98-24-07: Rudder Pedal Footrest

98-24-07 EXTRA FLUGZEUGBAU GMBH: Amendment 39-10893; Docket No. 98-CE-53-AD. Applicability: The following models and serial numbers, certificated in any category: Model Serial Number EA-300 all serial numbers, if factory equipped or retrofitted with the electric actuated rudder pedal adjustment that was produced prior to November 1995. EA-300S 001 through 028 EA-300L 001 through 015 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 (f) 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. Compliance: Required as follows: 1. Inspections specified in this AD are required within the next 50 hours time-in-service (TIS) after the effective date of this AD, unless already accomplished, and thereafter at intervals not to exceed 50 hours TIS. 2. Replacements or other follow-on corrective actions specified in this AD are required prior to further flight after the inspection when the discrepancy was found. To prevent failure of the rudder pedal footrest caused by overloading the rudder pedal safety control stop, which could result in loss of directional control of the airplane, accomplish the following: (a) Inspect the rudder pedal alignment in accordance with Figure 1 and Figure 2 and the Instructions Part I.1 section of EXTRA Service Bulletin No. 300-3-95, Issue: B, dated May 12, 1998. If not aligned,prior to further flight, accomplish one of the following, as applicable, in accordance with the service bulletin: (1) Re-rig the rudder cables to attain proper alignment; or (2) Replace the rudder cables if alignment cannot be attained. (b) For all airplanes equipped at manufacture with a safety control stop (See NOTE 2 of this AD), inspect the safety control stop for wear (rubbing, scrapes, etc.) in accordance with the Instructions Part I.2 section of EXTRA Service Bulletin No. 300-3-95, Issue: B, dated May 12, 1998. If the safety control stop is worn, prior to further flight, replace the safety control stop and accomplish one of the following, as applicable, in accordance with the service bulletin: (1) Re-rig the rudder cable if elongation of the cable is not evident; or (2) Replace the rudder cable if elongation of the cable is evident. NOTE 2: The Model EA-300/S airplanes, serial numbers 001 through 011, were not factory equipped with a safetycontrol stop. (c) Inspect the footrest flange in the area of the safety wire hole for cracks in accordance with the Instructions Part I.3 section of EXTRA Service Bulletin No. 300-3-95, Issue: B, dated May 12, 1998. If cracks are found, prior to further flight, replace the rudder pedal in accordance with the applicable maintenance manual or instructions obtained from the Small Airplane Directorate at the address specified in paragraph (f) of this AD. (d) For all airplanes equipped at manufacture with a safety control stop (See NOTE 2 of this AD), inspect the safety control stop clearance in accordance with the Instructions Part I.4 and Instructions Part II section of EXTRA Service Bulletin No. 300-3-95, Issue: B, dated May 12, 1998. If the clearance does not meet the minimum specified clearance, prior to further flight, accomplish one of the following, as applicable, in accordance with the service bulletin: (1) Adjust the foot rest to meet the required clearance ifelongation of the cable is not evident; or (2) Replace the rudder cable if elongation of the cable is evident. (e) Special flight permits may be issued in accordance with sections 21.197 and 21.199 of the Federal Aviation Regulations (14 CFR 21.197 and 21.199) to operate the airplane to a location where the requirements of this AD can be accomplished. (f) An alternative method of compliance or adjustment of the compliance times that provides an equivalent level of safety may be approved by the Manager, Small Airplane Directorate, FAA, 1201 Walnut, suite 900, Kansas City, Missouri 64106. The request shall be forwarded through an appropriate FAA Maintenance Inspector, who may add comments and then send it to the Manager, Small Airplane Directorate. NOTE 3: Information concerning the existence of approved alternative methods of compliance with this AD, if any, may be obtained from the Small Airplane Directorate. (g) Questions or technical information related toEXTRA Service Bulletin No. 300-3-95, Issue: B, dated May 12, 1998, should be directed to EXTRA Flugzeugbau GmbH, Flugplatz Dinslaken, D-46569 Hunxe, Federal Republic of Germany; telephone: (0 28 58) 91 37-00; facsimile: (0 28 58) 91 37-30. This service information may be examined at the FAA, Central Region, Office of the Regional Counsel, Room 1558, 601 E. 12th Street, Kansas City, Missouri 64106. (h) The inspections, modifications, or replacements required by this AD shall be done in accordance with EXTRA Service Bulletin No. 300-3-95, Issue: B, dated May 12, 1998. This incorporation by reference was approved by the Director of the Federal Register in accordance with 5 U.S.C. 552(a) and 1 CFR part 51. Copies may be obtained from EXTRA Flugzeugbau GmbH, Flugplatz Dinslaken, D-46569 Hunxe, Federal Republic of Germany. Copies may be inspected at the FAA, Central Region, Office of the Regional Counsel, Room 1558, 601 E. 12th Street, Kansas City, Missouri, or at the Office ofthe Federal Register, 800 North Capitol Street, NW, suite 700, Washington, DC. NOTE 4: The subject of this AD is addressed in German AD No. 95-443 EXTRA, dated November 29, 1995. (i) This amendment becomes effective on December 28, 1998.