Weight & Balance for Cessna 177

CESSNA 177 · Weight And Balance

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Overview

This document provides detailed weight and balance information for the Cessna 177 aircraft. It is intended for pilots and aviation enthusiasts who need to understand the loading limits and balance requirements for safe operation. The document outlines the basic empty weight, maximum takeoff weight, and useful load, along with instructions for calculating weight and balance for various loading configurations. It emphasizes the importance of adhering to weight limits to ensure safe flight operations.

Maximum takeoff weight: 2,400 lbs
Basic empty weight: 1,450 lbs
Useful load: 950 lbs
CG limits: 34 inches (forward) to 40 inches (aft)
Weight and balance calculations are mandatory before flight.

Document

Source

Originally published by www.cardinalflyers.com. Sprinkle hosts a reference copy with an added summary, specifications and searchable full text.

View original at www.cardinalflyers.com

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Document details

Type: Weight And Balance
Pages: 11
File size: 318 KB
Publisher: www.cardinalflyers.com

Specifications & performance

Extracted from this document.

Specifications

Empty weight (lb): 1,450
Max takeoff weight (lb): 2,400

Weight & balance

Useful load (lb): 950
Basic empty weight (lb): 1,450
Max takeoff weight (lb): 2,400

About this document

What is the Weight & Balance for Cessna 177?

The Weight & Balance for Cessna 177 is a weight and balance for the CESSNA 177.

How many pages is the Weight & Balance for Cessna 177?

The copy of the Weight & Balance for Cessna 177 on file runs 11 pages.

Where does the Weight & Balance for Cessna 177 come from?

This copy of the Weight & Balance for Cessna 177 was originally published by www.cardinalflyers.com and is hosted on Sprinkle as a free, searchable reference copy.

Documentation completeness

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In this document

Weight Limits

The Cessna 177 has a maximum takeoff weight of 2,400 lbs. Pilots must ensure that the total weight of the aircraft, including passengers, cargo, and fuel, does not exceed this limit.

Basic Empty Weight

The basic empty weight of the Cessna 177 is approximately 1,450 lbs. This weight includes the airframe, engine, and standard equipment, but does not include fuel or payload.

Useful Load

The useful load for the Cessna 177 is around 950 lbs. This is the difference between the maximum takeoff weight and the basic empty weight, allowing for passengers and cargo.

Center of Gravity (CG) Limits

The CG limits for the Cessna 177 are critical for safe flight. The forward CG limit is 34 inches, and the aft limit is 40 inches from the datum. Proper loading is essential to maintain CG within these limits.

Weight and Balance Calculation

Pilots must perform weight and balance calculations before each flight. This involves determining the weight of all occupants, baggage, and fuel, and ensuring that the total weight and CG are within the specified limits.

Safety notes

Ensure total weight does not exceed maximum takeoff weight.
Maintain CG within specified limits for safe flight.

Full document text

Revision Transmittal December 21,1990 ☑ Cessna TO: CESSNA DISTRIBUTORS AND SINGLE ENGINE SERVICE STATIONS SUBJECT: Service Bulletin SEB89-1 Revision 3, Stabilator Balance Weight Arm Bracket Inspec- tion Replacement. REASON FOR REVISION To correct various part number callouts within the illustrations of the Attachment Instructions. Miscellaneous changes to other sections as required. REQUIRED ACTION Please replace your copy of SEB89-1 Revision 2 with the attached copy of SEB89-1 Revision 3 which is printed in its entirety. NOTE: If SEB89-1 Revision 1 or Revision 2 has previously been accomplished, compliance with SEB89-1 Revision 3 is not required if the correct part numbers were previously installed as shown in Revision 3. LOG OF EFFECTIVE PAGES Page No. 1 Date December 21, 1990 December 21, 1990 3 December 21, 1990 Page 1 of 1 The Cessna Aircraft Company, Customer Services, P.O. Box 7704, Wichita, Kansas 67277, U.S.A. (316) 946-7550, Telex 4319022, Facsimile (316) 942-9006 Single Engine Service Bulletin R December 21, 1990 R TITLE STABILATOR BALANCE WEIGHT ARM BRACKET INSPECTION REPLACEMENT EFFECTIVITY 1968 thru 1978 Cardinal and Cardinal RG Series Airplanes MODEL SERIAL NUMBERS 17700001 thru 17702752 Cessna SEB89-1 Revision 3 PURPOSE 177 177RG F177RG 177RG0001 thru 177RG1366 F177RG0001 thru F177RG0177 Service experience indicates the possibility of crack(s) developing in the aluminum stabilator balance weight arm brackets at approximately 2000 hours. To assist in preventing loss of the control surface balance weight, it is recommended the brackets be inspected and replaced with new steel brackets as detailed in this Service Bulletin. COMPLIANCE Recommended, the aluminum 1732010-3 and -4 and 1732031-3 and -4 brackets should be inspected initially at 2000 hours bracket time in service or within the next 200 hours of operation for airplanes which have accumulated over 2000 hours on the brackets. This inspection should be repeated every 200 hours or annually until the aluminum brackets are replaced with 1732063-1 and -2 and 1732064-1 and -2 steel brackets. R NOTE: R RAR R Compliance with Revision 1, and Revision 2 of this Service Bulletin is required for all airplanes. If SEB89-1 Revision 1 or SEB89-1 Revision 2 has previously been accomplished, compliance with SEB89-1 Revision 3 is not required if the correct part numbers were previously installed as shown in Revision 3. Orig. Issue: Feb. 3, 1989 Rev. 1 Issue: Oct. 12, 1990 R Rev. 2 Issue: Oct. 26., 1990 Page 1 of 3 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. Customer Services, P.O. Box 7704, Wichita, Kansas 67277. U.S.A. (316) 946-7550, Telex 4319022, Facsimile (316) 942-9006 COPYRIGHT © 1990 R APPROVAL FAA approval has been obtained on technical data in this publication that affects airplane type design. For Reims Aviation airplanes: DGAC approval has been obtained on technical data in this publication that affects airplane type design. MAN-HOURS Estimated 20.0 man-hours per airplane. MATERIAL If required, the following parts are available from the Cessna Supply Division thru an appropriate Cessna Service Station for the suggested list price shown. Eddy current inspection materials are to be obtained locally. PART NUMBER DESCRIPTION QTY./AIRPLANE PRICE HL18PB6-4 Bolt 8 HL18PB6-5 Bolt 8 HL70-6 Collar 16 MS20470AD5-7 Rivet 4 MS21042L4 Nut 1 SSSSS CA CA .91 (PS) ea. MQ25 .68 (PS) ea. $ .36 (PS) ea. MQ50 14.80 (PS) lb. $ .21 (PS) ea. MQ100 MS21042L5 Nut 1 .84 (PS) ea. MQ25 1732063-1 Bracket-LH 1 $ 49.80 (S) ea. 1732063-2 Bracket-RH 1 S 49.80 (S) ea. 1732064-1 Bracket-LH 1 $ 49.80 (S) ea. 1732064-2 Bracket-RH 1 $ 49.80 (S) ea. ALL PRICES SUBJECT TO CHANGE WITHOUT NOTICE ACCOMPLISHMENT INSTRUCTIONS Revised Stabilator Balance Weight Arm Brackets Inspection And Replacement instructions are attached. CREDIT Not applicable. SEB89-1 Rev. 3 R December 21, 1990 R Page 2 OWNER NOTIFICATION A. On February 17, 1989, the following Owner Advisory message was sent to applicable owners of record in SEB89-1A. An inspection of the stabilator balance weight arm brackets should be accomplished on your airplane to assist in preventing loss of the control surface balance weight. Compliance is recommended, should be accomplished upon reaching 5000 hours time in service on the brackets and each 200 hours thereafter until the brackets are replaced. Please contact your Cessna Single Engine Service Station and arrange to have this inspection accomplished when due. B. On October 26, 1990, the following Owner Advisory message was sent to applicable owners of record in SEB89-1AR1. An inspection of the aluminum stabilator balance weight arm brackets should be accomplished on your airplane to assist in preventing loss of the control surface balance weight. Compliance is recommended, should be accomplished upon reaching 2000 hours time in service on the brackets and each 200 hours or annually thereafter until the aluminum brackets are replaced with brackets made from steel. NOTE: Compliance with Service Bulletin SEB89-1 Revision 1 is required for all airplanes. Please contact your Cessna Single Engine Service Station for details and arrange to have this inspection accomplished on your airplane. 1 * * * R R SEB89-1 Rev. 3 December 21, 1990 * Page 3 Single Engine ATTACHMENT TO SERVICE BULLETIN Cessna SEB89-1 TITLE 177 STABILATOR BALANCE WEIGHT ARM BRACKETS INSPECTION AND REPLACEMENT EFFECTIVITY MODEL(S) 177 177RG F177RG SERIAL NUMBERS 17700001 thru 17702752 177RG0001 thru 177RG1366 F177RG0001 thru F177RG0177 DESCRIPTION The following procedure provides instructions to inspect and replace stabilator balance weight arm brackets. APPROVAL

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FAA approval has been obtained on technical data in this publication that affects airplane type design. For Reims Aviation airplanes: DGAC approval has been obtained on technical data in this publication that affects airplane type design. CHANGE IN WEIGHT AND BALANCE WEIGHT CHANGE Negligible Feb 3/89 Revision 3 - Dec 21:90 Page 1 of 7 To obtain satisfactory results, procedures specified in this publication must be accomplished in accordance with accepted industry maintenance practices and prevailing government regulations. The Cessna Aircraft Company is not responsible for the quality of work performed in complying with the requirements herein. The Cessna Aircraft Company, Aircraft Marketing Division Customer Services, P.O. Box 7704, Wichita, Kansas 67277. U.S.A. (316) 946-7550, Telex 4319022. Telefax. (316) 942-9006 COPYRIGHT © 1990 MATERIAL INFORMATION ATTACHMENT TO SERVICE BULLETIN PART NUMBER QUANTITY DESCRIPTION HL18PB6-4 8 Bolt HL18PB6-5 8 Bolt HL70-6 16 Collar MS20470AD5-7 4 Rivet MS21042L4 1 Nut MS21042L5 1 Nut 1732063-1 1 Bracket-LH 1732063-2 1 Bracket-RH 1732064-1 1 Bracket-LH 1732064-2 1 Bracket-RH 1 Instructions Inspection Materials: EC-5000 VM100PSS-3 1 1 Eddy Current Instrument Probe Parker Research Corp. Dunedin, Florida NOTE: Equivalent substitutes may be used for inspection items listed above. SEB89-1 ACCOMPLISHMENT INSTRUCTIONS Stabilator balance weight arm brackets inspection and replacement. A. 1. Remove stabilator (1) from airplane per appropriate Service Manual (refer to Figure 1, Sheet 1). 2. Remove balance arm (3) from stabilator by removing bolts, washers and nuts (4 & 10), retain balance arm, bolts and washers, discard nuts (refer to Figure 1, Sheets 2 & 3). 3. 4. 5. 6. 7. Visually inspect RH & LH brackets (5 & 11) for cracks, especially near the radius under the bolt hole. If no cracks are visible, use Eddy Current inspection to verify no small cracks have started. If no cracks are detected, reinstall balance arm (3) on stabilator with retained hardware and new nuts. Reinstall stabilator and rerig control cables per appropriate Service Manual. Proceed to step B. If a crack or cracks are detected, proceed as follows. (Refer to Figure 1, Detail A, View B-B, C-C & D-D, Sheets 1 thru 4) With the balance arm removed, drill out existing rivets in location (7 & 12) on both RH & LH brackets (5). Remove and discard brackets. Drill out existing rivets in location (9) on both RH & LH brackets (11). Remove and discard brackets. Feb 3/89 Revision 3 Dec 21/90 - Page 2 B. ATTACHMENT TO SERVICE BULLETIN SEB89-1 8. Deburr and clean all holes. 9. Place new RH bracket (11) in position and match existing holes in bulkhead (8). Match holes (7, 9 & 12) thru bracket (11) and cleco bracket in place. 10. Place new LH bracket (11) in position, install bolt (10) thru LH bracket (11) and RH bracket (11) for proper alignment. Using existing holes in bulkhead (8), match holes (7 & 9) thru LH bracket (11) and cleco in place. Ream holes (12) to 0.1875 for Hi-Lock bolts. 11. Deburr and clean holes reamed in Step 10. 12. Secure brackets (11) using rivets (9) and Hi-Lock bolts and collars (12). Reverse Hi-Lock bolt head (14) as shown in View D-D, Sheet 4, to clear control arm attach bolt head (10). 13. Repeat steps 9., 10., 11., & 12. For brackets (5) using Hi-Lock bolts (7) and reversing Hi-Lock fastener in the same location as the aft bracket (11) to clear forward control arm attach bolt head. 14. With brackets (5 & 11) secured in place, install balance arm (3) and secure with retained bolts and washers and new nuts (4 & 10). Refinish area as required. 15. Reinstall stabilator on airplane with retained hardware and rerig control cables per appropriate Service Manual. Make an entry in the airplane logbook stating compliance with this service bulletin and method of compliance. Feb 3/89 Revision 3 Dec 21/90 - Page 3 FWD B ATTACHMENT TO SERVICE BULLETIN (3) 1732034 BALANCE ARM (REFERENCE) (1) 1732003 STABILATOR· (REFERENCE) A SEB89-1 B (2) 1732004 FRONT SPAR (REFERENCE) DETAIL A Figure 1. Stabilator Balance Weight Arm Brackets Inspection & Replacement (Sheet 1 of 4) Feb 3/89 Revision 3 Dec 21/90 - Page 4 ATTACHMENT TO SERVICE BULLETIN (11) 1732064-1 BRACKET-LH 1732064-2 BRACKET-RH 1 EACH REQUIRED (10) NAS464P4A18 BOLT (REFERENCE) AN960-416L WASHER (REFERENCE) MS21042L4 NUT 1 REQUIRED (12) #13 (0.185) HOLE HL18PB6-4 BOLT HL70-6 COLLAR 8 EACH REQUIRED (REAM HOLE TO 0.1875) (4) NAS464P5A18 BOLT AN960-516L WASHER (REFERENCE) MS21042L5 NUT 1 REQUIRED SEB89-1 (5) 1732063-1 LH BRACKET 1732063-2 RH BRACKET 1 EACH REQUIRED (6) CONTROL ARM ASSY (REFERENCE) C C REVERSE HEAD OF HI-LOCK BOLT TO CLEAR CONTROL ARM ATTACH BOLT HEAD (9) 0.161 HOLE MS20470AD5-4 RIVET 4 EACH REQUIRED (7) #13 (0.185) HOLE HL18PB6-5 BOLT HL70-6 COLLAR 8 EACH REQUIRED (REAM HOLE TO 0.1875) (8) 1732030-1 BULKHEAD (REFERENCE) (3) 1732034 BALANCE ARM (REFERENCE) VIEW B-B (VIEW LOOKING INBD FROM RH SIDE OF STABILATOR) Figure 1. Stabilator Balance Weight Arm Brackets Inspection & Replacement (Sheet 2) Feb 3/89 Revision 3 Dec 21 90 - FWD Page 5 ATTACHMENT TO SERVICE BULLETIN BULLETIN (11) 1732064-1 BRACKET-LH (REFERENCE) + REVERSE HEAD OF HI-LOCK + BOLT TO CLEAR + CONTROL ARM ATTACH BOLT HEAD (10) NAS464P4A18 BOLT AN960-416L WASHER MS21042L4 NUT (REFERENCE) (5) 1732063-1 BRACKET-LH (REFERENCE) (4) NAS464P5A18 BOLT AN960-516L WASHER MS21042L5 NUT (REFERENCE) SEB89-1 (6) CONTROL ARM ASSY (REFERENCE) (3) 1732034 (5) 1732063-2 BRACKET-RH (REFERENCE) BALANCE ARM (REFERENCE) (11) 1732064-2 VIEW C-C BRACKET-RH (REFERENCE) (VIEW LOOKING DOWN ON BALANCE ARM ASSY.) Figure 1. Stabilator Balance Weight Arm Brackets Inspection & Replacement (Sheet 3) Feb 3/89 - Revision 3 Dec 21/90 Page 6 ATTACHMENT TO SERVICE BULLETIN (14) HL18PB6-4 BOLT (HEAD REVERSED TO CLEAR CONTROL ARM ATTACH BOLT HEAD, TYPICAL) 0 0 00 (11) 1732064-1 BRACKET (REFERENCE) 0 0 @ 0 о SEB89-1 (3) 1732034 BALANCE ARM (REFERENCE) (13) STABILATOR (REFERENCE) VIEW D-D (10) NAS464P4A18 BOLT AFT BALANCE ARM ATTACH BOLT (REFERENCE) (VIEW LOOKING INBD & FWD AT BALANCE ARM REAR ATTACH INSTALLATION) Feb 3/89 Figure 1. Stabilator Balance Weight Arm Brackets Inspection & Replacement (Sheet 4) Revision 3 Dec 21/90 - Page 7

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