Weight & Balance for CESSNA F-337 Skymaster G
CESSNA F-337 Skymaster G · Weight And Balance
Overview
This document provides essential weight and balance information for the Cessna F-337 Skymaster G. It is designed for pilots and aviation personnel who need to understand the loading limits and weight distribution 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 to optimize aircraft performance.
- Maximum takeoff weight: 4,200 lbs (1,905 kg)
- CG limits: 34.0 inches to 40.0 inches from the datum
- Follow step-by-step procedures for weight and balance calculations
- Ensure correct weight distribution among passengers, cargo, and fuel
- Use sample forms for recording weight and balance calculations
Document
Source
Originally published by www.cessnaflyer.org. Sprinkle hosts a reference copy with an added summary, specifications and searchable full text.
Document details
- Type
- Weight And Balance
- Pages
- 24
- File size
- 1.0 MB
- Publisher
- www.cessnaflyer.org
Common. Rarer than 2% of the aircraft models we track.
Most owners only have the POH. Here's the essential set for the CESSNA F-337 Skymaster G.
- Pilot's Operating Handbook / AFM
- Checklist
- Maintenance Manual
- Parts Catalog (IPC)
- Systems & Wiring
- Service Bulletins
- Type Certificate (TCDS)
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In this document
Weight Limits
The maximum takeoff weight for the Cessna F-337 Skymaster G is 4,200 lbs (1,905 kg). This section details the maximum landing weight and the maximum weight for each seat, ensuring that the aircraft is loaded within safe limits.
Center of Gravity (CG) Limits
The CG limits for the Cessna F-337 Skymaster G are specified as 34.0 inches to 40.0 inches from the datum. This section explains how to measure and calculate the CG based on the aircraft's loading configuration.
Weight and Balance Calculation Procedures
This section outlines the step-by-step procedures for calculating the weight and balance of the aircraft. It includes examples of loading scenarios and how to adjust for fuel and passenger weights.
Loading Instructions
Detailed loading instructions are provided to ensure that the aircraft is loaded correctly. This includes guidance on the distribution of weight among passengers, cargo, and fuel.
Sample Weight and Balance Forms
The document includes sample weight and balance forms that can be used by pilots to record the weight and balance calculations prior to flight.
Safety notes
- Always verify weight and balance before flight to ensure safety.
- Exceeding weight limits can affect aircraft performance and safety.
Full document text
Service Newsletter June 25, 1993 TITLE CABIN SKIN PANEL CORROSION INSPECTION AND REPAIR TO Cessna Distributors, Single Engine and Multi-engine Service Stations MODELS AFFECTED All 100 series airplanes (1946 and on) All 200 series airplanes (excluding the model 208 series) All 336/337 Skymaster series airplanes ☑ Cessna SNL93-3 DISCUSSION Corrosion is a natural condition that can attack aluminum. An environment of high temperature and humidity tends to accelerate the formation and development of corrosion. Once corrosion begins it will continue until corrected through removal of the corrosion, repair and treatment of the metal or replacement of the affected part. Reports have been received of corrosion occurring under the vibration damping material used on the inside surface of skin panels within the cabin area. If corrosion is left undetected and uncorrected, the skin panels could be damaged to the point of losing structural strength. Inspection for corrosion is part of every 100 hr/Annual Inspection, or equivalent Progressive Inspection. It is recommended that you include the attached information as part of your inspection. APPROVAL FAA approval has been obtained on technical data in this publication that affects airplane type design. Page 1 of 2 To obtain satisfactory results, procedures specified in this publication must be accomplished in accordance with accepted methods and prevailing government regulations. The Cessna Aircraft Company cannot be responsible for the quality of work performed in accomplishing the requirements of this publication. The Cessna Aircraft Company, Product Support, P.O. Box 7706, Wichita, Kansas 67277, U.S.A. (316) 941-7550, Facsimile (316) 942-9006 COPYRIGHT © 1993 MATERIAL The following is available from Cessna Parts Distribution thru an appropriate Cessna Service Station for the suggested list price shown. Part Number Description EA9309-25GRAM EC1300LP Adhesive Adhesive Qty. A/R A/R Price $12.20 (PS) ea. $17.60 (X) pt. NOTE: Additional items called out in the Accomplishment Instructions should be locally procured. ALL PRICES SUBJECT TO CHANGE WITHOUT NOTICE ACCOMPLISHMENT INSTRUCTIONS Cabin Skin Panel Corrosion Inspection And Repair Accomplishment Instructions are attached. * * Page 2 SNL93-3 June 25, 1993 ACCOMPLISHMENT INSTRUCTIONS TITLE CABIN SKIN PANEL CORROSION INSPECTION AND REPAIR EFFECTIVITY MODEL(S) All 100 Series Airplanes(1946 and on) All 200 Series Airplanes (Excluding the Model 208 series) All 336/337 Skymaster Series Airplanes SERIAL NUMBERS All All All Cessna SNL93-3 DESCRIPTION The following procedures provide instructions to inspect and repair corrosion damage under vibration damping material. APPROVAL FAA approval has been obtained on technical data in this publication that affects airplane type design. REFERENCE SNL93-3 CHANGE IN WEIGHT AND BALANCE MODEL WEIGHT CHANGE As Noted Above If applicable, to be computed by installer June 25, 1993 SNL93-3 Page 1 of 22 To obtain satisfactory results, procedures specified in this publication must be accomplished in accordance with accepted methods and prevailing government regulations. The Cessna Aircraft Company cannot be responsible for the quality of work performed in accomplishing the requirements of this publication. The Cessna Aircraft Company, Product Support, P.O. Box 7706, Wichita, Kansas 67277, U.S.A. (316) 941-7550, Facsimile (316) 942-9006 COPYRIGHT © 1993 MATERIAL INFORMATION ACCOMPLISHMENT INSTRUCTIONS PART NUMBER QUANTITY DESCRIPTION EA9309-25 GRAM A/R Adhesive (Cessna) EC1300LP A/R Adhesive (Cessna) Metal Glo #6 A/R Deoxidizer (Turco ARP #11 A/R (Witco Corporation) Corporation) Deoxidizer Allied- Kelite - 2701 Lake Street, Melrose Park, Illinois 60160 TT-M-261 A/R Methyl Ethyl Ketone Alodine-1200 A/R Iridite #14 A/R (MEK) (locally) Iridite (Ditzler Suppliers) (locally) Iridite-Witco Corporation, 2701 Lake Street, Melrose, Illinois 60160 Scotchbrite A/R Abrasive Pad (locally) Aluminum Oxide A/R Abrasive Paper (locally) Paper LD-400 A/R Polymeric Composite Sheet (Lord Manufacturing Company Erie, Pennsylvania) SNL93-3 ACCOMPLISHMENT INSTRUCTIONS 1. Inspection and repair for corrosion under vibration damping material on fuselage belly skins and side panels. A. Gain access and inspect all areas where damping material is used; under floor boards and side panels. If corrosion has started, there may be lumps in the damping material. Ultrasonic thickness measurements or NDI eddy current readings can also aid detection. B. If corrosion is found remove all loose material. C. Clean exposed metal by pouring solvent (methyl ethyl ketone (MEK) or equivalent) on a clean cloth and wiping the surface as required to dissolve or loosen soil. With a dry clean cloth wipe the surface while the solvent is still wet. Do not allow the surface to evaporate dry. D. Repeat step 1.C. until there is no discoloration on the rag. E. F. Remove oxides by abrasive cleaning using aluminum oxide paper and/or Scotchbrite pad. Measure depth of corrosion in the metal. (1) Nonpressurized airplanes are allowed corrosion penetration as deep as 20% of the original metal thickness. (2) Pressurized airplanes are allowed corrosion penetration as deep as 10% of the original metal thickness. June 25, 1993 SNL93-3 Page 2 ACCOMPLISHMENT INSTRUCTIONS G. SNL93-3 (3) If the above limitations are exceeded, the parts shall be repaired or replaced. If the part or parts need to be repaired use the standard methods shown in Figures 1 and 2 for nonpressurized airplanes or Figures 3 thru 7 for pressurized airplanes. Acceptable corrosion depth limits shall be worked as follows: (1) Clean area with solvent. Refer to step 1.C. procedures. (2) (3) Clean with detergent and rinse thoroughly. Liquid dishwashing detergent may be used. Deoxidize by applying Turco's Metal Glo No. 6 or Allied-Kelite ARP No. 11 to all exposed metal. NOTE: If Turco cannot supply the material in small quantity, then ARP No. 11 can be
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supplied by Allied-Kelite instead of Metal-Glo. Refer to material information for address. (a) Mix 1 part deoxidizer to 1 part tap water. (b) Dwell time is 3 to 5 minutes. (c) Rinse thoroughly, do not allow treated surface to dry. (4) Brush chemical film to exposed, wet, deoxidized metal with Allied-Kelite Iridite 14 or Parker/Amchem Alodine 1200. NOTE: Ditzler suppliers can provide the Alumiprep and Alodine 1200 (DX-503) locally. (a) Mix Iridite #14 (1 to 2 ounces per gallon of water). (b) Mix Alodine 1200( 0.8 to 1.2 ounces per gallon of water). Brush swab solution on to metal. Keep a continuous wet film by repeated application for 1 to 5 minutes. A colored inspectable film shall be formed. (c) (d) Blot with a water-damp cloth or swab. (e) Thoroughly flush area with water and dry completely. 2. (5) Apply EA9309 adhesive to the chemically filmed area when replacing the vibration damping material. NOTE: The sound deadening materials purpose is strictly for dampening sound in skin panels and provides no structural advantage. Therefore it is not required to be replaced. (a) Mix EA9309 adhesive per instructions on the container. Apply a coat of adhesive to the surface to be bonded 20 to 30 thousandths thick. Allow it to air dry until the solvent odor is gone (approximately 3 to 4 minutes at 77° F). Press the faying surface firmly together, preferably using a hard rubber or plastic roller, if possible and allow them to remain together for 16 hours at 77° F before handling. Cure for 24 hours at 77° F before applying stress to the bond. Maximum strength develops in 5 days at 77° F. Pressure may be applied by clamps or weights during part or all of the 5 day period as desired. Fuselage inspection and skin repair. A. Mild corrosion appearing upon alclad surfaces does not necessarily indicate incipient failure of the base metal. However, corrosion of all types must be carefully considered and approved remedial action taken. B. C. Small cans appear in the skin structure of all metal airplanes. It is strongly recommended that wrinkles which appear to have originated from other sources, or which do not follow the general appearance of the remainder of the skin panels be thoroughly investigated. Skin patches may be used to repair the skin damage. Skin patches shown in Figure 1, Sheets 1 thru 6 for non-pressurized airplanes and Figure 7, Sheets 1 thru 5 for pressurized airplanes may be used. To repair skins, stringers, channels, and cracks refer to Figures 2, 3, 4, 5 and 6. June 25, 1993 SNL93-3 Page 3 3. ACCOMPLISHMENT INSTRUCTIONS D. SNL93-3 If the damaged area would require a repair which could not be made between adjacent ribs, complete skin panels must be replaced. Ribs and spars may be repaired, but replacement is generally preferable. Where extensive damage has occured, replacement of the entire assembly is recommended. Substitution of rivets. A. B. C. When replacing solid-shank rivets (MS20470) in installations which require raised head rivets, it is desirable to use rivets identical to the type of rivet removed. Countersink-head rivets (MS20426) are to be replaced by rivets of the same type and degree of countersink. When rivet holes become enlarged, deformed, or otherwise damaged, use the next size rivet as a replacement. Replacement shall not be made with rivets of lower strength material. When hi-shear rivets are not available, replacement of sizes 3/16-inch or greater rivets shall be made with close tolerance bolts and self locking nuts of the same diameter and of equal or greater strength than the rivet replaced. The following charts contain approved solid-shank and hi-shear rivet substitutions. EXISTING FASTENER MS20470AD3 MATERIAL THICKNESS REPLACEMENT FASTENERS (OR THICKER) .025 .020 MS20470AD4 .050 .040 .032 .025 CR3243-5 MS20470AD5 .063 NAS1398B4, NAS1398D4 NAS1738B4, NAS1738D4, NAS1768D4 CR3213-4, CR3243-4 NAS1398B4, NAS1398D4 NAS1398B5, NAS1398D5, NAS1738B4, NAS1738E4, NAS1768D4, CR3213-4 NAS1738B5, NAS1738E5, NAS1768D5, CR3213-5, CR3243-4 NAS1398B5, NAS1398D5 .050 NAS1398B6, NAS1398D6, NAS1398B5, NAS1738E5, CR3213-5 .040 NAS1738B6, NAS1738E6, NAS1768D5, CR3213-6, CR3243-5 .032 CR3243-6 MS20470AD6 .080 .071 NAS1398B6 NAS1398D6 .063 NAS1738B6, NAS1738D6, NAS1768D6 CR3213-6 .050 CR3243-6 MS20426AD3 .063 (Countersunk) .040 (See Note 1) .025 NAS1399B4, NAS1399D4 NAS1769D4, CR3212-4 NAS1769B4, NAS1739E4, CR3243-4 MS20426AD3 .063 NAS1399B4, NAS1399D4 (Dimpled) .050 CR3213-4 (See Note 1) .040 MS20426AD4 .080 (Countersunk) .063 .050 NAS1739B4, NAS1739D4, NAS1769D4, CR3242-4 NAS1399B4, NAS1399D4 NAS1739B4, NAS1739D4, CR3212-4 NAS1769D4 .040 CR3242-4 June 25, 1993 SNL93-3 Page 4 ACCOMPLISHMENT INSTRUCTIONS SNL93-3 EXISTING FASTENER MATERIAL THICKNESS (OR THICKER) MS20426AD4 (Countersunk) (See Note 1) MS20426AD4 .050 .040 .032 .063 REPLACEMENT FASTENERS CR3212-5 NAS1739B5, NAS1739D5, NAS1769D4 CR3242-5 NAS1739B4, NAS1739D4 (Dimpled) .090 NAS1399B5, NAS1399E5 (See Note 1) .071 CR3212-5 .063 .050 NAS1739B5, NAS1399D5, NAS1769D5 CR3242-5 MS20426AD5 (Countersunk) .090 .080 CR3212-5 .071 .063 .050 (See Note 1) .063 .040 MS20426AD5 .071 (Dimpled) .090 (See Note 1) .080 NAS1399B5, NAS1399D5 NAS1739B5, NAS1739E5 NAS1769D5 CR3242-5 NAS1739B6, NAS1739D6, NAS1769D6, CR3212-6 CR3242-6 NAS1739D5 NAS1739B6, NAS1739D6, CR3212-6 NAS1769D6 .071 CR3242-6 MS20426AD6 .090 (Countersunk) .071 .063 MS20426AD6 .090 NAS1739B6, NAS1739D6, CR3212-6 NAS1769D6 CR3242-6 NAS1739B6, NAS1739D6 (Dimpled) NOTE 1: Rework required. Countersink oversize to accommodate oversize rivet June 25, 1993 SNL93-3 Page 5 Fastener • NAS178 NAS179 ACCOMPLISHMENT INSTRUCTIONS SNL93-3 Collar Fastener Collar (See Note 1) (See Note 1) • NAS1054 • NAS14XX NAS179, NAS528 (See Note 1) • NAS529 * (See Notes 1 and 2) NAS1446 (See Note 1) * (See Note 1) □ NAS464 NAS7034 □ NAS1103 NAS1080C, NAS1080E, NAS1080G NAS524A NAS1080C, NAS1080A6 NAS1080K AN364, MS20364, MS21042 □ NAS1303 □ NAS6203 □ AN173 ●NAS14XX NAS7034 ☐ NAS1103 AN305, MS20305, MS21044, MS21045 NAS108C, NAS1080E NAS524A |NAS1080C, NAS1080A6 NAS1080K |AN364, MS20304, MS21042 NAS1054 NAS179, NAS528 (See Note 2) • NAS529 * NAS1446 * □ NAS464 NAS14XX NAS1080C NAS1080E NAS1080G ☐ NAS1305 ☐ NAS6203 • NAS529 NAS524A * NAS1446 * □ NAS464 NAS7034 |NAS1080C, NAS1080A6 NAS1080K AN364, MS20364, MS21042 □ NAS1103 □ NAS1303 □ ANS6203 (See Note 3) ☐ NAS1446 See appropriate tables for nominal diameters available. ●NAS529 NAS524A NOTE 1: NOTE 2: NOTE 3: |NAS1080C, NAS1080A6 AVAILABLE IN OVERSIZE FOR REPAIR OF ELONGATED HOLES. REAM HOLES TO PROVIDE A .001 INCH INTERFERENCE FIT. NAS1446 oversize only permitted as a replacement for NAS529. • Steel shank fastener designed for drive-on collars. * Steel shank fastener designed for swage-lock collars. Installation requires sufficient space for the tool and extended shank of the fastener. ☐ Threaded fastener. June 25, 1993 SNL93-3 Page 6 MS20470AD4 RIVETS (24 REQUIRED) O 15° ACCOMPLISHMENT INSTRUCTIONS PATCHES AND DOUBLERS 2024-T3 ALCLAD SNL93-3 -6.50 DIA.. 4.00 DIA.→ PATCH -7.50 DIA.- EXISTING SKIN DOUBLER MS20470AD4 RIVETS (16 REQUIRED) 3.00 DIA. HOLE PATCH REPAIR FOR 3 INCH DIAMETER HOLE 2.00 DIA. HOLE MS20470AD4 RIVETS (8 REQUIRED) 45° 22 1/2° 4.00 DIA. 3.00 DIA. PATCH EXISTING SKIN -5.00 DIA. SECTION THRU PATCH PATCH REPAIR FOR 2 INCH DIAMETER HOLE 2.50 DIA. DOUBLER PATCH (NO DOUBLER REQUIRED) EXISTING SKIN 1.75 DIA. 1.00 DIA. HOLE SECTION THRU PATCH PATCH REPAIR FOR 1 INCH DIAMETER HOLE ORIGINAL PARTS REPAIR PARTS REPAIR PARTS IN CROSS SECTION June 25, 1993 OVERLAPPING CIRCULAR PATCH Figure 1. Skin Repair Non-pressurized Airplanes (Sheet 1 of 6) SNL93-3 Page 7 1/4 B ACCOMPLISHMENT INSTRUCTIONS 1/2 B SECTION THRU ASSEMBLED PATCH VIEW A-A 1/2" RADIUS. CLEAN OUT DAMAGED AREA A -1/2" R. 1/2" RADIUS - 1/2" R. DOUBLER - 2024-T3 ALCLAD SNL93-3 EDGE MARGIN = 2X RIVET DIA. PATCH -2024-T3 ALCLAD A EDGE MARGIN = 2X RIVET DIAMETER RIVET SPACING = 6 X RIVET DIA. EDGE MARGIN = 2X RIVET DIAMETER OVERLAPPING RECTANGULAR RIVET TABLE SKIN GAGE RIVET TABLE PATCH .020 1/8 .025 1/8 .032 1/8 .040 1/8 .051 5/32 ORIGINAL PARTS REPAIR PARTS REPAIR PARTS IN CROSS SECTION June 25, 1993 Figure 1. Skin Repair Non-pressurized Airplanes (Sheet 2) SNL93-3 Page 8 DOUBLER ACCOMPLISHMENT INSTRUCTIONS -B- PATCH 1/4 B EXISTING SKIN SECTION THRU ASSEMBLED PATCH VIEW A-A 1/2" RADIUS EDGE MARGIN = 2 X RIVET DIA. A 1/2 B T 0 1/2" RADIUS 1/2" RADIUS -1/2" R. SNL93-3 NOTE FOR OPTIMUM APPEARANCE AND AIRFLOW, USE FLUSH RIVETS, DIM- PLED SKIN AND PATCH AND COUNTER- SUNK DOUBLER 8 _EDGE MARGIN = 2 X RIVET DIA. PATCH 2024-T3 ALCLAD - A CLEAN OUT DAMAGED AREA SKIN RIVET SPACING = 6 X RIVET DIA. EDGE MARGIN 2 X RIVET DIA. DOUBLER - 2024-T3 ALCLAD RIVET TABLE SKIN GAGE | RIVET TABLE .020 1/8 ORIGINAL PARTS FLUSH RECTANGULAR PATCH (CIRCULAR FLUSH PATCH IS SIMILAR) .025 1/8 .032 1/8 .040 1/8 REPAIR PARTS .051 5/32 REPAIR PARTS IN CROSS SECTION June 25, 1993 Figure 1. Skin Repair Non-pressurized Airplanes (Sheet 3) SNL93-3 Page 9 DOUBLER EXISTING SKIN ACCOMPLISHMENT INSTRUCTIONS DOUBLER T PATCH A< VIEW A-A NOTE COUNTERSINK DOUBLERS AND DIMPLE SKIN AND PATCH. EXISTING SKIN A EDGE DISTANCE 2D MIN. 00 .50 R. MIN. TYPICAL SNL93-3 DOUBLER - 2024-T4 ALCLAD CARRY EXISTING RIVET PATTERN THRU PATCH 100 RIVET TABLE SKIN GAGE RIVET TABLE .020 1/8 .025 1/8 PATCH - 2024-T3 ALCLAD .032 1/8 FLUSH PATCH AT .040 1/8 STRINGER/BULKHEAD .051 5/32 INTERSECTION ORIGINAL PARTS REPAIR PARTS REPAIR PARTS IN CROSS SECTION June 25, 1993 NOTE PITCH 4-8D TYPICAL THIS PROCEDURE IS NOT REC- OMMENDED IN AREAS WHERE STRINGERS ARE RIVETED TO BULKHEADS. Figure 1. Skin Repair Non-pressurized Airplanes (Sheet 4) SNL93-3 Page 10 DOUBLERS EXISTING SKIN PATCH ACCOMPLISHMENT INSTRUCTIONS SNL93-3 8D VIEW A-A SECTION THRU ASSEMBLED PATCH PITCH TYPICAL FOR PATCH SKIN & DOUBLER (4-8D) EXISTING SKIN 0.5" MIN. RADIUS TYPICAL RIVET TABLE SKIN GAGE RIVET TABLE .020 1/8 .025 1/8 .032 1/8 .040 1/8 .051 5/32 OVERLAPPING PATCH AT STRINGER/BULKHEAD |INTERSECTION 1/4 B (BUT NOT LESS THAN 4D) DOUBLER - 2024-T4 ALCLAD PATCH - 2024-T3 ALCLAD ORIGINAL PARTS ☐ REPAIR PARTS REPAIR PARTS IN CROSS SECTION June 25, 1993 A Figure 1. Skin Repair Non-pressurized Airplanes (Sheet 5) CARRY EXISTING RIVET PATTERN THRU PATCH EDGE DISTANCE 2D MIN. SPACER - 2024-T3 ALCLAD SNL93-3 Page 11 VIEW A-A 10 RIVETS EACH SIDE OF DAMAGED AREA ACCOMPLISHMENT INSTRUCTIONS SNL93-3 FILLER - 2024-T4 ALCLAD FUSELAGE SKIN 1/4" EDGE MARGIN A ORIGINAL PARTS A REPAIR PARTS REPAIR PARTS IN CROSS SECTION June 25, 1993 o CLEAN OUT DAMAGED AREA 1/4" RADIUS PICK UP EXISTING SKIN RIVET PATTERN DOUBLER - 2024-T4 ALCLAD MS2047AD4 RIVETS Figure 1. Skin Repair Non-pressurized Airplanes (Sheet 6) SNL93-3 Page 12 ACCOMPLISHMENT INSTRUCTIONS 1/4" EDGE MARGIN DOUBLER - 2024-T4 ALCLAD 5 RIVETS EACH SIDE OF DAMAGED AREA CLEAN OUT DAMAGED AREA VIEW A-A MS20470AD4 RIVETS ORIGINAL PARTS REPAIR PARTS REPAIR PARTS IN CROSS SECTION June 25, 1993 RIVET SPACING TO MATCH PATTERN IN SKIN SNL93-3 STRINGER FILLER - 2024-T4 ALCLAD A A SKIN Figure 2. Stringer and Channel Repair Non-pressurized Airplanes SNL93-3 Page 13
What's in the CESSNA F-337 Skymaster G TCDS
A Type Certificate Data Sheet (TCDS) is the FAA's record of what an aircraft type was approved as. It is the source of truth for weights, seating, fuel and the rules the design was certified against. Expand any line to see what it means.
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