AD 2015-03-05

[Federal Register Volume 80, Number 32 (Wednesday, February 18, 2015)]
[Rules and Regulations]
[Pages 8513-8516]
From the Federal Register Online via the Government Publishing Office [<a href="http://www.gpo.gov">www.gpo.gov</a>]
[FR Doc No: 2015-02697]


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DEPARTMENT OF TRANSPORTATION

Federal Aviation Administration

14 CFR Part 39

[Docket No. FAA-2014-0484; Directorate Identifier 2013-NM-245-AD; 
Amendment 39-18101; AD 2015-03-05]
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) 2012-09-07 for 
certain Airbus Model A319-111, -112, and -132 airplanes; Model A320-
111, -211, -212, -214, and -232 airplanes; and Model A321-111, -211, -
212, and -231 airplanes. AD 2012-09-07 required an electrical bonding 
test between the gravity fill re-fuel adaptor and the top skin panels 
on the wings; and, if necessary, an inspection for corrosion of the 
component interface and adjacent area; and repairing the gravity fuel 
adaptor if necessary. This new AD adds airplanes to the applicability 
and requires inspecting those airplanes to determine if a repair was 
done, and doing the electrical bonding test and corrective action if 
necessary. This AD was prompted by a determination that more airplanes 
are

[[Page 8514]]

subject to the identified unsafe condition. We are issuing this AD to 
detect and correct corrosion and improper bonding, which, in 
combination with a lightning strike in this area, could create a source 
of ignition in a fuel tank, resulting in a fire or explosion and 
consequent loss of the airplane.

DATES: This AD becomes effective March 25, 2015.
    The Director of the Federal Register approved the incorporation by 
reference of a certain publication listed in this AD as of March 25, 
2015.

ADDRESSES: You may examine the AD docket on the Internet at <a href="http://www.regulations.gov/#!docketDetail">http://www.regulations.gov/#!docketDetail</a>;D=FAA-2014-0484; 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 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#741517171b011a005a151d06031b06001c5911150734151d061601075a171b19"><span class="__cf_email__" data-cfemail="dabbb9b9b5afb4aef4bbb3a8adb5a8aeb2f7bfbba99abbb3a8b8afa9f4b9b5b7">[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-2014-
0484.

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 2012-09-07, Amendment 39-17042 (77 FR 28238, 
May 14, 2012). AD 2012-09-07 applied to certain Airbus Model A319-111, 
-112, and -132 airplanes; Model A320-111, -211, -212, -214, and -232 
airplanes; and Model A321-111, -211, -212, and -231 airplanes. The NPRM 
published in the Federal Register on July 30, 2014 (79 FR 44144).
    The European Aviation Safety Agency (EASA), which is the Technical 
Agent for the Member States of the European Union, has issued EASA 
Airworthiness Directive 2013-0277R1, dated December 4, 2013 (referred 
to after this as the Mandatory Continuing Airworthiness Information, or 
``the MCAI''), to correct an unsafe condition for all Airbus Model 
A318-111, -112, -121, and -122 airplanes; Model A319-111, -112, -113, -
114, -115, -131, -132, and -133 airplanes; Model A320-111, -211, -212, 
-214, -231, -232, and -233 airplanes; and Model A321-111, -112, -131, -
211, -212, -213, -231, and -232 airplanes. The MCAI states:

    Cases of corrosion findings were reported on the overwing 
refueling aperture (used to fill the fuel tank by gravity) on the 
wing top skin. The reported corrosion was on the mating surface of 
the aperture flange, underneath the refuel adaptor. Corrosion 
findings have been repaired on a case by case basis in accordance 
with approved data.
    For certain aeroplanes, the repair provided by Airbus contained 
instructions to apply primer coating on the mating surface. Since 
doing those repairs, it has been found that this primer coating may 
prevent proper electrical bonding provision between the overwing 
refueling cap adaptor and the wing skin.
    This condition, if not detected and corrected, could, in 
combination with a lightning strike in this area, create a source of 
ignition in a fuel tank, possibly resulting in a fire or explosion 
and consequent loss of the aeroplane.
    To address this potential unsafe condition, EASA issued AD 2011-
0034 [<a href="http://ad.easa.europa.eu/blob/easa_ad_2011_0034.pdf/AD_2011-0034">http://ad.easa.europa.eu/blob/easa_ad_2011_0034.pdf/AD_2011-0034</a>] to require a one-time electrical bonding check between the 
gravity fill re-fuel adaptor and the top skin panels on the affected 
aeroplanes (identified by MSN [manufacturer serial number] in the 
applicability section of that [EASA] AD) and, in case of findings, 
the accomplishment of applicable corrective actions.
    Since that [EASA] AD was issued, EASA has been made aware that 
some operators may inadvertently have applied an Airbus repair, 
approved for only one aeroplane MSN, to other aeroplanes, without 
requesting a revision of the repair to add aeroplanes, or to notify 
Airbus of such action(s). Consequently, the condition addressed by 
EASA AD 2011-0034 could affect more aeroplanes than initially 
determined.
    For the reasons described above, this [EASA] AD retains the 
requirements of EASA AD 2011-0034, which is superseded, and expands 
the Applicability to all A320 family aeroplane Models, all MSN.
    This [EASA] AD has been revised to amend and clarify paragraph 
(3), and to correct an error in the Type/Model designations on page 
1, where the A318 was inadvertently omitted.

For the newly added airplanes, required actions include inspecting for 
the presence of a corrosion repair on an overwing refueling aperture, 
and doing the electrical bonding test and applicable corrective actions 
if a repair has been installed. You may examine the MCAI in the AD 
docket on the Internet at <a href="http://www.regulations.gov/#!documentDetail">http://www.regulations.gov/#!documentDetail</a>;D=FAA-2014-0484-0002.

Comments

    We gave the public the opportunity to participate in developing 
this AD. The following presents the comment received on the NPRM (79 FR 
44144, July 30, 2014) and the FAA's response to the comment.

Request To Include Revised Service Information

    United Airlines (UAL) asked that we include a statement in the NPRM 
(79 FR 44144, July 30, 2014), which allows performing the required 
actions in accordance with the instructions of Airbus Service Bulletin 
A320-57-1152, Revision 01, dated December 19, 2013. UAL stated that the 
revised service information specifies the same method of inspection as 
specified in Airbus Service Bulletin A320-57-1152, dated June 14, 2010. 
UAL further stated that Revision 01 of this service bulletin also 
provides operators with updated repair instructions that were not 
available in the original issue of this service bulletin.
    We agree with the commenter's request. Since issuance of the NPRM 
(79 FR 44144, July 30, 2014), Airbus has issued Service Bulletin A320-
57-1152, Revision 01, dated December 19, 2013. This revision states 
that no additional work is necessary on airplanes changed in accordance 
with Airbus Service Bulletin A320-57-1152, dated June 14, 2010, which 
was specified as the appropriate source of service information in the 
NPRM (79 FR 44144, July 30, 2014).
    We have changed paragraph (g) of this AD to specify Airbus Service 
Bulletin A320-57-1152, Revision 01, dated December 19, 2013. We have 
also added a new paragraph (h) to this AD to give credit for actions 
done before the effective date of this AD using Airbus Service Bulletin 
A320-57-1152, dated June 14, 2010, and redesignated subsequent 
paragraphs accordingly.

Conclusion

    We reviewed the relevant data 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:
    <bullet> Are consistent with the intent that was proposed in the 
NPRM (79 FR 44144, July 30, 2014) for correcting the unsafe condition; 
and
    <bullet> Do not add any additional burden upon the public than was 
already

[[Page 8515]]

proposed in the NPRM (79 FR 44144, July 30, 2014).
    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 A320-57-1152, Revision 01, dated 
December 19, 2013. The service information describes procedures for 
inspecting certain airplanes to determine if a repair was done, and 
doing an electrical bonding test and corrective action if necessary. 
This service information is reasonably available; see ADDRESSES for 
ways to access this service information.

Costs of Compliance

    We estimate that this AD affects 851 airplanes of U.S. registry.
    The actions required by AD 2012-09-07, Amendment 39-17042 (77 FR 
28238, May 14, 2012), and retained in this AD take about 2 work-hours 
per product, at an average labor rate of $85 per work-hour. Based on 
these figures, the estimated cost of the actions that were required by 
AD 2012-09-07 is $170 per product.
    We also estimate that it takes about 2 work-hours per product to 
comply with the basic requirements of this AD. The average labor rate 
is $85 per work-hour. Required parts cost about $0 per product. Based 
on these figures, we estimate the cost of this AD on U.S. operators to 
be $144,670, or $170 per product.
    In addition, we estimate that any necessary follow-on actions will 
take about 11 work-hours, for a cost of $935 per product. We have no 
way of determining the number of aircraft that might need these 
actions.

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.

Examining the AD Docket

    You may examine the AD docket on the Internet at <a href="http://www.regulations.gov/#!docketDetail">http://www.regulations.gov/#!docketDetail</a>;D=FAA-2014-0484; 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 removing Airworthiness Directive (AD) 
2012-09-07, Amendment 39-17042 (77 FR 28238, May 14, 2012), and adding 
the following new AD:

2015-03-05 Airbus: Amendment 39-18101. Docket No. FAA-2014-0484; 
Directorate Identifier 2013-NM-245-AD.

(a) Effective Date

    This AD becomes effective March 25, 2015.

(b) Affected ADs

    This AD replaces AD 2012-09-07, Amendment 39-17042 (77 FR 28238, 
May 14, 2012).

(c) Applicability

    (1) This AD applies to Airbus Model A318-111, -112, -121, and -
122 airplanes; Model A319-111, -112, -113, -114, -115, -131, -132, 
and -133 airplanes; Model A320-111, -211, -212, -214, -231, -232, 
and -233 airplanes; and Model A321-111, -112, -131, -211, -212, -
213, -231, and -232 airplanes; certificated in any category; all 
manufacturer serial numbers, except airplanes identified in 
paragraph (c)(2) of this AD.
    (2) Airplanes that have been delivered from production with 
Airbus Modification 38209 (Removal of the Outer Wing Refueling 
Aperture) incorporated, and without Airbus Modification 38206 (Re-
introduction of the Outer Wing Refueling Aperture) incorporated, are 
not affected by the requirements of this AD.

(d) Subject

    Air Transport Association (ATA) of America Code 57, Wings.

(e) Reason

    This AD was prompted by a determination that more airplanes are 
subject to the identified unsafe condition. We are issuing this AD 
to detect and correct corrosion and improper bonding, which, in 
combination with a lightning strike in this area, could create a 
source of ignition in a fuel tank, resulting in a fire or explosion 
and consequent loss of the airplane.

(f) Compliance

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

(g) Retained Electrical Bonding Test, and General Visual Inspection if 
Necessary, With Changes

    This paragraph restates the requirements of paragraph (g) of AD 
2012-09-07, Amendment 39-17042 (77 FR 28238, May 14, 2012), with 
revised repair approval language and revised service information. 
For Model A319-111, -112, and -132 airplanes; Model A320-111, -211, 
-212, -214 and -232 airplanes; and Model A321-111, -211, -212, and -
231 airplanes; certificated in any category; having manufacturer 
serial numbers 0039, 0078, 0109, 0118, 0120, 0153, 0174, 0187, 0203, 
0215, 0218, 0226, 0227, 0228, 0236, 0237, 0269, 0270, 0278, 0285, 
0286, 0287, 0288, 0294, 0301, 0337, 0377, 0462, 0463, 0464, 0465, 
0520, 0523, 0528, 0876, 0888, 0921, 0935, 0974, 1014, 1102, 1130, 
1160, 1162, 1177, 1215, 1250, 1287, 1336, 1388, 1404, 1444, 1449, 
1476, 1505, 1524, 1564, 1605, 1616, 1622, 1640, 1645, 1658, 1677, 
1691, 1729, and 1905: Within 24 months after June 18, 2012 (the 
effective date of AD 2012-09-07), do an electrical bonding

[[Page 8516]]

test to check for bonding between the re-fuel adaptor of the gravity 
fill and the top skin panels on the left-hand and right-hand wings, 
in accordance with the Accomplishment Instructions of Airbus Service 
Bulletin A320-57-1152, Revision 01, dated December 19, 2013.
    (1) If the resistance value is 10 milliohms or less at the left-
hand and right-hand wing, no further action is required by this 
paragraph.
    (2) If the resistance value is greater than 10 milliohms at the 
left-hand or right-hand wing, before further flight, do a general 
visual inspection for corrosion of the component interface and 
adjacent area, in accordance with the Accomplishment Instructions of 
Airbus Service Bulletin A320-57-1152, Revision 01, dated December 
19, 2013. If any corrosion is found during the inspection, before 
further flight, repair the gravity fill fuel adaptor, in accordance 
with the Accomplishment Instructions of Airbus Service Bulletin 
A320-57-1152, Revision 01, dated December 19, 2013; except where 
Airbus Service Bulletin A320-57-1152, Revision 01, dated December 
19, 2013, specifies to contact Airbus, 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). If approved by the DOA, the approval must include the DOA-
authorized signature.

(h) Credit for Previous Actions

    This paragraph provides credit for the actions specified in 
paragraph (g) of this AD, if those actions were performed before the 
effective date of this AD using Airbus Service Bulletin A320-57-
1152, dated June 14, 2010, which was incorporated by reference in AD 
2012-09-07, Amendment 39-17042 (77 FR 28238, May 14, 2012).

(i) New Requirement of This AD: Maintenance Check/Electrical Bonding 
Test and Corrective Action if Necessary

    For airplanes other than those identified in paragraph (g) of 
this AD: Within 24 months after the effective date of this AD, 
determine whether a corrosion repair has been done on an overwing 
refueling aperture, whereby a primer coating has been applied on the 
mating surface of the aperture flange. A review of the airplane 
maintenance records is acceptable to make this determination, 
provided that whether a primer coat was applied can be conclusively 
determined from that review.
    (1) If it is determined that a primer coating was applied on the 
mating surface of the aperture flange; or if a determination cannot 
be made, or the outcome is inconclusive: Within 24 months after the 
effective date of this AD do the electrical bonding test specified 
in paragraph (g) of this AD, and before further flight, do all 
applicable actions specified in paragraph (g)(2) of this AD.
    (2) If it is determined that a corrosion repair has not been 
done, and a primer coating has not been applied on the mating 
surface of the aperture flange since first entry into service, no 
further action is required by this paragraph.

(j) Corrosion Repair Provision

    As of the effective date of this AD, any corrosion repair done 
on an overwing refueling aperture on any airplane must comply with 
the repair requirements of paragraph (g)(2) of 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#754c58343b38584444435834383a36582730242030262126351314145b121a03"><span class="__cf_email__" data-cfemail="754c58343b38584444435834383a36582730242030262126351314145b121a03">[email&#160;protected]</span></a>.
    (i) Before using any approved AMOC, notify your appropriate 
principal inspector, or lacking a principal inspector, the manager 
of the local flight standards district office/certificate holding 
district office. The AMOC approval letter must specifically 
reference this AD.
    (ii) AMOCs approved previously for AD 2012-09-07, Amendment 39-
17042 (77 FR 28238, May 14, 2012), are approved as AMOCs for the 
corresponding provisions of this AD.
    (2) Contacting the Manufacturer: As of the effective date of 
this AD, for any requirement in this AD to obtain corrective actions 
from a manufacturer, the action must be accomplished using a method 
approved by the Manager, International Branch, ANM-116, Transport 
Airplane Directorate, FAA; or EASA; or Airbus's EASA 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 2013-0277R1, dated December 4, 
2013, for related information. This MCAI may be found in the AD 
docket on the Internet at <a href="http://www.regulations.gov/#!documentDetail">http://www.regulations.gov/#!documentDetail</a>;D=FAA-2014-0484-0002.
    (2) Service information identified in this AD that is not 
incorporated by reference in this AD 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.
    (i) Airbus Service Bulletin A320-57-1152, Revision 01, dated 
December 19, 2013.
    (ii) Reserved.
    (3) 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#b7d6d4d4d8c2d9c399d6dec5c0d8c5c3df9ad2d6c4f7d6dec5d5c2c499d4d8da"><span class="__cf_email__" data-cfemail="472624242832293369262e35302835332f6a22263407262e352532346924282a">[email&#160;protected]</span></a>; Internet <a href="http://www.airbus.com">http://www.airbus.com</a>.
    (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: <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 February 4, 2015.
Dionne Palermo,
Acting Manager, Transport Airplane Directorate, Aircraft Certification 
Service.
[FR Doc. 2015-02697 Filed 2-17-15; 8:45 am]
BILLING CODE 4910-13-P