Instructions for Continued Airworthiness

when installed in accordance with Aviation Fabricators design data included on STC Drawing List AF-162 per Supplement Type Certificates (STC) SA00068WI. Modifications to an aircraft obligates the operator to include the maintenance information provided by this document into the operators aircraft Maintenance Manual and operator’s aircraft scheduled maintenance program. This document defines supplementary maintenance operations and frequencies recommended by Aviation Fabricators Inc., to ensure the aircraft’s airworthiness. The information contained herein addresses the requirements specified in 14 CFR 23.1529, Instructions for Continues Airworthiness and supplements the basic Airplane Maintenance Manual only in those areas listed as pertains to the installation of the stretchers, as installed per the Aviation Fabricators STC Drawing List AF-162. For limitations and procedures not contained in this supplement, consult the Airplane Maintenance Manual. DATA All information to support the continued airworthiness of this modification is contained in: STC SA00068WI STC Drawing List: AF-162 Installation: STC Drawing Lists: AF-162: Drawing AF-115 for p/n’s 32-0114K and 32-0114K-X Parts: Refer to p/n’s 32-0114 on respective drawings as listed on STC Drawing Lists AF-162. The stretcher is a self contained complete assembly that mounts to the existing seat track and foot fittings, using standard fittings and hardware. Design Change Control All data and changes to the parts and assemblies will be tracked per STC Drawing List AF-162 latest approved revisions. Applicable Aircraft Beechcraft models: 36, A36, A36TC, B36TC, 58, 58TC, 58A, 58TCA aircraft. Aviation Fabricators Inc. ICA Document No.: AF-609 805 North Fourth Street Revision (IR) Clinton, MO. 64735 Date: October 6, 2014 Page 6 of 12 Stretcher Assemblies P/N’s 32-0114K, 32-0114K-1 (shown) , 32-0114K-2 FLOOR FITTING STRETCHER LEG LOCK PIN LOCK BUSHING AFT FOOT ATTACHMENT FWD IB MATTRESS ASSEMBLY VELCROES TO STRETCHER COVER ASSEMBLY ALUMINUM TOP COVER STRETCHER COVER ASSEMBLY STRETCHER ASSEMBLY SEAT BELT FERNO 12-1 PORTABLE LITTER W/ OPTIONAL MATTRESS PAD INSTALLER TO USE AS PREFERRED OR FERNO 1402 PORTABLE LITTER W/ OPTIONAL MATTRESS PAD INSTALLER TO USE AS PREFERRED (SHOWN) (NOT SHOWN) SEAT BELT W/ HARNESS 2 PLCS Figure 1.0A Aviation Fabricators Inc. ICA Document No.: AF-609 805 North Fourth Street Revision (IR) Clinton, MO. 64735 Date: October 6, 2014 Page 7 of 12 Seat Belt & Shoulder Harness Attachment NUT WASHER SCREW SPACER RESTRAINTS Figure 1.0B 2.0 INSPECTION REQUIREMENTS AND OVERHAUL SCHEDULE 1. To comply with14 CFR 23.1529, continue the new stretcher and restraint system on the same inspection and maintenance schedule used per the applicable Beechcraft Maintenance Manual for seats. a. The new stretcher and restraint systems require no service other than inspection at normal inspection interval of 100 hours or annually. b. Perform a detailed visual inspection of the stretcher mattress bottom and top covering to detect apparent or obvious defects or irregularities. On the mattress assembly, check for cracks and punctures within a 4” diameter circle. The mattress assembly can have no more than three defects found within the 4” diameter circle. If it develops a “lump”, check to see if there are no more than two lumps within a 4” diameter circle. Any damage to the mattress assembly outside of the described limits will require it to be replaced. Visually inspect the covering assembly for holes, punctures, and tears. If the damage to the covering is holes smaller than ½” in diameter or a cut at a maximum of 2” in length then the covering is satisfactory. The sewing of the cover assembly cannot have a tear or cut exceeding 1” in length. Any damage to the covering assembly outside of the described limits will require it to be replaced. Aviation Fabricators Inc. ICA Document No.: AF-609 805 North Fourth Street Revision (IR) Clinton, MO. 64735 Date: October 6, 2014 Page 8 of 12 c. Visually inspect the stretcher assembly tubing and diaphragm for cracks and deformation. Damaged conditions can be detected as a crack at the edge of the tube or along the length of the tubes or as a crack, tear or cut found on the seat bottom diaphragm. Visually inspect all hardware for excessive wear before and after installation. Replace the stretcher top diaphragm if two cracks or deformations are found within a 4” diameter circle. If a tear or cut is found with a maximum 6” length, replace the diaphragm. There shall be no broken tubes. There shall be no sharp corners, edges, or protrusions that may injure passengers. Replace the tubes if they are bent in such a way that they are more than 2” off center. Replace the stretcher tubes if crack length is found to be .125” or greater. Replace the tube if a dent is found running longer than 3”. Replace the stretcher tubes if deformation is greater than .25” the overall thickness of the tube diameter. Cracked or broken fasteners or fittings are to be replaced with new immediately. For repair or replacement of damaged or broken parts or assemblies contact Aviation Fabricators Inc. Aviation Fabricators Inc. ICA Document No.: AF-609 805 North Fourth Street Revision (IR) Clinton, MO. 64735 Date: October 6, 2014 Page 9 of 12 2. Inspection Time Limit for Stretcher Assembly Installations: 100 hour or annual inspection for the stretcher and restraint systems Task Code Schedule Date Mech Insp AFI-100 a. Inspect for damage to upholstery. AFI-101 b. Inspect safety belts for wear, cuts, fraying, damage, and deterioration. AFI-102 c. Inspect safety belt attachment fittings for wear and damage AFI-103 d. Inspect foot fittings for damage, security, and function. AFI-104 e. Inspect stretcher frame for damage, and corrosion. AFI-105 f. Inspect overall stretcher assembly for fit and function. A. The new stretcher and restraint system are on the same inspection and maintenance schedule used per the applicable Beechcraft Maintenance Manual for passenger seats. Aviation Fabricators Inc. ICA Document No.: AF-609 805 North Fourth Street Revision (IR) Clinton, MO. 64735 Date: October 6, 2014 Page 10 of 12 3.0 DIMENSION AND ACCESS: The installation of the stretcher assembly does not change the dimensions of the aircraft or alter the access to any existing aircraft system. 4.0 LIFTING AND SHORING No change. 5.0 LEVELING AND WEIGHING Stretcher w/ Seat Belts = 21 lbs Optional Mattress = 8.5 lbs Ferno 12-1 Portable Litter = 15 lbs Ferno 1403 Portable Litter = 25 lbs Total = 44.5 lbs 54.5 lbs Stretcher Length = 72 inches 6.0 TOWING AND TAXIING No change. 7.0 PARKING AND MOORING No change. Aviation Fabricators Inc. ICA Document No.: AF-609 805 North Fourth Street Revision (IR) Clinton, MO. 64735 Date: October 6, 2014 Page 11 of 12 8.0 PLACARDS AND MARKINGS No change. 9.0 SERVICE INFORMATION Typical Stretcher Service Instructions: A. Upholstery Cleaning: Stretcher Service Instructions 1. Remove the mattress and cover assemblies from the stretcher. 2. Clean covering with Armour All leather cleaner or equivalent. 3. Clean drawer finish using Armour All multi-purpose cleaner or equivalent. 4. Clean and inspect restraint system for damage or excessive wear. 5. Inspect all attachment fittings and replace if necessary. 6. Inspect overall stretcher for fit and function. Typical Stretcher Service Instructions: Stretcher Assembly The stretcher is a self contained complete assembly that mounts to the existing seat track and foot fittings, using standard fittings and hardware. To remove the stretcher assembly from the aircraft removed lock pins and bushing from aft leg attaching points and slide stretcher off forward track. To install the stretcher slide the forward feet on existing T track and then align the aft legs to the existing foot fittings. Secure into place using existing lock pins and bushings. Refer to Figure 1.0A. Mattress and Seat Cover The mattress assembly is removed by simply pulling it upward from the Velcro on the stretcher cover. The stretcher cover is removed by pulling it away from the Velcro on underside of the stretcher top frame. Seat Belt and Shoulder Harness Seat belt and Shoulder Harness removal is accomplished by loosening attaching hardware and removing from the stretcher frame assembly. Refer to Figure 1.0B. B. RECOMMENDED OVERHAUL PERIODS No additional overhaul time limitations and requirements apply to the Aviation Fabricators Stretcher Assemblies. Aviation Fabricators Inc. ICA Document No.: AF-609 805 North Fourth Street Revision (IR) Clinton, MO. 64735 Date: October 6, 2014 Page 12 of 12 10.0 AIRWORTHINESS LIMITATIONS The Airworthiness Limitations section is FAA approved and specifies maintenance required under Sec. 43.16 and 91.403 of the Federal Aviation Regulations unless an alternative program has been FAA approved. There are no Airworthiness Limitations to the aircraft with the addition of the Stretcher Assembly installed by this STC. 11.0 TROUBLESHOOTING Refer to the existing Aircraft Maintenance Manual for troubleshooting the stretcher installation that is required beyond the information found on the installation drawing AF-115. For replacement parts or repair of damage parts: Contact Aviation Fabricators at (660) 885-8317. Troubleshooting this installation should only be accomplished by FAA approved repair stations with the appropriate ratings or appropriately rated operator/individuals, with required test equipment and service data.