Airworthiness directives › 2012-25-10
AD 2012-25-10 Airworthiness Directives; Airbus Airplanes
Models named: A330-301, -302, -303, -321, -322, -323, -341, -342, -343, A340-211. Read the applicability below — it usually turns on serial or part numbers too.
Applicability*9
This AD applies to all Airbus Model A330-301, -302, -303, -321, -322, -323, -341, -342, and -343 airplanes; and Model A340-211, -212, -213, -311, -312, and -313 airplanes; certificated in any category; all manufacturer serial numbers.
Compliance
You are responsible for having the actions required by this AD performed within the compliance times specified, unless the actions have already been done.
Required actions
Within 90 days after the effective date of this AD: Inspect to determine the part number (P/N) of all SSCs installed, in accordance with Airbus All Operators Telex (AOT) A330-27A3185 (for Model A330-300 series airplanes) or A340-27A4181 (for Model A340-200 and -300 series airplanes), both dated January 4, 2012. A review of airplane maintenance records is acceptable in lieu of the inspection to identify the part number of the SSC installed, provided that part number can be conclusively determined from that review. (1) For any SSC having P/N MZ4339390-12 or P/N MZ4306000-12 (MZ-type): Within 90 days after identification of the part, perform an operational test of the hydraulic locking function at each position fitted with an MZ-type SSC, in accordance with Airbus AOT A330-27A3185 (for Model A330-300 series airplanes) or A340-27A4181 (for Model A340-200 and -300 series airplanes), both dated January 4, 2012. (2) If any discrepancy is detected during the operational test specified in paragraph (g)(1) of this AD, or if the test fails, before further flight, replace the affected SSC with a new or serviceable SSC, in accordance with Airbus AOT A330-27A3185 (for Model A330-300 series airplanes) or A340-27A4181 (for Model A340-200 and -300 series airplanes), both dated January 4, 2012.
Unsafe condition
This AD was prompted by reports that, during flight test, several spoiler servo-controls (SSCs) did not remain locked in the retracted position (hydraulic locking function) after manual depressurization of the corresponding hydraulic circuit. Loss of that locking function—which is ensured by a blocking valve—was caused by an internal leak from a sheared seal on the blocking valve. We are issuing this AD to prevent loss of the hydraulic locking function during take-off and go-around phases, which, in combination with malfunction of one engine, could result in reduced controllability of the airplane.
Affected ADs
None.
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The directive text above is reproduced from the Federal Register, a work of the United States government and in the public domain. The separation into applicability, compliance and required actions is TrackAD's.*1