# TCDS A-698: Piper Aircraft Inc.

- Type: Type certificate data sheet
- Status: Current
- Holder: Piper Aircraft Inc.
- Revision: 14
- Revised: August 7, 2006
- Product: Aircraft, Small Airplane
- Certification basis: CAR 4a
- Registered aircraft: 195, by the registry models matched to it (OpenAirDocs)
- Data sheet PDF: https://openairdocs.org/files/sha256/a0/f1/a0f11397c7a672a1b80d1c82c95ac1088ec6d9f3831c43cbaf345f9e7ab981b3
- FAA DRS: https://drs.faa.gov/browse/excelExternalWindow/654CEC2E0F108D0A8625720900728D14.0001
- Page: https://openairdocs.org/tcds/A-698

## Models (4)

As the data sheet lists them.

- J3L-65S
- J3L
- J3L-S
- J3L-65 (Army L-4C)

## What the data sheet says

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

```text
DEPARTMENT OF TRANSPORTATION 
FEDERAL AVIATION ADMINISTRATION 
A-698 
Revision 14 
Piper Aircraft, Inc 
 
J3L 
J3L-S 
J3L-65 (ARMY L-4C) 
J3L-65S 
 
August 7, 2006 
 
AIRCRAFT SPECIFICATION A-698 
 
Type Certificate Holder Piper Aircraft, Inc. 
 2926 Piper Drive 
 Vero Beach, Florida  32960 
 
Type Certificate Holder Record The new Piper Aircraft, Inc transferred TC A-698 to Piper Aircraft, Inc on August 7, 
2006. 
 
I - Model J3L,   2 PCLM,   Approved September 17, 1938 and Model J3L-S,   2 PCSM,   Approved May 2, 1939 
 
Engine Lycoming O-145-A1  (See Item 309A for optional engines) 
 
Fuel 65 minimum  octane aviation gasoline 
 
Engine Limits For all operations, 2300 r.p.m.     (50 hp.) 
 
Airspeed Limits Level flight or climb   90 mph   (78 Knots) True Ind. 
 Glide or dive 122 mph (106 Knots) True Ind. 
 
Propeller Limits Static r.p.m. at maximum permissible throttle setting: 
  Seaplane  Not over 2335, not under 2125.  No additional tolerance permitted. 
  Landplane Not available 
 Diameter: Landplane Not over 80 in. 
    Seaplane  Not over 75 in., not under 68 in. 
 
C. G. Range Landplane (+10.6) to (+22.7) 
 Seaplane  (+10.6) to (+19.8) 
 See NOTE 3 for restricted range for certain Serial Nos. between 4373 and 4502. 
 
Empty Weight C. G. Range If placard  "Solo flying in rear seat only." is installed (See NOTE 2): 
  Landplane (+8.1) to (+20.7) 
  Seaplane  (+8.5) to (+17.8) 
 When empty weight C. G. falls within the pertinent range, computation of critical fore 
and aft  
 C. G. positions is unnecessary.  Ranges are not valid for non-standard arrangements. 
 
Maximum Weight Landplane: 1100 lbs. 
 Seaplane:  1160 lbs. 
 
Number of Seats 2 (one at +9 and one at +36) 
 
Maximum Baggage Landplane: 20 lbs. (+49) 
 Seaplane:    4 lbs. (+49) 
 
Fuel Capacity  12 gallons  (-18) 
Page No. 1 2 3 4 5 6 7 
Rev. No. 14 14 14 14 14 14 14

A-698 Pa ge 2 of 7 
 
I - Model J3L and Model J3L-S    (cont'd) 
Oil Capacity 5 quarts   (-39) 
 
Control Surface Movements Elevator 34° Up 29° Down 
 Aileron 18° Up 18° Down 
 Rudder 30° Left 30° Right 
 Stabilizer 2.5° Up 4° Down 
 
Serial Numbers Eligible  2325, 2327, 2339, 2340, 2342, 2344, 2345, 2347, 2349, 2351, 2355 and up, 2356-A, 
2357-A and up, and 8277-1 through 8277-40. 
 
Required Equipment In addition to the pertinent required basic equipment specified in CAR 4a, the following 
  items of equipment must be installed: 
  Landplane: Items 101, 102, 103, and 104. 
  Seaplane:  Items 103, 104 and 151. 
 
II - Models J3L-65   (ARMY L-4C) and J3L-65S,   2 PCL-SM,   Approved May 27, 1940 
 Same as Model J3L and J3L- S except engine installation. 
 
Engine Lycoming O-145-B1  (See Item 309B for optional engines) 
 
Fuel 73 min. octane aviation gasoline 
 
Engine Limits Takeoff and climb, 2550 r.p.m.  (65 hp.) 
 All other operations, 2412 r.p.m.  (55 hp.) 
 
 Airspeed Limits  Level flight or climb   90 mph (78 Knots) True Ind. 
 Glide or dive 122 mph (106 Knots) True Ind. 
 
Propeller Limits Static r.p.m. at maximum permissible throttle setting: 
  Landplane and Seaplane:  Not over 2525, not under 2225.  No additional tolerance  
  permitted. 
 Diameter: Landplane Not over 80 in., not under 64 in. 
    Seaplane  Not over 75 in., not under 68 in. 
 
C. G. Range Landplane (+10.6) to (+22.7) 
 Seaplane  (+10.6) to (+19.8) with Edo or Wollam floats 
    (+10.2)  to  (+17.1) with Heath floats 
 See NOTE 3 for restricted range for certain Serial Nos. between 4373 and 4502. 
 
Empty Weight C. G. Range If placard  "Solo flying in rear seat only" is installed (See NOTE 2): 
  Landplane (+8.1) to (+20.7) 
  Seaplane  (+8.4) to (+17.4) with Edo or Wollam floats 
     (+7.8) to (+14.0) with Heath floats 
 When empty weight C. G. falls within the pertinent range, computation of critical fore 
and aft  
 C. G. positions is unnecessary.  Ranges are not valid for non-standard arrangements. 
 
Maximum Weight Landplane: 1100 lbs.  (See NOTE 4 regarding eligibility for 1170 lbs.) 
 Seaplane:  1200 lbs. 
 
Number of Seats 2 (one at +9 and one at +36) 
 
Maximum Baggage Landplane: 20 lbs. (+49) 
 Seaplane:    4 lbs. (+49)

Page 3 of 7 A-698 
 
II - Models J3L-65 and J3L-65S    (cont'd) 
Fuel Capacity  12 gallons  (-18) 
 
Oil Capacity 5 quarts   (-39) 
 
Control Surface Movements Elevator 34° Up 29° Down 
 Aileron 18° Up 18° Down 
 Rudder 30° Left 30° Right 
 Stabilizer 2.5° Up 4° Down 
 
Serial Numbers Eligible 2325, 2327, 2339, 2340, 2342, 2344, 2345, 2347, 2349, 2351, 2355 and up, 2356-A, 
2357-A and up, and 8277-1 through 8277-40, and all AAF Nos. eligible.  (Use 
manufacturers serial numbers if available.) 
 
Required Equipment In addition to the pertinent required basic equipment specified in CAR 4a, the following  
 items of equipment must be installed: 
  Landplane: Items 101, 102, 103, and 104. 
  Seaplane:  Items 103, 104 and 151. 
 
Data Pertinent to All Models 
Datum Wing leading edge 
 
Leveling Means Left upper longeron at window 
 
Certification Basis Type Certificate No. 698 (CAR 4a) 
 
 Production Basis  Approved for production of spare parts only under Production Certificate No. 206. 
 
 Export Eligibility  Deleted as of - July 31, 1995 
 
 
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 an asterisk (*).  The asterisk denotes that approval has been obtained by someone 
other than the manufacturer.  An item marked with an asterisk may not have been manufactured under an FAA 
monitored or approved quality control system, and therefore attention should be paid to workmanship and 
conformity with pertinent data called for in this specification. 
 
Propellers and Propeller Accessories 
 
 1. Propeller - Hartzell ground adjustable, hub HA12U,  +18 lbs. (-52) 
  blades 7414 to 6814 or 7214M to 6814M. 
  Eligible on all models and engines at diamet er and static r.p.m. limits shown for fixed  
  pitch wood propellers. 
 
 2. Propeller - Sensenich M74CX-2 fixed pitch metal +21 lbs. (-52) 
  Static r.p.m. at maximum permissible throttle setting: 
   Not over 2550, not under 2225.  No additional tolerance permitted. 
  Diameter: Not over 72 in., not under 68 in. 
 
 103. Propeller - wood (fixed or adjustable pitch)  +11 lbs. (-52)

A-698 Pa ge 4 of 7 
 
Engines and Engine Accessories - Fuel and Oil System 
  No aircraft of these models shall be eligible fo r original certification with single ignition engines after 
August 1, 1941.  In addition, no aircraft of these models shall be eligible for recertification unless such 
aircraft were either previously certificated with single ignition engines or were originally certificated 
prior to August 1, 1941. 
 
 104. Carburetor air heater (Dwg. D726B)  +2 lbs. (-39) 
 
 105. Oil filter Fram PB-5, Kit No. 520, Fram installation Dwg. 61548 +4 lbs (-27) 
   
 106. Alternate fuel gauge, Scott model A-22P, installed per Scott Bulletin I-136. Neglect Weight 
 
 107. Auxiliary fuel tank  (6 gallon capacity)  +6 lbs. (+24) 
  Installed in accordance with Kit and Dwg. Nos.  P-18 and P-19 supplied by J. J. Villnave,  
  5607 Virginia, Kansas City, Missouri.  (Elig ible on land and seaplanes with wood spars.) 
 
 307. Alternate fuel tank   (9 gallons)   -3 lbs (-18) 
         
 309. Engines  (Lycoming  -- see Engi ne Specification No. 199 and 210)  (-39) 
  A. Models J3L and J3L-S   +13 lbs. 
   (1)  O-145-A2,  Engine Limits for all operations, 2300 r.p.m. (55 hp.) 
   (2) O-145-A3,  Engine Limits same as for O-145-A2 +15 lbs. 
 
  B. Models J3L-65 and J3L-65S  
   (1) O-145-B2,  Engine limits same as for O-145-B1 +11 lbs. 
   (2) O-145-B3,  Engine limits same as for O-145-B1 +14 lbs. 
 
 311. Cabin and carburetor heater   +1 lb.  (-39) 
 
 314. Carburetor heater, cabin heater and muffler combined  +3 lbs. (-39) 
  (Required if Item 104 is removed.) 
 
Landing Gear and Floats 
 101. 8.00-4 wheels  (Hayes 840) with tires  +20 lbs. (+3) 
 
 102. Tail skid     +4 lbs.(+190) 
 151. Edo 54-1140 floats with one wate r rudder (147 lbs.) +106 lbs. (+18) 
 204. Heath 1460A float installation  (Model J3L-65S only) (166 lbs.) +121 lbs. (+14) 
  Bungee must be installed in the elevator control system  
  per Piper Dwg. No. 80352 
 205. Scott Aviation Corporation Model B-711 br ake pressure unit Neglect Weight Change 
 206. Scott Model 4200-B1 Hydraulic parki ng brake valve  Neglect Weight Change 
  (See Scott Bulletin 1-116, Parking Brake Installation Instruction). 
 207. Edo 60-1320 floats with water rudde rs    (171 lbs.) +130 lbs. (+17) 
 *208. LCN shock strut      +7 lbs. (+3) 
  (Per LCN Corporation Dwg. 11000 and Kit Installation Instruction) 
  (Each shock strut must either have a CAA Form ACA-186 attached, or be identified with  
  the symbol "CAA-PMA".) 
 *209. Consolidair Model 17 wheel fenders, inst alled per Consolidair Dwg. 0041 +9 lbs. (+3) 
 *210. One nose wheel, 5.00-4, Type III,   Firestone Mode l 5C2M-1, with 5.00-4 4-ply rating tire  +8 lbs. (-31) 
  and tube.  (Used with Testerman Tricycle-Type landing gear, Item 211.) 
 *211. Tricycle landing gear - Testerman Model SPM-1  (J3L -65 only).  Install in accordance   +17 lbs.  (-29.5) 
  with Stewart-Pearce Company, Tulsa, Oklahoma,  
  Installation Manual (Report No. SPR-6), dated July 9, 1949.   
  Placard all airplanes "SOLO FROM REAR SEAT" and restrict C. G. range to (+11.2) to (+18.3).   
  Net weight change for SPM-1 installation (including Items 210 and 308(c)) 
 212. Shock strut - cord and hydraulic type Piper P/N 12843, installed per Piper Dwg. 10534. +4 lbs. (+3) 
 303. Wheel streamlines    +6 lbs. (+3)

Page 5 of 7 A-698 
 
 304. Tail Wheel Installations: 
  (a) 6x2.00 steerable tail wheel - Ai rcraft Associates +3 lbs. (+197) 
    
  (b) 6x2.00 steerable tail wheel - Scott Aviation Corp. Model CST-12 +3 lbs. (+197) 
    
  (c) 6x2.00 steerable tail wheel - Scott Aviation Corp. Model 3-21 +5 lbs. (+197) 
    
  *(d) Steerable tail wheel - Lang (former ly Decker) Model D-501A +2 lbs. (+197) 
 
 308. Wheels 
  (a) 18x8-3   (Goodyear 3LNBM) with tires  -2 lbs.  (+3) 
 
  (b) 7.00-4  (Shinn 2A or 2AV) with tires  -1 lbs. (+3) 
 
  (c) 8.00-4, Type III, wheel brake assemblies +12 lbs. (+3) 
   Goodrich Model 841; Wheel assembly No. D-3-13,  
   Brake assembly No. D-2-113, with 4-ply rating tires and tubes. 
   When used with Item 211   +12 lbs. (+24) 
 
  (d) Goodyear Model CL6HBM, (7.00-6)   (cross-wind wheel) +29 lbs. (+3) 
   Wheel Assembly No. 266AX36 
   Brake Assembly No. 266AX55 
   Wheel Installation No. 266AX54 
 
 310. Skis (Eligible on any airplane of these models provided the propeller Use Actual Weight Change 
  installation meets the minimum gr ound clearance.  The maximum weight 
  of the skiplane will be the same as for the corresponding landplane or that 
  shown in parenthesis after ski model, whichever is less). 
  
 *(a) Piper S-1000 (maximum 1200 lbs.). 
 *(b) Fairbanks MF-5  (maximum 1310 lbs.). 
 *(c) Federal SA-1  (maximum 1200 lbs.). 
 *(d) Federal SC-1   (maximum 1400 lbs.). 
 *(e) Aviation Service B   (maximum 1100 lbs.). 
 *(f) Air Transport 1220-480   (maximum 1220 lbs.). 
 *(g) Air Transport 1460-580   (maximum 1460 lbs.). 
 *(h) Marston MFS-1600   (maximum 1600 lbs.). 
 *(i) Heath 655   (maximum 1310 lbs.). 
 *(j) Heath 725   (maximum 1450 lbs.). 
 *(k) Air Transport 1224-580-1   (maximum 1220 lbs.). 
 *(l) Marston MFS-1200   (maximum 1200 lbs.). 
 *(m) Wollam W-1650   (maximum 1650 lbs.). 
 *(n) Heath 725A   (maximum 1450 lbs.). 
 *(o) Federal SKT-1   (maximum 1400 lbs.). 
 *(p) Federal SA-2   (maximum 1400 lbs.). 
 *(q) Federal SC-2   (maximum 1650 lbs.). 
 *(r) Washington Aircraft 1200   (maximum 1200 lbs.) 
 *(s) Troyer W-54   (maximum 1200 lbs.) 
 *(t) Call Model S-1 (with 8.00-4 tires onl y) per Call Dwg. 1002   (maximum 1800 lbs.) 
 *(u) Federal A-1500 or A-1500A   (maximum 1500 lbs.) per Federal Dwg. 11R262 
 *(v) Federal A-1850   (maximum 1850 lbs.) per  Federal Dwg. 11R262 
 *(w) Federal A-2000 or A-2000A   (maximum 2000 lbs.) per Federal Dwg. 11R262

A-698 Pa ge 6 of 7 
 
 *(x) Federal AWB-2100 wheel-ski installed in  accordance with Federal Aircraft Works,  
  Minneapolis, Minnesota, Dwg. 11R1101. 
 The following placards are required: 
   (a) "Do not extend or retract skis while in motion on the ground." 
   (b) On the ski position selector box 
   "Ski control"   "Up-Neutral-Down" 
 *(y) Wesco per Western Aircraft E quipment Company Dwgs. Nos. 12 and 148. 
  (1) A-15   maximum 1500 lbs.) 
  (2) A-20 or AS-2   (maximum 2000 lbs.) 
  (3) A-25, AS-2A or AS-2B   (maximum 2500 lbs.) 
 
 313. Dual brake installation   (Dwg. D4101-C) 
 
 316. Wollam 1200 plywood float in stallation  +137 lbs. (+16) 
  (Model J3L-65S only)   (182 lbs.) 
  Bungee must be installed in the elev ator control system per Piper Dwg. C-85. 
 
Electrical Equipment 
 202. Battery (Reading 3-BRL-6)   +8 lbs.   (+41) 
 
 302. Battery  (Exide 3AC-7 or Willard SYR-7-3) +10 lbs. (-19) 
 
 315. Generator installations (w ind-driven).  +11 lbs. (+3) 
  (a) General Armature AG-40 
 
 317. Landing lights in wing leading edge per Piper Dwg. 12534 +4 lbs. (+5) 
 
 
Interior Equipment 
 401. Windshield defroster    +1 lb. (-17) 
 
 402. Slip-not stabilizer control Model 10-C  +2 lbs. (+72) 
  (Installed per Westfield Industries, Salem, Illinois,  
  Dwg. 1 and Kit Installation Instructions) 
 
Miscellaneous   (Not Listed Above) 
 201. Anchor and rope    +12 lbs. (+49) 
 
 301. Friese type ailerons replacing unbalanced type No Weight Change 
 305. Emergency exit    No Weight Change 
 312. Two hinge tail surfaces (D-4152-C and D-4157-C) No Weight Change 
 *601. Wing tip spill plate (J3L-65 only) installed in  
  accordance with Flo-Trol Splate Co., Wahpeton,  
  North Dakota, Kit No. 100,  dated September 1, 1949,  
  for wings with wood spars and Kit No. 200, dated  
  October 1, 1949, on wings with metal spars.   
  Lower static propeller limit shall not be under 2440 r.p.m. 
 
 *602. Brodie Suspending Gear 
  (Aircraft of 1220 lbs. maxi mum weight, and 65 hp. min.) 
  installed in accordance with Brodie Engineering Corp. 
  2107 Maryland Avenue, Baltimore, Maryland 
  Dwg. No. X46R6187. 
 
  (a) Complete installation includi ng fixed mount, hook,  +37 lbs. (-2) 
   arm and cables.  The following placards are required: 
   (1) "Intentional spins prohibited with Brodie Hook installed; 
    (Spins permitted with fixed mount only installed)". 
 
   (2) At the release handle:  "Warning - Suspending gear hook release."

Page 7 of 7 A-698 
 
  (b) Installation of fixed mount only,   +15 lbs. (-3) 
   in accordance with Dwgs. X45D17370,  
   X45G17375, X45G17393 and X45B17394. 
 
   Aircraft incorporating Item (a) may be operated, in accordance with required operating  
   instructions, on the Brodie Aerial Track Airport erected at Diffendall (Eastern) Airport,  
   Baltimore, Maryland.  These operating inst ructions are contained in the CAA approved  
   Brodie pilot operating Manual entitled "Pilot Oper ating Instructions for Piper J3 and PA-11  
   Airplanes for Landing and Takeoff on Aerial Track Airports," which must remain in the  
   airplane during such operation, and must retain its identity as an individual manual. 
 
NOTE 1 Current weight and balance report includi ng list of equipment included in certificated  
  empty weight, and loading instructions when necessary, must be in each aircraft at the time  
  of original certification and at all times thereafter (except in the case of air carrier operators  
  having an approved weight control system). 
 
NOTE 2 Placard front cockpit, "Solo flying from rear seat only."  Placard may be removed if individual  
  aircraft actual weight and balance show that the approved C. G. limits will not be exceeded under  
  any loading condition.  Manufacturer recommends that all J-3 airplanes be flown solo from the rear seat. 
 
NOTE 3 Serial Nos. 4373, 4419, 4435, 4438, 4445, 4446,  4447, 4449, 4450, 4451, 4452, 4457, 4458, 4459, 4460,  
  4464, 4466, 4467, 4469, 4471, 4473, 4474, 4475, 4477, 4478, 4495, and 4502 eligible with the following  
  C. G. Range: 
  Landplane (+10.6) to (+21.5)  
  Seaplane (+10.7) to (+18.6)  with Edo and Wollam floats 
 
  Empty weight C. G. ranges: 
  Landplane (+8.1) to (+19.1)  
  Seaplane (+8.5) to (+16.4)  with Edo and Wollam floats 
 
NOTE 4 Serial Nos. 7842, 7845 to 7883, inclusive, 7912 a nd up of Model J3L-65 are eligible for 1170 lbs.  
  maximum weight with minimum pr opeller diameter of 68 inch.  All other serial numbers of this  
  model also eligible for 1170 lbs. maximum weight  with minimum propeller diameter of 68 inches  
  provided lift strut end fittings and fuselage lift strut attachment fittings are revised in accordance  
  with Piper Dwgs. C-16 and C-22, respectively. 
 
NOTE 5  Army TG-8 gliders having Serial Nos. G-1 and up are eligible for certification as J3L Series 
airplanes under the provisions of this aircraft specification, provided that they have been converted 
to J3L Series airplanes and are in conformity with the approved Piper data.  Conversion procedure 
is given in Safety Regulation Release No. 188. 
 
NOTE 6  The following parts from TG-8 gliders can be used  directly in Piper J3 Series airplanes.  The  
   replacement of such complete component parts is considered a minor repair in accordance with  
   Advisory Circular 43.13-1: 
 
   Tail surfaces; Landing gear tires and wheels; Tail wheel; Wings, provided the spoiler and spoiler  
   controls are removed; The control system from  (and including) the middle occupant aft; Wing  
   struts; Instruments, same as or equi valent to those used on powered aircraft. 
 
   The fuselage primary structure of the TG-8 glider  aft of the main landing gear fittings can be used  
   on Piper J-3 Series airplanes; however, the use of  such parts entails a major repair and must be  
   handled as such in accordance with current Advisory Circulars. 
 
 
 
 
.....END.....
```

## ADs (13, in force first)

- [AD 2025-02-11](https://openairdocs.org/ad/2025-02-11): Rudder Structure · FS 2001 J5A (Army L-4F), J5A-80, J5B (Army L-4G) and 67 more. Effective Mar 20, 2025
- [AD 2015-08-04](https://openairdocs.org/ad/2015-08-04): Wings · FS 2000 L-14, AE-1, HE-1 and 77 more. Effective Jun 3, 2015
- [AD 2001-23-17](https://openairdocs.org/ad/2001-23-17): GNS 430 units · Cessna 172, 182, 206 and 209 more. Effective Dec 28, 2001
- [AD 85-06-04](https://openairdocs.org/ad/85-06-04): Fuel Tank · FS 2001 AE-1, HE-1, J5A-80 and 60 more. Effective May 4, 1985
- [AD 78-10-03](https://openairdocs.org/ad/78-10-03): Fuel Venting · FS 2001 AE-1, HE-1, J5A-80 and 66 more. Effective May 23, 1978
- [AD 68-05-01](https://openairdocs.org/ad/68-05-01): Exhaust Mufflers · FS 2001 J5A-80, J5A (Army L-4F), J5B (Army L-4G) and 67 more. Effective Mar 31, 1968
- [AD 58-12-02](https://openairdocs.org/ad/58-12-02): Aileron Hinge Brackets · Piper J-3, J3C-40, J3C-50 and 20 more
- [AD 58-01-07](https://openairdocs.org/ad/58-01-07): Control System Turnbuckles · FS 2001 J5A-80, J5A (Army L-4F), J5B (Army L-4G) and 18 more
- [AD 52-07-03](https://openairdocs.org/ad/52-07-03): Lift Strut Rework · Piper J-3, J3C-40, J3C-50 and 15 more
- [AD 47-50-03](https://openairdocs.org/ad/47-50-03): Canvas Seat Inspection · Piper J-3, J3C-40, J3C-50 and 14 more
- [AD 49-14-01](https://openairdocs.org/ad/49-14-01): Elevator Connector Tube Fitting · FS 2003 J-3, J3C-40, J3C-50 and 17 more
- [AD 99-01-05 R1](https://openairdocs.org/ad/99-01-05-R1) (historical): Wings · FS 2000 L-14, AE-1, HE-1 and 73 more. Effective Jan 14, 2014
- [AD 99-01-05](https://openairdocs.org/ad/99-01-05) (historical): Wing Lift Struts or Forks · FS 2000 L-14, AE-1, HE-1 and 73 more. Effective Feb 8, 1999

## Registered aircraft by registry model (OpenAirDocs)

- [Piper J3L-65](https://openairdocs.org/model/piper-j3l-65): 179 aircraft (registry code 7100546)
- [Piper J3L](https://openairdocs.org/model/piper-j3l): 15 aircraft (registry code 7100542)
- [Piper J3L-65S](https://openairdocs.org/model/piper-j3l-65s): 1 aircraft (registry code 7100550)
- [Piper J3L-S](https://openairdocs.org/model/piper-j3l-s): 0 aircraft (registry code 7100544)

## STCs approved under this data sheet (93, first 50)

- [STC SA01233SE](https://openairdocs.org/stc/SA01233SE): Fabrication and installation of Alaskan Bushwheel LLC tail wheel and fork assembly. ABI, LLC
- [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 SA02525LA](https://openairdocs.org/stc/SA02525LA): Installation of Wheel and Brake Assemblies. Game Aerospace LLC
- [STC SA01704LA](https://openairdocs.org/stc/SA01704LA): Installation of the Grove Disk Brake System. Grove Aircraft Landing Gear Systems Inc.
- [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 SA00715CH](https://openairdocs.org/stc/SA00715CH): Installation of Air Energy Service P/N J-3-212 ball type, sight fuel tank quantity gauge on the side of an AESI P/N AESI-125 12-gallon wing tank.. Crown MN Aviation LLC
- [STC SA1496GL](https://openairdocs.org/stc/SA1496GL): Installation of a 12-gallon fuel tank and fuel system in the left wing or left and right wings.. Crown MN Aviation, LLC
- [STC SA02386AK](https://openairdocs.org/stc/SA02386AK): Replacement of existing landing and/or taxi light reflector and bulbs with Light Emitting Diode (LED) lighting systems. AeroLED's Holding LLC
- [STC SA03898NY](https://openairdocs.org/stc/SA03898NY): Installation and maintenance of ORATEX covering and coating material. Aircraft Design & Certification Ltd
- [STC SA4503NM](https://openairdocs.org/stc/SA4503NM): Remove original cloth covering and install Ceconite covering. Ceconite Division of Poly-Fiber Inc.
- [STC SA02582AK](https://openairdocs.org/stc/SA02582AK): Installation of Airframes Alaska Brake Pedal and Master Cylinder Assembly. Airframes Alaska LLC
- [STC SA02579AK](https://openairdocs.org/stc/SA02579AK): Installation of Swing bar. Willow Mountain Ranch
- [STC SA3-356](https://openairdocs.org/stc/SA3-356): Installation of Wipaire Skis Model C-2200 main ski and Model AWT-2500 or AWT-2500A tail wheel skis.. F.Atlee Dodge Aircraft Services
- [STC SA3-357](https://openairdocs.org/stc/SA3-357): Installation of Wipaire Skis Model C-2200 main skis and Model AWT-2500 or AWT-2500A tail wheel ski.. F.Atlee Dodge Aircraft Services
- [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 SA01015SE](https://openairdocs.org/stc/SA01015SE): Installation of eligible Alaska Bushwheel, Inc. wheels and TSO-C62d tires. ABI LLC
- [STC SA02553AK](https://openairdocs.org/stc/SA02553AK): Fabrication and installation of a Tail Wheel Anti-Shimmy Dampener. Keller Engineering Group 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 SA02268CH](https://openairdocs.org/stc/SA02268CH): Installation of Airwolf Filter Corp. Air Oil Separator. Airwolf Filter Corporation
- [STC SA00441WI-D](https://openairdocs.org/stc/SA00441WI-D): Installation of Bendix/King KLX 100 Emergency VHF Comm.. Honeywell International Inc
- [STC SA04165NY](https://openairdocs.org/stc/SA04165NY): Installation of Latitude Technologies Skynode S200 Satcom system must be performed. Latitude Technologies Corporation
- [STC SA2057SO](https://openairdocs.org/stc/SA2057SO): Installation of shoulder harness.. Alpha Aviation Inc
- [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 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 SA3606NM](https://openairdocs.org/stc/SA3606NM): Installation of landing gear fueling step.. F. Atlee Dodge Aircraft Services, LLC
- [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 SA00780SE](https://openairdocs.org/stc/SA00780SE): Installation of the True Lock Safety Retention Axle Lock Nut System. True Lock LLC
- [STC SA02452AK](https://openairdocs.org/stc/SA02452AK): Installation of F. Atlee Dodge Aircraft Services, LLC, Pilot s Safety Barrier Net. F. Atlee Dodge Aircraft Services, 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 2](https://openairdocs.org/stc/SA02402SE%20PAGE%202): 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 SA02295SE](https://openairdocs.org/stc/SA02295SE): Installation of an alternate method of fastening aluminum wing ribs to wood spars. Rainbow Flying Service LLC
- [STC SA02128LA](https://openairdocs.org/stc/SA02128LA): Installation of aileron and flap hinge repair bushings. Univair Aircraft Corporation
- [STC SA01765SE](https://openairdocs.org/stc/SA01765SE): Installation of Alaskan Bushwheel TSO-C26d wheels, Part Number (P/N) ABI-1010. ABI, LLC
- [STC SA01026SE](https://openairdocs.org/stc/SA01026SE): Improved fuel gascolator assembly.. Steve's Aircraft
- [STC SA02825NY PAGE 1](https://openairdocs.org/stc/SA02825NY%20PAGE%201): Installation of Aerospace Logic Aircraft Instruments. Aerospace Logic Inc.
- [STC SA00270BO](https://openairdocs.org/stc/SA00270BO): Installation of a Teledyne Continental A-65-8, A-65-8F, A-65-9, A-75-8, A-75-8F, A-75-9, C-75-8, C-75-12, C-85-8, C-85-12, C-90-8F or C-90-12F engine and corresponding propeller identified under Limitations and Conditions, and components for a landplane maximum gross weight of 1220 lbs.. Clyde R Smith Jr
- [STC SA3AL](https://openairdocs.org/stc/SA3AL): Installation of Fred A. Shaw tundra-bird Model 2500 skis.. Aircraft Innovations, LLC
- [STC SA5-13](https://openairdocs.org/stc/SA5-13): Installation of 8.50x6 tires and tubes with Hayes 6-inch wheels.. Aircraft Innovations, 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 SA01516SE](https://openairdocs.org/stc/SA01516SE): Replacement of the Scott Master Brake Cylinder (Non-Vented Diamphram type) with a Steve s Aircraft Model SA6-01 Master Cylinder with a vented reservoir.. Steve's Aircraft
- [STC SA02007AK](https://openairdocs.org/stc/SA02007AK): Installation of main landing gear long step no. 3195.. F Atlee Dodge Aircraft Service
- [STC SA00680SE](https://openairdocs.org/stc/SA00680SE): Installation of Electronics International model UBG-16 or UBG-16T bar graph engine analyzer.. Electronics International
- [STC SA5-65](https://openairdocs.org/stc/SA5-65): Installation of Goodyear 25 x 11.0 - 4 Type IV tires with tubes on Goodrich Model 841696 4-inch wheels on main landing gear, using Alaskan Aircraft Equipment Supply Model A-1 rim adapters. Douten Thomas
- [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.

All 93: https://openairdocs.org/tcds/A-698/stcs.md

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