Airworthiness Directives; Bombardier Model CL-600-1A11 (CL-600), CL-600-2A12 (CL-601), and CL-600-2B16 (CL-601-3A and CL-601-3R) Airplanes, 75725-75727 [05-24244]

Download as PDF Federal Register / Vol. 70, No. 244 / Wednesday, December 21, 2005 / Rules and Regulations D. Small Business Regulatory Enforcement Fairness Act The Small Business Regulatory Enforcement Fairness Act (SBREFA) of 1996 (Pub. L. 104–121) provides generally for congressional review of agency rules. A reporting requirement is triggered in instances where NCUA issues a final rule as defined by Section 551 of the Administrative Procedures Act. 5 U.S.C. 551. The Office of Information and Regulatory Affairs, an office within OMB, has determined that, for purposes of SBREFA, this is not a major rule. E. The Treasury and General Government Appropriations Act, 1999— Assessment of Federal Regulations and Policies on Families The NCUA has determined that this rule would not affect family well-being within the meaning of section 654 of the Treasury and General Government Appropriations Act, 1999, Public Law 105–277, 112 Stat. 2681 (1998). List of Subjects in 12 CFR Part 741 Insurance requirements. By the National Credit Union Administration Board on December 15, 2005. Mary Rupp, Secretary of the Board. For the reasons stated above, NCUA amends 12 CFR part 741 as follows: I PART 741—REQUIREMENTS FOR INSURANCE 1. The authority citation for part 741 is amended to read as follows: I Authority: 12 U.S.C. 1757, 1766(a), 1781– 1790, and 1790d; 31 U.S.C. 3717. I or pledged on the secondary market under § 701.23(b)(1)(iii) or (iv) of this chapter or comparable state law for state-chartered credit unions, or purchases of member loans under § 701.23(b)(1)(i) of this chapter or comparable state law for state-chartered credit unions; (2) Assumption of deposits, shares or liabilities as rollovers or transfers of member retirement accounts or in which a federally-insured credit union perfects a security interest in connection with an extension of credit to any member; or (3) Purchases of assets, including loans, or assumptions of deposits, shares, or liabilities by any credit union insured by the NCUSIF from another credit union insured by the NCUSIF, except a purchase or assumption as a part of a merger under Part 708b. (c) A credit union seeking approval under paragraph (a) of this section must submit a letter to the regional office with jurisdiction for the state where the credit union is headquartered. A corporate credit union seeking approval under paragraph (a) of this section must submit a letter to the Office of Corporate Credit Unions. The letter must request approval and state the nature of the transaction and include copies of relevant transaction documents. The regional director will make a decision to approve or disapprove the request as soon as possible depending on the complexity of the proposed transaction. Credit unions should submit a request for approval in sufficient time to close the transaction. [FR Doc. 05–24284 Filed 12–20–05; 8:45 am] BILLING CODE 7535–01–P 2. Amend § 741.8 to read as follows: rmajette on PROD1PC67 with RULES § 741.8 Purchase of assets and assumption of liabilities. DEPARTMENT OF TRANSPORTATION (a) Any credit union insured by the National Credit Union Share Insurance Fund (NCUSIF) must receive approval from the NCUA before purchasing loans or assuming an assignment of deposits, shares, or liabilities from: (1) Any credit union that is not insured by the NCUSIF; (2) Any other financial-type institution (including depository institutions, mortgage banks, consumer finance companies, insurance companies, loan brokers, and other loan sellers or liability traders); or (3) Any successor in interest to any institution identified in paragraph (a)(1) or (a)(2) of this section. (b) Approval is not required for: (1) Purchases of student loans or real estate secured loans to facilitate the packaging of a pool of loans to be sold Federal Aviation Administration VerDate Aug<31>2005 14:47 Dec 20, 2005 Jkt 208001 14 CFR Part 39 [Docket No. FAA–2005–22627; Directorate Identifier 2005–NM–156–AD; Amendment 39–14425; AD 2005–26–04] RIN 2120–AA64 Airworthiness Directives; Bombardier Model CL–600–1A11 (CL–600), CL– 600–2A12 (CL–601), and CL–600–2B16 (CL–601–3A and CL–601–3R) Airplanes Federal Aviation Administration (FAA), Department of Transportation (DOT). ACTION: Final rule. AGENCY: SUMMARY: The FAA is adopting a new airworthiness directive (AD) for certain Bombardier Model CL–600–1A11 (CL– PO 00000 Frm 00013 Fmt 4700 Sfmt 4700 75725 600), CL–600–2A12 (CL–601), and CL– 600–2B16 (CL–601–3A and CL–601–3R) airplanes. This AD requires measuring to detect migration of the lower gimbal pin and inspecting for other discrepancies of the horizontal stabilizer trim actuator (HSTA). This AD also requires replacing or modifying the HSTA, as applicable. This AD results from reports of failure of the lower gimbal pin of the HSTA. We are issuing this AD to prevent migration of the lower gimbal pin of the HSTA, which could result in loss of the horizontal stabilizer and consequent loss of control of the airplane. DATES: This AD becomes effective January 25, 2006. The Director of the Federal Register approved the incorporation by reference of certain publications listed in the AD as of January 25, 2006. ADDRESSES: You may examine the AD docket on the Internet at https:// dms.dot.gov or in person at the Docket Management Facility, U.S. Department of Transportation, 400 Seventh Street, SW., Nassif Building, room PL–401, Washington, DC. Contact Bombardier, Inc., Canadair, Aerospace Group, P.O. Box 6087, Station Centre-ville, Montreal, Quebec H3C 3G9, Canada, for service information identified in this AD. FOR FURTHER INFORMATION CONTACT: Daniel Parrillo, Aerospace Engineer, Systems and Flight Test Branch, ANE– 172, FAA, New York Aircraft Certification Office, 1600 Stewart Avenue, suite 410, Westbury, New York 11590; telephone (516) 228–7305; fax (516) 794–5531. SUPPLEMENTARY INFORMATION: Examining the Docket You may examine the airworthiness directive (AD) docket on the Internet at https://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 street address stated in the ADDRESSES section. Discussion The FAA issued a notice of proposed rulemaking (NPRM) to amend 14 CFR part 39 to include an AD that would apply to certain Bombardier Model CL– 600–1A11 (CL–600), CL–600–2A12 (CL– 601), and CL–600–2B16 (CL–601–3A and CL–601–3R) airplanes. That NPRM was published in the Federal Register on October 6, 2005 (70 FR 58355). That NPRM proposed to require measuring to E:\FR\FM\21DER1.SGM 21DER1 75726 Federal Register / Vol. 70, No. 244 / Wednesday, December 21, 2005 / Rules and Regulations detect migration of the lower gimbal pin and inspecting for other discrepancies of the horizontal stabilizer trim actuator (HSTA). That NPRM also proposed to require replacing or modifying the HSTA, as applicable. Comments We provided the public the opportunity to participate in the development of this AD. We received no comments on the NPRM or on the determination of the cost to the public. Clarification of Compliance Time We have revised paragraph (g)(1) of this AD to clarify that the actions in that paragraph must be done before further flight. Conclusion We have carefully reviewed the available data and determined that air safety and the public interest require adopting the AD with the change described previously. We have determined that this change will neither increase the economic burden on any operator nor increase the scope of the AD. Costs of Compliance This AD will affect about 269 airplanes of U.S. registry. The measurement/inspection and modification will take about 5 work hours per airplane, at an average labor rate of $65 per work hour. Required parts will cost about $462 per airplane. Based on these figures, the estimated cost of the AD for U.S. operators is $211,703, or $787 per airplane. rmajette on PROD1PC67 with RULES 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. VerDate Aug<31>2005 14:47 Dec 20, 2005 Jkt 208001 Regulatory Findings TABLE 1.—APPLICABILITY 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 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 and placed it in the AD docket. 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 Accordingly, under the authority delegated to me by the Administrator, the FAA amends 14 CFR part 39 as follows: I PART 39—AIRWORTHINESS DIRECTIVES 1. The authority citation for part 39 continues to read as follows: I Authority: 49 U.S.C. 106(g), 40113, 44701. § 39.13 [Amended] 2. The Federal Aviation Administration (FAA) amends § 39.13 by adding the following new airworthiness directive (AD): I 2005–26–04 Bombardier, Inc. (Formerly Canadair): Amendment 39–14425. Docket No. FAA–2005–22627; Directorate Identifier 2005–NM–156–AD. Effective Date (a) This AD becomes effective January 25, 2006. Affected ADs (b) None. Applicability (c) This AD applies to the Bombardier airplanes identified in Table 1 of this AD, certificated in any category. PO 00000 Frm 00014 Fmt 4700 Sfmt 4700 Bombardier airplane models CL–600–1A11 (CL– 600). CL–600–2A12 (CL– 601). CL–600–2B16 (CL– 601–3A and CL– 601–3R). Serial numbers 1004 through 1085 inclusive. 3001 through 3066 inclusive. 5001 through 5194 inclusive. Unsafe Condition (d) This AD results from reports of failure of the lower gimbal pin of the horizontal stabilizer trim actuator (HSTA). We are issuing this AD to prevent migration of the lower gimbal pin of the HSTA, which could result in loss of the horizontal stabilizer and consequent loss of control of the airplane. 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. Service Bulletin Reference (f) The term ‘‘service bulletin,’’ as used in this AD, means the Accomplishment Instructions of the service bulletins identified in paragraphs (f)(1) and (f)(2) of this AD, as applicable. (1) For Model CL–600–1A11 (CL–600) airplanes: Bombardier Service Bulletin 600– 0720, dated January 31, 2005. (2) For Bombardier Model CL–600–2A12 (CL–601) and CL–600–2B16 (CL–601–3A and CL–601–3R) airplanes: Bombardier Service Bulletin 601–0555, dated January 31, 2005. Note 1: The Bombardier service bulletins identified in paragraphs (f)(1) and (f)(2) of this AD refer to Goodrich Service Bulletin 21207–00X–27–05, dated January 31, 2005, as an additional source of service information for doing the modification of the HSTA. Measurement and Modification or Replacement (g) Within 600 flight hours or 16 months after the effective date of this AD, whichever is first: Measure the clearance between the yoke and the lower side of the gimbal pin head on the HSTA to detect migration of the lower gimbal pin of the HSTA, and do a detailed inspection to detect discrepancies of the HSTA, in accordance with the service bulletin. (1) If the lower gimbal pin has not migrated and no discrepancy is found: Before further flight, modify the HSTA by installing the gimbal pin kit, or replace the existing HSTA with a new or serviceable, modified HSTA, in accordance with the service bulletin. (2) If the lower gimbal pin has migrated or any discrepancy is found: Before further flight, replace the HSTA with a new or serviceable, modified HSTA, in accordance with the service bulletin. Note 2: For the purposes of this AD, a detailed inspection is: ‘‘An intensive examination of a specific item, installation, or assembly to detect damage, failure, or irregularity. Available lighting is normally E:\FR\FM\21DER1.SGM 21DER1 Federal Register / Vol. 70, No. 244 / Wednesday, December 21, 2005 / Rules and Regulations supplemented with a direct source of good lighting at an intensity deemed appropriate. Inspection aids such as mirror, magnifying lenses, etc., may be necessary. Surface cleaning and elaborate procedures may be required.’’ Reporting (h) If any gimbal pin is found migrated: Submit a report of the findings (migrated pins only) of the measurement and inspections required by paragraph (g) of this AD to Bombardier, Attention: Dept. Customer Support Program Office (CSPO), fax (514) 855–8798. Submit the report at the applicable time specified in paragraph (h)(1) or (h)(2) of this AD. The report must include the airplane serial number, the HSTA part number and serial number, the results of the inspection, and the action taken. Submitting the Service Bulletin Feedback Form of the service bulletin is an acceptable means of complying with this requirement. Under the provisions of the Paperwork Reduction Act of 1980 (44 U.S.C. 3501 et seq.), the Office of Management and Budget (OMB) has approved the information collection requirements contained in this AD and has assigned OMB Control Number 2120–0056. (1) If the measurement was done after the effective date of this AD: Submit the report within 30 days after the inspection. (2) If the measurement was done prior to the effective date of this AD: Submit the report within 30 days after the effective date of this AD. Parts Installation (i) As of the effective date of this AD, no person may install an HSTA on any airplane unless the actions required by paragraph (g) of this AD are accomplished on it. Alternative Methods of Compliance (AMOCs) (j)(1) The Manager, New York Aircraft Certification Office, FAA, has the authority to approve AMOCs for this AD, if requested in accordance with the procedures found in 14 CFR 39.19. (2) Before using any AMOC approved in accordance with 14 CFR 39.19 on any airplane to which the AMOC applies, notify the appropriate principal inspector in the FAA Flight Standards Certificate Holding District Office. rmajette on PROD1PC67 with RULES Related Information (k) Canadian airworthiness directive CF– 2005–20, dated June 23, 2005, also addresses the subject of this AD. Material Incorporated by Reference (l) You must use Bombardier Service Bulletin 600–0720, dated January 31, 2005; or Bombardier Service Bulletin 601–0555, dated January 31, 2005; as applicable, to perform the actions that are required by this AD, unless the AD specifies otherwise. The Director of the Federal Register approved the incorporation by reference of these documents in accordance with 5 U.S.C. 552(a) and 1 CFR part 51. Contact Bombardier, Inc., Canadair, Aerospace Group, P.O. Box 6087, Station Centre-ville, Montreal, Quebec H3C 3G9, Canada, for a copy of this service information. You may VerDate Aug<31>2005 14:47 Dec 20, 2005 Jkt 208001 review copies at the Docket Management Facility, U.S. Department of Transportation, 400 Seventh Street SW., Room PL–401, Nassif Building, Washington, DC; on the Internet at https://dms.dot.gov; or at the National Archives and Records Administration (NARA). For information on the availability of this material at the NARA, call (202) 741–6030, or go to https://www.archives.gov/ federal_register/code_of_federal_regulations/ ibr_locations.html. Issued in Renton, Washington, on December 13, 2005. Ali Bahrami, Manager, Transport Airplane Directorate, Aircraft Certification Service. [FR Doc. 05–24244 Filed 12–20–05; 8:45 am] BILLING CODE 4910–13–P DEPARTMENT OF TRANSPORTATION Federal Aviation Administration 14 CFR Part 39 [Docket No. FAA–2005–22403; Directorate Identifier 2005–NM–144–AD; Amendment 39–14426; AD 2005–26–05] RIN 2120–AA64 Airworthiness Directives; Bombardier Model DHC–8–400 Series Airplanes Federal Aviation Administration (FAA), Department of Transportation (DOT). ACTION: Final rule. AGENCY: SUMMARY: The FAA is adopting a new airworthiness directive (AD) for certain Bombardier Model DHC–8–400 series airplanes. This AD requires an inspection of the laminated shims for cracks, damage, or extrusion between the forward attachment fittings of the horizontal stabilizer and the top rib of the vertical stabilizer; a torque check of the attachment bolts in the attachment fittings of the front, middle, and rear spars; and corrective actions if necessary. This AD results from a report indicating that delaminated shims extruded from the interface between the forward attaching fittings of the horizontal stabilizer and the top rib of the vertical stabilizer, and that inadequate torque values of some bolts were found. We are issuing this AD to prevent reduced structural integrity of the horizontal stabilizer, and consequent loss of controllability of the airplane. DATES: This AD becomes effective January 25, 2006. The Director of the Federal Register approved the incorporation by reference of a certain publication listed in the AD as of January 25, 2006. PO 00000 Frm 00015 Fmt 4700 Sfmt 4700 75727 You may examine the AD docket on the Internet at https:// dms.dot.gov or in person at the Docket Management Facility, U.S. Department of Transportation, 400 Seventh Street SW., Nassif Building, Room PL–401, Washington, DC. Contact Bombardier, Inc., Bombardier Regional Aircraft Division, 123 Garratt Boulevard, Downsview, Ontario M3K 1Y5, Canada, for service information identified in this AD. FOR FURTHER INFORMATION CONTACT: George Duckett, 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) 228–7325; fax (516) 794–5531. SUPPLEMENTARY INFORMATION: ADDRESSES: Examining the Docket You may examine the airworthiness directive (AD) docket on the Internet at https://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 street address stated in the ADDRESSES section. Discussion The FAA issued a notice of proposed rulemaking (NPRM) to amend 14 CFR part 39 to include an AD that would apply to certain Bombardier Model DHC–8–400 series airplanes. That NPRM was published in the Federal Register on September 14, 2005 (70 FR 54316). (An NPRM correction was published in the Federal Register on September 30, 2005 (70 FR 57221).) That NPRM proposed to require an inspection of the laminated shims for cracks, damage, or extrusion between the forward attachment fittings of the horizontal stabilizer and the top rib of the vertical stabilizer; a torque check of the attachment bolts in the attachment fittings of the front, middle, and rear spars; and corrective actions if necessary. Comments We provided the public the opportunity to participate in the development of this AD. We have considered the comment received. Request for Credit for Doing Bombardier All Operator Message (AOM) One commenter requests that operators be given credit for doing the procedures in accordance with E:\FR\FM\21DER1.SGM 21DER1

Agencies

[Federal Register Volume 70, Number 244 (Wednesday, December 21, 2005)]
[Rules and Regulations]
[Pages 75725-75727]
From the Federal Register Online via the Government Printing Office [www.gpo.gov]
[FR Doc No: 05-24244]


=======================================================================
-----------------------------------------------------------------------

DEPARTMENT OF TRANSPORTATION

Federal Aviation Administration

14 CFR Part 39

[Docket No. FAA-2005-22627; Directorate Identifier 2005-NM-156-AD; 
Amendment 39-14425; AD 2005-26-04]
RIN 2120-AA64


Airworthiness Directives; Bombardier Model CL-600-1A11 (CL-600), 
CL-600-2A12 (CL-601), and CL-600-2B16 (CL-601-3A and CL-601-3R) 
Airplanes

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

ACTION: Final rule.

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

SUMMARY: The FAA is adopting a new airworthiness directive (AD) for 
certain Bombardier Model CL-600-1A11 (CL-600), CL-600-2A12 (CL-601), 
and CL-600-2B16 (CL-601-3A and CL-601-3R) airplanes. This AD requires 
measuring to detect migration of the lower gimbal pin and inspecting 
for other discrepancies of the horizontal stabilizer trim actuator 
(HSTA). This AD also requires replacing or modifying the HSTA, as 
applicable. This AD results from reports of failure of the lower gimbal 
pin of the HSTA. We are issuing this AD to prevent migration of the 
lower gimbal pin of the HSTA, which could result in loss of the 
horizontal stabilizer and consequent loss of control of the airplane.

DATES: This AD becomes effective January 25, 2006.
    The Director of the Federal Register approved the incorporation by 
reference of certain publications listed in the AD as of January 25, 
2006.

ADDRESSES: You may examine the AD docket on the Internet at https://
dms.dot.gov or in person at the Docket Management Facility, U.S. 
Department of Transportation, 400 Seventh Street, SW., Nassif Building, 
room PL-401, Washington, DC.
    Contact Bombardier, Inc., Canadair, Aerospace Group, P.O. Box 6087, 
Station Centre-ville, Montreal, Quebec H3C 3G9, Canada, for service 
information identified in this AD.

FOR FURTHER INFORMATION CONTACT: Daniel Parrillo, Aerospace Engineer, 
Systems and Flight Test Branch, ANE-172, FAA, New York Aircraft 
Certification Office, 1600 Stewart Avenue, suite 410, Westbury, New 
York 11590; telephone (516) 228-7305; fax (516) 794-5531.

SUPPLEMENTARY INFORMATION:

Examining the Docket

    You may examine the airworthiness directive (AD) docket on the 
Internet at https://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 street address stated in the ADDRESSES section.

Discussion

    The FAA issued a notice of proposed rulemaking (NPRM) to amend 14 
CFR part 39 to include an AD that would apply to certain Bombardier 
Model CL-600-1A11 (CL-600), CL-600-2A12 (CL-601), and CL-600-2B16 (CL-
601-3A and CL-601-3R) airplanes. That NPRM was published in the Federal 
Register on October 6, 2005 (70 FR 58355). That NPRM proposed to 
require measuring to

[[Page 75726]]

detect migration of the lower gimbal pin and inspecting for other 
discrepancies of the horizontal stabilizer trim actuator (HSTA). That 
NPRM also proposed to require replacing or modifying the HSTA, as 
applicable.

Comments

    We provided the public the opportunity to participate in the 
development of this AD. We received no comments on the NPRM or on the 
determination of the cost to the public.

Clarification of Compliance Time

    We have revised paragraph (g)(1) of this AD to clarify that the 
actions in that paragraph must be done before further flight.

Conclusion

    We have carefully reviewed the available data and determined that 
air safety and the public interest require adopting the AD with the 
change described previously. We have determined that this change will 
neither increase the economic burden on any operator nor increase the 
scope of the AD.

Costs of Compliance

    This AD will affect about 269 airplanes of U.S. registry. The 
measurement/inspection and modification will take about 5 work hours 
per airplane, at an average labor rate of $65 per work hour. Required 
parts will cost about $462 per airplane. Based on these figures, the 
estimated cost of the AD for U.S. operators is $211,703, or $787 per 
airplane.

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 
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 and placed it in the AD docket. 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 Federal Aviation Administration (FAA) amends Sec.  39.13 by 
adding the following new airworthiness directive (AD):

2005-26-04 Bombardier, Inc. (Formerly Canadair): Amendment 39-14425. 
Docket No. FAA-2005-22627; Directorate Identifier 2005-NM-156-AD.

Effective Date

    (a) This AD becomes effective January 25, 2006.

Affected ADs

    (b) None.

Applicability

    (c) This AD applies to the Bombardier airplanes identified in 
Table 1 of this AD, certificated in any category.

                         Table 1.--Applicability
------------------------------------------------------------------------
        Bombardier airplane models                 Serial numbers
------------------------------------------------------------------------
CL-600-1A11 (CL-600)......................  1004 through 1085 inclusive.
CL-600-2A12 (CL-601)......................  3001 through 3066 inclusive.
CL-600-2B16 (CL-601-3A and CL-601-3R).....  5001 through 5194 inclusive.
------------------------------------------------------------------------

Unsafe Condition

    (d) This AD results from reports of failure of the lower gimbal 
pin of the horizontal stabilizer trim actuator (HSTA). We are 
issuing this AD to prevent migration of the lower gimbal pin of the 
HSTA, which could result in loss of the horizontal stabilizer and 
consequent loss of control of the airplane.

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.

Service Bulletin Reference

    (f) The term ``service bulletin,'' as used in this AD, means the 
Accomplishment Instructions of the service bulletins identified in 
paragraphs (f)(1) and (f)(2) of this AD, as applicable.
    (1) For Model CL-600-1A11 (CL-600) airplanes: Bombardier Service 
Bulletin 600-0720, dated January 31, 2005.
    (2) For Bombardier Model CL-600-2A12 (CL-601) and CL-600-2B16 
(CL-601-3A and CL-601-3R) airplanes: Bombardier Service Bulletin 
601-0555, dated January 31, 2005.

    Note 1: The Bombardier service bulletins identified in 
paragraphs (f)(1) and (f)(2) of this AD refer to Goodrich Service 
Bulletin 21207-00X-27-05, dated January 31, 2005, as an additional 
source of service information for doing the modification of the 
HSTA.

Measurement and Modification or Replacement

    (g) Within 600 flight hours or 16 months after the effective 
date of this AD, whichever is first: Measure the clearance between 
the yoke and the lower side of the gimbal pin head on the HSTA to 
detect migration of the lower gimbal pin of the HSTA, and do a 
detailed inspection to detect discrepancies of the HSTA, in 
accordance with the service bulletin.
    (1) If the lower gimbal pin has not migrated and no discrepancy 
is found: Before further flight, modify the HSTA by installing the 
gimbal pin kit, or replace the existing HSTA with a new or 
serviceable, modified HSTA, in accordance with the service bulletin.
    (2) If the lower gimbal pin has migrated or any discrepancy is 
found: Before further flight, replace the HSTA with a new or 
serviceable, modified HSTA, in accordance with the service bulletin.

    Note 2: For the purposes of this AD, a detailed inspection is: 
``An intensive examination of a specific item, installation, or 
assembly to detect damage, failure, or irregularity. Available 
lighting is normally

[[Page 75727]]

supplemented with a direct source of good lighting at an intensity 
deemed appropriate. Inspection aids such as mirror, magnifying 
lenses, etc., may be necessary. Surface cleaning and elaborate 
procedures may be required.''

Reporting

    (h) If any gimbal pin is found migrated: Submit a report of the 
findings (migrated pins only) of the measurement and inspections 
required by paragraph (g) of this AD to Bombardier, Attention: Dept. 
Customer Support Program Office (CSPO), fax (514) 855-8798. Submit 
the report at the applicable time specified in paragraph (h)(1) or 
(h)(2) of this AD. The report must include the airplane serial 
number, the HSTA part number and serial number, the results of the 
inspection, and the action taken. Submitting the Service Bulletin 
Feedback Form of the service bulletin is an acceptable means of 
complying with this requirement. Under the provisions of the 
Paperwork Reduction Act of 1980 (44 U.S.C. 3501 et seq.), the Office 
of Management and Budget (OMB) has approved the information 
collection requirements contained in this AD and has assigned OMB 
Control Number 2120-0056.
    (1) If the measurement was done after the effective date of this 
AD: Submit the report within 30 days after the inspection.
    (2) If the measurement was done prior to the effective date of 
this AD: Submit the report within 30 days after the effective date 
of this AD.

Parts Installation

    (i) As of the effective date of this AD, no person may install 
an HSTA on any airplane unless the actions required by paragraph (g) 
of this AD are accomplished on it.

Alternative Methods of Compliance (AMOCs)

    (j)(1) The Manager, New York Aircraft Certification Office, FAA, 
has the authority to approve AMOCs for this AD, if requested in 
accordance with the procedures found in 14 CFR 39.19.
    (2) Before using any AMOC approved in accordance with 14 CFR 
39.19 on any airplane to which the AMOC applies, notify the 
appropriate principal inspector in the FAA Flight Standards 
Certificate Holding District Office.

Related Information

    (k) Canadian airworthiness directive CF-2005-20, dated June 23, 
2005, also addresses the subject of this AD.

Material Incorporated by Reference

    (l) You must use Bombardier Service Bulletin 600-0720, dated 
January 31, 2005; or Bombardier Service Bulletin 601-0555, dated 
January 31, 2005; as applicable, to perform the actions that are 
required by this AD, unless the AD specifies otherwise. The Director 
of the Federal Register approved the incorporation by reference of 
these documents in accordance with 5 U.S.C. 552(a) and 1 CFR part 
51. Contact Bombardier, Inc., Canadair, Aerospace Group, P.O. Box 
6087, Station Centre-ville, Montreal, Quebec H3C 3G9, Canada, for a 
copy of this service information. You may review copies at the 
Docket Management Facility, U.S. Department of Transportation, 400 
Seventh Street SW., Room PL-401, Nassif Building, Washington, DC; on 
the Internet at https://dms.dot.gov; or at the National Archives and 
Records Administration (NARA).
    For information on the availability of this material at the 
NARA, call (202) 741-6030, or go to https://www.archives.gov/
federal_register/code_of_federal_regulations/ibr_
locations.html.

    Issued in Renton, Washington, on December 13, 2005.
Ali Bahrami,
Manager, Transport Airplane Directorate, Aircraft Certification 
Service.
[FR Doc. 05-24244 Filed 12-20-05; 8:45 am]
BILLING CODE 4910-13-P

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