[Federal Register Volume 80, Number 40 (Monday, March 2, 2015)]
[Rules and Regulations]
[Pages 11101-11106]
From the Federal Register Online via the Government Publishing Office [www.gpo.gov]
[FR Doc No: 2015-02676]


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DEPARTMENT OF TRANSPORTATION

Federal Aviation Administration

14 CFR Part 39

[Docket No. FAA-2014-0189; Directorate Identifier 2013-NM-181-AD; 
Amendment 39-18099; AD 2015-03-03]
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 certain 
Airbus Model A300 series airplanes, 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). This AD was 
prompted by a report of chafing found on the overflow sensor harness of 
the surge tank, and subsequent contact between the electrical wiring 
and fuel tank structure. This AD requires a one-time inspection for 
chafing of the overflow sensor harness, and repair if necessary. This 
AD also requires modification of the sensor harness. We are issuing 
this AD to prevent chafing of the harness and subsequent contact 
between the electrical wiring and fuel tank structure, which could 
result in electrical arcing and a fuel tank explosion and consequent 
loss of the airplane.

DATES: This AD becomes effective April 6, 2015.
    The Director of the Federal Register approved the incorporation by 
reference of certain publications listed in this AD as of April 6, 
2015.

ADDRESSES: You may examine the AD docket on the Internet at http://www.regulations.gov/#!docketDetail;D=FAA-2014-0189 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--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 <a href="/cdn-cgi/l/email-protection#96f7f5f5f9e3f8e2b8f7ffe4e1f9e4e2febbf3f7e5d6f7ffe4f4e3e5b8f5f9fb"><span class="__cf_email__" data-cfemail="a3c2c0c0ccd6cdd78dc2cad1d4ccd1d7cb8ec6c2d0e3c2cad1c1d6d08dc0ccce">[email protected]</span></a>; Internet http://www.airbus.com. 
You may view this referenced service information at the FAA, Transport 
Airplane Directorate, 1601 Lind Avenue SW., Renton, WA.

[[Page 11102]]

For information on the availability of this material at the FAA, call 
425-227-1221. It is also available on the Internet at http://www.regulations.gov by searching for and locating Docket No. FAA-2014-
0189.

FOR FURTHER INFORMATION CONTACT: Dan Rodina, Aerospace Engineer, 
International Branch, ANM-116, Transport Airplane Directorate, FAA, 
1601 Lind Avenue SW., Renton, WA 98057-3356; phone: 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 
series airplanes, 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). The NPRM published in the 
Federal Register on April 8, 2014 (79 FR 19296).
    The European Aviation Safety Agency (EASA), which is the Technical 
Agent for the Member States of the European Union, has issued EASA 
Airworthiness Directive 2013-0193, dated August 23, 2013 (referred to 
after this as the Mandatory Continuing Airworthiness Information, or 
``the MCAI''), to correct an unsafe condition for all Airbus Model A300 
series airplanes, 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). The MCAI states:

    During a scheduled maintenance check on an A300 aeroplane, 
chafing was found on the surge tank overflow sensor harness. The 
harness was found to contact the Magnetic Fuel Level Indicator 
(MFLI) canister.
    Prompted by these findings, DGAC [Direction 
G[eacute]n[eacute]rale de l'Aviation Civile] France issued [(http://ad.easa.europa.eu/blob/easa_ad_1999_404_293.pdf/AD_1999-404-293)] to 
require modification of the harness routing in accordance with the 
instructions of Airbus SB [service bulletin] A300-28-0058 or SB 
A300-28-6020, as applicable to aeroplane model.
    Since that [DGAC] AD was issued, maintenance work on modified 
A300-600 aeroplanes revealed some chafing of the harness, creating a 
potential contact between the electrical wire and fuel tank 
structure. Investigations have shown that although measures were 
taken to prevent contact of the harness with the MFLI (through 
modification 04489), the installation can be subject to human error. 
As the MFLI is integral to the access panel in this location, any 
potential contact with the harness (as a result of incorrect 
installation) is hidden.
    This condition, if not detected and corrected, could lead to 
electrical arcing, possibly resulting in a fuel tank explosion and 
loss of the aeroplane. To address this potential unsafe condition, 
Airbus issued SB A300-28-0091 for A300 aeroplanes, SB A300-28-6109 
for A300-600 aeroplanes, and A300-28-9022 for A300-600ST aeroplanes.
    For the reasons described above, this [EASA] AD requires a one-
time inspection of the harness and, depending on findings, 
corrective actions, as well as replacement of angle brackets by 
error-proof harness brackets.

    You may examine the MCAI in the AD docket on the Internet at http://www.regulations.gov/#!documentDetail;D=FAA-2014-0189-0002.

Comments

    We gave the public the opportunity to participate in developing 
this AD. The following presents the comments received on the NPRM (79 
FR 19296, April 8, 2014) and the FAA's response to each comment.

Request To Remove AD Reference in Repair Approvals

    United Parcel Service (UPS) asked that we remove the requirement to 
include the AD reference in repair approvals, as specified in paragraph 
(g)(1) of the proposed AD (79 FR 19296, April 8, 2014), which states 
``For a repair to be approved, the repair must specifically refer to 
this AD.'' UPS stated the following: ``The proposed wording, being 
specific to repairs, eliminates the interpretation that Airbus messages 
are acceptable for approving minor deviations (corrective actions) 
needed during accomplishment of a mandated Airbus service bulletin.'' 
UPS added that this will result in an increase in alternative method of 
compliance (AMOC) requests.
    We agree with the commenter's request to remove the requirement 
that repair approvals specifically refer to this AD, from this AD.
    Since late 2006, we have included a standard paragraph titled 
``Airworthy Product'' in all MCAI ADs in which the FAA develops an AD 
based on a foreign authority's AD. The MCAI or referenced service 
information in an FAA AD often directs the owner/operator to contact 
the manufacturer for corrective actions, such as a repair. Briefly, the 
Airworthy Product paragraph allowed owners/operators to use corrective 
actions provided by the manufacturer if those actions were FAA-
approved. In addition, the paragraph stated that any actions approved 
by the State of Design Authority (or its delegated agent) are 
considered to be FAA-approved.
    In the NPRM (79 FR 19296, April 8, 2014), we proposed to prevent 
the use of repairs that were not specifically developed to correct the 
unsafe condition, by requiring that the repair approval provided by the 
State of Design Authority or its delegated agent specifically refer to 
this FAA AD. This change was intended to clarify the method of 
compliance and to provide operators with better visibility of repairs 
that are specifically developed and approved to correct the unsafe 
condition. In addition, we proposed to change the phrase ``its 
delegated agent'' to include ``the Design Approval Holder (DAH) with a 
State of Design Authority's design organization approval (DOA)'' to 
refer to a DAH authorized to approve required repairs for the AD.
    As stated previously, UPS commented that: ``The proposed wording, 
being specific to repairs, eliminates the interpretation that Airbus 
messages are acceptable for approving minor deviations (corrective 
actions) needed during accomplishment of an AD mandated Airbus service 
bulletin.'' This comment has made the FAA aware that some operators 
have misunderstood or misinterpreted the Airworthy Product paragraph to 
allow the owner/operator to use messages provided by the manufacturer 
as approval of deviations during the accomplishment of an AD-mandated 
action. The Airworthy Product paragraph does not approve messages or 
other information provided by the manufacturer for deviations to the 
requirements of the AD-mandated actions. The Airworthy Product 
paragraph only addresses the requirement to contact the manufacturer 
for corrective actions for the identified unsafe condition and does not 
cover deviations from other AD requirements. However, deviations to AD-
required actions are addressed in 14 CFR 39.17, and anyone may request 
the approval for an alternative method of compliance to the AD-required 
actions using the procedures found in 14 CFR 39.19.
    To address this misunderstanding and misinterpretation of the 
Airworthy Product paragraph, we have changed that paragraph and 
retitled it ``Contacting the Manufacturer.'' This paragraph now 
clarifies that for any requirement in this AD to obtain corrective 
actions from a manufacturer, the actions must be accomplished using a 
method approved by the FAA, EASA, or Airbus's EASA DOA.
    The Contacting the Manufacturer paragraph also clarifies that, if 
approved by the DOA, the approval must include the DOA-authorized 
signature. The DOA signature indicates that the data and information 
contained in the document are EASA-approved, which is also FAA-
approved. Messages and other information provided by the

[[Page 11103]]

manufacturer, that do not contain the DOA-authorized signature approval 
are not EASA-approved, unless EASA directly approves the manufacturer's 
message or other information.
    This clarification does not remove flexibility previously afforded 
by the Airworthy Product paragraph. Consistent with long-standing FAA 
policy, such flexibility was never intended for required actions. This 
is also consistent with the recommendation of the Airworthiness 
Directive Implementation Aviation Rulemaking Committee to increase 
flexibility in complying with ADs by identifying those actions in 
manufacturers' service instructions that are ``Required for 
Compliance'' with ADs. We continue to work with manufacturers to 
implement this recommendation. But once we determine that an action is 
required, any deviation from the requirement must be approved as an 
AMOC.
    Commenters to an NPRM having Directorate Identifier 2012-NM-101-AD 
(78 FR 78285, December 26, 2013) pointed out that in many cases the 
foreign manufacturer's service bulletin and the foreign authority's 
MCAI may have been issued some time before the FAA AD. Therefore, the 
DOA may have provided U.S. operators with an approved repair, developed 
with full awareness of the unsafe condition, before the FAA AD is 
issued. Under these circumstances, to comply with the FAA AD, the 
operator would be required to go back to the manufacturer's DOA and 
obtain a new approval document, adding time and expense to the 
compliance process with no safety benefit.
    Based on these comments, we removed the requirement from this AD 
that the DAH-provided repair specifically refer to this AD. Before 
adopting such a requirement in the future, the FAA will coordinate with 
affected DAHs and verify they are prepared to implement means to ensure 
that their repair approvals consider the unsafe condition addressed in 
an AD. Any such requirements will be adopted through the normal AD 
rulemaking process, including notice-and-comment procedures, when 
appropriate.
    We also have decided not to include a generic reference to either 
the ``delegated agent'' or the ``DAH with State of Design Authority 
design organization approval,'' but instead we have provided the 
specific delegation approval granted by the State of Design Authority 
for the DAH.

Request To Extend the Compliance Time

    UPS asked that we extend the compliance time specified in paragraph 
(g) of the proposed AD (79 FR 19296, April 8, 2014) from 30 to 36 
months. UPS stated that it expects to accomplish the inspection during 
its existing C-check interval, which is 30 months. UPS added that in 
order to perform the inspection and repair at its major maintenance 
facility during C-checks, it requires an additional 6 months to allow 
for planning, preparation, and prototyping of the service information. 
UPS noted that this additional time is for the prototyping effort 
necessary when a project is initiated; UPS has determined that service 
information is often revised during accomplishment of the required 
actions, which makes it difficult to maintain regular maintenance 
schedules. Therefore, UPS must schedule special visit check lines for 
accomplishing the actions.
    We do not agree with the commenter's request to extend the 
compliance time. In developing an appropriate compliance time for this 
action, we considered the safety implications, parts availability, and 
normal maintenance schedules for the timely accomplishment of the 
inspection and subsequent modification. In consideration of these 
items, as well as the possibility of chafing of the overflow sensor 
harness, we have determined that a 30-month compliance time will ensure 
an acceptable level of safety and allow the modification to be done 
during scheduled maintenance intervals for most affected operators. 
However, under the provisions of paragraph (j)(1) of this AD, we will 
consider requests for approval of an extension of the compliance time 
if sufficient data are submitted to substantiate that the new 
compliance time would provide an acceptable level of safety. We have 
not changed this AD in this regard.

Request To Include Another Source of Service Information

    FedEx Express asked that we allow the use of UTC Aerospace Systems 
Service Bulletin V-1577 for accomplishing the actions in the NPRM (79 
FR 19296, April 8, 2014). FedEx Express stated that it operates 71 
Airbus Model A300-600 series airplanes, and 65 of those airplanes have 
had the in-tank fuel quantity system modified by a certain supplemental 
type certificate (STC), which means Airbus Service Bulletin A300-28-
6109, Revision 01, dated December 20, 2013 (referred to as the 
appropriate source of service information for accomplishing the 
actions), cannot be used to accomplish the proposed actions. However, 
FedEx Express noted that six of its airplanes have the production in-
tank fuel quantity system installed, and the referenced service 
information can be used for those airplanes. FedEx Express stated that 
the UTC Aerospace Systems service bulletin has not been issued yet; 
however, after issuance it should be included in the NPRM as a source 
of service information for accomplishing the proposed actions in order 
to mitigate the unsafe condition.
    We partially agree with the commenter. We agree that airplanes that 
have had the in-tank fuel quantity system modified by STC ST00092BO 
(http://rgl.faa.gov/Regulatory_and_Guidance_Library/rgstc.nsf/0/D41C5AE8E46B4901862574900069E004?OpenDocument&Highlight=st00092bo) 
cannot accomplish the actions proposed in the NPRM (79 FR 19296, April 
8, 2014) by using Airbus Service Bulletin A300-28-6109, Revision 01, 
dated December 20, 2013. Since the issuance of the NPRM, UTC Aerospace 
Systems has issued service bulletin 300723-28-03 (V-1577), dated 
October 10, 2014, to address the unsafe condition for airplanes that 
have been modified by supplemental type certificate ST00092BO.
    We do not agree to revise this AD to require UTC Aerospace Systems 
Service Bulletin 300723-28-03 (V-1577), dated October 10, 2014. 
Instead, we are considering separate rulemaking to require the 
procedures and compliance time specified in UTC Aerospace Systems 
Service Bulletin 300723-28-03 (V-1577), dated October 10, 2014, for 
airplanes modified by STC ST00092BO. Therefore, we have revised 
paragraph (c) of this AD by removing airplanes modified by STC 
ST00092BO from the applicability of this AD.

Request To Include Revised Service Information

    FedEx Express asked that Revision 02 of Airbus Service Bulletin 
A300-28-6109 be included for accomplishing the actions in the NPRM (79 
FR 19296, April 8, 2014) before the final rule is issued. FedEx Express 
stated that it reviewed Airbus Service Bulletin A300-28-6109, Revision 
01, dated December 20, 2013, and submitted its findings to Airbus for 
incorporation into upcoming Revision 02 before issuance. FedEx Express 
added that its intent in doing so was to prevent future requests for 
AMOCs to the FAA.
    We disagree with the commenter's request to include Revision 02 of 
Airbus Service Bulletin A300-28-6109. We are aware that Airbus is 
considering

[[Page 11104]]

revising Airbus Service Bulletin A300-28-6109, Revision 01, dated 
December 20, 2013, to incorporate feedback received from FedEx Express 
in the Accomplishment Instructions of the service bulletin. We will 
consider approving Revision 02 of Airbus Service Bulletin A300-28-6109 
as an AMOC to the actions specified in paragraphs (g) and (h) of this 
AD, once this service bulletin is released. However, we find that 
delaying this AD action would be inappropriate in light of the urgency 
of the identified unsafe condition. Therefore, no change has been made 
to this AD in this regard.

Request To Clarify the ``Required for Compliance'' Instructions

    FedEx Express asked for clarification as to whether the Required 
for Compliance (RC) note identified in the Accomplishment Instructions 
of Airbus Service Bulletin A300-28-6109, Revision 01, dated December 
20, 2013, is applicable to the actions specified in the NPRM (79 FR 
19296, April 8, 2014) and EASA Airworthiness Directive 2013-0193, dated 
August 23, 2013.
    We acknowledge the commenter's concern and provide the following 
clarification:
    The FAA worked in conjunction with industry, under the 
Airworthiness Directives Implementation Aviation Rulemaking Committee 
(ARC), to enhance the AD system. One enhancement is a new process for 
annotating which steps in the service information are ``required for 
compliance'' with an AD. Differentiating these steps from other tasks 
in the service information is expected to improve an owner's and 
operator's understanding of AD requirements and help provide consistent 
judgment in AD compliance. In response to the AD Implementation ARC, 
the FAA released AC 20-176, Revision A, dated June 16, 2014, (http://
rgl.avs.faa.gov/Regulatory_and_Guidance_Library/rgAdvisoryCircular.nsf/
0/a78cc91a47b192278625796b0075f419/$FILE/AC%2020-176.pdf); and Order 
8110.117 (http://rgl.avs.faa.gov/Regulatory_and_Guidance_Library/
rgOrders.nsf/0/984bb9eb07cdd86986257a7f0070744c/$FILE/
Order%208110.117.pdf), which include the concept of RC. The FAA has 
begun implementing this concept in ADs when we receive service 
information containing RC steps. Therefore, the RC note does apply to 
the actions required by this AD when using Airbus Service Bulletin 
A300-28-6109, Revision 01, dated December 20, 2013, to accomplish the 
required actions. We do not have information concerning how EASA 
implements the RC concept in its ADs.
    We split paragraph (j)(1) and redesignated the content as 
paragraphs (j)(1) and (j)(1)(i) of this AD, and added paragraph 
(j)(1)(ii) to this AD to reflect information concerning the RC concept 
and to explain when it is necessary to request approval of an AMOC.

Clarification of Inspection Type

    Paragraph (g) of this AD has been revised to clarify the inspection 
type as a one-time general visual inspection.

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 changes:
    <bullet> Are consistent with the intent that was proposed in the 
NPRM (79 FR 19296, April 8, 2014) for correcting the unsafe condition; 
and
    <bullet> Do not add any additional burden upon the public than was 
already proposed in the NPRM (79 FR 19296, April 8, 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

    We reviewed Airbus Mandatory Service Bulletins A300-28-0091, dated 
March 5, 2013; and A300-28-6109, Revision 01, dated December 20, 2013. 
This service information describes procedures for a one-time inspection 
for chafing of the overflow sensor harness, and contacting the 
manufacturer for repair instructions. This service information also 
describes modification of the sensor harness. This service information 
is reasonably available; see ADDRESSES for ways to access this service 
information.

Costs of Compliance

    We estimate that this AD affects 123 airplanes of U.S. registry.
    We also estimate that it takes about 3 work-hours per product to 
comply with the inspection required by this AD. The average labor rate 
is $85 per work-hour. Based on these figures, we estimate the cost of 
this inspection on U.S. operators to be $31,365, or $255 per product.
    We estimate that it takes about 12 work-hours per product to comply 
with the modification requirements of this AD. The average labor rate 
is $85 per work-hour. Required parts cost about $500 per product. Based 
on these figures, we estimate the cost of this modification on U.S. 
operators to be $186,960, or $1,520 per product.
    We have received no definitive data that would enable us to provide 
cost estimates for the on-condition repairs specified in this AD.

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 http://www.regulations.gov/#!docketDetail;D=FAA-2014-0189; 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

[[Page 11105]]

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):

2015-03-03 Airbus: Amendment 39-18099. Docket No. FAA-2014-0189; 
Directorate Identifier 2013-NM-181-AD.

(a) Effective Date

    This AD becomes effective April 6, 2015.

(b) Affected ADs

    None.

(c) Applicability

    This AD applies to the Airbus airplanes specified in paragraphs 
(c)(1), (c)(2), (c)(3), (c)(4), and (c)(5) of this AD, certificated 
in any category, all manufacturer serial numbers; except for 
airplanes modified by supplemental type certificate ST00092BO 
(http://rgl.faa.gov/Regulatory_and_Guidance_Library/rgstc.nsf/0/D41C5AE8E46B4901862574900069E004?OpenDocument&Highlight=st00092bo).
    (1) Model A300 B2-1A, B2-1C, B2K-3C, B2-203, B4-2C, B4-103, and 
B4-203 airplanes.
    (2) Model A300 B4-601, B4-603, B4-620, and B4-622 airplanes.
    (3) Model A300 B4-605R and B4-622R airplanes.
    (4) Model A300 F4-605R and F4-622R airplanes.
    (5) Model A300 C4-605R Variant F airplanes.

(d) Subject

    Air Transport Association (ATA) of America Code 28, Fuel.

(e) Reason

    This AD was prompted by a report of chafing found on the 
overflow sensor harness of the surge tank, and subsequent contact 
between the electrical wiring and fuel tank structure. We are 
issuing this AD to prevent chafing of the harness and subsequent 
contact between the electrical wiring and fuel tank structure, which 
could result in electrical arcing and a fuel tank explosion and 
consequent loss of the airplane.

(f) Compliance

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

(g) One-Time Inspection and Repair

    Within 30 months after the effective date of this AD: Perform a 
one-time general visual inspection for chafing of the outer tank 
sensor harness between ribs 26 and 27, in accordance with the 
Accomplishment Instructions of Airbus Service Bulletin A300-28-0091, 
dated March 5, 2013 (for Model A300 series airplanes); or Airbus 
Service Bulletin A300-28-6109, Revision 01, dated December 20, 2013 
(for Model A300-600 series airplanes);
    (1) If any previous repairs are identified, or if braid and wire 
insulation is found damaged with the conductor exposed during the 
inspection required by the introductory text of paragraph (g) of 
this AD: 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).
    (2) If the braid and wire insulation is found damaged without 
the conductor exposed during the inspection required by the 
introductory text of paragraph (g) of this AD: Before further 
flight, repair, in accordance with the Accomplishment Instructions 
of Airbus Service Bulletin A300-28-0091, dated March 5, 2013 (for 
Model A300 series airplanes); or Airbus Service Bulletin A300-28-
6109, Revision 01, dated December 20, 2013 (for Model A300-600 
series airplanes).

(h) Modification

    (1) For airplanes on which no damage was found during the 
inspection required by the introductory text of paragraph (g) of 
this AD: Before further flight, install modified and error-proof 
angle brackets to stringer 15 between ribs 26 and 27 of the outer 
tank sensor harness, in accordance with the Accomplishment 
Instructions of Airbus Service Bulletin A300-28-0091, dated March 5, 
2013 (for Model A300 series airplanes); or Airbus Service Bulletin 
A300-28-6109, Revision 01, dated December 20, 2013 (for Model A300-
600 series airplanes).
    (2) For airplanes on which any damage was found during the 
inspection required by the introductory text of paragraph (g) of 
this AD, and the applicable repair required by paragraph (g)(1) or 
(g)(2) of this AD has been done: Before further flight, install 
modified and error-proof angle brackets to stringer 15 between ribs 
26 and 27 of the outer tank sensor harness, in accordance with the 
Accomplishment Instructions of Airbus Service Bulletin A300-28-0091, 
dated March 5, 2013 (for Model A300 series airplanes); or Airbus 
Service Bulletin A300-28-6109, Revision 01, dated December 20, 2013 
(for Model A300-600 series airplanes).

(i) Credit for Previous Actions

    This paragraph provides credit for actions required by 
paragraphs (g) and (h) of this AD, if those actions were performed 
before the effective date of this AD using Airbus Service Bulletin 
A300-28-6109, dated March 5, 2013, which is not incorporated by 
reference in this AD.

(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; phone: 425-227-2125; fax: 425-227-1149. Information may be 
emailed to: <a href="/cdn-cgi/l/email-protection#063f2b47484b2b3737302b474b49452b54435753435552554660676728616970"><span class="__cf_email__" data-cfemail="033a2e424d4e2e3232352e424e4c402e5146525646505750436562622d646c75">[email 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) Except as required by paragraph (g)(1) of this AD: If the 
service information contains procedures or tests that are identified 
as RC (Required for Compliance), those procedures and tests must be 
done to comply with this AD; any 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 a serviceable condition. Any substitutions or changes to 
procedures or tests identified as RC require approval of an AMOC.
    (2) Contacting the Manufacturer: For any requirement in this AD 
to obtain corrective actions from a manufacturer, the action must be 
accomplished using a method approved by the Manager, International 
Branch, ANM-116, Transport Airplane Directorate, FAA; or the EASA; 
or Airbus's EASA DOA. If approved by the DOA, the approval must 
include the DOA-authorized signature.

(k) Related Information

    (1) Refer to Mandatory Continuing Airworthiness Information 
(MCAI) EASA Airworthiness Directive 2013-0193, dated August 23, 
2013, for related information. This MCAI may be found in the AD 
docket on the Internet at http://www.regulations.gov/#!documentDetail;D=FAA-2014-0189-0002.
    (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

[[Page 11106]]

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 A300-28-0091, dated March 5, 2013.
    (ii) Airbus Service Bulletin A300-28-6109, Revision 01, dated 
December 20, 2013.
    (3) For service information identified in this AD, contact 
Airbus, 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 <a href="/cdn-cgi/l/email-protection#0f6e6c6c607a617b216e667d78607d7b67226a6e7c4f6e667d6d7a7c216c6062"><span class="__cf_email__" data-cfemail="d8b9bbbbb7adb6acf6b9b1aaafb7aaacb0f5bdb9ab98b9b1aabaadabf6bbb7b5">[email protected]</span></a>; 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 February 2, 2015.
Jeffrey E. Duven,
Manager, Transport Airplane Directorate, Aircraft Certification 
Service.
[FR Doc. 2015-02676 Filed 2-27-15; 8:45 am]
BILLING CODE 4910-13-P


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