Federal Register / Vol. 69, No. 25 / Friday, February 6, 2004 / Proposed Rules 5759

approved as alternative methods of 

compliance for this AD. 

May I Get Copies of the Documents 

Referenced in This AD? 

(g) You may get copies of the documents 

referenced in this AD from The Cessna 

Aircraft Company, Product Support, P.O. Box 

7706, Wichita, Kansas 67277; telephone: 

(316) 517–6000; facsimile: (316) 517–8500. 

You may view these documents at FAA, 

Central Region, Office of the Regional 

Counsel, 901 Locust, Room 506, Kansas City, 

Missouri 64106.

Issued in Kansas City, Missouri, on January 

29, 2004. 

Dorenda D. Baker, 

Manager, Small Airplane Directorate, Aircraft 

Certification Service.

[FR Doc. 04–2403 Filed 2–5–04; 8:45 am] 

BILLING CODE 4910–13–P

DEPARTMENT OF TRANSPORTATION

Federal Aviation Administration 

14 CFR Part 39 

[Docket No. 2003–NM–97–AD] 

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: Notice of proposed rulemaking 

(NPRM). 

SUMMARY: This document proposes the 

adoption of a new airworthiness 

directive (AD) that is applicable to 

certain Model EMB–135 and –145 series 

airplanes. This proposal would 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. 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: Comments must be received by 

March 8, 2004.

ADDRESSES: Submit comments in 

triplicate to the Federal Aviation 

Administration (FAA), Transport 

Airplane Directorate, ANM–114, 

Attention: Rules Docket No. 2003–NM–

97–AD, 1601 Lind Avenue, SW., 

Renton, Washington 98055–4056. 

Comments may be inspected at this 

location between 9 a.m. and 3 p.m., 

Monday through Friday, except Federal 

holidays. Comments may be submitted 

via fax to (425) 227–1232. Comments 

may also be sent via the Internet using 

the following address: 9–anm–

nprmcomment@faa.gov. Comments sent 

via fax or the Internet must contain 

‘‘Docket No. 2003–NM–97–AD’’ in the 

subject line and need not be submitted 

in triplicate. Comments sent via the 

Internet as attached electronic files must 

be formatted in Microsoft Word 97 or 

2000 or ASCII text. 

The service information referenced in 

the proposed rule may be obtained from 

Empresa Brasileira de Aeronautica S.A. 

(EMBRAER), P.O. Box 343—CEP 12.225, 

Sao Jose dos Campos—SP, Brazil. This 

information may be examined at the 

FAA, Transport Airplane Directorate, 

1601 Lind Avenue, SW., Renton, 

Washington.

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: 

Comments Invited 

Interested persons are invited to 

participate in the making of the 

proposed rule by submitting such 

written data, views, or arguments as 

they may desire. Communications shall 

identify the Rules Docket number and 

be submitted in triplicate to the address 

specified above. All communications 

received on or before the closing date 

for comments, specified above, will be 

considered before taking action on the 

proposed rule. The proposals contained 

in this action may be changed in light 

of the comments received. 

Submit comments using the following 

format: 

• Organize comments issue-by-issue. 

For example, discuss a request to 

change the compliance time and a 

request to change the service bulletin 

reference as two separate issues. 

• For each issue, state what specific 

change to the proposed AD is being 

requested. 

• Include justification (e.g., reasons or 

data) for each request. 

Comments are specifically invited on 

the overall regulatory, economic, 

environmental, and energy aspects of 

the proposed rule. All comments 

submitted will be available, both before 

and after the closing date for comments, 

in the Rules Docket for examination by 

interested persons. A report 

summarizing each FAA-public contact 

concerned with the substance of this 

proposal will be filed in the Rules 

Docket. 

Commenters wishing the FAA to 

acknowledge receipt of their comments 

submitted in response to this action 

must submit a self-addressed, stamped 

postcard on which the following 

statement is made: ‘‘Comments to 

Docket Number 2003–NM–97–AD.’’ The 

postcard will be date stamped and 

returned to the commenter. 

Availability of NPRMs 

Any person may obtain a copy of this 

NPRM by submitting a request to the 

FAA, Transport Airplane Directorate, 

ANM–114, Attention: Rules Docket No. 

2003–NM–97–AD, 1601 Lind Avenue, 

SW., Renton, Washington 98055–4056. 

Discussion 

The Departmento de Aviacao Civil 

(DAC), which is the airworthiness 

authority for Brazil, notified the FAA 

that an unsafe condition may exist on 

certain EMBRAER Model EMB–135 and 

–145 series airplanes. The DAC advises 

that several operators have reported 

temporary loss of the pitch trim 

command during the climb after take-off 

caused by probable failure of various 

components of the pitch trim system. 

The pitch trim system consists of 

several components including the 

horizontal stabilizer control unit 

(HSCU), the horizontal stabilizer 

actuator (HSA), the aural warning unit 

(AWU), integrated computer (IC) units, 

engine indicating and crew alerting 

system/electronic flight information 

system (EICAS/EFIS) software, the 

control yoke pitch trim switch, and the 

data acquisition unit (DAU). Failure of 

the pitch trim system, if not corrected, 

could result in reduced controllability 

of the airplane and consequent injury to 

the flightcrew and passengers.

Explanation of Relevant Service 

Information 

EMBRAER has issued the following 

service bulletins related to the 

modification of the pitch trim system. 

• EMBRAER Service Bulletin 

145LEG–27–0002, dated February 5, 

2003 (for Model EMB–135BJ series 

airplanes); and 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); which describe procedures 

for replacing the HSCU with a new unit 

having improved features. EMBRAER 

Service Bulletin 145–27–0084 specifies 

that EMBRAER Service Bulletin 145–

5760 Federal Register / Vol. 69, No. 25 / Friday, February 6, 2004 / Proposed Rules 

27–0091, Change 02, dated November 

27, 2002, must be accomplished either 

previously or concurrently with the 

replacement of the HSCU. 

EMBRAER Service Bulletins 145LEG–

27–0002 and 145–27–0084 also describe 

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). EMBRAER 

Service Bulletin 145–27–0084 specifies 

that EMBRAER Service Bulletins 145–

31–0028, Change 04, dated December 

20, 2002; 145–31–0033, Revision 03, 

dated August 25, 2003; and 145–27–

0083, Change 04, dated November 27, 

2002 must be accomplished prior to the 

connection of the HSCU and the DAU. 

• EMBRAER Service Bulletin 145–

27–0083, Change 04, dated November 

27, 2002 (for Model EMB–135ER, 

–135LR, –135KE, and –135KL series 

airplanes; and Model EMB–145, 

–145ER, –145MR, –145LR, –145XR, 

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

must be accomplished either previously 

or concurrently with Service Bulletin 

145–27–0084. Service Bulletin 145–27–

0083 contains procedures for installing 

electrical provisions for the new pitch 

trim system, which includes adding 

new cable harnesses in the front 

electronic compartment, the entire 

center fuselage, the cockpit, and the 

entire rear fuselage; to enable the 

connection of the HSCU through certain 

electrical connections, and to enable the 

connection of DAU #2 to the HSCU. 

• EMBRAER Service Bulletin 145–

27–0091, Change 02, dated November 

27, 2002 (for all affected models); which 

describes procedures for replacing the 

HSA with a new HSA. 

• EMBRAER Service Bulletin 145–

31–0028, Change 04, dated December 

20, 2002 (for all affected models); which 

describes procedures for replacing the 

AWU with an AWU having improved 

features. This service bulletin also 

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. 

• EMBRAER Service Bulletin 

145LEG–31–0001, dated August 19, 

2002 (for Model EMB–135BJ series 

airplanes); and 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); 

which describe procedures for replacing 

any IC units having certain part 

numbers with new units having new 

modification letters and new part 

numbers. These service bulletins also 

describe procedures for installing an 

updated version of the software for the 

EICAS/EFIS. EMBRAER Service 

Bulletin 145–31–0033 specifies that 

EMBRAER Service Bulletins 145–31–

0020, Change 03, dated July 30, 2002; 

and 145–27–0084, Revision 04, dated 

October 21, 2003 (described previously); 

must be accomplished previously. 

EMBRAER Service Bulletin 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–

31–0020, Change 03, dated July 30, 2002 

(for Model EMB–135ER, –135LR, 

–135KE, and –135KL series airplanes; 

and Model EMB–145, –145ER, –145MR, 

–145LR, –145XR, –145MP, and –145EP 

series airplanes), must be accomplished 

prior to accomplishment of Service 

Bulletin 145–31–0033. Service Bulletin 

145–31–0020 contains procedures for 

replacing the IC–600#1 and IC–600#2, 

and the DAU; and for upgrading the 

EICAS to version 17. 

• EMBRAER Service Bulletin 

145LEG–27–0004, dated January 21, 

2003 (for Model EMB–135BJ series 

airplanes); and 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); which describe procedures 

for replacing the control yoke pitch trim 

switch with a new switch; and 

procedures for replacing the placard 

around the switch knob, as applicable, 

with a new placard. 

• EMBRAER Service Bulletin 145–

27–0073, Change 02, dated February 26, 

2002 (for all affected models); which 

describes procedures for replacing the 

pitch trim back-up control switch with 

a new switch (including reidentifying 

the trim control panel). 

The DAC classified these service 

bulletins as mandatory and issued 

Brazilian airworthiness directive 2003–

03–01, dated April 3, 2003, to ensure 

the continued airworthiness of these 

airplanes in Brazil. 

FAA’s Conclusions 

These airplane models are 

manufactured in Brazil 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, the DAC has 

kept the FAA informed of the situation 

described above. The FAA has 

examined the findings of the DAC, 

reviewed all available information, and 

determined that AD action is necessary 

for products of this type design that are 

certificated for operation in the United 

States. 

Interim Action 

We consider this proposed AD 

interim action. The manufacturer is 

currently developing additional 

modifications that will address the 

unsafe condition identified in this 

proposed AD. Once these modifications 

are developed, approved, and available, 

we may consider additional rulemaking. 

Explanation of Requirements of 

Proposed Rule 

Since an unsafe condition has been 

identified that is likely to exist or 

develop on other airplanes of the same 

type design registered in the United 

States, the proposed AD would require 

accomplishment of the actions specified 

in the service bulletins described 

previously. 

Cost Impact 

The FAA estimates that 365 airplanes 

of U.S. registry would be affected by this 

proposed AD. 

For all affected airplanes, we estimate 

that it would take approximately 1 work 

hour per airplane to accomplish the 

proposed replacement of the HCSU, 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 proposed 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 would take 

approximately 6 work hours per 

airplane to accomplish the proposed 

replacement of the HSA, 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 

proposed replacement on U.S. operators 

is estimated to be $390 per airplane.

For airplanes subject to EMBRAER 

Service Bulletin 145–31–0028, we 

estimate that it would take 

approximately 2 work hours per 

airplane to accomplish the proposed 

replacement of the AWU, and that the 

average labor rate is $65 per work hour. 

Federal Register / Vol. 69, No. 25 / Friday, February 6, 2004 / Proposed Rules 5761

Required parts would cost 

approximately $1,100 per airplane. 

Based on these figures, the cost impact 

of the proposed AD on U.S. operators is 

estimated to be $1,230 per airplane. 

For airplanes subject to EMBRAER 

Service Bulletins 145LEG–31–0001, or 

145–31–0033, we estimate that it would 

take between 3 and 6 work hours per 

airplane to accomplish the proposed 

installation of the new EICAS/EFIS, and 

that the average labor rate is $65 per 

work hour. Required parts would cost 

approximately $10 per airplane. Based 

on these figures, the cost impact of the 

proposed AD on U.S. operators is 

estimated to be between $205 and $400 

per airplane. 

For airplanes subject to EMBRAER 

Service Bulletins 145LEG–27–0004, or 

145–27–0096, we estimate that it would 

take between 4 and 5 work hours per 

airplane to accomplish the proposed 

replacement of the yoke pitch trim 

switch, and that the average labor rate 

is $65 per work hour. Required parts 

would cost approximately between 

$1,042 and $1,056 per airplane. Based 

on these figures, the cost impact of the 

proposed AD on U.S. operators 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 would take 

approximately 3 work hours per 

airplane to accomplish the proposed 

replacement of pitch trim back-up 

control switch, and that the average 

labor rate is $65 per work hour. 

Required parts would cost 

approximately $371 per airplane. Based 

on these figures, the cost impact of the 

proposed AD on U.S. operators is 

estimated to be $566 per airplane. 

For airplanes subject to the 

requirements in EMBRAER Service 

Bulletin 145–27–0083, Change 04, dated 

November 27, 2002, we estimate that it 

would take approximately 38 hours to 

accomplish the proposed modifications, 

and that the average labor rate is $65 per 

work hour. Required parts would cost 

approximately $448. Based on these 

figures, the cost impact of the proposed 

AD on U.S. operators is estimated to be 

$2,918 per airplane. 

For airplanes subject to the 

requirements in EMBRAER Service 

Bulletin 145–31–0020, Change 03, dated 

July 30, 2002, we estimate that it would 

take between 9 and 56 hours to 

accomplish the proposed upgrade, and 

that the average labor rate is $65 per 

work hour. Required parts would cost 

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

figures, the cost impact of the proposed 

AD on U.S. operators is estimated to be 

approximately between $588 and $8,740 

per airplane. 

For all affected airplanes, we estimate 

that it would take between 1 and 3 

hours per airplane to accomplish the 

proposed connection between the HSCU 

and the DAU, and that the average labor 

rate is $65 per work hour. Required 

parts would cost between $3 and $52 

per airplane. Based on these figures, the 

cost impact of the proposed AD on U.S. 

operators 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 proposed 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 proposed herein 

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. Therefore, 

it is determined that this proposal 

would not have federalism implications 

under Executive Order 13132. 

For the reasons discussed above, I 

certify that this 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) if 

promulgated, 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 copy of the draft 

regulatory evaluation prepared for this 

action is contained in the Rules Docket. 

A copy of it may be obtained by 

contacting the Rules Docket at the 

location provided under the caption 

ADDRESSES.

List of Subjects in 14 CFR Part 39 

Air transportation, Aircraft, Aviation 

safety, Safety.

The Proposed Amendment 

Accordingly, pursuant to the 

authority delegated to me by the 

Administrator, the Federal Aviation 

Administration proposes to amend 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:

Empresa Brasileira de Aeronautica S.A. 

(EMBRAER): Docket 2003–NM–97–AD.

Applicability: Model EMB–135 and –145 

series airplanes, as listed in EMBRAER 

Service Bulletin 145LEG–27–0002, dated 

February 5, 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, dated February 5, 

5762 Federal Register / Vol. 69, No. 25 / Friday, February 6, 2004 / Proposed Rules 

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) 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.

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.

(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, dated February 5, 

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.

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, dated 

February 5, 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 Per Previous Issues of 

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 action specified in 

this AD.

TABLE 2.—PREVIOUS ISSUES OF

SERVICE BULLETINS

EMBRAER 

service

bulletin 

Revision and date 

145–31–0028 Original Issue, December 13, 

2001. 

Revision 01, January 22, 

2002. 

Revision 02, April 2, 2002. 

Revision 03, August 22, 2002. 

145–31–0033 Revision 02, April 27, 2003. 

Revision 03, August 25, 2003. 

TABLE 2.—PREVIOUS ISSUES OF

SERVICE BULLETINS—Continued

EMBRAER 

service

bulletin 

Revision and date 

145–27–0083 Original Issue, October 4, 

2001. 

Revision 01, March 15, 2002. 

Revision 02, April 11, 2002. 

Revision 03, July 16, 2002. 

145–27–0084 Revision 01, December 20, 

2002. 

Revision 02, February 25, 

2003. 

Revision 03, July 15, 2003. 

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

Revision 02, July 1, 2003. 

Revision 03, September 2, 

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.

Note 3: The subject of this AD is addressed 

in Brazilian airworthiness directive 2003–03–

01, dated April 3, 2003.

Issued in Renton, Washington, on January 

29, 2004. 

Kalene C. Yanamura, 

Acting Manager, Transport Airplane 

Directorate, Aircraft Certification Service.

[FR Doc. 04–2467 Filed 2–5–04; 8:45 am] 

BILLING CODE 4910–13–P

DEPARTMENT OF TRANSPORTATION

Federal Aviation Administration 

14 CFR Part 39 

[Docket No. 2002–NM–262–AD] 

RIN 2120–AA64 

Airworthiness Directives; 

Construcciones Aeronauticas, S.A. 

(CASA), Model C–212 Series Airplanes

AGENCY: Federal Aviation 

Administration, DOT.

ACTION: Notice of proposed rulemaking 

(NPRM). 

SUMMARY: This document proposes the 

adoption of a new airworthiness 

directive (AD) that is applicable to all 

CASA Model C–212 series airplanes. 

This proposal would require rework of 

the nose landing gear (NLG); 

modification of the hydraulic steering 

system; a test of the cable tension for the 

nosewheel steering system when 

abnormal vibration occurs, and 

adjustment of the cable tension, if 

necessary; and a revision to the