# TCDS 1A6: Piper Aircraft Inc.

- Type: Type certificate data sheet
- Status: Current
- Holder: Piper Aircraft Inc.
- Revision: 34
- Revised: August 7, 2006
- Product: Aircraft, Small Airplane
- Certification basis: CAR 3
- Registered aircraft: 2,943, by the registry models matched to it (OpenAirDocs)
- Data sheet PDF: https://openairdocs.org/files/sha256/b2/f0/b2f08cf7712fa136b1fa0f5e92e09ba5c078a777ff7e2d13a1311f43b9fd60cf
- FAA DRS: https://drs.faa.gov/browse/excelExternalWindow/FF3667736263DCEB862572090073CF58.0001
- Page: https://openairdocs.org/tcds/1A6

## Models (8)

As the data sheet lists them.

- PA-22S-135
- PA-22S-150
- PA-22-108 (Colt)
- PA-22-160
- PA-22-150
- PA-22
- PA-22S-160
- PA-22-135

## What the data sheet says

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

```text
DEPARTMENT OF TRANSPORTATION 
FEDERAL AVIATION ADMINISTRATION 
 
1A6 
Revision 34 
Piper Aircraft, Inc 
 
PA-22 
PA-22-108 
PA-22-135 
PA-22S-135 
PA-22-150 
PA-22S-150 
PA-22-160 
PA-22S-160 
 
August 7, 2006 
 
AIRCRAFT SPECIFICATION NO. 1A6 
 
Type Certificate Holder Piper Aircraft, Inc. 
 2926 Piper Drive 
 Vero Beach, Florida    32960 
 
Type Certificate Holder Record The New Piper Aircraft, Inc transferred TC 1A6 to Piper Aircraft, Inc on August 7, 2006. 
 
I - Model PA-22, 4 PCLM  (Normal Category Only),  Approved December 20, 1950 
 
Engine Ly coming O-290-D 
 
Fuel 80/87 minimum grade aviation gasoline 
 
Engine Limits For all operations, 2600 rpm (125 hp) 
 
Airspeed Limits Vne (never exceed) 158 mph (137 knots)
CAS Vno (maximum structural cruising) 126 mph (110 knots)
 Vp (maneuvering) 106 mph (92 knots)
 Vfe (flaps extended) 80 mph (70 knots)
 
C. G. Range (+17.5) to (+24.0) at 1800 lb. 
 (+10.0) to (+24.0) at 1380 lb. or less 
 Straight line variation between points given. 
 
Gross Weight
(l b.)
1000
1200
1400
1600
1800
81 0 12 14 16
Inches Aft of D
2000
18
atum
20 22 24 26
R
Li
ear
mit
Front
Limit
 
 
Empty Weight C. G. Range None 
 
Maximum Weight 1800 lb. 
 
Page No. 1 2 3 4 5 6 7 8 9 10 11 12 13 14 15
Rev. No. 34 33 33 33 33 33 33 33 33 33 33 33 33 33 33

1A6 Page 2 of 15 
 
Number Seats 4 (2 at +19.5 and 2 at +49) 
 
Maximum Baggage 50 lb. (+67) 
 
Fuel Capacity 36 gallons (2 Wing tanks at +24) 
 
Oil Capacity 2 gallons  (-29) 
 
Control Surface Movements Stabilizer 1° Up 6½° Down 
 Elevator 24° Up 12° Down 
 Aileron 15° Up 15° Down 
 Rudder 16° Right 16° Left 
 Flap 40° Down  
 
Serial Numbers Eligible 22-1 and up.   
 
Required Equipment In addition to the pertinent required basic equipment specified in CAR 3, the following 
items of equipment must be installed: 
 Items 1, 101, 201(a), 202, 205(a), 206, and 401(a). 
 
II.  Model PA-22-135, 4 PCLM  (Normal Category),  Approved May 5, 1952 
 
Engine Ly coming O-290-D2 
 
Fuel  80/87 minimum grade aviation gasoline 
 
Engine Limits For all operations, 2600 rpm (135 hp) 
 
Airspeed Limits Vne (never exceed) 158 mph (137 knots)
(CAS) Vno (maximum structural cruising) 126 mph (110 knots)
 Vp (maneuvering) 106 mph (92 knots)
 Vfe (flaps extended) 80 mph (70 knots)
 
C. G. Range (+17.5) to (+24.0) at 1950 lb. 
 (+10.0) to (+24.0) at 1380 lb. or less 
 Straight line variation between points given. 
 
Gross Weight
(l b.)
1000
1200
1400
1600
1800
81 0 12 14 16
Inches Aft of D
2000
18
atum
20 22 24 26
R
Li
ear
mit
Front
Limit
 
Empty Weight C. G. Range None 
 
Maximum Weight 1950 lb. 
 
Number of Seats 4 (2 at +21 and 2 at +49)

Page 3 of 15 1A6 
Maximum Baggage 50 lb. (+67) May be increased to 100 lb. provided: 
  (a) Baggage compartment placard is changed to "Maximum Baggage 100  
   Pounds." 
  (b) Airplane Flight Manual, Item 401(c), is available in the airplane. 
 
Fuel Capacity 36 gallons (2 wing tanks at +24).  See Item 104 for reserve tank. 
 
Oil Capacity 2 gallons  (-29) 
 
Control Surface Movements Stabilizer 1° Up 6½° Down 
 Elevator 24° Up 12° Down 
 Aileron 15° Up 15° Down 
 Rudder 16° Right 16° Left 
 Flap 40° Down  
 
Serial Numbers Eligible 22-534 and up. 
 
Required Equipment In addition to the pertinent required basic equipment specified in CAR 3, the following 
Items of equipment must be installed: 
 Items 1, 103, 201(a), 202, 205(a), 206, and 401(b). 
 
III - Model PA-22S-135, 3 PCSM  (Normal Category),  Approved May 14, 1954 
 
Engine Ly coming O-290-D2 
 
Fuel 80/87 minimum grade aviation gasoline 
 
Engine Limits For all operations, 2600 r.p.m. (135 hp) 
 
Airspeed Limits  Vne (never exceed) 140 mph (122 knots)
CAS Vno (maximum structural cruising) 117 mph (102 knots)
 Vp (maneuvering) 105 mph (91 knots)
 Vfe (flaps extended) 80 mph (70 knots)
 
C. G. Range (+14.0) to (+20.0) at 1850 lb. 
 (+10.0) to (+20.0) at 1300 lb. or less 
 Straight line variation between points given. 
 
Gross Weight
(l b.)
1000
1200
1400
1600
1800
81 0 12 14
Inches Aft
16
of Dat um
2000
18 20 22
Rear
Limit
Fro nt
Limit
 
Empty Weight C. G. Range None 
 
Maximum Weight 1850 lb. 
 
Number of Seats 4 (2 at +21 and 2 at +49) 
 
Maximum Baggage 50 lb. (+67)

1A6 Page 4 of 15 
 
Fuel Capacity 36 gallons (2 wing tanks at +24).  See Item 104 for reserve tank. 
 
Oil Capacity 2 gallons  (-29) 
 
Control Surface Movements Stabilizer 1° Up 6½° Down 
 Elevator 24° Up 12° Down 
 Aileron 15° Up 15° Down 
 Rudder 16° Right 16° Left 
 Flap 40° Down  
 
Serial Numbers Eligible 22-534 and up. 
 
Required Equipment In addition to the pertinent required basic equipment specified in CAR 3, the following 
Items of equipment must be installed: 
 Items 2, 103, 209, and 401(g). 
 
IV - Model PA-22-150,  4 PCLM  (Normal Category),  Approved September 3, 1954. 
 Model PA-22-150,  2 PCLM  (Utility Category),  Approved May 24, 1957  (See NOTE 3 for limitations) 
 
Engine Lycoming O-320-A2A or O-320-A2B  (Carburetor setting #10-3678-11,  
 #10-3678-12 or #10-3678-32)  (See Item 106 for optional engines) 
 
Fuel 80/87 minimum grade aviation gasoline 
 
Engine Limits For all operations, 2700 r.p.m. (150 hp) 
 
Airspeed Limits Vne (never exceed) 170 mph (148 knots)
CAS Vno (maximum structural cruising) 135 mph (117 knots)
 Vp (maneuvering) 112 mph (97 knots)
 Vfe (flaps extended) 95 mph (82 knots)
 
C. G. Range Normal Category: (+17.5) to (+23.0) at 2000 lb. 
  (+12.0) to (+23.0) at 1800 lb.  
  (+9.5) to (+23.0) at 1400 lb. or less 
 Utility Category:   (+13.5) at 1680 lb. 
  (+12.0) to (+13.5) at 1665 lb. 
  (+9.5) to (+13.5) at 1400 lb. or less 
 Straight line variation between points given. 
Gross Weight
(l b.)
100 0
120 0
140 0
160 0
180 0
81 0 12 14 16
Inches Aft
200 0
of Datum
18 20 22 24
2200
Utility
Categor y
Normal
Categor y
 
Empty Weight C. G. Range None 
 
Maximum Weight Normal Category: 2000 lb. 
 Utilit y Category: 1680 lb. 
 
Number of Seats 4 (2 at +21 and 2 at +49) 
 Rear seats not to be used when operating in the Utility Category. 
 
Maximum Baggage 100 lb. (+67)  (No baggage allowed when operating in the Utility Category)

Page 5 of 15 1A6 
Fuel Capacity 36 gallons (2 wing tanks at +24)  See Item 104 for reserve tank. 
 
Oil Capacity 2 gallons  (-29) 
 
Control Surface Movements Stabilizer 1° Up 6½° Down 
 Elevator 24° Up 12° Down 
 Aileron 15° Up 15° Down 
 Rudder 16° Right 16° Left 
 Flap 40° Down  
 
Serial Numbers Eligible 22-2378, 22-2425 and up (Normal Category).  See NOTE 3 for Utility Category. 
 
Required Equipment In addition to the pertinent required basic equipment specified in CAR 3, the following 
Items of equipment must be installed: 
 Normal Category:  Items 5, 103, 201(a), 202, 205(a), 206, and 401(h). 
 Normal and Utility Category:  Items 5, 103, 201(a), 202, 205(a), 206, 401(h), 
      401(r), and 407. 
 
V. - Model PA-22S-150,  3 PCSM  (Normal Category),  Approved September 3, 1954 
 
Engine O-320-A2A Lycoming   (Carburetor setting #10-3678-11, #10-3678-12) or 
 O-320-A2B  (Carburetor setting #10-3678-32)  (See Item 106 for optional engines) 
 
Fuel 80/87 minimum grade aviation gasoline 
 
Engine Limits For all operations, 2700 r.p.m.  (150 hp) 
 
Airspeed Limits  Vne (never exceed) 158 mph (137 knots)
CAS Vno (maximum structural cruising) 126 mph (109 knots)
 Vp (maneuvering) 111 mph (96 knots)
 Vfe (flaps extended) 80 mph (70 knots)
 
C. G. Range (+14.0) to (+20.0) at 1950 lb. 
 (+12.0) to (+20.0) at 1800 lb.  
 (+10.0) to (+20.0) at 1500 lb. or less 
 Straight line variation between points given. 
 
Gross Weight
(l b.)
1000
1200
1400
1600
1800
81 0 12 14
Inches Aft
16
of Dat um
2000
18 20 22
Rear
Limit
Fro nt
Limit
 
Empty Weight C. G. Range None 
 
Maximum Weight 1950 lb. 
 
Number Seats 4 (2 at +21 and 2 at +49) 
 
Maximum Baggage 100 lb. (+67) 
 
Fuel Capacity 36 gallons (2 wing tanks at +24).  See Item 104 for reserve tank.

1A6 Page 6 of 15 
 
Oil Capacity 2 gallons   (-29) 
 
Control Surface Movements Stabilizer 1° Up 6½° Down 
 Elevator 24° Up 12° Down 
 Aileron 15° Up 15° Down 
 Rudder 16° Right 16° Left 
 Flap 40° Down  
 
Serial Numbers Eligible 22-2378, 22-2425 and up. 
 
Required Equipment In addition to the pertinent required basic equipment specified in CAR 3, the following 
Items of equipment must be installed: 
 Items 5, 103, 209 and 401(i). 
 
VI - Model PA-22-160,  4 PCLM  (Normal Category),  Approved August 27, 1957 
 Model PA-22-160,  2 PCLM  (Utility Category),  Approved August 27, 1957  (See NOTE 3) 
 
Engine Lycoming O-320-B2A or O-320-B2B  (Carburetor setting #10-3678-11, #10-3678-12 or 
#10-3678-32). 
 
Fuel 91/96 minimum grade aviation gasoline 
 
Engine Limits For all operations, 2700 r.p.m. (160 hp) 
 
Airspeed Limits Vne (never exceed) 170 mph (148 knots)
(CAS) Vno (maximum structural cruising) 135 mph (117 knots)
 Vp (maneuvering) 112 mph (97 knots)
 Vfe (flaps extended) 95 mph (82 knots)
 
C. G. Range Normal Category: (+17.5) to (+23.0) at 2000 lb. 
  (+12.0) to (+23.0) at 1800 lb.  
  (+9.5) to (+23.0) at 1400 lb. or less 
 Utility Category:  (+13.5) at 1680 lb. 
  (+12.0) to (+13.5) at 1665 lb. 
  (+9.5) to (+13.5) at 1400 lb. or less 
 Straight line variation between points given. 
 
Gross Weight
(l b.)
1000
1200
1400
1600
1800
81 0 12 14 16
Inches Aft
2000
of Dat um
18 20 22 24
220 0
Utilit y
Category
Normal
Category
 
Empty Weight C. G. Range None 
 
Maximum Weight Normal Category: 2000 lb. 
 Utilit y Category: 1680 lb. 
 
Number of Seats 4 (2 at +21 and 2 at +49) 
 Rear seats not to be used when operating in the Utility Category. 
 
Maximum Baggage 100 lb.  (+67)  No baggage allowed when operating in the Utility Category.

Page 7 of 15 1A6 
Fuel Capacity 36 gallons (2 wing tanks at +24).  See Item 104 for reserve tank. 
 
Oil Capacity 2 gallons  (-29) 
 
Control Surface Movements Stabilizer 1° Up 6½ Down 
 Elevator 24° Up 12° Down 
 Aileron 15° Up 15° Down 
 Rudder 16° Right 16° Left 
 Flap 40° Down  
 
Serial Numbers Eligible 22-2378, 22-2425 and up (Normal Category).  See NOTE 3 for Utility Category. 
 
Required Equipment In addition to the pertinent required basic equipment specified in CAR 3, the following 
Items of equipment must be installed: 
 Normal Category:    Items 7, 103, 201(a), 202, 205(a), 206, and 401(s). 
 Normal and Utility Category:  Items 7, 103, 201(a), 202, 205(a), 206, 401(s), 
        401(t), and 407. 
 
VII - Model PA-22S-160,   3 PCSM  (Normal Category),   Approved October 25, 1957 
 
Engine Lycoming O-320-B2A  (Carburetor setting #10-3678-11, #10-3678-12) or  
 O-320-B2B  (Carburetor setting #10-3678-32). 
 
Fuel 91/96 minimum grade aviation gasoline 
 
Engine Limits For all operations, 2700 r.p.m.  (160 hp) 
 
Airspeed Limits Vne (never exceed) 158 mph (137 knots)
 Vno (maximum structural cruising) 126 mph (109 knots)
 Vp (maneuvering) 111 mph (96 knots)
 Vfe (flaps extended) 80 mph (70 knots)
 
C. G. Range (+14.0) to (+20.0) at 1950 lb. 
 (+12.0) to (+20.0) at 1800 lb.  
 (+10.0) to (+20.0) at 1500 lb. or less 
 Straight line variation between points given. 
 
Gross Weight
(l b.)
1000
1200
1400
1600
1800
81 0 12 14
Inches Aft
16
of Dat um
2000
18 20 22
Rear
Limit
Fro nt
Limit
 
Empty Weight C. G. Range None 
 
Maximum Weight 1950 lb. 
 
Number of Seats 4 (2 at +21 and 2 at +49) 
 
Maximum Baggage 100 lb.  (+67) 
 
Fuel Capacity 36 gallons (2 wing tanks at +24).  See Item 104 for reserve tank.

1A6 Page 8 of 15 
 
Oil Capacity 2 gallons  (-29) 
 
Control Surface Stabilizer 1° Up 6½° Down 
   Movements Elevator 24° Up 12° Down 
 Aileron 15° Up 15° Down 
 Rudder 16° Right 16° Left 
 Flap 40° Down  
 
Serial Numbers Eligible 22-2378, 22-2425 and up. 
 
Required Equipment In addition to the pertinent required basic equipment specified in CAR 3, the following 
Items of equipment must be installed: 
 Items 7, 103, 209, and 401(v). 
 
VIII - Model PA-22-108,  2 PCLM  (Normal and Utility Category),  Approved October 21, 1960 
 
Engine Lycoming O-235-C1 or O-235-C1B  (Carburetor setting #10-3103-1) 
 
Fuel 80/87 minimum grade aviation gasoline 
 
Engine Limits For all operations, 2600 r.p.m. (108 hp) 
 
Airspeed Limits Vne (never exceed) 138 mph (120 knots)
(CAS) Vno (maximum structural cruising) 110 mph (96 knots)
 Vp (maneuvering) 104 mph (90 knots)
 
C. G. Range Normal Category: (+12.0) to (+16.25) at 1650 lb. 
  (+9.5) to (+16.25) at 1300 lb. or less  
 Utility Category: (+10.9) to (+14.00) at 1500 lb.  
  (+9.5) to (+14.00) at 1300 lb. or less 
 Straight line variation between points given. 
 
Gross Weight
(l b.)
1000
1200
1400
1600
1800
81 0 12 14 16
Inches Aft of Dat um
18
U.C.
N.C.
N.C. - No
U.C. - Ut
rmal Category
ility Cate gory
 
Empty Weight C. G. Range None 
 
Maximum Weight Normal Category: 1650 lb. 
 Utilit y Category: 1500 lb. 
 
Number of Seats 2  at  (+21) 
 
Maximum Baggage 100 lb. (+45)  (Normal category only) 
 
Fuel Capacity 18 gallons  (+24)   (See Item 108 for auxiliary tank) 
 
Oil Capacity 1.5 gallons (-29) 
 
Control Surface Stabilizer 1° Up 6½° Down 
   Movements Elevator 24° Up 12° Down 
 Aileron 15° Up 15° Down 
 Rudder 16° Right 16° Left 
 
Serial Numbers Eligible 22-8000 and up.

Page 9 of 15 1A6 
 
Required Equipment In addition to the pertinent required basic equipment specified in CAR 3, the following 
Items of equipment must be installed: 
 Items 8, 201(a) or 211(a), 202, 205(a), 206, and 401(y). 
 
Specifications Pertinent to All Models 
Datum Wing leading edge 
 
Leveling Means Plumb from hole in upper channel of front door to center punch mark on front seat cross 
tube. 
 
Certification Basis CAR 3, effective November 1, 1949, and Amendments 3-1 through 3-6, effective  
 June 4, 1951. 
 Type Certificate No. 1A6 issued December 20, 1950. 
 Date of Application for Type Certificate September 13, 1950. 
 
Production Basis Approved for manufacture of spare parts only under Production Certificate No. 206. 
 
Equipment A plus (+) or minus (-) sign preceding the weight of an Item of equipment indicates net weight change when 
that Item is installed. 
 
  Approval for the installation of all Items of equipment listed herein has been obtained by the aircraft 
manufacturer except those Items preceded by an asterisk (*).  The asterisk denotes that approval has been 
obtained by someone other than the aircraft manufacturer.  An Item marked with an asterisk may not have 
been manufactured under an FAA monitored or approved quality control system, and therefore conformity 
must be determined if the Item is not identified by a Form FAA-186, PMA or other evidence or FAA 
production approval. 
 
Propeller and Propeller Accessories 
The following propellers are eligible at the limits shown for diameter and static r.p.m. at maximum permissible throttle setting, 
no additional tolerance permitted: 
1. Propeller (with Lycoming O-290D or O-290-D2 engine)   
 Sensenich 74FM59 or any other fixed pitch wood propeller which is rated for the 
engine power and speed: 
+11 lb. (-50) 
 Static r.p.m.:  Not over 2400, not under 2200. 
Diameter:  Not over 74 inches, not under 70.5 inches 
  
2. Propeller (with Lycoming O-290D or O-290-D2 engine) - fixed pitch metal   
 (a)  Sensenich M76AM-2  or +25 lb. (-50) 
 (b)  Sensenich M74DM +30 lb. (-50) 
 Airplane Flight Manual shall be revised to reflect the subject propeller and limits. 
Landplane: 
   Static r.p.m.:  Not over 2450, not under 2150 
   Diameter:  Not over 74 inches, not under 72.5 inches 
Seaplane: 
   Static r.p.m.:  Not over 2450, not under 2350 
   Diameter:  Not over 74 inches, not under 72.5 inches 
  
3. Propeller (with Lycoming O-290D or O-290-D2 engine)   
 Koppers Aeromatic, F200-H/00-74E +34 lb. (-50) 
 Parts List Assembly No. 4394H-1.  Installation and operation must be accomplished in  
accordance with Koppers "Adjustment Instructions and Operation Limitations  
No. 58." 
   Low pitch setting 14° at 24 in sta. 
   Static r.p.m.:  Not over 2600, not under 2550. 
   Diameter:  Not over 74 inches, not under 72.5 inches

1A6 Page 10 of 15 
 
 
4. Propeller (with Lycoming O-290D or O-290-D2 engine)   
 Sensenich hub CS3FM-4, blades PC374A7 or C374E, two position controllable.   
Propeller control installation required as per Sensenich Dwg. D-3028, Revision E. 
   Blade pitch setting at 3/4 radius (27.75 in. station): 
   Low 13°, high 16.6° 
   Diameter:  Not over 74 inches, not under 72.5 inches 
+34 lb. (-50) 
5. Propeller (with Lycoming O-320-A2A or O-320-A2B engine) - Fixed pitch metal 
Sensenich M74DM 
Landplane: 
   Static r.p.m.:  Not over 2480, not under 2250. 
   Diameter:  Not over 74 inches, not under 72.5 inches 
Seaplane: 
   Static r.p.m.:  Not over 2500, not under 2400 
   Diameter:  Not over 74 inches, not under 72.5 inches 
 
+30 lb. 
 
(-50) 
6. Propeller (with Lycoming O-320-A1A or O-320-A1B engine) - constant speed  
  controllable 
Hartzell hub HC82XG-6, blades 7636D-4 
 
 
+54 lb. 
 
 
(-50) 
 Installed per Piper Dwg. No. 14747 when Item 105 (vacuum pump) is installed, or per  
  Piper Dwg. No. 14792, without vacuum pump. 
Not eligible when Item 407 is installed. 
Note 2(f) placard required. 
Blade pitch settings at 30 in. sta.:  Low 12°, high 26°. 
Diameter:  Not over 72 inches, not under 70 inches 
Eligible only on Models PA-22-150 and PA-22S-150, Serial Nos. 22-3218, 22-3387  
  and up. 
When this propeller is used on Model PA-22S-150, the engine side cowls shall be  
  installed per Piper Dwg. No. 14450. 
  
7. Propeller (with Lycoming O-320-B2A or O-320-B2B engine) - fixed pitch metal  
Sensenich M74DM 
 
+34 lb. 
 
(-50) 
 Landplane: 
   Static r.p.m.:  Not over 2450, not under 2250 
   Diameter:  Not over 74 inches, not under 72 inches 
Seaplane: 
   Static r.p.m.:  Not over 2500, not under 2400 
   Diameter:  Not over 74 inches, not under 72 inches 
Applicable Airplane Flight Manual shall be revised by the Modifier and approved by  
the applicable FAA Aircraft Certification Office to reflect this installation change. 
  
8. Propeller (with Lycoming O-235-C1 or O-235-C1B engine) - fixed pitch metal  
   Sensenich M76AM-2 
   Static r.p.m.:  Not over 2450, not under 2200 
   Diameter:  Not over 74 inches, not under 72.5 inches 
 
+25 lb. 
 
(-50) 
 
Engines and Engine Accessories - Fuel and Oil Systems 
101. Oil cooler - Harrison No. AP06CJ04-02 or AP06CU04-2 and Piper Air Duct +3 lb. (-18) 
102. Oil filter, Fram PB-5, Kit No. K-520, Fram Dwg. No. 62832 and Instruction Sheet  
  No. 62831 (weight includes 1 quart oil) 
+5 lb. (-18.5) 
103. Oil Cooler Harrison No. AP13SJ03-01 or AP12CU03-01 installed in accordance  
  with Piper Dwg. 13724 or 14368 
+6 lb. (-46) 
104. 
 
 
 
 
 
 
 
 
 
or 
Reserve 8 gallons fuel tank with electric transfer fuel pump installed in accordance  
  with Piper Dwg. 14454.  When installed on Models PA-22S-135, PA-22S-150 or  
  PA-22S-160, fuselage reinforcement channel, Part No. 14725, also required. 
NOTE 2(e) placard required. 
Airplane Flight Manual Supplement required: 
   Item 401(j), Model PA-22-150 
   Item 401(k) Model PA-22-135 (Serial Nos. 22-534 and up eligible), 
   Item 401(p) Model PA-22S-135 (Serial Nos. 22-807 and up eligible), 
   Item 401(q) Model PA-22S-150 (Serial Nos. 22-2378, 22-2425 and up eligible), 
   Item 401(u) Model PA-22-160 (Serial Nos. 22-2378, 22-2425 and up eligible), 
   Item 401(w) Model PA-22S-160 (Serial Nos. 22-2378, 22-2425 and up eligible).  
+12 lb. (+46)

Page 11 of 15 1A6 
 
105. Vacuum pump 
(a)  Pesco Model 3P-194-F, Type B-11 
 
+4 lb. 
 
(-25) 
 (b)  Airborne Mechanisms Model 113A1 installed in accordance with Piper  
       Dwg. 15163.  (PA-22-108 only). 
+4 lb. (-25) 
 (c)  Airborne Mechanisms Model 113A5 installed in accordance with Piper  
       Dwg. 15163 or 15208.  (PA-22-108 only). 
+4 lb. (-25) 
106. Optional Engines 
A.  Model PA-22-150 
      (1) Lycoming O-320 
      (2) Lycoming O-320-A1A 
      (3) Lycoming O-320-A1B 
B.  Model PA-22S-150 
      (1) Lycoming O-320 
      (2) Lycoming O-320-A1A 
      (3) Lycoming O-320-A1B 
  
107. Starter, Delco Remy Model 1109657 (12 v.) +17 lb. (-40) 
108. Auxiliary 18 gallons fuel tank installed in accordance with Piper Dwg. 15147 
(PA-22-108 only).  NOTE 2(j) placard required. 
+25 lb. (+24) 
 
Landing Gear 
201. Two main wheel-brake assemblies, 6.00-6, Type III 
(a)  Cleveland Aircraft Products Model 6:00 DHB-3 
       Wheel Assembly No. C-38500H 
        Brake Assembly No. C-2000H 
+14 lb. (+31.5) 
202. Two main 4-ply rating tires, 6.00-6, Type III, with regular tubes +17 lb. (+31.5) 
205. One nose wheel, 6.00-6, Type III 
(a)  Cleveland Aircraft Products Wheel Assembly No. C-38500H (less brake-drum) 
(b)  Cleveland Aircraft Products Wheel Assembly No. 38501 
+5 lb. (-36) 
206. One nose wheel 4-ply rating, tire, 6.00-6, Type III, with regular tube +9 lb. (-36) 
*207. Nose wheel centering kit installed according to Javelin Aircraft Company  
(Wichita, Kansas) Dwg. 723 and Installation Instructions dated April 15, 1953. 
+2. lb. (-29) 
208. Skis: 
*(a)  Federal A-2000A main skis and NA-1200A nose ski, per Federal Dwg. 11R951,  
         Change E. 
*(b)  Federal AWB-2100 main skis and AWN-1200 nose ski, per Federal  
         Dwg. 11R1117. 
         The following placard is required with this installation: 
            "Do not extend or retract skis while in motion on the ground." 
Use Actual Weight 
Change 
 
209. Edo Model 89-2000 floats with water rudder installed in accordance with Edo  
Dwg. No. 16270. 
Piper modifications must be made and installed in accordance with Piper Dwg. 14375  
(Model PA-22S-135, Serial Nos. 22-534 to 22-2377, 22-2379 to 22-2424, inclusive)  
and Piper Dwg. 14450 (Model PA-22S-150 and PA-22S-160, Serial Nos. 22-2378,  
22-2425 and up.)  Serial Nos. 22-534 to 22-806, inclusive, require a fuselage 
reinforcement brace, Piper Part No. 12480. 
  
 
210. (a) Doyn Fiberglass wheel fairings installed in accordance with  
       Doyn Dwg. No. 1300 and Doyn Process Specification for  
       Fiberglass Part No. PS-100 
Nose Fairing 
Main Fairing 
+5.5 lb. 
+15.0 lb. 
(-36) 
(+31.5) 
or (b)  Piper wheel fairings installed in accordance with  
       Piper Dwg. 15054 and 15058 
Nose Fairing 
Main Fairing 
+5.5 lb. 
+15.0 lb. 
(-36) 
(+31.5) 
or (c)  Piper wheel fairings installed in accordance with  
       Piper Dwg. 15083 
Nose Fairing 
Main Fairing 
+5.5 lb. 
+15.0 lb. 
(-36) 
(+31.5) 
 
211. Two Main Wheel-Brake Assemblies, 6.00-6, Type III   
 (a)  Cleveland Aircraft Products, Model 20-6 (Model PA-22-108 only) + 14.5 lb. (+31.5) 
       Wheel Assembly No. 40-28   
       Brake Assembly No. 30-18

1A6 Page 12 of 15 
 
Electrical Equipment 
301. Battery - Reading S24-12V +25 lb. (+21) 
302. Landing lights in wing leading edge per Piper Dwg. No. 12534 
(Serial Nos. 22-534 to 22-2377, 22-2379 to 22-2424, inclusive) 
Piper Dwg. No. 14442 (Serial Nos. 22-2378, 22-2425 and up). 
+4 lb. (+5) 
303. Battery - Reading R33-12V 
Serial Nos. 22-267, 22-340, 22-349, 22-350, 22-351, 22-354 through 22-7999. 
+28 lb. (+21) 
 
Interior Equipment 
401. (a)    CAA (FAA) approved Airplane Flight Manual dated December 20, 1950, for airplanes  
        equipped with Lycoming O-290-D engines.  (Required with 100 lb. baggage allowance.) 
  
 (b)    FAA-DOA approved Airplane Flight Manual dated May 5, 1952, for airplanes  
        equipped with Lycoming O-290-D2 engines. 
  
 (c)    FAA-DOA approved Airplane Flight Manual dated October 23, 1952, for airplanes  
        equipped with Lycoming O-290-D2 engines. 
  
 *(d)  Supplement to Airplane Flight Manual dated January 17, 1952. 
        (Required with Item 402(a) without altitude controller.) 
  
 *(e)  Revised Supplement to Airplane Flight Manual dated January 19, 1953. 
        (Required with Item 402(a) without altitude controller.) 
  
 *(f)  Revised Supplement to Airplane Flight Manual dated November 18, 1953. 
        (Required with Item 402(b) with approach coupler.) 
  
 (g)    FAA-DOA approved Airplane Flight Manual dated May 14, 1954, for Model  
        PA-22S-135 seaplanes equipped with Edo Model 89-2000 floats. 
  
 (h)    FAA-DOA approved Airplane Flight Manual dated September 3, 1954, for Model 
         PA-22-150. 
  
 (i)     FAA-DOA approved Airplane Flight Manual dated September 3, 1954, for Model 
         PA-22S-150 seaplanes equipped with Edo Model 89-2000 floats. 
  
 (j)     FAA-DOA approved Supplement No. 1 to Airplane Flight Manual dated  
         September 3, 1954, (Required with Item 104 Auxiliary Fuel System) 
         for Model PA-22-150. 
  
 (k)    FAA-DOA approved Supplement No. 1 to Airplane Flight Manual dated  
         October 23, 1952,  (Required with Item 104 Auxiliary Fuel System) for Model  
         PA-22-135, Serial No. 22-534 and up. 
  
 *(l)   Supplement to Airplane Flight Manual dated November 17, 1954. 
         (Required with Item 404). 
  
 *(m) Supplement to Airplane Flight Manual dated April 20, 1955. (Required with Item 405).   
 (n)    FAA-DOA approved Supplement to Airplane Flight Manual dated 
         September 3, 1954, for Model PA-22-150 (Required with Item 6). 
  
 (o)    FAA-DOA approved Supplement to Airplane Flight Manual dated  
         September 3, 1954, for Model PA-22S-150  (Required with Item 6). 
  
 (p)    FAA-DOA approved Supplement No. 1 to Airplane Flight Manual dated  
         October 23, 1952,  (Required with Item 104 Auxiliary Fuel System) for Model  
         PA-22S-135. 
  
 (q)    FAA-DOA approved Supplement No. 1 to Airplane Flight Manual dated  
         September 3, 1954,  (Required with Item 104 Auxiliary Fuel System) for Model  
         PA-22S-150. 
  
 (r)     FAA-DOA approved Supplement No. 3 to Airplane Flight Manual dated  
         September 3,  1954, for Model PA-22-150 (Required with Item 407.). 
  
 (s)    FAA-DOA approved Airplane Flight Manual dated August 27, 1957, for airplanes  
         equipped with Lycoming O-320-B2A or O-320-B2B engines. 
  
 (t)    FAA-DOA approved Supplement No. 1 to Airplane Flight Manual dated  
        August 27, 1957, for Model PA-22-160  (Required with Item 407). 
  
 (u)    FAA-DOA approved Supplement No. 2 to Airplane Flight Manual dated  
         August 27, 1957, for Model PA-22-160  (Required with Item 104 Auxiliary Fuel  
         System). 
  
 (v)    FAA-DOA approved Airplane Flight Manual dated October 25, 1957, for Model 
         PA-22S-160 seaplanes equipped with Edo Model 89-2000 floats.

Page 13 of 15 1A6 
 
 (w)   FAA-DOA approved Supplement No. 1 to Airplane Flight Manual dated  
         October 25, 1957, for Model PA-22S-160 (Required with Item 104 Auxiliary  
         Fuel System). 
  
 (x)    FAA-DOA approved Supplement No. 3 to Airplane Flight Manual dated  
        August 27, 1957 (Model PA-22-160);  or FAA-DOA approved Supplement  
        No. 4 to Airplane Flight Manual dated September 3, 1954 (Model PA-22-150) 
        (Required with Item 408 Piper AutoControl, Mitchell Model AKO-64, Automatic 
        Pilot)  for Models PA-22-150 and PA-22-160, Serial No. 22-6328, 22-6344,  
        22-6352 and up. 
  
 (y)   FAA-DOA approved Airplane Flight Manual dated October 21, 1960, revised  
        November 22, 1960, for Model PA-22-108. 
  
 (z)   FAA-DOA approved Supplement No. 1 to Airplane Flight Manual dated  
        October 21, 1960, (Required with Item 409 Piper AutoControl, Mitchell Model  
        AKO-64, Automatic Pilot) for Model PA-22-108, Serial No. 22-8000 and up. 
  
 (aa)  FAA-DOA approved Supplement to Airplane Flight Manual dated  
        December 20, 1950, for Model PA-22 (Required when rear door removed under  
        provisions of NOTE 4). 
  
 (ab)  FAA-DOA approved Supplement No. 3 to Airplane Flight Manual dated  
         October 23, 1952, for Model PA-22-135 (Required when rear door removed  
         under provisions of NOTE 4). 
  
 (ac)   FAA-DOA approved Supplement No. 5 to Airplane Flight Manual dated  
         September 3, 1954, for Model PA-22-150 (Required when rear door removed  
         under provisions of NOTE 4). 
  
 (ad)   FAA-DOA approved Supplement No. 4 to Airplane Flight Manual dated  
         August 27, 1957 for Model PA-22-160 (Required when rear door removed  
         under provisions of NOTE 4). 
 
  
*402. Lear L-2B Automatic Pilot: 
(An approved vacuum system to operate automatic pilot gyros and a 35 ampere  
generator meeting requirements of Aircraft Engine Specification E-229 are required.   
Servo pitch drum diameter for all three axes 1.375 inches.) 
(a)  Automatic pilot and altitude controller (optional equipment) installed in  
      accordance with Lear Dwg. 95650. 
      Servo slip clutch stall torque, +0, -5 in.-lb. tolerance: 
           Aileron            40 in.-lb. 
           Elevator           25 in.-lb. 
           Rudder             50 in.-lb. 
      Items 401(d) or 401(e) and the following placard, installed in clear view of pilot,  
      are required with this installation: 
      "Do not use Autopilot in normal operation below 75 feet above terrain including 
      take-off, approach and landing." 
 
 
 
 
+51 lb. 
 
 
 
 
(+63) 
 (b)  Automatic pilot and approach coupler (optional equipment) and altitude control  
       (optional equipment) installed in accordance with Lear Dwg. 95650, Revision D. 
       Servo slip clutch stall torque + 0, - 5 in.-lb tolerance: 
           Aileron            40 in.-lb. 
           Elevator           40 in.-lb. 
           Rudder             50 in.-lb. 
       Item 401(f) and the following placards, installed in clear view of the pilot, are  
       required with this installation: 
        "Do no use Autopilot in normal operation below 300 feet above terrain except  
        during take-off, approach and landing." 
        "During take-off, approach and landing, do not use Autopilot below 75 feet  
        above terrain." 
        "Do not use transmitter #1 during an automatic approach." 
+7 lb. (+74) 
*403. Javelin A2 single axis automatic pilot installed in accordance with Javelin Dwg. 721  
and Instructions dated June 15, 1954.  Item 207 required with this installation. 
+18 lb. (+94) 
*404. Lear Arcon (Automatic rudder control) installed in accordance with Lear Dwg.  
701944.  Item 401(1) required with this installation.  Model PA-22-135 only. 
+12 lb. (+65)

1A6 Page 14 of 15 
 
 
*405. Ross Control System Conversion Kit Model 10 installed in accordance with Ross 
(F. W. Ross, 755 Kalamath Drive, Del Mar, California) Dwgs. 10R100 through 9A114 
on Drawing List dated November 5, 1955, and Installation Instructions dated  
November 5, 1955.  Placard required on instrument panel: 
  "Equipped with Ross Control System - See Flight Manual Supplement." 
  Item 401(m) required with this installation. 
Use Actual Weight 
and Balance Change 
 
*406. Deleted - November 26, 1957.  Now covered by Supplemental Type Certificate  
No. SA1-108 
  
407. Control modification kit (eliminating rudder and aileron interconnection) per  
Piper Dwg. No. 14926.  Item 401(r) or 401(t) and NOTE 2(g) placard required.  See  
limitations in NOTE 3. 
  
408. Piper AutoControl (Mitchell Model AKO-64)  Automatic Pilot installed in accordance  
with Piper Dwg. No. 14970.  Item 105 and 401(x), and NOTE 2(h) placard required.   
(Models PA-22-150 and PA-22-160) 
+5 lb. (-10) 
409. Piper Autocontrol (Mitchell Model AKO-64)  Automatic Pilot installed in accordance  
with Piper Dwg. No. 14970.  Item 105(b) or 105(c), and 401(z), and NOTE 2(h)  
placards required.  (Model PA-22-108) 
+5 lb. (-10) 
 
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. 
 
NOTE 2.  The following placards must be displayed: 
  (a) On the instrument panel in full view of the pilot (For all Models except PA-22-108): 
   (1) "Operate in Normal Category in compliance with approved Flight Manual. 
    Acrobatics (including spins) prohibited." 
  (b) On the baggage compartment (Serial Nos. 22-534 to 22-2377, 22-2379 to 22-2424): 
   (1) "Maximum Baggage 50 Pounds." or 
   (2) "Maximum Baggage 100 Pounds."  (For Model PA-22-135 when Airplane  
    Flight Manual, Item 401(c), is available in the airplane.) 
  (c) On the baggage compartment (Serial Nos. 22-2378, 22-2425 and up): 
   (1) "Maximum Baggage 100 Pounds." 
  (d) Deleted, December 30, 1955. 
  (e) Adjacent to reserve tank selector valve when Item 104 is installed in aircraft: 
   (1) "Reserve fuel 
      pull on 
      transfer fuel level flight only 
      operate only in accordance with flight manual." 
  (f) Adjacent to the propeller pitch control when Item 6 is installed: 
   (1) "Propeller-Push Increase R.P.M." 
  (g) On the instrument panel in full view of the pilot when Item 407 is installed: 
   (1) "Operate in Normal or Utility Category in compliance with the approved Flight Manual.   
    Airplane marked for Normal Category.  Acrobatics (including spins) prohibited in  
    Normal Category." 
  (h) When Item 408 or 409 is installed: 
   (1) On left side of circuit breaker panel: 
    "Piper Autocontrol 
    Push to Engage 
    Disengage During Take-off and Landing." 
   (2) Between Directional Gyro and Gyro Horizon: 
"Turn Control 
Pull For Direction Control 
On 0° Heading Only"

Page 15 of 15 1A6 
   (3) On left side window channel in full view of the pilot: 
    "Piper Autocontrol 
    To Engage: Push turn control at D. G. in and center knobs then push in engaging  
       control, rocking heel if necessary. 
    To Turn:  Move turn control in desired direction. 
    For Heading 
        Lock:  Set D. G. at 0° pull put turn control knob, use trim knob to maintain exact 0°  
       h eading." 
  (i) On the instrument panel in full view of the pilot (For Model PA-22-108 only): 
   "This airplane must be operated as a normal or utility category airplane in compliance with approved  
   Airplane Flight Manual.  All markings and placards on this airplane apply to its operation as a normal  
   category airplane.  For utility category operation, refer to the Airplane Flight Manual.  No acrobatics  
   maneuvers (including spins) are approved for normal category operation." 
  (j) On the instrument panel in full view of the pilot  (When Item 108 is installed): 
   "Right tank level flight only." 
  (k) On right fuel quantity gauge (Serial Nos. 22-1 to 22-7642) 
   "No take-off on right tank with less than 1/3 tank." 
 
NOTE 3.  Serial Nos. 22-3218, 22-3387 and up, of Model PA-22-150 or PA-22-160, are eligible to be operated as a 
Normal or Utility Category Airplane in compliance with the approved Airplane Flight Manual provided Item 
407 (Control modification kit) is installed.  Propeller Item 6 is not eligible when Item 407 is installed. 
 
NOTE 4.  Serial Nos. 22-1 through 22-7999 of Models PA-22, PA-22-135, PA-22-150, and PA-22-160, are eligible to 
be operated in the Normal Category with the rear door removed in compliance with the pertinent approved 
Flight Manual.  Item 401(aa) for the PA-22; Item 401(ab) for the PA-22-135; Item 401(ac) for the PA-22-
150;  or Item 401(ad) for the PA-22-160, must be in each aircraft operated in this configuration. 
 
  (a)  Airspeed Limits (CAS) 
   Vne  (never exceed)  128 mph (111 knots) 
   Vno  (max. structural cruising) 100 mph (87 knots) 
   Vp  (maneuvering)  100 mph (87 knots) 
   Vfe  (flaps extended) 80 mph (70 knots) 
 
  (b) When the rear door is removed the following placards must be displayed in full view of the pilot: 
   (1) "Airplane maneuvers are limited to normal take-offs, climbs, banks not to exceed 30°, glides and 
 landings at speeds not in excess of 128 mph." 
   (2) "No smoking permitted." 
 
  (c) No baggage may be carried when the aircraft is flown with the rear door removed. 
 
 
 
 
.....END.....
```

## ADs (34, in force first)

- [AD 2025-02-11](https://openairdocs.org/ad/2025-02-11): Rudder Structure · FS 2001 J5A (Army L-4F), J5A-80, J5B (Army L-4G) and 67 more. Effective Mar 20, 2025
- [AD 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 2015-08-04](https://openairdocs.org/ad/2015-08-04): Wings · FS 2000 L-14, AE-1, HE-1 and 77 more. Effective Jun 3, 2015
- [AD 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 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 2001-23-17](https://openairdocs.org/ad/2001-23-17): GNS 430 units · Cessna 172, 182, 206 and 209 more. Effective Dec 28, 2001
- [AD 85-02-05 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 96-09-06](https://openairdocs.org/ad/96-09-06): Air Filter Assemblies · Maule Aerospace Technology 7ACA, 7ECA, 7FC and 180 more. Effective Jun 7, 1996
- [AD 85-06-04](https://openairdocs.org/ad/85-06-04): Fuel Tank · FS 2001 AE-1, HE-1, J5A-80 and 60 more. Effective May 4, 1985
- [AD 78-10-03](https://openairdocs.org/ad/78-10-03): Fuel Venting · FS 2001 AE-1, HE-1, J5A-80 and 66 more. Effective May 23, 1978
- [AD 74-17-04](https://openairdocs.org/ad/74-17-04): Fabric Reinforcement · FS 2002 PA-14, PA-12, PA-12S and 18 more. Effective Apr 11, 1977
- [AD 73-09-06](https://openairdocs.org/ad/73-09-06): Operating Limitation Placard - Throttle Hangup · Piper PA-22, PA-22-108, PA-22-135 and 5 more. Effective May 7, 1973
- [AD 72-21-03](https://openairdocs.org/ad/72-21-03): Fuel Line Failure · Piper PA-20, PA-20-115, PA-20-135 and 11 more. Effective Oct 13, 1972
- [AD 68-05-01](https://openairdocs.org/ad/68-05-01): Exhaust Mufflers · FS 2001 J5A-80, J5A (Army L-4F), J5B (Army L-4G) and 67 more. Effective Mar 31, 1968
- [AD 67-24-02](https://openairdocs.org/ad/67-24-02): Engine Fuel Starvation · Piper PA-22, PA-22-108, PA-22-135 and 5 more
- [AD 64-05-04](https://openairdocs.org/ad/64-05-04): Upper Main Oleo Bearings · Piper PA-22, PA-22-108, PA-22-135 and 2 more. Effective Mar 30, 1964
- [AD 60-01-07](https://openairdocs.org/ad/60-01-07): Tail Brace Wires · FS 2002 PA-14, PA-12, PA-12S and 5 more
- [AD 61-16-05](https://openairdocs.org/ad/61-16-05): Control Cable Replacement · Piper PA-18-150, PA-18A-135, PA-18A-150 and 6 more. Effective Jul 26, 1961
- [AD 60-05-03](https://openairdocs.org/ad/60-05-03): Safety Belt · Piper PA-22-150 and PA-22-160
- [AD 60-10-08](https://openairdocs.org/ad/60-10-08): Fuel Selector Valve · Piper PA-18, PA-18-105 (Special), PA-18-125 (Army L-21A) and 30 more. Effective Jul 15, 1960
- [AD 57-22-01](https://openairdocs.org/ad/57-22-01): Fire Prevention Rework · Piper PA-16, PA-16S, PA-20 and 12 more
- [AD 59-10-08](https://openairdocs.org/ad/59-10-08): Gas Tank Cap Vent · Piper PA-18, PA-18A, PA-20 and 1 more. Effective Jul 15, 1959
- [AD 58-16-01](https://openairdocs.org/ad/58-16-01): Cigar Lighter Fuse · Piper PA-20 and PA-22
- [AD 51-19-02](https://openairdocs.org/ad/51-19-02): Oil Radiator Hose · Piper PA-18, PA-20 and PA-22
- [AD 51-23-03](https://openairdocs.org/ad/51-23-03): Battery Box Insulation · Piper PA-16, PA-20 and PA-22
- [AD 51-27-03](https://openairdocs.org/ad/51-27-03): Nose Wheel Drain · Piper PA-22
- [AD 53-24-04](https://openairdocs.org/ad/53-24-04): Fuel-Hydraulic Lines · Piper PA-18, PA-20 and PA-22
- [AD 55-07-02](https://openairdocs.org/ad/55-07-02): Landing Gear Tube Reinforcement · Piper PA-22
- [AD 55-08-04](https://openairdocs.org/ad/55-08-04): Ignition Filter Replacement · Piper PA-22
- [AD 55-22-03](https://openairdocs.org/ad/55-22-03): Fuel Tank Cap · Piper PA-22
- [AD 99-01-05 R1](https://openairdocs.org/ad/99-01-05-R1) (historical): Wings · FS 2000 L-14, AE-1, HE-1 and 73 more. Effective Jan 14, 2014
- [AD 99-01-05](https://openairdocs.org/ad/99-01-05) (historical): Wing Lift Struts or Forks · FS 2000 L-14, AE-1, HE-1 and 73 more. Effective Feb 8, 1999
- [AD 93-10-06](https://openairdocs.org/ad/93-10-06) (historical): Corroded Wing Lift Struts or Cracked Forks · Piper Aircraft, Inc., The New J-2, J-3, J4 and 28 more. Effective Jul 9, 1993

## Registered aircraft by registry model (OpenAirDocs)

- [Piper PA-22-150](https://openairdocs.org/model/piper-pa-22-150): 1,200 aircraft (registry code 7102210)
- [Piper PA-22-108](https://openairdocs.org/model/piper-pa-22-108): 587 aircraft (registry code 7102204)
- [Piper PA-22-160](https://openairdocs.org/model/piper-pa-22-160): 456 aircraft (registry code 7102214)
- [Piper PA-22-135](https://openairdocs.org/model/piper-pa-22-135): 409 aircraft (registry code 7102206)
- [Piper PA-22](https://openairdocs.org/model/piper-pa-22): 277 aircraft (registry code 7102202)
- [Piper PA-22S-150](https://openairdocs.org/model/piper-pa-22s-150): 8 aircraft (registry code 7102212)
- [Piper PA-22S-135](https://openairdocs.org/model/piper-pa-22s-135): 4 aircraft (registry code 7102208)
- [Piper PA-22S-160](https://openairdocs.org/model/piper-pa-22s-160): 1 aircraft (registry code 7102216)
- [Piper/Pierce Tony PA-22-150](https://openairdocs.org/model/piper-pierce-tony-pa-22-150): 1 aircraft (registry code 7102201)
- [Piper/Plasse/Hanks PA 22-135](https://openairdocs.org/model/piper-plasse-hanks-pa-22-135): 0 aircraft (registry code 7102205)

## STCs approved under this data sheet (380, first 50)

- [STC SA01233SE](https://openairdocs.org/stc/SA01233SE): Fabrication and installation of Alaskan Bushwheel LLC tail wheel and fork assembly. ABI, LLC
- [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 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 SA01005DE](https://openairdocs.org/stc/SA01005DE): Installation of a EarthX ETX900-TSO Lithium battery. EarthX Inc.
- [STC SA00081NY](https://openairdocs.org/stc/SA00081NY): Installation of Iceman Aviation Supplies, Inc. Carburetor Ice Detector.. Alcor LLC
- [STC SA12025AT](https://openairdocs.org/stc/SA12025AT): This STC allows the exchange of the valid Standard Airworthiness Certificate issued to aircraft serial
number 22-2838, a Piper PA-22-150 aircraft registered as N2463P, which meets the requirements of 14
CFR Part 21.24(a)(1) for a Special Airworthiness - Primary Category Airworthiness Certificate, under the
existing provisions of 14 CFR Part 21.184(c).. Christopher Allen Cox
- [STC SA316SO](https://openairdocs.org/stc/SA316SO): Carburetor ice detector.. LegacySTC.com
- [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 SA1-274](https://openairdocs.org/stc/SA1-274): Installation of Lycoming O-320(150 hp) series engine and Sensenich M74DM propeller.. Steve Pierce
- [STC SA26EA](https://openairdocs.org/stc/SA26EA): Conversion of aircraft for parachute jumping and aerial photography.. Steve Pierce
- [STC SA847EA](https://openairdocs.org/stc/SA847EA): Installation of Lycoming O-320-A(150 hp) or O-320-B (160 hp) engine.. Steve Pierce
- [STC SA11854CH](https://openairdocs.org/stc/SA11854CH): Installation of modified exhaust system in lieu of original components. Dakota Cub Aircraft Inc.
- [STC SA04378CH](https://openairdocs.org/stc/SA04378CH): Installation of an engine modified per STC SE04349CH. SureFly Partners Ltd.
- [STC SA02594SE](https://openairdocs.org/stc/SA02594SE): SkyView HDX Instrumentation and Autopilot System manufactured. Dynon Avionics
- [STC SA02386AK](https://openairdocs.org/stc/SA02386AK): Replacement of existing landing and/or taxi light reflector and bulbs with Light Emitting Diode (LED) lighting systems. AeroLED's Holding LLC
- [STC SA03898NY](https://openairdocs.org/stc/SA03898NY): Installation and maintenance of ORATEX covering and coating material. Aircraft Design & Certification Ltd
- [STC SA01343WI](https://openairdocs.org/stc/SA01343WI): Installation of B&C Specialty Products BC400 alternator. B & C Specialty Products Inc.
- [STC SA4503NM](https://openairdocs.org/stc/SA4503NM): Remove original cloth covering and install Ceconite covering. Ceconite Division of Poly-Fiber Inc.
- [STC SA09150SC](https://openairdocs.org/stc/SA09150SC): Replacement of Piper wheel assembly p/n 451-750 and brake assembly p/n 451-708 with Cleveland wheel assembly pn 40-86 and brake assembly pn 30-55.. Peter C. Morrison
- [STC SA8334SW](https://openairdocs.org/stc/SA8334SW): Installation of dual toe brakes including rudder pedals, linkages and torque tubes.. Peter C. Morrison
- [STC SA8438SW](https://openairdocs.org/stc/SA8438SW): Installation of dual toe brakes including rudder pedals, linkages and torque tubes.. Peter C. Morrison
- [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 SA01899WI](https://openairdocs.org/stc/SA01899WI): Installation of Garmin G3X Touch Electronic Flight Instrument System. Garmin International Inc.
- [STC SA02576AK](https://openairdocs.org/stc/SA02576AK): Installation of Cleveland and ABI, LLC Wheel and Brake Kits. ABI LLC
- [STC SA02019WI](https://openairdocs.org/stc/SA02019WI): Installation of the Trig Avionics TX56, TX56A, TX57, or TX57A VHF Nav-Com Radio.. Peregrine
- [STC SA02233AK](https://openairdocs.org/stc/SA02233AK): Installation of high visibility fuel sight gauge.. Dakota Cub Aircraft 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 SA3-477](https://openairdocs.org/stc/SA3-477): Installation of Model C-2200 main main and AWN1200A nose wheel skis.. F.Atlee Dodge Aircraft Services
- [STC SA3-494](https://openairdocs.org/stc/SA3-494): Installation of Model C2200 main ski and AWN-1200A nose wheel ski.. F.Atlee Dodge Aircraft Services
- [STC SA02987CH](https://openairdocs.org/stc/SA02987CH): Installation of the Electroair Electronic Ignition System. Electroair Acquisition Corporation
- [STC SA00954WI](https://openairdocs.org/stc/SA00954WI): Installation of Concorde RG Series Batteries in Piper Single Engine Airplanes.. Aero-Mach Wilco LLC
- [STC SA02534AK](https://openairdocs.org/stc/SA02534AK): Installation of Airframes Alaska Aluminum Lift Struts. Airframes Alaska LLC
- [STC SA01967WI](https://openairdocs.org/stc/SA01967WI): Use of GAMI G100UL High Octane Unleaded Avgas. General Aviation Modifications Inc.
- [STC SA04776NY](https://openairdocs.org/stc/SA04776NY): The HIPEC Covering and Finishing System must be performed and maintained. HIPEC Aircraft Coatings Inc.
- [STC SA02444AK](https://openairdocs.org/stc/SA02444AK): Approval of the L-3 Communications NGT 9000/9000R ADS-B system installed. ADS-B Technologies LLC
- [STC SA02153AK](https://openairdocs.org/stc/SA02153AK): Installation of Burl's Aircraft Rebuild Magnum I tail wheel Penetration ski. Burl's Aircraft Rebuild LLC
- [STC SA01015SE](https://openairdocs.org/stc/SA01015SE): Installation of eligible Alaska Bushwheel, Inc. wheels and TSO-C62d tires. ABI LLC
- [STC SA01818WI](https://openairdocs.org/stc/SA01818WI): Installation of Garmin G5 Electronic Flight Instrument. Garmin International Inc.

All 380: https://openairdocs.org/tcds/1A6/stcs.md

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