Like they Say
Read the frigging Dash One FIRST
Directional control on the ground is a challenge. The vertical stabilizer is a huge flat thing sticking twelve feet into the air. The tail wheel swivels. The brakes fade when they get hot. A quartering tailwind while taxiing on a narrow taxiway has embarrassed the best of us. Directional control on takeoff and landing is simplified by a locking tailwheel. Fear not, should you forget to lock it, you’ll know within seconds of advancing the power. Land with it unlocked and you stand a good chance of producing a 3,000 pound lump of crumpled sheet aluminum.
Are we having FUN yet ???
DEPARTMENT OF TRANSPORTATION
FEDERAL AVIATION ADMINISTRATION
A6EA
Revision 2
STOL
(United Consultants)
(Twin-Bee) UC-1
September 13, 1969
TYPE CERTIFICATE DATA SHEET NO. A6EA
This data sheet, which is a part of Type Certificate No. A6EA prescribes conditions and limitations under which the product for
which the Type Certificate was issued meets the Airworthiness requirements of the Civil Air
Regulations.
Type Certificate Holder: STOL Aircraft Corporation
P. O. Box 175
Norwood Airport
Norwood, Massachusetts 02062
I - Model UC-1 5 PCAM (Normal) Approved June 25, 1965
Engine 2 Lycoming IO-360-B1D
Fuel 100/130 Minimum grade aviation gasoline
Engine limits For all operations, 2700 r.p.m. (180 h.p.)
Propeller and 2 Hartzell HC-C2YK-2RB/7666A-2
propeller limits Diameter: not over 74", not under 72";
no further reduction permitted
Pitch setting at 30 in. station:
Low: 14.0
°Feathered: 79.3
°Placard: Avoid continuous operation between 2000 and 2250 r.p.m.
Airspeed limits (CAS) Maneuvering: Vp 131 m.p.h. (114 kt)
Maximum Structural Cruising: Vno 132 m.p.h. (115 kt)
Never exceed: Vne 166 m.p.h. (144 kt)
Flap Extended: Vfe 105 m.p.h. ( 91 kt)
C.G. range
109.9 115.2 119.8
3800
3383
110.6 118.6
3098
3708
B
C D
118.7
A F E
LANDPLANE
SEAPLANE
CG. Position - Inches Aft of Datum (Gear Extended)
Gear retraction moment 2900 in.-lb.
Aircraft
Weight
Lb.
Landplane Operation:
PTS. A-B-D-E-A
Seaplane Operation
PTS. F-C-D-E-F
6A1 2
Empty weight C.G. range None
Datum Longitudinal reference station 0 located 97.50 inches forward of
leading edge of wing. Horizontal reference is located 50.00 inches below
and parallel to Category the hull deck (W.L.0.00)
Level means Lugs on front and rear left-hand, and rear right-hand door frames
Maximum weight 3800 lb.
Minimum crew 1 (Pilot)
No. of seats 5 (2 at +62.0", 2 at +96.0", 1 at +127.0")
Maximum baggage 300 lb. (200 lb. at +118.0", 100 lb. at +147.0")
Fuel capacity Main Tank: 85 gallons at 116.0"
(unusable - 1.5 gallons)
Auxiliary Tank: 16 gallons at 299.5"
Oil capacity 2 gallons per engine at 101.9" (usable - 1.5 gallons). See Note 1 for system oil.
Control surface movements Wing Flaps Up 0
° Down 30°(Max.) Aileron Up 20
° Down 20°Rudder Right 30
° Left 30°Rudder trim tab Right 17 1/2
° Left 33°Elevator Up 25
° Down 25°Elevator trim tab Up 37
° Down 27°Serial Nos. eligible 1 and up
Certification basis CAR 3 dated May 15, 1956, plus Amendments 3-1 through 3-8, plus CAR 4b.356
(except for the requirement enabling the main cabin door to be opened from the
outside). Date of Application for Type Certificate February 2, 1963.
Production basis None. Prior to original certification of each aircraft an FAA representative must
perform a detailed inspection for workmanship, materials, and conformity with the
approved technical data, and a check of the flight characteristics.
Determine that all unmodified parts (parts built under the original Republic RC-3
Type Certificate No. 769) are in an airworthy and unaltered condition.
This determination may be accomplished by means of an examination of the
aircraft records, and to the extent possible, a visual inspection of the aircraft original
parts. Particular attention should be given to the following areas:
(1) The rudder spar at each of the rudder-fin hinges
(2) Both main landing gear (especially the actuating tube at the weld)
(3) The elevator torque tube fittings
(4) The hull fuel cells (for evidence of deterioration)
Any Republic Model RC-3 parts which may have been altered must be substantiated
by the applicant to the controlling region of the Republic Model RC-3 aircraft.
For information concerning the United Consultants Model UC-1 modification contact
the controlling region of the United Consultants Model UC-1 aircraft.
3 6A1
Equipment The basic required equipment as prescribed in the applicable airworthiness
regulations (see Certification Basis) must be installed in the aircraft for certification.
In addition, the following items of equipment are required:
(a) FAA approved Airplane Flight Manual
NOTE 1. Current weight and balance report including list of equipment included in certificated
empty weight, and loading instructions when necessary, must be provided for each
aircraft at the time of original certification. The certificated empty weight and
corresponding center of gravity location must include unusable fuel (included in main
tank capacity) of 9 lb. at (+116.0") and system oil (not included in oil capacity) of 4 lb.
at (+101.9")
NOTE 2. All placards required in the FAA approved airplane flight manual must be installed
in the appropriate locations.
NOTE 3. Airworthiness Directive 53-23-3 must be compiled with for original certification and at
the repetitive intervals as stated in the Airworthiness Directive.
...END...