Continental Refrigerator TSIO-360 Series User manual

Publication X30583
©CONTINENTAL MOTORS, INC. AUGUST 2011
TSIO-360-A, B, C, D, E, F, H
TSIO-360-AB, BB, CB, DB, EB, FB,
GB, HB, JB, KB AND
LTSIO-360-E, EB, & KB
CONTINENTAL® AIRCRAFT ENGINE
OPERATOR’S
MANUAL
FAA APPROVED

A TSIO-360 Series Engine Operator’s Manual
31 August 2011
1-1
Supersedure Notice
This manual revision replaces the front cover and list of effective pages for Publication Part
No. X30583, dated July 1985. Previous editions are obsolete upon release of this manual.
Effective Changes for this Manual
0........................ July 1985
1...............31 August 2011
List of Effective Pages
Document Title:TSIO-360 Series Engine Operator’s Manual
Publication Number: X30583 InitialPublication Date:July1985
Page Change Page Change Page Change Page Change
Cover..............................1
A......................................1
i.......................................1
ii thru vi............................0
1-1 thru 1-2 .....................0
2-1 thru 2-4 .....................0
3-1 thru 3-12 ...................0
4-1 thru 4-6 .....................0
5-1 thru 5-62 ...................0
6-1 thru 6-8 .....................0
7-1 thru 7-12 ...................0
8-1 thru 8-8 .....................0
9-1 thru 9-10 ...................0
10-1 thru 10-8 .................0
11-1 thru 11-6..................0
Published and printed in the U.S.A. by Continental Motors, Inc.
Available exclusively from the publisher: P.O. Box 90, Mobile, AL 36601.
Copyright © 2011 Continental Motors, Inc. All rights reserved. This material may not be reprinted,
republished, broadcast, or otherwise altered without the publisher's written permission. This man-
ualisprovided withoutexpress, statutory,orimplied warranties.Thepublisher will notbeheld liable
for any damages caused by or alleged to be caused by use, misuse, abuse, or misinterpretation of
the contents. Content is subject to change without notice. Other products and companies men-
tioned herein may be trademarks of the respective owners.

i
NOTICE
IN ORDER TO PROPERLY USE THIS ENGINE,
THE USER MUST COMPLY WITH ALL
INSTRUCTIONS CONTAINED HEREIN.
FAILURE TO SO COMPLY WILL BE DEEMED
MISUSE, RELIEVING THE ENGINE
MANUFACTURER OF ANY RESPONSIBILITY.
THIS MANUAL CONTAINS NO WARRANTIES,
EITHER EXPRESS OR IMPLIED. THE
INFORMATION AND PROCEDURES
CONTAINED HEREIN PROVIDE THE
OPERATOR WITH TECHNICAL INFORMATION
AND INSTRUCTIONS APPLICABLE TO SAFE
OPERATION.
Continental Motors engine operating instructions
are generated prior to and independently of the
aircraft operating instructions established by the
airframe manufacturer. Continental Motors
engine operating instructions are developed
using factory controlled parameters that are not
necessarily the same as those specifications
required to satisfy a specific aircraft I engine
installation. Because of this difference the
aircraft operator should use the airframe
manufacturer's operating instructions found in
the Pilots Operating Handbook (POH) while
operating the aircraft unless otherwise specified
by the original airframe manufacturer.

INTRODUCTION
SECTION
TABLE OF CONTENTS
Design Features
Page
vi
I-I
II Specifications and Limits .................... 2-1
III Normal Operating Procedures ................ 3-1
IV In-Flight Emergency Procedures .............. 4-1
V Engine Performance and Cruise Control. . . . . . . 5-1
VI Abnormal Environmental Conditions ......... 6-1
VII Engine Description ......................... 7-1
VIII Servicing and Inspection. . . . . . . . . . . . . . . . . . . . . 8-1
IX Troubleshooting. . . .. . . . . . .. . .. .. . . . . . . . . . . . 9-1
X Storage and Removal From Storage .......... 10-1
XI Glossary .................................. 11-1
ii

LIST OF ILLUSTRATIONS
FIG. PAGE
1 Sea Level Performance Curves, TSIO-360-A, AB, B, BB ..... 5-3
2 Altitude Performance Curves, TSIO-360-A, AB, B,
BB ...... 5-4
3 Fuel Flow
Vs. BHP, TSIO-360-A, AB, B, BB .............. 5-5
4 Sea Level Performance Curves, TSIO-360-C,
rB ...•....... 5-6
5 Altitude Performance Curves, TSIO-360-C, CB
............. 5-7
6 Fuel Flow
Vs. BHP, TSIO-360-C, CB ..................... 5-8
7 Sea Level Performance Curves, TSIO-360-D, DB ........... 5-9
8 Altitude Performance Curves, TSIO-360-D,
DB ............ 5-10
9 Fuel Flow
Vs. BHP, TSIO-360-D, DB ..............•..... 5-11
10 Sea Level Performance Curves. LjTSIO-360-E. EB ......... 5-12
11 Altitude Performance Curves. L/TSIO-360-E. EB ........... 5-13
12 Fuel Flow Vs. BHP. L'TSIO-360-E. EB ................... 5-14
13 Fuel Pump Inlet Press. Vs. IJ1 BHP. IIO°F Avgas.
L TSI0-360-E.
EB ..................................... 5-15
14 Sea Level Performance Curves. TS IO-360-F. FB ............ 5-16
15 Altitude Performance Curves. TSIO-360-F. FB ............. 5-17
16 Fuel Flow Vs. BH P. TSIO-360-F. FB ..................... 5-18
17 Sea Level Performance Curves. TSIO-360-GB .. , ........... 5-19
18 Altitude Performance. 2700 RPM. TSIO-360-GB ........... 5-20
19 Altitude Performam:e. 2600 RPM, TSIO-360-GB ........... 5-21
20 Altitude Performance. 2500 RPM, TSIO-360-GB ........... 5-22
21 Altitude Performance. 2400 RPM. TSI0-360-GB ........... 5-23
22 Altitude Performance. 2200
RPM. TSI0-360-GB ........... 5-24
23 Altitude Performance. 2000
RPM. TSIO-360-GB ........... 5-25
24 Altitude Performance.
HmO RPM. TSIO-360-GB ........... 5-26
25 Power Management Operating Recommendations.
TS10-360-G B
........................................ 5-27
26 Fuel Flow
Vs. BHP. TSIO-360-GB ........................ 5-28
27 Critical Altitude
Vs. Engine Speed (Standard Day),
TSIO-360-GB
........................................ 5-29
28 Sea Level Performance Curves, TSIO-360-H, HB ........... 5-30
29 Sea Level Performance to Altitude, TSIO-360-H, HB
....... 5-31
30 Altitude Performance, 2800 RPM, TSIO-360-H, HB ........ 5-32
31 Altitude Performance, 2700 RPM, TSIO-360-H, HB ........ 5-32
32 Altitude Performance, 2600 RPM, TSIO-360-H, HB ........ 5-33
33 Altitude Performance, 2500 RPM, TSIO-360-H, HB ........ 5-33
34 Altitude Performance, 2400
RPM, TSIO-360-H, HB ....•... 5-34
35 Altitude Performance, 2300 RPM, TSIO-360-H, HB ........ 5-34
36 Altitude Performance, 2200
RPM, TSIO-360-H, HB ........ 5-35
37 Fuel Flow Vs. BHP, TSIO-360-H, HB .................... 5-36
iii

LIST OF ILLUSTRATIONS
FIG. PAGE
38 Sea Level Performance Curves, TSIO-360-JB .............. 5-37
·39
Sea Level Performance to Altitude, TSIO-360-JB ........... 5-38
40 Altitude Performance, 2800
RPM, TSIO-360-JB ............ 5-39
41 Altitude Performance, 2700 RPM, TSIO-360-JB ............ 5-39
42 Altitude Performance, 2600 RPM, TSIO-360-JB ............ 5-40
43 Altitude Performance, 2500 RPM, TSIO-360-JB ............ 5-40
44 Altitude Performance, 2400 RPM, TSIO-360-JB ............ 5-41
45 Altitude Performance, 2300 RPM, TSIO-360-JB ............ 5-41
46 Altitude Performance, 2200 RPM, TSIO-360-JB ............ 5-42
47 Fuel Flow Vs. BHP, TSIO-360-JB ........................ 5-43
48
49
50
51
52
53
54
55
56
Sea Level Performance Curves, LjTSIO-360-KB ............ 5-44
Altitude Performance.
2HOO RPM, LjTSIO-360-KB ......... 5-45
Altitude
Performancl~. 2700 RPM, LjTSIO-360-KB ......... 5-46
Altitude Performance, 2600
RPM, LjTSIO-360-KH ......... 5-47
Altitude Performance, 2500
RPM, LjTSIO-360-KB ......... 5-48
Altitude Performance, 2400
RPM, LjTSIO-360-KB ......... 5-49
Altitude Performance, 2300
RPM, LjTSIO-360-KB ......... 5-50
Altitude Performance. 2200
RPM, L/TSIO-360-KB ......... 5-51
Power Management Operating Recommendations,
L/TSIO-360-KB
...................................... 5-52
57 Fuel Flow Vs. BHP. L/TSIO-360-KH ..................... 5-53
58 Critical Altitude Vs. Engine Speed (Standard Day),
L/TSIO-360-KB
...................... , ............... 5-54
59 Metered Fuel Press.
Vs. Fuel Flow. All Models ............. 5-55
60 Fuel
Pump Inlet Press. Vs. (if BHP, 1I0°F Avgas,
TSIO-360-F.
FH. GB. KB ............................. 5-56
61 Vapor Return Flow Vs. Pump Pressure.
TSIO-360-F, FB. GH,
KB ............................. 5-57
62 Fuel Flow Vs. Pressure Drop. TSIO-360-G B. KB ........... 5-58
63 Speed Correction Chart - S L to 2000 Ft. MSI..
TSIO-360-F, FB, GB.
KH ............................. 5-59
64 Critical Altitude Variations.
(I\pical) Simple Turbo Systems,
TSIO-360-F,
FH. GH, KH ............................. 5-60
65 Typical Engine Fuel System Operating Characteristics -
2600
RPM (Standard Day at SjL) ...................... 5-61
66 Oil Lubrication Diagram ................................ 7-2
67 Fuel System Schematic .................................. 7-5
68 Inductionj Exhaust System Schematic ..................... 7-7
69 Turbocharger Sectional .................................. 7-8
70 Fixed Orifice Wastegate. TSIO-360-E, EB. F. FB. GB. KB
I TSIO-360-F. FB. KH
............................... 7-8
71 Ignition Wiring Diagram ................................ 7-10
iv

INTRODUCTION
This booklet is intended to provide pilots, operators and main-
tenance personnel with recommended procedures relatingto engine
operation, servicing and periodic maintenance. Subjectsare limited
to engine operation and inspection normally carried out on engines
installed in aircraft. No effort
is made herein to describe extensive
repair work or overhaul. For such instructions, refer to the appli-
cable
overhaul manual. Careful observation of operating limits and
compliance with recommended inspection procedures herein will
result in greater engine reliability.
The operating instructions outlined in this manual have been
developed for general airframe installation; for a particular air-
frame refer
to the appropriate aircraft operator's manual. Recom-
mendations,
cautions and warnings regarding operation of this
engine
are not intended to impose undue restrictions on operation
of the aircraft, but are inserted to enable the pilot to obtain
maximum performance from the engine commensurate with safety
and efficiency. Abuse, misuse or neglect of any piece of equipment
can cause eventual failure. In the case of an aircraft engineit should
be obvious
that a failure may have disastrous consequences. Failure
to observe the instructions contained in this manual constitutes
unauthorized operation in areas unexplored during development of
the engine, or in areas in which experience has proved to be un-
desirable
or detrimental.
Notes,
Cautions and Warnings are included throughout this
manual. Application is as follows:
NOTE: Special interest information which
may facilitate the
operation of equipment.
CA UTION: Information issued to emphasizecertain instructionsor
10 pre\'enl possihle damage to engine or accessories.
WARNINGS:
Information which, if disregarded, may result in
severe
damage or destruction of the engine or endangerment to
personnel.
v

Users are advised to keep up with latest information by means of
service bulletins, which are available for study at any approved
Teledyne Continental Motors Distributor location, and are also
available
on an annual subscription basis. Subscription forms are
available at Distributors or from Teledyne Continental Motors,
P.O. Box 90, Mobile, Alabama 36601, Attention: Publications
Department.
WARNING . .. This engil!e must be installed in accordance
with all requirements and limitations listed
in the Specifi-
cations and Limits for Teledyne Continental Aircraft
Engines.
vi

--------;
SECTION I
DESIGN FEATURES
The engines described herein are turbocharged, fuel injected, six-
cylinder horizontally opposed,
air cooled, and incorporate an
overhead valve design. All provide a 360 cubic inch displacement,
4.44 inch bore, 3.87 inch stroke and 7.5 to 1 compression ratio. The
turbocharger is driven by exhaust gases and engine models A, AB,
B, BB, C, CB, D, DB, H, HB /¥- JB incorporate a variable pressure
cQntroller, pressure relief valve
and a wastegate assembly. The
models E, EB, F, FB, GB & KB use a fixed orifice type bypass
assembly.
The turbine and compressor assembly is connected to the
induction/ exhaust system with hoses, linkage and ducting required
for a functional installation
and is lubricated by engine oil.
Provisions are made for installation of variable pitched propeller
and propeller governor assembly. The crankshaftflange has six bolt
holes, two dowel pins and a center pilot extension provided for
attaching the propeller. Provisions are made in the pilot extension
for the hydraulic propeller control oil, which is supplied internally
from the
governor pad. The crankshaft is also equipped with
pendulum type torsional damper weights. The engine has remov-
able hydraulic tappets. Positive
rotation is provided for the valves
by the use of rotors. Tappets, pushrod ends, rocker arm bushings,
valves, etc.
are lubricated by the engine oil pressure system. The
engine is equipped with a right angle drive starter adapter and a
direct drive starter motor. The engine main fuel filter, engine
controls, vacuum pump and propellergovernor are furnished by the
aircraft manufacturer.
The relatively high power delivered by these engines, per pound of
weight, is achieved by utilization of carefully selected high strength
materials, by improvements
in design calculated to make the most
of these high quality materials, and by very close control of critical
dimensions, surface finishes, heat treatment
and hardening pro-
cesses. Careful work has produced rugged engines; however, no
amount
of ruggedness built into an engine will enable it to withstand
serious mistreatment. Overheating, neglect, inferior fuels
or
lubricants will seriously affect engine performance, particularly
since the specified power rating is high and each part must befree to
function properly in order to withstand the imposed loads with
1-1

minimum wear. These considerations are mentioned in order to
emphasize the necessity
of usingonly the manufacturer'sfuel and oil
recommendations and of keeping the fuel, oil and air filters clean.
The increased diameter
crankshaft versions of the TSIO-360 series
(identified by a second letter "B" in the model. i.e .. TSIO-360-EB)
have
the same operating limitations as the standard models. The
modified crankshaft engines may be used as replacement enginefor
the standard modeL but the reverse is not certified. For example, a
TSIO-360-EB may be installed to replace a TSlO-360-E, but a
TSIO-360-E may not be installed to replace a TSIO-360-EB.
1-2

SECTION II
SPECIFICATIONS AND LIMITS
Specifications for the TSIO-360 Series Aircraft Engines:
FAA Type Certificate Number
E9CE
RATINGS
Maximum Continuous BHP
See Tabulated Data
Maximum Continuous RPM ............ See Tabulated Data
Maximum Continuous Manifold
Pressure, In. HG. .
................... See Tabulated Data
CYLINDER DATA:
Number
of Cylinders ................................... 6
Displacement
(Cubic Inches) ........................... 360
Bore
and Stroke (Inches) ....................... 4.44 x 3.88
Compression Ratio .................................. 7.5:1
PROPELLER DRIVE DATA:
Type . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .
.. ARP 502
Direction
of rotation ..................... TS I0 - clockwise
L
TSIO -counterclockwise
Ratio (To
Crankshaft) ................................. 1:1
Vibration Dampers, Number & Order
Models A, B .................................. Two 6th
Models AB, BB, C, CB, D, DB, E, EB,
F, FB, GB, H, HB, lB, KB .............. One 6th, One 4YS
FUEL SYSTEM:
Type . . . . . . . . . . . . . . . . . . . . . .. Continuous Flow Fuel Injection
Make
........................ Teledyne Continental Motors
Fuel -(Min. Grade Aviation Gasoline
Conforming to ASTM-D41O-46) ............ 100 or 100LL
2-1

LUBRICATION SYSTEM:
Specification ................................... MHS-24B
Grade
(SAE)
Above 40°F Ambient Air (Sea Level) ............. SAE 50
Below 40° F Ambient Air (Sea Level) .... SAE 30 or IOW-30
Sump Capacity, Quarts Maximum
Models E,EB.F.FS,GB.KB .......................... 8
Models
A,AB.B,Bs'C.CB.D,DS,H,HB,JB ..........•.. 10
Usable Oil Quarts Nose Up .......................... 6.1
Usable Oil Quarts Nose Down ....................... 6.1
(Refer to Overhaul Manual for model and degrees of angle)
ACCESSORIES:
See appropriate parts catalog and specification list for accessories
pertaining
to your engine model.
2-2

TABULATED DATA
AND
LIMITS
A,AB B,BB C,CB
D,DB
E,EB
Cylinder Bore (inch) 4.44 4.44 4.44 4.44 4.44
Piston Stroke (inch) 3.87 3.87 3.87 3.87 3.87
Total Displacement (cu. in.) 360 360 360 360 360
Compression Ratio
7.5:1
7.5: I 7.5: I
7.5:1 7.5:1
Rated Max. Cont.
BHP
210 210
225
225
200
Rated Max. Cont.
RPM
2800 2800 2800 2800 2575
Rated Max.
Take-"Off
BHP
210 210
225
225
200
Rated Max. Take-off
RPM
2800 2800 2800 2800
2575
Max. Rec. Cruise
BHP
157
157
146
146 150
Max. Rec. Cruise
RPM
2600 2600
1800 1800
2450
Rec. Idling
RPM
600 600 600 600 700
Max. Man.
PR
Cont. 32.0 32.5 37.0 . 36.0 40.0
N Max. Man.
PR
Take-off
I
~
Min. Fuel Oct.
Rating
100LL/100 100LL/100 100LL/100 100LL/100 100LL/100
Oil Press. Cruise psi 30-60 30-60 30-60 30-60 30-80 Oil Press. Idle psi (Min.)
10 10
10 10
10
Oil Press. Max. Allow. (Cold)
100
100 100
100
100
Min. Oil Temp. for T.O. 0
F.
75 75
75 75 75
Max. Allow. Oil Temp. 0
F.
240 240 240 240 240
Max. All
CyJ.
Head Temp. 0
F.
460 460 460 460 460
Max. Allow. Oil Cons. Ibs/
BHP
/ hr.
(i)
.015 .015 .015 .015 .015
Firing Order 1-6-3-2-5-4 1-6-3-2-5-4 1-6-3-2-5-4 1-6-3-2-5-4 1-6-3-2-54 0
Ignition Timing 0 BTC Both Magnetos 20 20 20 20
20
Basic Engine Weight (No accessories) 300.75 296.75 285.0 285.0 285.0
Total Engine Dry Weight
with Accessories (Subject to
Production Variation
of
± 2.5%) 333.56 329.56 302.0 302.0 385.0
(j)
Formula: .006 x % Power
100
Q) 1-4-5-2-3-6 for LTSIO-360 Series.

TABULATED DATA
AND
LIMITS
F,FB GB
H,HB
JB
KB
Cylinder Bore (inch) 4.44 4.44 4.44 4.44 4.44
Piston Stroke (inch) 3.87 3.87 3.87 3.87 3.87
Total Displacement (cu. in.) 360 360 360 360 360
Compression Ratio 7.5:1 7.5:1
7.5:1
7.5:1
7.5:1
Rated Max. Cont.
BHP
200 210 210
225
220
Rated Max. Cont.
RPM
2575 2700 2800 2800
28.00
Rated Max. Take-off
BHP
200 210 210
225
220
Rated Max. Take-off
RPM
2575
2700 2800 2800 2800
Max. Rec. Cruise
BHP
150
160
137
147
160
Max. Rec. Cruise
RPM
2450 2450 2450 2450 2500
Rec. Idling
RPM
700 700 600 600 700
Max. Man.
PR
Cont. 41.0 40.0 34.5 ' 37.0 40.0
w Max. Man.
PR
Take-off
• Min. Fuel Oct. Rating 100LL/100
IOOLL/IOO
100LL/100 100LL/100
lOOLL/IOO
oIiIo.
Oil Press. Cruise psi 30-80 30-80 30-60 30-60 30-80 Oil Press. Idle psi (Min.)
10
10
10
10 10
Oil Press. Max. Allow. (Cold)
100 100 100 100 100
Min. Oil Temp. for T.O. 0
F.
75 75
75 75 75
Max. Allow. Oil Temp. 0
F.
240 240 240 240 240
Max. All Cyl. Head Temp. 0
F.
460 460 460 460 460
Max. Allow. Oil Cons. Ibs./
BHP
/ hr. (i) .015 .015 .015 .015 .015
Firing Order 1-6-3-2-5-4 1-6-3-2-5-4 1-6-3-2-5-4 1-6-3-2-5-4 1-6-3-2-5-4
G>
Ignition Timing 0
BTe
Both Magnetos 20
·20
20 20 20
Basic Engine Weight (No accessories) 342.05 350.0 296.00 296.00 350.0
Total Engine Dry Weight
with Accessories (Subject
to
Production Variation
of
±2.5%) 393.05 386.0 313.00 313.00 392.0
CD
Formula: .006 x % Power
100
~
1-4-5-2-3-6
for
LtSIO-360
Seric:s.

SECTION III
NORMAL OPERATING PROCEDURE
CAUTION . .. This section pertains to.flight operations conducted
under "Standard Day" conditions. The pilot should thoroughly
familiarize himse(f' with the Section
on Abnormal Operating
Conditions. Whenever such abnormal conditions are encountered
or anticipated. the procedures and techniquesfor normal operation
should be tailored accof'(ling~l'. For example. i/'the aircraft is to be
temporari~l' operatedin extreme coldor hot weather. consideration
should he Riven to an early oil chanRe and/or a routine inspection
servicing.
GENERAL
The life of your engine is determined by the care it receives. Follow
the instructions contained in this manual carefully.
The engine receives a run-in operation before leaving the factory.
Therefore, no break-in schedule need be followed. Straight mineral
oil (MIL-C-6529 Type II) should be used for the first oil change
period (25 hours).
The minimum grade aviation fuel for these engines is 100LL (Blue)
or 100 (Green). In case the grade required is not available, use a
higher rating. Never use a lower rated fuel.
WARNING ... The use of a lower octane rated fuel can
cause pre-ignition or detonation, which can damage an
engine the first time high power is applied. This will most
likely occur on takeoff. If the aircraft is inadvertently
serviced with the wrong grade of fuel, completely drain and
properly service fuel tank/tanks.
NOTE ... The following checklists are general in nature, since the
various airframe/powerplant combinations are not necessarily the
same in setup and layout. Consult your own pilot's operating
hand book for the specific challenge and response checklists
required for your aircraft.
3-1

PRESTARTING
Before each flight the engine and propeller must be examined for
damage, oil leaks, security
and proper servicing.
I. Place the ignition switch
to the "OFF" position.
2. Operate all controls and check for binding and full range of
travel.
3. Assure
that fuel tanks contain proper grade and quantity of
fuel. (100LL-Blue or 100-Green).
4.
Drain a quantity of fuel from all sumps and strainers into a
clean container. If water or foreign matter is noted, continue drain-
ing until only clean fuel appears.
5.
Check oil level in sump.
6. Check cowling for security.
STARTING
I. Fuel Selector -ON, appropriate tank.
2. Propeller
Control -HIGH RPM.
3. Mixture Control -FULL RICH.
4. Battery Switch -ON.
5. Throttle - FULL OPEN.
6. Boost Pumps or Primer -ON, 2 to 3 seconds.
7. Throttle -1/2 INCH OPEN.
8. Magneto/Start Switch - START position.
Release the
Magneto / Start Switch to BOTH positionas soon as the
engine starts.
3-2
l

CA UTION ... Do not engage thestarter when the engineis running
as this will damage the starter. Do not crank for longer than thirty
seconds at a time,
as this may cause the starter motor to overheat. rf
the engine does not start a/ier thirty seconds of cranking, allow a 3
to 5 minute cooling period hefore attempting to restart.
CA UTION ... rf engine kicks hack when starting, DO NOT attempt
to start. The ignition starting system is inoperative and must be
repaired before damaging starler adapter assembfl'.
(Cold Starts)
a. Throttle -FULL OPEN.
b. Mixture Control - FULL RICH.
c. Primer -ON, 2 to 3 seconds.
d. Throttle -1/2 INCH OPEN.
e. Magneto/Start Switch - START position.
f. Once engine starts, it may be necessary to keep engine running
with primer.
g. Magneto/Start Switch -BOTH position.
(Flooded Engine)
a.
Mixture Control - IDLE CUT-OFF.
b. Throttle - FULL OPEN.
c. Magneto/Start Switch -START.
d. Once engine starts, release
Magneto/Start Switch to BOTH.
Retard
the throttle to 1000 RPM and slowly advance the mixture
control
to FULL RICH position.
3-3

(Hot Starts)
a. Throttle -
FULL OPEN.
b. Mixture Control - IDLE CUT-OFF.
c. Boost Pump -ON, 10-15 seconds or until the fuel pumping
pulsations stabilize.
d. Mixture
Control - FULL RICH, momentary priming may be
required.
e. Throttle - Retard to 1/2 INCH.
f. Magneto/Start Switch - START position.
g. Once engine starts, release Magneto/Start Switch to BOTH.
STARTING (Cont'd.)
9. Throttle 1000 to 1500 RPM.
10 .. Oil Pressure -ABOVE 30 POUNDS WITHIN 30 SECONDS.
II. Alternator Switch -ON.
12. Use the same procedure to start other engie, if operating a twin
engine installation.
GROUND RUNNING: WARM-UP
Teledyne Continental aircraft engines are aircooled, and therefore
dependent upon the forward speed
of the aircraft for cooling. To
prevent overheating, it is important that the following rules be
observed.
I. Head the aircraft into the wind.
2. During ground operations the propeller should be in the "Full
Increase"
RPM position.
3-4

3. Avoid prolonged idling at low RPM. Fouled spark plugs can
. result from this practice.
4. Leave mixture in "Full Rich': (See "Ground Operation at High
Altitude Airports," Section VI for exceptions).
5. Warm-up 900-1000 RPM.
PRE-TAKEOFF CHECK
I. Maintain engine speed at approximately 1000 to 1500 RPM for
at least
one minute in warm weather, and as required during cold
weather
to prevent cavitation in the oil pump and to assure
adequate lubrication.
2. Advance throttle slowly until tachometer indicates an engine
speed
of 1200 RPM. Allow additional warm-up time at this speed
depending upon ambient temperature. This time may be used for
taxiing to take-off position. The minimum allowable oil tem-
perature for run-up is 75°F.
CA UTION ... Do not operate the engine at run-up speedunless oil
temperature is 75°F. minimum.
3. Perform all ground operations with cowl flaps, if installed, full
open, mixture control in "FULL RICH" and the propeller control
set for "Full Increase" RPM (except for brief testing of propeller
governor).
4. Restrict ground operations to the time necessary for warm-up
and testing.
5. Increase engine speed to 2000 RPM only long enough to
perform the following checks:
a. Magnetos: With both magnetos "ON': position the right
magneto switch "OFF" and note engine RPM; now back to both
magnetos "ON" to clear the spark plugs. Then position the left
magneto switch "OFF" and note engine RPM. Now return
switch to both magnetos "ON'~ The difference between the two
3-5

magnetos operated individually should not differ more than 50
RPM with a maximum drop for either magneto of 150 RPM.
Observe engine for excessive roughness during this check.
If no drop in RPM is observed when operating on either
magneto alone. the switch circuit should be inspected.
WARNING ... Absence of RPM drop when checking
magnetos may idicate a malfunction in the ignition
circuit.
This type of, malfunction should be corrected
prior to continued operation of the engine. Should the
propeller be moved by hand (as during preflight) the
engine may start and cause injury to personnel.
CAUTION . .. Do not underestimate the importance 0/ a pre-
takeoff"
magneto check. When operating on single ignition. some
RPM drop should he noted. Normal indications should he a 25-75
RPM drop and slight engineroughness as each magneto is switched
oft: A hsence
0/ a magneto drop ma)' heindicative 0/ an openswitch
circuit
or an improper~1' timed magneto. A drop in RPM that
exceeds 150 ma), indicate
afault}' magneto or/ouled spark plugs.
b. Minor spark plug fouling can usually be cleared as follows:
(I) Magnetos -
Both On.
(2) Throttle -2200 RPM.
(3) Mixture -Move toward idle cutoff until RPM
peaks and hold for ten seconds. Return mixture to full
rich.
(4) Magnetos -Recheck
(per paragraph 5a).
If the engine is not operating within specified limits, it
should be inspected and repaired prior to continued
operational service.
CA UTION . . . A void prolonged single magneto operation to
preclude
fouling 0/ the spark plugs.
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