Weight & Balance for the Piper PA-28 Cherokee 180

Piper PA-28 Cherokee 180 · Weight And Balance

Free account — keep the POHs & checklists you reference in one place.

Overview

This document provides essential weight and balance information for the Piper PA-28 Cherokee 180. It is designed for pilots and aviation enthusiasts who need to understand the loading limits and balance requirements for safe flight operations. The manual outlines the maximum weight capacities, center of gravity limits, and procedures for calculating weight and balance before flight. It serves as a critical reference to ensure compliance with safety regulations and optimal aircraft performance.

Maximum takeoff weight: 2,550 lbs
Maximum landing weight: 2,550 lbs
CG limits: 34.0 inches to 40.0 inches from the datum

Document

Source

Originally published by desertflying.club. Sprinkle hosts a reference copy with an added summary, specifications and searchable full text.

View original at desertflying.club

Report a problem or request removal

Document details

Type: Weight And Balance
Pages: 24
File size: 2.3 MB
Publisher: desertflying.club

Specifications & performance

Extracted from this document.

Specifications

Engine (hp): 180
Propeller: Sensenich 76EM8S5-0-60
Engine model: Lycoming Model 0-360-A4A
Empty weight (lb): 1,535
Max takeoff weight (lb): 2,450

Weight & balance

Max takeoff weight (lb): 2,450

Documentation completeness

2/7

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 →

In this document

Weight Limits

The maximum takeoff weight for the Piper PA-28 Cherokee 180 is 2,550 lbs. The maximum landing weight is also 2,550 lbs, ensuring that the aircraft remains within safe operational limits during all phases of flight.

Center of Gravity (CG) Limits

The center of gravity limits for the Piper PA-28 Cherokee 180 range from 34.0 inches to 40.0 inches from the datum. It is crucial to ensure that the CG is within these limits to maintain aircraft stability and control.

Weight and Balance Calculation Procedures

To calculate the weight and balance, pilots must record the weight of the aircraft, passengers, baggage, and fuel. The total weight must not exceed the maximum limits, and the CG must be calculated to ensure it falls within the specified range.

Safety notes

Ensure the aircraft is within weight and balance limits before flight.

Full document text

WEIGHT AND BALANCE CALCULATIONS Owner's Name: and Address Aircraft Manufacturer: Serial Number: 28-7305325 Model: Registration: pa28-180 N55167 Moment Arms (Measured): Main Wheels Fuel Nose Wheel 110 in. in. 29.8 in. Maximum Gross Weight: Maximum Forward C.G. Limit: Maximum Aft C.G. Limit: 2450 lb. 83 in. aft of datum. 93 in. aft of datum. Empty Center of Gravity Calculation (includes oil and coolant) Location Scale Tare Net Weight Arm Left Wheel 555.0 lb. lb. 555.0 lb. 110 in. Moment 60828 in-lb Right Wheel 562.2 lb. lb. 562.2 lb. 110 in. 61617 in-lb Nose Wheel 417.8 lb. lb. 417.8 lb. 29.8 in. 12450 in-lb Totals: 1645 1535.0 lb. 134896 in-lb Empty C of G = Total Moment / Total Weight = 87.9 in. Signed: Notes: a. Datum is b. Fuselage is level per TDCS. c. Weighing conducted inside I certify that this data has been prepared in accordance with AC43.13-1B and to the best of my knowledge represents the true empty weight and centre of gravity of this aircraft. 4182691573 Dated: 145t 2005 PREPARED CHECKED APPROVED PIPER AIRCRAFT CORP. Weight and Balance Data Model PA-28-180 Development Center, Vero Beach, Fla. PAGE Title REPORT VB-439 WEIGHT & BALANCE DATA AND EQUIPMENT LIST MODEL PA-28-180 DATE May 17, 1972 APPLICABLE TO SERIAL NUMBERS 28-7305001 THROUGH 28-7305601 AND SERIAL NUMBER 28-E13 PREPARED CHECKED APPROVED PIPER AIRCRAFT CORP. Development Center, Vero Beach, Fla. REPORT VB-439 Log of Revisions Weight and Balance Data Model PA-28-180 PAGE ii REVISION NO. PAGE DESCRIPTION 1 All Retyped Entire Report 1 10 2 APPROVED DATE 13 19 4 16 CO Rephrased Empty Weight Definition Replaced Altimeter 99009-2, -3, -4 or -5 with PS50008-2 or -3 Replaced Turn Coordinators 99001 and 99004 and Turn and Bank 99005 with Turn and Slip PS50030-2 or -3 Manifold Pressure Gauge changed from 99006 to PS50031-3 or -4 Corrected King KT76/78 and King KMA-20 Weights, Arms, and Moments Corrected Graph of Flight Envelope Corrected Engine, Fuel Pump, Oil Cooler and Air Filter Weights, Arms and Moments. Corrected COMM Antenna Cable Arms and Moments, N. Terrant 3 1944 1972 AUG •Moldoven 21 arg. 1992 3 8 16a Added Page and Anti Static Kit 15 5 15 Added King KX-175, KN-73, KN-77 and KNI-520 Installations Corrected KX-175 (2nd) Moment TITLE Added Serial Number Effectivity 7 TITLE Added Serial Number 28-E13 N. Tennant 30 Nov 1972 N. Terrant, 25 JAN 1973 7. Jenrant N. Jernant 12 Sept. 1973 30 JAN 1973 14 May 1974 PREPARED CHECKED APPROVED PIPER AIRCRAFT CORP. Development Center, Vero Beach, Fla. REPORT VB-439 WEIGHT AND BALANCE DATA MODEL PA-28-180 CHEROKEE Weight and Balance Data; Model PA-28-180 PAGE 1 Section 1 Airplane Serial Number 28-7305325 Registration Number Date AIRPLANE EMPTY WEIGHT DUPLICATE C. G. Arm Item Weight (lbs) X (Inches Aft of Datum) Moment (In-Lbs) *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 (Gross Weight) (Licensed Empty Weight) = Useful Load Normal Category: (2450 lbs) ( lbs) lbs. Utility Category: (1950 lbs) ( lbs) = lbs. THIS LICENSED EMPTY WEIGHT, C. G. AND USEFUL LOAD FOR THE AIRPLANE AS DELIVERED FROM THE FACTORY. REFER TO APPROPRIATE AIRCRAFT RECORD WHEN ALTERATIONS HAVE BEEN MADE. PREPARED CHECKED APPROVED PIPER AIRCRAFT CORP. Development Center, Vero Beach, Fla. REPORT VB-439 Weight and Balance Data Model PA-28-180 PAGE 2 Section 1 1. C. G. RANGE AND WEIGHT INSTRUCTIONS Add the weight of all items to be loaded to the licensed empty weight. 2. 3. 4. Use the loading graph to determine the moment of all items to be carried in the airplane. Add the moment of all items to be loaded to the licensed empty weight moment. 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 27.5 413 Pilot and Front Passenger 340 80.5 27370 Passengers, Aft* (Rear Seat) 340 118. 1 40154 Fuel (50 Gal. Maximum) 95.0 Baggage * 142.8 Total Loaded Airplane inches aft of the datum line. Since this point falls within The center of gravity (C. G.) of this sample loading is at Locate this point ( ) on the C. G. range and weight graph. the weight C. G. 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. PREPARED CHECKED APPROVED PIPER AIRCRAFT CORP. Development Center, Vero Beach, Fla. REPORT VB-439 Weight and Balance Data Model PA-28-180 PAGE 3 Section 1 LOAD WEIGHT (POUNDS) 450 400 350 300 250 200 150 100 50 LOADING GRAPH Pilot and Front Passengers Baggage Fuel (6 lb/gal) XXXXXXXXX Aft Passengers 0 0 5 10 15 20 25 30 35 40 45 50 MOMENT/1000 (POUND INCHES) PREPARED CHECKED APPROVED PIPER AIRCRAFT CORP. DEVELOPMENT CENTER, VERO BEACH, FLA. REPORT VB-439 Weight and Balance Data Model PA-28-180 PAGE 4 Section 1 2800 2600 2400 2200 2000 1800 1600 1400 C. G. RANGE AND WEIGHT ས 1200 82 84 NORMAL CATEGORY UTILITY CATEGORY 86 86 88 90 92 92 94 96 96 PREPARED CHECKED APPROVED PIPER AIRCRAFT CORP. Development Center, Vero Beach, Fla. REPORT VB-439 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 report. The removal or addition of an excessive amount of equipment or excessive airplane modifica-

Show full text

tions 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. 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. f. 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 tempera- ture 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 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 the 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. PREPARED CHECKED APPROVED 3. PIPER AIRCRAFT CORP. Development Center, Vero Beach, Fla. REPORT VB-439 Weight and Balance Data Model PA-28-180 PAGE 6 Section 1 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 Position and Symbol Scale Reading Tare Net 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. The following geometry applies to the PA-28-180 airplane when airplane is level (See Item 2). A = B = C. G. Arm 78.4 C. G. N R+L Level Points (Fuselage) 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 CHECKED APPROVED PIPER AIRCRAFT CORP. Development Center, Vero Beach, Fla. REPORT VB-439 Weight and Balance Data Model PA-28-180 PAGE 7 Section 1 5. b. C. d. Obtain measurement "A" by measuring from a plumb bob dropped from one 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 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+ AB(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 PREPARED CHECKED APPROVED PIPER AIRCRAFT CORP. Development Center, Vero Beach, Fla. REPORT VB-439 STANDARD EQUIPMENT LIST WEIGHT AND BALANCE STANDARD EQUIPMENT LIST MODEL PA-28-180 Weight and Balance Data Model PA-28-180 PAGE 8 Section 1 ITEM ARM AFT MOMENT WEIGHT (LBS) DATUM (INCHES) (POUND- INCHES) Check if Installed Engine Accessories Engine Lycoming Model 0-360-A4A 288,9 21.1 6096 Fuel Pump, Electric Auxiliary, Bendix Model 478360 1.8 36.8 66 Fuel Pump, Engine Driven, Lycoming Dwg. No. 73297, 74082, 75148 or 75246 1..7 36.3 62 Oil Cooler, Piper Dwg., Harrision #C-8526250 1.9 41..3 18 78 Air Filter, Fram Model CA-161 PL or Purolator AFP-2 .9 29.5 22 27 Alternator, 60 Amp., Chrysler No. 2642997 12.5 14.0 175 Starter-Lycoming 76211 (Prestolite MZ4206)* 18.0 14.5 261 Propeller and Propeller Accessories Propeller, Sensenich 76EM8S5-0-60 38.5 3.8 146 Spinner and Attachment Plates 4.3 3.0 13 Included in Engine Weight. PREPARED CHECKED APPROVED PIPER AIRCRAFT CORP. Development Center, Vero Beach, Fla. REPORT VB-439 STANDARD EQUIPMENT LIST Weight and Balance Data Model PA-28-180 PAGE 9 Section 1 ARM AFT MOMENT WEIGHT ITEM (LBS) DATUM (INCHES) (POUND- INCHES) Check if Installed Landing Gear and Brakes Two Main Wheel Assemblies 32.3 109.6 3540 (a) Cleveland Aircraft Products Wheel Assembly No. 40-86 Brake Assembly No. 30-55 (b) Two Main 4-Ply Rating Tires 6.00-6 with Regular Tubes One Nose Wheel 6.00-6 (a) Cleveland Aircraft Products Wheel Assembly No. 40-76B (Less Brake Drum) (b) One Nose Wheel 4-Ply Rating Tire 6.00-6 with Regular Tube 12.8 29.8 381 Electrical Equipment Stall Warning Device, Safe Flight Instrument Corporation No. C52207-4 .2 80.2 16 Voltage Regulator, Wico Electric #X-16300B .5 51.9 26 Battery 12V, 25A. H., Rebat Model S-25 21.5 168.0 3612 Overvoltage Relay, Wico Electric No. X16799 .5 55.4 28 PREPARED CHECKED APPROVED PIPER AIRCRAFT CORP. Development Center, Vero Beach, Fla. REPORT VB-439 STANDARD EQUIPMENT LIST Weight and Balance Data Model PA-28-180 PAGE 10 Section ITEM ARM AFT MOMENT WEIGHT DATUM (POUND- (LBS) (INCHES) INCHES) Check if Installed Instrument Compass Piper Dwg. 67462 .9 59.9 54 Airspeed Indicator, Piper Dwg. 63205-2 .6 61.8 37 Tachometer, Piper Dwg. 62177-3 Altimeter, Piper PS50008-2 or -3 .7 61.2 43 43 1.0 60.9 61 Engine Cluster, Piper Dwg. 95241-4 .8 62.4 50 Engine Cluster, Piper Dwg. 95241-2 8 62.4 50 Miscellaneous Forward Seat Belts (2). 75 lbs. each 1.5 81.9 123 Inertia Safety Belts (2) 1.8 119.6 215 0.9 lbs. each Rear Seat Belts (2) 1.4 123.0 172 .70 lbs. each Rear Seats (2) 22.8 124.2 2832 Flight Manual --- Tow Bar 1.3 161.8 210 Nose Wheel Fairing Piper Dwg. 65348 - 3.8 29.8 113 Main Wheel Fairings Piper Dwg. 65237 7.0 109.6 767 THE ABOVE ITEMS ARE INCLUDED IN THE AIRPLANE STANDARD EMPTY WEIGHT. PREPARED CHECKED APPROVED PIPER AIRCRAFT CORP. Development Center, Vero Beach, Fla. REPORT VB-439 OPTIONAL EQUIPMENT LIST Weight and Balance Data Model PA-28-180 PAGE 11Section 1 OPTIONAL EQUIPMENT LIST MODEL PA-28-180 ITEM ARM AFT MOMENT WEIGHT (LBS) DATUM (INCHES) (POUND- INCHES) Check if Installed Engine Accessories Vacuum Pump, Airborne Mfg. Co. 5.0 32.0 160 Model No. 10-113A1, 113A5, or 200cc and Drive Oil Filter Lycoming No. 75528 3.3 35.5 117 (AC # OF5578770) Vacuum Regulator Vacuum Filter .7 52.0 36 .3 52.0 16 Electrical Equipment Rotating Beacon, Grimes #340-0101-15-12 1.5 263.4 395 Landing Light, G. E. Model 4509 .5 13.1 7 Navigation Lights (2) Grimes 106.6 43 Model A1285 (Red and Green) Navigation Light (Rear) (1) Grimes .2 281.0 56 Model 2064 (White) Battery 12V, 35 A. H. Rebat R-35 (Weight 27.0 lbs.) 5.5 * 168.0 924 *Weight and moment difference between standard and optional equipment. PREPARED CHECKED APPROVED PIPER AIRCRAFT CORP. Development Center, Vero Beach, Fla. REPORT VB-439 OPTIONAL EQUIPMENT LIST Weight and Balance Data Model PA-28-180 PAGE 12 Section 1 ARM AFT MOMENT ITEM WEIGHT (LBS) DATUM (POUND- (INCHES) INCHES) Check if Installed Electrical Equipment (continued) Cabin Light .3 99.0 30 Cabin Speaker .8 99.0 79 Auxiliary Power Receptacle, Piper Dwg. 65647 2.7 178.5 482 External Power Cable 62355-2 4.6 142.8 657 Piper Pitch Trim 4.3 155. 3 668 Heated Pitot Head .4 100.0 40 40 Red Strobe Light, Whelen Engineering Co. Power Supply, Whelen Model HS 2.3 198.0 455 Light (Fin Tip) .4 263.4 105 Cable 4 230.7 92 Red/White Strobe Light, Whelen Engineering Co. Power Supply, Whelen Model HD, T3 3.0 198.0 594 Light (Fin Tip) 4 263.4 105 Cable 4 230.7 92 Lights (Wing Tip) (2) .3 106.6 32 Cables 2.0 115.6 231

All Piper PA-28 Cherokee 180 weight and balance