81 FR 21486 - Airworthiness Directives; Airbus Airplanes

DEPARTMENT OF TRANSPORTATION
Federal Aviation Administration

Federal Register Volume 81, Issue 70 (April 12, 2016)

We propose to adopt a new airworthiness directive (AD) for all Airbus Model A330-200 Freighter, -200, and -300 series airplanes. This proposed AD was prompted by a report of a manufacturing defect that affects the durability of affected parts in the cargo and cabin compartment. This proposed AD would require an inspection of affected structural parts in the cargo and cabin compartments to determine if proper heat-treatment has been done, and replacement if necessary. We are proposing this AD to prevent crack initiation and propagation, which could result in reduced structural integrity of the fuselage.

[Federal Register Volume 81, Number 70 (Tuesday, April 12, 2016)]
[Proposed Rules]
[Pages 21486-21488]
From the Federal Register Online  [www.thefederalregister.org]
[FR Doc No: 2016-08253]


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DEPARTMENT OF TRANSPORTATION

Federal Aviation Administration

14 CFR Part 39

[Docket No. FAA-2016-5460; Directorate Identifier 2015-NM-188-AD]
RIN 2120-AA64


Airworthiness Directives; Airbus Airplanes

AGENCY: Federal Aviation Administration (FAA), DOT.

ACTION: Notice of proposed rulemaking (NPRM).

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SUMMARY: We propose to adopt a new airworthiness directive (AD) for all 
Airbus Model A330-200 Freighter, -200, and -300 series airplanes. This 
proposed AD was prompted by a report of a manufacturing defect that 
affects the durability of affected parts in the cargo and cabin 
compartment. This proposed AD would require an inspection of affected 
structural parts in the cargo and cabin compartments to determine if 
proper heat-treatment has been done, and replacement if necessary. We 
are proposing this AD to prevent crack initiation and propagation, 
which could result in reduced structural integrity of the fuselage.

DATES: We must receive comments on this proposed AD by May 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: U.S. Department of Transportation, Docket 
Operations, M-30, West Building Ground Floor, Room W12-140, 1200 New 
Jersey Avenue SE., Washington, DC, between 9 a.m. and 5 p.m., Monday 
through Friday, except Federal holidays.
    For service information identified in this NPRM, contact Airbus 
SAS, Airworthiness Office-EAL, 1 Rond Point Maurice Bellonte, 31707 
Blagnac Cedex, France; telephone: +33 5 61 93 36 96; fax: +33 5 61 93 
45 80; email: [email protected]; Internet: http://www.airbus.com. You may view this referenced service information at the 
FAA, Transport Airplane Directorate, 1601 Lind Avenue SW., Renton, WA. 
For information on the availability of this material at the FAA, call 
425-227-1221.

Examining the AD Docket

    You may examine the AD docket on the Internet at http://www.regulations.gov by searching for and locating Docket No. FAA-2016-
5460; or in person at the Docket Management Facility between 9 a.m. and 
5 p.m., Monday through Friday, except Federal holidays. The AD docket 
contains this proposed AD, the regulatory evaluation, any comments 
received, and other information. The street address for the Docket 
Operations office (telephone 800-647-5527) is in the ADDRESSES section. 
Comments will be available in the AD docket shortly after receipt.

FOR FURTHER INFORMATION CONTACT: Vladimir Ulyanov, Aerospace Engineer, 
International Branch, ANM-116, Transport Airplane Directorate, FAA, 
1601 Lind Avenue SW., Renton, WA 98057-3356; telephone: 425-227-1138; 
fax: 425-227-1149.

SUPPLEMENTARY INFORMATION: 

Comments Invited

    We invite you to send any written relevant data, views, or 
arguments about this proposed AD. Send your comments to an address 
listed under the ADDRESSES section. Include ``Docket No. FAA-2016-5460; 
Directorate Identifier 2015-NM-188-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

[[Page 21487]]

for the Member States of the European Union, has issued European 
Airworthiness Directive 2015-0212, dated November 4, 2015, to correct 
an unsafe condition for all Airbus Model A330-200 Freighter, -200, and 
-300 series airplanes. The MCAI states:

    Airbus quality controls identified that several structural 
parts, intended for cargo or cabin compartment installation, were 
manufactured from improperly heat-treated materials. Subsequent 
review identified that some of those parts were installed on 
airplanes manufactured between November 2011 and February 2013. From 
February 2013, Airbus implemented measures into manufacturing 
processes to ensure detection and to prevent installation of such 
non-conforming parts.
    A detailed safety assessment was accomplished to identify the 
possible impact of affected parts on the airplane structure. The 
result of this structural analysis demonstrated the capability of 
the affected structure to sustain static limit loads, but failed to 
confirm that the affected structures met the certified fatigue life.
    This condition, if not detected and corrected, could lead to 
crack initiation and propagation, possibly resulting in reduced 
structural integrity of the fuselage.
    To address this potentially unsafe condition, Airbus issued 
[Mandatory] Service Bulletin (SB) SB A330-53-3227 and SB A330-53-
3228 to provide inspection instructions for affected cargo and cabin 
structural parts respectively.
    For the reasons described above, this [EASA] AD requires a one-
time Special Detailed Inspection (SDI) [eddy current inspection] to 
measure the electrical conductivity of affected structural parts, to 
identify the presence or absence of heat treatment, and, depending 
on findings, corrective action [replacement].

    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-
5460.

Related Service Information Under 1 CFR Part 51

    Airbus has issued the following service information:
     Airbus Mandatory Service Bulletin A330-53-3227, dated 
August 18, 2015. The service information describes procedures to 
inspect affected structural parts in the cargo compartment to determine 
if proper heat-treatment has been done, and replacement of parts; and
     Airbus Mandatory Service Bulletin A330-53-3228, dated 
August 18, 2015. The service information describes procedures to 
inspect affected structural parts in the cabin compartment to determine 
if proper heat-treatment has been done, and replacement of parts.
    This service information is reasonably available because the 
interested parties have access to it through their normal course of 
business or by the means identified in the ADDRESSES section.

FAA's Determination and Requirements of This Proposed AD

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

Differences Between This Proposed AD and the Service Information

    Figure A-GFAAA, Sheet 01, ``Inspection Flowchart,'' of Airbus 
Mandatory Service Bulletin A330-53-3227, dated August 18, 2015; and 
Figure A-GFAAA, Sheet 01, ``Inspection Flowchart'' of Airbus Mandatory 
Service Bulletin A330-53-3228, dated August 18, 2015, note that if any 
other measured (conductivity) value is found, to check the non-
destructive test (NDT) tool and perform a new measurement; and if that 
measured value is confirmed, contact Airbus for further instructions. 
This proposed AD would require that if a measured value is confirmed 
that is outside the measurements specified in the service information, 
a repair must be done using a method approved by the Manager, 
International Branch, ANM-116, Transport Airplane Directorate, FAA; or 
EASA; or Airbus's EASA Design Organization Approval (DOA).

Costs of Compliance

    We estimate that this proposed AD affects 20 airplanes of U.S. 
registry.
    We also estimate that it will take about 11 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 $18,700, or $935 
per product.
    In addition, we estimate that any necessary follow-on actions would 
take about 45 work-hours for a cost of $3,825 per product. We have 
received no definitive data that would enable us to provide cost of the 
parts for the on-condition actions specified in this proposed AD. We 
have no way of determining the number of aircraft that might need this 
action.
    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 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:

[[Page 21488]]

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-2016-5460; Directorate Identifier 2015-NM-
188-AD.

(a) Comments Due Date

    We must receive comments by May 27, 2016.

(b) Affected ADs

    None.

(c) Applicability

    This AD applies to Airbus Model A330-223F and -243F airplanes; 
A330-201, -202, -203, -223, and -243 airplanes; A330-301, -302, -
303, -321, -322, -323, -341, -342, and -343 airplanes, certificated 
in any category, manufacturer serial numbers 1175, 1180, 1287 
through 1475 inclusive, 1478, 1480, 1483, and 1506.

(d) Subject

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

(e) Reason

    This AD was prompted by a report of a manufacturing defect (i.e. 
improperly heat-treated materials) that affects the durability of 
affected parts in the cargo and cabin compartment. We are issuing 
this AD to prevent crack initiation and propagation, which could 
result in reduced structural integrity of the fuselage.

(f) Compliance

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

(g) Inspection of Affected Structure in the Cargo Compartment

    Within 72 months since first flight of the airplane, do an eddy 
current inspection (i.e., conductivity measurement) of affected 
structural parts in the cargo compartment to determine if proper 
heat treatment has been done as identified in, and in accordance 
with, the Accomplishment Instructions of Airbus Service Bulletin 
A330-53-3227, dated August 18, 2015.

(h) Replacement of Non-Conforming Parts in the Cargo Compartment

    If, during the inspection required by paragraph (g) of this AD, 
an affected structural part in the cargo compartment is identified 
to have a measured value greater than 26 megasiemens per meter (MS/
m) or greater than 44.8% International Annealed Copper Standard 
(IACS), before further flight, replace the affected structural part 
with a serviceable part, in accordance with the Accomplishment 
Instructions of Airbus Mandatory Service Bulletin A330-53-3227, 
dated August 18, 2015.

(i) Repair of Non-Conforming Parts in the Cargo Compartment

    If, during the inspection required by paragraph (g) of this AD, 
an affected structural part in the cargo compartment is identified 
to have a measured value other than those specified in Figure A-
GFAAA, Sheet 01, ``Inspection Flowchart,'' of Airbus Mandatory 
Service Bulletin A320-53-3227, dated August 18, 2015, before further 
flight, repair 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).

(j) Inspection of Affected Structure in the Cabin Compartment

    Within 72 months since first flight of the airplane, do an eddy 
current inspection of affected structural parts in the cargo 
compartment to determine if proper heat treatment has been done as 
identified in, and in accordance with, the Accomplishment 
Instructions of Airbus Mandatory Service Bulletin A330-53-3228, 
dated August 18, 2015.

(k) Replacement of Non-Conforming Parts in the Cabin Compartment

    If, during the inspection required by paragraph (j) of this AD, 
an affected structural part in the cabin compartment is identified 
to have a measured value greater than 26 MS/m or greater than 44.8% 
IACS, before further flight, replace the affected structural part 
with a serviceable part, in accordance with the Accomplishment 
Instructions of Airbus Mandatory Service Bulletin A330-53-3228, 
dated August 18, 2015.

(l) Repair of Non-Conforming Parts in the Cargo Compartment

    If, during the inspection required by paragraph (j) of this AD, 
an affected structural part in the cargo compartment is identified 
to have a measured value other than those specified in Figure A-
GFAAA, Sheet 01, ``Inspection Flowchart,'' of Airbus Service 
Bulletin A320-53-3228, dated August 18, 2015, before further flight, 
repair 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).

(m) Other FAA AD Provisions

    The following provisions also apply to this AD:
    (1) Alternative Methods of Compliance (AMOCs): The Manager, 
International Branch, ANM-116, Transport Airplane Directorate, FAA, 
has the authority to approve AMOCs for this AD, if requested using 
the procedures found in 14 CFR 39.19. In accordance with 14 CFR 
39.19, send your request to your principal inspector or local Flight 
Standards District Office, as appropriate. If sending information 
directly to the International Branch, send it to ATTN: Vladimir 
Ulyanov, Aerospace Engineer, International Branch, ANM-116, 
Transport Airplane Directorate, FAA, 1601 Lind Avenue SW., Renton, 
WA 98057-3356; telephone: 425-227-1138; fax: 425-227-1149. 
Information may be emailed to: [email protected]. 
Before using any approved AMOC, notify your appropriate principal 
inspector, or lacking a principal inspector, the manager of the 
local flight standards district office/certificate holding district 
office. The AMOC approval letter must specifically reference this 
AD.
    (2) Contacting the Manufacturer: For any requirement in this AD 
to obtain corrective actions from a manufacturer, the action must be 
accomplished using a method approved by the Manager, International 
Branch, ANM-116, Transport Airplane Directorate, FAA; or the 
European Aviation Safety Agency (EASA); or Airbus's EASA Design 
Organization Approval (DOA). If approved by the DOA, the approval 
must include the DOA-authorized signature.
    (3) Required for Compliance (RC): If any service information 
contains procedures or tests that are identified as RC, those 
procedures and tests must be done to comply with this AD; any 
procedures or tests that are not identified as RC are recommended. 
Those procedures and tests that are not identified as RC may be 
deviated from using accepted methods in accordance with the 
operator's maintenance or inspection program without obtaining 
approval of an AMOC, provided the procedures and tests identified as 
RC can be done and the airplane can be put back in an airworthy 
condition. Any substitutions or changes to procedures or tests 
identified as RC require approval of an AMOC.

(n) Related Information

    (1) Refer to Mandatory Continuing Airworthiness Information 
(MCAI) EASA AD 2015-0212, dated November 4, 2015, for related 
information. You may examine the MCAI on the Internet at http://www.regulations.gov by searching for and locating Docket No. FAA-
2016-5460.
    (2) For service information identified in this AD, contact 
Airbus SAS, Airworthiness Office-EAL, 1 Rond Point Maurice Bellonte, 
31707 Blagnac Cedex, France; telephone: +33 5 61 93 36 96; fax: +33 
5 61 93 45 80; email: [email protected]; Internet: 
http://www.airbus.com. You may view this service information at the 
FAA, Transport Airplane Directorate, 1601 Lind Avenue SW., Renton, 
WA. For information on the availability of this material at the FAA, 
call 425-227-1221.

    Issued in Renton, Washington, on March 30, 2016.
Victor Wicklund,
Acting Manager, Transport Airplane Directorate, Aircraft Certification 
Service.
[FR Doc. 2016-08253 Filed 4-11-16; 8:45 am]
BILLING CODE 4910-13-P