Airworthiness Directives; Airbus Airplanes, 21486-21488 [2016-08253]
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21486
Federal Register / Vol. 81, No. 70 / Tuesday, April 12, 2016 / Proposed Rules
(1) Airbus Service Bulletin A330–34–3271.
(2) Airbus Service Bulletin A330–34–3286.
(3) Airbus Service Bulletin A330–34–3301.
(4) Airbus Service Bulletin A340–34–4282.
(i) Parts Installation Limitations
As of the effective date of this AD,
installation on an airplane of a T3CAS unit
having a part number specified in paragraph
(g) of this AD is acceptable, provided that,
following installation, the T3CAS unit is
power cycled on a recurrent basis, as
required by paragraph (g) of this AD.
(j) Credit for Previous Actions
This paragraph provides credit for actions
required by paragraph (g) of this AD, if those
actions were performed before the effective
date of this AD using Airbus AOT A34L003–
13, dated November 25, 2013, which is not
incorporated by reference in this AD.
jstallworth on DSK7TPTVN1PROD with PROPOSALS
(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, 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: 9-ANM-116AMOC-REQUESTS@faa.gov. 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.
(l) Related Information
(1) Refer to Mandatory Continuing
Airworthiness Information (MCAI) EASA
Airworthiness Directive 2015–0125, dated
July 1, 2015, corrected on July 3, 2015, for
related information. This MCAI may be
found in the AD docket on the Internet at
https://www.regulations.gov by searching for
and locating Docket No. FAA–2016–5462.
(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
airworthiness.A330-A340@airbus.com;
Internet https://www.airbus.com. You may
view this service information at the FAA,
VerDate Sep<11>2014
15:12 Apr 11, 2016
Jkt 238001
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. 2016–08255 Filed 4–11–16; 8:45 am]
BILLING CODE 4910–13–P
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
Federal Aviation
Administration (FAA), DOT.
ACTION: Notice of proposed rulemaking
(NPRM).
AGENCY:
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.
SUMMARY:
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
https://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
DATES:
PO 00000
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Fmt 4702
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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:
airworthiness.A330–A340@airbus.com;
Internet: https://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 https://
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 https://
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
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Federal Register / Vol. 81, No. 70 / Tuesday, April 12, 2016 / Proposed Rules
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 nonconforming 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].
jstallworth on DSK7TPTVN1PROD with PROPOSALS
You may examine the MCAI in the
AD docket on the Internet at https://
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
VerDate Sep<11>2014
15:12 Apr 11, 2016
Jkt 238001
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 oncondition 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
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21487
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:
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21488
Federal Register / Vol. 81, No. 70 / Tuesday, April 12, 2016 / Proposed Rules
PART 39—AIRWORTHINESS
DIRECTIVES
1. The authority citation for part 39
continues to read as follows:
■
Authority: 49 U.S.C. 106(g), 40113, 44701.
§ 39.13
[Amended]
2. The FAA amends § 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 heattreated 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.
jstallworth on DSK7TPTVN1PROD with PROPOSALS
(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.
VerDate Sep<11>2014
15:12 Apr 11, 2016
Jkt 238001
(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
PO 00000
Frm 00005
Fmt 4702
Sfmt 9990
Avenue SW., Renton, WA 98057–3356;
telephone: 425–227–1138; fax: 425–227–
1149. Information may be emailed to: 9ANM-116-AMOC-REQUESTS@faa.gov.
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 https://
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:
airworthiness.A330-A340@airbus.com;
Internet: https://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
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]]>Agencies
[Federal Register Volume 81, Number 70 (Tuesday, April 12, 2016)]
[Proposed Rules]
[Pages 21486-21488]
From the Federal Register Online via the Government Publishing Office [www.gpo.gov]
[FR Doc No: 2016-08253]
-----------------------------------------------------------------------
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).
-----------------------------------------------------------------------
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 https://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: airworthiness.A330-A340@airbus.com; Internet: https://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 https://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 https://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 https://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: 9-ANM-116-AMOC-REQUESTS@faa.gov.
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 https://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: airworthiness.A330-A340@airbus.com; Internet:
https://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
