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Beechcraft ProceduresManual

Textron Aviation Beechcraft Model 300

300 (including FF Serials), 300LW, B300, B300C

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

AVIATION ADMINISTRATION - REVISION 9 DATED 08/28/2016.

COPYRIGHT © 2015 MMEL REVISION 9Textron AviationWICHITA, KANSAS, U.S.A.

COMP REVISION 01

300BPM-09-01

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.

300BPM-09-01 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.

300BPM-09-01 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-09-01 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-09-01 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-09-01 5

Page Intentionally Left Blank

300BPM-09-01 6

21-00-01 Cabin Altitude Annunciator System (white)(CABIN ALTITUDE) Ann. Only(B300 & B300C Only), (Except Proline FUSION)

C/1/0

(O) May be inoperative provided aircraft is configured and operated unpressurized.OPERATIONAL PROCEDURE

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

21-00-02 Cabin Altitude Annunciation (red) (ALT WARN)or(CABIN ALT HI)(Cabin Alt High) CAS

C/1/0



21-00-03 Cabin Differential High Annunciation (red),(CABIN DIFF HI) Ann.(Cabin Diff High) CAS, (B300 & B300C Only)

C/1/0



21-00-04 Cabin Altitude Warning Horn System (B300 & B300C Only)

C/1/0



300BPM-09-01 7

21-00-06 Bleed Air Fail Annunciator System, (L or R BLEED FAIL) Ann.(L or R BLEED AIR FAIL) CAS, (B300 & B300C Only), (Illuminates or Fails to Illuminate)

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) “BL AIR OFF” (amber) 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.

OPERATIONAL PROCEDURE

(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.

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) “BL AIR OFF” (amber) annunciator is operative on the operative bleed air source, andc) Aircraft is operated at or below Flight Level 250.


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.

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

C/2/0

(O) May be inoperative provided:a) Aircraft is configured and operated unpressurized, andb) Both Environmental Bleed Air Valves are verified closed prior to each flight.



300BPM-09-01 8

21-31-01 Cabin Pressurization System (Pressurization Control)

C/1/0

(O) May be inoperative provided:a) Cabin Dump is verified operative,b) CABIN PRESS switch is selected to DUMP,c) Red Cabin Altitude Warning is operative, andd) Aircraft is operated at 10,000 feet pressure altitude or below.

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 taken into account 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

21-32-01 Differential Pressure/Cabin Altitude Indicator

C/1/0



21-32-02 Cabin Rate of Climb Indicator

C/1/0



300BPM-09-01 9

21-33-01 Outflow Valve

C/1/0

(M) May be inoperative provided:a) Outflow Valve is secured open, andb) Cabin Pressurization System is considered inoperative.

MAINTENANCE PROCEDURE

The outflow valve cannot be secured open. It must be removed from its location and properly stored or stowed. All electrical connections must be secured and all plumbing must be capped and secured. Care must be taken so as not to damage the interior or surrounding structure while removing the valve.

21-33-02 Safety Valve

C/1/0

(M) May be inoperative provided:a) Safety Valve is secured open, andb) Cabin Pressurization System is considered inoperative.


The safety valve cannot be secured open. It must be removed from its location and properly stored or stowed. All electrical connections must be secured and all plumbing must be capped and secured. Care must be taken so as not to damage the interior or surrounding structure while removing the valve.

21-40-01 Aft Heat System

C/1/0

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

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-09-01 10

21-40-02 Electric Heat System

D/1/0

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

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

21-50-01 Vapor Cycle Air Conditioning System

C/1/0

(M) May be inoperative provided the vapor cycle air conditioning system is deactivated.MAINTENANCE PROCEDURE

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

21-50-02 Ground Air Cooling System

D/1/0

(M) May be inoperative provided the ground air cooling system is deactivated.MAINTENANCE PROCEDURE

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

21-60-01 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.


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. 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-09-01 11

22-10-00 Autopilot System

C/-/0

(M) May be inoperative provided:a) Autopilot is not used,b) Rudder boost system is verified operative prior to each takeoff in accordance with the

airplane flight manual,c) Operations do not require use of autopilot, andd) Aircraft is not operated RVSM.


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

22-10-00-01 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.

22-10-00-02 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.

300BPM-09-01 12

22-10-03 Autopilot Control Wheel Disengage Switches (AP/YD/RB/TRIM DISC)

B/-/0

(M) May be inoperative provided:a) Autopilot is considered inoperative,b) Electric Elevator Trim is considered inoperative, andc) Yaw Damp is considered inoperative.

MIANTENACE PROCEDURE

Maintenance procedure to ensure no electrical/mechanical fault exists that would have an adverse effect on any Flight Control function.

22-10-02 Yaw Damper (B300, B300C)

C/1/0

(M) May be inoperative provided aircraft is operated at or below 5,000 feet MSLMAINTENANCE PROCEDURE

Perform operational check of autopilot to verify proper operation of autopilot with Yaw Damper inoperative.

22-10-02 Yaw Damper

C/1/0

(M) May be inoperative provided:a) STC SA5151NM (Raisbeck Engineering Dual Aft Body Strakes) is installed, andb) Aircraft is operated at or below 19,000 feet MSL.


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

300BPM-09-01 13

22-10-02 Yaw Damper (300, 300LW with Raisbeck Engineering Dual Aft Body Strakes)

C/1/0

(M) May be inoperative provided:a) STC SA4733NM (Raisbeck Engineering Dual Aft Body Strakes) is installed, andb) Aircraft is operated at or below 18,500 feet MSL.



22-10-02 Yaw Damper (300,300LW)

C/1/0

(M) May be inoperative provided aircraft is operated at or below 11,000 feet MSL.MAINTENANCE PROCEDURE

Perform operational check of autopilot to verify proper operation of autopilot with Yaw Damper inoperative.

22-10-04 Autopilot Control Wheel Disengage Switches (AP/YD/RB/TRIM DISC)

B/-/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

Flight Director is not available for Takeoff or Go-Around with both TO/GA buttons inoperative. Flight crew shall use raw data for takeoff and go-around. For takeoff, once airborne and above 500 ft AGL, pilot-not-flying (PNF) shall select desired lateral mode (HDG or LNAV) on guidance panel as directed by pilot-flying (PF). Additionally, PNF shall select desired vertical mode (FLCH or VS or FPA) as directed by PF. For go-around, after flaps and landing gear have been retracted and airplane is above 500 ft AGL, PNF shall select desired lateral mode (HDG or LNAV) and vertical mode (FLCH or VS or FPA) on guidance panel at direction of PF.

300BPM-09-01 14

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.

***23-00-02-03 Flight Phone System, Automatic Flight Reporting Functions

D/-/0

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

Each operator must determine the most appropriate method to report any necessary data to the respective recipient.

300BPM-09-01 15

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.

23-20-01 Selective Call Systems (SELCAL)

C/-/0


1. In a flight plan where SELCAL may otherwise have been used make a comment in the flight plan "No SELCAL" so ATC is alerted.

2. Determine what appropriate HFNHF frequencies may be used on the flight leg.3. Upon first contact with ATC on an extended leg where SELCAL would be use advise

them that your SELCAL is inoperative and determine what the correct HFNHF frequency for that leg is.

23-20-01-01 Selective Call Systems (SELCAL), Channels

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.

300BPM-09-01 16

23-40-01 Cabin Interphone System (FF-serials Only)

C/2/0

(O) May be inoperative provided:a) Cockpit speakers are operative andb) Alternate normal and emergency procedures and/or operating restrictions are established

and used.OPERATIONAL PROCEDURE

Cabin crew will use the PA system for any required communications that the interphone system would normally be used for.

23-40-02-01 Crewmember Interphone System (Flight Deck to ground)

C/1/0

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

Crew members will establish communication with ground crew using another means, such as hand signals, cell phone, handheld radio, etc.

23-40-03-01 Passenger Address System (PA) Passenger Configuration

C/1/0

(O) May be inoperative provided alternate, normal, and emergency procedures and/or operating restrictions are established and used.OPERATIONAL PROCEDURE

Alternate procedures for passenger announcements must be established and used.

23-40-03-02 Passenger Address System (PA) Cargo Configuration

C/1/0

(O) May be inoperative provided alternate, normal, and emergency procedures and/or operating restrictions are established and used.OPERATIONAL PROCEDURE

Alternate procedures for passenger announcements must be established and used.

300BPM-09-01 17

***23-40-04 Recorded Passenger Briefing System

D/1/0

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

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

23-40-05 Passenger Seat Belt/Safety Chime (chime only)

C/1/0

(O) May be inoperative provided:a) Passenger address system is operative, andb) Alternate procedures are established and used for passenger seat belt briefing.


A crew member must use the PA system from the cockpit to 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)

D/1/0

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


300BPM-09-01 18

24-00-02 Generator Bus Tie Annunciation (amber), (L or R GEN TIE OPEN) Ann. (L or R or L-R Gen Tie Open) 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).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.

24-00-04 External Power Annunciation (amber), (EXT PWR) Ann. (Ext Pwr-Active or Ext Pwr-Cart) CAS

C/1/0

(O) May be inoperative provided alternate procedure is established and used.


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

24-01-01 Standby Power System

B/1/0

(M) May be inoperative provided:a) Airplane is operated day VFR only, andb) 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-09-01 19

24-40-01 External Power System

C/1/0

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

PULL and secure circuit breaker External Power Control.

Note: Before connecting an external power unit, turn all radio equipment, the generator switches, the battery switch, and the external power switch to OFF. Place the overhead voltmeter select switch in the EXT PWR position.

CAUTION: Voltage is required to energize the avionics master power relays to remove the power from the avionics equipment; therefore, never apply external power to the airplane without first applying battery voltage.

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.

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

C/-/0

(M) May be inoperative if secured in the full open (stowed) position.MAINTENANCE PROCEDURE

Secure solid doors open using tape or equivalent.

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

C/-/0

(M) May be missing or stowed in the full open position.MAINTENANCE PROCEDURE

Remove or secure partition curtains open using tape or equivalent.

300BPM-09-01 20

25-10-04-01 Flight Crew Seats Armrest(s)

C/-/0

(M) May be inoperative provided affected armrest is secured in the up position.MAINTENANCE PROCEDURE

1. Move the affected armrest to the full up or down position.2. Secure the armrest in place with strong cord or tape, making sure that the method, which

is used to secure the armrest, does not interfere with crew movement or operations of any panels and/or controls.

3. If it is not possible to move the armrest to the full up or full down position, remove and securely stow the armrest.

25-10-04-04 Flightcrew Seats, Seat Adjustment

A/-/0

(M) May be inoperative provided:a) Affected Seat is locked in a position that permits normal pilot visibility,b) Full Flight Control movement is available to the flightcrew,c) Position of the affected Seat is acceptable to the flightcrew, andd) Repairs are made within 1 flight day.


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

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

300BPM-09-01 21

25-20-01-01 Passengers Seat(s), Seat Controls (Recline, Swivel, or Tracing)

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.

25-20-04 Flight Inspection Panel Equipment (FF Serials Only)

D/1/0

(M) May be inoperative provided:a) Operation is not dependent on its use, andb) Affected equipment is deactivated.


Operator to develop procedure to deactivate defective system or component.

300BPM-09-01 22

25-30-01 Refreshment Cabinet Waste Receptacles Access Doors/Covers

C/-/-

(M)(O) May be inoperative provided:a) Container is empty and the access is secured to prevent waste introduction into the

compartment, andb) Procedures are established to ensure that sufficient Galley Waste Receptacles are

available to accommodate all waste that may be generated on a flight.MAINTENANCE PROCEDURE

Secure the Cabin Storage Compartment Door.

1. Put the cabin storage compartment door in the closed position.

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

Carefully attach sufficient lengths of 3M vinyl tape (or equivalent) across the door opening at a 90-degree angle to make sure that the door does not open during airplane operation.


Prior to each takeoff, a member of the flightcrew will brief all cabin occupants to use the alternate method of waste containment the operator has determined to be acceptable.

25-50-01 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-09-01 23

25-50-02 Cabin Storage Compartments/Closets

C/-/-

(M) May be inoperative provided:a) Procedures are established to secure compartment closed,b) Associated compartment is 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(s) 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-09-01 24

25-50-02 Cabin Storage Compartments/Closets

C/-/-

(M)(O) May be inoperative provided:a) Affected door is removed,b) Associated compartment is not used for storage of any items, except those permanently

affixed,c) Associated compartment is placarded “DO NOT USE”, andd) Passengers are briefed that associated 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.

300BPM-09-01 25

25-50-02-01 Storage Compartments Key Locks

D/-/-

(M) May be inoperative in the unlocked position provided door latch remains operative.MAINTENANCE PROCEDURE

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

***25-62-00-03 Emergency Locator Transmitter (ELT), Remote Switch

D/1/0

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


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

27-31-01 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. Operate all controls through their full range. No binding or resistance should be noted.2. Conduct a functional check of the manual trim system to determine proper operation,

full range of travel and freedom of movement.

300BPM-09-01 26

27-31-01-03 Electric Elevator Trim System, Pitch Trim ON-OFF Switch

C/1/0

(M) May be inoperative provided:a) Electric Pitch Trim is deactivated,b) Manual Trim is verified operative, andc) Autopilot is considered inoperative.


1. Operate all controls through their full range. No binding or resistance should be noted.2. Conduct a functional check of the manual trim system to determine proper operation, full

range of travel and freedom of movement.3. Pull and collar the PITCH TRIM circuit breaker on the right side breaker panel.

28-22-01 Standby Electric Boost Pumps

C/2/1

(M) One may be inoperative provided:a) Affected pump is deactivated,b) AFM defined Emergency Engine Fuels are not used,c) AFM Limitations On Use Of Aviation Gasoline are observed, andd) Aircraft is not operated more than 1 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.

28-41-10 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 Quantity Annunciators are operative.


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-09-01 27

30-00-20 Engine Ice Vane Annunciation, (L or R ENG ICE FAIL) Ann. (amber), (L and R ENG ANTI-ICE) Ann. (green), (L or R Engine Ice Fail) CAS (amber), (L or R Engine Anti-Ice) CAS (cyan)

C/4/2

(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.

30-00-20 Engine Ice Vane Annunciation, (L or R ENG ICE FAIL) Ann. (amber), (L and R ENG ANTI-ICE) Ann. (green), (L or R Engine Ice Fail) CAS (amber), (L or R Engine Anti-Ice) CAS (cyan)

C/4/0

(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.

30-20-01 Engine Inertial Ice Vane Actuator Motors

C/4/2

(O) One Actuator Motor on each inlet may be inoperative provided aircraft is not operated in visible moisture at +5 degrees C or below.


Do not fly into known or forecasted icing.

300BPM-09-01 28


C/4/2

(O) One Actuator Motor on each inlet may be inoperative provided:a) Inertial Ice Vanes are in the extended position,b) Appropriate Engine Anti-Ice On Performance Data is used, andc) Ambient temperature is +10 degrees C or below for takeoff.


1. Prior to each departure the flight crew will verify the Inertial Ice Vanes are in the extended position.

2. Flight crew will use the appropriate performance data for Engine Anti-Ice On for all phases of flight.

3. Flight crew will ensure that the ambient temperature is +10 degrees C or below for all phases of flight.


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) Ambient temperature is +10 degrees C or below for takeoff on B300 aircraft only.


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.

300BPM-09-01 29

30-30-01-01 Pitot Heat Annunciation (amber), (L or R PITOT HEAT)Ann., (L or R Pitot Heat) 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.

31-20-10 Flight Hour Recorder

C/1/0

(O) May be inoperative provided alternate procedures are established and used to track flight time.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 Aircraft Personality Module, (APM Fail) CAS, (Pro Line Fusion Only)

C/1/0

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


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

300BPM-09-01 30

31-40-12 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.

32-30-01 Hydraulic Fluid Low Annunciation (amber),(HYD FLUID LOW) Ann.,(Hyd Fluid Low) 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. Reference maintenance manual 12-10-05

32-34-10 Landing Gear Control Down Lock Solenoid

C/1/0

(O) May be inoperative provided:a) Down lock latch is verified operative, 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.

300BPM-09-01 31

32-40-01 Parking Brake

C/1/0

(O) May be inoperative provided alternate procedures are established and used to prevent unintended movement when stopped or parked.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.

***32-40-10 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.

***32-40-10 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-09-01 32

***32-40-10 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.

33-20-01 Passenger Notice Signs (Fasten Seat Belt) (No Smoking)

C/-/0

(O) May be inoperative provided alternate procedures are established and used to verbally brief the passengers.OPERATIONAL PROCEDURE

1. Notify the passengers before the flight that the NO SMOKING and FASTEN SEAT BELT 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-09-01 33

33-20-10 Cabin Lights

C/-/-

(O) May be partially inoperative provided:a) Cabin Emergency Exit Lighting is operative,b) Sufficient Lighting is available for crew to perform required duties,c) Sufficient Lighting is operative for passenger carrying operations at night, andd) Both Cabin Exit Lights are operative.


During the Cockpit/Cabin Inspection, make sure all Emergency Exit and Cabin Exit lights are operative.

***34-14-00-01 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.

34-16-20 Altitude Alerting System

A/-/0

(O) May be inoperative provided:a) Autopilot with Altitude Hold is operative,b) Aircraft is not operated RVSM,c) Enroute operations do not require its use, andd) Repairs are made within 3 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.

300BPM-09-01 34

34-16-20 Altitude Alerting System

A/-/0

(O) May be inoperative provided:a) Aircraft is operated with a Second-in-Command,b) Aircraft is not operated RVSM,c) Enroute operations do not require its use, andd) Repairs are made within 3 flight days.


1. Crew briefings will make reference to inoperative altitude alerting system.2. When flying with an inoperative altitude alerting system be especially careful of flying

through assigned altitudes (climbing or descending) or drifting off of an assigned altitude. To avoid such:a. When within 1,000 feet of an assigned altitude the pilot not flying will announce:

"Out of xxxx feet (or FL) for xxx feet (or FL)"b. When within 300 feet of an assigned altitude either climbing, descending or drifting off

of an assigned altitude the pilot not flying would state:"Altitude - Altitude"

34-23-01 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-09-01 35


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

34-25-20 Electronic Flight Instrument System (EFIS) Symbol Generators (FF Serials with Bendix EFS-10 Only)

A/2/1

(O) One may be inoperative provided:a) Aircraft is operated in day VMC,b) Aircraft is equipped with a standby attitude indicator,c) Navigation is not predicated on its use, andd) Repairs are made within 5 flight hours.

NOTE: The Autopilot will be inoperative on the failed side.OPERATIONAL PROCEDURE

1. Make sure that at each pilot’s station the MFD SG can be selected to provide the EFIS display.

2. Make sure that the operative SG is driving its on-side EFIS display.3. Switch the MFD SG so that it is driving the EFIS displays on the side with the failed SG.4. Make sure that the required number of EFDs show correct displays.

34-25-30-01 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.

300BPM-09-01 36

34-25-30-01 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.

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

C/-/0

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


THE BE-300 SERIES AIRCRAFT DOES NOT HAVE PREDICTIVE WINDSHEAR. THIS RELIEF WRITTEN IN ERROR BY THE FAA.

34-16-00 Radio Altimeter

C/-/0

(M)(O) May be inoperative provided:a) Class A TAWS and/or GPWS are considered inoperative,b) TCAS II is considered inoperative,c) Approach procedures do not require its use, andd) 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-09-01 37

34-16-00 Radio Altimeter

D/-/1

(M) May be inoperative provided TCAS, TAWS, and/or GPWS are not affected.


Pull and secure the RADIO ALTM circuit breaker on the right side circuit breaker panel.

34-44-11-01 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).

34-44-11-01-1 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-09-01 38

34-44-11-01-4 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.

34-44-11-01-4 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-09-01 39

***34-44-11-01-5 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.

34-44-11-02 Terrain Awareness and Warning System (TAWS) (Class A required by 14 CFR), errain 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.

34-44-12-01 Terrain Awareness and Warning System (TAWS) (Class B 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.



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-09-01 40

34-44-12-01-1 Terrain Awareness and Warning System (TAWS) (Class B required by 14 CFR), 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


34-44-12-01-4 Terrain Awareness and Warning System (TAWS) (Class B required by 14 CFR), Advisory Callouts

B/-/0






300BPM-09-01 41

34-44-12-01-4 Terrain Awareness and Warning System (TAWS) (Class B required by 14 CFR), Advisory Callouts

C/-/0

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






***34-44-12-01-5 Terrain Awareness and Warning System (TAWS) (Class B required by 14 CFR), 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-09-01 42

34-44-13 Ground Proximity Warning System (GPWS) Terrain Awareness and Warning System (TAWS) (Not required by 14 CFR)

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


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

C/-/0

(M) May be inoperative provided:a) Not required by 14 CFR,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.

300BPM-09-01 43

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 Traffic Alert and Collision Avoidance System (TCAS II)

C/-/0

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



34-45-10-02 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.

300BPM-09-01 44

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

C/-/0

(O) May be inoperative provided:a) RA visual display and audio functions are verified operative, andb) Enroute or approach procedures do not require its use.


During the Before Taxi: Avionics check, verify a Resolution Advisory along with the aural warning when the TCAS is tested.

34-50-10-01 Area Navigation (RNAV)(Multi-Sensor, LORAN, and/or GPS)Navigation Databases

C/-/-

(O) May be out of currency provided:a) Current aeronautical charts are used to verify navigation fixes prior to each departure,b) Procedures are established and used to verify status and suitability of navigation facilities

used to define route of flight,c) Approach navigation radios are manually tuned and identified, andd) RNAV departures, RNAV arrivals, RNAV instrument approaches, and published RNAV

routes based on RNAV guidance are not used.OPERATIONAL PROCEDURE

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.

***34-52-01-02 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.

300BPM-09-01 45

34-61-11-01 Flight Management System (Aircraft Integrated Systems) (Proline FUSION Only) FMS Navigation Databases

C/2/0

(O) May be out of currency provided:a) Current aeronautical charts are used to verify navigation fixes prior to each departure,b) Procedures are established and used to verify status and suitability of navigation facilities

used to define route of flight,c) Approach navigation radios are manually tuned and identified, andd) RNAV departures, RNAV arrivals, RNAV instrument approaches, and published RNAV

routes based on RNAV guidance are not used.OPERATIONAL PROCEDURE

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.

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.

35-20-10 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.

300BPM-09-01 46

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.


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.4. Do not operate aircraft in known or forecast icing conditions.5. Operate aircraft at or below FL250.

***38-10-00 Potable Water Systems

C/-/-

(M) Individual components may be inoperative provided:a) System is drained, andb) Procedures are established to ensure that system is not serviced.


1. Place placard near the inoperative water system (faucet or spigot) stating: "WATER SYSTEM INOPERATIVE".

For Aft Vanity Water Storage Tank:2. Remove access panels from upper vanity as needed to access tank.3. On most installations, turn the two fasteners at the top of the tank and depress the

collar on the quick disconnect water line connection to release the tank.4. Inspect tank and plumbing for leaks and dampness.5. Drain tank, and put in place without reconnecting plumbing.6. Reinstall access panels.

For Refreshment Center Liquid Storage Tanks:2. Remove access panels from Refreshment Center as needed to access tank.3. Slide tank out of its compartment, disconnect and cap any electrical connectors.4. Inspect tank and plumbing for leaks and dampness.5. Drain tank, and remove any plumbing lines.6. Replace tank without reconnecting any removed electrical or plumbing connections.7. Reinstall access panels.

300BPM-09-01 47

***38-30-00 Lavatory Waste Systems (Electric Circulation Toilet)

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 which operates normally may be used.MAINTENANCE PROCEDURE

Refer to the maintenance manual chapter 38-30-00 for deactivation and chapter 12-20-09 for servicing.

***38-30-00-01 Lavatory Waste Systems (Electric Circulation Toilet)

D/1/0

(M) May be inoperative provided:a) Toilet system is deactivated and emptied, andb) Toilet is placarded “INOPERATIVE – DO NOT USE”.


Refer to the maintenance manual chapter 38-30-00 for deactivation and chapter 12-20-09 for servicing.

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.

300BPM-09-01 48

46-10-10-02 Integrated Flight Information System (Pro Line 21 IFIS-5000) 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: If alternate source is electronic, dual redundancy is required for operation.


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.

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.

300BPM-09-01 49

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-09-01 50

***46-20-01 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 source is electronic, 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.

***46-20-01-01 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.

***46-20-01-02 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-09-01 51

***46-20-01-02 Electronic Flight Bag Systems (EFB)(excludes PED EFB), Mounting 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.


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.

***46-20-01-03 Electronic Flight Bag Systems (EFB)(excludes PED EFB), Mounting Device (Class 2)Data Connectivity (Class 2)

C/-/0


Utilize the Information from remaining operative EFB.

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

***49-00-01 Auxiliary Power Unit (APU)

C/1/0

(M) May be inoperative provided system is deactivated.


Pull and secure the APU circuit breaker.

300BPM-09-01 52

52-10-10 Cabin Door Snubber

C/1/0

(O) May be inoperative provided precautions are used when opening.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.

73-31-00 Fuel Flow Indicators

B/2/1

(M) One may be inoperative provided both fuel quantity indicating systems are operative.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-09-01 53

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