
[Federal Register Volume 79, Number 135 (Tuesday, July 15, 2014)]
[Rules and Regulations]
[Pages 41098-41101]
From the Federal Register Online via the Government Printing Office [www.gpo.gov]
[FR Doc No: 2014-15800]


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DEPARTMENT OF TRANSPORTATION

Federal Aviation Administration

14 CFR Part 39

[Docket No. FAA-2013-0973; Directorate Identifier 2013-NM-139-AD; 
Amendment 39-17893; AD 2014-13-17]
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 series airplanes; 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. This AD was prompted by reports of 
failures of the right inner tank fuel pump. This AD requires repetitive 
functional tests of the circuit breakers for the fuel pump power 
supply, and replacement of certain circuit breakers. We are issuing 
this AD to detect and correct failure of the circuit breakers for the 
fuel pump power supply, which could result in a fuel pump overheating, 
leading to a fuel tank explosion.

DATES: This AD becomes effective August 19, 2014.
    The Director of the Federal Register approved the incorporation by 
reference of a certain publication listed in this AD as of August 19, 
2014.

ADDRESSES: You may examine the AD docket on the Internet at http://www.regulations.gov/#!docketDetail;D=FAA-2013-0973; 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 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 FAA, call 425-227-1221.

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 
series airplanes; 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 22, 
2013 (78 FR 70003).
    The European Aviation Safety Agency (EASA), which is the Technical 
Agent for the Member States of the European Community, has issued EASA 
Airworthiness Directive 2013-0163, dated July 24, 2013 (referred to 
after this as the Mandatory Continuing Airworthiness Information, or 
``the MCAI''), to correct an unsafe condition for the specified 
products. The MCAI states:

    Two successive failures have been reported of a Right Hand 
1 inner tank fuel pump, Part Number 2052Cxx series (with 
placeholder ``xx'' indicating numerals). The fix consisted in the 
replacement of the pump, the associated circuit breaker and the AC 
[alternating current] bus load relay.
    Investigations determined that, in case of loss of one phase on 
the pump supply and the associated circuit breaker failing to trip, 
the fuel pump thermal fuses may not operate as quickly as expected.
    This condition, if not detected and corrected, would result in 
an overheat condition of the fuel pump in excess of 200 [deg]C and 
could lead to a fuel tank explosion.
    To address this potential unsafe condition, Airbus issued Alert 
Operator Transmission (AOT) A28W002-13 providing instructions for a 
functional test of circuit breakers and corrective action.
    For the reasons described above, as a temporary measure until 
further notice, this [EASA] AD mandates functional tests of the 
affected fuel pump power supply circuit breakers, and, depending on 
findings, replacement of circuit breakers.
    This [EASA] AD will be followed by further [EASA] AD action.

    You may examine the MCAI in the AD docket on the Internet at http://www.regulations.gov/#!documentDetail;D=FAA-2013-0973-0002.

Comments

    We gave the public the opportunity to participate in developing 
this AD. We received no comments on the NPRM (78 FR 70003, November 22, 
2013) or on the determination of the cost to the public.

``Contacting the Manufacturer'' Paragraph in 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 (78 FR 70003, November 22, 2013), 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 a design approval holder 
(DAH) with State of Design Authority design organization approval 
(DOA), as applicable, to refer to a DAH authorized

[[Page 41099]]

to approve required repairs for the proposed AD.
    No comments were provided to the NPRM (78 FR 70003, November 22, 
2013) about these proposed changes. However, a comment was provided for 
another NPRM, Directorate Identifier 2012-NM-101-AD (78 FR 78285, 
December 26, 2013). The commenter 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 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 action must be accomplished using a 
method approved by the FAA, the European Aviation Safety Agency (EASA), 
or Airbus's EASA DOA. Where necessary throughout this AD, we also 
replaced any reference to approvals of corrective actions with a 
reference to the Contacting the Manufacturer paragraph.
    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 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 
alternative method of compliance.
    Other commenters to the NPRM discussed previously, 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 might have been issued some time before the 
FAA AD. Therefore, the DOA might 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 that the DAH-
provided repair specifically refer to this AD. Before adopting such a 
requirement, 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 this 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 ``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 in the 
Contacting the Manufacturer paragraph of this AD.

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:
     Are consistent with the intent that was proposed in the 
NPRM (78 FR 70003, November 22, 2013) for correcting the unsafe 
condition; and
     Do not add any additional burden upon the public than was 
already proposed in the NPRM (78 FR 70003, November 22, 2013).
    We also determined that these changes will not increase the 
economic burden on any operator or increase the scope of this AD.

Costs of Compliance

    We estimate that this AD affects 156 airplanes of U.S. registry.
    We also estimate that it will take about 1 work-hour per product to 
comply with the basic requirements of this AD. The average labor rate 
is $85 per work-hour. Required parts will cost about $0 per product. 
Based on these figures, we estimate the cost of this AD on U.S. 
operators to be $85 per test, or $13,260 per test for U.S.-registered 
airplanes.
    We have received no definitive data that would enable us to provide 
cost estimates for the on-condition actions 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

[[Page 41100]]

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-2013-0973; 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):

2014-13-17 Airbus: Amendment 39-17893. Docket No. FAA-2013-0973; 
Directorate Identifier 2013-NM-139-AD.

(a) Effective Date

    This AD becomes effective August 19, 2014.

(b) Affected ADs

    None.

(c) Applicability

    This AD applies to the Airbus airplanes specified in paragraphs 
(c)(1), (c)(2), (c)(3), (c)(4), (c)(5), and (c)(6) of this AD; 
certificated in any category; all serial numbers.
    (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.
    (6) Model A310-203, -204, -221, -222, -304, -322, -324, and -325 
airplanes.

(d) Subject

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

(e) Reason

    This AD was prompted by reports of failures of the right inner 
tank fuel pump. We are issuing this AD to detect and correct failure 
of the circuit breakers for the fuel pump power supply, which could 
result in a fuel pump overheating, leading to a fuel tank explosion.

(f) Compliance

    You are responsible for having the actions required by this AD 
performed within the compliance times specified, unless the actions 
have already been done.

(g) Repetitive Functional Tests of Circuit Breakers

    (1) Within 6 months or 500 flight hours after the effective date 
of this AD, whichever occurs first: Do a functional test of the 
circuit breakers for the fuel pump power supply, as identified in 
paragraphs (g)(1)(i), (g)(1)(ii), and (g)(1)(iii) of this AD, as 
applicable, in accordance with Airbus Alert Operators Transmission 
A28W002-13, dated July 23, 2013. Repeat the functional test 
thereafter at intervals not to exceed 6 months or 500 flight hours, 
whichever occurs first.
    (i) For Airbus Model A300 B2-1A, B2-1C, B2K-3C, and B2-203 
airplanes: Inner and outer pump, No. 1 and No. 2 left-hand (LH) side 
and right-hand (RH) side.
    (ii) For Airbus Model A300 B4-2C, B4-103, B4-203, B4-601, B4-
603, B4-620, and B4-622 airplanes; and A310-203, -204, -221, and -
222 airplanes:
    (A) Inner and outer pump, No. 1 and No. 2, LH and RH; and
    (B) Center pump, LH and RH.
    (iii) For Airbus Model A300 B4-605R, B4-622R, F4-605R, F4-622R, 
and C4-605R Variant F airplanes; and Model A310-304, -322, -324, and 
-325 airplanes:
    (A) Inner and outer pump, No. 1 and No. 2, LH and RH;
    (B) Center pump, LH and RH; and
    (C) Trim tank pump No. 1 and No. 2.
    (2) If, during any functional test required by paragraph (g)(1) 
of this AD, any circuit breaker fails any functional test, or any 
circuit breaker is found to be stuck closed, before further flight, 
replace the affected circuit breaker with a serviceable part, in 
accordance with Airbus Alert Operators Transmission A28W002-13, 
dated July 23, 2013.
    (3) The replacement of one or more circuit breakers as required 
by paragraph (g)(2) of this AD does not terminate the repetitive 
functional tests required by paragraph (g)(1) of this AD.

(h) 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 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.

(i) Related Information

    Refer to Mandatory Continuing Airworthiness Information (MCAI) 
European Aviation Safety Agency Airworthiness Directive 2013-0163, 
dated July 24, 2013, for related information. This MCAI may be found 
in the AD docket on the Internet at http://www.regulations.gov/#!documentDetail;D=FAA-2013-0973-0002.

(j) 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 Alert Operators Transmission A28W002-13, dated July 
23, 2013.
    (ii) Reserved.
    (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. 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.

[[Page 41101]]

    (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 June 25, 2014.
Jeffrey E. Duven,
Manager, Transport Airplane Directorate, Aircraft Certification 
Service.
[FR Doc. 2014-15800 Filed 7-14-14; 8:45 am]
BILLING CODE 4910-13-P


