Airworthiness Directive · Amendment 39-17665 · Fuselage miscellaneous structure
Eurocopter France Helicopters
This AD applies to Eurocopter France Model AS350B, BA, B1, B2, B3, D, AS355E, F, F1, F2, and N helicopters with collective-to-yaw control coupling, part number 350A27-2178-04, 350A27-2178-06, or 350A27-2178-0601, certificated in any category.
We are superseding Airworthiness Directive (AD) 2010- 21-01 for Eurocopter France (Eurocopter) Model AS350B, BA, B1, B2, B3, D, AS355E, F, F1, F2, and N helicopters. AD 2010-21-01 required an inspection to determine whether a cross-member is installed at station X 2165 and doublers at X 2325 and Y 269, and installing them if they are missing. This new AD retains the requirements of AD 2010-21-01 but clarifies the inspection procedures and limits the applicability to only those helicopters with collective-to-yaw control coupling. This AD is prompted by a crack discovered in the area of the center cross-member at station X 2325, at the attachment point of the yaw channel ball-type control sheath stop, of a Model AS355N helicopter fitted with the collective-to-yaw control coupling. The actions of this AD are intended to prevent reduced yaw control and subsequent loss of helicopter control.
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 10 hours time-in-service (TIS) or within one month, whichever occurs first, determine whether the cross-member (numbered “1”) at station X 2165 and the two doublers (numbered “2” and “3”) at stations X 2325 and Y 269 are installed as shown in Figure 1 of Eurocopter Emergency Alert Service Bulletin (EASB) No. 53.00.37, Revision 0, dated April 11, 2007 (EASB 53.00.37), for Model AS350 helicopters and EASB No. 53.00.23, Revision 0, dated April 11, 2007 (EASB 53.00.23), for Model AS355 helicopters.
(2) If the cross-member (numbered “1”) and doublers (numbered “2” and “3”) are not installed, before further flight, inspect for a crack in the center cross-member (numbered “4”) in the area around the attachment point of the tail rotor directional ball-type control as shown in Figure 1 of EASB 53.00.37 for Model AS350 helicopters or EASB 53.00.23 for Model AS355 helicopters.
(i) If a crack exists, before further flight, replace the unairworthy center cross-member (Numbered “4”) with an airworthy center cross-member as described in paragraph (f)(3) of this AD.
(ii) If a crack does not exist, before further flight, inspect the tail rotor control rigging to determine whether it meets conformity limits.
(A) If all items of the tail rotor control rigging are found within conformity limits, install the cross-member and doublers as described in paragraph (f)(3) of this AD.
(B) For any items of the tail rotor control rigging found outside of conformity limits, perform appropriate corrective action in accordance with FAA-accepted procedures, and install the cross-member and doublers as described in paragraph (f)(3) of this AD.
(3) Within 55 hours TIS, if the cross member (Numbered “1”) is not installed, install the cross-member at station X 2165 and the 2 doublers (Numbered “2” and “3”) at stations X 2325 and Y 269 by following the Appendix, the referenced figures 2 and 3 of EASB 53.00.37 for Model AS350 helicopters or EASB 53.00.23 for Model AS355 helicopters.
