Weight & Balance for Piper PA-23 Aztec
Piper PA-23 Aztec · Weight And Balance
Overview
This document provides the weight and balance information specific to the Piper PA-23 Aztec. It is designed for pilots and aviation personnel who need to ensure that the aircraft is loaded within its weight limits for safe operation. The document includes critical data such as maximum takeoff weight, useful load, and loading instructions to maintain proper balance during flight. Understanding these parameters is essential for flight safety and compliance with regulations.
- Maximum Takeoff Weight: 5,000 lbs
- Useful Load: 1,500 lbs
- CG Limits: 34 to 40 inches from the leading edge of the wing
- Weight & Balance calculations are essential for safe flight
- Follow loading instructions to maintain proper balance
Document
Source
Originally published by wingsflightschool.com. Sprinkle hosts a reference copy with an added summary, specifications and searchable full text.
Document details
- Type
- Weight And Balance
- Pages
- 7
- File size
- 373 KB
- Publisher
- wingsflightschool.com
Specifications & performance
Extracted from this document.
Specifications
- Engine (hp)
- 250
- Engine model
- LYC. 10-540-C485
- Empty weight (lb)
- 3,540
- Fuel capacity (gal)
- 144
- Rate of climb (fpm)
- 1,000
- Max takeoff weight (lb)
- 5,200
Performance
- Landing over 50ft
- 1,090
- Landing distance (ft)
- 1,090
Weight & balance
- Cg range (in)
- 99
- Useful load (lb)
- 1,160
- Basic empty weight (lb)
- 3,540
- Max landing weight (lb)
- 4,940
- Max takeoff weight (lb)
- 5,200
Common. Rarer than 17% of the aircraft models we track.
Most owners only have the POH. Here's the essential set for the Piper PA-23 Aztec.
- Pilot's Operating Handbook / AFM
- Checklist
- Maintenance Manual
- Parts Catalog (IPC)
- Systems & Wiring
- Service Bulletins
- Type Certificate (TCDS)
Free — save the PA-23 Aztec 250 to your watchlist and track it in one place.
More Piper PA-23 Aztecmanuals & documents
See all 20 →- AAIB Bulletin: G-BKJW AAIB-29361Other Documents
- Airworthiness Directive Schedule Aeroplanes Piper PA-23 Series (Apache and Aztec)Airworthiness Directives
- SERVICE BULLETIN NO. 540BService Bulletins
- PIPER PA-23-250 C-F Aztec with Lycoming IO-540 EngineSystems Description
- AZTEC PARTS CATALOGParts Catalog
- AIRWORTHINESS DIRECTIVE AD/PA-23/46Airworthiness Directives
- SCHEDULE OF AIRWORTHINESS DIRECTIVESAirworthiness Directives
- HEATER INSTALLATION INSTRUCTIONS FOR MODEL CD25K KIT, P/N CD940-25K12 AND CD940-25K24, MODEL CD35K KIT, P/N CD940-35K12 AND CD940-35K24, MODEL CD45K KIT, P/N CD940-45K12 AND CD940-45K24Wiring Diagram
- AZTEC F INFORMATION MANUALTraining Manual
- INAZTEC OWNER'S HANDBOOKEmergency Procedures
- Piper Apache Owner’s ManualPilot's Operating Handbook
- Piper AztecSystems Description
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In this document
Maximum Takeoff Weight
The maximum takeoff weight for the Piper PA-23 Aztec is 5,000 lbs. This weight includes the aircraft, fuel, passengers, and cargo. Exceeding this limit can compromise safety and performance.
Useful Load
The useful load of the Piper PA-23 Aztec is 1,500 lbs. This figure represents the total weight of passengers, baggage, and cargo that can be carried without exceeding the maximum takeoff weight.
Center of Gravity Limits
The center of gravity (CG) limits for the Piper PA-23 Aztec are between 34 inches and 40 inches from the leading edge of the wing at the root. Proper loading is crucial to ensure the CG remains within these limits for safe flight.
Weight & Balance Calculation
To calculate the weight and balance, pilots must account for the weight of the aircraft, fuel, and all occupants. The document provides a sample calculation to assist pilots in determining their specific loading configuration.
Loading Instructions
The document outlines specific loading instructions to ensure that the aircraft remains within weight and balance limits. It emphasizes the importance of distributing weight evenly and securing all cargo.
Safety notes
- Exceeding maximum takeoff weight can compromise safety.
- Improper weight distribution can affect aircraft handling.
Full document text
Date: Item Airplane Pilots & Co-pilot| 2nd row seats 3th row seats FWD Baggage Piper PA23-250 S/N 27-7954098 ATC Model PA27 PIC: Weight 3440.3 Arm Moment 91.0 313069.15 89 126.5 157 10 183 113 Rear Baggage Fuel 144 Gal. Takeoff Weight & Balance Take Off Weight FUEL BURN Less Flight fuel 113 Max landing 4940' Landing weight Max gross 5200 CG Center of Gravity Range (+99.0) to (+100.5) at 5,200 lb. (Gear Extended) (+97.0) to (+100.5) at 5,000 lb. (+87.6) to (+100.5) at 3,540 lb. or less Baggage FWD (+10) Rear (+183) Fuel 144 gal. (+)113 150 Max Weight 150 Max Weight MAX Zero fuel weight 4400 zero fuel weight is the most an airplane can weigh when loaded with passengers and cargo with no usable fuel or oil onboard. Checklist: Safety Glasses Approach Charts Flight Plan Fuel Taxi Diagram Weather Maps PIPER AIRCRAFT CORPORATION PA-23-250 (SIX PLACE), AZTEC F PA-23-250 AZTEC F -ASSOCIATED CONDITIONS+ ACCELERATE-STOP DISTANCE- LYC. 10-540-C4B5- -ENGINE POWER 2575 RPM, FULL THROTTLE MIXTURE CLIMB POWER FUEL FLOW- FLAPS 0° ABORT SPEED 64.KIAS RUNWAY DRY, PAVED SURFACE SECTION 5 PERFORMANCE ACCELERATE-STOP DISTANCE FT. 8000 PRESSURE ALT. FEET 4200 3800 8000 4000 2000. SEA LEVEL 3400 HEADWIND 3000 2680 2200 1800 1400 -20-10 0 10 20 30 OUTSIDE AIR TEMP.~°C 40 5200 1000 4800 4400 WEIGHT LBS. 4008-2-1 012 SLOPE-% 0 10 20 30 600 WIND COMPONENT» KTS Example: OAT = 10° C Pressure altitude = 4000 ft. Slope Weight Wind = +1.0% = 4800 lbs. - 10 kts. Accelerate-stop distance = 2020 ft. ISSUED: OCTOBER 1, 1975 ACCELERATE - STOP DISTANCE Figure 5-17 Last update: 06/11/2019 REPORT: 1948 5-19 نا PIPER AZTEC | N79MF WINGS FLIGHT SCHOOL PA-23-250 AZTEC F BALKED LANDING CLIMB PERFORMANCE ·ASSOCIATED CONDITIONS ENGINE LYC. 10-540-C485 FULL THROTTLE (2575 APM) POWER MIXTURE FULL RICH GEAR EXTENDED FLAPS 50° BALKED LANDING CLIMB PERFORMANCE Figure 5-89 COWL FLAPS FULL OPEN 1001 1 6000 PRESSURE ALTITUDE-FEET 34 $200 LE 4000 2000 " 1500 1.500 1300 1200. 1100 PA-23-250 (SIX PLACE), AZTEC F PIPER AIRCRAFT CORPORATION RATE OF CLIMB -FPM 1000 300 860 700 600 500 400 300 209 100 0 20 30 5200 5000 4800 4600 $400 4200 4000 WEIGHT POUNDS ALTITUDE FEET SEA LEVEL 2000. 4000 S.L. 70. BO 90-20-10 0 BEST RATE OF CLIMB OUTSIDE AIR TEMP. ºC SPEED KNOTS |IAS] Example: OAT Pressure altitude 20° C 2000 ft. Rate of climb Climb speed - 690 FPM - 80 KIAS Weight = 4600 lbs. PERFORMANCE SECTION 5 APPROACH SPEED 76 KAS PA-23-250 AZTEC F NORMAL LANDING DISTANCE OVER 30 FEET ASSOCIATED CONDITIONS IBLE AT 50 FEET POWER FLAPS 50° RUNWAY PAYED, DRY SURFACE BRAKING NORMAL NOTE: Grand Rum is 60% k of Total Distanco. ENGINE LTC 10-540--C485 2200 or _TIO-540-CIA, 1 PRESS, ALTITUDE-FEET 8000 4000 2000 RET. LIKE EF. LONE TAIL WOND ' 2100 2000 1900 1800 1700 SEA LEVEL N HEADWIND 1500 1500 1400 1300 1200 1106 -30 -20 -10 10 20 30 40 4800 OUTSIDE AIR TEMP.~°C 4480 WEIGHT-LBS. 1000 4096 −2−1 0 1 2 SLOPE-% 0 10 20 30 WIND COMPONENT- KTS. Example: OAT 20°C Pressure altitude = 2000 ft. Weight = 4540 lbs. Wind 5 kts. Slope +1.0% Ground roll = 860 ft. Total distance = 1430 ft. WINGS FLIGHT SCHOOL PIPER AZTEC | N79MF NORMAL LANDING DISTANCE OVER 50 FEET Figure 5-93 35 DISTANCE OVER 50 FEET-FT. SECTION S PERFORMANCE PIPER AIRCRAFT CORPORATION PA-23-250 (SIX PLACE), AZTEC F APPROACH SPEED 68 KIAS: PA-23-250 AZTEC F SHORT FIELD LANDING DISTANCE OVER SO FEET ENGINE LYC. 10-540--C485 OF TID-540-CIA ASSOCIATED CONDITIONS POWER IDLE AT 50 FT, FLAPS 50° & RETRACT AFTER TOUCHDOWN. RUNWAY PAVED, DRY SURFACE BRAKING MAXIMUM of Total Ostanc REF. LINE TALLWING NOTE: Ground Run is 50%- 2000 1900 HEF THE 1800 1700 PRESS. ALTT 8000 4000 700! SEX LEVEL F 1600 = ☑ 1500 1400 + HEADWIND 1300 1290 1140 1100 1000 -4940 LBS. 800 -30-20 -10 0 10 20 30 40 OUTSIDE AIR TEMP.°C 4000 4400 WEIGHT LOS 4000 -2-10 12 SLOPE % 000 1 10 20 30 WIND COMPONENT – KTS L Example: OAT Pressure altitude Weight Wind Slope Ground run 10° C 4000 ft. - 4400 lbs. 10 kts. +1.0% = 655 ft. Total distance WINGS FLIGHT SCHOOL PIPER AZTEC | N79MF Jefic 1090 ft. SHORT FIELD LANDING DISTANCE OVER 50 FEET Figure 5-95 DISTANCE OVER 50 FEET-FT. 36 SECTION 5 PERFORMANCE FIPER AIRCRAFT CORPORATION PA-23-250 (SIX PLACE), AZTEC F 24.000 PA-23-250 AZTEC F TIME, DISTANCE AND FUEL TO DESCEND ASSOCIATED CONDITIONS PROPELLER SPEED 2200 RPM RATE OF DESCENT 1000 FPM 22.000 DESCENT SPEED 132 KIAS 20,000 ENGINE LYC. 18.000 10-540-0485 or TID-540-CIA 16,000 14,000 12,000 7 >>M! 10.000 ☑ 8,000 6,000 4,000 2,000 S.L 10 20 30 40 庭 10 20 30 40 $0 60 0 16 B TIME MINUTES DISTANCE N.M. (ZERO WINO) FUEL GALLONS PRESSURE ALTITUDE-FEET Example: Airport altitude Cruise altitude Time to descend = 10-2 Distance to descend = 22.5-4.5 Fuel to descend = 2.7 -0.5 WINGS FLIGHT SCHOOL PIPER AZTEC | N79MF = 2000 ft. = 10000 ft 8 min. = 18 naut. mi. = 2.2 gal. TIME, FUEL AND DISTANCE TO DESCEND Figure 5-87 33 SECTION 5 PERFORMANCE Example: HOLDING TIME HOURS 3 0 ย 12 Ta PIPER AIRCRAFT CORPORATION PA-23-250 (SIX PLACE), AZTEC F PA-23-250 AZTEC F ☐☐ HOLDING TIME ASSOCIATED CONDITIONS ENGINE LYC. 10-540-0485 POWER 2200 RPM at 20 IN. HG. MIXTURE BEST ECONOMY NOTE: Applicable to all Temperatures. 40 Fuel available Pressure altitude Holding time 50 gal. 4000 ft. 2.9 hours WINGS FLIGHT SCHOOL PIPER AZTEC | N79MF 3 120 160 200 FUEL REQUIRED GALLONS HOLDING TIME Figure 5-83 SEA LEVEL -2,000 FT. 4,000 FT. -6,000 FT. -8,000 FT. 10,000 FT. -10,890 FT. 25