Weight & Balance for Piper PA-28R Arrow
Piper PA-28R Arrow · Weight And Balance
Overview
This document provides the weight and balance information for the Piper PA-28R Arrow. It is intended for pilots and aviation personnel who need to ensure that the aircraft is loaded within its weight limits for safe operation. The document outlines the maximum weight limits, loading procedures, and how to calculate the center of gravity (CG) for various loading scenarios. Proper weight and balance calculations are critical for flight safety, as they affect the aircraft's performance and handling characteristics.
- Maximum takeoff weight: 2,800 lbs
- CG limits: 76 inches to 84 inches from the datum
- Follow specific loading procedures for safe weight distribution
- Example calculations help ensure accurate weight and balance assessments
Document
Source
Originally published by www.desu.edu. Sprinkle hosts a reference copy with an added summary, specifications and searchable full text.
Document details
- Type
- Weight And Balance
- Pages
- 8
- File size
- 2.5 MB
- Publisher
- www.desu.edu
Specifications & performance
Extracted from this document.
Specifications
- Max takeoff weight (lb)
- 2,650
Weight & balance
- Max takeoff weight (lb)
- 2,650
Most owners only have the POH. Here's the essential set for the Piper PA-28R Arrow.
- Pilot's Operating Handbook / AFM
- Checklist
- Maintenance Manual
- Parts Catalog (IPC)
- Systems & Wiring
- Service Bulletins
- Type Certificate (TCDS)
More Piper PA-28R Arrowmanuals & documents
In this document
Maximum Weight Limits
The maximum takeoff weight for the Piper PA-28R Arrow is 2,800 lbs. This includes the weight of the aircraft, passengers, baggage, and fuel. It is essential to ensure that the total weight does not exceed this limit to maintain safe flight operations.
Center of Gravity (CG) Limits
The CG limits for the Piper PA-28R Arrow are between 76 inches and 84 inches from the datum. Proper loading must ensure that the CG remains within these limits to avoid adverse flight characteristics.
Loading Procedures
The document outlines specific loading procedures to ensure that weight is distributed correctly within the aircraft. This includes recommendations for passenger seating arrangements and baggage placement to maintain the CG within limits.
Weight Calculation Example
An example calculation is provided to demonstrate how to determine the total weight and CG for a typical flight scenario. This includes the weights of passengers, baggage, and fuel, along with their respective moments.
Safety notes
- Always verify weight and balance before flight to ensure safety.
- Exceeding weight limits can lead to compromised aircraft performance.
Full document text
( WEIGHT AND BALANCE ARROW 1 1 In order to achieve the performance and flying characteristics which are designed into the aircraft, the Arrow must be flown with the weight and center of gravity (C.G.) position within the approved envelope. The aircraft offers flexibility of loading. However, you cannot fill the aircraft, with four adults, full fuel tanks and maximum baggage. With the flexibility comes responsibility. The pilot must insure that the airplane is loaded within the loading envelope before he makes a takeoff. Misloading carries consequences for any aircraft. An overloaded airplane will not take off. climb or cruise as well as when is properly loaded. The heavier the airplane is loaded the less climb performance it will have. Center of gravity is a determining factor in flight characteristics. If the C.G. is too far forward in any airplane, it may be difficult to rotate for takeoff or landing. If the C.G. is too far aft, the airplane may rotate prematurely on takeoff or try to pitch up during climb. Longitudinal stability will be reduced. This can lead to inadvertent stalls and even spins; and spin recovery becomes more difficult as the center of gravity moves aft of the approved limit. A properly loaded aircraft, however, will perform as intended. Before the aircraft is licensed, the Arrow is weighed and a licensed empty weight and C.G. location computed. Using the licensed empty weight and C.G. location, the pilot can easily determine the weight and C.G. position for the loaded airplane by computing the total weight and moment and then determining whether they are within the approved envelope. The licensed empty weight and C.G. location for a particular airplane are recorded in the weight and balance section of the Airplane Flight Manual. The current values should always be used. Whenever new equipment is added or any modification work is done, the mechanic respon- sible for the work is required to compute a new basic empty weight and C.G. position and to write these in the aircraft log book. The owner should make sure that it is done. A weight and balance calculation is necessary in determining how much fuel or baggage can be boarded so as to keep within allowable limits. Check calculations prior to adding fuel to insure against improper loading. The following pages are forms used in weighing an airplane in production and in computing empty weight, C.G. position, and useful load. Note that the useful load includes fuel, oil, baggage, cargo and passengers. Following this is the method for computing takeoff weight and C.G. ISSUED: MAY 14, 1973 REPORT: VB-549 PAGE 5-1 REVISED: FEBRUARY 29, 1984 MODEL:PA-28R-200 ARROW THIS PAGE INTENTIONALLY LEFT BLANK REPORT: VB-549 PAGE 5-2 MODEL: PA-28R-200 ISSUED: MAY 14, 1973 ARROW WEIGHT AND BALANCE DATA WEIGHING PROCEDURE At the time of licensing.Piper Aircraft Corporation provides each airplane with the licensed empty weight and center of gravity location. This data is on Page 5-7. The removal or addition of an excessive amount of equipment or excessive airplane modifications can affect the licensed empty weight and empty weight center of gravity. The following is a weighing procedure to determine this licensed empty weight and center of gravity location: 1. PREPARATION a. b. C. Be certain that all items checked in the airplane equipment list are installed in the proper location in the airplane. Remove excessive dirt, grease, moisture, foreign items such as rags and tools from the airplane before weighing. Defuel airplane. Then open all fuel drains until all remaining fuel is drained. Operate engine on each tank until all undrainable fuel is used and engine stops. CAUTION Whenever the fuel system is completely drained and fuel is re- plenished it will be necessary to run the engine for a minimum of 3 minutes at 1000 RPM on each tank to insure no air exists in the fuel supply lines. d. e. f. Drain all oil from the engine, by means of the oil drain, with the airplane in ground attitude. This will leave the undrainable oil still in the system. Engine oil temperature should be in the normal operating range before draining. Place pilot and copilot seats in fourth (4th) notch, aft of forward position. Put flaps in the fully retracted position and all control surfaces in the neutral position. Tow bar should be in the proper location and all entrance and baggage doors closed. Weigh the airplane inside a closed building to prevent errors in scale readings due to wind. 2. LEVELING a. With airplane on scales, block main gear oleo pistons in the fully extended position. ISSUED: MAY 14, 1973 REVISED: FEBRUARY 29, 1984 REPORT: VB-549 PAGE 5-3 MODEL: PA-28R-200 DATUM A B = ARROW b. Level airplane (see diagram) deflating nose wheel tire, to center bubble on level. 3. WEIGHING - AIRPLANE EMPTY WEIGHT a. With the airplane level and brakes released, record the weight shown on each scale. Deduct the tare, if any, from each reading. Scale Reading Tare Weight Scale Position and Symbol Nose Wheel (N) Right Main Wheel (R) Left Main Wheel (L) Airplane Empty Weight, as Weighed (T) 4. EMPTY WEIGHT CENTER OF GRAVITY a. The following geometry applies to the PA-28R-200 airplane when airplane is level (See Item 2). N C. G. ARM 78.4*. REPORT: VB-549 PAGE 5-4 MODEL: PA-28R-200 Level Points (Fuselage Left Side) R + L -Wing Leading Edge * The datum is 78.4 inches ahead of the wing leading edge at the intersection of the straight and tapered section. ISSUED: MAY 14, 1973 REVISED: APRIL 13, 1979 5. ARROW b. C. d. Obtain measurement "A" by measuring from a plumb bob dropped from the wing leading edge, at the intersection of the straight and tapered section, horizontally and parallel to the airplane centerline, to the main wheel centerline. Obtain measurement "B" by measuring the distance from the main wheel centerline, horizontally and parallel to the airplane centerline, to each side of the nose wheel axle. Then average the measurements.
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The empty weight center of gravity (as weighed including optional equipment and undrainable oil) can be determined by the following formula: C.G. Arm = 78.4A B(N) T - C. G. Arm = 78.4 + ( )-( ) ( inches LICENSED EMPTY WEIGHT AND EMPTY WEIGHT CENTER OF GRAVITY Weight Arm Moment Empty Weight (as weighed) Unusable Fuel (13 1/3 Pints) +10.0 103.0 +1030 Licensed Empty Weight ISSUED: MAY 14, 1973 REPORT: VB-549 PAGE 5-5 MODEL: PA-28R-200 1 Airplane Serial Number. Registration Number Date WEIGHT AND BALANCE DATA MODEL PA-28R-200 CHEROKEE AIRPLANE EMPTY WEIGHT ARROW Weight (Lbs) C. G. Arm (Inches Aft of Datum) Moment (In-Lbs) Item *Empty Weight Actual Computed Unusable Fuel (13-1/3 pints) 10.0 103.0 1030 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 - NORMAL CATEGORY OPERATION (Gross Weight) (Licensed Empty Weight) = Useful Load (2650 lbs) - ( lbs) ===== Ibs THIS LICENSED EMPTY WEIGHT, C.G. AND USEFUL LOAD ARE FOR THE AIRPLANE AS LICENSED AT THE FACTORY. REFER TO APPROPRIATE AIRCRAFT RECORD WHEN ALTERATIONS HAVE BEEN MADE. ISSUED: MAY 14, 1973 REPORT: VB-549 PAGE 5-7 REVISED: FEBRUARY 29, 1984 MODEL: PA-28R-200 LOAD WEIGHT (POUNDS) 450 400 350 300 250 200 150 100 50 0 05 10 15 20 LOADING GRAPH 25 25 Pilot and Front Passengers Fuel (6 lb/gal), Aft Passengers Baggage 30 30 35 40 45 50 MOMENT/1000 (POUND - INCHES) ISSUED: MAY 14, 1973 REPORT: VB-549 PAGE 5-9 MODEL: PA-28R-200 ARROW WEIGHT IN POUNDS ARROW IT IS THE RESPONSIBILITY OF THE OWNER AND PILOT TO ASCERTAIN THAT THE AIRPLANE ALWAYS REMAINS WITHIN THE ALLOWABLE WEIGHT VS. CENTER OF GRAVITY ENVELOPE WHILE IN FLIGHT. 2800 2600 2400 2200 2000 1800 1600 1400 80 C. G. RANGE AND WEIGHT 82 84 86 88 90 2 90 INCHES AFT OF DATUM 92 94 MOMENT DUE TO RETRACTING LANDING GEAR = +819 IN - LBS REPORT: VB-549 PAGE 5-10 MODEL: PA-28R-200 ISSUED: MAY 14, 1973