[Federal Register Volume 81, Number 76 (Wednesday, April 20, 2016)]
[Proposed Rules]
[Pages 23202-23206]
From the Federal Register Online via the Government Publishing Office [www.gpo.gov]
[FR Doc No: 2016-08960]


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DEPARTMENT OF TRANSPORTATION

Federal Aviation Administration

14 CFR Part 39

[Docket No. FAA-2016-5593; Directorate Identifier 2015-NM-184-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) 2015-02-
23, for certain Bombardier, Inc. Model CL-600-1A11 (CL-600), CL-600-
2A12 (CL-601), and CL-600-2B16 (CL-601-3A, and CL-601-3R Variants) 
airplanes. AD 2015-02-23 currently requires repetitive inspections for 
fractured or incorrectly oriented fasteners on the inboard flap hinge-
box forward fittings on both wings, and replacement of all fasteners if 
necessary. The preamble to AD 2015-02-23 explains that we consider the 
requirements interim action and are considering further rulemaking. We 
now have determined that further rulemaking is indeed necessary, and 
that replacement of the fasteners is necessary. This proposed AD would 
require terminating action to replace the fasteners on the inboard flap 
hinge-box forward fittings on both wings. We are proposing this AD to 
detect and correct incorrectly oriented or fractured fasteners, which 
could result in detachment of the flap hinge-box and the flap surface, 
and consequent reduced controllability of the airplane.

DATES: We must receive comments on this proposed AD by June 6, 2016.

ADDRESSES: You may send comments 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 NPRM, contact 
Bombardier, Inc., 400 C[ocirc]te-Vertu Road West, Dorval, Qu[eacute]bec 
H4S 1Y9, Canada; telephone 514-855-5000; fax 514-855-7401; email 
[email protected]; 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-2016-
5593; 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:

[[Page 23203]]

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-2016-5593; 
Directorate Identifier 2015-NM-184-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 substantive verbal contact we 
receive about this proposed AD.

Discussion

    On January 20, 2015, we issued AD 2015-02-23, Amendment 39-18092 
(80 FR 5670, February 3, 2015) (``AD 2015-02-23''). AD 2015-02-23 
requires actions intended to address an unsafe condition on certain 
Bombardier, Inc. Model CL-600-1A11 (CL-600), CL-600-2A12 (CL-601), and 
CL-600-2B16 (CL-601-3A, and CL-601-3R Variants) airplanes. AD 2015-02-
23 corresponds to Canadian Emergency Airworthiness Directive CF-2013-
39R2, dated December 12, 2014 (referred to after this as the Mandatory 
Continuing Airworthiness Information, or ``the MCAI''). The MCAI was 
issued by Transport Canada Civil Aviation (TCCA), which is the aviation 
authority for Canada.
    The preamble to AD 2015-02-23 explains that we consider the 
requirements interim action and are considering further rulemaking. We 
have now determined that further rulemaking is indeed necessary and 
that, instead of continuing repetitive inspections, replacement of the 
incorrectly oriented fasteners is necessary. This proposed AD follows 
from that determination. This proposed AD would require terminating 
action to replace the fasteners on the inboard flap hinge-box forward 
fittings on affected wings.
    The repetitive inspections can only detect if a fastener head has 
fractured and sheared off. For incorrectly oriented fasteners, it is 
not possible to detect whether a crack has already initiated and 
propagated. The fastener fracture speed is unpredictable due to the 
variability in the quality of the hole preparation prior to fastener 
installation and whether there was any misalignment in the installation 
of the fasteners. The failure of two fasteners could result in the loss 
of the flap attachment, causing flap asymmetry and consequent reduced 
controllability of the airplane.
    We are proposing this AD to detect and correct incorrectly oriented 
or fractured fasteners, which could result in detachment of the flap 
hinge-box and the flap surface, and consequent reduced controllability 
of the airplane.

Related Service Information Under 1 CFR Part 51

    Bombardier has issued Alert Service Bulletins A600-0763, Revision 
02, dated December 9, 2014, including Appendices 1 and 2, dated 
September 26, 2013; and A601-0627, Revision 02, dated December 9, 2014, 
including Appendices 1 and 2, dated September 26, 2013. The service 
information describes procedures for repetitive inspections of the 
fasteners on the inboard flap hinge-box forward fittings on both wings, 
and replacement of fasteners. 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 designs.

Clarification of Intent of the MCAI

    Paragraph C. of Canadian Emergency AD CF-2013-39R2, dated December 
12, 2014, specifies to do the replacement on ``both'' wings. We have 
clarified with TCCA that the intent of paragraph C. of Canadian 
Emergency AD CF-2013-39R2, dated December 12, 2014, is that for 
airplanes on which any incorrectly oriented fastener, and no fractured 
or missing fastener, was detected, the replacement only needs to be 
done on the affected wing on which incorrectly oriented fasteners were 
found but none were found to be fractured.
    The replacement of all forward and aft fasteners, regardless of 
condition or orientation, at wing station (WS) 76.50 and WS 127.25, on 
the affected wings, constitutes terminating action. Fasteners that have 
cracks or fractures were already addressed by the requirements of AD 
2015-02-13, which is restated in this proposed AD.

Costs of Compliance

    We estimate that this proposed AD affects 120 airplanes of U.S. 
registry.
    The actions required by AD 2015-02-23, and retained in this 
proposed AD, take about 1 work-hour per product, at an average labor 
rate of $85 per work-hour. Based on these figures, the estimated cost 
of the actions that are required by AD 2015-02-23 is $85 per product.
    We also estimate that it would take about 59 work-hours per product 
to comply with the basic requirements of this proposed AD. The average 
labor rate is $85 per work-hour. We have received no definitive data 
that would enable us to provide cost estimates for the parts cost. 
Based on these figures, we estimate the cost of this proposed AD on 
U.S. operators to be $601,800, or $5,015 per product.
    In addition, we estimate that any necessary follow-on actions will 
take about 58 work-hours and require parts costing $753, for a cost of 
$5,683 per product. We have no way of determining the number of 
aircraft that might need this action.
    According to the manufacturer, some of the costs of this proposed 
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 available 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.

[[Page 23204]]

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) 
2015-02-23, Amendment 39-18092 (80 FR 5670, February 3, 2015), and 
adding the following new AD:

Bombardier, Inc.: Docket No. FAA-2016-5593; Directorate Identifier 
2015-NM-184-AD.

(a) Comments Due Date

    We must receive comments by June 6, 2016.

(b) Affected ADs

    This AD replaces AD 2015-02-23, Amendment 39-18092 (80 FR 5670, 
February 3, 2015) (``AD 2015-02-23''). This AD affects AD 2014-03-
17, Amendment 39-17754 (79 FR 9389, February 19, 2014) (``AD 2014-
03-17'').

(c) Applicability

    This AD applies to the Bombardier, Inc. airplanes identified in 
paragraphs (c)(1), (c)(2), and (c)(3) of this AD, certificated in 
any category.
    (1) Bombardier, Inc. Model CL-600-1A11 (CL-600) airplanes, 
having serial numbers (S/Ns) 1004 through 1085 inclusive.
    (2) Bombardier, Inc. Model CL-600-2A12 (CL-601) airplanes, 
having S/Ns 3001 through 3066 inclusive.
    (3) Bombardier, Inc. Model CL-600-2B16 (CL-601-3A and CL-601-3R 
Variants) airplanes, having S/Ns 5001 through 5194 inclusive.

(d) Subject

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

(e) Reason

    This AD was prompted by reports of incorrectly oriented 
fasteners. We are issuing this AD to detect and correct incorrectly 
oriented or fractured fasteners, which could result in detachment of 
the flap hinge-box and the flap surface, and consequent reduced 
controllability of the airplane.

(f) Compliance

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

(g) Retained Inspection on Airplanes Not Previously Inspected, With No 
Changes

    This paragraph restates the requirements of paragraph (g) of AD 
2015-02-23, with no changes. For airplanes that have not been 
inspected as required by paragraph (g) of AD 2014-03-17, as of 
February 18, 2015 (the effective date of AD 2015-02-23): Within 10 
flight cycles after February 18, 2015, or 100 flight cycles after 
March 6, 2014 (the effective date of AD 2014-03-17), whichever 
occurs first, do a detailed visual inspection for incorrect 
orientation and any fractured or missing fastener heads of each 
inboard flap fastener of the hinge-box forward fitting at wing 
station (WS) 76.50 and WS 127.25, on both wings, in accordance with 
the Accomplishment Instructions of the applicable service 
information specified in paragraphs (g)(1) and (g)(2) of this AD. 
Accomplishing the inspection required by this paragraph terminates 
the requirements of paragraph (g) of AD 2014-03-17 for the inspected 
airplane only.
    (1) For Model CL-600-1A11 (CL-600) airplanes having S/Ns 1004 
through 1085 inclusive: Bombardier Alert Service Bulletin A600-0763, 
Revision 02, dated December 9, 2014, including Appendices 1 and 2, 
dated September 26, 2013.
    (2) For Model CL-600-2A12 (CL-601) airplanes having S/Ns 3001 
through 3066 inclusive, and Model CL-600-2B16 (CL-601-3A and CL-601-
3R Variants) airplanes having S/Ns 5001 through 5194 inclusive: 
Bombardier Alert Service Bulletin A601-0627, Revision 02, dated 
December 9, 2014, including Appendices 1 and 2, dated September 26, 
2013.

(h) Retained Corrective Actions for Paragraph (g) of This AD, With 
Revised Paragraph (h)(2) of This AD

    (1) This paragraph restates the requirements of paragraph (h)(1) 
of AD 2015-02-23, with no changes. If, during any inspection 
required by paragraph (g) of this AD, all fasteners are found 
correctly oriented and not fractured, and no fastener heads are 
missing (fasteners found intact): No further action is required by 
this AD.
    (2) This paragraph restates the requirements of paragraph (h)(2) 
of AD 2015-02-23, with revised references to replacement paragraphs. 
If, during any inspection required by paragraph (g) of this AD, any 
fastener is found incorrectly oriented but no fasteners are 
fractured or are missing a fastener head (fasteners found intact), 
repeat the inspection required by paragraph (g) of this AD 
thereafter at intervals not to exceed 10 flight cycles until the 
replacements specified in paragraph (h)(3), (k), or (n) of this AD 
is accomplished.
    (3) This paragraph restates the requirements of paragraph (h)(3) 
of AD 2015-02-23, with no changes. If, during any inspection 
required by paragraph (g) of this AD, any fastener is found 
fractured or has a missing fastener head: Before further flight, 
remove and replace all forward and aft fasteners (regardless of 
orientation or condition) at WS 76.50 and WS 127.25, on both wings, 
in accordance with the Accomplishment Instructions of the applicable 
service information specified in paragraphs (h)(3)(i) and (h)(3)(ii) 
of this AD, except as required by paragraph (m) of this AD. After 
accomplishing the replacements required by this paragraph, no 
further action is required by this AD.
    (i) For Model CL-600-1A11 (CL-600) airplanes having S/Ns 1004 
through 1085 inclusive: Bombardier Alert Service Bulletin A600-0763, 
Revision 02, dated December 9, 2014, including Appendices 1 and 2, 
dated September 26, 2013.
    (ii) For Model CL-600-2A12 (CL-601) airplanes having S/Ns 3001 
through 3066 inclusive, and Model CL-600-2B16 (CL-601-3A and CL-601-
3R Variants) airplanes having S/Ns 5001 through 5194 inclusive: 
Bombardier Alert Service Bulletin A601-0627, Revision 02, dated 
December 9, 2014, including Appendices 1 and 2, dated September 26, 
2013.

(i) Retained Inspection for Airplanes Previously Inspected and Found To 
Have Incorrectly Oriented Fastener(s), With No Changes

    This paragraph restates the requirements of paragraph (i) of AD 
2015-02-23, with no changes. For airplanes on which an inspection 
required by paragraph (g) or (j) of AD 2014-03-17, has been done as 
of the effective date of this AD, and on which any incorrectly 
oriented fastener was found but no fasteners were fractured 
(fasteners found intact): Except as provided by paragraph (l) of 
this AD, within 10 flight cycles after February 18, 2015 (the 
effective date of AD 2015-02-23), or within 100 flight cycles after 
accomplishing the most recent inspection required by AD 2014-03-17, 
whichever occurs first, do a detailed visual inspection for any 
fractured or missing fastener heads of each inboard flap fastener of 
the hinge-box forward fitting at WS 76.50 and WS 127.25, on both 
wings. Do the inspection in accordance with the Accomplishment 
Instructions of the applicable service information specified in 
paragraphs (i)(1) and (i)(2) of this AD. Accomplishing the

[[Page 23205]]

inspection required by this paragraph terminates the requirements of 
paragraphs (g) and (j) of AD 2014-03-17 for the inspected airplane 
only.
    (1) For Model CL-600-1A11 (CL-600) airplanes having S/Ns 1004 
through 1085 inclusive: Bombardier Alert Service Bulletin A600-0763, 
Revision 02, dated December 9, 2014, including Appendices 1 and 2, 
dated September 26, 2013.
    (2) For Model CL-600-2A12 (CL-601) airplanes having S/Ns 3001 
through 3066 inclusive, and Model CL-600-2B16 (CL-601-3A and CL-601-
3R Variants) airplanes having S/Ns 5001 through 5194 inclusive: 
Bombardier Alert Service Bulletin A601-0627, Revision 02, dated 
December 9, 2014, including Appendices 1 and 2, dated September 26, 
2013.

(j) Retained Corrective Actions for Paragraph (i) of This AD, With 
Revised Reference to Additional, New Requirements

    (1) This paragraph restates the requirements of paragraph (j)(1) 
of AD 2015-02-23, with revised reference to additional, new 
requirements. If, during any inspection required by paragraph (i) of 
this AD, no fasteners are found fractured or have missing fastener 
heads (fasteners are intact), repeat the inspection required by 
paragraph (i) of this AD thereafter at intervals not to exceed 10 
flight cycles until the replacement specified in paragraph (j)(2), 
(k), or (n) of this AD is accomplished.
    (2) This paragraph restates the requirements of paragraph (j)(2) 
of AD 2015-02-23, with no changes. If, during any inspection 
required by paragraph (i) of this AD, any fastener is found 
fractured or has a missing fastener head: Before further flight, 
remove and replace all forward and aft fasteners (regardless of 
orientation or condition) at WS 76.50 and WS 127.25, on both wings, 
in accordance with the Accomplishment Instructions of the applicable 
service information specified in paragraphs (j)(2)(i) and (j)(2)(ii) 
of this AD, except as required by paragraph (m) of this AD. After 
accomplishing the replacements required by this paragraph, no 
further action is required by this AD.
    (i) For Model CL-600-1A11 (CL-600) airplanes having S/Ns 1004 
through 1085 inclusive: Bombardier Alert Service Bulletin A600-0763, 
Revision 02, dated December 9, 2014, including Appendices 1 and 2, 
dated September 26, 2013.
    (ii) For Model CL-600-2A12 (CL-601) airplanes having S/Ns 3001 
through 3066 inclusive, and Model CL-600-2B16 (CL-601-3A and CL-601-
3R Variants) airplanes having S/Ns 5001 through 5194 inclusive: 
Bombardier Alert Service Bulletin A601-0627, Revision 02, dated 
December 9, 2014, including Appendices 1 and 2, dated September 26, 
2013.

(k) Retained Optional Terminating Action for Incorrectly Oriented 
Fasteners, With No Changes

    This paragraph restates the provisions of paragraph (k) of AD 
2015-02-23, with no changes. Replacement of all forward and aft 
fasteners (regardless of orientation or condition) at WS 76.50 and 
WS 127.25, on both wings, terminates the requirements of this AD. 
The replacement must be done in accordance with the Accomplishment 
Instructions of the applicable service information specified in 
paragraphs (k)(1) and (k)(2) of this AD, except as provided by 
paragraph (m) of this AD. Doing the replacements specified in this 
paragraph terminates the requirements of paragraphs (g) and (j) of 
AD 2014-03-17, only for the airplane on which the replacement was 
done.
    (1) For Model CL-600-1A11 (CL-600) airplanes having S/Ns 1004 
through 1085 inclusive: Bombardier Alert Service Bulletin A600-0763, 
Revision 02, dated December 9, 2014, including Appendices 1 and 2, 
dated September 26, 2013.
    (2) For Model CL-600-2A12 (CL-601) airplanes having S/Ns 3001 
through 3066 inclusive, and Model CL-600-2B16 (CL-601-3A and CL-601-
3R Variants) airplanes having S/Ns 5001 through 5194 inclusive: 
Bombardier Alert Service Bulletin A601-0627, Revision 02, dated 
December 9, 2014, including Appendices 1 and 2, dated September 26, 
2013.

(l) Retained Exception for Previously Replaced Fasteners, With No 
Changes

    This paragraph restates the provisions of paragraph (l) of AD 
2015-02-23, with no changes. Replacement of all fractured and 
incorrectly oriented forward and aft fasteners, as specified in 
paragraph (i) or (k) of AD 2014-03-17, if done before the effective 
date of this AD, is considered acceptable for compliance with the 
requirements of this AD.

(m) Retained Exception to the Service Information, With No Changes

    This paragraph restates the requirements of paragraph (m) of AD 
2015-02-23, with no changes. Where Bombardier Alert Service Bulletin 
A600-0763, Revision 02, dated December 9, 2014, including Appendices 
1 and 2, dated September 26, 2013; and Bombardier Alert Service 
Bulletin A601-0627, Revision 02, dated December 9, 2014, including 
Appendices 1 and 2, dated September 26, 2013; specify to contact 
Bombardier for repair instructions, before further flight, repair 
using a method approved by the Manager, New York Aircraft 
Certification Office (ACO), FAA; or Transport Canada Civil Aviation 
(TCCA); or Bombardier's TCCA Design Approval Organization (DAO).

(n) New Requirement of This AD: Terminating Action

    For airplanes on which any incorrectly oriented fastener, and no 
fractured or missing fastener, was detected during any inspection 
required by paragraph (g), (h)(2), (i), and (j)(1) of this AD: 
Within 24 months after the effective date of this AD, replace all 
forward and aft fasteners, regardless of condition or orientation, 
at WS 76.50 and WS 127.25, on affected wings, in accordance with the 
Accomplishment Instructions of the applicable service information 
specified in paragraphs (k)(1) and (k)(2) of this AD, except as 
provided by paragraph (m) of this AD. Doing the replacements 
specified in this paragraph terminates the requirements of this AD. 
Doing the replacements specified in this paragraph terminates the 
requirements of paragraphs (g) and (j) of AD 2014-03-17, only for 
the airplane on which the replacement was done.

(o) Credit for Previous Actions

    This paragraph restates the provisions of paragraph (n) of AD 
2015-02-23, with new credit for paragraph (n) of this AD. This 
paragraph provides credit for actions required by paragraphs (g), 
(h), (i), and (n) of this AD, if those actions were performed before 
the effective date of this AD using the applicable service 
information identified in paragraphs (o)(1) through (o)(4) of this 
AD.
    (1) Bombardier Alert Service Bulletin A600-0763, including 
Appendices 1 and 2, dated September 26, 2013, which was previously 
incorporated by reference on March 6, 2014 (79 FR 9389, February 19, 
2014).
    (2) Bombardier Alert Service Bulletin A600-0763, Revision 01, 
dated February 26, 2014, including Appendices 1 and 2, dated 
September 26, 2013, which is not incorporated by reference in this 
AD.
    (3) Bombardier Alert Service Bulletin A601-0627, including 
Appendices 1 and 2, dated September 26, 2013, which was previously 
incorporated by reference on March 6, 2014 (79 FR 9389, February 19, 
2014).
    (4) Bombardier Alert Service Bulletin A601-0627, Revision 01, 
dated February 26, 2014, including Appendices 1 and 2, dated 
September 26, 2013, which is not incorporated by reference in this 
AD.

(p) 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, Engine and Propeller Directorate, FAA; or TCCA; or 
Bombardier, Inc.'s TCCA DAO. If approved by the DAO, the approval 
must include the DAO-authorized signature.

(q) Related Information

    (1) Refer to Mandatory Continuing Airworthiness Information 
(MCAI) Canadian Emergency Airworthiness Directive CF-2013-39R2, 
dated December 12, 2014, for related information. This MCAI may be

[[Page 23206]]

found in the AD docket on the Internet at http://www.regulations.gov 
by searching for and locating Docket No. FAA-2016-5593.
    (2) For service information identified in this AD, contact 
Bombardier, Inc., 400 C[ocirc]te-Vertu Road West, Dorval, 
Qu[eacute]bec H4S 1Y9, Canada; telephone 514-855-5000; fax 514-855-
7401; email [email protected]; Internet http://www.bombardier.com. You may view this 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.

    Issued in Renton, Washington, on April 8, 2016.
Michael Kaszycki,
Acting Manager, Transport Airplane Directorate, Aircraft Certification 
Service.
[FR Doc. 2016-08960 Filed 4-19-16; 8:45 am]
 BILLING CODE 4910-13-P