Airplane Flight Manual

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. " In full view of the pilot: "Utility Category Only." Acrobatic maneuvers are limited to the following: Steep Turns Lazy Eights Chandelles Entry Speed 127 mph 127 127 FAA APPROVED 5/22/72 REVISED PREPARED CHECKED APPROVED Placards (cont'd) 10. 11. PIPER DEVELOPMENT 6 REPORT VB-437 .Airplane Flight Manual Model PA-28-180 PREY 5 of 2 On the instrument panel in full view of the pilot when the Auto Flite 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 SENSITI- VITY. LIMITATIONS: AUTOFLITE OFF FOR TAKEOFF AND LAND- ING." On the instrument panel in full view of the pilot when the supplement- ary 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 Never Exceed YELLOW arc Caution Range (Smooth Air Only) 171 mph (148 knots) 140 to 171 mph (121 to 148 knots) GREEN arc Normal Operating Range 68 to 140 mph (59 to 121 knots) WHITE arc Flap Down Range 61 to 115 mph (53 to 100 knots) Air Conditioned Airplanes. Air Conditioner must be off for takeoff and landing. 2. Procedures Section 1. The stall-warning system is inoperative with the master switch off. 2. 3. FAA APPROVED 5/22/72 Electric fuel pump must be on for both landing and takeoff. The PA-28-180 airplane is approved under FAA Regulation CAR 3 which prohibits intentional spins for both normal and utility category operation. The following information is noteworthy: a. The stall characteristics of the PA-28-180 are normal with the nose pitching down moderately following the stall, occa- sionally with a moderate roll which can be corrected by normal use of ailerons and rudder against the roll. REVISED PREPARED CHECKI PIPER AIRCRAFT CORP. Development Center, Vero Beach, Fla. Airplane Flight Manual Model PA-28-180 APPROVED Procedures Section (cont'd) REPORT VB-437 PAGE 6 of 9 4. 5. b. Prolonged use of full rudder during stall practice may result in a rapid roll followd by a spin and should be avoided. Recovery from an incipient spin may be effected in less than one additional turn by use of opposite rudder followed by full forward control wheel. c. In the event that a fully developed spin is inadvertently experi- enced, recovery is best made by using full opposite rudder followed by full forward wheel and full opposite aileron. The control positions against the spin should be maintained during the entire recovery, which may require several turns and a substantial loss of altitude if the airplane is loaded heavily with a rearward center of gravity. Except as noted above, all operating procedures for this airplane are normal. (Electric Pitch Trim Installation Only with Pitch Trim Switch) 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. In an emergency, electric pitch trim may be overpowered using manual pitch trim. c. In cruise configuration, malfunction results in 10° pitch change and 200 ft. altitude variation. d. In approach configuration, a malfunction can result in a 5º change and 50 ft. altitude loss. pitch 6. (Autoflite 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. Unit may be overpowered manually. FAA APPROVED 5/22/72 REVISED 6/29/72 PREPARES CHECKBO APPROVED Procedures Section (cont'd) 7. PIPER AIRCRAFT CORP. DEVELOPMENT CENTER, VERO BEACH, FLA. REPORT VB-437 Airplane Flight Manual Model PA-28-180 PAGE 7 of 9 d. In climb, cruise or descending flight an autopilot runaway, with a 3 second delay could result in a 50° bank, and 190 ft. altitude loss. e. In approach configuration an autopilot runaway, with a 1 second delay could result in a 15° bank and 40 ft. altitude loss. (AutoControl III Installation Only) I. Limitations: Autopilot off during takeoff and landing. Auto Flite use prohibited above 160 mph CAS. II. Procedures: a. Normal Operation Refer to Manufacturer's Operation Manual b. Emergency 1. In case of malfunction, turn off autopilot. 2. In emergency, autopilot may be overpowered manually. 3. In climb, cruise or descending flight an autopilot runaway, with a 3 second delay could result in 60° bank and 100 ft. altitude loss. 4. In approach configuration an autopilot runaway, with a 1 second delay could result in 10° bank and 10 ft. altitude loss. 8. (AutoFlite II Installation Only) I. Limitations: Auto Flite off for takeoff and landing. II. Procedures: Auto Flite use prohibited above 160 mph CAS. a. Normal Operation - Refer to Manufacturer's Operation Manual. b. Emergency 1. In case of malfunction PRESS disconnect switch on pilot's control wheel. 2. Rocker switch on instrument panel - OFF. FAA APPROVED 5/22/72 REVISED 9/1/72 - PREPARED CHICKED APPROVED PIPER AIRCRAFT CORP. DEVELOPMENT CENTER, VERO BEACH, FLA. REPORT VB-437 Airplane Flight Manual Model PA-28-180 PAGE 8 of 9 Procedures Section (cont'd) 3. Autopilot may be overpowered manually. 4. In climb, cruise or descending flight an autopilot runaway, with a 3 second delay could result in 60° bank, and 190 ft. altitude loss. 5. In approach configuration an autopilot runaway, with a 1 second delay results in 15° bank and 40 ft. altitude loss. 9. (Air Conditioned Models Only) Prior to takeoff, the air conditioner should be checked for proper operation as follows: a. Check aircraft master switch on b. (For aircraft serial numbers 7205092 through 7305071). Turn the air conditioner control switch to "AIR COND” · the "AIR COND DOOR OPEN" warning light will turn on, thereby indicating proper air conditioner condenser door actuation. c. d. (For aircraft serial numbers 7305072 and up). Turn the air conditioner control switch to "ON" and the fan switch to one of the operating positions - the "AIR COND DOOR OPEN" warning light will turn on, thereby indicating proper air conditioner condenser door actuation. - Turn the air conditioner control switch to OFF the "AIR COND DOOR OPEN" warning light will go out, thereby indicating the air conditioner condenser door is in the up position. If the "AIR COND DOOR OPEN" light does not respond as specified above, an air conditioner system or indicator bulb malfunction is indicated and further investigation should be conducted prior to flight. The above operational check may be performed during flight if an inflight failure is suspected. FAA APPROVED 5/22/72 REVISED 3/20/73 10. Air Conditioned Models only: Warning The air conditioner must be off to insure normal takeoff performance. - PREPARED CHECKED PIPER AIRCRAFT CORP. Airplane Flight Manual DEVELOPMENT CENTER, VERO BEACH, FLA. Model PA-28-180 APPROVED 3. Performance Section FAA APPROVED 5/22/72 REVISED 3/20/73 REPORT VB-437 PAGE 9 of 9 The following performance figures were obtained during FAA type tests and may be realized under conditions indicated with the airplane and engine in good condition and with average piloting technique. All performance is given for 2450 pounds. Loss of altitude during stalls varied from 100 to 250 feet, depending on configuration and power. Stalling speeds, in mph, power off, versus angle of bank . (Calibrated Airspeed): Angle of Bank 0 20 Flaps Up 68 Flaps Down 61 22 1 40 70 78 1 1888 50 60 85 96 1 Air Conditioned Models only: When the full throttle position is not used or in the event of a malfunction which causes the compressor to operate and the condenser door to remain extended, a decrease in rate of climb of as much as 100 fpm can be expected at all altitudes. PREPARED CHECKED APPROVED PIPER AIRCRAFT CORP. Development Center, Vero Beach, Fla. REPORT VB-439 WEIGHT & BALANCE DATA AND EQUIPMENT LIST MODEL PA-28-180 DATE May 17, 1972 Weight and Balance Data! Model PA-28-180 PAGE Title APPLICABLE TO SERIAL NUMBERS 28-7305001 THROUGH 28-7305601 AND SERIAL NUMBER 28-E13 PREPARED CHECKED APPROVED PIPER AIRCRAFT CORP. Development Center, Vero Beach, Fla. REPORT VB-439 Weight and Balance Data Model PA-28-180 PAGE ii Log of Revisions APPROVED DATE REVISION NO. PAGE DESCRIPTION 1 All Retyped Entire Report 1 10 13 19 Rephrased Empty Weight Definition Replaced Altimeter 99009-2, -3, -4 or -5 with PS50008-2 or -3 Replaced Turn Coordinators 99001 and 99004 and Turn and Bank 99005 with Turn and Slip PS50030-2 or -3 Manifold Pressure Gauge changed from 99006 to PS50031-3 or -4 Corrected King KT76/78 and King KMA-20 Weights, Arms, and Moments 2 + 3 8 16 N. Terrant 3 A49.1972 Corrected Graph of Flight Envelope Corrected Engine, Fuel Pump, Oil Cooler and Air Filter Weights, Arms and Moments. Corrected COMM Antenna Cable Arms and Moments, Boldloven 21 aug. 1972 16a Added Page and Anti Static Kit 4 15 Added King KX-175, KN-73, KN-77 and KNI-520 Installations 5 15 Corrected KX-175 (2nd) Moment TITLE Added Serial Number Effectivity 7 TITLE Added Serial Number 28-E13 N. Tennant 30 Nov 1972 N. Terrent, 25 JAN 1973 1. Tennant 30 JAN 1973 N. Jernant 12 Sept. 1973 14 May 1974 PREPARED CHECKED APPROVED PIPER AIRCRAFT CORP. Development Center, Vero Beach, Fla. REPORT VB-439 WEIGHT AND BALANCE DATA MODEL PA-28-180 CHEROKEE Weight and Balance Data: Model PA-28-180 PAGE 1 Section Airplane Serial Number 28-7305325. Registration Number Date *Empty Weight DUPLICATE AIRPLANE EMPTY WEIGHT C. G. Arm Item Weight (lbs) * (Inches Aft of Datum) Moment (In-Lbs) Actual Computed 10.0 103.0 1030 Unusable Fuel (13-1/3 pints) Standard Empty Weight Optional Equipment Licensed Empty Weight *Empty weight is defined as dry empty weight (including paint and hydraulic fluid) plus 1.8 lbs. undrainable engine oil AIRPLANE USEFUL LOAD (Gross Weight) (Licensed Empty Weight) = Useful Load Normal Category: (2450 lbs) lbs) lbs. Utility Category: (1950 lbs) lbs) lbs. THIS LICENSED EMPTY WEIGHT, C. G. AND USEFUL LOAD FOR THE AIRPLANE AS DELIVERED FROM THE FACTORY. REFER TO APPROPRIATE AIR CRAFT RECORD WHEN ALTERATIONS HAVE BEEN MADE. PREPARED CHECKED APPROVED PIPER AIRCRAFT CORP. Development Center, Vero Beach, Fla. REPORT VB-439 Weight and Balance Data Model PA-28-180 PAGE 2 Section 1 C. G. RANGE AND WEIGHT INSTRUCTIONS 1. Add the weight of all items to be loaded to the licensed empty weight. 2. Use the loading graph to determine the moment of all items to be carried in the airplane. 3. Add the moment of all items to be loaded to the licensed empty weight moment. 4. Divide the total moment by the total weight to determine the C. G. location. 5. By using the figures of Item 1 and Item 4, locate a point on the C. G. range and weight graph. If the point falls within the C. G. envelope, the loading meets the weight and balance requirements. SAMPLE LOADING PROBLEM (Normal Category) Weight (lbs) Arm Aft Datum (Inches) Moment (In - lbs) Licensed Empty Weight Oil (8 quarts) 15 27.5 413 Pilot and Front Passenger 340 80.5 27370 Passengers, Aft* (Rear Seat) 340 118. 1 40154 Fuel (50 Gal. Maximum) 95.0 Baggage * 142.8 Total Loaded Airplane The center of gravity (C. G.) of this sample loading is at inches aft of the datum line. Locate this point ( ) on the C. G. range and weight graph. Since this point falls within the weight C. G. envelope, this loading meets the weight and balance requirements. - IT IS THE RESPONSIBILITY OF THE PILOT AND AIRCRAFT OWNER TO INSURE THAT THE AIRPLANE IS LOADED PROPERLY. Utility Category Operation - No baggage or aft passengers allowed.