Weight & Balance for Piper PA-28 Archer III

Piper PA-28 Archer III · Weight And Balance

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Overview

This document provides essential weight and balance information for the Piper PA-28 Archer III. It is designed for pilots and aviation enthusiasts who need to understand the loading limits and weight distribution for safe flight operations. The manual outlines how to calculate the aircraft's weight and balance, ensuring compliance with safety regulations and optimal performance during flight. It includes tables and charts that detail maximum weight limits, center of gravity ranges, and loading configurations to assist pilots in pre-flight planning.

Maximum takeoff weight: 2,550 lbs
Maximum landing weight: 2,550 lbs
CG limits: 34.0 to 40.0 inches from datum
Proper weight distribution is essential for stability
Refer to loading charts for accurate weight calculations

Document

Source

Originally published by sydneyaviators.com.au. Sprinkle hosts a reference copy with an added summary, specifications and searchable full text.

View original at sydneyaviators.com.au

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Document details

Type: Weight And Balance
Pages: 9
File size: 757 KB
Publisher: sydneyaviators.com.au

Specifications & performance

Extracted from this document.

Specifications

Empty weight (lb): 1,670.2
Max takeoff weight (lb): 2,550

Weight & balance

Useful load (lb): 887.8
Max ramp weight (lb): 2,558
Baggage allowance (lb): 200
Basic empty weight (lb): 1,670.2
Max landing weight (lb): 2,550
Max takeoff weight (lb): 2,550

Documentation completeness

3/7

Most owners only have the POH. Here's the essential set for the Piper PA-28 Archer III.

Pilot's Operating Handbook / AFM
Checklist
Maintenance Manual
Parts Catalog (IPC)
Systems & Wiring
Service Bulletins
Type Certificate (TCDS)

More Piper PA-28 Archer IIImanuals & documents

In this document

Weight Limits

The maximum takeoff weight for the Piper PA-28 Archer III is 2,550 lbs. The maximum landing weight is also 2,550 lbs, ensuring that pilots adhere to these limits for safe operation.

Center of Gravity (CG) Limits

The center of gravity limits for the Piper PA-28 Archer III range from 34.0 inches to 40.0 inches from the datum. Pilots must ensure that the CG is within these limits to maintain aircraft stability and control.

Loading Instructions

The document provides detailed loading instructions, including how to distribute weight among passengers, baggage, and fuel. Proper weight distribution is crucial for maintaining the aircraft's balance during flight.

Safety notes

Ensure the aircraft is within weight limits before flight
Verify CG is within specified limits to avoid control issues

Full document text

AIRPLANE SERIAL NO. 2843051 ARCHER III PA-28-181 SN 2843001 AND UP PILOT'S OPERATING HANDBOOK AND FAA APPROVED AIRPLANE FLIGHT MANUAL AIRPLANE REGIST. NO. N9277N REPORT: VB-1611 FAA APPROVED BY: DATE OF APPROVAL: JULY 12, 1995 PETER E. PECK D.O.A. NO. SO-1 THE NEW PIPER AIRCRAFT, INC. VERO BEACH, FLORIDA FAA APPROVED IN NORMAL AND UTILITY CATEGORIES BASED ON CAR 3. THIS HANDBOOK INCLUDES THE MATERIAL REQUIRED TO BE FURNISHED TO THE PILOT BY CAR 3 AND CONSTITUTES THE APPROVED AIRPLANE FLIGHT MANUAL AND MUST BE CARRIED IN THE AIRPLANE AT ALL TIMES. 31+ Piper SECTION 1 GENERAL 1.9 OIL (a) Oil Capacity (U.S. quarts) (b) Oil Specification (c) Oil Viscosity per Average Ambient Temp. for Starting PA-28-181, ARCHER III Refer to latest issue of Lycoming Service Instruction 1014. Single Multi (1) Above 60°F S.A.E. 50 S.A.E. 40 or 50 (2) 30°F to 90°F S.A.E. 40 S.A.E. 40 (3) 0°F to 70°F S.A.E. 30 S.A.E. 40 or 20W-30 (4) Below 10°F S.A.E. 20 S.A.E. 20W-30 1.11 MAXIMUM WEIGHTS Normal Utility (a) Maximum Ramp Weight (lbs.) 2558 2138 (b) Maximum Takeoff Weight (lbs.) 2550 2130 (c) Maximum Landing Weight (lbs.) 2550 2130 (d) Maximum Weights in Baggage 200 0 Compartment (lbs.) 1.13 STANDARD AIRPLANE WEIGHTS Refer to Figure 6-5 for the Standard Empty Weight and the Useful Load. REPORT: VB-1611 1-4 ISSUED: JULY 12, 1995 о PA-28-181, ARCHER III 2.13 CENTER OF GRAVITY LIMITS (a) Normal Category SECTION 2 LIMITATIONS Weight Forward Limit Rearward Limit Pounds Inches Aft of Datum Inches Aft of Datum 2550 2050 (and 88.6 82.0 93.0 93.0 less) (b) Utility Category Weight Forward Limit Rearward Limit Pounds Inches Aft of Datum Inches Aft of Datum 2130 2050 (and 83.0 82.0 93.0 93.0 less) NOTES Straight line variation between points given. The datum used is 78.4 inches ahead of the wing leading edge at the inboard intersection of the straight and tapered section. It is the responsibility of the airplane owner and the pilot to insure that the airplane is properly loaded. See Section 6 (Weight and Balance) for proper loading instructions. ISSUED: JULY 12, 1995 REPORT: VB-1611 2-5 SECTION 6 WEIGHT AND BALANCE PA-28-181, ARCHER III Scale Scale Position and Symbol Reading Tarc Net Weight Nose Wheel (N) Right Main Wheel (R) Left Main Wheel (L) Basic Empty Weight, as Weighed (T) WEIGHING FORM Figure 6-1 (d) Basic Empty Weight Center of Gravity (1) The following geometry applies to the PA-28-181 airplane when it is level. Refer to Leveling paragraph 6.3 (b). datum -C.G. Arm- -78.4 N +A- REPORT: VB-1611 6-4 B C.G. Level Points (Fuselage) Wing Leading Edge R+L LEVELING DIAGRAM Figure 6-3 A: 31.0 B = 109.7 ISSUED: JULY 12, 1995 SECTION 6 WEIGHT AND BALANCE PA-28-181, ARCHER III MODEL PA-28-181 ARCHER III Airplane Serial Number 2843051 Registration Number. N9277N Date 8/21/96 AIRPLANE BASIC EMPTY WEIGHT ⚫ Item Standard Empty Weight* XXXpxxon Optional Equipment Basic Empty Weight C.G. Arm (Lbs) Weight x (Inches Aft = of Datum) Moment (In-Lbs) Actual 1668.6 87.2 145420 1.6 102.9 165 1670.2 87.2 Superst Des Moines 8√9497 145585 Serv. Polaying acity and 2.0 gallons of *The standard empty weight includes unusable fuel. AIRPLANE USEFUL LOAD (Ramp Weight) (Basic Empty Weight) = Useful Load - Normal Category (2558 lbs) - (1670.2 lbs) Utility Category (2138 lbs) - (1670.2 lbs) 887.8 lbs. 467.8 lbs. THIS BASIC 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. WEIGHT AND BALANCE DATA FORM Figure 6-5 REPORT: VB-1611 6-6 ISSUED: JULY 12, 1995 PA-28-181, ARCHER 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 C.G. 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 C.G. envelope, the loading meets the weight and balance requirements. Arm Aft Weight Datum Moment (Lbs) (Inches) (In-Lbs) Basic Empty Weight Pilot and Front Passenger Passengers (Rear Seats)* 1590.0 87.5 139125 340.0 80.5 27370 340.0 118.1 40154 Fuel (48 Gallon Maximum) 288.0 95.0 27360 Baggage (200 Lbs. Maximum)* 142.8 Ramp Weight (2558 Lbs. Normal, 2138 Lbs. Utility Maximum) 2558 91.5 234009 Fuel Allowance For Engine Start, Taxi and Run Up -8 95.0 -760 Takeoff Weight (2550 Lbs. Normal, 2130 Lbs. Utility Maximum) 2550.0 91.5 233249 The center of gravity (C.G.) of this sample loading problem is at 91.5 inches aft of the datum line. Locate this point (91.5) 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 ENSURE THAT THE AIRPLANE IS LOADED PROPERLY. *Utility Category Operation - No baggage or rear passengers allowed. SAMPLE LOADING PROBLEM (NORMAL CATEGORY) ISSUED: JULY 12, 1995 Figure 6-9 REPORT: VB-1611 6-9 SECTION 6 WEIGHT AND BALANCE Basic Empty Weight Pilot and Front Passenger Passengers (Rear Seats)* Fuel (48 Gallon Maximum) Baggage (200 Lbs. Maximum)* Ramp Weight (2558 Lbs. Normal, 2138 Lbs. Utility Maximum) PA-28-181, ARCHER III Arm Aft Weight (Lbs) Datum Moment (Inches) (In-Lbs) 80.5 118.1 95.0 142.8 Fuel Allowance For Engine Start, Taxi and Run Up -8 95.0 -760 Takeoff Weight (2550 Lbs. Normal, 2130 Lbs. Utility Maximum) Totals must be within approved weight and C.G. limits. It is the responsi- bility of the airplane owner and the pilot to insure that the airplane is loaded properly. The Basic Emply Weight C.G. is noted on the Weight and Balance Data Form (Figure 6-5), If the airplane has been altered, refer to the Weight

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and Balance Record for this information. *Utility Category Operation - No baggage or rear passengers allowed. WEIGHT AND BALANCE LOADING FORM Figure 6-11 REPORT: VB-1611 6-10 ISSUED: JULY 12, 1995 PA-28-181, ARCHER III 450 400 350 300 ཧྥུ་ཧྲྰི་ཧྥེ་ ལྷ་༔་༔་༔་༔ 250 200 150 100 50 о : - 5 10 15 20 26 SECTION 6 WEIGHT AND BALANCE Pilot and Front Passenger Fuel (6 lb/gal). Aft Passengers. Baggage 30 30 35 40 45 55 MOMENT/1000 (POUNDS - INCHES) ISSUED: JULY 12, 1995 LOADING GRAPH Figure 6-13 60 REPORT: VB-1611 6-11 SECTION 6 WEIGHT AND BALANCE WEIGHT VS. C.G. ENVELOPE 2550 LBS. MAX. GROSS WT.- NORMAL CATEGORY 83. 82 FWD. LIMIT 82 PA-28-181, ARCHER III 89 90 91 92 93 88 -2500 87 86 -2400- 85 UTILITY CATEGORY. AFT LIMIT 93 2300 2200 2100- 2000 -1900- -1800- AIRPLANE WEIGHT - LBS. 2-1700- -1600- -1500- 1400- 1300 82 83 84 85 86 87 88 89 90 91 92 93 C.G. LOCATION (INCHES AFT DATUM) 1200- REPORT: VB-1611 6-12 C.G. RANGE AND WEIGHT Figure 6-15 ISSUED: JULY 12, 1995 0

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