Airworthiness Directives; Airbus Airplanes

[Federal Register Volume 82, Number 180 (Tuesday, September 19, 2017)]
[Rules and Regulations]
[Pages 43671-43674]
From the Federal Register Online via the Government Publishing Office [www.gpo.gov]
[FR Doc No: 2017-19653]


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DEPARTMENT OF TRANSPORTATION

Federal Aviation Administration

14 CFR Part 39

[Docket No. FAA-2017-0339; Product Identifier 2016-NM-078-AD; Amendment 
39-19042; AD 2017-19-12]
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) 2014-13-17, 
which applied 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

[[Page 43672]]

called Model A300-600 series airplanes); and Airbus Model A310 series 
airplanes. AD 2014-13-17 required repetitive functional tests of the 
circuit breakers for the fuel pump power supply, and replacement of 
certain circuit breakers. This new AD requires installation of fuel 
pumps having a new standard, which terminates the repetitive functional 
tests. This AD was prompted by our determination that installation of a 
newly developed fuel pump standard will better address the unsafe 
condition. We are issuing this AD to address the unsafe condition on 
these products.

DATES: This AD is effective October 24, 2017.
    The Director of the Federal Register approved the incorporation by 
reference of certain publications listed in this AD as of October 24, 
2017.
    The Director of the Federal Register approved the incorporation by 
reference of a certain other publication listed in this AD as of August 
19, 2014 (79 FR 41098, July 15, 2014).

ADDRESSES: For service information identified in this final rule, 
contact Airbus SAS, Airworthiness Office--EAW, 1 Rond Point Maurice 
Bellonte, 31707 Blagnac Cedex, France; telephone +33 5 61 93 36 96; fax 
+33 5 61 93 44 51; email [email protected]; Internet 
http://www.airbus.com. You may view this referenced service information 
at the FAA, Transport Standards Branch, 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 http://www.regulations.gov by searching for and locating Docket No. FAA-2017-
0339.

Examining the AD Docket

    You may examine the AD docket on the Internet at http://www.regulations.gov by searching for and locating Docket No. FAA-2017-
0339; 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: Dan Rodina, Aerospace Engineer, 
International Section, Transport Standards Branch, 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 to supersede AD 2014-13-17, Amendment 39-17893 (79 FR 41098, 
July 15, 2014) (``AD 2014-13-17''). AD 2014-13-17 applied to all Airbus 
Model A300 series airplanes; Airbus Model A300-600 series airplanes; 
and Airbus Model A310 series airplanes. The NPRM published in the 
Federal Register on May 16, 2017 (82 FR 22445). The NPRM was prompted 
by reports of failures of the right inner tank fuel pump. The NPRM 
proposed to require installation of fuel pumps having the new standard. 
We are issuing this AD to prevent a fuel pump from overheating, which 
could result in a fuel tank explosion and consequent loss of the 
airplane.
    The European Aviation Safety Agency (EASA), which is the Technical 
Agent for the Member States of the European Union, has issued EASA 
Airworthiness Directive 2016-0080, dated April 21, 2016 (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; Airbus Model A300-600 series airplanes; and Airbus 
Model A310 series airplanes. The MCAI states:

    Two successive failures have been reported of a Right Hand #1 
inner tank fuel pump, Part Number (P/N) 2052Cxx series (where ``xx'' 
represents any numerical combination). These occurrences were solved 
by replacement of the pump, associated circuit breaker (CB) and the 
alternating current (AC) bus load relay.
    Investigations determined that, in case of loss of one phase on 
the pump supply and the associated CB failing to trip, the fuel pump 
thermal fuses may not operate as quickly as expected.
    This condition, if not detected and corrected, could lead to an 
overheat condition of the fuel pump in excess of 200 [deg]C, 
possibly resulting in a fuel tank explosion and loss of the 
aeroplane.
    To address this potential unsafe condition, Airbus issued Alert 
Operator Transmission (AOT) A28W002-13 providing instructions for 
functional tests of CBs.
    As a temporary measure, EASA issued AD 2013-0163 [which 
corresponds to FAA AD 2014-13-17] to require repetitive functional 
tests of the affected fuel pump power supply CBs, and, depending on 
findings, replacement.
    Since that [EASA] AD was issued, a new standard of fuel pump was 
developed, which improves the thermal protection, thereby preventing 
the potential unsafe condition and cancelling the need for 
repetitive functional tests of the affected CBs, as required by EASA 
AD 2013-0163. Airbus issued Service Bulletin (SB) A300-28-0093, SB 
A300-28-6111, SB A300-28-9025 and SB A310-28-2176 to provide 
instructions for this upgrade of the fuel pump for all positions on 
the aeroplane.
    For the reasons described above, this [EASA] AD retains the 
requirements EASA AD 2013-0163, which is superseded, and requires 
installation of the new standard fuel pump, which constitutes 
terminating action for the repetitive functional tests.

    You may examine the MCAI in the AD docket on the Internet at http://www.regulations.gov by searching for and locating Docket No. FAA-2017-
0339.

Comments

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

Support for the NPRM

    FedEx Express stated that it concurs with the proposed corrective 
actions.

Suggestion To Organize Files by Airplane Serial Number

    One commenter, Anani Fleur, suggested that the FAA set up files for 
every airplane by serial number. The commenter stated that the file 
system should be computerized and that FAA employees could do this.
    We acknowledge the commenter's suggestion. Since it does not 
address the unsafe condition identified in this AD, we have not changed 
this AD regarding this issue.

Conclusion

    We reviewed the available data, including the comments received, 
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

    Airbus has issued the following service information, which 
describes procedures for installing new standard fuel pumps with 
improved thermal protection. These documents are distinct since they 
apply to different airplane models in different configurations.

[[Page 43673]]

    <bullet> Service Bulletin A300-28-0093, dated December 15, 2015.
    <bullet> Service Bulletin A300-28-6111, Revision 01, dated February 
29, 2016.
    <bullet> Service Bulletin A310-28-2176, dated December 15, 2015.
    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 128 airplanes of U.S. registry.
    The actions required by AD 2014-13-17 and retained in this AD take 
about 1 work-hour per product, at an average labor rate of $85 per 
work-hour. Based on these figures, the estimated cost of the actions 
that are required by AD 2014-13-17 is $85 per product, per inspection 
cycle.
    We also estimate that it will take up to 21 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 per product is not 
available. Based on these figures, we estimate the cost of this AD on 
U.S. operators to be up to $228,480, or up to $1,785 per product.

Authority for This Rulemaking

    Title 49 of the United States Code specifies the FAA's authority to 
issue rules on aviation safety. Subtitle I, section 106, describes the 
authority of the FAA Administrator. ``Subtitle VII: Aviation 
Programs,'' describes in more detail the scope of the Agency's 
authority.
    We are issuing this rulemaking under the authority described in 
``Subtitle VII, Part A, Subpart III, Section 44701: General 
requirements.'' Under that section, Congress charges the FAA with 
promoting safe flight of civil aircraft in air commerce by prescribing 
regulations for practices, methods, and procedures the Administrator 
finds necessary for safety in air commerce. This regulation is within 
the scope of that authority because it addresses an unsafe condition 
that is likely to exist or develop on products identified in this 
rulemaking action.
    This AD is issued in accordance with authority delegated by the 
Executive Director, Aircraft Certification Service, as authorized by 
FAA Order 8000.51C. In accordance with that order, issuance of ADs is 
normally a function of the Compliance and Airworthiness Division, but 
during this transition period, the Executive Director has delegated the 
authority to issue ADs applicable to transport category airplanes to 
the Director of the System Oversight Division.

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) 
2014-13-17, Amendment 39-17893 (79 FR 41098, July 15, 2014), and adding 
the following new AD:

2017-19-12 Airbus: Amendment 39-19042; Docket No. FAA-2017-0339; 
Product Identifier 2016-NM-078-AD.

(a) Effective Date

    This AD is effective October 24, 2017.

(b) Affected ADs

    This AD replaces 2014-13-17, Amendment 39-17893 (79 FR 41098, 
July 15, 2014) (``AD 2014-13-17'').

(c) Applicability

    This AD applies to the Airbus airplanes, certificated in any 
category, identified in paragraphs (c)(1) through (c)(6) of this AD, 
all manufacturer serial numbers.
    (1) Airbus Model A300 B2-1A, B2-1C, B2K-3C, B2-203, B4-2C, B4-
103, and B4-203 airplanes.
    (2) Airbus Model A300 B4-601, B4-603, B4-620, and B4-622 
airplanes.
    (3) Airbus Model A300 B4-605R and B4-622R airplanes.
    (4) Airbus Model A300 C4-605R Variant F airplanes.
    (5) Airbus Model A300 F4-605R and F4-622R airplanes.
    (6) Airbus 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 prevent a fuel pump from 
overheating, which could result in 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) Retained: Repetitive Functional Tests of Circuit Breakers, With New 
Terminating Action

    This paragraph restates the requirements of paragraph (g) of AD 
2014-13-17, with a new terminating action.
    (1) Within 6 months or 500 flight hours after August 19, 2014 
(the effective date of AD 2014-13-17), 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, until the fuel pump 
installation required by paragraph (h) of this AD is accomplished.
    (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 Model 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.

[[Page 43674]]

    (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) New Requirement of This AD: Installation of Fuel Pumps Having a New 
Standard

    Within 72 months after the effective date of this AD: Install a 
fuel pump having a new standard at each applicable location on the 
airplane, in accordance with the Accomplishment Instructions of the 
applicable service information specified in paragraph (h)(1), 
(h)(2), or (h)(3) of this AD. Accomplishment of the installation of 
fuel pumps having the new standard terminates the requirement for 
the repetitive functional tests required by paragraph (g)(1) of this 
AD.
    (1) Airbus Service Bulletin A300-28-0093, dated December 15, 
2015.
    (2) Airbus Service Bulletin A300-28-6111, Revision 01, dated 
February 29, 2016.
    (3) Airbus Service Bulletin A310-28-2176, dated December 15, 
2015.

(i) Parts Installation Prohibition

    After the installation of any fuel pump having a new standard on 
an airplane, as required by paragraph (h) of this AD, no person may 
install any fuel pump having part number 2052Cxx (where ``xx'' 
represents any numerical combination) on that airplane.

(j) Credit for Previous Actions

    This paragraph provides credit for the installation required by 
paragraph (h) of this AD, if the installation was done before the 
effective date of this AD using Airbus Service Bulletin A300-28-
6111, dated December 15, 2015.

(k) Other FAA AD Provisions

    The following provisions also apply to this AD:
    (1) Alternative Methods of Compliance (AMOCs): The Manager, 
International Section, Transport Standards Branch, 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 Section, send it to the attention of 
the person identified in paragraph (l)(2) of this AD. Information 
may be emailed to: [email protected].
    (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 Section, Transport Standards 
Branch, 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.
    (3) Required for Compliance (RC): If any Airbus service 
information contains procedures or tests that are identified as RC, 
those procedures and tests must be done to comply with this AD; any 
procedures or tests that are not identified as RC are recommended. 
Those procedures and tests that are not identified as RC may be 
deviated from using accepted methods in accordance with the 
operator's maintenance or inspection program without obtaining 
approval of an AMOC, provided the procedures and tests identified as 
RC can be done and the airplane can be put back in an airworthy 
condition. Any substitutions or changes to procedures or tests 
identified as RC require approval of an AMOC.

(l) Related Information

    (1) Refer to Mandatory Continuing Airworthiness Information 
(MCAI) EASA AD 2016-0080, dated April 21, 2016, for related 
information. This MCAI may be found in the AD docket on the Internet 
at http://www.regulations.gov by searching for and locating Docket 
No. FAA-2017-0339.
    (2) For more information about this AD, contact Dan Rodina, 
Aerospace Engineer, International Section, Transport Standards 
Branch, FAA, 1601 Lind Avenue SW., Renton, WA 98057-3356; telephone 
425-227-2125; fax 425-227-1149.
    (3) Service information identified in this AD that is not 
incorporated by reference is available at the addresses specified in 
paragraphs (m)(5) and (m)(6) 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, 2017.
    (i) Airbus Service Bulletin A300-28-0093, dated December 15, 
2015.
    (ii) Airbus Service Bulletin A300-28-6111, Revision 01, dated 
February 29, 2016.
    (iii) Airbus Service Bulletin A310-28-2176, dated December 15, 
2015.
    (4) The following service information was approved for IBR on 
August 19, 2014 (79 FR 41098, July 15, 2014).
    (i) Airbus Alert Operators Transmission A28W002-13, dated July 
23, 2013.
    (ii) Reserved.
    (5) 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 [email protected]; 
Internet http://www.airbus.com.
    (6) You may view this service information at the FAA, Transport 
Standards Branch, 1601 Lind Avenue SW., Renton, WA. For information 
on the availability of this material at the FAA, call 425-227-1221.
    (7) 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 September 7, 2017.
Jeffrey E. Duven,
Director, System Oversight Division, Aircraft Certification Service.
[FR Doc. 2017-19653 Filed 9-18-17; 8:45 am]
 BILLING CODE 4910-13-P

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