warrior-iii-section-6.pdf

Piper PA-28 Cadet · Weight And Balance

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Overview

This document provides essential weight and balance information for the Piper PA-28-161 Warrior III. It outlines the procedures for weighing the aircraft, calculating the center of gravity (C.G.), and ensuring that the aircraft is loaded within the approved limits for safe operation. The manual emphasizes the importance of maintaining the aircraft's weight and C.G. within specified ranges to achieve optimal performance and safety. Pilots and aircraft owners are responsible for ensuring that the aircraft is loaded correctly before flight, and the document includes forms and data necessary for tracking weight changes and modifications.

The basic empty weight of the PA-28-161 Warrior III is 1554.2 lbs.
The maximum ramp weight is 2447 lbs for normal category operations.
The useful load for normal operations is 892.8 lbs.
The center of gravity must be maintained within specified limits to ensure safe flight characteristics.
Fuel capacity is 48 gallons, with 2 gallons considered unusable.

Document

Source

Originally published by www.ou.edu. Sprinkle hosts a reference copy with an added summary, specifications and searchable full text.

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Document details

Type: Weight And Balance
Year: 1995
Pages: 15
File size: 8.2 MB
Publisher: www.ou.edu

Specifications & performance

Extracted from this document.

Specifications

Empty weight (lb): 1,554.2
Fuel capacity (gal): 48
Max takeoff weight (lb): 2,440

Weight & balance

Useful load (lb): 892.8
Max ramp weight (lb): 2,447
Baggage allowance (lb): 200
Basic empty weight (lb): 1,554.2
Max takeoff weight (lb): 2,440

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In this document

General

This section explains the importance of maintaining the aircraft's weight and center of gravity (C.G.) within approved limits. It highlights the consequences of misloading, including reduced performance and potential safety hazards. The section also discusses the basic empty weight and C.G. location, which are critical for calculating the loaded aircraft's weight and balance.

Airplane Weighing Procedure

This section details the procedure for weighing the Piper PA-28-161 Warrior III, including preparation steps such as removing excess items and defueling. It describes how to level the aircraft and record the weight on scales, ensuring accurate measurements for determining the basic empty weight and C.G. location.

Weight and Balance Data and Record

This section provides specific weight and balance data for the aircraft, including the basic empty weight, C.G. location, and useful load. It emphasizes the need to update the Weight and Balance Record whenever modifications are made that affect weight or moment.

Weight and Balance Determination for Flight

This section outlines the steps for calculating the total weight and C.G. location for flight. It includes instructions for adding the weight of passengers, baggage, and fuel, and using graphs to ensure that the loading meets the weight and balance requirements.

Safety notes

Misloading can lead to reduced performance and safety hazards.
It is the pilot's responsibility to ensure the aircraft is loaded properly before flight.

Full document text

1 TABLE OF CONTENTS SECTION 6 WEIGHT AND BALANCE Paragraph No. Page No. 6.1 General 6-1 6.3 Airplane Weighing Procedure 6-2 6.5 Weight and Balance Data and Record.......................................... 6-6 6.7 Weight and Balance Determination for Flight 6-11 Equipment List (Form 240-0199) Supplied with aircraft paperwork REPORT: VB-1610 6-i PA-28-161, WARRIOR III SECTION 6 WEIGHT AND BALANCE SECTION 6 WEIGHT AND BALANCE 6.1 GENERAL In order to achieve the performance and flying characteristics which are designed into the airplane, it must be flown with the weight and center of gravity (C.G.) position within the approved operating range (envelope). Although the airplane offers a flexibility of loading, it cannot be flown with the maximum number of adult passengers, full fuel tanks and maximum baggage. With this loading flexibility comes responsibility. The pilot must insure that the airplane is loaded within the loading envelope before takeoff. Misloading carries consequences for any aircraft. An overloaded air- plane will not take off, climb or cruise as well as a properly loaded one. 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 CiG, is too far aft, the airplane may rotate prematurely on takeoff or tend 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 airplane, however, will perform as intended. Before the airplane is licensed, it is weighed, and a basic empty weight and e.G. location is computed (basic empty weight consists of the standard empty weight of the airplane plus the optional equipment). Using the basic empty weight and e.G. location, the pilot can easily determine the weight and e.G. position for the loaded airplane by computing the total weight and moment and then determining whether they are within the approved envelope. ISSUED: JULY 12, 1995 REPORT: VB-1610 6-1 SECTION 6 WEIGHT AND BALANCE PA-28-161, WARRIOR III The basic empty weight and e.G. location are recorded in the Weight and Balance Data Form (Figure 6-5) and the Weight and Balance Record (Figure 6-7). The current values should always be used. Whenever new equipment is added or any modification work is done, the mechanic responsible for the work is required to compute a new basic empty weight and e.G. position and to write these in the Aircraft Log Book and the Weight and Balance Record. 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 loaded 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 basic empty weight, e.G. position, and useful load. Note that the useful load includes usable fuel, baggage, cargo and passengers. Following this is the method for computing takeoff weight and c.o. 6.3 AIRPLANE WEIGHING PROCEDURE At the time of licensing, Piper provides each airplane with the basic empty weight and center of gravity location. This data is supplied by Figure 6-5. The removal or addition of equipment or airplane modifications can affect the basic empty weight and center of gravity. The following is a weighing procedure to determine this basic empty weight and center of gravity location: (a) Preparation (1) Be certain that all items checked in the airplane equipment list are installed in the proper location in the airplane. (2) Remove excessive dirt, grease, moisture, and foreign items, such as rags and tools, from the airplane before weighing. REPORT: VB-1610 6-2 ISSUED: JULY 12, 1995 PA-28-161, WARRIOR ill SECTION 6 WEIGHT AND BALANCE (3) Defuel airplane. Then open all fuel drains until all remain- ing fuel is drained. Operate engine on each tank until all undrainable fuel is used and engine stops. Then add the unusable fuel (2.0 gallons total, 1.0 gallon each wing). CAUTION Whenever the fuel system is completely drained and fuel is replenished, it will be necessary to run the engine for a minimum of three minutes at 1000 RPM on each tank to insure no air exists in the fuel supply lines. (4) Fill with oil to full capacity. (5) Place pilot and copilot seats in fourth (4th) notch, aft of forward position. Put flaps in 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 should be closed. (6) Weigh the airplane inside a closed building to prevent errors in the scale readings due to wind. (b) Leveling (1) With airplane on scales, block main gear oleo pistons in the fully extended position. (2) Level airplane (refer to Figure 6-3) by deflating the nose wheel tire to center bubble on level. ISSUED: JULY 12, 1995 REPORT: VB-1610 6-3 SECTION 6 WEIGHT AND BALANCE PA·28·161, WARRIOR III (c) Weighing - Airplane Basic Empty Weight With the airplane level and brakes released, record the weight shown on each scale. Deduct the tare, if any, from each reading. Scale Net Scale Position and Symbol Reading Tare Weight Nose Wheel (N) Right Main Wheel (R) Left Main Wheel (L) Basic Empty Weight, (as Weighed) (T) WEIGHING FORM Figure 6-1 REPORT: VB·1610 6·4 ISSUED: JULY 12, 1995 PA-28-161, WARRIOR ill SECTION 6 WEIGHT AND BALANCE (d) Basic Empty Weight Center of Gravity (1) The following geometry applies to the PA-28-161 airplane when it is leveL Refer to Leveling paragraph 6.3 (b). Level Points (Fuselage) 1~••t--78.4 Wing Leading Edge A = 31.0 B = 109.7 LEVELING DIAGRAM Figure 6-3 (2) The basic empty weight center of gravity (as weighed including optional equipment, full oil and unusable fuel) can

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be determined by the following formula: e.G. Arm - N (A) + (R + L) (B) inches T Where: T == N + R + L ISSUED: JULY 12, 1995 REPORT: VB-1610 6-5 SECTION 6 WEIGHT AND BALANCE PA-28-161, WARRIOR III 6.5 WEIGHT AND BALANCE DATA AND RECORD The Basic Empty Weight, Center of Gravity Location and Useful Load listed in Figure 6-5 are for the airplane as licensed at the factory. These figures apply only to the specific airplane serial number and registration number shown. The basic empty weight of the airplane as licensed at the factory has been entered in the Weight and Balance Record (Figure 6-7). This form is provided to present the current status of the airplane basic empty weight and a complete history of previous modifications. Any change to the per- manently installed equipment or modification which affects weight or moment must be entered in the Weight and Balance Record and Equip- ment List. REPORT: VB-1610 6-6 ISSUED: JULY 12, 1995 PA-28-161, WARRIOR ill SECTION 6 WEIGHT AND BALANCE MODEL PA-28-161 WARRIOR III Airplane Serial Number 2842227 Registration Number N4810U Date 03/08/05 AIRPLANE BASIC EMPTY WEIGHT C.G. Ann Weight x (Inches Aft Moment Item (Lbs) of Datum) (In-Lbs) Actual 1546.7 85.8332 132758.2 Standard Empty Weight* Computed Optional Equipment 7.5 66.0000 495.0 Basic Empty Weight 1554.2 85.7375 133253.2 *The standard empty weight includes full oil capacity and 2.0 gallons of unusable fuel. AIRPLANE USEFUL LOAD ---- NORMAL CATEGORY OPERATION (Ramp Weight) - (Basic Empty Weight) = Useful Load Nonna1 Category (2447 lbs) - ( 1554.2 lbs) 892.8 Ibs. Utility Category (2027 lbs) - ( 1554.2 lbs) 472.8 lbs. THIS BASIC EMPTY WEIGHT, c.o AND USEFUL LOAD ARE FOR THE AIRPLANE AS LICENSED AT THE FACTORY. REFER TO APPROPRIATE AIRCRAFT RECORD WHEN ALTERATIONS HAVE BEEN MADE. WEIGHT AND BALANCE DATA FORM Figure 6-5 ISSUED: JULY 12, 1995 REPORT: VB-1610 6-7 BE(2:fION 6 WlVIGHT AND BALANC.E PA-28-161, WARRIOR ill THIS PAGE INTENTIONALLY LEFT BLANK REPORT: 'vB-1610 6-8 ISSUED: JULY 12, 1995 •...rn o: c::1 M ~ d ~ •.... ~ •.... ~ \0 \0 U, •... ~1-3 ;l> 2: 'TIt::;:j <§. ~ Cil ~ ~~ (') M ~ o 0 ~ ~ .0 ::0 ~ .~b3< ' .l.'~,9"\~}e \0<:' PA-28-161 Serial Number 2842227 Registration Number N4810U Page Number ••....... Running Basic »<; ' Weight Change 0 +'--" Empty Weight '-' '1:::l Description of Article -0 II) Date Z II) > "._- S or Modification -0 0 Wt. Arm Moment Wt. Moment (\) -0 6 .=< <C II) (Lb.) (In.) 1100 (Lb.) 1100 0:: 03/08/05 As licensed 1554.2 ~., N .00 ;11 •.... 0\ !""' :~ .~ '0 .~ S .~•... £ .~ ~ t::;:jrn t::dl"'j ;l>(":) '''t.·d 'IIZ.O itQ~ SECTION 6 WEIGHT AND BALANCE 'ON urgn ~Ir -+ ~ 00 I C'l 2 I L~_'~ 8 __~ ~ PA-28-161, WARRIOR ill .~z ~ .!:,il •.. co 0 2 O!l~ E .5 ~r----+------------------------------------~ Z § 0., ::l E! kO ~~ I .•... ..s:: co '0 ~ ~! --~------------------------------~ (-) pgAourgCI C+) poppv WEIGHT AND BALANCE RECORD (cont) Figure 6-7 (cant) REPORT: VB-1610 6-10 ISSUED: JULY 12, 1995 PA-28-161, WARRIOR III SECTION 6 WEIGHT AND BALANCE 6.7 .WEIGHT AND BALANCE DETERMINATION FOR FLIGHT (a) Add the weight of all items to be loaded to the basic empty weight. (b) Use the Loading Graph (Figure 6-13) to determine the moment of all items to be carried in the airplane. (c) Add the moment of all items to be loaded to the basic empty weight moment. (d) Divide the total moment by the total weight to determine the CG. location. (e) By using the figures of item (a) and item (d) (above), locate a point on the C.G. range and weight graph (Figure 6-15). If the point falls within the CG. envelope, the loading meets the weight and balance requirements. Arm Aft Weight Datum Moment (Lbs) (Inches) (In-Lbs) Basic Empty Weight 1500.0 85.9 128850 Pilot and Front Passenger 340.0 80.5 27370 Passengers (Rear Seats)* 340.0 118.l 40154 Fuel (48 Gallon Maximum) 267.0 95.0 25365 Baggage* (200 Lbs. Maximum) 142.8 Ramp Weight (2447 Lbs. Normal, 2027 Lbs. Utility Maximum) 2447.0 90.6 221739 Fuel Allowance For Engine Start, Taxi and Run Up -7.0 95.0 -665 Takeoff Weight (2440 Lbs. Normal, 2020 Lbs. Utility Maximum) 2440.0 90.6 221074 The center of gravity (CG.) of this sample loading problem is at 90.6 inches aft of the datum line. Locate this point (90.6) on the C.G. range and weight graph. Since this point falls within the weight - CG. 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. SAMPLE LOADING PROBLEM (NORMAL CATEGORY) Figure 6-9 ISSUED: JULY 12, 1995 REPORT: VB-1610 6-11 SECTION 6 WEIGHT AND BALANCE PA-28-161, WARRIOR III Arm Aft Weight Datum Moment (Lbs) (Inches) (In-Lbs) Basic Empty Weight Pilot and Front Passenger , 80.5 Passengers (Rear Seats)* 118.1 Fuel (48 Gallon Maximum) 95.0 Baggage* (200 Lbs. Maximum) 142.8 Ramp Weight (2447 Lbs. Normal, 2027 Lbs. Utility Maximum) Fuel Allowance For Engine Start, Taxi and Run Up -7 95.0 -665 Takeoff Weight (2440 Lbs. Normal, 2020 Lbs. Utility Maximum) Totals must be within approved weight and e.G. limits. It is the responsi- bility of the airplane owner and the pilot to insure that the airplane is loaded properly. The Basic Empty Weight CiG. is noted on the Weight and Balance Data Form (Figure 6-5). If the airplane has been altered, refer to the Weight and Balance Record for this information. *Utility Category Operation - No baggage or aft passengers allowed. WEIGHT AND BALANCE LOADING FORM Figure 6-11 REPORT: VB-1610 6-12 ISSUED: JULY 12, 1995 PA-28-161, WARRIOR ill SECTION 6 WEIGHT AND BALANCE 450 e' <:~ 400 ,,'" <i.~~ -,<:'- ~~o l'.. ~ 350 -q,~o s- ,.\~ Q,e ~ •• <:- ~ .~i; ~q~ 1 300 «'" ~~, Vi 0 z ::::> 250 0 eo f- :I: , .. C) Q,"<> i:Li 200 '0••<> ' 3: 0 <:( 0 -' 150 100 10 20 25 30 35 15 MOMENT /1000 (POUNDS· INCHES) LOADING GRAPH Figure 6-13 ISSUED: JULY 12, 1995 REPORT: VB-1610 6-13 40 SECTION 6 WEIGHT AND BALANCE PA-28-161, WARRIOR ill WEIGHT VS C.G.ENVELOPE 2440MAX.GROSS WT. NORMAL CATEGORY 86 89 90 r-~---r---r--+-~r_-+---r--~--~-1------1900 C'l III C) CD \----+---+--1--+---+--+---+--+---+----1.1- ---'-1800 ~ I- - :r \---\--1--+--1--f-_+_-+----+---+----1. ;:-- ~-1700 LI. UJ <r ~ \---\--r--_+_--r--_+_--~_+_--~_+_-f-------~-1600 « -'0. r-~_4-+-_+-~~~--+_-+-1-----~-1500 « r-;--+-~~-+~r_+__+_--I-1------1400 r-+-~_+~-+-4-~_4~~4-------1300 ~----~~~~~~~~~~~~~~--------1200 83 84 85 86 87 88 89 90 91 92 93 C.G.LOCATION(INCHESAFTDATUM) REPORT: VB-1610 6-14 C.G. RANGE AND WEIGHT Figure 6-15 ISSUED: JULY 12, 1995

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