TCDS 1A6

DEPARTMENT OF TRANSPORTATION FEDERAL AVIATION ADMINISTRATION 1A6 Revision 34 Piper Aircraft, Inc PA-22 PA-22-108 PA-22-135 PA-22S-135 PA-22-150 PA-22S-150 PA-22-160 PA-22S-160 August 7, 2006 AIRCRAFT SPECIFICATION NO. 1A6 Type Certificate Holder Piper Aircraft, Inc. 2926 Piper Drive Vero Beach, Florida 32960 Type Certificate Holder Record The New Piper Aircraft, Inc transferred TC 1A6 to Piper Aircraft, Inc on August 7, 2006. I - Model PA-22, 4 PCLM (Normal Category Only), Approved December 20, 1950 Engine Ly coming O-290-D Fuel 80/87 minimum grade aviation gasoline Engine Limits For all operations, 2600 rpm (125 hp) Airspeed Limits Vne (never exceed) 158 mph (137 knots) CAS Vno (maximum structural cruising) 126 mph (110 knots) Vp (maneuvering) 106 mph (92 knots) Vfe (flaps extended) 80 mph (70 knots) C. G. Range (+17.5) to (+24.0) at 1800 lb. (+10.0) to (+24.0) at 1380 lb. or less Straight line variation between points given. Gross Weight (l b.) 1000 1200 1400 1600 1800 81 0 12 14 16 Inches Aft of D 2000 18 atum 20 22 24 26 R Li ear mit Front Limit Empty Weight C. G. Range None Maximum Weight 1800 lb. Page No. 1 2 3 4 5 6 7 8 9 10 11 12 13 14 15 Rev. No. 34 33 33 33 33 33 33 33 33 33 33 33 33 33 33 1A6 Page 2 of 15 Number Seats 4 (2 at +19.5 and 2 at +49) Maximum Baggage 50 lb. (+67) Fuel Capacity 36 gallons (2 Wing tanks at +24) Oil Capacity 2 gallons (-29) Control Surface Movements Stabilizer 1° Up 6½° Down Elevator 24° Up 12° Down Aileron 15° Up 15° Down Rudder 16° Right 16° Left Flap 40° Down Serial Numbers Eligible 22-1 and up. Required Equipment In addition to the pertinent required basic equipment specified in CAR 3, the following items of equipment must be installed: Items 1, 101, 201(a), 202, 205(a), 206, and 401(a). II. Model PA-22-135, 4 PCLM (Normal Category), Approved May 5, 1952 Engine Ly coming O-290-D2 Fuel 80/87 minimum grade aviation gasoline Engine Limits For all operations, 2600 rpm (135 hp) Airspeed Limits Vne (never exceed) 158 mph (137 knots) (CAS) Vno (maximum structural cruising) 126 mph (110 knots) Vp (maneuvering) 106 mph (92 knots) Vfe (flaps extended) 80 mph (70 knots) C. G. Range (+17.5) to (+24.0) at 1950 lb. (+10.0) to (+24.0) at 1380 lb. or less Straight line variation between points given. Gross Weight (l b.) 1000 1200 1400 1600 1800 81 0 12 14 16 Inches Aft of D 2000 18 atum 20 22 24 26 R Li ear mit Front Limit Empty Weight C. G. Range None Maximum Weight 1950 lb. Number of Seats 4 (2 at +21 and 2 at +49) Page 3 of 15 1A6 Maximum Baggage 50 lb. (+67) May be increased to 100 lb. provided: (a) Baggage compartment placard is changed to "Maximum Baggage 100 Pounds." (b) Airplane Flight Manual, Item 401(c), is available in the airplane. Fuel Capacity 36 gallons (2 wing tanks at +24). See Item 104 for reserve tank. Oil Capacity 2 gallons (-29) Control Surface Movements Stabilizer 1° Up 6½° Down Elevator 24° Up 12° Down Aileron 15° Up 15° Down Rudder 16° Right 16° Left Flap 40° Down Serial Numbers Eligible 22-534 and up. Required Equipment In addition to the pertinent required basic equipment specified in CAR 3, the following Items of equipment must be installed: Items 1, 103, 201(a), 202, 205(a), 206, and 401(b). III - Model PA-22S-135, 3 PCSM (Normal Category), Approved May 14, 1954 Engine Ly coming O-290-D2 Fuel 80/87 minimum grade aviation gasoline Engine Limits For all operations, 2600 r.p.m. (135 hp) Airspeed Limits Vne (never exceed) 140 mph (122 knots) CAS Vno (maximum structural cruising) 117 mph (102 knots) Vp (maneuvering) 105 mph (91 knots) Vfe (flaps extended) 80 mph (70 knots) C. G. Range (+14.0) to (+20.0) at 1850 lb. (+10.0) to (+20.0) at 1300 lb. or less Straight line variation between points given. Gross Weight (l b.) 1000 1200 1400 1600 1800 81 0 12 14 Inches Aft 16 of Dat um 2000 18 20 22 Rear Limit Fro nt Limit Empty Weight C. G. Range None Maximum Weight 1850 lb. Number of Seats 4 (2 at +21 and 2 at +49) Maximum Baggage 50 lb. (+67) 1A6 Page 4 of 15 Fuel Capacity 36 gallons (2 wing tanks at +24). See Item 104 for reserve tank. Oil Capacity 2 gallons (-29) Control Surface Movements Stabilizer 1° Up 6½° Down Elevator 24° Up 12° Down Aileron 15° Up 15° Down Rudder 16° Right 16° Left Flap 40° Down Serial Numbers Eligible 22-534 and up. Required Equipment In addition to the pertinent required basic equipment specified in CAR 3, the following Items of equipment must be installed: Items 2, 103, 209, and 401(g). IV - Model PA-22-150, 4 PCLM (Normal Category), Approved September 3, 1954. Model PA-22-150, 2 PCLM (Utility Category), Approved May 24, 1957 (See NOTE 3 for limitations) Engine Lycoming O-320-A2A or O-320-A2B (Carburetor setting #10-3678-11, #10-3678-12 or #10-3678-32) (See Item 106 for optional engines) Fuel 80/87 minimum grade aviation gasoline Engine Limits For all operations, 2700 r.p.m. (150 hp) Airspeed Limits Vne (never exceed) 170 mph (148 knots) CAS Vno (maximum structural cruising) 135 mph (117 knots) Vp (maneuvering) 112 mph (97 knots) Vfe (flaps extended) 95 mph (82 knots) C. G. Range Normal Category: (+17.5) to (+23.0) at 2000 lb. (+12.0) to (+23.0) at 1800 lb. (+9.5) to (+23.0) at 1400 lb. or less Utility Category: (+13.5) at 1680 lb. (+12.0) to (+13.5) at 1665 lb. (+9.5) to (+13.5) at 1400 lb. or less Straight line variation between points given. Gross Weight (l b.) 100 0 120 0 140 0 160 0 180 0 81 0 12 14 16 Inches Aft 200 0 of Datum 18 20 22 24 2200 Utility Categor y Normal Categor y Empty Weight C. G. Range None Maximum Weight Normal Category: 2000 lb. Utilit y Category: 1680 lb. Number of Seats 4 (2 at +21 and 2 at +49) Rear seats not to be used when operating in the Utility Category. Maximum Baggage 100 lb. (+67) (No baggage allowed when operating in the Utility Category) Page 5 of 15 1A6 Fuel Capacity 36 gallons (2 wing tanks at +24) See Item 104 for reserve tank. Oil Capacity 2 gallons (-29) Control Surface Movements Stabilizer 1° Up 6½° Down Elevator 24° Up 12° Down Aileron 15° Up 15° Down Rudder 16° Right 16° Left Flap 40° Down Serial Numbers Eligible 22-2378, 22-2425 and up (Normal Category). See NOTE 3 for Utility Category. Required Equipment In addition to the pertinent required basic equipment specified in CAR 3, the following Items of equipment must be installed: Normal Category: Items 5, 103, 201(a), 202, 205(a), 206, and 401(h). Normal and Utility Category: Items 5, 103, 201(a), 202, 205(a), 206, 401(h), 401(r), and 407. V. - Model PA-22S-150, 3 PCSM (Normal Category), Approved September 3, 1954 Engine O-320-A2A Lycoming (Carburetor setting #10-3678-11, #10-3678-12) or O-320-A2B (Carburetor setting #10-3678-32) (See Item 106 for optional engines) Fuel 80/87 minimum grade aviation gasoline Engine Limits For all operations, 2700 r.p.m. (150 hp) Airspeed Limits Vne (never exceed) 158 mph (137 knots) CAS Vno (maximum structural cruising) 126 mph (109 knots) Vp (maneuvering) 111 mph (96 knots) Vfe (flaps extended) 80 mph (70 knots) C. G. Range (+14.0) to (+20.0) at 1950 lb. (+12.0) to (+20.0) at 1800 lb. (+10.0) to (+20.0) at 1500 lb. or less Straight line variation between points given. Gross Weight (l b.) 1000 1200 1400 1600 1800 81 0 12 14 Inches Aft 16 of Dat um 2000 18 20 22 Rear Limit Fro nt Limit Empty Weight C. G. Range None Maximum Weight 1950 lb. Number Seats 4 (2 at +21 and 2 at +49) Maximum Baggage 100 lb. (+67) Fuel Capacity 36 gallons (2 wing tanks at +24). See Item 104 for reserve tank. 1A6 Page 6 of 15 Oil Capacity 2 gallons (-29) Control Surface Movements Stabilizer 1° Up 6½° Down Elevator 24° Up 12° Down Aileron 15° Up 15° Down Rudder 16° Right 16° Left Flap 40° Down Serial Numbers Eligible 22-2378, 22-2425 and up. Required Equipment In addition to the pertinent required basic equipment specified in CAR 3, the following Items of equipment must be installed: Items 5, 103, 209 and 401(i). VI - Model PA-22-160, 4 PCLM (Normal Category), Approved August 27, 1957 Model PA-22-160, 2 PCLM (Utility Category), Approved August 27, 1957 (See NOTE 3) Engine Lycoming O-320-B2A or O-320-B2B (Carburetor setting #10-3678-11, #10-3678-12 or #10-3678-32). Fuel 91/96 minimum grade aviation gasoline Engine Limits For all operations, 2700 r.p.m. (160 hp) Airspeed Limits Vne (never exceed) 170 mph (148 knots) (CAS) Vno (maximum structural cruising) 135 mph (117 knots) Vp (maneuvering) 112 mph (97 knots) Vfe (flaps extended) 95 mph (82 knots) C. G. Range Normal Category: (+17.5) to (+23.0) at 2000 lb. (+12.0) to (+23.0) at 1800 lb. (+9.5) to (+23.0) at 1400 lb. or less Utility Category: (+13.5) at 1680 lb. (+12.0) to (+13.5) at 1665 lb. (+9.5) to (+13.5) at 1400 lb. or less Straight line variation between points given. Gross Weight (l b.) 1000 1200 1400 1600 1800 81 0 12 14 16 Inches Aft 2000 of Dat um 18 20 22 24 220 0 Utilit y Category Normal Category Empty Weight C. G. Range None Maximum Weight Normal Category: 2000 lb. Utilit y Category: 1680 lb. Number of Seats 4 (2 at +21 and 2 at +49) Rear seats not to be used when operating in the Utility Category. Maximum Baggage 100 lb. (+67) No baggage allowed when operating in the Utility Category. Page 7 of 15 1A6 Fuel Capacity 36 gallons (2 wing tanks at +24). See Item 104 for reserve tank. Oil Capacity 2 gallons (-29) Control Surface Movements Stabilizer 1° Up 6½ Down Elevator 24° Up 12° Down Aileron 15° Up 15° Down Rudder 16° Right 16° Left Flap 40° Down Serial Numbers Eligible 22-2378, 22-2425 and up (Normal Category). See NOTE 3 for Utility Category. Required Equipment In addition to the pertinent required basic equipment specified in CAR 3, the following Items of equipment must be installed: Normal Category: Items 7, 103, 201(a), 202, 205(a), 206, and 401(s). Normal and Utility Category: Items 7, 103, 201(a), 202, 205(a), 206, 401(s), 401(t), and 407. VII - Model PA-22S-160, 3 PCSM (Normal Category), Approved October 25, 1957 Engine Lycoming O-320-B2A (Carburetor setting #10-3678-11, #10-3678-12) or O-320-B2B (Carburetor setting #10-3678-32). Fuel 91/96 minimum grade aviation gasoline Engine Limits For all operations, 2700 r.p.m. (160 hp) Airspeed Limits Vne (never exceed) 158 mph (137 knots) Vno (maximum structural cruising) 126 mph (109 knots) Vp (maneuvering) 111 mph (96 knots) Vfe (flaps extended) 80 mph (70 knots) C. G. Range (+14.0) to (+20.0) at 1950 lb. (+12.0) to (+20.0) at 1800 lb. (+10.0) to (+20.0) at 1500 lb. or less Straight line variation between points given. Gross Weight (l b.) 1000 1200 1400 1600 1800 81 0 12 14 Inches Aft 16 of Dat um 2000 18 20 22 Rear Limit Fro nt Limit Empty Weight C. G. Range None Maximum Weight 1950 lb. Number of Seats 4 (2 at +21 and 2 at +49) Maximum Baggage 100 lb. (+67) Fuel Capacity 36 gallons (2 wing tanks at +24). See Item 104 for reserve tank. 1A6 Page 8 of 15 Oil Capacity 2 gallons (-29) Control Surface Stabilizer 1° Up 6½° Down Movements Elevator 24° Up 12° Down Aileron 15° Up 15° Down Rudder 16° Right 16° Left Flap 40° Down Serial Numbers Eligible 22-2378, 22-2425 and up. Required Equipment In addition to the pertinent required basic equipment specified in CAR 3, the following Items of equipment must be installed: Items 7, 103, 209, and 401(v). VIII - Model PA-22-108, 2 PCLM (Normal and Utility Category), Approved October 21, 1960 Engine Lycoming O-235-C1 or O-235-C1B (Carburetor setting #10-3103-1) Fuel 80/87 minimum grade aviation gasoline Engine Limits For all operations, 2600 r.p.m. (108 hp) Airspeed Limits Vne (never exceed) 138 mph (120 knots) (CAS) Vno (maximum structural cruising) 110 mph (96 knots) Vp (maneuvering) 104 mph (90 knots) C. G. Range Normal Category: (+12.0) to (+16.25) at 1650 lb. (+9.5) to (+16.25) at 1300 lb. or less Utility Category: (+10.9) to (+14.00) at 1500 lb. (+9.5) to (+14.00) at 1300 lb. or less Straight line variation between points given. Gross Weight (l b.) 1000 1200 1400 1600 1800 81 0 12 14 16 Inches Aft of Dat um 18 U.C. N.C. N.C. - No U.C. - Ut rmal Category ility Cate gory Empty Weight C. G. Range None Maximum Weight Normal Category: 1650 lb. Utilit y Category: 1500 lb. Number of Seats 2 at (+21) Maximum Baggage 100 lb. (+45) (Normal category only) Fuel Capacity 18 gallons (+24) (See Item 108 for auxiliary tank) Oil Capacity 1.5 gallons (-29) Control Surface Stabilizer 1° Up 6½° Down Movements Elevator 24° Up 12° Down Aileron 15° Up 15° Down Rudder 16° Right 16° Left Serial Numbers Eligible 22-8000 and up. Page 9 of 15 1A6 Required Equipment In addition to the pertinent required basic equipment specified in CAR 3, the following Items of equipment must be installed: Items 8, 201(a) or 211(a), 202, 205(a), 206, and 401(y). Specifications Pertinent to All Models Datum Wing leading edge Leveling Means Plumb from hole in upper channel of front door to center punch mark on front seat cross tube. Certification Basis CAR 3, effective November 1, 1949, and Amendments 3-1 through 3-6, effective June 4, 1951. Type Certificate No. 1A6 issued December 20, 1950. Date of Application for Type Certificate September 13, 1950. Production Basis Approved for manufacture of spare parts only under Production Certificate No. 206. Equipment A plus (+) or minus (-) sign preceding the weight of an Item of equipment indicates net weight change when that Item is installed. Approval for the installation of all Items of equipment listed herein has been obtained by the aircraft manufacturer except those Items preceded by an asterisk (*). The asterisk denotes that approval has been obtained by someone other than the aircraft manufacturer. An Item marked with an asterisk may not have been manufactured under an FAA monitored or approved quality control system, and therefore conformity must be determined if the Item is not identified by a Form FAA-186, PMA or other evidence or FAA production approval. Propeller and Propeller Accessories The following propellers are eligible at the limits shown for diameter and static r.p.m. at maximum permissible throttle setting, no additional tolerance permitted: 1. Propeller (with Lycoming O-290D or O-290-D2 engine) Sensenich 74FM59 or any other fixed pitch wood propeller which is rated for the engine power and speed: +11 lb. (-50) Static r.p.m.: Not over 2400, not under 2200. Diameter: Not over 74 inches, not under 70.5 inches 2. Propeller (with Lycoming O-290D or O-290-D2 engine) - fixed pitch metal (a) Sensenich M76AM-2 or +25 lb. (-50) (b) Sensenich M74DM +30 lb. (-50) Airplane Flight Manual shall be revised to reflect the subject propeller and limits. Landplane: Static r.p.m.: Not over 2450, not under 2150 Diameter: Not over 74 inches, not under 72.5 inches Seaplane: Static r.p.m.: Not over 2450, not under 2350 Diameter: Not over 74 inches, not under 72.5 inches 3. Propeller (with Lycoming O-290D or O-290-D2 engine) Koppers Aeromatic, F200-H/00-74E +34 lb. (-50) Parts List Assembly No. 4394H-1. Installation and operation must be accomplished in accordance with Koppers "Adjustment Instructions and Operation Limitations No. 58." Low pitch setting 14° at 24 in sta. Static r.p.m.: Not over 2600, not under 2550. Diameter: Not over 74 inches, not under 72.5 inches 1A6 Page 10 of 15 4. Propeller (with Lycoming O-290D or O-290-D2 engine) Sensenich hub CS3FM-4, blades PC374A7 or C374E, two position controllable. Propeller control installation required as per Sensenich Dwg. D-3028, Revision E. Blade pitch setting at 3/4 radius (27.75 in. station): Low 13°, high 16.6° Diameter: Not over 74 inches, not under 72.5 inches +34 lb. (-50) 5. Propeller (with Lycoming O-320-A2A or O-320-A2B engine) - Fixed pitch metal Sensenich M74DM Landplane: Static r.p.m.: Not over 2480, not under 2250. Diameter: Not over 74 inches, not under 72.5 inches Seaplane: Static r.p.m.: Not over 2500, not under 2400 Diameter: Not over 74 inches, not under 72.5 inches +30 lb. (-50) 6. Propeller (with Lycoming O-320-A1A or O-320-A1B engine) - constant speed controllable Hartzell hub HC82XG-6, blades 7636D-4 +54 lb. (-50) Installed per Piper Dwg. No. 14747 when Item 105 (vacuum pump) is installed, or per Piper Dwg. No. 14792, without vacuum pump. Not eligible when Item 407 is installed. Note 2(f) placard required. Blade pitch settings at 30 in. sta.: Low 12°, high 26°. Diameter: Not over 72 inches, not under 70 inches Eligible only on Models PA-22-150 and PA-22S-150, Serial Nos. 22-3218, 22-3387 and up. When this propeller is used on Model PA-22S-150, the engine side cowls shall be installed per Piper Dwg. No. 14450. 7. Propeller (with Lycoming O-320-B2A or O-320-B2B engine) - fixed pitch metal Sensenich M74DM +34 lb. (-50) Landplane: Static r.p.m.: Not over 2450, not under 2250 Diameter: Not over 74 inches, not under 72 inches Seaplane: Static r.p.m.: Not over 2500, not under 2400 Diameter: Not over 74 inches, not under 72 inches Applicable Airplane Flight Manual shall be revised by the Modifier and approved by the applicable FAA Aircraft Certification Office to reflect this installation change. 8. Propeller (with Lycoming O-235-C1 or O-235-C1B engine) - fixed pitch metal Sensenich M76AM-2 Static r.p.m.: Not over 2450, not under 2200 Diameter: Not over 74 inches, not under 72.5 inches +25 lb. (-50) Engines and Engine Accessories - Fuel and Oil Systems 101. Oil cooler - Harrison No. AP06CJ04-02 or AP06CU04-2 and Piper Air Duct +3 lb. (-18) 102. Oil filter, Fram PB-5, Kit No. K-520, Fram Dwg. No. 62832 and Instruction Sheet No. 62831 (weight includes 1 quart oil) +5 lb. (-18.5) 103. Oil Cooler Harrison No. AP13SJ03-01 or AP12CU03-01 installed in accordance with Piper Dwg. 13724 or 14368 +6 lb. (-46) 104. or Reserve 8 gallons fuel tank with electric transfer fuel pump installed in accordance with Piper Dwg. 14454. When installed on Models PA-22S-135, PA-22S-150 or PA-22S-160, fuselage reinforcement channel, Part No. 14725, also required. NOTE 2(e) placard required. Airplane Flight Manual Supplement required: Item 401(j), Model PA-22-150 Item 401(k) Model PA-22-135 (Serial Nos. 22-534 and up eligible), Item 401(p) Model PA-22S-135 (Serial Nos. 22-807 and up eligible), Item 401(q) Model PA-22S-150 (Serial Nos. 22-2378, 22-2425 and up eligible), Item 401(u) Model PA-22-160 (Serial Nos. 22-2378, 22-2425 and up eligible), Item 401(w) Model PA-22S-160 (Serial Nos. 22-2378, 22-2425 and up eligible). +12 lb. (+46) Page 11 of 15 1A6 105. Vacuum pump (a) Pesco Model 3P-194-F, Type B-11 +4 lb. (-25) (b) Airborne Mechanisms Model 113A1 installed in accordance with Piper Dwg. 15163. (PA-22-108 only). +4 lb. (-25) (c) Airborne Mechanisms Model 113A5 installed in accordance with Piper Dwg. 15163 or 15208. (PA-22-108 only). +4 lb. (-25) 106. Optional Engines A. Model PA-22-150 (1) Lycoming O-320 (2) Lycoming O-320-A1A (3) Lycoming O-320-A1B B. Model PA-22S-150 (1) Lycoming O-320 (2) Lycoming O-320-A1A (3) Lycoming O-320-A1B 107. Starter, Delco Remy Model 1109657 (12 v.) +17 lb. (-40) 108. Auxiliary 18 gallons fuel tank installed in accordance with Piper Dwg. 15147 (PA-22-108 only). NOTE 2(j) placard required. +25 lb. (+24) Landing Gear 201. Two main wheel-brake assemblies, 6.00-6, Type III (a) Cleveland Aircraft Products Model 6:00 DHB-3 Wheel Assembly No. C-38500H Brake Assembly No. C-2000H +14 lb. (+31.5) 202. Two main 4-ply rating tires, 6.00-6, Type III, with regular tubes +17 lb. (+31.5) 205. One nose wheel, 6.00-6, Type III (a) Cleveland Aircraft Products Wheel Assembly No. C-38500H (less brake-drum) (b) Cleveland Aircraft Products Wheel Assembly No. 38501 +5 lb. (-36) 206. One nose wheel 4-ply rating, tire, 6.00-6, Type III, with regular tube +9 lb. (-36) *207. Nose wheel centering kit installed according to Javelin Aircraft Company (Wichita, Kansas) Dwg. 723 and Installation Instructions dated April 15, 1953. +2. lb. (-29) 208. Skis: *(a) Federal A-2000A main skis and NA-1200A nose ski, per Federal Dwg. 11R951, Change E. *(b) Federal AWB-2100 main skis and AWN-1200 nose ski, per Federal Dwg. 11R1117. The following placard is required with this installation: "Do not extend or retract skis while in motion on the ground." Use Actual Weight Change 209. Edo Model 89-2000 floats with water rudder installed in accordance with Edo Dwg. No. 16270. Piper modifications must be made and installed in accordance with Piper Dwg. 14375 (Model PA-22S-135, Serial Nos. 22-534 to 22-2377, 22-2379 to 22-2424, inclusive) and Piper Dwg. 14450 (Model PA-22S-150 and PA-22S-160, Serial Nos. 22-2378, 22-2425 and up.) Serial Nos. 22-534 to 22-806, inclusive, require a fuselage reinforcement brace, Piper Part No. 12480. 210. (a) Doyn Fiberglass wheel fairings installed in accordance with Doyn Dwg. No. 1300 and Doyn Process Specification for Fiberglass Part No. PS-100 Nose Fairing Main Fairing +5.5 lb. +15.0 lb. (-36) (+31.5) or (b) Piper wheel fairings installed in accordance with Piper Dwg. 15054 and 15058 Nose Fairing Main Fairing +5.5 lb. +15.0 lb. (-36) (+31.5) or (c) Piper wheel fairings installed in accordance with Piper Dwg. 15083 Nose Fairing Main Fairing +5.5 lb. +15.0 lb. (-36) (+31.5) 211. Two Main Wheel-Brake Assemblies, 6.00-6, Type III (a) Cleveland Aircraft Products, Model 20-6 (Model PA-22-108 only) + 14.5 lb. (+31.5) Wheel Assembly No. 40-28 Brake Assembly No. 30-18 1A6 Page 12 of 15 Electrical Equipment 301. Battery - Reading S24-12V +25 lb. (+21) 302. Landing lights in wing leading edge per Piper Dwg. No. 12534 (Serial Nos. 22-534 to 22-2377, 22-2379 to 22-2424, inclusive) Piper Dwg. No. 14442 (Serial Nos. 22-2378, 22-2425 and up). +4 lb. (+5) 303. Battery - Reading R33-12V Serial Nos. 22-267, 22-340, 22-349, 22-350, 22-351, 22-354 through 22-7999. +28 lb. (+21) Interior Equipment 401. (a) CAA (FAA) approved Airplane Flight Manual dated December 20, 1950, for airplanes equipped with Lycoming O-290-D engines. (Required with 100 lb. baggage allowance.) (b) FAA-DOA approved Airplane Flight Manual dated May 5, 1952, for airplanes equipped with Lycoming O-290-D2 engines. (c) FAA-DOA approved Airplane Flight Manual dated October 23, 1952, for airplanes equipped with Lycoming O-290-D2 engines. *(d) Supplement to Airplane Flight Manual dated January 17, 1952. (Required with Item 402(a) without altitude controller.) *(e) Revised Supplement to Airplane Flight Manual dated January 19, 1953. (Required with Item 402(a) without altitude controller.) *(f) Revised Supplement to Airplane Flight Manual dated November 18, 1953. (Required with Item 402(b) with approach coupler.) (g) FAA-DOA approved Airplane Flight Manual dated May 14, 1954, for Model PA-22S-135 seaplanes equipped with Edo Model 89-2000 floats. (h) FAA-DOA approved Airplane Flight Manual dated September 3, 1954, for Model PA-22-150. (i) FAA-DOA approved Airplane Flight Manual dated September 3, 1954, for Model PA-22S-150 seaplanes equipped with Edo Model 89-2000 floats. (j) FAA-DOA approved Supplement No. 1 to Airplane Flight Manual dated September 3, 1954, (Required with Item 104 Auxiliary Fuel System) for Model PA-22-150. (k) FAA-DOA approved Supplement No. 1 to Airplane Flight Manual dated October 23, 1952, (Required with Item 104 Auxiliary Fuel System) for Model PA-22-135, Serial No. 22-534 and up. *(l) Supplement to Airplane Flight Manual dated November 17, 1954. (Required with Item 404). *(m) Supplement to Airplane Flight Manual dated April 20, 1955. (Required with Item 405). (n) FAA-DOA approved Supplement to Airplane Flight Manual dated