Airworthiness Directive · Amendment 39-22519 · Horizontal stabilizer structure
Air Tractor, Inc. Airplanes
Superseded. A later AD replaced this one: AD 2024-16-06. Comply with the one in force.
This AD applies to Air Tractor, Inc. Model AT-802 and AT-802A airplanes, all serial numbers, certificated in any category, that have Wipaire, Inc. Supplemental Type Certificate (STC) No. SA01795CH installed.
The FAA is adopting a new airworthiness directive (AD) for all Air Tractor, Inc. (Air Tractor) Model AT-802 and AT-802A airplanes that have Wipaire Supplemental Type Certificate (STC) No. SA01795CH installed. This AD was prompted by reports of cracks found in the forward horizontal stabilizer spar where the vertical finlets tie to the horizontal tail forward spar. This AD requires repetitively inspecting both the left and right forward horizontal stabilizer spars for cracks and replacing any forward horizontal stabilizer spar found cracked. This AD also requires reporting inspection results to the FAA. The FAA is issuing this AD to address the unsafe condition on these products.
(1) At the compliance times in paragraphs (g)(1)(i) through (iii) of this AD, as applicable, and thereafter at intervals not to exceed 200 hours time-in-service (TIS), inspect the left and right forward horizontal stabilizer spars for cracks in accordance with Steps 1 through 9 of the Work Instructions of Wipaire, Inc. Service Letter 253, Revision B, dated July 27, 2023.
(i) For STC configuration 7D1-4399-01: Within 3 days or 24 hours TIS after the effective date of this AD or before the accumulation of 200 hours TIS since installation of STC No. SA01795CH, whichever occurs later.
(ii) For STC configuration 7D1-4399-02: Within 5 days or 24 hours TIS after the effective date of this AD or before the accumulation of 300 hours TIS since installation of STC No. SA01795CH, whichever occurs later.
(iii) For STC configuration 7D1-4399-03: Within 15 days or 24 hours TIS after the effective date of this AD or before the accumulation of 600 hours TIS since installation of STC No. SA01795CH, whichever occurs later.
(2) If any crack is found in a forward horizontal stabilizer spar during any inspection required by paragraph (g)(1) of this AD, before further flight, replace the cracked forward horizontal stabilizer spar. Replacement of the cracked forward horizontal stabilizer spar starts the initial and repetitive inspections over.
(3) Within 10 days after each inspection required by paragraph (g)(1) of this AD or within 10 days after the effective date of this AD, whichever occur later, report the following to the FAA at the address in paragraph (j)(1) of this AD. Report this information regardless of whether cracks are found.
(i) Model, engine configuration (with horsepower limits), and propeller type;
(ii) Serial number and N number;
(iii) Total hours TIS on airframe;
(iv) Total hours TIS operated with floats, if known;
(v) STC configuration and total hours with STC installed;
(vi) Crack location (right or left, upper/lower caps inboard/outboard hole);
(vii) Crack size;
(viii) Photos of cracks found, if available; and
(ix) Any additional operator/mechanic comments
The aircraft, engines and makers this AD names, by the model designations in its text. A model listed here may still be outside the AD's serial ranges.
