LEARJET 35135A/36136A MAINTENANCE MANUAL

Description .....................................................................´•...................´•´•´•´•´•´•´•´•´•´•´•´•´•´•´•´•´•´•´•´•´•´•´•´•´•´•´•´•´•´•´•´•´•´•´•34-21-00 1 Directional Gyro Maintenance Practices ..........................................................................34-21-00 Removal/Installation ........................................................................................´•.´•..........34-21-00 201 Flwe Valve Maintenance Practices 34-21-01 Removal/Installation ........................................................................................´•´•´•´•´•´•..´•..´•.34-21-01 201 Adjustment/Test...............................................................................................´•´•´•´•´•´•´•´•´•´•´•´•´•´•34-21-01 201 Calibration/Adjustment of Flux Valves and Magnetic Compass 34-21-01 201 VERTICAL GYRO MAINTENANCE PRACTICES................................. 34-22-00 Removal/Installation.......................................................... 34-22-00 201 FLIGHT DIRECTORS AND COURSE INDICATORS MAINTENANCE PRACTICES...............................................................................................34-23-00 Removal/Installation.......................................................... 34-23-00 201 Flight Director System Adjustment/Test.........................................................................34-23-01 General .........................................................................................´•´•.´•´•´•.´•.´•.´•.....´•..´•´•´•´•´•´•´•´•´•´•´•´•´•´•´•34-23-01 501 Tools and Equipment .....................................................................................................34-23-01 501 Adjustment/Test...............................................................................................´•..´•.´•........ 34-23-01 501 Flight Director System Adjustment/Test.........................................................................34-23-02 General .........................................................................................´•´•´•´•´•´•´•´•´•´•´•´•´•..´•´•´•´•-´•´•´•´•´•´•-´•´•-´•´•´•´•´•34-23-02 501 Tools and Equipment ..........................................................................................´•..........34-23-02 501 Adjushnent/Test............................................................................................´•..´•´•´•´•´•´•´•´•´•´•´•´•´•´• 34-23-02 501 VLF-1000-2 Navigation System Adjustment/Test..........................................................34-23-03 General ..............................................................................................................´•´•´•´•´•´•´•´•´•´•´•´•´•´•34-23-03 501 Tools and Equipment .......................................................................................´•´•´•´•´•´•´•´•´•´•´•´•´•´•34-23-03 501 Adjustment/Test. 34-23-03 501 GNS600 VLF Navigation System Description and Operation.....................................34-23-04 Description ...................................................................................´•.´•....´•..........´•..´•´•´•´•´•´•´•´•´•´•´•...34-23-04 1 GNS-500 VLF Navigation System Maintenance Practices.............................................34-23-04 General 34-23-04 201 GNS-500 VLF Navigation System Adjustment/Test...................................................... 34-23-04 General 34-23-04 501 Tools and Equipment 34-23-04 501 Adjustment/Test...............................................................................................´•´•´•´•´•´•´•´•´•´•´•´•´•´•34-23-04 501 TURN AND BANK INDICATOR DESCRIPTION AND OPERATION ....34r24-00 Description ...................................................................´•´•´•´•´•.´•.............´•.´•´•´•´•´•´•´•´•´•´•´•´•´•´•´•´•´•´•´•´•´•´•´•´•´•´•´•´•´•´•´•´•´•´•´•34-24-00 1 Turn and Bank Maintenance Practices .............................................................................34-24-00 Removal/Installation 34-24-00 201 h~ 34- CONTENTS Island Enterprises International AeroTech Academy For Training Purpose Only Learjet Chapter Section Subiect Subiect TURN COORDINATOR DESCRIPTION AND OPERATION ...........34-25-00 Description .........~.............................................´•...................´•´•´•´•................´•´•´•´•´•´•´•.´•´•´•´•´•´•´•´•´•´•´•´•´•´•´•´•´•´•´•´•´•34-25-00 1 Tum Coordinator- Maintenance Practices ...........34-25-00 Removal/Installation .......................................................´•..´•..´•34-25-00 201 MAGNETIC COMPASS MAINTENANCE PRACTICES .................................................34-26-00 Removal/Installation............................................... ....................................´•´•´•´•´•´•´•´•´•´•´•´•´•´•´•´•´•´•´•..34-26-00 201 LANDING AND TAXIING AIDS DESCRIPTION AND OPERATION .........................34-30-00 General ......................................................´•´•´•´•´•´•´•´•´•........´•´•.´•´•´•´•´•´•´•´•´•´•´•´•´•´•´•´•´•´•´•´•´•´•´•´•´•´•´•´•´•´•´•´•´•´•´•´•´•´•´•´•´•´•´•´•´•´•´•´•´•´•´•´•´•´•´•´•34-30-00 1 Glideslope Antenna Maintenance Practices.....................................................................34-30-01 Tools and Equipment ....................................................´•´•´•´•......´•...´•..´•´•´•´•´•´•´•´•´•´•.´•´•´•´•´•´•´•´•´•´•´•´•´•´•´•´•´•´•´•´•´•34-30-01 201 Removal/Installation ........................´•´•´•´•´•´•´•´•´•.´•´•´•´•´•´•´•´•´•´•´•34-30-01 201 Marker Beacon Antenna Maintenance Practices 3430-02 Removal/Installation .......................................................´•....................´•´•´•.´•´•´•´•´•.´•´•´•´•´•´•´•´•´•´•´•´•´•´•´•34-30-02 201 Inspection/Check............................................................´•.......................´•´•.´•´•´•´•´•´•´•´•´•´•´•´•´•´•´•´•´•´•´•´•´•34-30-02 201 WEATHER RADAR DESCRTPTION AND OPERATION ................................................34111-00 General ................................................;....~.......´•...................´•´•´•´•...´•´•´•´•´•´•´•´•´•´•´•´•´•´•´•´•´•´•´•´•´•´•´•´•´•´•´•´•´•´•´•´•´•´•´•´•´•´•´•´•´•´•34-41-00 1 Description ...........................................................................´•´•´•´•........´•.´•.´•.´•´•´•´•´•´•´•´•´•´•´•´•´•´•´•´•´•´•´•´•´•´•´•´•´•´•´•´•´•´•´•34-41-00 1 Weather Radar Maintenance Practices .............................................................................34-41-00 Tools and Equipment 201 Adjustment/Test............................................................´•´•´•´•.......´•...´•.´•´•´•´•´•´•´•´•´•´•.´•´•´•´•´•´•´•´•´•´•´•´•´•´•´•´•´•´•´•´•´•34-41-00 201 Inspection/Check...........................................................´•´•´•´•....´•´•´•.´•´•´•´•´•´•´•´•´•´•´•´•´•´•´•´•´•´•´•´•´•´•´•´•´•´•´•´•´•´•´•´•´•´•´•´•´•34-41-00 201 Receiver-Transmitter Maintenance Practices........................................~..........................34-41-01 Removal/Installation ....................................................´•.´•´•...............´•´•´•´•´•´•´•´•.´•´•´•´•´•´•´•´•´•´•´•´•´•´•´•´•´•´•´•´•´•34-41-01 201 Radar Antenna Maintenance Practices .............................................................................34-41-02 RemovaljInstallation .....................................................´•.....................´•.´•.´•´•´•´•´•´•´•´•´•´•´•´•´•´•´•´•´•´•´•´•´•´•34-41-02 201 Radar Indicator Maintenance Practices .....................................................................‘.......34-41-03 Removal/Installation ....................................................´•´•´•..................´•´•´•´•´•.´•´•´•´•´•´•´•´•´•´•´•´•´•´•´•´•´•´•´•´•´•´•34-41-03 201 INS-61B NAVIGATION SYSTEM DESCRIM?ON AND OPERATION .........................34-42-00 Description ......................................................´•................´•...´•´•´•´•´•´•´•´•´•´•´•´•´•´•´•´•´•´•´•´•´•.´•´•´•´•´•´•´•´•´•´•´•´•´•´•´•´•´•´•´•´•´•´•´•´•´•´•´•34-42-00 1 Supplementary Publications...................................................´•..................´•´•´•´•´•.´•´•´•´•´•´•´•´•´•´•´•´•´•´•´•´•´•´•´•´•´•34-42-00 1 INS-618 Navigation System Functional Test........ ..........................................34-42-00 General .................................................´•.´•´•´•´•´•´•......´•....´•´•´•´•´•´•´•´•´•´•´•´•´•´•´•´•´•´•´•´•´•´•´•´•´•´•´•´•´•´•´•´•´•´•´•´•´•´•´•´•´•´•´•´•´•´•´•´•´•´•´•´•´•´•´•´•34-42-00 501 Tools and Equipment 501 Functional Test ...............................................................´•´•´•´•..................´•´•´•´•´•.´•´•´•´•´•´•´•´•´•´•´•´•´•´•´•´•´•´•´•´•´•34-42-00 501 STORMSCOPE WEATHER MAPPING SYSTEM DESCRIPTION AND OPERATION......................................´•´•´•´•..............´•´•´•´•´•´•´•´•´•.´•´•´•´•´•´•´•´•´•´•´•´•´•´•´•´•´•´•´•´•.34-43-00 Description ....................................................´•´•´•´•´•..................´•´•´•´•´•´•´•´•´•´•´•´•´•´•´•´•´•´•´•´•´•´•´•´•´•´•´•´•´•´•´•´•´•´•´•´•´•´•´•´•´•´•´•´•´•´•´•´•´•34-43-00 1 Operation 34-43-00 1 Stormscope Weather Mapping System Troubleshooting ..............................................34-43-00 Tools and Equipment .........................................................................´•.´•´•´•´•.´•´•´•´•´•´•´•´•´•´•´•´•´•´•´•´•´•´•´•´•´•34-43-00 101 Self Test ......T.....~................´•´•.´•´•............´•.´•´•´•´•´•´•´•´•´•´•´•´•´•´•´•´•´•´•´•´•´•´•´•´•´•´•´•´•´•´•´•´•´•´•´•´•´•´•´•´•´•´•´•´•´•´•´•´•´•´•´•´•´•´•´•´•´•´•´•´•´•´•´•´•´•´•´•´•´•´•´•´•´•´•´•´•34-43-00 101 Troubleshooting ..................................´•´•´•´•´•´•´•´•´•´•´•´•´•´•´•´•´•´•´•´•´•´•´•´•´•´•´•´•´•´•´•´•´•´•´•´•´•´•´•´•´•´•´•´•´•´•´•´•´•´•´•´•´•´•´•´•´•´•´•´•´•´•´•´•´•´•´•´•´•´•´•´•´•´•´•´•34-43-00 103 Interference Test ..................................´•´•´•´•´•´•´•´•´•.´•.´•´•.´•´•´•´•´•´•´•´•´•´•´•´•´•´•´•´•´•´•´•´•´•´•´•´•´•´•´•´•´•´•´•´•´•´•´•´•´•´•´•´•´•´•´•´•´•´•´•´•´•´•´•´•´•´•´•´•´•´•´•´•´•34-43-00 106 Stormscope Weather Mapping System Maintenance Practices ....................................34-43-00 Tools and Equipment ....................................................´•´•´•´•.............´•´•´•´•´•´•´•´•´•´•.´•´•´•´•´•´•´•´•´•´•´•´•´•´•´•´•´•´•´•´•´•34-43-00 201 Inspection/Check................................´•´•´•´•´•´•´•´•´•´•´•´• ´•´•´•´•´•´•´•´•´•´•´•´•´•´•´•´•´•´•´•´•´•´•´•´•´•´•´•´•´•´•´•´•´•´•´•´•´•´•´•´•...................34-43-00 201 34-CONTENTS Page 3 MM-99 Jun 22/90 Island Enterprises International AeroTech Academy For Training Purpose Only Learjet Chapter Section Subiect Subiect Stormscope Processor Maintenance Practices .................................................................34-43-01 Removal/Installation 201 Stormscope Display Maintenance Practices ....................................................................34-43-02 Removal/Installation ....................................´•....´•´•´•´•´•´•´•´•´•´•´•´•´•´•´•´•´•´•´•´•´•´•´•´•´•´•´•´•´•´•´•´•´•´•´•´•´•´•´•´•´•´•´•´•´•´•´•´•´•´•´•´•´•´•´•´•´•´•´•´•34-23-02 201 Stormscope Antenna Maintenance Practices ...................................................................34-43-03 Removal/Znstallation ...........................................´•....´•..´•.´•.´•´•´•´•´•´•´•´•´•´•´•´•´•´•´•´•´•´•´•´•´•´•´•´•´•´•´•´•´•´•´•´•´•´•´•´•´•´•´•´•´•´•´•´•´•´•34-43-03 201 GROUND PROMMITY WARNING SYSTEM (GPWS) DESCRIPTION AND OPERATION.......................................................................................34-44-00 Description ´•´•´•´•´•´•´•´•´•´•´•´•´•´•´•´•;.:´•........34-44-00 1 Operation ................................................´•´•.´•´•´•´•´•´•´•´•´•´•´•´•´•´•´•´•´•´•´•´•´•´•´•´•´•´•´•´•´•´•´•´•´•´•´•´•´•´•´•´•´•´•´•´•´•´•´•´•´•´•´•´•´•´•´•´•´•´•-´•´•´•´•´•´•´•´•´•´•´•´•´•´•´•´•´•34-44-00 1 Ground Proximity Warning System (GPWS) Trouble Shooting ..................................34-44-00 Trouble Shooting............................... ´•´•´•´•´•´•34-44-00 101 Ground Proximity Warning System (GPWS) Maintenance Practices..........................34-44-00 Tools and Equipment ....................................................................´•´•.´•´•´•´•´•´•´•´•´•´•´•´•´•´•´•´•´•´•´•´•´•´•´•´•´•´•´•´•´•´•34-44-00 201 Adjustment/Test........................................ 34-44-00 201 Functional Test of Ground Proximity Warning System (GPWS) .....................34-44-00 201 Operational Test of Ground Proximity Warning System (GPWS) ...................34-44-00 202 Ground Proximity Warning System Computer Maintenance Practices......................34-44-01 Removal/Installation ..................................´•.´•´•.´•´•´•´•´•´•´•´•´•´•´•´•´•´•´•´•´•´•´•´•´•´•´•´•´•´•´•´•´•´•´•´•´•´•´•´•´•´•´•´•´•´•´•´•´•´•´•´•´•´•´•´•´•´•´•´•´•´•´•´•´•´•34-44-01 201 NAVIGATION DESCRIPTION AND OPERATION .........................................................34-51-00 Description ................................´•.´•.´•´•´•´•´•´•´•´•´•´•´•´•´•´•´•´•´•´•´•´•´•´•´•´•´•´•´•´•´•´•´•´•´•´•.´•´•´•´•´•´•´•´•´•´•´•´•´•´•´•´•´•´•´•´•´•´•´•´•´•´•´•´•´•´•´•´•´•´•´•´•´•´•´•´•´•´•´•´•´•´•´•´•´•´•´•´•´•34-51-00 1 Navigation Receivers Maintenance Practices .........................................................´•.´•.´•´•´•´•´•34-51-01 Removal/Installation ..........................................´•´•´•´•´•´•´•´•´•´•´•´•´•´•´•´•´•´•´•´•´•´•´•´•´•´•´•´•´•´•´•´•´•´•´•´•´•´•´•´•´•´•´•´•´•´•´•´•´•´•´•´•´•´•´•´•´•´•´•34-51-01 201 Navigation Antenna Maintenance Practices...............................................................´•´•´•..34-51-02 Removal/Installation ..................................´•....´•´•.´•´•´•´•´•´•´•´•´•´•´•´•´•´•´•´•´•´•´•´•´•´•´•´•´•´•´•´•´•´•´•´•´•´•´•´•´•´•´•´•´•´•´•´•´•´•´•´•´•´•´•´•´•´•´•´•´•´•´•34-51-02 201 DME DESCRIPTION AND OPERATION ................................................................´•-.-´•´•´•-´•´•´•3452-00 Description .............................´•.´•´•´•´•´•´•´•´•´•´•´•´•´•´•´•´•´•´•´•´•´•´•´•´•´•´•´•´•´•´•´•´•´•´•´•´•´•´•´•´•´•´•´•´•´•´•´•´•´•´•´•´•´•´•´•´•´•´•´•´•´•´•´•´•´•´•´•´•´•´•´•´•´•´•´•´•´•´•´•´•´•´•´•´•´•´•´•´•´•´•´•´•´•54-52-00 1 Operation ...........34-52-00 1 Interrogator Maintenance Practices ......................................................´•´•´•´•´•´•´•´•´•´•´•´•´•´•´•´•´•´•´•´•´•´•´•´•´•´•´•´•34-52-01 Removal/Installation ...............................´•.´•´•´•´•´•´•´•´•´•´•´•´•´•´•´•´•´•´•´•´•´•´•´•´•´•´•´•´•´•´•´•´•´•´•´•´•´•´•´•´•´•´•´•´•´•´•´•´•´•´•´•-´•´•´•´•´•´•´•´•´•´•´•´•´•´•´•´•34-52-01 201 DME Converter Maintenance Practices..................................................´•´•´•´•´•´•´•´•´•´•´•´•´•´•´•´•´•´•´•´•´•´•´•´•´•´•34-52-02 Removal/Installation .......................................´•´•´•´•´•´•´•´•´•´•´•´•´•´•´•´•´•´•´•´•´•´•´•´•´•´•´•´•´•´•´•´•´•´•´•´•´•´•´•´•´•´•´•´•´•´•´•´•´•´•´•´•´•´•´•´•´•´•´•´•´•´•34-52-02 201 DME Antenna Maintenance Practices ...............................................´•´•´•´•´•´•´•´•´•´•´•´•´•´•´•´•´•´•´•´•´•´•´•´•´•´•´•´•,,,34-52-03 RemovaljInstallation ................................´•´•´•´•´•´•´•´•´•´•´•´•´•´•´•´•´•´•´•´•´•´•´•´•´•´•´•´•´•´•´•´•´•´•´•´•´•´•´•´•´•´•´•´•´•´•´•´•´•´•´•´•´•´•´•´•´•´•´•´•´•´•´•´•´•´•´•´•´•34-52-03 201 Distance Ground Speed Indicator Maintenance Practices..............................~..............34-52-04 Removal/Installation ........................´•´•.´•´•´•.´•´•´•´•´•´•´•´•´•´•´•´•´•´•´•´•´•´•´•´•´•´•´•´•´•´•´•´•´•´•´•´•´•´•´•´•´•´•´•´•´•´•´•´•´•´•´•´•´•´•´•´•´•´•´•´•´•´•´•´•´•´•´•´•´•´•´•´•´•´•34-52-04 201 ADF DESCRIPTION AND OPERATION ................´•´•´•´•´•´•´•34-53-00 Description ...........................´•´•´•´•´•´•´•´•´•´•´•´•´•´•´•´•´•´•´•´•´•´•´•´•´•´•´•´•´•´•´•´•´•´•´•´•´•´•´•´•´•´•´•´•´•´•´•´•´•´•´•´•´•´•´•´•´•´•´•´•´•´•´•´•´•´•´•´•´•´•´•´•´•´•´•´•´•´•´•´•´•´•´•´•´•´•´•´•´•´•´•´•´•´•´•´•´•34-53-00 1 ADF Receiver Maintenance Practices .......................................................´•.´•´•´•´•´•´•´•´•´•´•´•´•´•´•´•´•´•´•....34-53-01 Removal/Installation ............................´•´•´•´•´•´•´•´•´•´•´•´•´•´•´•´•´•´•´•´•´•´•´•´•´•´•´•´•´•´•´•´•´•´•´•´•´•´•´•´•´•´•´•´•´•´•´•´•´•´•´•´•´•´•´•´•´•´•´•´•´•´•´•´•´•´•´•´•´•´•´•´•´•34-53-01 201 ADF Control Head Maintenance Practices ...............................................................´•´•´•´•´•´•´•34-53-02 Removal/Installation ..................´•´•´•´•´•´•´•´•´•´•´•´•´•´•´•´•´•´•´•´•´•´•´•´•´•´•´•´•´•´•´•´•´•´•´•´•´•´•´•´•´•´•´•´•´•´•´•´•´•´•´•´•´•´•´•´•´•´•´•´•´•´•´•´•´•´•´•´•´•´•´•´•´•´•´•´•´•´•´•´•´•´•´•34-53-02 201 ADF Sense Antenna Maintenance Practices ............................................;.................´•.´•´•´•´•34-53-03 Removal/Installation ............´•.´•´•´•´•´•´•´•´•´•´•´•´•´•´•´•´•´•´•´•´•´•´•´•´•´•´•´•´•´•´•´•´•´•´•´•´•´•´•´•´•´•´•´•´•´•´•´•´•´•´•´•´•´•´•´•´•´•´•´•´•´•´•´•´•´•´•´•´•´•´•´•´•´•´•´•´•´•´•´•´•´•´•´•´•´•´•´•34-53-03 201 ADF Loop Antenna Maintenance Practices 34-53-04 Removal/Installation ....................´•´•´•´•´•´•´•´•´•´•´•´•´•´•´•´•´•´•´•´•´•´•´•´•´•´•´•´•´•´•´•´•´•´•´•´•´•´•´•´•´•´•´•´•´•´•´•´•´•´•´•´•´•´•´•´•´•-´•´•´•-´•´•´•´•´•´•´•´•´•´•´•´•´•-´•´•´•´•´•34-53-04 201 34-CONTENTS Page 4 MM-99 Jun 22/90 Island Enterprises International AeroTech Academy For Training Purpose Only Learjet Chapter Section Subiect Subiect RADIO MAGNETIC INDICATOR DESCRIPTION AND OPERATION .......................34-54-00 Description ........................................´•´•.´•´•´•´•´•´•´•´•´•´•´•´•´•´•´•´•´•´•´•´•´•´•´•´•´•´•´•´•´•´•´•´•´•´•´•´•´•´•´•´•´•´•´•´•´•´•´•´•´•´•´•´•´•´•´•´•´•´•´•´•´•´•´•´•´•´•´•´•´•´•´•´•´•´•´•´•´•´•´•´•´•34-54-00 1 Operation .....................................´•´•´•´•´•´•´•´•´•´•´•´•´•´•´•´•´•´•´•´•´•´•´•´•´•´•´•´•´•´•´•´•´•´•´•´•´•´•´•´•´•´•´•´•´•´•´•´•´•´•´•´•´•´•´•´•´•´•´•´•´•´•´•´•´•´•´•´•´•´•´•´•´•´•´•´•´•´•´•´•´•´•´•´•´•´•´•´•´•´•34-54-00 1 Radio Magnetic Indicator Maintenance Practices...........................................................34-54-01 Removal/Installation 34-54-01 201 ATC TRANSPONDER DESCRIPTION AND OPERATION ............................................34-55-00 Description ........................................-.´•´•´•´•´•´•´•´•´•´•´•´•´•´•´•´•´•´•´•´•´•´•´•´•´•´•´•´•´•´•´•´•´•´•´•´•´•´•´•´•´•´•´•´•´•´•´•´•´•´•´•´•´•´•´•´•´•´•´•´•´•´•´•´•´•´•´•´•´•´•´•´•´•´•´•´•´•´•´•´•´•´•34-55-00 1 ATC Transponder Maintenance Practices........................................................................34-55-01 Removal/Installation .....................................´•´•´•.´•´•´•´•´•´•´•´•´•´•´•´•´•´•´•´•´•´•´•´•´•´•´•´•´•´•´•´•´•´•´•´•´•´•´•´•´•´•´•´•´•´•´•´•´•´•´•´•´•´•´•´•´•´•´•´•´•´•´•´•34-55-01 201 Transponder Control Head Maintenance Practices........................................................34-55-02 Removal/Installation .......................................´•.´•´•´•´•´•´•´•´•´•´•´•´•´•´•´•´•´•´•´•´•´•-´•´•´•´•´•´•´•´•´•´•´•´•´•´•´•´•´•´•´•´•´•´•´•´•´•´•´•´•´•´•´•´•´•´•´•´•´•´•34-55-02 201 Transponder Antenna Maintenance Practices.................................................................34-55-03 Removal/Installation ...............................................´•.´•....´•.´•´•´•´•´•´•´•´•´•´•´•´•´•´•´•´•´•´•´•´•´•´•´•´•´•´•´•´•´•´•´•´•´•´•´•´•´•´•´•´•´•´•´•´•´•34-55-03 201 34-CONTENTS Page 5 MM-99 Jun 22/90 Island Enterprises International AeroTech Academy For Training Purpose Only LEARJET 35/35A/36/36A MAINTENANCE MANUAL Chapter Chapter Section I Section Subiect Page Date Subiect Page Date 34- TITLE 1"34-11-01 206 Feb 11/00 34 Rec. of Temp. Rev. 1 Jun 12/87 1 34-11-01 207 Feb 11/00 54 List of Eff. Pgs. I Feb 11/00 1 34-11-01 208 Feb 11/00 34 List of Eff. Pgs. 2 Feb 11/00 1 34-11-02 201 Jun 12/87 34 List of Eff. Pgs. 3 Feb 11/00 34-11-02 202 Jun 12/87 *34-Contents I Feb 11/00 1 34-11-03 201 Feb 19/91 +34-Contents 2 Feb 11/00 1 34-11-03 202 Feb 19/91 34 Contents 3 Jun 22/90 1 34-11-03 203 Feb 19/91 34 Contents 4 Jun 22/90 1 34-11-04 201 Feb 19/91 34 Contents 5 Jun 22/90 34-11-04 202 Feb 19/91 34-00-00 1 Jun 12/87 1,34-12-00 1 Feb 11/00 34-10-00 1 Feb 19/91 1.34-12-00 2 Feb 11/00 34-10-00 2 Feb 19/91 1.34-12-00 3 Feb 11/00 34-10-01 201 Jun 12/87 1.34-12-00 4 Feb 11/00 34-10-02 201 Feb 19/91 1 34-12-00 201 Sep 25/92 34-10-03 201 Jun 12/87 1 34-12-00 202 Sep 25/92 34-10-04 201 Feb 19/91 1 34-12-00 203 Sep 25/92 34-10-04 202 Feb 19/91 1 34-12-00 204 Sep 25/92 34-11-00 1 Feb 19/91 1 34-12-01 201 Feb 19/91 34-11-00 2 Feb 19/91 1 34-12-01 202 Feb 19/91 34-11-00 3 Feb 19/91 1 ~C 34-14-00 1 Feb 11/00 34-11-00 4 Feb 19/91 1*34-14-01 201 Feb 11/00 34-11-00 5 Feb 19/91 1*34-14-01 202 Feb 11/00 34-11-00 6 Feb 19/91 1 34-14-02 201 Jun 12/87 34-11-00 7 Feb 19/91 1 34-14-02 202 Jun 12/87 34-11-00 8 Feb 19/91 1*34-14-03 201 Feb 11/00 34-11-00 9 Feb 19/91 1*34-14-03 202 Feb 11/00 *34-11-00 201 Feb 11/00 1*34-14-03 203 Feb 11/00 *34-11-00 202 Feb 11/00 1 34-15-00 1 Jun 12/87 .34-11-00 203 Feb 11/00 1 34-15-01 201 Jun 12/87 *34-11-00 204 Feb 11/00 1 34-15-02 201 Jun 12/87 *34-11-00 205 Feb 11/00 1 34-15-03 201 Jun 12/87 *34-11-00 206 Feb 11/00 1 34-15-03 202 Jun 12/87 *34-11-00 207 Feb 11/00 1 34-15-03 203 Jun 12/87 *34-11-00 208 Feb 11/00 1 34-20-00 1 Jun 12/87 *34-11-00 209 Feb 11/00 1 34-21-00 1 Jun 12/87 *34-11-00 210 Feb 11/00 1*34-21-00 201 Feb 11/00 34-11-00 211 Feb 19/91 1.34-21-00 202 Feb 11/00 34-11-00 212 Feb 19/91 1 34-21-01 201 Jun 12/87 *34-11-01 201 Feb 11/00 1 34-21-01 202 Jun 12/87 *34-11-01 202 Feb 11/00 1 34-21-01 203 Jun 12/87 ,34-11-01 203 Feb 11/00 1 34-21-01 204 Jun 12/87 .34-11-01 204 Feb 11/00 1 34-21-01 205 Jun 12/87 *34-11-01 205 Feb 11/00 1*34r22-00 201 Feb 11/00 Insert Latest Revised Pages; Destroy Superseded or Deleted Pages. Asterisk indicates pages revised, added, or deleted by current revision. The portion of the text affected by the current revision is indicated by a vertical line in the outer margin of the page. 34 LIST OF EFFECTNE PAGES Pagel MM-99 Feb 11/00 Island Enterprises International AeroTech Academy For Training Purpose Only LEARJET 35/35A/36/36A MAINTENANCE MANUAL Chapter I Chapter Section I Section Subiect Pae~e Date Subiect Page Date ,34-22-00 202 Feb 11/00 1 34-41-00 201 Jun 12/87 34-23-00 201 Jun 12/87 1 34-41-00 202 Jun 12/87 34-23-01 501 Jun 12/87 1 34-41-00 203 Jun 12/87 34-23-01 502 Jun 12/87 1 34-41-00 204 Jun 12/87 34-23-01 503 Jun 12/87 34-41-00 205 Jun 12/87 34r23-01 504 Jun 12/87 1 34-41-00 206 Jun 12/87 34-23-01 505 Jun 12/87 1 34-41-00 207 Jun 12/87 34-23-02 501 Jun 12/87 1 34-41-00 208 Jun 12/87 34-23-02 502 Jun 12/87 1 34-41-01 201 Jun 12/87 34-23-02 503 Jun 12/87 34-41-01 202 Jun 12/87 34-23-02 504 Jun 12/87 1 34-41-02 201 Jun 12/87 34-23-02 505 Jun 12/87 34-41-02 202 Jun 12/87 34-23-02 506 Jun 12/87 1 34-41-03 201 Jun 12/87 34-23-02 507 Jun 12/87 1 34-41-03 202 Jun 12/87 34-23-02 508 Jun 12/87 1 34-42-00 1 Jun 12/87 34-23-02 509 Jun 12/87 1 34-42-00 501 Jun 12/87 34-23-02 510 Jun 12/87 1 34-42-00 502 Jun 12/87 34-23-03 501 Jun 12/87 1 34-42-00 503 Jun 12/87 34-23-03 502 Jun 12/87 1 34-42-00 504 Jun 12/87 34-23-03 503 Jun 12/87 34-42-00 505 Jun 12/87 34-23-03 504 Jun 12/87 1 34-42-00 506 Jun 12/87 34-23-03 505 Jun 12/87 1 34-42-00 507 Jun 12/87 34-23-03 506 Jun 12/87 1 34-43-00 1 Jun 22/90 34-23-04 1 Jun 12/87 1 34-43-00 2 Jun 22/90 34-23-04 201 Jun 12/87 34-43-00 3 Jun 22/90 34-23-04 501 Jun 12/87 1 34-43-00 4 Jun 22/90 34-23-04 502 Jun 12/87 1 34-43-00 5 Jun 22/90 34-23-04 503 Jun 12/87 1 34-43-00 101 Jun 22/90 34-23-04 504 Jun 12/87 1 34-43-00 102 Jun 22/90 34-23-04 505 Jun 12/87 1 34-43-00 103 Jun 22/90 34-23-04 506 Jun 12/87 1 34-43-00 104 Jun 22/90 34-23-04 507 Jun 12/87 1 34-43-00 105 Jun 22/90 34-24-00 1 Jun 12/87 1 34-43-00 106 Jun 22/90 34-24-00 2 Jun 12/87 1 34r43-00 107 Jun 22/90 34-24-00 201 Jun 12/87 1 34r43-00 201 Jun 22/90 34-25-00 1 Jun 12/87 1 34-43-00 202 Jun 22/90 34-2500 2 Jun 12/87 1 34-43-01 201 Jun 22/90 34-25-00 201 Jun 12/87 34-43-01 202 Jun 22/90 34-26-00 201 Jun 12/87 1 34-43-02 201 Jun 22/90 34-30-00 1 Jun 12/87 1 34-43-02 202 Jun 22/90 34-30-01 201 Jun 12/87 1 34-43-03 201 Jun 22/90 34-30-01 202 Jun 12/87 1 34-43-03 202 Jun 22/90 34-30-02 201 Jun 22/90 1 34-44-00 1 Jun 22/90 34-30-02 202 Jun 22/90 1 34-44r00 2 Jun 22/90 34r41-00 1 Jun 12/87 1 34-44-00 3 Jun 2i/90 34-41-00 2 Jun 12/87 1 34-44-00 4 Jun 22/90 34 LIST OF EFFECTIVE PAGES Page2 MM-99 Feb 11/00 Island Enterprises International AeroTech Academy For Training Purpose Only LEARJET 35/35A/36/36A MAINTENANCE MANUAL Chapter Chapter Section I Section Subiect Page Date I Subiect Page Date 34-44-00 101 Jun 22/90 34-44-00 201 Jun 22/90 34-44-00 202 Jun 22/90 34-44-00 203 Jun 22/90 34-44-00 204 Jun 22/90 34-44-00 205 Jun 22/90 34-44-00 206 Jun 22/90 34-44-00 207 Jun 22/90 34-44-01 201 Jun 22/90 34-51-00 1 Jun 12/87 34-51-01 201 Jun 12/87 34-51-02 201 Jun 12/87 34-51-02 202 Jun 12/87 34-51-02 203 Jun 12/87 34-52-00 1 Sep 25/92 34-52-01 201 Jun12/87 34-52-02 201 Jun 12/87 34-52-03 201 Sep 25/92 34-52-03 202 Sep 25/92 34-52-04 201 Jun 12/87 34-53-00 1 Jun 12/87 34-53-01 201 Juh 12/87 34-53-02 201 Jun 12/87 34-53-03 201 Jun 12/87 34-53-03 202 Jun 12/87 34-53-04 201 Jun 12/87 34-53-04 202 Jun 12/87 34-53-04 203 Jun 12/87 34-54-00 1 Jun 12/87 34-54-01 201 Jun 12/87 34-55-00 1 Jun12/87 34-55-01 201 Jun12/87 34-55-01 202 Jun 12/87 34-55-02 201 Jun 12/87 34-55-03 201 Jun 12/87 34-5503 202 Jun12/87 34 LIST OF EFFECTIVE PAGES MM-99 Page 3 Feb 11/00 Island Enterprises International AeroTech Academy For Training Purpose Only Cates Learjet Corpori\tion~ maint~enallce manual Record of Temporary Revisions Rev. Date I Date Page Rev. Date I Date Page No, Inserted Removed Number No, Inserted Removed Number 34-1 Apr 8/75 Jun 30/75 34-12-00 Rev 3 Page 2 34-2 Apr 8/75 Jun 30/75 34-23-00 Rev 3 Page 201 34-3 Apr 8/75 Jun 30/75 34-23-01 Rev 3 Page 8 34-4 May 14/76 Sep 22/76 34-11-00 TR ~34-5 Page 206 34-5 Sep 22/76 May 11/79 34-11-00 Rev 14 Page 206 34-6 Jan 31/78 May 11/79 34-12-00 Rev 14 Page 1 34-7 Jan 31/78 Feb 28/79 34-12-00 TR ~34-10 Page 201 34-8 Jan 31/78 May 11/79 34-12-01 Rev 14 Page 201 34-9 Apr 7/78 May 11/79 34-11-00 Rev 14 Page 201 34-101Feb 28/79 May 11/79 34-12-00 Rev 14 Page 201 34-1110ct 10/80 Apr 30/82 34-12-00 Rev 27 Page 203 34-121Nov 17/80 Apr 30/82 34-11-00 Rev 27 Page 201 MM-99 Page 1 D914 Jun 12/87 Island Enterprises International AeroTech Academy For Training Purpose Only ~ates Learpt Corpor~tionaP mainleuanuu manual NBVI~TION DESCBIPTION END OPEBC~TION i. DESC~IPTION A. The aircraft navigation systems includes those components and systems which provide attitude, altitude, direction, speed, flight guidance, and enroute navigational information. B. Figure 1 illustrates the navigational system in block diagram form. PILOT’S I-- I ADF I COPILOT’S RMI I- I RECEIVER I I RMI PILOT’S COPILOT’S AUDIO AUDIO PANEL PANEL PRIMARY I I I I SECONDARY NAVTGATION I DME NAVIGATION RECEIVER I I I RECEIVER PILOT’S I I I COPILOT’S FLIGHT I I I COURSE DIRECTOR I i I I INDICATOR PRIMARY VERTICAL PILOT’S I I I VERTICAL I I I I SECONDARY GYRO COURSE GYRO VERTICAL INDICATOR INDICATOR GYRO RADAR RECEI~ER- TRANSMITTER PRIMARY 1 I I I i SECONDARY DIRECTIONAL AUTOPILOT DIRECTIONAL GYRO I I I GYRO Navigation System Block Magram Figure 1 gFFgCTIVITP: BU 34-00-00 MM-99 Page 1 Disk 914 Jun 12/87 Island Enterprises International AeroTech Academy For Training Purpose Only ~Learjet FLIGHT ENVIRONMENT DATA DESCRIPTION AND OPERATION 1. DESCRIPTION A. The flight environment data system consists of the pitot and static systems which sense and supply air pressure to the air data instruments. B. The air data instruments using pitot and static pressure are installed in the pilot’s and copilot’s instru- ment panels include the following: (1) On Aivcraft 35-002 thru 35-505 excwt 35-408, 36-002 thru 36-053 not modified tier AAK 83-2, "Installa- tion ofFC-530 Autonilot," rate-of-climb indicator, airspeed/machmeter, and altimeter. (2) On Aircraft 35-408, 35-506 and Subseauent, 36-054 and Subseauent, and arior Aircraft modified aer AAK 83-2, "Installation of FC-530 Aurot7ilot rate-of-climb indicator, altimeter, and airspeed/mach indi- cater. C. Other aircraft systems utilizing pitot and static air pressure are the cabin pressurization control and autopilot systems. (1) Refer to Chapter 22 for further information on the autopilot system. (2) Refer to Chapter 21 for further information on the cabin pressurization system. 2. OPERATION A. The copilot’s rate-of-climb indicator consists of two air enclosing chambers, a diaphragm, and the air- tight case. When the static pressure varies because of changing altitudes, the case pressure lags be- hind diaphragm pressure due to a restriction in the flow of air into and out of the case. The instru- ment mechanism converts the resultant pressure differential into a visual indication of the rate of climb or descent of the aircraft in feet per minute. The setting screw on the lower left corner of the in- strument is used to zero the pointer. The instrument has a single pointer and two adjoining scales. Refer to Chapter 31 for instrument markings. B. The pilot’s rate-of-climb is operated from a rated output from the pilot’s altimeter. This rated signal output, a phase reversing 400 Hz signal, is amplified and demodulated to operate a torque motor in the indicator. The motor drives the indicator pointer through instrument-type gearing. The instru- ment has a single pointer and two adjoining graduated scales. Refer to Chapter 31 for instrument markings. C. The airspeed/machmeter has a single pointer and dual scales for accurate speed control throughout the entire flight envelope. The pointer responds to pressure from the pitot heads. A conventional air- speed scale is calibrated in knots and has a reference pointer that is adjusted by rotating the MACH LIMIT PUSH knob on the face of the instrument. The Mach scale is calibrated in percent of Mach and is connected to an aneroid that moves the scale to compensate for changes in pressure altitude. A Mach scale reference pointer is adjusted by turning the MACH LIMIT PUSH knob on the face of the instrument. Refer to Chapter 31 for instrument markings. D. The copilot’s altimeter converts static pressure into a visual indication of aircraft altitude. The indica- tor, which has a barometric scale, and an adjustment knob and three pointers, is saduated in feet and has a range of 50,000 feet. The large pointer indicates hundreds of feet and makes 50 revolutions to move through the 50,000-foot range. The small pointer, which is an extension of the center dial disc, indicates ten-thousands of feet and makes one-half a revolution. The barometric scale indicates baro- metric pressure in inches of mercury, ranging from 28.1 to 31.0. Turning the adjustment knob will in- dex ambient pressure on the barometric scale. (Refer to 34-14-00 for further information on the pilot’s encoding altimeter system.) EFFECTIVITY: ALL 34-10-00 Page 1 MM-99 Feb 19/91 Island Enterprises International AeroTech Academy For Training Purpose Only ~Learjet E. One airspeed/mach indicator is installed for each crew position. Each instrument has a single pointer and dual scales for accurate Mach and airspeed indication throughout the flight envelope. The point- er responds to pressure supplied by the pitot-static probes. The indicator face consists of a stationary, circular airspeed scale reading from 0 to 400 knots, a movable circular Mach scale reading from .4 to .9 Mach, an airspeed/mach pointer, and a maximum allowable marker (barber pole). The movable Mach scale rotates with a change in altitude to maintain the correct Mach/airspeed relationship for any given altitude. Because the scales are maintained in the proper relationship, the airspeed/mach pointer indicates both Mach and airspeed over the range the Mach scale is visible. The maximum al- lowable marker (barber pole) is located over the Mach scale and rotates about the airspeed scale to compensate for altitude changes in the same manner as the Mach scale. The barber pole is positioned so that its lower edge is opposite 350 KIAS at all altitudes up to MMO. Once the MMO limit is ob- tained, the barber pole moves with the Mach scale to maintain the MMO position. A stationary red line is located at 300 KIAS. A white triangular reference ’bug" in the indicator is adjusted by rotating the knob on the instrument bezel. Three white "bugs" on the perimeter of the dial face are adjusted by sliding the "bug" to the desired position. The airspeed/mach indicators also contain airspeed and al- titude switches used by the overspeed warning system, stick puller, and stall warning system. I MM-99 Feb 19/91 EFFECTIVITY: ALL 34-10-00 Page 2 Island Enterprises International AeroTech Academy For Training Purpose Only Learjet Corpor;ition~ raillrcllance manual RBTE Cp CL~MB Z~DZCBTOB MAINTENBNCE PBBCTICES i. BIQIOVBLIINSTBLLBTION 4. Remove Pilot’s Bate of Climb Indicator (1) Remove electrical power from aircraft. (2) Lower pilot’s instrument panel. (3) Disconnect electrical connector from indicator. (4) Loosen instrument clamp screws and remove indicator from instrument panel. B, Install Pilot’s Bate of Qimb Indicator (1) Install indicator and tighten instrument clamp screws. (2) Connect electrical connector. (3) Raise and secure pilot’s instrument panel. (4) Restore electrical power to aircraft. C. Remove Copilot’s Bate of Climb Indicator (1) Remove electrical power from aircraft. (2) Lower copilot’s instrument panel. (3) Disconnect static line from indicator. Cap exposed openings. (4) Remove attaching parts and indicator from panel. D. Install Copilot’s Bate of Climb Indicator (1) Install indicator and secure with attaching parts. (2) Remove caps and connect static line to indicator. (3) Perform static system leakage check. (Refer to 34-11-00.) (4) Raise and secure copilot’s instrument panel. BPpBC’flVITI: BU. 34-10-01 Disk 914 Jun 12/87 IMM-99 Page 201 Island Enterprises International AeroTech Academy For Training Purpose Only ~Learjet AIRSPEED/MACHMETER MAINTENANCE PRACTICES i. REMOVAL/INSTALLATION A. Remove Airspeed/Machmeter (1) Remove electrical power from aircraft. (2) Ensure that Battery and Stall Warning Switches are OFF. (3) Lower applicable instrument panel. (4) Disconnect pitot and static lines from airspeed/machmeter. Cap all exposed fittings. (5) Remove attaching parts and airspeed/machmeter from instrument panel. B. Install Airspeed/Machmeter (1) Install airspeed/machmeter in panel and secure with attaching parts. (2) Remove caps and connect pitot and static lines to airspeed/machmeter. (3) Perform pitot and static systems leakage check. (Refer to 34-11-00.) (4) Raise and secure instrument panel. (5) Restore electrical power to aircraft. EFFECTIVITY: 35-002 THRU 35-505 EXCEPT 35-408, 36-002 THRU 34-10-02 36-053 NOT MODIFIED PER AAK 83-2, Page 201 MM-99 "Installation of FC-530 Autopilot" Feb 19/91 Island Enterprises International AeroTech Academy For Training Purpose Only Gates Le~rjet mainlenanoe ra~ual ALTMETBB HAI~II’ENBNCE PR8CTlCEs i. BEMOVBI~,IINSTBLLATION 8. Remove Bltimeter (1) Remove electrical power from aircraft. (2) Lower copilot’s instrument panel. (3) Disconnect static line from altimeter. Cap all exposed fittings. (4) Remove attaching parts and altimeter from aircraft. B, Install Altimeter (1) Install altimeter and secure with attaching parts. (2) Remove caps and connect static line to altimeter. (3) Perform static system leakage check. (Refer to 34-11-00.) (4) Raise and secure copilot’s instrument panel. (5) Restore electrical power to aircraft. EFFECTZVZTP: BI~L 34-10-03 MM-99 Page 201 Disk 914 Jun 12/87 Island Enterprises International AeroTech Academy For Training Purpose Only F~Learjet AIRSPEED/MACH INDICATOR ~1´•IAINTENANCE PRACTICES i. REMOVAL/INSTALLATION A. Remove Airspeed/Mach Indicator (See figure 201.) (1) Remove electrical power from aircraft. (2) Set Battery Switches and Stall Warning Switches to OFF. (3) Lower applicable instrument panel. (4) Disconnect electrical connector from airspeed/mach indicator. (5) Remove pitot and static lines from airspeed/mach indicator. Cap open ports of airspeed/mach indicator and pitot and static lines. (6) Remove attaching parts and remove airspeed/mach indicator from aircraft. B. Install Airspeed/Mach Indicator (See figure 201.) (1) Install airspeed/mach indicator and secure with attaching parts. (2) Remove caps from airspeed/mach indicator ports and pitot and static lines. Install pitot and stat- ic lines airspeed/mach indicator. (3) Connect electrical connector to airspeed/mach indicator. (4) Perform pitot and static systems leakage check. (Refer to 34-11-00.) (5) Raise and secure instrument panel. (6) Restore electrical power to aircraft. 2. ADJUSTMENT/TEST A. Functional Test of Stall Warning Altitude Switches NOTE: Perform functional test of stall warning altitude switches in accordance with the current in- spection interval specified in Chapter 5. (1) Connect pitot-static test to pitot and static systems. (Refer to Chapter 34.) (2) Set Stall Warning Switches to L and R and Battery Switches to BAT 1 and BAT 2. Ensure that an- gle-of-attack vanes are lowered to position where stall margin tangle-of-attack) indicator needles are in the green band. Ensure that flaps are fully retracted. (3) Slowly apply vacuum to system and observe pilot’s and copilot’s stall margin tangle-of-attack) in- dicators. At 22,500 (f750) feet, both indicators shall abruptly move toward yellow area. (4) Slowly bleed off vacuum and remove pitot-static tester. (5) Restore aircraft to normal. EFFECTIVITY: 35-408, 35-506 AND SUBSEQUENT, 36-054 AND SUBSEQUENT 34-10-04 AND PRIOR AIRCRAFT MODIFIED PER AAK 83-2, Page 201 MM-99 "Installation of FC-530 Autopilot" Feb 19/91 Island Enterprises International AeroTech Academy For Training Purpose Only Externally E(bunted Reference Bug (Typical Three Places) Maximum Allowable Airspeed Indicator KLAS Mal Mach Sub Mal 400 1 350 Single Airspeed 120C, internal Pointer 01130~ Reference cn Bug KNOfS 1 250 150 Reference Bug Control Knob ´•S .45 1(L Clamp Screw (Typical 4 Airspeed/Mach Indicator Figure 201 EFFECTIVITY: 35-408, 35-506 AND SUBSEQUENT, 36-054 AND SUBSEQUENT 34-10-04 AND PRIOR AIRCRAFT MODIFIED PER AAK 83-2, Page 202 MM-99 "Installation of FC-530 Autopilot" Feb 19/91 Island Enterprises International AeroTech Academy For Training Purpose Only ~Learjet PITOT AND STATIC SYSTEM DESCRIPTION AND OPERATION 1. DESCRIPTION (Seefigure 1.) A. Aircraft 35-002 thrt135-505 excez?t 35-408 and 36-002 thru 36-053 not modified t~er AAK 83-2, "lnsta2lation of FC-530 Autorn’lot. (1) Pitot pressure is obtained from two pitot heads, one located on each side of the nose compart- ment. (2) The left hand pitot head is connected to the pilot’s airspeed indicator. (3) The right hand pitot head is connected to the Mach Trim Switch, Mach Warning and Overspeed Switch, copilot’s airspeed indicator, and air data sensor. (4) Static pressure is sensed from 10 static ports. (a) The LH forward, LH aft, RH forward, and RH center static ports provide static pressure for the pilot’s and copilot’s instruments. On Aircraft 35-307 and Subseauent, 36-045 and Subseauent, and brior aircraft modified ~er AAK 79-10 or AMK 83-5, "lnstallation of Wing Fences, Stall Strips and Boundan/ Lauer Energizers," or SE 35/36-34-4, each of these four static ports will be circl’ed by a one-inch-wide, paint-free, polished band. (b) The RH forward and LH ah static ports are interconnected and are plumbed to the copilot’s instruments. (c) The LH forward and RH center static ports are interconnected and are plumbed to the pilot’s instruments. (d) An instrument alternate static source system is provided as a backup should blockage of the pilot’s static ports or tubes occur. The instrument alternate static source consists of a manual control valve mounted on the lower edge of the pilot’s instrument panel, a union installed in frame 5 which acts as a static port, and the hoses connecting the union and control valve to the pilot’s instruments through the union-type static port and the control valve. The control valve handle, when not in use, is safety wired in the CLOSED position with breakaway safety wire. (e) The RH aft static port provides static pressure for the cabin pressurization system. (f) An alternate static port, installed in the nose compartment, acts as a backup for the RH aft port should it become blocked. (g) The two shoulder static ports installed forward of the windshield halves supply static pres- sure to the autopilot air data sensor. For further information on the autopilot static system, re- fer to Chapter 22. (h) A static port located at frame 25 is used as the cabin safety valve static source. For further in- formation on the cabin safety valve static source, refer to Chapter 21. (5) The pitot heads, LH forward static port, LH aft static port, RH forward static port, and RH center static port are electrically heated to prevent moisture form freezing and obstructing the port openings. (Refer to Chapter 30 for coverage of the electric heating elements.) (6) On Aircraft 35-002 thru 35-059, 36-002 thru-36-017, the RH pitot and RH forward static port also provide pitot and static pressure to the flap load limiting airspeed switch. (7) Drain valves are installed at low points of the pitot and static plumbing to provide a means for rurrroft modlhai a~r AAK 13 12,"Installation of FC-530 Auto~ilot." (1) The pitot-static system consists of two pitot-static heads, four isolation valves, one STATIC SOURCE Switch, and six drain valves. (2) The LH pitot port is connected to the pilot’s mach/airspeed indicator (mach/overspeed switch- es). The RH pitot port is connected to the copilots’s mach/airspeed indicator (mach/overspeed switches), the mach switch, air data unit (Chapter 22), and optional equipment. Each pitot system is equipped with a drain valve to provide a means for draining accumulated moisture from the system. EFFECTIVITY: NOTED 34-11-00 Page 1 MM-99 Feb 19/91 Island Enterprises International AeroTech Academy For Training Purpose Only ~Learjet (3) forward static port on either pitot-static head is cross-connected to the aft static port on the opposite pitot-static head to eliminate yaw errors. The pilot’s instruments are connected to the LH static 1 port and RH static 2 port. The copilot’s instruments, the mach switch, the air data unit, and any optional equipment are connected to the RH static 1 port and the LH static 2 port. (4) The pilot’s and copilot’s static systems are equipped with two isolation valves for each system. Operation of the STATIC SOURCE Switch controls the isolation valves for best results. (5) The pressurization control module is equipped with a separate static source and alternate static source. Refer to Chapter 21 for pressurization system information. (6) On Aircraft 35-661 and Subseauent and 36-064 and Subseauent, a static test Port for cabin pressuriza- tion checks has been installed at frame 6 (7) Component Description. (a) The pitot-static heads are located just aft of frame 4 on each side of the nose section. The pitot- static heads aerodynamic shape provides an error correction factor in all flight configurations. The pitot-static heads are equipped with heating elements to prevent moisture from freezing on the obstructing the pitot-static ports. (b) The static isolation valves are located forward of frame 5. (c) The STATIC SOURCE Switch is located on the center switch panel. (d) The drain valves are located just outboard of the nose wheel well between frames 4 and 5. The valves are spring loaded to the closed position and are sealed with an internal O-ring. 2. OPERATION (See figure 2.) I (1) The pitot heads admit ram air pressure at their forward ends to provide pitot pressure to the in- struments connected to the pilot’s system. (2) The static ports accurately sense static air pressure for the instruments connected to the static sys- tem. (3) The drain valves are for draining accumulated moisture and are opened by depressing the knurled hollow stem. I B. Aircraft 35-408. 35-506 and Subseauent 36-054 and Subseauent and tlr’or aircraft modified aer AAK 83-2, Ins tallatiolz of FC-530 Au toai2ot. (1) The pitot-static heads admit ram air pressure at the forward end to provide pitot pressure to the instruments connected to the pitot system. The static ports on the sides of the pitot-static heads accurately sense static air pressure for the instruments connected to the pilot’s and copilot’s static systems. (2) The static system isolation valves are controlled by a three-position STATIC SOURCE Switch. The valves are solenoid actuated and normally open. (3) The STATIC SOURCE Switch leaves both static systems isolation valves open when set to BOTH, closes the LH isolation valves when set to RIGHT, or closes the RH isolation valves when set to LEFT. (4) The drain valves are for draining accumulated moisture and are opened by depressing the knurled hollow stem. EFFECTIVITY: NOTED 34-11-00 Page 2 MM-99 Feb 19/92 Island Enterprises International AeroTech Academy For Training Purpose Only ~Learjet Rate of Climb Indicator Airspeed/Mack Zndicator 1Utimeter Mach/Overspeed Switch ~irspeed S~Jitch Al time ter Alternate Static Source Mach Switch Static Port Manual Control Valve Drain Valve ~Airspeed/Mach Indicator RH Pitot Head P Drain Valve Static Port LH Pitot Bead Pitot and Static System Component Location Figure 1 (Sheet 1 of 4) EFFECTIVITY: 35-002 THRU 35-059, 36-002 THRU 34-11-00 36-017 NOT MODIFIED PER AAK 83-2, Page 3 MM-99 "Installation of FC-530 Autopilot" Feb 19/91 Island Enterprises International AeroTech Academy For Training Purpose Only ~9Learjet Rate of Climb Indicator Airspeed/Mach indicator Mach Switch ALtimeter ´•´•´•´•1´•´•--´• Illternate Mach Static Port A Drain Valve Manual a~P" Control Valve Z ~irspeed/Mach Indicator RH Pitot Head Drain Valve .~Y Static Port Pressure Switch 35-067 thru 35-505 except 35-408, 36-018 thru 36-053 and prior Aircraft equipped Approach Speed System Detail A Pitot and Static System Component Location Figure 1 (Sheet 2 of 4) EFFECTIVITY: 35-060 THRU 35-505 EXCEPT 35-408, 36-018 THRU 34-11-00 36-053 NOT MODIFIED PER AAK 83-2, Page 4 MM-99 "Installation of FC-530 Autopilot" Feb 19/91 Island Enterprises International AeroTech Academy For Training Purpose Only ~Ie 35663 and Subsequent and 36-064 and Subsequent Frase S I To Copilot’s Airspeed Indicator ____ Mach Switch (34-11-04) ~-To Pilot’s Airspeed Indicator Static I_ine (Ref) ~3 ~P ~Tee Ltot Drain Static lines (Ref) Valve (34-11-02) Right Pitot-Static Head (34-11-01) Pitot DrainValve (31-11-02) Pitot-Static Head (34-11-01) PITOT SYSTEM 14-174(3-1 14-174(3 Pitot and Static System Component Location Figure 1 (Sheet 3 of 4) EFFECTIVITY: 35-408, 35-506 AND SUBSEQUENT, 36-054 AND SUBSEQUENT 34-11-00 AND PRIOR AIRCRAFT MODIFIED PER AAK 83-2, Page 5 MM-99 "Installation of FC-530 Autopilot" Feb 19/91 Island Enterprises International AeroTech Academy For Training Purpose Only ~9Learjet ~Ic 35-661 and Subsequent and 36-064 and Subsequent ~Ic 35663 and Subsequent and Pressurization Static 36-064 and Subsequent Port (Chapter 21) To Pressurization Module (Chapter 21) Static Test Port ~I: To Copilot’s Instruments Mach Switch (34-11-04) klo Pilot’s Rate-of-ClimbToPilot’s Pitot Line Indicator (Ref) To Pilot’s Altimeter No. 2 Right Isolation Valve (8326) (34-11-03) Airspeed Indicator Tee No. 1 Right Isolation Valve (8327) (34-1 Frane 5 Static Drain Valve (34-11-02) No. 2 Isolation Static Line (S1) II II Valve (83129) (34-11-03) Static Line (S2) No. 1 Left Isolation Right Pitot-Static Valve (8328) Head (34-11-01) (34-11-03) Static Line (52) Static Line (S1) To Air Data Unit II a/l’ I_eft Pitot-Static Pitot Line (Ref) Head (34-11-01) Static Drain Valve (34-11-02) 14-174C-1 STATIC SYSTM 14-174C Pitot and Static System Component Location Figure 3 (Sheet 4 of 4) EFFECTTVITY: 35-408, 35-506 AND SUBSEQUENT, 36-054 AND SUBSEQUENT 34-11-00 AND PRIOR AIRCRAFT MODIFIED PER AAK 83-2, Page 6 MM-99 "Installation of FC-530 Autopilot" Feb 19/91 Island Enterprises International AeroTech Academy For Training Purpose Only ~4Learjet LH Pitot RH Pitot Head Head To Air Data Sensor (22-10-02) Airspeed Switch Drainll I I´• II Drain Valve U I I~ Y Valve LH Fwd n_ I II -nRH Fwd Staticll v///u////////////////~h ’IStatic Port Port Drain Drain Valve Valve RH Center LH AEt I, Static Port Static Port RH ~t Static Port Alt Static Port (In Nose Compt) ch Tr Switch Pressurization Module Assembly Altimeter YA AL timeter (Pilot) (Copilot) Mach Warning Overspeed Switch Airspeed and Mach Number Indicator (Pilot) Rate o~ Climb Static PortI_~(COpllor)Instrument AUternate Static Source Valve Airspeed and Mach Number Indicator (Copilo t) Pitot and Static System Schematic Figure 2 (Sheet 1 of 3) EFFECTIVITY: 35-002 THRU 35-059, 36-002 THRU 34-11-00 36-017 NOT MODIFIED PER AAK 83-2, Page 7 MM-99 "lnstallation of FC-530 Autopilot" Feb 19/91 Island Enterprises International AeroTech Academy For Training Purpose Only ~Learjet LH Pitot KH Pitot Head Head To Air Data Sensor (22-10-02) Drain II II Drain Valve u I I U Valve LH Fwd P I T~RH Fwd Static Portl’ Static Port Drain Y(G~ t~rlh, Drain Valve ~C´•3h I Valve LH Aft P C/1 I ~r ~e I M r ’JRH Center Static Portl’ IStatic Port AUtitude Pressure RH ~fe Switch Static Port Illt Static Port (In Nose Compt) Mach Trim Switch Pressurization Module Assembly Altimeter I I ALtimeter (Pilot) a (Copilot) Mach Warning Overspeed Switch Airspeed and Mach Number Indicator (Pilot) Static Port YA Rate of Climb (Frame 5) (Copilot) Instrument AUternate Static Source Valve Airspeed and Mac~ ~e 35-067 thru 35-505 except 35-408, 36-018 thru 36-053 and Number Indicator prior Aircraft equipped with Reduced Approach Speed (Copilot) System Pitot and Static System Schematic Figure 2 (Sheet 2 of 3) EFFECTIVITY: 35-060 THRU 35-505 EXCEPT 35-408, 36-018 THRU 34-11-00 36-053 NOT MODIFIED PER AAK 83-2, Page 8 MM-99 "Installationof FC-530 Autopilot" Feb 19/91 Island Enterprises International AeroTech Academy For Training Purpose Only ~Learjet PILOTS SI.ATIC SY~TEM I I COPILOTSSTAnCSYS~TM ALTERNATE STATIC SOURCE CABIN PRESSURIUTION ~------J L----~ I I STATIC CONTROL MODULE I 1 I) PORT P(LOrS COPILOTS INSTRUMENTS INSTRUMENTS VERTICAL SPEED lil I I VERTICAL SPEED INDICATOR R I I INDICATOR COPILOT’S PILOT~S PITOTISTATIC PITOTISTATIC PROBE PROBE ALTIMETER W II ALTIMETER PITOT I I PITOT STATIC (I ~nr I II YIILC I STATIC 1 L STATIC 2 MACHlAIRSPEED ISOLATION VALVE MACHIAIRSPEED INDICATOR NO ’ND’CATOR I I STAT16 2 STATIC 2 L STATIC ~e I I~R STATIC 2 ISOLATION VALVE I M II ’2 I I I I ISOLATION VALVE N.O I I II N.O. A STATIC ISOLATION VALVE N.O AIR DATA CENTER SWITCH PANEL OPTIONAL EOUIPMENT 1:--111 L .71 eorcl I MACH SWITCH n AIR DATA i~ i- DRAIN DRAIN V*LYEIYW n v*rvls Y*LYIS STATIC SOURCE Pitot and Static System Schematic Figure 2 (Sheet 3 of 3) EFFECTIVITY: 35-408, 35-506 AND SUBSEQUENT, 36-054 AND SUBSEQUENT 34-11-00 AND PRIOR AIRCRAF~ MODIFIED PER AAK 83-2, Page 9 ~M-99 "Installation of FC-530 Autopilot" Feb 19/91 Island Enterprises International AeroTech Academy For Training Purpose Only LEARJET 35/35A/36/36A MAINTENANCE MANUAL PITOT AND STATIC SYSTEM MAINTENANCE PRACTICES 1. Maintenance Practices NOTE: Maintenance personnel should familiarize themselves with the following general maintenance practices prior to performing maintenance on the system. A. When performing static system leak check, it will be necessary to apply vacuum to both pitot and static systems simultaneously. This will prevent severe pressure differential which could cause in- strument damage. Pressure in the pitot system must always be equal to or slightly greater than that in the static system. WARNING: PULL L PITOT HT CIRCUIT BREAKER ON PILOT’S C/B PANEL AND R PITOT HT CIRCUIT BREAKER ON COPILOT’S C/B PANEL BEFORE PERFORMING THE FOLLOWING PROCEDURES TO PREVENT DAMAGE TO EQUIPMENT AND POSSIBLE INJURY. CAUTION: TO AVOID DAMAGE TO AIR DATA SENSOR, ALWAYS APPLY EQUAL VA@U- UM TO RH PITOT HEAD, SHOULDER STATIC PORTS, AND COPILOT’S STAT- IC SYSTEM. B. Whenever a pitot or static line is disconnected, all exposed fittings should be capped or plugged. C. All pitot and static line B-nuts incorporate a fitting seal. Each time a line is disconnected, a new fit- ting seal must be installed. D. Pitot system leak check should be performed and all leaks repaired prior to performing static leak check. E. Pitot and static system leak checks should be performed in accordance with current inspection inter- vals specified in Chapter 5 as well as anytime an instrument is replaced or a connection is loosened. All maintenance and inspections should be completed prior to performing leak checks. F. Use of system schematic is recommended to prevent application of reverse pressure and to help de- termine location of leaks. G. Test equipment should be checked for leaks prior to use. H. The rate of pressure change or pressure applied should not exceed design limits of instruments speci- fied in the following procedures. 2. Inspection/Check (Aircvaft 35-002 thru 35-505 exc~t 35-408, 36-002 thru 36-053 not modified lier AAK 83-2, Installation of FC-530 Autotlilot A. Toolsand Equipment NOTE: Equivalent substitutes may be used in lieu of the following: NAME PART NUMBER MANUFACTURER USE Pitot and Static Tester 1811e Barfield Instrument, Co. Test System. Atlanta, GA Pressure Seal Tape 3M Co. Seal Pitot and Saint Paul, MN Static ports. B. PitotSystem Operational Check (1) The difference between the pilot’s and copilot’s airspeed indicator shall not exceed 5 knots while maintaining a constant speed within a range of 80 to 140 knots and not exceed 9 knots while maintaining a constant speed within a range of 150 to 400 knots. EFFECTIVITY: NOTED 34-11-00 Page 201 MM-99 Feb 11/00 Island Enterprises International AeroTech Academy For Training Purpose Only LEARJET 35135A138/36A MAIN7ENANCE MANUAL C. PitotSystem LeakageCheck NOTE: All pitot line B-nuts incorporate a fitting seal, P/N AP50A-4 or AP50A-6. Each time a pitot line B-nut is disconnected, a new fitting seal must be installed. (1) Ensure that all pitot lines are secure and pilot instruments are securely connected. (2) Attach hose from pitot static test set to left pitot tube making sure drain hole in pitot tube is cov- ered. CAUTION: APPLY ONLY PRESSURE (NOT VACUUM) TO THE PITOT LINES. APPLY PRESSURE VERY SLOWLY UNTIL 80 KNOTS IS REACHED; PRESSURE AP- PLICATION AFTER THIS POINT MUST NOT EXCEED 20 KNOTS PER SEC- OND. (3) Slowly apply pressure until pilot’s airspeed indicator indicates 300 knots. Rate of pressure in- crease shall not increase the airspeed indicator in excess of 20 knots per second after 80 knots is reached. (4) Turn off pressure; this will seal system. System pressure drop shall be less than 5 knots in a 5 minute period. (5) If excessive leakage is indicated, recheck fittings and repeat steps (1) through (4). CAUTION: TO AVOID DAMAGE TO AIRCRAFT INSTRUMENTS, DO NOT EXCEED 20 KNOTS PER SECOND WHEN VENTING ATMOSPHERIC PRESSURE INTO PITOT SYSTEM. (6) Slowly release pressure and remove test unit, checking that pitot tube is clear of obstructions. (7) Repeat above procedure utilizing right pitot tube and copilot’s airspeed indicator. D. Static System Leakage Check NOTE: All static line B-nuts incorporate a fitting seal, P/N AP50A-4 or AP50A-6. Each time a stat- ic line B-nut is disconnected, a new fitting seal must be installed. (1) Instrument Static Lines NOTE: The following procedure is applicable for either the pilot’s or copilot’s static systems. Check the static systems individually. Steps (a) thru (f) consist of a typical vacuum system check. Figures shown will vary with the geographical location where check is make. In all cases, the acceptable check consists of evacuation of the static system until a pressure differential is obtained. Without additional pumping, for a period of 1 minute, the indicated loss of altitude shall not exceed 2% of the equivalent altitude of the maximum cabin differential pres- sure or 100 feet, whichever is greater. An altitude to inches of mercury (Hg) conversion table is provided to assist personnel in performing the check. All altitude readings are taken to the nearest 100 feet. (a) Ensure that all instruments and lines are securely connected and all drain lines are tightly capped. Close the alternate static source manual control valve. (b) Connect pitot/static test set or equivalent to one static port (either right or left) while block- ing the remaining static port. EFFECTIVITY: 35-002 THRU 35-505 EXCEPT 35-408, 36-002 THRU 34-11-00 36-053 NOT MODIFIED PER AAK 83-2, Page 202 MM-99 "Installation of FC-530 Autopilot" Feb 11/00 Island Enterprises International AeroTech Academy For Training Purpose Only LEARJET 35/35A/36136A MAINTENANCE MANUAL (c) Determine local pressure altitude and convert to inches of mercury tin. Hg). The local pres- sure altitude may be determined by setting the Barometric Correction on the altimeter to 29.92 in. Hg and reading the altitude from the indicator. Alternatively, the barometric pres- sure can be determined directly using a barometer. Example: Set barometric correction on altimeter to 29.92 in. Hg and read current pressure altitude of 1300 feet. From Figure 202, 1300 feet 28.54in. Hg. (d) Convert the cabin differential pressure (8.9 psi) to inches of mercury by multiplying 8.9 by 2.04 (the equivalent of 1 psi in inches of mercury) which equals 18.15 Hg. (e) Subtract the results of step (d) from results of (c) and convert to altitude. This is the desired altimeter reading to which the system must be evacuated. Example: 28.54 Hg minus 18.15 Hg 10.39. 10.39 converted to altitude 26,500 feet (this is the required altimeter reading). CAUTION: TO AVOID DAMAGE TO AIRCRAFT INSTRUMENTS, APPLY ONLY SUCTION (VACUUM) TO STATIC SYSTEM AND ENSURE THE TEST SET CROSSBLEED VALVE IS OPEN. TO AVOID DAMAGE TO AIRCRAFT INSTRUMENTS, DO NOT EXCEED 5000 FEET PER MINUTE RATE OF CLIMB OR DESCENT. (f) Evacuate the system until the altimeter reading determined in step (e) is obtained. Turn off vacuum source, sealing the system. Loss of altitude in 1 minute shall not exceed 2% of the re- quired altimeter reading. Example: Required altimeter reading 26,500 feet. 2% of 26,500 feet 530 feet (maximum drop in 1 minute is 530 feet). (g) Check the alternate static source by blocking the external static source and opening the manu- al control valve. Loss of altitude shall not exceed the required reading obtained in step (f). (h) If acceptable, release vacuum slowly and perform check of remaining static system. EFFECTIVITY: 35-002 THRU 35505 EXCEPT 35-408, 36-002 THRU 34-11-00 36-053 NOT MODIFIED PER AAK 83-2, Page 203 MM-99 "Installation of FC-530 Autopilot" Feb 11/00 Island Enterprises International AeroTech Academy For Training Purpose Only LEARJET 35135A136/36A MAINTENANCE MANUAL Rate of Climb Indicator ALtspeed/Mach Indicator ALtimetet Mach/Overspeed SwitchAirspeed 1 Altimeter Snitch Alternate Static Source Static Port Mach Switch Manual Control Valve RH Pitot Head Airspeed/Mach Indicator Drain Valve Static Port LH Pitot Head Pitot and Static System Flumbing Installation Figure 201 (Sheet 1 of 2) EFFECTIVrTY: 35-002 THRU 35-059, 36-002 THRU 34-11-00 36-017 NOT MODIFIED PER AAK 83-2, Page 204 MM-99 "Installation of FC-530 Autopilot" Feb 11/00 Island Enterprises International AeroTech Academy For Training Purpose Only LEARJET 35/35A136136A MAINTENANCE MANUAL Rate of Climb indicator Airspeed/Mach indicator ALtimeter Mach Sw~tch Altimeter Alternate Static Source Static Port Mach Switch A Manual Control Valve Drain Valve ZRH Pitot Head Airspeed/Mach Indicator Drain Valve *Altitude Static Port Pressure Swi tch ~e 35-067 thru 35-505 except 35-408, 36-018 thru 36-053 and prior Aircraft equipped with Reduced Approach Speed System LH Pitot Head Detail A Pitot and Static System Plumbing Installation Figure 201 (Sheet 2 of 2) EFFECTIVITY: 35-060 THRU 35605 EXCEPT 35-408, 36-018 THRU 34-11-00 36-053 NOT MODIFIED PER AAK 83-2, Page 205 MM-99 "Installation of FC-530 Autopilot" Feb 11/00 Island Enterprises International AeroTech Academy For Training Purpose Only LEARJET 35135A/36136A MAINTENANCE MANUAL STATIC PRESSURE (IN INCHES OF MERCURY) FOR VALUES OF PRESSURE ALTITUDE (IN FEET) Pressure Altitude 0 100 200 300 1100 500 600 700 800 900 in Pt. (Above Sea -1,000 31.0185 -0 30.0295 30.1382 30.2471 30.3563 30.4659 30.5758 30.6860 30.7965 30.9073 0 29.9213 29.8133 29.7056 29.5983 29.4913 29.3846 29.2782 29.1721 29.0663 28.9608 1,000 28.8557 28.7508 28.&463 28.5421 28.4382 28.3345 28.2312 28.1282 28.0255 27.9231 2000 27´•8210 27.7193 27.6178 27.5166 27.4157 27.3151 27.2148 27.1148 27.0151 26.9158 3,000 26.8167 26.7179 26.6193 26.5211 26.4232 26.3256 26.2283 26.1312 26.0345 25.9380 4,000 25.8418 25.7459 25.6504 25.5550 25.4600 25.3653 25.2708 25.1767 25.0828 24.9892 5,000 24.8959 24.8029 24.7101 24.6177 24.5255 24.4336 24.3419 24.2506 24.1595 24.0687 6,000 23.9782 23.8880 23.7980 23.7083 23.6189 23.5297 23.4409 23.3523 23.2639 23.1759 7,000 23.0881 23.0006 22.9133 22.8263 22.7396 22.6532 22.5670 22.4811 22.3954 22.3100 8,000 22.2249 22.1401 22.0555 21.9711 21.8871 21.8033 21.7197 21.6364 21.5534 21.4706 9,000 21.3881 21.3058 21.2238 21.1421 21.0606 20.9793 20.8983 20.8176 20.7371 20.6569 10,000 20.5769 20.4972 20.4177 20.3385 20.2595~- 20.1808~- 20.1023 20.0241-19.9461 1 11,000 19.7909 19.7136 19.6366 19.5599 19.4834 19.4071 19.3310 19.2553 19.1797 19.1044 15000 19.0293 18.9545 18.8799 18.8055 18.7314 18.6575 18.5839 18.5105 18.4373 18.3614 13,000 18.2917 18.2192 18.1470 18.0749 18.0032 17.9316 17.8603 17.7892 17.7184 17.6477 14,000 17.5773 17.5072 17.4372 17.3675 17.2980 17.2287 17.1597 17.0909 17.0223 16.9539 15,000 16.8858 16.8187 16.7501 16.6827 16.6154 16.5183 16.4815 16.4149 16.3485 16.2824 16,000 16.2161 16.1507 16.0851 16.0198 15.9547 15.8899 15.8252 15.7608 15.6965 15.6325 17,000 15.5687 15.5051 15.4417 15.3785 15.3155 15.2582 15.1902 15.1279 15.0657 15.0038 18,000 14.9421 14.8806 14.8192 14.7581 14.6972 14.6365 14.5760 14.5157 14.4556 14.3957 19,000 14´•3360 14.2765 14.2173 14.1582 14.0993 14.0406 13.9821 13.9238 13.8657 13.8078 20,000 13.7501 13.6926 13.6352 13.5781 13.5212- 13.4~44- 13.4079 13.3516- 13.2954- 13.2394 21P00 13.1836 13.1281 13.0727 13.0175 12.9624 12.9076 12.8530 12.7985 12.7442 12.6902 22,000 12.6363 12.5826 12.5290 12.4757 12.4225 12.3696 12.3168 12.2642 12.2117 12.1595 23,000 12´•1074 12.0556 12.0039 11.9523 11.9010 11.8498 11.7988 11.7480 11.6974 11.6469 24,000 11.5967 11.5466 11.4966 11.4469 11.3973 11.3479 11.2987 11.2496 11.2007 11.1520 25,000 11´•1035 11.0551 11.0069 10.9589 10.9110 10.8634 10.8158 10.7685 10.7213 10.6743 26,000 10.6274 10.5808 10.5342 10.4879 10.4417 10.3957 10.3498 10.3041 10.2586 10.2133 27,000 10.1681 10.1230 10.0781 10.0334 9.9890 9.9445 9.90023 9.85616 9.81224 9.76&48 28,000 9.72488 9.68144 9.63815 9.59502 9.55205 9.50923 9.46658 9.42407 9.38172 9.33952 29,000 9.29748 9.25559 9.21385 9.17227 9.13083 9.08956 9.04843 9.00745 8.96662 8.92594 30,000 8.88541- 8.84503 8.80480-8.7~472 8.72479 8.68500-8.64536- 8.60587 8.56652 8.52732 31,000 8.48826 8.44935 8.41059 8.37197 8.33349 8.29515 8.25696 8.21891 8.18100 8.14324 32,000 8.10561 8.06813 8.03079 7.99358 7.95652 7.91960 7.88281 7.84616 7.80966 7.77328 33,000 7´•73705 7.70095 7.66199 7.62917 7.59348 7.55793 7.52251 7.48722 7.45208 7.41706 34,000 7´•38218 7.34743 7.31281 7.27833 7.24397 7.20975 7.17566 7.14170 7.10787 7.07417 35,000 7.04060 7.00716 6.97385 6.94066 6.90761 6.87468 6.84188 6.80920 6.77665 6.74423 36,000 6.71194 6.67977 6.61774 6.58414 6.52115 6.45877 37,000 6.39698 6.33578 6.27517 6.21514 6.15568 38,000 6.09679 6.03846 5.98070 5.92348 5.86681 39,000 5.81069 5.75510 5.70004 5.64551 5.59151 40,000 5.53801 5.48503 5.43256 5.38059 5.32911 41,000 5.27813 5.22764 5.17763 5.12809 5.07904 42,000 5.03045 4.98232 4.93466 4.88745 4.84069 93,000 4.79439 4.74852 4.70309 4.65810 4.61354 44,000 4.56940 4.52569 4.48239 4.43951 4.39704 45,000 4.35497 4.31331 4.27205 4.23118 4.19070 46,000 4.15061 4.11090 4.07157 4.03262 3.99405 47,000 3.95584 3.91799 3.88051 3.&1339 3.80662 48,000 3.77020 3.73413 3.69481 3.66303 3.62799 49,000 3.59328 3.55890 3.52486 3.49113 3.45774 50,000 3.42466 3.39189 3.35945 3.32731 3.29548 51,000 3.26395 3.23273 3.20180 3.17117 3.14083 Conversion Table Altitude to Inches of Mercury Figure 202 EFFECTIVITY: ALL 34-11-00 Page 206 MM-99 Feb 11/00 Island Enterprises International AeroTech Academy For Training Purpose Only LEARJET 35/35A136/36A MAINTENANCE MANUAL 3. Inspection/Check (Aircraft 35-408, 35-506 and Subse4uent, 36-054 and Subseauent and zlrior aircraft modified t7er AAK g3-2."lnstallafion of FC-530 Autotlilot A. Toolsand Equipment NOTE: Equivalent substitutes may be used in lieu of the following: NAME PART NUMBER MANUFACTURER USE Rtot and Static Tester 1811G Barfield Instrument Co. Test System. Atlanta, GA Pitot-Static Test Adapter L50-612* Learjet Inc. Adapt Pitot Wichita, KS Static Tester to Mast. Adapters (2 each) PSS 50476-3-4-4 must be modified with kits (2 each) SSR 476 to test Model 35/36 air- craft. The modified adapter part number is PSS 50476M1-3-4r4. B. PitotSystemOperational Check (1) The difference between the pilot’s and copilot’s airspeed indicator shall not exceed 5 knots while maintaining a constant speed within a range of 80 to 140 knots and not exceed 9 knots while maintaining a constant speed within a range of 150 to 400 knots. C. Pitot System Leakage Check (See Figure 204.) (1) Connect a pitot-static test adapter (P/N L50-612) to pilot’s pitot- static mast. (2) Connect pitot-static tester (P/N 1811G) to pitot-static test adapter. CAUTION: USE EXTREME CARE NOT TO CONTAMINATE INSTRUMENTS OR PITOT- STATIC SYSTEM. TO PREVENT DAMAGE TO AIRCRAFT INSTRUMENTS, APPLY PRESSURE TO PITOT-STATIC SYSTEM SLOWLY UNTIL THE AIRSPEED INDICATOR INDICATES 80 KNOTS. INCREASED AIRSPEED BEYOND 80 KNOTS SHALL NOT EXCEED A RATE OF 20 KNOTS PER SECOND. (3) Apply pressure to pitot system (very slowly until airspeed indicator indicates 80 knots). Increase airspeed to 300 knots at a rate not to exceed 20 knots per second. (4) Turn off pressure, sealing off the system. The system pressure drop in 5 minutes shall be less than 5 knots on airspeed indicator. (5) Depressurize system at a rate not more than 20 knots per second. (6) Repeat steps (1) through (5) for copilot’s pitot system. D. Static System Plumbing Check (See Figure 205.) (1) Set Battery and Primary and Secondary Inverter Switches on. (2) Set STATIC SOURCE Switch to RIGHT. (3) Ensure that pitot-static tester adapter with pitot-static tester attached is properly installed on right pitot-static mast. Disconnect tester from static 2 system at mast. EFFECTIVITY: 35-408, 35-506 AND SUBSEQUENT, 36-054 AND 34-11-00 SUBSEQUENT AND PRIOR AIRCRAFT MODIFIED Page 207 MM-99 PER AAK 83-2, "Installation of FC-530 Autopilot" Feb 11/00 Island Enterprises International AeroTech Academy For Training Purpose Only LEARJET 35/35A136136A MAINTENANCE MANUAL CAUTION: TO AVOID DAMAGE TO AIRCRAFT INSTRUMENTS AND TESTER AIR- SPEED INDICATOR, ENSURE THAT THE CROSS-BLEED VALVE ON PITOT- STATIC TESTER IS OPEN WHEN APPLYING A VACUUM TO THE PITOT- STATIC SYSTEM. TO AVOID DAMAGE TO AIRCRAFT INSTRUMENTS, DO NOT EXCEED 5000 FEET PER MINUTE RATE OF CLIMB OR DESCENT. DO NOT ALLOW AIRSPEED TO DECREASE BELOW ZERO. (4) Open tester cross-bleed valve. Apply a vacuum to copilot’s pitot- static system until tester altime- ter indicates 28,000 feet altitude. Do not exceed a rate-of-climb of 2,000 feet per minute. (5) Shut off vacuum source at 28,000 feet and seal off pitot-static system. System leakage in one min- ute shall not cause tester altimeter to indicate any less than 27,640 feet or 360 feet in one minute. CAUTION: TO AVOID DAMAGE TO AIRCRAFT INSTRUMENTS, DO NOT EXCEED 5000 FEET PER MINUTE RATE OF CLIMB OR DESCENT. DO NOT ALLOW AIRSPEED TO DECREASE BELOW ZERO. (6) With tester cross-bleed valve open, release vacuum from pitot-static system. Do not release vacu- um at a rate to exceed 2,000 feet per minute. (9) Remove pitot-static tester adapter with pitot-static tester attached from copilot’s pitot-static mast and install on pilot’s pitot-static mast. (8) Set STATIC SOURCE Switch to LEFT. (9) Repeat steps (4) through (6) for the pilot’s static system. I" ser AAK 83-2."lnstallation of FC-530 Autotlilot")Adjustment~est(Aircraft 35-408, 35-506 and Subseauent. 36-054 and Subseauent and Ilrior aircraft modified A. Pitot-Static Isolation Valve Functional Test I Perform Pitot-Static Isolation Valve Functional Test in accordance with inspection intervals specified in Chapter 5. (1) Install pitot-static test adapter to pilot’s pitot-static mast and connect pitot-static tester to pilot’s static port 1. (2) Set STATIC SOURCE Switch to BOTH. CAUTION: WHEN APPLYING VACUUM TO THE PITOT-STATIC SYSTEM, ENSURE THAT TESTER CROSS-BLEED VALVE IS OPEN. TO AVOID DAMAGE TO AIRCRAFT INSTRUMENTS, DO NOT EXCEED 5000 FEET PER MINUTE RATE OF CLIMB OR DESCENT. DO NOT ALLOW AIRSPEED TO DECREASE BELOW ZERO. (3) Seal off static ports on copilot’s mast. (4) With tester cross-bleed valve open, apply a vacuum to the pilot’s pitot-static port 1 until tester al- I timeter indicates 1,500 feet above field elevation. Do not exceed a rate-of-climb of 5000 feet per minute. (5) Slowly remove seal on copilot’s static port 2 (refer to Figure 204), and verify air flow at static port (6) Seal copilot’s static port 2. (7) Disconnect pitot/static tester vacuum source from pilot’s pitot/static port 1 and connect to pilot’s pitot/static port 2. (8) With tester cross-bleed valve open, apply a vacuum to pilot’s static Port 2 until tester altimeter in- I dicates 1,500 feet above field elevation. Do not exceed a rate-of-climb of 2,000 feet per minute. EFFECTIVITY: 35-408, 35-506 AND SUBSEQUENT, 36-054 AND 34-11-00 SUBSEQUENT AND PRIOR AIRCRAET MODIFIED Page 208 MM-99 PER AAK 83-2, "Installation of FC-530 Autopilot" Feb 11/00 Island Enterprises International AeroTech Academy For Training Purpose Only LEARJET 35/35A/36/36A MAINTENANCE MANUAL (9) Remove seal from copilot’s static port 1 and verify air flow at static port 1. (10) Seal off static ports on copilot’s mast. (11) Set STATIC SOURCE Switch to LEFT. (12) With tester cross-bleed valve open, apply a vacuum to pilot’s pitot-static system until aitimeter in- dicates 1,500 feet above field elevation. Do not exceed a rate-of-climb of 2,000 feet per minute. I (13) Slowly remove seals from copilot’s mast and verify no air flow at copilot’s static ports 1 and 2. (14) Set STATIC SOURCE Switch to BOTH. Verify airflow at copilot’s static ports 1 and 2. (15) Install pitot-static test adapter to copilot’s pitot-static mast and connect pitot-static tester to copi- Ilot’s static port 1. (16) Seal off static ports on pilot’s mast. (17) Set STATIC SOURCE Switch to RIGHT. (18) With tester cross-bleed valve open, apply a vacuum to copilot’s pitot-static system until tester al- timeter indicates 1,500 feet above field elevation. Do not exceed a rate-of-climb of 2,000 feet per I minute. (19) Remove seals from pilot’s mast and verify no air flow at Pilot’s static ports 1 and 2. 1 (20) Set STATIC SOURCE Switch to BOTH. Verify air flow at pilot’s static ports 1 and 2. CAUTION: TO AVOID DAMAGE TO AIRCRAFT INSTRUMENTS, DO NOT EXCEED 5000 FEET PER MINUTE RATE OF CLIMB OR DESCENT. DO NOT ALLOW AIRSPEED TO DECREASE BELOW ZERO. (21) Release vacuum from the pitot-static system. (22) Remove pitot-static tester from pitot-static test adapter. (23) Remove pitot-static test adapter from aircraft. EFFECTIVITY: 35-408, 35-506 AND SUBSEQUENT, 36-054 AND 34-11-00 SUBSEQUENT AND PRIOR AIRCRAFT MODIFIED Page 209 MM-99 PER AAK 83-2, "Installation of FC-530 Autopilot" Feb 11/00 Island Enterprises International AeroTech Academy For Training Purpose Only LEARJET 35135A/36136A MAINTENANCE MANUAL Static Port (Cabin Pressure Chapter 21) Pitot Pressure-Copilot’s --1 /-Mach Switch (Ref) Airspeed Indicator (Chapter 34) Frame 5 (Ref) Pitot Pressure-Pilot’s Airspeed Indicator Static System (Figure 204) Drain Valve Copilot’s Pitot-Static Head Pitot Pressure (to Pilot’s Pitot-Static Head Air Data Unit) (Chapter 22) Drain Valve Pitot System Plumbing Installation Figure 203 EFFECTIVITY: 35-408, 35-506 AND SUBSEQUENT, 36-054 AND 34-11-00 SUBSEQUENT AND PRIOR AIRCRAFT MODIFIED Page 210 MM-99 PER AAK 83-2, "Installation of FC-530 Autopilot" Feb 11/00 Island Enterprises International AeroTech Academy For Training Purpose Only ~Learjet Static Pressure-Copilot’s Instruments Mach Switch (Ref) (Chapter 34) Isolation Valve (B326) (No.2) Static Pressure-Pilot’s Altimeter Static Pressure-Pilot’s Rat e -o f -C 1 imb Frame 5 (Ref)-- Static Pressure- Pilot’s Airspeed Indicator opilot’sStatic No. 2 Drain Valvefsolation Valve Static No, (B329) iNo. 2) Isolation Valve Pitot-Static Head !B328) (No. 1) Isolation Valve (8327) (No. 1) Static No. 2 IStatic Pressure (To Air Static No. 1 Data Unit, Chapter 22) Drain Valv Pilot’s Pitot-Static Head Static System Plumbing Installation Figure 204 EFFECTrVITY: 35-408, 35-506 AND SUBSEQUENT, 36-054 AND SUBSEQUENT 34-11-00 AND PRIOR AIRCRAFT MODIFIED PER AAK 83-2, Page 211 MM-99 "Installation of FC-530 Autopilot" Feb 19/91 Island Enterprises International AeroTech Academy For Training Purpose Only ~Learjet Connections to Pitot-Static Tester Pitot-Static Test Adapter (P/N 1,50-612) Isolation Valve Installation Pitot/ Pitot i, static 1;1 II lr Il Static 1 Static 2 I L’ II Static 2 Pitot Static System Test Set-Up Figure 205 EFFECTnTITY: 35-408, 35-506 AND SUBSEQUENT, 36-054 AND SUBSEQUENT 34-11-00 AND PRIOR AIRCRAFT MODIFIED PER AAK 83-2, Page 212 MM-99 "Installation of FC-530 Autopilot" Feb 19/91 Island Enterprises International AeroTech Academy For Training Purpose Only LEARJET 35/35A/36/36A MAINTENANCE MANUAL PITOT TUBE MAINTENANCE PRACTICES 1. RemovaVInstallation NOTE: Aircraft 35-002 thru 35-505 excet3t 35-408, 36-002 thru 36-053 not modified per AAK 83-2, "lnstalla- tion of FC-530 Autotlilot," the pitot tubes are located on each side of the nose compartment at F.S. 137.88. Each pitot tube is equipped with two electrical heating elements to prevent mois- ture from freezing on the mast and/or obstructing the tubes. The tube heaters are powered by 28 vdc and controlled by the Pitot Heat Switches. Aircraft 35-408, 35-506 and Subseauent, 36-054 and Subseauent and tlrior aircraft modified tier AAK 83-2, "lnstallation of FC-530 Autoz~ilot," the pitot-static heads are located on each side of the nose compartment between frames 4 and 5. Each pitot-static head is equipped with three electrical heating elements to prevent moisture from freezing on and/or obstructing the pitot-static heads. Tube heaters are powered by 28 vdc and controlled by the Pitot Heat Switches. No pol- ishing, sanding, or abrasive cleaning should be done on the pitot tubes as this destroys the pre- cision contour of the head and rounds the corners of the static ports. A. Removal of Pitot Tube (Aircraft 35-002 thru 35-505 e3ccept 35-408, 36-002 thru 36-053 not modified per AAK 83-2. "lnstallation of FC-530 Auto2lilot (See Figure 201.) NOTE: Removal and installation procedures for either pitot tube is identical. (1) Remove nose compartment access doors. (2) Disconnect pitot line from pitot tube. Cap exposed line. (3) Disconnect electrical wiring from pitot tube. (4) Remove attaching parts and pitot tube from mast. B. Installation of Pitot Tube (Aircraft 35-002 thru 35-505 excettt 35-408, 36-002 thru 36-053 not modified per AAK 83-2, "lnstallation of FC-530 Autopilot (See Figure 201.) CAUTION: WHEN INSTALLING PITOT TUBE INTO MAST ASSEMBLY, DO NOT PUSH PI- TOT TUBE IN TOO FAR AS DAMAGE TO THE HEATING ELEMENT MAY RE- SULT. (1) Install pitot tube in mast. Apply Loctite Screwlock to screws and secure pitot tube to mast. (2) Remove cap from pitot line and connect line to pitot tube. (3) Connect electrical wiring to pitot tube. C. Removal of Pitot-Static Tube (Aircraft 35-408, 35-506 and Subseauent and 36-054 and Subse4uent and Ilrior aircraft modified t~er AAK 83-2, "lnstallation of FC-530 Autollilot.") (See Figure 202.) WARNING: THE FOLLOWING PROCEDURES ARE ONLY APPLICABLE TO REPLACING A PITOT-STATIC TUBE DUE TO HEATER ELEMENT FAILURE. IN CASE OF A DAMAGED PROBE, SUPPORT STRUCTURE ALIGNMENT MAY HAVE BEEN ALTERED. CONTACT LEARJET CUSTOMER SERVICE DE- PARTMENT FOR DISPOSITION OF AIRCRAFT. NOTE: The Rosemont pitot-static tube base mount incorporates an eccentric nut which is safety wired to the base mount. On some aircraft this eccentric nut is not safety wired. The follow- ing procedures provide instructions for safety wiring, if necessary. EFFECTIVITY: NOTED 34-11-01 Page 201 MM-99 Feb 11/00 Island Enterprises International AeroTech Academy For Training Purpose Only