The purpose of this CAN is to notify helicopter operators and maintenance providers of a number of recent occurrences reported to CAA of finding excessive play in AS350 tail rotor pitch control rod ball joints. Recently reported findings appear limited to pitch control rods manufactured under a FAA PMA by EXTEX.
This Continued Airworthiness Notice (CAN) alerts operators and maintenance providers of possible safety concerns related to incorrect assembly of the throttle cable to the Fuel Control Unit (FCU) on Gippsland GA8 Airvan aircraft.
This Continuing Airworthiness Notice (CAN) is issued to bring attention to defect reports submitted to the CAA of finding corrosion in the attachment lugs of fuselage extrusion P/N 28-2-1095-1 on five P2008 aircraft. For further details of the location of the corrosion found, refer to the photos in this CAN.
This Continuing Airworthiness Notice (CAN) is issued to bring attention to a defect report submitted to the CAA of finding cracks in the stabilator torque tubes on ten P2008 aircraft. For further details of the location of the cracks found, refer to the two photos in this CAN.
The purpose of this CAN is to notify affected helicopter operators and maintenance providers of a recent occurrence reported to the CAA of finding a significant crack in the tail rotor gearbox on a 369D helicopter.
CAA received a report from a maintenance provider of finding an Airwolf Aerospace Tension-Torsion strap with a PMA/STC holder log card which specified an incorrect life limit.
The purpose of this Continuing Airworthiness Notice (CAN) is to provide guidance for aircraft operators and maintenance engineers regarding compliance with Airworthiness Directives.
The purpose of this CAN is to notify helicopter operators and maintenance providers of a recent occurrence reported to the CAA of significant cracks found in the 4 Bladed Tail Rotor Hub of a MD500 helicopter.
The purpose of this CAN is to notify helicopter operators and maintenance providers of a recent occurrence reported to CAA of a winch cable which was damaged during a winching operation.
This Continuing Airworthiness Notice (CAN) is issued to bring attention to an issue reported to the CAA recently, where MS21042L3 nuts appeared to lose their self-locking function during installation.
The purpose of this CAN is to notify helicopter operators and maintenance providers of two recent occurrences reported to CAA of helicopter windows departing the aircraft doors during the first flight following window installation.
The purpose of this CAN is to notify helicopter operators of a number of recent occurrences recently reported to CAA of failures of lifting equipment, specifically load cells.
The purpose of this CAN is to notify MD369 helicopters operators and maintenance providers of occurrences recently reported to CAA of finding duplex bearing distress in numerous MD369 Tail Rotor Gearboxes (TRG).
The purpose of this Continuing Airworthiness Notice (CAN) is to provide guidance about manufacturers’ service information, such as Service Bulletins (SB), Service Letters (SL) etc.
The purpose of this Continuing Airworthiness Notice (CAN) is to advise MD helicopter operators and maintainers of a possible safety concern with the thruster control output drum assembly..
The purpose of this Continuing Airworthiness Notice (CAN) is to advise operators and maintainers of Guimbal Cabri G2 helicopters, of a possible safety issue with the main rotor swashplate assembly.
This Continuing Airworthiness Notice (CAN) at Revision 2 is revised to clarify the component maintenance requirements below and add a recommendation to replace parts which have reached the manufacturers recommended replacement interval, and inform aircraft operators and maintainers that Robinson Helicopters Corporation (RHC) have revised the component maintenance requirements in Chapter 1.102 of the R44 Series Maintenance Manual dated December 2021. Refer: https://robinsonheli.com/r44-maint-manual/ The revised component maintenance requirements: Electric Fuel Pump P/N D743-1, -2, -3 and -4 must be replaced with a new P/N D743-3 pump at 2200 hours TTIS; and Fuel Pressure Relief Valve P/N D321-1 must be replaced with a new or overhauled part at 12 years, or before 2200 hours TTIS.
The CAA has received a report of an incident where an operator experienced an in-flight failure of a cargo hook swing frame eyebolt attachment. Refer to Figure 1 in the CAN for a photograph of the failed part.
CAN 27-025 Revision 1 revised to expand the applicability to include AS 355 series helicopters. The intent of this CAN is to raise awareness among operators and maintenance providers of the importance of thoroughly completing the necessary duplicate safety inspections, ensuring correct assembly and function. Where necessary, reference should be made to the relevant Instructions for Continued Airworthiness. Operators are also reminded of the value of assessing manufacturers service information and establishing the configuration of an aircraft when inducting it into their fleet.
The intent of this CAN is to raise awareness among operators and maintenance providers of the importance of operators ensuring that they assess and give due consideration to following manufacturer service information.
