# TCDS A1EA: Piper Aircraft Inc.

- Type: Type certificate data sheet
- Status: Current
- Holder: Piper Aircraft Inc.
- Revision: 18
- Revised: June 9, 2011
- Product: Aircraft, Small Airplane
- Certification basis: Part 3, Part 23
- Registered aircraft: 960, by the registry models matched to it (OpenAirDocs)
- Data sheet PDF: https://openairdocs.org/files/sha256/07/a0/07a04b7f631b782411ca5c2fe2f544657fd277cf2426badfd571c857e29d330b
- FAA DRS: https://drs.faa.gov/browse/excelExternalWindow/50884682A9399A88862578AB0054C481.0001
- Page: https://openairdocs.org/tcds/A1EA

## Models (3)

As the data sheet lists them.

- PA-40
- PA-30 (Twin Comanche)
- PA-39

## 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 
Revision No. 18 11 15 11 15 18 15 15 16 
 
DEPARTMENT OF TRANSPORTATION 
FEDERAL AVIATION ADMINISTRATION 
 
A1EA 
Revision 18 
Piper Aircraft, Inc 
 
PA-30 
PA-39 
PA-40 
 
June 9, 2011  
 
TYPE CERTIFICATE DATA SHEET NO. A1EA 
 
This data sheet, which is a part of Type Certificate No. A1EA, prescribes conditions and limitations under which the product, for 
which the type certificate was issued, meets the airworthiness requirements of the Civil Air Regulations and 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, In c transferred TC A1EA to Piper Aircraft, Inc on August 7, 
2006. 
 
I - Model PA-30, 4 PCLM (Normal Category), Approved February 5, 1963, or 6 PCLM (Normal Category), Approved 
May 28, 1965  (See NOTE 4 for 6 PCLM Limitations). 
 
Engines 2  Lycoming IO-320-B1A 
 See NOTE 5 for optional engines. 
 
Fuel 91/96 minimum grade aviation gasoline 
 
Engine Limits For all operations 2700 r.p.m. (160 hp) 
 (See Maneuvers under Limita tions Section of AFM) 
 
Propellers and Propeller Limits 2  Hartzell, Hub Model HC-E2YL-2, -2A, -2B, -2BS, -2C, -2D or -2BSF 
  (-2BS and -2BSF not to be interm ixed with other propellers listed) 
 Blades Model 7663-4 or F7663-4 * 
 Pitch: High 78°, Low  12° at 30 in. station. 
 Diameter:  Not over 72 inches, not under 70 inches. 
 No further reduction permitted. 
 
 * Blades prefixed by an "F" may be used only on propeller hubs  
    suffixed by an "F". 
 
Governors  2  Hartzell hydraulic governors, Model F-6, F-6-3, F-6-3S or F-6-3A 
 
Airspeed Limits V ne Never Exceed 230 mph (200 Knots) 
(CAS) V no Maximum Structural Cruise 194 mph (168 Knots) 
 V p Maneuvering (3600 lb.) 162 mph (141 Knots) 
 V fe Flaps Extended 125 mph (108 Knots) 
 V lo Landing Gear Operating 150 mph (130 Knots) 
 V le Landing Gear Extended 150 mph (130 Knots) 
 V mc Minimum Control Speed   90 mph (  78 Knots)

A1EA Page 2 of 9 
 
Center of Gravity (C.G.) Range 
(Gear Extended) 
80 85 90
2450
3200
3600
81
83
86.5
92
Aircraft
Weight
(lb.)
C.G. Location
(inches aft of datum)
 
C. G. Range (+86.5)  to  (+92)  at 3600  lb.  
 (+83.0)  to  (+92)  at 3200 lb. 
 (+81.0)  to  (+92)  at 2450 lb. or less 
 Straight line variation between points given. 
 Moment change due to retracting landing gear (770 in.- lb.) 
 
Empty Weight C. G. Range None 
 
Datum 79 inch ahead of the wing leading edge at Wing Station 97. 
 (First leading edge skin lap outboard of engine nacelle) 
 
Leveling Means Level from two rivnuts located right side above baggage door (Serial Nos. 30-1 through 
30-852 and 30-854 through 30-901.  On Serial Nos. 30-853 and 30-902 and up still on 
right side fuselage, but baggage door moved to left side of fuselage). 
 
Maximum Weight 3600 lb. 
 
Number of Seats Serial Nos. 30-1 through 30-589:  
  4  (2 at +85, 2 at +118.5) 
 Serial Nos. 30-590 through 30-852 and 30-854 through 30-901: 
  4  (2 at +85, 2 at +120.5) 
 Serial Nos. 30-853 and 30-902 and up:  
  6  (2 at +85, 2 at +120.5, 2 at +148) 
 See NOTE 4 for weight limitations at Sta. 148. 
 
Maximum Baggage Serial Nos. 30-1 through 30-852 and 30-854 through 30-901: 
  200 lb. (Rear compartment) (+142) 
 Serial Nos. 30-853 and 30-902 and up: 
  250 lb. (Rear compartment) (+142) 
 See NOTE 4 for weight limitations. 
 
Fuel Capacity 90 gallons: 60 gallons (2 wing tanks) (+90) 
    30 gallons (2 wing tanks) (+95) 
 See NOTE 1 for unusable fuel data. 
 
Oil Capacity 4 gallons (2 gallons each engine -2 quarts unusable each engine) (+51)

A1EA Page 3 of 9 
 
Control Surface  Ailerons 19° Up 15° Down 
Movements Stabilator (T.E.) 15½° Up   4½° Down 
 Rudder 27° Right 27° Left 
 Anti-Servo Tab   9° Up   9° Down 
    (with stabilator in neutral) 
 Flaps   27° Down 
 
  When a PA-30 has been modified in accordance with Piper Service Letter  
  No. 558, the following control travel apply: 
 
 Ailerons 19°  (+ 1°) Up 15  (± 1°) Down 
 
 NOTE:  Neutral is rigged as follows:  The angle between the airplane leveling lugs and 
the upper surface of the aileron, parallel with and next to the rib rivets, 6½ inches from 
the inboard end of the aileron is 12°. 
 
 Stabilator (T.E.) 8½° (+ 0°, -1°) Up 4½° (± 1°) Down 
 Rudder 27° (+ 1°, -0°) Right 25° (+ 1°, -0°) Left 
 
  NOTE:  With rudder pedals aligned laterally rig rudder 1° right of the airplane centerline 
line, then rig to the above limits in normal manner. 
 
 Stabilator Trim Tab 9° (± 1°) Up 9° (± 1°) Down 
 Flaps  27° (± 1°) Down 
 
Serial Numbers Eligible 30-1 through 30-2000 
 
II - Model PA-39, 6 PCLM (Normal Category), Approved December 3, 1969. 
 
Engines 1 Lycoming IO-320-B1A (Left) 
 1 Lycoming LIO-320-B1A (Right) 
 
Fuel 100/130 minimum grade aviation gasoline 
 
Engine Limits For all operations, 2700 r.p.m.  (160 hp) 
 (See Maneuvers under Limita tions Section of AFM) 
 
Propellers and Propeller Limits 1 Hartzell , Hub Model HC-E2YL-2B or -2BF  (Left) 
 1 Hartzell, Hub Model HC-E2YL-2BL or -2BLF  (Right) 
  or 
 1 Hartzell, Hub Model HC-E2YL-2BS or -2BSF * (Left) 
 1 Hartzell , Hub Model HC-E2YL-2BLS or -2BLSF * (Right) 
 
 Blades Model  7663-4 or F7663-4  **  (Left) 
    J7663-4 or FJ7663-4 **  (Right) 
 Pitch Setting:   High 78°, Low 12° at 30 inch station. 
 Diameter:  Not over 72 inches, not under 70 inches 
No further reduction permitted. 
 
 * The -2BS, -2BSF, -2BLS and -2BLSF propelle rs not to be intermixed with other  
 propellers listed. 
 ** Blades prefixed by an "F" may be us ed only on propeller hubs suffixed by an "F". 
 
Governors 1 Hartzell hydraulic governor, Model F-6-3A (Left) 
 1 Hartzell hydraulic governor, Model F-6-3AL (Right)

A1EA Page 4 of 9 
 
Airspeed Limits V ne Never Exceed 230 mph (200 Knots) 
(CAS) V no Maximum Structural Cruise 194 mph (168 Knots) 
 V p Maneuvering (3600 lb.) 162 mph (141 Knots) 
 V fe Flaps Extended 125 mph (108 Knots) 
 V lo Landing Gear Operating 150 mph (130 Knots) 
 V le Landing Gear Extended 150 mph (130 Knots) 
 V mc Minimum Control Speed 80 mph   (69 Knots) 
 
C. G. Range (Gear Extended) (+86.5) to (+92) at 3600 lb. 
 (+83 0) to (+92) at 3200 lb. 
 (+82.0) to  (+92) at 2825 lb. or less 
 Straight line variation between points given. 
 Moment change due to retracting landing gear  (770 in -lb.) 
2825
3200
3600
80 85 90
82
8382
86.5
92
Aircraft Weight
(lb.)
C.G. Location
(inches aft of datum)
82
83
86.5 92
 
Empty Weight C. G. Range None 
  
Datum 79 inches ahead of the wing leading edge at Wing Station 97 
 (First leading edge skin lap outboard of engine nacelle.) 
 
Leveling Means Level from two rivnuts located right  side fuselage at window level 
 
Maximum Weight  3600 lb. 
  
Number of Seats 6 (2 at +85,  2 at +120.5,  2 at +148) 
 See NOTE 4 for Weight Limitations at Station 148. 
 
Maximum Baggage 250 lb. (Rear compartment) (+142) 
 See NOTE 4 for Weight Limitations. 
 
Fuel Capacity 90 gallons: 60 gallons (2 wing tanks)  (+90) 
    30 gallons (2 wing tanks)  (+95) 
 See NOTE 1 for unusable fuel data. 
 
Oil Capacity 4 gallons (2 gallons each engine -2  quarts unusable each engine)  (+51)

A1EA Page 5 of 9 
 
Control Surface Ailerons 19° ( 1°) Up 15° ( 1°) Down 
Movements Stabilator (T.E.) 15½° (+ 1, -1½°) Up 5½° (+1°, -0°) Down 
 Rudder 27° ( 1°) Right 27° ( 1°) Left 
 Anti-Servo Tab 9° ( 1°) Up 9° ( 1°) Down 
   (with stabilator in neutral) 
 Flaps   27° ( 1°) Down 
 
Serial Numbers Eligible 39-1 through 39-162 
 
 
III - Model PA-40, 4 PCLM (Normal Category), Approved July 18, 1974. 
 
Engines 1 Lycoming IO-320-B1A (Left) 
 1 Lycoming LIO-320-B1A (Right) 
 
Fuel 100/130 minimum grade aviation gasoline 
 
Engine Limits For all operations, 2700 r.p.m.  (160 hp) 
 (See Maneuvers under Limita tions Section of AFM) 
 
Propellers and Propeller Limits 1 Hartzell, Hub Model HC-E2YL-2BSF or HC-E2YL-2BS (Left) 
 1 Hartzell, Hub Model HC-E2YL- 2BLSF or HC-E2YL-2BLS (Right) 
 Blades Model F7663-4R or 7663-4 (Left) 
    FJ7663-4R or J7663-4 (Right) 
 Pitch Setting:   High 77°to 76°, Low 12° at 30 inch station. 
 Diameter:  Not over 72 inches, not under 70 inches 
 No further reduction permitted. 
 
Governors 1 Hartzell hydraulic governor, Model F-6-3A (Left) 
 1 Hartzell hydraulic governor, Model F-6-3AL (Right) 
 
Airspeed Limits V ne Never Exceed  * 230 mph (200 Knots) 
(CAS) V no Maximum Structural Cruise 194 mph (168 Knots) 
 V p Maneuvering (3800 lb.) 166 mph (145 Knots) 
 V fe Flaps Extended 125 mph (108 Knots) 
 V lo Landing Gear Operating 150 mph (130 Knots) 
 V le Landing Gear Extended 170 mph (148 Knots) 
 V mc Minimum Control Speed 80 mph (69 Knots) 
 
* Above 18,000 feet reduce Vne 2 mph per every 1000 feet.

A1EA Page 6 of 9 
 
C. G. Range (Gear Extended) (+86.0) to (+92) at 3800 lb. 
 (+82.0) to  (+92) at 2825 lb. or less 
 Straight line variation between points given. 
 Moment change due to retracting landing gear  (770 in. -lb.) 
 
2825
3200
80 85 90
82
86
92
Aircraft
Weight
C.G. Location
(inches aft of datum)
95
(Lb.)
3800
82
86 92
 
 
Empty Weight C.G. Range None 
 
Datum 79 inches ahead of the wing leading edge at Wing Station 143. 
 (First leading edge skin lap outboard of fuel filler neck.) 
 Level from two rivnuts located right side fuselage at window level. 
 
Maximum Weight 3800 lb. 
 
Number of Seats 4 (2 at +85,  2 at +120.5) 
 See NOTE 4 for Weight Limitations. 
 
Fuel Capacity 120 gallons (2 wing tanks)  (+92.5) 
 See NOTE 1 for unusable fuel data. 
 
Oil Capacity 14 quarts  (7 quarts each engine -2  quarts unusable each engine)  (+51) 
 
Control Surface Ailerons 19° ( 1°) Up 15° ( 1°) Down 
Movements Stabilator (T.E.) 12° ( 1°) Up 8° ( 1°) Down 
 Rudder 27° ( 1°) Right 27° ( 1°) Left 
 Anti-Servo Tab 4½° ( .5°) Up 8° ( .5°) Down 
  (with stabilator in neutral) 
 Flaps 27° ( 1°) Down 
 
Serial Numbers Eligible 40-7400002 
 
DATA PERTINENT TO ALL MODELS 
Certification Basis CAR 3 effective May 15, 1956, through Ame ndment 3-6 effective September 13, 1961, 
and Par. 3.705(a) of Amendment 3-7 effective May 3, 1962.  Also, FAR 23.1557(c)(1) of 
Amendment 23-7 effective September 14, 1969. 
 
 In addition, for Model PA-40, FAR 23. 1401 of Amendment 23-11 effective August 11, 
1971, and FAR 23.145, 23.161 and 23.175 of Amendment 23-14 effective December 20, 
1973.

A1EA Page 7 of 9 
 
Certification Basis (cont.) Type Certificate No. A1EA issued Februa ry 5, 1963, and reissued December 3, 1969 to 
include Model PA-39 under Delegation Option Authorization of Federal Aviation 
Regulations Part 21. 
 Date of Application for Type Certificate March 1, 1962. 
 
Production Basis Approved for manufacture of spare part s 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. (a) Stall warning indicator installa tion in accordance with Piper Dwg. 23945 and  
   23700 for Model PA-30, Serial Nos. 30-1 through 30-1716 and 30-1718  
   through 30-1744. 
  (b) Stall warning indicator installa tion in accordance with Piper Dwg. 26658 and  
   26651 for Model PA-30, Serial Nos. 30-1717 and 30-1745 through 30-2000. 
  (c) Stall warning indicator installa tion in accordance with Piper Dwg. 26651 for  
   Model PA-39, Serial Nos. 39-1 through 39-162. 
 
 2. (a) FAA-DOA approved Airplane Fli ght Manual Report 1269 for Model PA-30,  
   Serial Nos. 30-1 through 30-1716 and 30-1718 through 30-1744, dated  
   February 5, 1963, reissued N ovember 15, 1969, and FAA-DOA approved  
   Flight Manual Supplements. 
  (b) FAA-DOA approved Airplane Flight  Manual Report 1515 for Model PA-30,  
   Serial Nos. 30-1717 and 30-1745 th rough 3-2000, dated February 5, 1963, 
   reissued November 15, 1969 a nd FAA-DOA approved Flight Manual  
   Supplements. 
  (c) FAA-DOA approved Airplane Flight  Manual Report 1605 for Model PA-39,  
   Serial No. 39-1 through 39-162, dated November 28, 1969 and FAA-DOA  
   approved Flight Manual Supplements. 
  (d) FAA-DOA approved Airplane Flight  Manual Report 1840 for Model PA-40,  
   Serial No. 40-7400002, dated July 18, 1974, and FAA-DOA approved Flight  
   Manual Supplements. 
 
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. 
 
  The certificated empty weight and corresponding cente r of gravity location must include for PA-30 and 
PA-39 unusable fuel of 36 lb. at (+90) and 2 quarts unusable oil each engine at (+51), for PA-40 unusable 
fuel of 31.2 lb.  at (+90) and 2 quarts unusable to each engine at (+51). 
 
NOTE 2.  All placards required in the approved airplane  flight manual and approved airplane flight manual 
supplements must be installed in the appropriate location. 
 
  The following placards must be displayed: 
  
 1.  On pedestal in full view of the pilot fo r Model PA-30, Serial Nos. 30-1 through 30-1716 and  
   30-1718 through 30-1744. 
  On instrument panel for Model PA-30,  Serial Nos. 30-1717 and 30-1745 through 30-2000; 
  Model PA-39, Serial Nos. 39-1 through 39-162; and Model PA-40, Serial No. 40-7400002. 
 
  "THIS AIRPLANE MUST BE OPERATED  AS A NORMAL CATEGORY AIRPLANE IN 
COMPLIANCE WITH THE AIRPLANE FLIGHT MANUAL.  ACROBATICS MANEUVERS 
(INCLUDING SPINS) PROHIBITED"

A1EA Page 8 of 9 
NOTE 2.  2. In view of the pilot on aircraft equipped with  alternate instrument static source in accordance with Piper 
Drawing No. 25237 for Model PA-30 of Piper Drawing No. 26722 for Models PA-30, PA-39 and 
PA-40. 
 
  (a) "INSTRUCTIONS FOR USE OF ALTERNATE STATIC SOURCE" 
 
   (1) IN CASE OF STATIC PRESSU RE TUBE MALFUNCTION DUE TO ICE OR 
OTHER OBSTRUCTIONS CLOSE WINDOW AND ACTUATE ALTERNATE 
STATIC SOURCE VALVE. 
 
   (2) THE FOLLOWING AIRSPEEDS APPLY WHEN ALTERNATE STATIC 
SOURCE IS USED ON MODELS PA-30 AND PA-39. 
 
   INDICATOR READS     ACTUAL  
   104 MPH IAS  100 MPH CAS 
   140 MPH IAS 130 MPH CAS 
   163 MPH IAS 150 MPH CAS 
   185 MPH IAS 170 MPH CAS 
 
   (3) THE FOLLOWING AIRSPEEDS APPLY WHEN ALTERNATE STATIC 
SOURCE IS USED ON MODEL PA-40. 
 
   INDICATOR READS     ACTUAL  
   100 MPH IAS   96 MPH CAS 
   120 MPH IAS 114 MPH CAS 
   160 MPH IAS 151 MPH CAS 
   200 MPH IAS 187 MPH CAS 
 
  (b) (1) On instrument panel above alternat e static source actuating valve on Model PA-30, 
Serial Nos. 30-1 through 30-1716 and 30-1718 through 30-1744: 
    "         ALTERNATE STATIC SOURCE PULL AFT TO OPEN" 
 
   (2) On left side control quadrant on Model PA-30, Serial Nos. 30-1717 and 30-1745 
through 30-2000;  Model PA-39, Serial Nos. 39-1 through 39-162;  and Model     
PA-40, Serial No. 40-7400002. 
 
  "ALTERNATE STATIC ON 
                  OFF" 
 
NOTE 3.  Balance weights are required on stabilato r and rudder to provide the following moments: 
  
  (a.) Model PA-30, Serial Nos. 30-1 thr ough 30-852, 30-854 through 30-901, 30-1717, and 30-1745 through 
30-2000;  and Model PA-39, Serial Nos. 39-1 through 39-162: 
   Stabilator  49 in. - lb. (+0, -3  in. - lb.) (trailing edge heavy) 
   Rudder  13.5 in. - lb. (  1 in. - lb.) (trailing  edge heavy) 
 
  (b.) Model PA-30, Serial Nos. 30- 853, 30-902 through 30-1716, and 30-1718 through 30-1744: 
   Stabilator  24.6 in. - lb. (  4 in. - lb.) (leading edge heavy) 
   Rudder  13.5 in. -lb. (  1 in. - lb.) (trailing edge heavy) 
 
  (c.) Model PA-40, Serial No. 40-7400002: 
   Stabilator  3 in. - lb.  (  3 in. - lb.) (leading edge heavy) 
   Rudder  13.5 in.- lb. (-0, +3 in. - lb.) (trailing edge heavy) 
   Aileron  1 in.- lb.  (  1 in.- lb.) (leading edge heavy) 
 
NOTE 4. Maximum baggage a nd/or passenger weight 250 lb. in baggage area including seats.  See weight and 
balance.

A1EA Page 9 of 9 
NOTE 5. Optional engines eligible for installation and applicable limitations. 
  Engines  1 Lycoming IO-320-C1A  (Left) 
   1 Lycoming LIO-320-C1A  (Right) 
 
 Fuel  100/130 minimum grade aviation gasoline 
 
 Engine Limits  For all operations,  2700 r.p.m.     (160 hp) 
  (See Maneuvers under Lim itations Section of AFM) 
 
 Propellers and  1 Hartzell, Hub Model HC-E2YL-2, -2A, -2B, -2C, -2D, -2BS or -2BSF  (Left)    * 
 Propeller Limits  1 Hartzell, Hub Model HC-E2YL-2BL, -2BLS, -2BL F, or -2BLSF           (Right)   * 
  Blades Model 7663-4 or F7663-4     (Left)   ** 
   J7663-4 or FJ7663-4  (Right)  ** 
 
  *   The -2BS, -2BSF, -2BLS, and -2BL SF propellers not to be intermixed with  
       other propellers listed. 
  ** Blades prefixed by an "F" may be us ed only on propeller hubs suffixed by an "F". 
 
 Governors  1 Hartzell hydraulic governor, Model F-6, F-6-3, F-6-3S, or F-6-3A    (Left) 
  1 Hartzell hydraulic governor, Model F-6-3AL      (Right) 
 
 Airspeed Limits  V mc       Minimum Control Speed        80 mph      (69 Knots) 
 (CAS) 
 
 C.G. Range  
 (gear extended)  (+82.0)  to  (+92.0)  at 2825 lb. or less 
 
 Equipment  (a) FAA-DOA approved Airplane Flight  Manual Report 1269 for Model PA-30,  
   Serial Nos. 30-1 through 30-1716 and 30-1718 through 30-1744, dated  
   February 5, 1963, reissued Novemb er 15, 1969 and FAA-DOA approved Flight  
   Manual Supplements. 
 
  (b) FAA-DOA approved Airplane Flight  Manual Report 1515 for Model PA-30,  
   Serial Nos. 30-1717, 30-1745 through 30-2000,  dated February 5, 1963, reissued  
   November 15, 1969 and FAA-DOA a pproved Flight Manual Supplements. 
 
     The use of the optional engine installation is permitted only when installed in  
     accordance with Piper Kit No. 760 368. 
 
NOTE 6.  Piper PA-30 Airflow  Modification Kits for Model PA-30, Serial Nos. 30-1 through 30-2000: 
 
 When Airflow Modification Kit, Part Number  760 409, is installed, the FAA-DOA approved  
  airflow modification kit data are described in Piper Service Letter 558, dated July 1, 1970. 
 When Counter-Rotating Powerplant Conversion Kit 760 368 is installed, the FAA-DOA approved  
  counter-rotating powerplant conversion data are described in Piper Service Letter 552, dated  
  May 1, 1970.  Airflow Modification 760 409 must be  removed, if installed.  See Piper Service  
  Letter 552, for new airflow kit modifica tion requirements when counter rotating  
  powerplant is installed. 
  When Wiggins Supplemental Type Certificate SA233EA, Reservoir Type Pneumatic Wing De-Icing  
   Kit is installed, the FAA-DOA approved Pipe r Air Flow Modification Kit  760 564 data are  
   described in Piper Service Letter 558, dated July 1, 1970, Addendum No. 1 dated August 20, 1971,  
   and in "Rubber Wing Flow Strip Insta llation" Instructions for Piper Kit 760 563. 
 When Wiggins Supplemental Type Certificate SA 233EA, Reservoir Type Pneumatic Wing De-Icing  
  Kit, is installed with a "Counter-Rotating Po werplant Modification Propeller and Wing De-Icing  
  Equipment" Modification, the FAA-DOA approved Piper Air Flow Modification Kit 760 562 data are  
  described in Piper Service Letter 552, dated May 1, 1970, Addendum No. 2, dated August 20, 1971. 
 
 
...END...
```

## ADs (42, in force first)

- [AD 2024-14-03](https://openairdocs.org/ad/2024-14-03): Autopilot System · Garmin GFC 500 Autopilot (STC SA01866WI). Effective Aug 20, 2024
- [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 2017-15-05](https://openairdocs.org/ad/2017-15-05): Air Conditioning · Piper PA-23, PA-23-160, PA-23-235 and 3 more. Effective Aug 28, 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 2006-12-07](https://openairdocs.org/ad/2006-12-07): ECi cylinder assemblies · Aerostar AEIO-320-D1B, AEIO-320-D2B, AEIO-320-E1A and 386 more. Effective Jul 11, 2006
- [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 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 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 97-01-01 R1](https://openairdocs.org/ad/97-01-01-R1): Main Gear Sidebrace Stud · Piper PA-24, PA-24-250, PA-24-260 and 10 more. Effective Dec 8, 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 94-13-10](https://openairdocs.org/ad/94-13-10): Stabilizer Torque Tube · Piper PA-24, PA-24-250, PA-24-260 and 3 more. Effective Aug 12, 1994
- [AD 83-19-03](https://openairdocs.org/ad/83-19-03): Lower Spar Cap Inspection · Piper PA-24, PA-24-250, PA-24-260 and 3 more. Effective Sep 30, 1983
- [AD 83-10-01](https://openairdocs.org/ad/83-10-01): Water and Fuel System Inspection · Piper PA-24-400, PA-30 and PA-39. Effective Jun 15, 1983
- [AD 82-23-01 R1](https://openairdocs.org/ad/82-23-01-R1): Placard Near Flap Actuator · Leading edge cuffs, stall fences, stall strips drooped… (Sierra Industries STC SA2312WE or SA2495WE). Effective Apr 7, 1983
- [AD 81-19-04](https://openairdocs.org/ad/81-19-04): Hose Assembly · Rajay Hose Assemblies, 500A, 500B and 87 more. Effective Sep 17, 1981
- [AD 79-20-10](https://openairdocs.org/ad/79-20-10): Piper Kit 763 893 · Piper PA-24, PA-24-250, PA-24-260 and 3 more. Effective Oct 4, 1979
- [AD 79-12-08](https://openairdocs.org/ad/79-12-08): Fuel Selector Valves · Piper PA-24-400, PA-30 and PA-39. Effective Jun 19, 1979
- [AD 78-12-07](https://openairdocs.org/ad/78-12-07): Fuel Selector Valve · Piper PA-30 and PA-39. Effective Jun 19, 1978
- [AD 77-13-21](https://openairdocs.org/ad/77-13-21): Prevent Landing Gear Collapse · Piper PA-24, PA-24-250, PA-24-260 and 3 more. Effective Dec 16, 1977
- [AD 69-24-04](https://openairdocs.org/ad/69-24-04): Minimum Control Speed · Piper PA-30. Effective Aug 5, 1977
- [AD 77-09-10](https://openairdocs.org/ad/77-09-10): Electric Trim Switch · Piper PA-23-250, PA-23-250 (Navy UO-1), PA-24-260 and 6 more. Effective May 12, 1977
- [AD 77-08-01](https://openairdocs.org/ad/77-08-01): Aileron Spar Cracks · Piper PA-24, PA-24-250, PA-24-260 and 3 more. Effective Apr 18, 1977
- [AD 76-18-05](https://openairdocs.org/ad/76-18-05): Forward Fin Attachment · Piper PA-30 and PA-39. Effective Sep 10, 1976
- [AD 75-27-08](https://openairdocs.org/ad/75-27-08): Torque Tube Bearing Fittings · Piper PA-24, PA-24-250, PA-24-260 and 3 more. Effective Jun 3, 1976
- [AD 74-13-03](https://openairdocs.org/ad/74-13-03): Stabilator Attach Bolts · Piper PA-23-235, PA-23-250 (Navy UO-1), PA-24 and 5 more. Effective Apr 30, 1976
- [AD 74-16-08](https://openairdocs.org/ad/74-16-08): Aft Bulkhead Assembly · Piper PA-30 and PA-39. Effective Aug 9, 1974
- [AD 70-22-05](https://openairdocs.org/ad/70-22-05): Electrical System Modifications · Piper PA-23-250 (Navy UO-1), PA-30, PA-31 and 1 more. Effective Nov 30, 1971
- [AD 71-12-05](https://openairdocs.org/ad/71-12-05): Electric Trim Switch Modification · Piper PA-23-250 (Navy UO-1), PA-24-260, PA-30 and 5 more. Effective Jun 16, 1971
- [AD 70-22-02](https://openairdocs.org/ad/70-22-02): Fuel Selector Valves · Piper PA-28-235, PA-30, PA-32-260 and 3 more. Effective Nov 4, 1970
- [AD 70-15-17](https://openairdocs.org/ad/70-15-17): Operating Limitation Placard · Piper PA-30. Effective Aug 4, 1970
- [AD 67-19-05](https://openairdocs.org/ad/67-19-05): Oxygen Cylinder Mounting Channels · Piper PA-30. Effective Jun 7, 1967
- [AD 66-28-06](https://openairdocs.org/ad/66-28-06): Stabilator System · Piper PA-30. Effective Nov 25, 1966
- [AD 66-18-04](https://openairdocs.org/ad/66-18-04): Baggage Door Latch · Piper PA-24-260 and PA-30. Effective Aug 10, 1966
- [AD 65-11-04](https://openairdocs.org/ad/65-11-04): Stabilator Control System · Piper PA-24-250, PA-24-260, PA-24-400 and 1 more. Effective May 15, 1965
- [AD 64-28-03](https://openairdocs.org/ad/64-28-03): Heavy Walled Torque Tube · Piper PA-30. Effective Dec 24, 1964
- [AD 64-21-05](https://openairdocs.org/ad/64-21-05): Hartzell Propeller Governor · Piper PA-23-250 (Navy UO-1) and PA-30. Effective Sep 16, 1964
- [AD 64-16-06](https://openairdocs.org/ad/64-16-06): Nose Gear Retraction Tubes · Piper PA-30. Effective Aug 20, 1964
- [AD 64-09-05](https://openairdocs.org/ad/64-09-05): Induction System Alternate Air Doors · Piper PA-30. Effective Apr 29, 1964
- [AD 69-13-03](https://openairdocs.org/ad/69-13-03) (historical): Heater Exhaust Tube · Piper PA-23, PA-23-160, PA-23-235 and 3 more. Effective Dec 14, 1973

## Registered aircraft by registry model (OpenAirDocs)

- [Piper PA-30](https://openairdocs.org/model/piper-pa-30): 878 aircraft (registry code 7103002)
- [Piper PA-39](https://openairdocs.org/model/piper-pa-39): 82 aircraft (registry code 7103902)
- [Piper PA-40](https://openairdocs.org/model/piper-pa-40): 0 aircraft (registry code 7104002)

## STCs approved under this data sheet (358, 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 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 SA12406WI](https://openairdocs.org/stc/SA12406WI): Installation of a Garmin AXIS Flight Display System. Garmin International Inc.
- [STC SA04652CH](https://openairdocs.org/stc/SA04652CH): To allow use of 100R grade aviation fuel meeting Swift Fuel, LLC specification. Swift Fuels LLC
- [STC SA02636SE](https://openairdocs.org/stc/SA02636SE): Installation of Garmin GPS 175 Navigation System and GNX 375 Navigation System with ADS-B In/Out Transponder.. Garmin International Inc.
- [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 SA01866WI](https://openairdocs.org/stc/SA01866WI): Installation of Garmin GFC 500 Autopilot with Electronic Stability and Protection. Garmin International 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 SA00037WI](https://openairdocs.org/stc/SA00037WI): Installation of B & C Specialty Products BC100-1 battery.. B & C Specialty Products Inc
- [STC SA04378CH](https://openairdocs.org/stc/SA04378CH): Installation of an engine modified per STC SE04349CH. SureFly Partners Ltd.
- [STC SA01120SE](https://openairdocs.org/stc/SA01120SE): Installation of Door Steward.. Mountain View Aviation LLC
- [STC SA02386AK](https://openairdocs.org/stc/SA02386AK): Replacement of existing landing and/or taxi light reflector and bulbs with Light Emitting Diode (LED) lighting systems. AeroLED's Holding LLC
- [STC SA01757WI](https://openairdocs.org/stc/SA01757WI): To allow the use of UL91 or UL94 (minimum) grade aviation fuel. Swift Fuels LLC
- [STC SA04568CH](https://openairdocs.org/stc/SA04568CH): Installation of the uAvionix tailBeaconX, a tail mounted position light with integrated Automatic Dependent Surveillance - Broadcast (ADS-B) Out and 1090MHz Mode-S transponder functionality. uAvionix Corporation
- [STC 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 SA787WE](https://openairdocs.org/stc/SA787WE): Installation of turbosupercharged Lycoming IO-320-B1A, IO-320-C1A, LIO-320-B1A or LIO-320-C1A engines. TALCO Aviation
- [STC SA02019WI](https://openairdocs.org/stc/SA02019WI): Installation of the Trig Avionics TX56, TX56A, TX57, or TX57A VHF Nav-Com Radio.. Peregrine
- [STC SA04400NY](https://openairdocs.org/stc/SA04400NY): Installation of the Integrated Back-up Battery System (IBBS). TCW Technologies LLC
- [STC SA09766DS](https://openairdocs.org/stc/SA09766DS): Installation of an S-TEC 01326 Digital Flight Control System (DFCS). S-TEC Corporation
- [STC SA04192NY](https://openairdocs.org/stc/SA04192NY): KFD 900 Primary Flight Display System Additional Functions. Honeywell International Inc
- [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 SA00449AT](https://openairdocs.org/stc/SA00449AT): Installation of flap gap seals.. Whelen Aerospace Technologies
- [STC SA3105SO](https://openairdocs.org/stc/SA3105SO): Installation of 'speed spats' main landing gear fairings.. Whelen Aerospace Technologies
- [STC SA3282SO](https://openairdocs.org/stc/SA3282SO): Installation of flap bracket fairings.. Whelen Aerospace Technologies
- [STC SA3302SO](https://openairdocs.org/stc/SA3302SO): Installation of fiberglass nose bowl.. Whelen Aerospace Technologies
- [STC SA02987CH](https://openairdocs.org/stc/SA02987CH): Installation of the Electroair Electronic Ignition System. Electroair Acquisition Corporation
- [STC SA04586CH](https://openairdocs.org/stc/SA04586CH): Installation of Electroair Back Up Battery Panel System Control. Electroair Aquisition Corp.
- [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 SA2849WE](https://openairdocs.org/stc/SA2849WE): Installation of oxygen system.. Aerox Aviation Oxygen Systems LLC
- [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 SA01818WI](https://openairdocs.org/stc/SA01818WI): Installation of Garmin G5 Electronic Flight Instrument. Garmin International Inc.
- [STC SA09902AC](https://openairdocs.org/stc/SA09902AC): Installation of BendixKing KFD 900 Flight Display System. 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 SA10822SC](https://openairdocs.org/stc/SA10822SC): Installation of EFD1000 Primary Flight Display. Aspen Avionics Inc.
- [STC SA00401BO](https://openairdocs.org/stc/SA00401BO): Installation of a SkyTrax100B UAT receiver. Avidyne Corporation
- [STC SA4238WE](https://openairdocs.org/stc/SA4238WE): Installation of inflatable door seal.. TALCO Aviation Corp.
- [STC SA02426AK](https://openairdocs.org/stc/SA02426AK): Approval of the FreeFlight FDL-978-TX ADS-B system installed. FreeFlight Systems
- [STC SA01831WI](https://openairdocs.org/stc/SA01831WI): To allow the use of UL91 (minimum) grade aviation fuel. Petersen Aviation Inc
- [STC SA10236SC](https://openairdocs.org/stc/SA10236SC): Installation of a GDC 31 Roll Steering Converter. DAC International Inc

All 358: https://openairdocs.org/tcds/A1EA/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.