Airworthiness Directive · Amendment 39-21701 · Tail rotor system
Leonardo S.p.a. Helicopters
Superseded. A later AD replaced this one: AD 2022-07-11. Comply with the one in force.
This AD applies to Leonardo S.p.a. Model A109C, A109K2, A109E, A109S, and AW109SP helicopters, certificated in any category, all serial numbers.
The FAA is adopting a new airworthiness directive (AD) for all Leonardo S.p.a. Model A109C, A109K2, A109E, A109S, and AW109SP helicopters. This AD was prompted by a report of a crack on the tail rotor (TR) mast. This AD requires an inspection of certain TR sleeve assemblies for discrepancies, an inspection of certain TR shaft assemblies for discrepancies, a repetitive measurement of the position of the bushing of the TR sleeve assembly in relation to the pitch change slider assembly, and corrective actions if necessary, as specified in a European Union Aviation Safety Agency (EASA) AD, which is incorporated by reference. The FAA is issuing this AD to address the unsafe condition on these products.
Except as specified in paragraph (h) of this AD: Comply with all required actions and compliance times specified in, and in accordance with, European Union Aviation Safety Agency (EASA) AD 2021-0144, dated June 17, 2021 (EASA AD 2021-0144).
(1) Where EASA AD 2021-0144 refers to its effective date, this AD requires using the effective date of this AD.
(2) The “Remarks” section of EASA AD 2021-0144 does not apply to this AD.
(3) Where EASA AD 2021-0144 refers to flight hours (FH), this AD requires using hours time-in-service.
(4) Where paragraph (1) of EASA AD 2021-0144 specifies a compliance time of 25 FH or 3 months, whichever occurs first, this AD requires compliance within 25 hours time-in-service after the effective date of this AD.
(5) Where Note 1 of EASA AD 2021-0144 specifies a tolerance of 30 FH, this AD does not allow a tolerance.
(6) Where paragraph (6) of EASA AD 2021-0144 states the term “discrepancies,” for the purposes of this AD discrepancies include dents, corrosion, elongation, scratches, wear, excessive wear (web visible), fretting, or stepping.
(7) Where paragraph (7) of EASA AD 2021-0144 states the term “discrepancies,” for the purposes of this AD discrepancies include abnormal wear condition, corrosion, fretting, crack, or damage (including dents, elongation, scratches, or stepping).
(8) Paragraphs (5) and (9) of EASA AD 2021-0144 do not apply to this AD.
(9) Where EASA AD 2021-0144 defines “serviceable part,” and that definition specifies instructions that are “approved under Leonardo Design Organization Approval (DOA) or by EASA,” for this AD, the repair must be accomplished using a method approved by the Manager, General Aviation and Rotorcraft Section, International Validation Branch, FAA; or EASA; or Leonardo S.p.a.'s EASA DOA. If approved by the DOA, the approval must include the DOA-authorized signature.
(10) Where Note 2, and paragraph (7) of EASA AD 2021-0144 specify instructions that are “approved under Leonardo DOA or by EASA,” for this AD, the repair must be accomplished using a method approved by the Manager, General Aviation and Rotorcraft Section, International Validation Branch, FAA; or EASA; or Leonardo S.p.a.'s EASA DOA. If approved by the DOA, the approval must include the DOA-authorized signature.
(11) Where the service information referenced in EASA AD 2021-0144 specifies to contact the manufacturer for corrective action, this AD requires the repair to be done in accordance with a method approved by the Manager, General Aviation and Rotorcraft Section, International Validation Branch, FAA; or EASA; or Leonardo S.p.a.'s EASA DOA. If approved by the DOA, the approval must include the DOA-authorized signature.
(12) Where the service information referenced in EASA AD 2021-0144 specifies to discard a certain part, this AD requires removing that part from service.
The aircraft, engines and makers this AD names, by the model designations in its text. A model listed here may still be outside the AD's serial ranges.
Aircraft
