81 FR 26121 - Airworthiness Directives; Bombardier, Inc. Airplanes

DEPARTMENT OF TRANSPORTATION
Federal Aviation Administration

Federal Register Volume 81, Issue 84 (May 2, 2016)

We are superseding Airworthiness Directive (AD) 2014-17-51 for certain Bombardier, Inc. Model CL-600-2B16 airplanes. AD 2014-17-51 required inspecting the inboard flap fasteners of the hinge-box forward fitting at Wing Station (WS) 76.50 and WS 127.25 to determine the orientation and condition of the fasteners, as applicable, and replacement or repetitive inspections of the fasteners if necessary. AD 2014-17-51 also provided for optional terminating action for the requirements of that AD. This new AD requires accomplishment of the previously optional terminating action. This AD was prompted by a determination that that additional action is necessary. We are issuing this AD to detect and correct incorrectly oriented or fractured fasteners, that could result in premature failure of the fasteners attaching the inboard flap hinge-box forward fitting; failure of the fasteners could lead to the detachment of the flap hinge box and the flap surface, and consequent loss of control of the airplane.

[Federal Register Volume 81, Number 84 (Monday, May 2, 2016)]
[Rules and Regulations]
[Pages 26121-26124]
From the Federal Register Online  [www.thefederalregister.org]
[FR Doc No: 2016-08959]


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DEPARTMENT OF TRANSPORTATION

Federal Aviation Administration

14 CFR Part 39

[Docket No. FAA-2015-3988; Directorate Identifier 2015-NM-005-AD; 
Amendment 39-18491; AD 2016-08-15]
RIN 2120-AA64


Airworthiness Directives; Bombardier, Inc. Airplanes

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

ACTION: Final rule.

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SUMMARY: We are superseding Airworthiness Directive (AD) 2014-17-51 for 
certain Bombardier, Inc. Model CL-600-2B16 airplanes. AD 2014-17-51 
required inspecting the inboard flap fasteners of the hinge-box forward 
fitting at Wing Station (WS) 76.50 and WS 127.25 to determine the 
orientation and condition of the fasteners, as applicable, and 
replacement or repetitive inspections of the fasteners if necessary. AD 
2014-17-51 also provided for optional terminating action for the 
requirements of that AD. This new AD requires accomplishment of the 
previously optional terminating action. This AD was prompted by a 
determination that that additional action is necessary. We are issuing 
this AD to detect and correct incorrectly oriented or fractured 
fasteners, that could result in premature failure of the fasteners 
attaching the inboard flap hinge-box forward fitting; failure of the 
fasteners could lead to the detachment of the flap hinge box and the 
flap surface, and consequent loss of control of the airplane.

DATES: This AD is effective June 6, 2016.
    The Director of the Federal Register approved the incorporation by 
reference of certain publications listed in this AD as of June 6, 2016.
    The Director of the Federal Register approved the incorporation by 
reference of certain other publications listed in this AD as of 
November 12, 2014 (79 FR 64088, October 28, 2014).
    The Director of the Federal Register approved the incorporation by 
reference of certain other publications listed in this AD as of March 
6, 2014 (79 FR 9389, February 19, 2014).

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; 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. It is also available on the Internet at http://www.regulations.gov by searching for and locating Docket No. FAA-2015-
3988.

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-
3988; 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, 
Propulsion and Services Branch, ANE-173, 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 2014-17-51, Amendment 39-17999 (79 FR 64088, 
October 28, 2014) (``AD 2014-17-51''). AD 2014-17-51 applied to certain 
Bombardier, Inc. Model CL-600-2B16 airplanes. The NPRM published in the 
Federal Register on October 19, 2015 (80 FR 63141) (``the NPRM'').
    Transport Canada Civil Aviation (TCCA), which is the aviation 
authority for Canada, has issued Canadian Airworthiness Directive CF-
2014-27R1, dated August 29, 2014 (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-
2B16 airplanes. The MCAI states:

    There have been three in-service reports on 604 Variant 
aeroplanes of a fractured fastener head on the inboard flap hinge-
box forward fitting at Wing Station (WS) 76.50, found during a 
routine maintenance inspection. Investigation revealed that the 
installation of these fasteners on the inboard flap hinge-box 
forward fittings at WS 76.50 and WS 127.25, on both wings, does not 
conform to the engineering drawings. Incorrect installation may 
result in premature failure of the fasteners attaching the inboard 
flap hinge-box forward fitting. Failure of the fasteners could lead 
to the detachment of the flap hinge box and consequently the 
detachment of the flap surface. The loss of a flap surface could 
adversely affect the continued safe operation of the aeroplane.
    The original issue of [Canadian] AD CF-2013-39 [http://www.regulations.gov/#!documentDetail;D=FAA-2014-0054-0002] [which 
corresponds to FAA AD 2014-03-17, Amendment 39-17754 (79 FR 9389, 
February 19, 2014)] mandated a detailed visual inspection (DVI) of 
each inboard flap hinge-box forward fitting, on both wings, and 
rectification as required. Incorrectly oriented fasteners require 
repetitive inspections until the terminating action is accomplished.
    After the issuance of [Canadian] AD CF-2013-39, there has been 
one reported incident on a 604 Variant aeroplane where four 
fasteners were found fractured on the same flap hinge-box forward 
fitting. The investigation determined that the fasteners were 
incorrectly installed.
    The original issue of this [Canadian] AD was issued to reduce 
the initial and repetitive inspection intervals previously mandated 
in [Canadian] AD CF-2013-39, and to impose replacement of the 
incorrectly oriented fasteners within 24 months. The CL-600-1A11, -
2A12 and -2B16 (601-3A/-3R Variant) aeroplanes are addressed through 
[Canadian] AD CF-2013-39R1.
    Revision 1 of this [Canadian] AD is issued to clarify the 
requirements for the initial and repetitive inspections.

    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-
3988.

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.

Change to Paragraph (k) of This AD

    Paragraph (k) of the NPRM specified to do the replacement on 
``both'' wings. However, 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. We have revised paragraph (k) of this 
AD to specify accomplishing the replacement on the affected wings. We

[[Page 26122]]

have coordinated this change with TCCA.

Conclusion

    We reviewed the relevant data and determined that air safety and 
the public interest require adopting this AD with the change described 
previously and 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.
    We also determined that these changes will not increase the 
economic burden on any operator or increase the scope of this AD.

Related Service Information Under 1 CFR Part 51

    Bombardier has issued Alert Service Bulletins:
     A604-57-006, Revision 04, dated November 12, 2014, 
including Appendices 1 and 2, dated September 26, 2013; and
     A605-57-004, Revision 04, dated November 12, 2014, 
including Appendices 1 and 2, dated September 26, 2013.
    The service information describes repetitive detailed visual 
inspections of each inboard flap fastener of the hinge-box forward 
fitting at WS 76.50 and WS 127.25, on both wings, and, if necessary, 
replacement of the 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.

Costs of Compliance

    We estimate that this AD affects 285 airplanes of U.S. registry.
    The actions required by AD 2014-17-51, and retained in this AD take 
about 1 work-hour per product, at an average labor rate of $85 per 
work-hour. Required parts cost about $0 per product. Based on these 
figures, the estimated cost of the actions that are required by AD 
2014-17-51 is $85 per product.
    We also estimate that it will take about 58 work-hours per product 
to comply with the basic requirements of this AD. The average labor 
rate is $85 per work-hour. Required parts cost about $753 per product. 
Based on these figures, we estimate the cost of this AD on U.S. 
operators to be $1,619,655, or $5,683 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 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) 
2014-17-51, Amendment 39-17999 (79 FR 64088, October 28, 2014), and 
adding the following new AD:

2016-08-15 Bombardier, Inc.: Amendment 39-18491. Docket No. FAA-
2015-3988; Directorate Identifier 2015-NM-005-AD.

(a) Effective Date

    This AD is effective June 6, 2016.

(b) Affected ADs

    (1) This AD replaces AD 2014-17-51, Amendment 39-17999 (79 FR 
64088, October 28, 2014) (``AD 2014-17-51'').
    (2) This AD affects AD 2014-03-17, Amendment 39-17754 (79 FR 
9389, February 19, 2014) (``AD 2014-03-17''), only for the airplanes 
identified in paragraph (c) of this AD.

(c) Applicability

    This AD applies to Bombardier, Inc. Model CL-600-2B16 airplanes, 
certificated in any category, serial numbers 5301 through 5665 
inclusive, and 5701 through 5920 inclusive.

(d) Subject

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

(e) Reason

    This AD was prompted by reports of fractured fastener heads on 
the inboard flap hinge-box forward fitting at Wing Station (WS) 
76.50 due to incorrect installation. We are issuing this AD to 
detect and correct incorrectly oriented or fractured fasteners, that 
could result in premature failure of the fasteners attaching the 
inboard flap hinge-box forward fitting; failure of the fasteners 
could lead to the detachment of the flap hinge box and the flap 
surface, and consequent loss of control of the airplane.

(f) Compliance

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

(g) Retained Inspection, With New Service Information: Airplanes Not 
Previously Inspected

    This paragraph restates the requirements of paragraph (g) of AD 
2014-17-51, with new service information. For airplanes on which the 
actions required by AD 2014-03-17 have not been done as of November 
12, 2014 (the effective date of AD 2014-17-51): Within 10

[[Page 26123]]

flight cycles after November 12, 2014, or within 100 flight cycles 
after March 6, 2014 (the effective date of AD 2014-03-17), whichever 
occurs first, do a detailed visual inspection of each inboard flap 
fastener of the hinge-box forward fitting at WS 76.50 and WS 127.25, 
on both wings, to determine if the fasteners are correctly oriented 
and intact (non-fractured, with intact fastener head). Do the 
inspection in accordance with the Accomplishment Instructions of 
Bombardier Alert Service Bulletin A604-57-006, Revision 01, dated 
September 26, 2013, including Appendices 1 and 2, dated September 
26, 2013, Revision 02, dated January 22, 2014, including Appendices 
1 and 2, dated September 26, 2013, or Revision 04, dated November 
12, 2014, including Appendices 1 and 2, dated September 26, 2013 
(for serial numbers 5301 through 5665 inclusive); or Bombardier 
Alert Service Bulletin A605-57-004, Revision 01, dated September 26, 
2013, including Appendices 1 and 2, dated September 26, 2013, 
Revision 02, dated January 22, 2014, including Appendices 1 and 2, 
dated September 26, 2013, or Revision 04, dated November 12, 2014, 
including Appendices 1 and 2, dated September 26, 2013 (for serial 
numbers 5701 through 5920 inclusive). As of the effective date of 
this AD, only use Bombardier Alert Service Bulletin A604-57-006, 
Revision 04, dated November 12, 2014, including Appendices 1 and 2, 
dated September 26, 2013; or Bombardier Alert Service Bulletin A605-
57-004, Revision 04, dated November 12, 2014, including Appendices 1 
and 2, dated September 26, 2013; as applicable; for the actions 
required by this paragraph.
    (1) If all fasteners are found intact and correctly oriented, no 
further action is required by this AD.
    (2) If any fastener is found fractured: Before further flight, 
remove and replace all forward and aft fasteners at WS 76.50 and WS 
127.25, regardless of condition or orientation, on both wings, in 
accordance with the Accomplishment Instructions of the applicable 
service information identified in paragraph (g) of this AD. As of 
the effective date of this AD, only use Bombardier Alert Service 
Bulletin A604-57-006, Revision 04, dated November 12, 2014, 
including Appendices 1 and 2, dated September 26, 2013; or 
Bombardier Alert Service Bulletin A605-57-004, Revision 04, dated 
November 12, 2014, including Appendices 1 and 2, dated September 26, 
2013; as applicable; for the actions required by this paragraph. 
After replacement of all fasteners as required by this paragraph of 
this AD, no further action is required by this AD.
    (3) If any incorrectly oriented but intact fastener is found, 
and no fractured fastener is found, repeat the inspection required 
by paragraph (g) of this AD thereafter at intervals not to exceed 10 
flight cycles, until the requirements of paragraph (i)(1) or (k) of 
this AD have been done.

(h) Retained Actions, With New Service Information: Airplanes 
Previously Inspected, Having Incorrectly Oriented Fastener(s)

    This paragraph restates the requirements of paragraph (h) of AD 
2014-17-51, with new service information. For airplanes on which an 
inspection required by paragraph (g) or (j) of AD 2014-03-17 has 
been done as of November 12, 2014 (the effective date of AD 2014-17-
51), and on which any incorrectly oriented fastener, but no 
fractured fastener, was found: Except as provided by paragraph 
(i)(3) of this AD, do a detailed visual inspection of all inboard 
flap fasteners of the hinge-box forward fitting at WS 76.50 and WS 
127.25, on both wings, to determine if the fasteners are intact 
(non-fractured, with intact fastener head). Inspect within 10 flight 
cycles after November 12, 2014, or within 100 flight cycles after 
the most recent inspection done as required by AD 2014-03-17, 
whichever occurs first. Inspect in accordance with the 
Accomplishment Instructions of the applicable service information 
identified in paragraph (g) of this AD. As of the effective date of 
this AD, only use Bombardier Alert Service Bulletin A604-57-006, 
Revision 04, dated November 12, 2014, including Appendices 1 and 2, 
dated September 26, 2013; or Bombardier Alert Service Bulletin A605-
57-004, Revision 04, dated November 12, 2014, including Appendices 1 
and 2, dated September 26, 2013; as applicable; for the actions 
required by this paragraph.
    (1) If all fasteners are found intact, repeat the inspection 
thereafter at intervals not to exceed 10 flight cycles, until the 
requirements of paragraph (i)(1) or (k) of this AD have been done.
    (2) If any fastener is found fractured: Before further flight, 
remove and replace all forward and aft fasteners at WS 76.50 and WS 
127.25, regardless of condition or orientation, on both wings, in 
accordance with the Accomplishment Instructions of the applicable 
service information identified in paragraph (g) of this AD. As of 
the effective date of this AD, only use Bombardier Alert Service 
Bulletin A604-57-006, Revision 04, dated November 12, 2014, 
including Appendices 1 and 2, dated September 26, 2013; or 
Bombardier Alert Service Bulletin A605-57-004, Revision 04, dated 
November 12, 2014, including Appendices 1 and 2, dated September 26, 
2013; as applicable; for the actions required by this paragraph. 
After replacement of all fasteners as required by this paragraph, no 
further action is required by this AD.

(i) Retained Terminating Action, With New Service Information

    This paragraph restates the terminating action specified in 
paragraph (i) of AD 2014-17-51), with new service information.
    (1) Replacement of all forward and aft fasteners at WS 76.50 and 
WS 127.25, on both wings, in accordance with the Accomplishment 
Instructions of the applicable service information identified in 
paragraph (g) of this AD, terminates the requirements of this AD. As 
of the effective date of this AD, only use Bombardier Alert Service 
Bulletin A604-57-006, Revision 04, dated November 12, 2014, 
including Appendices 1 and 2, dated September 26, 2013; or 
Bombardier Alert Service Bulletin A605-57-004, Revision 04, dated 
November 12, 2014, including Appendices 1 and 2, dated September 26, 
2013; as applicable; for the actions specified in this paragraph.
    (2) Accomplishment of the applicable requirements of this AD 
constitutes terminating action for the requirements of AD 2014-03-17 
for that airplane only.
    (3) Replacement of all fractured and incorrectly oriented 
fasteners before November 12, 2014 (the effective date of AD 2014-
17-51), as provided by paragraph (i) or (k) of AD 2014-03-17, is 
acceptable for compliance with the requirements of this AD.

(j) Retained Special Flight Permit Prohibition

    This paragraph restates the requirements of paragraph (j) of AD 
2014-17-51. Special flight permits to operate the airplane to a 
location where the airplane can be repaired in accordance with 14 
CFR 21.197 and 21.199 are not allowed.

(k) New Requirement of This AD: Post-Inspection Fastener Replacement

    For airplanes on which incorrectly oriented fasteners were found 
during any inspection required by paragraph (g), (g)(3), (h), or 
(h)(1) of this AD, but none were found to be fractured: Within 24 
months after the effective date of this AD, remove and replace all 
forward and aft fasteners at WS 76.50 and WS 127.25, regardless of 
condition or orientation, on affected wings, in accordance with the 
Accomplishment Instructions of Bombardier Alert Service Bulletin 
A604-57-006, Revision 04, dated November 12, 2014, including 
Appendices 1 and 2, dated September 26, 2013 (for serial numbers 
5301 through 5665 inclusive); or Bombardier Alert Service Bulletin 
A605-57-004, Revision 04, dated November 12, 2014, including 
Appendices 1 and 2, dated September 26, 2013 (for serial numbers 
5701 through 5920 inclusive). Accomplishing the requirements of this 
paragraph terminates the requirements of this AD.

(l) Credit for Previous Actions

    (1) This paragraph provides credit for actions required by 
paragraphs (g), (h), and (i)(1) of this AD, if those actions were 
performed before the effective date of this AD using the applicable 
service information identified in paragraphs (l)(1)(i) and 
(l)(1)(ii) of this AD, which are not incorporated by reference in 
this AD.
    (i) Bombardier Alert Service Bulletin A604-57-006, Revision 03, 
dated August 19, 2014, including Appendices 1 and 2, dated September 
26, 2013.
    (ii) Bombardier Alert Service Bulletin A605-57-004, Revision 03, 
dated August 19, 2014, including Appendices 1 and 2, dated September 
26, 2013.
    (2) This paragraph provides credit for actions required by 
paragraph (k) of this AD, if those actions were done before the 
effective date of this AD using the applicable service information 
identified in paragraphs (l)(2)(i) through (l)(2)(iv) of this AD.
    (i) Bombardier Alert Service Bulletin A604-57-006, Revision 01, 
dated September 26, 2013, including Appendices 1 and 2, dated 
September 26, 2013, which is incorporated by reference in AD 2014-
03-17.
    (ii) Bombardier Alert Service Bulletin A604-57-006, Revision 02, 
dated January 22, 2014, including Appendices 1 and 2, dated

[[Page 26124]]

September 26, 2013, which was incorporated by reference in AD 2014-
17-51.
    (iii) Bombardier Alert Service Bulletin A605-57-004, Revision 
01, dated September 26, 2013, including Appendices 1 and 2, dated 
September 26, 2013, which is incorporated by reference in AD 2014-
03-17.
    (iv) Bombardier Alert Service Bulletin A604-57-004, Revision 02, 
dated January 22, 2014, including Appendices 1 and 2, dated 
September 26, 2013, which was incorporated by reference in AD 2014-
17-51.

(m) Other FAA AD Provisions

    The following provisions also apply to this AD:
    (1) Alternative Methods of Compliance (AMOCs): The Manager, New 
York Aircraft Certification Office (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.
    (i) 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.
    (ii) AMOCs previously approved for AD 2014-17-51 are acceptable 
for the corresponding requirements of this AD.
    (2) Contacting the Manufacturer: As of the effective date of 
this AD, 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 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.

(n) Related Information

    (1) Refer to Mandatory Continuing Airworthiness Information 
(MCAI) Canadian Emergency Airworthiness Directive CF-2014-27R1, 
dated August 29, 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-2015-3988.
    (2) Service information identified in this AD that is not 
incorporated by reference is available at the addresses specified in 
paragraphs (o)(6) and (o)(7) of this AD.

(o) 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 
June 6, 2016.
    (i) Bombardier Alert Service Bulletin A604-57-006, Revision 04, 
dated November 12, 2014, including Appendices 1 and 2, dated 
September 26, 2013.
    (ii) Bombardier Alert Service Bulletin A605-57-004, Revision 04, 
dated November 12, 2014, including Appendices 1 and 2, dated 
September 26, 2013.
    (4) The following service information was approved for IBR on 
November 12, 2014 (79 FR 64088, October 28, 2014).
    (i) Bombardier Alert Service Bulletin A604-57-006, Revision 02, 
dated January 22, 2014, including Appendices 1 and 2, dated 
September 26, 2013.
    (ii) Bombardier Alert Service Bulletin A605-57-004, Revision 02, 
dated January 22, 2014, including Appendices 1 and 2, dated 
September 26, 2013.
    (5) The following service information was approved for IBR on 
March 6, 2014 (79 FR 9389, February 19, 2014).
    (i) Bombardier Alert Service Bulletin A604-57-006, Revision 01, 
dated September 26, 2013, including Appendices 1 and 2, dated 
September 26, 2013.
    (ii) Bombardier Alert Service Bulletin A605-57-004, Revision 01, 
dated September 26, 2013, including Appendices 1 and 2, dated 
September 26, 2013.
    (6) 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.
    (7) 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.
    (8) 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 April 8, 2016.
Michael Kaszycki,
Acting Manager, Transport Airplane Directorate, Aircraft Certification 
Service.
[FR Doc. 2016-08959 Filed 4-29-16; 8:45 am]
BILLING CODE 4910-13-P