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


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


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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

PC-24 Aircraft Maintenance ManualUNCONTROLLED COPY

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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


Mandatory Structural In-spection Items

PC24-A-A04-20-0000-00A-000A-A


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


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



Mandatory life limited items - Function, data for plans and description...................................... 11 General................................................................................................................... 4


1 References............................................................................................................. 32 Mandatory life limited items.................................................................................... 4




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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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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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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




Mandatory structural inspection items - Function, data for plans and description...................... 11 General................................................................................................................... 4


1 References............................................................................................................. 32 Mandatory structural inspection items.................................................................... 5




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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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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


AL-27-00-027 Control wheelcolumn assy (Ap-plicable to MSN101 to 103)

Examination witha borescope


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


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


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


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)


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)


10,000 FH /10,000 LDG

5,000 FH / 5,000LDG

PC24-A-E53-05-0021-00B-284A-A




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AL-53-10-054 Cockpit upperlongeron


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


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


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


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


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


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


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


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


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


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


15,000 FH /15,000 LDG

7,500 FH / 7,500LDG

PC24-A-E53-05-0017-01A-284A-A




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AL-53-20-051 Aft pressure bulk-head


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


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


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


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


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


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


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


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


15,000 FH /15,000 LDG

7,500 FH / 7,500LDG

PC24-A-E57-05-0029-02A-284A-A




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AL-57-50-020 Inboard flap-hinge forward fit-ting (Applicableto MSN 101 to130)


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)


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


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


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


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


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


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


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


15,000 FH /15,000 LDG

N/A PC24-A-E71-05-0003-00A-284A-A

AL-71-20-006 Rear enginemount attach-ments


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




Certification maintenance requirements - Function, data for plans and description................... 11 General................................................................................................................... 4


1 References............................................................................................................. 32 Certification maintenance requirements................................................................. 4




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2019-10-14 Page 2



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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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


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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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


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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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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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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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




Critical design configuration control limitations - Function, data for plans and description......... 11 General................................................................................................................... 3


1 References............................................................................................................. 32 Critical design configuration control limitations - Periodic inspections................... 33 Critical design configuration control limitations - General design........................... 3




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2018-06-06 Page 2



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


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.




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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.




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pc-24 amm chapter 04 airworthiness limitations

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