# TCDS 6A6: Kelowna Flightcraft R & D Ltd.

- Type: Type certificate data sheet
- Status: Current
- Holder: Kelowna Flightcraft R & D Ltd.
- Revision: 12
- Revised: January 1, 2001
- Product: Aircraft, Large Airplane
- Certification basis: Part 1, Part 91, CAR 4b
- Registered aircraft: 12, by the registry models matched to it (OpenAirDocs)
- Data sheet PDF: https://openairdocs.org/files/sha256/2b/2d/2b2dbee22cabc62509685347f52ef1e83eb4754805b45a03a0d0f45015400a86
- FAA DRS: https://drs.faa.gov/browse/excelExternalWindow/86284B968DA5453386256AF800675521.0001
- Page: https://openairdocs.org/tcds/6A6

## Models (6)

As the data sheet lists them.

- Military C-131F/R4Y-1
- Military C-131B
- 340 (STC 580/640; Allison Conversion)
- Military C-131E
- Military C-131D
- 440 (STC 580/640; Allison Conversion)

## What the data sheet says

From the PDF's text layer, line by line; tables lose their columns. The PDF is the record.

```text
P a g e  N o . 1234567891 0 1 1 1 2 1 3 1 4 1 5 1 6 1 7 1 8 1 9 2 0 2 1
R e v .  N o . 1 21 11 11 11 11 11 11 11 11 21 11 11 11 11 11 11 11 11 11 11 1
P a g e  N o . 2 22 32 4
R e v .  N o . 1 11 11 1
DEPARTMENT OF TRANSPORTATION
FEDERAL AVATION ADMINISTRATION
6A6
Revision 12
Tracor (Convair)
340
440
Military C-131B
Military C-131D
Military C-131E
Military C-131F/R4Y-1
January 1, 2001
Aircraft Specification 6A6
Manufacturer Kelowna Flightcraft R & D Ltd.
#1 5855 Kelowna Airport
Kelowna, BC, Canada V1V 1S1
I - Model 340 Approved March 27, 1952
The Model 340 airplane is basically similar for all dash numbers, the only differences being in the type of equipment and
interiors for the customer's airplane.
Engines 2 P&W Double Wasp CB3, CB4, CB16, CB17 or Military R-2800-83AM7 (See NOTE 8
and 12)
Fuel 100/130 grade aviation gasoline (CB3 and CB16)
108/135 grade aviation gasoline (CB4, CB17 and R-2800-83AM7)
Engine Limits
HP. R.P.M.
M.P.
In. Hg. Alt.
P&W Double Wasp CB3
     Takeoff (two minutes) (dry) 2050 2700* 55.0 S.L.
     Takeoff (two minutes) (dry) 2050 2700* 53.0 6900'
     Takeoff (two minutes) (dry) 1950 2800* 53.0 S.L.
     Takeoff (two minutes) (dry) 1950 2800* 51.0 9800'
   *(See NOTE 3 for limitations)
     Takeoff (two minutes) (wet) 2400 2800 59.5 S.L.
     Takeoff (two minutes) (wet) 2400 2800 59.0 5000'
      (See Item 103(a) for ADI installation
      and Engine Specification E-264 for
      ADI fluid composition)
     Maximum continuous 1800 2600 48.5 S.L.
     Maximum continuous 1800 2600 46.5 9200'
(Straight line manifold pressure variation with altitude shown)
P&W Double Wasp CB16
  Low impeller gear ratio 7.29:1
     Takeoff (two minutes) (dry) 2050 2700* 55.0 S.L.
     Takeoff (two minutes) (dry) 2050 2700* 53.0 6900'
     Takeoff (two minutes) (dry) 1950 2800* 53.0 S.L.
     Takeoff (two minutes) (dry) 1950 2800* 51.0 9800'
   *(See NOTE 3 for limitations)

6A6
Page 2 of 24
Engine Limits (Cont'd)
HP. R.P.M.
M.P.
In. Hg. Alt.
P&W Double Wasp CB16 (Cont'd)
     Takeoff (two minutes) (wet) 2400 2800 59.5 S.L.
     Takeoff (two minutes) (wet) 2400 2800 59.0 5000'
      (See Item 103(a) for ADI installation
      and Engine Specification E-264 for
      ADI fluid composition)
     Maximum continuous 1800 2600 48.5 S.L.
     Maximum continuous 1800 2600 46.5 9200'
  High impeller gear ratio 8.58:1
     Maximum continuous 1700 2600 48.5 10,000'
     Maximum continuous 1700 2600 47.5 16,800'
(Straight line manifold pressure variation with altitude shown)
P&W Double Wasp CB4
     Takeoff (two minutes) (dry) 2200 2800* 60.0 S.L.
     Takeoff (two minutes) (dry) 2200 2800* 59.0 5200'
   *(See NOTE 3 for limitations)
     Takeoff (two minutes) (wet) 2500 2800 62.0 S.L.
     Takeoff (two minutes) (wet) 2500 2800 61.5 3700'
      (See Item 103(a) for ADI installation
      and Engine Specification E-264 for
      ADI fluid composition)
     Maximum continuous 1900 2600 51.5 S.L.
     Maximum continuous 1900 2600 50.0 7100'
(Straight line manifold pressure variation with altitude shown)
P&W Double Wasp CB17 and
Military R-2800-83AM7
  Low impeller gear ratio 7.29:1
     Takeoff (two minutes) (dry) 2200 2800* 60.0 S.L.
     Takeoff (two minutes) (dry) 2200 2800* 59.0 5200'
   *(See NOTE 3 for limitations)
     Takeoff (two minutes) (wet) 2500 2800 62.0 S.L.
     Takeoff (two minutes) (wet) 2500 2800 61.5 3700'
      (See Item 103(a) for ADI installation
      and Engine Specification E-264 for
      ADI fluid composition)
     Maximum continuous 1900 2600 51.5 S.L.
     Maximum continuous 1900 2600 50.0 7100'
  High impeller gear ratio 8.58:1
     Maximum continuous 1750 2600 51.5 10,000'
     Maximum continuous 1750 2600 49.5 15,000'
(Straight line manifold pressure variation with altitude shown)
Airspeed Limits V NO (Normal Operating) 260 knots True Ind. S.L. to 10,000'
VNE (Never Exceed) 293 knots True Ind. S.L. to 10,000'
(Above altitudes shown, reduce speed 6 knots per 1000')
VA (Maneuvering) 154 knots True Ind.
VFE (Flaps Down 0° to 20°) 174 knots True Ind.
VFE (Flaps Down 20° to 30°) 156 knots True Ind.

6A6, Rev. 11
Page 3 of 24
Airspeed Limits (Cont'd) V FE (Flaps Down 30° to 40°) 148 knots True Ind.
VLE (Landing Gear Extended) 174 knots True Ind.
VLO (Landing Gear Operation) (Retraction) 130 knots True Ind.
VLO (Landing Gear Operation) (Extension) 174 knots True Ind.
C.G. Range See NOTE 1(b) for retraction moment.
Forward Aft
Gross Weight (lbs.) Landing Gear Position
%
MAC Sta.
%
MAC Sta.
39,500 and Below Down (Takeoff & Landing) 13.0 365.8 34.0 389.8
43,000 Down (Takeoff & Landing) 17.0 370.4 34.0 389.8
47,000 Down (Takeoff) 19.0 372.7 34.0 389.8
39,500 and Below Up (Enroute Operation)   8.5 360.6 35.0 390.9
43,000 Up (Enroute Operation) 12.5 365.7 35.0 390.9
47,000 Up (Enroute Operation) 14.9 368.2 35.0 390.9
(Straight line variation between above listed values)
Maximum Weight Takeoff 47,000 lbs. (Model 340 airplanes which have the
requirements of Service Bulletin 340-144B
incorporated which are being operated at
the Model 440 weights and performance
limitations as contained in the Model 440
FAA Approved Airplane Flight Manual
may be operated at increased Maximum
Takeoff Weights.  See NOTE 7.)
Landing 46,500 lbs.
Zero Fuel 45,000 lbs. (All weight in airplane above this value must
consist of fuel, oil and ADI fluid in the wing)
Minimum Crew 2 - Pilot and Copilot (Sta. 84)
Maximum Passengers 44 (CAR 4b.362) (Also refer to FAR §91.607)
Maximum Baggage Compartment Capacity Max. Floor Loading Arm
Fwd. Luggage LH     (Sta. 176-243) 200 lbs.
300 lbs.
300 lbs.
    25#/ft2 (Shelf 3)
    25#/ft2 (Shelf 2)
   100#/ft2 (Floor)
(210.5)
Fwd. Baggage RH    (Sta. 131-243) 1800 lbs. 150#/ft 2 (187.0)
Belly Compt.           (Sta. 193-319) 1000 lbs. 65#/ft 2 (250.0)
Aft Baggage             (Sta. 730-798) 1800 lbs. 150#/ft 2 (765.0)
Fuel Capacity 1730 U.S. gal. (One 865 U.S. gal. tank in each wing) (Sta. 397)
(See NOTE 1(d) for "Unmeasurable fuel.")
Oil Capacity 30 U.S. gal. in each nacelle (Sta. 339)
Serial Numbers Eligible 2 through 311
Required Equipment In addition to the pertinent required basic equipment specified in CAR 4b, the following
items of equipment must be installed:  1; 3; 4; 100; 103; 105; 109; 112; 113(a); 114; 200;
201 except (c); 202; 204; 205; 206; 300; 310; 401; 429; 601

6A6
Page 4 of 24
II - Model 340-30 (Original Model 340  prototype modified)
Engines 2 P&W Double Wasp CB16 or CB17
Fuel 100/130 grade aviation gasoline (CB16); 108/135 grade aviation gasoline (CB17)
Engine Limits
HP. R.P.M.
M.P.
In. Hg. Alt.
P&W Double Wasp CB16
  Low impeller gear ratio 7.29:1
     Takeoff (two minutes) (dry) 2050 2700* 55.0 S.L.
     Takeoff (two minutes) (dry) 2050 2700* 53.0 6900'
     Takeoff (two minutes) (dry) 1950 2800* 53.0 S.L.
     Takeoff (two minutes) (dry) 1950 2800* 51.0 9800'
   *(See NOTE 3 for limitations)
     Takeoff (two minutes) (wet) 2400 2800 59.5 S.L.
     Takeoff (two minutes) (wet) 2400 2800 59.0 5000'
      (See Item 103(a) for ADI installation
      and Engine Specification E-264 for
      ADI fluid composition)
     Maximum continuous 1800 2600 48.5 S.L.
     Maximum continuous 1800 2600 46.5 9200'
  High impeller gear ratio 8.58:1
     Maximum continuous 1700 2600 48.5 10,000'
     Maximum continuous 1700 2600 47.5 16,800'
(Straight line manifold pressure variation with altitude shown)
P&W Double Wasp CB17
  Low impeller gear ratio 7.29:1
     Takeoff (two minutes) (dry) 2200 2800* 60.0 S.L.
     Takeoff (two minutes) (dry) 2200 2800* 59.0 5200'
   *(See NOTE 3 for limitations)
     Takeoff (two minutes) (wet) 2500 2800 62.0 S.L.
     Takeoff (two minutes) (wet) 2500 2800 61.5 3700'
      (See Item 103(a) for ADI installation
      and Engine Specification E-264 for
      ADI fluid composition)
     Maximum continuous 1900 2600 51.5 S.L.
     Maximum continuous 1900 2600 50.0 7100'
  High impeller gear ratio 8.58:1
     Maximum continuous 1700 2600 51.5 10,000'
     Maximum continuous 1700 2600 49.5 15,000'
(Straight line manifold pressure variation with altitude shown)
Airspeed Limits V NO (Normal Operating) 234 knots True Ind. S.L. to 16,500'
VNE (Never Exceed) 266 knots True Ind. S.L. to 16,500'
(Above altitudes shown, reduce speed 6 knots per 1000')
VA (Maneuvering) 154 knots True Ind.
VFE (Flaps Down 0° to 20°) 174 knots True Ind.
VFE (Flaps Down 20° to 30°) 156 knots True Ind.
VFE (Flaps Down 30° to 40°) 148 knots True Ind.

6A6, Rev. 11
Page 5 of 24
Airspeed Limits (Cont'd) V LE (Landing Gear Extended) 174 knots True Ind.
VLO (Landing Gear Operation) (Retraction) 130 knots True Ind.
VLO (Landing Gear Operation) (Extension) 174 knots True Ind.
C.G. Range See NOTE 1(b) for retraction moment.
Forward Aft
Gross Weight (lbs.) Landing Gear Position
%
MAC Sta.
%
MAC Sta.
31,000 to 39,500 Down (Takeoff & Landing) 13.0 365.8 34.0 389.8
43,000 Down (Takeoff & Landing) 17.0 370.4 34.0 389.8
46,725 Down (Takeoff) 18.8 372.4 34.0 389.8
31,000 to 39,500 Up (Enroute Operation)   8.5 360.6 35.0 390.9
43,000 Up (Enroute Operation) 12.5 365.7 35.0 390.9
46,725 Up (Enroute Operation) 15.0 368.0 35.0 390.9
(Straight line variation between above listed values)
Maximum Weight Takeoff 46,725 lbs.
Landing 44,500 lbs.
Zero Fuel 43,000 lbs. (All weight in airplane above this value must
consist of fuel, oil and ADI fluid in the wing)
Minimum Crew 2 - Pilot and Copilot (Sta. 84)
Maximum Passengers 22 (CAR 4b.362)
Fuel Capacity 1730 U.S. gal. (One 865 U.S. gal. tank in each wing) (Sta. 397)
(See NOTE 1(d) for "Unmeasurable fuel.")
Oil Capacity 30 U.S. gal. in each nacelle (Sta. 339)
Serial Numbers Eligible CVAC No. 1 only
Required Equipment In addition to the pertinent required basic equipment specified in CAR 4b, the following
items of equipment must be installed:  1(a); 3(a); 4; 100(a) or (b); 103; 109; 112; 113(a);
114; 200; 201(a) or (c); 202; 204; 205; 206; 300; 401; 429; 601
III - Model 440 Approved January 30, 1956
The Military Model C-131E is actually a Model 440.
See NOTE 5 for required changes to Military Model C-131E aircraft prior to operation under this section.
The Model 440 airplane is basically similar for all dash numbers, the only differences being in the type of equipment and
interiors for the customer's airplane.
Engines 2 P&W Double Wasp CB3, CB4, CB16, CB17 or Military R-2800-103W (See NOTE 8
and 12)
Fuel 100/130 grade aviation gasoline (CB3, CB16 and R-2800-103W at CB16 ratings)
108/135 grade aviation gasoline (CB4, CB17 and R-2800-103W at CB17 ratings)

6A6
Page 6 of 24
Engine Limits
HP. R.P.M.
M.P.
In. Hg. Alt.
P&W Double Wasp CB3
     Takeoff (two minutes) (dry) 2050 2700* 55.0 S.L.
     Takeoff (two minutes) (dry) 2050 2700* 53.0 6900'
     Takeoff (two minutes) (dry) 1950 2800* 53.0 S.L.
     Takeoff (two minutes) (dry) 1950 2800* 51.0 9800'
   *(See NOTE 3 for limitations)
     Takeoff (two minutes) (wet) 2400 2800 59.5 S.L.
     Takeoff (two minutes) (wet) 2400 2800 59.0 5000'
      (See Item 103(a) for ADI installation
      and Engine Specification E-264 for
      ADI fluid composition)
     Maximum continuous 1800 2600 48.5 S.L.
     Maximum continuous 1800 2600 46.5 9200'
(Straight line manifold pressure variation with altitude shown)
P&W Double Wasp CB16 and
Military R-2800-103W
  Low impeller gear ratio 7.29:1
     Takeoff (two minutes) (dry) 2050 2700* 55.0 S.L.
     Takeoff (two minutes) (dry) 2050 2700* 53.0 6900'
     Takeoff (two minutes) (dry) 1950 2800* 53.0 S.L.
     Takeoff (two minutes) (dry) 1950 2800* 51.0 9800'
   *(See NOTE 3 for limitations)
     Takeoff (two minutes) (wet) 2400 2800 59.5 S.L.
     Takeoff (two minutes) (wet) 2400 2800 59.0 5000'
      (See Item 103(a) for ADI installation
      and Engine Specification E-264 for
      ADI fluid composition)
     Maximum continuous 1800 2600 48.5 S.L.
     Maximum continuous 1800 2600 46.5 9200'
  High impeller gear ratio 8.58:1
     Maximum continuous 1700 2600 48.5 10,000'
     Maximum continuous 1700 2600 47.5 16,800'
(Straight line manifold pressure variation with altitude shown)
P&W Double Wasp CB4
     Takeoff (two minutes) (dry) 2200 2800* 60.0 S.L.
     Takeoff (two minutes) (dry) 2200 2800* 59.0 5200'
   *(See NOTE 3 for limitations)
     Takeoff (two minutes) (wet) 2500 2800 62.0 S.L.
     Takeoff (two minutes) (wet) 2500 2800 61.5 3700'
      (See Item 103(a) for ADI installation
      and Engine Specification E-264 for
      ADI fluid composition)
     Maximum continuous 1900 2600 51.5 S.L.
     Maximum continuous 1900 2600 50.0 7100'
(Straight line manifold pressure variation with altitude shown)

6A6, Rev. 11
Page 7 of 24
Engine Limits (Cont'd)
HP. R.P.M.
M.P.
In. Hg. Alt.
P&W Double Wasp CB17 and
Military R-2800-103W
  Low impeller gear ratio 7.29:1
     Takeoff (two minutes) (dry) 2200 2800* 60.0 S.L.
     Takeoff (two minutes) (dry) 2200 2800* 59.0 5200'
   *(See NOTE 3 for limitations)
     Takeoff (two minutes) (wet) 2500 2800 62.0 S.L.
     Takeoff (two minutes) (wet) 2500 2800 61.5 3700'
      (See Item 103(a) for ADI installation
      and Engine Specification E-264 for
      ADI fluid composition)
     Maximum continuous 1900 2600 51.5 S.L.
     Maximum continuous 1900 2600 50.0 7100'
  High impeller gear ratio 8.58:1
     Maximum continuous 1750 2600 51.5 10,000'
     Maximum continuous 1750 2600 49.5 15,000'
(Straight line manifold pressure variation with altitude shown)
Airspeed Limits V NO (Normal Operating) 260 knots True Ind. S.L. to 13,000'
VNE (Never Exceed) 293 knots True Ind. S.L. to 13,000'
(Above altitudes shown, reduce speed 6 knots per 1000')
VA (Maneuvering) 155 knots True Ind.
VFE (Flaps Down 0° to 20°) 174 knots True Ind.
VFE (Flaps Down 20° to 30°) 156 knots True Ind.
VFE (Flaps Down 30° to 40°) 148 knots True Ind.
VLE (Landing Gear Extended) 174 knots True Ind.
VLO (Landing Gear Operation) (Retraction) 130 knots True Ind.
VLO (Landing Gear Operation) (Extension) 174 knots True Ind.
C.G. Range See NOTE 1(b) for retraction moment.
Forward             Aft
Gross Weight (lbs.) Landing Gear Position
%
MAC Sta.
%
MAC Sta.
39,500 and Below Down (Takeoff & Landing) 13.0 365.8 34.0 389.8
43,000 Down (Takeoff & Landing) 17.0 370.4 34.0 389.8
48,000 Down (Takeoff) 19.6 373.3 34.0 389.8
49,100 Down (Takeoff) 20.1 373.9 34.0 389.8
49,700 Down (Takeoff) 20.4 374.2 34.0 389.8
39,500 and Below Up (Enroute Operation)   8.5 360.6 35.0 390.9
43,000 Up (Enroute Operation) 12.5 365.7 35.0 390.9
48,000 Up (Enroute Operation) 15.6 368.7 35.0 390.9
49,100 Up (Enroute Operation) 16.2 369.4 35.0 390.9
49,700 Up (Enroute Operation) 16.5 369.7 35.0 390.9
(Straight line variation between above listed values)

6A6
Page 8 of 24
Maximum Weight Takeoff 49,700 lbs. (CB17) (Model 440 airplanes which are being
operated per the Supplementary Performance
Information contained in Appendix "A" of the
Model 440 FAA Approved Airplane Flight
Manual and are listed therein.)
49,100 lbs. CB4/CB17
48,000 lbs. CB3/CB16
Landing 47,650 lbs.
Zero Fuel 47,000 lbs.
45,000 lbs. - C-131E
           and R4Y-1/-2
(All weight in airplane above this value must
consist of fuel, oil and ADI fluid in the wing)
Minimum Crew 2 - Pilot and Copilot (Sta. 84)
Maximum Passengers 52 (CAR 4b.362) (Also refer to FAR §91.607)
Cargo aircraft, none (for eligibility of Model 440 cargo aircraft as passenger carriers, see
NOTE 5, Part 2, for required changes).
Maximum Baggage Compartment Capacity Max. Floor Loading Arm
Fwd. Luggage LH    (Sta. 176-243)
     (44 Passenger Version Only)
     (52 Passenger Version Only)
200 lbs.
300 lbs.
300 lbs.
N/A
    25#/ft2 (Shelf 3)
    25#/ft2 (Shelf 2)
   100#/ft2 (Floor)
N/A
(210.5)
N/A
Fwd. Baggage RH     (Sta. 131-243)
     (44 Passenger Version Only)
1800 lbs. 150#/ft 2 (187.0)
Coat Rack Area RH  (Sta. 131-179)
No Floor or Side Wall Tie Downs
     (52 Passenger Version Only)
30 Coats
Per Rod
210# Per Coat Rod (155.0)
Belly Compt.            (Sta. 193-319) 1000 lbs. 65#/ft 2 (250.0)
Aft Baggage              (Sta. 730-798) 1800 lbs. 150#/ft 2 (765.0)
Fuel Capacity 1730 U.S. gal. (One 865 U.S. gal. tank in each wing) (Sta. 397)
(See NOTE 1(d) for "Unmeasurable fuel.")
Oil Capacity 30 U.S. gal. in each nacelle (Sta. 339)
Serial Numbers Eligible 312 through 510 (including 327A)
Required Equipment In addition to the pertinent required basic equipment specified in CAR 4b, the following
items of equipment must be installed:  1; 3; 4; 100; 103; 105; 109; 112; 113(b); 114; 200;
201 except (a), (b) and (c); 202; 204; 205; 206; 300; 310; 405; 429; 601
Specifications Pertinent to All Models
Datum Station 0 (Fuselage Nose)
MAC 114.3 in. L.E. MAC (Sta. 350.90)
Leveling Means Longitudinal leveling lugs inside nose wheel well LH side (Sta. 29.75 and Sta. 48.85).
Lateral leveling lugs inside nose wheel well on forward bulkhead (Sta. 9).
Control Surface Movements
Aileron (angular measurements from streamline)
21½°  +2°/-0° Up 21°  +2°/-0° Down
(Rig 3°  ±1° down from streamline)

6A6, Rev. 11
Page 9 of 24
Control Surface Movements (Cont'd)
Aileron Trim Tab (angular from tab position when ailerons drooped 3°  ±0°)
7°  ±½° Up 7°  ±½° Down
(tabs rigged 2½°  ±1° Up from streamline
when ailerons drooped 3°  ±0°)
Aileron Tab Servo Action (angular from streamline)
Tab Indicator
Setting Tab Position Aileron Position
0° 2½°  ±1° Up 3°  ±0° Droop
0° 17½°  ±2° Down 21½° Up
0° 17°  ±2° Up 21° Down
NOTE:  Settings are measured from a relative position when wing, aileron and tab are
streamline.
Rudder (angular dimension from stabilizer chord line)
18½°  +1°/-0° Right 15°  +0°/-1° Left
Rudder Flight Tab (angular dimension from stabilizer chord line)
2° Left
Rudder Flight Tab Servo Action (angular dimension from stabilizer chord line)
Full Right Rudder Pedal 15°  ±½° Left
Full Left Rudder Pedal 11°  ±½° Right
NOTE:  Rudder chord line and stabilizer chord line coincide at rudder neutral position.
Rudder Trim Tab Setting (angular dimension from stabilizer chord line)
Tab Control Setting Tab Setting
Full Right (clockwise) 9°  ±1° Left
Full Left (counterclockwise) 9°  ±1° Right
NOTE:  Check deflections with rudder held neutral
Rudder Trim Tab Servo
Action
(angular dimension from rudder chord line)
0°  ±2° Left
0°  ±2° Right
Servo action is negligible.  It is
measured with rudder at full
deflection.
NOTE:  Rudder chord line and stabilizer chord line coincide at rudder neutral position.
Elevator (angular dimension from elevator streamline position
24½°  +1°/-0° Up 9½°  +1°/-0° Down
Elevator Trim Tab (RH) (angular dimension with tab rigged at streamline with
elevator and with elevator streamline to stabilizer)
7½°  ±½° Up 11½°  ±½° Down
Elevator Trim Tab (RH)
Servo Action
(angular dimension from elevator chord line)
Tab Position Elevator Position
6¼°  ±½° Down 24½°  ±0° Up
1°  ±½° Down 9½°  ±0° Down

6A6
Page 10 of 24
Control Surface Movements (Cont'd)
Elevator Servo Tab (LH) (angular dimension from elevator chord line)
Tab Position Elevator Position
0°  ±0° (at streamline with
              elevator)
5° Down
12°  ±½° Down 24½°  ±0° Up
½°  ±½° Down 9½°  ±0° Down
Certification Basis Type Certificate No. 6A6 (Transport Category, CAR 4b, effective July 20, 1950, and
Amendment #1, #3, and #5, except smoke detectors not installed in cargo compartments.)
Production Basis None at this time.
General Dynamics, Convair Division, produced Model 340/440 aircraft, serial numbers 2
through 510, and parts under FAA Production Certificate (PC) Number 605 in San
Diego, California, until 1995. PC 605 became invalid when the Type Certificate (TC)
was transferred to Tracor Flight Systems, Inc.  Tracor was issued FAA Production
Certificate 708NM for the production of spare parts and type design changes for the
Model 340/440.  The Tracor PC was surrendered in 1998 when the TC was endorsed to
Kelowna Flightcraft, Kelowna, BC, Canada
Equipment Approval for the installation of all items of equipment listed herein has been obtained by
the aircraft manufacturer except those items preceded by an asterisk (*).  The asterisk
denotes that approval has been obtained by someone other than the aircraft manufacturer.
An item marked with an asterisk may not have been manufactured under a FAA
monitored or approved quality control system.  Conformity must be determined if the
item is not identified by a Form ACA-186, PMA or other evidence of FAA production
approval.
Propellers and Propeller Weight Arm
Accessories (Except 1. Propellers - Model 340 (Including Original C-131D)
Anti-Icing Equipment) (a) 2  Ham. Std. 43E60 Propellers
43E60-9 Hubs, 6895A-8 Blades with de-icing
equipment.  (Same as 43E60-301 propeller.)
1093 lbs. (227)
(b) 2  Ham. Std. 43E60-301 Propellers
6895B-8 Blades with de-icing equipment.
(Alternate - Ham. Std. 43E60-325 or
43E60-333 Propeller.)
1150 lbs. (227)
(c) 2  Ham. Std. 43E60-319 Propellers
6895D-8 Blades with de-icing equipment.
1150 lbs. (227)
(d) 2  Ham. Std. 43E60-325 Propellers
6895E-8 Blades with de-icing equipment.
(Including original C-131D installation –
Model 340 types).  (Alternate - Ham. Std.
43E60-385 Propeller.)
1150 lbs.
1153 lbs.
(227)
(227)
(e) 2  Ham. Std. 43E60-333 Propellers
6895G-8 Blades with de-icing equipment.
(Alternate - Ham. Std. 43E60-387 Propeller.)
1150 lbs.
1150 lbs.
(227)
(227)

6A6, Rev. 11
Page 11 of 24
Propellers and Propeller
Accessories  (Except
Anti-Icing Equipment) (Cont’d)
Model 340 aircraft were not originally equipped for propeller
reverse indication.  Hamilton Standard developed one method of
complying with the requirements of CAR Amendment 40-9 by
directly aiding operators and by providing the following drawings to
modify the propeller system to incorporate reverse indicating lights:
SK-33116, SK-33008,        SK-29660, SK-32994, SK-29316, SK-
32758,              HS-501733 and HS-86415.
2. Propellers - Model 440 (Including Original C-131D)
(f) 2  Ham. Std. 43E60-377 Propellers
6895E-8 Blades with de-icing equipment.
(Including original C-131D installation - Model 440
types).  (Has provisions for propeller reverse
indication.)
1152 lbs. (227)
(g) 2  Ham. Std. 43E60-435 Propellers
6895E-8 Blades with de-icing equipment.
(Has provisions for propeller reverse indication and
feather latch.)
1152 lbs. (227)
(h) 2  Ham. Std. 43E60-469 Propellers
6895E-8 Blades with de-icing equipment.
(Has provisions for propeller reverse indication,
feather latch, low-pressure barrel and sensitive low
pitch stop per Ham. Std. Bulletin No. 472.)
1159 lbs. (227)
Propellers - Military Versions
(i) 2  Ham. Std. 43E60-341 Propellers
6895B-8 Blades with de-icing equipment.
(C-131B (Model 340-70), C-131F/R4Y-1
(Model 340-71) and C-131E (Model 440-72) only.)
1152 lbs. (227)
(j) 2  Ham. Std. 43E60-501 Propellers
6895B-8 Blades with de-icing equipment.
(C-131F/R4Y-1 (Model 340-71) only per US Navy
Aircraft Service Change (ASC) No. 5.  Has
provisions for propeller reverse indications.)
1152 lbs. (227)
(k) 2  Ham. Std. 43E60-523 Propellers
6895B-8 Blades with de-icing equipment.
(C-131E (Model 440-72) only.  Has provisions for
propeller reverse indications.)
1152 lbs. (227)
(l) 2  Ham. Std. 43E60-539 Propellers
6895M-8 Blades with de-icing equipment.
(C-131B (Model 340-70), C-131D and C-131E
(Model 440-72) only per USAF T.O. 3-1-1.)
1158 lbs. (227)
(m) 2  Ham. Std. 43E60-565 Propellers
6895N-8 Blades with de-icing equipment.
(C-131B (Model 340-70), C-131D and C-131E
(Model 440-72) only per USAF T.O. 3-1-1.)
1158 lbs. (227)
Applicable to all propellers:
Diameter:  Max. 13' 5-5/16"
                  Min. allowable for repairs 13' 1-9/16"
Pitch settings at 42" Sta.:   Reverse -8°, minimum low 30°,
feathered 96° (approx.)

6A6
Page 12 of 24
Propellers and Propeller
Accessories  (Except
Anti-Icing Equipment) (Cont’d)
3. Propeller Governors - Model 340 (Including Original
C-131D)
(a) 2  Ham. Std. 5U18-1   Constant Speed Control
(Including original C-131D installation - Model 340 types)
26 lbs. (236)
(b) 2  Ham. Std. 5U18-18  Constant Speed Control 27 lbs. (236)
(c) 2  Ham. Std. 5U18-35  Constant Speed Control 28 lbs. (236)
Weight Arm
Propeller Governors - Model 440 (Including Original
C-131D)
(d) 2  Ham. Std. 5U18-62  Constant Speed Control
(Including original C-131D installation - Model 440
types)
28 lbs. (236)
(e) 2  Ham. Std. 5U18-94  Constant Speed Control 28 lbs. (236)
(f) 2  Ham. Std. 5U18-115 Constant Speed Control 28 lbs. (236)
Propeller Governors - Military Versions
(g) 2  Ham. Std. 5U18-28  Constant Speed Control
(C-131B, C-131E and C-131F/R4Y-1 only.)
28 lbs. (236)
(h) 2  Ham. Std. 5U18-47  Constant Speed Control
(C-131B, C-131D and C-131E only per USAF T.O.
3-1-1.)
28 lbs. (236)
4. 2  Propeller Feathering Pumps, Pesco 1E-777-BL-1
    (Ham. Std. Dwg. No. 66166-6)
28 lbs. (346)
Engine and Engine Accessories -
Fuel and Oil Systems 100. Engines (See NOTE 8 and 12)
(a) 2  P&W Double Wasp CB16 4800 lbs. (267)
(b) 2  P&W Double Wasp CB17 4800 lbs. (267)
(c) 2  P&W Military R-2800-103W 4800 lbs. (267)
(d) 2  P&W Double Wasp CB3 4734 lbs. (267)
(e) 2  P&W Double Wasp CB4 4734 lbs. (267)
(f) 2  P&W Military R-2800-83AM7 4800 lbs. (267)
103. (a) Water-alcohol injection (CVAC Dwg. No.
340-0020700) with water-alcohol regulators
(included with engines - P&W No. 169479 or
190255)
(b) Water-alcohol injection fluid, 22 U.S. gal. 164 lbs. (454)
105. System fuel, 8.8 U.S. gal. (See NOTE 1(c))
(1730 U.S. gal. wing fuel tanks)
53 lbs. (391)
109. Oil Coolers 80 lbs. (296)
(a) 2  AiResearch 86764-13 Regulator Assy
(Consists of 19469 Valve and 86745 Cooler.)
(b) 2  AiResearch 87295-13 Regulator Assy
(Consists of 18930-13 Valve and 86745
Cooler.)
(c) 2  AiResearch 87270-155-13 Regulator Assy
(Consists of 18910-2-155-13 Valve and 86745
Cooler.)

6A6, Rev. 11
Page 13 of 24
Engine and Engine Accessories –
Fuel and Oil Systems  (Cont'd)
112. System oil, 28.5 U.S. gal. (See NOTE 1(c)) (60 U.S.
gal. oil tank installation) Ham. Std. propeller
installation
213 lbs. (291)
113. 4  Engine Muff Type Augmentors - Installation
(a) CVAC Dwg. No. 340-6220195 (Model 340) 572 lbs. (385)
(b) CVAC Dwg. No. 340-6227195 (Model 440) 572 lbs. (385)
(Model 440 installation includes 2 exhaust
mufflers CVAC Dwg. No. 340-6220110.)
400 lbs. (452)
114. Starters
(a) 2  Jack & Heintz JH6ER12 53 lbs. (307)
(b) 2  Jack & Heintz JH6CE 53 lbs. (307)
(c) 2  Eclipse Pioneer 36E00-4 53 lbs. (307)
(d) 2  AN4116R6FA (C-131B only.) 56 lbs. (307)
115. 2  Exhaust Mufflers Installation - CVAC Dwg. No.
340-7310077.  (Required for Model 340 airplanes
incorporating Service Bulletin 340-157.  Required
for Model 340 airplanes operating at Model 440
weights and performance limitations - See NOTE 7.)
400 lbs. (452)
Landing Gear
200. 2  Main Gear Shock Strut Assemblies
(a) Menasco 528000 547 lbs. (410)
(b) Menasco 528400 523 lbs. (410)
Menasco 528000 and 528400 are interchangeable.
201. Main Wheel-Brake Assemblies, 12.50-16, Type III
    Model 340 only with 1400  psi braking system
(a) 4  Goodyear Model LF1216HBMF
    Assemblies
388 lbs. (408)
    Wheel assembly 9540512 Tube Type
    Brake assembly 9540621 (Skydrol)
(b) 4  Goodyear Model LF1216HBMG
    Assemblies
388 lbs. (408)
    Wheel assembly 9545012 Tube Type
    Brake assembly 9540622 (MIL-H-5606)
    Model 340-30 prototype only
(c) 4  Goodrich Model 6201M Assemblies 385 lbs. (408)
    Wheel assembly H-3-708-M1 Tube Type
    Brake assembly G-2-593 (MIL-H-5606)
4  Main Wheel Assemblies, 12.50-16, Type III
(d) Goodyear 9540512 Tube Type 188 lbs. (408)
(e) Goodyear 9540512-1 Tube Type with
steel drive ring
212 lbs. (408)
(f) Goodyear 9540977 Tubeless Type 192 lbs. (408)
(g) Goodyear 9540977-1 Tubeless Type
with steel drive ring
216 lbs. (408)
Wheels must be installed in pairs of the same part
number.

6A6
Page 14 of 24
Landing Gear (Cont'd) 4 Main Brake Assemblies (1400 or 1700 psi system)
(h) Goodyear 9540976 (MIL-H-5606) 232 lbs. (408)
(i) Goodyear 9540998-1 (Skydrol) 232 lbs. (408)
(j) Goodyear 95401104 (MIL-H-5606) 224 lbs. (408)
(k) Goodyear 95401105 (Skydrol) 224 lbs. (408)
Brake part numbers must not be mixed on the same
airplane.
202. 4 Main Wheel Tires 340 lbs. (408)
(a) 12.50-16, 12-ply rating, Type III, with Tubes
(b) 12.50-16, 12-ply rating, Type III, Tubeless Type
(c) 39x13, 14-ply rating, Type VII, Tubeless Type
Tires must be installed in pairs of the same size and
type.
It is not acceptable to install a tubeless tire on a
tube-type wheel without a tube.
The maximum permissible weight of a tire and tube
or tubeless tire is 110 pounds.  Either new or
retreaded, the total weight of a tire and tube or
tubeless tire must not exceed this limit.
The maximum permissible weight of a tire and tube
or tubeless tire is 98 pounds on wheels with steel
drive rings.  Either new or retreaded, the total weight
weight of a tire and tube or tubeless tire must not
exceed this limit.
Inflation pressure 69 psi.
204. Nose Gear Shock Strut Assembly, Menasco 523500 196 lbs. (92)
205. Co-rotating Nose Wheels
(a) 2  Goodrich G-3-704-M1 Wheel Assemblies
    26x6, Type II, Tube Type
32 lbs. (95)
(b) 2  Goodrich G3-853 Wheel Assemblies
    7.50x14, Type III, Tubeless Type
32 lbs. (95)
(c) 2  Goodrich 3-903 Wheel Assemblies
    7.50x14, Type III, Tube Type
32 lbs. (95)
(d) 2  Goodyear 9531502 Wheel Assemblies
    7.50x14, Type III, Tube or Tubeless Type
34 lbs. (95)
Wheel assemblies  must be installed in pairs of the
same part number.
206. 2  Nose Wheel Tires
(a) 7.50x14, 8 ply rating, Type III, Tube Type,
with standard Type III tube with TR-176A
form E 70º bent valve stem
58 lbs. (95)
(b) 7.50x14, 8 ply rating, Type III,
Tubeless Type
47 lbs. (95)

6A6, Rev. 11
Page 15 of 24
Landing Gear (Cont’d) Tires must be installed in pairs of the same size, type
and tread.  With equalized air pressures, tires to
match within 0.50 inch in circumference.
It is not acceptable to install a tubeless tire on a
tube-type wheel without a tube.
The maximum permissible weight of a tire and tube
or tubeless tire is 30.8 pounds.  Either new or
retreaded, the total weight of a tire and tube or
tubeless tire must not exceed this limit.
Inflation pressure 58 psi.
208. D ecelostat (Westinghouse Air Brake Co.)
installation per Westinghouse Dwgs. P20822 and
1126A as shown in Westinghouse Data Pamphlet
Convair 340 or 440 Airplane.
41 lbs. (409)
Electrical Equipment
300. Batteries
(a) 2  Exide 6-FH-13 (12 v. - 88 ampere hours) 155 lbs. (424)
(b) 1  Exide 12-TAS-13F (24 v. - 51 ampere hours) 104 lbs. (424)
310. Generators 128 lbs. (308)
(a) 2  Eclipse-Pioneer 30E02-9-C (375 amps)
(b) 2  Eclipse-Pioneer 30E02-9-E (375 amps)
(c) 2  Eclipse-Pioneer 30E02-9-F (375 amps)
(d) 2  Eclipse-Pioneer 30E02-9-G (375 amps)
(e) 2  General Electric 2CM82D2 (375 amps)
Generator continuous full load current rating
(375 amps) is based on a minimum air blast cooling
pressure of 8” H2O and a maximum inlet temperature
of 40°C (104° F).
Interior Equipment
401. FAA Approved Airplane Flight Manual - Model 340.
405. FAA Approved Airplane Flight Manual - Model 440
(ZM-440-010).
419. Oxygen System Installation
(a) Oxygen system (CVAC Dwg. No. 340-3090401) 54 lbs. (216)
(b) Oxygen system (CVAC Dwg. No. 340-3090402) 54 lbs. (216)
(c) Oxygen system (CVAC Dwg. No. 340-3090404) 55 lbs. (216)
428. Cabin Compressor 68 lbs. (308)
(a) AiResearch No. 57370 (Aero Shell 1AC fluid -
electrically controlled cabin pressure system)
(b) AiResearch No. 57430 (Skydrol fluid - electrically
controlled cabin pressure system)
(c) AiResearch No. 205120 (Aero Shell 1AC fluid -
pneumatically controlled cabin pressure system)
(d) AiResearch No. 205130 (Skydrol fluid -
pneumatically controlled cabin pressure system)
Interior Equipment (Cont'd) 429. Windshield Wipers Installation (ALCO Controls)
(CVAC Dwg. No. 340-3190601)
10 lbs. (60)

6A6
Page 16 of 24
450. Automatic Pilot System Installation
(a) Sperry A-12 or E-4 (2 servo units Sperry No.
678919-161 aileron and rudder, 1 servo unit
Sperry No. 678919-461 elevator, and 1 Servo
unit Sperry Unit 658648-11 elevator trim tab)
and Sperry SP-20 (identical to the A-12 but
equipped with a magnetic amplifier, Sperry
S/N 618319-1, and electrical engaging and
disengaging switches in addition to the manual
engaging lever).
(Use actual wt. & arm)
(1) Servo stall forces measured in lbs. at the
pilot's controls:
Rudder: Max. 61 Min. 46
Aileron: Max. 26 Min. 24
Elevator: Max. 17 Min.   9
Minimum stall forces are satisfactory for
automatic approach.
(2)  When using autopilot in cruise
      configuration the minimum terrain
      clearance is 1500 ft.  When using autopilot
      in approach configuration the minimum
      terrain clearance is 200 ft., pilot's seat belt
      fastened and hand on control wheel.  The
      minimum altitude in each case does not
      override any higher minimum operational
      altitudes.
(3)  Model 340 airplanes - FAA approved
       Convair 340 AFM with revision dated 5-7-59
       is required when the Sperry SP-20 autopilot
       is installed.  Model 440 airplanes - FAA
       approved Convair 440 AFM with Revision
       No. 17 dated September 9, 1958, is required
       when the Sperry SP-20 autopilot is installed.
*(b) Lear L-5 in accordance with Lear Dwg. 73950
(3 main servos 118AU, elevator tab
servo 2216B, rudder tab servo 2216C)
(Use actual wt. & arm)
(1)  Servo stall torques measured in inch pounds
       at the servos:
Rudder: Max. 100 Min.   80
Aileron: Max. 185 Min. 150
Elevator: Max. 200 Min. 160
These torques are satisfactory for automatic
approach.
(2)  Maximum speed for autopilot operation is
      300 mph.  (See FAA approved Airplane
      Flight Manual for altitude loss during
      autopilot malfunctions.)
(3)  FAA approved Lear AFM Supplement
      dated May 25, 1954, is required.

6A6, Rev. 11
Page 17 of 24
De-Icing Equipment
500. 2  Propeller De-icing Installation
(a) De-icing assembly (Ham. Std. No. 79000-2)
(Used with 43E60-9 Hub, 6895A Blades only.)
56 lbs. (236)
(b) De-icing and control brush bracket assembly,
non-rotating (Ham. Std. No. 88870)
20 lbs. (236)
(c) De-icing and control brush bracket assembly,
non-rotating (Ham. Std. No. 511719)
20 lbs. (236)
Ham. Std. No. 511719 is alternate and
interchangeable with Ham. Std. No. 88870.
Miscellaneous
601. Hydraulic fluid in system and reservoir (14 U.S. gal.)
(a) Skydrol main hydraulic system fluid 127 lbs. (142)
(b) MIL-H-5606 main hydraulic system fluid 98 lbs. (142)
NOTE 1 (a) Current weight and balance report including list of equipment included in
certificated weight empty, and loading instructions, must be in each aircraft at the
time of original certification and at all times thereafter (except in the case of air
carrier operators having an approved weight control system).  Manufacturer's Master
Equipment List contains list of approved equipment in addition to equipment listed
in this specification.
(b) The airplane must be loaded so that the C.G. is within the specified limits at all
times, with the effects of fuel use, gear retraction, and movement of the crew and
passengers from their assigned positions being considered.  (Model 340:  Retraction
of the main and nose gears causes the C.G. to move forward, the change in moment
due to this retraction being -88,926 in. Lbs.  Model 440 and Model 340
incorporating Service Bulletin 340-217:  Retraction of the main and nose gears
causes the C.G. to move forward, the change in moment due to this retraction being
-92,124 in. lbs.)
(c) "System Fuel and Oil" (Items 105 and 112) which must be included in the empty
weight, is that amount required to fill both systems and the tanks up to the tank
outlets to the engines, when the airplane is in the level attitude.  The propeller
feathering oil in aircraft incorporating Hamilton Standard propellers, is not
considered usable oil and is included in the "system oil".  The nacelle oil tank
capacities shown in this specification include only the usable oil for which the tanks
are to be placarded.  All hydraulic system fluid (See Item 601) must also be included
in the empty weight of the airplane.
(d) The fuel capacity is the amount of fuel measured by the fuel gages with the airplane
in level attitude and tanks full.  The "unmeasurable fuel" is approximately 15 U.S.
gallons, and is the amount of fuel remaining in the tanks when the fuel gages read
ZERO.  The "unmeasurable fuel" must either be included in the airplane empty
weight or be suitably accounted for in the airplane weight and balance report.
(e) For passengers and extra crew members seat locations, see Approved Loading
Schedule for the particular airplane.
NOTE 2 (a) The following placards must be displayed on the instrument panel in full view of the
pilot:
(1) "This airplane must be operated in compliance with the operating limitations
specified in FAA Approved Airplane Flight Manual."
(2) Fuel Valves.  "Fuel transfer from tank to tank is prohibited.  When operating
with the crossfeed system, turn off fuel valve for tank not being used."

6A6
Page 18 of 24
NOTE 2 cont’d (b) The following placards must be installed in the cabin:
(1) Placards restricting use during takeoff and landing, and limiting the number of
occupants at any time as follows:
"Lavatory - 1 person"
NOTE 3 (a) Applicable to Model 340 Aircraft.
When water-alcohol injection is not used for takeoff on aircraft equipped with P&W
engines, Item 100(a) and (d), temporary operation may be accomplished in
accordance with the procedure in the emergency Operating Procedures Section of
the FAA Approved Airplane Flight Manual.  Continuous operation with "Dry"
rating takeoff power (2800 r.p.m.) may be accomplished in accordance with
Appendix "A" of the FAA Approved Airplane Flight Manual.  Continuous operation
with "Dry" takeoff power (2700 r.p.m.) may be accomplished on same Models in
accordance with Appendix "B" of the FAA Approved Airplane Flight Manual.
While dry takeoff procedures for the CB4, CB17 or R-2800-83AM7 engines are not
included in the Model 340 Approved Airplane Flight Manual, temporary and
continuous operating procedures and performance information as outlined above for
the CB3/CB16 engines may be utilized.
(b) Applicable to Model 440 Aircraft.
When water-alcohol injection is not used for takeoff on aircraft equipped with P&W
Engines, Item 100(a), (b), (c), (d) or (e), operations may be conducted in accordance
with the following sections of the FAA Approved Airplane Flight Manual:
CB16 and R-2800-103W (2800 r.p.m.):  Section 3, Part "D"
CB16 and R-2800-103W (2700 r.p.m.):  Section 3, Part "E"
CB17 and R-2800-103W (2800 r.p.m.):  Section 3, Part "J"
CB3 (2800 r.p.m.):  Section 3, Part "D" - ZM 440-010 CB3/4 Supplement
CB3 (2700 r.p.m.):  Section 3, Part "E" - ZM 440-010 CB3/4 Supplement
CB4 (2800 r.p.m.):  Section 3, Part "J" - ZM 440-010 CB3/4 Supplement
NOTE 4 (a) Applicable to Model 340 Aircraft.
Ferry permits may be issued to all Model 340 aircraft on which the automatic
propeller feathering system is inoperative.  Continuous operation with the automatic
propeller feathering system inoperative can be accomplished on some Models in
accordance with Appendix "C" of the FAA Approved Airplane Flight Manual.
Operating procedures, power ratings and performance data contained in Appendix
"C" of the Approved Airplane Flight Manual applicable to the CB3/CB16 engines
may be used for the CB4/CB17 engines.
(b) Applicable to Model 440 Aircraft.
Ferry permits may be issued to all Model 440 aircraft on which the automatic
propeller feathering system is inoperative.  Continuous operation with the automatic
propeller feathering system inoperative can be accomplished in accordance with the
following sections of the FAA Approved Airplane Flight Manual:
CB16 and R-2800-103W:  Section 3, Part "F"
CB17 and R-2800-103W:  Section 3, Part "K"
CB3:  Section 3, Part "F" - ZM 440-010 CB3/4 Supplement
CB4:  Section 3, Part "K" - ZM 440-010 CB3/4 Supplement
NOTE 5 Part 1.  The Model C-131E is a military cargo version of the Model 440, including the
installation of a cargo door and bail-out door on the left side of the fuselage, a cargo floor
and installation of various items of military equipment.  Before the Model C-131E
aircraft may be considered eligible for certification as a Model 440-72 cargo carrier, the
following must be accomplished:  (all references to CAR 4b in this NOTE are to
CAR 4b, effective July 20, 1950 and Amendment #1, #3, and #5).

6A6, Rev. 11
Page 19 of 24
NOTE 5 (Cont’d) (a) The "Conformity Certificate - Military Aircraft" (CAA Form ACA 970) together
with all maintenance overhaul and modification records of each aircraft must be reviewed
for changes made by the military services which may affect airworthiness of the aircraft.
(b) The aircraft must be reworked and/or modified in accordance with the following
Airworthiness Directives or an alternate modification approved by the FAA:
55-15-02 56-24-01 59-01-01 77-10-11
55-18-01 56-24-02 59-02-01 78-17-04
56-04-02 56-27-01 59-04-02 78-22-04
56-18-02 57-12-05 63-06-03 80-08-03
56-20-04 58-01-03 68-07-01
The inspections, as applicable, and possible modifications or rework as required by
the following Airworthiness Directives shall be accomplished in the manner
prescribed in each AD:
57-14-01 70-12-01 73-19-11 92-06-06
60-14-01 70-12-05 74-16-01 92-25-13
63-10-03 70-12-07 81-22-02 93-04-03
63-11-02 70-13-02 82-19-02 93-24-06
63-15-04 71-02-03 83-01-02 96-03-04
64-18-04 71-21-04 87-17-10
65-12-01 73-07-01 90-13-13
68-10-04 73-18-01 91-12-05
Note:  All applicable Airworthiness Directives must be complied with.
(c) Each airplane must be inspected for possible hidden damage, and for workmanship
and materials used in making any repairs, to determine that the repairs and/or
modifications comply with the pertinent CAR.
(d) The relief tube installation shall be removed or made permanently inoperative and a
thorough inspection made of the rear of the fuselage and empennage for corrosion
and possible structural damage.  All corroded and damaged areas must be suitably
replaced or repaired.
(e) The oxygen system must be evaluated to determine that it meets the pertinent Civil
Air Regulations.
(f) The instrument panel and markings must be evaluated for compliance with
CAR 4b.600 through 4b.613 and 4b.737.
(g) The cargo compartments shall be placarded designating cargo load limits as follows:
Cargo
Compartment
Fuselage
Station
Max.
Capacity
(Pounds)
Max. Load per
Running Ft.
(Pounds)
Max. Load
per Sq. Ft.
(Pounds)
C 176.5-254.5 4900   750 300
D 254.5-314.5 5000 1000 300
E 314.5-375.0 5000 1000 300
F 375.0-435.5 5000 1000 300
G 435.5-494.5 5000 1000 300
H 494.5-554.5 5000 1000 300
I 554.5-614.5 3800   750 300
J 614.5-676.5 3800   750 300
K 676.5-754.5 3000   750 300
NOTE 5 (Cont’d) (h) The bail-out door shall be pl acarded as an emergency exit in accordance with
CAR 4b.738(c).

6A6
Page 20 of 24
(i) Hand fire extinguishers shall be provided in accordance with CAR 4b. 605(j).
(j) A FAA Approved Flight Manual must be provided for each airplane prior to
certification as a Civil Aircraft.
(k) Any autopilot not complying with Item 450 of this Aircraft Specification shall be
rendered inoperative.
(l) Data pertaining to the interior arrangement of the aircraft must be submitted to the
Administrator to determine that such items as emergency exits, placards, cargo
accommodations, etc. comply with the applicable Civil Air Regulations and Federal
Aviation Regulatoins..
Part 2.  To be eligible as a passenger carrying aircraft, the following modification must be
made to the Model 440-72 cargo aircraft in addition to those modifications specified in
Part 1 of this NOTE.
(m) A lockable door must be provided between the flight deck and cabin in accordance
with CAR 4b.350(e) and (f).
(n) Data pertaining to the interior arrangement of the aircraft must be submitted to the
Administrator to determine that such items as emergency exits, seating arrangement,
passenger oxygen provisions, placards, cargo accommodations, etc. comply with the
applicable Civil Air Regulations and Federal Aviation Regulations..
NOTE 6 Replacement parts manufactured by Canadair, Limited, Montreal, Canada, are eligible for
installation on Convair aircraft covered by this specification, when accompanied by a
Canadair Release Note containing the following statement and bearing a certification
signed by a Canadian Department of Transport representative:
"Parts listed on this release note have been manufactured by Canadair as an approved
Convair subsidiary manufacturer under Convair Production Certificate No. 605, in
accordance with FAR 21."
NOTE 7 Model 340 airplanes, S/N 2 through 311, are eligible for operation at Model 440 weights
and performance limitations as shown in the Model 440 FAA Approved Airplane Flight
Manual when the modifications outlined in Convair Service Bulletin 340-144 have been
incorporated.
NOTE 8 Pratt and Whitney R-2800-52W and R-2800-99W engines (Military Designations) are
equivalent to the Pratt and Whitney Double Wasp CB17 as shown on Engine
Specification 5E-8.  Convair 340 type carburetor (PR-58E5-17) must be used if
R-2800-52W or R-2800-99W engines are installed.  The accessory drive must be
modified to accept the Convair 340 Cabin Compressor if the aircraft is to be certified for
pressurized operations.  The engine limits for the R-2800-52W and R-2800-99W are the
same as those specified herein for the CB17 engine.

6A6, Rev. 11
Page 21 of 24
NOTE 9 The Model C-131D airplanes are military transport versions of the commercial Model
340 or Model 440.  Prior to certification of these airplanes as a Model 340-67, 340-68,
340-79 or 440-79, the following must be accomplished:
(a) The aircraft must be reworked and/or modified in accordance with the following
Airworthiness Directives or an alternate modification approved by the FAA:
55-15-02 56-24-01 59-01-01 68-07-01
55-18-01 56-24-02 59-02-01 77-10-11
56-04-02 56-27-01 59-04-02 78-17-04
56-18-02 57-12-05 63-06-03 78-22-04
56-20-04 58-01-03 67-02-03 80-08-03
The inspections, as applicable, and possible modifications or rework as required by
the following Airworthiness Directives shall be accomplished in the manner
prescribed in each AD:
55-03-01 68-10-04 73-18-01 91-12-05
57-14-01 70-12-01 73-19-11 92-06-06
60-14-01 70-12-05 74-16-01 92-25-13
63-10-03 70-12-07 81-22-02 93-04-03
63-11-02 70-13-02 82-19-02 93-24-06
63-15-04 71-02-03 83-01-02 96-03-04
64-18-04 71-21-04 87-17-10
65-12-01 73-07-01 90-13-13
Note:  All applicable Airworthiness Directives must be complied with.
(b) Each airplane must satisfactorily pass an inspection for conformity to data sheet,
possible hidden damage, corrosion, workmanship and materials used in making any
repairs and/or alterations.
(c) The maintenance, overhaul and modification records of each aircraft must be
reviewed for changes made by the military services that may affect the airworthiness
of the aircraft.  Modifications and changes of equipment which affect the safety or
performance of the aircraft must be removed or approved by the Federal Aviation
Administration.
(d) Instrument markings and placards must be installed as required by this Specification
and the pertinent Civil Air Regulation.
(e) Each airplane must be weighed to determine its weight and balance, and an
approved loading chart or device installed and flight tested by the applicant.  If
changes have been made to the original aircraft that may affect the flight
characteristics, the particular aircraft must be flight tested by the FAA to determine
that the airplane as modified will still meet the minimum requirements of CAR 4b in
this regard.  Upon completion of the conversion to certified status, an additional
nameplate should be installed on the aircraft adjoining the manufacturer's nameplate
and should include the name of the agency accomplishing the conversion, the date
of the conversion and the new commercial model designation.  Under no
circumstances should the original or any succeeding nameplate be altered or
removed from the aircraft.
(f) An FAA Approved Airplane Flight Manual must be provided for each aircraft.
(g) Following is a listing of Convair Model and Version  numbers with CVAC Serial
Number and USAF Serial Number:

6A6
Page 22 of 24
NOTE 9 (Cont’d C-131D  (340-67): CVAC s/n 204 (54-2808), 205 (54-2809), 208 (54-2811),
209 (54-2812), 216 (54-2814), 217 (54-2815),
220 (54-2816), 221 (54-2817), 225 (54-2818),
226 (54-2819), 228 (54-2820), 231 (54-2821),
232 (54-2822), 234 (54-2823), 235 (54-2824) and
238 (54-2825)
C-131D  (340-68): CVAC s/n 183 (54-2805)
C-131D  (340-79) : CVAC s/n 201 (54-2806), 203 (54-2807), 206 (55-290),
207 (54-2810), 212 (55-291), 215 (54-2813), 223 (55-295),
224 (55-296), 229 (55-298) and 233 (55-300)
) C-131D  (440-79): CVAC s/n 315 (55-292), 316 (55-293), 321 (55-294),
322 (55-297), 326 (55-299) and 329 (55-301)
(h) Some C-131D aircraft (Model 440 versions) were delivered with a mechanism to
jettison the rear service door (Ref:  Convair drawings 340-7790017 and
340-3550550).  As this feature has not been evaluated by the FAA for its effects on
the safety of the aircraft in civil operation this mechanism must be removed in its
entirety and the rear service door installation and rear service door forward hinge
cone installation must conform to an approved Model 440 configuration (Ref:
Convair drawings 340-3510604-803 and 340-3550570).
NOTE 10 The Model C-131B is a military electronics test bed/transport version of the Model 340
including a litter door on the left side of the fuselage, a bail-out door and installation of
various items of military equipment.  Prior to certification of these airplanes as a Model
340-70 the following must be accomplished:
(a) The aircraft must be modified in accordance with Report No. GDC- 272-0/80-1199,
Revision No. 1, dated August 13, 1980, or equivalent report approved by the FAA.
(b) The aircraft must be reworked and/or modified in accordance with the following
Airworthiness Directives or an alternate modification approved by the FAA:
55-15-02 56-24-01 59-01-01 77-10-11
55-18-01 56-24-02 59-02-01 78-17-04
56-04-02 56-27-01 59-04-02 78-22-04
56-18-02 57-12-05 63-06-03 80-08-03
56-20-04 58-01-03 68-07-01
The inspections, as applicable, and possible modifications or rework as required by
the following Airworthiness Directives shall be accomplished in the manner
prescribed in each AD:
55-03-01 68-10-04 73-18-01 91-12-05
57-14-01 70-12-01 73-19-11 92-06-06
60-14-01 70-12-05 74-16-01 92-25-13
63-10-03 70-12-07 81-22-02 93-04-03
63-11-02 70-13-02 82-19-02 93-24-06
63-15-04 71-02-03 83-01-02 96-03-04
64-18-04 71-21-04 87-17-10
65-12-01 73-07-01 90-13-13
Note:  All applicable Airworthiness Directives must be complied with.
(c) Each airplane must satisfactorily pass an inspection for conformity to data sheet,
possible hidden damage, corrosion, workmanship and materials used in making any
repairs and/or alterations.

6A6, Rev. 11
Page 23 of 24
NOTE 10 (Cont’d (d) The maintenance, overhaul and modification records of each aircraft must be
reviewed for changes made by the military services that may affect the airworthiness
of the aircraft.  Modifications and changes of equipment which affect the safety or
performance of the aircraft must be removed or approved by the Federal Aviation
Administration.
(e) Instrument markings and placards must be installed as required by this Specification
and the pertinent Civil Air Regulation.
(f) Each airplane must be weighed to determine its weight and balance, and an
approved loading chart or device installed.  If changes have been made to the
original aircraft that may affect the flight characteristics or performance, the
particular aircraft must be flight tested by FAA to determine that the airplane as
modified will still meet the minimum requirements of CAR 4b in this regard.  Upon
completion of the conversion to certified status, the manufacturer’s nameplate on the
aircraft should be altered to include the date of conversion and the new commercial
model designation.  In case the original nameplate is not sufficiently large to include
this additional information, a similar plate should be installed near the original plate.
Under no circumstances should the original or any succeeding nameplate be altered
or removed from the aircraft.
(g) An FAA Approved Airplane Flight Manual must be provided for each aircraft.
NOTE 11 The Model C-131F/R4Y-1 is a military cargo version of the Model 340, including the
installation of a cargo door and bail-out door on the left side of the fuselage, a cargo floor
and installation of various items of military equipment.  Prior to certification of these
airplanes as a Model 340-71 the following must be accomplished:
(a) The aircraft must be modified in accordance with Report No. GDC- 272-0/80-1283
dated July 13, 1981, or equivalent report approved by the FAA.
(b) The aircraft must be reworked and/or modified in accordance with the following
Airworthiness Directives or an alternate modification approved by the FAA:
55-15-02 56-24-01 59-01-01 77-10-11
55-18-01 56-24-02 59-02-01 78-17-04
56-04-02 56-27-01 59-04-02 78-22-04
56-18-02 57-12-05 63-06-03 80-08-03
56-20-04 58-01-03 68-07-01
The inspections, as applicable, and possible modifications or rework as required by
the following Airworthiness Directives shall be accomplished in the manner
prescribed in each AD:
55-03-01 68-10-04 73-18-01 91-12-05
57-14-01 70-12-01 73-19-11 92-06-06
60-14-01 70-12-05 74-16-01 92-25-13
63-10-03 70-12-07 81-22-02 93-04-03
63-11-02 70-13-02 82-19-02 93-24-06
63-15-04 71-02-03 83-01-02 96-03-04
64-18-04 71-21-04 87-17-10
65-12-01 73-07-01 90-13-13
Note:  All applicable Airworthiness Directives must be complied with.
(c) Each airplane must satisfactorily pass an inspection for conformity to data sheet,
possible hidden damage, corrosion, workmanship and materials used in making any
repairs and/or alterations.

6A6
Page 24 of 24
NOTE 11 (Cont’d) (d) The maintenance, overhaul and modification records of each aircraft must be
reviewed for changes made by the military services that may affect the airworthiness
of the aircraft.  Modifications and changes of equipment which affect the safety or
performance of the aircraft must be removed or approved by the Federal Aviation
Administration.
(e) Instrument markings and placards must be installed as required by this Specification
and the pertinent Civil Air Regulation.
(f) Each airplane must be weighed to determine its weight and balance, and an
approved loading chart or device installed.  If changes have been made to the
original aircraft that may affect the flight characteristics or performance, the
particular aircraft must be flight tested by FAA to determine that the airplane as
modified will still meet the minimum requirements of CAR 4b in this regard.  Upon
completion of the conversion to certified status, the manufacturer’s nameplate on the
aircraft should be altered to include the date of conversion and the new commercial
model designation.  In case the original nameplate is not sufficiently large to include
this additional information, a similar plate should be installed near the original plate.
Under no circumstances should the original or any succeeding nameplate be altered
or removed from the aircraft.
(g) An FAA Approved Airplane Flight Manual must be provided for each aircraft.
NOTE 12 To be eligible for the installation of P&W Double Wasp CB3/CB4 engines on Model 340
or Model 440 airplanes each 340-6160002 Engine Electrical Junction Box Assembly
requires modification by removing the 340-4563128, 340-4563128-1 or 340-4563128-3
Supercharger Control to Firewall Harness Assy and capping the junction box elbow (Ref:
340-6160002-809/-811 or -825/-827 assy configuration), performing the modifications
described on drawing 340-7360004, updating the aircraft's weight and balance report
including list of equipment installed and ensuring the correct CB3/CB4 AFM supplement
is inserted in the appropriate Airplane Flight Manual.
END
```

## ADs (65, first 50, in force first)

- [AD 2013-08-10](https://openairdocs.org/ad/2013-08-10): Wings · Rolls Royce Dart 542-4 engines (Kelowna Flightcraft STC SA1096WE or 2 others). Effective May 10, 2013
- [AD 98-08-17](https://openairdocs.org/ad/98-08-17): AFM - Power Levers · Kelowna Flightcraft R & D 240 Series, 340 and 440. Effective May 19, 1998
- [AD 97-04-15](https://openairdocs.org/ad/97-04-15): Fire Extinguisher Bottle Cartridges · Bombardier DHC-8-101, DHC-8-102, DHC-8-103 and 24 more. Effective Mar 7, 1997
- [AD 96-25-12](https://openairdocs.org/ad/96-25-12): Auxiliary Power Units · BAE Systems HS 748 Series 2A, HS 748 Series 2B, 707-100 Long Body and 74 more. Effective Jan 13, 1997
- [AD 95-26-15 R1](https://openairdocs.org/ad/95-26-15-R1): Traffic Alert and Collision Avoidance Systems · Airbus A300 B2-1A, A300 B2-1C, A300 B2-203 and 159 more. Effective Dec 26, 1996
- [AD 96-03-04](https://openairdocs.org/ad/96-03-04): AFM - Limitation, Icing Conditions · Kelowna Flightcraft R & D 240 Series, 340, 440 and 4 more. Effective Feb 28, 1996
- [AD 94-01-05](https://openairdocs.org/ad/94-01-05): Traffic Alert and Collision Avoidance System II Processors · Airbus A340-211, A340-212, A340-213 and 85 more. Effective Feb 4, 1994
- [AD 93-24-06](https://openairdocs.org/ad/93-24-06): Elevator & Rudder Hinge Pins & Bushings · Kelowna Flightcraft R & D 340, 440, Military C-131B and 3 more. Effective Jan 18, 1994
- [AD 93-04-03](https://openairdocs.org/ad/93-04-03): Horizontal And Vertical Stabilizers · Kelowna Flightcraft R & D 340, 440, Military C-131B and 3 more. Effective Apr 19, 1993
- [AD 92-25-13](https://openairdocs.org/ad/92-25-13): Corrosion Inspection · Kelowna Flightcraft R & D 240 Series, 340, 440 and 4 more. Effective Jan 12, 1993
- [AD 92-06-06](https://openairdocs.org/ad/92-06-06): Insp. Program Revision Structure · Kelowna Flightcraft R & D 340, 440, Military C-131B and 3 more. Effective Apr 22, 1992
- [AD 91-12-05](https://openairdocs.org/ad/91-12-05): Elevator Hinge Pins · Kelowna Flightcraft R & D 340, 440, Military C-131B and 3 more. Effective Jul 25, 1991
- [AD 90-13-13](https://openairdocs.org/ad/90-13-13): Fuselage Frames · Kelowna Flightcraft R & D 340, 440, Military C-131B and 3 more. Effective Jul 30, 1990
- [AD 87-17-10](https://openairdocs.org/ad/87-17-10): Main Landing Gear · Kelowna Flightcraft R & D 340, 440, Military C-131B and 3 more. Effective Sep 24, 1987
- [AD 83-01-02](https://openairdocs.org/ad/83-01-02): NLG Axle Fracture · Kelowna Flightcraft R & D 340, 440, Military C-131B and 3 more. Effective Jan 19, 1983
- [AD 82-19-02](https://openairdocs.org/ad/82-19-02): Horizontal Stabilizer Attach · Kelowna Flightcraft R & D 340, 440, Military C-131B and 3 more. Effective Sep 16, 1982
- [AD 81-22-02](https://openairdocs.org/ad/81-22-02): Elevator Outer Torque Tube · Kelowna Flightcraft R & D 340, 440, Military C-131B and 3 more. Effective Oct 29, 1981
- [AD 80-08-03](https://openairdocs.org/ad/80-08-03): Aircraft Windows · Kelowna Flightcraft R & D 240 Series, 340 and 440 with STC SA1054WE or 2 others. Effective May 5, 1980
- [AD 78-22-04](https://openairdocs.org/ad/78-22-04): Emergency Exit Window · Kelowna Flightcraft R & D 340 and 440 with STC SA1096WE or 2 others. Effective Nov 1, 1978
- [AD 78-17-04](https://openairdocs.org/ad/78-17-04): Emergency Window Release Handle · Kelowna Flightcraft R & D 340, 440 and Military C-131E. Effective Sep 5, 1978
- [AD 74-16-01](https://openairdocs.org/ad/74-16-01): Stringer Inspection · Kelowna Flightcraft R & D 340 and 440. Effective May 4, 1978
- [AD 77-10-11](https://openairdocs.org/ad/77-10-11): Landing Gear Lug · Kelowna Flightcraft R & D 240 Series, 340 and 440 with STC SA1054WE or 2 others. Effective May 26, 1977
- [AD 76-07-02](https://openairdocs.org/ad/76-07-02): Emergency Evacuation Systems · Air Cruisers Emergency Evacuation Slides, 340 and 440. Effective Apr 6, 1976
- [AD 68-10-04](https://openairdocs.org/ad/68-10-04): Front Spar Lower Rail · Kelowna Flightcraft R & D 340, 440 and Military C-131E. Effective Jul 30, 1975
- [AD 73-19-11](https://openairdocs.org/ad/73-19-11): Nose Landing Gear Drag Strut · Kelowna Flightcraft R & D 340, 440 and Military C-131E. Effective Oct 19, 1973
- [AD 73-18-01](https://openairdocs.org/ad/73-18-01): Nose Landing Gear · Kelowna Flightcraft R & D 340, 440 and Military C-131E. Effective Aug 27, 1973
- [AD 73-07-01](https://openairdocs.org/ad/73-07-01): Wing Front Spar Lower Cap Cracks · Kelowna Flightcraft R & D 340, 440 and Military C-131E with STC SA1096WE or SA4-1100. Effective Mar 26, 1973
- [AD 67-33-03](https://openairdocs.org/ad/67-33-03): Pressure Fueling Valves · Kelowna Flightcraft R & D 240 Series, 340 and 440 with STC SA1054WE or 3 others. Effective Oct 3, 1972
- [AD 71-21-04](https://openairdocs.org/ad/71-21-04): Piston Bearing Lock Pins · Kelowna Flightcraft R & D 340, 440 and Military C-131E. Effective Oct 28, 1971
- [AD 67-02-03](https://openairdocs.org/ad/67-02-03): Rear Service Door · Kelowna Flightcraft R & D 340. Effective Sep 8, 1971
- [AD 71-02-03](https://openairdocs.org/ad/71-02-03): Main Landing Gear Failure · Kelowna Flightcraft R & D 340, 440 and Military C-131E. Effective Mar 9, 1971
- [AD 70-13-02](https://openairdocs.org/ad/70-13-02): Windshield Longeron Cracks · Kelowna Flightcraft R & D 340 and 440 with STC SA1096WE or SA4-1100. Effective Jul 28, 1970
- [AD 70-12-07](https://openairdocs.org/ad/70-12-07): Kelowna Flightcraft R & D 340 and 440 with STC SA1096WE or SA4-1100. Effective Jun 12, 1970
- [AD 70-12-05](https://openairdocs.org/ad/70-12-05): MLG Trunnion Fitting Inspection · Kelowna Flightcraft R & D 340 and 440. Effective Jun 11, 1970
- [AD 70-12-01](https://openairdocs.org/ad/70-12-01): MLG Beam Web Inspection · Kelowna Flightcraft R & D 340 and 440 with STC SA1096WE or SA4-1100. Effective Jun 4, 1970
- [AD 70-10-03](https://openairdocs.org/ad/70-10-03): Engine Breather Oil Fumes · Kelowna Flightcraft R & D 240 Series, 340 and 440 with STC SA1054WE or SA1096WE. Effective May 12, 1970
- [AD 68-16-04](https://openairdocs.org/ad/68-16-04): Exhaust Ducts · Kelowna Flightcraft R & D 240 Series, 340 and 440 with STC SA1054WE or SA1096WE. Effective Dec 27, 1968
- [AD 68-07-01](https://openairdocs.org/ad/68-07-01): Direct Vision Window Frame Casting · Kelowna Flightcraft R & D 340, 440 and Military C-131E. Effective Apr 29, 1968
- [AD 67-07-05](https://openairdocs.org/ad/67-07-05): Propeller Gust Lock · Kelowna Flightcraft R & D 240 Series, 340 and 440 with STC SA1054WE or SA1096WE. Effective Feb 25, 1967
- [AD 65-12-01](https://openairdocs.org/ad/65-12-01): Main Land Gear Gland Nut · Kelowna Flightcraft R & D 340 and 440. Effective Jun 27, 1965
- [AD 64-18-04](https://openairdocs.org/ad/64-18-04): Nose Landing Gear Retract Forks · Kelowna Flightcraft R & D 240 Series, 340 and 440. Effective Aug 28, 1964
- [AD 64-03-03](https://openairdocs.org/ad/64-03-03): Blades · Boeing DC-6, DC-6A, DC-6B and 26 more. Effective Mar 1, 1964
- [AD 63-15-04](https://openairdocs.org/ad/63-15-04): Nose Landing Gear Rod End Eye-Bolts · Kelowna Flightcraft R & D 340 and 440. Effective Aug 15, 1963
- [AD 63-11-02](https://openairdocs.org/ad/63-11-02): Main Landing Gear · Kelowna Flightcraft R & D 340 and 440. Effective Jun 14, 1963
- [AD 63-10-03](https://openairdocs.org/ad/63-10-03): Lower Wing Skin Fatigue · Kelowna Flightcraft R & D 340 and 440. Effective May 7, 1963
- [AD 63-06-03](https://openairdocs.org/ad/63-06-03): Electrical Fault Detection Panel · Kelowna Flightcraft R & D 340 and 440. Effective Mar 20, 1963
- [AD 52-14-02](https://openairdocs.org/ad/52-14-02): Electrical Circuits · Kelowna Flightcraft R & D 240 Series and 340
- [AD 55-03-01](https://openairdocs.org/ad/55-03-01): Elevator Servo Tab · Kelowna Flightcraft R & D 340
- [AD 55-15-02](https://openairdocs.org/ad/55-15-02): Propeller Feathering System · Kelowna Flightcraft R & D 240 Series and 340
- [AD 55-18-01](https://openairdocs.org/ad/55-18-01): Solenoid Operated Throttle Locks · Kelowna Flightcraft R & D 240 Series and 340

All 65: https://openairdocs.org/tcds/6A6/ads.md

## Registered aircraft by registry model (OpenAirDocs)

- [Convair 340](https://openairdocs.org/model/convair-340): 7 aircraft (registry code 242270A)
- [Convair 440](https://openairdocs.org/model/convair-440): 5 aircraft (registry code 2422902)
- [Conrad Flight SUPERFLITE 440](https://openairdocs.org/model/conrad-flight-superflite-440): 0 aircraft (registry code 056135G)

## STCs approved under this data sheet (241, first 50)

- [STC SA2622NM](https://openairdocs.org/stc/SA2622NM): Installation of Precise Flight Pulselite Control Unit in landing/taxi system. (767-200 B17) (DHC-8 101). Precise Flight Inc.
- [STC ST00892LA](https://openairdocs.org/stc/ST00892LA): Installation of Emergency Vision Assurance System (EVAS).. VisionSafe LLC
- [STC ST04672CH](https://openairdocs.org/stc/ST04672CH): Installation of FreeFlight Systems RA-5500 Radio Altimeter system. IFL Group Inc.
- [STC ST03424CH](https://openairdocs.org/stc/ST03424CH): Certification of Automatic Dependent Surveillance - Broadcast (ADS-B) Out System with Rockwell Collins TDR-94/-94D Transponders. CMD Flight Solutions LLC
- [STC SA01967WI](https://openairdocs.org/stc/SA01967WI): Use of GAMI G100UL High Octane Unleaded Avgas. General Aviation Modifications Inc.
- [STC SA863EA](https://openairdocs.org/stc/SA863EA): Incorporation of DME Corporation emergency evacuation slide lighting system. Astronics Luminescent Systems Inc
- [STC SA3275SO](https://openairdocs.org/stc/SA3275SO): Installation of a CAS-81 TCAS II system.. Honeywell International Inc
- [STC SA3276SO](https://openairdocs.org/stc/SA3276SO): Installation of a dual TRA-67 mode S transponder system.. Honeywell International Inc
- [STC ST00559AT](https://openairdocs.org/stc/ST00559AT): Installation of RDR-4B Weather Radar/Windshear System. Honeywell International Inc
- [STC ST00771SE](https://openairdocs.org/stc/ST00771SE): Installation of the MK VII Enhanced Ground Proximity Warning System (EGPWS)(Tracor (convair) 340-31). Honeywell International Inc
- [STC ST01737SE](https://openairdocs.org/stc/ST01737SE): : Installation of the RDR-4000 Doppler Radar System in accordance with Master Drawing List 756-0174-001, Revision (E), dated August 20, 2006, or later FAA approved revisions.. Honeywell International Inc
- [STC ST01629WI-D](https://openairdocs.org/stc/ST01629WI-D): CONFIURATION 1
Installation of a Honeywell TPA-100B TCAS II Processor with Change 7.1 and Goodrich Electronic Flight Bag System with In-Trail Procedures Activation in accordance with Honeywell Master Drawing List 756-0234-001, revision A, dated June 3, 2011 or later FAA approved revision.
CONFIGURATION 2
Installation of a Honeywell TPA-100B TCAS II Processor with Change 7.1 in accordance with Honeywell Master Drawing List 756-0234-001, revision A, dated June 3, 2011 or later FAA approved revision.. Honeywell International Inc
- [STC ST00442NY](https://openairdocs.org/stc/ST00442NY): Installation of Kalowna Flightcraft cargo compartment conversion.. Kelowna Flightcraft Ltd
- [STC ST00870NY](https://openairdocs.org/stc/ST00870NY): Installation of a Fruehauf Floor and Cargo Net.. Kelowna Flightcraft Ltd
- [STC SA195SW](https://openairdocs.org/stc/SA195SW): Structural installation of Bendix ANA-12A-1 doppler antenna.. Associated Air Center, Inc. - c/o CT Corporation System
- [STC ST02632LA](https://openairdocs.org/stc/ST02632LA): Modification to replace the existing Mode S Transponder system with ACSS NXT-700 Mode S Transponder with ADS-B Out and optionally install ACSS NXG-900 GPS as a position source for ADS-B Out. Aviation Communications and Surveillance Systems
- [STC ST04220CH](https://openairdocs.org/stc/ST04220CH): Installation of a FreeFlight 2101 I/O Approach Plus GPS Navigation System. IFL Group Inc.
- [STC ST03410CH](https://openairdocs.org/stc/ST03410CH): Modification from a dual autopilot to a single autopilot configuration, by installing a configuration adapter in place of the existing FZ-450. IFL Group Inc.
- [STC ST03006AT](https://openairdocs.org/stc/ST03006AT): Installation of the Honeywell MK VI Enhanced Ground Proximity Warning System (EGPWS)  to a Kelowna Flightcraft (Convair) Model 340/440. Contact Aviation LLC
- [STC ST03005AT](https://openairdocs.org/stc/ST03005AT): Installation of the Collins Traffic Collision Avoidance System 4000 (TCAS II). Contact Aviation LLC
- [STC ST03340NY](https://openairdocs.org/stc/ST03340NY): Installation of Dual CMA-5024 GPS/SBAS Landing System Sensor Units, Dual CMA-5025 SBAS Control Panels, and an Enhanced Airborne Data Loader Unit. William J. Hughes FAA Technical Center
- [STC SA3-419](https://openairdocs.org/stc/SA3-419): General interior floor plan arrangement.. Sabreliner Aviation LLC
- [STC SA3-420](https://openairdocs.org/stc/SA3-420): Main cabin seat installations(including divan and seat belts).. Sabreliner Aviation LLC
- [STC SA3-421](https://openairdocs.org/stc/SA3-421): Installation of auxiliary power unit.. Sabreliner Aviation LLC
- [STC SA3-486](https://openairdocs.org/stc/SA3-486): Interior cabin configuration - general floor plan (20 passenger configuration).. Sabreliner Aviation LLC
- [STC SA3-487](https://openairdocs.org/stc/SA3-487): Janitrol heater installation(100,000 BTU).. Sabreliner Aviation LLC
- [STC SA3-488](https://openairdocs.org/stc/SA3-488): Installation of radar nose, Bendix ANT-1B antenna and pitot modification (including Radome fabrication).. Sabreliner Aviation LLC
- [STC ST02839CH](https://openairdocs.org/stc/ST02839CH): Reduction of payload to 7500 lbs. Installation of placard per Rezich & Rezich drawing RR002. Rezich and Rezich Aviation Consulting Inc.
- [STC SA5002NM](https://openairdocs.org/stc/SA5002NM): Installation of provisions for side looking radar.. General Dynamics Advanced Information systems
- [STC ST01824NY](https://openairdocs.org/stc/ST01824NY): Installation of Northern Airborne Technology Satphone.. Northern Airborne Technology Ltd
- [STC SA1992NM](https://openairdocs.org/stc/SA1992NM): Installation of a de-icing system on Rolls Royce RK45524A engine inlet cowl.. ROBERT W. MURRAY
- [STC SA2220NM](https://openairdocs.org/stc/SA2220NM): This modification splits the nose fairing assembly P/N 906425-201, Rev. M P/N 9064135-1, Rev. A, and P/N 1914-1, Rev. C. (440 MILITARY C-131E MODIFIED IN ACCORDANCE WITH STC SA4-1100). ROBERT W. MURRAY
- [STC SA3105NM](https://openairdocs.org/stc/SA3105NM): Installation of a de-icing system externally on the Dowty Rotol Part Number (C) 4CM/71 Propeller Spinner.. ROBERT W. MURRAY
- [STC ST01798LA](https://openairdocs.org/stc/ST01798LA): Installation of a flight deck door. Quiet Wing Technologies, Inc.
- [STC SA125CE](https://openairdocs.org/stc/SA125CE): Installation of Hoskins Supplemental Model B of F High Intensity Wing Tip Lights, Model C or 30-0329-3 Dual Tail Light, with or without Model 2 High Intensity Fuselage Lights.. BF Goodrich Aerospace
- [STC SA379CE](https://openairdocs.org/stc/SA379CE): Installation of Hoskins Twilighter MK V High Intensity Aircraft Lighting System.  This is a Supplemental Condenser Discharge (Strobe) Light System, consisting of five (5) Light Units and a Power Supply.. BF Goodrich Aerospace
- [STC ST03004NY](https://openairdocs.org/stc/ST03004NY): Installation of new MIL-C-5015 connectors at the wing to fuselage interface must be in accordance with Kelowna Flightcraft Ltd.Master Drawing List K116-00002 Revision NC, dated March 20, 2009 or later Transport Canada approved revision.. Kelowna Flightcraft Ltd
- [STC ST00682WI-D](https://openairdocs.org/stc/ST00682WI-D): Modification of Collins VHF-20/VHF-20A/VHF-20B VHF COMM Receiver Transmitter with CTL-20 Control Pro Line I System Installation to a Collins VHF-22C/VHF-22D VHF COMM Receiver Transmitter with CTL-22C Control 8.33 kHz Pro Line II System Installation in accordance with Collins Installation Instructions as listed on AML No. ST00682WI-D, Revision -, or later FAA approved revisions.. Rockwell Collins Inc
- [STC ST02737NY](https://openairdocs.org/stc/ST02737NY): The installation of new annunciator hood. Kelowna Flightcraft Ltd
- [STC SA1097SO](https://openairdocs.org/stc/SA1097SO): Installation of two (2) double seats to increase passenger configuration from 44 to 48.. Pemco World Air Services
- [STC SA1248SO](https://openairdocs.org/stc/SA1248SO): Installation of single point seat belt and shoulder harness restraint systems for the pilot's, co-pilot's, forward observer's and flight attendant's seat assemblies.. Pemco Aeroplex Inc
- [STC ST1035SO](https://openairdocs.org/stc/ST1035SO): Installation of a combination passenger/cargo interior to include all cargo, 44 passenger/cargo, 10 passenger/cargo, and 6 passenger/cargo configurations. (340 MODIFIED IN ACCORDANCE WITH STC SA4-1100) (440 MILITARY C-131E MODIFIED IN ACCORDANCE WITH ST C SA4-1100. Pemco Aeroplex Inc
- [STC SA6088NM](https://openairdocs.org/stc/SA6088NM): Conversion of the 6A6 Type Certified Aircraft into a Model CV 5800 by installation of Allison 501-D22G Engines per STC SA4-1100, Hamilton Standard Propellers per STC SA1825NM and lengthening the fuselage 14 ft. 3.0 inches with all design changes.. Kelowna Flightcraft Ltd.
- [STC ST02671NY](https://openairdocs.org/stc/ST02671NY): Palletized Cargo Interior. Kelowna Flightcraft Ltd
- [STC ST02591CH](https://openairdocs.org/stc/ST02591CH): Installation of dual Honeywell TRA-45A TDU/Radio Altimeter Indicators. IFL Group Inc.
- [STC ST02488NY](https://openairdocs.org/stc/ST02488NY): The installation of Honeywell TCAS II System.. Kelowna Flightcraft Ltd
- [STC ST02489NY](https://openairdocs.org/stc/ST02489NY): The installation of Honeywell Mark VI Enhanced Ground Proximity Warning System. Kelowna Flightcraft Ltd
- [STC ST03062AT](https://openairdocs.org/stc/ST03062AT): Installation of a single Sandel P/N ST3400-001 Terrain Awareness and Warning System with Remote Magnetic Indicator (TAWS/RMI) in accordance with DC Aerospace Report No. MDL-2524, Revision A, dated March 4, 2005 or later FAA 
approved revision.. Air Tahoma
- [STC ST00525WI-D](https://openairdocs.org/stc/ST00525WI-D): Modification of Collins 618M-4 VHF COMM Receiver Transmitter Installation to a 618M-5 VHF COMM Receiver Transmitter installation with either a Gables G7406-02 or Avtech 7522-1-2 VHF COMM Receiver Transmitter Control Series using with Collins Installation Instructions as listed on AML No. ST00525WI-D, or later FAA approved revisions.. Rockwell Collins Inc
- [STC SA7772SW](https://openairdocs.org/stc/SA7772SW): Replacement of existing torquemeters.. AVMAR a Michigan Corporation

All 241: https://openairdocs.org/tcds/6A6/stcs.md

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