Airworthiness Directives; Bombardier Model CL-600-2B16 (CL-604) Airplanes and Model CL-600-2B19 (Regional Jet Series 100 & 440) Airplanes, 67502-67506 [E6-19798]

Download as PDF 67502 Federal Register / Vol. 71, No. 225 / Wednesday, November 22, 2006 / Proposed Rules DEPARTMENT OF TRANSPORTATION Federal Aviation Administration 14 CFR Part 39 [Docket No. FAA–2006–26378; Directorate Identifier 2006–NM–230–AD] RIN 2120–AA64 Airworthiness Directives; Bombardier Model CL–600–2B16 (CL–604) Airplanes and Model CL–600–2B19 (Regional Jet Series 100 & 440) Airplanes Federal Aviation Administration (FAA), Department of Transportation (DOT). ACTION: Notice of proposed rulemaking (NPRM). jlentini on PROD1PC65 with PROPOSAL AGENCY: SUMMARY: The FAA proposes to supersede an existing airworthiness directive (AD) that applies to certain Bombardier Model CL–600–2B16 (CL– 604) airplanes and Model CL–600–2B19 (Regional Jet Series 100 & 440) airplanes. These models may be referred to by their marketing designations as RJ100, RJ200, RJ440, CRJ100, CRJ200, CRJ440, and CL–65. The existing AD currently requires revising the Emergency Procedures section of the airplane flight manual (AFM) to advise the flightcrew of additional procedures to follow in the event of stabilizer trim runaway. The existing AD also requires revising the Abnormal Procedures section of the AFM to advise the flightcrew of procedures to follow in the event of MACH TRIM, STAB TRIM, and horizontal stabilizer trim malfunctions. The existing AD also requires revising the Normal section of the AFM to require a review of the location of certain circuit breakers and a functional check of the stabilizer trim system. The existing AD also requires installing circuit breaker identification collars and provides an optional terminating action for the requirements of the AD. This proposed AD would require doing the previously optional terminating action (installation of a new horizontal stabilizer trim control unit). This proposed AD results from a determination that the terminating action is necessary to address uncommanded horizontal stabilizer trim motion. We are proposing this AD to prevent horizontal stabilizer trim uncommanded motion, which could result in reduced controllability of the airplane. We must receive comments on this proposed AD by December 22, 2006. DATES: VerDate Aug<31>2005 16:20 Nov 21, 2006 Jkt 211001 Use one of the following addresses to submit comments on this proposed AD. • DOT Docket Web site: Go to https:// dms.dot.gov and follow the instructions for sending your comments electronically. • Government-wide rulemaking Web site: Go to https://www.regulations.gov and follow the instructions for sending your comments electronically. • Mail: Docket Management Facility; U.S. Department of Transportation, 400 Seventh Street, SW., Nassif Building, Room PL–401, Washington, DC 20590. • Fax: (202) 493–2251. • Hand Delivery: Room PL–401 on the plaza level of the Nassif Building, 400 Seventh Street, SW., Washington, DC, between 9 a.m. and 5 p.m., Monday through Friday, except Federal holidays. Contact Bombardier, Inc., Canadair, Aerospace Group, P.O. Box 6087, Station Centre-ville, Montreal, Quebec H3C 3G9, Canada, for service information identified in this proposed 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: ADDRESSES: Comments Invited We invite you to submit any relevant written data, views, or arguments regarding this proposed AD. Send your comments to an address listed in the ADDRESSES section. Include the docket number ‘‘Docket No. FAA–2006–26378; Directorate Identifier 2006–NM–230– AD’’ at the beginning of your comments. We specifically invite comments on the overall regulatory, economic, environmental, and energy aspects of the proposed AD. We will consider all comments received by the closing date and may amend the proposed AD in light of those comments. We will post all comments we receive, without change, to https:// dms.dot.gov, including any personal information you provide. We will also post a report summarizing each substantive verbal contact with FAA personnel concerning this proposed AD. Using the search function of that Web site, anyone can find and read the comments in any of our dockets, including the name of the individual who sent the comment (or signed the comment on behalf of an association, business, labor union, etc.). You may review the DOT’s complete Privacy Act PO 00000 Frm 00036 Fmt 4702 Sfmt 4702 Statement in the Federal Register published on April 11, 2000 (65 FR 19477–78), or you may visit https:// dms.dot.gov. Examining the Docket You may examine the 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 DOT street address stated in the ADDRESSES section. Comments will be available in the AD docket shortly after the Docket Management System receives them. Discussion On October 13, 2006, we issued AD 2006–22–06, amendment 39–14803 (71 FR 63219, October 30, 2006), for certain Bombardier Model CL–600–2B16 (CL– 604) airplanes and Model CL–600–2B19 (Regional Jet Series 100 & 440) airplanes. That AD requires revising the Emergency Procedures section of the airplane flight manual (AFM) to advise the flightcrew of additional procedures to follow in the event of stabilizer trim runaway. That AD also requires revising the Abnormal Procedures section of the AFM to advise the flightcrew of procedures to follow in the event of MACH TRIM, STAB TRIM, and horizontal stabilizer trim malfunctions. That AD also requires revising the Normal section of the AFM to require a review of the location of certain circuit breakers and a functional check of the stabilizer trim system. That AD also requires installing circuit breaker identification collars and provides an optional terminating action for the requirements of the AD. That AD resulted from reports of uncommanded horizontal stabilizer trim motion. We issued that AD to ensure that the flightcrew is advised of appropriate procedures to follow in the event of uncommanded movement or stabilizer trim runaway. Failure to follow these procedures could result in excessive uncommanded movement of the horizontal stabilizer trim actuator (HSTA) and loss of ability to use trim switches to override uncommanded movement or yoke disconnect switches to disconnect the HSTA, which could result in reduction of or loss of pitch control and consequent reduced controllability of the airplane. Actions Since Existing AD Was Issued The preamble to AD 2006–22–06 explains that we consider the requirements of that AD ‘‘interim E:\FR\FM\22NOP1.SGM 22NOP1 67503 Federal Register / Vol. 71, No. 225 / Wednesday, November 22, 2006 / Proposed Rules action’’ and that we were considering further rulemaking. We now have determined that further rulemaking is indeed necessary, and this proposed AD follows from that determination. The optional terminating action specified in AD 2006–22–06 (installation of a new, improved horizontal stabilizer trim control unit (HSTCU)) is necessary to address the identified unsafe condition. Transport Canada Civil Aviation (TCCA), which is the airworthiness authority for Canada, mandated the terminating action and issued Canadian airworthiness directives CF–2006–20R1, dated October 4, 2006, and CF–2006– 21R1, dated October 3, 2006, to ensure the continued airworthiness of these airplanes in Canada. FAA’s Determination and Requirements of the Proposed AD These airplane models are manufactured in Canada and are type certificated for operation in the United States under the provisions of section 21.29 of the Federal Aviation Regulations (14 CFR 21.29) and the applicable bilateral airworthiness agreement. Pursuant to this bilateral airworthiness agreement, TCCA has kept the FAA informed of the situation described above. We have examined TCCA’s findings, evaluated all pertinent information, and determined that AD action is necessary for airplanes of this type design that are certificated for operation in the United States. This proposed AD would supersede AD 2006–22–06 and would continue to require revising the Emergency, Normal, and Abnormal Procedures sections of the AFM and installing circuit breaker identification collars. This proposed AD would also require doing the terminating action (installation of a new HSTCU). Difference Between Canadian Airworthiness Directives and Proposed AD Although Canadian airworthiness directives CF–2006–20R1 and CF–2006– 21R1 recommend accomplishing the terminating action within 12 months, this proposed AD would require accomplishment within 9 months in order to match the date the actions required by the Canadian airworthiness directives must be completed. We find that 9 months is an appropriate compliance time to complete the terminating action. This has been coordinated with TCCA. Change to Existing AD This proposed AD would retain only certain requirements of AD 2006–22–06. As a result, the corresponding paragraph identifiers have changed in this proposed AD, as listed in the following table: REVISED PARAGRAPH IDENTIFIERS Requirement in AD 2006–22–06 Corresponding requirement in this proposed AD Paragraph Paragraph Paragraph Paragraph Paragraph Paragraph Paragraph Paragraph Paragraph Paragraph Paragraph Paragraph Paragraph Paragraph Paragraph Paragraph (h) ........ (i) ......... (j) ......... (k) ........ (l) ......... (m) ....... (n) ........ (o) ........ (f). (g). (h). (i). (j). (l). (m). (k). Costs of Compliance The following table provides the estimated costs for U.S. operators to comply with this proposed AD. The average labor rate per hour is $80. ESTIMATED COSTS Work hours Action AFM Revisions and Installation of Circuit Breaker Collars (required by AD 2006–22–06). Installation of HSTCU (new proposed action). 2 11 jlentini on PROD1PC65 with PROPOSAL 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 16:20 Nov 21, 2006 Jkt 211001 Number of U.S.-registered airplanes Parts Cost per airplane $3 ........................... $163 ....................... 875 $142,625. Between $2,530 and $3,995. Between $3,410 and $4,875. 875 Between $2,983,750 and $4,265,625. Regulatory Findings We have determined that this proposed AD would not have federalism implications under Executive Order 13132. This proposed AD would 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 the proposed regulation: 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 PO 00000 Frm 00037 Fmt 4702 Sfmt 4702 Fleet cost this proposed 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, Safety. The Proposed Amendment Accordingly, under the authority delegated to me by the Administrator, the FAA proposes to amend 14 CFR part 39 as follows: PART 39—AIRWORTHINESS DIRECTIVES 1. The authority citation for part 39 continues to read as follows: Authority: 49 U.S.C. 106(g), 40113, 44701. § 39.13 [Amended] 2. The Federal Aviation Administration (FAA) amends § 39.13 E:\FR\FM\22NOP1.SGM 22NOP1 67504 Federal Register / Vol. 71, No. 225 / Wednesday, November 22, 2006 / Proposed Rules by removing amendment 39–14803 (71 FR 63219, October 30, 2006) and adding the following new airworthiness directive (AD): Bombardier, Inc. (Formerly Canadair): Docket No. FAA–2006–26378; Directorate Identifier 2006–NM–230–AD. Comments Due Date (a) The FAA must receive comments on this AD action by December 22, 2006. Affected ADs (b) This AD supersedes AD 2006–22–06. Applicability (c) This AD applies to Bombardier Model CL–600–2B16 (CL–604) airplanes, serial numbers 5301 through 5665 inclusive; and Model CL–600–2B19 (Regional Jet Series 100 & 440) airplanes, serial numbers 7003 through 7990 inclusive and 8000 through 8066 inclusive; certificated in any category. Note 1: The Model CL–600–2B19 (Regional Jet Series 100 & 440) airplanes may be referred to by their marketing designations as RJ100, RJ200, RJ440, CRJ100, CRJ200, CRJ440, and CL–65. Unsafe Condition (d) This AD results from reports of uncommanded horizontal stabilizer trim motion. We are issuing this AD to prevent horizontal stabilizer trim uncommanded motion, which could result in reduced controllability 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 Certain Requirements of AD 2006–22–06 Airplane Flight Manual (AFM) Revisions (f) Within 14 days after November 14, 2006 (the effective date of AD 2006–22–06), make the applicable AFM revisions specified in paragraph (f)(1) or (f)(2) of this AD by incorporating the applicable Canadair (Bombardier) temporary revisions (TRs) identified in Table 1 of this AD into the applicable AFM. (1) For Model CL–600–2B16 (CL–604) airplanes: Revise the Emergency and Abnormal Procedures sections of the AFM to advise the flightcrew of additional procedures to follow in the event of stabilizer trim runaway and to advise the flightcrew of revised procedures to follow in the event of MACH TRIM, STAB TRIM, and horizontal stabilizer trim malfunctions. (2) For Model CL–600–2B19 (Regional Jet Series 100 & 440) airplanes: Revise the Emergency and Abnormal Procedures sections of the AFM to advise the flightcrew of revised procedures to follow in the event of stabilizer trim runaway and in the event of MACH TRIM, STAB TRIM, and horizontal stabilizer trim malfunctions. TABLE 1.—TRS For Bombardier Model— Use— Dated— To the— CL–600–2B16 (CL–604) airplanes .............. Canadair Challenger TR 604/21–1. Canadair Regional Jet TR RJ/152–5. October 3, 2006 .............. Canadair Challenger CL–604 AFM, PSP 604–1. Canadair Regional Jet AFM, CSP A–012. CL–600–2B19 (Regional Jet Series 100 & 440) airplanes. jlentini on PROD1PC65 with PROPOSAL (g) When the applicable TR specified in paragraph (f) of this AD has been included in the general revisions of the applicable AFM, those general revisions may be inserted into the AFM and the applicable TR may be removed, provided the relevant information in the general revisions is identical to that in the TR. VerDate Aug<31>2005 16:20 Nov 21, 2006 Jkt 211001 October 3, 2006 .............. Installation of Circuit Breaker Identification Collars (h) Within 14 days after November 14, 2006, install circuit breaker identification collars in accordance with Bombardier Modification Summary Package IS601R27410051, Revision C, dated September 29, 2006 (for Model CL–600–2B19 (Regional Jet Series 100 & 440) airplanes); or the Accomplishment Instructions of Bombardier Alert Service Bulletin A604–27– 029, dated September 28, 2006 (for Model PO 00000 Frm 00038 Fmt 4702 Sfmt 4702 CL–600–2B16 (CL–604) airplanes); as applicable. Additional AFM Revision (i) For Model CL–600–2B19 (Regional Jet Series 100 & 440) airplanes: Within 14 days after November 14, 2006, revise the Normal section of the Canadair Regional Jet AFM, CSP A–012, to include the statement specified in Figure 1 of this AD. This may be done by inserting a copy of Figure 1 of this AD into the AFM. E:\FR\FM\22NOP1.SGM 22NOP1 Note 2: When a statement identical to that in paragraph (i) of this AD has been included in the general revisions of the applicable AFM, those general revisions may be inserted into the AFM, and the copy of this AD may be removed from the AFM. (j) For Model CL–600–2B16 (CL–604) airplanes: Within 14 days after November 14, 2006, revise the Normal section of the Canadair Challenger CL–604 AFM, PSP 604– 1, to include the following statement. This may be done by inserting a copy of this AD into the AFM. ‘‘Prior to the flightcrew’s first flight of the day, do the following actions: VerDate Aug<31>2005 16:20 Nov 21, 2006 Jkt 211001 1. Review the location of the STAB CH1 HSTCU and STAB CH2 HSTCU circuit breakers. 2. Check the stabilizer trim system as detailed in CL–604 AFM ’Normal Procedures’ section titled ‘Flight Controls Trim Systems, Before Flight—First Flight of the Day.’ ’’ Note 3: When a statement identical to that in paragraph (j) of this AD has been included in the general revisions of the applicable AFM, those general revisions may be inserted into the AFM, and the copy of this AD may be removed from the AFM. PO 00000 Frm 00039 Fmt 4702 Sfmt 4702 67505 Previous Actions Accomplished According to Modification Summary Package (k) Actions accomplished before November 14, 2006, in accordance with Bombardier Modification Summary Package IS601R27410051, Revision A, dated September 18, 2006; or Revision B, dated September 27, 2006; are considered acceptable for compliance with the action specified in paragraph (h) of this AD, provided that the circuit breaker collars meet the color requirements of Bombardier Modification Summary Package IS601R27410051, Revision C, dated September 29, 2006. E:\FR\FM\22NOP1.SGM 22NOP1 EP22NO06.011</GPH> jlentini on PROD1PC65 with PROPOSAL Federal Register / Vol. 71, No. 225 / Wednesday, November 22, 2006 / Proposed Rules 67506 Federal Register / Vol. 71, No. 225 / Wednesday, November 22, 2006 / Proposed Rules New Requirements of This AD DEPARTMENT OF TRANSPORTATION Terminating Action—Installation of New, Improved Part Federal Aviation Administration (l) Within 9 months after the effective date of this AD, install horizontal stabilizer trim control unit (HSTCU), part number (P/N) 601R92301–15 (vendor P/N 7060–10) or higher dash number, in accordance with the Accomplishment Instructions of Bombardier Alert Service Bulletin A604–27–029, dated September 28, 2006 (for Model CL–600–2B16 (CL–604) airplanes); or Bombardier Service Bulletin 601R–27–147, dated September 28, 2006 (for Model CL–600–2B19 (Regional Jet Series 100 & 440) airplanes); as applicable. After doing the installation, the AFM revisions required by paragraph (f) of this AD may be removed from the applicable AFM, and the circuit breaker identification collars required by paragraph (h) of this AD may be removed. After doing the installation, the AFM revision required by paragraphs (i) and (j) of this AD may also be removed from the AFM but operators should note that the functional check of the stabilizer trim system on the airplane’s first flight of the day, as described in the AFM, must still be done. Note 4: Bombardier Service Bulletin 601R– 27–147, dated September 28, 2006, refers to Sagem Service Bulletin HSTCU–27–011, dated September 22, 2006, as an additional source of service information for accomplishment of the installation. 14 CFR Part 39 Service Bulletin Exception (m) Although Bombardier Alert Service Bulletin A604–27–029, dated September 28, 2006, specifies to return certain parts to the manufacturer, this AD does not include that requirement. Alternative Methods of Compliance (AMOCs) (n)(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 § 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 jlentini on PROD1PC65 with PROPOSAL (o) Canadian airworthiness directives CF– 2006–20R1, dated October 4, 2006, and CF– 2006–21R1, dated October 3, 2006, also address the subject of this AD. Issued in Renton, Washington, on November 6, 2006. Ali Bahrami, Manager, Transport Airplane Directorate, Aircraft Certification Service. [FR Doc. E6–19798 Filed 11–21–06; 8:45 am] BILLING CODE 4910–13–P VerDate Aug<31>2005 16:20 Nov 21, 2006 Jkt 211001 [Docket No. FAA–2006–26236; Directorate Identifier 2006–CE–66–AD] RIN 2120–AA64 Airworthiness Directives; SOCATA— Groupe AEROSPATIALE Models TB 20 and TB 21 Airplanes Federal Aviation Administration (FAA), Department of Transportation (DOT). ACTION: Notice of proposed rulemaking (NPRM). AGENCY: SUMMARY: We propose to adopt a new airworthiness directive (AD) for the products listed above. This proposed AD results from mandatory continuing airworthiness information (MCAI) issued 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 reports of interference between the wing spar lower boom and the wheel fairing attaching screw. The proposed AD would require actions that are intended to address the unsafe condition described in the MCAI. DATES: We must receive comments on this proposed AD by December 22, 2006. You may send comments by any of the following methods: • DOT Docket Web Site: Go to https:// dms.dot.gov and follow the instructions for sending your comments electronically. • Fax: (202) 493–2251. • Mail: Docket Management Facility, U.S. Department of Transportation, 400 Seventh Street, SW., Nassif Building, Room PL–401, Washington, DC 20590– 0001. • Hand Delivery: Room PL–401 on the plaza level of the Nassif Building, 400 Seventh Street, SW., Washington, DC, between 9 a.m. and 5 p.m., Monday through Friday, except Federal holidays. • Federal eRulemaking Portal: https:// www.regulations.gov. Follow the instructions for submitting comments. ADDRESSES: Examining the AD Docket You may examine the AD docket on the Internet at https://dms.dot.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 proposed AD, the regulatory evaluation, any comments received, and other information. The street address for the PO 00000 Frm 00040 Fmt 4702 Sfmt 4702 Docket Office (telephone (800) 647– 5227) is in the ADDRESSES section. Comments will be available in the AD docket shortly after receipt. FOR FURTHER INFORMATION CONTACT: Doug Rudolph, Aerospace Engineer, FAA, Small Airplane Directorate, 901 Locust, Room 301, Kansas City, Missouri 64106; telephone: (816) 329– 4059; fax: (816) 329–4090. SUPPLEMENTARY INFORMATION: Streamlined Issuance of AD The FAA is implementing a new process for streamlining the issuance of ADs related to MCAI. The streamlined process will allow us to adopt MCAI safety requirements in a more efficient manner and will reduce safety risks to the public. This process continues to follow all FAA AD issuance processes to meet legal, economic, Administrative Procedure Act, and Federal Register requirements. We also continue to meet our technical decision-making responsibilities to identify and correct unsafe conditions on U.S.-certificated products. This proposed AD references the MCAI and related service information that we considered in forming the engineering basis to correct the unsafe condition. The proposed AD contains text copied from the MCAI and for this reason might not follow our plain language principles. Comments Invited We invite you to send any written relevant data, views, or arguments about this proposed AD. Send your comments to an address listed under the ADDRESSES section. Include ‘‘Docket No. FAA–2006–26236; Directorate Identifier 2006–CE–66–AD’’ at the beginning of your comments. We specifically invite comments on the overall regulatory, economic, environmental, and energy aspects of this proposed AD. We will consider all comments received by the closing date and may amend this proposed AD because of those comments. We will post all comments we receive, without change, to https:// dms.dot.gov, including any personal information you provide. We will also post a report summarizing each substantive verbal contact we receive about this proposed AD. Discussion The European Aviation Safety Agency (EASA), which is the Technical Agent for the Member States of the European Community, has issued AD No.: 2006– 0123, dated May 16, 2006 (referred to after this as ‘‘the MCAI’’), to correct an unsafe condition for the specified E:\FR\FM\22NOP1.SGM 22NOP1

Agencies

[Federal Register Volume 71, Number 225 (Wednesday, November 22, 2006)]
[Proposed Rules]
[Pages 67502-67506]
From the Federal Register Online via the Government Printing Office [www.gpo.gov]
[FR Doc No: E6-19798]



[[Page 67502]]

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DEPARTMENT OF TRANSPORTATION

Federal Aviation Administration

14 CFR Part 39

[Docket No. FAA-2006-26378; Directorate Identifier 2006-NM-230-AD]
RIN 2120-AA64


Airworthiness Directives; Bombardier Model CL-600-2B16 (CL-604) 
Airplanes and Model CL-600-2B19 (Regional Jet Series 100 & 440) 
Airplanes

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

ACTION: Notice of proposed rulemaking (NPRM).

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

SUMMARY: The FAA proposes to supersede an existing airworthiness 
directive (AD) that applies to certain Bombardier Model CL-600-2B16 
(CL-604) airplanes and Model CL-600-2B19 (Regional Jet Series 100 & 
440) airplanes. These models may be referred to by their marketing 
designations as RJ100, RJ200, RJ440, CRJ100, CRJ200, CRJ440, and CL-65. 
The existing AD currently requires revising the Emergency Procedures 
section of the airplane flight manual (AFM) to advise the flightcrew of 
additional procedures to follow in the event of stabilizer trim 
runaway. The existing AD also requires revising the Abnormal Procedures 
section of the AFM to advise the flightcrew of procedures to follow in 
the event of MACH TRIM, STAB TRIM, and horizontal stabilizer trim 
malfunctions. The existing AD also requires revising the Normal section 
of the AFM to require a review of the location of certain circuit 
breakers and a functional check of the stabilizer trim system. The 
existing AD also requires installing circuit breaker identification 
collars and provides an optional terminating action for the 
requirements of the AD. This proposed AD would require doing the 
previously optional terminating action (installation of a new 
horizontal stabilizer trim control unit). This proposed AD results from 
a determination that the terminating action is necessary to address 
uncommanded horizontal stabilizer trim motion. We are proposing this AD 
to prevent horizontal stabilizer trim uncommanded motion, which could 
result in reduced controllability of the airplane.

DATES: We must receive comments on this proposed AD by December 22, 
2006.

ADDRESSES: Use one of the following addresses to submit comments on 
this proposed AD.
     DOT Docket Web site: Go to https://dms.dot.gov and follow 
the instructions for sending your comments electronically.
     Government-wide rulemaking Web site: Go to https://
www.regulations.gov and follow the instructions for sending your 
comments electronically.
     Mail: Docket Management Facility; U.S. Department of 
Transportation, 400 Seventh Street, SW., Nassif Building, Room PL-401, 
Washington, DC 20590.
     Fax: (202) 493-2251.
     Hand Delivery: Room PL-401 on the plaza level of the 
Nassif Building, 400 Seventh Street, SW., Washington, DC, between 9 
a.m. and 5 p.m., Monday through Friday, except Federal holidays.
    Contact Bombardier, Inc., Canadair, Aerospace Group, P.O. Box 6087, 
Station Centre-ville, Montreal, Quebec H3C 3G9, Canada, for service 
information identified in this proposed 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:

Comments Invited

    We invite you to submit any relevant written data, views, or 
arguments regarding this proposed AD. Send your comments to an address 
listed in the ADDRESSES section. Include the docket number ``Docket No. 
FAA-2006-26378; Directorate Identifier 2006-NM-230-AD'' at the 
beginning of your comments. We specifically invite comments on the 
overall regulatory, economic, environmental, and energy aspects of the 
proposed AD. We will consider all comments received by the closing date 
and may amend the proposed AD in light of those comments.
    We will post all comments we receive, without change, to https://
dms.dot.gov, including any personal information you provide. We will 
also post a report summarizing each substantive verbal contact with FAA 
personnel concerning this proposed AD. Using the search function of 
that Web site, anyone can find and read the comments in any of our 
dockets, including the name of the individual who sent the comment (or 
signed the comment on behalf of an association, business, labor union, 
etc.). You may review the DOT's complete Privacy Act Statement in the 
Federal Register published on April 11, 2000 (65 FR 19477-78), or you 
may visit https://dms.dot.gov.

Examining the Docket

    You may examine the 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 DOT 
street address stated in the ADDRESSES section. Comments will be 
available in the AD docket shortly after the Docket Management System 
receives them.

Discussion

    On October 13, 2006, we issued AD 2006-22-06, amendment 39-14803 
(71 FR 63219, October 30, 2006), for certain Bombardier Model CL-600-
2B16 (CL-604) airplanes and Model CL-600-2B19 (Regional Jet Series 100 
& 440) airplanes. That AD requires revising the Emergency Procedures 
section of the airplane flight manual (AFM) to advise the flightcrew of 
additional procedures to follow in the event of stabilizer trim 
runaway. That AD also requires revising the Abnormal Procedures section 
of the AFM to advise the flightcrew of procedures to follow in the 
event of MACH TRIM, STAB TRIM, and horizontal stabilizer trim 
malfunctions. That AD also requires revising the Normal section of the 
AFM to require a review of the location of certain circuit breakers and 
a functional check of the stabilizer trim system. That AD also requires 
installing circuit breaker identification collars and provides an 
optional terminating action for the requirements of the AD. That AD 
resulted from reports of uncommanded horizontal stabilizer trim motion. 
We issued that AD to ensure that the flightcrew is advised of 
appropriate procedures to follow in the event of uncommanded movement 
or stabilizer trim runaway. Failure to follow these procedures could 
result in excessive uncommanded movement of the horizontal stabilizer 
trim actuator (HSTA) and loss of ability to use trim switches to 
override uncommanded movement or yoke disconnect switches to disconnect 
the HSTA, which could result in reduction of or loss of pitch control 
and consequent reduced controllability of the airplane.

Actions Since Existing AD Was Issued

    The preamble to AD 2006-22-06 explains that we consider the 
requirements of that AD ``interim

[[Page 67503]]

action'' and that we were considering further rulemaking. We now have 
determined that further rulemaking is indeed necessary, and this 
proposed AD follows from that determination. The optional terminating 
action specified in AD 2006-22-06 (installation of a new, improved 
horizontal stabilizer trim control unit (HSTCU)) is necessary to 
address the identified unsafe condition.
    Transport Canada Civil Aviation (TCCA), which is the airworthiness 
authority for Canada, mandated the terminating action and issued 
Canadian airworthiness directives CF-2006-20R1, dated October 4, 2006, 
and CF-2006-21R1, dated October 3, 2006, to ensure the continued 
airworthiness of these airplanes in Canada.

FAA's Determination and Requirements of the Proposed AD

    These airplane models are manufactured in Canada and are type 
certificated for operation in the United States under the provisions of 
section 21.29 of the Federal Aviation Regulations (14 CFR 21.29) and 
the applicable bilateral airworthiness agreement. Pursuant to this 
bilateral airworthiness agreement, TCCA has kept the FAA informed of 
the situation described above. We have examined TCCA's findings, 
evaluated all pertinent information, and determined that AD action is 
necessary for airplanes of this type design that are certificated for 
operation in the United States.
    This proposed AD would supersede AD 2006-22-06 and would continue 
to require revising the Emergency, Normal, and Abnormal Procedures 
sections of the AFM and installing circuit breaker identification 
collars. This proposed AD would also require doing the terminating 
action (installation of a new HSTCU).

Difference Between Canadian Airworthiness Directives and Proposed AD

    Although Canadian airworthiness directives CF-2006-20R1 and CF-
2006-21R1 recommend accomplishing the terminating action within 12 
months, this proposed AD would require accomplishment within 9 months 
in order to match the date the actions required by the Canadian 
airworthiness directives must be completed. We find that 9 months is an 
appropriate compliance time to complete the terminating action. This 
has been coordinated with TCCA.

Change to Existing AD

    This proposed AD would retain only certain requirements of AD 2006-
22-06. As a result, the corresponding paragraph identifiers have 
changed in this proposed AD, as listed in the following table:

                      Revised Paragraph Identifiers
------------------------------------------------------------------------
                                           Corresponding requirement in
      Requirement in AD 2006-22-06               this proposed AD
------------------------------------------------------------------------
Paragraph (h)..........................  Paragraph (f).
Paragraph (i)..........................   Paragraph (g).
Paragraph (j)..........................   Paragraph (h).
Paragraph (k)..........................  Paragraph (i).
Paragraph (l)..........................   Paragraph (j).
Paragraph (m)..........................  Paragraph (l).
Paragraph (n)..........................   Paragraph (m).
Paragraph (o)..........................   Paragraph (k).
------------------------------------------------------------------------

Costs of Compliance

    The following table provides the estimated costs for U.S. operators 
to comply with this proposed AD. The average labor rate per hour is 
$80.

                                                                     Estimated Costs
--------------------------------------------------------------------------------------------------------------------------------------------------------
                                                                                                Number of U.S.-
               Action                   Work             Parts             Cost per airplane      registered                   Fleet cost
                                       hours                                                       airplanes
--------------------------------------------------------------------------------------------------------------------------------------------------------
AFM Revisions and Installation of            2  $3....................  $163..................             875  $142,625.
 Circuit Breaker Collars (required
 by AD 2006-22-06).
Installation of HSTCU (new proposed         11  Between $2,530 and      Between $3,410 and                 875  Between $2,983,750 and $4,265,625.
 action).                                        $3,995.                 $4,875.
--------------------------------------------------------------------------------------------------------------------------------------------------------

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 proposed AD would not have federalism 
implications under Executive Order 13132. This proposed AD would 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 the proposed 
regulation:
    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 proposed 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, Safety.

The Proposed Amendment

    Accordingly, under the authority delegated to me by the 
Administrator, the FAA proposes to amend 14 CFR part 39 as follows:

PART 39--AIRWORTHINESS DIRECTIVES

    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]

    2. The Federal Aviation Administration (FAA) amends Sec.  39.13

[[Page 67504]]

by removing amendment 39-14803 (71 FR 63219, October 30, 2006) and 
adding the following new airworthiness directive (AD):

Bombardier, Inc. (Formerly Canadair): Docket No. FAA-2006-26378; 
Directorate Identifier 2006-NM-230-AD.

Comments Due Date

    (a) The FAA must receive comments on this AD action by December 
22, 2006.

Affected ADs

    (b) This AD supersedes AD 2006-22-06.

Applicability

    (c) This AD applies to Bombardier Model CL-600-2B16 (CL-604) 
airplanes, serial numbers 5301 through 5665 inclusive; and Model CL-
600-2B19 (Regional Jet Series 100 & 440) airplanes, serial numbers 
7003 through 7990 inclusive and 8000 through 8066 inclusive; 
certificated in any category.

    Note 1: The Model CL-600-2B19 (Regional Jet Series 100 & 440) 
airplanes may be referred to by their marketing designations as 
RJ100, RJ200, RJ440, CRJ100, CRJ200, CRJ440, and CL-65.

Unsafe Condition

    (d) This AD results from reports of uncommanded horizontal 
stabilizer trim motion. We are issuing this AD to prevent horizontal 
stabilizer trim uncommanded motion, which could result in reduced 
controllability 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 Certain Requirements of AD 2006-22-06

Airplane Flight Manual (AFM) Revisions

    (f) Within 14 days after November 14, 2006 (the effective date 
of AD 2006-22-06), make the applicable AFM revisions specified in 
paragraph (f)(1) or (f)(2) of this AD by incorporating the 
applicable Canadair (Bombardier) temporary revisions (TRs) 
identified in Table 1 of this AD into the applicable AFM.
    (1) For Model CL-600-2B16 (CL-604) airplanes: Revise the 
Emergency and Abnormal Procedures sections of the AFM to advise the 
flightcrew of additional procedures to follow in the event of 
stabilizer trim runaway and to advise the flightcrew of revised 
procedures to follow in the event of MACH TRIM, STAB TRIM, and 
horizontal stabilizer trim malfunctions.
    (2) For Model CL-600-2B19 (Regional Jet Series 100 & 440) 
airplanes: Revise the Emergency and Abnormal Procedures sections of 
the AFM to advise the flightcrew of revised procedures to follow in 
the event of stabilizer trim runaway and in the event of MACH TRIM, 
STAB TRIM, and horizontal stabilizer trim malfunctions.

                                                  Table 1.--TRs
----------------------------------------------------------------------------------------------------------------
        For Bombardier Model--                  Use--                   Dated--                  To the--
----------------------------------------------------------------------------------------------------------------
CL-600-2B16 (CL-604) airplanes.......  Canadair Challenger TR   October 3, 2006........  Canadair Challenger CL-
                                        604/21-1.                                         604 AFM, PSP 604-1.
CL-600-2B19 (Regional Jet Series 100   Canadair Regional Jet    October 3, 2006........  Canadair Regional Jet
 & 440) airplanes.                      TR RJ/152-5.                                      AFM, CSP A-012.
----------------------------------------------------------------------------------------------------------------

    (g) When the applicable TR specified in paragraph (f) of this AD 
has been included in the general revisions of the applicable AFM, 
those general revisions may be inserted into the AFM and the 
applicable TR may be removed, provided the relevant information in 
the general revisions is identical to that in the TR.

Installation of Circuit Breaker Identification Collars

    (h) Within 14 days after November 14, 2006, install circuit 
breaker identification collars in accordance with Bombardier 
Modification Summary Package IS601R27410051, Revision C, dated 
September 29, 2006 (for Model CL-600-2B19 (Regional Jet Series 100 & 
440) airplanes); or the Accomplishment Instructions of Bombardier 
Alert Service Bulletin A604-27-029, dated September 28, 2006 (for 
Model CL-600-2B16 (CL-604) airplanes); as applicable.

Additional AFM Revision

    (i) For Model CL-600-2B19 (Regional Jet Series 100 & 440) 
airplanes: Within 14 days after November 14, 2006, revise the Normal 
section of the Canadair Regional Jet AFM, CSP A-012, to include the 
statement specified in Figure 1 of this AD. This may be done by 
inserting a copy of Figure 1 of this AD into the AFM.

[[Page 67505]]

[GRAPHIC] [TIFF OMITTED] TP22NO06.011


    Note 2: When a statement identical to that in paragraph (i) of 
this AD has been included in the general revisions of the applicable 
AFM, those general revisions may be inserted into the AFM, and the 
copy of this AD may be removed from the AFM.

    (j) For Model CL-600-2B16 (CL-604) airplanes: Within 14 days 
after November 14, 2006, revise the Normal section of the Canadair 
Challenger CL-604 AFM, PSP 604-1, to include the following 
statement. This may be done by inserting a copy of this AD into the 
AFM.
    ``Prior to the flightcrew's first flight of the day, do the 
following actions:
    1. Review the location of the STAB CH1 HSTCU and STAB CH2 HSTCU 
circuit breakers.
    2. Check the stabilizer trim system as detailed in CL-604 AFM 
'Normal Procedures' section titled `Flight Controls Trim Systems, 
Before Flight--First Flight of the Day.' ''

    Note 3: When a statement identical to that in paragraph (j) of 
this AD has been included in the general revisions of the applicable 
AFM, those general revisions may be inserted into the AFM, and the 
copy of this AD may be removed from the AFM.

Previous Actions Accomplished According to Modification Summary 
Package

    (k) Actions accomplished before November 14, 2006, in accordance 
with Bombardier Modification Summary Package IS601R27410051, 
Revision A, dated September 18, 2006; or Revision B, dated September 
27, 2006; are considered acceptable for compliance with the action 
specified in paragraph (h) of this AD, provided that the circuit 
breaker collars meet the color requirements of Bombardier 
Modification Summary Package IS601R27410051, Revision C, dated 
September 29, 2006.

[[Page 67506]]

New Requirements of This AD

Terminating Action--Installation of New, Improved Part

    (l) Within 9 months after the effective date of this AD, install 
horizontal stabilizer trim control unit (HSTCU), part number (P/N) 
601R92301-15 (vendor P/N 7060-10) or higher dash number, in 
accordance with the Accomplishment Instructions of Bombardier Alert 
Service Bulletin A604-27-029, dated September 28, 2006 (for Model 
CL-600-2B16 (CL-604) airplanes); or Bombardier Service Bulletin 
601R-27-147, dated September 28, 2006 (for Model CL-600-2B19 
(Regional Jet Series 100 & 440) airplanes); as applicable. After 
doing the installation, the AFM revisions required by paragraph (f) 
of this AD may be removed from the applicable AFM, and the circuit 
breaker identification collars required by paragraph (h) of this AD 
may be removed. After doing the installation, the AFM revision 
required by paragraphs (i) and (j) of this AD may also be removed 
from the AFM but operators should note that the functional check of 
the stabilizer trim system on the airplane's first flight of the 
day, as described in the AFM, must still be done.

    Note 4: Bombardier Service Bulletin 601R-27-147, dated September 
28, 2006, refers to Sagem Service Bulletin HSTCU-27-011, dated 
September 22, 2006, as an additional source of service information 
for accomplishment of the installation.

Service Bulletin Exception

    (m) Although Bombardier Alert Service Bulletin A604-27-029, 
dated September 28, 2006, specifies to return certain parts to the 
manufacturer, this AD does not include that requirement.

Alternative Methods of Compliance (AMOCs)

    (n)(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 Sec.  
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

    (o) Canadian airworthiness directives CF-2006-20R1, dated 
October 4, 2006, and CF-2006-21R1, dated October 3, 2006, also 
address the subject of this AD.

    Issued in Renton, Washington, on November 6, 2006.
Ali Bahrami,
Manager, Transport Airplane Directorate, Aircraft Certification 
Service.
 [FR Doc. E6-19798 Filed 11-21-06; 8:45 am]
BILLING CODE 4910-13-P