AD 2014-04-13 Airworthiness Directives; Agusta S.p.A. Helicopters

This AD becomes effective March 25, 2014.

(1) The Manager, Safety Management Group, FAA, may approve AMOCs for this AD. Send your proposal to: Robert Grant, Aviation Safety Engineer, Safety Management Group, FAA, 2601 Meacham Blvd., Fort Worth, Texas 76137; telephone (817) 222-5110; email robert.grant@faa.gov. (2) For operations conducted under a 14 CFR part 119 operating certificate or under 14 CFR part 91, subpart K, we suggest that you notify your principal inspector, or lacking a principal inspector, the manager of the local flight standards district office or certificate holding district office, before operating any aircraft complying with this AD through an AMOC.

The subject of this AD is addressed in the European Aviation Safety Agency (EASA) AD. No. 2013-0185, dated August 14, 2013. You may view the EASA AD on the Internet at http://www.regulations.gov in Docket No. FAA-2014-0109.

(1) Within 25 hours time-in-service (TIS) or 30 days, whichever occurs first, and thereafter at intervals not to exceed 25 hours TIS or 30 days, whichever occurs first: (i) Clean each T/R blade by hand using a mild soap and cheesecloth on both sides of the blade in a spanwise direction and dry thoroughly. (ii) Using a 3X or higher power magnifying glass and a light, visually inspect the T/R blade skin, leading edge spar, doublers, grip plates, and trailing edge on both sides of each blade for a crack, corrosion (which may be indicated by blistering, peeling, flaking, bubbling, or cracked paint), a nick, a scratch, a dent, or other damage. Pay particular attention to both sides of each T/R blade in the area located 16 to 32 inches from the T/R blade tip (blade station 20.00 to 35.00; the T/R blade tip is located at blade station 51) as depicted by the shaded area in Figure 2 of AgustaWestland Bollettino Tecnico No. 412-136, dated August 13, 2013 (BT). Also, pay particular attention to the inboard T/R blade butt area near the attachment of the external balance weight and screws and to any T/R blade surface that was snagged by cheesecloth, as this may be an indication of a crack or paint chip that could lead to corrosion. (iii) Using a 10X or higher power magnifying glass and a light, visually inspect both sides of each T/R blade for a crack, corrosion (which may be indicated by blistering, peeling, flaking, bubbling, or cracked paint), a nick, a scratch, a dent or other damage between blade station 20.00 to 35.00 as depicted by the shaded area in Figure 2 of the BT. (iv) If there is any blistering, peeling, flaking, bubbling, or cracked paint on a T/R blade, remove the paint from the affected area by sanding in a spanwise direction first with abrasive cloth or paper 240-grit or finer and then with abrasive cloth or paper 400-grit or finer. After paint removal, wipe area with a clean cloth dampened with alcohol and dry thoroughly and then visually inspect the affected area for any corrosion or a crack using a 10X or higher power magnifying glass and a light. If any corrosion is found, measure the depth of the damage. (v) If there is a nick, scratch, or dent on the T/R blade, visually inspect for a crack using a 10X or higher power magnifying glass and a light. Measure the depth of the damage. (2) Before further flight, remove from service any T/R blade that has a crack, corrosion, a nick, a scratch, a dent, or other damage that exceeds any of the maximum repair damage limits. (3) Before further flight, repair or remove from service any T/R blade that has corrosion, a nick, a scratch, a dent or other damage that is within the maximum repair damage limits. (4) Do not install on any helicopter T/R blade P/N 212-010-750 (all dash numbers) unless it has been inspected in accordance with the requirements of this AD.

This AD defines the unsafe condition as fatigue cracking of a T/R blade, which could lead to failure of the T/R blade and subsequent loss of control of the helicopter.