Document ID: FAA-2010-1108-0003
Agency: faa
Document Type: Rule
Title: Airworthiness Directives: Bombardier, Inc. Model CL-215-1A10, CL-215-6B11 (CL-215T Variant), and CL-215-6B11 (CL-415 Variant) Airplanes
Posted Date: 2011-02-07T05:00Z

[Federal Register Volume 76, Number 25 (Monday, February 7, 2011)]
[Rules and Regulations]
[Pages 6536-6539]
From the Federal Register Online via the Government Printing Office [www.gpo.gov]
[FR Doc No: 2011-2444]

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DEPARTMENT OF TRANSPORTATION

Federal Aviation Administration

14 CFR Part 39

[Docket No. FAA-2010-1108; Directorate Identifier 2010-NM-151-AD; 
Amendment 39-16592; AD 2011-03-08]
RIN 2120-AA64

Airworthiness Directives; Bombardier, Inc. Model CL-215-1A10 (CL-
215), CL-215-6B11 (CL-215T Variant), and CL-215-6B11 (CL-415 Variant) 
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 the 
products listed above. This 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:

    Seven cases of on-ground hydraulic accumulator screw cap or end 
cap failure have been experienced * * * resulting in loss of the 
associated hydraulic system and high-energy impact damage to 
adjacent systems and structure. * * *
* * * * *
    A detailed analysis of the systems and structure in the 
potential line of trajectory of a failed screw cap/end cap for each 
accumulator has been conducted. It has identified that the worst-
case scenarios would be impact damage to various components, 
potentially resulting in fuel spillage, uncommanded flap movement, 
or loss of aileron control [and consequent reduced controllability 
of the airplane].
* * * * *
    We are issuing this AD to require actions to correct the unsafe 
condition on these products.

DATES: This AD becomes effective March 14, 2011.
    The Director of the Federal Register approved the incorporation by 
reference of certain publications listed in this AD as of March 14, 
2011.

ADDRESSES: You may examine the AD docket on the Internet at http://www.regulations.gov or in person at the

[[Page 6537]]

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: Christopher Alfano, 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) 228-7340; 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 November 9, 2010 (75 
FR 68728). That NPRM proposed to correct an unsafe condition for the 
specified products. The MCAI states:

    Seven cases of on-ground hydraulic accumulator screw cap or end 
cap failure have been experienced on CL-600-2B19 (CRJ) aircraft, 
resulting in loss of the associated hydraulic system and high-energy 
impact damage to adjacent systems and structure. To date, the lowest 
number of flight cycles accumulated at the time of failure has been 
6991.
    Although there have been no failures to date on any CL-215-1A10 
(CL-215) or CL-215-6B11 (CL-215T and CL-415) aircraft, similar 
accumulators, Part Number (P/N) 08-8423-010 (MS28700-3), to those 
installed on the CL-600-2B19, are installed on the aircraft listed 
in the Applicability section of this directive [MCAI].
    A detailed analysis of the systems and structure in the 
potential line of trajectory of a failed screw cap/end cap for each 
accumulator has been conducted. It has identified that the worst-
case scenarios would be impact damage to various components, 
potentially resulting in fuel spillage, uncommanded flap movement, 
or loss of aileron control [and consequent reduced controllability 
of the airplane].
    This directive [MCAI] mandates repetitive [ultrasonic] 
inspections of the accumulators for cracks and replacement of any 
accumulator in which a crack is detected.

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 received no comments on the NPRM or on the determination of 
the cost to the public.

Conclusion

    We reviewed the available data and determined that air safety and 
the public interest require adopting the AD as proposed.

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 required different actions in this AD from those 
in the MCAI in order to follow our FAA policies. Any such differences 
are highlighted in a Note within the AD.

Costs of Compliance

    We estimate that this AD will affect 6 products of U.S. registry. 
We also estimate that it will take about 7 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 $3,570, or $595 per product.
    In addition, we estimate that any necessary follow-on actions would 
take about 6 work-hours and require parts costing $4,055, for a cost of 
$4,565 per product. 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 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); 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 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.

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:

2011-03-08 Bombardier, Inc.: Amendment 39-16592. Docket No. FAA-
2010-1108; Directorate Identifier 2010-NM-151-AD.

Effective Date

    (a) This airworthiness directive (AD) becomes effective March 
14, 2011.

Affected ADs

    (b) None.

Applicability

    (c) This AD applies to Bombardier, Inc. airplanes, certificated 
in any category, identified in paragraphs (c)(1), (c)(2), and (c)(3) 
of this AD.

[[Page 6538]]

    (1) Model CL-215-1A10 (CL-215) airplanes, serial numbers 1001 
through 1990 inclusive;
    (2) Model CL-215-6B11 (CL-215T Variant) airplanes, serial 
numbers 1056 through 1125 inclusive;
    (3) Model CL-215-6B11 (CL-415 Variant) airplanes, serial numbers 
2001 through 2990 inclusive.

Subject

    (d) Air Transport Association (ATA) of America Code 27: Flight 
controls; and 32: Landing gear.

Reason

    (e) The mandatory continuing airworthiness information (MCAI) 
states:
    Seven cases of on-ground hydraulic accumulator screw cap or end 
cap failure have been experienced * * * resulting in loss of the 
associated hydraulic system and high-energy impact damage to 
adjacent systems and structure. * * *
* * * * *
    A detailed analysis of the systems and structure in the 
potential line of trajectory of a failed screw cap/end cap for each 
accumulator has been conducted. It has identified that the worst-
case scenarios would be impact damage to various components, 
potentially resulting in fuel spillage, uncommanded flap movement, 
or loss of aileron control [and consequent reduced controllability 
of the airplane].
* * * * *

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.

Inspection to Determine Flight Hours

    (g) Within 50 flight hours after the effective date of this AD, 
inspect to determine the number of flight cycles accumulated by each 
of the applicable accumulators (i.e., brake, aileron, elevator, and 
rudder accumulators) having part number (P/N) 08-8423-010 (MS28700-
3) installed on the airplane. A review of airplane maintenance 
records is acceptable in lieu of this inspection if the number of 
flight cycles accumulated can be conclusively determined from that 
review.

Initial Ultrasonic Inspection

    (h) For Model CL-215-1A10 (CL-215) and CL-215-6B11 (CL-215T) 
airplanes: do an ultrasonic inspection for cracking of the 
accumulator at the applicable time specified in paragraph (h)(1) or 
(h)(2) of this AD, in accordance with Part B of the Accomplishment 
Instructions of the applicable service bulletin listed in table 1 of 
this AD.

                                           Table 1--Service Bulletins
----------------------------------------------------------------------------------------------------------------
                                               Use Bombardier
                For model--                  Service Bulletin--   Revision--                Dated--
----------------------------------------------------------------------------------------------------------------
CL-215-1A10 (CL-215)......................              215-541            1  March 12, 2010.
CL-215-6B11 (CL-215T).....................             215-3155            1  March 12, 2010.
CL-600-6B11 (CL-415)......................             215-4414            1  March 12, 2010.
----------------------------------------------------------------------------------------------------------------

     (1) For any accumulator on which the inspection required by 
paragraph (g) of this AD shows an accumulation of more than 875 
total flight cycles or on which it is not possible to determine the 
number of total accumulated flight cycles, do the inspection within 
125 flight cycles after the effective date of this AD.
    (2) For any accumulator on which the inspection required by 
paragraph (g) of this AD shows an accumulation of 875 total flight 
cycles or fewer, do the inspection before the accumulation of 1,000 
flight cycles on the accumulator.
    (i) For Model CL-215-6B11 (CL-415) airplanes, do an ultrasonic 
inspection for cracking of the accumulator at the applicable time 
specified in paragraph (i)(1) or (i)(2) of this AD, in accordance 
with Part B of the Accomplishment Instructions of the applicable 
service bulletin listed in Table 1 of this AD.
    (1) For any accumulator on which the inspection required by 
paragraph (g) of this AD shows an accumulation of more than 750 
flight cycles or on which it is not possible to determine the number 
of total accumulated flight cycles, do the inspection within 250 
flight cycles after the effective date of this AD.
    (2) For any accumulator on which the inspection required by 
paragraph (g) of this AD shows an accumulation of 750 total flight 
cycles or fewer, do the inspection before the accumulation of 1,000 
flight cycles on the accumulator.

Repetitive Inspections

    (j) If no cracking is found during any inspection required by 
paragraph (h) or (i) of this AD, repeat the inspection thereafter at 
intervals not to exceed 750 flight cycles.
    (k) If any cracking is found during any inspection required by 
paragraph (h) or (i) of this AD, before further flight, replace the 
accumulator with a serviceable accumulator, in accordance with Part 
B of the Accomplishment Instructions of the applicable service 
bulletin listed in Table 1 of this AD. Doing the replacement does 
not end the inspection requirements of this AD. Repeat the 
inspections required by paragraph (h) or (i) of this AD at intervals 
not to exceed 750 flight cycles.

Parts Installation

    (l) As of the effective date of this AD, no person may install 
an accumulator (P/N) 08-8423-010 (MS28700-3) on any airplane unless 
the accumulator has been inspected in accordance with the 
requirements of this AD.

Credit for Actions Accomplished in Accordance With Previous Service 
Information

    (m) Inspections accomplished before the effective date of this 
AD in accordance with the applicable service bulletin listed in 
Table 2 of this AD are considered acceptable for compliance with the 
corresponding action specified in this AD.

                    Table 2--Credit Service Bulletins
------------------------------------------------------------------------
                                  Use Bombardier
         For model--            Service Bulletin--         Dated--
------------------------------------------------------------------------
CL-215-1A10 (CL-215).........              215-541  July 9, 2009.
CL-215-6B11 (CL-215T)........             215-3155  July 9, 2009.
CL-600-6B11 (CL-415).........             215-4414  July 9, 2009.
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FAA AD Differences

    Note 1: This AD differs from the MCAI and/or service information 
as follows:
    No differences.

Other FAA AD Provisions

    (n) 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. Send information to Attn: Program 
Manager, Continuing Operational Safety, FAA, New York ACO, 1600 
Stewart

[[Page 6539]]

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.
    (3) Reporting Requirements: A federal agency may not conduct or 
sponsor, and a person is not required to respond to, nor shall a 
person be subject to a penalty for failure to comply with a 
collection of information subject to the requirements of the 
Paperwork Reduction Act unless that collection of information 
displays a current valid OMB Control Number. The OMB Control Number 
for this information collection is 2120-0056. Public reporting for 
this collection of information is estimated to be approximately 5 
minutes per response, including the time for reviewing instructions, 
completing and reviewing the collection of information. All 
responses to this collection of information are mandatory. Comments 
concerning the accuracy of this burden and suggestions for reducing 
the burden should be directed to the FAA at: 800 Independence Ave., 
SW., Washington, DC 20591, Attn: Information Collection Clearance 
Officer, AES-200.

Related Information

    (o) Refer to MCAI Canadian Airworthiness Directive CF-2009-42R1, 
dated May 14, 2010; and the service bulletins listed in table 1 of 
this AD; for related information.

Material Incorporated by Reference

    (p) You must use the service information contained in Table 3 of 
this AD to do the actions required by this AD, unless the AD 
specifies otherwise.
    (1) The Director of the Federal Register approved the 
incorporation by reference of this service information under 5 
U.S.C. 552(a) and 1 CFR part 51.
    (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; e-mail 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.

               Table 3--Material Incorporated by Reference
------------------------------------------------------------------------
             Document                Revision             Date
------------------------------------------------------------------------
Bombardier Service Bulletin 215-             1  March 12, 2010.
 541.
Bombardier Service Bulletin 215-             1  March 12, 2010.
 3155.
Bombardier Service Bulletin 215-             1  March 12, 2010.
 4414.
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    Issued in Renton, Washington, on January 26, 2011.
Ali Bahrami,
Manager, Transport Airplane Directorate, Aircraft Certification 
Service.
[FR Doc. 2011-2444 Filed 2-4-11; 8:45 am]
BILLING CODE 4910-13-P