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5.1
1

Examine the vertical stabilizer spars for cracks (NDT) and/or deformation in the attachment area at frame 43.

5.1
2

Examine the vertical stabilizer outer surface for cracks, deformation and skin distortion.

5.1
3

Examine the vertical stabilizer fairing 32CT for damage.

5.1
4

Examine the composite lower rudder fairing 32AB for damage.

5.1
5

Look at the rudder mechanism below the cockpit floor and examine the rudder stops for damage.

Installation

6.1 Install the hinge support fitting Figure 3 [5] to the fuselage structure with a new Bolt Figure 3 [12] new

Washer Figure 3 [11] and new Nut Figure 3 [10].

6.2 Install the hinge bracket Figure 3 [4] to the fuselage structure with the bolts Figure 3 [14] washers

Figure 3 [13] washers Figure 3 [9] and nuts Figure 3 [8].

6.3 Assemble the rudder stop Figure 3 [15] to the rudder stop assembly Figure 3 [1].

6.4 Install the rudder stop fitting/assembly Figure 3 [1] and the bonding leads Figure 3 [3].

6.5 Install a new Bearing Figure 2 [4] in the cable quadrant Figure 2 [3]. Secure with a new Retaining

ring Figure 2 [5].

6.6 Install the cable quadrant Figure 2 [3]. Use a new Bolt Figure 2 [1], new Washer Figure 2 [2] new

Nut 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, make sure the painted rudder is balanced before installation. To balance the rudder,
refer to SRM

12-B-51-60-03-00A-276A-A

Note

Use a new

Bolt

Figure 4 [2]

when you attach the rudder to the top hinge.

6.9 Do the functional test of the rudder control system, refer to AMM 12-B-27-20-00-00A-903A-A.

6.1
0

Install the rear vertical stabilizer fairing 32CT and the horizontal stabilizer fairing.

6.1
1

Do the functional test of the elevator control system, refer to AMM 12-B-27-30-00-00A-903A-A.

6.1
2

Do the operational test of the horizontal stabilizer trim, refer to AMM 12-B-27-40-00-00A-903A-A.

6.1
3

Close access panels 31AB, 32AL, 32AR, 32CL and 32CR.

PC-12/47E AMM Doc No 02300, ISSUE 01 REVISION 27 MSN 545, 1001-1719, 1721-1942

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

UNCLASSIFIED

Effectivity: All

12-B-05-50-11-00A-282A-A

UNCLASSIFIED

04.12.2021 Page 5

Summary of Contents for PC-12/47E

Page 1: ...ing Hour Based Intervals 4 5 2 Calendar Time Based Intervals 4 5 3 Landing Based Intervals 4 5 4 Examples 4 Index of Tables Page 1 References 1 References Table 1 References Data module Technical publication Title 12 B 05 10 00 00A 018A A TIME LIMITS INTRODUCTION 12 B 05 10 10 00A 281A A OVERHAUL AND REPLACEMENT SCHEDULE SCHED ULED INSPECTIONS 12 B 05 10 20 00A 281A A TIME LIMITED INSPECTION REQUI...

Page 2: ...the 100 Hour and Annual Inspection Program you must complete an Annual Inspection in accordance with the AMM at Revision 18 before you use the new maintenance program with the extended inspection intervals 2 2 Progressive Inspection Program If you are on the PIP you need to complete the inspection program cycle Phase 1 to 6 given in the AMM at Revision 18 as scheduled before you use the new mainte...

Page 3: ...ours Months or Landings such as 600 FH or 12 Months the interval is understood as whichever comes first 4 1 Flying Hours FH Flying hours are defined as the total time between take off and landing 4 2 Months The date on the aircraft data plate is used as the start time for all the calendar month intervals The subsequent monitoring procedure for all the calendar time limited items after their initia...

Page 4: ...n 270 FH and 330 FH 10 or 30 FH The next inspection is still due at 600 FH 30 FH The inspection intervals do not change The 12 months inspection package can be accomplished any time between 11 months and 13 months 10 or 1 month The next inspection is still due at 24 months 1 month The inspection intervals do not change If you do an inspection earlier and outside the given tolerance then the planne...

Page 5: ...00 FH 12 Months 300 FH 300 FH 12 Months 1200 FH 12 Months 300 FH 300 FH 12 Months 600 FH 600 FH 12 Months 300 FH 300 FH 12 Months 300 FH 300 FH 12 Months 600 FH 600 FH 12 Months 1200 FH 12 Months 2400 FH 24 Months Toler ance 30 FH 30 FH 60 FH 30 FH 120 FH 30 FH 60 FH 30 FH 30 FH 60 FH PC 12 47E AMM Doc No 02300 ISSUE 01 REVISION 27 MSN 545 1001 1719 1721 1942 12 B AM 00 00 00 I UNCLASSIFIED Effect...

Page 6: ...C 12 47E AMM Doc No 02300 ISSUE 01 REVISION 27 MSN 545 1001 1719 1721 1942 12 B AM 00 00 00 I UNCLASSIFIED Intentionally left blank Effectivity All 12 B 05 00 00 00A 018A A UNCLASSIFIED 19 11 2019 Page 6 ...

Page 7: ...PLACEMENT SCHEDULE SCHED ULED INSPECTIONS 12 B 05 10 20 00A 281A A TIME LIMITED INSPECTION REQUIREMENTS 12 B 05 10 30 00A 280A A SUPPLEMENTAL STRUCTUAL INSPECTION DOCUMENT 12 B 05 20 00 00A 018A A SCHEDULED MAINTENANCE CHECKS INTRODUCTION Description 1 General The section has these data modules Time Limited Inspection Requirements refer to AMM 12 B 05 10 20 00A 281A A Overhaul and Replacement Sche...

Page 8: ...ction results at the end of the first overhaul or replacement task the operator can use these results to determine subsequent intervals applicable to the individual airplane or fleet operation provided the operator has an approved condition monitoring system If such an approved monitoring system is not available subsequent overhaul and replacement of components should be done at the stated interva...

Page 9: ...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 27 MSN 54...

Page 10: ...ace 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 31 Flap flexible drive shafts P N 945 02 02 203 204 205 and 206 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...

Page 11: ...603 latest re 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 27 MSN 545 1001 1719 1721 1942 12 B AM 00 00 00 I UNCLASSIFIED Effectivity All 12 B 05 10 10 00A 281A A End of data module UNCLASSIFIED 07 02 2022 Page 3 ...

Page 12: ...C 12 47E AMM Doc No 02300 ISSUE 01 REVISION 27 MSN 545 1001 1719 1721 1942 12 B AM 00 00 00 I UNCLASSIFIED Intentionally left blank Effectivity All 12 B 05 10 10 00A 281A A UNCLASSIFIED 07 02 2022 Page 4 ...

Page 13: ...SSURE 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 INSTALLATION 12 B 24 30 07 00A 920B A NI CAD BATTERY R...

Page 14: ...STEM MSN 1271 1719 1721 1999 OR POST SB 34 042 AIRCRAFT AD JUSTMENT TEST 12 B 34 54 00 00A 903A A DUAL DIVERSITY ATC TRANSPONDER SYSTEM ADJUST MENT TEST 12 B 34 54 00 00A 903B A DUAL NON DIVERSITY ATC TRANSPONDER SYSTEM ADJUSTMENT TEST 12 B 34 54 10 00A 903A A SINGLE DIVERSITY AIR TRAFFIC CONTROL TRANSPOND ER SYSTEM ADJUSTMENT TEST 12 B 34 54 10 00A 903B A SINGLE NON DIVERSITY AIR TRAFFIC CONTROL ...

Page 15: ... Table 6 Time Limited Inspection Requirements Task number Item Name Task Description Interval Data Module Refer ence 00 00 45 Aircraft Do the corrosion and corrosion protection inspections AMM 12 B 20 40 00 00A 901 A A 12 B 20 40 00 00A 901A A 21 30 46 MSN 1001 1719 Cabin positive pres sure relief Functional test 4 800 FH 48 Months 12 B 21 30 00 00A 903A A 21 30 466 MSN 1720 9999 Cabin pressurizat...

Page 16: ... field experience the inter val can be adjusted to a more effective level 21 50 461 Vapor cycle compres sor motor CCM P N 959 90 22 140 if in stalled Inspection check 600 Operating hours 12 B 21 50 03 00A 313A A 21 50 462 Vapor cycle compres sor motor drive belt CCM P N 959 90 22 140 if in stalled Check for tension 600 Operating hours 12 B 21 50 01 00A 903A A 24 30 339 Ni Cad batteries Remove and ...

Page 17: ... 27 00 00 00A 313A 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 control ca bles tension Check after replace ment of any rudder control system cables autopilot and or rud der At the next scheduled inspection but not later than 300 FH...

Page 18: ...00A 902A A 32 10 315 Main landing gear hinge pin and bushes Inspection check 2 400 FH 12 Months 12 B 32 10 00 00A 313A A or 12 B 32 10 00 00A 313B A 34 11 82 Pitot and static sys tem Leak check 24 Months 12 B 34 11 00 00A 903A A 34 11 343 Static ports plate height RVSM air craft Inspection check 24 Months 12 B 34 11 12 00A 313A A 34 21 84 Standby magnetic compass if installed Check swing 24 Months...

Page 19: ...r 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 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 0...

Page 20: ...5 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 24 Months Not...

Page 21: ...r 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 24 Months Note...

Page 22: ... 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 30 342 Static po...

Page 23: ...al can be set 56 11 332 Cockpit side windows Inspection check 11 000 FH 120 Months 12 B 56 11 02 00A 313A A 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 or 48 Months Severe Corrosive En vironment 2000 FH or 24 Months Note Local conditions may be ...

Page 24: ...Owner s Manual 149 Periodic Inspections and Maintenance 61 00 457 Five bladed compo site propeller Refer to the Hartzell Owner s Manual 147 Perform the period ic inspections and maintenance and do the time limited in spections items Refer to Hartzell Owner s Manual 147 Periodic Inspections and Maintenance 71 00 432 Power plant and ac cessories Refer to P WC EMM Chapter 72 00 00 Pe riodic Inspectio...

Page 25: ...er system single and dual sys tem Functional test 24 Months installed AMM 12 B 34 54 00 00A 903A A or 12 B 34 54 00 00A 903B A or 12 B 34 54 10 00A 903A A or 12 B 34 54 10 00A 903B A 53 30 342 Static ports critical area Inspection check 12 Months AMM 12 B 53 30 01 00A 313A A Requirements after job completion Required Conditions Table 8 Required Conditions Action Condition Data module Technical pub...

Page 26: ... 12 47E AMM Doc No 02300 ISSUE 01 REVISION 27 MSN 545 1001 1719 1721 1942 12 B AM 00 00 00 I UNCLASSIFIED Intentionally left blank Effectivity All 12 B 05 10 20 00A 281A A UNCLASSIFIED 07 02 2022 Page 14 ...

Page 27: ...ructural components that are serialized a placard installed with the component part number and serial number may remain in service provided that compliance is shown to Service Bulletin 04 009 latest revision and the Supplemental Structural Inspection Document SSID To show compliance with Service Bulletin 04 009 and the SSID Pilatus recommends that you follow the process given in Para 4 In addition...

Page 28: ...Seal installation 552 10 12 071 Stair installation 552 10 12 063 Handrail installation 552 10 12 086 Note P N on door plac ard 552 05 12 00x Pilatus internal P N 52 EMERGENCY EXIT DOOR Exit assy emergency 552 20 12 036 Including mechanism Note P N on door plac ard 552 05 12 00x Pilatus internal P N 52 CARGO DOOR Door installation freight 552 30 12 001 Including mechanism and struts Note P N on doo...

Page 29: ...27 12 12 003 57 FLAP LH Flap assy LH 557 50 12 003 57 AILERON RH Aileron assy RH 557 60 12 034 Note P N on aileron placard 557 05 12 00x Pilatus internal P N 57 WING RH Wing general RH excluding 557 00 12 003 Wing installation wing attachment bolts exclu ded as they are not traceable Wing tip flap and aileron excluded LEP done separately Landing gear door flap mechanism and aileron mechanism inclu...

Page 30: ... on an aircraft other than the original or be used as a spare part after 20 000 flying hours or 27 000 landings Certain kinds of structural components for example non serialized primary structural elements frames stringers fuselage skins primary attachment fittings etc typically attached with rivets are not allowed to be used for applications other than the original aircraft 4 Process The flowchar...

Page 31: ...Supplemental Structural Inspection Programm SSIP as defined in AMM Ch 04 and perform the required initial inspections and reviews S N specific release statement available for this component Continue operation up to the life limit or LOV whichever comes first i a w the SSID Component must stay on the original aircraft or be scrapped Scrap the component yes 1 no no yes yes 2 3 4 5 6 7 8 no Figure 1 ...

Page 32: ...s responsibility to ensure that the tracking system is acceptable to the local authority 5 The specific component may be returned to service under consideration of all required maintenance actions up to the life limit or the SSID threshold inspection at 25 000 flying hours or 30 000 landings whichever comes first 6 Those parts of the SSID that affect the specific component must be performed 7 On s...

Page 33: ...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 34: ...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 27 MSN 545 1001 1719 1721 1942 12 B AM 00 00 00 I UNCLASSIFIED Effectivity All 12 B 05 10 30 00A 280A A UNCLASSIFIED 04 12 2021 Page 2 ...

Page 35: ...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 36: ...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 AMM Doc No 02300...

Page 37: ...ar Operational Profile 4 References Table 1 References Data module Technical publication Title 12 B 05 10 00 00A 018A A TIME LIMITS INTRODUCTION 12 B 05 40 01 01A 000B A 300 FH INSPECTION 12 B 05 40 01 02A 000B A 300 FH OR 12 MONTHS INSPECTION 12 B 05 40 01 03A 000B A 600 FH INSPECTION 12 B 05 40 01 04A 000B A 600 FH OR 12 MONTHS INSPECTION 12 B 05 40 01 05A 000B A 1200 FH OR 12 MONTHS INSPECTION ...

Page 38: ...onths inspection packages must be considered At 1200 FH the 300 FH 300 FH or 12 Months 600 FH 600 FH or 12 Months and 1200 FH or 12 Months inspection packages must be considered Note The scheduled maintenance packages do not include requirements with special intervals or requirements from the Corrosion Protection Control Program For reference to such requirements refer to 12 B 05 10 00 00A 018A A ...

Page 39: ...12 Months 2400 FH 24 Months 1200 FH 12 Months 2400 FH 24 Months 300 FH 300 FH 12 Months 600 FH 12 Months 300 FH 300 FH 12 Months 600 FH 12 Months 300 FH 300 FH 12 Months 600 FH 600 FH 12 Months 1200 FH 12 Months 300 FH 300 FH 12 Months 600 FH 600 FH 12 Months 1200 FH 12 Months 2400 FH 24 Months 300 FH 300 FH 12 Months 600 FH 600 FH 12 Months 1200 FH 12 Months Months Flight Hours 300 FH Per Year Op...

Page 40: ...ear Operational Profile 2100 FH 30 FH 24 Months 1 Month 2400 FH 30 FH 300 FH 300 FH 12 Months 300 FH 300 FH 12 Months 600 FH 600 FH 12 Months 2400 FH 24 Months 1200 FH 12 Months 1800 FH 30 FH 300 FH 300 FH 12 Months 600 FH 600 FH 12 Months 12 B 052000 A S4080 01502 A 01 1 Figure 3 1200 FH Per Year Operational Profile 1of1 PC 12 47E AMM Doc No 02300 ISSUE 01 REVISION 27 MSN 545 1001 1719 1721 1942 ...

Page 41: ...ence should be made to the topics in this manual the EMM and Pilatus issued Service Bulletins for inspection repair removal and installation procedures called for in the inspection sheets It is the responsibility of the owner or operator to make sure that mechanics inspecting the aircraft have access to these documents as well as the inspection sheets 4 Inspection Terms and Definitions The most co...

Page 42: ...rational Test Show by normal operation and with no special equip ment or measurements that a system or component operates correctly Lubricate Apply lubricant Fill Fill to the correct level pressure or quantity This also includes where necessary the following Remove caps or covers Examine caps covers gaskets seals Install caps covers Install locking devices if appropriate PC 12 47E AMM Doc No 02300...

Page 43: ...CTICES 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 71 0...

Page 44: ...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 45: ...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 scheduled unscheduled...

Page 46: ...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 47: ...red Conditions Action Condition Data module Technical publication None PC 12 47E AMM Doc No 02300 ISSUE 01 REVISION 27 MSN 545 1001 1719 1721 1942 12 B AM 00 00 00 I UNCLASSIFIED Effectivity All 12 B 05 20 00 00A 913A A End of data module UNCLASSIFIED 04 12 2021 Page 5 ...

Page 48: ...C 12 47E AMM Doc No 02300 ISSUE 01 REVISION 27 MSN 545 1001 1719 1721 1942 12 B AM 00 00 00 I UNCLASSIFIED Intentionally left blank Effectivity All 12 B 05 20 00 00A 913A A UNCLASSIFIED 04 12 2021 Page 6 ...

Page 49: ...NGS 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...

Page 50: ...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 51: ...ILERON 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 EX AMINE 12 B 27 25 00 00A 903A...

Page 52: ...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 53: ...L 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 TEST ...

Page 54: ...R DOOR EXAMINE 12 B 52 10 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 ...

Page 55: ...55 20 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 20 01 00A 904B A ELEVATOR LEVER FITTING REPAIR 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 TI...

Page 56: ...M 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 ELECTRI...

Page 57: ...spection 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 must have the rudder bellcrank replaced within ...

Page 58: ...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 59: ...A 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 040A A 06 00 606 ...

Page 60: ...nels 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 00 615 Access pa...

Page 61: ...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 flap compartments...

Page 62: ... 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 Functional test...

Page 63: ... 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 Check for tensio...

Page 64: ...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 under volt age ...

Page 65: ... 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 12 Months 25 10...

Page 66: ... 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 920A A 25 20 2...

Page 67: ... 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 25 63 478 Und...

Page 68: ... 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 electrical bond...

Page 69: ... 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 10 444 Flight co...

Page 70: ...eduled 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 control ca bles ten...

Page 71: ...ystem 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 32 500 FH 42 0...

Page 72: ...300 FH 12 Months 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 s...

Page 73: ...quired for each P N 500 60 12 025 Threshold 30 000 FH 39 000 LDG 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...

Page 74: ...H 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 Retract to 0 as nec...

Page 75: ...alve 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 removed in this...

Page 76: ... 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 sue Note The dei...

Page 77: ... 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 Months whichev...

Page 78: ...0 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 bottom attachment ...

Page 79: ... 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 FH 30 000 LDG ...

Page 80: ...s 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 bearing movement...

Page 81: ...nstruments 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 24 Months 12 B...

Page 82: ...cu 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 Inspection check 36 M...

Page 83: ...ve 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 313A A 52 10 ...

Page 84: ...w 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 a wet cloth dr...

Page 85: ...ply 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 door Examine 1 ...

Page 86: ...t 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 the inter val ca...

Page 87: ...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 24 Months Note L...

Page 88: ...et 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 00 196 Fuselag...

Page 89: ...ough 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 12 500 FH 15 000...

Page 90: ...ch 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 or 12 B 55 30 03...

Page 91: ...e Based on field experience the inter val can be adjusted to more or less fre quent until an effec tive interval can be set 55 10 197 Horizontal stabilizer external surface Examine 300 FH 12 Months 55 10 319 Horizontal vertical stabilizer attachment Inspection check 1 200 FH 12 Months 12 B 55 00 00 00A 313A A 55 10 415 Horizontal stabilizer Life limit 25 000 FH 30 000 LDG 55 10 638 Horizontal stab...

Page 92: ...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 FH 42 000 LDG Repeat 12 500 FH 15 000 LDG 12 B 53 30 02 00A 353A A or 12 B 55 30 03 00A 353A A 55 30 371 Vertical stabilizer main attachment to horizontal stabilizer ...

Page 93: ...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 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 ...

Page 94: ... 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 or 48 Months Severe Corrosive En vironment 2000 FH or 24 Mont...

Page 95: ...H 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 12 Months 57 0...

Page 96: ... 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 00 412 Wing tips Ex...

Page 97: ... 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 147 Perform t...

Page 98: ...pection 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 Months 71 00 287 Po...

Page 99: ...n 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 Engine cowlings ...

Page 100: ...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 12 Months 12 B ...

Page 101: ...of Test Interval 1 Engine oil pressure 300FH 12 Months whichever comes first 2 Propeller blade feather 1200 FH 12 Months whichever comes first 3 DC Generation system 1200 FH 12 Months whichever comes first 4 Maximum propeller speed 1200 FH 12 Months whichever comes first 6 Torque limiter 600 FH 12 Months whichever comes first 7 Engine performance 600 FH 12 Months whichever comes first 8 Torquemete...

Page 102: ...ride 1200 FH 12 Months whichever comes first 17 Reverse power 1200 FH 12 Months whichever comes first 18 Environmental Control System ECS 1200 FH 12 Months whichever comes first 19 Engine stop time 300 FH 12 Months whichever comes first 20 After engine stop 300 FH 12 Months whichever comes first PC 12 47E AMM Doc No 02300 ISSUE 01 REVISION 27 MSN 545 1001 1719 1721 1942 12 B AM 00 00 00 I UNCLASSI...

Page 103: ...DUCTION 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 No 0...

Page 104: ...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 105: ...ure 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 27 MSN 545 1001 1719 1721 1942 12 B AM 00 00 00 I UNCLASSIFIED Effectivity All 12 B 05 40 01 01A 000B A End of data...

Page 106: ...C 12 47E AMM Doc No 02300 ISSUE 01 REVISION 27 MSN 545 1001 1719 1721 1942 12 B AM 00 00 00 I UNCLASSIFIED Intentionally left blank Effectivity All 12 B 05 40 01 01A 000B A UNCLASSIFIED 04 12 2021 Page 4 ...

Page 107: ...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 00A...

Page 108: ...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 109: ... 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 actua tors black ...

Page 110: ...bilizer 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 Examine the bra...

Page 111: ... 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 rivets If cracks ar...

Page 112: ...l 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 27 MSN 545 1001 1719 1721 1942 12 B AM 00 00 00 I UNCLASSIFIED Eff...

Page 113: ...TION 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 00A...

Page 114: ...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 27 MSN 545 1001 1719 1721 1942 12 B AM 00 00 00 I UNCLASSIFIED Effectivity All 12 B 05 40 01 03A 000B A End of data module UNCLASSIFIED 04 12 2021 Page...

Page 115: ... 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 PROPELLER DE ICE SYSTEM WITH ...

Page 116: ...eference 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 040A A 06 00 606 Access pan...

Page 117: ...tem 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 10 162 Main lan...

Page 118: ...lectro 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 10 189 Passen...

Page 119: ...s 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 pusher torque tran...

Page 120: ...C 12 47E AMM Doc No 02300 ISSUE 01 REVISION 27 MSN 545 1001 1719 1721 1942 12 B AM 00 00 00 I UNCLASSIFIED Intentionally left blank Effectivity All 12 B 05 40 01 04A 000B A UNCLASSIFIED 04 12 2021 Page 6 ...

Page 121: ... 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 00A ...

Page 122: ...TIC SYSTEM 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 ...

Page 123: ...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 124: ...DT 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 markings Examin...

Page 125: ... 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 cush ions covers ...

Page 126: ...leron 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 check 12 B 27 20 ...

Page 127: ...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 motor shaft sea...

Page 128: ...pment 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 Emergency door s...

Page 129: ...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 overspeed governo...

Page 130: ...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 27 MSN 545 1001 1719 1721 1942...

Page 131: ... 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 ACCUMUL...

Page 132: ...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 133: ...al 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 20 245 Rudder tr...

Page 134: ... 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 27 MSN 545 1001 1719 1721 1942 12 B AM 00 00 00 I UNCLAS...

Page 135: ...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 136: ...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 137: ...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 138: ...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 Determine the allo...

Page 139: ...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 27 MSN 545 1001 1719 1721 1942 12 B AM 00 00 00 I UNCLASSIFIED Effectivity All 12 B 05 50 00 00A 018A A UNCLASSIFIED 04 12 20...

Page 140: ...R 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 1of1 PC 12 47E AMM Doc No 02300 ISSUE 01 REVISION 27 MSN 545 1...

Page 141: ...AHRS 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 1of1 PC 12 47E AMM Doc No 02300 ISSUE 01 REVISION 27 MSN 545 1001 1719 1721 1942 12 B AM 00 00 00...

Page 142: ...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 143: ...00A 313A A FLAP DRIVE SYSTEM IN SITU INSPECTION CHECK 12 B 32 30 00 00A 903A A EXTENSION AND RETRACTION HYDRAULIC LANDING GEAR ADJUSTMENT TEST 12 B 32 30 00 00A 903B A EXTENSION AND RETRACTION ELECTRO MECHANICAL LANDING GEAR ADJUSTMENT TEST 12 B 34 21 00 00A 903A A STANDBY MAGNETIC COMPASS ADJUSTMENT TEST 12 B 34 25 00 00A 903A A AIR DATA ATTITUDE AND HEADING REFERENCE SYSTEM KSG 7200 ADJUSTMENT T...

Page 144: ...MALL AS TO BE IGNORED A CAREFUL EXAMINATION OF THE INTERNAL SUPPORTING STRUCTURE COULD SHOW MAJOR DAMAGE Procedure 1 General After a hard or overweight landing the following examination should be carried out before further flight An initial examination consists of determining if any external damage has occurred and a more detailed level of examination of any areas found damaged during the initial ...

Page 145: ... damage 3 Detailed Examination 3 1 Preparation Raise the aircraft on jacks refer to AMM 12 B 07 10 00 00A 901A A 3 2 Structure 3 2 1 Remove access panels near the damaged area and examine internal structure as far as possible 3 2 2 Lower the flaps Examine the flaps and flap coves Raise the flaps Make sure flap movement is smooth 3 2 3 Examine the flap drive arms refer to AMM 12 B 27 51 00 00A 313A...

Page 146: ...03B A 3 5 3 Do a check swing of the standby magnetic compass if installed refer to AMM 12 B 34 21 00 00A 903A 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 27 MSN 545 1001 1719 1721 1942 12 B AM 00 00 00 I UNCLASSIFIED Effectivity All 12 B 05 50 01 00A 282A A E...

Page 147: ...T AND SYMMETRY UNSCHEDULED INSPEC TIONS 12 B 07 10 00 00A 901A A JACKING MAINTENANCE PRACTICES 12 B 32 30 00 00A 903B A EXTENSION AND RETRACTION ELECTRO MECHANICAL LANDING GEAR ADJUSTMENT TEST 12 B 34 21 00 00A 903A A STANDBY MAGNETIC COMPASS ADJUSTMENT TEST 12 B 34 25 00 00A 903A A AIR DATA ATTITUDE AND HEADING REFERENCE SYSTEM KSG 7200 ADJUSTMENT TEST 12 B 34 26 40 00A 903B A ELECTRONIC STANDBY ...

Page 148: ...neral After a hard or overweight landing the following examination should be carried out before further flight An initial examination consists of determining if any external damage has occurred and a more detailed level of examination of any areas found damaged during the initial examination If no damage is found during the initial examination then it is not necessary to do the more detailed exami...

Page 149: ...ove access panels near the damaged area and examine internal structure as far as possible 3 2 2 Lower the flaps Examine the flaps and flap coves Raise the flaps Make sure flap movement is smooth 3 2 3 Move the ailerons up and down and make sure movement is smooth and there are no unusual noises 3 3 Landing Gear 3 3 1 Make sure that the wheels are free to rotate 3 3 2 Move the rudder pedals left an...

Page 150: ...fter 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 27 MSN 545 1001 1719 1721 1942 12 B AM 00 00 00 I UNCLASSIFIED Effectivity All 12 B 05 50 01 00A 282B A End of data module UNCLASSIFIED 19 11 2019 Page 4 ...

Page 151: ...cal publication Title 12 B 05 50 06 00A 282A A ALIGNMENT AND SYMMETRY UNSCHEDULED INSPEC TIONS 12 B 27 51 00 00A 313A A FLAP DRIVE SYSTEM IN SITU INSPECTION CHECK 12 B 45 45 00 00A 551A A CENTRAL MAINTENANCE SYSTEM INTERFACE FAULT MONITORING STORAGE READOUT DOWNLOAD DATA 12 B 55 00 00 00A 313A A STABILIZERS ATTACHMENT FITTINGS INSPEC TION CHECK Preliminary Requirements Required Conditions Table 2 ...

Page 152: ...ed to determine if an exceedance is real Use the refinement charts Fig 1 and Fig 2 to evaluate the exceedance limits This requires the following information Aircraft take off weight Fuel weight at take off and at the time of the exceedance The peak load factor recorded in the acms_aircraft_data_log_file txt of the ACMS data Obtain the aircraft gross weight and fuel weight at the time of the exceed...

Page 153: ...rons up and down and make sure movement is smooth and there are no unusual noises 2 2 Fuselage 2 2 1 Examine the fuselage skin for distortion at rivet rows and for loose or missing rivets 2 2 2 Examine the passenger crew cargo and emergency exit doors for distortion and correct closing 2 2 3 Examine the battery area for no electrolyte spillage 2 2 4 Examine the battery for security of attachment 2...

Page 154: ...or repair information If serious structural damage has occurred contact Pilatus Aircraft Ltd for assistance PC 12 47E AMM Doc No 02300 ISSUE 01 REVISION 27 MSN 545 1001 1719 1721 1942 12 B AM 00 00 00 I UNCLASSIFIED Effectivity All 12 B 05 50 02 00A 282A A UNCLASSIFIED 08 07 2021 Page 4 ...

Page 155: ...R 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 1of1 PC 12 47E AMM Doc No 02300 ISSUE 01 REVISION 27 MSN 545 1...

Page 156: ...AHRS 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 1of1 PC 12 47E AMM Doc No 02300 ISSUE 01 REVISION 27 MSN 545 1001 1719 1721 1942 12 B AM 00 00 00...

Page 157: ...red Conditions Action Condition Data module Technical publication None PC 12 47E AMM Doc No 02300 ISSUE 01 REVISION 27 MSN 545 1001 1719 1721 1942 12 B AM 00 00 00 I UNCLASSIFIED Effectivity All 12 B 05 50 02 00A 282A A End of data module UNCLASSIFIED 08 07 2021 Page 7 ...

Page 158: ...C 12 47E AMM Doc No 02300 ISSUE 01 REVISION 27 MSN 545 1001 1719 1721 1942 12 B AM 00 00 00 I UNCLASSIFIED Intentionally left blank Effectivity All 12 B 05 50 02 00A 282A A UNCLASSIFIED 08 07 2021 Page 8 ...

Page 159: ...018A A UNSCHEDULED MAINTENANCE CHECKS INTRODUC TION 12 B 27 50 00 00A 903A A FLAPS ADJUSTMENT TEST 12 B 27 51 00 00A 313A A FLAP DRIVE SYSTEM IN SITU INSPECTION CHECK 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 PC 12 47E AMM Doc No 02300 ...

Page 160: ...sing rivets 2 2 Lower the flaps Remove the flap fairings and examine the flaps and flap coves for distortion and loose or missing rivets 2 3 Examine the flap support mechanism For the flap drive arms refer to AMM 12 B 27 51 00 00A 313A A 2 4 Do the functional test of the flap system refer to AMM 12 B 27 50 00 00A 903A A Note When the flaps are moving listen for unusual noises indicating malfunctio...

Page 161: ...ADED PROPELLER BLADES REPAIR 12 B 61 00 00 00A 904B A FIVE BLADED PROPELLER BLADES REPAIR 12 B 61 10 01 00A 920A A FOUR BLADED PROPELLER REMOVAL INSTALLATION 12 B 61 10 01 00A 920B A FIVE BLADED PROPELLER REMOVAL INSTALLATION 12 B 71 00 00 00A 903A A POWER PLANT ADJUSTMENT TEST 12 B 71 10 00 00A 920A A ENGINE COWLINGS REMOVAL INSTALLATION Preliminary Requirements Required Conditions Table 2 Requir...

Page 162: ...ect or a stationary propeller is hit by a moving object If distortion of the skin is found do the Engine Alignment Check refer to AMM 12 B 05 50 06 00A 282A A 2 When A Sudden Propeller Stoppage Occurs 2 1 Remove the power plant access panels refer to AMM 12 B 71 10 00 00A 920A A 2 2 Remove the propeller refer to AMM 12 B 61 10 01 00A 920A A or 12 B 61 10 01 00A 920B A and replace or overhaul 2 3 E...

Page 163: ... damage is less than the permitted limits refer to AMM 12 B 61 00 00 00A 904A A or 12 B 61 00 00 00A 904B A 3 4 Examine the engine Ref P WC EMM 72 00 00 3 5 Install the power plant access panels refer to AMM 12 B 71 10 00 00A 920A 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 IS...

Page 164: ...C 12 47E AMM Doc No 02300 ISSUE 01 REVISION 27 MSN 545 1001 1719 1721 1942 12 B AM 00 00 00 I UNCLASSIFIED Intentionally left blank Effectivity All 12 B 05 50 04 00A 282A A UNCLASSIFIED 19 11 2019 Page 4 ...

Page 165: ... RETRACTION ELECTRO MECHANICAL LANDING GEAR ADJUSTMENT TEST 12 B 34 21 00 00A 903A A STANDBY MAGNETIC COMPASS ADJUSTMENT TEST 12 B 34 25 00 00A 903A A AIR DATA ATTITUDE AND HEADING REFERENCE SYSTEM KSG 7200 ADJUSTMENT TEST 12 B 34 26 40 00A 903B A ELECTRONIC STANDBY INSTRUMENT SYSTEM MSN 1271 1719 1721 1999 OR POST SB 34 042 AIRCRAFT AD JUSTMENT TEST Required Conditions Table 2 Required Conditions...

Page 166: ... discharge 2 4 Examine the static dischargers 2 5 Examine the bonding leads between the area of the lightning hit and the discharge point 2 6 If the lightning hit the aircraft on a control surface examine the hinge and bearings on the control surface 2 7 If the aircraft was hit by lightning while on the ground examine for damage 2 7 1 The landing gear 2 7 2 The nosewheel steering mechanism 2 7 3 T...

Page 167: ...mpass if installed refer to AMM 12 B 34 21 00 00A 903A A 2 1 6 If the aircraft was hit by lightning while on the ground do a Functional Test of the Extension and Retraction System refer to AMM 12 B 32 30 00 00A 903A A or 12 B 32 30 00 00A 903B A Requirements after job completion Required Conditions Table 6 Required Conditions Action Condition Data module Technical publication None PC 12 47E AMM Do...

Page 168: ...C 12 47E AMM Doc No 02300 ISSUE 01 REVISION 27 MSN 545 1001 1719 1721 1942 12 B AM 00 00 00 I UNCLASSIFIED Intentionally left blank Effectivity All 12 B 05 50 05 00A 282A A UNCLASSIFIED 07 02 2022 Page 4 ...

Page 169: ... 11 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 07 10 00 00A 901A A JACKING MAINTENANCE PRACTICES 12 B 12 10 01 00A 902A A FUEL SERVICING 12 B 32 30 00 00A 903A A EXTENSION AND RETRACTION HYDRAULIC LANDING GEAR ADJUSTMENT TEST 12 B 32 30 00 00A 903B A EXTENSION AND RETRACTION ELECTRO ME...

Page 170: ...pplies Name Identifications References Qty Reference Remark None Spares Table 5 Spares Name Identifications References Qty Reference Remark None Safety Conditions WARNING IF PERMITTED DEVIATIONS ARE EXCEEDED THE AIRCRAFT SHOULD NOT BE OPERATED UNTIL IT HAS BEEN RECTIFIED AND BROUGHT WITHIN ITS DESIGN STRENGTH SHAPE AND ALIGNMENT TOLERANCES Note To identify the AGE and tools used in this procedure ...

Page 171: ...vered during the subsequent investigation should also be included 2 Alignment and Symmetry 2 1 General A Reference Point RP is identified with contrasting paint usually colored red and by a washer under the rivet head Reference Dimensions A B C and D are distances between two reference points 2 2 Job Set Up 2 2 1 Defuel the aircraft refer to AMM 12 B 12 10 01 00A 902A A 2 2 2 Prepare an In Service...

Page 172: ...n Note The recorded reading is the Correction Factor The Correction Factor is needed to help determine the deformation check 2 4 Lateral Levelling Check Refer to Fig 1 Note If it is not possible to do the lateral levelling check because of damage to the wing s contact Pilatus for the data on how to continue 2 4 1 Set up the Transit theodolite Pt No T05 005 2 4 1 1 Adjust the tripod to allow readin...

Page 173: ...e check form 2 5 7 Repeat steps 3 4 5 and 6 for the Reference Points 7 5 4 3 2 10 and 13 left and right sides 2 5 8 Measure the dimension A left and right from RP 12 on top surface of wing to RP 10 on the horizontal stabilizer Make a record on the check form 2 5 9 Measure the dimensions B left and right from RP 12 to RP 8 on the upper leading edge of the vertical stabilizer Make a record on the ch...

Page 174: ...ice Check Form complete the Comparison Table 2 7 2 If the deviation from the build checks is not in the limits given contact Pilatus for advice Note Give as much information as possible about the incident which made the check necessary 2 8 Close Up 2 8 1 Remove the levelling bars and spacers 2 8 2 Lower the landing gear refer to AMM 12 B 32 30 00 00A 903A A or 12 B 32 30 00 00A 903B A 2 8 3 Lower ...

Page 175: ...T RP6 LEFT LEVELLING BARS Figure 1 Longitudinal and Lateral Levelling 1of1 PC 12 47E AMM Doc No 02300 ISSUE 01 REVISION 27 MSN 545 1001 1719 1721 1942 12 B AM 00 00 00 I UNCLASSIFIED Effectivity All 12 B 05 50 06 00A 282A A UNCLASSIFIED 19 11 2019 Page 7 ...

Page 176: ... 1 3 5 2 4 7 6 10 SAME BLADE LEFT AND RIGHT HORIZONTAL A B C 12 Figure 2 Reference Points and Dimensions 1of2 PC 12 47E AMM Doc No 02300 ISSUE 01 REVISION 27 MSN 545 1001 1719 1721 1942 12 B AM 00 00 00 I UNCLASSIFIED Effectivity All 12 B 05 50 06 00A 282A A UNCLASSIFIED 19 11 2019 Page 8 ...

Page 177: ... 10 13 8 10 10 2 3 4 5 6 7 2 3 4 5 6 7 Figure 2 Reference Points and Dimensions 2of2 PC 12 47E AMM Doc No 02300 ISSUE 01 REVISION 27 MSN 545 1001 1719 1721 1942 12 B AM 00 00 00 I UNCLASSIFIED Effectivity All 12 B 05 50 06 00A 282A A UNCLASSIFIED 19 11 2019 Page 9 ...

Page 178: ...imension Left Dimension Right 3 2 4 5 6 7 10 13 A B C D E Bottom Top Figure 3 Recommended In Service Check Form 1of1 PC 12 47E AMM Doc No 02300 ISSUE 01 REVISION 27 MSN 545 1001 1719 1721 1942 12 B AM 00 00 00 I UNCLASSIFIED Effectivity All 12 B 05 50 06 00A 282A A UNCLASSIFIED 19 11 2019 Page 10 ...

Page 179: ...al Deformation Check Check Reference Dimension Date Ac MSN Subtract right from left and indicate if the result is positive or negative Deviation From Build Checks Maximum Permitted Deviation mm Recorded Aircraft Build Checks In Service Check Results Remarks 15 20 25 5 4 5 4 5 4 5 4 2 2 3 3 4 4 must not exceed 8 must not exceed 10 must not exceed 4 must not exceed 6 must not exceed 8 Between 55 and...

Page 180: ...ed Conditions Action Condition Data module Technical publication None PC 12 47E AMM Doc No 02300 ISSUE 01 REVISION 27 MSN 545 1001 1719 1721 1942 12 B AM 00 00 00 I UNCLASSIFIED Effectivity All 12 B 05 50 06 00A 282A A End of data module UNCLASSIFIED 19 11 2019 Page 12 ...

Page 181: ...0 06 00A 282A A ALIGNMENT AND SYMMETRY UNSCHEDULED INSPEC TIONS 12 B 57 00 00 00A 313A A WING AND FUSELAGE FITTINGS INSPECTION CHECK 12 B 57 00 00 00A 520A A LEFT WING HYDRAULIC LANDING GEAR REMOVAL 12 B 57 00 00 00A 520B A LEFT WING ELECTRO MECHANICAL LANDING GEAR REMOVAL 12 B 57 00 00 00A 720A A LEFT WING HYDRAULIC LANDING GEAR INSTALLATION 12 B 57 00 00 00A 720B A LEFT WING ELECTRO MECHANICAL L...

Page 182: ... Includes items listed below Part BM 6107807 1 Stepped Pin Frame 21 Upper Part 6107806 05 1 per kit assy Long Pin Frame 21 Lower Part 6107806 06 1 per kit assy Short Pin Frame 24 Lower Part 6107806 07 1 per kit assy Knurled Nut Part 6107806 08 1 per kit assy Washer Part 6107806 09 1 per kit assy Bush Lugs C3 and D3 Part 6107806 10 2 per kit assy Bush Lugs D1 and D5 Part 6107806 11 2 per kit assy B...

Page 183: ...t the alignment of the fuselage wing carry through frames Frames 21 and 24 conform to the production build tolerances The check is carried out using a pair of dedicated Pilatus jigs Note Do the inspection before the aircraft flies again 2 Inspection 2 1 Carefully examine all rivets stringers longerons and panels to the fore aft and side of each frame for signs of distortion or cracking 2 2 Careful...

Page 184: ...50 06 00A 282A A 3 2 2 Level the aircraft laterally using Frame 21 upper surface refer to AMM 12 B 05 50 06 00A 282A A 3 2 3 Check the level of Frame 24 upper surface This must be parallel to Frame 21 within 0 1 degree 3 3 Interface Geometry Install the LH and RH Jig Assemblies to the aircraft as follows Note Three persons are needed for this procedure two to support the weight of each jig while t...

Page 185: ...re 3 C3 4 6 0 40 0 30 mm Jig Assy Figure 3 C3 Frame 21 Upper Figure 3 C4 2 5 0 10 mm Frame 21 Upper Figure 3 C4 Jig Assy Figure 3 C5 4 5 0 70 0 55 mm Jig Assy Figure 3 D1 Frame 21 Lower Figure 3 D2 2 5 0 95 1 10 mm Frame 21 Lower Figure 3 D2 Jig Assy Figure 3 D3 4 5 0 70 0 60 mm Jig Assy Figure 3 D3 Frame 21 Lower Figure 3 D4 2 5 0 40 mm Frame 21 Lower Figure 3 D4 Jig Assy Figure 3 D5 4 5 1 00 0 8...

Page 186: ... RH Jig Assemblies from the aircraft 4 2 Install the LH wing refer to AMM 12 B 57 00 00 00A 720A A or 12 B 57 00 00 00A 720B A 4 3 Install the RH wing refer to AMM 12 B 57 00 00 00B 720A A or 12 B 57 00 00 00B 720B A 4 4 Make sure that the work area is clean and clear of tools and other items PC 12 47E AMM Doc No 02300 ISSUE 01 REVISION 27 MSN 545 1001 1719 1721 1942 12 B AM 00 00 00 I UNCLASSIFIE...

Page 187: ...01 1 2 4 Figure 1 Jig Assembly LH RH Lug Bush Fitment 1of1 PC 12 47E AMM Doc No 02300 ISSUE 01 REVISION 27 MSN 545 1001 1719 1721 1942 12 B AM 00 00 00 I UNCLASSIFIED Effectivity All 12 B 05 50 07 00A 282A A UNCLASSIFIED 19 11 2019 Page 7 ...

Page 188: ... 02 1 4 LH SHOWN RH OPPOSITE Figure 2 Frame 21 and 24 Pin Fitment 1of1 PC 12 47E AMM Doc No 02300 ISSUE 01 REVISION 27 MSN 545 1001 1719 1721 1942 12 B AM 00 00 00 I UNCLASSIFIED Effectivity All 12 B 05 50 07 00A 282A A UNCLASSIFIED 19 11 2019 Page 8 ...

Page 189: ...3 1 2 3 3 1 1 2 1 2 1 3 1 mm 0 5 mm B RH SHOWN LH OPPOSITE Figure 3 Lug Gap Identification and Measurements 1of1 PC 12 47E AMM Doc No 02300 ISSUE 01 REVISION 27 MSN 545 1001 1719 1721 1942 12 B AM 00 00 00 I UNCLASSIFIED Effectivity All 12 B 05 50 07 00A 282A A UNCLASSIFIED 19 11 2019 Page 9 ...

Page 190: ... 6 6 6 7 8 9 10 2152 mm 1 3 mm A Figure 4 Wing Alignment and Longitudinal Roll Checks 1of1 PC 12 47E AMM Doc No 02300 ISSUE 01 REVISION 27 MSN 545 1001 1719 1721 1942 12 B AM 00 00 00 I UNCLASSIFIED Effectivity All 12 B 05 50 07 00A 282A A UNCLASSIFIED 19 11 2019 Page 10 ...

Page 191: ...ed Conditions Action Condition Data module Technical publication None PC 12 47E AMM Doc No 02300 ISSUE 01 REVISION 27 MSN 545 1001 1719 1721 1942 12 B AM 00 00 00 I UNCLASSIFIED Effectivity All 12 B 05 50 07 00A 282A A End of data module UNCLASSIFIED 19 11 2019 Page 11 ...

Page 192: ... 12 47E AMM Doc No 02300 ISSUE 01 REVISION 27 MSN 545 1001 1719 1721 1942 12 B AM 00 00 00 I UNCLASSIFIED Intentionally left blank Effectivity All 12 B 05 50 07 00A 282A A UNCLASSIFIED 19 11 2019 Page 12 ...

Page 193: ...res Page 1 Vmo Mmo Exceedance Envelope 4 References Table 1 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 PC 12 47E AMM Doc No 02300 ISSUE 01 REVISION 27 MSN 545 1001 1719 1721 1942 12...

Page 194: ...Altitude KCAS Exceedance Envelope defined in Fig 1 OR if vibration or buffeting was experienced OR if there were any other concurrent exceedances OR if the exact details of the exceedance are unknown you must do further inspections for damage Send details of the exceedance to Pilatus Aircraft Limited and request maintenance advice before the aircraft flies again 2 Inspections 2 1 Do these inspecti...

Page 195: ...lose correctly against the frame structure 2 1 5 Do visual and operational control checks for full and free movement of the following control surfaces the ailerons the elevators the rudder 2 1 6 Do an extension and retraction of the flaps and do a visual check for the following correct symmetrical extension and retraction that the operational speed of the flap drive motor is constant with no diffe...

Page 196: ...ELOPE DENSITY ALTITUDE ft KCAS 176 185 196 206 218 229 240 252 M 0 4800 M 0 5035 KCAS ENVELOPE AFM EXCEEDANCE ENVELOPE Figure 1 Vmo Mmo Exceedance Envelope 1of1 PC 12 47E AMM Doc No 02300 ISSUE 01 REVISION 27 MSN 545 1001 1719 1721 1942 12 B AM 00 00 00 I UNCLASSIFIED Effectivity All 12 B 05 50 08 00A 282A A UNCLASSIFIED 19 07 2017 Page 4 ...

Page 197: ...red Conditions Action Condition Data module Technical publication None PC 12 47E AMM Doc No 02300 ISSUE 01 REVISION 27 MSN 545 1001 1719 1721 1942 12 B AM 00 00 00 I UNCLASSIFIED Effectivity All 12 B 05 50 08 00A 282A A End of data module UNCLASSIFIED 19 07 2017 Page 5 ...

Page 198: ...C 12 47E AMM Doc No 02300 ISSUE 01 REVISION 27 MSN 545 1001 1719 1721 1942 12 B AM 00 00 00 I UNCLASSIFIED Intentionally left blank Effectivity All 12 B 05 50 08 00A 282A A UNCLASSIFIED 19 07 2017 Page 6 ...

Page 199: ...LED MAINTENANCE CHECKS INTRODUC TION 12 B 32 30 00 00A 903A A EXTENSION AND RETRACTION HYDRAULIC LANDING GEAR ADJUSTMENT TEST 12 B 32 30 00 00A 903B A EXTENSION AND RETRACTION ELECTRO MECHANICAL LANDING GEAR ADJUSTMENT TEST Required Conditions Table 2 Required Conditions Action Condition Data module Technical publication None Support equipment Table 3 Support equipment Name Identifications Referen...

Page 200: ...bly Nose landing gear actuator assembly Left and right main landing gear actuator assembly 1 2 Damage or distortion is not allowed Replace damaged or distorted parts as needed 1 3 Do the adjustment test of the extension and retraction system refer to AMM 12 B 32 30 00 00A 903A A or 12 B 32 30 00 00A 903B A Requirements after job completion Required Conditions Table 6 Required Conditions Action Con...

Page 201: ...0 08 00A 282A A MAXIMUM OPERATING SPEED VMO MMO EXCEEDANCE UNSCHEDULED INSPECTION 12 B 32 30 00 00A 903A A EXTENSION AND RETRACTION HYDRAULIC LANDING GEAR ADJUSTMENT TEST 12 B 32 30 00 00A 903B A EXTENSION AND RETRACTION ELECTRO MECHANICAL LANDING GEAR ADJUSTMENT TEST Required Conditions Table 2 Required Conditions Action Condition Data module Technical publication None Support equipment Table 3 S...

Page 202: ...ng gear doors for Distortion Loose missing fasteners Excessive play 1 3 Examine the brake pipes for Security Chafing Leaks 1 4 Damage is not allowed Replace parts as needed 1 5 Do the adjustment test of the extension and retraction system refer to AMM 12 B 32 30 00 00A 903A A or 12 B 32 30 00 00A 903B A Requirements after job completion Required Conditions Table 6 Required Conditions Action Condit...

Page 203: ...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 204: ...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 205: ... 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 206: ... a crack is suspected from visual inspection do the NDT inspection 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 ...

Page 207: ... 3 Use a new Bolt Figure 2 1 new Washer Figure 2 2 new Nut 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 1...

Page 208: ...1 2 1 1 2 1 Figure 1 Rudder Control Cables Adjustment 1of1 PC 12 47E AMM Doc No 02300 ISSUE 01 REVISION 27 MSN 545 1001 1719 1721 1942 12 B AM 00 00 00 I UNCLASSIFIED Effectivity All 12 B 05 50 11 00A 282A A UNCLASSIFIED 04 12 2021 Page 6 ...

Page 209: ...D 8 9 3 7 6 1 2 4 5 Figure 2 Cable Quadrant Removal Installation 1of1 PC 12 47E AMM Doc No 02300 ISSUE 01 REVISION 27 MSN 545 1001 1719 1721 1942 12 B AM 00 00 00 I UNCLASSIFIED Effectivity All 12 B 05 50 11 00A 282A A UNCLASSIFIED 04 12 2021 Page 7 ...

Page 210: ...5 8 9 13 4 2 1 3 3 14 Figure 3 Rudder Hinge Fittings Removal Installation 1of1 PC 12 47E AMM Doc No 02300 ISSUE 01 REVISION 27 MSN 545 1001 1719 1721 1942 12 B AM 00 00 00 I UNCLASSIFIED Effectivity All 12 B 05 50 11 00A 282A A UNCLASSIFIED 04 12 2021 Page 8 ...

Page 211: ... 2 3 B Figure 4 Vertical Stabilizer Attachment and Spars 1of1 PC 12 47E AMM Doc No 02300 ISSUE 01 REVISION 27 MSN 545 1001 1719 1721 1942 12 B AM 00 00 00 I UNCLASSIFIED Effectivity All 12 B 05 50 11 00A 282A A UNCLASSIFIED 04 12 2021 Page 9 ...

Page 212: ...ed Conditions Action Condition Data module Technical publication None PC 12 47E AMM Doc No 02300 ISSUE 01 REVISION 27 MSN 545 1001 1719 1721 1942 12 B AM 00 00 00 I UNCLASSIFIED Effectivity All 12 B 05 50 11 00A 282A A End of data module UNCLASSIFIED 04 12 2021 Page 10 ...

Page 213: ...TMENT TEST 12 B 32 30 00 00A 903A A EXTENSION AND RETRACTION HYDRAULIC LANDING GEAR ADJUSTMENT TEST 12 B 32 30 00 00A 903B A EXTENSION AND RETRACTION ELECTRO MECHANICAL LANDING GEAR ADJUSTMENT TEST 12 B 32 40 02 00A 920A A NOSE WHEEL REMOVAL INSTALLATION 12 B 32 50 00 00A 310A A NOSE WHEEL STEERING EXAMINE 12 B 32 50 00 00A 903A A NOSE WHEEL STEERING ADJUSTMENT TEST 12 B 51 00 00 00A 351A A PROCES...

Page 214: ...8 AR Bolt NAS1954C2H Part 932 35 16 702 AR Spares Table 5 Spares Name Identifications References Qty Reference Remark Wedge shear plate CSN 32 20 00 03 260 2 Rivet CSN 32 20 00 03 263 AR Wedge shear plate CSN 32 20 01 03E 260 2 Rivet CSN 32 20 01 03E 263 AR Safety Conditions WARNING BE CAREFUL WHEN YOU USE THE CONSUMABLE MATERIALS OBEY THE MANUFACTURERS HEALTH AND SAFETY INSTRUCTIONS AND ALL THE A...

Page 215: ... Visually examine the fork legs for twist and deformation 2 3 2 Insert the axle through the fork legs and examine the axle lugs for concentricity and alignment 2 3 3 Use a Magnifying glass 10x magnification Pt No Local supply and Light source Pt No Local supply and inspect the fork legs and axle for cracks 2 3 3 1 If cracks are suspected do an NDT inspection refer to SRM 12 B 51 00 00 00A 351A A o...

Page 216: ...repair the affected part refer to the CMM or contact Pilatus Aircraft Ltd 4 Testing The tests given here in Step 4 must be completed to do the tests the aircraft must be raised on jacks If you are unable to raise the aircraft on jacks the aircraft can be flown ferry flight to a maintenance facility were these tests can be completed It must be flown with the landing gear extended and locked in the ...

Page 217: ... A STOP PLATE TORQUE LINK NLG FORK NLG AXLE PART OF RUDDER CONTROL SYSTEM PRIMARY PATH SECONDARY PATH LEFT HARD STOP RIGHT HARD STOP Figure 1 Nose Landing Gear Overturning Unscheduled Inspection 1of1 PC 12 47E AMM Doc No 02300 ISSUE 01 REVISION 27 MSN 545 1001 1719 1721 1942 12 B AM 00 00 00 I UNCLASSIFIED Effectivity All 12 B 05 50 12 00A 282A A UNCLASSIFIED 08 07 2021 Page 5 ...

Page 218: ...red Conditions Action Condition Data module Technical publication None PC 12 47E AMM Doc No 02300 ISSUE 01 REVISION 27 MSN 545 1001 1719 1721 1942 12 B AM 00 00 00 I UNCLASSIFIED Effectivity All 12 B 05 50 12 00A 282A A End of data module UNCLASSIFIED 08 07 2021 Page 6 ...

Page 219: ...AFT EXTERIOR WASHING SERVICING 12 B 21 30 02 00A 250A A SAFETY VALVE CLEAN 12 B 21 30 03 00A 920A A OUTFLOW VALVE MSN 1001 1719 REMOVAL INSTAL LATION 12 B 21 30 03 00A 920B A OUTFLOW VALVE MSN 1720 AND UP REMOVAL INSTAL LATION 12 B 21 40 02 00A 313A A REFRIGERATION PACK INSPECTION CHECK 12 B 21 40 03 00A 250A A WATER SEPARATOR CLEAN 12 B 21 40 03 00A 920A A WATER SEPARATOR REMOVAL INSTALLATION 12 ...

Page 220: ...1 If the aircraft has flown through suspected or actual volcanic ash or smoke the following examinations should be carried out before further flight If any damage is found use the aircraft AMM and or SRM to do general repairs If no repair procedure is available contact Pilatus Aircraft Ltd 2 Exterior Fuselage 2 1 Do a visual inspection of the areas that follow for abrasion contamination and or dam...

Page 221: ...exchanger matrix is contaminated clean it with a Soft bristle brush Pt No Local Supply 5 3 Remove the ECS water separator refer to AMM 12 B 21 40 03 00A 920A A 5 4 Do a visual inspection of the ECS water separator for contamination If contamination is found do this work 5 4 1 Clean the separator refer to AMM 12 B 21 40 03 00A 250A A 5 4 2 Install the separator refer to AMM 12 B 21 40 03 00A 920A A...

Page 222: ...nt 7 2 Do a pitot static system leak check refer to AMM 12 B 34 11 00 00A 903A A 8 Detailed Examination Test 8 1 Do an operational test of the aircraft flight controls to make sure that movement is full free and smooth 8 2 If the aircraft has or is suspected to have been struck by a coronal discharge St Elmo s Fire refer to AMM 12 B 05 50 05 00A 282A A 8 3 Inspect the engine refer to P WC EMM 72 0...

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