
[Federal Register Volume 76, Number 3 (Wednesday, January 5, 2011)]
[Rules and Regulations]
[Pages 437-441]
From the Federal Register Online via the Government Printing Office [www.gpo.gov]
[FR Doc No: 2010-32998]


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DEPARTMENT OF TRANSPORTATION

Federal Aviation Administration

14 CFR Part 39

[Docket No. FAA-2008-1080; Directorate Identifier 2008-NM-118-AD; 
Amendment 39-16554; AD 2011-01-01]
RIN 2120-AA64


Airworthiness Directives; Empresa Brasileira de Aeronautica S.A. 
(EMBRAER) Model EMB-135BJ Airplanes

AGENCY: Federal Aviation Administration (FAA), Department of 
Transportation (DOT).

ACTION: Final rule.

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SUMMARY: We are superseding an existing 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 earlier MCAI, Brazilian 
Airworthiness Directive 2007-08-01, 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 February 9, 2011.
    The Director of the Federal Register approved the incorporation by 
reference of certain publications listed in this AD as of February 9, 
2011.
    On July 30, 2008 (73 FR 35908, June 25, 2008), the Director of the 
Federal Register approved the incorporation by reference of certain 
other publications 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 13684), and proposed to supersede AD 2008-13-
15, Amendment 39-15578 (73 FR 35908, June 25, 2008). That supplemental 
NPRM proposed to correct an unsafe condition for the specified 
products. Brazilian Airworthiness Directive 2007-08-01, 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. * * *

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 comment received.

Request To Consider Additional Service Information

    The commenter, EMBRAER, requested that we revise the supplemental 
NPRM to include Parker Service Bulletin 367-934-28-110, Revision A, 
dated December 19, 2006, as acceptable for compliance with the proposed 
requirements. Parker makes the fuel conditioning unit (FCU) and ventral 
fuel conditioning unit (VFCU). Parker revised certain references within 
that service bulletin, clarifying all checks and inspections to be 
performed on the FCU and/or FVCU to ensure that the ``safe life'' 
features are maintained. Parker also published certain data 
substantiating that CUs in compliance with the 10,000-flight-hour 
inspection in accordance with Parker Service Bulletin 367-934-28-110, 
Revision A, dated December 19, 2006, have had the equivalent inspection 
to the safe-life

[[Page 438]]

testing required in the recently updated references. When an FCU is 
returned to the field after having that service bulletin incorporated, 
the unit is returned to the customer with an FAA 8130-3 tag indicating 
that the service bulletin was done, and the FCU is also marked to 
indicate that service bulletin.
    We agree with the request and the commenter's rationale. We have 
added a provision to paragraph (g)(1) of this AD to consider FCUs 
inspected by Parker and marked with Parker Service Bulletin 367-934-28-
110 and the date of accomplishment to be in compliance with the 
requirements of paragraph (g)(1) of this AD. We have also revised the 
previous NPRM by removing paragraph (1) of Note 3, which implied that 
the Parker service bulletin was not acceptable for compliance.

Additional Change to Supplemental NPRM

    We have revised paragraph (g)(1) and added new Note 2 in this final 
rule to clarify the requirements to incorporate new limitations for 
fuel tank systems.

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 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 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

    Based on the service information, we estimate that this AD affects 
about 43 products of U.S. registry.
    The actions that are required by AD 2008-13-15 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 
new requirements on U.S. operators to be $3,655, 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 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 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 39-15578 (73 FR 
35908, June 25, 2008) and adding the following new AD:

2011-01-01 Empresa Brasileira de Aeronautica S.A. (EMBRAER): 
Amendment 39-16554. Docket No. FAA-2008-1080; Directorate Identifier 
2008-NM-118-AD.

Effective Date

    (a) This airworthiness directive (AD) becomes effective February 
9, 2011.

Affected ADs

    (b) This AD supersedes AD 2008-13-15, Amendment 39-15578.

Applicability

    (c) This AD applies to all Empresa Brasileira de Aeronautica 
S.A. (EMBRAER) Model EMB-135BJ airplanes, certificated in any 
category.

    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)(1) 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.

[[Page 439]]

Reason

    (e) The mandatory continuing airworthiness information (MCAI), 
Brazilian Airworthiness Directive 2007-08-01, 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. * * *
And 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 2008-13-15

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 Legacy BJ--Maintenance Planning Guide MPG-
1483, Revision 5, dated March 22, 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 Legacy BJ--Maintenance Planning Guide MPG-1483, Revision 5, 
dated March 22, 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 Legacy BJ--
Maintenance Planning Guide MPG-1483, Revision 5, dated March 22, 
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             Within 90 days after
                                          critical bonding            accumulation of       December 16, 2008.
                                          integrity of selected       30,000 total flight
                                          conduits inside the wing    hours.
                                          tank, Fuel Pump and FQIS
                                          connectors at tank wall
                                          by conductivity
                                          measurements.
28-13-01-720-002-A00...................  Functionally Check Aft      Before the             Within 90 days after
                                          Fuel tank critical          accumulation of       December 16, 2008.
                                          bonding integrity of Fuel   30,000 total flight
                                          Pump, FQGS and Low Level    hours.
                                          SW connectors at tank
                                          wall by conductivity
                                          measurements.
28-15-04-720-001-A00...................  Functionally Check Fwd      Before the             Within 90 days after
                                          Fuel tank critical          accumulation of       December 16, 2008.
                                          bonding integrity of Fuel   30,000 total flight
                                          Pump, FQGS and Low Level    hours.
                                          SW connectors at tank
                                          wall by conductivity
                                          measurements.
28-21-01-220-001-A00...................  Inspect Wing Electric Fuel  Before the             Within 90 days after
                                          Pump Connector.             accumulation of       December 16, 2008.
                                                                      10,000 total flight
                                                                      hours.
28-23-03-220-001-A00...................  Inspect Pilot Valve         Before the             Within 90 days after
                                          harness inside the          accumulation of       December 16, 2008.
                                          conduit.                    20,000 total flight
                                                                      hours.
28-23-04-220-001-A00...................  Inspect Vent Valve harness  Before the             Within 90 days after
                                          inside the conduit.         accumulation of       December 16, 2008.
                                                                      20,000 total flight
                                                                      hours.
28-41-03-220-001-A00...................  Inspect FQIS harness for    Before the             Within 90 days after
                                          clamp and wire jacket       accumulation of       December 16, 2008.
                                          integrity.                  20,000 total flight
                                                                      hours.
28-46-02-220-001-A00...................  Aft Fuel Tank Internal      Before the             Within 90 days after
                                          Inspection: FQGS harness    accumulation of       December 16, 2008.
                                          and Low Level SW harness    20,000 total flight
                                          for clamp and wire jacket   hours.
                                          integrity.
28-46-04-220-001-A00...................  Fwd Fuel Tank Internal      Before the             Within 90 days after
                                          Inspection: FQGS harness    accumulation of       December 16, 2008.
                                          and Low Level SW harness    20,000 total flight
                                          for clamp and wire jacket   hours.
                                          integrity.
----------------------------------------------------------------------------------------------------------------

    (2) Within 90 days after July 30, 2008 (the effective date of AD 
2008-13-15), 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 Legacy BJ--Maintenance 
Planning Guide MPG-1483, Revision 5, dated March 22, 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, add 
Tasks 28-41-01-720-001-A01 and 28-46-05-720-001-A01 identified in 
table 2 of this AD to Section A2.5.2 of Appendix 2 of EMBRAER Legacy 
BJ--Maintenance Planning Guide MPG-1483. The operator can accomplish 
this by placing a copy of this AD into that section of the 
operator's MPG-1483. Once these tasks have been added, Tasks 28-41-
01-720-001-A00 and 28-46-05-720-001-A00 identified in Section A2.5.2 
of Appendix 2 of EMBRAER Legacy BJ--Maintenance Planning Guide MPG-
1483, Revision 5, dated March 22, 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. Fuel 
condition units (FCUs) inspected by Parker and marked with Parker 
Service Bulletin 367-934-28-110 and the date of accomplishment are 
considered to be in compliance with the requirements of this 
paragraph.

[[Page 440]]



                                                                  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              367-934-002  Before the              Within 90 days after    10,000 flight hours on
                                      functional check as shown                    accumulation of         the effective date of   the FCU since the
                                      in Testing and Fault                         10,000 total flight     this AD.                most recent
                                      Isolation sections 1, 2,                     hours on the FCU.                               functional check.
                                      and 3; an external visual
                                      inspection as 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 with Illustrated
                                      Parts List (CMM) 28-41-69,
                                      Revision 2, dated March
                                      13, 2009.
28-46-05-720-001-A01...............  Perform an initial              367-934-004  Before the              Within 90 days after    10,000 flight hours on
                                      functional check as shown                    accumulation of         the effective date of   the AFCU since the
                                      in Testing and Fault                         10,000 total flight     this AD.                most recent
                                      Isolation sections 1, 2,                     hours on the AFCU.                              functional check.
                                      and 3; an external visual
                                      inspection as 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 auxiliary
                                      fuel conditioning unit
                                      (AFCU), in accordance with
                                      Parker CMM 28-41-66,
                                      Revision 1, dated March
                                      13, 2009.
28-46-05-720-001-A01...............  Perform an initial              367-934-006  Before the              Within 90 days after    10,000 flight hours on
                                      functional check as shown                    accumulation of         the effective date of   the AFCU since the
                                      in Testing and Fault                         10,000 total flight     this AD.                most recent
                                      Isolation sections 1, 2,                     hours on the AFCU.                              functional check.
                                      and 3; an external visual
                                      inspection as 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 AFCU, in
                                      accordance with Parker CMM
                                      28-41-90, dated April 3,
                                      2009.
--------------------------------------------------------------------------------------------------------------------------------------------------------


    Note 2:  Once EMBRAER incorporates Tasks 28-41-01-720-001-A01 
and 28-46-05-720-001-A01 into Section A2.5.2 of Appendix 2 of 
EMBRAER Legacy BJ--Maintenance Planning Guide MPG-1483, either by a 
temporary revision or by a general revision of Section A2.5.2 of 
Appendix 2 of EMBRAER Legacy BJ--Maintenance Planning Guide MPG-
1483, this AD may be removed from Section A2.5.2 of that document.

    (2) After accomplishment of the actions specified in paragraph 
(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) of this AD.

Explanation of CDCCL Requirements

    Note 3:  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 paragraphs (f)(1), (f)(2), and (g)(1) 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 4:  This AD differs from the MCAI and/or service 
information as follows:
    (1) The applicability of Brazilian Airworthiness Directive 2009-
08-03, effective August 20, 2009, includes models other than Model 
EMB-135BJ airplanes. However, this AD does not include those other 
models. Those models are included in the applicability of FAA AD 
2008-13-14, Amendment 39-15577. We are considering further 
rulemaking to revise AD 2008-13-14.
    (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

[[Page 441]]

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: A federal agency may not conduct or 
sponsor, and a person is not required to respond to, nor shall a 
person be subject to a penalty for failure to comply with a 
collection of information subject to the requirements of the 
Paperwork Reduction Act unless that collection of information 
displays a current valid OMB Control Number. The OMB Control Number 
for this information collection is 2120-0056. Public reporting for 
this collection of information is estimated to be approximately 5 
minutes per response, including the time for reviewing instructions, 
completing and reviewing the collection of information. All 
responses to this collection of information are mandatory. Comments 
concerning the accuracy of this burden and suggestions for reducing 
the burden should be directed to the FAA at: 800 Independence Ave., 
SW., Washington, DC 20591, Attn: Information Collection Clearance 
Officer, AES-200.

Related Information

    (i) Refer to MCAI Brazilian Airworthiness Directives 2007-08-01, 
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 Legacy BJ--Maintenance Planning Guide MPG-
1483, Revision 5, dated March 22, 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.

                                 Table 3--All Material Incorporated by Reference
----------------------------------------------------------------------------------------------------------------
               Document                               Revision                               Date
----------------------------------------------------------------------------------------------------------------
Parker Component Maintenance Manual     2..................................  March 13, 2009.
 With Illustrated Parts List 28-41-69.
Parker Component Maintenance Manual     1..................................  March 13, 2009.
 With Illustrated Parts List 28-41-66.
Parker Component Maintenance Manual     Original...........................  April 3, 2009.
 With Illustrated Parts List
 28[dash]41[dash]90.
Sections A2.5.2, Fuel System            5..................................  March 22, 2007.
 Limitation Items, and A2.4, Critical
 Design Configuration Control
 Limitation (CDCCL), of Appendix 2 of
 EMBRAER Legacy BJ--Maintenance
 Planning Guide MPG-1483.
----------------------------------------------------------------------------------------------------------------

(Parker Component Maintenance Manual With Illustrated Parts List 28-
41-69, Revision 2, dated March 13, 2009, contains an incorrect date 
on page 105; the correct date is March 13, 2009.)
    (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 Manual     2..................................  March 13, 2009.
 With Illustrated Parts List 28-41-69.
Parker Component Maintenance Manual     1..................................  March 13, 2009.
 With Illustrated Parts List 28-41-66.
Parker Component Maintenance Manual     Original...........................  April 3, 2009.
 With Illustrated Parts List
 28[dash]41[dash]90.
----------------------------------------------------------------------------------------------------------------

    (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 Legacy BJ--Maintenance 
Planning Guide MPG-1483, Revision 5, dated March 22, 2007, on July 
30, 2008 (73 FR 35908, 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 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 December 17, 2010.
Ali Bahrami,
Manager, Transport Airplane Directorate, Aircraft Certification 
Service.
[FR Doc. 2010-32998 Filed 1-4-11; 8:45 am]
BILLING CODE 4910-13-P


