# TCDS A20SO: Piper Aircraft Inc.

- Type: Type certificate data sheet
- Status: Current
- Holder: Piper Aircraft Inc.
- Revision: 13
- Revised: January 26, 2022
- Product: Aircraft, Small Airplane
- Certification basis: Part 23, Part 23, Part 23, Part 23
- Registered aircraft: 565, by the registry models matched to it (OpenAirDocs)
- Data sheet PDF: https://openairdocs.org/files/sha256/39/32/3932576808a64ce50d5ec9f1d4dac09d3e5377e0a2ce190d605a2f448c946e43
- FAA DRS: https://drs.faa.gov/browse/excelExternalWindow/C19665EBEF68D79A862587FA00708E5C.0001
- Page: https://openairdocs.org/tcds/A20SO

## Models (4)

As the data sheet lists them.

- PA-31
- PA-31-325
- PA-31-300
- PA-31-350

## What the data sheet says

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

```text
Page No. 1 2 3 4 5 6 7 8 9 10 11 12 13 14 15 
Rev. No. 12 10 7 9 7 10 7 10 10 5 9 12 13 12 12 
 
DEPARTMENT OF TRANSPORTATION 
FEDERAL AVIATION ADMINISTRATION 
A20SO 
Revision 13 
 
Piper Aircraft, Inc 
 PA-31 
 PA-31-300 
 PA-31-325 
 PA-31-350 
(See NOTE 7) 
January 26, 2022 
 
TYPE CERTIFICATE DATA SHEET NO. A20SO 
 
This data sheet, which is a part of Type Certificate A20SO, 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: Piper Aircraft, Inc. 
 2926 Piper Drive 
 Vero Beach, Florida   32960 
 
Type Certificate Holder Record The New Piper Aircraft, Inc transferred TC A20SO to Piper Aircraft, Inc on August 7, 
2006. 
 
I. - Model PA-31 (Navajo), 6 - 8 PCLM (Normal Category), Approved February 24, 1966 (Reissued July 25, 1966, See NOTE 3). 
 
Engine 2 Lycoming TIO-540-A1A, TIO-540-A1B, TIO-540-A2A, or  
 TIO-540-A2B (Applicable to S/N 31-2 through S/N 31-659 and 
 S/N 31-661 through 31-751); or 
 2 Lycoming TIO-540-A2B (Applicable to S/N 31-660 with nacelle  
 wing lockers only); or 
 2 Lycoming TIO-540-A2C (Applicable to S/N 31-712 through  
 S/N 31-751 with nacelle wing lockers only and S/N 31-752 through  
 S/N 31-8312019) 
 See NOTE 4. 
 
Fuel 100/130 minimum grade aviation gasoline 
 
Engine Limits Applicable to S/N 31-2 through 31-751 (TIO-540-AIA, TIO-540-AIB, TIO-540-A2A, or 
 TIO-540-A2B): 
 2,575 r.p.m., 310 hp. from sea level to 15,000 ft. altitude.  Full throttle operations at all  
 altitudes.  Maximum 43 in. hg. manifold pressure cumulative total with automatic  
 density control and altitude adjustment. 
 
 Applicable to S/N 31-712 through 31-900, and 31-7300901 through 31-7912124  
 (TIO-540-A2C): 
 2,575 r.p.m., 310 hp. from sea level to 15,800 ft. altitude.  Maximum 46.0 in. hg.  
 manifold pressure cumulative total with automatic density control and altitude  
 adjustment.  Do not exceed the following manifold pressure limitations:  46.0 in.  
 hg. manifold pressure at and below 15,800 ft. altitude, 31.0 in. hg. manifold  
 pressure at 24,000 ft. altitude.  Straight line variation between points given. 
 
 Applicable to S/N 31-8012001 through 31-8312019 (TIO-540-A2C): 
 Maximum continuous power 
 2,575 r.p.m. at 310 hp. from sea level to 15,800 ft. altitude.  Maximum 46.0 in. hg.  
 manifold pressure cumulative total with automatic density control and altitude 
 adjustment.  Do not exceed the following manifold pressure limitations:  46.0 in. 
 hg. manifold pressure at and below 15,800 ft. altitude, 31.0 in. hg. manifold 
 pressure at 24,000 ft. altitude.  Straight line variation between points given.

A20SO Page 2 of 15 
 
Engine Limits Maximum normal operating power 
  (continued) Do not exceed the following r.p.m. and manifold pressures:  2,400 r.p.m.,  
 39.5 in. hg. manifold pressure at and below 19,700 ft. altitude, 2,400 r.p.m.,  
 31.0 in. hg. manifold pressure at 24,000 ft. altitude.  Straight line variation  
 between points given. 
 
Propeller and Propeller Limits Hartzell Hub and Blade Models: 
 
 Eligible on TI0-540-A1A, TI0-540-A1B engines only: 
   HC-E2YK-2B/C8475-4 (2 Bld) 
   HC-E2YK-2BT/C8475-4 (2 Bld) 
 
 Eligible on TIO-540-AIA, TIO-540-AIB, TIO-540-A2A, TI0-540-A2B engines only: 
   HC-E2YR-2B/C8475-4 (2 Bld) 
   HC-E2YR-2BT/C8475-4 (2 Bld) 
   HC-E2YR-2BTF/FC8475-4 (2Bld) 
  
 Eligible on TIO-540-A2A, TI0-540-A2B, TI0-540-A2C egines only: 
   HC-E3YR-2/C8468-6R (3 Bld) 
   HC-E3YR-2T/C8468-6R (3 Bld) 
   HC-E3YR-2A/C8468-6R (3 Bld) 
   HC-E3YR-2AT/C8468-6R (3 Bld) 
 
 Eligible on TI0-540-A2A, TI0-540-A2B, TI0-540-A2C engines only: 
   HC-E3YR/2AF/FC8468-6R (3 Bld) 
   HC-E3YR-2ATF/FC8468-6R (3 Bld) 
 
 Pitch (2 Bld): High 81° ± 1.0° (feathered), Low 14.5° ± 0.1° at 30 in. station. 
 Pitch (3 Bld): High 82° ± 1.0° (feathered), Low 13° ± 0.1° (TIO-540-A2A and 
        TIO-540-A2B engines) or Low 13.2° ± 0.1° (TIO-540-A2C  
        engines) at 30 in. station. 
 Diameter:  Not over 80 in., not under 78 in. 
   No further reduction permitted. 
 
Propeller Governor 2 Hartzell F-6-24Z Propeller Governors or 
 2 Hartzell F-6-11S or F-6-11A Propeller Governors per Piper Drawing 24622-7 
 See Notes 13 & 14 
 
Airspeed Limits (CAS) Applicable to all S/N: 
 V NE (Never Exceed) 272 mph (236 knots) 
 VNO (Max. Structural Cruise) 216 mph (188 knots) 
 VFE (Flaps Extended) 40° 150 mph (130 knots) 
 VMC (Minimum Control)   85 mph (  74 knots) 
 
 Applicable to S/N 31-2 through 31-711: 
 VA (Maneuvering) 188 mph (163 knots) 
 
 Applicable to S/N 31-712 through 31-900 and 31-7300901 through 31-8312019: 
 VA (Maneuvering) 183 mph (159 knots) 
 
 Applicable to S/N 31-2 through 31-900 and 31-7300901 through 31-7712106: 
 VFE (Flaps Extended)  15° 175 mph (152 knots) 
 VLO (Landing Gear Operating)   
  Extension and Retraction 150 mph (130 knots) 
 VLE (Landing Gear Extended) 150 mph (130 knots)

Page 3 of 15 A20SO 
 
Airspeed Limits (CAS) Applicable to S/N 31-7812001 through 31-8312019: 
 VFE (Flaps Extended)  25° 184 mph (160 knots) 
 VLO (Landing Gear Operating)   
  Extension 180 mph (156 knots) 
  Retraction 150 mph (130 knots) 
 VLE (Landing Gear Extended) 180 mph (156 knots) 
 
C.G. Range (Gear Extended)  (+134.0) to (+138.0) at 6,500 lb. 
 (+128.5) to (+138.0) at 6,000 lb. 
 (+120.0) to (+138.0) at 4,800 lb. or less. 
 Straight line variation between points given. 
 Moment due to retracting landing gear:   + 860 in.-lb. 
 
7000
6500
6000
5500
5000
4500
115 125 130 135 140120
120
128.5
134 138
Aircraft Weight
(lb.)
 
      C. G. Location 
  (Inches aft of datum) 
 
Empty Weight C.G. Range None 
 
Maximum Weight 6,500 lb. - Takeoff;   6,200 lb. - Landing (S/N 31-2 through 31-711) 
 6,500 lb. - Takeoff or Landing (S/N 31-712 through 31-900 and  
       31-7300901 through 31-8312019) 
 
No. of Seats 6 - 8 seats (2 at +119.0, 2 at +166.0, 2 at +198.0)  
  (2 optional, 1 at +229.0, 1 at +234.0) 
 
Maximum Baggage Without Nacelle Lockers: 
 Total:   350 lb. 
 Fuselage:   150 lb. at +43;  200 lb. at +255 
 
 With Nacelle Lockers: 
 Total:   650 lb. 
 Fuselage:   150 lb. at +43;  200 lb. at +255 
 Nacelle Lockers:   150 lb. each side at +168 
 
Fuel Capacity Total - 192 gallons 
    56 gallons in each of 2 wing tanks at +126.8 
    40 gallons in each of 2 wing tanks at +148.0 
 See NOTE 1 for unusable fuel data. 
 
Oil Capacity Total - 6 gallons at (+77) 
    (3 gallons each engine - 2 ¾ qt. unusable each engine)

A20SO Page 4 of 15 
 
 
Control Surface Movements Aileron (±1.0°) Up 24° Down 14° 
 Aileron Tab (±1.0°) Up 15° Down 20° 
(All measurements taken at (Aileron neutral) 
trailing edge from neutral position) 
 Elevator (±1.0°) Up 25° Down 20° 
 Elevator Tab (±1.0°) Up 16° Down 29° 
 (Elevator neutral) 
 Rudder (±1.0°) Right 30° Left 30° 
 Rudder Tab (±1.0°) Right 18° Left 40° 
 (Rudder neutral) 
 Flaps (±1.0°)   Down 40° 
 
Maximum Operating Altitude 24,000 ft. pressure altitude 
 
Serial Numbers Eligible 31-2 through 31-900 and 31-7300901 through 31-8312019 (See NOTES 5 and 6 for  
 airworthiness certification eligibility in the United States). 
 
II. - Model PA-31-300 (Navajo), 6 - 8 PCLM (Normal Category), Approved June 12, 1967. 
 
Engine 2 Lycoming IO-540-M1A5 
 
Fuel 100/130 minimum grade aviation gasoline 
 
Engine Limits For all operations, 2700 r.p.m. (300 hp) 
 "Do not exceed 23 in. manifold pressure below 2,250 r.p.m." 
 
Propeller and Propeller Limits Hartzell Hub and Blade Models: 
 HC-E2YR-2B/C8475A-4 
 HC-E2YR-2BT/C8475A-4 
 HC-E2YR-2BTF/FC8475A-4 
 
 Pitch: High 81° ± 1.0° (feathered), Low 12.5° ± 0.1° at 30 in. station. 
 Diameter: Not over 80 in., not under 78 in. 
  No further reduction permitted. 
 
Propeller Governor 2 Hartzell F-6-15A Propeller Governors 
 
Airspeed Limits (CAS) V NE (Never Exceed) 272 mph (236 knots) 
 VNO (Max. Structural Cruise) 216 mph (188 knots) 
 VA (Maneuvering) 188 mph (163 knots) 
 VFE (Flaps Extended)  40° 150 mph (130 knots) 
 VLO (Landing Gear Operating) 150 mph (130 knots) 
 VLE (Landing Gear Extended) 150 mph (130 knots) 
 VMC (Minimum Control)   85 mph (  74 knots)

Page 5 of 15 A20SO 
 
 
C.G. Range (Gear Extended) (+132.0) to (+138.0) at 6,000 lb. 
 (+120.0) to (+138.0) at 4,800 lb. or less. 
 Straight line variation between points given. 
 Moment due to retracting landing gear:  + 860 in.-lb. 
6500
6000
5500
5000
4500
115 125 130 135 140120
132 138
Aircraft Weight
(lb.)
  
          C. G. Location 
  (Inches aft of datum) 
 
Empty Weight C.G. Range None 
 
Maximum Weight 6,000 lb. 
 
No. of Seats 6 - 8 seats (2 at +119.0, 2 at +166.0, 2 at +198.0)  
  (2 optional, 1 at +229.0, 1 at +234.0)  
 
Maximum Baggage Total:   400 lb.     (200 lb. at +43, 200 lb. at +255)  
 
Fuel Capacity Total:   192 gallons 
    56 gallons in each of 2 wing tanks at +126.8 
    40 gallons in each of 2 wing tanks at +148.0 
 See NOTE 1 for unusable fuel data. 
 
Oil Capacity Total - 6 gallons at (+77) 
    (3 gallons each engine - 2 ¾ qt. unusable each engine) 
 
Control Surface Movements Aileron (±1.0°) Up 24° Down 14° 
 Aileron Tab (±1.0°) Up 15° Down 20° 
(All measurements taken at (Aileron neutral) 
trailing edge from neutral position) 
 Elevator (±1.0°) Up 25° Down 20° 
 Elevator Tab (±1.0°) Up 16° Down 29° 
 (Elevator neutral) 
 Rudder (±1.0°) Right 30° Left 30° 
 Rudder Tab (±1.0°) Right 18° Left 40° 
 (Rudder neutral) 
 Flaps (±1.0°)   Down 40° 
 
Maximum Operating Altitude 24,000 ft. pressure altitude 
 
Serial Numbers Eligible 31-2 through 31-900 and 31-7300901 through 31-8312019  (See NOTES 5 and 6 for  
 airworthiness certification eligibility in the United States).

A20SO Page 6 of 15 
 
III. - Model PA-31-350 (Chieftain), and (T-1020), 6 - 11 PCLM (Normal Category), Approved May 3, 1972. 
 
Engine 1 Lycoming TIO-540-J2BD (Chieftain, S/N 31-5001 through 31-5004 and  
  31-7305005 through 31-8452024) 
 1 Lycoming LTIO-540-J2BD (Chieftain, S/N 31-5001 through 31-5004 and  
  31-7305005 through 31-8452024) 
 1 Lycoming TIO 540-J2B (T1020, S/N 31-8253001 through 31-8553002) 
 1 Lycoming LTIO-540-J2B (T1020, S/N 31-8253001 through 31-8553002) 
 
Fuel 100/130 minimum grade aviation gasoline 
 
Engine Limits Applicable to S/N 31-5001 through 31-5004 and 31-7305005 through 31-7952250: 
 2,575 r.p.m., 350 hp. from sea level to 15,000 ft. altitude.  Full throttle operations at all  
 altitudes.  Maximum 49 inches hg. manifold pressure cumulative total with automatic  
 density control and altitude adjustment.  Do not exceed the following manifold pressure  
  limitations:  49.0 inches hg. manifold pressure at and below 15,000 ft. altitude, 44.3  
 inches hg. manifold pressure at 22,300 ft., 40.5 inches hg. manifold pressure at 24,000  
 ft. altitude.  Straight line variation between points given. 
 
 Applicable to S/N 31-8052001 through 31-8553002: 
 Maximum continuous power 
 2,575 r.p.m., 350 hp. from sea level to 15,000 ft. altitude.  Full throttle operations at all  
 altitudes.  Maximum 49 inches hg. manifold pressure cumulative total with automatic  
 density control and altitude adjustment.  Do not exceed the following manifold pressure  
 limitations:  49.0 inches hg. manifold pressure at and  below 15,000 ft. altitude, 44.3  
 inches hg. manifold pressure at 22,300 ft., 40.5 inches hg. manifold pressure at 24,000  
 ft. altitude.  Straight line variation between points given. 
 
 Maximum normal operating power 
 Do not exceed the following r.p.m. and manifold pressures:  2,400 r.p.m., 40.0 inches hg.  
 manifold pressure at and below 18,700 ft. altitude, 2,400 r.p.m., 31.0 inches hg.  
 manifold pressure at 24,000 ft. altitude.  Straight line variation between points given. 
 
Propeller and Propeller Limits Hartzell Hub and Blade Models: 
 
 Eligible on TIO-540-J2BD engine: 
    HC-E3YR-2A/C8468-6R 
    HC-E3YR-2AT/C8468-6R 
    HC-E3YR-2AF/FC8468-6R 
    HC-E3YR-2ATF/FC8468-6R 
 
 Eligible on LTIO-540-J2BD engine: 
    HC-E3YR-2ALT/JC8468-6R 
    HC-E3YR-2AL/JC8468-6R 
    HC-E3YR-2ALF/FJC8468-6R 
    HC-E3YR-2ALTF/FJC8468-6R 
 
 Eligible on TIO-540-J2B engine: 
    HC-E3YR-2ATF/FC8468-6R 
 
 Eligible on LTIO-540-J2B engine: 
    HC-E3YR-2ALTF/FJC8468-6R 
 
 Pitch: High 82° ± 1.0° (feathered), Low 13.4° ± 0.1° at 30 in station. 
 Diameter: Not over 80 in., not under 78 in. 
  No further reduction permitted. 
 
Propeller Governor 1 Hartzell F-6-24LZ and 1 Hartzell F-6-24Z Propeller Governors 
 See Notes 8, 9 & 10

Page 7 of 15 A20SO 
 
Airspeed Limits (CAS) Applicable to all S/N: 
 V NE (Never Exceed) 272 mph (236 knots) 
 VNO (Max. Structural Cruise) 216 mph (187 knots) 
 VA (Maneuvering) 186 mph (162 knots) 
 VFE (Flaps Extended)  40° 150 mph (130 knots) 
 VMC (Minimum Control)   90 mph (  78 knots) 
 
 Applicable to S/N 31-5001 through 31-5004 and 31-7305005 through 31-7752201: 
 VFE (Flaps Extended)  15° 175 mph (152 knots) 
 VLO (Landing Gear Operating)   
  Extension and Retraction 150 mph (130 knots) 
 VLE (Landing Gear Extended) 150 mph (130 knots) 
 
 Applicable to S/N 31-7852001 through 31-8553002: 
 VFE (Flaps Extended)  25° 184 mph (160 knots) 
 VLO (Landing Gear Operating)   
  Extension  180 mph (156 knots) 
  Retraction 150 mph (130 knots) 
 VLE (Landing Gear Extended) 180 mph (156 knots) 
 
C.G. Range (Gear Extended) (+126.0) to (+135.0) at 7,000 lb. 
 (+122.0) to (+135.0) at 6,200 lb. 
 (+120.0) to (+135.0) at 5,200 lb. or less 
 Straight line variation between points given. 
 Moment due to retracting landing gear:   + 860 in.-lb. 
 
115 125 130 135 140120
6500
6000
5500
5000
4500
7000
120
122
126 135
Aircraft Weight
(lb.)
 
  
      C. G. Location 
   (Inches aft of datum) 
 
Empty Weight C.G. Range None 
 
Maximum Weight 7,000 lb. - Takeoff;   7,000 lb. - Landing 
 
No. of Seats 2 seats at +95.0 
 6 optional   (2 at +132/137 (reversed), 2 at +195.0, 1 at +229.0, 1 at +242.0)  
 8 optional   (2 at +132.0, 2 at +163.5, 2 at +195.0, 1 at +229.0, 1 at +242.0)  
 9 optional   (T1020, S/N 31-8253001 through 31-8553002:  2 at +130.9, 2 at +164.6,  
   2 at +193.6, 1 at +222.6, 2 at +253.5)

A20SO Page 8 of 15 
 
Maximum Baggage Total:   700 lb. 
 Fuselage:   200 lb. at +19.0 
                   200 lb. at +255 
 Nacelle Lockers:   150 lb. each side at +168.0 
  
 Chieftain, S/N 31-5001 through 31-5004 and 31-7305005 through 31-8452024: 
 With optional nacelle fuel tanks  
 Total:   500 lb. 
 Fuselage:   200 lb. at +19.0 
                   200 lb. at +255 
 Nacelle Lockers:   50 lb. each side at +192.0 
 
 T1020, S/N 31-8253001 through 31-8553002: 
 Total:   600 lb.   
 Fuselage:   200 lb. at +23.0 
                   100 lb. at +268 
 Nacelle Lockers: 150 lb. each side at +168.0 
 
Fuel Capacity T1020, S/N 31-8253001 through 31-8553002: 
 Total - 112 gallons   
    56 gallons in each of 2 wing tanks at +126.8   
 
 Chieftain, S/N 31-5001 through 31-5004 and 31-7305005 through 31-8452024: 
 Total - 192 gallons  
    56 gallons in each of 2 wing tanks at +126.8 
    40 gallons in each of 2 wing tanks at +148.0 
  
 
 Chieftain, S/N 31-5001 through 31-5004 and 31-7305005 through 31-8452024: 
 With optional nacelle fuel tanks 
 Total - 246 gallons  
    56 gallons in each of 2 wing tanks at +126.8 
    27 gallons in each of 2 nacelle tanks at +142.8 
    40 gallons in each of 2 wing tanks at +148.0 
 
 See NOTE 1 for unusable fuel data. 
 
Oil Capacity Total - 6 gallons at (+77) 
    (3 gallons each engine - 2 ¾ qt. unusable each engine) 
 
Control Surface Movements Aileron (±1.0°) Up 24° Down 14° 
 Aileron Tab (±1.0°) Up 15° Down 20° 
(All measurements taken at (Aileron neutral) 
trailing edge from neutral position) 
 Elevator (±1.0°) Up 16° Down 20° 
 Elevator Tab (±1.0°) Up  9° Down 36° 
 (Elevator neutral) 
 Rudder (±1.0°) Right 30° Left 30° 
 Rudder Tab (±1.0°) Right 18° Left 40° 
 (Rudder neutral) 
 Flaps (±1.0°)   Down 40° 
 
Maximum Operating Altitude 24,000 ft. pressure altitude 
 
Serial Numbers Eligible 31-5001 through 31-5004 and 31-7305005 through 31-8553002 (See NOTES 5 and  
 6 for airworthiness certification eligibility in the United States).

Page 9 of 15 A20SO 
 
IV. - Model PA-31-325 (Navajo C/R), 6 - 8 PCLM (Normal Category), Approved May 31, 1974. 
 
Engine 1 Lycoming TIO-540-F2BD 
 1 Lycoming LTIO-540 F2BD 
 
Fuel 100/130 minimum grade aviation gasoline 
 
Engine Limits Applicable to S/N 31-7400990, 31-7512001 through 31-7912124: 
 Maximum continuous power 
 2,575 r.p.m., 325 hp. from sea level to 14,000 ft. altitude, maximum 49.0 in. hg.  
 manifold pressure cumulative total with automatic density control and altitude  
 adjustment.  Do not exceed the following manifold pressure limitations:  49.0 in. hg  
 manifold pressure at and below 14,000 ft. altitude, 31.0 in. hg manifold pressure at  
 25,000 ft altitude.  Straight line variation between points given. 
 
 Applicable to S/N 31-8012001 through 31-8312019: 
 Maximum continuous power 
 2,575 r.p.m., 325 hp. from sea level to 14,000 ft. altitude, maximum 49.0 in. hg. 
 manifold pressure cumulative total with automatic density control and altitude  
 adjustment.  Do not exceed the following manifold pressure limitations:  49.0 in. hg  
 manifold pressure at and below 14,000 ft. altitude, 31.0 in. hg manifold pressure at  
 24,000 ft. altitude.  Straight line variation between points given. 
 
 Maximum normal operating power 
 Do not exceed the following r.p.m. and manifold pressures:  2,400 r.p.m., 39.5 in. hg  
 manifold pressure at and below 19,700 ft.. altitude, 2,400 r.p.m.,  
 31.0 in. hg manifold pressure at 24,000 ft. altitude.  
 Straight line variation between points given. 
 
Propeller and Propeller Limits Hartzell Hub and Blade Models: 
 
 HC-E3YR-2AF/FC8468-6R  (Eligible on TIO-540-F2BD engines) 
 HC-E3YR-2ATF/FC8468-6R 
 HC-E3YR-2ATF/FC8468-7R 
 
 HC-E3YR-2ALTF/FJC8468-6R   (Eligible on LTIO-540-F2BD engines) 
 HC-E3YR-2ALF/FJC8468-6R 
 HC-E3YR-2ALTF/FJC8468-7R 
 
 Pitch: High 82° ± 1.0°  (feathered), Low 13.2° ± 0.1° at 30 in station. 
 Diameter: Not over 80 in., not under 78 in. 
  No further reduction permitted. 
 
Propeller Governor 2 Hartzell F-6-24Z Propeller Governors 
 See Notes 11 & 12 
 
Airspeed Limits (CAS) Applicable to all S/N: 
 V NE (Never Exceed) 272 mph (236 knots) 
 VNO (Max. Structural Cruise) 216 mph (188 knots) 
  Above 21,000 ft. reduce VNO speed 3 mph per 1,000 ft. 
 
 VA (Maneuvering) 183 mph (159 knots) 
 VFE (Flaps Extended)  40° 150 mph (130 knots) 
 VMC (Minimum Control)   85 mph (  74 knots) 
 
 Applicable to S/N 31-7400990, 31-7512001 through 31-7712106: 
 VFE (Flaps Extended)  15° 175 mph (152 knots) 
 VLO (Landing Gear Operating)   
  Extension and Retraction 150 mph (130 knots) 
 VLE (Landing Gear Extended) 150 mph (130 knots)

A20SO Page 10 of 15 
 
Airspeed Limits (CAS) Applicable to S/N 31-7812001 through 31-8312019: 
 VFE (Flaps Extended)  25° 184 mph (160 knots) 
 VLO (Landing Gear Operating)   
  Extension 180 mph (156 knots) 
  Retraction 150 mph (130 knots) 
 VLE (Landing Gear Extended) 180 mph (156 knots) 
 
C.G. Range (Gear Extended) (+134.0) to (+138.0) at 6,500 lb. 
 (+128.5) to (+138.0) at 6,000 lb. 
 (+121.4) to (+138.0) at 5,000 lb. or less 
 Straight line variation between points given. 
 Moment due to retracting landing gear:   + 860 in.-lb. 
115 125 130 135 140120
6500
6000
5500
5000
4500
Aircraft Weight
(lb.)
121.4
128.5
134 138
 
      C. G. Location 
  (Inches aft of datum) 
 
Empty Weight C.G. Range None 
 
Maximum Weight 6,500 lb. - Takeoff or Landing 
 
No. of Seats 6 - 8 seats  (2 at +119.0, 2 at +166.0, 2 at +198.0)  
 (2 optional, 1 at +229.0, 1 at +234.0)  
 
Maximum Baggage Total:   650 lb. 
 Fuselage:   150 lb. at +43.0 
                   200 lb. at +255 
 Nacelle Lockers:   150 lb. each side at +168.0 
 With optional nacelle fuel tanks. 
 
 Total:   450 lb. 
 Fuselage:   150 lb. at +43.0 
                   200 lb. at +255.0 
 Nacelle Lockers:   50 lb. each side at +192.0 
 
Fuel Capacity Total - 192 gallons 
    56 gallons in each of 2 wing tanks at +126.8 
    40 gallons in each of 2 wing tanks at +148.0 
 With optional nacelle fuel tanks. 
 
 Total - 246 gallons 
    56 gallons in each of 2 wing tanks at +126.8 
    27 gallons in each of 2 nacelle tanks at +142.8 
    40 gallons in each of 2 wing tanks at +148.0 
 
 See NOTE 1 for unusable fuel data. 
 
Oil Capacity Total - 6 gallons at (+77) 
    (3 gallons each engine - 2 3/4 qt. unusable each engine)

Page 11 of 15 A20SO 
 
 
Control Surface Movements Aileron (±1.0°) Up 24° Down 14° 
 Aileron Tab (±1.0°) Up 15° Down 20° 
(All measurements taken at (Aileron neutral) 
trailing edge from neutral position) 
 Applicable to S/N 31-7400990, 31-7512001 through 31-7912124: 
 Elevator (±1.0°) Up 20° Down 20° 
 Elevator Tab (±1.0°) Up   1° Down 40° 
 (Elevator neutral) 
 
 Applicable to S/N 31-8012001 through 31-8312019: 
 Elevator (±1.0°) Up 20° Down 20° 
 Elevator Tab (±1.0°) Up   5° Down 40° 
 (Elevator neutral) 
 Rudder (±1.0°) Right 30° Left 30° 
 Rudder Tab (±1.0°) Right 18° Left 40° 
 (Rudder neutral) 
 Flaps (±1.0°)   Down 40° 
 
Maximum Operating Altitude 24,000 ft. pressure altitude. 
 
Serial Numbers Eligible 31-7400990, and 31-7512001 through 31-8312019 (See NOTES 5 and 6 for  
 airworthiness certification eligibility in the United States). 
 
DATA PERTINENT TO ALL MODELS 
 
Datum 137 inches forward of the main spar centerline. 
 
Leveling Means Top of two rivnuts on right side of nose, near access door. 
 
Certification Basis Type Certificate No. A20SO issued March 6, 1978, (originally issued February 24,  
 1966, under Type Certificate A8EA) obtained by the manufacturer under the delegation  
 option authorization. 
 Date of Type Certificate application March 15, 1962. 
 
 CAR 3 effective May 15, 1956, through Amendment 3-8, effective December 18, 1962;   
 and FAR 23.205, 23.1545, 23.1563 and 23.1585 as amended by Amendment 23-3,  
 effective November 11, 1965;  and FAR 23.1557(c)as amended by Amendment 23-7, 
 effective September 14, 1969. 
Eastern Region Engineering and Manufacturing Branch letter of December 6, 1965,  
 addresses the showing of equivalent safety with regard to CAR 3.682, 3.771, and 3.772. 
 
 In addition: 
 Model PA-31-350:  FAR 23.75(a), 23.77, 23.145, 23.161, 23.175(d), and 23.1527 as  
 amended by Amendment 23-7, effective September 14, 1969. 
  
 Model PA-31-325: FAR 23.75(a), 23.77(a), 23.145, 23.161, 23.175(a), 
 23.175(b), 23.175(c), 23.175(d), and 23.1527 as amended by Amendment 23 -7,  
 effective September 14, 1969. 
 
 Model PA-31 and PA-31-325 (S/N 31-8012001 through 31-8312019), and  
 Model PA-31-350 (S/N 31-8052001 through 31-8553002): FAR 36 as amended by 
 Amendments 1 through 6, effective January 24, 1977.  Compliance with ice  
 protection requirements have been demonstrated in accordance with FAR 23.1419 as  
 amended by Amendment 23-14, effective December 20, 1973, when ice protection  
 equipment is installed in accordance with the airplane equipment list.

A20SO Page 12 of 15 
 
Certification Basis Model PA-31-350 (S/N 31-7652124 through 31-7952250): 
  (continued) Compliance with ice protection requirements have been demonstrated in accordance  
 with FAR 23.1419 as amended by Amendment 23-14, effective December 20, 1973, 
 when ice protection equipment is installed in accordance with Piper Drawing 71983. 
 
Production Basis Approved for manufacture of spare parts only under Production Certificate Number 206. 
 
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: 
 
 1. D.O.A. No. EA-1 Approved Airplane Flight Manual per PAC Report No. 1362 for  
  Model PA-31, S/N 31-2 through 31-659, 31-661 through 31-711. 
 2. D.O.A. No. EA-1 Approved Airplane Flight Manual per PAC Report No. 1470 for  
  Model PA-31-300, S/N 31-2 through 31-511. 
 3. D.O.A. No. EA-1 Approved Airplane Flight Manual per PAC Report No. 1655 for  
  Model PA-31, S/N 31-712 through 31-751. 
 4. D.O.A. No. EA-1 Approved Airplane Flight Manual per PAC Report No. 1653 for  
  Model PA-31 with nacelle wing lockers and TIO-540-A2B engines, Serial  
  Number 31-660. 
 5. D.O.A. No. EA-1 Approved Airplane Flight Manual per PAC Report No. 1686 for  
  Model PA-31 with nacelle wing lockers and TIO-540-A2C engines, Serial  
  Number 31-712 through 31-751. 
 6. D.O.A. No. EA-1 Approved Airplane Flight Manual per PAC Report No. 1702 for  
  Model PA-31, S/N 31-752 through 31-900 and 31-7300901 through 31-7612110. 
 7. D.O.A. No. EA-1 Approved Airplane Flight Manual per PAC Report No. 1750 for  
  Model PA-31-350, S/N 31-5001 through 31-5004 and 31-7305005 through 31-7652176. 
 8. D.O.A. No. EA-1 Approved Airplane Flight Manual per PAC Report No. 1860 for  
  Model PA-31-325, S/N 31-7300932 through 31-7612110. 
 9. D.O.A. No. EA-1 Approved Pilot's Operating Handbook per PAC Report  
  No. 2045 for Model PA-31, S/N 31-7712001 through 31-7812073. 
 10. D.O.A. No. EA-1 Approved Pilot's Operating Handbook per PAC Report  
  No. 1964 for Model PA-31-325, S/N 31-7712001 through 31-7812072. 
 11. D.O.A. No. EA-1 Approved Pilot's Operating Handbook per PAC Report  
  No. 2046 for Model PA-31-350, S/N 31-7752001 through 31-7852079. 
 12. D.O.A. No. SO-2 Approved Pilot's Operating Handbook per PAC Report  
  No. 2045 for Model PA-31, S/N 31-7812074 through 31-7912124. 
 13. D.O.A. No. SO-2 Approved Pilot's Operating Handbook per PAC Report  
  No. 1964 for Model PA-31-325, S/N 31-7812073 through 31-7912124. 
 14. D.O.A. No. SO-2 Approved Pilot's Operating Handbook per PAC Report  
  No. 2046 for Model PA-31-350, S/N 31-7852080 through 31-7952250. 
 15. D.O.A. No. SO-2 Approved Pilot's Operating Handbook and FAA Approved  
  Airplane Flight Manual Report No. LK-1206 for Model PA-31, S/N  
  31-8012001 through 31-8312019. 
 16. D.O.A. No. SO-2 Approved Pilot's Operating Handbook and FAA Approved  
  Airplane Flight Manual Report No. LK-1207 for Model PA-31-325, Serial  
  Number 31-8012001 through 31-8312019. 
17. D.O.A. No. SO-2 Approved Pilot's Operating Handbook and FAA Approved  
  Airplane Flight Manual Report No. LK-1208 for Model PA-31-350, Serial  
  Number 31-8052001 through 31-8553002. 
 18. D.O.A. No. SO-2 Approved Pilot's Operating Handbook and FAA Approved  
  Airplane Flight Manual Report No. LK-1345 for PA-31-350, Serial  
  Number 31-8253001 through 31-8553002.

Page 13 of 15 A20SO 
 
NOTE 1. Current weight and balance report including list of equipment included in certified empty  
 weight and loading instructions when necessary, must be provided for each aircraft at the  
 time of original certification.  All the fuel and oil can be drained.  However, the certified  
 empty weight and corresponding center of gravity location must include unusable fuel as  
 follows: 
 
                For PA-31 S/N  31-3 thru 31-659,  31-661 thru 31-711 16 lb. at (+129) 
 
              For PA-31 S/N  31-660, 31-712 thru 31-751 16 lb. at (+129) 
  (with wing lockers) 
 
                  For PA-31 S/N  31-712 thru 31-751 16 lb. at (+129) 
  (without wing lockers) 
 
 
                 For PA-31 S/N  31-752 thru 31-7612110 16 lb. at (+129) 
    or 
   28.2 lb. at (+137)  
 
                  For PA-31 S/N  31-7712001 thru 31-7912124 28.2 lb. at (+137) 
 
                  For PA-31 S/N  31-8012001 and UP 28.2 lb. at (+137) 
 
 
        For PA-31-300 S/N  31-228, 31-230, 31-231, 31-270, 31-279, 16 lb. at (+129) 
  31-316, 31-339, 31-375, 31-415, 31-426, 
  31-451, 31-455, 31-483 & 31-511 
 
                  For PA-31-325 S/N  31-7512006 thru 31-7612110 51.6 lb. at ( +136.6) 
 
 
                  For PA-31-325 S/N  31-7712001 thru 31-7912124 51.6 lb. at (+136.6) 
 
 
                  For PA-31-325 S/N  31-8012001 and UP 51.6 lb. at (+136.6) 
 
 
                  For PA-31-325 S/N 31-8112001 51.6 lb. at (+136.6) 
  (with Optional Nayak Nacelle Fuel System) 
            
 
                  For PA-31-350 S/N  31-5000 thru 31-7652177 36 lb. at (+126.8) 
   24 lb. at (+148) 
 
                   For PA-31-350 S/N  31-7752001 thru 31-7952250 36 lb. at (+126.8) 
   24 lb. at (+148) 
 
                   For PA-31-350 S/N  31-8052001 and UP 36 lb. at (+126.8) 
   24 lb. at (+148) 
 
                   For PA-31-350 S/N 31-8152001 and UP 36 lb. at (+126.8) 
  (with Optional Nayak Nacelle Fuel System) 24 lb. at (+148) 
 
NOTE 2 All placards required in the approved Airplane Flight Manual must be installed in the appropriate locations.  
 
 In addition, the following placard must be displayed on the instrument panel in full view of the pilot: 
 "THIS AIRCRAFT MUST BE OPERATED AS A NORMAL CATEGORY AIRPLANE IN 
COMPLIANCE WITH THE OPERATING LIMITATIONS STATED IN THE FORM OF 
PLACARDS, MARKINGS, AND MANUALS.  NO ACROBATIC MANEUVERS (INCLUDING 
SPINS) APPROVED."

A20SO Page 14 of 15 
 
NOTE 3 Model PA-31 Type Certificate A20SO approved February 24, 1966, for a maximum gross weight of  
 6,200 lb. takeoff or landing.  For Model PA-31 aircraft, S/Ns 31-2 through 31-900 and 31-7300901 through 
31-8312019, Type Certificate A20SO reissued July 25, 1966, for maximum gross weight of 6,500 lb. takeoff 
and 6,200 lb. landing. 
 
NOTE 4 Model PA-31 with nacelle wing lockers is only approved with TIO-540-A2B or TIO-540-A2C engines and 
with three-blade propellers listed under Propeller and Propeller Limits section. 
 
NOTE 5 Any aircraft with a letter prefix on the serial number is not eligible for airworthiness certification in the 
United States.   Example:   AR31-XXXXXXXX. 
 
NOTE 6 The following serial numbers are not eligible for airworthiness certification in the United States: 
 
 PA-31, PA-31-300, and PA-31-325: 
  31-856, 31-7400991, 31-7512002, 31-7512026, 31-7612113, 31-7812011, 31-7812053, 31-7812070, 
 31-7812080, 31-7812101, 31-7812116, 31-7812122, 31-8012045, 31-8012056, 31-8012067, 31-8012071, 
31-8012083, 31-8012089, 31-8012101, 31-8012102, 31-8112037, 31-8112044, 31-8112052, 31-8112061, 
31-8112072, 31-8112073, 31-8112077, 31-8212023, 31-8212024, 31-8212028, 31-8212029, 31-8212034, 
31-8212036, 31-8312002, and 31-8312007. 
 
 PA-31-350: 
  31-7405218, 31-7405238, 31-7405485, 31-7405490, 31-7552043, 31-7552073, 31-7552076, 31-
7552080, 31-7552086, 31-7552090, 31-7552093, 31-7552100, 31-7552104, 31-7552112, 31-7552117, 31-
7552120, 31-7552122, 31-7552125, 31-7552127, 31-7552129, 31-7652005, 31-7652008, 31-7652011, 31-
7652013, 31-7652015, 31-7652018, 31-7652021, 31-7652024, 31-7652025, 31-7652026, 31-7652027, 31-
7652029, 31-7652031, 31-7652034, 31-7652036, 31-7652038, 31-7652040, 31-7652042, 31-7652045, 31-
7652047, 31-7652050, 31-7652052, 31-7652054, 31-7652060, 31-7652063, 31-7652066, 31-7652069, 31-
7652085, 31-7652089, 31-7652092, 31-7652096, 31-7652099, 31-7652103, 31-7652106, 31-7652108, 31-
7652111, 31-7652113, 31-7652116, 31-7652118, 31-7652121, 31-7652123, 31-7652126, 31-7652128, 31-
7652131, 31-7652136, 31-7652138, 31-7652140, 31-7652143, 31-7652144, 31-7652146, 31-7652149, 31-
7652152, 31-7652155, 31-7652158, 31-7652160, 31-7652161, 31-7652177, 31-7752003, 31-7752007, 31-
7752010, 31-7752014, 31-7752017, 31-7752018, 31-7752019, 31-7752020, 31-7752021, 31-7752022, 31-
7752023, 31-7752024, 31-7752025, 31-7752026, 31-7752037, 31-7752039, 31-7752041, 31-7752043, 31-
7752051, 31-7752053, 31-7752055, 31-7752057, 31-7752067, 31-7752069, 31-7752071, 31-7752073, 31-
7752082, 31-7752084, 31-7752086, 31-7752088, 31-7752098, 31-7752100, 31-7752102, 31-7752104, 31-
7752115, 31-7752116, 31-7752132, 31-7752133, 31-7752155, 31-7752156, 31-7752157, 31-7752158, 31-
7752177, 31-7752178, 31-7752179, 31-7752191, 31-7752192, 31-7852014, 31-7852042, 31-7852081, 31-
7852110, 31-7852123, 31-7852133, 31-7852169, 31-7952067, 31-7952093, 31-7952116, 31-7952130, 31-
7952140, 31-7952144, 31-7952163, 31-7952164, 31-7952176, 31-7952177, 31-7952178, 31-7952184, 31-
7952211, 31-7952212, 31-7952231, 31-7952236, 31-7952237, 31-7952238, 31-8052009, 31-8052015, 31-
8052016, 31-8052041, 31-8052042, 31-8052043, 31-8052080, 31-8052081, 31-8052082, 31-8052083, 31-
8052099, 31-8052100, 31-8052101, 31-8052132, 31-8052133, 31-8052145, 31-8052150, 31-8052151, 31-
8052156, 31-8052157, 31-8052158, 31-8052187, 31-8052188, 31-8052190, 31-8052191, 31-8052192, 31-
8052201, 31-8052209, 31-8052210, 31-8052211, 31-8052213, 31-8052214, 31-8052215, 31-8052216, 31-
8052217, 31-8052218, 31-8052219, 31-8052220, 31-8052221, 31-8152021, 31-8152022, 31-8152023, 31-
8152052, 31-8152064, 31-8152067, 31-8152068, 31-8152122, 31-8152123, 31-8152144, 31-8152145, 31- 
 8152201, 31-8152202, 31-8152203, 31-8252024, 31-8252037, 31-8252046, 31-8252058, 31-8252070, 31-
8252071, 31-8252084, 31-8252085, 31-8352002, 31-8352003, and 31-8352036. 
 
NOTE 7 This Type Certificate Data Sheet reflects the certification basis and approval for all PA-31,  
 PA-31-300, PA-31-325, and PA-31-350 aircraft.  The following aircraft were produced under Type 
Certificate A8EA: 
 
  PA-31  S/N 31-2 through 31-900 and 31-7300901 through 31-7812073 
  PA-31-300 S/N 31-2 through 31-511 
  PA-31-325 S/N 31-7300932 through 31-7812072 
  PA-31-350 S/N 31-5001 through 31-5004 and 31-7305005 through 31-7852079

Page 15 of 15 A20SO 
 
 This note reflects a split in the original Type Certificate for administrative purposes.  The information on this 
Type Certificate Data Sheet applies to all Piper Models PA-31, PA-31-300, PA-31-325, and PA-31-350, 
including: 
 (a) Those serial numbered aircraft listed above, manufactured under FAA Type Certificate A8EA, at 
Lock Haven, Pennsylvania, and  
(b) Those aircraft subsequent to the above serial numbers, manufactured under this Type Certificate at 
Lakeland, Florida. 
 
NOTE 8 For aircraft that received the optional 52947-2 Propeller Synchrophaser 
Installation the F-6-24 LH Side (Piper P/N 24622-18) and F-8-24L 
RH Side (Piper P/N 24622-14) governors are approved. 
       
NOTE 9  For aircraft that received the optional 49694-4 (Rev. D and higher) Propeller  
Synchrophaser Installation the F-6-24Z LH Side (Piper P/N 24622-24) and 
F-8-48LZ RH Side (Piper P/N 24622-26) governors are approved. 
 
NOTE 10  For aircraft that received the optional 49694-4 (pre Rev. D) Propeller  
Synchrophaser Installation the F-6-24 LH Side (Piper P/N 24622-18) and 
F-8-24L RH Side (Piper P/N 24622-21) governors are approved. 
 
NOTE 11  For aircraft that received the optional 49694-3 (Rev. D and higher) Propeller  
Synchrophaser Installation the F-6-24Z LH Side (Piper P/N 24622-24) and 
F-8-48LZ RH Side (Piper P/N 24622-26) governors are approved. 
 
NOTE 12  For aircraft that received the optional 49694-3 (pre Rev. D) Propeller  
Synchrophaser Installation the F-6-24 LH Side (Piper P/N 24622-18) and 
F-8-24L RH Side (Piper P/N 24622-21) governors are approved.  
 
NOTE 13  For aircraft that received the optional 49694 -2 (Rev. D and higher) Propeller  
Synchrophaser Installation the F-6-24Z LH side (Piper P/N 24622-24), F-6-11S 
LH side or F-6-11A LH side (Piper P/N 24622-7) LH side and F-8-48Z RH Side 
(Piper P/N 24622-25) governors are approved. 
 
NOTE 14  For aircraft that received the optional 49694 -2 (pre Rev. D) Propeller  
Synchrophaser Installation the F-6-24 LH side (Piper P/N 24622-18), F-6-11S 
LH side or F-6-11A LH side (Piper P/N 24622-7) LH side and F-8-48 RH Side 
(Piper P/N 24622-20) governors are approved. 
 
...END...
```

## ADs (83, first 50, in force first)

- [AD 2023-09-09](https://openairdocs.org/ad/2023-09-09): Exhaust Turbine System (Recip) · Aerostar PA-60-600 (Aerostar 600), PA-60-601 (Aerostar 601), PA-60-601P (Aerostar 601P) and 292 more. Effective Jul 17, 2023
- [AD 2022-03-15](https://openairdocs.org/ad/2022-03-15): Fuel Quantity Indicator · Garmin G3X Touch Electronic Flight Instrument System (STC SA01899WI or SA02658SE). Effective Mar 21, 2022
- [AD 2017-10-20](https://openairdocs.org/ad/2017-10-20): Fuselage--Main Bulkhead · Piper PA-31, PA-31-300, PA-31-325 and 1 more. Effective Jun 29, 2017
- [AD 2016-08-18](https://openairdocs.org/ad/2016-08-18): Engine Fuel and Control · Piper PA-31-350. Effective Jun 6, 2016
- [AD 2016-05-01](https://openairdocs.org/ad/2016-05-01): Fuselage · Piper PA-31, PA-31-300, PA-31-325 and 1 more. Effective Apr 15, 2016
- [AD 2015-24-05](https://openairdocs.org/ad/2015-24-05): PLACARDS AND MARKINGS; Interior Placards · Piper PA-23-250, PA-24-250, PA-24-260 and 7 more. Effective Jan 12, 2016
- [AD 2013-10-04](https://openairdocs.org/ad/2013-10-04): Engine Exhaust · Piper PA-31, PA-31-325 and PA-31-350. Effective Jul 17, 2013
- [AD 2009-13-06 R1](https://openairdocs.org/ad/2009-13-06-R1): Doors · Piper PA-23, PA-23-160, PA-23-235 and 16 more. Effective Nov 3, 2011
- [AD 2006-03-08](https://openairdocs.org/ad/2006-03-08): Vacuum pumps · Aero Advantage 14-19, 14-19-2, 14-19-3 and 299 more. Effective Mar 10, 2006
- [AD 2005-25-08](https://openairdocs.org/ad/2005-25-08): Electronic Flight Information System (EFIS) · B-N Group BN-2A, 172, 180 and 22 more. Effective Jan 23, 2006
- [AD 2005-18-20](https://openairdocs.org/ad/2005-18-20): "FASTprop" propeller de-icers · Hartzell PHC-C3YF-1RF/F8468A(B,K)-8R constant speed propeller (STC SA00718LA or 17 others). Effective Oct 14, 2005
- [AD 2004-25-16 R1](https://openairdocs.org/ad/2004-25-16-R1): Fuel regulator shutoff valve · Bombardier CL-215-1A10, CL-215-6B11 (CL-215T Variant), CL-215-6B11 (CL-415 Variant) and 64 more. Effective Jun 20, 2005
- [AD 2003-24-07](https://openairdocs.org/ad/2003-24-07): Rudder torque tube · Piper PA-31, PA-31-300, PA-31-325 and 7 more. Effective Feb 9, 2004
- [AD 2001-06-01](https://openairdocs.org/ad/2001-06-01): Elevator Structure · Piper PA-31, PA-31-300, PA-31-325 and 7 more. Effective May 8, 2001
- [AD 2000-25-01](https://openairdocs.org/ad/2000-25-01): Main Landing Gear Door Hinges · Piper PA-31, PA-31-300, PA-31-325 and 7 more. Effective Jan 19, 2001
- [AD 2000-06-06](https://openairdocs.org/ad/2000-06-06): Pneumatic Deicing Boots · Piper PA-31, PA-31-300, PA-31-325 and 7 more. Effective May 5, 2000
- [AD 98-21-21 R1](https://openairdocs.org/ad/98-21-21-R1): Electric Inflatable Door Seals · Cessna 17-30, 17-30A, 17-31 and 267 more. Effective May 1, 2000
- [AD 99-14-01](https://openairdocs.org/ad/99-14-01): AFM - Limitations Section - Icing · Piper PA-23, PA-23-160, PA-23-235 and 21 more. Effective Aug 17, 1999
- [AD 99-12-05](https://openairdocs.org/ad/99-12-05): Elevator Spar Assembly · Piper PA-31, PA-31-300, PA-31-325 and 2 more. Effective Jul 23, 1999
- [AD 99-06-01](https://openairdocs.org/ad/99-06-01): Horizontal Stabilizer Rear Spar · Piper PA-31, PA-31-300, PA-31-325 and 2 more. Effective Apr 20, 1999
- [AD 98-14-03](https://openairdocs.org/ad/98-14-03): Transponders · Cessna 172, 172A, 172B and 230 more. Effective Aug 16, 1998
- [AD 98-09-25](https://openairdocs.org/ad/98-09-25): Lower Spar Splice Plate · Piper PA-31, PA-31-300, PA-31-325 and 1 more. Effective Jun 15, 1998
- [AD 98-08-18](https://openairdocs.org/ad/98-08-18): Elevator Bungee Spring · Piper PA-31, PA-31-300, PA-31-325 and 2 more. Effective May 26, 1998
- [AD 97-16-10](https://openairdocs.org/ad/97-16-10): Filters · Cessna 310R, T310R, 36 and 17 more. Effective Sep 18, 1997
- [AD 97-07-03](https://openairdocs.org/ad/97-07-03): Nose Wheel Assembly · Piper PA-31, PA-31-300, PA-31-325 and 2 more. Effective May 15, 1997
- [AD 96-24-13](https://openairdocs.org/ad/96-24-13): Landing Gear Selector Cable · Piper PA-31, PA-31-325, PA-31-350 and 2 more. Effective Jan 17, 1997
- [AD 96-21-11](https://openairdocs.org/ad/96-21-11): Main Landing Gear Actuator Reinforcement Bracket · Piper PA-31, PA-31-300, PA-31-325 and 7 more. Effective Dec 16, 1996
- [AD 96-21-03](https://openairdocs.org/ad/96-21-03): Aileron Spar Crack Inspection · Piper PA-31, PA-31-300, PA-31-325 and 11 more. Effective Dec 10, 1996
- [AD 96-21-04](https://openairdocs.org/ad/96-21-04): Hydraulic Hose Inspection · Piper PA-23, PA-23-160, PA-23-235 and 13 more. Effective Dec 10, 1996
- [AD 96-10-14](https://openairdocs.org/ad/96-10-14): Main Landing Gear Sidebraces Inspection · Piper PA-31, PA-31-300, PA-31-325 and 5 more. Effective Jun 27, 1996
- [AD 96-10-15](https://openairdocs.org/ad/96-10-15): Wing Attachments WS 147.5 Inspection · Piper PA-31, PA-31-300, PA-31-325 and 1 more. Effective Jun 27, 1996
- [AD 93-24-02 R1](https://openairdocs.org/ad/93-24-02-R1): Elevator Control Tube Assembly · Piper PA-31, PA-31-300, PA-31-325 and 7 more. Effective Feb 15, 1994
- [AD 93-23-13](https://openairdocs.org/ad/93-23-13): Engine Baffle Seals · Piper PA-31, PA-31-300, PA-31-325 and 1 more. Effective Jan 21, 1994
- [AD 92-27-05](https://openairdocs.org/ad/92-27-05): Aileron Control System · Piper PA-31, PA-31-300, PA-31-325 and 7 more. Effective Jan 29, 1993
- [AD 87-21-01](https://openairdocs.org/ad/87-21-01): Fuel Filler Openings · Aerostar PA-60-600 (Aerostar 600), PA-60-601 (Aerostar 601), PA-60-601P (Aerostar 601P) and 14 more. Effective Nov 2, 1987
- [AD 85-08-05](https://openairdocs.org/ad/85-08-05): Strut Housing Inspection · Piper PA-31, PA-31-300, PA-31-325 and 6 more. Effective May 15, 1985
- [AD 82-27-13 R2](https://openairdocs.org/ad/82-27-13-R2): Flap Extension System · Piper PA-31, PA-31-300, PA-31-325 and 4 more. Effective Aug 18, 1983
- [AD 81-15-03](https://openairdocs.org/ad/81-15-03): Engine Inlet Air Filters · Replace existing engine induction air filter (Brackett Aero Filters STC SA693CE or SA71GL). Effective Jul 20, 1981
- [AD 80-18-10](https://openairdocs.org/ad/80-18-10): Fuel Selector Valves · Piper PA-23, PA-23-160, PA-23-235 and 8 more. Effective Sep 8, 1980
- [AD 80-17-06](https://openairdocs.org/ad/80-17-06): Placards · Piper PA-31, PA-31-325 and PA-31-350. Effective Aug 13, 1980
- [AD 80-17-02](https://openairdocs.org/ad/80-17-02): Elevator Balance Weights · Piper PA-31, PA-31-325 and PA-31-350. Effective Aug 8, 1980
- [AD 80-13-06](https://openairdocs.org/ad/80-13-06): Air Door Catch Assembly Attachment · Piper PA-31-325 and PA-31-350. Effective Jun 23, 1980
- [AD 79-20-07](https://openairdocs.org/ad/79-20-07): Lighter Circuit Breaker · Piper PA-31, PA-31-325 and PA-31-350. Effective Oct 2, 1979
- [AD 79-14-02](https://openairdocs.org/ad/79-14-02): Control Wheel Shaft Stud · Piper PA-31, PA-31-300, PA-31-325 and 4 more. Effective Jul 6, 1979
- [AD 79-12-02](https://openairdocs.org/ad/79-12-02): Elevator Surface Travel · Piper PA-31, PA-31-300, PA-31-325 and 4 more. Effective Jul 2, 1979
- [AD 78-25-03](https://openairdocs.org/ad/78-25-03): Hose Assemblies · Piper PA-23-250, PA-28R-180, PA-28R-200 and 11 more. Effective Jan 15, 1979
- [AD 78-26-11](https://openairdocs.org/ad/78-26-11): Elevator Control System · Piper PA-31-350. Effective Jan 4, 1979
- [AD 78-05-06](https://openairdocs.org/ad/78-05-06): Flexible Fuel Cells · Cessna 180, 182, 185 and 98 more. Effective Jun 30, 1978
- [AD 78-08-10](https://openairdocs.org/ad/78-08-10): Fuel Selector Lever · Piper PA-31 and PA-31-325. Effective Apr 25, 1978
- [AD 77-24-01](https://openairdocs.org/ad/77-24-01): Stabilizers and Fins · Piper PA-31, PA-31-325 and PA-31-350. Effective Apr 17, 1978

All 83: https://openairdocs.org/tcds/A20SO/ads.md

## Registered aircraft by registry model (OpenAirDocs)

- [Piper PA-31-350](https://openairdocs.org/model/piper-pa-31-350): 399 aircraft (registry codes 7103110, 7103125)
- [Piper PA-31-325](https://openairdocs.org/model/piper-pa-31-325): 137 aircraft (registry code 7103105)
- [Piper PA-31](https://openairdocs.org/model/piper-pa-31): 26 aircraft (registry code 7103103)
- [Piper PA-31-300](https://openairdocs.org/model/piper-pa-31-300): 3 aircraft (registry code 7103104)

## STCs approved under this data sheet (330, first 50)

- [STC SA01800SE](https://openairdocs.org/stc/SA01800SE): Fabrication and installation of new or replacement of  existing instrument panel lights dimmer control.. TCW Technologies, LLC
- [STC SA01861SE](https://openairdocs.org/stc/SA01861SE): Fabrication and installation of Landing Light Controller. TCW Technologies, LLC
- [STC SA01844WI](https://openairdocs.org/stc/SA01844WI): Installation of Garmin GFC 600 Automatic Flight Control System. Garmin International Inc.
- [STC SA12428CH](https://openairdocs.org/stc/SA12428CH): Installation of the Lycoming Engines Electronic Ignition System (EIS). Lycoming Engines, An Operating Division of AVCO Corporation
- [STC SA02279AT](https://openairdocs.org/stc/SA02279AT): Installation of a Boom Beam bulb, starter, and ballast. Whelen Aerospace Technologies
- [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 SA02019SE-D](https://openairdocs.org/stc/SA02019SE-D): Installation of Garmin Model GTN 625/635/650; 725/750 Navigation System. Garmin International Inc.
- [STC SA01147WI](https://openairdocs.org/stc/SA01147WI): Installation of Concorde FLA or VRSLA series batteries in Piper Light Airplanes.. Concorde Battery Corporation
- [STC SA800EA](https://openairdocs.org/stc/SA800EA): Installation of Whelen Anti-Collision, Position, or Anti-Collision/Position  Light System, and applicable associated power supplies. Whelen Aerospace Technologies
- [STC SA02511SE](https://openairdocs.org/stc/SA02511SE): Installation of replacement fuel quantity indicator sending unit(s). CiES Inc.
- [STC SA02738CH](https://openairdocs.org/stc/SA02738CH): Installation of L-3 Communications Avionics Systems. Acron Aviation Inc.
- [STC SA04046CH PAGE 2](https://openairdocs.org/stc/SA04046CH%20PAGE%202): Installation of L-3 GENESIS  (TM) Electronic Standby Instrument System (ESI-500/MAG-500). Acron Aviation Inc.
- [STC SA04378CH](https://openairdocs.org/stc/SA04378CH): Installation of an engine modified per STC SE04349CH. SureFly Partners Ltd.
- [STC SA00225IB](https://openairdocs.org/stc/SA00225IB): Installation of a Cockpit Combustion Heater Exhaust Extension on the Right-Hand Side (RHS) of the Fuselage. KASI Aviation Services Inc.
- [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 SA02658SE](https://openairdocs.org/stc/SA02658SE): Installation of Garmin GI 275 Multi-Function Display System. Garmin International Inc.
- [STC SA02571SE](https://openairdocs.org/stc/SA02571SE): Installation of Garmin G500/G600 TXi Integrated Avionics System (Primary Flight Display, Multi-Function Display, and Engine Indicating System Display).. Garmin International Inc.
- [STC SA02532AT](https://openairdocs.org/stc/SA02532AT): Installation of subject Michelin tires on appropriate aircraft. For Michelin 5, 6, 8, and 10-inch rim diameter tires on General Aviation Aircraft.. Michelin North America Inc.
- [STC SA04400NY](https://openairdocs.org/stc/SA04400NY): Installation of the Integrated Back-up Battery System (IBBS). TCW Technologies LLC
- [STC SA01435LA](https://openairdocs.org/stc/SA01435LA): Installation of engines modified with Firewall Forward Technologies LLC modified camshaft. Centri-Lube Technologies LLC
- [STC SA00756DE](https://openairdocs.org/stc/SA00756DE): Installation of Automatic Dependent Surveillance  Broadcast (ADS-B) Out Equipment using a Trig Avionics TT22 Transponder and an approved Global Positioning System (GPS) Position Sensor. Peregrine
- [STC SA04586CH](https://openairdocs.org/stc/SA04586CH): Installation of Electroair Back Up Battery Panel System Control. Electroair Aquisition Corp.
- [STC SA295GL](https://openairdocs.org/stc/SA295GL): Install Cleveland conversion kit, P/N 199-83.. Kaman Corporation Aircraft Wheel and Brake LLC
- [STC SA563GL](https://openairdocs.org/stc/SA563GL): Installation of Cleveland conversion kit, P/N 199-100.. Kaman Corporation Aircraft Wheel and Brake LLC
- [STC SA721GL](https://openairdocs.org/stc/SA721GL): Install Parker Hannifin Wheels & Brakes Conversion Kit 199-119. (PA-31-350 modified by STC SA4678SW). Kaman Corporation Aircraft Wheel and Brake LLC
- [STC SA01967WI](https://openairdocs.org/stc/SA01967WI): Use of GAMI G100UL High Octane Unleaded Avgas. General Aviation Modifications Inc.
- [STC SA02444AK](https://openairdocs.org/stc/SA02444AK): Approval of the L-3 Communications NGT 9000/9000R ADS-B system installed. ADS-B Technologies LLC
- [STC SA09066SC](https://openairdocs.org/stc/SA09066SC): Install LORI Oil Cooler, P/N L8535311.. Honeywell International Inc.
- [STC SA09856AC](https://openairdocs.org/stc/SA09856AC): Installation of BendixKing Aerowave 100 In-flight Data Link System for non-essential, non-required aircraft Cabin Systems & Equipments. Honeywell International Inc (Bendix King)
- [STC SA11174SC PAGE 2](https://openairdocs.org/stc/SA11174SC%20PAGE%202): Installation of BendixKing by Honeywell KSN 770 and KSN 765 WAAS LPV approach capable nav/comm systems. Honeywell International Inc (Bendix King)
- [STC SA1151SO](https://openairdocs.org/stc/SA1151SO): Installation of Hartzell four-blade Propellers, cowling changes, winglets or wingtip extension, optional governor arm adaptor, and optional engine isolator mounts. Mike Jones Aircraft Sales Inc.
- [STC SA02426AK](https://openairdocs.org/stc/SA02426AK): Approval of the FreeFlight FDL-978-TX ADS-B system installed. FreeFlight Systems
- [STC SA04083CH](https://openairdocs.org/stc/SA04083CH): Installation of universal bracket and a sight/viewing hole in the front baggage compartment. Certex Aviation LLC
- [STC SA10236SC](https://openairdocs.org/stc/SA10236SC): Installation of a GDC 31 Roll Steering Converter. DAC International Inc
- [STC SA09759DS](https://openairdocs.org/stc/SA09759DS): Installation of an S-TEC 01326 Digital Flight Control System (DFCS). S-TEC Corporation
- [STC SA02268CH](https://openairdocs.org/stc/SA02268CH): Installation of Airwolf Filter Corp. Air Oil Separator. Airwolf Filter Corporation
- [STC SA01161WI-D](https://openairdocs.org/stc/SA01161WI-D): Installation of the Bendix/King KFC 225 Flight Control System.. Honeywell International Inc
- [STC SA1187CE](https://openairdocs.org/stc/SA1187CE): Installation of King Model KCS 55A pictorial navigation (compass) system with optional KA 52 autopilot adapter.. Honeywell International Inc
- [STC SA1166CE](https://openairdocs.org/stc/SA1166CE): Installation of King KFC-200, 2 axis (3 optional) flight control system, autopilot only or autopilot with flight director. Honeywell International Inc
- [STC SA1529CE-D](https://openairdocs.org/stc/SA1529CE-D): Installation of King KAS 297 altitude selector option. Honeywell International Inc
- [STC SA3612NM](https://openairdocs.org/stc/SA3612NM): Installation of SAFT type 2376 nickel-cadmium battery.. Frontier Flying Service Inc.
- [STC SA3642NM](https://openairdocs.org/stc/SA3642NM): Installation of Hartzell HC-E3YR-2ATF/FC8468( )-8Q (left engine) and HC-E3YR-2ALTF/FJC8468( )-8Q (right engine) propeller assemblies. PA-31-350 (T-1020) and PA-31-350 (Chieftain). Serial numbers 31-7405218, 238, 485, 490; 31-7552043, 076; and 31-7652144 are ineligible for this installation.. Frontier Flying Service Inc.
- [STC SA01452CH](https://openairdocs.org/stc/SA01452CH): Installation of an air ambulance conversion kit.. Med-Pac Inc.
- [STC SA01714WI](https://openairdocs.org/stc/SA01714WI): Installation of a Garmin transponders: (a) GTX 330/330D/33/33D with ADS-B Out functionality; (b) GTX 335/335R/345/345R with ADS-B Out and In functionality; or (c) GTX 335R/345R with ADS-B Out functionality in select airplanes installed with G950/G1000 systems.. Garmin International Inc
- [STC SA03286CH](https://openairdocs.org/stc/SA03286CH): Install an electronic engine ignition system. Electroair Acquisition Corporation
- [STC SA04032CH](https://openairdocs.org/stc/SA04032CH): Install rocker switch assemblies. Electroair Acquisition Corporation
- [STC SA2124WE](https://openairdocs.org/stc/SA2124WE): Installation of air conditioning system.. Air Comm Corporation
- [STC SA00344BO PAGE 2](https://openairdocs.org/stc/SA00344BO%20PAGE%202): Installation of Parmetheus Plus LED PAR36 and PAR46 taxi and landing lights.. Whelen Aerospace Technologies
- [STC SA615EA](https://openairdocs.org/stc/SA615EA): Installation of a Whelen Anti-Collision Strobe Light System as replacement for originally installed anti-collision lights.. Whelen Aerospace Technologies
- [STC SA00528SE](https://openairdocs.org/stc/SA00528SE): Installation of emergency medical stretcher and base, oxygen, and electrical systems.. LifePort LLC

All 330: https://openairdocs.org/tcds/A20SO/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.