
[Federal Register Volume 76, Number 112 (Friday, June 10, 2011)]
[Proposed Rules]
[Pages 34014-34017]
From the Federal Register Online via the Government Printing Office [www.gpo.gov]
[FR Doc No: 2011-14397]


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

DEPARTMENT OF TRANSPORTATION

Federal Aviation Administration

14 CFR Part 39

[Docket No. FAA-2011-0565; Directorate Identifier 2010-NM-280-AD]
RIN 2120-AA64


Airworthiness Directives; Bombardier, Inc. Model CL-215-1A10, CL-
215-6B11 (CL-215T Variant), and CL-215-6B11 (CL-415 Variant) Airplanes

AGENCY: Federal Aviation Administration (FAA), DOT.

ACTION: Notice of proposed rulemaking (NPRM).

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

SUMMARY: We propose to adopt a new airworthiness directive (AD) for the 
products listed above. This proposed AD results from mandatory 
continuing airworthiness information (MCAI) originated by an aviation 
authority of another country to identify and correct an unsafe 
condition on an aviation product. The MCAI describes the unsafe 
condition as:

    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.
* * * * *

    The proposed AD would require actions that are intended to address 
the unsafe condition described in the MCAI.

DATES: We must receive comments on this proposed AD by July 25, 2011.

ADDRESSES: You may send comments by any of the following methods:
     Federal eRulemaking Portal: Go to http://www.regulations.gov. Follow the instructions for submitting comments.
     Fax: (202) 493-2251.
     Mail: U.S. Department of Transportation, Docket 
Operations, M-30, West Building Ground Floor, Room W12-140, 1200 New 
Jersey Avenue, SE., Washington, DC 20590.
     Hand Delivery: U.S. Department of Transportation, Docket 
Operations, M-30, West Building Ground Floor, Room W12-40, 1200 New 
Jersey Avenue, SE., Washington, DC, between 9 a.m. and 5 p.m., Monday 
through Friday, except Federal holidays.
    For service information identified in this proposed AD, contact 
Bombardier,

[[Page 34015]]

Inc., 400 C[ocirc]te-Vertu Road West, Dorval, Qu[eacute]bec H4S 1Y9, 
Canada; telephone 514-855-5000; fax 514-855-7401; e-mail 
thd.crj@aero.bombardier.com; Internet http://www.bombardier.com. You 
may review copies of the referenced 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.

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 this proposed AD, the regulatory 
evaluation, any comments received, and other information. The street 
address for the Docket Operations office (telephone (800) 647-5527) is 
in the ADDRESSES section. Comments will be available in the AD docket 
shortly after receipt.

FOR FURTHER INFORMATION CONTACT: Andy 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:

Comments Invited

    We invite you to send any written relevant data, views, or 
arguments about this proposed AD. Send your comments to an address 
listed under the ADDRESSES section. Include ``Docket No. FAA-2011-0565; 
Directorate Identifier 2010-NM-280-AD'' at the beginning of your 
comments. We specifically invite comments on the overall regulatory, 
economic, environmental, and energy aspects of this proposed AD. We 
will consider all comments received by the closing date and may amend 
this proposed AD based on those comments.
    We will post all comments we receive, without change, to http://www.regulations.gov, including any personal information you provide. We 
will also post a report summarizing each substantive verbal contact we 
receive about this proposed AD.

Discussion

    Transport Canada Civil Aviation, which is the aviation authority 
for Canada, has issued Canadian Airworthiness Directive CF-2010-38R2, 
dated March 17, 2011 (referred to after this as ``the MCAI''), 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 AD is issued to ensure that terminating 
action for this 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.

Relevant Service Information

    Bombardier, Inc. has issued Service Bulletin 215-A543, Revision 1, 
dated June 23, 2010; and Service Bulletin 215-A4424, Revision 2, dated 
June 23, 2010. The actions described in this service information are 
intended to correct the unsafe condition identified in the MCAI.

FAA's Determination and Requirements of This Proposed AD

    This product has been approved by the aviation authority of another 
country, and is approved for operation in the United States. Pursuant 
to our bilateral agreement with the State of Design Authority, we have 
been notified of the unsafe condition described in the MCAI and service 
information referenced above. We are proposing this AD because we 
evaluated all pertinent information and determined an unsafe condition 
exists and is likely to exist or develop on other products of the same 
type design.

Differences Between This AD and the MCAI or Service Information

    We have reviewed the MCAI and related service information and, in 
general, agree with their substance. But we might have found it 
necessary to use different words from those in the MCAI to ensure the 
AD is clear for U.S. operators and is enforceable. In making these 
changes, we do not intend to differ substantively from the information 
provided in the MCAI and related service information.
    We might also have proposed different actions in this AD from those 
in the MCAI in order to follow FAA policies. Any such differences are 
highlighted in a Note within the proposed AD.

Costs of Compliance

    Based on the service information, we estimate that this proposed AD 
would affect about 6 products of U.S. registry. We also estimate that 
it would take about 40 work-hours per product to comply with the basic 
requirements of this proposed AD. The average labor rate is $85 per 
work-hour. Based on these figures, we estimate the cost of the proposed 
AD on 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.

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 proposed AD would not have federalism 
implications under Executive Order 13132. This proposed AD would not 
have a substantial direct effect on the States, on the relationship 
between the national Government and the States, or on the distribution 
of power and responsibilities among the various levels of government.
    For the reasons discussed above, I certify this proposed 
regulation:

[[Page 34016]]

    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); and
    3. 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 proposed AD and placed it in the AD docket.

List of Subjects in 14 CFR Part 39

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

The Proposed Amendment

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

PART 39--AIRWORTHINESS DIRECTIVES

    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]

    2. The FAA amends Sec.  39.13 by adding the following new AD:

Bombardier, Inc.: Docket No. FAA-2011-0565; Directorate Identifier 
2010-NM-280-AD.

Comments Due Date

    (a) We must receive comments by July 25, 2011.

Affected ADs

    (b) None.

Applicability

    (c) 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.

Subject

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

Reason

    (e) The mandatory continuing airworthiness information (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.
* * * * *

Compliance

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

Inspections and Corrective Actions

    (g) 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 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 Service Bulletin 215-A4424, Revision 2, 
dated June 23, 2010 (for Model CL-215-6B11 (CL-415 Variant) 
airplanes).
    (h) 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 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 Service Bulletin 215-A4424, 
Revision 2, dated June 23, 2010 (for Model CL-215-6B11 (CL-415 
Variant) airplanes).
    (i) 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 
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 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 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 Service Bulletin 
215-A4424, Revision 2, dated June 23, 2010 (for Model CL-215-6B11 
(CL-415 Variant) airplanes).
    (j) 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 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 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 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 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 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 Service Bulletin 215-A4424, 
Revision 2, dated June 23, 2010 (for Model CL-215-6B11 (CL-415 
Variant) airplanes).

Credit for Actions Accomplished in Accordance With Previous Service 
Information

    (k) Actions accomplished before the effective date of this AD 
according to the service bulletins specified in Table 1 of this AD, 
are considered acceptable for compliance with the corresponding 
actions specified in this AD.

                                      Table 1--Service Bulletins for Credit
----------------------------------------------------------------------------------------------------------------
      Bombardier service bulletin--                 Revision--                           Dated--
----------------------------------------------------------------------------------------------------------------
215[dash]4424............................  Original....................  January 25, 2010.
215[dash]A4424...........................  1...........................  May 18, 2010.
215[dash]A543............................  Original....................  May 19, 2010.
----------------------------------------------------------------------------------------------------------------


[[Page 34017]]

FAA AD Differences

    Note 1:  This AD differs from the MCAI and/or service 
information as follows:
    (1) 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 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).
    (2) 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.

Other FAA AD Provisions

    (l) 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.

Related Information

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

    Issued in Renton, Washington, on June 2, 2011.
Kalene C. Yanamura,
Acting Manager, Transport Airplane Directorate, Aircraft Certification 
Service.
[FR Doc. 2011-14397 Filed 6-9-11; 8:45 am]
BILLING CODE 4910-13-P


