BOAC for commercial uses, they were the only flying boats in
service capable of long-range flights during the 1920s and early
The first variation of the Sikorsky S-42 was constructed in
1931 when Russian exile Igor Sikorsky designed a new airplane for
Pan Am. Juan Trippe, president of Pan Am, wanted a plane that
would perform more efficiently for long distance travel. When the
first one was flown to the Anacostia Naval Station in Florida,
Trippe called it the "flagship" of the Pan American fleet.
In its very outline the S-42 represents
simplicity. Diverting sharply from the past Sikorsky designs,
external bracing's have been reduced to a minimum. The tail,
instead of being supported by outriggers, is attached directly to
The one-piece wing with tapering tips is
attached to the hull by means of a superstructure. The necessary
large external struts brace from the hull to the outer portion of
the wing. These struts are the largest streamlined duralumin
sections ever extruded. With a span of II4ft. 2in., the wing has
an area of 1,330 square ft. Spars and compression members, of
modified Warren Truss design, are constructed of extruded
duralumin shapes. Stressed metal skin covers the major portion of
the wing surface. Flush type rivets are used throughout the
Extending along the full straight portion of
the rear spar is the hydraulically controlled flap. The flap is
mechanically operated by means of a substantial hydraulic piston.
The piston is actuated by an electrical pump that is controlled
from the pilot's compartment. For emergency use a manually
operated pump is provided. The angular position of the flap can be
altered in accordance with the attitude of flight, thus changing
the performance of the whole wing. Ailerons of conventional
design, tapering in conformity with the wing plan, are hinged to
the rear spar outboard of the flaps. The power plant units,
consisting of four Pratt and Whitney 700 h.p. geared Hornet
engines, together with the necessary accessories, are attached to
the front spar by means of welded steel tubular nacelles.
Completing these units are the three-bladed variable pitch
propellers, the largest of this type ever produced by the Hamilton
Standard Propeller Company.
The full anti-drag rings and nacelle cowls
merge into the wing at the front spar. Recessed into the leading
edge are powerful landing lights. The lenses of these lights
follow the curvature and form part of the leading edge. Eight
sections of the leading edge, one on either side of each engine,
fold down and form engine servicing platforms. Along the interior
of the leading edge run the control cables, electrical conduits
and other control and fuel units. All installations are made
suitable for easy inspection and maintenance. Cradled between the
spars and compression members are eight elliptical fuel tanks of a
total capacity of 1,240 gallons and four similar shaped oil tanks
of 74 gallons capacity. Holding these in place are metal straps
which are covered with thick padding to insure vibration
Removable panels, above the fuel and oil tanks, and on
the entire center of the lower surface afford access for inspection and
servicing. The re-fueling system in the center portion of the wing is an
interesting timesaving device. A single intake pipe directs fuel under
pressure to any one or all tanks by means of a series of control valves.
Equal in importance with the wing are the parts that make up the body
group. The two-step, long stern type hull measures 67ft. 8in,. from bow to
stern. Deep keel, transverse frames which are widely spaced in order to
facilitate maintenance, and heavy stringers form the hull skeleton. Keel
and frames are of plate girder type. Duralumin shapes and sheeting are
The skin covering has the appearance of a smooth
unbroken surface. This has been obtained by the use of a filler in the
skin seams and the impressions of the slightly indented flush type rivets.
Nine watertight doors separate the various compartments.
Marine equipment is located in the bow compartment.
This compartment has been designed especially large to afford easy
handling of a convenient anchor winch and to facilitate rapid mooring
The pilot's compartment following averages eight feet
wide and seven feet from bulkhead to bulkhead.
An aisle 20 inches wide separates the pilot and copilot
seats. These seats are extra roomy and are adjustable. They are designed
to supply the maximum of comfort for long flights.
Both pilots have an unobstructed view of the complete
flight instrument board. Special requirements as to making all instruments
and parts readily removable for checking and servicing have been rigidly
To the rear of the pilot's seat is located the flight
mechanic's quarters. From his position the mechanic can readily attend to
all the details under his control. Grouped on a separate panel directly in
front of the mechanic's seat. are all the instruments pertaining to power
Opposite the mechanic's quarters and in an uncrowded
space is the radio receiving and sending station.
Surface controls are of the dual type featuring ease of
operation. Controls are hooked up to the automatic pilot unit located
beneath the floor. Dials and instruments for setting and regulating the
automatic pilot are on the center of the flight instrument board within
easy reach of either pilot.
Engine control units are centered overhead, comfortably
reached by either pilot and the mechanic. It affords either unit control
for all engines, or selective control for each engine.
Next to this unit are the engine fire extinguisher
controls. A twist of a dial directs extinguishing gas to one or all
Reached from the outside by a hatch large enough to
accommodate large packages as well as permitting for passenger exit, and
located between the pilot's compartment and passenger cabins is the front
baggage compartment. The allowable baggage space is 157 cubic feet. Here
are also stored two life rafts and various tools. A strong box for
valuables is located under the floor.
At the main passenger stairway in the rear are located
additional baggage compartments with a total capacity of 95 cubic feet.
Large packages find ready access through the main passenger entrance that
measures 25 inches by 72 inches.
Between the front and rear baggage compartments are
located the passenger cabins and the lavatories.
The four passenger cabins, measuring 76 inches by 110
inches each, seat eight passengers. More than sufficient space is allowed
for wide aisles and comfortable leg room. The distance from the floor to
the ceiling is well over six feet.
Tubular racks suspended from the bulkheads support the
seats. This construction eliminates chair legs, thus permitting an
unobstructed space beneath each seat for luggage.
Seats are adjustable to meet individual comfort. High
head rests afford complete relaxation. Accessories, including- carpets,
removable tables, magazine racks, and curtains, harmonize with the
Sound and vibration have been the subjects of careful
study. Thick pads of soundproofing material fill in the space behind the
walls and ceiling. Because of their vibration, springs have been replaced
in cushions by a special material that is proving more serviceable and
comfortable. Windows are held in place by a clincher type rubber ring
without the need of fasteners that would cause shattering. In any
passenger cabin conversation may be carried on in a normal tone.
A concealed ventilating system supplies upwards of 30
cubic feet of air per passenger per minute. Auxiliary to this is an
efficient exhaust system.
Installation fittings on walls, ceiling, floors, and
seats are such that an entire passenger cabin can be stripped to its bare
structure within 40 to 50 minutes and reinstalled in a similar period.
Each cabin is equipped with safety belts and lifebelts
are distributed throughout the boat; in convenient locations are fire and
emergency equipment. The two -life rafts in the front baggag6 compartment
and the two located rearward of the main stairway are, suitable for,
carrying a full capacity crew and passenger list.
The superstructure, already mentioned, also serves as a
passage-way for items of controls that pass from hull to wing. Entrance is
afforded to this structure from the inside of the cabin as well as from
the outside. The internal space of this structure is such as to allow a
man to work with comfort.
Every external part of the hull may be reached by a
center ridge walk-way that extends from bow to stern. This walk-way,
together with the wing walkways and the engine platforms, makes it
possible to conduct almost any inspection or servicing operation, without
the need of outside scaffolding. The economic feature of this is obvious.
Pontoons, hinged from the wing on two streamline struts
and braced by cross wires, follow similar construction design as the hull.
Easy handling from sea to land, or vice versa, is
offered by the beaching gear. This is a three-part unit consisting of two
twin-wheels-on-a-strut carriages that attach to special fittings on the
front of the hull and a single tail wheel that fits into a socket at the
stern of the hull. All carriages may be turned on their axes so that
motion is possible in any direction. Seven to ten minutes is required to
attach or detach the entire gear.
Even more important than the structural characteristics
of the S-42 is its performance. Reports on performances were handed in by
three of the outstanding pilots in the aviation world-Captain Boris
Sergievsky, holder of numerous world records and chief test pilot for the
Sikorsky Aviation Corporation; Mr. Edwin Musick, chief pilot for the
Pan-American Airways, and an airman of outstanding experience and ability;
and the final stamp of approval by Colonel Charles A. Lindbergh.
Thirty-two flights on an average of over two hours each filled in the five
months' period of performance testing.
The final accepted report shows the performance as:
Gross weight ...................38,000lbs.
Full speed at 5,oooft. altitude .......188 m.p.h.
Full speed at sea level .......180 M.P. 11.
Speed at 75 per cent. b.h.p. at sea level .......160
Speed at 70 per cent. b.h.p. at 1 2, 000ft ..altitude
Climb, initial, four engines .......1,000 f.p.m.
Climb, initial, three engines ........400 f.p.m.
Ceiling, service, three engines .......7,500ft.
Full speed at sea level, three engines ........157
Speed at 75 per cent. b.h.p., sea level, three
Stalling speed .........65 m.p.h.
Time of take-off, dead
Ceiling, service, four engines .........16,000 ft.
Range at cruising speed, sea level .........1,200 miles
Range with pay load of i,5oolbs. (cruising speed
I45 m.p.h. at 6,oooft. altitude) .........3,000 miles
During the test flights the following world records for
Class C-2 seaplanes
were established :-
For a distance of 1,000 km. (621.4 mi-)-,
Speed 253.7 km./hr (157-7 mi./hr.).
Speed with 500 kg. (1,102.3lbs.) 253.7 km./hr (157.7
Speed with 1,000 kg. (2,204.6lbs.) 253.7 km./hr (157.7
Speed with 2,000 kg. (4,409.2lbs.) 253.7 km./hr (157.7
For a distance Of 2,000 km. (1,248.8 mi.).
Speed ..253.4 km./hr. (157.5 mi./hr.).
Speed with 500 kg. (1,1O2-3lbs.) 253.4 km./hr. (157.5
Speed with 1,000 kg. (2,204.6lbs.) ..253.4 km-/hr.
Speed with 2,000 kg. (4,409.2lbs.) ..253.4 km./hr.
Greatest load to 2,000 M. (6,561.6ft.) 7,533 kg.
Altitude with 5,000 kg. (11,023lbs.) 6,203.6 M.
In no way, however, has high performance reduced the
practical purposes of this boat. the weight ratio of useful load to gross
weight is very satisfactory. With a weight empty of 19,764lbs. and a
licensed gross weight of 38,000lbs.. a useful load of 18,236lbs. is
obtained. This ratio is then in the nature of 48:52, or the useful load
equals 48 per cent. of the gross weight.
The weight allocations for a gross weight of 38,000lbs.
and a range of 1,200 miles fit commercial requirements. The fuel and oil
for this range weigh 7,995lbs. ; equipment weighs 2, 181lbs., and pay load
equals 7,060lbs. Should consideration be given to using the S-42 for fast
freight only, practically all the 2,181lbs. of equipment, plus the chairs,
wall and ceiling trim and sound-proofing, can be dispensed with, giving a
pay load of approximately 10,000lbs. over a range Of 1,200 miles. For a
range Of 3,000 miles, cruising at I45 miles per hour and at 6,000 feet
altitude, the allowable pay load will be 1,500lbs. Thus the S-42, keeping
well within the safe limitations of structural strength, capable of
maintaining a high ceiling with only three motors, and at the same time
carrying a reasonable pay load, is entirely suitable for the establishment
of trans-oceanic routes.
The following table indicates the benefits of the S-42
as compared to the S-40:-
Gas and oil (1,000 miles)
Cruising speed (1,000ft.),m. p. h.
High speed, m.p.h.
Landing speed, m.p.h.
Here is an indicated increase in the S-42 Of 5,163lbs.
pay load over the S-40.
If equal pay loads are considered, that is, 7,500lbs.,
the range for the S-40 is 479 miles and in the S-42 is 1,130 miles, an
increase of 651 miles.
The extensive test made with the S-42 made it possible
to make some interesting comparative measurements. With the engines of the
S-42 throttled down to 575 b.h.p. to conform with the b.h.p. of the S-40's
Hornet " B " engines, the speed obtained was 163 m.p.h. as against 137
m.p.h. obtained from the S-40.
The improvement in efficiency of the S-42 is better
exemplified if a study is made of the cruising speed of the S-42 against
the S-40, using equal horsepower in each case. Using 432 b.h.p. per motor,
the S-40 cruises at 115 m.p.h., while with the same power and an increased
gross weight of 4,000lbs. the S-42 cruises at 145 m.p.h., an increase of
From an economic viewpoint, that is, comparing load
carried against fuel consumed, an important deviation is found. Each plane
using the same horsepower and the fuel consumption per hour of the S-42
being 144 gallons, and that of the S-40 140 gallons, the following
ton-mile gallon is given:-
Payload in Tons
Miles per gallon (1,000 Miles) Ton mile per gallon.
S-40 0.82 3300/2000=1.65 1.35
S-42 1.0 8505/2000=4.25 4.25
In view of the fact that operating and maintenance
costs are based on flying hours, consideration is here given to that item.
Equal in size, the S-40 is again taken for our analysis. The unit of
maintenance and operating costs per hour being considered equal, we find
that for each flying hour the S-40 is credited with (1.65 tons x 115 mi.)
169.75 ton-miles, and the S-42 (4.25 tons x 145 mi.) 616.25 ton-miles.
It is quite clear that, in this consideration of pay
load ton-miles that operation and maintenance cost vs. load carried would
be decreased in the same proportion. In reality, the decrease will be
substantially greater because of the refinement for fast and simplified
inspection, servicing, and maintenance incorporated by the Sikorsky
engineers in conjunction with the staff of the Pan American Airways.
Because of the general cleanliness of the S-42, due to
the careful study of the aerodynamic interference of parts, the total
parasite resistance at cruising speed of 160 m.p.h. is only 3,620lbs. At
the time of designing, careful consideration was given to the cantilever
wing, but it was felt that the increase in profile resistance, due to the
greater thickness of the center section of the wing, would be greater than
the drag of external struts. Research also revealed that the structural
weight of the cantilever wing would be greater than the present wing and
The table attached gives the curves of the original
estimated performance compared with data measured during test flights. It
should be noted that actual performance is in general accord with the
figures estimated by the more liberal simplified method in which the
profile drag of the wing and the resistance of engines are taken as having
a constant value subject to the square of speed. It is believed that the
slight excess of actual performance over the original estimate is due
partly to greater scale speed effect other than the one that was
considered, and partly due to the smooth surface created by flush
riveting. It is evident that the ship with full load is able to maintain
flight easily, using much less than half the power available. It is shown
further that the best LID ratio of the whole aeroplane is above thirteen.
The data on which the table is based were recorded during test flights
with calibrated intake manifold pressure gauges mounted on all engines.
The reading of these instruments, plus careful observation of the r.p.m.,
permitted the accurate establishment of the power used at various
conditions of speed and load.
After a careful study of the conditions under which
this ship would operate, it was decided to have a high wing loading. The
ship was designed primarily for high cruising speed and operation over
long trans-oceanic routes. A service of this character offers no
intermediate landing possibilities, and in view of the distances and
duration of flight, the ship must be able to withstand varying weather
conditions. Good airworthiness in stormy weather was considered most
essential. A simple aerodynamic study shows that the action of a squall or
of a vertical air gust becomes more violent as the wing loading decreases.
Therefore, a heavy wing loading of 28-5lbs., combined with ample h.p. per
square foot of 2.1 b.h.p., was found desirable.
Flight tests confirmed this decision. The S-42 flies
easily and smoothly in the roughest of weather. The comparatively small
and rigid wing has the added advantage of safely weathering strong wind
and heavy squalls while afloat, particularly with the flap in neutral
position. Added approval of this consideration is given by nature. It is
interesting to note that large birds that fly over the sea, having long
distances to traverse before being able to alight in case of stormy
weather, have a much heavier wing loading than birds of similar size that
fly over land.
The disadvantages of heavy wing loading, namely,
difficult take-off and fast landing, were avoided by the use of the
specially designed flap. After a very careful wind tunnel study of several
types of auxiliary surfaces, preference was given to the straight flap
that now fills up the rear of the wing between the ailerons.
This flap produces an increase in lift of about 40 per
cent. When placed at a 4o degree angle, the flap affords an actual
stalling and landing speed of 65 m.p.h.
Test showed that the best position for take-off is with
the flap set at + 10° to + 12°. Carrying a definite test load, the ship
with the flap in neutral position took 12 seconds for take-off. Landing
immediately, the flap was set at + 10° and the take-off time was reduced
from 12 seconds to 7 seconds, indicating that the flap decreased take-off
time by nearly 40 per cent.