diff --git a/sw/airborne/firmwares/fixedwing/guidance/guidance_v.c b/sw/airborne/firmwares/fixedwing/guidance/guidance_v.c
index a4ef4590db..d58d4c5fcc 100644
--- a/sw/airborne/firmwares/fixedwing/guidance/guidance_v.c
+++ b/sw/airborne/firmwares/fixedwing/guidance/guidance_v.c
@@ -1,6 +1,6 @@
 /*
  * $Id$
- *  
+ *
  * Copyright (C) 2006  Pascal Brisset, Antoine Drouin, Michel Gorraz
  *
  * This file is part of paparazzi.
@@ -18,11 +18,11 @@
  * You should have received a copy of the GNU General Public License
  * along with paparazzi; see the file COPYING.  If not, write to
  * the Free Software Foundation, 59 Temple Place - Suite 330,
- * Boston, MA 02111-1307, USA. 
+ * Boston, MA 02111-1307, USA.
  *
  */
 
-/** 
+/**
  *  \file v_ctl_ctl
  *  \brief Vertical control for fixed wing vehicles.
  *
@@ -123,14 +123,14 @@ void v_ctl_init( void ) {
   /* "auto throttle" inner loop parameters */
   v_ctl_auto_throttle_nominal_cruise_throttle = V_CTL_AUTO_THROTTLE_NOMINAL_CRUISE_THROTTLE;
   v_ctl_auto_throttle_cruise_throttle = v_ctl_auto_throttle_nominal_cruise_throttle;
-  v_ctl_auto_throttle_climb_throttle_increment = 
+  v_ctl_auto_throttle_climb_throttle_increment =
     V_CTL_AUTO_THROTTLE_CLIMB_THROTTLE_INCREMENT;
   v_ctl_auto_throttle_pgain = V_CTL_AUTO_THROTTLE_PGAIN;
   v_ctl_auto_throttle_igain = V_CTL_AUTO_THROTTLE_IGAIN;
   v_ctl_auto_throttle_dgain = 0.;
   v_ctl_auto_throttle_sum_err = 0.;
-  v_ctl_auto_throttle_pitch_of_vz_pgain = V_CTL_AUTO_THROTTLE_PITCH_OF_VZ_PGAIN; 
-  v_ctl_auto_throttle_pitch_of_vz_dgain = V_CTL_AUTO_THROTTLE_PITCH_OF_VZ_DGAIN; 
+  v_ctl_auto_throttle_pitch_of_vz_pgain = V_CTL_AUTO_THROTTLE_PITCH_OF_VZ_PGAIN;
+  v_ctl_auto_throttle_pitch_of_vz_dgain = V_CTL_AUTO_THROTTLE_PITCH_OF_VZ_DGAIN;
 
 #ifdef V_CTL_AUTO_PITCH_PGAIN
   /* "auto pitch" inner loop parameters */
@@ -161,7 +161,7 @@ void v_ctl_init( void ) {
   #define AGR_CLIMB_THROTTLE agr_climb_throttle
   agr_climb_pitch = AGR_CLIMB_PITCH;
   #undef   AGR_CLIMB_PITCH
-  #define   AGR_CLIMB_PITCH agr_climb_pitch 
+  #define   AGR_CLIMB_PITCH agr_climb_pitch
   agr_climb_nav_ratio = AGR_CLIMB_NAV_RATIO;
   #undef   AGR_CLIMB_NAV_RATIO
   #define   AGR_CLIMB_NAV_RATIO agr_climb_nav_ratio
@@ -177,9 +177,9 @@ void v_ctl_init( void ) {
 #endif
 }
 
-/** 
+/**
  * outer loop
- * \brief Computes v_ctl_climb_setpoint and sets v_ctl_auto_throttle_submode 
+ * \brief Computes v_ctl_climb_setpoint and sets v_ctl_auto_throttle_submode
  */
 void v_ctl_altitude_loop( void ) {
   float altitude_pgain_boost = 1.0;
@@ -228,9 +228,9 @@ void v_ctl_climb_loop ( void ) {
   }
 }
 
-/** 
+/**
  * auto throttle inner loop
- * \brief 
+ * \brief
  */
 
 #ifndef USE_AIRSPEED
@@ -242,12 +242,12 @@ inline static void v_ctl_climb_auto_throttle_loop(void) {
   float err  = estimator_z_dot - v_ctl_climb_setpoint;
   float d_err = err - last_err;
   last_err = err;
-  float controlled_throttle = v_ctl_auto_throttle_cruise_throttle 
-    + v_ctl_auto_throttle_climb_throttle_increment * v_ctl_climb_setpoint 
-    + v_ctl_auto_throttle_pgain * 
+  float controlled_throttle = v_ctl_auto_throttle_cruise_throttle
+    + v_ctl_auto_throttle_climb_throttle_increment * v_ctl_climb_setpoint
+    + v_ctl_auto_throttle_pgain *
     (err + v_ctl_auto_throttle_igain * v_ctl_auto_throttle_sum_err
      + v_ctl_auto_throttle_dgain * d_err);
-  
+
   /* pitch pre-command */
   float v_ctl_pitch_of_vz = (v_ctl_climb_setpoint + d_err * v_ctl_auto_throttle_pitch_of_vz_dgain) * v_ctl_auto_throttle_pitch_of_vz_pgain;
 
@@ -257,15 +257,15 @@ inline static void v_ctl_climb_auto_throttle_loop(void) {
     if (v_ctl_climb_setpoint > 0) { /* Climbing */
       f_throttle =  AGR_CLIMB_THROTTLE;
       nav_pitch = AGR_CLIMB_PITCH;
-    } 
+    }
     else { /* Going down */
       f_throttle =  AGR_DESCENT_THROTTLE;
       nav_pitch = AGR_DESCENT_PITCH;
     }
     break;
-    
+
   case V_CTL_AUTO_THROTTLE_BLENDED: {
-    float ratio = (fabs(v_ctl_altitude_error) - AGR_BLEND_END) 
+    float ratio = (fabs(v_ctl_altitude_error) - AGR_BLEND_END)
       / (AGR_BLEND_START - AGR_BLEND_END);
     f_throttle = (1-ratio) * controlled_throttle;
     nav_pitch = (1-ratio) * v_ctl_pitch_of_vz;
@@ -280,7 +280,7 @@ inline static void v_ctl_climb_auto_throttle_loop(void) {
     }
     break;
   }
-    
+
   case V_CTL_AUTO_THROTTLE_STANDARD:
   default:
 #endif
@@ -346,7 +346,7 @@ inline static void v_ctl_climb_auto_throttle_loop(void) {
 #endif // USE_AIRSPEED
 
 
-/** 
+/**
  * auto pitch inner loop
  * \brief computes a nav_pitch from a climb_setpoint given a fixed throttle
  */
@@ -356,7 +356,7 @@ inline static void v_ctl_climb_auto_pitch_loop(void) {
   v_ctl_throttle_setpoint = nav_throttle_setpoint;
   v_ctl_auto_pitch_sum_err += err;
   BoundAbs(v_ctl_auto_pitch_sum_err, V_CTL_AUTO_PITCH_MAX_SUM_ERR);
-  nav_pitch = v_ctl_auto_pitch_pgain * 
+  nav_pitch = v_ctl_auto_pitch_pgain *
     (err + v_ctl_auto_pitch_igain * v_ctl_auto_pitch_sum_err);
   Bound(nav_pitch, V_CTL_AUTO_PITCH_MIN_PITCH, V_CTL_AUTO_PITCH_MAX_PITCH);
 }
diff --git a/sw/airborne/firmwares/fixedwing/guidance/guidance_v.h b/sw/airborne/firmwares/fixedwing/guidance/guidance_v.h
index fb4de97091..b77718c032 100644
--- a/sw/airborne/firmwares/fixedwing/guidance/guidance_v.h
+++ b/sw/airborne/firmwares/fixedwing/guidance/guidance_v.h
@@ -1,6 +1,6 @@
 /*
  * Paparazzi $Id$
- *  
+ *
  * Copyright (C) 2006  Pascal Brisset, Antoine Drouin
  *
  * This file is part of paparazzi.
@@ -18,11 +18,11 @@
  * You should have received a copy of the GNU General Public License
  * along with paparazzi; see the file COPYING.  If not, write to
  * the Free Software Foundation, 59 Temple Place - Suite 330,
- * Boston, MA 02111-1307, USA. 
+ * Boston, MA 02111-1307, USA.
  *
  */
 
-/** 
+/**
  *
  * fixed wing vertical control
  *
@@ -51,7 +51,7 @@ extern float v_ctl_altitude_pgain;
 /* inner loop */
 extern float v_ctl_climb_setpoint;
 extern uint8_t v_ctl_climb_mode;
-#define V_CTL_CLIMB_MODE_AUTO_THROTTLE 0 
+#define V_CTL_CLIMB_MODE_AUTO_THROTTLE 0
 #define V_CTL_CLIMB_MODE_AUTO_PITCH    1
 
 extern uint8_t v_ctl_auto_throttle_submode;
diff --git a/sw/airborne/firmwares/fixedwing/guidance/guidance_v_n.c b/sw/airborne/firmwares/fixedwing/guidance/guidance_v_n.c
index 2247721552..3473a4c83d 100644
--- a/sw/airborne/firmwares/fixedwing/guidance/guidance_v_n.c
+++ b/sw/airborne/firmwares/fixedwing/guidance/guidance_v_n.c
@@ -1,6 +1,6 @@
 /*
  * $Id: $
- *  
+ *
  * Copyright (C) 2010 ENAC
  *
  * This file is part of paparazzi.
@@ -18,11 +18,11 @@
  * You should have received a copy of the GNU General Public License
  * along with paparazzi; see the file COPYING.  If not, write to
  * the Free Software Foundation, 59 Temple Place - Suite 330,
- * Boston, MA 02111-1307, USA. 
+ * Boston, MA 02111-1307, USA.
  *
  */
 
-/** 
+/**
  *  \file v_ctl_ctl_n
  *  \brief Vertical control for fixed wing vehicles.
  *
@@ -120,8 +120,8 @@ void v_ctl_init( void ) {
   v_ctl_auto_throttle_igain = V_CTL_AUTO_THROTTLE_IGAIN;
   v_ctl_auto_throttle_dgain = 0.;
   v_ctl_auto_throttle_sum_err = 0.;
-  v_ctl_auto_throttle_pitch_of_vz_pgain = V_CTL_AUTO_THROTTLE_PITCH_OF_VZ_PGAIN; 
-  v_ctl_auto_throttle_pitch_of_vz_dgain = V_CTL_AUTO_THROTTLE_PITCH_OF_VZ_DGAIN; 
+  v_ctl_auto_throttle_pitch_of_vz_pgain = V_CTL_AUTO_THROTTLE_PITCH_OF_VZ_PGAIN;
+  v_ctl_auto_throttle_pitch_of_vz_dgain = V_CTL_AUTO_THROTTLE_PITCH_OF_VZ_DGAIN;
 
   /* "auto pitch" inner loop parameters */
   v_ctl_auto_pitch_pgain = V_CTL_AUTO_PITCH_PGAIN;
@@ -146,9 +146,9 @@ void v_ctl_init( void ) {
   v_ctl_throttle_setpoint = 0;
 }
 
-/** 
+/**
  * outer loop
- * \brief Computes v_ctl_climb_setpoint and sets v_ctl_auto_throttle_submode 
+ * \brief Computes v_ctl_climb_setpoint and sets v_ctl_auto_throttle_submode
  */
 
 // Don't use lead controller unless you know what you're doing
@@ -172,7 +172,7 @@ void v_ctl_altitude_loop( void ) {
   float diff_climb = v_ctl_climb_setpoint - v_ctl_climb_setpoint_last;
   BoundAbs(diff_climb, V_CTL_AUTO_CLIMB_LIMIT);
   v_ctl_climb_setpoint = v_ctl_climb_setpoint_last + diff_climb;
-  
+
   // Limit climb setpoint
   BoundAbs(v_ctl_climb_setpoint, V_CTL_ALTITUDE_MAX_CLIMB);
   v_ctl_climb_setpoint_last = v_ctl_climb_setpoint;
@@ -289,4 +289,3 @@ void v_ctl_throttle_slew( void ) {
   BoundAbs(diff_throttle, TRIM_PPRZ(V_CTL_THROTTLE_SLEW*MAX_PPRZ));
   v_ctl_throttle_slewed += diff_throttle;
 }
-
diff --git a/sw/airborne/firmwares/fixedwing/guidance/guidance_v_n.h b/sw/airborne/firmwares/fixedwing/guidance/guidance_v_n.h
index ab8ada0e61..4a6261d35b 100644
--- a/sw/airborne/firmwares/fixedwing/guidance/guidance_v_n.h
+++ b/sw/airborne/firmwares/fixedwing/guidance/guidance_v_n.h
@@ -1,6 +1,6 @@
 /*
  * $Id: $
- *  
+ *
  * Copyright (C) 2010 ENAC
  *
  * This file is part of paparazzi.
@@ -18,11 +18,11 @@
  * You should have received a copy of the GNU General Public License
  * along with paparazzi; see the file COPYING.  If not, write to
  * the Free Software Foundation, 59 Temple Place - Suite 330,
- * Boston, MA 02111-1307, USA. 
+ * Boston, MA 02111-1307, USA.
  *
  */
 
-/** 
+/**
  *
  * fixed wing vertical control
  *
diff --git a/sw/airborne/firmwares/fixedwing/stabilization/stabilization_adaptive.c b/sw/airborne/firmwares/fixedwing/stabilization/stabilization_adaptive.c
index ea6972cf0b..346076ec88 100644
--- a/sw/airborne/firmwares/fixedwing/stabilization/stabilization_adaptive.c
+++ b/sw/airborne/firmwares/fixedwing/stabilization/stabilization_adaptive.c
@@ -1,6 +1,6 @@
 /*
  * Paparazzi $Id: fw_h_ctl.c 3603 2009-07-01 20:06:53Z hecto $
- *  
+ *
  * Copyright (C) 2009-2010 The Paparazzi Team
  *
  * This file is part of paparazzi.
@@ -18,11 +18,11 @@
  * You should have received a copy of the GNU General Public License
  * along with paparazzi; see the file COPYING.  If not, write to
  * the Free Software Foundation, 59 Temple Place - Suite 330,
- * Boston, MA 02111-1307, USA. 
+ * Boston, MA 02111-1307, USA.
  *
  */
 
-/** 
+/**
  *
  * fixed wing horizontal adaptive control
  *
@@ -150,8 +150,8 @@ void h_ctl_init( void ) {
 
 }
 
-/** 
- * \brief 
+/**
+ * \brief
  *
  */
 void h_ctl_course_loop ( void ) {
@@ -165,7 +165,7 @@ void h_ctl_course_loop ( void ) {
   last_err = err;
   NormRadAngle(d_err);
 
-  float speed_depend_nav = estimator_hspeed_mod/NOMINAL_AIRSPEED; 
+  float speed_depend_nav = estimator_hspeed_mod/NOMINAL_AIRSPEED;
   Bound(speed_depend_nav, 0.66, 1.5);
 
   h_ctl_roll_setpoint = h_ctl_course_pre_bank_correction * h_ctl_course_pre_bank
@@ -264,7 +264,7 @@ inline static void h_ctl_roll_loop( void ) {
   //x  cmd /= airspeed_ratio2;
 
   // Set aileron commands
-  h_ctl_aileron_setpoint = TRIM_PPRZ(cmd); 
+  h_ctl_aileron_setpoint = TRIM_PPRZ(cmd);
 }
 
 
@@ -342,4 +342,3 @@ inline static void h_ctl_pitch_loop( void ) {
 
   h_ctl_elevator_setpoint = TRIM_PPRZ(cmd);
 }
-
diff --git a/sw/airborne/firmwares/fixedwing/stabilization/stabilization_adaptive.h b/sw/airborne/firmwares/fixedwing/stabilization/stabilization_adaptive.h
index 74105717df..c4915364cd 100644
--- a/sw/airborne/firmwares/fixedwing/stabilization/stabilization_adaptive.h
+++ b/sw/airborne/firmwares/fixedwing/stabilization/stabilization_adaptive.h
@@ -1,6 +1,6 @@
 /*
  * Paparazzi $Id: fw_h_ctl.h 3784 2009-07-24 14:55:54Z poine $
- *  
+ *
  * Copyright (C) 2009  ENAC
  *
  * This file is part of paparazzi.
@@ -18,11 +18,11 @@
  * You should have received a copy of the GNU General Public License
  * along with paparazzi; see the file COPYING.  If not, write to
  * the Free Software Foundation, 59 Temple Place - Suite 330,
- * Boston, MA 02111-1307, USA. 
+ * Boston, MA 02111-1307, USA.
  *
  */
 
-/** 
+/**
  *
  * fixed wing horizontal adaptive control
  *
diff --git a/sw/airborne/firmwares/fixedwing/stabilization/stabilization_attitude.c b/sw/airborne/firmwares/fixedwing/stabilization/stabilization_attitude.c
index 492fb99314..b525a6dd91 100644
--- a/sw/airborne/firmwares/fixedwing/stabilization/stabilization_attitude.c
+++ b/sw/airborne/firmwares/fixedwing/stabilization/stabilization_attitude.c
@@ -1,6 +1,6 @@
 /*
  * Paparazzi $Id$
- *  
+ *
  * Copyright (C) 2006  Pascal Brisset, Antoine Drouin, Michel Gorraz
  *
  * This file is part of paparazzi.
@@ -18,11 +18,11 @@
  * You should have received a copy of the GNU General Public License
  * along with paparazzi; see the file COPYING.  If not, write to
  * the Free Software Foundation, 59 Temple Place - Suite 330,
- * Boston, MA 02111-1307, USA. 
+ * Boston, MA 02111-1307, USA.
  *
  */
 
-/** 
+/**
  *
  * fixed wing horizontal control
  *
@@ -164,8 +164,8 @@ nav_ratio=0;
 #endif
 }
 
-/** 
- * \brief 
+/**
+ * \brief
  *
  */
 void h_ctl_course_loop ( void ) {
@@ -180,7 +180,7 @@ void h_ctl_course_loop ( void ) {
   const float reference_advance = (NOMINAL_AIRSPEED / 2.);
   float advance = cos(err) * estimator_hspeed_mod / reference_advance;
 
-  if ( 
+  if (
        (advance < 1.)  &&                          // Path speed is small
        (estimator_hspeed_mod < reference_advance)  // Small path speed is due to wind (small groundspeed)
      )
@@ -203,12 +203,12 @@ void h_ctl_course_loop ( void ) {
     // Heading error
     float herr = estimator_psi - h_ctl_course_setpoint; //+crab);
     NormRadAngle(herr);
-   
+
     if (advance < -0.5)              //<! moving in the wrong direction / big > 90 degree turn
     {
       err = herr;
     }
-    else if (advance < 0.)           //<! 
+    else if (advance < 0.)           //<!
     {
       err = (-advance)*2. * herr;
     }
@@ -259,7 +259,7 @@ void h_ctl_course_loop ( void ) {
   }
 #endif
 
-  float speed_depend_nav = estimator_hspeed_mod/NOMINAL_AIRSPEED; 
+  float speed_depend_nav = estimator_hspeed_mod/NOMINAL_AIRSPEED;
   Bound(speed_depend_nav, 0.66, 1.5);
 
   float cmd = h_ctl_course_pgain * speed_depend_nav * (err + d_err * h_ctl_course_dgain);
@@ -272,11 +272,11 @@ void h_ctl_course_loop ( void ) {
     if (v_ctl_auto_throttle_submode == V_CTL_AUTO_THROTTLE_AGRESSIVE || V_CTL_AUTO_THROTTLE_BLENDED) {
       BoundAbs(cmd, h_ctl_roll_max_setpoint); /* bound cmd before NAV_RATIO and again after */
       if (v_ctl_altitude_error < 0) {
-	nav_ratio = AGR_CLIMB_NAV_RATIO + (1 - AGR_CLIMB_NAV_RATIO) * (1 - (fabs(v_ctl_altitude_error) - AGR_BLEND_END) / (AGR_BLEND_START - AGR_BLEND_END));
-	Bound (nav_ratio, AGR_CLIMB_NAV_RATIO, 1);
+    nav_ratio = AGR_CLIMB_NAV_RATIO + (1 - AGR_CLIMB_NAV_RATIO) * (1 - (fabs(v_ctl_altitude_error) - AGR_BLEND_END) / (AGR_BLEND_START - AGR_BLEND_END));
+    Bound (nav_ratio, AGR_CLIMB_NAV_RATIO, 1);
       } else {
-	nav_ratio = AGR_DESCENT_NAV_RATIO + (1 - AGR_DESCENT_NAV_RATIO) * (1 - (fabs(v_ctl_altitude_error) - AGR_BLEND_END) / (AGR_BLEND_START - AGR_BLEND_END));
-	Bound (nav_ratio, AGR_DESCENT_NAV_RATIO, 1);
+    nav_ratio = AGR_DESCENT_NAV_RATIO + (1 - AGR_DESCENT_NAV_RATIO) * (1 - (fabs(v_ctl_altitude_error) - AGR_BLEND_END) / (AGR_BLEND_START - AGR_BLEND_END));
+    Bound (nav_ratio, AGR_DESCENT_NAV_RATIO, 1);
       }
       cmd *= nav_ratio;
     }
@@ -316,7 +316,7 @@ inline static void h_ctl_roll_loop( void ) {
     - h_ctl_roll_rate_gain * estimator_p
     + v_ctl_throttle_setpoint * h_ctl_aileron_of_throttle;
 
-  h_ctl_aileron_setpoint = TRIM_PPRZ(cmd); 
+  h_ctl_aileron_setpoint = TRIM_PPRZ(cmd);
 }
 
 #else // H_CTL_ROLL_ATTITUDE_GAIN
@@ -324,7 +324,7 @@ inline static void h_ctl_roll_loop( void ) {
 /** Computes h_ctl_aileron_setpoint from h_ctl_roll_setpoint */
 inline static void h_ctl_roll_loop( void ) {
   float err = estimator_phi - h_ctl_roll_setpoint;
-  float cmd = h_ctl_roll_pgain * err 
+  float cmd = h_ctl_roll_pgain * err
     + v_ctl_throttle_setpoint * h_ctl_aileron_of_throttle;
   h_ctl_aileron_setpoint = TRIM_PPRZ(cmd);
 
@@ -336,7 +336,7 @@ inline static void h_ctl_roll_loop( void ) {
   } else {
     h_ctl_roll_rate_setpoint = h_ctl_roll_rate_setpoint_pgain * err;
     BoundAbs(h_ctl_roll_rate_setpoint, H_CTL_ROLL_RATE_MAX_SETPOINT);
-    
+
     float saved_aileron_setpoint = h_ctl_aileron_setpoint;
     h_ctl_roll_rate_loop();
     h_ctl_aileron_setpoint = Blend(h_ctl_aileron_setpoint, saved_aileron_setpoint, h_ctl_roll_rate_mode) ;
@@ -348,23 +348,23 @@ inline static void h_ctl_roll_loop( void ) {
 
 static inline void h_ctl_roll_rate_loop() {
   float err = estimator_p - h_ctl_roll_rate_setpoint;
-  
+
   /* I term calculation */
   static float roll_rate_sum_err = 0.;
   static uint8_t roll_rate_sum_idx = 0;
   static float roll_rate_sum_values[H_CTL_ROLL_RATE_SUM_NB_SAMPLES];
-  
+
   roll_rate_sum_err -= roll_rate_sum_values[roll_rate_sum_idx];
   roll_rate_sum_values[roll_rate_sum_idx] = err;
   roll_rate_sum_err += err;
   roll_rate_sum_idx++;
   if (roll_rate_sum_idx >= H_CTL_ROLL_RATE_SUM_NB_SAMPLES) roll_rate_sum_idx = 0;
-  
+
   /* D term calculations */
   static float last_err = 0;
   float d_err = err - last_err;
   last_err = err;
-  
+
   float throttle_dep_pgain =
     Blend(h_ctl_hi_throttle_roll_rate_pgain, h_ctl_lo_throttle_roll_rate_pgain, v_ctl_throttle_setpoint/((float)MAX_PPRZ));
   float cmd = throttle_dep_pgain * ( err + h_ctl_roll_rate_igain * roll_rate_sum_err / H_CTL_ROLL_RATE_SUM_NB_SAMPLES + h_ctl_roll_rate_dgain * d_err);
@@ -414,7 +414,7 @@ inline static void h_ctl_pitch_loop( void ) {
     h_ctl_elevator_of_roll = 0.;
 
   h_ctl_pitch_loop_setpoint =
-    h_ctl_pitch_setpoint 
+    h_ctl_pitch_setpoint
     - h_ctl_elevator_of_roll / h_ctl_pitch_pgain * fabs(estimator_phi);
 
   float err = estimator_theta - h_ctl_pitch_loop_setpoint;
@@ -426,5 +426,3 @@ inline static void h_ctl_pitch_loop( void ) {
 #endif
   h_ctl_elevator_setpoint = TRIM_PPRZ(cmd);
 }
-
-
diff --git a/sw/airborne/firmwares/fixedwing/stabilization/stabilization_attitude.h b/sw/airborne/firmwares/fixedwing/stabilization/stabilization_attitude.h
index 54fcda9f62..59850f5a06 100644
--- a/sw/airborne/firmwares/fixedwing/stabilization/stabilization_attitude.h
+++ b/sw/airborne/firmwares/fixedwing/stabilization/stabilization_attitude.h
@@ -1,6 +1,6 @@
 /*
  * Paparazzi $Id$
- *  
+ *
  * Copyright (C) 2006  Pascal Brisset, Antoine Drouin, Michel Gorraz
  *
  * This file is part of paparazzi.
@@ -18,11 +18,11 @@
  * You should have received a copy of the GNU General Public License
  * along with paparazzi; see the file COPYING.  If not, write to
  * the Free Software Foundation, 59 Temple Place - Suite 330,
- * Boston, MA 02111-1307, USA. 
+ * Boston, MA 02111-1307, USA.
  *
  */
 
-/** 
+/**
  *
  * fixed wing horizontal control
  *