Airworthiness Directive · Amendment 39-11903 · Empresa Brasileira de Aeronautica S.A. (EMBRAER) Model EMB-135 and EMB-145 Series Airplanes
Empresa Brasileira de Aeronautica S.A. (EMBRAER) Model EMB-135 and EMB-145 Series Airplanes
Superseded. A later AD replaced this one: AD 2005-08-02. Comply with the one in force.
All Model EMB-135 and EMB-145 series airplanes, certificated in any category.
Note 1: This AD applies to each airplane identified in the preceding applicability provision, regardless of whether it has been modified, altered, or repaired in the area subject to the requirements of this AD. For airplanes that have been modified, altered, or repaired so that the performance of the requirements of this AD is affected, the owner/operator must request approval for an alternative method of compliance in accordance with paragraph (e) of this AD. The request should include an assessment of the effect of the modification, alteration, or repair on the unsafe condition addressed by this AD; and, if the unsafe condition has not been eliminated, the request should include specific proposed actions to address it.
This amendment adopts a new airworthiness directive (AD) that is applicable to all EMBRAER Model EMB-135 and EMB-145 series airplanes. This action requires repetitive inspections of the electrical connectors of the electric fuel pumps to detect discrepancies, and follow-on corrective actions. This action is necessary to prevent failure of the electrical connectors of the fuel pumps, which could result in fuel leakage from the connectors or electrical arcing across the connector pins of the pump, and consequent fuel fire or explosion.
To prevent failure of the electrical connectors of the fuel pumps, which could result in fuel leakage from the connectors or electrical arcing across the connector pins of the pump, and consequent fuel fire or explosion; accomplish the following:
(a) Perform a general visual inspection of the electrical connectors of the fuel pumps in the right- and left-hand wings to detect discrepancies (including blackened connector pins, damage to elastomeric insert, cracks, erosion or charring), in accordance with Embraer Alert Service Bulletin S.B. 145-28-A013, dated August 16, 2000, at the times specified in paragraphs (a)(1), (a)(2), and (a)(3) of this AD, as applicable. Repeat the inspection thereafter at intervals not to exceed 400 flight hours.
(1) For airplanes having 1,200 total flight hours or less as of the effective date of this AD: Prior to the accumulation of 1,600 total flight hours.
(2) For airplanes having more than 1,200 total flight hours, but less than 4,000 total flight hours as of the effective date of this AD: Within 400 flight hours after the effective date of this AD.
(3) For airplanes having 4,000 total flight hours or more as of the effective date of this AD: Prior to the accumulation of 4,400 total flight hours or within 50 flight hours after the effective date of this AD, whichever occurs later.
(b) The inspection required by paragraph (a) of this AD applies to the six electric fuel pumps in the right- and left-hand wings (three pumps in each wing). For pump replacement planning purposes, the airplane may be operated in accordance with the provisions and limitations specified in an operator's FAA-approved MMEL, provided that no more than one fuel pump on each wing on the airplane is inoperative.
Note 2: When operating under the MMEL, the unusable fuel quantity as referenced in the Limitations Section of the appropriate FAA-approved Airplane Flight Manual (AFM) must be complied with.
(c) If any discrepancy (including blackened connector pins, damage to elastomeric insert, cracks, erosion or charring) is detected after accomplishment of any inspection required by paragraph (a) of this AD: Before further flight, replace the fuel pump and its mating airplane connector in accordance with Embraer Alert Service Bulletin S.B. 145-28-A013, dated August 16, 2000.
(d) After accomplishment of the replacement required by paragraph (c) of this AD, before further flight: Perform a general visual inspection of the electrical connectors adjacent to the fuel pump to detect damage (visible cracks, erosion or charring), in accordance with Embraer Alert Service Bulletin S.B. 145-28-A013, dated August 16, 2000, and accomplish the requirements in paragraph (c)(1) or (c)(2) of this AD, as applicable.
(1) If any damage is detected, before further flight, replace the connectors with new ones in accordance with the alert service bulletin.
(2) If no damage is detected, before further flight, replace only the socket contacts with new contacts in accordance with the alert service bulletin.
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
