AD 2004-18-14 Airworthiness Directives; Airbus Model A330 and Model A340-200 and -300 Series Airplanes

Models named: A330, A340-200, -300 series. Read the applicability below — it usually turns on serial or part numbers too.

Model A330 and A340-200 and -300 series airplanes, certificated in any category; equipped with any spoiler servo control having part number (P/N) 1386A0000-01, 1386B0000-01, 1387A0000-01, or 1387B0000-01.

Required as indicated, unless accomplished previously. To ensure that the flightcrew is advised of the proper procedures in the event of uncommanded movement of a spoiler during flight, which could result in reduced controllability of the airplane and consequent significant increased fuel consumption during flight, and could result in an in-flight turn-back or diversion to an unscheduled airport destination, accomplish the following: Restatement of Requirements of AD 2002-16-12 Revision to Airplane Flight Manual (AFM) (a) Within 10 days after September 20, 2002 (the effective date of AD 2002-16-12, amendment 39-12851), revise the Limitations Section of the AFM by including the procedures listed in Figure 1 of this AD. This revision may be done by inserting a copy of the following Figure 1 into the AFM: Figure 1       “PROCEDURE: • If “F/CTL SPLR FAULT” is triggered —F/CTL S/D page CHECK • If the affected spoiler is not indicated extended amber: The spoiler is faulty in the retracted position. In such a case, the specific OEB procedure does not apply. —LDG DIST PROC Multiply the landing distance by 1.1 for 3 or 4 spoilers lost per wing. Multiply the landing distance by 1.2 for 5 or 6 spoilers lost per wing. APPLY • If the affected spoiler is indicated extended amber, apply the following procedure: IN CRUISE CAUTION Disregard FMGC fuel predictions, as they do not take the increase in fuel consumption into account. —FUEL CONSUMPTION INCREASE Apply 18.5% increase in the fuel consumption. APPLY —IN-FLIGHT TURN BACK/DIVERSION In-flight turn back or diversion may have to be considered due to this fuel penalty. CONSIDER —MAX ACHIEVABLE ALTITUDE DECREASE With the maximum spoiler deflection, the maximum altitude in ISA conditions may decrease by 4,500 feet. CONSIDER FOR LANDING —FOR LDG Use CONF 3 for landing to avoid possible buffeting, which, however, may be high depending on the failed spoiler. USE FLAP 3 —VAPP NORM —LDG DIST x 1.1” Note 1: When the procedure in paragraph (a) of this AD has been incorporated into the general revisions of the AFM, the general revisions may be incorporated into the AFM, provided the procedures in this AD and the general revisions are identical. This AD may then be removed from the AFM. New Requirements of This AD Initial Detailed Inspection/Functional Check (b) Within 700 flight hours after the effective date of this AD: Do a detailed inspection/functional check of the blocking function of the pressure relief valves (PRVs) of affected spoiler servo controls (SSCs) by doing all the actions in accordance with paragraphs 3.A., 3.B.(1)(a), 3.D., and 3.E. of the Accomplishment Instructions of Airbus Service Bulletin A330-27-3090 (for A330 series airplanes) or A340-27-4096 (for A340-200 and -300 series airplanes), both Revision 02, both dated August 1, 2002, as applicable. Note 2: For the purposes of this AD, a detailed inspection is: “An intensive examination of a specific item, installation, or assembly to detect damage, failure, or irregularity. Available lighting is normally supplemented with a direct source of good lighting at an intensity deemed appropriate. Inspection aids such as mirror, magnifying lenses, etc., may be necessary. Surface cleaning and elaborate procedures may be required.” Note 3: Liebherr Service Bulletin 1386A-27-03, Revision 1, dated February 4, 2002, is referenced in Airbus Service Bulletins A330-27-3090 and A340-27-4096, both Revision 02, as an additional source of service information for accomplishment of the inspections. Corrective Action (c) For airplanes having an affected SSC on which any malfunction is found during the inspection/functional check required by paragraph (a) of this AD: Before further flight, do the terminating action required by paragraph (e) of this AD for that SSC. (d) For airplanes having affected SSCs on which no malfunction is found during the inspection/functional check required by paragraph (a) of this AD: Repeat the inspection/functional check one time within 1,600 flight hours after accomplishment of the initial inspection required by paragraph (a) of this AD. If no malfunction is found, repeat the inspection/functional check thereafter at intervals not to exceed 2,400 flight hours, until accomplishment of the terminating action required by paragraph (e) of this AD. Terminating Action (e) Except as required by paragraph (c) of this AD: Within 13 months after the effective date of this AD, modify all affected SSCs by doing all the actions in accordance with the Accomplishment Instructions of Airbus Service Bulletin A330-27-3094 (for A330 series airplanes) or A340-27-4100 (for A340-200 and -300 series airplanes), both Revision 01, both dated August 1, 2002; as applicable. Modification of all affected SSCs terminates the requirements of paragraphs (a), (b), (c), and (d) of this AD. After the modification has been done, the previously required AFM revision may be removed. Note 4: Liebherr Service Bulletin 1386A-27-05, dated February 25, 2002, is referenced in Airbus Service Bulletins A330-27-3094 and A340-27-4100 as an additional source of service information for accomplishment of the modification. Previously Accomplished Actions (f) Accomplishment of the inspections in accordance with Airbus Service Bulletins A330-27-3090 and A340-27-4096, both dated September 28, 2001; or A340-27-4096, Revision 01, dated December 12, 2001; as applicable; is considered acceptable for compliance with the inspections required by this AD. (g) Airbus Service Bulletins A330-27-3090 and A340-27-4096, both dated August 1, 2002, specify to submit inspection results to the manufacturer, however; this AD does not include that requirement. Parts Installation (h) As of the effective date of this AD, no person may install on any airplane a spoiler servo control having P/N 1386A0000-01, 1386B0000-01, 1387A0000-01, or 1387B0000-01, unless it has been modified per paragraph (e) of this AD. Alternative Methods of Compliance (i) In accordance with 14 CFR 39.19, the Manager, International Branch, ANM-116, FAA, Transport Airplane Directorate, is authorized to approve alternative methods of compliance for this AD. Incorporation by Reference (j) The actions shall be done in accordance with the applicable service bulletins listed in Table 1 of this AD, unless the AD specifies otherwise. Table 1.—Materials Incorporated by Reference Airbus service bulletin Revision level Date A330-27-3090 02 Aug. 1, 2002. A330-27-3094 01 Aug. 1, 2002. A340-27-4096 02 Aug. 1, 2002. A340-27-4100 01 Aug. 1, 2002. The Director of the Federal Register approved the incorporation by reference of these documents in accordance with 5 U.S.C. 552(a) and 1 CFR part 51. You can get copies of the documents from Airbus, 1 Rond Point Maurice Bellonte, 31707 Blagnac Cedex, France. You can review copies at the Docket Management Facility, U.S. Department of Transportation, 400 Seventh Street SW., room PL-401, Nassif Building, Washington, DC; or at the National Archives and Records Administration (NARA). For information on the availability of this material at NARA, call (202) 741-6030, or go to: http://www.archives.gov/federal_register/code_of_federal_regulations/ibr_locations.html . Note 5: The subject of this AD is addressed in French airworthiness directives 2002-552(B) and 2002-553(B), both dated November 13, 2002. Effective Date (k) This amendment becomes effective on October 19, 2004. Issued in Renton, Washington, on August 31, 2004. Ali Bahrami, Manager, Transport Airplane Directorate, Aircraft Certification Service. [FR Doc. 04-20407 Filed 9-13-04; 8:45 am] BILLING CODE 4910-13-P