[Federal Register Volume 81, Number 201 (Tuesday, October 18, 2016)]
[Rules and Regulations]
[Pages 71593-71596]
From the Federal Register Online via the Government Publishing Office [www.gpo.gov]
[FR Doc No: 2016-23647]


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DEPARTMENT OF TRANSPORTATION

Federal Aviation Administration

14 CFR Part 39

[Docket No. FAA-2016-6418; Directorate Identifier 2015-NM-158-AD; 
Amendment 39-18676; AD 2016-20-10]
RIN 2120-AA64


Airworthiness Directives; Airbus Airplanes

AGENCY: Federal Aviation Administration (FAA), DOT.

ACTION: Final rule.

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SUMMARY: We are adopting a new airworthiness directive (AD) for all 
Airbus Model A330-200 Freighter, -200, and -300 series airplanes; and 
Airbus Model A340-200, -300, -500, and -600 series airplanes. This AD 
was prompted by reports of fuel leaking through fuel pump electrical 
connectors and of fuel pump electrical connector damage caused by the 
build-up of moisture behind the electrical connectors. This AD requires 
an inspection of the fuel pumps to identify their part numbers and 
replacement of affected pumps. We are issuing this AD to prevent a 
potential ignition source and a fuel leak through damaged fuel pump 
electrical connectors, which creates a flammability risk in an area 
adjacent to the fuel tank.

DATES: This AD is effective November 22, 2016.
    The Director of the Federal Register approved the incorporation by 
reference of certain publications listed in this AD as of November 22, 
2016.

ADDRESSES: For service information identified in this final rule, 
contact Airbus SAS, Airworthiness Office--EAL, 1 Rond Point Maurice 
Bellonte, 31707 Blagnac Cedex, France; telephone +33 5 61 93 36 96; fax 
+33 5 61 93 45 80; email [email protected]; Internet 
http://www.airbus.com. You may view this referenced service information 
at the

[[Page 71594]]

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 http://www.regulations.gov by searching for and locating Docket No. FAA-2016-
6418.

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-2016-
6418; 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 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: Vladimir Ulyanov, Aerospace Engineer, 
International Branch, ANM-116, Transport Airplane Directorate, FAA, 
1601 Lind Avenue SW., Renton, WA 98057-3356; telephone: 425-227-1138; 
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 A330-200 
Freighter, -200, and -300 series airplanes; and Airbus Model A340-200, 
-300, -500, and -600 series airplanes. The NPRM published in the 
Federal Register on May 9, 2016 (81 FR 28033) (``the NPRM''). The NPRM 
was prompted by reports of fuel leaking through fuel pump electrical 
connectors and of fuel pump electrical connector damage caused by the 
build-up of moisture behind the electrical connectors. The NPRM 
proposed to require an inspection of the fuel pumps to identify their 
part numbers and replacement of affected pumps. We are issuing this AD 
to prevent a potential ignition source and a fuel leak through damaged 
fuel pump electrical connectors. This condition creates a flammability 
risk in an area adjacent to the fuel tank.
    The European Aviation Safety Agency (EASA), which is the Technical 
Agent for the Member States of the European Union, has issued EASA AD 
2015-0194, dated September 22, 2015, to correct an unsafe condition for 
all Airbus Model A330-200 Freighter, -200, and -300 series airplanes; 
and Airbus Model A340-200, -300, -500, and -600 series airplanes. The 
MCAI states:

    Operators reported cases of fuel leak through fuel pump 
electrical connectors. Subsequent investigation revealed fuel pump 
electrical connector damage caused by moisture build up behind the 
electrical connector.
    This condition, if not detected and corrected, could create 
concurrently an ignition source and fuel leak as a result of a 
single failure, resulting in exposure to a flammability risk in an 
adjacent area to the fuel tank.
    To address this unsafe condition, Airbus published Service 
Bulletins (SB) A330-28-3127, SB A340-28-4138 and SB A340-28-5060, 
providing inspection/identification instructions, and instructions 
for replacement of the fuel pumps.
    For the reasons described above, this [EASA] AD requires 
identification and replacement of the affected fuel pumps.

    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-2016-
6418.

Comments

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

Request To Clarify Compliance for Affected Pumps

    American Airlines (AAL) requested that we clarify which groups of 
pumps paragraphs (h)(1) and (h)(2) of the proposed AD are intended to 
control. Where individual items begin with ``All of the affected pumps. 
. . .'' AAL explained that paragraph (h) of the proposed AD must be 
intended to refer to all of the affected pumps on each airplane. AAL 
pointed out that this language creates a requirement for all airplanes 
that have one or more pumps having part number (P/N) 568-1-28300-001 or 
568-1-28300-002 installed to be modified in accordance with the service 
information within 72 months. AAL asserted that consistent references 
to ``each affected pump'' confuse that interpretation and seem to imply 
that each pump is treated separately. If the intent is to control the 
compliance time for replacement at the pump level, AAL stated that it 
would be more efficient to simply state that -001 and -002 pumps must 
be replaced within 72 months, while -100 and -101 pumps must be 
replaced within 96 months. If the intent is to control the compliance 
time at the airplane level, AAL stated that the language throughout 
paragraph (h) of the proposed AD should be revised to reflect that 
intent; American provided some example language.
    We agree that this AD should specify the compliance times at the 
airplane level. Therefore, we have revised paragraphs (h)(1) and (h)(2) 
of this AD by replacing the text in the beginning of the sentences, 
``For affected fuel pumps that have . . . , '' with the text ``For 
airplanes with fuel pumps that have . . .'' in order to clearly 
identify the airplane configuration.

Conclusion

    We reviewed the relevant data, considered the comment 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 minor changes:
     Are consistent with the intent that was proposed in the 
NPRM for correcting the unsafe condition; and
     Do not add any additional burden upon the public than was 
already proposed in the NPRM.
    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 the following service information:
     Airbus Service Bulletin A330-28-3127, Revision 02, dated 
April 14, 2016.
     Airbus Service Bulletin A340-28-4138, Revision 01, dated 
September 24, 2015.
     Airbus Service Bulletin A340-28-5060, Revision 01, dated 
September 24, 2015.
    The service information describes procedures to identify and 
replace affected fuel pumps with serviceable fuel pumps. These 
documents are distinct since they apply to different airplane models. 
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 99 airplanes of U.S. registry.
    We also estimate that it will take about 4 work-hours per product 
to comply with the basic requirements of this AD. The average labor 
rate is $85 per work-hour. Based on these figures, we estimate the cost 
of this AD on U.S. operators to be $33,660, or $340 per product.

[[Page 71595]]

    In addition, we estimate that any necessary follow-on actions would 
take about 17 work-hours and require parts costing $10,400, for a cost 
of $11,845 per product. We have no way of determining the number of 
airplanes 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.

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):

2016-20-10 Airbus: Amendment 39-18676; Docket No. FAA-2016-6418; 
Directorate Identifier 2015-NM-158-AD.

(a) Effective Date

    This AD is effective November 22, 2016.

(b) Affected ADs

    None.

(c) Applicability

    This AD applies to Airbus Model A330-223F and -243F airplanes; 
Model A330-201, -202, -203, -223, and -243 airplanes; Model A330-
301, -302, -303, -321, -322, -323, -341, -342, and -343 airplanes; 
Model A340-211, -212, and -213 airplanes; Model A340-311, -312, and 
-313 airplanes; Model A340-541 and A340-642 airplanes; certificated 
in any category; all manufacturer serial numbers.

(d) Subject

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

(e) Reason

    This AD was prompted by reports of fuel leaking through fuel 
pump electrical connectors and of fuel pump electrical connector 
damage caused by the build-up of moisture behind the electrical 
connectors. Electrical connections that become damaged by moisture 
can create an ignition source and a fuel leak. We are issuing this 
AD to prevent a potential ignition source and a fuel leak through 
damaged fuel pump electrical connectors, which creates a 
flammability risk in an area adjacent to the fuel tank.

(f) Compliance

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

(g) Identify Part Numbers (P/Ns)

    Within 48 months after the effective date of this AD, inspect 
each fuel pump to identify the part number, in accordance with the 
Accomplishment Instructions of Airbus Service Bulletin A330-28-3127, 
Revision 02, dated April 14, 2016; Airbus Service Bulletin A340-28-
4138, Revision 01, dated September 24, 2015; or Airbus Service 
Bulletin A340-28-5060, Revision 01, dated September 24, 2015; as 
applicable to airplane model. A review of airplane delivery or 
maintenance records is acceptable in lieu of this inspection if the 
part number of the fuel pump can be conclusively determined from 
that review.

(h) Modification

    If, during the inspection required by paragraph (g) of this AD, 
it is determined that any affected fuel pump is installed: Within 
the compliance time specified in paragraph (h)(1) or (h)(2) of this 
AD, depending on the configuration of the affected fuel pumps 
installed, replace each affected fuel pump with a serviceable fuel 
pump, in accordance with the Accomplishment Instructions of Airbus 
Service Bulletin A330-28-3127, Revision 02, dated April 14, 2016; 
Airbus Service Bulletin A340-28-4138, Revision 01, dated September 
24, 2015; or Airbus Service Bulletin A340-28-5060, Revision 01, 
dated September 24, 2015; as applicable to airplane model.
    (1) For airplanes with fuel pumps that have a part number or 
combination of part numbers that are specified in paragraphs 
(h)(1)(i) through (h)(1)(vi) of this AD: Do the replacement within 
72 months after the effective date of this AD.
    (i) All installed fuel pumps have P/N 568-1-28300-001.
    (ii) All installed fuel pumps have P/N 568-1-28300-002.
    (iii) Installed fuel pumps have a combination of P/Ns 568-1-
28300-001 and 568-1-28300-002.
    (iv) Installed fuel pumps have a combination of P/Ns 568-1-
28300-001 and 568-1-28300-101.
    (v) Installed fuel pumps have a combination of P/Ns 568-1-28300-
002 and 568-1-28300-101.
    (vi) Installed fuel pumps have a combination of P/Ns 568-1-
28300-001, 568-1-28300-002, and 568-1-28300-101.
    (2) For airplanes with fuel pumps that have a part number or 
combination of part numbers that are specified in paragraphs 
(h)(2)(i) through (h)(2)(iii) of this AD: Do the replacement within 
96 months after the effective date of this AD.
    (i) All installed fuel pumps have P/N 568-1-28300-100.
    (ii) All installed fuel pumps have P/N 568-1-28300-101.
    (iii) Installed fuel pumps have a combination of P/Ns 568-1-
28300-100 and 568-1-28300-101.

(i) Definitions

    (1) For the purpose of this AD, an ``affected fuel pump'' is 
defined as any pump having P/N 568-1-28300-001, 568-1-28300-002, 
568-1-28300-100, or 568-1-28300-101.
    (2) For the purpose of this AD, a ``serviceable fuel pump'' is a 
pump having a part number not listed in paragraph (i)(1) of this AD.

(j) No Reporting Requirement

    Although Airbus Service Bulletin A330-28-3127, Revision 02, 
dated April 14, 2016; Airbus Service Bulletin A340-28-4138, Revision 
01, dated September 24, 2015; and Airbus Service Bulletin A340-28-
5060, Revision 01, dated September 24, 2015; specify submitting 
certain information to the manufacturer, and specifies that action 
as ``RC'' (Required for Compliance), this AD does not include that 
requirement.

(k) Parts Installation Prohibition

    After the identification of the fuel pump part numbers required 
by paragraph (g) of this AD, comply with the prohibition

[[Page 71596]]

required by paragraph (k)(1) or (k)(2) of this AD, as applicable.
    (1) For an airplane that does not have an affected fuel pump 
installed: After the identification of the fuel pump part numbers 
required by paragraph (g) of this AD, no person may install an 
affected fuel pump on the airplane.
    (2) For an airplane that has an affected fuel pump installed: 
After modification of the airplane as required by paragraph (h) of 
this AD, no person may install an affected fuel pump on the 
airplane.

(l) 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 the applicable service 
information specified in paragraphs (l)(1), (l)(2), (l)(3), and 
(l)(4) of this AD. This service information is not incorporated by 
reference in this AD.
    (1) Airbus Service Bulletin A330-28-3127, dated July 14, 2015.
    (2) Airbus Service Bulletin A330-28-3127, Revision 01, dated 
September 24, 2015.
    (3) Airbus Service Bulletin A340-28-4138, dated July 14, 2015.
    (4) Airbus Service Bulletin A340-28-5060, dated July 14, 2015.

(m) 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: Vladimir 
Ulyanov, Aerospace Engineer, International Branch, ANM-116, 
Transport Airplane Directorate, FAA, 1601 Lind Avenue SW., Renton, 
WA 98057-3356; telephone: 425-227-1138; fax: 425-227-1149. 
Information may be emailed to: [email protected]. 
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.
    (3) Required for Compliance (RC): Except as provide by paragraph 
(j) of this AD, if any 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.

(n) Related Information

    (1) Refer to Continuing Airworthiness Information (MCAI) EASA AD 
2015-0194, dated September 22, 2015, for related information. You 
may examine the MCAI on the Internet at http://www.regulations.gov 
by searching for and locating Docket No. FAA-2016-6418.

(o) 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 A330-28-3127, Revision 02, dated 
April 14, 2016.
    (ii) Airbus Service Bulletin A340-28-4138, Revision 01, dated 
September 24, 2015.
    (iii) Airbus Service Bulletin A340-28-5060, Revision 01, dated 
September 24, 2015.
    (3) For service information identified in this AD, contact 
Airbus SAS, Airworthiness Office--EAL, 1 Rond Point Maurice 
Bellonte, 31707 Blagnac Cedex, France; telephone: +33 5 61 93 36 96; 
fax: +33 5 61 93 45 80; email: [email protected]; 
Internet: http://www.airbus.com. 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.
    (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 September 26, 2016.
Dionne Palermo,
Acting Manager, Transport Airplane Directorate, Aircraft Certification 
Service.
[FR Doc. 2016-23647 Filed 10-17-16; 8:45 am]
BILLING CODE 4910-13-P