2002-13-02: Wing Centerline Splice Joint

2002-13-02 Air Tractor, Inc.: Amendment 39-12789; Docket No. 2002"CE-22-AD. (a) What airplanes are affected by this AD? This AD applies to the following airplanes that are certificated in any category: (1) Models AT-300, AT-301, AT-302, and AT-400A airplanes, all serial numbers, that have aluminum spar caps; (2) Models AT-400 airplanes, serial numbers 400-0244 through 400-0415, that have aluminum spar caps; and (3) Models AT-300 and AT-301 airplanes, all serial numbers that have aluminum spar caps and are or have been converted to turbine power. (b) Who must comply with this AD? Anyone who wishes to operate any airplane identified in paragraph (a)(1), (a)(2), or (a)(3) of this AD must comply with this AD. (c) What problem does this AD address? The actions specified by this AD are intended to detect and correct cracks in the wing centerline splice joint. If not detected and corrected, these cracks could eventually result in the wing separating from theairplane during flight. (d) What must I do to address this problem? To address this problem, you must accomplish the following actions: Actions Compliance Procedures (1) Inspect, using eddy current inspection methods, the wing centerline splice joint. The particular inspection area depends on whether Snow Engineering Service Letter #55 is incorporated. Specifics are included in the service information. The inspection must be accompanied by one of the following: (i) a Level 2 or Level 3 inspector that is certified for eddy-current inspection using the guide-lines established by the American Society for Nondestructive Testing or MIL-STD-410; or (ii) A person authorized to perform AD work who has completed and passed the Air Tractor, Inc. training course on Eddy Current Inspection on wing lower spar caps. For affected airplanes (turbine-powered or piston engine-powered) with at least one wing spar lower cap having 6,990 or more hours time-in-service (TIS) as of the effective date of this AD: Inspect within the next 10 hours TIS after July 9, 2002 (the effective date of this AD), unless already accomplished after accumulating 6,000 hours TIS; For affected piston engine-powered airplanes with at least one wing spar lower cap having less than 6,990 hours TIS as of the effective date of this AD: Inspect upon the accumulation of 6,000 hours TIS or within the next 50 hours TIS after July 9, 2002 (the effective date of this AD), whichever occurs later, unless already accomplished after accumulating 6,000 hours TIS; or For affected turbine-powered aiplanes with at least one wing spar lower cap having less than 6,999 hours TIS as of the effective day of this AD. Upon the accumulation of 4,000 hours TIS or within the next 50 hours TIS after July 9, 2002 (the effective date of this AD), whichever occurs later, unless already accomplished after accumlating 4,000 hours TIS. Inspect in accordance with Snow Engineering Co. Service Letter #220, dated May 3, 2002; andSnow Engineering Co. Process Specification 197, dated February 23, 2001; Revised May 1, 2002, or Revised May 3, 2002. (2) If cracks are found during the inspection required by paragraph (d)(1) of this AD, replace the affected wing spar lower cap. Prior to further flight after the inspection required by paragraph (d)(1) of this AD. In accordance with the instructions in the applicable maintenance manual. (3) Report the results of the inspection in paragraph (d)(1) of this AD to FAA. The Office of Management and Budget (OMB) approved the information collection requirements contained in this regulation under the provisions of the Paperwork Reduction Act of 1980 (44 U.S.C. 3501 et seq.) and assigned OMB Control Number 2120-0056. If the inspection is accomplished after the effective date of this AD: Within 10 days after the inspection required in paragraph (d)(1) of this AD; or If the inspection was already accomplished prior to the effective date of this AD: within the next 10 days after July 9, 2002 (the effective date of this AD). Submit the form (Figure 1 of paragraph (d)(3) of this AD) to FAA, Fort Worth Airplane Certification Office, 2601 Meacham Boulevard, Fort Worth, Texas 76193-0150; telephone: (817) 222-5156; facsimile: (817) 222-5960. . (4) Replace each wing spar lower cap Replace each lower cap upon the accumulation of 7,000 hours TIS on each wing spar lower cap or within the next 200 hours TIS after July 9, 2002 (the effective date of this AD), whichever occurs later. In accordance with instructions in the applicable maintenance manual AD 2002-13-02 INSPECTION REPORT 1. Inspection Performed By: 2. Phone: 3. Aircraft Model: 4. Aircraft Serial Number: 5. Engine Model Number: 6. Aircraft Total TIS: 7. Wing Total TIS: 8. Lower Spar Cap TIS: 9. Has the lower spar cap been inspected before? (Eddy-Current, Dye Penetrant, Magnetic Particle, Ultrasound) -Yes - No 9a. If yes, Date:________ Inspection Method:________ Lower Spar Cap TIS:________ Cracks found? - Yes - No 10. Has there been any major repair or alteration performed to the spar cap? -Yes - No 10a. If yes, specify (Description and TIS) 11. Date of AD inspection:____________ 12. Inspection Results: Were any cracks found? - Yes - No 12a. If yes, Crack #1 -Left Hand - Right Hand Crack #2 - Left Hand - Right Hand 12b. Reference Location(s) by Crack Number: 4-Bolt Joint 5-Bolt Joint - Outermost Hole - Outermost Hole - 2nd Outermost Hole 12c. Crack Size Crack #1 Length/Depth:________ Crack #2 Length/Depth:________ Additional Description/Comments: ___________________________________________________________________________ ___________________________________________________________________________ Return to: Manager, Fort Worth ACO, ASW-150, 2601 Meacham Blvd., Fort Worth, TX 76193-0150; or fax to (817) 222-5960 Figure 1 of paragraph (d)(3) of this AD (e) Can I comply with thisAD 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, Fort Worth Airplane Certification Office (ACO), approves your alternative. Submit your request through an FAA Principal Maintenance Inspector. The inspector may add comments before sending it to the Manager, Fort Worth ACO. Note: This AD applies to each airplane identified in paragraphs (a)(1), (a)(2), and (a)(3) of this AD, 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 (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) What if I need to fly the airplane 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 airplane to a location where you can accomplish the requirements of this AD provided that the following is adhered to: (1) Operate in day visual flight rules (VFR) only. (2) Ensure that the hopper is empty. (3) Limit airspeed to 135 miles per hour (mph) indicated airspeed (IAS). (4) Avoid any unnecessary g-forces. (5) Avoid areas of turbulence. (6) Plan the flight to follow the most direct route. (g) Are any service bulletins incorporated into this AD by reference? Replacement and inspection actions required by this AD must be done in accordance with Snow Engineering Co. Service Letter #220, dated May 3, 2002; and Snow Engineering Co. Process Specification 197, dated February 23, 2001, Revised May 1, 2002, or Revised May 3, 2002. 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 Air Tractor, Inc., P.O. Box 485, Olney, Texas 76374. You may view copies at 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. (h) When does this amendment become effective? This amendment becomes effective on July 9, 2002.