
[Federal Register Volume 77, Number 54 (Tuesday, March 20, 2012)]
[Rules and Regulations]
[Pages 16151-16155]
From the Federal Register Online via the Government Printing Office [www.gpo.gov]
[FR Doc No: 2012-6117]


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DEPARTMENT OF TRANSPORTATION

Federal Aviation Administration

14 CFR Part 39

[Docket No. FAA-2011-0565; Directorate Identifier 2010-NM-280-AD; 
Amendment 39-16977; AD 2012-05-05]
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 adopting a new airworthiness directive (AD) for certain 
Bombardier, Inc. Model CL-215-1A10, CL-215-6B11 (CL-215T Variant), and 
CL-215-6B11 (CL-415 Variant) airplanes. This AD was prompted by reports 
of cracked or broken support bracket assemblies of the emergency water 
dump pulley. This AD requires inspecting the bracket assembly of the 
emergency water dump pulley to determine if certain rivets are 
installed; replacing rivets and installing new stiffeners on the 
bracket assembly, if necessary; inspecting the stiffeners for the 
bracket assembly for cracks, deformation, or corrosion, and replacement 
if necessary; and re-installing the bracket assembly with radius 
packers. We are issuing this AD to detect and correct failure of the 
support bracket assembly of the emergency water dump pulley, and in 
combination with other system failures, such as an engine failure 
during take off or a pitch control system jam, may result in loss of 
controllability of the airplane.

DATES: This AD becomes effective April 24, 2012.
    The Director of the Federal Register approved the incorporation by 
reference of certain publications listed in this AD as of April 24, 
2012.

ADDRESSES: You may examine the AD docket on the Internet at http://www.regulations.gov or in person at the U.S. Department of 
Transportation, Docket Operations, M-30, West Building Ground Floor, 
Room W12-140, 1200 New Jersey Avenue SE., Washington, DC.

FOR FURTHER INFORMATION CONTACT: Andreas Rambalakos, Aerospace 
Engineer, Airframe and Mechanical Systems Branch, ANE-171, FAA, New 
York Aircraft Certification Office, 1600 Stewart Avenue, Suite 410, 
Westbury, New York 11590; telephone (516) 228-7345; fax (516) 794-5531.

SUPPLEMENTARY INFORMATION:

Discussion

    We issued a notice of proposed rulemaking (NPRM) to amend 14 CFR 
part 39 to include an AD that would apply to the specified products. 
That NPRM was published in the Federal Register on June 10, 2011 (76 FR 
34014). That NPRM proposed to correct an unsafe condition for the 
specified products. The MCAI states:

    The emergency water dump pulley support bracket assembly, Part 
Number (P/N) 215-94711-2, has been found cracked or broken on a 
number of aeroplanes. Failure of the emergency water dump pulley 
support bracket assembly in combination with other system failures 
such as an engine failure during take off or pitch control system 
jam, may result in a loss of control of the aeroplane.
    Revision 2 of this [Transport Canada Civil Aviation (TCCA)] AD 
is issued to ensure that terminating action for this [TCCA] AD is 
carried out prior to the 2011 fire season.

The required actions include a general visual inspection to determine 
if either universal solid (round head) rivets or flush rivets of the 
bracket assembly of the emergency water dump pulley are installed; 
replacing the solid rivets with flush rivets and installing new 
stiffeners on the bracket assembly of the emergency water dump pulley, 
if necessary; a detailed inspection and a liquid penetrant inspection 
of the stiffeners for cracks, deformations, or signs of corrosion, and 
replacing the stiffeners with new stiffeners if necessary; and re-
installing the bracket assembly of the emergency water dump pulley 
using radius packers. You may obtain further information by examining 
the MCAI in the AD docket.

Comments

    We gave the public the opportunity to participate in developing 
this AD. We considered the comments received.

Request To Extend Proposed Compliance Time for Replacing Damaged 
Stiffeners for Airplanes Used in Utility-Category Flight Operations

    Aero-Flite, Inc. stated that it does not find that a reduction in 
operational safety exists for utility-category flight operations where 
the water tanks

[[Page 16152]]

remain empty and the emergency water dump system becomes inoperative. 
Aero-Flite, Inc. stated that its review of the airplane flight manual 
emergency and abnormal procedures for Model CL-215 airplanes conducting 
restricted category operations revealed that the emergency water dump 
system is required as a back up in the event of failure of the electro-
hydraulic water door system. Aero-Flite, Inc. also stated that 
prohibiting all flight operations if cracks, signs of corrosion, or 
deformation of the stiffeners is found during inspection creates an 
unnecessary burden for the operator, affecting mission availability and 
increasing the cost of compliance without providing a meaningful 
improvement in safety. Aero-Flite, Inc. stated the changes will allow 
the operator to plan for utility-category flight mission requirements.
    Aero-Flite, Inc. recommended that all flight limitations contained 
in the NPRM (76 FR 34014, June 10, 2011) be changed to consider that 
water or fire retardant must be in the tanks for the unsafe condition 
to exist. Therefore, Aero-Flite, Inc. suggested that all occurrences of 
``before further flight'' (specified in paragraphs (i) and (j) of the 
NPRM) be changed to ``before further approved restricted category 
operations with water or fire retardant in the tanks including scooping 
operations.''
    We do not agree. Per the type certificate data sheet for Model CL-
215-1A10, CL-215-6B11 (CL-215T Variant), and CL-215-6B11 (CL-415 
Variant) airplanes, these airplanes are certificated in the restricted 
category only and therefore no reference can be made to utility-
category operations. In addition, because of the safety implications 
and consequences associated with cracking, our policy requires repair 
of known cracks, deformation, and signs of corrosion, before further 
flight. This policy is based on the fact that such damaged airplanes do 
not conform to the FAA-certificated type design and, therefore, are not 
airworthy until a properly approved repair is made. While we recognize 
that repair deferrals might be necessary in certain cases of unusual 
need, routinely deferring repairs could reduce the safety of the type 
certificated design if such repair deferrals are practiced routinely. 
We have not changed the AD regarding this issue.

Request To Extend the Compliance Time for the Liquid Penetrant 
Inspection and Re-Installing the Bracket Assembly of the Emergency 
Water Dump Pulley

    Aero-Flite, Inc. requested that we change the compliance time in 
paragraph (j) of the NPRM (76 FR 34014, June 10, 2011) to ``Within 100 
flight cycles or 120 days after the effective date of this AD or as of 
November 1, 2011, whichever occurs later.'' Aero-Flite, Inc. stated 
that it finds that the compliance time specified in paragraph (j) of 
this NPRM may provide an unnecessary burden for the operator, resulting 
in airplanes becoming unavailable, and risking substantial loss of 
property and life from wild fires without providing a meaningful 
improvement in airplane operational safety.
    We disagree with extending the compliance time for the liquid 
penetrant inspection and re-installing the bracket assembly of the 
emergency water dump pulley. In developing an appropriate compliance 
time for the actions specified in paragraph (j) of this AD, we 
considered the safety implications, parts availability, and normal 
maintenance schedules for the timely accomplishment of the specified 
actions. We have determined that the proposed compliance time will 
ensure an acceptable level of safety and allow the actions to be done 
during scheduled maintenance intervals for most affected operators. In 
addition, investigations by Bombardier have revealed that the cracked 
support bracket assemblies did not pass limit and ultimate load 
conditions. Because this is a strength issue, Bombardier recommends 
replacement of affected parts followed by installation of radius 
packers to strengthen the support bracket assembly, which would 
terminate the need for repetitive inspections. Affected operators, 
however, may request an alternative method of compliance (AMOC) under 
the provisions of paragraph (1)(1) of this AD by submitting data 
substantiating that the change would provide an acceptable level of 
safety. We have not changed this AD in this regard.

Request To Use an Optional Service Inspection

    Aero-Flite, Inc. requested that we revise paragraph (l) of the NPRM 
(76 FR 34014, June 10, 2011) to add an optional visual inspection for 
the exposed areas of the stiffeners, paying special attention to the 
identified critical locations (removing the bolt from the critical bolt 
hole and inspect the hole).
    Aero-Flite, Inc. stated that accomplishing the repetitive 
inspections in accordance with Bombardier Service Bulletin 215-A543, 
Revision 1, dated June 23, 2010, requires removal of the bracket 
assembly from the airplane. Aero-Flite, Inc. stated that it finds that 
the repetitive visual inspections of the critical locations on the 
stiffeners can be accomplished without removing the bracket assembly 
and without substantial systems disassembly by removing the fastener 
common to the triangular flange. Aero-Flite, Inc. also stated that 
mandating removal of the bracket assembly to conduct visual inspections 
creates a burden on the operator, which may affect fire fighting 
mission availability, and increase the cost of compliance without 
providing a meaningful improvement in safety.
    We disagree with the request to use an optional visual inspection. 
Bombardier has only validated the required inspections in Bombardier 
Service Bulletin 215-A543, Revision 1, dated June 23, 2010. We have not 
received sufficient technical information from Bombardier validating 
that a visual inspection without removing the bracket assembly would 
identify the unsafe condition. Affected operators, however, may request 
an AMOC under the provisions of paragraph (l)(1) of this AD by 
submitting data substantiating that the change would provide an 
acceptable level of safety. We have not changed this AD in this regard.

Request To Use Optional Surface Eddy Current Inspection

    Aero-Flite, Inc. recommends that we revise paragraph (j)(1) of the 
NPRM (76 FR 34014, June 10, 2011) to include an optional surface eddy 
current inspection for detecting cracks, corrosion, and deformation of 
the stiffeners.
    Aero-Flite, Inc. stated that the liquid penetrant inspection 
specified in the NPRM (76 FR 34014, June 10, 2011) seems to eliminate 
an equivalent inspection, such as a surface eddy current inspection for 
detecting cracks, and a visual inspection for corrosion and 
deformation. Aero-Flite, Inc. also stated that general surface eddy 
current inspection procedures are published in the Bombardier CL-215 
nondestructive testing manual, and that the procedures can be used to 
detect cracks in the stiffeners with an accuracy that is at least 
equivalent to liquid penetrant inspection procedure. Aero-Flite, Inc. 
stated that using a visual inspection for signs of corrosion allows the 
inspector to look for loose paint, discoloration of the surface, or 
variations in surface roughness, and that a visual inspection provides 
detection that is equivalent to

[[Page 16153]]

the liquid penetrant inspection. Aero-Flite, Inc. stated that requiring 
the operator to inspect the stiffeners only using liquid penetrant may 
create a burden on the operator that may affect fire fighting mission 
availability and increase the cost of compliance without providing an 
improvement in safety.
    We disagree with the request to use an optional surface eddy 
current inspection. Bombardier has only validated the required 
inspections in Bombardier Service Bulletin 215-A543, Revision 1, dated 
June 23, 2010. We have not received sufficient technical information 
from Bombardier validating that an inspection other than visual would 
identify the unsafe condition. Affected operators, however, may request 
an optional inspection under the provisions of paragraph (l)(1) of this 
AD by submitting data substantiating that the change would provide an 
acceptable level of safety. We have not changed this AD in this regard.

Requests To Allow Use of Locally or Operator Fabricated Parts

    Aero-Flite, Inc. requested that we revise paragraph (j)(2) of the 
NPRM (76 FR 34014, June 10, 2011) to allow operators to install owner/
operator fabricated replacement parts.
    Aero-Flite, Inc. stated that the requirement for replacing 
defective stiffeners with new stiffeners, and using original equipment 
manufacturer radius packers appears to eliminate the possibility of 
using engineering dispositions for serviceable stiffeners or fabricated 
radius packers. Aero-Flite, Inc. also stated that it finds that 
installing locally fabricated stiffeners and radius packers will not 
reduce the level of safety achieved, and that requiring the operator to 
install only new parts and radius packers purchased from the OEM may 
create a burden on the operator that may affect fire fighting mission 
availability and increase the cost of compliance without providing an 
improvement in safety.
    We disagree with the request to use locally or operator fabricated 
parts. The requested list of non-OEM substitute parts and materials is 
extensive and uncontrolled--and, in many cases, not FAA-approved. An 
operator may request approval of an AMOC in accordance with the 
provisions of paragraph (l)(1) of this AD. We have not changed this AD 
regarding this issue.

Explanation of Change Made to This AD

    We have revised the heading for and the wording in paragraph (k) of 
this AD; this change has not changed the intent of that paragraph.

Conclusion

    We reviewed the available data, including the comments received, 
and determined that air safety and the public interest require adopting 
the 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 (76 FR 34014, June 10, 2011) for correcting the unsafe condition; 
and
     Do not add any additional burden upon the public than was 
already proposed in the NPRM (76 FR 34014, June 10, 2011).

Differences Between This AD and the MCAI or Service Information

    This AD differs from the MCAI and/or service information as 
follows:
    Although Canadian Airworthiness Directive CF-2010-38R2, dated March 
17, 2011, has a compliance time of ``No later than 01 June 2011,'' for 
Part II--Terminating Action, this AD has a compliance time for a 
terminating action of ``Within 100 flight cycles or 60 days after the 
effective date of this AD, whichever occurs first.'' We have 
coordinated this difference with Transport Canada Civil Aviation 
(TCCA).
    Although Canadian Airworthiness Directive CF-2010-38R2, dated March 
17, 2011, has an initial compliance time of ``within 50 flight cycles 
after the effective date of this AD'' for identifying the type of rivet 
installed, this AD has a compliance time of ``within 50 flight cycles 
or 30 days after the effective date of this AD, whichever occurs 
first.'' In addition, the follow-on inspections in paragraph (i) of 
this AD for airplanes on which flush rivets are determined to be 
installed, is ``within 100 flight cycles or 60 days after the effective 
date of this AD, whichever occurs first.'' We have coordinated this 
difference with TCCA.

Costs of Compliance

    We estimate that this AD will affect 6 products of U.S. registry. 
We also estimate that it will take about 40 work-hours per product to 
comply with the basic requirements of this AD. The average labor rate 
is $85 per work-hour. Based on these figures, we estimate the cost of 
this AD to the U.S. operators to be $20,400, or $3,400 per product.
    We have received no definitive data that would enable us to provide 
a cost estimate for the on-condition actions specified in this AD. We 
have no way of determining the number of products that may need these 
actions.

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.
    We prepared a regulatory evaluation of the estimated costs to 
comply with this AD and placed it in the AD docket.

Examining the AD Docket

    You may examine the AD docket on the Internet at http://www.regulations.gov; 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 the NPRM, 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.

[[Page 16154]]

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 AD:

2012-05-05 Bombardier, Inc.: Amendment 39-16977. Docket No. FAA-
2011-0565; Directorate Identifier 2010-NM-280-AD.

(a) Effective Date

    This airworthiness directive (AD) becomes effective April 24, 
2012.

(b) Affected ADs

    None.

(c) Applicability

    This AD applies to Bombardier, Inc. Model CL-215-1A10 airplanes, 
serial numbers 1051 through 1125 inclusive; Model CL-215-6B11 (CL-
215T Variant) airplanes, serial numbers 1056 through 1125 inclusive; 
and Model CL-215-6B11 (CL-415 Variant) airplanes; serial numbers 
2001 through 2085 inclusive; certificated in any category.

(d) Subject

    Air Transport Association (ATA) of America Code 25: Equipment/
Furnishings.

(e) Reason

    This AD was prompted by reports of cracked or broken support 
bracket assemblies of the emergency water dump pulley. We are 
issuing this AD to detect and correct failure of the support bracket 
assembly of the emergency water dump pulley, and in combination with 
other system failures, such as an engine failure during take off or 
a pitch control system jam, may result in loss of controllability of 
the airplane.

(f) Compliance

    You are responsible for having the actions required by this AD 
performed within the compliance times specified, unless the actions 
have already been done.

(g) Inspections

    Within 50 flight cycles or 30 days after the effective date of 
this AD, whichever occurs first, do a general visual inspection to 
determine if either universal solid (round head) rivets or flush 
rivets of the bracket assembly of the emergency water dump pulley 
are installed, in accordance with the Accomplishment Instruction of 
Bombardier Alert Service Bulletin 215-A543, Revision 1, dated June 
23, 2010 (for Model CL-215-1A10 and CL-215-6B11 (CL-215T Variant) 
airplanes); or Bombardier Alert Service Bulletin 215-A4424, Revision 
2, dated June 23, 2010 (for Model CL-215-6B11 (CL-415 Variant) 
airplanes).

(h) Corrective Action if Universal Solid Rivets are Installed

    If, during the inspection required by paragraph (g) of this AD, 
universal solid rivets are determined to be installed: Within 50 
flight cycles or 30 days after the effective date of this AD, 
whichever occurs first, replace the solid rivets with flush rivets, 
and install new stiffeners on the bracket assembly of the emergency 
water dump pulley, in accordance with the Accomplishment 
Instructions of Bombardier Alert Service Bulletin 215-A543, Revision 
1, dated June 23, 2010 (for Model CL-215-1A10 and CL-215-6B11 (CL-
215T Variant) airplanes); or Bombardier Alert Service Bulletin 215-
A4424, Revision 2, dated June 23, 2010 (for Model CL-215-6B11 (CL-
415 Variant) airplanes).

(i) Corrective Action if Flush Rivets are Installed

    If, during the inspection required by paragraph (g) of this AD, 
flush rivets are determined to be installed; and for airplanes on 
which flush rivets are installed in accordance with paragraph (h) of 
this AD: Within 100 flight cycles or 60 days after the effective 
date of this AD, whichever occurs first, do a detailed inspection of 
the stiffeners for cracks, deformation, and signs of corrosion, in 
accordance with the Accomplishment Instructions of Bombardier Alert 
Service Bulletin 215-A543, Revision 1, dated June 23, 2010 (for 
Model CL-215-1A10 and CL-215-6B11 (CL-215T Variant) airplanes); or 
Bombardier Alert Service Bulletin 215-A4424, Revision 2, dated June 
23, 2010 (for Model CL-215-6B11 (CL-415 Variant) airplanes). 
Thereafter, at intervals not to exceed 100 flight cycles, repeat the 
detailed inspections of the stiffeners. If any crack, deformation, 
or signs of corrosion are found, before further flight, replace the 
stiffeners with new stiffeners, in accordance with the 
Accomplishment Instructions of Bombardier Alert Service Bulletin 
215-A543, Revision 1, dated June 23, 2010 (for Model CL-215-1A10 and 
CL-215-6B11 (CL-215T Variant) airplanes); or Bombardier Alert 
Service Bulletin 215-A4424, Revision 2, dated June 23, 2010 (for 
Model CL-215-6B11 (CL-415 Variant) airplanes).

(j) Terminating Action

    Within 100 flight cycles or 60 days after the effective date of 
this AD, whichever occurs first, do the actions specified in 
paragraphs (j)(1) and (j)(2) of this AD. Installation of the radius 
packers terminates the repetitive detailed inspections of the 
support bracket assembly of the emergency water dump pulley required 
by paragraph (i) of this AD.
    (1) Do a liquid penetrant inspection of the stiffeners having P/
N 215-94711-6 and P/N 215-94711-8 for cracks, deformation, or signs 
of corrosion, in accordance with the Accomplishment Instructions of 
Bombardier Alert Service Bulletin 215-A543, Revision 1, dated June 
23, 2010 (for Model CL-215-1A10 and CL-215-6B11 (CL-215T Variant) 
airplanes); or Bombardier Alert Service Bulletin 215-A4424, Revision 
2, dated June 23, 2010 (for Model CL-215-6B11 (CL-415 Variant) 
airplanes). If any crack, deformation, or sign of corrosion is 
found, before further flight, replace damaged stiffeners with new 
stiffeners, in accordance with the Accomplishment Instructions of 
Bombardier Alert Service Bulletin 215-A543, Revision 1, dated June 
23, 2010 (for Model CL-215-1A10 and CL-215-6B11 (CL-215T Variant) 
airplanes); or Bombardier Alert Service Bulletin 215-A4424, Revision 
2, dated June 23, 2010 (for Model CL-215-6B11 (CL-415 Variant) 
airplanes).
    (2) Re-install the bracket assembly of the emergency water dump 
pulley using radius packers, in accordance with the Accomplishment 
Instructions of Bombardier Alert Service Bulletin 215-A543, Revision 
1, dated June 23, 2010 (for Model CL-215-1A10 and CL-215-6B11 (CL-
215T Variant) airplanes); or Bombardier Alert Service Bulletin 215-
A4424, Revision 2, dated June 23, 2010 (for Model CL-215-6B11 (CL-
415 Variant) airplanes).

(k) Credit Previous Actions

    This paragraph provides credit for the actions required by 
paragraphs (g), (h), (i), and (j) of this AD, if the actions were 
performed before the effective date of this AD using the service 
information specified in paragraphs (k)(1), (k)(2), and (k)(3) of 
this AD.
    (1) Bombardier Service Bulletin 215-4424, dated January 25, 
2010.
    (2) Bombardier Alert Service Bulletin 215-A4424, Revision 1, 
dated May 18, 2010.
    (3) Bombardier Alert Service Bulletin 215-A543, dated May 19, 
2010.

(l) 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, 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, 
New York 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) Airworthy Product: For any requirement in this AD to obtain 
corrective actions from a manufacturer or other source, use these 
actions if they are FAA-approved. Corrective actions are considered 
FAA-approved if they are approved by the State of Design Authority 
(or their delegated agent). You are required to assure the product 
is airworthy before it is returned to service.

[[Page 16155]]

(m) Related Information

    Refer to MCAI Canadian Airworthiness Directive CF-2010-38R2, 
dated March 17, 2011, and the service information specified in 
paragraphs (m)(1) and (m)(2) of this AD; for related information.
    (1) Bombardier Alert Service Bulletin 215-A543, Revision 1, 
dated June 23, 2010.
    (2) Bombardier Alert Service Bulletin 215-A4424, Revision 2, 
dated June 23, 2010.

(n) Material Incorporated by Reference

    (1) You must use the following service information to do the 
actions required by this AD, unless the AD specifies otherwise. The 
Director of the Federal Register approved the incorporation by 
reference (IBR) of the following service information under 5 U.S.C. 
552(a) and 1 CFR part 51:
    (i) Bombardier Alert Service Bulletin 215-A543, Revision 1, 
dated June 23, 2010.
    (ii) Bombardier Alert Service Bulletin 215-A4424, Revision 2, 
dated June 23, 2010.
    (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 thd.crj@aero.bombardier.com; Internet http://www.bombardier.com.
    (3) You may review copies of the service information at the FAA, 
Transport Airplane Directorate, 1601 Lind Avenue SW., Renton, 
Washington. For information on the availability of this material at 
the FAA, call 425-227-1221.
    (4) You may also review copies of the 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/code_of_federal_regulations/ibr_locations.html.

    Issued in Renton, Washington, on March 1, 2012.
Jeffrey E. Duven,
Acting Manager, Transport Airplane Directorate, Aircraft Certification 
Service.
[FR Doc. 2012-6117 Filed 3-19-12; 8:45 am]
BILLING CODE 4910-13-P


