Airworthiness Directives; Airbus Airplanes, 25940-25943 [2017-11290]
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Federal Register / Vol. 82, No. 107 / Tuesday, June 6, 2017 / Rules and Regulations
(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:
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-116AMOC-REQUESTS@faa.gov. Before using
any approved AMOC, notify your appropriate
principal inspector, or lacking a principal
inspector, the manager of the local flight
standards district office/certificate holding
district office.
(2) Contacting the Manufacturer: For any
requirement in this AD to obtain corrective
actions from a manufacturer, the action must
be accomplished using a method approved
by the Manager, International Branch, ANM–
116, Transport Airplane Directorate, FAA; or
EASA; or Airbus’s EASA DOA. If approved
by the DOA, the approval must include the
DOA-authorized signature.
(3) Required for Compliance (RC): Except
as required by paragraph (i) of this AD: If any
service information contains procedures or
tests that are identified as RC, those
procedures and tests must be done to comply
with this AD; any procedures or tests that are
not identified as RC are recommended. Those
procedures and tests that are not identified
as RC may be deviated from using accepted
methods in accordance with the operator’s
maintenance or inspection program without
obtaining approval of an AMOC, provided
the procedures and tests identified as RC can
be done and the airplane can be put back in
an airworthy condition. Any substitutions or
changes to procedures or tests identified as
RC require approval of an AMOC.
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(m) Related Information
(1) Refer to Mandatory Continuing
Airworthiness Information (MCAI) EASA
Airworthiness Directive 2016–0076, dated
April 18, 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–
2016–8182.
(2) Service information identified in this
AD that is not incorporated by reference is
available at the addresses specified in
paragraphs (n)(3), (n)(4), and (n)(5) of this
AD.
(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.
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(i) Airbus Service Bulletin A320–70–1003,
Revision 01, dated December 28, 2015.
(ii) Goodrich Aerostructures Service
Bulletin RA32078–137, Rev. 3, dated March
14, 2016.
(3) For Airbus service information
identified in this AD, contact Airbus 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) For Goodrich Aerostructures service
information identified in this AD, contact
Goodrich Aerostructures, 850 Lagoon Drive,
Chula Vista, CA 91910–2098; telephone 619–
691–2719; email jan.lewis@goodrich.com;
Internet https://techpubs.goodrich.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 May 17,
2017.
Michael Kaszycki,
Acting Manager, Transport Airplane
Directorate, Aircraft Certification Service.
[FR Doc. 2017–11129 Filed 6–5–17; 8:45 am]
BILLING CODE 4910–13–P
DEPARTMENT OF TRANSPORTATION
Federal Aviation Administration
14 CFR Part 39
[Docket No. FAA–2016–7262; Directorate
Identifier 2015–NM–079–AD; Amendment
39–18912; AD 2017–11–13]
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) 98–13–14,
for certain Airbus Model A320–211,
–212, and –231 airplanes. AD 98–13–14
required repetitive inspections of
certain fastener holes of the aft fuselage,
and corrective action if necessary. This
new AD continues to require the actions
in AD 98–13–14, with revised
inspection compliance times. This AD
was prompted by identification of
cracks in the fastener holes of the former
SUMMARY:
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junction of the aft fuselage, which
occurred during a fatigue test; and a
determination that certain compliance
times specified in AD 98–13–14 must be
reduced. We are issuing this AD to
address the unsafe condition on these
products.
DATES: This AD is effective July 11,
2017.
The Director of the Federal Register
approved the incorporation by reference
of certain publications listed in this AD
as of July 11, 2017.
The Director of the Federal Register
approved the incorporation by reference
of certain other publications listed in
this AD as of July 30, 1998 (63 FR
34556, June 25, 1998).
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–
7262.
Examining the AD Docket
You may examine the AD docket on
the Internet at https://
www.regulations.gov by searching for
and locating Docket No. FAA–2016–
7262; 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 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
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part 39 to supersede AD 98–13–14,
Amendment 39–10602 (63 FR 34556,
June 25, 1998) (‘‘AD 98–13–14’’). AD
98–13–14 applied to certain Airbus
Model A320 series airplanes (Model
A320–211, –212, and –231 airplanes).
Since we issued AD 98–13–14, an
evaluation by the DAH indicates that
the former junction of the aft fuselage is
subject to fatigue damage.
The NPRM published in the Federal
Register on June 21, 2016 (81 FR 40210).
The NPRM was prompted by the
identification of four cracks in the
fastener holes in the area of the former
junction at frame (FR) 68 between
stringers 4 and 5 (left- and right-hand
sides), which occurred during a fatigue
test, and a determination that certain
compliance times specified in AD 98–
13–14 must be reduced. The NPRM
proposed to continue to require the
actions in AD 98–13–14, with revised
inspection compliance times. We are
issuing this AD to prevent fatigue cracks
from occurring or propagating in certain
structures, which could adversely affect
the 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 AD 2015–0084,
dated May 13, 2015; corrected May 18,
2015 (referred to after this as the
Mandatory Continuing Airworthiness
Information, or ‘‘the MCAI’’); to correct
an unsafe condition for certain Airbus
Model A320–211, –212, and –231
airplanes. The MCAI states:
During a fatigue test campaign, four cracks
were identified in the fastener holes of the
former junction at frame (FR) 68 between
stringers 4 and 5.
This condition, if not detected and
corrected, could lead to crack propagation,
possibly resulting in reduced structural
integrity of the fuselage.
To address this unsafe condition, DGAC
´ ´
[Direction generale de l’aviation civile]
France issued * * * [an AD, which
corresponds to FAA AD 98–13–14] to require
repetitive inspections and, depending on
findings, the accomplishment of an
applicable repair solution.
That [DGAC] AD also provided
modification of FR 68 [cold working of
fastener and tooling holes] in accordance
with Airbus Service Bulletin (SB) A320–53–
1090 as optional terminating action.
Following new analyses, the thresholds
and inspection intervals have been reviewed
and adjusted.
For the reason described above, this
[EASA] AD retains the requirements of DGAC
France AD 96–298–093(B)R2 [https://
ad.easa.europa.eu/ad/F-1996-298R2], which
is superseded, and requires those actions
within the new thresholds and intervals.
This [EASA] AD was republished to correct
a typographical error in the Reason.
Repairs include doing applicable
related investigative actions (i.e.,
rotating probe inspection of the hole to
make sure the crack is removed and
eddy current inspection of the cold
expanded holes). 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–2016–7262.
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 to the comment.
Request To Update Service Information
Airbus requested that Airbus Service
Bulletin A320–53–1089, Revision 04,
dated June 1, 2016, be referred to in the
final rule. This service information
replaces a certain nondestructive test
manual (NTM) task, removes an eddy
current inspection for a certain service
bulletin task, and updates the service
bulletin airplane effectivity.
We agree with the request and have
revised paragraphs (h) and (i) of this AD
to refer to Airbus Service Bulletin
A320–53–1089, Revision 04, dated June
1, 2016. We have also added paragraph
(k)(1)(iii) to this AD to provide credit for
Airbus Service Bulletin A320–53–1089,
Revision 03, dated March 18, 2015.
Additional Changes to the NPRM
We have revised paragraphs (h)(2) and
(h)(3) of this AD to remove references to
the revision level and date of the service
information that must be used for
determining the compliance time,
because operators might have used other
25941
versions for their most recent
inspection. The number of affected U.S.
registered airplanes has also been
changed from 10 to 4. The total cost to
operators has been changed accordingly.
Conclusion
We reviewed the available data,
including 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 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 Airbus
service information:
• Service Bulletin A320–53–1089,
Revision 04, dated June 1, 2016. This
service information describes
procedures for a special detailed rototest
inspection for fatigue cracking of the
frame junction holes and the adjacent
tooling hole, as applicable, of the rightand left-hand former junctions at FR 68,
and repair, including doing applicable
related investigative actions.
• Service Bulletin A320–53–1090,
Revision 02, dated December 22, 1998.
This service information describes
procedures for modifying the airplane
(cold working of fastener and tooling
holes).
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 4
airplanes of U.S. registry.
We estimate the following costs to
comply with this AD:
ESTIMATED COSTS
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Action
Labor cost
Initial and repetitive inspections [retained from AD 98–
13–14].
8 work-hours × $85 per hour =
$680 per inspection cycle.
We estimate the following costs to do
any necessary repairs that will be
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Parts cost
$0
Cost per product
$680 per inspection cycle .......
required based on the results of the
inspection. We have no way of
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Cost on U.S. operators
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$2,720 per inspection cycle.
determining the number of aircraft that
might need these repairs:
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Federal Register / Vol. 82, No. 107 / Tuesday, June 6, 2017 / Rules and Regulations
ON-CONDITION COSTS
Action
Labor cost
Repair .............................................................................
52 work-hours × $85 per hour = $4,420 ........................
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.
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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:
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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
removing Airworthiness Directive (AD)
98–13–14, Amendment 39–10602 (63
FR 34556, June 25, 1998), and adding
the following new AD:
■
2017–11–13 Airbus: Amendment 39–18912;
Docket No. FAA–2016–7262; Directorate
Identifier 2015–NM–079–AD.
(a) Effective Date
This AD is effective July 11, 2017.
(b) Affected ADs
This AD replaces AD 98–13–14,
Amendment 39–10602 (63 FR 34556, June
25, 1998) (‘‘AD 98–13–14’’).
(c) Applicability
This AD applies to Airbus Model A320–
211, –212, and –231 airplanes, certificated in
any category, manufacturer serial numbers
(S/Ns) 0001 through 0123 inclusive, except
those that have embodied Airbus
Modifications 21780 and 21781 in
production.
(d) Subject
Air Transport Association (ATA) of
America Code 53, Fuselage.
(e) Reason
This AD was prompted by identification of
four cracks in the fastener holes of the former
junction at frame (FR) 68 between stringers
4 and 5, which occurred during a fatigue test,
and a determination that certain compliance
times specified in AD 98–13–14 must be
reduced. We are issuing this AD to prevent
fatigue cracks from occurring or propagating
in certain structures, which could adversely
affect the structural integrity of the airplane.
(f) Compliance
Comply with this AD within the
compliance times specified, unless already
done.
(g) Retained Repetitive Inspections and
Repair, With Additional Methods of
Approving Repairs
This paragraph restates the requirements of
paragraph (a) of AD 98–13–14, with
additional methods of approving repairs. For
Model A320 series airplanes, as listed in
Airbus Service Bulletins A320–53–1089 and
A320–53–1090, both dated November 22,
1995: Prior to the accumulation of 20,000
total flight cycles, or within 500 flight cycles
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Parts cost
$3,800
Cost per
product
$8,220
after July 30, 1998 (the effective date of AD
98–13–14), whichever occurs later, perform a
rotating probe inspection for fatigue cracking
of the fastener holes and/or the adjacent
tooling hole, as applicable, of the right- and
left-hand former junctions at FR 68, in
accordance with the Accomplishment
Instructions of Airbus Service Bulletin A320–
53–1089, dated November 22, 1995.
Accomplishing an inspection required by
paragraph (h) of this AD terminates the
actions required by this paragraph.
(1) If no crack is detected, accomplish
either paragraph (g)(1)(i) or (g)(1)(ii) of this
AD.
(i) Repeat the inspection thereafter at
intervals not to exceed 20,000 flight cycles;
or
(ii) Prior to further flight following the
accomplishment of the inspection required
by paragraph (g) of this AD, cold work the
fastener holes and/or the adjacent tooling
hole of the right- and left-hand former
junctions at FR 68, as applicable, in
accordance with the Accomplishment
Instructions of Airbus Service Bulletin A320–
53–1090, dated November 22, 1995.
Accomplishment of this cold working
constitutes terminating action for the
repetitive inspections required by paragraph
(g)(1)(i) of this AD.
(2) If any crack is detected, prior to further
flight, repair in accordance with 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).
(h) New Repetitive Inspection Requirement
Within the compliance time specified in
paragraph (h)(1), (h)(2), or (h)(3) of this AD,
whichever occurs latest: Accomplish a
special detailed rototest inspection for fatigue
cracking of the frame junction holes and the
adjacent tooling hole, as applicable, of the
right- and left-hand former junctions at FR
68, in accordance with the Accomplishment
Instructions of Airbus Service Bulletin A320–
53–1089, Revision 04, dated June 1, 2016.
Repeat the inspection thereafter at intervals
not to exceed 3,800 flight cycles or 7,600
flight hours, whichever occurs first, until a
repair required by paragraph (i) of this AD is
done or a modification specified in paragraph
(j) of this AD is done. Accomplishing an
inspection required by this paragraph
terminates the inspections required by
paragraph (g) of this AD.
(1) Within 28,700 flight cycles or 57,400
flight hours since airplane first flight,
whichever occurs first.
(2) Within 3,800 flight cycles or 7,600
flight hours, whichever occurs first, since the
most recent inspection done as specified in
the Accomplishment Instructions of Airbus
Service Bulletin A320–53–1089.
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(3) Within 3,800 flight cycles or 7,600
flight hours after the effective date of this AD,
whichever occurs first, without exceeding
20,000 flight cycles since the most recent
inspection done as specified in the
Accomplishment Instructions of Airbus
Service Bulletin A320–53–1089.
(i) New Repair Requirement
If any crack is detected during any
inspection required by paragraph (h) of this
AD: Before further flight, repair, including
doing all applicable related investigative
actions, in accordance with the
Accomplishment Instructions of Airbus
Service Bulletin A320–53–1089, Revision 04,
dated June 1, 2016. Do all applicable related
investigative actions before further flight.
Repair of an airplane in accordance with the
Accomplishment Instructions of Airbus
Service Bulletin A320–53–1089, Revision 04,
dated June 1, 2016, constitutes terminating
action for the repetitive inspections required
by paragraph (h) of this AD.
(j) New Optional Modification
Modification of an airplane, in accordance
with the Accomplishment Instructions of
Airbus Service Bulletin A320–53–1090,
Revision 02, dated December 22, 1998,
constitutes terminating action for the
repetitive inspections required by paragraphs
(g) and (h) of this AD, provided the
modification is accomplished before further
flight after accomplishing an inspection
required by paragraph (h) of this AD and no
cracks were detected.
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(k) Credit for Previous Actions
(1) 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 the
service information identified in paragraphs
(k)(1)(i), (k)(1)(ii), or (k)(1)(iii) of this AD.
(i) Airbus Service Bulletin A320–53–1089,
Revision 01, dated June 4, 1998.
(ii) Airbus Service Bulletin A320–53–1089,
Revision 02, dated February 3, 2003.
(iii) Airbus Service Bulletin A320–53–
1089, Revision 03, dated March 18, 2015.
(2) This paragraph provides credit for the
actions required by paragraph (j) of this AD,
if those actions were performed before the
effective date of this AD using the service
information identified in paragraphs (k)(2)(i)
or (k)(2)(ii) of this AD.
(i) Airbus Service Bulletin A320–53–1090,
dated November 22, 1995, which was
incorporated by reference in AD 98–13–14,
Amendment 39–10602 (63 FR 34556, June
25, 1998).
(ii) Airbus Service Bulletin A320–53–1090,
Revision 1, dated June 10, 1998, which is not
incorporated by reference in 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
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25943
Flight Standards District Office, as
appropriate. If sending information directly
to the manager of the International Branch,
send it to the attention of the person
identified in paragraph (m)(2) of this AD.
Information may be emailed to: 9-ANM-116AMOC-REQUESTS@faa.gov. Before using
any approved AMOC, notify your appropriate
principal inspector, or lacking a principal
inspector, the manager of the local flight
standards district office/certificate holding
district office.
(2) Contacting the Manufacturer: For any
requirement in this AD to obtain corrective
actions from a manufacturer, the action must
be accomplished using a method approved
by the Manager, International Branch, ANM–
116, Transport Airplane Directorate, FAA; or
the EASA; or Airbus’s EASA DOA. If
approved by the DOA, the approval must
include the DOA-authorized signature.
(3) Required for Compliance (RC): If any
service information contains procedures or
tests that are identified as RC, those
procedures and tests must be done to comply
with this AD; any procedures or tests that are
not identified as RC are recommended. Those
procedures and tests that are not identified
as RC may be deviated from using accepted
methods in accordance with the operator’s
maintenance or inspection program without
obtaining approval of an AMOC, provided
the procedures and tests identified as RC can
be done and the airplane can be put back in
an airworthy condition. Any substitutions or
changes to procedures or tests identified as
RC require approval of an AMOC.
identified as Revision 02, dated December 22,
1998.
(4) The following service information was
approved for IBR on July 30, 1998, AD 98–
13–14, Amendment 39–10602 (63 FR 34556,
June 25, 1998).
(i) Airbus Service Bulletin A320–53–1089,
dated November 22, 1995.
(ii) Airbus Service Bulletin A320–53–1090,
dated November 22, 1995.
(5) For service information identified in
this AD, contact Airbus SAS, 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 Airplane Directorate,
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.
(m) Related Information
(1) Refer to Mandatory Continuing
Airworthiness Information (MCAI) EASA AD
2015–0084, dated May 13, 2015; corrected
May 18, 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–
2016–7262.
(2) For more information about this AD,
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.
(3) Service information identified in this
AD that is not incorporated by reference is
available at the addresses specified in
paragraphs (n)(5) and (n)(6) of this AD.
BILLING CODE 4910–13–P
(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 the AD specifies otherwise.
(3) The following service information was
approved for IBR on July 11, 2017.
(i) Airbus Service Bulletin A320–53–1089,
Revision 04, dated June 1, 2016.
(ii) Airbus Service Bulletin A320–53–1090,
Revision 02, dated December 22, 1998. Pages
1, 2, 7, 8, 9, 10, and 11 of this document are
identified as Revision 1, dated June 10, 1998;
and pages 3, 4, 5, and 6 of this document are
PO 00000
Frm 00013
Fmt 4700
Sfmt 4700
Issued in Renton, Washington, on May 23,
2017.
Michael Kaszycki,
Acting Manager, Transport Airplane
Directorate, Aircraft Certification Service.
[FR Doc. 2017–11290 Filed 6–5–17; 8:45 am]
DEPARTMENT OF TRANSPORTATION
Federal Aviation Administration
14 CFR Part 39
[Docket No. FAA–2017–0124; Directorate
Identifier 2016–NM–166–AD; Amendment
39–18911; AD 2017–11–12]
RIN 2120–AA64
Airworthiness Directives; Bombardier,
Inc., Airplanes
Federal Aviation
Administration (FAA), Department of
Transportation (DOT).
ACTION: Final rule.
AGENCY:
We are adopting a new
airworthiness directive (AD) for certain
Bombardier, Inc., Model BD–100–1A10
airplanes. This AD was prompted by
several reports of nose wheel steering
failures in service. This AD requires a
part verification and replacement of
certain steering manifolds. We are
issuing this AD to address the unsafe
condition on these products.
DATES: This AD is effective July 11,
2017.
The Director of the Federal Register
approved the incorporation by reference
SUMMARY:
E:\FR\FM\06JNR1.SGM
06JNR1
Agencies
[Federal Register Volume 82, Number 107 (Tuesday, June 6, 2017)]
[Rules and Regulations]
[Pages 25940-25943]
From the Federal Register Online via the Government Publishing Office [www.gpo.gov]
[FR Doc No: 2017-11290]
-----------------------------------------------------------------------
DEPARTMENT OF TRANSPORTATION
Federal Aviation Administration
14 CFR Part 39
[Docket No. FAA-2016-7262; Directorate Identifier 2015-NM-079-AD;
Amendment 39-18912; AD 2017-11-13]
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) 98-13-14, for
certain Airbus Model A320-211, -212, and -231 airplanes. AD 98-13-14
required repetitive inspections of certain fastener holes of the aft
fuselage, and corrective action if necessary. This new AD continues to
require the actions in AD 98-13-14, with revised inspection compliance
times. This AD was prompted by identification of cracks in the fastener
holes of the former junction of the aft fuselage, which occurred during
a fatigue test; and a determination that certain compliance times
specified in AD 98-13-14 must be reduced. We are issuing this AD to
address the unsafe condition on these products.
DATES: This AD is effective July 11, 2017.
The Director of the Federal Register approved the incorporation by
reference of certain publications listed in this AD as of July 11,
2017.
The Director of the Federal Register approved the incorporation by
reference of certain other publications listed in this AD as of July
30, 1998 (63 FR 34556, June 25, 1998).
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-
7262.
Examining the AD Docket
You may examine the AD docket on the Internet at https://www.regulations.gov by searching for and locating Docket No. FAA-2016-
7262; 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 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
[[Page 25941]]
part 39 to supersede AD 98-13-14, Amendment 39-10602 (63 FR 34556, June
25, 1998) (``AD 98-13-14''). AD 98-13-14 applied to certain Airbus
Model A320 series airplanes (Model A320-211, -212, and -231 airplanes).
Since we issued AD 98-13-14, an evaluation by the DAH indicates that
the former junction of the aft fuselage is subject to fatigue damage.
The NPRM published in the Federal Register on June 21, 2016 (81 FR
40210). The NPRM was prompted by the identification of four cracks in
the fastener holes in the area of the former junction at frame (FR) 68
between stringers 4 and 5 (left- and right-hand sides), which occurred
during a fatigue test, and a determination that certain compliance
times specified in AD 98-13-14 must be reduced. The NPRM proposed to
continue to require the actions in AD 98-13-14, with revised inspection
compliance times. We are issuing this AD to prevent fatigue cracks from
occurring or propagating in certain structures, which could adversely
affect the 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 AD
2015-0084, dated May 13, 2015; corrected May 18, 2015 (referred to
after this as the Mandatory Continuing Airworthiness Information, or
``the MCAI''); to correct an unsafe condition for certain Airbus Model
A320-211, -212, and -231 airplanes. The MCAI states:
During a fatigue test campaign, four cracks were identified in
the fastener holes of the former junction at frame (FR) 68 between
stringers 4 and 5.
This condition, if not detected and corrected, could lead to
crack propagation, possibly resulting in reduced structural
integrity of the fuselage.
To address this unsafe condition, DGAC [Direction
g[eacute]n[eacute]rale de l'aviation civile] France issued * * * [an
AD, which corresponds to FAA AD 98-13-14] to require repetitive
inspections and, depending on findings, the accomplishment of an
applicable repair solution.
That [DGAC] AD also provided modification of FR 68 [cold working
of fastener and tooling holes] in accordance with Airbus Service
Bulletin (SB) A320-53-1090 as optional terminating action.
Following new analyses, the thresholds and inspection intervals
have been reviewed and adjusted.
For the reason described above, this [EASA] AD retains the
requirements of DGAC France AD 96-298-093(B)R2 [https://ad.easa.europa.eu/ad/F-1996-298R2], which is superseded, and
requires those actions within the new thresholds and intervals.
This [EASA] AD was republished to correct a typographical error
in the Reason.
Repairs include doing applicable related investigative actions
(i.e., rotating probe inspection of the hole to make sure the crack is
removed and eddy current inspection of the cold expanded holes). 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-
7262.
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 to the comment.
Request To Update Service Information
Airbus requested that Airbus Service Bulletin A320-53-1089,
Revision 04, dated June 1, 2016, be referred to in the final rule. This
service information replaces a certain nondestructive test manual (NTM)
task, removes an eddy current inspection for a certain service bulletin
task, and updates the service bulletin airplane effectivity.
We agree with the request and have revised paragraphs (h) and (i)
of this AD to refer to Airbus Service Bulletin A320-53-1089, Revision
04, dated June 1, 2016. We have also added paragraph (k)(1)(iii) to
this AD to provide credit for Airbus Service Bulletin A320-53-1089,
Revision 03, dated March 18, 2015.
Additional Changes to the NPRM
We have revised paragraphs (h)(2) and (h)(3) of this AD to remove
references to the revision level and date of the service information
that must be used for determining the compliance time, because
operators might have used other versions for their most recent
inspection. The number of affected U.S. registered airplanes has also
been changed from 10 to 4. The total cost to operators has been changed
accordingly.
Conclusion
We reviewed the available data, including 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 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 Airbus service information:
Service Bulletin A320-53-1089, Revision 04, dated June 1,
2016. This service information describes procedures for a special
detailed rototest inspection for fatigue cracking of the frame junction
holes and the adjacent tooling hole, as applicable, of the right- and
left-hand former junctions at FR 68, and repair, including doing
applicable related investigative actions.
Service Bulletin A320-53-1090, Revision 02, dated December
22, 1998. This service information describes procedures for modifying
the airplane (cold working of fastener and tooling holes).
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 4 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
----------------------------------------------------------------------------------------------------------------
Initial and repetitive 8 work-hours x $85 $0 $680 per inspection $2,720 per
inspections [retained from AD 98- per hour = $680 per cycle. inspection cycle.
13-14]. inspection cycle.
----------------------------------------------------------------------------------------------------------------
We estimate the following costs to do any necessary repairs that
will be required based on the results of the inspection. We have no way
of determining the number of aircraft that might need these repairs:
[[Page 25942]]
On-Condition Costs
----------------------------------------------------------------------------------------------------------------
Cost per
Action Labor cost Parts cost product
--------------------------------------------------------------------------------------------
Repair............................... 52 work-hours x $85 per $3,800 $8,220
hour = $4,420.
----------------------------------------------------------------------------------------------------------------
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 removing Airworthiness Directive (AD)
98-13-14, Amendment 39-10602 (63 FR 34556, June 25, 1998), and adding
the following new AD:
2017-11-13 Airbus: Amendment 39-18912; Docket No. FAA-2016-7262;
Directorate Identifier 2015-NM-079-AD.
(a) Effective Date
This AD is effective July 11, 2017.
(b) Affected ADs
This AD replaces AD 98-13-14, Amendment 39-10602 (63 FR 34556,
June 25, 1998) (``AD 98-13-14'').
(c) Applicability
This AD applies to Airbus Model A320-211, -212, and -231
airplanes, certificated in any category, manufacturer serial numbers
(S/Ns) 0001 through 0123 inclusive, except those that have embodied
Airbus Modifications 21780 and 21781 in production.
(d) Subject
Air Transport Association (ATA) of America Code 53, Fuselage.
(e) Reason
This AD was prompted by identification of four cracks in the
fastener holes of the former junction at frame (FR) 68 between
stringers 4 and 5, which occurred during a fatigue test, and a
determination that certain compliance times specified in AD 98-13-14
must be reduced. We are issuing this AD to prevent fatigue cracks
from occurring or propagating in certain structures, which could
adversely affect the structural integrity of the airplane.
(f) Compliance
Comply with this AD within the compliance times specified,
unless already done.
(g) Retained Repetitive Inspections and Repair, With Additional Methods
of Approving Repairs
This paragraph restates the requirements of paragraph (a) of AD
98-13-14, with additional methods of approving repairs. For Model
A320 series airplanes, as listed in Airbus Service Bulletins A320-
53-1089 and A320-53-1090, both dated November 22, 1995: Prior to the
accumulation of 20,000 total flight cycles, or within 500 flight
cycles after July 30, 1998 (the effective date of AD 98-13-14),
whichever occurs later, perform a rotating probe inspection for
fatigue cracking of the fastener holes and/or the adjacent tooling
hole, as applicable, of the right- and left-hand former junctions at
FR 68, in accordance with the Accomplishment Instructions of Airbus
Service Bulletin A320-53-1089, dated November 22, 1995.
Accomplishing an inspection required by paragraph (h) of this AD
terminates the actions required by this paragraph.
(1) If no crack is detected, accomplish either paragraph
(g)(1)(i) or (g)(1)(ii) of this AD.
(i) Repeat the inspection thereafter at intervals not to exceed
20,000 flight cycles; or
(ii) Prior to further flight following the accomplishment of the
inspection required by paragraph (g) of this AD, cold work the
fastener holes and/or the adjacent tooling hole of the right- and
left-hand former junctions at FR 68, as applicable, in accordance
with the Accomplishment Instructions of Airbus Service Bulletin
A320-53-1090, dated November 22, 1995. Accomplishment of this cold
working constitutes terminating action for the repetitive
inspections required by paragraph (g)(1)(i) of this AD.
(2) If any crack is detected, prior to further flight, repair in
accordance with 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).
(h) New Repetitive Inspection Requirement
Within the compliance time specified in paragraph (h)(1),
(h)(2), or (h)(3) of this AD, whichever occurs latest: Accomplish a
special detailed rototest inspection for fatigue cracking of the
frame junction holes and the adjacent tooling hole, as applicable,
of the right- and left-hand former junctions at FR 68, in accordance
with the Accomplishment Instructions of Airbus Service Bulletin
A320-53-1089, Revision 04, dated June 1, 2016. Repeat the inspection
thereafter at intervals not to exceed 3,800 flight cycles or 7,600
flight hours, whichever occurs first, until a repair required by
paragraph (i) of this AD is done or a modification specified in
paragraph (j) of this AD is done. Accomplishing an inspection
required by this paragraph terminates the inspections required by
paragraph (g) of this AD.
(1) Within 28,700 flight cycles or 57,400 flight hours since
airplane first flight, whichever occurs first.
(2) Within 3,800 flight cycles or 7,600 flight hours, whichever
occurs first, since the most recent inspection done as specified in
the Accomplishment Instructions of Airbus Service Bulletin A320-53-
1089.
[[Page 25943]]
(3) Within 3,800 flight cycles or 7,600 flight hours after the
effective date of this AD, whichever occurs first, without exceeding
20,000 flight cycles since the most recent inspection done as
specified in the Accomplishment Instructions of Airbus Service
Bulletin A320-53-1089.
(i) New Repair Requirement
If any crack is detected during any inspection required by
paragraph (h) of this AD: Before further flight, repair, including
doing all applicable related investigative actions, in accordance
with the Accomplishment Instructions of Airbus Service Bulletin
A320-53-1089, Revision 04, dated June 1, 2016. Do all applicable
related investigative actions before further flight. Repair of an
airplane in accordance with the Accomplishment Instructions of
Airbus Service Bulletin A320-53-1089, Revision 04, dated June 1,
2016, constitutes terminating action for the repetitive inspections
required by paragraph (h) of this AD.
(j) New Optional Modification
Modification of an airplane, in accordance with the
Accomplishment Instructions of Airbus Service Bulletin A320-53-1090,
Revision 02, dated December 22, 1998, constitutes terminating action
for the repetitive inspections required by paragraphs (g) and (h) of
this AD, provided the modification is accomplished before further
flight after accomplishing an inspection required by paragraph (h)
of this AD and no cracks were detected.
(k) Credit for Previous Actions
(1) 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 the service information
identified in paragraphs (k)(1)(i), (k)(1)(ii), or (k)(1)(iii) of
this AD.
(i) Airbus Service Bulletin A320-53-1089, Revision 01, dated
June 4, 1998.
(ii) Airbus Service Bulletin A320-53-1089, Revision 02, dated
February 3, 2003.
(iii) Airbus Service Bulletin A320-53-1089, Revision 03, dated
March 18, 2015.
(2) This paragraph provides credit for the actions required by
paragraph (j) of this AD, if those actions were performed before the
effective date of this AD using the service information identified
in paragraphs (k)(2)(i) or (k)(2)(ii) of this AD.
(i) Airbus Service Bulletin A320-53-1090, dated November 22,
1995, which was incorporated by reference in AD 98-13-14, Amendment
39-10602 (63 FR 34556, June 25, 1998).
(ii) Airbus Service Bulletin A320-53-1090, Revision 1, dated
June 10, 1998, which is not incorporated by reference in 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 manager of the International Branch, send it to the
attention of the person identified in paragraph (m)(2) of this AD.
Information may be emailed to: 9-ANM-116-AMOC-REQUESTS@faa.gov.
Before using any approved AMOC, notify your appropriate principal
inspector, or lacking a principal inspector, the manager of the
local flight standards district office/certificate holding district
office.
(2) Contacting the Manufacturer: For any requirement in this AD
to obtain corrective actions from a manufacturer, the action must be
accomplished using a method approved by the Manager, International
Branch, ANM-116, Transport Airplane Directorate, FAA; or the EASA;
or Airbus's EASA DOA. If approved by the DOA, the approval must
include the DOA-authorized signature.
(3) Required for Compliance (RC): If any service information
contains procedures or tests that are identified as RC, those
procedures and tests must be done to comply with this AD; any
procedures or tests that are not identified as RC are recommended.
Those procedures and tests that are not identified as RC may be
deviated from using accepted methods in accordance with the
operator's maintenance or inspection program without obtaining
approval of an AMOC, provided the procedures and tests identified as
RC can be done and the airplane can be put back in an airworthy
condition. Any substitutions or changes to procedures or tests
identified as RC require approval of an AMOC.
(m) Related Information
(1) Refer to Mandatory Continuing Airworthiness Information
(MCAI) EASA AD 2015-0084, dated May 13, 2015; corrected May 18,
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-2016-7262.
(2) For more information about this AD, 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.
(3) Service information identified in this AD that is not
incorporated by reference is available at the addresses specified in
paragraphs (n)(5) and (n)(6) of this AD.
(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 the AD specifies otherwise.
(3) The following service information was approved for IBR on
July 11, 2017.
(i) Airbus Service Bulletin A320-53-1089, Revision 04, dated
June 1, 2016.
(ii) Airbus Service Bulletin A320-53-1090, Revision 02, dated
December 22, 1998. Pages 1, 2, 7, 8, 9, 10, and 11 of this document
are identified as Revision 1, dated June 10, 1998; and pages 3, 4,
5, and 6 of this document are identified as Revision 02, dated
December 22, 1998.
(4) The following service information was approved for IBR on
July 30, 1998, AD 98-13-14, Amendment 39-10602 (63 FR 34556, June
25, 1998).
(i) Airbus Service Bulletin A320-53-1089, dated November 22,
1995.
(ii) Airbus Service Bulletin A320-53-1090, dated November 22,
1995.
(5) For service information identified in this AD, contact
Airbus SAS, 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
Airplane Directorate, 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/ibr-locations.html.
Issued in Renton, Washington, on May 23, 2017.
Michael Kaszycki,
Acting Manager, Transport Airplane Directorate, Aircraft Certification
Service.
[FR Doc. 2017-11290 Filed 6-5-17; 8:45 am]
BILLING CODE 4910-13-P