Airworthiness Directives; Empresa Brasileira de Aeronautica S.A. (EMBRAER) Model EMB-135BJ, -135ER, -135KE, -135KL, and -135LR Airplanes; and EMB-145, -145ER, -145MR, -145LR, -145XR, -145MP, and -145EP Airplanes, 5685-5689 [2010-1930]
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Federal Register / Vol. 75, No. 23 / Thursday, February 4, 2010 / Rules and Regulations
‘‘General requirements.’’ Under that
section, Congress charges the FAA with
promoting safe flight of civil aircraft in
air commerce by prescribing regulations
for practices, methods, and procedures
the Administrator finds necessary for
safety in air commerce. This regulation
is within the scope of that authority
because it addresses an unsafe condition
that is likely to exist or develop on
products identified in this rulemaking
action.
Regulatory Findings
We have determined that this AD will
not have federalism implications under
Executive Order 13132. This AD 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.
For the reasons discussed above, I
certify that the 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. 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.
We prepared an economic evaluation
of the estimated costs to comply with
this AD. See the AD docket to examine
the economic evaluation.
cprice-sewell on DSK2BSOYB1PROD with RULES
however, we invite you to submit any
written data, views, or arguments
regarding this AD. Send your comments
to an address listed under ADDRESSES.
Include ‘‘Docket No. FAA–2010–0066;
Directorate Identifier 2009–SW–52–AD’’
at the beginning of your comments. We
specifically invite comments on the
overall regulatory, economic,
environmental, and energy aspects of
the AD. We will consider all comments
received by the closing date and may
amend the AD in light of those
comments.
We will post all comments we
receive, without change, to https://
www.regulations.gov, including any
personal information you provide. We
will also post a report summarizing each
substantive verbal contact with FAA
personnel concerning this AD. Using the
search function of our docket Web site,
you can find and read the comments to
any of our dockets, including the name
of the individual who sent the
comment. You may review the DOT’s
complete Privacy Act Statement in the
Federal Register published on April 11,
2000 (65 FR 19477–78).
Authority: 49 U.S.C. 106(g), 40113, 44701.
Authority for This Rulemaking
Title 49 of the United States Code
specifies the FAA’s authority to issue
rules on aviation safety. Subtitle I,
Section 106, describes the authority of
the FAA Administrator. Subtitle VII,
Aviation Programs, describes in more
detail the scope of the Agency’s
authority.
We are issuing this rulemaking under
the authority described in Subtitle VII,
Part A, Subpart III, Section 44701,
VerDate Nov<24>2008
15:08 Feb 03, 2010
Jkt 220001
List of Subjects in 14 CFR Part 39
Air transportation, Aircraft, Aviation
safety, Incorporation by reference,
Safety.
Adoption of the Amendment
Accordingly, pursuant to the authority
delegated to me by the Administrator,
the Federal Aviation Administration
amends part 39 of the Federal Aviation
Regulations (14 CFR part 39) as follows:
■
PART 39—AIRWORTHINESS
DIRECTIVES
1. The authority citation for part 39
continues to read as follows:
■
§ 39.13
[Amended]
2. Section 39.13 is amended by adding
a new airworthiness directive to read as
follows:
■
2009–23–51 Sikorsky Aircraft Corporation:
Amendment 39–16190. Docket No.
FAA–2010–0066; Directorate Identifier
2009–SW–52–AD.
Applicability: Model S–92A helicopters,
with main gearbox (MGB) assembly, part
number (P/N) 92351–15000–042 or –043,
with MGB housing, P/N 92351–15110–042,
–043, –044, or –045, installed, certificated in
any category.
Compliance: Required as indicated.
To prevent loss of an MGB and subsequent
loss of control of the helicopter, do the
following:
(a) Within 10 hours time-in-service (TIS),
unless accomplished previously, and
thereafter at intervals not to exceed 10 hours
TIS, clean and inspect each MGB assembly
mounting foot pad and rib for a crack and
corrosion in the area depicted in Figure 1; as
shown in the examples in Figures 2, 3, and
4; of Sikorsky Alert Service Bulletin No. 92–
63–020, dated September 11, 2009 (ASB). If
no crack is found, apply the corrosion
preventive compound to each foot pad and
rib area.
Note 1: When conducting a visual
inspection, use a bright, non-LED light.
(1) If you find a crack, replace the MGB
before further flight.
(2) If you find corrosion, bubbled paint, or
paint discoloration, before further flight,
repair the affected area.
Note 2: Following the ASB
Accomplishment Instructions accomplishes
the intent of this AD.
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5685
(b) To request a different method of
compliance or a different compliance time
for this AD, follow the procedures in 14 CFR
39.19. Contact the Manager, Boston Aircraft
Certification Office, ATTN: Michael Schwetz,
Aviation Safety Engineer, 12 New England
Executive Park, Burlington, MA 01803,
telephone (781) 238–7761, fax (781) 238–
7170, for information about previously
approved alternative methods of compliance.
(c) The Joint Aircraft System/Component
(JASC) Code is 6320: Main Rotor Gearbox.
(d) Do the inspections by following the
specified portions of Sikorsky Alert Service
Bulletin No. 92–63–020, dated September 11,
2009. The Director of the Federal Register
approved this incorporation by reference
under 5 U.S.C. 552(a) and 1 CFR part 51.
Copies may be obtained from Sikorsky
Aircraft Corporation, Attn: Manager,
Commercial Technical Support, mailstop
s581a, 6900 Main Street, Stratford, CT,
telephone (203) 383–4866, e-mail address
tsslibrary@sikorsky.com, or at https://
www.sikorsky.com. Copies may be inspected
at the FAA, Office of the Regional Counsel,
Southwest Region, 2601 Meacham Blvd.,
Room 663, Fort Worth, Texas, 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: https://
www.archives.gov/federal_register/
code_of_federal_regulations/
ibr_locations.html.
(e) This amendment becomes effective on
February 19, 2010, to all persons except those
persons to whom it was made immediately
effective by Emergency AD 2009–23–51,
issued October 29, 2009, which contained the
requirements of this amendment.
Issued in Fort Worth, Texas, on December
18, 2009.
Mark R. Schilling,
Acting Manager, Rotorcraft Directorate,
Aircraft Certification Service.
[FR Doc. 2010–1723 Filed 2–3–10; 8:45 am]
BILLING CODE 4910–13–P
DEPARTMENT OF TRANSPORTATION
Federal Aviation Administration
14 CFR Part 39
[Docket No. FAA–2009–0659; Directorate
Identifier 2009–NM–060–AD; Amendment
39–16191; AD 2010–03–07]
RIN 2120–AA64
Airworthiness Directives; Empresa
Brasileira de Aeronautica S.A.
(EMBRAER) Model EMB–135BJ,
–135ER, –135KE, –135KL, and –135LR
Airplanes; and EMB–145, –145ER,
–145MR, –145LR, –145XR, –145MP, and
–145EP Airplanes
AGENCY: Federal Aviation
Administration (FAA), Department of
Transportation (DOT).
ACTION: Final rule.
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Federal Register / Vol. 75, No. 23 / Thursday, February 4, 2010 / Rules and Regulations
SUMMARY: We are adopting a new
airworthiness directive (AD) for the
products listed above. This AD results
from mandatory continuing
airworthiness information (MCAI)
originated by an aviation authority of
another country to identify and correct
an unsafe condition on an aviation
product. The MCAI describes the unsafe
condition as:
strut, which affects the airplane
controllability on ground.
It has been found occurrences of main
landing gear (MLG) trailing arm pins broken
due to a fatigue mechanism induced by an
excessive torque applied during the
assemblage of auxiliary door support
attachment and consequent deformation of
the MLG trailing arm axle. A broken pin can
lead to loss of the MLG trailing arm axle,
disconnecting the trailing arm from the main
strut, which affects the airplane
controllability on ground.
Relevant Service Information
*
*
*
*
*
We are issuing this AD to require
actions to correct the unsafe condition
on these products.
DATES: This AD becomes effective
March 11, 2010.
The Director of the Federal Register
approved the incorporation by reference
of certain publications listed in this AD
as of March 11, 2010.
You may examine the AD
docket on the Internet at https://
www.regulations.gov or in person at the
U.S. Department of Transportation,
Docket Operations, M–30, West
Building Ground Floor, Room W12–140,
1200 New Jersey Avenue, SE.,
Washington, DC.
ADDRESSES:
FOR FURTHER INFORMATION CONTACT:
Todd Thompson, Aerospace Engineer,
International Branch, ANM–116,
Transport Airplane Directorate, FAA,
1601 Lind Avenue, SW., Renton,
Washington 98057–3356; telephone
(425) 227–1175; fax (425) 227–1149.
SUPPLEMENTARY INFORMATION:
Discussion
cprice-sewell on DSK2BSOYB1PROD with RULES
We issued a notice of proposed
rulemaking (NPRM) to amend 14 CFR
part 39 to include an AD that would
apply to the specified products. That
NPRM was published in the Federal
Register on July 30, 2009 (74 FR 37965).
That NPRM proposed to correct an
unsafe condition for the specified
products. The MCAI states:
It has been found occurrences of main
landing gear (MLG) trailing arm pins broken
due to a fatigue mechanism induced by an
excessive torque applied during the
assemblage of auxiliary door support
attachment and consequent deformation of
the MLG trailing arm axle. A broken pin can
lead to loss of the MLG trailing arm axle,
disconnecting the trailing arm from the main
VerDate Nov<24>2008
15:08 Feb 03, 2010
Jkt 220001
*
*
*
*
*
Required actions include inspecting
for cracks, and, if necessary, replacing
the MLG trailing arm pin with a
serviceable pin; and modifying the MLG
auxiliary door mounting support. You
may obtain further information by
examining the MCAI in the AD docket.
EMBRAER has issued the following
revisions to the service information that
was referenced in the NPRM:
• Service Bulletin 145LEG–52–0014,
Revision 01, dated June 17, 2009, which
adds airplane serial number 145363.
• Service Bulletin 145LEG–32–0033,
Revision 01, dated June 18, 2009, which
changes the visual inspection to a
detailed inspection and includes the
option of using the same part number of
the landing gear trailing arm pin.
• Service Bulletin 145–32–0122,
Revision 01, dated April 29, 2009,
which changes the visual inspection to
a detailed inspection and includes the
option of using the same part number of
the landing gear trailing arm pin.
We have revised this final rule to cite
the revised service bulletins and to give
credit for accomplishment of the actions
done in accordance with the earlier
service information referred to in the
NPRM. We have also revised paragraph
(f)(1)(i) and Note 1 of this AD to clarify
that the inspection type is a detailed
inspection.
Comments
We gave the public the opportunity to
participate in developing this AD. We
considered the comments received.
Request for Clarification for a
Terminating Action
American Eagle Airlines (AEA)
requests that we add a statement to
paragraph (f) of this AD that clarifies
that the accomplishment of paragraph
(f) of this AD is a terminating action for
the requirements of this AD. AEA
suggests that it is not clear that no
further action is required after
inspection.
We agree to clarify the requirements.
We have added the phrase ‘‘one-time’’
before ‘‘detailed inspection’’ in
paragraph (f)(1)(i) of this AD to clarify
that no repeat inspections are required
after the initial inspection.
Request for Changing Compliance Time
AEA requests that we change the
compliance in paragraph (f)(1) of this
AD from ‘‘whichever occurs first’’ to
‘‘whichever occurs later.’’ AEA explains
that the actions specified in the NPRM
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require jacking the airplane and
compressing the landing gear, and that
specific tools required to complete these
tasks may not be stocked at every
maintenance base. AEA explains that
increasing the compliance time would
allow operators to arrange for having the
proper tools in their Main Base Visit
program.
While we agree that some of the tools
required to perform the tasks may not be
stocked at every maintenance base, we
do not agree with the commenter’s
request to extend the compliance time.
In developing an appropriate
compliance time for this action, we
considered the urgency associated with
the subject unsafe condition, and the
practical aspect of accomplishing the
required tasks within a period of time
that corresponds to the normal
scheduled maintenance for most
affected operators. However, according
to the provisions of paragraph (g) of the
final rule, we may approve requests to
adjust the compliance time if the
request includes data that prove that the
new compliance time would provide an
acceptable level of safety. We have not
changed the final rule in this regard.
Addition of an Airplane
Based on our original review of the
service information, we determined that
airplane serial number (S/N) 145363
was not affected. Therefore, the NPRM
proposed to exclude airplane S/N
145363 from the applicability. We have
now determined that airplane S/N
145363 should be included in the
applicability of this final rule, and we
have revised this final rule accordingly.
This airplane is not on the U.S. Register
and is known to be in compliance with
the requirements of this AD.
Explanation of Additional Changes
Made to This AD
We have revised this AD to identify
the legal name of the manufacturer as
published in the most recent type
certificate data sheet for the affected
airplane models.
Conclusion
We reviewed the available data,
including the comments received, and
determined that air safety and the
public interest require adopting the AD
with the changes described previously.
We determined that these changes will
not increase the economic burden on
any operator or increase the scope of the
AD.
Differences Between This AD and the
MCAI or Service Information
We have reviewed the MCAI and
related service information and, in
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Federal Register / Vol. 75, No. 23 / Thursday, February 4, 2010 / Rules and Regulations
general, agree with their substance. But
we might have found it necessary to use
different words from those in the MCAI
to ensure the AD is clear for U.S.
operators and is enforceable. In making
these changes, we do not intend to differ
substantively from the information
provided in the MCAI and related
service information.
We might also have required different
actions in this AD from those in the
MCAI in order to follow our FAA
policies. Any such differences are
highlighted in a NOTE within the AD.
Costs of Compliance
We estimate that this AD will affect
711 products of U.S. registry. We also
estimate that it will take about 2 workhours per product to comply with the
basic requirements of this AD. The
average labor rate is $80 per work-hour.
Required parts will cost about $240 per
product. Where the service information
lists required parts costs that are
covered under warranty, we have
assumed that there will be no charge for
these parts. As we do not control
warranty coverage for affected parties,
some parties may incur costs higher
than estimated here. Based on these
figures, we estimate the cost of this AD
to the U.S. operators to be $284,400, or
$400 per product.
Authority for This Rulemaking
cprice-sewell on DSK2BSOYB1PROD with RULES
Title 49 of the United States Code
specifies the FAA’s authority to issue
rules on aviation safety. Subtitle I,
section 106, describes the authority of
the FAA Administrator. ‘‘Subtitle VII:
Aviation Programs,’’ describes in more
detail the scope of the Agency’s
authority.
We are issuing this rulemaking under
the authority described in ‘‘Subtitle VII,
Part A, Subpart III, Section 44701:
General requirements.’’ Under that
section, Congress charges the FAA with
promoting safe flight of civil aircraft in
air commerce by prescribing regulations
for practices, methods, and procedures
the Administrator finds necessary for
safety in air commerce. This regulation
is within the scope of that authority
because it addresses an unsafe condition
that is likely to exist or develop on
products identified in this rulemaking
action.
Regulatory Findings
We determined that this AD will not
have federalism implications under
Executive Order 13132. This AD 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
VerDate Nov<24>2008
15:08 Feb 03, 2010
Jkt 220001
responsibilities among the various
levels of government.
For the reasons discussed above, I
certify this AD:
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. 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.
We prepared a regulatory evaluation
of the estimated costs to comply with
this AD and placed it in the AD docket.
Examining the AD Docket
You may examine the AD docket on
the Internet at https://
www.regulations.gov; or in person at the
Docket Operations office between 9 a.m.
and 5 p.m., Monday through Friday,
except Federal holidays. The AD docket
contains the NPRM, the regulatory
evaluation, any comments received, and
other information. The street address for
the Docket Operations office (telephone
(800) 647–5527) is in the ADDRESSES
section. Comments will be available in
the AD docket shortly after receipt.
List of Subjects in 14 CFR Part 39
Air transportation, Aircraft, Aviation
safety, Incorporation by reference,
Safety.
Adoption of the Amendment
Accordingly, under the authority
delegated to me by the Administrator,
the FAA amends 14 CFR part 39 as
follows:
■
PART 39—AIRWORTHINESS
DIRECTIVES
1. The authority citation for part 39
continues to read as follows:
■
Authority: 49 U.S.C. 106(g), 40113, 44701.
§ 39.13
[Amended]
2. The FAA amends § 39.13 by adding
the following new AD:
■
2010–03–07 Empresa Brasileira de
Aeronautica S.A. (EMBRAER):
Amendment 39–16191. Docket No.
FAA–2009–0659; Directorate Identifier
2009–NM–060–AD.
Effective Date
(a) This airworthiness directive (AD)
becomes effective March 11, 2010.
Affected ADs
(b) None.
Applicability
(c) This AD applies to Empresa Brasileira
de Aeronautica S.A. (EMBRAER) Model
EMB–135BJ, as identified in EMBRAER
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5687
Service Bulletin 145LEG–32–0033, dated
November 27, 2008; and Model EMB–135ER,
–135KE, –135KL, and –135LR airplanes, and
Model EMB–145, –145ER, –145MR, –145LR,
–145XR, –145MP, and –145EP airplanes, as
identified in EMBRAER Service Bulletin
145–32–0122, dated November 27, 2008;
certificated in any category.
Subject
(d) Air Transport Association (ATA) of
America Code 32: Landing Gear.
Reason
(e) The mandatory continuing
airworthiness information (MCAI) states:
It has been found occurrences of main
landing gear (MLG) trailing arm pins broken
due to a fatigue mechanism induced by an
excessive torque applied during the
assemblage of auxiliary door support
attachment and consequent deformation of
the MLG trailing arm axle. A broken pin can
lead to loss of the MLG trailing arm axle,
disconnecting the trailing arm from the main
strut, which affects the airplane
controllability on ground.
*
*
*
*
*
Required actions include inspecting for
cracks, and, if necessary, replacing the MLG
trailing arm pin with a serviceable pin; and
modifying the MLG auxiliary door mounting
support.
Actions and Compliance
(f) Unless already done, do the following
actions.
(1) Within 2,500 flight hours or 24 months
after the effective date of this AD, whichever
occurs first, do the actions specified in
paragraphs (f)(1)(i) and (f)(1)(ii) of this AD.
(i) Perform a one-time detailed inspection
for cracks on the MLG trailing arm pins, in
accordance with EMBRAER Service Bulletin
145–32–0122, Revision 01, dated April 29,
2009; or 145LEG–32–0033, Revision 01,
dated June 18, 2009; as applicable. If any
crack is found, before further flight, replace
the MLG trailing arm pin with a serviceable
pin, in accordance with EMBRAER Service
Bulletin 145–32–0122, Revision 01, dated
April 29, 2009; or 145LEG–32–0033, Revision
01, dated June 18, 2009; as applicable.
(ii) Prior to or concurrently with
accomplishing the inspection required by
paragraph (f)(1)(i) of this AD, modify the
MLG auxiliary door mounting support, in
accordance with EMBRAER Service Bulletin
145–52–0047, Revision 01, dated March 31,
2008; or 145LEG–52–0014, Revision 01,
dated June 17, 2009; as applicable.
Note 1: For the purposes of this AD, a
detailed inspection is: ‘‘An intensive
examination of a specific item, installation or
assembly to detect damage, failure or
irregularity. Available lighting is normally
supplemented with a direct source of good
lighting at an intensity deemed appropriate.
Inspection aids such as mirrors, magnifying
lenses, etc., may be necessary. Surface
cleaning and elaborate access procedures
may be required.’’
Note 2: For the purposes of this AD, a
‘‘serviceable’’ pin is a pin that has no
cracking.
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(2) Modifications and inspections
accomplished before the effective date of this
AD, according to a service bulletin listed in
Table 1 of this AD, are considered acceptable
for compliance with the corresponding action
specified in this AD.
TABLE 1—CREDIT SERVICE BULLETINS
Affected airplanes
Service Bulletin
Model EMB–135BJ airplanes .............................................
Model EMB–135BJ airplanes .............................................
Model EMB–135ER, –135KE, –135KL, and –135LR airplanes, and Model EMB–145, –145ER, –145MR,
–145LR, –145XR, –145MP, and –145EP airplanes.
Model EMB–135ER, –135KE, –135KL, and –135LR airplanes, and Model EMB–145, –145ER, –145MR,
–145LR, –145XR, –145MP, and –145EP airplanes.
EMBRAER Service Bulletin 145LEG–32–0033 .................
EMBRAER Service Bulletin 145LEG–52–0014 .................
EMBRAER Service Bulletin 145–32–0122 ........................
November 27, 2008.
October 28, 2008.
November 27, 2008.
EMBRAER Service Bulletin 145–52–0047 ........................
July 18, 2005.
FAA AD Differences
Note 3: This AD differs from the MCAI
and/or service information as follows:
ˆ
Agencia Nacional de Aviacao Civil (ANAC)
¸˜
Brazilian Airworthiness Directive 2009–02–
01, dated February 12, 2009, is applicable to
‘‘all EMB–145 and EMB–135 aircraft models
in operation.’’ However, this does not agree
with the service information specified in
Table 2 of this AD, which specifies that only
certain Model EMB–145 and EMB–135
Date
airplanes are affected and identifies them by
serial number. This AD is applicable only to
the airplanes listed in the applicable service
bulletins. This difference has been
coordinated with the ANAC.
TABLE 2—SERVICE INFORMATION
Document
EMBRAER
EMBRAER
EMBRAER
EMBRAER
Service
Service
Service
Service
Bulletin
Bulletin
Bulletin
Bulletin
Revision
145LEG–32–0033 ..................................................................................
145LEG–52–0014 ..................................................................................
145–32–0122 .........................................................................................
145–52–0047 .........................................................................................
Other FAA AD Provisions
(g) The following provisions also apply to
this AD:
(1) Alternative Methods of Compliance
(AMOCs): The Manager, International
Branch, ANM–116, Transport Airplane
Directorate, FAA, has the authority to
approve AMOCs for this AD, if requested
using the procedures found in 14 CFR 39.19.
Send information to ATTN: Todd Thompson,
Aerospace Engineer, International Branch,
ANM–116, Transport Airplane Directorate,
FAA, 1601 Lind Avenue, SW., Renton,
Washington 98057–3356; telephone (425)
227–1175; fax (425) 227–1149. Before using
any approved AMOC on any airplane to
which the AMOC applies, notify your
principal maintenance inspector (PMI) or
principal avionics inspector (PAI), as
appropriate, or lacking a principal inspector,
your local Flight Standards District Office.
The AMOC approval letter must specifically
reference this AD.
(2) Airworthy Product: For any requirement
in this AD to obtain corrective actions from
a manufacturer or other source, use these
actions if they are FAA-approved. Corrective
actions are considered FAA-approved if they
are approved by the State of Design Authority
(or their delegated agent). You are required
to assure the product is airworthy before it
is returned to service.
Date
01
01
01
01
June 18, 2009.
June 17, 2009.
April 29, 2009.
March 31, 2008.
(3) Reporting Requirements: For any
reporting requirement in this AD, under the
provisions of the Paperwork Reduction Act
(44 U.S.C. 3501 et seq.), the Office of
Management and Budget (OMB) has
approved the information collection
requirements and has assigned OMB Control
Number 2120–0056.
Related Information
ˆ
(h) Refer to MCAI Agencia Nacional de
Aviacao Civil Airworthiness Directive 2009–
¸˜
02–01, dated February 12, 2009; and the
service information contained in Table 3 of
this AD; for related information.
TABLE 3—RELATED SERVICE INFORMATION
Document
EMBRAER
EMBRAER
EMBRAER
EMBRAER
Service
Service
Service
Service
Bulletin
Bulletin
Bulletin
Bulletin
145LEG–32–0033 ..................................................................................
145LEG–52–0014 ..................................................................................
145–32–0122 .........................................................................................
145–52–0047 .........................................................................................
Material Incorporated by Reference
(i) You must use the service information
contained in Table 4 of this AD to do the
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Revision
Date
01
01
01
01
June 18, 2009.
June 17, 2009.
April 29, 2009.
March 31, 2008.
actions required by this AD, unless the AD
specifies otherwise.
TABLE 4—MATERIAL INCORPORATED BY REFERENCE
Document
EMBRAER
EMBRAER
EMBRAER
EMBRAER
Service
Service
Service
Service
VerDate Nov<24>2008
Bulletin
Bulletin
Bulletin
Bulletin
Revision
145LEG–32–0033 ..................................................................................
145LEG–52–0014 ..................................................................................
145–32–0122 .........................................................................................
145–52–0047 .........................................................................................
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Date
01
01
01
01
04FER1
June 18, 2009.
June 17, 2009.
April 29, 2009.
March 31, 2008.
Federal Register / Vol. 75, No. 23 / Thursday, February 4, 2010 / Rules and Regulations
(1) The Director of the Federal Register
approved the incorporation by reference of
this service information under 5 U.S.C.
552(a) and 1 CFR part 51.
(2) For service information identified in
this AD, contact Empresa Brasileira de
Aeronautica S.A. (EMBRAER), Technical
Publications Section (PC 060), Av. Brigadeiro
˜
Faria Lima, 2170—Putim—12227–901 Sao
Jose dos Campos—SP–BRASIL; telephone:
+55 12 3927–5852 or +55 12 3309–0732; fax:
+55 12 3927–7546; e-mail:
distrib@embraer.com.br; Internet: https://
www.flyembraer.com.
(3) You may review copies of the service
information at the FAA, Transport Airplane
Directorate, 1601 Lind Avenue, SW., Renton,
Washington. For information on the
availability of this material at the FAA, call
425–227–1221 or 425–227–1152.
(4) You may also review copies of the
service information that is incorporated by
reference 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: https://www.archives.gov/federal_register/
code_of_federal_regulations/
ibr_locations.html.
Issued in Renton, Washington, on January
22, 2010.
Ali Bahrami,
Manager, Transport Airplane Directorate,
Aircraft Certification Service.
[FR Doc. 2010–1930 Filed 2–3–10; 8:45 am]
BILLING CODE 4910–13–P
DEPARTMENT OF TRANSPORTATION
Federal Aviation Administration
14 CFR Part 39
[Docket No. FAA–2009–0889; Directorate
Identifier 2009–NE–35–AD; Amendment 39–
16189; AD 2010–03–06]
RIN 2120–AA64
Airworthiness Directives; Turbomeca
Arriel 2B and 2B1 Turboshaft Engines
AGENCY: Federal Aviation
Administration (FAA), DOT.
ACTION: Final rule.
We are adopting a new
airworthiness directive (AD) for the
products listed above. This AD results
from mandatory continuing
airworthiness information (MCAI)
issued by an aviation authority of
another country to identify and correct
an unsafe condition on an aviation
product. The MCAI describes the unsafe
condition as:
cprice-sewell on DSK2BSOYB1PROD with RULES
SUMMARY:
Several events of uncoupling of the lowpressure (LP) fuel pump impeller and the
high-pressure (HP) fuel pump shaft have
been reported on Arriel 2 engines which do
not incorporate Modification TU 147. In most
cases the ‘‘low fuel pressure switch’’
VerDate Nov<24>2008
15:08 Feb 03, 2010
Jkt 220001
enlightened, the pilot activated the aircraft
booster pump in accordance with the Flight
Manual Instructions and landed safely with
no other incident. One case, on a singleengine helicopter, led to a sudden engine
power loss. The uncoupling of the LP fuel
pump impeller and the HP fuel pump shaft
may lead to a limitation of engine power or,
at worst, an uncommanded in-flight
shutdown. On a single-engine helicopter, the
result may be an emergency autorotation
landing.
We are issuing this AD to prevent a
forced autorotation landing or an
accident.
DATES: This AD becomes effective
March 11, 2010. The Director of the
Federal Register approved the
incorporation by reference of certain
publications listed in this AD as of
March 11, 2010.
ADDRESSES: The Docket Operations
office is located at Docket Management
Facility, U.S. Department of
Transportation, 1200 New Jersey
Avenue, SE., West Building Ground
Floor, Room W12–140, Washington, DC
20590–0001.
Contact Turbomeca, 40220 Tarnos,
France; telephone (33) 05 59 74 40 00,
fax (33) 05 59 74 45 15, for the service
information identified in this AD.
FOR FURTHER INFORMATION CONTACT:
James Lawrence, Aerospace Engineer,
Engine Certification Office, FAA, Engine
and Propeller Directorate, 12 New
England Executive Park, Burlington, MA
01803; e-mail: james.lawrence@faa.gov;
telephone (781) 238–7176; fax (781)
238–7199.
SUPPLEMENTARY INFORMATION:
Discussion
We issued a notice of proposed
rulemaking (NPRM) to amend 14 CFR
part 39 to include an AD that would
apply to the specified products. That
NPRM was published in the Federal
Register on November 5, 2009 (74 FR
57277). That NPRM proposed to correct
an unsafe condition for the specified
products. The MCAI states that:
Several events of uncoupling of the LP fuel
pump impeller and the HP fuel pump shaft
have been reported on Arriel 2 engines which
do not incorporate Modification TU 147. In
most cases the ‘‘low fuel pressure switch’’
enlightened, the pilot activated the aircraft
booster pump in accordance with the Flight
Manual Instructions and landed safely with
no other incident. One case, on a singleengine helicopter, led to a sudden engine
power loss. The uncoupling of the LP fuel
pump impeller and the HP fuel pump shaft
may lead to a limitation of engine power or,
at worst, an uncommanded in-flight
shutdown. On a single-engine helicopter, the
result may be an emergency autorotation
landing.
PO 00000
Frm 00013
Fmt 4700
Sfmt 4700
5689
Comments
We gave the public the opportunity to
participate in developing this AD. We
considered the comment received.
One commenter, a private citizen,
states that the labor rate of $80 per
work-hour referenced in the proposed
AD is underestimated. He states that it
should be at least $95 per work-hour.
We partially agree. The work-hour
labor rate estimate is established by the
FAA’s Regulatory Analysis Division
which recently published a new rate;
$85 per work-hour. We changed the AD
to reflect this increase.
Conclusion
We reviewed the available data,
including the comment received, and
determined that air safety and the
public interest require adopting the AD
with the change described previously.
Differences Between This AD and the
MCAI or Service Information
The MCAI requires checking the
transmissible torque between the LP
pump impeller and the HP pump shaft
within 550 engine flight hours from the
effective date of the AD, but no later
than June 30, 2010.
This AD requires checking the
transmissible torque between the LP
pump impeller and the HP pump shaft
within 550 engine flight hours from the
effective date of the AD.
Costs of Compliance
Based on the service information, we
estimate that this AD will affect about
414 engines installed on helicopters of
U.S. registry. We also estimate that it
will take about 2.5 work-hours per
engine to comply with this AD. The
average labor rate is $85 per work-hour.
Replacement HP/LP pump metering
units (HMUs) will cost about $12,000
per engine. Based on these figures, if all
of the HMUs were to fail the check, we
estimate the cost of the AD to U.S.
operators to be $5,055,975.
Authority for This Rulemaking
Title 49 of the United States Code
specifies the FAA’s authority to issue
rules on aviation safety. Subtitle I,
section 106, describes the authority of
the FAA Administrator. ‘‘Subtitle VII:
Aviation Programs,’’ describes in more
detail the scope of the Agency’s
authority.
We are issuing this rulemaking under
the authority described in ‘‘Subtitle VII,
Part A, Subpart III, Section 44701:
General requirements.’’ Under that
section, Congress charges the FAA with
promoting safe flight of civil aircraft in
air commerce by prescribing regulations
for practices, methods, and procedures
E:\FR\FM\04FER1.SGM
04FER1
]]>Agencies
[Federal Register Volume 75, Number 23 (Thursday, February 4, 2010)]
[Rules and Regulations]
[Pages 5685-5689]
From the Federal Register Online via the Government Printing Office [www.gpo.gov]
[FR Doc No: 2010-1930]
-----------------------------------------------------------------------
DEPARTMENT OF TRANSPORTATION
Federal Aviation Administration
14 CFR Part 39
[Docket No. FAA-2009-0659; Directorate Identifier 2009-NM-060-AD;
Amendment 39-16191; AD 2010-03-07]
RIN 2120-AA64
Airworthiness Directives; Empresa Brasileira de Aeronautica S.A.
(EMBRAER) Model EMB-135BJ, -135ER, -135KE, -135KL, and -135LR
Airplanes; and EMB-145, -145ER, -145MR, -145LR, -145XR, -145MP, and -
145EP Airplanes
AGENCY: Federal Aviation Administration (FAA), Department of
Transportation (DOT).
ACTION: Final rule.
-----------------------------------------------------------------------
[[Page 5686]]
SUMMARY: We are adopting a new airworthiness directive (AD) for the
products listed above. This AD results from mandatory continuing
airworthiness information (MCAI) originated by an aviation authority of
another country to identify and correct an unsafe condition on an
aviation product. The MCAI describes the unsafe condition as:
It has been found occurrences of main landing gear (MLG)
trailing arm pins broken due to a fatigue mechanism induced by an
excessive torque applied during the assemblage of auxiliary door
support attachment and consequent deformation of the MLG trailing
arm axle. A broken pin can lead to loss of the MLG trailing arm
axle, disconnecting the trailing arm from the main strut, which
affects the airplane controllability on ground.
* * * * *
We are issuing this AD to require actions to correct the unsafe
condition on these products.
DATES: This AD becomes effective March 11, 2010.
The Director of the Federal Register approved the incorporation by
reference of certain publications listed in this AD as of March 11,
2010.
ADDRESSES: You may examine the AD docket on the Internet at https://www.regulations.gov or in person at the U.S. Department of
Transportation, Docket Operations, M-30, West Building Ground Floor,
Room W12-140, 1200 New Jersey Avenue, SE., Washington, DC.
FOR FURTHER INFORMATION CONTACT: Todd Thompson, Aerospace Engineer,
International Branch, ANM-116, Transport Airplane Directorate, FAA,
1601 Lind Avenue, SW., Renton, Washington 98057-3356; telephone (425)
227-1175; fax (425) 227-1149.
SUPPLEMENTARY INFORMATION:
Discussion
We issued a notice of proposed rulemaking (NPRM) to amend 14 CFR
part 39 to include an AD that would apply to the specified products.
That NPRM was published in the Federal Register on July 30, 2009 (74 FR
37965). That NPRM proposed to correct an unsafe condition for the
specified products. The MCAI states:
It has been found occurrences of main landing gear (MLG)
trailing arm pins broken due to a fatigue mechanism induced by an
excessive torque applied during the assemblage of auxiliary door
support attachment and consequent deformation of the MLG trailing
arm axle. A broken pin can lead to loss of the MLG trailing arm
axle, disconnecting the trailing arm from the main strut, which
affects the airplane controllability on ground.
* * * * *
Required actions include inspecting for cracks, and, if necessary,
replacing the MLG trailing arm pin with a serviceable pin; and
modifying the MLG auxiliary door mounting support. You may obtain
further information by examining the MCAI in the AD docket.
Relevant Service Information
EMBRAER has issued the following revisions to the service
information that was referenced in the NPRM:
Service Bulletin 145LEG-52-0014, Revision 01, dated June
17, 2009, which adds airplane serial number 145363.
Service Bulletin 145LEG-32-0033, Revision 01, dated June
18, 2009, which changes the visual inspection to a detailed inspection
and includes the option of using the same part number of the landing
gear trailing arm pin.
Service Bulletin 145-32-0122, Revision 01, dated April 29,
2009, which changes the visual inspection to a detailed inspection and
includes the option of using the same part number of the landing gear
trailing arm pin.
We have revised this final rule to cite the revised service
bulletins and to give credit for accomplishment of the actions done in
accordance with the earlier service information referred to in the
NPRM. We have also revised paragraph (f)(1)(i) and Note 1 of this AD to
clarify that the inspection type is a detailed inspection.
Comments
We gave the public the opportunity to participate in developing
this AD. We considered the comments received.
Request for Clarification for a Terminating Action
American Eagle Airlines (AEA) requests that we add a statement to
paragraph (f) of this AD that clarifies that the accomplishment of
paragraph (f) of this AD is a terminating action for the requirements
of this AD. AEA suggests that it is not clear that no further action is
required after inspection.
We agree to clarify the requirements. We have added the phrase
``one-time'' before ``detailed inspection'' in paragraph (f)(1)(i) of
this AD to clarify that no repeat inspections are required after the
initial inspection.
Request for Changing Compliance Time
AEA requests that we change the compliance in paragraph (f)(1) of
this AD from ``whichever occurs first'' to ``whichever occurs later.''
AEA explains that the actions specified in the NPRM require jacking the
airplane and compressing the landing gear, and that specific tools
required to complete these tasks may not be stocked at every
maintenance base. AEA explains that increasing the compliance time
would allow operators to arrange for having the proper tools in their
Main Base Visit program.
While we agree that some of the tools required to perform the tasks
may not be stocked at every maintenance base, we do not agree with the
commenter's request to extend the compliance time. In developing an
appropriate compliance time for this action, we considered the urgency
associated with the subject unsafe condition, and the practical aspect
of accomplishing the required tasks within a period of time that
corresponds to the normal scheduled maintenance for most affected
operators. However, according to the provisions of paragraph (g) of the
final rule, we may approve requests to adjust the compliance time if
the request includes data that prove that the new compliance time would
provide an acceptable level of safety. We have not changed the final
rule in this regard.
Addition of an Airplane
Based on our original review of the service information, we
determined that airplane serial number (S/N) 145363 was not affected.
Therefore, the NPRM proposed to exclude airplane S/N 145363 from the
applicability. We have now determined that airplane S/N 145363 should
be included in the applicability of this final rule, and we have
revised this final rule accordingly. This airplane is not on the U.S.
Register and is known to be in compliance with the requirements of this
AD.
Explanation of Additional Changes Made to This AD
We have revised this AD to identify the legal name of the
manufacturer as published in the most recent type certificate data
sheet for the affected airplane models.
Conclusion
We reviewed the available data, including the comments received,
and determined that air safety and the public interest require adopting
the AD with the changes described previously. We determined that these
changes will not increase the economic burden on any operator or
increase the scope of the AD.
Differences Between This AD and the MCAI or Service Information
We have reviewed the MCAI and related service information and, in
[[Page 5687]]
general, agree with their substance. But we might have found it
necessary to use different words from those in the MCAI to ensure the
AD is clear for U.S. operators and is enforceable. In making these
changes, we do not intend to differ substantively from the information
provided in the MCAI and related service information.
We might also have required different actions in this AD from those
in the MCAI in order to follow our FAA policies. Any such differences
are highlighted in a NOTE within the AD.
Costs of Compliance
We estimate that this AD will affect 711 products of U.S. registry.
We also estimate that it will take about 2 work-hours per product to
comply with the basic requirements of this AD. The average labor rate
is $80 per work-hour. Required parts will cost about $240 per product.
Where the service information lists required parts costs that are
covered under warranty, we have assumed that there will be no charge
for these parts. As we do not control warranty coverage for affected
parties, some parties may incur costs higher than estimated here. Based
on these figures, we estimate the cost of this AD to the U.S. operators
to be $284,400, or $400 per product.
Authority for This Rulemaking
Title 49 of the United States Code specifies the FAA's authority to
issue rules on aviation safety. Subtitle I, section 106, describes the
authority of the FAA Administrator. ``Subtitle VII: Aviation
Programs,'' describes in more detail the scope of the Agency's
authority.
We are issuing this rulemaking under the authority described in
``Subtitle VII, Part A, Subpart III, Section 44701: General
requirements.'' Under that section, Congress charges the FAA with
promoting safe flight of civil aircraft in air commerce by prescribing
regulations for practices, methods, and procedures the Administrator
finds necessary for safety in air commerce. This regulation is within
the scope of that authority because it addresses an unsafe condition
that is likely to exist or develop on products identified in this
rulemaking action.
Regulatory Findings
We determined that this AD will not have federalism implications
under Executive Order 13132. This AD 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.
For the reasons discussed above, I certify this AD:
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. 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.
We prepared a regulatory evaluation of the estimated costs to
comply with this AD and placed it in the AD docket.
Examining the AD Docket
You may examine the AD docket on the Internet at https://www.regulations.gov; or in person at the Docket Operations office
between 9 a.m. and 5 p.m., Monday through Friday, except Federal
holidays. The AD docket contains the NPRM, the regulatory evaluation,
any comments received, and other information. The street address for
the Docket Operations office (telephone (800) 647-5527) is in the
ADDRESSES section. Comments will be available in the AD docket shortly
after receipt.
List of Subjects in 14 CFR Part 39
Air transportation, Aircraft, Aviation safety, Incorporation by
reference, Safety.
Adoption of the Amendment
0
Accordingly, under the authority delegated to me by the Administrator,
the FAA amends 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.
Sec. 39.13 [Amended]
0
2. The FAA amends Sec. 39.13 by adding the following new AD:
2010-03-07 Empresa Brasileira de Aeronautica S.A. (EMBRAER):
Amendment 39-16191. Docket No. FAA-2009-0659; Directorate Identifier
2009-NM-060-AD.
Effective Date
(a) This airworthiness directive (AD) becomes effective March
11, 2010.
Affected ADs
(b) None.
Applicability
(c) This AD applies to Empresa Brasileira de Aeronautica S.A.
(EMBRAER) Model EMB-135BJ, as identified in EMBRAER Service Bulletin
145LEG-32-0033, dated November 27, 2008; and Model EMB-135ER, -
135KE, -135KL, and -135LR airplanes, and Model EMB-145, -145ER, -
145MR, -145LR, -145XR, -145MP, and -145EP airplanes, as identified
in EMBRAER Service Bulletin 145-32-0122, dated November 27, 2008;
certificated in any category.
Subject
(d) Air Transport Association (ATA) of America Code 32: Landing
Gear.
Reason
(e) The mandatory continuing airworthiness information (MCAI)
states:
It has been found occurrences of main landing gear (MLG)
trailing arm pins broken due to a fatigue mechanism induced by an
excessive torque applied during the assemblage of auxiliary door
support attachment and consequent deformation of the MLG trailing
arm axle. A broken pin can lead to loss of the MLG trailing arm
axle, disconnecting the trailing arm from the main strut, which
affects the airplane controllability on ground.
* * * * *
Required actions include inspecting for cracks, and, if
necessary, replacing the MLG trailing arm pin with a serviceable
pin; and modifying the MLG auxiliary door mounting support.
Actions and Compliance
(f) Unless already done, do the following actions.
(1) Within 2,500 flight hours or 24 months after the effective
date of this AD, whichever occurs first, do the actions specified in
paragraphs (f)(1)(i) and (f)(1)(ii) of this AD.
(i) Perform a one-time detailed inspection for cracks on the MLG
trailing arm pins, in accordance with EMBRAER Service Bulletin 145-
32-0122, Revision 01, dated April 29, 2009; or 145LEG-32-0033,
Revision 01, dated June 18, 2009; as applicable. If any crack is
found, before further flight, replace the MLG trailing arm pin with
a serviceable pin, in accordance with EMBRAER Service Bulletin 145-
32-0122, Revision 01, dated April 29, 2009; or 145LEG-32-0033,
Revision 01, dated June 18, 2009; as applicable.
(ii) Prior to or concurrently with accomplishing the inspection
required by paragraph (f)(1)(i) of this AD, modify the MLG auxiliary
door mounting support, in accordance with EMBRAER Service Bulletin
145-52-0047, Revision 01, dated March 31, 2008; or 145LEG-52-0014,
Revision 01, dated June 17, 2009; as applicable.
Note 1: For the purposes of this AD, a detailed inspection is:
``An intensive examination of a specific item, installation or
assembly to detect damage, failure or irregularity. Available
lighting is normally supplemented with a direct source of good
lighting at an intensity deemed appropriate. Inspection aids such as
mirrors, magnifying lenses, etc., may be necessary. Surface cleaning
and elaborate access procedures may be required.''
Note 2: For the purposes of this AD, a ``serviceable'' pin is a
pin that has no cracking.
[[Page 5688]]
(2) Modifications and inspections accomplished before the
effective date of this AD, according to a service bulletin listed in
Table 1 of this AD, are considered acceptable for compliance with
the corresponding action specified in this AD.
Table 1--Credit Service Bulletins
----------------------------------------------------------------------------------------------------------------
Affected airplanes Service Bulletin Date
----------------------------------------------------------------------------------------------------------------
Model EMB-135BJ airplanes............. EMBRAER Service Bulletin November 27, 2008.
145LEG-32-0033.
Model EMB-135BJ airplanes............. EMBRAER Service Bulletin October 28, 2008.
145LEG-52-0014.
Model EMB-135ER, -135KE, -135KL, and - EMBRAER Service Bulletin 145- November 27, 2008.
135LR airplanes, and Model EMB-145, - 32-0122.
145ER, -145MR, -145LR, -145XR, -
145MP, and -145EP airplanes.
Model EMB-135ER, -135KE, -135KL, and - EMBRAER Service Bulletin 145- July 18, 2005.
135LR airplanes, and Model EMB-145, - 52-0047.
145ER, -145MR, -145LR, -145XR, -
145MP, and -145EP airplanes.
----------------------------------------------------------------------------------------------------------------
FAA AD Differences
Note 3: This AD differs from the MCAI and/or service information
as follows: Ag[ecirc]ncia Nacional de Avia[ccedil][atilde]o Civil
(ANAC) Brazilian Airworthiness Directive 2009-02-01, dated February
12, 2009, is applicable to ``all EMB-145 and EMB-135 aircraft models
in operation.'' However, this does not agree with the service
information specified in Table 2 of this AD, which specifies that
only certain Model EMB-145 and EMB-135 airplanes are affected and
identifies them by serial number. This AD is applicable only to the
airplanes listed in the applicable service bulletins. This
difference has been coordinated with the ANAC.
Table 2--Service Information
----------------------------------------------------------------------------------------------------------------
Document Revision Date
----------------------------------------------------------------------------------------------------------------
EMBRAER Service Bulletin 145LEG-32-0033...... 01 June 18, 2009.
EMBRAER Service Bulletin 145LEG-52-0014...... 01 June 17, 2009.
EMBRAER Service Bulletin 145-32-0122......... 01 April 29, 2009.
EMBRAER Service Bulletin 145-52-0047......... 01 March 31, 2008.
----------------------------------------------------------------------------------------------------------------
Other FAA AD Provisions
(g) The following provisions also apply to this AD:
(1) Alternative Methods of Compliance (AMOCs): The Manager,
International Branch, ANM-116, Transport Airplane Directorate, FAA,
has the authority to approve AMOCs for this AD, if requested using
the procedures found in 14 CFR 39.19. Send information to ATTN: Todd
Thompson, Aerospace Engineer, International Branch, ANM-116,
Transport Airplane Directorate, FAA, 1601 Lind Avenue, SW., Renton,
Washington 98057-3356; telephone (425) 227-1175; fax (425) 227-1149.
Before using any approved AMOC on any airplane to which the AMOC
applies, notify your principal maintenance inspector (PMI) or
principal avionics inspector (PAI), as appropriate, or lacking a
principal inspector, your local Flight Standards District Office.
The AMOC approval letter must specifically reference this AD.
(2) Airworthy Product: For any requirement in this AD to obtain
corrective actions from a manufacturer or other source, use these
actions if they are FAA-approved. Corrective actions are considered
FAA-approved if they are approved by the State of Design Authority
(or their delegated agent). You are required to assure the product
is airworthy before it is returned to service.
(3) Reporting Requirements: For any reporting requirement in
this AD, under the provisions of the Paperwork Reduction Act (44
U.S.C. 3501 et seq.), the Office of Management and Budget (OMB) has
approved the information collection requirements and has assigned
OMB Control Number 2120-0056.
Related Information
(h) Refer to MCAI Ag[ecirc]ncia Nacional de
Avia[ccedil][atilde]o Civil Airworthiness Directive 2009-02-01,
dated February 12, 2009; and the service information contained in
Table 3 of this AD; for related information.
Table 3--Related Service Information
----------------------------------------------------------------------------------------------------------------
Document Revision Date
----------------------------------------------------------------------------------------------------------------
EMBRAER Service Bulletin 145LEG-32-0033...... 01 June 18, 2009.
EMBRAER Service Bulletin 145LEG-52-0014...... 01 June 17, 2009.
EMBRAER Service Bulletin 145-32-0122......... 01 April 29, 2009.
EMBRAER Service Bulletin 145-52-0047......... 01 March 31, 2008.
----------------------------------------------------------------------------------------------------------------
Material Incorporated by Reference
(i) You must use the service information contained in Table 4 of
this AD to do the actions required by this AD, unless the AD
specifies otherwise.
Table 4--Material Incorporated by Reference
----------------------------------------------------------------------------------------------------------------
Document Revision Date
----------------------------------------------------------------------------------------------------------------
EMBRAER Service Bulletin 145LEG-32-0033...... 01 June 18, 2009.
EMBRAER Service Bulletin 145LEG-52-0014...... 01 June 17, 2009.
EMBRAER Service Bulletin 145-32-0122......... 01 April 29, 2009.
EMBRAER Service Bulletin 145-52-0047......... 01 March 31, 2008.
----------------------------------------------------------------------------------------------------------------
[[Page 5689]]
(1) The Director of the Federal Register approved the
incorporation by reference of this service information under 5
U.S.C. 552(a) and 1 CFR part 51.
(2) For service information identified in this AD, contact
Empresa Brasileira de Aeronautica S.A. (EMBRAER), Technical
Publications Section (PC 060), Av. Brigadeiro Faria Lima, 2170--
Putim--12227-901 S[atilde]o Jose dos Campos--SP-BRASIL; telephone:
+55 12 3927-5852 or +55 12 3309-0732; fax: +55 12 3927-7546; e-mail:
distrib@embraer.com.br; Internet: https://www.flyembraer.com.
(3) You may review copies of the service information at the FAA,
Transport Airplane Directorate, 1601 Lind Avenue, SW., Renton,
Washington. For information on the availability of this material at
the FAA, call 425-227-1221 or 425-227-1152.
(4) You may also review copies of the service information that
is incorporated by reference 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: https://www.archives.gov/federal_register/code_of_federal_regulations/ibr_locations.html.
Issued in Renton, Washington, on January 22, 2010.
Ali Bahrami,
Manager, Transport Airplane Directorate, Aircraft Certification
Service.
[FR Doc. 2010-1930 Filed 2-3-10; 8:45 am]
BILLING CODE 4910-13-P
