CIRRUS AMM TEMPORARY REVISION MODEL SF50 SF50 AMM Temporary Revision --01 Brakes Affected Manuals: SF50 Airplane Maintenance Manual (18-001, Revision 1) Serial Numbers: SF50 Serials 0005 & subs Filing Instructions: Insert this temporary revision at the beginning of Chapter, Section in the SF50 Airplane Maintenance Manual; retain until further notice. Purpose: Update Brake Bleeding procedure and add Adjustment/Test - Brake System Pressure Test. This temporary revision, dated, adds, supersedes, or deletes information in the SF50 Airplane Maintenance Manual and is valid until further notice. This temporary revision replaces pages 1 thru, and 15 thru 0 of Chapter, Section of the affected manual. Pages that change due to the subject AMM Temporary Revision are dated and changed content is marked with a revision bar. FAA approval has been obtained on all technical data in these instructions that affect type design. 50AMM_TR_--01 Page 1 of
CIRRUS AMM TEMPORARY REVISION MODEL SF50 Intentionally Left Blank Page of 50AMM_TR_--01
CIRRUS AIRPLANE MAINTENANCE MANUAL Brakes CHAPTER -: BRAKES GENERAL -: BRAKES 1. General This chapter describes that portion of the system which provides for stopping the aircraft while on the ground and taxiing/directional control of the aircraft. Includes items such as the hydraulic brake fluid system, brake calipers, discs, and pad assemblies. The brake system consists of an aluminum brake assembly on each main landing gear with single steel disc and two sintered (metal/ceramic) brake pads, master cylinder for each rudder pedal, hydraulic fluid reservoir, parking brake, and associated hydraulic tubing and hoses. The hydraulically operated brakes are individually activated by floor mounted toe pedals located at both pilot stations. The master cylinders are located forward of the each rudder pedal. The hydraulic fluid reservoir is located in the nose compartment on the upper RH side of FS 7.5. The reservoir is serviced with MIL-PRF-8757 hydraulic fluid. A parking brake mechanism holds induced hydraulic pressure on the disc brakes for parking. The parking brake system consists of a parking brake valve, control cable with handle, indication switch, and associated hydraulic tubing and hoses. The parking brake valve is mounted to the forward cabin skin, outboard of the pilot rudder pedals. The parking brake control cable handle is mounted to the LH console rib on the pilot-side under GTC#1. A position sensor, mounted adjacent to the parking brake valve actuation arm, sends position data to the MFD via the GEA 71 engine airframe unit. An alert indicates in the CAS window of the MFD when the parking brake is set. 1 9 Jul 018 50AMM_TR_--01
CHAPTER -: BRAKES TROUBLESHOOTING. Troubleshooting CIRRUS AIRPLANE MAINTENANCE MANUAL Trouble Probable Cause Remedy Brakes won t hold. Improper conditioning of brake pads and disc. Brake fluid or grease on disc and pads. Wrong brake fluid has caused blocking of pistons. Pads worn below minimum wear limits Perform Adjustment/Test - Conditioning Procedure for Brake Pads. (Refer to -) Clean the disc and change the pads. (Refer to -) Change all seals of the brake system. Use correct brake fluid. (Refer to 1-10) Change brake pads. (Refer to -) Excessive toe pedal travel, spongy pedal. Air in brake system. Bleed brake system. (Refer to -) Leak in the system. Perform Adjustment/Test - Brake Pressure Test to locate leak. (Refer to -) Loosen and re-torque leaking fitting using system fluid as lubricant. Replace leaking fitting washers. Replace leaking fitting. Replace brake line or component. Caliper assembly bolts are not tight. Torque bolts to proper value. Perform Adjustment/Test - Brake Pressure Test (Refer to -) Defective seal in master cylinder or contamination in fluid. Replace master cylinder or inspect the brake reservoir for contamination. (Refer to -) 50AMM_TR_--01
CIRRUS AIRPLANE MAINTENANCE MANUAL CHAPTER -: BRAKES TROUBLESHOOTING Trouble Probable Cause Remedy Brake drag. Rapid disc and pads wear. Residual brake pressure due to excessive pressure in the reservoir. Wrong brake fluid has caused blocking of pistons. Pistons do not retract. Pads are blocked and do not release. Improper conditioning of pads and disc. Inspect for correct venting. Change all seals of the brake system. Use correct brake fluid. (Refer to 1-10) Check vent/return port in the master cylinder. Inspect and repair. Perform Adjustment/Test - Conditioning Procedure for Brake Pads. (Refer to -) Excessive rusting, scoring or pitting or large pad deposits on brake disc that is evident with tactile inspection of brake disc. Repair or replace the disc and pads. (Refer to -) (Refer to -) Small pieces of pad frictional material damaged or missing at edges. Large portions of pad frictional material damaged or missing Typical condition of pads during use. Pads worn below minimum wear limits. Pads overheated (RTO, high-airspeed landings, or improper taxiing technique.) Inspect pad wear at each pre-flight, see AFM. Change brake pads. (Refer to -) Change brake pads. (Refer to -) 50AMM_TR_--01
CHAPTER -: BRAKES. Maintenance Practices CIRRUS AIRPLANE MAINTENANCE MANUAL A. Brake System Replenishing (Refer to 1-10) B. Brake Assembly (See Figure --1) (1) Inspection/Check - Brake Assembly (a) (b) (c) (d) (e) Wipe off any debris from brake caliper assembly that may obstruct inspection. Check brake pad assemblies and discs for deterioration and maximum permissible wear. Ensure none of the following conditions exist. If damage is identified during inspection, brake cylinder and/or back plate must be replaced. 1 Signs of deep corrosion, Anodizing color removed on more than 15% of external surface, Heavy nicks, Anodizing removed on internal piston bore, 5 Scratched piston bore, and 6 Scratched or damaged seal groove. Anodizing coating must not be painted. Do not use sandpaper on any parts. Sandpaper will remove anodizing coating. Do not try to sand or polish internal piston bore, it will remove anodizing coating. See manufacturer s approved Instructions For Continued Airworthiness for more information regarding brake pad and brake disc wear limits. (Refer to 5-00) Verify brake pad assembly frictional material minimum thickness is not less than 0.00 inch (1 mm). Verify brake disc minimum thickness is not less than 0. inch (11 mm). 1 Dec 016 50AMM_TR_--01
CIRRUS AIRPLANE MAINTENANCE MANUAL CHAPTER -: BRAKES (d) Uncap fitting and connect brake hose to bulkhead fitting at Main Landing Gear rib, WS 51. (e) Perform Adjustment/Test - Bleeding the Brake System. (Refer to -) 15 9 Jul 018 50AMM_TR_--01
CHAPTER -: BRAKES CIRRUS AIRPLANE MAINTENANCE MANUAL Figure --1: Brake Assembly A 1 TRUNNION (REF) 18 10 5 17 16 15 1 1 1 1 11 DETAIL 10 A 5 9 5 6 7 8 LEGEND 1. Stand off. Clamp. Bolt. Nut 5. Washer 6. Brake Hose 7. Fitting 8. Cylinder 9. Screw, Bleeder 10. O-Ring 11. Piston 1. Brake Pad 1. Brake Disc 1. Cotter Pin 15. Back Stop 16. Back Plate 17. Screw 18. Spacer SF50_MM_0156A 16 50AMM_TR_--01
CIRRUS AIRPLANE MAINTENANCE MANUAL CHAPTER -: BRAKES F. Brake Master Cylinder (See Figure --) (1) Removal - Brake Master Cylinder (a) (b) (c) Remove bolts and washers securing brake line hoses from master cylinders. Plug hoses and cap master cylinder fittings. Remove bolts, washers, nuts, and cotter pins securing master cylinders from rudder pedal idler linkage. Remove bolts, washers, spacers, and nuts securing master cylinders to fuselage attach brackets. () Installation - Brake Master Cylinder (a) (b) (c) Place master cylinders on floorboard mounting points, install bolts and secure with washers, spacers, nuts, and cotter pins. NOTE For pilot-side master cylinders: Inlet is connected to co-pilot master cylinders. Outlet is connected to parking brake valve. For co-pilot side master cylinders: Inlet is connected to brake reservoir. Outlet is connected to pilot-side master cylinders. Install LH and RH brake hoses per marked labels. Install bolts and new washers securing brake hoses to master cylinders. Torque bolts 11-155 in-lb (15.9-17.5Nm). (Refer to 0-60) Connect piston rod to upper connection at rudder pedals and install bolts, washers, and nuts. (d) Perform Adjustment/Test - Bleeding the Brake System. (Refer to -) 17 50AMM_TR_--01
CHAPTER -: BRAKES CIRRUS AIRPLANE MAINTENANCE MANUAL G. Parking Brake Valve (See Figure --) (1) Removal - Parking Brake Valve (a) Remove LH valence trim. (Refer to 5-10) (b) Remove LH crew seat. (Refer to 5-10) (c) (d) (e) Disconnect brake lines and hoses. 1 Disconnect brake lines from parking brake valve. Cap or plug ports and lines. Remove bolts and washers securing master cylinder hoses from parking brake valve. Cap or plug ports and hoses. Remove cotter pin, washers, and clevis pin securing control cable to parking brake valve actuation arm. Remove bolts, washers, and nuts securing parking brake valve to forward cabin skin. Remove parking brake valve from airplane. () Installation - Parking Brake Valve (a) (b) (c) (d) (e) (f) Position parking brake valve to outboard console rib with actuation arm adjacent to firewall and brake line fittings oriented towards fuselage floor. Secure with bolts, washers, and nuts. Remove caps from ports, lines, and hoses. Connect LH brake line to LH outlet on parking brake valve. Connect RH brake line to RH outlet on parking brake valve. Do not cross LH and RH brake hoses. Connect master cylinder brake hoses. 1 Install bolts and new washers securing LH master cylinders brake hose to LH inlet on parking brake valve. Torque bolts 18 in-lb (16.7 Nm). (Refer to 0-60) Install bolts and new washers securing RH master cylinders brake hose to RH inlet on parking brake valve. Torque bolts 18 in-lb (16.7 Nm). (Refer to 0-60) Install clevis pin, washers, and cotter pin securing control cable to parking brake valve actuation arm. 18 50AMM_TR_--01
CIRRUS AIRPLANE MAINTENANCE MANUAL CHAPTER -: BRAKES (g) Perform Inspection/Check - Parking Brake Control Cable. (Refer to -) (h) Bleed brake system. (Refer to -) (i) Install LH valence trim. (Refer to 5-10) (j) Install LH crew seat. (Refer to 5-10) H. Parking Brake Control Cable (See Figure --) (1) Removal - Parking Brake Control Cable (a) Remove LH crew seat. (Refer to 5-10) (b) Remove LH valence trim. (Refer to 5-10) (c) (d) (e) (f) Remove cotter pin, washers, and clevis pin securing control cable to parking brake actuation arm. Remove bolt, washer, and clamp securing control cable to forward cabin skin, console rib, and handle mounting bracket. Remove nut and washer securing control cable handle to bolster panel mounting bracket. Remove control cable carefully, ensuring cable does not interfere with any flight controls, brake hoses, or wiring. NOTE Note routing of control cable prior to removal to facilitate re-installation. Pull control cable through installation hole in bolster panel mounting bracket. Remove control cable from airplane. () Installation - Parking Brake Control Cable (a) Acquire necessary tools, equipment, and supplies. Description P/N or Spec. Supplier Purpose Threadlocker Loctite Any Source Lock threads. 19 50AMM_TR_--01
CHAPTER -: BRAKES CIRRUS AIRPLANE MAINTENANCE MANUAL (b) (c) (d) (e) (f) (g) (h) (i) (j) Route control cable through installation hole in bolster panel mounting bracket and secure with washer and nut. Verify control cable does not interfere with or rub against any flight controls, brake hoses, or wiring. Route control cable through oval clearance hole, across pressure bulkhead, under outboard console rib, and over to parking brake valve. 1 From outboard console rib, route control cable above protruding electrical bulkhead fittings and down to parking brake valve. Install clevis pin and washers through parking brake valve actuation arm. Secure control cable to parking brake valve actuation arm by wrapping control cable 1.5 turns around clevis pin. Install cotter pin securing control cable to parking brake valve actuation arm. Install cable stop. 1 Place parking brake valve actuation arm in OFF position. Apply threadlocker to threads of cable stop installation screw. (Refer to 0-0) Position cable stop with 1.8 inches (.6 cm) of cable wire visible between end of cable sheath and top of cable stop. Install screw securing cable stop to control cable wire. Install bolt, washer, and clamp securing control cable to firewall. Do not tighten bolt. With parking brake control handle in OFF position, push cable sheath down so that parking brake valve is in OFF position. Tighten bolt securing control cable and clamp to firewall. Install standoffs and clamps securing control cable to firewall. (k) Install LH valence trim. (Refer to 5-10) (l) Install LH crew seat. (Refer to 5-10) () Adjustment/Test - Parking Brake Control Cable (a) (b) (c) (d) Remove bolts, washers, and clamps securing control cable to forward cabin skin, console rib, and handle mounting bracket. Loosen set-screw securing cable stop to cable. Push cable handle completely in (OFF position). Set parking brake valve arm with stop against mounting bracket. 0 50AMM_TR_--01
CIRRUS AIRPLANE MAINTENANCE MANUAL CHAPTER -: BRAKES (e) (f) (g) Install clamps, washers, and bolts securing control cable to forward cabin skin, console rib, and handle mounting bracket. Pull cable handle completely out until valve arm reaches parking brake sensor (SET Position). Adjust cable stop to contact end of cable sheath and secure set-screw. (h) Perform Inspection/Test - Parking Brake Control Cable. (Refer to -) () Inspection/Check - Parking Brake Control Cable (a) Remove LH crew seat. (Refer to 5-10) (b) Remove LH valence trim. (Refer to 5-10) (c) Push parking brake handle completely in (OFF position). (d) Verify parking brake arm stop contacts valve mounting bracket. If not, perform Adjustment/Test - Parking Brake Control Cable. (Refer to -) (e) Verify Parking Brake SET CAS is not present on PFD and/or Parking Brake OFF is indicated on Landing Gear synoptic page of EIS. (f) Pull parking brake handle completely to stop (SET position). (g) Verify parking brake arm reaches sensor and cable stop reaches the end of the cable sheath. If not, perform Adjustment/Test - Parking Brake Control Cable. (Refer to -) (h) Verify Parking Brake SET CAS is present on PFD and/or Parking Brake SET is indicated on Landing Gear synoptic page of EIS. (i) Install LH valence trim. (Refer to 5-10) (j) Install LH crew seat. (Refer to 5-10) 1 50AMM_TR_--01
CHAPTER -: BRAKES Figure --: Cabin Brake System (1 of ) CIRRUS AIRPLANE MAINTENANCE MANUAL RUDDER PEDAL IDLER LINKAGE (REF) 9 10 6 8 7 8 1 6 7 A FUSELAGE FLOOR (REF) 6 5 DETAIL A LEGEND 1. Brake Master Cylinder. Spacer. Bolt. Washer 5. Bracket 6. Nut 7. Cotter Pin 8. Brake Line Assembly 9. Elbow Fitting 10. Union B SF50_MM_0157 9 Jul 018 50AMM_TR_--01
CIRRUS AIRPLANE MAINTENANCE MANUAL CHAPTER -: BRAKES Figure --: Cabin Brake System ( of ) 1 1 7 1 19 1 1 1 18 1 15 5 6 1 17 16 1 1 1 FWD CONSOLE (REF) 8 BRAKE HANDLE MOUNT (REF) 1 8 6 11 1 DETAIL 6 B LEGEND. Spacer. Bolt. Washer 5. Bracket 6. Nut 7. Cotter Pin 8. Brake Line Assembly 11. Parking Brake Cable Assembly 1. Clamp 1. Stand off 1. Screw 15. Parking Brake Sensor 16. Parking Brake Valve 17. Clevis Pin 18. Actuation Arm 19. Cable Stop SF50_MM_006A 9 Jul 018 50AMM_TR_--01
CHAPTER -: BRAKES CIRRUS AIRPLANE MAINTENANCE MANUAL I. Bleeding the Brake System (See Figure --) If a brake line has been disconnected or the brake pedal has a spongy feel, there is a strong likelihood that air has entered the brake system. To ensure proper braking, all trapped air must be removed from the brake system. If brake fluid contaminates the disc, it must be completely cleaned with solvent. Do not apply solvent directly to the brake caliper. Solvent will damage seals. If brake fluid contaminates the brake pads, they must be replaced. The pads are porous and cannot be adequately cleaned with solvent. (1) Adjustment/Test - Bleeding the Brake System (a) Acquire necessary tools, equipment, and supplies. Description P/N or Spec. Supplier Purpose Wheel Chocks WCK1001 Cirrus Design Block wheels. Hydraulic Fluid MIL-PRF-8757 Any Source Replenish brake system. Pressurized Brake Bleeder 700 (or equivalent) Ammco Tools Pressurize brake system. Tubing - Any Source Drain brake fluid. Syringe - Any Source Add/remove brake fluid. Hose Clamps - Any Source Secure tubing to fittings. Container, one gallon Container, one quart - Any Source Contain overflow. - Any Source Contain overflow. (b) (c) (d) Place wheel chocks into position. Disengage parking brake. Verify pressure on both gauges reads zero before opening tank. Fluid may spray out if there is residual pressure in the system. 50AMM_TR_--01
CIRRUS AIRPLANE MAINTENANCE MANUAL CHAPTER -: BRAKES (e) (f) (g) (h) (i) (j) (k) (l) Verify there is sufficient hydraulic fluid in tank. Refill if less than one gallon of fluid is left with either new or recycled fluid. Filter fluid and follow procedure on tank. Verify valve on feed tubing is closed and pressure regulator is turned to zero (fully counter-clockwise). Connect an air source to the hydraulic tank. Slowly pressurize tank by adjusting regulator until pressure reaches 10 PSI. Place opposite end of feed tube in to empty gallon container. Open valve on feed tube and allow system to flow until all air has been purged, and then close valve. Remove and retain plastic plug from top of brake reservoir. Temporarily install 1/8" NPT fitting and feed tubing to reservoir. Connect overflow tubing to flared end of bleeder valves on both brake calipers. Place opposite tubing ends in empty gallon container. (m) Loosen both bleeder valves one turn. (n) Verify parking brake is off. (o) Slowly increase tank pressure by adjusting regulator until both gauges reach 5 to 0 psi. (p) Open feed valve from hydraulic tank to tubing attached to reservoir. (q) Verify there are no leaks in system. Address any leaks in system before continuing brake bleeding procedure. (r) (s) (t) (u) NOTE It is acceptable if fluid at the calipers is not yet clear of bubbles. Ensure end of RH overflow tubing is completely submerged in fluid. For approximately 1 to minutes, allow fluid to flow until feed tube is clear of bubbles and there is fluid flowing out of overflow tubing attached to both calipers. Move tubing as necessary to push air through system. Caliper may be damaged if bleeder is over tightened. Close bleeder valve on left side. Leave bleeder valve on right side open one turn. Fully depress, then slowly release RH pedal on co-pilot side times. Fully depress, then slowly release RH pedal on pilot side times. 5 50AMM_TR_--01
CHAPTER -: BRAKES CIRRUS AIRPLANE MAINTENANCE MANUAL (v) (w) (x) (y) (z) (aa) Purge air from RH caliper. 1 Fully depress and hold RH pedal on co-pilot side. Close RH bleeder valve, then slowly release RH pedal on co-pilot side. Open RH bleeder valve. Fully depress and hold RH pedal on pilot side. Close RH bleeder valve, then slowly release RH pedal on pilot side. Open RH bleeder valve. Repeat RH caliper air purge at least times. Verify fluid flowing out of tubing attached to RH caliper is clear of bubbles before continuing procedure. Caliper may be damaged if bleeder is over tightened. Ensure end of LH overflow tubing is completely submerged in fluid. Close bleeder valve on RH side. Leave bleeder valve on LH side open one turn. Fully depress, and then slowly release LH pedal on co-pilot side times. Fully depress, and then slowly release LH pedal on pilot side times. Purge air from LH caliper. 1 Fully depress and hold LH pedal on co-pilot side. Close LH bleeder valve, then slowly release LH pedal on co-pilot side. Open LH bleeder valve. Fully depress and hold LH pedal on pilot side. Close LH bleeder valve, then slowly release LH pedal on pilot side. Open LH bleeder valve. (ab) Repeat LH caliper air purge at least times. Verify fluid flowing out of tubing attached to LH caliper is clear of bubbles before continuing. NOTE The system is purged of air when there are no air bubbles in overflow tubing. Caliper may be damaged if bleeder is over tightened. (ac) Close both bleeder valves. (ad) Close hydraulic tank feed valve and depressurize tank by removing air source. Verify pressure on both gauges reads zero. (ae) Remove overflow tubing from bleeder valves. (af) Torque bleeder valves 18.0 ±7.0 in-lb (16.7 ±0.8 Nm). (Refer to 0-60) (ag) Clean any residual fluid from bleeder valves, including inside opening. (Refer to 0-0) 6 50AMM_TR_--01
CIRRUS AIRPLANE MAINTENANCE MANUAL CHAPTER -: BRAKES (ah) Remove 1/8" NPT fitting and feed tubing from brake reservoir. Cap off feed tubing after removal to prevent spillage. (ai) Perform Servicing - Brake Fluid Replenishing. (Refer to 1-10) (aj) (ak) Re-install plastic cap onto brake reservoir. Store overflow fluid in properly labeled gallon containers until tank needs to be refilled. NOTE While depressing rudder pedals, all pedals should feel similar. (al) Depress each rudder pedal with your feet and confirm there is solid pressure and pedals do not sink under steady pressure. (am) Engage parking brake. Verify brakes are holding by pushing on each end of wing and confirming airplane does not move. (an) If parking brake does not hold, but pedals have solid pressure, check rigging adjustment of parking brake valve. If rigging is determined to be correct, valve may be defective. (ao) If any of these checks fails, repeat brake bleeding procedure until satisfactory results are obtained. 7 50AMM_TR_--01
CHAPTER -: BRAKES CIRRUS AIRPLANE MAINTENANCE MANUAL Figure --: Bleeding the Brake System LEGEND 1. Pressurized Brake Bleeder. Tubing. Bleeder Valve. Brake Fluid Reservoir 5. Fitting 6. Overflow Container 7. Hose Clamp 8. Air Pressure Regulator 9. Brake Fluid Type Placard 6 9 7 5 1 8 SF50_MM_0158 8 9 Jul 018 50AMM_TR_--01
CIRRUS AIRPLANE MAINTENANCE MANUAL CHAPTER -: BRAKES J. Brake System Pressure Test This pressure test will identify the location of any leaks. (1) Adjustment/Test - Brake System Pressure Test (a) Acquire necessary tools, equipment, and supplies. Description P/N or Spec. Supplier Purpose Wheel Chocks WCK1001 Cirrus Design Block wheels. Hydraulic Fluid MIL-PRF-8757 Any Source Replenish brake system. Hydraulic Hand Pump Isopropyl Alcohol - Any Source Pressurize brake system. TT-I-75 Grade A or B Any Source Solvent clean. (b) (c) (d) (e) (f) (g) Place wheel chocks into position. Disengage parking brake. Verify pressure on gauge reads zero before opening tank. Cap and valve should be hand tightened only. Ensure relief valve is completely closed and filler cap is secure. Verify there is sufficient hydraulic fluid in tank. Refill if less than one gallon of fluid is left with either new or recycled fluid. Filter fluid and follow procedure on tank. Do not attach hydraulic hand pump to brake fluid reservoir inlet. Support attachment of pump to prevent damage to brake line. Disconnect brake fluid reservoir and attach hydraulic hand pump. NOTE Hold pressure for 1 minute and inspect all fittings for leaks between every increase. 9 50AMM_TR_--01
CHAPTER -: BRAKES CIRRUS AIRPLANE MAINTENANCE MANUAL (h) Increase pressure by 100 psig increments until maximum pressure of 900+0/-0 psig is reached. 1 At 900+0/-0 psig, system pressure should not drop during 1 minute hold and no brake fluid should leak. (i) If any leaks were discovered during pressure test, release system pressure and close valve. 1 Note location of leak. Service as required to repair leaks. Solvent clean any fluid that leaked on aircraft. (Refer to 0-0) (j) Perform Adjustment/Test - Bleeding the Brake System if any fittings were loosened or re-torqued, or if brake system was opened anywhere other than the brake fluid reservoir. (Refer to -) 0 50AMM_TR_--01