Airworthiness Directives; Bombardier, Inc., Airplanes, 23351-23355 [2018-09732]
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Federal Register / Vol. 83, No. 98 / Monday, May 21, 2018 / Rules and Regulations
segment assembly and inspect the adapter,
washers, and TR driveshaft for damage.
Replace the adapter retention nut and apply
a torque of 30 to 50 inch-pounds (5.7 to 7.9
Nm). Replace any part with damage or repair
the part if the damage is within the
maximum repair damage limitations.
(3) Repeat the actions specified in
paragraph (e)(1) of this AD at intervals not to
exceed 330 hours TIS.
(f) Special Flight Permits
Special flight permits are prohibited.
(g) Alternative Methods of Compliance
(AMOCs)
(1) The Manager, Safety Management
Section, Rotorcraft Standards Branch, FAA,
may approve AMOCs for this AD. Send your
proposal to: David Hatfield, Aviation Safety
Engineer, Safety Management Section,
Rotorcraft Standards Branch, FAA, 10101
Hillwood Pkwy., Fort Worth, TX 76177;
telephone (817) 222–5110; email 9-ASWFTW-AMOC-Requests@faa.gov.
(2) For operations conducted under a 14
CFR part 119 operating certificate or under
14 CFR part 91, subpart K, we suggest that
you notify your principal inspector, or
lacking a principal inspector, the manager of
the local flight standards district office or
certificate holding district office, before
operating any aircraft complying with this
AD through an AMOC.
(h) Additional Information
The subject of this AD is addressed in
Transport Canada AD No. CF–2016–21, dated
July 7, 2016. You may view the Transport
Canada AD on the internet at https://
www.regulations.gov in Docket No. FAA–
2017–0667.
sradovich on DSK3GMQ082PROD with RULES
(i) Subject
Joint Aircraft Service Component (JASC)
Code: 6510 Tail Rotor Drive Shaft.
(j) Material Incorporated by Reference
(1) The Director of the Federal Register
approved the incorporation by reference 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) Bell Alert Service Bulletin 407–16–113,
dated February 12, 2016.
(ii) Reserved.
(3) For Bell service information identified
in this AD, Bell Helicopter Textron Canada
Limited, 12,800 Rue de l’Avenir, Mirabel,
Quebec J7J1R4; telephone (450) 437–2862 or
(800) 363–8023; fax (450) 433–0272; or at
https://www.bellcustomer.com/files/.
(4) You may view this service information
at FAA, Office of the Regional Counsel,
Southwest Region, 10101 Hillwood Pkwy,
Room 6N–321, Fort Worth, TX 76177. For
information on the availability of this
material at the FAA, call (817) 222–5110.
(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://
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Jkt 244001
www.archives.gov/federal-register/cfr/ibrlocations.html.
Issued in Fort Worth, Texas, on May 7,
2018.
Lance T. Gant,
Director, Compliance & Airworthiness
Division, Aircraft Certification Service.
[FR Doc. 2018–10491 Filed 5–18–18; 8:45 am]
BILLING CODE 4910–13–P
DEPARTMENT OF TRANSPORTATION
Federal Aviation Administration
14 CFR Part 39
[Docket No. FAA–2017–0907; Product
Identifier 2017–NM–069–AD; Amendment
39–19274; AD 2018–09–17]
RIN 2120–AA64
Airworthiness Directives; Bombardier,
Inc., Airplanes
Federal Aviation
Administration (FAA), Department of
Transportation (DOT).
ACTION: Final rule.
AGENCY:
We are adopting a new
airworthiness directive (AD) for certain
Bombardier, Inc., Model CL–600–1A11
(CL–600), CL–600–2A12 (CL–601
Variant), and CL–600–2B16 (CL–601–
3A, CL–601–3R, and CL–604 Variants)
airplanes. This AD was prompted by
reports of fractured rudder pedal tubes
on the pilot-side rudder bar assembly.
This AD requires repetitive inspections
of the rudder pedal tubes for cracking
and corrective actions if necessary.
Replacement of both pilot-side rudder
bar assemblies terminates the
inspections. We are issuing this AD to
address the unsafe condition on these
products.
DATES: This AD is effective June 25,
2018.
The Director of the Federal Register
approved the incorporation by reference
of certain publications listed in this AD
as of June 25, 2018.
ADDRESSES: For service information
identified in this final rule, contact
ˆ
Bombardier, Inc., 400 Cote-Vertu Road
´
West, Dorval, Quebec H4S 1Y9, Canada;
Widebody Customer Response Center
North America toll-free telephone 1–
866–538–1247 or direct-dial telephone
1–514–855–2999; fax 514–855–7401;
email ac.yul@aero.bombardier.com;
internet https://www.bombardier.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
SUMMARY:
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23351
on the internet at https://
www.regulations.gov by searching for
and locating Docket No. FAA–2017–
0907.
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–2017–
0907; or in person at the Docket
Management Facility between 9 a.m.
and 5 p.m., Monday through Friday,
except Federal holidays. The AD docket
contains this AD, the regulatory
evaluation, any comments received, and
other information. The street address for
the Docket Office (telephone 800–647–
5527) is Docket Management Facility,
U.S. Department of Transportation,
Docket Operations, M–30, West
Building Ground Floor, Room W12–140,
1200 New Jersey Avenue SE,
Washington, DC 20590.
FOR FURTHER INFORMATION CONTACT: Aziz
Ahmed, Aerospace Engineer, Airframe
and Mechanical Systems Section, FAA,
New York ACO Branch, 1600 Stewart
Avenue, Suite 410, Westbury, NY
11590; telephone 516–228–7329; fax
516–794–5531.
SUPPLEMENTARY INFORMATION:
Discussion
We issued a notice of proposed
rulemaking (NPRM) to amend 14 CFR
part 39 by adding an AD that would
apply to certain Bombardier, Inc., Model
CL–600–1A11 (CL–600), CL–600–2A12
(CL–601 Variant), and CL–600–2B16
(CL–601–3A, CL–601–3R, and CL–604
Variants) airplanes. The NPRM
published in the Federal Register on
October 19, 2017 (82 FR 48668) (‘‘the
NPRM’’). The NPRM was prompted by
reports of fractured rudder pedal tubes
on the pilot-side rudder bar assembly.
The NPRM proposed to require
repetitive inspections of the rudder
pedal tubes for cracking and corrective
actions if necessary. Replacement of
both pilot-side rudder bar assemblies
terminates the inspections. We are
issuing this AD to address cracking of
the pilot-side rudder pedal tubes. Loss
of pilot rudder pedal input during flight
could result in reduced yaw
controllability of the airplane. Loss of
pilot rudder pedal input during takeoff
or landing could lead to a runway
excursion.
Transport Canada Civil Aviation
(TCCA), which is the aviation authority
for Canada, has issued Canadian
Airworthiness Directive CF–2017–09,
dated February 22, 2017 (referred to
after this as the Mandatory Continuing
Airworthiness Information, or ‘‘the
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MCAI’’), to correct an unsafe condition
for certain Bombardier, Inc., Model CL–
600–1A11 (CL–600), CL–600–2A12 (CL–
601 Variant), and CL–600–2B16 (CL–
601–3A, CL–601–3R, and CL–604
Variants) airplanes. The MCAI states:
There have been two in-service reports of
fractured rudder pedal tubes installed on the
pilot-side rudder bar assembly on CL–600–
2B19 aeroplanes. Laboratory examination of
the fractured rudder pedal tubes found that
in both cases, the fatigue cracks initiated at
the aft taper pin holes where the connecting
rod fitting is attached. Fatigue testing of the
rudder pedal tubes confirmed that the fatigue
cracking is due to loads induced during
parking brake application. Therefore, only
the rudder pedal tubes on the pilot’s side are
vulnerable to fatigue cracking as the parking
brake is primarily applied by the pilot.
Loss of pilot rudder pedal input during
flight would result in reduced yaw
controllability of the aeroplane. Loss of pilot
rudder pedal input during takeoff or landing
may lead to a runway excursion.
This [Canadian] AD mandates initial and
repetitive [detailed visual or eddy current]
inspections [for cracking] of both pilot-side
rudder pedal tubes, part number (P/N) 600–
90204–3 until the terminating action in Part
III of this [Canadian] AD is accomplished
[i.e., replacement of both pilot-side rudder
bar assemblies].
Corrective actions include
replacement of both pilot-side rudder
bar assemblies and repair. You may
examine the MCAI in the AD docket on
the internet at https://
www.regulations.gov by searching for
and locating Docket No. FAA–2017–
0907.
Comments
We gave the public the opportunity to
participate in developing this AD. The
following presents the comments
received on the NPRM and the FAA’s
response to each comment.
sradovich on DSK3GMQ082PROD with RULES
Requests To Correct Errors in Certain
Service Information Citations
Bombardier and NetJets both
requested that typographical errors in
certain service bulletin citations be
corrected. Bombardier stated that in the
NPRM, Bombardier ‘‘Service Bulletin
605–27–008’’ should be cited as
Bombardier ‘‘Service Bulletin 650–27–
008.’’ NetJets stated that Bombardier
‘‘Service Bulletin 605–27–002’’ should
be cited as Bombardier ‘‘Service
Bulletin 650–27–002.’’
We partially agree with the
commenters’ requests. We agree with
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NetJets’ request to correct the
typographical error in the preamble and
paragraph (g)(6) of this AD by removing
the incorrect citation and including the
correct citation, which is Bombardier
Service Bulletin 650–27–002, dated June
30, 2016, including Appendix A,
Revision 01, dated March 31, 2016.
We do not agree with Bombardier’s
request because a typographical error
does not exist in our citation of
Bombardier Service Bulletin 605–27–
008, dated March 31, 2016, including
Appendix A, Revision 01, dated March
31, 2016. We contacted the commenter,
and the company representative agreed
that there is not a typographical error.
Therefore, no change was made to this
AD in this regard.
Request To Change the Order of Certain
Service Information in the Related
Service Information Under 1 CFR Part
51 Paragraph
During a phone conversation between
Bombardier and the FAA that occurred
during the NPRM comment period,
Bombardier requested that the order of
certain service information in ‘‘Related
Service Information under 1 CFR part
51’’ be rearranged. Specifically, the
commenter requested that Service
Bulletin 605–27–008, dated March 31,
2016, including Appendix A, Revision
01, dated March 31, 2016, be listed
above Service Bulletin 650–27–002,
dated June 30, 2016, including
Appendix A, Revision 01, dated March
31, 2016. The commenter stated that
chronologically Bombardier issued
Service Bulletin 605–27–008, dated
March 31, 2016, including Appendix A,
Revision 01, dated March 31, 2016,
before issuing Service Bulletin 650–27–
002, dated June 30, 2016, including
Appendix A, Revision 01, dated March
31, 2016.
We agree to clarify. While we
recognize the benefit of listing service
information in chronological order
based on publication dates, we are
required by the Office of Federal
Register (OFR) to list service
information within the incorporated by
reference (IBR) paragraph of the AD
regulatory text (i.e. paragraph (n) of this
AD) according to the document name.
For consistency, the IBR material is
listed in the same alphanumerical
sequence within the 1 CFR part 51
paragraph of the AD preamble text. In
this case, as stated previously, we have
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changed a certain citation, and that
change places the service information in
the alphanumeric order shown within
this AD, which also addresses the
commenter’s request.
Conclusion
We reviewed the relevant data,
considered the comments received, and
determined that air safety and the
public interest require adopting this AD
with the changes described previously
and minor editorial changes. We have
determined that these minor changes:
• Are consistent with the intent that
was proposed in the NPRM for
correcting the unsafe condition; and
• Do not add any additional burden
upon the public than was already
proposed in the NPRM.
We also determined that these
changes will not increase the economic
burden on any operator or increase the
scope of this AD.
Related Service Information Under 1
CFR Part 51
Bombardier has issued the following
service information. The service
information describes procedures for
repetitive inspections of the rudder
pedal tubes for cracking, replacement of
both pilot-side rudder bar assemblies,
and repair. These documents are
distinct since they apply to different
airplane models.
• Service Bulletin 600–0770,
including Appendix A, both Revision
01, both dated March 31, 2016.
• Service Bulletin 601–0643,
including Appendix A, both Revision
01, both dated March 31, 2016.
• Service Bulletin 604–27–037,
including Appendix A, Revision 01,
both dated March 31, 2016.
• Service Bulletin 605–27–008,
including Appendix A, Revision 01,
both dated March 31, 2016.
• Service Bulletin 650–27–002, dated
June 30, 2016, including Appendix A,
Revision 01, dated March 31, 2016.
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 141
airplanes of U.S. registry.
We estimate the following costs to
comply with this AD:
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ESTIMATED COSTS
Action
Labor cost
Inspections .............................
10 work-hours × $85 per hour
= $850 per inspection cycle.
We estimate the following costs to do
any necessary replacements that would
Parts cost
Cost on U.S.
operators
Cost per product
$0
$850 per inspection cycle ......
be required based on the results of the
proposed inspection. We have no way of
$119,850 per inspection
cycle.
determining the number of airplanes
that might need these replacements:
ON-CONDITION COSTS
Action
Labor cost
Replacement ....................................
2 work-hours × $85 per hour = $170 ........................................................
We have received no definitive data
that will enable us to provide cost
estimates for any on-condition repairs
specified in this AD. We have no way
of determining the number of aircraft
that might need this repair.
sradovich on DSK3GMQ082PROD with RULES
Authority for This Rulemaking
Title 49 of the United States Code
specifies the FAA’s authority to issue
rules on aviation safety. Subtitle I,
section 106, describes the authority of
the FAA Administrator. Subtitle VII:
Aviation Programs, describes in more
detail the scope of the Agency’s
authority.
We are issuing this rulemaking under
the authority described in Subtitle VII,
Part A, Subpart III, Section 44701:
‘‘General requirements.’’ Under that
section, Congress charges the FAA with
promoting safe flight of civil aircraft in
air commerce by prescribing regulations
for practices, methods, and procedures
the Administrator finds necessary for
safety in air commerce. This regulation
is within the scope of that authority
because it addresses an unsafe condition
that is likely to exist or develop on
products identified in this rulemaking
action.
This AD is issued in accordance with
authority delegated by the Executive
Director, Aircraft Certification Service,
as authorized by FAA Order 8000.51C.
In accordance with that order, issuance
of ADs is normally a function of the
Compliance and Airworthiness
Division, but during this transition
period, the Executive Director has
delegated the authority to issue ADs
applicable to transport category
airplanes to the Director of the System
Oversight Division.
Regulatory Findings
We determined that this AD will not
have federalism implications under
Executive Order 13132. This AD will
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Parts cost
Cost per
product
$8,564
$8,734
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.
(b) Affected ADs
None.
List of Subjects in 14 CFR Part 39
(e) Reason
This AD was prompted by reports of
fractured rudder pedal tubes on the pilot-side
rudder bar assembly. We are issuing this AD
to address cracking of the pilot-side rudder
pedal tubes. Loss of pilot rudder pedal input
during flight could result in reduced yaw
controllability of the airplane. Loss of pilot
rudder pedal input during takeoff or landing
could lead to a runway excursion.
Air transportation, Aircraft, Aviation
safety, Incorporation by reference,
Safety.
Adoption of the Amendment
Accordingly, under the authority
delegated to me by the Administrator,
the FAA amends 14 CFR part 39 as
follows:
PART 39—AIRWORTHINESS
DIRECTIVES
1. The authority citation for part 39
continues to read as follows:
■
Authority: 49 U.S.C. 106(g), 40113, 44701.
§ 39.13
[Amended]
2. The FAA amends § 39.13 by adding
the following new airworthiness
directive (AD):
■
2018–09–17 Bombardier, Inc.: Amendment
39–19274; Docket No. FAA–2017–0907;
Product Identifier 2017–NM–069–AD.
(a) Effective Date
This AD is effective June 25, 2018.
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(c) Applicability
This AD applies to the Bombardier, Inc.,
airplanes identified in paragraphs (c)(1)
through (c)(3) of this AD, certificated in any
category.
(1) Model CL–600–1A11 (CL–600)
airplanes, serial numbers (S/Ns) 1004
through 1085 inclusive.
(2) Model CL–600–2A12 (CL–601 Variant)
airplanes, S/Ns 3001 through 3066 inclusive.
(3) Model CL–600–2B16 (CL–601–3A, CL–
601–3R, and CL–604 Variants) airplanes,
S/Ns 5001 through 5194 inclusive, S/Ns 5301
through 5665 inclusive, S/Ns 5701 through
5988 inclusive, and S/Ns 6050 through 6099
inclusive.
(d) Subject
Air Transport Association (ATA) of
America Code 27, Flight Controls.
(f) Compliance
Comply with this AD within the
compliance times specified, unless already
done.
(g) Repetitive Inspections and Part Marking
At the applicable time specified in figure
1 to paragraph (g) of this AD, do a detailed
or eddy current inspection of both pilot-side
rudder pedal tubes for cracking, in
accordance with Part A of the
Accomplishment Instructions of the
applicable service information identified in
paragraphs (g)(1) through (g)(6) of this AD. If
no cracking is found, before further flight,
mark the part in accordance with Part A of
the Accomplishment Instructions of the
applicable service information identified in
paragraphs (g)(1) through (g)(6) of this AD.
Repeat the detailed or eddy current
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inspection thereafter at intervals not to
exceed 600 flight cycles if a detailed
inspection was performed, or 1,000 flight
cycles if an eddy current inspection was
performed. Repeat the inspection until the
terminating action specified in paragraph (i)
of this AD is accomplished.
(1) For Model CL–600–1A11 (CL–600)
airplanes, S/Ns 1004 through 1085 inclusive:
Bombardier Service Bulletin 600–0770,
including Appendix A, both Revision 01,
both dated March 31, 2016.
(2) For Model CL–600–2A12 (CL–601
Variant) airplanes, S/Ns 3001 through 3066
inclusive: Bombardier Service Bulletin 601–
0643, including Appendix A, both Revision
01, both dated March 31, 2016.
(3) For Model CL–600–2B16 (CL–601–3A,
CL–601–3R, and CL–604 Variants) airplanes,
S/Ns 5001 through 5194 inclusive:
Bombardier Service Bulletin 601–0643,
including Appendix A, both Revision 01,
both dated March 31, 2016.
(4) For Model CL–600–2B16 (CL–601–3A,
CL–601–3R, and CL–604 Variants) airplanes,
S/Ns 5301 through 5665 inclusive:
Bombardier Service Bulletin 604–27–037,
including Appendix A, Revision 01, both
dated March 31, 2016.
(5) For Model CL–600–2B16 (CL–601–3A,
CL–601–3R, and CL–604 Variants) airplanes,
S/Ns 5701 through 5988 inclusive:
Bombardier Service Bulletin 605–27–008,
including Appendix A, Revision 01, both
dated March 31, 2016.
(6) For Model CL–600–2B16 (CL–601–3A,
CL–601–3R, and CL–604 Variants) airplanes,
S/Ns 6050 through 6099 inclusive:
Bombardier Service Bulletin 650–27–002,
dated June 30, 2016, including Appendix A,
Revision 01, dated March 31, 2016.
(h) Corrective Actions
0643, dated August 31, 2015; is not a
terminating action for the inspections
required by paragraph (g) of this AD.
(l) Special Flight Permits
(i) Optional Terminating Action
Replacement of both pilot-side rudder bar
assemblies in accordance with Part B of the
Accomplishment Instructions of the
applicable service information identified in
paragraphs (g)(1) through (g)(6) of this AD
terminates the inspections required by
paragraph (g) of this AD.
(j) Replacement—No Terminating Action
Replacement of both pilot-side rudder bar
assemblies using Part B of the
Accomplishment Instructions of Bombardier
Service Bulletin 600–0770, dated August 31,
2015; or Bombardier Service Bulletin 601–
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(k) 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
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 TCCA; or Bombardier, Inc.’s TCCA
DAO. If approved by the DAO, the approval
must include the DAO-authorized signature.
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Special flight permits, as described in
Section 21.197 and Section 21.199 of the
Federal Aviation Regulations (14 CFR 21.197
and 21.199), are not allowed if any cracking
is found during any inspection required by
paragraph (g) of this AD.
(m) Related Information
(1) Refer to Mandatory Continuing
Airworthiness Information (MCAI) Canadian
Airworthiness Directive CF–2017–09, dated
February 22, 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–2017–0907.
(2) For more information about this AD,
contact Aziz Ahmed, Aerospace Engineer,
Airframe and Mechanical Systems Section,
FAA, New York ACO Branch, 1600 Stewart
Avenue, Suite 410, Westbury, NY 11590;
telephone 516–228–7329; fax 516–794–5531.
(n) Material Incorporated by Reference
(1) The Director of the Federal Register
approved the incorporation by reference
(IBR) of the service information listed in this
paragraph under 5 U.S.C. 552(a) and 1 CFR
part 51.
(2) You must use this service information
as applicable to do the actions required by
this AD, unless this AD specifies otherwise.
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sradovich on DSK3GMQ082PROD with RULES
(1) If any cracking is found around the aft
tapered holes during any inspection required
by paragraph (g) of this AD, before further
flight, replace both pilot-side rudder bar
assemblies, in accordance with Part B of the
Accomplishment Instructions of the
applicable service information identified in
paragraphs (g)(1) through (g)(6) of this AD.
(2) If any other damage (e.g., corrosion) is
found, during any inspection required by
paragraph (g) of this AD, before further flight,
repair 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 DAOauthorized signature.
Federal Register / Vol. 83, No. 98 / Monday, May 21, 2018 / Rules and Regulations
(i) Bombardier Service Bulletin 600–0770,
including Appendix A, both Revision 01,
both dated March 31, 2016.
(ii) Bombardier Service Bulletin 601–0643,
including Appendix A, both Revision 01,
both dated March 31, 2016.
(iii) Bombardier Service Bulletin 604–27–
037, including Appendix A, Revision 01,
both dated March 31, 2016.
(iv) Bombardier Service Bulletin 605–27–
008, including Appendix A, Revision 01,
both dated March 31, 2016.
(v) Bombardier Service Bulletin 650–27–
002, dated June 30, 2016, including
Appendix A, Revision 01, dated March 31,
2016.
(3) For service information identified in
ˆ
this AD, contact Bombardier, Inc., 400 Cote
´
Vertu Road West, Dorval, Quebec H4S 1Y9,
Canada; Widebody Customer Response
Center North America toll-free telephone
1–866–538–1247 or direct-dial telephone
1–514–855–2999; fax 514–855–7401; email
ac.yul@aero.bombardier.com; internet https://
www.bombardier.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
April 27, 2018.
Michael Kaszycki,
Acting Director, System Oversight Division,
Aircraft Certification Service.
[FR Doc. 2018–09732 Filed 5–18–18; 8:45 am]
BILLING CODE 4910–13–P
DEPARTMENT OF TRANSPORTATION
Federal Aviation Administration
14 CFR Part 39
[Docket No. FAA–2017–0874; Product
Identifier 2015–SW–082–AD; Amendment
39–19282; AD 2018–10–07]
RIN 2120–AA64
Airworthiness Directives; Sikorsky
Aircraft Corporation
Federal Aviation
Administration (FAA), DOT.
ACTION: Final rule.
sradovich on DSK3GMQ082PROD with RULES
AGENCY:
We are adopting a new
airworthiness directive (AD) for
Sikorsky Aircraft Corporation (Sikorsky)
Model S–76C helicopters. This AD
requires inspecting the engine collective
position transducer (CPT). This AD was
prompted by reports of wear of the CPT
that has resulted in several One Engine
SUMMARY:
VerDate Sep<11>2014
15:54 May 18, 2018
Jkt 244001
Inoperative (OEI) incidents. The actions
of this AD are intended to detect and
prevent an unsafe condition on these
products.
DATES: This AD is effective June 25,
2018.
The Director of the Federal Register
approved the incorporation by reference
of certain documents listed in this AD
as of June 25, 2018.
ADDRESSES: For service information
identified in this final rule, contact
Sikorsky Aircraft Corporation, Customer
Service Engineering, 124 Quarry Road,
Trumbull, CT 06611; telephone 1–800–
Winged–S or 203–416–4299; email wcs_
cust_service_eng.gr-sik@lmco.com. You
may review a copy of the referenced
service information at the FAA, Office
of the Regional Counsel, Southwest
Region, 10101 Hillwood Pkwy, Room
6N–321, Fort Worth, TX 76177. It is also
available on the internet at https://
www.regulations.gov by searching for
and locating Docket No. FAA–2017–
0874.
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–2017–
0874; 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 AD, any
incorporated-by-reference service
information, the economic evaluation,
any comments received, and other
information. The street 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: Nick
Rediess, Aviation Safety Engineer,
Boston ACO Branch, Compliance &
Airworthiness Division, 1200 District
Avenue, Burlington, MA 01803;
telephone (781) 238–7159; email
nicholas.rediess@faa.gov.
SUPPLEMENTARY INFORMATION:
Discussion
On September 14, 2017, at 82 FR
43195, the Federal Register published
our notice of proposed rulemaking
(NPRM), which proposed to amend 14
CFR part 39 by adding an AD that
would apply to Sikorsky Model S–76C
helicopters with a Turbomeca, S.A.,
Arriel 2S1 or Arriel 2S2 engine with an
engine CPT part number (P/N) 76900–
01821–104 installed. The NPRM was
prompted by 20 reports of OEI incidents
resulting from wear of a CPT. One of
PO 00000
Frm 00007
Fmt 4700
Sfmt 4700
23355
these incidents resulted in a rejected
takeoff to an unprepared site.
The NPRM proposed to require initial
and recurring inspections of each CPT
by measuring resistance, linearity
resistance movement, and differential
voltage, and depending on the outcome
of the inspections, replacing the CPT.
The proposed requirements were
intended to detect wear of a CPT prior
to it causing an OEI condition and
possible emergency landing.
Comments
After our NPRM was published, we
received comments from Sikorsky.
Request To Include an Additional Part
to the AD
Sikorsky requested the AD also apply
to engine CPT P/N 76900–01821–105. In
support of this request, Sikorsky stated
that engine CPT P/N 76900–01821–105
is a new replacement for engine CPT P/
N 76900–01821–104, which does not
differ substantially from engine CPT P/
N 76900–01821–104 and therefore
should be subject to the periodic
inspections.
We partially agree. While engine CPT
P/N 76900–01821–105 may be subject to
the same unsafe condition because of
design similarity, adding this part
would increase the scope of the AD.
Therefore, we plan to publish another
NPRM for P/N 76900–01821–105 to give
the public an opportunity to comment
on those requirements.
Request To Remove a Test Box From
the AD
Sikorsky requested we remove Test
Box P/N 76700–40009–042 and only
allow the use of Test Box P/N 76700–
40009–043 to comply with the AD. In
support of this request, Sikorsky stated
it considers Test Box P/N 76700–40009–
042 obsolete because Test Box P/N
76700–40009–043 is easier to use and
provides less subjective results.
We disagree. The proposed AD
provided procedures for both test boxes
for the repetitive inspections. While
Test Box P/N 76700–40009–043 may be
more efficient, the use of Test Box P/N
76700–40009–042 also addresses the
unsafe condition. We do not find
justification for requiring operators who
have Test Box P/N 76700–40009–042 to
upgrade or replace their test box.
However, we have revised the initial
inspection requirements of the AD to
allow the use of Test Box P/N 76700–
40009–043 as an option. We have also
revised the repetitive inspection
procedures to allow the use of updated
testing procedures for Test Box P/N
76700–40009–043, which had not been
E:\FR\FM\21MYR1.SGM
21MYR1
]]>Agencies
[Federal Register Volume 83, Number 98 (Monday, May 21, 2018)]
[Rules and Regulations]
[Pages 23351-23355]
From the Federal Register Online via the Government Publishing Office [www.gpo.gov]
[FR Doc No: 2018-09732]
-----------------------------------------------------------------------
DEPARTMENT OF TRANSPORTATION
Federal Aviation Administration
14 CFR Part 39
[Docket No. FAA-2017-0907; Product Identifier 2017-NM-069-AD; Amendment
39-19274; AD 2018-09-17]
RIN 2120-AA64
Airworthiness Directives; Bombardier, Inc., Airplanes
AGENCY: Federal Aviation Administration (FAA), Department of
Transportation (DOT).
ACTION: Final rule.
-----------------------------------------------------------------------
SUMMARY: We are adopting a new airworthiness directive (AD) for certain
Bombardier, Inc., Model CL-600-1A11 (CL-600), CL-600-2A12 (CL-601
Variant), and CL-600-2B16 (CL-601-3A, CL-601-3R, and CL-604 Variants)
airplanes. This AD was prompted by reports of fractured rudder pedal
tubes on the pilot-side rudder bar assembly. This AD requires
repetitive inspections of the rudder pedal tubes for cracking and
corrective actions if necessary. Replacement of both pilot-side rudder
bar assemblies terminates the inspections. We are issuing this AD to
address the unsafe condition on these products.
DATES: This AD is effective June 25, 2018.
The Director of the Federal Register approved the incorporation by
reference of certain publications listed in this AD as of June 25,
2018.
ADDRESSES: For service information identified in this final rule,
contact Bombardier, Inc., 400 C[ocirc]te-Vertu Road West, Dorval,
Qu[eacute]bec H4S 1Y9, Canada; Widebody Customer Response Center North
America toll-free telephone 1-866-538-1247 or direct-dial telephone 1-
514-855-2999; fax 514-855-7401; email [email protected];
internet https://www.bombardier.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-2017-0907.
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-2017-
0907; or in person at the Docket Management Facility between 9 a.m. and
5 p.m., Monday through Friday, except Federal holidays. The AD docket
contains this AD, the regulatory evaluation, any comments received, and
other information. The street address for the Docket Office (telephone
800-647-5527) is Docket Management Facility, U.S. Department of
Transportation, Docket Operations, M-30, West Building Ground Floor,
Room W12-140, 1200 New Jersey Avenue SE, Washington, DC 20590.
FOR FURTHER INFORMATION CONTACT: Aziz Ahmed, Aerospace Engineer,
Airframe and Mechanical Systems Section, FAA, New York ACO Branch, 1600
Stewart Avenue, Suite 410, Westbury, NY 11590; telephone 516-228-7329;
fax 516-794-5531.
SUPPLEMENTARY INFORMATION:
Discussion
We issued a notice of proposed rulemaking (NPRM) to amend 14 CFR
part 39 by adding an AD that would apply to certain Bombardier, Inc.,
Model CL-600-1A11 (CL-600), CL-600-2A12 (CL-601 Variant), and CL-600-
2B16 (CL-601-3A, CL-601-3R, and CL-604 Variants) airplanes. The NPRM
published in the Federal Register on October 19, 2017 (82 FR 48668)
(``the NPRM''). The NPRM was prompted by reports of fractured rudder
pedal tubes on the pilot-side rudder bar assembly. The NPRM proposed to
require repetitive inspections of the rudder pedal tubes for cracking
and corrective actions if necessary. Replacement of both pilot-side
rudder bar assemblies terminates the inspections. We are issuing this
AD to address cracking of the pilot-side rudder pedal tubes. Loss of
pilot rudder pedal input during flight could result in reduced yaw
controllability of the airplane. Loss of pilot rudder pedal input
during takeoff or landing could lead to a runway excursion.
Transport Canada Civil Aviation (TCCA), which is the aviation
authority for Canada, has issued Canadian Airworthiness Directive CF-
2017-09, dated February 22, 2017 (referred to after this as the
Mandatory Continuing Airworthiness Information, or ``the
[[Page 23352]]
MCAI''), to correct an unsafe condition for certain Bombardier, Inc.,
Model CL-600-1A11 (CL-600), CL-600-2A12 (CL-601 Variant), and CL-600-
2B16 (CL-601-3A, CL-601-3R, and CL-604 Variants) airplanes. The MCAI
states:
There have been two in-service reports of fractured rudder pedal
tubes installed on the pilot-side rudder bar assembly on CL-600-2B19
aeroplanes. Laboratory examination of the fractured rudder pedal
tubes found that in both cases, the fatigue cracks initiated at the
aft taper pin holes where the connecting rod fitting is attached.
Fatigue testing of the rudder pedal tubes confirmed that the fatigue
cracking is due to loads induced during parking brake application.
Therefore, only the rudder pedal tubes on the pilot's side are
vulnerable to fatigue cracking as the parking brake is primarily
applied by the pilot.
Loss of pilot rudder pedal input during flight would result in
reduced yaw controllability of the aeroplane. Loss of pilot rudder
pedal input during takeoff or landing may lead to a runway
excursion.
This [Canadian] AD mandates initial and repetitive [detailed
visual or eddy current] inspections [for cracking] of both pilot-
side rudder pedal tubes, part number (P/N) 600-90204-3 until the
terminating action in Part III of this [Canadian] AD is accomplished
[i.e., replacement of both pilot-side rudder bar assemblies].
Corrective actions include replacement of both pilot-side rudder
bar assemblies and repair. You may examine the MCAI in the AD docket on
the internet at https://www.regulations.gov by searching for and
locating Docket No. FAA-2017-0907.
Comments
We gave the public the opportunity to participate in developing
this AD. The following presents the comments received on the NPRM and
the FAA's response to each comment.
Requests To Correct Errors in Certain Service Information Citations
Bombardier and NetJets both requested that typographical errors in
certain service bulletin citations be corrected. Bombardier stated that
in the NPRM, Bombardier ``Service Bulletin 605-27-008'' should be cited
as Bombardier ``Service Bulletin 650-27-008.'' NetJets stated that
Bombardier ``Service Bulletin 605-27-002'' should be cited as
Bombardier ``Service Bulletin 650-27-002.''
We partially agree with the commenters' requests. We agree with
NetJets' request to correct the typographical error in the preamble and
paragraph (g)(6) of this AD by removing the incorrect citation and
including the correct citation, which is Bombardier Service Bulletin
650-27-002, dated June 30, 2016, including Appendix A, Revision 01,
dated March 31, 2016.
We do not agree with Bombardier's request because a typographical
error does not exist in our citation of Bombardier Service Bulletin
605-27-008, dated March 31, 2016, including Appendix A, Revision 01,
dated March 31, 2016. We contacted the commenter, and the company
representative agreed that there is not a typographical error.
Therefore, no change was made to this AD in this regard.
Request To Change the Order of Certain Service Information in the
Related Service Information Under 1 CFR Part 51 Paragraph
During a phone conversation between Bombardier and the FAA that
occurred during the NPRM comment period, Bombardier requested that the
order of certain service information in ``Related Service Information
under 1 CFR part 51'' be rearranged. Specifically, the commenter
requested that Service Bulletin 605-27-008, dated March 31, 2016,
including Appendix A, Revision 01, dated March 31, 2016, be listed
above Service Bulletin 650-27-002, dated June 30, 2016, including
Appendix A, Revision 01, dated March 31, 2016. The commenter stated
that chronologically Bombardier issued Service Bulletin 605-27-008,
dated March 31, 2016, including Appendix A, Revision 01, dated March
31, 2016, before issuing Service Bulletin 650-27-002, dated June 30,
2016, including Appendix A, Revision 01, dated March 31, 2016.
We agree to clarify. While we recognize the benefit of listing
service information in chronological order based on publication dates,
we are required by the Office of Federal Register (OFR) to list service
information within the incorporated by reference (IBR) paragraph of the
AD regulatory text (i.e. paragraph (n) of this AD) according to the
document name. For consistency, the IBR material is listed in the same
alphanumerical sequence within the 1 CFR part 51 paragraph of the AD
preamble text. In this case, as stated previously, we have changed a
certain citation, and that change places the service information in the
alphanumeric order shown within this AD, which also addresses the
commenter's request.
Conclusion
We reviewed the relevant data, considered the comments received,
and determined that air safety and the public interest require adopting
this AD with the changes described previously and minor editorial
changes. We have determined that these minor changes:
Are consistent with the intent that was proposed in the
NPRM for correcting the unsafe condition; and
Do not add any additional burden upon the public than was
already proposed in the NPRM.
We also determined that these changes will not increase the
economic burden on any operator or increase the scope of this AD.
Related Service Information Under 1 CFR Part 51
Bombardier has issued the following service information. The
service information describes procedures for repetitive inspections of
the rudder pedal tubes for cracking, replacement of both pilot-side
rudder bar assemblies, and repair. These documents are distinct since
they apply to different airplane models.
Service Bulletin 600-0770, including Appendix A, both
Revision 01, both dated March 31, 2016.
Service Bulletin 601-0643, including Appendix A, both
Revision 01, both dated March 31, 2016.
Service Bulletin 604-27-037, including Appendix A,
Revision 01, both dated March 31, 2016.
Service Bulletin 605-27-008, including Appendix A,
Revision 01, both dated March 31, 2016.
Service Bulletin 650-27-002, dated June 30, 2016,
including Appendix A, Revision 01, dated March 31, 2016.
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 141 airplanes of U.S. registry.
We estimate the following costs to comply with this AD:
[[Page 23353]]
Estimated Costs
----------------------------------------------------------------------------------------------------------------
Cost on U.S.
Action Labor cost Parts cost Cost per product operators
----------------------------------------------------------------------------------------------------------------
Inspections...................... 10 work-hours x $85 $0 $850 per inspection $119,850 per
per hour = $850 cycle. inspection cycle.
per inspection
cycle.
----------------------------------------------------------------------------------------------------------------
.We estimate the following costs to do any necessary replacements
that would be required based on the results of the proposed inspection.
We have no way of determining the number of airplanes that might need
these replacements:
On-Condition Costs
----------------------------------------------------------------------------------------------------------------
Cost per
Action Labor cost Parts cost product
----------------------------------------------------------------------------------------------------------------
Replacement................................ 2 work-hours x $85 per hour = $170. $8,564 $8,734
----------------------------------------------------------------------------------------------------------------
We have received no definitive data that will enable us to provide
cost estimates for any on-condition repairs specified in this AD. We
have no way of determining the number of aircraft that might need this
repair.
Authority for This Rulemaking
Title 49 of the United States Code specifies the FAA's authority to
issue rules on aviation safety. Subtitle I, section 106, describes the
authority of the FAA Administrator. Subtitle VII: Aviation Programs,
describes in more detail the scope of the Agency's authority.
We are issuing this rulemaking under the authority described in
Subtitle VII, Part A, Subpart III, Section 44701: ``General
requirements.'' Under that section, Congress charges the FAA with
promoting safe flight of civil aircraft in air commerce by prescribing
regulations for practices, methods, and procedures the Administrator
finds necessary for safety in air commerce. This regulation is within
the scope of that authority because it addresses an unsafe condition
that is likely to exist or develop on products identified in this
rulemaking action.
This AD is issued in accordance with authority delegated by the
Executive Director, Aircraft Certification Service, as authorized by
FAA Order 8000.51C. In accordance with that order, issuance of ADs is
normally a function of the Compliance and Airworthiness Division, but
during this transition period, the Executive Director has delegated the
authority to issue ADs applicable to transport category airplanes to
the Director of the System Oversight Division.
Regulatory Findings
We determined that this AD will not have federalism implications
under Executive Order 13132. This AD will not have a substantial direct
effect on the States, on the relationship between the national
government and the States, or on the distribution of power and
responsibilities among the various levels of government.
For the reasons discussed above, I certify that this AD:
1. Is not a ``significant regulatory action'' under Executive Order
12866,
2. Is not a ``significant rule'' under the DOT Regulatory Policies
and Procedures (44 FR 11034, February 26, 1979),
3. Will not affect intrastate aviation in Alaska, and
4. Will not have a significant economic impact, positive or
negative, on a substantial number of small entities under the criteria
of the Regulatory Flexibility Act.
List of Subjects in 14 CFR Part 39
Air transportation, Aircraft, Aviation safety, Incorporation by
reference, Safety.
Adoption of the Amendment
Accordingly, under the authority delegated to me by the
Administrator, the FAA amends 14 CFR part 39 as follows:
PART 39--AIRWORTHINESS DIRECTIVES
0
1. The authority citation for part 39 continues to read as follows:
Authority: 49 U.S.C. 106(g), 40113, 44701.
Sec. 39.13 [Amended]
0
2. The FAA amends Sec. 39.13 by adding the following new airworthiness
directive (AD):
2018-09-17 Bombardier, Inc.: Amendment 39-19274; Docket No. FAA-
2017-0907; Product Identifier 2017-NM-069-AD.
(a) Effective Date
This AD is effective June 25, 2018.
(b) Affected ADs
None.
(c) Applicability
This AD applies to the Bombardier, Inc., airplanes identified in
paragraphs (c)(1) through (c)(3) of this AD, certificated in any
category.
(1) Model CL-600-1A11 (CL-600) airplanes, serial numbers (S/Ns)
1004 through 1085 inclusive.
(2) Model CL-600-2A12 (CL-601 Variant) airplanes, S/Ns 3001
through 3066 inclusive.
(3) Model CL-600-2B16 (CL-601-3A, CL-601-3R, and CL-604
Variants) airplanes, S/Ns 5001 through 5194 inclusive, S/Ns 5301
through 5665 inclusive, S/Ns 5701 through 5988 inclusive, and S/Ns
6050 through 6099 inclusive.
(d) Subject
Air Transport Association (ATA) of America Code 27, Flight
Controls.
(e) Reason
This AD was prompted by reports of fractured rudder pedal tubes
on the pilot-side rudder bar assembly. We are issuing this AD to
address cracking of the pilot-side rudder pedal tubes. Loss of pilot
rudder pedal input during flight could result in reduced yaw
controllability of the airplane. Loss of pilot rudder pedal input
during takeoff or landing could lead to a runway excursion.
(f) Compliance
Comply with this AD within the compliance times specified,
unless already done.
(g) Repetitive Inspections and Part Marking
At the applicable time specified in figure 1 to paragraph (g) of
this AD, do a detailed or eddy current inspection of both pilot-side
rudder pedal tubes for cracking, in accordance with Part A of the
Accomplishment Instructions of the applicable service information
identified in paragraphs (g)(1) through (g)(6) of this AD. If no
cracking is found, before further flight, mark the part in
accordance with Part A of the Accomplishment Instructions of the
applicable service information identified in paragraphs (g)(1)
through (g)(6) of this AD. Repeat the detailed or eddy current
[[Page 23354]]
inspection thereafter at intervals not to exceed 600 flight cycles
if a detailed inspection was performed, or 1,000 flight cycles if an
eddy current inspection was performed. Repeat the inspection until
the terminating action specified in paragraph (i) of this AD is
accomplished.
(1) For Model CL-600-1A11 (CL-600) airplanes, S/Ns 1004 through
1085 inclusive: Bombardier Service Bulletin 600-0770, including
Appendix A, both Revision 01, both dated March 31, 2016.
(2) For Model CL-600-2A12 (CL-601 Variant) airplanes, S/Ns 3001
through 3066 inclusive: Bombardier Service Bulletin 601-0643,
including Appendix A, both Revision 01, both dated March 31, 2016.
(3) For Model CL-600-2B16 (CL-601-3A, CL-601-3R, and CL-604
Variants) airplanes, S/Ns 5001 through 5194 inclusive: Bombardier
Service Bulletin 601-0643, including Appendix A, both Revision 01,
both dated March 31, 2016.
(4) For Model CL-600-2B16 (CL-601-3A, CL-601-3R, and CL-604
Variants) airplanes, S/Ns 5301 through 5665 inclusive: Bombardier
Service Bulletin 604-27-037, including Appendix A, Revision 01, both
dated March 31, 2016.
(5) For Model CL-600-2B16 (CL-601-3A, CL-601-3R, and CL-604
Variants) airplanes, S/Ns 5701 through 5988 inclusive: Bombardier
Service Bulletin 605-27-008, including Appendix A, Revision 01, both
dated March 31, 2016.
(6) For Model CL-600-2B16 (CL-601-3A, CL-601-3R, and CL-604
Variants) airplanes, S/Ns 6050 through 6099 inclusive: Bombardier
Service Bulletin 650-27-002, dated June 30, 2016, including Appendix
A, Revision 01, dated March 31, 2016.
[GRAPHIC] [TIFF OMITTED] TR21MY18.000
(h) Corrective Actions
(1) If any cracking is found around the aft tapered holes during
any inspection required by paragraph (g) of this AD, before further
flight, replace both pilot-side rudder bar assemblies, in accordance
with Part B of the Accomplishment Instructions of the applicable
service information identified in paragraphs (g)(1) through (g)(6)
of this AD.
(2) If any other damage (e.g., corrosion) is found, during any
inspection required by paragraph (g) of this AD, before further
flight, repair 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.
(i) Optional Terminating Action
Replacement of both pilot-side rudder bar assemblies in
accordance with Part B of the Accomplishment Instructions of the
applicable service information identified in paragraphs (g)(1)
through (g)(6) of this AD terminates the inspections required by
paragraph (g) of this AD.
(j) Replacement--No Terminating Action
Replacement of both pilot-side rudder bar assemblies using Part
B of the Accomplishment Instructions of Bombardier Service Bulletin
600-0770, dated August 31, 2015; or Bombardier Service Bulletin 601-
0643, dated August 31, 2015; is not a terminating action for the
inspections required by paragraph (g) of this AD.
(k) 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 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 TCCA; or Bombardier, Inc.'s TCCA DAO. If approved by
the DAO, the approval must include the DAO-authorized signature.
(l) Special Flight Permits
Special flight permits, as described in Section 21.197 and
Section 21.199 of the Federal Aviation Regulations (14 CFR 21.197
and 21.199), are not allowed if any cracking is found during any
inspection required by paragraph (g) of this AD.
(m) Related Information
(1) Refer to Mandatory Continuing Airworthiness Information
(MCAI) Canadian Airworthiness Directive CF-2017-09, dated February
22, 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-2017-0907.
(2) For more information about this AD, contact Aziz Ahmed,
Aerospace Engineer, Airframe and Mechanical Systems Section, FAA,
New York ACO Branch, 1600 Stewart Avenue, Suite 410, Westbury, NY
11590; telephone 516-228-7329; fax 516-794-5531.
(n) Material Incorporated by Reference
(1) The Director of the Federal Register approved the
incorporation by reference (IBR) of the service information listed
in this paragraph under 5 U.S.C. 552(a) and 1 CFR part 51.
(2) You must use this service information as applicable to do
the actions required by this AD, unless this AD specifies otherwise.
[[Page 23355]]
(i) Bombardier Service Bulletin 600-0770, including Appendix A,
both Revision 01, both dated March 31, 2016.
(ii) Bombardier Service Bulletin 601-0643, including Appendix A,
both Revision 01, both dated March 31, 2016.
(iii) Bombardier Service Bulletin 604-27-037, including Appendix
A, Revision 01, both dated March 31, 2016.
(iv) Bombardier Service Bulletin 605-27-008, including Appendix
A, Revision 01, both dated March 31, 2016.
(v) Bombardier Service Bulletin 650-27-002, dated June 30, 2016,
including Appendix A, Revision 01, dated March 31, 2016.
(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; Widebody Customer Response Center
North America toll-free telephone 1-866-538-1247 or direct-dial
telephone 1-514-855-2999; fax 514-855-7401; email
[email protected]; internet https://www.bombardier.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 April 27, 2018.
Michael Kaszycki,
Acting Director, System Oversight Division, Aircraft Certification
Service.
[FR Doc. 2018-09732 Filed 5-18-18; 8:45 am]
BILLING CODE 4910-13-P
