Pilatus PC-12/47E MSN-1001-UP Page 555 Maintenance Manual Download

Page: 555 / 715

Preliminary Requirements

Required Conditions

Table 2 Required Conditions

Action / Condition

Data module/Technical publication

None

Support equipment

Table 3 Support equipment

Name

Identifications/References

Qty

Reference

Remark

Safety clip (Circuit breaker hold
open)

Part T12-030

Sling

Part Local supply

Hoist

Part Local supply

Warning sign (DO NOT MOVE
THE ELEVATOR CONTROLS)

Part Local supply

Trestles

Part Local supply

Supplies

Table 4 Supplies

Name

Identifications/References

Qty

Reference

Remark

Grease

Part P04-004

Cable tie

Part P09-005

White Spirit

Part P01-008

Solvent (alcohol)

Part P01-011

Cloth, cotton

Part P02-019

CPC

Part P10-013

Spares

Table 5 Spares

Name

Identifications/References

Qty

Reference

Remark

Cotter pin

CSN 55-10-00-01-010

Washer

CSN 55-10-00-01-025

Safety Conditions

WARNING

BE CAREFUL WHEN YOU REMOVE OR INSTALL THE STABILIZER. IT IS HEAVY AND CAN CAUSE INJURY
TO PERSONS AND DAMAGE TO EQUIPMENT.

PC-12/47E AMM Doc No 02300, ISSUE 01 REVISION 26 MSN 545, 1001-1719,
1721-1999

12-B-AM-00-00-00-I

UNCLASSIFIED

Effectivity: All

12-B-55-10-01-00A-920A-A

UNCLASSIFIED

2021-12-04 Page 2

Summary of Contents for PC-12/47E MSN-1001-UP

Page 1: ...T LTD CH 6371 STANS SWITZERLAND Model type PC 12 47E MSN 1001 UP 12 B AM 00 00 00 I 12 B AM 00 00 00 I UNCLASSIFIED UNCLASSIFIED 12 B AM 00 00 00 I Effectivity All 02300 Aircraft Maintenance Manual AMM Document Number ...

Page 2: ...Intentionally left blank Effectivity All UNCLASSIFIED 12 B AM 00 00 00 I UNCLASSIFIED 12 B AM 00 00 00 I ...

Page 3: ...21 12 10 ALL PC 12 47E GENERAL AIRCRAFT MAINTENANCE MANUAL CHANGE HIGHLIGHTS REVISION 26 12 B 00 00 00 00A 003A A C 2021 12 10 ALL PC 12 47E AMM LIST OF REVISIONS 12 B 00 00 00 00A 004A A 2018 11 29 ALL PC 12 47E AMM LIST OF TEMPORA RY REVISIONS 12 B 00 00 00 00A 006A A C 2021 12 04 ALL GENERAL LIST OF ABBREVIATIONS 12 B 00 00 00 00A 005A A C 2021 12 04 All GENERAL AMM INTRODUCTION 12 B 00 00 00 0...

Page 4: ...FOR PLANS AND DESCRIPTION 12 B 05 40 00 00A 000B A C 2021 12 04 ALL ENGINE GROUND RUN TESTS FUNCTION DATA FOR PLANS AND DESCRIPTION 12 B 05 40 00 00A 000C A 2018 05 24 ALL 300 FH INSPECTION FUNCTION DATA FOR PLANS AND DESCRIP TION 12 B 05 40 01 01A 000B A C 2021 12 04 ALL 300 FH OR 12 MONTHS INSPECTION FUNCTION DATA FOR PLANS AND DESCRIPTION 12 B 05 40 01 02A 000B A C 2021 12 04 ALL 600 FH INSPECT...

Page 5: ...R EXTEN DED SPEED VLE EXCEEDANCE UNSCHEDULED INSPECTION 12 B 05 50 10 00A 282A A 2020 11 25 ALL TAIL DOWN DAMAGE INSPECTION UNSCHEDULED INSPECTION 12 B 05 50 11 00A 282A A C 2021 12 04 ALL NOSE LANDING GEAR OVERTURN ING UNSCHEDULED INSPECTIONS 12 B 05 50 12 00A 282A A 2021 07 08 ALL AFTER A FLIGHT THROUGH VOL CANIC ASH OR SMOKE UNSCHED ULED INSPECTION 12 B 05 50 15 00A 282A A 2019 11 19 ALL DIMENS...

Page 6: ... DESCRIPTION AND OPERA TION 12 B 11 00 00 00A 040A A 2017 07 19 ALL PLACARDS AND MARKINGS MAIN TENANCE PRACTICES 12 B 11 00 00 00A 901A A 2017 07 19 ALL EXTERIOR PLACARDS AND MARK INGS DESCRIPTION AND OPERA TION 12 B 11 20 00 00A 040A A 2017 07 19 ALL EXTERIOR PLACARDS AND MARK INGS MAINTENANCE PRACTICES 12 B 11 20 00 00A 901A A 2017 07 19 ALL INSTALLATION OF FLAP MARKINGS MAINTENANCE PRACTICES 12...

Page 7: ...8 FIVE BLADED PROPELLER WHEEL BEARING SERVICING 12 B 12 20 06 00A 902A A 2019 11 19 ALL FLAP UP AND DOWN LIMIT SWITCHES SERVICING 12 B 12 20 07 00A 902A A 2017 07 19 ALL EQUIPMENT HANDLING MAINTE NANCE PRACTICES 12 B 20 00 00 00A 901A A 2017 07 19 ALL LOCKING AND RETAINING DEVICES DESCRIPTION AND OPERATION 12 B 20 20 00 00A 040A A 2020 11 25 ALL TORQUE WRENCHES AND PROCE DURES DESCRIPTION AND OPER...

Page 8: ...E MOVAL INSTALLATION 12 B 21 20 01 00A 920A A 2019 11 19 ALL MICROSWITCH REMOVAL INSTAL LATION 12 B 21 20 01 01A 920A A 2019 11 19 ALL BLOWER UNIT REMOVAL INSTAL LATION 12 B 21 20 02 00A 920A A 2017 07 19 ALL PRESSURIZATION CONTROL MSN 1001 1719 DESCRIPTION AND OP ERATION 12 B 21 30 00 00A 040A A 2017 07 19 MSN 1001 1719 PRESSURIZATION CONTROL MSN 545 1720 AND UP DESCRIPTION AND OPERATION 12 B 21 ...

Page 9: ... 903B A 2018 05 24 MSN 1081 AND UP UNDERFLOOR HEATER REMOV AL INSTALLATION 12 B 21 40 01 00A 920A A 2019 11 19 ALL REFRIGERATION PACK INSPEC TION CHECK 12 B 21 40 02 00A 313A A 2017 07 19 ALL REFRIGERATION PACK SERVICING 12 B 21 40 02 00A 902A A 2019 11 19 ALL REFRIGERATION PACK REMOV AL INSTALLATION 12 B 21 40 02 00A 920A A 2019 11 19 ALL WATER SEPARATOR CLEAN 12 B 21 40 03 00A 250A A 2019 11 19 ...

Page 10: ... INSTALLATION 12 B 21 50 01 00A 920A A 2018 11 29 VAPOUR CY CLE COOL ING SYSTEM EVAPORATOR UNIT REFRIGERANT R134A REMOVAL INSTALLATION 12 B 21 50 02 00A 920A A 2018 05 24 REFRIGER ANT R134A COMPRESSOR DRIVE MOTOR IN SPECTION CHECK 12 B 21 50 03 00A 313A A 2018 11 29 VAPOUR CY CLE COOL ING SYSTEM TEMPERATURE CONTROL SYSTEM DESCRIPTION AND OPERATION 12 B 21 60 00 00A 040A A 2017 07 19 ALL INTEGRATED...

Page 11: ...REMOVAL IN STALLATION 12 B 22 10 02 00A 920A A C 2021 12 04 ALL ROLL ACTUATOR REMOVAL IN STALLATION 12 B 22 10 03 00A 920A A C 2021 12 04 ALL YAW ACTUATOR REMOVAL INSTAL LATION 12 B 22 10 04 00A 920A A C 2021 12 04 ALL FLIGHT CONTROL PANEL REMOV AL INSTALLATION 12 B 22 10 05 00A 920A A 2019 11 19 ALL TRIM ADAPTER REMOVAL INSTAL LATION 12 B 22 10 07 00A 920A A 2020 11 25 AIRCRAFT PRE SB 27 024 TRIM...

Page 12: ...2 B 23 11 02 00A 920A A 2017 07 19 HF COMMU NICATIONS SYSTEM COUPLER UNIT SERVICING 12 B 23 11 03 00A 902A A 2017 07 19 HF COUPLER UNIT COUPLER UNIT REMOVAL INSTAL LATION 12 B 23 11 03 00A 920A A 2017 07 19 HF COMMU NICATIONS SYSTEM ANTENNA REMOVAL INSTALLATION 12 B 23 11 04 00A 920A A 2019 11 19 HF COMMU NICATIONS SYSTEM OPTIONAL SHORT ANTENNA RE MOVAL INSTALLATION 12 B 23 11 04 00A 920B A 2019 1...

Page 13: ...ALLATION 12 B 23 16 04 00A 920B A 2020 11 25 WITH RF FIL TER WI FI ROUTER REMOVAL INSTAL LATION 12 B 23 16 05 00A 920A A 2020 11 25 ALL PASSENGER ADVISORY SYSTEM DESCRIPTION AND OPERATION 12 B 23 40 00 00A 040A A 2021 07 08 ALL PASSENGER ENTERTAINMENT DE SCRIPTION AND OPERATION 12 B 23 40 10 00A 040A A 2017 07 19 PASSENGER ENTERTAIN MENT SYS TEM AUDIO INTEGRATING SYSTEM KMA 29 DESCRIPTION AND OPER...

Page 14: ...01 00A 920A A 2019 11 19 ALL VOLTAGE REGULATOR 1 REMOV AL INSTALLATION 12 B 24 30 05 00A 920A A 2019 11 19 ALL VOLTAGE REGULATOR 2 REMOV AL INSTALLATION 12 B 24 30 06 00A 920A A 2019 11 19 ALL BATTERY AND OVERTEMPERATURE SYSTEM ADJUSTMENT TEST 12 B 24 30 07 00A 903A A 2020 11 25 ALL LEAD ACID BATTERY REMOVAL IN STALLATION 12 B 24 30 07 00A 920A A 2019 11 19 LEAD ACID BATTERY NI CAD BATTERY REMOVAL...

Page 15: ...R RIGHT POWER JUNCTION BOX RE MOVAL INSTALLATION 12 B 24 52 20 00A 920A A 2019 11 19 ALL EMERGENCY POWER SUPPLY EPS SYSTEM MSN 1001 1719 DE SCRIPTION AND OPERATION 12 B 24 52 51 00A 040A A 2018 02 13 MSN 1001 1719 EMERGENCY POWER SUPPLY EPS SYSTEM MSN 545 1720 AND UP DESCRIPTION AND OPERATION 12 B 24 52 51 00A 040B A 2018 02 13 MSN 545 1720 and Up EMERGENCY POWER SUPPLY EPS SYSTEM ADJUSTMENT TEST ...

Page 16: ...A A 2017 07 19 EXECUTIVE INTERIOR EXECUTIVE SEAT SAFETY HARNESS REMOVAL INSTALLATION 12 B 25 21 02 00A 920A A 2021 07 08 EXECUTIVE INTERIOR EXECUTIVE TRIM REMOVAL IN STALLATION 12 B 25 21 03 00A 920A A 2019 11 19 EXECUTIVE INTERIOR EXECUTIVE CARPETS REMOV AL INSTALLATION 12 B 25 21 04 00A 920A A 2019 11 19 EXECUTIVE INTERIOR LEFT STORAGE CABINET REMOV AL INSTALLATION 12 B 25 21 05 00A 920A A 2017 ...

Page 17: ...05 03 ALL KANNAD INTEGRA ELT ADJUST MENT TEST 12 B 25 63 00 00A 903B A 2021 07 08 KANNAD IN TEGRA ELT EMERGENCY LOCATOR TRANSMIT TER REMOVAL INSTALLATION 12 B 25 63 00 00A 920A A 2017 07 19 ALL KANNAD INTEGRA ELT REMOV AL INSTALLATION 12 B 25 63 00 00A 920B A 2019 11 19 KANNAD IN TEGRA ELT EMERGENCY LOCATOR TRANSMIT TER ANTENNA REMOVAL INSTAL LATION 12 B 25 63 02 00A 920A A 2019 11 19 ALL ELT NAVI...

Page 18: ... B 26 00 00 00A 040A A 2017 07 19 ALL FIRE OVERHEAT DETECTION DE SCRIPTION AND OPERATION 12 B 26 10 00 00A 040A A 2019 11 19 ALL FIRE OVERHEAT DETECTION AD JUSTMENT TEST 12 B 26 10 00 00A 903A A 2019 05 03 ALL FIREWIRE REMOVAL INSTALLATION 12 B 26 10 01 00A 920A A 2019 11 19 All EXTINGUISHING DESCRIPTION AND OPERATION 12 B 26 20 00 00A 040A A 2017 07 19 ALL FLIGHT CONTROLS DESCRIPTION AND OPERATIO...

Page 19: ...ALL AILERON CONTROL ROD CENTER WING REMOVAL INSTALLATION 12 B 27 10 06 00A 920A A 2019 11 19 ALL AILERON CONTROL ROD OUTER WING REMOVAL INSTALLATION 12 B 27 10 07 00A 920A A 2019 11 19 ALL AILERON CONTROL SYSTEM FUSE LAGE BELLCRANK MAGNETIC PAR TICLE INSPECTION 12 B 27 10 08 00A 352B A 2019 11 19 ALL AILERON CONTROL SYSTEM OUT ER WING BELLCRANK EDDY CUR RENT INSPECTION 12 B 27 10 08 00A 353A A 201...

Page 20: ... 00A 920A A 2021 07 08 ALL RUDDER CONTROL SYSTEM CA BLE QUADRANT EXAMINE 12 B 27 20 05 00A 310A A 2019 11 19 ALL RUDDER TRIM DESCRIPTION AND OPERATION 12 B 27 25 00 00A 040A A 2019 11 19 ALL RUDDER TRIM ADJUSTMENT TEST 12 B 27 25 00 00A 903A A 2017 07 19 ALL RUDDER TRIM ACTUATOR REMOV AL INSTALLATION 12 B 27 25 01 00A 920A A 2017 07 19 ALL ELEVATOR CONTROL SYSTEM DE SCRIPTION AND OPERATION 12 B 27...

Page 21: ... 11 19 ALL POWER DRIVE UNIT REMOVAL IN STALLATION 12 B 27 50 01 00A 920A A 2019 11 19 ALL FLAP DRIVE SHAFTS REMOVAL IN STALLATION 12 B 27 50 02 00A 920A A 2019 11 19 ALL FLAP ACTUATOR INSPEC TION CHECK 12 B 27 50 03 00A 313A A 2021 07 08 ALL FLAP ACTUATOR ADJUST MENT TEST 12 B 27 50 03 00A 903A A 2019 11 19 ALL FLAP ACTUATOR REMOVAL INSTAL LATION 12 B 27 50 03 00A 920A A 2017 07 19 ALL FLAP CONTRO...

Page 22: ...NISM REMOVAL IN STALLATION 12 B 27 51 02 00A 920A A 2017 07 19 ALL FLAP DRIVE SYSTEM WING OUT BOARD MECHANISM PARTS LIST KIT P N 500 60 12 025 12 B 27 51 03 00A 307A A 2017 07 19 ALL FLAP DRIVE SYSTEM WING OUT BOARD MECHANISM EDDY CUR RENT INSPECTION 12 B 27 51 03 00A 353A A 2019 05 03 ALL FLAP DRIVE SYSTEM WING OUT BOARD MECHANISM REMOVAL IN STALLATION 12 B 27 51 03 00A 920A A 2017 07 19 ALL GUST...

Page 23: ...ION 12 B 28 20 06 00A 920A A 2017 07 19 ALL FLOAT VALVE ADJUSTMENT TEST 12 B 28 20 07 00A 903A A 2018 02 13 ALL FLOAT VALVE REMOVAL INSTALLA TION 12 B 28 20 07 00A 920A A 2017 07 19 ALL FIREWALL SHUTOFF VALVE RE MOVAL INSTALLATION 12 B 28 20 08 00A 920A A 2017 07 19 ALL FUEL FILTER ASSEMBLY AND MAIN TENANCE SHUT OFF VALVE RE MOVAL INSTALLATION 12 B 28 20 12 00A 920A A 2021 07 08 ALL BALANCING SYST...

Page 24: ...INTENANCE PRACTICES 12 B 29 10 02 00A 901A A 2017 07 19 HYDRAULIC SYSTEM ACCUMULATOR REMOVAL INSTAL LATION 12 B 29 10 02 00A 920A A 2017 07 19 HYDRAULIC SYSTEM LOW PRESSURE SWITCH REMOV AL INSTALLATION 12 B 29 10 03 00A 920A A 2017 07 19 HYDRAULIC SYSTEM RETURN LINE FILTER DIFFERENTIAL PRESSURE INDICATOR INSPEC TION CHECK 12 B 29 10 04 00A 313A A 2017 07 19 HYDRAULIC SYSTEM RETURN LINE FILTER REMO...

Page 25: ...A 2017 07 19 ALL EJECTOR FLOW CONTROL VALVE REMOVAL INSTALLATION 12 B 30 10 02 00A 920A A 2019 11 19 ALL AIRFOIL DE ICE SYSTEM TIMER REMOVAL INSTALLATION 12 B 30 10 03 00A 920A A 2019 11 19 ALL AIRFOIL DE ICE SYSTEM PRES SURE SWITCH REMOVAL INSTAL LATION 12 B 30 10 04 00A 920A A 2020 11 25 ALL WING DE ICE BOOTS REMOVAL IN STALLATION 12 B 30 14 01 00A 920A A 2020 11 25 ALL HORIZONTAL STABILIZER DE ...

Page 26: ...019 11 19 FIVE BLADED PROPELLER FIVE BLADED PROPELLER DE ICE SYSTEM FAULT ISOLATION PROCE DURE 12 B 30 60 00 00A 420B A 2017 07 19 ALL FOUR BLADED PROPELLER DE ICE SYSTEM WITHOUT PROPELLER DE ICE TEST SET ADJUSTMENT TEST 12 B 30 60 00 00A 903A A 2018 11 29 WITHOUT PROPELLER DE ICE TEST SET FIVE BLADED PROPELLER DE ICE SYSTEM WITHOUT PROPELLER DE ICE TEST SET ADJUSTMENT TEST 12 B 30 60 00 00A 903B ...

Page 27: ...M877 REMOVAL IN STALLATION 12 B 31 20 12 00A 920B A 2019 11 19 DAVTRON M877 TIME COUNTERS DESCRIPTION AND OPERATION 12 B 31 20 20 00A 040A A 2017 07 19 ALL FLIGHT TIME COUNTER DESCRIP TION AND OPERATION 12 B 31 20 21 00A 040A A 2019 11 19 ALL FLIGHT TIME COUNTER REMOV AL INSTALLATION 12 B 31 20 21 00A 920A A 2019 11 19 ALL RECORDERS LDR DESCRIPTION AND OPERATION 12 B 31 30 01 00A 040A A C 2021 12 ...

Page 28: ...9 ALL LIGHTED PUSHBUTTON FILAMENT REMOVAL INSTALLATION 12 B 31 50 01 00A 920A A 2017 07 19 ALL AURAL WARNING SYSTEM DE SCRIPTION AND OPERATION 12 B 31 51 00 00A 040A A 2021 07 08 ALL CREW ALERTING SYSTEM DE SCRIPTION AND OPERATION 12 B 31 52 00 00A 040A A 2021 07 08 ALL FLIGHT ALERTING SYSTEM DE SCRIPTION AND OPERATION 12 B 31 53 00 00A 040A A 2017 07 19 ALL VIDEO INTERFACE DESCRIPTION AND OPERATI...

Page 29: ...2 10 00 00A 902A A 2021 07 08 ALL MAIN LANDING GEAR AND DOORS HYDRAULIC LANDING GEAR AD JUSTMENT TEST 12 B 32 10 00 00A 903A A 2017 07 19 HYDRAULIC LANDING GEAR MAIN LANDING GEAR AND DOORS ELECTRO MECHANICAL LANDING GEAR ADJUSTMENT TEST 12 B 32 10 00 00A 903B A C 2021 12 04 ALL MAIN GEAR AND DOORS REPAIR TO REMOVE THE MLG BAY SEAL 12 B 32 10 00 00A 904B A 2017 07 19 ALL MAIN LANDING GEAR LEG HY DR...

Page 30: ...HYDRAULIC LANDING GEAR NOSE LANDING GEAR AND DOORS ELECTRO MECHANICAL LANDING GEAR DESCRIPTION AND OPERA TION 12 B 32 20 00 00A 040B A 2021 07 08 ELECTRO MECHANICAL LANDING GEAR NLG AND DRAG LINK ATTACHMENT BEARINGS INSPECTION CHECK 12 B 32 20 00 00A 313A A 2019 11 19 ALL NOSE LANDING GEAR SHOCK AB SORBER SERVICING 12 B 32 20 00 00A 902A A 2021 07 08 ALL NOSE LANDING GEAR AND DOORS HYDRAULIC LANDI...

Page 31: ...ION CHECK 12 B 32 20 06 00A 313A A 2019 11 19 ALL DRAG LINK RIGHT PART HYDRAUL IC LANDING GEAR REMOVAL IN STALLATION 12 B 32 20 06 00A 920A A 2017 07 19 HYDRAULIC LANDING GEAR DRAG LINK RIGHT PART ELECTRO MECHANICAL LANDING GEAR RE MOVAL INSTALLATION 12 B 32 20 06 00A 920B A 2019 11 19 ELECTRO MECHANICAL LANDING GEAR EXTENSION AND RETRACTION HY DRAULIC LANDING GEAR DESCRIP TION AND OPERATION 12 B ...

Page 32: ...SELECTOR VALVE HYDRAULIC LANDING GEAR REMOVAL INSTAL LATION 12 B 32 30 03 00A 920A A 2017 07 19 HYDRAULIC LANDING GEAR LANDING GEAR SELECTOR HY DRAULIC LANDING GEAR REMOV AL INSTALLATION 12 B 32 30 04 00A 920A A 2017 07 19 HYDRAULIC LANDING GEAR LANDING GEAR SELECTOR ELEC TRO MECHANICAL LANDING GEAR REMOVAL INSTALLATION 12 B 32 30 04 00A 920B A 2019 11 19 ELECTRO MECHANICAL LANDING GEAR LANDING GE...

Page 33: ...INSTALLATION 12 B 32 30 10 03A 920A A 2019 11 19 ELECTRO MECHANICAL LANDING GEAR EMERGENCY GEAR EXTENSION SYSTEM ELECTRO MECHANICAL LANDING GEAR MLG CABLE AS SEMBLY REMOVAL INSTALLATION 12 B 32 30 10 04A 920A A 2017 07 19 ELECTRO MECHANICAL LANDING GEAR WHEELS AND BRAKES DESCRIP TION AND OPERATION 12 B 32 40 00 00A 040A A 2017 07 19 ALL WHEELS AND BRAKES SERVICING 12 B 32 40 00 00A 902A A 2019 11 ...

Page 34: ...OSITION AND WARNING ELECTRO MECHANICAL LANDING GEAR DE SCRIPTION AND OPERATION 12 B 32 60 00 00A 040B A 2019 11 19 ELECTRO MECHANICAL LANDING GEAR POSITION AND WARNING ELECTRO MECHANICAL LANDING GEAR AD JUSTMENT TEST 12 B 32 60 00 00A 903B A 2021 07 08 ELECTRO MECHANICAL LANDING GEAR POSITION AND WARNING MLG MI CROSWITCH REMOVAL INSTALLA TION 12 B 32 60 01 00A 920B A 2019 11 19 ELECTRO MECHANICAL ...

Page 35: ...A 920A A 2019 11 19 EXECUTIVE INTERIOR READING LIGHTS STANDARD INTE RIOR REMOVAL INSTALLATION 12 B 33 20 07 00A 920B A 2019 11 19 STANDARD INTERIOR CARGO AND SERVICE COMPART MENT LIGHTS DESCRIPTION AND OPERATION 12 B 33 30 00 00A 040A A 2017 07 19 ALL EXTERNAL LIGHTS DESCRIPTION AND OPERATION 12 B 33 40 00 00A 040A A 2017 07 19 ALL EXTERNAL LIGHTS ADJUST MENT TEST 12 B 33 40 00 00A 903A A 2019 11 ...

Page 36: ...TS RE MOVAL INSTALLATION 12 B 33 43 01 00A 920B A 2019 11 19 COMBINED LED NAVIGA TION ANTI COLLISION POSITION LIGHTS STROBE LIGHTS REMOVAL INSTAL LATION 12 B 33 43 02 00A 920A A 2017 07 19 MSN 1001 1450 STROBE LIGHT POWER SUPPLY REMOVAL INSTALLATION 12 B 33 43 03 00A 920A A 2017 07 19 MSN 1001 1450 LED ANTI COLLISION LIGHT POWER SUPPLY REMOVAL INSTALLATION 12 B 33 43 03 00A 920B A 2019 11 19 COMBI...

Page 37: ...LASHING BEACONS REMOV AL INSTALLATION 12 B 33 46 00 00A 920A A C 2021 12 04 ALL LED RED FLASHING BEACONS RE MOVAL INSTALLATION 12 B 33 46 00 00A 920B A 2019 11 19 All NAVIGATION GENERAL WARNINGS AND CAUTIONS AND RELATED SAFETY DATA 12 B 34 00 00 00A 012A A 2017 07 19 ALL NAVIGATION DESCRIPTION AND OPERATION 12 B 34 00 00 00A 040A A 2019 11 19 ALL FLIGHT ENVIRONMENT DATA DE SCRIPTION AND OPERATION ...

Page 38: ...IC COMPASS REMOVAL INSTALLATION 12 B 34 21 00 00A 920A A 2018 11 29 STANDBY MAGNETIC COMPASS AIR DATA ATTITUDE AND HEADING REFERENCE SYSTEM KSG 7200 DESCRIPTION AND OPERATION 12 B 34 25 00 00A 040A A 2017 07 19 ALL AIR DATA ATTITUDE AND HEADING REFERENCE SYSTEM KSG 7200 ADJUSTMENT TEST 12 B 34 25 00 00A 903A A C 2021 12 04 ALL AIR DATA ATTITUDE AND HEADING REFERENCE UNIT REMOVAL IN STALLATION 12 B...

Page 39: ...9 1721 1999 OR POST SB 34 042 ADJUSTMENT TEST 12 B 34 26 40 00A 903B A 2019 11 19 MSN 1271 1719 ELECTRONIC STANDBY INSTRU MENT REMOVAL INSTALLATION 12 B 34 26 40 00A 920A A 2017 07 19 MSN 1001 1270 PRE SB 34 042 ELECTRONIC STANDBY INSTRU MENT MSN 1271 1719 1721 1999 OR POST SB 34 042 REMOVAL IN STALLATION 12 B 34 26 40 00A 920B A 2019 11 19 L3 ESIS ELECTRONIC STANDBY INSTRU MENT SYSTEM MSN 1271 17...

Page 40: ... XM SATELLITE WEATHER ANTENNA REMOVAL INSTALLATION 12 B 34 41 12 00A 920A A 2019 11 19 XM SATEL LITE WEATH ER SYSTEM STORMSCOPE SYSTEM DESCRIP TION AND OPERATION 12 B 34 41 30 00A 040A A 2021 07 08 WX 500 STORM SCOPE STORMSCOPE SYSTEM ADJUST MENT TEST 12 B 34 41 30 00A 903A A 2017 07 19 WX500 STORM SCOPE STORMSCOPE PROCESSOR RE MOVAL INSTALLATION 12 B 34 41 31 00A 920A A 2017 07 19 WX500 STORM SCO...

Page 41: ...TEM MULTI HAZARD AWARENESS SYS TEM COMPUTER REMOVAL INSTAL LATION 12 B 34 45 10 01A 920A A 2017 07 19 MULTI HAZ ARD AWARE NESS SYS TEM MULTI HAZARD AWARENESS SYS TEM CONFIGURATION MODULE RE MOVAL INSTALLATION 12 B 34 45 10 02A 920A A 2017 07 19 MULTI HAZ ARD AWARE NESS SYS TEM DEPENDENT POSITION DETERMIN ING DESCRIPTION AND OPERA TION 12 B 34 50 00 00A 040A A 2017 07 19 ALL VHF NAVIGATION SYSTEM D...

Page 42: ... B OUT DUAL NON DIVERSITY ATC TRANS PONDER SYSTEM WITH ADS B OUT DESCRIPTION AND OPERATION 12 B 34 54 00 00A 040D A 2017 07 19 DUAL NON DIVERSITY ATC TRANS PONDER SYSTEM WITH ADS B OUT DUAL DIVERSITY ATC TRANSPOND ER SYSTEM ADJUSTMENT TEST 12 B 34 54 00 00A 903A A 2021 07 08 DUAL DIVER SITY ATC TRANSPOND ERS DUAL NON DIVERSITY ATC TRANS PONDER SYSTEM ADJUST MENT TEST 12 B 34 54 00 00A 903B A 2017 ...

Page 43: ... NON DIVERSITY AIR TRAF FIC CONTROL TRANSPONDER SYS TEM ADJUSTMENT TEST 12 B 34 54 10 00A 903B A 2017 07 19 SINGLE NON DIVERSITY ATC TRANS PONDER GLOBAL POSITIONING SYSTEM DE SCRIPTION AND OPERATION 12 B 34 57 00 00A 040A A 2017 07 19 KGS 200 GPS GLOBAL POSITIONING SYSTEM AD JUSTMENT TEST 12 B 34 57 00 00A 903A A 2017 07 19 ALL GLOBAL NAVIGATION SYSTEM SEN SOR UNIT REMOVAL INSTALLATION 12 B 34 57 ...

Page 44: ...5 PLUG IN MASK SYS TEM MSN 1001 1719 PASSENGER OXYGEN DROP DOWN MASK SYSTEM MSN 1001 1719 DESCRIPTION AND OPERATION 12 B 35 20 00 00A 040B A 2017 07 19 DROP DOWN MASK SYS TEM MSN 1001 1719 PASSENGER OXYGEN PLUG IN MASK SYSTEM MSN 545 1720 AND UP DESCRIPTION AND OPERATION 12 B 35 20 00 00A 040C A 2019 11 19 MSN 545 1720 AND UP PASSENGER OXYGEN DROP DOWN MASKS SYSTEM MSN 545 1720 AND UP DESCRIPTION ...

Page 45: ...9 11 19 ALL CENTRAL MAINTENANCE SYSTEM INTERFACE CHANGE THE SET TINGS FILE 12 B 45 45 00 00A 553A A 2021 07 08 ALL SYSTEMS INTEGRATION AND DIS PLAY DESCRIPTION AND OPERA TION 12 B 46 00 00 00A 040A A 2017 07 19 ALL WIRELESS DATA LOADING SYSTEM CONNECTED FLIGHT DECK DE SCRIPTION AND OPERATION 12 B 46 21 00 00A 040A A 2017 07 19 POST SB 46 004 OR CONNECTED FLIGHT DECK OPTION WIRELESS DATA LOADING SY...

Page 46: ...ATION 12 B 46 30 03 00A 040A A 2017 07 19 ALL MULTI FUNCTION DISPLAY REMOV AL INSTALLATION 12 B 46 30 03 00A 920A A 2017 07 19 ALL MULTI FUNCTION CONTROLLER DESCRIPTION AND OPERATION 12 B 46 30 04 00A 040A A 2017 07 19 ALL MULTI FUNCTION CONTROLLER LOAD DATA 12 B 46 30 04 00A 550A A 2017 07 19 POST SB 45 001 AND 46 001 MULTI FUNCTION CONTROLLER FAULT MONITORING STORAGE READOUT DOWNLOAD DATA 12 B 4...

Page 47: ...18 02 13 CURSOR CONTROL DEVICE CURSOR CONTROL DEVICE PUSH BUTTON REMOVAL INSTALLATION 12 B 46 30 07 03A 920A A 2018 02 13 CURSOR CONTROL DEVICE CURSOR CONTROL DEVICE WIRING HARNESS REMOVAL INSTALLATION 12 B 46 30 07 04A 920A A 2017 07 19 CURSOR CONTROL DEVICE CURSOR CONTROL UNIT REMOV AL INSTALLATION 12 B 46 30 08 00A 920A A 2019 05 03 CURSOR CONTROL DEVICE DOORS GENERAL DESCRIPTION AND OPERATION ...

Page 48: ...N 12 B 52 10 07 00A 920A A N 2021 12 04 ALL PASSENGER DOOR STRIKER PLATES MSN 1576 1942 REMOV AL INSTALLATION 12 B 52 10 07 00A 920B A N 2021 12 04 ALL EMERGENCY EXIT DOOR DESCRIP TION AND OPERATION 12 B 52 20 00 00A 040A A 2019 05 03 ALL EMERGENCY EXIT EXAMINE 12 B 52 20 00 00A 310A A 2019 11 19 ALL EMERGENCY EXIT REMOVAL IN STALLATION 12 B 52 20 00 00A 920A A 2017 07 19 ALL EMERGENCY EXIT DOOR S...

Page 49: ... 70 01 00A 920A A 2019 11 19 ALL PASSENGER CREW DOOR HANDLE SWITCH REMOVAL INSTALLATION 12 B 52 70 02 00A 920A A 2019 11 19 ALL CARGO DOOR BOLTS SWITCH RE MOVAL INSTALLATION 12 B 52 70 03 00A 920A A 2019 11 19 ALL CARGO DOOR HANDLE SWITCH REMOVAL INSTALLATION 12 B 52 70 04 00A 920A A 2017 07 19 ALL FUSELAGE DESCRIPTION AND OP ERATION 12 B 53 00 00 00A 040A A 2017 07 19 ALL FUSELAGE ANTENNA STRUCTU...

Page 50: ... 11 29 All VERTICAL STABILIZER ATTACHMENT FITTINGS EDDY CURRENT INSPEC TION 12 B 55 00 00 00A 353A A 2019 11 19 ALL HORIZONTAL STABILIZER REMOV AL INSTALLATION 12 B 55 10 01 00A 920A A C 2021 12 04 ALL ELEVATORS EXAMINE 12 B 55 20 00 00A 310A A 2019 11 19 ALL ELEVATOR DRIVE LEVER AND HINGE EDDY CURRENT INSPECTION 12 B 55 20 01 00A 353A A 2019 11 19 ALL ELEVATOR LEVER FITTING REPAIR 12 B 55 20 01 0...

Page 51: ...LA TION 12 B 56 11 01 00A 920A A C 2021 12 04 ALL COCKPIT SIDE WINDOWS EXAMINE 12 B 56 11 02 00A 310A A 2019 11 19 ALL COCKPIT SIDE WINDOWS INSPEC TION CHECK 12 B 56 11 02 00A 313A A 2020 05 15 ALL INNER SIDE WINDOWS REMOV AL INSTALLATION 12 B 56 11 02 00A 920A A 2019 11 19 ALL DIRECT VISION WINDOW REMOV AL INSTALLATION 12 B 56 14 01 00A 920A A 2019 11 19 ALL DIRECT VISION WINDOW ADJUST MENT TEST ...

Page 52: ...SPEC TION 12 B 57 00 03 00A 353A A 2018 11 29 ALL WING AND FUSELAGE ATTACHMENT FITTINGS HOLLOW BOLTS EDDY CURRENT INSPECTION 12 B 57 00 03 01A 353A A 2019 11 19 ALL WING SKINS EDDY CURRENT IN SPECTION 12 B 57 20 01 00A 353A A 2019 11 19 ALL TRAILING EDGE SEAL PLATE RE MOVAL INSTALLATION 12 B 57 20 01 00A 920A A 2017 07 19 MSN 1576 AND UP WING SKIN REFUEL PROTECTION FOIL REMOVAL INSTALLATION 12 B 5...

Page 53: ...P SUPPORT ARM REMOVAL IN STALLATION 12 B 57 50 02 01A 920A A 2019 11 19 ALL AILERONS EXAMINE 12 B 57 60 00 00A 310A A 2019 11 19 ALL AILERON REMOVAL INSTALLATION 12 B 57 60 02 00A 920A A 2021 07 08 ALL AILERON TRIM LH PARTS LIST KIT P N 500 60 12 039 12 B 57 60 04 00A 307A A 2017 07 19 ALL AILERON TRIM RH PARTS LIST KIT P N 500 60 12 040 12 B 57 60 04 00A 307B A 2017 07 19 ALL AILERON TRIM TAB EXA...

Page 54: ...ALL LOW PITCH WARNING SWITCH RE MOVAL INSTALLATION 12 B 61 20 02 00A 920A A 2017 07 19 ALL OVERSPEED GOVERNOR REMOV AL INSTALLATION 12 B 61 20 03 00A 920A A 2017 07 19 ALL POWERPLANT DESCRIPTION AND OPERATION 12 B 71 00 00 00A 040A A 2017 07 19 ALL POWERPLANT CLEAN 12 B 71 00 00 00A 250A A C 2021 12 04 ALL POWERPLANT MAINTENANCE PRACTICES 12 B 71 00 00 00A 901A A 2018 02 13 ALL POWER PLANT ADJUSTM...

Page 55: ...R PLANT TEST 17 REVERSE POWER ADJUSTMENT TEST 12 B 71 00 00 00A 903R A 2018 05 24 ALL POWER PLANT TEST 18 ENVIRON MENTAL CONTROL SYSTEM AD JUSTMENT TEST 12 B 71 00 00 00A 903S A 2018 05 24 ALL POWER PLANT TEST 19 ENGINE STOP TIME ADJUSTMENT TEST 12 B 71 00 00 00A 903T A 2017 07 19 ALL POWERPLANT TEST 20 AFTER EN GINE STOP ADJUSTMENT TEST 12 B 71 00 00 00A 903U A C 2021 12 04 ALL POWER PLANT REMOVA...

Page 56: ...920A A 2019 11 19 ALL SPARK IGNITORS REMOVAL IN STALLATION 12 B 74 20 00 00A 920A A 2018 11 29 ALL ENGINE CONTROLS DESCRIPTION AND OPERATION 12 B 76 00 00 00A 040A A 2017 07 19 ALL POWER CONTROLS ADJUST MENT TEST 12 B 76 10 00 00A 903A A 2018 05 24 ALL POWER CONTROLS MICROSWITCH ES ADJUSTMENT TEST 12 B 76 10 01 00A 903A A 2017 07 19 ALL PROPELLER FEATHER MICRO SWITCHES ADJUSTMENT TEST 12 B 76 10 0...

Page 57: ...IP DETECTOR ADJUST MENT TEST 12 B 79 30 01 00A 903A A 2017 07 19 ALL CHIP DETECTOR REMOVAL INSTAL LATION 12 B 79 30 01 00A 920A A 2017 07 19 ALL OIL PRESSURE TRANSDUCER AD JUSTMENT TEST 12 B 79 30 02 00A 903A A 2017 07 19 ALL OIL PRESSURE TRANSDUCER RE MOVAL INSTALLATION 12 B 79 30 02 00A 920A A 2017 07 19 ALL TEMPERATURE SENSOR REMOV AL INSTALLATION 12 B 79 30 03 00A 920A A 2017 07 19 ALL PRESSUR...

Page 58: ... 12 47E AMM Doc No 02300 ISSUE 01 REVISION 26 MSN 545 1001 1719 1721 1999 12 B AM 00 00 00 I UNCLASSIFIED Intentionally left blank Effectivity All 12 B 00 00 00 00A 002A A UNCLASSIFIED 2021 12 10 Page 56 ...

Page 59: ...al changes note numbering changed 23433 20 1 Authority approval statement added 12 B 05 10 10 00A 281A A Replaced 23238 3 7 Editorial updates to various tasks 12 B 05 10 20 00A 281A A Replaced 23238 3 7 Editorial updates to various tasks 12 B 05 10 30 00A 280A A Replaced 23308 1 1 Formatting changes 12 B 05 20 00 00A 913A A Replaced 23308 1 1 Formatting changes 12 B 05 40 00 00A 000B A Replaced 23...

Page 60: ...n added 12 B 22 10 04 00A 920A A Replaced 22988 1 3 Lockwiring illustration added 12 B 22 20 00 00A 040A A Replaced 23146 5 1 Stick pusher interrupt switch explanation updated and editorial updates 12 B 24 52 20 00A 903A A Replaced 22975 1 1 Updated the pins for linking relays K162A1 and K162K4 12 B 28 00 00 00A 901A A Replaced 23126 3 1 CML ref for petroleum jelly P04 030 added 12 B 28 10 02 00A ...

Page 61: ... module 12 B 52 10 07 00A 920B A Inserted Incorporation of new data module 12 B 55 10 01 00A 920A A Replaced 23013 5 1 Alternative washer added to the spares list 12 B 56 11 01 00A 920A A Replaced 23021 2 2 Wire idents updated 12 B 57 00 00 00A 720A A Replaced 23241 2 1 Step added to check loop clamps Editorial up dates 12 B 57 00 00 00A 720B A Replaced 23241 2 2 Step added to check loop clamps Ed...

Page 62: ...C 12 47E AMM Doc No 02300 ISSUE 01 REVISION 26 MSN 545 1001 1719 1721 1999 12 B AM 00 00 00 I UNCLASSIFIED Intentionally left blank Effectivity All 12 B 00 00 00 00A 003A A UNCLASSIFIED 2021 12 10 Page 4 ...

Page 63: ...01 May 05 09 May 14 09 Pilatus 2 Pilatus 25 01 Jun 30 09 Jul 02 09 Pilatus 3 Pilatus 00 04 Nov 10 09 Nov 10 09 Pilatus 4 Pilatus 05 02 Nov 11 09 Nov 11 09 Pilatus 4 Pilatus 34 08 Jun 23 10 Jun 23 10 Pilatus 5 Pilatus 22 01 Jul 07 10 Jul 07 10 Pilatus 5 Pilatus 56 01 Jul 05 10 Jul 05 10 Pilatus 5 Pilatus 27 02 Oct 05 10 Oct 05 10 Pilatus 5 Pilatus 28 01 Feb 10 12 Feb 10 12 Pilatus 9 Pilatus 22 02 M...

Page 64: ...7 Feb 10 17 Pilatus 17 Pilatus 00 09 Aug 18 17 Aug 18 17 Pilatus 18 Pilatus 32 03 Sep 11 17 Sep 11 17 Pilatus 18 Pilatus 05 04 Sep 28 17 Sep 28 17 Pilatus 18 Pilatus 27 03 Oct 20 17 Oct 20 17 Pilatus 18 Pilatus 05 05 Sep 17 18 Sep 17 18 Pilatus 20 Pilatus 55 01 Sep 08 18 Sep 08 18 Pilatus 20 Pilatus 32 04 Dec 13 18 Dec 13 18 Pilatus 21 Pilatus 32 05 Nov 08 19 Nov 08 19 Pilatus 22 Pilatus 22 03 Feb...

Page 65: ...Inserted Signature Date or Revision Removed Signature PC 12 47E AMM Doc No 02300 ISSUE 01 REVISION 26 MSN 545 1001 1719 1721 1999 12 B AM 00 00 00 I UNCLASSIFIED Effectivity All 12 B 00 00 00 00A 006A A UNCLASSIFIED 2021 12 04 Page 3 ...

Page 66: ...ignature Date or Revision Removed Signature PC 12 47E AMM Doc No 02300 ISSUE 01 REVISION 26 MSN 545 1001 1719 1721 1999 12 B AM 00 00 00 I UNCLASSIFIED Effectivity All 12 B 00 00 00 00A 006A A End of data module UNCLASSIFIED 2021 12 04 Page 4 ...

Page 67: ...ircraft Condition and Monitoring System ACP Audio Control Panel ACS Air Cycle System ADAHRS Air Data Attitude Heading Reference System ADC Air Data Computer ADF Automatic Direction Finder ADS B Automatic Dependent Surveillance Broadcast AECMA Association Européenne des Constructeurs de Matériel Aérospatial AFM Airplane Flight Manual AGB Accessory Gearbox AGE Aerospace Ground Equipment AGL Above Gr...

Page 68: ...uilt in Test BUS Busbar CAS Crew Alerting System CAT Computer Aided Testing CANbus Communication with ground support equipment CB Circuit Breaker CLDU Cockpit Lighting Dim Unit CMC Central Maintenance Computer CMCF Central Maintenance Computer Function CMM Component Maintenance Manual CMS Configuration Management System COMM Communication COMP Composite Comp Computer CPCS Cabin Pressurization Cont...

Page 69: ...ator Transmitter EMI Electromagnetic Interference EMM Engine Maintenance Manual EPM External Power Management EPMP Electrical Power Management Panel EPS Emergency Power Supply EPSU Emergency Power Supply Unit EPU External Power Unit EPU Estimated Position Uncertainty ESCM External Satcom Configuration Module ESD Electrostatic Discharge ESDS Electrostatic Discharge Sensitive ESIS Electronic Standby...

Page 70: ...ICN Illustration Control Number ICS Intercom System IETP Interactive Electronic Technical Publications ILS Instrument Landing System in Inch IOAT Indicated Outside Air Temperature I O Input Output IPD Illustrated Parts Data ITT Inter Turbine Temperature KCAS Knots Calculated Air Speed KIAS Knots Indicated Air Speed KTS Knots LAN Local Area Network lb Pound weight lbf in Pounds force inches torque ...

Page 71: ...Mmo Maximum Operating Speed Mach MON Monitoring MOR Manual Override MS Military Standard MSN Manufacturer s Serial Number MTOW Maximum Takeoff Weight MWS Monitor Warning System N Newton N A Not Applicable NDT Non Destructive Testing Nf Free Turbine Speed Ng Gas Generator Speed NIC Network Interface Controller Ni Cad Nickel Cadmium NLG Nose Landing Gear Nm Newton Meters NM Nautical Miles No Number ...

Page 72: ...nd Whitney Canada PWR Power QTY Quantity RAD ALT Radio Altimeter RAIM Receiver Autonomous Integrity Monitoring RAM Random Access Memory RCCB Remote Control Circuit Breaker Ref Refer or Reference RF Radio Frequency REL Relative RGB Reduction Gearbox RH Right RNG Range ROM Read Only Memory RPM Revolutions Per Minute RT Remote Terminal RVSM Reduced Vertical Separation Minima SATCOM Satellite Communic...

Page 73: ...ordinated Universal Time ULB Underwater Locator Beacon V Volt VERT Vertical Vfe Maximum Flaps extended Speed knots VFR Visual Flight Rules VHF Very High Frequency Vle Maximum Landing Gear Extended Speed knots Vlo Maximum Landing Gear Operation Speed knots VOR VHF Omni directional Range WOW Weight on Wheels Wx Weather Radar XFER Transfer XPDR Transponder PC 12 47E AMM Doc No 02300 ISSUE 01 REVISION...

Page 74: ...C 12 47E AMM Doc No 02300 ISSUE 01 REVISION 26 MSN 545 1001 1719 1721 1999 12 B AM 00 00 00 I UNCLASSIFIED Intentionally left blank Effectivity All 12 B 00 00 00 00A 005A A UNCLASSIFIED 2021 12 04 Page 8 ...

Page 75: ...ation Code 4 9 7 Information Code Variant 6 9 8 Item Location Code 6 10 Standard Numbering System 6 11 Punctuation in Units of Weight and Measurement 14 12 Consumable Materials 14 13 List of Abbreviations 14 14 Publication Revision Request 14 Index of Tables Page 1 References 1 References Table 1 References Data module Technical publication Title 12 B 00 00 00 00A 005A A LIST OF ABBREVIATIONS 12 B...

Page 76: ...dentified on the Title Page of the publication Additional statements are used within the Data Module DM where necessary to give pre and post SB status or component applicability DMs identified as optional may or may not be applicable and depends on aircraft configuration 3 Responsibilities It is the responsibility of the owner to ensure that the latest revision of the manual is used for servicing ...

Page 77: ...ement Pilatus Aircraft Ltd requests that Operators and Service Centers report aircraft malfunctions using the MyPilatus internet portal which will help Pilatus Aircraft Ltd to comply with this regulation 7 Publication Revisions Revisions to the IETP correct change and add new information A revision is issued as a new replacement DVD or downloaded from www pilatus aircraft com MyPilatus Customer Po...

Page 78: ...ystem YY Y YY YY YY YYY YYYY Y The Standard Numbering System SNS is used to codify the functional and or physical breakdown of the aircraft Refer to Para 10 for more details 9 4 Disassembly Code YY Y YY YY YY YYY YYYY Y The Disassembly Code DC identifies the breakdown condition of an assembly to which maintenance information applies Or in the Illustrated Parts Data IPD it is the IPD figure number ...

Page 79: ... Documentation 106 List of Software 250 Clean 255 Purge 256 Polish and Apply Protection 259 Apply Surface Protection 280 Inspections 281 Scheduled Inspections 282 Unscheduled Inspections 307 Parts List 310 Examine 313 Inspection Check 330 Prepare Test Equipment 331 Connect the Computer 350 Structure Test 352 Magnetic Particle Inspection 353 Eddy Current Inspection 361 Allowable Wear Dimension Chec...

Page 80: ...licable for codes A B and C 10 Standard Numbering System YY Y YY YY YY YYY YYYY Y The Standard Numbering System SNS contains three groups of characters The SNS allocates and provides definitions for the system subsystem sub subsystem and the unit or assembly System YY Y YY YY YY YYY YYYY Y The system is identified by two numeric characters Subsystem Sub subsystem YY Y YY YY YY YYY YYYY Y The first...

Page 81: ...heduled Maintenance Check Lists 40 Scheduled Maintenance Checks 50 Unscheduled Maintenance Checks 06 Dimensions and Areas 00 General 10 Dimensions and Zones 20 Access Provisions 07 Lifting and Shoring 00 General 10 Jacking 20 Shoring 08 Leveling and Weighing 00 General 10 Weighing 20 Leveling 09 Handling and Taxiing 00 General 10 Handling 20 Taxiing 10 Parking Mooring and Storing 00 General 10 Par...

Page 82: ...stribution 30 Pressurization Control 40 Heating 41 Engine Bay Ducts 43 Footwarmer 50 Cooling 60 Temperature Control 22 Auto Flight 00 General 10 Autopilot 20 Speed Attitude Correction 23 Communications 00 General 10 Speech Communication 11 HF Communication 12 VHF Communication 16 Satcom System 40 Passenger Advisory System 50 Audio Integrating System 51 Noise Cancelling Headsets 60 Static Dischargi...

Page 83: ...es 80 Insulation 90 Cold Weather Preheater System 26 Fire Protection 00 General 10 Detection 20 Extinguishing 27 Flight Controls 00 General 10 Aileron Control System 15 Aileron Trim 20 Rudder Control System 25 Rudder Trim 30 Elevator Control System 40 Horizontal Stabilizer Trim 50 Flaps 51 Flap Drive System Wing 70 Gust Lock 28 Fuel 00 General 10 Storage 20 Distribution 21 Balancing System 40 Indi...

Page 84: ...ters 41 Modular Avionics Unit 42 MAU Modules 43 MAU Cooling Fans 50 Central Advisory and Warning System 51 Aural Warning System 52 Crew Alerting System 53 Flight Alerting System 60 Central Display System 32 Landing Gear 00 General 10 Main Gear and Doors 20 Nose Gear and Doors 30 Extension and Retraction 40 Wheels and Brakes 50 Steering 60 Position and Warning 33 Lights 00 General 10 Flight Compart...

Page 85: ... Electronic Standby Instrument System 30 Landing and Taxiing Aids 32 Marker System 40 Independent Position Determining 41 Weather Radar 42 Radar Altimeter System 44 TCAS 45 Enhanced Ground Proximity Warning Sys tem 50 Dependent Position Determining 51 VHF Navigation 52 DME 53 ADF 54 ATC Transponder 57 Global Navigation 35 Oxygen 00 General 10 Crew 20 Passenger 45 Central Maintenance System 00 Gene...

Page 86: ...uselage 30 Rear Fuselage 55 Stabilizers 00 General 10 Horizontal Stabilizer 20 Elevators 30 Vertical Stabilizer 40 Rudder 56 Windows 00 General 11 Windshield 14 Direct Vision 20 Fuselage Compartment 57 Wings 00 General 20 Wing Structure 33 Wing Tip 50 Flaps 60 Ailerons 61 Propellers 00 General 10 Propeller Assembly 20 Controlling PC 12 47E AMM Doc No 02300 ISSUE 01 REVISION 26 MSN 545 1001 1719 17...

Page 87: ...istribution 76 Engine Controls 00 General 10 Power Control 20 Manual Override 77 Engine Indicating 00 General 40 Integrated Engine Instrument System 78 Exhaust 00 General 10 Exhaust Stubs 79 Oil 00 General 20 Distribution 30 Indicating 80 Starting 00 General 10 Cranking PC 12 47E AMM Doc No 02300 ISSUE 01 REVISION 26 MSN 545 1001 1719 1721 1999 12 B AM 00 00 00 I UNCLASSIFIED Effectivity All 12 B ...

Page 88: ...es a material number which is used throughout the manual 13 List of Abbreviations Refer to AMM 12 B 00 00 00 00A 005A A for the list of abbreviations 14 Publication Revision Request If operators have suggestions for improvements to the content of the manual or errors are found please submit the proposed changes use this form AMM 12 B 00 00 00 00A 030A A by email to publications pilatus aircraft co...

Page 89: ...e 12 B 00 00 00 10A 030A A PDF Description This DM gives the Primus APEX software part numbers and associated hardware compatibility tables refer to AMM 12 B 00 00 00 10A 030A A PDF PC 12 47E AMM Doc No 02300 ISSUE 01 REVISION 26 MSN 545 1001 1719 1721 1999 12 B AM 00 00 00 I UNCLASSIFIED Effectivity All 12 B 00 00 00 00A 106A A End of data module UNCLASSIFIED 2021 12 04 Page 1 ...

Page 90: ...C 12 47E AMM Doc No 02300 ISSUE 01 REVISION 26 MSN 545 1001 1719 1721 1999 12 B AM 00 00 00 I UNCLASSIFIED Intentionally left blank Effectivity All 12 B 00 00 00 00A 106A A UNCLASSIFIED 2021 12 04 Page 2 ...

Page 91: ...X X No Tools Disk not installed on a c includes Remote Terminal APM Settings Tool TM60000075 104 N A 985 99 12 257 X X X X No Remote Terminal part of TM60000075 104 RT 5 3 DLS 7 1 2 985 99 12 257 X X X X No APM Settings Tool part of TM60000075 104 APM Settings v2 1 985 99 12 257 X X X X X X No Primus Apex System Build 8 8 Software EB60000487 0111 MM60000486 012 985 99 12 270 X Yes Primus Apex Opti...

Page 92: ...A PWR 210 Power Supply Module 7038248 1901 HW MOD_A_B_C N A 985 99 12 346 X X X X X X X X X X N A NIC Module 7 NIC 100 NIC Module 7026542 1801 HW MOD_A_B_J N A 985 99 12 148 X X X X X X N A NIC 110 NIC Module 7038231 1801 HW MOD_B_D_E N A 985 99 12 231 X X X X X X X X X N A AGM Module 7 AGM 200 AGM Module 7036410 1902 HW MOD_B_C N A 985 99 12 157 X X X X X X X X X X N A AGM 200 AGM Module 7036410 ...

Page 93: ...1902 HW MOD_B_C_D_E_F N A 985 99 12 052 X X X AGM 200 AGM Module 7036410 1902 HW MOD_B_C_D_E_F_G N A 985 99 12 062 X X X AGM 200 AGM Module 7036410 1904 HW MOD_B_C N A 985 99 12 222 X X X AGM 200 AGM Module 7036410 1904 HW MOD_B_C_D N A 985 99 12 281 X X X AGM 200 AGM Module 7036410 1904 HW MOD_B_C_D_E N A 985 99 12 292 X X X AGM 200 AGM Module 7036410 1904 HW MOD_B_C_D_E_F N A 985 99 12 051 X X X...

Page 94: ...onent Limitations 5 4 Miscellaneous Limitations 7 5 Supplemental Structural Inspection Program 12 References Table 1 References Data module Technical publication Title 12 B 05 10 30 00A 280A A SUPPLEMENTAL STRUCTUAL INSPECTION DOCUMENT 12 B 20 40 00 00A 901A A CORROSION CONTROL MAINTENANCE PRACTICES 12 B 21 30 00 00A 903A A PRESSURIZATION CONTROL MSN 1001 1719 ADJUST MENT TEST 12 B 21 30 00 00A 90...

Page 95: ...TION CHECK 12 B 27 51 00 00A 353A A FLAP DRIVE SYSTEM IN SITU EDDY CURRENT INSPEC TION 12 B 27 51 01 00A 353A A FLAP DRIVE SYSTEM WING INBOARD MECHANISM EDDY CURRENT INSPECTION 12 B 27 51 02 00A 353A A FLAP DRIVE SYSTEM WING CENTER MECHANISM EDDY CURRENT INSPECTION 12 B 27 51 03 00A 353A A FLAP DRIVE SYSTEM WING OUTBOARD MECHANISM EDDY CURRENT INSPECTION 12 B 32 10 00 00A 310A A MAIN LANDING GEAR ...

Page 96: ... 00 00A 310A A ELEVATORS EXAMINE 12 B 55 20 01 00A 353A A ELEVATOR DRIVE LEVER AND HINGE EDDY CURRENT INSPECTION 12 B 55 30 00 00A 310A A VERTICAL STABILIZER EXAMINE 12 B 55 30 02 00A 353A A VERTICAL STABILIZER PITCH TRIM ACTUATOR ATTACH MENT EDDY CURRENT INSPECTION 12 B 55 30 03 00A 353A A VERTICAL STABILIZER SPARS EDDY CURRENT INSPEC TION 12 B 55 40 00 00A 310A A RUDDER EXAMINE 12 B 55 40 05 00A...

Page 97: ...s Limitations section is FAA approved and specifies maintenance required under Parts 43 16 and 91 403 of the Federal Aviation Regulations unless an alternate program has been FAA approved Refer to the Pilot s Operating Handbook Airplane Flight Manual for the approved seats and seat limitations On the PC 12 47E aircraft do not install the following components Nose Landing Gear 532 20 12 038 with se...

Page 98: ...e Pre SB 04 009 20 000 FH 27 000 LDG See Note 1 57 00 326 Wing structure Post SB 04 009 25 000 FH 30 000 LDG See Note 1 3 Component Limitations Table 3 Component Limitations Task number Component Life 26 20 2 Fire extinguisher except Model P3APP003010D 120 Months elapsed 26 20 516 Fire extinguisher Model P3APP003010D 144 Months elapsed 27 10 444 Flight control cables aileron 20 000 FH 27 000 LDG 2...

Page 99: ...17 MLG hydraulic actuator 25 000 FH 30 000 LDG 32 30 423 Electro mechanical landing gear ac tuators 30 000 LDG 32 30 518 Main landing gear actuator bottom attachment bolts P N 532 10 12 218 identified with 218 and VLG on bolt head 60 Months See Note 6 35 10 6 Oxygen bottle 180 Months elapsed 52 30 8 Cargo door lower lug fittings qty 3 13 000 FH 17 000 LDG 55 10 415 Horizontal stabilizer 25 000 FH ...

Page 100: ...ive pressure re lief valve Functional test 4 800 FH 48 Months 12 B 21 30 00 00A 903B A 21 30 468 MSN 1720 9999 Cabin pressurization altitude limiting func tion Functional test 4 800 FH 48 Months 12 B 21 30 00 00A 903B A 21 30 469 MSN 1720 9999 Cabin pressurization high cabin altitude warning Functional test 4 800 FH 48 Months 12 B 21 30 00 00A 903B A 24 30 311 Generator control units GCU 1 and GCU...

Page 101: ...mine 10 Year See Note 7 12 B 32 10 00 00A 310B A 32 20 338 NLG upper drag link right part P N 532 20 12 289 Inspection check Initially 2000 FH or 2500 landings then every 300 FH or 400 landings 12 B 32 20 06 00A 313A A 32 30 424 Emergency gear ex tension system Elec tro mechanical land ing gear Operational test 2 000 FH 12 Months See Note 2 12 B 32 30 10 00A 903A A 32 30 426 Time delay relays and ...

Page 102: ...or limi tations If chipped cracked only for inner side windows crazing scratched bubbles or delaminated 12 B 56 00 00 00A 313A A 56 11 14 Windshield LH and RH Replace If cracked in inner lamination 56 11 15 Windshield LH and RH Only unpressurized flight is permitted up to the next scheduled inspection providing it does not cause visual problems If cracked in outer lamination 57 00 427 Wing main sp...

Page 103: ...hever comes first Note Before starting implementation of SB 04 009 and or the SSID a suitability assessment performed by Pilatus is recommended to establish any potential resulting limitations related to the aircraft condition at time of the life extension Contact Pilatus for the lead time of the Pilatus support activities as listed in Para 5 2 and Para 5 3 www pilatus aircraft com contact In addi...

Page 104: ...t Pilatus can do the assessments for items b and the first part of c in addition to a above provided sufficient information is given 5 4 Supplemental Corrosion Prevention and Control Program CPCP The maximum corrosion level to be maintained is Corrosion Level 1 Refer to AMM 12 B 20 40 00 00A 901A A for Corrosion Control Maintenance Practices The supplemental CPCP inspection tasks are identified in...

Page 105: ...Eddy current and magnetic particle In spections 12 B 27 10 08 00A 353A A 12 B 27 10 08 00A 353B A 12 B 27 10 08 00A 352B A 32 500 42 000 12 500 15 000 27 10 400 Aileron hinge points Eddy current inspection 12 B 57 60 06 00A 353A A 32 500 42 000 12 500 15 000 27 20 374 Rudder control system Examine Inspection kit rudder control P N 500 60 12 018 12 B 27 20 00 00A 310A A 32 500 42 000 12 500 15 000 ...

Page 106: ...024 Inspection kit flap LH and RH outer one kit required for each P N 500 60 12 025 12 B 27 51 00 00A 310A A 30 000 39 000 10 000 12 000 6 27 50 387 Flap drive arm not removed Eddy current inspection 12 B 27 51 00 00A 353A A 25 000 30 000 2 500 3 000 27 50 388 Flap drive arm removed Eddy current inspection 12 B 27 51 01 00A 353A A or 12 B 27 51 02 00A 353A A or 12 B 27 51 03 00A 353A A 30 000 39 0...

Page 107: ...rew door Examine all structural elements 12 B 52 10 00 00A 310A A 32 500 42 000 12 500 15 000 6 52 20 349 Emergency door Examine all structural elements 12 B 52 20 00 00A 310A A 32 500 42 000 12 500 15 000 6 52 30 350 Cargo door Examine all structural elements 12 B 52 30 00 00A 310A A 32 500 42 000 12 500 15 000 6 53 00 351 Upper longerons Frame 10 Eddy current inspection Inspection kit longeron f...

Page 108: ...rames P N 500 50 12 327 12 B 53 20 02 00A 353A A 30 000 39 000 10 000 12 000 53 00 361 Frames 41 and 43 stabilizer attachment Eddy current inspection Inspection kit vertical stabilizer P N 500 50 12 325 12 B 53 30 02 00A 353A A or 12 B 55 30 03 00A 353A A 32 500 42 000 12 500 15 000 55 20 362 Elevator Examine 12 B 55 20 00 00A 310A A 32 500 42 000 12 500 15 000 6 55 20 367 Elevator drive lever Edd...

Page 109: ... 000 56 11 378 Windshield LH and RH and cockpit side windows Examine with windshield and side win dows removed Inspection kit windshield P N 500 50 12 326 12 B 56 11 01 00A 310A A and 12 B 56 11 02 00A 310A A and 12 B 53 10 16 00A 310A A 32 500 42 000 12 500 15 000 6 57 00 379 Wing Examine all structural elements Rib 1 to Rib 20 12 B 57 00 00 00A 310A A 30 000 39 000 10 000 12 000 6 57 00 380 Wing...

Page 110: ...00 4 000 57 00 385 Wing rear spar fastener holes Rib 2 thru Rib 3 Eddy current inspection 12 B 57 20 10 00A 353B A 25 000 30 000 12 500 15 000 57 60 393 Aileron Examine 12 B 57 60 00 00A 310A A 32 500 42 000 12 500 15 000 6 71 00 401 Engine mount Magnetic particle inspection Inspection kit engine mount P N 500 60 12 006 12 B 71 00 05 00A 352A A 26 600 35 000 6 600 8 000 The technical content of th...

Page 111: ... 12 47E AMM Doc No 02300 ISSUE 01 REVISION 26 MSN 545 1001 1719 1721 1999 12 B AM 00 00 00 I UNCLASSIFIED Intentionally left blank Effectivity All 12 B 04 00 00 00A 000A A UNCLASSIFIED 2021 12 04 Page 18 ...

Page 112: ...References Data module Technical publication Title None Required Conditions Table 2 Required Conditions Action Condition Data module Technical publication None Support equipment Table 3 Support equipment Name Identifications References Qty Reference Remark None Supplies Table 4 Supplies Name Identifications References Qty Reference Remark None PC 12 47E AMM Doc No 02300 ISSUE 01 REVISION 26 MSN 54...

Page 113: ...434 ELT Nav interface unit serial memory module if Kannad 406 AF Nav inter face unit installed 16 000 FH 120 Months 25 63 480 Underwater beacon locator if installed 72 Months 27 50 28 Flap power drive unit P N 978 73 20 003 10 000 FH 13 500 LDG 27 50 506 Flap actuators black anodized P N 978 73 20 309 5 000 FH 7 000 LDG 28 20 32 Engine driven pump 3 500 FH 32 30 435 NLG and MLG Electro mechanical ...

Page 114: ...vision 79 20 43 Oil cooler At engine overhaul Requirements after job completion Required Conditions Table 7 Required Conditions Action Condition Data module Technical publication None PC 12 47E AMM Doc No 02300 ISSUE 01 REVISION 26 MSN 545 1001 1719 1721 1999 12 B AM 00 00 00 I UNCLASSIFIED Effectivity All 12 B 05 10 10 00A 281A A End of data module UNCLASSIFIED 2021 12 04 Page 3 ...

Page 115: ...C 12 47E AMM Doc No 02300 ISSUE 01 REVISION 26 MSN 545 1001 1719 1721 1999 12 B AM 00 00 00 I UNCLASSIFIED Intentionally left blank Effectivity All 12 B 05 10 10 00A 281A A UNCLASSIFIED 2021 12 04 Page 4 ...

Page 116: ...FETY VALVE CLEAN 12 B 21 30 05 00A 310A A NEGATIVE PRESSURE RELIEF VALVE EXAMINE 12 B 21 40 06 00A 903A A OVERTEMPERATURE SWITCH ADJUSTMENT TEST 12 B 21 50 01 00A 903A A VAPOUR CYCLE COOLING SYSTEM ADJUSTMENT TEST 12 B 21 50 03 00A 313A A COMPRESSOR DRIVE MOTOR INSPECTION CHECK 12 B 21 60 05 00A 903A A DUCT OVERTEMPERATURE SWITCH ADJUST MENT TEST 12 B 24 30 07 00A 920A A LEAD ACID BATTERY REMOVAL ...

Page 117: ...IC SYSTEM ADJUSTMENT TEST 12 B 34 11 12 00A 313A A STATIC PORT RVSM INSPECTION CHECK 12 B 34 14 00 00A 903B A ALTITUDE AND VERTICAL SPEED INDICATION RVSM ADJUSTMENT TEST 12 B 34 21 00 00A 903A A STANDBY MAGNETIC COMPASS ADJUSTMENT TEST 12 B 34 26 40 00A 903B A ELECTRONIC STANDBY INSTRUMENT SYSTEM MSN 1271 1719 1721 1999 OR POST SB 34 042 ADJUST MENT TEST 12 B 34 54 00 00A 903A A DUAL DIVERSITY ATC...

Page 118: ...able 2 Required Conditions Action Condition Data module Technical publication None Support equipment Table 3 Support equipment Name Identifications References Qty Reference Remark None Supplies Table 4 Supplies Name Identifications References Qty Reference Remark None Spares Table 5 Spares Name Identifications References Qty Reference Remark None Safety Conditions None PC 12 47E AMM Doc No 02300 I...

Page 119: ...r cycle compres sor motor if installed Inspection check 500 Operating hours 12 B 21 50 03 00A 313A A 21 50 59 Vapor cycle compres sor motor drive belt if installed Check for tension 500 Operating hours 12 B 21 50 01 00A 903A A 21 50 433 Vapor cycle compres sor condenser mod ule including motor if installed Clean refer to OSCMM Initially at each scheduled inspection then based on field experience t...

Page 120: ...n locator if installed Functional test 24 Months 12 B 25 63 04 00A 903A A 25 63 479 Underwater locator beacon battery volt age if installed Functional test 24 Months 12 B 25 63 04 00A 903A A 26 20 24 Fire extinguisher except Model P3APP003010D Content check 12 Months elapsed 26 20 515 Fire extinguish er Model P3APP003010D Content check 24 Months elapsed 27 00 71 Flight control cables including aut...

Page 121: ...irfoil de icers Apply a surface coat ing of Age Master No 1 in accordance with the manufactur ers instructions CMM 30 10 31 latest is sue Note The deice boot treat ment with Age Mas ter No 1 can be performed by the op erator IAW the in structions given in the AFM 8 Deicing Boot Care 6 Months 32 10 80 Main and nose wheel bearings Lubricate Tire change or 12 Months whichever comes first 12 B 12 20 0...

Page 122: ...Examine the top step area around the insu lation mat for corro sion If corrosion is found write to Pilatus for a specific repair Examine door hinge pin and hinges Mild Corrosive Envi ronment 6000 FH or 72 Months Moderate Corrosive Environment 4000 FH or 48 Months Severe Corrosive En vironment 2000 FH or 24 Months Note Local conditions may be more or less se vere Based on field experience the inter...

Page 123: ... be set 12 B 25 21 03 00A 920A A or 12 B 25 22 03 00A 920A A and 12 B 52 30 00 00A 313A A 53 00 90 Front pressure bulk head Examine with insu lation on engine and cockpit sides re moved If insulation on cockpit side is wet remove dry and reinstall insulation Mild Corrosive Envi ronment 6000 FH or 72 Months Moderate Corrosive Environment 4000 FH or 48 Months Severe Corrosive En vironment 2000 FH or...

Page 124: ...nment 2000 FH or 24 Months Note Local conditions may be more or less se vere Based on field experience the inter val can be adjusted to more or less fre quent until an effec tive interval can be set 53 00 92 Rear pressure bulk head Examine with trim re moved Mild Corrosive Envi ronment 6000 FH or 72 Months Moderate Corrosive Environment 4000 FH or 48 Months Severe Corrosive En vironment 2000 FH or...

Page 125: ...ency exit frame Examine If insulation is installed in the door frames and is wet remove and discard it no longer installed on production Mild Corrosive Envi ronment 6000 FH or 72 Months Moderate Corrosive Environment 4000 FH or 48 Months Severe Corrosive En vironment 2000 FH or 24 Months Note Local conditions may be more or less se vere Based on field experience the inter val can be adjusted to mo...

Page 126: ...e or less fre quent until an effec tive interval can be set 55 10 96 Vertical stabilizer in ternal surfaces Examine as far as possible with panels removed Mild Corrosive Envi ronment 6000 FH or 72 Months Moderate Corrosive Environment 4000 FH or 48 Months Severe Corrosive En vironment 2000 FH or 24 Months Note Local conditions may be more or less se vere Based on field experience the inter val can...

Page 127: ... Corrosive Envi ronment 6000 FH or 72 Months Moderate Corrosive Environment 4000 FH or 48 Months Severe Corrosive En vironment 2000 FH or 24 Months Note Local conditions may be more or less se vere Based on field experience the inter val can be adjusted to more or less fre quent until an effec tive interval can be set 57 00 99 Wing to fuselage at tachments Examine attachment fittings with wings re...

Page 128: ... following time limited inspections must be complied with Table 7 Time Limited Inspection Requirements RVSM Aircraft Task No Item Name Task Description Interval Data Module Reference 34 11 82 Static system Leak check 24 Months AMM 12 B 34 11 00 00A 903A A 34 11 343 Static ports plate height Inspection check 24 Months AMM 12 B 34 11 12 00A 313A A 34 25 344 Altitude and vertical speed indication Fun...

Page 129: ... 12 47E AMM Doc No 02300 ISSUE 01 REVISION 26 MSN 545 1001 1719 1721 1999 12 B AM 00 00 00 I UNCLASSIFIED Intentionally left blank Effectivity All 12 B 05 10 20 00A 281A A UNCLASSIFIED 2021 12 04 Page 14 ...

Page 130: ...DY CURRENT INSPEC TION 12 B 52 10 01 00A 353A A PASSENGER CREW DOOR SKINS EDDY CURRENT IN SPECTION 12 B 52 30 00 01A 353A A CARGO DOOR HINGE EDDY CURRENT INSPECTION 12 B 52 30 01 00A 353A A CARGO DOOR SKINS EDDY CURRENT INSPECTION 12 B 53 30 02 00A 353A A REAR FUSELAGE FRAMES EDDY CURRENT INSPEC TION 12 B 55 30 03 00A 353A A VERTICAL STABILIZER SPARS EDDY CURRENT INSPEC TION 12 B 55 40 04 00A 310A...

Page 131: ...eference Remark None Supplies Table 4 Supplies Name Identifications References Qty Reference Remark None Spares Table 5 Spares Name Identifications References Qty Reference Remark None Safety Conditions None PC 12 47E AMM Doc No 02300 ISSUE 01 REVISION 26 MSN 545 1001 1719 1721 1999 12 B AM 00 00 00 I UNCLASSIFIED Effectivity All 12 B 05 10 30 00A 280A A UNCLASSIFIED 2021 12 04 Page 2 ...

Page 132: ...0 405 Passenger crew door piano hinge Eddy current inspection 12 B 52 00 01 00A 353A A 32 500 42 000 12 500 15 000 52 10 406 Passenger crew door skin Eddy current inspection 12 B 52 10 01 00A 353A A 25 000 30 000 12 500 15 000 6 52 30 407 Cargo door piano hinge Eddy current inspection 12 B 52 30 00 01A 353A A 32 500 42 000 12 500 15 000 52 30 408 Cargo door skin Eddy current inspection 12 B 52 30 ...

Page 133: ...ion 12 B 57 20 01 00A 353A A 25 000 30 000 2 500 3 000 57 60 411 Aileron trim tab Examine Inspection kit P N 500 50 12 317 or Inspection kit P N 500 60 12 039 and Inspection kit P N 500 60 12 040 12 B 57 60 04 00A 310A A 32 500 42 000 12 500 15 000 6 Requirements after job completion Required Conditions Table 7 Required Conditions Action Condition Data module Technical publication None PC 12 47E A...

Page 134: ...PRACTICES 12 B 12 20 01 00A 902A A AIRCRAFT EXTERIOR WASHING SERVICING 12 B 12 20 02 00A 902A A AIRCRAFT WINDOWS CLEANING SERVICING 12 B 12 20 03 00A 902A A AIRCRAFT INTERIOR CLEANING SERVICING 12 B 25 10 01 00A 920A A FLIGHT COMPARTMENT CREW SEATS REMOVAL IN STALLATION 12 B 25 21 01 00A 920A A EXECUTIVE SEATS REMOVAL INSTALLATION 12 B 25 22 01 00A 920A A STANDARD SEATS REMOVAL INSTALLATION 12 B 7...

Page 135: ...er Item Name Task Description Data Module Reference Signature Stamp Inspection 07 10 161 Aircraft Lift on jacks and connect the air craft to ground 12 B 07 10 00 00A 901A A 12 20 124 Aircraft Wash the exte rior including the landing gear and flap compart ments as required to perform the in spection 12 B 12 20 01 00A 902A A 12 20 125 Windshields and windows Clean 12 B 12 20 02 00A 902A A 12 20 126 ...

Page 136: ...on ground run is not a prerequisite but may be use ful to determine any repair work needed to main tain the airwor thiness of the aircraft 12 B 71 00 00 00A 903A A 71 10 207 Engine cowlings ENG 43AL and ENG 43AR Open and exam ine particularly for condition of rubbing strips and fasteners Lubri cate the hing es with a mini mum of material P10 001 3 Do the job close up as necessary to do the schedul...

Page 137: ...ect from ground 12 B 07 10 00 00A 901A A 25 10 297 Crew seats Install as neces sary to close the inspection 12 B 25 10 01 00A 920A A 25 20 299 Passenger seats Install as neces sary to close the inspection 12 B 25 21 01 00A 920A A or 12 B 25 22 01 00A 920A A 27 50 475 Flaps Retract to 0 as necessary to close the inspec tion 71 00 204 Power plant Post inspection ground run tests 12 B 71 00 00 00A 90...

Page 138: ...red Conditions Action Condition Data module Technical publication None PC 12 47E AMM Doc No 02300 ISSUE 01 REVISION 26 MSN 545 1001 1719 1721 1999 12 B AM 00 00 00 I UNCLASSIFIED Effectivity All 12 B 05 20 00 00A 913A A End of data module UNCLASSIFIED 2021 12 04 Page 5 ...

Page 139: ...C 12 47E AMM Doc No 02300 ISSUE 01 REVISION 26 MSN 545 1001 1719 1721 1999 12 B AM 00 00 00 I UNCLASSIFIED Intentionally left blank Effectivity All 12 B 05 20 00 00A 913A A UNCLASSIFIED 2021 12 04 Page 6 ...

Page 140: ...S MAINTENANCE PRACTICES 12 B 12 10 02 00A 902A A BRAKES SERVICING 12 B 12 10 04 00A 902A A TIRES SERVICING 12 B 12 20 01 00A 902A A AIRCRAFT EXTERIOR WASHING SERVICING 12 B 12 20 02 00A 902A A AIRCRAFT WINDOWS CLEANING SERVICING 12 B 12 20 03 00A 902A A AIRCRAFT INTERIOR CLEANING SERVICING 12 B 12 20 04 00A 902A A LANDING GEAR SERVICING 12 B 12 20 06 00A 902A A WHEEL BEARING SERVICING 12 B 12 20 0...

Page 141: ...MUNICATION ADJUSTMENT TEST 12 B 23 50 00 00A 903A A AUDIO INTEGRATING SYSTEM ADJUSTMENT TEST 12 B 24 30 01 00A 313A A STARTER GENERATOR INSPECTION CHECK 12 B 24 30 07 00A 920A A LEAD ACID BATTERY REMOVAL INSTALLATION 12 B 24 30 07 00A 920B A NI CAD BATTERY REMOVAL INSTALLATION 12 B 24 30 07 00A 920C A HEATED NI CAD BATTERY REMOVAL INSTALLATION 12 B 24 40 00 00A 903A A EXTERNAL POWER VOLTAGE DISCON...

Page 142: ...CONTROL SYSTEM FUSELAGE CABLE QUAD RANT EDDY CURRENT INSPECTION 12 B 27 15 00 00A 903A A AILERON TRIM ADJUSTMENT TEST 12 B 27 20 00 00A 310A A RUDDER CONTROL SYSTEM EXAMINE 12 B 27 20 00 00A 313A A RUDDER CONTROL SYSTEM INSPECTION CHECK 12 B 27 20 00 00A 903A A RUDDER CONTROL SYSTEM ADJUSTMENT TEST 12 B 27 20 05 00A 310A A RUDDER CONTROL SYSTEM CABLE QUADRANT EXAM INE 12 B 27 25 00 00A 903A A RUDD...

Page 143: ...0A 313A A RETURN LINE FILTER DIFFERENTIAL PRESSURE INDICA TOR INSPECTION CHECK 12 B 30 10 00 00A 313A A AIRFOIL DE ICE BOOTS INSPECTION CHECK 12 B 30 10 00 00A 903A A AIRFOIL DE ICE SYSTEM TIMER WITHOUT INHIBIT FUNC TION ADJUSTMENT TEST 12 B 30 10 00 00A 903B A AIRFOIL DE ICE SYSTEM TIMER WITH INHIBIT FUNC TION ADJUSTMENT TEST 12 B 30 20 00 00A 903A A AIR INTAKE DE ICE SYSTEM ADJUSTMENT TEST 12 B ...

Page 144: ...NSTAL LATION 12 B 32 30 02 01A 920B A NLG ACTUATOR ANTI ROTATION PAD REMOVAL INSTAL LATION 12 B 32 30 08 00A 903A A LANDING GEAR RELAY UNIT ELECTRO MECHANICAL LANDING GEAR ADJUSTMENT TEST 12 B 32 30 10 00A 903A A EMERGENCY GEAR EXTENSION SYSTEM ELECTRO ME CHANICAL LANDING GEAR ADJUSTMENT TEST 12 B 32 50 00 00A 310A A NOSE WHEEL STEERING EXAMINE 12 B 33 40 00 00A 903A A EXTERNAL LIGHTS ADJUSTMENT T...

Page 145: ...0 00 00A 313A A PASSENGER CREW DOOR INSPECTION CHECK 12 B 52 10 01 00A 353A A PASSENGER CREW DOOR SKINS EDDY CURRENT IN SPECTION 12 B 52 10 06 00A 353A A PASSENGER DOOR SHOOT BOLTS POST SB 52 007 EDDY CURRENT INSPECTION 12 B 52 20 00 00A 310A A EMERGENCY EXIT EXAMINE 12 B 52 30 00 00A 310A A CARGO DOOR EXAMINE 12 B 52 30 00 00A 313A A CARGO DOOR INSPECTION CHECK 12 B 52 30 00 01A 353A A CARGO DOOR...

Page 146: ...N 12 B 55 20 01 00A 904B A ELEVATOR LEVER FITTING UP AND DOWN STOPS RE PAIR 12 B 55 30 00 00A 310A A VERTICAL STABILIZER EXAMINE 12 B 55 30 02 00A 353A A VERTICAL STABILIZER PITCH TRIM ACTUATOR ATTACH MENT EDDY CURRENT INSPECTION 12 B 55 30 03 00A 353A A VERTICAL STABILIZER SPARS EDDY CURRENT INSPEC TION 12 B 55 40 00 00A 310A A RUDDER EXAMINE 12 B 55 40 00 00A 313A A RUDDER INSPECTION CHECK 12 B ...

Page 147: ...TAB EXAMINE 12 B 57 60 06 00A 353A A AILERON HINGE EDDY CURRENT INSPECTION 12 B 71 00 00 00A 903A A POWER PLANT ADJUSTMENT TEST 12 B 71 00 00 00A 903D A POWER PLANT TEST 3 DC GENERATION SYSTEM AD JUSTMENT TEST 12 B 71 00 00 00A 903G A POWER PLANT TEST 6 TORQUE LIMITER ADJUST MENT TEST 12 B 71 00 00 00A 903H A POWER PLANT TEST 7 ENGINE PERFORMANCE AD JUSTMENT TEST 12 B 71 00 03 00A 250A A ELECTRICA...

Page 148: ...fied by the asterisk Note 1 Do not do the inspection more than 500 FH or 500 landings before the stated inspection or life limit Note 2 A 10 tolerance only to the calendar time interval is applicable Note 3 A 10 tolerance is applicable to the flying hour and calendar time intervals Note 4 Aircraft with rudder bellcrank with more than 20 000 flying hours or 27 000 landings whichever comes first mus...

Page 149: ...2NB 52OB 52PB 52RB 52TB 52SB 61KB 61MB 61NB 62KB 62MB 62NB 62OB 62PB 62RB 62SB 62TB Remove and exam ine 1 200 FH 12 Months 12 B 06 20 00 00A 040A A 06 00 579 Access panels wing 51LB 51JB 51KB 51MB 51NB 52KB 52MB 52NB 52OB 52PB 52RB 52TB 52SB 61KB 61MB 61NB 62KB 62MB 62NB 62OB 62PB 62RB 62SB 62TB Install 1 200 FH 12 Months 12 B 06 20 00 00A 040A A 06 00 582 Access panels en gine 41AT 42AB 42AT Remo...

Page 150: ...6 20 00 00A 040A A 06 00 602 Access panels en gine 42AT 42AB Remove and exam ine 600 FH 12 B 06 20 00 00A 040A A 06 00 603 Access panels en gine 42AT 42AB Install 600 FH 12 B 06 20 00 00A 040A A 06 00 604 Access panels fuse lage 11AL 12EL 12QZ Remove and exam ine 600 FH 12 Months 12 B 06 20 00 00A 040A A 06 00 605 Access panels fuse lage 11AL 12EL 12QZ Install 600 FH 12 Months 12 B 06 20 00 00A 04...

Page 151: ...0 612 Access panels en gine 42AT 42AB Remove and exam ine 1 200 FH 12 Months 12 B 06 20 00 00A 040A A 06 00 613 Access panels en gine 42AT 42AB Install 1 200 FH 12 Months 12 B 06 20 00 00A 040A A 06 00 614 Access panels fuse lage 11AL 11AZ 11BL 12EL 12ER 12CZ 12EZ 12FZ 21JZ Open or remove Ex amine and make sure the access panel drain holes are clear 2 400 FH 24 Months 12 B 06 20 00 00A 040A A 06 0...

Page 152: ...Set Up 12 B 07 10 00 00A 901A A 10 10 428 External protective covers Examine Replace if any part of the cover is missing damaged torn or does not in stall properly 300 FH 12 Months 11 00 220 Placards and mark ings Examine and attach new placards if nec essary 1 200 FH 12 Months 12 B 11 00 00 00A 040A A 12 B 11 00 00 00A 901A A 12 20 124 Aircraft Wash the exterior including the land ing gear and fl...

Page 153: ...nal test 3 000 FH 12 Months See Note 2 12 B 21 30 00 00A 903A A 21 30 463 MSN 1720 9999 Cabin pressurization dump control Operational test 600 FH 12 Months See Note 2 12 B 21 30 00 00A 903B A 21 30 464 MSN 1720 9999 Cabin pressurization manual control Operational test 600 FH 12 Months See Note 2 12 B 21 30 00 00A 903B A 21 30 465 MSN 1720 9999 Cabin pressurization positive pressure re lief valve F...

Page 154: ...rational test 1 200 FH 12 Months 12 B 21 40 01 00A 903A A 12 B 21 40 01 00A 903B A 21 40 331 Underfloor heater thermal protection switch Functional test 1 200 FH 12 Months 12 B 21 40 01 00A 903A A 12 B 21 40 01 00A 903B A 21 50 58 Vapor cycle compres sor motor if installed Inspection check 500 Operating hours 12 B 21 50 03 00A 313A A 21 50 59 Vapor cycle compres sor motor drive belt if installed C...

Page 155: ...00 00A 903A A 23 10 323 Emergency frequen cy COMM tuning switch Operational test 2 400 FH 24 Months 12 B 23 12 00 00A 903A A 24 30 309 Generator 1 P N 978 91 23 437 Brush Check 300 FH 12 B 24 30 01 00A 313A A 24 30 310 Starter Generator 2 P N 978 91 23 437 Brush Check 300 FH 12 B 24 30 01 00A 313A A 24 30 311 Generator control units GCU 1 and GCU 2 Functional test of the GCU 1 and GCU 2 over and u...

Page 156: ...N 978 91 23 437 Overhaul 1 000 FH 24 30 497 Starter Generator 2 P N 978 91 23 437 Overhaul 1 000 FH 24 40 229 External Power Unit EPU receptacle Examine 2 400 FH 24 Months 24 50 70 Emergency power supply if installed Remove and cap test 12 Months 12 B 24 52 51 00A 920A A 24 60 133 Cockpit circuit break er panels and switch panels Examine 2 400 FH 24 Months 25 10 134 Crew seat belts Examine 300 FH ...

Page 157: ...u tive seatsand CMM 25 20 99 for standard seats For executive seats only with the seat cushion removed check the hydrolock rearattachment bolt for security of attach ment 1 200 FH 12 Months 25 20 295 Passenger seat belts and extensions Task deleted from the Maintenance Plan 25 20 298 Passenger seats Remove as necessa ry to do the inspec tion Job Set Up 12 B 25 21 01 00A 920A A or 12 B 25 22 01 00A...

Page 158: ...c inspec tions Refer to Kannad Service Letter Main tenance Policy for Kannad ELT SL S18XX50X 25 02 25 63 23 ELT battery Discard After 1 hour of use or as shown on the bat tery label 25 63 434 ELT Nav interface unit serial memory module if Kannad 406 AF Nav interface unit installed Discard 16 000 FH 120 Months 25 63 477 Underwater beacon locator if installed Clean 24 Months 12 B 25 63 04 00A 903A A...

Page 159: ...d 32 500 FH 42 000 LDG Repeat 12 500 FH 15 000 LDG 6 Year 27 10 139 Aileron LH and RH Examine and lubri cate the trim hinges with minimum quanti ty of CPC P10 001 300 FH 12 Months 27 10 234 Aileron LH and RH rods and levers Examine Spray PTFE Teflon Spray OKS 571 or equivalent around the aileron pushrod guide roller sleeves at all three locations in each wing 1 200 FH 12 Months 27 10 235 Aileron e...

Page 160: ... 500 FH 15 000 LDG 12 B 27 00 01 00A 352A A 27 10 398 Aileron bellcranks Eddy current and magnetic particle In spections Threshold 32 500 FH 42 000 LDG Repeat 12 500 FH 15 000 LDG 12 B 27 10 08 00A 353A A 12 B 27 10 08 00A 353B A 12 B 27 10 08 00A 352B A 27 10 400 Aileron hinge points Eddy current inspec tion Threshold 32 500 FH 42 000 LDG Repeat 12 500 FH 15 000 LDG 12 B 57 60 06 00A 353A A 27 10...

Page 161: ...d from the Scheduled Main tenance Plan 27 20 376 Rudder cable quad rant shear spigot Examine Threshold 32 500 FH 42 000 LDG Repeat 12 500 FH 15 000 LDG 6 Year 12 B 27 20 05 00A 310A A 27 20 430 Rudder control ca bles tension Check for new facto ry delivered aircraft that have not done the 1200 FH or 12 Months Inspection package Within the next 300 FH 12 B 27 20 00 00A 903A A 27 20 431 Rudder contr...

Page 162: ...ator control system cables autopilot stick push er and elevator At the next scheduled inspection but not later than 300 FH 12 B 27 30 00 00A 903A A 27 30 363 Elevator control sys tem Examine Inspection kit ele vator control P N 500 60 12 019 Threshold 32 500 FH 42 000 LDG Repeat 12 500 FH 15 000 LDG 6 Year 12 B 27 30 00 00A 310A A 27 30 364 Elevator control rods Eddy current inspec tion Threshold ...

Page 163: ...ths 12 B 27 40 00 00A 903A A 27 40 252 Pitch trim actuator and attachments Inspection check 1 200 FH 12 Months 12 B 27 40 01 00A 313A A 27 40 291 Horizontal stabilizer trim system Operational test 300 FH 12 B 27 40 00 00A 903A A 27 40 292 Horizontal stabilizer trim system Functional test 1 200 FH 12 Months 12 B 27 40 00 00A 903A A 27 40 307 Pitch trim actuator at tachment parts fail safe plates an...

Page 164: ...DG Repeat 10 000 FH 12 000 LDG 6 Year 12 B 27 51 00 00A 310A A 27 50 387 Flap drive arm not removed Eddy current inspec tion Threshold 25 000 FH 30 000 LDG Repeat 2 500 FH 3 000 LDG 12 B 27 51 00 00A 353A A 27 50 388 Flap drive arm re moved Eddy current inspec tion Threshold 30 000 FH 39 000 LDG Repeat 10 000 FH 12 000 LDG 12 B 27 51 01 00A 353A A or 12 B 27 51 02 00A 353A A or 12 B 27 51 03 00A 3...

Page 165: ... limit 25 000 FH 30 000 LDG 27 50 437 Inboard flap drive arms P N 527 52 12 153 or P N 527 52 12 154 In situ inspec tion check 600 FH 12 Months See Note 3 12 B 27 51 00 00A 313A A 27 50 443 Flap up and down limit switches Servicing 300 FH 12 Months 12 B 12 20 07 00A 902A A 27 50 451 Flap tension rods P N 527 52 12 135 527 52 12 136 527 52 12 137 Life limit 20 000 FH 27 000 LDG 27 50 475 Flaps Retr...

Page 166: ...ewall shutoff valve Operate FUEL EMERG SHUTOFF lever and make sure firewall shutoff valve opens and closes fully to each dead stop Make sure movement is free and check if initial pull out force at lever outer end is below 44 5 N 10 lbf 600 FH 12 Months 28 20 150 Engine driven pump Examine 300 FH 12 Months 28 20 256 Fuel system compo nents Examine as far as possible with those access panels opened ...

Page 167: ...FH 12 Months 12 B 29 00 00 00A 902A A 29 10 418 Nitrogen accumulator Life limit 25 000 FH 30 000 LDG 29 10 471 Nitrogen accumulator P N 960 30 01 292 If installed Check nitrogen pres sure and fill as nec essary 2 400 FH 24 Months 12 B 29 10 02 00A 901A A 30 10 79 Airfoil de icers Apply a surface coat ing of Age Master No 1 in accordance with the manufactur ers instructions CMM 30 10 31 latest is s...

Page 168: ...00 FH 12 Months 12 B 30 60 00 00A 313A A or 12 B 30 60 00 00A 313B A 30 60 159 Propeller de ice sys tem Operational test 600 FH 12 Months 12 B 30 60 00 00A 903A A or 12 B 30 60 00 00A 903B A or 12 B 30 60 00 00A 903C A or 12 B 30 60 00 00A 903D A 31 30 421 LDR if installed Operational test 1 200 FH 12 Months 12 B 31 30 01 00A 903A A 32 10 80 Main and nose wheel bearings Lubricate Tire change or 12...

Page 169: ...r 12 B 32 10 00 00A 310B A 32 10 438 Main landing gear leg forward attachment bolt and bush and rear attachment bolt and nut Examine 6 Year See Note 5 12 B 32 10 00 00A 310A A or 12 B 32 10 00 00A 310B A 32 10 439 Main landing gear spring pack assem bly top and bottom attachment bolts and nuts Examine 6 Year See Note 5 12 B 32 10 00 00A 310B A 32 10 440 Main landing gear folding strut top and bott...

Page 170: ... 500 60 12 029 Threshold 25 000 FH 30 000 LDG Repeat 8 300 FH 10 000 LDG 6 Year 32 20 416 NLG upper right hand drag link Life limit 25 000 FH 30 000 LDG 32 30 170 Extension and retrac tion system Hydraul ic landing gear Functional test of ex tension and retraction system and emergen cy extension system 1 200 FH 12 Months 12 B 32 30 00 00A 903A A 32 30 417 MLG hydraulic actua tor Life limit 25 000 ...

Page 171: ...t tachment bolts P N 532 10 12 218 iden tified with 218 and VLG on bolt head Life limit 60 Months See Note 6 32 40 171 Main wheels Examine Rotate wheels make sure bearing movement is smooth and free and no excessive play ex ists 600 FH 12 Months 32 40 172 Main wheel tires Examine and check tire pressure 300 FH 12 Months 12 B 12 10 04 00A 902A A 32 40 173 Nose wheel Examine Rotate wheel make sure b...

Page 172: ... 184 Cockpit instruments and avionic equip ment Examine 300 FH 12 Months 34 11 82 Pitot and static sys tem Leak check 24 Months 12 B 34 11 00 00A 903A A 34 11 185 Pitot tube Examine 300 FH 12 Months 34 11 186 Static ports Examine 300 FH 12 Months 34 11 268 Pitot and static sys tem Drain 1 200 FH 12 Months 12 B 34 11 00 00A 901A A 34 11 343 Static ports plate height RVSM air craft Inspection check ...

Page 173: ... Third Party Docu ments Zodiac 35 10 187 High pressure relief indicator green disk Make sure that it is not damaged 300 FH 12 Months 35 10 188 Oxygen system Check contents 300 FH 35 10 269 Oxygen pipelines and equipment Examine 1 200 FH 12 Months 35 10 458 Crew oxygen system Operational test 1 200 FH 12 Months 12 B 35 00 00 00A 903A A 12 B 35 00 00 00A 903B A 35 20 87 Passenger oxygen masks Inspec...

Page 174: ...s Mild Corrosive Envi ronment 6000 FH or 72 Months Moderate Corrosive Environment 4000 FH or 48 Months Severe Corrosive En vironment 2000 FH or 24 Months Note Local conditions may be more or less se vere Based on field experience the inter val can be adjusted to more or less fre quent until an effec tive interval can be set 12 B 25 21 03 00A 920A A or 12 B 25 22 03 00A 920A A and 12 B 52 10 00 00A...

Page 175: ...6 Passenger crew door skin Eddy current inspec tion Threshold 25 000 FH 30 000 LDG Repeat 12 500 FH 15 000 LDG 6 Year 12 B 52 10 01 00A 353A A 52 10 472 Passenger crew door shoot bolt fitting only if SB 52 007 Part C is done Eddy current inspec tion 3 000 FH 3 600 LDG 12 B 52 10 06 00A 353A A 52 20 272 Emergency door Examine door re moved 1 200 FH 12 Months 52 20 273 Emergency door seal Clean with...

Page 176: ... examine and apply french chalk P09 002 600 FH 12 Months 52 30 194 Cargo door shoot bolts door frame fit tings and hooks Examine Make sure the hook roller bush es are free to rotate For roller bush wear limits refer to AMM 600 FH 12 Months 12 B 52 30 00 00A 313A A 52 30 195 Cargo door hinges Examine and lubri cate as necessary with minimum quanti ty of CPC P10 001 600 FH 12 Months 52 30 274 Cargo ...

Page 177: ...1 53 00 90 Front pressure bulk head Examine with insu lation on engine and cockpit sides re moved If insulation on cockpit side is wet remove dry and reinstall insulation Mild Corrosive Envi ronment 6000 FH or 72 Months Moderate Corrosive Environment 4000 FH or 48 Months Severe Corrosive En vironment 2000 FH or 24 Months Note Local conditions may be more or less se vere Based on field experience t...

Page 178: ...ent 2000 FH or 24 Months Note Local conditions may be more or less se vere Based on field experience the inter val can be adjusted to more or less fre quent until an effec tive interval can be set 53 00 92 Rear pressure bulk head Examine with trim re moved Mild Corrosive Envi ronment 6000 FH or 72 Months Moderate Corrosive Environment 4000 FH or 48 Months Severe Corrosive En vironment 2000 FH or 2...

Page 179: ...rames and is wet remove and discard it no longer installed on production Mild Corrosive Envi ronment 6000 FH or 72 Months Moderate Corrosive Environment 4000 FH or 48 Months Severe Corrosive En vironment 2000 FH or 24 Months Note Local conditions may be more or less se vere Based on field experience the inter val can be adjusted to more or less fre quent until an effec tive interval can be set 53 ...

Page 180: ... 337 Carry through Frames 21 and 24 Inspection check 1 200 FH 12 Months 12 B 53 20 02 00A 313A A 53 00 351 Upper longerons Frame 10 Eddy current inspec tion Inspection kit longer on frame 10 P N 500 60 12 032 Threshold 32 500 FH 42 000 LDG Repeat 12 500 FH 15 000 LDG 12 B 53 10 06 01A 353A A 53 00 352 Fuselage Frames 10 to 16 Examine all structural elements Threshold 32 500 FH 42 000 LDG Repeat 12...

Page 181: ...side frame attach ments Eddy current inspec tion Inspection kit carry through frames P N 500 50 12 327 Threshold 30 000 FH 39 000 LDG Repeat 10 000 FH 12 000 LDG 12 B 53 20 02 00A 353A A 53 00 361 Frames 41 and 43 stabilizer attachment Eddy current inspec tion Inspection kit verti cal stabilizer P N 500 50 12 325 Threshold 32 500 FH 42 000 LDG Repeat 12 500 FH 15 000 LDG 12 B 53 30 02 00A 353A A o...

Page 182: ... interval can be set 55 10 96 Vertical stabilizer in ternal surfaces Examine as far as possible with panels removed Mild Corrosive Envi ronment 6000 FH or 72 Months Moderate Corrosive Environment 4000 FH or 48 Months Severe Corrosive En vironment 2000 FH or 24 Months Note Local conditions may be more or less se vere Based on field experience the inter val can be adjusted to more or less fre quent ...

Page 183: ...r to SRM for repair procedure 300 FH 12 Months 12 B 55 00 01 00A 664A A 55 30 281 Vertical stabilizer electrical bonding straps Examine 1 200 FH 12 Months 55 30 369 Vertical stabilizer Examine Threshold 32 500 FH 42 000 LDG Repeat 12 500 FH 15 000 LDG 6 Year 12 B 55 30 00 00A 310A A 55 30 370 Vertical stabilizer main and rear spar attachment to fuse lage Eddy current inspec tion Threshold 32 500 F...

Page 184: ...00A 353A A 55 40 410 Rudder trim tab Examine Threshold 32 500 FH 42 000 LDG Repeat 12 500 FH 15 000 LDG 6 Year 12 B 55 40 04 00A 310A A 56 11 12 Cockpit outer side DV windows and cab in windows Replace If cracked 56 11 13 Cockpit inner and outer side DV win dows and cabin win dows Refer to AMM for lim itations If chipped cracked only for inner side windows crazing scratched bubbles or delaminated ...

Page 185: ... with one hand 1 200 FH 12 Months 56 20 201 Cockpit and cabin windows Examine 300 FH 12 Months 12 B 56 00 00 00A 313A A 57 00 11 Wing structure Pre SB 04 009 Life limit 20 000 FH 27 000 LDG See Note 1 57 00 97 Wing internal surfa ces and flap compart ment Examine as far as possible with all wing panels removed Mild Corrosive Envi ronment 6000 FH or 72 Months Moderate Corrosive Environment 4000 FH ...

Page 186: ... moved 11 000 FH 120 Months 12 B 57 00 00 00A 313A A 57 00 202 Wing external surfa ces Examine 300 FH 12 Months 57 00 282 Wing tip static dis chargers Examine 2 400 FH 24 Months 57 00 283 Wing internal surfa ces and flap compart ment Examine as far as possible with panels in Task 06 00 218 opened removed 1 200 FH 12 Months 57 00 284 Wing to fuselage at tachments Examine as far as possible 1 200 FH...

Page 187: ... Rib 1 thru Rib 6 Eddy current inspec tion Inspection kit first oversize P N 500 60 12 030 or Inspection kit sec ond oversize P N 500 60 12 020 Threshold 25 000 FH 30 000 LDG Repeat 3 300 FH 4 000 LDG 12 B 57 20 10 00A 353A A 57 00 385 Wing rear spar fas tener holes Rib 2 thru Rib 3 Eddy current inspec tion Threshold 25 000 FH 30 000 LDG Repeat 12 500 FH 15 000 LDG 12 B 57 20 10 00A 353B A 57 00 4...

Page 188: ...reshold 32 500 FH 42 000 LDG Repeat 12 500 FH 15 000 LDG 6 Year 12 B 57 60 04 00A 310A A 61 00 456 Four bladed alumi num propeller Refer to Hartzell Owner s Manual 149 Periodic Inspections and Maintenance and do the time limited in spection items Refer to Hartzell Owner s Manual 149 Periodic Inspections and Maintenance 61 00 457 Five bladed compo site propeller Refer to the Hartzell Owner s Manual...

Page 189: ... plant Post inspection ground run tests Job Close Up 12 B 71 00 00 00A 903A A 71 00 205 Engine tubular mounting frame and shockmounts Examine Replace shockmount if cracks in elastomer are more than 25 4 mm 1 in long and or 1 5 mm 0 06 in deep 1 200 FH 12 Months 71 00 209 Engine drain mast and tank Examine the drain mast for fuel leaks no leaks permitted and drain the collec tor tank 300 FH 12 Mont...

Page 190: ...ited inspec tion items Refer to P WC EMM Chapter 72 00 00 Pe riodic Inspection 71 00 476 P WC airworthiness directives and service bulletins Reviewed and com plied with as neces sary Job Close Up 71 10 207 Engine cowlings ENG 43AL and ENG 43AR Open and examine particularly for condi tion of rubbing strips and fasteners Lubri cate the hinges with a minimum of material P10 001 Job Set Up 71 10 208 E...

Page 191: ...erational test Note Make sure the MOR is stowed correctly 1 200 FH 12 Months 12 B 76 10 00 00A 903A A 12 B 76 20 00 00A 903A A 76 00 304 Cockpit control quad rant Examine 300 FH 12 Months 76 10 117 Propeller feathering microswitches Functional test 3 000 FH 12 Months 12 B 76 10 02 00A 903A A 78 00 214 Exhaust stubs Examine 300 FH 12 Months 79 00 422 Oil filler cap dipstick Operational test 600 FH ...

Page 192: ...RODUC TION 12 B 22 20 00 00A 903A A SPEED AND ATTITUDE CORRECTION ADJUST MENT TEST 12 B 24 30 01 00A 313A A STARTER GENERATOR INSPECTION CHECK 12 B 27 40 00 00A 903A A HORIZONTAL STABILIZER TRIM ADJUSTMENT TEST 12 B 76 10 00 00A 903A A POWER CONTROLS ADJUSTMENT TEST Description 1 General The terms used for the item inspection requirements are defined in 12 B 05 20 00 00A 018A A PC 12 47E AMM Doc N...

Page 193: ...23 437 Brush Check 12 B 24 30 01 00A 313A A 25 10 135 Crew seats Examine as far as possible with seats installed 25 20 302 Passenger seats Examine as far as possible with seats installed Move the recline mechanism and swivel function executive seat only through its full motion and check for cor rect operation If necessary re fer to the applica ble supplier CMM CMM 25 20 07 for executive seats and ...

Page 194: ... max and make sure movement is full and free Condition lever Do the operation al test refer to AMM Manual override lever move be tween off and max and make sure movement is full and free Note Make sure the MOR is stored correctly 12 B 76 10 00 00A 903A A PC 12 47E AMM Doc No 02300 ISSUE 01 REVISION 26 MSN 545 1001 1719 1721 1999 12 B AM 00 00 00 I UNCLASSIFIED Effectivity All 12 B 05 40 01 01A 000...

Page 195: ...C 12 47E AMM Doc No 02300 ISSUE 01 REVISION 26 MSN 545 1001 1719 1721 1999 12 B AM 00 00 00 I UNCLASSIFIED Intentionally left blank Effectivity All 12 B 05 40 01 01A 000B A UNCLASSIFIED 2021 12 04 Page 4 ...

Page 196: ...25 63 00 00A 903B A KANNAD INTEGRA ELT ADJUSTMENT TEST 12 B 27 40 00 00A 903A A HORIZONTAL STABILIZER TRIM ADJUSTMENT TEST 12 B 27 50 00 00A 902A A FLAPS SERVICING 12 B 28 20 01 00A 250A A FUEL FILTER ELEMENT CLEAN 12 B 28 20 01 00A 920A A FUEL FILTER ELEMENT REMOVAL INSTALLATION 12 B 28 20 07 00A 903A A FLOAT VALVE ADJUSTMENT TEST 12 B 29 00 00 00A 902A A HYDRAULIC SYSTEM SERVICING 12 B 30 10 00 ...

Page 197: ...Description Data Module Reference Signature Stamp Inspection 06 00 594 Access panels fuselage 11BL 21PZ Remove and ex amine 12 B 06 20 00 00A 040A A 06 00 595 Access panels fuselage 11BL 21PZ Install 12 B 06 20 00 00A 040A A 06 00 596 Access panels empennage 31AB 32AB 33ET Open or remove Examine 12 B 06 20 00 00A 040A A 06 00 597 Access panels empennage 31AB 32AB 33ET Close or install 12 B 06 20 0...

Page 198: ...im hinges with mini mum quantity of CPC P10 001 27 20 140 Rudder Inspection check 12 B 55 40 00 00A 313A A 27 30 141 Elevators Examine 27 40 142 Horizontal stabil izer trim interrupt and alternate trim switches Operational test 12 B 27 40 00 00A 903A A 27 50 144 Flaps and flap support mecha nism Examine 27 50 443 Flap up and down limit switches Servicing 12 B 12 20 07 00A 902A A 27 50 576 Flap act...

Page 199: ...ori zontal stabilizer airfoil de ice boots Inspection check 12 B 30 10 00 00A 313A A 30 20 156 Engine air intake de ice lip Examine and look for signs of gas leaks none are permitted 32 40 172 Main wheel tires Examine and check tire pres sure 12 B 12 10 04 00A 902A A 32 40 174 Nose wheel tire Examine and check tire pres sure 12 B 12 10 04 00A 902A A 32 40 175 Brake system Apply the parking brake E...

Page 200: ...A 903A A 46 26 321 ADAHRS sensor source select switches Operational test 12 B 46 30 02 00A 903A A 53 00 196 Fuselage external surface Examine For air craft that experi ence stone dam age to the bel ly skin visually examine affected areas for cracks 55 10 197 Horizontal stabil izer external sur face Examine 55 30 198 Vertical stabilizer external surface Examine special ly around rear spar top rivet...

Page 201: ...stem Operational test 12 B 74 00 00 00A 903A A 76 00 211 Beta slip ring car bon block Make sure gap is not more than 0 25 mm 0 01 in 76 00 304 Cockpit control quadrant Examine 78 00 214 Exhaust stubs Examine 79 20 290 Oil system chip detector indica tion system Operational test 12 B 79 30 01 00A 903A A PC 12 47E AMM Doc No 02300 ISSUE 01 REVISION 26 MSN 545 1001 1719 1721 1999 12 B AM 00 00 00 I U...

Page 202: ...ERATION PACK SERVICING 12 B 24 30 01 00A 313A A STARTER GENERATOR INSPECTION CHECK Description 1 General The terms used for the item inspection requirements are defined in 12 B 05 20 00 00A 018A A 2 Inspections Table 2 600 FH Inspection Task number Item Name Task Description Data Module Reference Signature Stamp Inspection 06 00 602 Access panels engine 42AT 42AB Remove and ex amine 12 B 06 20 00 ...

Page 203: ...changer matrix Inspection check 12 B 21 40 02 00A 313A A 24 30 473 Generator 1 P N 978 91 23 407 Brush check 12 B 24 30 01 00A 313A A 24 30 474 Starter Generator 2 P N 978 91 23 407 Brush check 12 B 24 30 01 00A 313A A PC 12 47E AMM Doc No 02300 ISSUE 01 REVISION 26 MSN 545 1001 1719 1721 1999 12 B AM 00 00 00 I UNCLASSIFIED Effectivity All 12 B 05 40 01 03A 000B A End of data module UNCLASSIFIED ...

Page 204: ... 313A A FOUR BLADED PROPELLER DE ICE SYSTEM INSPEC TION CHECK 12 B 30 60 00 00A 313B A FIVE BLADED PROPELLER DE ICE SYSTEM INSPEC TION CHECK 12 B 30 60 00 00A 903A A FOUR BLADED PROPELLER DE ICE SYSTEM WITHOUT PROPELLER DE ICE TEST SET ADJUSTMENT TEST 12 B 30 60 00 00A 903B A FIVE BLADED PROPELLER DE ICE SYSTEM WITHOUT PROPELLER DE ICE TEST SET ADJUSTMENT TEST 12 B 30 60 00 00A 903C A FOUR BLADED ...

Page 205: ... Description Data Module Reference Signature Stamp Inspection 06 00 582 Access panels engine 41AT 42AB 42AT Remove and ex amine 12 B 06 20 00 00A 040A A 06 00 583 Access panels engine 41AT 42AB 42AT Install 12 B 06 20 00 00A 040A A 06 00 604 Access panels fuselage 11AL 12EL 12QZ Remove and ex amine 12 B 06 20 00 00A 040A A 06 00 605 Access panels fuselage 11AL 12EL 12QZ Install 12 B 06 20 00 00A 0...

Page 206: ...separation system Operational test 12 B 30 20 00 00A 903A A 30 30 329 Probes de ice system Functional test 12 B 30 30 20 00A 903A A 30 60 158 Propeller de ice system Inspection check 12 B 30 60 00 00A 313A A or 12 B 30 60 00 00A 313B A 30 60 159 Propeller de ice system Operational test 12 B 30 60 00 00A 903A A or 12 B 30 60 00 00A 903B A or 12 B 30 60 00 00A 903C A or 12 B 30 60 00 00A 903D A 32 1...

Page 207: ...ne 32 30 425 Electro mechani cal extension and retraction mecha nism Examine all com ponents and their attachments in the nose and main landing gear compartments 32 40 171 Main wheels Examine Rotate wheels make sure bearing movement is smooth and free and no excessive play exists 32 40 173 Nose wheel Examine Rotate wheel make sure bearing movement is smooth and free and no excessive play exists 52...

Page 208: ...k roll er bushes are free to rotate For roller bush wear limits refer to AMM 12 B 52 30 00 00A 313A A 52 30 195 Cargo door hing es Examine and lu bricate as nec essary with mini mum quantity of CPC P10 001 71 00 101 Power plant tor que limiter Operational test 12 B 71 00 00 00A 903G A 71 00 102 Power plant per formance Operational test 12 B 71 00 00 00A 903H A 71 00 107 Engine torque and stick pus...

Page 209: ...C 12 47E AMM Doc No 02300 ISSUE 01 REVISION 26 MSN 545 1001 1719 1721 1999 12 B AM 00 00 00 I UNCLASSIFIED Intentionally left blank Effectivity All 12 B 05 40 01 04A 000B A UNCLASSIFIED 2021 12 04 Page 6 ...

Page 210: ...ENT TEST 12 B 21 40 01 00A 903B A UNDERFLOOR HEATER MSN 1081 AND UP ADJUST MENT TEST 12 B 21 40 03 00A 250A A WATER SEPARATOR CLEAN 12 B 21 43 00 00A 903A A FOOTWARMER ADJUSTMENT TEST 12 B 22 10 00 00A 313A A AUTOPILOT INSPECTION CHECK 12 B 22 20 00 00A 903A A SPEED AND ATTITUDE CORRECTION ADJUST MENT TEST 12 B 25 10 01 00A 920A A FLIGHT COMPARTMENT CREW SEATS REMOVAL IN STALLATION 12 B 27 10 00 0...

Page 211: ... MAINTENANCE PRACTICES 12 B 35 00 00 00A 903A A OXYGEN PLUG IN MASK SYSTEM ADJUSTMENT TEST 12 B 45 45 00 00A 551A A CENTRAL MAINTENANCE SYSTEM INTERFACE FAULT MONITORING STORAGE READOUT DOWNLOAD DATA 12 B 52 70 00 00A 903A A DOOR WARNING ADJUSTMENT TEST 12 B 53 20 02 00A 313A A CENTER FUSELAGE CARRY THROUGH FRAMES IN SPECTION CHECK 12 B 54 20 02 00A 664A A ENGINE FRAME DAMAGED PAINT AND CORROSION ...

Page 212: ...2MB 52NB 52OB 52PB 52RB 52TB 52SB 61KB 61MB 61NB 62KB 62MB 62NB 62OB 62PB 62RB 62SB 62TB Install 12 B 06 20 00 00A 040A A 06 00 608 Access panels fuselage 11AL 11AR 11BR 11BL 11BZ 11DZ 12AL 12AR 12AB 12AZ 12BL 12BR 12BZ 12CZ 12DZ 12EL 12EZ 12FZ 12GZ 12HZ 12IZ 12JZ 12KZ 12LZ 12MZ 21GZ 21HZ 21JZ 21QZ 22PZ 22TZ 22UZ Open or remove Examine and make sure the ac cess panel drain holes are clear 12 B 06 ...

Page 213: ...T 33DT 33ET 34DT Open or remove Examine 12 B 06 20 00 00A 040A A 06 00 611 Access panels empennage 31AB 31AL 31AR 32AB 32BL 32BR 32AL 32CL 32CT 32DL 32DR 32BT 33DT 33ET 34DT Close or install 12 B 06 20 00 00A 040A A 06 00 612 Access panels engine 42AT 42AB Remove and ex amine 12 B 06 20 00 00A 040A A 06 00 613 Access panels engine 42AT 42AB Install 12 B 06 20 00 00A 040A A 11 00 220 Placards and m...

Page 214: ...al test 12 B 21 40 01 00A 903A A 12 B 21 40 01 00A 903B A 21 50 223 Vapor cycle cool ing system if in stalled Examine the cool ing unit 22 10 60 Servo mount pitch roll and yaw Remove for clutch check 12 B 22 10 00 00A 313A A 22 20 226 Stick pusher sys tem Functional test 12 B 22 20 00 00A 903A A 24 30 313 DC electrical sys tem Functional test 12 B 71 00 00 00A 903D A 25 10 300 Crew seats Remove cu...

Page 215: ... around the aileron push rod guide roller sleeves at all three locations in each wing 27 10 235 Aileron electrical bonding straps Examine 27 10 236 Aileron control system Inspection check 12 B 27 10 00 00A 313A A 27 10 237 Aileron cable ten sion Check 12 B 27 10 00 00A 903A A 27 10 470 Aileron control system bearings Lubricate 12 B 27 10 00 00A 901A A 27 20 241 Rudder control system Inspection che...

Page 216: ...mine 27 50 255 Flaps Functional test and asymmetry monitor test 12 B 27 50 00 00A 903A A 29 10 257 Power pack If in stalled Examine special ly for leaks and cracks on the end plates and where motor is attached 12 B 29 00 00 00A 902A A 29 10 258 Nitrogen accu mulator P N 960 30 01 291 If installed Check nitrogen pressure and fill as necessary 12 B 29 10 02 00A 901A A 29 10 259 Power pack elec tric ...

Page 217: ...lines and equipment Examine 35 10 458 Crew oxygen sys tem Operational test 12 B 35 00 00 00A 903A A 12 B 35 00 00 00A 903B A 45 45 454 Central mainte nance system Do a CMC RE PORTS EX PORT FAULT HISTORY SEND TO LO CAL STORAGE download 12 B 45 45 00 00A 551A A 52 10 271 Passenger crew door counterbal ance and cable support brackets Examine 52 20 272 Emergency door Examine door re moved 52 20 273 Em...

Page 218: ... 00 00A 313A A 55 30 281 Vertical stabilizer electrical bonding straps Examine 56 11 517 Cockpit DV Win dow Make sure that you can open and close the DV window with one hand 57 00 283 Wing internal sur faces and flap compartment Examine as far as possible with pan els in Task 06 00 218 opened removed 57 00 284 Wing to fuselage attachments Examine as far as possible 61 20 286 Propeller gover nor ov...

Page 219: ...n the mounting frame refer to SRM SRM 12 B 54 20 02 00A 664A A 76 00 303 Cockpit control quadrant Power control Operational test Manual override Operational test Note Make sure the MOR is stowed correctly 12 B 76 10 00 00A 903A A 12 B 76 20 00 00A 903A A 79 20 289 Engine oil cooler Examine Make sure outlet door has full and free movement PC 12 47E AMM Doc No 02300 ISSUE 01 REVISION 26 MSN 545 1001...

Page 220: ... 40 00 00A 903A A EXTERNAL POWER VOLTAGE DISCONNECTION ADJUST MENT TEST 12 B 27 10 00 00A 903A A AILERON CONTROL SYSTEM ADJUSTMENT TEST 12 B 27 15 00 00A 903A A AILERON TRIM ADJUSTMENT TEST 12 B 27 20 00 00A 903A A RUDDER CONTROL SYSTEM ADJUSTMENT TEST 12 B 27 25 00 00A 903A A RUDDER TRIM ADJUSTMENT TEST 12 B 27 30 00 00A 903A A ELEVATOR CONTROL SYSTEM ADJUSTMENT TEST 12 B 29 10 02 00A 901A A ACCU...

Page 221: ...00 00A 040A A 06 00 617 Access panels empennage 31AB 32AB 32BB 32CT 33ET Install 12 B 06 20 00 00A 040A A 06 00 618 Access panels engine 42AT 42AB Remove and ex amine 12 B 06 20 00 00A 040A A 06 00 619 Access panels engine 42AT 42AB Install 12 B 06 20 00 00A 040A A 06 00 620 Access panels wing 51AB 51BB 61AB 61BB Remove and ex amine 12 B 06 20 00 00A 040A A 06 00 621 Access panels wing 51AB 51BB 6...

Page 222: ...ction operational test 12 B 24 40 00 00A 903A A 24 40 229 External Power Unit EPU recep tacle Examine 24 60 133 Cockpit circuit breaker panels and switch panels Examine 27 10 238 Ailerons Functional test 12 B 27 10 00 00A 903A A 27 15 239 Aileron trim Functional test 12 B 27 15 00 00A 903A A 27 20 240 Rudder static dis chargers Examine 27 20 244 Rudder Functional test 12 B 27 20 00 00A 903A A 27 2...

Page 223: ... de ice system Operational test 12 B 30 40 00 00A 903A A 34 00 183 Communications and navigation antennas Examine 53 00 278 Baggage freight net mounting plates attachment bolts and sur rounding struc ture Examine for cor rosion 53 00 279 Baggage com partment Examine 57 00 282 Wing tip static dischargers Examine PC 12 47E AMM Doc No 02300 ISSUE 01 REVISION 26 MSN 545 1001 1719 1721 1999 12 B AM 00 ...

Page 224: ...12 B 05 50 01 00A 282A A HARD LANDING UNSCHEDULED INSPECTIONS 12 B 05 50 01 00A 282B A HARD LANDING ELECTRO MECHANICAL LANDING GEAR UNSCHEDULED INSPECTION 12 B 05 50 02 00A 282A A FLIGHT IN SEVERE TURBULENCE OR SEVERE MANEU VRES UNSCHEDULED INSPECTIONS 12 B 05 50 03 00A 282A A OVERSPEED WITH FLAPS EXTENDED UNSCHEDULED INSPECTIONS 12 B 05 50 04 00A 282A A PROPELLER SUDDEN STOPAGE OR IMPACT UNSCHED ...

Page 225: ...re the next flight following the incident 2 Unscheduled Checks Airframe Unscheduled checks must be done after the following incidents occur or permitted deviations are exceeded Refer to Table 2 for the airframe exceedance checks that are needed Check AMM Reference Hard landing 12 B 05 50 01 00A 282A A or 12 B 05 50 01 00A 282B A Flight in severe turbulence or after severe maneuvers 12 B 05 50 02 0...

Page 226: ...10 00A 282A A 252 Contact Pilatus OVER G Positive upward load factor nz g 2 9 Build 7 2 4 Build 6 R 1 00 None R 1 15 12 B 05 50 02 00A 282A A R 1 15 Contact Pilatus Negative down ward load factor nz g 2 9 Build 7 2 36 Build 6 R 1 00 None R 1 15 12 B 05 50 02 00A 282A A R 1 15 Contact Pilatus Lateral load fac tor ny g 0 8 Build 7 1 0 Build 6 0 8 None 1 0 No weight on wheels 12 B 05 50 02 00A 282A A...

Page 227: ...efer to Fig 1 Obtain the aircraft gross weight and fuel weight at the time of the exceedance Interrogate the Aircraft data txt log file to determine the peak load factor refer to AMM 12 B 45 45 00 00A 551A A This load factor is designated g actual Note The ADAHRS log files record g where 0g implies straight and level flight Therefore you must use a correction of 1 0g for all recorded g values Dete...

Page 228: ...ght and fuel loading at the time of the exceedence This load factor is designated g allowable Determine the ratio R by dividing g actual by g allowable Refer to Table 2 for the exceedance range and the required maintenance action PC 12 47E AMM Doc No 02300 ISSUE 01 REVISION 26 MSN 545 1001 1719 1721 1999 12 B AM 00 00 00 I UNCLASSIFIED Effectivity All 12 B 05 50 00 00A 018A A UNCLASSIFIED 2021 12 ...

Page 229: ...CTOR GIVEN FUEL QUANTITY GROSS WEIGHT 1200kg 1222kg Fuel total 0kg 399kg Fuel total 400kg 599kg Fuel total 600kg 1199kg Fuel total Notes 3 For this chart 0 0g means straight and level flight 1 ADAHRS recorded g must be within this envelope 2 Ensure MTOW 4740kg and MZFW 4100kg are not exceeded Figure 1 Refinement Chart Positive Load Factor PC 12 47E AMM Doc No 02300 ISSUE 01 REVISION 26 MSN 545 100...

Page 230: ...ADAHRS g ALLOWABLE NEGATIVE LOAD FACTOR GIVEN FUEL QUANTITY GROSS WEIGHT Notes 1 ADAHRS recorded g must be within this envelope 2 Ensure MTOW 4740kg and MZFW 4100kg are not exceeded 3 For this chart 0 0g means straight and level flight 0kg 1222kg Fuel total Figure 2 Refinement Chart Negative Load Factor PC 12 47E AMM Doc No 02300 ISSUE 01 REVISION 26 MSN 545 1001 1719 1721 1999 12 B AM 00 00 00 I ...

Page 231: ...rt 870 0 Start 870 5 Start 1000 0 Torque 44 34 20 EMM 71 00 00 Fig 503 Prop Owners Manual 61 00 49 Fig 5 4 61 0 Ng 104 0 EMM 72 00 00 Para C1 Np 1730 to 1870 20 EMM 72 00 00 Section 12 Para C1 Prop Owners Manual 61 00 49 Fig 5 3 1870 0 Ground 350 to 900 25 Prop Owners Manual 61 00 49 Fig 5 6 Oil pressure Ng 72 60 to 90 20 EMM 72 00 00 Section 12 Para R 40 to 60 20 40 0 135 to 200 20 200 0 Oil temp...

Page 232: ...901A A JACKING MAINTENANCE PRACTICES 12 B 27 20 00 00A 903A A RUDDER CONTROL SYSTEM ADJUSTMENT TEST 12 B 27 30 00 00A 903A A ELEVATOR CONTROL SYSTEM ADJUSTMENT TEST 12 B 27 40 00 00A 903A A HORIZONTAL STABILIZER TRIM ADJUSTMENT TEST 12 B 51 00 00 00A 353A A STRUCTURES STANDARD PRACTICES EDDY CUR RENT INSPECTION 12 B 51 10 00 00A 041A A INVESTIGATION CLEAN UP AND AERODYNAMIC SMOOTHNESS DESCRIPTION ...

Page 233: ...p circuit breaker hold open Part T12 030 AR Warning sign DO NOT OPER ATE THE FLIGHT CONTROLS Part Local supply AR Supplies Table 4 Supplies Name Identifications References Qty Reference Remark None Spares Table 5 Spares Name Identifications References Qty Reference Remark Bearing CSN 55 40 00 02 115 1 Bolt CSN 55 40 00 01 050 1 Bolt CSN 55 40 00 01 070 1 Bolt CSN 55 30 00 01 140 1 Cotter pin CSN 5...

Page 234: ... 041A A Even if there is no damage do the functional test of the rudder control system refer to AMM 12 B 27 20 00 00A 903A A 2 During the Inspection Procedure If you find damage during this procedure you must contact Pilatus Aircraft Ltd 3 Preparation 3 1 Lift the aircraft on jacks refer to AMM 12 B 07 10 00 00A 901A A 3 2 Make sure the flaps are set to 0 3 3 Open and install a Safety clip circuit...

Page 235: ...nspection to confirm the result Note If composite material has minor damage such as cracks scratches surface delamination and or abrasion use the standard repair procedures given in SRM 12 B 51 70 04 00A 663A A 5 1 Examine the cable quadrant and bearing housing for cracks NDT deformation and or distortion 5 2 Examine the rudder stop fitting assembly Figure 3 1 for cracks NDT or any damage 5 3 Exam...

Page 236: ...t Figure 2 6 and a new Cotter pin Figure 2 7 6 7 Attach the rudder cables Figure 2 9 to the cable quadrant Figure 2 3 and secure each rudder cable with a new Cotter pin Figure 2 8 6 8 Install the rudder refer to AMM 12 B 55 40 01 00A 920A A After installation of the rudder do an adjustment and test of the rudder control system refer to AMM 12 B 27 20 00 00A 903A A Note If a new rudder is installed...

Page 237: ... A 1 2 1 1 2 1 Figure 1 Rudder Control Cables Adjustment PC 12 47E AMM Doc No 02300 ISSUE 01 REVISION 26 MSN 545 1001 1719 1721 1999 12 B AM 00 00 00 I UNCLASSIFIED Effectivity All 12 B 05 50 11 00A 282A A UNCLASSIFIED 2021 12 04 Page 6 ...

Page 238: ...B D 8 9 3 7 6 1 2 4 5 Figure 2 Cable Quadrant Removal Installation PC 12 47E AMM Doc No 02300 ISSUE 01 REVISION 26 MSN 545 1001 1719 1721 1999 12 B AM 00 00 00 I UNCLASSIFIED Effectivity All 12 B 05 50 11 00A 282A A UNCLASSIFIED 2021 12 04 Page 7 ...

Page 239: ...12 5 8 9 13 4 2 1 3 3 14 Figure 3 Rudder Hinge Fittings Removal Installation PC 12 47E AMM Doc No 02300 ISSUE 01 REVISION 26 MSN 545 1001 1719 1721 1999 12 B AM 00 00 00 I UNCLASSIFIED Effectivity All 12 B 05 50 11 00A 282A A UNCLASSIFIED 2021 12 04 Page 8 ...

Page 240: ...B 1 2 3 B Figure 4 Vertical Stabilizer Attachment and Spars PC 12 47E AMM Doc No 02300 ISSUE 01 REVISION 26 MSN 545 1001 1719 1721 1999 12 B AM 00 00 00 I UNCLASSIFIED Effectivity All 12 B 05 50 11 00A 282A A UNCLASSIFIED 2021 12 04 Page 9 ...

Page 241: ...ed Conditions Action Condition Data module Technical publication None PC 12 47E AMM Doc No 02300 ISSUE 01 REVISION 26 MSN 545 1001 1719 1721 1999 12 B AM 00 00 00 I UNCLASSIFIED Effectivity All 12 B 05 50 11 00A 282A A End of data module UNCLASSIFIED 2021 12 04 Page 10 ...

Page 242: ...a module Technical publication Title 12 B 00 00 00 00A 060A A GENERAL LIST OF AEROSPACE GROUND EQUIPMENT AGE AND TOOLS 12 B 09 10 00 00A 901A A TOWING MAINTENANCE PRACTICES 12 B 10 10 01 00A 901A A STORING MAINTENANCE PRACTICES 12 B 10 20 00 00A 901A A MOORING MAINTENANCE PRACTICES 12 B 27 70 00 00A 040A A GUST LOCK DESCRIPTION AND OPERATION Preliminary Requirements Required Conditions Table 2 Req...

Page 243: ...ver oil cooler intake LH Part 990 00 00 892 1 Cover oil cooler intake RH Part 990 00 00 893 1 Cover ECS intake Part 990 00 00 894 1 Cover generator intake Part 990 00 00 895 1 Cover assembly air intakes CSN 10 10 00 01 080 1 Also used as an alternative to P N 990 00 00 892 P N 990 00 00 893 P N 990 00 00 894 and P N 990 00 00 895 Cover engine exhaust Part 510 10 12 046 1 Cover assembly exhaust LH ...

Page 244: ...k pin emergency exit CSN 10 10 00 01 010 1 Also used as an alternative to P N 940 26 81 205 Hand towbar Tail stand CSN 09 10 00 01 020 1 Safety Conditions CAUTION IF THE AIRCRAFT IS PARKED FOR A LONG PERIOD OF TIME WITH TEMPERATURES BELOW 0 C 32 F APPLY APPROXIMATELY 59 CC 2 OUNCES OF ISOPROPYL ALCOHOL TO THE OUTER DIAMETER OF THE BRAKE ASSEMBLY WITH A SPRAY BOTTLE APPLY THE ALCOHOL WHEN THE BRAKE...

Page 245: ...s Pt No T10 010 at the front and the rear of the nose wheel and each main wheel 2 4 If the aircraft is parked outside and heavy snowfall is expected install the Hand towbar Tail stand Figure 1 11 Figure 2 9 to support the rear fuselage Note The towbar tail stand is stowed in the rear fuselage of the aircraft 2 5 Ground the aircraft 2 6 Close the DV window the passenger crew door and the cargo door...

Page 246: ...ver assembly pitot tube Figure 2 8 Cover assembly propeller Figure 2 3 Install the Lock pin emergency exit Figure 2 6 in the inner handle of the emergency exit Figure 2 5 2 10 Engage the flying controls gust lock in the flight compartment refer to AMM 12 B 27 70 00 00A 040A A 2 11 Lock the passenger crew and cargo doors 2 12 Lock the service door 31AB PC 12 47E AMM Doc No 02300 ISSUE 01 REVISION 2...

Page 247: ...0033 A 02 1 IF INSTALLED M Figure 1 Parking Original Cover Set Maintenance Practices PC 12 47E AMM Doc No 02300 ISSUE 01 REVISION 26 MSN 545 1001 1719 1721 1999 12 B AM 00 00 00 I UNCLASSIFIED Effectivity All 12 B 10 10 00 00A 901A A UNCLASSIFIED 2021 12 04 Page 6 ...

Page 248: ...000 A S4080 00034 A 02 1 J M 11 Figure 1 Parking Original Cover Set Maintenance Practices PC 12 47E AMM Doc No 02300 ISSUE 01 REVISION 26 MSN 545 1001 1719 1721 1999 12 B AM 00 00 00 I UNCLASSIFIED Effectivity All 12 B 10 10 00 00A 901A A UNCLASSIFIED 2021 12 04 Page 7 ...

Page 249: ...8 2 3 M INSIDE CABIN LOOKING OUTBOARD 6 H 5 G H 9 M Figure 2 Parking Alternative Cover Set Maintenance Practices PC 12 47E AMM Doc No 02300 ISSUE 01 REVISION 26 MSN 545 1001 1719 1721 1999 12 B AM 00 00 00 I UNCLASSIFIED Effectivity All 12 B 10 10 00 00A 901A A UNCLASSIFIED 2021 12 04 Page 8 ...

Page 250: ...red Conditions Action Condition Data module Technical publication None PC 12 47E AMM Doc No 02300 ISSUE 01 REVISION 26 MSN 545 1001 1719 1721 1999 12 B AM 00 00 00 I UNCLASSIFIED Effectivity All 12 B 10 10 00 00A 901A A End of data module UNCLASSIFIED 2021 12 04 Page 9 ...

Page 251: ... 12 47E AMM Doc No 02300 ISSUE 01 REVISION 26 MSN 545 1001 1719 1721 1999 12 B AM 00 00 00 I UNCLASSIFIED Intentionally left blank Effectivity All 12 B 10 10 00 00A 901A A UNCLASSIFIED 2021 12 04 Page 10 ...

Page 252: ...publication Title 12 B 00 00 00 00A 060A A GENERAL LIST OF AEROSPACE GROUND EQUIPMENT AGE AND TOOLS 12 B 09 10 00 00A 901A A TOWING MAINTENANCE PRACTICES 12 B 10 10 01 00A 901A A STORING MAINTENANCE PRACTICES 12 B 10 20 00 00A 901A A MOORING MAINTENANCE PRACTICES 12 B 27 70 00 00A 040A A GUST LOCK DESCRIPTION AND OPERATION Preliminary Requirements Required Conditions Table 2 Required Conditions Ac...

Page 253: ...0 00 01 025 2 Cover assembly propeller CSN 10 10 00 01 050 2 Lock pin emergency exit CSN 10 10 00 01 010 1 Hand towbar Tail stand CSN 09 10 00 01 020 1 Safety Conditions CAUTION IF THE AIRCRAFT IS PARKED FOR A LONG PERIOD OF TIME WITH TEMPERATURES BELOW 0 C 32 F APPLY APPROXIMATELY 59 CC 2 OUNCES OF ISOPROPYL ALCOHOL TO THE OUTER DIAMETER OF THE BRAKE ASSEMBLY WITH A SPRAY BOTTLE APPLY THE ALCOHOL...

Page 254: ...is expected install the Hand towbar Tail stand Figure 1 9 to support the rear fuselage Note The towbar tail stand is stowed in the rear fuselage of the aircraft 2 5 Ground the aircraft 2 6 Close the DV window the passenger crew door and the cargo door Note Keep the DV window open if the aircraft is parked in a hangar 2 7 Make sure that all access panels are correctly installed and closed 2 8 Insta...

Page 255: ... F E D C B A 2 3 4 L K J 7 7 8 M 6 5 H 9 M G Figure 1 Parking Aircraft With Five Bladed Propeller Maintenance Practices PC 12 47E AMM Doc No 02300 ISSUE 01 REVISION 26 MSN 545 1001 1719 1721 1999 12 B AM 00 00 00 I UNCLASSIFIED Effectivity All 12 B 10 10 00 00A 901B A UNCLASSIFIED 2021 12 04 Page 4 ...

Page 256: ...red Conditions Action Condition Data module Technical publication None PC 12 47E AMM Doc No 02300 ISSUE 01 REVISION 26 MSN 545 1001 1719 1721 1999 12 B AM 00 00 00 I UNCLASSIFIED Effectivity All 12 B 10 10 00 00A 901B A End of data module UNCLASSIFIED 2021 12 04 Page 5 ...

Page 257: ...C 12 47E AMM Doc No 02300 ISSUE 01 REVISION 26 MSN 545 1001 1719 1721 1999 12 B AM 00 00 00 I UNCLASSIFIED Intentionally left blank Effectivity All 12 B 10 10 00 00A 901B A UNCLASSIFIED 2021 12 04 Page 6 ...

Page 258: ...o Material Name Product Name Alternative Product Specification Pilatus Part No Notes P01 Processing and Cleaning P01 001 Cleaner alkaline Turco 5884 910 21 31 008 MIL PRF 85704 Almon AL 333 Ardrox 624 B B 3100 Carbitol CLIX Magnus 1214 Rivenaes R MCS Rivenaes R MC G21 Softenol PF Ri II 908 40 34 085 Used for ultrasonic cleaning Surtec 151 908 40 34 089 P01 002 Triethanolamine P01 003 Emulsifier Wi...

Page 259: ... 52 006 P01 004 MIL A 6091 AMS3002 O E 760 type III PWC011 009 P01 016 Acetone O A 51 910 21 21 001 ASTM D329 95 P01 017 Electrical contact protector Progold G5S 6 908 24 32 024 P01 018 P01 020 P01 019 Cleaning fluid Kontakt Chemie Kontakt 60 908 18 12 094 P01 020 Electrical contact enhancer 908 24 32 026 P01 018 Stabilant 22 P01 021 Corrosion remover PHOS KLENE 1 SUPER 908 40 32 155 P01 022 Corro...

Page 260: ...75 P01 032 Degreaser Sikkens M600 910 09 00 058 P01 033 Wipes presaturated solvent Dispenser for SatWipes Diestone DLS 904 49 73 012 SatWipes Diestone DLS box of 12 rolls of 60 wipes 904 49 73 013 P01 034 Paint remover Socostrip A 0103N 910 10 00 005 P01 023 P01 035 Isopropyl isopropanol 111 77 3 908 21 21 018 P01 011 P01 036 Plastic media Dry Strip Typ II DS2 30 40 G MIL P 85891A 908 44 30 020 P0...

Page 261: ... 74 204 See note 1 P02 005 Sponge 904 49 75 303 See note 1 P02 006 Lockwire heat resistant MS 9226 03 diameter 0 6 mm 0 025 in 919 01 11 203 P02 007 Lockwire standard NASM20995 diameter 0 6 mm 0 025 in 919 01 11 103 MS20995C25 Cable safety Safe T Cable C10 121 diameter 0 6 mm 0 025 in 919 01 11 306 This alternative locking device is valid for the PC 12 only In some locations it might not be possib...

Page 262: ...16 in 919 01 11 101 P02 023 P02 024 P02 024 Abrasive cloth 1913 Siawat FC grade 600 904 47 22 223 P02 025 Cotton wool polishing raw 904 49 73 006 No longer procurable Wool polishing 904 49 73 001 No longer procurable Cloth polishing 290099 904 49 73 015 See note 1 P02 026 Abrasive cloth Grade 1500 907 71 22 703 See note 1 P02 027 Abrasive cloth Grade 1800 907 71 22 704 See note 1 P02 028 Abrasive ...

Page 263: ...o PT12 904 49 73 016 See note 1 For application on acrylic surfaces P02 003 See note 1 P02 019 See note 1 P02 042 Surface prep mitt 910 21 21 006 P02 043 Micro fiber cloth yellow 904 49 76 382 See note 1 P02 037 P02 044 Abrasive disk SIA 1913 SIA Watt P120 diameter 9 x 2 mm 0 354 x 0 08 in 990 00 04 006 See note 1 P02 045 Abrasive disk SIA 1913 SIA Watt P12 diameter 11 x 2mm 0 433 x 0 08 in 990 00...

Page 264: ...iller rod 347 AMS 5680 diameter 0 8 mm 0 032 in 907 83 32 501 Filler rod 347 AMS 5680 diameter 1 0 mm 0 039 in 907 83 32 502 Filler rod 347 AMS 5680 diameter 1 14 mm 0 045 in 907 83 32 503 Filler rod 347 AMS 5680 diameter 1 6 mm 0 064 in 907 83 32 505 P03 002 Welding rod Filler rod 1 7734 2 diameter 1 5 mm 0 06 in 907 83 31 911 No longer procurable Filler rod 1 7734 2 diameter 2 0 mm 0 08 in 907 8...

Page 265: ...23 No longer procurable P04 017 P04 009 High temperature compound Molybdenum Disulfide Petrolatum 908 25 71 802 MIL PRF 83483E P04 010 P04 009 P04 011 Dry lubricant air curing Molyslip ADF 908 10 09 002 No longer procurable P04 043 P04 012 Corrosion preventative Mastinox 6856H 910 31 20 040 No longer procurable P04 039 P04 013 P04 003 P04 014 Thermal transfer compound V5004 907 13 11 998 No longer...

Page 266: ...cant Ultra Plus Extra 908 40 01 002 P04 035 High temperature compound Molykote P 37 908 24 02 003 P04 036 Thermal transfer compound Dow Corning 340 907 13 11 997 P04 037 Grease AeroShell Grease 64 908 25 71 804 MIL G 21164D G 353 P04 038 Oxygen paste Krytox 240AC 908 25 71 702 No longer procurable P04 040 P04 039 Corrosion preventive Chromate free CA1000 910 31 20 042 Thinners 3924 0422 9000 910 3...

Page 267: ...PE P 0 2PCT 60ML 908 10 09 006 P04 048 Grease fluoro silicone Molykote FS 3451 908 20 02 095 P04 049 Lubricant BOELUBE 70307 908 15 12 062 Table 4 Jointing Compounds and Greases Continued Material No Material Name Product Name Alternative Product Specification Pilatus Part No Notes ...

Page 268: ... polish M 83 904 49 76 241 P05 009 Sealing Polymer sealing M 20 904 49 76 221 P05 010 Fine cleaner Last Touch Detailing spray D 155 904 49 76 165 P05 011 Plastic Acrylic cleaner Zip Chem X 405 5 gal container 908 64 22 215 Zip Chem X 405 12 oz spray 908 64 22 216 P05 003 P05 012 Plastic Acrylic cleaner Burnus Kunststoff Reiniger 20 l container 908 64 22 217 Burnus Kunststoff Reiniger 0 5 l contain...

Page 269: ...STM E1417 MIL STD 2132 or ASTM E165 AMS2644 Form d and e P06 006 P06 007 P06 004 Leak detector spray 907 12 11 004 No longer procurable MIL PRF 25567 ECO Leak Finder 907 12 11 005 P06 005 Fluorescent penetrant Ardrox 970P25E 25 l container 908 68 12 113 Used for dye inspections in accordance with ASTM E1417 MIL STD 2132 or ASTM E165 Ardrox 970P25E 1 l container 908 68 12 117 Ardrox 9705 AMS2644 Ty...

Page 270: ... 12 108 Used for dye inspections in accordance with ASTM E1417 MIL STD 2132 or ASTM E165 AMS2644 Class 2 P06 002 P06 009 A C system leak detection dye 957 30 00 070 Table 6 Inspecting Continued Material No Material Name Product Name Alternative Product Specification Pilatus Part No Notes ...

Page 271: ...o Nobel green 910 02 05 031 P07 003 Hardener 92140 hardener 910 02 05 032 Thinners C25 90 S 200 liters 910 09 00 101 Thinners C25 90 S 5 liters 910 09 00 104 P07 008 Paint marking Enictol 234183 125 red 910 33 82 150 No longer procurable P07 045 P07 009 Paint Celoflex 95 paint anti erosion 910 04 04 504 Hardener 0778 9000 hardener 910 04 04 505 Thinners 0470 9000 thinners 910 09 00 057 P07 010 Pai...

Page 272: ...er 910 04 04 050 Thinners 910 09 00 005 P07 020 Paint White Aerodur finish C21 100 UVR RAL 9010 910 04 04 320 No longer procurable P07 031 Paint Black Aerodur finish C21 100 UVR RAL 9005 equal gloss 910 04 04 314 No longer procurable P07 031 Paint Black Aerodur finish C21 100 UVR RAL 9005 equal gloss tinter 910 04 04 416 No longer procurable P07 031 Paint Red Aerodur finish C21 100 UVR RAL 3020 91...

Page 273: ... 11018 Eclipse HS PUR topcoat paint RAL 7035 910 04 04 521 Paint Gray ECL G 11017 Eclipse HS PUR topcoat paint RAL 7040 910 04 04 522 No longer procurable P07 031 Paint Black ECL G 92 Eclipse HS PUR topcoat paint RAL 9005 910 04 04 523 No longer procurable P07 031 Paint Blue ECL G 2843 Eclipse HS PUR topcoat paint RAL 5017 910 04 04 524 No longer procurable P07 031 Paint White ECL G 1681 Eclipse H...

Page 274: ...yl P25 910 08 06 013 Thinner Sikkens Plus Reducer Fast 917 00 40 019 P07 026 Wash primer ANAC Metaflex FCR Base 910 02 09 005 Hardener Metaflex FCR 910 02 09 006 Thinner C25 90S 910 09 00 101 P07 027 Conductive paint Pyroflex 7 D 713 Base 910 04 04 334 Hardener 0651 910 04 04 335 Thinner C25 90S 910 09 00 101 P07 028 Camouflage Dark grey topcoat Aerodur 5000 910 04 04 336 Light grey 910 04 04 337 ...

Page 275: ... 4200 RAL 5003 910 04 04 568 P07 020 and P07 022 Alumigrip 4200 RAL 7001 910 04 04 569 P07 020 and P07 022 Alumigrip 4200 RAL 1023 910 04 04 578 P07 020 and P07 022 Alumigrip 4200 RAL 7030 910 04 04 640 P07 020 and P07 022 Curing solution PC 242 910 04 04 553 Activator 4950 standard activator 910 04 04 555 Activator 4951 medium activator 910 04 04 556 Activator 4952 fast activator 910 04 04 559 Ac...

Page 276: ...ator A4962 cool weather 910 04 04 574 Activator A4968 standard 910 04 04 591 Activator A4969 fast stripe spot repair 910 04 04 592 P07 039 Topcoat base coat polyurethane Alumigrip 4400 base coat base for example snow white 910 04 04 579 Curing Solution For Alumigrip 4400 BC CS4904 910 04 04 584 Activator A4956 standard 910 04 04 583 Activator A4957 high temperature high humidity 910 04 04 586 Acti...

Page 277: ...5 white 910 04 04 636 Curing solution 910 04 04 584 Activator A4956 standard for Alumigrip 4400 BC CS4904 910 04 04 583 Activator A4957 high temperature high humidity 910 04 04 586 Activator A4965 fast stripe spot repair 910 04 04 587 P07 049 Paint Alumigrip 4400 CM407G4 red 910 04 04 655 Paint Alumigrip 4400 CM427B5 yellow 910 04 04 656 Paint Alumigrip 4400 CM470E4 blue 910 04 04 657 Paint Alumig...

Page 278: ...inner FRSL thinner 910 09 00 014 P07 063 Wash primer Desoprime 7530 910 02 09 010 Hardener Desoprime 7530B 910 02 09 009 P07 064 Primer Desoprime 7065 910 02 04 010 Hardener Desoprime 7065B 910 02 04 011 Thinner Desoprime 7065C 910 09 04 001 P07 065 Filler Desofill CA8620 kit 910 08 04 003 P07 066 Paint Desothane HS CA8800 solid 912 00 00 061 Hardener CA8800Z 910 04 04 612 Thinner CA8800CT 910 04 ...

Page 279: ...6 910 04 04 583 Activator A4957 910 04 04 586 Activator A4965 910 04 04 590 Activator A4967 910 04 04 582 P07 072 Paint Alumigrip 4400 metallic 912 00 00 067 Curing solution CS4904 910 04 04 584 Activator A4956 910 04 04 583 Activator A4957 910 04 04 586 Activator A4965 910 04 04 590 Activator A4967 910 04 04 582 P07 073 Paint Alumigrip 4400 mica 912 00 00 068 Curing solution CS4904 910 04 04 584 ...

Page 280: ...Primer filler group part number Primer surfacer CM0481968 910 02 05 056 Hardener CM0120828 910 02 05 053 Reducer CM0110933 910 09 00 024 Thinner CM0110944 910 09 00 025 Thinner CM0110099 910 09 00 021 P07 078 CCC liquid Bonderite M CR 1500 AERO 908 40 32 254 P07 079 Coating protective surface sealing Granitize X20 18 AECI 3 904 49 76 226 Table 7 Paints Varnishes and Thinners Continued Material No ...

Page 281: ...r procurable P08 024 P08 008 Adhesive Miranit 8526 BALCO ME 910 42 22 372 P08 009 Adhesive 3M Fastbond 10 910 42 22 037 No longer procurable P08 080 MIL A 21366 A A 1936 P08 010 Thinners 3M Fastbond 10 910 42 22 038 P08 011 Contact adhesive P08 009 P08 012 Thinner P08 010 P08 013 Sealant P08 018 P08 014 Sealant P08 056 P08 015 Adhesive Acrylic Tensol No 6 910 42 22 393 P08 016 Edge sealer P08 041 ...

Page 282: ...ige 509452 910 08 55 001 P08 031 Conductive sealant BFG A 56 B 910 07 19 012 P08 032 Sealant P08 057 P08 033 Sealant P08 058 P08 034 Adhesive Araldite two part adhesive 910 42 62 002 No longer procurable P08 104 P08 035 Thread sealing Loctite 586 910 42 12 130 P08 036 Resin Epoxy Dexter Hysol AE 9396 2 part 910 42 72 170 P08 037 Glass microspheres Cap o Sil 910 82 20 910 P08 038 Adhesive Epoxy Ara...

Page 283: ... 2 80 thickness 14 mm 0 55 in 917 00 25 210 P08 050 Honeycomb core Nomex 3 2 48 thickness 12 mm 0 50 in 917 00 25 227 P08 051 Foam core PMI Rohazell 51WF thickness 35 mm 1 37 in 917 33 14 146 P08 052 Adhesive Epoxy 3M DP490 910 42 72 205 SW9323 2B A Use for field repair P08 059 P08 053 Filler spray Filler 2K UP 910 08 06 004 P08 054 Resin Epoxy 5052 917 00 40 001 Resin Araldite 5052 Hardener Aradu...

Page 284: ...2 203 No longer procurable P08 059 P08 061 Adhesive Epoxy DP 100FR 2 part 910 42 62 003 P08 062 Adhesive INSUL Kleber 1000 910 42 22 351 P08 063 Adhesive Acrylic Tensol No 70 910 42 72 112 P08 064 Adhesive Epoxy Raychem S1005 910 42 72 206 P08 065 Adhesive Loctite grade 641 910 42 12 120 No longer procurable P08 066 Honeycomb core ECA 3 2 48 3 mm thick 917 00 25 220 P08 067 Honeycomb core ECA 3 2 ...

Page 285: ...itor 908 41 01 002 P01 030 P08 079 Adhesive Loctite grade 222 910 42 12 132 P08 080 Adhesive 3M Scotch Weld 10 910 42 22 041 P08 009 P08 081 Release agent Glisseal N 910 82 72 006 P08 082 Surface sealer Granitize Xzilon 3 904 49 76 222 P08 083 Adhesion promoter MC 110 For polysulfide sealants 907 10 11 238 P08 084 Adhesive 2 part CB200 40 ml dual pack syringe cartridge acrylic structural adhesive ...

Page 286: ...t group part number MC 238 B 1 2 907 10 11 229 MC 238 B 2 907 10 11 233 MC 238 B 4 907 10 11 239 P08 071 P08 096 Sealant interfay MC 780 C 48 907 10 11 240 P08 097 Sealer Paint edge seal 3950 1K transparent 910 04 04 354 P08 098 Sealant MC 780 C 8 907 10 11 228 P08 099 Sealant MC 780 C 4 907 10 11 247 P08 100 Adhesive L 9120 FST 910 42 72 210 High strength P08 101 Resin Hardener Epocast 50 A1 resi...

Page 287: ...0 11 234 MC 780 C 2 907 10 11 235 MC 780 C 12 907 10 11 236 MC 780 C 24 907 10 11 237 MC 780 C 48 907 10 11 240 MC 780 C 4 907 10 11 247 MC 780 C 60 907 10 11 249 P08 073 P08 074 P08 075 P08 094 P08 096 P08 098 P08 099 P08 107 Sealant high temperature fillet 551 32 99 006 Sealant group part number DAPCO 2200 2 5 oz kit 907 10 11 275 Table 8 Bonding Adhesives Fillers and Sealers Continued Material ...

Page 288: ...5 mm 1 0 in wide 917 40 80 006 P09 008 Cable ties MS3367 4 9 PA66 69 x 2 5 mm 2 72 x 0 10 in 971 32 51 104 SAE AS33671 69 x 2 5 mm 2 72 x 0 10 in P09 009 P09 024 P09 010 Rubber band 178 x 16 mm 7 00 x 0 63 in 944 85 82 112 P09 011 Lead seal 8 0 x 5 0 mm 0 32 x 0 20 in 911 21 91 005 P09 012 Tape aluminum Scotch 425 50 mm 2 0 in wide 917 40 91 005 FAR25 853 a L T 80 MIL T 23397 TO 1 1 8 P09 013 Tape...

Page 289: ...nk 4 76 mm 0 188 in diameter 917 99 88 605 P09 031 Glass fiber fabric WL8 4548 60 163 g m2 917 00 11 002 P09 032 Carbon fiber fabric No longer procurable P09 033 No longer procurable P09 034 Copper wire mesh Lightning strike protection 72 g m2 919 02 30 111 P09 035 No longer procurable P09 036 Tape adhesive 0 64 x 19 mm 0 025 x 0 75 in 917 40 67 312 P09 037 Spiralwrap 917 99 90 002 P09 038 P09 043...

Page 290: ...54 Carbon fiber fabric 200g m2 917 00 12 123 P09 055 Peel ply 51789 natural P09 056 Cable ties MS3367 5 9 PA66 971 32 51 106 SAE AS3367I P09 057 Tape adhesive 971 32 52 802 P09 058 Tape PTFT thread sealing 12 7 mm 0 50 in 917 47 71 104 No longer procurable P09 059 P09 059 Tape PTFE P 412 917 47 71 105 P09 001 and P09 058 P09 060 Protective tape application solution 3M 910 09 00 309 Typical Applica...

Page 291: ...75 in diameter 917 99 88 609 P09 080 Tape PTFE Adhesive backed thickness 0 17 mm 0 0067 in 917 40 70 009 P09 081 Tape Foil PTFE oneside etch 0 5 x 300 mm KT 01 1025 1050 917 40 70 381 P09 082 Tape hook self adhesive KLETTOSTAR hook tape 25 mm 0 98 in width 15147 45 0025 00 000 1002 917 47 28 022 P09 083 Tape loop self adhesive KLETTOSTAR loop tape 25 mm 0 98 in width 15244 45 0025 00 000 1002 917 ...

Page 292: ...17 73 17 063 P09 089 Tape anti chafe GORE tape PTFE 25 4mm 1 in wide x 0 5 mm thick GSC 21 99603 027 917 73 17 064 P09 090 Sleeve heat shrink black SFTW 202A 3 64 SCHWARZ 1 200 mm 0 047 in diameter 917 99 88 601 Table 9 General Stores Continued Material No Material Name Product Name Alternative Product Specification Pilatus Part No Notes ...

Page 293: ...lass 1 grade 1 4 P10 006 Hydraulic fluid AeroShell Fluid 31 908 14 12 016 MIL PRF 83282D P10 007 Compressor oil BVM 100N 908 12 22 101 Reniso KES 100 957 30 00 050 P10 008 Refrigerant R 12 957 30 00 058 No longer procurable P10 009 P10 004 P10 010 Refrigerant R 134a 957 30 00 063 P10 011 Compressor oil Castrol Icematic SW 32 957 30 00 051 Not to be used on PC12 45 47 47E P10 021 P10 012 Oil Heller...

Page 294: ...airforce red A R Texaco Canopus 13 white Unisol liquid green 2BHF AG A R Unisol liquid red BHF AG A R P10 021 Refrigeration lubricant Emkarate RL 100H 957 30 00 059 P10 022 Hydraulic fluid Castrol Brayco Micronic 881 908 14 12 020 MIL PRF 87257B or newer P10 023 Refrigeration lubricant Emkarate RL 46H 957 30 00 076 P10 024 Fluid assembly Assembly Fluid 1 908 14 12 102 P10 025 Oil penetrating Gasoi...

Page 295: ...efer to AFM Section 2 Limitations P11 001 Fuel For PC 12 NG aircraft For approved fuels refer to AFM Section 2 Limitations P11 001 Fuel For PC 12 NGX aircraft For approved fuels refer to AFM Section 2 Limitations P11 002 Fuel test kit FHR8 2 908 69 11 124 P11 003 Biocide aviation fuel BIOBOR JF 908 69 11 125 Fuel additive for curative and preventative treatment of micro biological biomass in fuel ...

Page 296: ...All 20 31 00 Page 39 Oct 04 21 Table 12 Packing Material No Material Name Product Name Alternative Product Specification Pilatus Part No Notes P12 Packing There are no Pilatus Recommended Materials in this section ...

Page 297: ...EFFECTIVITY All 20 31 00 Page 40 Oct 04 21 INTENTIONALLY BLANK ...

Page 298: ...hnical publication Title 12 B 00 00 00 00A 060A A GENERAL LIST OF AEROSPACE GROUND EQUIPMENT AGE AND TOOLS 12 B 20 31 00 00A 070A A STANDARD PRACTICES CONSUMABLE MATERIALS LIST 12 B 22 10 00 00A 903A A AUTOPILOT ADJUSTMENT TEST Preliminary Requirements Required Conditions Table 2 Required Conditions Action Condition Data module Technical publication None PC 12 47E AMM Doc No 02300 ISSUE 01 REVISIO...

Page 299: ...rocedure 1 Removal 1 1 Open and install a Safety clip circuit breaker hold open Pt No T12 030 on these circuit breakers A P SERVO AVIONICS 1 BUS A P SERVO ENABLE AVIONICS 1 BUS 1 2 Open the access panel 31AB 1 3 Disconnect the electrical connector Figure 1 1 from the pitch actuator Figure 1 4 1 4 Cut and remove the lockwire from the bolts Figure 1 2 1 5 Hold the pitch actuator Figure 1 4 Remove th...

Page 300: ...e electrical connector Figure 1 1 to the pitch actuator 2 7 Remove the safety clip and close the circuit breakers A P SERVO AVIONICS 1 BUS A P SERVO ENABLE AVIONICS 1 BUS 2 8 Do the operational test of the autopilot system refer to AMM 12 B 22 10 00 00A 903A A 2 9 Remove all the equipment tools and materials from the work area Make sure that the work area is clean 2 10 Close the access panel 31AB ...

Page 301: ... FRAME 39 1 2 3 2 4 5 3 B Figure 1 Pitch Actuator Removal Installation PC 12 47E AMM Doc No 02300 ISSUE 01 REVISION 26 MSN 545 1001 1719 1721 1999 12 B AM 00 00 00 I UNCLASSIFIED Effectivity All 12 B 22 10 02 00A 920A A UNCLASSIFIED 2021 12 04 Page 4 ...

Page 302: ... 1 C 6 Figure 1 Pitch Actuator Removal Installation PC 12 47E AMM Doc No 02300 ISSUE 01 REVISION 26 MSN 545 1001 1719 1721 1999 12 B AM 00 00 00 I UNCLASSIFIED Effectivity All 12 B 22 10 02 00A 920A A UNCLASSIFIED 2021 12 04 Page 5 ...

Page 303: ...red Conditions Action Condition Data module Technical publication None PC 12 47E AMM Doc No 02300 ISSUE 01 REVISION 26 MSN 545 1001 1719 1721 1999 12 B AM 00 00 00 I UNCLASSIFIED Effectivity All 12 B 22 10 02 00A 920A A End of data module UNCLASSIFIED 2021 12 04 Page 6 ...

Page 304: ... AEROSPACE GROUND EQUIPMENT AGE AND TOOLS 12 B 20 31 00 00A 070A A STANDARD PRACTICES CONSUMABLE MATERIALS LIST 12 B 22 10 00 00A 903A A AUTOPILOT ADJUSTMENT TEST 12 B 25 21 04 00A 920A A EXECUTIVE CARPETS REMOVAL INSTALLATION 12 B 25 22 04 00A 920A A STANDARD CARPETS REMOVAL INSTALLATION Preliminary Requirements Required Conditions Table 2 Required Conditions Action Condition Data module Technica...

Page 305: ...Procedure 1 Removal 1 1 Open and install a Safety clip circuit breaker hold open Pt No T12 030 on these circuit breakers A P SERVO AVIONIC 1 BUS A P SERVO ENABLE AVIONIC 1 BUS 1 2 Remove the center carpet For Executive interior refer to AMM 12 B 25 21 04 00A 920A A For Standard interior refer to AMM 12 B 25 22 04 00A 920A A 1 3 Open the access panel 12EZ 1 4 Disconnect the electrical connector Fig...

Page 306: ...al Pt No P08 076 to the bolts Figure 1 1 2 6 Connect the electrical connector Figure 1 4 to the actuator 2 7 Remove the safety clip and close the circuit breakers A P SERVO AVIONIC 1 BUS A P SERVO ENABLE AVIONIC 1 BUS 3 Close Up 3 1 Do the operational test of the autopilot system refer to AMM 12 B 22 10 00 00A 903A A 3 2 Remove all the equipment tools and materials from the work area Make sure tha...

Page 307: ...FRAME 23 1 2 1 2 3 4 5 C B Figure 1 Roll Actuator Removal Installation PC 12 47E AMM Doc No 02300 ISSUE 01 REVISION 26 MSN 545 1001 1719 1721 1999 12 B AM 00 00 00 I UNCLASSIFIED Effectivity All 12 B 22 10 03 00A 920A A UNCLASSIFIED 2021 12 04 Page 4 ...

Page 308: ...AME 23 C 6 6 Figure 1 Roll Actuator Removal Installation PC 12 47E AMM Doc No 02300 ISSUE 01 REVISION 26 MSN 545 1001 1719 1721 1999 12 B AM 00 00 00 I UNCLASSIFIED Effectivity All 12 B 22 10 03 00A 920A A UNCLASSIFIED 2021 12 04 Page 5 ...

Page 309: ...red Conditions Action Condition Data module Technical publication None PC 12 47E AMM Doc No 02300 ISSUE 01 REVISION 26 MSN 545 1001 1719 1721 1999 12 B AM 00 00 00 I UNCLASSIFIED Effectivity All 12 B 22 10 03 00A 920A A End of data module UNCLASSIFIED 2021 12 04 Page 6 ...

Page 310: ...cal publication Title 12 B 00 00 00 00A 060A A GENERAL LIST OF AEROSPACE GROUND EQUIPMENT AGE AND TOOLS 12 B 20 31 00 00A 070A A STANDARD PRACTICES CONSUMABLE MATERIALS LIST 12 B 22 10 00 00A 903A A AUTOPILOT ADJUSTMENT TEST Preliminary Requirements Required Conditions Table 2 Required Conditions Action Condition Data module Technical publication None PC 12 47E AMM Doc No 02300 ISSUE 01 REVISION 2...

Page 311: ... A Procedure 1 Removal 1 1 Open and install a Safety clip circuit breaker hold open Pt No T12 030 on these circuit breakers A P SERVO AVIONIC 1 BUS A P SERVO ENABLE AVIONIC 1 BUS 1 2 Open the access panel 31AB 1 3 Disconnect the electrical connector Figure 1 1 from the yaw actuator Figure 1 2 1 4 Cut and remove the lockwire from the bolts Figure 1 4 1 5 Hold the yaw actuator Figure 1 2 Remove the ...

Page 312: ...l connector Figure 1 1 to the yaw actuator Figure 1 2 2 7 Remove the safety clip and close the circuit breakers A P SERVO AVIONIC 1 BUS A P SERVO ENABLE AVIONIC 1 BUS 3 Close Up 3 1 Do the operational test of the autopilot system refer to AMM 12 B 22 10 00 00A 903A A 3 2 Remove all the equipment tools and materials from the work area Make sure that the work area is clean 3 3 Close the access panel...

Page 313: ...FRAME 39 1 2 3 4 3 4 5 C B Figure 1 Yaw Actuator Removal Installation PC 12 47E AMM Doc No 02300 ISSUE 01 REVISION 26 MSN 545 1001 1719 1721 1999 12 B AM 00 00 00 I UNCLASSIFIED Effectivity All 12 B 22 10 04 00A 920A A UNCLASSIFIED 2021 12 04 Page 4 ...

Page 314: ...RAME 38 C 6 6 Figure 1 Yaw Actuator Removal Installation PC 12 47E AMM Doc No 02300 ISSUE 01 REVISION 26 MSN 545 1001 1719 1721 1999 12 B AM 00 00 00 I UNCLASSIFIED Effectivity All 12 B 22 10 04 00A 920A A UNCLASSIFIED 2021 12 04 Page 5 ...

Page 315: ...red Conditions Action Condition Data module Technical publication None PC 12 47E AMM Doc No 02300 ISSUE 01 REVISION 26 MSN 545 1001 1719 1721 1999 12 B AM 00 00 00 I UNCLASSIFIED Effectivity All 12 B 22 10 04 00A 920A A End of data module UNCLASSIFIED 2021 12 04 Page 6 ...

Page 316: ...3 1 On Ground 5 3 2 In Flight 5 3 3 Stick Shaker 6 3 4 Stick Pusher 6 3 5 Ice Mode 6 3 6 CAS Captions 7 3 6 1 PUSHER 7 3 6 2 Air Ground Fail 7 3 6 3 Pusher Safe Mode 7 3 7 System Tests 7 3 7 1 System Start Up 7 3 7 2 Pre flight Test 7 3 7 3 In flight Test 8 Index of Tables Page 1 References 1 Index of Figures Page 1 Stick Pusher System Schematic 9 References Table 1 References Data module Technica...

Page 317: ... WARNING SYSTEM DESCRIPTION AND OPER ATION 12 B 32 60 00 00A 040A A POSITION AND WARNING HYDRAULIC LANDING GEAR DESCRIPTION AND OPERATION 12 B 32 60 00 00A 040B A POSITION AND WARNING ELECTRO MECHANICAL LAND ING GEAR DESCRIPTION AND OPERATION 12 B 79 00 00 00A 040A A OIL SYSTEM DESCRIPTION AND OPERATION Description 1 General The speed and attitude correction system gives a warning when the aircraf...

Page 318: ... installed below the floor between frames 17 and 18 in a rectangular box with three electrical connectors on the front It has two stick pusher channels which have separate 28 VDC supplies from different busbars Each channel gives a 28 VDC output to the torque transducer The two channel outputs to the torque transducer are connected to a terminal block The terminal block also connects the channels ...

Page 319: ...l slip clutch The clutch operates at a control force of 31 8 to 40 8 kgf 70 to 90 lbf A cable installed on the capstan connects to the elevator control cable The slip clutch lets the pilot override the stick pusher servo if incorrect operation occurs The slip clutch operates if the torque given to the capstan from the elevator control cable is more than the slip clutch limit The stick pusher servo...

Page 320: ...ck pusher computer 2 8 PUSHER Test Switch The PUSHER test switch is used to do a test of the stall warning and pusher functions of the system The system goes into PUSHER ICE MODE operation when the PUSHER test switch is pressed It can be used in flight or on the ground The in flight and on ground tests operate differently The PUSHER TEST push switch is on the TEST section of the Overhead Control P...

Page 321: ...gnal to the stick pusher servo The stick pusher servo operates the elevator cable system to move the elevators and make the aircraft pitch go nose down The stick shaker and stall warning tone stay on when the stick pusher servo operates The AOA value at which the stick pusher servo operates depends on several factors These include the flap position engine torque and mode of operation normal or ice...

Page 322: ...this occurs the stick shaker and aural stall warning are operational but the stick pusher is disabled 3 6 3 Pusher Safe Mode The cyan Pusher Safe Mode advisory message comes on if the stick pusher computer detects a flap position or flap asymmetry greater than 2 degrees for 10 seconds or more In safe mode the stall warning trigger points are rescheduled to operate at the 0 degrees flap position se...

Page 323: ... is released and the amber PUSHER ICE MODE caption on the CAS display goes off 3 7 3 In flight Test The in flight test is not the same as the pre flight test The amber PUSHER caption on the CAS display must remain off and the stick pusher must not operate The stick pusher computer must receive all of these signals to do the in flight test Aircraft not on ground Engine torque more than 5 psi PCL no...

Page 324: ...TED BY EITHER COMPUTER AND ACTIVATED BY BOTH COMPUTERS PCL IDLE ICE MODE INERT SEP OPEN PROP DEICE ON ENGINE RUNNING SWITCH 60 PSI STALL WARN 2 MAIN BUS PUSHER SYS MAU CH A AOA LH COMP FAIL PUSHER SERVO FAIL STALL AURAL STALL WARNING PILOT PFD PUSHER CAS AIR GND FAIL ICE PROTECTION PUSHER ICE MODE MAU CH B AOA RH COMP FAIL STALL CO PILOT PFD Figure 1 Stick Pusher System Schematic PC 12 47E AMM Doc...

Page 325: ... 12 47E AMM Doc No 02300 ISSUE 01 REVISION 26 MSN 545 1001 1719 1721 1999 12 B AM 00 00 00 I UNCLASSIFIED Intentionally left blank Effectivity All 12 B 22 20 00 00A 040A A UNCLASSIFIED 2021 12 04 Page 10 ...

Page 326: ...PMENT AGE AND TOOLS 12 B 24 00 00 00A 901A A ELECTRICAL POWER MAINTENANCE PRACTICES Preliminary Requirements Required Conditions Table 2 Required Conditions Action Condition Data module Technical publication None Support equipment Table 3 Support equipment Name Identifications References Qty Reference Remark Ampere probe Part Local supply 1 Jumper wire Part Local supply 1 Maintenance box Part T45 ...

Page 327: ...ons given in AMM 12 B 24 00 00 00A 901A A 2 Open and install a Safety clip Circuit breaker hold open Pt No T12 030 on these circuit breakers N ESS RIGHT HAND POWER JUNCTION BOX AV 2 RHPJB MAIN RHPJB U FLOOR HTR RHPJB HYD PWR RHPJB GEN 2 RHPJB F WARMER RHPJB if installed RH W SHLD RHPJB STARTER ESSENTIAL BUS IGNITION ESSENTIAL BUS FUEL CTL ESSENTIAL BUS LH FUEL PUMP ESSENTIAL BUS RH FUEL PUMP ESSEN...

Page 328: ...N Make sure that the pilot Primary Flight Display PFD powers up the Battery 2 voltage is 24 VDC 3 VDC the Battery 2 current reading is negative 12 On the OHP set the BAT 1 switch to ON 13 On the OHP set the EXT PWR switch to ON and make sure that the blue EXT PWR ON LED is ON the MFD Battery 1 and Battery 2 voltages show more than 25 VDC the MFD Battery 1 and Battery 2 currents show positive 14 Us...

Page 329: ...fety clip and close this circuit breaker FLT CONT CH B AVIONIC 2 BUS 30 On the CAS window make sure that the Flt Ctlr Ch A B Fail caution message is ON 31 On the OHP set the AV 2 BUS switch to ON 32 Make sure that the CAS Avionic 1 2 Bus caution message is ON the CAS Flt Ctlr Ch A B Fail caution message is ON 33 Remove the safety clip and close this circuit breaker AV 2 RHPJB 34 Make sure that the...

Page 330: ...does not operate 49 Open the GEN 2 circuit breaker 50 Close the N ESS circuit breaker on the RHPJB Make sure that the Maintenance Box green 28VDC AVAILABLE NON ESS BUS LED is off the CAS Non Essential Bus caution message is ON 51 Close the GEN 2 circuit breaker 52 Make sure that the Maintenance Box green 28VDC AVAILABLE NON ESS BUS LED is ON the CAS Non Essential Bus caution message is off Aircraf...

Page 331: ...ure that the voltage is 0 VDC 62 At the underfloor right relay panel remove the two relays K162A1 and K162K4 63 Use a Jumper wire Pt No Local supply to link pin B2 of relay K162A1 to pin B2 of relay K162K4 Make sure that the PFD green Starter caption is ON 64 Remove the jumper wire from pin B2 of relay K162A1 and pin B2 of relay K162K4 Make sure that the PFD green Starter caption is OFF 65 At the ...

Page 332: ...nels 21QZ 43AL 43AR 11DZ Requirements after job completion Required Conditions Table 6 Required Conditions Action Condition Data module Technical publication None PC 12 47E AMM Doc No 02300 ISSUE 01 REVISION 26 MSN 545 1001 1719 1721 1999 12 B AM 00 00 00 I UNCLASSIFIED Effectivity All 12 B 24 52 20 00A 903A A End of data module UNCLASSIFIED 2021 12 04 Page 7 ...

Page 333: ...C 12 47E AMM Doc No 02300 ISSUE 01 REVISION 26 MSN 545 1001 1719 1721 1999 12 B AM 00 00 00 I UNCLASSIFIED Intentionally left blank Effectivity All 12 B 24 52 20 00A 903A A UNCLASSIFIED 2021 12 04 Page 8 ...

Page 334: ...ary Requirements Required Conditions Table 2 Required Conditions Action Condition Data module Technical publication None Support equipment Table 3 Support equipment Name Identifications References Qty Reference Remark Warning sign DO NOT CON NECT ELECTRICAL POWER Part Local supply AR Warning sign FUEL LINES OPEN Part Local supply AR PC 12 47E AMM Doc No 02300 ISSUE 01 REVISION 26 MSN 545 1001 1719...

Page 335: ...regulations 1 1 2 Use only spark and explosion proof electrical equipment when work is done on the fuel system 1 1 3 Operate a vapor remover at all times when work is done in the fuel tanks 1 1 4 Approved personnel and fire extinguishing equipment must be available at all times 1 1 5 Wear only anti static clothing when work is done in a fuel tank 1 1 6 Wear air fed respirators in areas of high fue...

Page 336: ...pipe is installed in the correct position and the pipe ends align and are at 90 degrees to the connections 1 3 5 2 Make sure that the pipe ends touch the connections correctly and the pipe is not misaligned 1 3 5 3 Use spanners on the pipe end and the connection when the pipe is tightened 1 3 5 4 Tighten each end of the pipe in equal steps to the correct torque 1 3 5 5 Tighten the pipe end to the ...

Page 337: ...red Conditions Action Condition Data module Technical publication None PC 12 47E AMM Doc No 02300 ISSUE 01 REVISION 26 MSN 545 1001 1719 1721 1999 12 B AM 00 00 00 I UNCLASSIFIED Effectivity All 12 B 28 00 00 00A 901A A End of data module UNCLASSIFIED 2021 12 04 Page 4 ...

Page 338: ...0 00 00A 060A A GENERAL LIST OF AEROSPACE GROUND EQUIPMENT AGE AND TOOLS 12 B 28 10 02 00A 920A A DRAIN VALVE REMOVAL INSTALLATION Preliminary Requirements Required Conditions Table 2 Required Conditions Action Condition Data module Technical publication None Support equipment Table 3 Support equipment Name Identifications References Qty Reference Remark Fuel sample unit Part T12 020 AR PC 12 47E ...

Page 339: ... IS DANGEROUS AND CAN CAUSE INJURY TO PERSONNEL CAUTION MAKE SURE THAT THE FUEL COMPONENTS ARE FULLY CLEAN DURING THE MAINTENANCE DO NOT LET UNWANTED MATERIAL GO INTO THE AIRCRAFT FUEL SYSTEM CONTAMINATION OF THE FUEL SYSTEM CAN CAUSE DAMAGE CORROSION AND ENGINE FAILURE Note To identify the AGE and tools used in this procedure refer to the List of AGE and Tools TEM 12 B 00 00 00 00A 060A A Procedu...

Page 340: ...ou can see the O ring Figure 1 4 2 2 Remove and discard the O ring Figure 1 4 2 3 Install a new O ring Pt No CSN 28200008 240 28200010 165 Figure 1 4 on the valve mechanism 2 4 Use the Fuel sample unit Pt No T12 020 to gently push the valve mechanism into the valve body and turn it counter clockwise to close the valve mechanism 2 5 Make sure that the drain valve Figure 1 1 does not leak 2 6 If the...

Page 341: ...3 A 1 4 2 3 VALVE IN CLOSED POSITION VALVE IN OPEN POSITION B B Figure 1 Fuel Drain Valve Maintenance Practices PC 12 47E AMM Doc No 02300 ISSUE 01 REVISION 26 MSN 545 1001 1719 1721 1999 12 B AM 00 00 00 I UNCLASSIFIED Effectivity All 12 B 28 10 02 00A 901A A UNCLASSIFIED 2021 12 04 Page 4 ...

Page 342: ...red Conditions Action Condition Data module Technical publication None PC 12 47E AMM Doc No 02300 ISSUE 01 REVISION 26 MSN 545 1001 1719 1721 1999 12 B AM 00 00 00 I UNCLASSIFIED Effectivity All 12 B 28 10 02 00A 901A A End of data module UNCLASSIFIED 2021 12 04 Page 5 ...

Page 343: ...C 12 47E AMM Doc No 02300 ISSUE 01 REVISION 26 MSN 545 1001 1719 1721 1999 12 B AM 00 00 00 I UNCLASSIFIED Intentionally left blank Effectivity All 12 B 28 10 02 00A 901A A UNCLASSIFIED 2021 12 04 Page 6 ...

Page 344: ...itle 12 B 00 00 00 00A 060A A GENERAL LIST OF AEROSPACE GROUND EQUIPMENT AGE AND TOOLS 12 B 12 10 01 00A 902A A FUEL SERVICING 12 B 28 00 00 00A 901A A FUEL MAINTENANCE PRACTICES 12 B 28 10 02 00A 901A A DRAIN VALVE MAINTENANCE PRACTICES Preliminary Requirements Required Conditions Table 2 Required Conditions Action Condition Data module Technical publication None PC 12 47E AMM Doc No 02300 ISSUE ...

Page 345: ...WARNING BE CAREFUL WHEN YOU DO MAINTENANCE ON THE FUEL SYSTEM IF YOU GET AIRCRAFT FUEL IN YOUR EYES YOU MUST FLUSH YOUR EYES WITH CLEAN WATER AND SEEK MEDICAL HELP IMMEDIATELY IF YOU GET AIRCRAFT FUEL ON YOUR SKIN YOU MUST REMOVE ALL PROTECTIVE CLOTHING SOAKED IN FUEL FLUSH YOUR SKIN WITH CLEAN WATER AND USE SOAP AND WATER TO CLEAN YOUR SKIN FUEL IS DANGEROUS AND CAN CAUSE INJURY TO PERSONNEL CAUT...

Page 346: ...flange Figure 1 3 O ring Figure 1 2 and drain valve Figure 1 1 from the wing 2 5 Discard the O ring Figure 1 2 and drain valve Figure 1 1 3 Installation Drain Valves without a Replaceable O Ring 3 1 Install a new Drain valve Figure 1 1 into position on the wing 3 2 Install a newO ring Figure 1 2 into position around the drain valve Figure 1 1 3 3 Install the flange Figure 1 3 over the drain valve ...

Page 347: ...ING SHOWN RIGHT WING SIMILAR B 1 2 3 4 Figure 1 Drain Valve Removal Installation PC 12 47E AMM Doc No 02300 ISSUE 01 REVISION 26 MSN 545 1001 1719 1721 1999 12 B AM 00 00 00 I UNCLASSIFIED Effectivity All 12 B 28 10 02 00A 920A A UNCLASSIFIED 2021 12 04 Page 4 ...

Page 348: ...red Conditions Action Condition Data module Technical publication None PC 12 47E AMM Doc No 02300 ISSUE 01 REVISION 26 MSN 545 1001 1719 1721 1999 12 B AM 00 00 00 I UNCLASSIFIED Effectivity All 12 B 28 10 02 00A 920A A End of data module UNCLASSIFIED 2021 12 04 Page 5 ...

Page 349: ...C 12 47E AMM Doc No 02300 ISSUE 01 REVISION 26 MSN 545 1001 1719 1721 1999 12 B AM 00 00 00 I UNCLASSIFIED Intentionally left blank Effectivity All 12 B 28 10 02 00A 920A A UNCLASSIFIED 2021 12 04 Page 6 ...

Page 350: ...Title 12 B 00 00 00 00A 060A A GENERAL LIST OF AEROSPACE GROUND EQUIPMENT AGE AND TOOLS 12 B 20 31 00 00A 070A A STANDARD PRACTICES CONSUMABLE MATERIALS LIST 12 B 24 00 00 00A 901A A ELECTRICAL POWER MAINTENANCE PRACTICES 12 B 30 10 00 00A 255A A AIRFOIL DE ICE BOOTS PURGE 12 B 30 10 02 00A 901A A EJECTOR FLOW CONTROL VALVE MAINTENANCE PRAC TICES Preliminary Requirements Required Conditions Table ...

Page 351: ...ditions WARNING BE CAREFUL WHEN YOU USE THE CONSUMABLE MATERIALS OBEY THE MANUFACTURERS HEALTH AND SAFETY INSTRUCTIONS AND ALL THE APPLICABLE LOCAL INSTRUCTIONS CONSUMABLE MATERIALS CAN BE DANGEROUS AND CAN CAUSE DEATH OR INJURY TO PERSONNEL AND OR DAMAGE TO EQUIPMENT Note To identify the AGE and tools used in this procedure refer to the list of AGE and tools TEM 12 B 00 00 00 00A 060A A Note To i...

Page 352: ...the solenoid Figure 2 2 of the wing outboard top ejector flow control valve for approximately one minute Make sure no air bubbles show on the pressurized area of the left and right outboard top boots 2 2 4 Push in and hold the solenoid Figure 2 3 of the wing outboard bottom ejector flow control valve for approximately one minute Make sure no air bubbles show on the pressurized area of the left and...

Page 353: ... PROTECTION window is ON 3 2 3 3 The horizontal stabilizer de ice boots pressurize for 8 seconds 1 second then fully de pressurize 3 2 3 4 The lower part of the inboard de ice boots on the wings pressurize for 8 seconds 1 second then fully de pressurize 3 2 3 5 The upper part of the inboard de ice boots on the wings pressurize for 8 seconds 1 second then fully de pressurize 3 2 3 6 The lower part ...

Page 354: ...nd air supply to 1 4 bar 20 psi 3 2 13 Set the BOOTS switch to 1 MIN 3 2 14 Wait for three full cycles 3 minutes 30 seconds 3 2 15 The DE ICE BOOTS caution message on the CAS display does not come on 3 2 16 Set the BOOTS switch to OFF 3 2 17 Set the ground air supply to OFF 3 2 18 Set the BOOTS switch to 3 MIN 3 2 19 Make sure the BOOTS advisory caption on the lower MFD ICE PROTECTION window is ON...

Page 355: ...equipment tools and materials from the work area Make sure that the work area is clean 4 2 Close the engine cowling 43AR 4 3 Refer to manufacturers instructions and apply a layer of Protective coating Pt No P08 027 to the de ice boots 4 4 Remove the safety clip and close this circuit breaker STARTER ESSENTIAL BUS PC 12 47E AMM Doc No 02300 ISSUE 01 REVISION 26 MSN 545 1001 1719 1721 1999 12 B AM 0...

Page 356: ...487 A 03 1 Figure 1 Airfoil De ice System Adjustment Test PC 12 47E AMM Doc No 02300 ISSUE 01 REVISION 26 MSN 545 1001 1719 1721 1999 12 B AM 00 00 00 I UNCLASSIFIED Effectivity All 12 B 30 10 00 00A 903A A UNCLASSIFIED 2021 12 04 Page 7 ...

Page 357: ...RD TOP LEFT RIGHT INBOARD BOTTOM TO WING B C A B 12 A 301000 A S4080 00488 A 03 1 C A 7 3 2 5 4 1 6 Figure 2 Leak Test Of The De ice Boots PC 12 47E AMM Doc No 02300 ISSUE 01 REVISION 26 MSN 545 1001 1719 1721 1999 12 B AM 00 00 00 I UNCLASSIFIED Effectivity All 12 B 30 10 00 00A 903A A UNCLASSIFIED 2021 12 04 Page 8 ...

Page 358: ...red Conditions Action Condition Data module Technical publication None PC 12 47E AMM Doc No 02300 ISSUE 01 REVISION 26 MSN 545 1001 1719 1721 1999 12 B AM 00 00 00 I UNCLASSIFIED Effectivity All 12 B 30 10 00 00A 903A A End of data module UNCLASSIFIED 2021 12 04 Page 9 ...

Page 359: ... 12 47E AMM Doc No 02300 ISSUE 01 REVISION 26 MSN 545 1001 1719 1721 1999 12 B AM 00 00 00 I UNCLASSIFIED Intentionally left blank Effectivity All 12 B 30 10 00 00A 903A A UNCLASSIFIED 2021 12 04 Page 10 ...

Page 360: ...0 00A 901A A ELECTRICAL POWER MAINTENANCE PRACTICES Required Conditions Table 2 Required Conditions Action Condition Data module Technical publication None Support equipment Table 3 Support equipment Name Identifications References Qty Reference Remark None Supplies Table 4 Supplies Name Identifications References Qty Reference Remark None PC 12 47E AMM Doc No 02300 ISSUE 01 REVISION 26 MSN 545 10...

Page 361: ... switch to ON 2 7 On the lower MFD display make sure that the green PUSHER ICE MODE caption is ON 2 8 Set the ICE PROTECTION PROPELLER switch to OFF 2 9 On the lower MFD display make sure that the green PUSHER ICE MODE caption is OFF 2 10 On the left inner cross bar panel set the ICE PROTECTION INERT SEP switch to CLOSED 2 11 Visually make sure that the bypass door fully closes 2 12 On the left in...

Page 362: ...aker PROP DE ICE MAIN BUS 2 20 De energize the aircraft electrical system refer to AMM 12 B 24 00 00 00A 901A A Requirements after job completion Required Conditions Table 6 Required Conditions Action Condition Data module Technical publication None PC 12 47E AMM Doc No 02300 ISSUE 01 REVISION 26 MSN 545 1001 1719 1721 1999 12 B AM 00 00 00 I UNCLASSIFIED Effectivity All 12 B 30 20 00 00A 903A A E...

Page 363: ...C 12 47E AMM Doc No 02300 ISSUE 01 REVISION 26 MSN 545 1001 1719 1721 1999 12 B AM 00 00 00 I UNCLASSIFIED Intentionally left blank Effectivity All 12 B 30 20 00 00A 903A A UNCLASSIFIED 2021 12 04 Page 4 ...

Page 364: ...COMPARTMENT TRIM REMOVAL INSTALLATION 12 B 30 40 00 00A 903A A WINDSHIELD DE ICE SYSTEM ADJUSTMENT TEST 12 B 30 40 01 00A 920A A WINDSHIELD DE ICE CONTROLLER REMOVAL INSTAL LATION Preliminary Requirements Required Conditions Table 2 Required Conditions Action Condition Data module Technical publication None Support equipment Table 3 Support equipment Name Identifications References Qty Reference R...

Page 365: ...it becomes necessary to replace the windshield 2 Check of the Windshield De Ice System 2 1 Remove the left or right bottom sidewall panel refer to AMM 12 B 25 10 03 00A 920A A 2 2 De energize the aircraft electrical system refer to AMM 12 B 24 00 00 00A 901A A 2 3 Disconnect the electrical connector A111P1 from the pilot de ice controller and A112P1 from the copilot de ice controller 2 4 Use the M...

Page 366: ...uity through the pilot and copilot windshield temperature sensors connect the electrical connector A111P1 to the pilot de ice controller and the electrical connector A112P1 to the co pilot de ice controller 2 9 Do the operational test of the windshield de ice system refer to AMM 12 B 30 40 00 00A 903A A to identify which windshield de ice system is defective 2 10 If the pilot windshield de ice is ...

Page 367: ...C 12 47E AMM Doc No 02300 ISSUE 01 REVISION 26 MSN 545 1001 1719 1721 1999 12 B AM 00 00 00 I UNCLASSIFIED Intentionally left blank Effectivity All 12 B 30 40 00 00A 901A A UNCLASSIFIED 2021 12 04 Page 4 ...

Page 368: ...AEROSPACE GROUND EQUIPMENT AGE AND TOOLS 12 B 20 31 00 00A 070A A STANDARD PRACTICES CONSUMABLE MATERIALS LIST 12 B 24 00 00 00A 901A A ELECTRICAL POWER MAINTENANCE PRACTICES Preliminary Requirements Required Conditions Table 2 Required Conditions Action Condition Data module Technical publication None Support equipment Table 3 Support equipment Name Identifications References Qty Reference Remark...

Page 369: ... OPERATE THE PROPELLER DE ICE SYSTEM ABOVE 38 C 100 F AMBIENT TEMPERATURE FOR MORE THAN 5 MINUTES LET THE DE ICE BOOTS BECOME COOL BEFORE YOU DO THE TEST AGAIN Note To identify the AGE and tools used in this procedure refer to the List of AGE and Tools TEM 12 B 00 00 00 00A 060A A Note To identify the consumable items used in this procedure refer to the Consumable Materials List AMM 12 B 20 31 00 ...

Page 370: ...cuit breaker hold open Pt No T12 030 on this circuit breaker STARTER ESSENTIAL BUS 2 1 6 Energize the aircraft electrical system refer to AMM 12 B 24 00 00 00A 901A A 2 2 Procedure Note The aircraft is on the ground weight on wheels for this procedure Note The CAS PROPELLER DEICE caution message has a time delay of 20 seconds from when the DE ICING PROP switch is set to ON 2 2 1 Set the ICE PROTEC...

Page 371: ...est set 2 2 16 Set the ICE PROTECTION PROPELLER switch to ON 2 2 17 On the lower MFD make sure that The CAS PROPELLER DE ICE caution message comes ON The ICE PROTECTION window PROPELLER green caption is OFF 2 2 18 Set and hold the AIR GND switch to AIR 2 2 19 On the lower MFD make sure that The CAS PROPELLER DE ICE caution message is OFF The ICE PROTECTION window PROPELLER green caption is ON 2 2 ...

Page 372: ... from the propeller de ice test set 3 1 10 Connect a Decade resistance box Pt No Local supply or an OAT simulator Pt No T30 005 between sockets G and H identified as DE ICE TIMER on the propeller de ice test set 3 1 11 Install a jumper between socket H and J identified as DE ICE TIMER on the propeller de ice test set Note The output B from the OAT sensor is spliced and goes to the Prop De Ice Time...

Page 373: ...e ICE PROTECTION PROPELLER switch to ON 3 2 13 On the lower MFD make sure that The CAS PROPELLER DE ICE caution message is OFF The ICE PROTECTION window PROPELLER green caption is ON 3 2 14 Make sure that the propeller de icing boots become warm in pairs and that they follow this mode 2 heating sequence TIME INTERVALS SECONDS PROPELLER BLADES 1 AND 3 HEATING 45 ON 135 OFF PROPELLER BLADES 2 AND 4 ...

Page 374: ...ROPELLER switch to ON 3 2 33 On the lower MFD make sure that after approximately 20 seconds The CAS PROPELLER DE ICE caution message comes ON The ICE PROTECTION window PROPELLER green caption is OFF 3 2 34 Set the ICE PROTECTION PROPELLER switch to OFF 3 2 35 Disconnect the right decade resistance box or the OAT simulator from sockets G and H on the propeller de ice test set 3 2 36 Disconnect the ...

Page 375: ... A 3 2 51 Remove the jumper wire from electrical connector S045P 3 2 52 Connect electrical connector S045P to the engine oil pressure switch 3 2 53 Disconnect the Maintenance box from the maintenance panel 3 2 54 Do the operational test procedure refer to Step 2 2 4 Close Up 4 1 Remove all the equipment tools and materials from the work area Make sure that the work area is clean 4 2 Close access p...

Page 376: ... 00 00A 060A A GENERAL LIST OF AEROSPACE GROUND EQUIPMENT AGE AND TOOLS 12 B 20 31 00 00A 070A A STANDARD PRACTICES CONSUMABLE MATERIALS LIST 12 B 24 00 00 00A 901A A ELECTRICAL POWER MAINTENANCE PRACTICES 12 B 30 60 00 00A 420B A FIVE BLADED PROPELLER DE ICE SYSTEM FAULT ISO LATION PROCEDURE Preliminary Requirements Required Conditions Table 2 Required Conditions Action Condition Data module Tech...

Page 377: ...OCK IS NOT CAUSING BURN MARKS ON THE SLIP RINGS CAUTION DO NOT ALLOW THE PROPELLER DE ICE BOOTS TO BE HEATED FOR MORE THAN 10 SECONDS YOU CAN CAUSE SEVERE DAMAGE TO THE COMPOSITE BLADES IF THE DE ICE BOOTS ARE HEATED FOR MORE THAN 10 SECONDS CONTACT HARTZELL PRODUCT SUPPORT CAUTION WAIT FOR 2 MINUTES BETWEEN TESTS TO ALLOW THE PROPELLER BLADES TO COOL BEFORE YOU DO THE OPERATIONAL TEST AGAIN Note ...

Page 378: ...imer A030 and connect the Propeller de ice test set Pt No T30 010 between the timer and the aircraft wiring 2 1 6 Make sure that all the jumpers are installed on the propeller de ice test set 2 1 7 Remove jumpers D E and F from the propeller de ice test set 2 1 8 Connect a Decade resistance box Pt No Local supply or an OAT simulator Pt No T30 005 between sockets D and E identified as DE ICE TIMER ...

Page 379: ...engine is not running except during the system self test 2 2 6 Set the maintenance box AIR GND switch to AIR for no longer than 10 seconds 2 2 7 On the lower MFD make sure The CAS PROPELLER DE ICE caution message is off The ICE PROTECTION window PROPELLER green caption is ON 2 2 8 Use your hand to make sure that all five de ice boots are heated on the outboard sector 2 2 9 Set the ICE PROTECTION P...

Page 380: ...ove all the equipment tools and materials from the work area Make sure that the work area is clean 3 7 Install the access panel 12QZ 3 8 Close the engine cowling 43AR 3 9 Remove the safety clip and close the circuit breaker STARTER ESSENTIAL BUS Requirements after job completion Required Conditions Table 6 Required Conditions Action Condition Data module Technical publication None PC 12 47E AMM Do...

Page 381: ...C 12 47E AMM Doc No 02300 ISSUE 01 REVISION 26 MSN 545 1001 1719 1721 1999 12 B AM 00 00 00 I UNCLASSIFIED Intentionally left blank Effectivity All 12 B 30 60 00 00A 903D A UNCLASSIFIED 2021 12 04 Page 6 ...

Page 382: ...ences Table 1 References Data module Technical publication Title 12 B 31 30 01 00A 903A A RECORDERS LDR ADJUSTMENT TEST Description 1 General Refer to Fig 1 The Lightweight Data Recorder LDR is an L3 Model LDR1000 airborne crash survivable recording device which automatically records both cockpit voice and aircraft flight data when electrical power is connected The LDR was previously known as the ...

Page 383: ... ON or has a fault the LED will not come on when the CVFDR TEST rocker switch is operated A CAM Installed on the lower sidewall right hand panel in the flight compartment A 5A CVFDR POWER Circuit Breaker CB mounted on a bracket installed on frame 37 adjacent to the LDR The LDR is housed in an 203 20 mm 8 in deep 61 mm 2 40 in wide and 125 22 mm 4 93 in tall case that is painted international orang...

Page 384: ... header and footer information for every 4 frames of 256 words each Flight data is stored in a Packed Binary Raw Data Output File Type The packed flight data stores four 12 bit data words in three 16 bit words For ARINC 717 data each consecutive 48 16 bit words form a subframe Each flight data dat file will contain a maximum of one hour of data 3 4 Status Monitoring and Fault Log Management Built ...

Page 385: ... the system clock resets on power up or that the custom settings are lost then it is possible that the battery may need replacement To do this the LDR must be returned to the manufacturer PC 12 47E AMM Doc No 02300 ISSUE 01 REVISION 26 MSN 545 1001 1719 1721 1999 12 B AM 00 00 00 I UNCLASSIFIED Effectivity All 12 B 31 30 01 00A 040A A UNCLASSIFIED 2021 12 04 Page 4 ...

Page 386: ...O COPILOT AUXILIARY PANEL LDR UNIT INTERFACE CIRCUITS PROCESSING MODULE CSMU LAPTOP 28V DC SUPPLY CVFDR TEST LED Figure 1 LDR Block Diagram PC 12 47E AMM Doc No 02300 ISSUE 01 REVISION 26 MSN 545 1001 1719 1721 1999 12 B AM 00 00 00 I UNCLASSIFIED Effectivity All 12 B 31 30 01 00A 040A A UNCLASSIFIED 2021 12 04 Page 5 ...

Page 387: ... 45 CONNECTOR AV CONNECTORS CAM C V F D R P O W E R C B 3 6 2 CVFDR LDR POWER CIRCUIT BREAKER Figure 2 LDR Equipment Location PC 12 47E AMM Doc No 02300 ISSUE 01 REVISION 26 MSN 545 1001 1719 1721 1999 12 B AM 00 00 00 I UNCLASSIFIED Effectivity All 12 B 31 30 01 00A 040A A UNCLASSIFIED 2021 12 04 Page 6 ...

Page 388: ...CVERASE CVFDRTEST Figure 3 CV ERASE CVFDR TEST Switch and CVFDR LED PC 12 47E AMM Doc No 02300 ISSUE 01 REVISION 26 MSN 545 1001 1719 1721 1999 12 B AM 00 00 00 I UNCLASSIFIED Effectivity All 12 B 31 30 01 00A 040A A End of data module UNCLASSIFIED 2021 12 04 Page 7 ...

Page 389: ...C 12 47E AMM Doc No 02300 ISSUE 01 REVISION 26 MSN 545 1001 1719 1721 1999 12 B AM 00 00 00 I UNCLASSIFIED Intentionally left blank Effectivity All 12 B 31 30 01 00A 040A A UNCLASSIFIED 2021 12 04 Page 8 ...

Page 390: ...00 00A 060A A GENERAL LIST OF AEROSPACE GROUND EQUIPMENT AGE AND TOOLS 12 B 06 20 00 00A 040A A ACCESS PROVISION DESCRIPTION 12 B 20 31 00 00A 070A A STANDARD PRACTICES CONSUMABLE MATERIALS LIST 12 B 31 30 01 00A 903A A RECORDERS LDR ADJUSTMENT TEST Preliminary Requirements Required Conditions Table 2 Required Conditions Action Condition Data module Technical publication None PC 12 47E AMM Doc No ...

Page 391: ...umable items used in this procedure refer to the Consumable Materials List AMM 12 B 20 31 00 00A 070A A Procedure 1 Removal 1 1 Open the access panel 31AB refer to AMM 12 B 06 20 00 00A 040A A 1 2 On the CVFDR Panel in the battery bay open and install a Safety clip circuit breaker hold open Pt No T12 030 on the following circuit breaker CVFDR POWER 1 3 Make sure that the ESD wrist strap Pt No Loca...

Page 392: ...2 022 Figure 1 1 2 6 Connect the DB 50 connector Figure 1 5 to the LDR Figure 1 4 2 7 Hand tighten the two DB 50 connector screws Figure 1 6 2 8 On the CVFDR Panel in the battery bay remove the safety clip and close the following circuit breaker CVFDR POWER 3 Close Up 3 1 Do an operational test of the LDR refer to AMM 12 B 31 30 01 00A 903A A 3 2 Remove all the equipment tools and materials from t...

Page 393: ... 3 2 3 5 6 6 7 8 9 B C V F D R P O W E R C B 3 6 2 Figure 1 LDR Removal Installation PC 12 47E AMM Doc No 02300 ISSUE 01 REVISION 26 MSN 545 1001 1719 1721 1999 12 B AM 00 00 00 I UNCLASSIFIED Effectivity All 12 B 31 30 01 00A 920A A UNCLASSIFIED 2021 12 04 Page 4 ...

Page 394: ...red Conditions Action Condition Data module Technical publication None PC 12 47E AMM Doc No 02300 ISSUE 01 REVISION 26 MSN 545 1001 1719 1721 1999 12 B AM 00 00 00 I UNCLASSIFIED Effectivity All 12 B 31 30 01 00A 920A A End of data module UNCLASSIFIED 2021 12 04 Page 5 ...

Page 395: ...C 12 47E AMM Doc No 02300 ISSUE 01 REVISION 26 MSN 545 1001 1719 1721 1999 12 B AM 00 00 00 I UNCLASSIFIED Intentionally left blank Effectivity All 12 B 31 30 01 00A 920A A UNCLASSIFIED 2021 12 04 Page 6 ...

Page 396: ... LIST OF AEROSPACE GROUND EQUIPMENT AGE AND TOOLS 12 B 06 20 00 00A 040A A ACCESS PROVISION DESCRIPTION 12 B 20 31 00 00A 070A A STANDARD PRACTICES CONSUMABLE MATERIALS LIST 12 B 25 10 01 00A 920A A FLIGHT COMPARTMENT CREW SEATS REMOVAL IN STALLATION 12 B 25 10 03 00A 920A A FLIGHT COMPARTMENT TRIM REMOVAL INSTALLATION 12 B 25 21 07 00A 920A A TOILET COMPARTMENT REMOVAL INSTALLATION 12 B 31 30 01 ...

Page 397: ...and Tools TEM 12 B 00 00 00 00A 060A A Note To identify the consumable items used in this procedure refer to the Consumable Materials List AMM 12 B 20 31 00 00A 070A A Procedure 1 Removal 1 1 Open the access panel 31AB refer to AMM 12 B 06 20 00 00A 040A A 1 2 In the battery bay open and install a Safety clip circuit breaker hold open Pt No T12 030 on the following circuit breaker CVFDR PWR CB362 ...

Page 398: ...t 2 Installation 2 1 Hold the CAM Figure 2 4 in position on the right bottom sidewall 21MZ and install the four screws Figure 2 3 2 2 Connect the CAM electrical connector A118P Figure 2 2 to the aircraft electrical connector A118J Figure 2 1 2 3 Install the right bottom side wall 21MZ Figure 1 3 refer to AMM 12 B 25 10 03 00A 920A A 2 4 Install the copilots seat refer to AMM 12 B 25 10 01 00A 920A...

Page 399: ...02 1 FRAME 12 FRAME 12 1 A 2 3 Figure 1 CAM Location PC 12 47E AMM Doc No 02300 ISSUE 01 REVISION 26 MSN 545 1001 1719 1721 1999 12 B AM 00 00 00 I UNCLASSIFIED Effectivity All 12 B 31 30 02 00A 920A A UNCLASSIFIED 2021 12 04 Page 4 ...

Page 400: ... 12 B FRAME 12 B A 4 3 3 2 1 Figure 2 CAM Removal Installation PC 12 47E AMM Doc No 02300 ISSUE 01 REVISION 26 MSN 545 1001 1719 1721 1999 12 B AM 00 00 00 I UNCLASSIFIED Effectivity All 12 B 31 30 02 00A 920A A UNCLASSIFIED 2021 12 04 Page 5 ...

Page 401: ...red Conditions Action Condition Data module Technical publication None PC 12 47E AMM Doc No 02300 ISSUE 01 REVISION 26 MSN 545 1001 1719 1721 1999 12 B AM 00 00 00 I UNCLASSIFIED Effectivity All 12 B 31 30 02 00A 920A A End of data module UNCLASSIFIED 2021 12 04 Page 6 ...

Page 402: ... 00A 106A A LIST OF SOFTWARE 12 B 24 00 00 00A 901A A ELECTRICAL POWER MAINTENANCE PRACTICES 12 B 31 41 00 00A 903A A MODULAR AVIONICS UNIT ADJUSTMENT TEST 12 B 31 41 00 00A 920A A MODULAR AVIONICS UNIT REMOVAL INSTALLATION 12 B 45 45 00 00A 550A A CENTRAL MAINTENANCE SYSTEM INTERFACE LOAD SOFTWARE Preliminary Requirements Required Conditions Table 2 Required Conditions Action Condition Data modul...

Page 403: ...UTLET SCREEN THAT COVERS THE MAU FANS CAN BE DAMAGED EASILY BE CAREFUL NOT TO DAMAGE THE SCREEN WHEN YOU REMOVE OR INSTALL THE MAU OR A FAN Procedure 1 General 1 1 MAU Modules This is a general procedure for these different types of replaceable modules in the MAU Figure 1 1 Power Supply PS module the applicable MAU slots are mechanically keyed for a PS module only Network Interface Controller NIC ...

Page 404: ...E BACKSHELLS AND THE MODULES Disconnect the backshell Figure 1 7 from the module Figure 1 2 to be removed as follows 2 3 1 Turn the captive bolt Figure 1 8 on the backshell Figure 1 7 counterclockwise until it disengages from the module Figure 1 2 2 3 2 Tilt the backshell Figure 1 7 away from the top of the module Figure 1 2 until the curved alignment pin Figure 1 9 disengages from the alignment h...

Page 405: ...4 1 3 3 4 Make sure that the edges of the module Figure 1 2 are correctly aligned with the upper and lower slot guides in the MAU Figure 1 1 3 3 5 Carefully push the module Figure 1 2 in its slot until the jack screws Figure 1 5 engage with the MAU Figure 1 1 3 3 6 CAUTION THE MODULE AND MAU WILL BE DAMAGED IF YOU TIGHTEN THE JACK SCREWS ON A MISALIGNED CARD OR IF YOU DO NOT TIGHTEN THE JACK SCREW...

Page 406: ...0 00A 903A A 3 6 Do the MAU Installation procedure refer to AMM 12 B 31 41 00 00A 920A A PC 12 47E AMM Doc No 02300 ISSUE 01 REVISION 26 MSN 545 1001 1719 1721 1999 12 B AM 00 00 00 I UNCLASSIFIED Effectivity All 12 B 31 42 00 00A 920A A UNCLASSIFIED 2021 12 04 Page 5 ...

Page 407: ... C B REFERENCE ARROW 2 1 3 5 6 7 8 9 10 4 Figure 1 MAU Module Removal Installation Example PC 12 47E AMM Doc No 02300 ISSUE 01 REVISION 26 MSN 545 1001 1719 1721 1999 12 B AM 00 00 00 I UNCLASSIFIED Effectivity All 12 B 31 42 00 00A 920A A UNCLASSIFIED 2021 12 04 Page 6 ...

Page 408: ...red Conditions Action Condition Data module Technical publication None PC 12 47E AMM Doc No 02300 ISSUE 01 REVISION 26 MSN 545 1001 1719 1721 1999 12 B AM 00 00 00 I UNCLASSIFIED Effectivity All 12 B 31 42 00 00A 920A A End of data module UNCLASSIFIED 2021 12 04 Page 7 ...

Page 409: ...C 12 47E AMM Doc No 02300 ISSUE 01 REVISION 26 MSN 545 1001 1719 1721 1999 12 B AM 00 00 00 I UNCLASSIFIED Intentionally left blank Effectivity All 12 B 31 42 00 00A 920A A UNCLASSIFIED 2021 12 04 Page 8 ...

Page 410: ...12 B 07 10 00 00A 901A A JACKING MAINTENANCE PRACTICES 12 B 20 31 00 00A 070A A STANDARD PRACTICES CONSUMABLE MATERIALS LIST 12 B 24 00 00 00A 901A A ELECTRICAL POWER MAINTENANCE PRACTICES 12 B 32 30 00 00A 903B A EXTENSION AND RETRACTION ELECTRO MECHANICAL LANDING GEAR ADJUSTMENT TEST 12 B 32 40 01 00A 920A A MAIN WHEEL REMOVAL INSTALLATION Preliminary Requirements Required Conditions Table 2 Req...

Page 411: ...FT ELECTRICAL POWER CAN CAUSE INJURY OR DEATH AND OR DAMAGE TO EQUIPMENT WARNING BEFORE YOU APPLY ELECTRICAL POWER TO THE AIRCRAFT ALWAYS MAKE SURE THAT THE LANDING GEAR SELECTOR HANDLE AND THE LANDING GEAR POSITION AGREE IF YOU DO NOT THE LANDING GEAR CAN RETRACT THIS CAN CAUSE INJURY OR DEATH TO PERSONNEL AND OR DAMAGE TO THE AIRCRAFT Note To identify the consumable items used in this procedure ...

Page 412: ...TH TO PERSONNEL AND OR DAMAGE TO THE AIRCRAFT Remove the safety clip and close this circuit breaker LDG GEAR PWR RH POWER JUNCTION BOX 2 2 3 Retract the landing gear 2 2 4 Make sure the MLG leg fully retracts 2 2 5 Open and install a Safety clip circuit breaker hold open Pt No T12 030 on this circuit breaker LDG GEAR PWR RH POWER JUNCTION BOX 2 2 6 Adjust the rod Figure 1 9 to get a gap of 0 004 i...

Page 413: ...elector handle is set to DOWN 3 1 5 Energize the aircraft electrical system refer to AMM 12 B 24 00 00 00A 901A A 3 1 6 Set the PCL to MAX 3 1 7 Set the flaps to zero degrees 3 2 Procedure Note This procedure is applicable to the left and right MLG door proximity switches 3 2 1 Remove the lockwire from the two locknuts Figure 1 12 3 2 2 Loosen the two locknuts Figure 1 12 3 2 3 WARNING IF THE EMER...

Page 414: ... aircraft to the ground and remove the jacks refer to AMM 12 B 07 10 00 00A 901A A 4 Adjustment Of The Weight On Wheels Proximity Switches 4 1 Preparation This procedure is applicable to the left and right weight on wheels proximity switches 4 1 1 Lift the aircraft clear of the ground on jacks refer to AMM 12 B 07 10 00 00A 901A A 4 1 2 Open and install a Safety clip circuit breaker hold open Pt N...

Page 415: ...GE TO THE AIRCRAFT Remove the safety clip and close this circuit breaker LDG GEAR PWR RH POWER JUNCTION BOX 4 2 9 Do the functional test of the extension and retraction system refer to AMM 12 B 32 30 00 00A 903B A 4 3 Close Up 4 3 1 Remove all the equipment tools and materials from the work area Make sure that the work area is clean 4 3 2 Lower the aircraft to the ground and remove the jacks refer...

Page 416: ...1 1 0 5 mm 0 02 in 0 1 mm 0 004 in 2 mm 0 079 in Figure 1 Electro Mechanical Landing Gear Adjustment Test PC 12 47E AMM Doc No 02300 ISSUE 01 REVISION 26 MSN 545 1001 1719 1721 1999 12 B AM 00 00 00 I UNCLASSIFIED Effectivity All 12 B 32 10 00 00A 903B A UNCLASSIFIED 2021 12 04 Page 7 ...

Page 417: ...red Conditions Action Condition Data module Technical publication None PC 12 47E AMM Doc No 02300 ISSUE 01 REVISION 26 MSN 545 1001 1719 1721 1999 12 B AM 00 00 00 I UNCLASSIFIED Effectivity All 12 B 32 10 00 00A 903B A End of data module UNCLASSIFIED 2021 12 04 Page 8 ...

Page 418: ...IST OF AEROSPACE GROUND EQUIPMENT AGE AND TOOLS 12 B 07 10 00 00A 901A A JACKING MAINTENANCE PRACTICES 12 B 20 31 00 00A 070A A STANDARD PRACTICES CONSUMABLE MATERIALS LIST 12 B 24 00 00 00A 901A A ELECTRICAL POWER MAINTENANCE PRACTICES 12 B 32 00 00 00A 901B A LANDING GEAR ELECTRO MECHANICAL MAINTE NANCE PRACTICES 12 B 32 10 00 00A 903B A MAIN LANDING GEAR AND DOORS ELECTRO MECHANI CAL LANDING GE...

Page 419: ...JUSTMENT TEST 12 B 33 41 01 00A 920B A LED LANDING LIGHT REMOVAL INSTALLATION Preliminary Requirements Required Conditions Table 2 Required Conditions Action Condition Data module Technical publication None Support equipment Table 3 Support equipment Name Identifications References Qty Reference Remark Safety clip Circuit breaker hold open Part T12 030 AR Feeler gage Part Local supply AR Supplies ...

Page 420: ...M 12 B 00 00 00 00A 060A A Note To identify the consumables used in this procedure refer to the Consumable Materials List AMM 12 B 20 31 00 00A 070A A Procedure 1 Removal Note This procedure is applicable to the left and right Main Landing Gear MLG Note A minimum of two persons is recommended for this procedure 1 1 CAUTION WHEN THE EMERGENCY GEAR EXTENSION SYSTEM IS OPERATED AN ABNORMAL LANDING GE...

Page 421: ...3 16 1 12 Hold the folding strut assembly Figure 3 15 and MLG drag link away from the work area 1 13 If necessary remove the shock absorber refer to AMM 12 B 32 10 03 00A 920B A 1 14 Disconnect the brake pressure pipe Figure 2 6 from the MLG 1 14 1 Remove the screws Figure 2 1 the washers Figure 2 2 and move the brake pressure pipe Figure 2 6 away from the bracket Figure 2 4 1 14 2 Remove the clam...

Page 422: ... for this procedure 2 1 Pre Installation Procedure 2 1 1 Put the items that follow in position on the MLG leg fitting The bush Figure 3 35 The special washer Figure 3 30 The washers Figure 3 28 and Figure 3 29 2 1 2 Put the bolt Figure 3 27 through the MLG leg fitting and push the bolt Figure 3 27 hard against the washers Figure 3 28 and Figure 3 29 2 1 3 Use a Feeler gage Pt No Local supply to me...

Page 423: ...4 Make sure that the bush Figure 3 35 is installed in the front spar and that the hole in the bush aligns with the pin Figure 3 36 If the bush is not installed contact Pilatus Aircraft Ltd 2 2 5 Move the MLG leg Figure 3 16 forward until the bush Figure 3 35 is fully engaged on the pin Figure 3 36 2 2 6 Make sure that the trunnion Figure 3 22 is fully engaged in the rear spar then align the hole i...

Page 424: ...G 2 2 24 1 Remove the blanking caps from the connections of the brake pressure pipe Figure 2 6 and the elbow Figure 2 5 2 2 24 2 Connect the brake pressure pipe Figure 2 6 to the elbow connection Figure 2 5 2 2 24 3 Put the clamps Figure 2 3 in position on the brake pressure pipe Figure 2 6 2 2 24 4 Align the clamps Figure 2 3 with the bracket Figure 2 4 and install the washers Figure 2 2 and the ...

Page 425: ...rical system refer to AMM 12 B 24 00 00 00A 901A A 3 3 Set the flaps to zero degrees 3 4 WARNING MAKE SURE THAT THE AREA IS CLEAR OF PERSONNEL AND EQUIPMENT BEFORE YOU OPERATE THE LANDING GEAR THE LANDING GEAR MOVES QUICKLY AND CAN CAUSE INJURY TO PERSONNEL AND OR DAMAGE TO EQUIPMENT Set the handle of the landing gear control unit to DOWN 3 5 Make sure the landing gear is down 3 6 Open and install...

Page 426: ... and remove the jacks refer to AMM 12 B 07 10 00 00A 901A A PC 12 47E AMM Doc No 02300 ISSUE 01 REVISION 26 MSN 545 1001 1719 1721 1999 12 B AM 00 00 00 I UNCLASSIFIED Effectivity All 12 B 32 10 01 00A 920B A UNCLASSIFIED 2021 12 04 Page 9 ...

Page 427: ... 1 A A B 2 4 3 5 7 6 1 Figure 1 Main Landing Gear Door PC 12 47E AMM Doc No 02300 ISSUE 01 REVISION 26 MSN 545 1001 1719 1721 1999 12 B AM 00 00 00 I UNCLASSIFIED Effectivity All 12 B 32 10 01 00A 920B A UNCLASSIFIED 2021 12 04 Page 10 ...

Page 428: ...2 11 10 13 A LEFT SHOWN RIGHT SIMILAR Figure 2 Main Landing Gear Leg Removal Installation typical view PC 12 47E AMM Doc No 02300 ISSUE 01 REVISION 26 MSN 545 1001 1719 1721 1999 12 B AM 00 00 00 I UNCLASSIFIED Effectivity All 12 B 32 10 01 00A 920B A UNCLASSIFIED 2021 12 04 Page 11 ...

Page 429: ...TION G G 37 22 38 37 37 27 29 X 35 Y 30 28 31 SECTION H H 38 32 33 34 36 G H G H Figure 3 Main Landing Gear Leg Removal Installation PC 12 47E AMM Doc No 02300 ISSUE 01 REVISION 26 MSN 545 1001 1719 1721 1999 12 B AM 00 00 00 I UNCLASSIFIED Effectivity All 12 B 32 10 01 00A 920B A UNCLASSIFIED 2021 12 04 Page 12 ...

Page 430: ...ed Conditions Action Condition Data module Technical publication None PC 12 47E AMM Doc No 02300 ISSUE 01 REVISION 26 MSN 545 1001 1719 1721 1999 12 B AM 00 00 00 I UNCLASSIFIED Effectivity All 12 B 32 10 01 00A 920B A End of data module UNCLASSIFIED 2021 12 04 Page 13 ...

Page 431: ... 12 47E AMM Doc No 02300 ISSUE 01 REVISION 26 MSN 545 1001 1719 1721 1999 12 B AM 00 00 00 I UNCLASSIFIED Intentionally left blank Effectivity All 12 B 32 10 01 00A 920B A UNCLASSIFIED 2021 12 04 Page 14 ...

Page 432: ...le 12 B 07 10 00 00A 901A A JACKING MAINTENANCE PRACTICES 12 B 32 00 00 00A 901B A LANDING GEAR ELECTRO MECHANICAL MAINTE NANCE PRACTICES 12 B 32 10 00 00A 903B A MAIN LANDING GEAR AND DOORS ELECTRO MECHANI CAL LANDING GEAR ADJUSTMENT TEST 12 B 32 30 00 00A 903B A EXTENSION AND RETRACTION ELECTRO MECHANICAL LANDING GEAR ADJUSTMENT TEST Preliminary Requirements Required Conditions Table 2 Required ...

Page 433: ...ircuit breaker hold open Pt No T12 030 on this circuit breaker LDG GEAR PWR RH POWER JUNCTION BOX 2 4 Remove the nut Figure 1 13 washer Figure 1 12 bush Figure 1 9 and bolt Figure 1 8 and disconnect the rod Figure 1 14 from the fitting Figure 1 10 2 5 If needed remove the bush Figure 1 11 2 6 Remove and discard the cotter pins Figure 1 5 and Figure 1 16 2 7 Remove the nuts Figure 1 4 and Figure 1 ...

Page 434: ... 14 to the fitting Figure 1 10 with the bush Figure 1 9 bolt Figure 1 8 washer Figure 1 12 and nut Figure 1 13 3 8 Safety the nuts Figure 1 4 and Figure 1 17 with new Cotter pin Figure 1 5 and Figure 1 16 3 9 Remove the safety clip and close the circuit breaker LDG GEAR PWR RH POWER JUNCTION BOX 3 10 Do the rigging of the main landing gear doors refer to AMM 12 B 32 10 00 00A 903B A 3 11 Do the fu...

Page 435: ... 16 17 18 19 20 21 32104 Figure 1 Main Landing Gear Door Removal Installation PC 12 47E AMM Doc No 02300 ISSUE 01 REVISION 26 MSN 545 1001 1719 1721 1999 12 B AM 00 00 00 I UNCLASSIFIED Effectivity All 12 B 32 10 02 00A 920B A UNCLASSIFIED 2021 12 04 Page 4 ...

Page 436: ...red Conditions Action Condition Data module Technical publication None PC 12 47E AMM Doc No 02300 ISSUE 01 REVISION 26 MSN 545 1001 1719 1721 1999 12 B AM 00 00 00 I UNCLASSIFIED Effectivity All 12 B 32 10 02 00A 920B A End of data module UNCLASSIFIED 2021 12 04 Page 5 ...

Page 437: ...C 12 47E AMM Doc No 02300 ISSUE 01 REVISION 26 MSN 545 1001 1719 1721 1999 12 B AM 00 00 00 I UNCLASSIFIED Intentionally left blank Effectivity All 12 B 32 10 02 00A 920B A UNCLASSIFIED 2021 12 04 Page 6 ...

Page 438: ...0A 060A A GENERAL LIST OF AEROSPACE GROUND EQUIPMENT AGE AND TOOLS 12 B 07 10 00 00A 901A A JACKING MAINTENANCE PRACTICES 12 B 12 10 04 00A 902A A TIRES SERVICING 12 B 20 31 00 00A 070A A STANDARD PRACTICES CONSUMABLE MATERIALS LIST 12 B 32 00 00 00A 901A A LANDING GEAR HYDRAULIC MAINTENANCE PRACTI CES 12 B 32 00 00 00A 901B A LANDING GEAR ELECTRO MECHANICAL MAINTE NANCE PRACTICES PC 12 47E AMM Do...

Page 439: ...art P04 031 AR Anti seize compound Part P04 010 AR Spares Table 5 Spares Name Identifications References Qty Reference Remark Cotter pin CSN 32 10 00 02 020 AR MSN 1001 1299 1301 1450 Cotter pin CSN 32 10 01 02E 020 AR MSN 1300 1451 1719 1721 1999 Safety Conditions WARNING BE CAREFUL WHEN YOU USE THE CONSUMABLE MATERIALS OBEY THE MANUFACTURERS HEALTH AND SAFETY INSTRUCTIONS AND ALL THE APPLICABLE ...

Page 440: ...reaker Hydraulic Landing Gear HYD CTL ESSENTIAL BUS Electro Mechanical Landing Gear LDG GEAR PWR RH POWER JUNCTION BOX 2 5 Deflate the tire 2 6 Remove the nut Figure 1 22 washer Figure 1 21 and bolt Figure 1 17 then disconnect the rod eye end Figure 1 19 from the landing gear door Figure 1 1 2 7 Make sure that the bush Figure 1 18 and Figure 1 20 remain installed on the landing gear door Figure 1 ...

Page 441: ...Figure 1 2 on the axle Figure 1 16 3 4 Install the nut Figure 1 10 on the axle Figure 1 16 3 5 Release the parking brake 3 6 Tighten the nut Figure 1 10 to make sure the bearings Figure 1 15 are correctly installed 3 7 Loosen the nut Figure 1 10 then tighten it until there is no play between the axle Figure 1 16 and the wheel Figure 1 2 Tighten the nut Figure 1 10 to align it with the next lockbol...

Page 442: ...nect the rod eye end Figure 1 19 to the landing gear door Figure 1 1 with the bolt Figure 1 17 washer Figure 1 21 and nut Figure 1 22 4 Close Up 4 1 Make sure that the work area is clean and clear of tools and other items 4 2 Remove the safety clip and close the circuit breaker Hydraulic Landing Gear HYD CTL ESSENTIAL BUS Electro Mechanical Landing Gear LDG GEAR PWR RH POWER JUNCTION BOX 4 3 Lower...

Page 443: ... 15 15 14 13 16 5 4 6 2 7 A A C C 22 21 19 17 20 18 Figure 1 Main Wheel Removal Installation PC 12 47E AMM Doc No 02300 ISSUE 01 REVISION 26 MSN 545 1001 1719 1721 1999 12 B AM 00 00 00 I UNCLASSIFIED Effectivity All 12 B 32 40 01 00A 920A A UNCLASSIFIED 2021 12 04 Page 6 ...

Page 444: ...red Conditions Action Condition Data module Technical publication None PC 12 47E AMM Doc No 02300 ISSUE 01 REVISION 26 MSN 545 1001 1719 1721 1999 12 B AM 00 00 00 I UNCLASSIFIED Effectivity All 12 B 32 40 01 00A 920A A End of data module UNCLASSIFIED 2021 12 04 Page 7 ...

Page 445: ...C 12 47E AMM Doc No 02300 ISSUE 01 REVISION 26 MSN 545 1001 1719 1721 1999 12 B AM 00 00 00 I UNCLASSIFIED Intentionally left blank Effectivity All 12 B 32 40 01 00A 920A A UNCLASSIFIED 2021 12 04 Page 8 ...

Page 446: ...AL LIST OF AEROSPACE GROUND EQUIPMENT AGE AND TOOLS 12 B 07 10 00 00A 901A A JACKING MAINTENANCE PRACTICES 12 B 20 20 01 00A 040A A TORQUE WRENCHES AND PROCEDURES DESCRIPTION AND OPERATION 12 B 20 31 00 00A 070A A STANDARD PRACTICES CONSUMABLE MATERIALS LIST 12 B 32 00 00 00A 901A A LANDING GEAR HYDRAULIC MAINTENANCE PRACTI CES 12 B 32 40 00 00A 902A A WHEELS AND BRAKES SERVICING 12 B 32 40 01 00A...

Page 447: ... Identifications References Qty Reference Remark Lockwire Part P02 001 AR Anti seize compound Part P04 010 AR Spares Table 5 Spares Name Identifications References Qty Reference Remark O ring CSN 32 40 00 07 070 AR O ring CSN 32 40 00 07 135 AR Safety Conditions WARNING BE CAREFUL WHEN YOU USE THE CONSUMABLE MATERIAL OBEY THE MANUFACTURERS HEALTH AND SAFETY INSTRUCTIONS AND ALL APPLICABLE LOCAL IN...

Page 448: ...om the axle Figure 1 10 2 8 If necessary loosen the locknut Figure 1 8 and remove the union Figure 1 9 from the brake assembly Figure 1 4 Remove and discard the O ring Figure 1 7 3 Installation 3 1 Make sure the bleeder fitting Figure 1 3 is at the top of the brake assembly Figure 1 4 If not do the following steps 3 1 1 Remove and discard the lockwire from the bleeder plug Figure 1 6 3 1 2 Remove ...

Page 449: ... value is 46 8 Nm 415 lbf in 3 5 3 1 If you use Adaptor Pt No T32 105 together with Torque wrench Pt No T32 095 adjust the torque wrench to 43 Nm 382 lbf in 3 5 3 2 If you use Adaptor Pt No T32 106 together with Torque wrench Pt No T32 096 adjust the torque wrench to 42 Nm 370 lbf in 3 5 4 If you use any other applicable Torque Wrench Adaptor Pt No Local supply and Torque wrench Pt No Local supply...

Page 450: ... the ground and remove the jacks refer to AMM 12 B 07 10 00 00A 901A A PC 12 47E AMM Doc No 02300 ISSUE 01 REVISION 26 MSN 545 1001 1719 1721 1999 12 B AM 00 00 00 I UNCLASSIFIED Effectivity All 12 B 32 40 03 00A 920A A UNCLASSIFIED 2021 12 04 Page 5 ...

Page 451: ... 5 B 10 2 6 2 3 8 7 9 Figure 1 Brake Assembly Removal Installation PC 12 47E AMM Doc No 02300 ISSUE 01 REVISION 26 MSN 545 1001 1719 1721 1999 12 B AM 00 00 00 I UNCLASSIFIED Effectivity All 12 B 32 40 03 00A 920A A UNCLASSIFIED 2021 12 04 Page 6 ...

Page 452: ...red Conditions Action Condition Data module Technical publication None PC 12 47E AMM Doc No 02300 ISSUE 01 REVISION 26 MSN 545 1001 1719 1721 1999 12 B AM 00 00 00 I UNCLASSIFIED Effectivity All 12 B 32 40 03 00A 920A A End of data module UNCLASSIFIED 2021 12 04 Page 7 ...

Page 453: ...C 12 47E AMM Doc No 02300 ISSUE 01 REVISION 26 MSN 545 1001 1719 1721 1999 12 B AM 00 00 00 I UNCLASSIFIED Intentionally left blank Effectivity All 12 B 32 40 03 00A 920A A UNCLASSIFIED 2021 12 04 Page 8 ...

Page 454: ...able 1 References Data module Technical publication Title 12 B 00 00 00 00A 060A A GENERAL LIST OF AEROSPACE GROUND EQUIPMENT AGE AND TOOLS 12 B 20 31 00 00A 070A A STANDARD PRACTICES CONSUMABLE MATERIALS LIST 12 B 33 40 00 00A 903A A EXTERNAL LIGHTS ADJUSTMENT TEST Preliminary Requirements Required Conditions Table 2 Required Conditions Action Condition Data module Technical publication None PC 1...

Page 455: ...consumables used in this procedure refer to the list of consumable items AMM 12 B 20 31 00 00A 070A A Note To identify the Aerospace Ground Equipment AGE and tools used in this procedure refer to the List of AGE and Tools TEM 12 B 00 00 00 00A 060A A Procedure 1 General This procedure is applicable to the top and bottom red flashing beacons 2 Removal of the Top and Bottom Red Flashing Beacons 2 1 ...

Page 456: ...ve the red flashing light Figure 2 6 gasket Figure 2 5 necessary cable ties Figure 2 3 and the cable assembly Figure 2 2 3 Installation of the Top and Bottom Red Flashing Beacons 3 1 Install the bottom red flashing beacon Note The bottom red beacon light has a drain hole in the lens 3 1 1 Put the electrical connector Figure 2 1 and cable assembly Figure 2 2 through the hole in the gasket Figure 2 ...

Page 457: ...Install the top or bottom filament 3 3 1 Install the filament Figure 1 3 or Figure 2 10 in the red flashing light Figure 1 4 or Figure 2 6 3 3 2 Install the clamp ring and lens Figure 1 1 or Figure 2 8 and tighten the screw Figure 1 2 or Figure 2 7 3 4 Remove the safety clips and close these circuit breakers RED BEACON GENERATOR 1 BUS EXT LTS GND OP ESSENTIAL BUS NAV LIGHTS MAIN BUS 3 5 Do the ope...

Page 458: ...gure 1 Top Red Flashing Beacon Removal Installation PC 12 47E AMM Doc No 02300 ISSUE 01 REVISION 26 MSN 545 1001 1719 1721 1999 12 B AM 00 00 00 I UNCLASSIFIED Effectivity All 12 B 33 46 00 00A 920A A UNCLASSIFIED 2021 12 04 Page 5 ...

Page 459: ... 4 A Figure 2 Bottom Red Flashing Beacon Removal Installation PC 12 47E AMM Doc No 02300 ISSUE 01 REVISION 26 MSN 545 1001 1719 1721 1999 12 B AM 00 00 00 I UNCLASSIFIED Effectivity All 12 B 33 46 00 00A 920A A UNCLASSIFIED 2021 12 04 Page 6 ...

Page 460: ...red Conditions Action Condition Data module Technical publication None PC 12 47E AMM Doc No 02300 ISSUE 01 REVISION 26 MSN 545 1001 1719 1721 1999 12 B AM 00 00 00 I UNCLASSIFIED Effectivity All 12 B 33 46 00 00A 920A A End of data module UNCLASSIFIED 2021 12 04 Page 7 ...

Page 461: ...C 12 47E AMM Doc No 02300 ISSUE 01 REVISION 26 MSN 545 1001 1719 1721 1999 12 B AM 00 00 00 I UNCLASSIFIED Intentionally left blank Effectivity All 12 B 33 46 00 00A 920A A UNCLASSIFIED 2021 12 04 Page 8 ...

Page 462: ...00 00 00A 901A A ELECTRICAL POWER MAINTENANCE PRACTICES Preliminary Requirements Required Conditions Table 2 Required Conditions Action Condition Data module Technical publication None Support equipment Table 3 Support equipment Name Identifications References Qty Reference Remark Safety clip circuit breaker hold open Part T12 030 AR Pitot static test set Part Local supply AR Pitot adaptor kit Par...

Page 463: ...PNDR 2 AVIONIC 2 BUS 6 Energize the aircraft electrical system refer to AMM 12 B 24 00 00 00A 901A A 7 Set the pitot pressure on the pitot static test set to 150 kts 8 In the AVIONICS SETUP window set the BARO CORRECTION to InHg 9 On the Primary Flight Display PFD Controllers press the BARO rotary control to set 29 92 InHg 10 On the Electronic Standby Instrument System ESIS Thales ESIS press the S...

Page 464: ...tot pressure on the pitot static test set to 150 kts 19 On the pitot static test set set the reference altitudes in the following tables Make sure that the pilot PFD copilot PFD if installed and the ESIS altitude displays are within the limits Reference altitude ft PFD Altitude display ft Thales ESIS altitude display ft L3 ESIS altitude dis play ft 0 11 20 11 16 11 20 100 111 20 111 16 111 20 500 ...

Page 465: ...ence vertical speed ft min Altitude trend vector Vertical speed display ft min 2000 200 2000 100 0 0 0 45 2000 200 2000 100 23 Slowly adjust the pitot static test set static and pitot pressures to ambient 24 Close Up 24 1 On the maintenance panel set the AIR GND switch to GND 24 2 De energize the aircraft electrical system refer to AMM 12 B 24 00 00 00A 901A A 24 3 Remove the safety clip and close...

Page 466: ...B 24 00 00 00A 901A A ELECTRICAL POWER MAINTENANCE PRACTICES Preliminary Requirements Required Conditions Table 2 Required Conditions Action Condition Data module Technical publication None Support equipment Table 3 Support equipment Name Identifications References Qty Reference Remark Safety clip circuit breaker hold open Part T12 030 AR Pitot static test set Part Local supply AR Pitot adaptor ki...

Page 467: ... panel 21QZ 5 Open and install a Safety clip circuit breaker hold open Pt No T12 030 on these circuit breakers XPNDR 1 AVIONIC 1 BUS XPNDR 2 AVIONIC 2 BUS 6 Energize the aircraft electrical system refer to AMM 12 B 24 00 00 00A 901A A 7 Set the pitot pressure on the pitot static test set to 150 kts 8 In the AVIONICS SETUP window set the BARO CORRECTION to InHg 9 On the Primary Flight Display PFD C...

Page 468: ...Pa 29 92 InHg L3 ESI 1000 ESIS press the S button to set 1013 hPa 29 92 InHg L3 EFD 750 ESIS press the knob to set 1013 hPa 29 92 InHg 1013 mb 18 Set the pitot pressure on the pitot static test set to 150 kts 19 On the pitot static test set set the reference altitudes in the following table Make sure that the pilot PFD copilot PFD if installed and the ESIS altitude displays are within the limits R...

Page 469: ... 9192 30000 9144 157 29973 to 30117 9135 to 9179 21 Slowly adjust the pitot static test set static pressure towards an altitude display of 1400 feet 427 m Watch the PFD display 21 1 When the altitude display is 1550 feet 472 m make sure that a semi transparent rectangular box is shown in the upper right corner of the PFD ADI 21 2 When the altitude display is 1500 feet 457 m make sure that an amber...

Page 470: ...et from the left and right static ports and the left and right pitot heads 25 7 Install the protective covers on the left and right pitot heads Requirements after job completion Required Conditions Table 6 Required Conditions Action Condition Data module Technical publication None PC 12 47E AMM Doc No 02300 ISSUE 01 REVISION 26 MSN 545 1001 1719 1721 1999 12 B AM 00 00 00 I UNCLASSIFIED Effectivit...

Page 471: ...C 12 47E AMM Doc No 02300 ISSUE 01 REVISION 26 MSN 545 1001 1719 1721 1999 12 B AM 00 00 00 I UNCLASSIFIED Intentionally left blank Effectivity All 12 B 34 14 00 00A 903B A UNCLASSIFIED 2021 12 04 Page 6 ...

Page 472: ...R MAINTENANCE PRACTICES 12 B 34 11 00 00A 903A A PITOT STATIC SYSTEM ADJUSTMENT TEST Preliminary Requirements Required Conditions Table 2 Required Conditions Action Condition Data module Technical publication None Support equipment Table 3 Support equipment Name Identifications References Qty Reference Remark Safety clip circuit breaker hold open Part T12 030 AR Pitot static test set Part Local su...

Page 473: ...lates 1 4 Open and install a Safety clip circuit breaker hold open Pt No T12 030 on the circuit breakers XPNDR 1 AVIONIC 1 BUS XPNDR 2 AVIONIC 2 BUS RAD ALT 1 AVIONICS 1 BUS 2 Procedure 2 1 Energize the aircraft electrical system refer to AMM 12 B 24 00 00 00A 901A A 2 2 Do a leak test of the left and right pitot and static systems refer to AMM 12 B 34 11 00 00A 903A A 2 3 Make sure that the Prima...

Page 474: ...3 ESIS 50 5 4 0 NIV 100 100 NIV PFD ADI 100 5 2 PFD HSI 100 5 8 PFD HSI NIV Thales ESIS 100 5 2 5 NIV L3 ESIS 100 5 2 0 NIV 2 11 On the pitot static test set increase the pitot pressure until the airspeed displays show 131 kts Make sure that the PFD airspeed rolling digits are shown in red reverse video white digits on a red background The PFD OVERSPEED Flight Alerting System FAS warning is shown ...

Page 475: ...pitot pressure and the static pressure to ambient 3 2 On the maintenance panel set the AIR GND switch to GND 3 3 De energize the aircraft electrical system refer to AMM 12 B 24 00 00 00A 901A A 3 4 Remove the safety clip and close the circuit breakers XPNDR 1 AVIONIC 1 BUS XPNDR 2 AVIONIC 2 BUS RAD ALT 1 AVIONICS 1 BUS 3 5 Disconnect the pitot static test set from the static ports and the pitot he...

Page 476: ...0 00 00A 901A A ELECTRICAL POWER MAINTENANCE PRACTICES 12 B 34 14 00 00A 903A A ALTITUDE AND VERTICAL SPEED INDICATION ADJUST MENT TEST 12 B 34 14 00 00A 903B A ALTITUDE AND VERTICAL SPEED INDICATION RVSM ADJUSTMENT TEST 12 B 34 16 00 00A 903A A AIRSPEED INDICATION ADJUSTMENT TEST 12 B 45 45 00 00A 551A A CENTRAL MAINTENANCE SYSTEM INTERFACE FAULT MONITORING STORAGE READOUT DOWNLOAD DATA 12 B 46 3...

Page 477: ...sion AR Compass swing trolley Part T34 035 AR Supplies Table 4 Supplies Name Identifications References Qty Reference Remark None Spares Table 5 Spares Name Identifications References Qty Reference Remark None Safety Conditions Note To identify the AGE and tools used in this procedure refer to the List of AGE and Tools TEM 12 B 00 00 00 00A 060A A Procedure 1 General This data module gives the pro...

Page 478: ... Software and Data Services an account on https aerospace honeywell com is required The file can be found under Software Data Services ASDS Go to my downloads On the tab Refine Product select under Purchase Category FOC and under A C Model select PC 12 Download the applicable Certification File 2 7 On the laptop computer click on the Start icon and select ProgramFiles KSG7200_Maintenance_Program K...

Page 479: ...M 12 B 00 00 00 00A 106A A 2 27 Make sure that the DATE and TIMESTAMP is updated with current values 2 28 Click the CLOSE button to return to the CHOOSE ITEM TO VIEW screen 2 29 Click the BUILT IN TEST RESULTS button Make sure that the results screen shows MC565 Processor Fault Passed Unknown Watchdog Reset Passed Watchdog Test Passed RAM Test Passed RS232 Loopback Test Passed ROM Boot CRC32 Test ...

Page 480: ...S CH A ESSENTIAL BUS ADAHRS CH B MAIN BUS 4 5 Energize the aircraft electrical system refer to AMM 12 B 24 00 00 00A 901A A 4 6 Wait two minutes after the ADAHRS self test to let the ADAHRS unit warm up 4 7 START the KSG 7200 Field Maintenance Program on the laptop computer 4 8 Select the appropriate COMM port on the laptop computer then click on the START MAINTENANCE button Note If the software c...

Page 481: ... on SET ADAHRS PITCH ROLL HEADING OFFSET button With all fields completed click on the STORE ADAHRS OFFSETS button The Storing Data screen is shown When the data is stored the screen shows SUCCESS CLOSE this window Do a compass swing after completing the Alignment Check 4 20 Make sure that the ADAHRS Mounting Direction box shows ADAHRS CONNECTORS POINTING OUT LEFT OF AIRCRAFT Note If the mounting ...

Page 482: ... sure that the Primary Flight Display PFD attitude indication shows the actual aircraft attitude 4 31 Connect the RS232 cable to the J4 connector on the Maintenance Box 4 32 Close these circuit breakers ADAHRS CH A ESSENTIAL BUS ADAHRS CH B MAIN BUS 4 33 START the KSG 7200 Field Maintenance Program on the laptop computer 4 34 Select the appropriate COMM port on the laptop computer then click on th...

Page 483: ...DAHRS PITCH ROLL HEADING OFFSET button With all fields completed click on the STORE ADAHRS OFFSETS button The Storing Data screen is shown When the data is stored the screen shows SUCCESS CLOSE this window Do a compass swing after completing the Alignment Check 4 46 Make sure that the ADAHRS Mounting Direction box shows ADAHRS CONNECTORS POINTING OUT LEFT OF AIRCRAFT Note If the mounting direction...

Page 484: ...e Maintenance box 4 56 Close these circuit breakers ADAHRS CH A ESSENTIAL BUS ADAHRS CH B MAIN BUS 4 57 Make sure that the Primary Flight Display PFD attitude indication shows the actual aircraft attitude 4 58 De energize the aircraft electrical system refer to AMM 12 B 24 00 00 00A 901A A 4 59 Disconnect the Maintenance box 4 60 Make sure that the work area is clean and clear of tools and other i...

Page 485: ...witch Left crossbar panel ICE PROTECTION switches 5 2 7 Set the right crossbar panel ACS BLEED AIR switch to AUTO 5 2 8 On the Overhead Control Panel OCP make sure that these switches are ON GEN 1 normally ON GEN 2 normally ON AV 1 BUS normally ON AV 2 BUS normally ON CABIN BUS EPS 5 2 9 WARNING THE BRIGHT WHITE LIGHT AND THE ULTRA VIOLET RADIATION FROM THE STROBE LIGHT CAN CAUSE DAMAGE TO THE EYE...

Page 486: ...uter Pt No Local supply Connect the other end of the Sub D cable to the J4 connector on the Maintenance box 5 3 9 Boot up the laptop computer s 5 3 10 Click on the START icon and select Program Files KSG7200_Maintenance_Program KSG_7200_Maintenance_Program 5 3 11 Make sure that the KSG 7200 Field Maintenance Program is shown on the laptop computer screen 5 3 12 Set the appropriate COMM port for th...

Page 487: ...rform 12 point compass rose calibration screen click on the TAKE MAGNETOMETER READING button Note The 0 heading is stored in the ADAHRS after a few seconds The laptop computer screen will then show you the next heading to store i e 30 This will repeat in the steps that follow for the complete compass calibration 5 3 23 Put the aircraft on a heading of 30 then put the aircraft brakes on 5 3 24 Wait...

Page 488: ...e energize the aircraft electrical system refer to AMM 12 B 24 00 00 00A 901A A 5 4 6 WARNING THE PITOT HEAD THE STATIC PORTS AND THE AOA TRANSMITTERS WILL BE HOT LET THEM BECOME COOL BEFORE YOU TOUCH THEM OR INSTALL THE PROTECTIVE COVERS Install the protective covers on the pitot heads and AOA transmitters 5 4 7 Install the access panel 21QZ 5 4 8 If necessary remove the compass swing trolley 5 4...

Page 489: ... 12 47E AMM Doc No 02300 ISSUE 01 REVISION 26 MSN 545 1001 1719 1721 1999 12 B AM 00 00 00 I UNCLASSIFIED Intentionally left blank Effectivity All 12 B 34 25 00 00A 903A A UNCLASSIFIED 2021 12 04 Page 14 ...

Page 490: ...00 00 00 00A 060A A GENERAL LIST OF AEROSPACE GROUND EQUIPMENT AGE AND TOOLS 12 B 24 00 00 00A 901A A ELECTRICAL POWER MAINTENANCE PRACTICES 12 B 25 21 04 00A 920A A EXECUTIVE CARPETS REMOVAL INSTALLATION 12 B 25 22 04 00A 920A A STANDARD CARPETS REMOVAL INSTALLATION Preliminary Requirements Required Conditions Table 2 Required Conditions Action Condition Data module Technical publication None PC ...

Page 491: ...nd Equipment AGE and tools used in this procedure refer to the List of AGE and Tools TEM 12 B 00 00 00 00A 060A A Procedure 1 General This data module gives the procedures to Calibrate the height Do an operational test of the system Do a function test of the system Do the height calibration when a part of the system is replaced or when the height readout is not correct Do the function test when a ...

Page 492: ...he radar altitude digital display on the Primary Flight Display PFD shows 0 feet 3 5 If the radar altitude digital display does not show 0 feet do the height calibration procedure Step 2 3 6 De energize the aircraft electrical system refer to AMM 12 B 24 00 00 00A 901A A 4 Function Test 4 1 Connect the aircraft Maintenance box Pt No T45 005 4 2 Set the AIR GND switch on the maintenance box to AIR ...

Page 493: ...ltage until a light blue box is shown on the PFD to the right of the attitude roll scale 4 24 Make sure that the radar altitude digital display shows 300 feet 4 25 Slowly reduce the power supply voltage until An amber MIN is shown in the light blue box A MINIMUMS audio callout is heard from the cockpit speaker 4 26 Make sure that the radar altitude digital display shows 250 feet 10 feet 4 27 On th...

Page 494: ...ools and materials from the work area Make sure that the work area is clean 4 41 Close the access panel 12HZ 4 42 Install the center carpet For executive interior refer to AMM 12 B 25 21 04 00A 920A A For standard interior refer to AMM 12 B 25 22 04 00A 920A A PC 12 47E AMM Doc No 02300 ISSUE 01 REVISION 26 MSN 545 1001 1719 1721 1999 12 B AM 00 00 00 I UNCLASSIFIED Effectivity All 12 B 34 42 00 0...

Page 495: ... ALT TEST ENABLE 1 ALT TEST ENABLE 2 ALT TEST I P 0 5Vdc 10mV Ft ARINC A429 Tx BLACK SHEATHED 300mm LONG 2500 mm LONG BACKSHELL PIL 9717498367 BACKSHELL PIL 9717498367 CONNECTOR PLUG PIL 9717516163 Figure 1 Radar Altimeter Break in Cable Schematic PC 12 47E AMM Doc No 02300 ISSUE 01 REVISION 26 MSN 545 1001 1719 1721 1999 12 B AM 00 00 00 I UNCLASSIFIED Effectivity All 12 B 34 42 00 00A 903A A UNC...

Page 496: ...red Conditions Action Condition Data module Technical publication None PC 12 47E AMM Doc No 02300 ISSUE 01 REVISION 26 MSN 545 1001 1719 1721 1999 12 B AM 00 00 00 I UNCLASSIFIED Effectivity All 12 B 34 42 00 00A 903A A End of data module UNCLASSIFIED 2021 12 04 Page 7 ...

Page 497: ...C 12 47E AMM Doc No 02300 ISSUE 01 REVISION 26 MSN 545 1001 1719 1721 1999 12 B AM 00 00 00 I UNCLASSIFIED Intentionally left blank Effectivity All 12 B 34 42 00 00A 903A A UNCLASSIFIED 2021 12 04 Page 8 ...

Page 498: ...9 7 CMC Compatability 9 8 Compatability Mode 10 9 System and Security 11 10 Windows Firewall 11 11 Windows Firewall Setting 12 12 Firewall Exemption 13 References Table 1 References Data module Technical publication Title 12 B 00 00 00 00A 060A A GENERAL LIST OF AEROSPACE GROUND EQUIPMENT AGE AND TOOLS 12 B 00 00 00 00A 106A A LIST OF SOFTWARE 12 B 45 45 00 00A 066A A LAPTOP COMPUTER AGE AND TOOLS...

Page 499: ...20 Alterna tive Now obsolete LAN Kit 10 Mbit Part T45 020 Alterna tive Supplies Table 4 Supplies Name Identifications References Qty Reference Remark None Spares Table 5 Spares Name Identifications References Qty Reference Remark None Safety Conditions Note To identify the AGE and tools used in this data module refer to the List of AGE and tools TEM 12 B 00 00 00 00A 060A A PC 12 47E AMM Doc No 02...

Page 500: ... in Step 2 5 to configure the Ethernet 100 Base T network interface built in to the laptop computer Note The LAN Kit LTEPIC 25 Pt No T45 020 can also be used although it is now obsolete and no longer recommended for use In this case the network to be configured is the PCMCIA card network adaptor inserted in the laptop computer PCMCIA card slot Note If the Wireless data Loading System network or th...

Page 501: ... is set to Category SB 2362 Figure 1 Control Panel Network and Sharing 2 5 1 2 Click on Change adapter settings PC 12 47E AMM Doc No 02300 ISSUE 01 REVISION 26 MSN 545 1001 1719 1721 1999 12 B AM 00 00 00 I UNCLASSIFIED Effectivity All 12 B 45 45 00 00A 330A A UNCLASSIFIED 2021 12 04 Page 4 ...

Page 502: ...ht click on the applicable LAN connection and open the Properties window PC 12 47E AMM Doc No 02300 ISSUE 01 REVISION 26 MSN 545 1001 1719 1721 1999 12 B AM 00 00 00 I UNCLASSIFIED Effectivity All 12 B 45 45 00 00A 330A A UNCLASSIFIED 2021 12 04 Page 5 ...

Page 503: ... Internet Protocol Version 4 TCP IPv4 in the item list and click Properties PC 12 47E AMM Doc No 02300 ISSUE 01 REVISION 26 MSN 545 1001 1719 1721 1999 12 B AM 00 00 00 I UNCLASSIFIED Effectivity All 12 B 45 45 00 00A 330A A UNCLASSIFIED 2021 12 04 Page 6 ...

Page 504: ...s from Automatic private IP address to User configured and enter the following details IP address 192 168 200 1 Subnet mask 255 255 0 0 PC 12 47E AMM Doc No 02300 ISSUE 01 REVISION 26 MSN 545 1001 1719 1721 1999 12 B AM 00 00 00 I UNCLASSIFIED Effectivity All 12 B 45 45 00 00A 330A A UNCLASSIFIED 2021 12 04 Page 7 ...

Page 505: ...ith the following procedure 2 5 2 1 Right click on the CMC Remote Terminal program shortcut and click Properties then select the Compatability tab Note If needed create a program shortcut for the CMC_RT exe executive file The CMC_RT exe file is stored in C CMC by default PC 12 47E AMM Doc No 02300 ISSUE 01 REVISION 26 MSN 545 1001 1719 1721 1999 12 B AM 00 00 00 I UNCLASSIFIED Effectivity All 12 B...

Page 506: ...Properties SB 2368 Figure 7 CMC Compatability PC 12 47E AMM Doc No 02300 ISSUE 01 REVISION 26 MSN 545 1001 1719 1721 1999 12 B AM 00 00 00 I UNCLASSIFIED Effectivity All 12 B 45 45 00 00A 330A A UNCLASSIFIED 2021 12 04 Page 9 ...

Page 507: ...5 2 3 Close all windows by acknowledging with OK 2 5 3 Disable all Firewalls 2 5 3 1 From the Windows Start Menu go to Control Panel and open settings System and Security PC 12 47E AMM Doc No 02300 ISSUE 01 REVISION 26 MSN 545 1001 1719 1721 1999 12 B AM 00 00 00 I UNCLASSIFIED Effectivity All 12 B 45 45 00 00A 330A A UNCLASSIFIED 2021 12 04 Page 10 ...

Page 508: ...5 3 2 Open Allow a program through Windows Firewall and press the Allow another program button PC 12 47E AMM Doc No 02300 ISSUE 01 REVISION 26 MSN 545 1001 1719 1721 1999 12 B AM 00 00 00 I UNCLASSIFIED Effectivity All 12 B 45 45 00 00A 330A A UNCLASSIFIED 2021 12 04 Page 11 ...

Page 509: ... Terminal to the Firewall exemption list and make sure that all checkboxes are ticked PC 12 47E AMM Doc No 02300 ISSUE 01 REVISION 26 MSN 545 1001 1719 1721 1999 12 B AM 00 00 00 I UNCLASSIFIED Effectivity All 12 B 45 45 00 00A 330A A UNCLASSIFIED 2021 12 04 Page 12 ...

Page 510: ... to AMM 12 B 45 45 00 00A 331A A Note If you also use the CMC Remote Terminal computer for other purposes make sure that you restore the original configuration after disconnecting from the aircraft If you do not your personal network may not work Requirements after job completion Required Conditions Table 6 Required Conditions Action Condition Data module Technical publication None PC 12 47E AMM D...

Page 511: ... 12 47E AMM Doc No 02300 ISSUE 01 REVISION 26 MSN 545 1001 1719 1721 1999 12 B AM 00 00 00 I UNCLASSIFIED Intentionally left blank Effectivity All 12 B 45 45 00 00A 330A A UNCLASSIFIED 2021 12 04 Page 14 ...

Page 512: ...le Technical publication Title 12 B 00 00 00 00A 060A A GENERAL LIST OF AEROSPACE GROUND EQUIPMENT AGE AND TOOLS 12 B 00 00 00 00A 106A A LIST OF SOFTWARE 12 B 24 00 00 00A 901A A ELECTRICAL POWER MAINTENANCE PRACTICES 12 B 45 45 00 00A 330A A CENTRAL MAINTENANCE SYSTEM INTERFACE PRE PARE TEST EQUIPMENT Preliminary Requirements Required Conditions Table 2 Required Conditions Action Condition Data ...

Page 513: ...00 00 00 00A 060A A Procedure 1 Connect the Computer 1 1 Make sure that the aircraft is configured as follows Weight on wheels aircraft on the ground Aircraft is stationary airspeed less than 52 knots All Modular Avionics Unit MAU and display unit circuit breakers closed If the Wireless Data Loading System option is installed SB 46 004 or Factory Option make sure the WLAN DATA LOAD and MAU DATA LO...

Page 514: ...Panel has two RJ 45 connector marked NIC1 and NIC2 3 2 1 Use the two modified Ethernet cables from the LAN Kit 100Mbit Pt No T45 025 Connect the ends marked Aircraft Side to the aircraft Maintenance Panel NIC1 and NIC2 RJ 45 connectors 3 2 2 Connect the other ends of the Ethernet cables to the Ethernet switch part of the LAN Kit 100Mbit Pt No T45 025 3 2 3 Use the standard Ethernet cable part of t...

Page 515: ...the aircraft Maintenance Panel LAN Bus connector 3 4 5 Connect the other end of the BNC coaxial cable to the BNC dongle adaptor included in the LAN kit 3 4 6 Connect the BNC dongle adaptor to the PCMCIA card in the laptop computer 3 5 Start the laptop computer and make sure that Windows is running correctly 3 6 Energize the aircraft electrical system refer to AMM 12 B 24 00 00 00A 901A A 3 7 Wait ...

Page 516: ...0002 A 01 1 Figure 1 CMC Connection Failed PC 12 47E AMM Doc No 02300 ISSUE 01 REVISION 26 MSN 545 1001 1719 1721 1999 12 B AM 00 00 00 I UNCLASSIFIED Effectivity All 12 B 45 45 00 00A 331A A UNCLASSIFIED 2021 12 04 Page 5 ...

Page 517: ... B 00 00 00 00A 106A A 4 3 4 4 If you see the screen shown in Fig 3 the CMC Cyclic Redundancy Check CRC did not pass De energize the aircraft electrical system wait two minutes then energize the aircraft electrical system PC 12 47E AMM Doc No 02300 ISSUE 01 REVISION 26 MSN 545 1001 1719 1721 1999 12 B AM 00 00 00 I UNCLASSIFIED Effectivity All 12 B 45 45 00 00A 331A A UNCLASSIFIED 2021 12 04 Page ...

Page 518: ...0003 A 01 1 Figure 2 Incompatible Software PC 12 47E AMM Doc No 02300 ISSUE 01 REVISION 26 MSN 545 1001 1719 1721 1999 12 B AM 00 00 00 I UNCLASSIFIED Effectivity All 12 B 45 45 00 00A 331A A UNCLASSIFIED 2021 12 04 Page 7 ...

Page 519: ...004 A 01 1 Figure 3 Cyclic Redundancy Check PC 12 47E AMM Doc No 02300 ISSUE 01 REVISION 26 MSN 545 1001 1719 1721 1999 12 B AM 00 00 00 I UNCLASSIFIED Effectivity All 12 B 45 45 00 00A 331A A UNCLASSIFIED 2021 12 04 Page 8 ...

Page 520: ... respond for example ping 192 168 1 17 and press Enter 5 2 If the ping command is successful the computer is connected to the CMC You can now do maintenance and troubleshooting using the CMC Requirements after job completion Required Conditions Table 6 Required Conditions Action Condition Data module Technical publication None PC 12 47E AMM Doc No 02300 ISSUE 01 REVISION 26 MSN 545 1001 1719 1721 ...

Page 521: ... 12 47E AMM Doc No 02300 ISSUE 01 REVISION 26 MSN 545 1001 1719 1721 1999 12 B AM 00 00 00 I UNCLASSIFIED Intentionally left blank Effectivity All 12 B 45 45 00 00A 331A A UNCLASSIFIED 2021 12 04 Page 10 ...

Page 522: ...NDARD PRACTICES CONSUMABLE MATERIALS LIST 12 B 21 30 00 00A 903A A PRESSURIZATION CONTROL MSN 1001 1719 ADJUST MENT TEST 12 B 25 21 03 00A 920A A EXECUTIVE TRIM REMOVAL INSTALLATION 12 B 25 22 03 00A 920A A STANDARD TRIM REMOVAL INSTALLATION 12 B 52 10 07 00A 920A A MSN 1001 1575 PASSENGER CREW DOOR STRIKER PLATES REMOVAL INSTALLATION Preliminary Requirements Required Conditions Table 2 Required C...

Page 523: ...he consumables used in this procedure refer to the Consumable Materials List AMM 12 B 20 31 00 00A 070A A Procedure 1 General The passenger crew door is locked with six shoot bolts which all engage in striker plates The shoot bolts are adjusted to operate in sequence the lower shoot bolts engage first These pull the door in and move the center and upper shoot bolts into position so that they can e...

Page 524: ...ecks and replacement procedures that follow can be done to decrease the hand force 3 Checks to Find the Cause of High Hand Force 3 1 Causes for High Hand Force There are three conditions which will give a high hand force The shoot bolt does not engage easily because it is touching on the outboard side of the striker plate Ref Figure 1 5 The shoot bolt does not engage easily because it is touching ...

Page 525: ...ure 1 1 and the cotter pin holes of the shoot bolts Figure 1 7 and the fork ends Figure 1 11 align It is possible that a selection of shoot bolts will have to be tried to get these conditions 3 7 13 Turn the door handle Figure 1 4 to the open position 3 7 14 Use a 2 mm drill to drill the cotter pin holes in the fork ends Figure 1 11 using the hole in the shoot bolts Figure 1 7 as a guide Remove al...

Page 526: ...10 bolts Figure 1 13 and washers Figure 1 14 from the fork ends Figure 1 11 4 6 Remove the indicators Figure 1 15 from the covers Figure 1 16 4 7 Remove the fork ends Figure 1 11 from the connecting rods Figure 1 12 Discard the fork ends Figure 1 11 4 8 Position the new fork ends Figure 1 11 on the connecting rods Figure 1 12 and loosely install the bolts Figure 1 13 washers Figure 1 14 and nuts F...

Page 527: ...fy the striker plates to be replaced Most frequently this will be the lower pair nearest to the door hinge It is recommended not to replace more than one pair of striker plates at a time 5 Close Up 5 1 Remove all the equipment tools and materials from the work area Make sure that the work area is clean 5 2 Install the passenger crew door trim panel refer to AMM 12 B 25 21 03 00A 920A A or 12 B 25 ...

Page 528: ...RD SIDE STRIKER PLATE INBOARD SIDE TYPICAL C 5 6 C Figure 1 Passenger Crew Door Adjustment Test PC 12 47E AMM Doc No 02300 ISSUE 01 REVISION 26 MSN 545 1001 1719 1721 1999 12 B AM 00 00 00 I UNCLASSIFIED Effectivity All 12 B 52 10 00 00A 903A A UNCLASSIFIED 2021 12 04 Page 7 ...

Page 529: ... 521000 A S4080 00811 A 02 1 F F F E F D Figure 1 Passenger Crew Door Adjustment Test PC 12 47E AMM Doc No 02300 ISSUE 01 REVISION 26 MSN 545 1001 1719 1721 1999 12 B AM 00 00 00 I UNCLASSIFIED Effectivity All 12 B 52 10 00 00A 903A A UNCLASSIFIED 2021 12 04 Page 8 ...

Page 530: ...red Conditions Action Condition Data module Technical publication None PC 12 47E AMM Doc No 02300 ISSUE 01 REVISION 26 MSN 545 1001 1719 1721 1999 12 B AM 00 00 00 I UNCLASSIFIED Effectivity All 12 B 52 10 00 00A 903A A End of data module UNCLASSIFIED 2021 12 04 Page 9 ...

Page 531: ... 12 47E AMM Doc No 02300 ISSUE 01 REVISION 26 MSN 545 1001 1719 1721 1999 12 B AM 00 00 00 I UNCLASSIFIED Intentionally left blank Effectivity All 12 B 52 10 00 00A 903A A UNCLASSIFIED 2021 12 04 Page 10 ...

Page 532: ...OF AEROSPACE GROUND EQUIPMENT AGE AND TOOLS 12 B 20 31 00 00A 070A A STANDARD PRACTICES CONSUMABLE MATERIALS LIST 12 B 21 30 00 00A 903A A PRESSURIZATION CONTROL MSN 1001 1719 ADJUST MENT TEST 12 B 21 30 00 00A 903B A PRESSURIZATION CONTROL MSN 545 1720 AND UP ADJUSTMENT TEST 12 B 25 21 03 00A 920A A EXECUTIVE TRIM REMOVAL INSTALLATION 12 B 25 22 03 00A 920A A STANDARD TRIM REMOVAL INSTALLATION 12...

Page 533: ...otter pin CSN 52 10 00 04A 090 AR Safety Conditions WARNING BE CAREFUL WHEN YOU USE THE CONSUMABLE MATERIALS OBEY THE MANUFACTURERS HEALTH AND SAFETY INSTRUCTIONS AND ALL THE APPLICABLE LOCAL INSTRUCTIONS CONSUMABLE MATERIALS CAN BE DANGEROUS AND CAN CAUSE DEATH OR INJURY TO PERSONNEL AND OR DAMAGE TO EQUIPMENT Note To identify the AGE and tools used in this procedure refer to the List of AGE and ...

Page 534: ...e classed as follows High if more than 75 N 16 9 lbf Satisfactory if between 55 N and 75 N 12 4 lbf and 16 9 lbf Low if less than 55 N 12 4 lbf Note For aircraft that are less than 3 years old the force will be higher A force of up to 95 N 21 4 lbf must be accepted as satisfactory This is because it takes time for the door seal to sufficiently compress to its correct shape Note A low door force ca...

Page 535: ...ting rods Figure 1 12 Discard the fork ends Figure 1 11 3 7 7 Position the new fork ends Figure 1 11 on the connecting rods Figure 1 12 and loosely install the bolts Figure 1 13 washers Figure 1 14 and nuts Figure 1 10 3 7 8 If required apply a thin layer of Lubricating paste Pt No P04 029 to the new shoot bolts Figure 1 7 3 7 9 Install the shoot bolts Figure 1 7 removed at Step 3 7 3 on the fork ...

Page 536: ...enger crew door trim panels as necessary refer to AMM 12 B 25 21 03 00A 920A A or 12 B 25 22 03 00A 920A A 4 2 Remove and discard the cotter pinsFigure 1 9 from the shoot bolts Figure 1 7 4 3 Remove and discard the shoot bolts Figure 1 7 from the fork ends Figure 1 11 4 4 Remove the nuts Figure 1 10 bolts Figure 1 13 and washers Figure 1 14 from the fork ends Figure 1 11 4 5 Remove the indicators ...

Page 537: ...aced Most frequently this will be the lower pair nearest to the door hinge It is recommended not to replace more than one pair of striker plates at a time 5 Close Up 5 1 Remove all the equipment tools and materials from the work area Make sure that the work area is clean 5 2 Install the passenger crew door trim panels refer to AMM 12 B 25 21 03 00A 920A A or 12 B 25 22 03 00A 920A A 5 3 Do a cabin...

Page 538: ...TRIKER PLATE INBOARD SIDE TYPICAL C D C 5 6 Figure 1 MSN 1576 9999 Passenger Crew Door Adjustment Test PC 12 47E AMM Doc No 02300 ISSUE 01 REVISION 26 MSN 545 1001 1719 1721 1999 12 B AM 00 00 00 I UNCLASSIFIED Effectivity All 12 B 52 10 00 00A 903B A UNCLASSIFIED 2021 12 04 Page 7 ...

Page 539: ... 12 F F F F F D E Ø10 4 2 3 4 E F Figure 1 MSN 1576 9999 Passenger Crew Door Adjustment Test PC 12 47E AMM Doc No 02300 ISSUE 01 REVISION 26 MSN 545 1001 1719 1721 1999 12 B AM 00 00 00 I UNCLASSIFIED Effectivity All 12 B 52 10 00 00A 903B A UNCLASSIFIED 2021 12 04 Page 8 ...

Page 540: ...red Conditions Action Condition Data module Technical publication None PC 12 47E AMM Doc No 02300 ISSUE 01 REVISION 26 MSN 545 1001 1719 1721 1999 12 B AM 00 00 00 I UNCLASSIFIED Effectivity All 12 B 52 10 00 00A 903B A End of data module UNCLASSIFIED 2021 12 04 Page 9 ...

Page 541: ... 12 47E AMM Doc No 02300 ISSUE 01 REVISION 26 MSN 545 1001 1719 1721 1999 12 B AM 00 00 00 I UNCLASSIFIED Intentionally left blank Effectivity All 12 B 52 10 00 00A 903B A UNCLASSIFIED 2021 12 04 Page 10 ...

Page 542: ...00 00A 070A A STANDARD PRACTICES CONSUMABLE MATERIALS LIST 12 B 21 30 00 00A 903A A PRESSURIZATION CONTROL MSN 1001 1719 ADJUST MENT TEST 12 B 25 21 03 00A 920A A EXECUTIVE TRIM REMOVAL INSTALLATION 12 B 25 22 03 00A 920A A STANDARD TRIM REMOVAL INSTALLATION 12 B 52 10 00 00A 903A A MSN 1001 1575 PASSENGER CREW DOOR ADJUST MENT TEST Preliminary Requirements Required Conditions Table 2 Required Con...

Page 543: ... 030 AR FWD position of the passen ger crew door structure Striker plate CSN 53 10 00 02 050 AR FWD position of the passen ger crew door structure Safety Conditions WARNING BE CAREFUL WHEN YOU USE THE CONSUMABLE MATERIALS OBEY THE MANUFACTURERS HEALTH AND SAFETY INSTRUCTIONS AND ALL THE APPLICABLE LOCAL INSTRUCTIONS CONSUMABLE MATERIALS CAN BE DANGEROUS AND CAN CAUSE DEATH OR INJURY TO PERSONNEL A...

Page 544: ...done to find the cause of the high hand force and to identify the striker plates Figure 1 2 or Figure 1 9 to be replaced are done in the adjustment test of the passenger crew door AMM 12 B 52 10 00 00A 903A A Most frequently this will be the lower pair nearest to the door hinge It is recommended not to replace more than one pair of striker plates at a time 3 Installation 3 1 Note The four bolts th...

Page 545: ...The maximum permitted play is 0 7 mm 0 03 in If the play is more than the permitted replace the striker plate with an applicable offset striker plate 3 6 7 Do Step 3 6 to make sure the play of all of the shoot bolts are in the limit 3 7 Do the adjustment test of the passenger crew door refer to AMM 12 B 52 10 00 00A 903A A 4 Close up 4 1 Remove all the equipment tools and materials from the work a...

Page 546: ...521007 A S4080 04105 A 01 1 Figure 1 Passenger Door Striker Plate Removal Installation PC 12 47E AMM Doc No 02300 ISSUE 01 REVISION 26 MSN 545 1001 1719 1721 1999 12 B AM 00 00 00 I UNCLASSIFIED Effectivity All 12 B 52 10 07 00A 920A A UNCLASSIFIED 2021 12 04 Page 5 ...

Page 547: ...red Conditions Action Condition Data module Technical publication None PC 12 47E AMM Doc No 02300 ISSUE 01 REVISION 26 MSN 545 1001 1719 1721 1999 12 B AM 00 00 00 I UNCLASSIFIED Effectivity All 12 B 52 10 07 00A 920A A End of data module UNCLASSIFIED 2021 12 04 Page 6 ...

Page 548: ...ation Title 12 B 20 31 00 00A 070A A STANDARD PRACTICES CONSUMABLE MATERIALS LIST 12 B 21 30 00 00A 903A A PRESSURIZATION CONTROL MSN 1001 1719 ADJUST MENT TEST 12 B 21 30 00 00A 903B A PRESSURIZATION CONTROL MSN 545 1720 AND UP ADJUSTMENT TEST 12 B 25 21 03 00A 920A A EXECUTIVE TRIM REMOVAL INSTALLATION 12 B 25 22 03 00A 920A A STANDARD TRIM REMOVAL INSTALLATION 12 B 52 10 00 00A 903B A MSN 1576 ...

Page 549: ... 5 Spares Name Identifications References Qty Reference Remark Striker plate CSN 53 10 00 14 010 AR AFT position of the passenger crew door structure Striker plate CSN 53 10 00 14 030 AR AFT position of the passenger crew door structure Striker plate CSN 53 10 00 02 030 AR FWD position of the passen ger crew door structure Striker plate CSN 53 10 00 02 050 AR FWD position of the passen ger crew do...

Page 550: ...h their heads cut off and a screwdriver slot made across the shanks These bolts are then installed in the nut plate as each striker plate bolt is removed 2 3 Remove the second bolt Figure 1 4 from the applicable striker plate Figure 1 2 or Figure 1 9 2 4 Do Step 2 1 thru Step 2 3 again to remove the two bolts Figure 1 3 from the striker plates 2 5 Remove and discard the striker plates 2 6 If neces...

Page 551: ...his distance on the center striker plates It is recommended to use a vernier caliper for this task 3 6 2 Open the passenger crew door Figure 1 6 3 6 3 Measure the distance L2 3 6 4 Measure the distance D on the shoot bolt 3 6 5 Calculate the play G from this formula G L2 L1 D 3 6 6 The maximum permitted play is 0 7 mm 0 03 in If the play is more than the permitted replace the striker plate with an...

Page 552: ...007 A S4080 04112 A 01 1 C Figure 1 Passenger Door Striker Plates Removal Installation PC 12 47E AMM Doc No 02300 ISSUE 01 REVISION 26 MSN 545 1001 1719 1721 1999 12 B AM 00 00 00 I UNCLASSIFIED Effectivity All 12 B 52 10 07 00A 920B A UNCLASSIFIED 2021 12 04 Page 5 ...

Page 553: ...red Conditions Action Condition Data module Technical publication None PC 12 47E AMM Doc No 02300 ISSUE 01 REVISION 26 MSN 545 1001 1719 1721 1999 12 B AM 00 00 00 I UNCLASSIFIED Effectivity All 12 B 52 10 07 00A 920B A End of data module UNCLASSIFIED 2021 12 04 Page 6 ...

Page 554: ...S 12 B 11 20 02 00A 901A A INSTALLATION OF HORIZONTAL STABILIZER TRIM MARK INGS MAINTENANCE PRACTICES 12 B 20 31 00 00A 070A A STANDARD PRACTICES CONSUMABLE MATERIALS LIST 12 B 27 40 00 00A 903A A HORIZONTAL STABILIZER TRIM ADJUSTMENT TEST 12 B 30 10 00 00A 903A A AIRFOIL DE ICE SYSTEM TIMER WITHOUT INHIBIT FUNC TION ADJUSTMENT TEST 12 B 30 10 00 00A 903B A AIRFOIL DE ICE SYSTEM TIMER WITH INHIBIT...

Page 555: ...tifications References Qty Reference Remark Grease Part P04 004 AR Cable tie Part P09 005 AR White Spirit Part P01 008 AR Solvent alcohol Part P01 011 AR Cloth cotton Part P02 019 AR CPC Part P10 013 AR Spares Table 5 Spares Name Identifications References Qty Reference Remark Cotter pin CSN 55 10 00 01 010 AR Washer CSN 55 10 00 01 025 AR Safety Conditions WARNING BE CAREFUL WHEN YOU REMOVE OR IN...

Page 556: ...H TRIM ALTN MAIN BUS BOOTS DE ICE MAIN BUS 1 2 Put the Warning sign DO NOT MOVE THE ELEVATOR CONTROLS Pt No Local supply in the flight compartment 1 3 Remove the access panels 32BT 32CT 33DT upper and lower 33ET and 34DT upper and lower 1 4 If necessary remove the elevators refer to AMM 12 B 55 20 01 00A 920A A 1 5 Remove the cable ties and move the electrical cable Figure 1 21 away from the stabi...

Page 557: ...ct thickness Washer Figure 1 3 as necessary to remove the axial movement Note Install the washers Figure 1 3 between the structure and the left part of each stabilizer hinge 2 5 Install the washers Figure 1 6 nuts Figure 1 4 Tighten the nuts Figure 1 4 sufficiently to fully install the bolts Loosen the nuts Figure 1 4 and torque to a maximum of 2 0 Nm 17 7 lbf in Safety the nuts Figure 1 4 with a ...

Page 558: ...se circuit breakers PITCH TRIM ESSENTIAL BUS PITCH TRIM ALTN MAIN BUS BOOTS DE ICE MAIN BUS 3 2 Remove the warning sign from the flight compartment 3 3 Do the adjustment test of the horizontal stabilizer trim system refer to AMM 12 B 27 40 00 00A 903A A 3 4 Do the adjustment test of the airfoil de ice system refer to AMM 12 B 30 10 00 00A 903A A or 12 B 30 10 00 00A 903B A 3 5 Do the installation ...

Page 559: ... 27 A E F B C D F E D C B A 12 B 551000 A S4080 01557 A 01 1 Figure 1 Horizontal Stabilizer Removal Installation PC 12 47E AMM Doc No 02300 ISSUE 01 REVISION 26 MSN 545 1001 1719 1721 1999 12 B AM 00 00 00 I UNCLASSIFIED Effectivity All 12 B 55 10 01 00A 920A A UNCLASSIFIED 2021 12 04 Page 6 ...

Page 560: ...red Conditions Action Condition Data module Technical publication None PC 12 47E AMM Doc No 02300 ISSUE 01 REVISION 26 MSN 545 1001 1719 1721 1999 12 B AM 00 00 00 I UNCLASSIFIED Effectivity All 12 B 55 10 01 00A 920A A End of data module UNCLASSIFIED 2021 12 04 Page 7 ...

Page 561: ...C 12 47E AMM Doc No 02300 ISSUE 01 REVISION 26 MSN 545 1001 1719 1721 1999 12 B AM 00 00 00 I UNCLASSIFIED Intentionally left blank Effectivity All 12 B 55 10 01 00A 920A A UNCLASSIFIED 2021 12 04 Page 8 ...

Page 562: ...A STANDARD PRACTICES CONSUMABLE MATERIALS LIST 12 B 21 30 00 00A 903A A PRESSURIZATION CONTROL MSN 1001 1719 ADJUST MENT TEST 12 B 21 30 00 00A 903B A PRESSURIZATION CONTROL MSN 545 1720 AND UP ADJUSTMENT TEST 12 B 24 00 00 00A 901A A ELECTRICAL POWER MAINTENANCE PRACTICES 12 B 25 10 03 00A 920A A FLIGHT COMPARTMENT TRIM REMOVAL INSTALLATION 12 B 30 40 00 00A 903A A WINDSHIELD DE ICE SYSTEM ADJUST...

Page 563: ... Local supply AR WM 30 40 00 and 30 40 10 Solvent Part P01 010 AR Grease Part P04 004 AR Alternative to P04 020 Grease Part P04 020 AR Polyethylene foil Self adhesive Part P09 025 AR Petroleum Jelly Part P04 007 AR Grease Part P04 030 AR Alternative to P04 007 Sealant Part P08 040 AR Sealant Part P08 056 AR Alternative to P08 040 Spares Table 5 Spares Name Identifications References Qty Reference ...

Page 564: ... from around the left or right windshield Figure 1 5 or Figure 1 7 to make it possible to move the doubler Figure 1 6 away from the left or right side window Figure 1 4 or Figure 1 1 1 4 Carefully break the bond between the doubler Figure 1 6 and the left or right side window Figure 1 4 or Figure 1 1 and move the doubler Figure 1 6 away 1 5 Carefully break the bond between the left or right side w...

Page 565: ...t or right windshield Figure 1 5 or Figure 1 7 and the structure Figure 1 2 with Petroleum Jelly Pt No P04 007 3 4 Put the left or right windshield Figure 1 5 or Figure 1 7 in position on the structure Figure 1 2 3 5 Install the two lengths of Extruded foam rubber 0 7 m 2 3 ft Figure 1 9 around the frame Figure 1 8 of the DV window 3 6 Lubricate the mating surfaces of the seal on the left or right...

Page 566: ...ence Outwards from the middle of the side post of the doubler Figure 1 6 to the top and bottom of the doubler Rearwards along the top and bottom of the doubler Figure 1 6 4 6 Use a suitable tool to align the remaining holes in the doubler Figure 1 6 with the holes in the structure Figure 1 2 then install the remaining screws Figure 1 10 hand tight 4 7 Torque the screws Figure 1 10 to between 2 and...

Page 567: ...move all the equipment tools and materials from the work area Make sure that the work area is clean 5 2 Install the flight compartment trim panels 21CZ 21EZ and 21LZ refer to AMM 12 B 25 10 03 00A 920A A PC 12 47E AMM Doc No 02300 ISSUE 01 REVISION 26 MSN 545 1001 1719 1721 1999 12 B AM 00 00 00 I UNCLASSIFIED Effectivity All 12 B 56 11 01 00A 920A A UNCLASSIFIED 2021 12 04 Page 6 ...

Page 568: ... 2 1 C C SECTION C C Figure 1 Windshield Removal Installation PC 12 47E AMM Doc No 02300 ISSUE 01 REVISION 26 MSN 545 1001 1719 1721 1999 12 B AM 00 00 00 I UNCLASSIFIED Effectivity All 12 B 56 11 01 00A 920A A UNCLASSIFIED 2021 12 04 Page 7 ...

Page 569: ...VERLAPPING SLEEVE EXISTING SLEEVE MAX 50 mm INLINE SPLICE POWER WIRE SENSOR WIRE NEW SLEEVE 917 99 88 605 Figure 1 Windshield Removal Installation PC 12 47E AMM Doc No 02300 ISSUE 01 REVISION 26 MSN 545 1001 1719 1721 1999 12 B AM 00 00 00 I UNCLASSIFIED Effectivity All 12 B 56 11 01 00A 920A A UNCLASSIFIED 2021 12 04 Page 8 ...

Page 570: ...red Conditions Action Condition Data module Technical publication None PC 12 47E AMM Doc No 02300 ISSUE 01 REVISION 26 MSN 545 1001 1719 1721 1999 12 B AM 00 00 00 I UNCLASSIFIED Effectivity All 12 B 56 11 01 00A 920A A End of data module UNCLASSIFIED 2021 12 04 Page 9 ...

Page 571: ... 12 47E AMM Doc No 02300 ISSUE 01 REVISION 26 MSN 545 1001 1719 1721 1999 12 B AM 00 00 00 I UNCLASSIFIED Intentionally left blank Effectivity All 12 B 56 11 01 00A 920A A UNCLASSIFIED 2021 12 04 Page 10 ...

Page 572: ...emoval Installation Preparation and Close Up 21 References Table 1 References Data module Technical publication Title 12 B 05 50 06 00A 282A A ALIGNMENT AND SYMMETRY UNSCHEDULED INSPEC TIONS 12 B 07 10 00 00A 901A A JACKING MAINTENANCE PRACTICES 12 B 20 31 00 00A 070A A STANDARD PRACTICES CONSUMABLE MATERIALS LIST 12 B 22 20 00 00A 903A A SPEED AND ATTITUDE CORRECTION ADJUST MENT TEST 12 B 24 30 0...

Page 573: ...02A A WHEELS AND BRAKES SERVICING 12 B 33 40 00 00A 903A A EXTERNAL LIGHTS ADJUSTMENT TEST 12 B 34 11 00 00A 903A A PITOT STATIC SYSTEM ADJUSTMENT TEST 12 B 57 00 00 00A 520A A LEFT WING HYDRAULIC LANDING GEAR REMOVAL 12 B 57 33 00 00A 920A A WING TIP REMOVAL INSTALLATION Preliminary Requirements Required Conditions Table 2 Required Conditions Action Condition Data module Technical publication Non...

Page 574: ...EADS DO NOT USE ANY CORRECTION FACTORS WHEN YOU TORQUE THE FASTENERS Note To identify the consumables used in this procedure refer to the Consumable Materials List AMM 12 B 20 31 00 00A 070A A Procedure 1 General This procedure assumes that the left wing is removed as given in AMM 12 B 57 00 00 00A 520A A 2 Installation 2 1 CAUTION DAMAGE TO THE FUSELAGE AND WING BUSHINGS WILL OCCUR IF TOO MUCH FO...

Page 575: ...y lift the wing and move it into position Align the forward top bushes in the wing fittings Figure 1 4 and the fuselage fittings 2 1 10 Install the forward top long bolt Figure 1 5 through the wing and fuselage fittings Figure 1 4 Use hand force to install the long bolt Figure 1 5 Remove the installation tools Figure 1 30 and Figure 1 31 from the long bolt Figure 1 5 If the long bolt Figure 1 5 ca...

Page 576: ...igure 1 2 with the chamfer towards the bolt Figure 1 1 head washers Figure 1 3 and the new nut Figure 1 6 Torque the nut Figure 1 6 to between 24 and 25 6 Nm 213 and 226 lbf in plus the nut friction torque 2 1 21 Use Grease Pt No P04 029 to lubricate the parts Install the new forward bottom bolt Figure 1 7 washers Figure 1 8 and Figure 1 9 and the new nut Figure 1 12 Torque the nut Figure 1 12 to ...

Page 577: ... B A A LEFT SHOWN RIGHT SIMILAR 12 A 570000 A S4080 30109 A 03 1 C Figure 1 Wing Installation Attachment Fittings PC 12 47E AMM Doc No 02300 ISSUE 01 REVISION 26 MSN 545 1001 1719 1721 1999 12 B AM 00 00 00 I UNCLASSIFIED Effectivity All 12 B 57 00 00 00A 720A A UNCLASSIFIED 2021 12 04 Page 6 ...

Page 578: ...T SIMILAR SECTION A A 28 29 SECTION B B 28 29 Figure 1 Wing Installation Attachment Fittings PC 12 47E AMM Doc No 02300 ISSUE 01 REVISION 26 MSN 545 1001 1719 1721 1999 12 B AM 00 00 00 I UNCLASSIFIED Effectivity All 12 B 57 00 00 00A 720A A UNCLASSIFIED 2021 12 04 Page 7 ...

Page 579: ...and Figure 2 6 from around the forward and aft main spars 2 2 4 Remove the lift strap Figure 2 7 and shackle Figure 2 8 from the outer wing adapter Figure 2 3 2 2 5 Remove the screws Figure 2 2 and the outer wing adapter Figure 2 3 from the end of the wing Figure 2 4 PC 12 47E AMM Doc No 02300 ISSUE 01 REVISION 26 MSN 545 1001 1719 1721 1999 12 B AM 00 00 00 I UNCLASSIFIED Effectivity All 12 B 57 ...

Page 580: ...MILAR C 2 3 4 7 8 1 Figure 2 Wing Removal Installation Sling Attachment Removal PC 12 47E AMM Doc No 02300 ISSUE 01 REVISION 26 MSN 545 1001 1719 1721 1999 12 B AM 00 00 00 I UNCLASSIFIED Effectivity All 12 B 57 00 00 00A 720A A UNCLASSIFIED 2021 12 04 Page 9 ...

Page 581: ...move the caps and connect the pitot pipes Figure 3 5 and Figure 3 7 to the tee piece Figure 3 6 2 3 4 Attach the pitot pipe Figure 3 7 to the support angle Figure 3 10 with the Cable tie Pt No P09 008 Figure 3 8 2 3 5 Remove the caps and connect the wing electrical connectors Figure 3 1 Figure 3 2 Figure 3 3 and Figure 3 4 to the fuselage electrical connectors PC 12 47E AMM Doc No 02300 ISSUE 01 R...

Page 582: ... 10 11 12 14 15 8 16 5 3 B 18 19 20 17 1 B A Figure 3 Left Wing Removal Top and Rear Equipment PC 12 47E AMM Doc No 02300 ISSUE 01 REVISION 26 MSN 545 1001 1719 1721 1999 12 B AM 00 00 00 I UNCLASSIFIED Effectivity All 12 B 57 00 00 00A 720A A UNCLASSIFIED 2021 12 04 Page 11 ...

Page 583: ...lage and the wing 2 4 3 Remove the caps and install the grommet Figure 4 4 and the three fuel pipes Figure 4 1 Figure 4 2 and Figure 4 3 between the fuselage and the connections in the landing gear compartment 2 4 4 Remove the caps and connect the two rear de ice pipes Figure 4 12 Tighten the two clamps Figure 4 13 PC 12 47E AMM Doc No 02300 ISSUE 01 REVISION 26 MSN 545 1001 1719 1721 1999 12 B AM...

Page 584: ...T SIMILAR C 12 A 570000 A S4080 00869 A 02 1 Figure 4 Left Wing Removal Installation Bottom Center Equipment PC 12 47E AMM Doc No 02300 ISSUE 01 REVISION 26 MSN 545 1001 1719 1721 1999 12 B AM 00 00 00 I UNCLASSIFIED Effectivity All 12 B 57 00 00 00A 720A A UNCLASSIFIED 2021 12 04 Page 13 ...

Page 585: ... and install the hydraulic pipe Figure 5 7 between the fuselage connection and the service tray assembly Figure 5 16 2 5 8 Remove the caps and install the hydraulic pipe Figure 5 6 between the fuselage connection and the service tray assembly Figure 5 16 2 5 9 Remove the caps and install the hydraulic pipe Figure 5 5 between the fuselage connection and the service tray assembly Figure 5 16 2 5 10 ...

Page 586: ... D 7 6 2 10 11 12 B 13 K 14 15 L 17 18 3 6 7 5 4 Figure 5 Left Wing Removal Installation Hydraulic Pipelines PC 12 47E AMM Doc No 02300 ISSUE 01 REVISION 26 MSN 545 1001 1719 1721 1999 12 B AM 00 00 00 I UNCLASSIFIED Effectivity All 12 B 57 00 00 00A 720A A UNCLASSIFIED 2021 12 04 Page 15 ...

Page 587: ...efer to Fig 6 Make sure that The loop clamps are correctly secured to the de ice pipe and the hydraulic pipe The wires do not touch any pipes or structure PC 12 47E AMM Doc No 02300 ISSUE 01 REVISION 26 MSN 545 1001 1719 1721 1999 12 B AM 00 00 00 I UNCLASSIFIED Effectivity All 12 B 57 00 00 00A 720A A UNCLASSIFIED 2021 12 04 Page 16 ...

Page 588: ...G PIPES B B HYDRAULIC PIPE A B TYPICAL HYDRAULIC SYSTEM Figure 6 Wiring Harness Loop Clamp Check PC 12 47E AMM Doc No 02300 ISSUE 01 REVISION 26 MSN 545 1001 1719 1721 1999 12 B AM 00 00 00 I UNCLASSIFIED Effectivity All 12 B 57 00 00 00A 720A A UNCLASSIFIED 2021 12 04 Page 17 ...

Page 589: ...tem leak test refer to AMM 12 B 34 11 00 00A 903A A 3 13 Do the functional test of the flap system refer to AMM 12 B 27 50 00 00A 903A A 3 14 Do the functional test of the ailerons refer to AMM 12 B 27 10 00 00A 903A A 3 15 Lower the aircraft from jacks refer to AMM 12 B 07 10 00 00A 901A A 3 16 Remove the bolts Figure 8 10 washers Figure 8 9 and nuts Figure 8 8 from the two fuselage jacking point...

Page 590: ...ork area is clean 3 26 Install the access panels 12AL 12BL 12DL 12EL and 12FL 3 27 Close the access panel 11AL PC 12 47E AMM Doc No 02300 ISSUE 01 REVISION 26 MSN 545 1001 1719 1721 1999 12 B AM 00 00 00 I UNCLASSIFIED Effectivity All 12 B 57 00 00 00A 720A A UNCLASSIFIED 2021 12 04 Page 19 ...

Page 591: ... C 2 B 12 FR 12 ER Figure 7 Left Wing Removal Installation Preparation PC 12 47E AMM Doc No 02300 ISSUE 01 REVISION 26 MSN 545 1001 1719 1721 1999 12 B AM 00 00 00 I UNCLASSIFIED Effectivity All 12 B 57 00 00 00A 720A A UNCLASSIFIED 2021 12 04 Page 20 ...

Page 592: ...7 4 3 3 A 6 5 Figure 8 Wing Removal Installation Preparation and Close Up PC 12 47E AMM Doc No 02300 ISSUE 01 REVISION 26 MSN 545 1001 1719 1721 1999 12 B AM 00 00 00 I UNCLASSIFIED Effectivity All 12 B 57 00 00 00A 720A A UNCLASSIFIED 2021 12 04 Page 21 ...

Page 593: ...ed Conditions Action Condition Data module Technical publication None PC 12 47E AMM Doc No 02300 ISSUE 01 REVISION 26 MSN 545 1001 1719 1721 1999 12 B AM 00 00 00 I UNCLASSIFIED Effectivity All 12 B 57 00 00 00A 720A A End of data module UNCLASSIFIED 2021 12 04 Page 22 ...

Page 594: ... MSN 1576 9999 Close Up 19 8 Left Wing Installation Close Up 20 References Table 1 References Data module Technical publication Title 12 B 00 00 00 00A 060A A GENERAL LIST OF AEROSPACE GROUND EQUIPMENT AGE AND TOOLS 12 B 05 50 06 00A 282A A ALIGNMENT AND SYMMETRY UNSCHEDULED INSPEC TIONS 12 B 07 10 00 00A 901A A JACKING MAINTENANCE PRACTICES 12 B 20 31 00 00A 070A A STANDARD PRACTICES CONSUMABLE M...

Page 595: ...REMOVAL INSTALLATION 12 B 32 30 10 00A 903A A EMERGENCY GEAR EXTENSION SYSTEM ELECTRO ME CHANICAL LANDING GEAR ADJUSTMENT TEST 12 B 32 40 00 00A 902A A WHEELS AND BRAKES SERVICING 12 B 33 40 00 00A 903A A EXTERNAL LIGHTS ADJUSTMENT TEST 12 B 34 11 00 00A 903A A PITOT STATIC SYSTEM ADJUSTMENT TEST 12 B 57 00 00 00A 520B A LEFT WING ELECTRO MECHANICAL LANDING GEAR REMOVAL 12 B 57 33 00 00A 920B A WI...

Page 596: ...AL INSTRUCTIONS CONSUMABLE MATERIALS CAN BE DANGEROUS AND CAN CAUSE DEATH OR INJURY TO PERSONNEL AND OR DAMAGE TO EQUIPMENT CAUTION THE TORQUE VALUES GIVEN IN THIS PROCEDURE ARE FOR LUBRICATED THREADS DO NOT USE ANY CORRECTION FACTORS WHEN YOU TORQUE THE FASTENERS Note To identify the consumable items used in this procedure refer to the Consumable Materials List AMM 12 B 20 31 00 00A 070A A Note T...

Page 597: ...er of Corrosion preventive Pt No P04 039 to the outer surface of the long bolt Figure 1 5 Make sure the outer surface of the bolt is completely covered with the corrosion preventative Put the installation tools Figure 1 30 and Figure 1 31 in the ends of the long bolt Figure 1 5 as shown in the example on Fig 1 2 1 7 Put the new rear top bolt Figure 1 25 and washer Figure 1 23 in position through t...

Page 598: ...1 1 head washers Figure 1 3 and Figure 1 2 and the nut Figure 1 6 Torque the nut Figure 1 6 to 50 Nm 443 lbf in Remove the nut Figure 1 6 washers Figure 1 3 Figure 1 2 and the bolt Figure 1 1 Discard the used bolt Figure 1 1 Note The bolt Figure 1 1 is a tension bolt which can only be torque tightened once It is used in the above step as a tool with a high torque value to correctly position the bu...

Page 599: ...1 23 with the chamfer towards the fitting Use Grease Pt No P04 029 to lubricate the nut Install the new nut Figure 1 22 and torque to between 112 and 120 Nm 992 and 1062 lbf in plus the nut friction torque Make sure the washer Figure 1 23 does not turn when the nut Figure 1 22 is torque tightened PC 12 47E AMM Doc No 02300 ISSUE 01 REVISION 26 MSN 545 1001 1719 1721 1999 12 B AM 00 00 00 I UNCLASS...

Page 600: ... B A A LEFT SHOWN RIGHT SIMILAR 12 A 570000 A S4080 30109 A 03 1 C Figure 1 Wing Installation Attachment Fittings PC 12 47E AMM Doc No 02300 ISSUE 01 REVISION 26 MSN 545 1001 1719 1721 1999 12 B AM 00 00 00 I UNCLASSIFIED Effectivity All 12 B 57 00 00 00A 720B A UNCLASSIFIED 2021 12 04 Page 7 ...

Page 601: ...T SIMILAR SECTION A A 28 29 SECTION B B 28 29 Figure 1 Wing Installation Attachment Fittings PC 12 47E AMM Doc No 02300 ISSUE 01 REVISION 26 MSN 545 1001 1719 1721 1999 12 B AM 00 00 00 I UNCLASSIFIED Effectivity All 12 B 57 00 00 00A 720B A UNCLASSIFIED 2021 12 04 Page 8 ...

Page 602: ...5 and Figure 2 6 from around the forward and aft main spars 2 2 4 Remove the lift strap Figure 2 7 and shackle Figure 2 8 from the outer wing adapter Figure 2 3 2 2 5 Remove the screws Figure 2 2 and the outer wing adapter Figure 2 3 from the end of the wing Figure 2 4 PC 12 47E AMM Doc No 02300 ISSUE 01 REVISION 26 MSN 545 1001 1719 1721 1999 12 B AM 00 00 00 I UNCLASSIFIED Effectivity All 12 B 5...

Page 603: ... SIMILAR C 2 3 4 7 8 1 Figure 2 Wing Installation Sling Attachment Removal PC 12 47E AMM Doc No 02300 ISSUE 01 REVISION 26 MSN 545 1001 1719 1721 1999 12 B AM 00 00 00 I UNCLASSIFIED Effectivity All 12 B 57 00 00 00A 720B A UNCLASSIFIED 2021 12 04 Page 10 ...

Page 604: ...4 8 2 3 6 Remove the caps and connect the wing electrical connectors Figure 4 1 Figure 4 2 Figure 4 3 and Figure 4 4 to the fuselage electrical connectors 2 4 Equipment Connection at the Wing Bottom Center 2 4 1 Put the ends of the bonding straps Figure 3 9 in position and install the bolt Figure 3 10 and nut Figure 3 11 2 4 2 Remove the caps and install the brake pipe Figure 3 8 between the fusel...

Page 605: ...RIGHT SIMILAR C 12 A 570000 A S4080 00869 A 02 1 Figure 3 Left Wing Installation Bottom Center Equipment PC 12 47E AMM Doc No 02300 ISSUE 01 REVISION 26 MSN 545 1001 1719 1721 1999 12 B AM 00 00 00 I UNCLASSIFIED Effectivity All 12 B 57 00 00 00A 720B A UNCLASSIFIED 2021 12 04 Page 12 ...

Page 606: ...0 11 12 14 15 8 16 5 3 B 18 19 20 17 1 B A Figure 4 Left Wing Installation Top and Rear Equipment PC 12 47E AMM Doc No 02300 ISSUE 01 REVISION 26 MSN 545 1001 1719 1721 1999 12 B AM 00 00 00 I UNCLASSIFIED Effectivity All 12 B 57 00 00 00A 720B A UNCLASSIFIED 2021 12 04 Page 13 ...

Page 607: ...on light refer to Fig 5 Make sure that The loop clamps are correctly secured to the de ice pipe The wires do not touch any pipes or structure PC 12 47E AMM Doc No 02300 ISSUE 01 REVISION 26 MSN 545 1001 1719 1721 1999 12 B AM 00 00 00 I UNCLASSIFIED Effectivity All 12 B 57 00 00 00A 720B A UNCLASSIFIED 2021 12 04 Page 14 ...

Page 608: ...PIPES 12 B 570000 A S4080 04091 A 01 1 Figure 5 Wiring Harness Loop Clamp Check PC 12 47E AMM Doc No 02300 ISSUE 01 REVISION 26 MSN 545 1001 1719 1721 1999 12 B AM 00 00 00 I UNCLASSIFIED Effectivity All 12 B 57 00 00 00A 720B A UNCLASSIFIED 2021 12 04 Page 15 ...

Page 609: ... 15 Do the functional test of the ailerons refer to AMM 12 B 27 10 00 00A 903A A 3 16 Lower the aircraft from jacks refer to AMM 12 B 07 10 00 00A 901A A 3 17 MSN 1300 1451 1575 Remove the bolts Figure 6 10 washers Figure 6 9 and nuts Figure 6 8 from the two fuselage jacking points Figure 6 11 Put the straps Figure 6 12 in position on the jack points Figure 6 11 and install the four bolts Figure 6...

Page 610: ...rational test of the probes de ice system refer to AMM 12 B 30 30 20 00A 903A A 3 26 Remove all the equipment tools and materials from the work area Make sure that the work area is clean 3 27 Install the access panels 12AL 12BL 12DL 12EL and 12FL 3 28 Close the access panel 11AL PC 12 47E AMM Doc No 02300 ISSUE 01 REVISION 26 MSN 545 1001 1719 1721 1999 12 B AM 00 00 00 I UNCLASSIFIED Effectivity ...

Page 611: ...0 7 4 3 3 A 6 5 Figure 6 Wing Installation MSN 1300 1451 9999 Close Up PC 12 47E AMM Doc No 02300 ISSUE 01 REVISION 26 MSN 545 1001 1719 1721 1999 12 B AM 00 00 00 I UNCLASSIFIED Effectivity All 12 B 57 00 00 00A 720B A UNCLASSIFIED 2021 12 04 Page 18 ...

Page 612: ... 570000 A S4080 79090 A 01 1 13 14 Figure 7 Wing Installation MSN 1576 9999 Close Up PC 12 47E AMM Doc No 02300 ISSUE 01 REVISION 26 MSN 545 1001 1719 1721 1999 12 B AM 00 00 00 I UNCLASSIFIED Effectivity All 12 B 57 00 00 00A 720B A UNCLASSIFIED 2021 12 04 Page 19 ...

Page 613: ...BL B 12 B 570000 A S4080 00014 A 02 1 Figure 8 Left Wing Installation Close Up PC 12 47E AMM Doc No 02300 ISSUE 01 REVISION 26 MSN 545 1001 1719 1721 1999 12 B AM 00 00 00 I UNCLASSIFIED Effectivity All 12 B 57 00 00 00A 720B A UNCLASSIFIED 2021 12 04 Page 20 ...

Page 614: ...ed Conditions Action Condition Data module Technical publication None PC 12 47E AMM Doc No 02300 ISSUE 01 REVISION 26 MSN 545 1001 1719 1721 1999 12 B AM 00 00 00 I UNCLASSIFIED Effectivity All 12 B 57 00 00 00A 720B A End of data module UNCLASSIFIED 2021 12 04 Page 21 ...

Page 615: ... 12 47E AMM Doc No 02300 ISSUE 01 REVISION 26 MSN 545 1001 1719 1721 1999 12 B AM 00 00 00 I UNCLASSIFIED Intentionally left blank Effectivity All 12 B 57 00 00 00A 720B A UNCLASSIFIED 2021 12 04 Page 22 ...

Page 616: ...Preparation and Close Up 19 References Table 1 References Data module Technical publication Title 12 B 05 50 06 00A 282A A ALIGNMENT AND SYMMETRY UNSCHEDULED INSPEC TIONS 12 B 07 10 00 00A 901A A JACKING MAINTENANCE PRACTICES 12 B 20 31 00 00A 070A A STANDARD PRACTICES CONSUMABLE MATERIALS LIST 12 B 22 20 00 00A 903A A SPEED AND ATTITUDE CORRECTION ADJUST MENT TEST 12 B 24 30 07 00A 920A A LEAD AC...

Page 617: ... 11 00 00A 903A A PITOT STATIC SYSTEM ADJUSTMENT TEST 12 B 34 41 00 00A 903A A WEATHER RADAR ADJUSTMENT TEST 12 B 57 00 00 00B 520A A RIGHT WING HYDRAULIC LANDING GEAR REMOVAL 12 B 57 33 00 00A 920A A WING TIP REMOVAL INSTALLATION Preliminary Requirements Required Conditions Table 2 Required Conditions Action Condition Data module Technical publication None Support equipment Table 3 Support equipm...

Page 618: ...DO NOT USE ANY CORRECTION FACTORS WHEN YOU TORQUE THE FASTENERS Note To identify the consumables used in this procedure refer to the Consumable Materials List AMM 12 B 20 31 00 00A 070A A Procedure 1 General This procedure assumes that the right wing is removed as given in AMM 12 B 57 00 00 00B 520A A 2 CAUTION DAMAGE TO THE FUSELAGE AND WING BUSHINGS WILL OCCUR IF TOO MUCH FORCE IS ON THE WING BO...

Page 619: ...y lift the wing and move it into position Align the forward top bushes in the wing fittings and the fuselage fittings 2 1 9 Install the forward top long bolt Figure 1 5 through the wing and fuselage fittings Figure 1 4 Use only hand force to install the long bolt Figure 1 5 Remove the installation tools Figure 1 30 and Figure 1 31 from the long bolt Figure 1 5 If the long bolt Figure 1 5 cannot be...

Page 620: ... 3 with the chamfer towards the bolt Figure 1 1 head washer Figure 1 3 washer Figure 1 2 and the new nut Figure 1 6 Torque the nut Figure 1 6 to between 24 and 25 6 Nm 213 and 226 lbf in plus the nut friction torque 2 1 20 Use Grease Pt No P04 029 to lubricate the parts Install the new rear bottom bolt Figure 1 21 washers Figure 1 17 and Figure 1 16 and the new nut Figure 1 15 Torque the nut Figur...

Page 621: ... B A A LEFT SHOWN RIGHT SIMILAR 12 A 570000 A S4080 30109 A 03 1 C Figure 1 Wing Installation Attachment Fittings PC 12 47E AMM Doc No 02300 ISSUE 01 REVISION 26 MSN 545 1001 1719 1721 1999 12 B AM 00 00 00 I UNCLASSIFIED Effectivity All 12 B 57 00 00 00B 720A A UNCLASSIFIED 2021 12 04 Page 6 ...

Page 622: ...T SIMILAR SECTION A A 28 29 SECTION B B 28 29 Figure 1 Wing Installation Attachment Fittings PC 12 47E AMM Doc No 02300 ISSUE 01 REVISION 26 MSN 545 1001 1719 1721 1999 12 B AM 00 00 00 I UNCLASSIFIED Effectivity All 12 B 57 00 00 00B 720A A UNCLASSIFIED 2021 12 04 Page 7 ...

Page 623: ... and Figure 2 6 from around the forward and aft main spar 2 2 4 Remove the lift strap Figure 2 7 and shackle Figure 2 8 from the outer wing adapter Figure 2 3 2 2 5 Remove the screws Figure 2 2 and the outer wing adapter Figure 2 3 from the end of the wing Figure 2 4 PC 12 47E AMM Doc No 02300 ISSUE 01 REVISION 26 MSN 545 1001 1719 1721 1999 12 B AM 00 00 00 I UNCLASSIFIED Effectivity All 12 B 57 ...

Page 624: ...MILAR C 2 3 4 7 8 1 Figure 2 Wing Removal Installation Sling Attachment Removal PC 12 47E AMM Doc No 02300 ISSUE 01 REVISION 26 MSN 545 1001 1719 1721 1999 12 B AM 00 00 00 I UNCLASSIFIED Effectivity All 12 B 57 00 00 00B 720A A UNCLASSIFIED 2021 12 04 Page 9 ...

Page 625: ... 9 2 3 3 Remove the caps and connect the three wing electrical connectors Figure 3 1 Figure 3 2 and Figure 3 3 and four if installed to the fuselage electrical connectors 2 3 4 Connect the right inboard flap drive shaft Figure 3 6 refer to AMM 12 B 27 50 02 00A 920A A 2 3 5 Attach the pitot pipe Figure 3 8 to the support angle Figure 3 4 with the Cable tie Pt No P09 008 Figure 3 5 PC 12 47E AMM Do...

Page 626: ... 4 5 6 B 16 15 C B C Figure 3 Right Wing Removal Installation Top and Rear Equipment PC 12 47E AMM Doc No 02300 ISSUE 01 REVISION 26 MSN 545 1001 1719 1721 1999 12 B AM 00 00 00 I UNCLASSIFIED Effectivity All 12 B 57 00 00 00B 720A A UNCLASSIFIED 2021 12 04 Page 11 ...

Page 627: ...el pipes Figure 4 3 Figure 4 4 and Figure 4 5 between the fuselage and the connections in the landing gear compartment 2 4 3 Remove the caps and install the two hydraulic pipes Figure 4 1 and Figure 4 2 that go across below the fuselage PC 12 47E AMM Doc No 02300 ISSUE 01 REVISION 26 MSN 545 1001 1719 1721 1999 12 B AM 00 00 00 I UNCLASSIFIED Effectivity All 12 B 57 00 00 00B 720A A UNCLASSIFIED 2...

Page 628: ...000 A S4080 00876 A 02 1 Figure 4 Right Wing Removal Installation Bottom Center Equipment PC 12 47E AMM Doc No 02300 ISSUE 01 REVISION 26 MSN 545 1001 1719 1721 1999 12 B AM 00 00 00 I UNCLASSIFIED Effectivity All 12 B 57 00 00 00B 720A A UNCLASSIFIED 2021 12 04 Page 13 ...

Page 629: ...he de ice pipe Figure 5 3 between the elbow connection Figure 5 4 and the fuselage connection 2 5 4 Connect the two de ice pipes Figure 5 5 and Figure 5 6 that go across below the fuselage 2 5 5 Remove the caps and install the de ice pipe Figure 5 8 to the cross connector Figure 5 9 2 5 6 Install the screw Figure 5 7 through the clip and distance bush Figure 5 10 PC 12 47E AMM Doc No 02300 ISSUE 0...

Page 630: ...2 13 11 Figure 5 Right Wing Removal Installation Rear De ice Pipelines PC 12 47E AMM Doc No 02300 ISSUE 01 REVISION 26 MSN 545 1001 1719 1721 1999 12 B AM 00 00 00 I UNCLASSIFIED Effectivity All 12 B 57 00 00 00B 720A A UNCLASSIFIED 2021 12 04 Page 15 ...

Page 631: ...en the rear cross connector Figure 6 6 and the fuselage 2 6 8 Remove the caps and install the de ice pipe Figure 6 1 between the forward cross connector Figure 6 19 and the fuselage 2 6 9 Remove the caps and install the two forward de ice pipes Figure 6 2 and Figure 6 17 between the wing and the forward and rear cross reducers Figure 6 6 and Figure 6 19 2 6 10 Remove the electrical cable temporary...

Page 632: ...FR 12 ER 12 DR 12 AB B Figure 6 Right Wing Removal Installation Panels and Forward De ice Pipelines PC 12 47E AMM Doc No 02300 ISSUE 01 REVISION 26 MSN 545 1001 1719 1721 1999 12 B AM 00 00 00 I UNCLASSIFIED Effectivity All 12 B 57 00 00 00B 720A A UNCLASSIFIED 2021 12 04 Page 17 ...

Page 633: ...cking points Figure 7 11 Put the straps Figure 7 12 in position on the jack points Figure 7 11 and install the four bolts Figure 7 10 washers Figure 7 9 and nuts Figure 7 8 3 12 Do the test of fuel balancing system refer to AMM 12 B 28 21 00 00A 903A A 3 13 Examine all the fuel and hydraulic pipes that were removed and disconnected for leaks No leaks are permitted 3 14 Install the fuel pipe covers...

Page 634: ...7 4 3 3 A 6 5 Figure 7 Wing Removal Installation Preparation and Close Up PC 12 47E AMM Doc No 02300 ISSUE 01 REVISION 26 MSN 545 1001 1719 1721 1999 12 B AM 00 00 00 I UNCLASSIFIED Effectivity All 12 B 57 00 00 00B 720A A UNCLASSIFIED 2021 12 04 Page 19 ...

Page 635: ...ed Conditions Action Condition Data module Technical publication None PC 12 47E AMM Doc No 02300 ISSUE 01 REVISION 26 MSN 545 1001 1719 1721 1999 12 B AM 00 00 00 I UNCLASSIFIED Effectivity All 12 B 57 00 00 00B 720A A End of data module UNCLASSIFIED 2021 12 04 Page 20 ...

Page 636: ...tallation MSN 1300 1451 1575 Close Up 21 8 Wing Installation MSN 1576 9999 Close Up 22 References Table 1 References Data module Technical publication Title 12 B 00 00 00 00A 060A A GENERAL LIST OF AEROSPACE GROUND EQUIPMENT AGE AND TOOLS 12 B 05 50 06 00A 282A A ALIGNMENT AND SYMMETRY UNSCHEDULED INSPEC TIONS 12 B 07 10 00 00A 901A A JACKING MAINTENANCE PRACTICES 12 B 20 31 00 00A 070A A STANDARD...

Page 637: ...MECHANI CAL LANDING GEAR REMOVAL INSTALLATION 12 B 32 40 00 00A 902A A WHEELS AND BRAKES SERVICING 12 B 33 40 00 00A 903A A EXTERNAL LIGHTS ADJUSTMENT TEST 12 B 34 11 00 00A 903A A PITOT STATIC SYSTEM ADJUSTMENT TEST 12 B 34 41 00 00A 903A A WEATHER RADAR ADJUSTMENT TEST 12 B 57 00 00 00B 520B A RIGHT WING ELECTRO MECHANICAL LANDING GEAR REMOVAL 12 B 57 33 00 00A 920B A WING TIP LED EXTERNAL LIGHT...

Page 638: ...S HEALTH AND SAFETY INSTRUCTIONS AND ALL THE APPLICABLE LOCAL INSTRUCTIONS CONSUMABLE MATERIALS CAN BE DANGEROUS AND CAN CAUSE DEATH OR INJURY TO PERSONNEL AND OR DAMAGE TO EQUIPMENT CAUTION THE TORQUE VALUES GIVEN IN THIS PROCEDURE ARE FOR LUBRICATED THREADS DO NOT USE ANY CORRECTION FACTORS WHEN YOU TORQUE THE FASTENERS Note To identify the consumables used in this procedure refer to the Consuma...

Page 639: ... the rear top fitting bolt Figure 1 25 2 1 5 Apply a layer of Corrosion preventive Pt No P04 039 to sides of the washers Figure 1 3 Figure 1 9 and Figure 1 17 that touch the fuselage and wing fittings 2 1 6 Apply a layer of Corrosion preventive Pt No P04 039 to the outer surface of the long bolt Figure 1 5 Make sure the outer surface of the bolt is completely covered with the corrosion preventive ...

Page 640: ...ol Figure 1 28 with hand force only to turn the knurled nut to fully install the long bolt 2 1 17 Remove all the unwanted corrosion preventive material from the wing and fuselage fittings 2 1 18 Install the forward top bolt Figure 1 1 that was removed during the wing removal washer Figure 1 2 washer Figure 1 3 with the chamfer towards the bolt Figure 1 1 head washers Figure 1 3 and Figure 1 2 and ...

Page 641: ...install a shim Figure 1 26 between the fuselage frame 24 and the wing rear spar 2 1 25 Install the shim Figure 1 26 if previously installed and the washer Figure 1 23 with the chamfer towards the fitting Use Paste Pt No P04 029 to lubricate the nut Install the new nut Figure 1 22 and torque to between 112 and 120 Nm 992 and 1062 lbf in plus the nut friction torque Make sure the washer Figure 1 23 ...

Page 642: ... B A A LEFT SHOWN RIGHT SIMILAR 12 A 570000 A S4080 30109 A 03 1 C Figure 1 Wing Installation Attachment Fittings PC 12 47E AMM Doc No 02300 ISSUE 01 REVISION 26 MSN 545 1001 1719 1721 1999 12 B AM 00 00 00 I UNCLASSIFIED Effectivity All 12 B 57 00 00 00B 720B A UNCLASSIFIED 2021 12 04 Page 7 ...

Page 643: ...T SIMILAR SECTION A A 28 29 SECTION B B 28 29 Figure 1 Wing Installation Attachment Fittings PC 12 47E AMM Doc No 02300 ISSUE 01 REVISION 26 MSN 545 1001 1719 1721 1999 12 B AM 00 00 00 I UNCLASSIFIED Effectivity All 12 B 57 00 00 00B 720B A UNCLASSIFIED 2021 12 04 Page 8 ...

Page 644: ...and Figure 2 6 from around the forward and aft main spars 2 2 4 Remove the lift strap Figure 2 7 and shackle Figure 2 8 from the outer wing adapter Figure 3 3 2 2 5 Remove the screws Figure 2 2 and the outer wing adapter Figure 3 3 from the end of the wing Figure 2 4 PC 12 47E AMM Doc No 02300 ISSUE 01 REVISION 26 MSN 545 1001 1719 1721 1999 12 B AM 00 00 00 I UNCLASSIFIED Effectivity All 12 B 57 ...

Page 645: ... SIMILAR C 2 3 4 7 8 1 Figure 2 Wing Installation Sling Attachment Removal PC 12 47E AMM Doc No 02300 ISSUE 01 REVISION 26 MSN 545 1001 1719 1721 1999 12 B AM 00 00 00 I UNCLASSIFIED Effectivity All 12 B 57 00 00 00B 720B A UNCLASSIFIED 2021 12 04 Page 10 ...

Page 646: ...and the nut Figure 3 20 2 3 4 Remove the caps and connect the wing electrical connectors Figure 3 1 Figure 3 2 Figure 3 3 and Figure 3 4 to the fuselage electrical connectors 2 3 5 Connect the right inboard flap drive shaft refer to AMM 12 B 27 50 02 00A 920A A 2 3 6 Attach the pitot pipe Figure 3 10 to the support angle Figure 3 5 with the Cable tie Pt No P09 008 Figure 3 6 2 3 7 Connect the emer...

Page 647: ...4 9 8 5 6 15 16 C 17 18 19 20 C 21 3 1 2 13 4 A Figure 3 Right Wing Installation Top and Rear Equipment PC 12 47E AMM Doc No 02300 ISSUE 01 REVISION 26 MSN 545 1001 1719 1721 1999 12 B AM 00 00 00 I UNCLASSIFIED Effectivity All 12 B 57 00 00 00B 720B A UNCLASSIFIED 2021 12 04 Page 12 ...

Page 648: ...e caps and install the grommet Figure 4 7 and the three fuel pipes Figure 4 1 Figure 4 2 and Figure 4 3 between the fuselage and the connections in the landing gear compartment PC 12 47E AMM Doc No 02300 ISSUE 01 REVISION 26 MSN 545 1001 1719 1721 1999 12 B AM 00 00 00 I UNCLASSIFIED Effectivity All 12 B 57 00 00 00B 720B A UNCLASSIFIED 2021 12 04 Page 13 ...

Page 649: ...80 00008 A 02 1 D B Figure 4 Right Wing Installation Bottom Center Equipment PC 12 47E AMM Doc No 02300 ISSUE 01 REVISION 26 MSN 545 1001 1719 1721 1999 12 B AM 00 00 00 I UNCLASSIFIED Effectivity All 12 B 57 00 00 00B 720B A UNCLASSIFIED 2021 12 04 Page 14 ...

Page 650: ...ce pipe Figure 5 3 between the elbow connection Figure 5 4 and the fuselage connection 2 5 4 Connect the two de ice pipes Figure 5 5 and Figure 5 6 that go across below the fuselage 2 5 5 Remove the caps and install the de ice pipe Figure 5 8 to the cross connector Figure 5 9 2 5 6 Install the screw Figure 5 7 through the clip and distance bush Figure 5 10 PC 12 47E AMM Doc No 02300 ISSUE 01 REVIS...

Page 651: ... 9 12 13 11 Figure 5 Right Wing Installation Rear De ice Pipelines PC 12 47E AMM Doc No 02300 ISSUE 01 REVISION 26 MSN 545 1001 1719 1721 1999 12 B AM 00 00 00 I UNCLASSIFIED Effectivity All 12 B 57 00 00 00B 720B A UNCLASSIFIED 2021 12 04 Page 16 ...

Page 652: ...en the rear cross connector Figure 6 6 and the fuselage 2 6 8 Remove the caps and install the de ice pipe Figure 6 1 between the forward cross connector Figure 6 19 and the fuselage 2 6 9 Remove the caps and install the two forward de ice pipes Figure 6 2 and Figure 6 17 between the wing and the forward and rear cross reducers Figure 6 6 and Figure 6 19 2 6 10 Remove the electrical cable temporary...

Page 653: ... 12 FR 12 ER 12 DR 12 AB B Figure 6 Right Wing Installation Panels and Forward De ice Pipelines PC 12 47E AMM Doc No 02300 ISSUE 01 REVISION 26 MSN 545 1001 1719 1721 1999 12 B AM 00 00 00 I UNCLASSIFIED Effectivity All 12 B 57 00 00 00B 720B A UNCLASSIFIED 2021 12 04 Page 18 ...

Page 654: ...ack points Figure 8 11 from frame 21 Put the fuselage jack points Figure 8 11 and the two bolts removed from the aft positions into the Wing removal installation kit MSN 1001 9999 Pt No T57 010 Install the original aft bolts removed and kept during wing removal and the existing forward bolts Figure 8 10 the washers Figure 8 9 and Figure 8 13 and the nuts Figure 8 8 and Figure 8 14 Note The longer ...

Page 655: ...lose the access panel 11AL PC 12 47E AMM Doc No 02300 ISSUE 01 REVISION 26 MSN 545 1001 1719 1721 1999 12 B AM 00 00 00 I UNCLASSIFIED Effectivity All 12 B 57 00 00 00B 720B A UNCLASSIFIED 2021 12 04 Page 20 ...

Page 656: ...0 7 4 3 3 A 6 5 Figure 7 Wing Installation MSN 1300 1451 1575 Close Up PC 12 47E AMM Doc No 02300 ISSUE 01 REVISION 26 MSN 545 1001 1719 1721 1999 12 B AM 00 00 00 I UNCLASSIFIED Effectivity All 12 B 57 00 00 00B 720B A UNCLASSIFIED 2021 12 04 Page 21 ...

Page 657: ... 570000 A S4080 79090 A 01 1 13 14 Figure 8 Wing Installation MSN 1576 9999 Close Up PC 12 47E AMM Doc No 02300 ISSUE 01 REVISION 26 MSN 545 1001 1719 1721 1999 12 B AM 00 00 00 I UNCLASSIFIED Effectivity All 12 B 57 00 00 00B 720B A UNCLASSIFIED 2021 12 04 Page 22 ...

Page 658: ...ed Conditions Action Condition Data module Technical publication None PC 12 47E AMM Doc No 02300 ISSUE 01 REVISION 26 MSN 545 1001 1719 1721 1999 12 B AM 00 00 00 I UNCLASSIFIED Effectivity All 12 B 57 00 00 00B 720B A End of data module UNCLASSIFIED 2021 12 04 Page 23 ...

Page 659: ... 12 47E AMM Doc No 02300 ISSUE 01 REVISION 26 MSN 545 1001 1719 1721 1999 12 B AM 00 00 00 I UNCLASSIFIED Intentionally left blank Effectivity All 12 B 57 00 00 00B 720B A UNCLASSIFIED 2021 12 04 Page 24 ...

Page 660: ...Title 12 B 00 00 00 00A 060A A GENERAL LIST OF AEROSPACE GROUND EQUIPMENT AGE AND TOOLS 12 B 06 20 00 00A 040A A ACCESS PROVISION DESCRIPTION 12 B 12 20 05 00A 902B A FIVE BLADED PROPELLER SERVICING 12 B 20 31 00 00A 070A A STANDARD PRACTICES CONSUMABLE MATERIALS LIST 12 B 24 00 00 00A 901A A ELECTRICAL POWER MAINTENANCE PRACTICES 12 B 61 10 01 00A 920B A FIVE BLADED PROPELLER REMOVAL INSTALLATION...

Page 661: ...ations References Qty Reference Remark Lockwire Part P02 007 AR Cable tie Part P09 014 AR Masking tape Part Local supply AR Spares Table 5 Spares Name Identifications References Qty Reference Remark Bolt AN3 10A Propeller balance weights CSN 61 10 00 01 035 AR Bolt AN3 7A Propeller balance weights CSN 61 10 00 01 040 AR Bolt AN3 6A Propeller balance weights CSN 61 10 00 01 045 AR Bolt AN3 5A Prope...

Page 662: ... 00 00 00A 060A A Note To identify the access panels refer to access provision AMM 12 B 06 20 00 00A 040A A Note For removal and installation of engine cowlings refer to AMM 12 B 71 10 00 00A 920A A Procedure 1 General This document gives the procedures to do a dynamic balance of the propeller with the Vibrex 8350 or the Vibrex 2000 propeller balancing equipment The job set up information preparat...

Page 663: ...Figure 1 5 2 2 Install The Propeller Balancing Kit 2 2 1 From the Propeller balancing kit Vibrex 8350 Pt No 513 61 12 001 or the Dynamic balancing equipment Pt No T61 005 install the interrupter bracket Figure 1 12 and counterweight Figure 1 20 2 2 1 1 On the spinner dome Figure 1 3 remove a center screw Figure 1 6 and washer Figure 1 5 from between the propeller blades 2 2 1 2 Install the interru...

Page 664: ... electrical cables Figure 1 1 and Figure 1 2 along the engine and out of the engine compartment through the access hole of access panel 21AL 2 2 3 4 Open the DV window and put the electrical cables Figure 1 1 and Figure 1 2 through the DV window and into the flight compartment 2 2 3 5 Attach the electrical cables Figure 1 1 and Figure 1 2 to the engine and the structure with Cable tie Pt No P09 01...

Page 665: ...itch 3 2 12 Move the PCL forward until the torque gage on the PFD shows approximately 35 psi Note Use the 35 psi torque setting for all subsequent tests until the propeller is balanced 3 2 13 Adjust the RPM TUNE selector on the balancer phazor until the counter shows the same Np as the PFD divided by 10 3 2 14 Make a note of the clock position of the phazor light that is on VERIFY TUNE switch rele...

Page 666: ... at the propeller Figure 1 4 from the front of the aircraft and install the balance weights on the propeller bulkhead at the positions shown on data sheet Chart C 3 3 6 Install the engine cowling 42AB 3 3 7 Do the test of the propeller balance again 3 4 Disconnect The Balancer Phazor 3 4 1 Disconnect the 28 VDC connection on the balancer phazor from the test box 3 4 2 Disconnect the electrical cab...

Page 667: ...ive a torque indication of approximately 35 psi at maximum rpm Note Use the same torque value on all subsequent checks 4 2 15 Monitor the note on the display when the RPM is stable push the START key 4 2 16 When the unit has collected the data push the START key 4 2 17 Make a record of the indications shown on the screen on the Propeller Balance Chart B then push the START key 4 2 18 If the screen...

Page 668: ...lectrical cables Figure 1 1 and Figure 1 2 5 4 Disconnect the electrical connector Figure 1 7 from the velometer Figure 1 8 5 5 Disconnect the electrical connector Figure 1 17 from the magnetic pick up Figure 1 18 5 6 Remove the cable ties and the masking tape from the electrical wires Figure 1 1 and Figure 1 2 5 7 Remove the electrical cables Figure 1 1 and Figure 1 2 from the engine compartment ...

Page 669: ... 5 17 Remove the safety clip and close the circuit breaker STARTER ESSENTIAL BUS 6 Close Up 6 1 Make sure that the work area is clean and clear of tools and other items 6 2 Close the engine cowling 43AL 6 3 Install the engine cowling 42AT 6 4 Make sure that the Propeller Balance Chart Data Sheet is complete 6 5 Make a note of the quantities and the positions of the balance weights added to the pro...

Page 670: ... C 12 B 611000 A S4080 79148 A 02 1 Figure 1 Five Bladed Propeller Adjustment Test Preparation PC 12 47E AMM Doc No 02300 ISSUE 01 REVISION 26 MSN 545 1001 1719 1721 1999 12 B AM 00 00 00 I UNCLASSIFIED Effectivity All 12 B 61 00 00 00A 903B A UNCLASSIFIED 2021 12 04 Page 11 ...

Page 671: ...100 999 R P M MAX 99 900 R P M MAX X10 9 9990 R P M MAX A B TRACK FUNCTION PHAZOR INTERRUPTER LOGIC SWITCH TEST SWITCH PHAZOR LIGHTS R P M RANGE SELECTOR MAGNETIC PICKUP SWITCH ACCELEROMETER CONNECTION CHANNEL A FUNCTION SELECTOR R P M TUNE SELECTOR BANDPASS FILTER VERIFY TUNE SWITCH Figure 2 Dynamic Balancer Phazor Connection Test PC 12 47E AMM Doc No 02300 ISSUE 01 REVISION 26 MSN 545 1001 1719 ...

Page 672: ...N OFF CONNECTION INTERFACES CONTEXT KEYS CONTRAST KEYS KEYPAD DISPLAY SCREEN BATTERY END PLATE Figure 3 Vibrex 2000 Dynamic Balancer PC 12 47E AMM Doc No 02300 ISSUE 01 REVISION 26 MSN 545 1001 1719 1721 1999 12 B AM 00 00 00 I UNCLASSIFIED Effectivity All 12 B 61 00 00 00A 903B A UNCLASSIFIED 2021 12 04 Page 13 ...

Page 673: ...OSITION CLOCK 5th 4th 3rd 2nd 1st TRACKING CHECK MAXIMUM PROPELLER RPM IDLE CONDITION VIEWED FROM FRONT WEIGHT POSITIONS 11 10 9 8 7 6 5 4 3 2 1 12 GRAMS WEIGHT REQUIRED IPS IPS IPS 1 0 9 8 7 6 5 4 3 2 1 1 0 9 8 7 6 5 4 3 2 1 1 0 9 8 7 6 5 4 3 2 1 120 96 72 48 24 12 11 10 9 8 7 6 5 4 3 2 1 Figure 4 Propeller Balance Chart Data Sheet Layout PC 12 47E AMM Doc No 02300 ISSUE 01 REVISION 26 MSN 545 10...

Page 674: ...ed Conditions Action Condition Data module Technical publication None PC 12 47E AMM Doc No 02300 ISSUE 01 REVISION 26 MSN 545 1001 1719 1721 1999 12 B AM 00 00 00 I UNCLASSIFIED Effectivity All 12 B 61 00 00 00A 903B A End of data module UNCLASSIFIED 2021 12 04 Page 15 ...

Page 675: ... 12 47E AMM Doc No 02300 ISSUE 01 REVISION 26 MSN 545 1001 1719 1721 1999 12 B AM 00 00 00 I UNCLASSIFIED Intentionally left blank Effectivity All 12 B 61 00 00 00A 903B A UNCLASSIFIED 2021 12 04 Page 16 ...

Page 676: ...plant Compressor Wash Post SB 71 012 12 References Table 1 References Data module Technical publication Title 12 B 00 00 00 00A 060A A GENERAL LIST OF AEROSPACE GROUND EQUIPMENT AGE AND TOOLS 12 B 20 31 00 00A 070A A STANDARD PRACTICES CONSUMABLE MATERIALS LIST 12 B 24 00 00 00A 901A A ELECTRICAL POWER MAINTENANCE PRACTICES 12 B 71 00 00 00A 901A A POWERPLANT MAINTENANCE PRACTICES 12 B 74 20 00 00...

Page 677: ...Circuit breaker hold open Part T12 030 AR Spray tube Part P WC 32271 AR Compressor wash rig fitting Part T71 025 1 Post SB 71 012 Supplies Table 4 Supplies Name Identifications References Qty Reference Remark Cleaner alkaline Part P01 001 AR Anti seize compound Part P04 015 AR Emulsifier Part P01 003 AR Lockwire heat resistant Part P02 006 AR 0 6 mm 0 025 in diameter Lockwire standard Part P02 007...

Page 678: ...gives the procedures to do A desalination wash of the engine A performance recovery wash of the engine with operation of the starter motor A compressor turbine wash 2 Desalination Wash 2 1 Preparation 2 1 1 Refer to the vendor instructions and prepare the rinse solution in the Engine compressor wash rig Pt No T71 010 wash rig refer to Table 6 and Table 7 Note To prevent the precipitation of deposi...

Page 679: ...n the cockpit to measure the time of the operation 2 2 4 Stop the starter motor after 30 seconds 2 2 5 When the Ng decreases to 5 stop the supply of rinse solution to the engine 2 2 6 If a water methyl alcohol solution was used do a dry motor of the engine refer to AMM 12 B 71 00 00 00A 901A A 2 2 7 De energize the aircraft electrical system refer to AMM 12 B 24 00 00 00A 901A A 2 3 Close Up 2 3 1...

Page 680: ... cooling is 40 minutes since last operation 3 1 2 Pressurize the wash rig to between 2 and 3 5 bar 30 and 50 psi 3 1 3 Open and install a Safety clip Circuit breaker hold open Pt No T12 030 on this circuit breaker IGNITION ESSENTIAL BUS STARTER ESSENTIAL BUS 3 1 4 Remove the engine cowlings 42AT and 42AB 3 1 5 Open the engine cowlings 43AL and 43AR 3 1 6 Remove the clamp Figure 1 4 gasket Figure 1...

Page 681: ...the Ng decreases to 5 stop the supply of wash solution to the engine 3 2 6 Let the wash solution stay in the engine for between 15 and 30 minutes 3 2 7 Do the dry motor of the engine refer to AMM 12 B 71 00 00 00A 901A A When the Ng increases to 5 operate the wash rig to supply half of the rinse solution to the engine at a rate of 7 6 to 11 3 liter min 2 to 3 gal min 3 2 8 Use the chronograph in t...

Page 682: ...Figure 1 16 3 3 11 Remove the blanking cap Figure 1 10 from the P3 pipe Figure 1 9 3 3 12 Apply Anti seize compound Pt No P04 015 to the P3 pipe Figure 1 9 threads Connect the flexible hose Figure 1 11 to the P3 pipe Figure 1 9 3 3 13 Remove all the equipment tools and materials from the work area Make sure that the work area is clean 3 3 14 Install the engine cowlings 42AB and 42AT 3 3 15 Close t...

Page 683: ... increases to 5 operate the wash rig to supply the rinse solution to the engine 4 2 3 Use the chronograph in the cockpit to measure the time of the operation 4 2 4 Stop the starter motor after 30 seconds 4 2 5 When the Ng decreases to 5 stop the supply of rinse solution to the engine 4 2 6 If a water methyl alcohol solution was used do a dry motor of the engine refer to AMM 12 B 71 00 00 00A 901A ...

Page 684: ...s Necessary RINSE METHOD QUANTITY Liters US gals Dry Motor 10 2 66 Table 7 Rinse Solution Water Methyl Alcohol Ratios AMBIENT TEMPERATURE C F WATER BY VOLUME METHYL ALCOHOL BY VOLUME More than 2 36 100 Nil Between 25 and 2 12 and 36 50 50 Less than 25 12 40 60 Table 8 Wash Solution Quantities Necessary WASH METHOD QUANTITY Liters US gals Dry Motor 5 1 33 Table 9 Wash Solution Ratios AMBIENT TEMPER...

Page 685: ... 12 A 710000 A S4080 71127 A 02 1 C Figure 1 Powerplant Clean and Apply Surface Protection PC 12 47E AMM Doc No 02300 ISSUE 01 REVISION 26 MSN 545 1001 1719 1721 1999 12 B AM 00 00 00 I UNCLASSIFIED Effectivity All 12 B 71 00 00 00A 250A A UNCLASSIFIED 2021 12 04 Page 10 ...

Page 686: ...A 03 1 D E F G G F E D C Figure 1 Powerplant Clean and Apply Surface Protection PC 12 47E AMM Doc No 02300 ISSUE 01 REVISION 26 MSN 545 1001 1719 1721 1999 12 B AM 00 00 00 I UNCLASSIFIED Effectivity All 12 B 71 00 00 00A 250A A UNCLASSIFIED 2021 12 04 Page 11 ...

Page 687: ...1 2 A Figure 2 Powerplant Compressor Wash Post SB 71 012 PC 12 47E AMM Doc No 02300 ISSUE 01 REVISION 26 MSN 545 1001 1719 1721 1999 12 B AM 00 00 00 I UNCLASSIFIED Effectivity All 12 B 71 00 00 00A 250A A UNCLASSIFIED 2021 12 04 Page 12 ...

Page 688: ...red Conditions Action Condition Data module Technical publication None PC 12 47E AMM Doc No 02300 ISSUE 01 REVISION 26 MSN 545 1001 1719 1721 1999 12 B AM 00 00 00 I UNCLASSIFIED Effectivity All 12 B 71 00 00 00A 250A A End of data module UNCLASSIFIED 2021 12 04 Page 13 ...

Page 689: ... 12 47E AMM Doc No 02300 ISSUE 01 REVISION 26 MSN 545 1001 1719 1721 1999 12 B AM 00 00 00 I UNCLASSIFIED Intentionally left blank Effectivity All 12 B 71 00 00 00A 250A A UNCLASSIFIED 2021 12 04 Page 14 ...

Page 690: ...on Title 12 B 12 10 03 00A 902A A ENGINE OIL SERVICING Required Conditions Table 2 Required Conditions Action Condition Data module Technical publication None Support equipment Table 3 Support equipment Name Identifications References Qty Reference Remark None Supplies Table 4 Supplies Name Identifications References Qty Reference Remark None PC 12 47E AMM Doc No 02300 ISSUE 01 REVISION 26 MSN 545...

Page 691: ...A 902A A 1 5 Make sure all accessories installed on the engine are correctly attached 1 6 WARNING HIGH TEMPERATURES WILL CAUSE INJURY USE PROTECTIVE GLOVES TO DO THE CHECK ON THE OIL TO FUEL HEATER Check the oil to fuel heater in less than 15 minutes after the engine stops for a high operating temperature refer to P WC EMM 73 10 01 Adjustment Test 1 7 Install the engine cowlings 42AT and 42AB 1 8 ...

Page 692: ...dule Technical publication Title 12 B 00 00 00 00A 060A A GENERAL LIST OF AEROSPACE GROUND EQUIPMENT AGE AND TOOLS 12 B 20 31 00 00A 070A A STANDARD PRACTICES CONSUMABLE MATERIALS LIST 12 B 22 20 05 00A 920A A TORQUE TRANSDUCER REMOVAL INSTALLATION 12 B 28 20 03 00A 920A A ENGINE DRIVEN PUMP REMOVAL INSTALLATION 12 B 73 30 01 00A 920A A FUEL FLOW TRANSMITTER REMOVAL INSTALLATION 12 B 77 40 03 00A ...

Page 693: ...diameter Lockwire standard Part P02 007 AR 0 6 mm 0 025 in diameter Corrosion preventive Part P04 039 AR High temperature compound Part P04 015 AR Cable tie heat resistant Part P09 017 AR Grease Part P04 028 AR Lockwire Part P02 007 AR Grease Part P04 028 AR Engine oil Part P10 004 AR Adhesive Part P08 017 AR Activator Part P08 072 AR Spares Table 5 Spares Name Identifications References Qty Refer...

Page 694: ...dentify the AGE and tools used in this procedure refer to the List of AGE and Tools TEM 12 B 00 00 00 00A 060A A Note To identify the consumable items used in this procedure refer to the Consumable Materials List AMM 12 B 20 31 00 00A 070A A Procedure 1 General This data module gives the procedures to Remove stripdown components from an engine that has been removed from an airframe Install build u...

Page 695: ...epair Refer to Fig 2 and Fig 3 2 2 1 Disconnect and remove the pipe Figure 2 2 from the compressor wash ring fitting Figure 2 1 and from the coupling Figure 2 8 2 2 2 Remove the nut Figure 2 6 the washer Figure 2 7 and the support Figure 2 5 The coupling Figure 2 8 can remain on the support Figure 2 5 Note You must make sure that the nut Figure 2 6 self locking is serviceable If the nut self locki...

Page 696: ...ure 6 13 screw Figure 6 11 and clamps Figure 6 14 from the pipes Figure 6 3 and Figure 6 7 2 4 2 Remove the pipes Figure 6 2 Figure 6 3 Figure 6 5 Figure 6 7 Figure 6 8 and Figure 6 10 the unions Figure 6 1 and Figure 6 6 from the torque transducers Figure 6 4 and Figure 6 9 and the engine 2 4 3 Remove the torque transducer Figure 6 4 refer to AMM 12 B 77 40 03 00A 920A A 2 4 4 Remove the torque t...

Page 697: ... Figure 8 13 and remove the fitting Figure 8 14 retainer Figure 8 12 and O ring Figure 8 11 from the reduction gearbox Figure 8 10 Discard the retainer Figure 8 12 and O ring Figure 8 11 2 6 9 Remove the union Figure 8 23 and O ring Figure 8 22 from the HP pump Figure 8 21 Discard the O ring Figure 8 22 2 6 10 Remove the union Figure 8 25 from the starter generator drain on the accessory gearbox F...

Page 698: ...3 2 2 Put the bottom front part Figure 7 5 of the plenum in position on the engine and loosely install some of the screws Figure 7 16 and washers Figure 7 15 3 2 3 Put the top right part Figure 7 6 of the plenum in position on the engine and loosely install some of the screws Figure 7 16 and washers Figure 7 15 3 2 4 Put the top left part Figure 7 1 of the plenum in position on the engine and loos...

Page 699: ...n the rear position Install the plates Figure 6 21 bush Figure 6 22 and core assemblies Figure 6 20 on the shockmounts Figure 6 23 Make sure that the pins and holes align correctly 3 3 8 Install the bracket Figure 6 15 on the reduction gearbox Figure 6 17 with the two bolts Figure 6 16 3 3 9 Install the torque transducer Figure 6 4 refer to AMM 12 B 77 40 03 00A 920A A 3 3 10 Install the torque tr...

Page 700: ... the bolt Figure 5 16 and nut Figure 5 15 3 4 16 Install the clamps Figure 5 6 and Figure 5 7 on the engine with the screws Figure 5 3 washers Figure 5 4 and nuts Figure 5 5 3 4 17 Put the firewire Figure 5 1 in position on the engine 3 4 18 Make sure that all the insulators are in the correct position and close the all clamps to hold the firewire Figure 5 1 3 4 19 Install the bracket Figure 5 57 ...

Page 701: ...e 2 8 3 5 14 Align the pipe Figure 2 2 so that it does not contact other items then tighten the nuts on the pipe Figure 2 2 3 5 15 Install the protective cap Figure 2 9 on the coupling Figure 2 8 3 5 16 Safety the protective cap Figure 2 9 to the coupling Figure 2 8 with the clip and the lanyard on the protective cap Figure 2 9 3 6 Install Components On The Accessory Gearbox 3 6 1 Install the star...

Page 702: ...gging pin from the rigging holes Figure 1 22 3 6 14 Install the fuel flow transmitter refer to AMM 12 B 73 30 01 00A 920A A 4 Close Up 4 1 Remove the spillage containers from below the engine 4 2 Remove all the equipment tools and materials from the work area Make sure that the work area is clean PC 12 47E AMM Doc No 02300 ISSUE 01 REVISION 26 MSN 545 1001 1719 1721 1999 12 B AM 00 00 00 I UNCLASS...

Page 703: ... 10 18 19 6 5 5 4 3 2 1 Figure 1 Engine Accessory Gearbox Strip Build PC 12 47E AMM Doc No 02300 ISSUE 01 REVISION 26 MSN 545 1001 1719 1721 1999 12 B AM 00 00 00 I UNCLASSIFIED Effectivity All 12 B 71 00 00 00A 920A B UNCLASSIFIED 2021 12 04 Page 12 ...

Page 704: ...Figure 1 Engine Accessory Gearbox Strip Build PC 12 47E AMM Doc No 02300 ISSUE 01 REVISION 26 MSN 545 1001 1719 1721 1999 12 B AM 00 00 00 I UNCLASSIFIED Effectivity All 12 B 71 00 00 00A 920A B UNCLASSIFIED 2021 12 04 Page 13 ...

Page 705: ... 7 5 A Figure 2 Compressor Wash Kit If Installed Removal Installation PC 12 47E AMM Doc No 02300 ISSUE 01 REVISION 26 MSN 545 1001 1719 1721 1999 12 B AM 00 00 00 I UNCLASSIFIED Effectivity All 12 B 71 00 00 00A 920A B UNCLASSIFIED 2021 12 04 Page 14 ...

Page 706: ...Figure 3 Compressor Wash Kit If Installed Removal Installation PC 12 47E AMM Doc No 02300 ISSUE 01 REVISION 26 MSN 545 1001 1719 1721 1999 12 B AM 00 00 00 I UNCLASSIFIED Effectivity All 12 B 71 00 00 00A 920A B UNCLASSIFIED 2021 12 04 Page 15 ...

Page 707: ...71 012 POST SB 71 012 A A A Figure 4 Firewire Clamp Compressor Wash Kit if installed PC 12 47E AMM Doc No 02300 ISSUE 01 REVISION 26 MSN 545 1001 1719 1721 1999 12 B AM 00 00 00 I UNCLASSIFIED Effectivity All 12 B 71 00 00 00A 920A B UNCLASSIFIED 2021 12 04 Page 16 ...

Page 708: ...6 5 4 3 1 1 G A D G A B C E F H J K L N O Q R S G G G O O O B K L 1 2 Figure 5 Engine Firewire Strip Build PC 12 47E AMM Doc No 02300 ISSUE 01 REVISION 26 MSN 545 1001 1719 1721 1999 12 B AM 00 00 00 I UNCLASSIFIED Effectivity All 12 B 71 00 00 00A 920A B UNCLASSIFIED 2021 12 04 Page 17 ...

Page 709: ...50 52 44 43 42 41 40 39 38 35 36 34 33 32 31 30 29 28 27 26 25 24 Figure 5 Engine Firewire Strip Build PC 12 47E AMM Doc No 02300 ISSUE 01 REVISION 26 MSN 545 1001 1719 1721 1999 12 B AM 00 00 00 I UNCLASSIFIED Effectivity All 12 B 71 00 00 00A 920A B UNCLASSIFIED 2021 12 04 Page 18 ...

Page 710: ... 7 6 5 4 3 2 1 B A B C D 35 mm 1 38 in 45 mm 1 77 in D Figure 6 Engine Components Strip Build PC 12 47E AMM Doc No 02300 ISSUE 01 REVISION 26 MSN 545 1001 1719 1721 1999 12 B AM 00 00 00 I UNCLASSIFIED Effectivity All 12 B 71 00 00 00A 920A B UNCLASSIFIED 2021 12 04 Page 19 ...

Page 711: ... 12 A 710002 A S4080 00943 A 03 1 Figure 6 Engine Components Strip Build PC 12 47E AMM Doc No 02300 ISSUE 01 REVISION 26 MSN 545 1001 1719 1721 1999 12 B AM 00 00 00 I UNCLASSIFIED Effectivity All 12 B 71 00 00 00A 920A B UNCLASSIFIED 2021 12 04 Page 20 ...

Page 712: ... 15 15 16 20 19 14 13 16 15 6 16 15 16 15 1 16 15 16 15 16 15 13 14 16 15 Figure 7 Engine Plenum Strip Build PC 12 47E AMM Doc No 02300 ISSUE 01 REVISION 26 MSN 545 1001 1719 1721 1999 12 B AM 00 00 00 I UNCLASSIFIED Effectivity All 12 B 71 00 00 00A 920A B UNCLASSIFIED 2021 12 04 Page 21 ...

Page 713: ...3 16 15 16 15 13 14 5 3 4 7 6 5 3 2 1 Figure 7 Engine Plenum Strip Build PC 12 47E AMM Doc No 02300 ISSUE 01 REVISION 26 MSN 545 1001 1719 1721 1999 12 B AM 00 00 00 I UNCLASSIFIED Effectivity All 12 B 71 00 00 00A 920A B UNCLASSIFIED 2021 12 04 Page 22 ...

Page 714: ...7 3 2 1 B 12 A 710002 A S4080 00946 A 02 1 13 12 D E Figure 8 Engine Stripdown Build up Pipes and Unions PC 12 47E AMM Doc No 02300 ISSUE 01 REVISION 26 MSN 545 1001 1719 1721 1999 12 B AM 00 00 00 I UNCLASSIFIED Effectivity All 12 B 71 00 00 00A 920A B UNCLASSIFIED 2021 12 04 Page 23 ...

Page 715: ...ed Conditions Action Condition Data module Technical publication None PC 12 47E AMM Doc No 02300 ISSUE 01 REVISION 26 MSN 545 1001 1719 1721 1999 12 B AM 00 00 00 I UNCLASSIFIED Effectivity All 12 B 71 00 00 00A 920A B End of data module UNCLASSIFIED 2021 12 04 Page 24 ...

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