Page 1 of 7 B36TC POH Revision, December 2003 Return to home page Raytheon Aircraft Company has issued a complete, remove-and-replace-everything revision to the B36TC (EA-320, EA-389 and after) Pilot s Operating Handbook part number 36-590006-19B, dated December 2003. To help B36TC owners more quickly identify the specific changes incorporated in the new POH, some of which may be operationally important, what follows is a list of changed items in the revision. Many of these changes also appear in part number 36-590006-3A9 (also dated December 2003), a less-sweeping update to the POH for B36TCs EA-242, EA-273 thru EA-388 except EA-320. Changes that directly affect operations and maintenance are identified in bold type. Review the revision/update (as appropriate) prior to operating an affected airplane. Contact Beech s Technical Manuals/Documents Center at 800-796-2665 to obtain a copy if you have not already received one. The following refers specifically to the revision to the B36TC EA-320, EA-389 and after POH. Comments are clearly marked in parentheses, and underlined. GENERAL NOTES Remember that, as an FAA-approved flight manual, all information contained in SECTION II, LIMITATIONS is regulatory. All other information is merely recommended procedure, but Raytheon, Teledyne Continental Motors, and other suppliers reserve the right to make decisions about warranty, etc., based on adherence to the entire POH. Raytheon Aircraft Company and Raytheon Authorized Outlets replace Beechcraft and Beech Maintenance Centers throughout the new POH. Minor formatting and wording changes appear throughout. Many prior notes contained in the EMERGENCY and NORMAL PROCEDURES sections now appear in the form of checklist steps. Remember that the WEIGHT AND BALANCE EQUIPMENT LIST and SUPPLEMENTS sections of the POH are airplane-specific, and should be transferred to the new POH when making updates. UPDATES TO SECTION I: GENERAL 1) Removes thank you for purchasing a Beechcraft section. 2) Adds note about SECTION X, SAFETY INFORMATION 3) Adds new warning: Use only Raytheon Aircraft Corporation or Raytheon-approved parts. 4) Adds new warning about suspect condition of salvage parts. 5) Adds: Raytheon Aircraft Corporation expressly disclaims any responsibility for malfunctions, failures, damage or injury caused by use of non-raytheon approved parts. 6) Clarifies that the POH is the FAA Approved Flight Manual for the B36TC. 7) Clarifies FARs and FAR 91 as Title 14 Code of Federal Regulations (14 CFR), and that 14 CFR, not the POH, assigns pilot, owner and mechanic responsibilities. 8) Adds description of the following terms: a) WARNING: involves risk of personal injury or loss of life. b) CAUTION: Involves risk of equipment damage. c) NOTE: Items considered essential to emphasize. 9) Adds a new LIST OF EFFECTIVE PAGES and instructions for its use. 10) New note that Raytheon reserves the right to revise, supercede, cancel, or declare obsolete, without prior notice, any part, part number, kit or publication. 11) Adds new warning that it is the owner/operator s responsibility to ensure the POH is updated with the latest revisions, and SUPPLEMENTS applicable to the specific airplane. 12) Provides instructions on using the Log of Supplements page.
Page 2 of 7 13) Changes propeller low pitch setting tolerance from +0.2 degrees to +0.3 degrees. 14) Changes Approved oil types to Specification, and changes MIL-L-22851 to SAE Specification J1899. 15) Changes Maximum Cruise Power from Highest power rating for which engine can be leaned for cruise to Maximum power setting for which specific values of fuel flow and airspeed are presented. (COMMENT: This would suggest that power settings above 31 MP and/or 2400 RPM are not permitted, although in SECTION I this is not an FAA limitation. Section II, Limitations, does in fact imply the Manifold Pressure Vs. RPM graph in the SECTION 5 PERFORMANCE section should be considered a limitation; if so, then the 31 and/or 2400 rpm restriction would be a legal operating limitation. See below.). UPDATES TO SECTION II: LIMITATIONS (NOTE: Reminder that Section II items carry the force and effect of a Federal Air Regulation). 1) Adds under MANUAL LEANING LIMITATIONS: Refer to the Manifold Pressure vs. RPM graph in SECTION 5, PERFORMANCE, for engine leaning limitations. (COMMENT: By requiring use of the MP vs. RPM graph in the LIMITATIONS section of the POH, this in fact does make the maximum cruise of 31 inches MP and/or 2400 rpm an operating limitation for anything other than a full rich mixture setting. It does NOT specifically prohibit LOP operation if the pilot elects to use such technique. It would almost certainly be necessary, if the pilot elects to use LOP technique, to employ The Big Mixture Pull technique advocated by GAMI, to avoid exceeding the 899C TIT redline while setting the mixture.). 2) The phrase operating range becomes normal operating range in several places. 3) Adds that Maximum combined weight of aft seat occupants is 400 pounds unless otherwise placarded. (COMMENT: This coincides with the existing limitation of 400 pounds from the rear spar to Station 170, which is the aft end of the aft baggage area. As seats 3 and 4 are on, not aft of the rear spar, and as the WEIGHT AND BALANCE section allows for loadings to exceed this figure, the 400 pound limitation does not apply to seats 3 and 4 regardless of whether there are passengers in seats 5 and 6. The A36 limitation of no more than 250 pounds combined in seats 5 and 6 does not appear in the B36TC POH either, and therefore does not meet the definition of as otherwise placarded ). 4) Adds -0 G load factor limitation with flaps extended. 5) Adds Approved airplane deicing fluids SAE AMS 1424 Type I and ISO 11075 Type I as a limitation. 6) Adds And those in compliance with Service Bulletin 2670 to illustration of fuel selector valve for EA-592 and after. 7) Adds warning: Flight in icing conditions prohibited as a limitation. 8) On the Kinds of Operations Equipment List table: a) under FLIGHT INSTRUMENTS, the following are added as required for day and night IFR: i) Attitude indicator. ii) Directional gyro. iii) Clock (COMMENT: permanently installed in the airframe, per 14 CFR 91). iv) Slip-skid indicator. v) Rate-of-turn indicator. b) Under RESTRAINT SYSTEM adds for all operations: i) Seat belts for all seats. ii) Shoulder harnesses for all crew seats. c) (COMMENT: [a] and [b] above are no change from existing FAR requirements, and have merely been added to the POH). UPDATES TO SECTION III: EMERGENCY PROCEDURES 1) Adds bold print (memory) items to emergency procedures checklists, stating immediate action procedures are delineated by solid bold type with the remaining procedures following. 2) Adds note: Braking effectiveness is improved if the brakes are not locked.
Page 3 of 7 3) On the ENGINE FAILURE/LOSS OF POWER IMMEDIATELY AFTER LIFTOFF checklist, adds steps and targets for airspeed control. 4) On the MAXIMUM GLIDE checklist, adds: a) ELT (if installed) ON (red transmit light illuminated) b) Air Conditioner (if installed) OFF. 5) On the LANDING WITH GEAR RETRACTED WITH POWER checklist, adds: Flaps DOWN. 6) On the AUXILIARY FUEL PUMP FAILURE checklist, adds: If fuel flow continues to fluctuate--descend to a lower altitude. 7) On the ALTERNATOR OUT/LOW BUS VOLTAGE ILLUMINATES checklist, adds: a) Refer to Standby Alternator supplement for procedure. b) If loadmeter reads above 25 volts, Alternator Switch CONFIRM ON. 8) Removes the BUS VOLT ILLUMINATED AFTER AIR START checklist (COMMENT: This procedure is now incorporated in the preceding checklist). 9) On the ELECTRICAL FIRE OR SMOKE CHECKLIST, adds: a) Warning: Turn coordinator, HSI, engine instruments (except MAP and TIT) and stall warning horn will become inoperative with battery and alternator OFF. b) Checklist step: Heading Control MAINTAIN USING STANDBY COMPASS IF REQUIRED. c) Warning: Dissipation of smoke is not sufficient evidence that the fire has been extinguished. If it cannot be visually confirmed that no fire exists, land at the nearest suitable airport. 10) On the LANDING GEAR MANUAL EXTENSION checklist, add: Autopilot ON (if desired). 11) On the INSTRUMENT AIR PRESSURE SYSTEM FAILURE checklist, refers to the supplement for airplanes equipped with standby instrument air. 12) Expands previous text information into checklists for the following procedures: a) UNLATCHED DOOR IN FLIGHT b) SPINS c) EMERGENCY SPEED REDUCTION UPDATES TO SECTION IV: NORMAL PROCEUDRES 1) Increases the airspeed for CLIMB AT MAXIMUM CONTINUOUS POWER from 112 kts to 120 knots (COMMENT: This is already common practice for cooling and visibility purposes). 2) On the PREFLIGHT INSPECTION checklist, on the step Emergency Locator Transmitter ARMED adds the note (aft fuselage installation). 3) On the BEFORE STARTING checklist adds: a) Standby Alternator (if installed) SEE SUPPLEMENT FMS 410-1. b) ELT Switch (if installed) ARM, Transmitter light extinguished. c) Standby instrument air (if installed) CHECK (use supplement). (COMMENT: My experience is that, if this step is done just before engine start, that the attitude gyro will precess on engine start and take up to 15 minutes to properly erect. I prefer to test the standby instrument air pressure system at the beginning of the PREFLIGHT inspection, before the exterior walk-around, giving the gyro time to spin back down, and air to bleed out of the instrument air pressure lines/t-valve, before reintroducing pressurized air on engine start. This in my experience avoids tumbling of the attitude indicator). 4) On EXTERNAL POWER checklist, adds: a) The battery must be ON and all avionics and electrical switches OFF prior to applying external power to the airplane. This protects the voltage regulators and associated electrical equipment from voltage transients (power fluctuations). b) Standby Alternator (if installed) SEE SUPPLEMENT FMS 410-1.
Page 4 of 7 5) On TAKEOFF checklist: a) Regarding fuel flow, changes 31.5 to 34.2 gph; will increase up to 1 gph as rpm increases during take-off roll to 33.2 gph (will increase.). b) In Warning, changes if fuel flow exceeds red line (34.2 gph), manually lean to the fuel flow redline prior to takeoff to if fuel flow manually lean to 33.2 gph prior to takeoff. (COMMENT: This assumes the 1 gph increase as rpm increases). c) Airspeed (when clear of obstacles) changed from 112 kts to 120 knots. 6) On CLIMB checklist: a) Changes Maintain 32.5 to 34.2 gph up to critical altitude to Maintian 34.2 gph up to critical altitude. b) Changes ranges of fuel flows for manifold pressures above critical altitude to single fuel flow figures equaling the high end of each earlier range. c) Changes climb speed from 112 kts to 120 kts. 7) On CRUISE CLIMB checklist: a) Changes 28.0 to 31.0 gph to 31.0 gph. b) Changes ranges of fuel flows for manifold pressures above critical altitude to single fuel flow figures equaling the high end of each earlier range. c) Adds Airspeed--120 kts. 8) On LEANING MIXTURE USING TURBINE INLET TEMEPRATURE (TIT) INDICATOR, adds caution: Do not turn Auxiliary Fuel Pump OFF after fuel flow has been leaned without first returning mixture control to FULL RICH. 9) On BALKED LANDING checklist, adds: Mixture 34.2 gph. 10) On SHUTDOWN checklist adds: Standby Generator/Alternator OFF. 11) Under ENVRIONMENTAL SYSTEMS, OXYGEN SYSTEM section, adds: a) Oxygen system preflight checklist. b) Warning that beards and mustaches may prevent proper seal of oxygen masks. 12) COLD WEATHER OPERATION, PREFLIGHT INSPECTION section has been expanded. UPDATES TO SECTION V: PREFORMANCE 1) Revised the EXAMPLE section. 2) Contains larger-format, fold-out PERFORMANCE charts. 3) Revises CLIMB chart to reflect 120 kt climb speed. 4) Revises CRUISE PERFOMRANCE charts: for each recommended power setting no has a SEPARATE page for ISA -20C, ISA, and ISA +20C performance. UPDATES TO SECTION VI: WEIGHT AND BALANCE 1) No changes. (COMMENT: Remember that airplane-specific equipment list and any other records of empty weight and moment need to be transferred to replacement POH). UPDATES TO SECTION VII: SYSTEMS DESCRIPTION 1) WING FLAPS section adds: a) Description of wing flap position indicating system. b) Effects of lowering flaps in flight: i) Attitude Nose Down ii) Airspeed Reduced iii) Stall Speed Reduced.
Page 5 of 7 2) BAGGAGE COMPARTMENT section adds warning: Do not carry children in the baggage compartment unless secured in a seat. 3) PROPELLER section: repeats the change in tolerance to the low pitch setting. 4) VOLTAGE REGULATOR section adds: Following an over-voltage shutdown the LOW bus VOLTS annunciator will illuminate when the bus voltage falls below 25 volts. 5) EXTERNAL POWER RECEPTICLE section: After before connecting an external power unit, ensure that a battery is installed in the airplane, adds: Turn the battery ON and all avionic and electrical switches OFF. This protects the electronic voltage regulators and associated electrical equipment from voltage transients (power fluctuations). If polarity is reversed, a diode in the coil circuit will prevent contactor operation. 6) INTERIOR LIGHTING section adds, under COURTESY LIGHTS, To reset the timer for the step light and courtesy light, both doors must be closed and latched. The lights will illuminate when either door or both doors are opened. (COMMENT: This refers to illuminating the lights after they were already illuminated, and extinguished after the 15-minute timer has timed out ). 7) OXYGEN SYSTEM section adds a new note: Push oxygen control knob OFF until inflight use is required. System must be OFF for takeoffs and landings. (COMMENT: This note is repeated several times in the OXYGEN SYSTEM section. The requirement for the knob to be OFF for takeoff and landing, a very good idea, does not appear as a LIMITATION in SECTION II). 8) INSTRUMENT AIR PRESSURE SYSTEM adds a note mentioning the existence of the standby instrument air pressure system. 9) STALL WARNING HORN section adds a note: The stall warning horn is inoperative when the battery and alternator switches are turned off. Airplane certification requires the stall warning system be on during flight except in emergency conditions as stated in SECTION 3, EMERGENCY PROCEDURES. 10) ENGINE BREAK-IN PROCEDURES section: a) Changes MIL-SPEC references with SAE specifications. b) To: Failure to remove the corrosion-preventative oil and replace the oil filter within the time interval specified may cause varnish deposits to form on the pistons and cylinders walls... adds and deteriorate the filter element. c) Changes Use full throttle for every takeoff and maintain until at least 1000 feet AGL to at least 400 feet AGL. d) Changes Maintain the highest power recommended for cruie operation during the break-in period to during the break-in period (50 to 75 hours) and interrupt cruise power every 30 minutes or so by smoothly advancing to takeoff power settings for about 30 seconds, then return to cruise power. e) Changes Avoid long power-off descents to Avoid long power-off descents especially during the break-in period. UPDATES TO SECTION VIII: HANDLING, SERVICING AND MAINTENANCE 1) PARKING section: to To set the parking brake, pull the parking brake control knob out add (T-handle on serials EA-441 and after). 2) PROLONG OUT OF SERVICE CARE section: a) Under MOORING, remove Attach a line to the nose gear. b) Under FLIGHT CONTROL SURFACES change Lock with internal locks to Lock with internal and external locks. 3) EXTERNAL POWER section adds: A battery must be installed in the airplane. 4) OIL SYSTEM section expands on the oil change procedure. 5) TIRE section adds new note: While Raytheon Aircraft Corporation cannot recommend the use of recapped tires, tires retreaded by an FAA-approved repair station with a specialized service-limited rating in accordance with the latest revision of TSO-C62 may be used. 6) INSTRUMENT AIR PRESSURE SYSTEM section:
Page 6 of 7 a) Regarding the pump intake filter, changes replace this filter on condition to this filter should be changed every 100 hours or annually, whichever comes first. If the airplane is operated in dusty conditions, the filter should be changed more frequently. (COMMENT: This 100-hour recommendation is not repeated, and sometimes contradicted with higher values, elsewhere in the POH). b) Regarding the intake and inline filters, adds: Both filters are to be changed whenever the pressure pump is replaced. Refer to Airborne Service Letter 59A or later revision for latest recommendations. 7) LUBRICATION POINTS AND DIAGRAMS section changes MEK to MPK. 8) RECOMMENDED SERVICING SCHEDULE section: a) Reformats the tables. b) Adds 100-hour clean fuel injection control valve screen recommendation. c) Changes 500-hr Change pressure pump intake filter to a 100-hr recommendation. d) Changes AS REQUIRED, NOTE 3 Check emergency locator transmitter battery to Recharge or replace ELT battery. 9) CONSUMABLE MATERIALS section: a) Reformats the tables. b) Changes Lubricating grease, Molybdenum Disulfide from Aeroshell grease No. 17 or MIL-G-21164 to MIL- M-7866. c) To Lubricating Oil, General Purpose adds Alternates: CRC 3-36, LPS No. 1, WD-40. d) To Lubricating Grease, Wheel Bearing removes the note Do not mix. e) Makes several changes as applicable to the above, to the notes section of the table. f) Updates the APPROVED ENGINE OILS list. g) LAMP REPLACEMENT GUIDE table adds entries for: i) Control wheel map light (prior to EA-696) and (EA-696 and after). ii) Flashing beacon (EA-491 and after)(whelen). h) Changes All hose section to Hoses carrying flammable liquids. i) Adds All other hoses: On condition. 10) PROPELLER section: a) changes At engine overhaul or at unscheduled engine change but not to exceed McCauley 1500 hours or 5 years whichever occurs first to Propeller (McCauley): 1600 hours or 5 calendar years. b) Adds: Propeller (Hartzell): Refer to supplement. 11) FUEL SELECTOR VALVE section changes Overhaul every 10 years to Inspect every 500 hours; overhaul every 1500 hours. 12) INSTRUMENTS section: a) Change Pressure system pump intake filter every 500 hours in-line filter every 300 hours to Instrument pressure system pump intake filter and in-line filters: every 300 hours. (COMMENT: This contradicts earlier guidance to replace the pump inlet filter every 100 hours). b) Adds All other instruments: on condition. 13) ELECTRICAL SYSTEM section changes Starter inspect at engine overhaul; overhaul or replace on condition to Overhaul or replace at engine overhaul or replace on condition. 14) FLAPS AND FLIGHT CONTROLS section adds the reminder that any time the control surfaces are altered, repaired, or repainted, they must be rebalanced per the Bonanza Maintenance Manual. (COMMENT: Elsewhere this is referred to as the Bonanza Series Maintenance Manual). 15) NOTES section at the end of the table adds: a) (Engine TBO): The recommended engine overhaul period applies to engines with nickel-coated exhaust valves or nimonic exhaust valves, provided that normal periodic inspections properly (are) carried out with
Page 7 of 7 particular attention to throttle response, smooth power, and oil consumption, a qualified certified mechanic must determine that the engine is operating normally at the time of each periodic inspection. b) (TBO): When an engine has been overhauled or a new engine installed, it is recommended that high power settings be used until oil consumption has stabilized. The average time for piston seating is approximately 50 hours. (COMMENT: High power settings is elsewhere defined as 75% or greater power. This translates to use of the maximum cruise power setting of 31 inches MP/2400 rpm and a TIT at or below 899C on the rich side of peak, per SECTION 5: PERFORMANCE). c) (Hoses): Time limited item. Refer to 14 CFR Part 91. UPDATES TO SECTION IX: SUPPLEMENTS 1) No changes. (COMMENT: Remember that airplane-specific supplements need to be transferred to replacement POH). UPDATES TO SECTION X: SAFETY INFORMATION 1) No changes. (COMMENT: Section 10 has not been updated with this revision. It is still dated May 1994). (end) Return to home page