# TCDS A-737: STOL Aviation LLC

- Type: Type certificate data sheet
- Status: Current
- Holder: STOL Aviation LLC
- Revision: 9
- Revised: October 31, 2007
- Product: Aircraft, Small Airplane
- Certification basis: CAR 4a
- Registered aircraft: 78, by the registry models matched to it (OpenAirDocs)
- Data sheet PDF: https://openairdocs.org/files/sha256/7d/d2/7dd20048f232c40b88085566b88a5ffdfda11efe62c221c8d5315538caa9aca4
- FAA DRS: https://drs.faa.gov/browse/excelExternalWindow/F5F8D40CE0A21B66862574C6005F05E1.0001
- Page: https://openairdocs.org/tcds/A-737

## Models (4)

As the data sheet lists them.

- S-1A-90F
- S-1A
- S-1A-85F
- S-1A-65F

## 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 
Rev. No. 9 9 9 9 9 9 9 9 
 
DEPARTMENT OF TRANSPORTATION 
FEDERAL AVIATION ADMINISTRATION 
A-737 
 │ Revision 9 
 │ INTERSTATE 
S-1A 
S-1A-65F 
S-1A-85F 
S-1A-90F 
 
 │ October 31, 2007  
 
AIRCRAFT SPECIFICATION NO. A-737 
 
Type Certificate Holder STOL Aviation LLC 
  c/o Downs Rachlin Martin 
  P.O. Box 191 
  Lebanon, NH 03766 
 
Type Certificate Ownership Record Interstate Aircraft and Engineering Corporation transferred ownership of Aircraft 
  Type Certificate No. 737 to Harlow Aircraft Company on July 23, 1945. 
 
  Harlow Aircraft Company transferred ownership of Aircraft Type Certificate 
  No. 737 to Call Aircraft Company on July 15, 1950. 
 
  Call Aircraft Company transferred owners hip of Aircraft Type Certificate No. 737 
  to Nikiski Marine Corporation on May 14, 1969. 
 
  Nikiski Marine Corporation transferred ownership of Aircraft Type Certificate 
  No. 737 to Arctic Aircraft Company, Inc., on May 15, 1970. 
 
  Arctic Aircraft Company, Inc., transfe rred ownership of Aircraft Type Certificate 
  No. 737 to Interstate Engineering & Ty pe Design Company, Inc., on June 23, 1999. 
 
  Interstate Engineering & Type Design Compan y, Inc., transferred ownership of Aircraft  
  Type Certificate No. 737 to STOL Aviation LLC, on October 31, 2007. 
 
 
I - Model S-1A, 2 PCLM (Normal Category), Approved February 26, 1941 
 
 Engine Continental A-65-8, Engine Type Certificate No. 205 
 
 Fuel 73 min. octane aviation gasoline 
 
 Engine limits For all operations, 2300 rpm (65 hp) 
 
 Airspeed limits Level flight or climb 103 mph (90 knots) TIAS 
  Glide or dive  139 mph (121 knots) TIAS 
 
 Propeller limits Static rpm at maximum permissible throttle setting: 
    Not over 2200, not under 1900.  No additional tolerance permitted. 
  Diameter:  Not over 76 in., not under 72 in.  No further reduction permitted. 
 
 C.G. range (+9.3) to (+19.6).  When larger ve rtical tail surfaces in accordance with Interstate 
  Aircraft and Engineering Corpora tion Drawings No. D-3-3002 and No. G-3-3006 
  are installed, rear limit may be (+20.3). 
 
 Empty weight C.G. range (+13.9) to (+14.4) for standard airplane. 
  (+13.9) to (+15.3) with larger vertical surfaces. 
  When empty weight C.G. falls within pe rtinent range, computation of critical fore 
  and aft C.G. positions is unnecessary.  Ranges are not valid for non-standard  
  arrangements except as noted.

A-737, Rev. 9 Page 2  
 
 
 
 Maximum weight 1200 lb.  When larger vertical tail surfaces in accordance with Interstate Aircraft and 
  Engineering Corporation Drawings No . D-3-3002 and No. G-3-3006 are installed, 
  maximum weight is 1250 lb. 
 
 No. of seats 2 (one at +7 and one at +37) 
 
 Maximum baggage 40 lb. (+70) 
 
 Fuel capacity 15 gal. (-18) 
 
 Oil capacity 4 qt. (-38.2) 
 
 Control surface movements Elevator 30° Up 30°  Down  
  Elevator  tab 23.5° Up  29°  Down 
  Ailerons 20° Up  19.5°  Down 
  Rudder 30° right and left from centerline 
 
 Serial Nos. (S/N) eligible 2 and up 
 
 Required equipment In addition to the pertinent basic required equipment as prescribed in the applicable 
  airworthiness regulations (see Certifica tion basis), the following items of equipment 
  must be installed in the aircraft fo r certification:  Items 1(a), 201, and 202. 
 
 
II - Model S-1A-65F, 2 PCLM (Normal Category), Approved October 1, 1941 
 (Same as Model S-1A except fo r powerplant and engine mount.) 
 
 Engine Franklin 4AC-176-B2, Engine Type Certificate No. 221 
 
 Fuel 73 min. octane aviation gasoline 
 
 Engine limits For all operations, 2200 rpm (65 hp) 
 
 Airspeed limits Level flight or  climb  103 mph (90 knots)  TIAS 
  Glide or dive  139 mph (121 knots)  TIAS 
 
 Propeller limits Static rpm at maximum permissible throttle setting: 
    Not over 2120, not under 2020.  No additional tolerance permitted. 
  Diameter:  Not over 76 in., not under 72 in.  No further reduction permitted. 
 
 C.G. range (+9.3) to (+19.6).  When larger ve rtical tail surfaces in accordance with Interstate 
  Aircraft and Engineering Corpora tion Drawings No. D-3-3002 and No. G-3-3006 
  are installed, rear limit may be (+20.3). 
 
 Empty weight C.G. range (+13.9) to (+14.4) for standard airplane. 
  (+13.9) to (+15.3) with larger vertical surfaces. 
  When empty weight C.G. falls with in pertinent range, computation of  
  critical fore and aft C.G. positions is unnecessary.  Ranges are not  
  valid for non-standard arrangements except as noted. 
 
 Maximum weight 1200 lb.  When larger vertical tail surfaces in accordance with Interstate Aircraft and 
  Engineering Corporation Drawings No . D-3-3002 and No. G-3-3006 are installed, 
  maximum weight is 1250 lb. 
 
 No. of seats 2 (one at +7 and one at +37) 
 
 Maximum baggage 40 lb. (+70) 
 
 Fuel capacity 15 gal. (-18) 
 
 Oil capacity 5 qt. (-43.5)

Page 3 A-737, Rev. 9 
 
 Control surface movements Elevator 30° Up 30°  Down  
  Elevator  tab 23.5° Up 25°  Down 
  Ailerons 21° Up 22°  Down 
  Rudder 30° right and left from centerline 
 
 Serial Nos. (S/N) eligible 2 and up 
 
 Required equipment In addition to the pertinent basic required equipment as prescribed in the applicable 
  airworthiness regulations (see Certifica tion basis), the following items of equipment 
  must be installed in the aircraft fo r certification:  Items 1(c), 201, and 202. 
 
 
III - Model S-1A-85F, 2 PCLM (Normal Category), Approved January 5, 1942 
  (Same as Model S-1A-65F S/N 180 and up except fo r wing, control surfaces, fuselage, and powerplant.) 
 
 Engine Franklin 4AC-199-D2, Engine Type Certificate No. 226 
 
 Fuel 73 min. octane aviation gasoline 
 
 Engine limits For all operations, 2500 rpm (85 hp) 
 
 Airspeed limits Level flight or  climb  117 mph (102 knots)  TIAS 
  Glide or dive  158 mph (137 knots)  TIAS 
 
 
 Propeller limits Range 1:  Static rpm at maximum permissible throttle setting: 
      Not over 2350, not under 2250.  No additional tolerance permitted. 
    Diameter:  Not over 76 in., not under 74 in. 
      No further reduction permitted. 
 
  Range 2:  Static rpm at maximum permissible throttle setting: 
      Not over 2480, not under 2380.  No additional tolerance permitted. 
    Diameter:  Not over 72 in., not under 70 in. 
      No further reduction permitted. 
 
 C.G. range (+9.9) to (+20.3) 
 
 Empty weight C.G. range (+14.2) to (+17.1).  When empty weight C.G. falls within this range,  
  computation of critical fore and af t C.G. positions is unnecessary.  Range  
  is not valid for non-standard arrangements. 
 
 Maximum weight 1300 lb. 
 
 No. of seats 2 (one at +7 and one at +37) 
 
 Maximum baggage 40 lb. (+70) 
 
 Fuel capacity 15 gal. (-18) 
 
 Oil capacity 5 qt. (-43.5) 
 
 Control surface movements Elevator 30° Up 29°  Down  
  Elevator  tab 24° Up 29°  Down 
  Ailerons 19.5° Up 20.5°  Down 
  Rudder 30° right and left from centerline 
 
 Serial Nos. (S/N) eligible 180 and up provided ailer ons are balanced and wing, control surfaces, fuselage, 
  and powerplant conform to technical data defining Model S-1A-85F on approved 
  drawing list.

A-737, Rev. 9 Page 4  
 
 Required equipment In addition to the pertinent basic required equipment as prescribed in the applicable 
  airworthiness regulations (see Certifica tion basis), the following items of equipment 
  must be installed in the aircraft for certification:  Items 1(d), 201, 202, and 601. 
 
 
IV - Model S-1A-90F, 2 PCLM (Normal Category), Approved January 5, 1942 
  (Same as Model S-1A-85F except for powerplant and fuel grade.) 
 
 Engine Franklin 4AC-199-E2, Engine Type Certificate No. 226 
 
 Fuel 80 min. octane aviation gasoline 
 
 Engine limits For all operations, 2500 rpm (90 hp) 
 
 Airspeed limits Level flight or  climb  117 mph (102 knots)  TIAS 
  Glide or dive  158 mph (137 knots)  TIAS 
 
 Propeller limits Static rpm at maximum permissible throttle setting: 
    Not over 2275, not under 2175.  No additional tolerance permitted. 
  Diameter:  Not over 72 in., not under 70 in.  No further reduction permitted. 
 
 C.G. range (+9.9) to (+20.3) 
 
 Empty weight C.G. range (+14.2)  to (+17.1).  When empty weight C.G. falls within this range, 
  computation of critical fore and af t C.G. positions is unnecessary.  Range 
  is not valid for non-standard arrangements. 
 
 Maximum weight 1300 lb. 
 
 No. of seats 2 (one at +7 and one at +37) 
 
 Maximum baggage 40 lb. (+70) 
 
 Fuel capacity 15 gal. (-18) 
 
 Oil capacity 5 qt. (-43.5) 
 
 Control surface movements Elevator 30° Up 29°  Down 
  Elevator  tab 21.5° Up 29°  Down 
  Ailerons 19.5° Up 20.5°  Down 
  Rudder 30° right and left from centerline 
 
 Serial Nos. (S/N) eligible 180 and up provided ailer ons are balanced and wing, control surfaces, fuselage, 
  and powerplant conform to technical data defining Model S-1A-90F on approved 
  drawing list. 
 
 Required equipment In addition to the pertinent basic required equipment as prescribed in the applicable 
  airworthiness regulations (see Certifica tion basis), the following items of equipment 
  must be installed in the aircraft for certification:  Items 1(d), 201, 202, and 601. 
 
 
Specifications Pertinent to All Models 
 
 Datum Wing leading edge 
 
 Leveling means Fuselage tube at door sill 
 
 Certification basis Aircraft Type Certificate No. 737 
 
  Model S-1A :  Part 04 of the Civil Air Regulations effective November 1, 1937, 
  and amendments in effect on March 20,  1940.  Date of Application for Type 
  Certificate March 20, 1940.

Page 5 A-737, Rev. 9 
 
  Model S-1A-65F :  Part 04 of the Civil Air Regulations effective November 1, 1937, 
  and amendments in effect on October 15, 1940.  Date of Application for Type 
  Certificate October 15, 1940. 
 
  Models S-1A-85F and S-1A-90F :  Part 04 of the Civil Air Regulations as amended to 
  April 1, 1941, and additional amendments in effect on October 23, 1941.  Date of 
  Applications for Type Certificate October 23, 1941. 
 
 
 Production basis None.  Prior to original certifi cation of each aircraft manufactured subsequent 
  to April 2, 1943, a CAA or FAA repres entative must perform a detailed inspection 
  for workmanship, material s, and conformity with the approved technical data, and 
  a check of the flight characteristics. 
 
Equipment: A plus (+) or minus (-) sign preceding the we ight of an optional item indicates the net weight 
  change when that item is installed. 
 
  Approval for the installation of all items of equipment listed herein has been obtained by the 
  aircraft manufacturer except those items preceded by an asterisk (*).  This symbol denotes 
  that approval has been obtained by someone ot her than the aircraft manufacturer.  An item so 
  marked may not have been manufactured under a CAA or FAA monitored or approved quality 
  control system and, therefore, its conformity  with CAA or FAA approved technical data must 
  be determined if the item is not identif ied by a CAA Form ACA-186, FAA Form 186, FAA 
  Form 8130-3, FAA PMA, or other evidence of CAA or FAA conformity inspection or 
  production approval. 
 
Propellers and Propeller Accessories 
 
 1. Propeller 
  (a) Wood (fixed or adjustable pitch) and Continental A3746 hub assembly 15.4 lb. (-56.5) 
   (Model S-1A only) 
  (b) Wood (fixed or adjustable pitch) (Model S- 1A with Item 101(a) engine only) 11 lb. (-56.5) 
  (c) Wood (fixed or adjustable pitch) (Model S-1A-65F only) 11 lb. (-57.5) 
  (d) Wood (fixed or adjustable pitch) (Models S-1A-85F & S-1A-90F) 13 lb. (-58) 
 
 2. Propeller  
  (a) McCauley 1A90/CH or 1A90/CF fixed pitch metal, 25.4 lb. (-56.5) 
   Propeller Type Certificate No. 842, 
   and Continental A3746 hub assembly (Model S-1A only) 
   with the following limits: 
   Static rpm at maximum permissible throttle setting: 
     Not over 2200, not under 1900.  No additional tolerance permitted. 
   Diameter:  not over 76 in., not under 72 in.  No further reduction permitted. 
  (b) McCauley 1A90/CF fixed pitch metal, Propeller Type Certificate No. 842 21 lb. (-56.5) 
   (Model S-1A with Item 101(a)  or Item 101(d) engine only) 
   with the following limits: 
   When installed on Item 101(a) engine: 
   Static rpm at maximum permissible throttle setting: 
     Not over 2200, not under 1900.  No additional tolerance permitted. 
   Diameter:  not over 76 in., not under 72 in.  No further reduction permitted. 
   When installed on Item 101(d) engine: 
   Static rpm at maximum permissible throttle setting: 
     Not over 2375, not under 2275.  No additional tolerance permitted. 
   Diameter:  not over 73 in., not under 71.5 in.  No further reduction permitted. 
 
 *3. Propeller - Sensenich M74CK fi xed pitch metal, Propeller Type Certificate No. 1P2 21 lb. (-56.5) 
  (Model S-1A with Item 101(a) engine only) 
  with the following limits: 
  Static rpm at maximum permissible throttle setting: 
    Not over 2200, not under 1900.  No additional tolerance permitted. 
  Diameter:  Not over 74 in., not under 72. 5 in.  No further reduction permitted.

A-737, Rev. 9 Page 6  
 *4. Propeller - fixed pitch wood and Con tinental A3746 hub assembly 15.4 lb. (-56.5) 
  (Model S-1A with Item 101*(c) engine only) 
  with the following limits: 
  Static rpm at maximum permissible throttle setting: 
    Not over 2200, not under 2000.  No additional tolerance permitted. 
  Diameter:  Not over 74 in., not under 72 in.  No further reduction permitted. 
 
 5. Propeller spinner installation  
  (a) Spinner installation in accordance with Inte rstate Aircraft and Engineering 0.3 lb. (-59.9) 
   Corporation Drawing No. B-6259 (Model S-1A with Item 1(a), Item 2(a),  
   or Item *4 propeller only)  
  (b) Spinner installation in accordance with Inte rstate Aircraft and Engineering 0.3 lb. (-60.9) 
   Corporation Drawing No. B-6256 (Model S-1A-65F only)  
  (c) Spinner installation in accordance with Inte rstate Aircraft and Engineering 0.3 lb. (-61.4) 
   Corporation Drawing No. B-6256 (Models S-1A-85F and S-1A-90F)  
 
Engines and Engine Accessories - Fuel and Oil System 
 
 101. Engine 
  (a) Continental A-65-8F, Engine Type Certificate No. 205 +1 lb. (-55) 
   (Model S-1A only) 
   with limits unchanged from Contin ental A-65-8 engine as installed 
   on Model S-1A (Item 1(b), Item 2(b), or Item *3 propeller required) 
  (b) Franklin 4AC-199-E3, Engine Type Certificate No. 226 +7 lb. (-36.1) 
   (Model S-1A-90F only) 
   with limits unchanged from Frank lin 4AC-199-E2 engine as installed 
   on Model S-1A-90F 
  *(c)  Continental C75-8, Engine Type Certificate No. 233 +7 lb. (-44.25) 
    (Model S-1A only) 
    with the following limits: 
    For all operations, 2275 rpm (75 hp) 
    Fuel:  73 min. octane aviation gasoline 
    (Item *4 propeller required) 
  (d) Continental C90-8F, Engine Type Ce rtificate No. 252 Use actual weight change 
   (Model S-1A only) 
   with the following limits: 
   For all operations, 2475 rpm (90 hp) 
   Fuel:  80 min. octane aviation gasoline 
   (Item 2(b) propeller required) 
   Installation of this engine requi res fuel system revisions and engine 
   cowl modifications as outlined in approved Call Aircraft Company 
   technical data. 
 
 102. Starter - 6 volt or 12 volt, Auto-Lite MBG or MZ  16 lb. (-33) 
  (Model S-1A-90F with Item 101(b) engine only) 
  (Item 301(a) 6 volt battery or Item  301(b) 12 volt battery and Item 305(a) 
  6 volt wind-driven generator, Item 305(b) 12 volt wind-driven generator, or 
  Item 308 6 volt or 12 volt engine-dri ven generator to match voltage rating 
  of starter required) 
 
 103. Carburetor air filter in accordance with Intersta te Aircraft and Engineering Neglect weight change 
  Corporation Drawing No. D-6221 
  (Models S-1A-65F, S-1A-85F, and S-1A-90F) 
 
 104. Cabin heater in accordance with Inters tate Aircraft and Engineering 1 lb. (-39) 
  Corporation Drawing No. K-6041 (Model S-1A only)  
  or in accordance with Interstate Aircraft and Engineering Corporation 
  Drawing No. K-6087 (Models S-1A -65F, S-1A-85F, and S-1A-90F)

Page 7 A-737, Rev. 9 
 
Landing Gear and Floats 
 
 201. Two main wheel/brake assemblies a nd tires - Firestone (Shinn) 29 lb. (-1.6) 
  6C5WB or 6C5WFB 6.00 - 6 wheels with brakes and Firestone 
  6.00 - 6, 2-ply tires 
 
 202. Steerable tail wheel and tire - Firestone  6 x 2.00 solid tail wheel/tire 3 lb. (+174.4) 
  assembly in accordance with Interstate Aircraft and Engineering 
  Corporation Drawing No. D-5099 
 
 203. Wheel fairings in accordance with Inters tate Aircraft and Engineering 5 lb. (-1.6) 
  Corporation Drawing No. D-5112 and inner cutout cover plates in 
  accordance with Interstate Aircraft and Engineering Corporation 
  Drawing No. A-5090 
 
 204. Two main wheel replacement skis - Federal SC-2  Use actual weight change 
  (Eligible provided the propeller installation meets the minimum 
  9-in. ground clearance requirement specified by § 04.611 of 
  CAR Part 04 as amended to April 1, 1941) 
 
Electrical and Radio Equipment 
 
 301. Battery installation 
  (a) Battery - 6 volt, Willard Type SYR- 7-3 (Pacific Airmotive No. 4209), 10 lb. (-23) 
   and box in accordance with Interstate Aircraft and Engineering  
   Corporation Drawings No. D-8036 and No. A-8037 
  (b) Battery - 12 volt, Reading Model R24L, and box in accordance 28 lb. (+13) 
   with Interstate Aircraft and Engineering Corporation 
   Drawing No. D-8102 
 
 302. Position light installation 
  (a) Position lights - Grimes Model B tail and wing lights, and wiring, 2.7 lb. (+58.2) 
   in accordance with Interstate Aircraft and Engineering Corporation 
   Drawings No. R-0006, No. D-3087, and No. A-8037 
   (Models S-1A and S-1A-65F with original vertical tail surfaces) 
   (Item 301(a) 6 volt battery or Item 301(b) 12 volt battery to match 
   voltage rating of installed bulbs required) 
  (b) Position lights - Grimes Model A tail li ght and Grimes Model B wing 2.7 lb. (+58.6) 
   lights, and wiring, in accordance with Interstate Aircraft and Engineering 
   Corporation Drawings No. R-0014, No. D-3-3002,  No. A-8037, No. 
   B-8038, and No. B-8041 
   (Models S-1A and S-1A-65F with larger vertical tail surfaces, and 
   Models S-1A-85F and S-1A-90F) 
   (Item 301(a) 6 volt battery or Item 301(b) 12 volt battery to match 
   voltage rating of installed bulbs required) 
 
 303. Antenna installation 
  (a) Trailing - reel, in accordance with Interstate Aircraft and Engineering 4 lb. (+37) 
   Corporation Drawing No. B-8041 
  (b) Overhead - fixed, in accordance with In terstate Aircraft and Neglect weight change 
   Engineering Corporation Drawing No. B-8043 
  (c) Overhead - fixed, with Air Associates AR-6 loading coil, in Neglect weight change 
   accordance with Interstate Aircraft and Engineering Corporation 
   Drawing No. D-8069 
  (d) Belly - fixed, in accordance with Interstate Aircraft and Engineering 1 lb. (+49) 
   Corporation Drawing No. D-8064 
  (e) Whip - Air Associates Model AR-7, in accordance with Interstate 2 lb. (+47) 
   Aircraft and Engineering Corporation Drawing No. B-8049 
 
 304. Radio installation 
  (a) Receiver - Air Associates Model BR-3,  in accordance with Interstate 7 lb. (+11) 
   Aircraft and Engineering Corporation Drawing No. B-8048 
 
  (b) Receiver-Transmitter - American Aircra ft Model AAR-7 receiver and 16 lb. (+15.9) 
   Model AAT-5 transmitter, in accord ance with Interstate Aircraft and 
   Engineering Corporation Drawing No. D-8051

A-737, Rev. 9 Page 8  
  (c) Receiver-Transmitter - Air Associates Model BR-3T, in accordance with 12 lb. (-10.6) 
   Interstate Aircraft and Engi neering Corporation Drawing No. R-8070 
  (d) Receiver-Transmitter - Air Associates Model BR-3T, in accordance with 12 lb. (+9.4) 
   Interstate Aircraft and Engi neering Corporation Drawing No. R-8100 
 
 305. Wind-driven generator installation in  accordance with Interstate Aircraft  
  and Engineering Corporation Drawing No. D-8072 
  (a) Wind-driven generator - 6 volt, Champion Model W612 12 lb. (-25) 
   (Item 301(a) 6 volt battery required) 
  (b) Wind-driven generator - 12 volt, Champion Model W128 12 lb. (-25) 
   (Item 301(b) 12 volt battery required) 
 
 306. Instrument panel light installation - 6 vo lt or 12 volt, 2 Western Auto #E6317 0.5 lb. (-8) 
  dash lights and 1 Pacific Airmotive Grif-Ho instrument light, in accordance 
  with Interstate Aircraft and Engi neering Corporation Drawings No. A-8037 
  and No. D-8073 
  (Item 301(a) 6 volt battery and Item  305(a) 6 volt wind-driven generator, 
  or Item 301(b) 12 volt battery and either Item 305(b) 12 volt wind-driven 
  generator or Item 308 12 volt engine -driven generator to match voltage 
  rating of installed bulbs required) 
 
 307. Landing light installation - 12 volt, U.S.  Army Air Corps Type A6A 4.5 lb. (+8) 
  with Type A19 12 volt, 240 watt bulb in accordance with Interstate 
  Aircraft and Engineering Corporation Drawing No. D-8074 
  (Item 301(b) 12 volt battery and either Item 305(b) 12 volt wind-driven 
  generator or Item 308 12 volt e ngine-driven generator required) 
 
 308. Engine-driven generator - 6 volt or 12 vo lt, Auto-Lite Model GDY or GAS 12 lb. (-32.5) 
  (Model S-1A-90F with Item 101(b) engine only) 
  (Item 301(a) 6 volt battery or Item 301(b) 12 volt battery to match 
  voltage rating of generator required) 
 
Miscellaneous (not listed above) 
 
 601. Lead ballast in accordance with Interstate Ai rcraft and Engineering Weight as required (+190) 
  Corporation Drawing No. D-1262 
  (Models S-1A-85F and S-1A-90F) 
 
 
NOTE 1. A current weight and balance report including a list of the equipment included in the certificated empty weight, and 
  loading instructions when necessary must be provided for each aircraft at the time of original certification. 
 
NOTE 2. The following placards must be displayed in plain view a nd installed in the appropriate locations.  If the aircraft is 
  approved for night flight, the interior placards  must be suitably lighted during night operations. 
 
  (a) On the instrument panel of each aircraft approved for night flight: 
   "SOLO NIGHT FLYING FROM FRONT SEAT ONLY" 
  (b) On the front of the baggage compartment: 
   "BAGGAGE COMPARTMENT 
   MAXIMUM CAPACITY 40 LB." 
 
 
…END…
```

## ADs

None name its models.

## Registered aircraft by registry model (OpenAirDocs)

- [Interstate S-1A](https://openairdocs.org/model/interstate-s-1a): 66 aircraft (registry code 1850202)
- [Interstate S-1A-90F](https://openairdocs.org/model/interstate-s-1a-90f): 6 aircraft (registry code 1850208)
- [Interstate S-1A-65F](https://openairdocs.org/model/interstate-s-1a-65f): 5 aircraft (registry code 1850204)
- [Interstate S-1A-85F](https://openairdocs.org/model/interstate-s-1a-85f): 1 aircraft (registry code 1850206)
- [Callair S-1A](https://openairdocs.org/model/callair-s-1a): 0 aircraft (registry code 1850210)
- [Callair S-1A-65F](https://openairdocs.org/model/callair-s-1a-65f): 0 aircraft (registry code 1850212)
- [Callair S-1A-85F](https://openairdocs.org/model/callair-s-1a-85f): 0 aircraft (registry code 1850214)
- [Callair S-1A-90F](https://openairdocs.org/model/callair-s-1a-90f): 0 aircraft (registry code 1850216)
- [Security National Acft S1-A](https://openairdocs.org/model/security-national-acft-s1-a): 0 aircraft (registry code 0620303)

## STCs approved under this data sheet (52, first 50)

- [STC SA04837NY](https://openairdocs.org/stc/SA04837NY): Installation of AeroLED's Holdings, LLC., position lights, navigation lights, strobe lights and beacon lights. AeroLED's Holdings, LLC
- [STC SA04652CH](https://openairdocs.org/stc/SA04652CH): To allow use of 100R grade aviation fuel meeting Swift Fuel, LLC specification. Swift Fuels LLC
- [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 SA00081NY](https://openairdocs.org/stc/SA00081NY): Installation of Iceman Aviation Supplies, Inc. Carburetor Ice Detector.. Alcor LLC
- [STC SA7965SW](https://openairdocs.org/stc/SA7965SW): Application of fabric and polyurethane finishing system.. Shady Aviation LLC
- [STC SA01240SE](https://openairdocs.org/stc/SA01240SE): Installation of secondary voltage indication system. Visual Instruments LLC
- [STC SA01757WI](https://openairdocs.org/stc/SA01757WI): To allow the use of UL91 or UL94 (minimum) grade aviation fuel. Swift Fuels LLC
- [STC SA4503NM](https://openairdocs.org/stc/SA4503NM): Remove original cloth covering and install Ceconite covering. Ceconite Division of Poly-Fiber Inc.
- [STC SA01967WI](https://openairdocs.org/stc/SA01967WI): Use of GAMI G100UL High Octane Unleaded Avgas. General Aviation Modifications Inc.
- [STC SA04776NY](https://openairdocs.org/stc/SA04776NY): The HIPEC Covering and Finishing System must be performed and maintained. HIPEC Aircraft Coatings Inc.
- [STC SA01831WI](https://openairdocs.org/stc/SA01831WI): To allow the use of UL91 (minimum) grade aviation fuel. Petersen Aviation Inc
- [STC SA02268CH](https://openairdocs.org/stc/SA02268CH): Installation of Airwolf Filter Corp. Air Oil Separator. Airwolf Filter Corporation
- [STC SA00344BO PAGE 2](https://openairdocs.org/stc/SA00344BO%20PAGE%202): Installation of Parmetheus Plus LED PAR36 and PAR46 taxi and landing lights.. Whelen Aerospace Technologies
- [STC SA00433NY](https://openairdocs.org/stc/SA00433NY): Installation of Airwolf remote mounted engine oil filter model AFC-500 or AFC-600 on multi engine fixed wing light aircraft incorporating Franklin reciprocating engines of 450 horsepower or less.. Airwolf Filter Corporation
- [STC SA02212AK](https://openairdocs.org/stc/SA02212AK): Replacement of existing landing and/or taxi light reflector and bulbs with high intensity discharge (HID) lighting systems. Seaplanes North LLC
- [STC SA02428SE](https://openairdocs.org/stc/SA02428SE): Installation of an Air Stream Switch for an electric time recording device on non-pressurized aircraft. Henry F Rogers/David E Polley
- [STC SA10077SC](https://openairdocs.org/stc/SA10077SC): Installation of push-button starter system.. Hartzell Engine Technologies, LLC
- [STC SA00478CH](https://openairdocs.org/stc/SA00478CH): Installation of Cooper Superflite 102 Fabric.. Aviation Products Systems Inc.
- [STC SA4305WE](https://openairdocs.org/stc/SA4305WE): Installation of GAR-AERO wheel adapters and tundra type tires on the main landing gear. Seaplanes North LLC
- [STC SA02283SE PAGE 1](https://openairdocs.org/stc/SA02283SE%20PAGE%201): Installation of Electronics International Inc. Glass Panel Engine Monitor (with In Flight Data) CGR-30P. Electronics International Inc.
- [STC SA02402SE PAGE 1](https://openairdocs.org/stc/SA02402SE%20PAGE%201): Installation of Electronics International Inc. Glass Panel Engine Monitor (with In-Flight Data) CGR-30C. Electronics International Inc.
- [STC SA02428AK](https://openairdocs.org/stc/SA02428AK): Installation of a hydraulically actuated ski drag assembly. Northern Airframes LLC
- [STC SA01026SE](https://openairdocs.org/stc/SA01026SE): Improved fuel gascolator assembly.. Steve's Aircraft
- [STC SA2693NM](https://openairdocs.org/stc/SA2693NM): Installation of Electronics International digital volt/amp gauges and accessories.. Electronics International Inc.
- [STC SA01988SE](https://openairdocs.org/stc/SA01988SE): Installation of Electronics International Inc. Glass Panel Engine Monitor (with In-Flight Data) MVP-50P.. Electronics International Inc.
- [STC SA593CH](https://openairdocs.org/stc/SA593CH): Install Champion SlickSTART magneto booster system.. Champion Aerospace LLC
- [STC SA02033AT](https://openairdocs.org/stc/SA02033AT): Modification to install an air-oil separator to prevent oil from being aspirated from the engine breather line.. M-20 Oil Separators LLC
- [STC SA4005NM](https://openairdocs.org/stc/SA4005NM): Precise Flight Inc. Pulselite Control System. Precise Flight Inc
- [STC SA1355WE](https://openairdocs.org/stc/SA1355WE): Installation of fiberglass cowling.. STOL Aviation LLC c/o Tom Csatari
- [STC SA573AL](https://openairdocs.org/stc/SA573AL): Install Cleveland wheel assembly 40-28 and Cleveland brake assembly30-18.. STOL Aviation LLC c/o Tom Csatari
- [STC SA2683NM](https://openairdocs.org/stc/SA2683NM): Installation of Precise Flight, Inc. stand-by vacuum system (SVS). Precise Flight Inc
- [STC SA01944CH](https://openairdocs.org/stc/SA01944CH): Modify airplane to fly on unleaded automotive gasoline, 87 minimum antiknock index, per ASTM Specification D-439 or D-4818 of any volatility class, A through E, or 82UL AVGAS per ASTM D-6227.. Experimental Aircraft Association Inc.
- [STC SA743GL](https://openairdocs.org/stc/SA743GL): Superseded by STC SA01944CH.  Modify airplane to fly on unleaded automotive gasoline, 87 minimum antiknock index.. EAA Aviation Foundation
- [STC SA8075SW](https://openairdocs.org/stc/SA8075SW): Installation of fiberglass covering. (M-62 SERIES PT-19) (G-73 SCHWEIZER). Razorback Fabrics Inc
- [STC SA1008WE](https://openairdocs.org/stc/SA1008WE): Installation of Poly-Fiber covering material.. Poly-Fiber Inc.
- [STC SA489EA](https://openairdocs.org/stc/SA489EA): Installation of ARP Inc. carburetor ice detection system. Aircraft & Rotorcraft Products (ARP) Inc
- [STC SA2687NM](https://openairdocs.org/stc/SA2687NM): Installation of Truboplus/ Electronics Int'l gauges and switches.. Aero Manufacturing Inc.
- [STC SA4724NM](https://openairdocs.org/stc/SA4724NM): Installation of Cleveland brakes.. Machen Inc
- [STC SA1626NM PAGE 1](https://openairdocs.org/stc/SA1626NM%20PAGE%201): Installation of Electronics Int'l Digital EGT/CHT Instruments and accessories. (201 Series). Electronics International
- [STC SA5755NM](https://openairdocs.org/stc/SA5755NM): Installation of a propeller anti theft device.. Davis Ray G
- [STC SA2350NM PAGE 1](https://openairdocs.org/stc/SA2350NM%20PAGE%201): Installation of Electronics International Inc digital carburetor/outside air temperature gauges. Electronics International
- [STC SA4624NM](https://openairdocs.org/stc/SA4624NM): Installation of F. Atlee Dodge springs 2097 and 2127 to replace bungee cords on ski equipped airplanes.. F Atlee Dodge Aircraft Service
- [STC SA4302NM](https://openairdocs.org/stc/SA4302NM): Installation of Electronics Int'l digital automatic engine analyzer.. Electronics International
- [STC SA3862NM PAGE 1](https://openairdocs.org/stc/SA3862NM%20PAGE%201): Installation of Electronics International Primary TIT/EGT/CHT instruments, remote switches and associated accessories.. Electronics International
- [STC SA2190NM PAGE 1](https://openairdocs.org/stc/SA2190NM%20PAGE%201): Installation of electronics International Digital Volt/Amp Gauges and Accessories.. Electronics International
- [STC SA1351WE](https://openairdocs.org/stc/SA1351WE): Replace existing fabric on wings, fuselage, empennage, and/or control surfaces, with Ceconite101 material. (262A Series -12). Ceconite Inc
- [STC SA4-1210](https://openairdocs.org/stc/SA4-1210): Installation of Eonnex cover on aircraft surfaces.. Ceconite, Inc
- [STC SA308EA](https://openairdocs.org/stc/SA308EA): Installation of carburetor ice detection system 105AP in single and twin engine aircraft and single engine helicopters powered by Continental, Franklin, and Lycoming type engines equipped with Marvel-Schebler MA-2, MA-3, MA-4, MA-4-5, MA-6 and HA-6 series carburetors. (Normal,Utility and Acrobatic Category airplanes and helicopters equipped with engines and carburetors as described.). Alfred R Puccinelli
- [STC SA682NW](https://openairdocs.org/stc/SA682NW): Installation of two, 6 Gallon auxilliary fuel tanks. Ross, Warren B.
- [STC SA4-1514](https://openairdocs.org/stc/SA4-1514): Ceconite 101 covering of entire airplane.. Cooper Engineering Corporation

All 52: https://openairdocs.org/tcds/A-737/stcs.md

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