furnishings. (e) Reason This AD was prompted by reports of chafed wiring at the upper left corner of the cockpit door. The affected wire bundle was not grounded on the cockpit door frame. We are issuing this AD to prevent electrical E:\FR\FM\18SEP1.SGM 18SEP1 Federal Register / Vol. 80, No. 181 / Friday, September 18, 2015 / Proposed Rules shock injury to persons contacting the cockpit door. (f) Compliance Comply with this AD within the compliance times specified, unless already done. (g) Door Modification and Installation Within 24 months after the effective date of this AD, modify the cockpit door frame structure and install bonding-leads to the upper cockpit door frame, in accordance with the Accomplishment Instructions of the applicable service information identified in paragraphs (g)(1), (g)(2), and (g)(3) of this AD. (1) Airbus Service Bulletin A330–25–3534, Revision 01, dated October 23, 2014. (2) Airbus Service Bulletin A340–25–4349, Revision 01, dated October 27, 2014. (3) Airbus Service Bulletin A340–25–5212, Revision 01, dated October 27, 2014. tkelley on DSK3SPTVN1PROD with PROPOSALS (h) Cover Plate Modification of the Upper Flight Deck Door Except for airplanes on which Airbus Modification 52869 or Modification 53292 has been embodied in production: Before or concurrently with accomplishing the modification required by paragraph (g) of this AD, modify the upper cockpit door plate cover, in accordance with the Accomplishment Instructions of the applicable service information identified in paragraphs (h)(1), (h)(2), and (h)(3) of this AD. (1) Airbus Service Bulletin A330–25–3534, Revision 01, dated October 23, 2014. (2) Airbus Service Bulletin A340–25–4349, Revision 01, dated October 27, 2014. (3) Airbus Service Bulletin A340–25–5212, Revision 01, dated October 27, 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: 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-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 European Aviation Safety Agency VerDate Sep<11>2014 17:14 Sep 17, 2015 Jkt 235001 (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 obtaining approval of an AMOC, provided the procedures and tests identified as RC can be done and the airplane can be put back in a serviceable condition. Any substitutions or changes to procedures or tests identified as RC require approval of an AMOC. (j) Related Information (1) Refer to Mandatory Continuing Airworthiness Information (MCAI) EASA Airworthiness Directive 2015–0037, dated March 2, 2015, 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– 2015–3631. (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 September 11, 2015. Michael Kaszycki, Acting Manager, Transport Airplane Directorate, Aircraft Certification Service. [FR Doc. 2015–23409 Filed 9–17–15; 8:45 am] BILLING CODE 4910–13–P DEPARTMENT OF TRANSPORTATION Federal Aviation Administration 14 CFR Part 39 [Docket No. FAA–2014–0774; Directorate Identifier 2013–NM–154–AD] RIN 2120–AA64 Airworthiness Directives; The Boeing Company Airplanes Federal Aviation Administration (FAA), DOT. ACTION: Supplemental notice of proposed rulemaking (SNPRM); reopening of comment period. AGENCY: We are revising an earlier proposed airworthiness directive (AD) that proposed to supersede AD 2006– SUMMARY: PO 00000 Frm 00009 Fmt 4702 Sfmt 4702 56407 22–15 for all The Boeing Company Model 747–100, 747–100B, 747–100B SUD, 747–200B, 747–200C, 747–200F, 747–300, 747–400, 747–400D, 747– 400F, 747SR, and 747SP series airplanes. AD 2006–22–15 requires repetitive inspections for cracking of certain panel webs and stiffeners of the nose wheel well (NWW), and corrective actions if necessary; and replacement of certain panels with new panels, which terminates the repetitive inspections. The notice of proposed rulemaking (NPRM) proposed to reduce a compliance time and add certain inspections and applicable repair. The NPRM was prompted by reports of fatigue cracking in the panel webs and stiffeners of the NWW found prior to the inspection threshold of AD 2006–22–15. This action revises the NPRM by specifying a repetitive inspection interval for a certain NWW area inspection. We are proposing this SNPRM to prevent fatigue cracking of the NWW side and top panels, which could result in a NWW depressurization event severe enough to reduce the structural integrity of the fuselage. Since these actions impose an additional burden over that proposed in the NPRM, we are reopening the comment period to allow the public the chance to comment on these proposed changes. DATES: We must receive comments on this SNPRM by November 2, 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: U.S. Department of Transportation, Docket Operations, M– 30, West Building Ground Floor, Room W12–140, 1200 New Jersey Avenue SE., Washington, DC 20590, 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 E:\FR\FM\18SEP1.SGM 18SEP1

Agencies

[Federal Register Volume 80, Number 181 (Friday, September 18, 2015)]
[Proposed Rules]
[Pages 56405-56407]
From the Federal Register Online via the Government Publishing Office [www.gpo.gov]
[FR Doc No: 2015-23409]


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DEPARTMENT OF TRANSPORTATION

Federal Aviation Administration

14 CFR Part 39

[Docket No. FAA-2015-3631; Directorate Identifier 2015-NM-060-AD]
RIN 2120-AA64


Airworthiness Directives; Airbus 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 Airbus Model A330-200 and -300 series airplanes; Model A330-200 
Freighter series airplanes; and Model A340-200, -300, -500, and -600 
series airplanes. This proposed AD was prompted by reports of chafed 
wiring at the upper left corner of the cockpit door. The affected wire 
bundle was not grounded on the cockpit door frame. This proposed AD 
would require modifying the cockpit door frame structure, installing 
bonding-leads to the upper cockpit door frame, and modifying the upper 
cockpit door plate cover. We are proposing this AD to prevent 
electrical shock injury to persons contacting the cockpit door.

DATES: We must receive comments on this proposed AD by November 2, 
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: 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 
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 referenced service information at the 
FAA, Transport Airplane Directorate, 1601 Lind Avenue SW., Renton, WA. 
For information on the availability of this material at the FAA, call 
425-227-1221.

Examining the AD Docket

    You may examine the AD docket on the Internet at http://www.regulations.gov by searching for and locating Docket No. FAA-2015-
3631; or in person at the Docket Management Facility between 9 a.m. and 
5 p.m., Monday through Friday, except Federal holidays. The AD docket 
contains this proposed AD, the regulatory evaluation, any comments 
received, and other information. The street address for the Docket 
Operations office (telephone 800-647-5527) is in the ADDRESSES section. 
Comments will be available in the AD docket shortly after receipt.

FOR FURTHER INFORMATION CONTACT: 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.

SUPPLEMENTARY INFORMATION: 

Comments Invited

    We invite you to send any written relevant data, views, or 
arguments about this proposed AD. Send your comments to an address 
listed under the ADDRESSES section. Include ``Docket No. FAA-2015-3631; 
Directorate Identifier 2015-NM-060-AD'' at the beginning of your 
comments. We specifically invite comments on the overall regulatory, 
economic, environmental, and energy aspects of this proposed AD. We 
will consider all comments received by the closing date and may amend 
this proposed AD based on those comments.
    We will post all comments we receive, without change, to 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

    The European Aviation Safety Agency (EASA), which is the Technical 
Agent for the Member States of the European Union, has issued EASA 
Airworthiness Directive 2015-0037, dated March 2, 2015 (referred to 
after this as the Mandatory Continuing Airworthiness Information, or 
``the MCAI''), to correct an unsafe condition for certain Airbus Model 
A330-200 and -300 series airplanes; Model A330-200 Freighter series 
airplanes; and Model A340-200, -300, -500, and -600 series airplanes. 
The MCAI states:

    An operator has reported chafed wiring at the upper left corner 
of the cockpit door. The investigation concluded that the affected 
wire bundle, which supplies a voltage of 115V [volt] AC [alternating 
current], was not grounded on the cockpit door frame as part of the 
design of A330 and A340 aeroplanes.
    This condition, if not corrected, could result in injury 
[electrical shock], in case any person gets in contact with the door 
frame.
    Prompted by these findings, Airbus issued SB [service bulletin] 
A330-25-3534, SB A340-25-4349 and SB A340-25-5212 to provide 
instructions to modify the electrical bonding of the cockpit door.
    For the reasons described above, this [EASA] AD requires 
modification of the cockpit door frame structure, installation of 
bonding-leads to the upper cockpit door frame and modification of 
the upper cockpit door plate cover.

    You may examine the MCAI in the AD docket on the Internet at http://www.regulations.gov by searching for and locating Docket No. FAA-2015-
3631.

Related Service Information Under 1 CFR Part 51

    Airbus has issued the following service information.
     Service Bulletin A330-25-3534, Revision 01, dated October 
23, 2014. This service information describes procedures for modifying 
the cockpit door frame structure and installing bonding-leads to the 
upper cockpit door frame.
     Service Bulletin A340-25-4349, Revision 01, dated October 
27, 2014. This service information describes procedures for modifying 
the cockpit door frame structure and installing bonding-leads to the 
upper cockpit door frame.
     Service Bulletin A340-25-5212, Revision 01, dated October 
27, 2014. This service information describes procedures for modifying 
the cockpit door frame structure and installing

[[Page 56406]]

bonding-leads to the upper cockpit door frame.
    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 and Requirements of This Proposed AD

    This product has been approved by the aviation authority of another 
country, and is approved for operation in the United States. Pursuant 
to our bilateral agreement with the State of Design Authority, we have 
been notified of the unsafe condition described in the MCAI and service 
information referenced above. We are proposing this AD because we 
evaluated all pertinent information and determined an unsafe condition 
exists and is likely to exist or develop on other products of these 
same type designs.

Explanation of ``RC'' Procedures and Tests 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 procedures and tests in the service information are 
required for compliance with an AD. Differentiating these procedures 
and tests 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 procedures 
and tests identified as Required for Compliance (RC) in any service 
information have a direct effect on detecting, preventing, resolving, 
or eliminating an identified unsafe condition.
    As specified in a NOTE under the Accomplishment Instructions of the 
specified service information, procedures and tests that are identified 
as RC in any service information must be done to comply with the 
proposed AD. However, procedures and 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 obtaining 
approval of an alternative method of compliance (AMOC), provided the 
procedures and tests identified as RC can be done and the airplane can 
be put back in a serviceable condition. Any substitutions or changes to 
procedures or tests identified as RC will require approval of an AMOC.

Costs of Compliance

    We estimate that this proposed AD affects 70 airplanes of U.S. 
registry.
    We also estimate that it would take about 27 work-hours per product 
to comply with the basic requirements of this proposed AD. The average 
labor rate is $85 per work-hour. Required parts would cost about $2,620 
per product. Based on these figures, we estimate the cost of this 
proposed AD on U.S. operators to be $344,050, or $4,915 per product.
    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):

Airbus: Docket No. FAA-2015-3631; Directorate Identifier 2015-NM-
060-AD.

(a) Comments Due Date

    We must receive comments by November 2, 2015.

(b) Affected ADs

    None.

(c) Applicability

    This AD applies to all the Airbus airplanes identified in 
paragraphs (c)(1), (c)(2), and (c)(3) of this AD, certificated in 
any category, except airplanes on which Airbus Modification 203066, 
Modification 203074, or Modification 203372 has been embodied in 
production.
    (1) Model A330-201, -202, -203, -223, -223F, -243, -243F, -301, 
-302, -303, -321, -322, -323, -341, -342, and -343 airplanes; all 
manufacturer serial numbers (MSNs); if modified in-service as 
specified in Airbus Service Bulletin A330-25-3161, or in production 
with Airbus Modification 50014.
    (2) Model A340-211, -212, -213, -311, -312, and -313 airplanes; 
all MSNs, if modified in-service as specified in Airbus Service 
Bulletin A340-25-4181, or in production with Airbus Modification 
50014.
    (3) Model A340-541 airplanes; and Model A340-642 airplanes; all 
MSNs.

(d) Subject

    Air Transport Association (ATA) of America Code 25, Equipment/
Furnishings.

(e) Reason

    This AD was prompted by reports of chafed wiring at the upper 
left corner of the cockpit door. The affected wire bundle was not 
grounded on the cockpit door frame. We are issuing this AD to 
prevent electrical

[[Page 56407]]

shock injury to persons contacting the cockpit door.

(f) Compliance

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

(g) Door Modification and Installation

    Within 24 months after the effective date of this AD, modify the 
cockpit door frame structure and install bonding-leads to the upper 
cockpit door frame, in accordance with the Accomplishment 
Instructions of the applicable service information identified in 
paragraphs (g)(1), (g)(2), and (g)(3) of this AD.
    (1) Airbus Service Bulletin A330-25-3534, Revision 01, dated 
October 23, 2014. (2) Airbus Service Bulletin A340-25-4349, Revision 
01, dated October 27, 2014. (3) Airbus Service Bulletin A340-25-
5212, Revision 01, dated October 27, 2014.

(h) Cover Plate Modification of the Upper Flight Deck Door

    Except for airplanes on which Airbus Modification 52869 or 
Modification 53292 has been embodied in production: Before or 
concurrently with accomplishing the modification required by 
paragraph (g) of this AD, modify the upper cockpit door plate cover, 
in accordance with the Accomplishment Instructions of the applicable 
service information identified in paragraphs (h)(1), (h)(2), and 
(h)(3) of this AD.
    (1) Airbus Service Bulletin A330-25-3534, Revision 01, dated 
October 23, 2014. (2) Airbus Service Bulletin A340-25-4349, Revision 
01, dated October 27, 2014. (3) Airbus Service Bulletin A340-25-
5212, Revision 01, dated October 27, 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: 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-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 
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 obtaining 
approval of an AMOC, provided the procedures and tests identified as 
RC can be done and the airplane can be put back in a serviceable 
condition. Any substitutions or changes to procedures or tests 
identified as RC require approval of an AMOC.

(j) Related Information

    (1) Refer to Mandatory Continuing Airworthiness Information 
(MCAI) EASA Airworthiness Directive 2015-0037, dated March 2, 2015, 
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-2015-3631.
    (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 September 11, 2015.
Michael Kaszycki,
Acting Manager, Transport Airplane Directorate, Aircraft Certification 
Service.
[FR Doc. 2015-23409 Filed 9-17-15; 8:45 am]
BILLING CODE 4910-13-P