Airplane Flight Manual for the Piper PA-28 Cherokee 160

DEVELOPMENT CENTER, VERO BEACH, FLA. REPORT VB-160 Airplane Flight Manual Model PA-28-140 PAGE 2 of 7 Maximum Weight 1950 lbs. Baggage Capacity 2150 lbs. 100 lbs. (+117) 200 lbs. (+117) 300 lbs. (+117) ( & ) (+133) Utility Category - S/N 28-20001 and up Normal Category - S/N 28-20001 through 28-20939 (Normal category maximum weight for aircraft with S/N 28-20001 through 28-20939 may be increased to 2150 lbs. by the installation of Piper Kit 756962 and Sensenich propeller M74DM58) Normal Category Only (S/N 28-20940 and up) S/N 28-20001 through 28-20939 (Maximum baggage may be increased to 200 lbs. by the installation of Piper Kit 756 962 and Sensenich propeller M74DM58 or 74DM6-0-58. Maxi- mum baggage may be increased to 300 lbs. by the installa- tion of Piper Kit 756962, Sensenich propeller M74DM58 or 74DM6-0-58 and when modified in accordance with Piper drawing 66671. See Page 2A of the weight and balance section for proper loading of baggage). S/N 28-20940 and up. (See Page 2A of the weight and balance section for proper loading of baggage). S/N 28-20940 and up. (Aircraft are eligible for 300-lb maxi-| mum baggage when modified in accordance with Piper draw- ing 66671. See Page 2A of the weight and balance section for proper loading of baggage). The datum used is 78.4 inches ahead of the wing leading edge at the section of the straight and tapered section. C. G. Range 1. Normal Category Weight (Pounds) Forward Limit (In. Aft of Datum) Rearward Limit (In. Aft of Datum) 88.4 85.9 84.0 2150 1975 1650 2. Utility Category Weight Forward Limit (Pounds) (In. Aft of Datum) Rearward Limit (In. Aft of Datum) 1950 1650 85.8 84.0 86.5 86.5 95.9 95.9 95.9 FAA APPROVED 2/14/64 Straight line variation between given points. NOTE: It is the responsibility of the airplane owner and/or the pilot to insure that the airplane is properly loaded. See weight and balance section for loading information. REVISED 1/6/70 Rev. No. 19 PREPARED CHECKED PIPER AIRCRAFT CORP. DEVELOPMENT CENTER, VERO BEACH, FLA. Airplane Flight Manual Model PA-28-140 APPROVED Maneuvers 1. 2. Placards REPORT VB-160 PAGE 3 of 7 Normal Category - All acrobatic maneuvers including spins prohibited. Utility Category - Approved maneuvers for Utility Category only. - Spins (Flaps Up) Steep Turns Lazy Eights Chandelles 1. In full view of the pilot: 2. 3. 4. 5. Entry Speed Stall 129 mph 129 129 "THIS AIRPLANE MUST BE OPERATED AS A NORMAL OR UTILITY CATEGORY AIR PLANE IN COMPLIANCE WITH THE OPERATING LIMITATIONS STATED IN THE FORM OF PLACARDS, MARKINGS AND MANUALS. ALL MARKINGS AND PLACARDS ON THIS AIRPLANE APPLY TO ITS OPERATION AS A UTILITY CATEGORY AIRPLANE. FOR NORMAL AND UTILITY CATEGORY OPERATIONS, REFER TO THE AIRPLANE FLIGHT MANUAL. FOR SPIN RECOVERY, USE FULL RUDDER AGAINST SPIN, FOL- LOWED IMMEDIATELY BY FORWARD WHEEL. NO ACROBATIC MANEUVERS (INCLUDING SPINS) ARE APPROVED FOR NORMAL CATEGORY OPERATIONS. " Adjacent to upper door latch: "ENGAGE LATCH BEFORE FLIGHT." On aft side of baggage compartment: "UTILITY CATEGORY OPERA- TION NO BAGGAGE OR AFT PASSENGERS ALLOWED. NORMAL CATEGORY OPERATION SEE AIRPLANE FLIGHT MANUAL WEIGHT BALANCE SECTION FOR BAGGAGE AND AFT PASSENGER LIMITA- TIONS." - On the instrument panel in full view of the pilot when the oil cooler winterization kit is installed: "OIL COOLER WINTERIZATION PLATE TO BE REMOVED WHEN AMBIENT TEMPERATURE EXCEEDS 50°F." On the instrument panel in full view of the pilot when the autoflite is installed: "FOR HEADING CHANGES: PRESS DISENGAGE SWITCH ON CONTROL WHEEL. CHANGE HEADING. RELEASE DISENGAGE SWITCH. FAA APPROVED 2/14/64 REVISED 1/6/70 Rev. No. 19 PREPARED CHECKED APPROVED PIPER AIRCRAFT CORP. DEVELOPMENT CENTER, VERO BEACH, FLA. REPORT VB-160 Airplane Flight Manual Model PA-28-140 PAGE 4 of 7 Placards (Cont'd) 6. 7. 8. 9. In full view of the pilot: Utility Category Only Acrobatic maneuvers are limited to the following: Spins (Flaps Up) Steep Turns ... Entry Speed Stall 129 mph Lazy Eights Chandelles 129 129 In full view of the pilot: "ROUGH AIR OR MANEUVERING SPEED - 129 MPH. ་་ On the instrument panel in full view of the pilot when the AutoFlite II is installed; "TURN AUTOFLITE ON. ADJUST TRIM KNOB FOR MINIMUM HEAD- ING CHANGE. FOR HEADING CHANGE, PRESS DISENGAGE SWITCH ON CONTROL WHEEL, CHANGE HEADING, RELEASE SWITCH. ROTATE TURN KNOB FOR TURN COMMANDS. PUSH TURN KNOB IN TO ENGAGE TRACKER. PUSH TRIM KNOB IN FOR HI SENSITIVITY. LIMITATIONS AUTOFLITE OFF FOR TAKEOFF AND LANDING. " On the instrument panel in full view of the pilot when the supple- mentary white strobe lights are installed: "WARNING - TURN OFF STROBE LIGHTS WHEN TAXIING IN VICINITY OF OTHER AIRCRAFT, OR DURING FLIGHT THROUGH CLOUD, FOG OR HAZE." Airspeed Instrument Markings RED radial line YELLOW arc Never Exceed Caution Range (Smooth Air Only) GREEN arc Normal Operating Range WHITE arc Flaps Down Range FAA APPROVED 2/14/64 REVISED 8/10/70 Rev. No. 20 171 mph (148 knots) 140 to 171 mph (121 to 148 knots) 64 to 140 mph (56 to 121 knots) 55 to 115 mph (48 to 100 knots) PREPARED CHECKED PIPER AIRCRAFT CORP. DEVELOPMENT CENTER, VERO BEACH, FLA. Airplane Flight Manual Model PA-28-140 APPROVED REPORT VB-160 PAGE 5 of 7 2. Procedures 1. The stall warning system is inoperative with the master switch off. Section 2. The electric fuel pump must be on for both takeoff and landing. 3. 4. 5. Except as noted above, all operating procedures for this airplane are normal. (Electric Pitch Trim Installation Without Pitch Trim Switch) The following emergency information applies in case of electric pitch trim malfunction: a. b. C. In case of malfunction, disengage electric pitch trim by pulling out circuit breaker on instrument panel. In emergency, electric pitch trim may be overpowered using manual pitch trim. In cruise configuration, malfunction results in 10° pitch change and 30 ft. altitude variation. (Auto Flite Installation Only) The following emergency information applies in case of autoflite malfunction: a. In case of malfunction PRESS disconnect switch on pilot's control wheel. b. Rocker switch on instrument panel - OFF. C. d. e. Unit may be overpowered manually. In cruise configuration malfunction, 3 seconds delay results in 60° bank, and 100' altitude loss. In approach configuration malfunction, 1 second delay results in 10° bank and O' altitude loss. FAA APPROVED 2/14/64 REVISED 1/6/70 Rev. No. 19 PREPARED CHECKED PIPER AIRCRAFT CORP. DEVELOPMENT CENTER, VERO BEACH, FLA. Airplane Flight Manual Model PA-28-140 APPROVED REPORT VB-160 PAGE 6 of 7 2. Procedures Section (Cont'd) 6. (Electric Pitch Trim Installation With Pitch Trim Switch) 7. The following emergency information applies in case of electric pitch trim malfunction: a. In case of malfunction, disengage electric pitch trim by pushing pitch trim switch on instrument panel to OFF position. b. C. In an emergency, electric pitch trim may be overpowered using manual pitch trim. In cruise configuration, malfunction results in 10° pitch change and 30' altitude variation. (AutoFlite II Installation Only) I II Limitations: AutoFlite off for takeoff and landing. Procedures: a. Normal Operation - Refer to Manufacturer's Operation Manual. Emergency b. 1. In case of malfunction PRESS disconnect switch on pilot's control wheel. FAA APPROVED 2/14/64 REVISED 8/10/70 Rev. No. 20 2. Rocker switch on instrument panel OFF. - 3. Unit may be overpowered manually. 4. 5. In cruise configuration malfunction, 3 seconds delay results in 60° bank, and 100' altitude loss. In approach configuration malfunction, 1 second delay results in 10° bank and O' altitude loss. PREPARED CHECKED APPROVED PIPER AIRCRAFT CORP. DEVELOPMENT CENTER, VERO BEACH, FLA. REPORT VB-160 Airplane Flight Manual Model PA-28-140 PAGE 7 of 7 2. Procedures 8. Section (Cont'd) 3. Performance Section (AutoControl III Installation Only) I Limitations: AutoPilot off during takeoff and landing. II Procedures: a. Normal Operation - Refer to Manufacturer's Operation Manual. b. Emergency In case of malfunction, disengage manual controls. 1. 2. In emergency, pilot may be overpowered manually. 3. In cruise configuration malfunction, 3 seconds delay results in 60° bank and 100 ft. altitude loss. 4. In approach configuration malfunction, 1 second delay results in 10° bank and 0 ft. altitude loss. All performance is given for a weight of 2150 pounds. Loss of altitude during stalls can be as great as 200 feet, depending on configuration and power. Stalling speeds, in MPH, power off, versus angle of bank (Calibrated Airspeed): Angle of Bank 0 Flaps Up 64 Flaps Down 55 261 20 66 128 40 50 73 80 02: 58 1 60 91 FAA APPROVED 2/14/64 REVISED 8/10/70 Rev. No. 20