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Beechcraft ProceduresManual

Textron Aviation Model 300

300 (including FF Serials), 300LW, B300, B300C (MC-12W, UC-12W)

THIS GUIDE IS CURRENT WITH THE MASTER MINIMUM EQUIPMENT LIST WHICH IS DISTRIBUTED BY THE DEPARTMENT OF TRANSPORTATION

FEDERAL AVIATION ADMINISTRATION - REVISION 10a DATED 10/04/2018.

COPYRIGHT © 2018 MMEL REVISION 10aTextron AviationWICHITA, KANSAS, U.S.A.

BPM REVISION 0

300BPM-10a-0 1

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. Textron Aviation does not support Minimum Equipment List items not published in the MMEL.

Textron Aviation’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. Textron Aviation reserves the right to make format changes without generating a new revision.

Maintenance (M) or Operational (O) procedures in this manual are recommended by Textron Aviation. 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.

14 CFR 91 operators must have the following statement included in their procedures 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.

300BPM-10-01 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 Textron Aviation Maintenance Manual for the associated aircraft model. In the event of conflict, use the more restrictive maintenance procedure to accomplish the task.

300BPM-10-01 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 CARRIAGE OF CARGO (EXCLUDING BALLAST) IS PROHIBITED SINGLE-PILOT OPERATIONS 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.

300BPM-10-01 4

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.

300BPM-10-01 5

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300BPM-10-01 6

21-01-02 Vapor Cycle Air Conditioning System

C/1/0

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

Pull and secure C/B 24 – AIR COND CLUTCH (air conditioning clutch) located in the DC power distribution panel inside the lower forward equipment bay.

***21-01-03 Ground Air Cooling System

D/1/0


Pull and secure the compressor-clutch C/B 24 – AIR COND CLUTCH circuit breaker located in the DC power distribution panel inside the lower forward equipment bay.

21-10-01-01 Cabin Pressurization System

C/1/0

(O) May be inoperative provided:a) CABIN PRESS switch is selected to DUMP and verified operative,b) Aircraft is operated at 12,000 feet cabin pressure altitude or below, andc) Oxygen system is used as required by 14 CFR operating rule.

NOTE 1: When 300/300LW cabin pressure altitude reaches 12,000 to 12,500 feet, an “ALT WARN” (red) annunciator will illuminate.

NOTE 2: When B300/B300C pressure altitude reaches approximately 10,000 feet, the CABIN ALTITUDE (white) annunciator will illuminate. When the cabin pressure altitude exceeds 11,500 to 12,000 feet, a “CABIN ALT HI” (red) annunciator will illuminate.OPERATIONAL PROCEDURE

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

2. Minimum enroute altitudes must be considered for the planned route.3. Place both Bleed Air Valves to ENVIR OFF.4. Place the Cabin Press switch to DUMP position.5. Passengers must be briefed prior to each flight that cabin pressurization will be

unavailable.

NOTE: CABIN ALTITUDE white annunciator may appear at 10,000 feet

300BPM-10-01 7

21-10-01-02 Cabin Pressurization System

C/1/0

(M) (O) May be inoperative provided:a) No cabin passengers are carried,b) CABIN PRESS switch is selected to DUMP and verified operative,c) Pull the OXY circuit breaker to disarm the passenger oxygen valve,d) Aircraft is operated at FL 250 or below, ande) Flight crew oxygen system is used as required by 14 CFR operating rule.

NOTE 1: When 300/300LW cabin pressure altitude reaches 12,000 to 12,500 feet, an “ALT WARN” (red) annunciator will illuminate.

NOTE 2: When B300/B300C pressure altitude reaches approximately 10,000 feet, the CABIN ALTITUDE (white) annunciator will illuminate. When the cabin pressure altitude exceeds 11,500 to 12,000 feet, a “CABIN ALT HI” (red) annunciator will illuminate.MAINTENCE PROCEDURE

Pull and secure the Oxy circuit breaker.OPERATIONAL PROCEDURE


2. Minimum enroute altitudes must be considered for the planned route.3. Place both Bleed Air Valves to ENVIR OFF.4. Place the Cabin Press switch to DUMP position.5. Passengers must be briefed prior to each flight that cabin pressurization will be

unavailable.

NOTE: CABIN ALTITUDE white annunciator may appear at 10,000 feet

21-20-01-01 Environmental Bleed Air Systems (Environmental)

C/2/1

(O) One may be inoperative provided:a) Environmental bleed air valve on inoperative side is verified closed prior to each flight,b) L or R BL AIR OFF amber annunciator is operative on the operative bleed air source,

andc) Aircraft is operated at or below Flight Level 250.

OPERATIONAL PROCEDURE

Prior to every flight, the pilot in command will verify the respective BL AIR OFF annunciator functions properly by selecting the operative bleed air switch to ENVIR OFF position and verifying the respective BL AIR OFF annunciator comes ON.

300BPM-10-01 8

21-20-01-02 Environmental Bleed Air Systems (Environmental)

C/2/0

(O) May be inoperative provided:a) Cabin pressurization system is considered inoperative, andb) Both environmental bleed air valves are verified CLOSED prior to each takeoff.


Select the BLEED AIR VALVE switches to the PNEU & ENVIR OFF position.

21-32-02 Safety/Outflow Valve

C/1/0

(M) May be inoperative provided:a) Affected valve is removed, or secured open, andb) Cabin Pressurization System is considered inoperative.

MAINTENANCE PROCEDURE

Refer to the B300 MM1. Remove outflow valve from its location and properly store. 2. Secure all electrical connections and cap all plumbing.

Secure Valve Open1. Install a 4 in long by ¼ in diameter peg between the valve and the seat.

NOTE: Care must be taken so as not to damage the interior or surrounding structure while removing the valve.

***21-40-00 Aft Heat System

D/1/0


Pull and secure circuit breaker 36 GROUND HEAT, located beneath the center floorboard, aligned with the fifth row of passenger seats. Doing so will disengage the ground heating mechanism rendering the system inoperative. System is only operation when the airplane is on the ground and the cabin temperature is 55°F (+5°F /-0°F) or below.

For FL-1, FL-4-492, FL-494-500:1. Remove the wires from the back of the Aft Heat switch.2. Cap each individual wire and stow and secure the wires.

300BPM-10-01 9

21-40-01 Electric Heat System

D/1/0


Pull and secure CB49 FWD ELECT HEAT and CB48 AFT ELECT HEAT circuit breakers.

21-60-00 Environmental Temperature Control System

C/1/0

(O) May be inoperative provided:a) Cabin Pressurization system is considered inoperative,b) Both Environmental Bleed Air Valves are verified closed prior to each flight, andc) Cabin temperatures remain suitable for operation.



2. Minimum enroute altitudes must be considered for the planned route.3. Place both Bleed Air Valves to ENVIR OFF.4. Place the Cabin Press switch to DUMP position.5. Passengers must be briefed prior to each flight that cabin pressurization will be unavailable.

NOTE: CABIN ALTITUDE white annunciator may appear at 10,000 feet.

22-10-01 Autopilot System (Collins Pro-Line 21 and Fusion)

C/-/0

(O) May be inoperative provided:a) Enroute procedures and approach minimums do not require use of autopilot system,b) Aircraft is not operated single-pilot,c) Autopilot is not used and AP button is not selected on the FGP,d) Rudder boost system is verified operative prior to each takeoff in accordance with the

airplane flight manual, ande) Aircraft is not operated RVSM.


Perform operational check of Rudder Boost per pilot checklist prior to each takeoff.

300BPM-10-01 10

22-10-01-01 Autopilot Mode Control Panel Switch Indicator Lamps (Collins FCS-65 Only)

C/-/0

(O) May be inoperative provided the affected model(s) is/are selected momentarily prior to departure to verify that proper Mode Annunciation is displayed on the pilot’s EFIS display or mode annunciator panel.OPERATIONAL PROCEDURE

1. Perform operational check of autopilot and flight director prior to each departure to verify proper mode annunciations are displayed on the pilot's panel, and

2. Verify that autopilot and flight director are responding correctly to mode selections.

22-10-10-02 Autopilot Mode Annunciator Panel lamps (Collins FCS-65 Only)

C/-/0

(O) May be inoperative provided the affected mode(s) is/are selected momentarily prior to departure to verify that proper Mode Annunciation is displayed on the pilot’s EFIS display.OPERATIONAL PROCEDURE

1. Perform operational check of autopilot and flight director prior to each departure to verify proper mode annunciations are displayed on the pilot's panel, and

2. Verify that autopilot and flight director are responding correctly to mode selections.

22-10-04 Autopilot/Flight Director Go-Around Button

C/1/0

(O) May be inoperative provided:a) Approach minimums do not require its use, andb) Alternate procedures are established and used to disconnect the autopilot and establish

initial pitch and wings level attitude.OPERATIONAL PROCEDURE

Manually disconnect autopilot prior to minimums. Crew must establish initial pitch and wings level attitude for GO-AROUND procedure.

300BPM-10-01 11

22-13-00 Flight Director System

C/-/0

(O) May be inoperative provided:a) Autopilot is verified operative, andb) Approach procedures do not require use of flight director.

NOTE: Any operative mode may be used.OPERATIONAL PROCEDURE

Perform operational check of autopilot and operative flight director modes prior to each departure to verify proper mode annunciations are displayed on the pilot's panel and that autopilot and flight director are responding correctly to mode selections.

22-13-01 Flight Director Mode Control Panel Switch Indicator Lamps (Collins FCS-65 Only)

C/-/0

(O) May be inoperative provided the affected mode(s) is/are selected momentarily prior to departure to verify that proper mode annunciation is displayed on the pilot’s EFIS display or mode annunciator panel.OPERATIONAL PROCEDURE

Perform operational check of autopilot and flight director prior to each departure to verify proper mode annunciations are displayed on the pilot's panel and that autopilot and flight director are responding correctly to mode selections.

22-13-02 Flight Director Mode Annunciator Panel Lamps (Collins FCS-65 Only)

C/-/0

(O) May be inoperative provided the affected mode(s) is/are selected momentarily prior to departure to verify that proper Mode Annunciation is displayed on the pilot’s EFIS display.OPERATIONAL PROCEDURE

Perform operational check of autopilot and flight director prior to each departure to verify proper mode annunciations are displayed on the pilot's panel and that autopilot and flight director are responding correctly to mode selections.

300BPM-10-01 12

23-10-01 High Frequency (HF) Communication System

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. Determine what available alternate communications is available, such as VHF or SATCOM.2. Ensure that you will have adequate communications coverage over the flight leg.3. On initial ATC contact on a flight leg that would otherwise use HF, advise ATC

of your communications limitations.

23-20-02-02 Selective Call Systems (SELCAL) (System or individual channel) (SELCAL required)C/-/0

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

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.

23-40-05 Passenger Seat Belt/Safety Chime

C/1/0

(O) May be inoperative provided cabin occupants are briefed by alternate means.OPERATIONAL PROCEDURE

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

300BPM-10-01 13

***23-40-06 Recorded Passenger Briefing System

D/1/0

(O) May be inoperative provided passengers are appropriately briefed.OPERATIONAL PROCEDURE

A crew member may use the PA system from the cockpit or verbally make the appropriate announcements.

23-50-02-02 Handheld Microphone Holder

D/-/0

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

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

***23-70-02 Active Noise Canceling System (STC SA483CH)

THIS STC IS NOT OWNED BY TEXTRON AVIATION. OPERATORS MUST CONTACT THE STC HOLDER FOR ASSISTANCE.

24-00-05 Standby Power System

B/1/0

(M) May be inoperative provided:a) Airplane is operated VFR only,b) Airplane is not operated at night, andc) Standby battery is disconnected and removed.


1. Ensure all aircraft power is off and no equipment is operating.2. Gain access to standby battery through the right-side avionics compartment door.3. Disconnect battery leads and remove battery.4. Cap and secure leads.5. Placard "Standby Battery Removed" on forward instrument panel.6. If necessary, make appropriate adjustments to airplane weight and balance.

300BPM-10-01 14

24-40-01 External Power System

C/1/0

(M) May be inoperative provided Ground Power Relay is verified open.MAINTENANCE PROCEDURE

1. Place the external power switch to the off position.

2. Pull and collar C/B 204 for the relay & C/B 205 for the sense line.

3. Verify external power is reading ZERO on the gauge and the busses do not power up.

24-50-01 Cabin AC Power System

C/1/0

(M) May be inoperative provided system is deactivated.MAINTENANCE PROCEDUREPull and secure C/B 270 Inverter Control located under the center floorboard, just aft of the wing spar.

***24-60-01 Isolated Instrumentation Bus (STC# SA03698AT)


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

C/1/0

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

Place required document(s) in a clear, plastic bag and relocate near the original location. A method to relocate can be taping the bag to the structure or any other non-destructive method.

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25-00-02-01 Cockpit/Cabin Partition Solid Doors

D/-/0

(O) May be inoperative provided affected door is secured in the taxi, takeoff and landing position.OPERATIONAL PROCEDURE

Secure solid doors open using tape or equivalent.

25-00-01-02 Cockpit/Cabin Partition, Curtains

D/-/0

(O) May be inoperative provided affected curtain is secured in the taxi, takeoff and landing position.OPERATIONAL PROCEDURE

Secure curtain open using tape or equivalent.

25-10-04-02 Flight Crew Seats Armrest(s)

C/4/0

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

1. Remove the affected armrest(s).a. If armrest is to be carried on-board, bag and stow.b. If armrest(s) is to be removed from the airplane, bag and stow for reinstallation.

25-10-04-01 Flight Crew Seat Recline/Tilt Function

C/1/0

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


Using the appropriate seat manual as a reference, secure the seat in the desired position.

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25-10-04-06-01 Flight Crew Seat Vertical Adjustment

C/1/0

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


Using the appropriate seat manual as a reference, secure the seat in the desired position.

25-20-00-01 Passengers Seat(s), Seat Controls (Includes recline, headrest, floor tracking, pedestal tracking, swivel and other positioning controls)

D/-/0

(M) May be inoperative and seat occupied provided seatback is secured in the taxi, takeoff and landing position.MAINTENANCE PROCEDURE

Reference the appropriate vendor component maintenance manual

1. If the recline mechanism is failed in the upright position and is locked in place, proceed to step 3.2. If the seat back is failed in any other position and not locked in place, the recline lock mechanism

must be manually locked with seat back in the upright position in the following manner:a. Remove the recline cylinder and replace with a same length fixed rod or bar using the

existing hardware.3. Place a placard stating "RECLINE INOP - DO NOT USE" on the front of the seat.

25-50-00 Cargo Restraint Systems

C/-/-

(M) May be inoperative, or missing provided acceptable cargo loading limits from an approved source, i.e., an approved cargo loading manual, cargo handling manual or weight and balance document are observed.MAINTENANCE PROCEDURE

1. Using the weight and balance section of the POH/AFM, load the aircraft according to approved loading zone and limitation data.

2. Any affected area must not have cargo loaded in that location.

300BPM-10-01 17

25-50-01-01 Cabin Storage Compartments/Closets

C/-/-

(M) May be inoperative provided:a) Procedures are established and used to secure compartment in the closed position,b) Affected compartment is prominently placarded “DO NOT USE”,c) Any emergency equipment located in affected compartment is considered inoperative, andd) Affected compartment is not used for storage of any item except for those permanently

affixed.MAINTENANCE PROCEDURE

1. Inoperative cabin and galley storage compartments and closets must be secured CLOSED as follows:a) Remove loose items from affected location (If affixed, the item(s) must be

relocated to another compartment or considered inoperative).b) Close and latch affected Compartment/Closet (or use silver tape if needed) to secure

affected door(s)/drawer(s) in CLOSED position.2. Place a placard stating "INOP-DO NOT USE" next to the affected component's

latch/handle assembly.

300BPM-10-01 18

25-50-01-02 Cabin Storage Compartments/Closets

C/-/-

(M)(O) May be inoperative provided:a) For non-retractable doors, affected door is removed. b) For retractable doors, affected door is removed or secured in the retracted (fully open)

position,c) Affected compartment is not used for storage of any items except for those permanently

affixed,d) Affected compartment is prominently placarded "DO NOT USE",e) Procedures are established and used to alert crew members and passengers of inoperative

compartments, andf) Passengers are briefed that affected compartment is not used

NOTE: Any permanently affixed Emergency Equipment located in the associated storage compartment is available for use. OPERATIONAL PROCEDURE

If no equipment is installed at the affected location (liquid containment, microwave, etc.) the affected door may be removed and stowed so it is not damaged. All contents located at the affected location must be removed and relocated.

If equipment listed in the above example is installed at the affected location the door may not be removed. The door is the certificated method to demonstrate mass properties containment.MAINTENANCE PROCEDURE

If no equipment is installed at the affected location (liquid containment, microwave, etc.) the affected door may be removed and stowed so it is not damaged. All contents located at the affected location must be removed and relocated.

If equipment listed in the above example is installed at the affected location the door may not be removed. The door is the certificated method to demonstrate mass properties containment.

25-50-01-03 Storage Compartments Key Locks

D/-/-

(M) May be inoperative in the unlocked position provided doors can be secured by other means.MAINTENANCE PROCEDURE

Before each departure, maintenance will insure that the associated latch is operative and door cannot be opened without use of the latch.

300BPM-10-01 19

***25-50-02 Wing Locker Door Gas Spring (Raisbeck Engineering STC only)


***25-62-01-02 Emergency Locator Transmitter (ELT), Fixed ELTs

A/-/0

(M) May be inoperative provided:a) System is deactivated, andb) Repairs are made within 90 days.c) Placard stating, “ELT not installed” is placed in view of the pilot.


Remove wire from pin 11 on plug 2371P3 and ensure ELT is armed.

***25-62-01-02 Emergency Locator Transmitter (ELT), Fixed ELTs

D/-/-

(M) May be inoperative provided: a) Any in excess of those required by 14 CFR may be inoperative provided system is

deactivated, andb) Placard stating, “ELT not installed” is placed in view of the pilot.



***25-62-01-03 Emergency Locator Transmitter (ELT), Remote Switch

D/1/0

(M) May be inoperative provided:c) Remote switch is disconnected from the ELT, andd) ELT is ARMED.



300BPM-10-01 20

27-21-00 Trim Tab Indicators (Rudder and Aileron)

C/2/0

(O) May be inoperative provided:a) Tab is visually checked for full range of operation,b) Tab operation is not restricted, andc) Tab is positioned to neutral prior to each departure and neutral position is verified by

visual inspection.

NOTE: Controls must be held neutral to determine tab settings.OPERATIONAL PROCEDURE

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.

27-30-00 Electric Elevator Trim System

C/1/0

(M) May be inoperative provided:a) Electric Trim is deactivated,b) Manual Trim is verified operative with full and free movement, andc) Autopilot is considered inoperative.


1. Pull and secure the PITCH TRIM circuit breaker.2. Operate all controls through their full range. No binding or resistance should be noted.3. Conduct a functional check of the manual trim system to determine proper operation,

full range of travel and freedom of movement.

27-51-00 Flap Position Indicator

C/1/0

(O) May be inoperative provided:a) Flaps are visually checked for full travel and flap operation is not restricted, andb) Flaps are visually checked for proper setting prior to each departure.


NOTE: STEEP APPROACHES ARE NOT PERMITTED

1. Conduct a functional check of the flap system to determine proper operation, full range of travel and freedom of movement.

2. Prior to takeoff, visually verify the flaps are in an allowable takeoff configuration.3. Landing with flaps up performance data should be considered.

300BPM-10-01 21

28-22-00 Standby Electric Boost Pumps

C/2/1

(M) One may be inoperative provided:a) Both engine driven low-pressure fuel boost pumps are operative,b) Affected pump is deactivated,c) AFM defined emergency engine fuels are not used, andd) Aircraft is not operated more than one hour, at one-engine-inoperative cruise, from a

suitable airport.MAINTENANCE PROCEDURE

Pull and secure affected circuit breaker STANDBY PUMP (CB12 – LEFT ENGINE, CB2 – RIGHT ENGINE) on the left side fuel control circuit breaker panel.

28-41-00 Fuel Quantity Indicator System

A/2/1

(O) One may be inoperative provided:a) A reliable means is established to determine that fuel quantity on board meets the

regulatory requirements for the flight,b) Both Fuel Flow Indicators are operative, andc) Both fuel low level indications (annunciator or CAS) are operative.d) Over water operations are limited to 30 min away from land at all times.


1. To achieve a known quantity in the affected tank, the tank may be defueled then fueled to a known quantity. It may be completely fueled, or fuel may be transferred out of the tank until it is empty.

2. 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.

300BPM-10-01 22

30-20-01-02 Engine Inertial Ice Vane Actuator Motors

C/4/0

(M) Both actuator motors of each Inlet may be inoperative provided:a) Inertial ice vanes are secured in the extended position,b) Appropriate ENGINE ANTI-ICE ON performance data is used, andc) Aircraft is not operated in POH/AFM defined engine ice protection conditions.


1. Fully manually extend the inertial ice vanes then pull and secure the following circuit breakers on the A146 cockpit circuit breaker panel: engine anti-ice, LEFT STBY circuit breaker on the L GEN bus or L STBY ENG ANTI-ICE, engine anti-ice RIGHT STBY circuit breaker on the R GEN bus or R STBY ENG ANTI-ICE, MN ENG ANTI-ICE LEFT, or L MAIN ENGINE ANTI-ICE and MN ENG ANTI-ICE RIGHT, or R MAIN ENGINE ANTI-ICE circuit breakers on the triple-fed bus on the right circuit breaker panel. (nomenclatures may vary depending on model)

2. Place a placard with the wording "Inertial Ice Vanes Secured in Extended Position", and place the placard on the forward instrument panel in clear view of the aircrew, and airplane limited to 10° C or colder.

30-40-10 Windshield Heat

C/2/0

(M) May be inoperative provided:a) Windshield heat is deactivated, andb) Aircraft is not operated in known or forecast icing conditions.


Pull and secure the circuit breaker for the windshield heating system.

***31-00-10 Engine Trend Condition Monitoring System

D/1/0

(O) May be inoperative provided alternate procedures are established and used for engine trend monitoring.


Operator must establish and use alternate procedures for Engine Trend Monitoring.

300BPM-10-01 23

***31-20-10 Flight Hour Recorder

C/-/0

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

1. A clock is used to record the flight time. Aircraft flight time is recorded in hours and minutes and then converted to hours and tenths and written on the flight log.

2. The maintenance personnel responsible for the aircraft's permanent maintenance logs shall record the time into summaries in the aircraft logbook, with special attention to the sequence of time to ensure that accurate times are recorded and tracked not only for the aircraft but also for other time limited maintenance items.

NOTE: A tenth of an hour is represented as 6 minutes. During conversion, it is necessary to round to the NEXT tenth of an hour. (Example: 122 Minute Flight time is recorded as 2.1 Hours).

31-40-01 Amber CHECK MAINTENANCE CAS Message Displayed(Collins Proline Fusion Equipped Airplanes)

C/1/0

(O) May be inoperative provided CHECK MAINTENANCE procedure in the AFM is followed to determine APM Fail message is displayed.

NOTE: Check Maintenance amber caution CAS message may be displayed.


Using the appropriate section of the AFM with Fusion avionics, follow the detailed procedure to check messages.

31-50-01-06 Annunciators Failure to Illuminate or Extinguish L or R BLEED FAIL Red Annunciator (B300 & B300C Only)

C/2/1

(O) May be inoperative provided:a) Environmental and instrument bleed air valves on inoperative side are verified closed prior

to each flight,b) Bleed Air Off Annunciator is operative on the operative bleed air source,c) Aircraft is operated at or below Flight Level 250, andd) Aircraft is not operated in known or forecast icing conditions.


1. Start the engine on the inoperative side, and with the other engine shutdown, select the inoperative BLEED AIR VALVE to the PNEU & ENVIR OFF position.

2. Verify the PNEUMATIC PRESSURE gauge indicates zero or near zero.3. Keep inoperative valve closed.

300BPM-10-01 24

31-50-01-09 Annunciators Failure to Illuminate or Extinguish GENERATOR BUS TIEorL or R GEN TIE OPEN Amber Annunciation

B/2/0

(O) May be inoperative provided:a) Affected generator bus tie relay is verified CLOSED prior to each departure, andb) Both DC GEN annunciators operative prior to each departure.


1. Rotate the VOLTMETER BUS SELECT switch through the L GEN, R GEN, CTR, and TPL FD positions.

2. Observe the voltages at each position for correct output (nominal 28 volts).3. Observe that the amber L DC GEN, R DC GEN, R GEN TIE OPEN, L GEN TIE OPEN, and

red INVERTER warning annunciators are NOT illuminated.

31-50-01-10 Annunciators Failure to Illuminate or Extinguish DC GENERATORorL or R DC GEN Amber Annunciation

B/2/1

(O) One may be inoperative provided both DC load meters are operative and monitored.OPERATIONAL PROCEDURE

A member of the flight crew will monitor the DC load meters during aircraft operations.

31-50-01-11 Annunciators Failure to Illuminate or Extinguish EXT PWR Amber Annunciation

C/1/0

(O) May be inoperative provided ground power is verified disconnected from aircraft prior to aircraft movement.


Prior to towing and/or taxi, a member of the flight crew must verify the ground power unit is not connected to the aircraft.

300BPM-10-01 25

31-50-01-14 Annunciators Failure to Illuminate or Extinguish L or R PITOT HEAT Amber Annunciator

C/-/0

(O) May be inoperative provided both pitot heaters are verified operative.OPERATIONAL PROCEDURE

Before each departure, flight crew will perform an operational check of the pitot heaters by engaging to ON and verifying heat form the pitot tubes.

CAUTION: Surface may be hot. Do not come into contact with skin as sever burning may occur. NOTE: Do not operate pitot heaters on ground for more than 5 min or damage may result.

31-50-01-15 Annunciators Failure to Illuminate or Extinguish HYD FLUID LOW Amber Annunciator

C/1/0

(M) May be inoperative provided hydraulic fluid level is verified full each flight day.MAINTENANCE PROCEDURE

A charging gauge is mounted on the landing gear accumulator. A fill reservoir, located above the power pack, contains a cap and dipstick assembly graduated in degrees of fluid temperature. Add hydraulic fluid as required to fill the system.

31-50-01-18 Annunciators Failure to Illuminate or Extinguish FUEL CROSSFEED Green Annunciation

C/1/0

(O) May be inoperative provided:a) Crossfeed system is verified operative prior to engine start, andb) Both fuel pressure annunciator lights are operative.


1. Position aircraft in a suitable engine operation location.2. Ensure aircraft is chocked and park brake is set.3. Start left engine.4. Select fuel Crossfeed from right tank to left engine.5. Ensure engine operates at all power settings.6. Select fuel Crossfeed off and shut down left engine.7. Repeat above steps for right engine with fuel Crossfeed selected from left tank to right

engine.

300BPM-10-01 26

31-50-01-19-01 Annunciators Failure to Illuminate or Extinguish L or R ENG ICE FAIL Amber Annunciator

C/2/1

(O) One may be inoperative on each side.OPERATIONAL PROCEDURE

Prior to each flight, the flight crew must verify operation of Ice Vane, and that the remaining annunciators are accurate.

31-50-01-19-02 Annunciators Failure to Illuminate or Extinguish L or R ENG ICE FAIL Amber Annunciator

C/2/0

(M) Both may be inoperative on one or both sides provided:a) Inertial ice vanes are secured in the extended position,b) Appropriate ENGINE ANTI-ICE ON performance data is used, andc) Ambient surface temperature is +10 degrees C or below for takeoff.


Manually extend the inertial ice vanes and secure in position. Reference 30-20 of the maintenance manual.

31-50-01-20-01 Annunciators Failure to Illuminate or Extinguish L or R ENG ICE FAIL Green Annunciator

C/2/1



31-50-01-20-02 Annunciators Failure to Illuminate or Extinguish L or R ENG ICE FAIL Green Annunciator

C/2/0

(M) Both may be inoperative on one or both sides provided:a) Inertial ice vanes are secured in the extended position,b) Appropriate engine anti-ice on performance data is used, andc) Ambient surface temperature is +10 degrees C or below for takeoff.



300BPM-10-01 27

31-50-02-03 CAS Messages Failure to Display or False Posting L - R Pitot Heat Amber CAS

C/-/0

(O) May be inoperative provided both pitot heaters are verified operative.OPERATIONAL PROCEDURE

Before each departure, flight crew will perform an operational check of the pitot heaters by engaging to ON and verifying heat form the pitot tubes.

CAUTION: Surface may be hot. Do not come into contact with skin as sever burning may occur. NOTE: Do not operate pitot heaters on ground for more than 5 min or damage may result.

31-50-02-04 CAS Messages Failure to Display or False Posting Hyd Fluid Low Amber CAS

C/1/0

(M) May be inoperative provided hydraulic fluid level is verified full each flight day.MAINTENANCE PROCEDURE

A charging gauge is mounted on the landing gear accumulator. A fill reservoir, located above the power pack, contains a cap and dipstick assembly graduated in degrees of fluid temperature. Add hydraulic fluid as required to fill the system.

31-50-02-07 CAS Messages Failure to Display or False Posting L or R Bleed Air Fail Amber CAS (B300 & B300C Only)

C/2/1

(O) May be inoperative provided:a) Environmental and instrument bleed air valves on inoperative side are verified closed

prior to each flight,b) BLEED AIR OFF CAS is operative on the operative bleed air source,c) Aircraft is operated at or below Flight Level 250, andd) Aircraft is not operated in known or forecast icing conditions.



2. Verify the PNEUMATIC PRESSURE gauge indicates zero or near zero.3. Keep inoperative valve closed.

300BPM-10-01 28

31-50-02-08 CAS Messages Failure to Display or False Posting L or R DC Generator Amber CAS

B/2/1

(O) One may be inoperative provided both DC load meters are operative and monitored.OPERATIONAL PROCEDURE

A member of the flight crew will monitor the DC load meters during aircraft operations.

31-50-02-09 CAS Messages Failure to Display or False Posting Ext Pwr-Active Amber CAS

C/1/0

(O) May be inoperative provided adequate ground power voltage is verified.


Prior to engaging ground power, verify proper voltage is available and set on the GPU. Refer to AFM/POH Limitations section for voltage requirements.

31-50-02-10 CAS Messages Failure to Display or False Posting Ext Pwr-Cart Amber CAS

C/1/0

(O) May be inoperative provided ground power unit is disconnected prior to aircraft movement.


Prior to towing and/or taxi, a member of the flight crew must verify the ground power unit is not connected to the aircraft.

31-50-02-13 CAS Messages Failure to Display or False Posting L-R Gen Tie Open Amber CAS

B/2/0

(O) May be inoperative provided:a) Affected Generator Bus Tie Relay is verified CLOSED prior to each departure, andb) Both DC GEN Annunciators are verified operative prior to each departure.


1. Rotate the VOLTMETER BUS SELECT switch through the L GEN, R GEN, CTR, and TPL FD positions.

2. Observe the voltages at each position for correct output (nominal 28 volts).

300BPM-10-01 29

31-50-02-14-01 CAS Messages Failure to Display or False Posting L or R Eng Ice Fail Amber CAS

C/2/1



31-50-02-14-02 CAS Messages Failure to Display or False Posting L or R Eng Ice Fail Amber CAS

C/2/0




31-50-02-15-01 CAS Messages Failure to Display or False Posting L or R Eng Ice Fail Cyan CAS

C/2/1



31-50-02-15-02 CAS Messages Failure to Display or False Posting L or R Eng Ice Fail Cyan CAS

C/2/0




300BPM-10-01 30

31-50-02-15-02 CAS Messages Failure to Display or False Posting Fuel Crossfeed Cyan CAS

C/1/0

(O) May be inoperative provided:a) Crossfeed system is verified operative prior to engine start, andb) Both fuel pressure annunciator lights are operative.


1. Position aircraft in a suitable engine operation location.2. Ensure aircraft is chocked and park brake is set.3. Start left engine.4. Select fuel Crossfeed from right tank to left engine.5. Ensure engine operates at all power settings.6. Select fuel Crossfeed off and shut down left engine.7. Repeat above steps for right engine with fuel Crossfeed selected from left tank to right

engine.

32-00-10 Landing Gear Control Down Lock Solenoid

C/1/0

(O) May be inoperative provided:a) Red down lock latch is visually verified engaged, andb) Down lock release button is verified operative.


Depress the red button on the landing gear handle downlock latch and visibly observe the release operation of the latch. Release the red button and ensure that the latch returns to the latched position.

32-40-01 Parking Brake

C/1/0

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

1. Parked aircraft must be chocked at all times.2. During engine start, PIC will apply normal braking and take precautions that all persons are

clear of the aircraft.3. Do not stop aircraft on a sloping ramp unless there is someone there to chock the airplane

while the PIC is holding the brakes, after engine shutdown.

300BPM-10-01 31

***32-40-02-01 Brake Deice System (300 & 300LW)

C/1/0

(M) May be inoperative provided:a) Brake de-ice bleed air valve is verified in closed position,b) Brake Deice system is deactivated, andc) “L/R BK DEICE ON” (green) annunciator is not illuminated.


Perform pressure test and functional test of brake deice system per 32-41-00-001 of the maintenance manual.

***32-40-02-02 Brake Deice System (B300 & 300C) (except Proline FUSION)

C/1/0

(M) May be inoperative provided:a) Brake de-ice bleed air valve is closed,b) Brake Deice system is deactivated, andc) “L/R BK DEICE ON” (green) annunciator is not illuminated.


1. Inspect brake deice components for cracks, obvious signs of wear and security.2. Inspect the distributor manifold located around each brake assembly for security.3. Inspect the flex hose for chaffing, cracks, security and other defects.4. Disconnect outlet side of affected brake deice shutoff valve. Cap valve with AN929-12J cap

and plug removed line with AN806-12J plug. Secure line. 5. Pull and secure CB82 brake deice circuit breaker on the A146 panel. Verify brake deice switch is

in the OFF position.6. Perform a check to determine that the system is OFF. With both engines operating note that

Brake Deice Light is extinguished.

300BPM-10-01 32

***32-40-02-03 Brake Deice System (B300 & B300C) (Proline FUSION Only)

C/1/0

(M) May be inoperative provided:a) Brake de-ice bleed air valve is closed,b) Brake Deice system is deactivated, andc) “L/R Brake Deice On” (cyan) annunciator is not illuminated.


1. Disconnect outlet side of affected brake deice shutoff valve. Cap valve with AN929-12J cap and plug removed line with AN806-12J plug. Secure line.

2. Pull and secure CB82 brake deice circuit breaker on the A146 panel. Verify brake deice switch is in the OFF position.

3. Perform a check to determine that the system is OFF. With both engines operating note that Brake Deice Light is extinguished.

4. Perform a check to determine that the rudder boost is not affected. With both engines running, reduce power on one engine to idle and advance power on the opposite engine. Movement of the rudder (high engine side) should occur. Repeat procedure in reverse sequence.

NOTE: See BE-300, BE-300LW FAA Approved Flight Manual for Limitations.

***32-41-01 Anti-Skid System (STC# SA03275CH)


33-20-03 Lighted Passenger Information Sign (Excluding cabin exit signs)

C/-/0

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

1. Notify the passengers before the flight that the signs are inoperative and that you will give the appropriate verbal commands from the cockpit during flight.

2. Utilize the passenger address (PA) system (If available) or keep the cockpit divider open during flight to be able to give verbal commands or authorizations to the passengers.

300BPM-10-01 33

***34-14-00-02 Airspeed Indicator (Mechanical Airspeed Indicators Only) (Except Collins Proline 21 or FUSION equipped aircraft), External Airspeed Indicator Bugs

C/-/0

(O) May be inoperative or missing.OPERATIONAL PROCEDURE

1. Aircrew will review critical airspeed information in the airplane f light manual prior to flight and at appropriate times in flight.

2. Aircrew may use a thin grease pencil, china marker, water-soluble marker, or other non-permanent marker to mark critical airspeed on A/S indicator glass, as long as such markings do not obstruct permanent instrument markings.

34-23-01-01 Non-Stabilized Magnetic Compass

B/1/0

(O) May be inoperative provided any combination of three Gyro, AHRS or INS (IRU) stabilized compass systems are operative.OPERATIONAL PROCEDURE

Ensure that combinations of three gyro or INS (IRU) stabilized compass systems are operative.


B/1/0

(O) May be inoperative provided:a) Any combination of two gyro, AHRS or INS (IRU) stabilized compass systems operate

normally, andb) Airplane is operated with dual independent navigation capability and under positive radar

control by ATC on the enroute portion of the flight.OPERATIONAL PROCEDURE

Ensure that either two gyros or INS (IRU) stabilized compass systems operate normally, or the airplane is operated with DUAL independent navigation capability and under positive radar control by ATC on the enroute portion of the flight.

300BPM-10-01 34


B/1/0

(O) May be inoperative for flights that are entirely within areas of magnetic unreliability provided at least two stabilized directional gyro systems are installed, operate normally, and used in conjunction with approved free gyro navigation techniques.OPERATIONAL PROCEDURE

Ensure that the flight will be entirely within areas of magnetic unreliability with at least two stabilized directional gyro systems installed and operating normally and free gyro navigation techniques are used

34-25-01-01 Electronic Flight Instrument System (EFIS) Multi-Function Display Unit (MFD) (Collins EFIS-85B Only), 3 Tube System

C/1/0

(O) May be inoperative provided the Multi-Function Processing Unit (MPU) is operative.OPERATIONAL PROCEDURE

Prior to flight, the flight crew will verify all remaining required displays are operative and brief the flight based on the configuration.

34-25-01-02 Electronic Flight Instrument System (EFIS) Multi-Function Display Unit (MFD) (Collins EFIS-85B Only), 5 Tube System

C/1/0

(O) May be inoperative provided the multi-function processing unit (MPU) is operative.OPERATIONAL PROCEDURE

Prior to flight, the flight crew will verify all remaining required displays are operative and brief the flight based on the configuration.

34-25-02-03 Adaptive Flight Display System (AFD) (Collins Pro Line Fusion Equipped Airplanes) Touchscreen Control

C/3/0

(O) May be inoperative provided:a) Touchscreen is inhibited on the inoperative display with the display control inhibit switch

on the reversion switch panel, andb) Both cursor control panels are operative.


Select Display Inhibit for inoperative Touchscreen on the reversion switch panel.

300BPM-10-01 35

***34-42-00-03 Weather Radar/Thunderstorm Detection Equipment Windshear Detection and Avoidance System (Predictive)

B/-/0

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

NOTE: Operator’s alternate procedures should include reviewing windshear avoidance and windshear recovery proceduresOPERATIONAL PROCEDURE

Operator must establish and use alternate procedures for Windshear detection and Avoidance procedures.

34-44-00-01 Terrain Awareness and Warning System (TAWS) (Class A TAWS Equipment Required by 14 CFR) Ground Proximity Warning System (GPWS)

A/1/0

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


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

2. Flight crew will review MEA, MSA, DH, MDA, as appropriate of the route being flown. 3. Flight manual and operating manual can be consulted for climb gradients available for the

phase of flight being approached, and the ambient conditions (weight, temp, altitude).

34-44-00-01-01 Terrain Awareness and Warning System (TAWS) (Class A TAWS Equipment Required by 14 CFR) Ground Proximity Warning System (GPWS), Modes 1-4

A/4/0

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

OPERATIONAL PROCEDURE1. Crew briefings will include aural callouts through use of appropriate aircraft equipment to

ensure obstacle and terrain clearance. 2. Flight crew will review MEA, MSA, DH, MDA, as appropriate of the route being flown. 3. Flight manual and operating manual can be consulted for climb gradients available for the


300BPM-10-01 36

34-44-00-01-05 Terrain Awareness and Warning System (TAWS) (Class A TAWS Equipment Required by 14 CFR) Ground Proximity Warning System (GPWS), Advisory Callouts

B/-/0


1. Crew briefings will include aural callouts during approach, through the use of appropriate aircraft equipment to ensure obstacle and terrain clearance.

2. Briefing should include MDA or DH, and procedure for one flight crewmember.to call out 500 feet above airport elevation, plus any other call outs agreed upon by the flight crew.

34-44-00-01-06 Terrain Awareness and Warning System (TAWS) (Class A TAWS Equipment Required by 14 CFR) Ground Proximity Warning System (GPWS), Advisory Callouts

C/-/0

(O) May be inoperative provided:a) Advisory callout not required by FAR andb) Alternate procedures are established and used.


NOTE: Reference FAR 91.233, FAR 135.154, TSOC151b, Pilot’s Guide for the GPWS installed in aircraft. Advisory callouts include:1. Bank Angle (some systems).2. “FIVE HUNDRED.”3. Altitude callouts intended to assist in the approach phase of flight (depending

on aircraft model and version).

Advisory callouts may also be referred to as “Mode 6” or “Altitude Callouts” in the GPWS Pilots Guide.

Crew briefings must include aural callouts during approach through the use of appropriate aircraft equipment to make sure 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, and any other agreed upon by the flight crew.

300BPM-10-01 37

***34-44-00-01-07 Terrain Awareness and Warning System (TAWS) (Class A TAWS Equipment Required by 14 CFR) Terrain Awareness and Warning System (TAWS) (Class A required by 14 CFR), GPWS, Windshear Warning and Flight Guidance System (Reactive)

C/-/0

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

NOTE: Operator’s alternate procedures should include reviewing windshear avoidance and windshear recovery procedure.OPERATIONAL PROCEDURE

1. Prior to each flight, ensure that the windshear detection and avoidance system operates normally.

2. Prior to each takeoff and prior to each approach, crew will obtain available weather reports to ensure windshear conditions are neither reported nor forecast in the aircraft flight path.

3. Crew briefings will include aural callouts through use of appropriate aircraft equipment, i.e., airspeed, IVSI, etc., and available weather reports for detection and prompt resolution of windshear encounter.

34-44-00-02 Terrain Awareness and Warning System (TAWS) (Class A TAWS Equipment Required by 14 CFR) Terrain System-Forward Looking Terrain Avoidance (FLTA) and Premature Descent Alert (PDA) Functions

B/1/0


NOTE: “Terrain Fail” message only affects the “Enhanced” GPWS function.OPERATIONAL PROCEDURE

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

34-44-01-01 Class B TAWS Equipment Required by 14 CFR operating rule GPWS

A/1/0

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



2. Flight crew will review MEA, MSA, DH, MDA, as appropriate of the route being flown. 3. Flight manual and operating manual can be consulted for climb gradients available for the


300BPM-10-01 38

34-44-01-01-01 Class B TAWS Equipment Required by 14 CFR operating rule Modes 1 & 3

A/2/0

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



2. Flight crew will review MEA, MSA, DH, MDA, as appropriate of the route being flown.3. Flight manual and operating manual can be consulted for climb gradients available for the


34-44-01-01-04 Class B TAWS Equipment Required by 14 CFR operating rule Advisory Callouts

B/-/0






300BPM-10-01 39

34-44-01-01-05 Class B TAWS Equipment Required by 14 CFR operating rule Advisory Callouts

C/-/0

(O) May be inoperative provided:a) Advisory Callouts not required by 14 CFR andb) Alternate procedures are established and used.






***34-44-01-01-06 Class B TAWS Equipment Required by 14 CFR operating rule Windshear Mode (Reactive)

C/1/0


1. Prior to each flight ensure that the windshear detection and avoidance system operates normally.

2. Prior to each takeoff and prior to each approach, crew will obtain available weather reports to ensure windshear conditions are neither reported nor forecast in the aircraft flight path.

3. Crew briefings will include aural callouts through use of appropriate aircraft equipment, i.e., airspeed IVSI etc., and available weather reports for detection and prompt resolution of windshear encounter.

300BPM-10-01 40

***34-44-02-01Class C TAWS Equipment Not Required by 14 CFR Operating Rule TAWS/GPWS

C/1/0


NOTE 1: Any mode that operates normally may be used.

NOTE 2: If TEST mode is inoperative, TAWS/GPWS must be considered Inoperative.OPERATIONAL PROCEDURE


2. Flight crew will review MEA, MSA, DH, MDA, as appropriate of the route being flown.3. Flight manual and operating manual can be consulted for climb gradients available for the


34-44-02-02-10 Class C TAWS Equipment Not Required by 14 CFR Operating Rule Advisory Callouts

B/-/0


NOTE: Reference FAR 91.233, FAR 135.154, TSOC151b, Pilot’s Guide for the GPWS installed in aircraft. Advisory callouts include:

1. Bank Angle (some systems).2. “FIVE HUNDRED.”3. Altitude callouts intended to assist in the approach phase of flight (depending




300BPM-10-01 41

34-44-02-02-20 Class C TAWS Equipment Not Required by 14 CFR Operating Rule Advisory Callouts

C/-/0

(O) May be inoperative provided:a) Advisory Callouts not required by 14 CFR andb) Alternate procedures are established and used.


NOTE: Reference FAR 91.233, FAR 135.154, TSOC151b, Pilot’s Guide for the GPWS installed in aircraft. Advisory callouts include:

1. Bank Angle (some systems).2. “FIVE HUNDRED.”3. Altitude callouts intended to assist in the approach phase of flight (depending




34-44-04 Radio Altimeter

C/-/0

(M) (O) May be inoperative provided:a) Radio Altimeter is deactivated,b) Class A TAWS and/or GPWS are considered inoperative,c) TCAS II is considered inoperative,d) Approach procedures do not require its use, ande) Alternate procedures are established and used.


Pull and secure the RADIO ALTM circuit breaker on the right-side circuit breaker panelOPERATIONAL PROCEDURE

Pre-Flight planning shall include the inoperative radio altimeter and operations must not require the use of TCAS, TAWS or GPWS.Copilot will call out altitudes during approach including minimum altitudes.

NOTE: TCAS II is inoperative and red RA flag on the PFD will remain.

NOTE: As per Part 91, Appendix A, a radio altimeter or marker beacon receiver providing aural and visual indications of the inner marker is required for Category II and Category Ill operations with decision heights below 150 feet.

300BPM-10-01 42

34-45-00 Traffic Alert and Collision Avoidance System (TCAS I)

B/-/0

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


Pull and secure the CB 120 “TCAS" circuit breaker located on the right-side circuit breaker panel.

34-45-00-01 Traffic Alert and Collision Avoidance System (TCAS I)

C/-/0

(M) May be inoperative provided:a) Not required by 14 CFR operating rule,b) System is deactivated and secured, andc) Enroute or approach procedures do not require its use.


Pull and secure the CB 120 “TCAS" circuit breaker.

34-45-10 Traffic Alert and Collision Avoidance System (TCAS II)

B/-/0

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



34-45-10-01 Traffic Alert and Collision Avoidance System (TCAS II)

C/-/0

(M) May be inoperative provided:a) Not required by 14 CFR operating rule,b) System is deactivated and secured, andc) Enroute or approach procedures do not require its use.



300BPM-10-01 43

34-45-10-03 Traffic Alert and Collision Avoidance System (TCAS II) Resolution Advisory (RA) Display System(s)

C/-/0

(O) May be inoperative provided:a) Traffic Alert (TA) visual display and audio functions are verified operative,b) TA ONLY mode is selected by the crew, andc) Enroute or approach procedures do not require its use.


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

2. Select TA only mode of operation.

***34-52-01-05 ATC Transponders and Automatic Altitude Reporting Systems, ADS-B Squitter Transmissions

C/-/0


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

For flight planning purposes, the flight crew will not file as ADS-B compliant.

***34-52-10-01-01 Automatic Dependent Surveillance-Broadcast (ADS-B) System

C/-/0

(O) May be inoperative provided: a) Alternate procedures are established and used, and b) It is not required by 14 CFR.

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


300BPM-10-01 44

***34-52-10-02-01 Automatic Dependent Surveillance-Broadcast (ADS-B) System ADS-B Out Extended Squitter Transmissions

C/-/0

(O) May be inoperative provided: a) Alternate procedures are established and used, b) Authorization is obtained from ATC facilities having jurisdiction over planned route of

flight, andc) It is not required by 14 CFR.



***34-52-10-03-01 Automatic Dependent Surveillance-Broadcast (ADS-B) System ADS-B Out UAT Transmissions

C/-/0





***34-52-10-04-01 Automatic Dependent Surveillance-Broadcast (ADS-B) System ADS-B in Transmissions

C/-/0





300BPM-10-01 45

35-00-01 External Oxygen Gauge

C/1/0

(M) May be inoperative provided the internal oxygen gauge is monitored during servicing to avoid over-servicing.MAINTENANCE PROCEDURE

A crewmember or qualified mechanic shall occupy the cockpit and monitor the oxygen pressure while another maintenance personnel services the oxygen.

35-20-00-03 Passenger Oxygen Mask

C/-/0

(M) May be inoperative provided:a) Corresponding Passenger Seat is blocked and placarded “DO NOT OCCUPY”, andb) Affected Mask does not permit flow when Cabin Oxygen System is activated.


1. If necessary, remove the affected mask cover (lid).2. Using a tie wrap or other appropriate device, secure the affected mask lanyard to the

shutoff valve.3. Replace the cover (lid) provided the cover is not being deferred in addition to the mask.

37-10-00 Instrument Air Valve (B300 & B300C Only)

C/2/1

(O) One may be inoperative provided:a) Inoperative Valve is verified closed,b) Aircraft is not operated in known or forecast icing conditions, andc) Aircraft is operated at or below Flight Level 250.



2. Verify the PNEUMATIC PRESSURE gauge indicates Zero or near zero.3. Keep inoperative valve closed.4. Do not operate aircraft in known or forecast icing conditions.5. Operate aircraft at or below FL250.

300BPM-10-01 46

***46-00-01 Electronic Flight Bag Systems (EFB) (excludes PED EFB)

C/-/0

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

NOTE 1: If alternate procedures involve electronic devices, dual redundancy is required for operation.

NOTE 2: Any function, program or document which operates normally may be used.OPERATIONAL PROCEDURE

If affected EFB cannot be safely secured in the cockpit and accessible to the flight crew the use of a second EFB or paper manuals must be readily available.

NOTE: If more than One EFB are installed and operative, dual redundancy is required.

***46-00-01-02 Electronic Flight Bag Systems (EFB) (excludes PED EFB), Power Connection (Class 1 & 2)

C/-/0


Pilot-In-Command will verify EFB internal power supply and/or external battery backup source is fully charged and adequate for duration of planned flight.

***46-00-01-03 Electronic Flight Bag Systems (EFB) (excludes PED EFB), Mounting Device (Class 2)

C/-/0

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

the aircraft andb) Alternate procedures are established and used.


If EFB mounting device has the possibility to interfere with flight crew duties it must be removed before flight and stowed in the cargo compartment or ballast. If not, secure in a position that will not interfere with flight crew.OPERATIONAL PROCEDURE

If EFB cannot be safely secured in the cockpit and accessible to the flight crew the use of paper, manuals must be readily available.

300BPM-10-01 47


D/-/0

(M) (O) May be inoperative provided:a)The associated EFB and hardware is secured by an alternate means or removed from the

aircraft andb)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

Utilize the Information from remaining operative EFB.


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.


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.

300BPM-10-01 48

46-10-10-01 Integrated Flight Information System (Pro Line 21 IFIS-5000) File Server Unit (FSU) (FSU INOP Message)

C/1/0

(O) May be inoperative provided alternate procedures are established and used to ensure all information pertinent to the flight is accessible at the pilot station in current and appropriate form.

NOTE: If alternate source is electronic, dual redundancy is required for operation.


Each operator will develop a method to provide the most current navigation product to the flight crew and make it accessible during the flight.

46-10-10-02 Integrated Flight Information System (Pro Line 21 IFIS-5000) Right Side Cursor Control Panel (CCP)

C/1/0

(O) May be inoperative provided alternate procedures are established and used to ensure all information pertinent to the flight is accessible at the pilot station in current and appropriate form.

NOTE 1: If alternate procedures involve electronic devices, dual redundancy is required for operation.

NOTE 2: CCP 2 Inop amber CAS message may be displayed.


1. Traditional paper data will be carried and used for intended flight, or2. Operations are to be conducted in accordance with FAA approved EFB Policy and

procedures manual.

***46-10-10-03 Integrated Flight Information System (Pro Line 21 IFIS-5000), Communications Management Unit (CMU)

C/1/0

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

Weather data for the intended flight path including alternates shall be obtained prior to departure.

300BPM-10-01 49

46-10-10-04 Integrated Flight Information System (Pro Line 21 IFIS-5000), Third VHF Communications Radio

C/1/0

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

Weather data for the intended flight path including alternates shall be obtained prior to departure.

46-10-20-01 File Server Application (FSA) (Pro Line FUSION FSA-5000), FSA Integrated Flight Information System (Includes Map, Charts, XM Graphical Weather, and Datalink Graphical Weather)

C/-/0

(O) May be inoperative provided alternate procedures are established and used to ensure all information associated with the flight is available at the pilot station in current and appropriate form.

NOTE 1: If alternate source is electronic, dual redundancy is required for operation.

NOTE 2: The following CAS Messages may be displayed: PFD 1 IFIS Inop, MFD IFIS Inop, or PFD 2 IFIS Inop.

NOTE 3: The following messages may be displayed: Chart Not Available, Graphical Weather Not Available, XM Graphical Weather Not Available, or Map Not Available.



46-10-20-02 File Server Application (FSA) (Pro Line FUSION FSA-5000), IFIS Databases, If Installed (Terminal Charts, XM Weather, Enhanced Maps, and Datalink WXR)

C/-/0

(O) May be inoperative provided alternate procedures are established and used to ensure all information associated with the flight is available at the pilot station in current and appropriate form.



300BPM-10-01 50

46-40-12 Baro Single Knob Panel (SKP) (Proline FUSION Only)

C/2/1

(O) May be inoperative provided Baro is in SYNC Mode on the Display Setup Page of the system menu.


This procedure is available in the Pro Line Fusion for King Air Quick Reference Guide, 523-0822518.

52-10-01 Cabin Door Snubber

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 that the main cabin door snubber is inoperative.2. When opened, the step cable should be used to ease the step down until it is fully deployed

and the stay is resting on the fuselage. Do not allow the door to freefall.3. Brief ground crew of inoperative snubber to prevent injury to ground crew or damage to door.

52-70-01 Cabin Door Warning System

C/1/0

(O) May be inoperative provided flight crewmember confirms by visual inspection that the cabin door is closed, latched and locked prior to each takeoffOPERATIONAL PROCEDURE

Prior to aircraft operations, a member of the flight crew will visually verify the cabin door is closed, latched, and locked.

52-70-02 Cabin Door Lock and Upper Door Latch Observation Light System

C/1/0

(O) May be inoperative provided a crewmember confirms, by visual inspection, using a flashlight that latches are in the locked position prior to each departure.OPERATIONAL PROCEDURE

Prior to aircraft operations, a member of the flight crew will use a flashlight to visually verify the cabin door is closed, latched, and locked.

300BPM-10-01 51

73-31-00 Fuel Flow Indicators

B/2/1

(M) One may be inoperative provided both fuel quantity indicating systems are operative and transducer is not leaking.MAINTENANCE PROCEDURE

With the aircraft positioned on a level surface, apply electrical power to the aircraft and verify that the cockpit fuel quantity indicators are operative and fuel quantity onboard correlates to that indicated by the FQIS. Verify fuel flow transducer is not leaking.

300BPM-10-01 52

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