[Federal Register Volume 82, Number 165 (Monday, August 28, 2017)]
[Rules and Regulations]
[Pages 40670-40672]
From the Federal Register Online via the Government Publishing Office [www.gpo.gov]
[FR Doc No: 2017-17536]



[[Page 40670]]

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DEPARTMENT OF TRANSPORTATION

Federal Aviation Administration

14 CFR Part 39

[Docket No. FAA-2016-7264; Product Identifier 2015-NM-185-AD; Amendment 
39-18998; AD 2017-17-08]
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 certain 
Airbus Model A330-200, -200 Freighter, and -300 series airplanes; and 
Model A340-500 and -600 series airplanes. 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. This AD requires 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. We are issuing this AD to 
address the unsafe condition on these products.

DATES: This AD is effective October 2, 2017.
    The Director of the Federal Register approved the incorporation by 
reference of certain publications listed in this AD as of October 2, 
2017.

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 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-2016-
7264.

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 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 Section, Transport Standards Branch, FAA, 1601 Lind 
Avenue SW., Renton, WA 98057-3356; telephone 425-227-1138; fax 425-227-
1149.

SUPPLEMENTARY INFORMATION: 

Discussion

    We issued a supplemental notice of proposed rulemaking (SNPRM) 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 SNPRM published in the Federal 
Register on May 19, 2017 (82 FR 22907) (``the SNPRM''). We preceded the 
SNPRM with a notice of proposed rulemaking (NPRM) that published in the 
Federal Register on June 21, 2016 (81 FR 40201) (``the NPRM''). 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 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 SNPRM proposed to require new inspection 
locations for certain airplanes, and removing incorrect part numbers. 
We are issuing this AD to detect and replace structural parts made of 
an incorrect aluminum alloy. This condition could result in reduced 
structural integrity 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 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.
    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.

Comments

    We gave the public the opportunity to participate in developing 
this AD. We received no comments on the SNPRM or on the determination 
of the cost to the public.

Conclusion

    We reviewed the relevant data 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:
     Are consistent with the intent that was proposed in the 
SNPRM for correcting the unsafe condition; and
     Do not add any additional burden upon the public than was 
already proposed in the SNPRM.

Related Service Information Under 1 CFR Part 51

    Airbus has issued 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.

[[Page 40671]]

     Airbus Service Bulletin A340-53-5072, including Appendixes 
01 and 02, dated June 23, 2015.
    This 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. These 
documents are distinct because they apply 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.

Costs of Compliance

    We estimate that this AD affects 37 airplanes of U.S. registry.
    We also estimate that it takes about 17 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 $53,465, or $1,445 per product.
    In addition, we estimate that any on-condition repairs take about 
45 work-hours and will 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 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.
    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 adding the following new airworthiness 
directive (AD):

2017-17-08 Airbus: Amendment 39-18998; Docket No. FAA-2016-7264; 
Product Identifier 2015-NM-185-AD.

(a) Effective Date

    This AD is effective October 2, 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, including Appendixes 01, 02, and 03, 
dated November 10, 2016; and/or Airbus Service Bulletin A330-53-
3262, including Appendixes 01 and 02, 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 an 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.

[[Page 40672]]



  Table 1 to Paragraphs (g) and (h) of This AD--Parts To Be Inspected/
                                Installed
------------------------------------------------------------------------
                                          Acceptable
         Affected part No.           replacement part No.       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 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 manager of the International Section, send it to the 
attention of 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 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 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 Section, Transport 
Standards Branch, FAA, 1601 Lind Avenue SW., Renton, WA 98057-3356; 
telephone 425-227-1138; fax 425-227-1149.

(n) 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 A330-53-3261, Revision 01, including 
Appendixes 01, 02, and 03, dated November 10, 2016.
    (ii) Airbus Service Bulletin A330-53-3262, including Appendixes 
01 and 02, dated June 23, 2015.
    (iii) Airbus Service Bulletin A340-53-5072, including Appendixes 
01 and 02, dated June 23, 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.
    (4) 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.
    (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 August 9, 2017.
Dionne Palermo,
Acting Director, System Oversight Division, Aircraft Certification 
Service.
[FR Doc. 2017-17536 Filed 8-25-17; 8:45 am]
 BILLING CODE 4910-13-P