CIRRUS AIRPLANE MAINTENANCE MANUAL

Transcription

1 REPLENISHING 1. DESCRIPTION This section covers the replenishing of fuel, engine oil, hydraulic brake fluid, tire pressure, battery electrolyte, de-icing fluid, and air conditioning refrigerant. (See Figure 1) Page 1

2 Description P/N or Spec. Capacity Fuel 100 LL (Blue) or 100 (Green) Serials 0002 thru 2437: Total Tank Capacity: 84.0 Gallons (318.0 L) total wing 42.0 Gallons (159.0 L) each wing Usable: 81.0 Gallons (306.0 L) total wing 40.5 Gallons (153.0 L) each wing Usable Filled To Tab: 47.0 Gallons (178.0 L) total wing 23.5 Gallons (89.0 L) each wing Serials 2438 & subs: Total Tank Capacity: 94.5 Gallons (358.0 L) total wing Gallons (179.0 L) each wing Usable: 92.0 Gallons (348.0 L) total wing 46.0 Gallons (174.0 L) each wing Usable Filled To Tab: 60.0 Gallons (228.0 L) total wing 30.0 Gallons (114.0 L) each wing Oil SAE J1966 Mineral Oil (1st 25 Hours) See Approved Oil Listing (Refer to ) 8.0 US Quarts (7.6 L) De-Icing Fluid DTD 406-B Serials 0002 thru 2437: 2.96 Gallons (11.2 L) Serials 2438 & subs: 3.75 Gallons (14.2 L) Battery 1 Distilled Water As Required Brakes Mil-H-5606 Hydraulic 0.25 US Quart (0.24 L) Nose Tire Dry Compressed Air Serials 0002 thru 2437: 40 psi (276 kpa) Serials 2438 & subs: 30 psi (207 kpa) Main Tires Dry Compressed Air 62 psi (427 kpa) Refrigerant R134a 2.0 lb (0.91 kg) Figure 1 Approved Materials and Service Capacities Page 2

3 Description P/N or Spec. Capacity Caution: Polyester oil and polyalkyline glycol oil are not interchangeable. Air Conditioning Compressor P/N P/N Polyester Oil (Viscosity ISO 68) Polyalkyline Glycol Oil (PAG) 5 oz (0.15 L) 4 oz (0.12 L) Figure 1 Approved Materials and Service Capacities Page 3

4 2. MAINTENANCE PRACTICES A. Fuel System (1) Safety Precautions WARNING: A fire extinguisher must be available. Ground exhaust pipe outlet and fuel service equipment prior to every fueling and defueling procedure. Check wing fuel tank vents for obstruction before refueling. Do not fill tanks within 100 feet (30.48 meters) of any energized electrical equipment capable of producing sparks. Do not smoke or allow smoking or open flame within 100 feet (30.48 meters) of airplane or vehicle. Do not operate electronic equipment or electrical switches during the fueling or defueling procedure. Frequently check fuel for ice formation during cold weather operation. Sample fuel after each refueling and before the first flight of the day for any moisture or contaminates. Wait at least five minutes for any moisture and sediment to settle before flushing fuel drain valves. (2) Approved Fuels and Capacities (See Figure 1) WARNING: Service the fuel tanks with 100 (green) or 100LL (blue) minimum grade fuel only. The use of lower octane rated fuel can result in destruction of an engine the first time high power is applied. If the airplane is inadvertently serviced with the wrong grade of fuel, the fuel system must be completely drained, properly serviced, and the proper engine inspection completed. Engine inspection should be performed in accordance with the manufacturer's approved service instructions. (3) Refueling Procedure (a) Acquire necessary tools, equipment, and supplies. Description P/N or Spec. Supplier Purpose Fire Extinguisher (Type AB or ABC) - Any Source Extinguish fire in an emergency. Rubber Protective Cover - Any Source Protect finish of airplane. Fuel Sampler Cup Cirrus Design Inspect fuel for contaminates. WARNING: Place a fire extinguisher near the fuel tank to be serviced. (b) (c) (d) Ground fuel truck or cart to suitable earth ground. Connect ground wire from fuel service nozzle to engine exhaust pipe outlet. Place a rubber protective cover over upper portion of wing, around fuel tank filler. Page 4

5 Do not permit fuel nozzle to come in contact with bottom of fuel tanks. Keep fuel tanks full at all times to minimize condensation and moisture accumulation in tanks. In extreme humid areas the fuel should be checked frequently and drained of condensation to prevent potential problems. (e) Remove fuel cap and fill fuel tank to desired level. If fuel is going to be added to only one fuel tank, the tank being serviced should be filled to the same level as the other fuel tank. (f) (g) (h) (i) (j) (k) (l) (m) (n) Remove fuel service nozzle and install fuel cap. Move fire extinguisher, rubber protective cover and fuel service nozzle to remaining tank to be filled. Place rubber protective cover over remaining fuel tank filler. Remove fuel cap and fill fuel tank to desired level. Remove fuel service nozzle and install fuel cap. Remove rubber protective cover from fuel tank servicing area. Remove ground wire from engine exhaust pipe outlet. Disconnect fuel truck or cart from suitable earth ground. Put fire extinguisher away. (4) Airplane De-fueling - Siphoning Method (a) Acquire necessary tools and equipment. Fire Extinguisher (Type AB or ABC) - Any Source Extinguish fire in an emergency. Rubber Protective Cover - Any Source Protect finish of airplane. Fuel Drain Container - Any Source Drain old fuel into. Hand Operated Pump - Any Source Siphon fuel. Fuel Sampler Cup Cirrus Design Drain collector tanks and gascolator. Fuel Supply 100LL (Blue) 100 (Green) Any Source Fuel airplane. (b) (c) (d) (e) (f) (g) (h) (i) Position fuel drain container at fuel tank filler neck. Ground fuel drain container to exhaust pipe outlet and airplane to a suitable earth ground. Place a rubber protective cover over upper portion of wing around fuel tank servicing area. Remove filler cap. Remove all fuel using a hand operated siphoning pump. Install filler cap. Repeat for remaining fuel tank. To completely drain fuel system, use fuel sampler cup to remove all fuel and any contaminates from gascolator and collector tanks. (j) Fuel airplane. (Refer to ) (k) Inspect complete fuel system for any signs of leaks and service as required. Page 5

6 If fuel system is drained or a fuel tank is empty for any reason, air may enter the system. To ensure proper engine operation, ground run engine for several minutes on each fuel tank until air is removed. Refer to the Pilot s Operating Handbook before starting and operating engine. (l) Ground run engine to purge air from fuel system. (m) Reinspect complete fuel system for any signs of leaks and service as required. (5) Airplane De-fueling - Electric Fuel Pump Method (a) Acquire necessary tools and equipment. Fire Extinguisher (Type AB, or ABC) - Any Source Extinguish fire in an emergency. Fuel Drain Container - Any Source Drain old fuel into. Fuel Drain Hose (extension) - Any Source Drain fuel. Fuel Supply 100LL (Blue) 100 (Green) Any Source Fuel airplane. Fuel Sampler Cup Cirrus Design Drain collector tanks and gascolator. (b) (c) (d) (e) (f) (g) (h) Position fuel drain container at electric fuel pump, located aft of engine. Ground fuel drain container to exhaust pipe outlet and airplane to a suitable earth ground. Disconnect fuel supply hose at electric fuel pump. Attach an auxiliary fuel drain hose extension to end of existing fuel supply hose. Place opposing end of fuel drain hose extension into fuel drain container. Set fuel selector valve to tank to be drained. Remove filler cap. Never allow electric fuel pump to run dry. (i) Set electric fuel pump switch to ON position. ow fuel pump to operate until fuel tank is empty, then immediately set electric fuel pump switch to OFF position. (j) Install filler cap. (k) Repeat for remaining fuel tank. (l) To completely drain fuel system, use fuel sampler cup to remove all fuel and any contaminates from gascolator and collector tanks. (m) Remove auxiliary fuel drain hose extension. (n) Secure fuel supply hose to engine driven fuel pump. (o) Fuel airplane. (Refer to ) (p) Inspect complete fuel system for any signs of leaks and service as required. If fuel system is drained or a fuel tank is empty for any reason, air may enter the system. To ensure proper engine operation, ground run engine for several minutes on each fuel tank until air is removed. Refer to the Pilot s Operating Handbook before starting and operating engine. Page 6 (q) Ground run engine to purge air from fuel system.

7 (r) Reinspect complete fuel system for any signs of leaks and service as required. (6) Airplane De-fueling - Drain Valve Method The fastest and most efficient way to de-fuel the airplane is by removing the fuel drain valves. For maintenance practices pertinent to the fuel drain valves, see Chapter 28, Fuel. (Refer to 28-10) Page 7

8 B. Engine Oil System The Teledyne Continental IO-550-N engine uses a wet sump pressurized lubrication system with an 8 quart (7.57 L) capacity. A filler cap with integral dipstick is provided for determining the amount of oil in the crankcase. The oil level should be brought to full before each long flight. Never fly the airplane with less than 6 quarts of oil (5.7 Liters) in engine crankcase. Oil consumption tends to be higher during break-in periods on new engines. Under no circumstances should automotive oil be used, for such oils could cause engine damage. If oil system becomes contaminated, the complete oil system must be flushed and the oil cooler replaced. For the first 25 hours of operation (on a new or rebuilt engine) or until oil consumption stabilizes, use straight mineral oil conforming to SAE J1966. After oil consumption has stabilized, the mineral oil should be drained and an approved engine oil used. (Refer to ) Straight mineral oil conforming to MIL-C-6529 with a corrosion preventive compound added, can cause coking with extended use; therefore Cirrus Design does not recommend its use for break-in or post break-in. Oil conforming to MIL-P with a corrosion preventive compound added is recommended by TCM and Cirrus Design for indefinite storage. (Refer to 10-30) (1) Oil System Replenishing (a) Acquire necessary tools and equipment Description P/N or Spec. Supplier Purpose Aeroshell (R) W See Desc. Shell Australia Lubrication Aeroshell Oil W Aeroshell Oil 15W-50 Anti-Wear Formulation Aeroshell Oil W Aeroshell Oil 15W-50 Anti-Wear Formulation Aeroshell Oil W Plus See Desc. Shell Canada Ltd. Lubrication See Desc. Shell Oil Company Lubrication BP Aero Oil See Desc. BP Oil Corporation Lubrication Castrol Aero AD Oil See Desc. Castrol Lubrication Castrol Aero AD Oil See Desc. Castrol Ltd. (Australia) Lubrication Chevron Aero Oil See Desc. Chevron U.S.A. Inc. Lubrication Conoco Aero S See Desc. Continental Oil Lubrication Delta Avoil Oil See Desc. Delta Petroleum Co. Lubrication Exxon Aviation Oil EE Exxon Elite See Desc. Exxon Company, U.S.A. Lubrication Gulfpride Aviation AD See Desc. Gulf Oil Company Lubrication Mobil Aero Oil See Desc. Mobil Oil Company Lubrication Page 8

9 Description P/N or Spec. Supplier Purpose Pennzoil Aircraft Engine Oil See Desc. Pennzoil Company Lubrication Phillips 66 Aviation Oil Type A 100 AD, See Desc. 120 AD X/C Aviation Multi Viscosity Oil SAE 20W- 50, SAE 25W-60 Phillips Petroleum Company Quaker State AD Aviation Oil See Desc. Quaker State Oil & Refining Co. Red Ram X/C Aviation Oil 20W-50 See Desc. Red Ram Ltd. (Canada) Lubrication Lubrication Lubrication Sinclair Avoil See Desc. Sinclair Oil Company Lubrication Texaco Aircraft Engine Oil - Premium AD See Desc. Texaco Inc. Lubrication Total Aero DM 15W-50 See Desc. Total France Lubrication Turbonycoil 3570 See Desc. NYCO S.A. Lubrication Union Aircraft Engine Oil HD See Desc. Union Oil Company of California Lubrication (b) (c) Ensure airplane is sitting on a level surface with the engine off. Open access door on upper LH side of engine cowling. Ensure minimum oil quantity of 6 quarts (5.7 Liters). (d) Using filler cap dipstick, verify engine oil level. (e) Add approved oil as necessary. (f) Verify engine oil level and install filler cap. (g) Secure access door to engine cowling. (2) Changing Engine Oil and Filter (a) During periods of prolonged operation in dusty areas or in cold climates, or when flights have been of short duration with prolonged idling time, change oil and filter every 25 hours. Acquire necessary tools and equipment. Oil Filter Strap Wrench GA340 Snap-on Tools Kenosha, WI Remove oil filter. Oil Drain Pan - Any Source Drain used engine oil. Safety Wire, Inch MS20995 Any Source Secure fasteners. Safety Wire Pliers M-84 Genair Ltd. Tension safety wire. Flexible Oil Funnel - Any Source Replenish engine oil. Page 9

10 (b) Warm engine to operating temperatures prior to changing oil. (c) Remove engine cowling. (Refer to 71-10) (d) Position oil drain pan under drain plug. A flexible oil funnel may be used to aid draining process. (e) Serials 0002 thru 1820, 1822 thru 1839, 1841 thru 1862: Remove safety wire securing drain plug. Remove drain plug and allow oil to completely drain out. (f) Serials 1821, 1840, 1863 & subs: Open drain valve and allow oil to completely drain out. (g) Remove safety wire securing oil filter. (h) Remove oil filter from airplane. (i) Lubricate seal with oil and secure new filter. Torque filter to ft-lb ( Nm). (j) Safety wire oil filter. (k) Serials 0002 thru 1820, 1822 thru 1839, 1841 thru 1862: Install drain plug using a new gasket. Torque drain plug to 17 ft-lb (23 Nm) (l) Serials 0002 thru 1820, 1822 thru 1839, 1841 thru 1862: Safety wire drain plug. (Refer to 20-50) (m) Serials 1821, 1840, 1863 & subs: Close drain valve. (n) Replenish engine oil sump with approved oil. (Refer to ) (o) Using filler cap dipstick, verify engine oil level. (p) Install filler cap. (q) Install engine cowling. (Refer to 71-10) (r) Perform Inspection/Check - Oil System Leak. (Refer to ) (3) Inspection/Check - Oil System Leak If oil pressure is not present after 10 seconds of running time, shut the engine down immediately. (a) Start the engine in accordance with Pilot s Operating Handbook procedures and monitor the engine oil pressure gage for proper oil pressure. ow the engine to idle for a few minutes and shutdown the engine in accordance with POH procedures. (b) Remove engine cowling. (Refer to 71-10) (c) Visually inspect engine for any obvious leaks. Repair leaks immediately. (d) Verify engine oil level. Replenish as required. (e) Secure filler cap. (f) Install engine cowling. (Refer to 71-10) (4) Inspection/Check - Oil Filter Particles (a) Acquire necessary tools and equipment. Oil Filter Can Cutter CT-470 Champion Spark Plug Toledo, OH Inspecting oil filter element. Page 10 (b) (c) (d) Secure oil filter in a vise. Using a can cutter, secure cutter on filter mounting plate. Tighten knurled head screw until cutter blade meets metal can surface of filter. Rotate cutter 360 while observing that cutter blade is penetrating metal can portion of filter. Continue tightening knurled head screw and rotating cutter until filter mounting plate is free from canister.

11 (e) (f) Carefully remove element from canister. Cut filter material from end caps. Carefully unfold element and inspect for abnormal metal particles trapped in filter element. Page 11

12 C. Hydraulic Brake System The main wheels have hydraulically operated, single-cylinder dual piston type disc brakes, individually activated by floor mounted toe pedals at both pilot stations. A parking brake mechanism holds induced hydraulic pressure on the disc brake for parking. The brake reservoir is located on the right side of the firewall in the engine compartment. The brake system is filled with MIL-H-5606 hydraulic brake fluid. The fluid level should be checked periodically and at every inspection and replenished when necessary. If entire system must be filled, fill with fluid under pressure from brake end of system. This will eliminate air in system. If system is low, the reason for fluid loss must be determined before continued operation of the aircraft. For additional brake information refer to Chapter 32. (Refer to 32-42) WARNING: Never service the hydraulic reservoir while the parking brake is activated. Fluid in the wheel cylinders may be under high pressure due to expansion. Therefore, be sure parking brake is released and wheel chocks are in place, prior to beginning hydraulic system servicing. If the brake pedal feels spongy, the complete brake system must be bled. If the system is low, the reason for fluid loss, must be determined before continued operation of the airplane. Any spilled brake fluid must be removed immediately as it will damage any painted surface upon contact. Remove any dirt on the brake fluid reservoir filler cap before opening. (1) Brake Fluid Replenishing (a) Acquire necessary tools and equipment. Hydraulic Brake Fluid Type MIL-H-5606 Any Source Fill reservoir. Syringe - Any Source Remove hydraulic fluid. (b) Remove upper engine cowling. (Refer to 71-10) (c) Remove any dirt from hydraulic brake fluid reservoir before opening filler cap. (d) Remove filler cap and add hydraulic brake fluid to reservoir until full. (e) Use syringe to remove approximately 0.24 oz (7 ml) of hydraulic fluid from brake reservoir. (f) Install filler cap. (g) Inspect entire brake system for leakage or problems. (h) Install engine cowling. (Refer to 71-10) (2) Brake Fluid Draining (a) Acquire necessary tools, equipment, and supplies. Drain Pans - Any Source Fluid recovery. (b) (c) (d) Place drain pans under LH and RH brake bleeder fitting on brake assemblies. Remove bleeder caps and screws from bleeder fittings. Pump brake pedals to drain brake fluid from system. Page 12

13 D. Tires The nose tire uses a wheel with a 5.00 x 5, six-ply rated tire with tube. The main landing gear uses 15 x 6.00 X 6 wheels with 15 x , six-ply rated tires with tubes. Always keep tires inflated to the rated pressure to ensure maximum service and to reduce damage when landing on stones with sharp edges. When adjusting tire pressure, inspect the tires for any signs of abnormal wear, cuts, or bruises. If airplane tires should ever freeze to ground surface, use hot air or water to free tires before attempting to move airplane. For additional tire and wheel information refer to Chapter 32. (Refer to 32-41) (1) Tire Air Pressure Replenishing (a) Acquire necessary tools, equipment, and supplies. Compressed Air Supply - Any Source Adding air pressure to tires. Air Pressure Gage - Any Source Checking tire pressure. Wheel Chocks - Any Source Securing airplane. The following procedure must be performed in calm, warm weather, with the airplane sitting on a smooth and level surface. Always check air pressure using an accurate gage. Always consider load factor and ambient temperature when checking air pressure. Air pressure will increase when the tire is subjected to a load and when the temperature increases. Whenever an air pressure specification is called out, but not defined as loaded or unloaded, it should be considered as unloaded. Always service tires in a warm environment, this will keep the valve stem from freezing and eliminate the possibility of leaks through the valve core. After inspecting or adjusting tire pressure, always inspect valve core for leaks before reinstalling valve cap. Always install a valve cap to prevent contaminates from entering valve core. (b) Set parking brake and place wheel chocks into position. (c) Remove access plug from wheel pant. (d) Release parking brake and remove wheel chocks. (e) Move airplane until valve stem is accessible through wheel pant inspection hole. (f) Place wheel chocks into position. (g) Remove valve cap. (h) Using an accurate gage, verify tire pressure. (See Figure 1) (i) Add compressed air to tire as required to obtain recommended pressure. If tire is over inflated, push in on valve core and release air to obtain recommended pressure. (j) Inspect valve core for leaking. (k) Install valve cap. (l) Install access plug to wheel pant. (m) Reset parking brake and place wheel chocks into position. Page 13

14 E. Battery System Two batteries are used for power storage on the airplane. Battery 1 is located in the engine compartment and is the only battery requiring electrolyte maintenance. Battery 2 is located aft of bulkhead 222 and is considered a sealed, maintenance free battery. Visual inspection of battery 1 should be done every month or 25 flight hours until experience indicates a longer inspection interval. Check the battery, container, cover, and connections for distortion or damage. Proper battery charging procedures for both types of batteries, along with other pertinent information can be found in Chapter 24. (Refer to 24-30) WARNING: Always wear a face shield and remove all jewelry before servicing the battery. Metal objects may fuse to electrical connections and cause severe burns. Neutralize electrolyte spills with a solution of baking soda and water, then rinse with clean water. Do not add acid to battery unless electrolyte has been lost by spillage. When it is necessary to add acid, the battery should be fully charged, on charge, and gassing freely. Specific gravity may then be adjusted by adding acid or distilled water, or drawing off electrolyte. (1) Battery 1 Electrolyte Level Check (a) Remove battery 1. (Refer to 24-30) (b) Remove battery cell caps. (c) Visually inspect battery cells for proper electrolyte level. As an example, a warm battery condition would exist just after a bench charge or following a flight of ninety minutes or more. 1 If battery is warm and in a good state of charge, verify electrolyte level just touches or is slightly short of level indicator eyelet. 2 At all other times, verify electrolyte level is approximately 1/4 inch (6.4 mm) above the plates. (d) If a battery cell is low, add distilled water to obtain proper electrolyte level and charge battery to mix the electrolyte. (Refer to 24-30) (e) Perform Battery 1 Electrolyte Specific Gravity Check. (Refer to ) (f) Install battery cell caps. (g) Install battery 1. (Refer to 24-30) (2) Battery 1 Electrolyte Specific Gravity Check Electrolyte is a diluted solution of sulfuric acid and distilled water with a specific gravity of Pure distilled water has a specific gravity of and concentrated sulfuric acid has a specific gravity of The specific gravity of the electrolyte in a battery cell is a good index to the state of charge in the cell, due to the fact that as the battery is discharged, the acid in the electrolyte is used up. A specific gravity reading from to usually indicates a fully charged cell. If the reading is from to 1.260, the charge is considered low. It must be noted that the specific gravity reading is not always an indication of the state of charge in a cell. If electrolyte is removed from a discharged cell and replaced with an electrolyte of high specific gravity, the cell will still be in a discharged condition even though the hydrometer indicates a full charge reading. Page 14

15 Temperature must be considered when measuring specific gravity. Hydrometer readings will vary as the temperature goes above or below 80 F (26.70 C). The standard temperature used in rating lead acid battery performance is 77 F (25 C). (a) Acquire necessary tools and equipment. Hydrometer FR-1 Teledyne Continental Measure specific gravity. Small Plastic Syringe - Any Source Replenish electrolyte. Distilled Water - Any Source Replenish electrolyte. Bicarbonate of Soda (baking soda) - Any Source Neutralize electrolyte. Rubber Apron and Gloves - Any Source Prevent electrolyte exposure. Face Shield and Goggles - Any Source Prevent electrolyte exposure. (b) Remove battery 1. (Refer to 24-30) (c) Remove battery cell cap. If electrolyte level is too low for accurate hydrometer readings, add just enough distilled water to cover the plates. Charge battery to mix the electrolyte. Continue charging until the voltage and specific gravity readings are constant over three readings taken at 1/2 hour intervals. (d) (e) (f) Draw electrolyte into hydrometer. Verify specific gravity of electrolyte measures or above. Return electrolyte to same cell from which electrolyte was removed. To prevent contamination between cells, immediately install cell caps to original location after testing specific gravity. (g) Install battery cell cap. Adjust electrolyte level at the end of a charge because the level will rise from acid coming back into the electrolyte mix, normal gassing, and expansion from the temperature rise. (h) If necessary, adjust specific gravity of battery cell by adding distilled water or drawing off electrolyte. (i) Repeat for remaining battery cells. (j) Install battery 1. (Refer to 24-30) Page 15

16 F. Ice Protection System - Serials 0334 and subs w/ Optional Installation (1) De-Icing Fluid Replenishment Serials 0334 thru 2437: The de-icing fluid tank holds 2.96 gallons (11.2 L) and is serviced through a filler located on the LH side of the fuselage, just forward of the baggage door. Serials 2438 & subs: The de-icing fluid tank holds 3.75 gallons (14.2 L) and is serviced through a filler cap and neck located on the upper LH wing skin. To prevent de-icing fluid contamination, maintain a clean, dedicated measuring container and ensure mouth of fluid container is clean before dispensing. Secure the filler cap immediately after filling. (a) Acquire necessary tools, equipment, and supplies. Description P/N or Spec. Supplier Purpose Funnel - Any Source Replenishment aid. Measuring Container - Any Source Replenishment aid. Approved De-Icing Fluid DTD 406-B DW Davies & Company Racine, WI Replenish de-icing fluid tank. Only use approved de-icing fluids. (b) Dispense approved de-icing fluid into clean measuring container. (c) Remove filler cap. (d) Use funnel to fill fluid tank to desired level. (e) Install filler cap. (2) De-Icing Fluid Draining WARNING: If the Ice Protection System has been inadvertently filled with gasoline, ensure fire extinguisher is readily available before draining. If the Ice Protection System has been inadvertently filled with gasoline, the system filter must be replaced. (a) Acquire necessary tools, equipment, and supplies. Description P/N or Spec. Supplier Purpose 5 Gallon Container - Any Source Drain de-icing fluid into. Approved De-Icing Fluid DTD 406-B DW Davies & Company Racine, WI Replenish de-icing fluid tank. Page 16 (b) Serials 0334 thru 2437: Drain fluid from airplane. 1 Locate de-icing fluid drain on LH side of fuselage belly just forward of fluid tank and place container beneath drain. Serials 0334 and subs w/ Optional Installation

17 ow approximately 60 minutes to completely drain ice protection system. (c) 2 Remove safety wire and remove drain valve to allow non-approved fluid to drain into container. 3 Reinstall and safety wire drain valve. Serials 2438 & subs: Drain fluid from airplane. 1 Locate de-icing fluid drain on wing access panel LW2. (Refer to 06-00) ow approximately 60 minutes to completely drain ice protection system. 2 Using hex key, open drain valve to allow non-approved fluid to drain into container. 3 Using hex key, close drain valve. (3) Porous Panel Purging The following procedure provides instructions for purging the porous panels of contaminates, non-approved fluids, and air bubbles. If porous panels are not wetting out properly, perform the procedure once for each set of wing panels and once for the horizontal panels. (a) Acquire necessary tools, equipment, and supplies. Description P/N or Spec. Supplier Purpose TKS Cart TBD TBD Purge de-icing fluid from porous panel membranes. Approved De-Icing Fluid DTD 406-B DW Davies & Company Racine, WI Replenish de-icing fluid tank. Plastic Gutters and Buckets - Any Source Collect de-icing fluid during purge. 5 Gallon Buckets - Any Source Collect de-icing fluid during purge. High Density Sponge - Any Source Inspect de-icing fluid flow. (b) (c) (d) (e) Position a panel length plastic gutter below panel to collect de-icing fluid during purging process. Position empty 5 gallon bucket at lower end of gutter. Position TKS cart in front of wing to be purged. If purging horizontal panels, position TKS cart in front of empennage access panel RE3. (Refer to 06-00) Set up TKS cart. 1 Connect 5/16 inch line with equal tee to the 5/16 System Output port on TKS cart. 2 Remove access lid from TKS cart pressure vessel. 3 Fill pressure vessel 3/4 full with approved de-icing fluid. 4 Install access lid to pressure vessel, ensuring gasket is in position. 5 Rotate air regulator knob counterclockwise to adjust pressure to zero. Serials 0334 and subs w/ Optional Installation Page 17

18 Disconnect air source when making connections and repositioning TKS cart. (f) (g) (h) (i) (j) (k) 6 Connect air source to pressure vessel. Serials 0334 thru 2437: Connect TKS cart to wing porous panels. 1 Remove wing access panels LW6 and LW16 or RW6 and RW16. (Refer to 06-00) 2 Disconnect system supply line from porous panel inlet port. 3 Connect in-line pressure gauge to porous panel inlet port. 4 Connect TKS cart 5/16 inch supply line to in-line pressure gauge. 5 Repeat for remaining porous panel. Serials 2438 & subs: Connect TKS cart to wing porous panels. 1 Remove wing access panels LW4 and LW9 or RW4 and RW9. (Refer to 06-00) 2 Remove cable tie securing coupler assembly to wing. 3 Disconnect system supply line from coupler assembly. 4 Connect in-line pressure gauge to coupler assembly. 5 Connect TKS cart 5/16 inch supply line to in-line pressure gauge. 6 Repeat for remaining porous panel. Serials 0334 thru 2437: Connect TKS cart to horizontal porous panels. 1 Remove empennage access panel RE3. (Refer to 06-00) 2 Disconnect system supply line from horizontal proportioning unit inlet port. 3 Connect in-line pressure gauge to horizontal proportioning unit inlet port. 4 Connect TKS cart 5/16 inch supply line to in-line pressure gauge. Serials 2438 & subs: Connect TKS cart to horizontal porous panels. 1 Remove empennage access panel RE3. (Refer to 06-00) 2 Remove cable tie securing coupler assemblies to fuselage. 3 Disconnect system supply line from each coupler assembly. 4 Connect in-line pressure gauge to each coupler assembly. 5 Connect TKS cart 5/16 inch supply line to each in-line pressure gauge. Verify TKS cart control settings. 1 Set water regulator to CLOSED position. 2 Set air regulator to CLOSED position. 3 Set selector valve to TKS FLUID position. 4 Set output selector to 5/16 position. 5 Set feed valve position to DOWN - SINGLE FEED position. Initiate fluid flow. Ensure pressure does not exceed 150 psi (1034 kpa). Do not allow pressure vessel to run dry. If vessel runs dry, isolate and purge panel individually at 70 psi (483 kpa) or higher for at least 10 minutes. 1 At each pressure gauge, open shutoff valve. 2 Rotate air regulator knob clockwise to increase pressure by 5 psi (34.5 kpa) every 5 seconds up to 60 psi (414 kpa). If unable to obtain minimum required pressure on both panels, isolate and purge one panel at a time. Page 18 Serials 0334 and subs w/ Optional Installation

19 (l) 3 Continue to adjust air pressure on TKS cart until each in-line pressure gauge indicates at least 60 psi for wing panels and 65 psi for horizontal panels. 4 Start timer. Inspect de-icing fluid flow from porous panel. 1 Wipe leading edge with high density sponge as flow becomes evident. 2 Inspect flow distribution along entire active area of porous panel. 3 ow panel to flow a minimum of 5 minutes and for as long as 15 minutes. It is permissible to have a dry area no larger than two rows by two inches (5 cm) long. (m) 4 Inspect porous panel for consistent and even distribution along entire length of leading edge, ensuring all laser-drilled holes are wetting out. 5 Visually inspect porous panel surface to verify that air is being purged in the form of very small air bubbles. As the membrane becomes saturated, the frequency of bubbles will reduce dramatically. Observe initial frequency of air bubbles, and verify that the frequency is drastically reduced or eliminated before 15 minutes has elapsed. For wing porous panels: Porous panel flow is adequate if flow of each panel is consistent along entire length of panel, and purging of air bubbles is drastically reduced by the time 15 minutes has elapsed. If wing porous panel flow is inadequate, perform the following procedure. 1 Isolate porous panel by using a shutoff valve to open and close lines as needed. 2 Fill pressure vessel 1/2 full with approved de-icing fluid. Ensure pressure does not exceed 150 psi (1034 kpa). Do not allow pressure vessel to run dry. If vessel runs dry, isolate and purge panel individually at 70 psi (483 kpa) or higher for at least 10 minutes. (n) (o) 3 Rotate air regulator knob clockwise to increase pressure by 5 psi (34.5 kpa) every 5 seconds up to 70 psi (483 kpa). 4 Continue to adjust air pressure on TKS cart until in-line pressure gauge indicates at least 70 psi (483 kpa). 5 Start timer. 6 Inspect de-icing fluid flow from porous panel as described above. (Refer to ) 7 If flow is still inadequate, replace the porous panel. (Refer to 30-10) For horizontal porous panels: Porous panel flow is adequate if flow of each panel is consistent along entire length of panel, and purging of air bubbles is drastically reduced by the time 15 minutes has elapsed. If horizontal porous panel flow is inadequate, replace the porous panel. (Refer to 30-10) Shutdown TKS cart. 1 At each pressure gauge, close shutoff valve. 2 Rotate air regulator knob counterclockwise to close. 3 Pull up on pressure vessel safety valve to relieve pressure. 4 Disconnect air source from TKS cart. Use fresh de-icing fluid if there is evidence of contamination. 5 Replenish pressure vessel with de-icing fluid collected from 5 gallon buckets. Serials 0334 and subs w/ Optional Installation Page 19

20 (p) Serials 0334 thru 2437: Disconnect TKS cart from wing porous panels. 1 Disconnect in-line pressure gauge from porous panel inlet port. 2 Connect system supply line to porous panel inlet port. 3 Repeat for remaining porous panel. 4 Install wing access panels LW6 and LW16 or RW6 and RW16. (Refer to 06-00) (q) Serials 2438 & subs: Disconnect TKS cart from wing porous panels. 1 Disconnect in-line pressure gauge from coupler assembly. 2 Connect system supply line to coupler assembly. 3 Position coupler assembly to wing with service loop and secure with cable tie. 4 Repeat for remaining porous panel. 5 Install wing access panels LW4 and LW9 or RW4 and RW9. (Refer to 06-00) (r) Serials 0334 thru 2437: Disconnect TKS cart from horizontal porous panels. 1 Disconnect in-line pressure gauge from horizontal proportioning unit inlet port. 2 Connect system supply line to horizontal proportioning unit inlet port. 3 Install empennage access panel RE3. (Refer to 06-00) (s) Serials 2438 & subs: Disconnect TKS cart from horizontal porous panels. 1 Disconnect in-line pressure gauge from each coupler assembly. 2 Connect system supply line to each coupler assembly. 3 Position coupler assemblies to fuselage and secure with cable tie. 4 Install empennage access panel RE3. (Refer to 06-00) (t) Relocate TKS cart and repeat procedure for remaining panels. (u) Fill fluid tank with approved de-icing fluid. (Refer to ) (v) Perform Operational Test - Ice Protection System. (Refer to 30-05) Page 20 Serials 0334 and subs w/ Optional Installation

21 G. Air Conditioning System - Serials 1602, 1821, 1840, 1863 and subs w/ Optional Installation (1) Inspection/Check - Refrigerant Level Check refrigerant level when ambient temperature is above 65 F. (a) Start engine. (Refer to Pilot s Operating Handbook, Section 4) (b) Set air conditioning switch to ON position. (c) Run air conditioning system for at least 5 minutes. If outlet measures considerably cooler, the receiver/drier may be plugged and may require replacement. (d) Verify temperature at receiver/drier inlet equals temperature at receiver/drier outlet. (e) Verify sight glass is free of bubbles. (f) Set air conditioning switch to OFF position. (g) Shut down engine. (Refer to Pilot s Operating Handbook, Section 4) (h) Adjust refrigerant level as necessary. (2) Refrigerant Recharging (a) Acquire necessary tools, equipment, and supplies. R134a Compatible Recovery/Recycling/ Recharging Unit - Any Source Recharge refrigerant. Compressor Oil (See Figure ) Any Source Replenish compressor oil. (b) Set BAT 1, BAT 2, and AVIONICS switches to OFF positions. (c) Pull COMPRESSOR/CONTROL PANEL circuit breaker. (d) Pull EVAPORATOR FAN circuit breaker. (e) Pull CONDENSER circuit breaker. (f) Remove RH sidewall air duct trim. (Refer to 25-10) (g) Empty oil drain bottle on recharging unit. (h) At RH crew seat, remove caps from air conditioning service ports. (i) Connect recharging unit pressure hoses to service ports. (j) Open coupler valves on pressure hoses. Operate recharging unit in accordance with manufacturer s instructions. (k) Recover refrigerant from system. Note the amount of oil collected in drain bottle during recovery. The same amount of oil must be added to system during recharging. (l) (m) (n) Record amount of oil collected in drain bottle during recovery. Evacuate system for at least 15 minutes to remove any air, moisture, or contaminants. Perform recharging unit automated leak check. Serials 1602, 1821, 1840, 1863 and subs w/ Optional Installation Page 21

22 Add the same amount of oil to system as was removed during recovery. Polyester oil and polyalkyline glycol oil are not interchangeable. Verify compressor part number to determine which oil type to use. (See Figure ) (o) Replenish system with same amount of oil as removed during recovery. To ensure a full charge is delivered, the recharging unit must be set to deliver slightly more than the recommended 2.0 lb (0.91 kg) to account for refrigerant that stays in the recharging unit lines. Consult manufacturer s instructions to determine specifics for the recharging unit being used. (p) Recharge system with 2.0 lb (0.91 kg) of R134a refrigerant. (q) Perform Inspection/Check - Refrigerant Leak Test. (Refer to ) (r) Close coupler valves on pressure hoses. (s) Disconnect recharging unit pressure hoses from service ports. (t) Cap air conditioning system service ports. (u) Install RH sidewall air duct trim. (Refer to 25-10) (v) Reset CONDENSER circuit breaker. (w) Reset EVAPORATOR FAN circuit breaker. (x) Reset COMPRESSOR/CONTROL PANEL circuit breaker. (3) Refrigerant Discharging (a) Acquire necessary tools, equipment, and supplies. R134a Compatible Recovery/Recycling/ Recharging Unit - Any Source Remove refrigerant. (b) Set BAT 1, BAT 2, and AVIONICS switches to OFF positions. (c) Pull COMPRESSOR/CONTROL PANEL circuit breaker. (d) Pull EVAPORATOR FAN circuit breaker. (e) Pull CONDENSER circuit breaker. (f) Empty oil drain bottle on recovery unit. (g) Remove RH sidewall air duct trim. (Refer to 25-10) (h) At RH crew seat, remove caps from air conditioning system service ports. (i) Connect recovery unit pressure hoses to service ports. (j) Open coupler valves on pressure hoses. (k) Recover refrigerant from system. Note the amount of oil collected in drain bottle during recovery. The same amount of oil must be added to system during recharging. (l) Record amount of oil collected in drain bottle during recovery. (m) Close coupler valves on pressure hoses. (n) Disconnect recovery unit pressure hoses from service ports. (o) Cap air conditioning system service ports. (4) Inspection/Check - Refrigerant Leak Test Page 22 Serials 1602, 1821, 1840, 1863 and subs w/ Optional Installation

23 (a) Perform Inspection/Check - Refrigerant Leak Test when ambient temperature is above 65 F. Acquire necessary tools, equipment, and supplies. (b) (c) Refrigerant Detector - Any Source Detect leaks. Set BAT 1, BAT 2, and AVIONICS switches to OFF positions. Pull COMPRESSOR/CONTROL PANEL, EVAPORATOR FAN, and CONDENSER circuit breakers. (d) Remove engine cowling. (Refer to 71-10) (e) Remove RH crew seat. (Refer to 25-10) (f) Remove RH sidewall air duct trim. (Refer to 25-10) (g) Remove RH rear cabin side trim. (Refer to 25-10) (h) Remove floor access panel CF5. (Refer to 06-00) (i) Using electronic refrigerant detector, check all plumbing connections and components for leaks. (j) If leak is detected, perform the following: 1 Discharge air conditioning system. (Refer to ) 2 Repair or replace components and plumbing as needed. Ensure oil from leak is cleaned up and any residual refrigerant has dissipated prior to recharging air conditioning system. 3 Charge air conditioning system. (Refer to ) 4 Repeat leak check. (k) Install floor access panel CF5. (Refer to 06-00) (l) Install RH rear cabin side trim. (Refer to 25-10) (m) Install RH sidewall air duct trim. (Refer to 25-10) (n) Install RH crew seat. (Refer to 25-10) (o) Install engine cowling. (Refer to 71-10) (5) Air Conditioning System Flushing If any air conditioning component has been disconnected and exposed to air for an extended period of time, an unapproved compressor oil has been added to the system, or if replacement compressor uses a different oil type than the previously installed compressor, perform the following procedure to flush the air conditioning system. (a) Acquire necessary tools, equipment, and supplies. Receiver/Dryer Test Fitting TBD Cirrus Design Duluth, MN Flush air conditioning system. Open Expansion Valve Test Fitting TBD Cirrus Design Duluth, MN Flush air conditioning system. Serials 1602, 1821, 1840, 1863 and subs w/ Optional Installation Page 23

24 Flushing Pump - Any Source Flush air conditioning system. Flushing Container - Any Source Flush air conditioning system. Isopropyl Alcohol TT-I-735 Grade A or B Any Source Flush air conditioning system. Compressor Oil (See Figure ) Any Source Lubricate O-rings. (b) Discharge air conditioning system. (Refer to ) Before disconnecting plumbing, ensure vacuum in system is minimal or the O-rings could be pulled into the system. (c) Disconnect expansion valve from evaporator. Discard O-rings. (d) Connect open expansion valve test fitting to evaporator. (e) Disconnect receiver/drier from condenser. Discard O-rings. (f) Connect receiver/drier test fitting to condenser. (g) Disconnect high and low pressure hoses from compressor. Discard O-rings. (h) Cap expansion valve, receiver/drier, and compressor fittings. (i) Connect high pressure hose to flushing pump. (j) Insert low hose into flushing container. (k) Pump 3 to 4 quarts of isopropyl alcohol through system. (l) Disconnect flushing pump. (m) Using dry nitrogen or dry air with regulator set to 25 to 30 PSI, blow through system for 5 minutes to evaporate remaining alcohol. (n) Remove caps from expansion valve, receiver/drier, and compressor fittings. Polyester oil and polyalkyline glycol oil are not interchangeable. Verify compressor part number to determine which oil type to use. (See Figure ) (o) Lubricate new O-rings with compressor oil. (p) Connect low pressure hose to compressor. Torque hose and fittings to 180 to 240 in-lb ( Nm). (q) Connect high pressure hose to compressor. Torque hose and fittings to 120 to 160 in-lb ( Nm). (r) Disconnect receiver/drier test fitting from condenser. (s) Connect receiver/drier to condenser. Torque fittings to 120 to 160 in-lb ( Nm). (t) Disconnect open expansion valve test fitting from evaporator. (u) Connect expansion valve to evaporator. (v) Charge air conditioning system. (Refer to ) Page 24 Serials 1602, 1821, 1840, 1863 and subs w/ Optional Installation