[Federal Register Volume 81, Number 150 (Thursday, August 4, 2016)]
[Rules and Regulations]
[Pages 51325-51328]
From the Federal Register Online via the Government Publishing Office [www.gpo.gov]
[FR Doc No: 2016-18168]
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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;
Amendment 39-18599; AD 2016-16-01]
RIN 2120-AA64
Airworthiness Directives; Airbus Airplanes
AGENCY: Federal Aviation Administration (FAA), Department of
Transportation (DOT).
ACTION: Final rule.
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SUMMARY: We are adopting a new airworthiness directive (AD) for certain
Airbus Model A330-200 Freighter, -200, and -300 series airplanes. This
AD was prompted by a report of a manufacturing defect that affects the
durability of affected parts in the cargo and cabin compartment. This
AD requires 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 issuing this AD to prevent crack
initiation and propagation, which could result in reduced structural
integrity of the fuselage.
DATES: This AD is effective September 8, 2016.
The Director of the Federal Register approved the incorporation by
reference of certain publications listed in this AD as of September 8,
2016.
ADDRESSES: For service information identified in this final rule,
contact Airbus SAS, Airworthiness Office-EAL, 1 Rond Point Maurice
Bellonte, 31707 Blagnac Cedex, France; telephone: +33 5 61 93 36 96;
fax: +33 5 61 93 45 80; email: [email protected];
Internet: http://www.airbus.com. You may view this referenced service
information at the FAA, Transport 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-2016-5460.
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 AD, the regulatory evaluation, any comments received, and
other information. The street address for the Docket Office (telephone
800-647-5527) is Docket Management Facility, U.S. Department of
Transportation, Docket Operations, M-30, West Building Ground Floor,
Room W12-140, 1200 New Jersey Avenue SE., Washington, DC 20590.
FOR FURTHER INFORMATION CONTACT: Vladimir Ulyanov, Aerospace Engineer,
International 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:
Discussion
We issued a notice of proposed rulemaking (NPRM) to amend 14 CFR
part 39 by adding an AD that would apply to all Airbus Model A330-200
Freighter, -200, and -300 series airplanes. The NPRM published in the
Federal Register on April 12, 2016 (81 FR 21486) (``the NPRM''). The
NPRM was prompted by a report of a manufacturing defect that affects
the durability of affected parts in the cargo and cabin compartment.
The NPRM proposed to 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 issuing
this AD to prevent crack initiation and propagation, which could result
in reduced structural integrity of the fuselage.
The European Aviation Safety Agency (EASA), which is the Technical
Agent 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
[[Page 51326]]
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
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.
Comments
We gave the public the opportunity to participate in developing
this AD. We received no comments on the NPRM or on the determination of
the cost to the public.
Conclusion
We reviewed the relevant data and determined that air safety and
the public interest require adopting this AD as proposed except for
minor editorial changes. We have determined that these minor changes:
Are consistent with the intent that was proposed in the
NPRM for correcting the unsafe condition; and
Do not add any additional burden upon the public than was
already proposed in the NPRM.
Related Service Information Under 1 CFR Part 51
Airbus has issued the following service information:
Airbus 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 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.
Costs of Compliance
We estimate that this AD affects 20 airplanes of U.S. registry.
We estimate the following costs to comply with this AD:
Estimated Costs
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Cost per Cost on U.S.
Action Labor cost Parts cost product operators
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Inspection........................ 11 work-hours x $85 per $0 $935 $18,700
hour = $935.
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We estimate the following costs to do any necessary replacements
that will be required based on the results of the required inspection.
We have received no definitive data that will enable us to provide the
cost of replacement parts for the on-condition actions specified in
this AD, nor the cost of repairs. We have no way of determining the
number of aircraft that might need this action.
On-Condition Costs
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Action Labor cost Parts cost Cost per product
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Replacement.......................... 45 work-hours x $85 per Not Available.......... Not Available.
hour = $3,825.
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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;
[[Page 51327]]
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):
2016-16-01 Airbus: Amendment 39-18599; Docket No. FAA-2016-5460;
Directorate Identifier 2015-NM-188-AD.
(a) Effective Date
This AD is effective September 8, 2016.
(b) Affected ADs
None.
(c) Applicability
This AD applies to the Airbus airplanes identified in paragraphs
(c)(1), (c)(2), and (c)(3) of this AD, certificated in any category,
manufacturer serial numbers 1175, 1180, 1287 through 1475 inclusive,
1478, 1480, 1483, and 1506.
(1) Model A330-223F and -243F airplanes.
(2) Model A330-201, -202, -203, -223, and -243 airplanes.
(3) Model A330-301, -302, -303, -321, -322, -323, -341, -342,
and -343 airplanes.
(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 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 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 cabin
compartment to determine if proper heat treatment has been done as
identified in, and in accordance with, the Accomplishment
Instructions of Airbus Service Bulletin A330-53-3228, 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 Service Bulletin A330-53-3228, dated August
18, 2015.
(l) Repair 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 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 EASA; or
Airbus's EASA 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 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.
(n) Related Information
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.
(o) 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.
[[Page 51328]]
(2) You must use this service information as applicable to do
the actions required by this AD, unless this AD specifies otherwise.
(i) Airbus Service Bulletin A330-53-3227, dated August 18, 2015.
(ii) Airbus Service Bulletin A330-53-3228, dated August 18,
2015.
(3) For service information identified in this AD, contact
Airbus SAS, Airworthiness Office--EAL, 1 Rond Point Maurice
Bellonte, 31707 Blagnac Cedex, France; telephone: +33 5 61 93 36 96;
fax: +33 5 61 93 45 80; email: [email protected];
Internet: http://www.airbus.com.
(4) You may view this service information at the FAA, Transport
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 July 21, 2016.
Michael Kaszycki,
Acting Manager, Transport Airplane Directorate, Aircraft Certification
Service.
[FR Doc. 2016-18168 Filed 8-3-16; 8:45 am]
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