98-24-11: Aileron Control Links

98-24-11 MOONEY AIRCRAFT CORPORATION: Amendment 39-10897; Docket No. 98-CE-20-AD. Applicability: The following airplane models and serial numbers, certificated in any category. Models Serial Numbers M20B all serial numbers M20C all serial numbers M20D all serial numbers M20E all serial numbers M20F all serial numbers M20G all serial numbers M20L all serial numbers M20J 24-0001 through 24-3359 M20K 25-0001 through 25-1999 M20M 27-0001 through 27-0197 M20R 29-0001 through 29-0042 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 indicated in the body of this AD, unless already accomplished. To detect and correct cracked aileron control links, which could result in loss of aileron control and loss of the airplane, accomplish the following: (a) Within the next 100 hours time-in-service (TIS) after the effective date of this AD, visually inspect the aileron control links (left-hand and right-hand) at the second 90-degree angle joint from the Heim bearing for the installation of a reinforcement gusset. Accomplish this inspection in accordance with the Instructions section of Mooney Engineering Design Service Bulletin (SB) No. M20-264, Issue Date: February 1, 1998. (b) If a reinforcement gusset is installed, this AD requires no further action. (c) If a reinforcement gusset is not installed, prior to further flight after the inspection required in paragraph (a) of this AD, and thereafter at intervals not to exceed 100 hours TIS, inspect, using magnetic particle methods, the aileron control links for cracks. Accomplish this inspection in accordance with the Instructions section of Mooney Engineering Design SB No. M20-264, Issue Date: February 1, 1998. (1) If cracks are found, prior to further flight, replace the cracked aileron control link with an aileron control link of improved design (part numbers as specified in the referenced service information or FAA-approved equivalent numbers). Accomplish this replacement in accordance with the Instructions section of Mooney Engineering Design SB No. M20-264, Issue Date: February 1, 1998. (2) Replacing both aileron control links with aileron control links of improved design (part numbers as specified in the referenced service information or FAA-approved equivalent numbers) may be accomplished at any time as terminating action for the repetitive inspection requirement of this AD, but must be accomplished prior to further flight on any aileron control link found cracked. (3) If one aileron control link is replaced prior to further flight when a crack is found, the other aileron control link must still be repetitively inspected every 100 hours TIS until replacement with an improved design part. (d) Replacing the aileron control links in accordance with Mooney Engineering Design SB No. M20-264, Issue Date: February 1, 1998, is considered terminating action for the repetitive inspection requirement of this AD. (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 initial or repetitive compliance times that provides an equivalent level of safety may be approved by the Manager, Fort Worth Airplane Certification Office (ACO), 2601 Meacham Boulevard, Fort Worth, Texas 76193-0150. The request shall be forwarded through an appropriate FAA Maintenance Inspector, who may add comments and then send it to the Manager, Fort Worth ACO. NOTE 2: Information concerning the existence of approved alternative methods of compliance with this AD, if any, may be obtained from the Fort Worth Aircraft Certification Office. (g) The inspections and replacements required by this AD shall be done in accordance with Mooney Engineering Design Service Bulletin No. M20-264, Issue Date: February 1, 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 the Mooney Aircraft Corporation, Louis Schreiner Field, Kerrville, Texas, 78028. 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 of the Federal Register, 800 North Capitol Street, NW, suite 700, Washington, DC. (h) This amendment becomes effective on December 28, 1998.