[Federal Register Volume 69, Number 25 (Friday, February 6, 2004)]
[Proposed Rules]
[Pages 5759-5762]
From the Federal Register Online via the Government Publishing Office [www.gpo.gov]
[FR Doc No: 04-2467]


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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).

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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: 
[email protected]. 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-

[[Page 5760]]

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-6001 and IC-
6002, 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.

[[Page 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.


Sec. 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,

[[Page 5762]]

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   1.C.(1)(a)
 21, 2003.
145LEG-27-0002, dated February 5, 2003..  1.C.(1)(a)
145-27-0091, Change 02, dated November    1.C.(1)(a)
 27, 2002.
145-31-0028, Change 04, dated December    1.C.(a)
 20, 2002.
145-31-0033, Revision 03, dated August    1.C.(1)
 25, 2003.
------------------------------------------------------------------------

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.
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