
[Federal Register: August 5, 2010 (Volume 75, Number 150)]
[Rules and Regulations]               
[Page 47184-47190]
From the Federal Register Online via GPO Access [wais.access.gpo.gov]
[DOCID:fr05au10-6]                         

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DEPARTMENT OF TRANSPORTATION

Federal Aviation Administration

14 CFR Part 39

[Docket No. FAA-2008-1079; Directorate Identifier 2008-NM-116-AD; 
Amendment 39-16377; AD 2010-16-01]
RIN 2120-AA64

 
Airworthiness Directives; Empresa Brasileira de Aeronautica S.A. 
(EMBRAER) Model EMB-135ER, -135KE, -135KL, and -135LR Airplanes, and 
Model 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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[[Page 47185]]

SUMMARY: We are superseding an existing airworthiness directive (AD) 
for the products listed above. This AD results from mandatory 
continuing airworthiness information (MCAI) issued by an airworthiness 
authority of another country to identify and correct an unsafe 
condition on an aviation product. The earlier MCAI, Brazilian 
Airworthiness Directive 2007-08-02, effective September 27, 2007, 
describes the unsafe condition as:

    Fuel system reassessment, performed according to RBHA-E88/SFAR-
88 (Regulamento Brasileiro de Homologacao Aeronautica 88/Special 
Federal Aviation Regulation No. 88), requires the inclusion of new 
maintenance tasks in the Critical Design Configuration Control 
Limitations (CDCCL) and in the Fuel System Limitations (FSL), 
necessary to preclude ignition sources in the fuel system. * * *

    The new MCAI, Brazilian Airworthiness Directive 2009-08-03, 
effective August 20, 2009, describes the unsafe condition as:

    An airplane fuel tank systems review required by Special Federal 
Aviation Regulation Number 88 (SFAR 88) and ``RBHA Especial 
N[uacute]mero 88'' (RBHA E 88) has shown that additional maintenance 
and inspection instructions are necessary to maintain the design 
features required to preclude the existence or development of an 
ignition source within the fuel tanks of the airplane.

    We are issuing this AD to require actions to correct the unsafe 
condition on these products.

DATES: This AD becomes effective September 9, 2010.
    The Director of the Federal Register approved the incorporation by 
reference of certain publications listed in this AD as of September 9, 
2010.
    On July 30, 2008 (73 FR 35904, June 25, 2008), the Director of the 
Federal Register approved the incorporation by reference of a certain 
publication listed in this AD.

ADDRESSES: You may examine the AD docket on the Internet at http://
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 supplemental notice of proposed rulemaking (NPRM) to 
amend 14 CFR part 39 to include an AD that would apply to the specified 
products. That supplemental NPRM was published in the Federal Register 
on March 23, 2010 (75 FR 13689), and proposed to supersede AD 2008-13-
14, Amendment 39-15577 (73 FR 35904, June 25, 2008). That NPRM proposed 
to require revision of the airworthiness limitations section of the 
Instructions for Continued Airworthiness to incorporate new limitations 
for fuel tank systems. The earlier MCAI, Brazilian Airworthiness 
Directive 2007-08-02, effective September 27, 2007, describes the 
unsafe condition as:

    Fuel system reassessment, performed according to RBHA-E88/SFAR-
88 (Regulamento Brasileiro de Homologacao Aeronautica 88/Special 
Federal Aviation Regulation No. 88), requires the inclusion of new 
maintenance tasks in the Critical Design Configuration Control 
Limitations (CDCCL) and in the Fuel System Limitations (FSL), 
necessary to preclude ignition sources in the fuel system. * * *

    The new MCAI, Brazilian Airworthiness Directive 2009-08-03, 
effective August 20, 2009, describes the unsafe condition as:

    An airplane fuel tank systems review required by Special Federal 
Aviation Regulation Number 88 (SFAR 88) and ``RBHA Especial 
N[uacute]mero 88'' (RBHA E 88) has shown that additional maintenance 
and inspection instructions are necessary to maintain the design 
features required to preclude the existence or development of an 
ignition source within the fuel tanks of the airplane.

    The corrective action is revising the Airworthiness Limitations 
Section (ALS) of the Instructions for Continued Airworthiness (ICA) to 
incorporate new limitations for fuel tank systems. You may obtain 
further information by examining the MCAI in the AD docket.

Comments

    We gave the public the opportunity to participate in developing 
this AD. We considered the comments received.

Request To Allow Service Bulletin for Compliance

    ExpressJet Airlines and EMBRAER request that we revise the 
supplemental NPRM to consider Parker Service Bulletin 367-934-28-110, 
Revision A, dated December 19, 2006, as documentation for past 
compliance with the inspections and functional checks of the safe-life 
features.
    ExpressJet reports that, since early 2007, Parker has been 
referencing this service bulletin (by marking the inspected units with 
the service bulletin number and date of accomplishment) to show 
compliance with these inspections.
    EMBRAER notes that the fuel conditioning unit (FCU) and the ventral 
fuel conditioning unit (VFCU) are manufactured by Parker. To clarify 
which checks and inspections are to be performed on the FCU and VFCU, 
and ensure that the safe-life features are maintained, Parker has 
published Component Maintenance Manuals (CMMs) 28-41-36, Revision 4, 
dated March 13, 2009; 28-41-69, Revision 2, dated March 13, 2009; and 
28-41-80, dated April 3, 2009. Parker also issued Test Manual (TM) 
4213-025, ``Identicallity of Testing Performed--EMB-145 FCU CMM 28-41-
XX/Service Bulletin 367-934-28-110 for EMB-145 FAMILY--Fuel 
Conditioning Units,'' Revision A, dated October 13, 2009. EMBRAER 
states that the purpose of the TM is to describe the identicality of 
the testing performed on EMB-145 FCUs returned under the current 
service bulletin to the CMMs. The TM substantiates that all CUs already 
in compliance with the 10,000-flight-hour inspection in accordance with 
Parker Service Bulletin 367-934-28-110 have had the equivalent 
inspection to the safe-life testing required in the CMMs. EMBRAER 
reports that, when an FCU is returned to the field after having the 
service bulletin incorporated, the unit is returned to the customer 
with an FAA 8130-3 tag indicating that Parker Service Bulletin 367-934-
28-110 was accomplished, and the FCU is also marked accordingly.
    We agree with the request and the commenters' rationale. We have 
added a provision to this AD to consider FCUs inspected by Parker and 
marked with the service bulletin number and the date of accomplishment 
to be in compliance with the requirements of paragraph (g)(1) of this 
AD.

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 
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 a U.S. court of 
law. In making these changes, we do not intend to differ substantively

[[Page 47186]]

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 described in a separate paragraph of the AD. These requirements, if 
any, take precedence over the actions copied from the MCAI.

Costs of Compliance

    Based on the service information, we estimate that this AD affects 
about 41 products of U.S. registry.
    The actions that are required by AD 2008-13-14 and retained in this 
AD take about 1 work-hour per product, at an average labor rate of $85 
per work hour. Based on these figures, the estimated cost of the 
currently required actions is $85 per product.
    We estimate that it takes about 1 work-hour per product to comply 
with the new basic requirements of this AD. The average labor rate is 
$85 per work-hour. Based on these figures, we estimate the cost of the 
AD on U.S. operators to be $3,485, or $85 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 that this AD:
    (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.
    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 http://
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 removing Amendment 39-15577 (73 FR 
35904, June 25, 2008) and adding the following new AD:

2010-16-01 Empresa Brasileira de Aeronautica S.A. (EMBRAER): 
Amendment 39-16377. Docket No. FAA-2008-1079; Directorate Identifier 
2008-NM-116-AD.

Effective Date

    (a) This airworthiness directive (AD) becomes effective 
September 9, 2010.

Affected ADs

    (b) This AD supersedes AD 2008-13-14, Amendment 39-15577.

Applicability

    (c) This AD applies to Empresa Brasileira de Aeronautica S.A. 
(EMBRAER) Model EMB-135ER, -135KE, -135KL, and -135LR airplanes, and 
Model EMB-145, -145ER, -145MR, -145LR, -145XR, -145MP, and -145EP 
airplanes; certificated in any category; except for Model EMB-145LR 
airplanes modified according to Brazilian Supplemental Type 
Certificate 2002S06-09, 2002S06-10, or 2003S08-01.

    Note 1: This AD requires revisions to certain operator 
maintenance documents to include new inspections. Compliance with 
these inspections is required by 14 CFR 91.403(c). For airplanes 
that have been previously modified, altered, or repaired in the 
areas addressed by these inspections, the operator may not be able 
to accomplish the inspections described in the revisions. In this 
situation, to comply with 14 CFR 91.403(c), the operator must 
request approval for an alternative method of compliance according 
to paragraph (h) of this AD. The request should include a 
description of changes to the required inspections that will ensure 
the continued operational safety of the airplane.

Subject

    (d) Air Transport Association (ATA) of America Code 28: Fuel.

Reason

    (e) The mandatory continuing airworthiness information (MCAI), 
Brazilian Airworthiness Directive 2007-08-02, effective September 
27, 2007, states:
    Fuel system reassessment, performed according to RBHA-E88/SFAR-
88 (Regulamento Brasileiro de Homologacao Aeronautica 88/Special 
Federal Aviation Regulation No. 88), requires the inclusion of new 
maintenance tasks in the Critical Design Configuration Control 
Limitations (CDCCL) and in the Fuel System Limitations (FSL), 
necessary to preclude ignition sources in the fuel system. * * *
    The MCAI, Brazilian Airworthiness Directive 2009-08-03, 
effective August 20, 2009, states:
    An airplane fuel tank systems review required by Special Federal 
Aviation Regulation Number 88 (SFAR 88) and ``RBHA Especial 
N[uacute]mero 88'' (RBHA E 88) has shown that additional maintenance 
and inspection instructions are necessary to maintain the design 
features required to preclude the existence or development of an 
ignition source within the fuel tanks of the airplane.
    The corrective action is revising the Airworthiness Limitations 
Section (ALS) of the Instructions for Continued Airworthiness (ICA) 
to incorporate new limitations for fuel tank systems.

Restatement of Requirements of AD 2008-13-14

Actions and Compliance

    (f) Unless already done, do the following actions.
    (1) Before December 16, 2008, revise the ALS of the ICA to 
incorporate Section A2.5.2, Fuel System Limitation Items, of 
Appendix 2 of EMBRAER EMB135/ERJ140/EMB145 Maintenance Review Board 
Report MRB-145/1150, Revision 11, dated September 19, 2007, except 
as provided by paragraph (g) of this AD. Except as required by 
paragraph (g) of this AD, for all tasks identified in Section A2.5.2 
of Appendix 2 of EMBRAER EMB135/ERJ140/EMB145 Maintenance Review 
Board

[[Page 47187]]

Report MRB-145/1150, Revision 11, dated September 19, 2007, the 
initial compliance times start from the applicable times specified 
in Table 1 of this AD; and the repetitive inspections must be 
accomplished thereafter at the interval specified in Section A2.5.2 
of Appendix 2 of EMBRAER EMB135/ERJ140/EMB145 Maintenance Review 
Board Report MRB-145/1150, Revision 11, dated September 19, 2007, 
except as provided by paragraphs (f)(3) and (h) of this AD.

                                          Table 1--Initial Inspections
----------------------------------------------------------------------------------------------------------------
                                                                   Compliance time (whichever occurs later)
          Reference No.                   Description        ---------------------------------------------------
                                                                      Threshold               Grace period
----------------------------------------------------------------------------------------------------------------
28-11-00-720-001-A00.............  Functionally Check         Before the accumulation   Within 90 days after
                                    critical bonding           of 30,000 total flight    December 16, 2008.
                                    integrity of selected      hours.
                                    conduits inside the wing
                                    tank, Fuel Pump and FQIS
                                    connectors at tank wall
                                    by conductivity
                                    measurements.
28-17-01-720-001-A00.............  Functionally Check         Before the accumulation   Within 90 days after
                                    critical bonding           of 30,000 total flight    December 16, 2008.
                                    integrity of Fuel Pump,    hours.
                                    VFQIS and Low Level SW
                                    connectors at tank wall
                                    by conductivity
                                    measurements.
28-21-01-220-001-A00.............  Inspect Electric Fuel      Before the accumulation   Within 90 days after
                                    Pump Connector.            of 10,000 total flight    December 16, 2008.
                                                               hours.
28-23-03-220-001-A00.............  Inspect Pilot Valve        Before the accumulation   Within 90 days after
                                    harness inside the         of 20,000 total flight    December 16, 2008.
                                    conduit.                   hours.
28-23-04-220-001-A00.............  Inspect Vent Valve         Before the accumulation   Within 90 days after
                                    harness inside the         of 20,000 total flight    December 16, 2008.
                                    conduit.                   hours.
28-27-01-220-001-A00.............  Inspect Electric Fuel      Before the accumulation   Within 90 days after
                                    Transfer Pump Connector.   of 10,000 total flight    December 16, 2008.
                                                               hours.
28-41-03-220-001-A00.............  Inspect FQIS harness for   Before the accumulation   Within 90 days after
                                    clamp and wire jacket      of 20,000 total flight    December 16, 2008.
                                    integrity.                 hours.
28-41-07-220-001-A00.............  Inspect VFQIS and Low      Before the accumulation   Within 90 days after
                                    Level SW Harness for       of 20,000 total flight    December 16, 2008.
                                    clamp and wire jacket      hours.
                                    integrity.
----------------------------------------------------------------------------------------------------------------

    (2) Within 90 days after July 30, 2008 (the effective date of AD 
2008-13-14), revise the ALS of the ICA to incorporate items 1, 2, 
and 3 of Section A2.4, Critical Design Configuration Control 
Limitation (CDCCL), of Appendix 2 of EMBRAER EMB135/ERJ140/EMB145 
Maintenance Review Board Report MRB-145/1150, Revision 11, dated 
September 19, 2007.
    (3) After accomplishing the actions specified in paragraphs 
(f)(1) and (f)(2) of this AD, no alternative inspections, inspection 
intervals, or CDCCLs may be used unless the inspections, intervals, 
or CDCCLs are approved as an alternative method of compliance (AMOC) 
in accordance with the procedures specified in paragraph (h) of this 
AD.

New Requirements of This AD

Actions and Compliance

    (g) Unless already done, do the following actions.
    (1) Within 30 days after the effective date of this AD, revise 
the ALS of the ICA to incorporate Tasks 28-41-01-720-001-A01 and 28-
41-04-720-001-A01 identified in Table 2 of this AD into Section 
A2.5.2, Fuel System Limitation Items, of Appendix 2 of EMBRAER 
EMB135/ERJ140/EMB145 Maintenance Review Board Report MRB-145/1150. 
After incorporating Tasks 28-41-01-720-001-A01 and 28-41-04-720-001-
A01 identified in Table 2 of this AD, Tasks 28-41-01-720-001-A00 and 
28-41-04-720-001-A00 identified in Section A2.5.2 of Appendix 2 of 
EMBRAER EMB135/ERJ140/EMB145 Maintenance Review Board Report MRB-
145/1150, Revision 11, dated September 19, 2007, are no longer 
required. For the fuel limitation tasks identified in Table 2 of 
this AD, do the initial task at the later of the applicable 
``Threshold'' and ``Grace Period'' times specified in Table 2 of 
this AD. FCUs on which Parker has performed the initial tasks 
required by this paragraph before the effective date of this AD, and 
which are marked with ``Service Bulletin 367-934-28-110, Revision 
A'' and the date of accomplishment, are in compliance with the 
corresponding task required by this paragraph.

[[Page 47188]]



                                                                  Table 2--Inspections
--------------------------------------------------------------------------------------------------------------------------------------------------------
                                                                                          Compliance time (whichever occurs later)
             Task No.                          Description                  Part No.    -------------------------------------------- Repetitive interval
                                                                                               Threshold           Grace period        (not to exceed)
--------------------------------------------------------------------------------------------------------------------------------------------------------
28-41-01-720-001-A01.............  Perform an initial functional check     367-934-001   Before the            Within 90 days after  10,000 flight hours
                                    as shown in Testing and Fault                         accumulation of       the effective date    on the FCU since
                                    Isolation sections 1, 2, and 3; an                    10,000 total flight   of this AD.           the most recent
                                    external visual inspection as                         hours on the FCU.                           functional check.
                                    shown in the Check section 2; an
                                    internal visual inspection as
                                    shown in the Repair section 1; a
                                    functional check of the safe-life
                                    features as shown in Testing and
                                    Fault Isolation section 4; and a
                                    final functional check as shown in
                                    Testing and Fault Isolation
                                    sections 1, 2, and 3; of the fuel
                                    conditioning unit (FCU), in
                                    accordance with Parker Component
                                    Maintenance Manual (CMM) 28-41-36,
                                    Revision 4, dated March 13, 2009.
28-41-01-720-001-A01.............  Perform an initial functional check     367-934-002   Before the            Within 90 days after  10,000 flight hours
                                    as shown in Testing and Fault                         accumulation of       the effective date    on the FCU since
                                    Isolation sections 1, 2, and 3; an                    10,000 total flight   of this AD.           the most recent
                                    external visual inspection as                         hours on the FCU.                           functional check.
                                    shown in Check section 2; an
                                    internal visual inspection as
                                    shown in Repair section 1; a
                                    functional check of the safe-life
                                    features as shown in Testing and
                                    Fault Isolation section 4; and a
                                    final functional check as shown in
                                    Testing and Fault Isolation
                                    sections 1, 2, and 3; of the FCU,
                                    in accordance with Parker CMM 28-
                                    41-69, Revision 2, dated March 13,
                                    2009.
28-41-04-720-001-A01.............  Perform an initial functional check     367-934-005   Before the            Within 90 days after  10,000 flight hours
                                    as shown in Testing and Fault                         accumulation of       the effective date    on the VFCU since
                                    Isolation sections 1, 2, and 3; an                    10,000 total flight   of this AD.           the most recent
                                    external visual inspection as                         hours on the VFCU.                          functional check.
                                    shown in Check section 2; an
                                    internal visual inspection as
                                    shown in Repair section 1; a
                                    functional check of the safe-life
                                    features as shown in Testing and
                                    Fault Isolation section 4; and a
                                    final functional check as shown in
                                    Testing and Fault Isolation
                                    sections 1, 2, and 3; of the
                                    ventral FCU (VFCU), in accordance
                                    with Parker CMM 28-41-80, dated
                                    April 3, 2009.
--------------------------------------------------------------------------------------------------------------------------------------------------------


[[Page 47189]]

    (2) After accomplishing the actions specified in paragraphs 
(g)(1) of this AD, no alternative inspections or inspection 
intervals may be used unless the inspections or intervals are 
approved as an AMOC in accordance with the procedures specified in 
paragraph (h)(1) of this AD.

Explanation of CDCCL Requirements

    Note 2: Notwithstanding any other maintenance or operational 
requirements, components that have been identified as airworthy or 
installed on the affected airplanes before the revision of the ALS 
of the ICA, as required by paragraph (f)(3) of this AD, do not need 
to be reworked in accordance with the CDCCLs. However, once the ALS 
of the ICA has been revised, future maintenance actions on these 
components must be done in accordance with the CDCCLs.

FAA AD Differences

    Note 3: This AD differs from the MCAI and/or service information 
as follows:
    (1) The applicability of Brazilian AD 2009-08-03, effective 
August 20, 2009, includes Model EMB-135BJ airplanes. This AD does 
not include that model because that model is included in the 
applicability of FAA AD 2008-13-15, Amendment 39-15578. We are 
considering further rulemaking to revise AD 2008-13-15.
    (2) Although Brazilian Airworthiness Directive 2009-08-03, 
effective August 20, 2009, specifies both revising the airworthiness 
limitations and repetitively inspecting, this AD only requires the 
revision. Requiring a revision of the airworthiness limitations, 
rather than requiring individual repetitive inspections, requires 
operators to record AD compliance status only at the time they make 
the revision, rather than after every inspection. Repetitive 
inspections specified in the airworthiness limitations must be 
complied with in accordance with 14 CFR 91.403(c).

Other FAA AD Provisions

    (h) The following provisions also apply to this AD:
    (1) Alternative Methods of Compliance (AMOCs): The Manager, 
International Branch, ANM-116, 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

    (i) Refer to MCAI Brazilian Airworthiness Directives 2007-08-02, 
effective September 27, 2007, and 2009-08-03, effective August 20, 
2009; Sections A2.5.2, Fuel System Limitation Items, and A2.4, 
Critical Design Configuration Control Limitation (CDCCL), of 
Appendix 2 of EMBRAER EMB135/ERJ140/EMB145 Maintenance Review Board 
Report MRB-145/1150, Revision 11, dated September 19, 2007; and the 
Parker CMMs listed in Table 2 of this AD; for related information.

Material Incorporated by Reference

    (j) You must use the applicable service information contained in 
Table 3 of this AD to do the actions required by this AD, unless the 
AD specifies otherwise. (Parker Component Maintenance Manual 28-41-
36, Revision 4, dated March 13, 2009, contains an incorrect date on 
page 105; the correct date is March 13, 2009.) (Parker Component 
Maintenance Manual 28-41-69, Revision 2, dated March 13, 2009, 
contains the following errors: Page 105 contains an incorrect date; 
the correct date is March 13, 2009; and there are 3 pages identified 
with the same page number (i.e., LEP-2); the first page identified 
as LEP-2 (i.e., Sheet 1 of 2) should be identified as LEP-1 and the 
third page identified as LEP-2 (i.e., the blank page) should be 
identified as LEP-3.)

             Table 3--All Material Incorporated by Reference
------------------------------------------------------------------------
           Document                 Revision               Date
------------------------------------------------------------------------
Sections A2.5.2, Fuel System    11.............  September 19, 2007.
 Limitation Items, and A2.4,
 Critical Design Configuration
 Control Limitation (CDCCL),
 of Appendix 2 of EMBRAER
 EMB135/ERJ140/EMB145
 Maintenance Review Board
 Report MRB-145/1150.
Parker Component Maintenance    4..............  March 13, 2009.
 Manual 28-41-36.
Parker Component Maintenance    2..............  March 13, 2009.
 Manual 28-41-69.
Parker Component Maintenance    Original.......  April 3, 2009.
 Manual 28-41-80.
------------------------------------------------------------------------

    (1) The Director of the Federal Register approved the 
incorporation by reference of the service information contained in 
Table 4 of this AD under 5 U.S.C. 552(a) and 1 CFR part 51.

             Table 4--New Material Incorporated by Reference
------------------------------------------------------------------------
           Document                Revision                Date
------------------------------------------------------------------------
Parker Component Maintenance   4...............  March 13, 2009.
 Manual 28-41-36.
Parker Component Maintenance   2...............  March 13, 2009.
 Manual 28-41-69.
Parker Component Maintenance   Original........  April 3, 2009.
 Manual 28-41-80.
------------------------------------------------------------------------

    (2) The Director of the Federal Register previously approved the 
incorporation by reference of Sections A2.5.2, Fuel System 
Limitation Items, and A2.4, Critical Design Configuration Control 
Limitation (CDCCL), of Appendix 2 of EMBRAER EMB135/ERJ140/EMB145 
Maintenance Review Board Report MRB-145/1150, Revision 11, dated 
September 19, 2007, on July 30, 2008 (73 FR 35904, June 25, 2008).
    (3) For EMBRAER 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: http://www.flyembraer.com. For 
Parker service information identified in this AD, contact Parker 
Hannifin Corporation, Aerospace Group, Electronic Systems Division, 
300 Marcus Boulevard, Smithtown, New York

[[Page 47190]]

11787; telephone 631-231-3737; e-mail csoengineering@parker.com; 
Internet: http://www.parker.com.
    (4) 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.
    (5) 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 http://
www.archives.gov/federal_register/code_of_federal_regulations/
ibr_locations.html.

    Issued in Renton, Washington on July 16, 2010.
Ali Bahrami,
Manager, Transport Airplane Directorate, Aircraft Certification 
Service.
[FR Doc. 2010-18293 Filed 8-4-10; 8:45 am]
BILLING CODE 4910-13-P

