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 toparagraph (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.
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 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 Appendix2 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 critical bonding integrity of selected conduits inside the wing tank, Fuel Pump and FQIS connectors at tank wall by conductivity measurements.
Before the accumulation of 30,000 total flight hours.
Within 90 days after December 16, 2008.
28 13 01 720 002 A00
Functionally Check Aft Fuel tank critical bonding integrity of Fuel Pump, FQGS and LowLevel SW connectors at tank wall by conductivity measurements.
Before the accumulation of 30,000 total flight hours.
Within 90 days after December 16, 2008.
28 15 04 720 001 A00
Functionally Check Fwd Fuel tank critical bonding integrity of Fuel Pump, FQGS and Low Level SW connectors at tank wall by conductivity measurements.
Before the accumulation of 30,000 total flight hours.
Within 90 days after December 16, 2008.
28 21 01 220 001 A00
Inspect Wing Electric Fuel Pump Connector
Before the accumulation of 10,000 total flight hours.
Within 90 days after December 16, 2008.
28 23 03 220 001 A00
Inspect Pilot Valve harness inside the conduit
Before the accumulation of 20,000 total flight hours.
Within 90 days after December 16, 2008.
28 23 04 220 001 A00
Inspect Vent Valve harness inside the conduit
Before the accumulation of 20,000 total flight hours.
Within 90 days after December 16, 2008.
28 41 03 220 001 A00
Inspect FQIS harness for clamp and wire jacket integrity.
Before the accumulation of 20,000 total flight hours.
Within 90 days after December 16, 2008.
28 46 02 220 001 A00
Aft Fuel Tank Internal Inspection: FQGS harness and Low Level SW harness for clamp and wire jacket integrity.
Before the accumulation of 20,000 total flight hours.
Within 90 days after December 16, 2008.
28 46 04 220 001 A00
Fwd Fuel Tank Internal Inspection: FQGS harness and Low Level SW harness for clamp and wire jacket integrity.
Before the accumulation of 20,000 total flight hours.
Within 90 days after December 16, 2008.
(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 thisAD, 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.
Table 2--Inspections
Compliance time (whichever occurs later)
Task No.
Description
Part No.
Threshold
Grace period
Repetitive interval (not to exceed)
28 41 01 720 001 A01.
Perform an initial functional check as shown in Testing and Fault Isolation sections 1, 2, 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.
367 934 002
Before the accumulation of 10,000 total flight hours on the FCU.
Within 90 days after the effective date of this AD.
10,000 flight hours on the FCU since the most recent functional check.
28 46 05 720 001 A01.
Perform an initial functional check as shown in Testing and Fault Isolation sections 1, 2, 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.
367 934 004
Before the accumulation of 10,000 total flight hours on the AFCU.
Within90 days after the effective date of this AD.
10,000 flight hours on the AFCU since the most recent functional check.
28 46 05 720 001 A01.
Perform an initial functional check as shown in Testing and Fault Isolation sections 1, 2, 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.
367 934 006
Before the accumulation of 10,000 total flight hours on the AFCU.
Within 90 days after the effective date of this AD.
10,000 flight hours on the AFCU since the most recent functional check.
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 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 With Illustrated Parts List 28 41 69
2
March 13, 2009.
Parker Component Maintenance Manual With Illustrated Parts List 28 41 66
1
March 13, 2009.
Parker Component Maintenance Manual With Illustrated Parts List 28-41-90
Original
April 3, 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.
5
March 22, 2007.
(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 With IllustratedParts List 28 41 69
2
March 13, 2009.
Parker Component Maintenance Manual With Illustrated Parts List 28 41 66
1
March 13, 2009.
Parker Component Maintenance Manual With Illustrated Parts List 28-41-90
Original
April 3, 2009.
(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.