Airworthiness Directive · Amendment 39-16377 · Fuel
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
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.
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:
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 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.
| Description | Compliance time (whichever occurs later) | 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. |
| 28-17-01-720-001-A00 | Functionally Check critical bonding integrity of Fuel Pump, VFQIS 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 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. |
| 28-27-01-220-001-A00 | Inspect Electric Fuel Transfer Pump Connector | Before the accumulation of 10,000 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. |
| 28-41-07-220-001-A00 | Inspect VFQIS 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 2008-13-14), 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.
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.
| Description | Part No. | Compliance time (whichever occurs later) | 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 (CMM) 28-41-36, Revision 4, dated March 13, 2009 | 367-934-001 | 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. |
| 28-41-01-720-001-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 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 | 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. |
| 28-41-04-720-001-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 ventral FCU (VFCU), in accordance with Parker CMM 28-41-80, dated April 3, 2009 | 367-934-005 | Before the accumulation of 10,000 total flight hours on the VFCU | Within 90 days after the effective date of this AD | 10,000 flight hours on the VFCU since the most recent functional check. |
(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.
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.
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).
The aircraft, engines and makers this AD names, by the model designations in its text. A model listed here may still be outside the AD's serial ranges.
