CIRRUS DESIGN CAPS Скачать руководство пользователя | Manualshive

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Содержание CAPS

Страница 1: ...NICAL DATA IN THIS PUBLICATION THAT AFFECTS AIRPLANE TYPE DESIGN COPYRIGHT 2002 CIRRUS DESIGN CORPORATION DULUTH MINNESOTA USA P N 12128 001 ISSUED SEPT 2002 Procedures and parts listed in this manual are reflective of Cirrus Design SR20 airplanes serial numbers 1195 and subsequent SR22 airplanes serial numbers 0210 and subsequent and all prior airplanes incorporating Service Bulletin SB 20 95 05 ...

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Страница 3: ...12128 001 95 RevLog Page 1 Log of Revisions Revision Number Issue Date Date Inserted Inserted By Revision Number Issue Date Date Inserted Inserted By 15 Sept 2002 ...

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Страница 5: ...95 01 8 15 SEPT 2002 95 01 9 15 SEPT 2002 95 01 11 15 SEPT 2002 95 01 12 15 SEPT 2002 95 01 13 15 SEPT 2002 95 01 14 15 SEPT 2002 95 01 15 15 SEPT 2002 95 01 16 15 SEPT 2002 95 01 17 15 SEPT 2002 95 01 18 15 SEPT 2002 95 01 19 15 SEPT 2002 95 01 20 15 SEPT 2002 95 01 21 15 SEPT 2002 95 01 22 15 SEPT 2002 95 01 23 15 SEPT 2002 95 01 24 15 SEPT 2002 95 01 25 15 SEPT 2002 95 01 26 15 SEPT 2002 95 01 ...

Страница 6: ...ge 2 CHAPTER 95 CIRRUS AIRFRAME PARACHUTE SYSTEM LIST OF EFFECTIVE PAGES Chapter Section Page Date 95 01 36 15 SEPT 2002 95 01 37 15 SEPT 2002 95 01 38 15 SEPT 2002 95 01 39 15 SEPT 2002 95 01 40 15 SEPT 2002 15 Sept 2002 ...

Страница 7: ...11 General 11 Servicing Cirrus Airframe Parachute System 11 Removal Pyrotechnic Line Cutters Replacement 11 Installation Pyrotechnic Line Cutters Replacement 12 CAPS Cover 15 Removal CAPS Cover 15 Installation CAPS Cover 15 CAPS Rocket Assembly 20 Removal CAPS Rocket Assembly 20 Disassembly CAPS Rocket Assembly 20 Reassembly CAPS Rocket Assembly 20 Installation CAPS Rocket Assembly 21 CAPS Parachu...

Страница 8: ...IRFRAME PARACHUTE SYSTEM TABLE OF CONTENTS Subject Chapter Section Page ILLUSTRATED PARTS LIST 95 01 33 General 33 SR2X CAPS Installation Sheet 1 of 3 34 SR2X CAPS Installation Sheet 2 of 3 35 SR2X CAPS Installation Sheet 3 of 3 36 15 Sept 2002 ...

Страница 9: ... writ ten to cover a whole class of aircraft rather than a particular model some deviations from the specification were made for clarity 2 USING THE CAPS COMPONENT MANUAL This CAPS Component Manual is divided into two major sections the CAPS Maintenance Guide which outlines approved maintenance practices and the CAPS Illustrated Parts List prepared to aid technicians in identifying and procuring r...

Страница 10: ... dynamics of the airplane during the deployment cycle by limiting the aft attachment strap s length until the cycle is complete This is accomplished by utilizing a variable length strap section The shorter section which initially supports the load employes a mechanical release that is activated by two pyrotechnic cut ters which fire when the short section is pulled taut during extraction The harne...

Страница 11: ...12128 001 95 01 Page 3 Figure 95 011 CAPS System and Deployment 15 Sept 2002 ...

Страница 12: ...sses the rocket igniter spring and cocks the plunger One half inch of plunger travel is required to release the ball bearings and allow the plunger to strike the firing pins The firing pins then strike the shotgun type primers which ignite a black powder and magnesium primary booster in the end of the igniter The igniter is unarmed in its normal configuration since the spring is un compressed and ...

Страница 13: ...12128 001 95 01 Page 5 Figure 95 012 CAPS Handle and Ignition System 15 Sept 2002 ...

Страница 14: ...re 95 014 The parachute slows the airplane to a descent speed that is conducive to a safe touchdown The basic structure of the parachute assembly consists of the canopy suspension lines and the slider a compo nent used to aerodynamically reef the parachute and limit inflation loads 1 Canopy and Suspension Lines The 2400 sq ft round canopy which creates the aerodynamic drag is made up of a series o...

Страница 15: ...12128 001 95 01 Page 7 Figure 95 013 Incremental Bridle and Deployment Bag 15 Sept 2002 ...

Страница 16: ...ocated directly in front of the parachute enclosure The CAPS har ness system is designed to control the pitch dynamics of the airplane during the deployment cycle by limiting the aft aircraft attachment harness length until the deployment cycle is complete The rear harness assembly has two sections of different length The shorter section has a mechanical release mechanism that is activated by two ...

Страница 17: ...12128 001 95 01 Page 9 Figure 95 014 Parachute Assembly and Line Cutters 15 Sept 2002 ...

Страница 18: ...THIS PAGE INTENTIONALLY LEFT BLANK ...

Страница 19: ...APS deployment FAA Type Certification for the airplane is contingent on a functional Cirrus Airframe Parachute System CAPS The airplane may not be flown when CAPS is rendered inoperative Note CAPS part identification and descriptions can be found in the Illustrated Parts List section of this manual A Servicing Cirrus Airframe Parachute System See Figure 95 015 1 Removal Pyrotechnic Line Cutters Re...

Страница 20: ...all link i Position line cutters inside securing flaps and route nylon cord up between link cutters j With one end of nylon cord make one complete loop around mini ring CAUTION Ensure no slack exists in nylon cord between rear harness sleeve and mini ring and line cutter installation holes and small link k Cinch nylon cord tight l Tie CAPS knot 1 Cross upper cord end end looped around mini ring ov...

Страница 21: ...12128 001 95 01 Page 13 Figure 95 015 Pyrotechnic Line Cutters Replacement Sheet 1 of 2 15 Sept 2002 ...

Страница 22: ...12128 001 95 01 Page 14 Figure 95 015 Pyrotechnic Line Cutters Replacement Sheet 2 of 2 15 Sept 2002 ...

Страница 23: ...lt in damage to CAPS system and failure upon deployment Note CAPS cover remnant may be used as an outline template to facilitate cover installation Avoid unnecessary damage to remnant cover during removal e Beginning at the aft RH edge of cover seam line carefully pry cover away from adhesive using a small chisel Avoid scratching or denting fuselage with chisel Work edge back until it is possible ...

Страница 24: ...ion of CAPS cover is located above CAPS rocket Maximum gap between CAPS cover and fuselage is 0 10 inch 2 5 mm g Position CAPS cover to final fit and draw four reference lines across cover fuselage seam line to facilitate installation WARNING The CAPS cover is secured with a low strength bond which allows the rocket to more easily detach the cover when extracting the parachute An improper bond cou...

Страница 25: ...g cup 4 Measure 5 0 gm of modifier Heloxy 68 and add to base resin Mix material thor oughly 5 Measure 8 5 gm of hardener Epicure 3234 and add to resin modifier mixture Mix material thoroughly 6 Mix 4 7 gm of Filler1 Aerosil with 5 3 gm Filler2 Sil Cell 7 Add Filler1 Filler2 mixture to resin modifier hardener mixture Mix adhesive thor oughly k With applicator stick fill 0 50 inch 1 3 cm gap between...

Страница 26: ... 2 03 0 13 mm 3 Ensure adhesive is devoid of air pockets Inspect bond line for voids or high spots Clean any adhesive that squeezes out o Through access cover CB7 remove tape and plastic sheet Inspect and clean enclosure for any spilled adhesive or debris p Utilizing Heated Air Cure methods fully cure adhesive for 1 hour at 140 F 60 C Refer to AMM 51 20 q Fill seal and paint CAPS cover enclosure R...

Страница 27: ...12128 001 95 01 Page 19 Figure 95 016 CAPS Cover Installation 15 Sept 2002 ...

Страница 28: ... to rocket motor launch tube and remove rocket lanyard from rocket motor m Remove rocket assembly from airplane 2 Disassembly CAPS Rocket Assembly a Remove screws securing rocket cone to rocket motor igniter and remove cone b Remove screws securing rocket motor to rocket shelf and slide rocket shelf off of rocket motor c Slide rocket shield off of rocket motor d Safety the rocket motor by wiring f...

Страница 29: ...ication is meant only to ensure firing pin capture A very slight pull force 0 25 lb 0 113 kg is all that is required to verify cap ture f Slightly pull cable projecting from rocket motor assembly base to verify firing pin capture g Screw cone adapter to rocket cone h Install access hole plug to rocket cone CAUTION Do not overtighten nylon shear screws WARNING Position rocket lanyard around top cir...

Страница 30: ...12128 001 95 01 Page 22 Figure 95 017 CAPS Rocket Assembly Sheet 1 of 2 15 Sept 2002 ...

Страница 31: ...12128 001 95 01 Page 23 Figure 95 017 CAPS Rocket Assembly Sheet 2 of 2 15 Sept 2002 ...

Страница 32: ...spacers bolts washers and nuts securing forward harness straps to parachute assembly three point shackles j Lift parachute assembly off saddle and store in clean dark and dry environment 2 Installation Caps Parachute Assembly a Acquire necessary tools equipment and supplies CAUTION Do not attempt to lift or carry parachute assembly by rear harness or rocket lanyards For lifting use 1 inch wide ret...

Страница 33: ...ong parachute assembly through buckle over clasp back through buckle and cinch tight CAUTION Do not overtighten straps to point of overshooting and misaligning hook and loop sewn to strap ends l Using a large blunt flat bladed screwdriver further tighten retaining straps by inserting screwdriver head into strap end pocket and applying down force Secure strap with hook and loop sewn to strap ends C...

Страница 34: ...acilitate screw removal push attaching screws up to break filler covering screw heads and use a small knife to remove remaining filler o At CAPS activation handle remove nuts washers bushings and screws securing activa tion handle and cable assembly to fuselage p Locate cut and remove all cable ties securing activation cable to the fuselage ceiling q Remove aluminum tape securing CAPS activation c...

Страница 35: ...ion cable so that cable will not chafe on speaker or antenna installations m Install spiral wrap to aft portion of activation cable behind BH 222 so that cable will not chafe on static lines or BH 222 cable pass through hole n Perform Operational Check Caps Activation Handle Cable Assembly Refer to 95 01 o Install CAPS Rocket Assembly Refer to 95 01 p Position cabin headliner to ceiling and instal...

Страница 36: ...otion l Verify power unit reads green indicating correct CAPS activation cable installation m If power unit reads red verify activation cable is properly connect to test fixture and routing is correct and clear of other components n Re check CAPS Activation Cable o If power unit reads red a second time contact Cirrus Design for disposition Otherwise remove test fixture from airplane p Install CAPS...

Страница 37: ...12128 001 95 01 Page 29 Figure 95 018 CAPS Activation System 15 Sept 2002 ...

Страница 38: ...12128 001 95 01 Page 30 Figure 95 019 Sheet 1 of 2 CAPS Test Fixture 15 Sept 2002 ...

Страница 39: ...12128 001 95 01 Page 31 Figure 95 019 Sheet 2 of 2 CAPS Test Fixture 15 Sept 2002 ...

Страница 40: ...THIS PAGE INTENTIONALLY LEFT BLANK ...

Страница 41: ... Procedures and parts listed in this manual are reflective of Cirrus Design SR20 airplanes serial numbers 1195 and subsequent SR22 airplanes serial numbers 0210 and subsequent and all prior airplanes incor porating Service Bulletin SB 20 95 05 or SB 22 95 05 respectively ...

Страница 42: ...12128 001 95 01 Page 34 Figure 01 SR2X CAPS Installation Sheet 1 of 3 15 Sept 2002 39 42 45 48 51 66 75 78 81 84 87 90 99 105 93 180 177 72 ...

Страница 43: ...12128 001 95 01 Page 35 Figure 01 SR2X CAPS Installation Sheet 2 of 3 15 Sept 2002 153 156 93 96 102 174 180 177 72 177 ...

Страница 44: ...12128 001 95 01 Page 36 Figure 01 SR2X CAPS Installation Sheet 3 of 3 15 Sept 2002 9 12 15 18 21 24 27 30 33 36 54 57 60 63 111 114 117 120 123 126 129 132 135 141 144 147 150 159 165 168 171 72 177 72 ...

Страница 45: ...69 SJ3572 A HOOK TAPE V1LF36 1005 AR ORDER CIRRUS P N 50458 001 72 15047 003 ACTIVATION ASSEMBLY 1196 1 75 PRT OF ITEM 15 A BRACKET 1196 1 78 PRT OF ITEM 15 A SCREW 1196 1 81 MS24694 S53 A SCREW 1196 2 84 NAS1149F0363P A WASHER 1196 2 87 24SW0010 A SHOULDER WASHER V13764 1196 2 ORDER CIRRUS P N 51191 201 90 MS21044N3 A NUT 1196 2 93 EMS A DO A FORWARD AND MIDDLE TIE DOWN V06383 1196 2 ORDER CIRRUS...

Страница 46: ...489 97 GROMMET 1005 1 168 22AF1250 ADJUSTABLE BUSHING V13764 1196 1 ORDER CIRRUS P N 51192 125 171 91F7326 GROMMET FLEXIBLE V02927 1005 1 ORDER CIRRUS P N 50892 001 174 15045 001 PLACARD CAPS ROUTING 1196 3 177 LLP 250 100 LOOM V58961 1196 AR ORDER CIRRUS P N 50943 025 180 MS3367 1 9 A STRAP 4 FIG N O P I C ITEM PART NUMBER S Y M B O L A T T A C H NOMENCLATURE EFFECTIVE UNITS PER ASSY 12345678 VEN...

Страница 47: ...69 SJ3572 A HOOK TAPE V1LF36 0002 AR ORDER CIRRUS P N 50458 001 72 15047 003 ACTIVATION ASSEMBLY 0210 1 75 PRT OF ITEM 15 A BRACKET 0210 1 78 PRT OF ITEM 15 A SCREW 0210 1 81 MS24694 S53 A SCREW 0210 2 84 NAS1149F0363P A WASHER 0210 2 87 24SW0010 A SHOULDER WASHER V13764 0210 2 ORDER CIRRUS P N 51191 201 90 MS21044N3 A NUT 0210 2 93 EMS A DO A FORWARD AND MIDDLE TIE DOWN V06383 0210 2 ORDER CIRRUS...

Страница 48: ...489 97 GROMMET 0002 1 168 22AF1250 ADJUSTABLE BUSHING V13764 0210 1 ORDER CIRRUS P N 51192 125 171 91F7326 GROMMET FLEXIBLE V02927 0002 1 ORDER CIRRUS P N 50892 001 174 15045 001 PLACARD CAPS ROUTING 0219 3 177 LLP 250 100 LOOM V58961 0169 AR ORDER CIRRUS P N 50943 025 180 MS3367 1 9 A STRAP 4 FIG N O P I C ITEM PART NUMBER S Y M B O L A T T A C H NOMENCLATURE EFFECTIVE UNITS PER ASSY 12345678 VEN...

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