# TCDS A26WE: Weatherly Aircraft Company

- Type: Type certificate data sheet
- Status: Current
- Holder: Weatherly Aircraft Company
- Revision: 8
- Revised: November 5, 2014
- Product: Aircraft, Small Airplane
- Certification basis: Part 21, Part 23, Part 36, Part 91, Part 137
- Registered aircraft: 32, by the registry models matched to it (OpenAirDocs)
- Data sheet PDF: https://openairdocs.org/files/sha256/47/55/4755d767765d99b82596afe38970688e24492d20d62d4c3b74bd9d459d7e2d68
- FAA DRS: https://drs.faa.gov/browse/excelExternalWindow/F558ED89B701B13B86257D8E00641825.0001
- Page: https://openairdocs.org/tcds/A26WE

## Models (5)

As the data sheet lists them.

- 620B-TG
- 620
- 620A
- 620TP
- 620B

## 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 
Rev. No. 8 6 6 6 6 6 6 6 6 
 
DEPARTMENT OF TRANSPORTATION 
FEDERAL AVIATION ADMINISTRATION 
 
A26WE 
Revision 8 
Weatherly 
620 
620TP 
620A 
620B 
620B-TG 
November 5, 2014 
TYPE CERTIFICATE DATA SHEET A26WE 
 
Type Certificate Holder: Weatherly Aircraft Company  
 2034 W/ Potomac Avenue 
 Chicago, Illinois 60622-3152 
 
Type Certificate Ownership Record GBECK, Inc. (D.B.A.) Weatherly Aviation Company, Inc., 2100 Flightline Drive. 
Lincoln, California 95648 transferred ownership of TC A26WE to Weatherly Aircraft 
Company on November 6, 2000 
 
I  - Model 620 (Restricted Category) Approved October 24, 1979 
  (See ALL MODEL Section) (See NOTES Section) 
 
Engine Pratt & Whitney R985-AN-1, AN-3, or AN-14B 
 
Fuel 80/87 Minimum Grade Aviation Gasoline.  Alternate fuel is 100LL. 
 
Engine Limits Engine Model AN-1 & AN-3 HP RPM In. Hg. Press Alt. 
 Takeoff (1 min.) at SL 450 2300 37.5 SL 
 Maximum Continuous at SL 350 2100 33.0 SL 
 Maximum Continuous 350 2100 32.0 3000 ft. 
 (Rated Pressure Alt.) 350 2100 31.0 6000 ft. 
 
 Straight line variation of manifold pressure between points listed. 
 
 Engine Model AN-14B HP RPM In. Hg. Press Alt. 
 Takeoff (1 min.) at SL 450 2300 36.5 SL 
 Maximum Continuous at SL 350 2100 31.5 SL 
 Maximum Continuous 350 2100 30.5 3000 ft. 
 (Rated Pressure Alt.) 350 2100 29.5 6000 ft. 
  350 2100 29.0 7800 ft. 
 
 Straight line variation of manifold pressure between points listed. 
 
Propeller & Propeller Limits Hartzell HC-B3R30-4 or -4B Hub with R10152-5½ R Blades 
 Diameter:  Not over 95½ ins.; Not under 95½ ins. 
 Pitch settings at 30" station: 
 (Constant Speed) - 16° Low, 28° High 
 Static RPM at maximum throttle setting not over 2300 RPM; not under 2200 RPM.  
 
Airspeed Limits Without Spreader or Tip Vanes 
 VNE - Never Exceed 176 mph (153 knots) IAS or CAS 
 VNO - Normal Operating 140 mph (122 knots) IAS or CAS 
 VA   - Maneuvering 129 mph (112 knots) IAS or CAS 
 
 With P/N 50453 Spreader Installed 
 VNE - Never Exceed 155 mph (135 knots) IAS or CAS

A26WE 2 
 
 
 With P/N 50520 Tip Vanes Installed 
 VNE - Never Exceed 166 mph (144 knots) IAS or CAS 
 
 Airspeed limits are unchanged with Cowl Speed Ring installed P/N 50784 per  
 Drawing 50783 
 
Maximum Operating 
Altitude 15,500 ft. 
 
C.G. Range Inches aft of datum (+22.1) to (+26.0) at all weights 
 
Empty Weight C.G. Range None 
 
Maximum Weight 4000 lbs. 
 
No. of Seats 1 (+68.0) 
 
Hopper Capacity 2000 lbs. (+15.0) 
 
Baggage Shelf 25 lbs. (+91.25) 
 
Fuel Capacity 72.5 gal. total 
 Right Wing Tank 27½ gal. with unusable 2½ gal. (+36.0) 
 Left Wing Tank (combined with center tank) 45 gal. with unusable 5 gal. (+36.0) 
 
Oil Capacity 6.7 gal. plus 1 gal. in system (-22.2) 
 
Control Surface Rudder Left 20° ± 1° Right 20° ± 1° 
 Elevator Up 27° ± 1° Down 15° ± 1° 
 Aileron Up 26° ± 1½° Down 13½° ± 1½° 
 
Serial Nos. Eligible 1501 and subsequent 
 
II - Model 620TP (Restricted Category) Approved October 17, 1980 
  (See ALL MODEL Section) (See NOTES Section) 
 
Engine Pratt & Whitney PT6A-11AG 
 
Fuel Jet A and Jet B fuel.  Refer to P&WC Service Bulletin No. 12144.  With certain 
limitations, automotive diesel fuels are approved for use. 
 
Engine Limits Engine HP NP RPM NG RPM 
 Takeoff (5 min. SL) 500 2200 (100%) 38,100 (101.5%) 
 Maximum Cont., SL 350 2000 (91%) 38,100 
 Maximum Reverse 475 2112 (96%) 38,100 
   
  Maximum torque (steady) = 1194 lb. ft. (38.6 psig) 
      (5 min. SL) 
  Maximum torque (accel.) = 1800 lb. ft. (58.3 psig) 
      (5 sec.) 
 
Maximum Permissible Temperature Inter-Turb. Temp. 
     Takeoff 1292°F   (700°C) 
     Maximum Continuous 1292°F   (700°C) 
     Starting Transient 1994°F   (1090°C) 
 
  Oil Temperature 
   Normal range 50°F to 210°F (10°C to 99°C) 
   Maximum 210°F (99°C)

3 A26WE 
 
  Oil Pressure 
     Normal range (27,000 RPM NG or above) 80-100 psig 
   Minimum  40 psig 
   Maximum  100 psig 
 
  Fuel Pressure 
   Engine inlet pressure is measured at the inlet to 
the engine high pressure gear pump.  (This point is also the outlet of the Weatherly 
installed low pressure pump mounted on the engine). 
 
   Minimum 15 psig 
   Maximum 35 psig     
 
Propeller & Propeller Limits Hartzell reversing propeller with Woodward overspeed governor 
 
  Model HC-B3T 
  Hub No. HC-B3TN-3 
  Blade No. T10282-6 
  Diameter Maximum 96 inches 
    Minimum 92 inches 
  Pitch settings at 30 inch radius 
   Low pitch 16° ± 0.5° 
  Propeller spinner, Hartzell P/N 3434-6 
  Overspeed governor, Woodward P/N A210507 
 
Airspeed Limits Without Spreader or Tip Vanes 
 VNE - Never Exceed 176 mph (153 knots) IAS or CAS 
 VNO - Normal Operating 140 mph (122 knots) IAS or CAS 
 VA   - Maneuvering 129 mph (112 knots) IAS or CAS 
  
 With P/N 50453 Spreader Installed 
 VNE - Never Exceed 155 mph (135 knots) IAS or CAS 
 
 With P/N 50520 Tip Vanes Installed 
 VNE - Never Exceed 166 mph (144 knots) IAS or CAS 
 
C.G. Range Inches 3500 lbs. gross weight (+24.8) to (+22.1) with 
  straight line variation to 4000 lbs. gross weight 
  (+23.6) to (+22.1) 
 
Empty Weight C.G. Range None 
 
Maximum Weight 4000 lbs. 
 
No. of Seats 1 (+68.0) 
 
Hopper Capacity 2000 lbs. (+15.0) 
 
Baggage Shelf 15 lbs. (+91.25) 
 
Fuel Capacity 96 gal. total 
 Right Main Tank with Right Outer Wing Tank, 42 gal.,  unusable 6 gal. (+36.0) 
 Left Main Tank (combined with center tank) with Left Outer Wing Tank,  54 gal., 
 unusable 6 gal. (+36.0) 
 
Oil Capacity 2.3 gal. plus .75 gal. in system (-24.0) 
 
Maximum Operating Altitude 15,000 ft.

A26WE 4 
 
 
Control Surface Rudder Left 20° ± 1° Right 20° ± 1° 
 Elevator Up 27° ± 1° Down 15° ± 1° 
 Aileron Up 26° ± 1½° Down 13½° ± 1½° 
 
Serial Nos. Eligible 1502 and subsequent, Model 620TP airplanes have the letters TP following the 
 numerical serial number. 
 
III - Model 620A (Restricted Category) Approved March 25, 1987 
  (See ALL MODEL Section) (See NOTES Section) 
 
Engine Pratt & Whitney R985-AN-1, AN-3, or AN-14B 
 
Fuel 80/87 Minimum Grade Aviation Gasoline.  Alternate fuel is 100LL. 
 
Engine Limits Engine Model AN-1 & AN-3 HP RPM In. Hg. Press Alt. 
 Takeoff (1 min.) at SL 450 2300 37.5 SL 
 Maximum Continuous at SL 350 2100 33.0 SL 
 Maximum Continuous 350 2100 32.0 3000 ft. 
 (Rated Pressure Alt.) 350 2100 31.0 6000 ft. 
 
 Straight line variation of manifold pressure between points listed. 
 
 Engine Model AN-14B HP RPM In. Hg. Press Alt. 
 Takeoff (1 min.) at SL 450 2300 36.5 SL 
 Maximum Continuous at SL 350 2100 31.5 SL 
 Maximum Continuous 350 2100 30.5 3000 ft. 
 (Rated Pressure Alt.) 350 2100 29.5 6000 ft. 
  350 2100 29.0 7800 ft. 
 Straight line variation of manifold pressure between points listed. 
 
Propeller & Propeller Limits Hartzell HC-B3R30-4B Hub with R10152-5½  Blades 
 Diameter:  Not over 95½ ins.; Not under 95½ ins. 
 Pitch settings at 30" station: 
 (Constant Speed) - 16° Low, 28° High 
 Static RPM at maximum throttle setting not over 2300 RPM; not under 2200 RPM.  
 
Airspeed Limits Without Spreader 
 VNE - Never Exceed 176 mph (153 knots) IAS or CAS 
 VNO - Normal Operating 140 mph (122 knots) IAS or CAS 
 VA   - Maneuvering 129 mph (112 knots) IAS or CAS 
  
 With P/N 50453 Spreader Installed 
 VNE - Never Exceed 155 mph (135 knots) IAS or CAS 
 
 Airspeed limits are unchanged with Cowl Speed Ring installed P/N 50784 per  
 Drawing 50783 
 
Maximum Operating 
Altitude 15,500 ft. 
 
C.G. Range Inches aft of datum (+22.1) to (+26.75) at all weights 
 
Empty Weight C.G. Range None 
 
Maximum Weight 4000 lbs. 
 
No. of Seats 1 (+68.0) 
 
Hopper Capacity 2000 lbs. (+15.0)

5 A26WE 
 
Baggage Shelf 25 lbs. (+91.25) 
 
Fuel Capacity 72.5 gal. total 
 Right Wing Tank 27½ gal. with unusable 2½ gal. (+36.0) 
 Left Wing Tank (combined with center tank) 45 gal. with unusable 5 gal. (+36.0) 
 
Oil Capacity 6.7 gal. plus 1 gal. in system (-22.2) 
 
Control Surface Rudder Left 20° ± 1° Right 20° ± 1° 
 Elevator Up 27° ± 1° Down 15° ± 1° 
 Aileron Up 29° ± 1½° Down 11½° ± 1° 
 
Serial Nos. Eligible 1520 and subsequent 
 
IV - Model 620B (Restricted Category) Approved July 17, 1992 
  (See ALL MODEL Section) (See NOTES Section) 
 
Engine Pratt & Whitney R985-AN-1, AN-3, or AN-14B 
 
Fuel 80/87 Minimum Grade Aviation Gasoline.  Alternate fuel is 100LL. 
 
Engine Limits Engine Model AN-1 & AN-3 HP RPM In. Hg. Press Alt. 
 Takeoff (1 min.) at SL 450 2300 37.5 SL 
 Maximum Continuous at SL 350 2100 33.0 SL 
 Maximum Continuous 350 2100 32.0 3000 ft. 
 (Rated Pressure Alt.) 350 2100 31.0 6000 ft. 
 
 Straight line variation of manifold pressure between points listed. 
 
 Engine Model AN-14B HP RPM In. Hg. Press Alt. 
 Takeoff (1 min.) at SL 450 2300 36.5 SL 
 Maximum Continuous at SL 350 2100 31.5 SL 
 Maximum Continuous 350 2100 30.5 3000 ft. 
 (Rated Pressure Alt.) 350 2100 29.5 6000 ft. 
  350 2100 29.0 7800 ft. 
 
 Straight line variation of manifold pressure between points listed. 
 
Propeller & Propeller Limits Hartzell HC-B3R30-4B Hub with R10152-5½ R Blades 
 Diameter:  Not over 95½ ins.; Not under 95½ ins. 
 Pitch settings at 30" station: 
 (Constant Speed) - 16° Low, 28° High 
 Static RPM at maximum throttle setting not over 2300 RPM; not under 2200 RPM.  
 
Airspeed Limits Without Spreader 
 VNE - Never Exceed 176 mph (153 knots) IAS or CAS 
 VNO - Normal Operating 140 mph (122 knots) IAS or CAS 
 VA   - Maneuvering 129 mph (112 knots) IAS or CAS 
  
 With P/N 50453 Spreader Installed 
 VNE - Never Exceed 155 mph (135 knots) IAS or CAS 
 
 Airspeed limits are unchanged with Cowl Speed Ring installed P/N 50784 per  
 Drawing 50783 
 
Maximum Operating 
Altitude 15,000 ft. 
 
C.G. Range Inches aft of datum (+22.1) to (+27.5) at all weights 
 
Empty Weight C.G. Range None

A26WE 6 
 
 
Maximum Weight 4000 lbs. 
 
No. of Seats 1 (+70.0) 
 
Hopper Capacity 2000 lbs. (+15.0) 
 
Baggage Shelf 25 lbs. (+93.25) 
 
Fuel Capacity 97.5 gal. total 
 Right Wing Tank 40 gal. with unusable 2½ gal. (+36.0) 
 Left Wing Tank (combined with center tank) 57.5 gal. with unusable 5 gal. (+36.0) 
 
Oil Capacity 6.7 gal. plus 1 gal. in system (-22.2) 
 
Control Surface Rudder Left 20° ± 1° Right 20° ± 1° 
 Elevator Up 27° ± 1° Down 15° ± 1° 
 Aileron Up 29° ± 1½° Down 11½° ± 1° 
 
Serial Nos. Eligible 1550 and subsequent 
 
V- Model 620B-TG (Restricted Category)  Approved March 12, 1997 
  (See ALL MODEL Section) (See NOTES Section) 
 
Engine Allied Signal TPE331-1-151A  (See NOTE 7) 
 
Fuel Jet A , Jet A-1, Jet B, Jet P-4, and Jet P-5 fuel.  Refer to Allied Signal Service Bulletin 
No. EMS 53111, EMS 53112, EMS 53113, and EMS 53116.  (See NOTE 8).  
          
Engine Limits Engine HP NP RPM  
 Takeoff (SL) 500∗ 2000 (100%)  
 Maximum Cont., SL 500∗ 2000 (100%)  
 Maximum Reverse 475 1910 (96.5 %)  
  ∗ Maximum steady torque (SL)  = 1313 lb. ft (47.0 psig) 
 
 Ground Idle   64-66% (speed lever low)   
 Flight Idle   94.5-96.5% (speed lever high)  
   
Maximum Permissible Temperature Exhaust Gas Temp  
     Takeoff 1047°F   (564°C)  
     Maximum Continuous 1047°F   (564°C)  
     Starting Transient (1 sec.) 1472°F   (800°C)  
   
  Oil Temperature 
   Type I Oil Normal Range  40°F (-40°C) to 200°F (93°C) 
   Type II Oil Normal Range 40°F (-40°C) to 260°F (127°C) 
   Oil conforming to Allied Signal EMS 53110 ( Type I and Type II) 
 
  Oil Pressure 
     Normal  @ 100% speed (green) 70-120 psig 
   Normal Caution  (amber)  50-70 psig  
   Minimum @ 65% speed ground idle 50 psig 
   Maximum 120 psig 
 
  Fuel Pressure 
  Engine fuel pump inlet pressure is 5 psig plus true vapor pressure of fuel.  Engine inlet 
pressure is measured at the inlet to the engine high pressure gear pump.  (This point is 
also the outlet of the Weatherly installed low pressure pump mounted on the engine).  
See NOTE 9.

7 A26WE 
 
  Minimum (red line)   15 psig 
   Normal (amber arc) 15-20 psig 
   Normal (green arc) 20- 50 psig 
   Maximum (red line) 50 psig 
 
Propeller & Propeller Limits McCauley reversing propeller with Woodward overspeed governor 
  
  Model 3GFR34C602/100LA-2 
  Hub No. 3GFR34C602 
  Blade No. 100LA-2   
  Diameter: Maximum 98.0 inches 
     Minimum 96.0 inches 
   Pitch setting at 30 inch radius 
   Low pitch 9.5° ± 0.5° 
   Propeller spinner, McCauley  P/N E4858 
  Overspeed governor, Woodward P/N 895282-14 
 
  Propeller Speed 
   Normal 2000 rpm 
   Maximum (5 sec.) 2100 rpm   
   Maximum  (5 min.) 2020 rpm  
  
Airspeed Limits VMO - Maximum Operating  without Spreader 176 mph (153 knots) IAS 
 VMO - Maximum Operating  with Spreader 155 mph (135 knots) IAS 
 VNO - Normal Operating 140 mph (122 knots) IAS 
 VA - Maneuvering 129 mph (112 knots) IAS 
  Vy - Best Rate Climb    90 mph (  78 knots) IAS 
  
C.G. Range +19.5 to +26.5 inches aft of datum for all weights. 
 
Empty Weight C.G. Range 3328 lb. at +19.1 in. (with optional Spreader P/N 72097 installed 3272 lb. at +17.4 in.)  
  
Maximum Weight 4300 lb. (+24.73)  See NOTE 11. 
  
No. of Seats 1 (+73.0) 
 
Hopper Capacity 2000 lb. (+15.0) 
  
Baggage Shelf 25 lb. (+93.25) 
  
Fuel Capacity 130 gal. total , 14 gal. unusable (+36.0).  
 The fuel tank system consists of 7 interconnected tanks (2 in the left wing, 2 in the right  
wing, and 3 in wing center section) . 
   
Oil  Capacity 1.56 gal. total (-54.0) 
  
Maximum Operating Altitude 15,000 ft. 
  
Control Surface Rudder Left 20° ± 1° Right 20° ± 1° 
 Elevator Up 27° ± 1° Down 15° ± 1° 
 Aileron Up 29° ± 1½° Down 11½° ± 1½° 
  
Serial Nos. Eligible 1615, 1636, and 3000 and subsequent  
  
Specifications Pertinent to all Models 
 
Datum Wing leading edge outboard of fillet ( 6 inches forward of the main gear axle). 
 
Level Means Leveling lugs on outboard side of right hand fuselage frame near pilot's seat.

A26WE 8 
 
Certification Basis FAR 21.25(a) effective February 1, 1965, with policies contained in CAM 8 Appendix B 
Airworthiness Requirements for the Special Purpose of: 
   
  Agricultural Operations under FAR 21.25(b)(1). 
  Note:  In accordance with FAR 36.1(a)(2), compliance with the noise requirements 
was not shown.  Therefore, aircraft certificated under this certificate are only eligible 
for agricultural operations excepted by FAR 36.1(a)(2) and defined under FAR 137.3. 
 
  620TP Turboprop Installation:  FAR 23, Amendments 23-1 to 23-21; Subpart B - Flight, 
Subpart E - Powerplant and 23.1305 Powerplant Instruments.  (FAR’s 23.221, 23.954, 
23.967(a)(6), 23.973(d), 23.1093, 23.1305(q), 23.1305(s), and 23.1305(t) have been 
waived under the provisions of FAR 21.25) 
    
620B-TG Turboprop Installation:  FAR 23, Amendments 23-1 to 23-46; Subpart B - 
Flight, Subpart E - Powerplant.  (FAR’s 23.1305(s) and 23.1305(t) have been waived 
under the provision of FAR 21.25) 
 
Noise Control Act of 1972 
 
  Restricted Type Certificate issued October 24, 1979 
  Application for Type Certificate dated June 16, 1978 
 
Production Basis Production Certificate No. 416 
 
Export Eligibility Aircraft will be eligible for issuance of an Export Certificate of Airworthiness subject to 
compliance with Federal Aviation Regulations Part 21, Subpart L, Sections 21.321 
through 21.339.  The applicable procedures are contained in Advisory Circular 21.2.  
 
Equipment The basic required equipment as prescribed in the applicable airworthiness regulations 
(see Certification Basis) must be installed in the aircraft for certification. 
 
  In addition, the following items of equipment are required: 
 
 620: (a) FAA Approved Airplane Flight Manual dated October 24, 1979, and  
                                                                                           FAA approved revisi ons 
 
  (b) Weatherly Equipment List A-620 
 
 620TP: (a) FAA Approved Airplane Flight Manual dated October 15, 1980, and    
                                                                                           FAA approved revisions  
 
  (b) Weatherly Equipment list A-620TP 
 
 620A: (a) FAA Approved Airplane Flight Manual dated March 25, 1987, and    
           FAA approved revisions 
 
  (b) Weatherly Equipment List A-620A 
 
 620B: (a) FAA Approved Airplane Flight Manual dated July 16, 1992, and FAA  
                                                                                           approved revisions  
 
  (b) Weatherly Equipment List A-620B 
 
 620B-TG: (a) FAA Approved Airplane Flight Manual dated March 20, 1997, and   
                                                                                           FAA approved revisions  
 
  (b) Weatherly Equipment List A-620B-TG 
 
NOTE 1. Current weight and balance report including list of equipment included in certificated 
empty weight, and loading instructions, when necessary, must be provided for each 
aircraft at the time of original certification.

9 A26WE 
 
 The certification weight and corresponding center of gravity must include for Models 
620, 620A, and 620B undrainable system oil of 2.3 lb. at (-22.2) and unusable fuel of 7.5 
gals. at (+36.0). 
 
 The certificated empty weight and corresponding center of gravity must include for 
Model 620TP undrainable system oil for 5.25 lb. at (-24.0) and unusable fuel of 12 gals. 
at (+36.0). 
 
 The certificated empty weight and corresponding center of gravity must include for 
Model 620B-TG undrainable system oil for 11.7 lb. at (-54.0) and unusable fuel of 14 
gals. at (+36.0). 
 
NOTE 2. In addition to the operating limitations in this data sheet, area, economic, passenger and 
other appropriate operating limitations in accordance with FAR 21.25 shall be shown on 
placard or listing accessible to the pilot. 
 
 The following placard must be displayed in front of and in clear view of the pilot: 
 
 "This airplane must be operated as a restricted category airplane in compliance with the 
operating limitations stated in the form of placards, markings, and manuals." 
 
 For additional placards, see Weatherly Model 620, 620A, 620B, 620TP, and  620B -TG 
Airplane Flight Manuals. 
 
NOTE 3. 620 and 620A:  Alternator 24 volt, Motorola Model AN24N900, Maximum current load 
is limited to a total load of 20.8 Amps. 
 620B :  Alternator 24 volt, 50 Amps. Skytronics Model JASCO 7555T and/or 70 Amps 
Model JASCO 7655T with Voltage Controller J12M24SP is approved for thi s installation. 
 620B-TG:  Starter Generator Lucas Aerospace Model 23048-023 with Voltage Regulator 
General Electric CSV1105-30 is approved for this installation.  Maximum current load is 
limited to a total load of 250 Amps, 28.5 Volts.  
 
NOTE 4. 620TP and  620B-TG:  Flight into known icing conditions is prohibited.  Do not fly into 
areas of visible moisture when the temperature is below 40°F. 
 
NOTE 5. 620TP and  620B-TG:  Approved for reverse thrust during ground operation only. 
 
NOTE 6. All fuel and oil capacities are in US gallons. 
 
NOTE 7. The Allied Signal TPE331-1-151A engine is a derivative of the TPE331 -1 engine 
approved for this installation. 
 
NOTE 8. 620B-TG:  When operating at ambient temperature of 0°C or below, the fuel must 
contain an icing inhibitor, the quantity not to exceed 0.15% by volume in compliance 
with MIL-I-27686D or E. 
 
NOTE 9. 620B-TG:  A Fuel Pressure \ Flow Instrument (Electronic International Model FP-5) and 
a Flow Transducer (EG&G Model FT-8AEXSBLEA-2) may be used as an option to the 
standard Fuel Pressure Gage with the following placard installed: 
 
 “Do not rely on the electronic fuel  flow instrument to determine fuel quantity level in 
tanks.” 
 
NOTE 10. Noise Certification:   This airplane has not been shown to comply with the noise limits in 
FAR Part 36 and must be operated in accordance with the noise operation limitation 
required by FAR 91.815. 
 
NOTE 11. The 620B-TG  model aircraft has been certificated up to a Maximum Gross Weight of 
4300 lbs.  Any increase in Gross Weight will require FAA evaluation and approval. 
 
--- END ---
```

## ADs (3, in force first)

- [AD 2020-10-03](https://openairdocs.org/ad/2020-10-03): Wing Attach Hinge Fitting · Weatherly 201, 201A, 201B and 6 more. Effective Jun 15, 2020
- [AD 2016-07-11](https://openairdocs.org/ad/2016-07-11): Wing Attach Fittings · Weatherly 201, 201A, 201B and 6 more. Effective Apr 15, 2016
- [AD 96-16-06](https://openairdocs.org/ad/96-16-06): Wing Hinge Pin · Weatherly 620A and 620B. Effective Oct 6, 1996

## Registered aircraft by registry model (OpenAirDocs)

- [Weatherly 620B](https://openairdocs.org/model/weatherly-620b): 23 aircraft (registry codes 9630605, 9630607)
- [Weatherly 620A](https://openairdocs.org/model/weatherly-620a): 6 aircraft (registry code 9630603)
- [Weatherly 620](https://openairdocs.org/model/weatherly-620): 2 aircraft (registry code 9630602)
- [Weatherly 620TP](https://openairdocs.org/model/weatherly-620tp): 1 aircraft (registry code 9630604)
- [Weatherly 620B TG](https://openairdocs.org/model/weatherly-620b-tg): 0 aircraft (registry code 9630606)

## STCs approved under this data sheet (38)

- [STC SA04652CH](https://openairdocs.org/stc/SA04652CH): To allow use of 100R grade aviation fuel meeting Swift Fuel, LLC specification. Swift Fuels 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 SA01967WI](https://openairdocs.org/stc/SA01967WI): Use of GAMI G100UL High Octane Unleaded Avgas. General Aviation Modifications 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 SA5190NM](https://openairdocs.org/stc/SA5190NM): Installation of Gustin Aviation chip detector light system.. A & L Aircraft Parts Inc
- [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 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 SA2586NM](https://openairdocs.org/stc/SA2586NM): Installation of J.P. Instruments temperature monitoring systems.. J P Instruments
- [STC SA02283SE PAGE 2](https://openairdocs.org/stc/SA02283SE%20PAGE%202): 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 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
- [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 SA4005NM](https://openairdocs.org/stc/SA4005NM): Precise Flight Inc. Pulselite Control System. Precise Flight Inc
- [STC SA00680SE](https://openairdocs.org/stc/SA00680SE): Installation of Electronics International model UBG-16 or UBG-16T bar graph engine analyzer.. Electronics International
- [STC SA01258SE](https://openairdocs.org/stc/SA01258SE): Installation of the Automatic Flagman Dispenser Models in accordance with Automatic Flagman Master Drawing Lists specified in attached AML, or later FAA approved revision.This STC supercedes several existing STC s as listed in the notes on the attached AML.. R-S Sales Inc.
- [STC SA02475AT](https://openairdocs.org/stc/SA02475AT): Install Sankyo (Sanden) SD505 air conditioner. Approval limited to Weatherly Model 620B serial number 1592 ONLY.. Priewe Conrad
- [STC SA00622LA](https://openairdocs.org/stc/SA00622LA): Installation of an electronic digital engine tachometer horizon model P-1000.. Horizon Instruments Inc
- [STC SA330NW](https://openairdocs.org/stc/SA330NW): Installation of automatic flagman model no 4. R-S Sales Inc.
- [STC SA02168AK](https://openairdocs.org/stc/SA02168AK): Installation of hourmeter airspeed switch. For unpressurized aircraft only. Pressurized aircraft must have pressurization system deactivated.. Avalaska Inc
- [STC SA2687NM](https://openairdocs.org/stc/SA2687NM): Installation of Truboplus/ Electronics Int'l gauges and switches.. Aero Manufacturing Inc.
- [STC SA00458SE](https://openairdocs.org/stc/SA00458SE): Fabrication and installation of vortex generators mounted on wings.. Aeronautical Testing Service Inc.
- [STC SA00444SE](https://openairdocs.org/stc/SA00444SE): Install vortex generators on wings.. Micro AeroDynamics Inc
- [STC SA00477WI](https://openairdocs.org/stc/SA00477WI): Installation of a Compro Driftfinder DFS-10 to system which injects oil into engine exhaust to produce smoke to determine wind speed and direction.. Compro Aviation Inc
- [STC ST00368WI](https://openairdocs.org/stc/ST00368WI): Installation of scavenger engine oil filter.. Weatherly Aviation Company
- [STC SA00368WI](https://openairdocs.org/stc/SA00368WI): Installation of scavanger engine oil filter. AG Flight Incorporated
- [STC SA5895NM](https://openairdocs.org/stc/SA5895NM): Installation of an air conditioner.. Weatherly Aviation Company
- [STC SA1626NM PAGE 2](https://openairdocs.org/stc/SA1626NM%20PAGE%202): Installation of Electronics Int'l Digital EGT/CHT Instruments and accessories. (201 Series). Electronics International
- [STC SA2350NM PAGE 2](https://openairdocs.org/stc/SA2350NM%20PAGE%202): Installation of Electronics International Inc digital carburetor/outside air temperature gauges. Electronics International
- [STC SA4302NM](https://openairdocs.org/stc/SA4302NM): Installation of Electronics Int'l digital automatic engine analyzer.. Electronics International
- [STC SA2423SO](https://openairdocs.org/stc/SA2423SO): Installation of Chemical Evacuation System to remove residue from the agricultural spray dispersal system.. Paul S Woods
- [STC SA3862NM PAGE 2](https://openairdocs.org/stc/SA3862NM%20PAGE%202): Installation of Electronics International Primary TIT/EGT/CHT instruments, remote switches and associated accessories.. Electronics International
- [STC SA2190NM PAGE 2](https://openairdocs.org/stc/SA2190NM%20PAGE%202): Installation of electronics International Digital Volt/Amp Gauges and Accessories.. Electronics International
- [STC SA1877CE](https://openairdocs.org/stc/SA1877CE): Operation of airplane on unleaded and leaded automotive gasoline.. Petersen Aviation Inc
- [STC SA2350NM](https://openairdocs.org/stc/SA2350NM) (historical): Installation of Electronics International Inc digital carburetor/outside air temperature gauges listed on the attached continuation sheet and the associated accessories.. Electronics International

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