Document ID: FAA-2018-0801-0001
Agency: faa
Document Type: Proposed Rule
Title: Airworthiness Directives: Bombardier, Inc., Airplanes
Posted Date: 2018-10-01T04:00Z

[Federal Register Volume 83, Number 190 (Monday, October 1, 2018)]
[Proposed Rules]
[Pages 49317-49322]
From the Federal Register Online via the Government Publishing Office [www.gpo.gov]
[FR Doc No: 2018-20950]

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DEPARTMENT OF TRANSPORTATION

Federal Aviation Administration

14 CFR Part 39

[Docket No. FAA-2018-0801; Product Identifier 2017-NM-147-AD]
RIN 2120-AA64

Airworthiness Directives; Bombardier, Inc., Airplanes

AGENCY: Federal Aviation Administration (FAA), DOT.

ACTION: Notice of proposed rulemaking (NPRM).

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SUMMARY: We propose to supersede Airworthiness Directive (AD) 2008-24-
14, which applies to all Bombardier, Inc., Model CL-600-2B19 (Regional 
Jet Series 100 & 440) airplanes. AD 2008-24-14 requires revising the 
instructions for continued airworthiness to incorporate certain 
airworthiness limitations for the main landing gear (MLG) trunnion 
fitting assembly. Since we issued AD 2008-24-14, new airworthiness 
limitation (AWL) tasks have been introduced with revised inspection, 
modification, and safe-life requirements. This proposed AD would 
require revising the maintenance or inspection program, as applicable, 
to incorporate certain AWLs. It would also require reworking the 
trunnion fitting in order to meet new structural safe-life limits. We 
are proposing this AD to address the unsafe condition on these 
products.

DATES: We must receive comments on this proposed AD by November 15, 
2018.

ADDRESSES: You may send comments, using the procedures found in 14 CFR 
11.43 and 11.45, by any of the following methods:
     Federal eRulemaking Portal: Go to 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 [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.

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-2018-
0801; 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 proposal. Send your comments to an address listed 
under the ADDRESSES section. Include ``Docket No. FAA-2018-0801; 
Product Identifier 2017-NM-147-AD'' at the beginning of your comments. 
We specifically invite comments on the overall regulatory, economic, 
environmental, and energy aspects of this proposed AD. We will consider 
all comments received by the closing date and may amend this proposed 
AD 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

[[Page 49318]]

substantive verbal contact we receive about this proposed AD.

Discussion

    We issued AD 2008-24-14, Amendment 39-15758 (73 FR 73785, December 
4, 2008) (``AD 2008-24-14''), for all Bombardier, Inc., Model CL-600-
2B19 (Regional Jet Series 100 & 440) airplanes. AD 2008-24-14 requires 
revising the Airworthiness Limitations Section (ALS) of the 
Instructions for Continued Airworthiness to incorporate new structural 
inspection requirements. AD 2008-24-14 resulted from reports of the 
discovery of cracks on the MLG trunnion fitting web during fatigue 
testing. We issued AD 2008-24-14 to detect and correct fatigue cracking 
of the MLG trunnion fitting web.

Actions Since AD 2008-24-14 Was Issued

    Since we issued AD 2008-24-14, new AWL tasks have been introduced 
with revised inspection, modification, and safe-life requirements, and 
we have determined that the trunnion fitting lower flange and both 
forward and aft bore holes are also subject to fatigue cracking.
    Transport Canada Civil Aviation (TCCA), which is the aviation 
authority for Canada, has issued Canadian Airworthiness Directive CF-
2017-27, dated August 2, 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-600-2B19 
(Regional Jet Series 100 & 440) airplanes. The MCAI states:

    Cracks on the main landing gear (MLG) trunnion fitting web 
discovered during fatigue testing led to the issuance of [Canadian] 
AD CF-2008-21 [which corresponds to FAA AD 2008-24-14], which 
mandated new inspection requirements to ensure that fatigue cracking 
of the trunnion web would be detected and corrected.
    Additional fatigue test article findings and in-service findings 
have shown that the trunnion fitting lower flange and both forward 
and aft bore holes are also subject to fatigue cracking. Failure of 
the main landing gear trunnion fitting could result in the collapse 
of the main landing gear. Bombardier Inc. has decided to implement a 
series of design changes to improve the fatigue life of the trunnion 
fitting that is now a safe-life assembly.
    New and revised Airworthiness Limitation (AWL) tasks for the MLG 
trunnion fitting assembly have been introduced in order to require 
new inspection, modification, and safe-life requirements. This 
[Canadian] AD mandates the incorporation of these new and revised 
AWL tasks, and removal of the AWL tasks they replace, to ensure that 
fatigue cracking of the MLG trunnion fitting is detected and 
corrected. This [Canadian] AD also requires rework of the trunnion 
fitting in order to meet new structural safe-life limits.

    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-2018-
0801.

Related Service Information Under 1 CFR Part 51

    Bombardier has issued the following service information.
     Bombardier Service Bulletin 601R-57-046, Revision C, dated 
December 20, 2012, describes the cold working of fastener holes in the 
MLG trunnion fitting, and related investigative and corrective actions.
     Bombardier Service Bulletin 601R-57-047, Revision B, dated 
October 2, 2012, describes the installation of forcemate bushings in 
the MLG trunnion, and related investigative and corrective actions.
     Bombardier Service Bulletin 601R-57-048, Revision C, dated 
June 6, 2013, describes the cold working of holes on the web of the MLG 
trunnion, and related investigative and corrective actions.
    These documents are distinct because they apply to different parts 
of the airplane.
    The following service information describes certain AWL tasks for 
the MLG trunnion fitting assembly.
     Bombardier Maintenance Requirements Manual Temporary 
Revision (TR) 2B-2237, dated June 19, 2014.
     Bombardier Maintenance Requirements Manual Temporary 
Revision (TR) 2B-2238, dated June 19, 2014.
     Bombardier Maintenance Requirements Manual Temporary 
Revision (TR) 2B-2239, dated June 19, 2014.
     Bombardier Maintenance Requirements Manual Temporary 
Revision (TR) 2B-2241, dated June 19, 2014.
     Bombardier Maintenance Requirements Manual Temporary 
Revision (TR) 2B-2242, dated June 19, 2014.
     Bombardier Maintenance Requirements Manual Temporary 
Revision (TR) 2B-2246, dated November 7, 2014.
    These documents are distinct because they describe different 
actions. 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 the same 
type design.
    This proposed AD would require revisions to certain operator 
maintenance documents to include new actions (e.g., inspections). 
Compliance with these actions is required by 14 CFR 91.403(c). For 
airplanes that have been previously modified, altered, or repaired in 
the areas addressed by this proposed AD, the operator may not be able 
to accomplish the actions described in the revisions. In this 
situation, to comply with 14 CFR 91.403(c), the operator must request 
approval for an alternative method of compliance according to paragraph 
(p)(1) of this proposed AD. The request should include a description of 
changes to the required actions that will ensure the continued 
operational safety of the airplane.

Differences Between This Proposed AD and the Service Information

    The MCAI includes the following statement: ``If it is not possible 
to complete all of the instructions in the SBs . . . due to the 
configuration of the aircraft, contact Bombardier Inc. for approved 
instructions.'' This issue is addressed in 14 CFR 39.17, which states 
that ``If a change in a product affects your ability to accomplish the 
actions required by the AD in any way, you must request FAA approval of 
an AMOC [alternative method of compliance]. . . .'' Since we do not 
currently have the authority to delegate AMOC approvals to foreign 
civil aviation authorities, the FAA is responsible for these approvals.

Costs of Compliance

    We estimate that this proposed AD affects 460 airplanes of U.S. 
registry. We estimate the following costs to comply with this proposed 
AD:

[[Page 49319]]

                                                 Estimated Costs
----------------------------------------------------------------------------------------------------------------
            Action                 Labor cost       Parts cost    Cost per product     Cost on U.S. operators
----------------------------------------------------------------------------------------------------------------
Retained actions..............  1 work-hour x                 $0  >$85              $39,100.
                                 $85 per hour =
                                 $85.
Rework trunnion bearings (new   Up to 178 work-           38,928  Up to $54,058...  Up to $24,866,680.
 proposed actions).              hours x $85 per
                                 hour = Up to
                                 $15,130.
----------------------------------------------------------------------------------------------------------------

    We have determined that revising the maintenance or inspection 
program takes an average of 90 work-hours per operator, although we 
recognize that this number may vary from operator to operator. In the 
past, we have estimated that this action takes 1 work-hour per 
airplane. Since operators incorporate maintenance or inspection program 
changes for their affected fleet(s), we have determined that a per-
operator estimate is more accurate than a per-airplane estimate. 
Therefore, we estimate the total cost per operator to be $7,650 (90 
work-hours x $85 per work-hour).
    We have received no definitive data that would enable us to provide 
cost estimates for the on-condition actions specified in this proposed 
AD.
    According to the manufacturer, some or all of the costs of this AD 
may be covered under warranty, thereby reducing the cost impact on 
affected individuals. We do not control warranty coverage for affected 
individuals. As a result, we have included all costs in our cost 
estimate.

Authority for This Rulemaking

    Title 49 of the United States Code specifies the FAA's authority to 
issue rules on aviation safety. Subtitle I, section 106, describes the 
authority of the FAA Administrator. ``Subtitle VII: Aviation 
Programs,'' describes in more detail the scope of the Agency's 
authority.
    We are issuing this rulemaking under the authority described in 
``Subtitle VII, Part A, Subpart III, Section 44701: General 
requirements.'' Under that section, Congress charges the FAA with 
promoting safe flight of civil aircraft in air commerce by prescribing 
regulations for practices, methods, and procedures the Administrator 
finds necessary for safety in air commerce. This regulation is within 
the scope of that authority because it addresses an unsafe condition 
that is likely to exist or develop on products identified in this 
rulemaking action.
    This proposed AD is issued in accordance with authority delegated 
by the Executive Director, Aircraft Certification Service, as 
authorized by FAA Order 8000.51C. In accordance with that order, 
issuance of ADs is normally a function of the Compliance and 
Airworthiness Division, but during this transition period, the 
Executive Director has delegated the authority to issue ADs applicable 
to transport category airplanes to the Director of the System Oversight 
Division.

Regulatory Findings

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

List of Subjects in 14 CFR Part 39

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

The Proposed Amendment

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

PART 39--AIRWORTHINESS DIRECTIVES

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

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

Sec.  39.13   [Amended]

0
2. The FAA amends Sec.  39.13 by removing Airworthiness Directive (AD) 
2008-24-14, Amendment 39-15758 (73 FR 73785, December 4, 2008), and 
adding the following new AD:

Bombardier, Inc.: Docket No. FAA-2018-0801; Product Identifier 2017-
NM-147-AD.

(a) Comments Due Date

    We must receive comments by November 15, 2018.

(b) Affected ADs

    This AD replaces AD 2008-24-14, Amendment 39-15758 (73 FR 73785, 
December 4, 2008) (``AD 2008-24-14'').

(c) Applicability

    This AD applies to Bombardier, Inc., Model CL-600-2B19 (Regional 
Jet Series 100 & 440) airplanes, certificated in any category, 
serial numbers 7002 and subsequent.

(d) Subject

    Air Transport Association (ATA) of America Code 57, Wings.

(e) Reason

    This AD was prompted by reports of cracks on the main landing 
gear trunnion (MLG) fitting during fatigue testing, the introduction 
of new airworthiness limitation (AWL) tasks with revised inspection, 
modification, and safe-life requirements, and a determination that 
the trunnion fitting lower flange and both forward and aft bore 
holes are also subject to fatigue cracking. We are issuing this AD 
to detect and correct fatigue cracking of the MLG trunnion fitting. 
Failure of the MLG trunnion fitting web could compromise the 
structural integrity of the trunnion fitting and result in MLG 
collapse.

(f) Compliance

    Comply with this AD within the compliance times specified, 
unless already done.

(g) Retained Revision of Airworthiness Limitation Section With No 
Changes

    This paragraph restates the requirements of paragraph (f)(1) of 
AD 2008-24-14, with no changes. Within 30 days after December 19, 
2008 (the effective date of AD 2008-24-14), revise the Airworthiness 
Limitations Section (ALS) of the Instructions for Continued 
Airworthiness to incorporate AWL 57-21-161, as identified in 
Bombardier Temporary Revision 2B-2136, dated May 1, 2008, to the 
Bombardier CL-600-2B19 Maintenance Requirements Manual, Part 2, 
Appendix B--Airworthiness Limitations. The initial compliance time 
for the task starts from the applicable time specified in table 1 or 
table 2 to paragraphs (g) and (j) of this AD, as applicable. Repeat 
the inspection thereafter at the applicable interval specified in 
Bombardier Temporary Revision 2B-2136, dated May 1, 2008.

[[Page 49320]]

[GRAPHIC] [TIFF OMITTED] TP01OC18.000

(h) Retained No Alternative Actions or Intervals With New Exception

    This paragraph restates the requirements of paragraph (f)(2) of 
AD 2008-24-14, with a new exception: Except as required by paragraph 
(i) of this AD, after accomplishing the actions specified in 
paragraph (g) of this AD, no alternative inspections or inspection 
intervals may be used unless the inspection or inspection interval 
is approved as an alternative method of compliance (AMOC) in 
accordance with the procedures specified in paragraph (p)(1) of this 
AD.

(i) New Requirement of This AD: Revision of Maintenance or Inspection 
Program

    (1) Within 60 days after the effective date of this AD: Revise 
the maintenance or inspection program, as applicable, by 
incorporating the AWL tasks specified in figure 1 to paragraphs (i) 
and (o) of this AD. Except as specified in paragraph (j) of this AD, 
the initial compliance times for the tasks are at the applicable 
times specified in the temporary revisions (TRs) identified in 
figure 1 to paragraph (i) and (o) of this AD, or within 60 days 
after the effective date of this AD, whichever occurs later. When 
the information in AWL tasks identified in the TRs specified in 
figure 1 to paragraphs (i) and (o) of this AD has been included in 
the general revisions of Bombardier Maintenance Requirements Manual 
(MRM), CSP A-053, Part 2, Appendix B, the general revisions may be 
inserted in the MRM, and the TRs may be removed.

[[Page 49321]]

[GRAPHIC] [TIFF OMITTED] TP01OC18.001

    (2) Within 60 days after the effective date of this AD: Revise 
the maintenance or inspection program, as applicable, by removing 
the AWL tasks specified in figure 2 to paragraph (i) of this AD.
[GRAPHIC] [TIFF OMITTED] TP01OC18.002

(j) New Requirement of This AD: Initial Compliance Times for AWL Tasks

    (1) For AWL 57-21-161, the compliance time for the initial 
inspection of AWL 57-21-161 is as specified in tables 1 or 2 to 
paragraphs (g) and (j) of this AD, as applicable; or within 60 days 
after the effective date of this AD, whichever occurs later.
    (2) For AWL 57-21-161, the compliance time for the limitation 
section is at the applicable time specified in AWL 57-21-161 or 
within 2,000 flight cycles after the effective date of this AD, 
whichever occurs later.
    (3) For AWL 57-21-145 and AWL 57-21-155, the compliance times 
for the initial inspections are at the applicable times specified in 
AWL 57-21-145 and AWL 57-21-155 or within 2,000 flight cycles after 
the effective date of this AD, whichever occurs later.

(k) New Requirement of This AD: No Alternative Actions or Intervals

    After the maintenance or inspection program has been revised as 
required by paragraph (i) of this AD, no alternative actions (e.g., 
inspections) or intervals may be used unless the actions or 
intervals are approved as an alternative method of compliance (AMOC) 
in accordance with the procedures specified in paragraph (p)(1) of 
this AD.

(l) New Requirement of This AD: Rework of MLG Trunnion To Meet 
Structural Safe-Life Limits

    Except as specified in paragraphs (m)(1) and (m)(2) of this AD: 
Within the phase-in times specified in paragraphs (j)(2) and (j)(3) 
of this AD, rework the MLG trunnion in accordance with the 
Accomplishment Instructions of the service information identified in 
paragraphs (l)(1) through (l)(3) of this AD, as applicable.
    (1) Bombardier Service Bulletin 601R-57-046, Revision C, dated 
December 20, 2012, for the cold working of fastener holes in the MLG 
trunnion fitting, and related investigative and corrective actions.
    (2) Bombardier Service Bulletin 601R-57-047, Revision B, dated 
October 2, 2012, for the installation of forcemate bushings in the 
MLG trunnion, and related investigative and corrective actions.
    (3) Bombardier Service Bulletin 601R-57-048, Revision C, dated 
June 6, 2013, for the cold work of holes on the web of the MLG 
trunnion, and related investigative and corrective actions.

(m) Exceptions to Rework Requirements

    (1) For airplanes on which Bombardier Service Bulletin 601R-57-
046, Revision A, dated December 21, 2009; or Bombardier Service 
Bulletin 601R-57-046, Initial Issue, dated July 17, 2009; was 
accomplished prior to the effective date of this AD: Within 6 months 
after the effective date of this AD, do Part G of the Accomplishment 
Instructions of Bombardier Service Bulletin 601R-57-046, Revision C, 
dated December 20, 2012.
    (2) For airplanes on which Bombardier Service Bulletin 601R-57-
048, Revision A, dated November 24, 2009; or Bombardier Service 
Bulletin 601R-57-048, Initial Issue, dated July 17, 2009; was 
accomplished prior to the effective date of this AD: Within 6 months 
after the effective date of this AD, do Part C of the Accomplishment 
Instructions of Bombardier Service Bulletin 601R-57-048, Revision C, 
dated June 6, 2013.

(n) Credit for Previous Actions

    (1) This paragraph provides credit for actions required by 
paragraph (l)(1) of this AD, if those actions were performed before 
the effective date of this AD, using Bombardier Service Bulletin 
601R-57-046, Revision B, dated August 24, 2012.
    (2) This paragraph provides credit for actions required by 
paragraph (l)(2) of this AD, if those actions were performed before 
the effective date of this AD, using the service information 
specified in paragraph (n)(2)(i) or (n)(2)(ii) of this AD.
    (i) Bombardier Service Bulletin 601R-57-047, Revision A, dated 
February 1, 2012.
    (ii) Bombardier Service Bulletin 601R-57-047, Initial Issue, 
dated June 29, 2011.
    (3) This paragraph provides credit for actions required by 
paragraph (l)(3) of this

[[Page 49322]]

AD, if those actions were performed before the effective date of 
this AD, using Bombardier Service Bulletin 601R-57-048, Revision B, 
dated August 24, 2012.
    (4) This paragraph provides credit for actions required by 
paragraph (m)(1) of this AD, if those actions were performed before 
the effective date of this AD, using Part G of the Accomplishment 
Instructions of Bombardier Service Bulletin 601R-57-046, Revision B, 
dated August 24, 2012.
    (5) This paragraph provides credit for actions required by 
paragraph (m)(2) of this AD, if those actions were performed before 
the effective date of this AD, using Part C of the Accomplishment 
Instructions of Bombardier Service Bulletin 601R-57-048, Revision B, 
dated August 24, 2012.

(o) Repairs and Alternative Actions or Intervals

    (1) If any damage is found during an inspection required by the 
AWLs identified in figure 1 to paragraphs (i) and (o) of this AD, 
repair before further flight 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. The approved repair instructions must specifically refer 
to this AD or Canadian AD CF-2017-27, dated August 2, 2017.
    (2) Repairs approved by Bombardier, Inc., that deviate from the 
AWLs identified in figure 1 to paragraphs (i) and (o) of this AD are 
acceptable methods of compliance if 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. The approved repair instructions must specifically refer 
to this AD or Canadian AD CF-2017-27, dated August 2, 2017.
    (3) For repairs approved before the effective date of this AD 
that affect the AWLs identified in figure 1 to paragraphs (i) and 
(o) of this AD and the approved repair instructions do not 
specifically refer to Canadian AD CF-2017-27, dated August 2, 2017: 
Within 6 months of the effective date of this AD, contact the 
Manager, New York ACO Branch, FAA; or TCCA; or Bombardier, Inc.'s 
TCCA DAO Inc., for new or revised limitations or inspection 
requirements on the repair area and comply with the revised 
limitations or inspections requirements. The new or revised 
limitations or inspection requirements must specifically refer to 
this AD or Canadian AD CF-2017-27, dated August 2, 2017.
    (4) Canadian AMOC No. AARDG-2018/A21, dated May 1, 2018, which 
was approved before the effective date of this AD by TCCA, is an 
acceptable method of compliance to the corresponding requirements of 
this AD.

(p) Other FAA AD Provisions

    (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. The 
approved corrective action instructions must specifically refer to 
this AD or Canadian AD CF-2017-27, dated August 2, 2017.

(q) Related Information

    (1) Refer to Mandatory Continuing Airworthiness Information 
(MCAI) Canadian Airworthiness Directive CF-2017-27, dated August 2, 
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-2018-0801.
    (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 
[email protected]; internet http://www.bombardier.com. You 
may view this service information at the FAA, Transport Standards 
Branch, 2200 South 216th St., Des Moines, WA. For information on the 
availability of this material at the FAA, call 206-231-3195.

    Issued in Des Moines, Washington, on September 11, 2018.
Michael Kaszycki,
Acting Director, System Oversight Division, Aircraft Certification 
Service.
[FR Doc. 2018-20950 Filed 9-28-18; 8:45 am]
 BILLING CODE 4910-13-P