[Federal Register Volume 69, Number 245 (Wednesday, December 22, 2004)]
[Rules and Regulations]
[Pages 76605-76610]
From the Federal Register Online via the Government Publishing Office [www.gpo.gov]
[FR Doc No: 04-27509]


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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.

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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)

[[Page 76606]]

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 re-
identification. 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 re-identifying 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

[[Page 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

0
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

0
1. The authority citation for part 39 continues to read as follows:

    Authority: 49 U.S.C. 106(g), 40113, 44701.

[[Page 76608]]

Sec.  39.13  [Amended]

0
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 re-
identify 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.

[[Page 76609]]



                 Table 1.--Parts Installation Paragraphs
------------------------------------------------------------------------
                                                   Parts installation
           EMBRAER service bulletin                    paragraph
------------------------------------------------------------------------
145-27-0084, Revision 04, dated October 21,    1.C.(1)(a).
 2003.
145LEG-27-0002, Revision 01, dated April 15,   1.C.(1)(a).
 2003.
145-27-0091, Change 02, dated November 27,     1.C.(1)(a).
 2002.
145-31-0028, Change 04, dated December 20,     1.C.(a).
 2002.
145-31-0033, Revision 03, dated August 25,     1.C.(1).
 2003.
------------------------------------------------------------------------

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
----------------------------------------------------------------------------------------------------------------
                                                              Change/revision
     EMBRAER service bulletin              Page No.                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-   03..................  July 15, 2003.
                                     40.
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,    Original............  December 18, 2002.
                                     17-22.
                                    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- 03..................  August 25, 2003.
                                     24, 56-58.
                                    6-8, 12-14, 17-20, 25- 02..................  April 17, 2003.
                                     55, 59.
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.

[[Page 76610]]

 
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