Airplane Flight Manual

SUPPLEMENT No. 7 AUTOMATIC PILOT LEAR MODEL L-2 EMERGENCY OPERATING PROCEDURE (1) (2) (3) (4) Maximum altitude lost during malfunction tests in cruise configura- tion 50 feet. Maximum altitude lost during malfunction tests in approach con- figuration 100 feet. In the event a malfunction in the autopilot performance is detected, you may readily disengage the autopilot by placing the "ENGAGE" switch in the off position. Slip clutches are provided on the servo output capstans to permit the human pilot to override the autopilot with a minimum of effort. In the event of a malfunction the following forces at the pilot's controls are required to overpower the autopilot: Rudder 30 pounds, aileron 9 pounds, and elevator 10 pounds, "If one engine becomes inoperative while in unbanked flight with the autopilot ON, the autopilot rudder servo force will attempt to compensate for the unsymmetrical power and the resulting yow will be less than 3° per second. However, if the autopilot TURN CONTROL knob is displaced following the above condition, the autopilot rudder servo force will become zero and an appreciable rate of yaw will be induced. In order to avoid the above conditions, the human pilot should disconnect the autopilot immediately subse- quent to an engine failure and retrim the aircraft prior to re- engaging the autopilot." Jmmary J. W. McNARY Assist. Chief Engineer PIPER AIRCRAFT CORPORATION Lock Haven, Pennsylvania DMCR 1-1 Approval Basis CAR 3 & 410 Sept. 1, 1955 PIPER AIRCRAFT CORPORATION Page 1 of 1 MODEL PA-23 Airplane Flight Manual SUPPLEMENT No. 9 OPTIONAL SEAT ARRANGEMENT PLACARDS REQUIRED: 2. UNDER BOTH REAR WINDOWS "Lotch seats for take-off and landing." ON BAGGAGE DOOR FRAME "When five seats are installed see weight and balance for baggage capacity and loading schedule," PROCEDURES: Since it is possible, with the addition of optional equipment, to exceed the 1 gross weight of the airplane a loading schedule is submitted for the convenience of the pilot and will be found in the weight and balance section of this manual. Any one of the loadings, which are based on the actual empty weight of the airplane, assures loading within the gross weight limits and must not be exceeded. If any item is added to the airplane which will cause a change in its empty weight, the loading schedule must be altered accordingly. Matang. J. W. McNARY Assist. Chief Engineer PIPER AIRCRAFT CORPORATION Lock Haven, Pennsylvania DMCR 1-1 PIPER AIRCRAFT CORPORATION MODEL PA-23 Airplane Flight Manual WEIGHT AND BALANCE (Cont.) Fuel ( Gal. Aux.) Passenger (1 Rear Seat) MOST REARWARD C. G. Weight 22839 30 Page 3 of 3 207940,1 1770 117 432 216 48816 24408 30260 ITEM Empty Weight Oil (4 Gal.) Arm 90,0 Moment Fuel (72 Gal. Main) Pilot and Passenger (Front Seat) Baggage 340 170 18.8 59.0 113.0 113.0 89.0 126.5 150:0 21505 2820 TOTAL 34907 9466 46 3373.76.1 Most Rearward C. G. Is Inches Aft Datum MOST REARWARD C. G. (ALTERNATE) ITEM Oil (4 Gal.) Weight Arm Empty Weight 22.839 95.1 Moment 201940 30 59.0 1770 Fuel (72 Gal. Main) 432 113.0 48816 Fuel ( Gal. Aux.) 113.0 Pilot and Passenger (Front Seat) Passenger (2 Rear Seat) 340 89.0 30260 340 126.5 43010 Baggage 150.0 Airplane Weight (Pounds) TOTAL 34259 96.8 331672.7 Most Rearward C. G. (Alternate) Is Inches Aft Datum 3600 3400 3200 APPROVED C. G. RANGE VS. WEIGHT 3000 2800 2600 2400 2200 88 89 90 PIPER 86 91 92 93 94 95 96 97 98 C. G. Inches Aft Datum AIRCRAFT 94 99 100 CORPORATION Item No. MODEL PA-23 Airplane Flight Manual EQUIPMENT LIST itzm Page 1 of 7 Weight Arm Aft. Datum PROPELLERS AND PROPELLER ACCESSORIES ―1. Two, full feathering, constant speed, propeller installations (a) Hartzell HC-82xG-2 Hubs with 7636D Blades 63 Lbs. ea, (35) Pitch settings at 30 in. sta.: Low 10°, High 80.5° (Feathered) Diameter: Not over 76 in. Not under 74.5 in. or Hartzell HC-82xG-2B Hubs with 7636D-4 blades 63 Lbs. ea. (35) Item 401 (j) required Pitch settings at 30 in. sta.: Low 12°, High 80° (Feathered) Diameter: Not over 72 in. Not under 70.5 in. X (b) Two Woodward hydraulic governor assemblies, 210080 3 Lbs. ea. (68.5) (c) Hartzell prop. spinner dome C-888 and bulkhead adapter C-885 6 Lbs. ea. (35) (d) Two Hamilton Standard hydraulic governor assemblies Model No. 1Q12 per Hartzell Modification B2 3 Lbs. ea. (68.5) PIPER AIRCRAFT CORPORATION MODEL PA-23 Airplane Flight Manual EQUIPMENT LIST (Cont.) Page 5 of 7 Item No. ✗401. Item INTERIOR EQUIPMENT Arm Weight Aft. Datum DMCR Approved Airplane Flight Manual dated Sept. 1, 1955. 403. 402, Heater, Modified Stewart Warner Model 979-B-1 or 940-B12 Lear L-2B Automatic Pilot 18 Lbs. (33) -(a) Lear L-2B Autopilot Altitude 104 Lbs. (114) Control and 1350B Approach Coupler Installed According to Lear Dwg. 701950 or - Piper Dwg. 18759. Item 301B Required. -(b) Lear L-2B Autopilot With Automatic Altitude Control In- stalled According to Lear Dwg. 701950 or Piper Dwg. 18759. Item 301B Required. -(c) Lear L-2B Autopilot Installed According to Lear Dwg. 701950 or Piper Dwg. 18759. Item 301B Required. 54 Lbs. (156) 51 Lbs. (154) PIPER AIRCRAFT CORPORATION Page 4 of 7 MODEL PA-23 Airplane Flight Manual EQUIPMENT LIST (Cont.) Item No. X 301. I Generators Item ELECTRICAL EQUIPMENT Weight Arm Aft. Datum 18 Lbs. (45) -(a) One 35 Amp. Generator-Delco-Remy 12 Volt, With Bracket (b) Auxiliary 35 Amp. Generator Delco-Remy 12 Volt, With Brackets and Relays 23 Lbs. (521 302. Battery (a) One 12 Volt 33 Amp. Hour 27 Lbs. (40.51 I 303. One Landing Light G. E. Model 4509 2 Lbs. (11.5) X 304. One Anti-Collision Light. Grimes No. D7080 Rotating Beacon Installed in Accordance With Piper Dwg. 18714 2 Lbs. (260) PIPER AIRCRAFT CORPORATION Page 2 of 3 A. MODEL PA-23 Airplane Flight Manual WEIGHT AND BALANCE (Cont.) Empty Weight C. G. Forward Main Wheel Centerline Is (N) (T) X90 Inches B. Empty Weight C. G. Aft Wing Leading Edge Is 34.5- ― (A) C. Empty Weight C. G. Aft Datum Is 80.0+(B) Inches Inches Empty weight & C. G. corrected to include all items on equipment list as of 2283.77 901 207940.9 MOST FORWARD C. G. (REDUCED WEIGHT) 1-10-85 ITEM Empty Weight Oil (4 Gal.) Fuel (25 Gal. Main) Pilot Weight Arm Moment 22839 90.1 2078167 30 59.0 1770 150 113.0 16950 170 89.0 15130 TOTAL 26 339 Most Forward C. G. (Reduced Weight) Is 91,75 3316727 Inches Aft Datum MOST FORWARD C. G. (ALTERNATE) ITEM Empty Weight Oil (4 Gal.) Fuel (72 Gal. Main) Pilot Passenger Weight Arm Moment 22839 90.1 2079407 30 59.0 1770 432 113.0 48816 170 89.0 15130 170 89.0 15130 TOTAL 3085.9 93.24 288 G Most Forward C. G. (Alternate) Is Inches Aft Datum PIPER AIRCRAFT CORPORATION Page 2 of 3 8. 9. 10. MODEL PA-23 Airplane Flight Manual SUPPLEMENT No. 7 AUTOMATIC PILOT LEAR MODEL L-2 AUTOMATIC PITCH TRIM operates whenever the autopilot is en- gaged. To manually operate the elevator trim tab, "ENGAGE" switch should be placed in the "OFF" position. AUTOMATIC ALTITUDE CONTROLLER: (IF INSTALLED). The aircraft shall be placed in a level flight attitude before the "Automatic Altitude Control" switch is placed in the "ON" position. Do not operate the "NOSE" control when the automatic altitude controller is engaged. Place the automatic altitude control in the "OFF" position before beginning a descent with the automatic pilot. AUTOMATIC APPROACH CONTROLLER: (IF INSTALLED). The automatic approach control should not be engaged until the airplane is positioned near the localizer path and at an intersection angle up to 90° (smaller angles are preferable) to the inbound ILS course. When the localizer needle begins to swing toward center the localizer button may be depressed. The airplane will then bracket the localizer beam. The maximum bank angle during the bracketing of the localizer should not exceed 30°. When the glide path needle becomes centered the "FINAL" glide path button may be depressed. This will automatically disconnect the "ALTITUDE CONTROL" and the airplane will bracket the glide path slope and begin a rate of descent commensurate with the glide path angle and airspeed. Complete "BEFORE LANDING CHECK" at this point. The controller may be disengaged from the autopilot at any time necessary for "GO-AROUND" by merely lifting the autopilot turn knob from the detent position and dropping it again. This leaves the autopilot still in normal control of the airplane and a "GO-AROUND" may be made on autopilot. If a manual "GO-AROUND" is desired, however, the autopilot "ENGAGE" switch may be turned "OFF" which will remove both controller and autopilot from control of the airplane. If the approach is carried to completion, the automatic pilot "ENGAGE" switch must be turned "OFF" prior to landing thus disconnecting both the automatic pilot and approach controller and returning the aircraft to manual control for completion of the landing. PIPER AIRCRAFT CORPORATION Page 6 MODEL PA-23 Airplane Flight Manual PERFORMANCE STALLS Loss of altitude during a single engine power-on stall is 225 feet. stall configurations result in less loss of altitude. Other Jhang J. W. McNARY Assist. Chief Engineer PIPER AIRCRAFT CORPORATION Lock Haven, Pennsylvania DMCR 1-1 Approval Basis CAR 3 & 410 Sept. 1, 1955 PIPER AIRCRAFT CORPORATION