WSK (WYTWÓRNIA SPRZĘTU
KOMUNIKACYJNEGO)
WSK Kalisz ASz-62
IR
Radial Engine Adjustment
procedures
Copy of Type Certificate for ASz-62 IR
Polish Type Cert. for ASz-62 series engines
Front Rear
The WSK
Kalisz ASz-62 engine is a 1000hp nine cylinder air cooled
supercharged
radial engine. It was developed, by license,
from the Wright R-1820 Cyclone. It is the
standard power plant for all versions of the
AN-2.
The aircraft engine type ASz-62IR is a single row nine
cylinder,air-cooled
carburetor
radial engine with reduction gear. The engine is provided with a
singlespeed centrifugal
supercharger, a double ignition system, and inertia starter. It
is adapted to drive several
accessories including those of the agricultural equipment. The
engineis
used to power
the An-2 and M-1 8 aircraft. It has proven to be very reliable when
operated under
extremely severe conditions in arctic and desert climates. It has
also proven dependable
for agricultural aviation.
The ASz-62IR engine meets the requirements of FAR-33 and has met
the certification
requirements of Poland, Canada, Brazil, China and the USA. It is
also approved for use
on the Dehaviland Otter in Canada.
The more modern versions of the ASz-621R engine are the K9-AA,
Kg-BA
and K9-BB.
These engines have been improved by increasing their power. Their
take-offpower is
860 kW and their power rating is 698 kW. The K9-BA engine is also
equipped with an
adapter which allows setting the propeller into the feathered
airscrew
position.The K9-AA
and the K9-BBengines are suitable for the PZL M-24 (Super Dromader)
aircraft.
The H9-BA engine is suitable for the DC-3 (Dakota) aircraft and used
on Russian Li-2.
Cylinder Bore 6.125
inch(155.5
mm) Stroke 6.875 inch
(174.6
mm)
Swept Volume 1823 Cu.
inches(29.67
liters)
Compression Ratio 6.4:1
Gear Reduction ratio
0.637:1
11:16
Supercharger to crankshaft ratio 7:1
Dimensions:
Diameter 54
1/8 inches (1375 mm)
Length
44 1/2 inches (1130 mm) (without Starter and
Generator)
Dry Weight: 1250 pounds
Fuel 100 octane
aviationfuel
(91 octane minimum)
Oil
Aeroshell
100 or 120
Time to First Overhaul 1200
hrs
Time to 2nd Overhaul 1000 hrs
Total Engine Life 6200 hrs
Cylinders are numbered CW as viewed from Cockpit with cylinder number1 at the top.
Cylinders 4, 5, 6 & 7 , being lower, are therefore more
prone
to Hydraulic Lock problems,
with number 5 and number 6 being the most prone. The Oil
Sump is located between cylinders
5 and 6.
The intake pipes on cylinders 3, 4 & 5 have drain plugs installed in their low points.
Spark Plug installation torque 40 ft-lbs
Carburetor:
The AKM-62 IRA carburetor is a 4 barrel down-draft carburetor fed with
two float chambers.
It is equipped with an aneroid operated Altitude Compensator.
Magnetos:
The engine is equipped with two BSM-9 magnetos. Right Mag. Spark
advance
is 20 degrees BTDC.
Left hand Mag. Spark advance is 15 degrees BTDC. The right hand
magneto fires the front
spark plugs and the left hand magneto fires the rear plugs.
Starter:
The AN-2 engine is started with an RIM-U-24 Inertial Starter and
auxilliary
vibrator spark coil.
The inertial flywheel turns at 10,000 to 12,500 RPM and is geared
133:1to
turn the engine
at 75 to 94 RPM. Starter Clutch
is limited to 795 ft-lbs.
Generator:
The GSN-3000M generator is rated at 28.5 VDC and 100 Amperes
(fused at 150 Amps.) regulated by carbon pile.
Fuel Pump:
The BNK-12BK engine driven fuel pump is mounted on the right side
rearof
the engine and
includes a demand fuel pressure regulator.
Prop Speed Governor:
The R-9SM2, mounted on reduction gear cover, controls AW-2 propellor
pitch.
Some AN2V seaplanes use the RV-101 reversing governor with the AW2R
reversible hub.
Air Compressor:
The AK-50P Air Compressor is mounted on right rear crankcase coverand
provides air
pressure for the pneumatic brake system. An 8 liter ball-shaped air
tank stores 50 KG/cm2
(711 psi) air.
Vacuum Pump:
The 212CW Vacuum Pump provides vacuum for Aircraft Gyros.
Note: Agricultural versions of AN-2 may have a PLTZ-15
Hydraulic Pump
installed in place of a Vacuum Pump.
Note: The Dromedar M-18 Ag plane uses an AW-2-30 which has the same hub but slightly shorter 3.3 meter blades.
The AW-2-30 Series 01 can be used on
both
engine type ASz-62IRz or ASz-62M with three-passage
oil outlet .... and with constant speed
governor R9SM-2.
The AW-2-30 Series 02 is intended for use on
the engine type ASz-62M but can be adapted to the ASz-62IRz
by replacing the spacing sleeve 30-037 with
spacing
sleeve 62-10-310.
The propellor is manufactured by Polskie Zaklady Lotnicze, Warsaw, Okecie.
Prop/Crank ratio 11:16 (0.6875:1)
Max prop RPM = 1510 (max engine rpm=2200)
Fine Pitch angle @ 1meter radius = 17
degrees
min
Coarse Pitch
angle
"
= 32 degrees max
Blade sweep Diameter 3.3 meters (note:
the AW-2 prop was 3.6 meters in diameter)
Number of
Blades
4
Weight
187 Kg (412 pounds)
(each blade weighs 56 pounds and the hub assy. weighs about 188 pounds)
Time to first
OH
2000 hours
TBO
1500 hours
Note: Blade threads should be lubricated with black bear
grease
or bo-shield every 50 hours or during
each annual inspection.
--------------------------------------------------------------------------
Magneto Replacement
and
Timing Procedure
Engine Removal from Aircraft Photo
Gallery
