USA: AIRCRAFT-VOLPAR

• Document Type: CREST
• Collection: General CIA Records
• Document Number (FOIA) /ESDN (CREST): CIA-RDP80B01495R001200120004-5
• Release Decision: RIPPUB
• Original Classification: K
• Document Page Count: 2
• Document Creation Date: December 19, 2016
• Document Release Date: October 26, 2005
• Sequence Number: 4
• Content Type: OPEN

Approved For Release 2005/11/23 : CIA-RDP80BO1495R001200120004-5
479, USA: AIRCRAFT-VOLPAR
Volpar Turbo 18, a conversion of the Beechcraft Model 18 with AiResearch TPE 331 turboprops and Volpar Mk IV tricycle landing gear
position -indicator. Existing airstair doors can
be retained with only minor modification.
Basically, the modification moves the main
landing gear 4 it 0 in (1-22 m) aft of the original
position, attaching it to a welded tube truss that
increases the torsional strength of the centre wing
structure by 60% in landing configuration. The
nose assembly is completely new and includes a
streamlined nose fairing which adds 2 ft 2} in
(0-67 in) to the fuselage.length. Space inside the
fairing can be used for additional equipment,
including a weather radar dish of up to 12 in
(30 cm) diameter.
All three wheels are of aluminium and can be
fitted with either Goodrich or Goodyear tubed or
tubeless tyros, size 8.50-10, ten-ply rating.
Main-wheel tyre pressure 65 lb/sq in (4.67 kg/cm'),
nosewheel tyre pressure 46 lb/sq in (3.16 kg/cm').
Shock-absorption is provided by hydraulic oleo
struts of Volpar manufacture. Goodrich multiple
disc brakes. All three wheels retract forward in
less than eight seconds. On the.ground the cabin
floor is only 3 ft 6 in (1.07 m) off the ground at the
door. Wheelbase is 8 ft 7 in (2.62 m). The aircraft
will turn on a 4 it (1.22 in) radius of the inside
wheel and a centering device is incorporated on
the Shimmy damper for take-off and landing.
- The current Mk IV Volpar conversion incorpor-
ates Goodrich nine-piston full-circle brakes with
twice the braking energy and - three times the
service life of the two-piston type fitted formerly.
Thenow brakes fit on the original gear and are
obtainable from either Volpar or Goodrich.
A total of more than 400 sets of Volpar tri-gear
have been delivered.
VOLPAR (BEECHCRAFT) TURBO 18
The Turbo 18 is a Beechcraft Model 18 fitted -
with the Volpar Mk IV tricycle landing gear
described above and re-engined with two 705 Shp
AiResearch TPE 331-1-101B turboprop engines,
flat fated to 605 Blip. The wing planform is
charmed, by extending forward the entire leading.
edge inboard of each engine nacelle and carrying
the new leading edge line past the nacelle, so
increasing the chord and ewoepback to a point
some distance outboard of the nacelle. - The
rectangular: wingtip panels of the standard Super
18 are replaced by smaller tips which decrease the
wing span and maintain the normal leading-edge
sweep to the tip. -
Inetallation of 11PE 331 eng ea and Hartzell
Model HC-$3TN-5 three-blade reversible-pitch
capacity is increased by 100 US gallons (379 litres)
by installing new integral tanks in the leading-
edge immediately outboard of each engine nacelle.
These become the main tanks; each delivering fuel
directly to the adjacent engine. They increase
the maximum fuel capacity to 630 US gallons
(2,385 litres), with a normal capacity of 306 US
gallons (1,159 litres). -
Air-conditioning and heating installations are
available, using engine bleed air. A large cargo
door, 5 ft 2 in (1.57 m) wide, with a max height of
3 it 7 in (1-09 m), can he provided, incorporating
the existing airstair door.
The detailed description of the Turboliner
(which follows), applies also to the Turbo 18,
except that this latter model does not have the
"stretched" fuselage. - - -
FAA Supplemental Type Approval of the Turbo
18 was received on 17 February 1966. Two were
in service with the US Public Health Service at the
end of that month and conversion kite are in full
production. Customers include Air Asia of
Taiwan, which has boon supplied with 15 kits.
DIMENSIONS, EXTERNAL:
Wing span
Length overall
Height overall
Wheelbase
DIMENSIONS, INTERNAL:
46ft0in (14.02m)
37ftSin(11.40m)
9 ft 7 in (2.92 in)
8 It 7 in (2.62 m)
Length
Max width
Max height
Volume
WEIGHTS AND LOADINGS:
Weight empty, basic
Max payload -
Max T-O weight
,
.
g)
Max zero-fuel weight 9,000 lb (4,082 kg)
Max landing weight 9,772 lb (4,433 kkgg)
Max wing loading 27.61 Ib/sq ft(134.3 kg/nd
Max power loading 8.94 lb/ehp (4.05 k
h
)
g/c
p
PERFORMANCE (at max T-O weight): M
i
i
ax cru
s
ng speed at 10,000 It (3,050 m)
243 knots (280 mph; 451 km/h)
Econ cruising speed at 10,000 it (3,050 m) -
222 knots Stalling speed, wheels and (256
flaps mph; 412
power ffh)
0 Stalling speed, wheels akno ndsfi flaps down, p48 ower km/h)
78
knots (88 mph; (142 13:m/h)
Max rate of climb at 8/1, 1,710 ft (521 rri)Jmin
Service ceiling
T-O run 1,665 it (507 in)
T-O to 50 ft (15 in) 2,380 ft (725 m)
Landing from 50 ft (15 m) 2,107 ft (642 in)
Landing run with reverse thrust 870 ft (265 m)
Range with max fuel at 222 knots (256 mph;
412 km/h), 45 min reserve
1,884 nm (2,170 miles; 3,492 km)
Range with max payload, 45 min reserve
400 nm (461 miles; 741 km)
VOLPAR (BEECHCRAFT) TURBOLINER
This is a "stretched" 15-passenger version of
the Volpar (Beechcraft) Turbo 18, intended
for the third-level airline market. Design was
started in August 1966 and construction of the
prototype began in- December 1966. The
prototype flew for the first time on 12 April 1967
and FAA certification was granted on 29 March
1968, the Turboliner being approved for operation
at a new gross weight of 11,500 lb (5,216 kg).
By the end of February 1974 a total of 24 Turbo.
liners had been-tlolivored and were in service with
small airlines throughout the world. In March
1970 a Turboliner (N353V), on a delivery flight
from Los Angeles to Singapore, set six official
international speed records. It carried on board
during the flight all necessary spares. for one
year's normal operation, together with a 400 US
gallon (1,615 litre) ferry tank in the fuselage, -
and was in operation with a commuter airline
two days after arrival in Singapore. .
TYPE: Twin-turboprop light transport aircraft.
WINGS: Cantilever lowikving monoplane. Winmgg
section NACA..63-016 at station 28.0, NACA
23014 at station 144.5, NACA 23012 at station
260-4. Dihedral 6?. Incidence-5? 20' at root,
1? at tip. Sweepback 16? 21' on inner wings.;
8?23' on outer panels.. Steel truss centre
and plain trailing-edge flaps of conventional
aluminium construction. Trim tab in pore -
aileron. Optional Goodrich pneumatic do-icing
boots on leading-edges.
FUSELAGE: Conventional aluminium semi-mono-
coque structure.
TAIL UNIT: Cantilever aluminium Semi-mono-
coque structure with twin endplate fins and
ru dders. Fixed-incidence tailplane. Trim
tabs in rudder and elevators. Optional
Goodrich pneumatic de-icing boots on leading-
: 1/23 : CA1QOLR?It 81495 i QAg ' n t%"" d 1'e
12ft 8}in (3-87 m)
4ft4in(1.32m)
5 it 6 ih (1.08m)
260ouR(7.36ru')
4,780 lb (2,171 kg)
10
286 lb (4
666 k
 Approved For Release 2005/11/23 : CIA-RDP80BO1495R001200120004-5
Approved For Release 2005/11/23 : CIA-RDP80BO1495R001200120004-5