[Federal Register Volume 83, Number 236 (Monday, December 10, 2018)]
[Proposed Rules]
[Pages 63444-63447]
From the Federal Register Online via the Government Publishing Office [www.gpo.gov]
[FR Doc No: 2018-26462]
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DEPARTMENT OF TRANSPORTATION
Federal Aviation Administration
14 CFR Part 39
[Docket No. FAA-2018-1005; Product Identifier 2018-NM-109-AD]
RIN 2120-AA64
Airworthiness Directives; Airbus SAS Airplanes
AGENCY: Federal Aviation Administration (FAA), DOT.
ACTION: Notice of proposed rulemaking (NPRM).
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SUMMARY: We propose to supersede Airworthiness Directive (AD) 2016-16-
01, which applies to certain Airbus SAS Model A330-200 Freighter, -200,
and -300 series airplanes. AD 2016-16-01 requires an inspection of
affected structural parts in the cargo and cabin compartments to
determine if proper heat treatment has been done, and replacement or
repair if necessary. Since we issued AD 2016-16-01, we have determined
that additional affected parts in the cabin compartment structure must
also be inspected. This proposed AD would retain the requirements of AD
2016-16-01 and require inspection of additional locations of the cabin
compartment structure. We are proposing this AD to address the unsafe
condition on these products.
DATES: We must receive comments on this proposed AD by January 24,
2019.
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
SAS, Airworthiness Office--EIAS, Rond-Point Emile Dewoitine No: 2,
31700 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 Standards Branch, 2200 South 216th St., Des Moines, WA.
For information on the availability of this material at the FAA, call
206-231-3195.
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-2018-
1005; or in person at Docket Operations between 9 a.m. and 5 p.m.,
Monday through Friday, except Federal holidays. The AD docket contains
this NPRM, the regulatory evaluation, any comments received, and other
information. The street address for Docket Operations (phone 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 Section, Transport Standards Branch, FAA, 2200 South
216th St., Des Moines, WA 98198; telephone and fax 206-231-3229.
SUPPLEMENTARY INFORMATION:
Comments Invited
We invite you to send any written relevant data, views, or
arguments about this proposal. Send your comments to an address listed
under the ADDRESSES section. Include ``Docket No. FAA-2018-1005;
Product Identifier 2018-NM-109-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
We issued AD 2016-16-01, Amendment 39-18599 (81 FR 51325, August 4,
2016) (corrected September 1, 2016 (81 FR 60246)) (``AD 2016-16-01''),
for certain Airbus SAS Model A330-200 Freighter, -200, and -300 series
airplanes. AD 2016-16-01 requires an inspection of affected structural
parts in the cargo and cabin compartments to determine if proper heat
treatment has been done, and replacement or repair if necessary. AD
2016-16-01 was prompted by a report of a manufacturing defect that
affects the durability of affected parts in the cargo and cabin
compartment. We issued AD 2016-16-01 to address crack initiation and
propagation in structural parts of the cargo and cabin compartments,
which could result in reduced structural integrity of the fuselage.
Actions Since AD 2016-16-01 Was Issued
Since we issued AD 2016-16-01, we have determined that additional
affected parts in the cabin compartment structure must also be
inspected.
The European Aviation Safety Agency (EASA), which is the Technical
Agent for the Member States of the European Union, has issued EASA AD
2018-0147, dated July 13, 2018 (referred to after this as the Mandatory
Continuing Airworthiness Information, or ``the MCAI''), to correct an
unsafe condition for certain Model A330-200 Freighter, -200, and -300
series airplanes. The MCAI states:
[[Page 63445]]
It was determined that several structural parts, intended for
cargo or cabin compartment installation, were manufactured from
improperly heat-treated materials. A subsequent review identified
that some of those parts were installed on aeroplanes manufactured
between November 2011 and February 2013. Consequently, Airbus
implemented measures into manufacturing processes to ensure
detection and to prevent further installation of such non-conforming
parts. A detailed safety assessment was accomplished to identify the
possible impact of these parts on the aeroplane 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 meet 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 unsafe condition, Airbus published the
applicable SBs [service bulletins] to provide inspection
instructions for affected structural cargo and cabin parts,
respectively. Consequently, EASA issued AD 2015-0212 [which
corresponds to FAA AD 2016-16-01] to require a one-time special
detailed inspection (SDI) [eddy current inspection] to measure the
electrical conductivity of affected parts, to identify the presence
or absence of heat treatment, and, depending on findings, applicable
corrective action(s) [replacement or repair].
Since that AD was issued, Airbus identified that some additional
affected parts, located in the cabin compartment structure, have
been missed and need to be inspected. Consequently, Airbus issued SB
A330-53-3228 Revision 01 to introduce the locations of those missed
structural parts to be inspected.
For the reasons described above, this [EASA] AD retains the
requirements of EASA AD 2015-0212, which is superseded, and expands
the number and locations of structural parts to be inspected.
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-2018-
1005.
Related Service Information Under 1 CFR Part 51
Airbus has issued Service Bulletin A330-53-3227, Revision 02, dated
July 25, 2018, which describes procedures for inspecting affected
structural parts in the cargo compartment to determine if proper heat
treatment has been done, and replacing discrepant parts.
Airbus has also issued Service Bulletin A330-53-3228, Revision 01,
dated April 11, 2018, which describes procedures for inspecting
affected structural parts in the cabin compartment to determine if
proper heat treatment has been done, doing additional work (inspecting
additional locations of the cabin compartment structure), and doing
related investigative and corrective actions. Related investigative
actions include an eddy current inspection to verify the measurement
from the inspection to determine if proper heat treatment has been
done. Corrective actions include replacing discrepant 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
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 the relevant information and determined the unsafe
condition described previously is likely to exist or develop on other
products of the same type design.
Proposed Requirements of This NPRM
This proposed AD would retain all of the requirements of AD 2016-
16-01. This proposed AD would also require accomplishing the additional
work specified in Airbus Service Bulletin A330-53-3228, Revision 01,
dated April 11, 2018, described previously.
Costs of Compliance
We estimate that this proposed AD affects 20 airplanes of U.S.
registry. We estimate the following costs to comply with this proposed
AD:
Estimated Costs for Required Actions
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Cost per Cost on U.S.
Actions Labor cost Parts cost product operators
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Retained actions from AD 2016-16-01 11 work-hours x $85 per $0 $935 $18,700
hour = $935.
New proposed additional work....... 5 work-hours x $85 per hour 0 425 8,500
= $425.
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We estimate the following costs to do any necessary on-condition
action that would be required based on the results of any required
actions. We have no way of determining the number of aircraft that
might need this on-condition action:
Estimated Costs of On-Condition Action
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Cost per
Labor cost Parts cost product
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45 work-hours x $85 per hour = $3,825. $0 * $3,825
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* We have received no definitive data on the parts cost for the on-
condition action.
According to the manufacturer, some or all 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 known 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,
[[Page 63446]]
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.
This proposed AD is issued in accordance with authority delegated
by the Executive Director, Aircraft Certification Service, as
authorized by FAA Order 8000.51C. In accordance with that order,
issuance of ADs is normally a function of the Compliance and
Airworthiness Division, but during this transition period, the
Executive Director has delegated the authority to issue ADs applicable
to transport category airplanes and associated appliances to the
Director of the System Oversight Division.
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 removing Airworthiness Directive (AD)
2016-16-01, Amendment 39-18599 (81 FR 51325, August 4, 2016) (corrected
September 1, 2016 (81 FR 60246)), and adding the following new AD:
Airbus SAS: Docket No. FAA-2018-1005; Product Identifier 2018-NM-
109-AD.
(a) Comments Due Date
We must receive comments by January 24, 2019.
(b) Affected ADs
This AD replaces AD 2016-16-01, Amendment 39-18599 (81 FR 51325,
August 4, 2016) (corrected September 1, 2016 (81 FR 60246)) (``AD
2016-16-01'').
(c) Applicability
This AD applies to the Airbus SAS airplanes, certificated in any
category, identified in paragraphs (c)(1), (c)(2), and (c)(3) of
this AD, 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 compartments. We
are issuing this AD to address crack initiation and propagation in
affected parts in the cargo and cabin compartments, 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) Retained Inspection of Affected Structure in the Cargo Compartment,
With Revised Service Information
This paragraph restates the requirements of paragraph (g) of AD
2016-16-01, with revised service information. 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; or Airbus Service Bulletin A330-53-3227, Revision 02,
dated July 25, 2018. As of the effective date of this AD, only
Airbus Service Bulletin A330-53-3227, Revision 02, dated July 25,
2018, may be used.
(h) Retained Replacement of Non-Conforming Parts in the Cargo
Compartment, With Revised Service Information
This paragraph restates the requirements of paragraph (h) of AD
2016-16-01, with revised service information. 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; or
Airbus Service Bulletin A330-53-3227, Revision 02, dated July 25,
2018. As of the effective date of this AD, only Airbus Service
Bulletin A330-53-3227, Revision 02, dated July 25, 2018, may be
used.
(i) Retained Repair of Non-Conforming Parts in the Cargo Compartment,
With Revised Service Information
This paragraph restates the requirements of paragraph (i) of AD
2016-16-01, with revised service information. 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 A330-53-
3227, dated August 18, 2015; or Airbus Service Bulletin A330-53-
3227, Revision 02, dated July 25, 2018; before further flight,
repair using a method approved by the Manager, International
Section, Transport Standards Branch, FAA; or the European Aviation
Safety Agency (EASA); or Airbus SAS's EASA Design Organization
Approval (DOA). If approved by the DOA, the approval must include
the DOA-authorized signature. As of the effective date of this AD,
only Airbus Service Bulletin A330-53-3227, Revision 02, dated July
25, 2018, may be used to identify the measured value.
(j) Retained Inspection of Affected Structure in the Cabin Compartment,
With Revised Service Information
This paragraph restates the requirements of paragraph (j) of AD
2016-16-01, with revised service information. 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; or Airbus Service
Bulletin A330-53-3228, Revision 01, dated April 11, 2018. As of the
effective date of this AD, only Airbus Service Bulletin A330-53-
3228, Revision 01, dated April 11, 2018, may be used.
(k) Retained Replacement of Non-Conforming Parts in the Cabin
Compartment, With Revised Service Information
This paragraph restates the requirements of paragraph (k) of AD
2016-16-01, with
[[Page 63447]]
revised service information. 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; or Airbus Service Bulletin A330-53-
3228, Revision 01, dated April 11, 2018. As of the effective date of
this AD, only Airbus Service Bulletin A330-53-3228, Revision 01,
dated April 11, 2018, may be used.
(l) Retained Repair of Non-Conforming Parts in the Cabin Compartment,
With Revised Service Information and New Alternative Actions
This paragraph restates the requirements of paragraph (l) of AD
2016-16-01, with revised service information and new alternative
actions. 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 A330-53-3228, dated August 18, 2015; or to have to
a measured value between 22 MS/m and 26 MS/m or between 37.9 and
44.8% IACS, as specified in Airbus Service Bulletin A330-53-3228,
Revision 01, dated April 11, 2018, before further flight, do the
actions specified in paragraph (l)(1) or (l)(2) of this AD. As of
the effective date of this AD, only Airbus Service Bulletin A330-53-
3228, Revision 01, dated April 11, 2018, may be used to identify the
measured value.
(1) Repair using a method approved by the Manager, International
Section, Transport Standards Branch, FAA; or the EASA; or Airbus
SAS's EASA DOA. If approved by the DOA, the approval must include
the DOA-authorized signature.
(2) Do an eddy current inspection to verify the measurement, in
accordance with the Accomplishment Instructions of Airbus Service
Bulletin A330-53-3228, Revision 01, dated April 11, 2018.
(i) If an affected structural part in the cabin compartment is
identified to have a measured value between 22 MS/m and 26 MS/m or
between 37.9 and 44.8% IACS, before further flight, repair using a
method approved by the Manager, International Section, Transport
Standards Branch, FAA; or the EASA; or Airbus SAS's EASA DOA. If
approved by the DOA, the approval must include the DOA-authorized
signature.
(ii) If 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, do the replacement specified
in paragraph (k) of this AD.
(m) New Requirement of This AD: Inspection of Additional Cabin
Locations
For an airplane on which the cabin compartment structure was
inspected and corrective actions were done before the effective date
of this AD as specified in the Accomplishment Instructions of Airbus
Service Bulletin A330-53-3228, dated August 18, 2015: Before
exceeding 108 months since the airplane's first flight, do an eddy
current conductivity test of the forward cabin overhead compartment,
and do all applicable related investigative and corrective actions,
in accordance with the applicable ``additional work'' task in the
Accomplishment Instructions of Airbus Service Bulletin A330-53-3228,
Revision 01, dated April 11, 2018. Do all applicable related
investigative and corrective actions before further flight. Where
Airbus Service Bulletin A330-53-3228, Revision 01, dated April 11,
2018, specifies to contact Airbus for appropriate action: Before
further flight, accomplish corrective actions in accordance with the
procedures specified in paragraph (p)(2) of this AD.
(n) No Reporting
Although Airbus Service Bulletin A330-53-3227, Revision 02,
dated July 25, 2018, and Airbus Service Bulletin A330-53-3228,
Revision 01, dated April 11, 2018, specify to submit certain
information to the manufacturer, and specify that action as ``RC''
(required for compliance), this AD does not include that
requirement.
(o) Credit for Previous Actions
This paragraph provides credit for the actions specified in
paragraphs (g), (h), and (i) of this AD, if those actions were
performed before the effective date of this AD using Airbus Service
Bulletin A330-53-3227, Revision 01, dated July 5, 2016.
(p) Other FAA AD Provisions
(1) Alternative Methods of Compliance (AMOCs): The Manager,
International Section, Transport Standards Branch, 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 Section, send it to the attention of
the person identified in paragraph (q)(2) of this AD. Information
may be emailed to [email protected].
(i) 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.
(ii) AMOC letters ANM-116-17-118, dated February 2, 2017, and
AIR-676-18-369, dated September 17, 2018, approved previously for AD
2016-16-01, are approved as AMOCs for the corresponding provisions
of this AD.
(2) Contacting the Manufacturer: As of the effective date of
this AD, 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 Section, Transport Standards
Branch, FAA; or the EASA; or Airbus SAS's EASA Design Organization
Approval (DOA). If approved by the DOA, the approval must include
the DOA-authorized signature.
(3) Required for Compliance (RC): Except as required by
paragraphs (i), (l), (m), and (o) of this AD: 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.
(q) Related Information
(1) Refer to Mandatory Continuing Airworthiness Information
(MCAI) EASA Airworthiness Directive 2018-0147, dated July 13, 2018,
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-2018-1005.
(2) For more information about this AD, contact Vladimir
Ulyanov, Aerospace Engineer, International Section, Transport
Standards Branch, FAA, 2200 South 216th St., Des Moines, WA 98198;
telephone and fax 206-231-3229.
(3) For service information identified in this AD, contact
Airbus SAS, Airworthiness Office--EIAS, Rond-Point Emile Dewoitine
No: 2, 31700 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 Standards Branch, 2200 South 216th St., Des Moines,
WA. For information on the availability of this material at the FAA,
call 206-231-3195.
Issued in Des Moines, Washington, on November 23, 2018.
John P. Piccola,
Acting Director, System Oversight Division, Aircraft Certification
Service.
[FR Doc. 2018-26462 Filed 12-7-18; 8:45 am]
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