Airworthiness Directive · Amendment 39-15417 · Airbus Model A330-200, A330-300, A340-200, and A340-300 Series Airplanes
Airbus Model A330-200, A330-300, A340-200, and A340-300 Series Airplanes
This AD applies to the airplanes identified in Table 1 of this AD, certificated in any category.
| Airbus model— | Excluding those airplanes on which any of the following— | Has been installed— |
|---|---|---|
| A330-200, A330-300, A340-200, and A340-300 series airplanes | Airbus Modification 50394, 52195, 53969, or 54833 | In production. |
| Airbus Service Bulletin A330-27-3128, dated May 3, 2005 | In service. | |
| Airbus Service Bulletin A340-27-4129, dated May 3, 2005 | In service. | |
| Airbus Service Bulletin A330-27-3136, Revision 01, dated July 19, 2006 | In service. | |
| Airbus Service Bulletin A340-27-4135, dated January 12, 2006 | In service. | |
| Goodrich Actuation Systems Service Bulletin SC4800-27-16, Revision 3, dated May 19, 2006 | In service. |
The FAA is superseding an existing airworthiness directive (AD), which applies to all Airbus Model A330-200, A330-300, A340-200, and A340-300 series airplanes. That AD currently requires a revision of the airplane flight manual to include procedures for a pre-flight elevator check before each flight, repetitive inspections for cracks of the attachment lugs of the mode selector valve position transducers on the elevator servo controls, and corrective actions if necessary. This new AD retains the existing requirements, reduces the applicability of the existing AD, and adds terminating actions. For certain airplanes, this AD requires upgrading the flight control primary computers. This AD results from a report of cracks of the transducer body at its attachment lugs. We are issuing this AD to ensure proper functioning of the elevator surfaces, and to prevent cracking of the attachment lugs, which could result in partial loss of elevator function and consequent reduced controllability of the airplane.
You are responsible for having the actions required by this AD performed within the compliance times specified, unless the actions have already been done.
Within 30 days after February 26, 2004 (the effective date of AD 2004-03-24), revise the Limitations section of the AFM to include a pre-flight elevator check, by including the following language. This may be done by inserting a copy of this AD into the applicable AFM. Thereafter perform the pre-flight check before every flight in accordance with the procedure.
Prior or During Taxi:
1. AT A CONVENIENT STAGE, PRIOR TO OR DURING TAXI, AND BEFORE ARMING THE AUTOBRAKE, THE PF SILENTLY APPLIES FULL LONGITUDINAL AND LATERAL SIDESTICK DEFLECTION. ON THE F/CTL PAGE, THE PNF CHECKS FULL TRAVEL OF ALL ELEVATORS AND ALL AILERONS, AND THE CORRECT DEFLECTION AND RETRACTION OF ALL SPOILERS. THE PNF CALLS OUT “FULL UP,” “FULL DOWN,” “NEUTRAL,” “FULL LEFT,” “FULL RIGHT,” “NEUTRAL,” AS EACH FULL TRAVEL/NEUTRAL POSITION IS REACHED. THE PF SILENTLY CHECKS THAT THE PNF CALLS ARE IN ACCORDANCE WITH THE SIDESTICK ORDER.
NOTE: IN ORDER TO REACH FULL TRAVEL, FULL SIDESTICK MUST BE HELD FOR A SUFFICIENT PERIOD OF TIME.
2. THE PF PRESSES THE PEDAL DISC PUSHBUTTON ON THE NOSEWHEEL TILLER, AND SILENTLY APPLIES FULL LEFT RUDDER, FULL RIGHT RUDDER, AND NEUTRAL. THE PNF CALLS OUT “FULL LEFT,” “FULL RIGHT,” “NEUTRAL,” AS EACH FULL TRAVEL/NEUTRAL POSITION IS REACHED.
3. THE PNF APPLIES FULL LONGITUDINAL AND LATERAL SIDESTICK DEFLECTION, AND SILENTLY CHECKS FULL TRAVEL AND CORRECT SENSE OF ALL ELEVATORS AND ALL AILERONS, AND CORRECT DEFLECTION AND RETRACTION OF ALL SPOILERS, ON THE ECAM F/CTL PAGE.”
Note 1: Full and complete elevator travel (position commanded) can be verified on the ECAM Flight Control Page. A determination of “correct sense” should include verification that there is complete and full motion of the sidesticks without binding.
(g) If any pre-flight check required by paragraph (f) of this AD reveals improper function of the elevator: Before further flight, perform the inspections required by paragraph (h) of this AD.
At the applicable time specified in paragraph (h)(1) or (h)(2) of this AD, except as required by paragraph (g) of this AD: Perform a dye penetrant inspection of the attachment lugs of the mode selector valve position transducers on each elevator servo control installed at damping positions 3CS1 and 3CS2. Do the inspection in accordance with the Accomplishment Instructions of Airbus Service Bulletin A330-27-3115 or A340-27-4119, both Revision 03, both including Appendix 01, both dated April 22, 2005, as applicable (in paragraphs (h) through (k) of this AD, referred to as “the service bulletin”). An inspection that is done before February 26, 2004, is acceptable for compliance with the initial inspection requirement of this paragraph, if the inspection is done in accordance with any of the following Airbus all operators telexes (AOTs): AOT A330-27A3115 or A340-27A4119, dated September 11, 2003, or Revision 01 of each AOT dated September 25, 2003; as applicable. Repeat the inspection thereafter at intervals not to exceed 350 flight cycles, until the applicable actions required by paragraphs (m) and (n) of this AD have been done.
(1) If the age of the servo control from the date of its first installation on the airplane can be positively determined: Do the inspection before the accumulation of 1,000 total flight cycles on the elevator servo control, or within 350 flight cycles on the servo control after February 26, 2004, whichever occurs later.
(2) If the age of the servo control from the date of its first installation on the airplane cannot be positively determined, do the inspection within 350 flight cycles on the servo control after February 26, 2004.
(3) Actions done before the effective date of this AD in accordance with Airbus Service Bulletin A330-27A3115 or A340-27A4119, both Revision 02, both including Appendix 01, both dated December 30, 2003, are acceptable for compliance with the corresponding requirements of this AD.
Note 2: The service bulletin refers to Goodrich Actuation Systems Inspection Service Bulletin SC4800-27-13 as an additional source of service information for the inspection.
(i) If any crack is found during any inspection required by paragraph (h) of this AD: Before further flight, replace either the transducer or servo control with a new part, in accordance with the service bulletin.
If any crack is found during any inspection required by paragraph (h) of this AD: Submit a report in accordance with the service bulletin at the applicable time(s) specified in paragraphs (j)(1) and (j)(2) of this AD: Submit reports to Airbus Customer Services, Engineering and Technical Support, Attention: J. Laurent, SEE53, fax +33/(0)5.61.93.44.25, Sita Code TLSBQ7X. Under the provisions of the Paperwork Reduction Act of 1980 (44 U.S.C. 3501 et seq.), the Office of Management and Budget (OMB) has approved the information collection requirements contained in this AD and has assigned OMB Control Number 2120-0056.
(1) For an initial inspection done before February 26, 2004: Submit the report within 30 days after February 26, 2004.
(2) For an inspection done after February 26, 2004: Submit the report within 30 days after the inspection.
As of February 26, 2004, no person may install the following part on any airplane: a transducer, or a transducer fitted on an elevator servo control, in the operator's inventory before September 25, 2003, unless that transducer has been inspected in accordance with the service bulletin and is crack free.
For Model A340-200 and -300 series airplanes: Within 2 months after the effective date of this AD, upgrade the three FCPCs in accordance with the Accomplishment Instructions of Airbus Service Bulletin A340-27-4131, dated February 21, 2005.
Note 3: Airbus Service Bulletin A340-27-4131 refers to Airbus Vendor Service Bulletins LA2K0-27-017 and LA2K1-27-009, both dated January 25, 2005, as additional sources of service information for upgrading the FCPCs.
Within 17 months after the effective date of this AD, do the actions specified in Table 2 of this AD.
| Inspect— | In accordance with the Accomplishment Instructions of Airbus Service Bulletin— | And if— | Then— | In accordance with— |
|---|---|---|---|---|
| (1) The elevator servo control to determine whether part number (P/N) SC4800-7A or -9 is installed | A330-27-3128, dated May 3, 2005 (for Model A330-200 and -300 series airplanes); or A340-27-4129, dated May 3, 2005 (for Model A340-200 and -300 series airplanes); as applicable | P/N SC4800-7A or -9 is found installed | Modify the four elevator servo controls | The Accomplishment Instructions of the applicable Airbus Service Bulletin. |
| (2) The elevator servo controls, P/N SC4800-10 and SC4800-11 to determine the serial number (S/N) installed | None | S/N 2324 or below is found installed | Replace the mode selector valve position transducer (MVT) of the elevator servo controls with a new MVT | Paragraphs 3.A.(2) and 3.B.(2) of the Accomplishment Instructions of Goodrich Actuation Systems Service Bulletin SC4800-27-16, Revision 3, dated May 19, 2006. |
Note 4: Airbus Service Bulletins A330-27-3128 and A340-27-4129 refer to Goodrich Actuation Systems Service Bulletin SC4800-27-16, Revision 3, dated May 19, 2006, as an additional source of service information for accomplishing the modification of the four elevator servo controls.
(n) Prior to or concurrently with the replacement, if required, specified in paragraph (m)(2) of this AD, replace the eye-end equipped with a self-lubricated bearing with a new eye-end equipped with a roller bearing, grease the new eye-end, and reidentify the servo control, in accordance with paragraph 2.A. of the Accomplishment Instructions of TRW Service Bulletin SC4800-27-34-09, Revision 1, dated November 9, 2001.
(o) Accomplishing all of the applicable actions required by paragraphs (m) and (n) of this AD constitutes terminating action for paragraphs (f) through (k) of this AD.
