Pitch Control and Trim

Size: px
Start display at page:

Download "Pitch Control and Trim"

Transcription

1 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 items such as pitch system rigging, torque tube, cables and push rods, pulleys and bellcranks, pitch trim system, pitch trim servo, and pitch relays. For pitch servo autopilot, see GFC 700 Automated Flight Control System section of Autoflight. (Refer to 22-0) For ruddervator flight surfaces, see Ruddervator section of Stabilizers. (Refer to 55-20) A. Pitch Control System Pitch control motion is operated from a side stick control located on either side of the cockpit. The side stick rotates about a pivot on the side stick tube. Each side stick is mounted via a short arm to a rotary input. Forward and aft movement of either side stick is mechanically transmitted by push rods and bellcranks aft to the mixer. Two push rods connect the mixer to the ruddervator surfaces. The pitch control system utilizes a bellcrank connected by a shaft (shared with the yaw control system) mounted directly to the mixer mount shelf on the drag link bulkhead. Fixed control stops at the mixer bellcrank limit control surface travel. The mixer assembly is located within the rear fuselage. One push rod actuates the pitch portion of the mixer. Two push rods connect the mixer to the ruddervator surfaces. The mixer includes a pitch sector (push rod) and multiple links and levers swiveling on a vertical shaft. Fixed control stops at the rudder empennage bellcrank limit control surface travel. The mixer assembly is used to route the yaw system control cables and pitch push rods. For maintenance practices pertinent to the mixer assembly, see Yaw Control and Trim section of Flight Controls. (Refer to 27-20) The ruddervators deflect +20 up and -5 down for pitch action. Deflections are added and subtracted irrespective of yaw actuation. B. Pitch Trim System Pitch trim is controlled from a four-way hat switch mounted to the top of each side stick control or alternatively from a mechanical trim wheel mounted to the center console. Pitch trim is provided by two tabs attached to the inboard trailing edge of both ruddervators via an upper surface mounted piano hinge (full length). Pitch trim is controlled by a mechanical trim wheel or by an electrical servomotor which drive dual jack screw-type linear actuators mounted within each V-tail stabilizer surface. Dual push rods connect both actuators to the 2 Dec 206

2 GENERAL tab surface. Motion and force is transferred from the trim wheel to the actuators via cables and pulleys. The servomotor is located within the cable loop. Trim tab deflections are between +5 up and -2 down. Trim position is provided from the left cable driven actuator to a pitch trim position indicator located on the upper right side of the panel. A system rigging Inspection/Check must be performed after loosening any flight control cable to ensure proper control surface operation. Refer to the appropriate control system s rigging procedures for the Inspection/Check maintenance practices. Pitch trim adjustment is achieved by changing the deflection angle of the pitch trim tab. For maintenance practices pertinent to the pitch trim tab, see Ruddervator section of Stabilizers. (Refer to 55-20) 2 2 Dec 206

3 2. Maintenance Practices A system rigging Inspection/Check must be performed after loosening any flight control cable to ensure proper control surface operation. Refer to the appropriate control system s rigging procedures for the Inspection/Check maintenance practices. A. Pitch Control System (See Figure ) (See Figure ) (See Figure ) NOTE For pitch control system color-coded identification refer to Chapter (Refer to 20-90) () Removal - Pitch System Push Rods (Flight Controls) (a) Set BAT, BAT 2, GEN, and GEN 2 switches to OFF positions. (b) Pull AP SERVOS, AP CTRL, STICK SHAKER, AUTOTHROTTLE, PITCH TRIM, ROLL (c) Remove crew seats. (Refer to 25-0) (d) Remove LH and RH outer instrument trim. (Refer to 25-0) (e) Remove LH and RH forward center console trim. (Refer to 25-0) (f) Remove center console trim. (Refer to 25-0) (g) Remove MFD. (Refer to 3-60) (h) Remove carpet and access panel CF2C. (Refer to 6-00) (i) At console, remove LH and RH pitch push rod #2. Remove cotter pin, nut, washers, and bolt securing pitch push rod #2 to side stick control pitch stop. 2 Remove cotter pin, nut, washers, and bolt securing pitch push rod #2 to outboard pitch torque tube clip (pitch bellcrank #). Remove pitch push rod #2 from airplane. 3 Repeat at opposite side. (j) At console, remove pitch push rod #3. Remove cotter pin, nut, washers, and bolt securing pitch push rod #3 to mid pitch torque tube clip (pitch bellcrank #2). 2 Remove cotter pin, nut, washers, and bolt securing pitch push rod #3 to pitch bellcrank #3. Remove pitch push rod #3 from airplane. 3 9 Jul 208

4 (2) Installation - Pitch System Push Rods (Flight Controls) CAUTION Tighten all push rod attaching hardware by hand. Do not install cotter pins until system rigging is completed. (a) At console, install pitch push rod #3. Position and secure pitch push rod #3 to pitch bellcrank #3 with bolt, washers, and nut. 2 Position and secure pitch push rod #3 to mid pitch torque tube clip (pitch bellcrank #2) with bolt, washers, and nut. (b) At console, install LH and RH pitch push rod #2. Position and secure pitch push rod #2 to outboard pitch torque tube clip (pitch bellcrank #) with bolt, washers, and nut. 2 Position and secure pitch push rod #2 to side stick control pitch stop with bolt, washers, and nut. 3 Repeat at opposite side. (c) Perform Adjustment/Test - Pitch Control System Rigging. (Refer to 27-30) (d) Install new cotter pins for all unfastened push rod attach fittings and safety wire as required. (Refer to 20-50) (e) Install access panel CF2C, and carpet. (Refer to 6-00) (f) Install MFD. (Refer to 3-60) (g) Install center console trim. (Refer to 25-0) (h) Install LH and RH forward center console trim. (Refer to 25-0) (i) Install LH and RH outer instrument trim. (Refer to 25-0) (j) Install crew seats. (Refer to 25-0) (k) Reset AP SERVOS, AP CTRL, STICK SHAKER, AUTOTHROTTLE, PITCH TRIM, ROLL (3) Removal - Pitch System Bellcranks (Flight Controls) (a) Set BAT, BAT 2, GEN, and GEN 2 switches to OFF positions. (b) Pull AP SERVOS, AP CTRL, STICK SHAKER, AUTOTHROTTLE, PITCH TRIM, ROLL (c) Remove crew seats. (Refer to 25-0) (d) Remove LH and RH outer instrument trim. (Refer to 25-0) (e) Remove LH and RH forward center console trim. (Refer to 25-0) 4 2 Dec 206

5 (f) Remove center console trim. (Refer to 25-0) (g) Remove MFD. (Refer to 3-60) (h) Remove carpet and access panel CF2C. (Refer to 6-00) (i) At side stick control assembly, remove pitch torque tube (pitch bellcrank # - outboard clips, and #2 - mid clip). Remove cotter pins, nuts, washers, and bolts securing pitch torque tube to outboard mounting brackets. Remove pitch torque tube from airplane. (j) At console, remove pitch bellcrank #3. Remove cotter pin, nut, washer, and bolt securing pitch bellcrank #3 to LH cabin intercostal row #. Remove roll bellcrank #3 from airplane. (4) Installation - Pitch System Bellcranks (Flight Controls) CAUTION Tighten all push rod attaching hardware by hand. Do not install cotter pins until system rigging is completed. (a) At console, install pitch bellcrank #3. Position and secure pitch bellcrank #3 to LH cabin intercostal row # with bolt, washer, nut, and new cotter pin. (b) At side stick control assembly, install pitch torque tube (pitch bellcrank # - outboard clips, and #2 - mid clip). Position and secure pitch torque tube to outboard mounting brackets with bolts, washers, nuts, and new cotter pins. (c) Perform Adjustment/Test - Pitch Control System Rigging. (Refer to 27-30) (d) Install new cotter pins for all unfastened push rod attach fittings and safety wire as required. (Refer to 20-50) (e) Install access panel CF2C, and carpet. (Refer to 6-00) (f) Install MFD. (Refer to 3-60) (g) Install center console trim. (Refer to 25-0) (h) Install LH and RH forward center console trim. (Refer to 25-0) (i) Install LH and RH outer instrument trim. (Refer to 25-0) (j) Install crew seats. (Refer to 25-0) (k) Reset AP SERVOS, AP CTRL, STICK SHAKER, AUTOTHROTTLE, PITCH TRIM, ROLL 5 2 Dec 206

6 (5) Removal - Pitch Push Rod Pressure Seal (Cabin) (a) Set BAT, BAT 2, GEN, and GEN 2 switches to OFF positions. (b) Pull AP SERVOS, AP CTRL, STICK SHAKER, AUTOTHROTTLE, PITCH TRIM, ROLL (c) Remove crew seats. (Refer to 25-0) (d) Remove carpet and access panels CF2C, CF3C, and FBC. (Refer to 6-00) (e) At access panel CF3C hole, remove cotter pin, nut, washer, and bolt securing pitch push rod #5 to pitch bellcrank #4. (f) At access panel CF3C hole, disassemble and remove push rod pressure seal. Remove safety wire from bolts securing linkages to half bushing assembly and tube adapter. 2 Remove bolts, washers, and bushings securing linkages to half bushing assembly and tube adapter. Remove linkages from airplane. 3 Gently slide half bushing assembly out from tube. 4 Remove bolts, washers, nuts, and large o-ring from half bushings. Remove half bushings from airplane. 5 Gently remove large and small o-rings from push rod. 6 Remove tube from push rod. (g) At access panel FBC hole, remove safety wire and bolts securing tube adapter to airplane. (h) At access panel CF3C hole, gently pry tube adapter form aircraft structure and remove adapter from push rod seal bracket. (i) Remove o-ring from adapter. (6) Installation - Pitch Push Rod Pressure Seal (Cabin) CAUTION Prior to installation of the pressure seal, apply grease to all o-rings and o-ring grooves, the inner surface of the tube, and to the outside diameter of the link bushings. Apply grease liberally to all indicated locations. Do not apply grease to linkage retention bolts and fuselage mount holes. (a) Acquire necessary tools, equipment, and supplies. Description P/N or Spec. Supplier Purpose Grease, Aeroshell 22 ASG 22 Aeroshell Lubricate seals. 6 9 Jul 208

7 (b) (c) If installing new push rods, paint push rod clevises and bellcranks appropriate color. (Refer to 20-90) Install pitch push rod #5 pressure seal. Temporarily install tube adapter to aircraft structure and secure with bolts. 2 Install large o-ring to tube adapter. 3 At access panel CF3C hole, assemble and install push rod pressure seal. a) Apply grease to inner surface of tube, approximately 0.50 inch (2.70 mm) from each end. b) Install tube to tube adapter. c) Gently install small o-ring to push rod. NOTE Insert large o-ring onto tube prior to installing half bushings. After installation of half bushings, ensure the half bushing assembly moves freely on the push rod. d) Install half bushings around small o-ring and secure with bolts, washers, and nuts. e) Install large o-ring to half bushing assembly. f) Apply grease to push rod portion extending into pressure vessel. g) Gently insert half bushing assembly to tube. h) Reapply grease to push rod portion extending into pressure vessel. i) Position linkages to half bushing assembly and tube adapter and secure with bushings, washers, bolts, and safety wire. (Refer to 20-50) 4 At access panel CF3C hole, position pitch push rod #5 to pitch bellcrank #4 and secure with bolt, washer, and nut. (d) Perform Adjustment/Test - Pitch Control System Rigging. (Refer to 27-30) (e) Install new cotter pins for all unfastened push rod attach fittings and safety wire as required. (Refer to 20-50) (f) At access panel FBC hole, remove bolts securing tube adapter to airplane. Remove adapter from airplane. (g) At access panel CF3C hole, prepare aircraft structure for bonding tube adapter. NOTE Fay seal tube adapter and wet install bolts. (h) Wet install tube adapter to aircraft structure and secure with washers and bolts. Torque bolts 8.8 to 0.8 inch pounds (.0 to.2 Nm). (i) Install access panels CF2C and CF3C, FBC, and carpet. (Refer to 6-00) 7 9 Jul 208

8 (j) Install crew seats. (Refer to 25-0) (k) Reset AP SERVOS, AP CTRL, STICK SHAKER, AUTOTHROTTLE, PITCH TRIM, ROLL (7) Removal - Pitch System Push Rods (Forward Cabin) (a) Set BAT, BAT 2, GEN, and GEN 2 switches to OFF positions. (b) Pull AP SERVOS, AP CTRL, STICK SHAKER, AUTOTHROTTLE, PITCH TRIM, ROLL (c) Remove crew seats. (Refer to 25-0) (d) Remove carpet and access panels CF2C and CF3C. (Refer to 6-00) (e) Remove access panels FBC and FB4L. (Refer to 6-00) (f) At cabin access holes, remove pitch push rod #4. Remove cotter pin, nut, washers, and bolt securing pitch push rod #4 to pitch bellcrank #3. 2 Remove cotter pin, nut, washers, and bolt securing pitch push rod #4 to pitch bellcrank #4. Remove pitch push rod #4 from airplane. NOTE It is not necessary to remove pressure seal tube adapter to remove pitch push rod #5. (g) Remove pitch push rod #5 pressure seal. (Refer to 27-30) (h) At cabin and fuselage belly access holes, remove pitch push rod #5. At access panel CF3C hole, remove cotter pin, nut, washer, and bolt securing pitch push rod #5 to pitch bellcrank #4. 2 At access panel FBC hole, remove cotter pin, nut, washer, and bolt securing pitch push rod #5 to pitch bellcrank #5. Remove pitch push rod #5 from airplane. (i) At fuselage belly access holes, remove pitch push rod #6. Remove cotter pin, nut, washers, and bolt securing pitch push rod #6 to pitch bellcrank #5. 2 Remove cotter pin, nut, washers, and bolt securing pitch push rod #6 to pitch bellcrank #6. Remove pitch push rod #6 from airplane. 8 9 Jul 208

9 (8) Installation - Pitch System Push Rods (Forward Cabin) CAUTION Tighten all push rod attaching hardware by hand. Do not install cotter pins until system rigging is completed. (a) If installing new push rods, paint push rod clevises and bellcranks appropriate color. (Refer to 20-90) (b) At fuselage belly access holes, install pitch push rod #6. Position and secure pitch push rod #6 to pitch bellcrank #6 with bolt, washers, and nut. 2 Position and secure pitch push rod #6 to pitch bellcrank #5 with bolt, washers, and nut. (c) Install pitch push rod #5 pressure seals. (Refer to 27-30) (d) At cabin and fuselage belly access holes, install pitch push rod #5: At access panel FBC hole, position pitch push rod #5 to pitch bellcrank #5 and secure with bolt, washer, and nut. 2 At access panel CF3C hole, position pitch push rod #5 to pitch bellcrank #4 and secure with bolt, washer, and nut. (e) At cabin access holes, install pitch push rod #4. Position and secure pitch push rod #4 to pitch bellcrank #4 with bolt, washers, and nut. 2 Position and secure pitch push rod #4 to pitch bellcrank #3 with bolt, washers, and nut. (f) Perform Adjustment/Test - Pitch Control System Rigging. (Refer to 27-30) (g) Install new cotter pins for all unfastened push rod attach fittings and safety wire as required. (Refer to 20-50) (h) Install access panels FBC and FB4L. (Refer to 6-00) (i) Install access panels CF2C and CF3C, and carpet. (Refer to 6-00) (j) Install crew seats. (Refer to 25-0) (k) Reset AP SERVOS, AP CTRL, STICK SHAKER, AUTOTHROTTLE, PITCH TRIM, ROLL (9) Removal - Pitch System Bellcranks (Forward Cabin) (a) (b) Set BAT, BAT 2, GEN, and GEN 2 switches to OFF positions. Pull AP SERVOS, AP CTRL, STICK SHAKER, AUTOTHROTTLE, PITCH TRIM, ROLL 9 9 Jul 208

10 (c) Remove crew seats. (Refer to 25-0) (d) Remove carpet and access panels CF2C and CF3C. (Refer to 6-00) (e) Remove access panels FBC and FB4L. (Refer to 6-00) (f) At cabin access holes, remove pitch bellcrank #4. Remove cotter pin, nut, washer, and bolt securing pitch bellcrank #4 to LH intercostal weldment #. Remove roll bellcrank #4 from airplane. (g) At fuselage belly access hole, remove pitch bellcrank #5. Remove cotter pin, nut, washer, and bolt securing pitch bellcrank #5 to LH intercostal weldment #3. Remove roll bellcrank #5 from airplane. (h) At fuselage belly access hole, remove pitch bellcrank #6. Remove cotter pin, nut, washer, and bolt securing pitch bellcrank #6 to bracket on LH center longeron. Remove roll bellcrank #6 from airplane. (0) Installation - Pitch System Bellcranks (Forward Cabin) CAUTION Tighten all push rod attaching hardware by hand. Do not install cotter pins until system rigging is completed. (a) At fuselage belly access hole, install pitch bellcrank #6. Position and secure pitch bellcrank #6 to bracket on LH center longeron with bolt, washer, nut, and new cotter pin. (b) At fuselage belly access hole, install pitch bellcrank #5. Position and secure pitch bellcrank #5 to LH intercostal weldment #3 with bolt, washer, nut, and new cotter pin. (c) At cabin access holes, install pitch bellcrank #4. Position and secure pitch bellcrank #4 to LH intercostal weldment # with bolt, washer, nut, and new cotter pin. (d) Perform Adjustment/Test - Pitch Control System Rigging. (Refer to 27-30) (e) Install new cotter pins for all unfastened push rod attach fittings and safety wire as required. (Refer to 20-50) (f) Install access panels FBC and FB4L. (Refer to 6-00) (g) Install access panels CF2C and CF3C, and carpet. (Refer to 6-00) (h) Install crew seats. (Refer to 25-0) (i) Reset AP SERVOS, AP CTRL, STICK SHAKER, AUTOTHROTTLE, PITCH TRIM, ROLL 0 9 Jul 208

11 () Removal - Pitch System Push Rods (Aft Cabin) (a) Set BAT, BAT 2, GEN, and GEN 2 switches to OFF positions. (b) Pull AP SERVOS, AP CTRL, STICK SHAKER, AUTOTHROTTLE, PITCH TRIM, ROLL (c) Remove access panels FB4L and FB5L. (Refer to 6-00) (d) Remove access panel E2R. (Refer to 6-00) (e) At fuselage belly access holes, remove pitch push rod #7. Remove cotter pin, nut, washers, and bolt securing pitch push rod #7 to pitch bellcrank #6. 2 Remove cotter pin, nut, washers, and bolt securing pitch push rod #7 to pitch bellcrank #7. Remove pitch push rod #7 from airplane. (f) At fuselage belly and empennage access holes, remove pitch push rod #8. Remove cotter pin, nut, washers, and bolt securing pitch push rod #8 to pitch bellcrank #7. 2 Remove cotter pin, nut, washers, and bolt securing pitch push rod #8 to pitch bellcrank on mixer assembly. Remove pitch push rod #8 from airplane. (2) Installation - Pitch System Push Rods (Aft Cabin) CAUTION Tighten all push rod attaching hardware by hand. Do not install cotter pins until system rigging is completed. (a) At fuselage belly and empennage access holes, install pitch push rod #8. Position and secure pitch push rod #8 to pitch bellcrank on mixer assembly with bolt, washers, and nut. 2 Position and secure pitch push rod #8 to pitch bellcrank #7 with bolt, washers, and nut. (b) At fuselage belly access holes, install pitch push rod #7. Position and secure pitch push rod #7 to pitch bellcrank #7 with bolt, washers, and nut. 2 Position and secure pitch push rod #7 to pitch bellcrank #6 with bolt, washers, and nut. (c) Perform Adjustment/Test - Pitch Control System Rigging. (Refer to 27-30) (d) Install new cotter pins for all unfastened push rod attach fittings and safety wire as required. (Refer to 20-50) 9 Jul 208

12 (e) Install access panel E2R. (Refer to 6-00) (f) Install access panels FB4L and FB5L. (Refer to 6-00) (g) Reset AP SERVOS, AP CTRL, STICK SHAKER, AUTOTHROTTLE, PITCH TRIM, ROLL (3) Removal - Pitch System Bellcrank (Aft Cabin) (a) Set BAT, BAT 2, GEN, and GEN 2 switches to OFF positions. (b) Pull AP SERVOS, AP CTRL, STICK SHAKER, AUTOTHROTTLE, PITCH TRIM, ROLL (c) Remove access panel E2R. (Refer to 6-00) (d) At empennage access hole, remove pitch bellcrank #7. Remove cotter pin, nut, washer, and bolt securing pitch bellcrank #6 to bracket on LH center longeron. Remove roll bellcrank #6 from airplane. (4) Installation - Pitch System Bellcrank (Aft Cabin) CAUTION Tighten all push rod attaching hardware by hand. Do not install cotter pins until system rigging is completed. (a) At empennage access hole, install pitch bellcrank #7. Position and secure pitch bellcrank #7 to bracket on LH center longeron with bolt, washer, nut, and new cotter pin. (b) Perform Adjustment/Test - Pitch Control System Rigging. (Refer to 27-30) (c) Install new cotter pins for all unfastened push rod attach fittings and safety wire as required. (Refer to 20-50) (d) Install access panel E2R. (Refer to 6-00) (e) Reset AP SERVOS, AP CTRL, STICK SHAKER, AUTOTHROTTLE, PITCH TRIM, ROLL 2 9 Jul 208

13 Figure : Pitch Control System SIDE STICK ASSEMBLY (REF) LEGEND. Pitch Torque Tube 2. Push Rod #2, LH 3. Push Rod #2, RH 4. Push Rod #3 5. Bellcrank #3 6. Push Rod #4 7. Bellcrank #4 8. Push Rod #5 9. Bellcrank #5 0.Push Rod #6. Bellcrank #6 2. Push Rod #7 3. Bellcrank #7 4. Push Rod #8 5. Ruddervator Push Rod, LH 6. Ruddervator Push Rod, RH 7. Bolt 8. Washer 9. Nut 20. Cotter Pin BELLCRANK (REF) PUSH ROD (REF) Typical Push Rod Installation NOTE Torque nut by hand and do not install cotter pin until system rigging is complete. 3 PITCH/YAW MIXER (REF) RUDDERVATOR TORQUE TUBE (REF) SF50_MM27_ Jul 208

14 Figure ATAIL : Pitch Control System Pressure Seal A RUSH ROD #5 (REF) RUSH ROD SEAL BRACKET (REF) LEGEND. Screw 2. Half Bushing 3. Washer 4. Nut 5. O-Ring 6. Tube 7. Bushing 8. Linkage 9. Bolt 0. Tube Adapter DETAIL A SF50_MM27_ Jul 208

15 (5) Adjustment/Test - Pitch Control System Rigging CAUTION Allow temperature to stabilize for a period of four hours before setting cable tensions. Maintain a inch (7.620 mm) minimum clearance between flight control cables and composite structure. This requirement excludes any composite structure protected by fairleads, rub strips, or grommets. Prior to rigging the pitch system, ensure the system is installed per Installation - Pitch System Push Rods with the following exceptions: ) Specific flight control parts must be color identified. (Refer to 20-90) 2) The ruddervator push rods must not be connected to the ruddervator. 3) Pitch push rod #3 must be disconnected from pitch torque tube (pitch bellcrank #2). 4) Pitch push rod #8 must be disconnected from pitch bellcrank on mixer assembly. 5) The stop bolt threads at each side stick stop must be fully engaged. 6) Do not wet install pressure seals or torque associated hardware prior to rigging. 7) Lock out yaw and roll systems. (Refer to 27-20) (Refer to 27-0) NOTE Prior to rigging the pitch trim system, ensure the system is installed per Installation - Pitch Trim System Cables with the following exceptions: ) Specific flight control parts must be color identified. (Refer to 20-90) 2) No tension in pitch trim cable. 3) Do not wet install pressure seals or torque associated hardware prior to rigging. 4) Lock out pitch and yaw systems. (Refer to 27-30) (Refer to 27-20) (a) Acquire necessary tools, equipment, and supplies. Description P/N or Spec. Supplier Purpose Rigging Lockout Tool Cirrus Aircraft Lock out bellcranks. 3/6-inch Lockout Pin - Any Source Lock out bellcranks. Scale, 2-inch - Any Source Rig ruddervator. 5 9 Jul 208

16 Description P/N or Spec. Supplier Purpose Tensiometer BT-33-75D Kent Moore Determine cable tension. (b) Set BAT, BAT 2, GEN, and GEN 2 switches to OFF positions. (c) Pull AP SERVOS, AP CTRL, STICK SHAKER, AUTOTHROTTLE, PITCH TRIM, ROLL (d) Remove crew seats. (Refer to 25-0) (e) Remove LH and RH outer instrument trim. (Refer to 25-0) (f) Remove LH and RH forward center console trim. (Refer to 25-0) (g) Remove center console trim. (Refer to 25-0) (h) Remove MFD. (Refer to 3-60) (i) Remove carpet and access panel CF2C. (Refer to 6-00) (j) Remove access panel FBC. (Refer to 6-00) (k) Remove access panel E2R. (Refer to 6-00) (l) Remove cotter pins, nuts, washers, and bolts securing ruddervator rod ends to ruddervator bellcranks. (m) Disconnect pitch push rods #3 and #8 as specified. At console, remove cotter pin, nut, washer, and bolt securing pitch push rod #3 to pitch torque tube (pitch bellcrank #2). 2 At access panel E2R hole, remove cotter pin, nut, washer, and bolt securing pitch push rod #8 to pitch bellcrank on mixer assembly. (n) Using rigging lockout tool and pin, lockout each stage in its neutral position at pitch bellcrank sector on mixer, pitch bellcrank #5, and outboard pitch torque tube clip (pitch bellcrank #). (o) Loosen pitch trim system turnbuckles so all cable tension is removed. (p) Adjust pitch push rods #3 and #8. Adjust pitch push rod #8 until it can easily be bolted to the mixer pitch bellcrank, and then secure with bolt, washer, and nut. 2 Adjust pitch push rod #3 until it can easily be bolted to the pitch torque tube bellcrank, and then secure with bolt, washer, and nut. (q) Set pitch deflection. NOTE The correct pitch deflection (TEU 20.0 ±, TED 5.0 ± ) is obtained by measuring perpendicular to the ruddervator hinge line. With full up pitch applied, verify deflection angle is equal to 20.0 ±. 6 9 Jul 208

17 (r) (s) (t) (u) (v) NOTE Adjusting push rod length affects the center location of the pitch deflection. The limits of deflection are not adjustable. It may be necessary to set each side off of nominal to meet tolerance on both sides. 2 To increase deflection angle, lengthen push rod by removing bolt securing rod end to aft ruddervator bellcrank, loosening jam nut, and turning rod end counterclockwise. 3 Shorten push rod for opposite results. 4 Repeat procedure for down pitch travel (deflection angle equal to 5.0 ± ). Set pitch trim deflection. Set the tension of the forward pitch trim chain assembly. 2 Turn the forward assembly in the pitch trim up direction until the center console chain is approximately 0.5 inch from pitch trim pulley #2. 3 Shift the aft pitch trim chain assembly to the full pitch trim up position while holding the forward assembly in the full pitch trim up position. The bottom chain stop should be engaged. 4 Remove the bottom pitch trim push rods and adjust the top pitch trim push rods until the tab deflections are at Check the neutral position, and TEU position (7.0 ± ), of the pitch trim system against the avionics and rigging boards. Reset avionics as necessary 6 Check that the both control surface stops engage prior to the actuator internal stops. If this is not the case, the chain can be shifted one or two links over the actuator sprocket such that both control surface stops engage before the actuator stops. Set pitch trim cable tension. Verify pitch trim cable tension is 30.0 to 40.0 lb (3.6 to 8. kg). Set side stick control neutral position. When the rigged system is deflected by moving the side stick control directly, verify surface stops contact before contact is made at the side stick stops. Verify a gap of 0.05 to inch (0.38 to.397 mm) exists between the mixer pitch stops and the corresponding pitch stop pad in the cockpit. If not, adjust pitch stops at mixer assembly and/or side stick as required. 2 Repeat procedure on RH side. Install new cotter pins for all unfastened push rod attach fittings and safety wire as required. (Refer to 20-50) Remove rigging lockout tool and pin from pitch bellcrank sector on mixer, pitch bellcrank #5, and outboard pitch torque tube clip (pitch bellcrank #). 7 9 Jul 208

18 CAUTION Applying aft motion to side stick control should deflect rudder trailing edge down. If this is not true, system is improperly rigged. The system MUST BE RIGGED CORRECTLY. Check for crossed or wrapped cables and verify color identification is correct. (w) Verify application of down pitch deflects ruddervator trailing edge down. (x) Install pressure seals. Wet install seal assemblies to the cabin structure. (Refer to 20-0) 2 Center each seal on their respective control push rod / cable to allow full range of motion with minimal flight control interference. 3 Remove any sealant that may come in contact with the flight control push rods / cables. 4 Install and torque seal attachment hardware. (y) Perform Inspection/Check - Pitch Down Spring. (Refer to 27-30) (z) Perform Adjustment/Test - Pitch Servo Mount (GSM 900) Bridle Cable Tension. (Refer to 22-0) (aa) Perform Inspection/Check - Pitch Control System Rigging. (Refer to 27-30) (ab) Perform Inspection/Check - Pitch Trim Control System Rigging. (Refer to 27-30) (ac) Install access panel E2R. (Refer to 6-00) (ad) Install access panel FBC. (Refer to 6-00) (ae) Install carpet and access panel CF2C. (Refer to 6-00) (af) Install MFD. (Refer to 3-60) (ag) Install center console trim. (Refer to 25-0) (ah) Install LH and RH forward center console trim. (Refer to 25-0) (ai) Install LH and RH outer instrument trim. (Refer to 25-0) (aj) Install crew seats. (Refer to 25-0) (ak) Reset AP SERVOS, AP CTRL, STICK SHAKER, AUTOTHROTTLE, PITCH TRIM, ROLL (6) Inspection/Check - Pitch Control System Rigging (a) (b) Verify minimum rod end thread engagement up to the witness (sight) hole. Verify proper installation of safety wires and cotter pins on all fasteners and engagement of all jam nuts throughout entire pitch control system. (Refer to 20-50) 8 9 Jul 208

19 (7) Operational Test - Pitch Control System Rigging (a) Acquire necessary tools, equipment, and supplies. Description P/N or Spec. Supplier Purpose Scale, 6-inch - Any Source Rig rudder. (b) Perform Inspection/Check - Ruddervator Gap and Overlap. (Refer to 55-20) (c) Verify ruddervator neutral position remains at 0 ±0.5 with side stick control in neutral position. (d) (e) (f) (g) NOTE The correct ruddervator pitch deflection (TEU 20.0 ±, TED 5.0 ± ) is obtained by measuring perpendicular to the ruddervator hinge line. Verify 20.0 ± up ruddervator deflection angle. Verify 5.0 ± down ruddervator deflection angle. Verify minimum rod end thread engagement up to the witness (sight) hole. Verify proper installation of safety wires and cotter pins on all fasteners and engagement of all jam nuts throughout entire pitch control system. (Refer to 20-50) 9 9 Jul 208

20 Figure : Pitch Control System Rigging ( of 2) A A TEU CHORD LINE TED Pitch Direction TEU TED Deflection Limit 20.0 ± ±.0 SECTION A SF50_MM27_ Jul 208

21 Figure : Pitch Control System Rigging (2 of 2) 4 4 NOTE Push Rod adjustment LEGEND. Rigging Pin 2. Pitch Stop Pad 3. Cockpit Pitch Stop 4. Pitch Surface Stop SF50_MM27_ Jul 208

22 B. Pitch Trim System (See Figure ) (See Figure ) (See Figure ) The pitch trim system cable clevises and turnbuckle ends are marked with blue, yellow, and black paint to allow visual verification of proper pitch system assembly and installation. Description Color Identification All Down Drive(n), Pitch Trim Cable Terminals Bottom of Pitch Trim Stop Bracket All Up Drive(n), Pitch Trim Cable Terminals Top of Pitch Trim Stop Bracket Balance Driven Pitch Trim Cable Clevises Primary Blue Primary Yellow Black () Removal - Pitch Trim System Cables (a) Set BAT, BAT 2, GEN, and GEN 2 switches to OFF positions. (b) Pull AP SERVOS, AP CTRL, STICK SHAKER, AUTOTHROTTLE, PITCH TRIM, ROLL (c) Remove crew seats. (Refer to 25-0) (d) Remove passenger seats. (Refer to 25-0) (e) Remove LH and RH outer instrument trim. (Refer to 25-0) (f) Remove LH and RH forward center console trim. (Refer to 25-0) (g) Remove center console trim. (Refer to 25-0) (h) Remove MFD. (Refer to 3-60) (i) Remove carpet and access panels CF2C and CF3C. (Refer to 6-00) (j) Remove access panels FBC, FB4R, and FB6R. (Refer to 6-00) (k) Remove access panel E2R. (Refer to 6-00) (l) Remove tailcone. (Refer to 53-50) (m) Remove forward pitch trim cable Jul 208

23 (n) NOTE To facilitate cable routing during installation, attach string to end of cables prior to removing from airplane. At cabin access panel CF3C hole, remove turnbuckle from forward pitch trim cable. Route disconnected forward end of cable to console. 2 At console, disengage control chain from pitch trim wheel. 3 At console, remove pulley guard pins from pitch trim pulley gang #, and disengage cables from pulleys. 4 At cabin access panel CF2C hole, remove pulley guard pins from pitch trim pulley gang #2, and disengage cables from pulleys. 5 At access panel FBC hole, remove pulley guard pins from pitch trim pulley gang #3, and disengage cables from pulleys. 6 At access panel FBC hole, remove pulley guard pins from pitch trim pulley gang #4, and disengage cables from pulleys. 7 At access panel FB4R hole, remove nuts, washers, and bolts securing fairleads to bracket on RH wing saddle. 8 At access panel FB6R hole, remove pulley guard pin from pitch trim pulley gang #5, and disengage cables from pulleys. 9 Disengage forward pitch trim cable from pitch trim servo, and route cable forward through pitch trim pulley gangs #5, #4, #3, #2, and # to console. 0 At console, pull forward pitch trim cables through and remove cables from airplane. Remove aft pitch trim cable. NOTE To facilitate cable routing during installation, attach string to end of cables prior to removing from airplane. At pitch trim servo, remove turnbuckle from aft pitch trim cable. 2 At access panel FB4R hole, remove cotter pins, nuts, washers, and bolts securing retainer to pitch stop bracket. 3 Disengage aft pitch trim cable from pitch trim servo, and route cable aft to stabilizer bulkhead. 4 At tailcone opening, remove pulley guard pins from LH, center, and RH pitch trim pulley gang #6, and disengage cables from pulleys. 5 Disengage control cable from LH and RH pitch trim actuators. 6 At tailcone opening, pull aft pitch trim cables through and remove cables from airplane Jul 208

24 (2) Installation - Pitch Trim System Cables CAUTION Maintain a inch minimum clearance between flight control cables and composite structure. (a) (b) (c) If installing new cables, paint turnbuckle ends appropriate color. Install aft pitch trim cable. At tailcone opening, feed aft pitch trim cables through inboard ruddervator ribs to LH and RH pitch trim actuators. 2 Engage control cable to LH and RH pitch trim actuators. 3 Route pitch trim cables through inboard ruddervator ribs to pulley gang #6. 4 At tailcone opening, engage cables to pulleys at LH, center, and RH pitch trim pulley gang #6. 5 At LH, center, and RH pitch trim pulley gang #6, verify cable routing and install pulley guard pins. 6 Route cable forward through stabilizer bulkhead to empennage. 7 Engage pitch trim cable to pitch trim servo. 8 At access panel FB4R hole, position and secure retainer to pitch stop bracket with bolts, washers, nuts, and new cotter pins. 9 At pitch trim servo, install turnbuckles on aft pitch trim cable. Install forward pitch trim cable. At console, feed forward pitch trim cable through pitch trim pulley gangs #, #2, #3, #4, and #5, and route cable aft to pitch trim servo. 2 Engage forward pitch trim cable to pitch trim servo. 3 At pitch trim pulley gang #5, verify cable routing and install pulley guard pin. 4 Position and secure fairleads to bracket on RH wing saddle with bolts, washers, and nuts. 5 At pitch trim pulley gang #4, verify cable routing and install pulley guard pins. 6 At pitch trim pulley gang #3, verify cable routing and install pulley guard pins. 7 At pitch trim pulley gang #2, verify cable routing and install pulley guard pins. 8 At pitch trim pulley gang #, verify cable routing and install pulley guard pins. 9 At console, engage control chain to pitch trim wheel. 0 At cabin access panel CF3C hole, install turnbuckles on forward pitch trim cable Jul 208

25 (d) Perform Adjustment/Test - Pitch Control System Rigging. (Refer to 27-30) (e) Perform Operational Test - Pitch Trim Control System. (Refer to 27-30) (f) Install tailcone. (Refer to 53-50) (g) Install access panel E2R. (Refer to 6-00) (h) Install access panels FBC, FB4R, and FB6R. (Refer to 6-00) (i) Install carpet and access panels CF2C and CF3C. (Refer to 6-00) (j) Install MFD. (Refer to 3-60) (k) Install center console trim. (Refer to 25-0) (l) Install LH and RH forward center console trim. (Refer to 25-0) (m) Install LH and RH outer instrument trim. (Refer to 25-0) (n) Install passenger seats. (Refer to 25-0) (o) Install crew seats. (Refer to 25-0) (p) Reset AP SERVOS, AP CTRL, STICK SHAKER, AUTOTHROTTLE, PITCH TRIM, ROLL (3) Inspection/Check - Pitch Trim Control System Rigging (a) (b) Verify minimum rod end thread engagement up to the witness (sight) hole. Verify proper installation of safety wires and cotter pins on all fasteners and engagement of all jam nuts throughout entire pitch trim control system. (Refer to 20-50) (4) Operational Test - Pitch Trim Control System (a) (b) (c) (d) (e) Verify when pitch trim wheel is turned to trim up, trim tab deflects trailing edge down. Verify when pitch trim wheel is turned to trim down, trim tab deflects trailing edge up. Verify there is no jamming, or excessive friction through full range of motion of trim travel. Ensure sufficient clearance exists between cable ends and turnbuckles, and pulleys and pass-throughs. Ensure mechanical stops on aft chain contact prior to actuator stops engaging Jul 208

26 Figure : Pitch Trim System Cables ( of 2) A8 A9 A2 A4 A5 A6 A7 2 3 A A3 A CONTROL CHAIN (REF) PITCH TRIM WHEEL (REF) PULLEY GANG #4 (REF) 4 PULLEY GANG # (REF) 4 4 PULLEY PULLEY GANG #3 (REF) GANG #2 (REF) A2 A A4 LEGEND. Fwd Pitch Trim Cable 2. Turnbuckle 3. Locking Clip 4. Pulley Guard Pin 5. Screw 6. Washer 7. Bracket 8. Fairlead 9. Nut SF50_MM27_ Jul 208

27 Figure : Pitch Trim System Cables (2 of 2) 4 PULLEY GANG #5 (REF) A5 PITCH TRIM SERVO (REF) A6 3 CENTER PULLEY GANG #6 (REF) A7 RH PULLEY GANG #6 (REF) LH PULLEY GANG #6 (REF) A8 5 6 EL/ER ACCESS (REF) 6 CONTROL CHAIN (REF) 7 A9 LEGEND. Fwd Pitch Trim Cable 2. Turnbuckle 3. Locking Clip 4. Pulley Guard Pin 5. Screw 6. Washer 7. Bracket 8. Fairlead 9. Nut 0. Stiffener Ring. Cable Guard 2. Aft Pitch Trim Cable 3. Cotter Pin 4. Bolt 5. Retainer 6. Pulley Guard 7. Pitch Trim Actuator SF50_MM27_ Jul 208

28 (5) Removal - Pitch Trim Wheel A maintenance check flight must be performed after the installation of a replacement (new or different) pitch trim wheel. (a) Set BAT, BAT 2, GEN, and GEN 2 switches to OFF positions. (b) Pull AP SERVOS, AP CTRL, STICK SHAKER, AUTOTHROTTLE, PITCH TRIM, ROLL (c) Remove crew seats. (Refer to 25-0) (d) Remove LH and RH outer instrument trim. (Refer to 25-0) (e) Remove LH and RH forward center console trim. (Refer to 25-0) (f) Remove center console trim. (Refer to 25-0) (g) Remove MFD. (Refer to 3-60) (h) Remove carpet and access panel CF2C. (Refer to 6-00) (i) At cabin access panel CF3C hole, loosen turnbuckle from forward pitch trim cable. (j) At console, disengage control chain from pitch trim wheel. (k) Remove cotter pin, nut, bushing, washer, and bolt securing pitch trim wheel assembly to center console. Remove pitch trim wheel assembly from airplane. (6) Installation - Pitch Trim Wheel (a) Position pitch trim wheel assembly to center console and secure with bolt, washer, bushing, nut, and new cotter pin. (b) At console, engage control chain to pitch trim wheel. (c) At cabin access panel CF3C hole, tighten turnbuckle to forward pitch trim cable. (d) Perform Operational Test - Pitch Trim Control System. (Refer to 27-30) (e) Install access panel CF2C, and carpet. (Refer to 6-00) (f) Install MFD. (Refer to 3-60) (g) Install center console trim. (Refer to 25-0) (h) Install LH and RH forward center console trim. (Refer to 25-0) (i) Install LH and RH outer instrument trim. (Refer to 25-0) (j) Install crew seats. (Refer to 25-0) (k) Reset AP SERVOS, AP CTRL, STICK SHAKER, AUTOTHROTTLE, PITCH TRIM, ROLL 28 9 Jul 208

29 (7) Removal - Pitch Down Spring (a) Remove LH outer instrument trim. (Refer to 25-0) (b) Disengage lower end of pitch down spring from spring clip on pitch torque tube. (c) Disengage upper end of pitch down spring from eyebolt at cabin skin of forward pressure bulkhead. Remove pitch down spring from airplane. (8) Installation - Pitch Down Spring (a) Engage upper end of pitch down spring to eyebolt at cabin skin of forward pressure bulkhead. (b) Engage lower end of pitch down spring to spring clip on pitch torque tube. (c) Perform Inspection/Check - Pitch Down Spring. (Refer to 27-30) (d) Install LH outer instrument trim. (Refer to 25-0) (9) Inspection/Check - Pitch Down Spring (a) Verify correct pitch control system rigging. (Refer to 27-30) (b) Verify pitch down spring is adjusted such that ruddervators return to full pitch down position, TED, 5.0 ±, when pitch and yaw flight control systems are not actuated Jul 208

30 Figure : Pitch Down Spring CABIN SKIN (REF) A B 7 PITCH DOWN SPRING CLIP (REF) DETAIL B CONTROL CHAIN (REF) DETAIL A LEGEND. Bolt 2. Washer 3. Pitch Trim Wheel 4. Bushing 5. Nut 6. Cotter Pin 7. Spring SF50_MM27_ Jul 208

31 (0) Removal - Pitch Trim Actuator (a) Remove access panel EL and/or ER. (Refer to 6-00) (b) Remove ruddervator. (Refer to 55-20) (c) LH only: Disconnect electrical connector from elevator trim actuator and route harness outboard through grommet. (d) LH only: Remove cable ties securing electrical harness to anchors on upper stabilizer skin. (e) Remove bolts and washers securing pitch trim actuator to aft spar of V-tail stabilizer. Remove pitch trim actuator from airplane. () Installation - Pitch Trim Actuator (a) Position pitch trim actuator to aft spar of V-tail stabilizer and secure with washers and bolts. (b) LH only: Position electrical harness to anchors on upper stabilizer skin and secure with cable ties. (c) LH only: Route harness inboard through grommet and connect electrical connector from elevator trim actuator. (d) Install ruddervator. (Refer to 55-20) (e) Perform Inspection/Check - Pitch Trim Actuator. (Refer to 27-30) (f) Install access panel EL and/or ER. (Refer to 6-00) (2) Inspection/Check - Pitch Trim Actuator (a) Acquire necessary tools, equipment, and supplies. Description P/N or Spec. Supplier Purpose Inclinometer PRO360 Macklanburg Duncan Determine deflection angle. (b) Verify correct pitch system rigging. (Refer to 27-30) (c) Fasten inclinometer to left ruddervator and set at 0. (d) Verify pitch trim actuator is adjusted to hold ruddervators in neutral position ±. 3 9 Jul 208

32 (e) (f) (g) (h) (i) NOTE The correct ruddervator pitch trim deflection (TEU 7.0 ±, TED 8.0 ± ) is obtained by measuring perpendicular to the ruddervator hinge line. Run pitch trim actuator to full up trim position and verify 7.0 ± ruddervator trim deflection indication on MFD. Run pitch trim actuator to full down trim position and verify 8.0 ± ruddervator trim deflection indication on MFD. Remove inclinometer. Verify minimum rod end thread engagement up to the witness (sight) hole. Verify proper installation of safety wires and cotter pins on all fasteners. (Refer to 20-50) 32 9 Jul 208

33 Figure : Pitch Trim System A A Pitch Trim Direction TEU TED Deflection Limit 7.0 ± ±.0 A CHORD LINE TEU TED 2 3 SECTION A 4 LEGEND. Pitch Trim Actuator 2. Bolt 3. Washer 4. Connector DETAIL A SF50_MM27_ Jul 208

34 Intentionally Left Blank 34 9 Jul 208

Yaw Control and Trim. 1. General. A. Yaw Control System. B. Yaw Trim System

Yaw 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 information

CIRRUS AIRPLANE MAINTENANCE MANUAL

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 information

CIRRUS AIRPLANE MAINTENANCE MANUAL

CIRRUS 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 information

Flaps System. 1. General

Flaps System. 1. General 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

More information

CIRRUS AIRPLANE MAINTENANCE MANUAL

CIRRUS 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 information

53-40 ATTACH FITTINGS

53-40 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 information

57-50 FLIGHT SURFACES

57-50 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 information

Service Bulletin. ATA 27-00: Flight Controls Rudder-Aileron Interconnect Modification

Service 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 information

CIRRUS AIRPLANE MAINTENANCE MANUAL

CIRRUS 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 information

Cabin. 1. General. A. Cabin Seats

Cabin. 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 information

CIRRUS AMM TEMPORARY REVISION

CIRRUS 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 information

CIRRUS AIRPLANE MAINTENANCE MANUAL

CIRRUS 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 information

CHAPTER 27 - FLIGHT CONTROLS TABLE OF CONTENTS

CHAPTER 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 information

Page: REV 3: Add drill and tap information to Figure 4 DRILL #3, TAP 1/4-28 BOTH ENDS.

Page: 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 information

22-11 SYSTEM 55 AUTOPILOT

22-11 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 information

FORM: 2391 DRAWING NO: ICA Cessna Aircraft Company P.O Box 7704 WICHITA, KS 67277

FORM: 2391 DRAWING NO: ICA Cessna Aircraft Company P.O Box 7704 WICHITA, KS 67277 FORM: 2391 DRAWING NO: ICA-525-27-00005 Cessna Aircraft Company P.O Box 7704 WICHITA, KS 67277 ENGINEERING DRAWING AND PART LIST SIGNATURE AUTHORIZATION Originals Electronically Signed in the VPM System

More information

Wing Structure. 1. General

Wing 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 information

CIRRUS AIRPLANE MAINTENANCE MANUAL

CIRRUS 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 information

12.0 CONTROLS 3/3/2006. Page 1

12.0 CONTROLS 3/3/2006. Page 1 Page 1 Page 2 SR3500 Rudder Pedal Parts List ITEM DESCRIPTION PART NUMBER QTY 1 MASTER BRAKE PEDAL RP0015 2 2 SLAVE BRAKE PEDAL RP0016 2 3 PUSH ROD RP0017 4 4 SLAVE BRAKE TORQUE TUBE RP0018 2 5 MASTER

More information

Chapter 27 FLIGHT CONTROLS

Chapter 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 information

Passenger And Crew Door

Passenger 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 information

PASSENGER AND CREW DOORS

PASSENGER 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 information

C I R R U S CABIN 1. DESCRIPTION A. Cabin Seats B. Radio Module Assembly

C 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 information

In-Flight Entertainment System

In-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 information

Chapter 27. Flight Controls

Chapter 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 information

A. Stall Warning System - Serials w/o Ice Protection

A. 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 information

CIRRUS AIRPLANE MAINTENANCE MANUAL

CIRRUS 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 information

CIRRUS AIRPLANE MAINTENANCE MANUAL VISION SF50 CHAPTER 32-42: BRAKES GENERAL. Brakes 32-42: BRAKES. 1. General

CIRRUS 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 information

STALL WARNING SYSTEM 1. DESCRIPTION A.

STALL 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 information

Service Bulletin. ATA 52-10: Passenger and Crew Doors Door Latching Assembly Upgrade

Service 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 information

CIRRUS AIRPLANE MAINTENANCE MANUAL

CIRRUS 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 information

Rotary Speed Brake Actuation System ICA Supplement

Rotary 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 information

Storage. 1. General. A. Fuel Storage System

Storage. 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 information

CIRRUS AIRPLANE MAINTENANCE MANUAL

CIRRUS 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 information

CIRRUS AIRPLANE MAINTENANCE MANUAL

CIRRUS 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 information

FUSELAGE ASSEMBLY SECOND SECTION (of three)

FUSELAGE ASSEMBLY SECOND SECTION (of three) FUSELAGE ASSEMBLY SECOND SECTION (of three) 1 FRONT FLOOR ASSEMBLY The front floor assembly is fabricated from three pieces of the two ply pre-pregnated panel material supplied. The basic floor panel and

More information

Aileron Pulley Shield ICA Supplement

Aileron 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 information

SD3-60 AIRCRAFT MAINTENANCE MANUAL PRIMARY CONTROLS - DESCRIPTION & OPERATION

SD3-60 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 information

FLIGHT SIMULATOR SYSTEMS

FLIGHT 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 information

CHAPTER 21 ENVIRONMENT CONTROL. Section Title Page

CHAPTER 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 information

57-20 AUXILIARY STRUCTURE

57-20 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 information

CIRRUS AIRPLANE MAINTENANCE MANUAL

CIRRUS 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 information

36-01 REV 1: Updated figure to depict current F Bellcrank configuration.

36-01 REV 1: Updated figure to depict current F Bellcrank configuration. REVISION DESCRIPTION: 36-01 REV 1: Updated figure to depict current F-00067 Bellcrank configuration. 36-06 REV 1: Updated Figure 1 and Figure 2 to depict current F-00067 Bellcrank configuration. 36-07

More information

CIRRUS AIRPLANE MAINTENANCE MANUAL

CIRRUS 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 information

Propeller Assembly. 1. General

Propeller 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 information

REVISION LIST CHAPTER 6: AILERON CONTROLS

REVISION 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 information

SPECIAL PURPOSE EQUIPMENT

SPECIAL 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 information

33-40 EXTERIOR LIGHTING

33-40 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 information

33-10 FLIGHT COMPARTMENT

33-10 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 information

CIRRUS AIRPLANE MAINTENANCE MANUAL

CIRRUS 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 information

CIRRUS AIRPLANE MAINTENANCE MANUAL

CIRRUS 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 information

Dimensions And Areas. 1. General. A. Airplane Dimensions and Areas

Dimensions 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 information

CHAPTER 29 HYDRAULICS Description Hydraulic Pump Hydraulic Reservoir Hydraulic Servos

CHAPTER 29 HYDRAULICS Description Hydraulic Pump Hydraulic Reservoir Hydraulic Servos Section Title CHAPTER 29 HYDRAULICS 29-00 Description............................................... 29.1 29-10 Hydraulic Pump............................................ 29.1 29-20 Hydraulic Reservoir.........................................

More information

Mooney Mite M-18X Plans and Drawings Index Arranged by Group Miscellaneous Group

Mooney Mite M-18X Plans and Drawings Index Arranged by Group Miscellaneous Group Miscellaneous Group 110470 Bushings - Special 314410 Airspeed & Altimeter Installation 110190 Arm - Landing Warning 110070 Button - Static Airspeed 213260 Cone - Wing Fillet 110120 Control - Placard 616100

More information

FLIGHT CONTROLS SYSTEM

FLIGHT CONTROLS SYSTEM FLIGHT CONTROLS SYSTEM DESCRIPTION Primary flight control of the aircraft is provided by aileron, elevator and rudder control surfaces. The elevator and rudder control surfaces are mechanically operated.

More information

Page: REV 1: In Step 4 "a minimum of 1/16 [1.6 mm] gap" was "an approximately 1/16 [1.6 mm] gap."

Page: 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 information

C I R R U S HOISTING DESCRIPTION

C 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 information

REVISION LIST CHAPTER 19: ELEVATOR CONTROLS

REVISION LIST CHAPTER 19: ELEVATOR CONTROLS REVISION LIST CHAPTER 19: 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 information

CHAPTER 15 FURNISHINGS. Section Title Page

CHAPTER 15 FURNISHINGS. Section Title Page CHAPTER 15 FURNISHINGS Section Title Page 15.000 Description..................................... 15.1 15.100 Seat Harnesses................................... 15.3 15.110 Four-Point Harness Assembly.................

More information

SNOW ENGINEERING CO. ENGINEERING NUMBER 02 Wichita Falls, Texas REPORT ORDER MODEL All

SNOW ENGINEERING CO. ENGINEERING NUMBER 02 Wichita Falls, Texas REPORT ORDER MODEL All LETTER INDE DATE *6/21/17 PAGE 1 OF *5 * 401/402 SERVICE INFORMATION LETTERS 0001 Flap Actuator Travel Limit Mircro Switches 0002 Hopper Rinse Spray Ball 0003 Converting to Argentine Configuration 0004

More information

C I R R U S BRAKES DESCRIPTION

C 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 information

C I R R U S DISTRIBUTION DESCRIPTION

C 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 information

performance 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 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 information

CHAPTER 63 MAIN ROTOR DRIVE SYSTEM

CHAPTER 63 MAIN ROTOR DRIVE SYSTEM Section Title CHAPTER 63 MAIN ROTOR DRIVE SYSTEM 63-00 Description............................................... 63.1 63-10 Engine Shaft Weldment...................................... 63.1 63-11 (Engine

More information

Attitude And Direction

Attitude 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 information

Chapter 52 DOORS -Title

Chapter 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 information

SD3-60 AIRCRAFT MAINTENANCE MANUAL. This chapter includes information on dimensions, areas, zoning, etc. and is presented as follows:

SD3-60 AIRCRAFT MAINTENANCE MANUAL. This chapter includes information on dimensions, areas, zoning, etc. and is presented as follows: AMM 6-00-00 1.0.0.0GENERAL 1. General This chapter includes information on dimensions, areas, oning, etc. and is presented as follows: Measurements and Figures which show the stations of fuselage frames,

More information

Seabee Annual Inspection Procedures

Seabee 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 information

C I R R U S WING STRUCTURE DESCRIPTION

C 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 information

CIRRUS AIRPLANE MAINTENANCE MANUAL

CIRRUS 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 information

C I R R U S CONTROLLING DESCRIPTION

C 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 information

N398CM. RC-3 Serial Number 387 Zero Timed Restoration Details

N398CM. RC-3 Serial Number 387 Zero Timed Restoration Details RC-3 Serial Number 387 Zero Timed Restoration Details WING GROUP: Complete disassembly of wings, flaps, ailerons, lift struts, floats, and float struts. removal, alodine dip, and epoxy prime, w/bms 10-11.

More information

CIRRUS AIRPLANE MAINTENANCE MANUAL

CIRRUS 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 information

CIRRUS AIRPLANE MAINTENANCE MANUAL

CIRRUS 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 information

REVISION LIST CHAPTER 21: FLAP SYSTEM COMPLETION

REVISION 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 information

Flight Compartment. 1. General

Flight Compartment. 1. General CIRRUS AIRPLANE MAINTENANCE MANUAL Flight Compartment CHAPTER 56-10: FLIGHT COMPARTMENT GENERAL 56-10: FLIGHT COMPARTMENT 1. General The windshield is manufactured of acrylic and is adhesive bonded to

More information

CHAPTER 11 FLIGHT CONTROLS

CHAPTER 11 FLIGHT CONTROLS CHAPTER 11 FLIGHT CONTROLS CONTENTS INTRODUCTION -------------------------------------------------------------------------------------------- 3 GENERAL ---------------------------------------------------------------------------------------------------------------------------

More information

CHAPTER 32 LANDING GEAR. Section Title Page

CHAPTER 32 LANDING GEAR. Section Title Page CHAPTER 32 LANDING GEAR Section Title Page 32-00 Description........................................ 32.1 32-10 Landing Gear Assembly............................... 32.1 32-20 Cross Tubes.......................................

More information

TEMPORARY REVISION NUMBER

TEMPORARY REVISION NUMBER TEMPORARY REVISION NUMBER 7 DATED 1 DECEMBER 2011 MANUAL TITLE MANUAL NUMBER - PAPER COPY TEMPORARY REVISION NUMBER Model 188 & T188 Series 1966 Thru 1984 Service Manual D2054-1-13 D2054-1TR7 MANUAL DATE

More information

12/03 EXPLODED VIEW 1) L angles on first rear rib: moved from inboard to outboard side of rib (12/03)

12/03 EXPLODED VIEW 1) L angles on first rear rib: moved from inboard to outboard side of rib (12/03) ZODIAC CH 601 XL Drawing list December 04, 2003 3 rd revision of 2 nd edition 12/03 Summary of revisions from 07/03 to 11/03 AIRFRAME 6-X-0 DRAWING LIST Dec 4, 2003 6-X-1 6-T-0 6-T-1 6-T-2 6-T-3 6-T-4

More information

Flight Compartment. 1. General

Flight Compartment. 1. General CIRRUS AIRPLANE MAINTENANCE MANUAL Flight Compartment CHAPTER 56-10: FLIGHT COMPARTMENT GENERAL 56-10: FLIGHT COMPARTMENT 1. General The windshield is manufactured of acrylic and is adhesive bonded to

More information

CHAPTER 76 ENGINE CONTROLS. Section Title Page

CHAPTER 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 information

REPAIR AND OVERHAUL OF AFCS ACTUATORS P/N S ; -113 (ROLL), ; -115 (PITCH), ; -117 (YAW)

REPAIR AND OVERHAUL OF AFCS ACTUATORS P/N S ; -113 (ROLL), ; -115 (PITCH), ; -117 (YAW) TECHNICAL BULLETIN 214ST-90-117 9 November 1990 Revision A, 31 May 2012 MODEL AFFECTED: SUBJECT: HELICOPTERS AFFECTED: COMPLIANCE: 214ST Helicopters REPAIR AND OVERHAUL OF AFCS ACTUATORS P/N S 214-001-540-107;

More information

ASK 21 - Flight Manual. Check List / 1

ASK 21 - Flight Manual. Check List / 1 Check List / 1 Pre Flight Check 1. Main pins secured? 2. Rear wing attachment pins: is the safety lock visible above the pin? 3. Horizontal tail unit pins secured. Is the spring retainer engaged? 4. Elevator

More information

Seabee Annual/100-Hour Inspection

Seabee Annual/100-Hour Inspection Date Completed Seabee Annual/100-Hour Inspection ENGINE Mechanic s Initials 1 Drain engine oil and check for foreign material 2 Check oil screen for proper rotation or looseness 3 Safety Oil Plug 4 Refill

More information

MANPOWER REQUIREMENTS

MANPOWER 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 information

CIRRUS AIRPLANE MAINTENANCE MANUAL

CIRRUS 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 information

Jabiru Aircraft Pty. Ltd. Final Inspection Checklist. Engine Compartment

Jabiru Aircraft Pty. Ltd. Final Inspection Checklist. Engine Compartment Jabiru Aircraft Pty. Ltd. Final Inspection Checklist Registration No: Aircraft Checklist Pre Ground Test Model: Serial No: Engine Compartment Propeller: Prop Size: 60 x 53 Other:.. Propeller Serial No:

More information

Chapter 3: Aircraft Construction

Chapter 3: Aircraft Construction Chapter 3: Aircraft Construction p. 1-3 1. Aircraft Design, Certification, and Airworthiness 1.1. Replace the letters A, B, C, and D by the appropriate name of aircraft component A: B: C: D: E: 1.2. What

More information

LANCAIR LEGACY PRE-TEST FLIGHT INSPECTION (8-04)

LANCAIR LEGACY PRE-TEST FLIGHT INSPECTION (8-04) LANCAIR LEGACY PRE-TEST FLIGHT INSPECTION (8-04) OWNER PHONE # ADDRESS N SERIAL # AIRCRAFT TYPE DATE / / TACH TIME hrs. TOTAL TIME hrs. EMPTY WEIGHT CG. PAINT & INTERIOR? YES NO ENGINE TYPE PROPELLER ALL

More information

TEMPORARY REVISION NUMBER

TEMPORARY REVISION NUMBER TEMPORARY REVISION NUMBER 8 DATED 1 DECEMBER 2011 MANUAL TITLE MANUAL NUMBER - PAPER COPY TEMPORARY REVISION NUMBER 1978 Thru 1986 Model R182 & TR182 Service Manual D2069-3-13 D2069-3TR8 MANUAL DATE 15

More information

DESCRIPTION AND OPERATION

DESCRIPTION AND OPERATION FLIGHT COMPARTMENT 1. DESCRIPTION AND OPERATION The windshield is manufactured of acrylic and is adhesive bonded to the fuselage. Replacement is accomplished by removing the interior trim around the windshield,

More information

SERVICE INFORMATION LETTER

SERVICE INFORMATION LETTER SERVICE INFORMATION LETTER DATE: August 19, 2015 SERVICE INFORMATION LETTER NO. 0183 Page 1 of 18 1. SUBJECT: Collective Stick Socket Replacement 2. MODEL: F28A, 280, F28C, 280C, F28F, 280F, and 280FX

More information

CIRRUS AIRPLANE MAINTENANCE MANUAL

CIRRUS 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 information

A Simplified Index of Mooney M-18 Drawings at the NASM

A Simplified Index of Mooney M-18 Drawings at the NASM A Simplified Index of Mooney M-18 Drawings at the NASM Dwg. No. Dwg. date Title Models Remarks IDnum Price 0000 23-Aug-54 M-18 Aileron Crank Mooney M-18 17 x 22 DD-0029487 $2.10 0000 [Lower Pick-Up Strap

More information

PARAVION TECHNOLOGY, INC AIRWAY AVENUE FT. COLLINS, COLORADO 80524

PARAVION 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 information

USA G-103 Twin Astir

USA G-103 Twin Astir USA G-103 Procedures for safe assembly and dis-assembly of the glider (Trailers 2 and 3) Grob Glider Rigging Tools Required: Needle nosed pliers Wire cutters (side cut) Very large crescent wrench (for

More information

CHAPTER 65 TAIL ROTOR DRIVE SYSTEM. Section Title Page

CHAPTER 65 TAIL ROTOR DRIVE SYSTEM. Section Title Page CHAPTER 65 TAIL ROTOR DRIVE SYSTEM Section Title Page 65-00 Description........................................ 65.1 65-10 Tail Rotor Drive Fan Shaft.............................. 65.1 65-20 Tail Rotor

More information

ST 93 RIPPER INSTALL KIT

ST 93 RIPPER INSTALL KIT ST 93 RIPPER INSTALL KIT P/N 2883777;2883778;2883779 APPLICATION The Timbersled Ripper ST93 Install Kit is designed to fit all Timbersled ST90 and ST93 Ripper models. This includes; Timbersled Model No.

More information

CHAPTER 22 AUTOPILOT

CHAPTER 22 AUTOPILOT Section Title CHAPTER 22 AUTOPILOT 22-00 Description............................................... 22.1 22-10 (Pitch) Servo Assembly...................................... 22.3 22-20 (Roll) Servo Assembly.......................................

More information