83_FR_23449 83 FR 23351 - Airworthiness Directives; Bombardier, Inc., Airplanes

83 FR 23351 - Airworthiness Directives; Bombardier, Inc., Airplanes

DEPARTMENT OF TRANSPORTATION
Federal Aviation Administration

Federal Register Volume 83, Issue 98 (May 21, 2018)

Page Range23351-23355
FR Document2018-09732

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.

Federal Register, Volume 83 Issue 98 (Monday, May 21, 2018) 
[Federal Register Volume 83, Number 98 (Monday, May 21, 2018)]
[Rules and Regulations]
[Pages 23351-23355]
From the Federal Register Online  [www.thefederalregister.org]
[FR Doc No: 2018-09732]


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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 http://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 http://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 http://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 http://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 http://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 http://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: http://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

Federal Register / Vol. 83, No. 98 / Monday, May 21, 2018 / Rules and Regulations 23351 segment assembly and inspect the adapter, www.archives.gov/federal-register/cfr/ibr- on the internet at http:// washers, and TR driveshaft for damage. locations.html. www.regulations.gov by searching for Replace the adapter retention nut and apply Issued in Fort Worth, Texas, on May 7, and locating Docket No. FAA–2017– a torque of 30 to 50 inch-pounds (5.7 to 7.9 2018. 0907. Nm). Replace any part with damage or repair the part if the damage is within the Lance T. Gant, Examining the AD Docket maximum repair damage limitations. Director, Compliance & Airworthiness (3) Repeat the actions specified in Division, Aircraft Certification Service. You may examine the AD docket on paragraph (e)(1) of this AD at intervals not to [FR Doc. 2018–10491 Filed 5–18–18; 8:45 am] the internet at http:// exceed 330 hours TIS. BILLING CODE 4910–13–P www.regulations.gov by searching for (f) Special Flight Permits and locating Docket No. FAA–2017– 0907; or in person at the Docket Special flight permits are prohibited. DEPARTMENT OF TRANSPORTATION Management Facility between 9 a.m. (g) Alternative Methods of Compliance and 5 p.m., Monday through Friday, (AMOCs) Federal Aviation Administration except Federal holidays. The AD docket (1) The Manager, Safety Management contains this AD, the regulatory Section, Rotorcraft Standards Branch, FAA, 14 CFR Part 39 evaluation, any comments received, and may approve AMOCs for this AD. Send your other information. The street address for proposal to: David Hatfield, Aviation Safety [Docket No. FAA–2017–0907; Product Identifier 2017–NM–069–AD; Amendment the Docket Office (telephone 800–647– Engineer, Safety Management Section, 5527) is Docket Management Facility, Rotorcraft Standards Branch, FAA, 10101 39–19274; AD 2018–09–17] Hillwood Pkwy., Fort Worth, TX 76177; U.S. Department of Transportation, RIN 2120–AA64 Docket Operations, M–30, West telephone (817) 222–5110; email 9-ASW- FTW-AMOC-Requests@faa.gov. Building Ground Floor, Room W12–140, Airworthiness Directives; Bombardier, (2) For operations conducted under a 14 1200 New Jersey Avenue SE, Inc., Airplanes CFR part 119 operating certificate or under Washington, DC 20590. 14 CFR part 91, subpart K, we suggest that AGENCY: Federal Aviation FOR FURTHER INFORMATION CONTACT: Aziz you notify your principal inspector, or Administration (FAA), Department of lacking a principal inspector, the manager of Ahmed, Aerospace Engineer, Airframe Transportation (DOT). and Mechanical Systems Section, FAA, the local flight standards district office or certificate holding district office, before ACTION: Final rule. New York ACO Branch, 1600 Stewart operating any aircraft complying with this Avenue, Suite 410, Westbury, NY AD through an AMOC. SUMMARY: We are adopting a new 11590; telephone 516–228–7329; fax airworthiness directive (AD) for certain 516–794–5531. (h) Additional Information Bombardier, Inc., Model CL–600–1A11 The subject of this AD is addressed in SUPPLEMENTARY INFORMATION: (CL–600), CL–600–2A12 (CL–601 Transport Canada AD No. CF–2016–21, dated Variant), and CL–600–2B16 (CL–601– Discussion July 7, 2016. You may view the Transport 3A, CL–601–3R, and CL–604 Variants) Canada AD on the internet at http:// We issued a notice of proposed airplanes. This AD was prompted by rulemaking (NPRM) to amend 14 CFR www.regulations.gov in Docket No. FAA– 2017–0667. reports of fractured rudder pedal tubes part 39 by adding an AD that would on the pilot-side rudder bar assembly. apply to certain Bombardier, Inc., Model (i) Subject This AD requires repetitive inspections CL–600–1A11 (CL–600), CL–600–2A12 Joint Aircraft Service Component (JASC) of the rudder pedal tubes for cracking (CL–601 Variant), and CL–600–2B16 Code: 6510 Tail Rotor Drive Shaft. and corrective actions if necessary. (CL–601–3A, CL–601–3R, and CL–604 (j) Material Incorporated by Reference Replacement of both pilot-side rudder Variants) airplanes. The NPRM (1) The Director of the Federal Register bar assemblies terminates the published in the Federal Register on approved the incorporation by reference of inspections. We are issuing this AD to October 19, 2017 (82 FR 48668) (‘‘the the service information listed in this address the unsafe condition on these NPRM’’). The NPRM was prompted by paragraph under 5 U.S.C. 552(a) and 1 CFR products. reports of fractured rudder pedal tubes part 51. DATES: This AD is effective June 25, (2) You must use this service information on the pilot-side rudder bar assembly. as applicable to do the actions required by 2018. The NPRM proposed to require this AD, unless the AD specifies otherwise. The Director of the Federal Register repetitive inspections of the rudder (i) Bell Alert Service Bulletin 407–16–113, approved the incorporation by reference pedal tubes for cracking and corrective dated February 12, 2016. of certain publications listed in this AD actions if necessary. Replacement of (ii) Reserved. as of June 25, 2018. both pilot-side rudder bar assemblies (3) For Bell service information identified ADDRESSES: For service information terminates the inspections. We are in this AD, Bell Helicopter Textron Canada identified in this final rule, contact issuing this AD to address cracking of Limited, 12,800 Rue de l’Avenir, Mirabel, Quebec J7J1R4; telephone (450) 437–2862 or Bombardier, Inc., 400 Côte-Vertu Road the pilot-side rudder pedal tubes. Loss (800) 363–8023; fax (450) 433–0272; or at West, Dorval, Québec H4S 1Y9, Canada; of pilot rudder pedal input during flight http://www.bellcustomer.com/files/. Widebody Customer Response Center could result in reduced yaw (4) You may view this service information North America toll-free telephone 1– controllability of the airplane. Loss of at FAA, Office of the Regional Counsel, 866–538–1247 or direct-dial telephone pilot rudder pedal input during takeoff Southwest Region, 10101 Hillwood Pkwy, 1–514–855–2999; fax 514–855–7401; or landing could lead to a runway Room 6N–321, Fort Worth, TX 76177. For email ac.yul@aero.bombardier.com; excursion. sradovich on DSK3GMQ082PROD with RULES information on the availability of this internet http://www.bombardier.com. Transport Canada Civil Aviation material at the FAA, call (817) 222–5110. You may view this referenced service (TCCA), which is the aviation authority (5) You may view this service information that is incorporated by reference at the information at the FAA, Transport for Canada, has issued Canadian National Archives and Records Standards Branch, 2200 South 216th St., Airworthiness Directive CF–2017–09, Administration (NARA). For information on Des Moines, WA. For information on the dated February 22, 2017 (referred to the availability of this material at NARA, call availability of this material at the FAA, after this as the Mandatory Continuing (202) 741–6030, or go to: http:// call 206–231–3195. It is also available Airworthiness Information, or ‘‘the VerDate Sep<11>2014 15:54 May 18, 2018 Jkt 244001 PO 00000 Frm 00003 Fmt 4700 Sfmt 4700 E:\FR\FM\21MYR1.SGM 21MYR1

23352 Federal Register / Vol. 83, No. 98 / Monday, May 21, 2018 / Rules and Regulations MCAI’’), to correct an unsafe condition NetJets’ request to correct the changed a certain citation, and that for certain Bombardier, Inc., Model CL– typographical error in the preamble and change places the service information in 600–1A11 (CL–600), CL–600–2A12 (CL– paragraph (g)(6) of this AD by removing the alphanumeric order shown within 601 Variant), and CL–600–2B16 (CL– the incorrect citation and including the this AD, which also addresses the 601–3A, CL–601–3R, and CL–604 correct citation, which is Bombardier commenter’s request. Variants) airplanes. The MCAI states: Service Bulletin 650–27–002, dated June Conclusion There have been two in-service reports of 30, 2016, including Appendix A, fractured rudder pedal tubes installed on the Revision 01, dated March 31, 2016. We reviewed the relevant data, pilot-side rudder bar assembly on CL–600– We do not agree with Bombardier’s considered the comments received, and 2B19 aeroplanes. Laboratory examination of request because a typographical error determined that air safety and the the fractured rudder pedal tubes found that does not exist in our citation of public interest require adopting this AD in both cases, the fatigue cracks initiated at Bombardier Service Bulletin 605–27– with the changes described previously the aft taper pin holes where the connecting 008, dated March 31, 2016, including and minor editorial changes. We have rod fitting is attached. Fatigue testing of the Appendix A, Revision 01, dated March determined that these minor changes: rudder pedal tubes confirmed that the fatigue 31, 2016. We contacted the commenter, • Are consistent with the intent that cracking is due to loads induced during parking brake application. Therefore, only and the company representative agreed was proposed in the NPRM for the rudder pedal tubes on the pilot’s side are that there is not a typographical error. correcting the unsafe condition; and vulnerable to fatigue cracking as the parking Therefore, no change was made to this • Do not add any additional burden brake is primarily applied by the pilot. AD in this regard. upon the public than was already Loss of pilot rudder pedal input during proposed in the NPRM. flight would result in reduced yaw Request To Change the Order of Certain We also determined that these controllability of the aeroplane. Loss of pilot Service Information in the Related changes will not increase the economic rudder pedal input during takeoff or landing Service Information Under 1 CFR Part burden on any operator or increase the may lead to a runway excursion. 51 Paragraph scope of this AD. This [Canadian] AD mandates initial and During a phone conversation between repetitive [detailed visual or eddy current] Related Service Information Under 1 inspections [for cracking] of both pilot-side Bombardier and the FAA that occurred during the NPRM comment period, CFR Part 51 rudder pedal tubes, part number (P/N) 600– 90204–3 until the terminating action in Part Bombardier requested that the order of Bombardier has issued the following III of this [Canadian] AD is accomplished certain service information in ‘‘Related service information. The service [i.e., replacement of both pilot-side rudder Service Information under 1 CFR part information describes procedures for bar assemblies]. 51’’ be rearranged. Specifically, the repetitive inspections of the rudder Corrective actions include commenter requested that Service pedal tubes for cracking, replacement of replacement of both pilot-side rudder Bulletin 605–27–008, dated March 31, both pilot-side rudder bar assemblies, bar assemblies and repair. You may 2016, including Appendix A, Revision and repair. These documents are examine the MCAI in the AD docket on 01, dated March 31, 2016, be listed distinct since they apply to different the internet at http:// above Service Bulletin 650–27–002, airplane models. www.regulations.gov by searching for dated June 30, 2016, including • Service Bulletin 600–0770, and locating Docket No. FAA–2017– Appendix A, Revision 01, dated March including Appendix A, both Revision 0907. 31, 2016. The commenter stated that 01, both dated March 31, 2016. chronologically Bombardier issued • Service Bulletin 601–0643, Comments Service Bulletin 605–27–008, dated including Appendix A, both Revision We gave the public the opportunity to March 31, 2016, including Appendix A, 01, both dated March 31, 2016. participate in developing this AD. The Revision 01, dated March 31, 2016, • Service Bulletin 604–27–037, following presents the comments before issuing Service Bulletin 650–27– including Appendix A, Revision 01, received on the NPRM and the FAA’s 002, dated June 30, 2016, including both dated March 31, 2016. response to each comment. Appendix A, Revision 01, dated March • Service Bulletin 605–27–008, 31, 2016. including Appendix A, Revision 01, Requests To Correct Errors in Certain We agree to clarify. While we both dated March 31, 2016. Service Information Citations recognize the benefit of listing service • Service Bulletin 650–27–002, dated Bombardier and NetJets both information in chronological order June 30, 2016, including Appendix A, requested that typographical errors in based on publication dates, we are Revision 01, dated March 31, 2016. certain service bulletin citations be required by the Office of Federal This service information is reasonably corrected. Bombardier stated that in the Register (OFR) to list service available because the interested parties NPRM, Bombardier ‘‘Service Bulletin information within the incorporated by have access to it through their normal 605–27–008’’ should be cited as reference (IBR) paragraph of the AD course of business or by the means Bombardier ‘‘Service Bulletin 650–27– regulatory text (i.e. paragraph (n) of this identified in the ADDRESSES section. 008.’’ NetJets stated that Bombardier AD) according to the document name. ‘‘Service Bulletin 605–27–002’’ should For consistency, the IBR material is Costs of Compliance be cited as Bombardier ‘‘Service listed in the same alphanumerical We estimate that this AD affects 141 Bulletin 650–27–002.’’ sequence within the 1 CFR part 51 airplanes of U.S. registry. We partially agree with the paragraph of the AD preamble text. In We estimate the following costs to sradovich on DSK3GMQ082PROD with RULES commenters’ requests. We agree with this case, as stated previously, we have comply with this AD: VerDate Sep<11>2014 15:54 May 18, 2018 Jkt 244001 PO 00000 Frm 00004 Fmt 4700 Sfmt 4700 E:\FR\FM\21MYR1.SGM 21MYR1

Federal Register / Vol. 83, No. 98 / Monday, May 21, 2018 / Rules and Regulations 23353 ESTIMATED COSTS Cost on U.S. Action Labor cost Parts cost Cost per product operators Inspections ............................. 10 work-hours × $85 per hour $0 $850 per inspection cycle ...... $119,850 per inspection = $850 per inspection cycle. cycle. We estimate the following costs to do be required based on the results of the determining the number of airplanes any necessary replacements that would proposed inspection. We have no way of that might need these replacements: ON-CONDITION COSTS Cost per Action Labor cost Parts cost product Replacement .................................... 2 work-hours × $85 per hour = $170 ........................................................ $8,564 $8,734 We have received no definitive data not have a substantial direct effect on (b) Affected ADs that will enable us to provide cost the States, on the relationship between None. estimates for any on-condition repairs the national government and the States, (c) Applicability specified in this AD. We have no way or on the distribution of power and of determining the number of aircraft responsibilities among the various This AD applies to the Bombardier, Inc., airplanes identified in paragraphs (c)(1) that might need this repair. levels of government. through (c)(3) of this AD, certificated in any Authority for This Rulemaking For the reasons discussed above, I category. certify that this AD: (1) Model CL–600–1A11 (CL–600) Title 49 of the United States Code 1. Is not a ‘‘significant regulatory airplanes, serial numbers (S/Ns) 1004 specifies the FAA’s authority to issue action’’ under Executive Order 12866, through 1085 inclusive. rules on aviation safety. Subtitle I, 2. Is not a ‘‘significant rule’’ under the (2) Model CL–600–2A12 (CL–601 Variant) section 106, describes the authority of airplanes, S/Ns 3001 through 3066 inclusive. DOT Regulatory Policies and Procedures the FAA Administrator. Subtitle VII: (3) Model CL–600–2B16 (CL–601–3A, CL– (44 FR 11034, February 26, 1979), 601–3R, and CL–604 Variants) airplanes, Aviation Programs, describes in more 3. Will not affect intrastate aviation in S/Ns 5001 through 5194 inclusive, S/Ns 5301 detail the scope of the Agency’s Alaska, and through 5665 inclusive, S/Ns 5701 through authority. 4. Will not have a significant 5988 inclusive, and S/Ns 6050 through 6099 We are issuing this rulemaking under economic impact, positive or negative, inclusive. the authority described in Subtitle VII, on a substantial number of small entities (d) Subject Part A, Subpart III, Section 44701: under the criteria of the Regulatory ‘‘General requirements.’’ Under that Air Transport Association (ATA) of Flexibility Act. America Code 27, Flight Controls. section, Congress charges the FAA with promoting safe flight of civil aircraft in List of Subjects in 14 CFR Part 39 (e) Reason air commerce by prescribing regulations Air transportation, Aircraft, Aviation This AD was prompted by reports of for practices, methods, and procedures safety, Incorporation by reference, fractured rudder pedal tubes on the pilot-side the Administrator finds necessary for Safety. rudder bar assembly. We are issuing this AD safety in air commerce. This regulation to address cracking of the pilot-side rudder is within the scope of that authority Adoption of the Amendment pedal tubes. Loss of pilot rudder pedal input because it addresses an unsafe condition during flight could result in reduced yaw Accordingly, under the authority controllability of the airplane. Loss of pilot that is likely to exist or develop on delegated to me by the Administrator, rudder pedal input during takeoff or landing products identified in this rulemaking the FAA amends 14 CFR part 39 as could lead to a runway excursion. action. follows: This AD is issued in accordance with (f) Compliance authority delegated by the Executive PART 39—AIRWORTHINESS Comply with this AD within the Director, Aircraft Certification Service, DIRECTIVES compliance times specified, unless already as authorized by FAA Order 8000.51C. done. In accordance with that order, issuance ■ 1. The authority citation for part 39 (g) Repetitive Inspections and Part Marking of ADs is normally a function of the continues to read as follows: At the applicable time specified in figure Compliance and Airworthiness Authority: 49 U.S.C. 106(g), 40113, 44701. 1 to paragraph (g) of this AD, do a detailed Division, but during this transition or eddy current inspection of both pilot-side period, the Executive Director has § 39.13 [Amended] rudder pedal tubes for cracking, in delegated the authority to issue ADs accordance with Part A of the ■ 2. The FAA amends § 39.13 by adding applicable to transport category Accomplishment Instructions of the the following new airworthiness sradovich on DSK3GMQ082PROD with RULES airplanes to the Director of the System applicable service information identified in directive (AD): paragraphs (g)(1) through (g)(6) of this AD. If Oversight Division. no cracking is found, before further flight, 2018–09–17 Bombardier, Inc.: Amendment Regulatory Findings 39–19274; Docket No. FAA–2017–0907; mark the part in accordance with Part A of Product Identifier 2017–NM–069–AD. the Accomplishment Instructions of the We determined that this AD will not applicable service information identified in have federalism implications under (a) Effective Date paragraphs (g)(1) through (g)(6) of this AD. Executive Order 13132. This AD will This AD is effective June 25, 2018. Repeat the detailed or eddy current VerDate Sep<11>2014 15:54 May 18, 2018 Jkt 244001 PO 00000 Frm 00005 Fmt 4700 Sfmt 4700 E:\FR\FM\21MYR1.SGM 21MYR1

23354 Federal Register / Vol. 83, No. 98 / Monday, May 21, 2018 / Rules and Regulations inspection thereafter at intervals not to inclusive: Bombardier Service Bulletin 601– including Appendix A, Revision 01, both exceed 600 flight cycles if a detailed 0643, including Appendix A, both Revision dated March 31, 2016. inspection was performed, or 1,000 flight 01, both dated March 31, 2016. (5) For Model CL–600–2B16 (CL–601–3A, cycles if an eddy current inspection was (3) For Model CL–600–2B16 (CL–601–3A, CL–601–3R, and CL–604 Variants) airplanes, performed. Repeat the inspection until the CL–601–3R, and CL–604 Variants) airplanes, S/Ns 5701 through 5988 inclusive: terminating action specified in paragraph (i) Bombardier Service Bulletin 605–27–008, S/Ns 5001 through 5194 inclusive: of this AD is accomplished. including Appendix A, Revision 01, both Bombardier Service Bulletin 601–0643, (1) For Model CL–600–1A11 (CL–600) dated March 31, 2016. airplanes, S/Ns 1004 through 1085 inclusive: including Appendix A, both Revision 01, (6) For Model CL–600–2B16 (CL–601–3A, Bombardier Service Bulletin 600–0770, both dated March 31, 2016. CL–601–3R, and CL–604 Variants) airplanes, including Appendix A, both Revision 01, (4) For Model CL–600–2B16 (CL–601–3A, S/Ns 6050 through 6099 inclusive: both dated March 31, 2016. CL–601–3R, and CL–604 Variants) airplanes, Bombardier Service Bulletin 650–27–002, (2) For Model CL–600–2A12 (CL–601 S/Ns 5301 through 5665 inclusive: dated June 30, 2016, including Appendix A, Variant) airplanes, S/Ns 3001 through 3066 Bombardier Service Bulletin 604–27–037, Revision 01, dated March 31, 2016. (h) Corrective Actions 0643, dated August 31, 2015; is not a (l) Special Flight Permits (1) If any cracking is found around the aft terminating action for the inspections Special flight permits, as described in tapered holes during any inspection required required by paragraph (g) of this AD. Section 21.197 and Section 21.199 of the by paragraph (g) of this AD, before further (k) Other FAA AD Provisions Federal Aviation Regulations (14 CFR 21.197 flight, replace both pilot-side rudder bar and 21.199), are not allowed if any cracking The following provisions also apply to this assemblies, in accordance with Part B of the is found during any inspection required by AD: Accomplishment Instructions of the paragraph (g) of this AD. applicable service information identified in (1) Alternative Methods of Compliance paragraphs (g)(1) through (g)(6) of this AD. (AMOCs): The Manager, New York ACO (m) Related Information (2) If any other damage (e.g., corrosion) is Branch, FAA, has the authority to approve AMOCs for this AD, if requested using the (1) Refer to Mandatory Continuing found, during any inspection required by procedures found in 14 CFR 39.19. In Airworthiness Information (MCAI) Canadian paragraph (g) of this AD, before further flight, accordance with 14 CFR 39.19, send your Airworthiness Directive CF–2017–09, dated repair using a method approved by the Manager, New York ACO Branch, FAA; or request to your principal inspector or local February 22, 2017, for related information. Transport Canada Civil Aviation (TCCA); or Flight Standards District Office, as This MCAI may be found in the AD docket Bombardier, Inc.’s TCCA Design Approval appropriate. If sending information directly on the internet at http://www.regulations.gov Organization (DAO). If approved by the DAO, to the manager of the certification office, by searching for and locating Docket No. the approval must include the DAO- send it to ATTN: Program Manager, FAA–2017–0907. authorized signature. Continuing Operational Safety, FAA, New (2) For more information about this AD, York ACO Branch, 1600 Stewart Avenue, contact Aziz Ahmed, Aerospace Engineer, (i) Optional Terminating Action Suite 410, Westbury, NY 11590; telephone Airframe and Mechanical Systems Section, Replacement of both pilot-side rudder bar 516–228–7300; fax 516–794–5531. Before FAA, New York ACO Branch, 1600 Stewart assemblies in accordance with Part B of the using any approved AMOC, notify your Avenue, Suite 410, Westbury, NY 11590; Accomplishment Instructions of the appropriate principal inspector, or lacking a telephone 516–228–7329; fax 516–794–5531. applicable service information identified in principal inspector, the manager of the local paragraphs (g)(1) through (g)(6) of this AD flight standards district office/certificate (n) Material Incorporated by Reference terminates the inspections required by holding district office. (1) The Director of the Federal Register sradovich on DSK3GMQ082PROD with RULES paragraph (g) of this AD. (2) Contacting the Manufacturer: For any requirement in this AD to obtain corrective approved the incorporation by reference (j) Replacement—No Terminating Action actions from a manufacturer, the action must (IBR) of the service information listed in this Replacement of both pilot-side rudder bar be accomplished using a method approved paragraph under 5 U.S.C. 552(a) and 1 CFR assemblies using Part B of the by the Manager, New York ACO Branch, part 51. Accomplishment Instructions of Bombardier FAA; or TCCA; or Bombardier, Inc.’s TCCA (2) You must use this service information Service Bulletin 600–0770, dated August 31, DAO. If approved by the DAO, the approval as applicable to do the actions required by ER21MY18.000</GPH> 2015; or Bombardier Service Bulletin 601– must include the DAO-authorized signature. this AD, unless this AD specifies otherwise. 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Federal Register / Vol. 83, No. 98 / Monday, May 21, 2018 / Rules and Regulations 23355 (i) Bombardier Service Bulletin 600–0770, Inoperative (OEI) incidents. The actions these incidents resulted in a rejected including Appendix A, both Revision 01, of this AD are intended to detect and takeoff to an unprepared site. both dated March 31, 2016. prevent an unsafe condition on these The NPRM proposed to require initial (ii) Bombardier Service Bulletin 601–0643, products. including Appendix A, both Revision 01, and recurring inspections of each CPT both dated March 31, 2016. DATES: This AD is effective June 25, by measuring resistance, linearity (iii) Bombardier Service Bulletin 604–27– 2018. resistance movement, and differential 037, including Appendix A, Revision 01, The Director of the Federal Register voltage, and depending on the outcome both dated March 31, 2016. approved the incorporation by reference of the inspections, replacing the CPT. (iv) Bombardier Service Bulletin 605–27– of certain documents listed in this AD The proposed requirements were 008, including Appendix A, Revision 01, as of June 25, 2018. intended to detect wear of a CPT prior both dated March 31, 2016. to it causing an OEI condition and (v) Bombardier Service Bulletin 650–27– ADDRESSES: For service information identified in this final rule, contact possible emergency landing. 002, dated June 30, 2016, including Appendix A, Revision 01, dated March 31, Sikorsky Aircraft Corporation, Customer Comments 2016. Service Engineering, 124 Quarry Road, (3) For service information identified in Trumbull, CT 06611; telephone 1–800– After our NPRM was published, we this AD, contact Bombardier, Inc., 400 Côte Winged–S or 203–416–4299; email wcs_ received comments from Sikorsky. Vertu Road West, Dorval, Québec H4S 1Y9, cust_service_eng.gr-sik@lmco.com. You Canada; Widebody Customer Response Request To Include an Additional Part may review a copy of the referenced to the AD Center North America toll-free telephone 1–866–538–1247 or direct-dial telephone service information at the FAA, Office of the Regional Counsel, Southwest Sikorsky requested the AD also apply 1–514–855–2999; fax 514–855–7401; email to engine CPT P/N 76900–01821–105. In ac.yul@aero.bombardier.com; internet http:// Region, 10101 Hillwood Pkwy, Room www.bombardier.com. 6N–321, Fort Worth, TX 76177. It is also support of this request, Sikorsky stated (4) You may view this service information available on the internet at http:// that engine CPT P/N 76900–01821–105 at the FAA, Transport Standards Branch, www.regulations.gov by searching for is a new replacement for engine CPT P/ 2200 South 216th St., Des Moines, WA. For and locating Docket No. FAA–2017– N 76900–01821–104, which does not information on the availability of this 0874. differ substantially from engine CPT P/ material at the FAA, call 206–231–3195. N 76900–01821–104 and therefore (5) You may view this service information Examining the AD Docket should be subject to the periodic that is incorporated by reference at the You may examine the AD docket on inspections. National Archives and Records the internet at http:// We partially agree. While engine CPT Administration (NARA). For information on the availability of this material at NARA, call www.regulations.gov by searching for P/N 76900–01821–105 may be subject to 202–741–6030, or go to: http:// and locating Docket No. FAA–2017– the same unsafe condition because of www.archives.gov/federal-register/cfr/ibr- 0874; or in person at Docket Operations design similarity, adding this part locations.html. between 9 a.m. and 5 p.m., Monday would increase the scope of the AD. Issued in Des Moines, Washington, on through Friday, except Federal holidays. Therefore, we plan to publish another April 27, 2018. The AD docket contains this AD, any NPRM for P/N 76900–01821–105 to give Michael Kaszycki, incorporated-by-reference service the public an opportunity to comment information, the economic evaluation, on those requirements. Acting Director, System Oversight Division, Aircraft Certification Service. any comments received, and other Request To Remove a Test Box From information. The street address for [FR Doc. 2018–09732 Filed 5–18–18; 8:45 am] the AD Docket Operations (phone: 800–647– BILLING CODE 4910–13–P 5527) is U.S. Department of Sikorsky requested we remove Test Transportation, Docket Operations, M– Box P/N 76700–40009–042 and only DEPARTMENT OF TRANSPORTATION 30, West Building Ground Floor, Room allow the use of Test Box P/N 76700– W12–140, 1200 New Jersey Avenue SE, 40009–043 to comply with the AD. In Federal Aviation Administration Washington, DC 20590. support of this request, Sikorsky stated FOR FURTHER INFORMATION CONTACT: Nick it considers Test Box P/N 76700–40009– 14 CFR Part 39 Rediess, Aviation Safety Engineer, 042 obsolete because Test Box P/N Boston ACO Branch, Compliance & 76700–40009–043 is easier to use and [Docket No. FAA–2017–0874; Product provides less subjective results. Identifier 2015–SW–082–AD; Amendment Airworthiness Division, 1200 District 39–19282; AD 2018–10–07] Avenue, Burlington, MA 01803; We disagree. The proposed AD telephone (781) 238–7159; email provided procedures for both test boxes RIN 2120–AA64 nicholas.rediess@faa.gov. for the repetitive inspections. While SUPPLEMENTARY INFORMATION: Test Box P/N 76700–40009–043 may be Airworthiness Directives; Sikorsky more efficient, the use of Test Box P/N Aircraft Corporation Discussion 76700–40009–042 also addresses the AGENCY: Federal Aviation On September 14, 2017, at 82 FR unsafe condition. We do not find Administration (FAA), DOT. 43195, the Federal Register published justification for requiring operators who ACTION: Final rule. our notice of proposed rulemaking have Test Box P/N 76700–40009–042 to (NPRM), which proposed to amend 14 upgrade or replace their test box. SUMMARY: We are adopting a new CFR part 39 by adding an AD that However, we have revised the initial sradovich on DSK3GMQ082PROD with RULES airworthiness directive (AD) for would apply to Sikorsky Model S–76C inspection requirements of the AD to Sikorsky Aircraft Corporation (Sikorsky) helicopters with a Turbomeca, S.A., allow the use of Test Box P/N 76700– Model S–76C helicopters. This AD Arriel 2S1 or Arriel 2S2 engine with an 40009–043 as an option. We have also requires inspecting the engine collective engine CPT part number (P/N) 76900– revised the repetitive inspection position transducer (CPT). This AD was 01821–104 installed. The NPRM was procedures to allow the use of updated prompted by reports of wear of the CPT prompted by 20 reports of OEI incidents testing procedures for Test Box P/N that has resulted in several One Engine resulting from wear of a CPT. One of 76700–40009–043, which had not been VerDate Sep<11>2014 15:54 May 18, 2018 Jkt 244001 PO 00000 Frm 00007 Fmt 4700 Sfmt 4700 E:\FR\FM\21MYR1.SGM 21MYR1


Document Created: 2018-11-02 11:07:47
Document Modified: 2018-11-02 11:07:47
CategoryRegulatory Information
CollectionFederal Register
sudoc ClassAE 2.7:
GS 4.107:
AE 2.106:
PublisherOffice of the Federal Register, National Archives and Records Administration
SectionRules and Regulations
ActionFinal rule.
DatesThis AD is effective June 25, 2018.
ContactAziz 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.
FR Citation83 FR 23351 
RIN Number2120-AA64
CFR AssociatedAir Transportation; Aircraft; Aviation Safety; Incorporation by Reference and Safety
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