Document ID: FAA-2010-0039-0005
Agency: faa
Document Type: Rule
Title: Airworthiness Directives: Bombardier, Inc. Model CL-600-1A11 (CL-600), CL-600-2A12 (CL-601), CL-600-2B16 (CL-601-3A, CL-601-3R, and CL-604 Variants (Including CL-605 Marketing Variant)) Airplanes
Posted Date: 2010-07-01T04:00Z

[Federal Register: July 1, 2010 (Volume 75, Number 126)]
[Rules and Regulations]               
[Page 37994-37997]
From the Federal Register Online via GPO Access [wais.access.gpo.gov]
[DOCID:fr01jy10-4]                         

[[Page 37994]]

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DEPARTMENT OF TRANSPORTATION

Federal Aviation Administration

14 CFR Part 39

[Docket No. FAA-2010-0039; Directorate Identifier 2009-NM-239-AD; 
Amendment 39-16350; AD 2010-14-05]
RIN 2120-AA64

 
Airworthiness Directives; Bombardier, Inc. Model CL-600-1A11 (CL-
600), CL-600-2A12 (CL-601), CL-600-2B16 (CL-601-3A, CL-601-3R, and CL-
604 Variants (Including CL-605 Marketing Variant)) Airplanes

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

ACTION: Final rule.

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

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 on CL-600-2B19 (CRJ) aircraft, 
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 been identified that 
the worst case scenario would be failure of one of the brake 
accumulator screw caps/end caps, resulting in impact damage causing 
loss of both hydraulic systems No. 2 and No. 3, with consequent loss 
of both braking and nose wheel steering and the potential for a 
runway excursion [resulting in damage to the airplane and hazards to 
persons or property on the ground].
* * * * *

We are issuing this AD to require actions to correct the unsafe 
condition on these products.

DATES: This AD becomes effective August 5, 2010.
    The Director of the Federal Register approved the incorporation by 
reference of certain publications listed in this AD as of August 5, 
2010.

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: 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 February 12, 2010 
(75 FR 6862). 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. The lowest number 
of flight cycles accumulated at the time of failure, to date, has 
been 6991 flight cycles.
    Although there have been no failures to date on any CL-600-1A11, 
CL-600-2A12 or CL-600-2B16 aircraft, the same accumulators as those 
installed on the CL-600-2B19, Part Numbers (P/N) 08-60163-001, 08-
60163-002, 08-60164-001 and 08-60164-002, are installed on some of 
the aircraft listed in the Applicability section of this directive.
    Notes:
    1. Earlier accumulators, P/Ns 2770571-102, 2770571-103, 2770571-
104 and 2770571-105, were installed in production on the following 
aircraft: CL-600-1A11 [all Serial Numbers (S/Ns)], CL-600-2A12 (all 
S/Ns) and CL-600-2B16 (S/Ns 5001 through 5194 and 5301 through 5524 
only). These accumulators do not require inspection or replacement. 
However, if any of the accumulators with the above P/Ns have been 
replaced in-service by P/Ns 08-60163-001, 08-60163-002, 08-60164-001 
and 08-60164-002, these latter accumulators require replacement.
    2. The only accumulators ever installed on CL-600-2B16 aircraft, 
S/Ns 5525 through 5665 and 5701 and subsequent, are P/Ns 08-60163-
001, 08-60163-002, 08-60164-001 and 08-60164-002; these accumulators 
require replacement.
    A detailed analysis of the systems and structure in the 
potential line of trajectory of a failed screw cap/end cap for each 
accumulator, P/Ns 08-60163-001, 08-60163-002, 08-60164-001 and 08-
60164-002, has been conducted. It has been identified that the worst 
case scenario would be failure of one of the brake accumulator screw 
caps/end caps, resulting in impact damage causing loss of both 
hydraulic systems No. 2 and No. 3, with consequent loss of both 
braking and nose wheel steering and the potential for a runway 
excursion [resulting in damage to the airplane and hazards to 
persons or property on the ground].
    This directive gives instructions to perform identification and 
records checks, where applicable, and replace accumulators, P/Ns 08-
60163-001, 08-60163-002, 08-60164-001 and 08-60164-002, within the 
time compliance specified.

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 Revise the AD to Allow Replacement of Accumulators With an 
Overhauled or Refurbished Unit

    Bombardier Aerospace requests that we revise the NPRM to allow 
replacement of the accumulator with either a new accumulator with the 
same part number, or an overhauled accumulator with the same part 
number containing a T-suffix, in accordance with a future revision of 
the applicable service bulletin listed in the following table ``Service 
Bulletins.'' Bombardier states that Transport Canada Civil Aviation 
(TCCA) has been notified of this upcoming change, and a similar request 
will be made to revise Canadian Airworthiness Directive CF-2009-39, 
dated October 27, 2009.

                            Service Bulletins
------------------------------------------------------------------------
   Bombardier service bulletin--     Revision--          Dated--
------------------------------------------------------------------------
600-0742...........................          01  July 6, 2009.
601-0597...........................          01  July 6, 2009.
604-29-008.........................          01  July 6, 2009.
605-29-001.........................          01  July 6, 2009.
------------------------------------------------------------------------

     We agree with the request to revise the AD. Since the NPRM was 
issued, Bombardier has issued Revision 02 of the service bulletins, as 
specified in Table 1 of this AD. These revised service bulletins allow 
for the replacement of the accumulators with an overhauled or 
refurbished unit identified by a ``T'' or ``TNA'' suffix. Paragraph (g) 
of this AD has been changed accordingly.

Request for Confirmation of Compliance Time

    Pittco, Inc., requests confirmation that a calendar or schedule 
requirement for the replacement of the system accumulators will not be 
added. The commenter states that according to the compliance time in 
the proposed AD, airplanes with low flight cycles could take many years 
to reach the threshold to replace the accumulator. The

[[Page 37995]]

commenter wants to confirm that this compliance time is acceptable and 
will not be changed to a calendar or schedule requirement.
    We confirm that accumulator failures are based on flight cycles and 
not calendar schedule. The compliance times for this AD are based on a 
parameter related to failure of a particular component. In this case 
the failure of an accumulator screw cap or end cap is related to the 
number of flight cycles. Therefore, this AD includes no calendar or 
schedule requirement. No change has been made to the AD in this regard.

Request for Clarification of Compliance Time

    Pittco, Inc., requests clarification regarding the manufacturer's 
compliance time for replacing the accumulator. The commenter states 
that the service bulletin recommends not replacing the accumulator 
earlier than at the due cycles.
    We agree that clarification is necessary. The manufacturer's 
recommendation was based on the availability of parts. According to the 
MCAI and this AD, replacement of the accumulators is required 
``within'' the applicable number of flight cycles, rather than the 
service bulletin's compliance time of replacing the accumulators ``at'' 
3,750 landings. Operators are permitted to accomplish the requirements 
of this AD before the specified compliance time. No change has been 
made to the AD in this regard.

Request for Clarification of Inspections in the Original and Revision 
01 of Bombardier Service Bulletin 601-0597

    Pittco, Inc., requests a change of wording to state that Bombardier 
Service Bulletin 601-0597, dated November 10, 2008, specifies an 
inspection; and that Bombardier Service Bulletin 601-0597, Revision 01, 
dated July 6, 2009, does not specify an inspection, but merely provides 
data for replacement of the accumulators. The commenter requests that 
stronger language be incorporated to clarify the difference.
    We find that clarification is necessary. The actions required by 
paragraph (g) of the AD include an inspection, which is not specified 
in Revision 01 of the applicable service bulletin specified in Table 2 
of this AD, to determine if the airplane has an affected accumulator. 
If the airplane has an affected accumulator, it must be replaced within 
the specified number of flight cycles. Credit for the previous 
accomplishment of the original version of the applicable service 
bulletin specified in Table 2 of this AD as noted in paragraph (g)(4) 
of the AD, is for the replacement of an accumulator with a new 
accumulator having the same part number, which is also acceptable for 
compliance with the requirements of paragraph (g)(2) of the AD. An 
ultrasonic inspection for cracking, which was specified in the original 
version of the applicable service bulletins specified in Table 2 of 
this AD, was removed from Revision 01 of these service bulletins, and 
is no longer required. No change has been made to the AD in this 
regard.

Request for Addition of Equivalent Part Numbers to AD

    Pittco, Inc., requests the addition of equivalent part numbers to 
the proposed AD. The commenter states that Bombardier and its vendors 
use the terms ``specification numbers'' and ``part numbers'' 
synonymously, which is not consistent with the service bulletins listed 
in Table 1 of the NPRM. The commenter states that there are other 
identification numbers that are likely to be found during a review of 
the maintenance records. The commenter states that the service 
bulletins listed in Table 1 of the NPRM have tables that specify 
equivalent Bombardier part numbers. The commenter requests that the 
equivalent part numbers be added to the AD.
    We agree. This AD requires an inspection to determine the part 
numbers of the system accumulators that are installed on the airplane. 
This AD also states that a review of airplane maintenance records is 
acceptable in lieu of this inspection if the part number of the 
accumulator can be conclusively determined from that review. The 
service bulletins listed in Table 1 of this AD list the equivalent 
Bombardier accumulator part numbers to identify the suspect system 
accumulators; therefore, we have added those equivalent part numbers in 
parentheses in paragraphs (g)(2)(i), (g)(2)(ii), (g)(2)(iii), and 
(g)(3) of this AD.

Conclusion

    We reviewed the available data, including the comments received, 
and determined that air safety and the public interest require adopting 
the AD with the changes described previously. We determined that these 
changes will not increase the economic burden on any operator or 
increase the scope of the AD.

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 340 products of U.S. registry. 
We also estimate that it will take about 20 work-hours per product to 
comply with the basic requirements of this AD. The average labor rate 
is $85 per work-hour. Required parts will cost about $7,717 per 
product. Where the service information lists required parts costs that 
are covered under warranty, we have assumed that there will be no 
charge for these parts. As we do not control warranty coverage for 
affected parties, some parties may incur costs higher than estimated 
here. Based on these figures, we estimate the cost of this AD to the 
U.S. operators to be $3,201,780, or $9,417 per product.

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.

[[Page 37996]]

    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

0
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:

2010-14-05 Bombardier, Inc.: Amendment 39-16350. Docket No. FAA-
2010-0039; Directorate Identifier 2009-NM-239-AD.

Effective Date

    (a) This airworthiness directive (AD) becomes effective August 
5, 2010.

Affected ADs

    (b) None.

Applicability

    (c) This AD applies to the Bombardier, Inc. airplanes, 
certificated in any category, identified in paragraphs (c)(1), 
(c)(2), and (c)(3) of this AD.
    (1) Bombardier, Inc. Model CL-600-1A11 (CL-600) airplanes, 
serial numbers 1004 through 1085 inclusive;
    (2) Bombardier, Inc. CL-600-2A12 (CL-601) airplanes, serial 
numbers 3001 through 3066 inclusive; and
    (3) Bombardier, Inc. CL-600-2B16 (CL-601-3A, CL-601-3R, and CL-
604) airplanes, serial numbers 5001 through 5194 inclusive, 5301 
through 5665 inclusive, and 5701 and subsequent.

    Note 1: Some Model CL-600-2B16 (CL-604) airplanes might be 
referred to by the marketing designation CL-605 in the applicable 
service bulletins listed in Table 1 of this AD.

Subject

    (d) Air Transport Association (ATA) of America Code 29: 
Hydraulic power.

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 on CL-600-2B19 (CRJ) aircraft, 
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 been identified that 
the worst case scenario would be failure of one of the brake 
accumulator screw caps/end caps, resulting in impact damage causing 
loss of both hydraulic systems No. 2 and No. 3, with consequent loss 
of both braking and nose wheel steering and the potential for a 
runway excursion [resulting in damage to the airplane and hazards to 
persons or property on the ground].
* * * * *

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.

Actions

    (g) Do the following actions as applicable.
    (1) Within 50 flight hours after the effective date of this AD, 
inspect to determine the part numbers of the system accumulators 
numbers 1, 2, and 3 and brake accumulators numbers 2 and 3 that are 
installed on the airplane. A review of airplane maintenance records 
is acceptable in lieu of this inspection if the part number of the 
accumulator can be conclusively determined from that review. If all 
of the installed accumulators have P/N 2770571-102, 2770571-103, 
2770571-104, or 2770571-105, no further action is required by this 
AD.
    (2) At the applicable time in paragraph (g)(2)(i), (g)(2)(ii), 
or (g)(2)(iii) of this AD, replace the accumulator with a new, 
overhauled, or refurbished accumulator with the same part number, in 
accordance with the Accomplishment Instructions of the applicable 
service bulletin listed in Table 1 of this AD.

                                           Table 1--Service Bulletins
----------------------------------------------------------------------------------------------------------------
                                           Bombardier
            Airplane model--                 service       Revision--                    Dated--
                                           bulletin--
----------------------------------------------------------------------------------------------------------------
CL-600-1A11 (CL-600)...................        600-0742              02  May 10, 2010.
CL-600-2A12 (CL-601), CL-600-2B16 (CL-         601-0597              02  May 10, 2010.
 601-3A, CL-601-3R variant).
CL-600-2B16 (CL-604 variant)...........      604-29-008              02  May 10, 2010.
CL-600-2B16 (CL-605)...................      605-29-001              02  May 10, 2010.
----------------------------------------------------------------------------------------------------------------

     (i) For each accumulator having P/Ns 08-60163-001 (601R75138-
1), 08-60163-002 (601R75138-1), 08-60164-001 (601R75138-3), and 08-
60164-002 (601R75138-3), as applicable, that has accumulated more 
than 3,650 total flight cycles as of the effective date of this AD: 
Replace the accumulator within 100 flight cycles after the effective 
date of this AD.
    (ii) For each accumulator having P/N 08-60163-001 (601R75138-1), 
08-60163-002 (601R75138-1), 08-60164-001 (601R75138-3), and 08-
60164-002 (601R75138-3), as applicable, that has accumulated 3,650 
total flight cycles or fewer as of the effective date of this AD: 
Replace the accumulator before the accumulation of 3,750 total 
flight cycles on the accumulator.
    (iii) For each accumulator having P/N 08-60163-001 (601R75138-
1), 08-60163-002 (601R75138-1), 08-60164-001 (601R75138-3), and 08-
60164-002 (601R75138-3), as applicable, for which it is not possible 
to determine the number of flight cycles accumulated: Replace the 
accumulator within 100 flight cycles after the effective date of 
this AD.
    (3) Thereafter, before the accumulation of 3,750 total flight 
cycles on any accumulator having P/Ns 08-60163-001 (601R75138-1), 
08-60163-002 (601R75138-1), 08-60164-001 (601R75138-3), and 08-
60164-002 (601R75138-3), as applicable, replace the accumulator with 
a new, overhauled, or refurbished accumulator having the same part 
number, in accordance with the

[[Page 37997]]

Accomplishment Instructions of the applicable service bulletin 
listed in Table 1 of this AD.

    Note 2:  The part numbers in parentheses in paragraphs 
(g)(2)(i), (g)(2)(ii), (g)(2)(iii), and (g)(3) of this AD, are 
equivalent specification part numbers, as specified in the 
applicable service bulletin listed in Table 1 of this AD.

    (4) Replacement of an accumulator with a new accumulator having 
the same part number is also acceptable for compliance with the 
requirements of paragraph (g)(2) of this AD, if done before the 
effective date of this AD in accordance with the applicable service 
bulletin listed in Table 2 of this AD.

                                       Table 2--Previous Service Bulletins
----------------------------------------------------------------------------------------------------------------
                                       Bombardier
          Airplane model--               service            Revision--                      Dated--
                                       bulletin--
----------------------------------------------------------------------------------------------------------------
CL-600-1A11 (CL-600)...............        600-0742  Original...............  November 10, 2008.
CL-600-1A11 (CL-600)...............        600-0742  01.....................  July 6, 2009.
CL-600-2A12 (CL-601), CL-600-2B16          601-0597  Original...............  November 10, 2008.
 (CL-601-3A, CL-601-3R variant).
CL-600-2A12 (CL-601), CL-600-2B16          601-0597  01.....................  July 6, 2009.
 (CL-601-3A, CL-601-3R variant).
CL-600-2B16 (CL-604 variant).......      604-29-008  Original...............  November 10, 2008.
CL-600-2B16 (CL-604 variant).......      604-29-008  01.....................  July 6, 2009.
CL-600-2B16 (CL-605)...............      605-29-001  Original...............  November 10, 2008.
CL-600-2B16 (CL-605)...............      605-29-001  01.....................  July 6, 2009.
----------------------------------------------------------------------------------------------------------------

FAA AD Differences

    Note 3:  This AD differs from the MCAI and/or service 
information as follows:
    (1) The MCAI specifies that certain airplanes do not need to be 
inspected for the part number; however, this AD requires that 
inspections be done on all airplanes to determine the part number.
    (2) The MCAI specifies to record the number of flight cycles 
accumulated on each affected part. This AD does not require that 
operators record the number of flight cycles.

Other FAA AD Provisions

    (h) 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 Avenue, Suite 410, Westbury, New York, 11590; telephone 516-
228-7300; fax 516-794-5531. Before using any approved AMOC on any 
airplane to which the AMOC applies, notify your principal 
maintenance inspector (PMI) or principal avionics inspector (PAI), 
as appropriate, or lacking a principal inspector, your local Flight 
Standards 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: For any reporting requirement in 
this AD, under the provisions of the Paperwork Reduction Act (44 
U.S.C. 3501 et seq.), the Office of Management and Budget (OMB) has 
approved the information collection requirements and has assigned 
OMB Control Number 2120-0056.

Related Information

    (i) Refer to MCAI Canadian Airworthiness Directive CF-2009-39, 
dated October 27, 2009, and the service bulletins listed in Table 1 
of this AD, for related information.

Material Incorporated by Reference

    (j) You must use the service information contained in Table 3 of 
this AD, as applicable, 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
------------------------------------------------------------------------
   Bombardier service  bulletin--    Revision--          Dated--
------------------------------------------------------------------------
600-0742...........................          02  May 10, 2010.
601-0597...........................          02  May 10, 2010.
604-29-008.........................          02  May 10, 2010.
605-29-001.........................          02  May 10, 2010.
------------------------------------------------------------------------

    Issued in Renton, Washington, on June 17, 2010.
Robert D. Breneman,
Acting Manager, Transport Airplane Directorate, Aircraft Certification 
Service.
[FR Doc. 2010-15845 Filed 6-30-10; 8:45 am]
BILLING CODE 4910-13-P