64856 Federal Register / Vol. 69, No. 216 / Tuesday, November 9, 2004 / Rules and Regulations 

TABLE 2.—MATERIAL INCORPORATED BY REFERENCE

Service bulletin Revision 

level Date 

Airbus Service Bulletin A300–29–6048 ............................................................................................................... 01 July 12, 2000. 

Airbus Service Bulletin A300–29–6050, excluding Appendix 01 ........................................................................ 02 April 16, 2003. 

Airbus Service Bulletin A310–29–2086 ............................................................................................................... 01 July 12, 2000. 

Airbus Service Bulletin A310–29–2088, excluding Appendix 01 ........................................................................ 01 February 3, 2003. 

(1) The Director of the Federal Register 

approved the incorporation by reference of 

Airbus Service Bulletin A300–29–6050, 

Revision 02, excluding Appendix 01, dated 

April 16, 2003; and Airbus Service Bulletin 

A310–29–2088, Revision 01, excluding 

Appendix 01, dated February 3, 2003; in 

accordance with 5 U.S.C. 552(a) and 1 CFR 

part 51. 

(2) The incorporation by reference of 

Airbus Service Bulletin A300–29–6048, 

Revision 01, dated July 12, 2000; and Airbus 

Service Bulletin A310–29–2086, Revision 01, 

dated July 12, 2000, was approved previously 

by the Director of the Federal Register as of 

August 6, 2001 (66 FR 34798, July 2, 2001). 

(3) For copies of the service information, 

contact Airbus, 1 Rond Point Maurice 

Bellonte, 31707 Blagnac Cedex, France. For 

information on the availability of this 

material at the National Archives and 

Records Administration (NARA), call (202) 

741–6030, or go to http://www.archives.gov/

federal_register/code_of_federal_regulations/

ibr_locations.html. You may view the AD 

docket at the Docket Management Facility, 

U.S. Department of Transportation, 400 

Seventh Street, SW., room PL–401, Nassif 

Building, Washington, DC.

Issued in Renton, Washington, on October 

20, 2004. 

Kalene C. Yanamura, 

Acting Manager, Transport Airplane 

Directorate, Aircraft Certification Service.

[FR Doc. 04–24628 Filed 11–8–04; 8:45 am] 

BILLING CODE 4910–13–P

DEPARTMENT OF TRANSPORTATION

Federal Aviation Administration 

14 CFR Part 39

[Docket No. 2003–NM–11–AD; Amendment 

39–13851; AD 2004–22–23] 

RIN 2120–AA64

Airworthiness Directives; Bombardier 

Model CL–600–2B19 (Regional Jet 

Series 100 & 440) Airplanes

AGENCY: Federal Aviation 

Administration, DOT.

ACTION: Final rule.

SUMMARY: This amendment adopts a 

new airworthiness directive (AD), 

applicable to certain Bombardier Model 

CL–600–2B19 (Regional Jet Series 100 & 

440) airplanes, that requires a one-time 

inspection of the shafts of the main 

landing gear (MLG) side-brace fittings to 

detect corrosion, and the forward and 

aft bushings in the left-hand and righthand MLG side-brace fittings to detect 

discrepancies. This AD also requires 

corrective and related actions if 

necessary. This action is necessary to 

prevent fractures of the MLG side-brace 

fitting shafts, and possible collapse of 

the MLG. This action is intended to 

address the identified unsafe condition.

DATES: Effective December 14, 2004. 

The incorporation by reference of a 

certain publication listed in the 

regulations is approved by the Director 

of the Federal Register as of December 

14, 2004.

ADDRESSES: The service information 

referenced in this AD may be obtained 

from Bombardier, Inc., Canadair, 

Aerospace Group, PO Box 6087, Station 

Centre-ville, Montreal, Quebec H3C 

3G9, Canada. This information may be 

examined at the Federal Aviation 

Administration (FAA), Transport 

Airplane Directorate, Rules Docket, 

1601 Lind Avenue, SW., Renton, 

Washington; or at the FAA, New York 

Aircraft Certification Office, 1600 

Stewart Avenue, suite 410, Westbury, 

New York; 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.

FOR FURTHER INFORMATION CONTACT:

Serge Napoleon, Aerospace Engineer, 

Airframe and Propulsion Branch, ANE–

171, FAA, New York Aircraft 

Certification Office, 1600 Stewart 

Avenue, suite 410, Westbury, New York 

11590; telephone (516) 228–7312; fax 

(516) 794–5531.

SUPPLEMENTARY INFORMATION: A 

proposal to amend part 39 of the Federal 

Aviation Regulations (14 CFR part 39) to 

include an airworthiness directive (AD) 

that is applicable to certain Bombardier 

Model CL–600–2B19 (Regional Jet 

Series 100 & 440) airplanes was 

published in the Federal Register on 

June 14, 2004 (69 FR 32924). That action 

proposed to require a one-time 

inspection of the shafts of the main 

landing gear (MLG) side-brace fittings to 

detect corrosion, and the forward and 

aft bushings in the left-hand and righthand MLG side-brace fittings to detect 

discrepancies. That action also 

proposed to require corrective and 

related actions if necessary. 

Comments 

Interested persons have been afforded 

an opportunity to participate in the 

making of this amendment. Due 

consideration has been given to the 

comments received. 

Request for Credit for Actions Done per 

the Original Issue of the Service 

Bulletin 

One commenter requests that actions 

done per the original issue of 

Bombardier Service Bulletin 601R–57–

036 be considered acceptable for 

compliance with the corresponding 

actions in the proposed AD. The 

commenter notes that Revisions A and 

B of the service bulletin are mentioned 

in paragraph (c) of the proposed AD as 

being acceptable for compliance with 

the corresponding actions but the 

paragraph does not state that actions 

done per the original issue are 

considered acceptable for compliance 

with the corresponding actions. 

The FAA agrees that actions done per 

the original issue of the service bulletin 

are considered acceptable for 

compliance with the corresponding 

actions of the final rule. Revision C of 

the service bulletin, cited as the 

appropriate source of service 

information for the final rule, specifies 

that no additional action is needed for 

airplanes on which actions were done 

per previous issues of the service 

bulletin. We have revised paragraph (c) 

of the final rule accordingly. 

Request To Remove Reference to 

Functional Test 

The same commenter requests that 

references to the functional test in the 

proposed AD need not be specified. The 

commenter states that the ‘‘Explanation 

of Requirements of Proposed AD’’

paragraph of the proposed AD specifies 

that the Canadian airworthiness 

directive CF–2002–41, dated September 

20, 2002, does not include the 

Federal Register / Vol. 69, No. 216 / Tuesday, November 9, 2004 / Rules and Regulations 64857

requirement for a functional test of the 

MLG system, and that the functional test 

is included in Revision C of the service 

bulletin. The commenter contends that 

someone may then believe that the 

functional test is not a part of the 

original issue, Revision A, or Revision B 

of the service bulletin. The commenter 

notes that the functional test is included 

in the work instructions of all issues of 

the service bulletin. 

We partially agree with the 

commenter’s request. We acknowledge 

that the functional test is included in all 

revisions of the service bulletin. We 

referenced only Revision C of the 

service bulletin in the preamble of the 

proposed AD because it is cited as the 

appropriate source of service 

information. Our intent was to explain 

a ‘‘difference’’ between the Canadian 

airworthiness directive and the 

proposed AD in that the Canadian 

airworthiness directive does not 

specifically call out the functional test. 

We confirmed with Transport Canada 

Civil Aviation (TCCA), which is the 

airworthiness authority for Canada, that 

operators are expected to do the 

functional test and that this AD will call 

attention to accomplishing the 

functional test. We do not find that any 

further clarification is needed. Since the 

references to the functional test are in 

certain parts of the preamble of the 

proposed AD that are not restated in the 

final rule, we have made no change to 

the final rule regarding this issue. 

Conclusion 

After careful review of the available 

data, including the comments noted 

above, we have determined that air 

safety and the public interest require the 

adoption of the rule with the changes 

described previously. We have 

determined that these changes will 

neither increase the economic burden 

on any operator nor increase the scope 

of the AD. 

Interim Action 

This AD is considered to be interim 

action. The inspection reports that are 

required by this AD will enable the 

manufacturer to obtain better insight 

into the nature, cause, and extent of the 

corrosion of the shafts of the MLG sidebrace fittings, and eventually to develop 

final action to address the unsafe 

condition. Once final action has been 

identified, we may consider further 

rulemaking. 

Cost Impact 

We estimate that 462 airplanes of U.S. 

registry will be affected by this AD, that 

it will take approximately 5 work hours 

per airplane to accomplish the required 

inspections and functional test, and that 

the average labor rate is $65 per work 

hour. Based on these figures, the cost 

impact of the actions required by this 

AD on U.S. operators is estimated to be 

$150,150, or $325 per airplane. 

The cost impact figure discussed 

above is based on assumptions that no 

operator has yet accomplished any of 

the requirements of this AD action, and 

that no operator would accomplish 

those actions in the future if this AD 

were not adopted. The cost impact 

figures discussed in AD rulemaking 

actions represent only the time 

necessary to perform the specific actions 

actually required by the AD. These 

figures typically do not include 

incidental costs, such as the time 

required to gain access and close up, 

planning time, or time necessitated by 

other administrative actions. 

Regulatory Impact 

The regulations adopted herein 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. Therefore, it is 

determined that this final rule does not 

have federalism implications under 

Executive Order 13132. 

For the reasons discussed above, I 

certify that this action (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. A final evaluation has 

been prepared for this action and it is 

contained in the Rules Docket. A copy 

of it may be obtained from the Rules 

Docket at the location provided under 

the caption ADDRESSES.

List of Subjects in 14 CFR Part 39

Air transportation, Aircraft, Aviation 

safety, Incorporation by reference, 

Safety.

Adoption of the Amendment

■ Accordingly, pursuant to the authority 

delegated to me by the Administrator, 

the Federal Aviation Administration 

amends part 39 of the Federal Aviation 

Regulations (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. Section 39.13 is amended by adding 

the following new airworthiness 

directive:

2004–22–23 Bombardier, Inc. (Formerly 

Canadair): Amendment 39–13851. 

Docket 2003–NM–11–AD.

Applicability: Model CL–600–2B19 

(Regional Jet Series 100 & 440) airplanes, 

serial numbers 7003 through 7651 inclusive; 

certificated in any category. 

Compliance: Required as indicated, unless 

accomplished previously. 

To prevent fractures of the main landing 

gear (MLG) side-brace fitting shafts, and 

possible collapse of the MLG, accomplish the 

following: 

Inspections, Corrective Actions, and Related 

Actions 

(a) Within 20 months or 4,000 flight cycles 

after the effective date of this AD, whichever 

occurs first: Do a general visual inspection of 

the shafts of the side-brace fittings of the 

MLG for corrosion, and of the forward and 

aft bushings in the left-hand and right-hand 

MLG side-brace fittings for discrepancies 

(gouges, scores, corrosion, or other damage); 

and any applicable corrective and related 

actions. Do all of the actions in accordance 

with the Accomplishment Instructions of 

Bombardier Service Bulletin 601R–57–036, 

Revision ‘‘C’’, including Appendix A, dated 

January 30, 2003. Do any applicable 

corrective and related actions before further 

flight. Where the service bulletin specifies to 

contact the manufacturer for certain 

replacement instructions: Before further 

flight, replace per a method approved by 

either the Manager, New York Aircraft 

Certification Office (ACO), FAA; or Transport 

Canada Civil Aviation (TCCA) (or its 

delegated agent).

Note 1: For the purposes of this AD, a 

general visual inspection is defined as: ‘‘A 

visual examination of an interior or exterior 

area, installation, or assembly to detect 

obvious damage, failure, or irregularity. This 

level of inspection is made from within 

touching distance unless otherwise specified. 

A mirror may be necessary to enhance visual 

access to all exposed surfaces in the 

inspection area. This level of inspection is 

made under normally available lighting 

conditions such as daylight, hangar lighting, 

flashlight, or droplight and may require 

removal or opening of access panels or doors. 

Stands, ladders, or platforms may be required 

to gain proximity to the area being checked.’’

Reporting 

(b) Submit a report of any corrosion of the 

shafts of the side-brace fittings of the MLG 

found during the inspections required by 

paragraph (a) of this AD to the Bombardier 

Technical Help Desk at fax number (514) 

833–8501. Submit the report at the applicable 

time specified in paragraph (b)(1) or (b)(2) of 

this AD. Submission of the Field-Report Data 

Sheet in Appendix A of the service bulletin 

is an acceptable method for complying with 

this requirement. Include the inspection 

results (including the percentage of the 

64858 Federal Register / Vol. 69, No. 216 / Tuesday, November 9, 2004 / Rules and Regulations 

corrosion), a digital photo of the shafts (if 

available), the location (zone) in which the 

corrosion is found, the serial number of the 

airplane, the name of the inspector, the 

service bulletin number, and the date of the 

inspection. Under the provisions of the 

Paperwork Reduction Act of 1980 (44 U.S.C. 

3501 et seq.), the Office of Management and 

Budget (OMB) has approved the information 

collection requirements contained in this AD 

and has assigned OMB Control Number 

2120–0056. 

(1) If the inspections are done after the 

effective date of this AD: Submit the report 

within 30 days after the inspection. 

(2) If the inspections were done before the 

effective date of this AD: Submit the report 

within 30 days after the effective date of this 

AD. 

Actions Accomplished per Previous Issue of 

Service Bulletin 

(c) Actions accomplished before the 

effective date of this AD in accordance with 

Bombardier Service Bulletin 601R–57–036, 

including Appendix A, dated April 30, 2002; 

Revision ‘‘A’’, including Appendix A, dated 

May 17, 2002; or Revision ‘‘B’’, including 

Appendix A, dated July 4, 2002; are 

considered acceptable for compliance with 

the corresponding actions specified in this 

AD. 

Alternative Methods of Compliance 

(d) In accordance with 14 CFR 39.19, the 

Manager, New York ACO, is authorized to 

approve alternative methods of compliance 

for this AD. 

Incorporation by Reference 

(e) Unless otherwise specified in this AD, 

the actions shall be done in accordance with 

Bombardier Service Bulletin 601R–57–036, 

Revision ‘‘C’’, including Appendix A, dated 

January 30, 2003. This incorporation by 

reference was approved by the Director of the 

Federal Register in accordance with 5 U.S.C. 

552(a) and 1 CFR part 51. Copies may be 

obtained from Bombardier, Inc., Canadair, 

Aerospace Group, P.O. Box 6087, Station 

Centre-ville, Montreal, Quebec H3C 3G9, 

Canada. Copies may be inspected at the FAA, 

Transport Airplane Directorate, 1601 Lind 

Avenue, SW., Renton, Washington; or at the 

FAA, New York Aircraft Certification Office, 

1600 Stewart Avenue, suite 410, Westbury, 

New York; 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.

Note 2: The subject of this AD is addressed 

in Canadian airworthiness directive CF–

2002–41, dated September 20, 2002.

Effective Date 

(f) This amendment becomes effective on 

December 14, 2004.

Issued in Renton, Washington, on October 

20, 2004. 

Kalene C. Yanamura, 

Acting Manager, Transport Airplane 

Directorate, Aircraft Certification Service.

[FR Doc. 04–24629 Filed 11–8–04; 8:45 am] 

BILLING CODE 4910–13–P

DEPARTMENT OF TRANSPORTATION

Federal Aviation Administration 

14 CFR Part 39

[Docket No. 2004–CE–11–AD; Amendment 

39–13856; AD 2004–22–28] 

RIN 2120–AA64

Airworthiness Directives; Raytheon 

Aircraft Company Model B100 

Airplanes

AGENCY: Federal Aviation 

Administration (FAA), DOT.

ACTION: Final rule.

SUMMARY: The FAA adopts a new 

airworthiness directive (AD) for certain 

Raytheon Aircraft Company (Raytheon) 

Model B100 airplanes. This AD requires 

you to drill holes in the hot lip tube ‘‘B’’

nuts, tighten the ‘‘B’’ nuts to specified 

torque ranges, and secure the ‘‘B’’ nuts 

with safety wire. This AD is the result 

of reports of loose ‘‘B’’ nuts on the 

engine inlet that may loosen and permit 

a leak in the engine inlet anti-ice 

system. We are issuing this AD to detect 

and correct loose ‘‘B’’ nuts on the engine 

inlet, which could result in failure of 

the engine inlet anti-ice system and 

consequent ice buildup. This failure and 

ice buildup could lead to an engine’s 

ingestion of ice with loss of engine 

power or loss of engine.

DATES: This AD becomes effective on 

December 27, 2004. 

As of December 27, 2004, the Director 

of the Federal Register approved the 

incorporation by reference of certain 

publications listed in the regulation.

ADDRESSES: You may get the service 

information identified in this AD from 

Raytheon Aircraft Company, 9709 E. 

Central, Wichita, Kansas 67201–0085; 

telephone: (800) 429–5372 or (316) 676–

3140. 

You may view the AD docket at FAA, 

Central Region, Office of the Regional 

Counsel, Attention: Rules Docket No. 

2004–CE–11–AD, 901 Locust, Room 

506, Kansas City, Missouri 64106. Office 

hours are 8 a.m. to 4 p.m., Monday 

through Friday, except Federal holidays.

FOR FURTHER INFORMATION CONTACT: Jeff 

Pretz, Aerospace Engineer, Wichita 

Aircraft Certification Office, FAA, 1801 

Airport Road, Wichita, Kansas 67209; 

telephone: (316) 946–4153; facsimile: 

(316) 946–4407.

SUPPLEMENTARY INFORMATION:

Discussion 

What events have caused this AD?

The FAA has received six reports of 

loose ‘‘B’’ nuts on the Raytheon Model 

B100 engine inlet anti-ice system found 

during routine maintenance. These 

loose ‘‘B’’ nuts may permit a leak in the 

engine inlet anti-ice system that would 

result in failure of the system with 

consequent ice buildup on the engine 

inlet. 

What is the potential impact if FAA 

took no action? Failure of the engine 

inlet anti-ice system and consequent ice 

buildup could lead to an engine’s 

ingestion of ice with loss of engine 

power or loss of engine. 

Has FAA taken any action to this 

point? We issued a proposal to amend 

part 39 of the Federal Aviation 

Regulations (14 CFR part 39) to include 

an AD that would apply to certain 

Raytheon Model B100 airplanes. This 

proposal was published in the Federal 

Register as a notice of proposed 

rulemaking (NPRM) on May 26, 2004 

(69 FR 29910). The NPRM proposed to 

require you to drill holes in the hot lip 

tube ‘‘B’’ nuts, tighten the ‘‘B’’ nuts to 

specified torque ranges, and secure the 

‘‘B’’ nuts with safety wire. 

Comments 

Was the public invited to comment?

We provided the public the opportunity 

to participate in developing this AD. We 

received no comments on the proposal 

or on the determination of the cost to 

the public. 

Conclusion 

What is FAA’s final determination on 

this issue? We have carefully reviewed 

the available data and determined that 

air safety and the public interest require 

adopting the AD as proposed except for 

minor editorial corrections. We have 

determined that these minor 

corrections: 

—Are consistent with the intent that 

was proposed in the NPRM for 

correcting the unsafe condition; and 

—Do not add any additional burden 

upon the public than was already 

proposed in the NPRM. 

Changes to 14 CFR Part 39—Effect on 

the AD 

How does the revision to 14 CFR part 

39 affect this AD? On July 10, 2002, the 

FAA published a new version of 14 CFR 

part 39 (67 FR 47997, July 22, 2002), 

which governs the FAA’s AD system. 

This regulation now includes material 

that relates to altered products, special