diff --git a/src/modules/vtol_att_control/standard.cpp b/src/modules/vtol_att_control/standard.cpp
index 8a5896999e..c5a015eb4d 100644
--- a/src/modules/vtol_att_control/standard.cpp
+++ b/src/modules/vtol_att_control/standard.cpp
@@ -54,6 +54,7 @@ Standard::Standard(VtolAttitudeControl *attc) :
 	_mc_roll_weight = 1.0f;
 	_mc_pitch_weight = 1.0f;
 	_mc_yaw_weight = 1.0f;
+	_mc_throttle_weight = 1.0f;
 
 	_params_handles_standard.front_trans_dur = param_find("VT_F_TRANS_DUR");
 	_params_handles_standard.back_trans_dur = param_find("VT_B_TRANS_DUR");
@@ -113,6 +114,7 @@ void Standard::update_vtol_state()
 			_mc_roll_weight = 1.0f;
 			_mc_pitch_weight = 1.0f;
 			_mc_yaw_weight = 1.0f;
+			_mc_throttle_weight = 1.0f;
 
 		} else if (_vtol_schedule.flight_mode == FW_MODE) {
 			// transition to mc mode
@@ -126,6 +128,7 @@ void Standard::update_vtol_state()
 			_mc_roll_weight = 1.0f;
 			_mc_pitch_weight = 1.0f;
 			_mc_yaw_weight = 1.0f;
+			_mc_throttle_weight = 1.0f;
 
 		} else if (_vtol_schedule.flight_mode == TRANSITION_TO_MC) {
 			// transition to MC mode if transition time has passed
@@ -151,6 +154,7 @@ void Standard::update_vtol_state()
 			_mc_roll_weight = 0.0f;
 			_mc_pitch_weight = 0.0f;
 			_mc_yaw_weight = 0.0f;
+			_mc_throttle_weight = 0.0f;
 
 		} else if (_vtol_schedule.flight_mode == TRANSITION_TO_FW) {
 			// continue the transition to fw mode while monitoring airspeed for a final switch to fw mode
@@ -207,12 +211,14 @@ void Standard::update_transition_state()
 			_mc_roll_weight = weight;
 			_mc_pitch_weight = weight;
 			_mc_yaw_weight = weight;
+			_mc_throttle_weight = weight;
 
 		} else {
 			// at low speeds give full weight to mc
 			_mc_roll_weight = 1.0f;
 			_mc_pitch_weight = 1.0f;
 			_mc_yaw_weight = 1.0f;
+			_mc_throttle_weight = 1.0f;
 		}
 
 	} else if (_vtol_schedule.flight_mode == TRANSITION_TO_MC) {
@@ -223,11 +229,13 @@ void Standard::update_transition_state()
 			_mc_roll_weight = weight;
 			_mc_pitch_weight = weight;
 			_mc_yaw_weight = weight;
+			_mc_throttle_weight = weight;
 
 		} else {
 			_mc_roll_weight = 1.0f;
 			_mc_pitch_weight = 1.0f;
 			_mc_yaw_weight = 1.0f;
+			_mc_throttle_weight = 1.0f;
 		}
 
 		// in fw mode we need the multirotor motors to stop spinning, in backtransition mode we let them spin up again
@@ -241,6 +249,7 @@ void Standard::update_transition_state()
 	_mc_roll_weight = math::constrain(_mc_roll_weight, 0.0f, 1.0f);
 	_mc_pitch_weight = math::constrain(_mc_pitch_weight, 0.0f, 1.0f);
 	_mc_yaw_weight = math::constrain(_mc_yaw_weight, 0.0f, 1.0f);
+	_mc_throttle_weight = math::constrain(_mc_throttle_weight, 0.0f, 1.0f);
 }
 
 void Standard::update_mc_state()
@@ -280,7 +289,7 @@ void Standard::fill_actuator_outputs()
 	_actuators_out_0->control[actuator_controls_s::INDEX_YAW] = _actuators_mc_in->control[actuator_controls_s::INDEX_YAW] *
 			_mc_yaw_weight;	// yaw
 	_actuators_out_0->control[actuator_controls_s::INDEX_THROTTLE] =
-		_actuators_mc_in->control[actuator_controls_s::INDEX_THROTTLE];	// throttle
+		_actuators_mc_in->control[actuator_controls_s::INDEX_THROTTLE] * _mc_throttle_weight;	// throttle
 
 	/* fixed wing controls */
 	_actuators_out_1->control[actuator_controls_s::INDEX_ROLL] = -_actuators_fw_in->control[actuator_controls_s::INDEX_ROLL]
diff --git a/src/modules/vtol_att_control/tailsitter.cpp b/src/modules/vtol_att_control/tailsitter.cpp
index 106f91a8e4..e7daa2c3a3 100644
--- a/src/modules/vtol_att_control/tailsitter.cpp
+++ b/src/modules/vtol_att_control/tailsitter.cpp
@@ -178,7 +178,7 @@ void Tailsitter::update_vtol_state()
 
 			// check if we have reached airspeed  and pitch angle to switch to TRANSITION P2 mode
 			if ((_airspeed->true_airspeed_m_s >= _params_tailsitter.airspeed_trans
-			    && _v_att->pitch <= PITCH_TRANSITION_FRONT_P1) || !_armed->armed) {
+			     && _v_att->pitch <= PITCH_TRANSITION_FRONT_P1) || !_armed->armed) {
 				_vtol_schedule.flight_mode = FW_MODE;
 				//_vtol_schedule.transition_start = hrt_absolute_time();
 			}
@@ -461,7 +461,8 @@ void Tailsitter::fill_actuator_outputs()
 			// NOTE: There is no mistake in the line below, multicopter yaw axis is controlled by elevon roll actuation!
 			_actuators_out_1->control[actuator_controls_s::INDEX_ROLL] =
 				_actuators_mc_in->control[actuator_controls_s::INDEX_YAW];	//roll elevon
-			_actuators_out_1->control[actuator_controls_s::INDEX_PITCH] = _actuators_mc_in->control[actuator_controls_s::INDEX_PITCH];	//pitch elevon
+			_actuators_out_1->control[actuator_controls_s::INDEX_PITCH] =
+				_actuators_mc_in->control[actuator_controls_s::INDEX_PITCH];	//pitch elevon
 		}
 
 		break;
diff --git a/src/modules/vtol_att_control/vtol_type.h b/src/modules/vtol_att_control/vtol_type.h
index 196751016c..2f9211885b 100644
--- a/src/modules/vtol_att_control/vtol_type.h
+++ b/src/modules/vtol_att_control/vtol_type.h
@@ -117,6 +117,8 @@ protected:
 	float _mc_roll_weight;	// weight for multicopter attitude controller roll output
 	float _mc_pitch_weight;	// weight for multicopter attitude controller pitch output
 	float _mc_yaw_weight;	// weight for multicopter attitude controller yaw output
+	float _mc_throttle_weight;	// weight for multicopter throttle command. Used to avoid
+	// motors spinning up or cutting too fast whend doing transitions.
 
 	float _yaw_transition;	// yaw angle in which transition will take place
 	float _pitch_transition_start;  // pitch angle at the start of transition (tailsitter)