[Federal Register Volume 81, Number 91 (Wednesday, May 11, 2016)]
[Proposed Rules]
[Pages 29209-29212]
From the Federal Register Online via the Government Publishing Office [www.gpo.gov]
[FR Doc No: 2016-11094]


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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]
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 
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 proposed 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 proposed AD would 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 proposing 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.

DATES: We must receive comments on this proposed AD by June 27, 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: Deliver to Mail address above between 9 
a.m. and 5 p.m., Monday through Friday, except Federal holidays.
    For service information identified in this NPRM, 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.

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-
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 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: 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: 

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-2016-6431; 
Directorate Identifier 2015-NM-182-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 
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.

Related Service Information Under 1 CFR Part 51

    Airbus has issued the following service information:
     Airbus Service Bulletin A320-53-1292, dated July 23, 2015; 
including Appendices 01 and 02, dated July 23, 2015.
     Airbus Service Bulletin A320-53-1293, dated July 30, 2015; 
including Appendices 01 and 02, dated July 30, 2015.
     Airbus Service Bulletin A320-53-1294, dated July 23, 2015; 
including Appendices 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. 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.

[[Page 29210]]

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

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-2016-6431; Directorate Identifier 2015-NM-
182-AD.

(a) Comments Due Date

    We must receive comments by June 27, 2016.

(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 (h) 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.
    (1) For cabin structural parts: Airbus Service Bulletin A320-53-
1292, dated July 23, 2015; including Appendices 01 and 02, dated 
July 23, 2015.
    (2) For cargo compartment structural parts: Airbus Service 
Bulletin A320-53-1293, dated July 30, 2015; including Appendices 01 
and 02, dated July 30, 2015.
    (3) For frame structural parts: Airbus Service Bulletin A320-53-
1294, dated July 23, 2015; including Appendices 01 and 02, dated 
July 23, 2015.

  Table 1 to Paragraphs (g) and (h) of this AD--Parts to be Inspected/
                                Installed
                 [Airbus Service Bulletin A320-53-1292]
------------------------------------------------------------------------
                                      Acceptable
         Affected P/N              replacement P/N            Area
------------------------------------------------------------------------
D2127245500000................  D2127245500000.......  Cabin
D2127247600200................  D2127247600200.......  Cabin

[[Page 29211]]

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


  Table 2 to Paragraphs (g) and (h) of this AD--Parts to be Inspected/
                                Installed
                 [Airbus Service Bulletin A320-53-1293]
------------------------------------------------------------------------
                                      Acceptable
         Affected P/N              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 (h) of this AD--Parts to be Inspected/
                                Installed
                 [Airbus Service Bulletin A320-53-1294]
------------------------------------------------------------------------
                                      Acceptable
         Affected P/N              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
------------------------------------------------------------------------


[[Page 29212]]

(h) Replacement

    If during the measurement required by paragraph (g) of this AD, 
any affected P/N specified in table 1, 2, or 3 to paragraphs (g) and 
(h) 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 (h) 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.

(i) 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. 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 EASA; 
or Airbus's EASA 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.

(j) Related Information

    (1) 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.
    (2) 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. 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 4, 2016.
Michael Kaszycki,
Acting Manager, Transport Airplane Directorate, Aircraft Certification 
Service.
[FR Doc. 2016-11094 Filed 5-10-16; 8:45 am]
 BILLING CODE 4910-13-P