Airworthiness Directives; Airbus Airplanes, 13382-13385 [2017-04657]
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Federal Register / Vol. 82, No. 47 / Monday, March 13, 2017 / Rules and Regulations
(j) New Requirement of This AD:
Maintenance or Inspection Program
Revision and Actions
Within 90 days after the effective date of
this AD, revise the maintenance program or
inspection program, as applicable, by
incorporating Airbus A330 Airworthiness
Limitations Section (ALS) Part 4—SEMR,
Revision 05, dated October 19, 2015. The
initial compliance times for the actions
specified in Airbus A330 ALS Part 4—SEMR,
Revision 05, dated October 19, 2015, are
within the applicable compliance times
specified in Airbus A330 ALS Part 4—SEMR,
Revision 05, dated October 19, 2015, or
within 60 days after the effective date of this
AD, whichever is later, except as required by
paragraph (h) of this AD. Accomplishing the
revision of the maintenance program or
inspection program, as applicable, required
by this paragraph terminates the
requirements of paragraph (g) of this AD.
Revising the maintenance program or
inspection program, as applicable, by
incorporating Airbus A330 ALS Part 4—
SEMR—Variation 5.1, dated December 20,
2015, is an acceptable method of compliance
for the components specified in the variation.
jstallworth on DSK7TPTVN1PROD with RULES
(k) New Requirement of This AD: No
Alternative Actions or Intervals
After accomplishing the revision required
by paragraph (j) of this AD, no alternative
actions (e.g., inspections) or intervals may be
used unless the actions or intervals are
approved as an AMOC in accordance with
the procedures specified in paragraph (l)(1)
of this AD.
(l) 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: 9ANM-116-AMOC-REQUESTS@faa.gov.
(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. The AMOC
approval letter must specifically reference
this AD.
(ii) AMOCs approved previously for AD
2015–16–02 are approved as AMOCs for the
corresponding provisions of paragraph (g) of
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–
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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.
(m) Related Information
Refer to Mandatory Continuing
Airworthiness Information (MCAI) EASA AD
2016–0011, dated January 13, 2016, 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–2016–9069.
(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 A330 Airworthiness Limitations
Section (ALS) Part 4—System Equipment
Maintenance Requirements (SEMR), Revision
05, dated October 19, 2015.
(ii) Airbus A330 ALS Part 4—System
Equipment Maintenance Requirements
(SEMR)—Variation 5.1, dated December 20,
2015.
(3) The following service information was
approved for IBR on September 15, 2015 (80
FR 48019, August 11, 2015).
(i) Airbus A330 Airworthiness Limitations
Section (ALS) Part 4—Aging Systems
Maintenance, Revision 04, dated August 27,
2013.
(ii) Airbus A330 ALS Part 4—Aging
Systems Maintenance (ASM), Variation 4.1,
dated July 23, 2014.
(iii) Airbus A330 ALS Part 4—Aging
Systems Maintenance (ASM), Variation 4.2,
dated July 23, 2014.
(4) 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.
(5) 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.
(6) 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: https://
www.archives.gov/federal-register/cfr/ibrlocations.html.
Issued in Renton, Washington, on February
28, 2017.
Michael Kaszycki,
Acting Manager, Transport Airplane
Directorate, Aircraft Certification Service.
[FR Doc. 2017–04515 Filed 3–10–17; 8:45 am]
BILLING CODE 4910–13–P
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DEPARTMENT OF TRANSPORTATION
Federal Aviation Administration
14 CFR Part 39
[Docket No. FAA–2016–6431; Directorate
Identifier 2015–NM–182–AD; Amendment
39–18823; AD 2017–05–12]
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 A318–112 airplanes,
A319–111, –112, –115, –132, and –133
airplanes, A320–214, –232, and –233
airplanes, and A321–211, –212, –213,
–231, and –232 airplanes. This AD was
prompted by a quality control review on
the final assembly line, which
determined that aluminum alloy with
inadequate heat treatment had been
delivered and used on several structural
parts. This AD requires a one-time eddy
current conductivity measurement of
certain cabin, cargo compartment, and
frame structural parts to determine if
aluminum alloy with inadequate heat
treatment was used, and replacement if
necessary. We are issuing this AD to
address the unsafe condition on these
products.
SUMMARY:
This AD is effective April 17,
2017.
The Director of the Federal Register
approved the incorporation by reference
of certain publications listed in this AD
as of April 17, 2017.
ADDRESSES: For service information
identified in this final rule, contact
Airbus, Airworthiness Office—EIAS, 1
Rond Point Maurice Bellonte, 31707
Blagnac Cedex, France; telephone: +33 5
61 93 36 96; fax: +33 5 61 93 44 51;
email: account.airworth-eas@
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. It is also available on the Internet
at https://www.regulations.gov by
searching for and locating Docket No.
FAA–2016–6431.
DATES:
Examining the AD Docket
You may examine the AD docket on
the Internet at https://
www.regulations.gov by searching for
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Federal Register / Vol. 82, No. 47 / Monday, March 13, 2017 / Rules and Regulations
and locating Docket No. FAA–2016–
6431; 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:
Sanjay Ralhan, Aerospace Engineer,
International Branch, ANM–116,
Transport Airplane Directorate, FAA,
1601 Lind Avenue SW., Renton, WA
98057–3356; telephone: 425–227–1405;
fax: 425–227–1149.
SUPPLEMENTARY INFORMATION:
jstallworth on DSK7TPTVN1PROD with RULES
Discussion
We issued a notice of proposed
rulemaking (NPRM) to amend 14 CFR
part 39 by adding an AD that would
apply to certain Airbus Model A318–
112 airplanes, A319–111, –112, –115,
–132, and –133 airplanes, A320–214,
–232, and –233 airplanes, and A321–
211, –212, –213, –231, and –232
airplanes. The NPRM published in the
Federal Register on May 11, 2016 (81
FR 29209). The NPRM was prompted by
a quality control review on the final
assembly line, which determined that
aluminum alloy with inadequate heat
treatment had been delivered and used
on several structural parts. The NPRM
proposed to require a one-time eddy
current conductivity measurement of
certain cabin, cargo compartment, and
frame structural parts to determine if
aluminum alloy with inadequate heat
treatment was used, and replacement if
necessary. We are issuing this AD to
detect and replace structural parts made
of aluminum alloy with inadequate heat
treatment. 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 2015–0219, dated November 3,
2015 (referred to after this as the
Mandatory Continuing Airworthiness
Information, or ‘‘the MCAI’’), to correct
an unsafe condition for certain Airbus
Model A318–112 airplanes, A319–111,
–112, –115, –132, and –133 airplanes,
A320–214, –232, and –233 airplanes,
and A321–211, –212, –213, –231, and
–232 airplanes. The MCAI states:
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Following an Airbus quality control review
on the final assembly line, it was discovered
that aluminum alloy with inadequate heat
treatment were delivered by a supplier for
several structural parts. The results of the
investigations highlighted that 1% of the
stock could be impacted by this wrong
material.
Structural investigations demonstrated the
capability to sustain the static limits loads,
and sufficient fatigue life up to a certain
inspection threshold.
This condition, if not detected and
corrected, could reduce the aeroplane
structural integrity following fatigue load.
To address this potential unsafe condition,
Airbus issued Service Bulletin (SB) A320–
53–1292, SB A320–53–1293, and SB A320–
53–1294 to provide inspection instructions.
For the reasons described above, this
[EASA] AD requires a one-time Special
Detailed Inspection (SDI) [i.e., eddy current
conductivity measurement] of certain cabin,
cargo compartment and frame parts [for
material identification] and, depending on
findings, replacement with serviceable parts.
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–
6431.
Comments
We gave the public the opportunity to
participate in developing this AD. The
following presents the comment
received on the NPRM and the FAA’s
response.
Request To Include the Correction in
the Technical Adaptation to Certain
Service Information
Virgin America asked that we include
the correction in Airbus Technical
Adaptation (TA) 80095365/011/2016,
Issue 1, dated December 1, 2016, to
Figure A–GVAAA and Figure A–
GRAAA of Airbus Service Bulletin
A320–53–1293, dated July 30, 2015, in
this AD. Virgin America stated that the
parts shown in Figure A–GVAAA and
Figure A–GRAAA and highlighted for
inspection are the four hinge brackets
identified as having part number (P/N)
‘‘D4918518320201, A-profile.’’
However, the correct identification is P/
N ‘‘D4918518320200, A-profile.’’ Virgin
America noted that Airbus issued TA
80095365/011/2016, Issue 1, to update
Figure A–GVAAA and Figure A–
GRAAA of Airbus Service Bulletin
A320–53–1293, dated July 30, 2015, to
identify the correct part number. Virgin
America also stated that the TA
specified that Airbus Service Bulletin
A320–53–1293 is currently under
revision and the correction will be
included when the revision is issued.
We agree with the commenter’s
request to include the specified
correction. We have added a new
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13383
paragraph (h) to this AD to provide an
exception to Figure A–GVAAA of
Airbus Service Bulletin A320–53–1293,
dated July 30, 2015, which is needed for
compliance with paragraph (g) of this
AD. However, Figure A–GRAAA,
‘‘Reporting Sheet,’’ of Airbus Service
Bulletin A320–53–1293, dated July 30,
2015, is not needed for compliance with
this AD. We have added a note to
paragraph (h) of this AD to provide the
information in Airbus Technical
Adaptation (TA) 80095365/011/2016,
Issue 1, dated December 1, 2016, which
specifies the corrected information for
Figure A–GVAAA and Figure A–
GRAAA of Airbus Service Bulletin
A320–53–1293, dated July 30, 2015. We
have also added paragraph (j) to clarify
that reporting is not required by this
AD; however, reporting is recommended
for research and tracking. We have
redesignated subsequent paragraphs
accordingly.
Conclusion
We reviewed the relevant data,
considered the comment received, and
determined that air safety and the
public interest require adopting this AD
with the changes described previously
and 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.
We also determined that these
changes will not increase the economic
burden on any operator or increase the
scope of this AD.
Related Service Information Under 1
CFR Part 51
We reviewed the following service
information:
• Airbus Service Bulletin A320–53–
1292, dated July 23, 2015; including
Appendixes 01 and 02, dated July 23,
2015.
• Airbus Service Bulletin A320–53–
1293, dated July 30, 2015; including
Appendixes 01 and 02, dated July 30,
2015.
• Airbus Service Bulletin A320–53–
1294, dated July 23, 2015; including
Appendixes 01 and 02, dated July 23,
2015.
The service information describes
procedures for a one-time eddy current
conductivity measurement of certain
cabin, cargo compartment, and frame
structural parts to determine if
aluminum alloy with inadequate heat
treatment was used, and replacement of
any affected part with a serviceable part.
These documents are distinct since they
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apply to different parts on the airplane.
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 46
airplanes of U.S. registry.
We also estimate that it takes about 6
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
$23,460, or $510 per product.
We have received no definitive data
that enables us to provide cost estimates
for the on-condition actions specified in
this AD.
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.
jstallworth on DSK7TPTVN1PROD 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.
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;
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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):
■
2017–05–12 Airbus: Amendment 39–18823;
Docket No. FAA–2016–6431; Directorate
Identifier 2015–NM–182–AD.
(a) Effective Date
This AD is effective April 17, 2017.
(b) Affected ADs
None.
(c) Applicability
This AD applies to the Airbus airplanes
identified in paragraphs (c)(1) through (c)(4)
of this AD, certificated in any category;
manufacturer serial numbers 4895, 4903,
4911, 4919, 4929, 4938, 4942, 4944, 4946,
4948, and 4951, 4956 through 5541 inclusive,
5544, 5547, 5550, 5551, 5553, 5556, 5559,
5561, 5562, 5563, 5565, 5566, 5570, 5572,
5576, and 5578.
(1) Airbus Model A318–112 airplanes.
(2) Airbus Model A319–111, –112, –115,
–132, and –133 airplanes.
(3) Airbus Model A320–214, –232, and
–233 airplanes.
(4) Airbus Model A321–211, –212, –213,
–231, and –232 airplanes.
(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 aluminum alloy with
inadequate heat treatment had been delivered
and used on several structural parts. We are
issuing this AD to detect and replace
structural parts made of aluminum alloy with
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inadequate heat treatment. 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
Within 6 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, cargo compartment, and frame
structural parts identified in the ‘‘Affected P/
N (part number)’’ column of tables 1, 2, and
3 to paragraphs (g) and (i) of this AD to
determine if aluminum alloy with inadequate
heat treatment was used, in accordance with
the Accomplishment Instructions of the
applicable service information identified in
paragraphs (g)(1), (g)(2), and (g)(3) of this AD,
except as required by paragraph (h) of this
AD.
(1) For cabin structural parts: Airbus
Service Bulletin A320–53–1292, dated July
23, 2015; including Appendixes 01 and 02,
dated July 23, 2015.
(2) For cargo compartment structural parts:
Airbus Service Bulletin A320–53–1293,
dated July 30, 2015; including Appendixes
01 and 02, dated July 30, 2015.
(3) For frame structural parts: Airbus
Service Bulletin A320–53–1294, dated July
23, 2015; including Appendixes 01 and 02,
dated July 23, 2015.
TABLE 1 TO PARAGRAPHS (g) AND (i)
OF THIS AD—Parts To Be Inspected/Installed
[Airbus Service Bulletin A320–53–1292]
Affected P/N
D2127245500000
D2127247600200
D2127247600300
D2127399900200
D2127399900300
D2127698900800
D2127698902400
D2527075131200
D2527075131300
D2527075138000
D2527075138100
D2527075138200
D2527075138300
D2527075138600
D2527075138800
D2527240220600
D2527240220700
D2527240220800
D9249591201000
D9249591201800
D9249591227800
D9249591227900
D9249591228000
D9249591228100
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Acceptable
replacement P/N
Area
D2127245500000
D2127247600200
D2127247600300
D2127399900200
D2127399900300
D2127698900800
D2127698902400
D2527075131251
D2527075131351
D2527075138000
D2527075138100
D2527075138200
D2527075138300
D2527075138651
D2527075138851
D2527240220651
D2527240220751
D2527240220851
D9249591201000
D9249591201800
D9249591227851
D9249591227951
D9249591228051
D9249591228151
Cabin.
Cabin.
Cabin.
Cabin.
Cabin.
Cabin.
Cabin.
Cabin.
Cabin.
Cabin.
Cabin.
Cabin.
Cabin.
Cabin.
Cabin.
Cabin.
Cabin.
Cabin.
Cabin.
Cabin.
Cabin.
Cabin.
Cabin.
Cabin.
Federal Register / Vol. 82, No. 47 / Monday, March 13, 2017 / Rules and Regulations
TABLE 2 TO PARAGRAPHS (g) AND (i)
OF THIS AD—Parts To Be Inspected/Installed
[Airbus Service Bulletin A320–53–1293]
Acceptable
replacement P/N
Affected P/N
D2707033520000
D2827027120000
D2827093500400
D2907013701200
D2907013800400
D3247012900000
D3817003820000
D3817012320200
D3837021201600
D3837033300400
D4918518320200
D5347043420400
D9248511000000
D9249254100200
D9249282300000
Area
D2707033520000
D2827027120000
D2827093500400
D2907013701251
D2907013800451
D3247012900051
D3817003820000
D3817012320251
D3837021201600
D3837033300400
D4918518320200
D5347043420451
D9248511000051
D9249254100251
D9249282300000
Cargo.
Cargo.
Cargo.
Cargo.
Cargo.
Cargo.
Cargo.
Cargo.
Cargo.
Cargo.
Cargo.
Cargo.
Cargo.
Cargo.
Cargo.
TABLE 3 TO PARAGRAPHS (g) AND (i)
OF THIS AD—Parts To Be Inspected/Installed
[Airbus Service Bulletin A320–53–1294]
Acceptable
replacement P/N
Affected P/N
jstallworth on DSK7TPTVN1PROD with RULES
D2827098326800
D5347051620600
D5347051720600
D5347057120000
D5347067520600
D5347067521400
D5347067520800
D5347067521000
D5347067521600
D5347067620600
D5347067720200
D5347067720400
D5347986520200
Area
D2827098326851
D5347051620651
D5347051720651
D5347057120051
D5347067520651
D5347067521451
D5347067520851
D5347067521051
D5347067521651
D5347067620600
D5347067720251
D5347067720451
D5347986520251
Frame.
Frame.
Frame.
Frame.
Frame.
Frame.
Frame.
Frame.
Frame.
Frame.
Frame.
Frame.
Frame.
(h) Exception to Paragraph (g) of This AD
Where Subtask 531293–832–207–001 of
Airbus Service Bulletin A320–53–1293,
dated July 23, 2015; including Appendixes
01 and 02, dated July 23, 2015, specifies
inspecting Item 19 of Figure A–GVAAA for
material heat treatment conformity, and that
figure (incorrectly) identifies the inspection
area for Item 19 as the four hinge brackets
adjacent to the A-profile, this AD requires
inspecting part number D491–85183–202–00,
which is the A-profile, and not just the
brackets.
Note 1 to paragraph (h) of this AD: Airbus
Technical Adaptation 80095365/011/2016,
Issue 1, dated December 1, 2016 (‘‘TA’’)
specifies that for Figure A–GVAAA, Sheet 01,
of Airbus Service Bulletin A320–53–1293,
dated July 30, 2015, Item 19 should point to
part number D491–85183–202–00 (and not
just to the brackets). The TA also specifies
that for Figure A–GRAAA, Sheet 01, of
Airbus Service Bulletin A320–53–1293,
dated July 30, 2015, the correct Item 19
identification is part number D491–85183–
202–00.
(i) Replacement
If during the measurement required by
paragraph (g) of this AD, any affected part
number specified in table 1, 2, or 3 to
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paragraphs (g) and (i) of this AD is found to
have a measured value greater than that
specified in Figure A–GFAAA, Sheet 01,
‘‘Inspection Flowchart,’’ of the applicable
service information identified in paragraphs
(g)(1), (g)(2), and (g)(3) of this AD: Before
further flight, replace the affected part with
the corresponding acceptable replacement
part specified in table 1, 2, or 3 to paragraphs
(g) and (i) of this AD, in accordance with the
Accomplishment Instructions of the
applicable service information identified in
paragraphs (g)(1), (g)(2), and (g)(3) of this AD.
(j) No Reporting Requirement
Although the service information
identified in paragraphs (g)(1), (g)(2), and
(g)(3) of this AD specifies to submit certain
information to the manufacturer, this AD
does not include that requirement.
(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, 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:
Sanjay Ralhan, Aerospace Engineer,
International Branch, ANM–116, Transport
Airplane Directorate, FAA, 1601 Lind
Avenue SW., Renton, WA 98057–3356;
telephone: 425–227–1405; 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.
(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.
PO 00000
Frm 00007
Fmt 4700
Sfmt 4700
13385
(l) Related Information
Refer to Mandatory Continuing
Airworthiness Information (MCAI) EASA AD
2015–0219, dated November 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–2016–6431.
(m) 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 A320–53–1292,
dated July 23, 2015; including Appendixes
01 and 02, dated July 23, 2015.
(ii) Airbus Service Bulletin A320–53–1293,
dated July 30, 2015; including Appendixes
01 and 02, dated July 30, 2015.
(iii) Airbus Service Bulletin A320–53–
1294, dated July 23, 2015; including
Appendixes 01 and 02, dated July 23, 2015.
(3) For service information identified in
this AD, contact Airbus, Airworthiness
Office—EIAS, 1 Rond Point Maurice
Bellonte, 31707 Blagnac Cedex, France;
telephone: +33 5 61 93 36 96; fax: +33 5 61
93 44 51; email: account.airworth-eas@
airbus.com; Internet: https://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: https://
www.archives.gov/federal-register/cfr/ibrlocations.html.
Issued in Renton, Washington, on March 2,
2017.
Michael Kaszycki,
Acting Manager, Transport Airplane
Directorate, Aircraft Certification Service.
[FR Doc. 2017–04657 Filed 3–10–17; 8:45 am]
BILLING CODE 4910–13–P
DEPARTMENT OF TRANSPORTATION
Federal Aviation Administration
14 CFR Part 39
[Docket No. FAA–2016–8183; Directorate
Identifier 2015–NM–083–AD; Amendment
39–18822; AD 2017–05–11]
RIN 2120–AA64
Airworthiness Directives; Bombardier,
Inc. Airplanes
Federal Aviation
Administration (FAA), Department of
Transportation (DOT).
ACTION: Final rule.
AGENCY:
E:\FR\FM\13MRR1.SGM
13MRR1
]]>Agencies
[Federal Register Volume 82, Number 47 (Monday, March 13, 2017)]
[Rules and Regulations]
[Pages 13382-13385]
From the Federal Register Online via the Government Publishing Office [www.gpo.gov]
[FR Doc No: 2017-04657]
-----------------------------------------------------------------------
DEPARTMENT OF TRANSPORTATION
Federal Aviation Administration
14 CFR Part 39
[Docket No. FAA-2016-6431; Directorate Identifier 2015-NM-182-AD;
Amendment 39-18823; AD 2017-05-12]
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 A318-112 airplanes, A319-111, -112, -115, -132, and -133
airplanes, A320-214, -232, and -233 airplanes, and A321-211, -212, -
213, -231, and -232 airplanes. This AD was prompted by a quality
control review on the final assembly line, which determined that
aluminum alloy with inadequate heat treatment had been delivered and
used on several structural parts. This AD requires a one-time eddy
current conductivity measurement of certain cabin, cargo compartment,
and frame structural parts to determine if aluminum alloy with
inadequate heat treatment was used, and replacement if necessary. We
are issuing this AD to address the unsafe condition on these products.
DATES: This AD is effective April 17, 2017.
The Director of the Federal Register approved the incorporation by
reference of certain publications listed in this AD as of April 17,
2017.
ADDRESSES: For service information identified in this final rule,
contact Airbus, Airworthiness Office--EIAS, 1 Rond Point Maurice
Bellonte, 31707 Blagnac Cedex, France; telephone: +33 5 61 93 36 96;
fax: +33 5 61 93 44 51; email: account.airworth-eas@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. It is also available on the
Internet at https://www.regulations.gov by searching for and locating
Docket No. FAA-2016-6431.
Examining the AD Docket
You may examine the AD docket on the Internet at https://www.regulations.gov by searching for
[[Page 13383]]
and locating Docket No. FAA-2016-6431; 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: Sanjay Ralhan, Aerospace Engineer,
International Branch, ANM-116, Transport Airplane Directorate, FAA,
1601 Lind Avenue SW., Renton, WA 98057-3356; telephone: 425-227-1405;
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 certain Airbus Model A318-
112 airplanes, A319-111, -112, -115, -132, and -133 airplanes, A320-
214, -232, and -233 airplanes, and A321-211, -212, -213, -231, and -232
airplanes. The NPRM published in the Federal Register on May 11, 2016
(81 FR 29209). The NPRM was prompted by a quality control review on the
final assembly line, which determined that aluminum alloy with
inadequate heat treatment had been delivered and used on several
structural parts. The NPRM proposed to require a one-time eddy current
conductivity measurement of certain cabin, cargo compartment, and frame
structural parts to determine if aluminum alloy with inadequate heat
treatment was used, and replacement if necessary. We are issuing this
AD to detect and replace structural parts made of aluminum alloy with
inadequate heat treatment. 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 2015-0219, dated November 3, 2015 (referred to
after this as the Mandatory Continuing Airworthiness Information, or
``the MCAI''), to correct an unsafe condition for certain Airbus Model
A318-112 airplanes, A319-111, -112, -115, -132, and -133 airplanes,
A320-214, -232, and -233 airplanes, and A321-211, -212, -213, -231, and
-232 airplanes. The MCAI states:
Following an Airbus quality control review on the final assembly
line, it was discovered that aluminum alloy with inadequate heat
treatment were delivered by a supplier for several structural parts.
The results of the investigations highlighted that 1% of the stock
could be impacted by this wrong material.
Structural investigations demonstrated the capability to sustain
the static limits loads, and sufficient fatigue life up to a certain
inspection threshold.
This condition, if not detected and corrected, could reduce the
aeroplane structural integrity following fatigue load.
To address this potential unsafe condition, Airbus issued
Service Bulletin (SB) A320-53-1292, SB A320-53-1293, and SB A320-53-
1294 to provide inspection instructions.
For the reasons described above, this [EASA] AD requires a one-
time Special Detailed Inspection (SDI) [i.e., eddy current
conductivity measurement] of certain cabin, cargo compartment and
frame parts [for material identification] and, depending on
findings, replacement with serviceable parts.
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-
6431.
Comments
We gave the public the opportunity to participate in developing
this AD. The following presents the comment received on the NPRM and
the FAA's response.
Request To Include the Correction in the Technical Adaptation to
Certain Service Information
Virgin America asked that we include the correction in Airbus
Technical Adaptation (TA) 80095365/011/2016, Issue 1, dated December 1,
2016, to Figure A-GVAAA and Figure A-GRAAA of Airbus Service Bulletin
A320-53-1293, dated July 30, 2015, in this AD. Virgin America stated
that the parts shown in Figure A-GVAAA and Figure A-GRAAA and
highlighted for inspection are the four hinge brackets identified as
having part number (P/N) ``D4918518320201, A-profile.'' However, the
correct identification is P/N ``D4918518320200, A-profile.'' Virgin
America noted that Airbus issued TA 80095365/011/2016, Issue 1, to
update Figure A-GVAAA and Figure A-GRAAA of Airbus Service Bulletin
A320-53-1293, dated July 30, 2015, to identify the correct part number.
Virgin America also stated that the TA specified that Airbus Service
Bulletin A320-53-1293 is currently under revision and the correction
will be included when the revision is issued.
We agree with the commenter's request to include the specified
correction. We have added a new paragraph (h) to this AD to provide an
exception to Figure A-GVAAA of Airbus Service Bulletin A320-53-1293,
dated July 30, 2015, which is needed for compliance with paragraph (g)
of this AD. However, Figure A-GRAAA, ``Reporting Sheet,'' of Airbus
Service Bulletin A320-53-1293, dated July 30, 2015, is not needed for
compliance with this AD. We have added a note to paragraph (h) of this
AD to provide the information in Airbus Technical Adaptation (TA)
80095365/011/2016, Issue 1, dated December 1, 2016, which specifies the
corrected information for Figure A-GVAAA and Figure A-GRAAA of Airbus
Service Bulletin A320-53-1293, dated July 30, 2015. We have also added
paragraph (j) to clarify that reporting is not required by this AD;
however, reporting is recommended for research and tracking. We have
redesignated subsequent paragraphs accordingly.
Conclusion
We reviewed the relevant data, considered the comment received, and
determined that air safety and the public interest require adopting
this AD with the changes described previously and 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.
We also determined that these changes will not increase the
economic burden on any operator or increase the scope of this AD.
Related Service Information Under 1 CFR Part 51
We reviewed the following service information:
Airbus Service Bulletin A320-53-1292, dated July 23, 2015;
including Appendixes 01 and 02, dated July 23, 2015.
Airbus Service Bulletin A320-53-1293, dated July 30, 2015;
including Appendixes 01 and 02, dated July 30, 2015.
Airbus Service Bulletin A320-53-1294, dated July 23, 2015;
including Appendixes 01 and 02, dated July 23, 2015.
The service information describes procedures for a one-time eddy
current conductivity measurement of certain cabin, cargo compartment,
and frame structural parts to determine if aluminum alloy with
inadequate heat treatment was used, and replacement of any affected
part with a serviceable part. These documents are distinct since they
[[Page 13384]]
apply to different parts on the airplane. 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 46 airplanes of U.S. registry.
We also estimate that it takes about 6 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 $23,460, or $510 per product.
We have received no definitive data that enables us to provide cost
estimates for the on-condition actions specified in this AD.
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;
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):
2017-05-12 Airbus: Amendment 39-18823; Docket No. FAA-2016-6431;
Directorate Identifier 2015-NM-182-AD.
(a) Effective Date
This AD is effective April 17, 2017.
(b) Affected ADs
None.
(c) Applicability
This AD applies to the Airbus airplanes identified in paragraphs
(c)(1) through (c)(4) of this AD, certificated in any category;
manufacturer serial numbers 4895, 4903, 4911, 4919, 4929, 4938,
4942, 4944, 4946, 4948, and 4951, 4956 through 5541 inclusive, 5544,
5547, 5550, 5551, 5553, 5556, 5559, 5561, 5562, 5563, 5565, 5566,
5570, 5572, 5576, and 5578.
(1) Airbus Model A318-112 airplanes.
(2) Airbus Model A319-111, -112, -115, -132, and -133 airplanes.
(3) Airbus Model A320-214, -232, and -233 airplanes.
(4) Airbus Model A321-211, -212, -213, -231, and -232 airplanes.
(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 aluminum alloy with inadequate
heat treatment had been delivered and used on several structural
parts. We are issuing this AD to detect and replace structural parts
made of aluminum alloy with inadequate heat treatment. 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
Within 6 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, cargo compartment, and frame
structural parts identified in the ``Affected P/N (part number)''
column of tables 1, 2, and 3 to paragraphs (g) and (i) of this AD to
determine if aluminum alloy with inadequate heat treatment was used,
in accordance with the Accomplishment Instructions of the applicable
service information identified in paragraphs (g)(1), (g)(2), and
(g)(3) of this AD, except as required by paragraph (h) of this AD.
(1) For cabin structural parts: Airbus Service Bulletin A320-53-
1292, dated July 23, 2015; including Appendixes 01 and 02, dated
July 23, 2015.
(2) For cargo compartment structural parts: Airbus Service
Bulletin A320-53-1293, dated July 30, 2015; including Appendixes 01
and 02, dated July 30, 2015.
(3) For frame structural parts: Airbus Service Bulletin A320-53-
1294, dated July 23, 2015; including Appendixes 01 and 02, dated
July 23, 2015.
Table 1 to Paragraphs (g) and (i) of This AD--Parts To Be Inspected/
Installed
[Airbus Service Bulletin A320-53-1292]
------------------------------------------------------------------------
Affected P/N Acceptable replacement P/N Area
------------------------------------------------------------------------
D2127245500000 D2127245500000 Cabin.
D2127247600200 D2127247600200 Cabin.
D2127247600300 D2127247600300 Cabin.
D2127399900200 D2127399900200 Cabin.
D2127399900300 D2127399900300 Cabin.
D2127698900800 D2127698900800 Cabin.
D2127698902400 D2127698902400 Cabin.
D2527075131200 D2527075131251 Cabin.
D2527075131300 D2527075131351 Cabin.
D2527075138000 D2527075138000 Cabin.
D2527075138100 D2527075138100 Cabin.
D2527075138200 D2527075138200 Cabin.
D2527075138300 D2527075138300 Cabin.
D2527075138600 D2527075138651 Cabin.
D2527075138800 D2527075138851 Cabin.
D2527240220600 D2527240220651 Cabin.
D2527240220700 D2527240220751 Cabin.
D2527240220800 D2527240220851 Cabin.
D9249591201000 D9249591201000 Cabin.
D9249591201800 D9249591201800 Cabin.
D9249591227800 D9249591227851 Cabin.
D9249591227900 D9249591227951 Cabin.
D9249591228000 D9249591228051 Cabin.
D9249591228100 D9249591228151 Cabin.
------------------------------------------------------------------------
[[Page 13385]]
Table 2 to Paragraphs (g) and (i) of This AD--Parts To Be Inspected/
Installed
[Airbus Service Bulletin A320-53-1293]
------------------------------------------------------------------------
Affected P/N Acceptable replacement P/N Area
------------------------------------------------------------------------
D2707033520000 D2707033520000 Cargo.
D2827027120000 D2827027120000 Cargo.
D2827093500400 D2827093500400 Cargo.
D2907013701200 D2907013701251 Cargo.
D2907013800400 D2907013800451 Cargo.
D3247012900000 D3247012900051 Cargo.
D3817003820000 D3817003820000 Cargo.
D3817012320200 D3817012320251 Cargo.
D3837021201600 D3837021201600 Cargo.
D3837033300400 D3837033300400 Cargo.
D4918518320200 D4918518320200 Cargo.
D5347043420400 D5347043420451 Cargo.
D9248511000000 D9248511000051 Cargo.
D9249254100200 D9249254100251 Cargo.
D9249282300000 D9249282300000 Cargo.
------------------------------------------------------------------------
Table 3 to Paragraphs (g) and (i) of This AD--Parts To Be Inspected/
Installed
[Airbus Service Bulletin A320-53-1294]
------------------------------------------------------------------------
Affected P/N Acceptable replacement P/N Area
------------------------------------------------------------------------
D2827098326800 D2827098326851 Frame.
D5347051620600 D5347051620651 Frame.
D5347051720600 D5347051720651 Frame.
D5347057120000 D5347057120051 Frame.
D5347067520600 D5347067520651 Frame.
D5347067521400 D5347067521451 Frame.
D5347067520800 D5347067520851 Frame.
D5347067521000 D5347067521051 Frame.
D5347067521600 D5347067521651 Frame.
D5347067620600 D5347067620600 Frame.
D5347067720200 D5347067720251 Frame.
D5347067720400 D5347067720451 Frame.
D5347986520200 D5347986520251 Frame.
------------------------------------------------------------------------
(h) Exception to Paragraph (g) of This AD
Where Subtask 531293-832-207-001 of Airbus Service Bulletin
A320-53-1293, dated July 23, 2015; including Appendixes 01 and 02,
dated July 23, 2015, specifies inspecting Item 19 of Figure A-GVAAA
for material heat treatment conformity, and that figure
(incorrectly) identifies the inspection area for Item 19 as the four
hinge brackets adjacent to the A-profile, this AD requires
inspecting part number D491-85183-202-00, which is the A-profile,
and not just the brackets.
Note 1 to paragraph (h) of this AD: Airbus Technical Adaptation
80095365/011/2016, Issue 1, dated December 1, 2016 (``TA'')
specifies that for Figure A-GVAAA, Sheet 01, of Airbus Service
Bulletin A320-53-1293, dated July 30, 2015, Item 19 should point to
part number D491-85183-202-00 (and not just to the brackets). The TA
also specifies that for Figure A-GRAAA, Sheet 01, of Airbus Service
Bulletin A320-53-1293, dated July 30, 2015, the correct Item 19
identification is part number D491-85183-202-00.
(i) Replacement
If during the measurement required by paragraph (g) of this AD,
any affected part number specified in table 1, 2, or 3 to paragraphs
(g) and (i) of this AD is found to have a measured value greater
than that specified in Figure A-GFAAA, Sheet 01, ``Inspection
Flowchart,'' of the applicable service information identified in
paragraphs (g)(1), (g)(2), and (g)(3) of this AD: Before further
flight, replace the affected part with the corresponding acceptable
replacement part specified in table 1, 2, or 3 to paragraphs (g) and
(i) of this AD, in accordance with the Accomplishment Instructions
of the applicable service information identified in paragraphs
(g)(1), (g)(2), and (g)(3) of this AD.
(j) No Reporting Requirement
Although the service information identified in paragraphs
(g)(1), (g)(2), and (g)(3) of this AD specifies to submit certain
information to the manufacturer, this AD does not include that
requirement.
(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, 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: Sanjay
Ralhan, Aerospace Engineer, International Branch, ANM-116, Transport
Airplane Directorate, FAA, 1601 Lind Avenue SW., Renton, WA 98057-
3356; telephone: 425-227-1405; 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.
(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.
(l) Related Information
Refer to Mandatory Continuing Airworthiness Information (MCAI)
EASA AD 2015-0219, dated November 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-
2016-6431.
(m) 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 A320-53-1292, dated July 23, 2015;
including Appendixes 01 and 02, dated July 23, 2015.
(ii) Airbus Service Bulletin A320-53-1293, dated July 30, 2015;
including Appendixes 01 and 02, dated July 30, 2015.
(iii) Airbus Service Bulletin A320-53-1294, dated July 23, 2015;
including Appendixes 01 and 02, dated July 23, 2015.
(3) For service information identified in this AD, contact
Airbus, Airworthiness Office--EIAS, 1 Rond Point Maurice Bellonte,
31707 Blagnac Cedex, France; telephone: +33 5 61 93 36 96; fax: +33
5 61 93 44 51; email: account.airworth-eas@airbus.com; Internet:
https://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: https://www.archives.gov/federal-register/cfr/ibr-locations.html.
Issued in Renton, Washington, on March 2, 2017.
Michael Kaszycki,
Acting Manager, Transport Airplane Directorate, Aircraft Certification
Service.
[FR Doc. 2017-04657 Filed 3-10-17; 8:45 am]
BILLING CODE 4910-13-P
