# TCDS A-743: The Boeing Company

- Type: Type certificate data sheet
- Status: Current
- Holder: The Boeing Company
- Revision: 16
- Revised: April 25, 2023
- Product: Aircraft, Small Airplane
- Certification basis: CAR 4a
- Registered aircraft: 1,654, by the registry models matched to it (OpenAirDocs)
- Data sheet PDF: https://openairdocs.org/files/sha256/c7/23/c7236250fd24062f0a42c96a2c829ec760e5ae307265f4d81c20c2fdbacbc621
- FAA DRS: https://drs.faa.gov/browse/excelExternalWindow/DRSDOCID131948451020230425205902.0001
- Page: https://openairdocs.org/tcds/A-743

## Models (12)

As the data sheet lists them.

- B75N1 (Navy N2S-3)
- 75 (Army PT-13)
- A75J1 (Army PT-18)
- E75 (Army PT-13D; Navy N2S-5; PT-13D/N2S-5)
- A75L3
- E75N1 (Army PT-13D; Navy N2S-5; PT-13D/N2S-5)
- A75L300
- A75 (Army PT-13A; -13B; -13C)
- A75N1 (Army PT-17; -17A; Navy N2S-1; -4)
- D75N1 (Army PT-27)
- B75 (Navy N2S-5)
- IB75A

## 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 
Rev. No. 16 15 15 15 15 15 15 15 15 15 16 
 
DEPARTMENT OF TRANSPORTATION 
FEDERAL AVIATION ADMINISTRATION 
 
 
 
TYPE CERTIFICATE DATA SHEET NO. A-743 
 
This data sheet which is part of Type Certificate No. A-743 prescribes conditions and limitations under which the product for  
which the type certificate was issued meets the airworthiness requirements of the Federal Aviation Regulations. 
 
Type Certificate Holder:  The Boeing Company 
 6001 S. Air Depot Blvd 
 Oklahoma City, OK 73135 
 
Type Certificate Holder Record: Boeing Airplane Company Wichita Division transferred to 
  The Boeing Company on April 2, 2014 
 
 
I. Model A75L3, 2 PO-CLB, (Acrobatic Category) (S ee NOTE 7), approved June 3, 1941; 75 (Army PT-13), A75 
(Army PT-13A, -13B, -13C), B75 (Navy N2S-5), E75 (Army PT-13D, Navy N2S-5, PT-13D/N2S-5), 2 PO-CLB, 
approved April 21, 1945 
(Airplanes with the Model No. E75N1 marked on their na me plates are actually Model E75 (Army PT-13D, Navy N2S-5  
or PT-13D/N2S-5) airplanes and are eligible for certification without correction of the name plates.) 
 
 Engine Lycoming R-680-B4B 506 lbs.  (-55) or   
  Lycoming R-680-B4C 497 lbs.  (-55) or 
  Lycoming R-680-B4D 490 lbs.  (-55) or 
  Lycoming R-680-B4E 512 lbs.  (-55) 
 
 Fuel 65 minimum octane aviation gasoline 
 
 Engine Limits For all operations, 2100 rpm (225 hp)   
 
 Airspeed Limits (TIAS) Leve l flight or climb  125 mph  
  Glide or dive 186 mph 
 
 Propeller Limits S ee Item: 1(a)(b)(d)(e) 
 
 C.G. Range (-1.0) to (+7.1) 
 
 
 
   
A-743 
Revision 16 
BOEING 
A75L3 
75 (Army PT-13) 
A75 (Army PT-13A, -13B, -13C) 
B75 (Navy N2S-5) 
E75 (Army PT-13D, Navy N2S-5, 
      PT-13D/N2S-5) 
A75J1 (Army PT-18) 
A75L300 
A75N1 (Army PT-17, -17A;  
         Navy N2S-1, -4) 
B75N1 (Navy N2S-3)  
D75N1 (Army PT-27) 
IB75A 
E75N1 
April 25, 2023

Rev. 16 2  A-743  
 
I. Model A75L3 (cont’d) 
 
 Empty Weight C.G. Range (-1.5) to (+0.5) solo from either seat 
  (-4.4) to (+0.5) placard in front cockpit:  "Solo from rear seat only." 
  When empty weight C.G. falls within this range, computation of critical fore  and aft C.G. 
positions is unnecessary. Ranges are not valid for non-standard  arrangement or for crop 
duster or sprayer installations. 
 
 Maximum Weight 2950 lbs.  See NO TE 6 for 3200 lbs. maximum weight. 
 
 Number of Seats 2  (+19) and (+55) 
 
 Maximum Baggage 60 lbs.   (+84) 
 
 Fuel Capacity 46 gals.  (-5)  (One tank in upper wing center section) 
 
 Oil Capacity 4.4 gals. (-26) 
 
 Control Surface Movements Elevator tabs Up 15 ˚ Down 15 ˚ 
  Elevator Up 24 ˚ Down 22 ˚ 
  Aileron Up 23 ˚ Down 18 ˚ 
  Rudder Right 30 ˚ Left 30 ˚ 
 
 Serial Numbers Eligible 75001 and On and all Army and Navy serial numbers.  Use manufacturer's 
  number if available. 
 
 Required Equipment See Items: 1(a) or (b) or (d) or (e); 105(a) or (b) or (c); 203(a) or (b);  
204(a) or (b); 205(a) or (b); 401(a) or (b), 402 
 
II. Model A75N1 (Army PT-17, -17A, Navy N2S-1, -4); B75N1 (Navy N2S-3, D75N1 (Army PT-27), 2 PO-CLB,   
(Acrobatic Category) (See NOTE 7), approved April 21, 1945 
 
 Engine Continental W-670-6A 465 lbs.  (-55) or   
  Continental W-670-6N 470 lbs.  (-55) 
 
 Fuel 65 minimum octane aviation gasoline 
 
 Engine Limits For all operations, 2075 rpm (220 hp)   
  
 Airspeed Limits (TIAS) Le vel flight or climb 125 mph 
  Glide or dive 186 mph 
 
 Propeller limits See Item 1(b), 1(d), or 1(e) 
 
 C.G. Range (-1.0) to (+7.1) 
 
 Empty Weight C.G. Range (-1.5) to +0.5) Solo from either seat 
  (-4.4) to (+0.5) placard in front cockpit:  "Solo from rear seat only." 
 When empty weight C.G. falls within this range, computation of critical fore and aft  
 C.G. positions is unnecessary. Ranges are not valid for non-standard  arrangements or  
 for crop duster or sprayer installations. 
 
 Maximum Weight 2950 lbs.  See No te 6 for 3200 lbs. maximum weight.  
 No. of Seats 2 (+19) and (+55) 
 Maximum Baggage 60 lbs.  (+84)

A-743 3  Rev. 16 
 
II. Model A75N1 (cont’d) 
 
 Fuel Capacity 46 gals. (-5)  (One tank in upper wing center section) 
 
 Oil Capacity 4.4 gals. (-26) 
 
 Control Surface Movements Elevator trim tabs Up 15 ˚ Down 15 ˚ 
  Elevator Up 24 ˚ Down 22 ˚ 
  Aileron Up 23 ˚ Down 18 ˚ 
    Rudder Right 30 ˚ Left 30 ˚ 
 Serial Numbers Eligible 75001 and On and all Army and Navy serial numbers.  Use manufacturer's 
number if available. 
 
 Required Equipment See Items: 1(b) or (d) or (e); 105(a) or (b) or (c); 203(a) or (b); 204(a) or (b);  
  205(a) or (b); 401(a) or (b); 402 
 
 
III. Model A75J1 (Army PT-18) 2 PO-CLB, (Acroba tic Category) (See NOTE 7), approved May 28, 1945 
 
 Engine Jacobs R-755-7.  See NOTE 4 for required modifications. 
 
 Fuel 73 minimum octane aviation gasoline 
 
 Engine Limits For all operations, 2000 rpm (225 hp)   
 
 Airspeed Limits (TIAS) Le vel flight or climb 125 mph 
  Glide or dive 186 mph 
 
 Propeller Limits See item 1(b). 
 
 C.G. Range (-1.0) to (+7.1) 
 
 Empty Weight C.G. Range (-1.5) to +0.5) Solo from either seat 
  (-4.4) to (+0.5) placard in front cockpit:  "Solo from rear seat only." 
  When empty weight C.G. falls within this range, computation of critical fore  and aft C.G. 
   positions is unnecessary. Range s are not valid for non-standard arrangements or for crop 
   duster or sprayer installations. 
 
 Maximum Weight 2950 lbs. 
 
 No. of Seats 2  (+19) and (+55) 
 
 Maximum Baggage 60 lbs.  (+84) 
 
 Fuel Capacity 46 gals. (-5)  (One tank in upper wing center section) 
 
 Oil Capacity 4.4 gals. (-26) 
 
 Control Surface Movements Elevator trim tabs Up 15 ˚ Down 15 ˚ 
  Elevator Up 24 ˚ Down 22 ˚ 
  Aileron Up 23 ˚ Down 18 ˚ 
  Rudder Right 30 ˚ Left 30 ˚ 
 
 Serial Numbers Eligible 75001 and On and all Army and Navy serial numbers.   
  Use manufacturer's number if available. 
 
 Required Equipment See Items: 1(b); 105(a) or (b) or (c); 203(a) or (b); 204(a) or (b); 205(a) or (b);  
  401(a) or (b); 402

Rev. 16 4  A-743  
 
IV. *Model A75L300 (applies only to models  listed under Sections I, II, and III wh en modified according to Mississippi  
 Valley Aircraft Service, Clarksdale, MS, data or Mid-Continent Aircraft Corporation, Hayti, MO, data or  
 equivalent) 
  *Note:   Models listed under Sections 1, II, or III when modified according to Brandt, Perkins & Brandt,  Marysville, CA, 
  data, eligible for certification with  the following limitation but will retain  original model designation: 
 
 Engine Lycoming B680-E3 525 lbs.  (-54) or  
  Lycoming B680-E3A 535 lbs.  (-55) or 
  Lycoming B680-E3B 565 lbs.  (-55) 
 
 Fuel 87 minimum octane aviation gasoline 
 Engine Limits Maximum, except takeoff 2200 rpm (285 hp) 
  Takeoff (one minute) 2300 rpm (300 hp) 
 Airspeed Limits (TIAS) Level flight or climb 125 mph 
  Glide or dive 186 mph 
 
 Propeller Limits See Item: 1(f) 
 
 C.G Range Maximum Weights 
  2950 lbs. or less 3200 lbs. 3520 lbs. 
 Fwd. C.G. Limit (-1.0) (-1.0) (-1.0) 
 Aft. C.G. Limit (+7.1) (+4.5) (+4.5) 
 Note: Straight line variation aft of C.G. limit above 2950 lbs. with Item 601  
  not  installed.  
 
 LBS. 
 
 3200 
 
 3100 
 
 3000 
 
 2900 
 
 
 
 -1 0 +1 2 3 4 5 6 7 8 
INCHES 
 
 Empty Weight C.G. Range (-1.3) to (-0.4) Solo from either seat. 
  (-3.7) to (-0.4) When front cockpit placarded:  “Solo from rear seat only.” 
  When empty weight C.G. falls within this  range, computation of critical fore and aft C.G. 
  positions is unnecessary.  Ranges are not  valid for non-standard arrangements or for crop 
  duster or sprayer installations. 
 
 Maximum Weight Takeoff:   NC Certification,  3200 lbs. 
   ***NR certification  3520 lbs. 
(prior to October 11, 1950)  
  Landing:    3200 lbs. 
 
  Placards 
 1.  “Intentional spins prohibited at weights above 2950 lbs.” with Item 601 not installed. 
  2.  “Intentional spins prohibited” if  elevator up-travel is more than 24°. 
  ***3.  For NR cer tification (prior to October 11, 1950):   
   “Maneuvering speed at maximum weight not to exceed 115 m.p.h.” 
 
 Required Equipment See Items: 1(f); 105(a) or (b) or (c);  204(a) or (b); 205(a) or (b); 401(a) or (b); 402 
 
   
FRONT 
LIMIT 
AFT 
LIMIT

A-743 5  Rev. 16 
 
 
V. **Model IB75A (applies only to models  listed under Sections I, II, or III when modified according to Inland Aviation  
 Company, Los Banos, CA, data, or equivalent) 
**Note: Models listed under Sections I, II, or III modified accord ing to Air-Repair, Clarksburg, CA, data, eligible for certifi cation   
 with the following limitations but will  retain original model designation:  
 
 Engine Pratt & Whitney T1B-3 (R-985-AN-1 or -AN-3) 668 lbs. or 669 lbs. (-48.5) 
 
 Fuel 87 minimum octane aviation gasoline 
 
 Engine Limits Maximum, except takeoff 1950 rpm (310 hp)   
  Takeoff (one minute) 2300 rpm (450 hp) 
 
 Airspeed Limits (TIAS) Le vel flight or climb 125 mph 
  Glide or dive 150 mph 
 
 Propeller Limits See Item: 1(g)(h). 
 C.G. Range (-2.1) to (+4.0)   
 
 Empty Weight C.G. Range (-5.3) to (-1.6) 
  When empty weight C.G. falls within th is range, computation of critical fore and aft C. G. 
  positions is unnecessary.  Ranges are not valid for non-standard  arrangements or crop 
  duster or sprayer installations. 
 
 Maximum Weight Takeoff:  NC Certification, 3200 lbs 
  ***NR certification (prior to October 11, 1950), 3520 lbs. 
  Landing: 3200 lbs. 
 Control surface movements Elevator Up    28° Down    22°   
 
  Placards  
  1. "METO power not to exceed 310 hp (1950 rpm)" 
  2. Intentional spins prohibited" 
  3. "SOLO from rear seat only." 
  ***4. NR certifica tion (prior to October 11, 1950):   
   "Maneuvering speed at  maximum weight not to exceed 115 mph." 
 
 Required Equipment See Items: 1(g) or (h); 105(a) or (b) or (c); 203(a) or (b); 204(a) or (b);  
  205(a) or (b); 401(a) or (b); 402   
 
  ***All original certification in the Restricted Category afte r October 11, 1950, must be in accordance with CAR and CAM 8.  
 
SPECIFICATIONS PERTINENT TO ALL MODELS 
 
 Datum Leading edge of lower wing 
 
 Leveling Means Leveling lugs provided in front cockpit 
 
 Certification Basis Type Certificate No. 743 (CAR 4a) 
 
 Production Basis None.  Each aircraft manufactured subs equent to October 3, 1945, for civil use must, prior 
to original certification, satisfactorily pass a detailed inspection for workmanship, 
materials, and conformity with the approved technical data and a check of the flight 
characteristics by an FAA representative. 
 
 Export Eligibility Eligible for export to all countries subject to the provisions of MOP 2-4, 
  except as follows: 
 
  Canada:  Landplane -  eligible 
    Skiplane -  not eligible

Rev. 16 6  A-743  
 
SPECIFICATIONS PERTINENT TO ALL MODELS (cont’d) 
 
 Equipment     A plus (+) or minus (-) sign preceding the weight of an item indicates 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 four 
asterisks (****).  The asterisks denote that approval  has been obtained by other than the 
aircraft manufacturer. 
 
***All original certification in the Restricted Category after October 11, 1950, must be in  accordance with CAR and CAM 8.  
 
Propellers and Propeller Accessories 
1. Propellers 
(a) Curtiss 55501-5 (eligible only with engines listed under Se ction I) ................................................. 57 lbs. ( -69) 
Static rpm at maximum permissible throttle setting: 
 Not over 1750, not under 1650.   
 No additional tolerance permitted. 
 Diameter:  Not over 102 in., not under 99 in. 
(b) Sensenich 98AA64 or 98AA66 or Fahlin D760-68-94 (including hub)  
 or any  other fixed pitch wood propeller meeting following limits which  
 is eligible for the engine power and speed:  ................................................................................. ...... 57 lbs. (-69) 
 Static rpm at maximum permissible throttle setting:  Not over 1950, not under 1725. 
 No additional tolerance permitted.  Diameter:  Not over 98 in., not under 94 in. 
 Reduce glide or dive speed to 150 mph. TIAS when using propeller with static rpm above 1775. 
 Indexing:  When this propeller is insta lled on Continental W-670-6A or -6N engine, the propeller  
 must be indexed in the 90 degree position (blades at right angles to the crankthrow). 
(c) Deleted February 15, 1946. 
(d) McCauley with the following hubs and blades: 
 (Eligible only when used with Continental W-670-6A, -6N (Army R-670) or  Lycoming R-680-B4 engines.) 
 
  Hubs Blades 
  D-1093 SS-138-6 
   Or SS-135-6M 82 lbs. (-69) 
  41D5926 SS-135-6 82 lbs. (-69) 
 
 Static rpm, at maximum permissible throttle setting:   
  Not over 1925, not under 1575. 
  No additional tolerance permitted. 
 Pitch settings at 42 in. sta.:    9° to 11.7°   
 Diameter:  Not over 102 in., not under 100 in. 
When installed on Continental W-670-6A or -6N engine, this propeller must be  
indexed in the zero degree position (blades in line with the crankthrow) and the   
tachometer should be placarded as follows:   
"Avoid continuous operation between 1500 and 1650 rpm." 
(e) Hamilton Standard blades 11C1 (Navy 4350, 4350F, 4350F1) 
 in hub 5404, or other eligible 2-way gr ound adjustable hub.  (Eligible only with 
 engines listed under Sections I an d II)  ..................................................................................... ..... 87 lbs. (-69) 
 Static rpm at maximum permissible throttle setting: 
 Not over 1975, not under 1500.   
 No additional tolerance permitted. 
 Diameter:  Not over 102 in., not under 100 in.  On Continental W-670 engines,  index in 
 the zero degree (blades in line with crankthrow) position and placard  tachometer as 
 follows:  "Avoid continuous cruise operation above 1900 rpm." 
(f) Hamilton Standard, constant speed,  hub 2B20, blades 6135-9 through -16,  with 
 1012G1 or 1012A1 governor, eligible on Lycoming R-680-E3, -E3A, 
 and -E3B engines only  ....................................................................................................... ........... 110 lbs. (-70) 
 Pitch settings at 42 in. sta.:  Low 7° for 6135-9 blades and 10° for 6135-16 blades   
 Diameter:  8'3" max., 7' 7-1/8" min. allowable for repairs 
(g) Hamilton Standard, ground adjustable 5406-AL hub, 1C1-12 through 1C1-14 blades 
 Eligible with P&W T1B3 engine only  .......................................................................................... .... 99 lbs. (-67) 
 Pitch setting at 42 in. sta.:  13.0° 
 Diameter:  9'0" max., 8' 9-7/ 8" min. allowable for repairs

A-743 7  Rev. 16 
 
SPECIFICATIONS PERTINENT TO ALL MODELS (cont’d) 
 
(h) Hamilton Standard, controllable, 2D30 hub, 6101-12 through -20 blades  ...... ................................ 163 lbs. (-67) 
 Eligible with P&W T1B3 engine only. 
 Pitch setting at 42 in. sta.:  low 12-1/2°, high 16-1/2°   
 Diameter:  9'0" max., 8' 3-7/8" min. allowable for repairs 
 
Engines and Engine Accessories - Fuel and Oil System 
101. Starter and shaft (manual) 
(a)   Eclipse M-2046-C (ACO 150976, Ty pe B-11)  ...............................................................................  24 lbs. (-36) 
(on Models A75L3, 75, A75, B75, and E75 only) 
(b)   Eclipse 94C, Model 1 (ACO 150976, Type B-11)  .......................................................................... 24 lbs. (-44) 
(on Models A75N1, B75N1, D75N1 only) 
102. Magneto, booster 
(a) Bendix - Scintilla 10-12290-1 (modified to fit airplane) (on Model 75 only)  ................................... 4 lbs. (-11)  
(b)   Bendix - Scintilla 10-15590-1   ......................................................................................... ................. 6 lbs. (-24) 
103. Carburetor air cleaner, Air Maze 5AWA  ................................................................................... ............... 6 lbs. (-33) 
104. Oil dilution system  ................................ ..................................................................... ............................. 2 lbs. (-34) 
105. Oil tank 
(a) Plain type, Boeing-Wichita Dwg. 75-3001 or 75- 3028  ..................................................................... 6 lbs. (-26) 
(b) Hopper type, Boeing-Wichita Dwg. D75N1-3001  ............................................................................ 6  lbs. (-26) 
(c) Hopper type, Boeing-Wichita Dwg. E75N1-3002  ..............................................................................  8 lbs. (-26) 
 Capacity:  4.76 gals. 
106. Winter front cowl installation (Models A75N1, B75N1 and D75N1 only) ….............................................. 9 lbs.  (-61) 
107. Engine fire extinguisher system  ................. ........................................................................ ....................... 21 lbs. (-20) 
 
Landing Gear and Floats 
(Main gear shock struts of the air-oil type and conforming to Boeing-Wichita Dwg. 75-2602 and main landing gear  
carry-through structures conforming to Boeing-Wichita Dwg. 75-2603 may be used on Model 75 (Army PT-13) only.) 
201. Main landing gear wheels 
a. 24 in. streamline (Bendix or Hayes) with hyd. brakes and 24 in. 4-ply 
 streamline tires.............................................................................................................. ................... 94 lbs. (-17) 
b. 24 in. streamline (Bendix or Hayes) with hyd. brakes and 8.90-12.50 4-ply low 
 pressure tires. .............................................................................................................. ...................... 96 lbs. (-17) 
202. Tail wheel 
(a) 8 in. smooth contour wheel and 6-ply tire.................................................................................. ......... 4 lbs. (+196) 
(b) 10 in. smooth contour wheel and 6-ply tire................................................................................. ........ 7 lbs. (+196) 
203. Tail wheel gear (less wheel and tire) 
(a) Steerable ................................................................................................................. ......................... 18 lbs. (+190) 
(b) Free swivel with lock...................................................................................................... .................. 18 lbs. (+190) 
 
Electrical Equipment 
301. Battery 
(a) 12 volt - 34 amp. hr. (5 hr. rate)......................................................................................... ............... 41 lbs. (-16) 
(b) 24 volt - 11 amp hr. (5 hr. rate).......................................................................................... ............... 34 lbs. (-16) 
302. Interphone 
(a) Type TIC .................................................................................................................. ........................... 9 lbs. (-13) 
(b) Type RC-73 ................................................................................................................ ......................... 5 lbs. (+39) 
303. (a) Wing (NAF 1021) 
(b) Wing (AN 3033) 
 
Interior Equipment 
401. Seats 
(a) Metal (Boeing-Wichita Dwg. 75-3720)  .............................................................................. 8 lbs. ( +26) & (+62) 
(b) Wood (Boeing-Wichita Dwg. B75N1-3610 ...................................................................... 13 lbs. (+26) & (+62) 
402. Safety belts, Army Types B-6,  B-10, B-11, and B-12 and NAF 1045-1 
403. Fire extinguisher - portable 
(a) One quart carbon tetrachloride (Type A-2) ................................................................................. ........ 7 lbs. (+51) 
(b) Two Pound CO 2 (Type 2TA 2TB) ..................................................................................................... 6 lbs. (+4 6)

Rev. 16 8  A-743  
 
SPECIFICATIONS PERTINENT TO ALL MODELS (cont’d) 
Miscellaneous 
601. Spoilers (spin strips) over leading edge upper and lower wings or lower wing only 
602. (a) Blind flying hood..................................................................................................... ............................ 6 lbs. (+67) 
(b) Fling flying hood provisions............................................................................................... ................. 2 lbs. (+55) 
603. Cockpit enclosure (Boeing).  When this it em is installed, airplane not eligible for   
 night flying and must be placarded as follows:  "Close hatches before entering spin or dive." 
604. Windshield extension...................................................................................................... .......................... 9 lbs. (+19) 
****605. Cockpit enclosure (R.A.D. Air Devices, St. Louis, MO) ................................................................ ......... 47 lbs. (+50) 
****606. Cockpit enclosure (Rawdon Dwg. PT-1050) .............................................................................. ............. 10 lbs. (+44) 
****607. Sprayer and Duster Installations (all 75  series airplanes unless otherwise noted) 
(a) Goettl's Metalcraft Co., 2431 E. Buhanan, Phoenix, AZ. 
Duster installation kit approved, subject to inspection, when installed according to  
drawings and installation instru ctions furnished with kit. 
(b) Barrie Aeronautical Corp., Lee Airport, Lockport, NY. 
Model 20 dust hopper approved, subject to inspection, when installed according  
to Barrie Dwg. 001. 
(c) Transland Company, 223 California St., El Segundo, CA. 
Spray installation approved, subject to inspection, when installed in accordance with 
combination Spray Tank and Hopper Dwg. 1001, Dwgs. 1 through 10, and installation 
instructions: 
Airspeed Limits: Level flight or climb 100 mph TIAS 
 Glide or dive  120 mph TIAS 
(d) Transland Company, 223 California St., El Segundo, CA. 
Duster installation approved, subject to inspection, when installed in accordance with  combination Spray 
Tank and Hopper Dwg. 1001, Dwgs. 2001, 2004 and 2005 and installation instructions: 
Airspeed Limits: Level flight or climb 112 mph TIAS 
 Glide or dive  134 mph TIAS 
(e) Rawdon Bros. Aircraft, Inc., Box 1135, Wichita, KS. 
 Spray kit approved, subject to  inspection, when installed according to Rawdon Report PT-6025. 
(f) Burnam Aviation Co., Arlington, TX. 
Six venturi spray kit approved, subject to inspection, when installed according to Burnam Dwgs. and 
Instructions B-1, B-2, B-3, RB-100, RB-101, RB-102, RB-1 and RB-2.  
Airspeed Limits: Level flight or climb 119 mph TIAS 
 Glide or dive  143 mph TIAS 
(g) Independent Crop Dusting, Inc., Campbell, CA. 
ICD Model 600 rotary spray two unit kit approved, subject to inspection, when installed according to ICD 
Dwgs. 600-102 to -106 inclusive and installation instructions, and when mounted to the wing structure in 
accordance with ICD Dwg. 600-101 or ICD Mounting Kit No. 600-1B. 
Airspeed Limits: Level fli ght or climb  92 mph TIAS 
 Glide or dive  110 mph TIAS 
(h) Airplane Vapor Spray Company, Route 3, Box 567b, Visalia, CA. 
Duster, spray or combination duster and spray kit approved, subject to inspection, when installed according to 
assembly Dwg. No 8904-A and P-100 through P-107, inclusive, and installation Dwgs. 1001 through 1008 
inclusive.  Kits include instructions for Pratt and Whitney R-985-AN3 engine installation and the airplane was 
eligible for NR certification prior to October 11, 1950, with  the engine and limitations listed in Section V. 
(i) Ong Aircraft Corp., Kansas City, MO. 
Aero Dust King Model DS-12 kit approved, subject to inspection, when installed according to Ong Installation 
Instructions and DWg. DS-1200. 
(j) Airplane Dust and Spray Equipment Company, Kern County Airport, Bakersfield, CA.  
Sprayer pump and boom assembly kit, subject to inspection, when installed according to Dwg. 50320-207-75 
and installation instructions. 
Airspeed Limits: Level fli ght or climb  92 mph TIAS 
 Glide or dive  110 mph TIAS 
(k) Rawdon Seeder-Duster, Rawdon Bros. Aircraft Inc., Box 1135, Wichita, KS. 
Kit approved, subject to inspection, when installed according to Rawdon Report No. PT-7100.

A-743 9  Rev. 16 
 
SPECIFICATIONS PERTINENT TO ALL MODELS (cont’d) 
 
****608. Metal cente r wing section, Goettls Metalcraft Company, 2431 E. Buchanan Street, Phoenix, AZ.  
Per Goettls Metalcraft Company Dwgs. Nos. G-2348-M, and/or G-2348-M modified. 
****609. Wings ma de in accordance with Dwgs. 53040-1 through 53040-5, owned by Arvin-Wings, Inc., 
P.O. Box 668, Arvin, CA, comply with the structural requirements of CAR 8 when installed on 75 Series 
aircraft.  This configuration was substantiated under Part 8 for the following weights and speeds: 
3200 lbs. gross weight, takeoff and landing  
Vc = 110 mph V ne - 139 mph 
Airplanes equipped with these wings are eligible for certification under CAR 8 only.  For certification at 
higher weights and speeds than those shown above,  these airplanes should be flight tested in  accordance with 
CAM 8.10-3 and the maximum weight established in accordance with CAM 8.10-4 for the intended special 
purpose. 
****610. Wings ma de in accordance with Dwgs. NA101 through NA131, owned by National Aircraft Corporation, 
8075 Woodley Avenue, Van Nuys, CA, comply with structural requirements of CAR 8 only when installed on 
75 series aircraft.  This configuration wa s substantiated under Part 8 for the following  weights and speeds: 
3632 lbs.   Gross weight, takeoff       
3200 lbs.   Gross weight, landing  
Vc = 105 mph       Vn e - 141mph 
Airplanes equipped with these wings are eligible for certification under CAR 8 only.  For certification at 
higher weights and speeds than those shown above,  these airplanes should be flight tested in  accordance with 
CAM 8.10-3 and the maximum weight established in accordance with CAM 8.10-4 for the intended special 
purpose. 
 
 
NOTE 1. Current weight and balance re port 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 ai r carrier operators having an approved weight control 
system). 
 
NOTE 2. Prior to original certification of any surplus military aircraft the following revisions must be made: 
(These revisions are also covered in Boeing Airplane Company, Wichita Division, Service Bulletin No. 75-1, 
A75-1, B75-1, E75-1, A75N1-1, D75N1-1, A75J1-1 (one bulletin). 
(a) The 0.040 inch thick aluminum firewall must be replaced, covered, or backed by 0.015 inch thick 
stainless steel or 0.018 inch thick mild steel suitably protected against corrosion.  As an alternative,  the 
back of the present firewall may be covered with a sheet 1/8 inch thick asbestos covered, in turn, with 
0.020 inch thick aluminum. The entire assembly  should be securely riveted together. The  asbestos and 
second sheet of aluminum need not be applied in one piece. However, any joints should be well matched 
and asbestos joints should not coinci de with joints in the aluminum. 
(b) A suitable stick or gauge for measuring the oil quantity shall be provided. 
(c) The baggage compartment shall be marked "maximum capacity 60 lbs." or as limited by pertinent weight 
and balance report, if less. 
 
NOTE 3. Prior to original certification of any surplus m ilitary aircraft of the subject models equipped with an electrical 
system, the following conditions should be complied with or electrical installations should be removed:   
 (These revisions are also c overed in Boeing Airplane Company, Wichita Division, Service Bulletin No. 75-1, 
A75-1, B75-1, E75-1, A75N1-1, B75N1-1, D75N1-1, A75J1-1 (one bulletin)). 
(a) Any unapproved position lights must be replaced with Federal Aviation Administration certificated or 
approved lights.  The wing lights on some airplanes are already of an approved type.  These approved 
lights are NAF-1021 and AN 3033 models.  However, if the AN 3033 lights have a streamlined glass 
cover, the sandblasted area on the inside of the  cover should be painted black or the cover should be 
replaced with a glass globe and a streamlined metal cover which can be obtained from the light 
manufacturer.  None of the rudder light assemblies incorporated on these military airplanes is approved. 
(b) A battery switch must be installed that will disconnect the battery from the electrical  system as near the 
battery as practicable. 
(c) If the battery switch is operable from only one seat the airplane should be placarded for  solo flight from 
that seat.

Rev. 16 10  A-743  
 
SPECIFICATIONS PERTINENT TO ALL MODELS (cont’d) 
 
NOTE 4. Jacobs R-755-7 engines used in Ar my PT-18 airplanes must be inspected and modified as follows, prior to 
certification: 
The rear main engine crankcase must be part no. 30068.  If any other rear main crankcase is installed it must 
be replaced. 
(a) Inspect all gears and bushings in the engine star ter gear train to assure that they are in 
airworthy condition.  Any unsatisfactory parts must be replaced. 
(b) Eclipse type 946 starters must not be used w ith the R-755-7 engine due to their excessively high 
clutch setting. In addition, no inertia type starters with a clutch setting above 300 ft. lbs. should 
be used with this engine. 
 
NOTE 5. Rigging specifications are as follows: 
 (Complete maintenance instructions , including detailed rigging information, may be purchased from the 
Boeing Airplane Company, Wichita Division.) 
 
 Center section centering - With fuselage leveled laterally the center section is centered by hanging a plumb 
bob over the outboard side of the bushing at the front spar  terminal bolt and measuri ng the lateral distance 
from the plumb line to the fuselage box tube.  This dimension is normally 23" plus or minus 1/32" and 
should be equal within plus or minus 1/16" on both sides of the fuselage. 
 
Dihedral -  Upper wing 1/2°, lower wing 1-1/2° 
ncidence -  Upper wing 4°, lower wing 3° 
 Stagger -  26-13/16" plus or minus 1/8" at strut point (spoilers on both wings or 
   on neither wing) 
 -  26-9/16" plus or minus 1/8" at st rut point (spoilers on lower wing only) 
Sweepback -  0° 
 
NOTE 6. Models with engines listed unde r Sections I and II are also eligible for NC certification at a maximum 
weight of 3200 lbs. under the following conditions: 
 
 Airspeed Limits Level f light or climb 123 mph (TIAS) 
  Glide or dive 148 mph (TIAS) 
 
Propeller Limits Static rpm, at maximum permissi ble throttle setting: 
   Not over 1970, not under 1870  
  No additional tolerance admitted  
 Diameter:  Not over 102 in., not under 100 in. 
 Pitch setting: 9° at 42 in. station 
 (Limits shown in Item 1(d)(e) are not applicable at 3200 lb. weight). 
 
 C.G. Range (-1.0) to (+4.5) at 3200 lbs. 
  (-1.0) to (+7.1) at 2950 lbs. or less 
  Straight line variation of aft C.G. limit between 2950 lbs. and 3200 lbs. 
 
 
 LBS. 
 3200 
 
 3100 
 
 3000 
 
 2900 
 
 
 -1 0 +1 2 3 4 5 6 7 8 
INCHES 
   
FRONT 
LIMIT 
AFT 
LIMIT

A-743 11  Rev. 16 
 
SPECIFICATIONS PERTINENT TO ALL MODELS (cont’d) 
NOTE 6. (cont’d) 
Empty Wt. C.G. Range (-1.3) to (-0 .4)  "Solo from rear seat only." 
 (-3.7) to (-0.4)  When front cockpit placarded:  "Solo from rear seat only." 
 When empty weight C.G. falls within this range computation of critical fore and aft C.G. 
  positions is unnecessary.  Range s are not valid for non-standard arrangements or for crop 
  duster or sprayer installations. 
 
Placards "Intentional spinning prohibited" 
 "80 minimum octane fuel to be used" 
 
Required Equipment See Item: 1(d) or (e) re quired.  Item 601 not be installed.   
 Front windshield to be removed and front cockpit  covered over. 
 
NOTE:    Above aircraft with external configuration changes such as approved dusters, sprayers, etc.,  listed under item 607, or similar, are 
eligible for NC or standard certification with the above  limitations unless otherwise noted. 
 
NOTE 7. The certification basis for these airplanes does not contain operating categorie s, i.e., normal, utility or  
acrobatic, as listed in the current certification regulations.  However, since certain of these models were  
designed to perform and have demonstrated the capability to perform the acrobatic maneuvers not exceeding 
the load factors listed below, the words "acrobatic category" are included so that those persons concerned 
with these airplanes understand their cap acity in terms of current practices. 
 Maneuvering load factors are as follows: 
 
 A75L3, 75, A75, B75, E75, A75N1, B75N1, D75N1, A75J1 +6.67 to -2.67 
 
 For the above reasons, the airwor thiness certificate for A75L3, 75, A75, B75, E75, A75N1, B75N1, D75N1 
and A75J1 airplanes is to be issued in the acrobatic category. 
 
NOTE 8. Manufacturer name change effective April 2, 2014.  The following serials are manufactured under the name 
  Boeing Airplane Company: 75001 and On, a nd all Army and Navy serial numbers.   
  Use manufacturer's number if available. 
 
 
....END....
```

## ADs (7, in force first)

- [AD 2023-10-02](https://openairdocs.org/ad/2023-10-02): Indicating/Recording System, Navigation · Boeing 18, 23, 35 and 1,060 more. Effective May 26, 2023
- [AD 63-13-01](https://openairdocs.org/ad/63-13-01): Propeller Inspection · Boeing Airplane Company, Wichita Division 75 (Army PT-13), A75 (Army PT-13A, -13B, -13C), A75J1 (Army PT-18) and 9 more. Effective Jun 21, 1963
- [AD 46-24-01](https://openairdocs.org/ad/46-24-01): Wing Drain Holes · Boeing Airplane Company, Wichita Division 75 (Army PT-13), A75 (Army PT-13A, -13B, -13C), A75J1 (Army PT-18) and 6 more
- [AD 49-23-01](https://openairdocs.org/ad/49-23-01): Fuselage Truss · Boeing Airplane Company, Wichita Division 75 (Army PT-13), A75 (Army PT-13A, -13B, -13C), A75J1 (Army PT-18) and 9 more
- [AD 50-06-02](https://openairdocs.org/ad/50-06-02): Wing Spar Inspection · Boeing Airplane Company, Wichita Division 75 (Army PT-13), A75 (Army PT-13A, -13B, -13C), A75J1 (Army PT-18) and 9 more
- [AD 60-08-02](https://openairdocs.org/ad/60-08-02): Longeron Cracks · Boeing Airplane Company, Wichita Division 75 (Army PT-13), A75 (Army PT-13A, -13B, -13C), A75J1 (Army PT-18) and 9 more
- [AD 2019-20-02](https://openairdocs.org/ad/2019-20-02) (historical): Fuselage · Boeing Airplane Company, Wichita Division 75 (Army PT-13), 737-600 Series, 737-700 Series and 4 more. Effective Oct 3, 2019

## Registered aircraft by registry model (OpenAirDocs)

- [Boeing A75N1(PT17)](https://openairdocs.org/model/boeing-a75n1-pt17): 759 aircraft (registry code 1380134)
- [Boeing E75](https://openairdocs.org/model/boeing-e75): 261 aircraft (registry code 1380120)
- [Boeing B75N1](https://openairdocs.org/model/boeing-b75n1): 241 aircraft (registry code 1380144)
- [Boeing A75](https://openairdocs.org/model/boeing-a75): 93 aircraft (registry code 1380108)
- [Boeing E75N1](https://openairdocs.org/model/boeing-e75n1): 79 aircraft (registry code 1380154)
- [Boeing A75N1](https://openairdocs.org/model/boeing-a75n1): 59 aircraft (registry code 1380165)
- [Boeing D75N1](https://openairdocs.org/model/boeing-d75n1): 35 aircraft (registry code 1380148)
- [Boeing A75L300](https://openairdocs.org/model/boeing-a75l300): 33 aircraft (registry code 1380132)
- [Boeing A75L3](https://openairdocs.org/model/boeing-a75l3): 32 aircraft (registry code 1380102)
- [Boeing 75](https://openairdocs.org/model/boeing-75): 18 aircraft (registry code 1380104)
- [Boeing B75](https://openairdocs.org/model/boeing-b75): 15 aircraft (registry code 1380116)
- [Boeing IB75A](https://openairdocs.org/model/boeing-ib75a): 12 aircraft (registry code 1380152)
- [Boeing A75J1](https://openairdocs.org/model/boeing-a75j1): 2 aircraft (registry code 1380131)
- [Boeing E75(N2S-5)](https://openairdocs.org/model/boeing-e75-n2s-5): 2 aircraft (registry code 1380123)
- [Boeing B75(N2S-2)](https://openairdocs.org/model/boeing-b75-n2s-2): 1 aircraft (registry code 1380598)
- [Boeing Stearman/Huff A75-N1](https://openairdocs.org/model/boeing-stearman-huff-a75-n1): 1 aircraft (registry code 1380129)
- [Boeing/Cains Richard G A75N1](https://openairdocs.org/model/boeing-cains-richard-g-a75n1): 1 aircraft (registry code 1380161)
- [Boeing/Dekker A75N1](https://openairdocs.org/model/boeing-dekker-a75n1): 1 aircraft (registry code 1380127)
- [Boeing/Hawk E-75](https://openairdocs.org/model/boeing-hawk-e-75): 1 aircraft (registry code 1380147)
- [Boeing/Humm Stanley A75-N1](https://openairdocs.org/model/boeing-humm-stanley-a75-n1): 1 aircraft (registry code 1380171)
- [Boeing/Johnson A75N1](https://openairdocs.org/model/boeing-johnson-a75n1): 1 aircraft (registry code 1380164)
- [Boeing/Mays A75N1](https://openairdocs.org/model/boeing-mays-a75n1): 1 aircraft (registry code 1380133)
- [Boeing/Mehrer A75N1](https://openairdocs.org/model/boeing-mehrer-a75n1): 1 aircraft (registry code 1380160)
- [Boeing/Mountain View Air Rep A75N1](https://openairdocs.org/model/boeing-mountain-view-air-rep-a75n1): 1 aircraft (registry code 1380155)
- [Boeing/Porter/Epperson B-75N1](https://openairdocs.org/model/boeing-porter-epperson-b-75n1): 1 aircraft (registry code 1380149)
- [Boeing/Smith A75N1](https://openairdocs.org/model/boeing-smith-a75n1): 1 aircraft (registry code 1380125)
- [Boeing/Stiles R B75N1](https://openairdocs.org/model/boeing-stiles-r-b75n1): 1 aircraft (registry code 1380166)
- [Boeing / Farhat B75N1](https://openairdocs.org/model/boeing-farhat-b75n1): 0 aircraft (registry code 1380157)
- [Boeing / Ryan STEARMAN A75N1](https://openairdocs.org/model/boeing-ryan-stearman-a75n1): 0 aircraft (registry code 1380158)
- [Boeing A75 (PT13)](https://openairdocs.org/model/boeing-a75-pt13): 0 aircraft (registry code 1380180)
- [Boeing E75 (PT-13D)](https://openairdocs.org/model/boeing-e75-pt-13d): 0 aircraft (registry code 1380170)
- [Boeing E75(N2S5)](https://openairdocs.org/model/boeing-e75-n2s5): 0 aircraft (registry code 1380168)
- [Boeing-Phibbs 75](https://openairdocs.org/model/boeing-phibbs-75): 0 aircraft (registry code 1385140)
- [Boeing-Stearman/Shacklette A75N1](https://openairdocs.org/model/boeing-stearman-shacklette-a75n1): 0 aircraft (registry code 1380135)
- [Boeing/Alianelli/Prim A75-N1](https://openairdocs.org/model/boeing-alianelli-prim-a75-n1): 0 aircraft (registry code 1380167)
- [Boeing/Classic Planes 75](https://openairdocs.org/model/boeing-classic-planes-75): 0 aircraft (registry code 1380111)
- [Boeing/Corsaut A75N1](https://openairdocs.org/model/boeing-corsaut-a75n1): 0 aircraft (registry code 1380151)
- [Boeing/Cox A75-N1](https://openairdocs.org/model/boeing-cox-a75-n1): 0 aircraft (registry code 1380163)
- [Boeing/Gillespie A75N1](https://openairdocs.org/model/boeing-gillespie-a75n1): 0 aircraft (registry code 1380126)
- [Boeing/Mocabee B75N1](https://openairdocs.org/model/boeing-mocabee-b75n1): 0 aircraft (registry code 1380145)
- [Boeing/White Scott E75N1](https://openairdocs.org/model/boeing-white-scott-e75n1): 0 aircraft (registry code 1380173)
- [Boeing/Wright Joe W B75N1](https://openairdocs.org/model/boeing-wright-joe-w-b75n1): 0 aircraft (registry code 1380169)
- [Boeing/Younkin A-75](https://openairdocs.org/model/boeing-younkin-a-75): 0 aircraft (registry code 1380109)

## STCs approved under this data sheet (162, 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 SA1208WE](https://openairdocs.org/stc/SA1208WE): Steel aileron actuating fitting replacement for Boeing P/N 75-1417.. AvComp LLC
- [STC SA1299WE](https://openairdocs.org/stc/SA1299WE): Installation of Pratt & Whitney R985-AN-1 Engine, Hamilton Standard 2D30/6101A-12 Propeller; B75N1 (Navy N2S-3), N450V, S/N 75-6484. AvComp, LLC
- [STC SA1540WE](https://openairdocs.org/stc/SA1540WE): Installation of Pratt & Whitney R-985-AN-1, -AN-3, -AN14B, or -AN14BM engine, Hamilton Standard 2D30/6101A-12 or 2D30/6101A-12 or 22D30/6533A-12 propeller, modified fuel and oil systems.. AvComp LLC
- [STC SA1703WE](https://openairdocs.org/stc/SA1703WE): Installation of Serv-Aero four aileron system.. AvComp, LLC
- [STC SA26WE](https://openairdocs.org/stc/SA26WE): Removable aluminum fuselage panels. (Restricted category only.). AvComp LLC
- [STC SA3250NM](https://openairdocs.org/stc/SA3250NM): Installation of cockpit canopy enclosure.. AvComp LLC
- [STC SA3251NM](https://openairdocs.org/stc/SA3251NM): Installation of Speed Ring engine cowling.. AvComp LLC
- [STC SA3277NM](https://openairdocs.org/stc/SA3277NM): Installation of wheel fairings; B75N1 (Navy N2S-3), S/N 75-787 (N5121N) Only. AvComp LLC
- [STC SA4-1197](https://openairdocs.org/stc/SA4-1197): Control lock, locking rudder, elevator, and ailerons.. AvComp LLC
- [STC SA266SW](https://openairdocs.org/stc/SA266SW): Installation of engine mount P/N M1 for Pratt & Whitney R-985 or R-1340 engine installation.. AirCorps Aviation
- [STC SA4-326](https://openairdocs.org/stc/SA4-326): Aerial dust and spray equipment.. Texas Transland LLC
- [STC SA4-589](https://openairdocs.org/stc/SA4-589): Installation of Swathmaster dispensing unit.. Texas Transland LLC
- [STC SA7965SW](https://openairdocs.org/stc/SA7965SW): Application of fabric and polyurethane finishing system.. Shady Aviation LLC
- [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 SA4503NM](https://openairdocs.org/stc/SA4503NM): Remove original cloth covering and install Ceconite covering. Ceconite Division of Poly-Fiber Inc.
- [STC SA02682AT](https://openairdocs.org/stc/SA02682AT): Replacement of original chevron seals with improved Main Landing Gear Dynamic Seal, P/N: AR1102 and Adapter Ring, P/N: AR1101.. Air Repair Inc.
- [STC SA02866AT](https://openairdocs.org/stc/SA02866AT): Replacement of MLG chevron seals with Parker seals. Air Repair Inc.
- [STC SA692NW](https://openairdocs.org/stc/SA692NW): Installation of a Lycoming engine, Hamilton Standard hub, Boeing E75-300 engine mount. Terrence R. Martin
- [STC SA04776NY](https://openairdocs.org/stc/SA04776NY): The HIPEC Covering and Finishing System must be performed and maintained. HIPEC Aircraft Coatings Inc.
- [STC SA02322AT](https://openairdocs.org/stc/SA02322AT): Installation of Jacobs model R-755-A2, -A2M, -B2 or -B2M engine.. Air Repair Inc
- [STC SA1151NW](https://openairdocs.org/stc/SA1151NW): Installation of the Flight Grip Model 135 Control Stick Grip. Air Products & Parts LLC
- [STC SA220SO](https://openairdocs.org/stc/SA220SO): Tow bar, release mechanism, and safety tow link.. Fliegen Works Inc. 
      d/b/a Pacific Aerial Tow Hooks
- [STC SE02712SE](https://openairdocs.org/stc/SE02712SE): Installation of the Oil Scavenging Pump System for Jacobs L-4 and R-755. Henry F. Rogers
- [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 SA02268CH](https://openairdocs.org/stc/SA02268CH): Installation of Airwolf Filter Corp. Air Oil Separator. Airwolf Filter 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 SA01435SE](https://openairdocs.org/stc/SA01435SE): Installation of J.P. Instruments (JPI) Primary Engine Data Management System. J. P. Instruments
- [STC SA6070NM](https://openairdocs.org/stc/SA6070NM): Installation of a 'quick-disconnect drain plug' on the engine rocker sump for the oil drain retrieval system after engine shutdown.. West Coast Air Creations
- [STC SA00024NY](https://openairdocs.org/stc/SA00024NY): Installation of Airwolf remote mounted engine oil filter kit AFC-K007 on single or multi-engine fixed wing light aircraft incorporating Lycoming reciprocating engines of 450 horsepower or less.. Airwolf Filter Corporation
- [STC SA01282NY](https://openairdocs.org/stc/SA01282NY): Installation of Airwolf remote mounted engine oil filter kit AFC-K015 on aircraft powered by Pratt & Whitney radial reciprocating engine Series R-985, R-1340 and R-1830.. Airwolf Filter Corporation
- [STC SA01406NY](https://openairdocs.org/stc/SA01406NY): Installation of Airwolf remote mounted engine oil filter kit AFC-K017 on single and multi-engine fixed light aircraft and
rotary wing. 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 SA2586NM](https://openairdocs.org/stc/SA2586NM): Installation of J.P. Instruments temperature monitoring systems.. J P Instruments
- [STC SA1109WE](https://openairdocs.org/stc/SA1109WE): Installation of Pratt & Whitney R-985 AN1 Engine (S/N 20458). Continental Motors, Inc.
- [STC SA01734SE](https://openairdocs.org/stc/SA01734SE): Application of Stewart Systems synthetic fabric covering system to aircraft fuselage, wings, tail surfaces, control surfaces and related parts.. Andrew D. Humphrey
- [STC SA00478CH](https://openairdocs.org/stc/SA00478CH): Installation of Cooper Superflite 102 Fabric.. Aviation Products Systems Inc.
- [STC SA1289SO](https://openairdocs.org/stc/SA1289SO): This approves the modification of the Bendix Brake Control Units to improve braking performance. AirCorps Aviation
- [STC ST03413CH](https://openairdocs.org/stc/ST03413CH): Installation of an aircraft smoke system. Yesteryear Aviation Inc
- [STC SA7493SW](https://openairdocs.org/stc/SA7493SW): Install Jasco P/N 6555-1 alternator and 12 volt electrical system. Rare Aircraft Ltd
- [STC SA7591SW](https://openairdocs.org/stc/SA7591SW): Install a Schweizer fuel shut-off valve.. Rare Aircraft Ltd
- [STC SA8056SW](https://openairdocs.org/stc/SA8056SW): Install engine throttle, mixture, and carburetor heat cable controls.. Rare Aircraft Ltd
- [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 SA00432SE](https://openairdocs.org/stc/SA00432SE): Installation of EGT 701 series fuel flow instrument.. J P Instruments
- [STC SA00861SE](https://openairdocs.org/stc/SA00861SE): Installation of J.P. Instruments (JPI) fuel flow indicating system. J P Instruments

All 162: https://openairdocs.org/tcds/A-743/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.