Airworthiness Directive · Amendment 39-16554 · Fuel
Empresa Brasileira de Aeronautica S.A. (EMBRAER) Model EMB-135BJ Airplanes
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.
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:
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.
| 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. |
| 28-13-01-720-002-A00 | Functionally Check Aft 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. |
| 28-15-04-720-001-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 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, 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.
| 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 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 | Within 90 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.
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.
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).
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.
Aircraft
