1 FAA Aviation Safety EMERGENCY AIRWORTHINESS DIRECTIVE www.faa.gov/aircraft/safety/alerts/

DATE: March 4, 2015 AD #: 20 15 - 05 - 5 2 This e mergency airworthiness directive ( EAD ) 20 15

- 05

- 5 2 is being sent to owners and operators of Agusta S.p.A. (Agusta) Model A109, A109A, A109A II, A109C, A109K2, A109E, A119, A109S, AW119 MKII, and AW109SP helicopter s . Background This EAD was prompted by a report of an in

- flight failure of tail rotor (T/R) pitch control link (pitch link) part number (P/N) 109

- 0130

- 05

- 117 on an Agusta Model AW119 MKII helicopter

. This EAD requires inspecting certain pitch links P/N 109

- 0130

- 05

- 117 for freedom of movement, corrosion, excessive friction of the spherical bearings , and cracks

. These EAD actions are intended to prevent loss of T/R pit ch control and subsequent loss of control of the helicopter. Discussion The European Aviation Safety Agency (EASA), which is the Technical Agent for the Member States of the European Union, issued EASA E AD No. 2015

- 0035

- E , dated February 27, 2015 (2015

- 0035

- E) , to correct an unsafe condition for AgustaWestland S.p.A. Model A109A, A109AII, A109C, A109E, A109K2, A109LUH, A109S, AW109SP A119, and AW119MKII helicopters , all serial numbers . EASA advises of the reported “ in

- flight breaking ” of the T/R pitch c ontrol link P/N 109

- 0130

- 05

- 117

. EASA EAD 2015

- 0035

- E requires inspecting the T/R pitch control link for corrosion , rotation resistance and/or binding, and cracks

. FAA’s Determination These helicopters have been approved by the aviation authority of Italy and a re approved for operation in the United States. Pursuant to our bilateral agreement with Italy , EASA, its technical representative, has notified us of the unsafe condition described in the EASA E AD. We are issuing this E AD because we evaluated all in formation provided by EASA and determined the unsafe condition exists and is likely to exist or develop on other helicopters of these same type designs. Related Service Information AgustaWestland issued Alert Bollettino Tecnico (BT) No s . 109

- 145, 109EP

- 141, 109K

- 65 , 109S

- 065, 109SP

- 087, and 119

- 072, all revision A, and all dated February 27, 2015. These alert BTs specify inspection s of pitch link P/N 109

- 0130

- 05

- 117 for corrosion, freedom of movement, excessive friction of the spherical bearings, and cra cks

. EAD Requirements This EAD requires i nspect ing the pitch link for freedom of movement for rotation resistance or binding

. This EAD also requires removing the pitch link and inspecting each pitch link spherical bearing for corrosion and the force requir ed to rotate each pitch link spherical bearing. If there is any corrosion, the pitch link is unairworthy. If the force required to rotate a spherical bearing in either end2 of the pitch link is greater than 7.30 N (1.64 pounds force), the pitch link is unai rworthy. If the force required to rotate the spherical bearings in both ends of the pitch link is equal to or less than 7.30 N (1.64 pounds force), this EAD requires cleaning and visually inspect ing the pitch link rod for a crack using a 10x or higher powe r magnifying glass or by performing a dye penetrant inspection. If there is a crack, the pitch link is unairworthy. Inte rim Action We consider this EAD to be an interim action. If final action is later identified, we might consider further rulemaking. Aut hority for this Rulemaking Title 49 of the United States Code specifies the FAA’s authority to issue rules on aviation safety. Subtitle I, Section 106, describes the authority of the FAA Ad ministrator. “ Subtitle VII, Aviation Programs, ” describes in more detail the scope of the Agency’s authority. We are issuing this rulemaking under the authority described in “ Subtitle VII, Part A, Subpart III, Section 44701, General requirements.” Under that section, Congress charges the FAA with promoting safe flight o f civil aircraft in air commerce by prescribing regulations for practices, methods, and procedures the Ad ministrator finds necessary for safety in air commerce. This regulation is within the scope of that authority because it ad dresses an unsafe condition that is likely to exist or develop on products identified in this rulemaking action. Ad option of the E mergency A irworthiness D irective ( EAD ) We are issuing this EAD under 49 U.S.C. Section s 106(g), 40113, and 44701 according to the authority delegated to m e by the Ad ministrator. 20 15

- 05

- 5 2 Agusta S.p.A. : D irectorate Identifier 20 15

- SW

- 007

- AD

. ( a ) Applicability This EAD applies to A gusta S.p.A. Model A109, A109A, A109A II, A109C, A109K2, A109E, A119, A109S, AW119 MKII, and AW109SP helicopters , certificated i n any category , with a tail rotor pitch control link (pitch link) part number 109

- 0130

- 05

- 117 with 100 hours or less time

- in

service since overhaul

. ( b ) Unsafe Condition This EAD defines the unsafe condition as failure of a pitch link

. This condition coul d result in loss of tail rotor pitch control and subsequent loss of control of the helicopter. (c) Effective Date This E AD is effective upon receipt. ( d ) Compliance You are responsible for performing each action required by this EAD within the specified co mpliance time unless it has alr ead y been accomplished prior to that time.3 ( e ) Required Actions (1) Before further flight , i nspect the pitch link for freedom of movement while it is installed on the helicopter. (i) If there is rotation resistance or bindin g, before further flight, perform the actions in paragraph s ( e) ( 2 ) through (e)(3) of this EAD

. (ii) If there is no rotation resistance and no binding, within 5 hours time

- in

- service, perform the actions in paragraphs (e)(2) through (e)(3) of this EAD

. ( 2 ) Remove the pitch link and i nspect each pitch link spherical bearing for corrosion. If there is any corrosion, the pitch link is un airworthy. ( 3 ) Determine the force required to rotate each pitch link spherical bearing as depicted in Figure 1 of AgustaWestl and Alert Bollettino Tecnico (BT) No. 109

- 145, 109EP

- 141, 109K

- 65, 109S

065, 109SP

- 087, or 119

- 072, all revision A, and all dated February 27, 2015, as applicable to your model helicopter. ( i ) If the force required to rotate a spherical bearing in either e nd of the pitch link is greater than 7.30 N (1.64 pounds force), the pitch link is unairworthy. (i i ) If the force required to rotate the spherical bearing s in both ends of the pitch link is equal to or less t han 7.30 N (1.64 pounds force), after clean ing t he pitch link rod using aliphatic naphtha or equivalent and a s oft non

- metallic bristle brush, visually inspect the pitch link rod for a crack in the area depicted in Figure 1 of AgustaWestland Alert BT No. 109

- 145, 109EP

- 141, 109K

- 65, 109S

- 065, 109SP

- 087, or 119

- 072, all revision A, and all dated February 27, 2015, as applicable to your model helicopter , using a 10x or higher power magnifying glass or by d ye penetrant inspection. If there is a crack, the pitch link is unairworthy. ( f

) Alternative Methods o f Compliance (AMOCs) (1) The Ma nager, Safety Management Group , FAA, m a y approve AMOCs for this EAD

. S end your proposal to: Martin Crane, Aviation Safety Engineer, Rotorcraft Certification Office, Rotorcraft Directorate, FAA, 2601 Meacham Blvd., Fort Worth, Texas 76137; telephone (817) 222

- 5 110 ; email m artin. r . c rane@faa.gov

. ( 2 ) For operations conducted under a 14 CFR p art 119 operating certificate or under 14 CFR p art 91, s ubpart 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 EAD through an AMOC. ( g ) Ad ditional Information . (1) For further information contact: Martin Cra ne, Aviation Safety Engineer, Rotorcraft Certification Office, Rotorcraft Directorate, FAA, 2601 Meacham Blvd., Fort Worth, Texas 76137; t elephone (817) 222

- 5 110 ; email m artin. r . c rane@faa.gov

. (2) For a copy of the service information referenced in this AD , contact: AgustaWestland, Product Support Engineering, Via del Gregge, 100, 21015 Lonate Pozzolo (VA) Italy, ATTN: Maurizio D’Angelo; telephone 39

- 0331

- 664757; fax 39 0331

- 664680; or at http://www.agustawestland.com/technical

- bulletins

.4 ( 3 ) The subject o f this AD is addressed in European Aviation Safety Agency E A D No. 2015

- 0035

- E, dated February 27, 2015

. ( h ) Subject Joint Aircraft Service Component (JASC) Code: 6720, Tail Rotor Controls. Issued in Fort Worth, Texas , on March 4, 2015. Bruce E. Cain, A cting Directorate Manager, Rotorcraft Directorate, Aircraft Certification Service.