Weight & Balance for the Reims-Cessna F177RG Cardinal

Approved Revision 18 Cenna 206 ACE CAR 3 1000 Revision H. dated 14/29/2000 11/20/2000, or later FAA FAA Approved Arting Manage Seattle Alterall Certification Office Amended: August 31, 1994, September 7, 1994 June 6, 1995 November 29, 2000 Aproved Revision 19 Cems P206 through E JACE CAR 3 1000 Revision E. dated 11/29/2000 11/29/2000, or later FAA Approved Revision 20 Camona TP206A through E A4CE CAR 1000 Revition E, dated 118293030 11/29/2000 or later FAA Approved Revision IMPORTANT DOCUMENTS KEEP WITH AIRCRAFT RECORDS B.A.S, INC INSTALLATION INSTRUCTIONS INERTIA REEL HARNESS CESSNA CARDINAL 177 MARCH 31, 1989 1. The 177 has had many small changes throughout its life. This is why you as a mechanic must determine if things don't look right and either call me or return the kit for a full refund. 2. Early pre 1971 models had 3.5" lightening holes in the carry-through spar as opposed to the later models 3" lightening holes. These holes must be measured to insure that the correct kit is ordered. 3. In the mid 1970's fuel vent lines were installed in the area forward of the carry-through spar. These lines cross from the bottom of one tank to the top of the other. So far, in my experience, these lines have not proved to be a problem because the harness comes out between them. (Refer to Cardinal Installation Photo Sheet) To check for these lines, remove center headliner console cover and cabin light cover and look aft. If the 3/8" vent lines or other objects are in the area, remove the front half of the headliner and attach moldings. This only takes about 15 minutes and allows easy access for installing the reel assemblies. It's also a good time to do a corrosion check. CAUTION IF THE VENT LINES OR ANYTHING ELSE WILL NOT ALLOW THE HARNESS SYSTEM TO BE INSTALLED ABSOLUTELY PROPERLY, IN AN AIRWORTHY MANNER, RECONNECT CENTER VENT LINE CLAMP, REINSTALL HEADLINER AND RETURN SHOULDER HARNESS KIT FOR FULL REFUND. In the event you discover a problem I would appreciate a photo. If you find any everything is OK, continue with step 1. INSTRUCTIONS 1. Remove inspection panel behind carry-through spar, look at carry-through spar and locate the second from the center lightning hole on each side of the spar center line (refer to drawing). These holes should be directly behind pilot and co-pilot. Check to see that no lines or wires travel through these holes which can not be moved to the top of the hole and the lines or wires are not larger than 4" for spars with 3" holes and %" for spars with 3 " holes. This is to allow for the inertia reel mounting bracket. The 2" Acroduct in front of the spar can be moved up and forward. You may have to remove the Coroseal cord or tie wrap that holds the Acroduct to the spar for added slack. 2A. Aircraft Without Vent Lines. If there is room to install reel mounts continue on to step 3. below 2B. Aircraft With Vent Lines, (Front half of the headliner removed) Disconnect the center vent line clamp so that you can spread the fuel lines apart. Slip the reel and mounting bracket between lines and install on the carry-through spar as per step number 4, Cardinal 177 Rev A August 1, 2000 Installation Instructions BAS Incorporated Report 1200 Sheet 1 of 3 STC SA 2067NM AGRODA MAMA DONN After the reel assemblies have been installed, reconnect the fuel vent line clamp. Refer to the Cardinal Installation Photo Sheet and mark and cut holes in headliner as per step number 3. Reinstall headliner by fitting the buckle and belts through the small preliminary hole cut in the headliner. Finish attaching moldings, etc. Finish cutting hole to fit and carry on with steps 5,6 and 7. 3. Locate exact center line of carry-through spar and mark at the forward edge of the headliner where it curves around front bottom edge of carry-through spar. Masking tape may be used in these locations for easier clean up. From this mark, measure outboard 8 ½" and make light pencil mark. Now measure upward 24" from center of front radius as shown in the drawing and photo. This is the center for the 2 1/4" by 4" hole as shown in the drawing At this point insert a long needle or sharpened welding rod through the plastic headliner. The needle should be in the exact vertical center of the lightening hole and if laid fore and aft, horizontally, it should be approximately 1/4" to " above bottom of the lightening hole (depending on the hole size being 3" or 3 ½"). If these measurements look pretty close, mark out a horizontal hole 4" long and 24" high with the needle hole as the center. Now use a sharp knife or razor blade to cut out a hole approximately 1/4" in from the lines, NOTE: LOOK THROUGH THIS HOLE TO MAKE SURE THE 3" HOLE IN THE SPAR IS IN ALIGNMENT WITH THE MARKS AND ADJUST MARKS IF NECESSARY. Finish cutting out the 2" by 4" hole. This is a good time to inspect the front face of the carry-through spar. Clean any corrosion off and paint the area if necessary, Also make slack in the Aeroduct if necessary (refer to instruction #1). 4. Install reel and bracket assembly through the 2" by 4" hole by putting the top of the rectangular mounting bracket in first, then twist up and push the rest of the reel in through the hole. NOTE: WHILE INSTALLING THIS PART, REACH UP THROUGH THE INSPECTION HOLE AND THROUGH THE SPAR HOLE TO PUSH THE AERODUCT UP AND FORWARD. 4A. Now hold mounting bracket over hold in spar and install bolts, washers and back up plate (PN 1B-177) in through rear inspection hole and place over back side of the hole with holes closest together at the bottom (refer to drawing). Install bolts into mut plates on PN 1A-177 mounting bracket finger tight. Align the belt guides in front so that they are horizontal and level. Tighten mounting bolts, but do not over torque, 15 to 20 inch pounds is sufficient. 5. Fit dress plates over belt with split towards the top and tuck up into position (refer to drawing). Trim if and where necessary. When the dress plate looks right, mark the two attachment holes with a pencil or an awl and install tinnerman nuts, trim headliner if necessary to slip muts over hole locations. Re-position dress plate and install with #6 sheet metal screws. Reinstall rear inspection Cover. 6. Remove old lap belts and attach new lap belts in the same manner. NOTE: CESSNA USES A '\" BOLT THROUGH A SHORT LENGTH OF 3/8" TUBING THAT GOES THROUGH THE HOLE IN THE BELT END FITTING. SEE PARTS MANUAL IF PARTS ARE MISSING OR WORN. 7. Fill out logs and send in FAA Form 337. Revise the weight and balance. Weight difference between the lap belt only and the BAS, Inc. Inertia Reel Shoulder Harness System is 3½ pounds total for both front seats. If the BAS. Inc. system replaces a Cessna shoulder harness, figure weight of actual parts. The additional weight is centered at Fuselage Station 110.00. Cardinal 177 Rev A August 1, 2000 Installation Instructions BAS Incorporated Report 1200 Sheet 2 of 3 STC SA 2067NM Vent Linos Use these holes Photo No. 1 Installation Item No. 2B Photo No. 4 Installation Item No. 4 Photo No. 2 Aircraft With Vent Lines Photo No. 5 Installation Item No. 4A 4 2314 21/2 Confer of aircraft 8 1/2 Photo No. 3 Installation Item No. 3 Photo No. 6 Installation Item No. 5 Cardinal 177 Photographs Rev A August 1, 2000 BAS Incorporated Report 1200 Sheet 3 of 3 STC SA 2067NM A- Symmetric 0:0 о 8-1/2" Carry-Through Spar (Looking forward) Cabin Roof PN 1-8-177 Molded Plastic Headliner PN 1-A-177 (incl. plate nuts) AmSafe PN 505321 421 Inertia Reel PN 2 HT PN 4-177 PN 3-177 Shoulder Harness Webbing Hardware 4. ea. AN3-6A Boll 4 eo. AN960-10 Washer 4 eg. MS24694-850 Screw A ea. NAS679-A3W Nut 1 ea. AN525-10R7 Screw I ea. NAS679-A3W Nut 2 ea. NA5679-A3W Nul 2 ea. AN525-10R7 Screw 2 ea Plastic Spacer 2 ea. $1021A6-B Screw 2 ea. A1784-62-1 Tinnerman Nut NO SCALE Figure No. 1-177 Section A-A Installation Rev. B November 1, 2005 BAS Incorporated STC SA 2067NM IMPORTANT DOCUMENTS KEEP WITH AIRCRAFT RECORDS B.A.S., INC. INERTIAL REEL SHOULDER HARNESS SYSTEM 1. Introduction: INSTRUCTIONS FOR CONTINUED AIRWORTHINESS These ICA pertain to the inertia reel shoulder harness system installed in the 2 forward seating positions, 2. Description: The shoulder harness system consists of an inertia reel mounted to the aircraft cabin roof above and behind each seat a "Y" shaped shoulder harness, a lap belt with mating buckle and associated bracketry and hardware to attach the system to the aircraft. 3. Special control or operation information: See Owner's Manual Supplement. Report 1302, for proper placement of harness. Servicing information: There is no regular servicing required for the shoulder harness system beyond normal cleaning. Refer to AmSafe website for cleaning instructions. [www.amsafeaviation.com] There is no regular servicing of the attachment hardware required. 5. Maintenance instructions Maintenance of the inertia reel and harness is limited to cleaning. The attachment hardware and brackety should be inspected as part of the annual inspection of the aircraft for deformation or cracking of the bracketry and that the hardware is secure (see AC 43.13-1B, 9-8-98. Paragraph 5-15). Check the attachment bracketry and hardware for corrosion per AC 43.13-1B, 9-8-98, Chapter 6. Any bent, broken, damaged or corroded parts must be replaced. 6. Troubleshooting: N/A 7. Removal and replacement information: Refer to BAS Installation Instructions, used during original installation, for removal and replacement information on the inertia reel. These should be included as part of the maintenance records of the aircraft, but may also be obtained from BAS, Inc. If the reel is removed, ensure that all of the components Such as the tension strap (when installed) are properly reattached upon reinstallation of the reel, 8. Diagrams: N/A 9. Special inspection requirements; The inertia reel and attachment hardware and bracketry should be inspected for proper operation during annual inspection of the aircraft. The reel should allow for extension of the harness during a slow pull. but should lock up during a quick pull of the harness. Failure of the reel to function properly in either of these conditions is cause for removal and return to AmSafe for repair or replacement. 10. Application of protective treatments: N/A Continued Airworthiness Report 1502 Rev C May 3, 2006 Page 1 of 2 BAS Incorporated STEM 000 TMATFORM B.A.S., INC. INERTIAL REEL SHOULDER HARNESS SYSTEM INSTRUCTIONS FOR CONTINUED AIRWORTHINESS (cont) 11 Data: N/A 12 List special tools: None 13. For commuter category aircraft: N/A 14. Recommended overhaul periods: The shoulder harness does not have a fixed overhaul period, but should be inspected and replaced on condition. Refer to AmSafe website for removal and replacement information on the shoulder harness system. 15. Airworthiness Limitation Section: There are no limitations on the operation of the aircraft due to the installation of the shoulder harness system This Airworthiness Limitations section is FAA approved and specifies maintenance required under Secs. 43.16 and 91.403 of the Federal Aviation Regulations unless an alterative prograin has been FAA approved. 16. Revisions: These Instructions for Continued Airworthiness have been reviewed and accepted by the FAA. In the event a revision is required, BAS, Inc. will submit the revision to the FAA for review and approval. The revised ICA will then be posted on the BAS website or contact BAS, Inc. and the revision will be mailed. The revised ICA must become a part of the aircraft records and a logbook entry made noting the revision. For harness & lap belt maintenance refer to AmSafe Aviation information at www.amsafeavitiation.com If the AmSafe website is unavailable, please contact BAS, Inc. 888-255-6566 360-832-6566 360-832-6466 Fax For the latest revision of ICA refer to BAS information at www.basine-aeromod.com Continued Airworthiness Report 1502 Rev C May 3, 2006 Page 2 of 2 BAS Incorporated US Department of Transportation Federal Aviation Administration MAJOR REPAIR AND ALTERATION (Airframe, Powerplant, Propeller, or Appliance) Fom Approved OMB No. 2120-0020 For FAA Use Only Office Identification INSTRUCTIONS Print or type all entries See FAR 439, FAR 43 Appendix B, and AC 43.9-1 (or subsequent revision thereof) for instructions and disposition of this form. This report is required by law (49 US.C. 1421) Failure to report can result in civil penalty not to exceed $1.000 for each such violation (Section 901 Federal Aviation Act of 1958). Make 1. Aircraft Serial No. 2. Owner Cessna 17700512 Name (As shown on registration certificate) Charles H Mount Jr. Unit Make AIRFRAME POWERPLANT PROPELLER Type APPLIANCE Manufacturer Model 177 Nationality and Registration Mark N3212T Address (As shown on registration certificate) 3. For FAA Use Only 4. Unit Identification Model (As described in Item 1 above)- 1621 Hampton Place Orange Park Fl 32003-7284 5. Type Serial No. Repair Alteration X A. Agency's Name and Address Bryan M Wood Southeast Aero Services Inc. 385 Hawkeye View Lane St Augustine Fl 32095 6. Conformity Statement B. Kind of Agency XUS Certificated Mechanic Foroian Certificated Mechanic Certificated Repair Station Manufacturer C. Certificate No. 254306757 D. I certify that the repair andar alteration made to the unit(s) identified in item above and desorbed on the reverse or attachments here to have been made in accordance with the requrements of Part 43 of the US Federal Aviation Regulationis and that the information furnished herin is true and correct to the best of my knowledge. Date Signature of Authorized-individual 2-23-07 7. Approval for Return To Service Pursuant to the authority given persons specified below, the unit identified in item 4 was inspected in the manner prescribed by the Administrator of the Federal Aviation Administration and is FAA FIL Standards Inspector BY Manufacturer FAA Designee Repair Station Date of Approval or Rejection 2-23-07 FAA Form 337 (126) APPROVED Inspection Authorization REJECTED Other (Specify) Certificate or Designation No. 254396757 Person Approved by Transport Canada Airworthiness Group Signature of Authorized individual Electronic Version) Work completed for f NOTICE N3212Ton 2-23.07 Weight and balance or operating limitation changes shall be entered in the appropriate aircraft record. An alteration m be compatible with at previous alterations to assure continued conformity with the applicable airworthiness requirements 8. Description of Work Accomplished Installed BAS Inc. Inertia Reel Shoukider Harness System STC# SA2067NM in accordance with manufacturers install document 1200 Rev.A. STC, Approved model list, Instructions for Continued Airworthiness and Weight & Balance Revision entered into Aircraft Permanent Records. --END [ ] Additional Sheets Are Attached