Federal Register / Vol. 69, No. 245 / Wednesday, December 22, 2004 / Rules and Regulations 76605

Actions Compliance Procedures 

(i) Contact the manufacturer for replacement parts at mailing address Eagle Aircraft, P.O. Box 1028, Pejabat Pos Besar, 

Melaka, Malaysia 75150; telephone: 

(606) 317–4105, facsimile: (606) 317–

7213; 

(ii) Install the replacement parts. Before further flight after the inspection required by paragraph (e)(1) of this AD. Follow Eagle Aircraft Alert Service Bulletin SB 

1123, dated August 8, 2004. 

May I Request an Alternative Method of 

Compliance? 

(f) You may request a different method of 

compliance or a different compliance time 

for this AD by following the procedures in 14 

CFR 39.19. Unless FAA authorizes otherwise, 

send your request to your principal 

inspector. The principal inspector may add 

comments and will send your request to the 

Manager, Standards Office, Small Airplane 

Directorate, FAA. For information on any 

already approved alternative methods of 

compliance, contact Karl Schletzbaum, 

Aerospace Engineer, Small Airplane 

Directorate, ACE–112, 901 Locust, Rm 301, 

Kansas City, Missouri 64106; telephone: 

(816) 329–4146; facsimile: (816) 329–4149. 

Is There Other Information That Relates to 

This Subject? 

(g) DCA CAM AD 001–08–2004, dated 

August 12, 2004, also addresses the subject 

of this AD. 

Does This AD Incorporate Any Material by 

Reference? 

(h) You must do the actions required by 

this AD following the instructions in Eagle 

Aircraft Alert Service Bulletin SB 1123, dated 

August 8, 2004. The Director of the Federal 

Register approved the incorporation by 

reference of this service bulletin in 

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

part 51. To get a copy of this service 

information, contact Eagle Aircraft, P.O. Box 

1028, Pejabat Pos Besar, Melaka, Malaysia, 

75150; telephone: 011 606 317 4105; 

facsimile: 011 606 317 7213. To review 

copies of this service information, go to the 

National Archives and Records 

Administration (NARA). For information on 

the availability of this material at NARA, go 

to: http://www.archives.gov/federal_register/

code_of_federal_regulations/

ibr_locations.html or call (202) 741–6030. To 

view the AD docket, go to the Docket 

Management Facility; U.S. Department of 

Transportation, 400 Seventh Street, SW., 

Nassif Building, Room PL–401, Washington, 

DC 20590–001 or on the Internet at http://

dms.dot.gov. The docket number is FAA–

2004–19222.

Issued in Kansas City, Missouri, on 

December 13, 2004. 

James E. Jackson, 

Acting Manager, Small Airplane Directorate, 

Aircraft Certification Service.

[FR Doc. 04–27814 Filed 12–21–04; 8:45 am] 

BILLING CODE 4910–13–P

DEPARTMENT OF TRANSPORTATION

Federal Aviation Administration 

14 CFR Part 39

[Docket No. 2003–NM–97–AD; Amendment 

39–13909; AD 2004–25–21] 

RIN 2120–AA64

Airworthiness Directives; Empresa 

Brasileira de Aeronautica S.A. 

(EMBRAER) Model EMB–135 and –145 

Series Airplanes

AGENCY: Federal Aviation 

Administration, DOT.

ACTION: Final rule.

SUMMARY: This amendment adopts a 

new airworthiness directive (AD), 

applicable to certain Model EMB–135 

and –145 series airplanes. This AD 

requires modification of the pitch trim 

system, which includes replacing 

certain components of the system with 

new or serviceable components, and 

upgrading certain software to a newer 

version. This action is necessary to 

prevent the temporary loss of the pitch 

trim command, which could result in 

reduced controllability of the airplane 

and consequent injury to the flightcrew 

and passengers. This action is intended 

to address the identified unsafe 

condition.

DATES: Effective January 26, 2005. 

The incorporation by reference of 

certain publications listed in the 

regulations is approved by the Director 

of the Federal Register as of January 26, 

2005.

ADDRESSES: The service information 

referenced in this AD may be obtained 

from Empresa Brasileira de Aeronautica 

S.A. (EMBRAER), PO Box 343—CEP 

12.225, Sao Jose dos Campos—SP, 

Brazil. 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 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:

Todd Thompson, Aerospace Engineer, 

International Branch, ANM–116, FAA, 

Transport Airplane Directorate, 1601 

Lind Avenue, SW., Renton, Washington 

98055–4056; telephone (425) 227–1175; 

fax (425) 227–1149.

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 Model 

EMB–135 and –145 series airplanes was 

published in the Federal Register on 

February 6, 2004 (69 FR 5759). That 

action proposed to require modification 

of the pitch trim system, which includes 

replacing certain components of the 

system with new or serviceable 

components, and upgrading certain 

software to a newer version. 

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 To Include New Revision of 

Service Bulletin 145–31–0042

One commenter requests that we use 

EMBRAER Service Bulletin 145–31–

0042, Revision 01, dated January 7, 

2004, as the appropriate source of 

service information for replacing certain 

integrated computers (IC) in paragraph 

(b)(4) of the proposed AD. The 

commenter states that the ICs in this 

service bulletin are upgrades, and 

classified as optional replacements for 

the IC–600 computers referenced in 

EMBRAER Service Bulletin 145–31–

0033, Revision 03, dated August 25, 

2003, which is the appropriate source of 

service information for replacing certain 

IC–600 computers per paragraph (b)(4) 

of the proposed AD. 

We partially agree with the 

commenter’s request. We agree that 

EMBRAER Service Bulletin 145–31–

0042, Revision 01, may be used as an 

optional source of service information 

for doing the actions in paragraph (b)(4) 

76606 Federal Register / Vol. 69, No. 245 / Wednesday, December 22, 2004 / Rules and Regulations 

of the AD. Additionally, the 

manufacturer has also issued Revision 

02, dated June 23, 2004, and it may also 

be used as an optional source of service 

information. Since these revisions are 

not the only source of appropriate 

service information, operators may still 

choose to do the replacement in 

accordance with the service information 

in the proposed AD. Therefore, we have 

revised paragraph (b)(4) of this final rule 

to include EMBRAER Service Bulletin 

145–31–0042, Revision 01 and Revision 

02, as sources of service information for 

operators of airplanes listed in that 

service bulletin to choose as an optional 

way to replace the IC–600 computers as 

proposed in paragraph (b)(4). This 

optional replacement includes 

reidentifying IC–600 #1 and IC–600 #2, 

and loading a new configuration file to 

the IC–600 #1 and IC–600 #2 

configuration modules. 

EMBRAER Service Bulletin 145–31–

0042 references Honeywell Service 

Bulletin 7017000–22–6102, dated 

November 25, 2003, as an additional 

source of service information for 

accomplishing the upgrade and reidentification. EMBRAER Service 

Bulletin 145–31–0042 also contains 

other procedures that are not applicable 

to the IC–600 upgrade, but these actions 

are not required by this final rule. 

EMBRAER Service Bulletin 145–31–

0042 specifies that the following service 

bulletins must be accomplished 

previously, as applicable, on the 

airplanes listed in these service 

bulletins: 

• EMBRAER Service Bulletin 145–

31–0020, Change 03, dated July 30, 

2002, which contains procedures for 

replacing the IC–600 #1 and IC–600 #2, 

and the data acquisition unit (DAU); 

and for upgrading the engine indicating 

and crew alerting system (EICAS) to 

version 17.

• EMBRAER Service Bulletin 145–

25–0210, dated March 30, 2001, which 

describes procedures for removing and/

or replacing certain placards in the 

cockpit. These placards are related to 

the EICAS. 

• EMBRAER Service Bulletin 145–

45–0003, dated July 5, 2000, which 

describes procedures for modifying and 

re-identifying the central maintenance 

computer (CMC). This service bulletin 

refers to Vibro-Meter Service Bulletin 

145–45–0503, dated March 20, 2000, as 

an additional source of service 

information for modifying and reidentifying the CMC. The Vibro-Meter 

service bulletin is included with 

EMBRAER Service Bulletin 145–45–

0003. 

Request To Include New Revision of 

Service Bulletin 145LEG–27–0002

Another commenter requests that we 

refer to EMBRAER Service Bulletin 

145LEG–27–0002, Revision 01, dated 

April 15, 2003, as the appropriate 

source of service information for 

accomplishing the actions in paragraphs 

(b)(1) and (b)(7) of the proposed AD on 

Model EMB–135BJ series airplanes. The 

commenter advises that this is the latest 

revision of the service bulletin with the 

most current information. 

We agree with the commenter. The 

new revision of the service bulletin 

identifies two new and improved 

horizontal stabilizer control units 

(HSCU), and reduces the number of 

airplanes to which this service bulletin 

applies. We have revised the 

applicability section, paragraphs (b)(1) 

and (b)(7), and Table 1 of the final rule 

to include references to EMBRAER 

Service Bulletin 145LEG–27–0002, 

Revision 01. We have also revised Table 

2 of the final rule to include a reference 

to the original issue of EMBRAER 

Service Bulletin 145LEG–27–0002, 

dated February 5, 2003. EMBRAER 

Service Bulletin 145LEG–27–0002 is 

applicable to Model EMB–135BJ series 

airplanes, and describes procedures for 

replacing the HSCU with a new unit 

having improved features. This service 

bulletin also describes procedures for 

connecting the HSCU and the DAU 

(including the replacement of the pitch 

trim system circuit breakers with new 

circuit breakers sized for the new 

system load capacity, as applicable). 

Request To Extend Compliance Time 

One commenter, an airplane operator, 

requests that the compliance time for 

accomplishing the seven actions in 

paragraph (b) of the proposed AD be 

extended to better accommodate the 

commenter’s existing maintenance 

program. The compliance time, as 

proposed, is: ‘‘Within 18 months or 

5,000 flight hours after the effective date 

of this AD, whichever occurs first.’’ The 

commenter requests that the statement 

be revised to say, ‘‘Within 18 months or 

5,000 flight hours after the effective date 

of this AD, whichever occurs later,’’ or, 

‘‘Within 36 months or 5,000 flight hours 

after the effective date of this AD, 

whichever occurs first.’’ The commenter 

states that 5,000 flight hours work better 

with its existing maintenance program, 

and that 36 months is approximately 

equivalent to 5,000 flight hours for its 

operation. The commenter requests the 

extension in order to comply with the 

requirements of the proposed AD in a 

smooth and effective manner, and to 

reduce the time and effort to the 

commenter and the FAA in requesting 

and addressing alternative methods of 

compliance (AMOCs). 

We do not agree with the commenter’s 

request to extend the compliance time. 

The commenter provides no technical 

justification that extending the 

compliance time will still maintain an 

appropriate level of safety. In 

developing an appropriate compliance 

time for this proposed AD, we 

considered safety issues as well as the 

recommendations of the manufacturer 

and the Departmento de Aviacao Civil, 

(which is the airworthiness authority for 

Brazil), the availability of necessary 

parts, and the practical aspects of 

accomplishing the required actions 

within an interval of time that 

corresponds to the normal maintenance 

schedules of most affected operators. 

We do not find it necessary to change 

this proposal in this regard; however, 

the commenter still may apply for 

approval of an AMOC to extend the 

compliance time. 

Request To Shorten Compliance Time 

Another commenter supports the 

proposal and requests that the 

compliance time for accomplishing the 

proposed actions be shortened 

substantially. The commenter states that 

the unsafe condition is severe enough to 

warrant a more immediate compliance 

time. In addition, the commenter 

understands that the parts necessary to 

complete the modification are readily 

available and, therefore, the parts 

should be available to accomplish the 

proposed actions more quickly. 

We do not agree that the unsafe 

condition is severe enough to justify 

shortening the compliance time 

substantially. The proposed compliance 

time was determined to be appropriate 

in consideration of the safety 

implications, the average utilization rate 

of the affected fleet, the practical aspects 

of modifications during regular 

maintenance periods, and the 

availability of required modification 

parts. We do agree with the commenter 

that parts are available to accomplish 

the actions in the allotted time in the 

original NPRM. We have not revised the 

proposal to shorten the compliance 

time. 

Request To Remove ‘‘Interim Action’’

Another commenter, the airplane 

manufacturer, requests that we remove 

the section of the NPRM that describes 

this proposal as ‘‘interim action.’’ The 

commenter states that the corrective 

action in the proposal completely 

addresses the specific unsafe conditions 

identified during the development of 

the Brazilian airworthiness directive 

Federal Register / Vol. 69, No. 245 / Wednesday, December 22, 2004 / Rules and Regulations 76607

and the FAA NPRM. In addition, the 

commenter states that recent pitch trim 

failures induced by airspeed 

miscompares will be addressed by a 

new HSCU that is under development. 

Therefore, the commenter believes that 

it is not appropriate to label this 

proposal as ‘‘interim action.’’

We agree that the NPRM was issued 

to correct the stated known unsafe 

condition. In stating that the proposal is 

‘‘interim action,’’ we are advising the 

public that rulemaking on this subject 

may be issued in the future. This 

additional rulemaking could include a 

new HSCU that is under development. 

We have not changed the proposal to 

remove the reference to ‘‘interim 

action.’’

Conclusion 

After careful review of the available 

data, including the comments noted 

above, the FAA has determined that air 

safety and the public interest require the 

adoption of the rule with the changes 

described previously. The FAA has 

determined that these changes will 

neither increase the economic burden 

on any operator nor increase the scope 

of the AD. 

Cost Impact 

There are approximately 365 

airplanes of U.S. registry affected by this 

AD. 

For all affected airplanes, we estimate 

that it will take approximately 1 work 

hour per airplane to replace the HSCU, 

and that the average labor rate is $65 per 

work hour. The manufacturer will 

provide replacement parts at no cost. 

Based on these figures, the cost impact 

of this replacement on U.S. operators is 

estimated to be $23,725, or $65 per 

airplane. 

For airplanes subject to EMBRAER 

Service Bulletin 145–27–0091, we 

estimate that it will take approximately 

6 work hours per airplane to replace the 

horizontal stabilizer actuator, and that 

the average labor rate is $65 per work 

hour. The manufacturer will provide 

replacement parts at no cost. Based on 

these figures, the cost impact of this 

replacement is estimated to be $390 per 

airplane. 

For airplanes subject to EMBRAER 

Service Bulletin 145–31–0028, we 

estimate that it will take approximately 

2 work hours per airplane to replace the 

aural warning unit, and that the average 

labor rate is $65 per work hour. 

Required parts will cost approximately 

$1,100 per airplane. Based on these 

figures, the cost impact of this 

replacement is estimated to be $1,230 

per airplane.

For airplanes subject to EMBRAER 

Service Bulletin 145LEG–31–0001 or 

145–31–0033; or on which the optional 

action in EMBRAER Service Bulletin 

145–31–0042 is done, we estimate that 

it will take between 1 and 6 work hours 

per airplane to install the new EICAS/

electronic flight information system, 

and that the average labor rate is $65 per 

work hour. Required parts will cost 

between $10 and $25 per airplane. 

Based on these figures, the cost impact 

of this action is estimated to be between 

$75 and $415 per airplane. 

For airplanes subject to EMBRAER 

Service Bulletin 145LEG–27–0004 or 

145–27–0096, we estimate that it will 

take between 4 and 5 work hours per 

airplane to replace the yoke pitch trim 

switch, and that the average labor rate 

is $65 per work hour. Required parts 

will cost between $1,042 and $1,056 per 

airplane. Based on these figures, the cost 

impact of this action is estimated to be 

between $1,302 and $1,381 per airplane. 

For airplanes subject to EMBRAER 

Service Bulletin 145–27–0073, we 

estimate that it will take approximately 

3 work hours per airplane to replace the 

pitch trim back-up control switch, and 

that the average labor rate is $65 per 

work hour. Required parts will cost 

approximately $371 per airplane. Based 

on these figures, the cost impact of this 

replacement is estimated to be $566 per 

airplane. 

For airplanes subject to the 

requirements in EMBRAER Service 

Bulletin 145–27–0083, we estimate that 

it will take approximately 38 hours to 

accomplish the modifications, and that 

the average labor rate is $65 per work 

hour. Required parts will cost 

approximately $448. Based on these 

figures, the cost impact of these 

modifications is estimated to be $2,918 

per airplane. 

For airplanes subject to the 

requirements in EMBRAER Service 

Bulletin 145–31–0020, we estimate that 

it will take between 9 and 56 hours to 

accomplish the proposed upgrade, and 

that the average labor rate is $65 per 

work hour. Required parts will cost 

between $3 and $5,100. Based on these 

figures, the cost impact of this action is 

estimated to be approximately between 

$588 and $8,740 per airplane. 

For all affected airplanes, we estimate 

that it will take between 1 and 3 hours 

per airplane to accomplish the 

connection between the HSCU and the 

DAU specified in EMBRAER Service 

Bulletin 145LEB–27–0002, and that the 

average labor rate is $65 per work hour. 

Required parts will cost between $3 and 

$52 per airplane. Based on these figures, 

the cost impact of this action is 

estimated to be between $24,820 and 

$90,155, or between $68 and $247 per 

airplane. 

The cost impact figures discussed 

above are 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.

76608 Federal Register / Vol. 69, No. 245 / Wednesday, December 22, 2004 / Rules and Regulations 

§ 39.13 [Amended]

■ 2. Section 39.13 is amended by adding 

the following new airworthiness 

directive:

2004–25–21 Empresa Brasileira de 

Aeronautica S.A. (EMBRAER):

Amendment 39–13909. Docket 2003–

NM–97–AD.

Applicability: Model EMB–135 and –145 

series airplanes, as listed in EMBRAER 

Service Bulletin 145LEG–27–0002, Revision 

01, dated April 15, 2003; EMBRAER Service 

Bulletin 145–27–0084, Revision 04, dated 

October 21, 2003; and EMBRAER Service 

Bulletin 145–27–0096, Revision 03, dated 

September 2, 2003; certificated in any 

category. 

Compliance: Required as indicated, unless 

accomplished previously. 

To prevent the temporary loss of the pitch 

trim command, which could result in 

reduced controllability of the airplane and 

consequent injury to the flightcrew and 

passengers, accomplish the following:

Prior or Concurrent Requirements 

(a) Prior to the accomplishment of the 

actions in paragraph (b) of this AD, 

accomplish any applicable prior or 

concurrent requirement listed in paragraph 

(a)(1) or (a)(2) of this AD. 

(1) For airplanes listed in EMBRAER 

Service Bulletin 145–31–0020, Change 03, 

dated July 30, 2002, that are equipped with 

engine indicating and crew alerting system/

electronic flight information system (EICAS/

EFIS) software version 16.5 or earlier: 

Upgrade to software version 17 of the EICAS/

EFIS software, in accordance with the 

Accomplishment Instructions of the service 

bulletin. 

(2) For airplanes listed in EMBRAER 

Service Bulletin 145–27–0083, Change 04, 

dated November 27, 2002: Install electrical 

provisions for the new pitch trim system in 

accordance with the Accomplishment 

Instructions of the service bulletin. 

Modification of the Pitch Trim System: 

Replacement, Installation, and Connection 

(b) Within 18 months or 5,000 flight hours 

after the effective date of this AD, whichever 

occurs first, but following any applicable 

prior or concurrent requirement listed in 

paragraph (a)(1) or (a)(2) of this AD: Modify 

the pitch trim system for the affected 

airplanes by accomplishing the actions in 

paragraphs (b)(1), (b)(2), (b)(3), (b)(4), (b)(5), 

(b)(6), and (b)(7), as applicable. Accomplish 

the actions in the sequence specified in this 

AD. 

(1) For all airplanes: Replace the horizontal 

stabilizer control unit (HSCU) with a new 

unit with improved features, and having a 

new part number, in accordance with 

paragraph 3.J. (Part I) of EMBRAER Service 

Bulletin 145LEG–27–0002, Revision 01, 

dated April 15, 2003 (for Model EMB–135BJ 

series airplanes); or paragraph 3.J. (Part I) of 

EMBRAER Service Bulletin 145–27–0084, 

Revision 04, dated October 21, 2003 (for 

Model EMB–135ER, –135LR, –135KE, and 

–135KL series airplanes; and Model EMB–

145, –145ER, –145MR, –145LR, –145XR, 

–145MP, and –145EP series airplanes); as 

applicable. 

(2) For airplanes listed in EMBRAER 

Service Bulletin 145–27–0091, Change 02, 

dated November 27, 2002: Replace the 

horizontal stabilizer actuator (HSA) with a 

new HSA having a new part number in 

accordance with the Accomplishment 

Instructions of the service bulletin. 

(3) For airplanes listed in EMBRAER 

Service Bulletin 145–31–0028, Change 04, 

dated December 20, 2002: Replace the aural 

warning unit (AWU) with an AWU having 

improved features and a new part number in 

accordance with the Accomplishment 

Instructions of the service bulletin.

Note 1: EMBRAER Service Bulletin 145–

31–0028 references Grimes Aerospace 

Company Service Bulletin 80–0694–33–

SB01, dated January 1, 2002, as an additional 

source of service information for 

accomplishment of the replacement. The 

Grimes Aerospace service bulletin is 

included in the EMBRAER service bulletin.

(4) Replace the IC–600 units in accordance 

with paragraph (b)(4)(i) or (b)(4)(ii) of this 

AD. 

(i) For airplanes listed in EMBRAER 

Service Bulletin 145LEG–31–0001, dated 

August 19, 2002 (for Model EMB–135BJ 

series airplanes); or EMBRAER Service 

Bulletin 145–31–0033, Revision 03, dated 

August 25, 2003 (for Model EMB–135ER, 

–135LR, –135KE, and –135KL series 

airplanes; and Model EMB–145, –145ER, 

–145MR, –145LR, –145XR, –145MP, and 

–145EP series airplanes): Replace any IC–600 

units having part numbers (P/N) 7107000–

82407, –82407 MODS–B, –82427, –83407, 

and –83407 MODS–B, with new IC–600 MOD 

AB units having P/Ns 7107000–82428 or 

–83428, as applicable; and install a new 

software version 18.5 (phase 8.5) of the 

EICAS/EFIS system for all IC–600 MOD AB 

hardware. Accomplish the actions in 

accordance with the Accomplishment 

Instructions of the applicable service 

bulletin. 

(ii) For airplanes listed in EMBRAER 

Service Bulletin 145–31–0042, Revision 01, 

dated January 7, 2004: Replace any IC–600 

units having P/N 7107000–82428 and –82438 

with new IC–600 units having P/Ns 

7017000–82430 or –83430, in accordance 

with EMBRAER Service Bulletin 145–31–

0042, Revision 01, dated January 7, 2004, or 

Revision 02, dated June 23, 2004. Prior to or 

concurrently with the actions specified in 

Revision 01 or 02 of EMBRAER Service 

Bulletin 145–31–0042, remove or replace 

certain placards in the cockpit in accordance 

with the Accomplishment Instructions of 

EMBRAER Service Bulletin 145–25–0210, 

dated March 30, 2001; and modify and reidentify the central maintenance computer in 

accordance with the Accomplishment 

Instructions of EMBRAER Service Bulletin 

145–45–0003, dated July 5, 2000.

Note 2: EMBRAER Service Bulletins 

145LEG–31–0001 and 145–31–0033 reference 

Honeywell Service Bulletin 7017000–22–

6089, Revision 003, dated October 16, 2003, 

as an additional source of service information 

for accomplishment of the replacement and 

installation. EMBRAER Service Bulletin 145–

31–0042 references Honeywell Service 

Bulletin 7017000–22–6102, dated November 

25, 2003, as an additional source of service 

information for accomplishment of the 

replacement with P/Ns 7017000–82430 or 

–83430.

(5) For airplanes listed in EMBRAER 

Service Bulletin 145LEG–27–0004, dated 

January 21, 2003 (for Model EMB–135BJ 

series airplanes); or EMBRAER Service 

Bulletin 145–27–0096, Revision 03, dated 

September 2, 2003 (for Model EMB–135ER, 

–135LR, –135KE, and –135KL series 

airplanes; and Model EMB–145, –145ER, 

–145MR, –145LR, –145XR, –145MP, and 

–145EP series airplanes): Replace the control 

yoke pitch trim switch with a new switch 

having a new part number; and replace the 

placard around the switch knob, as 

applicable, with a new placard having a new 

part number in accordance with the 

Accomplishment Instructions of the 

applicable service bulletin.

(6) For airplanes listed in EMBRAER 

Service Bulletin 145–27–0073, Change 02, 

dated February 26, 2002: Replace the pitch 

trim back-up control switch with a new 

switch having a new part number (including 

reidentifying the trim control panel) in 

accordance with the Accomplishment 

Instructions of the service bulletin. 

(7) For all airplanes: Connect the HSCU 

and the data acquisition unit (DAU) 

(including the replacement of the pitch trim 

system circuit breakers with new circuit 

breakers sized for the new system load 

capacity, as applicable) in accordance with 

paragraph 3.K. (Part II) of EMBRAER Service 

Bulletin 145LEG–27–0002, Revision 01, 

dated April 15, 2003 (for Model EMB–135BJ 

series airplanes); or paragraphs 3.K., 3.L., 

3.M., and 3.N. (Parts II, III, IV, and V) of 

EMBRAER Service Bulletin 145–27–0084, 

Revision 04, dated October 21, 2003 (for 

Model EMB–135ER, –135LR, –135KE, and 

–135KL series airplanes; and Model EMB–

145, –145ER, –145MR, –145LR, –145XR, 

–145MP, and –145EP series airplanes). 

Parts Installation 

(c) As of the effective date of this AD, no 

person may install, on any airplane, a part 

unless it has been modified in accordance 

with the applicable paragraph of the affected 

service bulletins listed in Table 1 of this AD.

Federal Register / Vol. 69, No. 245 / Wednesday, December 22, 2004 / Rules and Regulations 76609

TABLE 1.—PARTS INSTALLATION PARAGRAPHS

EMBRAER service bulletin Parts installation 

paragraph 

145–27–0084, Revision 04, dated October 21, 2003 .................................................................................................................... 1.C.(1)(a). 

145LEG–27–0002, Revision 01, dated April 15, 2003 .................................................................................................................. 1.C.(1)(a). 

145–27–0091, Change 02, dated November 27, 2002 ................................................................................................................. 1.C.(1)(a). 

145–31–0028, Change 04, dated December 20, 2002 ................................................................................................................. 1.C.(a). 

145–31–0033, Revision 03, dated August 25, 2003 ...................................................................................................................... 1.C.(1). 

Actions Accomplished Previously in 

Accordance With Certain Service Bulletins 

(d) Actions accomplished before the 

effective date of this AD in accordance with 

the service bulletins listed in Table 2 of this 

AD are considered acceptable for compliance 

with the corresponding actions specified in 

this AD.

TABLE 2.—PREVIOUS ISSUES OF SERVICE BULLETINS

EMBRAER service bulletin Change/revision level Date 

145–27–0083 ........................................................................ Original ................................................................................. October 4, 2001. 

145–27–0083 ........................................................................ 01 ......................................................................................... March 15, 2002. 

145–27–0083 ........................................................................ 02 ......................................................................................... April 11, 2002. 

145–27–0083 ........................................................................ 03 ......................................................................................... July 16, 2002. 

145–27–0084 ........................................................................ 01 ......................................................................................... December 20, 2002. 

145–27–0084 ........................................................................ 02 ......................................................................................... February 25, 2003. 

145–27–0084 ........................................................................ 03 ......................................................................................... July 15, 2003. 

145–27–0096 ........................................................................ 01 ......................................................................................... April 7, 2003. 

145–27–0096 ........................................................................ 02 ......................................................................................... July 1, 2003. 

145–31–0028 ........................................................................ Original ................................................................................. December 13, 2001. 

145–31–0028 ........................................................................ 01 ......................................................................................... January 22, 2002. 

145–31–0028 ........................................................................ 02 ......................................................................................... April 2, 2002. 

145–31–0028 ........................................................................ 03 ......................................................................................... August 22, 2002. 

145–31–0033 ........................................................................ 02 ......................................................................................... April 17, 2003. 

145LEG–27–0002 ................................................................. Original ................................................................................. February 5, 2003. 

Alternative Methods of Compliance 

(e) In accordance with 14 CFR 39.19, the 

Manager, International Branch, ANM–116, 

FAA, Transport Airplane Directorate, is 

authorized to approve alternative methods of 

compliance for this AD. 

Incorporation by Reference 

(f) Unless otherwise specified in this AD, 

the actions shall be done in accordance with 

the service bulletins in Table 3 of this AD.

TABLE 3.—MATERIAL INCORPORATED BY REFERENCE

EMBRAER service bulletin Page No. Change/revision level Date 

145–25–0210 ....................................... 1–12 ..................................................... Original ................................................ March 30, 2001. 

145–27–0073 ....................................... 1, 2 ...................................................... 02 ......................................................... February 26, 2002. 

3, 4 ...................................................... 01 ......................................................... August 29, 2000. 

5–9 ....................................................... Original ................................................ June 30, 2000. 

145–27–0083 ....................................... 1, 2 ...................................................... 04 ......................................................... November 27, 2002. 

3–8, 15–30, 33–54 .............................. 01 ......................................................... March 15, 2002. 

9–12 ..................................................... 03 ......................................................... July 16, 2002. 

13, 14, 31, 32 ...................................... 02 ......................................................... April 11, 2002. 

145–27–0084 ....................................... 1–4, 6, 11, 12, 15 ................................ 04 ......................................................... October 21, 2003. 

5, 7–10, 13, 14, 16–40 ........................ 03 ......................................................... July 15, 2003. 

145–27–0091 ....................................... 1, 2 ...................................................... 02 ......................................................... November 27, 2002. 

3–11 ..................................................... Original ................................................ February 8, 2002. 

145–27–0096 ....................................... 1–2 ....................................................... 03 ......................................................... September 2, 2003. 

3, 5–8, 12, 14, 15, 17–22 .................... Original ................................................ December 18, 2002. 

4, 13, 16 .............................................. 02 ......................................................... July 1, 2003.

9–11 ..................................................... 01 ......................................................... April 7, 2003. 

145–31–0020 ....................................... 1–81 ..................................................... 03 ......................................................... July 30, 2002. 

145–31–0028 ....................................... 1–17 ..................................................... 04 ......................................................... December 20, 2002. 

145–31–0033 ....................................... 1–5, 9–11, 15, 16, 21–24, 56–58 ........ 03 ......................................................... August 25, 2003. 

6–8, 12–14, 17–20, 25-55, 59 ............. 02 ......................................................... April 17, 2003. 

145–31–0042 ....................................... 1–114 ................................................... 01 ......................................................... January 7, 2004. 

145–31–0042 ....................................... 1–10, 21–24, 99, 100 .......................... 02 ......................................................... June 23, 2004. 

11–20, 25–98, 101–114 ...................... 01 ......................................................... January 7, 2004. 

145LEG–27–0002 ................................ 1, 5 ...................................................... 01 ......................................................... April 15, 2003. 

2–4, 6–15 ............................................ Original ................................................ February 5, 2003. 

145–45–0003 ....................................... 1–15 ..................................................... Original ................................................ July 5, 2000. 

145LEG–27–0004 ................................ 1–16 ..................................................... Original ................................................ January 21, 2003. 

76610 Federal Register / Vol. 69, No. 245 / Wednesday, December 22, 2004 / Rules and Regulations 

TABLE 3.—MATERIAL INCORPORATED BY REFERENCE—Continued

EMBRAER service bulletin Page No. Change/revision level Date 

145LEG–31–0001 ................................ 1–12 ..................................................... Original ................................................ August 19, 2002.

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 Empresa Brasileira de Aeronautica S.A. 

(EMBRAER), PO Box 343—CEP 12.225, Sao 

Jose dos Campos—SP, Brazil. Copies may be 

inspected at the FAA, Transport Airplane 

Directorate, 1601 Lind Avenue, SW., Renton, 

Washington; or at the National Archives and 

Records Administration (NARA). For 

information on the availability of this 

material at NARA, call (202) 741–6030, or go 

to: http://www.archives.gov/federal_register/

code_of_federal_regulations/

ibr_locations.html.

Note 3: The subject of this AD is addressed 

in Brazilian airworthiness directive 2003–03–

01, dated April 3, 2003.

Effective Date 

(g) This amendment becomes effective on 

January 26, 2005.

Issued in Renton, Washington, on 

December 6, 2004. 

Ali Bahrami, 

Manager, Transport Airplane Directorate, 

Aircraft Certification Service.

[FR Doc. 04–27509 Filed 12–21–04; 8:45 am] 

BILLING CODE 4910–13–P

DEPARTMENT OF TRANSPORTATION

Federal Aviation Administration 

14 CFR Part 39

[Docket No. 2003–NE–67–AD; Amendment 

39–13914; AD 2004–26–02] 

RIN 2120–AA64

Airworthiness Directives; GE Aircraft 

Engines (GE) CF34–3A, CF34–3A2, 

CF34–1A, CF34–3A1, CF34–3B, and 

CF34–3B1 Series Turbofan Engines

AGENCY: Federal Aviation 

Administration (FAA), DOT.

ACTION: Final rule.

SUMMARY: The FAA is adopting a new 

airworthiness directive (AD) for GE 

CF34–3A, CF34–3A2, CF34–1A, CF34–

3A1, CF34–3B, and CF34–3B1 series 

turbofan engines. This AD requires 

removal from service of certain high 

pressure compressor (HPC) forward 

spools, at the first piece-part level 

exposure after 6,000 cycles since new 

(CSN); but not later than 20,000 CSN for 

CF34–3B engines, and not later than 

22,000 CSN for CF34–3A, CF34–3A2, 

CF34–1A, CF34–3A1, and CF34–3B1 

engines. This AD results from an 

updated low-cycle fatigue (LCF) 

analysis performed on certain HPC 

forward spools. We are issuing this AD 

to prevent LCF cracks and failure of the 

HPC forward spool, which could result 

in an uncontained engine failure and 

damage to the airplane.

DATES: This AD becomes effective 

January 26, 2005.

ADDRESSES: You may examine the AD 

docket at the FAA, New England 

Region, Office of the Regional Counsel, 

12 New England Executive Park, 

Burlington, MA.

FOR FURTHER INFORMATION CONTACT:

Robert Grant, Aerospace Engineer, 

Engine Certification Office, FAA, Engine 

& Propeller Directorate, 12 New England 

Executive Park, Burlington, MA 01803–

5299; telephone (781) 238–7757; fax 

(781) 238–7199.

SUPPLEMENTARY INFORMATION: The FAA 

proposed to amend 14 CFR part 39 with 

a proposed AD. The proposed AD 

applies to GE CF34–3A, CF34–3A2, 

CF34–1A, CF34–3A1, CF34–3B, and 

CF34–3B1 series turbofan engines. We 

published the proposed AD in the 

Federal Register on May 18, 2004 (69 

FR 28093). That action proposed to 

require removal from service of certain 

HPC forward spools, at the first piecepart level exposure after 6,000 CSN, but 

not later than 20,000 CSN for CF34–3B 

engines and not later than 22,000 CSN 

for CF34–3A, CF34–3A2, CF34–1A, 

CF34–3A1, and CF34–3B1 engines. That 

action results from GE updating the LCF 

analysis for these HPC forward spools. 

Examining the AD Docket 

You may examine the AD Docket 

(including any comments and service 

information), by appointment, between 

8 a.m. and 4:30 p.m., Monday through 

Friday, except Federal holidays. See

ADDRESSES for the location. 

Comments 

We provided the public the 

opportunity to participate in the 

development of this AD. We have 

considered the one comment received. 

Request for Definition Clarification of 

Serviceable HPC Forward Spool 

One commenter requests that we 

clarify the definition of a serviceable 

HPC forward spool. The commenter 

states that a clarification would ensure 

that operators are not led to believe that 

HPC forward spools installed in their 

engines are not serviceable based on the 

AD’s definition of a serviceable HPC 

forward spool. 

We partially agree. As written in the 

proposal, the compliance requires 

replacing certain HPC forward spools 

with a serviceable HPC forward spool at 

next piece-part level exposure, and then 

defines what a serviceable HPC forward 

spool is and what it is not. We agree that 

this definition could cause confusion. 

We do not agree that a clarification to 

the existing definition is the best 

approach to ensure that the AD is 

understandable. For clarification, we 

have rewritten the compliance in the 

final rule to require operators to remove 

certain specific spools from service. We 

have also added a paragraph in the final 

rule to clarify that after the effective 

date of this AD, do not install any HPC 

forward spool, P/N 6078T56P03. We 

have also clarified the requirement that 

after the effective date of this AD, do not 

install any HPC forward spool, P/N 

6078T56P04, with more than 0 CSN. We 

have also deleted from the final rule the 

definition which described serviceable 

spools. 

Conclusion 

We have carefully reviewed the 

available data, including the comment 

received, and determined that air safety 

and the public interest require adopting 

the AD 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.

Costs of Compliance 

There are about 2,681 GE CF34–3A, 

CF34–3A2, CF34–1A, CF34–3B and 

CF34–3B1 series turbofan engines of the 

affected design in the worldwide fleet. 

We estimate that 1,826 engines installed 

on airplanes of U.S. registry would be 

affected by this AD. We also estimate 

that 59% of the replacements will not be 

done at piece-part exposure, and will 

require approximately 650 work hours 

per engine to perform the actions, and 

that the average labor rate is $65 per 

work hour. Required parts will cost 

about $16,000 per engine (a prorated 

cost of the unused spool life to the 

original life). Based on these figures, we 

estimate the total cost of the AD to U.S. 

operators to be $74,420,000.