2000-14-51 AIR TRACTOR INCORPORATED: Amendment 39-11837; Docket No. 2000-CE-40-AD.
(a) What airplanes are affected by this AD? This AD applies to the following Air Tractor airplane models and serial numbers:
Model
Serial Numbers
AT-501
501-002 through 501-0060 that have been converted to turboprop power.
AT-502
502-003 through 502-0061, except those that have been upgraded to the 8,000-pound gross weight configuration through the incorporation of Snow Engineering Co. Service Letter #80J.
AT-502A
All serial numbers.
(b) Who must comply with this AD? Anyone who wishes to operate any of the above airplanes on the U.S. Register must comply with this AD.
(c) What problem does this AD address? This AD is intended to detect and correct fatigue cracks in the wing lower spar cap, which could result in an in-flight separation of the wing from the airplane.
(d) What actions must I accomplish to address this problem? To address this problem, you mustaccomplish the following:
Action When Procedures
(1) Initial Inspection: Visually inspect the wing lower spar cap at the wing center splice connection for cracks. At whichever of the following that is applicable:
(i) For the Models AT-501 and AT-502 airplanes: Upon accumulating 4,000 hours time-in-service (TIS) on each wing or within the next 10 hours TIS after the effective date of this AD, whichever occurs later; or
(ii) For the Model AT-502A airplanes: Upon accumulating 3,000 hours TIS on each wing or within the next 10 hours TIS after the effective date of this AD, whichever occurs later. Accomplish this inspection in accordance with the INSPECTION REQUIREMENTS section of Snow Engineering Co. Service Letter #197, dated June 13, 2000.
Action When Procedures
(2) Repetitive Inspections: Inspect using visual or ultrasonic methods the wing lower spar cap at the center splice connection for cracks. For all affected airplanes, accomplish the repetitive inspections as follows:
(i) Visually: Within 50 hours TIS after the initial inspection and thereafter at intervals not to exceed 50 hours TIS; or
(ii) Using ultrasonic methods: Within 400 hours TIS after the initial inspection and thereafter at intervals not to exceed 400 hours TIS. Accomplish these inspections in accordance with the INSPECTION REQUIREMENTS section of Snow Engineering Co. Service Letter #197, dated June 13, 2000.
(3) Replace or modify any cracked wing lower spar cap, as specified in the service information. Prior to further flight after the inspection where the crack is found. Accomplish the replacement and modification as follows:
(i) Replacement: Remove the wing with the cracked lower spar cap and return to Air Tractor for spar cap replacement. Immediately notify Air Tractor that you are sending the wing if the cracked spar cap can not be modified.
(ii) Modification: In accordance with the TERMINATING ACTION section of Snow Engineering Co. Service Letter #197, dated June 13, 2000.
(4) Modifying each lower spar cap is considered terminating action for the repetitive inspection requirement. This modification can only be accomplished if the lower spar caps are inspected before the modification is incorporated and:
(i) no cracks are found; or
(ii) any crack found can be removed by drilling the hole to the next larger size. This terminating action may be accomplished at any time provided the lower spar caps are not cracked. Accomplish in accordance with the TERMINATING ACTION section of Snow Engineering Co. Service Letter #197, dated June 13, 2000.
(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, 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 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 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) Where can I get information about any already-approved alternative methods of compliance? Contact Rob Romero, Aerospace Engineer, FAA, Fort Worth ACO, 2601 Meacham Boulevard, Fort Worth, Texas 76193-0150; telephone: (817) 222-5102; facsimile: (817) 222-5960.
(g) 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 you comply with the following:
(1) The hopper is empty;
(2) Vne is reduced to 138 miles per hour (mph) (120 knots) indicated airspeed (IAS); and
(3) Flight into known turbulence is prohibited.
(h) Are any service bulletins incorporated into this AD by reference? Actions required by this AD must be done in accordance with Snow Engineering Co. Service Letter #197, dated June 13, 2000. The Director of the Federal Register approved this incorporation by reference under 5 U.S.C. 552(a) and 1 CFR part 51. You may get copies of this document from Air Tractor, Incorporated, P.O. Box 485, Olney, Texas 76374. You may look at 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.
(i) When does this AD become effective? This AD becomes effective August 4, 2000, to all affected persons who did not receive emergency AD 2000-14-51, issued July 3, 2000. Emergency AD 2000-14-51 contained the requirements of this amendment and became effective immediately upon receipt.