diff --git a/ArduPlane/ArduPlane.cpp b/ArduPlane/ArduPlane.cpp
index 45c4f0a517..0bd28534ad 100644
--- a/ArduPlane/ArduPlane.cpp
+++ b/ArduPlane/ArduPlane.cpp
@@ -323,7 +323,7 @@ void Plane::one_second_loop()
     // make it possible to change orientation at runtime
     ahrs.set_orientation();
 
-    adsb.set_stall_speed_cm(airspeed.get_airspeed_min());
+    adsb.set_stall_speed_cm(aparm.airspeed_min);
 
     // sync MAVLink system ID
     mavlink_system.sysid = g.sysid_this_mav;
@@ -398,8 +398,8 @@ void Plane::airspeed_ratio_update(void)
         // don't calibrate when not moving
         return;        
     }
-    if (airspeed.get_airspeed() < airspeed.get_airspeed_min() &&
-        gps.ground_speed() < (uint32_t)airspeed.get_airspeed_min()) {
+    if (airspeed.get_airspeed() < aparm.airspeed_min && 
+        gps.ground_speed() < (uint32_t)aparm.airspeed_min) {
         // don't calibrate when flying below the minimum airspeed. We
         // check both airspeed and ground speed to catch cases where
         // the airspeed ratio is way too low, which could lead to it
diff --git a/ArduPlane/Attitude.cpp b/ArduPlane/Attitude.cpp
index 496d4643cd..8e2169abac 100644
--- a/ArduPlane/Attitude.cpp
+++ b/ArduPlane/Attitude.cpp
@@ -1388,7 +1388,7 @@ void Plane::update_load_factor(void)
         return;
     }
 
-    float max_load_factor = smoothed_airspeed / airspeed.get_airspeed_min();
+    float max_load_factor = smoothed_airspeed / aparm.airspeed_min;
     if (max_load_factor <= 1) {
         // our airspeed is below the minimum airspeed. Limit roll to
         // 25 degrees
diff --git a/ArduPlane/Parameters.cpp b/ArduPlane/Parameters.cpp
index b35b674b0b..cb3705f88b 100644
--- a/ArduPlane/Parameters.cpp
+++ b/ArduPlane/Parameters.cpp
@@ -476,6 +476,24 @@ const AP_Param::Info Plane::var_info[] = {
     // @User: Standard
     ASCALAR(stall_prevention, "STALL_PREVENTION",  1),
 
+    // @Param: ARSPD_FBW_MIN
+    // @DisplayName: Minimum Airspeed
+    // @Description: This is the minimum airspeed you want to fly at in modes where the autopilot controls the airspeed. This should be set to a value around 20% higher than the level flight stall speed for the airframe. This value is also used in the STALL_PREVENTION code.
+    // @Units: m/s
+    // @Range: 5 100
+    // @Increment: 1
+    // @User: Standard
+    ASCALAR(airspeed_min, "ARSPD_FBW_MIN",  AIRSPEED_FBW_MIN),
+
+    // @Param: ARSPD_FBW_MAX
+    // @DisplayName: Maximum Airspeed
+    // @Description: This is the maximum airspeed that you want to allow for your airframe in auto-throttle modes. You should ensure that this value is sufficiently above the ARSPD_FBW_MIN value to allow for a sufficient flight envelope to accurately control altitude using airspeed. A value at least 50% above ARSPD_FBW_MIN is recommended.
+    // @Units: m/s
+    // @Range: 5 100
+    // @Increment: 1
+    // @User: Standard
+    ASCALAR(airspeed_max, "ARSPD_FBW_MAX",  AIRSPEED_FBW_MAX),
+
     // @Param: FBWB_ELEV_REV
     // @DisplayName: Fly By Wire elevator reverse
     // @Description: Reverse sense of elevator in FBWB and CRUISE modes. When set to 0 up elevator (pulling back on the stick) means to lower altitude. When set to 1, up elevator means to raise altitude.
@@ -1406,9 +1424,6 @@ const AP_Param::ConversionInfo conversion_table[] = {
     { Parameters::k_param_serial1_baud,       0,      AP_PARAM_INT16, "SERIAL1_BAUD" },
     { Parameters::k_param_serial2_baud,       0,      AP_PARAM_INT16, "SERIAL2_BAUD" },
 
-    { Parameters::k_param_airspeed_min,       0,      AP_PARAM_INT16, "ARSPD_FBW_MIN" },
-    { Parameters::k_param_airspeed_max,       0,      AP_PARAM_INT16, "ARSPD_FBW_MAX" },
-
     // these are needed to cope with the change to treat nested index 0 as index 63
     { Parameters::k_param_quadplane,          3,      AP_PARAM_FLOAT, "Q_RT_RLL_P" },
     { Parameters::k_param_quadplane,          4,      AP_PARAM_FLOAT, "Q_RT_PIT_P" },
diff --git a/ArduPlane/Parameters.h b/ArduPlane/Parameters.h
index 9dabe7eec3..14f4b762c7 100644
--- a/ArduPlane/Parameters.h
+++ b/ArduPlane/Parameters.h
@@ -172,8 +172,8 @@ public:
 
         // 120: Fly-by-wire control
         //
-        k_param_airspeed_min = 120,     // unused
-        k_param_airspeed_max,           // unused
+        k_param_airspeed_min = 120,
+        k_param_airspeed_max,
         k_param_FBWB_min_altitude_cm,  // 0=disabled, minimum value for altitude in cm (for first time try 30 meters = 3000 cm)
         k_param_flybywire_elev_reverse,
         k_param_alt_control_algorithm,
diff --git a/ArduPlane/Plane.h b/ArduPlane/Plane.h
index acd5c835ad..2648b8c7ae 100644
--- a/ArduPlane/Plane.h
+++ b/ArduPlane/Plane.h
@@ -394,7 +394,7 @@ private:
 #endif
 
     // Airspeed Sensors
-    AP_Airspeed airspeed;
+    AP_Airspeed airspeed {aparm};
 
     // ACRO controller state
     struct {
diff --git a/ArduPlane/config.h b/ArduPlane/config.h
index d3d4a4bcf6..d0cc8cf6f1 100644
--- a/ArduPlane/config.h
+++ b/ArduPlane/config.h
@@ -275,6 +275,13 @@
 //////////////////////////////////////////////////////////////////////////////
 // FLY_BY_WIRE_B airspeed control
 //
+#ifndef AIRSPEED_FBW_MIN
+ # define AIRSPEED_FBW_MIN               9
+#endif
+#ifndef AIRSPEED_FBW_MAX
+ # define AIRSPEED_FBW_MAX               22
+#endif
+
 #ifndef ALT_HOLD_FBW
  # define ALT_HOLD_FBW 0
 #endif
diff --git a/ArduPlane/is_flying.cpp b/ArduPlane/is_flying.cpp
index ac5251a8c5..b94487d9ac 100644
--- a/ArduPlane/is_flying.cpp
+++ b/ArduPlane/is_flying.cpp
@@ -24,7 +24,7 @@ void Plane::update_is_flying_5Hz(void)
                                     (gps.ground_speed_cm() >= ground_speed_thresh_cm);
 
     // airspeed at least 75% of stall speed?
-    bool airspeed_movement = ahrs.airspeed_estimate(&aspeed) && (aspeed >= (airspeed.get_airspeed_min()*0.75f));
+    bool airspeed_movement = ahrs.airspeed_estimate(&aspeed) && (aspeed >= (aparm.airspeed_min*0.75f));
 
 
     if (quadplane.is_flying()) {
diff --git a/ArduPlane/navigation.cpp b/ArduPlane/navigation.cpp
index 6327c0a6c3..9baf75f107 100644
--- a/ArduPlane/navigation.cpp
+++ b/ArduPlane/navigation.cpp
@@ -92,10 +92,10 @@ void Plane::calc_airspeed_errors()
     // FBW_B airspeed target
     if (control_mode == FLY_BY_WIRE_B || 
         control_mode == CRUISE) {
-        target_airspeed_cm = ((int32_t)(airspeed.get_airspeed_max() -
-                                        airspeed.get_airspeed_min()) *
+        target_airspeed_cm = ((int32_t)(aparm.airspeed_max -
+                                        aparm.airspeed_min) *
                               channel_throttle->get_control_in()) +
-                             ((int32_t)airspeed.get_airspeed_min() * 100);
+                             ((int32_t)aparm.airspeed_min * 100);
     }
 
     // Landing airspeed target
@@ -138,9 +138,8 @@ void Plane::calc_airspeed_errors()
     }
 
     // Apply airspeed limit
-    if (target_airspeed_cm > ((int32_t)airspeed.get_airspeed_max() * 100)) {
-        target_airspeed_cm = ((int32_t)airspeed.get_airspeed_max() * 100);
-    }
+    if (target_airspeed_cm > (aparm.airspeed_max * 100))
+        target_airspeed_cm = (aparm.airspeed_max * 100);
 
     // use the TECS view of the target airspeed for reporting, to take
     // account of the landing speed
diff --git a/ArduPlane/quadplane.cpp b/ArduPlane/quadplane.cpp
index 6c371caa05..43e51866a5 100644
--- a/ArduPlane/quadplane.cpp
+++ b/ArduPlane/quadplane.cpp
@@ -856,8 +856,8 @@ float QuadPlane::assist_climb_rate_cms(void)
 float QuadPlane::desired_auto_yaw_rate_cds(void)
 {
     float aspeed;
-    if (!ahrs.airspeed_estimate(&aspeed) || aspeed < plane.airspeed.get_airspeed_min()) {
-        aspeed = plane.airspeed.get_airspeed_min();
+    if (!ahrs.airspeed_estimate(&aspeed) || aspeed < plane.aparm.airspeed_min) {
+        aspeed = plane.aparm.airspeed_min;
     }
     if (aspeed < 1) {
         aspeed = 1;
@@ -925,7 +925,7 @@ void QuadPlane::update_transition(void)
             transition_start_ms = millis();
         }
 
-        if (have_airspeed && aspeed > plane.airspeed.get_airspeed_min() && !assisted_flight) {
+        if (have_airspeed && aspeed > plane.aparm.airspeed_min && !assisted_flight) {
             transition_start_ms = millis();
             transition_state = TRANSITION_TIMER;
             GCS_MAVLINK::send_statustext_all(MAV_SEVERITY_INFO, "Transition airspeed reached %.1f", (double)aspeed);
@@ -1825,7 +1825,7 @@ int8_t QuadPlane::forward_throttle_pct(void)
     float fwd_vel_error = vel_error_body * Vector3f(1,0,0);
 
     // scale forward velocity error by maximum airspeed
-    fwd_vel_error /= MAX(plane.airspeed.get_airspeed_max(), 5.0f);
+    fwd_vel_error /= MAX(plane.aparm.airspeed_max, 5);
 
     // add in a component from our current pitch demand. This tends to
     // move us to zero pitch. Assume that LIM_PITCH would give us the
diff --git a/ArduPlane/radio.cpp b/ArduPlane/radio.cpp
index 6651992d21..fdb195c5c9 100644
--- a/ArduPlane/radio.cpp
+++ b/ArduPlane/radio.cpp
@@ -216,7 +216,7 @@ void Plane::read_radio()
     if (g.throttle_nudge && channel_throttle->get_servo_out() > 50 && geofence_stickmixing()) {
         float nudge = (channel_throttle->get_servo_out() - 50) * 0.02f;
         if (ahrs.airspeed_sensor_enabled()) {
-            airspeed_nudge_cm = ((int16_t)airspeed.get_airspeed_max()*100 - g.airspeed_cruise_cm) * nudge;
+            airspeed_nudge_cm = (aparm.airspeed_max * 100 - g.airspeed_cruise_cm) * nudge;
         } else {
             throttle_nudge = (aparm.throttle_max - aparm.throttle_cruise) * nudge;
         }