diff --git a/Engines/PT6A-27.xml b/Engines/PT6A-27.xml
index d21de4d..fe9eac4 100644
--- a/Engines/PT6A-27.xml
+++ b/Engines/PT6A-27.xml
@@ -1,110 +1,110 @@
-<?xml version="1.0"?>
-
-<!--
-    File:     my_engine.xml
-    Author:   AeromatiC++ v 3.2.5
-
-    See: http://wiki.flightgear.org/JSBSim_Engines#FGTurboprop
-
-    Inputs:
-        name:                   PT6A-27
-        type:                   Turboprop Engine
-        power:                  620.0 hp
-        inlet temperature:      725.0 degrees C
-        overall pressure ratio: 15.0:1
-
-    Outputs:
-        psfc:                   0.579 lbs/hr/hp
-        engine weight:          336.3 lbs
-        engine length:          4.9 ft
-        engine diameter:        1.9 ft
--->
-
-<turboprop_engine name="PT6A-27">
-    <milthrust unit="LBS">       1523.2  </milthrust>
-    <idlen1>                       52.0  </idlen1>
-    <maxn1>                       101.5  </maxn1>
-    <idlen2>                       40.0  </idlen2>
-    <maxn1>                        96.0  </maxn1>
-    <maxpower unit="HP">          620.0  </maxpower>
-    <psfc unit="LBS/HR/HP">         0.74 </psfc>
-    <n1idle_max_delay>              1.2  </n1idle_max_delay>
-    <maxstartingtime>               0.1  </maxstartingtime>
-    <startern1>                    20.0  </startern1>
-    <ielumaxtorque unit="FT*LB"> 1536.0  </ielumaxtorque>
-    <itt_delay>                     3.0  </itt_delay>
-    <betarangeend>                 10.0  </betarangeend>
-    <reversemaxpower>              91.0  </reversemaxpower>
-
-    <function name="EnginePowerVC">
-        <table>
-            <description> Engine power, function of airspeed and pressure </description>
-            <independentVar lookup="row">atmosphere/P-sl-psf</independentVar>
-            <independentVar lookup="column">velocities/ve-kts</independentVar>
-            <tableData>
-                       0      50    100    150    200    250
-                 503   0.357  0.380  0.400  0.425  0.457  0.486
-                1048   0.586  0.589  0.600  0.621  0.650  0.686
-                1328   0.707  0.721  0.731  0.757  0.786  0.821
-                1496   0.779  0.786  0.808  0.821  0.857  0.900
-                1684   0.850  0.857  0.874  0.900  0.943  0.979
-                1896   0.914  0.929  0.946  0.971  1      1.057
-                2135   1      1.011  1.029  1.043  1.083  1.150
-                2213   1.029  1.043  1.057  1.079  1.114  1.171
-            </tableData>
-        </table>
-    </function>
-
-    <!--function name="EnginePowerVC">
-        <table>
-            <description> Engine power, function of airspeed and pressure </description>
-            <independentVar lookup="row">atmosphere/pressure-altitude</independentVar>
-            <independentVar lookup="column">velocities/ve-kts</independentVar>
-            <tableData>
-                        0  250
-                    0   1    1
-                25000   1    1
-            </tableData>
-        </table>
-    </function-->
-
-    <table name="EnginePowerRPM_N1" type="internal">
-        <description> Engine Power, function of RPM and N1 </description>
-        <tableData>
-                       0       5       60      86      94      95      96      97      98      99     100     101
-               0.0     0.0     0.4     0.4     0.4     0.4     0.4     0.4     0.4     0.4     0.4     0.4     0.4
-             803.5     0.0     0.4    29.2   166.9   292.1   317.1   350.5   383.8   417.2   442.2   484.0   517.4
-            1203.0     0.0     0.4    25.0   192.0   333.8   358.8   392.2   421.4   458.9   492.3   534.1   567.4
-            1604.8     0.0     0.4     4.2   200.3   367.2   396.4   425.6   458.9   496.5   525.7   567.4   600.8
-            2006.5     0.0     0.1     0.1   187.7   375.5   413.0   438.1   471.4   509.0   542.4   584.1   621.7
-            2207.4     0.0     0.1     0.1   171.1   367.2   400.5   429.7   467.3   504.9   538.2   579.9   620.0
-        </tableData>
-    </table>
-
-    <table name="ITT_N1" type="internal">
-        <description> Inter-Turbine Temperature ITT [deg C] depending on N1 and engine run (0=off / 1=running) </description>
-        <tableData>
-                    0     1
-              0     0     0
-             12   105   105
-             60   188   432
-             96   283   691
-            100   294   720
-        </tableData>
-    </table>
-
-    <table name="CombustionEfficiency_N1" type="internal">
-        <description>Dependency of fuel efficiency coefficient on N1 (and RPM)</description>
-        <tableData>
-             90    0.1221
-             91.2  0.2834
-             92.2  0.5336
-             93.4  0.7188
-             94.1  0.7741
-             95.2  0.8471
-             96.5  0.9001
-            100    1
-        </tableData>
-    </table>
-
-</turboprop_engine>
+<?xml version="1.0"?>
+
+<!--
+  File:     PT6A-27.xml
+  Author:   AeromatiC++ v 3.3.21
+
+  See: http://wiki.flightgear.org/JSBSim_Engines#FGTurboprop
+
+  Inputs:
+    name:                   PT6A-27
+    type:                   Turboprop Engine
+    power:                  620.0 hp
+    inlet temperature:      1713.2 degrees F
+    overall pressure ratio: 6.7:1
+
+  Outputs:
+    psfc:                   0.590 lbs/hr/hp
+    engine weight:          336.31 lbs
+    engine length:          4.87 ft
+    engine diameter:        1.88 ft
+-->
+
+<turboprop_engine name="PT6A-27">
+  <milthrust unit="LBS">1388.80</milthrust>
+
+  <!-- 
+    The idle speed of the gas generator (N1) expressed as a percentage of maximum N1 RPM. 
+    In turboprop engines like the PT6A-27, N1 refers to the gas generator speed, 
+    which includes the compressor and turbine stages driving the compressor.
+   -->
+  <idlen1>60.0</idlen1>
+
+  <!-- The maximum allowable gas generator speed (N1) as a percentage of maximum N1 RPM. -->
+  <maxn1>100.0</maxn1>
+
+  <!-- The maximum shaft horsepower (shp) the engine can produce. This value of 620shp is easily verifiable online. -->
+  <maxpower unit="HP">620.0</maxpower>
+
+  <!-- Power Specific Fuel Consumption (PSFC), measured in pounds of fuel burned per hour per horsepower produced. -->
+  <psfc unit="LBS/HR/HP">0.612</psfc>
+
+  <!-- The maximum delay (in seconds) for N1 to reach idle speed during engine start-up. -->
+  <n1idle_max_delay>1</n1idle_max_delay>
+
+  <!-- The maximum allowable time (in seconds) for the engine to start. -->
+  <maxstartingtime>20</maxstartingtime>
+  <startern1>20</startern1>
+  <ielumaxtorque unit="FT*LB">1578.4</ielumaxtorque>
+  <itt_delay>0.05</itt_delay>
+  <betarangeend>64</betarangeend>
+  <reversemaxpower>60</reversemaxpower>
+
+  <function name="EnginePowerVC">
+    <table>
+      <description> Engine power, function of airspeed and pressure </description>
+      <independentVar lookup="row">atmosphere/P-psf</independentVar>
+      <independentVar lookup="column">velocities/ve-kts</independentVar>
+      <tableData>
+              0      50     100    150    200    250    300    350
+        503   0.357  0.380  0.400  0.425  0.457  0.486  0.517  0.550
+       1048   0.586  0.589  0.600  0.621  0.650  0.686  0.724  0.764
+       1328   0.707  0.721  0.731  0.757  0.786  0.821  0.858  0.896
+       1496   0.779  0.786  0.808  0.821  0.857  0.900  0.945  0.993
+       1684   0.850  0.857  0.874  0.900  0.943  0.979  1.016  1.055
+       1896   0.914  0.929  0.946  0.971  1      1.057  1.117  1.181
+       2135   1      1.011  1.029  1.043  1.083  1.150  1.221  1.297
+       2213   1.029  1.043  1.057  1.079  1.114  1.171  1.231  1.294
+     </tableData>
+   </table>
+  </function>
+
+  <table name="EnginePowerRPM_N1" type="internal">
+    <description> Engine Power, function of RPM and N1 </description>
+    <tableData>
+              0       5       60      86      94      95      96      97      98      99     100     101
+      0.0     0.0     0.4     0.4     0.4     0.4     0.4     0.4     0.4     0.4     0.4     0.4     0.4
+    803.5     0.0     0.4    29.2   166.9   292.1   317.1   350.5   383.8   417.2   442.2   484.0   517.4
+   1203.0     0.0     0.4    25.0   192.0   333.8   358.8   392.2   421.4   458.9   492.3   534.1   567.4
+   1604.8     0.0     0.4     4.2   200.3   367.2   396.4   425.6   458.9   496.5   525.7   567.4   600.8
+   2006.5     0.0     0.1     0.1   187.7   375.5   413.0   438.1   471.4   509.0   542.4   584.1   621.7
+   2207.4     0.0     0.1     0.1   171.1   367.2   400.5   429.7   467.3   504.9   538.2   579.9   620.0
+    </tableData>
+  </table>
+
+  <table name="ITT_N1" type="internal">
+    <description> Inter-Turbine Temperature ITT [deg C] depending on N1 and engine run (0=off / 1=running) </description>
+    <tableData>
+              0     1
+        0     0     0
+       15   248.4   248.4
+       60   445.4  1291.8
+       96   669.9  1689.2
+      100   695.6  1867.4
+    </tableData>
+  </table>
+
+  <table name="CombustionEfficiency_N1" type="internal">
+    <description>Dependency of fuel efficiency coefficient on N1 (and RPM)</description>
+    <tableData>
+      90    0.1221
+      91.2  0.2834
+      92.2  0.5336
+      93.4  0.7188
+      94.1  0.7741
+      95.2  0.8471
+      96.5  0.9001
+     100    1
+      </tableData>
+  </table>
+</turboprop_engine>