# TCDS A-793: Kelowna Flightcraft R & D Ltd.

- Type: Type certificate data sheet
- Status: Current
- Holder: Kelowna Flightcraft R & D Ltd.
- Revision: 26
- Revised: January 2, 2001
- Product: Aircraft, Large Airplane
- Certification basis: CAR 4b
- Data sheet PDF: https://openairdocs.org/files/sha256/e8/54/e854b1f9d4a2478fea907ccdd052723fc77b0a7abe50f0ee0ef0468d3813463d
- FAA DRS: https://drs.faa.gov/browse/excelExternalWindow/7CC9ABC2CE9B04DF86256AF80065E173.0001
- Page: https://openairdocs.org/tcds/A-793

## Models (1)

As the data sheet lists them.

- 240 Series (USAF T-29A, VT-29A, T-29B, T-29C, T-29D, C-131A)

## 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
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P a g e  N o . 2 22 32 4
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DEPARTMENT OF TRANSPORTATION
FEDERAL AVIATION ADMINISTRATION
A-793
Revision 26
General Dynamics
240 Series
 USAF T-29A, VT-29A,
T-29B, T-29C, T-29D,
 & C-131A
January 2, 2001
Aircraft Specification A-793
Manufacturer Kelowna Flightcraft R & D Ltd.
#1 5855 Kelowna Airport
Kelowna, BC, Canada V1V 1S1
I - Model 240-0 Approved December 7, 1948
This Section deleted.  All Model 240-0 airplanes have been revised to allow their operation in accordance with the provisions of
Section II.
II - Model 240-0, -1, -2, -3, -4, -5, -6, -7, -8, -10, -11, -12, -13, -14, -15, -17, -19, -26
      Model 240-6 approved December 7, 1948
      Model 240-17 approved December 28, 1978
NOTE 8 for explanations of model designations
NOTE 14 for required changes to the military T-29A and VT-  29A for operation as a Model 240-17
Engines 2 P&W Double Wasps CA3, CA15, CA18, or R2800-83AM3, -83AM4A or -83AM9
(20:9 propeller reduction gearing); or CB3, CB16, R2800-83AM5, -52WM1 or -99W
(20:9 propeller reduction gearing).  Note:   R2800-97W is equivalent to R2800 CA-18.
Fuel 100/130 grade aviation gasoline
Engine Limits (Straight line manifold pressure variation with altitudes shown)
HP. R.P.M.
MP
In. Hg. Alt.
P&W Double Wasp CA3, CA15,
R2800-83AM3 & -83AM4A
  Low impeller gear ratio 7.29:1
     Takeoff (two minutes) (dry) 2100 2800 53.5* S.L.
     Takeoff (two minutes) (wet) 2400 2800 56.5 S.L.
     Maximum continuous 1800 2600 45.0 S.L.
     Maximum continuous 1800 2600 44.0 6500'
  or (for CA3, CA15 & -83AM4A only)
     Maximum continuous 1900 2600 47.5 S.L.
     Maximum continuous 1900 2600 46.5 4900'
  High impeller gear ratio 9.45:1
     (CA15, R2800-83AM3, & -83AM4 only)
     Maximum continuous 1600 2600 46.5 10000'
     Maximum continuous 1600 2600 45.0 16200'

A-793
Page 2 of 24
Engine Limits (Cont'd)
HP. R.P.M.
MP
In. Hg. Alt.
P&W Double Wasp CA18 & R2800-83AM9
  Low impeller gear ratio 7.29:1
     Takeoff (two minutes) (dry) 2100 2800 53.5* S.L.
     Takeoff (two minutes) (wet) 2400 2800 56.5 S.L.
     Maximum continuous 1800 2600 45.0 S.L.
     Maximum continuous 1800 2600 44.0 6500'
     Maximum continuous 1900 2600 47.5 S.L.
     Maximum continuous 1900 2600 46.5 4500'
  High impeller gear ratio 9.1:1
     Maximum continuous 1675 2600 49.0 8000'
     Maximum continuous 1675 2600 47.0 13500'
P&W Double Wasp CB3, CB16,
R2800-83AM5, -52WM1 & -99W
  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'
     Takeoff (two minutes) (wet) 2400 2800 59.5 S.L.
     Takeoff (two minutes) (wet) 2400 2800 59.0 5000
     Maximum continuous 1800 2600 48.5 S.L.
     Maximum continuous 1800 2600 46.5 9200'
  High impeller gear ratio 8.58:1
  (CB16, R2800-83AM5, -52WM1 &
  -99W only)
     Maximum continuous 1700 2600 48.5 10000'
     Maximum continuous 1700 2600 47.5 16800'
*54 In. Hg. for R2800-83AM3, -83AM4A, and -83AM9
Airspeed Limits
VC (Maximum cruising) (S.L. to 7600')
(Above 7600' reduce speed)
See NOTE 9 for alternate values
280 m.p.h.
    6 m.p.h.
(244 knots)
(    5 knots)
True Ind.
per 1000'
VNE (Never exceed) (S.L. to 7600')
(Above 7600' reduce speed)
See NOTE 9 for alternate values
315 m.p.h.
    6 m.p.h.
(274 knots)
(    5 knots)
True Ind.
per 1000'
VP (Maneuvering) 180 m.p.h. (157 knots) True Ind.
VF (Flaps down) 15° maximum 215 m.p.h. (187 knots) True Ind.
VF (Flaps down) 20° maximum 200 m.p.h. (174 knots) True Ind.
VF (Flaps down) 30° maximum 178 m.p.h. (155 knots) True Ind.
VF (Flaps down) 40° full 160 m.p.h. (139 knots) True Ind.
VLE (Landing gear extended) 200 m.p.h. (174 knots) True Ind.
VLO (Landing gear operation) (Retracted) 150 m.p.h. (131 knots) True Ind.
VLO (Landing gear operation) (Extended) 200 m.p.h. (174 knots) True Ind.

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C. G. Range Takeoff and landing (351.4) (17% MAC) to (367.7) (31% MAC) with landing gear
extended.  Normal enroute operation (346.8) (13% MAC) to (370.1) (33% MAC) with
landing gear retracted.
Effect of retracting landing gear:  -69,160 in. lbs.
See NOTE 5 for modifications accomplished.
Maximum Weight Takeoff 40,500 lbs.
(See NOTE 11 for 41,200 lbs. with fuel dump system)
(See NOTE 5 for modifications accomplished)
(See NOTE 18 for 41,200 lbs. or 41,790 lbs. without outer panel tanks)
(See NOTE 19 for 41,790 lbs. with outer panel tanks)
(See NOTE 20 for 42,500 lbs. or 42,400 lbs. with fuel dump installation (with or without
outer panel tanks))
Landing 38,600 lbs.
(See NOTES 18, 19, and 20 for 39,800 lbs.)
Zero fuel 37,400 lbs.
(See NOTE 18 for 38,900 lbs. or 38,600 lbs. without outer panel tanks)
(See NOTE 19 for 38,900 lbs. with outer panel tanks)
(See NOTE 20 for 38,100 lbs.,  38,400 lbs., or 38,170 lbs. with fuel dump installation)
Minimum Crew 2 - Pilot and Copilot (Sta. 84)
Maximum Passengers 40 (CAR 4b.381)
Maximum Baggage (See NOTE 4)
Fuel Capacity 1000 gal. (one 500 gal. tank in each wing) (Sta.375)
Oil Capacity 41 gal. with Item 1(b), (c), or (d) installed (one 20.5 gal. tank in each nacelle) (Sta. 323)
45 gal. with Item 1(a) installed (one 22.5 gal. tank in each nacelle) (Sta. 323)
Serial Numbers Eligible 1 and up (566 aircraft were produced)
Required Equipment 1.(a), (b), (d), (e), (f), or (g); 111.(a); 115.(a) or (b); 116.(a) or (b); 201.(a) or (b); 202.(b)
or (c); 204.(a); 205.(a); 207.(a), (b), or (c); 208.(a) or (b); 209.(a) or (b); 210.(a); 211.(a)
or (b); 415.
III -Models 240-23, -24, -25, -27, -52, and  -53
Model 240-23 Approved September 1, 1950
Model 240-27 Approved July 8, 1963, & June 5, 1979
Models 240-52, 240-53 Approved June 12, 1980
NOTE 10 for eligibility of additional models
NOTE 13 for required changes to the Military T29B for operation as a Model 240-27
NOTE 15 for required changes to the Military T-29C for operation as a Model 240-27
NOTE 16 for required changes to the Military T-29D for operation as a Model 240-52
NOTE 17 for required changes to the Military C-131A for operation as  Model 240-53
Fuel 100/130 grade aviation gasoline.

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Page 4 of 24
Engine Limits Same as Section II
Airspeed Limits
VC (Maximum cruising) (S.L. to 16500')
(Above 16500' reduce speed
See NOTE 10 for alternate values
270 m.p.h.
    6 m.p.h.
(235 knots)
(    5 knots)
True Ind.
per 1000')
VNE (Never exceed) (S.L. to 16500')
(Above 16500' reduce speed
See NOTE 10 for alternate values
306 m.p.h.
    6 m.p.h.
(266 knots)
(    5 knots)
True Ind.
per 1000')
VP (Maneuvering) 180 m.p.h. (157 knots) True Ind.
VF (Flaps down) 15° maximum 215 m.p.h. (187 knots) True Ind.
VF (Flaps down) 20° maximum 200 m.p.h. (174 knots) True Ind.
VF (Flaps down) 30° maximum 178 m.p.h. (155 knots) True Ind.
VF (Flaps down) 40° full 160 m.p.h. (139 knots) True Ind.
VLE (Landing gear extended) 200 m.p.h. (174 knots) True Ind.
VLO (Landing gear operation) (Retracted) 150 m.p.h. (131 knots) True Ind.
VLO (Landing gear operation) (Extended) 200 m.p.h. (174 knots) True Ind.
C. G. Range Takeoff and landing (351.4) (17% MAC) to (367.7) (31% MAC) with landing gear
extended.  Normal enroute operation (346.8) (13% MAC) to (370.1) (33% MAC) with
landing gear retracted.
Effect of retracting landing gear:  -69,160 in. lbs.
See NOTE 5 for modifications accomplished.
Maximum Weights
Engines (1)
CA3, CA15, CA18,
CB3, CB16,
R2800-83AM3;
-83AM4A, -83AM5,
-83AM9, -52WM1,
-99W
(1)(2)
CA3, CA15, CA18,
CB3, CB16,
R2800-83AM4A,
-83AM5, -83AM9,
-52WM1, -99W
(3)
CA3, CA15, CA18,
CB3, CB16,
R2800-83AM4A,
-83AM5, -83AM9,
-52WM1, -99W
(3)
CA3, CA15, CA18,
CB3, CB16,
R2800-83AM4A,
-83AM5, -83AM9,
-52WM1, -99W
Propellers Curtiss
C632S-B/740-6C2-0
C632S-B/740-9C2-0
Hamilton Standard
23260/2H17K3-48R
23260/2H17U3-48R
or /2H17AA3-48R
or /2H17AC3-48R
43E60/6895A-12
Curtiss
C632S-B/740-6C2-0
C632S-B/740-9C2-0
Hamilton Standard
23260/2H17K3-48R
23260/2H17U3-48R
or /2H17AA3-48R
or /2H17AC3-48R
43E60/6895A-12
Curtiss
C632S-B/740-9C2-0
Hamilton Standard
43E60/6895A-12
Curtiss
C632S-B/740-9C2-0
Hamilton Standard
23260/2H17K3-48R
23260/2H17U3-48R
or /2H17AA3-48R
or /2H17AC3-48R
43E60/6895A-12
T.O. Gross Wt. 41200 41790 42400 42500
Zero Fuel Wt. 38900 38600/38900(4) 38160/38460(4) 38100/38400(4)
Landing Weight 39800 39800 39800 39800
(1) For airplanes modified in accordance with CVAC Service Bulletin 240-377 not incorporating outer panel fuel tanks.
(2) For airplanes modified in accordance with CVAC Service Bulletin 240-376A  incorporating outer panel fuel tanks.
(3) For airplanes modified in accordance with CVAC Service Bulletin 240-308B and 240-426.
(4) Upper figure Zero Fuel Wt. without outer panel fuel tanks.  Lower figure Zero Fuel Wt. with outer panel fuel tanks.

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Minimum Crew 2 - Pilot and Copilot (Sta. 84)
Maximum Passengers 40 (CAR 4b.381) (32 for Model 240-23)
Maximum Baggage (See NOTE 4)
Fuel Capacity 1000 gal. (one 500 gal. tank in each wing) (Sta. 375)
1550 gal. with outer fuel tanks, CVAC 240-1406001 (one 500 gal. and one 275 gal. tank
in each wing) (Sta. 375)
(Tanks in each wing are interconnected to function as a single 775 gal. tank)
Oil Capacity 41 gal. with Item 1(b) or (d) installed (one 20.5 gal. tank in each nacelle ) (Sta.323)
45 gal. with Item 1(a) installed (one 22.5 gal. tank in each nacelle) (Sta. 323)
5 gal. in fuselage (required when outer wing fuel tanks are installed) (Sta. 126)
Serial Numbers Eligible 1 and up (566 aircraft were produced)
Required Equipment 1.(a), (b), (d), (e), (f), or (g); 111.(a) or (b);  115.(a), (b), (c), or (d); 116.(b); 201.(a) or
(b); 202.(b) or (c); 204.(a); 205.(a); 207.(b), or (c); 208.(a) or (b); 209.(a),(b), or (c);
210.(a) or (b); 211.(b); 415.
Specifications Pertinent to All Models
Datum Station 0 (Fuselage Nose).  (Distance from data to centerline rear main wheel 393.1 in.)
MAC 116.6 in. L.E. MAC Sta. 331.6
Leveling Means Leveling lugs inside nose wheel well L.H. side.
Control Surface Movements Main Surfaces:
  Elevators 25° Up 12° Down
  Rudder 18° Left 18° Right
  Ailerons
  (Rig 1½° Drooped on Ground)
17° Up 20° Down
Flight (Spring) Tabs:
  Elevator
   (Rig 7° Up from Chord at Neutral)*
12° Up 12° Down
  Rudder
  (Rig 2° to Left of Chord Neutral)
14° Left 10° Right
Servo and Trim Tabs (Main Surfaces in Neutral):
  Elevator, Servo-Trim
  (Rig 5° Down from chord at Neutral)
3° Up 17° Down
  Rudder Trim 9° Left 9° Right
Aileron Servo-Trim
  (Rig 1½° Up from Chord at Neutral)
8½° Up 5½° Down
Flaps 39° Total Angular Travel
*With control column counter-balance and elevator bungee spring disconnected.  This
up-rigging becomes 9½° with counter-balance and spring connected.

A-793
Page 6 of 24
Certification Basis Type Certificate No. A-793 (Transport Category, CAR 4b, effective November 9, 1945,
and Amendment 4b-1, effective November 1, 1946) (Model 240-8, certified under the
combined requirements of CAR 4b, effective November 9, 1945, and Amendment 4b-1,
effective November 1, 1946, and CAR 3, effective November 13, 1945.)
Production Basis None at this time.
General Dynamics, Convair Division, produced 566 Model 240 aircraft 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 240.  The Tracor PC was
surrendered in 1998 when the TC was endorsed to Kelowna Flightcraft, Kelowna, BC,
Canada
Export Eligibility Eligible for export to all countries subject to the provisions of MOP 2-4 except as
follows:
Canada - Landplane only eligible.
Propellers and Propeller
Accessories (Except
Anti-Icing Equipment)
1. (a) 2 Curtiss-Wright, hubs C632SB with 740-6C2-0
blades
  926 lbs. (Sta. 220)
Diameter:  13'1"
Pitch settings at 42" sta., for use with engines
having 2100 hp. dry takeoff power rating only:
   Reverse -13.5°, minimum low 24°, feathered
   91.7°
Pitch settings at 42" sta., for use with engines
having 2400 hp. wet takeoff power rating:
   Reverse -17.5°, minimum low 26.5°, feathered
   91.7°
Following placards required:
(1)  "Avoid continuous operation in flight below
       1500 engine rpm."
(2)  "Avoid continuous operation on ground
       between 1250 & 1500 engine r.p.m.."
   (b) 2 Hamilton Standard, hubs 23260 with 2H17K3-
48R blades
  882 lbs. (Sta. 224)
Diameter:  13'1"
Pitch settings at 72" sta.:
   Reverse -23°, or -25°, minimum low 14°,
   feathered 81°.

A-793
Page 7 of 24
Propellers and Propeller
Accessories (Except
Anti-Icing Equipment) (Cont’d)
Some airplanes incorporate restricted throttle
travel in reverse, limiting reverse power to
approximately 75% of the 2400 hp. takeoff rating
of the engines.  These airplanes have a reverse
blade angle of -23°.  Airplanes with full power
available in reverse have a reverse blade angle of -25°
   (c) Deleted June 26, 1953
   (d) 2 Hamilton Standard, hubs 23260 with 2H17U3-
48R or 2H17AA3-48R blades (See Prop. Spec.
P-853 (NOTE 6) for interchangeable blades)
  888 lbs. (Sta. 224)
Diameter:  13'1"
Pitch settings at 72" sta.:
   Reverse -23°, or -25°, minimum low 14°,
   feathered 81°
Some airplanes incorporate restricted throttle
travel in reverse, limiting reverse power to
approximately 75% of the 2400 hp takeoff rating
of the engines.  These airplanes have a reverse
blade angle of -23°.  Airplanes with full power
available in reverse have a reverse blade angle of -25°.
3. 2 Curtiss-Wright, hubs C632SB with 740-9C2-0
blades
  980 lbs. (Sta. 220)
Diameter:  13'1"
Pitch settings at 42" sta., for use with engines
having 2100 hp. dry takeoff rating only:
   Reverse -13.5°, minimum low 24°, feathered
   91.7°
Pitch settings at 42" sta., for use with engines
having 2400 hp. wet takeoff power rating:
   Reverse -17.5°, minimum low 26.5°, feathered
   91.7°
Following placards required:
(1)  "Avoid continuous operation in flight below
      1500 engine rpm."
(2)  "Avoid continuous operation on ground
      between 1250 & 1500 engine rpm."
   (f) 2 Hamilton Standard, hubs 43E60 with 6895-12
blades
 1080
lbs.
(Sta. 224)
Diameter:  Max. 13’1-5/16”, minimum allowable
for repairs 12’9-5/8”
No further tolerance permitted
Pitch setting at 42” sta.:
   Reverse –13°; minimum low 29°; feathered 95°

A-793
Page 8 of 24
Propellers and Propeller
Accessories (Except
Anti-Icing Equipment) (Cont’d)
   (g) 2 Hamilton Standard hubs 23260 with  blades
2H17AC3-48R (See Prop. Spec.  P-853 (NOTE 6)
for interchangeable blades)
  906 lbs. (Sta. 224)
Diameter:  13'1"
Pitch settings at 72" sta.:
   Reverse -23° or -25°, minimum low 14°,
   feathered 81°
Some airplanes incorporate restricted throttle
travel in reverse, limiting reverse power to
approximately 75% of the 2400 hp. takeoff rating
of the engines.  These airplanes have a reverse
blade angle of -23°.  Airplanes with full power
available in reverse have a reverse blade angle of
-25°.
111. (a) System fuel  47 lbs. (Sta. 375)
(b) System fuel (with outer wing tanks installed)  53 lbs. (Sta. 375)
115. (a) System oil (with Item 1(a) or (e) installed) 133 lbs. (Sta. 275)
(b) System oil (with Item 1(b), (d), (f), or (g)
 installed)
204 lbs. (Sta. 274)
(c) System oil (with Item 1(a) or 1(e) and
auxiliary oil installed)
145 lbs. (Sta. 275)
(d) System oil (with Item 1(b), (d), (f), or (g) and
auxiliary oil installed)
216 lbs. (Sta. 274)
116. 4 engine augmenters
(a) Deleted December 12, 1950
(b) Muff type augmenters:
(1)  CVAC Part No. 240-6220195 with any of the following forward
      augmenter sections:
      240-6221107, -0, -168, -172, -182, -190, -202, -250, -252, -260,
      -262, -264, -268, -280, -290, -300, -314, -360
117. Fuel dump system (See CVAC Service Bulletin 240-426 for part numbers,
weight and basic moment changes.)
Landing Gear 201. 2 Main Gear Shock Struts
(a) Bendix 155370 (Left) and 155371 (Right) 450 lbs. (Sta 396)
(b) Bendix 155150 (Left) and 155151 (Right) 444 lbs. (Sta. 396)
(c) For Model 240-17, -27, -52, and -53 only
Bendix 160570 (Left) and 160570 (Right)
(See Notes)
455 lbs. (Sta. 396)
(d) Bendix 159695 (Left) and 159696 (Right)
(155370/155371 Shock Struts modified per
Bendix Service Bulletin  No. L.G. 516.
Required for 41,200 lbs. and higher maximum
take-off weight.  Ref. CVAC S.B. 240-308A)
440 lbs. (Sta. 396)

A-793
Page 9 of 24
Landing Gear (Cont'd) (e) Bendix 159589 (Left) and 159590 (Right)
(155150/155151 Shock Struts modified per
Bendix Service Bulletin No. L.G. 516
Required for 41,200 lbs. and higher maximum
take-off  weight.  Ref. CVAC S.B. 240-308A)
454 lbs. (Sta. 396)
 Notes: 1.  Must be used in pairs.
Not to be used on other 240 aircraft (use only on 240-17, -27,
-52, and  -53)
2. Parts in Bendix 155150/155151, 155370/155371,
159589/159590, and 159695/159696 Commercial Gears and
Bendix 160570 Military Gears are not interchangeable.
3. The Bendix 160570 Strut can be used in R.H. or L.H.
installations  depending on component assembly.
202. 4 Main Wheel Brake Assemblies (34 x 9.9)
 Type VII-B (E.H.P.)
(a) Deleted - December 12, 1950
202 (b) Goodyear Model L34 x 9.9 HBM
Wheel Assembly No. 9540082
Brake Assembly No. 9540245
Brake Assembly No. 9540485
Brake Assembly No. 9530222*
332 lbs. (Sta. 393)
(c) Goodyear Model L34d x 9.9 HBM
Wheel Assembly No. 9540316
Brake Assembly No. 9540245
Brake Assembly No. 9540485
Brake Assembly No. 9530222*
334 lbs. (Sta. 393)
(d) Goodyear Model L34 x 9.9 for 240-17
Wheel Assembly No. 9540316
Wheel Assembly No. 9540316 M-1
Brake Assembly No. 9540245
Brake Assembly No. 9540245M
334 lbs. (Sta. 393)
(e) Goodyear Model L34 x 9.9 for 240-27,
-52, -53
Wheel Assembly No. 9540591
Wheel Assembly No. 9540316 M-1
Brake Assembly No. 9540485
 334 lbs. (Sta. 393)
*Note:  Brake  assembly must be reworked per
            S.B. 240-22A II

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Page 10 of 24
Landing Gear (Cont’d)
204. (a) 4 Main Wheel 12 Ply Rating Tires (34 x 9.9)
Type VII B (Inflation Pressure = 95 PSI)
209 lbs. (Sta. 393)
(b) 4 Main Wheel 14 Ply Rating Tires (34 x 9.9)
Type VII B (Inflation Pressure = 109 PSI)
209 lbs. (Sta. 393)
The maximum permissible weight of a tire and
tube is 73.016 lbs.  Either new or retreaded, the
total weight of a tire and tube must not exceed
this limit.
205. 4 Main Wheel Tubes (34 x 9.9) Type VII B,
Plain with TR-150 Valve
  31 lbs. (Sta. 393)
207. Nose Gear Shock Strut
(a) Bendix 155155 131 lbs. (Sta. 92)
(b) Menasco 523500 187 lbs. (Sta. 92)
(Required for 41,200 lbs. and higher maximum
take-off weight.  Ref. CVAC S.B. 240-308A.
Required for Model 240-17, -27, -52, and -53)
(c) For Model 240-0, -10, and -26 only 183 lbs. (Sta. 92)
Bendix 159845
(Ref. American Airlines E.A. C.732A.
Alternate for Menasco 523500.  Requires E.A.
C.825 for 41,200 lbs. maximum take-off
weight)
208. 2 Nose Wheels (26 x 6) Type II Tire (Model 240)
(a) Goodrich Model 2665-M (Includes Fairings)
Mag
  36 lbs. (95)
(b) Goodrich Model 2665-M1 (Without Fairings)
Mag
  36 lbs. (95)
(c) Goodrich Assy. No. G-3-615-M Tube Type
(d) Goodrich Assy. No. G-3-615-M1 Tube Type
(e) Goodrich Assy. No. G-3-701M Tube Type
(f) Goodrich Assy. No. G-3-701M1 Tube Type
(g) Goodrich Assy. No. G3-677M1 Tube Type
(T-29A only) 240-17
(h) Goodrich Assy. No. G3-704M Tube Type
(i) Goodrich Assy. No. G3-704M1 Tube Type

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Page 11 of 24
Landing Gear (Cont'd) 2 Nose Wheels (26 x 6.6) Type VII Tire (Model T-29)
(See note at end of paragraph 209. for limitations)
(j) Goodrich Assy. No. G3-725M Tube Type
(T-29A, B, C, D, C-131A)
(k) Goodrich Assy. No. G3-725M1 Tube Type
(T-29A, B, C, D, C-131A)
2 Nose Wheels (7.50 x 14) Type III with S.B. 240-308B or S.B. 240-397.
Requires Menasco Nose Gear Shock Strut (Ref. 207.(b)) and
240-5210103-104 Nose Gear Drag Strut (Ref. 211.(b)).
(l) Goodrich Assy. No. G3-902 Tube or Tubeless
(m) Goodrich Assy. No. G3-904 Tube Type
 209. 2 Nose Wheel Tires (See NOTE 5 regarding Item 209.a)
(a) Goodrich Pre Rotating
10 Ply Rating Rotovane
(26 x 6) Type II Tube Type
Inflation Pressure = 97 PSI
 44 lbs. (Sta. 95)
(b) 10 Ply Rating (26 x 6) Type II Tube Type
Inflation Pressure = 97 PSI
 44 lbs. (Sta. 95)
(c) 8 Ply Ratings (7.50 x 14) Type III Tube Type  46 lbs. (Sta. 95)
with S.B. 240-308B or S.B. 240-397. Requires
Menasco Nose Gear Shock Strut (Ref. 207.(b))
and 240-5210103-104 Nose Gear Drag Strut
(Ref. 211.(b)).  Inflation Pressure = 54 PSI
(May be used on 26.6 wheel) 8 Ply Tire Only
(d) 12 Ply Rating (26 x 6.6) Type VII Tube Type
for G3-725M and M1 Only (240-17, -27, -52,
-53)
Inflation Pressure = 117.5 PSI
(e) 12 Ply Rating (7.50 x 14) Type III for G3-902
Only (with S. B. 240-397 installed)
Inflation Pressure = 82 PSI
Notes: (1) 26 x 6.6 Tires, Tubes, and Wheels must be used only in pairs
on nose wheel installations and the 26 x 6.6 Tires, Tubes, and
Wheels are not interchangeable with the 26 x 6 items used on
other models of the 240 aircraft.
The 7.50 x 14  8 Ply Tires may be used on the 26 x 6 Wheels
(Ref. 209.(c)).
The 7.50 x 14  8 Ply Tires may be installed provided the
Menasco Nose Gear Shock Strut (Ref. 207.(b)) and the
240-5210103-104 Nose Gear Drag Strut (Ref. 211.(b)) have
been installed per S.B. 240-308B or S.B. 240-397.

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Landing Gear (Cont'd) Notes (2) The tire pressures shown are nominal.
(3) The maximum permissible weight of a tire and tube is 30.8 lbs.
Either new or retreaded, the total weight of a tire and tube must
 not exceed this limit.
 210. 2 Nose Wheel Tubes
(a) (26 x 6) Type II Plain
with 2.5 inch TR-150 Valve
Bent 70°
  9 lbs. (Sta. 95)
(b) (7.50 x 14) Type III Plain   9 lbs. (Sta. 95)
(c) (26 x 6.6) Type VII for
Wheel G3-725 Only (240-17, -27, -52, and -53)
10 lbs. (Sta. 95)
211. Nose Gear Drag Strut
(a) CVAC 240-5210101 Assy. 46 lbs.
(b) CVAC 240-5210101 Assy. (including
240-5210103 -104 LH Upper Drag Strut)
(Required for 41,200 lbs. and higher maximum
take-off weight.  Ref. CVAC S.B. 240-308A.
Required to permit use of 7.50 x 14 Nose
Wheel Tires.  Ref. CVAC S.B. 240-397)
48 lbs.
(c) CVAC 240-5210101-815 Assy.
(For 240-17, -27, -52, -53 only)
Electrical Equipment
340. 2 landing lights
(a) Grimes 3800-3
13 lbs. (Sta. 335)
342. 1 taxi light
( a) General Electric 4560
 3 lbs. (Sta. 2)
344. 1 forward position light
(a) General Electric 4541
2 lbs. (Sta. 8)
345. 2 generators
(a) General Electric 2CM75C4 (300 a.) 120 lbs. (Sta. 299)
(b) General Electric 2CM82C1 (375 a.) 120 lbs. (Sta. 299)
Interior Equipment 415. FAA Approved Model 240 Airplane Flight Manual.  (The Manual may be 
carried as part of, or bound with, the operator's "Approved Operations Manual", 
but must retain its identity as an individual manual.)
416. (a) Cabin Supercharger, AiResearch Part No.
52351
  50 lbs. (Sta. 408)
(b) Cabin Supercharger, AiResearch Part No.
52851, Serial Nos. eligible for (a) and (b),
7-300 and up.

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Page 13 of 24
Interior Equipment (Cont'd) (c) Cabin Supercharger, Stratos Model S60-5,
installed in accordance with American
Airlines' Drawing FYC 1800A.
(d) Cabin Supercharger, Stratos Model S60-11,
installed in accordance with Pan American
World Airways' Report No. LA-442
417. Sperry A-12 Autopilot installed per pages APW-1 through APW-23 of Convair
Parts Catalog - Autopilot Section as revised June 15, 1950, and as modified by
Sperry Drawing SK No. 5232-65381E
(1) Servo Motor Cable Forces Limits
Elevator
Aileron
Rudder
89 lbs. min.
70 lbs. min
50 lbs. min.
130 lbs. max.
  89 lbs. max.
  71 lbs. max
(2) Power Gear Ratios
Elevator
Aileron
Rudder
148:1
104:1
104:1
(3) Maximum speed (TIAS) for autopilot operation:  234 knots
The maximum altitude loss during actual Automatic Pilot hard-over
malfunctions are listed below:
(a) Cruise configuration 350 ft.
(b) Approach configuration
Note:  A FAA Approved Airplane Flight
Manual Supplement must be supplied
100 ft.
Anti-Icing Equipment (See NOTE 6 regarding operation in icing conditions.)
506. (a) 2 Propeller Deicing Installation (Curtiss propellers), CVAC Drawing
 No. 240-0060906.
(b) 2 Propeller Deicing Installation (Hamilton Standard), CVAC Drawing
 No. 240-0061906.
(c) 2 Propeller Deicing Installation (Hamilton Standard), CVAC Drawing
 No. 240-0062906.
(d) 2 Propeller Deicing Installation (Hamilton Standard), American Airlines
E.A. No. C.875 (with manual control inoperative)
Miscellaneous 601. Stall Warning Indicator Installation (No longer required equipment)
NOTE 1 (a) Current weight and balance report including list of equipment included in
certificated weight empty, and loading instructions when necessary, 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).  See
Approved Master Equipment List CVAC Report No. ZL-240-002 for Approved
Alternate or Additional Items of Equipment.

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Page 14 of 24
NOTE 1 (Cont'd) (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 the movement of the crew and
passengers from their assigned positions being considered.  (Retraction of the main
and nose gears causes the C.G. to move forward, the change in moment due to this
retraction being -69,160 in. lbs.).  At takeoff, the airplane shall be loaded so that,
due to fuel use, the C.G. cannot move forward of Sta. 351.4 (17% MAC).
(c) (1) "System Fuel and Oil" 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.
"System Fuel and Oil" and all hydraulic fluid must be included in the
certification weight empty.
(2) Fuel and oil tank capacities do not include any "System Fuel and Oil".
Propeller feathering oil is not included as usable oil in installations with
Hamilton Standard propellers.
(d) For passengers and extra crew members seat locations, see Approved Weight and
Balance Report for the particular model 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."
(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 Deleted - December 12, 1950.  All aircraft converted to incorporate Equipment Item
116.(b).
NOTE 4
Compartment
Capacity
(pounds)
Maximum
Floor
Loading
(psf)
Moment
  Arm
(a) Baggage for Model 240-0, -3, -10,
-11, -12, -13, -14:
Forward (Models 240-0, -3, -10,
               -13, -14)
              (Models 240-11)
              (Models 240-12)
1800
1200
1550
150 R.H.
100 L.H.
(196)
Lower
    Total capacity of forward and
    lower compartments not to
    exceed 2500 lbs.
1500   65 (233)

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NOTE 4 (Cont’d)
Compartment
Capacity
(pounds)
Maximum
Floor
Loading
(psf)
Moment
  Arm
Aft 1500 150 (715)
Buffet
    Total capacity of aft compartments
    (including buffet) not to exceed
    1830 lbs.)
  620 (682)
(b) Baggage for Model 240-1, -7:
Forward 1550 150 R.H.
100 L.H.
(157)
Lower
    Total capacity of forward and
    lower compartments not to
    exceed 2500 lbs.
1500   65 (225)
Aft   200   50 (705)
(c) Baggage for Model 240-2:
Forward
*Left front portion of forward
     compartment, 40 lbs. psf
1150 100* (170)
Lower
    Total capacity of forward and
    lower compartments not to
    exceed 2500 lbs.
1500   65 (225)
Aft 1500 150 (715)
Auxiliary Passenger Compartment
(To be used when first two rows of
seats are removed)
1240   35 (265)
(d) Baggage for Model 240-4:
Forward  350 150 (196)
Lower
    Total capacity of forward and
    lower compartments not to
    exceed 1700 lbs.
1500   65 (225)
Aft 1500 150 (715)
Auxiliary Passenger Compartment
(To be used when first two rows of
seats are removed)
1240   35 (265)
(e) Baggage for Model 240-5:
Forward 1900 150 R.H.
100 L.H.
(153)
Lower
    Total capacity of forward and
    lower compartments not to
    exceed 2500 lbs.
1500   65 (225)
Aft 1000 150 (707)

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NOTE 4 (Cont'd)
Compartment
Capacity
(pounds)
Maximum
Floor
Loading
(psf)
Moment
  Arm
(f) Baggage for Model 240-6:
Forward Cargo
Forward Coat
1000
  150
  50 (196)
(133)
Lower
    Total capacity of forward and
    lower compartments not to
    exceed 2300 lbs.
1500   65 (233)
Aft 1500 150 (715)
(g) Baggage for Model 240-8:
Forward   580 125 (193)
Lower
    Total capacity of forward and
    lower compartments not to
    exceed 1930 lbs.
1350   65 (233)
(h) Baggage for Model 240-23:
Forward 3350   55 (244)
Lower
    Total capacity of forward and
    lower compartments not to
    exceed 4410 lbs.
1500   55 (233)
Aft 1500 150 (715)
Buffet   620 (682)
    Total capacity of aft compartments
    (including buffet) not to exceed
    1830 lbs.
NOTE 5 All aircraft have been modified to include provisions of CVAC Service Bulletin No. 240-
22A, Bendix Bulletin No. L.G. 500, and Equipment Item 202.(b).  Weight and C.G.
Range Limitations previously listed under NOTE 5 are now shown under the
corresponding limitations of Section II.
For operation of the airplane at altitude airports, incorporation of Equipment Item 209.(a)
may be necessary.  Consult FAA Approved Airplane Flight Manual for determination of
specific requirements.  With airplanes incorporating Item 207.(b), prerotation type tires
are not required.
NOTE 6 Model 240 aircraft are presently approved for operation in "light icing" conditions when
either Equipment Items 116.(a) or (b) are installed (provided Equipment Item 506.(a),
(b), or (c), and other pertinent anti-icing equipment are installed) under the following
provision:
(a) Deleted July 15, 1963.
NOTE 6 (Cont'd) (b) When Equipment Item 116.(b) is installed, the airplane, to be eligible for operation
into "light icing" conditions, must incorporate Convair Service Bulletins 240-21,
240-143, 240-200, and Convair Service Information Letter 389.  Convair Service
Bulletin 240-21 covers incorporation of the muff type augmenters and other
miscellaneous changes.  Service Bulletin 240-143 specifies incorporation of
stainless steel augmenter troughs.  Service Bulletin 240-200 incorporates the
installation of thermo-override switches in the heater ducts adjacent to the

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Page 17 of 24
augmenter tubes.  Service Information Letter 389 requires the relocation of the wing
anti-icing temperature pick-up bulbs to the respective wing tips.  Service Bulletin
240-143 need not be incorporated on aircraft incorporating the long augmenter
stacks which extend to a position at least flush with the end of the engine nacelle.
Before aircraft revised in accordance with the above technical data can be operated
under the terms of this icing approval, it will be necessary that a flight check be
accomplished to determine that the revised anti-icing installation meets the
following minimum standard:  With the airplane operating in level flight, two
engine, 1000 horsepower per engine at 10,000 feet augmenter vanes in trail position,
at least the following minimum temperatures above outside air temperature must
appear on the pilot's instruments:
Wing tips   93°C.
Tail 100°C.
NOTE 7 Ferry permits may be issued to Model 240 series aircraft on which the automatic
feathering system is inoperative.  See FAA Approved Airplane Flight Manual for
pertinent limitations.
NOTE 8 The various dash numbers listed under Section I and II are actually versions of the basic
Model 240 series aircraft, the certification basis for which is Type Certificate No. A-793.
These dash numbers were selected by CVAC primarily for contractual and clerical
purposes and should not be considered to define different models of airplanes.  Any one
version may be converted to another by incorporation of pertinent required equipment
and complete conformity with corresponding approved drawings.
It should be noted, however, that the identification plate in the cockpit indicates the
specific airplane version and that different FAA Approved Airplane Flight Manuals,
dependent primarily upon the propellers installed, are applicable to different groups of
versions.  Accordingly, when any version of a 240 series aircraft is converted to another,
an additional identification plate should be installed adjacent to the  manufacturer's plate.
It should include the name of the agency accomplishing the conversion, the date of the
conversion, and the new version number.  It should be determined that the FAA
Approved Airplane Flight Manual pertinent to the new version is installed.
NOTE 9 To airplanes certificated for a maximum takeoff weight of 40,500 lbs., the following
airspeed limits are applicable upon incorporation, in their entirety, of CVAC Service
Bulletins 240-56A, -176A, -205, -219, -225, -247A, -268, and CVAC Service
Information Letter No. 415 and, if applicable, CVAC Service Difficulties and Parts
Failures Report No. 245:
Airspeed limits:
VC (Maximum cruising) 280 m.p.h. (244 knots) True Ind. (S.L. to 15000')
(Above 15000' reduce speed 6 m.p.h. (5 knots) per 1000')
VNE (Never exceed) 315 m.p.h. (274 knots) True Ind. (S.L. to 15000')
(Above 15000' reduce speed 6 m.p.h. (5 knots) per 1000')
NOTE 10 Airplane models listed under Section II which have been modified in accordance with
CVAC Service Bulletins No. 240-22A and 240-308B, CVAC Service Information Letter
No. 551, and which have been further modified in accordance with the rework outlined in
NOTE 9, are eligible for operation under the provisions of Section II.

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NOTE 10 (Cont’d) Service  Bulletin 240-308B includes extensive rework of the wing center section, rework
of the fuselage in the area of the wing attachment, increasing the orifice in the main
landing gear struts to .535 in., and incorporation of Equipment Items 207.(b) or (c) and
211.(b).
For airplanes which do not incorporate the modifications outlines in NOTE 9 in their
entirety, the following Airspeed Limits are applicable:
Airspeed limits:
VC (Maximum cruising) 270 m.p.h. (235 knots) True Ind. (S.L. to 7600')
(Above 7600' reduce speed 6 m.p.h. (5 knots) per 1000')
VNE (Never exceed) 306 m.p.h. (266 knots) True Ind. (S.L. to 7600')
(Above 7600' reduce speed 6 m.p.h. (5 knots) per 1000')
NOTE 11 Airplane models listed under Section II which have been modified in accordance with
Pan American Airways, LAD Division, Engineering Report No. 415, "CV-240 Fuel
Dump System," may be operated at the following weights:
Takeoff 41,200 lbs.
Landing 38,600 lbs.
Zero Fuel 37,400 lbs.
The undumpable fuel is 114 gallons per tank (228 gallons total).
NOTE 12 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 Transportation 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 United States Civil Air Regulations and Civil Aeronautics Manual 1."
NOTE 13 The military Model T-29B is basically the same as Model 240.  Prior to the certification
of the T-29B as a Model 240-27, the following must be accomplished:
(a) The aircraft must be modified in accordance with Convair Report No. GDC-63- 115,
Revision 3, dated May 22, 1963, or an equivalent modification approved by the
FAA.
(b) The airplane must be reworked and/or modified in accordance with the following
Airworthiness Directives or a FAA Los Angeles Aircraft Certification Office
approved equivalent, unless already accomplished:
48-22-01 49-34-01 52-11-02 55-18-01 56-24-01 59-01-01 77-10-11
48-41-01 49-44-02 52-14-02 56-04-02 56-24-02 59-02-01 80-08-03
48-50-04 49-45-02 53-05-01 56-08-01 57-14-01 59-04-02
48-51-02 50-19-02 54-01-02 56-18-01 58-06-01 64-18-04
49-30-02 51-28-01 55-15-02 56-20-04 58-25-01 64-19-04
The inspections, as applicable, and as required by the following Airworthiness
Directives, shall be accomplished in the manner prescribed in each AD:
49-30-01 50-13-01 51-05-01 74-03-04 83-01-01 93-21-02
49-38-01 50-36-01 53-23-01 79-21-06 83-23-05
49-43-01 50-52-01 57-03-01 81-18-05 92-25-13

A-793
Page 19 of 24
NOTE 13 (Cont’d) Comply with the rework and/or modification required by all other
Airworthiness Directives that are applicable to the engines, propeller, or items of
equipment that are installed in the airplane.
(c) Each airplane must satisfactorily pass an inspection for conformity, possible hidden
damage, and for workmanship and materials used in making any repairs and/or
alterations.
(d) The maintenance, overhaul, and modification records of each aircraft must be
reviewed for changes made by 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 approved by the FAA.
(e) Instrument markings and placards must be installed as required by this Specification
and the pertinent Civil Air Regulations.
(f) Each airplane must be weighed to determine its weight and balance and an approved
loading chart or device installed.  The aircraft must have a functional check flight.
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 form the aircraft.
(g) A FAA Approved Airplane Flight Manual must be provided for each aircraft.
(h) The military R2800-97 is identical to the Double Wasp CA18.  Prior to certification,
the engine nameplate should be revised to include the corresponding civil model
designation CA18 and the T.C. No. E-231.
NOTE 14 The military Model T-29A/VT-29A airplanes are basically the same as the Model 240
except the T-29A series airplanes are not designed to be pressurized and must be so
placarded.  Prior to the certification of these models as a Model 240-17, the following
must be accomplished:
(a) The aircraft must be modified in accordance with Convair Report No. GDC- 057-
0/78-1200, Revision 2, dated August 22, 1978, or an equivalent modification
approved by the FAA.
(b) The airplane must be reworked and/or modified in accordance with the following
Airworthiness Directives or a FAA Los Angeles Aircraft Certification Office
approved equivalent, unless already accomplished:
48-22-01 49-34-01 52-11-02 55-18-01 56-24-01 59-01-01 77-10-11
48-41-01 49-44-02 52-14-02 56-04-02 56-24-02 59-02-01 80-08-03
48-50-04 49-45-02 53-05-01 56-08-01 57-14-01 59-04-02
48-51-02 50-19-02 54-01-02 56-18-01 58-06-01 64-18-04
49-30-02 51-28-01 55-15-02 56-20-04 58-25-01 64-19-04

A-793
Page 20 of 24
NOTE 14 (Cont’d) The inspections, as applicable, and as required by the following Airworthiness
Directives, shall be accomplished in the manner prescribed in each AD:
49-30-01 50-13-01 51-05-01 74-03-04 83-01-01 93-21-02
49-38-01 50-36-01 53-23-01 79-21-06 83-23-05
49-43-01 50-52-01 57-03-01 81-18-05 92-25-13
Comply with the rework and/or modification required by all other Airworthiness
Directives that are applicable to the engines, propellers, or items or equipment that
are installed in the airplane.
(c) Each airplane must satisfactorily pass an inspection for conformity, possible hidden
damage, corrosion, and for workmanship and materials used in making any repairs
and/or alterations.
(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 FAA.
(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.  The aircraft must have a functional check flight.
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 removed from the
aircraft.
(g) A FAA Approved Airplane Flight Manual must be provided for each aircraft.
(h) The military R2800-97 is identical to the Double Wasp CA18.  Prior to certification
the engine nameplate should be revised to include the corresponding civil model
designation CA18 and the T.C. No. E-231.
NOTE 15 The military T-29C airplanes are basically the same as the Model 240.   Prior to the
certification of these airplanes as 240-27 models, the following must be accomplished:
(a) The aircraft must be modified in accordance with Convair Report No. GDC- 057-
0/79-1010, Revision 2, dated January 15, 1979, or an equivalent modification
approved by the FAA.
(b) The airplane must be reworked and/or modified in accordance with the following
Airworthiness Directives or a FAA Los Angeles Aircraft Certification Office
approved equivalent, unless already accomplished:
48-22-01 49-34-01 52-11-02 55-18-01 56-24-01 59-01-01 77-10-11
48-41-01 49-44-02 52-14-02 56-04-02 56-24-02 59-02-01 80-08-03
48-50-04 49-45-02 53-05-01 56-08-01 57-14-01 59-04-02
48-51-02 50-19-02 54-01-02 56-18-01 58-06-01 64-18-04
49-30-02 51-28-01 55-15-02 56-20-04 58-25-01 64-19-04

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NOTE 15 (Cont’d) The inspections, as applicable, and as required by the following Airworthiness
Directives, shall be accomplished in the manner prescribed in each AD:
49-30-01 50-13-01 51-05-01 74-03-04 83-01-01 93-21-02
49-38-01 50-36-01 53-23-01 79-21-06 83-23-05
49-43-01 50-52-01 57-03-01 81-18-05 92-25-13
Comply with the rework and/or modification required by all other Airworthiness
Directives that are applicable to the engines, propellers, or items or equipment that
are installed in the airplane.
(c) Each airplane must satisfactorily pass an inspection for conformity, possible hidden
damage, corrosion, and for workmanship and materials used in making any repair
and/or alterations.
(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 FAA.
(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.  The aircraft must have a functional check flight.
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 removed from the
aircraft.
(g) A FAA Approved Airplane Flight Manual must be provided for each aircraft.
NOTE 16 The military T-29D airplanes are basically the same as the Model 240.  Prior to the
certification of these airplanes as 240-52 models, the following must be accomplished:
(a) The aircraft must be modified in accordance with Convair Report No. GDC- 057-
0/79-1160, dated June 15, 1979, or an equivalent modification approved by the
FAA.
(b) The airplane must be reworked and/or modified in accordance with the following
Airworthiness Directives or a FAA Los Angeles Aircraft Certification Office
approved equivalent, unless already accomplished:
48-22-01 49-34-01 52-11-02 55-18-01 56-24-01 59-01-01 77-10-11
48-41-01 49-44-02 52-14-02 56-04-02 56-24-02 59-02-01 80-08-03
48-50-04 49-45-02 53-05-01 56-08-01 57-14-01 59-04-02
48-51-02 50-19-02 54-01-02 56-18-01 58-06-01 64-18-04
49-30-02 51-28-01 55-15-02 56-20-04 58-25-01 64-19-04

A-793
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NOTE 16 (Cont’d) The inspections, as applicable, and as required by the following Airworthiness
Directives, shall be accomplished in the manner prescribed in each AD:
49-30-01 50-13-01 51-05-01 74-03-04 83-01-01 93-21-02
49-38-01 50-36-01 53-23-01 79-21-06 83-23-05
49-43-01 50-52-01 57-03-01 81-18-05 92-25-13
Comply with the rework and/or modification required by all other Airworthiness
Directives that are applicable to the engines, propellers, or items or equipment that
are installed in the airplane.
(c) Each airplane must satisfactorily pass an inspection for conformity, possible hidden
damage, corrosion, and for workmanship and materials used in making any repair
and/or alterations.
(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 FAA.
(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.  The aircraft must have a functional check flight.
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 removed from the
aircraft.
(g) A FAA Approved Airplane Flight Manual must be provided for each aircraft.
NOTE 17 The military C-131A airplanes are basically the same as the Model 240.  Prior to the
certification of these airplanes as 240-53 models, the following must be accomplished:
(a) The aircraft must be modified in accordance with Convair Report No. GDC- 057-
0/79-1172, Revision 1, dated April 4, 1980, or an equivalent modification approved
by the FAA.
(b) The airplane must be reworked and/or modified in accordance with the following
Airworthiness Directives or a FAA Los Angeles Aircraft Certification Office
approved equivalent, unless already accomplished:
48-22-01 49-34-01 52-11-02 55-18-01 56-24-01 59-01-01 77-10-11
48-41-01 49-44-02 52-14-02 56-04-02 56-24-02 59-02-01 80-08-03
48-50-04 49-45-02 53-05-01 56-08-01 57-14-01 59-04-02
48-51-02 50-19-02 54-01-02 56-18-01 58-06-01 64-18-04
49-30-02 51-28-01 55-15-02 56-20-04 58-25-01 64-19-04

A-793
Page 23 of 24
NOTE 17 (Cont’d) The inspections, as applicable, and as required by the following Airworthiness
Directives, shall be accomplished in the manner prescribed in each AD:
49-30-01 50-13-01 51-05-01 74-03-04 83-01-01 93-21-02
49-38-01 50-36-01 53-23-01 79-21-06 83-23-05
49-43-01 50-52-01 57-03-01 81-18-05 92-25-13
Comply with the rework and/or modification required by all other Airworthiness
Directives that are applicable to the engines, propellers, or items or equipment that
are installed in the airplane.
(c) Each airplane must satisfactorily pass an inspection for conformity, possible hidden
damage, corrosion, and for workmanship and materials used in making any repair
and/or alterations.
(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 FAA.
(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.  The aircraft must have a functional check flight.
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 removed from the
aircraft.
(g) A FAA Approved Airplane Flight Manual must be provided for each aircraft.
NOTE 18 Model 240, -1, -2, -3, -4, -5, -6, -7, -8, -11, -12, -13, -14, -15, and –26 aircraft without
outer panel tanks (CVAC Service Bulletin 240-377) are eligible for certification at
41,200 lbs. and 41,790 lbs. take-off gross weight (at S.L. – with water alcohol injection)
when reworked in accordance with the following CVAC Service Bulletins:  240-176A,
240-219, 240-247A, 240-268, and 240-308B.  Aircraft reworked in accordance with the
noted service bulletins are eligible for certification at the following weights:
Maximum Take-Off 41,200 lbs.
Maximum Landing 39,800 lbs.
Zero Fuel Weight 38,900 lbs.
Aircraft reworked in accordance with the noted service bulletins are also eligible for
certification at the following weights without rework or  placard change:
Maximum Take-Off 41,790 lbs.
Maximum Landing 39,800 lbs.
Zero Fuel Weight 38,600 lbs.
Note:  The reduction in zero fuel weight from 38,900 lbs. to 38,600 lbs. will
permit the higher take-off weight.  This limitation is required because of
structural considerations.

A-793
Page 24 of 24
NOTE 18 (Cont’d) The present maximum continuous engine power rating is satisfactory for operation at
41,200 lbs. take-off gross weight.  For operation at 41,790 lbs. take-off gross weight,  it will
be necessary to increase this rating to 1900 BHP.  This increase does not require rework of
the engine, but the serial number of the engine to be used in the higher power configuration
must be cleared through Pratt & Whitney Aircraft Corporation.
Refer to the Model 240-1 Convair-Liner AFM or the appropriate AFM General
Appendix Supplement (A, B, C, D, E, or F) for the installed engine/propeller
combination for certificated weight limitations.
NOTE 19 Model 240-0, -3, -6, -8, -10, -13, -14, -15, and –26 aircraft with outer panel tanks (CVAC
Service Bulletin 240-376) are eligible for certification at 41,790 lbs. take-off gross weight
(at S.L. – with water alcohol injection) when reworked in accordance with the following
CVAC Service Bulletins:  240-176A, 240-219, 240-247A, 240-268, and 240-308B.
Aircraft reworked in accordance with the noted service bulletins are eligible for certification
at the following weights:
Maximum Take-Off 41,790 lbs.
Maximum Landing 39,800 lbs.
Zero Fuel Weight 38,900 lbs.
Refer to the Model 240 Convair-Liner AFM or the appropriate AFM General Appendix
Supplement (A, B, C, D, E, or F) for the installed engine/propeller combination for
certificated weight limitations.
NOTE 20 Model 240-0, -1, -2, -3, -4, -5, -6, -7, -8, -10, -11, -12, -13, -14, -15, and –26 aircraft with
Fuel Dump Installation (CVAC Service Bulletin 240-426) are eligible for certification at
42,500 lbs. take-off gross weight (at S.L. – with water alcohol injection) when reworked in
accordance with the following CVAC Service Bulletins:  240-176A, 240-219, 240-247A,
240-268, 240-308B, and either 240-376 or 240-377.  Aircraft reworked in accordance with
the noted service bulletins are eligible for certification at the following weights:
Without Outer Panel Tanks (CVAC S.B. 240-377)
Maximum Take-Off 42,500 lbs.
Maximum Landing 39,800 lbs.
Zero Fuel Weight 38,100 lbs.
With Outer Panel Tanks (CVAC S.B. 240-376)
Maximum Take-Off 42,500 lbs.
Maximum Landing 39,800 lbs.
Zero Fuel Weight 38,400 lbs.
AFM General Appendix Supplement F
(With or Without Outer Panel Tanks)
Maximum Take-Off 42,400 lbs.
Maximum Landing 39,800 lbs.
Zero Fuel Weight 38,170 lbs.
NOTE:  For operation at gross weights above 41.790 lbs., the aircraft must be
equipped with an operable fuel jettison installation.
Refer to the appropriate Model 240 Convair-Liner AFM General Appendix Supplement (B,
D, E, or F) for the installed engine/propeller combination for certificated weight limitations.
- END -
```

## ADs (55, first 50, in force first)

- [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 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 93-21-02](https://openairdocs.org/ad/93-21-02): Elevators And Rudder · Kelowna Flightcraft R & D 240 Series. Effective Nov 26, 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 91-12-04](https://openairdocs.org/ad/91-12-04): Elevator Hinge Pins · Kelowna Flightcraft R & D 240 Series. Effective Jul 25, 1991
- [AD 83-23-04](https://openairdocs.org/ad/83-23-04): Lock Warning Switch · Kelowna Flightcraft R & D 240 Series with STC SA4025WE or SA4026WE. Effective Nov 28, 1983
- [AD 83-23-05](https://openairdocs.org/ad/83-23-05): Main Door Latching Systems · Kelowna Flightcraft R & D 240 Series. Effective Nov 28, 1983
- [AD 83-01-01](https://openairdocs.org/ad/83-01-01): NLG Axle Fracture · Kelowna Flightcraft R & D 240 Series. Effective Jan 19, 1983
- [AD 81-18-05](https://openairdocs.org/ad/81-18-05): Wing Structure Inspection · Kelowna Flightcraft R & D 240 Series. Effective Nov 15, 1982
- [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 79-21-06](https://openairdocs.org/ad/79-21-06): Elevator Flight Tab Spring Tube · Kelowna Flightcraft R & D 240 Series. Effective Jan 21, 1980
- [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 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 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 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 64-19-04](https://openairdocs.org/ad/64-19-04): Emergency Circuits · Kelowna Flightcraft R & D 240 Series. Effective Sep 7, 1964
- [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 53-05-01](https://openairdocs.org/ad/53-05-01): Propellers Slip Rings · Aero Spacelines 377, 377MG, 377SGT and 6 more
- [AD 74-03-04](https://openairdocs.org/ad/74-03-04): Pilot and Co-pilot Window Frame Castings · Kelowna Flightcraft R & D 240 Series with STC SA1054WE. Effective Feb 4, 1947
- [AD 48-41-01](https://openairdocs.org/ad/48-41-01): Wing Bulkhead Flanges and Stringers · Kelowna Flightcraft R & D 240 Series
- [AD 48-50-04](https://openairdocs.org/ad/48-50-04): Nose Gear · Kelowna Flightcraft R & D 240 Series
- [AD 48-51-02](https://openairdocs.org/ad/48-51-02): Horizontal Tail Surfaces · Kelowna Flightcraft R & D 240 Series
- [AD 49-30-01](https://openairdocs.org/ad/49-30-01): Hub Barrels · Boeing DC-6, DC-6A, DC-6B and 1 more
- [AD 49-30-02](https://openairdocs.org/ad/49-30-02): Augmenter Vanes · Kelowna Flightcraft R & D 240 Series
- [AD 49-34-01](https://openairdocs.org/ad/49-34-01): Cockpit Checklist · Kelowna Flightcraft R & D 240 Series
- [AD 49-38-01](https://openairdocs.org/ad/49-38-01): Nose Gear Landing Struts · Kelowna Flightcraft R & D 240 Series
- [AD 49-43-01](https://openairdocs.org/ad/49-43-01): Augmenter Tube · Kelowna Flightcraft R & D 240 Series
- [AD 49-44-02](https://openairdocs.org/ad/49-44-02): Horizontal Tail · Kelowna Flightcraft R & D 240 Series
- [AD 49-45-02](https://openairdocs.org/ad/49-45-02): Reverse Lock Solenoid Linkage · Kelowna Flightcraft R & D 240 Series
- [AD 50-13-01](https://openairdocs.org/ad/50-13-01): Aileron Hinge · Kelowna Flightcraft R & D 240 Series
- [AD 50-19-02](https://openairdocs.org/ad/50-19-02): Rudder Flight Tab Balance Weight Brackets · Kelowna Flightcraft R & D 240 Series
- [AD 50-36-01](https://openairdocs.org/ad/50-36-01): Nose Strut Cylinder · Kelowna Flightcraft R & D 240 Series
- [AD 50-52-01](https://openairdocs.org/ad/50-52-01): Blades · Boeing DC-6, DC-6A, DC-6B and 4 more
- [AD 51-28-01](https://openairdocs.org/ad/51-28-01): Engine Accessory Section · Kelowna Flightcraft R & D 240 Series
- [AD 52-11-02](https://openairdocs.org/ad/52-11-02): Nacelle · Kelowna Flightcraft R & D 240 Series
- [AD 52-14-02](https://openairdocs.org/ad/52-14-02): Electrical Circuits · Kelowna Flightcraft R & D 240 Series and 340
- [AD 53-23-01](https://openairdocs.org/ad/53-23-01): Nose Landing Gear Clutch Plate · Kelowna Flightcraft R & D 240 Series
- [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
- [AD 56-04-02](https://openairdocs.org/ad/56-04-02): Fuel Supply Lines · Kelowna Flightcraft R & D 240 Series and 340
- [AD 56-18-01](https://openairdocs.org/ad/56-18-01): Generator · Kelowna Flightcraft R & D 240 Series
- [AD 56-20-04](https://openairdocs.org/ad/56-20-04): Fire Seals · Kelowna Flightcraft R & D 240 Series, 340 and 440
- [AD 56-24-01](https://openairdocs.org/ad/56-24-01): Cylinder · Kelowna Flightcraft R & D 240 Series, 340 and 440
- [AD 56-24-02](https://openairdocs.org/ad/56-24-02): Carburetors · Kelowna Flightcraft R & D 240 Series, 340, 440 and 2 more
- [AD 57-03-01](https://openairdocs.org/ad/57-03-01): Main Outboard Landing Gear Fitting · Kelowna Flightcraft R & D 240 Series
- [AD 57-14-01](https://openairdocs.org/ad/57-14-01): Nose Gear · Kelowna Flightcraft R & D 240 Series and 340
- [AD 58-06-01](https://openairdocs.org/ad/58-06-01): Main Landing Gear Axle · Kelowna Flightcraft R & D 240 Series
- [AD 58-25-01](https://openairdocs.org/ad/58-25-01): Elevator Torque Tube · Kelowna Flightcraft R & D 240 Series

All 55: https://openairdocs.org/tcds/A-793/ads.md

## Registered aircraft by registry model (OpenAirDocs)

- [Convair 240](https://openairdocs.org/model/convair-240): 0 aircraft (registry code 2422601)
- [General Dynamics 240](https://openairdocs.org/model/general-dynamics-240): 0 aircraft (registry code 3790202)

## STCs approved under this data sheet (110, first 50)

- [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 SA16CE](https://openairdocs.org/stc/SA16CE): Float Type Fuel Gage Installation - Ground Visual Fuel.. 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 SA3-497](https://openairdocs.org/stc/SA3-497): Throttle reverse lock mechanism.. Sabreliner Aviation LLC
- [STC SA3-500](https://openairdocs.org/stc/SA3-500): General interior arrangement #1(16 passenger). General interior arrangement #2 (17 passenger).. Sabreliner Aviation LLC
- [STC SA3-501](https://openairdocs.org/stc/SA3-501): Typical divan installation (Divan P/N DC3-22021).. Sabreliner Aviation LLC
- [STC SA3-506](https://openairdocs.org/stc/SA3-506): Installation of weather radar antenna mount and radar nose.. Sabreliner Aviation LLC
- [STC SA3-567](https://openairdocs.org/stc/SA3-567): Chair and desk installation - Station 167.. Sabreliner Aviation LLC
- [STC SA3-579](https://openairdocs.org/stc/SA3-579): Rectangular Exit Exhaust Muffler Installation.. Sabreliner Aviation LLC
- [STC SA3-580](https://openairdocs.org/stc/SA3-580): General Interior Configuration - Floor Plan Arrangement #2.. Sabreliner Aviation LLC
- [STC SA3-582](https://openairdocs.org/stc/SA3-582): General interior configuration floor plan arrangement #3.. Sabreliner Aviation LLC
- [STC SA3-583](https://openairdocs.org/stc/SA3-583): General Interior Configuration - Floor Plan #4.. Sabreliner Aviation LLC
- [STC SA3-584](https://openairdocs.org/stc/SA3-584): Forward Lavatory Installation (Sta. 287).. Sabreliner Aviation LLC
- [STC SA3-585](https://openairdocs.org/stc/SA3-585): Rear galley installation (STA 644).. Sabreliner Aviation LLC
- [STC SA3-589](https://openairdocs.org/stc/SA3-589): Removal and Closure of Rear Service Door - Sta. 672.. Sabreliner Aviation LLC
- [STC SA3-590](https://openairdocs.org/stc/SA3-590): Installation Stewart-Warner 940-F24 cabin heater - STA 620.. Sabreliner Aviation LLC
- [STC SA3-601](https://openairdocs.org/stc/SA3-601): Typical swivel seat installation (Hardman Tool & Engineering Co. Seat Model 3004, TSO C-39).. Sabreliner Aviation LLC
- [STC SA3-645](https://openairdocs.org/stc/SA3-645): General interior configuration floor plan #5.. Sabreliner Aviation LLC
- [STC SA3-646](https://openairdocs.org/stc/SA3-646): Navigator chair and desk installation (STA 155).. Sabreliner Aviation LLC
- [STC SA3-648](https://openairdocs.org/stc/SA3-648): Flight Observer Jump Seat Installation - Sta. 109.. Sabreliner Aviation LLC
- [STC SA3-710](https://openairdocs.org/stc/SA3-710): Rear airstair door installation STA 628- 812.. Sabreliner Aviation LLC
- [STC SA3-711](https://openairdocs.org/stc/SA3-711): Closure installation L.H. entrance door (F.S. 638).. Sabreliner Aviation LLC
- [STC SA3-712](https://openairdocs.org/stc/SA3-712): Fabrication and installation of 360 degree swivel seat.. Sabreliner Aviation LLC
- [STC SA3-713](https://openairdocs.org/stc/SA3-713): General interior configuration floor plan #6.. Sabreliner Aviation LLC
- [STC SA3-714](https://openairdocs.org/stc/SA3-714): Utility shower installation - aft cabin.. Sabreliner Aviation LLC
- [STC SA3-734](https://openairdocs.org/stc/SA3-734): Lavatory/vanity installation - station 644.. Sabreliner Aviation LLC
- [STC SA3-735](https://openairdocs.org/stc/SA3-735): General interior configuration floor plan #8.. Sabreliner Aviation LLC
- [STC SA32CE](https://openairdocs.org/stc/SA32CE): Interior General Arrangement, Floor Plan #9.. Sabreliner Aviation LLC
- [STC SA35CE](https://openairdocs.org/stc/SA35CE): Installation of generator overheat indicator.. Sabreliner Aviation LLC
- [STC SA4-1179](https://openairdocs.org/stc/SA4-1179): Outer wing fuel tank installation.. Sabreliner Aviation LLC
- [STC SA7CE](https://openairdocs.org/stc/SA7CE): Cockpit auxiliary heater installation. Sabreliner Aviation LLC
- [STC SA83CE](https://openairdocs.org/stc/SA83CE): Utility avionics rack installation (in radar nose).. Sabreliner Aviation LLC
- [STC SA1054WE](https://openairdocs.org/stc/SA1054WE): Installation of Rolls-Royce model Dart 542-4 engines with Dowty Rotol R245/4-40-4.5/13 propellers and associated modifications to engine mounting, nacelle, empennage, accessories, systems and equipment.. Executive Jet Aircraft Co. LTD. c/o Southeast Aero Tek Inc.
- [STC SA1993NM](https://openairdocs.org/stc/SA1993NM): Installation of a de-icing system on the Rolls Royce RK45524A engine inlet cowl.. ROBERT W. MURRAY
- [STC SA3106NM](https://openairdocs.org/stc/SA3106NM): Installation of a de-icing system externally on the Dowty Rotol  (C) 4CM/71 propeller spinner.. ROBERT W. MURRAY
- [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 SA1048SO](https://openairdocs.org/stc/SA1048SO): Conversion of USAF Model T-29B into the civil Model 240-27 with deviations to TCDS A-793.. Pemco Aeroplex Inc
- [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 SA4-470](https://openairdocs.org/stc/SA4-470): ADF loop.. Vanaero Company
- [STC SA1-392](https://openairdocs.org/stc/SA1-392): 2008X series radome.. Saint-Gobain Performance Plastics Corp
- [STC SA1627SO](https://openairdocs.org/stc/SA1627SO): Conversion of a military model C-131A to Civil Model 240-53 freighter with a Class B cargo compartment.. Associated Design
- [STC SA1890WE](https://openairdocs.org/stc/SA1890WE): Installation of executive interior. Approved for Convair model 240, serial number 160 ONLY.. Kelowna Flightcraft Ltd
- [STC SA13SW](https://openairdocs.org/stc/SA13SW): Installation of ground operated APU.. Signature Flight Support Corporation
- [STC SA2-286](https://openairdocs.org/stc/SA2-286): Installation of three-place divan.. Signature Flight Support Corporation
- [STC SA2-969](https://openairdocs.org/stc/SA2-969): Installation of Lawrence auxiliary power unit in aft baggage compartment for ground operation only.. Signature Flight Support Corporation
- [STC SA2-985](https://openairdocs.org/stc/SA2-985): Installation of high rate discharge fire extinguisher system.. Signature Flight Support Corporation
- [STC SA189SW](https://openairdocs.org/stc/SA189SW): Modification of Convair 240, N618S, to change existing General Electric 2CM-76C4 engine driven DC generators to Jack & Heintz G29-7B, and to add to left engine an auxiliary J & H G29-7B DC generator controlled by Bendix Feeder Fault System... Rockwell Collins Inc
- [STC SA2-1508](https://openairdocs.org/stc/SA2-1508): Modification of CV-240, N618S to incorporate the following changes: Interior arrangement, Generator control system, electrical distribution system, radio, communication and electronic systems, cockpit instrumentation, miscellaneous mechanical installations. Rockwell Collins Inc
- [STC SA4077WE](https://openairdocs.org/stc/SA4077WE): Conversion of military model T29A to model 240-17, T-29B to Model240-27, T29D to Model 240-52 and C131-A to Model 240-53. (240 SERIES 17). Luft Air, Inc

All 110: https://openairdocs.org/tcds/A-793/stcs.md

---
OpenAirDocs.org is an independent research project of [Contrail Labs](https://contraillabs.com/). It is not affiliated with the FAA or the NTSB. Source documents are U.S. government works in the public domain.