AD 2016-19-02

[Federal Register Volume 81, Number 181 (Monday, September 19, 2016)]
[Rules and Regulations]
[Pages 64051-64053]
From the Federal Register Online via the Government Publishing Office [<a href="http://www.gpo.gov">www.gpo.gov</a>]
[FR Doc No: 2016-22191]



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Federal Register / Vol. 81, No. 181 / Monday, September 19, 2016 / 
Rules and Regulations

[[Page 64051]]



DEPARTMENT OF TRANSPORTATION

Federal Aviation Administration

14 CFR Part 39

[Docket No. FAA-2016-5591; Directorate Identifier 2014-NM-193-AD; 
Amendment 39-18651; AD 2016-19-02]
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 superseding Airworthiness Directive (AD) 2005-15-07 for 
certain Airbus Model A320-111 airplanes and Model A320-200 series 
airplanes. AD 2005-15-07 required installing insulator and cable ties 
to the electrical cables of the S routes at the gaps in the raceway in 
the wing trailing edge and the wing tip and wing root areas. This new 
AD requires additional modifications in the trailing edges of both 
wings. This new AD also removes airplanes from the applicability. This 
AD was prompted by reports of wire chafing in the left-hand wing 
trailing edge. We are issuing this AD to prevent wire chafing in the 
trailing edge of the wings, which could result in a short circuit in 
the vicinity of the fuel tanks, consequently resulting in a potential 
source of ignition in a fuel tank vapor space and consequent fuel tank 
explosion.

DATES: This AD is effective October 24, 2016.
    The Director of the Federal Register approved the incorporation by 
reference of certain publications listed in this AD as of October 24, 
2016.

ADDRESSES: For service information identified in this final rule, 
contact Airbus, Airworthiness Office--EIAS, 1 Rond Point Maurice 
Bellonte, 31707 Blagnac Cedex, France; telephone +33 5 61 93 36 96; fax 
+33 5 61 93 44 51; email <a href="/cdn-cgi/l/email-protection#c7a6a4a4a8b2a9b3e9a6aeb5b0a8b5b3afeaa2a6b487a6aeb5a5b2b4e9a4a8aa"><span class="__cf_email__" data-cfemail="4f2e2c2c203a213b612e263d38203d3b27622a2e3c0f2e263d2d3a3c612c2022">[email&#160;protected]</span></a>; Internet 
<a href="http://www.airbus.com">http://www.airbus.com</a>. 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 <a href="http://www.regulations.gov">http://www.regulations.gov</a> by searching for and locating Docket No. FAA-2016-
5591.

Examining the AD Docket

    You may examine the AD docket on the Internet at <a href="http://www.regulations.gov">http://www.regulations.gov</a> by searching for and locating Docket No. FAA-2016-
5591; 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 address for the Docket Office (telephone 800-
647-5527) is 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 20590.

FOR FURTHER INFORMATION CONTACT: 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.

SUPPLEMENTARY INFORMATION: 

Discussion

    We issued a notice of proposed rulemaking (NPRM) to amend 14 CFR 
part 39 to supersede AD 2005-15-07, Amendment 39-14196 (70 FR 43024, 
July 26, 2005) (``AD 2005-15-07''). AD 2005-15-07 applied to certain 
Airbus Model A320-111 airplanes and Model A320-200 series airplanes. 
The NPRM published in the Federal Register on April 20, 2016 (81 FR 
23199). The NPRM was prompted by reports of wire chafing in the left-
hand wing trailing edge. The NPRM proposed to continue to require 
installing insulator and cable ties to the electrical cables of the S 
routes at the gaps in the raceway in the wing trailing edge and the 
wing tip and wing root areas. The NPRM proposed to require additional 
modifications in the trailing edges of both wings. The NPRM also 
proposed to remove airplanes from the applicability. We are issuing 
this AD to prevent wire chafing in the trailing edge of the wings, 
which could result in a short circuit in the vicinity of the fuel 
tanks, consequently resulting in a potential source of ignition in a 
fuel tank vapor space and consequent fuel tank explosion.
    The European Aviation Safety Agency (EASA), which is the Technical 
Agent for the Member States of the European Union, has issued EASA 
Airworthiness Directive 2014-0198, dated September 5, 2014 (referred to 
after this as the Mandatory Continuing Airworthiness Information, or 
``the MCAI''), to correct an unsafe condition for certain Airbus Model 
A320-211, -212, and -231 airplanes. The MCAI states:

    Prompted by an accident * * *, the FAA published Special Federal 
Aviation Regulation (SFAR) 88 [(66 FR 23086, May 7, 2001)], and the 
Joint Aviation Authorities (JAA) published Interim Policy INT/POL/
25/12.
    Prompted by that regulation, the results of an Airbus review of 
the A320 type design identified, on certain aeroplanes, a possible 
ignition source in fuel tank vapour space(s). That condition, if not 
corrected, could result in a fuel tank explosion and consequent loss 
of the aeroplane.
    It was, therefore, decided to modify the cable routes of the 
wing trailing edge, aft of the rear spar and wing tip of those 
aeroplanes, to be applied in service in accordance with the 
instructions of Airbus Service Bulletin (SB) A320-24-1062 Revision 
05. Following that decision, DGAC France issued AD F-2004-173 (EASA 
approval number 2004-10570) to require that modification.
    After that AD was issued, it was found that additional work, 
introduced by Airbus SB A320-24-1062 Revision 05, was not included 
as part of the normal accomplishment instructions, which meant that 
the additional work might not be accomplished. Consequently, EASA 
issued AD 2008-0051, retaining the requirements of DGAC France AD F-
2004-173 [which corresponds to FAA AD 2005-15-07], which was 
superseded, and required the accomplishment of the additional work 
in accordance with the instructions of Airbus SB A320-24-1062 
Revision 06. EASA AD 2008-0051 was revised to reduce the 
Applicability and to add a clarification to paragraph (2).
    After EASA AD 2008-0051R1 was issued, some operators reported 
wire chafing in the left hand wing trailing edge. Investigation

[[Page 64052]]

established that the wire chafing, initiated at raceway gaps, was 
either due to maintenance action(s), or to structure vibrations.
    Prompted by these findings, Airbus developed two modifications 
to prevent any further wire chafing by introducing an additional 
protection at raceway gaps and a new cable standard in the trailing 
edges of both wings.
    Airbus published SB A320-92-1049 and SB A320-92-1052 to make 
these modifications available for in-service application. At the 
time of incorporation of Airbus SB A320-24-1062, these two 
modifications were considered recommended only.
    EASA recently determined that this condition, if not corrected, 
could lead to a short circuit on 115 volts in the vicinity of fuel 
tanks, consequently creating another risk of ignition source in a 
fuel tank vapour space.
    For the reasons described above, this [EASA] AD retains the 
requirements of EASA AD 2008-0051R1, which is superseded, and 
requires modifications to install the additional anti-chafing 
protection and the new cable standard.

    This AD also removes Model A320-214, -232, and -233 airplanes from 
the applicability because those airplane models have been modified in 
production or in service. This AD also removes Model A320-111 airplanes 
from the applicability because those airplanes are no longer on the 
U.S. type certificate data sheet (there are no more A320-111 airplanes 
in service in the U.S. and none in storage). You may examine the MCAI 
in the AD docket on the Internet at <a href="http://www.regulations.gov">http://www.regulations.gov</a> by 
searching for and locating Docket No. FAA-2016-5591.

Comments

    We gave the public the opportunity to participate in developing 
this AD. We received no comments on the NPRM or on the determination of 
the cost to the public.

Conclusion

    We reviewed the available data and determined that air safety and 
the public interest require adopting this AD as proposed, except for 
minor editorial changes. We have determined that these minor changes:
    <bullet> Are consistent with the intent that was proposed in the 
NPRM for correcting the unsafe condition; and
    <bullet> Do not add any additional burden upon the public than was 
already proposed in the NPRM.

Related Service Information Under 1 CFR Part 51

    We reviewed Airbus Service Bulletins A320-92-1049, Revision 01, 
dated November 28, 2011; A320-92-1052, dated December 5, 2007; and 
A320-24-1062, Revision 07, dated November 28, 2011.
    Airbus Service Bulletin A320-92-1049, Revision 01, dated November 
28, 2011, describes procedures for installing the additional anti-
chafing protection.
    Airbus Service Bulletin A320-92-1052, dated December 5, 2007, 
describes procedures for replacing the current electrical cable with 
the new standard one.
    Airbus Service Bulletin A320-24-1062, Revision 07, dated November 
28, 2011, describes procedures for installing insulator and cable ties 
to the electrical cables of the S routes at the gaps in the raceway in 
the wing trailing edge and the wing tip and wing root areas.
    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.

Costs of Compliance

    We estimate that this AD affects 47 airplanes of U.S. registry.
    The actions required by AD 2005-15-07, and retained in this AD take 
about 35 work-hours per product, at an average labor rate of $85 per 
work-hour. Required parts cost about $0 per product. Based on these 
figures, the estimated cost of the actions that were required by AD 
2005-15-07 is $2,975 per product.
    We also estimate that it would take about 76 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 about $13,000 per 
product. Based on these figures, we estimate the cost of this AD on 
U.S. operators to be $914,620, or $19,460 per product.
    According to the manufacturer, some of the costs of this 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 AD will not have federalism implications 
under Executive Order 13132. This AD will 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 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.

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 removing Airworthiness Directive (AD) 
2005-15-07, Amendment 39-14196 (70 FR 43024, July 26, 2005), and adding 
the following new AD:

2016-19-02 Airbus: Amendment 39-18651; Docket No. FAA-2016-5591; 
Directorate Identifier 2014-NM-193-AD.

(a) Effective Date

    This AD is effective October 24, 2016.

(b) Affected ADs

    This AD replaces AD 2005-15-07, Amendment 39-14196 (70 FR 43024, 
July 26, 2005) (``AD 2005-15-07'').

[[Page 64053]]

(c) Applicability

    This AD applies to Airbus Model A320-211, -212, and -231 
airplanes, certificated in any category, all manufacturer serial 
numbers except those on which Airbus Modification 22626 has been 
embodied in production.

(d) Subject

    Air Transport Association (ATA) of America Code 24, Electrical 
Power; and Code 92.

(e) Reason

    This AD was prompted by reports of wire chafing in the left-hand 
wing trailing edge. We are issuing this AD to prevent wire chafing 
in the trailing edge of the wings, which could result in a short 
circuit in the vicinity of the fuel tanks, consequently resulting in 
a potential source of ignition in a fuel tank vapor space and 
consequent fuel tank explosion.

(f) Compliance

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

(g) Retained Modification, With Revised Service Information

    This paragraph restates the requirements of paragraph (f) of AD 
2005-15-07, with revised service information. Within 60 months after 
August 30, 2005 (the effective date of AD 2005-15-07), install 
insulator and cable ties to the electrical cables of the S routes at 
the gaps in the raceway in the wing trailing edge and the wing tip 
and wing root areas, in accordance with Airbus Service Bulletin 
A320-24-1062, Revision 05, dated June 27, 2002; or the 
Accomplishment Instructions of Airbus Service Bulletin A320-24-1062, 
Revision 07, dated November 28, 2011. As of the effective date of 
this AD, only Airbus Service Bulletin A320-24-1062, Revision 07, 
dated November 28, 2011, may be used.

(h) New Requirement of This AD: Modification of Trailing Edges

    Within 60 months after the effective date of this AD, modify the 
trailing edges of both wings by accomplishing the actions specified 
in paragraphs (h)(1) and (h)(2) of this AD.
    (1) Install the additional anti-chafing protection in accordance 
with the Accomplishment Instructions of Airbus Service Bulletin 
A320-92-1049, Revision 01, dated November 28, 2011.
    (2) Replace the current electrical cable with the new standard 
one in accordance with the Accomplishment Instructions of Airbus 
Service Bulletin A320-92-1052, dated December 5, 2007. During the 
replacement, ensure that the anti-chafing protection specified in 
Airbus Service Bulletin A320-92-1049, Revision 01, dated November 
28, 2011, as required by paragraph (h)(1) of this AD, remains in 
place.

(i) New Additional Modification

    For airplanes on which the installation specified in Airbus 
Service Bulletin A320-24-1062, Revision 05, dated June 27, 2002, has 
been done: Within 60 months after the effective date of this AD, 
install insulators and cable ties, in accordance with 
``Modification--Additional Work (Introduced at Revision No. 06)'' of 
the Accomplishment Instructions of Airbus Service Bulletin A320-24-
1062, Revision 07, dated November 28, 2011.

(j) Credit for Previous Actions

    (1) This paragraph provides credit for actions required by 
paragraphs (g) and (i) of this AD, if those actions were performed 
before the effective date of this AD using Airbus Service Bulletin 
A320-24-1062, Revision 06, dated June 26, 2007, which is not 
incorporated by reference in this AD.
    (2) This paragraph provides credit for actions required by 
paragraph (h) of this AD, if those actions were performed before the 
effective date of this AD using Airbus Service Bulletin A320-92-
1049, dated July 23, 2007, which is not incorporated by reference in 
this AD.

(k) 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: <a href="/cdn-cgi/l/email-protection#9ca5b1ddd2d1b1adadaab1ddd1d3dfb1ced9cdc9d9cfc8cfdcfafdfdb2fbf3ea"><span class="__cf_email__" data-cfemail="2b12066a6566061a1a1d066a66646806796e7a7e6e787f786b4d4a4a054c445d">[email&#160;protected]</span></a>. 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: As of the effective date of 
this AD, for any requirement in this AD to obtain corrective actions 
from a manufacturer, the action must be accomplished using a method 
approved by the Manager, International Branch, ANM-116, Transport 
Airplane Directorate, FAA; or the European Aviation Safety Agency 
(EASA); or Airbus's EASA Design Organization Approval (DOA). If 
approved by the DOA, the approval must include the DOA-authorized 
signature.

(l) Related Information

    (1) Refer to Mandatory Continuing Airworthiness Information 
(MCAI) EASA Airworthiness Directive 2014-0198, dated September 5, 
2014, for related information. This MCAI may be found in the AD 
docket on the Internet at <a href="http://www.regulations.gov">http://www.regulations.gov</a> by searching 
for and locating Docket No. FAA-2016-5591.
    (2) Service information identified in this AD that is not 
incorporated by reference is available at the addresses specified in 
paragraphs (m)(4) and (m)(5) of this AD.

(m) 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.
    (2) You must use this service information as applicable to do 
the actions required by this AD, unless this AD specifies otherwise.
    (3) The following service information was approved for IBR on 
October 24, 2016.
    (i) Airbus Service Bulletin A320-24-1062, Revision 07, dated 
November 28, 2011.
    (ii) Airbus Service Bulletin A320-92-1049, Revision 01, dated 
November 28, 2011.
    (iii) Airbus Service Bulletin A320-92-1052, dated December 5, 
2007. (4) For service information identified in this AD, contact 
Airbus, Airworthiness Office--EIAS, 1 Rond Point Maurice Bellonte, 
31707 Blagnac Cedex, France; telephone +33 5 61 93 36 96; fax +33 5 
61 93 44 51; email <a href="/cdn-cgi/l/email-protection#771614141802190359161e05001805031f5a12160437161e051502045914181a"><span class="__cf_email__" data-cfemail="432220202c362d376d222a31342c31372b6e26223003222a312136306d202c2e">[email&#160;protected]</span></a>; Internet <a href="http://www.airbus.com">http://www.airbus.com</a>.
    (5) 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.
    (6) 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: <a href="http://www.archives.gov/federal-register/cfr/ibr-locations.html">http://www.archives.gov/federal-register/cfr/ibr-locations.html</a>.

    Issued in Renton, Washington, on September 6, 2016.
Michael Kaszycki,
Acting Manager, Transport Airplane Directorate, Aircraft Certification 
Service.
[FR Doc. 2016-22191 Filed 9-16-16; 8:45 am]
 BILLING CODE 4910-13-P