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CessnaProceduresManual

Textron AviationCessna 500 Series Citation500/501, 550/S550/551, 560

THIS GUIDE IS CURRENT WITH THE MASTER MINIMUM EQUIPMENT LIST WHICH IS DISTRIBUTED BY THE DEPARTMENT OF TRANSPORTATION FEDERAL AVIATION ADMINISTRATION - REVISION 10a DATED

04/05/2019.

COPYRIGHT © 2020 MMEL REVISION 10aTextron AviationWICHITA, KANSAS, U.S.A.

CPM REVISION 01a

500CPM-10a-01a

NOTICE

The Master Minimum Equipment List (MMEL) is distributed by the Department of Transportation Federal Aviation Administration. This Master Minimum Equipment List Operation and Maintenance Procedures manual contains only the items from the Master Minimum Equipment List which have Maintenance (M) or Operational (O) procedure requirements. Cessna does not support Minimum Equipment List items not published in the MMEL.

Cessna’s policy is to revise this manual only to accommodate changes to a new MMEL revision, which requires a change to, or a new, Maintenance (M) or Operational (O) required procedure. If a revised MMEL is released, but does not affect any required procedure, the Operational and Maintenance manual will not be revised at that time. Cessna reserves the right to make format changes without generating a new revision.

Maintenance (M) or Operational (O) procedures in this manual are recommended by Cessna Aircraft Company. Most of the procedures in this manual have been approved in some MEL’s. This document is not FAA approved, but is intended to aid operators in writing and gaining approval for their specific Minimum Equipment List (MEL). The Operator is responsible to make sure that all crew members are properly trained in the use of MEL (M) and (O) procedures.

The Narrative section of each Maintenance (M) procedure is intended to satisfy the FAR 135 MEL requirement for training non-maintenance individuals who are authorized, in the MEL, to perform maintenance tasks.

500CPM-10a-01a

NOTES

For all provisos – Unless the proviso requires a system to be verified, it is assumed that all other systems are operative and no action is required to test these systems.

Where ever a dash (-) is listed in Column 2: Number Installed or Column 3: Number Required for Dispatch, it is the responsibility of the operator to replace the dash (-) with the actual number of each item, if any, installed on the aircraft in question

The operator must make an appropriate entry in the discrepancy report for each inoperative item.

The diagrams, drawings and/or pictures in this document may not reflect all possible installations. Refer to the aircraft equipment list, continuous history report and/or STC for current installed equipment.

The Code of Federal Regulations (CFR), Title 14, Aeronautics and Space, listed in this document may not be up to date with the most current regulation. It is the responsibility of the operators to make sure all applicable 14 CFR parts are listed in their operational documents.

The maintenance procedures in this document may be different than those found in the current revision of the Cessna Maintenance Manual for the associated aircraft model. In the event of conflict, use the more restrictive maintenance procedure to accomplish the task.

500CPM-10a-01a

PLACARDING REQUIREMENTS

When relief is taken for an item listed in a MMEL or operator’s MEL, regulations require the operator to placard the item or system as inoperative or missing. The following guidelines are designed to assist operators with placarding inoperative or missing items or systems. Operators may develop alternate procedures for placarding inoperative or missing items or systems.

Placards should be placed above, adjacent to or on the associated / affected control (annunciator, circuit breaker, switch, button, gauge, indicator, knob or light).

Pre-manufactured “INOP” or “INOPERATIVE” placards may be used at the discretion of the operator.

For missing items or systems, the placard should include text which specifies the component that is missing.

If the inoperative item or system is not within view of the flight crew, an additional placard should be placed on the instrument panel in view of the flight crew. The placard should include text which specifies the component that is inoperative.

If the relief for an item or system includes limitations on aircraft operations, an additional placard should be placed on the instrument panel in view of the flight crew. The placard should include text which states the limitation. If the limitation contracts a permanent placard installed in the cockpit as a part of the certified aircraft, the placard should be placed adjacent to the permanent placard. For example, a placard restricting VMO should be placed near the MAX OPERATING SPEED placard. Examples of common limitations on aircraft operations are:

RVSM OPERATIONS ARE PROHIBITED OPERATIONS IN IMC ARE PROHIBITED FLIGHT INTO ICING IS PROHIBITED OPERATIONS AT NIGHT ARE PROHIBITED CARRIAGE OF CABIN OCCUPANTS IS PROHIBITED CARRIAGE OF CARGO (EXCLUDING BALLAST) IS PROHIBITED SINGLE-PILOT OPERATIONS ARE PROHIBITED OPERATIONS ABOVE FL410 ARE PROHIBITED

For indications shown on an electronic display, the placard should be placed adjacent to or on the bezel of the display and should include text which specifies the indication that is inoperative. The placard should NOT be placed on the display as this may obstruct the view of other indications in alternate or reversionary modes. This also applies to specific software functions or items within a system.

Placards installed on equipment used by cabin passengers should include text such as “DO NOT USE” if the item or system is deactivated. For example, a vanity basin with an inoperative drain should include a placard stating, “DO NOT POUR LIQUIDS INTO BASIN”. Make sure the placard can be easily understood by all passengers. Consider any passengers whose primary language is not the same as the placard’s language.

Items or systems which have external access such as a baggage door or refueling panel should include a placard on the exterior side of the door or on the interior side provided it is prominently

500CPM-10a-01a

in view when accessed. The placard should include text specifying the item or system that is inoperative and / or states limitations on aircraft operations.

Placard text should be of appropriate size, font and color so that it can be easily read. Placards placed on the exterior of the aircraft should be made of materials that will not degrade or depart the aircraft, such as aerodynamic tape and permanent marker.

Placarding does NOT satisfy the requirement to make an appropriate entry in the discrepancy report for an inoperative or missing item or system.

500CPM-10a-01a

Regulatory References

When an item’s proviso includes language such as “any in excess of those required by 14 CFR” or “not required by 14 CFR”, the operator is required to replace this reference with the specific operating requirement applicable to their operation. The following table lists 14 CFR references for certain systems. This table may include references for items not installed on this aircraft or which MMEL relief is not offered. This list is based on Appendix A of FAA MMEL Policy Letter 25.

ATA Item Title 14 CFR Reference(s)22 -10-XX Autopilot System App G23 -00-XX SATCOM 135.98, 135.16523 -10-XX High Frequency (HF) Communication

System91.511, 135.98, 135.165

23 -11-XX Ultra High Frequency (UHF) Communication System

91.126, 91.127, 91.129, 91.130, 91.131, 91.135, 91.205, 91.511, 135.161, 135.165

23 -12-XX Very High Frequency (VHF) Communication System

91.126, 91.127, 91.129, 91.130, 91.131, 91.135, 91.205, 91.511, 135.161, 135.165

23 -40-XX Passenger Address (PA) System 135.15023 -50-XX Headsets 91.511, 135.151, 135.16523 -50-XX Microphone 91.511, 135.16523 -70-XX Cockpit Voice Recorder 91.609, 91.1045, 135.15124 -30-XX DC Generator 135.16325 -10-XX Passenger seat shoulder harness 91.20525 -20-XX Under seat restraining bars 91.52325 -20-XX Passenger Briefing Cards 91.519, 91.103525 -20-XX Tables 91.53525 -20-XX Movie Screens (In aisle) 91.53525 -20-XX Observer’s Seat 135.7525 -60-XX Emergency Medical Kit (EMK)25 -60-XX First Aid Kit (FAK) 91.51325 -60-XX Automatic External Defibrillator (AED)25 -60-XX Pyrotechnic Signaling Device 91.205, 91.509, 135.16725 -60-XX Crash Axe25 -61-XX Flotation Device 91.205, 91.509, 135.16725 -62-XX Emergency Locator Transmitter (ELT)

(Fixed, Automatic)91.207

25 -62-XX Emergency Locator Transmitter (ELT) (Survival)

91.207, 91.509, 135.167

25 -64-XX Life Raft 91.509, 135.16726 -22-XX Portable Fire Extinguishers 91.513, 135.15530 -10-XX Anti-Ice System 91.527

500CPM-10a-01a

ATA Item Title 14 CFR Reference(s)30 -30-XX Pitot Heat 135.163, App A30 -40-XX Windshield Wiper App A31 -20-XX Clock 91.20531 -30-XX Flight Data Recorder 91.609, 91.1045, 135.15233 -20-XX Passenger Information Sign 91.51733 -40-XX Wing Illumination Lights 91.52733 -40-XX Anti-Collision Light System 91.205, 91.209, 135.15933 -40-XX Landing Light 91.205, 91.50733 -40-XX Position / Navigation Lights 91.205, 91.20933 -50-XX Flashlight 91.503, 135.15934 -11-XX Static Pressure System 135.163, App A34 -12-XX Free Air Temperature Indicator 135.16334 -13-XX Vertical Speed Indicator 135.163, App A34 -14-XX Airspeed Indicator 91.205, App A,34 -15-XX Overspeed Warning 91.60334 -16-XX Altitude Alerter 91.219, App G34 -16-XX Altimeter 91.20534 -16-XX Sensitive Altimeter 91.205, 135.149, App A34 -17-XX Altitude Measurement Systems App G34 -21-XX Gyro Pitch and Bank 91.205, 135.159, App A34 -22-XX Standby Attitude Indicator 135.14934 -22-XX Magnetic Direction Indicator 91.205, 135.15934 -22-XX Gyro Direction Indicator 91.609, 91.1045,

135.152, 135.15934 -24-XX Gyro Rate of Turn 91.205, 135.15934 -24-XX Slip-Skid Indicator 91.205, 135.15934 -25-XX Flight Director App A34 -31-XX Instrument Landing System (ILS) 135.165, App A34 -34-XX Marker Beacon 135.165, App A34 -42-XX Weather Radar System 91.1045, 135.173,

135.17534 -44-XX Terrain Awareness and Warning System 91.223, 91.1045, 135.15434 -44-XX Radio Altimeter App A34 -45-XX Traffic Alert and Collision Avoidance

System (TCAS)91.221, 91.1045, 135.180

34 -46-XX Thunderstorm Detection System 91.1045, 135.17334 -51-XX Distance Measuring Equipment (DME) 91.205, 135.16534 -52-XX ATC Transponder and Automatic Altitude

Reporting System91.130, 91.131, 91.135, 91.215,

34 -52-XX Automatic Dependent Surveillance-Broadcast

91.130, 91.131, 91.135, 91.225,

34 -52-XX Elementary and Enhanced Downlink Aircraft Reportable Parameters

135.143

34 -52-XX ADS-B Squitter Transmissions 91.227

500CPM-10a-01a

ATA Item Title 14 CFR Reference(s)34 -54-XX Very High Frequency Omnirange (VOR)

System91.131, 91.205, 91.511, 135.161, 135.165

34 -55-XX Automatic Direction Finder (ADF) 91.205, 135.16134 -57-XX

-60-XXLong-Range Navigation System 91.131, 91.205, 91.511,

135.16535 -10-XX Flight Crew Oxygen System 91.211, 135.15735 -20-XX Passenger Oxygen System 91.211, 135.15735 -30-XX Portable Breathing Equipment (PBE)37 -20-XX Vacuum Indicator 135.16371 -60-XX Carburetor Heat 135.14977 Engine Indications 91.205

500CPM-10a-01a

Page Intentionally Left Blank

500CPM-10a-01a

21-00-02-01

Precool SystemPressurized

C 2 1 (M) One may be inoperative provided:a) Affected system is deactivated,b) Pressurization Source Selector

remains on the opposite source, and

c) Flight is conducted at FL250 or below.

Maintenance Procedure

NOTE: The 500 Series airplane has a specific Maintenance Manual for the respective model(s). Refer to the appropriate Cessna Maintenance Manual and/or Interiors Manual for information of the individual aircraft installation.

NOTE: The Flow Control and Shutoff Valves are powered CLOSED and cannot be deactivated without unregulated air entering the system.

Failure mode – Powered, stuck closed:

Position the Pressurization Source Selector to the unaffected source.

Failure mode – Unpowered, stuck closed:

1. Fabricate a 0.020 inch (0.51 mm) thick blocking plate from Type 301, 1/2-hard stainless steel of the applicable diameter.

2. Access the affected Flow Control and Shutoff Valve.3. Install the blocking plate on the inlet side of the Flow Control and Shutoff Valve.4. Reconnect the system.5. Move the airplane to a suitable area to run the engines.6. Start both engines and allow them to stabilize.7. Inspect the valve with the blocking plate for any leaks. Correct any leaks prior to

airplane operations.

500CPM-10a-01a

21-00-02-02

Precool SystemUnpressurized

C 2 0 (O) May be inoperative provided:a) Flow Control Valves are verified

CLOSED,b) Cabin Pressurization Source

Selector remains OFF,c) Flight is conducted

unpressurized,d) Flight planning must consider

the fuel burn and range associated at lower altitudes, and

e) Aircraft is operated at 10,000 feet MSL or below.

Operational Procedure

NARRATIVE

The affected Flow Control and Shutoff valve has failed in the closed position. Failure in the open position will not allow the affected source to be shut off in an emergency situation. To verify the valve is closed, the engine that supplies bleed air to the affected system is started and the PRESS SOURCE switch is turned to that engine. The A/C and OVHD fans must be OFF to verify the airflow in the system is coming from the engine and not from a fan. If airflow is detected, the valve is not closed and must be repaired/replaced prior to flight.

With engines running:

1. Select OVHD fan, DEFOG fan, and A/C (Freon air conditioner) switches to OFF.2. Select temperature control to MANUAL.3. Turn PRESS SOURCE selector to OFF. Absence of airflow (e.g., overhead duct

outlets, armrest manifolds, cabin foot warmer manifolds, cockpit foot warmer outlets) indicates that both valves are closed.

500CPM-10a-01a

21-20-02 Ground Flow Control Valve

C 1 0 (O) May be inoperative provided:a) Ground flow control valve is

verified CLOSED, andb) BLEED AIR GND is not used.


NARRATIVE

The affected Ground Flow Control Valve has failed in the closed position. Failure in the open position will not allow the affected source to be shut off in an emergency situation. To verify the valve is closed, the engine that supplies bleed air to the affected system is started and the PRESS SOURCE switch is turned to that engine. The A/C and OVHD fans must be OFF to verify the airflow in the system is coming from the engine and not from a fan. If airflow is detected, the valve is not closed and must be repaired/replaced prior to flight.




4. Once system is verified CLOSED, place the PRESS SOURCE knob to BOTH and continue operations.

500CPM-10a-01a

21-22-01 Flood Cooling SystemModel 550-0356 & on,S550-0001 thru -0160 and 560-0001 thru -0538. And (550-0019, -0120, -0494, -0497, -0501, -0505)

D 1 0 (M) May be inoperative provided system is deactivated.


Pull and secure the FLOOD circuit breaker.

500CPM-10a-01a

21-33-01-01

Flow Control and Shutoff ValvesUnpressurized

C 2 0 (M) May be inoperative provided:a) Both flow control and shutoff

valves verified closed (no bleed air flow),

b) Flight planning must consider the fuel burn and range associated with flight at lower altitudes,

c) Cabin Pressurization Source Selector remains OFF, and

d) Aircraft is operated at 10,000 feet MSL or below.



NARRATIVE

The affected Flow Control and Shutoff valve has failed in the closed position. Failure in the open position will not allow the affected source to be shut off in an emergency situation. To verify the valve is closed, the engine that supplies bleed air to the affected system is started and the PRESS SOURCE switch is turned to that engine. The A/C and OVHD fans must be OFF to verify the airflow in the system is coming from the engine and not from a fan. If airflow is detected, the valve is not closed and must be repaired/replaced prior to flight.




500CPM-10a-01a

21-33-01-02

Flow Control and Shutoff ValvesPressurized

C 2 1 (M) One may be inoperative provided:a) Failed valve is verified closed

(no bleed air flow),b) Cabin Pressurization Source

Selector is selected to the opposite side, and

c) Flight is conducted at FL250 or below.


NOTE 1: The 500 Series airplane has a specific Maintenance Manual for the respective model(s). Refer to the appropriate Cessna Maintenance Manual and/or Interiors Manual for information of the individual aircraft installation.

NOTE 2: Blanking the system accomplishes the requirement to verify there is no bleed air flow

Position the Pressurization Source Selector to the unaffected source.

1. Fabricate a 0.020 inch (0.51 mm) thick blocking plate from Type 301, 1/2-hard stainless steel of the applicable diameter.

2. Access the affected Flow Control and Shutoff Valve.3. Install the blocking plate on the inlet side of the Flow Control and Shutoff Valve.4. Reconnect the system.5. Move the airplane to a suitable area to run the engines.6. Start both engines and allow them to stabilize.7. Inspect the valve with the blocking plate for any leaks. Correct any leaks prior to

airplane operations.

500CPM-10a-01a

21-33-02 Outflow Valves C 2 0 (M) Both may be inoperative provided:a) At least one valve is removed

from its location,b) Flight planning must consider

the fuel burn and range associated with flight at lower altitudes,

c) Aircraft is operated unpressurized, and

d) Aircraft is operated at 10,000 feet MSL or below.



1. Gain access to the Outflow Valves via both sides of the aft pressure bulkhead.2. From the tailcone side of the aft pressure bulkhead, remove bolts securing either Outflow

Valve to its mount on the forward side of the aft pressure bulkhead.

NOTE: If the outflow valve being removed is the RH valve, we recommend removing the aluminum tube which vents the vacuum ejector overboard through the aft pressure bulkhead, as well as the aluminum tube with the particulate trap which leads from the RH outflow valve to the ejector. Be sure to cap all fittings and plug all lines. It should not be necessary to disturb any of the nylon plumbing.

3. Remove the outflow valve and store/stow.

500CPM-10a-01a

***21-50-02

Freon Air Conditioning System

C 1 0 (M) May be inoperative provided system is deactivated.



Pull and secure the AIR COND circuit breaker.

500CPM-10a-01a

***23-00-01

Radio Management Unit (RMU)

C 2 1 (O) One may be inoperative provide:a) Remaining RMU operates

normally, andb) Auxiliary Com/Nav control

display unit is verified to operate normally.


Prior to each flight a crewmember will use the Auxiliary Com/Nav Control Display Unit to tune at least one com channel and at least one navigational aid, checking for proper reception and transmission.

500CPM-10a-01a

***23-10-01-00B

High Frequency (HF) Communication System(Dual LRCS required)

C - 1 (O) May be inoperative while conducting operations which require two Long-Range Communication Systems (LRCS) provided:

a) Aircraft SATVOICE system operates normally,

b) SATVOICE services are available as a LRCS over intended route of flight,

c) ICAO flight plan is updated, as required, to notify ATC od communications equipment status of aircraft, and

d) Alternate procedures are established and used.


1. Prior to each flight, a crew member shall make sure that SATCOM Data Link and ACARS systems are operational for transmitting and receiving information from a ground station.

2. Prior to each flight, a crew member shall review SATCOM system user’s guide/manual to ensure coverage exists for the intended route of flight.

3. Prior to flight, a crew member shall coordinate with the appropriate ATC facility to advise of intended flight without INMARSAT codes, if codes are not available.

500CPM-10a-01a

***23-10-01-01

High Frequency (HF) Communication SystemWire Antenna

C 1 0 (M) May be inoperative, missing, or damaged provided:

a) Horizontal and vertical stabilizers are inspected for damage,

b) Any remaining portions of wire antenna is removed, and

c) HF communication system is considered inoperative.



1. If the antenna came loose in flight, inspect the aircraft for damage. If damage is found, contact Cessna Customer Support Structures Team for aircraft evaluation.

2. Remove the HF Antenna.3. Bag and stow any loose connectors.4. Cover any openings in the fuselage with aerodynamic tape.

500CPM-10a-01a

***23-10-04-02

Radio Package Cooling Fan(Com/NAV/XSPDR)(550 units 0801 thru 1136)FAN1 FAIL Amber Annunciator

C 1 0 (O) May be inoperative provided Fan 1 and Fan 2 are verified operative.


NOTE: This item is applicable to the Citation Bravo King KY-196A integrated radio package only. The following procedure can be used to verify that either Fan 1 or Fan 2 is operative.

To verify both fans are operative:

Perform Fan 2 operational test.

1. Verify that the 7.5 amp EQUIP COOL circuit breaker in the left circuit breaker panel is engaged.

2. Verify operation of glare shield cooling fan, Instrument cooling fans, and nose compartment fan. The FAN 2 annunciator should be extinguished.

3. Disengage the EQUIP COOL circuit breaker.4. Verify glare shield cooling fan, instrument cooling fans, and nose compartment fan

stop operating. The FAN 2 annunciator should be illuminated.

Perform Boxer Fan Operational Test.

1. Disengage the 5 amp NAV 1 circuit breaker in the right circuit breaker panel.2. Ensure that the NAV 2 circuit breaker is engaged.3. Verify that both of the instrument panel rack mounting assembly boxer fans are not

operating. The FAN 1 annunciator should be illuminated.4. Engage the NAV 1 circuit breaker and verify both boxer fans are operating. The FAN

1 annunciator should be extinguished5. Disengage the NAV 2 circuit breaker and verify both boxer fans remain operational.6. Engage the NAV 2 circuit breaker.7. Disengage the NAV 1 circuit breaker8. Engage the COMM 1 circuit breaker and verify both of the instrument panel rack

mounting assembly boxer fans are not operating.9. Engage the NAV 1 circuit breaker and verify both boxer fans are operating.10. Disengage the COMM 1 circuit breaker and verify both boxer fans remain operational11. Engage the COMM 1 circuit breaker.12. Disengage the NAV 1 circuit breaker.13. Engage the COMM 2 circuit breaker and verify both of the instrument panel rack

mounting assembly boxer fans are not operational.14. Engage the NAV 1 circuit breaker and verify both boxer fans are operational.15. Disengage the COMM 2 circuit breaker and verify both boxer fans remain operational.16. Engage the COMM 2 circuit breaker.

500CPM-10a-01a

***23-20-01-00B

Selective Call (SELCAL)(System or individual channel)(SELCAL required)

C - 0 (O) May be inoperative provided alternate procedures are established and used.


1. Flight crew must advise ATC of inoperative SELCAL, as appropriate.2. Flight crew will monitor the appropriate radios at all times in the absence of SELCAL.

Consideration should be given to the effect of increased fatigue due to this requirement and the possibility of having only one crew member monitor the radios via headset (especially HF) if required for the given flight.

500CPM-10a-01a

24-22-01 Avionics A.C. Power Inverters(All except 560 units -0751 thru -5000)

C 2 1 (M) One may be inoperative provided:a) Affected inverter is deactivated,

andb) Flight is not conducted at night.



NOTE: The following procedure may also be accomplished by a member of the flight crew.

1. Pull and secure the affected inverter circuit breaker.2. Leave inverter in operative inverter switch position.3. With an inoperative inverter and secured CB, AC POWER test is not required and

should not be performed.

NOTE: If AC POWER test is performed, following indications will be displayed in NORM: red ATT FAIL and HDG FAIL on affected side PFD; master warning lights will not illuminate

500CPM-10a-01a

25-00-01 Required Documents Holder(Airworthiness Certificate, Registration, etc.)

D 1 0 (O) May be inoperative or missing provided an alternate means of securing and displaying documents is used.


Place the required documents in a transparent plastic bag and display them in a manner that is visible to the appropriate authorities, crew members, and passengers.

500CPM-10a-01a

25-10-05-01B

Flight Crew SeatArmrest

C 4 0 (M) May be inoperative provided affected armrest is removed.



Using the appropriate seat manual, remove and store the affected armrest(s).

500CPM-10a-01a

25-10-05-03

Flight Crew Seatrecline/Tilt Function

C 2 0 (M) (O) May be inoperative provided:a) Affected seat is secured or failed

in a position that permits normal visibility,

b) Full flight control movement is available, and

c) Crewmember can reach all necessary controls and equipment while restrained.

MAINTENANCE PROCEDURE


Using the appropriate seat manual, secure the seat in the desired position.OPERATIONAL PROCEDURE

1. Prior to flight, a crew member shall occupy the affected seat and fasten the restraining system.

2. Make sure full flight control movement and brake application are available.3. Make sure all necessary controls and equipment can be reached.

500CPM-10a-01a

25-10-05-06

Flight Crew SeatVertical adjustment

C 2 0 (M) (O) May be inoperative provided:a) Affected seat is secured or failed

in a position that permits pilot normal visibility,

b) Full flight control movement is available, and

c) Crewmember can reach all necessary controls and equipment while restrained.



Using the appropriate seat manual, secure the seat in the desired position.OPERATIONAL PROCEDURE

1. Prior to flight, a crew member shall occupy the affected seat and fasten the restraining system.

2. Make sure full flight control movement and brake application are available.3. Make sure all necessary controls and equipment can be reached.

500CPM-10a-01a

25-10-08 Eye Relief Balls C 3 0 (O) May be inoperative or missing provided alternate procedures are established and used for eye position reference.


1. Prior to flight, a crew member will occupy the affected seat and fasten the seat belt and shoulder harnesses to make sure the following conditions are met:

a. Full flight control movement and brake application.b. Access to all necessary controls and equipment.

2. Position the affected seat(s) so the pilot aligns the eyeball locator bracket so that the following sight picture with the bracket is achieved:

a. Eyeball locator base is flat.3. The flange opposite to the affected seat is aligned for a straight edge.

500CPM-10a-01a

***25-20-03

Cabin Curtains D - 0 (M) May be missing, or inoperative provided curtain is secured open.



Secure the affected curtain in the OPEN position. Methods of securing can be, but are not limited to, taping, zip ties, etc.

500CPM-10a-01a

25-20-06-02A

Passenger Seat(Including side-facing seats, folding seats and couches)Seat Controls(Includes recline, headrest, footrest, floor tracking, pedestal tracking, swivel, and other positioning controls)

D - 0 (M) May be inoperative with seat occupied provided seat is secured in taxi, takeoff and landing position.



Using the appropriate seat manual, secure the seat in the full upright position.

500CPM-10a-01a

25-30-01 Refreshment Center Hot Liquid Storage System Heater

D - 0 (M) May be inoperative provided system is deactivated.



1. Access the appropriate junction box.2. Pull and secure the appropriate circuit breaker.

500CPM-10a-01a

***25-30-02

Refreshment Center Microwave / Oven

D - 0 (M) May be inoperative provided system is deactivated.


NOTE: NOTE: The 500 Series airplane has a specific Maintenance Manual for the respective model(s). Refer to the appropriate Cessna Maintenance Manual and/or Interiors Manual for information of the individual aircraft installation.

1. Access the appropriate junction box.2. Pull and secure the appropriate circuit breaker.

500CPM-10a-01a

25-50-01-01B

Baggage Restraint SystemAnchor Plate

C - 0 (M) Individual anchor plates may be damaged provided:

a) Attaching structure is inspected for damage, and

b) Baggage is secured using remaining anchor plates or not carried.



Do an Inspection of the Cargo Latch Plates and Structure:

1. Open the tailcone baggage compartment door2. Remove upholstery panels as necessary to get access to the tailcone baggage

compartment floor.3. Remove aft baggage compartment panels as necessary to get access to the baggage

anchor plates and structure.4. Examine the baggage latch plates and structure for damage, corrosion, cracks, loose

fasteners, correct installation, or failure.5. Identify and indicate the unserviceable baggage latch plates that must not be used.6. Install aft baggage compartment panels.7. Install upholstery panels as necessary.8. Close the tailcone baggage compartment door.

500CPM-10a-01a

25-50-02-00A

Cabin Storage Compartment

C - 0 (M) May be inoperative provided:a) Compartment does not contain

any aircraft system protection devices,

b) Any emergency equipment located in affected compartment is considered inoperative,

c) Affected compartment is not used for storage of any item except for those permanently affixed,

d) Procedures are established and used to secure compartment closed, and

e) Affected compartment is prominently placarded “DO NOT USE”.



CAUTION: Do not use duct tape or other tapes that can contain substances known to cause damage to the furniture finish or leave residues.

Put the cabin storage compartment door in the closed position. Carefully attach sufficient lengths of 3M vinyl tape (or equivalent) across the door.

500CPM-10a-01a

25-50-02-00B

Cabin Storage Compartment

C - 0 (M) May be inoperative provided:a) Affected door is removed,b) Affected compartment is not

used for storage of any item, including those permanently affixed,

c) Cabin occupants are briefed that affected compartment may not be used, and

d) Affected compartment is prominently placarded “DO NOT USE”.



1. Remove the affected door.2. Remove any unsecured equipment/items for all affected locations.3. Store/stow the door to prevent damage.

500CPM-10a-01a

25-50-02-01

Cabin Storage CompartmentShelving

C - 0 (O) May be inoperative provided:a) Any permanently affixed

emergency equipment located on affected shelf is relocated and available for use, and

b) Cabin occupants are briefed on location of relocated equipment.


Prior to dispatch, a member of the flight crew will brief cabin occupants regarding the status of the affected shelf and to temporary location of any relocated items.

500CPM-10a-01a

25-50-02-02

Cabin Storage CompartmentKey Lock

D - 0 (M) May be inoperative in the unlocked position provided door can be secured by other means.


Using caution not to damage the interior finish, secure the affected door closed by using adhesive tape or other medium.

500CPM-10a-01a

25-62-01-02A

Emergency Locator Transmitter (ELT)Fixed, Automatic

A - 0 (M) May be inoperative provided:a) System is deactivated or

removed, andb) Repairs are made within

90 calendar days.Maintenance Procedure


Isolate the ELT Antenna:

1. Disconnect the ELT antenna coaxial connector adapter from the ELT antenna.2. Put protective covers on the coaxial connector plug and jack.3. Stow the coaxial cable.

500CPM-10a-01a

25-62-01-02B

Emergency Locator Transmitter (ELT) Fixed, Automatic

D - - (M) Any in excess of those required by 14 CFR may be inoperative provided system is deactivated or removed.



Isolate the ELT Antenna:

1. Disconnect the ELT antenna coaxial connector adapter from the ELT antenna.2. Put protective covers on the coaxial connector plug and jack.3. Stow the coaxial cable.

500CPM-10a-01a

27-20-01 Rudder Pedal Adjustment System

B 4 2 (M) (O) Two may be inoperative provided:

a) Two pedal adjustments are not inoperative at same pilot station,

b) Affected pedal is positioned in a detent and adjustment mechanism is secured from movement,

c) Unaffected pedal is adjusted to match affected pedal, and

d) Crewmember seated at affected station verifies full control movement and brake application is available while restrained, prior to each flight.



Match the Position and Secure the Rudder Pedals.1. Set and secure the rudder pedal with the unserviceable adjustment mechanism in a

detent position acceptable to the affected flightcrew member.2. Set and secure the rudder pedal with the serviceable adjustment mechanism in the same

detent position.3. Have the flightcrew member operate the rudder pedals through their full range of motion

to make sure that there is full rudder control movement and brake application.OPERATIONAL PROCEDURE

Make sure full flight control movement and brake application are available prior to each flight.

500CPM-10a-01a

27-31-01 Electric Elevator Trim B 1 0 (M) May be inoperative provided:a) Electric elevator trim system is

deactivated,b) Autopilot is considered

inoperative, andc) Aircraft is not operated RVSM.



1. Pull and secure the PITCH TRIM and AUTOPILOT circuit breakers.2. Check the manual trim throughout its travel for smooth operation. The limit marks

adjacent to the trim wheel can be used to confirm this, or a count of the trim wheel revolutions can be used; the wheel should turn approximately three and one quarter revolutions.

500CPM-10a-01a

27-41-01 Trim and Flap Position Indicator Tips (All except 560 units 0751 thru 5000)

C 4 0 (M) May be missing or inoperative provided alternate means of marking pointer is established and used.



Using a method to visually identify the position of the affected trim indicator tip.

Methods can be, but are not limited to, tape, RTV, etc.

500CPM-10a-01a

27-70-01 Control/Gust Lock System(Failed Unlocked)

C 1 0 (O) May be inoperative provided pilot verifies full flight control and throttle movement.


During the flight control check in the Before Taxi checklist, verify both throttles can be moved freely.

500CPM-10a-01a

31-10-01 Low Hydraulic Fluid Amber Annunciator/ Light Failure to Illuminate or Extinguish

C 1 0 (O) May be inoperative provided adequate fluid level is verified before each takeoff.


Before each takeoff, inspect the hydraulic system for proper servicing. Service if required.

500CPM-10a-01a

31-10-02 LO HYD FLOW L/R HYD FLOW LOW LH/RH Amber Annunciator Failure to Illuminate or Extinguish

C 2 1 (O) May be inoperative provided:a) Adequate fluid level is verified

prior to each takeoff, andb) Hydraulic system operation is

verified operative on the affected side,


Before the first flight of the day:

1. Inspect the hydraulic system for proper servicing. Service if required.2. If needed, tow the airplane to an area adequate to start the engine on the affected

side.3. Once the engine is started and stabilized, cycle/operate the following systems to verify

that the hydraulic system on the side with the inoperative annunciator is functional:a. speed brakes,b. thrust reverser on operating engine, andc. flaps.

Any abnormalities in operation indicate that the problem goes beyond mere indication fault, and must be resolved.

Before each takeoff:

Inspect the hydraulic system for proper servicing. Service if required.

500CPM-10a-01a

31-10-04 Nose Baggage Doors Amber Annunciator System Fails to Illuminate/Display (550 units -0801 thru 1136, 560 units -0260 thru -5000)

C 2 0 (O) May be inoperative provided affected door(s) are verified closed, latched and locked prior to each takeoff.


Prior to each departure, a crew member will visually inspect each door affected by the failed annunciator, ensuring that latches are secured, and key locks are locked.

500CPM-10a-01a

31-10-05 Aft Baggage or Tailcone Door Amber Annunciator System Fails to Illuminate/Display (550 units -0801 thru -1136, 560 units -0260 thru -5000)

C 1 0 (O) May be inoperative provided affected door is verified closed, latched and locked prior to each takeoff.


Prior to each departure, a crew member will visually inspect each door affected by the failed annunciator, ensuring that latches are secured, and key locks are locked.

500CPM-10a-01a

31-10-06-01

DOOR SEAL Amber Annunciator System Fails to Illuminate/Display (550 units -0801 thru -1136, 560)Pressurized

C 1 0 (O) May be inoperative provided:a) Primary door seal is verified

operative, andb) Flight is conducted at FL250 or

below.


1. Position aircraft in a suitable run-up area.2. Close and latch the cabin door.3. Using AFM Normal Procedures, start the engines and advance power to 60% N1.4. One crewmember shall gain access to the door seal through the protective cover and

verify that the doors seal is inflated.5. Place PRESSURIZATION SYSTEM SELECT switch to AUTO and ensure cabin is

fully depressurized.6. Using AFM Normal Procedures, power down aircraft.

500CPM-10a-01a

31-10-07 Cabin Door Amber Annunciator System Fails to Illuminate/Display (550 units -0801 thru -1136, 560 units -0260 thru -5000)

B 1 0 (O) May be inoperative provided:a) All door lock flags are visible in

the sight glass locations on the door, and

b) Interior door handle securing pin is verified engaged (unable to rotate handle without depressing push button).


1. Once the airplane is fully boarded, a member of the flight crew will close, latch and lock the cabin door.

2. Visually verify:a. Cabin door handle cannot be rotated without depressing the push button.b. All door flags are visible through the sight glass.

500CPM-10a-01a

31-10-011 Pitot/Static Heater Off Annunciators

B - 0 (O) May be inoperative provided:a) All other components of the Pitot

Heat system are verified operative before each takeoff, and

b) Aircraft is not operated in known, forecast, or AFM-defined icing conditions.


During the Exterior Inspection, a member of the flight crew will activate the pitot static heaters to make sure they are heating.

500CPM-10a-01a

31-20-02 Flight Hour Meter C 1 0 (O) May be inoperative provided flight time is tracked by other means.


NOTE: Use UTC and/or local time zones.

Record airplane operating times from takeoff to landings (except touch-and-go). At the end of airplane operations, record the total flight time in the Aircraft Log.

500CPM-10a-01a

***33-10-02-00A

Windshield Ice Detection System (Glareshield Mounted) Stalk Lights

C 2 1 (O) One may be inoperative provided:a) Aircraft is operated with two

pilots, andb) Alternate procedures are

established and used to monitor ice accretion.


Using a method of illumination that prevents deterioration of night vision:

During night operations in known or forecast icing conditions or if icing is suspected, a member of the flight crewmember with the affected light should inspect the windscreen for icing.

If icing is found or if conditions require additional monitoring area; every thirty (30) minutes inspect the affected area until the condition is clear.

500CPM-10a-01a

33-20-01-00A

Cabin Interior Lighting(Excluding cabin emergency lighting)

C - - (O) Individual lights may be inoperative provided:

a) Sufficient lighting is operative for crew to perform required duties,

b) Cabin emergency lighting is verified operative, and

c) Sufficient lighting is operative for carrying cabin occupants at night.


1. Disconnect main ship battery.2. Position the Passenger Safety Switch on the pilot’s instrument panel to PASSENGER

SAFETY.3. The following lights should illuminate:

a. Cabin entry doorb. Emergency exit door floodlights

4. Select Passenger Safety Switch to OFF.5. Reconnect main battery.

500CPM-10a-01a

33-20-01-00B

Cabin Interior Lighting(Excluding cabin emergency lighting)

D - 0 (O) May be inoperative provided:a) Cabin emergency lighting is

verified operative, andb) Aircraft is not operated at night

or cabin occupants are not carried.


1. Disconnect main ship battery.2. Position the Passenger Safety Switch on the pilot’s instrument panel to PASSENGER

SAFETY.3. The following lights should illuminate:

a. Cabin entry doorb. Emergency exit door floodlights

4. Select Passenger Safety Switch to OFF.5. Reconnect main battery.

500CPM-10a-01a

33-20-02-00A

Lighted Passenger Information Sign(Excluding cabin exit signs)(With cabin occupants)

C - 0 (O) May be inoperative provided alternate procedures are established and used to notify cabin occupants.


A crew member will use the PA system or turn and face the cabin occupants to make appropriate announcements.

500CPM-10a-01a

34-25-07 Flight Director Mode Selector Annunciations

C - 0 (O) May be inoperative provided:a) Corresponding mode function

displays on PFD/MFD, andb) Crew verifies mode displayed is

appropriate to that selected.Operational Procedure

During airplane operation, when a flight director mode is selected, a crewmember will visually verify the respective mode annunciation is displayed on a PFD or EADI.

500CPM-10a-01a

34-36-01***

Reactive Windshear System(Includes TAWS windshear mode)

C 1 0 (O) May be inoperative provided alternate procedures are established and used.


Crew briefings must include escape procedures for a windshear encounter and alternate methods used for monitoring for windshear encounters.

500CPM-10a-01a

***34-44-02

Terrain Awareness and Warning System (TAWS) (Including test mode) (Class A or B TAWS not required)

C 1 0 (O) May be inoperative provided alternate procedures are established and used.

NOTE: Any mode that operates normally may be used.


Crew briefings must include aural callouts through use of appropriate aircraft equipment to ensure obstacle and terrain clearance.

500CPM-10a-01a

34-44-02 Terrain Awareness and Warning System (TAWS) (Including test mode) (Class A or B TAWS required)

A 1 0 (O) May be inoperative provided:a) Alternate procedures are

established and used, andb) Repairs are made within two

flight days.Operational Procedure


500CPM-10a-01a

34-44-02-01

Terrain Awareness and Warning System (TAWS) (Including test mode) (Class A or B TAWS required)Forward Looking Terrain Avoidance Function and Premature Descent Alert Function

B 2 0 (O) May be inoperative provided alternate procedures are established and used.



500CPM-10a-01a

34-44-02-02

Terrain Awareness and Warning System (TAWS) (Including test mode) (Class A or B TAWS required)Excessive Rate of Descent (Mode 1)andAltitude Loss After Takeoff or Missed Approach (Mode 3)

A 2 0 (O) May be inoperative provided:a) Alternate procedures are

established and used, andb) Repairs are made within two

flight days.



500CPM-10a-01a

34-44-02-03A

Terrain Awareness and Warning System (TAWS) (Including test mode) (Class A or B TAWS required)Voice Callouts(Mode 6)("Five-Hundred")

B 1 0 (O) May be inoperative provided alternate procedures are established and used.


Crew briefings must include aural callouts during approach through the use of appropriate aircraft equipment to ensure obstacle and terrain clearance. Briefing must include a procedure for a crew member to call out 500 feet above airport elevation.

500CPM-10a-01a

34-44-02-03B

Terrain Awareness and Warning System (TAWS) (Including test mode) (Class A or B TAWS required)Voice Callouts(Mode 6)(Other)



Crew briefings must include aural callouts during approach through the use of appropriate aircraft equipment to ensure obstacle and terrain clearance. Briefing must include MDA or DH and a procedure for a crew member to call out 500 feet above airport elevation, plus any other agreed upon by the flight crew.

500CPM-10a-01a

***34-45-01-00A

Traffic Alert and Collision Avoidance System(TCAS I or TCAS II)(TCAS not required)

C 1 0 (M) May be inoperative provided:a) System is deactivated,b) System is not required by 14

CFR, andc) Enroute or approach procedures

do not require its use.Maintenance Procedure


Locate, Pull, and secure the TCAS circuit breaker.

500CPM-10a-01a

***34-45-01-00B

Traffic Alert and Collision Avoidance System(TCAS I or TCAS II)(TCAS required)

B 1 0 (M) May be inoperative provided:a) System is deactivated, andb) Enroute or approach procedures

do not require its use.



Locate, Pull, and secure the TCAS circuit breaker.

500CPM-10a-01a

***34-45-01-01

Traffic Alert and Collision Avoidance System(TCAS I or TCAS II)Traffic Advisory (TA) Display(TCAS II only)

C - 0 (O) May be inoperative provided:a) Resolution Advisory (RA) display

and audio function are operative, and

b) Enroute or approach procedures do not require its use.


During the before taxi avionics check, verify the PFD shows a Resolution Advisory along with the aural warning when the TCAS is tested.

500CPM-10a-01a

***34-45-01-02B

Traffic Alert and Collision Avoidance System(TCAS I or TCAS II)Resolution Advisory (RA) Display(TCAS II only)

C 2 0 (O) May be inoperative provided:a) Traffic Alert (TA) visual display

and audio function are operative,b) TA-only mode is selected by

flight crew, andc) Enroute or approach procedures

do not require its use.Operational Procedure

During the Before Taxi: Avionics check, verify the MFD shows a Traffic Alert along with the aural warning when the TCAS is tested.

500CPM-10a-01a

34-58-01***

Automatic Dependent Surveillance-Broadcast (ADS-B) System

C - 0 (O) May be inoperative provided:a) Alternate procedures are

established and used, andb) It is not required by 14 CFR.

NOTE: Any ADS-B function that operates normally may be used.


Prior to takeoff, perform the TCAS self-test. Make sure the TA display appears on the appropriate displays and the aural alerts sound.

500CPM-10a-01a

34-58-01***

Automatic Dependent Surveillance-Broadcast (ADS-B) SystemADS-B Out Extended Squitter Transmissions


established and used,b) Authorization is obtained from

ATC facilities having jurisdiction over planned route of flight, and

c) It is not required by 14 CFR.




500CPM-10a-01a

34-58-01***

Automatic Dependent Surveillance-Broadcast (ADS-B) SystemADS-B Out UAT Transmissions


established and used,b) Authorization is obtained from

ATC facilities having jurisdiction over planned route of flight, and

c) It is not required by 14 CFR.




500CPM-10a-01a

34-58-01***

Automatic Dependent Surveillance-Broadcast (ADS-B) SystemADS-B In Transmissions





500CPM-10a-01a

35-00-01-01

Oxygen SystemFill Port

C 1 0 (M) May be inoperative provided bottle is filled using alternate means, if service is required.


If airplane is operated unpressurized, oxygen system is not required to be serviced.

NOTE: The 500 Series airplane has a specific Maintenance Manual for the respective model(s). Refer to the appropriate Cessna Maintenance Manual and/or Interiors Manual for information of the individual aircraft installation.Nose-Mounted Installations:

Open the right nose door and remove the access panel to gain access to the oxygen cylinder.1. Cut safety wire and position the oxygen cylinder shutoff valve to OFF.2. Disconnect and cap the line from the back side of the oxygen filler port to the oxygen

cylinder at the neck of the cylinder slowly to allow trapped air to escape.3. Place additional maintenance personnel inside the cockpit to monitor the oxygen

pressure gauge.4. Connect oxygen supply to the oxygen cylinder, position the oxygen cylinder shutoff

valve to OPEN and slowly fill the cylinder.5. When the desired pressure has been obtained, position the oxygen cylinder shutoff

valve to OFF. Turn off the oxygen supply and disconnect the supply line.6. Clean old Teflon tape from oxygen cylinder fitting and apply new tape.7. Uncap and reconnect the oxygen filler port line to the neck of the oxygen cylinder.8. Position the oxygen cylinder shutoff valve to ON and safety wire shutoff valve. Refer to

Maintenance Manual Chapter 20, Safetying – Maintenance Practices.9. Install access panel.10. Close and secure nose baggage door.11. Place an “INOP” placard adjacent to filler port.12. Make appropriate entry in discrepancy report.

Tail-Mounted Installations:

1. Remove tailcone access panel to gain access to oxygen cylinder.2. Cut safety wire and position the oxygen cylinder shutoff valve to OFF.3. Disconnect and cap the line from the back side of the oxygen filler port to the oxygen

cylinder at the neck of the cylinder slowly to allow trapped air to escape.4. Place additional maintenance personnel inside the cockpit to monitor the oxygen

pressure gauge.5. Connect oxygen supply to the oxygen cylinder, position the oxygen cylinder shutoff

valve to OPEN and slowly fill the cylinder.6. When the desired pressure has been obtained, position the oxygen cylinder shutoff

valve to OFF. Turn off the oxygen supply and disconnect the supply line.7. Clean old Teflon tape from oxygen cylinder fitting and apply new tape. 8. Uncap and reconnect the oxygen filler port line to the neck of the oxygen cylinder.9. Position the oxygen cylinder shutoff valve to ON and safety wire shutoff valve. Refer to

Maintenance Manual Chapter 20, Safetying – Maintenance Practices.10. Install access panel.

500CPM-10a-01a

35-00-01-02

Oxygen SystemBlowout Disk/Green Label

C 1 0 (O) May be missing or damaged provided oxygen pressure is verified prior to each flight.


Verify adequate servicing of oxygen system if system is required for flight. If airplane is operated unpressurized, oxygen system is not required to be serviced.

500CPM-10a-01a

35-20-01-01

Passenger Oxygen SystemMask

C - 0 (M) Individual oxygen masks or dispensers may be inoperative or missing provided:

a) Affected mask pintle pin is installed, and

b) Associated seat or lavatory is placarded "DO NOT OCCUPY".



Passenger oxygen mask pintle pin must be installed to prevent oxygen loss from removed mask(s).

500CPM-10a-01a

35-20-01-02

Passenger Oxygen SystemDrop-out Panel

C - 0 (M) Individual panels may be out of normal position provided:

a) Affected oxygen mask and drop out panel are removed,

b) Affected mask pintle pin is installed, and

c) Associated seat or lavatory is placarded "DO NOT OCCUPY".



1. Refer to Chapter 35-20 Passenger Oxygen System for oxygen mask removal.2. Passenger oxygen mask pintle pin must be installed to prevent oxygen loss from

removed mask(s).3. If desired, tape of other material may be used to cover the affected area for aesthetic

purposes.

500CPM-10a-01a

38-10-01-00A

Potable Water System C - - (M) Individual components may be inoperative provided:

a) Associated components are deactivated or isolated, and

b) Associated system components are verified not to have leaks.

NOTE: Any portion of the system that works normally may be used.



NOTE: Potable water systems in the 500-Series Citations include, but are not limited to: Water tanks in the upper aft vanity plumbed and gravity-fed to a wash basin, Water tanks with spigots in the refreshment centers, Water tanks (optional on 500’s and 550’s) mounted in part of the forward partition, using an electric pump to feed a wash basin, installed in conjunction with the optional forward lavatory installation.

For Aft Vanity Water Storage Tank:1. Remove access panels from upper vanity as needed to access tank.2. On most installations, turn the two fasteners at the top of the tank and depress the collar on the

quick disconnect water line connection to release the tank.3. Inspect tank and plumbing for leaks and dampness.4. Drain tank, and put in place without reconnecting plumbing.5. Reinstall access panels.

For Refreshment Center Liquid Storage Tanks:1. Remove access panels from Refreshment Center as needed to access tank.2. Slide tank out of its compartment, disconnect and cap any electrical connectors.3. Inspect tank and plumbing for leaks and dampness.4. Drain tank, and remove any plumbing lines.5. Replace tank without reconnecting any removed electrical or plumbing connections.6. Reinstall access panels.

For wash basin water tank installed with forward toilet (early 500 and 550):

To isolate pump and check for leaks:1. Carefully pull wash basin switch from the front of the sink cabinet.2. Disassemble wire spice for the 28-volt power source.3. Insulate and tag wire end.4. Reinstall switch.5. Remove drawers beneath sink.6. Inspect tank and plumbing for leaks and dampness.

To drain system:1. Remove drawers beneath sink to gain access to plumbing.2. Take precautions to catch any spilled water. Remove water line from pump. Drain tank into

suitable container.

500CPM-10a-01a

38-10-01-00B

Potable Water System C - - (M) May be inoperative provided:a) System is drained, andb) System is not serviced.



1. Drain all liquids from the affected system.2. Inspect for leaks. If leaks are found, adequately clean and dry the affected areas.

500CPM-10a-01a

38-30-01 Lavatory Waste System

C - - (M) Individual components may be inoperative provided:

a) Associated components are deactivated or isolated, and

b) Associated system components are verified not to have leaks.

NOTE: Any portion of the system that works normally may be used.



For flushing toilet:

1. Lift seat assembly or remove access cover to gain access to wiring. 2. Disconnect ship wiring from toilet. Cap, bag and stow any loose wiring.3. Visually inspect tank and reservoir for any leaks. Address any leaks prior to flight.

For non-flushing toilet:

1. Visually inspect tank and reservoir for any leaks. Address any leaks prior to flight.

If leaks are found in flushing or non-flushing toilet, do not re-service.

500CPM-10a-01a

***46-00-03-00B

Electronic Flight Bag System (EFB)Class 3 EFB(Includes IFIS)

C - 0 (O) May be inoperative provided alternate procedures are used.

NOTE: Any function, program, or document which operates normally may be used.


NOTE: Subscription based products such as SafeTaxi or any other product that provides aircraft data (displayed on the airplane displays) the airplane operator has not purchased or maintained do not put the equipment in an “Inoperative” condition.

Appropriate and current navigational publications for route of flight and alternates must be carried onboard.

500CPM-10a-01a

***46-00-03-01B

Electronic Flight Bag System (EFB)Data Connectivity(Class 2)



Appropriate and current navigational publications for route of flight and alternates must be carried onboard.

500CPM-10a-01a

***46-00-03-02B

Electronic Flight Bag System (EFB)Power Connection(Class 1 & 2)



Each affected EFB should have adequate power for the intended flight. Additional batteries or a supplemental power supply may be used to provide necessary power requirements for the flight. Current and appropriate paper products for the intended flight may be used if adequate power requirements cannot be met.

500CPM-10a-01a

***46-00-03-03A

Electronic Flight Bag System (EFB)Mounting Device(Class 2)

D - 0 (M) May be inoperative provided:a) Associated EFB and hardware is

secured by alternate means or removed from aircraft, and

b) Procedures do not require its use.



Remove the EFB.1. Remove the EFB from the mounting device.

(a) Remove the EFB from the airplane or stow it in a location where it will not be mistaken for a serviceable EFB.

2. Remove the manufacturer-supplied hardware that attaches the mounting device to the airplane.

3. Remove the mounting device from the airplane.4. If supplied, stow or remove related electrical wiring.

500CPM-10a-01a

***46-00-03-03B

Electronic Flight Bag System (EFB)Mounting Device(Class 2)

C - 0 (M) (O) May be inoperative provided:a) Associated EFB and hardware is

secured by alternate means or removed from aircraft, and

b) Alternate procedures are established and used.



Remove the EFB.1. Remove the EFB from the mounting device.

(a) Remove the EFB from the airplane or stow it in a location where it will not be mistaken for a serviceable EFB.

2. Remove the manufacturer-supplied hardware that attaches the mounting device to the airplane.

3. Remove the mounting device from the airplane.4. If supplied, stow or remove related electrical wiring.Operational Procedure

1. The affected flight crew member(s) will determine an adequate storage location for the EFB(s) prior to flight.

2. The flight crew will brief on alternate EFB usage for the intended flight.

500CPM-10a-01a

52-10-02 Cabin Door Seal(500/501, S550, 551, 550 units -0001 thru -0733)

C 1 0 (O) May be inoperative or sections missing provided:

a) Door seal does not interfere with door operation, and

b) Pressurization is considered inoperative.


NOTE: missing cabin door seal material may cause aircraft operating noises in the cabin to be louder than normal.

During door actuation, make sure no section or part of the cabin door seal prevents the cabin door from closing and properly latching/locking.

500CPM-10a-01a

52-10-03-00A

Cabin Door Secondary Seal(550 units -0801 thru -1136, 560)


a) Secondary seal does not interfere with door operation,

b) Primary seal is operative, andc) Flight is conducted at FL 250 or

below.Operational Procedure



500CPM-10a-01a

52-10-03-00B

Cabin Door Secondary Seal(550 units -0801 thru -1136, 560)


a) Secondary door seal does not interfere with door operation, and





500CPM-10a-01a

52-10-04-00A

Cabin Door Primary Seal(550 units -0801 thru 1136, 560)


a) Primary seal does not interfere with door operation,

b) Secondary seal is operative, andc) Flight is conducted at FL 250 or

below.Operational Procedure



500CPM-10a-01a

52-10-04-00B

Cabin Door Primary Seal(550 units -0801 thru 1136, 560)


a) Primary door seal does not interfere with door operation, and





500CPM-10a-01a

52-30-02 Aft Baggage/Tailcone Door Key Lock

D 1 0 (O) May be inoperative in the unlocked position provided the door is verified closed and latched prior to each takeoff.


Prior to each flight, a crew member must make sure the affected door(s) is closed and latched.

500CPM-10a-01a

***52-46-01

Single Point Refueling Door Key Lock

D 1 0 (O) May be inoperative provided door is verified closed and latched.


Prior to each flight, a crew member must make sure the single point refueling door is closed and latched.

500CPM-10a-01a

***52-60-01-02

Entry Step Support ComponentsCables/Chains

C - 0 (O) May be inoperative provided:a) Cables/chains do not interfere

with door operation,b) Alternate procedures are used

for safe entry/egress.Operational Procedure

NOTE: Inoperative door step cables/chains will cause the door steps to be unsupported and prevent the steps from bearing weight. Extreme caution should be taken to make sure airplane occupants do not use the door steps to prevent injury and damage to the step assembly/door structure.

NOTE: Damage to the cabin door/door structure can occur from unrestricted cables/chains.

1. Unless supporting personnel are briefed on the condition of the door step, a flightcrew member should perform all cabin door/door step actuations.

2. Use caution to make sure the cabin steps do not move unrestricted to prevent injury or damage.

3. A portable step stool or other appropriate device adequate to support load bearing should be used to assist in the ingress/egress of the airplane.

4. Prior to closing the cabin door, make sure all cables/chains are positioned not to interfere with door operation.

5. Prior to starting engines, make sure any loose equipment used to assist in airplane entry/exit are properly secured/stowed/stored.

500CPM-10a-01a

***78-30-00

Thrust Reverser C 2 0 (M) May be inoperative provided affected reverser is disabled using the Maintenance Manual procedure.



One or both thrust reversers may be electrically and/or hydraulically deactivated and secured. Refer to the most current revision to the Textron Aviation Model 500 Maintenance Manual Chapter 78, Exhaust, Maintenance practice(s)

500CPM-10a-01a

VOLUME 8 CABIN ALTITUDE vs. CABIN PRESSURE DIFFERENTIAL CONVERSION (PSID)

(Cabin Pressure Differential Display or Cabin Altimeter Inoperative)

AIRCRAFT PRESSURE ALTITUDE ´ 1000'

CA

BIN

ALT

ITU

DE

x 10

00'

x 1000' 0 5 10 15 20 25 28 31 33 35 37 39 41 43 45 47 49 5111.0 1.4 3.0 4.3 4.9 5.6 5.9 6.3 6.6 6.9 7.1 7.4 7.6 7.8 8.0 8.110.5 1.6 3.2 4.5 5.1 5.7 6.1 6.4 6.8 7.1 7.3 7.5 7.8 8.0 8.1 8.310.0 0.0 1.8 3.4 4.7 5.3 5.9 6.3 6.6 7.0 7.3 7.5 7.7 8.0 8.2 8.3 8.59.5 0.2 2.0 3.6 4.9 5.5 6.1 6.5 6.8 7.2 7.5 7.7 7.9 8.2 8.4 8.5 8.79.0 0.4 2.2 3.8 5.1 5.7 6.3 6.7 7.0 7.4 7.7 7.9 8.1 8.4 8.6 8.7 8.98.5 0.6 2.4 4.0 5.3 5.9 6.5 6.9 7.2 7.6 7.9 8.1 8.3 8.6 8.8 8.9 9.18.0 0.8 2.6 4.2 5.5 6.1 6.7 7.1 7.5 7.8 8.1 8.3 8.6 8.8 9.0 9.2 9.37.5 1.0 2.8 4.4 5.7 6.4 7.0 7.3 7.7 8.0 8.3 8.5 8.8 9.0 9.2 9.4 9.57.0 1.2 3.0 4.6 5.9 6.6 7.2 7.5 7.9 8.2 8.5 8.7 9.0 9.2 9.4 9.6 9.76.5 1.5 3.3 4.8 6.1 6.8 7.4 7.8 8.1 8.4 8.7 9.0 9.2 9.4 9.6 9.8 10.06.0 1.7 3.5 5.0 6.3 7.0 7.6 8.0 8.3 8.6 8.9 9.2 9.4 9.6 9.8 10.05.5 1.9 3.7 5.2 6.5 7.2 7.8 8.2 8.5 8.9 9.1 9.4 9.6 9.9 10.15.0 0.0 2.1 3.9 5.5 6.8 7.5 8.1 8.4 8.8 9.1 9.4 9.6 9.9 10.14.5 0.2 2.4 4.2 5.7 7.0 7.7 8.3 8.7 9.0 9.3 9.6 9.9 10.14.0 0.5 2.6 4.4 5.9 7.2 7.9 8.5 8.9 9.2 9.5 9.8 10.13.5 0.7 2.8 4.6 6.2 7.5 8.2 8.8 9.1 9.5 9.8 10.13.0 0.9 3.1 4.9 6.4 7.7 8.4 9.0 9.4 9.7 10.02.5 1.2 3.3 5.1 6.7 8.0 8.6 9.2 9.6 10.02.0 1.4 3.6 5.4 6.9 8.2 8.9 9.5 9.9 10.21.5 1.7 3.8 5.6 7.2 8.5 9.1 9.8 10.11.0 1.9 4.1 5.9 7.4 8.7 9.4 10.00.5 2.2 4.3 6.1 7.7 9.0 9.70.0 0.0 2.5 4.6 6.4 7.9 9.2 9.9-0.5 0.3 2.7 4.9 6.7 8.2 9.5 10.2-1.0 0.5 3.0 5.1 6.9 8.5 9.8 10.5

*Data in this chart has been calculated using data found in the following document: U.S. STANDARD ATMOSPHERE, 1976 (NASA-TM-X-74335). Published by the National Aeronautics and Space Administration.

EXAMPLE: Aircraft is at FL 350 and Cabin Pressure Differential Gauge reads 8.8 psid, Cabin Altitude is 5,000'.

EXAMPLE: Aircraft Is at FL 350 and Cabin Altimeter reads 5,000', Cabin Pressure Differential is 8.8 psid.

500CPM-10a-01a