AD 97-10-13 Airworthiness Directives; Fairchild Aircraft, Inc. SA226 and SA227 Series Airplanes

The following airplane models and serial numbers, certificated in any category, that do not incorporate an elevator torque tube with either part number (P/N) 27-44026-005, P/N 27- 44026-007, or P/N 27-44026-SEO-1-03: ------------------------------------------------------------------------ Model Serial Nos. ------------------------------------------------------------------------ SA226-T............................. T201 through T275 and T277 through T291. SA226-T(B).......................... T(B)276 and T(B)292 through T(B)417. SA226-AT............................ AT001 through AT074. SA226-TC............................ TC201 through TC419. SA227-TT............................ TT421 through TT541. SA227-AT............................ AT423 through AT695. SA227-AC............................ AC406, AC415, AC416, and AC420 through AC772. SA227-BC............................ BC762, BC764, BC766, BC770, BC771, and BC772. ------------------------------------------------------------------------ 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 (d) 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.

Required within the next 6 calendar months after the effective date of this AD, unless already accomplished (compliance with AD 96-21-05). To prevent failure of the flight control system caused by a corroded elevator torque tube, which could result in loss of control of the airplane, accomplish the following: (a) Drill two .5-inch diameter holes in the inboard side of the elevator torque tube arm in accordance with the ACCOMPLISHMENT INSTRUCTIONS section of, and as specified in Figure 1 of, Fairchild Aircraft Service Bulletin (SB) 226-27-050 or Fairchild Aircraft SB 227-27-028, both Issued: January 22, 1990, as applicable. (b) Inspect the elevator torque tube in accordance with the ACCOMPLISHMENT INSTRUCTIONS section of Fairchild Aircraft SB 226-27- 050 or Fairchild Aircraft SB 227-27-028, both Issued: January 22, 1990, as applicable. (1) If corrosion is found inside the elevator torque tube, prior to further flight after the inspection required by paragraph (b) of this AD, replace the corroded elevator torque tube with either a P/N 27-44026-005, P/N 27-44026-007, or P/N 27-44026-SEO-1-03 elevator torque tube in accordance with the applicable maintenance manual. (2) If corrosion is not found inside the elevator torque tube, prior to further flight after the inspection required by paragraph (b) of this AD, apply a corrosion preventive compound in accordance with the ACCOMPLISHMENT INSTRUCTIONS section of Fairchild Aircraft SB 226-27-050 or Fairchild Aircraft SB 227-27-028, both Issued: January 22, 1990, as applicable. (c) 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. (d) An alternative method of compliance or adjustment of the compliance time that provides an equivalent level of safety may be approved by the Manager, Airplane Certification Office (ACO), FAA, 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. Alternative methods of compliance approved in accordance with AD 96-21-05 (superseded by this AD) are considered approved for this AD. Note 2: Information concerning the existence of approved alternative methods of compliance with this AD, if any, may be obtained from the Fort Worth ACO. (e) The inspection access hole drilling, the inspection, and the corrosion preventive compound application required by this AD shall be done in accordance with Fairchild Aircraft SB 226-27-050 or Fairchild Aircraft SB 227-27-028, both Issued: January 22, 1990, as applicable. This incorporation by reference was previously approved by the Director of the Federal Register in accordance with 5 U.S.C. 552(a) and 1 CFR part 51, as of November 29, 1996 (61 FR 54538, October 21, 1996). Copies may be obtained Fairchild Aircraft, P.O. Box 790490, San Antonio, Texas 78279-0490. Copies may be inspected at the FAA, Central Region, Office of the Assistant Chief 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. (f) This amendment (39-10025) supersedes AD 96-21-05, mendment 39-9782. (g) This amendment (39-10025) becomes effective on July 8, 1997. Issued in Kansas City, Missouri, on May 7, 1997. Henry A. Armstrong, Acting Manager, Small Airplane Directorate, Aircraft Certification Service. [FR Doc. 97-12517 Filed 5-12-97; 8:45 am] BILLING CODE 4910-13-U