
[Federal Register Volume 81, Number 69 (Monday, April 11, 2016)]
[Rules and Regulations]
[Pages 21236-21240]
From the Federal Register Online via the Government Publishing Office [www.gpo.gov]
[FR Doc No: 2016-07373]


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DEPARTMENT OF TRANSPORTATION

Federal Aviation Administration

14 CFR Part 39

[Docket No. FAA-2014-0775; Directorate Identifier 2014-NM-046-AD; 
Amendment 39-18467; AD 2016-07-22]
RIN 2120-AA64


Airworthiness Directives; Airbus Airplanes

AGENCY: Federal Aviation Administration (FAA), Department of 
Transportation (DOT).

ACTION: Final rule.

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SUMMARY: We are adopting a new airworthiness directive (AD) for all 
Airbus Model A300 B4-600, B4-600R, and F4-600R series airplanes, Model 
A300 C4-605R Variant F airplanes (collectively called Model A300-600 
series airplanes), and Model A310 series airplanes. This AD was 
prompted by reports of insufficient clearance for the electrical wiring 
bundles in the leading and trailing edges of the right-hand (RH) and 
left-hand (LH) wings. This AD requires modifying the electrical routing 
installation at the RH and LH wings. We are issuing this AD to prevent 
insufficient clearance of electrical wiring bundles located in the 
leading and trailing edges of the RH and LH wings, which could lead to 
chafing damage and arcing, possibly resulting in an on-board fire.

DATES: This AD becomes effective May 16, 2016.
    The Director of the Federal Register approved the incorporation by 
reference of certain publications listed in this AD as of May 16, 2016.

ADDRESSES: You may examine the AD docket on the Internet at http://www.regulations.gov/#!docketDetail;D=FAA-2014-0775; or in person at the 
Docket Management Facility, U.S. Department of Transportation, Docket 
Operations, M-30, West Building Ground Floor, Room W12-140, 1200 New 
Jersey Avenue SE., Washington, DC.
    For service information identified in this final rule, 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 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

[[Page 21237]]

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-2014-
0775.

FOR FURTHER INFORMATION CONTACT: Dan Rodina, Aerospace Engineer, 
International Branch, ANM-116, Transport Airplane Directorate, FAA, 
1601 Lind Avenue SW., Renton, WA 98057-3356; telephone (425) 227-2125; 
fax (425) 227-1149.

SUPPLEMENTARY INFORMATION: 

Discussion

    We issued a notice of proposed rulemaking (NPRM) to amend 14 CFR 
part 39 by adding an AD that would apply to all Airbus Model A300 B4-
600, B4-600R, and F4-600R series airplanes and Model A300 C4-605R 
Variant F airplanes (collectively called Model A300-600 series 
airplanes); and Model A310 series airplanes. The NPRM published in the 
Federal Register on November 21, 2014 (79 FR 69377) (``the NPRM'').
    The European Aviation Safety Agency (EASA), which is the Technical 
Agent for the Member States of the European Union, has issued EASA 
Airworthiness Directive 2015-0176, dated August 25, 2015 (referred to 
after this as the Mandatory Continuing Airworthiness Information, or 
``the MCAI''), to correct an unsafe condition for all Airbus Model A300 
B4-600, B4-600R, and F4-600R series airplanes, and Model A300 C4-605R 
Variant F airplanes (collectively called Model A300-600 series 
airplanes); and Model A310 series airplanes. The MCAI states:

    Following publication of FAA SFAR 88 (Special Federal Aviation 
Regulation 88) [http://rgl.faa.gov/Regulatory_and_Guidance_Library%5CrgFAR.nsf/0/EEFB3F94451DC06286256C93004F5E07?OpenDocument), EASA issued AD 2006-
0076 (http://ad.easa.europa.eu/ad/2006-0076] requiring inspection 
and corrective action to improve the explosion risk protection 
system for the left hand (LH) and right hand (RH) wings on A300, 
A300-600, A300-600ST and A310 aeroplanes.
    For A300-600, A300-600ST and A310 aeroplanes, the required 
detailed visual inspections of electrical bundles located in the 
leading and trailing edges of the RH and LH wings and a review of 
the wing electrical installation on the final assembly line have 
shown that the wing electrical installation does not comply with the 
minimum distance inspection criteria to the surrounding structure in 
a few wing locations.
    This condition, if not detected and corrected, could lead to 
damage on the electrical harnesses and on the surrounding structure.
    To address this unsafe condition, Airbus developed an 
improvement of the wing electrical installation to prevent possible 
chafing and subsequent damage to the electrical harnesses and 
surrounding structure.
    Consequently EASA issued AD 2014-0034 [http://www.regulations.gov/#!documentDetail;D=FAA-2014-0775-0002] to 
require installation of new bracket assemblies to ensure the 
clearance between the wiring and the structure, and installation of 
protective split sleeves as mechanical protection to the electrical 
harnesses.
    Since EASA AD 2014-0034 was issued, during embodiment of Airbus 
Service Bulletin (SB) A300-24-6103 Revision 02 on an aeroplane, an 
installation problem was identified, which prompted Airbus to revise 
SB A300-24-9014 Revision 01, and A300-24-6103 Revision 02.
    Service Bulletin Information Transmission (SBIT) 14-0044 
Revision 01 dated 06 February 2015 recommended to postpone 
embodiment of these two SB's, and to wait for the availability of 
Airbus SB A300-24-9014 Revision 02 and A300-24-6103 Revision 03.
    For the reasons described above, this [EASA]AD retains the 
requirement of the EASA AD 2014-0034, which is superseded, and 
requires in addition for the A300-600 and A300-600ST aeroplanes 
only, installation of new bracket assemblies in shroud box (LH and 
RH side) to ensure adequate clearance between wirings and flap track 
carriage (LH and RH side).

    Required actions include modifying the electrical routing 
installation at the RH and LH wings by installing new bracket 
assemblies to ensure adequate clearance between the wiring and the 
structure, and installing protective split sleeves as mechanical 
protection to the electrical harnesses.
    You may examine the MCAI in the AD docket on the Internet at http://www.regulations.gov/#!documentDetail;D=FAA-2014-0775-0002.

Comments

    We gave the public the opportunity to participate in developing 
this AD. The following presents the comments received on the NPRM and 
the FAA's response to each comment.

Requests To Use the Latest Service Information

    FedEx and United Parcel Service (UPS) requested that the NPRM 
reference the latest revision of Airbus Service Bulletin A300-24-6103, 
Revision 02, dated February 7, 2013. UPS stated that Airbus released an 
operators information transmission in October 2014, which stated that 
an operator reported that the installation of the clamps was not 
possible. UPS and FedEx stated that a revised version of the service 
information should be mandated.
    We agree with the commenters' request. Since the NPRM was issued, 
we have reviewed Airbus Service Bulletin A300-24-6103, Revision 03, 
dated July 3, 2015, excluding Appendices 01, 02, 03, and 04, Revision 
03, dated July 3, 2015; and Airbus Service Bulletin A310-24-2105, 
Revision 02, dated January 5, 2015, excluding Appendix 01, Revision 02, 
dated January 5, 2015. Airbus Service Bulletin A300-24-6103, Revision 
03, dated July 3, 2015, excluding Appendices 01, 02, 03, and 04, 
Revision 03, dated July 3, 2015, adds an installation of new bracket 
assemblies in the shroud box (LH and RH sides) to the modification. 
Airbus Service Bulletin A310-24-2105, Revision 02, dated January 5, 
2015, excluding Appendix 01, Revision 02, dated January 5, 2015, only 
includes minor changes to the modification. We have updated paragraphs 
(g) and (h) of this AD accordingly. Similar to the MCAI, credit is not 
given for Airbus Service Bulletin A300-24-6103, Revision 02, dated 
February 7, 2013.

Request To Revise Costs of Compliance Section

    FedEx requested that we revise the Costs of Compliance section of 
the NPRM. FedEx stated that the 37 work-hour estimate is consistent 
with what is specified in Airbus Service Bulletin A300-24-6103, 
Revision 02, dated February 7, 2013. However, FedEx stated that Airbus 
Service Bulletin A310-24-2105, Revision 01, dated December 11, 2013, 
shows an estimate of up to 55.5 work-hours, and does not include 
preparation and set up time. Airbus also stated that, from their 
experience, the work-hours tend to be understated compared to the 
actual time required to accomplish the actions. FedEx commented that it 
believes an estimate of 60 work-hours is more realistic. FedEx stated 
that it must be noted that 102 FedEx-registered airplanes are listed in 
the effectivity section of both service bulletins, and that the overall 
cost assessment omits the fact that over half of the total U.S. fleet 
cost will be borne by a single operator.
    We agree with the commenter's request to revise the estimated costs 
of compliance; however, we have used the cost estimate identified in 
Airbus Service Bulletin A310-24-2105, Revision 02, dated January 5, 
2015, excluding Appendix 01, Revision 02, dated January 5, 2015, which 
does include access and close-up work-hours. We have revised the Costs 
of Compliance section of this final rule to specify up to 56 work-hours 
per product to comply with the basic requirements of this AD.

[[Page 21238]]

Request To Supersede and Revise the Affected ADs Paragraph of the 
Proposed AD

    FedEx requested that AD 2006-22-07, Amendment 39-14800 (71 FR 
62890, October 27, 2006) (``AD 2006-22-07''), be listed as an affected 
AD in the proposed AD, and that the NPRM supersede AD 2006-22-07. FedEx 
stated that the manufacturer has linked the NPRM to AD 2006-22-07.
    FedEx commented that it has complied with the proposed requirements 
of the proposed AD, and all but two airplanes were found to be 
compliant with the clearance requirements specified in the applicable 
service information. FedEx stated that it has contacted the 
manufacturer for an approved method of compliance. FedEx stated that 
Airbus issued an EASA-approved technical adaptation requiring that the 
affected wire bundles be wrapped and a repetitive inspection be 
performed until a permanent fix is available. FedEx stated that the 
permanent fix is ``Airbus Service Bulletin A300-24-6103,'' which was 
specified in the NPRM.
    FedEx commented that the manufacturer has linked the NPRM to AD 
2006-22-07 because Airbus Service Bulletin A300-24-6103 will act as 
terminating action for the requirements of AD 2006-22-07 and the NPRM. 
FedEx also stated that it thinks that all airplanes that comply with AD 
2006-22-07 without requiring additional permanent modifications should 
be exempt from the NPRM.
    We agree that AD 2006-22-07 and this AD are related; however, we 
disagree with the commenter's request to supersede AD 2006-22-07 and 
include that AD as an affected AD in paragraph (b) of this AD. We also 
disagree with the commenter's request to exempt airplanes that comply 
with AD 2006-22-07 from this AD.
    Prior issues of Airbus Service Bulletin A300-24-6103 (issued before 
Revision 03, dated July 3, 2015) are not acceptable for compliance with 
this AD because this AD and AD 2006-22-07 address two different unsafe 
conditions and require different corrective actions. AD 2006-22-07 and 
prior issues of Airbus Service Bulletin A300-24-6103 (issued before 
Revision 03, dated July 3, 2015) do not address insufficient clearance 
of electrical wiring bundles located in the leading and trailing edges 
of the RH and LH wings, which is the unsafe condition identified in 
this final rule. Additional actions are required in Airbus Service 
Bulletin A300-24-6103, Revision 03, dated July 3, 2015, to address the 
unsafe conditions identified by this final rule that were not addressed 
on airplanes modified using previous issues of Airbus Service Bulletin 
A300-24-6103.
    Therefore, this final rule will not supersede AD 2006-22-07. 
Regardless of the findings or corrective actions accomplished in 
accordance with AD 2006-22-07, the service information in this final 
rule must still be required. We have not change this final rule in this 
regard.

Conclusion

    We reviewed the relevant data, considered the comments received, 
and determined that air safety and the public interest require adopting 
this AD with the changes described previously and minor editorial 
changes. We have determined that these minor changes:
     Are consistent with the intent that was proposed in the 
NPRM for correcting the unsafe condition; and
     Do not add any additional burden upon the public than was 
already proposed in the NPRM.
    We also determined that these changes will not increase the 
economic burden on any operator or increase the scope of this AD.

Related Service Information Under 1 CFR Part 51

    Airbus has issued Service Bulletin A300-24-6103, Revision 03, dated 
July 3, 2015, excluding Appendices 01, 02, 03, and 04, Revision 03, 
dated July 3, 2015; and Service Bulletin A310-24-2105, Revision 02, 
dated January 5, 2015, excluding Appendix 01, Revision 02, dated 
January 5, 2015. The service information describes procedures for 
modifying the electrical routing installation at the RH and LH wings. 
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.

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 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 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 will 
require approval of an AMOC.

Costs of Compliance

    We estimate that this AD affects 199 airplanes of U.S. registry.
    We also estimate that it will take about 56 work-hours per product 
to comply with the basic requirements of this AD. The average labor 
rate is $85 per work-hour. Required parts would cost up to $18,000 per 
product. Based on these figures, we estimate the cost of this AD on 
U.S. operators to be $4,529,240, or $22,760 per product.

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 AD will not have federalism implications 
under Executive Order 13132. This AD will not have a substantial direct 
effect on

[[Page 21239]]

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 that this AD:
    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.

Examining the AD Docket

    You may examine the AD docket on the Internet at http://www.regulations.gov/#!docketDetail;D=FAA-2014-0775; 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 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.

List of Subjects in 14 CFR Part 39

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

Adoption of the Amendment

    Accordingly, under the authority delegated to me by the 
Administrator, the FAA amends 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):

2016-07-22 Airbus: Amendment 39-18467. Docket No. FAA-2014-0775; 
Directorate Identifier 2014-NM-046-AD.

(a) Effective Date

    This AD becomes effective May 16, 2016.

(b) Affected ADs

    None.

(c) Applicability

    This AD applies to the airplanes identified in paragraphs (c)(1) 
and (c)(2) of this AD, certificated in any category.
    (1) All Airbus Model A300 B4-601, B4-603, B4-620, and B4-622 
airplanes; Model A300 B4-605R and B4-622R airplanes; Model A300 F4-
605R and F4-622R airplanes; and Model A300 C4-605R Variant F 
airplanes.
    (2) All Airbus Model A310-203, -204, -221, -222, -304, -322, -
324, and -325 airplanes.

(d) Subject

    Air Transport Association (ATA) of America Code 24, Electrical 
Power.

(e) Reason

    This AD was prompted by reports of insufficient clearance for 
the electrical wiring bundles in the leading and trailing edges of 
the right-hand (RH) and left-hand (LH) wings. We are issuing this AD 
to detect and correct insufficient clearance of electrical wiring 
bundles located in the leading and trailing edges of the RH and LH 
wings, which could lead to chafing damage and arcing, possibly 
resulting in an on-board fire.

(f) Compliance

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

(g) Modification

    Within 30 months after the effective date of this AD: Modify the 
electrical routing installation at the RH and LH wings in accordance 
with the Accomplishment Instructions of Airbus Service Bulletin 
A300-24-6103, Revision 03, July 3, 2015, excluding Appendices 01, 
02, 03, and 04, Revision 03, dated July 3, 2015; or Airbus Service 
Bulletin A310-24-2105, Revision 02, dated January 5, 2015, excluding 
Appendix 01, Revision 02, dated January 5, 2015; as applicable; 
except as required by paragraph (h) of this AD.

(h) Exception to Service Information

    If, during any modification required by paragraph (g) of this 
AD: Any gap between the structure and the clamp has insufficient 
clearance, in accordance with the Accomplishment Instructions of 
Airbus Service Bulletin A300-24-6103, Revision 03, July 3, 2015, 
excluding Appendices 01, 02, 03, and 04, Revision 03, dated July 3, 
2015; or Airbus Service Bulletin A310-24-2105, Revision 02, dated 
January 5, 2015, excluding Appendix 01, Revision 02, dated January 
5, 2015; as applicable; before further flight, repair 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).

(i) Credit for Previous Actions

    This paragraph provides credit for the actions required by 
paragraph (g) of this AD, if those actions were performed before the 
effective date of this AD using Airbus Service Bulletin A310-24-
2105, dated March 20, 2013; or Airbus Service Bulletin A310-24-2105, 
Revision 01, dated December 11, 2013.

(j) 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: Dan Rodina, 
Aerospace Engineer, International Branch, ANM-116, Transport 
Airplane Directorate, FAA, 1601 Lind Avenue SW., Renton, WA 98057-
3356; telephone (425) 227-2125; 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 EASA; or 
Airbus's EASA DOA. If approved by the DOA, the approval must include 
the DOA-authorized signature.
    (3) Required for Compliance (RC): Except as required by 
paragraph (h) of this AD: 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 an airworthy condition. Any 
substitutions or changes to procedures or tests identified as RC 
require approval of an AMOC.

(k) Related Information

    (1) Refer to Mandatory Continuing Airworthiness Information 
(MCAI) EASA Airworthiness Directive 2015-0176, dated August 25, 
2015, for related information. This MCAI may be found in the AD 
docket on the Internet at http://www.regulations.gov/#!documentDetail;D=FAA-2014-0775-0002.
    (2) Service information identified in this AD that is not 
incorporated by reference is available at the addresses specified in 
paragraphs (l)(3) and (l)(4) of this AD.

(l) Material Incorporated by Reference

    (1) The Director of the Federal Register approved the 
incorporation by reference (IBR) of the service information listed 
in this paragraph under 5 U.S.C. 552(a) and 1 CFR part 51.

[[Page 21240]]

    (2) You must use this service information as applicable to do 
the actions required by this AD, unless this AD specifies otherwise.
    (i) Airbus Service Bulletin A300-24-6103, Revision 03, dated 
July 3, 2015, excluding Appendices 01, 02, 03, and 04, Revision 03, 
dated July 3, 2015.
    (ii) Airbus Service Bulletin A310-24-2105, Revision 02, dated 
January 5, 2015, excluding Appendix 01, Revision 02, dated January 
5, 2015.
    (3) 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.
    (4) 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.
    (5) You may view this service information that is incorporated 
by reference at the National Archives and Records Administration 
(NARA). For information on the availability of this material at 
NARA, call 202-741-6030, or go to: http://www.archives.gov/federal-register/cfr/ibr-locations.html.

    Issued in Renton, Washington, on March 24, 2016.
Michael Kaszycki,
Acting Manager, Transport Airplane Directorate, Aircraft Certification 
Service.
[FR Doc. 2016-07373 Filed 4-8-16; 8:45 am]
 BILLING CODE 4910-13-P


