Airworthiness Directive · Amendment 39-17338 · Rotorcraft tailboom
Schweizer Aircraft Corporation
This AD applies to Schweizer Aircraft Corporation (Schweizer) Model 269D and Model 269D Configuration A helicopters, serial numbers 0001 to 0062A, with aft fuselage assembly part number (P/N) 269D3300-1 installed, certificated in any category.
Note to Applicability: The type certificate for these models is currently held by Sikorsky Aircraft Corporation.
We are adopting a new airworthiness directive (AD) for the Schweizer Aircraft Corporation (Schweizer) Model 269D and Model 269D Configuration A helicopters. The type certificate for these models is currently held by Sikorsky Aircraft Corporation (Sikorsky). This AD requires inspecting the aft fuselage assembly in the area around the attachment point of the horizontal stabilizer, including the paint, for a crack. This AD also requires inspecting the tailboom interior support structure, and if necessary, installing an inspection panel kit in the aft fuselage assembly, and installing doublers in the stabilizer support brackets. This AD is prompted by reports of loose horizontal stabilizers and cracks in the stabilizer support structure for the extruded tailboom. The actions are intended to prevent separation of the horizontal stabilizer from the helicopter and subsequent loss of control of the helicopter.
You are responsible for performing each action required by this AD within the specified compliance time unless it has been accomplished previously.
(1) Before the first flight of each day, visually inspect the aft fuselage assembly in the area around the attachment point of the horizontal stabilizer, including the paint, for a crack. If there is a crack, remove the horizontal stabilizer and perform an interior inspection in accordance with Part II: Internal Inspection, paragraphs b. and c., of Schweizer Service Bulletin DB-018.3, dated December 13, 2007 (SB).
(i) If there is a crack in the aft fuselage assembly clip, in the aft bulkhead, or in adjacent skins, repair the crack. Thereafter, at intervals not to exceed 200 hours time-in-service (TIS), remove the horizontal stabilizer and repeat the interior inspection in accordance with Part II: Internal Inspection, paragraphs b. and c., of the SB, or replace the aft fuselage assembly, P/N 269D3300-1,with an airworthy aft fuselage assembly, P/N 269D3300-35.
(ii) If there is a crack in a longeron, tailboom tube collar or a forward stabilizer bulkhead, replace the aft fuselage assembly with an airworthy aft fuselage assembly, P/N 269D3300-35.
(2) Within 100 hours TIS or three months, whichever occurs first:
(i) Remove the horizontal stabilizer, clean the horizontal stabilizer mounting brackets, and inspect the mounting brackets for wear greater than 0.002-inch deep. If the bracket wear exceeds 0.002-inch deep, replace the mounting bracket with an airworthy mounting bracket.
(ii) Modify the aft fuselage assembly by installing Inspection Panel kit P/N SA-269DK-035.
(iii) Install doublers on the forward side of each mounting bracket in accordance with Part III-2, paragraphs e. through i., of the SB.
(iv) Inspect the horizontal stabilizer forward and aft spars for wear in the mounting attachment areas. If the wear exceeds 0.002-inch deep, replace the spar with an airworthy spar.
(v) Inspect for rivet interference between the rivet heads and skin on the top surface of the horizontal stabilizer and the tailboom stiffening Web near Station 232.4. If interference exists, replace with airworthy rivets.
(vi) Install an airworthy horizontal stabilizer using 4 bolts, P/N NAS1304-4, and 4 washers, P/N AN960KD416 or NAS1149D0463K.
(3) Removing aft fuselage assembly, P/N 269D3300-1, and replacing it with aft fuselage assembly, P/N 269D3300-35, is terminating action for the requirements of this AD.
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.
Aircraft
