[Federal Register Volume 81, Number 89 (Monday, May 9, 2016)]
[Proposed Rules]
[Pages 28033-28035]
From the Federal Register Online via the Government Publishing Office [www.gpo.gov]
[FR Doc No: 2016-10633]


 ========================================================================
 Proposed Rules
                                                 Federal Register
 ________________________________________________________________________
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 This section of the FEDERAL REGISTER contains notices to the public of 
 the proposed issuance of rules and regulations. The purpose of these 
 notices is to give interested persons an opportunity to participate in 
 the rule making prior to the adoption of the final rules.
 
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 

  Federal Register / Vol. 81, No. 89 / Monday, May 9, 2016 / Proposed 
Rules  

[[Page 28033]]



DEPARTMENT OF TRANSPORTATION

Federal Aviation Administration

14 CFR Part 39

[Docket No. FAA-2016-6418; Directorate Identifier 2015-NM-158-AD]
RIN 2120-AA64


Airworthiness Directives; Airbus Airplanes

AGENCY: Federal Aviation Administration (FAA), DOT.

ACTION: Notice of proposed rulemaking (NPRM).

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SUMMARY: We propose to adopt 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 
proposed AD was prompted by reports of fuel leaking through fuel pump 
electrical connectors and fuel pump electrical connector damage caused 
by the build-up of moisture behind the electrical connector. Electrical 
connectors that become damaged by moisture can create an ignition 
source and a fuel leak. This proposed AD would require an inspection of 
the fuel pumps to identify their part numbers and replacement of 
affected pumps. We are proposing this AD to prevent a potential 
ignition source and a fuel leak due to damaged fuel pump electrical 
connectors. This condition creates a flammability risk in an area 
adjacent to the fuel tank.

DATES: We must receive comments on this proposed AD by June 23, 2016.

ADDRESSES: You may send comments, using the procedures found in 14 CFR 
11.43 and 11.45, by any of the following methods:
     Federal eRulemaking Portal: Go to http://www.regulations.gov. Follow the instructions for submitting comments.
     Fax: 202-493-2251.
     Mail: U.S. Department of Transportation, Docket 
Operations, M-30, West Building Ground Floor, Room W12-140, 1200 New 
Jersey Avenue SE., Washington, DC 20590.
     Hand Delivery: U.S. Department of Transportation, Docket 
Operations, M-30, West Building Ground Floor, Room W12-140, 1200 New 
Jersey Avenue SE., Washington, DC, between 9 a.m. and 5 p.m., Monday 
through Friday, except Federal holidays.
    For service information identified in this NPRM, 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 
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.

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 proposed 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. 
Comments will be available in the AD docket shortly after receipt.

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:

Comments Invited

    We invite you to send any written relevant data, views, or 
arguments about this proposed AD. Send your comments to an address 
listed under the ADDRESSES section. Include ``Docket No. FAA-2016-6418; 
Directorate Identifier 2015-NM-158-AD'' at the beginning of your 
comments. We specifically invite comments on the overall regulatory, 
economic, environmental, and energy aspects of this proposed AD. We 
will consider all comments received by the closing date and may amend 
this proposed AD based on those comments.
    We will post all comments we receive, without change, to http://www.regulations.gov, including any personal information you provide. We 
will also post a report summarizing each substantive verbal contact we 
receive about this proposed AD.

Discussion

    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.

Related Service Information Under 1 CFR Part 51

    Airbus has issued the following service information:
     Airbus Service Bulletin A330-28-3127, Revision 01, dated 
September 24, 2015.
     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

[[Page 28034]]

affected fuel pumps with serviceable fuel pumps. 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.

FAA's Determination and Requirements of This Proposed AD

    This product has been approved by the aviation authority of another 
country, and is approved for operation in the United States. Pursuant 
to our bilateral agreement with the State of Design Authority, we have 
been notified of the unsafe condition described in the MCAI and service 
information referenced above. We are proposing this AD because we 
evaluated all pertinent information and determined an unsafe condition 
exists and is likely to exist or develop on other products of these 
same type designs.

Costs of Compliance

    We estimate that this proposed 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 proposed AD. The average 
labor rate is $85 per work-hour. Based on these figures, we estimate 
the cost of this proposed AD on U.S. operators to be $33,660, or $340 
per product.
    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 
aircraft that might need these actions.

Authority for This Rulemaking

    Title 49 of the United States Code specifies the FAA's authority to 
issue rules on aviation safety. Subtitle I, section 106, describes the 
authority of the FAA Administrator. ``Subtitle VII: Aviation 
Programs,'' describes in more detail the scope of the Agency's 
authority.
    We are issuing this rulemaking under the authority described in 
``Subtitle VII, Part A, Subpart III, Section 44701: General 
requirements.'' Under that section, Congress charges the FAA with 
promoting safe flight of civil aircraft in air commerce by prescribing 
regulations for practices, methods, and procedures the Administrator 
finds necessary for safety in air commerce. This regulation is within 
the scope of that authority because it addresses an unsafe condition 
that is likely to exist or develop on products identified in this 
rulemaking action.

Regulatory Findings

    We determined that this proposed AD would not have federalism 
implications under Executive Order 13132. This proposed AD would 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 this proposed 
regulation:
    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.

The Proposed Amendment

    Accordingly, under the authority delegated to me by the 
Administrator, the FAA proposes to amend 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):

Airbus: Docket No. FAA-2016-6418; Directorate Identifier 2015-NM-
158-AD.

(a) Comments Due Date

    We must receive comments by June 23, 2016.

(b) Affected ADs

    None.

(c) Applicability

    This AD applies to Airbus Model A330-223F and -243F airplanes; 
A330-201, -202, -203, -223, and -243 airplanes; A330-301, -302, -
303, -321, -322, -323, -341, -342, and -343 airplanes; and Airbus 
Model A340-211, -212, and -213 airplanes; A340-311, -312, and -313 
airplanes; A340-541 airplanes; 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 fuel pump electrical connector damage 
caused by the build-up of moisture behind the electrical connector. 
Electrical connectors 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 due to damaged fuel pump 
electrical connectors. This condition 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

    Within 48 months after the effective date of this AD, inspect 
each fuel pump to identify the part number (P/N) in accordance with 
the Accomplishment Instructions of Airbus Service Bulletin A330-28-
3127, Revision 01, dated September 24, 2015; 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 type. 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 an 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 01, dated September 24, 2015; 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 type.
    (1) For affected 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 of the affected fuel pumps have P/N 568-1-28300-001.
    (ii) All of the affected fuel pumps have P/N 568-1-28300-002.
    (iii) The affected fuel pumps have a combination of P/Ns 568-1-
28300-001 and 568-1-28300-002.
    (iv) The affected fuel pumps have a combination of P/Ns 568-1-
28300-001 and 568-1-28300-101.
    (v) The affected fuel pumps have a combination of P/Ns 568-1-
28300-002 and 568-1-28300-101.

[[Page 28035]]

    (vi) The affected fuel pumps have a combination of P/Ns 568-1-
28300-001, 568-1-28300-002, and 568-1-28300-101.
    (2) For affected 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 of the affected fuel pumps have P/N 568-1-28300-100.
    (ii) All of the affected fuel pumps have P/N 568-1-28300-101.
    (iii) The affected 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 01, 
dated September 24, 2015; 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, specifies to 
submit 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 as 
required by paragraph (g) of this AD, comply with the prohibition 
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 as 
required by paragraph (g) of this AD, do not install an affected 
fuel pump.
    (2) For an airplane that has an affected fuel pump installed: 
After modification of an airplane as required by paragraph (h) of 
this AD, no person may install an affected fuel pump on any 
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 service information 
included in paragraphs (l)(1), (l)(2), and (l)(3) of this AD, which 
are not incorporated by reference in this AD.
    (1) Airbus Service Bulletin A330-28-3127 dated July 14, 2015.
    (2) Airbus Service Bulletin A340-28-4138 dated July 14, 2015.
    (3) 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.
    (2) 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.

    Issued in Renton, Washington, on April 28, 2016.
Dionne Palermo,
Acting Manager, Transport Airplane Directorate, Aircraft Certification 
Service.
[FR Doc. 2016-10633 Filed 5-6-16; 8:45 am]
 BILLING CODE 4910-13-P