DEPARTMENT OF TRANSPORTATION

FEDERAL AVIATION ADMINISTRATION

TYPE CERTIFICATE DATA SHEET NO. 1A15	1A15
Revision 32
PIPER
PA-24
PA-24-250
PA-24-260
PA-24-400
August 2, 1985	

This data sheet which is a part of type certificate No. 1A15 prescribes conditions and limitations under which the product for which the type certificate was issued meets the requirements of the Civil Air Regulations.

Type Certificate Holder 		PIPER AIRCRAFT CORPORATION
						P.O. Box 1328
						Vero Beach, Florida 31960

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 rpm (180 hp)

	Airspeed Limits 			V ne 	(Never Exceed) 				202 mph 		(175 knots)
							V no		(Maximum Structural Cruise) 		160 mph 		(139 knots)
							V p 		(Maneuvering) 					154 mph 		(134 knots)
							V fe 		(Flaps Extended) 				125 mph 		(108 knots)
							V le 		(Landing Gear Extended) 			125 mph 		(108 knots)
															Serial Nos. 24-2 thru 24-102 only
																150 mph 		(130 knots)
															Serial Nos. 24-1 thru 24-103 and up)

	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.)

Aircr aft Weight				*** CG Figure to be inserted
	(lb. )
2550
2206
1900
82.0
83.0
89.0
94.0
							Inches Aft or Datum

1A15																			Page 2

	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 (+142)
							100 lb. 	(Serial No. 24-2 through 24-102 only)
							200 lb. 	(Serial No. 24-1, 24-103 and up)

	Fuel Capacity 				60 gallons 		(Two wing tanks) (+90)

	Oil Capacity 				2 gallons (+25) 		(+24 when Item 111 is installed.)
	
	Control Surface Movements 	Main Surfaces 		Aileron 			19° Up 		15° Down
											Horizontal T.E.		11° Up 		5° Down
												(Serial No. 24-2 thru 24-102)
											Horizontal T.E.		13° Up 		5° Down
												(Serial No. 24-1, 24-103 and up)
											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 and up

	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), 401(a), (d) or (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 rpm (250 hp)

	Airspeed Limits 			V ne 	(Never Exceed)*** 			203 mph 		(177 knots)
									*** See item 618 for approved speed increase
							V no 	(Maximum Structural Cruise) 	180 mph 		(156 knots)
							V le 		(Landing gear extended) 		150 mph 		(130 knots)
							V p 		(Maneuvering) 				144 mph 		(125 knots)
							V fe 		(Flaps Extended) 			125 mph 		(108 knots)

1A15																			Page 3

	Center of Gravity 			Serial No. 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.
							Serial No. 24-2003, 24-2299 and up:
							(+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.)

							*** CG Figure to be inserted
Aircraft Weight (lb.)
2900	2600	2000
Inches Aft or Dat um
Serial No. 24-2003, 24-2299 and up
80.5	82.5	86.0 	93.0
Aircraft Weight (lb.)
2800	2400	1900
Inches Aft or Datum
Serial No. 24-1, 24-103 thru 24-2248
Except 24-2003
80.5	82.5	87.7	93.0

	Empty Weight C. G. Range 	None.

	Maximum Weight 			2800 lb. 		(Serial No. 24-1, 24-103 through 24-2298 except 24-2003)
							2900 lb. 		(Serial No. 24-2003, 24-2299 and up)

	Number of Seats 			4 			(2 at +85, 2 at +118.5)

	Maximum Baggage 			200 lb. 		(Rear compartment) (+142)

	Fuel Capacity 				60 gallons 	(Two 30 gallon Wing Tanks) (+90) (Serial No. 24-1, 24-103 through
											24-2843 except 24-2563)
							56 gallons 	(Two 28 gallon Wing Tanks) (+90) (Serial No. 24-2563, 24-2844 and up)
											(See NOTE 1 for unusable fuel)
							(See Item 112 for auxiliary fuel tanks)

	Oil Capacity 				3 gallons 		(+28)

	Control Surface Movements 	Main Surfaces 		Aileron 				19° Up 		15° Down
											Horizontal T.E. 		13° Up 		5° Down
												(Serial No. 24-1, 24-103 thru 24-2843 except 24-2563)
											Horizontal T.E. 		14° Up 		4° Down
												(Serial No. 24-2563, 24-2844 up)
											Rudder 				25° Left 		25° Right
											Flap 								27° Down
												(Serial No. 24-1, 24-103 thru 24-2843 except 24-2563)
											Flap 								32° Down
												(Serial No. 24-2563, 24-2844 and up)

							Anti-Servo tab (with stabilizer in
								neutral position) 					7° Up 		13° Down
									(Serial No. 24-1, 24-103 thru 24-2843 except 24-2563)
									(Serial No. 24-2563, 24-2844 and up)
																7° Up 		15° Down
1A15																			Page 4

	Serial Numbers Eligible 		24-1, 24-103 and up

	Required Equipment 			In addition to the pertinent required basic equipment specified in CAR 3, the following
							items of equipment must be installed:
							3(a) or (b), 103, 106, 107(a) or (b), 201(a), 202(b), 205, 206(a), 301(a) or (b), 302(a),
							401(c) or (f), or (n), or (s) or (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 AP-24-400, 4 PCLM (Normal Category) Approved December 27, 1963
	
	Engine					Lycoming IO-720-A1A

	Fuel						100/130 min. grade aviation gasoline
	
	Engine Limits 				All operations, 2650 rpm (400 hp)
	
	Airspeed Limits 			V ne 	(Never Exceed) 			250 mph 		(219 knots)
							V no 	(Maximum Structural Cruise) 	210 mph 		(182 knots)
							V p 		(Maneuvering) 				160 mph 		(139 knots)
							V le 		(Landing Gear Extended) 		150 mph 		(130 knots)
							V fe 		(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.)

							****CG Figure to be inserted
Inches Aft or Datum
Ai rcraft Wei ght
(lb. )
3600
3300
2500
77.0
81.5
84.8
90.0

	Empty Weight C. G. Range 	None

	Maximum Weight 			3600 lb.

	Number of Seats 			4 	(2 at +85, 2 at +118.5) 	(Serial No. 26-2 through 26-124)
							4 	(2 at +85, 2 at +120.5) 	(Serial No. 26-125 and up)

	Maximum Baggage 			200 lb. 	(Rear compartment)	(+142)

1A15																			Page 5

	Fuel Capacity 				130 gallons (124 gallon usable)
							Two 30 gallon wing tanks (+90)
							Two 35 gallon wing tanks (+94)
							See NOTE 1 for unusable fuel data

	Oil Capacity 				17 quarts (+21) (12 quart 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 Tab4					.5° Up 			9° Down
							(Stabilizer Neutral)

	Serial Numbers Eligible 		26-2 and up

	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, 605.

IV. Model AP-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), (g), for additional optional engines and 109(h)
						for optional turbocharged engine)

	Fuel 					91/96 min. grade aviation gasoline (normally aspirated engine)
						100/130 min. grade aviation gasoline (turbocharged engine)

	Engine Limits 			All operations, 2700 rpm (260 hp)

	Airspeed Limits 		V ne 	(Never Exceed)*** 				203 mph 		(177 knots)
								*** See item 618 for approved speed increase
						V no 	(Maximum Structural Cruise) 		180 mph 		(156 knots)
						V le 		(Landing Gear Extended) 			150 mph 		(130 knots)
						V p 		(Maneuvering) 					144 mph 		(125 knots)
						V fe 		(Flaps Extended) 				125 mph 		(108 knots)
						V p 		(Maneuvering) 					150 mph 		(130 knots)
						* Serial No. 14-3642, 24-4000 through 24-4782 and 24-4784 through 24-4803
						** Serial No. 24-4783, 24-4804 and up.

1A15																			Page 6

	Center of Gravity		 Serial No. 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.)
						
						****CG Figure to be inserted
2000
2600
2900
Inches Aft of Datum
80.5
86.0
82.5
93.0

	Center of Gravity 		Serial No. 24-4247, and 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
						Serial No. 42-4783 and 24-4804 and up (with normally aspirated engine only)
	(C. G. Range) 			(+89.6) 	to 	(+93.0) 	at 	3200 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.)

3200						*** CG Figure to be inserted
Serial No. 24-4783
and 24-4804 and up
2000
2600
3100
80.5
82.5
88.4
89.6
93.0
Aircraft Weight
(lb.)
Serial No. 24-4247;
24-4300 through
24-4782; 24-4784
t hrough 24-4803.
Inches Aft of Datum

1A15																			Page 7

							Serial No. 24-4783 and 24-4804 and up (with turbocharged engines only)
							(+87.6) 	to 	(+93.0) 	at 	3200 lb.
							(+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				** CG Figure to be inserted
2800
3200
80.5
83.2
87.6
93.0
Air craft Weight
(lb.)
Inches Aft of Datum

	Empty Weight C. G. Range 	None

	Maximum Weight 			2900 lb. Serial No. 24-3642, 24-4000 through 24-4246, and 24-4248 through 24-4299.
							3100 lb. - Takeoff, 2945 lb. - Landing Serial No. 24-4247, 24-4300 through 24-4782,
							and 24-4784 through 24-4803.
							3200 lb. - Takeoff, 3040 Landing, Serial No. 24-4783, 24-4804 and up.

	Number of Seats 			4 	(2 at +85, 2 at +120.5); or
							On Serial No. 24-4247 and 42-4300 and up when Item 611 is installed.
							6 	(2 at +85, 2 at +120.5, 2 at +148)

	Maximum Baggage 			200 lb. 	(Rear compartment) (+142) Serial No. 24-3642, 24-4000 through 24-4246, and
							24-4248 through 24-4299.
							250 lb. 	(Max. baggage and/or passenger allowance in baggage area, including seats)
							(+142) Serial No. 24-4247, and 24-4300 and up.

	Fuel Capacity 				56 gallons 	(Two 28 gallon wing tanks) (+90)
							(See NOTE 1 for unusable fuel)
							(See Item 112 for auxiliary fuel tanks)

	Oil Capacity 				3 gallons 	(+28)

	Control Surface Movements	Main Surfaces 			Aileron 			19° Up 			15° Down
												Stabilator (L.E.) 1	4° Up 			4° Down
												Rudder 			25° Left 			25° Right
												Flap 								32° Down
							Anti-Servo Tab
							(Stabilizer Neutral)						 7° Up 			15° Down

	Serial Numbers Eligible 		24-3642, 24-4000 and up

	Required Equipment 			In addition to the pertinent required basic equipment specified in CAR 3, the following
							items of equipment must be installed:
							On Serial No. 24-3642, 240-4000 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), 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.

1A15																			Page 8

	Required Equipment (cont'd) 	On Serial No. 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), 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.
							On Serial No. 24-4783, 24-4804 and up (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), 410(bz).
							On Serial No. 24-4783, 24-4804 and up (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,
							208(a), 124, 302(a), 305(c), 401(pb), 603, 616(a), 617(a), 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 Serial No. 24-4247
							and 24-4300 and up 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 to 3-12, inclusive).
							Type Certificate issued and the DMCR authorized to issue airworthiness certificates
							under the delegation option provisions of Part 410 of Regulations of the Administrator.
							Piper Aircraft Corporation authorized to issue airworthiness certificates under the
							delegation option authorization procedures of Subpart J of Part 21 of the Federal
							Aviation Regulations as of November 22, 1965.

	Production Basis 			None. Prior to original certification of each aircraft manufactured subsequent to
							August 3, 1984, an FAA representative must perform a detailed inspection for
							workmanship, materials, and conformity with the approved technical data, and a check
							of the flight characteristics.

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			63 lb. 		(+3)		 - - - - 			- - - - 			- - - -
		model HC92ZK-8D, blades model 8447A-12A
		Pitch: High 27°, low 13°, at 30 in. sta.'
		Diameter Not over 72¼ in., not under 70.5 in.
	(b)	Governor Assembly: Woodward 210185, 210260, 			5 lb. 		(+39) 		- - - - 			- - - - 			- - - -
		210305, or Hartzell D1-1, D1-5.
	(c)	Deleted May 5, 1958.
		Included in Item 4)
2. 	(a) 	Propeller - McCauley constant speed controllable, 			60 lb. 		(+3)		 - - - - 			- - - - 			- - - -
		hub model 2D36C14, blades model 78KM-4.
		Pitch: High 27.5°, low 12.7°, at 330 in. sta.
		Diameter: Not over 74 in. not under 72 in.
		Item 401(b) or 401(1) required.
	(b) 	Governor Assembly: Woodward 210185, 210250, 			5 lb.		(+39)		- - - - 			- - - - 			- - - -
		210260, 210305 or Hartzell D1-1, D1-5.

1A15																			Page 9

														PA-24 	PA-24-250 		PA-24-400 		PA-24-260
3. 	(a)	Propeller - Hartzell constant speed controllable, hub			63 lb.		 - - - - 		(+1.5) 		- - - -			 - - - -
		model HC8XK-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°
		Diameter: Not over 77 7/16 in., not under 76 in.
		Placard required: (For O-540A1A engine only)
		"Avoid continuous operation between 2225 and 2275
		rpm."
	 (b)	Governor Assembly: Woodward						5 lb.		 - - - - 		(+10) 			- - - - 			- - - -
		Woodward 210185 or 210250 or
		Hartzell B-4-2.

4.	(a)	Hartzell spinner dome C-888 and bulkhead adapter			3 lb. 		(+3) 		(+1.5) 		- - - - 			- - - -
		C-885 (Eligible on Items 1(a) and 3(a) only)
	(b)	Piper spinner dome and bulkhead adapter 				3 lb. 		(+3) 		(+1.5) 		- - - - 			(+1.5)

5. 	(a) 	Propeller - McCauley constant speed controllable, hub		60 lb. 		- - - - 		(+1.5) 		- - - - 			- - - -
		model 2D36C28, blades model 80MM-6.
		Pitch: High 32°, low 15.7° at 30 in. sta.
		Diameter: Not over 74 in., not under 73 in.
		Placard required: (For O-540A1A engine only)
		"Avoid continuous operation between 2225 and
		2275 rpm." Item 401 (e), (g) or (o) required.
	(b)	Woodward hydraulic governor assembly Mode				l5 lb.		 - - - - 		(+10) 			- - - -			- - - -

6.		A210185 per PAC Dwg. 21764-3 or Model A210305
		per PAC Dwg. 21764-4 when Item 5(a) is installed.
		Deleted October 24, 1960.

7. 	(a)	Propeller - Hartzell constant speed controllable, hub			88 lb. 		- - - - 		- - - - 			(-3.5)			 - - - -
		model HC-A3VK-4, blades model V8433-7.
		Pitch: High 36°, low 14° at 30 in. sta.
		Diameter: Not over 77 5/8 in., not under 75 5/8 in.
		See NOTE 2(k)
	(b)	Governor Assy. Hartzell F-4-1 per PAC					6 lb. 		- - - - 		- - - - 			(+3.5) 		- - - -
		Dwg. 24622-2.

8.	Spinner Dome per Piper Dwg. 22752-2 and spinner				4 lb. 		- - - -		 - - - - 			(-3.5) 			- - - -
	Bulkhead Adapter per Piper Dwg. 2274-2.

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. sta.
		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 RPM
		above 25 inch manifold pressure" must be displayed
		near the manifold pressure gauge.

1A15																			Page 10

														PA-24 	PA-24-250 		PA-24-400 		PA-24-260
9. 	(b)	Governor Assy. Hartzell F-4-4 per PAC Dwg. No. 			6 lb. 		- - - - 	 	- - - -			- - - - 			(+10)
		24622-5 or F-4-4A per PAC Dwg. No. 24622-10
	(c)	Propeller - Hartzell constant speed controllable, hub			56 lb. 		- - - - 	 	- - - - 			- - - -			(+1.5)
		model HC-C2YK-1B, blades model 8467-7R
		Pitch: High 32° to 34°, low 15° at 30 in. sta.
		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 rpm
		above 25 inch manifold pressure", must be displayed
		near the manifold pressure gauge.
	(d)	Propeller - Hartzell constant speed controllable, hub			59 lb. 		- - - - 	 	- - - -			- - - -			(-3.4)
		model HC-E2YR-18, blades model 8467-7R
		Pitch at 30 in. Station:
		High 32° to 34°, low 15°
		Diameter: not over 77 in., not under 75 in.
	(e)	Spinner dome PAC 26326 with bulkhead adapter PAC		4 lb. 		- - - -		- - - - 			- - - - 			(-4.1)
		26313
	(f)	Propeller - Hartzell constant speed controllable, hub			59 lb. 		- - - - 		- - - - 			- - - - 			(-3.4)
		model HC-E2YR-18, blades model 8467-7R
		Pitch at 30 in. Station:
		High 32° to 34°, low 13.5° +.3° -0°
		Diameter: Not over 77 in., not under 75 in.
	(g)	Propeller - Hartzell constant speed controllable, Hub			59 lb.		- - - - 		- - - - 			- - - - 			(-3.4)
		Model HC-E2YR-1BF, Blades Model F8467-7R
		Pitch at 30 in. Station: High 32° to 34°, low 15°
		Diameter: Not over 77 in., not under 75 in.
	(h)	Propeller - Hartzell constant speed controllable, Hub			59 lb. 		- - - - 		- - - - 			- - - - 			(-3.4)
		Model HC-E2YR-1BF, Blades Model F8467-7R
		Pitch at 30 in. Station: High 32° to 34°
		low 13.5° +.3° -0°
		Diameter: Not over 77 in., not under 75 in.

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			2 lb. 		(+38) 		- - - - 			- - - - 			- - - -
	478360

102.	Fuel pump, engine-driven
	(a)	AC No. 5594068 								3 lb. 		(+33) 		- - - - 			- - - - 			- - - -
	(b)	AC No. 5623467 (Lycoming P/N 74060) or				1.5 lb. 	(+33) 		- - - - 			- - - - 			- - - -
		AC No. 5656880 (Lycoming P/N 74082) or
		AC No. 6440295 (Lycoming P/N 75246)

103.	Oil radiator, Harrison Mod. AP07AU06-03 					3 lb. 		(+12) 		(+10.5)		- - - - 			(+10.5)

104. 	Starter, Delco-Remy, Mod. 1109673 or 1109689, 12 volt			19 lb. 		(+15) 		- - - -			- - - - 			- - - -
	geared (2.27:1)

1A15																			Page 11

Engine and Engine Accessories - Fuel and Oil System 						PA-24 	PA-24-250 		PA-24-400 		PA-24-260
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) 			(+43)

106.	2 fuel pumps, elec. aux. Bendix Mod. 476087 or 478360. 			2 lb. each 	- - - - 		(+43) 			- - - - 			(+60)
	Required except when Item 109(e) or 109(f) is installed.

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				1.5 lb. 	- - - - 		(+39.5) 		- - - - 			- - - -
		AC No. 5656880 (Lycoming P/N 74083)
	 (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, 1009504, or			18 lb. 		- - - - 		(+13.5) 		- - - - 			(+13.5)
		1109511; 12 Volt, Geared 3.38:1. On Model
		PA-24-260 starter eligible only Model 1109511
		starter eligible
	 (b)	Starter, Prestolite Model MZ-4206, 12 Volt,				17 lb. 		- - - - 		- - - - 			- - - - 			(+13.5)
		Geared  3.38:1

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-540A1D5 (Item 401(f), 401(n) and 401(s) required 		Neg.Wt.Ch. 	- - - - 		Elig. 			- - - - 			- - - -
	(e) 	IO-540-C1B5 (Fuel injection installed per PAC 			Neg. Wt.Ch.	- - - - 		Elig. 			- - - - 			- - - -
		Dwg. No. 23144) (Items 113, 114(a) or 114(b)
		and 401(v) required).
	 (f)	IO-540-D4A5 (Fuel injection installed per PAC 			Use Actual	- - - -		 - - - -			- - - - 			Elig.
		Dwg. No. 24923) (Items 113, 114 and 104(ak) or 			Wt. Ch.
		401(ba) required).
	 (g)	IO-540-N1A5 								Use Actual	- - - - 		- - - - 			- - - - 			Elig.
												Wt. Chg.
	(h)	IO-540-R1A5 (Turbocharged - Items 122a required) 			Use Actual	- - - -		- - - - 			- - - - 			Elig.
		installed per PAC Dwg. 27137 						Wt. Chg.

110 	Carburetor air filter, Fram Paper Filter No. CA-161-PL.			Neg.Wt.Ch.	- - - -		Elig. 			- - - - 			Elig.

111.	Engine relocated per PAC Dwg. No. 22000. Eligible on 			Use Actual 	Elig.		 - - - - 			- - - - 			- - - -
	Model PA-24, Serial No. 24-1684 and up. Item 401(k) required. 		Wt. Change
	(a)	Lycoming O-360-A1A

1A15																			Page 12

111. 	(cont'd)
	(b)	Lycoming O-360-A1A
		(Limits same as for O-360-A1A)
		The following is the new arm aft datum for each item of equipment that is relocated when Item 111 is installed:
			Item 			Arm
			1(a) 			(+1.5)
			1(b) 			(+35)
			2(a) 			(+1.5)
			2(b) 			(+35)
			4 			(+1.5)
			6(a) 			(+1.5)
			6(b) 			(+35)
			102 			(+32.5)
			103 			(+10.5)
			104 			(+13.5)
			105 			(+31.5)
			301(a) 		(+11.5)
			301(b) 		(+11.5)

Engine and Engine Accessories - Fuel and Oil System (cont'd) 					PA-24 	PA-24-250 		PA-24-400 		PA-24-260
112.	Two 15 gallon auxiliary wing fuel tanks, Eligible Mode			l13 lb. 	- - - - 		(+97) 			- - - - 			(+97)
	PA-24-250 and Model PA-24-260, Serial No. 24-2003,
	24-2299 and up.

113.	Fuel Pump, boost, rotary motor-driven
	(a)	Bendix No. 480518-1 or 480528 						5 lb.		 - - - - 		(+60) 			- - - - 			(+60)
	(b)	ukes No. 4140-00-218							2 lb. 		- - - - 		(+60) 			- - - - 			(+60)
		quired with Items 109(e), 109(f) and 109(g)

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, 			1 lb.		 - - - -		- - - - 			(+43) 			(+39.5)
	Lyc. No. 74547.

116.	Oil radiator, 2 req. Harrison Model AP13AU06-01 				3 lb. ea	- - - -		- - - - 			(+39) 			- - - -

117.	Starter, Delco-Remy Model 1113471, Lyc. No. 72279,			35 lb. 		- - - - 		- - - - 			(+12) 			- - - -
	12 v. geared 3.00:1

118.	Induction air filter, Fram Paper Filter No. CA-173PL				1 lb. 		- - - - 		- - - - 			(+10) 			- - - -

119.	(a)	Fuel pump, boost rotary motor-driven, Bendix No. 			5 lb. 		- - - - 		- - - - 			(+60) 			- - - -
		480533
	(b)	Fuel pump-boost-elec. Airborne Mfg. Co. No. 2B6-26. 		3.7 lb. 	- - - - 		- - - - 			(+60) 			- - - -

120.	(a)	Oil radiator - Harrison Model AP09AU06-02				2.4 lb. 	- - - - 		- - - - 			- - - - 			(+45.8)
		PAC #16943
	(b)	Harrison Model AP18AU06-03 PAC #43378 				3.6 lb. 	- - - - 		- - - - 			- - - - 			(+45.8)
	(c)	Harrison Model AP09AU06-04 PAC #32912 				2.4 lb. 	- - - - 		- - - - 			- - - - 			(+45.8)

1A15																			Page 13

Engine and Engine Accessories - Fuel and Oil System (cont'd) 					PA-24 	PA-24-250 		PA-24-400 		PA-24-260
121.	(a)	Fuel Pump, elec. aux. (boost)						 2 lb.		- - - - 		- - - - 			- - - - 			(+60)
		Dukes #4140-00-SPC

122.	(a)	Turbocharger								13.5 lb. ea 	- - - - 		- - - - 			- - - - 			(+26.0)
		Rayay #RJ0080-102
		(2 required when Item 109(h) is installed)

123.	 Manually Controlled Heated Alternate Engine Induction
	Air System.
	(a)	Installation per PAC Drawing 27186 					+3 lb. 		- - - - 		- - - - 			- - - - 			(+27.2)
		NOTE 2(w) placards 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, 				2 lb. 		- - - - 		- - - -			 - - - - 			(+40)
	Lycoming No. 74911, Lycoming No. 75528 or AC No.
	5578770

Landing Gear 												PA-24 	PA-24-250		 PA-24-400		PA-24-260

201.	(a)	Two main wheel assemblies (with No. 3000-250			8 lb. ea. 	(+108.5) 	(+108.5)		 - - - -			- - - -
		brake assemblies) 6.00-6, Type III, Cleveland Aircraft
		Products No. 3070.
	(b)	Two main wheel assemblies (with No. 30-41 brake			8 lb. ea. 	(+108.5) 	(+108.5)		 - - - - 			- - - -
		assemblies) 6.00.-6 Type III Cleveland Aircraft
		Products No. 40-58.

	(c)	Two main wheel assemblies (with No. 2-852 brake			11 lb.		- - - - 		- - - - 			(+108.5) 		- - - -
		assemblies) 6.00-6, Type III B.F. Goodrich No.
		3-1038
	(d)	Two main wheel assemblies (with No. 30-41 brake			8 lb. ea. 	- - - - 		- - - -			- - - - 			(+108.5)
		assemblies) 6.00-6, Type III Cleveland Aircraft
		Products No. 40-84
	(e)	Two main wheel assemblies (with No. 30-23 brake			9.5 lb. ea. 	- - - - 		- - - - 			(+108.5) 		- - - -
		assemblies) 6.00-6, Type III Cleveland Aircraft
		Products No. 40-90.

202.	(a)	Two main 4-ply rating tires 6.00-6, Type III with			9 lb. ea. 	(+108.5) 	- - - - 			- - - - 			- - - -
		regular tubes
	(b)	Two main 6-ply rating tires 6.00-6, Type III with			9.5 lb. ea. 	- - - - 		(+108.5) 		(+108.5) 		(+108.5)
		regular tubes.

205.	(a)	One nose wheel 6.00-6 Type III, Cleveland Aircraft			5 lb. 		(+30.7) 	(+30.7) 		(+30.7) 		(+30.7)
		Products No. 38501.
	(b)	One nose wheel 6.00-6, Type III, Cleveland Aircraft			3.8 lb. 	(+30.7) 	(+30.7) 		(+30.7) 		(+30.7)
		Products No. 40-76(B).

206.	(a)	One nose wheel 4-ply rating tire 6.00-6, Type III, with		9 lb. 		(+30.7) 	(+30.7) 		- - - - 			(+30.7)
		regular tube.
	(b)	One nose wheel 6-ply rating tire 6.00-6, Type III with			9 lb. 		- - - - 		- - - - 			(+30.7) 		(+30.7)
		regular tube.

1A15																			Page 14

207. 	(a)	Landing Gear Emergency Extension Security Kit 			Neglect	Elig. 		Elig. 			Elig. 			Elig.
		No. 760-627. Flight Manual Supplement 				Weight
		(Piper Report 1769) required. 						Change
	* 	Model PA-24-260
		Serial Nos. eligible are 24-3642, 24-4000 to 24-4803
		inclusive except 24-4783.	
		Electrical Equipment

301.	Generators
	(a)	One 12 volt, 35 amp generator, Delco Remy Mode			l18 lb. 	(+13) 		(+11.5) 		- - - - 			- - - -
		1101900, with bracket and voltage regulator No.
		1118704.
	(b)	One 12 volt, 50 amp. generator, Delco Remy Mode			l18 lb. 	(+13) 		(+11.5) 		- - - - 			- - - -
		1101915, with bracket and voltage regulator No.
		1119224, Eligible Serial No. 24-1, 24-103 and up.

302.	Battery
	(a)	Wisconsin Storage Battery, Reading R35, Bowers			27 lb. 		(+46) 		- - - - 			- - - - 			- - - -
		B-34, one 12 volt, 33 ampere-hour. Serial No. 24-2
		through 24-102 only.		
		24-1, 24-103 and up 									(+162) 	(+162) 		- - - - 			- - - -
		26-2 and up 									- - - - 		- - - - 		- - - -			(+162) 		- - - -
		24-3642, 24-4000 through 24-4246 					- - - - 		- - - - 		- - - -			 - - - - 			(+162)
		24-4248 through 24-4299, 24-4783 					- - - - 		- - - - 		- - - - 			- - - - 			(+162)
		24-4804 and up 								- - - - 		- - - - 		- - - - 			- - - - 			(+162)
		Serial No. 24-4247, 24-4300 through 24-4782 and			27 lb. 		- - - - 		- - - - 			- - - - 			(+46)
		24-4784 through 24-4803

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				2 lb. 		(+161) 	(+161) 		(+161) 		(+161)
		D-7080A-1-12
	(b)	Rotating Beacon - Whelen No. WRM-12, WRMA-12		2 lb. 		(+161) 	(+161) 		(+161) 		(+161)
		or WRML-12
	(c)	Strobe - Red Whelen Model HS Installation PAC			2.9 lb. 	- - - - 		- - - - 			- - - - 			(+161.7)
		Dwg. 27054 (S/N Eligible 24-4783 and 24-4804 and
		up) Flight Manual Supplement 401 bt or 401-(bu)
		and placard per NOTE 2(u) required with this
		installation.

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 PAC Dwg. 24889 and 26754				+4 lb. 		- - - - 		- - - - 			- - - - 			(+163).
	Not eligible when Item 402 (c) is installed.

1A15																			Page 15

307. Anti-Collision Light (Wing Tips) 									PA-24 	PA-24-250 		PA-24-400 		PA-24-260
	(a) 	Strobe - White Whelen Model HG-T2. Installation			4 lb. 		- - - - 		- - - - 			- - - - 			(+143.2)
		Dwg. PAC 27060 (S/N Eligible 24-4783 and 24-4804
		and up) Flight Manual Supplement 402 (bt) or 401
		(bu) and placard per NOTE 2(v) required with this
		installation

Interior Equipment
401.	(a)	DMCR Approved Airplanes Flight Manual dated June 19, 1957, revised March 7, 1958. Eligible Serial No. 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 Model PA-24-250, Serial No. 24-1,
		24-103 through 24-332.

	(d)	DMCR Approved Airplane Flight Manual dated March 7, 1958. Eligible Model PA-24, Serial No. 24-103 through
		24-1683.

	(e) 	DMCR Approved Airplane Flight Manual Supplement No. 1, date 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 Model PA-24-250, Serial No.
		24-1, 24-103 through 24-2002, 24-2004 through 24-2298. 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 204(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 Model PA-24, Serial No.
		24-1684 and up. 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.

	(n) 	DMCR Approved Airplane Flight Manual No. 1127, dated September 27, 1960. Eligible Model PA-24-250, Serial
		No. 24-2003, 24-2299 through 24-2562, 24-2564 through 24-2843. 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.

1A15																			Page 16

	(q)	DMCR Approved Airplane Flight Manual Supplement No. 3, dated December 13, 1960, to Airplane Flight Manual
		No. 1127 for Model PA-242-50, 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 Model PA-24-250, Serial
		No. 24-2563, 24-2844 and up, 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 Model PA-24-250, Serial
		No. 24-2563, 24-2844 and up. 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
		9(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)	MCR Approved Airplane Flight Manual Supplement No. 4, dated August 7, 1962, to Airplane Flight Manual No.
		47 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(k). Required when Item 402(c), Piper AutoControl II is installed.

	(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.

	(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 Model PA-24-400.

	(ah)	DMCR Approved Airplane Flight Manual No. 1333, dated June 19, 1964. Eligible Model PA-24-260 (carburetor
		Model), on Serial No. 24-3642, 24-4000 through 24-4246 and 24-4248 through 24-4299 only.

1A15																			Page 17

	(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 Model PA-24-260 (Fuel
		Injection Model), Serial No. 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 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(d) Piper
		AutoControl 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 Model PA-24-260 (Carburetor Model), Serial No. 24-4247, 24-4300 through 24-4782
		and 24-4784 through 24-4803.

	(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), Oxygen System 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.

1A15																			Page 18

	(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 Model PA-24-260 (Fuel Injection Model), Serial No. 24-4247, 24-4300 through 24-4782 and
		24-4784 through 24-4803.

	(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. 5, 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.

	(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 Model PA-24-260,
		Serial No. 24-4783, 24-4804 and up.

	(bp)	D.O.A. No. EA-1 Approved Airplane Flight Manual No. 1640 dated May 25, 1970. Eligible Model PA-24-260
		(equipped with Turbocharger) Serial No. 24-4783, 24-4804 and up.

1A15																			Page 19

	(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 supplement #1770 to Piper 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 1770 dated August
		8, 1972, with no revision date are eligible and approved for us. Copies with tow 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.)

402. Automatic Pilot 											PA-24 	PA-24-250   		PA-24-200 		PA-24-260
	(a)	Piper AutoControl, Model AK066, manufactured by		+4.5 lb. 		(+56.5) 	(+56.5) 		 - - - -			 - - - -
		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. Serial Nos. eligible are 24-1, 24-103
		and up. 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), (i), (j), or (p) are applicable.

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402. Automatic Pilot (cont'd) 										PA-24 	PA-24-250  		 PA-24-200 		PA-24-260
	(b)	Piper Altimatic, Model AK083, manufactured by		+10.5 lb.		(+57.8)	(+57.8)        		 - - - - 			- - - -
		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. Serial No. eligible are
		24-2003, 24-2203, 24-2299 and up. Flight Manual
		Supplement items 401(q), 401(r), 401(u), or 401(x)
		required with this installation.
	(c)	Piper Altimatic, Model AK089, manufactured by		+13.1 lb.		(+56.5)	(+56.5)	 	(+56.5)		 - - - -
		Mitchell Industries, Inc. in accordance with FAR		+17.1 lb		- - - -		- - - -		   	 - - - -			(+81.4)
		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. Serial No.
		eligible are 24-2003, 24-2203, 24-2299 and up. 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.
	(d)	Piper AutoControl II, Model AK065E manufactured		+4.6 lb. 		(+55.3) 	(+55.3) 		- - - - 			(+55.3)
		by Mitchell Industries, Inc. in accordance with FAR
		1.303, 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. Serial
		No. eligible are 240-2003, 24-2203, 24-2299 and up.
		Flight Manual Supplement Items 401(ac), 410(ad),
		401(ae), 401(af), 401(ai), 401(am), 401(ao), 401(ax),
		or 401(bc) required with this installation.
	(e)	Piper AutoControl III, Model AK161 manufactured by	+4			 - - - - 		- - - - 			- - - - 			(+113)
		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. Serial
		No. eligible are 24-4247, 24-4300 to 24-4782 and 24-
		4784 to 4-4803. Flight Manual Supplement Items
		401(bf) or 401(bg) required with this installation.
	(f)	Piper Altimatic III, installed in accordance with Piper		+18.9 lb. 		- - - -		 - - - - 			- - - - 			(119.5)
		Dwg. 25708. (Weight does not include weight of
		gyros). Serial No. eligible, 24-4247, 24-4300 to 24-
		4782 and 24-4784 to 24-4803. Flight Manual
		Supplement Items 401(bh) or 401(bi) required with
		this installation.

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402. 	Automatic Pilot (cont'd) 										PA-24 	PA-24-250 		PA-24-200 		PA-24-260
	(g)	Piper AutoControl III, installed in accordance with		+4 lb. 			- - - - 		- - - - 			- - - - 			(+113)
		Piper Dwg. 26735 (Weight does not include gyros).
		Serial No. eligible, 24-4783, 24-4804 and up. Flight
		Manual Supplement Item 401(bl) or 401(bq) required.
	 (h)	Piper Altimatic IIIB, installed in accordance with		+19.3			- - - - 		- - - -			 - - - - 			(+119)
		Piper Dwg. 26884. (Weight does not include gyros).
		Serial No. eligible, 24-4783, 24-4804 and up. Flight
		Manual Supplement Items 401(bm) or 401(br) required.
	(I)	Piper Altimatic IIIB1, installed in accordance with		20.2 			- - - - 		- - - - 			- - - - 			(94.0)
		Piper Dwg. 27333-2. (Weight includes Gyros and
		Turn and Bank Instrument.) (Serial Nos. eligible,
		24-4783, 24-4804 and up. Flight Manual Supplement
		Items 401(bx) or 401(by) required.

601.	Heated Pitot Head-Kollsman, Model No. 372D-01,			+1 lb. 			(+99) 		(+99) 			(+99) 			- - - -
	12 volt.

602.	Heated Pitot Tube Assembly, PAC Dwg. 21301 			+1 lb. 			(+99) 		(+99) 			(+99) 			(+99)

603.	Stall warning indicator installation installed in accordance		Negl.			 - - - - 		Required 		Required		Required
	with PAC Dwg. 21754.							Wt.
	
604. 	Stabilizer guard installation in accordance with PAC			+1 lb. 			(+255) 	(+255) 		- - - - 			(+255)
	Dwg. 22004.

605. 	Manifold pressure gauge. NOTE 2(k) placard required on		+l lb. 			- - - - 		- - - - 			Required 		See Item
	Model PA-24-400																			9(a) or (c)
	
606.	(a)	Piper Radio Coupler Per PAC Dwg. 24997 or 23619. 	+.5 lb. 		- - - - 		- - - - 			(+66) 			(+66)
	(b)	Piper Radio Coupler Per PAC Dwg. 25678 NOTE		+.5 lb.			 - - - 		- - - - 			- - - - - 		(+66)
		2(p) placard required.
	(c)	Piper Radio Coupler per PAC Dwg. 26825 NOTE 2(r)	+.5 lb 			- - - - 		- - - -			 - - - - 			(+66)
		placard required

607.	(a)	Exhaust Gas Temperature Indicator per STC			+1 lb.			 - - - - 		- - - - 			(+55) 			(+55)
		SA788WE, installed per PAC Drawing 25287.
	(b)	Exhaust Gas Temperature Indicator per STC			+1 lb. 			- - - - 		- - - - 			- - - - 			(+55)
		SA522SW, installed per PAC Drawing 25667
	(c)	Exhaust Gas Temperature Indicator per STC			2 lb. 			- - - - 		- - - - 			- - - - 			(54)
		SA1315WE, installed per PAC Drawing 26333.
	(d)	Exhaust Gas Temperature Indicator per STC			2 lb. 			- - - - 		- - - - 			- - - - 			(+54)
		SA1315WE, installed per PAC Drawing 26851.

608.	(a)	Alternate instrument static air source installed per 		Negl. 			- - - - 		- - - - 			Elig. 			Elig.
		PAC Dwg. 25301 and 26723. NOTE 2(1) placards 		Wt.
		required.
609. 	(a) 	Oxygen System Installation per PAC Dwg. 25342. 		+41.5 lb.		 - - - - 		- - - - 			(+161.2) 		(+161.2)
		On PA-24-260, 24-3642, 24-4000 through 24-4246,
		and 24-4248 through 24-4299. NOTE 2(q) placards
		required.

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609.	(cont'd) 												PA-24 	PA-24-250 		PA-24-200 		PA-24-260
	(b) 	Oxygen System Installation per PAC Dwg. 25542 or		+41.5 lb. 		- - - - 		- - - - 			- - - - 			(+161.2)
		25724 at 26682. Eligible on PA-24-260 Serial No.
		24-4247, 24-4300 and up. NOTE 2(q) placards
		required.

610.	(a)	Auxiliary Power Receptacle Installation per PAC		7 lb. 			(+153.3) 	(+153.3) 		(+153.3) 		(+153.3)
		Dwg. 24628. (Weight includes Jumper Cable
		Assembly). On Models PA-24, PA-24-250 and
		PA-24-260, eligible only on Serial No. 24-2299
		through 24-4246 and 24-4248 through 24-4299 and up.
	(b)	Auxiliary Power Receptacle Installation per PAC		+6.4 lb. 		- - - - 		- - - - 			- - - - 			(+121.5)
		Dwg. 25584. (5 lb. Jumper Cable included - carried
		in baggage compartment ). Eligible PA-24-260 Serial
		No. 24-4247, 24-4300 and up.

611.	(a)	Optional Seating Seat Installation-Fifth and Sixth		+7.5 lb. 		- - - - 		- - - -			- - - - 			(+148)
		per PAC Dwg. 25302 and 26602.				   ea
		Eligible PA-24-260 Serial No. 24-4247, 24-4300 and up.
		NOTE: 2(m) placard required.

612.	(a)	Front Seat - Vertically adjustable - 				21.3 lb. 		- - - - 		- - - - 			- - - - 			(+84.8)
		Left and/or Right PAC Drawing 26971

613. 	(a)	Piper Glide Slope Coupler per PAC Dwg. 26729. 		1.5 lb.			 - - - - 		- - - - 			- - - - 			(+61.3)
		Serial No. eligible 24-4783, 24-4804 and up. NOTE
		2(s) placard required.

614.	(a)	Shoulder Harness PAC Dwg. 27006 Left Front and/or	6 lb. ea. 		- - - - 		- - - -			- - - - 			(+100)
		Right front.
		Left Center and/or Right Center 					6 lb. ea. 		- - - - 		- - - - 			- - - - 			(+100)

615. 	(a)	Brake Installation - dual PAC No. 27062			+5 lb. 			- - - - 		- - - - 			- - - - 			(+58)
		Serial No. eligible 24-4783, 24-4804 and up.

616.	(a)	Manifold Pressure Gauge PAC Dwg. 27149 			1 lb. 			- - - - 		- - - -			 - - - - 			(+66)

617.	(a)	Balance Weight - Rudder Install in accordance with		4.5 lb.			 (+272.0)	 (+272.0)	 	- - - - 			(+272.0)
		PAC Dwg. 27972 or instructions per Service Kit #760
		705. Flight Manual Supplement Item 401(bz) and
		placard NOTE 2(x) required on Models PA-24-250
		and PA-24-260 only.

618. 	Stabilator Modification Modified in accordance with			7 lb. 			- - - - 		(+260.0) 		- - - - 			(+260)
	service kit instructions 760 747.
	Change Vne speed to 227 M.P.H. and delete flight
	manual and placard specified with item 617 (rudder
	balance weight) when items 617 and 618 are both
	installed. Note: This speed change is not approved
	without installation of both items.

1A15																			Page 23

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. (+90) for Model PA-24-205 Serial No. 24-2563, 24-2844
		and up, and PA-24-260; and 36 lb. (+90) for Model PA-24-400, Serial No. 26.2 and up

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 Serial
			No. 24-2844 and up, Model PA-24 Serial No. 24-3286 and up PA-24-400, Serial No. 26-2 and up,
			and Model PA-24-260).

		(e)	On baggage compartment (Model PA-24, Serial No. 24-2 through 24-103 only):
			"MAXIMUM BAGGAGE 100 POUNDS."

		(f)	On baggage compartment (for Models PA-24 and PA-24-250 Serial No. 24-1, 24-102 and up; for
			Model PA-24-400 Serial No. 26-2 and up; and Model PA-24-260 Serial No. 24-3642, 24-4000
			through 24-4246, and 24-4248 through 24-4299): "MAXIMUM BAGGAGE 200 POUNDS."

		(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."

1A15																			Page 24

		(g)	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."

		(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
					ALT.
					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. 	djacent to the pitch control knob:
					"UP
					DN"

		(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.
								Engage 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
								heading.
				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"

1A15																			Page 25

			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, Serial No. 26-2 and up 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."

		(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 USED:

					On Model 					INDICATOR READS	 		ACTUAL
					PA-24-260 only 					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 					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 Model PA-24-400 and PA-24-260 Serial No. 24-3642,m 24-4000 through 24-4892,.
					24-4784 through 24-4803.)
				On throttle quadrant aft of alternate static source actuating valve:
					OFF
			
					ALT
					STATIC
					AIR
			
					ON
			(For aircraft Serial No. 24-4783, 24-4804 and up)

		(m)	On baggage compartment (For Model PA-24-260, Serial No. 24-4247, 24-4300 and up).
			"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-240-260, Serial No. 24-42476, 24-4300 and up.

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		(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"

		(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 SMO7KING WITH OXYGEN IN USE."
				at oxygen control knob:
				" PULL ON, OXYGEN:

		(r)	On instrument panel beside radio coupler switch
				A/P NAV SEL

					ON
					OFF
					ON

		(s)	On instrument panel beside the glide slope indicator light.

					G/S
				ENGAGED

		(t)	On Model PA-24-260, Serial Nos. 24-4783 and 24-4804 and up, 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"

1A15																			Page 27

		(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.

		(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

		(y)	On instrument panel (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...