Airworthiness Directives; Bombardier Model CL-215-6B11 (CL215T Variant) and CL-215-6B11 (CL415 Variant) Series Airplanes

[Federal Register Volume 70, Number 3 (Wednesday, January 5, 2005)]
[Rules and Regulations]
[Pages 684-685]
From the Federal Register Online via the Government Publishing Office [www.gpo.gov]
[FR Doc No: 05-101]


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

DEPARTMENT OF TRANSPORTATION

Federal Aviation Administration

14 CFR Part 39

[Docket No. FAA-2004-19496; Directorate Identifier 2003-NM-181-AD; 
Amendment 39-13920; AD 2004-26-08]
RIN 2120-AA64


Airworthiness Directives; Bombardier Model CL-215-6B11 (CL215T 
Variant) and CL-215-6B11 (CL415 Variant) Series Airplanes

AGENCY: Federal Aviation Administration (FAA), DOT.

ACTION: Final rule.

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

SUMMARY: The FAA is adopting a new airworthiness directive (AD) for 
certain Bombardier Model CL-215-6B11 (CL215T variant) and CL-215-6B11 
(CL415 variant) series airplanes. This AD requires replacing the 
mounting pad studs of the auxiliary feather pump with new, longer 
studs, and installing a pressure relief valve. This AD is prompted by a 
few incidents of external oil leaks from the oil pump of the power 
control unit due to a malfunction of the pressure regulating valve. We 
are issuing this AD to prevent fracturing of the pump body, which could 
result in loss of engine oil, and consequent inability to maintain 
engine oil pressure and to feather the propeller.

DATES: This AD becomes effective February 9, 2005.
    The incorporation by reference of certain publications listed in 
the AD is approved by the Director of the Federal Register as of 
February 9, 2005.

ADDRESSES: For service information identified in this AD, contact 
Bombardier, Inc., Canadair, Aerospace Group, P.O. Box 6087, Station 
Centre-ville, Montreal, Quebec H3C 3G9, Canada. You can examine this 
information 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.
    You can examine the contents of this AD docket on the Internet at 
http://dms.dot.gov, or in person at the Docket Management Facility, 
U.S. Department of Transportation, 400 Seventh Street SW., Room PL-401, 
on the plaza level of the Nassif Building, Washington, DC. This docket 
number is FAA-2004-19496; the directorate identifier for this docket is 
2003-NM-181-AD.

FOR FURTHER INFORMATION CONTACT: Richard Fiesel, Aerospace Engineer, 
Airframe and Propulsion Branch, ANE-171, FAA, New York Aircraft 
Certification Office, 1600 Stewart Avenue, Suite 410, Westbury, New 
York 11590; telephone (516) 228-7304; fax (516) 794-5531.

Examining the Docket

    The AD docket contains the proposed AD, comments, and any final 
disposition. You can examine the AD docket on the Internet at http://dms.dot.gov, or in person at the Docket Management Facility office 
between 9 a.m. and 5 p.m., Monday through Friday, except Federal 
holidays. The Docket Management Facility office (telephone (800) 647-
5227) is located on the plaza level of the Nassif Building at the DOT 
street address stated in the ADDRESSES section.

SUPPLEMENTARY INFORMATION: The FAA proposed to amend 14 CFR part 39 
with an AD for certain Bombardier Model CL-215-6B11 (CL215T variant) 
and CL-215-6B11 (CL415 variant) series airplanes. That action, 
published in the Federal Register on November 3, 2004 (69 FR 63968), 
proposed to require replacing the mounting pad studs of the auxiliary 
feather pump with new, longer studs, and installing a pressure relief 
valve.

Comments

    We provided the public the opportunity to participate in the 
development of this AD. No comments have been submitted on the proposed 
AD or on the determination of the cost to the public.

Conclusion

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

Costs of Compliance

    The following table provides the estimated costs for U.S. operators 
to comply with this AD.

                                                 Estimated Costs
----------------------------------------------------------------------------------------------------------------
                                                                                         Number  of
                                   Work      Average                         Cost per      U.S.-
             Action                hours    labor rate         Parts         airplane    registered   Fleet cost
                                             per hour                                    airplanes
----------------------------------------------------------------------------------------------------------------
Replacement....................         2          $65  Free..............        $130            3         $390
Installation...................         4           65  Free..............         260            3          780
----------------------------------------------------------------------------------------------------------------

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 have 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

[[Page 685]]

the National Government and the States, or on the distribution of power 
and responsibilities among the various levels of government.
    For the reasons discussed above, I certify that this AD:
    (1) Is not a ``significant regulatory action'' under Executive 
Order 12866;
    (2) Is not a ``significant rule'' under DOT Regulatory Policies and 
Procedures (44 FR 11034, February 26, 1979); 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. See the ADDRESSES section for a location to 
examine the regulatory evaluation.

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 airworthiness 
directive (AD):

2004-26-08 Bombardier, Inc. (Formerly Canadair): Amendment 39-13920. 
Docket No. FAA-2004-19496; Directorate Identifier 2003-NM-181-AD.

Effective Date

    (a) This AD becomes effective February 9, 2005.

Affected ADs

    (b) None.

Applicability

    (c) This AD applies to Bombardier Model CL-215-6B11 (CL215T 
variant) series airplanes, having serial numbers (S/N) 1056 through 
1125 inclusive, and Model CL-215-6B11 (CL415 variant) series 
airplanes having S/Ns 2001 through 2053 inclusive; certificated in 
any category.

Unsafe Condition

    (d) This AD was prompted by a few incidents of external oil 
leaks from the oil pump of the power control unit due to a 
malfunction of the pressure regulating valve. We are issuing this AD 
to prevent fracturing of the pump body, which could result in loss 
of engine oil, and consequent inability to maintain engine oil 
pressure and to feather the propeller.

Compliance

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

Replacement

    (f) Within 12 months after the effective date of this AD, 
replace the mounting pad studs of the auxiliary feather pump with 
new, longer studs, and install a pressure relief valve; in 
accordance with the Accomplishment Instructions of Bombardier 
Service Bulletin 215-3108, dated March 28, 2001 (for Model CL-215-
6B11 (CL215T variant) series airplanes); or Bombardier Service 
Bulletin 215-4234, dated March 28, 2001 (for Model CL-215-6B11 
(CL415 variant) series airplanes); as applicable.

    Note 1: Bombardier Service Bulletin 215-3108 and Bombardier 
Service Bulletin 215-4234 refer to Pratt & Whitney Canada Service 
Bulletin PW100-72-21636, Revision 2, dated June 26, 2002, as an 
additional source of service information for accomplishing the 
replacement of the mounting pad studs.

No Reporting

    (g) Although the service bulletin refers to a reporting 
requirement in paragraph 2.B, that reporting is not required by this 
AD.

Alternative Methods of Compliance (AMOCs)

    (h) The Manager, New York Aircraft Certification Office, FAA, 
has the authority to approve AMOCs for this AD, if requested using 
the procedures found in 14 CFR 39.19.

Related Information

    (i) Canadian airworthiness directive CF-2002-14, dated February 
13, 2002, also addresses the subject of this AD.

Material Incorporated by Reference

    (j) You must use Bombardier Service Bulletin 215-3108, dated 
March 28, 2001; or Bombardier Service Bulletin 215-4234, dated March 
28, 2001; as applicable; to perform the actions that are required by 
this AD, unless the AD specifies otherwise. The Director of the 
Federal Register approves the incorporation by reference of these 
documents in accordance with 5 U.S.C. 552(a) and 1 CFR part 51. For 
copies of the service information, contact Bombardier, Inc., 
Canadair, Aerospace Group, P.O. Box 6087, Station Centre-ville, 
Montreal, Quebec H3C 3G9, Canada. For information on the 
availability of this material at the National Archives and Records 
Administration (NARA), call (202) 741-6030, or go to http://www.archives.gov/federal_register/code_of_federal_regulations/ibr_locations.html.
    You may view the AD docket at the Docket Management Facility, 
U.S. Department of Transportation, 400 Seventh Street SW., Room PL-
401, Nassif Building, Washington, DC.

    Issued in Renton, Washington, on December 20, 2004.
Kevin M. Mullin,
Acting Manager, Transport Airplane Directorate, Aircraft Certification 
Service.
[FR Doc. 05-101 Filed 1-4-05; 8:45 am]
BILLING CODE 4910-13-P

The complete text was extracted from the official GovInfo HTML edition for this publication. Acquired 2026-10-09T03:59:49.714523+00:00. Text extraction preserves the recorded source wording; it does not determine current requirements.

Open the captured official edition

Source SHA-256

816c5f3a0138b587df3971044e47d2d26dbe869adf7211be6e48ce6efa23a077

Text SHA-256

85cf14397bd15e2688045135c439421826c1f95b80278478dc829ffb377d1116