2001-01-11: Airbrake Locking Bracket

2001-01-11 ROLLADEN SCHNEIDER FLUGZEUGBAU GMBH: Amendment 39-12081; Docket No. 99-CE-75-AD. (a) What sailplanes are affected by this AD? This AD affects models LS 4 and LS 4a sailplanes, serial numbers 4000 through 4852, that are certificated in any category. (b) Who must comply with this AD? Anyone who wishes to operate any of the above sailplanes must comply with this AD. (c) What problem does this AD address? The actions specified by this AD are intended to detect and correct damage to the airbrake locking bracket caused by asymmetric loads. This condition could result in the pilot's inability to operate the airbrake controls with consequent loss of sailplane control. (d) What actions must I accomplish to address this problem? To address this problem, you must accomplish the following: Actions Compliance Procedures (1) Inspect the airbrake locking bracket on the rear landing gear box for signs of fatigue (cracks in the paint, paint chips, or cracks in the welding region to the tube) and inspect for proper rigging of the airbrake system Within the next 30 calendar days after March 9, 2001 (the effective date of this AD). Inspect for proper rigging in accordance with the procedures contained in the applicable maintenance manual. Inspect the airbrake locking bracket in accordance with the procedures contained in Rolladen Schneider Technical Bulletin No. 4042, dated July 2, 1999 (2) If any sign of fatigue is evident, accomplish the following: (i) Disassemble the airbrake system; (ii) Obtain a modified airbrake locking bracket from the manufacturer (2-day turnaround time) and install this bracket; and (iii) Reassemble the airbrake system and accomplish the adjustments listed in the service bulletin. Accomplish all actions prior to further flight after the inspection required in paragraph (d)(1) of this AD Accomplish the disassembly, installation, assembly, and adjustments in accordance with procedures contained in the applicable maintenance manual and the procedures in Rolladen Schneider Technical Bulletin No. 4042, dated July 2, 1999. (3) If no signs of fatigue are found but the airbrake system is incorrectly assembled, disassemble the system and reassemble, including accomplishing the adjustments listed in the service bulletin. Accomplish all actions prior to further flight after the inspection required in paragraph (d)(1) of this AD Accomplish in accordance with procedures contained in the applicable maintenance manual and the procedures in Rolladen Schneider Technical Bulletin No. 4042, dated July 2, 1999. (4) If no signs of fatigue are found and the airbrake system is correctly assembled, then no further action is required by this AD. AD complied with. AD complied with. (5) If any discrepancy is found that requires additional work as requiredby paragraphs (d)(2) and (d)(3) of this AD, then send information describing the discrepancies found and the follow-on work that was necessary to the FAA. Within 10 days after the inspection required by this AD or within 10 days after March 9, 2001 (the effective date of this AD), whichever occurs later Within 10 days after the inspection required by this AD or within 10 days after March 9, 2001 (the effective date of this AD), whichever occurs later. (e) Can I comply with this AD in any other way? You may use an alternative method of compliance or adjust the compliance time if: (1) Your alternative method of compliance provides an equivalent level of safety; and (2) The Manager, Small Airplane Directorate, approves your alternative. Submit your request through an FAA Principal Maintenance Inspector, who may add comments and then send it to the Manager, Small Airplane Directorate. Note 1: This AD applies to each sailplane identified in paragraph (a) of this AD, regardless of whether it has been modified, altered, or repaired in the area subject to the requirements of this AD. For sailplanes 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 (e) 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 you have not eliminated the unsafe condition, specific actions you propose to address it. (f) Where can I get information about any already-approved alternative methods of compliance? Contact Brian Hancock, Aerospace Engineer, Small Airplane Directorate, 901 Locust, Room 301, Kansas City, Missouri 64106; telephone: (816) 329-4143; facsimile: (816) 329-4090. (g) What if I need to fly the sailplane to another location to comply with this AD? The FAA can issue a special flight permit under sections 21.197 and 21.199 of the Federal Aviation Regulations (14 CFR 21.197 and 21.199) to operate your sailplane to a location where you can accomplish the requirements of this AD. (h) Are any service bulletins incorporated into this AD by reference? Actions required by this AD must be done in accordance with Rolladen Schneider Technical Bulletin No. 4042, dated July 2, 1999. The Director of the Federal Register approved this incorporation by reference under 5 U.S.C. 552(a) and 1 CFR part 51. You can get copies from Rolladen-Schneider Flugzeugbau GmbH, Muhlstrasse 10, D-63329 Egelsbach, Germany. You can look at copies at the FAA, Central Region, Office of the Regional Counsel, 901 Locust, Room 506, Kansas City, Missouri, or at the Office of the Federal Register, 800 North Capitol Street, NW, suite 700, Washington, DC. (i) When does this amendment become effective? This amendment becomes effective on March 9, 2001. Note 2: The subject of this AD is addressed in German AD 1999-270, dated July 22, 1999.