AD 2018-09-17

[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 [<a href="http://www.gpo.gov">www.gpo.gov</a>]
[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.

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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 <a href="/cdn-cgi/l/email-protection#563735782f233a16373324397834393b343724323f33247835393b"><span class="__cf_email__" data-cfemail="1574763b6c6079557470677a3b777a78777467717c70673b767a78">[email&#160;protected]</span></a>; 
internet <a href="http://www.bombardier.com">http://www.bombardier.com</a>. 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 <a href="http://www.regulations.gov">http://www.regulations.gov</a> by searching for and locating 
Docket No. FAA-2017-0907.

Examining the AD Docket

    You may examine the AD docket on the internet at <a href="http://www.regulations.gov">http://www.regulations.gov</a> 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 <a href="http://www.regulations.gov">http://www.regulations.gov</a> 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:
    <bullet> Are consistent with the intent that was proposed in the 
NPRM for correcting the unsafe condition; and
    <bullet> 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.
    <bullet> Service Bulletin 600-0770, including Appendix A, both 
Revision 01, both dated March 31, 2016.
    <bullet> Service Bulletin 601-0643, including Appendix A, both 
Revision 01, both dated March 31, 2016.
    <bullet> Service Bulletin 604-27-037, including Appendix A, 
Revision 01, both dated March 31, 2016.
    <bullet> Service Bulletin 605-27-008, including Appendix A, 
Revision 01, both dated March 31, 2016.
    <bullet> 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 <a href="http://www.regulations.gov">http://www.regulations.gov</a> 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 
<a href="/cdn-cgi/l/email-protection#debfbdf0a7abb29ebfbbacb1f0bcb1b3bcbfacbab7bbacf0bdb1b3"><span class="__cf_email__" data-cfemail="bedfdd90c7cbd2fedfdbccd190dcd1d3dcdfccdad7dbcc90ddd1d3">[email&#160;protected]</span></a>; internet <a href="http://www.bombardier.com">http://www.bombardier.com</a>.
    (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: <a href="http://www.archives.gov/federal-register/cfr/ibr-locations.html">http://www.archives.gov/federal-register/cfr/ibr-locations.html</a>.

    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