Airworthiness Directive · Amendment 39-17029 · Hydraulic power
Airbus Airplanes
This AD applies to Airbus Model A310-203, -204, -221, -222, -304, -322, -324, and -325 airplanes, certificated in any category, all serial numbers.
We are adopting a new airworthiness directive (AD) for all Airbus Model A310 series airplanes. This AD was prompted by a report of an electrical arc and hydraulic haze in the wheel bay of the left-hand main landing gear (MLG) possibly resulting from chafing between the hydraulic high pressure hose and electrical wiring of the green electrical motor pump (EMP). This AD requires temporarily prohibiting in-flight use of the green EMPs; temporarily revising the airplane flight manual (AFM) limitations section; temporarily installing a placard in the cockpit overhead panel; doing a one-time general visual inspection for correct condition and installation of hydraulic pressure hoses, electrical conduits, feeder cables, and associated clamping devices; and corrective action if necessary. We are issuing this AD to detect and correct chafing of hydraulic pressure hoses and electrical wiring of the green EMPs, which in combination with a system failure, could cause an uncontrolled and undetected fire in the MLG bay.
You are responsible for having the actions required by this AD performed within the compliance times specified, unless the actions have already been done.
For all airplanes, as of the effective date of this AD, the in-flight use of green EMPs is prohibited. Before the next flight, do the actions specified in paragraphs (g)(1) and (g)(2) of this AD.
(1) Install in the cockpit on the hydraulic power overhead panel 427VU, a locally manufactured self-adhesive placard temporarily prohibiting the in-flight use of the green EMPs, in accordance with the instructions in Airbus All Operators Telex A310-29A2101, Revision 01, dated April 12, 2011 (for airplanes equipped with EATON (formerly VICKERS) hydraulic EMPs); or Airbus All Operators Telex A310-29A2102, dated April 12, 2011 (for airplanes equipped with PARKER (formerly ABEX) hydraulic EMPs).
(2) Revise the Limitations section of the applicable AFM to prohibit the in-flight use of the green EMPs. This may be accomplished by inserting a copy of this AD into the Limitations section of the AFM.
Within 500 flight hours or 4 months after the effective date of this AD, whichever occurs first, do a one-time general visual inspection for correct condition (i.e., no damage and no chafing) and correct installation of the hydraulic pressure hoses, electrical conduits, feeder cables, and associated clamping devices at frame 54, as well as the electrical conduits and feeder cables underneath the clamps (including removal of the concerned clamps), in accordance with the instructions in Airbus All Operators Telex A310-29A2101, Revision 01, dated April 12, 2011 (for airplanes equipped with EATON (formerly VICKERS) hydraulic EMPs); or Airbus All Operators Telex A310-29A2102, dated April 12, 2011 (for airplanes equipped with PARKER (formerly ABEX) hydraulic EMPs). If any incorrect installation is found, before further flight, install the affected parts correctly, in accordance with Airbus All Operators Telex A310-29A2101, Revision 01, dated April 12, 2011 (for airplanes equipped with EATON (formerly VICKERS) hydraulic EMPs); or Airbus All Operators Telex A310-29A2102, dated April 12, 2011 (for airplanes equipped with PARKER (formerly ABEX) hydraulic EMPs).
(1) If any damage or chafing marks are found during the inspection required by paragraph (h) of this AD, before further flight, replace or repair the affected parts (hydraulic pressure hoses, electrical conduits, feeder cables, clamps, and spacer, if installed), in accordance with the instructions in Airbus All Operators Telex A310-29A2101, Revision 01, dated April 12, 2011 (for airplanes equipped with EATON (formerly VICKERS) hydraulic EMPs); or Airbus All Operators Telex A310-29A2102, dated April 12, 2011 (for airplanes equipped with PARKER (formerly ABEX) hydraulic EMPs).
(2) Before further flight after compliance with the requirements of paragraph (h) of this AD, as applicable, remove the placard required by paragraph (g)(1) of this AD; and remove the revision of the Limitations section of the AFM, as required by paragraph (g)(2) of this AD; from the airplane and the AFM, respectively.
