[Federal Register Volume 82, Number 96 (Friday, May 19, 2017)]
[Proposed Rules]
[Pages 22907-22910]
From the Federal Register Online via the Government Publishing Office [www.gpo.gov]
[FR Doc No: 2017-10035]


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DEPARTMENT OF TRANSPORTATION

Federal Aviation Administration

14 CFR Part 39

[Docket No. FAA-2016-7264; Directorate Identifier 2015-NM-185-AD]
RIN 2120-AA64


Airworthiness Directives; Airbus Airplanes

AGENCY: Federal Aviation Administration (FAA), DOT.

ACTION: Supplemental notice of proposed rulemaking (SNPRM); reopening 
of comment period.

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SUMMARY: We are revising an earlier notice of proposed rulemaking 
(NPRM) for certain Airbus Model A330-200, -200 Freighter, and -300 
series airplanes; and Model A340-500 and -600 series airplanes. This 
action revises the NPRM by including new inspection locations for 
certain airplanes, and removing incorrect part numbers. We are 
proposing this airworthiness directive (AD) to address the unsafe 
condition on these products. Since these actions impose an additional 
burden over those proposed in the NPRM, we are reopening the comment 
period to allow the public the chance to comment on these proposed 
changes.

DATES: The comment period for the NPRM published in the Federal 
Register on June 21, 2016 (81 FR 40201), is reopened.
    We must receive comments on this SNPRM by July 3, 2017.

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 SNPRM, 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-
7264; 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 SNPRM, the regulatory evaluation, any comments received, 
and other information. The street address for the Docket 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-2016-7264; 
Directorate Identifier 2015-NM-185-AD'' at the beginning of your 
comments. We specifically invite comments on the overall regulatory, 
economic, environmental, and energy aspects of this SNPRM. We will 
consider all comments received by the closing date and may amend this 
SNPRM 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 SNPRM.

Discussion

    We issued an NPRM to amend 14 CFR part 39 by adding an AD that 
would apply to certain Airbus Model A330-200, -200 Freighter, and -300 
series airplanes; and Model A340-500 and -600 series airplanes. The 
NPRM published in the Federal Register on June 21, 2016 (81 FR 40201) 
(``the NPRM''). The NPRM was prompted by a quality control review on 
the final assembly line, which determined that the wrong aluminum alloy 
was used to manufacture several structural parts. The NPRM proposed to 
require a one-time eddy current conductivity measurement of certain 
cabin and cargo compartment structural parts to determine if an 
incorrect aluminum alloy was used, and replacement of any affected part 
with a serviceable part.
    The European Aviation Safety Agency (EASA), which is the Technical 
Agent for the Member States of the European Union, has issued EASA 
Airworthiness Directive 2017-0021, dated February 8, 2017 (referred to 
after this as the Mandatory Continuing Airworthiness Information, or 
``the MCAI''), to correct an unsafe condition for certain Airbus Model 
A330-200, -200 Freighter, and -300 series airplanes; and Model A340-500 
and -600 series airplanes. The MCAI states:

    Following an Airbus quality control review on the final assembly 
line, it was discovered that wrong aluminum alloy was used to 
manufacture several structural parts.
    This condition, if not detected and corrected, could reduce the 
structural integrity of the aeroplane.
    To address this potential unsafe condition, Airbus published 
[Service Bulletin] (SB) A330-53-3261, SB A330-53-3262, and SB A340-
53-5072, as applicable to aeroplane type/model, to provide 
instructions to identify the affected parts. Consequently, EASA 
issued AD 2015-0206 to require a one-time special detailed 
inspection (SDI) [eddy current conductivity measurements] of certain 
cabin and/or cargo compartment parts for material identification 
and, depending on findings, replacement with serviceable parts.

[[Page 22908]]

    Since that [EASA] AD was issued, Airbus identified that the list 
of affected structural parts in SB A330-53-3261 was incorrect. 
Prompted by these findings, Airbus issued SB A330-53-3261 Revision 
01 to introduce the new locations to be inspected and remove other 
parts not affected.
    For the reasons described above, this [EASA] AD retains the 
requirements of EASA AD 2015-0206, which is superseded, and expands 
the locations to be inspected.

    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-
7264.

Related Service Information Under 1 CFR Part 51

    We reviewed the following service information:
     Airbus Service Bulletin A330-53-3261, Revision 01, 
including Appendixes 01, 02, and 03, dated November 10, 2016.
     Airbus Service Bulletin A330-53-3262, including Appendixes 
01 and 02, dated June 23, 2015.
     Airbus Service Bulletin A340-53-5072, including Appendixes 
01 and 02, dated June 23, 2015.
    The service information describes procedures for a one-time eddy 
current conductivity measurement of certain cabin and cargo compartment 
structural parts to determine if an incorrect aluminum alloy was used, 
and replacement of any affected part with a serviceable part. This 
service information is distinct since it applies to different parts on 
different airplanes. 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.

Comments

    We gave the public the opportunity to participate in developing the 
NPRM. We considered the comments received.

Request To Change Compliance Time

    American Airlines (AA) asked that we change the compliance time for 
the on-condition replacement specified in paragraph (h) of the proposed 
AD (in the NPRM) from ``before further flight'' to ``within 6 years 
after the effective date of the AD, or within 12 years from the 
aeroplane date of manufacture, whichever occurs first'' to correspond 
with the compliance time in the EASA AD. AA stated that this would 
provide more flexibility to operators in order to have a better plan to 
procure the parts and accomplish the replacement without extended 
downtime if the replacement parts are not immediately available after 
doing the inspection.
    We agree with the commenter for the reasons provided. We have 
changed the compliance time specified in paragraph (h) of this proposed 
AD accordingly.

Request To Correct Typographical Error

    AA asked that we correct a typographical error specified in the 
second box of Figure A-GFAAA, Sheet 02, ``Inspection Flowchart,'' of 
the service information identified in paragraphs (g)(2) and (g)(3) of 
the proposed AD (in the NPRM). AA stated that the conductivity 
measurement should specify Sigma 60 instead of Sigma 480.
    We agree that the conductivity measurement specified in the second 
box of the specified inspection flowchart is incorrect. We have added 
paragraph (i) to this proposed AD to specify this exception to the 
inspection flowchart in the service information. We have redesignated 
subsequent paragraphs accordingly.

Additional Changes to This Proposed AD

    As stated previously, we have revised this proposed AD to include 
new inspection locations for certain airplanes, and to remove incorrect 
part numbers from table 1 to paragraphs (g) and (h) of this proposed 
AD.

FAA's Determination and Requirements of This SNPRM

    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 the same 
type design.
    Certain changes described above expand the scope of the NPRM. As a 
result, we have determined that it is necessary to reopen the comment 
period to provide additional opportunity for the public to comment on 
this SNPRM.

Costs of Compliance

    We estimate that this proposed AD affects 37 airplanes of U.S. 
registry.
    We also estimate that it would take about 17 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 $53,465, or $1,445 
per product.
    In addition, we estimate that any on-condition repairs would take 
about 45 work-hours and would require parts costing $0, for a cost of 
$3,825 per product. We have no way of determining the number of 
aircraft that might need these repairs.
    According to the manufacturer, some of the costs of this proposed 
AD may be covered under warranty, thereby reducing the cost impact on 
affected individuals. We do not control warranty coverage for affected 
individuals. As a result, we have included all available costs in our 
cost estimate.

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.

[[Page 22909]]

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-2016-7264; Directorate Identifier 2015-NM-
185-AD.

(a) Comments Due Date

    We must receive comments by July 3, 2017.

(b) Affected ADs

    None.

(c) Applicability

    This AD applies to the Airbus airplanes identified in paragraphs 
(c)(1) and (c)(2) of this AD, certificated in any category.
    (1) Airbus Model A330-201, -202, -203, -223, -223F, -243, -243F, 
-301, -302, -303, -321, -322, -323, -341, -342, and -343 airplanes, 
manufacturer serial numbers identified in Airbus Service Bulletin 
A330-53-3261, Revision 01, dated November 10, 2016; and/or Airbus 
Service Bulletin A330-53-3262, dated June 23, 2015.
    (2) Airbus Model A340-541 and -642 airplanes, manufacturer 
serial numbers 1030, 1040, 1079, 1091, 1102, and 1122.

(d) Subject

    Air Transport Association (ATA) of America Code 53, Fuselage.

(e) Reason

    This AD was prompted by a quality control review on the final 
assembly line, which determined that the wrong aluminum alloy was 
used to manufacture several structural parts. We are issuing this AD 
to detect and replace structural parts made of incorrect aluminum 
alloy. This condition could result in reduced structural integrity 
of the airplane.

(f) Compliance

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

(g) One-time Measurement

    Except as provided by paragraph (i) of this AD: Within 6 years 
after the effective date of this AD, but not exceeding 12 years 
since the date of issuance of the original certificate of 
airworthiness or the date of issuance of the original export 
certificate of airworthiness; do a one-time eddy current 
conductivity measurement of the cabin and cargo compartment 
structural parts identified in the ``Affected Part Number'' column 
of table 1 to paragraphs (g) and (h) of this AD to determine if an 
incorrect aluminum alloy was used, in accordance with the 
Accomplishment Instructions of the applicable service information 
identified in paragraph (g)(1), (g)(2), or (g)(3) of this AD.
    (1) For cargo compartment structural parts for Model A330 
airplanes: Airbus Service Bulletin A330-53-3261, Revision 01, 
including Appendixes 01, 02, and 03, dated November 10, 2016.
    (2) For cabin structural parts for Model A330 airplanes: Airbus 
Service Bulletin A330-53-3262, including Appendixes 01 and 02, dated 
June 23, 2015; except part number F5377004320300, which is located 
in the ``cabin'' area, but must be inspected in accordance with 
Airbus Service Bulletin A330-53-3261, Revision 01, including 
Appendixes 01, 02, and 03, dated November 10, 2016.
    (3) For cargo compartment structural parts for Model A340 
airplanes: Airbus Service Bulletin A340-53-5072, including 
Appendixes 01 and 02, dated June 23, 2015.

  Table 1 to Paragraphs (g) and (h) of This AD--Parts To Be Inspected/
                                Installed
------------------------------------------------------------------------
                               Acceptable  replacement
   Affected  part number             part number               Area
------------------------------------------------------------------------
F5347126620600               F5347126620000               Cabin.
F5347126621000               F5347126620400               Cabin.
F5377004320300               F5377004320351               Cabin.
F5347170420400               F5347170420400               Cargo.
F5347170420600               F5347170420600               Cargo.
G5367131300000               G5367131300000               Cargo.
G5367173700000               G5367173700000               Cargo.
G5367173800000               G5367173800000               Cargo.
------------------------------------------------------------------------

(h) Replacement

    If during the inspection required by paragraph (g) of this AD, 
any affected part having a part number specified in table 1 to 
paragraphs (g) and (h) of this AD is found to have a measured value 
greater than that specified in Figure A-GFAAA, Sheet 02, 
``Inspection Flowchart,'' of the applicable service information 
identified in paragraphs (g)(1), (g)(2), and (g)(3) of this AD, 
except as provided by paragraph (i) of this AD: Within 6 years after 
the effective date of this AD, but not exceeding 12 years since the 
date of issuance of the original certificate of airworthiness or the 
date of issuance of the original export certificate of 
airworthiness, replace the affected part with an acceptable 
replacement part having a part number specified in table 1 to 
paragraphs (g) and (h) of this AD, in accordance with the 
Accomplishment Instructions of the applicable service information 
identified in paragraph (g)(1), (g)(2), or (g)(3) of this AD.

(i) Exception to Certain Service Information

    Where Figure A-GFAAA, Sheet 02, ``Inspection Flowchart,'' of the 
service information identified in paragraphs (g)(2) and (g)(3) of 
this AD specifies to ``do the conductivity ([sigma]) measurement 
with 60kHz (refer to Appendix 01) [sigma]480 = __ MS/m,'' the 
correct conductivity measurement is ``[sigma]60 = __ MS/m.''

(j) Additional Inspection for Certain Airplanes

    For Model A330 airplanes on which the inspection and 
replacement, as applicable, specified in paragraphs (g) and (h) of 
this AD were done before the effective date of this AD, in 
accordance with Airbus Service Bulletin A330-53-3261, dated June 23, 
2015: Within 6 years after the effective date of this AD, but not 
exceeding 12 years since the date of issuance of the original 
certificate of airworthiness or the date of issuance of the original 
export certificate of airworthiness, do a one-time eddy current 
conductivity measurement of structural parts having part number (P/
N) G5367131300000, P/N G5367173700000, and P/N G5367173800000, 
located in fuselage section 15, in accordance with the ``Additional 
Work'' section of the Accomplishment Instructions of Airbus Service 
Bulletin A330-53-3261, Revision 01, including Appendixes 01, 02, and 
03, dated November 10, 2016.

(k) Replacement

    If during the inspection required by paragraph (j) of this AD, 
any affected part having a part number specified in paragraph (j) of 
this AD is found to have a measured value greater than that 
specified in Figure A-GFAAA, Sheet 02, ``Inspection Flowchart,'' of 
Airbus Service Bulletin A330-53-3261, Revision 01, including 
Appendixes 01, 02, and 03, dated November 10, 2016: Within 6 years 
after the effective date of this AD, but not exceeding 12 years 
since the date of issuance of the original certificate of 
airworthiness or the date of issuance of the original export 
certificate of airworthiness, replace the affected part with an 
acceptable replacement part having a part number specified in table 
1 to paragraphs (g) and (h) of this AD, in accordance with the 
Accomplishment Instructions of Airbus Service Bulletin A330-53-3261, 
Revision 01, including Appendixes 01, 02, and 03, dated November 10, 
2016.

(l) 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 the person 
identified in paragraph (m)(2) of this AD. 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.
    (2) Contacting the Manufacturer: For any requirement in this AD 
to obtain corrective actions from a manufacturer, the action must

[[Page 22910]]

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): 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.

(m) Related Information

    (1) Refer to Mandatory Continuing Airworthiness Information 
(MCAI) EASA Airworthiness Directive 2017-0021, dated February 8, 
2017, 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-2016-7264.
    (2) For more information about this AD, 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.
    (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.

    Issued in Renton, Washington, on May 8, 2017.
Michael Kaszycki,
Acting Manager, Transport Airplane Directorate, Aircraft Certification 
Service.
[FR Doc. 2017-10035 Filed 5-18-17; 8:45 am]
 BILLING CODE 4910-13-P