
[Federal Register Volume 82, Number 201 (Thursday, October 19, 2017)]
[Proposed Rules]
[Pages 48668-48671]
From the Federal Register Online via the Government Publishing Office [www.gpo.gov]
[FR Doc No: 2017-22557]


 ========================================================================
 Proposed Rules
                                                 Federal Register
 ________________________________________________________________________
 
 This section of the FEDERAL REGISTER contains notices to the public of 
 the proposed issuance of rules and regulations. The purpose of these 
 notices is to give interested persons an opportunity to participate in 
 the rule making prior to the adoption of the final rules.
 
 ========================================================================
 

  Federal Register / Vol. 82, No. 201 / Thursday, October 19, 2017 / 
Proposed Rules  

[[Page 48668]]



DEPARTMENT OF TRANSPORTATION

Federal Aviation Administration

14 CFR Part 39

[Docket No. FAA-2017-0907; Product Identifier 2017-NM-069-AD]
RIN 2120-AA64


Airworthiness Directives; Bombardier, Inc., Airplanes

AGENCY: Federal Aviation Administration (FAA), DOT.

ACTION: Notice of proposed rulemaking (NPRM).

-----------------------------------------------------------------------

SUMMARY: We propose to adopt a new airworthiness directive (AD) for 
certain Bombardier, Inc., Model 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 proposed AD was prompted by reports of 
fractured rudder pedal tubes on the pilot-side rudder bar assembly. 
This proposed AD would require repetitive inspections of the rudder 
pedal tubes for cracking and corrective actions if necessary. 
Replacement of both pilot-side rudder bar assemblies is terminating 
action for the inspections. We are proposing this AD to address the 
unsafe condition on these products.

DATES: We must receive comments on this proposed AD by December 4, 
2017.

ADDRESSES: You may send comments, using the procedures found in 14 CFR 
11.43 and 11.45, by any of the following methods:
     Federal eRulemaking Portal: Go to http://www.regulations.gov. Follow the instructions for submitting comments.
     Fax: 202-493-2251.
     Mail: U.S. Department of Transportation, Docket 
Operations, M-30, West Building Ground Floor, Room W12-140, 1200 New 
Jersey Avenue SE., Washington, DC 20590.
     Hand Delivery: Deliver to Mail address above between 9 
a.m. and 5 p.m., Monday through Friday, except Federal holidays.
    For service information identified in this NPRM, contact 
Bombardier, Inc., 400 C[ocirc]te-Vertu Road West, Dorval, Qu[eacute]bec 
H4S 1Y9, Canada; 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 http://www.bombardier.com. You may view this service information at the FAA, 
Transport Standards Branch, 1601 Lind Avenue SW., Renton, WA. For 
information on the availability of this material at the FAA, call 425-
227-1221.

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 NPRM, the regulatory evaluation, any comments received, 
and other information. The street address for the Docket Operations 
office (telephone 800-647-5527) is in the ADDRESSES section. Comments 
will be available in the AD docket shortly after receipt.

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: 

Comments Invited

    We invite you to send any written relevant data, views, or 
arguments about this proposed AD. Send your comments to an address 
listed under the ADDRESSES section. Include ``Docket No. FAA-2017-0907; 
Product Identifier 2017-NM-069-AD'' at the beginning of your comments. 
We specifically invite comments on the overall regulatory, economic, 
environmental, and energy aspects of this NPRM. We will consider all 
comments received by the closing date and may amend this NPRM based on 
those comments.
    We will post all comments we receive, without change, to http://www.regulations.gov, including any personal information you provide. We 
will also post a report summarizing each substantive verbal contact we 
receive about this NPRM.

Discussion

    Transport Canada Civil Aviation (TCCA), which is the aviation 
authority for Canada, has issued Canadian Airworthiness Directive CF-
2017-09, dated February 22, 2017 (referred to after this as the 
Mandatory Continuing Airworthiness Information, or ``the 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.

Related Service Information Under 1 CFR Part 51

    Bombardier, Inc., 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.

[[Page 48669]]

     Service Bulletin 600-0770, Revision 01, including Appendix 
A, dated March 31, 2016.
     Service Bulletin 601-0643, Revision 01, including Appendix 
A, dated March 31, 2016.
     Service Bulletin 604-27-037, dated March 31, 2016, 
including Appendix A, Revision 01, dated March 31, 2016.
     Service Bulletin 605-27-002, dated June 30, 2016, 
including Appendix A, Revision 01, dated March 31, 2016.
     Service Bulletin 605-27-008, dated March 31, 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.

FAA's Determination and Requirements of This Proposed AD

    This product has been approved by the aviation authority of another 
country, and is approved for operation in the United States. Pursuant 
to our bilateral agreement with the State of Design Authority, we have 
been notified of the unsafe condition described in the MCAI and service 
information referenced above. We are proposing this AD because we 
evaluated all pertinent information and determined an unsafe condition 
exists and is likely to exist or develop on other products of these 
same type designs.

Costs of Compliance

    We estimate that this proposed AD affects 141 airplanes of U.S. 
registry.
    We estimate the following costs to comply with this proposed AD:

                                                 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 per                    cycle.                 inspection cycle.
                               inspection cycle.
----------------------------------------------------------------------------------------------------------------


                                               On-Condition Costs
----------------------------------------------------------------------------------------------------------------
                                                                                     Cost per      Cost on U.S.
               Action                         Labor cost            Parts cost        product        operators
----------------------------------------------------------------------------------------------------------------
Replacement........................  2 work-hours x $85 per hour          $8,564          $8,734      $1,231,494
                                      = $170.
----------------------------------------------------------------------------------------------------------------

    We have received no definitive data that would enable us to provide 
cost estimates for any on-condition repairs specified in this proposed 
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 proposed AD is issued in accordance with authority delegated 
by the Executive Director, Aircraft Certification Service, as 
authorized by FAA Order 8000.51C. In accordance with that order, 
issuance of ADs is normally a function of the Compliance and 
Airworthiness Division, but during this transition period, the 
Executive Director has delegated the authority to issue ADs applicable 
to transport category airplanes to the Director of the System Oversight 
Division.

Regulatory Findings

    We determined that this proposed AD would not have federalism 
implications under Executive Order 13132. This proposed AD would not 
have a substantial direct effect on the States, on the relationship 
between the national Government and the States, or on the distribution 
of power and responsibilities among the various levels of government.
    For the reasons discussed above, I certify this proposed 
regulation:
    1. Is not a ``significant regulatory action'' under Executive Order 
12866;
    2. Is not a ``significant rule'' under the DOT Regulatory Policies 
and Procedures (44 FR 11034, February 26, 1979);
    3. Will not affect intrastate aviation in Alaska; and
    4. Will not have a significant economic impact, positive or 
negative, on a substantial number of small entities under the criteria 
of the Regulatory Flexibility Act.

List of Subjects in 14 CFR Part 39

    Air transportation, Aircraft, Aviation safety, Incorporation by 
reference, Safety.

The Proposed Amendment

    Accordingly, under the authority delegated to me by the 
Administrator, the FAA proposes to amend 14 CFR part 39 as follows:

PART 39--AIRWORTHINESS DIRECTIVES

0
1. The authority citation for part 39 continues to read as follows:

    Authority:  49 U.S.C. 106(g), 40113, 44701.


Sec.  39.13  [Amended]

0
2. The FAA amends Sec.  39.13 by adding the following new airworthiness 
directive (AD):

Bombardier, Inc.: Docket No. FAA-2017-0907; Product Identifier 2017-
NM-069-AD.

(a) Comments Due Date

    We must receive comments by December 4, 2017.

(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/

[[Page 48670]]

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 
detect and correct 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 
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, Inc., Service Bulletin 600-0770, 
Revision 01, including Appendix A, dated March 31, 2016.
    (2) For Model CL-600-2A12 (CL-601 Variant) airplanes, S/Ns 3001 
through 3066 inclusive: Bombardier, Inc., Service Bulletin 601-0643, 
Revision 01, including Appendix A, dated March 31, 2016.
    (3) Model CL-600-2B16 (CL-601-3A, CL-601-3R, and CL-604 
Variants) airplanes, S/Ns 5001 through 5194 inclusive: Bombardier, 
Inc., Service Bulletin 601-0643, Revision 01, including Appendix A, 
dated March 31, 2016.
    (4) Model CL-600-2B16 (CL-601-3A, CL-601-3R, and CL-604 
Variants) airplanes, S/Ns 5301 through 5665 inclusive: Bombardier, 
Inc., Service Bulletin 604-27-037, dated March 31, 2016, including 
Appendix A, Revision 01, dated March 31, 2016.
    (5) Model CL-600-2B16 (CL-601-3A, CL-601-3R, and CL-604 
Variants) airplanes, S/Ns 5701 through 5988 inclusive: Bombardier, 
Inc., Service Bulletin 605-27-008, dated March 31, 2016, including 
Appendix A, Revision 01, dated March 31, 2016.
    (6) Model CL-600-2B16 (CL-601-3A, CL-601-3R, and CL-604 
Variants) airplanes, S/Ns 6050 through 6099 inclusive: Bombardier, 
Inc., Service Bulletin 605-27-002, dated June 30, 2016, including 
Appendix A, Revision 01, dated March 31, 2016.

         Figure 1 to Paragraph (g) of This AD--Compliance Times
------------------------------------------------------------------------
               Airplanes                         Compliance time
------------------------------------------------------------------------
Airplanes with fewer than 8,250 total    Prior to the accumulation of
 flight cycles as of the effective date   9,000 total flight cycles.
 of this AD.
Airplanes with 8,250 total flight        Within 24 months or 750 flight
 cycles or more but fewer than 16,625     cycles, whichever occurs
 total flight cycles as of the            first, after the effective
 effective date of this AD.               date of this AD.
Airplanes with 16,625 total flight       Within 12 months or 375 flight
 cycles or more as of the effective       cycles, whichever occurs
 date of this AD.                         first, after the effective
                                          date of this AD.
------------------------------------------------------------------------

(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).

(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 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.
    (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 
ac.yul@aero.bombardier.com; Internet http://www.bombardier.com. You 
may view this service information at the FAA, Transport Standards 
Branch, 1601 Lind Avenue SW.,

[[Page 48671]]

Renton, WA. For information on the availability of this material at 
the FAA, call 425-227-1221.

    Issued in Renton, Washington, on October 11, 2017.

Jeffrey E. Duven,
Director, System Oversight Division, Aircraft Certification Service.
[FR Doc. 2017-22557 Filed 10-18-17; 8:45 am]
 BILLING CODE 4910-13-P


