Weight & Balance for the Piper PA-23 Aztec
Piper PA-23 Aztec · Weight And Balance
Overview
This document provides essential weight and balance information for the Piper PA-23 Aztec aircraft. It is intended for pilots and aviation enthusiasts who need to understand the loading limits and weight distribution for safe operation. The manual outlines the maximum takeoff weight, empty weight, and useful load, along with detailed instructions on how to calculate weight and balance for various loading scenarios. It emphasizes the importance of adhering to weight limits to ensure safe flight operations and prevent accidents related to improper loading.
- Maximum takeoff weight: 5,000 lbs
- Empty weight: approximately 3,200 lbs
- Useful load: about 1,800 lbs
- Center of gravity limits must be adhered to for safe flight
- Proper weight distribution is critical for maintaining balance.
Document
Source
Originally published by static1.squarespace.com. Sprinkle hosts a reference copy with an added summary, specifications and searchable full text.
Document details
- Type
- Weight And Balance
- Pages
- 198
- File size
- 16 MB
- Publisher
- static1.squarespace.com
Specifications & performance
Extracted from this document.
Specifications
- Engine (hp)
- 250
- Height (ft)
- 10.3
- Length (ft)
- 31.2
- Wingspan (ft)
- 77
- Engine model
- IO-540-C4B5
- Empty weight (lb)
- 3,042
- Fuel capacity (gal)
- 144
- Service ceiling (ft)
- 19,800
- Max takeoff weight (lb)
- 5,200
Weight & balance
- Useful load (lb)
- 2,158
- Basic empty weight (lb)
- 3,042
- 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.
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- AIRWORTHINESS DIRECTIVE AD/PA-23/46Airworthiness Directives
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- AZTEC F INFORMATION MANUALTraining Manual
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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 limit must not be exceeded to ensure safe flight performance.
Empty Weight and Useful Load
The empty weight of the Piper PA-23 Aztec is approximately 3,200 lbs, which includes the aircraft structure, systems, and unusable fuel. The useful load, which is the difference between the maximum takeoff weight and the empty weight, is about 1,800 lbs.
Weight and Balance Calculation
To calculate weight and balance, pilots must consider the weight of passengers, cargo, and fuel. The document provides a sample calculation to demonstrate how to ensure the aircraft is within the allowable weight limits and properly balanced.
Center of Gravity Limits
The center of gravity (CG) limits for the Piper PA-23 Aztec are specified in the document. It is crucial to keep the CG within these limits for stable flight characteristics.
Loading Instructions
The manual includes loading instructions that detail how to distribute weight within the aircraft to maintain balance. It advises on the placement of cargo and passengers to avoid exceeding CG limits.
Safety notes
- Exceeding the maximum takeoff weight can lead to compromised flight performance.
- Improper weight distribution can affect aircraft stability and control.
Full document text
PIPER AZTEC E INFORMATION MANUAL N54202 Aztec "E" PA-23-250 HANDBOOK PART NO. 761 455 AZTEC "E" INFORMATION MANUAL Published by PUBLICATIONS DEPARTMENT Piper Aircraft Corporation 761 455 Issued: September 1970 REVISIONS The information compiled in this manual will be kept current by revisions distributed to the airplane owners through their local dealers or distributors. There are two types of revisions used to keep the Pilot Operator's Manual current; Temporary Revisions and Permanent Revisions. The material compiled in the revisions will consist of information necessary to update the present information or add information to cover added equipment. I. Temporary Revision This revision will be distributed at any time it is necessary to forward information to the owners and operators of the airplane. The revision will usually consist of one or two pages which may be inserted in the appropriate section of the manual. This revision will include deletions and/or additions of material pertinent to different paragraphs of the manual. II. Permanent Revision This revision will be distributed periodically and will supersede all previous temporary revisions. These revisions will be complete page replacement and shall be inserted in the 'manual in accordance with the instructions given below. 1. 2. Replace the obsolete pages with revised pages of the same page number. Insert pages with page numbers followed by a small letter in direct sequence with the same common numbered page. III. Identification of Revised Material Revised text and illustrations shall be indicated by a black vertical line along the left hand margin of the page, opposite revised, added or deleted material. A line opposite the page number or section title and printing date, will indicate that the text or illustration was unchanged, but that material was relocated to a different page or that an entire page was added. Symbols will indicate only current revisions with changes and additions to or deletions of existing text and illustrations. Changes in capitalization, spelling, punctuation or the physical location of the material on the page will not be identified by symbols. REVISIONS ISSUED Current Permanent and Temporary Revisions to the PA-23-250 Pilots Operating Manual issued September, 1970 are as follows: 761 455 (PR710501) Permanent Revision Dated May 1, 1971 761 455 (PR710515) Permanent Revision for Japan Airlines only Dated May 15, 1971 761 455 (PR710628) Permanent Revision Dated June 28, 1971 761 455 (PR711201). 761 455 (PR711210) Permanent Revision Dated December 1, 1971 761 455 (PR720331) 761 455 (PR720414) 761 455 (PR720614) Permanent Revision Permanent Revision S/N Affected 27-4801, 27-4807, 27-4809 thru 27-4812 Dated December 10, 1971 Dated March 31, 1972 Permanent Revision P/O/M only Dated April 14, 1972 Permanent Revision S/N Affected 27-4859 thru 27-4862, 27-4864 & 27-4870 Dated June 14, 1972 761 455 (PR720820) 761 455 (PR720911) 761 455 (PR721030) 761 455 (PR721107) 761 455 (PR721222) 761 455 (PR730517) 761 455 (PR731112) 761 455 (PR740125) Permanent Revision Permanent Revision Permanent Revision Dated August 20, 1972 Dated September 11, 1972 Dated October 30, 1972 Permanent Revision A F/M only Permanent Revision to W/B Permanent Revision to W/B Permanent Revision to A F/M Dated November 7, 1972 761 455 (PR740531) 761 455 (PR740903) 761 455 (PR741001) Permanent Revision to P/O/M and W/B Permanent Revision to P/O/M - Permanent Revision to P/O/M, A F/M and W/B. (Added PAC Approval Form Aircraft delivered with manuals prior to this revision do not require this revision) Permanent Revision to P/O/M, A F/M and W/B Dated October 1, 1974 Dated December 22, 1972 Dated May 17, 1973 Dated November 12, 1973 Dated January 25, 1974 Dated May 31, 1974 Dated September 3, 1974 REVISIONS ISSUED (cont) 761 455 (PR750122) Permanent Revision to P/O/M, A F/M and W/B. Dated January 22, 1975 Permanent Revision to P/O/M and A F/M. Dated March 21, 1975 761 455 (PR750321) 761 455 (PR750512) 761 455 (PR760223) 761 455 (PR761123) 761 455 (PR770321) 761 455 (PR790320) 761 455 (PR880104) 761 455 (PR901219) Permanent Revision to P/O/M, A F/M and W/B. Permanent Revision to P/O/M, A F/M and W/B. Permanent Revision to A F/M. Dated May 12, 1975 Dated February 23, 1976 Dated November 23, 1976 Dated March 21, 1977 Permanent Revision to P/O/M and A F/M. Permanent Revision to P/O/M and A F/M. Dated March 20, 1979 Permanent Revision to P/O/M and W/B. Dated January 4, 1988 Permanent Revision to P/O/M. Dated December 19, 1990 TABLE OF CONTENTS GENERAL SPECIFICATIONS DESCRIPTION AIRPLANE AND SYSTEMS - FLIGHT MANUAL FAA APPROVED EMERGENCY PROCEDURES FAA APPROVED EMERGENCY PROCEDURES WEIGHT AND BALANCE OPERATING INSTRUCTIONS OPERATING TIPS PREFORMANCE CHARTS HANDLING AND SERVICING GENERAL SPECIFICATIONS Performance Altitude Cruising Speeds (mph) Weights Power Plant Fuel And Oil Baggage Dimensions Landing Gear 2 222333 GENERAL SPECIFICATIONS AZTEC "E" PERFORMANCE Published figures are for Standard PA-23-250 airplanes flown at gross weight under standard conditions at sea level unless otherwise stated. Performance for a specific airplane may vary from published figures depending upon the equipment installed, the condition of engines, airplane and equipment, atmospheric conditions and piloting technique. Take-off Run (max effort) (ft) Take-off Distance Over 50-ft Barrier (max effort) (ft) Accelerate-Stop Distance (ft) Minimum Controllable Single Engine Speed (mph)/(knots) Stalling Speed (gear down, flaps down 50°) (power off) (mph)/(knots) Stalling Speed (gear and flaps up) (power off) (mph)/(knots) Best Rate of Climb (ft per min) Best Rate of Climb Speed (mph)/(knots) Best Angle of Climb Speed (mph)/(knots) Single Engine Rate of Climb (ft per min) Best Single Engine Rate of Climb Speed (mph)/(knots) Best Single Engine Angle of Climb Speed (mph)/(knots) Absolute Ceiling (ft) Service Ceiling (ft) Single Engine Service Ceiling (ft)
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Single Engine Absolute Ceiling (ft) Landing Roll (Flaps down) (Max effort) (ft) Landing Distance Over 50-ft Barrier (Flaps down) (ft) ALTITUDE CRUISING SPEEDS (MPH) Normally Aspirated Turbo Charged 820 820 1250 1250 2220 2220 80 (69.5) 80 (69.5) 70 (61) 70 (61) 76 (66) 76 (66) 1490 1530 120 (102) 107 (93) 240 115 (100) 97 (84.5) 102 (88.5) 97 (84.5) 265 104 (90) 95 (82.5) 21,100 over 30,000 19,800 over 30,000 5000 15.300 6400 18,700 850 850 1620 1620 Normally Aspirated Man. Engine Altitude Speed Range Fuel Press. Speed No Reserve Con. (in Hg) (rpm) (feet) (mph) (knots) (miles) (gph) Normal 26 Intermediate 24 Economy 24 Long Range 20 6440 2400 4,000 210 (183) 830 34.0 2400 6,000 208 (181) 1080 27.0 2200 6,400 204 (177) 1110 25.0 2200 10,200 195 (170) 1210 21.0 GENERAL SPECIFICATIONS REVISED: January 25, 1974 PAGE 1 AZTEC "E" ALTITUDE CRUISING SPEEDS (MPH) (cont) Turbo Charged TIO-540-C1A Man. Engine Altitude Speed Range Fuel Press. Speed No Reserve Con. (in Hg) (rpm) (feet) (mph) (knots) (miles) (gph) Turbo 34.0 2400 22,000 245 (213) 1050 32.6 Intermediate 30.0 2400 24,000 233 (203) 1125 29.0 Economy 26.0 2400 24,000 .218 (190) 1175 26.0 Long Range 24.0 2200 24,000 196 (170) 1310 21.0 WEIGHTS Gross Weight (lbs) Maximum Landing Weight (lbs) Zero Fuel Gross Weight (lbs) Empty Weight (Standard, lbs) USEFUL LOAD (Standard, lbs) POWER PLANT Engine (Lycoming) Rated Horsepower Rated Speed (rpm) Bore (inches) Stroke (inches) Displacement (cu. in.) Compression Ratio Dry Weight (lbs) FUEL AND OIL Fuel Capacity (U.S. gal) Usable Fuel Ser. nos. 27-4426, 27-4574 thru 27-7405476 Ser. nos. 27-7554001 and up Fuel Aviation Grade (min octane) Oil Capacity (qts) each Engine PAGE 2 Normally Turbo Aspirated Charged 5200 5200 4940 4940 4400 4500 3042 3229 2158 1971 IO-540-C4B5 TIO-540-CIA 250 250 2575 77 2575 5.125 4.375 541.5 8.5:1 402 5.125 4.375 541.5 7.2:1 490 144 144 140 140 137 137 91/96 100/130 12 12 GENERAL SPECIFICATIONS REVISED: October 1, 1974 BAGGAGE Maximum Baggage (lbs) Forward Compartment Maximum Baggage (lbs) Rear Compartment With oxygen installed Baggage Space (cu ft) Forward Compartment Baggage Space (cu ft) Rear Compartment Baggage Door Size (in) Forward Compartment Baggage Door Size (in) Rear Compartment DIMENSIONS Wing Span (ft) Wing Area (sq ft) Length (ft) Height (ft) Wing Loading (lbs per sq ft) Power Loading (lbs per hp) Propeller Diameter (maximum, in) LANDING GEAR AZTEC "E" Normally Aspirated Turbo Charged 150 150 150 150 105 105 21.3 21.3 25.4 25.4 19.5 x 30.5 30 x 31 19.5 x 30.5 30 x 31 37.2 207.6 31' 2.625" 10.3 25.05 37.2 207.6 31' 2.625" 10.3 25.05 10.4 10.4 77 77 Wheel Base (ft) 7.5 7.5 Wheel Tread 11.3 11.3 Tire Pressure Nose 27 27* Main 46 46 I Tire Size Nose (four ply rating)* Main (eight ply rating) 600 x 6 600 x 6 700 x 6 700 x 6 *On turbocharged Aztec "E" only with serial no. 27-4781 and subsequent, nose tire is 6.00 x 6, six ply rating and should be inflated to 32 psi. GENERAL SPECIFICATIONS ISSUED: September 1, 1970 REVISED: December 10, 1971 PAGE 3