Airworthiness Directives; Bombardier Model CL-600-2B19 (Regional Jet Series 100 & 440) Airplanes, 19979-19982 [E8-7294]

Download as PDF Federal Register / Vol. 73, No. 72 / Monday, April 14, 2008 / Rules and Regulations 2008–08–14 Precision Airmotive LLC: Amendment 39–15466. Docket No. FAA–2008–0420; Directorate Identifier 2008–NE–10–AD. Effective Date (a) This airworthiness directive (AD) becomes effective April 29, 2008, to all persons except those persons to whom it was made immediately effective by emergency AD 2008–06–51, issued March 12, 2008, which contained the requirements of this amendment. Affected ADs (b) This AD supersedes AD 2008–06–51. Applicability (c) This AD applies to the following reciprocating engines with an installed Precision Airmotive LLC, RSA–5 or RSA–10 series fuel injection servo, having a servo plug gasket, part number (P/N) 365533, installed under the fuel injection servo plug, P/N 383493: (1) Lycoming Engines IO, (L)IO, TIO, (L)TIO, AEIO, AIO, IGO, IVO, and HIO series reciprocating engines, regardless of displacement, either new, rebuilt, overhauled, or repaired since August 22, 2006, and/or with an affected fuel injection servo installed either new, rebuilt, overhauled, or repaired since August 22, 2006. (2) Teledyne Continental Motors TSIO– 360–RB reciprocating engines, either new, rebuilt, overhauled, or repaired since August 22, 2006, and/or with an affected fuel injection servo installed either new, rebuilt, overhauled, or repaired since August 22, 2006. (3) Superior Air Parts, Inc. IO–360 series reciprocating engines, either new, rebuilt, overhauled, or repaired since August 22, 2006, and/or with an affected fuel injection servo installed either new, rebuilt, overhauled, or repaired since August 22, 2006. (4) This AD also applies to any other Precision Airmotive LLC fuel injection servos received since August 22, 2006, or any fuel injection servos that have had the fuel injection servo plug, P/N 383493, removed during maintenance since August 22, 2006. cprice-sewell on PROD1PC62 with RULES Unsafe Condition (d) This AD results from eighteen reports of fuel injection servo plugs, P/N 383493, that had loosened or completely backed out of the threaded plug hole on the regulator cover of the fuel injection servo. We are issuing this AD to prevent a lean running engine, which could result in a substantial loss of engine power and subsequent loss of control of the airplane. Compliance (e) You are responsible for having the actions required by this AD performed before further flight, unless the actions have already been done. The actions required by this AD must be done by an FAA-licensed mechanic. Initial Inspection (f) Inspect the fuel injection servo plug, P/ N 383493, for looseness, by attempting to turn it by hand, while being careful not to VerDate Aug<31>2005 15:37 Apr 11, 2008 Jkt 214001 damage the safety wire or seal. If the plug moves, it is loose. (g) If the plug is not loose, go to paragraph (i) of this AD. (h) If the plug is loose, do the following: (1) Carefully cut and remove the safety wire that spans between the servo plug and regulator cover only. (2) Remove the servo plug while ensuring that the gasket, P/N 365533, that is behind the plug, is not lost. The gasket may be slightly stuck to the regulator cover. (3) Examine the threads on the servo plug and regulator cover for damage. Threads should be smooth and consistent, with no burrs or chips. The servo plug outer diameter threads should also measure within 0.7419– 0.7500-inch. (4) If the threads on either the servo plug or the regulator cover are damaged, or do not measure within the limits in paragraph (h)(3) of this AD, the servo is not eligible for any installation and must be replaced before further flight. (5) Inspect the gasket, P/N 365533, for tears and other damage. We are allowing the re-use of undamaged gaskets. Replace damaged gaskets with a new gasket, P/N 365533. (6) When reassembling, do not install any servo plug or regulator cover that is not eligible for installation. Install the gasket onto the servo plug and reassemble the servo plug to the regulator cover. (7) Torque the servo plug to a new, higher torque of 90–100 in-lbs, to help maintain the proper clamp-up force against the plug and cover. (8) Safety wire the servo plug with 0.025inch diameter wire to the regulator cover. Information on properly safety wiring the plug can be found in Precision Airmotive LLC Mandatory Service Bulletin No. PRS– 107, Revision 1, dated March 6, 2008. (9) Inspect all other safety wire on the servo. Replace any that are damaged. Repetitive Inspections (i) At every engine oil change or within every 50 hours of engine run time, whichever occurs first, repeat the inspection and remedial steps specified in paragraphs (f) through (h)(9) of this AD. Special Flight Permits Prohibited (j) Under 14 CFR part 39.23, we are prohibiting special flight permits. Alternative Methods of Compliance (k) The Manager, Seattle Aircraft Certification Office, may approve alternative methods of compliance for this AD if requested using the procedures found in 14 CFR 39.19. Related Information (l) Precision Airmotive LLC Mandatory Service Bulletin No. PRS–107, Revision 1, dated March 6, 2008, pertains to the subject of this AD. You can get the service information identified in this AD from https://www.precisionairmotive.com. (m) For Precision Airmotive LLC, Richard Simonson, Aerospace Engineer, Propulsion Branch, FAA, Transport Airplane Directorate, 1601 Lind Avenue, SW., Renton, Washington 98055; e-mail: Richard.simonson@faa.gov; PO 00000 Frm 00021 Fmt 4700 Sfmt 4700 19979 telephone: (425) 917–6507; fax: (425) 917– 6590. (n) For Lycoming Engines, Norm Perenson, Aerospace Engineer, New York Aircraft Certification Office, FAA, Engine & Propeller Directorate, 1600 Stewart Avenue, Suite 410, Westbury, NY 11590; e-mail: Norman.perenson@faa.gov; telephone: (516) 228–7337; fax: (516) 794–5531. (o) For Teledyne Continental Motors, Kevin Brane, Aerospace Engineer, Atlanta Aircraft Certification Office, FAA, Small Airplane Directorate, One Crown Center, 1895 Phoenix Blvd., Suite 450, Atlanta, GA 30349; e-mail: kevin.brane@faa.gov; telephone: (770) 703–6063; fax: (770) 703– 6097. (p) For Superior Air Parts, Inc., Tausif Butt, Aerospace Engineer, Special Certification Office, FAA, Rotorcraft Directorate, Southwest Regional Headquarters, 2601 Meacham Blvd., Fort Worth, Texas 76137; email: Tausif.butt@faa.gov; telephone: (817) 222–5195; fax: (817) 222–5785. Issued in Burlington, Massachusetts, on April 4, 2008. Francis A. Favara, Manager, Engine and Propeller Directorate, Aircraft Certification Service. [FR Doc. E8–7574 Filed 4–11–08; 8:45 am] BILLING CODE 4910–13–P DEPARTMENT OF TRANSPORTATION Federal Aviation Administration 14 CFR Part 39 [Docket No. FAA–2008–0047; Directorate Identifier 2007–NM–295–AD; Amendment 39–15461; AD 2008–08–09] RIN 2120–AA64 Airworthiness Directives; Bombardier Model CL–600–2B19 (Regional Jet Series 100 & 440) Airplanes Federal Aviation Administration (FAA), Department of Transportation (DOT). ACTION: Final rule. AGENCY: SUMMARY: The FAA is superseding an existing airworthiness directive (AD), which applies to certain Bombardier Model CL–600–2B19 (Regional Jet Series 100 & 400) airplanes. That AD currently requires revising the airworthiness limitations section of the Instructions for Continued Airworthiness of the maintenance requirements manual (MRM) by incorporating procedures for repetitive functional tests of the pilot input lever of the pitch feel simulator (PFS) units. That AD also requires new repetitive functional tests of the pilot input lever of the PFS unit, and corrective actions if necessary; and after initiating the new tests, requires removal of the existing procedures for the repetitive functional E:\FR\FM\14APR1.SGM 14APR1 19980 Federal Register / Vol. 73, No. 72 / Monday, April 14, 2008 / Rules and Regulations tests from the MRM. This new AD requires revised procedures for the functional tests. This AD results from a report that the shear pin located in the input lever of two PFS units failed due to fatigue. We are issuing this AD to prevent undetected failure of the shear pins of both PFS units simultaneously, which could result in loss of pitch feel forces and consequent reduced control of the airplane. DATES: This AD becomes effective May 19, 2008. The Director of the Federal Register approved the incorporation by reference of a certain publication listed in the AD as of May 19, 2008. On March 27, 2006 (71 FR 12277, March 10, 2006), the Director of the Federal Register approved the incorporation by reference of Bombardier Alert Service Bulletin A601R–27–144, Revision A, dated February 14, 2006, including Appendix A, dated September 15, 2005. On February 13, 2004 (69 FR 4234, January 29, 2004), the Director of the Federal Register approved the incorporation by reference of Bombardier Temporary Revision 2B– 1784, dated October 24, 2003, to the CL– 600–2B19 Canadair Regional Jet Maintenance Requirements Manual, Part 2, Appendix B, ‘‘Airworthiness Limitations.’’ 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. Examining the AD Docket You may examine the AD docket on the Internet at https:// www.regulations.gov; or in person at the Docket Management Facility between 9 a.m. and 5 p.m., Monday through Friday, except Federal holidays. The AD docket contains this AD, the regulatory evaluation, any comments received, and other information. The address for the Docket Office (telephone 800–647–5527) is the Document Management Facility, U.S. Department of Transportation, Docket Operations, M–30, West Building Ground Floor, Room W12–140, 1200 New Jersey Avenue, SE., Washington, DC 20590. FOR FURTHER INFORMATION CONTACT: Dan Parrillo, Aerospace Engineer, Systems and Flight Test Branch, ANE–172, New York Aircraft Certification Office, FAA, 1600 Stewart Avenue, Suite 410, Westbury, New York 11590; telephone 516–228–7305; fax 516–794–5531. SUPPLEMENTARY INFORMATION: published in the Federal Register on January 24, 2008 (73 FR 4125). That NPRM proposed to continue to require revising the airworthiness limitations section of the Instructions for Continued Airworthiness of the maintenance requirements manual (MRM) by incorporating procedures for repetitive functional tests of the pilot input lever of the pitch feel simulator (PFS) units. That NPRM also proposed to continue to require new repetitive functional tests of the pilot input lever of the PFS unit, and corrective actions if necessary; and after initiating the new tests, requires removal of the existing procedures for the repetitive functional tests from the MRM. That NPRM also proposed to require revised procedures for the functional tests. Comments We provided the public the opportunity to participate in the development of this AD. No comments have been received on the NPRM or on the determination of the cost to the public. Discussion Conclusion The FAA issued a notice of proposed rulemaking (NPRM) to amend 14 CFR part 39 to include an AD that supersedes AD 2006–05–11 R1, amendment 39–14528 (71 FR 15323, March 28, 2006). The existing AD applies to certain Bombardier Model CL–600–2B19 (Regional Jet Series 100 & 400) airplanes. That NPRM was 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 Action Average labor rate per hour Work hours Revise MRM .......................... Functional tests ..................... 1 1 cprice-sewell on PROD1PC62 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 VerDate Aug<31>2005 15:37 Apr 11, 2008 Jkt 214001 Cost per airplane $80 80 $80 ........................................ $80, per test cycle ................ 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: PO 00000 Frm 00022 Number of U.S.-registered airplanes Fmt 4700 Sfmt 4700 684 684 Fleet cost $54,720. $54,720, per test cycle. (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. E:\FR\FM\14APR1.SGM 14APR1 19981 Federal Register / Vol. 73, No. 72 / Monday, April 14, 2008 / Rules and Regulations List of Subjects in 14 CFR Part 39 Air transportation, Aircraft, Aviation safety, Incorporation by reference, Safety. the compliance times specified, unless the actions have already been done. Restatement of Requirements of AD 2006– 05–11 R1 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 removing amendment 39–14528 (71 FR 15323, March 28, 2006) and by adding the following new airworthiness directive (AD): I 2008–08–09 Bombardier, Inc. (Formerly Canadair): Amendment 39–15461. Docket No. FAA–2008–0047; Directorate Identifier 2007–NM–295–AD. Effective Date (a) This AD becomes effective May 19, 2008. Affected ADs (b) This AD supersedes AD 2006–05–11 R1. Applicability (c) This AD applies to Bombardier Model CL–600–2B19 (Regional Jet Series 100 & 400) airplanes, certificated in any category, serial numbers 7003 through 7990 inclusive, and 8000 and subsequent. Unsafe Condition (d) This AD results from a report that the shear pin located in the input lever of two pitch feel simulator (PFS) units failed due to fatigue. We are issuing this AD to prevent undetected failure of the shear pins of both PFS units simultaneously, which could result in loss of pitch feel forces and consequent reduced control of the airplane. Compliance (e) You are responsible for having the actions required by this AD performed within Revise Airworthiness Limitations (AWL) Section of Maintenance Requirements Manual (f) For airplanes having serial numbers 7003 through 7990 inclusive: Within 14 days after February 13, 2004 (the effective date of AD 2004–02–07, which was superseded by AD 2006–05–11 R1), revise the AWL section of the Instructions for Continued Airworthiness of the maintenance requirements manual by incorporating the functional check of the PFS pilot input lever, Task R27–31–A024–01, as specified in Bombardier Temporary Revision (TR) 2B– 1784, dated October 24, 2003, to the CL–600– 2B19 Canadair Regional Jet Maintenance Requirements Manual, Part 2, Appendix B, ‘‘Airworthiness Limitations,’’ into the AWL section. New Repetitive Functional Tests and Corrective Actions (g) Before the accumulation of 4,000 total flight hours, or within 100 flight hours after March 27, 2006 (the effective date of AD 2006–05–11 R1), whichever occurs later: Do a functional test of the pilot input lever of the PFS units to determine if the lever is disconnected, in accordance with the Accomplishment Instructions of Bombardier Alert Service Bulletin A601R–27–144, Revision A, dated February 14, 2006, including Appendix A, dated September 15, 2005, except as required by paragraph (j) of this AD. Repeat the test at intervals not to exceed 100 flight hours. Accomplishing the initial functional test terminates the requirements of paragraph (f) of this AD and the repetitive functional checks of the PFS pilot input lever, Task R27–31–A024–01, as specified in the AWL section of the Instructions for Continued Airworthiness of CL–600–2B19 Canadair Regional Jet Maintenance Requirements Manual. (h) If any lever is found to be disconnected during any functional test required by paragraph (g) of this AD, do the actions specified in paragraphs (h)(1) and (h)(2) of this AD in accordance with the Accomplishment Instructions of Bombardier Alert Service Bulletin A601R–27–144, Revision A, dated February 14, 2006, including Appendix A, dated September 15, 2005, except as required by paragraph (j) of this AD. (1) Before further flight, replace the defective PFS with a serviceable PFS in accordance with the Accomplishment Instructions of the alert service bulletin; and (2) Within 30 days after removing the defective PFS, submit a test report to the manufacturer in accordance with the Accomplishment Instructions of the alert service bulletin. 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 contained in this AD and has assigned OMB Control Number 2120–0056. Previously Accomplished Actions (i) Actions done before March 27, 2006, in accordance with Bombardier Alert Service Bulletin A601R–27–144, including Appendix A, dated September 15, 2005, are acceptable for compliance with the requirements of paragraph (g) of this AD. New Requirements of This AD New Service Bulletin for Functional Tests (j) As of the effective date of this AD, Bombardier Alert Service Bulletin A601R– 27–144, Revision B, dated December 20, 2006, including Appendix A, Revision A, dated December 20, 2006, must be used for the actions required by paragraphs (g) and (h) of this AD. Alternative Methods of Compliance (AMOCs) (k)(1) The Manager, New York Aircraft Certification Office (ACO), FAA, has the authority to approve AMOCs for this AD, if requested in accordance with the procedures found in 14 CFR 39.19. (2) To request a different method of compliance or a different compliance time for this AD, follow the procedures in 14 CFR 39.19. Before using any approved AMOC on any airplane to which the AMOC applies, notify your appropriate principal inspector (PI) in the FAA Flight Standards District Office (FSDO), or lacking a PI, your local FSDO. Related Information (l) Canadian airworthiness directive CF– 2005–41, dated December 22, 2005, also addresses the subject of this AD. Material Incorporated by Reference (m) You must use the applicable service information listed in Table 1 of this AD to perform the actions that are required by this AD, unless the AD specifies otherwise. TABLE 1.—MATERIAL INCORPORATED BY REFERENCE cprice-sewell on PROD1PC62 with RULES Bombardier service information Revision level Alert Service Bulletin A601R–27–144, including Appendix A, dated September 15, 2005 ............ Alert Service Bulletin A601R–27–144, including Appendix A, Revision A, dated December 20, 2006. Temporary Revision 2B–1784 to the CL–600–2B19 Canadair Regional Jet Maintenance Requirements Manual, Part 2, Appendix B, ‘‘Airworthiness Limitations. A ................................ B ................................ February 14, 2006. December 20, 2006. Original ...................... October 24, 2003. (1) The Director of the Federal Register approved the incorporation by reference of 2006, including Appendix A, Revision A, VerDate Aug<31>2005 15:37 Apr 11, 2008 Jkt 214001 Bombardier Alert Service Bulletin A601R– 27–144, Revision B, dated December 20, PO 00000 Frm 00023 Fmt 4700 Sfmt 4700 E:\FR\FM\14APR1.SGM 14APR1 Date 19982 Federal Register / Vol. 73, No. 72 / Monday, April 14, 2008 / Rules and Regulations dated December 20, 2006, in accordance with 5 U.S.C. 552(a) and 1 CFR part 51. (2) On March 27, 2006 (71 FR 12277, March 10, 2006), the Director of the Federal Register approved the incorporation by reference of Bombardier Alert Service Bulletin A601R–27–144, Revision A, dated February 14, 2006, including Appendix A, dated September 15, 2005. (3) On February 13, 2004 (69 FR 4234, January 29, 2004), the Director of the Federal Register approved the incorporation by reference of Bombardier Temporary Revision 2B–1784, dated October 24, 2003, to the CL– 600–2B19 Canadair Regional Jet Maintenance Requirements Manual, Part 2, Appendix B, ‘‘Airworthiness Limitations.’’ (4) 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 FAA, Transport Airplane Directorate, 1601 Lind Avenue, SW., Renton, Washington; or 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: https:// www.archives.gov/federal-register/cfr/ibrlocations.html. Issued in Renton, Washington, on March 31, 2008. Dionne Palermo, Acting Manager, Transport Airplane Directorate, Aircraft Certification Service. [FR Doc. E8–7294 Filed 4–11–08; 8:45 am] BILLING CODE 4910–13–P DEPARTMENT OF TRANSPORTATION Federal Aviation Administration 14 CFR Part 39 [Docket No. FAA–2008–0011; Directorate Identifier 2007–NM–203–AD; Amendment 39–15460; AD 2008–08–08] Airworthiness Directives; Boeing Model 757 Airplanes Federal Aviation Administration (FAA), DOT. ACTION: Final rule. cprice-sewell on PROD1PC62 with RULES AGENCY: SUMMARY: We are adopting a new airworthiness directive (AD) for certain Boeing Model 757 airplanes. This AD requires an inspection to determine the manufacturer and manufacture date of the oxygen masks in the passenger service units and the lavatory and attendant box assemblies, and corrective action if necessary. This AD results from a report that several passenger masks with broken in-line flow indicators were found following a mask deployment. We are issuing this AD to prevent the inline flow indicators of the passenger oxygen masks from fracturing and 15:37 Apr 11, 2008 Jkt 214001 Examining the AD Docket You may examine the AD docket on the Internet at https:// www.regulations.gov; or in person at the Docket Management Facility between 9 a.m. and 5 p.m., Monday through Friday, except Federal holidays. The AD docket contains this AD, the regulatory evaluation, any comments received, and other information. The address for the Docket Office (telephone 800–647–5527) is the Document Management Facility, U.S. Department of Transportation, Docket Operations, M–30, West Building Ground Floor, Room W12–140, 1200 New Jersey Avenue, SE., Washington, DC 20590. FOR FURTHER INFORMATION CONTACT: Robert Hettman, Aerospace Engineer, Cabin Safety and Environmental Systems Branch, ANM–150S, FAA, Seattle Aircraft Certification Office, 1601 Lind Avenue, SW., Renton, Washington 98057–3356; telephone (425) 917–6457; fax (425) 917–6590. SUPPLEMENTARY INFORMATION: Discussion RIN 2120–AA64 VerDate Aug<31>2005 separating, which could inhibit oxygen flow to the masks and consequently result in exposure of the passengers and cabin attendants to hypoxia following a depressurization event. DATES: This AD is effective May 19, 2008. The Director of the Federal Register approved the incorporation by reference of a certain publication listed in this AD as of May 19, 2008. ADDRESSES: For service information identified in this AD, contact Boeing Commercial Airplanes, P.O. Box 3707, Seattle, Washington 98124–2207. We issued a notice of proposed rulemaking (NPRM) to amend 14 CFR part 39 to include an airworthiness directive (AD) that would apply to certain Boeing Model 757 airplanes. That NPRM was published in the Federal Register on January 14, 2008 (73 FR 2195). That NPRM proposed to require an inspection to determine the manufacturer and manufacture date of the oxygen masks in the passenger service units and the lavatory and attendant box assemblies, and corrective action if necessary. Comments We gave the public the opportunity to participate in developing this AD. We considered the comment received. Boeing supports the NPRM. Conclusion We reviewed the relevant data, considered the comments received, and PO 00000 Frm 00024 Fmt 4700 Sfmt 4700 determined that air safety and the public interest require adopting the AD as proposed. Costs of Compliance There are about 1,035 airplanes of the affected design in the worldwide fleet. This AD affects about 640 airplanes of U.S. registry. The required actions take about 20 work hours per airplane, for an average of 240 oxygen masks per airplane, at an average labor rate of $80 per work hour. Based on these figures, the estimated cost of the AD for U.S. operators is $1,024,000, or $1,600 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 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. You can find our regulatory evaluation and the estimated costs of compliance in the AD Docket. E:\FR\FM\14APR1.SGM 14APR1

Agencies

[Federal Register Volume 73, Number 72 (Monday, April 14, 2008)]
[Rules and Regulations]
[Pages 19979-19982]
From the Federal Register Online via the Government Printing Office [www.gpo.gov]
[FR Doc No: E8-7294]


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

DEPARTMENT OF TRANSPORTATION

Federal Aviation Administration

14 CFR Part 39

[Docket No. FAA-2008-0047; Directorate Identifier 2007-NM-295-AD; 
Amendment 39-15461; AD 2008-08-09]
RIN 2120-AA64


Airworthiness Directives; Bombardier Model CL-600-2B19 (Regional 
Jet Series 100 & 440) Airplanes

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

ACTION: Final rule.

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

SUMMARY: The FAA is superseding an existing airworthiness directive 
(AD), which applies to certain Bombardier Model CL-600-2B19 (Regional 
Jet Series 100 & 400) airplanes. That AD currently requires revising 
the airworthiness limitations section of the Instructions for Continued 
Airworthiness of the maintenance requirements manual (MRM) by 
incorporating procedures for repetitive functional tests of the pilot 
input lever of the pitch feel simulator (PFS) units. That AD also 
requires new repetitive functional tests of the pilot input lever of 
the PFS unit, and corrective actions if necessary; and after initiating 
the new tests, requires removal of the existing procedures for the 
repetitive functional

[[Page 19980]]

tests from the MRM. This new AD requires revised procedures for the 
functional tests. This AD results from a report that the shear pin 
located in the input lever of two PFS units failed due to fatigue. We 
are issuing this AD to prevent undetected failure of the shear pins of 
both PFS units simultaneously, which could result in loss of pitch feel 
forces and consequent reduced control of the airplane.

DATES: This AD becomes effective May 19, 2008.
    The Director of the Federal Register approved the incorporation by 
reference of a certain publication listed in the AD as of May 19, 2008.
    On March 27, 2006 (71 FR 12277, March 10, 2006), the Director of 
the Federal Register approved the incorporation by reference of 
Bombardier Alert Service Bulletin A601R-27-144, Revision A, dated 
February 14, 2006, including Appendix A, dated September 15, 2005.
    On February 13, 2004 (69 FR 4234, January 29, 2004), the Director 
of the Federal Register approved the incorporation by reference of 
Bombardier Temporary Revision 2B-1784, dated October 24, 2003, to the 
CL-600-2B19 Canadair Regional Jet Maintenance Requirements Manual, Part 
2, Appendix B, ``Airworthiness Limitations.''

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.

Examining the AD Docket

    You may examine the AD docket on the Internet at https://
www.regulations.gov; or in person at the Docket Management Facility 
between 9 a.m. and 5 p.m., Monday through Friday, except Federal 
holidays. The AD docket contains this AD, the regulatory evaluation, 
any comments received, and other information. The address for the 
Docket Office (telephone 800-647-5527) is the Document Management 
Facility, U.S. Department of Transportation, Docket Operations, M-30, 
West Building Ground Floor, Room W12-140, 1200 New Jersey Avenue, SE., 
Washington, DC 20590.

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

SUPPLEMENTARY INFORMATION:

Discussion

    The FAA issued a notice of proposed rulemaking (NPRM) to amend 14 
CFR part 39 to include an AD that supersedes AD 2006-05-11 R1, 
amendment 39-14528 (71 FR 15323, March 28, 2006). The existing AD 
applies to certain Bombardier Model CL-600-2B19 (Regional Jet Series 
100 & 400) airplanes. That NPRM was published in the Federal Register 
on January 24, 2008 (73 FR 4125). That NPRM proposed to continue to 
require revising the airworthiness limitations section of the 
Instructions for Continued Airworthiness of the maintenance 
requirements manual (MRM) by incorporating procedures for repetitive 
functional tests of the pilot input lever of the pitch feel simulator 
(PFS) units. That NPRM also proposed to continue to require new 
repetitive functional tests of the pilot input lever of the PFS unit, 
and corrective actions if necessary; and after initiating the new 
tests, requires removal of the existing procedures for the repetitive 
functional tests from the MRM. That NPRM also proposed to require 
revised procedures for the functional tests.

Comments

    We provided the public the opportunity to participate in the 
development of this AD. No comments have been received on the NPRM 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 U.S.-
            Action               Work hours     Average labor      Cost per        registered       Fleet cost
                                                rate per hour      airplane         airplanes
----------------------------------------------------------------------------------------------------------------
Revise MRM...................               1             $80  $80.............             684  $54,720.
Functional tests.............               1              80  $80, per test                684  $54,720, per
                                                                cycle.                            test cycle.
----------------------------------------------------------------------------------------------------------------

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.

[[Page 19981]]

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 
removing amendment 39-14528 (71 FR 15323, March 28, 2006) and by adding 
the following new airworthiness directive (AD):

2008-08-09 Bombardier, Inc. (Formerly Canadair): Amendment 39-15461. 
Docket No. FAA-2008-0047; Directorate Identifier 2007-NM-295-AD.

Effective Date

    (a) This AD becomes effective May 19, 2008.

Affected ADs

    (b) This AD supersedes AD 2006-05-11 R1.

Applicability

    (c) This AD applies to Bombardier Model CL-600-2B19 (Regional 
Jet Series 100 & 400) airplanes, certificated in any category, 
serial numbers 7003 through 7990 inclusive, and 8000 and subsequent.

Unsafe Condition

    (d) This AD results from a report that the shear pin located in 
the input lever of two pitch feel simulator (PFS) units failed due 
to fatigue. We are issuing this AD to prevent undetected failure of 
the shear pins of both PFS units simultaneously, which could result 
in loss of pitch feel forces and consequent reduced 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.

Restatement of Requirements of AD 2006-05-11 R1

Revise Airworthiness Limitations (AWL) Section of Maintenance 
Requirements Manual

    (f) For airplanes having serial numbers 7003 through 7990 
inclusive: Within 14 days after February 13, 2004 (the effective 
date of AD 2004-02-07, which was superseded by AD 2006-05-11 R1), 
revise the AWL section of the Instructions for Continued 
Airworthiness of the maintenance requirements manual by 
incorporating the functional check of the PFS pilot input lever, 
Task R27-31-A024-01, as specified in Bombardier Temporary Revision 
(TR) 2B-1784, dated October 24, 2003, to the CL-600-2B19 Canadair 
Regional Jet Maintenance Requirements Manual, Part 2, Appendix B, 
``Airworthiness Limitations,'' into the AWL section.

New Repetitive Functional Tests and Corrective Actions

    (g) Before the accumulation of 4,000 total flight hours, or 
within 100 flight hours after March 27, 2006 (the effective date of 
AD 2006-05-11 R1), whichever occurs later: Do a functional test of 
the pilot input lever of the PFS units to determine if the lever is 
disconnected, in accordance with the Accomplishment Instructions of 
Bombardier Alert Service Bulletin A601R-27-144, Revision A, dated 
February 14, 2006, including Appendix A, dated September 15, 2005, 
except as required by paragraph (j) of this AD. Repeat the test at 
intervals not to exceed 100 flight hours. Accomplishing the initial 
functional test terminates the requirements of paragraph (f) of this 
AD and the repetitive functional checks of the PFS pilot input 
lever, Task R27-31-A024-01, as specified in the AWL section of the 
Instructions for Continued Airworthiness of CL-600-2B19 Canadair 
Regional Jet Maintenance Requirements Manual.
    (h) If any lever is found to be disconnected during any 
functional test required by paragraph (g) of this AD, do the actions 
specified in paragraphs (h)(1) and (h)(2) of this AD in accordance 
with the Accomplishment Instructions of Bombardier Alert Service 
Bulletin A601R-27-144, Revision A, dated February 14, 2006, 
including Appendix A, dated September 15, 2005, except as required 
by paragraph (j) of this AD.
    (1) Before further flight, replace the defective PFS with a 
serviceable PFS in accordance with the Accomplishment Instructions 
of the alert service bulletin; and
    (2) Within 30 days after removing the defective PFS, submit a 
test report to the manufacturer in accordance with the 
Accomplishment Instructions of the alert service bulletin. 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 contained in this AD and has 
assigned OMB Control Number 2120-0056.

Previously Accomplished Actions

    (i) Actions done before March 27, 2006, in accordance with 
Bombardier Alert Service Bulletin A601R-27-144, including Appendix 
A, dated September 15, 2005, are acceptable for compliance with the 
requirements of paragraph (g) of this AD.

New Requirements of This AD

New Service Bulletin for Functional Tests

    (j) As of the effective date of this AD, Bombardier Alert 
Service Bulletin A601R-27-144, Revision B, dated December 20, 2006, 
including Appendix A, Revision A, dated December 20, 2006, must be 
used for the actions required by paragraphs (g) and (h) of this AD.

Alternative Methods of Compliance (AMOCs)

    (k)(1) The Manager, New York Aircraft Certification Office 
(ACO), FAA, has the authority to approve AMOCs for this AD, if 
requested in accordance with the procedures found in 14 CFR 39.19.
    (2) To request a different method of compliance or a different 
compliance time for this AD, follow the procedures in 14 CFR 39.19. 
Before using any approved AMOC on any airplane to which the AMOC 
applies, notify your appropriate principal inspector (PI) in the FAA 
Flight Standards District Office (FSDO), or lacking a PI, your local 
FSDO.

Related Information

    (l) Canadian airworthiness directive CF-2005-41, dated December 
22, 2005, also addresses the subject of this AD.

Material Incorporated by Reference

    (m) You must use the applicable service information listed in 
Table 1 of this AD to perform the actions that are required by this 
AD, unless the AD specifies otherwise.

                                  Table 1.--Material Incorporated by Reference
----------------------------------------------------------------------------------------------------------------
    Bombardier service information                 Revision level                            Date
----------------------------------------------------------------------------------------------------------------
Alert Service Bulletin A601R-27-144,    A..................................  February 14, 2006.
 including Appendix A, dated September
 15, 2005.
Alert Service Bulletin A601R-27-144,    B..................................  December 20, 2006.
 including Appendix A, Revision A,
 dated December 20, 2006.
Temporary Revision 2B-1784 to the CL-   Original...........................  October 24, 2003.
 600-2B19 Canadair Regional Jet
 Maintenance Requirements Manual, Part
 2, Appendix B, ``Airworthiness
 Limitations.
----------------------------------------------------------------------------------------------------------------

    (1) The Director of the Federal Register approved the 
incorporation by reference of Bombardier Alert Service Bulletin 
A601R-27-144, Revision B, dated December 20, 2006, including 
Appendix A, Revision A,

[[Page 19982]]

dated December 20, 2006, in accordance with 5 U.S.C. 552(a) and 1 
CFR part 51.
    (2) On March 27, 2006 (71 FR 12277, March 10, 2006), the 
Director of the Federal Register approved the incorporation by 
reference of Bombardier Alert Service Bulletin A601R-27-144, 
Revision A, dated February 14, 2006, including Appendix A, dated 
September 15, 2005.
    (3) On February 13, 2004 (69 FR 4234, January 29, 2004), the 
Director of the Federal Register approved the incorporation by 
reference of Bombardier Temporary Revision 2B-1784, dated October 
24, 2003, to the CL-600-2B19 Canadair Regional Jet Maintenance 
Requirements Manual, Part 2, Appendix B, ``Airworthiness 
Limitations.''
    (4) 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 
FAA, Transport Airplane Directorate, 1601 Lind Avenue, SW., Renton, 
Washington; or 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: https://www.archives.gov/federal-
register/cfr/ibr-locations.html.

    Issued in Renton, Washington, on March 31, 2008.
Dionne Palermo,
Acting Manager, Transport Airplane Directorate, Aircraft Certification 
Service.
[FR Doc. E8-7294 Filed 4-11-08; 8:45 am]
BILLING CODE 4910-13-P
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