81 FR 79381 - Airworthiness Directives; Bombardier, Inc. Airplanes

DEPARTMENT OF TRANSPORTATION
Federal Aviation Administration

Federal Register Volume 81, Issue 219 (November 14, 2016)

We are superseding 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 required 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. This new AD also requires replacement of the fasteners, which terminates the requirements of this AD. This AD was prompted by reports of incorrectly oriented fasteners. We are issuing this AD to prevent 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.

[Federal Register Volume 81, Number 219 (Monday, November 14, 2016)]
[Rules and Regulations]
[Pages 79381-79384]
From the Federal Register Online  [www.thefederalregister.org]
[FR Doc No: 2016-25009]



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Federal Register / Vol. 81, No. 219 / Monday, November 14, 2016 / 
Rules and Regulations

[[Page 79381]]



DEPARTMENT OF TRANSPORTATION

Federal Aviation Administration

14 CFR Part 39

[Docket No. FAA-2016-5593; Directorate Identifier 2015-NM-184-AD; 
Amendment 39-18687; AD 2016-21-06]
RIN 2120-AA64


Airworthiness Directives; Bombardier, Inc. Airplanes

AGENCY: Federal Aviation Administration (FAA), Department of 
Transportation (DOT).

ACTION: Final rule.

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

SUMMARY: We are superseding 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 required 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. 
This new AD also requires replacement of the fasteners, which 
terminates the requirements of this AD. This AD was prompted by reports 
of incorrectly oriented fasteners. We are issuing this AD to prevent 
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: This AD is effective December 19, 2016.
    The Director of the Federal Register approved the incorporation by 
reference of certain publications listed in this AD as of February 18, 
2015 (80 FR 5670, February 3, 2015).

ADDRESSES: For service information identified in this final rule, 
contact Bombardier, Inc., 400 C[ocirc]te-Vertu Road West, Dorval, 
Qu[eacute]bec H4S 1Y9, Canada; Widebody Customer Response Center North 
America toll-free telephone: 1-866-538-1247 or direct-dial telephone: 
1-514-855-2999; fax 514-855-7401; email: [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. It is also available on 
the Internet at http://www.regulations.gov by searching for and 
locating Docket No. FAA-2016-5593.

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 AD, the regulatory evaluation, any comments received, and 
other information. The address for the Docket Office (telephone: 800-
647-5527) is Docket Management Facility, U.S. Department of 
Transportation, Docket Operations, M-30, West Building Ground Floor, 
Room W12-140, 1200 New Jersey Avenue SE., Washington, DC 20590.

FOR FURTHER INFORMATION CONTACT: Aziz Ahmed, Aerospace Engineer, 
Airframe and Mechanical Systems Branch, ANE-171, FAA, New York Aircraft 
Certification Office (ACO), 1600 Stewart Avenue, Suite 410, Westbury, 
NY 11590; telephone: 516-228-7329; fax: 516-794-5531.

SUPPLEMENTARY INFORMATION: 

Discussion

    We issued a notice of proposed rulemaking (NPRM) to amend 14 CFR 
part 39 to supersede AD 2015-02-23, Amendment 39-18092 (80 FR 5670, 
February 3, 2015) (``AD 2015-02-23''). AD 2015-02-23 applied to 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 
corresponded to Canadian Emergency AD 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 explained that we considered the 
requirements interim action and were considering further rulemaking. We 
have now determined that further rulemaking is indeed necessary and 
that, instead of continuing repetitive inspections, for airplanes which 
have any incorrectly oriented fastener, and no fractured or missing 
fastener, replacement of all forward and aft fasteners, regardless of 
condition or orientation, is necessary. This AD follows from that 
determination.
    The NPRM published in the Federal Register on April 20, 2016 (81 FR 
23202). The NPRM was prompted by reports of incorrectly oriented 
fasteners. The NPRM proposed to continue to require 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 NPRM also proposed to require 
replacement of the fasteners, which would terminate the requirements of 
this AD. We are issuing this AD to prevent 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.

Comments

    We gave the public the opportunity to participate in developing 
this AD. We received no comments on the NPRM or on the determination of 
the cost to the public.

Conclusion

    We reviewed the available data and determined that air safety and 
the public interest require adopting this AD as proposed except for 
minor editorial changes. We have determined that these minor changes:
     Are consistent with the intent that was proposed in the 
NPRM for correcting the unsafe condition; and
     Do not add any additional burden upon the public than was 
already proposed in the NPRM.

[[Page 79382]]

Related Service Information Under 1 CFR Part 51

    Bombardier has issued Alert Service Bulletins A600-0763, Revision 
02, dated December 9, 2014, including Appendixes 1 and 2, dated 
September 26, 2013; and A601-0627, Revision 02, dated December 9, 2014, 
including Appendixes 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. These documents are distinct since they 
apply to different airplane models. This service information is 
reasonably available because the interested parties have access to it 
through their normal course of business or by the means identified in 
the ADDRESSES section.

Costs of Compliance

    We estimate that this AD affects 120 airplanes of U.S. registry.
    The actions required by AD 2015-02-23, and retained in this 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 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 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 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.

Regulatory Findings

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

List of Subjects in 14 CFR Part 39

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

Adoption of the Amendment

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

PART 39--AIRWORTHINESS DIRECTIVES

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

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


Sec.  39.13   [Amended]

0
2. The FAA amends Sec.  39.13 by removing Airworthiness Directive (AD) 
2015-02-23, Amendment 39-18092 (80 FR 5670, February 3, 2015), and 
adding the following new AD:

2016-21-06 Bombardier, Inc.: Amendment 39-18687; Docket No. FAA-
2016-5593; Directorate Identifier 2015-NM-184-AD.

(a) Effective Date

    This AD is effective December 19, 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 prevent 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 Appendixes 1 and 2, 
dated September 26, 2013.
    (2) For Model CL-600-2A12 (CL-601) airplanes having S/Ns 3001 
through 3066

[[Page 79383]]

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 Appendixes 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 paragraphs (h)(3), (k), or (n) of this AD 
are 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 Appendixes 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 Appendixes 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 
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 Appendixes 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 Appendixes 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 Appendixes 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 Appendixes 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 Appendixes 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 Appendixes 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 Appendixes 
1 and 2, dated September 26, 2013; and Bombardier Alert Service 
Bulletin A601-0627, Revision 02, dated December 9, 2014, including 
Appendixes 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).

[[Page 79384]]

(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 
Appendixes 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 Appendixes 1 and 2, dated 
September 26, 2013, which is not incorporated by reference in this 
AD.
    (3) Bombardier Alert Service Bulletin A601-0627, including 
Appendixes 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 Appendixes 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.
    (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.

(q) Related Information

    (1) Refer to Mandatory Continuing Airworthiness Information 
(MCAI) Canadian Emergency AD CF-2013-39R2, dated December 12, 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-2016-5593.
    (2) Service information identified in this AD that is not 
incorporated by reference is available at the addresses specified in 
paragraphs (r)(4) and (r)(5) of this AD.

(r) Material Incorporated by Reference

    (1) The Director of the Federal Register approved the 
incorporation by reference (IBR) of the service information listed 
in this paragraph under 5 U.S.C. 552(a) and 1 CFR part 51.
    (2) You must use this service information as applicable to do 
the actions required by this AD, unless this AD specifies otherwise.
    (3) The following service information was approved for IBR on 
February 18, 2015 (80 FR 5670, February 3, 2015).
    (i) Bombardier Alert Service Bulletin A600-0763, Revision 02, 
dated December 9, 2014, including Appendixes 1 and 2, dated 
September 26, 2013.
    (ii) Bombardier Alert Service Bulletin A601-0627, Revision 02, 
dated December 9, 2014, including Appendixes 1 and 2, dated 
September 26, 2013.
    (4) 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.
    (5) 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.
    (6) You may view this service information that is incorporated 
by reference at the National Archives and Records Administration 
(NARA). For information on the availability of this material at 
NARA, call 202-741-6030, or go to: http://www.archives.gov/federal-register/cfr/ibr-locations.html.

    Issued in Renton, Washington, on October 7, 2016.
Michael Kaszycki,
Acting Manager, Transport Airplane Directorate, Aircraft Certification 
Service.
[FR Doc. 2016-25009 Filed 11-10-16; 8:45 am]
 BILLING CODE 4910-13-P