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[Federal Register Volume 79, Number 208 (Tuesday, October 28, 2014)]
[Rules and Regulations]
[Pages 64088-64092]
From the Federal Register Online via the Government Printing Office [www.gpo.gov]
[FR Doc No: 2014-25018]

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DEPARTMENT OF TRANSPORTATION

Federal Aviation Administration

14 CFR Part 39

[Docket No. FAA-2014-0581; Directorate Identifier 2014-NM-167-AD; 
Amendment 39-17999; AD 2014-17-51]
RIN 2120-AA64

Airworthiness Directives; Bombardier, Inc. Airplanes

AGENCY: Federal Aviation Administration (FAA), DOT.

ACTION: Final rule; request for comments.

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SUMMARY: We are adopting a new airworthiness directive (AD) for certain 
Bombardier, Inc. Model CL-600-2B16 airplanes. This emergency AD was 
sent previously to all known U.S. owners and operators of these 
airplanes. This AD requires 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. This AD also provides for optional terminating action for 
the requirements of the AD. This AD was prompted by reports of 
fractured fastener heads on the inboard flap hinge-box forward fitting 
at WS 76.50 due to incorrect installation. We are issuing this AD to 
detect and correct

[[Page 64089]]

incorrectly oriented or fractured fasteners, which 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 November 12, 2014 to all persons except 
those persons to whom it was made immediately effective by Emergency AD 
2014-17-51, issued on August 19, 2014, which contained the requirements 
of this amendment.
    The Director of the Federal Register approved the incorporation by 
reference of certain publications identified in this AD as of November 
12, 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).
    We must receive comments on this AD by December 12, 2014.

ADDRESSES: You may send comments, using the procedures found in 14 CFR 
11.43 and 11.45, by any of the following methods:
     Federal eRulemaking Portal: Go to http://www.regulations.gov. Follow the instructions for submitting comments.
     Fax: 202-493-2251.
     Mail: U.S. Department of Transportation, Docket 
Operations, M-30, West Building Ground Floor, Room W12-140, 1200 New 
Jersey Avenue SE., Washington, DC 20590.
     Hand Delivery: Deliver to Mail address above between 9 
a.m. and 5 p.m., Monday through Friday, except Federal holidays.
    For service information identified in this 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 
thd.crj@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-2014-
0581; or in person at the Docket Operations Office 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 street address for the Docket Operations Office 
(phone: 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, 
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

    On August 19, 2014, we issued Emergency AD 2014-17-51, which 
requires inspecting the inboard flap fasteners of the hinge-box forward 
fitting at 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. Emergency AD 
2014-17-51 also provides for optional terminating action for the 
requirements of the AD. This emergency AD was sent previously to all 
known U.S. owners and operators of these airplanes. This action 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. This condition, if not corrected, 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.
    Transport Canada Civil Aviation (TCCA), which is the aviation 
authority for Canada, has issued Canadian Emergency Airworthiness 
Directive CF-2014-27, dated August 15, 2014 (referred to after this as 
the Mandatory Continuing Airworthiness Information, or ``the MCAI''), 
to correct an unsafe condition on certain 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 AD CF-2013-39 [dated December 6, 2013] 
[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 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.
    This [Canadian] AD is issued to reduce the initial and 
repetitive inspection intervals previously mandated in 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 AD CF-2013-39R1 [dated 
August 15, 2014].

You may examine the MCAI on the Internet at http://www.regulations.gov 
by searching for and locating Docket No. FAA-2014-0581.

Relevant Service Information

    We reviewed the following service information:
     Bombardier Alert Service Bulletin A604-57-006, Revision 
01, dated September 26, 2013, including Appendices 1 and 2, dated 
September 26, 2013.
     Bombardier Alert Service Bulletin A604-57-006, Revision 
02, dated January 22, 2014, including Appendices 1 and 2, dated 
September 26, 2013.
     Bombardier Alert Service Bulletin A605-57-004, Revision 
01, dated September 26, 2013, including Appendices 1 and 2, dated 
September 26, 2013.
     Bombardier Alert Service Bulletin A605-57-004, Revision 
02, dated January 22, 2014, including Appendices 1 and 2, dated 
September 26, 2013.
    The actions described in this service information are intended to 
correct the unsafe condition identified in the MCAI.
    Revision 02 of the service information instructs operators to 
contact Bombardier for repair procedures for certain configurations; 
paragraph (k)(2) of this AD addresses this issue.

FAA's Determination and AD Requirements

    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

[[Page 64090]]

MCAI and service information referenced above. We are issuing this AD 
because we evaluated all pertinent information and determined the 
unsafe condition exists and is likely to exist or develop on other 
products of the same type design.
    Accomplishment of the requirements of this AD constitutes 
terminating action for the requirements of AD 2014-03-17, Amendment 39-
17754 (79 FR 9389, February 19, 2014), for the airplanes identified in 
paragraph (c) of this AD.
    FAA AD 2014-03-17, Amendment 39-17754 (79 FR 9389, February 19, 
2014), corresponds to Canadian AD CF-2013-39, dated December 6, 2013. 
FAA AD 2014-03-17 applies to Bombardier, Inc. Model CL-600-1A11 (CL-
600), CL-600-2A12 (CL-601), and CL-600-2B16 (CL-601-3A, CL-601-3R, and 
CL-604 Variants) airplanes. Because of the urgency of this unsafe 
condition for the CL-604 Variant airplanes, we have determined that it 
is necessary to issue an emergency AD, only for CL-604 Variant 
airplanes, to reduce the compliance times for the inspection required 
by AD 2014-03-17.

Explanation of Applicability

    This AD applies to Bombardier, Inc. Model CL-600-2B16 airplanes 
with certain serial numbers. The CL-605 is a marketing designation for 
the Challenger CL-600-2B16, CL-604 Variant, with Modsums 604DX10000, 
604DX20000, and 604DX30000 incorporated, beginning with serial numbers 
5701 and subsequent. All CL-604 and CL-605 airplanes are type certified 
as CL-600-2B16 airplanes. Therefore this AD applies to all CL-600-2B16 
models in the specified serial-number range.

Differences Between This AD and the MCAI/Service Information

    Canadian Airworthiness Directive CF-2014-27, dated August 15, 2014, 
specifies to replace all forward and aft fasteners at WS 76.50 and 
127.25 within 24 months, if any incorrectly installed fasteners are 
found. We are considering requiring this replacement, which would 
terminate the actions required by this AD. However, the planned 
compliance time for the replacement would allow enough time to provide 
notice and opportunity for prior public comment on the merits of the 
replacement.
    Although the service information identified previously specifies 
that operators may contact the manufacturer for disposition of certain 
repair conditions, this AD requires operators to repair those 
conditions in accordance with a method approved by the FAA, or TCCA, or 
Bombardier, Inc.'s TCCA Design Approval Organization (DAO).

FAA's Determination of the Effective Date

    An unsafe condition exists that requires the immediate adoption of 
this AD. The FAA has found that the risk to the flying public justifies 
waiving notice and comment prior to adoption of this rule because 
incorrect installation of the fasteners attaching the inboard flap 
hinge-box forward fitting may result in their premature failure, and 
possible detachment of the flap hinge box and the flap surface, and 
loss of control of the airplane. Therefore, we find that notice and 
opportunity for prior public comment are impracticable and that good 
cause exists for making this amendment effective in less than 30 days.

Comments Invited

    This AD is a final rule that involves requirements affecting flight 
safety and was not preceded by notice and an opportunity for public 
comment. However, we invite you to send any written data, views, or 
arguments about this AD. Send your comments to an address listed under 
the ADDRESSES section. Include the docket number FAA-2014-0581 and 
Directorate Identifier 2014-NM-167-AD at the beginning of your 
comments. We specifically invite comments on the overall regulatory, 
economic, environmental, and energy aspects of this AD. We will 
consider all comments received by the closing date and may amend this 
AD because of 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 AD.

Costs of Compliance

    We estimate that this AD affects 285 airplanes of U.S. registry. We 
estimate the following costs to comply with this AD:

                                                 Estimated Costs
----------------------------------------------------------------------------------------------------------------
                                                                                    Cost per       Cost on U.S.
              Action                        Labor cost            Parts cost        product         operators
----------------------------------------------------------------------------------------------------------------
Inspection........................  1 work-hour x $85 per                  $0              $85          $24,225
                                     hour = $85.
----------------------------------------------------------------------------------------------------------------

    We estimate the following costs to do any necessary replacements 
that would be required based on the results of the inspection. We have 
no way of determining the number of aircraft that might need these 
replacements:

                                               On-Condition Costs
----------------------------------------------------------------------------------------------------------------
                                                                                                     Cost per
                  Action                                Labor cost                 Parts cost        product
----------------------------------------------------------------------------------------------------------------
Fastener replacement......................  Up to 58 work-hours x $85 per hour              $0           $4,930
                                             = $4,930.
----------------------------------------------------------------------------------------------------------------

    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,

[[Page 64091]]

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

    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 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 adding the following new airworthiness 
directive (AD):

2014-17-51 Bombardier, Inc.: Amendment 39-17999; Docket No. FAA-
2014-0581; Directorate Identifier 2014-NM-167-AD.

(a) Effective Date

    This AD is effective November 12, 2014 to all persons except 
those persons to whom it was made immediately effective by Emergency 
AD 2014-17-51, issued on August 19, 2014, which contained the 
requirements of this amendment.

(b) Affected ADs

    The requirements of this AD terminate the requirements of AD 
2014-03-17, Amendment 39-17754 (79 FR 9389, February 19, 2014), 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) Unsafe Condition

    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, 
which 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) Inspection: Airplanes Not Previously Inspected

    For airplanes on which the actions required by AD 2014-03-17, 
Amendment 39-17754 (79 FR 9389, February 19, 2014), have not been 
done as of the effective date of this AD: Within 10 flight cycles 
after the effective date of this AD, or within 100 flight cycles 
after March 6, 2014 (the effective date of AD 2014-03-17, Amendment 
39-17754 (79 FR 9389, February 19, 2014)), 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, or Revision 
02, dated January 22, 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, or Revision 02, dated January 22, 2014, including 
Appendices 1 and 2, dated September 26, 2013 (for serial numbers 
5701 through 5920 inclusive).
    (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 Bombardier Alert 
Service Bulletin A604-57-006, Revision 01, dated September 26, 2013, 
including Appendices 1 and 2, dated September 26, 2013, or Revision 
02, dated January 22, 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, or Revision 02, dated January 22, 2014, including 
Appendices 1 and 2, dated September 26, 2013 (for serial numbers 
5701 through 5920 inclusive). After replacement of all fasteners as 
required by paragraph (g)(2) 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) of this AD 
have been done.

(h) Airplanes Previously Inspected, With Incorrectly Oriented 
Fastener(s)

    For airplanes on which an inspection required by paragraph (g) 
or (j) of AD 2014-03-17, Amendment 39-17754 (79 FR 9389, February 
19, 2014), has been done as of the effective date of this AD, 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 the effective 
date of this AD, 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 
Bombardier Alert Service Bulletin A604-57-006, Revision 01, dated 
September 26, 2013, including Appendices 1 and 2, dated September 
26, 2013, or Revision 02, dated January 22, 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, or Revision 02, dated 
January 22, 2014, including Appendices 1 and 2, dated September 26, 
2013 (for serial numbers 5701 through 5920 inclusive).
    (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) 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 Bombardier Alert 
Service Bulletin A604-57-006,

[[Page 64092]]

Revision 01, dated September 26, 2013, including Appendices 1 and 2, 
dated September 26, 2013, or Revision 02, dated January 22, 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, or Revision 
02, dated January 22, 2014, including Appendices 1 and 2, dated 
September 26, 2013 (for serial numbers 5701 through 5920 inclusive). 
After replacement of all fasteners as required by paragraph (h)(2) 
of this AD, no further action is required by this AD.

(i) Terminating Action

    (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 Bombardier Alert Service Bulletin A604-57-006, 
Revision 01, dated September 26, 2013, including Appendices 1 and 2, 
dated September 26, 2013, or Revision 02, dated January 22, 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, or Revision 
02, dated January 22, 2014, including Appendices 1 and 2, dated 
September 26, 2013 (for serial numbers 5701 through 5920 inclusive); 
terminates the requirements of this AD.
    (2) Accomplishment of the applicable requirements of this AD 
constitutes terminating action for the requirements of AD 2014-03-
17, Amendment 39-17754 (79 FR 9389, February 19, 2014), for that 
airplane only.
    (3) Replacement, before the effective date of this AD, of all 
fractured and incorrectly oriented fasteners, as provided by 
paragraph (i) or (k) of AD 2014-03-17, Amendment 39-17754 (79 FR 
9389, February 19, 2014), is acceptable for compliance with the 
requirements of this AD.

(j) Special Flight Permit

    Special flight permits to operate the airplane to a location 
where the airplane can be repaired in accordance with sections 
21.197 and 21.199 of the Federal Aviation Regulations (14 CFR 21.197 
and 21.199) are not allowed.

(k) Other FAA Provisions

    (1) Alternative Methods of Compliance (AMOCs): The Manager, New 
York Aircraft Certification Office, 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 
Aircraft Certification Office, ANE-170, FAA; or the TCCA; or 
Bombardier, Inc.'s TCCA Design Approval Organization (DAO). If 
approved by the DAO, the approval must include the DAO-authorized 
signature.

(l) Related Information

    Refer to Mandatory Continuing Airworthiness Information (MCAI) 
Canadian Emergency Airworthiness Directive CF-2014-27, dated August 
15, 2014, for related information. You may examine the MCAI on the 
Internet at http://www.regulations.gov by searching for and locating 
Docket No. FAA-2014-0581.

(m) 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 the AD specifies otherwise.
    (3) The following service information was approved for IBR on 
November 12, 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.
    (4) 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.
    (5) 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 thd.crj@aero.bombardier.com; Internet http://www.bombardier.com.
    (6) 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.
    (7) 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 13, 2014.
Michael Kaszycki,
Acting Manager, Transport Airplane Directorate, Aircraft Certification 
Service.
[FR Doc. 2014-25018 Filed 10-27-14; 8:45 am]
BILLING CODE 4910-13-P
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