[Federal Register Volume 82, Number 47 (Monday, March 13, 2017)]
[Rules and Regulations]
[Pages 13382-13385]
From the Federal Register Online via the Government Publishing Office [www.gpo.gov]
[FR Doc No: 2017-04657]


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DEPARTMENT OF TRANSPORTATION

Federal Aviation Administration

14 CFR Part 39

[Docket No. FAA-2016-6431; Directorate Identifier 2015-NM-182-AD; 
Amendment 39-18823; AD 2017-05-12]
RIN 2120-AA64


Airworthiness Directives; Airbus Airplanes

AGENCY: Federal Aviation Administration (FAA), Department of 
Transportation (DOT).

ACTION: Final rule.

-----------------------------------------------------------------------

SUMMARY: We are adopting a new airworthiness directive (AD) for certain 
Airbus Model A318-112 airplanes, A319-111, -112, -115, -132, and -133 
airplanes, A320-214, -232, and -233 airplanes, and A321-211, -212, -
213, -231, and -232 airplanes. This AD was prompted by a quality 
control review on the final assembly line, which determined that 
aluminum alloy with inadequate heat treatment had been delivered and 
used on several structural parts. This AD requires a one-time eddy 
current conductivity measurement of certain cabin, cargo compartment, 
and frame structural parts to determine if aluminum alloy with 
inadequate heat treatment was used, and replacement if necessary. We 
are issuing this AD to address the unsafe condition on these products.

DATES: This AD is effective April 17, 2017.
    The Director of the Federal Register approved the incorporation by 
reference of certain publications listed in this AD as of April 17, 
2017.

ADDRESSES: For service information identified in this final rule, 
contact Airbus, Airworthiness Office--EIAS, 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 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-2016-6431.

Examining the AD Docket

    You may examine the AD docket on the Internet at http://www.regulations.gov by searching for

[[Page 13383]]

and locating Docket No. FAA-2016-6431; 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: Sanjay Ralhan, Aerospace Engineer, 
International Branch, ANM-116, Transport Airplane Directorate, FAA, 
1601 Lind Avenue SW., Renton, WA 98057-3356; telephone: 425-227-1405; 
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 certain Airbus Model A318-
112 airplanes, A319-111, -112, -115, -132, and -133 airplanes, A320-
214, -232, and -233 airplanes, and A321-211, -212, -213, -231, and -232 
airplanes. The NPRM published in the Federal Register on May 11, 2016 
(81 FR 29209). The NPRM was prompted by a quality control review on the 
final assembly line, which determined that aluminum alloy with 
inadequate heat treatment had been delivered and used on several 
structural parts. The NPRM proposed to require a one-time eddy current 
conductivity measurement of certain cabin, cargo compartment, and frame 
structural parts to determine if aluminum alloy with inadequate heat 
treatment was used, and replacement if necessary. We are issuing this 
AD to detect and replace structural parts made of aluminum alloy with 
inadequate heat treatment. 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 2015-0219, dated November 3, 2015 (referred to 
after this as the Mandatory Continuing Airworthiness Information, or 
``the MCAI''), to correct an unsafe condition for certain Airbus Model 
A318-112 airplanes, A319-111, -112, -115, -132, and -133 airplanes, 
A320-214, -232, and -233 airplanes, and A321-211, -212, -213, -231, and 
-232 airplanes. The MCAI states:

    Following an Airbus quality control review on the final assembly 
line, it was discovered that aluminum alloy with inadequate heat 
treatment were delivered by a supplier for several structural parts. 
The results of the investigations highlighted that 1% of the stock 
could be impacted by this wrong material.
    Structural investigations demonstrated the capability to sustain 
the static limits loads, and sufficient fatigue life up to a certain 
inspection threshold.
    This condition, if not detected and corrected, could reduce the 
aeroplane structural integrity following fatigue load.
    To address this potential unsafe condition, Airbus issued 
Service Bulletin (SB) A320-53-1292, SB A320-53-1293, and SB A320-53-
1294 to provide inspection instructions.
    For the reasons described above, this [EASA] AD requires a one-
time Special Detailed Inspection (SDI) [i.e., eddy current 
conductivity measurement] of certain cabin, cargo compartment and 
frame parts [for material identification] and, depending on 
findings, replacement with serviceable parts.

    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-
6431.

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.

Request To Include the Correction in the Technical Adaptation to 
Certain Service Information

    Virgin America asked that we include the correction in Airbus 
Technical Adaptation (TA) 80095365/011/2016, Issue 1, dated December 1, 
2016, to Figure A-GVAAA and Figure A-GRAAA of Airbus Service Bulletin 
A320-53-1293, dated July 30, 2015, in this AD. Virgin America stated 
that the parts shown in Figure A-GVAAA and Figure A-GRAAA and 
highlighted for inspection are the four hinge brackets identified as 
having part number (P/N) ``D4918518320201, A-profile.'' However, the 
correct identification is P/N ``D4918518320200, A-profile.'' Virgin 
America noted that Airbus issued TA 80095365/011/2016, Issue 1, to 
update Figure A-GVAAA and Figure A-GRAAA of Airbus Service Bulletin 
A320-53-1293, dated July 30, 2015, to identify the correct part number. 
Virgin America also stated that the TA specified that Airbus Service 
Bulletin A320-53-1293 is currently under revision and the correction 
will be included when the revision is issued.
    We agree with the commenter's request to include the specified 
correction. We have added a new paragraph (h) to this AD to provide an 
exception to Figure A-GVAAA of Airbus Service Bulletin A320-53-1293, 
dated July 30, 2015, which is needed for compliance with paragraph (g) 
of this AD. However, Figure A-GRAAA, ``Reporting Sheet,'' of Airbus 
Service Bulletin A320-53-1293, dated July 30, 2015, is not needed for 
compliance with this AD. We have added a note to paragraph (h) of this 
AD to provide the information in Airbus Technical Adaptation (TA) 
80095365/011/2016, Issue 1, dated December 1, 2016, which specifies the 
corrected information for Figure A-GVAAA and Figure A-GRAAA of Airbus 
Service Bulletin A320-53-1293, dated July 30, 2015. We have also added 
paragraph (j) to clarify that reporting is not required by this AD; 
however, reporting is recommended for research and tracking. We have 
redesignated subsequent paragraphs accordingly.

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

    We reviewed the following service information:
     Airbus Service Bulletin A320-53-1292, dated July 23, 2015; 
including Appendixes 01 and 02, dated July 23, 2015.
     Airbus Service Bulletin A320-53-1293, dated July 30, 2015; 
including Appendixes 01 and 02, dated July 30, 2015.
     Airbus Service Bulletin A320-53-1294, dated July 23, 2015; 
including Appendixes 01 and 02, dated July 23, 2015.
    The service information describes procedures for a one-time eddy 
current conductivity measurement of certain cabin, cargo compartment, 
and frame structural parts to determine if aluminum alloy with 
inadequate heat treatment was used, and replacement of any affected 
part with a serviceable part. These documents are distinct since they

[[Page 13384]]

apply to different parts on the airplane. 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 46 airplanes of U.S. registry.
    We also estimate that it takes about 6 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 $23,460, or $510 per product.
    We have received no definitive data that enables us to provide cost 
estimates for the on-condition actions specified in this AD.
    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.

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):

2017-05-12 Airbus: Amendment 39-18823; Docket No. FAA-2016-6431; 
Directorate Identifier 2015-NM-182-AD.

(a) Effective Date

    This AD is effective April 17, 2017.

(b) Affected ADs

    None.

(c) Applicability

    This AD applies to the Airbus airplanes identified in paragraphs 
(c)(1) through (c)(4) of this AD, certificated in any category; 
manufacturer serial numbers 4895, 4903, 4911, 4919, 4929, 4938, 
4942, 4944, 4946, 4948, and 4951, 4956 through 5541 inclusive, 5544, 
5547, 5550, 5551, 5553, 5556, 5559, 5561, 5562, 5563, 5565, 5566, 
5570, 5572, 5576, and 5578.
    (1) Airbus Model A318-112 airplanes.
    (2) Airbus Model A319-111, -112, -115, -132, and -133 airplanes.
    (3) Airbus Model A320-214, -232, and -233 airplanes.
    (4) Airbus Model A321-211, -212, -213, -231, and -232 airplanes.

(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 aluminum alloy with inadequate 
heat treatment had been delivered and used on several structural 
parts. We are issuing this AD to detect and replace structural parts 
made of aluminum alloy with inadequate heat treatment. 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

    Within 6 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, cargo compartment, and frame 
structural parts identified in the ``Affected P/N (part number)'' 
column of tables 1, 2, and 3 to paragraphs (g) and (i) of this AD to 
determine if aluminum alloy with inadequate heat treatment was used, 
in accordance with the Accomplishment Instructions of the applicable 
service information identified in paragraphs (g)(1), (g)(2), and 
(g)(3) of this AD, except as required by paragraph (h) of this AD.
    (1) For cabin structural parts: Airbus Service Bulletin A320-53-
1292, dated July 23, 2015; including Appendixes 01 and 02, dated 
July 23, 2015.
    (2) For cargo compartment structural parts: Airbus Service 
Bulletin A320-53-1293, dated July 30, 2015; including Appendixes 01 
and 02, dated July 30, 2015.
    (3) For frame structural parts: Airbus Service Bulletin A320-53-
1294, dated July 23, 2015; including Appendixes 01 and 02, dated 
July 23, 2015.

  Table 1 to Paragraphs (g) and (i) of This AD--Parts To Be Inspected/
                                Installed
                 [Airbus Service Bulletin A320-53-1292]
------------------------------------------------------------------------
        Affected P/N          Acceptable replacement P/N       Area
------------------------------------------------------------------------
D2127245500000               D2127245500000               Cabin.
D2127247600200               D2127247600200               Cabin.
D2127247600300               D2127247600300               Cabin.
D2127399900200               D2127399900200               Cabin.
D2127399900300               D2127399900300               Cabin.
D2127698900800               D2127698900800               Cabin.
D2127698902400               D2127698902400               Cabin.
D2527075131200               D2527075131251               Cabin.
D2527075131300               D2527075131351               Cabin.
D2527075138000               D2527075138000               Cabin.
D2527075138100               D2527075138100               Cabin.
D2527075138200               D2527075138200               Cabin.
D2527075138300               D2527075138300               Cabin.
D2527075138600               D2527075138651               Cabin.
D2527075138800               D2527075138851               Cabin.
D2527240220600               D2527240220651               Cabin.
D2527240220700               D2527240220751               Cabin.
D2527240220800               D2527240220851               Cabin.
D9249591201000               D9249591201000               Cabin.
D9249591201800               D9249591201800               Cabin.
D9249591227800               D9249591227851               Cabin.
D9249591227900               D9249591227951               Cabin.
D9249591228000               D9249591228051               Cabin.
D9249591228100               D9249591228151               Cabin.
------------------------------------------------------------------------


[[Page 13385]]


  Table 2 to Paragraphs (g) and (i) of This AD--Parts To Be Inspected/
                                Installed
                 [Airbus Service Bulletin A320-53-1293]
------------------------------------------------------------------------
        Affected P/N          Acceptable replacement P/N       Area
------------------------------------------------------------------------
D2707033520000               D2707033520000               Cargo.
D2827027120000               D2827027120000               Cargo.
D2827093500400               D2827093500400               Cargo.
D2907013701200               D2907013701251               Cargo.
D2907013800400               D2907013800451               Cargo.
D3247012900000               D3247012900051               Cargo.
D3817003820000               D3817003820000               Cargo.
D3817012320200               D3817012320251               Cargo.
D3837021201600               D3837021201600               Cargo.
D3837033300400               D3837033300400               Cargo.
D4918518320200               D4918518320200               Cargo.
D5347043420400               D5347043420451               Cargo.
D9248511000000               D9248511000051               Cargo.
D9249254100200               D9249254100251               Cargo.
D9249282300000               D9249282300000               Cargo.
------------------------------------------------------------------------


  Table 3 to Paragraphs (g) and (i) of This AD--Parts To Be Inspected/
                                Installed
                 [Airbus Service Bulletin A320-53-1294]
------------------------------------------------------------------------
        Affected P/N          Acceptable replacement P/N       Area
------------------------------------------------------------------------
D2827098326800               D2827098326851               Frame.
D5347051620600               D5347051620651               Frame.
D5347051720600               D5347051720651               Frame.
D5347057120000               D5347057120051               Frame.
D5347067520600               D5347067520651               Frame.
D5347067521400               D5347067521451               Frame.
D5347067520800               D5347067520851               Frame.
D5347067521000               D5347067521051               Frame.
D5347067521600               D5347067521651               Frame.
D5347067620600               D5347067620600               Frame.
D5347067720200               D5347067720251               Frame.
D5347067720400               D5347067720451               Frame.
D5347986520200               D5347986520251               Frame.
------------------------------------------------------------------------

(h) Exception to Paragraph (g) of This AD

    Where Subtask 531293-832-207-001 of Airbus Service Bulletin 
A320-53-1293, dated July 23, 2015; including Appendixes 01 and 02, 
dated July 23, 2015, specifies inspecting Item 19 of Figure A-GVAAA 
for material heat treatment conformity, and that figure 
(incorrectly) identifies the inspection area for Item 19 as the four 
hinge brackets adjacent to the A-profile, this AD requires 
inspecting part number D491-85183-202-00, which is the A-profile, 
and not just the brackets.

    Note 1 to paragraph (h) of this AD: Airbus Technical Adaptation 
80095365/011/2016, Issue 1, dated December 1, 2016 (``TA'') 
specifies that for Figure A-GVAAA, Sheet 01, of Airbus Service 
Bulletin A320-53-1293, dated July 30, 2015, Item 19 should point to 
part number D491-85183-202-00 (and not just to the brackets). The TA 
also specifies that for Figure A-GRAAA, Sheet 01, of Airbus Service 
Bulletin A320-53-1293, dated July 30, 2015, the correct Item 19 
identification is part number D491-85183-202-00.

(i) Replacement

    If during the measurement required by paragraph (g) of this AD, 
any affected part number specified in table 1, 2, or 3 to paragraphs 
(g) and (i) of this AD is found to have a measured value greater 
than that specified in Figure A-GFAAA, Sheet 01, ``Inspection 
Flowchart,'' of the applicable service information identified in 
paragraphs (g)(1), (g)(2), and (g)(3) of this AD: Before further 
flight, replace the affected part with the corresponding acceptable 
replacement part specified in table 1, 2, or 3 to paragraphs (g) and 
(i) of this AD, in accordance with the Accomplishment Instructions 
of the applicable service information identified in paragraphs 
(g)(1), (g)(2), and (g)(3) of this AD.

(j) No Reporting Requirement

    Although the service information identified in paragraphs 
(g)(1), (g)(2), and (g)(3) of this AD specifies to submit certain 
information to the manufacturer, this AD does not include that 
requirement.

(k) 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: Sanjay 
Ralhan, Aerospace Engineer, International Branch, ANM-116, Transport 
Airplane Directorate, FAA, 1601 Lind Avenue SW., Renton, WA 98057-
3356; telephone: 425-227-1405; 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.
    (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): 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.

(l) Related Information

    Refer to Mandatory Continuing Airworthiness Information (MCAI) 
EASA AD 2015-0219, dated November 3, 2015, 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-
2016-6431.

(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.
    (i) Airbus Service Bulletin A320-53-1292, dated July 23, 2015; 
including Appendixes 01 and 02, dated July 23, 2015.
    (ii) Airbus Service Bulletin A320-53-1293, dated July 30, 2015; 
including Appendixes 01 and 02, dated July 30, 2015.
    (iii) Airbus Service Bulletin A320-53-1294, dated July 23, 2015; 
including Appendixes 01 and 02, dated July 23, 2015.
    (3) For service information identified in this AD, contact 
Airbus, Airworthiness Office--EIAS, 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.
    (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 March 2, 2017.
Michael Kaszycki,
Acting Manager, Transport Airplane Directorate, Aircraft Certification 
Service.
[FR Doc. 2017-04657 Filed 3-10-17; 8:45 am]
 BILLING CODE 4910-13-P