# TCDS 1A3: Bellanca Aircraft Inc.

- Type: Type certificate data sheet
- Status: Current
- Holder: Bellanca Aircraft Inc.
- Revision: 40
- Revised: March 5, 2024
- Product: Aircraft, Small Airplane
- Certification basis: CAR 3
- Registered aircraft: 233, by the registry models matched to it (OpenAirDocs)
- Data sheet PDF: https://openairdocs.org/files/sha256/25/ae/25ae14a295cfb1c5b50be60701aae206ad84e9545c652a319fcb543d513fffd6
- FAA DRS: https://drs.faa.gov/browse/excelExternalWindow/DRSDOCID113459699520240320135700.0001
- Page: https://openairdocs.org/tcds/1A3

## Models (7)

As the data sheet lists them.

- 14-19-2
- 17-31TC
- 14-19-3
- 17-30
- 14-19-3A
- 14-19
- 17-31

## What the data sheet says

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

```text
Page No. 1 2 3 4 5 6 7 8 9 10 11 12 13 14 15 16 17 18 
Rev No. 40 35 35 35 38 35 35 35 35 36 35 35 35 35 35 35 35 38 
 
DEPARTMENT OF TRANSPORTATION 
FEDERAL AVIATION ADMINISTRATION 
 
1A3 
Revision 40 
BELLANCA  
AIRCRAFT  
14-19 
14-19-2 
14-19-3 
14-19-3A 
17-30 
17-31 
17-31TC 
 
March 5, 2024 
AIRCRAFT SPECIFICATION NO. 1A3 
 
Type Certificate Holder Bellanca Aircraft, Inc. 
  3620 Sacramento Drive, Suite 100 
  San Luis Obispo, CA  93401 
 
Type Certificate Holder Record Bellanca Aircraft Corp. transferred TC 1A3 to Viking Aviation, 
Inc. on March 26, 1982 
   
  Viking Aviation, Inc. transferred TC 1A3 to Bellanca, Inc. on 
June 11, 1982 
   
  Bellanca, Inc. transferred TC 1A3 to Alexandria Aircraft LLC 
on May 30, 2002 
   
  Alexandria Aircraft LLC . transferred TC 1A3 to Bellanca 
Aircraft, Inc. on March 5, 2024 
 
I - Model 14-19, 4 PCLM (Normal Category), 2 PCLM (Utility Category), Approved September 26, 1949 
 Engine Lycoming O-435-A 
 Fuel 80 minimum grade aviation gasoline 
 Engine limits For all operations, 2550 r.p.m. (190 hp.) 
 Airspeed limits Never exceed 226 m.p.h. (197 knots) True Ind. 
  Maximum structural cruising 167 m.p.h. (145 knots) True Ind. 
  Maneuvering (Normal Category) 115 m.p.h. (100 knots) True Ind. 
  Maneuvering (Utility Category) 124 m.p.h. (108 knots) True Ind. 
  Flaps extended   86 m.p.h.   ( 75 knots)   True Ind. 
  Landing gear extended 167 m.p.h. (145 knots) True Ind. 
  Landing gear operation 125 m.p.h.   (108 knots)   True Ind. 
 C.G. range (landing) Normal Category (+19.9) to (+24.4) at 2600 lb. 
   gear extended) Utility Category (+19.8) to (+24.4) at 2400 lb. 
  Both Categories (+16.4) to (+24.4) at 1800 lb. or less 
  Straight line variation between points given

1A3  Page 2 of 19 
 
1 6 1 8 2 0 2 2
INCHES
2 8 0 0
2 4 0 0
1 6 0 0
1 4 0 0
LB.
FWD.
LIM IT
1 8 0 0
2 0 0 0
2 2 0 0
2 6 0 0
REA R
LIM IT
2 4
 
 
Empty weight C.G. range None 
 Maximum weight Normal Category 2600 lb. 
  Utility Category 2400 lb. 
I - Model 14-19  (con'd) 
 No. of seats 4 (2 at +20, 2 at +53) 
 Maximum baggage  Normal Utility 
                                                                       Category Category 
  Without auxiliary fuel tank 198 lb. (+84) 171 lb. (+84) 
  With empty auxiliary fuel tank 186 lb. (+84) 159 lb. (+84) 
  (item 104) (see loading schedule) 
 Fuel capacity Main wing tanks 40 gal. (+29).  See items 104, 105 and 106 for auxiliary tanks. 
 Oil capacity 12 qt. (-35) 
 Control surface movements Elevator trim tab Up 12° Down 29° 
   (within + 1°) Elevator  Up 22° Down 15° 
  Aileron  Up 20° Down 20° 
   Rudders Right 22° Left 22° 
  Flaps     Down 46° 
 
 Serial Nos. eligible 2000, 2002 thru 4000 
 Required equipment Items 1 or 2, 102, 103, 110(c), 201, 202(a), 204(a) and 401(a) 
 
II - Model 14-19-2, 4 PCLM (Normal Category), Approved January 7, 1957 
 Engine Continental O-470-K 
 Fuel 80/87 minimum grade aviation gasoline 
 Engine limits For all operations, 2600 r.p.m.   (230 hp.) 
 Airspeed limits Never exceed 226 m.p.h. (197 knots) True Ind. 
  Maximum structural cruising 167 m.p.h. (145 knots) True Ind. 
  Maneuvering 115 m.p.h. (100 knots) True Ind. 
  Flaps extended 86 m.p.h. ( 75 knots) True Ind. 
  Landing gear extended 167 m.p.h. (145 knots) True Ind. 
  Landing gear operation 124 m.p.h. (108 knots) True Ind. 
 C.G. range (landing) (+20.5) to (+24.4) at 2700 lb. 
   gear extended) (+16.4) to (+24.4) at 1800 lb. or less 
  Straight line variation between points given

Page 3 of 19 1A3 
 
 
1 6
2 8 0 0
1 8 2 0 22 2 4
INCHES
2 6 0 0
2 4 0 0
2 2 0 0
2 0 0 0
1 8 0 0
LB.
FWD.
LIM IT
REA R
LIM IT
 
 Empty weight C.G. range None 
 
 Maximum weight 2700 lb. 
 No. of seats 4 (2 at +20, 2 at +53) 
 Maximum baggage (see Without auxiliary fuel tank: 198 lb. (+84) 
   loading schedule) With empty auxiliary fuel tank (item 105): 186 lb. (+84)

1A3  Page 4 of 19 
 
II - Model 14-19-2  (cont'd) 
 Fuel capacity Main wing tanks 40 gal. (+29).  See item 105 or item 112 for auxiliary  
  tank and NOTE 1 for data on system fuel. 
 Oil capacity 12 qt. (-35), 7 qt. usable.  See NOTE 1 for data on system oil. 
 Control surface movements Elevator trim tab Up 12° Down 29° 
   (within + 1°) Elevator Up 22° Down 15° 
  Aileron Up 20° Down 20° 
  Rudders Right 22° Left 22° 
  Flaps   Down 46° 
 
 Serial Nos. eligible 4001 thru 4105 
 Required equipment Items 3 or 4, 107, 108, 201, 202(a), 204(a), 401(b) or (c) and 403 
 
III - Model 14-19-3, 4 PCLM (Normal Category), Approved February 20, 1959 
 Engine Continental IO-470-F 
 Fuel 100/130 minimum grade aviation gasoline 
 Engine limits For all operations, 2625 r.p.m. (260 hp.) 
 Airspeed limits Never exceed 226 m.p.h. (197 knots) CAS 
  Maximum structural cruising 167 m.p.h. (145 knots) CAS 
  Maneuvering 115 m.p.h. (100 knots) CAS 
  Flaps extended 110 m.p.h. ( 96 knots) CAS 
  Landing gear extended 167 m.p.h. (145 knots) CAS 
  Landing gear operation 124 m.p.h. (108 knots) CAS 
 C.G. range (landing) (+20.5) to (+24.4) at 2700 lb. 
   gear extended) (+17.5) to (+24.4) at 2200 lb. or less 
  Straight line variation between points given 
 
1 6
2 8 0 0
1 8 2 0 22 2 4
INCHES
2 6 0 0
2 4 0 0
2 0 0 0
1 9 0 0
LB.
FWD.
LIM IT2 1 0 0
2 2 0 0
2 3 0 0
2 5 0 0
2 7 0 0
REA R
LIM IT
 
 
 Empty weight C.G. range None 
 
 Maximum weight 2700 lb. 
 No. of seats 4 (2 at +20, 2 at +53) 
 Maximum baggage 186 lb. (+84).  (See loading schedule). 
 Fuel capacity Main wing tanks 39.2 gal. (+29).  See item 112 for auxiliary tank and NOTE 1  
  for data on system fuel. 
 O il capacity 12 qt. (-35), 7 qt. usable.  See NOTE 1 for data on system oil. 
 Control surface movements Elevator trim tab Up 12° Down 29° 
   (within +1°) Elevator Up 22° Down 15° 
  Aileron Up 20° Down 20° 
  Rudder Right 22° Left 22° 
  Flaps   Down 46° 
 Serial Nos. eligible 4106 thru 4228 
 Required equipment Items 5 or 6, 107, 108, 201(c) or (d), 202(a) or (c), 205(a), (b) or (e)  
  and (c) or (d) or 205(f) and (g), 401(d) and 403 
 
 
IV - Model 14-19-3A, 4 PCLM (Normal Category), Approved March 1, 1963

Page 5 of 19 1A3 
 
 
 Engine Continental IO-470-F 
 Fuel 100/130 minimum grade aviation gasoline 
 Engine limits For all operations, 2625 r.p.m. (260 hp.) 
 Airspeed limits Never exceed 226 m.p.h. (197 knots) CAS 
  Maximum structural cruising 190 m.p.h. (165 knots) CAS 
  Maneuvering 142 m.p.h. (123 knots) CAS 
  Flaps extended 120 m.p.h. (104 knots) CAS 
  Landing gear extended 167 m.p.h. (145 knots) CAS 
  Landing gear operation 140 m.p.h. (122 knots) CAS 
 
 C.G. range (landing) (+19.8) to (+23.0) at 3000 lb. 
   gear extended) (+17.75) to (+23.0) at 2350 lb. or less 
  Straight line variation between points given 
 
1 7 1 9 2 1 2 3
INCHES
3 2 0 0
2 8 0 0
2 0 0 0
1 8 0 0
LB.
FWD.
LIM IT
2 2 0 0
2 4 0 0
2 6 0 0
3 0 0 0
REA R
LIM IT
2 5
 
 
 Empty weight C.G. range None 
 
 Maximum weight 3000 lb. 
 No. of seats 4 (2 at +20, 2 at +53) 
 Maximum baggage 186 lb. (+84).  (See loading schedule). 
 Fuel capacity 58 gal. usable (2 wing tanks 19 gal. each at +29, and 1 auxiliary tank in fuselage  
  20 gal. at +72).  See item 113 for optional auxiliary tanks in outboard wing  
  panels and NOTE 1 for data on system fuel. 
 Oil capacity 12 qt. (-35), 7 qt. usable.  See NOTE 1 for data on system oil. 
 Control surface movements Elevator trim tab Up 7° Down 34.5° 
   (within +1°) Elevator Up 22° Down 15° 
  Aileron Up 20° Down 20° 
  Rudder Right 22° Left 22° 
  Flaps   Down 46° 
 Serial Nos. eligible 4229 thru 4342 
 Required equipment Items 7, 107, 108, 201(c) or (d), 202(a) or (c), 205(f) and (h), 401(e) and 403 
 
V - Model 17-30, 4 PCLM (Normal Category), Approved September 23, 1966 
 Engine Continental IO-520-D 
 Fuel 100/130 minimum grade aviation gasoline 
 Engine limits Takeoff:  2850 r.p.m. (300 hp.) (5 min. maximum) 
  Max. continuous operation:  2700 r.p.m (285 hp.) 
 Airspeed limits Never exceed 226 m.p.h. (197 knots) CAS 
  Maximum structural cruising 190 m.p.h. (165 knots) CAS 
  Maneuvering 142 m.p.h. (123 knots) CAS 
  Flaps extended 120 m.p.h. (104 knots) CAS 
  Landing gear extended 167 m.p.h. (145 knots) CAS 
  Landing gear operation 140 m.p.h. (122 knots)  CAS

1A3  Page 6 of 19 
 
V - Model 17-30  (cont'd) 
 C.G. range (landing) (+19.8) to (+24.0) at 3000 lb. 
   gear extended) (+17.75) at 2400 lb. or less 
  Straight line variation between points given 
 
1 7 1 9 2 1 2 3
INCHES
3 2 0 0
2 8 0 0
2 0 0 0
1 8 0 0
LB.
FWD.
LIM IT
2 2 0 0
2 4 0 0
2 6 0 0
3 0 0 0
REA R
LIM IT
2 5
 
 Empty weight C.G. range None 
 
 Maximum weight 3000 lb.  (See NOTE 4 for 3200 lb. airplanes) 
 No. of seats 4 (2 at +20, 2 at +53) 
 Maximum baggage 186 lb. (+84), 35 lb. min.   (See loading schedule). 
 Fuel capacity 58 gal. usable (2 wing tanks, 19 gal. ea. at +29, and 1 auxiliary tank in  
  fuselage 20 gal. at +72).  See item 113 for optional auxiliary tanks in  
  outboard wing panels and NOTE 1 for data on system fuel. 
 Oil capacity 12 qt. (-41), 6.3 qt. usable.  See NOTE 1 for data on system oil. 
 Control surface movements Elevator trim tab Up  7° Down 34.5° 
   (within +1°) Elevator Up 22° Down 15° 
  Aileron Up 20° Down 20° 
  Rudder Right 22° Left 22° 
  Flaps   Down 46° 
 Serial Nos. eligible 30001 thru 30262 excluding 30004 
 Required equipment Items 8 or 9 or 10 or 11, 101(d) or (f), 107(c) or (d) or (g), 108(b), 110(c),  
  111(a), 201(d), 202(c), 205(f) and (h), 301(c) or 304(b), 302(f) or (g), 401(f) and 403. 
 
VI - Model 17-31TC, 4 PCLM (Normal Category), Approved February 20, 1969 
 Engine Lycoming IO-540-G1E5, with two (2) Rajay Model 315A10-2 Turbochargers  
  per STC SE6WE 
 Fuel 100/130 minimum grade aviation gasoline 
 Engine limits Non turbo charged: all operations 2575 RPM (290 hp.) 
  Turbo charged: all operations 2400 RPM 27.0 in. Hg (250 hp) 
   Turbocharger used only with throttle full open 
   Minimum turbocharger - 2200 RPM 
 Maximum operating 24,000 ft with oxygen 12,000 ft. without oxygen 
   Altitude 
 Airspeed limits Never exceed 226 m.p.h. (197 knots) CAS 
 Below 15,000 ft. Maximum structural cruising 190 m.p.h. (165 knots) CAS 
  Maneuvering 142 m.p.h. (123 knots) CAS 
  Flaps extended 120 m.p.h. (104 knots) CAS 
  Landing gear extended 167 m.p.h. (145 knots) CAS 
  Landing gear operation 140 m.p.h. (122 knots) CAS 
 Above 15,000 ft. 
 Same as below 15,000 ft. 
 except Never exceed 200 m.p.h. (174 knots) CAS 
  Maximum structural cruising 165 m.p.h. (144 knots) CAS 
 C.G. range (landing) (+19.8) to (+24.0) at 3000 lb. 
   gear extended) (+17.75) to (+24.0) at 2400 lb. or less 
  Straight line variation between points given 
 
 
 
 
VI - Model 17-31TC  (cont'd)

Page 7 of 19 1A3 
 
 
1 6 1 8 2 0 2 2
INCHES
3 0 0 0
2 8 0 0
2 4 0 0
2 3 0 0
LB.
FORWA RD
LIM ITS
2 5 0 0
2 6 0 0
2 7 0 0
2 9 0 0
A FT.
LIM ITS
2 4
 
 Empty weight C.G. range None 
 Maximum weight 3000 lb.  (See NOTE 4 for 3200 lb. airplanes) 
 No. of seats 4 (2 at +20, 2 at +53) 
 Maximum baggage 166 lb. max. (+84), 35 lb. min.   (See loading schedule). 
 Fuel capacity 72 gal. usable (2 wing tanks, 19 gal. ea. at +29, and 2 auxiliary tanks in  
`  wing, 17 gal. each at +29). See NOTE 1 for data on unusable fuel. 
 Oil capacity 12 qt. (-42), 9 1/4 qt. usable.  See NOTE 1 for data on undrainable 
  oil. 
 Control surface movements Elevator trim tab Up  7° Down 34.5° 
   (within +1°) Elevator Up 22° Down 15° 
  Aileron Up 20° Down 20° 
  Rudder Left 22° Right 22° 
  Flaps   Down 46° 
 Serial Nos. eligible 31001 thru 31003 
 Required equipment  Items 12, 101(e), 107(e), 107(f) or (g), 108(c), 111(a), 113, 114, 201(e),  
  202(d), 205(b) and (j), 302(g), 304, 401(g) and 403.  Item 404 is  
  required for flight above 12,000 ft. 
 
VII - Model 17-31, 4 PCLM (Normal Category), Approved April 29, 1969. 
 Engine Lycoming IO-540-G1B5 (except IO-540-G1E5 for S/N 32-1 only) 
 Fuel 100/130 minimum grade aviation gasoline 
 Engine limits All operations 2575 RPM (290 hp) 
 Airspeed limits Never exceed 226 m.p.h. (197 knots) CAS 
  Maximum structural cruising   90 m.p.h. (165 knots) CAS 
  Maneuvering 142 m.p.h. (123 knots) CAS 
  Flaps extended 120 m.p.h. (104 knots)  CAS 
  Landing gear extended 167 m.p.h. (145 knots) CAS 
  Landing gear operation 140 m.p.h. (122 knots) CAS 
 C.G. range (landing) (+19.8) to (+24.0) at 3000 lb. 
   gear extended) (+17.75) TO (+24.0) at 2400 lb. or less 
  Straight line variation between points given 
 
1 7 19 2 1 2 3
INCHES
3 0 0 0
2 8 0 0
2 4 0 0
2 3 0 0
LB.
FORWA RD
LIM ITS
2 5 0 0
2 6 0 0
2 7 0 0
2 9 0 0
A FT.
LIM ITS
2 5

1A3  Page 8 of 19 
 
VII - Model 17-31  (cont'd) 
 Empty weight C.G. range None 
 Maximum weight 3000 lb.  (See NOTE 4 for 3200 lb. airplanes) 
 No. of seats 4 (2 at +20, 2 at +53) 
 Maximum baggage 166 lb. max. (+84), 35 lb. min.   (See loading schedule). 
 Fuel capacity 58, 72 or 92 gal. (2 wing tanks, 19 gal. each at +29), plus [item 112 (20 gal. at +72)  
  or item 113 (2-17 gal. each at +29)] or [items 112 and 113 (92 gal.)].  See  
  NOTE 1 for data on unusable fuel. 
 Oil capacity 12 qt. total (-42), 9 1/4 qt. usable.  See NOTE 1 for data on undrainable oil. 
 Control surface movements Elevator trim tab Up  7° Down 34.5° 
   (within -1°) Elevator Up 2 2° Down 15° 
  Aileron Up 20° Down 20° 
  Rudder Left 22° Right 22° 
  Flaps   Down 46° 
 Serial Nos. eligible 32-1 thru 32-14 
 Required equipment Items 12, 101(e), 107(e), 107 (g), 108(c),112 or 113, 111(b), 114, 201(e), 202(d),  
  205(b) and (j), 302(g), 304(a),  401(h) and 403. 
 
Specifications Pertinent to All Models 
 Datum Leading edge of Rib No. 1 (23.5 in. outboard of airplane center line).  For  
  reference:  (1) Datum is 10.75 in. forward of fuselage station 2;  (2) Forward face  
  of firewall is 17.05 in. forward of datum, when aircraft is leveled. 
 Leveling means Lugs at fuselage stations 2 and 3 in cabin on right side (wing spar station). 
 Certification basis Model 14-19: Part 03 of the Civil Air Regulations dated 
   December 15, 1946 
  Model 14-19-2: Part 03 of the Civil Air Regulations dated 
   December 15, 1946 as amended by 03-1 through 03-4 
  Model 14-19-3: Part 03 of the Civil Air Regulations dated 
   December 15, 1946 as amended by 03-1 thru 03-4; 
   plus amendment 3-4 (paragraphs 3.80, 3.84A, 3.85a, 
   3.87, 3.112(c), 3.120 and 3.124(a) only) and 
   amendment 3-6 to CAR 3 dated November 1, 1949 
  Model 14-19-3A: Same as Model 14-19-3 plus amendments 3-7 and 
   3-13 (paragraph 3.74 only) to CAR 3 dated November 1,  
   1949 and amendment 3-2 (paragraph 3.75(c) only) 
   to CAR 3 dated May 15, 1956 
  Model 17-30: Same as Model 14-19-3A 
  Model 17-31: Same as Model 14-19-3A 
  Model 17-31TC: Same as Model 17-31 plus amendment 3-5 paragraph 
   3.638(a) only) to CAR 3 dated May 15, 1956 
  Type Certificate No. 1A3 issued September 26, 1949 
 Production basis None.  Prior to original certification of each aircraft an FAA representative must  
  perform a detailed inspection for workmanship, materials and conformity with 
  the approved technical data, and a check of the flight characteristics. 
 
Equipment: A plus (+) or minus (-) sign preceding the weight of an optional item indicates the net weight change  
  when that item is installed.

Page 9 of 19 1A3 
 
 
 
Propellers and Propeller Accessories 14-19 14-19-2 14-19-3 14-19-3A 17-30 17-31TC 17-31 
1. (a) Propeller - Koppers Aeromatic, hub x       
  model 220-1, blade model 0-74A,        
  Parts list Assembly 4329-1.  In-     
  stalled in accordance with Koppers     
  Co. Adjustment Instructions and     
  Operating Limitations No. 31     
  Pitch settings at 30 in. sta.      
  Low 12.5°      
  Static r.p.m. at maximum permissible     
  throttle setting not over 2500, not      
  under 2450.  No additional tolerance     
  permitted.      
   51 lb. (-58)       
 (b) Koppers Aeromatic Altitude x     
  Control Assembly 4349-L      
   11 lb. (-50)       
2. Propeller - Hartzell controllable     
 (a) Hub model HC-12x20-8, blade model x    
  8428-6        
  Pitch settings at 30 in. sta.      
  Low 9.2°, high 21.8°       
  Diameter not over 78 in., not      
  under 75 in.        
   68 lb. (-58)        
 (b) Hub model HC-12x20-8C, blade model x    
  8433-6        
  Pitch settings at 30 in. sta.      
  Low 11°, high 22°       
  Diameter not over 78 in., not     
  under 76.5 in.       
   61 lb. (-58)  
 (c) Hartzell propeller control x 
   1  lb.  (-6)  
3. Propeller - Hartzell Constant Speed 
 (a) Hub model HC-82XF-1, blade model  x 
  8433-6 
  Pitch settings at 30 in. sta. 
  Low 12-1/2°, high 25-1/2° 
  Diameter not over 78.5 in., not 
  under 78 in. 
   62 lb. (-58) 
 (b) Governor, Woodward D210105 or  x 
  D210340 
    4 lb. (-49)  
 (c) Spinner, Hartzell 835-3  x 
    3 lb. (-58)    
4. Propeller - McCauley Constant Speed 
 (a) Hub model 2A36C18,, blade model  x 
  90M-12 
  Pitch settings at 36 in. sta. 
  Low 10°, high 23° 
  Diameter not over 78 in., not 
  under 76 in. 
   62 lb. (-58)     
  Supplement to Item 401(b) dated  x 
   July 11, 1957 required

1A3  Page 10 of 19 
 
 
Propellers and Propeller Accessories (contd.) 14-19 14-19-2 14-19-3 14-19-3A 17-30 17-31TC 17-31 
 (b) Governor, Woodward D210105 or  x 
  D210345 
   4 lb.  (-49)  
 (c) Spinner and dome kit, McCauley  x 
  AK8053-21 
   4 lb.  (-58)  
5. Propeller - McCauley 
 (a) Hub model B2A36C31, blade model   x 
  90M-8 
  Pitch settings at 36 in. sta. 
  Low 11°, high 27.3° 
  Diameter not over 82 in., not 
  under 80 in. 
   60 lb. (-57.5)  
 (b) Governor, Woodward D210105 or    x 
  D210345 
   4 lb.  (-49.5)  
 (c) McCauley spinner installation   x 
   3 lb.  (-57.5)  
  (1) Kit AK8053-21 (McCauley B-2792) 
   adapter ring or 0752004-5 bulk- 
   head required with hub models 
   in items 5(d) and 5(e) 
  (2) D-2771 spinner installation  
   (eligible with hub models in 
   items 5(d) and 5(e) only) 
 (d) Hub model D2A36C31, blade model   x 
  90M-8 
  Pitch settings at 36 in. sta. 
  Low 11°, high 26.3° 
  Diameter not over 82 in., not 
  under 80 in. 
   60 lb. (-57.5)  
  Revision to item 401(d) dated 
  May 10, 1960, required 
 (e) Hub model D2A36C33, blade model   x 
  90M-8 
  Pitch settings at 36 in. sta. 
  Low 10.8°, high 25.8° 
  Diameter not over 82 in., not 
  under 80 in. 
   60 lb. (-57.5)  
  Revision to item 401(d) dated 
  May 10, 1960, required 
6. Propeller - Hartzell Constant Speed 
 (a) Hub model HC-A2XF-1, blade model   x 
  8433-2 or -4 
  P itch settings at 30 in. sta.  
  Low 14°, high 27° 
  Diameter not over 82 in., not 
  under 80 in. 
   63 lb. (-57)  
  Revision to item 401(d) dated 
  November 24, 1959 required 
 (b) Governor, Woodward D210105 or   x 
  D210340 
   4 lb.  (-49)

Page 11 of 19 1A3 
 
 
 
Propellers and Propeller Accessories (cont'd.)     14-19 14-19-2 14-19-3 14-19-3A 17-30 17-31TC 17-31 
 (c) Spinner, Hartzell 835-13   x 
   4 lb.  (-58)  
7. Propeller - Hartzell Constant Speed 
 (a) Hub model HC-C2YF-1A, blade model   x x 
  8468-4 
  Pitch settings at 30 in. sta. 
  Low 13.4°, high 31° 
  Diameter not over 80 in., not 
  under 80 in. 
   51 lb. (-57)  
 (b) Governor, Woodward H210452G   x x 
   3 lb.   (-49)  
 (c) Spinner and dome - Hartzell 835-23   x x 
   5 lb.  (-58)  
8. Propeller - McCauley Constant Speed 
 (a) Hub model D3A32C90, blade model    x x 
  82NC-4 
  Pitch settings at 30 in. sta. 
  Low 11.7+.2°°, high 28.1°+.5° 
  Diameter not over 78 in., not 
  under 76 in. 
   64 lb. (-63.5)  
 (b) Governor, Woodward Model P210452G    x x 
   3 lb.  (-55)  
 (c) Spinner and dome - McCauley    x x 
  model D3669 or D3867 
   5 lb.  (-64)  
9. Propeller - McCauley Constant Speed 
 (a) Hub model D2A34C58, blade model     x 
  90AT-10 
  Pitch settings at 36 in. sta. 
  Low 8.2+0.1°°, high 27.3°+.5° 
  Diameter not over 80 in., not 
  under 78 in. 
   53 lb. (-63.5)  
  Revision 1 to item 401(f) dated 
  May 18, 1967 required 
 (b) Governor, Woodward Model P210452G     x 
   3 lb.  (-55)  
 (c) Spinner and dome-McCauley     x 
  Model D2771 or D3766 
   4.5 lb. (-64)  
10. Propeller - Hartzell Constant Speed 
 (a) Hub model HC-C3YF-1, blade model     x 
  8468-8R 
  Pitch settings at 30 in. sta. 
  Low 10.0°, high 32.5° 
  Diameter not over 78 in., not 
  under 76 in. 
   76 lb. (-63.5)  
  Revision 7 to item 401(f) dated 
  August 10, 1968 required 
 (b) Governor, Woodward P210452     x 
   3 lb.  (-55)  
 (c) Spinner and dome - Hartzell     x 
  model C3535 
   4 lb.  (-64)

1A3  Page 12 of 19 
 
 
Propellers and Propeller Accessories (cont'd.)     14-19 14-19-2 14-19-3 14-19-3A 17-30 17-31TC 17-31 
11. Propeller - Hartzell Constant Speed 
 (a) Hub model HC-C2YF-1, blade model     x 
  8475-6 
  Pitch settings at 30 in. sta. 
  L ow 11.1°, high 36.2° 
  Diameter not over 78 in., not 
  under 76 in. 
   53 lb. (-63.5)  
  Revision to item 401(f) dated 
  August 10, 1968 required 
 (b) Governor, Woodward Model P210452     x 
   3 lb.  (-55)  
 (c) Spinner and dome - Hartzell     x 
  model C3533 
   4 lb.  (-64)  
12. Propeller - Hartzell Constant Speed 
 (a) Hub model HC-C3YR-1, blade model      x x 
  4 68-6R 
  Pitch settings at 30 in. sta. 
  Low 13°, high 38° 
  Diameter not over 80 in., not 
  under 78 in. 
   75 lb. (-64)  
 (b) Governor, Woodward Model B210460      x x 
    3 lb. (-55)  
 (c) Spinner and dome - Hartzell      x x 
  model C3552 
   4.5 lb. (-64)  
 
Engine and Engine Accessories - Fuel and 
Oil Systems 
101. (a) Starter, Delco-Remy model 1109652 x 
   18 lb. (-21)  
 (b) Starter, Delco-Remy model 1109678  x x x 
   18 lb. (-21)  
 (c) Starter, Delco-Remy model 1109684   x x 
   18 lb. (-21)  
 (d) Starter, Delco-Remy model 1108249     
  or 1109926 
   18 lb. (-21)     x 
   18 lb. (-27)      x 
 (e) Starter-Prestolite model MZ4206      x x 
   18 lb. (-51.5)  
 (f) Starter-Prestolite model MCL6501,     x 
  CMC P/N 634592 
   18 lb. (-27)  
102. Fuel pump, AC Type AH No. 1539722 x 
    3 lb. (-20)  
103. Oil Cooler, Heat Exchangers, Inc. x 
 No. 102C 
    7 lb. (-45) 
104. Auxiliary fuel tank 25 gal. Eligible x 
 only when installed in accordance 
 with Bellanca dwg. 18046 and 18175 
   12 lb. (+77) 
 See NOTE 2(c) for placard required

Page 13 of 19 1A3 
 
 
 
Engines and Engine Accessories-Fuel (cont'd.)      14-19 14-19-2 14-19-3 14-19-3A 17-30 17-31TC 17-31 
 and Oil Systems                               
105. Auxiliary fuel tank 14 gal. Eligible x x 
 only when installed in accordance 
 with Bellanca dwg. 18183 and 18184 
    8 lb. (+70) 
 See NOTE 2(d) for placard required 
106. Auxiliary fuel tanks, 32.5 gal.: 
 One 14 gal. tank  x  
    8 lb. (+70) 
 One 18.5 gal. tank  x 
    9 lb. (+77) 
 eligible only when installed in 
 accordance with Bellanca dwg. 18207 
 and 18199 and Airplane Flight Manual 
 is revised to include pages 4 and 
 4(a) dated July 3, 1951 
 See NOTE 2(e) for placard required 
107. Fuel pumps 
 (a)  Engine-driven, Lear ROMEC  x 
  RD-7420-A1  
    3 lb. (-20)  
 (b) Hand emergency, AN-4009-D2  x 
    3 lb. (+ 2) 
 (c) Electric Auxiliary fuel pump,   x x x 
  Weldon 4020A2A 
    4 lb. (+6.5) 
 (d) Electric auxiliary fuel pump,     x 
  Bendix 480531 
    2 lb. (+18)  
 (e) Engine driven fuel pump, Titan      x x 
  4101B68, Type G6 
   2.5 lb. (+23.5) 
 (f) Electric auxiliary fuel pump,      x 
  Lear ROMEC P2688-D 
    4 lb. (+18) 
 (g) Electric auxiliary fuel pump,     x x x 
  Airborne Mfg. Co. 286-9 
    4 lb. (+18) 
 (h)  Engine-drive, Lear ROMEC      x x 
  RG17980D 
   2.5 lb. (-23.5)  
108. (a) Oil radiator, Continental  x x x 
  Motors P/N 8520912 
    5 lb. (-49)  
 (b ) Oil radiator, GMC Model     x 
  AP13AV10-02 
    5 lb. (-55)  
 (c) Oil radiator, Harrison Radiator      x x 
  Div. GMC, Model AP13AV06-01, 
  P/N 8534108 
    5 lb. (-20.5)  
109. Vacuum pump, Pesco B-11  x x x 
    4 lb. (-20)  
110. Hydraulic pumps 
 (a) New York Air Brake model 67B025  x x x 
    2 lb. (-20)  
 (b) Pesco No. 1P-677  x x x 
    2 lb. (-20)

1A3  Page 14 of 19 
 
 
Engines and Engine Accessories-Fuel (cont'd.) 14-19 14-19-2 14-19-3 14-19-3A 17-30 17-31TC 17-31 
 and Oil Systems 
 (c) E astern Industries model 102-129 
  or 1235HBG 
    2 lb. (-20)  x x x x 
    2 lb. (-26)      x 
111. (a) Dry vacuum pump, Airborne 
  Mechanisms, Model 10-113-A2, 
  113A5 or 200 CW 
    4 lb. (-20)   x x x 
    4 lb. (-26)      x 
 (b) Dry vacuum pump, Airborne 
  Mechanisms Model 200 CCW 
    4 lb. (-26)       x x 
112. Auxiliary fuel tank 20 gal. Installed  x x x x  x 
 in accordance with Bellanca dwg. 19643 
   11 lb. (+72) 
 See NOTE 2(f) for placard required 
   For the 14-19-2 only Flight Manual 
   Supplement dated February 27, 1970 
   is required 
 Revision to item 401(f) dated April 10,     x 
 1968 required 
113. Outboard wing auxiliary fuel tanks:    x x x x 
 (17 gal. each) Installed in accordance 
 with Bellanca dwg. 192500 
   39 lb. (+29) 
 See NOTE 2(g) for placard required 
 Revision to Item 401(e) dated    x 
 April 10, 1968 required 
 Revision to Item 401(f) dated     x 
 May 18, 1967 required 
114. Oil filter, AC. PMA OF-81-A, P/N 
 6437032         x x 
   2.5 lb. (-26)  
 
Landing Gear 
201. Two main wheel-brake assemblies, 
 6.00-6, Type III 
 (S/N prior to 2071)  (+8) x 
 (S/N 2071 thru 4105) (+6) x x 
 (S/N 4106 thru 4342) (+32)   x x 
 (S/N 30001 and up) (+38)     x 
 (S/N 31001 and up) (+38)      x 
 (S/N 32-1 and up)  (+38)       x 
 
 (a) Goodrich model 605MD  x 
  Brake assembly No. D-2-112 
  Wheel assembly No. D-3-105-MD 
   15 lb. 
 (b) Firestone 
  Wheel assembly No. DFA180  x 
    7 lb. (+6) 
  Brake assembly No. CFA252  x 
    3 lb. (+6) 
 (c) Goodrich model 14-1132 
  Wheel assembly No. 3-958   x x 
    7 lb. (+38)

Page 15 of 19 1A3 
 
 
 
Landing Gear (cont'd)  14-19 14-19-2 14-19-3 14-19-3A 17-30 17-31TC 17-31 
  Brake assembly No. 2-747  x x 
    3 lb. (+38) 
  Eligible only with Goodrich master 
  cylinders model 87-87 and Bellanca 
  P/N's 19503-10 Inboard and 19503-20 
  Outboard Rudder Pedal shafts, 
  19503-1 brackets on 19504 Rudder 
  Pedal Torque tubes. 
 (d) Goodyear tubeless PD932-2   x x x 
  Wheel assembly 9532111 or 9532673 
   11 lb. (+38) 
  Bra ke assembly 9532278 or 9532181   x x x 
    6 lb. (+38) 
  Eligible only with Paramount master 
  cylinders, model VHR .750, 
  Bellanca P/N 19588 Inboard and 
  19589 Outboard Rudder Pedal shafts, 
  19592 brackets on 19504 Rudder 
  Pedal Torque tubes for 14-19-3; 
  195268 Inboard and 195272 Outboard 
  Rudder Pedal Shafts for 14-19-3A 
  and 17-30 
 (e) Goodyear tube type PD932-2 wheel 
  assembly 9532522     x x x 
   11 lb. (+38) 
  Brake assembly 9532278 or 9532181     x x x 
    6 lb. (+38) 
 (f) Cleveland Wheel assy. No. 40-75E 
   11 lb. (+38)     x x x 
  Cleveland Brake assy. No. B-30-52M 
   6 lb. (+38)     x x x 
202. Two main wheel tires, 6-ply rating, 
 Type III 
 (S/N prior to 2071) (+8)  x 
 (S/N 2071 thru 4105) (+6) x x 
 (S/N 4106 thru 4342) (+38)   x x 
 (S/N 30001 and up) (+38)     x  
 (S/N 31001 and up) +38)      x x 
 
 (a) 6.00-6 Tires and Tubes x x 
   17 l b.  (+8) 
  6.00-6 Tires and Tubes x x 
   20 lb. (+8) 
 (b) 7.00-6 Tires and Tubes x 
   19 lb. (+6) 
 (c) 6.00-6 Tubeless    x x x 
   20 lb. (+38) 
 (d) 6.00-6 Tires and Tubes     x x x 
   20 lb. (+38) 
204. Tail wheel assembly 
 (a) Firestone model 206-8B, swivel x x 
  6.0 x 2.0 
    3 lb. (+186) 
 (b) Maule model SFS-12, swivel 6.00 x 
  2.50 
    4 lb. (+186) x 
    4 lb. (+181)  x 
  Either (a) or (b) per Bellanca 
  d wg. 18016

1A3  Page 16 of 19 
 
 
Landing Gear (cont'd)   14-19 14-19-2 14-19-3 14-19-3A 17-30 17-31TC 17-31 
 (c) Maule hub and axle model SFS-P8, x 
  General Tire, 8.00, SC per Bellanca 
  dwg. 18222.  Use act. wt. chg. 
 (d) Maule model P-8 hub and tire  x 
    3 lb. (+186) 
205. Nose wheel assembly 6.00-6 Type III 
 (a) Goodrich model D3609, MD-1 wheel   x 
  assembly 
    4 lb. (-40.5)  
 (b) Goodyear PD941-1 wheel assembly 
  9532186 
    5 lb. (-40.5)     x 
    5 lb. (-46.5)       x x x 
 (c) One nose wheel tire, 6-ply and tube   x 
   1 0 lb. (-40.5)  
 (d) One nose wheel tire, 4-ply and tube   x 
    9 lb. (-40.5)  
 (e) Firestone wheel assembly DFA180   x 
    4 lb. (-40.5)  
 (f) Goodyear PD941 wheel assembly 
  9532112  
    5 lb. (-40.5)     x x 
    5 lb. (-46.5)       x 
 (g) One nose wheel tubeless tire, 4-ply   x 
    9 lb. (-40.5)  
 (h) One nose wheel tubeless tire, 6-ply 
  rating, 15 x 6.00-6, Type III 
    9 lb. (-40.5)      x 
    9 lb. (-46.5)       x 
 (i) One nose wheel tube type tire, 
   6-ply        x x x 
    9 lb. (-46.5)  
 (j) Cleveland wheel assy. 40-76C 
   11 lb. (+38)      x x x 
 
Electrical Equipment 
301. Generator 
 (a) 12 v. 25 a.  Delco-Remy 1101882 x 
   16 lb. (-21)  
 (b) 12 v. 25 a.  Delco-Remy 1101892  x 
   16 lb. (-21)  
 (c) 12 v. 50 a.  Delco-Remy 1101912 
   16 lb. (-21)     x x 
   16 lb. (-27)       x 
 
302. Batteries 
 (a) 12 v. 34 a. hr. Bowers B-34 x 
   26 lb. (+156) 
 (b) 12 v. 33 a. hr. Reading R-331 x 
   28 lb. (+156) 
 (c) 12 v. 34 a. hr. Exide 6TAS-9B  x 
   34 lb. (+156) 
 (d) 12 v. 33 a. hr. Exide Type AC-69-1   x 
  wt. 27 lb. plus 6.5 lb. ballast 
   34 lb. (+156)

Page 17 of 19 1A3 
 
 
 
302. Batteries (cont'd)   14-19 14-19-2 14-19-3 14-19-3A 17-30 17-31TC 17-31 
 (e) 12 v. 33 a. hr. Exide type AC-66   x 
  wt. 27 lb. plus 6.5 lb. ballast 
   34 lb. (+156) 
 (f) 12 v. 34 a. hr. Exide Type AC-78 
  wt. 28 lb. plus 5.5 lb. ballast 
   34 lb. (+156)   x 
   28 lb. (+86.5) or (+19.5)    x 
   28 lb. (+86.5)     x x x 
 (g) 12 v. 35 a. hr. Rebat R-35 
   28 lb. (+86.5)     x x x 
  (Model 17-30, S/N 30210 an up) 
303. G.E. 4509 landing light and 4503 taxi 
 light in left wing per Bellanca dwg. 
 18182 (dwg. 19235 for 14-19-3; dwg. 
 192513 for 14-19-3A and 17-30) x x x x x x x 
    2 lb. (+9) 
304. Alternator¦ 
 (a) 12 v. 40 a. Prestolite ALE-8406      x x 
   13 lb. (-52.5)  
 (b) 12 v. 50a. Prestolite ALY 8402-10A     x 
   13 lb. (-27.0)  
  (S/N 30202 and up) 
305. Supplementary Lights 
 Whelen Strobe Lights A429, A430     x x x 
 Installed per Bellanca dwg. 197263 
    2 lb. (+185) 
 
Interior Equipment 
401. (a) FAA Approved Airplane Flight  x 
  Manual dated February 6, 1950 
 (b) FAA Approved Airplane Flight  x 
  Manual dated January 17, 1957 
  (for aircraft with two valve 
  fuel system) 
 (c) FAA Approved Airplane Flight  x 
  Manual revised August 7, 1959 
  (for aircraft with one valve 
  fuel system) 
 (d) FAA Approved Airplane Flight   x 
  Manual dated September 1, 1959    x 
 (e) FAA Approved Airplane Flight 
  Manual dated March 1, 1963 with 
  Revision No. 1 dated July 25, 1963 
  (this AFM eligible only until 
  November 22, 1969), or FAA 
  Approved Airplane Flight Manual 
  dated August 11, 1966 with Revision 
  No. 5 dated October 26, 1968 
 (f) FAA Approved Airplane Flight     x 
  Manual dated September 21, 1966 
  with Revision No. 4 dated 
  August 28, 1968 
 (g) FAA Approved Airplane Flight      x 
  Manual dated February 20, 1969 
 (h) FAA Approved Airplane Flight       x 
  Manual dated April 29, 1969

1A3  Page 18 of 19 
 
 
Interior Equipment (cont'd)  14-19 14-19-2 14-19-3 14-19-3A 17-30 17-31TC 17-31 
402. Flares (5 one-minute, International) x x x x x x x 
   17 lb. (+86) 
403. Stall warning indicator, Safe Flight  x x x x x x 
 Model R 
404. Oxygen System, Sky-Ox Kit      x x 
 SK1001-4b-TV, Installed in accordance  
 with Bellanca dwg. 196795 
   45 lb. (+86) 
 
NOTE 1. 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.  A copy of  
  the approved loading instructions should be posted inside the baggage compartment at all times.           
                                                       
  The Model 14-19-2 certificated weight empty and corresponding center of gravity location must include 
  unusable fuel of 25 lb. at +29 (included in total fuel capacity), and unusable oil of 9 lb.  
  at -35 (included in total oil capacity). 
                                                       
  The Models 14-19-3 and 14-19-3A certificated weight empty and corresponding center of gravity  
  location must include unusable fuel of 25 lb. at +29 and unusable oil of 9 lb. at -35.                                     
                                                       
  The Model 17-30 certificated empty weight and corresponding center of gravity location must include  
  unusable fuel of 25 lb. at +29 ad unusable oil of 11 lb. at -41. 
 
  For the Models 14-19-3A and 17-30 with optional outboard wing panel auxiliary fuel tanks add  
  unusable fuel of 24 lb. to the above certificated weights for these models. 
 
  The Model 17-31TC certificated empty weight and corresponding center of gravity location must include  
  unusable fuel of 26 lb. at +29 and undrainable oil of 3.7 lb. at -42. 
 
  The Model 17-31 certificated empty weight and corresponding center of gravity location must include  
  unusable fuel of 26 lb. at +29 (item 113) and 1 lb. at +72 (item 112) and undrainable oil of 3.0 lb. at -42. 
 
NOTE 2. The following placards must be displayed in addition to those listed in the limitations section of the Airplane  
  Flight Manual: 
 
  (a) In front of and in clear view of the pilot: 
   (1) Models 14-19 and 14-19-2 
    "This airplane must be operated in compliance with operating limitations in 
    the FAA Approved Airplane Flight Manual." 
   (2) Models 14-19-3, 14-19-3A and 17-30 
    "This airplane must be operated as a normal category airplane in compliance 
    with the approved Airplane Flight Manual." 
 
  (b) On left side of pilot's storm window: 
   Models 14-19 and 14-19-2 
    "Do not open above 110 m.p.h." 
 
  (c) On or adjacent to the auxiliary fuel tank selector valve when item 104 auxiliary 
   f uel tank is installed: 
   (1) "Auxiliary tank, 25 gal. - Use in level flight only." 
   (2) "Caution:  use fuel from only one tank at a time and keep valves in 'OFF' 
    position when not in use." 
 
  (d) On or adjacent to the auxiliary fuel tank selector valve, when item 105 auxiliary 
   fuel tank is installed: 
   (1) "Auxiliary tank, 14 gal. - Use in level flight only." 
   (2) "Caution: (for two valve fuel system) - use fuel from only one tank at a time 
    and keep valve in 'OFF' position when not in use."

Page 19 of 19 1A3 
 
 
 
  (e) On or adjacent to fuel tank selector valve, when item 106 auxiliary fuel tanks are 
   installed: 
   (1) "Auxiliary tanks - Use in level flight only - 14 gal. rear, 18.5 gal. 
    auxiliary." 
   (2) "Caution:  use fuel from only one tank at a time and keep valves in 'OFF' 
    position when not in use."  (Required for two valve fuel system only). 
  (f) On or adjacent to the fuel tank selector valve when item 112, auxiliary fuel tank 
   is installed: 
   "Auxiliary tank 20 gal. - use in level flight only." 
 
  (g) On or adjacent to the fuel tank selector valve when item 113, outboard wing 
   auxiliary fuel tanks are installed: 
   "Left auxiliary tank 17 gal. - use in level flight only.  Right auxiliary tank 17 
   gal. - use in level flight only.  Fuselage auxiliary tank 20 gal. - use in level 
   flight only.  The fuel remaining in the tank when the gage reads zero cannot be 
   used safely in flight." 
 
NOTE 3. No life limited structural components. 
 
NOTE 4. The following airplanes may be operated at the weights and center of gravity ranges shown below  
  when Bellanca Kit No. SK-1024 is installed. 
 
  Model 17-30  Serial Nos. 30001 thru 30262 
  Model 17-31  Serial Nos. 32-1  thru 32-14 
  Model 17-31TC Serial Nos. 31001 thru 31003 
 
  C.G. Range (Landing  (+20.6) to (+24.0) at 3200 lb. 
    gear extended)  (+17.75) to (+24.0) at 2400 lb. or less 
       Straight line variation between points given 
  Empty wt. C.G. range None 
  Maximum weight  3200 lb. 
  No. of seats   4 (2 at +20, 2 at +53) 
  Maximum baggage  Model  17-30:   186 lb. max. (+84), 35 lb. min. 
                    Models 17-31 and 17-31TC:  166 lb. max. (+84), 35 lb. min. 
                    (See Loading Schedule) 
 
1 6
3 2 0 0
1 8 2 0 22 2 3
INCHES A FT OF DA TUM
3 0 0 0
2 8 0 0
2 6 0 0
2 2 0 0
1 7 1 9 2 1 2 4
2 4 0 0
W EIGHT
(LBS.)
 
 
 
NOTE 5.   Model 17-30, Serial Number 30004 as originally approved under Type Certificate number 1A3 is now converted to Model 
17-30ATC, Serial Number 30004 and approved under Type Certificate number A18CE  
 
 
 
END
```

## ADs (23, in force first)

- [AD 2022-03-15](https://openairdocs.org/ad/2022-03-15): Fuel Quantity Indicator · Garmin G3X Touch Electronic Flight Instrument System (STC SA01899WI or SA02658SE). Effective Mar 21, 2022
- [AD 2014-20-12](https://openairdocs.org/ad/2014-20-12): Fuselage · Alexandria 14-19-3A, 17-30, 17-30A and 4 more. Effective Nov 12, 2014
- [AD 2008-05-11](https://openairdocs.org/ad/2008-05-11): Muffler and tailpipe assemblies · Alexandria 17-30, 17-30A, 17-31 and 2 more. Effective Apr 8, 2008
- [AD 2006-03-08](https://openairdocs.org/ad/2006-03-08): Vacuum pumps · Aero Advantage 14-19, 14-19-2, 14-19-3 and 299 more. Effective Mar 10, 2006
- [AD 2005-01-19](https://openairdocs.org/ad/2005-01-19): Mode S transponders · GARMIN International GTX 330D, GTX 330, GTX 33D and 830 more. Effective Feb 23, 2005
- [AD 98-21-21 R1](https://openairdocs.org/ad/98-21-21-R1): Electric Inflatable Door Seals · Cessna 17-30, 17-30A, 17-31 and 267 more. Effective May 1, 2000
- [AD 96-18-07](https://openairdocs.org/ad/96-18-07): Nose Landing Gear Drag Strut Brackets · Alexandria 17-30, 17-30A, 17-31 and 3 more. Effective Oct 25, 1996
- [AD 90-02-17](https://openairdocs.org/ad/90-02-17): Landing Gear Fitting Assemblies · Alexandria 14-19-3, 14-19-3A, 17-30 and 5 more. Effective Feb 5, 1990
- [AD 87-11-01 R1](https://openairdocs.org/ad/87-11-01-R1): Fuel Caps & Drains · Alexandria 17-30, 17-30A, 17-31 and 3 more. Effective Aug 28, 1987
- [AD 86-25-06](https://openairdocs.org/ad/86-25-06): Wing Main and Auxiliary Fuel Tanks · Alexandria 17-30, 17-30A, 17-31 and 3 more. Effective Dec 22, 1986
- [AD 77-22-02](https://openairdocs.org/ad/77-22-02): Nose Landing Gear Engine Mount · Alexandria 14-19-3, 14-19-3A, 17-30 and 1 more. Effective Nov 2, 1977
- [AD 76-08-04](https://openairdocs.org/ad/76-08-04): Wood Deterioration · Alexandria 14-19, 14-19-2, 14-19-3 and 7 more. Effective Sep 9, 1976
- [AD 75-11-06](https://openairdocs.org/ad/75-11-06): Check Valve · Alexandria 17-31, 17-31A, 17-31ATC and 1 more. Effective Jun 25, 1975
- [AD 72-13-03](https://openairdocs.org/ad/72-13-03): Fuel Boost Pump Circuit · Alexandria 17-30. Effective Jun 20, 1972
- [AD 72-01-01](https://openairdocs.org/ad/72-01-01): Engine Flex Hose Assemblies · Alexandria 14-19-2, 14-19-3, 14-19-3A and 1 more. Effective Dec 31, 1971
- [AD 71-10-01](https://openairdocs.org/ad/71-10-01): Fuel Leakage · Alexandria 17-30. Effective May 8, 1971
- [AD 69-12-04](https://openairdocs.org/ad/69-12-04): Stabilizer Strut Clevis · Alexandria 14-19-3A and 17-30. Effective Jun 13, 1969
- [AD 68-23-08](https://openairdocs.org/ad/68-23-08): Horizontal Tail Surface · Alexandria 14-19-3A and 17-30. Effective Nov 22, 1968
- [AD 63-06-02](https://openairdocs.org/ad/63-06-02): Rudder Bellcrank · Alexandria 14-19, 14-19-2, 14-13 and 3 more. Effective Mar 19, 1963
- [AD 51-16-02](https://openairdocs.org/ad/51-16-02): Trim Tab Modification · Alexandria 14-19, 14-19-2, 14-19-3 and 1 more
- [AD 53-16-01](https://openairdocs.org/ad/53-16-01): Elevator Trim Tab Looseness · Alexandria 14-19, 14-19-2, 14-19-3 and 1 more
- [AD 76-23-03 R1](https://openairdocs.org/ad/76-23-03-R1) (historical): Exhaust System · Alexandria 17-30, 17-30A, 17-31 and 1 more. Effective Nov 7, 1986
- [AD 75-20-06](https://openairdocs.org/ad/75-20-06) (historical): Vertical Tubes · Alexandria 14-19-3A, 17-30, 17-31 and 4 more. Effective Sep 26, 1975

## Registered aircraft by registry model (OpenAirDocs)

- [Bellanca 17-30](https://openairdocs.org/model/bellanca-17-30): 83 aircraft (registry codes 1220432, 1250020)
- [Bellanca 14-19-3](https://openairdocs.org/model/bellanca-14-19-3): 57 aircraft (registry codes 3080106, 1250012)
- [Bellanca 14-19-2](https://openairdocs.org/model/bellanca-14-19-2): 49 aircraft (registry code 3080104)
- [Bellanca 14-19](https://openairdocs.org/model/bellanca-14-19): 30 aircraft (registry codes 3080102, 1250010)
- [Bellanca 17-31](https://openairdocs.org/model/bellanca-17-31): 5 aircraft (registry codes 1220434, 1250030)
- [Downer 14-19-3](https://openairdocs.org/model/downer-14-19-3): 4 aircraft (registry code 3080126)
- [Bellanca 14-19-3A](https://openairdocs.org/model/bellanca-14-19-3a): 2 aircraft (registry code 1250013)
- [Downer 14-19-3A](https://openairdocs.org/model/downer-14-19-3a): 2 aircraft (registry code 3080128)
- [Downer 14-19-2](https://openairdocs.org/model/downer-14-19-2): 1 aircraft (registry code 3080124)
- [Bellanca 17-31TC](https://openairdocs.org/model/bellanca-17-31tc): 0 aircraft (registry codes 1220436, 1250033)
- [Bellanca/Biemond 14-19](https://openairdocs.org/model/bellanca-biemond-14-19): 0 aircraft (registry code 1220403)
- [Downer 14-19](https://openairdocs.org/model/downer-14-19): 0 aircraft (registry code 3080122)

## STCs approved under this data sheet (180, first 50)

- [STC SA01800SE](https://openairdocs.org/stc/SA01800SE): Fabrication and installation of new or replacement of  existing instrument panel lights dimmer control.. TCW Technologies, LLC
- [STC SA01861SE](https://openairdocs.org/stc/SA01861SE): Fabrication and installation of Landing Light Controller. TCW Technologies, LLC
- [STC SA12406WI](https://openairdocs.org/stc/SA12406WI): Installation of a Garmin AXIS Flight Display System. Garmin International Inc.
- [STC SA04652CH](https://openairdocs.org/stc/SA04652CH): To allow use of 100R grade aviation fuel meeting Swift Fuel, LLC specification. Swift Fuels LLC
- [STC SA02636SE](https://openairdocs.org/stc/SA02636SE): Installation of Garmin GPS 175 Navigation System and GNX 375 Navigation System with ADS-B In/Out Transponder.. Garmin International Inc.
- [STC SA02019SE-D](https://openairdocs.org/stc/SA02019SE-D): Installation of Garmin Model GTN 625/635/650; 725/750 Navigation System. Garmin International Inc.
- [STC SA800EA](https://openairdocs.org/stc/SA800EA): Installation of Whelen Anti-Collision, Position, or Anti-Collision/Position  Light System, and applicable associated power supplies. Whelen Aerospace Technologies
- [STC SA00079NY](https://openairdocs.org/stc/SA00079NY): Installation of Airwolf remote mounted engine oil filter kit AFC-K008 on single and multi engine fixed wing light aircraft incorporating Teledyne Continental reciprocating engines of 450 horsepower or less.. Airwolf Filter Corporation
- [STC SA01005DE](https://openairdocs.org/stc/SA01005DE): Installation of a EarthX ETX900-TSO Lithium battery. EarthX Inc.
- [STC SA00081NY](https://openairdocs.org/stc/SA00081NY): Installation of Iceman Aviation Supplies, Inc. Carburetor Ice Detector.. Alcor LLC
- [STC SA5581SW](https://openairdocs.org/stc/SA5581SW): Installation of ALCOR true-flow/ totalizer system. Alcor LLC
- [STC SA02738CH](https://openairdocs.org/stc/SA02738CH): Installation of L-3 Communications Avionics Systems. Acron Aviation Inc.
- [STC SA04046CH PAGE 1](https://openairdocs.org/stc/SA04046CH%20PAGE%201): Installation of L-3 GENESIS  (TM) Electronic Standby Instrument System (ESI-500/MAG-500). Acron Aviation Inc.
- [STC SA7965SW](https://openairdocs.org/stc/SA7965SW): Application of fabric and polyurethane finishing system.. Shady Aviation LLC
- [STC SA04378CH](https://openairdocs.org/stc/SA04378CH): Installation of an engine modified per STC SE04349CH. SureFly Partners Ltd.
- [STC SA02594SE](https://openairdocs.org/stc/SA02594SE): SkyView HDX Instrumentation and Autopilot System manufactured. Dynon Avionics
- [STC SA01757WI](https://openairdocs.org/stc/SA01757WI): To allow the use of UL91 or UL94 (minimum) grade aviation fuel. Swift Fuels LLC
- [STC SA04568CH](https://openairdocs.org/stc/SA04568CH): Installation of the uAvionix tailBeaconX, a tail mounted position light with integrated Automatic Dependent Surveillance - Broadcast (ADS-B) Out and 1090MHz Mode-S transponder functionality. uAvionix Corporation
- [STC SA01375AT](https://openairdocs.org/stc/SA01375AT): Installation of an adapter ring, P/N J1001-1, and fuel cap assembly (usher type), P/N Uo03,. Bellanca Aircraft Incorporated
- [STC SA4503NM](https://openairdocs.org/stc/SA4503NM): Remove original cloth covering and install Ceconite covering. Ceconite Division of Poly-Fiber Inc.
- [STC SA02658SE](https://openairdocs.org/stc/SA02658SE): Installation of Garmin GI 275 Multi-Function Display System. Garmin International Inc.
- [STC SA02571SE](https://openairdocs.org/stc/SA02571SE): Installation of Garmin G500/G600 TXi Integrated Avionics System (Primary Flight Display, Multi-Function Display, and Engine Indicating System Display).. Garmin International Inc.
- [STC SA01899WI](https://openairdocs.org/stc/SA01899WI): Installation of Garmin G3X Touch Electronic Flight Instrument System. Garmin International Inc.
- [STC SA02019WI](https://openairdocs.org/stc/SA02019WI): Installation of the Trig Avionics TX56, TX56A, TX57, or TX57A VHF Nav-Com Radio.. Peregrine
- [STC SA01435LA](https://openairdocs.org/stc/SA01435LA): Installation of engines modified with Firewall Forward Technologies LLC modified camshaft. Centri-Lube Technologies LLC
- [STC SA00756DE](https://openairdocs.org/stc/SA00756DE): Installation of Automatic Dependent Surveillance  Broadcast (ADS-B) Out Equipment using a Trig Avionics TT22 Transponder and an approved Global Positioning System (GPS) Position Sensor. Peregrine
- [STC SA04776NY](https://openairdocs.org/stc/SA04776NY): The HIPEC Covering and Finishing System must be performed and maintained. HIPEC Aircraft Coatings Inc.
- [STC SA02444AK](https://openairdocs.org/stc/SA02444AK): Approval of the L-3 Communications NGT 9000/9000R ADS-B system installed. ADS-B Technologies LLC
- [STC SA01818WI](https://openairdocs.org/stc/SA01818WI): Installation of Garmin G5 Electronic Flight Instrument. Garmin International Inc.
- [STC SA11174SC PAGE 1](https://openairdocs.org/stc/SA11174SC%20PAGE%201): Installation of BendixKing by Honeywell KSN 770 and KSN 765 WAAS LPV approach capable nav/comm systems. Honeywell International Inc (Bendix King)
- [STC SA10822SC](https://openairdocs.org/stc/SA10822SC): Installation of EFD1000 Primary Flight Display. Aspen Avionics Inc.
- [STC SA00401BO](https://openairdocs.org/stc/SA00401BO): Installation of a SkyTrax100B UAT receiver. Avidyne Corporation
- [STC SA2511NM](https://openairdocs.org/stc/SA2511NM): Installation of inflatable door seal.. TALCO Aviation Corp.
- [STC SA00410BO](https://openairdocs.org/stc/SA00410BO): Installation of an AV-30-C Multi-Mode Indicator. uAvionix Corporation
- [STC SA01831WI](https://openairdocs.org/stc/SA01831WI): To allow the use of UL91 (minimum) grade aviation fuel. Petersen Aviation Inc
- [STC SA10236SC](https://openairdocs.org/stc/SA10236SC): Installation of a GDC 31 Roll Steering Converter. DAC International Inc
- [STC SA02268CH](https://openairdocs.org/stc/SA02268CH): Installation of Airwolf Filter Corp. Air Oil Separator. Airwolf Filter Corporation
- [STC SA01714WI](https://openairdocs.org/stc/SA01714WI): Installation of a Garmin transponders: (a) GTX 330/330D/33/33D with ADS-B Out functionality; (b) GTX 335/335R/345/345R with ADS-B Out and In functionality; or (c) GTX 335R/345R with ADS-B Out functionality in select airplanes installed with G950/G1000 systems.. Garmin International Inc
- [STC SA03286CH](https://openairdocs.org/stc/SA03286CH): Install an electronic engine ignition system. Electroair Acquisition Corporation
- [STC SA04032CH](https://openairdocs.org/stc/SA04032CH): Install rocker switch assemblies. Electroair Acquisition Corporation
- [STC SA00344BO PAGE 1](https://openairdocs.org/stc/SA00344BO%20PAGE%201): Installation of Parmetheus Plus LED PAR36 and PAR46 taxi and landing lights.. Whelen Aerospace Technologies
- [STC SA615EA](https://openairdocs.org/stc/SA615EA): Installation of a Whelen Anti-Collision Strobe Light System as replacement for originally installed anti-collision lights.. Whelen Aerospace Technologies
- [STC SA00744DE](https://openairdocs.org/stc/SA00744DE): Installation of the Automatic Dependent Surveillance  Broadcast (ADS-B) Out Equipment using a Trig Avionics TT31 Transponder and an approved position sensor. Peregrine
- [STC SA00765DE](https://openairdocs.org/stc/SA00765DE): Installation of Automatic Dependent Surveillance  Broadcast (ADS-B) Out functionality using the BendixKing KT74 Transponder and qualified position sensor. Peregrine
- [STC SA04165NY](https://openairdocs.org/stc/SA04165NY): Installation of Latitude Technologies Skynode S200 Satcom system must be performed. Latitude Technologies Corporation
- [STC SA01435SE](https://openairdocs.org/stc/SA01435SE): Installation of J.P. Instruments (JPI) Primary Engine Data Management System. J. P. Instruments
- [STC SA02153LA-D PAGE 1](https://openairdocs.org/stc/SA02153LA-D%20PAGE%201): Installation of Garmin G600 Primary Flight Display (PFD) and Multifunction Display (MFD) System. Garmin International Inc.
- [STC SA02503AK](https://openairdocs.org/stc/SA02503AK): Installation of AMSAFE State of the Art Restraint System (SOARS) inflatable restraints. AMSAFE Inc.
- [STC SA02013CH](https://openairdocs.org/stc/SA02013CH): Installation of Avidyne Corporation Traffic Advisory System (TAS). Avidyne Corporation
- [STC SA01835WI](https://openairdocs.org/stc/SA01835WI): Installation of Trig Avionics TY-96 or TY-97 VHF Communications Radio. Peregrine

All 180: https://openairdocs.org/tcds/1A3/stcs.md

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