CIRRUS AIRPLANE MAINTENANCE MANUAL

Transcription

1 INTRODUCTION 1. COVERAGE This Cirrus Design SR20 Airplane Maintenance Manual was prepared by Cirrus Design Technical Publications. This manual contains information necessary to enable a trained mechanic to inspect, service, clean, trouble shoot, functionally test, and repair systems and equipment in the Cirrus Design SR20. It also includes information necessary for the mechanic to perform maintenance or make minor repair to units in the airplane normally requiring such action on the flight line or in the maintenance hangar. This manual covers the as delivered airplane configuration. The Cirrus Design SR20 Airplane Maintenance Manual was prepared using GAMA Specification No. 2 (Specification for Manufacturers Maintenance data), Revised September 1982 as a content model and format guide. However, as the specification is written to cover a whole class of aircraft rather than a particular model, some deviations from the specification were made for clarity. This Maintenance Manual does not reflect part numbers and cannot be used for ordering replacement parts. Spares and replacement parts should be ordered using the current Cirrus Design SR20 Illustrated Parts Catalog. Wiring schematics within the description and operation sections of this manual are for general information purposes only. Troubleshooting shall be performed using the Wiring Manual, and the optional avionics and electrical wiring diagrams provided at delivery. 2. USING THE MAINTENANCE MANUAL This Maintenance Manual is divided into four major sections, each of which is separated into chapters. Each chapter contains its own list of effective pages and table of contents. A. Page Numbering System Page numbers used in this Maintenance Manual consist of two-element numbers separated by dashes, under which the page number and date are printed. Whenever the chapter/system element number is followed by zeros in the section/subsystem (32-00) the information presented on the page is applicable to the entire system. The section/subsystem number is used to identify information applicable to section or subsystems within a chapter or system respectively. The subject/unit element number progresses from the number 10 in accordance with GAMA Specification No. 2 and the number of section/subsystem units covered. system/subsystem data is page numbered separately. 3. WARNINGS, CAUTIONS, AND NOTES Warnings, Cautions, and Notes are used to highlight or emphasize important points. Warnings call attention to use of materials, processes, methods, procedures, or limits which must be followed precisely to avoid bodily injury. Cautions call attention to methods and procedures which must be followed to avoid damage to equipment. Notes call attention to methods which make the procedure easier. Page 1 15 Jun 2010

2 4. AIRPLANE SERIAL NUMBER EFFECTIVITY Airplane serial number effectivity references are used throughout the maintenance manual to distinguish between different system designs and procedures. The effectivities are italicized and are displayed in the same font weight as the adjacent text. Effectivity references under the General or Description sections are handled in one of two ways. If effectivity applies to entire paragraph, the effectivity reference will preface the paragraph with a colon. If effectivity applies to only a section of the paragraph, the affected content shall be followed by the effectivity reference in parentheses. Effectivity references under the Troubleshooting section are handled one of three ways. If effectivity applies to the probable cause and/or remedy item in the table, the effectivity reference will preface the paragraph followed by a colon and may share the table cell with one or more additional effectivity blocks. If effectivity applies to the trouble item in the table, the effectivity reference will preface the paragraph followed by a colon. probable cause and remedy items in that table row will pertain only to the effectivity defined for the trouble item. Alternately, a standalone table may be defined for a particular effectivity if troubleshooting differs greatly due to varying model configurations. Effectivity references under the Maintenance Practices section are handled in one of two ways. If effectivity applies to only a few steps in a procedure, the effectivity reference will preface the step followed by a colon. If procedures differ greatly based on effectivity, the component and related procedures will be presented in blocks with an effectivity reference for each block. Effectivity is also indicated in the effectivity block in the bottom corner of each page. On illustration pages, the effectivity is on the face of the illustration and in the title block beneath the illustration. Note: For content specified with serials followed by and subsequent or & subs, effectivity in this AMM ends as follows: Model End Effectivity SR A. Aircraft Equipped with G3 Wing Airplane serial numbers 1878, 1886 and subsequent are equipped with a redesigned wing. Where necessary, this document may use the terms G3 or G3 Wing to identify this installation. The list below shows the primary structural and system changes which accompany G3 Wing configuration: 1 degree increase in wing dihedral, Removal of the aileron-rudder interconnect, Increased fuel capacity and associated updates to sensing and indicating system, Main landing gear location moved slightly, strut angle increased, and strut lengthened, Redesigned main landing gear fairings, Redesigned nose landing gear fairings, Redesigned lightning protection plan, Relocation of stall warning port, RH lower engine cowling modified, Redesigned environmental control system, Redesigned wing root fairings, Modification of interior trim panels, Page 2

3 Redesigned bolster switch panel, Leading-edge wing tip recognition lights. B. Special Conditions New features are sometimes introduced on a pilot airplane before going into regular production. As a result, certain parts or assemblies are installed on a range of airplanes with a split or a break in affected serial number range. For example, a split effectivity listing of Serials 1878, 1886 & subs indicates that a part or assembly was installed on aircraft serial number 1878, then removed on serial numbers 1879 through 1885, and then introduced as standard configuration on aircraft serial numbers 1886 and subsequent. In many instances these split effectivities can result in difficult-to-interpret descriptions listing multiple serial numbers. To avoid including these cumbersome descriptions throughout the length of this publication, see the following Special Conditions table for a list of affected aircraft serial numbers and instruction on how to disposition the aircraft s as-built configuration. Serial Number Special Condition Disposition 1301 Aircraft installed with updated bulkhead 306. Unless otherwise noted, refer to serial number 1307 for part identification Aircraft installed with Environmental Control System with factory installed fan Aircraft installed with G3 Wing and associated systems. C. Service Bulletins Aircraft installed with Aircraft Data Logger (ADL) and associated systems Aircraft installed with Perspective Avionics and associated systems Aircraft installed with Air Conditioning System. Aircraft installed with Oleo Strut Aircraft installed with Lycoming Engine. Aircraft installed with Perspective+ Avionics. Unless otherwise noted, refer to serial number 1639 for part identification. Unless otherwise noted, refer to serial number 1886 for part identification of systems affected by G3 Wing and ADL installations. Unless otherwise noted, refer to serial number 2016 for part identification. Unless otherwise noted, refer to serial number 2065 for part identification. Unless otherwise noted, refer to serial number 2339 in AMM P/N for part identification. Note: When part effectivities are conditional to modifications, such as service bulletins, the airplane logbook should be checked to determine the proper replacement parts. Installation of service bulletins are shown by notations in the maintenance procedure and figure. The term Before SB 20-XX-XX" indicates that the part effectivity is as written unless the subject Service Bulletin was installed. The term After SB 20-XX-XX indicates that the part effectivity is as written when the airplane has been modified in accordance with the subject Service Bulletin. Page 3

4 D. Avionics Configuration Airplane serial effectivities shown in a maintenance procedure or figure may be further limited by the airplane s avionics configuration. Cirrus Design offers the SR20 with the avionic options listed in the table below; therefore, the effectivity for a maintenance procedure or figure may also be limited by the installed avionics. Standard avionics suites are available in the following configurations: Serials 1005 through 1267: Configuration A Moving Map Display (ARNAV ICDS 2000 MFD) Single-Axis Autopilot (S-Tec System 20) One IFR Approach-Certified GPS (Garmin GNS 430) and One VFR GPS (Garmin GNC 250XL) Two VHF Communications (Garmin GNS 430 and Garmin GNC 250XL) Single Navigation (VOR/LOC/GS) Receiver (Garmin GNS 430) Mode C Transponder with Altitude Encoder (Serials 1005 thru 1099: Garmin GTX 320, Serials 1100 thru 1267: Garmin GTX 327) Course Deviation Indicator (Serials 1005 thru 1047: Garmin GI 102, Serials 1048 thru 1267: Garmin GI 102A) Directional Gyro Configuration B Moving Map Display (ARNAV ICDS 2000 MFD) Two-Axis Autopilot (S-Tec System 30) Two IFR Approach-Certified GPS (Garmin GNS 430 and Garmin GNC 420) Two VHF Communications Transceivers (Garmin GNS 430 and Garmin GNC 420) Single Navigation (VOR/LOC/GS) Receiver (Garmin GNS 430) Mode C Transponder with Altitude Encoder (Serials 1005 thru 1099: Garmin GTX 320, Serials 1100 thru 1267: Garmin GTX 327) Horizontal Situation Indicator (Century NSD 360A) Course Deviation Indicator (Serials 1005 thru 1047: Garmin GI 102, Serials 1048 thru 1267: Garmin GI 102A) Page 4

5 Serials 1268 thru 1336: Configuration C Moving Map Display (ARNAV ICDS 2000 MFD) Two-Axis Autopilot (S-Tec System 55) Two IFR Approach-Certified GPS (Garmin GNS 430) Two VHF Communications Transceivers (Garmin GNS 430) Two Navigation (VOR/LOC/GS) Receiver (Garmin GNS 430) Horizontal Situation Indicator (Century NSD 1000) Course Deviation Indicator (Serials 1005 thru 1047: Garmin GI 106, Serials 1048 thru 1267: Garmin GI 106A) Configuration 2.0 Moving Map Display (Avidyne EX3000C MFD) Single-Axis Autopilot (S-Tec System 20) One IFR Approach-Certified GPS (Garmin GNS 430) and One VFR GPS (Garmin GNC 250XL) Two VHF Communications (Garmin GNS 430 and Garmin GNC 250XL) Single Navigation (VOR/LOC/GS) Receiver (Garmin GNS 430) Horizontal Situation Indicator (Century NSD 1000) Course Deviation Indicator (Garmin GI 106) Configuration 2.1 Moving Map Display (Avidyne EX5000C MFD) Two-Axis Autopilot (S-Tec System 30) Two IFR Approach-Certified GPS (Garmin GNS 430 and Garmin GNC 420) Two VHF Communications Transceivers (Garmin GNS 430 and Garmin GNC 420) Single Navigation (VOR/LOC/GS) Receiver (Garmin GNS 430) Horizontal Situation Indicator (Century NSD 1000) Course Deviation Indicator (Garmin GI 102A) Page 5

6 Configuration 2.2 Moving Map Display (Avidyne EX5000C MFD) Two-Axis Autopilot (S-Tec System 55X) Two IFR Approach-Certified GPS (Garmin GNS 430) Two VHF Communications Transceivers (Garmin GNS 430) Two Navigation (VOR/LOC/GS) Receiver (Garmin GNS 430) Electronic Navigation Display (Sandel SN3308) Course Deviation Indicator (Garmin GI 106A) Serials 1337 and subsequent: Configuration PFD Primary Flight Display (Avidyne FlightMax Entegra PFD) Moving Map Display (Avidyne EX5000C MFD) Two-Axis Autopilot (S-Tec System 55SR) One IFR Approach-Certified GPS (Garmin GNS 430) and One VFR GPS (Garmin GNC 250XL) Two VHF Communications (Garmin GNS 430 and Garmin GNC 250XL) Single Navigation (VOR/LOC/GS) Receiver (Garmin GNS 430) Serials 1359 and subsequent: Configuration SRV Primary Flight Display (Avidyne FlightMax Entegra PFD) Moving Map Display (Avidyne EX3000C MFD) One IFR Certified GPS (Garmin GNC 420) One VHF Communications (Garmin GNC 420) Page 6

7 Serials 2016 and subsequent: Configuration Perspective Multi-Function Display (Garmin MFD) Primary Flight Display (Garmin PFD) Two-Axis Autopilot (Garmin GFC 700) Serials 2016 thru 2126: Integrated Audio System with Intercom (Garmin GMA 347) Serials 2127 & subs: Integrated Audio System with Intercom (Garmin GMA 350) Serials 2016 thru 2126: Marker Beacon Receiver (Garmin GMA 347) Serials 2127 & subs: Marker Beacon Receiver (Garmin GMA 350) Two IFR Approach-Certified GPS (Garmin GIA 63W) Two VHF Communications Transceivers (Garmin GIA 63W) Two Navigation (VOR/LOC/GS) Receiver (Garmin GIA 63W) Mode C Transponder with Altitude Encoder (Garmin GTX 32) Flight Management System Keyboard (Garmin GCU 478) Attitude and Heading Reference System (Garmin GRS 77) Air Data Computer (Garmin GDC 74A) Engine Airframe Unit (Garmin GEA 71) Serials 2086, 2087, 2117, 2120, 2122 thru 2126, 2129 thru 2132, 2136 thru 2147 with Option Installed: Configuration S United States Airforce Academy Perspective Avionics Configuration with following options installed: - 10-inch PFD Display - 10-inch MFD Display - Single Attitude and Heading Reference System (Garmin GRS 77) - Single Air Data Computer (Garmin GDC 74A) - Engine Airframe Unit (Garmin GEA 71) - Integrated Audio System with Intercom (Garmin GMA 347) - Marker Beacon Receiver (Garmin GMA 347) - Two IFR Approach-Certified GPS (Garmin GIA 63W) - Two VHF Communications Transceivers (Garmin GIA 63W) - Two Navigation (VOR/LOC/GS) Receiver (Garmin GIA 63W) - Flight Management System Keyboard (Garmin GCU 478) - Mode C Transponder with Altitude Encoder (Garmin GTX 32) - Garmin GTS 800 Traffic Advisory System - No Automatic Flight Control System (ACFS) - No Garmin Synthetic Vision (SynVis) Page 7

8 E. Optional Equipment Airplane serial effectivities shown in a maintenance procedure or figure may be further limited by optional equipment installed in the airplane. Cirrus Design offers the SR20 with the optional equipment listed in the table below; therefore, the effectivity for a maintenance procedure or figure may also be limited by the installed optional equipment. Page 8 Configuration S United States Airforce Academy (Continued) - No Weather System (WX) - No Terrain Awareness & Warning (TAWS) - No Terminal Procedure Chart System Artex ME406 Emergency Locator Transmitter (ELT) Vent-Only Environment Control System Fabric Seats 2-Blade Propeller No Wheel Pants No Rear Seats No Rear Seat Headset Plugs No Ice Protection System No Carbon Monoxide (CO) Detector No Enhanced Vision System (EVS) No Wing Recognition Lights Optional Equipment Serials 1005 through 1336: Century NSD 1000 Horizontal Situation Indicator Serials 1148 & subs: L3 SkyWatch Serials 1032 & subs: L3 Stormscope Serials 1148 & subs: S-Tec System 55X Serials 1148 through 1336: Sandel SN3308 Electronic Navigation Display Serials 1179 & subs: Avidyne EX3000C and EX5000C MFD Serials 1233 & subs: Avidyne EMax Engine Monitoring System Serials 1425 & subs: Garmin Mode S Transponder Serials 1441 & subs: Honeywell Terrain Awareness and Warning System Serials 1473 & subs Avidyne XM Weather System Serials 2127 & subs: Iridium Weather System Serials 1494 & subs: Avidyne Flight Director Serials 1533 & subs: XM Radio System Serials 1633, 1639 & subs: Cabin Air Fan Assembly Serials 2065 & subs w/ Perspective Avionics: Air Conditioning System Serials 2065 & subs: Oleo Strut

9 Optional Equipment (Continued) Serials 1639 & subs: Artex ME406 Emergency Locator Transmitter (ELT) Serials 2016 & subs: Bendix/King Distance Measuring Equipment Serials 2016 & subs: Bendix/King Automatic Direction Finder Serials 2016 & subs: Garmin Synthetic Vision Serials 2016 & subs: Enhanced Vision System Serials 2127 & subs: 2+1 Rear Seat Serials 2127 & subs: Three-Harness Shoulder Belt Serials 2127 & subs: Cargo Net Serials 2273 & subs: MD302 Standby Attitude Module 5. REVISIONS This manual has been prepared in loose-leaf form for ease in inserting revisions. Tabbed dividers, throughout the manual, are in standard GAMA format and numbering and allow quick reference to data in each section. Logical and convenient Tables of Contents are located at the beginning of each chapter to aid in locating specific data within that chapter. Numbered revisions will be issued periodically. These revisions are printed on white paper and contain a revision instruction sheet to assist the user in filing the change. Upon receipt of a numbered revision, file it according to the provided instructions as soon as possible. Additionally, a record of filing must be made on the following Log of Revisions page. 6. REVISION BARS Changes to data in an existing section will be identified by a revision bar in the outer margin of the page. Change bars are used in figures to indicate changes. 7. TEMPORARY REVISIONS Temporary revisions are used to provide time sensitive information and changes as they become available. Temporary revisions provide, with the least possible delay, new information which assists in maintaining safe and efficient flight/ground operations.temporary revisions are incorporated at the next regularly scheduled revision and become a permanent part of the Maintenance Manual. Upon receipt of a Temporary Revision, file the revision in the applicable chapter in accordance with filing instructions that appear on the Temporary Revision. Additionally, a record of filing the Temporary Revision must be made in the Log of Temporary Revisions for that AMM chapter. Typically, the Log Of Temporary Revisions for a chapter will be replaced by a blank log when a numbered revision for that chapter is issued. Temporary Revisions should be removed from this manual only when removal instructions are noted on the regular revision summary sheet or by instructions noted on a superseding Temporary Revision. 8. PUBLICATION CHANGE REQUEST FORM A Publication Change Request form can be found online at the following link: Use the form to submit a Publications Change Request to our Engineering Department and/or to tell us what you think of the quality of the publication. We will use the data you provide us to improve the quality of our technical publications. Page 9

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