Airworthiness Directives; Airbus Airplanes, 40670-40672 [2017-17536]
Download as PDF
<![CDATA[
40670
Federal Register / Vol. 82, No. 165 / Monday, August 28, 2017 / Rules and Regulations
DEPARTMENT OF TRANSPORTATION
Federal Aviation Administration
14 CFR Part 39
[Docket No. FAA–2016–7264; Product
Identifier 2015–NM–185–AD; Amendment
39–18998; AD 2017–17–08]
RIN 2120–AA64
Airworthiness Directives; Airbus
Airplanes
Federal Aviation
Administration (FAA), Department of
Transportation (DOT).
ACTION: Final rule.
AGENCY:
We are adopting a new
airworthiness directive (AD) for certain
Airbus Model A330–200, –200
Freighter, and –300 series airplanes; and
Model A340–500 and –600 series
airplanes. This AD was prompted by a
quality control review on the final
assembly line, which determined that
the wrong aluminum alloy was used to
manufacture several structural parts.
This AD requires a one-time eddy
current conductivity measurement of
certain cabin and cargo compartment
structural parts to determine if an
incorrect aluminum alloy was used, and
replacement of any affected part with a
serviceable part. We are issuing this AD
to address the unsafe condition on these
products.
DATES: This AD is effective October 2,
2017.
The Director of the Federal Register
approved the incorporation by reference
of certain publications listed in this AD
as of October 2, 2017.
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 airworthiness.A330-A340@
airbus.com; Internet http://
www.airbus.com. You may view this
referenced service information at the
FAA, Transport Standards Branch, 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–
7264.
asabaliauskas on DSKBBXCHB2PROD with RULES
SUMMARY:
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–
7264; or in person at the Docket
VerDate Sep<11>2014
17:58 Aug 25, 2017
Jkt 241001
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 Section, Transport
Standards Branch, FAA, 1601 Lind
Avenue SW., Renton, WA 98057–3356;
telephone 425–227–1138; fax 425–227–
1149.
SUPPLEMENTARY INFORMATION:
Discussion
We issued a supplemental notice of
proposed rulemaking (SNPRM) to
amend 14 CFR part 39 by adding an AD
that would apply to certain Airbus
Model A330–200, –200 Freighter, and
–300 series airplanes; and Model A340–
500 and –600 series airplanes. The
SNPRM published in the Federal
Register on May 19, 2017 (82 FR 22907)
(‘‘the SNPRM’’). We preceded the
SNPRM with a notice of proposed
rulemaking (NPRM) that published in
the Federal Register on June 21, 2016
(81 FR 40201) (‘‘the NPRM’’). The
NPRM proposed to require a one-time
eddy current conductivity measurement
of certain cabin and cargo compartment
structural parts to determine if an
incorrect aluminum alloy was used, and
replacement of any affected part with a
serviceable part. The NPRM was
prompted by a quality control review on
the final assembly line, which
determined that the wrong aluminum
alloy was used to manufacture several
structural parts. The SNPRM proposed
to require new inspection locations for
certain airplanes, and removing
incorrect part numbers. We are issuing
this AD to detect and replace structural
parts made of an incorrect aluminum
alloy. This condition could result in
reduced structural integrity of the
airplane.
The European Aviation Safety Agency
(EASA), which is the Technical Agent
for the Member States of the European
Union, has issued EASA Airworthiness
Directive 2017–0021, dated February 8,
2017 (referred to after this as the
Mandatory Continuing Airworthiness
Information, or ‘‘the MCAI’’), to correct
an unsafe condition for certain Airbus
Model A330–200, –200 Freighter, and
–300 series airplanes; and Model A340–
PO 00000
Frm 00002
Fmt 4700
Sfmt 4700
500 and –600 series airplanes. The
MCAI states:
Following an Airbus quality control review
on the final assembly line, it was discovered
that wrong aluminum alloy was used to
manufacture several structural parts.
This condition, if not detected and
corrected, could reduce the structural
integrity of the aeroplane.
To address this potential unsafe condition,
Airbus published [Service Bulletin] (SB)
A330–53–3261, SB A330–53–3262, and SB
A340–53–5072, as applicable to aeroplane
type/model, to provide instructions to
identify the affected parts. Consequently,
EASA issued AD 2015–0206 to require a onetime special detailed inspection (SDI) [eddy
current conductivity measurements] of
certain cabin and/or cargo compartment parts
for material identification and, depending on
findings, replacement with serviceable parts.
Since that [EASA] AD was issued, Airbus
identified that the list of affected structural
parts in SB A330–53–3261 was incorrect.
Prompted by these findings, Airbus issued
SB A330–53–3261 Revision 01 to introduce
the new locations to be inspected and remove
other parts not affected.
For the reasons described above, this
[EASA] AD retains the requirements of EASA
AD 2015–0206, which is superseded, and
expands the locations 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–2016–
7264.
Comments
We gave the public the opportunity to
participate in developing this AD. We
received no comments on the SNPRM 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 SNPRM for
correcting the unsafe condition; and
• Do not add any additional burden
upon the public than was already
proposed in the SNPRM.
Related Service Information Under 1
CFR Part 51
Airbus has issued the following
service information:
• Airbus Service Bulletin A330–53–
3261, Revision 01, including
Appendixes 01, 02, and 03, dated
November 10, 2016.
• Airbus Service Bulletin A330–53–
3262, including Appendixes 01 and 02,
dated June 23, 2015.
E:\FR\FM\28AUR1.SGM
28AUR1
Federal Register / Vol. 82, No. 165 / Monday, August 28, 2017 / Rules and Regulations
• Airbus Service Bulletin A340–53–
5072, including Appendixes 01 and 02,
dated June 23, 2015.
This service information describes
procedures for a one-time eddy current
conductivity measurement of certain
cabin and cargo compartment structural
parts to determine if an incorrect
aluminum alloy was used, and
replacement of any affected part with a
serviceable part. These documents are
distinct because they apply to different
parts on different airplanes. 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 37
airplanes of U.S. registry.
We also estimate that it takes about 17
work-hours per product to comply with
the basic requirements of this AD. The
average labor rate is $85 per work-hour.
Based on these figures, we estimate the
cost of this AD on U.S. operators to be
$53,465, or $1,445 per product.
In addition, we estimate that any oncondition repairs take about 45 workhours and will require parts costing $0,
for a cost of $3,825 per product. We
have no way of determining the number
of aircraft that might need these repairs.
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.
asabaliauskas on DSKBBXCHB2PROD with RULES
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.
VerDate Sep<11>2014
17:58 Aug 25, 2017
Jkt 241001
This 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 to the Director of the System
Oversight Division.
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;
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
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):
■
2017–17–08 Airbus: Amendment 39–18998;
Docket No. FAA–2016–7264; Product
Identifier 2015–NM–185–AD.
(a) Effective Date
This AD is effective October 2, 2017.
(b) Affected ADs
None.
PO 00000
Frm 00003
Fmt 4700
Sfmt 4700
40671
(c) Applicability
This AD applies to the Airbus airplanes
identified in paragraphs (c)(1) and (c)(2) of
this AD, certificated in any category.
(1) Airbus Model A330–201, –202, –203,
–223, –223F, –243, –243F, –301, –302, –303,
–321, –322, –323, –341, –342, and –343
airplanes, manufacturer serial numbers
identified in Airbus Service Bulletin A330–
53–3261, Revision 01, including Appendixes
01, 02, and 03, dated November 10, 2016;
and/or Airbus Service Bulletin A330–53–
3262, including Appendixes 01 and 02, dated
June 23, 2015.
(2) Airbus Model A340–541 and –642
airplanes, manufacturer serial numbers 1030,
1040, 1079, 1091, 1102, and 1122.
(d) Subject
Air Transport Association (ATA) of
America Code 53, Fuselage.
(e) Reason
This AD was prompted by a quality control
review on the final assembly line, which
determined that the wrong aluminum alloy
was used to manufacture several structural
parts. We are issuing this AD to detect and
replace structural parts made of an incorrect
aluminum alloy. This condition could result
in reduced structural integrity of the
airplane.
(f) Compliance
Comply with this AD within the
compliance times specified, unless already
done.
(g) One-Time Measurement
Except as provided by paragraph (i) of this
AD: Within 6 years after the effective date of
this AD, but not exceeding 12 years since the
date of issuance of the original certificate of
airworthiness or the date of issuance of the
original export certificate of airworthiness;
do a one-time eddy current conductivity
measurement of the cabin and cargo
compartment structural parts identified in
the ‘‘Affected Part Number’’ column of table
1 to paragraphs (g) and (h) of this AD to
determine if an incorrect aluminum alloy
was used, in accordance with the
Accomplishment Instructions of the
applicable service information identified in
paragraph (g)(1), (g)(2), or (g)(3) of this AD.
(1) For cargo compartment structural parts
for Model A330 airplanes: Airbus Service
Bulletin A330–53–3261, Revision 01,
including Appendixes 01, 02, and 03, dated
November 10, 2016.
(2) For cabin structural parts for Model
A330 airplanes: Airbus Service Bulletin
A330–53–3262, including Appendixes 01
and 02, dated June 23, 2015; except part
number F5377004320300, which is located in
the ‘‘cabin’’ area, but must be inspected in
accordance with Airbus Service Bulletin
A330–53–3261, Revision 01, including
Appendixes 01, 02, and 03, dated November
10, 2016.
(3) For cargo compartment structural parts
for Model A340 airplanes: Airbus Service
Bulletin A340–53–5072, including
Appendixes 01 and 02, dated June 23, 2015.
E:\FR\FM\28AUR1.SGM
28AUR1
40672
Federal Register / Vol. 82, No. 165 / Monday, August 28, 2017 / Rules and Regulations
TABLE 1 TO PARAGRAPHS (g) AND (h)
OF THIS AD—PARTS TO BE INSPECTED/INSTALLED
Affected part No.
F5347126620600
F5347126621000
F5377004320300
F5347170420400
F5347170420600
G5367131300000
G5367173700000
G5367173800000
...
...
...
...
...
...
...
...
Acceptable
replacement
part No.
F5347126620000
F5347126620400
F5377004320351
F5347170420400
F5347170420600
G5367131300000
G5367173700000
G5367173800000
Area
...
...
...
...
...
..
..
..
Cabin.
Cabin.
Cabin.
Cargo.
Cargo.
Cargo.
Cargo.
Cargo.
(h) Replacement
If during the inspection required by
paragraph (g) of this AD, any affected part
having a part number specified in table 1 to
paragraphs (g) and (h) of this AD is found to
have a measured value greater than that
specified in Figure A–GFAAA, Sheet 02,
‘‘Inspection Flowchart,’’ of the applicable
service information identified in paragraphs
(g)(1), (g)(2), and (g)(3) of this AD, except as
provided by paragraph (i) of this AD: Within
6 years after the effective date of this AD, but
not exceeding 12 years since the date of
issuance of the original certificate of
airworthiness or the date of issuance of the
original export certificate of airworthiness,
replace the affected part with an acceptable
replacement part having a part number
specified in table 1 to paragraphs (g) and (h)
of this AD, in accordance with the
Accomplishment Instructions of the
applicable service information identified in
paragraph (g)(1), (g)(2), or (g)(3) of this AD.
asabaliauskas on DSKBBXCHB2PROD with RULES
(i) Exception to Certain Service Information
Where Figure A–GFAAA, Sheet 02,
‘‘Inspection Flowchart,’’ of the service
information identified in paragraphs (g)(2)
and (g)(3) of this AD specifies to ‘‘do the
conductivity (s) measurement with 60kHz
(refer to Appendix 01) s480 = lllMS/m,’’
the correct conductivity measurement is
‘‘s60 = lllMS/m.’’
(j) Additional Inspection for Certain
Airplanes
For Model A330 airplanes on which the
inspection and replacement, as applicable,
specified in paragraphs (g) and (h) of this AD
were done before the effective date of this
AD, in accordance with Airbus Service
Bulletin A330–53–3261, dated June 23, 2015:
Within 6 years after the effective date of this
AD, but not exceeding 12 years since the date
of issuance of the original certificate of
airworthiness or the date of issuance of the
original export certificate of airworthiness,
do a one-time eddy current conductivity
measurement of structural parts having part
number (P/N) G5367131300000, P/N
G5367173700000, and P/N G5367173800000,
located in fuselage section 15, in accordance
with the ‘‘Additional Work’’ section of the
Accomplishment Instructions of Airbus
Service Bulletin A330–53–3261, Revision 01,
including Appendixes 01, 02, and 03, dated
November 10, 2016.
(k) Replacement
If during the inspection required by
paragraph (j) of this AD, any affected part
VerDate Sep<11>2014
17:58 Aug 25, 2017
Jkt 241001
having a part number specified in paragraph
(j) of this AD is found to have a measured
value greater than that specified in Figure A–
GFAAA, Sheet 02, ‘‘Inspection Flowchart,’’
of Airbus Service Bulletin A330–53–3261,
Revision 01, including Appendixes 01, 02,
and 03, dated November 10, 2016: Within 6
years after the effective date of this AD, but
not exceeding 12 years since the date of
issuance of the original certificate of
airworthiness or the date of issuance of the
original export certificate of airworthiness,
replace the affected part with an acceptable
replacement part having a part number
specified in table 1 to paragraphs (g) and (h)
of this AD, in accordance with the
Accomplishment Instructions of Airbus
Service Bulletin A330–53–3261, Revision 01,
including Appendixes 01, 02, and 03, dated
November 10, 2016.
(l) Other FAA AD Provisions
The following provisions also apply to this
AD:
(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 manager of the International
Section, send it to the attention of the person
identified in paragraph (m)(2) of this AD.
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.
(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 Section,
Transport Standards Branch, 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 DOAauthorized 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.
(m) Related Information
(1) Refer to Mandatory Continuing
Airworthiness Information (MCAI) EASA
Airworthiness Directive 2017–0021, dated
February 8, 2017, for related information.
PO 00000
Frm 00004
Fmt 4700
Sfmt 4700
This MCAI may be found in the AD docket
on the Internet at http://www.regulations.gov
by searching for and locating Docket No.
FAA–2016–7264.
(2) For more information about this AD,
contact Vladimir Ulyanov, Aerospace
Engineer, International Section, Transport
Standards Branch, FAA, 1601 Lind Avenue
SW., Renton, WA 98057–3356; telephone
425–227–1138; fax 425–227–1149.
(n) 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.
(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 A330–53–3261,
Revision 01, including Appendixes 01, 02,
and 03, dated November 10, 2016.
(ii) Airbus Service Bulletin A330–53–3262,
including Appendixes 01 and 02, dated June
23, 2015.
(iii) Airbus Service Bulletin A340–53–
5072, including Appendixes 01 and 02, dated
June 23, 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
airworthiness.A330-A340@airbus.com;
Internet http://www.airbus.com.
(4) You may view this service information
at the FAA, Transport Standards Branch,
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/ibrlocations.html.
Issued in Renton, Washington, on August
9, 2017.
Dionne Palermo,
Acting Director, System Oversight Division,
Aircraft Certification Service.
[FR Doc. 2017–17536 Filed 8–25–17; 8:45 am]
BILLING CODE 4910–13–P
DEPARTMENT OF TRANSPORTATION
Federal Aviation Administration
14 CFR Part 39
[Docket No. FAA–2017–0337; Product
Identifier 2017–NM–006–AD; Amendment
39–19006; AD 2017–17–16]
RIN 2120–AA64
Airworthiness Directives; The Boeing
Company Airplanes
Federal Aviation
Administration (FAA), DOT.
AGENCY:
E:\FR\FM\28AUR1.SGM
28AUR1
]]>Agencies
[Federal Register Volume 82, Number 165 (Monday, August 28, 2017)]
[Rules and Regulations]
[Pages 40670-40672]
From the Federal Register Online via the Government Publishing Office [www.gpo.gov]
[FR Doc No: 2017-17536]
[[Page 40670]]
=======================================================================
-----------------------------------------------------------------------
DEPARTMENT OF TRANSPORTATION
Federal Aviation Administration
14 CFR Part 39
[Docket No. FAA-2016-7264; Product Identifier 2015-NM-185-AD; Amendment
39-18998; AD 2017-17-08]
RIN 2120-AA64
Airworthiness Directives; Airbus Airplanes
AGENCY: Federal Aviation Administration (FAA), Department of
Transportation (DOT).
ACTION: Final rule.
-----------------------------------------------------------------------
SUMMARY: We are adopting a new airworthiness directive (AD) for certain
Airbus Model A330-200, -200 Freighter, and -300 series airplanes; and
Model A340-500 and -600 series airplanes. This AD was prompted by a
quality control review on the final assembly line, which determined
that the wrong aluminum alloy was used to manufacture several
structural parts. This AD requires a one-time eddy current conductivity
measurement of certain cabin and cargo compartment structural parts to
determine if an incorrect aluminum alloy was used, and replacement of
any affected part with a serviceable part. We are issuing this AD to
address the unsafe condition on these products.
DATES: This AD is effective October 2, 2017.
The Director of the Federal Register approved the incorporation by
reference of certain publications listed in this AD as of October 2,
2017.
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 airworthiness.A330-A340@airbus.com; Internet
http://www.airbus.com. You may view this referenced service information
at the FAA, Transport Standards Branch, 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-
7264.
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-
7264; 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 Section, Transport Standards Branch, FAA, 1601 Lind
Avenue SW., Renton, WA 98057-3356; telephone 425-227-1138; fax 425-227-
1149.
SUPPLEMENTARY INFORMATION:
Discussion
We issued a supplemental notice of proposed rulemaking (SNPRM) to
amend 14 CFR part 39 by adding an AD that would apply to certain Airbus
Model A330-200, -200 Freighter, and -300 series airplanes; and Model
A340-500 and -600 series airplanes. The SNPRM published in the Federal
Register on May 19, 2017 (82 FR 22907) (``the SNPRM''). We preceded the
SNPRM with a notice of proposed rulemaking (NPRM) that published in the
Federal Register on June 21, 2016 (81 FR 40201) (``the NPRM''). The
NPRM proposed to require a one-time eddy current conductivity
measurement of certain cabin and cargo compartment structural parts to
determine if an incorrect aluminum alloy was used, and replacement of
any affected part with a serviceable part. The NPRM was prompted by a
quality control review on the final assembly line, which determined
that the wrong aluminum alloy was used to manufacture several
structural parts. The SNPRM proposed to require new inspection
locations for certain airplanes, and removing incorrect part numbers.
We are issuing this AD to detect and replace structural parts made of
an incorrect aluminum alloy. This condition could result in reduced
structural integrity of the airplane.
The European Aviation Safety Agency (EASA), which is the Technical
Agent for the Member States of the European Union, has issued EASA
Airworthiness Directive 2017-0021, dated February 8, 2017 (referred to
after this as the Mandatory Continuing Airworthiness Information, or
``the MCAI''), to correct an unsafe condition for certain Airbus Model
A330-200, -200 Freighter, and -300 series airplanes; and Model A340-500
and -600 series airplanes. The MCAI states:
Following an Airbus quality control review on the final assembly
line, it was discovered that wrong aluminum alloy was used to
manufacture several structural parts.
This condition, if not detected and corrected, could reduce the
structural integrity of the aeroplane.
To address this potential unsafe condition, Airbus published
[Service Bulletin] (SB) A330-53-3261, SB A330-53-3262, and SB A340-
53-5072, as applicable to aeroplane type/model, to provide
instructions to identify the affected parts. Consequently, EASA
issued AD 2015-0206 to require a one-time special detailed
inspection (SDI) [eddy current conductivity measurements] of certain
cabin and/or cargo compartment parts for material identification
and, depending on findings, replacement with serviceable parts.
Since that [EASA] AD was issued, Airbus identified that the list
of affected structural parts in SB A330-53-3261 was incorrect.
Prompted by these findings, Airbus issued SB A330-53-3261 Revision
01 to introduce the new locations to be inspected and remove other
parts not affected.
For the reasons described above, this [EASA] AD retains the
requirements of EASA AD 2015-0206, which is superseded, and expands
the locations 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-2016-
7264.
Comments
We gave the public the opportunity to participate in developing
this AD. We received no comments on the SNPRM 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
SNPRM for correcting the unsafe condition; and
Do not add any additional burden upon the public than was
already proposed in the SNPRM.
Related Service Information Under 1 CFR Part 51
Airbus has issued the following service information:
Airbus Service Bulletin A330-53-3261, Revision 01,
including Appendixes 01, 02, and 03, dated November 10, 2016.
Airbus Service Bulletin A330-53-3262, including Appendixes
01 and 02, dated June 23, 2015.
[[Page 40671]]
Airbus Service Bulletin A340-53-5072, including Appendixes
01 and 02, dated June 23, 2015.
This service information describes procedures for a one-time eddy
current conductivity measurement of certain cabin and cargo compartment
structural parts to determine if an incorrect aluminum alloy was used,
and replacement of any affected part with a serviceable part. These
documents are distinct because they apply to different parts on
different airplanes. 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 37 airplanes of U.S. registry.
We also estimate that it takes about 17 work-hours per product to
comply with the basic requirements of this AD. The average labor rate
is $85 per work-hour. Based on these figures, we estimate the cost of
this AD on U.S. operators to be $53,465, or $1,445 per product.
In addition, we estimate that any on-condition repairs take about
45 work-hours and will require parts costing $0, for a cost of $3,825
per product. We have no way of determining the number of aircraft that
might need these repairs.
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.
This 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 to
the Director of the System Oversight Division.
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;
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):
2017-17-08 Airbus: Amendment 39-18998; Docket No. FAA-2016-7264;
Product Identifier 2015-NM-185-AD.
(a) Effective Date
This AD is effective October 2, 2017.
(b) Affected ADs
None.
(c) Applicability
This AD applies to the Airbus airplanes identified in paragraphs
(c)(1) and (c)(2) of this AD, certificated in any category.
(1) Airbus Model A330-201, -202, -203, -223, -223F, -243, -243F,
-301, -302, -303, -321, -322, -323, -341, -342, and -343 airplanes,
manufacturer serial numbers identified in Airbus Service Bulletin
A330-53-3261, Revision 01, including Appendixes 01, 02, and 03,
dated November 10, 2016; and/or Airbus Service Bulletin A330-53-
3262, including Appendixes 01 and 02, dated June 23, 2015.
(2) Airbus Model A340-541 and -642 airplanes, manufacturer
serial numbers 1030, 1040, 1079, 1091, 1102, and 1122.
(d) Subject
Air Transport Association (ATA) of America Code 53, Fuselage.
(e) Reason
This AD was prompted by a quality control review on the final
assembly line, which determined that the wrong aluminum alloy was
used to manufacture several structural parts. We are issuing this AD
to detect and replace structural parts made of an incorrect aluminum
alloy. This condition could result in reduced structural integrity
of the airplane.
(f) Compliance
Comply with this AD within the compliance times specified,
unless already done.
(g) One-Time Measurement
Except as provided by paragraph (i) of this AD: Within 6 years
after the effective date of this AD, but not exceeding 12 years
since the date of issuance of the original certificate of
airworthiness or the date of issuance of the original export
certificate of airworthiness; do a one-time eddy current
conductivity measurement of the cabin and cargo compartment
structural parts identified in the ``Affected Part Number'' column
of table 1 to paragraphs (g) and (h) of this AD to determine if an
incorrect aluminum alloy was used, in accordance with the
Accomplishment Instructions of the applicable service information
identified in paragraph (g)(1), (g)(2), or (g)(3) of this AD.
(1) For cargo compartment structural parts for Model A330
airplanes: Airbus Service Bulletin A330-53-3261, Revision 01,
including Appendixes 01, 02, and 03, dated November 10, 2016.
(2) For cabin structural parts for Model A330 airplanes: Airbus
Service Bulletin
A330-53-3262, including Appendixes 01 and 02, dated June 23,
2015; except part number F5377004320300, which is located in the
``cabin'' area, but must be inspected in accordance with Airbus
Service Bulletin A330-53-3261, Revision 01, including Appendixes 01,
02, and 03, dated November 10, 2016.
(3) For cargo compartment structural parts for Model A340
airplanes: Airbus Service Bulletin A340-53-5072, including
Appendixes 01 and 02, dated June 23, 2015.
[[Page 40672]]
Table 1 to Paragraphs (g) and (h) of This AD--Parts To Be Inspected/
Installed
------------------------------------------------------------------------
Acceptable
Affected part No. replacement part No. Area
------------------------------------------------------------------------
F5347126620600.................... F5347126620000....... Cabin.
F5347126621000.................... F5347126620400....... Cabin.
F5377004320300.................... F5377004320351....... Cabin.
F5347170420400.................... F5347170420400....... Cargo.
F5347170420600.................... F5347170420600....... Cargo.
G5367131300000.................... G5367131300000....... Cargo.
G5367173700000.................... G5367173700000....... Cargo.
G5367173800000.................... G5367173800000....... Cargo.
------------------------------------------------------------------------
(h) Replacement
If during the inspection required by paragraph (g) of this AD,
any affected part having a part number specified in table 1 to
paragraphs (g) and (h) of this AD is found to have a measured value
greater than that specified in Figure A-GFAAA, Sheet 02,
``Inspection Flowchart,'' of the applicable service information
identified in paragraphs (g)(1), (g)(2), and (g)(3) of this AD,
except as provided by paragraph (i) of this AD: Within 6 years after
the effective date of this AD, but not exceeding 12 years since the
date of issuance of the original certificate of airworthiness or the
date of issuance of the original export certificate of
airworthiness, replace the affected part with an acceptable
replacement part having a part number specified in table 1 to
paragraphs (g) and (h) of this AD, in accordance with the
Accomplishment Instructions of the applicable service information
identified in paragraph (g)(1), (g)(2), or (g)(3) of this AD.
(i) Exception to Certain Service Information
Where Figure A-GFAAA, Sheet 02, ``Inspection Flowchart,'' of the
service information identified in paragraphs (g)(2) and (g)(3) of
this AD specifies to ``do the conductivity ([sigma]) measurement
with 60kHz (refer to Appendix 01) [sigma]480 = ___MS/m,'' the
correct conductivity measurement is ``[sigma]60 = ___MS/m.''
(j) Additional Inspection for Certain Airplanes
For Model A330 airplanes on which the inspection and
replacement, as applicable, specified in paragraphs (g) and (h) of
this AD were done before the effective date of this AD, in
accordance with Airbus Service Bulletin A330-53-3261, dated June 23,
2015: Within 6 years after the effective date of this AD, but not
exceeding 12 years since the date of issuance of the original
certificate of airworthiness or the date of issuance of the original
export certificate of airworthiness, do a one-time eddy current
conductivity measurement of structural parts having part number (P/
N) G5367131300000, P/N G5367173700000, and P/N G5367173800000,
located in fuselage section 15, in accordance with the ``Additional
Work'' section of the Accomplishment Instructions of Airbus Service
Bulletin A330-53-3261, Revision 01, including Appendixes 01, 02, and
03, dated November 10, 2016.
(k) Replacement
If during the inspection required by paragraph (j) of this AD,
any affected part having a part number specified in paragraph (j) of
this AD is found to have a measured value greater than that
specified in Figure A-GFAAA, Sheet 02, ``Inspection Flowchart,'' of
Airbus Service Bulletin A330-53-3261, Revision 01, including
Appendixes 01, 02, and 03, dated November 10, 2016: Within 6 years
after the effective date of this AD, but not exceeding 12 years
since the date of issuance of the original certificate of
airworthiness or the date of issuance of the original export
certificate of airworthiness, replace the affected part with an
acceptable replacement part having a part number specified in table
1 to paragraphs (g) and (h) of this AD, in accordance with the
Accomplishment Instructions of Airbus Service Bulletin A330-53-3261,
Revision 01, including Appendixes 01, 02, and 03, dated November 10,
2016.
(l) Other FAA AD Provisions
The following provisions also apply to this AD:
(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 manager of the International Section, send it to the
attention of the person identified in paragraph (m)(2) of this AD.
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.
(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
Section, Transport Standards Branch, 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.
(m) Related Information
(1) Refer to Mandatory Continuing Airworthiness Information
(MCAI) EASA Airworthiness Directive 2017-0021, dated February 8,
2017, for related information. This MCAI may be found in the AD
docket on the Internet at http://www.regulations.gov by searching
for and locating Docket No. FAA-2016-7264.
(2) For more information about this AD, contact Vladimir
Ulyanov, Aerospace Engineer, International Section, Transport
Standards Branch, FAA, 1601 Lind Avenue SW., Renton, WA 98057-3356;
telephone 425-227-1138; fax 425-227-1149.
(n) 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.
(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 A330-53-3261, Revision 01, including
Appendixes 01, 02, and 03, dated November 10, 2016.
(ii) Airbus Service Bulletin A330-53-3262, including Appendixes
01 and 02, dated June 23, 2015.
(iii) Airbus Service Bulletin A340-53-5072, including Appendixes
01 and 02, dated June 23, 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 airworthiness.A330-A340@airbus.com;
Internet http://www.airbus.com.
(4) You may view this service information at the FAA, Transport
Standards Branch, 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 August 9, 2017.
Dionne Palermo,
Acting Director, System Oversight Division, Aircraft Certification
Service.
[FR Doc. 2017-17536 Filed 8-25-17; 8:45 am]
BILLING CODE 4910-13-P
