# TCDS A8EA: Piper Aircraft Inc.

- Type: Type certificate data sheet
- Status: Current
- Holder: Piper Aircraft Inc.
- Revision: 25
- Revised: July 30, 2013
- Product: Aircraft, Small Airplane
- Certification basis: Part 3, Part 23
- Registered aircraft: 242, by the registry models matched to it (OpenAirDocs)
- Data sheet PDF: https://openairdocs.org/files/sha256/52/27/52274f316abc7dfe33c7e537c44de701e88a149483ae295a59a96a0a6eb5b0cf
- FAA DRS: https://drs.faa.gov/browse/excelExternalWindow/4E30B03FC2BEFF3786257BB9004C3EFB.0001
- Page: https://openairdocs.org/tcds/A8EA

## Models (6)

As the data sheet lists them.

- PA-31T2
- PA-31P-350
- PA-31T
- PA-31T1
- PA-31P
- PA-31T3

## 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 16 17 
Rev. No. 25 23 24 23 24 19 24 25 20 24 20 24 20 21 22 20 21 
 
DEPARTMENT OF TRANSPORTATION 
FEDERAL AVIATION ADMINISTRATION 
 
A8EA 
Revision 25 
Piper Aircraft, Inc 
 PA-31P 
 PA-31T 
 PA-31T1 
 PA-31T2 
 PA-31T3 
 PA-31P-350 
 
July 30, 2013 
 
TYPE CERTIFICATE DATA SHEET NO. A8EA 
 
This data sheet which is a part of type certificate No. A8EA 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 A8EA to Piper Aircraft, Inc on August 7, 
2006. 
 
I. - Model PA-31P (Pressurized Navajo), 6 - 8 PCLM (Normal Category). Approved November 26, 1969. 
 
Engine Two Lycoming TIGO-541-E series 
 
Fuel 100/130 minimum grade aviation gasoline 
 
Engine Limits 3200 r.p.m. (2133 propeller r.p.m.) 425 hp, from sea level to 15,000 ft. altitude.  
 Full throttle operations at all altitudes. 
 Maximum 45.5 inches Hg. manifold pressure. 
 
Propeller and Propeller Limits Hartzell Hub and Blade Models: 
 HC-C3YN-2LU/JC9684-3R, HC-C3YN-2LUF/FJC9684-3R, or 
 HC-C3YN-2LAUF/FJC9684-3R 
 Pitch:  High 85.7 ± 1° (Feathered) 
 Diameter:  93.0” to 93.5” 
 
Propeller Governor 2 Woodward 210664 or 2 Woodward 210463 
 2 Woodward 210464 used when aircraft is equipped with Synchronizer 
 2 Woodward 210665 used when aircraft is equipped with Synchronizer. 
 2 Woodward 210772 used when aircraft is equipped with Synchronizer.

A8EA Page 2 of 17 
 
 
Airspeed Limits (CAS) *VNE (Never exceed) 283 mph (246 knots) 
 *VNO (Maximum structural cruise) 230 mph (200 knots) 
  VA (Maneuvering)   
    Minimum weight - 6000 lb. 180 mph (156 knots) 
    Maximum weight - 7800 lb. 198 mph (172 knots) 
  VFE (Flaps extended)   
    15° Flaps - Takeoff range 200 mph (174 knots) 
    Full flaps 150 mph (130 knots) 
  VLO (Landing gear operating)   
    Extend 180 mph (156 knots) 
    Retract 150 mph (130 knots) 
  VLE (Landing gear extended) 180 mph (156 knots) 
  VMC (Minimum control speed) - 15° Flaps 95 mph   (83 knots) 
 *See NOTE 9 for variation of VNE and VNO at altitudes of 13,000 ft. and above. 
 
C.G. Range (Gear Extended) (+128.8) to (+137.0) at 7800 lb. 
 (+125.0) to (+137.0) at 7200 lb. 
 (+122.0) to (+137.0) at 6000 lb. or less 
 Straight line variation between points given. 
 
8000
7500
7000
6500
6000
5500
5000 115 120 125 130 135 140
C.G. Location (Inches Aft of Datum)
122
125
128.8 137
Aircraft Weight
(lb.)
 
Empty Weight C. G. Range None 
 
Maximum Weight 7800 lb. - Takeoff 
 7800 lb. - 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 +242.0) 
 
Maximum Baggage 400 lb.  (200 lb. at +30, 200 lb. at +225) 
 
Fuel Capacity Total - 242 gallons 
  56 gallons at (+126.8) (Two wing tanks) 
  40 gallons at (+148.0) (Two wing tanks) 
  25 gallons at (+140.0) (Two nacelle tanks) 
 See NOTE 1 for unusable fuel data. 
 
Oil Capacity 36 quarts at (+83.0)  (4.5 gallons each engine - 5 quarts unusable each engine)

Page 3 of 17 A8EA 
 
Control Surface Movements Aileron 24° Up 14° Down 
 Aileron Tab 1 15° Up 20° Down 
(All measurements taken (Aileron Neutral)     
 at trailing edge from  Elevator 18° Up 20° Down 
 neutral position) Elevator Tab 10° Up 25° Down 
 (Elevator Neutral)     
 Rudder 35° Right 35° Left 
 Rudder Tab 35° Right 18° Left 
 (Rudder Neutral)     
 Flaps   40° Down 
 
Maximum Operating Altitude 29,000 feet pressure altitude 
 
Serial Numbers Eligible 31P-1 through 31P-80 and 31P-7300110 through 31P-7730012 (See NOTE 7 and 8 for 
 airworthiness certification eligibility in the United States). 
 
II. - Model PA-31T (Cheyenne/Cheyenne II), 6 - 9 PCLM (Normal Category), Approved May 3, 1972. 
 
Engine Two Pratt Whitney of Canada Ltd. PT6A-28 (TC No. E4EA) or Two Pratt & Whitney 
PT6A-28 (TC No. E2NE). 
 
Fuel If fuel PWA 522 is not available, Aviation Gasoline MIL-G-5572, all grades, may be 
used for maximum of 150 hours between overhauls. 
 
Oil UACL PT6 Service Bulletin No. 1 lists approved brand oils. 
 
Engine Limits (2200 r.p.m.) Static Sea Level Ratings PT6A-28 
   
 
 
Shaft  
Horsepower 
 
 
 
Jet 
Thrust 
 
 
Equiv. 
Shaft 
hp 
 
 
 
Prop Shaft  
Speed 
Maximum  
Permissible  
Turbine  
Interstage  
Temp. (°C) 
 Takeoff 620** 80 652 2200* 750 
 Maximum Cont. 620** 80 652 2200* 750 
 Strtg. Trans. (2 Sec.)     1090 
 Maximum Reverse 200   2068  
 
Engine Limits (2000 r.p.m.) Static Sea Level Ratings PT6A-28, Special Configuration - Ref. Piper Drawing No. 51670 
 (See Equipment Items 13 and 17) 
   
 
 
Shaft  
Horsepower 
 
 
 
Jet 
Thrust 
 
 
Equiv. 
Shaft 
hp 
 
 
 
Prop Shaft  
Speed 
Maximum  
Permissible  
Turbine  
Interstage  
Temp. (°C) 
 Takeoff 620** 80 652 2200* 750 
 Maximum Cont. 620** 80 652 2200* 750 
 Strtg. Trans. (2 Sec.)     1090 
 Maximum Reverse 200   1920  
 
 *See NOTE 6  
 **Available to ISA + 18°C 
 
Propeller and Propeller Limits Hartzell Hub and Blade Models: 
  HC-B3TN-3B/T-10173-HB-8 or HC-B3TN-3B/T-10173-B-8 
 Pitch:  High 87° ± 1° (Feathered), Low 20.2° at 30 in. station. 
 Diameter:  93.0” to 93.5” 
 
Propeller Governor 2 Woodward 8210-003 Propeller Governors

A8EA Page 4 of 17 
 
 
Airspeed Limits VMO (Maximum operating - up to 12,000 ft.) 283 mph (246 knots) 
    See VMO Chart for speeds above 12,000 ft. in Flight Manual   
 VA (Maneuvering)   
    Minimum weight - 5,195 lb. 168 mph (146 knots) 
    Maximum weight - 9,000 lb. - up to 26,900 ft. 207 mph (180 knots) 
      See VMO Chart for speeds above 26,900 ft. in Flight Manual   
 VFE (Flaps extended)   
      15° flaps 200 mph (174 knots) 
      Full flaps 165 mph (144 knots) 
 VLO (Landing gear - operating)   
      Extended 180 mph (156 knots) 
      Retracted 150 mph (143 knots) 
 VLE (Landing gear extended) 180 mph (156 knots) 
 VMC (Minimum control speed) 110 mph   (96 knots) 
 
C.G. Range (Gear Extended)  (+131.9) to (+138.0) at 9000 lb. (S/N 31T-7400002 through 31T-7720069) 
 (+129.6) to (+138.0) at 8500 lb. (S/N 31T-7400002 through 31T-8120104) 
 (+126.0) to (+138.0) at 7170 lb. or less (S/N 31T-8020001 through 31T-8120104) 
 (+125.0) to (+138.0) at 6800 lb. or less (S/N 31T-7400002 through 31T-7920094) 
 Straight line variation between points given. 
 
8000
7500
7000
6500
6000
5500
5000 115 120 125 130 135 140
C.G. Location (Inches Aft of Datum)
126.0
129.6
Aircraft Weight
(lb.)
8500
9000 131.9 138.0
125.0
 
 
Empty Weight C. G. Range None 
 
Maximum Weight 9000 lb. - Takeoff 
 9000 lb. - Landing 
 9050 lb. - Ramp 
 
No. of Seats 6 - 8  (2 at +119.0, 2 at +166.0, 2 at +198.0)  
   (2 Optional:  1 at +229.0, 1 at +242.0) 
 
Maximum Baggage 500 lb.  (300 lb. at +30, 200 lb. at +255) 
 Piper Kit No. 760 987 required for S/N 31T-7400002 through 31T-7520050 if more than  
  200 lb. forward baggage capacity is used.

Page 5 of 17 A8EA 
Fuel Capacity 390 gallons maximum at (+138.9) 
 195 gallons when filled through wing tip filler (two wing tanks) 
   or 
 346 gallons maximum at (+138.9) 
 173 gallons when filled through wing tip filler (two wing tanks) 
 See NOTE 1 for unusable fuel data. 
 
Oil Capacity 26 quarts at (+91.8)  (13 quarts each engine - 3 quarts unusable each engine) 
 
Control Surface Movements Aileron 24° Up 14° Down 
 Aileron Tab 1 15° Up 20° Down 
(All measurements taken at (Aileron Neutral)     
trailing edge from neutral  Elevator 16° Up 20° Down 
position) Elevator Tab 1 1° Up 36° Down 
 (Elevator Neutral)     
 Rudder 35° Right 35° Left 
 (Rudder Neutral)     
 Flaps   40° Down 
 
Maximum Operating Altitude 29,000 ft. pressure altitude 
 31,000 ft. pressure altitude (S/N 31T-8020001 through 31T-8120104) 
 
Serial Numbers Eligible 31T-7400002 through 31T-7400018; and 
 31T-7520001 through 31T-8120104  
 Note:  For the serial number range specified (31T-7520001 through 31T-8120104, only 
serial numbers with the following format are eligible; 
 31T-XX20XXX  where X is a number between zero (0) and nine (9) inclusive.  The 
characters “31T” and “20” must appear in the positions shown.   
 For example, 31T-7820055 is a valid serial number for model PA-31T, but serial number 
31T-7804010 is not. 
 (See NOTE 7 and 8 for airworthiness certification eligibility in the United States). 
 
III. - Model PA-31T1 (Cheyenne I/IA), 6 - 7 PCLM (Normal Category), Approved March 6, 1978. 
 
Engine Two UACL PT6A-11 
 
Fuel If fuel PWA 522 is not available, Aviation Gasoline MIL-G-5572, all grades, may be 
used for maximum of 150 hours between overhauls. 
 
Oil UACL PT6 Service Bulletin No. 1 lists approved brand oils. 
 
Engine Limits Static Sea Level Ratings PT6A-11 
   
 
 
Shaft  
Horsepower 
 
 
 
Jet 
Thrust 
 
 
Equiv. 
Shaft 
hp 
 
 
 
Prop Shaft  
Speed 
Maximum  
Permissible  
Turbine  
Interstage  
Temp. (°C) 
 Takeoff 500** 70 528 2200*   700 
 Maximum Cont. 455** 65 481 2000*   685 
 Strtg. Trans. (2 Sec.)     1090 
 Maximum Reverse 200   2068  
 *See NOTE 6 
 **Available to ISA + 18°C 
 
Propeller and Propeller Limits Hartzell Hub and Blade Models: 
  HC-B3TN-3B/T10173B-8 
  HC-B3TN-3B/T-10173K-8 for S/N 31T-8304001 through 31T-8304003, and 
   31T-1104004 through 31T-1104017 
 Pitch:  High 87° (Feathered), Low 20.2° at 30 in. station. 
 Diameter:  93.0” to 93.5” 
 
Propeller Governor 2 Woodward 8210-003 or 8210-035 Propeller Governors

A8EA Page 6 of 17 
 
Airspeed Limits   (CAS) VMO (Maximum operating -without tip tanks) 265 mph (230 knots) 
 VMO (Maximum operating - with tip tanks - 283 mph (246 knots) 
    up to 9,500 ft.) (For speeds above 9,500 ft., see Flight Manual)    
 VA (Maneuvering - without tip tanks)   
    Minimum weight - 5,195 lb. 168 mph (146 knots) 
    Maximum weight  - 8,700 lb. - up to  207 mph (180 knots) 
      24,600 ft. (For speeds above 24,600 ft., see Flight Manual.)   
 VA (Maneuvering - with tip tanks)   
    Minimum weight  - 5,195 lb. 168 mph (146 knots) 
    Maximum weight - 8,700 lb.--up to 207 mph (180 knots) 
    27,700 ft. (For speeds above  27,700 ft., see Flight Manual.)   
 VFE (Flaps extended)   
    15° Flaps 200 mph (174 knots) 
    Full Flaps 165 mph (143 knots) 
 VLO (Landing gear - operating)   
    Extend 180 mph (156 knots) 
    Retract 165 mph (143 knots) 
 VLE (Landing gear extended) 180 mph (156 knots) 
 VMC (Minimum control speed) 104 mph (90 knots) 
 
C.G. Range (Gear Extended) (+130.5) to (+136.0) at 8700 lb. 
 (+129.6) to (+136.0) at 8500 lb. 
 (+126.5) to (+136.0) at 7200 lb. or less 
 Straight line variation between points given. 
 
8000
7500
7000
6500
6000
5500
5000 115 120 125 130 135 140
C.G. Location (Inches Aft of Datum)
126.5
129.6
Aircraft Weight
(lb.)
8500
9000 130.5 136.0
 
Empty Weight C. G. Range None 
 
Maximum Weight 8700 lb. - Takeoff 
 8700 lb. - Landing 
 8750 lb. - Ramp 
 
No. of Seats 31T-7804001 through 31T-8104073 and 31T-8104101: 
  6 - 7 Seats (2 at +119.0, 2 at +166.0, 2 at +198.0)  
     (2 optional, 1 at +229.0) 
 
 31T-8304001 through 31T-8304003, 31T-1104004 through 31T-1104017: 
  6 - 7 Seats (2 at +116.96 to +121.09) 
     (2 at +149.85 to +172.85) 
     (2 at +196.50 to +212.35) 
     (1 at +232.60 to +240.50)

Page 7 of 17 A8EA 
 
Maximum Baggage 31T-7804001 through 31T-8104073 and 31T-8104101: 
  500 lb. (300 lb. at +30, 200 lb. at +255)  
 
 31T-8304001 through 31T-8304003, and 31T-1104004 through 31T-1104017: 
  500 lb. (300 lb. at +37, 200 lb. at +260.0)  
 
 Fuel Capacity (Standard) 308 gallons maximum at (+138.9) 
  154 gallons (two wing tanks) when filled through nacelle filler. 
 Fuel Capacity (including 
   optional tip tanks) 390 gallons maximum at (+138.9) 
 195 gallons (two wing tanks) when filled through wing tip filler.  
or 
 346 gallons maximum at (+138.9) 
 173 gallons (two wing tanks) when filled through nacelle filler. 
  
 31T-8304001 through 31T-8304003, and 31T-1104004 through 31T-1104017: 
 374 gallons maximum at (+138.3) 
 187 gallons (two wing tanks) when filled through nacelle filler. 
or 
 336 gallons maximum at (+138.3) 
 168 gallons (two wing tanks) when filled through nacelle filler. 
  
 See NOTE 1 for unusable fuel data. 
 
Oil Capacity 26 quarts at (+91.8)  (13 quarts each engine - 3 quarts unusable each engine) 
 
Control Surface Movements Aileron 24° Up 14° Down 
 Aileron Tab 1 15° Up 20° Down 
(All measurements taken at (Aileron Neutral)     
trailing edge from neutral  Elevator 16° Up 20° Down 
position) Elevator Tab 1° Up 36° Down 
 (Elevator Neutral)     
 Rudder 35° Right 35° Left 
 Rudder Tab 20° Right 45° Left 
 (Rudder Neutral)     
 Flaps   40° Down 
 
Maximum Operating Altitude 29,000 ft. pressure altitude 
 
Serial Numbers Eligible 31T-7804001 through 31T-8104073;  31T-8104101;  31T-8304001 through  
 31T-8304003;  and 31T-1104004 through 31T-1104017  
 Note:  only serial numbers with the following format are eligible: 31T-XX04XXX 
 where X is a number between zero (0) and nine (9) inclusive.  The characters “31T” 
                                                        and “04” must appear in the posit ions shown.  For example, 31T-7804010 is  
                                                        a valid serial number for model PA -31T1, but serial number 31T-7820055 is not. 
                                                        (See NOTE 7 and 8 for   airworthiness certification eligibility in the United States). 
 
IV. - Model PA-31T2 (Cheyenne IIXL), 6 - 10 PCLM (Normal Category), Approved February 12, 1981. 
 
Engine 2 UACL PT6A-135 
 
Fuel If fuel PWA 522 is not available, Aviation Gasoline MIL-G-5572, all grades, may be 
used for maximum of 150 hours between overhauls (See PWA Service Bulletin No. 
1244).

A8EA Page 8 of 17 
 
Oil CPW 202 or PWA 521 Type II  (See PWA PT6 Service Bulletin No. 1001 for approved 
brands.) 
 
Engine Limits Static Sea Level Ratings PT6A-135 
   
 
 
Shaft  
Horsepower 
 
 
 
Torque 
ft-lb. 
 
 
 
Prop Shaft  
Speed 
Maximum  
Permissible  
Turbine  
Interstage  
Temp. (°C) 
 Takeoff 620** 1714 1900*   805 
 Maximum Cont. 620*** 1714 1900*   805 
 Strtg. Trans. (2 Sec.)    1090 
 Maximum Reverse 200   655 1815   805 
       *See NOTE 11 
   **Available to ISA +23°C 
 ***Available to ISA +24°C 
 
Propeller and Propeller Limits Hartzell Hub and Blade Models: 
  HC-B3TN-3B/T10178B-8R 
 Pitch:  High 88.2° ± .5° (Feathered);  Low 20.2° ± 1°;  Reverse -11° ± 5° at  
    30 in. station. 
 Diameter:  93.0” to 93.5” 
 
Propeller Governor 2 Woodward 8210-003 Propeller Governors 
 
Airspeed Limits (CAS) VMO (Maximum operating - up to 12,000 ft.) 283 mph (246 knots) 
    (For speeds above 12,000 ft., see Flight Manual)   
 VA (Maneuvering)   
    Minimum weight - 5,704 lb. 176 mph (153 knots) 
    Maximum weight - 9,474 lb. - up to 25,300 ft. 215 mph (187 knots) 
       (See VMO chart for speeds above 25,300 ft. in Flight Manual)   
 VFE (Flaps extended)   
    15° Flaps 200 mph (174 knots) 
    Full Flaps 166  mph (144 knots) 
 VLO (Landing gear operating)   
     Extend 180 mph (156 knots) 
     Retract 165 mph (143 knots) 
 VLE (Landing gear extended 200 lb. at (+255)) 180 mph (156 knots) 
  (Nitrogen system) 138 mph (120 knots) 
 VMC (Minimum control speed) 110 mph (96 knots)

Page 9 of 17 A8EA 
 
C.G. Range (Gear Extended (+124.0) to (+136.0) at 5850 lb. and less 
 (+129.5) to (+136.0) at 9474 lb. 
 Straight line variation between points given. 
 Location of datum is 137.0 inches forward of the main spar centerline. 
 
8000
7500
7000
6500
6000
5500
5000
115 120 125 130 135 140
C.G. Location (Inches Aft of Datum)
124.0
129.5
Aircraft Weight
(lb.)
8500
9000
136.09500
 
 
Empty Weight C. G. Range None 
 
Maximum Weight 9474 lb. - Takeoff 
 9000 lb. - Landing 
 9540 lb. - Ramp 
 7600 lb. - Maximum Zero Fuel Weight 
 
No. of Seats 6 - 8 Seats (2 at +95.0, 2 at +142.6 (aft facing)) 
    (2 at +165.9 (fwd facing)) 
    (2 at +196.5, or 1 at +229.0 and 1 at +242.0)  
 
 6 - 8 Seats (2 at +95.0) 
    (2 at +130.9) 
    (2 at +165.9) 
    (1 at +229.0) 
    (1 at +242.0) 
 
 6 - 10 Seats * (2 at +95.0) 
    (2 at +130.9) 
    (2 at +165.6) 
    (2 at +196.5) 
    (1 at +229.0) 
    (1 at +242.0) 
 *For aircraft modified per Piper Dwg. No. 02252.  See Equipment Item No. 23. 
 
Maximum Baggage 500 lb.  (300 lb. at +3) 
   (200 lb. at +255)

A8EA Page 10 of 17 
 
 Fuel Capacity 390 gallons maximum at (+138.9) 
  195 gallons (two wing tanks) when filled through wing tip filler. 
or 
  346 gallons maximum at (+138.9) 
  173 gallons (two wing tanks) when filled through nacelle filler. 
 See NOTE 1 for unusable fuel data. 
 
Control Surface Movements Aileron 24° Up 14° Down 
 Aileron Tab 15° Up 20° Down 
(All measurements taken at (Aileron Neutral)     
trailing edge from neutral  Elevator 16° Up 20° Down 
position) Elevator Tab 1° Up 36° Down 
 (Elevator Neutral)     
 Rudder 35° Right 35° Left 
 Rudder Tab 20° Right 45° Left 
 (Rudder Neutral)     
 Flaps 40° Down   
 
Maximum Operating Altitude 31,000 ft. pressure altitude 
 
Serial Numbers Eligible 31T-8166001 through 31T-8166076, and 31T-1166001 through 31T-1166008 
 (See NOTE 7 and 8 for airworthiness certification eligibility in the United States). 
 
V. - Model PA-31T3 (T-1040), 9 - 11 PCLM (Normal Category), Approved February 25, 1982. 
 
Engine Two UACL PT6A-11 
 
Fuel If fuel PWA 522 is not available, Aviation Gasoline MIL-G-5572, all grades, may be 
used for maximum of 150 hours between overhauls. 
 
Oil UACL PT6 Service Bulletin 1 lists approved brand oils. 
 
Engine Limits Static Sea Level Ratings PT6A-11 
   
 
 
Shaft  
Horsepower 
 
 
 
Jet 
Thrust 
 
 
Equiv. 
Shaft 
hp 
 
 
 
Prop Shaft  
Speed 
Maximum  
Permissible  
Turbine  
Interstage  
Temp. (°C) 
 Takeoff 500** 70 528 2200*   700 
 Maximum Cont. 500** 70 528 2200*   700 
 Strtg. Trans. (2 Sec.)     1090 
 Maximum Reverse 200   2112  
   *See NOTE 6. 
 **Available to ISA + 18°C 
 
Propeller and Propeller Limits Hartzell Hub and Blade Models: 
  HC-B3TN-3B/T-10173B-8 
 Pitch:  High 87° ± 1° (Feathered), Low 20.2° at 30 in. station. 
 Diameter:  93.0” to 93.5” 
 
Propeller Governor 2 Woodward 8210-003 or 8210-035 Propeller Governors

Page 11 of 17 A8EA 
 
Airspeed Limits (CAS) VMO (Maximum operating - up to 12,000 ft.) 265 mph (230 knots) 
    (See VMO chart for speeds above 12,000 ft. in Flight Manual)   
 VA (Maneuvering)   
    Minimum weight - 4924 lb. 166 mph (144 knots) 
    Maximum weight - 9000 lb. 210 mph (183 knots) 
    (Up to 23,600 ft., see VMO  chart for speeds above 23,600 ft. in Flight Manual)   
 VFE (Flaps extended)   
    15° flaps 200 mph (174 knots) 
    Full flaps 165 mph (143 knots) 
 VLO (Landing gear operating)   
     Extend 180 mph (156 knots) 
     Retract 165 mph (143 knots) 
 VLE (Landing gear extended) 180 mph (156 knots) 
 VMC (Minimum control speed) 103 mph (90 knots) 
 
C.G. Range (Gear Extended) (+128.5) to (+135.0) at 9000 lb. 
 (+120.0) to (+135.0) at 5200 lb. or less 
 Straight line variation between points given. 
 
7500
7000
6500
6000
5500
5000
4500
115 120 125 130 135 140
C.G. Location (Inches Aft of Datum)
120.0
128.5
Aircraft Weight
(lb.)
8000
8500
135.09000
 
 
Empty Weight C.G. Range None 
 
Maximum Weight 9000 lb. - Takeoff 
 9000 lb. - Landing 
 9050 lb. - Ramp 
 7600 lb. - Maximum Zero Fuel Weight 
 
No. of Seats 9 - 11 Seats (2 at +95.0, 2 at +130.9, 
    2 at +164.6, 2 at +193.6, 
    1 at +222.6, 2 at +253.5)

A8EA Page 12 of 17 
 
 Maximum Baggage Standard Total 700 lb. 
 With Optional Cargo Pod 1050 lb. 
  Fuselage 300 lb. at (+13) 
   100 lb. at (+268) 
  Nacelle Lockers 150 lb. each side at (+182) 
  Cargo Pod 350 lb. 
 See Supplement 8 to Airplane Flight Manual - Piper Report 2297 for data  
  concerning C.G. 
 Minimum Zero Fuel Weight for loading Nacelle Lockers - 5066 lb. 
 
Fuel Capacity (Standard) 300 gallons maximum at (+135.9) (150 gallons each wing) 
 See NOTE 1 for unusable fuel data. 
 
Oil Capacity 26 quarts at (+91.8)  (13 quarts each engine - 3 quarts unusable each engine) 
 
Control Surface Movements Aileron 24° Up 14° Down 
 Aileron Tab 1 15° Up 20° Down 
(All measurements taken at (Aileron Neutral)     
trailing edge from neutral  Elevator 16° Up 20° Down 
position) Elevator Tab 1° Up 36° Down 
 (Elevator Neutral)     
 Rudder 35° Right 35° Left 
 Rudder Tab 20° Right 45° Right 
 (Rudder Neutral)     
 Flaps   40° Down 
 
Maximum Operating Altitude 24,000 ft. pressure altitude 
 
Serial Numbers Eligible 31T-8275001 through 31T-8475001, and 31T-5575001 
 
VI. - Model PA-31P-350 (Mojave), 6 - 7 PCLM (Normal Category), Approved June 9, 1983. 
 
Engine Two Lycoming TIO-LTIO-540V2AD 
 
Fuel 100 or 100LL minimum grade aviation gasoline 
 
Engine Limits 2600 r.p.m., 42 in. Hg., 350 hp. to 18,000 ft.  
 Above 18,000 ft., 2600 r.p.m., reduce manifold pressure to 33.6 in. Hg. at 25,000 ft.  
 (Straight line variation between 18,000 ft. and 25,000 ft.) 
 
Propeller and Propeller Limits Hartzell Hub and Blade Models: 
  HC-I3YR-2UF/FC7854 or HC-I3YR-2UF/FC7854K  (Left) 
  HC-I3YR-2LUF/FJC7854 or HC-I3YR-2LUF/FJC7854K  (Right) 
 Pitch:  High 16.5° to 19.5°;  Low 12.5° ± 0.1°;  Feather 80° ± 0.5° at  
    30 in. station. 
 Diameter:         80 in. 
    No reduction permitted. 
 
Propeller Governor 1 Hartzell Model V-1 
 1 Hartzell Model V-1L

Page 13 of 17 A8EA 
 
Airspeed Limits (CAS) VNE (Never exceed- up to 12,264 ft.) 271 mph (236 knots) 
    For speeds above 12,264 feet, see Flight Manual   
 VNO (Maximum structural cruise speed) 215 mph (187 knots) 
 VA (Maneuvering speed at maximum   
      gross weight) 188 mph (164 knots) 
 VFE (Flaps extended)   
      15° 184 mph (160 knots) 
      Full flaps 150 mph (130 knots) 
 VLO (Landing gear operating)   
      Extend 180 mph (156 knots) 
      Retract 150 mph (130 knots) 
 VLE (Landing gear extended) 180 mph (156 knots) 
 VMC (Minimum control speed) 85 mph (74 knots) 
 
C.G. Range (Gear Extended) (+126.4) to (+134.5) at 7200 lb. 
 (+123.0) to (+134.5) at 5600 lb. or less 
 (+126.5) to (+134.5) at 7245 lb. ramp weight 
 Straight line variation between points given. 
 
7000
6000
5000
120 124 128 132 136
C.G. Location (Inches Aft of Datum)
Aircraft Weight
(lb.)
123.0
126.4 134.5
 
 
Empty Weight C.G. Range None 
 
Maximum Weight 7200 lb. - Takeoff 
 7000 lb. - Landing 
 7245 lb. - Ramp 
 6700 lb. - Maximum Zero Fuel Weight 
 
No. of Seats 6 - 7 Seats (2 at +116.96 to +121.09) 
    (2 at +149.85 to +162.60) 
    (2 at +196.50 to +212.35) 
    (1 at +232.60 to +240.50) 
 
Maximum Baggage Total -   680 lb. 
 Fuselage - 300 lb. at +37.0 
    200 lb. at +260.40 
 Nacelle Lockers, 90 lb. each side at +180.00

A8EA Page 14 of 17 
 
Fuel Capacity 242 gallons maximum at (+134.9)  (12.5 gallons each wing) 
 See NOTE 1 for unusable fuel data. 
 
Oil Capacity 26 quarts at (+77.5)  (13 quarts each side) 
 13 quarts unusable at (+77.5)  (6.5 quarts each side) 
 
Control Surface Movements Aileron (± 1°) 24°  Up 14°  Down 
 Aileron Tab (± 1°) 15°  Up 20°  Down 
(All measurements taken at (Aileron Neutral)      
trailing edge from neutral  Elevator (± 1°) 16° Up 20° Down 
position) Elevator Tab (± 1°) 9° Up 36° Down 
 (Elevator Neutral)      
 Rudder (+ 0°, - 1°) 30° Left 30° Right 
 Rudder Tab (± 1°) 40° Left 18° Right 
 (Rudder Neutral)      
 Flaps (± 1°) 40° Down   
 
Maximum Operating Altitude 25,000 ft. pressure altitude 
 
Serial Numbers Eligible 31P-8414001 through 31P-8414050. 
 
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. A8EA issued February 24, 1966, reissued June 25, 1966 and October 
25, 1972, 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-31T: Special Conditions Nos. 23-3-EA-1 Docket No. 9245 including 
Amendment No. 1 and AEA-210 letter of November 11, 1971, and FAR 23.991 as 
amended by Amendment 23-7, effective September 14, 1969. 
 
 Model PA-31T1: Special Conditions No. 23-3-EA-1 Docket No. 9245 including 
Amendment No. 1 and AEA-210 letter of November 11, 1971, as amended by AEA-210 
letter of February 1, 1978, referring to Amendment 23-14 and FAR 23.991 as amended 
by Amendment 23-7, effective September 14, 1969, and SFAR 27 (Fuel Venting). 
 
 Model PA-31T2: Special Conditions No. 23-3-EA-1 Docket No. 9245 including 
Amendment No. 1 and AEA-210 letter of November 11, 1971, as amended by AEA-210 
letter of February 1, 1978, referring to Amendment 23-14 and FAR 23.991 as amended 
by Amendment 23-7, effective September 14, 1969. 
  Noise Certification - FAR 36 up to Amendment 10, as applicable. 
  Fuel Venting Emissions - SFAR 27 up to Amendment 3, as applicable.

Page 15 of 17 A8EA 
 
Certification Basis Model PA-31T3: Special Conditions No. 23-3-EA-1 Docket No. 9245 including 
Amendment No. 2 and AEA-210 letter of November 11, 1971, as amended by AEA-210 
letter of February 1, 1978, referring to Amendment 23-14 and FAR 23.991 as amended 
by Amendment 23-7, effective September 14, 1969. 
  Noise Certification - FAR 36 up to Amendment 10, as applicable. 
  Fuel Venting Emissions - SFAR 27 up to Amendment 3, as applicable. 
 Model PA-31P-350: FAR 23.75(a) and 23.77 as amended by Amendment 23-7, effective 
September 14, 1969, and FAR 23.145, 23.161, 23.173, and 23.175 as amended by 
Amendment 23-14, effective December 20, 1973. 
 Noise Certification - FAR 36 up to Amendment 12, as applicable. 
 
Production Basis Approved for manufacture of spare parts only under Production Certificate No. 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. Stall Warning Indicator 
  (a) Deleted April, 1978 
  (b) Installed per Piper Drawing 46600 on Model PA-31P 
  2. Deleted April, 1978 
  3. Deleted April, 1978 
  4. D.O.A. No. EA-1 approved Airplane Flight Manual Report No. 1615 dated 
 January 23, 1970 for Model PA-31P, S/N 31P-1 through 31P-80, and  
  31P-7300110 through 31P-7630019. 
  5. Deleted April, 1978 
  6. Deleted April, 1978 
  7. Deleted April, 1978 
  8. Deleted April, 1978 
  9. D.O.A. No. EA-1 Approved Airplane Flight Manual per Piper Report 1740 dated  
  May 3, 1972, issued February 11, 1974, for Model PA-31T, S/N 31T-7400002  
  through 31T-7620057. 
 10. Deleted April, 1978 
 11. Deleted April, 1978 
 12. Stability Augmentation System (SAS) installed per Piper Drawing 51770 for 
 PA-31T, S/N 31T-7400002 through 31T-8120104. 
 13. D.O.A. No. EA-1 Approved Airplane Flight Manual per Piper Report 1942 dated  
  June 20, 1975, for Model PA-31T, S/N 31T-7400002 through 31T-7620057  
  when airplane is modified per Piper Drawing No. 51670.  (2000 r.p.m.). 
 14. D.O.A. No. EA-1 Approved Pilot's Operating Handbook per Piper Report 2047  
  dated October 14, 1976, for Model PA-31P, S/N 31P-7730001 through  
  31P-7730012. 
 15. D.O.A. No. EA-1 Approved Pilot's Operating Handbook per Piper Report 2048  
  dated October 21, 1976, for Model PA-31T, S/N 31T-7720001 through  
  31T-7920094. 
 16. D.O.A. No. EA-1 Approved Pilot's Operating Handbook per Piper Report 2124 
 dated May 15, 1978, for Model PA-31T1, S/N 31T-7804002 through 31T-8104073;  
  31T-8104101;  31T-8304001 through 31T-8304003;  and 31T-1104004 through  
  31T-1104017. 
 17a. When PA-31T, S/N 31T-7720001 through 31T-7920094 are modified per  Piper 
Dwg. No. 51670 (2000 r.p.m.), Piper Supplemental Report No. 2092 dated  August 
12, 1977, "2000 R.P.M. Limitation" must be added to the basic Pilot's  
  Operating Handbook. 
 17b. When PA-31T, S/N 31T-8020001 through 31T-8120104 are modified per Piper 
  Dwg. No. 51670 (2000 r.p.m.), Piper Supplement Report No. 2259 dated June 27,  
  1980, "2000 R.P.M. Limitation" must be added to the basic Pilot's  
  Operating Handbook. 
 18. D.O.A. No. EA-1 Approved Pilot's Operating Handbook per Piper Report 2210 for 
 Model PA-31T, S/N 31T-8020001 through 31T-8120104.

A8EA Page 16 of 17 
 
Equipment (cont.) 19. D.O.A. No. EA-1 Approved Pilot's Operating Handbook per Piper Report 2272  
  dated May 26, 1981, for Model PA-31T2, S/N 31T-8166001 through  
  31T-8166076, and 31T-1166001 through 31T-1166008. 
 20. D.O.A. No. EA-1 Approved Pilot's Operating Handbook per Piper Report 2297 
  dated February 25, 1982, for Model PA-31T3, S/N 31T-8275001 through  
  31T-8475001, and 31T-5575001. 
 21. D.O.A. No. EA-1 Approved Pilot's Operating Handbook per Piper Report 2311 
 dated May 6, 1983, for Model PA-31T1, S/N 31T-8304001 through 
 31T-8304003, and 31T-1104004 through 31T-1104017. 
 22. D.O.A. No. EA-1 Approved Pilot's Operating Handbook per Piper Report 
 Number 2313, dated June 9, 1983, for Model PA-31P-350, S/N 31P-8414001 
 through 31P-8414050. 
 23. When Model PA-31T2, S/N 31T-8166001 through 31T-8166076, and 31T-1166001  
  through 31T-1166008 are modified per Piper Dwg. No. 02252, Piper Supplement 8  
  Report 2272 dated July 6, 1983, must be added to the basic Pilot's Operating  
  Handbook. 
 
 
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.  
All of the fuel and oil can be drained.  However, the certificated empty weight and corresponding center of 
gravity location must include unusable fuel of 36 lb. at (+129.0) for Model PA-31P; 54 lb. at (+129.0) for 
Models PA-31T and PA-31T1; 54 lb. at (+133.0) for Model PA-31T2; 54 lb. at (+125.0) for Model 
PA-31T3; 30 lb. at (+125.1) for Model PA-31P-350. 
 
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 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." 
 
NOTE 3  For Models PA-31T, PA-31T1, PA-31T2 and PA-31T3, the elevator downspring, P/N 51484, must be 
replaced upon the accumulation of 2,000 hours time-in-service, and thereafter at every 2000 hours time-in-
service. 
 
NOTE 4  Deleted April, 1978 
 
NOTE 5  Deleted April, 1978 
 
NOTE 6  The maximum propeller shaft overspeed limit is 110% of all ratings and may be employed for sustained 
periods in emergencies.  100% propeller shaft speed is defined as 2200 r.p.m. and is the operating limit.  Gas 
generator speeds up to 102.5% are permissible for 10 seconds and to 101.5% for unlimited periods subject to 
applicable temperature and other limits.  100% gas generator speed is defined as 37,500 r.p.m.. 
 
NOTE 7  Any aircraft with a letter prefix on the serial number is not eligible for Airworthiness Certification in the 
United States; for example, AR31-XXXXXXX.

Page 17 of 17 A8EA 
 
NOTE 8  The following S/N are not eligible for Airworthiness Certification in the United States: 
 
  PA-31P: 
   31P-7400211, 31P-7400213, 31P-7400219, 31P-7400230, 31P-7530016, and 31P-7530021. 
 
  PA-31T: 
   31T-7920017, 31T-7920031, 31T-7920033, 31T-7920050, 31T-7920076, 31T-7920080, 31T-7920085,  
   31T-8020013, 31T-8020028, 31T-8020040, 31T-8020047, 31T-8020054, 31T-8020077, 31T-8020079,  
   31T-8020092, 31T-8120015, 31T-8120032, 31T-8120037, 31T-8120047, 31T-8120051, 31T-8120062, 
   and 31T-8120064. 
 
  PA-31T1: 
   31T-7904045. 
 
  PA-31T2: 
   31T-8166019, 31T-8166035, 31T-8166053, 31T-8166059,and 31T-8166073. 
 
NOTE 9  For Model PA-31P - Reduce VNO and VNE speeds as follows: 
 
 Altitude 
(1000 feet) 
VNO 
(mph) 
VNE 
(mph) 
 13 230 278 
 15 230 268 
 17 230 258 
 19 221 248 
 21 212 238 
 23 203 228 
 25 194 218 
 27 185 208 
 29 176 198 
 
NOTE 10  Refer to Type Certificate Data Sheet No. A20SO for Models PA-31, PA-31-300, PA-31-325, and 
PA-31-350.  Models PA-31, PA-31-300, PA-31-325 and PA-31-350, originally produced under this type 
certificate are now under Type Certificate A20SO.  Information pertaining to these model aircraft is 
published on Type Certificate Data Sheet A20SO.  This applies to the following serial numbered aircraft: 
 
  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 
 
  This NOTE reflects a split in the original Type Certificate for administrative purposes.  All serial numbered 
aircraft subsequent to the above are manufactured under Type Certificate A20SO.  Refer to Type Certificate 
Date Sheet A20SO for all information pertaining to Models PA-31, PA-31-300, PA-31-325, and PA-31-350. 
 
NOTE 11  The maximum propeller shaft overspeed limit is 110% of all ratings and may be employed for sustained 
periods in emergencies.  100% propeller shaft speed is defined as 33,000 r.p.m. power turbine and 1900 
r.p.m. propeller speed.  This is the normal steady state operating limit.  Gas generator speeds up to 102.6% 
are permissible for 2 seconds and to 101.5% for unlimited periods subject to applicable temperature and 
other limits.  100% gas generator speed (Ng) is defined at 37,500 r.p.m.. 
 
 
 
 
...END...
```

## ADs (71, 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 2017-02-06](https://openairdocs.org/ad/2017-02-06): Electrical Power/Electrical Power System Wiring · Piper PA-31P-350, PA-31T, PA-31T1 and 2 more. Effective Feb 22, 2017
- [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 2014-23-03](https://openairdocs.org/ad/2014-23-03): Engine Exhaust · Piper PA-31P. Effective Dec 18, 2014
- [AD 2012-10-09](https://openairdocs.org/ad/2012-10-09): Placards and Markings · Piper PA-31T and PA-31T1. Effective Jun 29, 2012
- [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 2006-16-18 R1](https://openairdocs.org/ad/2006-16-18-R1): Installing a warning placard on the TAWS/RMI · Airbus A300 B2-1A, A300 B2-1C, A300 B2-203 and 100 more. Effective Jul 18, 2008
- [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 2005-18-20](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 2005-01-19](https://openairdocs.org/ad/2005-01-19): Mode S transponders · GARMIN International GTX 330D, GTX 330, GTX 33D and 830 more. Effective Feb 23, 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 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 98-25-02](https://openairdocs.org/ad/98-25-02): Top-mounted Antenna · Bell Helicopter Textron Canada 407, 172, 172A and 243 more. Effective Dec 22, 1998
- [AD 98-14-03](https://openairdocs.org/ad/98-14-03): Transponders · Cessna 172, 172A, 172B and 230 more. Effective Aug 16, 1998
- [AD 98-08-18](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 97-26-12](https://openairdocs.org/ad/97-26-12): AFM - Limitations Section - Power Levers · Piper PA-31T, PA-31T1, PA-31T2 and 4 more. Effective Jan 28, 1998
- [AD 85-02-05 R1](https://openairdocs.org/ad/85-02-05-R1): Piper P/N s 81090-02, 683-107 Placard Installation · Lavia Argentina PA-25, PA-25-235, PA-25-260 and 32 more. Effective Nov 21, 1997
- [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 97-02-01](https://openairdocs.org/ad/97-02-01): Landing Gear Emergency Extension Air Line · Piper PA-31T2 with STC SA599GL. Effective Feb 14, 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 96-10-13](https://openairdocs.org/ad/96-10-13): Bulkhead Assembly Inspection · Piper PA-31T, PA-31T1, PA-31T2 and 1 more. Effective Jun 27, 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 94-06-04](https://openairdocs.org/ad/94-06-04): Mask Regulators · Airbus A320-111, A320-211, A320-212 and 19 more. Effective May 23, 1994
- [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 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 85-05-01](https://openairdocs.org/ad/85-05-01): Inspection of F.S. 332.0 Bulkhead · Piper PA-31P. Effective Mar 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 82-11-04](https://openairdocs.org/ad/82-11-04): Emergency Exit Window Modification · Piper PA-31T, PA-31T1 and PA-31T2. Effective Jun 3, 1982
- [AD 81-23-06](https://openairdocs.org/ad/81-23-06): Flap Track Structure · Piper PA-31P, PA-31T and PA-31T1. Effective Nov 16, 1981
- [AD 81-01-01](https://openairdocs.org/ad/81-01-01): Propeller Deice Relay · Piper PA-31T and PA-31T1. Effective Feb 27, 1981
- [AD 80-25-05](https://openairdocs.org/ad/80-25-05): Voltage Regulator Modification · Piper PA-31T and PA-31T1. Effective Feb 12, 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 80-14-08](https://openairdocs.org/ad/80-14-08): Airplane Flight Manual Revision · Piper PA-31T. Effective Jul 7, 1980
- [AD 80-01-08](https://openairdocs.org/ad/80-01-08): Oil Cooler Inlet Hose Assembly · Piper PA-31T and PA-31T1. Effective Jan 14, 1980
- [AD 79-19-09](https://openairdocs.org/ad/79-19-09): Electroluminescent Panel Inverters · Piper PA-31T and PA-31T1. Effective Sep 25, 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 78-02-01](https://openairdocs.org/ad/78-02-01): Main Landing Gear · Piper PA-31T and PA-31T1. Effective May 9, 1979

All 71: https://openairdocs.org/tcds/A8EA/ads.md

## Registered aircraft by registry model (OpenAirDocs)

- [Piper PA-31T](https://openairdocs.org/model/piper-pa-31t): 87 aircraft (registry code 7103124)
- [Piper PA-31T1](https://openairdocs.org/model/piper-pa-31t1): 64 aircraft (registry code 7103126)
- [Piper PA-31P](https://openairdocs.org/model/piper-pa-31p): 40 aircraft (registry codes 7103120, 7103144)
- [Piper PA 31P 350](https://openairdocs.org/model/piper-pa-31p-350): 25 aircraft (registry code 7103111)
- [Piper PA-31T2](https://openairdocs.org/model/piper-pa-31t2): 24 aircraft (registry code 7103127)
- [Piper PA-31T3](https://openairdocs.org/model/piper-pa-31t3): 2 aircraft (registry code 7103128)

## STCs approved under this data sheet (318, first 50)

- [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 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 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 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 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 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 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 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 SA11137SC](https://openairdocs.org/stc/SA11137SC): Installation of Plane-Power ALT-FLX alternator. Hartzell Engine Technologies, LLC
- [STC SA00843WI](https://openairdocs.org/stc/SA00843WI): Installation of Concorde Battery Corporation (VRSLA) Valve Regulated Sealed Lead Acid Battery. Aero-Mach Wilco LLC
- [STC SA284GL](https://openairdocs.org/stc/SA284GL): Install Cleveland Conversion Kit P/N 199-83. Kaman Corporation Aircraft Wheel and Brake LLC
- [STC SA599GL](https://openairdocs.org/stc/SA599GL): Installation of Cleveland Wheel & Brake conversion kit No. 199-111.. 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 SA02203AK](https://openairdocs.org/stc/SA02203AK): Installation of FlightLogic Synthetic Vision Electronic Flight Information System (EFIS-SV).. Genesys Aerosystems 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 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 SA02265SE](https://openairdocs.org/stc/SA02265SE): Installation of a camera housing. Airborne Sensor LLC
- [STC ST01930LA](https://openairdocs.org/stc/ST01930LA): Installation of Sandel Avionics SN4500 Electronic Horizontal Situation Indicator (EHSI). Sandel Avionics LLC
- [STC SA02426AK](https://openairdocs.org/stc/SA02426AK): Approval of the FreeFlight FDL-978-TX ADS-B system installed. FreeFlight Systems
- [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 SA1405CE](https://openairdocs.org/stc/SA1405CE): Install King KFC-250 autopilot/flight director.. 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 SA1188CE](https://openairdocs.org/stc/SA1188CE): Intallation of King KFC 300 automatic flight control system.. 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 SA1566CE-D](https://openairdocs.org/stc/SA1566CE-D): Installation of King KFC 250A, two axis (third axis optional) flight control system with 3-inch or 4-inch instruments and optional altitude preselect or manual electric trim only.. Honeywell International Inc
- [STC SA4143WE](https://openairdocs.org/stc/SA4143WE): Installation of Sperry SPZ-200A automatic flight control system.. Honeywell International Inc
- [STC SA1558CE-D](https://openairdocs.org/stc/SA1558CE-D): Installation of King KFC-300 automatic flight control system.. Honeywell International Inc
- [STC SA1773CE-D](https://openairdocs.org/stc/SA1773CE-D): Installation of King KFC 250 3-axis Flight Control System with 3-inch or 4-inch indicators and optional Altitude Preselect.. Honeywell International 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 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
- [STC SA00560CH](https://openairdocs.org/stc/SA00560CH): Install air ambulance conversion.. Spectrum Aeromed LLC dba Spectrum Aeromed
- [STC SA00744DE](https://openairdocs.org/stc/SA00744DE): Installation of the Automatic Dependent Surveillance  Broadcast (ADS-B) Out Equipment using a Trig Avionics TT31 Transponder and an approved position sensor. Peregrine
- [STC SA00765DE](https://openairdocs.org/stc/SA00765DE): Installation of Automatic Dependent Surveillance  Broadcast (ADS-B) Out functionality using the BendixKing KT74 Transponder and qualified position sensor. Peregrine
- [STC SA04165NY](https://openairdocs.org/stc/SA04165NY): Installation of Latitude Technologies Skynode S200 Satcom system must be performed. Latitude Technologies Corporation
- [STC SA02153LA-D PAGE 2](https://openairdocs.org/stc/SA02153LA-D%20PAGE%202): Installation of Garmin G600 Primary Flight Display (PFD) and Multifunction Display (MFD) System. Garmin International Inc.
- [STC SA00764SE](https://openairdocs.org/stc/SA00764SE): Installation of vortex generators on wing and vertical stabilizer, and strakes on inboard and outboard sides of nacelles.. BLR Aerospace LLC.
- [STC SA02119AK](https://openairdocs.org/stc/SA02119AK): Installation of damage protection plates to inboard, lower side of flaps.. Hageland Aviation Services, Inc
- [STC SA02013CH](https://openairdocs.org/stc/SA02013CH): Installation of Avidyne Corporation Traffic Advisory System (TAS). Avidyne Corporation

All 318: https://openairdocs.org/tcds/A8EA/stcs.md

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