Airworthiness Directive · Amendment 39-18146 · Main rotor blades
Airbus Helicopters (Type Certificate Previously Held by Eurocopter France)
This AD applies to Model EC225LP helicopters with a main rotor blade (blade), part number 332A11.0050.00, 332A11.0055.00, 332A11.0050.02, or 332A11.0055.02, installed, certificated in any category.
We are adopting a new airworthiness directive (AD) for Airbus Model EC225LP helicopters. This AD requires repetitive visual and tap test inspections of each main rotor blade (blade) leading edge stainless steel protective strip (strip) for a crack, cut, or blind or open debonding (debonding), and taking approved corrective measures. If there is a crack or if there is debonding that exceeds acceptable limits, this AD requires, before further flight, repairing or replacing the blade with an airworthy part. This AD was prompted by suspected water seepage through a crack in the blade strip resulting in significant debonding. The actions of this AD are intended to prevent loss of the blade strip, excessive vibrations induced by blade weight imbalance, 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 already been accomplished prior to that time.
Within 15 hours time-in-service (TIS) and thereafter at intervals not to exceed 85 hours TIS, visually and tap test inspect each blade strip for a crack, a cut, or open and blind debonding. For purposes of this AD, open debonding, also known as edge bond separation, occurs when a bonded part becomes unattached (debonded) leaving the surface under it exposed to open air around the periphery of the part. Blind debonding occurs when a bonded part becomes unattached internally yet remains bonded around its entire periphery.
(1) If there is open or blind debonding within acceptable limits and the debonded area is located inside Area D of Figure 1 of Eurocopter Emergency Alert Service Bulletin No. 05A010, Revision 2, dated April 22, 2013 (EASB), no further action is required until the next inspection.
(2) If there is open or blind debonding and the debonded area is located outside Area D of Figure 1 of the EASB, before further flight, repair or replace the blade.
(3) If there is open or blind debonding beyond acceptable limits, before further flight, repair or replace the blade.
(4) If there is a cut in the blade root polyurethane protective strip as depicted in Area A of Figure 2 of the EASB, tap test inspect the area.
(i) If there is no open and blind debonding, at intervals not to exceed 15 hours TIS, tap test inspect the blade strip in the blade root area, in the stainless steel leading edge/neoprene junction area for open or blind debonding.
(ii) If there is open or blind debonding within acceptable limits and the debonded area is located inside Area D of Figure 1 of the EASB, no further action is required until the next inspection.
(iii) If there is open or blind and the debonded area is located outside Area D of Figure 1 of the EASB, before further flight, repair or replace the blade.
(iv) If there is open or blind debonding beyond acceptable limits, before further flight, repair or replace the blade.
(5) If there is a crack within acceptable limits, before further flight, seal the crack. If there is a crack beyond the acceptable limits, before further flight, repair or replace the blade.
