Airworthiness Directive · Amendment 39-19787 · Tail rotor system
Leonardo S.p.A. Helicopters
This AD applies to Leonardo S.p.A. Model AW169 and AW189 helicopters, certificated in any category, with a tail rotor (T/R) actuator part number (P/N) 6F6730V00331 with a serial number (S/N) up to 489 inclusive, except those marked with “SB 67-0007.”
The FAA is adopting a new airworthiness directive (AD) for Leonardo S.p.A. Model AW169 and AW189 helicopters. This AD requires inspecting certain part-numbered and serial-numbered tail rotor (T/R) actuators, reporting information, and depending on the inspection outcome, marking a part, performing an additional inspection, and removing the T/R actuator from service. This AD also prohibits the installation of affected T/R actuators. This AD is prompted by reports of incorrect installations of the T/R actuator back-end input lever. The actions of this AD are intended to address an unsafe condition on these products.
You are responsible for performing each action required by this AD within the specified compliance time unless it has already been accomplished prior to that time.
(1) Within 30 hours time-in-service (TIS), for Model AW169 helicopters, with access panels 470AT and 470BT removed; and for Model AW189 helicopters, with access panels 496A and 495A removed, inspect the T/R actuator input lever assembly by following the Accomplishment Instructions, paragraph 3.B. through 3.C.4., of UTC Aerospace Systems Service Bulletin 67-0007, Basic Issue, dated January 17, 2019 (SB 67-0007).
(i) Report the information requested in the form at the end of SB 67-0007, along with a photo of each side of the installed T/R actuator back-end input lever, by email to: pse_aw189.mbx.aw@leonardocompany.com. Refer to Figure 4 and Figure 5 of SB 67-0007 for an example of each photo.
(ii) If the width of the bearing circular collar of the input lever is within the allowable limits of 4 ±0.3 mm, the input lever pin head is not on side “A” of the T/R actuator as shown in Figure 2b of SB 67-0007 (the input lever pin head is on side “B”), and the nut and cotter pin of the intermediate bolt are installed on side “A” of the T/R actuator side as shown in Figure 3 of SB 67-0007, before further flight, mark “SB 67-0007” on the input lever with permanent ink as shown in Figure 4 of SB 67-0007.
(iii) If the width of the bearing circular collar of the input lever is outside the allowable limits of 4 ±0.3 mm, the input lever pin head is on side “A” of the T/R actuator, or the nut and cotter pin of the intermediate bolt are not installed on side “A” of the T/R actuator side, before further flight, use Table 1 to paragraph (e)(1)(iii) of this AD for next instruction.
(iv) Before further flight, inspect for correct bonding (no axial or rotational relative movement compared to the lever) of each bearing by moving the input lever along the pin axial direction.
(A) If there is no axial or rotational relative movement compared to the lever in both bearings, within 10 hours TIS after completing the inspections required by paragraph (e)(1) of this AD, remove from service the T/R actuator.
(B) If there is axial or rotational relative movement compared to the lever in one or both bearings, before further flight, remove from service the T/R actuator.
(v) Within 60 hours TIS after completing the inspections required by paragraph (e)(1) of this AD, remove from service the T/R actuator.
(2) After the effective date of this AD, do not install a T/R actuator P/N 6F6730V00331 with an S/N up to 489 inclusive, except those marked with “SB 67-0007,” on any helicopter.
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
