diff --git a/src/modules/fw_pos_control_l1/mtecs/mTecs.cpp b/src/modules/fw_pos_control_l1/mtecs/mTecs.cpp
index c6301bcdb5..94a614bc03 100644
--- a/src/modules/fw_pos_control_l1/mtecs/mTecs.cpp
+++ b/src/modules/fw_pos_control_l1/mtecs/mTecs.cpp
@@ -51,6 +51,8 @@ mTecs::mTecs() :
 	/* Parameters */
 	_mTecsEnabled(this, "ENABLED"),
 	_airspeedMin(this, "FW_AIRSPD_MIN", false),
+	/* Publications */
+	_status(&getPublications(), ORB_ID(tecs_status)),
 	/* control blocks */
 	_controlTotalEnergy(this, "THR"),
 	_controlEnergyDistribution(this, "PIT", true),
@@ -97,6 +99,11 @@ int mTecs::updateAltitudeSpeed(float flightPathAngle, float altitude, float alti
 		debug("updateAltitudeSpeed: altitudeSp %.4f, altitude %.4f, flightPathAngleSp %.4f", (double)altitudeSp, (double)altitude, (double)flightPathAngleSp);
 	}
 
+	/* Write part of the status message */
+	_status.altitudeSp = altitudeSp;
+	_status.altitude = altitude;
+
+
 	/* use flightpath angle setpoint for total energy control */
 	return updateFlightPathAngleSpeed(flightPathAngle, flightPathAngleSp, airspeed, airspeedSp, mode);
 }
@@ -120,6 +127,13 @@ int mTecs::updateFlightPathAngleSpeed(float flightPathAngle, float flightPathAng
 		debug("updateFlightPathAngleSpeed airspeedSp %.4f, airspeed %.4f, accelerationLongitudinalSp%.4f", (double)airspeedSp, (double)airspeed, (double)accelerationLongitudinalSp);
 	}
 
+	/* Write part of the status message */
+	_status.flightPathAngleSp = flightPathAngleSp;
+	_status.flightPathAngle = flightPathAngle;
+	_status.airspeedSp = airspeedSp;
+	_status.airspeed = airspeed;
+
+
 	/* use longitudinal acceleration setpoint for total energy control */
 	return updateFlightPathAngleAcceleration(flightPathAngle, flightPathAngleSp, airspeed, accelerationLongitudinalSp, mode);
 }
@@ -144,18 +158,18 @@ int mTecs::updateFlightPathAngleAcceleration(float flightPathAngle, float flight
 		airspeedDerivative = _airspeedDerivative.update(airspeed);
 	}
 	float airspeedDerivativeNorm = airspeedDerivative / CONSTANTS_ONE_G;
-	float airspeedSpDerivative = accelerationLongitudinalSp;
-	float airspeedSpDerivativeNorm = airspeedSpDerivative / CONSTANTS_ONE_G;
-	float airspeedSpDerivativeNormError = airspeedSpDerivativeNorm - airspeedDerivativeNorm;
+	float airspeedDerivativeSp = accelerationLongitudinalSp;
+	float airspeedDerivativeNormSp = airspeedDerivativeSp / CONSTANTS_ONE_G;
+	float airspeedDerivativeNormErrorSp = airspeedDerivativeNormSp - airspeedDerivativeNorm;
 
 	float totalEnergyRate = flightPathAngle + airspeedDerivativeNorm;
-	float totalEnergyRateError = flightPathAngleError + airspeedSpDerivativeNormError;
-	float totalEnergyRateSp = flightPathAngleSp + airspeedSpDerivativeNorm;
+	float totalEnergyRateError = flightPathAngleError + airspeedDerivativeNormErrorSp;
+	float totalEnergyRateSp = flightPathAngleSp + airspeedDerivativeNormSp;
 	float totalEnergyRateError2 = totalEnergyRateSp - totalEnergyRate;
 
 	float energyDistributionRate = flightPathAngle - airspeedDerivativeNorm;
-	float energyDistributionRateError = flightPathAngleError - airspeedSpDerivativeNormError;
-	float energyDistributionRateSp = flightPathAngleSp - airspeedSpDerivativeNorm;
+	float energyDistributionRateError = flightPathAngleError - airspeedDerivativeNormErrorSp;
+	float energyDistributionRateSp = flightPathAngleSp - airspeedDerivativeNormSp;
 	float energyDistributionRateError2 = energyDistributionRateSp - energyDistributionRate;
 
 	/* Debug output */
@@ -188,6 +202,14 @@ int mTecs::updateFlightPathAngleAcceleration(float flightPathAngle, float flight
 		outputLimiterPitch = &_BlockOutputLimiterUnderspeedPitch;
 	}
 
+	/* Write part of the status message */
+	_status.airspeedDerivativeSp = airspeedDerivativeSp;
+	_status.airspeedDerivative = airspeedDerivative;
+	_status.totalEnergyRateSp = totalEnergyRateSp;
+	_status.totalEnergyRate = totalEnergyRate;
+	_status.energyDistributionRateSp = energyDistributionRateSp;
+	_status.energyDistributionRate = energyDistributionRate;
+
 	/** update control blocks **/
 	/* update total energy rate control block */
 	_throttleSp = _controlTotalEnergy.update(totalEnergyRateSp, totalEnergyRateError, outputLimiterThrottle);
@@ -203,6 +225,8 @@ int mTecs::updateFlightPathAngleAcceleration(float flightPathAngle, float flight
 				(double)accelerationLongitudinalSp, (double)airspeedDerivative);
 	}
 
+	/* publish status messge */
+	_status.update();
 
 	/* clean up */
 	_firstIterationAfterReset = false;
diff --git a/src/modules/fw_pos_control_l1/mtecs/mTecs.h b/src/modules/fw_pos_control_l1/mtecs/mTecs.h
index 147c108f3d..376d396986 100644
--- a/src/modules/fw_pos_control_l1/mtecs/mTecs.h
+++ b/src/modules/fw_pos_control_l1/mtecs/mTecs.h
@@ -47,6 +47,8 @@
 
 #include <controllib/block/BlockParam.hpp>
 #include <drivers/drv_hrt.h>
+#include <uORB/Publication.hpp>
+#include <uORB/topics/tecs_status.h>
 
 namespace fwPosctrl
 {
@@ -97,6 +99,9 @@ protected:
 	control::BlockParamInt _mTecsEnabled;		/**< 1 if mTecs is enabled */
 	control::BlockParamFloat _airspeedMin;		/**< minimal airspeed */
 
+	/* Publications */
+	uORB::Publication<tecs_status_s> _status;	/**< publish internal values for logging */
+
 	/* control blocks */
 	BlockFFPILimitedCustom _controlTotalEnergy;		/**< FFPI controller for total energy control: output is throttle */
 	BlockFFPILimitedCustom _controlEnergyDistribution;	/**< FFPI controller for energy distribution control: output is pitch */