Airworthiness Directives; Bombardier, Inc., Airplanes, 40703-40708 [2018-17622]
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Federal Register / Vol. 83, No. 159 / Thursday, August 16, 2018 / Proposed Rules
Reorganization Act of 1974, secs. 201, 202,
206, 211 (42 U.S.C. 5841, 5842, 5846, 5851);
Nuclear Waste Policy Act of 1982, sec. 306
(42 U.S.C. 10226); National Environmental
Policy Act of 1969 (42 U.S.C. 4332); 44 U.S.C.
3504 note; Sec. 109, Pub. L. 96–295, 94 Stat.
783.
2. In § 50.55a:
a. Remove and reserve paragraphs
(a)(1)(iii)(E) and (G);
■ b. Revise paragraph (a)(3) introductory
text;
■ c. In paragraph (a)(3)(i), remove the
phrase ‘‘Revision 37’’ and add in its
place the phrase ‘‘Revision 38’’;
■ d. In paragraph (a)(3)(ii), remove the
phrase ‘‘Revision 18’’ and add in its
place the phrase ‘‘Revision 19’’;
■ e. In paragraph (a)(3)(iii), remove the
phrase ‘‘Revision 2’’ and add in its place
the phrase ‘‘Revision 3’’;
■ f. Remove paragraph (b)(2)(xxxvii);
and
■ g. Remove and reserve paragraph
(b)(3)(x).
The revision reads as follows:
■
■
§ 50.55a
Codes and standards.
(3) U.S. Nuclear Regulatory
Commission (NRC) Public Document
Room, 11555 Rockville Pike, Rockville,
Maryland 20852; telephone: 1–800–
397–4209; email: pdr.resource@nrc.gov;
https://www.nrc.gov/reading-rm/doccollections/reg-guides/. The use of Code
Cases listed in the NRC regulatory
guides in paragraphs (a)(3)(i) through
(iii) of this section is acceptable with the
specified conditions in those guides
when implementing the editions and
addenda of the ASME BPV Code and
ASME OM Code incorporated by
reference in paragraph (a)(1) of this
section.
*
*
*
*
*
Dated at Rockville, Maryland, this 26th day
of July, 2018.
For the Nuclear Regulatory Commission.
Michele G. Evans,
Deputy Director, Office of Nuclear Reactor
Regulation.
[FR Doc. 2018–17650 Filed 8–15–18; 8:45 am]
BILLING CODE 7590–01–P
DEPARTMENT OF TRANSPORTATION
Federal Aviation Administration
sradovich on DSK3GMQ082PROD with PROPOSALS
14 CFR Part 39
[Docket No. FAA–2018–0710; Product
Identifier 2018–NM–079–AD]
RIN 2120–AA64
Airworthiness Directives; Bombardier,
Inc., Airplanes
Federal Aviation
Administration (FAA), DOT.
AGENCY:
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Notice of proposed rulemaking
(NPRM).
ACTION:
We propose to adopt a new
airworthiness directive (AD) for certain
Bombardier, Inc., Model BD–700–1A10
and BD–700–1A11 airplanes. This
proposed AD was prompted by inservice findings that a cotter pin at the
main fitting joint of the nose landing
gear (NLG) retraction actuator to the
NLG strut showed evidence of shearing
after a NLG retraction-extension cycling.
This proposed AD would require
revising the maintenance or inspection
program, as applicable, a general visual
inspection for damage of a certain cotter
pin present on certain configurations of
the NLG strut assembly and for the
modification number shown on the
identification plate for the NLG strut,
and modification of the NLG retraction
actuator hardware on any damaged NLG
strut assembly. We are proposing this
AD to address the unsafe condition on
these products.
DATES: We must receive comments on
this proposed AD by October 1, 2018.
ADDRESSES: You may send comments,
using the procedures found in 14 CFR
11.43 and 11.45, by any of the following
methods:
• Federal eRulemaking Portal: Go to
https://www.regulations.gov. Follow the
instructions for submitting comments.
• Fax: 202–493–2251.
• Mail: U.S. Department of
Transportation, Docket Operations,
M–30, West Building Ground Floor,
Room W12–140, 1200 New Jersey
Avenue SE, Washington, DC 20590.
• Hand Delivery: Deliver to Mail
address above between 9 a.m. and 5
p.m., Monday through Friday, except
Federal holidays.
For service information identified in
this NPRM, contact Bombardier, Inc.,
ˆ
400 Cote-Vertu Road West, Dorval,
´
Quebec H4S 1Y9, Canada; telephone
514–855–5000; fax 514–855–7401; email
thd.crj@aero.bombardier.com; internet
https://www.bombardier.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.
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–
0710; 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 NPRM, the
regulatory evaluation, any comments
received, and other information. The
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40703
street address for Docket Operations
(phone: 800–647–5527) is in the
ADDRESSES section. Comments will be
available in the AD docket shortly after
receipt.
FOR FURTHER INFORMATION CONTACT:
Cesar Gomez, Aerospace Engineer,
Airframe and Mechanical Systems
Section, FAA, New York ACO Branch,
1600 Stewart Avenue, Suite 410,
Westbury, NY 11590; telephone 516–
228–7318; fax 516–794–5531; email 9avs-nyaco-cos@faa.gov.
SUPPLEMENTARY INFORMATION:
Comments Invited
We invite you to send any written
relevant data, views, or arguments about
this proposal. Send your comments to
an address listed under the ADDRESSES
section. Include ‘‘Docket No. FAA–
2018–0710; Product Identifier 2018–
NM–079–AD’’ at the beginning of your
comments. We specifically invite
comments on the overall regulatory,
economic, environmental, and energy
aspects of this NPRM. We will consider
all comments received by the closing
date and may amend this NPRM
because of those comments.
We will post all comments we
receive, without change, to https://
www.regulations.gov, including any
personal information you provide. We
will also post a report summarizing each
substantive verbal contact we receive
about this NPRM.
Discussion
Transport Canada Civil Aviation
(TCCA), which is the aviation authority
for Canada, has issued Canadian AD
CF–2018–05, dated January 23, 2018
(referred to after this as the Mandatory
Continuing Airworthiness Information,
or ‘‘the MCAI’’), to correct an unsafe
condition for certain Bombardier, Inc.,
Model BD–700–1A10 and BD–700–
1A11 airplanes. The MCAI states:
There have been in-service findings
whereby the cotter pin at the retraction
actuator to nose landing gear (NLG) strut
main fitting was observed to be damaged
after a NLG retraction-extension cycling. This
condition could lead to a loss of hardware
and result in an actuator disconnect resulting
in a failure to retract or extend, or in an
undamped freefall of the NLG [which could
adversely affect the airplane’s continued safe
flight and landing].
This AD mandates a revision to the
approved maintenance schedule. This AD
also mandates a visual inspection of the
cotter pin for certain configurations of NLG
strut assembly, and if found damaged, the
incorporation of a modification which
introduces a new castellated nut, spacer, end
plate and sleeve to the NLG retraction
actuator to main fitting joint.
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The required actions also include a
prohibition on accomplishing LiebherrAerospace Service Bulletin 1285A–32–
07 at any revision level on the NLG strut
assemblies of any Bombardier, Inc.,
Model BD–700–1A10 or BD–700–1A11
airplane in order to prevent the
installation of the affected configuration
of the NLG strut assembly. 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–
0710.
Related Service Information Under 1
CFR Part 51
Bombardier has issued the following
service information, which describes
procedures for a general visual
inspection for damage of the cotter pin
retaining the bolt that secures the main
fitting joint of the NLG retraction
actuator to the NLG strut and for the
modification number shown on the
identification plate for the NLG strut,
and modifying the attachment hardware
that secures the NLG retraction actuator
to the NLG strut. These documents are
distinct since they apply to different
airplane models in different
configurations.
• Bombardier Service Bulletin 700–
1A11–32–022, Revision 2, dated
November 6, 2017.
• Bombardier Service Bulletin 700–
32–035, Revision 2, dated November 6,
2017.
• Bombardier Service Bulletin 700–
32–5011, Revision 2, dated November 6,
2017.
• Bombardier Service Bulletin 700–
32–6011, Revision 2, dated November 6,
2017.
Bombardier has issued the following
service information, which identifies
airworthiness limitation tasks for
restoration of the main fitting joint of
the NLG retraction actuator to the NLG
strut. These documents are distinct
since they apply to different airplane
models in different configurations.
• Task 32–33–01–111 of Bombardier
Global 5000 BD–700 Time Limits/
Maintenance Checks, Revision 19, dated
November 13, 2017, for Bombardier
Model BD–700–1A11 airplanes.
• Task 32–33–01–111 of Bombardier
Global 5000 GL 5000 Featuring Global
Vision Flight Deck—Time Limits/
Maintenance Checks, Revision 9, dated
November 13, 2017, for Bombardier
Model BD–700–1A11 airplanes.
• Task 32–33–01–111 of Bombardier
Global Express BD–700 Time Limits/
Maintenance Checks, Revision 28, dated
November 13, 2017, for Bombardier
Model BD–700–1A10 airplanes.
• Task 32–33–01–111 of Bombardier
Global Express XRS BD–700 Time
Limits/Maintenance Checks, Revision
15, dated November 13, 2017, for
Bombardier Model BD–700–1A10
airplanes.
• Task 32–33–01–111 of Bombardier
Global 6000 GL 6000 Time Limits/
Maintenance Checks, Revision 9, dated
November 13, 2017, for Bombardier
Model BD–700–1A10 airplanes.
This service information is reasonably
available because the interested parties
have access to it through their normal
course of business or by the means
identified in the ADDRESSES section.
FAA’s Determination
This product has been approved by
the aviation authority of another
country, and is approved for operation
in the United States. Pursuant to our
bilateral agreement with the State of
Design Authority, we have been notified
of the unsafe condition described in the
MCAI and service information
referenced above. We are proposing this
AD because we evaluated all the
relevant information and determined
the unsafe condition described
previously is likely to exist or develop
on other products of the same type
design.
This proposed AD requires revisions
to certain operator maintenance
documents to include new actions (e.g.,
inspections). Compliance with these
actions is required by 14 CFR 91.403(c).
For airplanes that have been previously
modified, altered, or repaired in the
areas addressed by this proposed AD,
the operator may not be able to
accomplish the actions described in the
revisions. In this situation, to comply
with 14 CFR 91.403(c), the operator
must request approval for an alternative
method of compliance according to
paragraph (l)(1) of this proposed AD.
The request should include a
description of changes to the required
actions that will ensure the continued
damage tolerance of the affected
structure.
Proposed Requirements of This NPRM
This proposed AD would require
accomplishing the actions specified in
the service information described
previously.
Explanation of Service Bulletin
Effectivity
Where Bombardier Service Bulletin
700–1A11–32–022 erroneously specifies
‘‘BD–700–1A10 aircraft’’ in paragraph
1.A, ‘‘Effectivity,’’ the effectivity should
be Bombardier, Inc., Model ‘‘BD–700–
1A11 airplanes’’ instead.
Costs of Compliance
We estimate that this proposed AD
affects 60 airplanes of U.S. registry. We
estimate the following costs to comply
with this proposed AD:
ESTIMATED COSTS
Parts cost
Cost per
product
Cost on U.S.
operators
4 work-hours × $85 per hour = $340 ..........................................................................................
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Labor cost
$0
$340
$20,400
We have determined that revising the
maintenance or inspection program
takes an average of 90 work-hours per
operator, although we recognize that
this number may vary from operator to
operator. In the past, we have estimated
that this action takes 1 work-hour per
airplane. Since operators incorporate
maintenance or inspection program
changes for their affected fleet(s), we
have determined that a per-operator
estimate is more accurate than a per-
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airplane estimate. Therefore, we
estimate the total cost per operator to be
$7,650 (90 work-hours × $85 per workhour).
We estimate the following costs to do
the necessary on-condition action that
would be required based on the results
of any required actions. We have no way
of determining the number of aircraft
that might need this on-condition
action:
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ESTIMATED COSTS OF ON-CONDITION
ACTION
Labor cost
Parts
cost
Cost per
product
1 work-hour × $85
per hour = $85 ......
$10,487
$10,572
According to the manufacturer, some
or all of the costs of this proposed AD
may be covered under warranty, thereby
reducing the cost impact on affected
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Federal Register / Vol. 83, No. 159 / Thursday, August 16, 2018 / Proposed Rules
individuals. We do not control warranty
coverage for affected individuals. As a
result, we have included all known
costs in our cost estimate.
Authority for This Rulemaking
Title 49 of the United States Code
specifies the FAA’s authority to issue
rules on aviation safety. Subtitle I,
section 106, describes the authority of
the FAA Administrator. Subtitle VII:
Aviation Programs, describes in more
detail the scope of the Agency’s
authority.
We are issuing this rulemaking under
the authority described in Subtitle VII,
Part A, Subpart III, Section 44701:
‘‘General requirements.’’ Under that
section, Congress charges the FAA with
promoting safe flight of civil aircraft in
air commerce by prescribing regulations
for practices, methods, and procedures
the Administrator finds necessary for
safety in air commerce. This regulation
is within the scope of that authority
because it addresses an unsafe condition
that is likely to exist or develop on
products identified in this rulemaking
action.
This proposed AD is issued in
accordance with authority delegated by
the Executive Director, Aircraft
Certification Service, as authorized by
FAA Order 8000.51C. In accordance
with that order, issuance of ADs is
normally a function of the Compliance
and Airworthiness Division, but during
this transition period, the Executive
Director has delegated the authority to
issue ADs applicable to transport
category airplanes to the Director of the
System Oversight Division.
sradovich on DSK3GMQ082PROD with PROPOSALS
Regulatory Findings
We determined that this proposed AD
would not have federalism implications
under Executive Order 13132. This
proposed AD would not have a
substantial direct effect on the States, on
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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 this proposed regulation:
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.
The Proposed Amendment
Accordingly, under the authority
delegated to me by the Administrator,
the FAA proposes to amend 14 CFR part
39 as follows:
PART 39—AIRWORTHINESS
DIRECTIVES
1. The authority citation for part 39
continues to read as follows:
■
Authority: 49 U.S.C. 106(g), 40113, 44701.
§ 39.13
[Amended]
2. The FAA amends § 39.13 by adding
the following new airworthiness
directive (AD):
■
Bombardier, Inc.: Docket No. FAA–2018–
0710; Product Identifier 2018–NM–079–
AD.
(a) Comments Due Date
We must receive comments by October 1,
2018.
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40705
(b) Affected ADs
None.
(c) Applicability
This AD applies to Bombardier, Inc.,
Model BD–700–1A10 and BD–700–1A11
airplanes, certificated in any category, serial
numbers 9002 through 9638 inclusive and
9998.
(d) Subject
Air Transport Association (ATA) of
America Code 32, Landing gear.
(e) Reason
This AD was prompted by in-service
findings that a cotter pin at the main fitting
joint of the nose landing gear (NLG)
retraction actuator to the NLG strut showed
evidence of shearing after a NLG retractionextension cycling. We are issuing this AD to
address this condition which could lead to a
loss of hardware and result in an actuator
disconnect and the NLG failing to retract or
extend, or in an undamped freefall, which
could adversely affect the airplane’s
continued safe flight and landing.
(f) Compliance
Comply with this AD within the
compliance times specified, unless already
done.
(g) Maintenance or Inspection Program
Revision
Within 30 days after the effective date of
this AD: Revise the maintenance or
inspection program, as applicable, to
incorporate the information specified in
Airworthiness Limitation (AWL) Task 32–
33–01–111, ‘‘Restoration of the Nose Landing
Gear Shock-Strut Assembly to RetractionActuator Main-Fitting Joint,’’ as specified in
the applicable time limits/maintenance
checks (TLMC) manual identified in figure 1
to paragraph (g) of this AD, as applicable.
The initial compliance time for doing the
task is at the time specified in the applicable
TLMC manual listed in figure 1 to paragraph
(g) of this AD, or within 30 days after the
effective date of this AD, whichever occurs
later.
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(h) Inspection and Modification
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(1) Except for airplanes identified in
paragraph (h)(2) of this AD: Within 6 months
from the effective date of this AD, perform a
general visual inspection for damage of the
cotter pin retaining the bolt that secures the
NLG retraction actuator to the NLG strut, and
a general visual inspection of the
modification number shown on the
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identification plate for the NLG strut, and, if
applicable, mark the correct modification
number on the identification plate of the
NLG strut, in accordance with the applicable
Bombardier service information as shown in
figure 2 to paragraph (h) of this AD. If
damage to the cotter pin is present: Before
further flight, perform the modification of the
NLG attachment joint in accordance with the
Accomplishment Instructions of the
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applicable Bombardier service information as
shown in figure 2 to paragraph (h) of this AD.
(2) The actions specified in paragraph
(h)(1) of this AD are not required for
airplanes that do not have the NLG
configuration specified in Paragraph 1.A,
‘‘Effectivity’’ of the applicable Bombardier
service information as shown in figure 2 to
paragraph (h) of this AD.
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compliance (AMOC) in accordance with the
procedures specified in paragraph (l)(1) of
this AD.
BILLING CODE 4910–13–C
(i) Bombardier Service Bulletin 700–1A11–
32–022, dated May 13, 2015.
(ii) Bombardier Service Bulletin 700–
1A11–32–022, Revision 1, dated August 26,
2015.
(iii) Bombardier Service Bulletin 700–32–
035, dated May 13, 2015.
(iv) Bombardier Service Bulletin 700–32–
035, Revision 1, dated August 26, 2015.
(v) Bombardier Service Bulletin 700–32–
5011, dated May 13, 2015.
(vi) Bombardier Service Bulletin 700–32–
5011, Revision 1, dated August 26, 2015.
(vii) Bombardier Service Bulletin 700–32–
6011, dated May 13, 2015.
(viii) Bombardier Service Bulletin 700–32–
6011, Revision 1, dated August 26, 2015.
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(1) This paragraph provides credit for
actions required by paragraph (g) of this AD,
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(k) Service Information Prohibition
As of the effective date of this AD, no
person may incorporate Liebherr-Aerospace
Service Bulletin 1285A–32–07 at any
revision level on the NLG strut assemblies of
any Bombardier, Inc., Model BD–700–1A10
or BD–700–1A11 airplane.
(l) Other FAA AD Provisions
The following provisions also apply to this
AD:
(1) Alternative Methods of Compliance
(AMOCs): The Manager, New York 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
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(2) This paragraph provides credit for
actions required by paragraph (h)(1) of this
AD, if those actions were performed before
the effective date of this AD using the service
information specified in paragraphs (j)(2)(i)
through (j)(2)(viii) of this AD, provided that
it can be confirmed that at least 25 NLG
extension-retraction cycles had been
completed on the NLG at the time of
completion of the Accomplishment
Instructions of the applicable service
information specified in paragraphs (j)(2)(i)
through (j)(2)(viii) of this AD; and provided
neither the NLG nor the NLG retract actuator
has been replaced or modified since the
completion of the Accomplishment
Instructions of the applicable service
information specified in paragraphs (j)(2)(i)
through (j)(2)(viii) of this AD.
(j) Credit for Previous Actions
if those actions were performed before the
effective date of this AD using the service
information specified in figure 3 to paragraph
(j)(1) of this AD.
EP16AU18.001
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(i) No Alternative Actions or Intervals
After the maintenance or inspection
program has been revised as required by
paragraph (g) of this AD, no alternative
actions (e.g., inspections) or intervals, may be
used unless the actions or intervals are
approved as an alternative method of
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Federal Register / Vol. 83, No. 159 / Thursday, August 16, 2018 / Proposed Rules
appropriate. If sending information directly
to the manager of the certification office,
send it to ATTN: Program Manager,
Continuing Operational Safety, FAA, New
York ACO Branch, 1600 Stewart Avenue,
Suite 410, Westbury, NY 11590; telephone
516–228–7300; fax 516–794–5531. 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, New York ACO Branch,
FAA; or Transport Canada Civil Aviation
(TCCA); or Bombardier, Inc.’s TCCA Design
Approval Organization (DAO). If approved by
the DAO, the approval must include the
DAO-authorized signature.
(m) Related Information
(1) Refer to Mandatory Continuing
Airworthiness Information (MCAI) Canadian
AD CF–2018–05, dated January 23, 2018, 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–2018–0710.
(2) For more information about this AD,
contact Cesar Gomez, Aerospace Engineer,
Airframe and Mechanical Systems Section,
FAA, New York ACO Branch, 1600 Stewart
Avenue, Suite 410, Westbury, NY 11590;
telephone 516–228–7318; fax 516–794–5531;
email 9-avs-nyaco-cos@faa.gov.
(3) For service information identified in
ˆ
this AD, contact Bombardier, Inc., 400 Cote´
Vertu Road West, Dorval, Quebec H4S 1Y9,
Canada; telephone 514–855–5000; fax 514–
855–7401; email thd.crj@
aero.bombardier.com; internet https://
www.bombardier.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.
Issued in Des Moines, Washington, on
August 7, 2018.
Michael Kaszycki,
Acting Director, System Oversight Division,
Aircraft Certification Service.
[FR Doc. 2018–17622 Filed 8–15–18; 8:45 am]
BILLING CODE 4910–13–P
DEPARTMENT OF TRANSPORTATION
Federal Aviation Administration
sradovich on DSK3GMQ082PROD with PROPOSALS
14 CFR Part 39
[Docket No. FAA–2018–0758; Product
Identifier 2018–NM–093–AD]
RIN 2120–AA64
Airworthiness Directives; Airbus SAS
Airplanes
Federal Aviation
Administration (FAA), DOT.
AGENCY:
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Notice of proposed rulemaking
(NPRM).
ACTION:
We propose to adopt a new
airworthiness directive (AD) for certain
Airbus SAS Model A350–941 airplanes.
This proposed AD was prompted by a
review of the Airbus A350 structure
design principles database for type
definition that revealed that the
balancer fitting part, installed on the tail
cone, on a certain frame (FR) has several
corrosion-resistant stainless steel nuts
that do not meet the requirements for
protection against corrosion. This
proposed AD would require application
of a new additional overcoat sealant and
elastic varnish on the affected nuts and
fasteners. We are proposing this AD to
address the unsafe condition on these
products.
SUMMARY:
We must receive comments on
this proposed AD by October 1, 2018.
ADDRESSES: You may send comments,
using the procedures found in 14 CFR
11.43 and 11.45, by any of the following
methods:
• Federal eRulemaking Portal: Go to
https://www.regulations.gov. Follow the
instructions for submitting comments.
• Fax: 202–493–2251.
• Mail: U.S. Department of
Transportation, Docket Operations, M–
30, West Building Ground Floor, Room
W12–140, 1200 New Jersey Avenue SE,
Washington, DC 20590.
• Hand Delivery: Deliver to Mail
address above between 9 a.m. and 5
p.m., Monday through Friday, except
Federal holidays.
For service information identified in
this NPRM, contact Airbus SAS,
Airworthiness Office—EAL, Rond-Point
Emile Dewoitine No: 2, 31700 Blagnac
Cedex, France; telephone +33 5 61 93 36
96; fax +33 5 61 93 45 80; email
continued-airworthiness.a350@
airbus.com; internet https://
www.airbus.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.
DATES:
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–
0758; 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 NPRM, the
regulatory evaluation, any comments
received, and other information. The
street address for Docket Operations
(phone: 800–647–5527) is in the
PO 00000
Frm 00024
Fmt 4702
Sfmt 4702
ADDRESSES section. Comments will be
available in the AD docket shortly after
receipt.
FOR FURTHER INFORMATION CONTACT:
Kathleen Arrigotti, Aerospace Engineer,
International Section, Transport
Standards Branch, FAA, 2200 South
216th St., Des Moines, WA 98198;
telephone and fax 206–231–3218.
SUPPLEMENTARY INFORMATION:
Comments Invited
We invite you to send any written
relevant data, views, or arguments about
this proposal. Send your comments to
an address listed under the ADDRESSES
section. Include ‘‘Docket No. FAA–
2018–0758; Product Identifier 2018–
NM–093–AD’’ at the beginning of your
comments. We specifically invite
comments on the overall regulatory,
economic, environmental, and energy
aspects of this NPRM. We will consider
all comments received by the closing
date and may amend this NPRM
because of those comments.
We will post all comments we
receive, without change, to https://
www.regulations.gov, including any
personal information you provide. We
will also post a report summarizing each
substantive verbal contact we receive
about this NPRM.
Discussion
The European Aviation Safety Agency
(EASA), which is the Technical Agent
for the Member States of the European
Union, has issued EASA Airworthiness
Directive 2018–0123, dated June 4, 2018
(referred to after this as the Mandatory
Continuing Airworthiness Information,
or ‘‘the MCAI’’), to correct an unsafe
condition for certain Airbus SAS Model
A350–941 airplanes. The MCAI states:
Following a complete review of the Airbus
A350 structure design principles database for
type definition, it was revealed that the
balancer fitting part, installed on the tail
cone, lower section of Frame (FR) 103, has
several corrosion resistant stainless steel nuts
installed on elementary aluminium parts,
which does not meet the requirements for
protection against corrosion.
This condition, if not corrected, could
reduce the structural integrity of the
aeroplane.
To address this unsafe condition, Airbus
developed production mod 110319 to
improve protection against corrosion, and
issued the SB [Airbus Service Bulletin A350–
53–P024] to provide modification
instructions for in-service pre-mod
aeroplanes. At the same time the production
mod 110348 is equivalent to in-service
solution.
For the reasons described above, this
[EASA] AD requires a modification, adding
new additional overcoat sealant and elastic
varnish on the affected nuts and fastener
heads.
E:\FR\FM\16AUP1.SGM
16AUP1
Agencies
[Federal Register Volume 83, Number 159 (Thursday, August 16, 2018)]
[Proposed Rules]
[Pages 40703-40708]
From the Federal Register Online via the Government Publishing Office [www.gpo.gov]
[FR Doc No: 2018-17622]
=======================================================================
-----------------------------------------------------------------------
DEPARTMENT OF TRANSPORTATION
Federal Aviation Administration
14 CFR Part 39
[Docket No. FAA-2018-0710; Product Identifier 2018-NM-079-AD]
RIN 2120-AA64
Airworthiness Directives; Bombardier, Inc., Airplanes
AGENCY: Federal Aviation Administration (FAA), DOT.
ACTION: Notice of proposed rulemaking (NPRM).
-----------------------------------------------------------------------
SUMMARY: We propose to adopt a new airworthiness directive (AD) for
certain Bombardier, Inc., Model BD-700-1A10 and BD-700-1A11 airplanes.
This proposed AD was prompted by in-service findings that a cotter pin
at the main fitting joint of the nose landing gear (NLG) retraction
actuator to the NLG strut showed evidence of shearing after a NLG
retraction-extension cycling. This proposed AD would require revising
the maintenance or inspection program, as applicable, a general visual
inspection for damage of a certain cotter pin present on certain
configurations of the NLG strut assembly and for the modification
number shown on the identification plate for the NLG strut, and
modification of the NLG retraction actuator hardware on any damaged NLG
strut assembly. We are proposing this AD to address the unsafe
condition on these products.
DATES: We must receive comments on this proposed AD by October 1, 2018.
ADDRESSES: You may send comments, using the procedures found in 14 CFR
11.43 and 11.45, by any of the following methods:
Federal eRulemaking Portal: Go to https://www.regulations.gov. Follow the instructions for submitting comments.
Fax: 202-493-2251.
Mail: U.S. Department of Transportation, Docket
Operations, M-30, West Building Ground Floor, Room W12-140, 1200 New
Jersey Avenue SE, Washington, DC 20590.
Hand Delivery: Deliver to Mail address above between 9
a.m. and 5 p.m., Monday through Friday, except Federal holidays.
For service information identified in this NPRM, contact
Bombardier, Inc., 400 C[ocirc]te-Vertu Road West, Dorval, Qu[eacute]bec
H4S 1Y9, Canada; telephone 514-855-5000; fax 514-855-7401; email
[email protected]; internet https://www.bombardier.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.
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-
0710; 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 NPRM, the regulatory evaluation, any comments received, and other
information. The street address for Docket Operations (phone: 800-647-
5527) is in the ADDRESSES section. Comments will be available in the AD
docket shortly after receipt.
FOR FURTHER INFORMATION CONTACT: Cesar Gomez, Aerospace Engineer,
Airframe and Mechanical Systems Section, FAA, New York ACO Branch, 1600
Stewart Avenue, Suite 410, Westbury, NY 11590; telephone 516-228-7318;
fax 516-794-5531; email [email protected].
SUPPLEMENTARY INFORMATION:
Comments Invited
We invite you to send any written relevant data, views, or
arguments about this proposal. Send your comments to an address listed
under the ADDRESSES section. Include ``Docket No. FAA-2018-0710;
Product Identifier 2018-NM-079-AD'' at the beginning of your comments.
We specifically invite comments on the overall regulatory, economic,
environmental, and energy aspects of this NPRM. We will consider all
comments received by the closing date and may amend this NPRM because
of those comments.
We will post all comments we receive, without change, to https://www.regulations.gov, including any personal information you provide. We
will also post a report summarizing each substantive verbal contact we
receive about this NPRM.
Discussion
Transport Canada Civil Aviation (TCCA), which is the aviation
authority for Canada, has issued Canadian AD CF-2018-05, dated January
23, 2018 (referred to after this as the Mandatory Continuing
Airworthiness Information, or ``the MCAI''), to correct an unsafe
condition for certain Bombardier, Inc., Model BD-700-1A10 and BD-700-
1A11 airplanes. The MCAI states:
There have been in-service findings whereby the cotter pin at
the retraction actuator to nose landing gear (NLG) strut main
fitting was observed to be damaged after a NLG retraction-extension
cycling. This condition could lead to a loss of hardware and result
in an actuator disconnect resulting in a failure to retract or
extend, or in an undamped freefall of the NLG [which could adversely
affect the airplane's continued safe flight and landing].
This AD mandates a revision to the approved maintenance
schedule. This AD also mandates a visual inspection of the cotter
pin for certain configurations of NLG strut assembly, and if found
damaged, the incorporation of a modification which introduces a new
castellated nut, spacer, end plate and sleeve to the NLG retraction
actuator to main fitting joint.
[[Page 40704]]
The required actions also include a prohibition on accomplishing
Liebherr-Aerospace Service Bulletin 1285A-32-07 at any revision level
on the NLG strut assemblies of any Bombardier, Inc., Model BD-700-1A10
or BD-700-1A11 airplane in order to prevent the installation of the
affected configuration of the NLG strut assembly. 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-2018-0710.
Related Service Information Under 1 CFR Part 51
Bombardier has issued the following service information, which
describes procedures for a general visual inspection for damage of the
cotter pin retaining the bolt that secures the main fitting joint of
the NLG retraction actuator to the NLG strut and for the modification
number shown on the identification plate for the NLG strut, and
modifying the attachment hardware that secures the NLG retraction
actuator to the NLG strut. These documents are distinct since they
apply to different airplane models in different configurations.
Bombardier Service Bulletin 700-1A11-32-022, Revision 2,
dated November 6, 2017.
Bombardier Service Bulletin 700-32-035, Revision 2, dated
November 6, 2017.
Bombardier Service Bulletin 700-32-5011, Revision 2, dated
November 6, 2017.
Bombardier Service Bulletin 700-32-6011, Revision 2, dated
November 6, 2017.
Bombardier has issued the following service information, which
identifies airworthiness limitation tasks for restoration of the main
fitting joint of the NLG retraction actuator to the NLG strut. These
documents are distinct since they apply to different airplane models in
different configurations.
Task 32-33-01-111 of Bombardier Global 5000 BD-700 Time
Limits/Maintenance Checks, Revision 19, dated November 13, 2017, for
Bombardier Model BD-700-1A11 airplanes.
Task 32-33-01-111 of Bombardier Global 5000 GL 5000
Featuring Global Vision Flight Deck--Time Limits/Maintenance Checks,
Revision 9, dated November 13, 2017, for Bombardier Model BD-700-1A11
airplanes.
Task 32-33-01-111 of Bombardier Global Express BD-700 Time
Limits/Maintenance Checks, Revision 28, dated November 13, 2017, for
Bombardier Model BD-700-1A10 airplanes.
Task 32-33-01-111 of Bombardier Global Express XRS BD-700
Time Limits/Maintenance Checks, Revision 15, dated November 13, 2017,
for Bombardier Model BD-700-1A10 airplanes.
Task 32-33-01-111 of Bombardier Global 6000 GL 6000 Time
Limits/Maintenance Checks, Revision 9, dated November 13, 2017, for
Bombardier Model BD-700-1A10 airplanes.
This service information is reasonably available because the
interested parties have access to it through their normal course of
business or by the means identified in the ADDRESSES section.
FAA's Determination
This product has been approved by the aviation authority of another
country, and is approved for operation in the United States. Pursuant
to our bilateral agreement with the State of Design Authority, we have
been notified of the unsafe condition described in the MCAI and service
information referenced above. We are proposing this AD because we
evaluated all the relevant information and determined the unsafe
condition described previously is likely to exist or develop on other
products of the same type design.
This proposed AD requires revisions to certain operator maintenance
documents to include new actions (e.g., inspections). Compliance with
these actions is required by 14 CFR 91.403(c). For airplanes that have
been previously modified, altered, or repaired in the areas addressed
by this proposed AD, the operator may not be able to accomplish the
actions described in the revisions. In this situation, to comply with
14 CFR 91.403(c), the operator must request approval for an alternative
method of compliance according to paragraph (l)(1) of this proposed AD.
The request should include a description of changes to the required
actions that will ensure the continued damage tolerance of the affected
structure.
Proposed Requirements of This NPRM
This proposed AD would require accomplishing the actions specified
in the service information described previously.
Explanation of Service Bulletin Effectivity
Where Bombardier Service Bulletin 700-1A11-32-022 erroneously
specifies ``BD-700-1A10 aircraft'' in paragraph 1.A, ``Effectivity,''
the effectivity should be Bombardier, Inc., Model ``BD-700-1A11
airplanes'' instead.
Costs of Compliance
We estimate that this proposed AD affects 60 airplanes of U.S.
registry. We estimate the following costs to comply with this proposed
AD:
Estimated Costs
----------------------------------------------------------------------------------------------------------------
Cost per Cost on U.S.
Labor cost Parts cost product operators
----------------------------------------------------------------------------------------------------------------
4 work-hours x $85 per hour = $340........................... $0 $340 $20,400
----------------------------------------------------------------------------------------------------------------
We have determined that revising the maintenance or inspection
program takes an average of 90 work-hours per operator, although we
recognize that this number may vary from operator to operator. In the
past, we have estimated that this action takes 1 work-hour per
airplane. Since operators incorporate maintenance or inspection program
changes for their affected fleet(s), we have determined that a per-
operator estimate is more accurate than a per-airplane estimate.
Therefore, we estimate the total cost per operator to be $7,650 (90
work-hours x $85 per work-hour).
We estimate the following costs to do the necessary on-condition
action that would be required based on the results of any required
actions. We have no way of determining the number of aircraft that
might need this on-condition action:
Estimated Costs of On-Condition Action
------------------------------------------------------------------------
Cost per
Labor cost Parts cost product
------------------------------------------------------------------------
1 work-hour x $85 per hour = $85................ $10,487 $10,572
------------------------------------------------------------------------
According to the manufacturer, some or all of the costs of this
proposed AD may be covered under warranty, thereby reducing the cost
impact on affected
[[Page 40705]]
individuals. We do not control warranty coverage for affected
individuals. As a result, we have included all known costs in our cost
estimate.
Authority for This Rulemaking
Title 49 of the United States Code specifies the FAA's authority to
issue rules on aviation safety. Subtitle I, section 106, describes the
authority of the FAA Administrator. Subtitle VII: Aviation Programs,
describes in more detail the scope of the Agency's authority.
We are issuing this rulemaking under the authority described in
Subtitle VII, Part A, Subpart III, Section 44701: ``General
requirements.'' Under that section, Congress charges the FAA with
promoting safe flight of civil aircraft in air commerce by prescribing
regulations for practices, methods, and procedures the Administrator
finds necessary for safety in air commerce. This regulation is within
the scope of that authority because it addresses an unsafe condition
that is likely to exist or develop on products identified in this
rulemaking action.
This proposed AD is issued in accordance with authority delegated
by the Executive Director, Aircraft Certification Service, as
authorized by FAA Order 8000.51C. In accordance with that order,
issuance of ADs is normally a function of the Compliance and
Airworthiness Division, but during this transition period, the
Executive Director has delegated the authority to issue ADs applicable
to transport category airplanes to the Director of the System Oversight
Division.
Regulatory Findings
We determined that this proposed AD would not have federalism
implications under Executive Order 13132. This proposed AD would 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 this proposed
regulation:
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.
The Proposed Amendment
Accordingly, under the authority delegated to me by the
Administrator, the FAA proposes to amend 14 CFR part 39 as follows:
PART 39--AIRWORTHINESS DIRECTIVES
0
1. The authority citation for part 39 continues to read as follows:
Authority: 49 U.S.C. 106(g), 40113, 44701.
Sec. 39.13 [Amended]
0
2. The FAA amends Sec. 39.13 by adding the following new airworthiness
directive (AD):
Bombardier, Inc.: Docket No. FAA-2018-0710; Product Identifier 2018-
NM-079-AD.
(a) Comments Due Date
We must receive comments by October 1, 2018.
(b) Affected ADs
None.
(c) Applicability
This AD applies to Bombardier, Inc., Model BD-700-1A10 and BD-
700-1A11 airplanes, certificated in any category, serial numbers
9002 through 9638 inclusive and 9998.
(d) Subject
Air Transport Association (ATA) of America Code 32, Landing
gear.
(e) Reason
This AD was prompted by in-service findings that a cotter pin at
the main fitting joint of the nose landing gear (NLG) retraction
actuator to the NLG strut showed evidence of shearing after a NLG
retraction-extension cycling. We are issuing this AD to address this
condition which could lead to a loss of hardware and result in an
actuator disconnect and the NLG failing to retract or extend, or in
an undamped freefall, which could adversely affect the airplane's
continued safe flight and landing.
(f) Compliance
Comply with this AD within the compliance times specified,
unless already done.
(g) Maintenance or Inspection Program Revision
Within 30 days after the effective date of this AD: Revise the
maintenance or inspection program, as applicable, to incorporate the
information specified in Airworthiness Limitation (AWL) Task 32-33-
01-111, ``Restoration of the Nose Landing Gear Shock-Strut Assembly
to Retraction-Actuator Main-Fitting Joint,'' as specified in the
applicable time limits/maintenance checks (TLMC) manual identified
in figure 1 to paragraph (g) of this AD, as applicable. The initial
compliance time for doing the task is at the time specified in the
applicable TLMC manual listed in figure 1 to paragraph (g) of this
AD, or within 30 days after the effective date of this AD, whichever
occurs later.
BILLING CODE 4910-13-P
[[Page 40706]]
[GRAPHIC] [TIFF OMITTED] TP16AU18.000
(h) Inspection and Modification
(1) Except for airplanes identified in paragraph (h)(2) of this
AD: Within 6 months from the effective date of this AD, perform a
general visual inspection for damage of the cotter pin retaining the
bolt that secures the NLG retraction actuator to the NLG strut, and
a general visual inspection of the modification number shown on the
identification plate for the NLG strut, and, if applicable, mark the
correct modification number on the identification plate of the NLG
strut, in accordance with the applicable Bombardier service
information as shown in figure 2 to paragraph (h) of this AD. If
damage to the cotter pin is present: Before further flight, perform
the modification of the NLG attachment joint in accordance with the
Accomplishment Instructions of the applicable Bombardier service
information as shown in figure 2 to paragraph (h) of this AD.
(2) The actions specified in paragraph (h)(1) of this AD are not
required for airplanes that do not have the NLG configuration
specified in Paragraph 1.A, ``Effectivity'' of the applicable
Bombardier service information as shown in figure 2 to paragraph (h)
of this AD.
[[Page 40707]]
[GRAPHIC] [TIFF OMITTED] TP16AU18.001
(i) No Alternative Actions or Intervals
After the maintenance or inspection program has been revised as
required by paragraph (g) of this AD, no alternative actions (e.g.,
inspections) or intervals, may be used unless the actions or
intervals are approved as an alternative method of compliance (AMOC)
in accordance with the procedures specified in paragraph (l)(1) of
this AD.
(j) Credit for Previous Actions
(1) This paragraph provides credit for actions required by
paragraph (g) of this AD, if those actions were performed before the
effective date of this AD using the service information specified in
figure 3 to paragraph (j)(1) of this AD.
[GRAPHIC] [TIFF OMITTED] TP16AU18.002
BILLING CODE 4910-13-C
(2) This paragraph provides credit for actions required by
paragraph (h)(1) of this AD, if those actions were performed before
the effective date of this AD using the service information
specified in paragraphs (j)(2)(i) through (j)(2)(viii) of this AD,
provided that it can be confirmed that at least 25 NLG extension-
retraction cycles had been completed on the NLG at the time of
completion of the Accomplishment Instructions of the applicable
service information specified in paragraphs (j)(2)(i) through
(j)(2)(viii) of this AD; and provided neither the NLG nor the NLG
retract actuator has been replaced or modified since the completion
of the Accomplishment Instructions of the applicable service
information specified in paragraphs (j)(2)(i) through (j)(2)(viii)
of this AD.
(i) Bombardier Service Bulletin 700-1A11-32-022, dated May 13,
2015.
(ii) Bombardier Service Bulletin 700-1A11-32-022, Revision 1,
dated August 26, 2015.
(iii) Bombardier Service Bulletin 700-32-035, dated May 13,
2015.
(iv) Bombardier Service Bulletin 700-32-035, Revision 1, dated
August 26, 2015.
(v) Bombardier Service Bulletin 700-32-5011, dated May 13, 2015.
(vi) Bombardier Service Bulletin 700-32-5011, Revision 1, dated
August 26, 2015.
(vii) Bombardier Service Bulletin 700-32-6011, dated May 13,
2015.
(viii) Bombardier Service Bulletin 700-32-6011, Revision 1,
dated August 26, 2015.
(k) Service Information Prohibition
As of the effective date of this AD, no person may incorporate
Liebherr-Aerospace Service Bulletin 1285A-32-07 at any revision
level on the NLG strut assemblies of any Bombardier, Inc., Model BD-
700-1A10 or BD-700-1A11 airplane.
(l) Other FAA AD Provisions
The following provisions also apply to this AD:
(1) Alternative Methods of Compliance (AMOCs): The Manager, New
York 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
[[Page 40708]]
appropriate. If sending information directly to the manager of the
certification office, send it to ATTN: Program Manager, Continuing
Operational Safety, FAA, New York ACO Branch, 1600 Stewart Avenue,
Suite 410, Westbury, NY 11590; telephone 516-228-7300; fax 516-794-
5531. 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, New York ACO
Branch, FAA; or Transport Canada Civil Aviation (TCCA); or
Bombardier, Inc.'s TCCA Design Approval Organization (DAO). If
approved by the DAO, the approval must include the DAO-authorized
signature.
(m) Related Information
(1) Refer to Mandatory Continuing Airworthiness Information
(MCAI) Canadian AD CF-2018-05, dated January 23, 2018, 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-2018-0710.
(2) For more information about this AD, contact Cesar Gomez,
Aerospace Engineer, Airframe and Mechanical Systems Section, FAA,
New York ACO Branch, 1600 Stewart Avenue, Suite 410, Westbury, NY
11590; telephone 516-228-7318; fax 516-794-5531; email [email protected].
(3) For service information identified in this AD, contact
Bombardier, Inc., 400 C[ocirc]te-Vertu Road West, Dorval,
Qu[eacute]bec H4S 1Y9, Canada; telephone 514-855-5000; fax 514-855-
7401; email [email protected]; internet https://www.bombardier.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.
Issued in Des Moines, Washington, on August 7, 2018.
Michael Kaszycki,
Acting Director, System Oversight Division, Aircraft Certification
Service.
[FR Doc. 2018-17622 Filed 8-15-18; 8:45 am]
BILLING CODE 4910-13-P