75830 Federal Register / Vol. 69, No. 243 / Monday, December 20, 2004 / Rules and Regulations 

DEPARTMENT OF TRANSPORTATION

Federal Aviation Administration 

14 CFR Part 39 

[Docket No. FAA–2004–19862; Directorate 

Identifier 2004–NM–228–AD; Amendment 

39–13907; AD 2004–25–19] 

RIN 2120–AA64 

Airworthiness Directives; Bombardier 

Model CL–600–1A11 (CL–600), CL–

600–2A12 (CL–601), CL–600–2B16 (CL–

601–3A, CL–601–3R, and CL–604) 

Series Airplanes

AGENCY: Federal Aviation 

Administration (FAA), DOT.

ACTION: Final rule; request for 

comments. 

SUMMARY: The FAA is adopting a new 

airworthiness directive (AD) for certain 

Bombardier Model CL–600–1A11 (CL–

600), CL–600–2A12 (CL–601), CL–600–

2B16 (CL–601–3A, CL–601–3R, and CL–

604) series airplanes. This AD requires 

revising the airplane flight manual to 

provide the flightcrew with procedures 

and limitations for operating an airplane 

with out-of-tolerance angle of attack 

(AOA) transducers. This AD also 

requires repetitive linearity tests of the 

AOA transducers, and corrective action 

if necessary. This AD is prompted by a 

report of premature wear of the 

potentiometers in AOA transducers 

having a certain part number. We are 

issuing this AD to prevent a delay in the 

stall computer commands for stall 

warning, stick shaker, and stick pusher 

operation, due to premature wear of the 

potentiometers of the AOA transducers, 

which may cause the airplane to enter 

a stall condition, and result in loss of 

control of the airplane.

DATES: Effective January 4, 2005. 

The incorporation by reference of 

certain publications listed in the AD is 

approved by the Director of the Federal 

Register as of January 4, 2005. 

We must receive comments on this 

AD by February 18, 2005.

ADDRESSES: Use one of the following 

addresses to submit comments on this 

AD. 

• DOT Docket Web site: Go to

http://dms.dot.gov and follow the 

instructions for sending your comments 

electronically. 

• Government-wide rulemaking Web 

site: Go to http://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. 

For service information identified in 

this AD, contact Bombardier, Inc., 

Canadair, Aerospace Group, P.O. Box 

6087, Station Centre-ville, Montreal, 

Quebec H3C 3G9, Canada. You can 

examine this information at the National 

Archives and Records Administration 

(NARA). For information on the 

availability of this material at NARA, 

call (202) 741–6030, or go to: http://

www.archives.gov/federal_register/

code_of_federal_regulations/

ibr_locations.html.

You can examine the contents of this 

AD docket on the Internet at http://

dms.dot.gov, or in person at the Docket 

Management Facility, U.S. Department 

of Transportation, 400 Seventh Street 

SW., Room PL–401, on the plaza level 

of the Nassif Building, Washington, DC. 

This docket number is FAA–2004–

19862; the directorate identifier for this 

docket is 2004–NM–228–AD. 

Docket Management System (DMS) 

The FAA has implemented new 

procedures for maintaining AD dockets 

electronically. As of May 17, 2004, new 

AD actions are posted on DMS and 

assigned a docket number. We track 

each action and assign a corresponding 

directorate identifier. The DMS AD 

docket number is in the form ‘‘Docket 

No. FAA–2004–99999.’’ The Transport 

Airplane Directorate identifier is in the 

form ‘‘Directorate Identifier 2004–NM–

999–AD.’’ Each DMS AD docket also 

lists the directorate identifier (‘‘Old 

Docket Number’’) as a cross-reference 

for searching purposes. 

Examining the Docket 

You can examine the AD docket on 

the Internet at http://dms.dot.gov, or in 

person at the Docket Management 

Facility office between 9 a.m. and 5 

p.m., Monday through Friday, except 

Federal holidays. The Docket 

Management Facility office (telephone 

(800) 647–5227) is located on the plaza 

level of the Nassif Building at the DOT 

street address stated in the ADDRESSES

section. Comments will be available in 

the AD docket shortly after the DMS 

receives them.

FOR FURTHER INFORMATION CONTACT:

Technical information: Wing Chan, 

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–

7311; fax (516) 794–5531. 

Plain language information: Marcia 

Walters, marcia.walters@faa.gov.

SUPPLEMENTARY INFORMATION: Transport 

Canada Civil Aviation (TCCA), which is 

the airworthiness authority for Canada, 

notified the FAA that an unsafe 

condition may exist on certain 

Bombardier Model CL–600–1A11 (CL–

600), CL–600–2A12 (CL–601), CL–600–

2B16 (CL–601–3A, CL–601–3R, and CL–

604) series airplanes. TCCA advises that 

angle of attack (AOA) transducers 

having a certain part number may have 

potentiometers that wear prematurely. 

The problem is dormant and can only be 

identified on in-service airplanes by a 

linearity test of each AOA transducer. 

Prematurely worn potentiometers in the 

AOA transducers, if not corrected, could 

result in a delay in the stall computer 

commands for stall warning, stick 

shaker, and stick pusher operation, 

which may cause the airplane to enter 

a stall condition, and result in loss of 

control of the airplane. 

Relevant Service Information 

Bombardier has issued the following 

temporary revisions (TR) to the 

applicable Canadair Challenger airplane 

flight manual (AFM).

BOMBARDIER TEMPORARY REVISIONS

Model Temporary

revision 

Product support

publication Dated 

CL–600–1A11 (CL–600) series airplanes .................. 600/20–2 600 (not stated in document) ......... October 15, 2004 

600–1/15–2 600–1 (not stated in document) ..... October 15, 2004 

CL–600–2A12 (CL–601) series airplanes .................. 601/12–2 601–1B–1 ....................................... October 15, 2004 

601/13–2 601–1A–1 ....................................... October 15, 2004 

601/17–2 601–1B ........................................... October 15, 2004 

601/25–2 601–1A–18 (not stated in document).October 15, 2004 

Federal Register / Vol. 69, No. 243 / Monday, December 20, 2004 / Rules and Regulations 75831

BOMBARDIER TEMPORARY REVISIONS—Continued

Model Temporary

revision 

Product support

publication Dated 

CL–600–2B16 (CL–601–3A and –3R) series airplanes.601/22–2 601A–1–1 ....................................... October 15, 2004 

601/23–2 601A–1 ........................................... October 15, 2004 

CL–600–2B16 (CL–604) series airplanes .................. 604/9–6 604–1 ............................................. October 15, 2004 

Among other things, the TRs describe 

procedures for revising the Limitations, 

Performance, and Normal Procedures 

Sections of the applicable Canadair 

Challenger AFM, to provide the 

flightcrew with procedures and 

limitations for operating an airplane 

with any out-of-tolerance AOA 

transducer. 

Bombardier has also issued the 

following alert service bulletins:

ALERT SERVICE BULLETINS

For model— Bombardier alert

service bulletin Dated 

CL–600–1A11 (CL–600) series airplanes ................... A600–0729 October 14, 2004 

CL–600–2A12 (CL–601) series airplanes and CL–

600–2B16 (CL–601–3A and –3R) series airplanes A601–0571 October 14, 2004 

CL–600–2B16 (CL–604) series airplanes ................... A604–27–026 October 14, 2004 

The alert service bulletins describe 

procedures for doing repetitive linearity 

checks (tests) for each AOA transducer, 

and corrective action if necessary. The 

corrective action includes replacing any 

AOA transducer that does not meet the 

specified linearity requirements with a 

serviceable AOA transducer. 

TCCA mandated the temporary 

revisions and alert service bulletins and 

issued Canadian airworthiness directive 

CF–2004–22, dated October 22, 2004, to 

ensure the continued airworthiness of 

these airplanes in Canada. 

FAA’s Determination and Requirements 

of This 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. According to this bilateral 

airworthiness agreement, TCCA has 

kept us informed of the situation 

described above. We have examined the 

TCCA’s findings, evaluated all pertinent 

information, and determined that we 

need to issue an AD for products of this 

type design that are certificated for 

operation in the United States. 

Therefore, we are issuing this AD to 

require revising the airplane flight 

manual to provide the flightcrew with 

procedures and limitations for operating 

an airplane with out-of-tolerance AOA 

transducers. This AD also requires 

repetitive linearity tests of the AOA 

transducers, and corrective action if 

necessary. This AD requires 

accomplishing the actions specified in 

the service information described 

previously, except as described in 

‘‘Differences Between This AD and 

Referenced Alert Service Bulletins.’’

Difference Between Proposed AD and 

Referenced Alert Service Bulletins 

Operators should note that, although 

the Accomplishment Instructions of the 

referenced alert service bulletins 

describe procedures for submitting 

service bulletin incorporation notices to 

the manufacturer, this AD does not 

require those actions. 

Clarification of Terminology 

In this AD, the linearity ‘‘checks’’ of 

the AOA transducers specified in the 

Canadian airworthiness directive and 

the Bombardier alert service bulletins 

are referred to as ‘‘tests.’’

Interim Action 

This is considered to be interim 

action until final action is identified, at 

which time we may consider further 

rulemaking. 

FAA’s Determination of the Effective 

Date 

An unsafe condition exists that 

requires the immediate adoption of this 

AD; therefore, providing notice and 

opportunity for public comment before 

the AD is issued is impracticable, and 

good cause exists to make this AD 

effective in less than 30 days. 

Comments Invited 

This AD is a final rule that involves 

requirements that affect flight safety and 

was not preceded by notice and an 

opportunity for public comment; 

however, we invite you to submit any 

relevant written data, views, or 

arguments regarding this AD. Send your 

comments to an address listed under 

ADDRESSES. Include ‘‘Docket No. FAA–

2004–19862; Directorate Identifier 

2004–NM–228–AD’’ at the beginning of 

your comments. We specifically invite 

comments on the overall regulatory, 

economic, environmental, and energy 

aspects of the AD. We will consider all 

comments received by the closing date 

and may amend the AD in light of those 

comments. 

We will post all comments we 

receive, without change, to http://

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 AD. Using the 

search function of our docket 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 can review the DOT’s 

complete Privacy Act Statement in the 

Federal Register published on April 11, 

2000 (65 FR 19477–78), or you can visit 

http://dms.dot.gov.

We are reviewing the writing style we 

currently use in regulatory documents. 

We are interested in your comments on 

whether the style of this document is 

clear, and your suggestions to improve 

the clarity of our communications with 

you. You can get more information 

about plain language at http://www/

faa.gov/language and http://

www.plainlanguage.gov.

75832 Federal Register / Vol. 69, No. 243 / Monday, December 20, 2004 / Rules and Regulations 

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 the 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 AD. See the ADDRESSES section for 

a location to examine the regulatory 

evaluation.

List of Subjects in 14 CFR Part 39 

Air transportation, Aircraft, Aviation 

safety, Incorporation by reference, 

Safety.

Adoption of the Amendment

■ Accordingly, under the authority 

delegated to me by the Administrator, 

the FAA amends 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 FAA amends § 39.13 by adding 

the following new airworthiness 

directive (AD):

2004–25–19 Bombardier, Inc., (Formerly 

Canadair): Amendment 39–13907. 

Docket No. FAA–2004–19862; 

Directorate Identifier 2004–NM–228–AD. 

Effective Date 

(a) This AD becomes effective January 4, 

2005. 

Affected ADs 

(b) None. 

Applicability 

(c) This AD applies to the Bombardier 

airplanes, certificated in any category, that 

are listed in Table 1 of this AD.

TABLE 1.—APPLICABILITY

Bombardier model Having serial numbers 

Which have an angle of 

attack transducer (AOA) 

with the following part 

number 

CL–600–1A11 (CL–600) series airplanes ........................................ 1004 through 1085 inclusive ................................. 600–59154–5 

CL–600–2A12 (CL–601) series airplanes ........................................ 3001 through 3066 inclusive ................................. 600–59154–5 

CL–600–2B16 (CL–601–3A and CL–601–3R) series airplanes ...... 5001 through 5194 inclusive ................................. 600–59154–5 

CL–600–2B16 (CL–604) series airplanes ........................................ 5301 and subsequent ........................................... 600–59154–5 

Unsafe Condition 

(d) This AD was prompted by a report of 

premature wear of the potentiometers in 

AOA transducers having a certain part 

number. The FAA is issuing this AD to 

prevent a delay in the stall computer 

commands for stall warning, stick shaker, 

and stick pusher operation, due to premature 

wear of the potentiometers of the AOA 

transducers, which may cause the airplane to 

enter a stall condition, and result in loss of 

control of the airplane. 

Compliance 

(e) You are responsible for having the 

actions required by this AD performed within 

the compliance times specified, unless the 

actions have already been done. 

Airplane Flight Manual (AFM) Revisions 

(f) Within 7 days after the effective date of 

this AD: Revise the Limitations, Performance, 

and Normal Procedures Sections of the 

applicable Canadair Challenger AFM by 

inserting the applicable Bombardier 

temporary revision (TR), as listed in Table 2 

of this AD. Some TRs listed in Table 2 of this 

AD contain Product Support Publication 

(PSP) identifiers.

TABLE 2.—BOMBARDIER TEMPORARY REVISIONS

Model Temporary

revision PSP Dated 

CL–600–1A11 (CL–600) series airplanes .................. 600/20–2 600 (not stated in document) ......... October 15, 2004. 

600–1/15–2 600–1 (not stated in document) ..... October 15, 2004. 

CL–600–2A12 (CL–601) series airplanes .................. 601/12–2 601–1B–1 ....................................... October 15, 2004. 

601/13–2 601–1A–1 ....................................... October 15, 2004. 

601/17–2 601–1B ........................................... October 15, 2004. 

601/25–2 601–1A–18 (not stated in document).October 15, 2004. 

CL–600–2B16 (CL–601–3A and –3R) series airplanes.601/22–2 601A–1–1 ....................................... October 15, 2004. 

601/23–2 601A–1 ........................................... October 15, 2004. 

CL–600–2B16 (CL–604) series airplanes .................. 604/9–6 604–1 ............................................. October 15, 2004. 

Repetitive Tests 

(g) Prior to the accumulation of 100 total 

flight hours on any AOA transducer, part 

number (P/N) 600–59154–5, since new, or 

within 50 flight hours after the effective date 

of this AD, whichever is later: Perform a 

linearity test of each AOA transducer by 

accomplishing all of the applicable actions 

specified in the Accomplishment 

Instructions of the applicable Bombardier 

alert service bulletin listed in Table 3 of this 

AD. Repeat the linearity test of each AOA 

transducer thereafter at intervals not to 

exceed 100 flight hours. Although the alert 

service bulletins specify to submit certain 

information to the manufacturer, this AD 

does not include such a requirement.

Federal Register / Vol. 69, No. 243 / Monday, December 20, 2004 / Rules and Regulations 75833

TABLE 3.—BOMBARDIER ALERT SERVICE BULLETINS

For model— Bombardier alert 

service bulletin Dated Excluding 

CL–600–1A11 (CL–600) series airplanes ............................. A600–0729 October 14, 2004 .................. Appendix A 

CL–600–2A12 (CL–601) series airplanes and CL–600–

2B16 (CL–601–3A and –3R) series airplanes.

A601–0571 October 14, 2004 .................. Appendix A 

CL–600–2B16 (CL–604) series airplanes ............................. A604–27–026 October 14, 2004 .................. Appendix A 

Corrective Action 

(h) For any AOA transducer, P/N 600–

59154–5, that does not pass any linearity test 

as required by paragraph (g) of this AD: 

Before further flight, replace the affected 

AOA transducer with a serviceable 

transducer by accomplishing the applicable 

actions specified in the Accomplishment 

Instructions of the applicable Bombardier 

alert service bulletin listed in Table 3 of this 

AD. 

Alternative Methods of Compliance 

(AMOCs) 

(i) 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. 

Related Information 

(j) Canadian airworthiness directive CF–

2004–22, dated October 22, 2004, also 

addresses the subject of this AD. 

Material Incorporated by Reference 

(k) You must use the Bombardier alert 

service bulletins and temporary revisions to 

the applicable Canadair Challenger airplane 

flight manuals specified in Table 4 of this 

AD, to perform the actions that are required 

by this AD, unless the AD specifies 

otherwise. The Director of the Federal 

Register approves the incorporation by 

reference of those documents in accordance 

with 5 U.S.C. 552(a) and 1 CFR part 51. For 

copies of the service information, contact 

Bombardier, Inc., Canadair, Aerospace 

Group, P.O. Box 6087, Station Centre-ville, 

Montreal, Quebec H3C 3G9, Canada. You can 

review copies at the Docket Management 

Facility, U.S. Department of Transportation, 

400 Seventh Street SW., Room PL–401, 

Nassif Building, Washington, DC; 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 http://

www.archives.gov/federal_register/

code_of_federal_regulations/

ibr_locations.html.

TABLE 4.—MATERIAL INCORPORATED BY REFERENCE

Bombardier document PSP Document date 

Alert Service Bulletin A600–0729, excluding Appendix A ...................................... None ...................................................... October 14, 2004 

Alert Service Bulletin A601–0571, excluding Appendix A ...................................... None ...................................................... October 14, 2004 

Alert Service Bulletin A604–27–026, excluding Appendix A .................................. None ...................................................... October 14, 2004 

Temporary Revision 600/20–2 ................................................................................ 600 (not stated in document) ................ October 15, 2004 

Temporary Revision 600–1/15–2 ............................................................................ 600–1 (not stated in document) ............ October 15, 2004 

Temporary Revision 601/12–2 ................................................................................ 601–1B–1 .............................................. October 15, 2004 

Temporary Revision 601/13–2 ................................................................................ 601–1A–1 .............................................. October 15, 2004 

Temporary Revision 601/17–2 ................................................................................ 601–1B .................................................. October 15, 2004 

Temporary Revision 601/22–2 ................................................................................ 601A–1–1 .............................................. October 15, 2004 

Temporary Revision 601/23–2 ................................................................................ 601A–1 .................................................. October 15, 2004 

Temporary Revision 601/25–2 ................................................................................ 601–1A–18 (not stated in document) .... October 15, 2004 

Temporary Revision 604/9–6 .................................................................................. 604–1 ..................................................... October 15, 2004 

Issued in Renton, Washington, on 

December 6, 2004. 

Ali Bahrami, 

Manager, Transport Airplane Directorate, 

Aircraft Certification Service.

[FR Doc. 04–27507 Filed 12–17–04; 8:45 am] 

BILLING CODE 4910–13–P

DEPARTMENT OF TRANSPORTATION

Federal Aviation Administration 

14 CFR Part 39 

[Docket No. FAA–2004–19896; Directorate 

Identifier 2004–CE–44–AD; Amendment 39–

13913; AD 2004–25–51] 

RIN 2120–AA64 

Airworthiness Directives; Raytheon 

Aircraft Company Beech Models 45 

(YT–34), A45 (T–34A, B–45), and D45 

(T–34B) Airplanes

AGENCY: Federal Aviation 

Administration (FAA), DOT.

ACTION: Final rule; request for 

comments. 

SUMMARY: The FAA is adopting a new 

airworthiness directive (AD) for all 

Raytheon Aircraft Company (Raytheon) 

Beech Models 45 (YT–34), A45 (T–34A, 

B–45), and D45 (T–34B) airplanes. This 

AD requires you to perform an 

inspection and/or modification program 

approved specifically for this AD by the 

FAA Wichita Aircraft Certification 

Office (ACO). This AD is the result of a 

total of three accidents on the affected 

airplanes, including a recent accident 

where the wing separated from the 

airplane in flight. We are issuing this 

AD to detect and correct cracking in the 

wing structure of the affected airplanes, 

which could result in the wing 

separating from the airplane with 

consequent loss of control of the 

airplane.

DATES: This AD becomes effective on 

December 21, 2004, to all affected 

persons who did not receive emergency 

AD 2004–25–51, issued December 10, 

2004. Emergency AD 2004–25–51 

contained the requirements of this 

amendment and became effective 

immediately upon receipt.