Airworthiness Directive · Amendment 39-22507 · Main rotor gearbox
Airbus Helicopters
This AD applies to all Airbus Helicopters Model EC155B1 helicopters, certificated in any category.
The FAA is adopting a new airworthiness directive (AD) for all Airbus Helicopters Model EC155B1 helicopters. This AD was prompted by reports of failure of the main gearbox (MGB) oil cooling fan hub (fan hub). This AD requires, for helicopters with an affected part (fan hub) installed, using an endoscope, repetitively inspecting the fan hub, including the area around the fan hub attachment screws, for a crack. Depending on the inspection results, this AD requires performing additional inspections and replacing an affected fan hub. This AD also allows an affected fan hub to be installed on a helicopter if certain actions are accomplished, 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 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 (EASA) AD 2022-0006R2, dated January 31, 2022 (EASA AD 2022-0006R2).
(1) Where EASA AD 2022-0006R2 requires compliance in terms of flight hours, this AD requires using hours time-in-service (TIS).
(2) Where EASA AD 2022-0006R2 refers to its effective date, this AD requires using the effective date of this AD.
(3) Where paragraph (2.2) of EASA AD 2022-0006R2 requires within 50 FH [flight hours] after crack detection around the attachment screw, replace the affected part [fan hub] with a serviceable part, for this AD, within 50 hours TIS after crack detection around the attachment screw, remove the affected fan hub from service, and replace it with a serviceable fan hub.
(4) Where paragraph (3) of EASA AD 2022-0006R2 requires replacing an affected part with a serviceable part before next flight if any crack is detected in any area other than around the attachment screw, for this AD, if any crack is detected in any area other than around the attachment screw, before further flight, remove the affected fan hub from service, and replace it with a serviceable fan hub.
(5) Where the service information referenced in EASA AD 2022-0006R2 specifies to “make sure that there is no crack,” this AD requires inspecting the area for a crack.
(6) Where the service information referenced in EASA AD 2022-0006R2 specifies to discard certain parts, this AD requires removing those parts from service.
(7) Where the service information referenced in EASA AD 2022-0006R2 specifies creating a Technical Event and sending certain information to Airbus Helicopters, this AD does not include those requirements.
(8) Where the service information referenced in EASA AD 2022-0006R2 specifies to use tooling, this AD allows the use of equivalent tooling.
(9) This AD does not adopt the “Remarks” section of EASA AD 2022-0006R2.
Although the service information referenced in EASA AD 2022-0006R2 specifies to submit certain information to the manufacturer, this AD does not include that requirement.
