Aero Commander 500
By Milton Shupe, Scott Thomas, and André Folkers
For MSFS2004 / FS9
and FS2002
Model 500
Data from various sources provided by Barry Collman
Type Certificate:
6A1Certificated: July 24th 1958
PCLM: 7 (2 at +94; 2 at +128; 3 at +168)
Number Built: 101
Certificated by: Aero Design & Engineering Company
Serial numbers 618 through 656 (16 aircraft)
Aero Design & Engineering Company (subsidiary of Rockwell-Standard Corp)
Serial numbers 657 through 852 (85 aircraft)
Engines: Lycoming O-540-A1A5
Serial number 618 (1 aircraft)
Lycoming O-540-A2B
Serial numbers 635 through 852 (100 aircraft)
Propellers (hub/blade): Hartzell HC-82XK-2/8433-4
Serial number 618 (1 aircraft)
Hartzell HC-82XK-2B/8433-4
Serial numbers 635 through 740 (54 aircraft)
Hartzell HC-82XK-2B1/8433-4
Serial numbers 742, 838 & 846 (3 aircraft)
Hartzell HC-82XK-2C1/8433-4
Serial numbers 748 through 836, 840, 842, 848 & 852 (43 aircraft)
Fuel: 91/96 minimum grade aviation gasoline
Fuel consumption: 11.9 U.S. gallons per engine per hour at 2,300r.p.m.
Fuel capacity: 158.5 U.S. gallons (600 litres) total [5 inter-connected tanks]
156.0 U.S. gallons (591 litres) usable
or 225.5 U.S. gallons (854 litres) total (with optional 67 U.S. gallons auxiliary fuel)
223.0 U.S. gallons (844 litres) usable
Oil capacity: 6.000 U.S. gallons (22.71 litres) total (3 gallons each engine)
4.625 U.S. gallons (17.51 litres) usable
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Weights & Balance: |
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Pounds |
Kilograms |
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Ramp Weight |
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MTOW |
6,000 |
2,722 |
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6,500 |
2,948 |
per STC SA377SO |
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MLW |
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ZFW |
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Empty Weight (typical) |
3,850 |
1,746 |
(Factory Empty Weight, with standard equipment) |
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Useful load |
2,150 |
975 |
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Basic Operating Weight |
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Payload |
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Maximum baggage |
350 |
159 |
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Maximum Wing Loading |
23.53 lb/sq.ft. |
114.88 kg/m2 |
6,000lb. / 255 sq.ft. |
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25.49 lb/sq.ft. |
124.45 kg/m2 |
6,500lb. / 255 sq.ft. |
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Maximum Power Loading |
12.00 lb/h.p. |
5.44 kg/h.p. |
7.30 kg/kW |
6,000lb. / 500 h.p. |
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11.21 lb/h.p. |
5.08 kg/h.p. |
6.82 kg/kW |
6,500lb. / 580 h.p. |
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C.G. range |
(+166.0) to (+175.1) - gear extended |
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Effect of retracting gear |
+6210 in./lb. |
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Empty Weight C.G. range |
None |
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Datum |
Located 152 inches (12' 8") forward of wing leading edge at center section. |
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Leveling means |
Longitudinal |
Top of fuselage centerline aft of wing trailing edge. |
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Lateral |
Transverse beams at front or rear of baggage compartment floor. |
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Control Surface Movements: |
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o up |
o down |
o right |
o left |
Remarks |
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Aileron |
23 ± 2 |
15 +2 |
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Flaps |
40 +2 |
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Elevator |
30 +1/-0 |
10 +2/-0 |
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Elevator tab |
2.5 +2/-0.5 |
20 +2/-0 |
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Rudder |
20 +2/-0 |
20 +2/-0 |
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Rudder tab |
26 +2/-0 |
26 +2/-0 |
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Dimensions: |
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Feet/Inches |
Inches |
Meters |
Remarks |
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Wing span |
49' 0.56" |
588.56 |
14.949 |
Wing section is NACA 23012 modified |
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Wing chord at root |
8’ 4.00" |
100.00 |
2.540 |
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Wing chord at tip |
2’ 1.42" |
25.42 |
0.646 |
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Wing - ground to wingtip height |
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Wing Aspect Ratio |
9.45 |
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Wing Taper Ratio |
3.93 |
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Wing dihedral |
4 degrees |
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Wing incidence at root |
3 degrees |
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Wing incidence at tip |
minus 3.5 degrees |
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Wing - sweep forward at trailing edge |
14 degrees |
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Wing area - inc. Flaps & Ailerons |
255 sq.ft. |
23.690 m2 |
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Total Flap area |
21.20 sq.ft. |
1.970 m2 |
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Total Aileron area |
20.52 sq.ft. |
1.906 m2 |
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Fuselage Length |
35' 1.25" |
421.25 |
10.700 |
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Overall Length |
35’ 5.50" |
425.50 |
10.808 |
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Overall Height |
14' 6.00" |
174.00 |
4.420 |
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Height - ground to top of fuselage |
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Height - ground to bottom of fuselage |
0’ 5.50" |
5.50 |
0.140 |
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Total Overall Fin area |
39.40 sq.ft. |
3.660 m2 |
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Fin fixed surface area |
24.00 sq.ft. |
2.230 m2 |
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Rudder area |
15.40 sq.ft. |
1.430 m2 |
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Tailplane span |
16’ 8.95" |
200.95 |
5.104 |
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Ground to tailplane tip height |
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Tailplane dihedral |
10 degrees |
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Tailplane - angle of incidence |
0.75 degrees |
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Total Overall Tailplane area |
53.60 sq.ft. |
4.980 m2 |
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Tailplane fixed surface area |
33.06 sq.ft. |
3.072 m2 |
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Elevators area |
20.54 sq.ft. |
1.908 m2 |
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Wheel track (tread) |
12’ 11.00" |
155.00 |
3.937 |
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Wheelbase (nose to main) |
14’ 0.00" |
168.00 |
4.267 |
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Minimum ground turning radius |
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Cabin Length (Total) |
10’ 7.50" |
127.50 |
3.239 |
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Cabin Height |
4’ 5.00" |
53.00 |
1.346 |
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Cabin Width |
4’ 4.00" |
52.00 |
1.321 |
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Maximum external fuselage width |
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Cabin door Height |
3’ 7.00" |
43.00 |
1.092 |
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Cabin door Width |
2’ 4.00" |
28.00 |
0.711 |
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Cabin door, Height to sill |
1’ 6.50" |
18.50 |
0.470 |
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Cabin volume |
177 cu.ft. |
5.012 m3 |
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Baggage compartment Length |
2’ 7.00" |
31.00 |
0.787 |
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Baggage compartment Height |
3’ 5.00" |
41.00 |
1.041 |
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Baggage compartment Width |
3’ 11.00" |
47.00 |
1.194 |
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Baggage door Height |
1’ 11.50" |
23.50 |
0.597 |
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Baggage door Width |
1’ 7.50" |
19.50 |
0.495 |
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Baggage door, Height to sill |
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Baggage compartment volume |
32 cu.ft. |
0.906 m3 |
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Performance: |
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Feet |
Meters |
Remarks |
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Takeoff distance, over 50ft obstacle |
1,400 |
427 |
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Takeoff run |
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Short-field takeoff, over 50 ft obstacle |
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Short-field takeoff run |
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Landing distance, over 50ft obstacle |
1,350 |
410 |
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Landing run |
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Short-field landing distance, over 50ft obstacle |
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Short-field landing run |
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Maximum Operating Altitude |
FAA Operational Ceiling |
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Service ceiling |
21,375 |
6,515 |
RCAH says 22,500ft |
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Single-engine ceiling |
8,150 |
2,485 |
RCAH says 8,000ft |
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Naut. miles |
Statute miles |
Kilo-meters |
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Range, maximum cruising power |
956 |
1,100 |
1,770 |
with 30 minutes reserve |
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Range, economy cruising power |
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Range, maximum cruising power, max payload |
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Range, economy cruising power, max payload |
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mph |
kts |
km/hr |
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Maneuvering |
160 |
139 |
257 |
True Indicated |
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Max. structural cruising (Max. Operating Speed) (Vmo) |
210 |
182 |
338 |
True Indicated |
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Never Exceed (Vne) |
270 |
235 |
435 |
True Indicated |
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Flaps extended – Half (Vfe) |
150 |
130 |
241 |
True Indicated |
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Flaps extended – Full |
130 |
113 |
209 |
True Indicated |
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Landing gear extended |
180 |
156 |
290 |
True Indicated |
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Maximum level speed (TAS) |
218 |
189 |
351 |
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Maximum cruising speed (TAS) - at 70% power |
205 |
178 |
330 |
at 10,000ft / 3,048m |
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Economy cruising speed (TAS) - at 65% power |
199 |
173 |
320 |
at 10,000ft / 3,048m |
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Takeoff speed |
87 |
76 |
140 |
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Landing speed |
82 |
71 |
132 |
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Best rate-of-climb speed (Vy) |
110 |
96 |
177 |
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Best Angle of Climb speed (Vx) |
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Minimum Control speed (Vmc) |
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Stall Speed (Clean) (Vsi) |
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Stall Speed (Dirty) (Vso) - power off |
63 |
55 |
101 |
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fpm |
mpm |
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Initial Rate of Climb |
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Max. Rate of Climb at Sea Level |
1,400 |
427 |
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Max. Rate of Climb at Sea Level, single engine |
310 |
95 |
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Engines (1): |
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Characteristics |
Piston, air-cooled, with 6 horizontally Opposed cylinders |
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Manufacturer |
Lycoming |
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Engine Type |
O-540 |
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Engine Variant |
-A1A |
-A1A5 |
-A2B |
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Type Certificate Number |
E-295 |
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Type Certificate Date |
October 31st 1957 |
June 18th 1958 |
July 24th 1958 |
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Applicable under STC No. |
n/a |
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Maximum continuous HP |
250 |
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Maximum continuous RPM |
2,575 |
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Takeoff HP (5 minutes) |
250 |
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Takeoff RPM |
2,575 |
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Weight (lb.) |
374 |
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Reduction Gear Ratio |
n/a |
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Supercharging Ratio |
n/a |
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Bore & Stroke (inches) |
5.125 x 4.375 |
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Displacement (cu.in.) |
541.5 |
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Compression Ratio |
8.50 : 1 |
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Carburetor Make & Model |
PAC MA-4-5 (formerly Marval Schebler/Facet) |
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Notes: |
The O-540-A1A has two 6th order counterweights (dampers). |
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The O-540-A1A5 has one 5th and one 6th order counterweights (dampers). |
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The -A2B is an -A1A with short propeller governor studs and propeller locating bushing re-located 60 degrees counter-clockwise. |
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Engines (2): |
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Characteristics |
Piston, air-cooled, Fuel Injected, with 6 horizontally Opposed cylinders |
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Manufacturer |
Lycoming |
Continental |
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Engine Type |
IO-540 |
IO-470 |
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Engine Variant |
-A1A5 |
-B1A |
-E |
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Type Certificate Number |
1E4 |
n/a ? |
3E1 |
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Type Certificate Date |
June 30th 1961 |
n/a ? |
November 26th 1958 |
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Applicable under STC No. |
SA257CE |
n/a |
n/a |
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Maximum continuous HP |
290 |
260 |
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Maximum continuous RPM |
2,575 |
2,625 |
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Takeoff HP (5 minutes) |
290 |
260 |
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Takeoff RPM |
2,575 |
2,625 |
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Weight (lb.) |
414 |
411 |
429 |
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Reduction Gear Ratio |
n/a |
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Supercharging Ratio |
n/a |
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Bore & Stroke (inches) |
5.125 x 4.375 |
5.00 x 4.00 |
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Displacement (cu.in.) |
541.5 |
471 |
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Compression Ratio |
8.70 : 1 |
8.60 : 1 |
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Injector Make & Model |
PAC RS10ED1 |
TCM |
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Notes: |
The IO-540-A1A5 has one 5th and one 6th order counterweights (dampers). |
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The IO-540-B1A is the same as the -A1A5 except for updraft exhaust cooling. |
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The IO-470-E has four 6th order dampers. |
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Propellers (1): |
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Characteristics |
Constant speed, hydraulic, with feathering and unfeathering features. |
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Manufacturer |
Hartzell |
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Hub Model |
HC-82XK |
HC-82VK |
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Hub Variant |
-2 |
-2B |
-2B1 |
-2C1 |
-2B |
-2B1 |
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Type Certificate Number |
P-878 |
P23EA |
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Type Certificate Date |
October 8th 1952 |
March 4th 1966 |
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Hub Material |
Alloy Steel |
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Blade Model |
8433-4 |
8433-6 |
8433-4 |
V8433-4 |
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Blade Material |
Aluminum Alloy |
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Number of Blades |
2 |
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Diameter (inches) |
80 |
78 |
80 |
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Diameter (meters) |
2.032 |
1.981 |
2.032 |
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Cut-off permitted |
none |
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Prop tip ground clearance (inches) |
23.29 |
22.29 |
23.29 |
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Prop tip fuselage clearance (inches) |
12.00 |
11.00 |
12.00 |
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Distance between propeller centers |
153" |
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Pitch setting at 30" Station - Low |
14o |
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- High |
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- Feathered |
82o to 84o |
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Max. Hub & Blade weight (lb.) |
67 |
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Maximum continuous - HP |
260 |
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Maximum continuous - RPM |
2,625 |
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Maximum Takeoff - HP |
260 |
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Maximum Takeoff - RPM |
2,625 |
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Propellers (2): |
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Characteristics |
Constant speed, hydraulic, with feathering and unfeathering features. |
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Manufacturer |
Hartzell |
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Hub Model |
HC-A2XK |
HC-A2VK |
HC-A3VK |
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Hub Variant |
-2C1 |
-2B |
-2C1 |
-2B |
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Type Certificate Number |
P-908 |
P24EA |
P6EA |
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Type Certificate Date |
Oct 7th 1958 |
Apr 1st 1966 |
August 15th 1962 |
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Applicable under STC No. |
n/a |
n/a |
SA1547WE / SA1735SO |
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Hub Material |
Alloy Steel |
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Blade Model |
8433-4 |
V8433-4 |
V7636D-4 |
V7636D |
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Blade Material |
Aluminum Alloy |
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Number of Blades |
2 |
3 |
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Diameter (inches) |
80 |
72.625 |
76.625 |
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Diameter (meters) |
2.03 |
1.84 |
1.95 |
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Cut-off permitted |
none |
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Prop tip ground clearance (inches) |
23.29 |
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Prop tip fuselage clearance (inches) |
12.00 |
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Distance between propeller centers |
153" |
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Pitch setting at 30" Station - Low |
14o |
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- High |
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- Feathered |
82o to 84o |
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Max. Hub & Blade weight (lb.) |
67 |
90 |
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Maximum continuous - HP |
260 |
336 |
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Maximum continuous - RPM |
2,625 |
2,850 |
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Maximum Takeoff - HP |
260 |
336 |
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Maximum Takeoff - RPM |
2,625 |
2,850 |
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Engine & Propeller combinations: |
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Engines |
Propellers (Hub / Blade) |
Factory or other |
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Continental IO-470-E |
? |
Factory (tests - serial 654 only) |
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Lycoming O-540-A1A |
? |
Factory (tests - serial 654 only) |
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Lycoming O-540-A1A5 |
Hartzell HC-82XK-2 / 8433-4 |
Factory (tests - serial 618 only) |
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Lycoming O-540-A2B |
Hartzell HC-82XK-2B / 8433-4 |
Factory |
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Hartzell HC-82XK-2B1 / 8433-4 |
Factory |
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Hartzell HC-82XK-2C1 / 8433-4 |
Factory |
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Hartzell HC-A3VK-2B / V7636D |
Field - STC SA1735SO |
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Hartzell HC-A3VK-2B / V7636D-4 |
Field - Kensair STC SA1547WE |
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Lycoming O-540-A2B (assumed) |
Hartzell HC-82VK-2B / V8433-4 |
Field |
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Hartzell HC-82VK-2B1 / (unquoted) |
Field - probably blade V8433-4 |
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Hartzell HC-82XK-2B / 8433-6 |
Field |
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Hartzell HC-A2VK-2B / V8433-4 |
Field |
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Hartzell HC-A2XK-2C1 / (unquoted) |
Listed on TCDS - no trace of usage |
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Hartzell HC-A2VK-2C1 / V8433-4 |
Listed on TCDS - no trace of usage |
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Lycoming IO-540-A1A5 |
Hartzell HC-A3VK-2B / (unquoted) |
turbo-charged engines (SA257CE) |
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Lycoming IO-540-B1A |
? |
Factory (tests - serial 654 only) |
Notes
:The FAA Type Certificate Data Sheet quotes the HC-82XK-2C1 propeller hub as "HC-82XX-2C1."
The FAA Type Certificate Data Sheet quotes the HC-A2XK-2C1 propeller hub as "HC-A2XX-2C1."
The Model 500 also was equipped with the outboard wing panel extensions even though it didn't have the 'E' prefix on its model number.
