Airworthiness Directives; Airbus Airplanes, 44903-44907 [2017-20567]
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Federal Register / Vol. 82, No. 186 / Wednesday, September 27, 2017 / Rules and Regulations
(j) New Provision: No Alternative Actions or
Intervals
After the action required by paragraph (i)
of this AD has been done, 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 (k)(1)
of this AD.
asabaliauskas on DSKBBXCHB2PROD with RULES
(k) Other FAA AD Provisions
The following provisions also apply to this
AD:
(1) Alternative Methods of Compliance
(AMOCs): The Manager, International
Branch, Transport Standards Branch, FAA,
has the authority to approve AMOCs for this
AD, if requested using the procedures found
in 14 CFR 39.19. In accordance with 14 CFR
39.19, send your request to your principal
inspector or local Flight Standards District
Office, as appropriate. If sending information
directly to the International Branch, send it
to ATTN: Sanjay Ralhan, Aerospace
Engineer, International Branch, Transport
Standards Branch, FAA, 1601 Lind Avenue
SW., Renton, WA 98057–3356; telephone:
425–227–1405; fax: 425–227–1149.
Information may be emailed to: 9-ANM-116AMOC-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.
(ii) AMOCs approved previously for AD
2014–26–10 are approved as AMOCs for the
corresponding provisions of paragraph (g) of
this AD.
(iii) AMOCs approved previously for AD
2014–26–10, which are included in the
AMOC letters specified in paragraphs
(k)(1)(iii)(A) and (k)(1)(iii)(B), are approved
as AMOCs for the provisions of paragraph (i)
of this AD.
(A) AMOC letter ANM–116–17–002R1,
dated November 14, 2016.
(B) AMOC letter ANM–116–17–323, dated
June 12, 2017.
(2) Contacting the Manufacturer: As of the
effective date of this AD, for any requirement
in this AD to obtain corrective actions from
a manufacturer, the action must be
accomplished using a method approved by
the Manager, International Section, Transport
Standards Branch, FAA; or the European
Aviation Safety Agency (EASA); or EASA
Design Organization Approval (DOA). If
approved by the DOA, the approval must
include the DOA-authorized signature.
(l) Related Information
(1) Refer to Mandatory Continuing
Airworthiness Information (MCAI) EASA AD
2016–0093, dated May 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–2017–0248.
(2) For more information about this AD,
contact Sanjay Ralhan, Aerospace Engineer,
International Section, Transport Standards
Branch, 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-AMOCREQUESTS@faa.gov.
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(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.
(3) The following service information was
approved for IBR on November 1, 2017.
(i) Airbus A318/A319/A320/A321
Airworthiness Limitations Section (ALS) Part
4, ‘‘System Equipment Maintenance
Requirements (SEMR),’’ Revision 03 at Issue
02, dated January 22, 2016.
(ii) Reserved.
(4) The following service information was
approved for IBR on February 25, 2015 (80
FR 2813, January 21, 2015).
(i) Airbus A318/A319/A320/A321
Airworthiness Limitations Section, ALS Part
4, ‘‘Aging Systems Maintenance,’’ Revision
01, dated June 15, 2012. The revision level
of this document is identified on only the
title page and in the Record of Revisions. The
revision date is not identified on the title
page of this document.
(ii) Reserved.
(5) 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.
(6) 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.
(7) 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
September 14, 2017.
Jeffrey E. Duven,
Director, System Oversight Division, Aircraft
Certification Service.
[FR Doc. 2017–20113 Filed 9–26–17; 8:45 am]
BILLING CODE 4910–13–P
PO 00000
44903
DEPARTMENT OF TRANSPORTATION
Federal Aviation Administration
14 CFR Part 39
[Docket No. FAA–2017–0498; Product
Identifier 2016–NM–175–AD; Amendment
39–19053; AD 2017–19–23]
RIN 2120–AA64
Airworthiness Directives; Airbus
Airplanes
Federal Aviation
Administration (FAA), Department of
Transportation (DOT).
ACTION: Final rule.
AGENCY:
We are superseding
Airworthiness Directive (AD) 2015–15–
10, which applied to all Airbus Model
A318, A319, A320, and A321 series
airplanes. AD 2015–15–10 required
repetitive inspections of the trimmable
horizontal stabilizer actuator (THSA) for
damage, and replacement if necessary;
and replacement of the THSA after
reaching a certain life limit. This AD
requires repetitive detailed inspections
of certain THSAs, and related
investigative and corrective actions if
necessary. This AD was prompted by
the establishment of an additional life
limit for the THSA, based on flight
cycles. In addition, the THSA
manufacturer has issued service
information which, when accomplished,
increases the life limit of the THSA. We
are issuing this AD to address the unsafe
condition on these products.
DATES: This AD is effective November 1,
2017.
The Director of the Federal Register
approved the incorporation by reference
of a certain publication listed in this AD
as of November 1, 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
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 https://
www.regulations.gov by searching for
and locating Docket No. FAA–2017–
0498.
SUMMARY:
Examining the AD Docket
You may examine the AD docket on
the Internet at https://
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44904
Federal Register / Vol. 82, No. 186 / Wednesday, September 27, 2017 / Rules and Regulations
www.regulations.gov by searching for
and locating Docket No. FAA–2017–
0498; 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 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 Section, Transport
Standards Branch, 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 to supersede AD 2015–15–10,
Amendment 39–18219 (80 FR 43928,
July 24, 2015) (‘‘AD 2015–15–10’’). AD
2015–15–10 applied to all Airbus Model
A318, A319, A320, and A321 series
airplanes. The NPRM published in the
Federal Register on June 2, 2017 (82 FR
25542). The NPRM was prompted by the
establishment of an additional life limit
for the THSA, based on flight cycles.
The NPRM proposed to require
repetitive detailed inspections of certain
THSAs, and related investigative and
corrective actions if necessary. We are
issuing this AD to detect and correct
wear of the THSA, which could reduce
the remaining life of the THSA, possibly
resulting in premature failure and
consequent reduced controllability 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 2016–0184, dated September
13, 2016 (referred to after this as the
Mandatory Continuing Airworthiness
Information, or ‘‘the MCAI’’), to correct
an unsafe condition for all Airbus
Model A318 and A319 series airplanes;
Model A320–211, –212, –214, –231,
–232, and –233 airplanes; and Model
A321–111, –112, –131, –211, –212,
–213, –231, and –232 airplanes. The
MCAI states:
In the frame of the A320 Extended Service
Goal (ESG) project and the study on the
Trimmable Horizontal Stabilizer Actuator
(THSA), a sampling programme of in-service
units was performed and several cases of
wear at different THSA levels were reported.
This condition, if not detected and
corrected, would reduce the remaining life of
the THSA, possibly resulting in premature
failure and consequent reduced control of the
aeroplane.
Prompted by these findings, Airbus issued
Service Bulletin (SB) A320–27–1227 to
provide THSA inspection instructions.
Consequently, EASA issued AD 2014–0011
(later revised) [which corresponds to AD
2015–15–10] to require repetitive inspections
of the THSA [and related investigative and
corrective actions] and to introduce a life
limit for the THSA, based on flight hours
(FH).
Since EASA AD 2014–0011R1 was issued,
an additional life limitation has been
established, based on flight cycles (FC).
Furthermore, United Technologies
Corporation Aerospace Systems (UTAS), the
THSA manufacturer, issued an SB which,
after accomplishment on THSA, increases the
life limit of the THSA.
For the reasons described above, this
[EASA] AD retains the requirements of EASA
AD 2014–0011R1, which is superseded, and
introduces an additional FC life limit for the
affected THSA. This [EASA] AD also
provides a revised life limit for the THSA
after UTAS SB accomplishment on that
THSA.
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–2017–
0498.
Comments
We gave the public the opportunity to
participate in developing this AD. We
considered the comments received. Air
Line Pilots Association, International
(ALPA) and United Airlines expressed
their support for the NPRM.
Changes Made to This AD
The NPRM specified that a THSA that
had been repaired in-shop as specified
in UTAS Component Maintenance
Manual 27–44–51 would be an
equivalent method of compliance for the
initial inspection required by paragraph
(h) of this AD. We have revised
paragraph (m) of this AD to specify that
a THSA that has been repaired in-shop
using a method approved by the
Manager, International Section,
Transport Standards Branch, FAA; or
the EASA; or Airbus’s EASA Design
Organization Approval (DOA), is
acceptable for compliance with the
initial inspection required by paragraph
(h) of this AD. We have also added Note
1 to paragraph (m) of this AD to
reference UTAS Component
Maintenance Manual 27–44–51 as an
additional source of guidance for the inshop repair of the THSA.
Conclusion
We reviewed the relevant data,
considered the comments 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
Airbus has issued Service Bulletin
A320–27–1227, Revision 03, dated April
29, 2016. This service information
describes procedures for repetitive
special detailed inspections for wear of
the THSA, and related investigative and
corrective actions.
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 1,182
airplanes of U.S. registry.
We estimate the following costs to
comply with this AD:
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ESTIMATED COSTS
Action
Labor cost
Inspections .............
6 work-hours × $85 per hour =
$510 per inspection cycle.
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Parts cost
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Cost per product
$0
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Cost on U.S. operators
$510 per inspection cycle ...........
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$602,820 per inspection cycle.
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We have received no definitive data
that would enable us to provide cost
estimates for the spectrometric analysis
of the oil drained from the THSA
gearbox. We estimate the following costs
to do any necessary replacements or
overhauls that would be required based
on the results of the inspection. We
44905
have no way of determining the number
of aircraft that might need these
replacements or overhauls:
ON-CONDITION COSTS
Labor cost
Replacement of THSA (retained from AD 2015–15–
10).
Overhaul of THSA (new action) ...................................
11 work-hours × $85 per hour = $935 .........................
$240,000
$240,935
66 work-hours × $85 per hour = $5,610 ......................
115,000
120,610
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.
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.
Regulatory Findings
§ 39.13
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
asabaliauskas on DSKBBXCHB2PROD with RULES
Parts cost
Cost per
product
Action
[Amended]
■
2. The FAA amends § 39.13 by
removing Airworthiness Directive (AD)
2015–15–10, Amendment 39–18219 (80
FR 43928, July 24, 2015), and adding the
following new AD:
2017–19–23 Airbus: Amendment 39–19053;
Docket No. FAA–2017–0498; Product
Identifier 2016–NM–175–AD.
(a) Effective Date
This AD is effective November 1, 2017.
(b) Affected ADs
This AD replaces AD 2015–15–10,
Amendment 39–18219 (80 FR 43928, July 24,
2015) (‘‘AD 2015–15–10’’).
(c) Applicability
This AD applies to the airplanes identified
in paragraphs (c)(1) through (c)(4) of this AD,
certificated in any category, all manufacturer
serial numbers.
(1) Airbus Model A318–111, –112, –121,
and –122 airplanes.
(2) Airbus Model A319–111, –112, –113,
–114, –115, –131, –132, and –133 airplanes.
(3) Airbus Model A320–211, –212, –214,
–231, –232, and –233 airplanes.
(4) Airbus Model A321–111, –112, –131,
–211, –212, –213, –231, and –232 airplanes.
(d) Subject
Air Transport Association (ATA) of
America Code 27, Flight controls.
(e) Reason
This AD was prompted by reports of wear
at different levels in the trimmable horizontal
stabilizer actuator (THSA). We are issuing
this AD to detect and correct wear of the
THSA, which could reduce the remaining life
of the THSA, possibly resulting in premature
failure and consequent reduced
controllability of the airplane.
(f) Compliance
Comply with this AD within the
compliance times specified, unless already
done.
(g) Serviceable THSA Definition
For the purposes of this AD, a serviceable
THSA is a THSA that does not exceed the life
limits as identified in table 1 to paragraphs
(g) and (j) of this AD.
TABLE 1 TO PARAGRAPHS (G) AND (J) OF THIS AD—THSA Life Limits
Configuration, based on service bulletin (SB) embodiment
Compliance time (whichever occurs first)
THSA on which United Technologies Corporation Aerospace Systems
(UTAS) SB 47145–27–19 has not been embodied.
Before exceeding 67,500 flight hours (FH) since first installation on an
airplane, or before exceeding 48,000 flight cycles (FC) since first installation on an airplane.
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Federal Register / Vol. 82, No. 186 / Wednesday, September 27, 2017 / Rules and Regulations
TABLE 1 TO PARAGRAPHS (G) AND (J) OF THIS AD—THSA Life Limits—Continued
Configuration, based on service bulletin (SB) embodiment
Compliance time (whichever occurs first)
THSA on which UTAS SB 47145–27–19 has been embodied ...............
Before exceeding 52,500 FH after embodiment of UTAS SB 47145–
27–19 on an airplane, without exceeding 120,000 FH since first installation on an airplane; or before exceeding 27,000 FC after embodiment of UTAS SB 47145–27–19 on an airplane, without exceeding 75,000 FC since first installation on an airplane.
(h) Repetitive Inspection and Related
Investigative Actions
For any airplane on which UTAS Service
Bulletin 47145–27–19 has not been
embodied: Before the THSA exceeds 48,000
flight hours or 30,000 flight cycles,
whichever occurs first since first installation
on an airplane, do a special detailed
inspection of the THSA and do all applicable
related investigative actions, in accordance
with the Accomplishment Instructions of
Airbus Service Bulletin A320–27–1227,
Revision 03, dated April 29, 2016. Do all
applicable related investigative actions at the
applicable times specified in paragraph 1.E.,
‘‘Compliance’’ of Airbus Service Bulletin
A320–27–1227, Revision 03, dated April 29,
2016. Repeat the inspections thereafter at
intervals not to exceed 24 months.
(i) Corrective Action
If, during any inspection required by
paragraph (h) of this AD, any finding as
described in the Accomplishment
Instructions of Airbus Service Bulletin A320–
27–1227, Revision 03, dated April 29, 2016,
is identified: At the applicable time
(depending on the applicable finding)
specified in paragraph 1.E., ‘‘Compliance,’’ of
Airbus Service Bulletin A320–27–1227,
Revision 03, dated April 29, 2016, replace the
THSA with a serviceable THSA, as specified
in paragraph (g) of this AD, in accordance
with the Accomplishment Instructions of
Airbus Service Bulletin A320–27–1227,
Revision 03, dated April 29, 2016.
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(j) THSA Replacement
Within the applicable compliance time
specified in table 1 to paragraphs (g) and (j)
of this AD, replace each THSA with a
serviceable THSA, as specified in paragraph
(g) of this AD, in accordance with the
Accomplishment Instructions of Airbus
Service Bulletin A320–27–1227, Revision 03,
dated April 29, 2016.
(k) Replacement of a THSA: Not Terminating
Action
Replacement of a THSA on an airplane, as
required by paragraph (i) or (j) of this AD,
does not constitute terminating action for the
repetitive inspections required by paragraph
(h) of this AD for that airplane, unless the
THSA has been overhauled as specified in
UTAS Service Bulletin 47145–27–19 (i.e.,
post-service bulletin).
(l) Optional Terminating Action: Overhaul of
THSA
Accomplishment of a modification of an
airplane by installing a THSA that has been
overhauled as specified in UTAS Service
Bulletin 47145–27–19 constitutes terminating
action for the repetitive inspections required
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by paragraph (h) of this AD, provided that,
following modification, no THSA is
reinstalled on the airplane unless it has been
overhauled as specified in UTAS Service
Bulletin 47145–27–19.
(m) Replacement THSA Equivalency
As of the effective date of this AD: A THSA
that has been repaired in-shop is acceptable
for compliance with the initial inspection
required by paragraph (h) of this AD,
provided that repair was done 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).
Note 1 to paragraph (m) of this AD:
Guidance for THSA repair in-shop can be
found in UTAS Component Maintenance
Manual 27–44–51.
(n) Parts Installation Limitation
As of the effective date of this AD: Do not
install on any airplane a THSA unless it is
a serviceable THSA as specified in paragraph
(g) of this AD.
(o) Credit for Previous Actions
This paragraph provides credit for the
actions required by paragraphs (h) and (i) of
this AD, if those actions were performed
before the effective date of this AD using any
of the service information specified in
paragraphs (o)(1), (o)(2), or (o)(3) of this AD.
(1) Airbus Service Bulletin A320–27–1227,
dated July 1, 2013, which is not incorporated
by reference in this AD.
(2) Airbus Service Bulletin A320–27–1227,
Revision 01, dated October 7, 2013, which
was incorporated by reference in AD 2015–
15–10.
(3) Airbus Service Bulletin A320–27–1227,
Revision 02, dated February 2, 2015, which
is not incorporated by reference in this AD.
(p) 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 International Section, send it
to the attention of the person identified in
paragraph (q)(2) of this AD. Information may
be emailed to: 9-ANM-116-AMOCREQUESTS@faa.gov. Before using any
approved AMOC, notify your appropriate
principal inspector, or lacking a principal
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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
EASA; or Airbus’s EASA DOA. If approved
by the DOA, the approval must include the
DOA-authorized signature.
(3) Required for Compliance (RC): If any
service information contains procedures or
tests that are identified as RC, those
procedures and tests must be done to comply
with this AD; any procedures or tests that are
not identified as RC are recommended. Those
procedures and tests that are not identified
as RC may be deviated from using accepted
methods in accordance with the operator’s
maintenance or inspection program without
obtaining approval of an AMOC, provided
the procedures and tests identified as RC can
be done and the airplane can be put back in
an airworthy condition. Any substitutions or
changes to procedures or tests identified as
RC require approval of an AMOC.
(q) Related Information
(1) Refer to Mandatory Continuing
Airworthiness Information (MCAI) EASA
Airworthiness Directive 2016–0184, dated
September 13, 3016, 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–2017–0498.
(2) For more information about this AD,
contact Sanjay Ralhan, Aerospace Engineer,
International Section, Transport Standards
Branch, FAA, 1601 Lind Avenue SW.,
Renton, WA 98057–3356; telephone 425–
227–1405; fax 425–227–1149.
(3) Service information identified in this
AD that is not incorporated by reference is
available at the addresses specified in
paragraphs (r)(3) and (r)(4) of this AD.
(r) 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 A320–27–1227,
Revision 03, dated April 29, 2016.
(ii) Reserved.
(3) For Airbus service information
identified in this AD, contact Airbus,
Airworthiness Office—EIAS, 1 Rond Point
Maurice Bellonte, 31707 Blagnac Cedex,
E:\FR\FM\27SER1.SGM
27SER1
Federal Register / Vol. 82, No. 186 / Wednesday, September 27, 2017 / Rules and Regulations
asabaliauskas on DSKBBXCHB2PROD with RULES
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 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: https://
www.archives.gov/federal-register/cfr/ibrlocations.html.
This AD is effective October 12,
2017.
The Director of the Federal Register
approved the incorporation by reference
of certain publications listed in this AD
as of August 28, 2017 (82 FR 34251, July
24, 2017).
We must receive comments on this
AD by November 13, 2017.
ADDRESSES: You may send comments,
using the procedures found in 14 CFR
11.43 and 11.45, by any of the following
methods:
• Federal eRulemaking Portal: Go to
https://www.regulations.gov. Follow the
Issued in Renton, Washington, on
instructions for submitting comments.
September 14, 2017.
• Fax: 202–493–2251.
Jeffrey E. Duven,
• Mail: U.S. Department of
Director, System Oversight Division, Aircraft
Transportation, Docket Operations, M–
Certification Service.
30, West Building Ground Floor, Room
[FR Doc. 2017–20567 Filed 9–26–17; 8:45 am]
W12–140, 1200 New Jersey Avenue SE.,
BILLING CODE 4910–13–P
Washington, DC 20590.
• Hand Delivery: U.S. Department of
DEPARTMENT OF TRANSPORTATION Transportation, Docket Operations, M–
30, West Building Ground Floor, Room
W12–140, 1200 New Jersey Avenue SE.,
Federal Aviation Administration
Washington, DC, between 9 a.m. and 5
p.m., Monday through Friday, except
14 CFR Part 39
Federal holidays.
[Docket No. FAA–2017–0813; Product
For Airbus service information
Identifier 2017–NM–109–AD; Amendment
identified in this final rule, contact
39–19059; AD 2017–20–02]
Airbus, Airworthiness Office–EIAS, 1
RIN 2120–AA64
Rond Point Maurice Bellonte, 31707
Blagnac Cedex, France; telephone: +33 5
Airworthiness Directives; Airbus
61 93 36 96; fax: +33 5 61 93 44 51;
Airplanes
email: account.airworth-eas@
airbus.com; Internet: https://
AGENCY: Federal Aviation
www.airbus.com.
Administration (FAA), Department of
You may view this referenced service
Transportation (DOT).
information at the FAA, Transport
ACTION: Final rule; request for
Standards Branch, 1601 Lind Avenue
comments.
SW., Renton, WA. For information on
SUMMARY: We are superseding
the availability of this material at the
Airworthiness Directive (AD) 2017–13–
FAA, call 425–227–1221. It is also
05, which applied to all Airbus Model
available on the Internet at https://
A330–200, A330–300, A340–200, A340– www.regulations.gov by searching for
300, A340–500, and A340–600 series
and locating Docket No. FAA–2017–
airplanes. AD 2017–13–05 required an
0813.
inspection, corrective actions if
Examining the AD Docket
necessary, lubrication of the ball-nut,
You may examine the AD docket on
modification of the trimmable
the Internet at https://
horizontal stabilizer actuator (THSA),
www.regulations.gov by searching for
and additional work for previously
and locating Docket No. FAA–2017–
modified airplanes. For certain
0813; or in person at the Docket
airplanes, AD 2017–13–05 required
Management Facility between 9 a.m.
installation of an electronic harness,
and 5 p.m., Monday through Friday,
terminating actions, and a ball-screw
except Federal holidays. The AD docket
assembly inspection. This AD clarifies
contains this AD, the regulatory
the formatting of a figure in the
evaluation, any comments received, and
published version of AD 2017–13–05.
other information. The street address for
This AD was prompted by reports
the Docket Office (telephone 800–647–
indicating that affected parties
5527) is Docket Management Facility,
misinterpreted the intent of a figure as
U.S. Department of Transportation,
formatted in the published version of
Docket Operations, M–30, West
AD 2017–13–05, which could result in
Building Ground Floor, Room W12–140,
a negative effect on compliance. We are
1200 New Jersey Avenue SE.,
issuing this AD to address the unsafe
Washington, DC 20590.
condition on these products.
VerDate Sep<11>2014
17:24 Sep 26, 2017
Jkt 241001
DATES:
PO 00000
Frm 00029
Fmt 4700
Sfmt 4700
44907
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
On June 15, 2017, we issued AD
2017–13–05, Amendment 39–18935 (82
FR 34251, July 24, 2017) (‘‘AD 2017–13–
05’’), which applied to all Airbus Model
A330–200, A330–300, A340–200, A340–
300, A340–500, and A340–600 series
airplanes. AD 2017–13–05 was
prompted by the need for a modification
that automatically detects failure of the
ball-screw assembly. AD 2017–13–05
required an inspection, corrective
actions if necessary, lubrication of the
ball-nut, modification of the trimmable
horizontal stabilizer actuator (THSA),
and additional work for previously
modified airplanes. For certain
airplanes, AD 2017–13–05 required
installation of an electronic harness,
terminating actions, and a ball-screw
assembly inspection. We issued AD
2017–13–05 to detect and correct wear
on the THSA, possibly resulting in
damage to the ball-screw and fail-safe
nut, which could jam the THSA and
result in reduced control of the airplane.
Since we issued AD 2017–13–05, we
have received reports indicating that
affected parties could misinterpret the
identity of applicable service
information to use for the modification,
due to the formatting of figure 2 to
paragraphs (h) and (i) in the published
version of AD 2017–13–05. Since the
published figure could result in a
negative effect on compliance, we have
determined that clarification of the
formatting of the published figure is
necessary.
The European Aviation Safety Agency
(EASA), which is the Technical Agent
for the Member States of the European
Union, has issued EASA AD 2014–0219,
dated September 29, 2014 (referred to
after this as the Mandatory Continuing
Airworthiness Information, or ‘‘the
MCAI’’), to correct an unsafe condition
for all Airbus Model A330 and Model
A340 series airplanes. (Model A330–
223F and A330–243F airplanes were
removed from AD 2017–13–05 to
correspond with the MCAI.) The EASA
AD is referenced in AD 2017–13–05.
EASA has not revised its AD since the
issuance of AD 2017–13–05.
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–2017–
0813.
E:\FR\FM\27SER1.SGM
27SER1
Agencies
[Federal Register Volume 82, Number 186 (Wednesday, September 27, 2017)]
[Rules and Regulations]
[Pages 44903-44907]
From the Federal Register Online via the Government Publishing Office [www.gpo.gov]
[FR Doc No: 2017-20567]
-----------------------------------------------------------------------
DEPARTMENT OF TRANSPORTATION
Federal Aviation Administration
14 CFR Part 39
[Docket No. FAA-2017-0498; Product Identifier 2016-NM-175-AD; Amendment
39-19053; AD 2017-19-23]
RIN 2120-AA64
Airworthiness Directives; Airbus Airplanes
AGENCY: Federal Aviation Administration (FAA), Department of
Transportation (DOT).
ACTION: Final rule.
-----------------------------------------------------------------------
SUMMARY: We are superseding Airworthiness Directive (AD) 2015-15-10,
which applied to all Airbus Model A318, A319, A320, and A321 series
airplanes. AD 2015-15-10 required repetitive inspections of the
trimmable horizontal stabilizer actuator (THSA) for damage, and
replacement if necessary; and replacement of the THSA after reaching a
certain life limit. This AD requires repetitive detailed inspections of
certain THSAs, and related investigative and corrective actions if
necessary. This AD was prompted by the establishment of an additional
life limit for the THSA, based on flight cycles. In addition, the THSA
manufacturer has issued service information which, when accomplished,
increases the life limit of the THSA. We are issuing this AD to address
the unsafe condition on these products.
DATES: This AD is effective November 1, 2017.
The Director of the Federal Register approved the incorporation by
reference of a certain publication listed in this AD as of November 1,
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 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 https://www.regulations.gov by searching for and locating Docket No. FAA-2017-
0498.
Examining the AD Docket
You may examine the AD docket on the Internet at https://
[[Page 44904]]
www.regulations.gov by searching for and locating Docket No. FAA-2017-
0498; 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 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 Section, Transport Standards Branch, 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 to supersede AD 2015-15-10, Amendment 39-18219 (80 FR 43928,
July 24, 2015) (``AD 2015-15-10''). AD 2015-15-10 applied to all Airbus
Model A318, A319, A320, and A321 series airplanes. The NPRM published
in the Federal Register on June 2, 2017 (82 FR 25542). The NPRM was
prompted by the establishment of an additional life limit for the THSA,
based on flight cycles. The NPRM proposed to require repetitive
detailed inspections of certain THSAs, and related investigative and
corrective actions if necessary. We are issuing this AD to detect and
correct wear of the THSA, which could reduce the remaining life of the
THSA, possibly resulting in premature failure and consequent reduced
controllability 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 2016-0184, dated September 13, 2016 (referred
to after this as the Mandatory Continuing Airworthiness Information, or
``the MCAI''), to correct an unsafe condition for all Airbus Model A318
and A319 series airplanes; Model A320-211, -212, -214, -231, -232, and
-233 airplanes; and Model A321-111, -112, -131, -211, -212, -213, -231,
and -232 airplanes. The MCAI states:
In the frame of the A320 Extended Service Goal (ESG) project and
the study on the Trimmable Horizontal Stabilizer Actuator (THSA), a
sampling programme of in-service units was performed and several
cases of wear at different THSA levels were reported.
This condition, if not detected and corrected, would reduce the
remaining life of the THSA, possibly resulting in premature failure
and consequent reduced control of the aeroplane.
Prompted by these findings, Airbus issued Service Bulletin (SB)
A320-27-1227 to provide THSA inspection instructions. Consequently,
EASA issued AD 2014-0011 (later revised) [which corresponds to AD
2015-15-10] to require repetitive inspections of the THSA [and
related investigative and corrective actions] and to introduce a
life limit for the THSA, based on flight hours (FH).
Since EASA AD 2014-0011R1 was issued, an additional life
limitation has been established, based on flight cycles (FC).
Furthermore, United Technologies Corporation Aerospace Systems
(UTAS), the THSA manufacturer, issued an SB which, after
accomplishment on THSA, increases the life limit of the THSA.
For the reasons described above, this [EASA] AD retains the
requirements of EASA AD 2014-0011R1, which is superseded, and
introduces an additional FC life limit for the affected THSA. This
[EASA] AD also provides a revised life limit for the THSA after UTAS
SB accomplishment on that THSA.
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-2017-
0498.
Comments
We gave the public the opportunity to participate in developing
this AD. We considered the comments received. Air Line Pilots
Association, International (ALPA) and United Airlines expressed their
support for the NPRM.
Changes Made to This AD
The NPRM specified that a THSA that had been repaired in-shop as
specified in UTAS Component Maintenance Manual 27-44-51 would be an
equivalent method of compliance for the initial inspection required by
paragraph (h) of this AD. We have revised paragraph (m) of this AD to
specify that a THSA that has been repaired in-shop using a method
approved by the Manager, International Section, Transport Standards
Branch, FAA; or the EASA; or Airbus's EASA Design Organization Approval
(DOA), is acceptable for compliance with the initial inspection
required by paragraph (h) of this AD. We have also added Note 1 to
paragraph (m) of this AD to reference UTAS Component Maintenance Manual
27-44-51 as an additional source of guidance for the in-shop repair of
the THSA.
Conclusion
We reviewed the relevant data, considered the comments 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
Airbus has issued Service Bulletin A320-27-1227, Revision 03, dated
April 29, 2016. This service information describes procedures for
repetitive special detailed inspections for wear of the THSA, and
related investigative and corrective actions.
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 1,182 airplanes of U.S. registry.
We estimate the following costs to comply with this AD:
Estimated Costs
----------------------------------------------------------------------------------------------------------------
Cost on U.S.
Action Labor cost Parts cost Cost per product operators
----------------------------------------------------------------------------------------------------------------
Inspections...................... 6 work-hours x $85 $0 $510 per inspection $602,820 per
per hour = $510 cycle. inspection cycle.
per inspection
cycle.
----------------------------------------------------------------------------------------------------------------
[[Page 44905]]
We have received no definitive data that would enable us to provide
cost estimates for the spectrometric analysis of the oil drained from
the THSA gearbox. We estimate the following costs to do any necessary
replacements or overhauls that would be required based on the results
of the inspection. We have no way of determining the number of aircraft
that might need these replacements or overhauls:
On-Condition Costs
----------------------------------------------------------------------------------------------------------------
Cost per
Action Labor cost Parts cost product
----------------------------------------------------------------------------------------------------------------
Replacement of THSA (retained from AD 2015-15- 11 work-hours x $85 per hour = $240,000 $240,935
10). $935.
Overhaul of THSA (new action)................. 66 work-hours x $85 per hour = 115,000 120,610
$5,610.
----------------------------------------------------------------------------------------------------------------
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 removing Airworthiness Directive (AD)
2015-15-10, Amendment 39-18219 (80 FR 43928, July 24, 2015), and adding
the following new AD:
2017-19-23 Airbus: Amendment 39-19053; Docket No. FAA-2017-0498;
Product Identifier 2016-NM-175-AD.
(a) Effective Date
This AD is effective November 1, 2017.
(b) Affected ADs
This AD replaces AD 2015-15-10, Amendment 39-18219 (80 FR 43928,
July 24, 2015) (``AD 2015-15-10'').
(c) Applicability
This AD applies to the airplanes identified in paragraphs (c)(1)
through (c)(4) of this AD, certificated in any category, all
manufacturer serial numbers.
(1) Airbus Model A318-111, -112, -121, and -122 airplanes.
(2) Airbus Model A319-111, -112, -113, -114, -115, -131, -132,
and -133 airplanes.
(3) Airbus Model A320-211, -212, -214, -231, -232, and -233
airplanes.
(4) Airbus Model A321-111, -112, -131, -211, -212, -213, -231,
and -232 airplanes.
(d) Subject
Air Transport Association (ATA) of America Code 27, Flight
controls.
(e) Reason
This AD was prompted by reports of wear at different levels in
the trimmable horizontal stabilizer actuator (THSA). We are issuing
this AD to detect and correct wear of the THSA, which could reduce
the remaining life of the THSA, possibly resulting in premature
failure and consequent reduced controllability of the airplane.
(f) Compliance
Comply with this AD within the compliance times specified,
unless already done.
(g) Serviceable THSA Definition
For the purposes of this AD, a serviceable THSA is a THSA that
does not exceed the life limits as identified in table 1 to
paragraphs (g) and (j) of this AD.
Table 1 to Paragraphs (g) and (j) of This AD--THSA Life Limits
------------------------------------------------------------------------
Configuration, based on service Compliance time (whichever
bulletin (SB) embodiment occurs first)
------------------------------------------------------------------------
THSA on which United Technologies Before exceeding 67,500 flight
Corporation Aerospace Systems (UTAS) hours (FH) since first
SB 47145-27-19 has not been embodied. installation on an airplane,
or before exceeding 48,000
flight cycles (FC) since first
installation on an airplane.
[[Page 44906]]
THSA on which UTAS SB 47145-27-19 has Before exceeding 52,500 FH
been embodied. after embodiment of UTAS SB
47145-27-19 on an airplane,
without exceeding 120,000 FH
since first installation on an
airplane; or before exceeding
27,000 FC after embodiment of
UTAS SB 47145-27-19 on an
airplane, without exceeding
75,000 FC since first
installation on an airplane.
------------------------------------------------------------------------
(h) Repetitive Inspection and Related Investigative Actions
For any airplane on which UTAS Service Bulletin 47145-27-19 has
not been embodied: Before the THSA exceeds 48,000 flight hours or
30,000 flight cycles, whichever occurs first since first
installation on an airplane, do a special detailed inspection of the
THSA and do all applicable related investigative actions, in
accordance with the Accomplishment Instructions of Airbus Service
Bulletin A320-27-1227, Revision 03, dated April 29, 2016. Do all
applicable related investigative actions at the applicable times
specified in paragraph 1.E., ``Compliance'' of Airbus Service
Bulletin A320-27-1227, Revision 03, dated April 29, 2016. Repeat the
inspections thereafter at intervals not to exceed 24 months.
(i) Corrective Action
If, during any inspection required by paragraph (h) of this AD,
any finding as described in the Accomplishment Instructions of
Airbus Service Bulletin A320-27-1227, Revision 03, dated April 29,
2016, is identified: At the applicable time (depending on the
applicable finding) specified in paragraph 1.E., ``Compliance,'' of
Airbus Service Bulletin A320-27-1227, Revision 03, dated April 29,
2016, replace the THSA with a serviceable THSA, as specified in
paragraph (g) of this AD, in accordance with the Accomplishment
Instructions of Airbus Service Bulletin A320-27-1227, Revision 03,
dated April 29, 2016.
(j) THSA Replacement
Within the applicable compliance time specified in table 1 to
paragraphs (g) and (j) of this AD, replace each THSA with a
serviceable THSA, as specified in paragraph (g) of this AD, in
accordance with the Accomplishment Instructions of Airbus Service
Bulletin A320-27-1227, Revision 03, dated April 29, 2016.
(k) Replacement of a THSA: Not Terminating Action
Replacement of a THSA on an airplane, as required by paragraph
(i) or (j) of this AD, does not constitute terminating action for
the repetitive inspections required by paragraph (h) of this AD for
that airplane, unless the THSA has been overhauled as specified in
UTAS Service Bulletin 47145-27-19 (i.e., post-service bulletin).
(l) Optional Terminating Action: Overhaul of THSA
Accomplishment of a modification of an airplane by installing a
THSA that has been overhauled as specified in UTAS Service Bulletin
47145-27-19 constitutes terminating action for the repetitive
inspections required by paragraph (h) of this AD, provided that,
following modification, no THSA is reinstalled on the airplane
unless it has been overhauled as specified in UTAS Service Bulletin
47145-27-19.
(m) Replacement THSA Equivalency
As of the effective date of this AD: A THSA that has been
repaired in-shop is acceptable for compliance with the initial
inspection required by paragraph (h) of this AD, provided that
repair was done 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).
Note 1 to paragraph (m) of this AD: Guidance for THSA repair in-
shop can be found in UTAS Component Maintenance Manual 27-44-51.
(n) Parts Installation Limitation
As of the effective date of this AD: Do not install on any
airplane a THSA unless it is a serviceable THSA as specified in
paragraph (g) of this AD.
(o) Credit for Previous Actions
This paragraph provides credit for the actions required by
paragraphs (h) and (i) of this AD, if those actions were performed
before the effective date of this AD using any of the service
information specified in paragraphs (o)(1), (o)(2), or (o)(3) of
this AD.
(1) Airbus Service Bulletin A320-27-1227, dated July 1, 2013,
which is not incorporated by reference in this AD.
(2) Airbus Service Bulletin A320-27-1227, Revision 01, dated
October 7, 2013, which was incorporated by reference in AD 2015-15-
10.
(3) Airbus Service Bulletin A320-27-1227, Revision 02, dated
February 2, 2015, which is not incorporated by reference in this AD.
(p) 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 International Section, send it to the attention of
the person identified in paragraph (q)(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 EASA; or Airbus's
EASA DOA. If approved by the DOA, the approval must include the DOA-
authorized signature.
(3) Required for Compliance (RC): If any service information
contains procedures or tests that are identified as RC, those
procedures and tests must be done to comply with this AD; any
procedures or tests that are not identified as RC are recommended.
Those procedures and tests that are not identified as RC may be
deviated from using accepted methods in accordance with the
operator's maintenance or inspection program without obtaining
approval of an AMOC, provided the procedures and tests identified as
RC can be done and the airplane can be put back in an airworthy
condition. Any substitutions or changes to procedures or tests
identified as RC require approval of an AMOC.
(q) Related Information
(1) Refer to Mandatory Continuing Airworthiness Information
(MCAI) EASA Airworthiness Directive 2016-0184, dated September 13,
3016, 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-2017-0498.
(2) For more information about this AD, contact Sanjay Ralhan,
Aerospace Engineer, International Section, Transport Standards
Branch, FAA, 1601 Lind Avenue SW., Renton, WA 98057-3356; telephone
425-227-1405; fax 425-227-1149.
(3) Service information identified in this AD that is not
incorporated by reference is available at the addresses specified in
paragraphs (r)(3) and (r)(4) of this AD.
(r) 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 A320-27-1227, Revision 03, dated
April 29, 2016.
(ii) Reserved.
(3) For Airbus service information identified in this AD,
contact Airbus, Airworthiness Office--EIAS, 1 Rond Point Maurice
Bellonte, 31707 Blagnac Cedex,
[[Page 44907]]
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
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: https://www.archives.gov/federal-register/cfr/ibr-locations.html.
Issued in Renton, Washington, on September 14, 2017.
Jeffrey E. Duven,
Director, System Oversight Division, Aircraft Certification Service.
[FR Doc. 2017-20567 Filed 9-26-17; 8:45 am]
BILLING CODE 4910-13-P