Airworthiness Directive · Amendment 39-22441 · Main rotor system
Leonardo S.p.a. Helicopters
This AD applies to all Leonardo S.p.a. Model AB139 and AW139 helicopters, certificated in any category.
The FAA is superseding Emergency Airworthiness Directive (AD) 2023-07-51, which applied to all Leonardo S.p.a. Model AB139 and AW139 helicopters and which was previously sent to all known U.S. owners and operators of those helicopters. Emergency AD 2023-07-51 required inspecting for a gap between the main rotor (M/R) pitch link upper rod end assembly bearing and the pitch control lever assembly and, depending on the results, replacing or re-identifying the M/R pitch link upper rod end assembly. Emergency AD 2023-07-51 also prohibited installing an affected M/R pitch link upper rod end assembly. Since the FAA issued Emergency AD 2023-07-51, it has been determined that a gap between the M/R pitch link upper rod end assembly bearing and the pitch control lever assembly that is within a certain dimension tolerance is acceptable. This AD continues to require the actions in Emergency AD 2023-07-51, as specified in a European Union Aviation Safety Agency (EASA) AD, which is incorporated by reference in this AD, but allows a gap of less than 0.5 mm. The FAA is issuing this AD to address the unsafe condition on these products.
Except as specified in paragraphs (h) and (i) of this AD: Comply with all required actions and compliance times specified in, and in accordance with, European Union Aviation Safety Agency Emergency AD 2023-0071-E, dated March 31, 2023 (EASA AD 2023-0071-E).
(1) Where EASA AD 2023-0071-E refers to its effective date, this AD requires using the effective date of this AD.
(2) Where EASA AD 2023-0071-E requires compliance in terms of flight hours, this AD requires using hours time-in-service.
(3) Where paragraph (1) of EASA AD 2023-0071-E states, “before next flight;” for this AD, replace that text with, “within four calendar days.”
(4) Where paragraph (1) of EASA AD 2023-0071-E requires a dimensional check, this AD requires an inspection for a gap.
(5) Instead of complying with paragraph (2) of EASA AD 2023-0071-E, comply with the following: “As a result of the inspection required by paragraph (1) of EASA AD 2023-0071-E, for this AD, if there is any gap that measures 0.5 mm or more between the M/R pitch link upper rod end assembly bearing and the pitch control lever assembly on either side, before further flight, remove the affected part, as defined in EASA AD 2023-0071-E, from service and replace it with a serviceable part, as defined in EASA AD 2023-0071-E.”
(6) Where paragraph (3) of EASA AD 2023-0071-E states, “Within 25 flight hours, or at the next removal of an affected part, whichever occurs first;” for this AD, replace that text with, “Within 25 hours time-in-service.”
(7) This AD does not adopt the “Remarks” section of EASA AD 2023-0071-E.
Although the service information referenced in EASA AD 2023-0071-E specifies to submit certain information to the manufacturer, this AD does not include that requirement.
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
