Stinson Voyager 150 Operation manual

OWNER'S OPERATING
MANUAL
for
STINSON
VOYAGER 150
1947

FOREWORD
In the Ow ner's OPerating Manual for the Sfinso'n
Voya g f' r 150 a large amount of engineeri ng and re-
se arc h da a h a~ been reduced to an e as ily understood
reference sou rc e th at will c ont ribu te to I ng life
an d econ omi cal op eration of the airplane. The manual
is on e of t wo books available to the owner. The ot her
is the General SC rl l;CC Manllal, whi h is a o nvenicntly
arra nged, au th or itat ive guide t constr uc tion detail s
and maintenan e rcqu ir me nt s for t he airplane . Care-
ful
study of b oth man uals will provide the informati on
needed to keep the Stins on Voyager 150 oper ating
eco
no m ically at top efficie ncy.

TA BLE OF CON TE NTS
Page
CHAPTER I
Design Features ..................................
.. ... ........................................... 1
C
HAPT ER II
Operating Instruc
ci ons .. ....................... ... .................. .... .................... 21
CHAPTER III
Operating Limitations
.. ...... .. ........ .. ...... .. .. ................ .. . ... ................. .. . 33

N <
o
-<
1.
Transmitting
Indicator
>
2.
Radio
C>
3.
Oil
Pressure
Gouge
QI
4.
Oil
Temperature
Gauge
5.
Airspeed
Indicdtor
VI
o
6. Compass
Correction
Card
7. Compass
8.
Altimeter
9
Altimeter
Adjusting
Knob
10
.
Tachomeler
I I. Fuel
Quantity
Gauge
12.
Ammetor
13
.
Gloy,
:
Comportment
I ".
P(II~
i
f'l9
IhCJk~
Canlrol
1,5. Mi
crophon
e Sockel
16
Ma
~
IN
Swilch
11
Po
s
ition
L
ights
Switch
18
.
Landing
Lights Switch
19.
Carburetor
Heat
Control
20
. Fuel
Gauge
Switch
21. File! Tank
Selector
Valve
22.
Throttle
23.
Slarter·lgnition
Switch
24.
Mixture
Control
25.
Cab
in Heat Conl
rol
26.
Operati
ng
Limitations
Placard
27. Rudder
and
Brake Pedals
28. Panel
lights
Dimm
er
29.
Flap
Co
rrt
rol
Handle
30.
En
g
ine
Primer
31. Ash Rece
ptacl
e
.......
---
Figure
1-
Front
of
Ca
bi
n

DESI GN FEA lURES
SURFACE CONTROLS AN D BRAKES
6. Th e ailero ns and elevator are operated by dual control wheels and
shafts.
The full up travel of the elevator is obtained only when the flaps
are lowered. W hen the
fl aps are r ai sed, a stop on the el ev ator push-pull
tube engages tbe lower arm
of tbe fl ap handle ont rol assembly, limit-
ing the elevator up t
1"a1)el co approximately nine degr es less than full
up travel.
7. Th e fl aps are operated by a comrol lever located between the twO
fro nt seats. A three-position locking d ev ic e in the control mechanism
allows the flaps
to be sec in ny one of rhree positions: raised, take-off,
or landing. The fl aps are raised fully when the control lever is in the
posicion neare t
th e BOOL Di sengage the locking dev ice by pressing the
but
tO n on the end of the control lever. Do not fl y at spee ds greater than
88
mph with flaps down.
8. The eleva ro r trim tab is operated by a hand crank located overhead.
Th ere is a tab p osiC ion indicator on the pl aca rd of the crank assembly.
Th is control is prov id ed to correct the airplane for nose heavy or tail
heavy conditio
ns, us ua ll y caused by variations of loadi ng arrangements
or powe
r.
9. The rudder and steerable tail wheel are controlled by both sets of
pedals.
Th e brake ro e- peda ls are attached ro, and extend abo ve, the left
set of
ru dder peda ls. The br akes ca n be set for parking by pulling out
the parking brake control knob while the brakes are de
pr es se d. Th e
br akes ca n be used for curning the airplane while taxiing, but to avoid
exce
ss ive brake wea r, the steerable tail wheel should be used as the
principal means of turning when
on the ground.
FLI GHT INSTRUMENTS
1 0. The altimeter, the airsp ee d indicato r, and the co mpa ss are mounted
on the instrument pane
l. Th e d ia l of the altimeter can be rotated and
set to the proper pressure altitude
by turning the adjusting knob at the
b
ase of the dial.
11. The airspeed indICator
is marked with colured lines and letters to
show the various speed range limitatio ns of the airplane. The green arc
ind
ic ates the normal operating range. Th e white arc, inscribed along-
side the green arc mclicates (he permissib
le speed range with the flaps
dow
n. A ye llow arc mdicates the speed range at which the airp la ne
3

4
VOYAGER 150
7. Ash Rece ptacle
8. Ba gga ge li m itation Placard
9. Do or Ha nd le
10. Door
lo ck
11.
Wind ow Lock
12. Air craft Data File
1. Aileron and Fl ap C ontrols Access
Zipper
2. Dome Light Switch
J. Radio loud-Speaker
4. Trim Tab Control Access Zipper
5. Elevator Trim Tob Control
6.
Cabin Ventil ator
Figure 2-Left Side of Ca bi n
should be operated with caution to av oid abru pt maneuvers. Red radial
lines and letters on the instrument indica
te maximum speeds permis-
sible: "
N" for maximum speed in the normal category (gross weight
between ]925 and 2230
pounds); and " U" for maximum speed in the
utility ategory gross weight 1925 pounds or less).
12. The compass can be adjusted for eviation by turning the com-
pensatjng screws on the face of [he instrument with a non-magnetic
screw driver. T e compensating screws are located at the extreme
tOp

DESIGN FEATURES
of the inst rument and are marked "N -S " and "E- W" to indicate the
ad justment that can be made by tu rning the screws. The compass cor-
rection card is beneath the compas
s.
EN GIN E CON TROLS AND INDIC AT ORS
13. All of the power pla nt co nt rols and indicators, except the oil level
dip stick, are mounted on the control and instrume
nt panels. The control
panel, beneath the main panel, exten
ds the width of the cabin. The oil
level dip stick
is on the right rear side of the engine crankcase, inside
the engine b
afHes.
14. Th e throttle concrol, located in the center of the control panel, is
the push-pull typ e. A knu rled loc ki ng nut adjusts the friction applied
to the push-pull rod and determines the ease with which the throttle
control can be adjusted. By turning the nut clockwise, the throttle con-
trol can
be locked in any positio n. Engine speed is increased by pushing
the throttle control toward the control panel.
15.
The fuel selector valve, mounted on the aft side of the firewall, is
operated by a torque rod and a combination handle and pointer on the
control pane
l. The position of the valve deter min es from wh ich tank
fuel can flow to the
en gine. The valve can be se t to anyone of three
positions:
lef t tank, right t ank , or off. W hen the valve handle is turned
to the off position, all fuel
is sh ut off from the engine at the val ve.
16. The engine primer control kn ob is on the lower edge of the con-
rrol panel, below the throttle control.
To prime the engine, turn the
co nt rol knob counter clockwise; pull the knob out as far as possible,
then push it back to the normal position.
When the primer is not being
us ed, it must be lo cked securely in th e normal position.
17.
The combination starter and ignition switch is mounted on the
co ntt ol panel to the right of the throttle control. A stop incorporated
within th
is swiech prevents the switch from being turned to start posi-
tion unless the button direccly above the handle
is depressed. The switch
is spring loaded and will return to the both magnetos position from the
start positi on when the switch is released. Both magnetos are on with
the switch in start position.
18. The carburetor heat control knob
is mounted on the control panel
to the left
of the fuel selector valve control. As the control knob is pulled
5

6
VOYAGER 150
ouc, an increasing amount of heated air enters the carburetor. When
the control knob is pu lled all the way out, only heated air enters the
carburetor. A mixture of cold and heated air enters the carburetor when
the knob
is set at intermediate points. The carburetor heat control can
be locked in any position to provide any desired mixture of hot and
cold air. The concrol knob m
us t be turned to unlock the push-pull rod
before the control can be
se t at the desired position.
19. Th e primary purpo se of carburetor air heat is to eliminate or pre-
vent carburetor icing. Use carburetor heat during engine warm-up and
1. Ri gh t Po rf Duct
2. Cabin He at Control
3. left Ventila t or
4. Ri gh t Ve ntilator
5. Ve ntilator Air Intake-
6.
Re o'r P ort Duct
7. Heat C ontr ol Valve
8. Fresh Air Intake
9. Heater Muff
10. Hat Air Intoke
Figure 3-Heatlng and Ventilat i ng 5y .te m

DESIGN FE AT URES
during climb whenever there is danger that ice will form in the carbu-
retor. Ice
is most likely to form in the carbure tOr when the outside air
temperature
is between 20 and 68 degrees Fahrenheit. Use heat also
during any prolonged glide or descent. Any time the engine loses speed
without apparent cause, the use of carburetor heat may correct the con-
dition.
Do not use carburetor heat during take-off or landing.
20. The mixture control knob, mounted on the control panel to the
right of the ignition-starrer switc
h, regulates the amount of fuel in the
fuel-air mixture going into the engine.
With the control pushed in, the
mixture
is full rich. Pulli ng the knob out leans the mixture progres-
sively until, at full extension of the control, the idle cut-off stops the flow
of fuel at the carburetor.
21.
When flying at altitudes greater than 3000 feet above sea level,
use mixture control to lean carburetor fuel-air mixture to obtain smooth
engine performance. Stop engine by use of idle cut-off on mixture
control.
22. The t
ac hometer, oil pressure gauge, and oil temperature gauge are
mounted on the instrument pan
el. An ind ic ator that registers accumu-
lated hours
of engine operation, recordi ng one ho ur at 2566 rpm, is an
integral part
of th e tachometer.
23. The oil pressure gauge
is mounted to the rig ht of the left control
wheel.
Th e sa fe operating pressure range for the engine is marked on
this instrument by a green arc with red radial lines at its extremities,
35 psi mini mum and 55 p si maximum. Do not operate the engine at
full throttle when the oil pressure
is outside of these limits.
24. The oil temperature gauge is mounted to the right of the oil pres-
sure gauge.
The normal operating temperature range for the engine is
marked on this instrument by a green arc. The yellow arc indicates the
temperature at which the engine m
ay be operated with caution, and a
red radial line indicates the extreme high temperature of 230 degrees
Fahrenheit that must never
be exceeded. The caution range is from 60
to 80 degrees Fa
ru enheit.
HEAT IN G AND VENTILAT ING
25. Th e cabin heat concrol knob regulates the temperature of the air
ent ering the cabin through three heater po r ts. W ith the control pushed
7

VOYAGER 150
R
7
II
10
16
'ST
36
L.H. TANK
TRANS
~
19
N
LANDING
LIG HTS
G
5
15
FU EL
GAUGE
BATTERY § 12Y
RELAY -
{-
FU EL
R
l~: N~
T RA NS. -=
Figure 4-Electrlcal System D iagram
8

DESIGN FEATURES
in, unheated air enters throLlgh the ports and when the control is pulled
out, heated air
is supplied. The temperature of the incoming air is regu-
lated according to the amount the knob
is pulled out. Outlets for the
front seats are located on the firewall under the instrument panel
on each
side of the cabin. A grilled outlet, located in the cabin floor just behind
the front seats,
is provided for the rear of the cabin. These outlets may
be individually lased to modify the distribution
of air as desired.
26. Additional ventilation
is provided by two ports admitting fresh
air; one at each
up per c rner of the windshield. These vents are opened
by pulling
out the cylindrical tubes. The tube may be rotated to direct
a stream of fresh air in any desired direction.
E LE CT RIC AL SY ST EM
27. A 12-volt battery and engine-driven generator, supply power for
the single wire type electrical system (refer to Figure
2). The battery
and its case are mounted under the left front seat.
The case is vented
and provided with a drain to prevent acid damage to the airplane
or
inj ur y to its occupants. The battery supplies the power to start the en-
gine.
The generator suppli es energy to the electrical system after the
engine
is operating at sufficient speed. Electrical power from the gen-
erator
is fed into the electrical system through a voltage regulator that
maintains constant voltage
in the system. Power from b ot h the battery
an d the generator is supplied to a main bus from which current is
drawn for the various electrical circuits.
28. The master switch co
nt rol is a combination battery relay switch
and generator field switch and must be
on before current is supplied to
the electrical system. W hen the master control switch
is on) the battery
relay closes and allows the
ba tt ery to supply current to the main bus;
it also completes the generator
fiel d circuit that allows the generator to
develop voltage. T he airplane may be operated in flight with the master
control switch off)
but the generator will not charge, nor will any elec-
trical equi
pm em opera te.
29. The electrical system is divided i nt o the following five main cir-
cuits: eng
in e starting, na igarion lights, panel lights, dome light, landing
lights,
fu el ta nk level gauge, and radio. The main bus, from which
power for the vanous
Clf CUHS is taken, is mounted on the forward side
of the co nt rol panel. under the radio. Curre nt for the circuits, except
9

12
J
)
1
VOYA GE R 150
are a transmitter-receiver unit, a loudspeaker, and a microphon~. Two
jac
ks are provided, one for the microphone and the other for head-
phone
s. Headphones are not normally required because of the loud-
speaker installation.
j6 . The airplane is equipped with two antennas, an extern!ll ~ntenn~
that extends from the top of the tabin to the verdcal stabilizer, apd a
fixed loop antenna inside the fuselage, aft of the cabin (ref~r to Fig~
ure 5). Th e loop is perpen<1icular to· the longitudinal axis of the air,.
plape so that homing is accomplished by tuning the null.
37. Transmission may be accomplished at any setting of the radio
contro
ls as long as the radio is operating. The transmitter is activated
NOTE: R iO ht and UIt Tonka en SImIlar
1. Vent
6. Le'ft Wing 'Tank
2. F
ill er Cap 7.
Selector Vaivi l1andl.
3. R ig ht Wing Tank 8. Primer Pump
4. Dr ain Pl ug 9. Fuel
Strainer On Firewall
5. Fuel Stra i ner in Wing Tan k 10. Fuel
Strainer in C arbur.tor 1"I.t
Fi gu re 6-F u el Sys te m
J

DES IGN F EAT URES
Fi gur e 7-0il Filler Cap an d Dip Stick
by pressing the button on the microphone. The pin-point light just
below the radio dial will glow
during transmission to indicate the
strength
of the energy being dispensed. The transmission frequency of
the Skyfone radio set is fixed at 3105 kilocycles by a factory installed
crystal.
The frequency is variable from 2000 to 7000 kilocycles by ex-
changing crystals.
FUEL SYSTEM
38. The fuel supply is in two 20 gallon tanks, one in each wing pa nel;
refer to Figure
6. Use 80 octa ne unleaded aviation fuel. The net usable
fuel capacity of each tank
is 18 gallon s; the rem aining being the non-
us able residual fuel in the tanks, the weight of which is included in the
airplane empty weight. Fuel Bows by gravity fr'om the
wing tanks to the
carburetor and
is drawn from either the right or left tank or shut off
entirely by means
of the fuel selector valve. Fuel for the primer is taken
from the
main fuel line through the strainer attached to the fi rewall.
There are four strainers
in the fu el lines, one at each point where the
fuel lines are connected to the fuel tanks, anOther attached
to the fire-
wall, and a fo
urth where the fuel line is attached to the carburetor. Quick
acting drains are provided
at the low point of each fuel tank so that
tanks may be bled
ro avoid the accumulation of water. The fuel tank
filler necks extend above the
upper surface of the wing: Th e filler caps
have tubular vents that
mu st p oint fo rw ard when the cap is installe d.
13

VOYAGER 150
1. Generator
2. Starter
3. Cabin Heater Valve
4. Voltage Regulator
S. Oil Cooler
39. The fuel gauge is mounted on the instrum e nt panel. By means
of the fuel gauge selector switch, located above the fuel selector valve
control, the level
of fuel in either the left or the ri gh t wing t ank can
be made to register on the fuel gauge. The fu el remaini ng in the tank
when the gauge reads E cannot safely be used in flight.
OIL SYSTEM
40. Eight quarts of oil are carried within the engine crankcase. Use
motor oil of the following viscosity:
Summer (Abo e 40°F.)
SAE 40
Wincer (Above lOoF.)
SAE 30
Winter (Below lOoF.) ShE
20
14
6. Cabin A ir Healer Muff
7. Carbur e tor Air Mixing Box
8.
Carburetor Air Heat Conlr ol
9. Cabin Fres h Air In to ke
10. Parking Broke Control
Figure 8-Left Side of Engine

DESIGN FEATURES
1. C abin He ater Duct 7.
Mixture Co ntro l
2. Gen er a to r 8. C
ar bu re to r
3.
Ri ght M agn eto
9. Thro
ttle Con tro l
-t. Starter
10. Primer Line
5. Engine Shock M
ount
11.
Carburet or Air Heater Muff
6. Fuel St r ain er
Fi gur e 9-Rlght S id e of Engine
A dip-sti k for measuring the quantity of oil in the engine is acces-
sible upon lifting the right engine cowl panel. The stick
is on the top
right side of the engine crankcase, inside the baffles. Never operate the
engine with less than 4 quarts of oil in the crankcase. Oil pressure and
temperature gauges are mounted on the instrument panel (see para-
gr aphs 23 and 24).
EN GI NE A ND ENGINE AC CES SORIES
41. The power plant is an ai r- co le d, six-cylinder, horizontally op-
posed
15 0 ho rs epower Franklin engine. Th e rated maximum contin-
uous engine s
pe ed is 2600 pounds rpm. The propeller ' is mounted
directly on the crankshaft.
15

16
VOYAGER 150
Lock Release
I
I
I
I
Figure 10- Sea' L.ock Relea$e
42. The engine accessories include a starter, a generator, two mag-
netos, a carburetor, a carburetor air filter, an oil cooler, and a carburetor
heater muff. Refer to Figures 8 and
9. The starter is mounted on the
top aft end of the engine crankcase. The magnetos are below and on
each side of the starter, and the generator
is directly below the starter
and magnetos. The carburetor
is attached to the lower aft end of the
engine. The oil cooler and carburetor air
fi lter are mounted ben~ath
the forward end of the engine. The carburetor heater muff is attached
to the right exhaust manifold and the muff for cabin heat is on the left
exhaust manifold.
ACCOMMODATIONS
43. Seats are provided for four persons. The from seats are adjustable
and can
be moved forward or back by releasing a locking device (see
Figure
10). The backs of both front seats fold forward permitting en-
trance to the rear seats.
44. The rear
se ats are the hammock type and are not adjustable. Three
straps support
ea ch of the rear sea ts, and either or both seats can be
removed easily. Each seat is provided with a safety belt. Inasmuch as
the lower cushions are not sec ured, it is recommended that the safety
belts be strapped across the rear seat cushions when these seats are
not occupied.

DESIGN FEATURES
1. Rpar Heater Port
2. Baggage Drape
3. Map Pocket
F igur e ll-Rear of Cabin
45. The entrance doors on each side of the cabin can be locked. Both
doors can be locked from inside the airplane
by turning down a lever
beneath the door hand
le. The left door is provided with a key lock and
can be locked from outside the airplane.
The doors have two-piece
windows, the forward panel of which slides back.
To unlock the win-
dow, depress the small knob below the forward panel.
17

VOYAGER 150
46. Stowage space for small articles is provided by a glove comP tt Ft-I
ment on the instrument panel, and by twO pockets in the upholstery.
One pocket is on the back of the right front seat and another is on the
left side of the cabin just forward of the cabin door. There are ash
receivers
at the side of each seat.
BAGGAGE
47. Provi si on is made beneath the rear seat for baggage. The drape
from the fro
nt edge of the seat is attached to the floor by curtain
fasteners. Unsnapping these fasteners will allow access to this space.
After the baggage is in place, the drape should be lowered and securely
fastened to the floor.
48. Removal of either or both sections of the rear seat will make the
rear of the cabin available for larger baggage
or light cargo. Th e) ()r-
ward tube across the ca bin may also. be removed. To remove either seat
section, lift off the lower seat cushion and unlock the canvas hammqfk
straps.
49. Any combination of baggage, passengers, and
fuel may be carr ~ ~d
that does not exceed anyone of the following limitations. The rear seat I
cannot be occupied during the performance of maneuvers.
(a) Do not exceed 2230 pounds gross weight. See Actual Weight
and Balance sheets for airplane weight empty. . I
(b) . Do not exceed most rearward Center of Gravity posit ien .per-
missible. See Operating Limitations Manual for effect of baggage
on
Center of Gravity position.
(c) Do not exceed 350 pounds on floor in rear of cabin. This is the
maximum load for which the floor structure
is approved. I
50 . Securely fasten all loads. The drape extending from the front of
the seat to the floor has been proven strong enough to retain 100 pounds
of baggage beneath the seat.
Wi th the rear seat removed, the safety
belts and their lugs on the floor may be used to secure baggage
or cargo. I
STATIO N W A GON
51. The Station Wagon loading limitations are the ,same as for the I
standard airplane
as given in paragraph 49, except for the rear of the I
18

DESIGN FEATURES
cabin. Baggage is not to be carried beneath the rear seats at any time.
A maximum load of 90 pounds per square foot, not to exceed a total
of 600 pounds,
is permissible on the floor with the rear seats removed.
52. A sling is provided to secure cargo loads against forward motion.
The straps on each side are attached to the rear outer seat belt lugs, and
the center strap
is attached to the rear ce nter seat belt lug. Position
sling over the up per forward corner of the cargo and draw all buckles
tight. Keep load a minimum of eight inches aft of front seat back.
BAGGAGE COMPARTMENT
53. A separate baggage compartment aft of the cabin is provided 1ll
later airplanes. This compartment is designed to carry 100 pounds and
has a capacity of
13 cubic feet. Baggage placed in this compartment
need not be tied down. This compartment
is accessible through a door
in the right side of the fuselage, aft of the cabin. This door
is provided
with a key lock.
19