Flaps System. 1. General
|
|
- Abigayle Paul
- 5 years ago
- Views:
Transcription
1 CIRRUS AIRPLANE MAINTENANCE MANUAL Flaps System CHAPTER 27-50: FLAPS SYSTEM GENERAL 27-50: FLAPS SYSTEM 1. General This section describes that portion of the flight control system which controls the position and movement of the flaps. Included are the flap assembly, flap actuator assembly, torque tube assembly, flap switch assembly, flap switch panel, and flap relays. Flap control is achieved via a flap activation switch mounted on the center console. Indicator lights identify flap position. A linear actuator, located under the baggage floor, drives a torque tube interconnect between the left and right flaps. A load limiting clutch on the actuator prevents flap deployment at high speeds. Proximity sensors on the flap linear actuator identify flap position and surface travel. In the event of a sensor failure, torque tube/actuator geometry prevents the flaps from causing an uncontrollable flight condition. Electromagnetic Interference Suppression (EMI) cores are integral to the flap system wire harness. 1
2 CHAPTER 27-50: FLAPS SYSTEM 2. Maintenance Practices CIRRUS AIRPLANE MAINTENANCE MANUAL A. Flap Actuator Assembly (See Figure ) (See Figure ) (1) Removal - Flap Actuator Assembly CAUTION To prevent damage to flap hinges and flaps, tape flaps to wing prior to disconnecting flap actuator. (a) Pull FLAPS circuit breaker. (b) Remove passenger seats. (Refer to 25-10) (c) Remove carpet. (Refer to 25-10) (d) Remove access panels CF4C and CF5. (Refer to -00) (e) Serials w/ Air Conditioning: Remove condenser. (Refer to 21-50) (f) Remove cotter pin, nut, washers, and bolt securing flap actuator to torque tube coupler. (g) Disconnect flap actuator electrical connector. (h) Remove retainer rings and pin securing flap actuator assembly to mounting bracket. (i) Remove flap actuator assembly from airplane. (j) If replacing flap actuator with new assembly, remove screws securing collar at flap actuator shaft. Retain collar and screws. (2) Disassembly - Flap Actuator Assembly (a) (b) (c) (d) Loosen jam nut securing rod end to flap actuator end fitting. Remove rod end and jam nut. Loosen jam nut securing flap actuator end fitting to flap actuator. Remove end fitting. 2
3 CIRRUS AIRPLANE MAINTENANCE MANUAL CHAPTER 27-50: FLAPS SYSTEM (3) Assembly - Flap Actuator Assembly (a) Acquire necessary tools, equipment, and supplies. Description P/N or Spec. Supplier Purpose Threadlocker Loctite 242 Any Source Lock threads. (b) Back jam nut to bottom of flap actuator and install end fitting on actuator. (c) Bottom out end fitting onto flap actuator to ensure maximum thread engagement. (d) Apply threadlocker to jam nut thread area. (Refer to 20-40) (e) Torque jam nut to in-lb (15.8 to 17.5 Nm). (Refer to 20-0) (f) Bottom out jam nut onto rod end. (g) Install rod end into actuator end fitting and bottom out. Leave jam nut loose at this time. (4) Installation - Flap Actuator Assembly (a) Acquire necessary tools, equipment, and supplies. Description P/N or Spec. Supplier Purpose Threadlocker Loctite 242 Any Source Lock threads. (b) If secured, cut cable ties securing proximity sensor wiring to flap actuator. (c) Position flap actuator assembly to mounting bracket and secure with pin and retaining rings. (d) Manually extend actuator to approximately 50% full deployment. (e) Connect flap actuator electrical connector. (f) Reset FLAPS circuit breaker. (g) Turn flap switch to UP. (h) Set BAT 1 switch to ON position. (i) After flap actuator stops, turn flap switch to 50%. (j) Set BAT 1 switch to OFF position. (k) Loosen adjustment screws and reposition full up proximity sensor to within 1.0 inch (2.5 cm) of middle proximity sensor. 3
4 CHAPTER 27-50: FLAPS SYSTEM CIRRUS AIRPLANE MAINTENANCE MANUAL (l) Loosen adjustment screws and reposition full down proximity sensor to within 1.0 inch (2.5 cm) of middle proximity sensor. NOTE Stack-up order may be altered to allow for better alignment between flap actuator and torque tube coupler. (m) Install bolt and washers connecting rod end to torque tube coupler and secure with new nut. Do not install cotter pin at this time. (n) Remove tape securing flaps to wing. (o) If removed, position collar so that screws are seated against flats on flap actuator rod. Tighten screws securing collar to flap actuator rod. (p) Reset FLAPS circuit breaker. (q) Perform Adjustment/Test - Flap Travel. (Refer to 27-50) (r) If jam nut was loosely installed during flap actuator assembly: 1 Apply threadlocker to jam nut thread area. (Refer to 20-40) NOTE By design, the collar will deform when specified torque is applied to screws. 2 Tighten jam nut securing rod end to actuator end fitting. Torque jam nut 0.0 to 70.0 in-lb (.8 to 7.9 Nm). (Refer to 20-0) (s) Torque bolt securing rod end to torque tube coupler. (Refer to 20-0) (t) Install new cotter pin at attaching hardware securing rod end to torque tube coupler. (Refer to 20-70) (u) Install cable ties securing proximity switch wiring to flap actuator. (v) Set BAT 1 switch to ON position. (w) Rotate FLAPS switch to 100% position. (x) Rotate FLAPS switch to UP position. (y) Set BAT 1 switch to OFF position. (z) Serials w/ Air Conditioning: Install condenser. (Refer to 21-50) (aa) Install access panels CF4C and CF5. (Refer to -00) (ab) Install carpet. (Refer to 25-10) (ac) Install passenger compartment seats. (Refer to 25-10) 4
5 CIRRUS AIRPLANE MAINTENANCE MANUAL CHAPTER 27-50: FLAPS SYSTEM (5) Adjustment/Test - Flap Travel NOTE When in the 0% position, a minimum 0.05 inch (1.27 mm) clearance must be maintained between end fitting and torque tube coupler. When adjusting position proximity sensors, it may be necessary to lengthen actuator to achieve full 0% position. Accomplish by backing out rod end, but do not exceed 2 turns maximum. (a) Acquire necessary tools, equipment, and supplies. Description P/N or Spec. Supplier Purpose WS 40 Wing Template /-102 Cirrus Design Flap rigging. WS 132 Wing Template /-108 Cirrus Design Flap rigging. Inclinometer PRO30 Macklanburg Duncan Deflection angle determination. NOTE Flap may exhibit a slight twist from root to tip. Average the inboard and outboard angle to set the neutral point. (b) Remove passenger compartment seats. (Refer to 25-10) (c) Remove carpet and access panels CF4C and CF5. (Refer to -00) (d) If secured, cut cable ties securing proximity sensor wiring to flap actuator. (e) Set BAT 1 switch to ON position. (f) Turn flap switch to UP. (g) Mark WS 132 reference line for left and right wing templates as follows: 1 From wing cuff, measure 1.75 inches inboard and mark. 2 From flap outboard edge, measure 10.7 inches inboard and mark. 3 Draw WS 132 reference mark line from leading edge to trailing edge. (h) Mark WS 40 reference line for left and right wing templates as follows: 1 From flap inboard edge, measure 1.75 inches outboard and mark. 2 From wing cuff, measure 90 inches inboard and mark. 3 Draw WS 40 reference mark line from leading edge to trailing edge. (i) Position WS 40 and WS 132 template on left and right wing to verify flaps are in full up position. 5
6 CHAPTER 27-50: FLAPS SYSTEM CIRRUS AIRPLANE MAINTENANCE MANUAL (j) If flaps are not in full up position, adjust flap actuator proximity sensor. 1 Turn flap switch to 50%. 2 Set BAT 1 switch to OFF position. NOTE For best results in determining proximity sensor location, do not move sensor more than 0.10 inch (2.5 mm) per positioning attempt. 3 Adjust full up proximity sensor by loosening screw and repositioning sensor on flap actuation extension tube. 4 Set BAT 1 switch to ON position. 5 Turn flap switch to UP. Using the templates, verify flaps are in full up position. 7 If necessary, repeat repositioning of proximity switch until flaps are in full up position. (k) Fasten inclinometer to inboard side of left flap and set at 0. (l) Turn flap switch to 100%. (m) Verify flap exhibits a 35.5 angle change. (n) If flaps are not in 100% deployed position, adjust flap actuator proximity sensor. 1 Turn flap switch to 50%. 2 Set BAT 1 switch to OFF position. NOTE For best results in determining proximity sensor location, do not move sensor more than 0.10 inch (2.5 mm) per positioning attempt. 3 Adjust 100% proximity sensor by loosening screw and repositioning sensor on flap actuation extension tube. 4 Set BAT 1 switch to ON position. 5 Turn flap switch to 100%. If necessary, repeat repositioning of proximity switch until flaps are in 100% deployed position. (o) Turn flap switch to UP. After flaps stop, turn flap switch to 50%. (p) Verify flap exhibits a 1 angle change. (q) If flaps are not in 50% deployed position, adjust flap actuator proximity sensor. 1 Turn flap switch to UP. 2 Set BAT 1 switch to OFF position.
7 CIRRUS AIRPLANE MAINTENANCE MANUAL CHAPTER 27-50: FLAPS SYSTEM NOTE For best results in determining proximity sensor location, do not move sensor more than 0.10 inch (2.5 mm) per positioning attempt. 3 Adjust 50% proximity sensor by loosening screw and repositioning sensor on flap actuation extension tube. 4 Set BAT 1 switch to ON position. 5 Turn flap switch to 50%. If necessary, repeat repositioning of proximity switch until flaps are in 50% deployed position. (r) Remove inclinometer from flap. (s) Verify operation of flaps circuit. 1 Activate flaps circuit from 0% position to 50% position and press Push-to-Talk Switch while flaps are in transit. Flaps shall travel to 50% position without hesitation and stop. 2 Activate flaps circuit from 100% position to 50% position and press Push-to-Talk Switch while flaps are in transit. Flaps shall travel to 50% position without hesitation and stop. 3 Activate flaps circuit from 50% position to 0% position. (t) Verify torque tube clearance. 1 Push torque tube all the way to the left. 2 Verify gap between left end of torque tube and nearest part of flap assembly, hinge, or linkage is at least 0.1 inch (2.54 mm). 3 Push torque tube all the way to the right. 4 Verify gap between right end of torque tube and nearest part of flap assembly, hinge, or linkage is at least 0.1 inch (2.54 mm). (u) Install cable ties securing proximity switch wiring to flap actuator. (v) Install carpet and access panels CF4C and CF5. (Refer to -00) (w) Install passenger compartment seats. (Refer to 25-10) 7
8 CHAPTER 27-50: FLAPS SYSTEM CIRRUS AIRPLANE MAINTENANCE MANUAL () Inspection/Check - Flap System Rigging (See Figure ) NOTE The gap and overlap inspection of the following procedure need only be performed after the installation of a replacement (new or different) flap. If the following flap leading edge gap and overlap inspections do not fall within the specified clearances, contact Cirrus Design Customer Service for disposition. (Refer to AMM-Intro-00) (a) Acquire necessary tools, equipment, and supplies. Description P/N or Spec. Supplier Purpose 90 Square - Any Source Flap rigging. (b) (c) (d) (e) Replacement Flap Installation Only: Verify flap gap and overlap. 1 Using 90 square with flaps fully extended, verify maximum gap between crown of flap and trailing edge of wing is 0.917±0.200 inch (2.33±0.50 cm) at root of the flap, and 0.958±0.200 inch (2.43±0.50 cm) at tip of flap. 2 Using 90 square with flaps fully extended, verify maximum overlap between leading edge of flap and trailing edge of wing is 1.512±0.200 inch (3.84±0.50 cm) at root of flap, and 0.52±0.200 inch (1.43±0.50 cm) at tip of flap. Verify flap UP, 50%, and 100% deployment positions. Verify minimum rod end thread engagement of inch (0.79 cm). Verify proper installation of safety wires and cotter pins on all fasteners and engagement of all jam nuts through complete flap control system. 8
9 CIRRUS AIRPLANE MAINTENANCE MANUAL CHAPTER 27-50: FLAPS SYSTEM Figure : Flap Gap and Overlap Inspections SQUARE LEADING EDGE GAP OVERLAP Max. at Root of Flap Min. at Root of Flap Max. at Tip of Flap Min. at Tip of Flap Leading Edge Gap Overlap 1.117" 0.717" 2.83 cm 1.83 cm 1.712" 4.34 cm 1.312" 3.34 cm 1.158" 0.758" 2.93 cm 1.93 cm 0.72" 1.93 cm 0.32" 0.93 cm SR22_MM27_4484 9
10 CHAPTER 27-50: FLAPS SYSTEM CIRRUS AIRPLANE MAINTENANCE MANUAL B. Torque Tube Assembly (See Figure ) (1) Removal - Torque Tube Assembly (a) Remove nuts, washers, spacers, and bolts securing torque tube thrust collar and end fitting to flap torque tube. (b) Remove passenger compartment seats. (Refer to 25-10) (c) Remove carpet and access panel CF4C. (Refer to -00) (d) Remove cotter pin, nut, washers, and bolt securing flap actuator push/pull rod to torque tube coupler. (e) Remove nuts, washers, spacers, and bolts securing torque tube coupler and torque tubes. (f) Withdraw torque tube from outboard tube bushing. (g) Withdraw torque tube coupler from inboard tube bushing. (2) Installation - Torque Tube Assembly (a) Insert torque tube coupler into inboard tube bushing. (b) Insert LH torque tube through outboard bushing into torque tube coupler. (c) Insert RH torque tube through outboard bushing into torque tube coupler. (d) Install bolts, washers, spacers, and nuts securing torque tube coupler and torque tubes. (e) Install bolts, washers, spacers, and nuts securing torque tube thrust collar and end fitting to flap torque tube. (f) Install bolt, washers, nut, and new cotter pin securing flap actuator push/pull rod to torque tube coupler. (g) Perform Adjustment/Test - Flap Travel. (Refer to 27-50) (h) Install access panel and carpet. (Refer to -00) (i) Install passenger compartment seats. (Refer to 25-10) 10
11 CIRRUS AIRPLANE MAINTENANCE MANUAL CHAPTER 27-50: FLAPS SYSTEM Figure : Flap Actuator and Torque Tube Installation (1 of 3) A1 11 0% A1 2 FUSELAGE SKIN (REF) 50% 100% NOTE Refer to sheet 2 for continuation. Collar Installation. Stack-up order may be altered to allow for better alignment between flap actuator and torque tube coupler. LEGEND 1. Flap Actuator 2. Proximity Sensor 3. Connector 4. Actuator End Fitting 5. Rod End. Washer 7. Bracket 8. Bushing 9. Pin 10. Retainer Ring 11. Screw 12. Nut 13. Collar 14. Bolt 15. Cotter Pin 1. Spacer 17. Torque Tube 18. Torque Tube Coupler SR22_MM27_
12 CHAPTER 27-50: FLAPS SYSTEM CIRRUS AIRPLANE MAINTENANCE MANUAL Figure : Flap Actuator and Torque Tube Installation (2 of 3) AFT FLOOR LONGERON (REF) FUSELAGE (REF) (LEFT SIDE SHOWN) NOTE Refer to sheet 1 for continuation. LEGEND. Washer 8. Bushing 12. Nut 14. Bolt 1. Spacer 17. Torque Tube 18. Thrust Collar 19. Torque Tube End Fitting 20. Bushing Mount 21. Backing Plate SR22_MM27_448 12
13 CIRRUS AIRPLANE MAINTENANCE MANUAL CHAPTER 27-50: FLAPS SYSTEM Figure : Flap Actuator and Torque Tube Installation (3 of 3) 18 ACTUATOR SEAL (REF) % POSITION NOTE Position collar so that screws are seated against flats on flap actuator rod. 0% POSITION VIEW A1 1 LEGEND 1. Flap Actuator 2. Proximity Sensor 4. Actuator End Fitting 5. Rod End 11. Screw 13. Collar 18. Torque Tube Coupler SR22_MM27_
14 CHAPTER 27-50: FLAPS SYSTEM CIRRUS AIRPLANE MAINTENANCE MANUAL C. Flap Switch Panel (See Figure ) (1) Removal - Flap Switch Panel (a) (b) (c) (d) Pull FLAPS circuit breaker. Remove screws securing flap switch panel to engine control panel. Disconnect flap switch connector. Remove flap switch panel from airplane. (2) Installation - Flap Switch Panel (a) Connect flap switch connector. (b) Position flap switch panel to engine control panel and secure with screws. (c) Reset FLAPS circuit breaker. (d) Perform Operational Test - Flap Switch Panel. (Refer to 27-50) (3) Operational Test - Flap Switch Panel (a) (b) (c) (d) Set BAT 1 switch to ON position. Before testing the flaps system, verify flaps and flaps actuator are connected and no obstructions to movement are present. Set flaps switch to same position as current flaps position. Set flaps switch to "UP" position. Verify flaps position is up with "UP" LED illuminated. (e) Set flaps switch to "50%" position. Verify flaps position stops at 50% with "50%" LED illuminated. (f) Set flaps switch to "100%" position. Verify flaps position stops at 100% with "100%" LED illuminated. (g) Set flaps switch to "50%" position. Verify flaps position stops at 50% with "50%" LED illuminated. (h) Set flaps switch to "UP" position. Verify flaps position stops at up position with "UP" LED illuminated. 14
15 CIRRUS AIRPLANE MAINTENANCE MANUAL CHAPTER 27-50: FLAPS SYSTEM (i) (j) (k) Set flaps switch to "100%". While flaps are passing 50%, verify 50% LED only flashes once. Set flaps switch to "UP". While flaps are passing 50%, verify 50% LED only flashes once. Set BAT 1 switch to OFF position. 15
16 CHAPTER 27-50: FLAPS SYSTEM CIRRUS AIRPLANE MAINTENANCE MANUAL Figure : Flap Switch Panel Installation ENGINE CONTROL PANEL (REF) LEGEND 1. Flap Switch Panel 2. Screw 3. Connector SR22_MM27_4488 1
17 CIRRUS AIRPLANE MAINTENANCE MANUAL CHAPTER 27-50: FLAPS SYSTEM D. Flap Relays (See Figure ) (1) Removal - Flap Relay (a) Pull FLAPS circuit breaker. (b) Remove access panel CF3R. (Refer to -00) (c) Remove relay from socket. (2) Installation - Flap Relay (a) Position relay to socket and push firmly to install. (b) Install access panel CF3R. (Refer to -00) (c) Reset FLAPS circuit breaker. 17
18 CHAPTER 27-50: FLAPS SYSTEM CIRRUS AIRPLANE MAINTENANCE MANUAL Figure : Flap Relay Installation A RH LONGERON (REF) 3 ROLL RELAY (REF) GROUND BUS (REF) DETAIL A LEGEND 1. Mounting Plate, Forward 2. Screw 3. Washer 4. Spacer 5. Nut. Bolt 7. Relay Socket 8. Flap Relay SR22_MM27_
CIRRUS AIRPLANE MAINTENANCE MANUAL
ELEVATOR AND PITCH TRIM SYSTEM 1. DESCRIPTION This section describes that portion of the flight control system which controls the position and movement of the elevator. Included are; elevator system torque
More informationYaw Control and Trim. 1. General. A. Yaw Control System. B. Yaw Trim System
CIRRUS AIRPLANE MAINTENANCE MANUAL MODELS SR AND SRT Yaw Control and Trim CHAPTER 7-0: YAW CONTROL AND TRIM GENERAL 7-0: YAW CONTROL AND TRIM. General This section describes that portion of the flight
More informationCIRRUS AIRPLANE MAINTENANCE MANUAL
MODEL SR0 YAW CONTROL AND TRIM. GENERAL This section describes that portion of the flight control system which controls the position and movement of the rudder. Included are; rudder system rigging, rudder
More informationPitch Control and Trim
Pitch Control and Trim GENERAL 27-30: PITCH CONTROL AND TRIM. General This section describes that portion of the flight control system which controls the position and movement of the elevator. This includes
More informationCIRRUS AIRPLANE MAINTENANCE MANUAL
FLIGHT SURFACES. DESCRIPTION The flaps are mounted to the trailing edge of each wing between the inboard end of the ailerons and the fuselage. The ailerons are located near the wing tips and hinge to the
More informationService Bulletin. ATA 27-00: Flight Controls Rudder-Aileron Interconnect Modification
Service Bulletin Issued: 09 May 2007 Models SR20 and SR22 ATA 27-00: Flight Controls Rudder-Aileron Interconnect Modification COMPLIANCE Mandatory: Accomplish this Service Bulletin within 25 Flight Hours
More information57-50 FLIGHT SURFACES
FLIGHT SURFACES 1. DESCRIPTION The flaps are mounted to the trailing edge of each wing between the inboard end of the ailerons and the fuselage. The ailerons are located near the wing tips and hinge to
More information53-40 ATTACH FITTINGS
ATTACH FITTINGS. DESCRIPTION Attach fittings are provided for attachment of the seats (Refer to -0), baggage straps (Refer to -0), rear seat harnesses (Refer to -0), cargo net straps (Refer to -0), cabin
More informationCabin. 1. General. A. Cabin Seats
CIRRUS AIRPLANE MAINTENANCE MANUAL Cabin CHAPTER 25-10: CABIN GENERAL 25-10: CABIN 1. General This section covers cabin compartment seats, seat harnesses, trim, cabin headliner, floor covering, sunvisors,
More informationWing Structure. 1. General
CIRRUS AIRPLANE MAINTENANCE MANUAL Wing Structure CHAPTER 57-10: WING STRUCTURE GENERAL 57-10: WING STRUCTURE 1. General The wing is constructed in a conventional spar, rib, and shear section arrangement.
More informationCIRRUS AIRPLANE MAINTENANCE MANUAL
PASSENGER COMPARTMENT 1. DESCRIPTION This section covers the passenger compartment lighting. A. Passenger Eyeball Lights Individual eyeball-type reading lights are installed in the headliner above each
More informationPassenger And Crew Door
CIRRUS AIRPLANE MAINTENANCE MANUAL Passenger And Crew Door CHAPTER 5-10: PASSENGER AND CREW DOOR GENERAL 5-10: PASSENGER AND CREW DOOR 1. General The two crew/passenger doors incorporate a flush-mount
More informationA. Stall Warning System - Serials w/o Ice Protection
Stall Warning System GENERAL 27-31: STALL WARNING SYSTEM 1. General A. Stall Warning System - Serials w/o Ice Protection The airplane uses an electro-pneumatic stall warning system. As the angle of attack
More informationCIRRUS AIRPLANE MAINTENANCE MANUAL
POWER CONTROL. DESCRIPTION This section describes those components which furnish a means of controlling engine power. Engine controls for the airplane include the following: control quadrant, throttle
More informationC I R R U S CABIN 1. DESCRIPTION A. Cabin Seats B. Radio Module Assembly
CABIN. DESCRIPTION This section covers cabin compartment seats, seat harnesses, trim, cabin headliner, floor covering, sunvisors, grab handles, headset hooks, coat hooks, drink holders, storage pockets,
More information57-20 AUXILIARY STRUCTURE
AUXILIARY STRUCTURE 1. DESCRIPTION The leading edge of the wing is manufactured from composite materials. This airplane has a one-piece wing with individual wing tips. The wing tips are manufactured from
More informationCIRRUS AIRPLANE MAINTENANCE MANUAL
MODEL SR PASSENGER AND CREW DOORS. DESCRIPTION AND OPERATION Serials 000 thru 00: The two crew/passenger doors incorporate a flush-mount outside door handle, key-operated door lock, and a conventional
More informationCIRRUS AIRPLANE MAINTENANCE MANUAL
AUXILIARY STRUCTURE 1. DESCRIPTION The leading edge of the wing is manufactured from composite materials. This airplane has a one-piece wing with individual wing tips. The wing tips are manufactured from
More informationPASSENGER AND CREW DOORS
MODELS SR AND SRT PASSENGER AND CREW DOORS. DESCRIPTION AND OPERATION Serials -000 thru -00: The two crew/passenger doors incorporate a flush-mount outside door handle, key-operated door lock, and a conventional
More informationSTALL WARNING SYSTEM 1. DESCRIPTION A.
STALL WARNING SYSTEM 1. DESCRIPTION A. Stall Warning System - Serials w/o Perspective Avionics The airplane uses an electro-pneumatic stall warning system. As the angle of attack increases and the airplane
More informationCIRRUS AIRPLANE MAINTENANCE MANUAL
NOISE SUPPRESSOR 1. DESCRIPTION Noise suppression is accomplished through use of a heat exchanger (Serials 0002 thru 019) or a heat exchanger and muffler (Serials 020 & subs) connected to the exhaust header
More information33-40 EXTERIOR LIGHTING
EXTERIOR LIGHTING. DESCRIPTION This section covers that portion of the system which provides illumination outside of the aircraft. This includes the landing light, anti-collision strobe light, and recognition
More informationSPECIAL PURPOSE EQUIPMENT
All SPECIAL PURPOSE EQUIPMENT 1. GENERAL This section describes special purpose equipment on the airplane. This equipment includes the Cirrus Airplane Parachute System (CAPS) the aft tiedown ballast bracket,
More informationCIRRUS AIRPLANE MAINTENANCE MANUAL
INDICATING 1. DESCRIPTION This section describes that portion of the oil system which is used to indicate the quantity, temperature, and pressure of the oil. Components included are the oil filler cap/dipstick,
More informationService Bulletin. ATA 52-10: Passenger and Crew Doors Door Latching Assembly Upgrade
Service Bulletin Issued: 5 Oct 00 Models SR0 and SR ATA 5-10: Passenger and Crew Doors Door Latching Assembly Upgrade COMPLIANCE Optional: Accomplishment of this Service Bulletin is at the owner s option.
More informationCIRRUS AIRPLANE MAINTENANCE MANUAL
DIMENSIONS AND AREAS 1. GENERAL This section describes those diagrams and text which shows the area, dimensions, stations, access doors, and physical locations of the structural members of the airplane.
More informationFLIGHT SIMULATOR SYSTEMS
FLIGHT SIMULATOR SYSTEMS 1. GENERAL This section describes systems required for simulator operation. This equipment includes the Cirrus Landing Gear Simulator (CLGS). 2. DESCRIPTION The intent of the CLGS
More informationCIRRUS AIRPLANE MAINTENANCE MANUAL
MODEL SR0 EXTERIOR LIGHTING. DESCRIPTION This section covers that portion of the system which provides illumination outside of the aircraft. This includes the landing light, anti-collision strobe light,
More informationCIRRUS AIRPLANE MAINTENANCE MANUAL
SPECIAL PURPOSE EQUIPMENT 1. GENERAL This section describes special purpose equipment on the airplane. This equipment includes the Cirrus Airplane Parachute System (CAPS) and the aft tiedown ballast bracket.
More informationCIRRUS AIRPLANE MAINTENANCE MANUAL
MODEL SR0 All PASSENGER AND CREW DOORS. DESCRIPTION AND OPERATION Serials 005 thru 4: The two crew/passenger doors incorporate a flush-mount outside door handle, key-operated door lock, and a conventional
More informationDimensions And Areas. 1. General. A. Airplane Dimensions and Areas
Dimensions And Areas 600: DIMENSIONS AND AREAS 1. General This section describes those diagrams and text which shows the area, dimensions, stations, access doors, and physical locations of the structural
More informationCIRRUS AMM TEMPORARY REVISION
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
More informationCIRRUS AIRPLANE MAINTENANCE MANUAL
STALL WARNING SYSTEM 1. DESCRIPTION A. Stall Warning System - Serials 05 thru 2015, 2016 & subs w/o Perspective Avionics The airplane uses an electro-pneumatic stall warning system. As the angle of attack
More informationC I R R U S HOISTING DESCRIPTION
HOISTING 1. DESCRIPTION This chapter describes those instructions necessary to support the airplane during maintenance and repair. In some instances (i.e. off-runway landing, collapsed gear, etc.) it may
More informationC I R R U S COWLING DESCRIPTION
COWLING 1. DESCRIPTION Serials 22-0002 thru 22-019, 22-0821 thru 22-711: The engine cowling, fabricated from fiberglass and epoxy, consists of one upper and two lower halves. A one-piece (22-0002 thru
More information33-10 FLIGHT COMPARTMENT
FLIGHT COMPARTMENT. DESCRIPTION Flight compartment interior lighting consists of instrument lights, glareshield flood lights, overhead dome light, individual reading lights, pilot control lights, CAPS
More informationCIRRUS SR2X SB 2X Service Bulletin. Issued: February 27, SNS SUBJECT: TEMPERATURE CONTROL - Cabin Air Coupler Actuator Rigging
CIRRUS SR2X Service Bulletin Number: Issued: February 27, 2012 SNS SUBJECT: 21-60 TEMPERATURE CONTROL - Cabin Air Coupler Actuator Rigging 1. COMPLIANCE Recommended, On Condition: Accomplish this Service
More informationC I R R U S DISTRIBUTION DESCRIPTION
MODELS SR AND SRT DISTRIBUTION. DESCRIPTION This section contains information on the distribution system. The fuel distribution system consists of electric and mechanical (engine-driven) fuel pumps, fuel
More informationCIRRUS AIRPLANE MAINTENANCE MANUAL
ELECTRICAL LOAD DISTRIBUTION. DESCRIPTION The power distribution system for this airplane consists of the main distribution bus and the essential distribution bus in the MCU along with the associated buses
More informationC I R R U S CONTROLLING DESCRIPTION
CONTROLLING 1. DESCRIPTION Serials 22-0002 & subs: An electric two-speed fuel pump provides boost (low speed) and prime (high speed) for the engine. A console mounted rocker switch located on the center
More informationCIRRUS AIRPLANE MAINTENANCE MANUAL
AIR INTAKES 1. DESCRIPTION This section describes that portion of the power plant which directs mass air flow to the engine. Induction air enters the engine through a filter mounted on the left, forward
More informationSD3-60 AIRCRAFT MAINTENANCE MANUAL PRIMARY CONTROLS - DESCRIPTION & OPERATION
AMM 5.0.0.0AILERON PRIMARY CONTROLS - DESCRIPTION & OPERATION 1. Description A. General Aileron movement is differentially controlled by a system of push/pull rods and levers which directly connect the
More informationCIRRUS AIRPLANE MAINTENANCE MANUAL
ANALYZERS - ENGINE MONITORING. DESCRIPTION This section describes that portion of the engine indicating system which is used to analyze engine performance, temperature, and condition. Serials 00 thru 8
More informationCHAPTER 27 - FLIGHT CONTROLS TABLE OF CONTENTS
FLIGHT CONTROLS 27-00 General 1 Troubleshooting 2 AILERON AND ROLL TRIM SYSTEM 27-10 Aileron System Cables 2 Removal - Aileron System Cables 2 Installation - Aileron System Cables 2 Adjustment/Test - Aileron
More information22-11 SYSTEM 55 AUTOPILOT
SYSTEM 55 AUTOPILOT 1. DESCRIPTION This section covers those systems and components which use inputs to the system to automatically control the flight path of the aircraft through adjustment to the pitch/roll
More informationREVISION LIST CHAPTER 21: FLAP SYSTEM COMPLETION
REVISION LIST CHAPTER 21: The following list of revisions will allow you to update the Legacy construction manual chapter listed above. Under the Action column, R&R directs you to remove and replace the
More informationRotary Speed Brake Actuation System ICA Supplement
CESSNA AIRCRAFT COMPANY AIRCRAFT DIVISION WICHITA, KANSAS 67277 Rotary Speed Brake Actuation System ICA Supplement MODEL NO: 510 SUPPLEMENT NO: ICA-510-27-00001 SUPPLEMENT DATE: 04/28/2009 PREPARED BY:
More informationCHAPTER 76 ENGINE CONTROLS. Section Title Page
CHAPTER 76 ENGINE CONTROLS Section Title Page 76-00 Description........................................ 76.1 76-10 Fuel Control Unit (FCU)............................... 76.1 76-11 FCU Throttle Control
More informationCIRRUS AIRPLANE MAINTENANCE MANUAL
SYSTEM 55 AUTOPILOT 1. DESCRIPTION The S-TEC System 55 is a dual axis autopilot system that provides roll stability, heading hold, NAV/GPS tracking, altitude hold, vertical speed selection, automatic glideslope
More informationC I R R U S WING STRUCTURE DESCRIPTION
WING STRUCTURE 1. DESCRIPTION The wing is constructed in a conventional spar, rib, and shear section arrangement. The upper and lower skins are bonded to the spar, ribs, and aft shear web forming a torsion
More informationCIRRUS AIRPLANE MAINTENANCE MANUAL
AERODYNAMIC FAIRINGS 1. DESCRIPTION This section describes those components which make up the aerodynamic fairings. A fixed, composite wing root fairing is installed around the wing root, enclosing the
More informationC I R R U S COLLECTOR DESCRIPTION
COLLECTOR 1. DESCRIPTION This section describes the portion of the exhaust system which collects the exhaust gases from the cylinder and conducts them overboard. Included are the exhaust headers and collector
More informationCIRRUS AIRPLANE MAINTENANCE MANUAL
JACKING 1. DESCRIPTION Three jack points, located at each wing tiedown and tail tiedown, are provided to perform maintenance operations. Tie-down rings must be removed and replaced with jack points prior
More informationCIRRUS AIRPLANE MAINTENANCE MANUAL
AIR INTAKES 1. DESCRIPTION This section describes that portion of the power plant which directs mass air flow to the engine. Induction air enters the engine through a filter mounted on the right, aft side
More informationPropeller Assembly. 1. General
Propeller Assembly GENERAL 61-10: PROPELLER ASSEMBLY 1. General The propeller assembly consists of a hollow aluminum hub which supports the propeller blades and also houses the pitch changing mechanism.
More informationChapter 27 FLIGHT CONTROLS
Chapter 27 FLIGHT CONTROLS 27-Title Page 1 January 23, 2012 INTENTIONALLY LEFT BLANK 27-Title Page 2 January 23, 2012 LIST OF EFFECTIVE PAGES Chapter Section Page No. Date 27 27-Title 1 January 23, 2012
More informationCHAPTER 21 ENVIRONMENT CONTROL. Section Title Page
CHAPTER 21 ENVIRONMENT CONTROL Section Title Page 21-00 Description........................................ 21.1 21-10 Ventilation........................................ 21.3 21-11 Nose Vent................................
More informationAttitude And Direction
CIRRUS AIRPLANE MAINTENANCE MANUAL Attitude And Direction CHAPTER 34-20: ATTITUDE AND DIRECTION GENERAL 34-20: ATTITUDE AND DIRECTION 1. General This section contains information pertaining to those portions
More informationChapter 27. Flight Controls
Chapter 27 Flight Controls PAGE 1 Chapter 27 Table of Contents Chapter Title 27-00-00 GENERAL.................................. 3 27-00-01 Control Rods................................. 6 27-00-02 Bellcranks...................................
More informationChapter 52 DOORS -Title
Chapter 52 DOORS 52-Title Page 1 January 23, 2012 INTENTIONALLY LEFT BLANK 52-Title Page 2 January 23, 2012 LIST OF EFFECTIVE PAGES Chapter Section Page No. Date 52 52-Title 1 January 23, 2012 2 January
More informationCIRRUS AIRPLANE MAINTENANCE MANUAL VISION SF50 CHAPTER 32-42: BRAKES GENERAL. Brakes 32-42: BRAKES. 1. General
Brakes GENERAL 32-2: 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
More informationC I R R U S BRAKES DESCRIPTION
BRAKES. DESCRIPTION The brake system consists of a single disc brake assembly on each main landing gear wheel, master cylinder for each rudder pedal, hydraulic fluid reservoir, parking brake, and associated
More informationCIRRUS AIRPLANE MAINTENANCE MANUAL MODELS SR22 AND SR22T CHAPTER 28-00: FUEL GENERAL. Fuel 28-00: FUEL. 1. General
CIRRUS AIRPLANE MAINTENANCE MANUAL Fuel CHAPTER 28-00: GENERAL 28-00: 1. General This chapter contains information on the storage, distribution, and indicating components of the fuel system. The engine
More informationZODIAC 601 XL. Trim the outboard corner of the front flange of the center spar 6W4-1. Corner should not touch the side of the cabin floor skin 6B10-1.
Trim the outboard corner of the front flange of the center spar 6W4-1. Corner should not touch the side of the cabin floor skin 6B10-1. Tape the side skins to the cabin floor skin (area in front of the
More informationIn-Flight Entertainment System
GENERAL In-Flight Entertainment System 44-20: IN-FLIGHT ENTERTAINMENT SYSTEM 1. General This chapter describes the systems, units, and components which provide entertainment to the passengers with music,
More informationCIRRUS SR2X SB 2X R2. Service Bulletin. Issued: Revised: June 26, 2012 July 31, 2012
CIRRUS SR2X Service Bulletin Number: Issued: Revised: June 26, 2012 SNS SUBJECT: 57-40 ATTACH FITTINGS - Lower Landing Gear Attach Bracket Torque 1. COMPLIANCE Mandatory: Cirrus Design considers this Service
More informationTUBES, HOSES, AND FITTINGS
TUBES, HOSES, AND FITTINGS 1. DESCRIPTION This section contains instructions and specifications for aircraft system plumbing and fittings. Page 1 2. MAINTENANCE PRACTICES A. Ice Protection System Compression
More informationCIRRUS AIRPLANE MAINTENANCE MANUAL
CIRRUS AIRPLANE MAINENANCE MANUAL DISRIUION. DESCRIPION his section describes the maintenance practices of that portion of the ignition system which conducts high-voltage electricity from the magnetos
More informationPage: REV 1: In Step 4 "a minimum of 1/16 [1.6 mm] gap" was "an approximately 1/16 [1.6 mm] gap."
14401 Keil Road NE, Aurora, Oregon, USA 97002 PHONE 503-678-6545 FAX 503-678-6560 www.vansaircraft.com info@vansaircraft.com Service Letters and Bulletins: www.vansaircraft.com/public/service.htm REVISION
More informationStorage. 1. General. A. Fuel Storage System
CIRRUS AIRPLANE MAINTENANCE MANUAL Storage CHAPTER 28-10: STORAGE GENERAL 28-10: STORAGE 1. General A. Fuel Storage System The fuel storage system consists primarily of a vented integral 47.5-gallon (180-liters)
More informationMANPOWER REQUIREMENTS
CIRRUS SF5X Service Bulletin Number: Issued: Revised: 09 Aug 208 SNS SUBJECT: 25-0 CABIN - Armrest Installation. COMPLIANCE Optional: Accomplishment of this Service Bulletin is at the owner s option. This
More informationStorage. 1. General. A. Fuel Storage System
Storage GENERAL 28-10: STORAGE 1. General A. Fuel Storage System The fuel storage system consists primarily of a vented integral 149.25-gallon (1009-liter) capacity main fuel tank in each wing, an integral
More informationFlight Environmental Systems
CIRRUS AIRPLANE MAINTENANCE MANUAL Flight Environmental Systems CHAPTER 34-0: FLIGHT ENVIRONMENTAL SYSTEMS GENERAL 34-0: FLIGHT ENVIRONMENTAL SYSTEMS. General This section covers that portion of the system
More informationUnscheduled Maintenance Checks
CIRRUS AIRPLANE MAINTENANCE MANUAL CHAPTER 5-50: UNSCHEDULED MAINTENANCE CHECKS GENERAL Unscheduled Maintenance Checks 5-50: UNSCHEDULED MAINTENANCE CHECKS 1. General The following describes those maintenance
More information2000 SERIES SPEEDBRAKE INSTALLATION MANUAL PA28/PA32 STC # SA00762SE
INSTALLATION REPORT NO. 08067 Serial Number PRECISE FLIGHT, INC. 800-547-2558 2000 SERIES SPEEDBRAKE INSTALLATION MANUAL PA28/PA32 STC # SA00762SE NOTE: READ THESE DIRECTIONS BEFORE STARTING! CHECK FOR
More informationperformance S T O L Installation Instructions Manual No. PSTOL-013 Double Slotted Flaps for Piper PA-18 Series Aircraft
performance S T O L Installation Instructions Manual No. PSTOL-013 Double Slotted Flaps for Piper PA-18 Series Aircraft 1 This Page Intentionally Left Blank 2 Record of Revisions Rev Level Date Page By
More informationSeabee Annual Inspection Procedures
Procedures Due to the wide variety of Seabee s flying out there, these procedures should be modified to fit YOUR Seabee. Make sure that all AD s are complied with as well as any required Service Bulletins
More informationCIRRUS AIRPLANE MAINTENANCE MANUAL
MODEL SR FLIGHT ENVIRONMENTAL SYSTEMS. DESCRIPTION This section covers that portion of the system which senses environmental conditions and uses the data to influence navigation of the airplane. This includes
More informationSERVICE BULLETIN REVISION TRANSMITTAL
REVISION TRANSMITTAL This sheet transmits Revision 1 to, which: A. Rearranges the sub-steps in Step 5 for better flow. NOTE: There are no technical changes in Step 5. B. Adds Steps 6 thru 9 to the Accomplishment
More informationCIRRUS AIRPLANE MAINTENANCE MANUAL
MODEL SR0 FLIGHT ENVIRONMENTAL SYSTEMS. DESCRIPTION This section covers that portion of the system which senses environmental conditions and uses the data to influence navigation of the airplane. This
More informationREVISION LIST CHAPTER 6: AILERON CONTROLS
REVISION LIST CHAPTER 6: The following list of revisions will allow you to update the Legacy construction manual chapter listed above. Under the Action column, R&R directs you to remove and replace the
More informationWHEELS 1. DESCRIPTION A.
WHEELS 1. DESCRIPTION A. Main Wheels Serials 22-0002 thru 22-4045 before SB2X-32-21, 22T-0001 thru 22T-0689 before SB2X-32-21: The main wheels are of aluminum construction and designed to be used with
More informationDetroit Speed, Inc. Rear QUADRAlink Conversion Kit Camaro/Firebird P/N:
Detroit Speed, Inc. Rear QUADRAlink Conversion Kit 1982-92 Camaro/Firebird P/N: 041721 The Detroit Speed Inc. QUADRAlink Conversion Kit, eliminates the factory torque arm configuration. It features no-compromise
More informationSCION xa 2004 SATELLITE RADIO TUNER Section I Installation Preparation
Section I Installation Preparation Part Number: PT546 52040 Section I Installation Preparation Kit Contents Item # Quantity Reqd. Description 1 1 Satellite Tuner 2 1 Ground Cable 3 1 Tuner Cable 4 2 Tuner
More informationINTEGRATED ENGINE INSTRUMENT SYSTEMS
All INTEGRATED ENGINE INSTRUMENT SYSTEMS. DESCRIPTION This section describes that portion of the engine indicating system which is used to analyze engine performance, temperature, and condition. Serials
More informationAileron Pulley Shield ICA Supplement
CESSNA AIRCRAFT COMPANY AIRCRAFT DIVISION WICHITA, KANSAS 67277 Aileron Pulley Shield ICA Supplement MODEL NO: 510 SUPPLEMENT NO: ICA-510-27-00002 SUPPLEMENT DATE: 05/18/2010 PREPARED BY: CHECKED BY: APPROVED
More informationSCION xb 2004 SATELLITE RADIO TUNER Section I Installation Preparation
Section I Installation Preparation Part Number: PT546 52040 Section I Installation Preparation Kit Contents Item # Quantity Reqd. Description 1 1 Satellite Tuner 2 1 Ground Cable 3 1 Tuner Cable 4 2 Tuner
More informationMANDATORY SERVICE BULLETIN NO. MSB /1
DAI MSB-42-042/1 Page 1 of 4 08-Aug-2007 MANDATORY SERVICE BULLETIN NO. MSB-42-042/1 SUPERSEDES MSB-42-042 I TECHNICAL DETAILS I.1 Category Mandatory I.2 Airplanes Affected Type: DA 42 Serial Numbers:
More informationCIRRUS AIRPLANE MAINTENANCE MANUAL
1. GENERAL This chapter contains information on the storage, distribution, and indicating components of the fuel system. The engine is supplied with fuel drawn out of the left or right integral fuel tank
More informationInstallation Guide. Stowe Cargo Management System. Table of Contents
Installation Guide Stowe Cargo Management System Table of Contents 1. Pre-Installation (Page 2) a. Notes, Installation Kit contents & Tools needed 2. How to Install the Stowe Cargo Management System (Pages
More informationPARAVION TECHNOLOGY, INC AIRWAY AVENUE FT. COLLINS, COLORADO 80524
PARAVION TECHNOLOGY, INC. 2001 AIRWAY AVENUE FT. COLLINS, COLORADO 80524 DOCUMENT NO. INSTALLATION INSTRUCTIONS BELL 206A/B/L/L1/L3/L4 HELICOPTER MODELS Page i Rev. H, 02/06/06 REVISIONS REV. DATE DESCRIPTION
More informationEFFECTIVITY Serial Numbers thru , 698
Conquest TITLE AILERON HINGE BRACKET REPLACEMENT EFFECTIVITY Model Serial Numbers 441 441-0001 thru 441-0349, 698 DESCRIPTION To install stainless-steel aileron hinge brackets as a replacement for aluminum
More informationINSTALLATION INSTRUCTIONS DODGE DAKOTA 2 KIT # 682 (2WD), 692 (4WD) 3 KIT # 683 (2WD), 693 (4WD)
INSTALLATION INSTRUCTIONS 1997-1999 DODGE DAKOTA 2 KIT # 682 (2WD), 692 (4WD) 3 KIT # 683 (2WD), 693 (4WD) Installation of a Performance Accessories body lift kit will change the vehicle s center of gravity
More informationPage: REV 3: Add drill and tap information to Figure 4 DRILL #3, TAP 1/4-28 BOTH ENDS.
REVISION DESCRIPTION: 1) Page: 32-03 MEMO: Step 4 should not be bold. Fix WD-1213 callout in Figure 3. Page: 32-04 REV 3: Add drill and tap information to Figure 4 DRILL #3, TAP 1/4-28 BOTH ENDS. Add make
More informationI. Before starting installation
5. Park the vehicle on a clean, dry, flat, level surface and block the tires so the vehicle cannot roll in either direction. A. Disconnect battery cables 1. Disconnect the negative cable first, then the
More informationPARTS TOOLS. Set Screw. Washer (2) Blue Bushing (2) Black Bushing (2) B&M Short Throw Shifter. Jam Nut Grease. Retaining Ring (2) Insert (2)
Installation Instructions SHORT THROW SHIFTER Fits: Porsche Boxter, Boxter S, 911, 996 Cayman & Cayman S models See Application Guide for specific year ranges and engine sizes Catalog # 45135 WORK SAFELY!
More informationThe RICON Eclipse F8000 (A) Series Export Use Wheelchair and Standee Lift is installed in a
II. INSTALLATION TABLE OF CONTENTS The RICON Eclipse F8000 (A) Series Export Use Wheelchair and Standee Lift is installed in a cassette mounted to the underside of the vehicle and behind the bottom step
More informationWARNING TAKE NOTE OF THE FOLLOWING: THIS PRODUCT MUST BE INSTALLED EXACTLY AS PER THESE INSTRUCTIONS USING ONLY THE HARDWARE SUPPLIED.
ARB WINCH/NONWINCH BUMPER TO SUIT TOYOTA HJ100 IFS PRODUCT No. 3913140 5100050 Top Tube Kit 5100160 Buffer Kit With hole (required when fitting Top Tube) 5100170 Buffer Kit With no hole Fitting Kit No.
More informationFastener Identification And Torque Data
CIRRUS AIRPLANE MAINTENANCE MANUAL CHAPTER 20-60: FASTENER IDENTIFICATION AND TORQUE DATA GENERAL Fastener Identification And Data 20-60: FASTENER IDENTIFICATION AND TORQUE DATA 1. General This section
More informationCIRRUS AIRPLANE MAINTENANCE MANUAL
STORAGE 1. DESCRIPTION A. Fuel Storage System - Serials 1005 thru 1885 The fuel storage system consists primarily of a vented integral 30.3-gallon (114.5-liters) capacity fuel tank in each wing, a fuel
More information