# TCDS 1A15: 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: Part 3, Part 21
- Registered aircraft: 2,232, by the registry models matched to it (OpenAirDocs)
- Data sheet PDF: https://openairdocs.org/files/sha256/08/91/089146ebb9596aab1f4a8eabe9b9748e2772edf20d430e2034ae549a4c41ac99
- FAA DRS: https://drs.faa.gov/browse/excelExternalWindow/4FCC8AD41F3024CC86257209007581EC.0001
- Page: https://openairdocs.org/tcds/1A15

## Models (4)

As the data sheet lists them.

- PA-24 (Comanche 180)
- PA-24-260 (Comanche 260)
- PA-24-250 (Comanche 250)
- PA-24-400 (Comanche 400)

## 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 
1A15 
Revision 34 
Piper Aircraft, Inc 
 PA-24 
 PA-24-250 
 PA-24-260 
 PA-24-400 
 
August 7, 2006 
AIRCRAFT SPECIFICATION NO. 1A15 
 
Type Certificate Holder Piper Aircraft, Inc. 
 2926 Piper Drive 
 Vero Beach, Florida    32960 
 
Type Certificate Holder Record The New Piper Aircraft, Inc transferred TC 1A15 to Piper Aircraft, Inc on August 7, 
2006 
 
I. - Model  PA-24,  4 PCLM  (Normal Category),  Approved June 20, 1957. 
 
Engine Lycoming O-360-A1A  (See Item 111 for eligible relocated engines) 
 
Fuel 91/96 min. grade aviation gasoline 
 
Engine Limits All operations, 2700 r.p.m.  (180 hp) 
 
Airspeed Limits Vne (Never Exceed) 202 mph (175 knots) 
 Vno (Maximum Structural Cruise) 160 mph (139 knots) 
 Vp (Maneuvering) 154  mph (134 knots) 
 Vfe (Flaps Extended) 125 mph (108 knots) 
 Vle (Landing Gear Extended)   
  S/N 24-2 through 24-102: 125 mph (108 knots) 
  S/N 24-1, and 24-103 through 
24-3687: 
 
150 mph
 
(130 knots) 
 
Center of Gravity (+89.0) to (+94.0) at 2550 lb. 
(C. G.) Range (+83.0) to (+94.0) at 2206 lb. 
(Gear Extended) (+82.0) to (+94.0) at 1900 lb. or less 
 
 Straight line variation between points given. 
 Moment due to retracting of landing gear   (1266 in. -lb.) 
 
 
Aircraf t Weight
(lb.)
2550
2206
1900
Inches Aft of Datum
94.089.0
83.0
82.0
Page No. 1 2 3 4 5 6 7 8 9 10 11 12 13 14 15 16 17 18 19 20 21 22 23 24 
 
Rev. No. 34 33 33 33 33 33 33 33 33 33 33 33 33 33 33 33 33 33 33 33 33 33 33 33 
Page No. 25 26 27 28                    
Rev. No. 33 33 33 33

1A15 Page 2 of 28 
 
Empty Weight C. G. Range None 
 
Maximum Weight 2550 lb. 
 
Number of Seats 4 (2 at +85, 2 at +118.5) 
 
Maximum Baggage Rear compartment at (+142) 
 100 lb. (S/N 24-2 through 24-102) 
 200 lb. (S/N 24-1, and 24-103 through 24-3687) 
 
Fuel Capacity 60 gallons at  (+90) (Two wing tanks) 
 
Oil Capacity 2 gallons at (+25) (+24 when Item 111 is installed.) 
 
Control Surface Movements Main Surfaces Aileron 19° Up 15° Down 
  Horizontal T.E.     
    S/N 24-2 
  through 24-102: 
 
11° 
 
Up 
 
5° 
 
Down 
    S/N 24-1, 24-103 
  through 24-3687: 
 
13° 
 
Up 
 
5° 
 
Down 
  Rudder 25° Left 25° Right 
  Flap   27° Down 
 Anti-Servo tab (with stabilizer in 
  neutral position) 
 
7° 
 
Up 
 
13° 
 
Down 
 
Serial Numbers Eligible 24-1 through 24-3687. 
 
Required Equipment In addition to the pertinent required basic equipment specified in CAR 3, the following 
items of equipment must be installed:  1(a), 1(b), 101, 102, 103, 201(a), 205, 206(a), 
301(a), 302(a), and 401(a), 401(d) or 401(k). 
 
 
II. - Model PA-24-250,  4 PCLM  (Normal Category),  Approved April 16, 1958. 
 
Engine Lycoming O-540-A1A  (See Item 109 for optional engines) 
 
Fuel 91/96 min. grade aviation gasoline 
 
Engine Limits All operations, 2575 r.p.m.  (250 hp) 
 
Airspeed Limits Vne (Never Exceed)*** 203 mph (177 knots)
 Vno (Maximum Structural Cruise) 180 mph (156 knots)
 Vle (Landing gear extended) 150 mph (130 knots)
 Vp (Maneuvering) 144 mph (125 knots)
 Vfe (Flaps Extended)  125 mph (108 knots)
 
 ***   See Item 618 for approved speed increase.

Page 3 of 28 1A15 
 
Center of Gravity S/N 24-1, 24-103 through 24-2298, except 24-2003: 
(C.G.) range (+87.7) to (+93.0) at 2800 lb. 
 (+82.5) to (+93.0) at 2400 lb. 
 (+80.5) to (+93.0) at 1900 lb. 
 
 S/N 24-2003, 24-2299 through 24-3687: 
 (+86.0) to (+93.0) at 2900 lb. 
 (+82.5) to (+93.0) at 2600 lb. 
 (+80.5) to (+93.0) at 2000 lb. 
 Straight line variation between points given. 
 Moment due to retracting of landing gear   (1266 in. -lb.) 
 
Aircraft
Weight
(lb.)
2900
2600
2000
Aircraft
Weight
(lb.)
280 0
240 0
19 00
93.087.7
82.5
80.5
Inches Aft of Datum
86.0
82.5
80.5
S/N 24-1, 24-103 through 24-2298
Except 24-2003
S/N 24-2003, 24-2299 through 24-3687
Inches Aft of Datum
93.0
 
 
Empty Weight C. G. Range None 
 
Maximum Weight 2800 lb.   (S/N 24-1, 24-103 through 24-2298, except 24-2003) 
 2900 lb.  (S/N 24-2003, 24-2299 through 24-3687) 
 
Number of Seats 4 (2 at +85, 2 at +118.5) 
 
Maximum Baggage 200 lb. at  (+142) (Rear compartment) 
 
Fuel Capacity S/N 24-1, 24-103 through 24-2843, except 24-2563: 
     60 gallons at    (+90) (Two 30 gallon wing tanks) 
 
 S/N 24-2563, 24-2844 through 24-3687: 
     56 gallons at    (+90) (Two 28 gallon wing tanks) 
 
 See NOTE 1 for unusable fuel. 
 See Item 112 for auxiliary fuel tanks. 
 
Oil Capacity 3 gallons at  (+28) 
 
Control Surface Movements Main Surfaces Aileron 19° Up 15° Down 
  Horizontal T.E.     
    S/N 24-1, 24-103 through 24-2843,     
    except 24-2563: 13° Up 5° Down 
    S/N 24-2563, 24-2844      
    through 24-3687: 14° Up 4° Down 
  Rudder 25° Left 25° Right 
  Flap     
    S/N 24-1, 24-103 through 24-2843     
    except 24-2563:   27° Down 
    S/N 24-2563, 24-2844     
    through 24-3687:   32° Down

1A15 Page 4 of 28 
 
 
Control Surface Movements Anti-Servo tab (with stabilizer in neutral position)  
   S/N 24-1, 24-103 through 
  24-2843, except 24-2563: 
 
7° 
 
Up 
 
13° 
 
Down 
   S/N 24-2563, 24-2844 through 
  24-3687: 
 
7° 
 
Up 
 
15° 
 
Down 
 
Serial Numbers Eligible 24-1, 24-103 through 24-3687. 
 
Required Equipment  In addition to the pertinent required basic equipment specified in CAR 3, the following 
items of equipment must be installed: 
 3(a) and 3(b), 103, 106, 107(a) or 107(b), 201(a), 202(b), 205, 206(a), 301(a) or 301(b), 
302(a), 401(c), or 401(f), or 401(n), or 401(s), or 401(v), 603, 617(a), 401(bz) 
 When Item 109(e) is installed, substitute Items 113 and 114(a) or 114(b) in place of 
Items 106 and 107(a) or 107(b), respectively. 
 
 
III. Model PA-24-400,  4 PCLM  (Normal Category),  Approved December 27, 1963. 
 
Engine Lycoming IO-720-A1A or IO-720-A1B 
 
Fuel 100/130 min. grade aviation gasoline 
 
Engine Limits All operations, 2650 r.p.m.  (400 hp) 
 
Airspeed Limits Vne (Never Exceed) 250 mph (219 knots) 
 Vno (Maximum Structural Cruise) 210 mph (182 knots) 
 Vp (Maneuvering) 160 mph (139 knots) 
 Vle (Landing Gear Extended) 150 mph (130 knots) 
 Vfe (Flaps Extended) 125 mph (108 knots) 
 
 
Center of Gravity (+84.8) to (+90) at 3600 lb. 
(C. G.) Range (+81.5) to (+90) at 3300 lb. 
(Gear Extended) (+77.0) to (+90) at 2500 lb. or less 
 Straight line variation between points given. 
 Moment due to retracting of landing gear   (1266 in. -lb.) 
 
Aircra ft Weight
(lb.)
3600
3300
2500
Inches Aft of Datum
90.084.8
81.5
77.0
 
Empty Weight C. G. Range None 
 
Maximum Weight 3600 lb.

Page 5 of 28 1A15 
 
 
Number of Seats 4 (2 at +85, 2 at +118.5) (S/N 26-2 through 26-124) 
 4 (2 at +85, 2 at +120.5) (S/N 26-125 through 26-148) 
 
Maximum Baggage 200 lb. at  (+142) (Rear compartment) 
 
Fuel Capacity 130 gallons at   (+90) (Two 30 gallon wing tanks) (124 gallons usable) 
 130 gallons at   (+94) (Two 35 gallon wing tanks) (124 gallons usable) 
 See NOTE 1 for unusable fuel data. 
 
Oil Capacity 17 quarts at (+21) (12 quarts usable) 
 
Control Surface  Main Surfaces Aileron 19° Up 15° Down 
   Movements  Stabilator (L.E.) 4.5° Up 15.5° Down 
  Rudder 25° Left 25° Right 
  Flap   38° Down 
 Anti-Servo Tab 
(Stabilizer Neutral) 
 4.5° Up 9° Down 
 
Serial Numbers Eligible 26-2 through 26-148. 
 
Required Equipment In addition to the pertinent required basic equipment specified in CAR 3, the following 
items of equipment must be installed:  7(a), 7(b), 115, 116, 118, 119, 201(c), 205, 206(b), 
302(a), 305, 401(ag), 603, and 605. 
 
 
IV.  Model PA-24-260,  4 PCLM  (Normal Category),  Approved June 19, 1964, or 6 PCLM  (Normal Category),  Approved 
June 30, 1965, and April 11, 1969 when Item 611 is installed (See NOTE 2(m) placard for 6 PCLM Limitations.). 
 
Engine Lycoming O-540-E4A5 (See Item 109(f) and 109(g) for additional optional engines and 
109(h) for optional turbocharged engines) 
 
Fuel 91/96 min. grade aviation gasoline (normally aspirated engine) 
 100/130 min. grade aviation gasoline (turbocharged engine) 
 
Engine Limits All operations, 2700 r.p.m.   (260 hp) 
 
Airspeed Limits Vne (Never Exceed)*** 203 mph (177 knots) 
 Vno (Maximum Structural Cruise) 180 mph (156 knots)
 Vle (Landing Gear Extended) 150 mph (130 knots)
 Vp (Maneuvering) 144 mph *(125 knots)
 Vfe (Flaps Extended)  125 mph (108 knots)
 Vp (Maneuvering) 150 mph **(130 knots)
 
 *  S/N 24-3642, 24-4000 through 24-4782, and 24-4784 through 24-4803. 
 **  S/N 24-4783, 24-4804 through 24-5034. 
 *** See Item 618 for approved speed increase.

1A15 Page 6 of 28 
 
 
Center of Gravity S/N 24-3642, 24-4000 through 24-4246, and 24-4248 through 24-4299: 
(C. G.) Range (+86.0) to (+93.0) at 2900 lb. 
(Gear Extended) (+82.5) to (+93.0) at 2600 lb. 
 (+80.5) to (+93.0) at 2000 lb. or less 
 
 Straight line variation between points given. 
 Moment due to retracting of landing gear   (1266 in. -lb.) 
 
 
2000
2600
2900
Inches Aft of Datu m
80.5 86.082.5 93.0
24-478 3
04
 
 
 S/N 24-4247, 24-4300 through 24-4782, and 24-4784 through 24-4803: 
 (+88.4) to (+93.0) at 3100 lb. 
 (+82.5) to (+93.0) at 2600 lb. 
 (+80.5) to (+93.0) at 2000 lb. or less 
 
 S/N 42-4783, and 24-4804 through 24-5034 (with normally aspirated engine only): 
 (+89.6) to (+93.0) at    3200 lb. 
 (+82.5) to (+93.0) at    2600 lb. 
 (+80.5) to (+93.0) at    2000 lb. or less 
 
 Straight line variation between points given. 
 Moment due to retracting of landing gear   (1266 in. -lb.) 
 
 
3200
Serial No.
and 24-48
2000
2600
3100
Aircra ft Weight
(lb.)
Serial No. 24-4247;
24-4300 through
24-4782; 24-4784
through 24-4 803.
In ches Aft of Datum
80.5
82.5
88.4 89.6 93.0   through 24-5034

Page 7 of 28 1A15 
 
Center of Gravity S/N 24-4783, and 24-4804 through 24-5034 (with turbocharged engines only): 
(C. G.) Range (+87.6) to (+93.0) at 3200 lb. 
Gear Extended (+83.2) to (+93.0) at 2800 lb. 
 (+80.5) to (+93.0) at 2000 lb. or less 
 
 Straight line variation between points given. 
 Moment due to retracting of landing gear   (1266 in. -lb.) 
 
 
2000
2800
3200
80.5 83.2 87.6 93.0
Aircraft Weight
(lb.)
Inches Aft of Datum  
 
Empty Weight C. G. Range None 
 
Maximum Weight S/N 24-3642, 24-4000 through 24-4246, and 24-4248 through 24-4299: 
  2900 lb. 
 S/N 24-4247, 24-4300 through 24-4782, and 24-4784 through 24-4803: 
  3100 lb. - Takeoff 
  2945 lb. - Landing 
 S/N 24-4783, and 24-4804 through 24-5034: 
  3200 lb. - Takeoff 
  3040 lb. - Landing 
 
Number of Seats 4 (2 at +85, 2 at +120.5) 
 
 S/N 24-4247, and 24-4300 through 24-5034 when Item 611 is installed: 
 6 (2 at +85, 2 at +120.5, 2 at +148) 
  
Maximum Baggage S/N 24-3642, 24-4000 through 24-4246, and 24-4248 through 24-4299: 
  200 lb. at (+142) (Rear compartment) 
 
 S/N 24-4247, and 24-4300 through 24-5034: 
  250 lb. at (+142) (Max. baggage and/or passenger allowance in baggage area,  
     including seats) 
 
Fuel  Capacity 56 gallons at (+90) (Two 28 gallon wing tanks) 
 See NOTE 1 for unusable fuel. 
 See Item 112 for auxiliary fuel tanks. 
 
Oil Capacity 3 gallons at (+28) 
 
Control Surface  Main Surfaces Aileron 19° Up 15° Down 
   Movements  Stabilator (L.E.) 14° Up 4° Down 
  Rudder 25° Left 25° Right 
  Flap  32° Down 
 Anti-Servo Tab 
(Stabilizer Neutral) 
 
7° 
 
Up 15°
 
Down

1A15 Page 8 of 28 
 
 
Serial Numbers Eligible 24-3642, 24-4000 through 24-5034. 
 
Required Equipment In addition to the pertinent required basic equipment specified in CAR 3, the following 
items of equipment must be installed: 
 
 S/N 24-3642, 24-4000 through 24-4246, and 24-4248 through 24-4299: 
 4(b), 9(a) or 9(c), 9(b), 103, 106, 107(c), 107(d) or 107(e), 201(d), 202(b), 205, 206(a), 
302(a), 305, 401(ah), 603, 617(a), and 401(bz). 
 When Item 109(f) is installed, substitute Items 113 and 114 and 401(ak) in place of Items 
106, 107(c), 107(d), or 107(e), and 401(ah), respectively. 
 
 S/N 24-4247, 24-4300 through 24-4782, and 24-4784 through 24-4803: 
 4(b), 9(a), 9(b), 103, 106, 107(e), 201(d), 202(b), 205, 206(a), 124, 305, 401(av), 603, 
617(a), and 401(bz). 
 When Item 109(f) is installed, substitute Items 113, 114(d), and 401(ba) in place of 106, 
107(e), and 401(av), respectively. 
 
 S/N 24-4783, and 24-4804 through 24-5034 (with normally aspirated engine): 
 9 (b), 9(d) or 9(g), (9e), 109(g), 113, 114(d), 120(a) or 120(c), 201(d), 202(b), 205, 
206(a), 302(a), 305(c), 401(bo), 603, 617(a), and 410(bz). 
 
 S/N 24-4783, and 24-4804 through 24-5034 (with turbocharged engine): 
 9(b), 9(f) or 9(h), 9(e), 109(h), 115, 120(b), 121(a), 122(a), 201(d), 202(b), 205, 206(a), 
124, 302(a), 305(c), 401(bp), 603, 616(a), 617(a), and 401(bz). 
 
Specifications Pertinent to All Models 
 
Datum 79 in. ahead of the wing leading edge at Wing Station 65.5 (intersection point of tapered 
edge with straight leading edge). 
 
Leveling Means Level from two rivnuts located right side above baggage door. 
 On S/N 24-4247, and 24-4300 through 24-5034 still on right side of fuselage, but 
baggage door moved to left side of fuselage. 
 
Certification Basis Type Certificate No. 1A15  (CAR 3, effective November 1, 1949, including 
Amendments 3-1 through 3-12, effective April 13, 1954). 
  
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 indicates net weight change when that item is  
  installed. 
 
Propeller and Propeller Accessories 
  PA-24 PA-24-250 PA-24-400 PA-24-260 
1. (a) Propeller - Hartzell constant speed controllable, hub 
model HC92ZK-8D, blades model 8447A-12A 
Pitch:  High 27°, Low 13° at 30 in. station 
Diameter  Not over 72¼ in., not under 70.5 in. 
63 lb. (+3) - - - - - - - - - - - - 
 (b) Governor Assembly:  Woodward 210185, 210260, 
210305, or Hartzell D1-1, D1-5. 
5 lb. (+39) - - - - - - - - - - - - 
 (c)  Deleted May 5, 1958. 
(Included in Item 4)

Page 9 of 28 1A15 
 
 
Propeller and Propeller Accessories (cont.) 
    PA-24 PA-24-250 PA-24-400 PA-24-260 
2. (a) Propeller - McCauley constant speed controllable, hub 
model 2D36C14, blades model 78KM-4. 
Pitch:  High 27.5°, Low 12.7° at 30 in. station 
Diameter:  Not over 74 in., not under 72 in. 
Item 401(b) or 401(1) required. 
60 lb. (+3) - - - - - - - - - - - - 
 (b) Governor Assembly:  Woodward 210185, 210250, 
210260, 210305 or Hartzell D1-1, D1-5. 
  5 lb. (+39) - - - - - - - - - - - - 
        
3. (a) Propeller - Hartzell constant speed controllable, hub 
model HC82XK-1D or HC-A2XK-1, blades model 
8433-7, or hub Model HC-A2VK-1, blades Model 
V8433N-7. 
Pitch:  High 31° to 33°, Low 14.5° at 30 in. station 
Diameter:  Not over 77 7/16 in., not under 76 in. 
Placard required:  (For O-540-A1A engine only) 
"Avoid continuous operation between 2225 and 2275 
r.p.m." 
63 lb. - - - - (+1.5) - - - - - - - - 
 (b) Governor Assembly:  Woodward 210185 or 210250 or 
Hartzell B-4-2. 
5 lb. - - - - (+10) - - - - - - - - 
        
4. (a) Hartzell spinner dome C-888 and bulkhead adapter  
C-885 (Eligible on Items 1(a) and 3(a) only) 
  3 lb. (+3) (+1.5) - - - - - - - - 
 (b) Piper spinner dome and bulkhead adapter   3 lb. (+3) (+1.5) - - - -- (+1.5) 
        
5. (a) Propeller - McCauley constant speed controllable, hub 
model 2D36C28, blades model 80MM-6. 
Pitch:  High 32°, Low 15.7° at 30 in. station 
Diameter:  Not over 74 in., not under 73 in. 
Placard required:  (For O-540-A1A engine only) 
"Avoid continuous operation between 2225 and 
2275 rpm."  Item 401(e), 401(g) or 401(o) required. 
60 lb. - - - - (+1.5) - - - - - - - - 
 (b) Woodward hydraulic governor assembly Model 
A210185 per Piper Dwg. 21764-3 or Model A210305 
per Piper Dwg. 21764-4 when Item 5(a) is installed. 
  5 lb. - - - - (+10) - - - - - - - - 
      
6. Deleted October 24, 1960.     
        
7. (a) Propeller - Hartzell constant speed controllable, hub 
model HC-A3VK-4, blades model V8433-7. 
Pitch:  High 36°, Low 14° at 30 in. station 
Diameter:  Not over 77 5/8 in., not under 75 5/8 in. 
See NOTE 2(k) 
88 lb. - - - - - - - - (-3.5) - - - - 
 (b) Governor Assy. - Hartzell F-4-1 per Piper 
Dwg. 24622-2.  
6 lb. - - - - - - - - (+3.5) - - - - 
        
8. Spinner Dome per Piper Dwg. 22752-2 and spinner 
Bulkhead Adapter per Piper Dwg. 22774-2. 
  4 lb. - - - - - - - - (-3.5) - - - -

1A15 Page 10 of 28 
 
 
Propeller and Propeller Accessories (cont.) 
    PA-24 PA-24-250 PA-24-400 PA-24-260 
9. (a) Propeller - Hartzell constant speed controllable, hub 
model HC-C2YK-1A, blades model 8467-7R. 
Pitch:  High 32° to 34°, Low 15° at 30 in. station 
Diameter:  Not over 77 in., not under 75 in. 
NOTE:  If it becomes necessary to reduce the propeller 
diameter below 77 inches, for maintenance or 
rebalancing purposes, a placard stating "Avoid 
continuous operation between 2500 and 2600 r.p.m. 
above 25 inch manifold pressure" must be displayed 
near the manifold pressure gauge. 
54 lb.    (+1.5) 
 (b) Governor Assy. Hartzell F-4-4 per Piper Dwg. No. 
24622-5 or F-4-4A per Piper Dwg. No. 24622-10 
6 lb. - - - - - - - - - - - -- (+10) 
 (c) Propeller - Hartzell constant speed controllable, hub 
model HC-C2YK-1B, blades model 8467-7R 
Pitch:  High 32° to 34°, Low 15° at 30 in. station 
Diameter:  Not over 77 in., not under 75 in. 
NOTE:  If it becomes necessary to reduce the propeller 
diameter below 77 inches, for maintenance or 
rebalancing purposes, a placard stating "Avoid 
continuous operation between 2500 and 2600 r.p.m. 
above 25 inch manifold pressure", must be displayed 
near the manifold pressure gauge. 
56 lb. - - - - - - - - - - - - (+1.5) 
 (d) Propeller - Hartzell constant speed controllable, hub 
model HC-E2YR-1B, blades model 8467-7R 
Pitch:  High 32° to 34°, Low 15° at 30 in. station 
Diameter:  Not over 77 in., not under 75 in. 
59 lb. - - - - - - - - - - - - (-3.4) 
 (e) Spinner dome Piper P/N 26326 with bulkhead adapter 
Piper P/N 26313 
  4 lb. - - - - - - - - - - - - (-4.1) 
 (f) Propeller - Hartzell constant speed controllable, hub 
model HC-E2YR-1B, blades model 8467-7R 
Pitch:  High 32° to 34°, Low 13.5° (+.3°, -0°) 
           at 30 in. station 
Diameter:  Not over 77 in., not under 75 in. 
59 lb. - - - - - - - - - - - - (-3.4) 
 (g) Propeller - Hartzell constant speed controllable, hub 
Model HC-E2YR-1BF, blades Model F8467-7R 
Pitch:  High 32° to 34°, Low 15° at 30 in. station 
Diameter:  Not over 77 in., not under 75 in. 
59 lb. - - - - - - - - - - - - (-3.4) 
 (h) Propeller - Hartzell constant speed controllable, Hub 
Model HC-E2YR-1BF, Blades Model F8467-7R 
Pitch:  High 32° to 34°, Low 13.5° (+.3°, -0°) 
           at 30 in. station 
Diameter:  Not over 77 in., not under 75 in. 
59 lb. - - - - - - - - - - - - (-3.4) 
 (i) Spinner Dome and Bulkhead Installation per Piper Kit 
760-452. 
5 lb. - - - - - - - - - - - - (+1.5)

Page 11 of 28 1A15 
 
 
Engine and Engine Accessories - Fuel and Oil System  PA-24 PA-24-250 PA-24-400 PA-24-260 
101. Fuel pump, electric auxiliary, Bendix Model 476087 or 
478360 
2 lb. (+38) - - - - - - - - - - - - 
       
102. Fuel pump, engine-driven      
 (a) AC No. 5594068 3 lb. (+33) - - - - - - - - - - - - 
 (b) AC No. 5623467 (Lycoming P/N 74060), 
AC No. 5656880 (Lycoming P/N 74082) or 
AC No. 6440295 (Lycoming P/N 75246) 
1.5 lb. (+33) - - - - - - - - - - - - 
      
103. Oil radiator, Harrison  Model AP07AU06-03 3 lb. (+12) (+10.5) - - - - (+10.5) 
       
104. Starter, Delco-Remy, Model 1109673 or 1109689, 12 volt 
geared (2.27:1) 
19 lb. (+15) - - - - - - - - - - - - 
       
105. Vacuum pump      
 (a) Pesco Model 3P-194-F Type B-11 4 lb. (+33) (+39) - - - - - - - - 
 (b) Deleted February 12, 1959      
 (c) Garwin G-455L 4 lb. (+33) (+39) - - - - - - - - 
 (d) Airborne Mechanisms 113A1, 113A5 or 200CC 4 lb. (+33) (+39) (+43) (+39) 
      
106. 2 fuel pumps, elec. aux. Bendix Model 476087 or 
478360.  Required except when Item 109(e) or 109(f) is 
installed. 
2 lb. 
each 
- - - - (+43) - - - - (+60) 
       
107. Fuel pump, engine-driven 
Required except when Item 109(e) or 109(f) is installed. 
     
 (a) AC No. 5594605 4 lb. - - - - (+39.5) - - - - - - - - 
 (b) AC No. 5623467 (Lycoming P/N 74060 ) or  
AC No. 5656880 (Lycoming P/N 74082) 
1.5 lb. - - - - (+39.5) - - - - - - - - 
 (c) AC No. 6440152 (Lycoming P/N 74798) 1.5 lb.  - - - - - - - - - - - - (+39.5) 
 (d) AC No. 6440174 2 lb. - - - - - - - - - - - - (+39.5) 
 (e) AC No. 6440295 2 lb. - - - - - - - - - - - - (+39.5) 
        
108. (a) Starter, Delco-Remy Model 1109695, 1109504, or 
1109511; 12 Volt, Geared 3.38:1.  Model 1109511 is  
eligible for installation on Model PA-24-260 only. 
18 lb. - - - - (+13.5) - - - - (+13.5) 
 (b) Starter, Prestolite Model MZ-4206, 12 Volt, Geared 
3.38:1 
17 lb. - - - - - - - - - - - - (+13.5) 
       
109. Optional engines (Lycoming)    
 (a) O-540-A1A5 (Item 401(f) and 401(n) required) Neg.Wt.Ch. - - - - Elig. - - - - - - - - 
 (b) O-540-A1B5 (Item 401(f) and 401(n) required) Neg.Wt.Ch. - - - - Elig. - - - - - - - - 
 (c) O-540-A1C5 (Item 401(f) and 401 (n) required) Neg.Wt.Ch. - - - - Elig. - - - - - - - - 
 (d) O-540-A1D5 (Item 401(f), 401(n) and 401(s) 
required) 
Neg.Wt.Ch. - - - - Elig. - - - - - - - - 
 (e) IO-540-C1B5 (Fuel injection installed per Piper  
Dwg. No. 23144) (Items 113, 114(a) or 114(b)  
and 401(v) required). 
Neg. Wt.Ch. - - - - Elig. - - - - - - - - 
 (f) IO-540-D4A5  (Fuel injection installed per Piper 
Dwg. No. 24923)  (Items 113, 114 and 401(ak) or 
401(ba) required). 
Use Actual 
Wt. Ch. 
- - - - - - - - - - - - Elig.

1A15 Page 12 of 28 
 
Engine and Engine Accessories - Fuel and Oil System (cont.) 
    PA-24 PA-24-250 PA-24-400 PA-24-260 
109. (g) IO-540-N1A5 Use Actual 
Wt. Chg. 
- - - - - - - - - - - - Elig. 
` (h) IO-540-R1A5 (Turbocharged - Items 122(a) required) 
installed per Piper Dwg. 27137 
Use Actual 
Wt. Chg. 
- - - - - - - - - - - - Elig. 
        
110 Carburetor air filter, Fram Paper Filter No. CA-161-PL Neg.Wt.Ch. Elig. Elig. - - - - Elig. 
       
111. Engine relocated per Piper Dwg. No. 22000. Eligible on 
Model PA-24, S/N 24-1684 through 24-3687.  Item 
401(k) required. 
Use Actual 
Wt. Change
Elig. - - - - - - - - - - - - 
 (a) Lycoming O-360-A1A    
 (b) Lycoming O-360-A1D (Limits same as for O-360-A1A) 
  The following is the new arm aft of datum for each item of equipment that is relocated when Item 111 is installed: 
 
Item Arm Item Arm 
1(a) (+1.5) 102 (+32.5) 
1(b) (+35) 103 (+10.5) 
2(a) (+1.5) 104 (+13.5) 
2(b) (+35) 105 (+31.5) 
4 (+1.5) 301(a) (+11.5) 
6(a) (+1.5) 301(b) (+11.5) 
6(b) (+35)   
 
  PA-24 PA-24-250 PA-24-400 PA-24-260 
112. Two 15 gallon auxiliary wing fuel tanks.   Eligible on 
Models PA-24-250 and PA-24-260, S/N 24-2003, 24-2299 
through 24-5034. 
13 lb. - - - - (+97) - - - - (+97) 
      
113. Fuel Pump, boost, rotary, motor-driven     
 (a) Bendix No. 480518-1 or 480528   5 lb. - - - - (+60) - - - - (+60) 
 (b) Dukes No. 4140-00-218 
Required with Items 109(e), 109(f) and 109(g). 
  2 lb. - - - - (+60) - - - - (+60) 
       
114. Fuel Pump - Engine Driven. 
Required with Items 109(e) and 109(f). 
    
 (a) AC No. 5656696A   2 lb. - - - - (+39.5) - - - - (+39.5) 
 (b) AC No. 6440160 (Lycoming No. 74999)   2 lb. - - - - (+39.5) - - - - (+39.5) 
 (c) AC No. 5656999 (Lycoming No. 75131)   2 lb. - - - - - - - - - - - - (+39.5) 
 (d) AC No. 6440296   2 lb. - - - - - - - - - - - - (+39.5) 
        
115. Fuel Pump, engine driven, Lear Siegler No. RG17980, 
Lycoming No. 74547 
  1 lb. - - - - - - - - (+43) (+39.5) 
       
116. Oil radiator, 2 required, Harrison Model AP13AU06-01   3 lb. ea - - - - - - - - (+39) - - - - 
       
117. Starter, Delco-Remy Model 1113471, Lycoming No. 
72279, 12V, geared 3.00:1 
35 lb. - - - - - - - - (+12) - - - -- 
      
118. Induction air filter, Fram Paper Filter No. CA-173PL   1 lb. - - - - - - - - (+10) - - - - 
       
119. (a) Fuel pump, boost rotary motor-driven, Bendix No. 
480533 
  5 lb. - - - - - - - - (+60) - - - - 
 (b) Fuel pump-boost-elec. Airborne Mfg. Co. No. 2B6-26. 3.7 lb. - - - - - - - - (+60) - - - -

Page 13 of 28 1A15 
 
 
Engine and Engine Accessories - Fuel and Oil System (cont'd) 
    PA-24 PA-24-250 PA-24-400 PA-24-260 
120. (a) Oil radiator - Harrison Model AP09AU06-02, 
Piper P/N 16943 
2.4 lb. - - - - - - - - - - - - (+45.8) 
 (b) Harrison Model AP18AU06-03, Piper P/N 43378 3.6 lb. - - - - - - - - - - - - (+45.8) 
 (c) Harrison Model AP09AU06-04, Piper P/N 32912  2.4 lb. - - - - - - - - - - - - (+45.8) 
       
121. (a) Fuel Pump, elec. aux. (boost)  
Dukes No. 4140-00-SPC 
2 lb. - - - - - - - - - - - - (+60) 
       
122. (a) Turbocharger 
Rayjay No. RJ0080-102 
(2 required when Item 109(h) is installed) 
13.5 lb. ea - - - - - - - - - - - - (+26.0) 
       
123. Manually Controlled Heated Alternate Engine Induction 
Air System 
   
 (a) Installation per Piper Dwg. 27186 3 lb. - - - - - - - - - - - - (+27.2) 
 Placards in NOTE 2(w) are required. 
(Eligible S/N 24-3642, 24-4000 through 24-4299, except 24-4247.  Item 401(bv) required.) 
(Eligible S/N 24-4247, 24-4300 through 24-4803, except 24-4783.  Item 401(bw) required.) 
       
124. Full Flow Oil filter and Adapter AC No. 5578941, 
Lycoming No. 74911, Lycoming No. 75528 or AC No. 
5578770 
 
2 lb. - - - - - - - -- - - - - (+40) 
Landing Gear     
201. (a) Two main wheel assemblies (with No. 3000-250 brake 
assemblies) 6.00-6, Type III, Cleveland Aircraft 
Products No. 3070. 
  8 lb. ea. (+108.5) (+108.5) - - - - - - - - 
 (b) Two main wheel assemblies (with No. 30-41 brake 
assemblies) 6.00.-6, Type III, Cleveland Aircraft 
Products No. 40-58. 
  8 lb. ea. (+108.5) (+108.5) - - - - - - - - 
 (c) Two main wheel assemblies (with No. 2-852 brake 
assemblies) 6.00-6, Type III, B.F. Goodrich No.  
3-1038. 
11 lb. - - - - - - - - (+108.5) - - - - 
 (d) Two main wheel assemblies (with No. 30-41 brake 
assemblies) 6.00-6, Type III, Cleveland Aircraft 
Products No. 40-84. 
  8 lb. ea. - - - - - - - -- - - - - (+108.5) 
 (e) Two main wheel assemblies (with No. 30-23 brake 
assemblies) 6.00-6, Type III, Cleveland Aircraft 
Products No. 40-90. 
9.5 lb. ea. - - - - - - - - (+108.5) - - - - 
        
202. (a) Two main 4-ply rating tires 6.00-6, Type III with 
regular tubes. 
9 lb. ea. (+108.5) - - - - - - - - - - - - 
 (b) Two main 6-ply rating tires 6.00-6, Type III with 
regular tubes. 
9.5 lb. ea. - - - - (+108.5) (+108.5) (+108.5)

1A15 Page 14 of 28 
 
Landing Gear (cont.) 
    PA-24 PA-24-250 PA-24-400 PA-24-260 
205. (a) One nose wheel 6.00-6, Type III, Cleveland Aircraft 
Products No. 38501. 
5 lb.  (+30.7) (+30.7) (+30.7) (+30.7) 
 (b) One nose wheel 6.00-6, Type III, Cleveland Aircraft 
Products No. 40-76(B). 
3.8 lb. (+30.7) (+30.7) (+30.7) (+30.7) 
        
206. (a) One nose wheel 4-ply rating tire 6.00-6, Type III with 
regular tube. 
9 lb. (+30.7) (+30.7) - - - - (+30.7) 
 (b) One nose wheel 6-ply rating tire 6.00-6, Type III with 
regular tube. 
9 lb. - - - - - - - - (+30.7) (+30.7) 
        
207. (a) Landing Gear Emergency Extension Security Kit 
No. 760-627.  Flight Manual Supplement, Piper Report 
1769, required. 
Neglect 
Weight 
Change 
Elig. Elig. Elig. Elig. 
  For Model PA-24-260, eligible on S/N 24-3642,  
24-4000 through 24-4803, except 24-4783, only. 
     
        
Electrical Equipment 
301. Generators     
 (a) One 12 volt, 35 amp generator, Delco Remy Model 
1101900, with bracket and voltage regulator No. 
1118704. 
18 lb. (+13) (+11.5) - - - - - - - - 
 (b) One 12 volt, 50 amp. generator, Delco Remy Model 
1101915, with bracket and voltage regulator No. 
1119224.  Eligible on S/N 24-1, 24-103 through  
24-3687 only. 
18 lb. (+13) (+11.5) - - - - - - - -- 
        
302. Battery     
 (a) Wisconsin Storage Battery, Reading R35, Bowers 
B-34, one 12 volt, 33 ampere-hour 
For S/N 24-2 through 24-102: 
 
 
27 lb. 
 
 
(+46) 
 
 
- - - - 
 
 
- - - - 
 
 
- - - - 
  For S/N 24-1, 24-103 through 24-3687: 27 lb. (+162) (+162) - - - - - - - - 
  For S/N 26-2 through 26-148: 27 lb. - - - - - - - - (+162) - - - - 
  For S/N 24-3642, and 24-4000 through 24-4246: 27 lb. - - - - - - - - - - - - (+162) 
  For S/N 24-4248 through 24-4299, and 24-4783: 27 lb. - - - - - - - - - - - - (+162) 
  For S/N 24-4804 through 24-5034: 27 lb. - - - - - - - - - - - - (+162) 
  For S/N 24-4247, 24-4300 through 24-4782, and  
24-4784 through 24-4803: 
 
27 lb. 
 
- - - - 
 
- - - - 
 
- - - - 
 
(+46) 
        
303. Landing Light, two G.E. Model 4509 2 lb. (+86) (+86) (+86) (+86) 
       
304. Anti-Collision Light      
 (a) Rotating Beacon - Grimes No. D-7080-1-12 or  
D-7080A-1-12 
2 lb. (+161) (+161) (+161) (+161) 
 (b) Rotating Beacon - Whelen No. WRM-12, WRMA-12 
or WRML-12 
2 lb. (+161) (+161) (+161) (+161) 
 (c) Strobe - Red Whelen Model HS Installation Piper 
Dwg. 27054.  Eligible on S/N 24-4783, and 24-4804 
through 24-5034 only.  Flight Manual Supplement 
401(bt) or 401(bu) and placard per NOTE 2(u) 
required with this installation. 
2.9 lb. - - - - - - - - - - - - (+161.7)

Page 15 of 28 1A15 
 
Electrical Equipment (cont.) 
  PA-24 PA-24-250 PA-24-400 PA-24-260 
305. Alternator 12 V., 70 ampere     
 (a) Delco-Remy No. 1100660 (Lycoming No. 74319) 12 lb. - - - - - - - - (+7) (+11.5) 
 (b) Delco-Remy No. 1100717 12 lb. - - - - - - - - (+7) (+11.5) 
 (c) Prestolite No. ALX-8403 12.2 lb. - - - - - - - - - - - -- (+11.5) 
       
306. Piper Elec. Trim per Piper Dwg. 24889 and 26754. 
Not eligible when Item 402 (c) is installed. 
4 lb. - - - - - - - - - - - - (+163) 
307. Anti-Collision Light (Wing Tips)     
 (a) Strobe - White Whelen Model HG-T2.  Piper 
Installation Dwg. 27060.  Eligible on S/N 24-4783, 
and 24-4804 through 24-5034 only.  Flight Manual 
Supplement 402(bt) or 401 (bu) and placard per NOTE 
2(v) required with this installation. 
4 lb. - - - - - - - - - - - - (+143.2) 
 
Interior Equipment 
401. (a) DMCR Approved Airplane Flight Manual dated June 19, 1957, revised March 7, 1958.  Eligible for S/N 24-2 
through 24-102 only. 
 
 (b) DMCR Approved Airplane Supplement No. 1, revised November 11, 1958, to Airplane Flight Manual Item 401(a).  
Required when Item 2(a) or 6(a) is installed. 
 
 (c) DMCR Approved Airplane Flight Manual dated April 16, 1958.  Eligible for Model PA-24-250, S/N 24-1, 24-103 
through 24-332. 
 
 (d) DMCR Approved Airplane Flight Manual dated March 7, 1958.  Eligible Model for PA-24, S/N 24-103 through  
24-1683 only. 
 
 (e) DMCR Approved Airplane Flight Manual Supplement No. 1 dated May 5, 1958, to Airplane Flight Manual for 
Model PA-24-250, Item 401(c).  Required when Item 5(a) is installed. 
 
 (f) DMCR Approved Airplane Flight Manual No. 997 dated July 10, 1958.  Eligible for Model PA-24-250, S/N 24-1,  
24-103 through 24-2002, 24-2004 through 24-2298 only.  Required when Item 109(a), (b), (c), or (d) is installed. 
 
 (g) DMCR Approved Airplane Flight Manual Supplement No. 1 dated July 10, 1958, revised August 15, 1958, to 
Airplane Flight Manual No. 997 for Model PA-24-250, Item 401(f).  Required when Item 5(a) is installed. 
 
 (h) DMCR Approved Airplane Flight Manual Supplement No. 2 dated July 31, 1958, to Airplane Flight Manual No. 997 
for Model PA-24-250, Item 401(f).  Required when Item 402(a), Piper AutoControl, is installed. 
 
 (i) DMCR Approved Airplane Flight Manual Supplement No. 2 dated July 31, 1958, to Airplane Flight Manual for 
Model PA-24, Item 401(d).  Required when Item 402(a), Piper AutoControl, is installed. 
 
 (j) DMCR Approved Airplane Flight Manual Supplement No. 2, dated July 31, 1958, to Airplane Flight Manual 
Supplement No. 973 for Model PA-24-250, Item 401(c).  Required when Item 402(a), Piper AutoControl, is 
installed. 
 
 (k) DMCR Approved Airplane Flight Manual No. 1047, dated December 11, 1959.  Eligible for Model PA-24, S/N  
24-1684 through 24-3687 only.  Required when Item 111 is installed. 
 
 (l) DMCR Approved Airplane Flight Manual Supplement No. 1, dated December 11, 1959, to Airplane Flight Manual 
No. 1047 for Model PA-24, Item 401(k).  Required when Item 2(a) is installed. 
 
 (m) DMCR Approved Airplane Flight Manual Supplement No. 2, dated December 11, 1959, to Airplane Flight Manual 
No. 1047 for Model PA-24, Item 401(k).  Required when Item 402(a) is installed.  Revision dated June 28, 1962, 
required when Course Selector directional gyro is installed.

1A15 Page 16 of 28 
 
Interior Equipment (cont.) 
401. (n) DMCR Approved Airplane Flight Manual No. 1127, dated September 27, 1960.  Eligible for Model PA-24-250, S/N 
24-2003, 24-2299 through 24-2562, and 24-2564 through 24-2843 only.  Required when Item 112 is installed. 
 
 (o) DMCR Approved Airplane Flight Manual Supplement No. 1 dated September 27, 1960, to Airplane Flight Manual 
No. 1127 for Model PA-24-250, Item 401(n).  Required when Item 5(a) is installed. 
 
 (p) DMCR Approved Airplane Flight Manual Supplement No. 2, dated September 27, 1960, to Airplane Flight Manual 
No. 1127 for Model PA-24-250, Item 401 (n).  Required when Item 402(a), Piper AutoControl, is installed. 
 
 (q) DMCR Approved Airplane Flight Manual Supplement No. 3, dated December 13, 1960, to Airplane Flight Manual 
No. 1127 for Model PA-24-250, Item 401(n).  Required when Item 402(b), Piper Altimatic, is installed. 
 
 (r) DMCR Approved Airplane Flight Manual Supplement No. 3, dated December 13, 1960, to Airplane Flight Manual 
No. 1047 for Model PA-24, Item 401(k).  Required when Item 402(b), Piper Altimatic, is installed. 
 
 (s) DMCR Approved Airplane Flight Manual No. 1179, dated September 18, 1961.  Eligible for Model PA-24-250, S/N 
24-2563, 24-2844 through 24-3687, except when Item 109(e) is installed. 
 
 (t) DMCR Approved Airplane Flight Manual Supplement No. 1, dated September 18, 1961, to Airplane Flight Manual 
No. 1179 for Model PA-24-250, Item 401(s).  Required when Item 402(a), Piper AutoControl, is installed.  Revision 
dated June 28, 1962, required when Course Selector directional gyro is installed. 
 
 (u) DMCR Approved Airplane Flight Manual Supplement No. 2, dated September 18, 1961, to Airplane Flight Manual 
No. 1179 for Model PA-24-250, Item 401(s).  Required when Item 402(b), Piper Altimatic, is installed. 
 
 (v) DMCR Approved Airplane Flight Manual No. 1220, dated February 15, 1962.  Eligible for Model PA-24-250, S/N  
24-2563, and 24-2844 through 24-3687 only.  Required when Item 109(e) is installed. 
 
 (w) DMCR Approved Airplane Flight Manual Supplement No. 1, dated February 15, 1962, to Airplane Flight Manual 
No. 1220 for Model PA-24-250, Item 401(v).  Required when Item 402(a), Piper AutoControl, is installed with Item 
109(e).  Revision dated June 28, 1962, required when Course Selector directional gyro is installed. 
 
 (x) DMCR Approved Airplane Flight Manual Supplement No. 2, dated February 15, 1962, to Airplane Flight Manual 
No. 1220 for Model PA-24-250, Item 401(v).  Required when Item 402(b), Piper Altimatic, is installed with Item 
109(e). 
 
 (y) DMCR Approved Airplane Flight Manual Supplement No. 4, dated August 7, 1962, to Airplane Flight Manual No. 
1047 for Model PA-24, Item 401(k).  Required when Item 402(c), Piper Altimatic II, is installed. 
 
 (z) DMCR Approved Airplane Flight Manual Supplement No. 4, dated August 7, 1962, to Airplane Flight Manual No. 
1127 for Model PA-24-250, Item 401(n).  Required when Item 402(c), Piper Altimatic II, is installed. 
 
 (aa) DMCR Approved Airplane Flight Manual Supplement No. 3, dated August 7, 1962 to Airplane Flight Manual No. 
1179 for Model PA-24-250, Item 401(s).  Required when Item 402(c), Piper Altimatic II, is installed. 
 
 (ab) DMCR Approved Airplane Flight Manual Supplement No. 3, dated August 7, 1962, to  Airplane Flight Manual No. 
1220 for Model PA-24-250, Item 401(v).  Required when Item 402(c), Piper Altimatic II, is installed with Item 
109(e). 
 
 (ac) DMCR Approved Airplane Flight Manual Supplement No. 5, dated August 15, 1962, to Airplane Flight Manual No. 
1047 for Model PA-24, Item 401(k).  Required when Item 402(d), Piper AutoControl II, is installed. 
 
 (ad) DMCR Approved Airplane Flight Manual Supplement No. 5, dated August 15, 1962, to Airplane Flight Manual No. 
1127 for Model PA-24-250, Item 401(n).  Required when Item 402(d), Piper AutoControl II, is installed. 
 
 (ae) DMCR Approved Airplane Flight Manual Supplement No. 4, dated August 15, 1962, to Airplane Flight Manual No. 
1179 for Model PA-24-250, Item 401(s).  Required when Item 402(d), Piper AutoControl II, is installed.

Page 17 of 28 1A15 
 
Interior Equipment (cont.) 
401. (af) DMCR Approved Airplane Flight Manual Supplement No. 4, dated August 15, 1962, to Airplane Flight Manual No. 
1220 for Model PA-24-250, Item 401(v).  Required when Item 402(d), Piper AutoControl II, is installed with Item 
109(e). 
 
 (ag) DMCR Approved Airplane Flight Manual No. 1295, dated December 27, 1963.  Eligible for Model PA-24-400 only.
 
 (ah) DMCR Approved Airplane Flight Manual No. 1333, dated June 19, 1964.  Eligible for Model PA-24-260 
(Carburetor Model), S/N 24-3642, 24-4000 through 24-4246, and 24-4248 through 24-4299, only. 
 
 (ai) DMCR Approved Airplane Flight Manual Supplement No. 2, dated June 19, 1964, revised July 16, 1964, to 
Airplane Flight Manual No. 1333, for Model PA-24-260, Item 401(ah).  Required when Item 402(d), Piper 
AutoControl II, is installed. 
 
 (aj) DMCR Approved Airplane Flight Manual Supplement No. 1, dated June 19, 1964, revised July 16, 1964, to 
Airplane Flight Manual No. 1333, for Model PA-24-260, Item 401(ah).  Required when Item 402(c), Piper Altimatic 
II, is installed. 
 
 (ak) DMCR Approved Airplane Flight Manual No. 1334, dated June 19, 1964.  Eligible for Model PA-24-260 (Fuel 
Injection Model), S/N 24-3642, 24-4000 through 24-4246, and 24-4248 through 24-4299, only. 
 
 (al) DMCR Approved Airplane Flight Manual Supplement No. 1, dated June 19, 1964, revised July 16, 1964, to 
Airplane Flight Manual No. 1334, for Model PA-24-260, Item 401(ak).  Required when Item 402(c), Piper Altimatic 
II, is installed. 
 
 (am) DMCR Approved Airplane Flight Manual Supplement No. 2, dated June 19, 1964, revised July 16, 1964, to 
Airplane Flight Manual No. 1334, for Model PA-24-260, Item 401(ak).  Required when Item 420(d), Piper Auto 
Control II, is installed. 
 
 (an) DMCR Approved Airplane Flight Manual Supplement No. 1, dated May 5, 1964, revised July 16, 1964, to Airplane 
Flight Manual No. 1295, for Model PA-24-400, Item 401(ag).  Required when Item 402(c), Piper Altimatic II, is 
installed. 
 
 (ao) DMCR Approved Airplane Flight Manual Supplement No. 2, dated May 5, 1964, revised July 16, 1964, to Airplane 
Flight Manual No. 1295, for Model PA-24-400, Item 401(ag).  Required when Item 402(d), Piper AutoControl II, is 
installed. 
 
 (ap) DMCR Approved Airplane Flight Manual Supplement No. 3, dated February 19, 1965, to Airplane Flight Manual 
No. 1295, for Model PA-24-400, Item 401(ag).  Required when Item 607(a) is installed. 
 
 (aq) DMCR Approved Airplane Flight Manual Supplement No. 3, dated February 19, 1965, to Airplane Flight Manual 
No. 1333, for Model PA-24-260, Item 401(ah).  Required when Item 607(a) is installed. 
 
 (ar) DMCR Approved Airplane Flight Manual Supplement No. 3, dated February 19, 1965, to Airplane Flight Manual 
No. 1334, for Model PA-24-260, Item 401(ak).  Required when Item 607(a) is installed. 
 
 (as) DMCR Approved Airplane Flight Manual Supplement No. 4, dated April 30, 1965, to Airplane Flight Manual No. 
1295, for Model PA-24-400, Item 401(ag).  Required when Item 609(a) is installed. 
 
 (at) DMCR Approved Airplane Flight Manual Supplement No. 4, dated April 30, 1965, to Airplane Flight Manual No. 
1333, for Model PA-24-260, Item 401 (ah).  Required when Item 609(a), Oxygen System, is installed. 
 
 (au) DMCR Approved Airplane Flight Manual Supplement No. 4, dated April 30, 1965, to Airplane Flight Manual No. 
1334, for Model PA-24-260, Item 401(ak).  Required when Item 609(a), Oxygen System, is installed. 
 
 (av) DMCR Approved Airplane Flight Manual No. 1358, dated June 30, 1965, revised December 21, 1965, and 
January 6, 1966.  Eligible for Model PA-24-260 (Carburetor Model), S/N 24-4247, 24-4300 through 24-4782, and 
24-4784 through 24-4803, only.

1A15 Page 18 of 28 
 
Interior Equipment (cont.) 
401. (aw) DMCR Approved Airplane Flight Manual Supplement No. 1, dated June 30, 1965, to Airplane Flight Manual No. 
1358, for Model PA-24-260, Item 401 (av).  Required when Item 402(c), Piper Altimatic II, is installed. 
 
 (ax) DMCR Approved Airplane Flight Manual Supplement No. 2, dated June 30, 1965, to Airplane Flight Manual No. 
1358, for Model PA-24-260, Item 401(av).  Required when Item 402(d), Piper AutoControl II, is installed. 
 
 (ay) DMCR Approved Airplane Flight Manual Supplement No. 3, dated June 30, 1965, to Airplane Flight Manual No. 
1358, for Model PA-24-260, Item 401(av).  Required when Item 607(a) or 607 (b), Exhaust Gas Temperature 
Indicator, is installed. 
 
 (az) DMCR Approved Airplane Flight Manual Supplement No. 4, dated June 30, 1965, to Airplane Flight Manual No. 
1358, for Model PA-24-260, Item 401(av).  Required when Item 609(b), Oxygen System, is installed. 
 
 (ba) DMCR Approved Airplane Flight Manual No. 1359, dated June 30, 1965, revised December 21, 1965, and  
January 6, 1966.  Eligible for Model PA-24-260 (Fuel Injection Model), S/N 24-4247, 24-4300 through 24-4782, 
and 24-4784 through 24-4803, only. 
 
 (bb) DMCR Approved Airplane Flight Manual Supplement No. 1, dated June 30, 1965, to Airplane Flight Manual No. 
1359, for Model PA-24-260, Item 401(ba).  Required when Item 402(c), Piper Altimatic II, is installed. 
 
 (bc) DMCR Approved Airplane Flight Manual Supplement No. 2, dated June 30, 1965, to Airplane Flight Manual No. 
1359, for Model PA-24-260, Item 401(ba).  Required when Item 402(d), Piper AutoControl II, is installed. 
 
 (bd) DMCR  Approved Airplane Flight Manual Supplement No. 3, dated June 30, 1965, to Airplane Flight Manual No. 
1359, for Model PA-24-260, Item 401(ba).  Required when Item 607(a) or 607(b), Exhaust Gas Temperature 
Indicator, is installed. 
 
 (be) DMCR Approved Airplane Flight Manual Supplement No. 4, dated June 30, 1965, to Airplane Flight Manual No. 
1359, for Model PA-24-260, Item 401(ba).  Required when Item 609(b), Oxygen System, is installed. 
 
 (bf) D.O.A. No. EA-1 Approved Airplane Flight Manual Supplement No. 5, dated May 27, 1966, to Airplane Flight 
Manual No. 1358, for Model PA-24-260, Item 401(av).  Required when Item 402(e), Piper AutoControl II 
(Model AK161), is installed. 
 
 (bg) D.O.A.  No. EA-1 Approved Airplane Flight Manual Supplement No. 5, dated May 27, 1966, to Airplane Flight 
Manual No. 1359, for Model PA-24-260, Item 401(ba).  Required when Item 402(e), Piper AutoControl III (Model 
AK161), is installed. 
 
 (bh) D.O.A. No. EA-1 Approved Airplane Flight Manual Supplement No. 6, dated August 5, 1966, to Airplane Flight 
Manual No. 1358, for Model PA-24-260, Item 401(av).  Required when Item 402(f), Piper Altimatic III, is installed.
 
 (bi) D.O.A. No. EA-1 Approved Airplane Flight Manual Supplement No. 6, dated August 5, 1966, to Airplane Flight 
Manual No. 1359, for Model PA-24-260, Item 401(ba).  Required when Item 402(f), Piper Altimatic III, is installed.
 
 (bj) D.O.A. No. EA-1 Approved Airplane Flight Manual Supplement No. 7, dated August 7, 1967, to Airplane Flight 
Manual No. 1358, for Model PA-24-260, Item 401(av).  Required when Item 607(c), Exhaust Gas Temperature 
Indicator, is installed. 
 
 (bk) D.O.A. No. EA-1 Approved Airplane Flight Manual Supplement No. 7, dated August 7, 1967, to Airplane Flight 
Manual No. 1359, for Model PA-24-260, Item 401 (ba). Required when Item 607(c), Exhaust Gas Temperature 
Indicator, is installed. 
 
 (bl) D.O.A. No. EA-1 Approved Airplane Flight Manual Supplement No. 1 to Airplane Flight Manual No. 1545.  
Required when Item 402(g), AutoControl III, is installed.

Page 19 of 28 1A15 
 
 
Interior Equipment (cont.) 
401. (bm) D.O.A. No. EA-1 Approved Airplane Flight Manual Supplement No. 2 to Airplane Flight Manual No. 1545.  
Required when Item 402(h), Altimatic IIIB, is installed. 
 
 (bn) D.O.A. No. EA-1 Approved Airplane Flight Manual Supplement No. 3 to Airplane Flight Manual No. 1545.  
Required when Item 609(b), Oxygen System, is installed. 
 
 (bo) D.O.A. No. EA-1 Approved Airplane Flight Manual No. 1545, dated April 11, 1969.  Eligible for Model  
PA-24-260, S/N 24-4783, and 24-4804 through 24-5034 only. 
 
 (bp) D.O.A. No. EA-1 Approved Airplane Flight Manual No. 1640, dated May 25, 1970.  Eligible Model for PA-24-260 
(equipped with Turbocharger), S/N 24-4783, and 24-4804 through 24-5034 only. 
 
 (bq) D.O.A. No. EA-1 Approved Airplane Flight Manual Supplement No. 1 to Airplane Flight Manual No. 1640.  
Required when Item 402(g), AutoControl III, is installed. 
 
 (br) D.O.A. No. EA-1 Approved Airplane Flight Manual Supplement No. 2 to Airplane Flight Manual No. 1640.  
Required when Item 402(h), Altimatic IIIB, is installed. 
 
 (bs) D.O.A. No. EA-1 Approved Airplane Flight Manual Supplement No. 3 to Airplane Flight Manual No. 1640.  
Required when Item 609(b), Oxygen System, is installed. 
 
 (bt) D.O.A. No. EA-1 Approved Airplane Flight Manual Supplement No. 4 to Airplane Flight Manual No. 1640.  
Required when Item 304(c) or 307(a) strobe light is installed. 
 
 (bu) D.O.A. No. EA-1 Approved Airplane Flight Manual Supplement No. 4 to Airplane Flight Manual No. 1545.  
Required when Item 304(c) or 307(a) strobe light is installed. 
 
 (bv) D.O.A. No. EA-1 Approved Airplane Flight Manual Supplement No. 5 to Airplane Flight Manual No. 1334.  
Required when Item 123, Manually Controlled Heated Alternate Engine Induction Air, is installed. 
 
 (bw) D.O.A. No. EA-1 Approved Airplane Flight Manual Supplement No. 8 to Airplane Flight Manual No. 1359.  
Required when Item 123, Manually Controlled Heated Alternate Engine Induction Air, is installed. 
 
 (bx) D.O.A. No. EA-1 Approved Airplane Flight Manual Supplement No. 5 to Airplane Flight Manual No. 1545.  
Required when Item 402(i), Altimatic IIIB1, is installed. 
 
 (by) D.O.A. No. EA-1 Approved Airplane Flight Manual Supplement No. 5 to Airplane Flight Manual No. 1640.  
Required when Item 402(i), Altimatic IIIB1, is installed. 
 
 (bz) D.O.A. No. EA-1 approved Airplane Flight Manual Supplement No. 1770 for Models PA-24-250 and PA-24-260 
Airplane Flight Manuals dated August 8, 1972, revised September 5 and September 27, 1972.  (Copies of 
Supplement No. 1770 dated August 8, 1972, with no revision date are eligible and approved for use.  Copies with 
two revision dates (September 5 and September 27, 1972) are eligible and approved for use.  Copies with only one 
revision date (September 5, 1972) are not eligible for use.)

1A15 Page 20 of 28 
 
Automatic Pilot 
    PA-24 PA-24-250 PA-24-400 PA-24-260 
402. (a) Piper AutoControl, Model AK066, manufactured by 
Mitchell Industries, Inc. in accordance with FAR 
21.303, installed in accordance with Piper Dwg. 21780 
or 22465.  (Weight does not include weight of gyros)  
AutoControl may be overpowered manually by an 
exertion of 16 lb. of force on the control wheel.  S/N 
eligible are 24-1, and 24-103 through 24-3687 only.  
Flight Manual Supplement Items 401(h), 401(i), 
401(j), 401(m), 401(p), 401(t), or 401(w) required with 
this installation.  Course Selector directional gyro 
option not eligible on those aircraft to which Items 
401(h), 401(i), 401(j), or 401(p) are applicable. 
+4.5 lb. (+56.5) (+56.5) - - - - - - - - 
 (b) Piper Altimatic, Model AK083, manufactured by 
Mitchell Industries, Inc. in accordance with FAR 
21.303, installed in accordance with Piper Dwg. 
22545.  (Weight does not include weight of gyros) 
Altimatic may be overpowered as follows:  Exertion of 
16 lb. of force on the control wheel for roll servo, 
exertion of 20 lb. of force fore or aft on the control 
wheel for pitch servo, and in addition, a force of 40 lb. 
on the control wheel to completely disengage the pitch 
servo from the control system.  S/N eligible are  
24-2003, 24-2203, and 24-2299 through 24-3687 only.  
Flight Manual Supplement items 401(q), 401(r), 
401(u), or 401(x) required with this installation. 
+10.5 lb. (+57.8) (+57.8) - - - - - - - - 
 (c) Piper Altimatic II, Model AK089, manufactured by 
Mitchell Industries, Inc. in accordance with FAR 
21.303, installed in accordance with Piper Dwg. 23587 
or 24997.  (Weight does not include weight of gyros) 
Altimatic may be overpowered as follows:  Exertion of 
16 lb. of force on the control wheel for roll servo, 
exertion of 20 lb. of force fore or aft on the control 
wheel for pitch servo, and in addition, a force of 40 lb. 
on the control wheel to completely disengage the pitch 
servo from the control system.  S/N eligible are  
24-2003, 24-2203, and 24-2299 through 24-5034 only.  
Flight Manual Supplement Items 401(y), 401(z), 
401(aa), 401(ab), 401(aj), 401(al), 401(an), 401(aw), 
or 401(bb) required with this installation. 
+13.1 lb.
+17.1 lb.
 
(+56.5) 
- - - - 
(+56.5) 
- - - - 
(+56.5) 
- - - - 
- - - - 
(+81.4) 
 (d) Piper AutoControl II, Model AK065E manufactured 
by Mitchell Industries, Inc. in accordance with FAR 
21.303, installed in accordance with Piper Dwg. 
23619.  (Weight does not include weight of gyros)  
AutoControl II may be overpowered manually by an 
exertion of 16 lb. of force on the control wheel.  S/N 
eligible are 24-2003, 24-2203, and 24-2299 through 
24-5034 only.  Flight Manual Supplement Items 
401(ac), 401(ad), 401(ae), 401(af), 401(ai), 401(am), 
401(ao), 401(ax), or 401(bc) required with this 
installation. 
+4.6 lb. (+55.3) (+55.3) - - - - (+55.3)

Page 21 of 28 1A15 
 
Automatic Pilot (cont.) 
   PA-24 PA-24-250 PA-24-400 PA-24-260 
402. (e) Piper AutoControl III, Model AK161 manufactured by 
Mitchell Industries, Inc. in accordance with FAR 
21.303, installed in accordance with Piper Dwg. 25676 
(Weight does not include weight of gyros).  
AutoControl III may be overpowered manually by an 
exertion of 12 lb. of force on the control wheel.  S/N 
eligible are 24-4247, 24-4300 through 24-4782, and 
24-4784 through 24-4803 only.  Flight Manual 
Supplement Items 401(bf) or 401(bg) required with 
this installation. 
+4 lb. - - - - - - - - - - - - (+113) 
 (f) Piper Altimatic III, installed in accordance with Piper 
Dwg. 25708 (Weight does not include weight of 
gyros).  S/N eligible are 24-4247, 24-4300 through 24-
4782, and 24-4784 through 24-4803 only.  Flight 
Manual Supplement Items 401(bh) or 401(bi) required 
with this installation. 
+18.9 lb. - - - - - - - - - - - - (119.5) 
 (g) Piper AutoControl III, installed in accordance with 
Piper Dwg. 26735 (Weight does not include gyros).  
S/N eligible are 24-4783, and 24-4804 through  
24-5034 only.  Flight Manual Supplement Item 401(bl) 
or 401(bq) required. 
+4 lb. - - - - - - - - - - - - (+113) 
 (h) Piper Altimatic IIIB, installed in accordance with Piper 
Dwg. 26884 (Weight does not include gyros).  S/N 
eligible are 24-4783, and 24-4804 through  
24-5034 only.  Flight Manual Supplement Items 
401(bm) or 401(br) required. 
+19.3 lb. - - - - - - - - - - - - (+119) 
 (i) Piper Altimatic IIIB1, installed in accordance with 
Piper Dwg. 27333-2 (Weight includes Gyros and Turn 
and Bank Instrument).  S/N eligible are 24-4783, and 
24-4804 through 24-5034 only.  Flight Manual 
Supplement Items 401(bx) or 401(by) required. 
+20.2 lb. - - - - - - - - - - - - (94.0) 
      
Miscellaneous Equipment 
601. Heated Pitot Head-Kollsman, Model No. 372D-01, 12 
volt. 
+1 lb. (+99) (+99) (+99) - - - - 
      
602. Heated Pitot Tube Assembly, Piper Dwg. 21301 +1 lb. (+99) (+99) (+99) (+99) 
      
603. Stall warning indicator installation installed in accordance 
with Piper Dwg. 21754. 
Negl. Wt. - - - - Required Required Required 
      
604. Stabilizer guard installation in accordance with Piper 
Dwg. 22004. 
+1 lb. (+255) (+255) - - - - (+255) 
      
605. Manifold pressure gauge.  NOTE 2(k) placard required on 
Model PA-24-400. 
+l lb. - - - - - - - - Required See Item 9(a) 
or 9(c) 
       
606. (a) Piper Radio Coupler per Piper Dwg. 24997 or 23619. +.5 lb. - - - - - - - - (+66) (+66) 
 (b) Piper Radio Coupler per Piper Dwg. 25678.  
NOTE 2(p) placard required. 
+.5 lb. - - - - - - - - - - - - (+66) 
 (c) Piper Radio Coupler per Piper Dwg. 26825.  
NOTE 2(r) placard required. 
+.5 lb - - - - - - - - - - - - (+66)

1A15 Page 22 of 28 
 
Miscellaneous Equipment (cont.) 
   PA-24 PA-24-250 PA-24-400 PA-24-260 
607. (a) Exhaust Gas Temperature Indicator per STC 
SA788WE, installed per Piper Drawing 25287. 
+1 lb. - - - - - - - - (+55) (+55) 
 (b) Exhaust Gas Temperature Indicator per STC 
SA522SW, installed per Piper Drawing 25667. 
+1 lb. - - - - - - - - - - - - (+55) 
 (c) Exhaust Gas Temperature Indicator per STC 
SA1315WE, installed per Piper Drawing 26333. 
+2 lb. - - - - - - - - - - - - (+54) 
 (d) Exhaust Gas Temperature Indicator per STC 
SA1315WE, installed per Piper Drawing 26851. 
+2 lb. - - - - - - - - - - - - (+54) 
        
608. (a) Alternate instrument static air source installed per  
Piper Dwg. 25301 and 26723.  NOTE 2(1) placards 
required. 
Negl. Wt. - - - - - - - -- Elig. Elig. 
       
609. (a) Oxygen System Installation per Piper Dwg. 25342. 
For Model PA-24-260, eligible only on S/N 24-3642, 
24-4000 through 24-4246, and 24-4248 through 
24-4299.  NOTE 2(q) placards required. 
+41.5 lb. - - - - - - - - (+161.2) (+161.2) 
 (b) Oxygen System Installation per Piper Dwg. 25542 or 
25724 or 26682.  For Model PA-24-260, eligible only 
on S/N 24-4247, and 24-4300 through 24-5034.  
NOTE 2(q) placards required. 
+41.5 lb. - - - - - - - - - - - - (+161.2) 
       
610. (a) Auxiliary Power Receptacle Installation per Piper 
Dwg. 24628 (Weight includes Jumper Cable 
Assembly).  For Models PA-24, PA-24-250 and 
PA-24-260, eligible only on S/N 24-2299 through  
24-4246, and 24-4248 through 24-5034. 
+7 lb. (+153.3) (+153.3) (+153.3) (+153.3) 
 (b) Auxiliary Power Receptacle Installation per Piper 
Dwg. 25584 (5 lb. Jumper Cable included - carried in 
baggage compartment).  Eligible only on S/N 24-4247, 
and 24-4300 through 24-5034. 
+6.4 lb. - - - - - - - - - - - - (+121.5) 
        
611. (a) Optional Seating Seat Installation - Fifth and Sixth per 
Piper Dwg. 25302 and 26602.  Eligible only on S/N  
24-4247, and 24-4300 through 24-5034.  NOTE 2(m) 
placard required. 
+7.5 lb. ea - - - - - - - -- - - - - (+148) 
       
612. (a) Front Seat - Vertically adjustable - Left and/or Right 
per Piper Drawing 26971. 
+21.3 lb. - - - - - - - - - - - - (+84.8) 
       
613. (a) Piper Glide Slope Coupler per Piper Dwg. 26729.  
Eligible only on S/N 24-4783, and 24-4804 through  
24-5034.  NOTE 2(s) placard required. 
+1.5 lb. - - - - - - - - - - - - (+61.3) 
       
614. (a) Shoulder Harness per Piper Dwg. 27006.   
Left Front and/or Right Front. +6 lb. ea.
 
- - - - 
 
- - - - 
 
- - - - 
 
(+100) 
  Left Center and/or Right Center +6 lb. ea. - - - - - - - - - - - - (+100) 
        
615. (a) Brake Installation - dual per Piper Dwg. 27062.  
Eligible only on S/N 24-4783, and 24-4804 through  
24-5034. 
+5 lb. - - - - - - - - - - - - (+58)

Page 23 of 28 1A15 
 
Miscellaneous Equipment (cont.) 
   PA-24 PA-24-250 PA-24-400 PA-24-260 
616. (a) Manifold Pressure Gauge per Piper Dwg. 27149. +1 lb. - - - - - - - - - - - - (+66) 
       
617. (a) Balance Weight - Rudder.  Install in accordance with 
Piper Dwg. 27972 or Piper Kit 760 705.  Flight 
Manual Supplement Item 401(bz) and placard NOTE 
2(x) required on Models PA-24-250 and PA-24-260. 
+4.5 lb. (+272.0) (+272.0) - - - - (+272.0) 
       
618. Stabilator Modification.  Modified in accordance with 
Piper Kit 760 747 instructions. 
+7 lb. - - - - (+260.0) - - - - (+260) 
 Change Vne speed to 227 m.p.h. and delete flight manual 
and placard specified with Item 617 (rudder balance 
weight) when Item 617 and Item 618 are both installed.  
NOTE:  This speed change is not approved without 
installation of both items. 
     
 
 
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 the corresponding center of gravity location must include unusable fuel 
(not included in fuel capacity) as follows:  24 lb. at (+90) for Model PA-24-250; S/N 24-2563, and 24-2844 
through 24-3687; and for Model PA-24-260; and 36 lb. at (+90) for Model PA-24-400; S/N 26-2 through  
  26-148. 
 
NOTE 2.  The following placards must be displayed: 
 
  (a) On the instrument panel in full view of the pilot: 
   "THIS AIRPLANE MUST BE OPERATED AS A NORMAL CATEGORY AIRPLANE IN 
 COMPLIANCE WITH THE AIRPLANE FLIGHT MANUAL.  ACROBATICS MANEUVERS 
 (INCLUDING SPINS) PROHIBITED." 
 
  (b) On floor at base of landing gear manual operating lever:  "EMERGENCY GEAR HANDLE". 
 
  (c) On landing gear operating motor access door: 
   "EMERGENCY GEAR EXTENSION.  REMOVE COVER.  EXTENSION INSTRUCTIONS ON 
 REVERSE SIDE".  
 
  (d) At inside of cabin door:  "ENGAGE LATCH BEFORE FLIGHT."  (except Model PA-24-250, S/N 
   24-2844 through 24-3687; Model PA-24, S/N 24-3286 through 24-3687; PA-24-400, S/N 26-2 through  
   26-148; and Model PA-24-260). 
 
  (e) On baggage compartment (Model PA-24, S/N 24-2 through 24-103 only):  "MAXIMUM 
 BAGGAGE 100 POUNDS." 
 
  (f) On baggage compartment (for Models PA-24 and PA-24-250, S/N 24-1, 24-102 through 24-3687; for 
   Model PA-24-400, S/N 26-2 through 26-148; and Model PA-24-260, S/N 24-3642, 24-4000 through  
   24-4246, and 24-4248 through 24-4299):  "MAXIMUM BAGGAGE 200 POUNDS."

1A15 Page 24 of 28 
 
 
NOTE 2.  (g) Unless otherwise specified:  On the instrument panel when Item 402(a) is installed.  When the 
 AutoControl autopilot is equipped with the zero heading directional gyro:  
 
   1. Piper AutoControl (Operating Instructions) 
    "Piper AUTOCONTROL 
    TO ENGAGE:  Push turn control at D. G. in the center knobs.  Then push in engaging  
      control, rock wheel if necessary. 
    TO TURN:  Move turn control in desired direction. 
    FOR HEADING 
        LOCK:  Set D. G. at 0° pull out turn control knob.  Use trim to maintain exact  
      0 ° heading." 
 
   2. On or adjacent to the autopilot engagement control knob:   
     "PIPER AUTOCONTROL.  Push to engage.  Disengage during takeoff and landing." 
 
   3. On or adjacent to the turn control:  "TURN CONTROL.    Pull for direction control on 0° heading  
  only ." 
 
   4. On the face of the directional gyro:  "MODIFIED FOR PIPER AUTOCONTROL" 
 
  When the Auto Control autopilot is equipped with the Course Selector directional gyro: 
 
   1. Piper AutoControl (Operating Instructions) 
    TO ENGAGE:  Push turn control at D. G. in the center knobs.  Then push in engaging 
        control, rock wheel if necessary. 
    TO TURN:  Move turn control in desired direction. 
    FOR HEADING 
        LOCK:  Set course selector and D. G. at magnetic heading.  Pull turn control knob. 
        Use trim knob to maintain heading." 
 
   2. On or adjacent to the autopilot engagement control knob: 
    "PIPER AUTOCONTROL.  Push to Engage.  Disengage during takeoff and landing." 
 
   3. On or adjacent to the autopilot turn control knob: 
    "TURN CONTROL.  Pull for heading lock." 
 
   4. On or adjacent to the D. G. caging knob: 
    "PULL TO SELECT HEADING." 
 
   5. On the face of the directional gyro: 
    "PIPER COURSE SELECTOR."

Page 25 of 28 1A15 
 
 
NOTE 2.  (h) Unless otherwise specified:  On the instrument panel when Item 402(b) or 402(c) is installed. 
 
   1. On or adjacent to the D. G. caging knob: 
    "PULL TO SELECT HEADING." 
 
   2. Adjacent to the pitch control knob: 
     " PULL  
     A LT. 
     HOLD" 
 
   3. "Piper Altimatic Pilot Instructions 
    1. Pilot off during takeoff and landing 
    2. Pilot off above 180 M.P.H. 
    Normal Operations: 
    1. Refer to Flight Manual 
    Emergency: 
    1. Disengage Altimatic Controls 
    2. Altimatic Pilot may be over-powered manually." 
 
   4. Adjacent to the pitch control knob: 
     " UP 
     D N" 
 
  (i) Unless otherwise specified:  On the instrument panel when Item 402(d) is installed. 
   When the AutoControl II autopilot is equipped with the Zero Heading directional gyro: 
 
   1. Piper AutoControl II (Operating Instructions) 
    "PIPER AUTOCONTROL II 
    TO ENGAGE:  Push heading lock button to "OUT" position.  Center turn-trim knob. 
        E ngage roll. 
    TO TURN:  Move turn-trim knob in desired direction. 
    FOR HEADING 
        LOCK:  Set D. G. with magnetic compass, pull knob out, select desired heading, push  
      heading lock button to "IN" position.  Use turn-trim knob to obtain exact  
      h eading. 
    DISENGAGE:  During takeoff and landing." 
 
   2. Adjacent to the autopilot engage knob: 
    "ROLL 
    PUSH TO ENGAGE" 
 
   3. Adjacent to the turn control: 
    "TURN-TRIM" 
 
   4. Adjacent to heading lock knob: 
    "HEADING LOCK" 
 
   5. Adjacent to the D. G. Caging knob: 
    "PULL TO SELECT HEADING" 
 
   6. On the face of the directional gyro: 
    "PIPER COURSE SELECTOR." 
 
  (j) On the fuel valve protector plate (Model PA-24-400, S/N 26-2 through 26-148 only): 
   "DRAIN STRAINER FOR EACH TANK - SELECT EACH TANK - AND LIFT KNOB" 
 
  (k) On instrument panel near manifold pressure gauge (required and eligible on Model PA-24-400 only):  
 "DO NOT EXCEED 24 INCH MP BELOW 2000 RPM."

1A15 Page 26 of 28 
 
 
NOTE 2.  (l) In view of the pilot on Model PA-24-260 and Model PA-24-400 aircraft equipped with alternate 
 instrument static air source, Item 608(a): 
 
   1. "INSTRUCTIONS FOR USE OF  
    ALTERNATE STATIC SOURCE 
    1. IN CASE OF STATIC PRESSURE 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  
   U SED: 
 (On Model INDICATOR READS ACTUAL 
 PA-24-260 only, per 105 MPH IAS 100 MPH IAS 
 Piper Dwg. 25296) 136 MPH IAS 130 MPH IAS 
  158 MPH IAS 150 MPH IAS 
  178 MPH  IAS 170 MPH IAS 
 
 (On Model INDICATOR READS ACTUAL 
 PA-24-400 only, per 103 MPH IAS 100 MPH IAS 
 Piper Dwg. 25297) 137 MPH IAS 130 MPH IAS 
  158 MPH IAS 150 MPH IAS 
  180 MPH  IAS 170 MPH IAS 
 
   2. On instrument panel above alternate static source actuating valve: 
    " 
     "↓ALTERNATE STATIC SOURCE 
                 PULL AFT TO OPEN" 
     (For Models PA-24-400 and PA-24-260, S/N 24-3642, 24-4000 through 24-4782, 
      24-4784 through 24-4803) 
     On throttle quadrant aft of alternate static source actuating valve: 
       O FF 
 
       A LT 
            STATIC 
       A IR 
 
        ON 
     (For Model PA-24-260, S/N 24-4783, and 24-4804 through 24-5034) 
 
  (m) On baggage compartment (For Model PA-24-260, S/N 24-4247, and 24-4300 through 24-5034). 
   "Maximum baggage and/or Passenger Weight 250 lb. in Baggage area, including seats.  See Weight  
 and Balance." 
 
  (n) On inner surface of Emergency Exit door.  "Emergency Exit", "Hold Knob Up", "Turn Latch 
 Clockwise".  Required on Model PA-24-260, S/N 24-4247, and 24-4300 through 24-5034. 
 
  (o) Unless otherwise specified:  On the instrument panel in front of the pilot when Item 402(f) is installed. 
 
   1. On left control wheel: 
    "NOSE  "DOWN 
    TRIM"  UP" 
 
   2. On left control wheel: 
       "AUTOFLITE PUSH "OFF"" 
 
   3. On instrument panel: 
       "AUTOFLITE ON/OFF TRIM"

Page 27 of 28 1A15 
 
 
NOTE 2.  (p) On instrument panel centered above Radio Coupler Switch: 
    "OMNI-1"  "OFF"  "OMNI-2" 
 
  (q) Required, when Item 609 is installed, at each Oxygen outlet: 
    "NO SMOKING WITH OXYGEN IN USE." 
    at oxygen control knob: 
    " PULL ON, OXYGEN" 
 
  (r) On instrument panel beside radio coupler switch 
    "A/P NAV SEL 
     O N 
           OFF 
     O N" 
 
  (s) On instrument panel beside the glide slope indicator light. 
 
     " G/S 
        ENGAGED" 
 
  (t) On Model PA-24-260, S/N 24-4783, and 24-4804 through 24-5034, equipped with turbocharged  
 engine (Item 109(h)) 
 
   1. On overhead panel: 
 
    "FUEL BOOST PUMP ON ABOVE 15,000' MSL AND 75% POWER" 
 
    "TURBOCHARGER OPERATION POWER LIMITS:  TAKEOFF AND 
    MAX. ONT. -29.0 MAP AT 2700 RPM" 
 
    "REDUCE Vne 6 MPH PER 1000' ABOVE 18,000' MSL" 
 
    "FOR EMERGENCY DESCENT IDLE POWER GEAR DOWN IAS 150 MPH" 
 
    "OPERATION ABOVE 12,000' PROHIBITED WITHOUT SATISFACTORY 
    OXYGEN SUPPLY AVAILABLE FOR ALL OCCUPANTS" 
 
    "FLIGHT OPERATION OVER 25,000' IS PROHIBITED" 
 
   2. On fuel filler doors: 
    "100/130 OCTANE MINIMUM" 
 
  (u) On left window molding in full view of the pilot when Item 304(c) is installed: 
 
"WARNING 
 TO AVOID OPTICAL ILLUSION AND SEVERE 
 VERTIGO TURN ANTI-COLLISION LIGHTS 
 OFF UPON ENTERING CLOUDS, FOG OR HAZE." 
 
  (v) On left window molding in full view of the pilot when item 307(a) is installed: 
 
"WARNING 
  TURN OFF STROBE LIGHTS WHEN TAXING IN  
  VICINITY OF OTHER AIRCRAFT, OR DURING  
  FLIGHT THROUGH CLOUD, FOG OR HAZE. 
 
  STANDARD POSITION LIGHTS TO BE ON FOR  
  ALL NIGHT OPERATIONS."

1A15 Page 28 of 28 
 
 
NOTE 2.  (w) 1. On instrument panel in full view of the pilot: 
                           "CAUTION 
    This airplane is equipped with a manually 
    controlled heated alternate engine induction 
    air system.  Alternate air is available only by  
    pulling ALT AIR control full on.  See Flight 
    Manual Supplement." 
 
   2. On instrument panel above the induction air control: 
     " ALT AIR 
           Pull 
           Open" 
 
  (x) On airspeed indicator*: 
   "DO NOT EXCEED 203 MPH CAS" 
 
   * For Models PA-24-250 and PA-24-260 unless Kit 760 705 and Kit 760 747 are installed. 
 
  (y) On instrument panel (For Models PA-24-250 and PA-24-260 
   equipped with fuel injected engine - Item 109(e), 109(f), 109(g) or 109(h)): 
 
  "WARNING - UNCOORDINATED MANEUVERS, 
  INCLUDING LONG SIDE SLIPS AND FAST 
  TAXI TURNS JUST PRIOR TO TAKEOFF,  
  MAY CAUSE LOSS OF POWER, ESPECIALLY  
  IF FUEL TANK IN USE IS LESS THAN 
  HALF FULL." 
 
  (z) On instrument panel (Model PA-24-400): 
 
  "WARNING - UNCOORDINATED MANEUVERS, 
  INCLUDING LONG SIDE SLIPS AND FAST 
  TAXI TURNS JUST PRIOR TO TAKEOFF, 
  MAY CAUSE LOSS OF POWER, ESPECIALLY  
  IF FUEL TANK IN USE IS NOT FULL." 
 
 
 
 
 
...END...
```

## ADs (52, first 50, 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 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 2012-17-06](https://openairdocs.org/ad/2012-17-06): Flight Controls · Piper PA-24, PA-24-250 and PA-24-260. Effective Oct 22, 2012
- [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 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 99-05-09](https://openairdocs.org/ad/99-05-09): Induction Air Filter · Piper PA-23-235, PA-23-250, PA-23-250 (Navy UO-1) and 20 more. Effective Mar 19, 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 91-21-09](https://openairdocs.org/ad/91-21-09): Air Induction System · Piper PA-24-260. Effective Nov 29, 1991
- [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 81-15-03](https://openairdocs.org/ad/81-15-03): Engine Inlet Air Filters · Replace existing engine induction air filter (Brackett Aero Filters STC SA693CE or SA71GL). Effective Jul 20, 1981
- [AD 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 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 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 76-19-07](https://openairdocs.org/ad/76-19-07): Stabilator Weight Assembly · Piper PA-24-250 and PA-24-260. Effective Sep 29, 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 75-12-06](https://openairdocs.org/ad/75-12-06): Fin Forward Spar · Piper PA-24, PA-24-250, PA-24-260 and 1 more. Effective Jun 5, 1975
- [AD 75-05-02](https://openairdocs.org/ad/75-05-02): Engine Oil · Beryl D Shannon Aviation Specialties Engine Crankcase… (D'Shannon Products STC SA2653WE). Effective Feb 21, 1975
- [AD 72-22-05](https://openairdocs.org/ad/72-22-05): Operation Limitation Placard · Piper PA-24, PA-24-250 and PA-24-260. Effective Dec 26, 1974
- [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 68-13-03](https://openairdocs.org/ad/68-13-03): Fuel Cell Collapse · Piper PA-24 and PA-24-250
- [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 66-30-07](https://openairdocs.org/ad/66-30-07): Fuel Purge Valve Hose Assembly · Piper PA-24-400. Effective Dec 23, 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 65-25-03](https://openairdocs.org/ad/65-25-03): Nose Landing Gear Drag Link Clevis · Piper PA-24 and PA-24-250. Effective Dec 10, 1965
- [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 64-22-03](https://openairdocs.org/ad/64-22-03): Landing Gear Safety Switch · Piper PA-24 and PA-24-250. Effective Sep 28, 1964
- [AD 64-10-04](https://openairdocs.org/ad/64-10-04): Carburetor Air Box Deflector Vanes · Piper PA-24-250. Effective May 12, 1964
- [AD 63-27-03](https://openairdocs.org/ad/63-27-03): Landing Gear Retraction Motor Circuit · Piper PA-24 and PA-24-250. Effective Jan 23, 1964
- [AD 62-26-05](https://openairdocs.org/ad/62-26-05): Exhaust System · Piper PA-24 and PA-24-250. Effective Dec 5, 1962
- [AD 62-10-03](https://openairdocs.org/ad/62-10-03): Aileron Counterweight Bay Rework · Piper PA-24 and PA-24-250. Effective Apr 26, 1962
- [AD 61-20-02](https://openairdocs.org/ad/61-20-02): Exhaust Stack Reinforcement · Piper PA-24-250. Effective Oct 20, 1961
- [AD 61-16-06](https://openairdocs.org/ad/61-16-06): Fuel Selector Valve Handles · Piper PA-24 and PA-24-250 with STC SA4-1235 or SA4-1351. Effective Aug 31, 1961
- [AD 60-24-03](https://openairdocs.org/ad/60-24-03): Fuel Vent Tubes · Piper PA-24 and PA-24-250. Effective Dec 19, 1960
- [AD 59-26-02](https://openairdocs.org/ad/59-26-02): Two Fuel Cell Vent Tubes · Piper PA-24 and PA-24-250
- [AD 59-13-02](https://openairdocs.org/ad/59-13-02): Aileron Balance Weight · Piper PA-24 and PA-24-250
- [AD 59-12-09](https://openairdocs.org/ad/59-12-09): Control Wheel Sprocket Stud · Piper PA-24 and PA-24-250. Effective Jun 30, 1959
- [AD 59-07-05](https://openairdocs.org/ad/59-07-05): Oil Cooler Lines Clearance · Piper PA-24

All 52: https://openairdocs.org/tcds/1A15/ads.md

## Registered aircraft by registry model (OpenAirDocs)

- [Piper PA-24-250](https://openairdocs.org/model/piper-pa-24-250): 1,222 aircraft (registry code 7102404)
- [Piper PA-24-260](https://openairdocs.org/model/piper-pa-24-260): 590 aircraft (registry code 7102406)
- [Piper PA-24](https://openairdocs.org/model/piper-pa-24): 345 aircraft (registry code 7102402)
- [Piper PA-24-400](https://openairdocs.org/model/piper-pa-24-400): 75 aircraft (registry code 7102408)

## STCs approved under this data sheet (442, 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 SA04075CH](https://openairdocs.org/stc/SA04075CH): Installation of Dynon EFIS-D10A EAA sales kit part number 102778-000. Dynon Avionics 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 SA5758SW](https://openairdocs.org/stc/SA5758SW): Install ALCOR fuel flow/totalizer system 24606 which includes transducer 86216 24606 indicator and related hardware.. Alcor LLC
- [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 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 SA01757WI](https://openairdocs.org/stc/SA01757WI): To allow the use of UL91 or UL94 (minimum) grade aviation fuel. Swift Fuels LLC
- [STC SA01941LA](https://openairdocs.org/stc/SA01941LA): Installation of stabilizer trim handle and cabin door handle. McFarlane Aviation LLC
- [STC SA00343AT](https://openairdocs.org/stc/SA00343AT): Installation of engine cowl and full length gear doors and relocation of engine oil cooler and replacement exhaust system. For PA-24-250, S/N 24-103 and up; for PA-24-260, S/N 24-3642, 24-4000 to 24-4782 and 24-4784 to 24-4803.. Air Comanche Performance
- [STC SA01082AT](https://openairdocs.org/stc/SA01082AT): Installation of new fiberglass cowling, full length gear doors, relocation of engine oil cooler and replacement of the exhaust system. S/N 24-1 and u. Aire Comanche Performance
- [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 SA2359WE](https://openairdocs.org/stc/SA2359WE): Installation of Turbocharged Lycoming 1O-720-A1A engine. TALCO Aviation
- [STC SA811WE](https://openairdocs.org/stc/SA811WE): Installation of turbocharged Lycoming IO-540-C1B5 or -C1C5 engine.. 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 SA01435LA](https://openairdocs.org/stc/SA01435LA): Installation of engines modified with Firewall Forward Technologies LLC modified camshaft. Centri-Lube Technologies LLC
- [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 SA11137SC](https://openairdocs.org/stc/SA11137SC): Installation of Plane-Power ALT-FLX alternator. Hartzell Engine Technologies, LLC
- [STC SA00424AT](https://openairdocs.org/stc/SA00424AT): Installation of flap gap seals.. Whelen Aerospace Technologies
- [STC SA00426AT](https://openairdocs.org/stc/SA00426AT): Installation of a composite WHOLLEY COWL.. Whelen Aerospace Technologies
- [STC SA3077SO](https://openairdocs.org/stc/SA3077SO): Installation of 'speed spats' main landing gear fairings and/or installation of 'Comanche speed slipper' nose gear fairing.. Whelen Aerospace Technologies
- [STC SA3281SO](https://openairdocs.org/stc/SA3281SO): Installation of flap bracket fairings.. Whelen Aerospace Technologies
- [STC SA1845WE](https://openairdocs.org/stc/SA1845WE): Installation of Vibration Isolation Products (VIP) engine mount P/N VIP-50804-20 on various aircraft as shown on FAA Approved Model List (AML) No. SA1845WE.. FTG Inc.
- [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 SA00954WI](https://openairdocs.org/stc/SA00954WI): Installation of Concorde RG Series Batteries in Piper Single Engine Airplanes.. Aero-Mach Wilco LLC
- [STC SA01967WI](https://openairdocs.org/stc/SA01967WI): Use of GAMI G100UL High Octane Unleaded Avgas. General Aviation Modifications Inc.
- [STC SA00618AT](https://openairdocs.org/stc/SA00618AT): Installation of a stabilator modification kit.. Whelen Aerospace Technologies

All 442: https://openairdocs.org/tcds/1A15/stcs.md

---
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