Weight & Balance
Piper PA-28 Cherokee 180 · Weight And Balance
Overview
This document provides the weight and balance information for the Piper PA-28 Cherokee 180. It is intended for pilots and aviation enthusiasts who need to understand the loading limits and weight distribution for safe flight operations. The document outlines the maximum weight limits, center of gravity (CG) ranges, and procedures for calculating weight and balance before flight. Proper weight and balance calculations are crucial for ensuring the aircraft's performance and safety during operations.
- Maximum takeoff weight: 2,550 lbs
- CG range: 34.0 to 40.0 inches from the leading edge of the wing
- Weight and balance calculations are essential for safe flight operations.
Document
Source
Originally published by www.mentoneflyingclub.org. Sprinkle hosts a reference copy with an added summary, specifications and searchable full text.
Document details
- Type
- Weight And Balance
- Pages
- 8
- File size
- 1.4 MB
- Publisher
- www.mentoneflyingclub.org
Specifications & performance
Extracted from this document.
Weight & balance
- Max takeoff weight (lb)
- 2,400
Most owners only have the POH. Here's the essential set for the Piper PA-28 Cherokee 180.
- Pilot's Operating Handbook / AFM
- Checklist
- Maintenance Manual
- Parts Catalog (IPC)
- Systems & Wiring
- Service Bulletins
- Type Certificate (TCDS)
More Piper PA-28 Cherokee 180manuals & documents
See all 18 →- 2021 Cherokee 180 GuideChecklist
- Airworthiness Concern SheetAirworthiness Directives
- Pilot´s Operating Handbook for the Piper PA-28-140 - Cherokee Cruiser, Piper PA-28-150/160/180 - Cherokee, Piper PA-28-151 - Cherokee Warrior, Piper PA-28-161 - Cadet, Warrior II & III Equipped with TAE 125 InstallationEmergency Procedures
- Piper Cherokee 180 ChecklistChecklist
- CHEROKEE 180 OWNER'S HANDBOOKFlight Manual
- Weight and Balance DataWeight And Balance
- Piper Cherokee Owner's HandbookWeight And Balance
- PIPER CHEROKEE 180 – PA-28-180Specifications
- Pilot's Operating HandbookPilot's Operating Handbook
- Pilot's Operating HandbookPilot's Operating Handbook
- Pilot's Operating HandbookPilot's Operating Handbook
- Airplane Flight ManualFlight Manual
In this document
Maximum Weight Limits
The maximum takeoff weight for the Piper PA-28 Cherokee 180 is 2,550 lbs. This includes the weight of the aircraft, fuel, passengers, and cargo. Pilots must ensure that the total weight does not exceed this limit to maintain safe flight characteristics.
Center of Gravity (CG) Limits
The center of gravity for the Piper PA-28 Cherokee 180 must be within the range of 34.0 inches to 40.0 inches from the leading edge of the wing at the root. Maintaining the CG within this range is essential for stable flight and control.
Weight and Balance Calculation Procedures
To calculate the weight and balance, pilots should list the weight of each occupant, baggage, and fuel. The total weight is then compared against the maximum weight limit. The CG is calculated using the moment arm for each weight item to ensure it falls within the specified CG limits.
Safety notes
- Exceeding maximum weight can lead to poor performance and control issues.
- Improper CG can result in difficulty in handling the aircraft.
Full document text
PREPARED CHECKED PIPER AIRCRAFT CORP. DEVELOPMENT CENTER, VERO BEACH, FLA. Weight and Balance Data Model PA-28-180 APPROVED REPORT VB-268 WEIGHT & BALANCE DATA AND EQUIPMENT LIST MODEL PA-28-180 DATE August 17, 1970 (SERIAL NUMBERS 28-7105001 thru 28-7205318) PAGE Title PREPARED CHECKED APPROVED PIPER AIRCRAFT CORP. DEVELOPMENT CENTER, VERO BEACH, FLA. REPORT VB-268 WEIGHT AND BALANCE DATA MODEL PA-28-180 CHEROKEE Weight and Balance Data Model PA-28-180 PAGE 1 Section 1 Airplane Serial Number 28- Registration Number Date AIRPLANE EMPTY WEIGHT C. G. Arm Item Weight X (Inches Aft = Moment (lbs) of Datum) (In-lbs) Standard Empty Weight Actual Computed Optional Equipment Unusable Fuel (3 Pints) 2.2 103.0 227 Licensed Empty Weight = Total of Above Items Standard Empty Weight includes paint, hydraulic fluid and undrainable engine oil. AIRPLANE USEFUL LOAD - (Gross Weight) (Licensed Empty Weight) = Useful Load Normal Category: (2400 lbs) - ( lbs) Utility Category: (1950 lbs) lbs) lbs. lbs. THIS LICENSED EMPTY WEIGHT, C. G. AND USEFUL LOAD ARE FOR THE AIRPLANE AS DELIVERED FROM THE FACTORY. REFER TO APPROPRIATE AIRCRAFT RECORD WHEN ALTERATIONS HAVE BEEN MADE. PREPARED CHOCKE APPROVED PIPER AIRCRAFT CORP. DEVELOPMENT CENTER, VERO BEACH, FLA. REPORT VB-268 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 32.5 488 Pilot and Front Passenger 340 85.5 29070 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 s. ple loading problem 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 require-- ments. 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. LOAD WEIGHT (POUNDS) PREPARED CHECKED PIPER AIRCRAFT CORP. DEVELOPMENT CENTER, VERO BEACH, FLA. Weight & Balance Data Model PA 28-180 APPROVED 450 400 350 300 250 200 150 100 50 REPORT VB-268 LOADING GRAPH Fuel (6 lb/gal) Rilet and Front Passenge Aft Passengers Baggage 5 10 15 20 20 25 25 30 35 40 45 50 MOMENT/1000 (POUND INCHES) 3 Section 1 PAGE PREPARSO CHOCK APPROVED PIPER AIRCRAFT CORP. DEVELOPMENT CENTER, VERO BEACH, FLA. REPORT VB-268 Weight & Balance Data Model PA-28-180 PAGE 4 Section 1 WEIGHT IN POUNDS C. G. RANGE AND WEIGHT 2400 NORMAL CATEGORY 2200 2000 1800 -UTILITY CATEGORY 1600 1400 1200 84 86 88 90 92 94 INCHES AFT OF DATUM 96 PREPARED CHOCKE APPROVED PIPER AIRCRAFT CORP. DEVELOPMENT CENTER, VERO BEACH, FLA. REPORT VB-268 Weight and Balance Data Model PA-28-180 PAGE 5 Section 1 WEIGHT AND BALANCE DATA WEIGHING PROCEDURE At the time of delivery, Piper Aircraft Corporation provides each airplane with the licensed empty weight and center of gravity location. This data is on Page 1, Section 1 of this Flight Manual. The removal or addition of an excessive amount of equipment or excessive airplane modifi- cations can affect the licensed empty weight and empty weight center of gravity. The follow- ing is a weighing procedure to determine this licensed empty weight and center of gravity location: 1. 2. PREPARATION a. Be certain that all items checked in the airplane equipment list are installed in the proper location in the airplane. b. C. d. e. 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. 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 co-pilot seats in fourth (4th) notch, aft of forward position. Put flaps in the fully retracted position and all control surfaces in the neutral posi- tion. Tow bar should be in the proper location and all entrance and baggage doors closed. f. Weigh the airplane inside a closed building to prevent errors in scale readings due to wind. LEVELING a. b. With airplane on scales, block main gear oleo pistons in the fully extended position. Level airplane (see diagram) by deflating nose wheel tire, to center bubble on level. Datum PREPARED CHECKED APPROVED PIPER AIRCRAFT CORP. DEVELOPMENT CENTER, VERO BEACH, FLA. Weight and Balance Data "Model PA-28-180 PAGE 6 Section REPORT VB-268 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 Net Scale Position and Symbol Reading Tare Weight Nose Wheel (N) Right Main Wheel (R) Left Main Wheel (L) Airplane Empty Weight, as Weighed (T) 4. EMPTY WEIGHT CENTER OF GRAVITY A = B = a. The following geometry applies to the PA-28-180 airplane when airplane is level (See Item 2). C. G. Arm 78.4 Level Points (Fuselage Left Side) N C. G. R+L B Wing Leading Edge The datum is 78.4 inches ahead of the wing leading edge at the intersection of the straight and tapered section. PREPARED CHOCKE APPROVED b. C. d.
Show full textShow less
PIPER AIRCRAFT CORP. DEVELOPMENT CENTER, VERO BEACH, FLA. REPORT VB-268 Weight and Balance Data Model PA-28-180 PAGE 7 Section 1 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 center- line, horizontally and parallel to the airplane centerline, to each side of the nose wheel axle. Then average the measurements. The empty weight center of gravity (as weighed including optional equipment and undrainable oil) can be determined by the following formula: C. G. Arm = 78.4 + A -> B(N) T ) ( C. G. Arm = 78.4 + ( 5. LICENSED EMPTY WEIGHT AND EMPTY WEIGHT CENTER OF GRAVITY inches Weight Arm Moment Empty Weight (as weighed) Unusable Fuel (3 pints) + 2.2 103.0 +227 Licensed Empty Weight