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CessnaOperational &MaintenanceProcedures

Cessna Aircraft Company680A (Citation Latitude)

THIS GUIDE IS CURRENT WITH THE MASTER MINIMUM EQUIPMENT LIST WHICH IS DISTRIBUTED BY THE DEPARTMENT OF TRANSPORTATION FEDERAL AVIATION ADMINISTRATION - REVISION 01 DATED

08/01/2018.

COPYRIGHT © 2018 MMEL REVISION 01CESSNA AIRCRAFT COMPANYWICHITA, KANSAS, U.S.A.

COMP REVISION 06

68ACOMP-01-06

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.

68ACOMP-01-06 1

14 CFR 91 operators must have the following statement included in their COMPs Manual or operator produced Procedures Guide. All other operators must remove or delete the following statement.

THIS DOCUMENT IS APPLICABLE TO PART 91 OPERATIONS ONLY AND MAY NOT BE USED FOR OPERATIONS CONDUCTED

UNDER PARTS 121, 125, 129, OR 135.

68ACOMP-01-06 2

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.

68ACOMP-01-06 3

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

68ACOMP-01-06 4

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 such as a Flight Management System (FMS) Navigation Database.

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 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.

68ACOMP-01-06 5

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.

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

System 91.511, 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

68ACOMP-01-06 6

ATA Item Title 14 CFR Reference(s)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 91.52730 -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, 135.159 34 -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,

68ACOMP-01-06 7

ATA Item Title 14 CFR Reference(s)34 -52-XX Automatic Dependent Surveillance-

Broadcast91.130, 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 91.22734 -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

68ACOMP-01-06 8

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68ACOMP-01-06 9

21-21-04-01 Recirculation Shutoff Valve

C/1/0

(M) May be inoperative provided valve is secured in the closed position.MAINTENANCE PROCEDURE

Secure valve in the closed position.

1) Remove locking pin from its stowed position.2) Using a .50 in. wrench, rotate valve to the closed position.3) Install the locking pin into the LOCKED CLOSED position.

21-30-01 Cabin Dump Function(Unpressurized)

C/1/0

(M) May be inoperative provided:a) Outflow valve is removed, anda) Cabin pressurization system is considered inoperative (Refer to item 21-30-

02).MAINTENANCE PROCEDURE

Refer to 680A Maintenance Manual Chapter 21, Air Conditioning - Dispatch Deviation.

68ACOMP-01-06 10

21-30-02-00A Cabin Pressurization System(Unpressurized with cabin occupants)

C/1/0

(O) May be inoperative provided:a) PRESSURIZATION AUTO/MAN is selected to MANUAL,b) CABIN DUMP is selected to DUMP,c) Aircraft is operated at 13,500 feet cabin altitude or below, andd) Flight crew oxygen system is used as required by 14 CFR.

NOTE: Amber CABIN ALTITUDE CAS message may appear at 8,500 feet cabin altitude. CABIN ALTITUDE red message may appear and CABIN ALTITUDE aural warning may sound at 9,650 feet cabin altitude.

OPERATIONAL PROCEDURE

1. Flight planning must consider the fuel burn and range associated with flight at lower altitudes.

2. Minimum enroute altitudes must be taken into account for the planned route.3. Passengers must be briefed prior to each flight that cabin pressurization will be

unavailable. Any medical complications or concerns must be considered in determination of the enroute altitude.

4. Portable or therapeutic oxygen may be used as needed for passenger comfort.5. Cabin pressure must be monitored throughout the flight.

21-30-02-00B Cabin Pressurization System(Unpressurized without cabin occupants)

C/1/0

(M) (O) May be inoperative provided:a) PRESSURIZATION AUTO/MAN is selected to MANUAL,b) Emergency pressurization system is deactivated,c) CABIN DUMP is selected to DUMP,d) PASS OXY is selected OFF,e) No cabin occupants are carried,f) Aircraft is operated at FL250 or below, andg) Flight crew oxygen system is used as required by 14 CFR.

NOTE: Amber CABIN ALTITUDE message may appear at 8,500 feet cabin altitude. CABIN ALTITUDE red message may appear and CABIN ALTITUDE aural warning may sound at 9,650 feet cabin altitude.

MAINTENANCE PROCEDURE

Pull and secure the EMER PRESSURE circuit breaker on the copilot’s circuit breaker panel. OPERATIONAL PROCEDURE

1. Flight planning must consider the fuel burn and range associated with flight at lower altitudes.

2. Minimum enroute altitudes must be taken into account for the planned route.3. Cabin pressure must be monitored throughout the flight.

68ACOMP-01-06 11

21-30-03 Emergency Pressurization System(Failed closed)

C/1/0

(M) May be inoperative provided:a) Emergency pressurization valve is secured closed,b) Aircraft is operated at FL250 or below.


Verify the emergency pressurization valve is closed.

1. Pull and collar EMER PRESSURE circuit breaker on copilot’s circuit breaker panel.

2. Using the Airplane Flight Manual, start both engines.3. Select PRESS SOURCE to EMER.4. Verify no airflow exists from the cabin floor ducting.5. Select PRESS SOURCE to NORM.

21-32-01-00A Cabin Altitude Gauge/Indication(Pressurized)

C/1/0

(O) May be inoperative provided:a) Cabin pressurization system automatic schedule mode is operative,b) Cabin differential pressure gauge/indication is operative, andc) A chart is provided to convert differential pressure and aircraft altitude to cabin

altitude.OPERATIONAL PROCEDURE

Use the chart in Appendix A to convert differential pressure and aircraft altitude to cabin altitude.

21-32-02-00A Cabin Differential Pressure Gauge/Indication(Pressurized)

C/1/0

(O) May be inoperative provided:a) Cabin altitude gauge/indication is operative,b) Cabin pressurization system automatic schedule mode is operative, andc) A chart is provided to convert cabin and aircraft altitude to differential pressure.


Use the chart in Appendix A to convert cabin and aircraft altitude to differential pressure.

68ACOMP-01-06 12

21-33-01 Cabin Outflow Valve

C/2/0

(M) May be inoperative provided:a) Outflow valve is secured open, andb) Cabin pressurization system is considered inoperative (Refer to item 21-30-

02).MAINTENANCE PROCEDURE


21-33-02-00A Pressure Regulating Valve(Mass Flow Control Valve)(Pressurized)

C/2/1

(M) One may be inoperative provided:a) Affected mass flow control valve is secured for no flow,b) PRESS SOURCE is selected to operative source, andc) Aircraft is operated at FL410 or below.

NOTE: Amber PRESS SRC NOT NORM message may appear.MAINTENANCE PROCEDURE


21-33-02-00B Pressure Regulating Valve(Mass Flow Control Valve)(Unpressurized)

C/2/0

(M) May be inoperative provided:a) Both mass flow control valves are secured for no flow,b) PRESS SOURCE is selected OFF,c) BAG HEAT is selected OFF,d) Cockpit and cabin temperature control systems are considered inoperative

(Refer to item 21-60-01), ande) Cabin pressurization system is considered inoperative (Refer to item 21-30-

02).

NOTE: Amber PRESS SRC NOT NORM message may appear.MAINTENANCE PROCEDURE


68ACOMP-01-06 13

21-50-01 Air Cycle Machine

C/1/0

(O) May be inoperative provided:a) PRESS SOURCE is selected OFF,b) APU BLEED AIR is selected OFF,c) Both mass flow valves are verified closed,d) Cockpit and cabin temperature control systems are considered inoperative

(Refer to item 21-60-01), ande) Cabin pressurization system is considered inoperative (Refer to item 21-30-

02).

NOTE: Amber PRESS SRC NOT NORM message may appear.OPERATIONAL PROCEDURE

1. Start the left and the right engines. Refer to the Model 680A Approved Airplane Flight Manual. The APU should remain OFF.

2. Make sure that no warm air flows from the cabin warm air ducts or the overhead outlets with PRESS SOURCE SELECT selected OFF.

21-62-01-01A Temperature Indication SystemCabin(With cabin occupants)

C/1/0

(O) May be inoperative provided alternate means are established and used to determine cabin temperature.OPERATIONAL PROCEDURE

Make sure the cabin has been warmed to an acceptable temperature prior to flight. Refer to the Model 680A Approved Airplane Flight Manual. A portable temperature indicating device may be used to determine the temperature.

68ACOMP-01-06 14

22-10-01-01 Autopilot Disconnect Button(AP/TRIM/NWS DISC)(Failed deselected)Left Control Wheel

B/1/0

(O) May be inoperative provided:a) Right control wheel button is operative,b) Alternate procedures for disconnecting nose wheel steering during ground

operations are established and used,c) Pilot remains seated in right seat with seat belt fastened during all autopilot

operations,d) Autopilot system is not used below AFM cruise minimum use height, ande) Approach minimums do not require use of autopilot system.


The flight crew must brief that during all aircraft ground movements (including takeoff and landing), the copilot will have control of the AP/TRIM/NWS DISC function so that, in the event of a system malfunction, the copilot will activate the disconnect and the pilot will maintain directional control of the aircraft using a combination of tiller wheel steering, differential braking and thrust.

22-10-03 Autopilot System

B/1/0

(M) May be inoperative provided:a) Autopilot system is deactivated,b) Yaw damper is considered inoperative (Refer to item 22-10-05),c) Enroute procedures and approach minimums do not require use of autopilot

system,d) Cabin pressurization system is not operated in manual mode, ande) Aircraft is not operated RVSM.


Pull and secure the AUTOPILOT circuit breaker on the pilot’s circuit breaker panel.

NOTE-1: Amber “DATA BUS FAIL” message may be displayed on the ground.

NOTE-2: Providing “DATA BUS FAIL” message is not displayed prior to AUTOPILOT (HC073) circuit breaker pull, Aircraft is ok to for flight.

68ACOMP-01-06 15

22-10-05 Yaw Damper

B/1/0

(M) May be inoperative provided:a) Yaw damper is deactivated, andb) Autopilot system is considered inoperative (Refer to item 22-10-03).


Pull and secure the AUTOPILOT circuit breaker on the pilot’s circuit breaker panel.


NOTE-2: Providing “DATA BUS FAIL” message is not displayed prior to AUTOPILOT circuit breaker pull, Aircraft is ok to for flight.

22-30-01 Autothrottle System

C/1/0

(M) May be inoperative provided:a) Autothrottle system is deactivated, andb) Procedures do not require its use.


Pull and secure the AUTO THROTTLE circuit breaker on the pilot’s circuit breaker panel.


NOTE-2: Providing “DATA BUS FAIL” message is not displayed prior to AUTO THROTTLE circuit breaker pull, Aircraft is ok to for flight.

68ACOMP-01-06 16

23-10-01-00B High Frequency (HF) Communications 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 of communications

equipment status of aircraft, andd) 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.

23-20-01-02B Satellite Datalink ServiceWeather

C/-/0

(O) May be inoperative provided alternate procedures are established and used.OPERATIONAL PROCEDURE

Crew shall use other available means to obtain weather information such as HIWAS or FLIGHTWATCH as well as radar.

68ACOMP-01-06 17

23-20-03-00B Selective Call (SELCAL)(System or individual channel)

C/-/0


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.

23-40-02 Crewmember Interphone System (Flight Deck to Ground)

C/1/0


Alternate procedures for communication with ground crew must be established and used.

23-40-03 Passenger Address (PA) System

C/1/0

(O)May be inoperative provided:a) PA not required by 14 CFR, andb) Alternate, normal and emergency procedures, and/or operating restrictions are

established and used.

Note: Any station function(s) that operate normally may be used.OPERATIONAL PROCEDURE

Alternate procedures for passenger announcements must be established and used.

23-40-04 Passenger Seat Belt / Safety Chime

C/1/0

(O) May be inoperative provided:a) Passenger address system is operative, andb) Cabin occupants are briefed by alternate means.


A crew member must use the PA system from the cockpit to make the appropriate announcements.

68ACOMP-01-06 18

23-50-04-02 Cockpit Hand MicrophoneHolder

D/-/0

(O) May be inoperative provided associated hand microphone is secured by alternate means.OPERATIONAL PROCEDURE

Prior to flight, a crew member must ensure that the hand micro phone is secured in a manner that will not interfere with aircraft operations. One method is to utilize adhesive hook and loop (Velcro) strips on the pedestal.

23-50-07-01 Push-to-talk (PTT) SwitchYoke Switch

B/2/1

(O) One may be inoperative provided alternate procedures are established and used for transmitting.OPERATIONAL PROCEDURE

Prior to flight, the crew member with the operative switch will be assigned all radio transmissions.

68ACOMP-01-06 19

24-60-03 Interior Disconnect

C/1/0

(M) (O) May be inoperative provided:a) Interior power system is deactivated, b) Cabin emergency lighting is verified operative, andc) Passengers are briefed on disabled cabin electrical systems or are not carried.

NOTE: Items powered by interior bus are considered inoperative. This includes, but is not limited to: Cabin interior lighting, cabin window shade system, galley appliances, galley drain, vanity drain, forward equipment fan, aft equipment fan, cabin AC inverter, and cabin entertainment system.MAINTENANCE PROCEDURE

Pull the LEFT INTERIOR FEED BUS fuse in the LH power junction box and the RIGHT INTERIOR FEED BUS fuse in the RH power junction box.OPERATIONAL PROCEDURE

1. With both batteries off and no generators running, select EMER LTS to ON.2. Quickly verify the EXIT signs and the aisle lighting near the main cabin door is

operative.3. Select EMER LTS to OFF.

68ACOMP-01-06 20

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

D/1/0

(O) May be missing or inoperative provided an alternate means of securing and displaying required documents is used.OPERATIONAL PROCEDURE

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

25-10-02 Cockpit Curtain

D/-/0

(M) May be missing, or inoperative provided curtain is secured open.MAINTENANCE PROCEDURE

Carefully attach sufficient lengths of 3M vinyl tape (or equivalent) around the cockpit curtain and from the cockpit curtain to adjacent interior components to make sure that the cockpit curtain does not close or become loose during airplane operation.

25-10-05-01B Flight Crew Seat(Per seat)Armrest

C/2/0

(M) May be missing, or inoperative provided affected armrest is removed.MAINTENANCE PROCEDURE

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

NOTE: Refer to the appropriate Cessna Maintenance Manual and/or seat manual for information of the individual aircraft installation.

68ACOMP-01-06 21

25-10-05-03 Flight Crew Seat(Per seat)Recline/Tilt Function

C/2/0

(M) (O) May be inoperative provided:a) Affected seat is secured or failed in a position that permits normal visibilty,b) Full flight control movement is available, andc) Crewmember can reach all necessary controls and equipment while

restrained.MAINTENANCE PROCEDURE

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



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.

25-10-05-06 Flight Crew Seat(per seat)Vertical Adjustment

D/1/0

(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, andc) Crewmember can reach all necessary controls and equipment while

restrained.MAINTENANCE PROCEDURE

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




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

68ACOMP-01-06 22

25-10-08 Eye Reference Ball

C/3/0

(O) May be inoperative or missing provided alternate procedures are established and used for eye position reference.OPERATIONAL PROCEDURE

1. Prior to flight, a crew member shall occupy the affected seat and fasten the restraining system to ensure the following conditions are met:

(a) Make sure full flight control movement and brake application.(b) Make sure access to all necessary controls and equipment.

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

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

25-20-03 Cabin Curtain

D/-/0

(M) May be missing, or inoperative provided curtain is secured open.MAINTENANCE PROCEDURE

Carefully attach sufficient lengths of 3M vinyl tape (or equivalent) around the cockpit curtain and from the cockpit curtain to adjacent interior components to make sure that the cockpit curtain does not close or become loose during airplane operation.

68ACOMP-01-06 23

25-20-06-02A Passenger Seat(Including side-facing seats, folding seats and couches)(Per seat)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.MAINTENANCE PROCEDURE

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

NOTE: Refer to the appropriate Cessna Maintenance Manual and/or Interiors Manual for information of the individual aircraft installation.

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

D/-/0

(M) May be inoperative provided system is deactivated.MAINTENANCE PROCEDURE

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

NOTE: Refer to the appropriate Interiors Manual for information of the individual aircraft installation.

25-30-02 Refreshment Center Microwave / Oven

D/1/0



NOTE:Refer to the appropriate Interiors Manual for information of the individual aircraft installation.

68ACOMP-01-06 24

25-40-02 Aft Vanity Hot Liquid Storage System Heater

D/1/0



NOTE:Refer to the appropriate Interiors Manual for information of the individual aircraft installation.

25-50-01-01B Baggage Restraint SystemAnchor Plate

C/-/0

(M) Individual anchor plates may be inoperative provided:a) Attaching structure is inspected for damage, andb) Baggage is secured using remaining anchor plates or not carried.


Refer to 680A Maintenance Manual Chapter 25, Equipment/Furnishings - Dispatch Deviation.

25-50-02-00A Cabin Storage Compartment

C/-/-

(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, ande) Affected compartment is prominently placarded "DO NOT USE".



68ACOMP-01-06 25

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



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, andb) Cabin occupants are briefed on location of relocated equipment.


1. Make sure all equipment located on affected shelf has been relocated and is available for use.

2. Brief cabin occupants on location of relocated equipment.

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.



68ACOMP-01-06 26

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.MAINTENANCE PROCEDURE


68ACOMP-01-06 27

26-13-01-02 Bleed Leak Detection System(Failed to pass preflight test)Horizontal Stabilizer

B/1/0

(M) May be inoperative provided:a) Both ANTI-ICE ENGINE/STAB switches are selected OFF,b) Both stabilizer anti-ice valves are verified closed, andc) Aircraft is not operated in known, forecast, or AFM-defined icing conditions.


Refer to 680A Maintenance Manual Chapter 26, Fire Protection - Dispatch Deviation.

26-13-01-03 Bleed Leak Detection System(Failed to pass preflight test)Wing

B/2/0

(O) May be inoperative provided:a) Both ANTI-ICE ENGINE/STAB switches are selected OFF,b) Both ANTI-ICE WING switches are selected OFF,c) Both wing anti-ice valves are verified closed, andd) Aircraft is not operated in known, forecast, or AFM-defined icing conditions.


1. On the ground, with engines running and bleed air ON, select both ANTI-ICE WING switches ON.

2. With engines set slightly above idle, verify no airflow at the wing outboard anti-ice air outlets on both wings.

68ACOMP-01-06 28

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, andd) Crewmember seated at affected station verifies full control movement and

brake application is available while restrained, prior to each flight.MAINTENANCE PROCEDURE

Refer to 680A Maintenance Manual Chapter 27, Flight Controls - Dispatch Deviation.OPERATIONAL PROCEDURE


2. Make sure full flight control movement and brake application are available.

27-70-02 Control / Gust Lock System(Failed unlocked)

C/1/0

(O) May be inoperative provided pilot verifies full flight control and throttle movement.OPERATIONAL PROCEDURE

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

68ACOMP-01-06 29

28-41-01 Fuel Low Level Indicating System

A/2/1

(O) One may be inoperative provided:a) Procedures for monitoring fuel quantity are established and used,b) Both fuel quantity indicating systems are operative, andc) Repairs are made within three flight days.


1. Flight crew shall brief the loss of low fuel quantity warning system on the affected side.

2. Flight crew shall monitor fuel balance during flight to make sure adequate fuel remains in both wing fuel tanks for planned mission.

28-41-02 Fuel Quantity Indicating System(Wing Tank)

A/2/1

(O) One may be inoperative provided:a) Both fuel low level indicating systems and both fuel flow indicating systems are

operative,b) Fuel required for route to be flown is increased by 10%,c) Flight is restricted to a maximum of three hours, remaining within one hour of a

suitable airport at all points along route,d) Both fuel tanks are fueled over-wing to a known, balanced quantity,e) APU use is limited to thirty cumulative minutes if RH indicator is inoperative,f) Fuel use is tracked,g) If autopilot is used, it is disconnected every twenty minutes to detect possible

lateral fuel imbalance, monitor trim required and RETRIM L-R WING DOWN amber message, and

h) Repairs are made within three flight cycles.OPERATIONAL PROCEDURE

1. During preflight planning, increase the fuel required for the route to be flown by 10%. Also plan the route so that the flight will last no longer than three hours while remaining within one hour of a suitable airport at all points.

2. To achieve a known quantity in the affected tank, the tank may be emptied using Single-Point defueling then fueled to a known quantity. It may be completely fueled, or fuel may be transferred out of the tank until it is empty.

3. To track fuel use, operators may use a fuel log or develop their own procedure. This can include matched fuel flow techniques, use of the FMS fuel quantity system or other means.

4. During flight, disconnect the autopilot every twenty minutes. Make sure a crew member has control of the aircraft prior to disconnecting the autopilot. Check for any abnormal roll tendencies. Check for roll trim required.

5. Re-engage the autopilot. Monitor the RETRIM L or R WING DOWN amber message.

68ACOMP-01-06 30

30-10-02 Horizontal Stabilizer Bleed Air Anti-Ice System(Failed open)

C/2/1

(M) One may be inoperative provided:a) Affected horizontal stabilizer valve is secured for no flow,b) Affected ANTI-ICE ENGINE/STAB switch is selected OFF, andc) Aircraft is not operated in known, forecast, or AFM-defined icing conditions.


Refer to 680A Maintenance Manual Chapter 30, Ice and Rain Protection - Dispatch Deviation.

30-10-04-01 Wing Bleed Air Anti-Ice SystemInboard Leading Edge

A/2/0

(M) May be inoperative provided:a) Both inboard wing valves are secured for no flow,b) Both ANTI-ICE ENGINE/STAB switches are selected OFF,c) Aircraft is not operated in known, forecast, or AFM-defined icing condition, andd) Repairs are made within three flight days.



30-10-04-02 Wing Bleed Air Anti-Ice SystemOutboard Leading Edge

C/2/0

(M) May be inoperative provided:a) Both outboard wing valves are secured for no flow,b) Both ANTI-ICE WING switches are selected OFF, andc) Aircraft is not operated in known, forecast, or AFM-defined icing conditions.



68ACOMP-01-06 31

30-20-01 Engine Anti-Ice System

A/2/1

(M) One may be inoperative provided:a) Affected valve is secured for no flow,b) Affected ANTI-ICE ENGINE/STAB switches are selected OFF,c) Aircraft is not operated in known, forecast, or AFM-defined icing conditions,

andd) Repairs are made within three flight days.



30-40-02 Windshield Electric Anti-Ice System

C/2/1

(M) One may be inoperative provided:a) Affected windshield anti-ice system is deactivated,b) A means to clear windshield of moisture is readily available,c) Opposite side frost pane defog is considered inop(Refer to 30-40-05), andd) Aircraft is not operated in known, forecast, or AFM-defined icing conditions.

NOTE: Amber TRU FAIL message may be displayed.MAINTENANCE PROCEDURE

Pull and secure the L W/S ANTI-ICE circuit breaker on the pilot’s circuit breaker panel or the R W/S ANTI-ICE circuit breaker on the copilot’s circuit breaker panel.

NOTE: Amber TRU FAIL message may be displayed.

30-70-01 Drain Heater(Refreshment center and aft vanity basin)

C/-/0

(M) May be inoperative provided:a) Drain heaters are deactivated,b) Refreshment center and aft vanity basin overboard drains are considered

inoperative (Refer to item 38-30-04), andc) External lavatory service system heater gasket is considered inoperative

(Refer to item 38-30-02-08).MAINTENANCE PROCEDURE

Pull and secure the DRAIN HEATERS circuit breaker on the aft interior junction box.

68ACOMP-01-06 32

31-10-02-02 Panel Switch Lights(Failed to illuminate)Anti-Collision Lights(ANTI-COLL - ON)

C/1/0

(O) May be inoperative provided anti-collision lights (strobes) are visually verified on prior to each flight.OPERATIONAL PROCEDURE

1. During the Cockpit/Cabin Inspection: Exterior Lights procedure, press the ANTI-COLL switch.

2. Visually verify the anti-collision lights illuminate.3. Press the switch again, verify the lights extinguish.

31-10-02-03 Panel Switch Lights(Failed to illuminate)Anti- Ice Crossflow(WING XFLOW - XFLOW / OFF)

C/2/0

(O) May be inoperative provided:a) Switch functionality is verified operative, andb) A/I WING XFLOW OPEN white and amber messages are monitored.


1. During the Before Takeoff: Anti-Ice Systems procedure, press the WING XFLOW switch.

2. Verify the A/I WING XFLOW OPEN white message appears.3. Press the switch again, verify the message(s) extinguishes.

31-10-02-04 Panel Switch Lights(Failed to illuminate)APU Bleed Air(APU BLEED AIR - ON / OFF)

C/2/0

(O) May be inoperative provided:a) Switch functionality is verified operative, andb) APU BLD VALVE OPEN amber message and APU BLD VALVE CLOSED

white message are monitored.OPERATIONAL PROCEDURE

1. Following the Cockpit Preparation: APU start procedure, press the APU BLEED AIR switch.

2. Verify the APU BLD VALVE CLOSE white message extinguishes.3. Press the switch again, verify the message appears.

68ACOMP-01-06 33

31-10-02-14 Panel Switch Lights(Failed to illuminate)Auxiliary Hydraulic Pump(HYDRAULIC PUMP AUX - ON / OFF)

C/2/0

(O) May be inoperative provided switch functionality is verified operative.

NOTE: Use HYD AUX PUMP ON white message to verify switch position.OPERATIONAL PROCEDURE

1. During the Before Start procedure, press the HYDRAULIC PUMP AUX switch.2. Verify the AUX HYDRAULIC PUMP ON white message appears.3. Press the switch again, verify the message(s) extinguishes.

31-10-02-23 Panel Switch Lights(Failed to illuminate)Display Reversion(DISPLAY REV - NORM / REV)

C/2/0

(O) May be inoperative provided switch functionality is verified operative.OPERATIONAL PROCEDURE

1. With avionics on, press the affected DISPLAY REV switch.2. Verify the associated PFD and MFD enter reversionary mode.3. Press the DISPLAY REV switch again.4. Verify the associated PFD and MFD return to normal mode.

31-10-02-27 Panel Switch Lights(Failed to illuminate)Engine / Stabilizer Anti-Ice(ENGINE/STAB - ON / OFF)

C/4/0


NOTE: Use ANTI-ICE ON ENG/STAB white message to verify switch position.OPERATIONAL PROCEDURE

1. During the Before Takeoff: Anti-Ice Systems procedure, press the affected ENGINE/STAB switch.

2. Verify the associated ANTI-ICE ON ENG/STAB and/or A/I ENGINE COLD white messages appear.

3. Press the switch again, verify the message(s) extinguishes.

68ACOMP-01-06 34

31-10-02-32 Panel Switch Lights(Failed to illuminate)Fuel Boost(BOOST PUMP - NORM / ON)

C/4/0


NOTE: Use FUEL BST PUMP ON L-R white and amber messages to verify switch position.OPERATIONAL PROCEDURE

1. Following engine start, press the affected BOOST PUMP button.2. Verify the associated FUEL BST PUMP ON L-R white message appears.3. Press the switch again.4. Verify the message extinguishes.

31-10-02-35 Panel Switch Lights(Failed to illuminate)Interior Power(INTERIOR - ON)

C/1/0

(O) May be inoperative provided switch functionality is verified operative.OPERATIONAL PROCEDURE

1. With main DC power active, press the INTERIOR button.2. Verify the OFF annunciator illuminates.3. Verify items on the INTERIOR bus, such as downwash lighting, are inoperative.4. Press the INTERIOR button again.5. Verify the OFF annunciator extinguishes.6. Verify the same interior items are now operative.

31-10-02-37 Panel Switch Lights(Failed to illuminate)Max Cool(MAX COOL – OFF)

C/1/0


NOTE: Use MAX COOL – ON switch light to verify switch position.OPERATIONAL PROCEDURE

1. Following the Cockpit Preparation: APU start procedure, press the MAX COOL switch.

2. Verify the operative MAX COOL ON switch light illuminates.3. Press the switch again, verify the switch light extinguishes.

68ACOMP-01-06 35

31-10-02-41 Panel Switch Lights(Failed to illuminate)Pitot / Static Anti-Ice(PITOT/STATIC - ON / OFF)

B/4/0

(O) May be inoperative provided:a) Switch functionality is verified operative, andb) P/S COLD L-R-STBY white and amber messages are monitored.


1. During the Cockpit/Cabin Inspection: Anti-Ice PITOT/STATIC check, press the affected PITOT/STATIC switch.

2. Externally verify the associated pitot and static heaters are heating.3. Verify the associated P/S COLD L-R-STBY white message appears briefly and

then extinguishes.

31-10-02-53 Panel Switch Lights(Failed to illuminate)Wing Anti-Ice(WING - ON / OFF)

C/4/0

O) May be inoperative provided:a) Switch functionality is verified operative, andb) A/I WING COLD L-R white and amber messages are monitored.


1. During the Before Takeoff: Anti-Ice Systems procedure, press the affected WING switch and both ENGINE/STAB switches.

2. Verify the ANTI-ICE ON ALL white messages appears and/or associated A/I WING COLD white message appears briefly.

3. Press the switch again, verify the message(s) extinguishes.

68ACOMP-01-06 36

31-10-02-54 Panel Switch Lights(Failed to illuminate)Wing Inspection Light(WING INSP - ON)

C/1/0

(O) May be inoperative provided:a) Switch functionality is verified operative, andb) Wing inspection lights are visually monitored.


1. During the Cockpit/Cabin Inspection: Exterior Lights procedure, press the WING INSP switch.

2. Visually verify the wing inspection lights illuminate.3. Press the switch again, verify the lights extinguish.

31-20-01 APU Hour Meter

C/1/0

(O) May be inoperative provided APU operation time is tracked by alternate means.OPERATIONAL PROCEDURE

1. Log elapsed time of APU in aircraft logbook after each flight. This includes ground operation times during any maintenance performed when the aircraft is not intended to fly.

2. Once the APU hour meter is repaired, place a placard next to the hour meter showing the additional time accumulated while inoperative (e.g. “+ 14.2 hours”).

31-20-04 Flight Hour Meter

C/1/0

(O) May be inoperative provided flight time is tracked by alternate means.OPERATIONAL PROCEDURE

1. Record Zulu time of takeoff and landing.2. Log elapsed time in aircraft logbook after each flight.3. Once the flight hour meter is repaired, place a placard next to the hour meter

showing the additional time accumulated while inoperative (e.g. “+ 14.2 hours”).

68ACOMP-01-06 37

31-50-06-07 WHITE CAS MESSAGE(Displayed)NO STANDBY DATA

A/1/0

O) May be displayed provided repairs are completed within ten flight days.OPERATIONAL PROCEDURE

Crew must manually compare displayed Data.

31-50-06-08 WHITE CAS MESSAGE(Displayed) OIL FILTER BYPASS

A/1/0

(O) May be displayed provided:a) ENG CHIP DETECT L or R is not displayed,b) Engine oil pressure and temperature are monitored, andc) Repairs are made within 10 operating hours.


During operation the flight crew must:1. Monitor ENG CHIP DETECT L or R is not displayed, and2. Monitor Engine oil pressure and temperature.

31-50-06-09 WHITE CAS MESSAGE(Displayed) OIL LEVEL LOW L or R

A/1/0

(O) May be displayed provided:a) Engine oil level is verified above MIN, andb) Repairs are made within 3 flight days.


During preflight walk around, a flight crewmember must visually verify the oil level is above minimum.

68ACOMP-01-06 38

33-10-05-00A Windshield Ice Detection Light

C/2/1

(O) One may be inoperative provided alternate procedures are established and used to monitor ice accretion.OPERATIONAL PROCEDURE

The flight crew member with the operative light must be assigned responsibility for monitoring the windshield for ice accumulation and alerted the other flight crew member.

33-20-02-00A Cabin Interior Lighting(Excluding cabin emergency lighting)

D/-/-

(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, andc) Sufficient lighting is operative for carrying cabin occupants at night.




33-20-02-00B 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.




68ACOMP-01-06 39

33-20-04-00A 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.OPERATIONAL PROCEDURE

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

33-40-03-01 Landing LightRecognition Light Mode

C/1/0

(O) May be inoperative provided at least one landing light is verified operative for night operations.OPERATIONAL PROCEDURE

During the Preliminary Exterior Inspection, verify at least one landing light is operative.

33-40-03-02 Landing LightPulse Light Mode

D/1/0

(O) May be inoperative provided at least one landing light is verified operative for night operations.OPERATIONAL PROCEDURE

During the Preliminary Exterior Inspection, verify at least one landing light is operative.

68ACOMP-01-06 40

33-50-03 Emergency Lighting Battery(CBS 28)(Excluding Pack 1 UF004)

B/3/0

(O) May be inoperative provided:a) Main cabin door exit signs are verified operative,b) Left forward dropped-aisle lighting is verified operative,c) Exterior emergency lights are considered inoperative (Refer to item 33-50-04).d) No cabin occupants are carried, ande) Aircraft is not operated at night.


1. With both batteries off and no generators running, select EMER LTS to ON.2. Quickly verify the main cabin door EXIT signs and the left forward aisle lighting is


68ACOMP-01-06 41

34-16-01 Altitude Alerting System

A/-/0

(O) May be inoperative provided:a) Autopilot with altitude hold and capture operates normally,b) Aircraft does not depart from an airport where repair or replacement can be

made,c) Aircraft is not operated RVSM, andd) Repairs are made within three flight days.


1. Crew briefings must include a reminder that the Altitude Alerting System is inoperative.

2. The flight crew will use aural callouts pertaining to approach target altitudes as assigned by ATC or depicted on approach charts.

34-25-07 Touchscreen Controller(GTC)(L PFD or R PFD)

C/2/1

(M) One may be inoperative provided controller is deactivated. NOTE: Any functions or controls that operate normally may be used.MAINTENANCE PROCEDURE

Pull and secure the L PFD GTC circuit breaker on the pilot’s circuit breaker panel or the R PFD GTC circuit breaker on the copilot’s circuit breaker panel.


NOTE-2: Providing “DATA BUS FAIL” message is not displayed prior to PFD circuit breaker pull, Aircraft is ok to for flight.

34-36-01 Reactive Windshear System(Includes TAWS windshear mode)

C/1/0


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

68ACOMP-01-06 42

34-44-01-00B Radio Altimeter System(TAWS or TCAS II required)

A/1/0

(M) May be inoperative provided:a) Radio altimeter system is deactivated,b) Approach minimums or operating procedures do not require its use,c) Basic TAWS modes are considered inoperative (Refer to item 34-40-03),d) TCAS II is considered inoperative (Refer to item 34-45-01), ande) Repairs are made within two flight days.

NOTE 1: Landing gear warning system will function differently without radio altimeter input. Landing gear warning may occur at higher altitudes above ground with flaps extended.

NOTE 2: Landing Operations Phase Inhibit (LOPI) operation will be affected. LOPI will not activate during approach or go-around.MAINTENANCE PROCEDURE

Pull and secure the appropriate circuit breaker.

34-44-03 Terrain Awareness and Warning System (TAWS)(Includes test mode)(Class A or B TAWS required)

A/1/0

(O) May be inoperative provided:a) Alternate procedures are established and used,b) RNP AR procedures are not conducted, andc) Repairs are made within two flight days.


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

34-44-03-01 Terrain Awareness and Warning System (TAWS)Forward Looking Terrain Avoidance Function and Premature Descent Alert Function

B/2/0



68ACOMP-01-06 43

34-44-03-02 Terrain Awareness and Warning System (TAWS)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.



34-44-03-03A Terrain Awareness and Warning System (TAWS)Voice Callouts (Mode 6)(“Five-Hundred”)

B/1/0


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.

34-44-03-03B Terrain Awareness and Warning System (TAWS)Voice Callouts (Mode 6)(Other)

C/-/0


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.

68ACOMP-01-06 44

34-44-03-04A Terrain Awareness and Warning System (TAWS)Excessive Closure Rate to Terrain (Mode 2) and Flight Into

TerrainNot in Landing Configuration (Mode 4)(Class A TAWS required)

A/2/0

(O) May be inoperative provided:a) Alternate procedures are established and used, andb) Repairs are made within two flight days.



34-45-01-00A Traffic Alert and Collision Avoidance System (TCAS II)(TCAS not required)

B/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.


Pull and secure the TCAS circuit breaker on the pilot’s circuit breaker panel.

34-45-01-00B Traffic Alert and Collision Avoidance System(TCAS II)(TCAS required)

C/1/0

(M) May be inoperative provided:a) System is deactivated, andb) Enroute or approach procedures do not require its use.


Pull and secure the TCAS circuit breaker on the pilot’s circuit breaker panel.

68ACOMP-01-06 45

34-45-01-01 Traffic Alert and Collision Avoidance System(TCAS II)Traffic Advisory (TA) Display

C/-/0

(O) May be inoperative provided:a) Resolution Advisory (RA) display and audio function are operative, andb) Enroute or approach procedures do not require use of TCAS.

OPERATIONAL PROCEDURE:

1. Using test function, confirm that RA display elements (including VSI “fly to” and “do not fly” areas) and voice command audio functions are operative.

2. Monitor PFD VSI for RA commands.

34-45-01-02B Traffic Alert and Collision Avoidance System(TCAS II)Resolution Advisory (RA) Display

C/2/0

(O) May be inoperative provided:a) Traffic Advisory (TA) display and audio function are operative,b) TA-only mode is selected on TCAS controller or menu, andc) Enroute or approach procedures do not require use of TCAS.

OPERATIONAL PROCEDURE:

1. Using test function, confirm that Traffic Advisory display elements and voice command audio functions are operative.

2. Select TA only mode of operation.

34-61-01 Navigation Database

C/-/-

(O) May be out of currency provided:a) Current aeronautical charts are used to verify navigation fixes prior to each

flight,b) Procedures are established and used to verify status and suitability of

navigation facilities used to define route of flight, andc) Approach navigation radios are manually tuned and identified.


The navigation database can only be used for enroute and terminal navigation when out of currency. Before using the FMS to navigate to a facility, verify the status, identifier, frequency and lat/long position with an alternate, current source of information. Refer to the applicable Airplane Flight Manual supplement for additional information.

68ACOMP-01-06 46

35-00-03-01 Oxygen SystemFill Port

C/-/0

(M) May be inoperative provided bottle is filled using alternate means, if service is required.MAINTENANCE PROCEDURE

Refer to 680A Maintenance Manual Chapter 35, Oxygen - Dispatch Deviation.

35-00-03-02 Oxygen SystemServicing Panel Pressure Gauge

C/-/0

(M) May be inoperative provided bottle is filled using alternate means, if service is required.MAINTENANCE PROCEDURE


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



68ACOMP-01-06 47

36-10-01-00A Bleed Air Shutoff ValveLeft

B/1/0

(M) May be inoperative provided:a) Affected valve is secured for no flow,b) Emergency pressurization system is considered inoperative (Refer to item 21-

30-03),c) L ENG BLD AIR is selected OFF,d) Aircraft is operated at FL250 or below, ande) Aircraft is not operated in known, forecast, or AFM-defined icing conditions.

NOTE: Amber BLD SEL NOT NORM L message may appear.MAINTENANCE PROCEDURE

Refer to 680A Maintenance Manual Chapter 36, Pneumatics - Dispatch Deviation.

36-10-01-00B Bleed Air Shutoff ValveRight

B/1/0

(M) May be inoperative provided:a) Affected valve is secured for no flow,b) R ENG BLD AIR is selected OFF,c) BAG HEAT is selected OFF, andd) Aircraft is not operated in known, forecast, or AFM-defined icing conditions.

NOTE: Amber BLD SEL NOT NORM R message may appear.MAINTENANCE PROCEDURE


68ACOMP-01-06 48

36-10-01-01A Bleed Air Shutoff ValveHigh-pressure (HP)

C/2/1

(M) One may be inoperative provided:a) Affected valve is secured for no flow,b) Associated ENG BLD AIR knob is selected to LP,c) Aircraft is not operated in known, forecast, or AFM-defined icing conditions,

andd) Aircraft is operated at FL410 or below).

NOTE: Amber BLD SEL NOT NORM L-R message may appear.MAINTENANCE PROCEDURE


36-10-01-01B Bleed Air Shutoff ValveHigh-pressure (HP)

C/2/0

(M) May be inoperative provided:a) Both valves are secured for no flow,b) Both ENG BLD AIR knobs are selected to LP,c) Aircraft is not operated in known, forecast, or AFM-defined icing conditions,

andd) Aircraft is operated at FL410 or below.

NOTE: Amber BLD SEL NOT NORM L-R message may appear.MAINTENANCE PROCEDURE


36-10-02-00A Engine Bleed Air Precooler Temperature Control System(Dual bleed air source)

B/2/1

(M) One may be inoperative provided:a) Precooler temperature control system is deactivated,b) Precooler bypass air butterfly valve is secured open, andc) Aircraft is not operated in known, forecast, or AFM-defined icing conditions.



68ACOMP-01-06 49

38-10-01 Potable Water System

C/-/0

(M) May be inoperative provided:a) System is drained, andb) Procedures are established and used to ensure system is not serviced.


Refer to 680A Maintenance Manual Chapter 38, Water/Waste - Dispatch Deviation.

38-10-01-01 Potable Water SystemIndividual Components

C/-/0

(M) Individual components may be inoperative provided:a) Associated components are deactivated or isolated, andb) Associated system components are verified not to have leaks.

NOTE: Any portion of system operating normally may be used.MAINTENANCE PROCEDURE

1. Deactivate the associated components. Refer to the appropriate Interior Maintenance Manual.

2. Verify no leaks are found. If leaks are found, system must be drained and all leaked fluid cleaned, system must not be re-serviced, and weight and Balance with missing fluid must be computed and provided to the flight crew for flight planning purposes.

38-30-02 Lavatory External Service System

C/1/0

(M) Individual components may be inoperative provided:a) Associated components are deactivated or isolated, andb) Associated system components are verified not to have leaks.

NOTE: Any portion of the system operating normally may be used.MAINTENANCE PROCEDURE

1. Deactivate the associated components. Refer to the appropriate Interior or Airframe Maintenance Manual.

2. Verify no leaks are found. If leaks are found, system must be drained and all leaked fluid cleaned, system must not be re-serviced, and weight and Balance with missing fluid must be computed and provided to the flight crew for flight planning purposes.

68ACOMP-01-06 50

38-30-02-01B Lavatory External Service SystemDump Cable

C/1-/0

(M) May be inoperative provided lavatory is serviced by alternate means.MAINTENANCE PROCEDURE

Refer to 680A Maintenance Manual Chapter 38, Water/Waste - Dispatch Deviation.

38-30-02-08 Lavatory External Service SystemHeater Gasket

C/1/0

(M) May be inoperative provided:a) Waste line is drained of all fluids,b) Heater gasket is deactivated,c) Drain heaters are considered inoperative (Refer to item 30-70-01), andd) Toilet is not serviced within four hours of landing or at surface temperatures

below +10 C.MAINTENANCE PROCEDURE

Pull and secure the DRAIN HEATERS circuit breaker on the aft interior junction box.

38-30-04-01 Overboard Drain(Excluding drain heater)Aft Vanity Basin

C/1/0

(O) May be damaged or obstructed provided:a) All liquid is removed from basin, andb) Basin is placarded "DO NOT USE".


Remove all liquid from the basin by allowing it to drain while on the ground or using other means such as towels or wet vac.

68ACOMP-01-06 51

38-30-04-03 Overboard Drain(Excluding drain heater)Refreshment Center

C/1/0

(O) May be damaged or obstructed provided:a) All liquid is removed from refreshment center hot liquid storage and drip pan,b) Refreshment center hot liquid storage and drip pan are placarded "DO NOT

USE", andc) Ice drawer drain valve remains closed.


1. Remove all liquid from the drip pan by allowing it to drain while on the ground or using other means such as towels or wet vac.

2. Empty the hot liquid storage tanks.

68ACOMP-01-06 52

46-00-01-00B Electronic Flight Bag (EFB) SystemClass 3 EFB

C/-/0

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

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

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

46-00-01-01B Electronic Flight Bag (EFB) SystemData Connectivity(Class 2)

C/-/0



46-00-01-02B Electronic Flight Bag (EFB) SystemPower Connection(Class 1 & 2)

C/-/0



46-00-01-03A Electronic Flight Bag (EFB) SystemMounting Device(Class 2)

D/-/0

(M) May be inoperative provided:a) Associated EFB and hardware is secured by an alternate means or removed

from the aircraft, andb) Procedures do not require its use.



68ACOMP-01-06 53

46-00-01-03B Electronic Flight Bag (EFB) SystemMounting Device(Class 2)

C/-/0

(M) May be inoperative provided:c) Associated EFB and hardware is secured by an alternate means or removed

from the aircraft, andd) Procedures do not require its use.


Refer to 680A Maintenance Manual Chapter 25, Equipment/Furnishings - Dispatch Deviation.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.

68ACOMP-01-06 54

49-20-01 Auxiliary Power Unit (APU)

C/1/0

(M) May be inoperative provided:a) APU is deactivated, andb) Procedures do not require its use.


Pull and secure the APU MASTER circuit breaker on the copilot’s circuit breaker panel.

49-30-01 APU Fuel Shutoff Valve

C/1/0

(M) May be inoperative provided:a) APU fuel shutoff valve is verified closed, andb) APU is considered inoperative (Refer to item 49-20-01).


Refer to 680A Maintenance Manual Chapter 49, Auxiliary Power Unit - Dispatch Deviation.

49-50-02 APU Bleed Air System

C/1/0

(O) May be inoperative provided:a) APU BLEED AIR is selected OFF, andb) APU bleed air valve is verified closed.


1. Prior to engine start, start the APU.2. Verify no air flow exists from the overhead air outlets.

68ACOMP-01-06 55

52-10-01-07 Main Cabin DoorHandrail

C/1/0

(O) May be inoperative or damaged provided:a) Door operates and latches normally, andb) Alternate procedures are established and used for assisting passengers during

entry and exit.OPERATIONAL PROCEDURE

1. Prior to entry and exit, occupants are briefed by a crew member not to utilize the handrail.

2. Passengers may need assistance entering and exiting the aircraft.

52-10-01-10 Main Cabin DoorLift Motor

C/1/0

(O) May be inoperative provided:a) Lift motor clutch is disengaged, andb) Gas Strut is operable.


WARNING: Gas strut must be operable for safe door opening with the lift motor disengaged.

1. Disengage the lift motor clutch.(a) Remove access panel in the left fwd cabinet.(b) Push handle located on motor aft, until latched.(c) While standing on the ground outside the airplane, lift door to verify motor

has disengaged. Door should lift easily.2. Persons on the ground can lift the door into the frame.

(a) If no ground assistance is available, crew can use the cabin door strap from the drawer beneath the fwd side facing seat to lift the door into the frame.

i. Insert the ball catch pin on the strap into the receptacle located at the top of the view port (referenced with the door open) of the first step riser.

ii. Stand securely in the cabin and use the cabin door strap to lift the door into the frame.

iii. Two crew members may be required to successfully lift and close the door.

3. While holding the door in frame, move the latching handle into the closed and latched position.

(a) Verify the cabin door amber DOOR OPEN light extinguishes.(b) Verify all locking flags are visible in the 6 sight glass locations.

68ACOMP-01-06 56

WARNING: Door is not secure if latch lock flags are not fully visible.

4. If cabin door strap was used, remove the ball catch pin from the cabin door receptacle and stow the strap in the drawer beneath the fwd side facing seat.

52-30-01-02 Aft Baggage DoorDoor Seal

C/1/0

(O) May be damaged provided baggage compartment is verified empty prior to each flight.OPERATIONAL PROCEDURE

Prior to each flight, a crew member must make sure the aft baggage compartment is empty.

68ACOMP-01-06 57

52-30-01-05 Aft Baggage DoorDoor Cable

B/2/1

(M) One may be inoperative or missing provided:a) Affected cable is removed, andb) Door steps are not used


Refer to the 680A Maintainence manual section 52 for removal of the Baggage Door Cable.

52-30-01-05 Aft Baggage DoorGas Spring

C/1/0

(O) May be inoperative or missing provided precautions are taken when opening door.OPERATIONAL PROCEDURE

1. The flight crew should brief any occupants or crewmembers that would need to access the aft baggage that the spring is inoperative.

2. When opened, the door shall be held open or supported by another means which is secure enough to prevent the door from swinging in the wind.

52-50-01 Cockpit Divider Door

C/2/0

(M) May be inoperative provided door is secured open.MAINTENANCE PROCEDURE


52-50-02 Lavatory Door

C/2/0

(M) May be inoperative provided door is secured open.MAINTENANCE PROCEDURE


68ACOMP-01-06 58

52-50-07 Door Warning SystemMain Cabin Door

B/1/0

(O) May be inoperative provided:a) Flight crew follows AFM CHECK DOORS procedures,b) Lock flags are fully engaged in all door site glass locations, andc) Internal door handle is verified in the fully latched position.


Following the completion of the AFM CHECK DOORS procedures, a crew member must verify that all door flags are engaged and fully visible in the site glasses. Also a visual check of the internal door handle to ensure it is in the fully latched position is required.

68ACOMP-01-06 59

78-30-01 Thrust Reverser

C/2/0

(M) May be inoperative provided:a) Affected thrust reverser is deactivated and secured in forward thrust position,

andb) Takeoffs on contaminated runways are prohibited.

NOTE: Flight crew should review AFM Single-Engine Reversing procedure.MAINTENANCE PROCEDURE

Refer to 680A Maintenance Manual Chapter 78, Exhaust - Dispatch Deviation.

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APPENDIX A

CABIN ALTITUDE vs. CABIN PRESSURE DIFFERENTIAL CONVERSION(Cabin Pressure Differential Display or Cabin Altimeter Inoperative)

CABIN ALT AIRCRAFT PRESSURE ALTITUDE x 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 5.8 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 6.0 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 6.2 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 6.4 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 6.6 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 6.8 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 7.1 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 7.3 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 7.5 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 7.7 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 7.9 8.2 8.5 8.9 9.1 9.4 9.6 9.9 10.15.0 2.1 3.9 5.5 6.8 7.5 8.2 8.4 8.8 9.1 9.4 9.6 9.9 10.14.5 2.4 4.2 5.7 7.0 7.7 8.4 8.7 9.0 9.3 9.6 9.9 10.14.0 2.6 4.4 5.9 7.2 7.9 8.6 8.9 9.2 9.5 9.8 10.13.5 2.8 4.6 6.2 7.5 8.2 8.9 9.1 9.5 9.8 10.13.0 3.1 4.9 6.4 7.7 8.4 9.1 9.4 9.7 10.02.5 3.3 5.1 6.7 8.0 8.6 9.3 9.6 10.02.0 3.6 5.4 6.9 8.2 8.9 9.6 9.9 10.21.5 3.8 5.6 7.2 8.5 9.1 9.8 10.11.0 4.1 5.9 7.4 8.7 9.4 10.10.5 0.0 4.3 6.1 7.7 9.0 9.70.0 0.0 0.3 4.6 6.4 7.9 9.2 9.9-0.5 0.3 0.6 4.9 6.7 8.2 9.5 10.2-1.0 0.5 0.8 5.1 6.9 8.5 9.8 10.5

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.

68ACOMP-01-06 61