Continental Motors O-470-B User manual

Publication X30097
©CONTINENTAL MOTORS, INC. AUGUST 2011
O-470-A, B, E
G, J, K
L, M, R
S & U
CONTINENTAL® AIRCRAFT ENGINE
OPERATOR’S
MANUAL
FAA APPROVED

A O-470 Series Engine Operator’s Manual
31 August 2011
Supersedure Notice
This manual revision replaces the front cover and list of effective pages for Publication Part
No. X30097, dated April 1985. Previous editions are obsolete upon release of this manual.
Effective Changes for this Manual
0........................April 1985
1...............31 August 2011
List of Effective Pages
Document Title:O-470 Series Engine Operator’s Manual
Publication Number: X30097 InitialPublicationDate:April1985
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 2-6 .....................0
3-1 thru 3-12...................0
4-1 thru 4-4 .....................0
5-1 thru 5-24...................0
6-1 thru 6-8 .....................0
7-1 thru 7-4 .....................0
8-1 thru 8-6 .....................1
9-1 thru 9-8 .....................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
manual is provided without express, statutory, or implied warranties. The publisher will not be held
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 mentioned 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
PURPOSE OF THE DATA PRESENTED IS
INSTRUCTION, INFORMATION, AND SAFETY.
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
I Design Features
Page
vi
1-1
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
VI I I Servicing and Inspection ..................... 8-1
IX Troubleshooting. . . . . . . . . . . . . . . . . . . . . . . . . . . . 9-1
X Storage and Removal From Storage .......... 10-1
XI Glossary. ... . . . . . . . . . . . .. . . . . . . . . . . . . . . . .. 11-1
ii

____ --'~~___ _ ___ ~- __ ----~o~~ ___ ~:~ _____ ~~ ____ ~~ __ ~ ________________ _
-----~--l
LIST OF IttUSTRATIONS
FIGURE
PAGE
Sea Level Performance for 0-470-A
5-3
2
Altitude Performance for 0-470-A ............ 5-4
3
Sea Level Performance for 0-470-8 ........... 5-5
4
Altitude Performance for 0-470-8 ............ 5-6
5
Sea Level Performanee for 0-470-E ........... 5-7
6
Altitude Performance for 0-470-E ............ 5-8
7
Sea Level Performance for 0-470-G .......... 5-9
8
Altitude Performance for 0-470-G ............ 5-10
9
Fuel Flow Limits for 0-470-G ................. 5-11
10 Sea Level Performance for 0-470-J ........... 5-12
II Altitude Performance for 0-470-J ............ 5-13
12 Fuel Flow Limits for 0-470-J ................. 5-14
13 Sea Level Performance for 0-470-K&L .. . . . . .. 5-15
14 Sea Level Performance for 0-470-R&S ......... 5-16
15·
Altitude Performance for 0-470-K,L,R&S . . . . .. 5-17
16 Fuel Flow Limits for 0~470-K,L,R&S .......... 5-18
17 Sea Level Performance for 0-470-M .......... 5-19
18 Altitude Performance for 0-470-M ........... 5-20
19 Fuel Flow Limits for 0-470-M ............... 5-21
20
Sea Level Performance for 0-470-U .......... 5-22
21 Altitude Performance for 0-470-U ............ 5-23
22 Fuel Flow Limits for 0-470-U ............ ;... 5-24
23 Lubrication Diagram ....................... 7-2
24
Wiring Diagram ............................ 7-3
iii

INTRODUCTION
This booklet is intended to provide pilots, operators and main-
tenance personnel with recommended procedures relating to engine
operation, servicing and periodic maintenance. Subjects are 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 recommen~ed inspection procedures herein will
result in
greater engine relia bility.
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 engine it 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.
CAUTION: Information issued to emphasize certain instructions
or to pre\'ent possihle damaRe 10
el1Rine or accessories.
WARNINGS: Information which, if disregarded, may result in
severe
damage or destruction of the engine or endangerment to
personnel.
iv

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 engine must be installed in accordance
with all requirements ang limitations listed in the Specifi-
cations and Limits for Teledyne Continental Aircraft
Engines.
v

- -.-=.~.=~==~~~-------------------------.----~----

SECTION I
DESIGN FEATURES
The engines have overhead valve cylinders with 5.00 inch bore, 4.00
inch stroke,
471 cubic inch displacement and a compression ratio of
7.0:1. The exception is a compression ratio of 8.0:1 for the 0-470-B,
G & M Engines and 8.6: I for the 0-470-U. The cylinders have down-
directed exhaust outlets. All models with the exception ofO-470-A,
E & J, have
rotation provided for the exhaust valves by the use of
rotators. The crankshaft is equipped with pendulum-type torsional
damper weights. The engines have removable-type hydraulic
tappets.
Tappets, pushrod ends and rocker arm bearings are lubri-
cated by the
engine main oil pressure system.
The engines are furnished with a direct cranking starter and a belt-
driven
generator or alternator. The exhaust systems are not
supplied with the engines. The engine main fuel filter, engine
cntrols,
vacuum pump and propeller governor are furnished by the
aircraft manufacturer.
The relatively high power delivered by the 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
processes. Careful work has produced more rugged engines than
could be built by less exacting methods; however, no amount of
ruggedness built into an engine will enable it to withstand serious
mistreatment.
Overheating, neglect and inferior fuels and lubricants
will seriously affect engine
performance, particularly when the
specific power rating is high and each part must be free to function
properly in order to withstand the imposed loads with minimum
wear. These considerations are mentioned here in order to empha-
size the necessity of using only the manufacturer's recommended
gasoline and oil and of keeping the fuel, oil and air filters clean. The
octane rating of engine fuel should be as specified under detailed
specifications in
Section II.
1-1

~-----------------------------------------------------------------------------------

SECTION II
SPECIFICATIONS AND LIMITS
DETAILED SPECIFICATIONS
This specification is for the 0-470 series Aircraft Engines which
have:
FAA Type Certificate Number ......................... 273
RATINGS:
Maximum continuous, sea level BHP - RPM .... see page 2-4
Manifold
Pressure, in. Hg. at Sea Level .............. N / A
Manifold
Pressure, in. Hg. Critical Altitude (Feet) ..... N /A
CYLINDER DATA:
Number of Cylinders ................................... 6
Displacement
(Cubic Inches) ........................... 471
Bore and Stroke (Inches) ....................... 5.00 X 4.00
Compression
Ratio ........................... see page 2-4
PROPELLER DRIVE DATA:
Type ............................. Flanged, 6 Bolt ARP 502
Direction
of Rotation ........................... Clockwise
Ratio
(To Crankshaft) ............................. Direct
Vibration Dampers, Number and Order ... One 6th, One 4-1/2
(0-470-V ................. Two 6th, One 5th, One 4-1/2)
FUEL SYSTEM:
Type .............................. Carburetor, see page 2-5
Fuel-Aviation Gasoline (Grade Min.) ........... see page 2-4
2-1

LUBRICATION SYSTEM:
Oil Specification ................................ MHS-24
Oil Grade (SAE)
Above 40°F.
Ambient Air (Sea Level) .................. 50
Below 40°F. Ambient Air (Sea Level) ........ 30 or IOW-30
All Temperatures .............. Multiviscosity, see page 7-3
Sump Capacity, Quarts Maximum ............. see page 2-4
Usable Oil
Quarts 15° Nose Up ........................ 6
Usable Oil
Quarts 15° Nose Down ...................... 6
IGNITION SYSTEM:
Timing (0 BTC) ............................... see page 2-5
See appropriate parts catalog and specification list for accessories
pertaining to
your engine model.
2-2

~
I
~
DETAILED SPECIFICATIONS
Basic Engine Dry Weight,
Not Including Listed
Accessories
........................ Ibs.
Total Engine
Dry Weight,
With Accessories (subject to
Production Variation of 2.5%) ....... Ibs.
ENGINE MODEL
A B E G J
380.96 409.50 389.58 431.60 380.96
414.93 450.00 395.18 466.50 414.93
·with 15 limp generator 450.00 Ibs.
with 25 amp generator 454.25 Ibs.
K L
404.03 404.03
438.00 438.00
M R S U
409.50 383.06 386.53 388.93
* 401.00 409.56 412.1 I

DETAILED SPECIFICATIONS
ENGINE MODEL
A B E G J K L M R&S
U
Type Certificate Number
273
273 273
273 273
273
273
273 273
273
Number of Cylinders
6 6 6 6 6 6 6 6 6 6
Cylinder Bore (inches)
5.00
5.00
5.00 5.00
5.00 5.00 5.00 5.00 5.00 5.00
Piston Stroke (inches)
4.00 4.00 4.00 4.00
4.00 4.00
4.00 4.00 4.00 4.00
Total Displacement (cubic in.)
471 471 471 471
471
471 471 471 471
471
Compression Ratio
7.0:1 8.0:1 7.0:1 8.0:1 . 7.0:1
7.0:}
7.0:1 8.0:1 7.0:1
8.6:1
Rated Maximum Continuous BHP
225 240 225 240. 225 230
'
230
240 230 230
N
Rated Maximum Continuous RPM 2600
2600 2600 2600 2550 2600
2600
2600
2600 2400
I
""
Rated Take-Off HP
225
240
225 240 225
230 230
240
230
230
Rated Maximum Take-Off RPM 2600
2600 2600 2600 2550 2600 2600 2600 2600
2400
Recommended Cruise RPM
2300 2300 2300 2300 2300
2300 2300 2300
2300 2400
Recommended Cruise Manifold
Pressure (in. Hg.)
23 23 23 23 23 23 23
23 23 23
Minimum Fuel Grade
80 J
100ll
80 J
100ll
. 80 J 80 J
80 J
100ll
80 I
100LL
Oil Pressure (cruise - Ib./sq. in.)
30-60
30-60 30-60
30-60 30-60 30-60 30-60 30-60 30-60 30-60
Oil Pressure Minimum (idling - Ib./sq.in.)
10
10 10 10 10 10
10 10 10 10
Oil Sump Capacity (qts.)
12
12 12
12 .
~ 12
. 12
. 12
12 12 12
Minimum Oil Le\'el for Operation
-- --I
,miCA
ED B LOW MARl< ON D
PSTIC
--
--
Minimum Oil Consumption at Rated
Power & RPM (Ibs. BHP 'hr.)
.018 .015 .018 .015 .018 .012
.012 .012
~ ~
--- ----------_ .. _--- ----
------- --~- ------------

N
I
VI
Minimum Oil. Temperature for Take-Off 0 F.
Maximum Allo\\'iible Oil Temperature
I
Maximum Allowable Cylinder Head
Temperature
Carburetor
Type
A
75°
·225°
450 4
Marvel
Scheb.
MA-4
-5
B E
75° 75°
225° 225°
475 4
450 4
Bendix Bendix
Strom. Strom.
PSD- PSD-
5C 5C
ENGINE MODEL
G J K L M
R&S
U
75° 75° 75° 75° 75° 75° 75°
225° 225° 225° 225° 225° 225° 240°
4604 460 4 460 4 460 4 475 4 460 4 460
Bendix Marvel Marvel
Marvel
Bendix
Marvel Marvel
Strom.
Scheb. Scheb .. Scheb. Strom. Scheb.
Schch.
PSH-
MA-4 MA-4 MA-4 PSD-
MA-4 MA-4
5BD
-5 -5
-5 5C
-5 -5
(float) (float)
I(float) I (float) (float) I(float)
F~el Pressure (psi) 1.5-9 I 9-11 9-11 9-11 0.5-6 I 1.5-9 I 1.5-9 I 9-11 0.5-6 I 0.5-6
Approximate Fuel Consumption
(gal.l hr.)
Firing Order
Ignition Timing
Right Magneto BTC
Left Magneto BTC
Magneto Manufacturer Model No.
Approved Spark Plugs
Valve Rocker Clearance
-- -t-- S~E FUEL CURltE --,---
-l---+- 1-6-3h-5-4 -I---~
26° 24° 26° 24° 20° .22° 2r 24° I 22°
26° 24° 26° 24° 20° 22° 22° 24° 22°
S6RN- S6RN- S6RN- S6RN- S6RN- S6RN- S6RN- S6RN-
25 25 25 25 25 25 25 25
f---+-- SEJ: SER'fICE BtJLLETIN M77\-10 -~--
-1.---4 0.060 t0.200 t--_J-
o 1001.1. rna\' he substituted when XO octane is unavailahle.
o Ahove 75% power .OOH. up to 75% power .000,
G 0-470-S - 240
0
F.
o Indicates temperature measured hy plug-type thcrm()(:oupic in tapped opening at hottom of cylinder head,
o One each SliRN-201 (I.) & SoRN-205 (R): or two SliRN-2S: or two Slick Eil:ctro No. lif>2 (optional per customer spec.).
24°
24°
Slick
662

SECTION III NNNO
ROCEDURE
CA LIT/ON . .. This se("fion pertains to/light operations conducted
under" Standardized Day" conditions. The pilot should thoroughly
familiari::e
himself with the Section on Abnormal Operating
COfl(/iliof1.\'. Whene\'er such abnormal condilions are encoul1lered
or alllicipaled. Ihe procedures
and Techniques/or normal operaTion
should he lailored {[ccordingZI', For example, tithe aircraft is 10 be
Temporarily
operaled ill exTreme cold or hot lI'emller, consideraTion
should be given To all early oil change and/or a rOUTine inspection
sen'icing.
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 is 80 octane for models A. E. J, K,
L, Rand Sand 1001 100lL for models B, G, M, U. A grade offuel
other than that specified should be limited to emergencies only. In
case the grade required is not available, use a higher rating. Never
use a
lower rated fuel. Using higher octane fuels may cause higher
cylinder
temperatures and engine instruments should be closely
monitored, staying within normal limits. (See Section II) ..
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
likel)' 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 airframelpowerplant 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

_~ __ ~ ___ ~~. ~~_~ ____ ~~~ __________ . _______ ~ __________ -- ---~- -O---·~-·---------------I
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.
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 position as soon as the
engine starts.
3-2

CA UT/ON ... Do nol el1RaRe Ihe .\'Iarter when Ihe engine is running
as Ihis lI'ill danlage Ihe :\'tarter, Do nol crankfor/onger than thiN.\'
seconds al a lime. as Ihis
may cause Ihe startermolOr to overheat. If
Ihe ellRine does 1101 Slarl ({Iier Ihirl.\' seconds of cranking. allow a 3
105 lIIinllfe cooling period before allempling to restart.
CAUTION . .. If ellRine kicks hack II'hen slarting. DO NOTallempt
10 Slarl. The ignition .\·Ial'ling system is inoperative and must be
repaired hefore damaging Slarler adapter assembly.
( ('old 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 -(if airframe equipped) 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 engine, 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