Bell 412 Specs

This document is intended for the use of BHTI employees, and BHTI independent representatives (international dealers), and for prospective customers as an aid in determining estimated weight and performance of the helicopter when configured with equipment for specific missions. Disclosure, reproduction, or use of any material in this document by persons other than BHTI employees, and BHTI independent representatives, and prospective customers are forbidden without written permission from Bell Helicopter Textron Inc. The listings of Optional Equipment (â€Å"Kits†) are subject to revision and change, and also may be different for specific serial number helicopters or special custom configurations. Please consult the â€Å"Notes† column found in the optional equipment list tables for equipment compatibility. The continuing product improvement process of BHTI may cause some components, equipment, and compatibility to be changed or replaced. The specifications, weights, dimensions, and performance data shown in this document are subject to change without notice. 2012 Bell Helicopter Textron Inc. Bell, 206, 407, 407GX, 429, 412, Huey II, LongRanger and JetRanger are registered trademarks of Textron Innovations Inc. All rights reserved Specifications subject to change without notice. Bell 412EP Product Specification May 2012 412EP Product Spec 2012-02. indd 1 1  © 2012 Bell Helicopter Textron Inc. 6/5/2012 8:37:05 PM Page Intentionally Left Blank  © 2012 Bell Helicopter Textron Inc. 412EP Product Spec 2012-02. indd 2 2 Bell 412EP Production Specification May 2012 6/5/2012 8:37:05 PM Bell 412EP RELIABLE, RUGGED AND READY The Bell 412EP is the workhorse of the helicopter industry with a reputation of getting up and going to work every day in even the most extreme environments. †¢ Proven Pratt Whitney PT6T-3D Twin Pac engines with more than 25 million flight hours in more than 2,000 aircraft worldwide †¢ High retirement and overhaul intervals 5,000 hour drive system TBO 4,000 hour engine overhaul interval On-condition composite main rotor blades †¢ 25,000 hours between premature engine removals †¢ Excellent Category A / JAR OPS 3 capability †¢ Rugged fuselage with rollover bulkhead protection and rupture resistant fuel cells The data set forth in this document are general in nature and may vary with conditions. For performance data and operating limitations for any specific flight mission, reference must be made to the approved Flight Manual Bell 412EP Product Specification May 2012 412EP Product Spec 2012-02. indd 3 3  © 2012 Bell Helicopter Textron Inc. 6/5/2012 8:37:05 PM Specification Summary (U. S. Units) Weight lb Weight lb Empty Weight (IFR Std. Config. ) 1 6,964 Maximum Gross Weight (Internal) 11,900 Useful Load (Internal, IFR Std. Config. ) 4,936 Maximum Gross Weight (External) 11,900 Maximum External Load 4,500 Performance Summary: Takeoff, Gross Weight lb IGE Hovering Ceiling 9,500 10,500 11,900 ISA OGE Hovering Ceiling ft 17,400 14,300 10,200 ISA + 20  °C ft 14,400 10,900 6,200 ISA 10,400 5,200 10,300 6,050 (11,890 lb @ SL) ISA ft 14,000 11,270 7,270 ft 12,120 9,000 4,990 ISA Service Ceiling (AEO) 13,800 ft ISA + 20  °C FAA Take Off and Landing Limit, WAT 2 ft ISA + 20  °C ft 19,840 18,760 16,290 (continuous OEI) ISA ft 11,450 8,850 5,400 (30 minute OEI) 3 ISA ft 12,850 10,500 7,600 4,000 ft, ISA kts 132 130 125 n mi 366 364 358 kts 126 125 122 n mi 414 410 401 kts 131 130 125 Maximum Continuous Cruise (true airspeed) Cruise at Long Range Cruise (LRC) Speed Range 4 LRC Speed (average true airspeed) Range SL, ISA 4 LRC Speed (average true airspeed) Catagory A Takeoff and Landing Ceiling 4,000 ft, ISA ft 6,000 3,400 (11,580 lb @ SL) ft 3,750 1,200 (10,800 lb @ SL) SL, ISA hr 4. 0 3. 9 3. 6 4,000 ft, ISA Endurance at Loiter Speed 4 ISA ISA + 20  °C Elevated Helipad hr 4. 3 4. 2 3. 9 Uninstalled Thermodynamic Power Engine Ratings: (100% RPM) Engine Rated Power 2 x 950 2 x 900 Standard: Pratt Whitney PT6T-3D Twin Pac Takeoff (5 minutes) SHP Max Continuous Power SHP 2 x 950 2 x 800 OEI (2-1/2 minutes) SHP 1 x 1,140 1 x 1,133 OEI (continuous) SHP 1 x 970 1 x 1,024 OEI (30 minutes) SHP 1 x 1,066 1 x 1,079 OEI (continuous) SHP 1 x 950 N/A Optional: Pratt Whitney PT6T-3DF Twin Pac Transmission Ratings (100% RPM, at mast) Takeoff (5-minute) 1,370 SHP Max Continuous Power 1,110 SHP Single Engine Limited by Power Available Fuel (usable) Type Aviation Turbine Capacity 330. 5 US Gallons Note 1 IFR Standard Configuration includes all items listed in the Standard Configuration table of this document as well as twenty-five pounds (eleven kilograms) of engine oil. Ballast is not included in the standard configuration (ballast is a function of installed equipment). Note 2 With BLR FastFin ® System. Does not apply for Catagory B, 9-passenger seat configuration. The data set forth in this document are general in nature and may vary with conditions. For performance data and operating limitations for any specific flight mission, reference must be made to the approved Flight Manual  © 2012 Bell Helicopter Textron Inc. 412EP Product Spec 2012-02. indd 4 4 Bell 412EP Production Specification May 2012 6/5/2012 8:37:06 PM Specification Summary (Metric Units) Weight kg Weight kg Empty Weight (IFR Std. Config. ) 1 3,159 Maximum Gross Weight (Internal) 5,398 Useful Load (Internal, IFR Std. Config. ) 2,239 Maximum Gross Weight (External) 5,398 Maximum External Load 2,041 Performance Summary: Takeoff, Gross Weight kg IGE Hovering Ceiling ISA 4,309 4,763 5,398 m 5,304 4,359 3,109 ISA + 20  °C m 4,389 3,322 1,890 ISA OGE Hovering Ceiling m 4,206 3,170 1,585 ISA + 20  °C m 3,139 1,844 (5,393 kg @ SL) ISA m 4,267 3,435 2,216 ISA + 20  °C FAA Take Off and Landing Limit, WAT 2 m 3,694 2,743 1,521 Service Ceiling (AEO) ISA m 6,047 5,718 4,919 (continuous OEI) ISA m 3,490 2,697 1,646 ISA m 3,917 3,200 2,316 1,219 m, ISA km/h 244 241 232 km 678 674 663 (30 minute OEI) 3 Maximum Continuous Cruise (true airspeed) Cruise at Long Range Cruise (LRC) Speed Range 4 LRC Speed (average true airspeed) Range 4 LRC Speed (average true airspeed) SL, ISA 1,219 m, ISA km/h 233 232 226 km 767 757 743 243 241 232 m 1,829 1,036 (5,253 kg @ SL) m 1,143 366 (4,899 kg @ SL) SL, ISA hr 4. 0 3. 9 3. 6 1,219 m, ISA Elevated Helipad Endurance at Loiter Speed 4 km/h ISA + 20  °C Catagory A Takeoff and Landing Ceiling hr 4. 3 4. 2 3. 9 ISA Uninstalled Thermodynamic Power Engine Ratings: (100% RPM) Engine Rated Power Standard: Pratt Whitney PT6T-3D Twin Pac Takeoff (5 minutes) kW 2 x 708 2 x 671 Max Continuous Power kW 2 x 708 2 x 597 OEI (2-1/2 minutes) kW 1 x 850 1 x 845 OEI (continuous) kW 1 x 723 1 x 764 OEI (30 minutes) kW 1 x 795 1 x 805 OEI (continuous) kW 1 x 708 N/A Optional: Pratt Whitney PT6T-3DF Twin Pac Transmission Ratings (100% RPM, at mast) Takeoff (5-minute) 1,022 kW Max Continuous Power 828 kW Single Engine Limited by Power Available Fuel (usable) Type Aviation Turbine Capacity 1,251 liters Note 3 Increased capability available with optional Pratt Whitney PT6T-3DF (30 minute OEI Power Kit). Note 4 Standard fuel, no reserve. The data set forth in this document are general in nature and may vary with conditions. For performance data and operating limitations for any specific flight mission, reference must be made to the approved Flight Manual Bell 412EP Product Specification May 2012 412EP Product Spec 2012-02. indd 5 5  © 2012 Bell Helicopter Textron Inc. 6/5/2012 8:37:06 PM BLR Strake and FastFin ® Bell Helicopter has partnered with BLR Aerospace to provide its performance, safety and efficiency-enhancing FastFin ® system as a standard feature on new Bell 412EP aircraft orders. The system incorporates two parallel stall strips along the tail boom and a reshaped vertical fin. These modifications combine to optimize airflow around the tail boom, improving the handling, stability and lifting capacity of the Bell 412EP in all environments, especially high and hot conditions. The FastFin ® system is a combination of two separate modifications, one to the vertical fin and the other to the tailboom. For clarity, the term FastFin ® refers to the BLR modification that changes the shape and contour of the vertical fin. The term FastFin ® System refers to the combined FastFin ® and Dual Tail Boom Strake installation. The performance benefits of this system include increased tail rotor effectiveness and higher crosswind speed tolerance at hover in certain conditions. In conditions where the aircraft is currently tail rotor limited the FastFin ® System results in increased Weight-Altitude-Temperature (WAT) capability for takeoff, landing and in-ground-effect maneuvers, providing substantial improvement in useful load for hot/high operation (See performance chart below). 14,000 Be ll 41 M 2EP ax G wit Be ro h ss Fa ll 41 W stF 2E ei in gh TM P M tL S ax im ys G it tem ro ss W ei gh tL im it 12,000 Density Altitude (feet) 10000 8,000 6,000 4,000 2,000 0 8,000 9,000 10,000 Gross Weight (lb) 11,000 12,000 Bell 412EP WAT Improvement with FastFin ® System The data set forth in this document are general in nature and may vary with conditions. For performance data and operating limitations for any specific flight mission, reference must be made to the approved Flight Manual  © 2012 Bell Helicopter Textron Inc. 412EP Product Spec 2012-02. indd 6 6 Bell 412EP Production Specification May 2012 6/5/2012 8:37:06 PM Page Intentionally Left Blank Bell 412EP Product Specification May 2012 412EP Product Spec 2012-02. indd 7 7  © 2012 Bell Helicopter Textron Inc. 6/5/2012 8:37:06 PM External Dimensions LOW SKID GEAR Bell 412EP Low Skid Gear OPTIONAL HIGH SKID GEAR WITH AAI FLITESTEP ® Bell 412EP High Skid Gear Specifications subject to change without notice.  © 2012 Bell Helicopter Textron Inc. 412EP Product Spec 2012-02. indd 8 8 Bell 412EP Production Specification May 2012 6/5/2012 8:37:08 PM OPTIONAL EMERGENCY FLOAT GEAR WITH AAI FLOATSTEPâ„ ¢ Bell 412EP Float Kit OPTIONAL BLADE FOLDING KIT DIMENSIONS Minimum Hanger Size* Rotor Not Folded 33. 0 ft x 49. 6 ft (10. 1 m x 15. 2 m) Minimum Hanger Size* Rotor Folded 9. 5 ft x 55. 8 ft (2. 9 m x 17. 1 m) *Allowance should be made for high skid gear, ground wheels, emply fuel condition and door lip when considering hangar door width and height Specifications subject to change without notice. Bell 412EP Product Specification May 2012 412EP Product Spec 2012-02. indd 9 9  © 2012 Bell Helicopter Textron Inc. 6/5/2012 8:37:10 PM Bell 412EP Seating and Interior Trim Choices Crew Seats Two individual energy attenuating seats, fore/aft and up/down adjustable, each equipped with seat belt, double strap shoulder harness and inertia reel. Available with Grey, Blue, Red, or Tan upholstery which will match that selected for the cabin. Passenger Seats 13 seats offered in three options. (NOTE: Seating option 1 meets the criteria required by FAA regulations for installation in U. S. registered helicopters. Seating Options 2 3 require the addition of the STC Alpine 412 Passenger Shoulder Harness Kit for installation in U. S. registered helicopters. ) 1) Standard Seating Fabric covered high-backed folding seats with individual seat belts and single strap shoulder harness and inertia reel, arranged with one row of four (two 2-place benches) forward facing seats, and one row of five forward facing seats, and two outward facing two place benches (one on either side of the transmission). Available with Grey, Blue, Red, or Tan upholstery with Black seat belts. Seats are are also available in all vinyl at additional cost. (210. lb [95. 7 kg] included in the standard configuration weight. ) STANDARD SEATING (Shown with standard interior trim and floor covering) SEATING OPTIONS 2 AND 3 NOT ILLUSTRATED 2) Utility Seating Available for U. S. registered helicopters ONLY with addition of STC Alpine 412 Passenger Shoulder Harness Kit. Nylon covered bench type seating arranged with one row of four rearward facing seats (behind the crew seats), one row of five forward facing seats (in front of the transmission), and two outward facing two place benches (one on either side of the transmission). Each seat has an individual seat belt. Available in Tan or Black. The Utility Seating decreases the standard configuration weight (-93. 3 lb [-42. 3 kg], with Alpine Shoulder Harness -59. 5 lb [-27. 0 kg]). 3) Cushioned Utility Seating Available for U. S. registered helicopters ONLY with addition of STC Alpine 412 Passenger Shoulder Harness Kit. As in 2) above with the addition of fabric covered cushions, available in the same colors as the Standard Seating. The Cushioned Utility Seating decreases the standard configuration weight (-81. 1 lb [-36. 8 kg], with Alpine Shoulder Harness -47. 3 lb [-21. 5 kg]). Specifications subject to change without notice.  © 2012 Bell Helicopter Textron Inc. 12EP Product Spec 2012-02. indd 10 10 Bell 412EP Production Specification May 2012 6/5/2012 8:37:10 PM INTERIOR TRIM CHOICES 1) Standard Interior Trim The Standard Interior Trim is provided as a NO COST OPTION, but is not included in the Standard Configuration Empty Weight. Included are: Plastic closeouts on upper sidewalls, window reveals, and cabin headlin er; Padded vinyl covering the floor and lower door panels; Lower aft bulkhead covered with padded vinyl blankets. The hard plastic headliner and closeouts are off-white in color, and the padded bulkhead blankets and floor covering are color coordinated to match the seat color selection. The Standard Interior Trim increases the standard configuration empty weight (165. 7 lb [75. 2 kg]). 2) Utility Interior Trim The Utility Interior Trim consists of: Light beige vinyl covered headliner and bulkhead blankets; Doors painted light beige; Floor painted brown. The Utility Interior Trim is included in the standard configuration empty weight (33. 3 lb [15. 1 kg]). CUSTOMIZED SEATING [Example] Customized Seating Custom designed interiors are available from aircraft completion centers to meet the needs of Corporate or Emergency Medical Service customers. Specifications subject to change without notice. Bell 412EP Product Specification May 2012 412EP Product Spec 2012-02. indd 11 11  © 2012 Bell Helicopter Textron Inc. 6/5/2012 8:37:10 PM Standard Configuration (Items Included In List Price) AIRFRAME TRANSMISSION/ DRIVE SYSTEM Aluminum alloy fuselage (over 240 ft3 [6. 8M3]) loading space Glass windshields Main rotor transmission with 4 chip detectors/2 debris collectors Tinted overhead windows Vibration isolation / suspension mounts (4) Dual windshield wipers Main Lift link (single point suspension) Fresh air ventilators with adjustable outlets (8 cockpit and 12 aft cabin) 42? gearbox (sight gage and magnetic drain plug/chip detector) Bleed air heater and defroster with air noise suppression 90? gearbox (sight gage and magnetic drain plug/chip detector) Cargo tie-down fittings (51 aft cabin floor) Hydraulic pumps for controls (2 independent systems) Map and data case Transmission oil cooler Cabin fire extinguisher (2) Swingout jettisonable doors (2 for forward cabin) POWER PLANT Sliding doors (2 for aft cabin access with 2 emergency exit panels on each door) Automatic governors (2) Pratt Whitney of Canada PT6T-3D â€Å"Twin Pac† (1800 SHP) Swingout panels for extended access to aft cabin (2) Magnetic chip detectors Fixed step on skids for entry to forward cabin (2) Torque limiter Fuel System (330. 5 US Gal [1251 liter] usable, rupture resistant cells and breakaway vent fitting) Retractable steps for aft cabin access (2) Baggage compartment in tail boom (over 28 ft [0. 8M ], 400 lb [181kg] capacity). 3 3 Pumps on engines and submerged in fuel tanks Skid-type landing gear with replaceable wear shoes Fuel filter assembly Mooring and jacking fittings (4) Oil coolers (2) External attachment fittings (16) Fire detection system (2) Semi-monocoque tailboom Fire extinguisher system (2) BLR Strake and FastFin RPM warning system  ® Elevator (airspeed / spring-cartridge controlled) Hinged cowling Tail skid Starter-generators (2) Cargo hook provisions Power turbine RPM control actuators AUDIO Combining gearbox with chip detector Two station aft intercom system w/crew interface Separate firewall protection for each engine ROTORS CONTROLS Overriding clutches (2) Soft-in-plane flex beam hub with four fiberglass blades Extended Engine Exhaust Deflectors Main rotor droop restraint COMMUNICATIONS NAVIGATION Pendulum vibration absorbers 720 Channel VHF rec/trans transceiver (KTR-908) Semi-rigid, two bladed all-metal tail rotor VHF antenna All controls hydraulically boosted (dual systems for main rotor) 2 Headsets (pilot copilot) Force trim system and artificial feel (electrically set) 2 Intercomunication Panels (ICS) (pilot copilot) Dual controls Emergency Transmit Switch Cyclic stick centering Horizontal Situation Indicator RPM governor selector control Attitude Director Indicator Manual engine torque matching and trim Attitude and Heading Reference Systems (2) Dual Digital Three axis AFCS (2 flight control computers) Cockpit voice recorder provisions Rotor brake Specifications subject to change without notice.  © 2012 Bell Helicopter Textron Inc. 412EP Product Spec 2012-02. indd 12 12 Bell 412EP Production Specification May 2012 6/5/2012 8:37:10 PM Standard Configuration (continued) FLIGHT ENGINE INSTRUMENTS FLIGHT ENGINE INSTRUMENTS (continued) Flight Director Nav Coupler (3-axis) Master warning lights on the instrument panel draw attention to: Free air temperature indicator RPM Pitot static system with electric pitot heat Eng 2 Out Eng 2 Fire Eng 1 Out AL-300 Data Display Eng 1 Fire Baggage Fire Cyclic Radar altimeter #1 Over torque centering Altimeter (barometric) (mast) IFR EQUIPMENT Clock, digital quartz chronometer Co-pilot clock Hourmeter Distance Measuring Equipment (DME) (KDM-706) Magnetic compass, pilot’s standby IFR FAA kit Airspeed indicator Automatic Direction Finder (ADF) (XDF-806) Rate of climb indicator Nav receiver #1 VOR/LOC with HB/HSI (KNR-634) Turn and slip indicator Nav receiver #2 VOR/LOC with HSI (KNR-634) Triple tachometer (rotor and engines) VHF-AM Comm #2 radio (KTR-908) Dual hydraulic press/temp indicator (2) Transponder (MST67) Gas producer tach indicator (2) Co-pilot instruments (FAA) Triple torque indicator (Eng 1, Eng 2, mast) Standby attitude indicator Engine oil-temp/press indicator (2) ELECTRICAL Turbine inlet temperature indicator (2) Generator (2) (30 volt, 200 ampere DC startergenerator derated to 150 amperes) Fuel pressure indicator Transmission oil-temp/press indicator Inverters (2), (450 volt ampere single phase, solid state) Dual DC and AC voltmeters Nickel cadmium battery (40 ampere hours) Dual DC loadmeter Battery over-temp warning Fire detection warning (3) Generator voltage regulators Combining gearbox oil-temp/press indicator Instrument (integral) lights (white) Flight data recorder provisions Navigation lights Caution Warning System Master caution light on panel draws attention to the pedestal mounted annunciator panel when worded segments illuminate: Landing light-retractable Anticollision light (2) Engine oil press (2) DC generator (2) Tritium lighted emergency exit signs Trans oil press Gen overheat (2) Cockpit lights (2) Trans oil temp AC inverter (2) Dome lights (3) Comb box oil press External power External power receptacle Comb box oil temp Battery switch Twin ignition and starting systems Chip detectors (5) Battery temp Seat belt sign Fuel boost (2) Hydraulic Passenger step lights Fuel filter (2) Door locks Baggage compartment light fire sensor Fuel valve (2) Heater Utility cabin lights (removable) Fuel low (2) Part sep off (2) Fuel X feed Rotor brake (2) PAINT Emerg gov manual (2) Caution panel Markings for high visibility M/R blades (white orange) Specifications subject to change without notice. Bell 412EP Product Specification May 2012 412EP Product Spec 2012-02. indd 13 13  © 2012 Bell Helicopter Textron Inc. 6/5/2012 8:37:10 PM Standard Configuration (continued) MISCELLANEOUS Covers, tail pipe, turbine air inlet, and pitot tube Flight bag Ground handling wheels, hydraulically activated Manuals: Aircraft log, Engine log, Engine operations, Flight, Maintenance Overhaul Manual, Illustrated Parts Catalog Tie-down assemblies, main rotor tail rotor INTERIOR TRIM Choice of Standard or Utility Interior Trim. Standard; Rigid three-piece headliner in cabin, padded iberglass floor covering, bulkheads, trimmed with cream-colored plastic and color-coordinated vinyl coated fiberglass, cabin doors trimmed with plastic, special soundproofing, seat upholstered with foam and fabric. Selection of fabric colors. Not included in Standard Configuration Weight, increases empty weight 165. 6 pounds (75. 1 kilograms) when installed. Utility; Be ige soundproofing blankets on bulkheads and overhead; doors painted beige, floor painted brown. Included in Standard Configuration Weight (approximately 32. 6 pounds, 914. 8 kilograms). Specifications subject to change without notice. 2012 Bell Helicopter Textron Inc. 412EP Product Spec 2012-02. indd 14 14 Bell 412EP Production Specification May 2012 6/5/2012 8:37:10 PM Page Intentionally Left Blank Bell 412EP Product Specification May 2012 412EP Product Spec 2012-02. indd 15 15  © 2012 Bell Helicopter Textron Inc. 6/5/2012 8:37:10 PM Optional Accessories [Kits listed below are compatible with the FAA IFR 3-axis / non-EFIS configuration except as individually noted] Additional kits and STC items may be available for factory installation. Please consult sales or contract personnel regarding special needs prior to selection of final configuration. Wt (lb) Wt (kg) Notes 11. 7 5. 3 1, 2 FIXED STEP RIGHT HAND 11. 6 5. 3 1, 2 HEAVY DUTY HIGH SKID GEAR w/o STEPS 18. 5 8. 4 1, 3 HEAVY DUTY HIGH CROSS TUBES FOR EMER. FLOATS 3. 8 1. 7 EMERGENCY FLOATS (provisions) 51. 0 23. 2 EMERGENCY FLOATS /RESERVOIR NOSE 97. 5 44. 2 4 EMERGENCY FLOATS (L. G. w/ FLOATS PWR STEPS) 168. 8 76. 6 1, 4 HEATED WINDSHIELD 9. 8 4. 4 1 EXPANDABLE BOLTS MAIN ROTOR 3. 0 1. 4 FUEL KIT MANIFOLD DRAIN 0. 3 0. 1 Kit Description AIRFRAME FIXED STEP LEFT HAND 9 CELL FUEL SYS 4 -16. 1 -7. 3 SEAT BELT SIGN STD INTR 0. 3 0. 1 SEAT BELT SIGN DLX INTR 0. 3 0. 1 AUX FUEL PROVS 5. 4 . 5 5 AUX FUEL, 16. 3 GAL LH 20. 2 9. 1 5 AUX FUEL, 16. 3 GAL RH 20. 2 9. 1 5 AUX FUEL, 81. 7 GAL LH (REQUIRES REMOVAL OF 2 OUTBOARD-FACING PAX SEATS) 50. 3 22. 8 5 AUX FUEL, 81. 7 GAL RH (REQUIRES REMOVAL OF 2 OUTBOARD-FACING PAX SEATS) 50. 3 22. 8 5 5 INDICATOR, FUEL QTY, AUX FUEL -0. 1 0. 0 TOLERANT FUEL 98. 5 44. 7 EFIS (ELECTRONIC FLIGHT INSTRUMENT SYSTEM) 113. 4 51. 4 1, 6 4-AXIS D DAFCS W/ DUAL FLIGHT DIRECTOR 26. 4 12. 0 7 PRIMUS 700 WEATHER RADAR 49. 1 22. 3 7 PRIMUS 700 WEATHER RADAR W/ EFIS 54. 6 24. 8 7 ENCODING ALTIMETER 0. 1 0. 0 1, 7 RADAR ALTIMETER #2 12. 2 5. 6 7 CABIN PA SYSTEM (NON-EFIS)