[Federal Register: December 22, 2004 (Volume 69, Number 245)]
[Rules and Regulations]
[Page 76605-76610]
From the Federal Register Online via GPO Access [wais.access.gpo.gov]
[DOCID:fr22de04-5]
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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