Airworthiness Directives; Airbus SAS Airplanes, 48920-48924 [2018-20951]
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Federal Register / Vol. 83, No. 189 / Friday, September 28, 2018 / Rules and Regulations
(e) Unsafe Condition
This AD was prompted by the potential for
an un-annunciated failure of the bidirectional data bus that sends critical signals
from the flight control computer to the flight
controls. This unsafe condition, if not
addressed, could result in the flight control
computer’s inability to identify when a
problematic flight control surface needs to be
damped, which could result in loss of control
of the airplane.
(f) Compliance
Comply with this AD within the
compliance times specified, unless already
done.
(g) Airplane Flight Manual Revisions
Within 30 days after October 15, 2018 (the
effective date of this AD), revise the Normal
Procedures and Abnormal Procedures
sections of the airplane flight manual by
adding the information in Gulfstream
Aerospace G650 Airplane Flight Manual
Supplement No. G650–2018–01, dated
August 14, 2018; or Gulfstream Aerospace
G650ER Airplane Flight Manual Supplement
No. G650ER–2018–01, dated August 14,
2018; as applicable to the model
configuration of your airplane.
(h) Alternative Methods of Compliance
(AMOCs)
(1) The Manager, Atlanta ACO Branch,
FAA, has the authority to approve AMOCs
for this AD, if requested using the procedures
found in 14 CFR 39.19. In accordance with
14 CFR 39.19, send your request to your
principal inspector or local Flight Standards
District Office, as appropriate. If sending
information directly to the manager of the
certification office, send it to the attention of
the person identified in paragraph (i) of this
AD.
(2) 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.
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(i) Related Information
For more information about this AD,
contact Myles Jalalian, Aerospace Engineer,
Systems and Equipment Section, AIR–7A3,
Atlanta ACO Branch, FAA, 1701 Columbia
Avenue, College Park, GA 30337; phone:
404–474–5572; fax: 404–474–5606; email:
Myles.Jalalian@faa.gov.
(j) 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.
(i) Gulfstream Aerospace G650 Airplane
Flight Manual, Supplement No. G650–2018–
01, dated August 14, 2018.
(ii) Gulfstream Aerospace G650ER Airplane
Flight Manual, Supplement No. G650ER–
2018–01, dated August 14, 2018.
(3) For service information identified in
this AD, contact Gulfstream Aerospace
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Corporation, Technical Publications Dept.,
P.O. Box 2206, Savannah, GA 31402–2206;
telephone: 800–810–4853; fax: 912–965–
3520; email: pubs@gulfstream.com; internet:
https://www.gulfstream.com/product-support/
technical-publications.
(4) You may view this service information
at the FAA, Policy and Innovation Division,
901 Locust, Kansas City, Missouri 64106. For
information on the availability of this
material at the FAA, call (816) 329–4148.
(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.
[FR Doc. 2018–21103 Filed 9–27–18; 8:45 am]
This AD is effective November 2,
2018.
The Director of the Federal Register
approved the incorporation by reference
of certain publications listed in this AD
as of November 2, 2018.
ADDRESSES: For service information
identified in this final rule, contact
Airbus SAS, Airworthiness Office—
EIAS, Rond-Point Emile Dewoitine No:
2, 31700 Blagnac Cedex, France;
telephone +33 5 61 93 36 96; fax +33 5
61 93 44 51; email account.airwortheas@airbus.com; internet https://
www.airbus.com. You may view this
referenced service information at the
FAA, Transport Standards Branch, 2200
South 216th St., Des Moines, WA. For
information on the availability of this
material at the FAA, call 206–231–3195.
It is also available on the internet at
https://www.regulations.gov by searching
for and locating Docket No. FAA–2018–
0455.
BILLING CODE 4910–13–P
Examining the AD Docket
Issued in Kansas City, Missouri, on
September 20, 2018.
Melvin J. Johnson,
Aircraft Certification Service, Deputy
Director, Policy and Innovation Division,
AIR–601.
DEPARTMENT OF TRANSPORTATION
Federal Aviation Administration
14 CFR Part 39
[Docket No. FAA–2018–0455; Product
Identifier 2017–NM–121–AD; Amendment
39–19436; AD 2018–20–02]
RIN 2120–AA64
Airworthiness Directives; Airbus SAS
Airplanes
Federal Aviation
Administration (FAA), Department of
Transportation (DOT).
ACTION: Final rule.
AGENCY:
We are superseding
Airworthiness Directive (AD) 98–18–24,
which applied to certain Airbus SAS
Model A320 series airplanes. AD 98–
18–24 required repetitive inspections to
detect cracking in the inner flange of a
certain door frame, and corrective
actions, if necessary. AD 98–18–24 also
provided an optional terminating action
for the repetitive inspections. This AD
continues to require the repetitive
inspections of the inner flange of a
certain door frame, with reduced
repetitive inspection intervals, and
corrective action if necessary. This AD
was prompted by a report of cracks on
the inner flange of a certain door frame,
and by the results of a full scale fatigue
test that indicated the intervals for the
repetitive inspections required by AD
98–18–24 must be reduced. We are
issuing this AD to address the unsafe
condition on these products.
SUMMARY:
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DATES:
You may examine the AD docket on
the internet at https://
www.regulations.gov by searching for
and locating Docket No. FAA–2018–
0455; or in person at Docket Operations
between 9 a.m. and 5 p.m., Monday
through Friday, except Federal holidays.
The AD docket contains this final rule,
the regulatory evaluation, any
comments received, and other
information. The address for Docket
Operations (phone: 800–647–5527) is
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; 2200 South
216th St., Des Moines, WA 98198;
telephone and fax 206–231–3223.
SUPPLEMENTARY INFORMATION:
Discussion
We issued a notice of proposed
rulemaking (NPRM) to amend 14 CFR
part 39 to supersede AD 98–18–24,
Amendment 39–10740 (63 FR 49272,
September 15, 1998) (‘‘AD 98–18–24’’).
AD 98–18–24 applied to certain Airbus
SAS Model A320 series airplanes. The
NPRM published in the Federal
Register on May 30, 2018 (83 FR 24690).
The NPRM was prompted by a report of
cracks on the inner flange of door frame
66 at stringer positions 18 and 20, and
by the results of a full scale fatigue test
that indicated the intervals for the
repetitive inspections required by AD
98–18–24 must be reduced. The NPRM
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proposed to continue to require the
repetitive inspections of the inner flange
of a certain door frame, with reduced
repetitive inspection intervals, and
corrective actions if necessary. We are
issuing this AD to address fatigue
cracking in the inner flange of door
frame 66, which could result in reduced
structural integrity of the airplane.
The European Aviation Safety Agency
(EASA), which is the Technical Agent
for the Member States of the European
Union, has issued EASA AD 2017–0128,
dated July 24, 2017 (referred to after this
as the Mandatory Continuing
Airworthiness Information, or ‘‘the
MCAI’’), to correct an unsafe condition
for certain Airbus SAS Model A320–211
and A320–231 airplanes. The MCAI
states:
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During fatigue test on simulated flights,
cracks developed on the inner flange of door
frame 66 at stringer 18 and 20 positions.
These cracks were located in the gusset plate
attachment holes and were hidden by the
plates.
This condition, if not detected and
corrected, could affect the structural integrity
of the fuselage.
To address this potential unsafe condition,
Airbus issued Service Bulletin (SB) A320–
53–1071, later revised, to provide
instructions to inspect and repair the gusset
plate attachment holes at frame 66, at
stringers 18, 20 and 22 both left hand (LH)
and right hand (RH) side of the fuselage
(hereafter collectively referred to as ‘‘the
attachment holes’’ in this [EASA] AD), and
[Airbus] SB A320–53–1072, providing
instructions for reworking of the attachment
holes.
Consequently, DGAC France issued
[French] AD 1996–234–087, later revised
[which corresponds to FAA AD 98–18–24],
requiring repetitive inspections and,
depending on findings, repair of the
attachment holes, and including reference to
a reworking procedure, which constitutes
optional terminating action for the repetitive
inspections of the attachment holes.
Since that [French] AD was issued, based
on results from a full scale fatigue test, it was
determined that the inspection intervals must
be reduced. Airbus issued SB A320–53–1071
Revision 03, modifying the inspection
threshold and intervals, and not changing the
inspection instructions.
For the reason described above, this
[EASA] AD retains the requirement of DGAC
France AD 1996–234–087 R1, which is
superseded, and requires reduction of the
repetitive inspection interval.
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–2018–
0455.
Comments
We gave the public the opportunity to
participate in developing this final rule.
We received no comments on the NPRM
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or on the determination of the cost to
the public.
Conclusion
We reviewed the relevant data and
determined that air safety and the
public interest require adopting this
final rule as proposed, except for minor
editorial changes. We have determined
that these minor changes:
• Are consistent with the intent that
was proposed in the NPRM for
addressing the unsafe condition; and
• Do not add any additional burden
upon the public than was already
proposed in the NPRM.
Related Service Information Under 1
CFR Part 51
Airbus has issued Service Bulletin
A320–53–1071, Revision 03, dated July
20, 2017. This service information
describes procedures for detailed
inspections of the gusset plate
attachment holes at door frame 66 for
cracking and corrective action.
Airbus also issued Service Bulletin
A320–53–1072, Revision 02, dated May
5, 2016. This service information
describes procedures for modification of
the gusset frame attachment at door
frame 66.
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 3
airplanes of U.S. registry.
The actions required by AD 98–18–24,
and retained in this AD, take about 8
work-hours per product, at an average
labor rate of $85 per work-hour. Based
on these figures, the estimated cost of
the actions that are required by AD 98–
18–24 is $680 per product.
We estimate that it would take about
19 work-hours per product to comply
with the basic requirements of this AD.
The average labor rate is $85 per workhour. Based on these figures, we
estimate the cost of this AD on U.S.
operators to be $4,845, or $1,615 per
product.
We have received no definitive data
that would enable us to provide cost
estimates for the on-condition actions
specified in this AD.
In addition, we estimate that the
optional terminating action would take
about 20 work-hours per product, at an
average labor rate of $85 per work-hour.
Required parts costs would be about
$60. Based on these figures, the
estimated cost of the optional
terminating action would be $1,760 per
product.
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We also estimate that it would take
about 1 work-hour per product to
comply with the proposed reporting
requirement in this AD. The average
labor rate is $85 per hour. Based on
these figures, we estimate the cost of
reporting the inspection results on U.S.
operators to be $255, or $85 per product.
Paperwork Reduction Act
A federal agency may not conduct or
sponsor, and a person is not required to
respond to, nor shall a person be subject
to penalty for failure to comply with a
collection of information subject to the
requirements of the Paperwork
Reduction Act unless that collection of
information displays a current valid
OMB control number. The control
number for the collection of information
required by this AD is 2120–0056. The
paperwork cost associated with this AD
has been detailed in the Costs of
Compliance section of this document
and includes time for reviewing
instructions, as well as completing and
reviewing the collection of information.
Therefore, all reporting associated with
this AD is mandatory. Comments
concerning the accuracy of this burden
and suggestions for reducing the burden
should be directed to the FAA at 800
Independence Ave. SW, Washington,
DC 20591, ATTN: Information
Collection Clearance Officer, AES–200.
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
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delegated the authority to issue ADs
applicable to transport category
airplanes and associated appliances to
the Director of the System Oversight
Division.
Regulatory Findings
We determined that this 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:
1. The authority citation for part 39
continues to read as follows:
■
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Authority: 49 U.S.C. 106(g), 40113, 44701.
17:35 Sep 27, 2018
Jkt 244001
[Amended]
2. The FAA amends § 39.13 by
removing Airworthiness Directive (AD)
98–18–24, Amendment 39–10740 (63
FR 49272, September 15, 1998), and
adding the following new AD:
2018–20–02 Airbus SAS: Amendment 39–
19436; Docket No. FAA–2018–0455;
Product Identifier 2017–NM–121–AD.
(a) Effective Date
This AD is effective November 2, 2018.
(b) Affected ADs
This AD replaces AD 98–18–24,
Amendment 39–10740 (63 FR 49272,
September 15, 1998) (‘‘AD 98–18–24’’).
(c) Applicability
This AD applies to Airbus SAS Model
A320–211 and Model A320–231 airplanes,
certificated in any category, serial numbers
0029, 0045, 0046, 0049 through 0057
inclusive, 0059, 0064, and 0065.
(d) Subject
Air Transport Association (ATA) of
America Code 53, Fuselage.
(e) Reason
This AD was prompted by a report of
cracks on the inner flange of door frame 66
at stringer positions 18 and 20, and by the
results of a full scale fatigue test that
indicated the intervals for the repetitive
inspections required by AD 98–18–24 must
be reduced. We are issuing this AD to
address fatigue cracking in the inner flange
of door frame 66, which could result in
reduced structural integrity of the airplane.
(f) Compliance
Comply with this AD within the
compliance times specified, unless already
done.
PART 39—AIRWORTHINESS
DIRECTIVES
VerDate Sep<11>2014
§ 39.13
■
(g) Retained Eddy Current Inspection, With
No Changes
This paragraph restates the requirements of
paragraph (a) of AD 98–18–24, with no
changes. For Model A320 series airplanes on
which Airbus Modification 21778 (reference
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Airbus Service Bulletin A320–53–1072,
dated November 7, 1995, as revised by
Change Notice 0A, dated July 5, 1996) has
not been accomplished: Prior to the
accumulation of 20,000 total flight cycles, or
within 1 year after October 20, 1998 (the
effective date of AD 98–18–24), whichever
occurs later: Perform a rotating probe eddy
current inspection to detect cracking around
the edges of the gusset plate attachment holes
of the inner flange of door frame 66, left and
right, at stringer positions P18, P20, and P22,
in accordance with Airbus Service Bulletin
A320–53–1071, dated November 7, 1995, as
revised by Change Notice 0A, dated July 5,
1996. If any crack is detected, prior to further
flight, repair in accordance with a method
approved by the Manager, International
Section, Transport Standards Branch, FAA.
Repeat the inspection thereafter at intervals
not to exceed 20,000 flight cycles.
(h) Retained Optional Terminating Action,
With No Changes
This paragraph restates the optional
terminating action of paragraph (b) of AD 98–
18–24, with no changes. Modification of the
gusset plate attachment holes of the inner
flange of door frame 66, left and right (Airbus
Modification 21778), in accordance with
Airbus Service Bulletin A320–53–1072,
dated November 7, 1995, as revised by
Change Notice 0A, dated July 5, 1996,
constitutes terminating action for the
repetitive inspection requirements of
paragraph (g) of this AD.
(i) New Requirement of This AD: Repetitive
Inspections
At the applicable compliance time
specified in figure 1 to paragraph (i) of this
AD, do a rotating probe eddy current
inspection to detect cracking around the
edges of the gusset plate attachment holes of
the inner flange of door frame 66, left and
right, in accordance with the
Accomplishment Instructions of Airbus
Service Bulletin A320–53–1071, Revision 03,
dated July 20, 2017. Repeat the inspection
thereafter at intervals not to exceed 10,900
flight cycles.
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(k) Terminating Action for This AD
(1) Repair of a gusset plate attachment hole
area as required by paragraph (j)(1) of this AD
terminates the repetitive inspections required
by paragraph (i) of this AD for that
attachment hole area on that airplane only.
(2) Repair of any other hole of the gusset
plate, as required by paragraph (j)(2) of this
AD, does not terminate the repetitive
inspections required by paragraph (i) of this
AD for that airplane, unless specified
otherwise in the repair instructions provided
by the Manager, International Section,
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Transport Standards Branch, FAA; or the
EASA; or Airbus’s EASA DOA.
(3) Accomplishing the initial inspection
required by paragraph (i) of this AD
terminates the inspections required by
paragraph (g) of this AD.
(l) Optional Modification
Modification of the gusset plate attachment
holes of the inner flange of door frame 66, left
and right, in accordance with the
Accomplishment Instructions of Airbus
Service Bulletin A320–53–1072, Revision 02,
dated May 5, 2016, terminates the repetitive
inspections required by paragraph (i) of this
AD for that airplane.
(m) Reporting
Report the results of the inspection
required by paragraph (i) of this AD that are
done on or after the effective date of this AD
to Airbus Service Bulletin Reporting Online
Application on Airbus World (https://
w3.airbus.com/), or submit the results to
Airbus in accordance with the instructions of
Airbus Service Bulletin A320–53–1071,
Revision 03, dated July 20, 2017. Submit the
report within 30 days after accomplishing the
inspection required by paragraph (i) of this
AD. The report must include the inspection
results, a description of any discrepancies
found, the airplane serial number, and the
number of landings and flight hours on the
airplane. If operators have reported findings
as part of obtaining any corrective actions
approved by the EASA DOA, operators are
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not required to report those findings as
specified in this paragraph.
(n) Service Information Exception
Where Airbus Service Bulletin A320–53–
1071, Revision 03, dated July 20, 2017,
specifies to contact Airbus for appropriate
action, and specifies that action as ‘‘RC’’
(Required for Compliance): Before further
flight, accomplish corrective actions in
accordance with the procedures specified in
paragraph (q)(2) of this AD.
(o) Credit for Previous Actions
(1) This paragraph provides credit for
actions required by paragraph (i) of this AD,
if those actions were performed before the
effective date of this AD using Airbus Service
Bulletin A320–53–1071, Revision 01, dated
July 4, 2002; or Airbus Service Bulletin
A320–53–1071, Revision 02, dated May 5,
2016.
(2) This paragraph provides credit for
actions identified in paragraph (l) of this AD,
if those actions were performed before the
effective date of this AD using Airbus Service
Bulletin A320–53–1072, dated November 7,
1995, as revised by Change Notice 0A, dated
July 5, 1996; or Airbus Service Bulletin
A320–53–1072, Revision 01, dated July 4,
2002.
(p) Paperwork Reduction Act Burden
Statement
A federal agency may not conduct or
sponsor, and a person is not required to
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(j) Corrective Actions
(1) If, during any inspection required by
paragraph (i) of this AD, any crack is found
on a gusset plate attachment hole: Before
further flight, repair the affected attachment
hole, in accordance with the
Accomplishment Instructions of Airbus
Service Bulletin A320–53–1071, Revision 03,
dated July 20, 2017, except as required by
paragraph (n) of this AD.
(2) If, during any inspection required by
paragraph (i) of this AD, any crack is found
on any other hole of the gusset plate: Before
further flight, contact the Manager,
International Section, Transport Standards
Branch, FAA; or the European Aviation
Safety Agency (EASA); or Airbus’s EASA
Design Organization Approval (DOA); for
approved repair instructions and accomplish
those instructions accordingly. If approved
by the DOA, the approval must include the
DOA-authorized signature.
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respond to, nor shall a person be subject to
a penalty for failure to comply with a
collection of information subject to the
requirements of the Paperwork Reduction
Act unless that collection of information
displays a current valid OMB Control
Number. The OMB Control Number for this
information collection is 2120–0056. Public
reporting for this collection of information is
estimated to be approximately 1 hour per
response, including the time for reviewing
instructions, completing and reviewing the
collection of information. All responses to
this collection of information are mandatory.
Comments concerning the accuracy of this
burden and suggestions for reducing the
burden should be directed to the FAA at: 800
Independence Ave. SW, Washington, DC
20591, Attn: Information Collection
Clearance Officer, AES–200.
(q) Other FAA AD Provisions
(1) Alternative Methods of Compliance
(AMOCs): The Manager, International
Section, Transport Standards Branch, FAA,
has the authority to approve AMOCs for this
AD, if requested using the procedures found
in 14 CFR 39.19. In accordance with 14 CFR
39.19, send your request to your principal
inspector or local Flight Standards District
Office, as appropriate. If sending information
directly to the International Section, send it
to the attention of the person identified in
paragraph (r)(2) of this AD. Information may
be emailed to: 9-ANM-116-AMOCREQUESTS@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
98–18–24 are approved as AMOCs for the
corresponding provisions of this AD.
(2) Contacting the Manufacturer: As of the
effective date of this AD, for any requirement
in this AD to obtain corrective actions from
a manufacturer, the action must be
accomplished using a method approved by
the Manager, International Section, Transport
Standards Branch, FAA; or the EASA; or
Airbus SAS’s EASA DOA. If approved by the
DOA, the approval must include the DOAauthorized signature.
(3) Required for Compliance (RC): Except
as required by paragraph (n) 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.
(r) Related Information
(1) Refer to Mandatory Continuing
Airworthiness Information (MCAI) EASA AD
2017–0128, dated July 24, 2017, for related
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17:35 Sep 27, 2018
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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–2018–0455.
(2) For more information about this AD,
contact Sanjay Ralhan, Aerospace Engineer,
International Section, Transport Standards
Branch, FAA; 2200 South 216th St., Des
Moines, WA 98198; telephone and fax 206–
231–3223.
(3) Service information identified in this
AD that is not incorporated by reference is
available at the addresses specified in
paragraphs (s)(3) and (s)(4) of this AD.
(s) Material Incorporated by Reference
(1) The Director of the Federal Register
approved the incorporation by reference
(IBR) of the service information listed in this
paragraph under 5 U.S.C. 552(a) and 1 CFR
part 51.
(2) You must use this service information
as applicable to do the actions required by
this AD, unless this AD specifies otherwise.
(i) Airbus Service Bulletin A320–53–1071,
Revision 03, dated July 20, 2017.
(ii) Airbus Service Bulletin A320–53–1072,
Revision 02, dated May 5, 2016.
(3) For service information identified in
this AD, contact Airbus SAS, Airworthiness
Office—EIAS, Rond-Point Emile Dewoitine
No: 2, 31700 Blagnac Cedex, France;
telephone +33 5 61 93 36 96; fax +33 5 61
93 44 51; email account.airworth-eas@
airbus.com; internet https://www.airbus.com.
(4) You may view this service information
at the FAA, Transport Standards Branch,
2200 South 216th St., Des Moines, WA. For
information on the availability of this
material at the FAA, call 206–231–3195.
(5) You may view this service information
that is incorporated by reference at the
National Archives and Records
Administration (NARA). For information on
the availability of this material at NARA, call
202–741–6030, or go to: https://
www.archives.gov/federal-register/cfr/ibrlocations.html.
Issued in Des Moines, Washington, on
September 13, 2018.
Michael Kaszycki,
Acting Director, System Oversight Division,
Aircraft Certification Service.
[FR Doc. 2018–20951 Filed 9–27–18; 8:45 am]
BILLING CODE 4910–13–P
DEPARTMENT OF TRANSPORTATION
Federal Aviation Administration
14 CFR Part 39
[Docket No. FAA–2018–0306; Product
Identifier 2018–NM–039–AD; Amendment
39–19426; AD 2018–19–25]
RIN 2120–AA64
ACTION:
Final rule.
We are adopting a new
airworthiness directive (AD) for all
Dassault Aviation Model FALCON 2000
airplanes. This AD was prompted by a
determination that new or more
restrictive airworthiness limitations are
necessary. This AD requires revising the
maintenance or inspection program, as
applicable, to incorporate new
maintenance requirements and
airworthiness limitations. We are
issuing this AD to address the unsafe
condition on these products.
DATES: This AD is effective November 2,
2018.
The Director of the Federal Register
approved the incorporation by reference
of a certain publication listed in this AD
as of November 2, 2018.
ADDRESSES: For service information
identified in this final rule, contact
Dassault Falcon Jet Corporation,
Teterboro Airport, P.O. Box 2000, South
Hackensack, NJ 07606; telephone 201–
440–6700; internet https://
www.dassaultfalcon.com. You may
view this service information at the
FAA, Transport Standards Branch, 2200
South 216th St., Des Moines, WA. For
information on the availability of this
material at the FAA, call 206–231–3195.
It is also available on the internet at
https://www.regulations.gov by searching
for and locating Docket No. FAA–2018–
0306.
SUMMARY:
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–2018–
0306; or in person at Docket Operations
between 9 a.m. and 5 p.m., Monday
through Friday, except Federal holidays.
The AD docket contains this final rule,
the regulatory evaluation, any
comments received, and other
information. The address for Docket
Operations (phone: 800–647–5527) is
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: Tom
Rodriguez, Aerospace Engineer,
International Section, Transport
Standards Branch, FAA, 2200 South
216th St., Des Moines, WA 98198;
telephone and fax 206–231–3226.
SUPPLEMENTARY INFORMATION:
Airworthiness Directives; Dassault
Aviation Airplanes
Discussion
Federal Aviation
Administration (FAA), Department of
Transportation (DOT).
We issued a notice of proposed
rulemaking (NPRM) to amend 14 CFR
part 39 by adding an AD that would
AGENCY:
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[Federal Register Volume 83, Number 189 (Friday, September 28, 2018)]
[Rules and Regulations]
[Pages 48920-48924]
From the Federal Register Online via the Government Publishing Office [www.gpo.gov]
[FR Doc No: 2018-20951]
-----------------------------------------------------------------------
DEPARTMENT OF TRANSPORTATION
Federal Aviation Administration
14 CFR Part 39
[Docket No. FAA-2018-0455; Product Identifier 2017-NM-121-AD; Amendment
39-19436; AD 2018-20-02]
RIN 2120-AA64
Airworthiness Directives; Airbus SAS Airplanes
AGENCY: Federal Aviation Administration (FAA), Department of
Transportation (DOT).
ACTION: Final rule.
-----------------------------------------------------------------------
SUMMARY: We are superseding Airworthiness Directive (AD) 98-18-24,
which applied to certain Airbus SAS Model A320 series airplanes. AD 98-
18-24 required repetitive inspections to detect cracking in the inner
flange of a certain door frame, and corrective actions, if necessary.
AD 98-18-24 also provided an optional terminating action for the
repetitive inspections. This AD continues to require the repetitive
inspections of the inner flange of a certain door frame, with reduced
repetitive inspection intervals, and corrective action if necessary.
This AD was prompted by a report of cracks on the inner flange of a
certain door frame, and by the results of a full scale fatigue test
that indicated the intervals for the repetitive inspections required by
AD 98-18-24 must be reduced. We are issuing this AD to address the
unsafe condition on these products.
DATES: This AD is effective November 2, 2018.
The Director of the Federal Register approved the incorporation by
reference of certain publications listed in this AD as of November 2,
2018.
ADDRESSES: For service information identified in this final rule,
contact Airbus SAS, Airworthiness Office--EIAS, Rond-Point Emile
Dewoitine No: 2, 31700 Blagnac Cedex, France; telephone +33 5 61 93 36
96; fax +33 5 61 93 44 51; email [email protected];
internet https://www.airbus.com. You may view this referenced service
information at the FAA, Transport Standards Branch, 2200 South 216th
St., Des Moines, WA. For information on the availability of this
material at the FAA, call 206-231-3195. It is also available on the
internet at https://www.regulations.gov by searching for and locating
Docket No. FAA-2018-0455.
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-2018-
0455; or in person at Docket Operations between 9 a.m. and 5 p.m.,
Monday through Friday, except Federal holidays. The AD docket contains
this final rule, the regulatory evaluation, any comments received, and
other information. The address for Docket Operations (phone: 800-647-
5527) is 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; 2200 South
216th St., Des Moines, WA 98198; telephone and fax 206-231-3223.
SUPPLEMENTARY INFORMATION:
Discussion
We issued a notice of proposed rulemaking (NPRM) to amend 14 CFR
part 39 to supersede AD 98-18-24, Amendment 39-10740 (63 FR 49272,
September 15, 1998) (``AD 98-18-24''). AD 98-18-24 applied to certain
Airbus SAS Model A320 series airplanes. The NPRM published in the
Federal Register on May 30, 2018 (83 FR 24690). The NPRM was prompted
by a report of cracks on the inner flange of door frame 66 at stringer
positions 18 and 20, and by the results of a full scale fatigue test
that indicated the intervals for the repetitive inspections required by
AD 98-18-24 must be reduced. The NPRM
[[Page 48921]]
proposed to continue to require the repetitive inspections of the inner
flange of a certain door frame, with reduced repetitive inspection
intervals, and corrective actions if necessary. We are issuing this AD
to address fatigue cracking in the inner flange of door frame 66, which
could result in reduced structural integrity of the airplane.
The European Aviation Safety Agency (EASA), which is the Technical
Agent for the Member States of the European Union, has issued EASA AD
2017-0128, dated July 24, 2017 (referred to after this as the Mandatory
Continuing Airworthiness Information, or ``the MCAI''), to correct an
unsafe condition for certain Airbus SAS Model A320-211 and A320-231
airplanes. The MCAI states:
During fatigue test on simulated flights, cracks developed on
the inner flange of door frame 66 at stringer 18 and 20 positions.
These cracks were located in the gusset plate attachment holes and
were hidden by the plates.
This condition, if not detected and corrected, could affect the
structural integrity of the fuselage.
To address this potential unsafe condition, Airbus issued
Service Bulletin (SB) A320-53-1071, later revised, to provide
instructions to inspect and repair the gusset plate attachment holes
at frame 66, at stringers 18, 20 and 22 both left hand (LH) and
right hand (RH) side of the fuselage (hereafter collectively
referred to as ``the attachment holes'' in this [EASA] AD), and
[Airbus] SB A320-53-1072, providing instructions for reworking of
the attachment holes.
Consequently, DGAC France issued [French] AD 1996-234-087, later
revised [which corresponds to FAA AD 98-18-24], requiring repetitive
inspections and, depending on findings, repair of the attachment
holes, and including reference to a reworking procedure, which
constitutes optional terminating action for the repetitive
inspections of the attachment holes.
Since that [French] AD was issued, based on results from a full
scale fatigue test, it was determined that the inspection intervals
must be reduced. Airbus issued SB A320-53-1071 Revision 03,
modifying the inspection threshold and intervals, and not changing
the inspection instructions.
For the reason described above, this [EASA] AD retains the
requirement of DGAC France AD 1996-234-087 R1, which is superseded,
and requires reduction of the repetitive inspection interval.
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-2018-
0455.
Comments
We gave the public the opportunity to participate in developing
this final rule. We received no comments on the NPRM or on the
determination of the cost to the public.
Conclusion
We reviewed the relevant data and determined that air safety and
the public interest require adopting this final rule as proposed,
except for minor editorial changes. We have determined that these minor
changes:
Are consistent with the intent that was proposed in the
NPRM for addressing the unsafe condition; and
Do not add any additional burden upon the public than was
already proposed in the NPRM.
Related Service Information Under 1 CFR Part 51
Airbus has issued Service Bulletin A320-53-1071, Revision 03, dated
July 20, 2017. This service information describes procedures for
detailed inspections of the gusset plate attachment holes at door frame
66 for cracking and corrective action.
Airbus also issued Service Bulletin A320-53-1072, Revision 02,
dated May 5, 2016. This service information describes procedures for
modification of the gusset frame attachment at door frame 66.
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 3 airplanes of U.S. registry.
The actions required by AD 98-18-24, and retained in this AD, take
about 8 work-hours per product, at an average labor rate of $85 per
work-hour. Based on these figures, the estimated cost of the actions
that are required by AD 98-18-24 is $680 per product.
We estimate that it would take about 19 work-hours per product to
comply with the basic requirements of this AD. The average labor rate
is $85 per work-hour. Based on these figures, we estimate the cost of
this AD on U.S. operators to be $4,845, or $1,615 per product.
We have received no definitive data that would enable us to provide
cost estimates for the on-condition actions specified in this AD.
In addition, we estimate that the optional terminating action would
take about 20 work-hours per product, at an average labor rate of $85
per work-hour. Required parts costs would be about $60. Based on these
figures, the estimated cost of the optional terminating action would be
$1,760 per product.
We also estimate that it would take about 1 work-hour per product
to comply with the proposed reporting requirement in this AD. The
average labor rate is $85 per hour. Based on these figures, we estimate
the cost of reporting the inspection results on U.S. operators to be
$255, or $85 per product.
Paperwork Reduction Act
A federal agency may not conduct or sponsor, and a person is not
required to respond to, nor shall a person be subject to penalty for
failure to comply with a collection of information subject to the
requirements of the Paperwork Reduction Act unless that collection of
information displays a current valid OMB control number. The control
number for the collection of information required by this AD is 2120-
0056. The paperwork cost associated with this AD has been detailed in
the Costs of Compliance section of this document and includes time for
reviewing instructions, as well as completing and reviewing the
collection of information. Therefore, all reporting associated with
this AD is mandatory. Comments concerning the accuracy of this burden
and suggestions for reducing the burden should be directed to the FAA
at 800 Independence Ave. SW, Washington, DC 20591, ATTN: Information
Collection Clearance Officer, AES-200.
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
[[Page 48922]]
delegated the authority to issue ADs applicable to transport category
airplanes and associated appliances to the Director of the System
Oversight Division.
Regulatory Findings
We determined that this 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)
98-18-24, Amendment 39-10740 (63 FR 49272, September 15, 1998), and
adding the following new AD:
2018-20-02 Airbus SAS: Amendment 39-19436; Docket No. FAA-2018-0455;
Product Identifier 2017-NM-121-AD.
(a) Effective Date
This AD is effective November 2, 2018.
(b) Affected ADs
This AD replaces AD 98-18-24, Amendment 39-10740 (63 FR 49272,
September 15, 1998) (``AD 98-18-24'').
(c) Applicability
This AD applies to Airbus SAS Model A320-211 and Model A320-231
airplanes, certificated in any category, serial numbers 0029, 0045,
0046, 0049 through 0057 inclusive, 0059, 0064, and 0065.
(d) Subject
Air Transport Association (ATA) of America Code 53, Fuselage.
(e) Reason
This AD was prompted by a report of cracks on the inner flange
of door frame 66 at stringer positions 18 and 20, and by the results
of a full scale fatigue test that indicated the intervals for the
repetitive inspections required by AD 98-18-24 must be reduced. We
are issuing this AD to address fatigue cracking in the inner flange
of door frame 66, which could result in reduced structural integrity
of the airplane.
(f) Compliance
Comply with this AD within the compliance times specified,
unless already done.
(g) Retained Eddy Current Inspection, With No Changes
This paragraph restates the requirements of paragraph (a) of AD
98-18-24, with no changes. For Model A320 series airplanes on which
Airbus Modification 21778 (reference Airbus Service Bulletin A320-
53-1072, dated November 7, 1995, as revised by Change Notice 0A,
dated July 5, 1996) has not been accomplished: Prior to the
accumulation of 20,000 total flight cycles, or within 1 year after
October 20, 1998 (the effective date of AD 98-18-24), whichever
occurs later: Perform a rotating probe eddy current inspection to
detect cracking around the edges of the gusset plate attachment
holes of the inner flange of door frame 66, left and right, at
stringer positions P18, P20, and P22, in accordance with Airbus
Service Bulletin A320-53-1071, dated November 7, 1995, as revised by
Change Notice 0A, dated July 5, 1996. If any crack is detected,
prior to further flight, repair in accordance with a method approved
by the Manager, International Section, Transport Standards Branch,
FAA. Repeat the inspection thereafter at intervals not to exceed
20,000 flight cycles.
(h) Retained Optional Terminating Action, With No Changes
This paragraph restates the optional terminating action of
paragraph (b) of AD 98-18-24, with no changes. Modification of the
gusset plate attachment holes of the inner flange of door frame 66,
left and right (Airbus Modification 21778), in accordance with
Airbus Service Bulletin A320-53-1072, dated November 7, 1995, as
revised by Change Notice 0A, dated July 5, 1996, constitutes
terminating action for the repetitive inspection requirements of
paragraph (g) of this AD.
(i) New Requirement of This AD: Repetitive Inspections
At the applicable compliance time specified in figure 1 to
paragraph (i) of this AD, do a rotating probe eddy current
inspection to detect cracking around the edges of the gusset plate
attachment holes of the inner flange of door frame 66, left and
right, in accordance with the Accomplishment Instructions of Airbus
Service Bulletin A320-53-1071, Revision 03, dated July 20, 2017.
Repeat the inspection thereafter at intervals not to exceed 10,900
flight cycles.
[[Page 48923]]
[GRAPHIC] [TIFF OMITTED] TR28SE18.001
(j) Corrective Actions
(1) If, during any inspection required by paragraph (i) of this
AD, any crack is found on a gusset plate attachment hole: Before
further flight, repair the affected attachment hole, in accordance
with the Accomplishment Instructions of Airbus Service Bulletin
A320-53-1071, Revision 03, dated July 20, 2017, except as required
by paragraph (n) of this AD.
(2) If, during any inspection required by paragraph (i) of this
AD, any crack is found on any other hole of the gusset plate: Before
further flight, contact the Manager, International Section,
Transport Standards Branch, FAA; or the European Aviation Safety
Agency (EASA); or Airbus's EASA Design Organization Approval (DOA);
for approved repair instructions and accomplish those instructions
accordingly. If approved by the DOA, the approval must include the
DOA-authorized signature.
(k) Terminating Action for This AD
(1) Repair of a gusset plate attachment hole area as required by
paragraph (j)(1) of this AD terminates the repetitive inspections
required by paragraph (i) of this AD for that attachment hole area
on that airplane only.
(2) Repair of any other hole of the gusset plate, as required by
paragraph (j)(2) of this AD, does not terminate the repetitive
inspections required by paragraph (i) of this AD for that airplane,
unless specified otherwise in the repair instructions provided by
the Manager, International Section, Transport Standards Branch, FAA;
or the EASA; or Airbus's EASA DOA.
(3) Accomplishing the initial inspection required by paragraph
(i) of this AD terminates the inspections required by paragraph (g)
of this AD.
(l) Optional Modification
Modification of the gusset plate attachment holes of the inner
flange of door frame 66, left and right, in accordance with the
Accomplishment Instructions of Airbus Service Bulletin A320-53-1072,
Revision 02, dated May 5, 2016, terminates the repetitive
inspections required by paragraph (i) of this AD for that airplane.
(m) Reporting
Report the results of the inspection required by paragraph (i)
of this AD that are done on or after the effective date of this AD
to Airbus Service Bulletin Reporting Online Application on Airbus
World (https://w3.airbus.com/), or submit the results to Airbus in
accordance with the instructions of Airbus Service Bulletin A320-53-
1071, Revision 03, dated July 20, 2017. Submit the report within 30
days after accomplishing the inspection required by paragraph (i) of
this AD. The report must include the inspection results, a
description of any discrepancies found, the airplane serial number,
and the number of landings and flight hours on the airplane. If
operators have reported findings as part of obtaining any corrective
actions approved by the EASA DOA, operators are not required to
report those findings as specified in this paragraph.
(n) Service Information Exception
Where Airbus Service Bulletin A320-53-1071, Revision 03, dated
July 20, 2017, specifies to contact Airbus for appropriate action,
and specifies that action as ``RC'' (Required for Compliance):
Before further flight, accomplish corrective actions in accordance
with the procedures specified in paragraph (q)(2) of this AD.
(o) Credit for Previous Actions
(1) This paragraph provides credit for actions required by
paragraph (i) of this AD, if those actions were performed before the
effective date of this AD using Airbus Service Bulletin A320-53-
1071, Revision 01, dated July 4, 2002; or Airbus Service Bulletin
A320-53-1071, Revision 02, dated May 5, 2016.
(2) This paragraph provides credit for actions identified in
paragraph (l) of this AD, if those actions were performed before the
effective date of this AD using Airbus Service Bulletin A320-53-
1072, dated November 7, 1995, as revised by Change Notice 0A, dated
July 5, 1996; or Airbus Service Bulletin A320-53-1072, Revision 01,
dated July 4, 2002.
(p) Paperwork Reduction Act Burden Statement
A federal agency may not conduct or sponsor, and a person is not
required to
[[Page 48924]]
respond to, nor shall a person be subject to a penalty for failure
to comply with a collection of information subject to the
requirements of the Paperwork Reduction Act unless that collection
of information displays a current valid OMB Control Number. The OMB
Control Number for this information collection is 2120-0056. Public
reporting for this collection of information is estimated to be
approximately 1 hour per response, including the time for reviewing
instructions, completing and reviewing the collection of
information. All responses to this collection of information are
mandatory. Comments concerning the accuracy of this burden and
suggestions for reducing the burden should be directed to the FAA
at: 800 Independence Ave. SW, Washington, DC 20591, Attn:
Information Collection Clearance Officer, AES-200.
(q) Other FAA AD Provisions
(1) Alternative Methods of Compliance (AMOCs): The Manager,
International Section, Transport Standards Branch, FAA, has the
authority to approve AMOCs for this AD, if requested using the
procedures found in 14 CFR 39.19. In accordance with 14 CFR 39.19,
send your request to your principal inspector or local Flight
Standards District Office, as appropriate. If sending information
directly to the International Section, send it to the attention of
the person identified in paragraph (r)(2) of this AD. Information
may be emailed to: [email protected].
(i) Before using any approved AMOC, notify your appropriate
principal inspector, or lacking a principal inspector, the manager
of the local flight standards district office/certificate holding
district office.
(ii) AMOCs approved previously for AD 98-18-24 are approved as
AMOCs for the corresponding provisions of this AD.
(2) Contacting the Manufacturer: As of the effective date of
this AD, for any requirement in this AD to obtain corrective actions
from a manufacturer, the action must be accomplished using a method
approved by the Manager, International Section, Transport Standards
Branch, FAA; or the EASA; or Airbus SAS's EASA DOA. If approved by
the DOA, the approval must include the DOA-authorized signature.
(3) Required for Compliance (RC): Except as required by
paragraph (n) 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.
(r) Related Information
(1) Refer to Mandatory Continuing Airworthiness Information
(MCAI) EASA AD 2017-0128, dated July 24, 2017, 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-2018-0455.
(2) For more information about this AD, contact Sanjay Ralhan,
Aerospace Engineer, International Section, Transport Standards
Branch, FAA; 2200 South 216th St., Des Moines, WA 98198; telephone
and fax 206-231-3223.
(3) Service information identified in this AD that is not
incorporated by reference is available at the addresses specified in
paragraphs (s)(3) and (s)(4) of this AD.
(s) Material Incorporated by Reference
(1) The Director of the Federal Register approved the
incorporation by reference (IBR) of the service information listed
in this paragraph under 5 U.S.C. 552(a) and 1 CFR part 51.
(2) You must use this service information as applicable to do
the actions required by this AD, unless this AD specifies otherwise.
(i) Airbus Service Bulletin A320-53-1071, Revision 03, dated
July 20, 2017.
(ii) Airbus Service Bulletin A320-53-1072, Revision 02, dated
May 5, 2016.
(3) For service information identified in this AD, contact
Airbus SAS, Airworthiness Office--EIAS, Rond-Point Emile Dewoitine
No: 2, 31700 Blagnac Cedex, France; telephone +33 5 61 93 36 96; fax
+33 5 61 93 44 51; email [email protected]; internet
https://www.airbus.com.
(4) You may view this service information at the FAA, Transport
Standards Branch, 2200 South 216th St., Des Moines, WA. For
information on the availability of this material at the FAA, call
206-231-3195.
(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 Des Moines, Washington, on September 13, 2018.
Michael Kaszycki,
Acting Director, System Oversight Division, Aircraft Certification
Service.
[FR Doc. 2018-20951 Filed 9-27-18; 8:45 am]
BILLING CODE 4910-13-P
