PC-24 AMM Chapter 04 Airworthiness Limitations
Transcript of PC-24 AMM Chapter 04 Airworthiness Limitations
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PC-24 Aircraft Maintenance Manual UNCONTROLLED COPY
PC-24 AMM Chapter 04 Airworthiness Limitations
Table of Contents The PC-24 Airworthiness Limitations Section (ALS) consists of the following AMM Chapter 04 Sub-sections:
Data Module Title Data Module Reference Issue Date Issue / Revision Number
00 - General PC24-A- A04-00-0000-00A-040A-A
26 May 2020 Issue 008 Revision 00
10 - Mandatory Life Limited Items
PC24-A- A04-10-0000-00A-000A-A
06 June 2018 Issue 004 Revision 00
20 - Mandatory Structural Inspection Items
PC24-A- A04-20-0000-00A-000A-A
26 May 2020 Issue 005 Revision 00
30 - Certification Maintenance Requirement
PC24-A- A04-30-0000-00A-000A-A
14 October 2019 Issue 007 Revision 00
40 - Critical Design Configuration Control Limitation
PC24-A- A04-40-0000-00A-000A-A
06 June 2018 Issue 004 Revision 00
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Airworthiness limitations
Description
Applicable to all PC-24 aircraft: PC24 A
Table of Contents Page
Airworthiness limitations - Description........................................................................................ 11 General................................................................................................................... 32 Permissible tolerances........................................................................................... 52.1 Elapsed and installed time intervals....................................................................... 52.2 Flying hours based intervals................................................................................... 52.3 Calendar time based intervals................................................................................ 52.4 Landings based intervals........................................................................................ 5
Index of Tables Page
1 References............................................................................................................. 3
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ReferencesTable 1 References
Data module/Technical publication Title
PC24-A-A04-10-0000-00A-000A-A Mandatory life limited items - Function, data for plans and de-scription
PC24-A-A04-20-0000-00A-000A-A Mandatory structural inspection items - Function, data for plansand description
PC24-A-A04-30-0000-00A-000A-A Certification maintenance requirements - Function, data forplans and description
PC24-A-A04-40-0000-00A-000A-A Critical design configuration control limitations - Function, datafor plans and description
PC24-A-E20-40-0000-00A-913A-A Corrosion control - General maintenance procedure
PC24-A-E51-10-0001-00A-040A-A Structural classification - Description
Description
1 General
Note
Aircraft Maintenance Manual Document Number: 02378 Issue 005 Revision 19 dated 26 May 2020.
The Airworthiness Limitations (AL) section consists of four subsections:
Data Module Title Data Module Reference Issue Date Issue / Revision Number
Mandatory Life LimitedItems
PC24-A-A04-10-0000-00A-000A-A
06 June 2018 Issue 004 Revision 00
Mandatory Structural In-spection Items
PC24-A-A04-20-0000-00A-000A-A
26 May 2020 Issue 005 Revision 00
Certification MaintenanceRequirement
PC24-A-A04-30-0000-00A-000A-A
14 October 2019 Issue 007 Revision 00
Critical Design Configura-tion Control Limitation
PC24-A-A04-40-0000-00A-000A-A
06 June 2018 Issue 004 Revision 00
The limit of validity of the maintenance program defined as the Aircraft Maintenance Manual (AMM) including theAL section is 30,000 FH or 30,000 landings, whichever comes first.
Table 2, Temporary life limit table deleted.
For the life limited parts of the engine (rotors and turbines) refer to section 05-00-00 of the Williams FJ44-4A-QPMLine Maintenance Manual 110990-201.
The AL section is approved by EASA and variations must also be approved.
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The AL section is also FAA approved for US registered aircraft in accordance with the provisions of FAR 21.29 ofthe US Federal Aviation Regulations. In addition, this section specifies maintenance required under FAR 43.16 andFAR 91.403 of the US Federal Aviation Regulations unless an alternate program has been FAA approved.
The tables defined in Chapter 04 of the AMM list the mandatory inspection items and life limited items forinspection, removal or installation and state the level of action required. They include, together with the necessaryrequirements, cross references to the maintenance procedures which are necessary to do the inspections,removals or installations.
The determination of inspection thresholds, repeat intervals and life limits contained in this AMM are based onaverage usage assumptions and average environmental conditions. If the aircraft is operated in a manner thatwould invalidate these assumptions, the operator / owner is advised to contact Pilatus Aircraft Ltd. for furtheradvice on the maintenance program. This is the case if:− More than 50% of the ground operations are performed on unpaved runways on an annual basis.− More than 25% of the ground operations are performed on grass runways on an annual basis.− Special missions are flown on a very frequent basis such as low altitude flights in combination with flight
durations above 1 hour.− Operation in extremely humid tropics, or in exceptionally cold, damp climates, or salt-laden conditions.
The maximum corrosion level to be maintained is Corrosion Level 1, PC24-A-E20-40-0000-00A-913A-A.
The date on the aircraft data plate is to be used as the start time for all the calendar time limited items listed in thissection.
All Class 1 parts (PC24-A-E51-10-0001-00A-040A-A) are to be tracked when they are removed from the aircraftand details of their total usage recorded.
For all structural and component life limited items and inspection items where no landing records are available, afactor on the flying hours must be applied if there is a flying hours and landing limitation: The calculated applicablelandings equal to 2 x flying hours.
If the interval, or threshold, is given as any combination of Flying Hours, Months or Landings, such as 600 FH or 12Months, the interval, or threshold, is understood as “whichever comes first”.
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2 Permissible tolerances
It is the responsibility of the owner or operator to ensure the airworthiness of the aircraft. The owner or operator isresponsible for complying with any national regulations.
Note
Tolerances are not applicable to the mandatory life limited items nor to the mandatory structural inspection items.
The following permissible tolerances can be only applied to the task interval of Certification MaintenanceRequirements (CMR) items listed in PC24-A-A04-30-0000-00A-000A-A, or Critical Design Configuration ControlLimitation (CDCCL) tasks listed in PC24-A-A04-40-0000-00A-000A-A that have intervals marked with an asterisksymbol (*) on a case-by-case basis. It is the responsibility of the owner or operator to ensure that any extension isaccepted by the local airworthiness authority of the affected aircraft.
The CMR intervals defined in PC24-A-A04-30-0000-00A-000A-A are at least 10% lower than the required intervaldefined in the System Safety Assessment (SSA). Therefore, the permissible tolerances would not compromise therequired interval stated in the SSAs.
2.1 Elapsed and installed time intervals
The date on the aircraft data plate is to be used as the start time for all the tasks with calendar time listed inChapter 4 and Chapter 5.
The subsequent monitoring procedure for all the calendar time limited items after their initial replacement orinspection, will be in installed or elapsed time. Each task with a calendar time is understood as installed time unlessstated as “elapsed”. This applies to task in Chapter 4 and Chapter 5.
Elapsed time is the time interval since manufacture of the component.
Installed time is the time interval since the installation of the component on the aircraft.
2.2 Flying hours based intervals
The tolerances permissible for the flying hour based intervals is ±10%, but not more than 500 Flying Hours.
2.3 Calendar time based intervals
The tolerances permissible for the calendar time based intervals is ±10%, but not more than 6 Months.
2.4 Landings based intervals
The tolerances permissible for the landings based intervals is ±10%, but not more than 500 Landings.
This Airworthiness Limitation Section is approved by EASA on 29 April 2020 under project numbers10073159 and 10073160.
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Mandatory life limited items
Function, data for plans and description
Applicable to all PC-24 aircraft: PC24 A
Table of Contents Page
Mandatory life limited items - Function, data for plans and description...................................... 11 General................................................................................................................... 4
Index of Tables Page
1 References............................................................................................................. 32 Mandatory life limited items.................................................................................... 4
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ReferencesTable 1 References
Data module/Technical publication Title
PC24-A-E21-60-0003-00A-520A-A Flow control valve - Remove procedure
PC24-A-E21-60-0003-00A-720A-A Flow control valve - Install procedure
PC24-A-E21-60-0004-00A-520A-A Temperature control valve - Remove procedure
PC24-A-E21-60-0004-00A-720A-A Temperature control valve - Install procedure
PC24-A-E25-65-0001-00A-520A-A Portable fire extinguisher - Remove procedure
PC24-A-E25-65-0001-00A-720A-A Portable fire extinguisher - Install procedure
PC24-A-E27-10-0005-00A-520A-A Aileron trim actuator, LH - Remove procedure
PC24-A-E27-10-0005-00A-720A-A Aileron trim actuator, LH - Install procedure
PC24-A-E27-10-0021-00A-520A-A Control yoke pitch trim switch - Remove procedure
PC24-A-E27-10-0021-00A-720A-A Control yoke pitch trim switch - Install procedure
PC24-A-E27-20-0006-00A-520A-A Rudder trim actuator - Remove procedure
PC24-A-E27-20-0006-00A-720A-A Rudder trim actuator - Install procedure
PC24-A-E27-40-0001-00A-520A-A Pitch trim actuator - Remove procedure
PC24-A-E27-40-0001-00A-720A-A Pitch trim actuator - Install procedure
PC24-A-E27-50-0002-00A-520A-A Flap actuator inboard - Remove procedure
PC24-A-E27-50-0002-00A-720A-A Flap actuator inboard - Install procedure
PC24-A-E27-50-0004-00A-520A-A Flap actuator, RH inboard - Remove procedure
PC24-A-E27-50-0004-00A-720A-A Flap actuator, RH inboard - Install procedure
PC24-A-E32-10-0001-00A-520A-A Main landing gear assembly - Remove procedure
PC24-A-E32-10-0001-00A-720A-A Main landing gear assembly - Install procedure
PC24-A-E32-20-0001-00A-520A-A Nose landing gear assembly - Remove procedure
PC24-A-E32-20-0001-00A-720A-A Nose landing gear assembly - Install procedure
PC24-A-E32-40-0010-00A-520A-A Motor pump - Remove procedure
PC24-A-E32-40-0010-00A-720A-A Motor pump - Install procedure
PC24-A-E32-40-0011-00A-520A-A Hydraulic reservoir - Remove procedure
PC24-A-E32-40-0011-00A-720A-A Hydraulic reservoir - Install procedure
PC24-A-E32-50-0001-00A-520A-A Nose wheel steering mechanism - Remove procedure
PC24-A-E32-50-0001-00A-720A-A Nose wheel steering mechanism - Install procedure
PC24-A-E35-10-0001-00A-520A-A Oxygen standard cylinder - Remove procedure
PC24-A-E35-10-0001-00A-720A-A Oxygen standard cylinder - Install procedure
PC24-A-E35-10-0002-00A-520A-A Oxygen large cylinder - Remove procedure
PC24-A-E35-10-0002-00A-720A-A Oxygen large cylinder - Install procedure
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Description
1 General
Life limits are applicable to structural items, which are certified according to safe-life requirements, such as thelanding gear and system components such as actuators. Life limits also apply to oxygen bottles.
A life limit for that element is set to the threshold which is within the life of the aircraft. Items that have reached theirlife limit must be discarded.
Life limited replacements of system components may be required to prevent safety critical failures or due toinadequate performance experienced during equipment endurance testing. Items that have reached their life limitmust be discarded at the specified threshold/interval.
Mandatory life limited items for the PC-24 aircraft are listed in Table 2. The intervals are expressed in Flying Hours,Landings or Calendar Time.
Table 2 Mandatory life limited items
Task number Item name Task description Life limit Data module refer-ence
AL-21-60-011Temperature controlvalve (P/N963.30.11.116)
Life limit (Removeand install a service-able temperaturecontrol valve)
20,000 FH
PC24-A-E21-60-0004-00A-520A-A
PC24-A-E21-60-0004-00A-720A-A
AL-21-60-012 Flow control valve
Life limit (Removeand install a service-able flow controlvalve)
27,000 FH
PC24-A-E21-60-0003-00A-520A-A
PC24-A-E21-60-0003-00A-720A-A
AL-25-65-014 Portable fire extin-guisher
Life limit (Removeand install a service-able portable fire ex-tinguisher)
120 Months(elapsed)
PC24-A-E25-65-0001-00A-520A-A
PC24-A-E25-65-0001-00A-720A-A
AL-27-10-024 Aileron trim actuator(P/N 978.73.15.124)
Life limit (Removeand install a service-able aileron trim ac-tuator)
13,200 FH / 30,000LDG
PC24-A-E27-10-0005-00A-520A-A
PC24-A-E27-10-0005-00A-720A-A
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Table 2 Mandatory life limited items
Task number Item name Task description Life limit Data module refer-ence
AL-27-20-019 Rudder trim actuator(P/N 978.73.15.124)
Life limit (Removeand install a service-able rudder trim ac-tuator)
13,200 FH / 30,000LDG
PC24-A-E27-20-0006-00A-520A-A
PC24-A-E27-20-0006-00A-720A-A
AL-27-40-020 Pitch trim actuator(P/N 978.73.14.214)
Life limit (Removeand install a service-able pitch trim actua-tor)
7,525 FH / 30,000LDG
PC24-A-E27-40-0001-00A-520A-A
PC24-A-E27-40-0001-00A-720A-A
AL-27-40-023Pitch trim switches(Pilot and copilotcontrol yokes)
Life limit (Removeand install new pitchtrim switches)
10,000 FH
PC24-A-E27-10-0021-00A-520A-A
PC24-A-E27-10-0021-00A-720A-A
AL-27-50-021
Flap actuator, INBDLH and RH (P/N960.10.04.173 (LH)and 960.10.04.174(RH))
Life limit (Removeand install a service-able INBD flap actua-tor)
29,700 FH
PC24-A-E27-50-0002-00A-520A-A
PC24-A-E27-50-0002-00A-720A-A
PC24-A-E27-50-0004-00A-520A-A
PC24-A-E27-50-0004-00A-720A-A
AL-32-10-024
Main landing gearassemblies (P/N532.10.24.921 and532.10.24.922)
Life limit (Removeand install new Mainlanding gear assem-blies)
30,000 FH / 30,000LDG
PC24-A-E32-10-0001-00A-520A-A
PC24-A-E32-10-0001-00A-720A-A
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Table 2 Mandatory life limited items
Task number Item name Task description Life limit Data module refer-ence
AL-32-20-023Nose landing gearassembly (P/N532.20.24.904)
Life limit (Removeand install a service-able nose landinggear assembly)
30,000 FH / 30,000LDG
PC24-A-E32-20-0001-00A-520A-A
PC24-A-E32-20-0001-00A-720A-A
AL-32-40-021 Hydraulic systemreservoir
Life limit (Removeand install a service-able hydraulic sys-tem reservoir)
21,000 FH
PC24-A-E32-40-0011-00A-520A-A
PC24-A-E32-40-0011-00A-720A-A
AL-32-40-022Hydraulic systemmotor pump (P/N960.30.01.167)
Life limit (Removeand install a service-able hydraulic sys-tem motor pump)
4,560 FH
PC24-A-E32-40-0010-00A-520A-A
PC24-A-E32-40-0010-00A-720A-A
AL-32-50-025
Nose landing gearsteering mechanism(P/N 532.50.24.905and 532.50.24.906)
Life limit (Removeand install a service-able nose landinggear steering mecha-nism)
30,000 FH / 30,000LDG
PC24-A-E32-50-0001-00A-520A-A
PC24-A-E32-50-0001-00A-720A-A
AL-35-10-007 Oxygen cylinderRemove and install aserviceable oxygencylinder
180 Months(elapsed)
PC24-A-E35-10-0001-00A-520A-A
PC24-A-E35-10-0001-00A-720A-A
PC24-A-E35-10-0002-00A-520A-A
PC24-A-E35-10-0002-00A-720A-A
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Mandatory structural inspection items
Function, data for plans and description
Applicable to all PC-24 aircraft: PC24 A
Table of Contents Page
Mandatory structural inspection items - Function, data for plans and description...................... 11 General................................................................................................................... 4
Index of Tables Page
1 References............................................................................................................. 32 Mandatory structural inspection items.................................................................... 5
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ReferencesTable 1 References
Data module/Technical publication Title
PC24-A-E27-00-0001-00A-312A-A Control tube - Examination with a borescope
PC24-A-E27-05-0001-00A-284A-A Pitch trim actuator upper and lower attachments - Special ir-regular inspection
PC24-A-E27-05-0010-01A-310A-A Control-units sprocket wheels - Visual examination
PC24-A-E52-05-0003-00A-284A-A Pax Door Mechanism, shoot bolts - Special irregular inspection
PC24-A-E52-05-0004-00A-284A-A Cargo Door Mechanism, shoot bolts - Special irregular inspec-tion
PC24-A-E52-05-0005-00A-284A-A Cargo Door Mechanism, hook bolts - Special irregular inspec-tion
PC24-A-E53-05-0014-00A-284A-A Cabin attachments, emergency exit plug-in corner - Special ir-regular inspection
PC24-A-E53-05-0015-00A-284A-A Cabin window frames - Special irregular inspection
PC24-A-E53-05-0016-00A-284A-A Cargo door frame 32, LH - Special irregular inspection
PC24-A-E53-05-0017-00A-284A-A Upper cargo door longeron casing - Special irregular inspec-tion
PC24-A-E53-05-0017-01A-284A-A Upper cargo door longeron casing, inner corner - Special irreg-ular inspection
PC24-A-E53-05-0018-00A-284A-A Lower cargo door longeron casing - Special irregular inspec-tion
PC24-A-E53-05-0019-00A-284A-A Cabin side skin - Special irregular inspection
PC24-A-E53-05-0020-00A-284A-A Aft pressure bulkhead - Special irregular inspection
PC24-A-E53-05-0021-00A-284A-A Cockpit lower longeron (101 to 124) - Special irregular inspec-tion
PC24-A-E53-05-0021-00B-284A-A Cockpit lower longeron (125 up) - Special irregular inspection
PC24-A-E53-05-0022-00A-284A-A Cockpit upper longeron - Special irregular inspection
PC24-A-E53-05-0023-00A-284A-A Cockpit middle skin - Special irregular inspection
PC24-A-E53-05-0024-00A-284A-A Cockpit lower skin - Special irregular inspection
PC24-A-E53-05-0025-00A-284A-A Cockpit angle frame 12 - Special irregular inspection
PC24-A-E55-05-0003-00A-284A-A Horizontal stabilizer to vertical stabilizer attachment, bolts -Special irregular inspection
PC24-A-E55-05-0004-00A-284A-A Rudder skin - Special irregular inspection
PC24-A-E57-05-0021-00A-284A-A Wing lower skin, access hole cut-out - Special irregular inspec-tion
PC24-A-E57-05-0022-00A-284A-A Wing to fuselage FR24 and FR28 attachments - Special irregu-lar inspection
PC24-A-E57-05-0023-00A-284A-A Wing lower skin attachment - Special irregular inspection
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Data module/Technical publication Title
PC24-A-E57-05-0024-00A-284A-A Wing lower skin, MLG cut-out - Special irregular inspection
PC24-A-E57-05-0025-00A-284A-A Wing lower skin to rear spar attachment - Special irregular in-spection
PC24-A-E57-05-0026-00A-284A-A Wing upper skin fuel hole - Special irregular inspection
PC24-A-E57-05-0027-00A-284A-A Wing front spar - Special irregular inspection
PC24-A-E57-05-0029-01A-284A-A Inboard flap joint-twelve, segment fitting two - Special irregularinspection
PC24-A-E57-05-0029-02A-284A-A Middle flap joint-twelve, segment fitting two - Special irregularinspection
PC24-A-E57-05-0030-01A-284A-A Inboard flap-hinge forward fitting (101-130) - Special irregularinspection
PC24-A-E57-05-0030-01B-284A-A Inboard flap-hinge forward fitting (131 up) - Special irregular in-spection
PC24-A-E57-05-0031-02A-284A-A Middle flap-hinge forward fitting - Special irregular inspection
PC24-A-E57-05-0031-03A-284A-A Outboard flap-hinge forward fitting - Special irregular inspec-tion
PC24-A-E57-05-0032-01A-284A-A Inboard flap-hinge beam - Special irregular inspection
PC24-A-E57-05-0032-02A-284A-A Middle flap-hinge beam - Special irregular inspection
PC24-A-E57-05-0032-03A-284A-A Outboard flap-hinge beam - Special irregular inspection
PC24-A-E57-05-0033-01A-284A-A Inboard flap-hinge intercostal - Special irregular inspection
PC24-A-E71-05-0002-00A-284A-A Engine drag strut - Special irregular inspection
PC24-A-E71-05-0003-00A-284A-A Forward engine mount attachments - Special irregular inspec-tion
PC24-A-E71-05-0004-00A-284A-A Rear engine attachments - Special irregular inspection
Description
1 General
The Mandatory Structural Inspection Items (MSII) are failure critical items arising from damage toleranceevaluation. The MSII must be inspected not later than the threshold and repeated not later than the subsequentinterval.
MSII for the PC-24 aircraft are listed in Table 2. The intervals are expressed in Flying Hours, Landings or CalendarTime.
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Table 2 Mandatory structural inspection items
Task number Item name Task description Threshold Interval Data module ref-erence
AL-27-00-025 Control columnsprocket gear as-sy (Applicable toMSN 101 to 134with no corrosionprotection com-pound or primer)
Visual examina-tion
N/A 12 Months PC24-A-E27-05-0010-01A-310A-A
AL-27-00-026 Control columnsprocket gear as-sy (Applicable toMSN 101 to 134with only corro-sion protectioncompound)
Visual examina-tion
N/A 120 Months PC24-A-E27-05-0010-01A-310A-A
AL-27-00-027 Control wheelcolumn assy (Ap-plicable to MSN101 to 103)
Examination witha borescope
N/A 24 Months PC24-A-E27-00-0001-00A-312A-A
AL-27-40-024 Pitch trim actua-tor upper andlower attach-ments
Special irregularinspection
15,000 FH /15,000 LDG
N/A PC24-A-E27-05-0001-00A-284A-A
AL-52-10-015 Passenger doormechanism,shoot bolts
Special irregularinspection
15,000 FH /15,000 LDG
7,500 FH / 7,500LDG
PC24-A-E52-05-0003-00A-284A-A
AL-52-30-016 Cargo doormechanism,shoot bolts
Special irregularinspection
15,000 FH /15,000 LDG
7,500 FH / 7,500LDG
PC24-A-E52-05-0004-00A-284A-A
AL-52-30-017 Cargo doormechanism, hookbolts
Special irregularinspection
15,000 FH /15,000 LDG
N/A PC24-A-E52-05-0005-00A-284A-A
AL-53-10-052 Cockpit lowerlongeron (appli-cable to MSN101 to 124)
Special irregularinspection
10,000 FH /10,000 LDG
5,000 FH / 5,000LDG
PC24-A-E53-05-0021-00A-284A-A
AL-53-10-053 Cockpit lowerlongeron (Appli-cable to MSN125 UP)
Special irregularinspection
10,000 FH /10,000 LDG
5,000 FH / 5,000LDG
PC24-A-E53-05-0021-00B-284A-A
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Table 2 Mandatory structural inspection items
Task number Item name Task description Threshold Interval Data module ref-erence
AL-53-10-054 Cockpit upperlongeron
Special irregularinspection
10,000 FH /10,000 LDG
5,000 FH / 5,000LDG
PC24-A-E53-05-0022-00A-284A-A
AL-53-10-055 Cockpit middleskin
Special irregularinspection
15,000 FH /15,000 LDG
5,000 FH / 5,000LDG
PC24-A-E53-05-0023-00A-284A-A
AL-53-10-056 Cockpit lowerskin
Special irregularinspection
15,000 FH /15,000 LDG
5,000 FH / 5,000LDG
PC24-A-E53-05-0024-00A-284A-A
AL-53-10-057 Cockpit angleframe 12
Special irregularinspection
15,000 FH /15,000 LDG
N/A PC24-A-E53-05-0025-00A-284A-A
AL-53-20-043 Cabin attach-ments, emergen-cy exit plug-incorner
Special irregularinspection
15,000 FH /15,000 LDG
7,500 FH / 7,500LDG
PC24-A-E53-05-0014-00A-284A-A
AL-53-20-044 Cabin windowframes
Special irregularinspection
15,000 FH /15,000 LDG
7,500 FH / 7,500LDG
PC24-A-E53-05-0015-00A-284A-A
AL-53-20-045 Cargo door frame32, LH
Special irregularinspection
15,000 FH /15,000 LDG
7,500 FH / 7,500LDG
PC24-A-E53-05-0016-00A-284A-A
AL-53-20-046 Upper cargo doorlongeron casing
Special irregularinspection
15,000 FH /15,000 LDG
7,500 FH / 7,500LDG
PC24-A-E53-05-0017-00A-284A-A
AL-53-20-047 Lower cargo doorlongeron casing
Special irregularinspection
15,000 FH /15,000 LDG
5,000 FH / 5,000LDG
PC24-A-E53-05-0018-00A-284A-A
AL-53-20-048 Wing to fuselageFR24 and FR28attachments
Special irregularinspection
15,000 FH /15,000 LDG
N/A PC24-A-E57-05-0022-00A-284A-A
AL-53-20-049 Cabin side skin Special irregularinspection
15,000 FH /15,000 LDG
5,000 FH / 5,000LDG
PC24-A-E53-05-0019-00A-284A-A
AL-53-20-050 Upper cargo doorlongeron casing,inner corner
Special irregularinspection
15,000 FH /15,000 LDG
7,500 FH / 7,500LDG
PC24-A-E53-05-0017-01A-284A-A
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Table 2 Mandatory structural inspection items
Task number Item name Task description Threshold Interval Data module ref-erence
AL-53-20-051 Aft pressure bulk-head
Special irregularinspection
15,000 FH /15,000 LDG
10,000 FH /10,000 LDG
PC24-A-E53-05-0020-00A-284A-A
AL-55-10-023 Horizontal stabil-izer to verticalstabilizer attach-ment, bolts
Special irregularinspection
15,000 FH /15,000 LDG
N/A PC24-A-E55-05-0003-00A-284A-A
AL-55-40-022 Rudder skin Special irregularinspection
25,000 FH /25,000 LDG
5,000 FH / 5,000LDG
PC24-A-E55-05-0004-00A-284A-A
AL-57-20-012 Wing lower skin,access hole cut-out
Special irregularinspection
10,000 FH /10,000 LDG
5,000 FH / 5,000LDG
PC24-A-E57-05-0021-00A-284A-A
AL-57-20-013 Wing lower skinattachment andaccess panel cut-outs
Special irregularinspection
15,000 FH /15,000 LDG
5,000 FH / 5,000LDG
PC24-A-E57-05-0023-00A-284A-A
AL-57-20-014 Wing lower skin,MLG cut-out andfront spar spliceattachment
Special irregularinspection
15,000 FH /15,000 LDG
7,500 FH / 7,500LDG
PC24-A-E57-05-0024-00A-284A-A
AL-57-20-015 Wing lower skinto rear spar at-tachment
Special irregularinspection
25,000 FH /25,000 LDG
5,000 FH / 5,000LDG
PC24-A-E57-05-0025-00A-284A-A
AL-57-20-016 Wing upper skinfuel opening
Special irregularinspection
20,000 FH /20,000 LDG
5,000 FH / 5,000LDG
PC24-A-E57-05-0026-00A-284A-A
AL-57-20-017 Wing front spar Special irregularinspection
20,000 FH /20,000 LDG
10,000 FH /10,000 LDG
PC24-A-E57-05-0027-00A-284A-A
AL-57-50-018 Inboard flap joint-twelve, segmentfitting two
Special irregularinspection
15,000 FH /15,000 LDG
7,500 FH / 7,500LDG
PC24-A-E57-05-0029-01A-284A-A
AL-57-50-019 Middle flap joint-twelve, segmentfitting two
Special irregularinspection
15,000 FH /15,000 LDG
7,500 FH / 7,500LDG
PC24-A-E57-05-0029-02A-284A-A
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Table 2 Mandatory structural inspection items
Task number Item name Task description Threshold Interval Data module ref-erence
AL-57-50-020 Inboard flap-hinge forward fit-ting (Applicableto MSN 101 to130)
Special irregularinspection
15,000 FH /15,000 LDG
7,500 FH / 7,500LDG
PC24-A-E57-05-0030-01A-284A-A
AL-57-50-021 Inboard flap-hinge forward fit-ting (Applicableto MSN 131 UP)
Special irregularinspection
15,000 FH /15,000 LDG
7,500 FH / 7,500LDG
PC24-A-E57-05-0030-01B-284A-A
AL-57-50-022 Middle flap-hingeforward fitting
Special irregularinspection
15,000 FH /15,000 LDG
7,500 FH / 7,500LDG
PC24-A-E57-05-0031-02A-284A-A
AL-57-50-023 Outboard flap-hinge forward fit-ting
Special irregularinspection
15,000 FH /15,000 LDG
7,500 FH / 7,500LDG
PC24-A-E57-05-0031-03A-284A-A
AL-57-50-024 Inboard flap-hinge beam
Special irregularinspection
15,000 FH /15,000 LDG
7,500 FH / 7,500LDG
PC24-A-E57-05-0032-01A-284A-A
AL-57-50-025 Middle flap-hingebeam
Special irregularinspection
15,000 FH /15,000 LDG
7,500 FH / 7,500LDG
PC24-A-E57-05-0032-02A-284A-A
AL-57-50-026 Outboard flap-hinge beam
Special irregularinspection
15,000 FH /15,000 LDG
7,500 FH / 7,500LDG
PC24-A-E57-05-0032-03A-284A-A
AL-57-50-027 Inboard flap-hinge intercostal
Special irregularinspection
15,000 FH /15,000 LDG
7,500 FH / 7,500LDG
PC24-A-E57-05-0033-01A-284A-A
AL-71-20-005 Forward enginemount attach-ments
Special irregularinspection
15,000 FH /15,000 LDG
N/A PC24-A-E71-05-0003-00A-284A-A
AL-71-20-006 Rear enginemount attach-ments
Special irregularinspection
15,000 FH /15,000 LDG
N/A PC24-A-E71-05-0004-00A-284A-A
AL-71-20-007 Engine drag strut Special irregularinspection
15,000 FH /15,000 LDG
N/A PC24-A-E71-05-0002-00A-284A-A
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Certification maintenance requirements
Function, data for plans and description
Applicable to all PC-24 aircraft: PC24 A
Table of Contents Page
Certification maintenance requirements - Function, data for plans and description................... 11 General................................................................................................................... 4
Index of Tables Page
1 References............................................................................................................. 32 Certification maintenance requirements................................................................. 4
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ReferencesTable 1 References
Data module/Technical publication Title
PC24-A-E21-20-0000-00A-320A-A Bleed air flow switch - Operation test
PC24-A-E21-30-0000-00A-320A-A Pressurization control - Operation test
PC24-A-E21-30-0002-00A-340A-A Pressure relief valve - Function test
PC24-A-E21-30-0004-00A-310A-A Negative pressure relief valve - Visual examination
PC24-A-E24-94-0005-00A-320A-A Vapor cycle contactor - Operation test
PC24-A-E26-00-0000-00A-320A-A Fire protection - Operation test
PC24-A-E26-10-0002-00A-320A-A Smoke detector - Operation test
PC24-A-E27-10-0004-00A-310A-A Aileron trim - Visual examination
PC24-A-E27-10-0005-00A-340A-A Aileron trim actuator current limiter - Function test
PC24-A-E27-20-0005-00A-310A-A Rudder trim mechanism - Visual examination
PC24-A-E27-20-0006-00A-520A-A Rudder trim actuator - Remove procedure
PC24-A-E27-20-0006-00A-720A-A Rudder trim actuator - Install procedure
PC24-A-E27-40-0000-00A-320A-A Horizontal stabilizer secondary trim system - Operation test
PC24-A-E27-40-0000-01A-320A-A Horizontal stabilizer primary trim system secondary powersource - Operation test
PC24-A-E27-50-0000-00A-310A-A Flaps control - Visual examination
PC24-A-E27-60-0000-00A-310A-A Spoilers control - Visual examination
PC24-A-E28-20-0003-00A-320A-A Cross-feed shutoff valve actuator - Operation test
PC24-A-E28-20-0016-00A-320A-A Inward/outward relief valve - Operation test
PC24-A-E28-40-0000-00A-320A-A Fuel indicating - Operation test
PC24-A-E28-40-0004-00A-340A-A Fuel gauging protection box - Function test
PC24-A-E30-10-0005-00A-312A-A Fixed leading edge internal structure - Examination with aborescope
PC24-A-E30-10-0007-00A-320A-A Ejector flow check valve pressure switch - Operation test
PC24-A-E30-40-0000-00A-320A-A Windshield heating - Operation test
PC24-A-E30-40-0000-01A-369A-A Windshield heating - Examination with Infrared camera
PC24-A-E32-30-0002-00A-320A-A Emergency gear extension cable - Operation test
PC24-A-E34-11-0000-00A-310A-A Pitot static probes - Visual examination
PC24-A-E34-11-0000-00A-366A-A Pitot static probes - Heater resistance check
PC24-A-E34-14-0001-00A-366A-A Angle of attack sensor heater - Resistance check
PC24-A-E35-10-0000-00A-340A-A Crew oxygen system - Function test
PC24-A-E35-10-0001-00A-520A-A Oxygen standard cylinder - Remove procedure
PC24-A-E35-10-0001-00A-720A-A Oxygen standard cylinder - Install procedure
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Data module/Technical publication Title
PC24-A-E35-10-0002-00A-520A-A Oxygen large cylinder - Remove procedure
PC24-A-E35-10-0002-00A-720A-A Oxygen large cylinder - Install procedure
PC24-A-E35-20-0000-00A-320A-A Passenger oxygen system - Operation test
PC24-A-E36-10-0000-00A-320A-A Bleed air distribution system - Operation test
PC24-A-E36-10-0008-00A-310A-A Bleed air heat shield - Visual examination
PC24-A-E36-11-0000-00A-320A-A Bleed air leak detection system - Operation test
Description
1 General
A Certification Maintenance Requirement (CMR) is a maintenance action which is necessary for achieving thesafety objectives of CS 23.1309(b). Table 2 contains the list of CMRs currently identified.
Table 2 Certification maintenance requirements
Task number Item name Task description Interval Data module refer-ence
AL-21-20-013 Bleed air flow switch Operation test *4,800 FH / 96Months
PC24-A-E21-20-0000-00A-320A-A
AL-21-30-004Cabin pressurizationcontrol system man-ual control function
Operation test 600 FHPC24-A-E21-30-0000-00A-320A-A
AL-21-30-005 Pressure relief valve Function test *4,800 FH / 96Months
PC24-A-E21-30-0002-00A-340A-A
AL-21-30-006 Negative pressurerelief valve Visual examination *4,800 FH / 96
Months
PC24-A-E21-30-0004-00A-310A-A
AL-21-30-007Cabin pressurizationcontrol system dumpcontrol function
Operation test 600 FHPC24-A-E21-30-0000-00A-320A-A
AL-21–30–008 Moved to ScheduledMaintenance
AL-21-30-009Cabin Pressure Con-troller Altitude-Limit-ing Function
Function test *4,800 FH / 96Months
PC24-A-E35-20-0000-00A-320A-A
AL-24-60-007Vapor cycle coolingsystem contactor(Pre SB 42-005)
Operation test *4,800 FH / 96Months
PC24-A-E24-94-0005-00A-320A-A
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Table 2 Certification maintenance requirements
Task number Item name Task description Interval Data module refer-ence
AL-26-10-009 Smoke detector Operation test 600 FHPC24-A-E26-10-0002-00A-320A-A
AL-26-20-001 Engine isolation sys-tem Operation test 600 FH
PC24-A-E26-00-0000-00A-320A-A
AL-26-20-002 Engine fire extin-guisher system Operation test 600 FH
PC24-A-E26-00-0000-00A-320A-A
AL-27-10-004 Aileron trim mecha-nism Visual examination *600 FH / 12 Months
PC24-A-E27-10-0004-00A-310A-A
AL-27-10-017 Aileron trim actuator Overhaul *3,600 FHPC24-A-E27-10-0005-00A-340A-A
AL-27-20-007 Rudder Trim Mecha-nism
Visual examination *600 FH / 12 Months PC24-A-E27-20-0005-00A-310A-A
AL-27-20-018 Rudder trim actuator Overhaul *3,600 FH
PC24-A-E27-20-0006-00A-520A-A
PC24-A-E27-20-0006-00A-720A-A
AL-27-40-012Horizontal stabilizersecondary trim sys-tem
Operation test 600 FHPC24-A-E27-40-0000-00A-320A-A
AL-27-40-022
Horizontal stabilizerprimary trim systemsecondary powersource
Operation test 600 FH
PC24-A-E27-40-0000-01A-320A-A
Note
This procedure wasupdated to issue
007–00 dated2019.09.25. This is-sue, or any later is-sue must be used.
AL-27-50-013 Flap interconnectmechanism Visual examination *1,200 FH / 24
Months
PC24-A-E27-50-0000-00A-310A-A
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Table 2 Certification maintenance requirements
Task number Item name Task description Interval Data module refer-ence
AL-27-60-015Ground spoiler over-center locking devicemechanism
Visual examination *1,200 FH / 12Months
PC24-A-E27-60-0000-00A-310A-A
AL-28-20-005 Cross feed valve(Pre SB 42-005)
Operational test *600 FH PC24-A-E28-20-0003-00A-320A-A
AL-28-20-007 Inward-Outward Re-lief Valve
Operational test *2,400 FH / 48Months
PC24-A-E28-20-0016-00A-320A-A
AL-28-40-012 Reed Low Level FuelSwitch
Operation test *2,400 FH / 48Months
PC24-A-E28-40-0000-00A-320A-A
AL-28-40-013Transient suppressordevice lightning pro-tection function
Function test *2,400 FH / 48Months
PC24-A-E28-40-0004-00A-340A-A
AL-30-10-004 Fixed Leading EdgeAssembly PiccoloTube
Examination with aborescope
*3,600 FH PC24-A-E30-10-0005-00A-312A-A
AL-30-10-008 Ejector flow controlvalve pressure switch Function test 600 FH
PC24-A-E30-10-0007-00A-320A-A
AL-30-40-007 Windshield emergen-cy heating system Operation test *600 FH
PC24-A-E30-40-0000-00A-320A-A
AL-30-40-010
Left windshield heat-ing (P/N959.81.10.135 and959.81.10.141)
Examination with In-frared camera
80 Landings repeat-ed interval i.a.w. ac-ceptance criteria ma-trix
PC24-A-E30-40-0000-01A-369A-A
AL-30–40–011
Right windshieldheating (P/N959.81.10.136 and959.81.10.142)
Examination with In-frared camera
80 Landings repeat-ed interval i.a.w. ac-ceptance criteria ma-trix
PC24-A-E30-40-0000-01A-369A-A
AL-32-30-008Landing gear emer-gency release mech-anism
Operation test 600 FH / 12 MonthsPC24-A-E32-30-0002-00A-320A-A
AL-34-11-007 LH Pitot-static probe Visual examination 600 FH / 12 MonthsPC24-A-E34-11-0000-00A-310A-A
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Table 2 Certification maintenance requirements
Task number Item name Task description Interval Data module refer-ence
AL-34-11-008 RH Pitot-static probe Visual examination 600 FH / 12 MonthsPC24-A-E34-11-0000-00A-310A-A
AL-34-11-009 Standby Pitot-staticprobe Visual examination 600 FH / 12 Months
PC24-A-E34-11-0000-00A-310A-A
AL-34-11-010 Left pitot static probeheater Resistance check 600 FH
PC24-A-E34-11-0000-00A-366A-A
AL-34-11-011 Right pitot staticprobe heater Resistance check 600 FH
PC24-A-E34-11-0000-00A-366A-A
AL-34-11-012 Standby pitot staticprobe heater Resistance check 600 FH
PC24-A-E34-11-0000-00A-366A-A
AL-34-14-013 Left angle of attacksensor heater Resistance check 600 FH
PC24-A-E34-14-0001-00A-366A-A
AL-34-14-014 Right angle of attacksensor heater Resistance check 600 FH
PC24-A-E34-14-0001-00A-366A-A
AL-35-10-004 Temperature andpressure transducer Operation test *1,200 FH / 24
Months
PC24-A-E35-10-0000-00A-340A-A
AL-35-10-008 Oxygen cylinder Hydrostatic Testing 60 Months
PC24-A-E35-10-0001-00A-520A-A
PC24-A-E35-10-0001-00A-720A-A
PC24-A-E35-10-0002-00A-520A-A
PC24-A-E35-10-0002-00A-720A-A
AL-35-20-011 Passenger oxygendeployment system Operation test *1,200 FH / 24
Months
PC24-A-E35-20-0000-00A-320A-A
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Table 2 Certification maintenance requirements
Task number Item name Task description Interval Data module refer-ence
AL-36-10-005 Bleed air leak detec-tion system Operation test *3,600 FH
PC24-A-E36-11-0000-00A-320A-A
AL-36-10-006Bleed air heatshield / Overwingsandwich panel
Visual examination 1,200 FH / 24Months
PC24-A-E36-10-0008-00A-310A-A
AL-36–10–007 Moved to scheduledmaintenance
AL-36-10-008 Bleed air selectorswitch Operation test 600 FH
PC24-A-E36-10-0000-00A-320A-A
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Critical design configuration control limitations
Function, data for plans and description
Applicable to all PC-24 aircraft: PC24 A
Table of Contents Page
Critical design configuration control limitations - Function, data for plans and description......... 11 General................................................................................................................... 3
Index of Tables Page
1 References............................................................................................................. 32 Critical design configuration control limitations - Periodic inspections................... 33 Critical design configuration control limitations - General design........................... 3
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ReferencesTable 1 References
Data module/Technical publication Title
PC24-A-E28-00-0000-00A-369A-A Fuel - Bonding check
PC24-A-E28-20-0001-00A-310A-A Fuel booster pump bonding strap - Visual examination
Description
1 General
As required by the EASA Certification Review Item CRI E-10, the following CDCCL, inspections, or otherprocedures must be adhered to when performing maintenance, repairs, or alterations. These CDCCLs preclude theintegrity of the original type design of the fuel tank system from being unintentionally violated, and thereforeprevents the development of ignition sources within the fuel tank system. CDCCLs are defined in this AirworthinessLimitations section and are listed in Table 2 and Table 3 below.
Table 2 Critical design configuration control limitations - Periodic inspections
Task number Item name Task description Interval Data module refer-ence
AL-28-20-014 Fuel booster pumpbonding straps
Visual examination *4,800 FH / 96Months
PC24-A-E28-20-0001-00A-310A-A
Table 3 Critical design configuration control limitations - General design
Item name Task description
Fuel boost pump The hardware configuration and installation of the pumpmust not be modified.
Transient suppressor device The installation of the device must not be modified or re-moved.
Fuel system wire harness (Fuel 1 LH and Fuel 2 RHside)
The routing of the two wire harnesses must not bemodified.
Bleed air heat shield (Over wing foil) The installation of the foil must not be modified or re-moved.
PC-24 Aircraft Maintenance ManualUNCONTROLLED COPY
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Table 3 Critical design configuration control limitations - General design
Item name Task description
Fuel system component bonding:− Fuel boost pump− Fuel shutoff valve− Cross feed valve− Fuel low sensor (Reed switch)− Refuel/defuel shutoff valve− Fuel quantity gauging probe− High level sensor− Transient suppressor device− Flapper valves− Drain valves− Vent valves− Check valves− Main ejector fuel pump− Scavenge ejector pump− Fuel pipes.
If a fuel system component is replaced, a bonding checkmust be performed as part of the installation procedure.Refer to PC24-A-E28-00-0000-00A-369A-A.
PC-24 Aircraft Maintenance ManualUNCONTROLLED COPY
Effectivity: see data module page 1 PC24-A-A04-40-0000-00A-000A-AIssue 004 Revision 00
End of data moduleUNCLASSIFIED 2018-06-06 Page 4 PC
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