AD 95-13-02

Final rule

95-13-02 TWIN COMMANDER AIRCRAFT CORPORATION: Amendment 39-9283; Docket No. 94-CE-27-AD.

Applicability: The following airplane models and serial numbers, certificated in any category, that do not have the vertical stabilizer modified in accordance with the ACCOMPLISHMENT INSTRUCTIONS: PART II - MODIFICATION section of Twin Commander Service Bulletin (SB) No. 218, dated May 19, 1994, including Revision Notices 1 and 2, dated July 11, 1994, and September 23, 1994, respectively:

Model Serial Numbers
685 12000 through 12066
690 11000 through 11079
690A 11100 through 11344
690B 11350 through 11566
690C 11600 through 11735
690D 15001 through 15042
695 95000 through 95084
695A 96001 through 96100

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 use the authority provided in paragraph (f) of this AD to request approval from the FAA. This approval may address either no action, if the current configuration eliminates the unsafe condition, or different actions necessary to address the unsafe condition described in this AD. Such a request should include an assessment of the effect of the changed configuration on the unsafe condition addressed by this AD. In no case does the presence of any modification, alteration, or repair remove any airplane from the applicability of this AD.

Compliance: Required upon the accumulation of 2,000 hours time-in-service (TIS) on a vertical stabilizer or within the next 50 hours TIS after the effective date of this AD, whichever occurs later, unless already accomplished, and thereafter as indicated in the body of this AD.

To prevent failure of the vertical stabilizer as a result of cracks, which, if notdetected and corrected, could result in loss of control of the airplane, accomplish the following:

(a) Inspect the vertical stabilizer for cracks in accordance with the ACCOMPLISHMENT INSTRUCTIONS: PART I - INSPECTION section of Twin Commander SB No. 218, dated May 19, 1994, including Revision Notices 1 and 2, dated July 11, 1994, and September 23, 1994, respectively.

(b) If damage or cracks are found within the limits of Figures 1 and 2 of the service information referenced above, prior to further flight, modify the vertical stabilizer in accordance with the ACCOMPLISHMENT INSTRUCTIONS: PART II - MODIFICATION section of Twin Commander SB No. 218, dated May 19, 1994, including Revision Notices 1 and 2, dated July 11, 1994, and September 23, 1994, respectively.

(c) If damage or cracks are found outside the limits referenced in Figures 1 and 2 of the service information referenced above or if cracks intersect, prior to further flight, replace the damaged parts with new parts in accordance with the applicable maintenance manual instructions. The requirements of this AD still apply when the damaged parts are replaced, unless the stabilizer is modified as specified in paragraph (b) of this AD.

(d) If no cracks are found, accomplish one of the following:

(1) Reinspect at intervals not to exceed 500 hours TIS, and modify any damaged or cracked vertical stabilizer as specified in paragraph (b) and (c) of this AD; or

(2) Prior to further flight, modify the vertical stabilizer in accordance with the ACCOMPLISHMENT INSTRUCTIONS: PART II - MODIFICATION section of Twin Commander SB No. 218, dated May 19, 1994, including Revision Notices 1 and 2, dated July 11, 1994, and September 23, 1994, respectively. This modification may be accomplished prior to further flight after any repetitive inspection as terminating action for the repetitive inspections provided no cracks are found.

(e) Special flight permits may be issued in accordance with sections21.197 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, Seattle Aircraft Certification Office (ACO), FAA, Northwest Mountain Region, 1601 Lind Avenue S.W., Renton, Washington 98055-4056. The request shall be forwarded through an appropriate FAA Maintenance Inspector, who may add comments and then send it to the Manager, Seattle ACO.

NOTE 2: Information concerning the existence of approved alternative methods of compliance with this AD, if any, may be obtained from the Seattle ACO.

(g) The inspections and modification required by this AD shall be done in accordance with Twin Commander Service Bulletin 218, dated May 19, 1994, including Revision Notices 1 and 2, dated July 11, 1994, and September 23, 1994, respectively. 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 Twin Commander Aircraft Corporation, 19003 59th Drive, NE., Arlington, Washington 98223. 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.

(h) This amendment becomes effective on July 22, 1995.