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[Federal Register Volume 80, Number 201 (Monday, October 19, 2015)]
[Proposed Rules]
[Pages 63147-63151]
From the Federal Register Online via the Government Publishing Office [www.gpo.gov]
[FR Doc No: 2015-26217]

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DEPARTMENT OF TRANSPORTATION

Federal Aviation Administration

14 CFR Part 39

[Docket No. FAA-2015-3986; Directorate Identifier 2015-NM-057-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 adopt a new airworthiness directive (AD) for 
certain Bombardier, Inc. Model DHC-8-400, -401, and -402 airplanes. 
This proposed AD was prompted by reports of chafing damage due to 
insufficient clearance on the main landing gear (MLG) stabilizer brace, 
the nacelle A-frame structure, and the adjacent electrical wiring 
harnesses. An insufficient fillet radius may also exist on certain 
airplanes. This proposed AD would require, depending on airplane 
configuration, an inspection of the nacelle A-frame structure for 
insufficient fillet radius; an inspection for cracking of affected 
structure, and rework or repair if necessary, and rework of the nacelle 
A-frame structure; repetitive inspections of the nacelle A-frame 
structure and the MLG stabilizer brace for insufficient clearance and 
damage, and repair if necessary, and rework of the nacelle A-frame 
structure, which would terminate the repetitive inspections; 
installation of new stop brackets and a shim on each MLG stabilizer 
brace assembly; and rework of the electrical wiring harnesses in the 
nacelle area. We are proposing this AD to detect and correct chafing 
damage and subsequent premature cracking and fracture of the nacelle A-
frame structure, which could result in failure of the MLG stabilizer 
brace and loss of the MLG down-lock indication, which could adversely 
affect the safe landing of the airplane.

DATES: We must receive comments on this proposed AD by December 3, 
2015.

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: U.S. Department of Transportation, Docket 
Operations, M-30, West Building Ground Floor, Room W12-140, 1200 New 
Jersey Avenue SE., Washington, DC, between 9 a.m. and 5 p.m., Monday 
through Friday, except Federal holidays.
    For service information identified in this proposed AD, contact 
Bombardier, Inc., Q-Series Technical Help Desk, 123 Garratt Boulevard, 
Toronto, Ontario M3K 1Y5, Canada; telephone 416-375-4000; fax 416-375-
4539; email thd.qseries@aero.bombardier.com; Internet http://www.bombardier.com. You may view this referenced service information at 
the FAA, Transport Airplane Directorate, 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-2015-
3986; 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 proposed AD, 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 Branch, ANE-171, FAA, New York Aircraft 
Certification Office, 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-2015-3986; 
Directorate Identifier 2015-NM-057-AD'' at the beginning of your 
comments. We specifically invite comments on the overall regulatory,

[[Page 63148]]

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 substantive verbal contact we 
receive about this proposed AD.

Discussion

    Transport Canada Civil Aviation (TCCA), which is the aviation 
authority for Canada, has issued Canadian Airworthiness Directive CF-
2014-45, dated December 23, 2014 (referred to after this as the 
Mandatory Continuing Airworthiness Information, or ``the MCAI''), to 
correct an unsafe condition on certain Bombardier, Inc. Model DHC-8-
400, -401, and -402 airplanes. The MCAI states:

    The aeroplane manufacturer has discovered that an insufficient 
fillet radius may exist on the flange of the nacelle A-frame 
structure on certain aeroplanes. There have also been several in-
service reports of chafing damage on the main landing gear (MLG) 
stabilizer brace, the nacelle A-frame structure and its adjacent 
electrical wiring harnesses due to insufficient clearance.
    An insufficient fillet radius and chafing damage on the nacelle 
A-frame structure and MLG stabilizer brace could lead to premature 
cracking. Fracture of the nacelle A-frame structure or failure of 
the MLG stabilizer brace could adversely affect the safe landing of 
the aeroplane. The damage to the electrical wiring harnesses could 
result in the loss of the MLG downlock indication.
    This [Canadian] AD mandates the inspection and rework of the 
nacelle A-frame structure, and the rework of the forward MLG 
stabilizer brace assembly and the electrical harnesses in the 
nacelle area adjacent to the A-frame structure.

    Required actions include, depending on airplane configuration, the 
following actions:
     A detailed inspection of the nacelle A-frame structure for 
insufficient fillet radius, an eddy current or fluorescent dye 
penetrant inspection for cracking of affected structure, and rework or 
repair if necessary.
     Rework of the left-hand (LH) side and right-hand (RH) side 
nacelle A-frame structure, including doing a measurement of the 
clearance between the fasteners/A-frame structure and MLG stabilizer 
brace assembly and making sure no fouling condition exists, and repair 
if necessary.
     Repetitive detailed inspections of the nacelle A-frame 
structure and the MLG stabilizer brace for insufficient clearance and 
damage, and repair if necessary.
     Rework of the nacelle A-frame structure, including a 
measurement of the clearance between the A-frame structure and MLG 
stabilizer brace assembly and a fluorescent dye penetrant inspection or 
high frequency eddy current inspection for cracking and repair if 
necessary, which would terminate the repetitive inspections.
     Installation of new stop brackets and a shim on each MLG 
stabilizer brace assembly.
     Rework of the electrical wiring harnesses in the nacelle 
area. The rework includes a detailed inspection of the conduit assembly 
for certain conditions and repair if any condition is found, 
replacement of damaged conduit, a measurement of the clearance between 
the stabilizer brace and electrical harness on both LH and RH nacelles 
to make sure there is 0.100 inch (2.54 millimeters (mm)) minimum 
clearance between the MLG stabilizer brace, and a check for damage on 
the A-frame structure and MLG stabilizer brace and repair if necessary.

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-2015-
3986.

Related Service Information Under 1 CFR Part 51

    Bombardier has issued the following service information.
     ModSum IS4Q2400028, Revision B, dated June 22, 2012; and 
ModSum IS4Q240029, Revision A, dated July 6, 2014. These modsums 
describe procedures for rerouting certain electrical harnesses and 
installing grommets.
     ModSum IS4Q5450002, Revision B, dated April 30, 2012. This 
modsum describes procedures for installing specified fasteners on the 
MLG A-frame, in both the LH and RH nacelles.
     ModSum IS4Q5450003, Revision C, released November 29, 
2012. This modsum describes procedures for trimming the horizontal and 
vertical stiffeners on the MLG A frame in both the LH and RH nacelles.
     Service Bulletin 84-32-112, Revision B, dated September 
12, 2014, and Goodrich Service Bulletin 46400-32-102R1, Revision 1, 
dated June 24, 2013, as referenced in Bombardier Service Bulletin 84-
32-112, Revision B, dated September 12, 2014. This service information 
describes procedures for incorporating Bombardier ModSum 4-902416 by 
installing new stop brackets and new stop shims for all MLG stabilizer 
brace assemblies.
     Service Bulletin 84-32-114, Revision A, dated September 
18, 2013. This service information describes procedures for rework of 
the electrical wiring harnesses in the nacelle area. The rework 
includes a detailed inspection of the conduit assembly for certain 
conditions and repair, replacement of damaged conduit, a measurement of 
the clearance to make sure there is 0.100 inch (2.54 mm) minimum 
clearance between the MLG stabilizer brace, and a check for damage on 
the A-frame structure and MLG stabilizer brace and repair.
     Service Bulletin 84-54-19, dated April 18, 2013. This 
service information describes procedures for detailed inspections of 
the nacelle A-frame structure for insufficient fillet radius, an eddy 
current or fluorescent dye penetrant inspection for cracking of 
affected structure, and rework or repair.
     Service Bulletin 84-54-20, Revision B, dated October 2, 
2014. This service information describes procedures for detailed 
inspections of the nacelle A-frame structure and the MLG stabilizer 
brace for insufficient clearance and damage, and repair. This service 
information also describes procedures for rework of the nacelle A-frame 
structure, including a measurement of the clearance between the A-frame 
structure and MLG stabilizer brace assembly, and a fluorescent dye 
penetrant inspection or high frequency eddy current inspection for 
cracking and repair, which would end the inspections.
     Service Bulletin 84-54-21, dated May 9, 2013. This service 
information describes procedures for rework of the LH side and RH side 
nacelle A-frame structure, including a measurement of the clearance 
between the fasteners/A-frame structure and MLG stabilizer brace 
assembly and to make sure no fouling condition exists, and repair.
    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 of this 
NPRM.

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

[[Page 63149]]

develop on other products of the same type design.

Costs of Compliance

    We estimate that this proposed AD affects 80 airplanes of U.S. 
registry.
    We also estimate that it would take up to 50 work-hours per product 
to comply with the basic requirements of this proposed AD. The average 
labor rate is $85 per work-hour. Required parts would cost $8,452 per 
product. Based on these figures, we estimate the cost of this proposed 
AD on U.S. operators to be up to $1,016,160, or $12,702 per product.
    We have received no definitive data that would enable us to provide 
cost estimates for the on-condition actions specified in this proposed 
AD.

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.

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-2015-3986; Directorate 
Identifier 2015-NM-057-AD.

(a) Comments Due Date

    We must receive comments by December 3, 2015.

(b) Affected ADs

    None.

(c) Applicability

    This AD applies to Bombardier, Inc. Model DHC-8-400, -401, and -
402 airplanes, certificated in any category, serial numbers (S/Ns) 
4001 through 4431 inclusive.

(d) Subject

    Air Transport Association (ATA) of America Code 32, Landing 
Gear.

(e) Reason

    This AD was prompted by reports of chafing damage due to 
insufficient clearance on the main landing gear (MLG) stabilizer 
brace, the nacelle A-frame structure, and the adjacent electrical 
wiring harnesses. An insufficient fillet radius might also exist on 
certain airplanes. We are issuing this AD to detect and correct 
chafing damage and subsequent premature cracking and fracture of the 
nacelle A-frame structure, which could result in failure of the MLG 
stabilizer brace and loss of the MLG down-lock indication, which 
could adversely affect the safe landing of the airplane.

(f) Compliance

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

(g) Inspection, Corrective Actions if Necessary, and Rework

    For airplanes having S/Ns 4001 through 4055 inclusive: Do the 
actions required by paragraphs (g)(1) and (g)(2) of this AD.
    (1) Within 600 flight hours or 100 days after the effective date 
of this AD, whichever occurs first: Do a detailed inspection of the 
left-hand (LH) side and right-hand (RH) side nacelle A-frame 
structure for insufficient fillet radius, in accordance with ``Part 
A--Inspection'' of the Accomplishment Instructions of Bombardier 
Service Bulletin 84-54-19, dated April 18, 2013. If an insufficient 
fillet radius exists, before further flight, do an eddy current or 
fluorescent dye penetrant inspection for cracking, in accordance 
with ``Part A--Inspection'' of the Accomplishment Instructions of 
Bombardier Service Bulletin 84-54-19, dated April 18, 2013.
    (i) If any cracking is found: Before further flight, repair 
using a method approved by the Manager, New York ACO, ANE-170, FAA; 
or Transport Canada Civil Aviation (TCCA); or Bombardier, Inc.'s 
TCCA Design Approval Organization (DAO).
    (ii) If no cracking is found: Before further flight, rework the 
structure, in accordance ``Part B--Rectification'' of the 
Accomplishment Instructions of Bombardier Service Bulletin 84-54-19, 
dated April 18, 2013.
    (2) Within 6,000 flight hours or 36 months after the effective 
date of this AD, whichever occurs first: Rework the LH side and RH 
side nacelle A-frame structure, including doing a measurement of the 
clearance between the fasteners/A-frame structure and MLG stabilizer 
brace assembly and making sure no fouling condition exists, in 
accordance with paragraph 3.B. ``Procedure,'' of the Accomplishment 
Instructions of Bombardier Service Bulletin 84-54-21, dated May 9, 
2013. If the clearance is found to be less than 0.100 inch (2.54 
millimeters (mm)) between the fasteners/A-frame structure and MLG 
stabilizer brace assembly after the rework is done, or a fouling 
condition exists during the extension of the MLG after rework is 
done, before further flight, repair using a method approved by the 
Manager, New York ACO, ANE-170, FAA; or TCCA; or Bombardier, Inc.'s 
TCCA DAO.

(h) Repetitive Inspections and Corrective Actions if Necessary

    For airplanes having S/Ns 4056 through 4426 inclusive: Within 
600 flight hours or 100 days after the effective date of this AD, 
whichever occurs first: Do a detailed inspection of the LH side and 
RH side nacelle A-frame structure and upper surface of the MLG 
stabilizer brace for insufficient clearance and damage (e.g., 
cracking), in accordance with ``Part A--Inspection,'' of the 
Accomplishment Instructions of Bombardier Service Bulletin 84-54-20, 
Revision B, dated October 2, 2014. If no damage is found and 
clearance is sufficient: Repeat the inspection thereafter at 
intervals not to exceed 600 flight hours until the terminating 
action required by paragraph (i) of this AD has been done.
    (1) If a clearance less than 0.100 inch (2.54 mm) exists between 
the A-frame structure and the MLG stabilizer brace assembly in the 
retracted position, after the rework is done, before further flight, 
repair using a method approved by the Manager, New York ACO, ANE-
170, FAA; or TCCA; or Bombardier, Inc.'s TCCA DAO.
    (2) If any damage is found: Before further flight, repair using 
a method approved by the

[[Page 63150]]

Manager, New York ACO, ANE-170, FAA; or TCCA; or Bombardier, Inc.'s 
TCCA DAO.

(i) Terminating Action for Certain Airplanes

    For airplanes having S/Ns 4056 through 4426 inclusive: Within 
6,000 flight hours or 36 months after the effective date of this AD, 
whichever occurs first; Rework the LH side and RH side nacelle A-
frame structure, including doing a measurement of the clearance 
between the A-frame structure and MLG stabilizer brace assembly and 
doing a fluorescent dye penetrant inspection or high frequency eddy 
current inspection for cracking, in accordance with ``Part B-
Rework,'' of the Accomplishment Instructions of Bombardier Service 
Bulletin 84-54-20, Revision B, dated October 2, 2014. Accomplishment 
of the actions required by this paragraph terminates the repetitive 
inspections required by paragraph (h) of this AD.
    (1) If a clearance less than 0.100 inch (2.54 mm) exists between 
the A-frame structure and the MLG stabilizer brace assembly in the 
retracted position after the rework is done, before further flight, 
repair using a method approved by the Manager, New York ACO, ANE-
170, FAA; or TCCA; or Bombardier, Inc.'s TCCA DAO.
    (2) If any cracking is found: Before further flight, repair 
using a method approved by the Manager, New York ACO, ANE-170, FAA; 
or TCCA; or Bombardier, Inc.'s TCCA DAO.

(j) Modification of MLG Stabilizer Brace Assembly

    For airplanes having S/Ns 4001 through 4431 inclusive with a MLG 
stabilizer brace assembly having part number 46400-27 installed: 
Within 6,000 flight hours or 36 months after the effective date of 
this AD, whichever occurs first; incorporate Bombardier ModSum 4-
902416 by installing new stop brackets and a new shim on each MLG 
stabilizer brace assembly, in accordance with the Accomplishment 
Instructions of Bombardier Service Bulletin 84-32-112, Revision B, 
dated September 12, 2014, and Goodrich Service Bulletin 46400-32-
102R1, Revision 1, dated June 24, 2013, as referenced in Bombardier 
Service Bulletin 84-32-112, Revision B, dated September 12, 2014.

(k) Rework of the Electrical Wiring Harnesses

    For airplanes having S/Ns 4001 through 4411 inclusive: Within 
6,000 flight hours or 36 months after the effective date of this AD, 
whichever occurs first; rework the LH and RH sides of the electrical 
wiring harnesses in the nacelle area adjacent to the A-frame 
structure, including doing the actions specified in paragraphs 
(k)(1) through (k)(4) of this AD, in accordance with the 
Accomplishment Instructions of Bombardier Service Bulletin 84-32-
114, Revision A, dated September 18, 2013. If any damage is found on 
the A-frame structure or MLG stabilizer brace, before further 
flight, repair using a method approved by the Manager, New York ACO, 
ANE-170, FAA; or TCCA; or Bombardier, Inc.'s TCCA DAO.
    (1) Doing a detailed inspection of the conduit assembly for the 
conditions specified in Bombardier Service Bulletin 84-32-114, 
Revision A, dated September 18, 2013, and, before further flight, 
repairing if any condition is found.
    (2) Replacing damaged conduit.
    (3) Measuring the clearance between the stabilizer brace and 
electrical harness on both LH and RH nacelles to make sure there is 
0.100 inch (2.54 mm) minimum clearance between the MLG stabilizer 
brace.
    (4) Checking for damage on the A-frame structure and MLG 
stabilizer brace.

(l) Optional Installations

    (1) Installing specified fasteners on the MLG A-frame, in both 
LH and RH nacelles, in accordance with Bombardier ModSum 
IS4Q5450002, Revision B, dated April 30, 2012, is acceptable for 
compliance with the actions specified in paragraph (g) of this AD, 
provided the actions specified in Bombardier ModSum IS4Q5450002 are 
done within the compliance time specified in paragraph (g) of this 
AD, except where ModSum IS4Q5450002, Revision B, dated April 30, 
2012, specifies to contact Bombardier for reduced clearances, before 
further flight, repair using a method approved by the Manager, New 
York ACO, ANE-170, FAA; or TCCA; or Bombardier, Inc.'s TCCA DAO.
    (2) Trimming the horizontal and vertical stiffeners on MLG A-
frame in both LH and RH nacelles, in accordance with Bombardier 
ModSum IS4Q5450003, Revision C, released November 29, 2012, is 
acceptable for compliance with the actions specified in paragraph 
(i) of this AD, provided the actions specified in Bombardier ModSum 
IS4Q5450003 are done within the compliance time specified in 
paragraph (i) of this AD, except where ModSum IS4Q5450003, Revision 
C, released November 29, 2012, specifies to contact Bombardier for 
reduced clearances, before further flight, repair using a method 
approved by the Manager, New York ACO, ANE-170, FAA; or TCCA; or 
Bombardier, Inc.'s TCCA DAO.
    (3) Rerouting certain electrical harnesses and installing 
grommets, in accordance with Bombardier ModSum IS4Q2400028, Revision 
B, dated June 22, 2012 (for S/Ns 4001 through 4098 inclusive) or 
Bombardier ModSum IS4Q2400029, Revision A, dated July 6, 2014 (for 
S/Ns 4090 through 4411 inclusive), is acceptable for compliance with 
the actions specified in paragraph (k) of this AD, provided the 
actions specified in the applicable modsum are done within the 
compliance time specified in paragraph (k) of this AD, except where 
Bombardier ModSum IS4Q2400028, Revision B, dated June 22, 2012; and 
Bombardier ModSum IS4Q2400029, Revision A, dated July 6, 2014; 
specify to contact Bombardier to report stabilizer brace or 
structural damaged findings, before further flight, repair using a 
method approved by the Manager, New York ACO, ANE-170, FAA; or TCCA; 
or Bombardier, Inc.'s TCCA DAO.

(m) Credit for Previous Actions

    (1) This paragraph provides credit for actions required by 
paragraph (i) of this AD, if those actions were performed before the 
effective date of this AD using the applicable service information 
specified in paragraph (m)(1)(i) or (m)(1)(ii) of this AD. This 
service information is not incorporated by reference in this AD.
    (i) Bombardier Service Bulletin 84-54-20, dated April 25, 2013.
    (ii) Bombardier Service Bulletin 84-54-20, Revision A, dated 
April 9, 2014.
    (2) This paragraph provides credit for actions required by 
paragraph (j) of this AD, if those actions were performed before the 
effective date of this AD using the applicable service information 
specified in paragraph (m)(2)(i) or (m)(2)(ii) of this AD. This 
service information is not incorporated by reference in this AD.
    (i) Bombardier Service Bulletin 84-32-112, dated December 20, 
2012.
    (ii) Bombardier Service Bulletin 84-32-112, Revision A, dated 
April 16, 2014.
    (3) This paragraph provides credit for actions required by 
paragraph (k) of this AD, if those actions were performed before the 
effective date of this AD using Bombardier Service Bulletin 84-32-
114, dated June 6, 2013. This service information is not 
incorporated by reference in this AD.

(n) Other FAA AD Provisions

    The following provisions also apply to this AD:
    (1) Alternative Methods of Compliance (AMOCs): The Manager, New 
York ACO, ANE-170, 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 ACO, send it to ATTN: Program 
Manager, Continuing Operational Safety, FAA, New York ACO, 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. The AMOC approval letter must 
specifically reference this AD.
    (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, 
ANE-170, FAA; or TCCA; or Bombardier, Inc.'s TCCA DAO. If approved 
by the DAO, the approval must include the DAO-authorized signature.

(o) Related Information

    (1) Refer to Mandatory Continuing Airworthiness Information 
(MCAI) Canadian Airworthiness Directive CF-2014-45, dated December 
23, 2014, 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-2015-3986.
    (2) For service information identified in this AD, contact 
Bombardier, Inc., Q-Series Technical Help Desk, 123 Garratt 
Boulevard, Toronto, Ontario M3K 1Y5, Canada; telephone 416-375-4000; 
fax 416-375-4539; email thd.qseries@aero.bombardier.com; Internet 
http://www.bombardier.com. You may view this service information at 
the FAA, Transport Airplane Directorate, 1601

[[Page 63151]]

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

    Issued in Renton, Washington, on October 5, 2015.
Jeffrey E. Duven,
Manager, Transport Airplane Directorate, Aircraft Certification 
Service.
[FR Doc. 2015-26217 Filed 10-16-15; 8:45 am]
 BILLING CODE 4910-13-P
```