| 1 |
FAA 2026-04-01 |
This AD was prompted by a report that the measured resistance value of the pyrotechnic cartridge of the engine fire extinguisher was out of tolerance. The FAA is issuing this AD to detect and address degradation of the pyrotechnic cartridge. The unsafe condition, if not addressed, could result in failure of the cartridge to activate the engine fire extinguisher in the case of an engine fire with consequent damage to the helicopter or injury to occupants. |
SA330J |
|
|
|
| 2 |
FAA 2026-03-07 |
This AD was prompted by a determination that new and more restrictive airworthiness limitations are necessary. The FAA is issuing this AD to address a safety-significant latent failure (that is not annunciated) that, in combination with one or more other specific failures or events, could result in hazardous or catastrophic failure condition. |
A330-201 | A330-202 | A330-203 | A330-223 | A330-223F | A330-243 | A330-243F | A330-301 | A330-302 | A330-303 | A330-321 | A330-322 | A330-323 | A330-341 | A330-342 | A330-343 | A330-841 | A330-941 |
FAA 2024-08-05 |
|
|
| 3 |
FAA 2026-03-08 |
This AD was prompted by report of excessive axial play of the scissors spherical bearings (rotating and non-rotating). The FAA is issuing this AD to address excessive axial play of the scissors spherical bearings. The unsafe condition, if not addressed, could result in reduced control of the helicopter. |
H160-B |
FAA 2025-07-06 |
|
|
| 4 |
FAA 2026-03-06 |
This AD was prompted by the manufacturer's revision of the aircraft maintenance manual (AMM) to introduce more restrictive inspection intervals. The FAA is issuing this AD to prevent undetected cracks in the engine mount and vertical stabilizer front and rear spar caps. The unsafe condition, if not addressed, could result in reduced structural integrity and consequent reduced controllability of the airplane. |
525B |
|
|
|
| 5 |
FAA 2026-02-09 |
This AD was prompted by reports of a cracked main gearbox (MGB) support case. The FAA is issuing this AD to prevent structural failure of the MGB support case. The unsafe condition, if not addressed, could result in loss of control of the helicopter. |
AB412 | AB412 EP |
|
|
|
| 6 |
FAA 2026-03-02 |
This AD was prompted by fatigue crack found on the ring frame ring that attaches the fuselage tail boom structure to the tail rotor housing. The FAA is issuing this AD to detect and address fatigue cracking in the ring frame. The unsafe condition, if not addressed, could result in loss of a tail rotor and consequent loss of control of the helicopter. |
This AD applies to Airbus Helicopters Deutschland GmbH (AHD) Model EC135P1, EC135P2, EC135P2+, EC135P3, EC135T1, EC135T2, EC135T2+, EC135T3, and EC635T2+ helicopters, certificated in any category with mounting ring frame X9227, part number (P/N) L535H2120301, L535H2120303, or L535H2120304, installed, except those with frame reinforcement P/N L535H2100201 or L535H2100202 installed.
Note 1 to paragraph (c): Helicopters with an EC135P3H designation are Model EC135P3 helicopters. Helicopters with EC135T3H designation are Model EC135T3 helicopters |
FAA 2014-13-09 |
|
|
| 7 |
FAA 2026-02-07 |
This AD was prompted by reports that certain lower torque links of the nose landing gear (NLG) were manufactured without bright shot peening; the omission of bright shot peening could result in reduced fatigue life of the parts. The FAA is issuing this AD to address omitted bright shot peening. The unsafe condition, if not addressed, could lead to failure of the nose landing gear, possibly resulting in damage to the airplane and injury to occupants. |
A350-941 | A350-1041 |
|
|
|
| 8 |
FAA 2026-02-11 |
This AD was prompted by an inconsistency identified in the takeoff calculation module of the computerized airplane flight manual (CAFM). The FAA is issuing this AD to address the inconsistency which could lead to an erroneous calculation that, in certain operating conditions and airports, could result in the airplane being unable to overcome obstacles in the first segment of the takeoff flight path in the event of an engine failure during takeoff. |
ERJ 190-300 | ERJ 190-400 |
|
|
|
| 9 |
FAA 2026-03-01 |
This AD was prompted by reports of electronic centralized aircraft monitor (ECAM) messages requiring flight control remote module (FCRM) replacement linked to solder structural fatigue. The FAA is issuing this AD to address potential failure of a flight control actuator. The unsafe condition, if not addressed, could result in reduced control of the airplane. |
A350-941 | A350-1041 |
|
|
|
| 10 |
FAA 48-27-03 |
Propeller Hub Peening |
649-79 | 749-79 |
|
|
|