TBM700 · 850 · 900 series

Cracks have been found on the outboard hinge fittings of certain TBM 700 airplanes. This AD requires inspection and corrective actions to address these cracks.

Landing gear actuator rods and pistons can become unscrewed during operation, and ball joints can become uncrimped, creating a landing gear failure risk. This AD requires inspection and corrective actions to address the unsafe condition on the landing gear actuator system.

An incorrect part number may have been installed during nose landing gear overhaul on some TBM 700 airplanes. This AD requires inspecting and correcting any incorrect landing gear installations.

Installation of switched aileron control cables in the wing can restrict aileron movement and reduce airplane control. This AD requires inspection and correction of aileron control cable installation.

An unsafe condition has been identified on certain SOCATA TBM 700 airplanes that requires corrective action. This AD mandates inspection and correction of the identified condition on affected aircraft.

This airworthiness directive addresses an unsafe condition identified on SOCATA TBM 700 airplanes through mandatory continuing airworthiness information. The specific corrective actions and inspection requirements are detailed in the full directive.

This AD supersedes a previous directive for the SOCATA TBM 700 following mandatory continuing airworthiness information to correct an unsafe condition. Operators must comply with the requirements specified in the superseding AD.

A chemical oxygen generation system on certain TBM 700 airplanes may present an unsafe condition. This AD requires implementing a SOCATA modification that terminates the requirement.

An unsafe condition has been identified on SOCATA Model TBM 700 airplanes that requires corrective action. This AD requires operators to implement the mandatory continuing airworthiness information to identify and correct the unsafe condition.

This AD addresses an unsafe condition on SOCATA TBM 700 airplanes identified through mandatory continuing airworthiness information from another aviation authority. The AD requires corrective actions to address the identified unsafe condition.

This AD addresses an unsafe condition identified on SOCATA Model TBM 700 airplanes through mandatory continuing airworthiness information from another aviation authority. Operators must comply with the requirements of this AD to correct the identified unsafe condition.

Loose rivets on frames C18 BIS and C19 could reduce structural integrity of the tail area. The AD requires inspection of these rivets and corrective action if necessary.

An unsafe condition has been identified on SOCATA TBM 700 airplanes. The AD requires corrective action as mandated by continuing airworthiness information.

This airworthiness directive addresses an unsafe condition identified on EADS SOCATA TBM 700 airplanes. The AD requires compliance with corrective actions as detailed in the directive.

This AD addresses an unsafe condition identified on EADS SOCATA TBM 700 airplanes through mandatory continuing airworthiness information from another aviation authority. Operators must comply with the requirements specified in the AD to correct the identified unsafe condition.

This airworthiness directive addresses an unsafe condition on EADS SOCATA Model TBM 700 airplanes. The AD requires inspection and/or corrective action as mandated by continuing airworthiness information from aviation authorities.

This AD addresses an unsafe condition on EADS SOCATA Model TBM 700 airplanes identified through mandatory continuing airworthiness information from another aviation authority. The AD supersedes a previous directive and requires compliance with corrective actions to restore safe operations.

An unsafe condition has been identified on TBM 700 airplanes that requires correction through mandatory continuing airworthiness information. The AD requires operators to take corrective action as specified to restore the airplane to a safe condition.

An unsafe condition has been identified on EADS SOCATA TBM 700 airplanes that requires corrective action. This AD mandates the necessary fixes to return the aircraft to an airworthy condition.

An unsafe condition has been identified on EADS SOCATA TBM 700 airplanes. This airworthiness directive requires corrective actions to address the unsafe condition.

Propeller control cables may have defective crimping where cable ends are uncrimped, creating an unsafe condition. The AD requires inspection and corrective actions on affected propeller control cables.

Two fatigue failures of flap carriage rollpins have occurred on in-service TBM 700 airplanes. This AD requires actions to correct the unsafe condition caused by these fatigue failures.

Some pulley brackets have improper geometry that can offset the cable in the sheave. This AD requires corrective actions to address this unsafe condition.

An excessive lateral play caused by a nonconforming washer in the elevator trim tab bearing may lead to deterioration of fatigue resistance. This AD requires correcting the nonconforming washer condition.

A master cylinder yoke failure has been reported on certain TBM 700 aircraft. This AD requires inspection and corrective action to prevent master cylinder yoke failure.

The elevator trim actuator may be inadequately greased, causing icing of the elevator trim system and an untrimmed nose-up attitude after autopilot disconnection. This AD requires corrective actions to address the unsafe condition.

Cracks in the fuselage skin near the VHF1 antenna mounting area could cause loss of pressurization and incapacitate the flight crew. Inspect the fuselage skin in that area for cracks and loose rivets, and modify if defects are found.

Flap attaching bolts and screws may become loose and separate from the airplane, causing rough or irregular control that could lead to loss of control. The AD requires applying Loctite to bolt and screw threads, increasing tightening torques, replacing central carriage attaching bolts, and inspecting flap carriage attaching bolts, screws, and barrel nuts.

Water can accumulate in the fuselage, freeze, and seize the elevator controls, causing loss of airplane control. Install a new strainer draining system in the cabin fuselage.

External electrical noise can cause inaccurate course deviation displays on GNS 430 units, potentially leading pilots to make unsafe flight decisions. This AD requires modification of affected GNS 430 units to incorporate circuitry changes that prevent external noise from degrading course deviation and flag outputs.

Certain TBM 700 airplanes may have defective Amendment A fuel tank air vent valves that can cause abnormal venting and structural damage to wing skins during flight. This AD requires inspection for defective valves and replacement with improved design parts.

Oil from the engine breather vent can enter the gaseous oxygen system service compartment, creating a fire or explosion hazard. This AD requires relocating the oil breather vent to prevent contamination of the oxygen system.

The propeller governor flexible cable can harden or block, preventing propeller pitch control and feathering, which could lead to loss of airplane control. Install a thermal protection sleeve on the propeller governor flexible cable.

Certain TBM 700 airplanes may have a low point in the fuel tank air vent valve hose that can cause abnormal venting and wing skin damage, leading to handling problems or structural failure. Inspect for and reroute the hose as necessary to restore proper venting.

Flightcrews may not activate pneumatic wing and tail deicing boots at the first signs of ice accumulation, risking reduced aircraft controllability. This AD requires revising the Airplane Flight Manual to include procedures for activating the airframe pneumatic deicing boots.

Cracks can develop in the flap carriage web, potentially causing loss of flap function and reduced airplane control. The AD requires repetitive visual inspections of the left and right flap carriage for cracks and replacement of any cracked carriage with an improved design.

BFGoodrich SKYWATCH SKY497 installations with top-mounted antennas can experience internal component failure that changes the antenna configuration, causing target indicators to display on the wrong side of the aircraft. This AD requires verifying correct antenna configuration at power-up and removing from service any installations with incorrect antenna configuration.

Oxygen generators in certain TBM 700 airplanes may fail due to firing pin misalignment, risking crew incapacitation and loss of the airplane. This AD requires modification of the oxygen generators.

Cracks in elevator trim tab fittings could cause the trim tab to separate, resulting in loss of control of the airplane. This AD requires inspecting the elevator trim tab fittings for cracks and replacing any trim tabs found to have cracks.

Interference between the left-hand front side lower panel trim and the roll control compass on the left wheel assembly could result in loss of directional control. This AD requires modifying the left-hand front side lower panel.

The starter generator mounting adapter on certain TBM 700 airplanes can fail, causing loss of the starter generator and electrical power. This AD requires replacement of the mounting adapter with an improved design.

This AD requires revising the Airplane Flight Manual to prohibit flight in severe icing conditions and limit use of flight control devices in icing. Operators must follow new procedures for recognizing and exiting severe icing conditions.

Corroded main landing gear inboard door locking hinges can jam the doors and prevent the landing gear from extending. This AD requires removing the main landing gear inboard doors and door locking control mechanism.

Certain PT6 series turboprop engines may have defective compressor bleed-off valves due to improper cotter pins or guide shaft pins, which could cause inflight engine power reduction and a forced landing. This AD requires a one-time visual inspection of the bleed valve cover, and if an affected supplier code is found, removal and inspection of the valve assembly with modification or replacement if defects are discovered.