Airworthiness Directive · Amendment 39-14009 · Eurocopter France Model EC 155B and EC 155B1 Helicopters
Eurocopter France Model EC 155B and EC 155B1 Helicopters
Model EC 155B and EC 155B1 helicopters with cabin sliding doors, part number (P/N) 365A82-1064-02 (left-hand door) and P/N 365A82-1064-03 (right-hand door) and stop, P/N 365A25-8085-21, installed, certificated in any category.
This amendment adopts a new airworthiness directive (AD) for Eurocopter France (Eurocopter) Model EC 155B and EC 155B1 helicopters that requires inspecting the chamfer of the stop on the cabin sliding doors (doors) and installing an airworthy stop if the chamfer exceeds a certain length; and prior to each flight, visually checking the door to determine if it is correctly locked in the open position before flying with the doors open, and checking the locking indicator light and the position of the door handles before flying with the doors closed. This amendment also requires revising the Limitations Section of the Rotorcraft Flight Manual (RFM) to prohibit the opening or closing of a cabin sliding door at airspeeds of 40 or greater knots indicated airspeed (KIAS). This amendment is prompted by a report of a door separating from a helicopter during flight. The actions specified by this AD are intended to prevent separation of a door during flight and damage to the helicopter, resulting in a forced landing or loss of control of the helicopter.
To prevent separation of a door during flight and damage to the helicopter, resulting in a forced landing or loss of control of the helicopter, accomplish the following:
(a) Before further flight, revise the Limitations Section of the Rotorcraft Flight Manual (RFM) permitting the opening or closing of the cabin sliding doors only at speeds of less than 40 knots indicated airspeed.
(b) Within 50 hours time-in-service, inspect the length of the chamfer on the stop of the lower rail aft fitting on each cabin sliding door (door), and if the chamfer is more than 2mm in length, install an airworthy stop in accordance with paragraph 2.B., Operational Procedure, of Eurocopter Alert Telex No. 52A013, Revision 1, dated September 24, 2003.
Note 1: The inspection required by paragraph (b) of this AD has already been accomplished for all Model EC 155B1 helicopters prior to delivery.
(c) Before each flight with a door open, check that each open door is locked in the “open” position with the upper roller in its rail and the door open locking latch engaged.
(d) Before each flight with a door closed, check that:
(1) The locking indicator light on the instrument panel is “off,”
(2) The door handle is in the correct “closed” position, and
(3) The lower locking pin is positioned in its catch.
Note 2: If the door is correctly closed and latched, when viewed from the outside, the door handle will be flush with the profile of the housing and the aft lower corner of the door will be flush with the profile of the fuselage; when viewed from the inside, the door handle will be positioned opposite the locking indicator with no gap between the structure seal and the aft lower sealing surface of the door.
Note 3: If the door is closed and the lower locking pin is outside its catch, when viewed from the outside, the aft lower corner of the door is approximately 15 to 20mm from the fuselage; when viewed from the inside, the aft lower corner of the door is approximately 10 to 15mm from the fuselage.
(e) An owner/operator (pilot) holding at least a private pilot certificate may perform the visual checks required by paragraphs (c) and (d) of this AD and must enter compliance with those paragraphs into the aircraft maintenance records in accordance with 14 CFR 43.11 and 91.417(a)(2)(v).
(f) After the stops of the lower rail aft fitting with a chamfer 2mm or less in length are installed and in accordance with MOD 0753C48, the mounting plate supports are modified and the door micro-switches are adjusted, the checks required by paragraph (d) of this AD are no longer required.
(g) To request a different method of compliance or a different compliance time for this AD, follow the procedures in 14 CFR 39.19. Contact the Safety Management Group, Rotorcraft Directorate, FAA, for information about previously approved alternative methods of compliance.
