Document Na Mix-0891~1 DIAMOND IA MU-300 PILOT’S OPERATING MANUAL ORIGINAL ISSUE JANUARY 6, 1986 REVISION DATE April 1, 1988 THE INFORMATION CONTAINED IN THIS PILOT'S OPERATING MANUAL IS NOT FAA APPROVED, IF ANY DATA INCONSISTENCY EXISTS BETWEEN THIS MANUAL AND THE FAA APPROVED AIRPLANE FLIGHT MANUAL, THE AIRPLANE FLIGHT MANUAL SHALL BE THE GOVERNING AUTHORITY. MITSUBISHI HEAVY INDUSTRIES, LT! (LOGO CHANGE 4-1-96) THIS PUBLICATION IS APPLICABLE TO SERTAL NUMBERS AQ6GSA, ADE9SA AND SUBSEQUENT, AND THOSE MODIFIED GY SERVICE RECOMMENDATION SR 71-001.Sy }‘ating Manual Document NO, MR-O891-1 ‘Always destroy superseded pages when you insert revised pages. LOG OF REVIS{ONS Rev, Nunber Date Sections affected Original January 6, 1986 a Rev. 1 October 15, 1986 Section 3 Rev. 2 duly 1, 1987 Section 3 Rev. 3 April 1, 1988 Section 4 NOTE:A list of the effective pages will be found in the Rev. next successive page of the title page. 3MITSUBTSHE PILOTS OPERATING MANUAL EFFECTIVE Mu-300 DIAMOND IA PAGES Section Page Date Section Page Date LIST OF EFFECTIVE SECTION 2 2-3 dan 6/86 PAGES 1 Apr 1/88 2-4 Jan 6/86 *2 Apr 1/88 2-8 Jan 6/86 «3 Apr 1/88 2-6 Jan 6/86 *4 Apr 1/88 2-7 Jan 6/86 *5 Apr 1/88 2-8 Jan 6/36 2-9 Jan 6/86 RECORD OF REVISIONS *1 Apr 1/88 2-10 Jan 6/86 2-11 dan 6/86 RECORD OF 2-12 Jan 6/86 TEMPORARY REVISIONS 1 dan 6/86 SECTION 3 i Jan 6/36 REVISION JNSTRUCTIONS 1 Jan 6/86 ii dan 6/86 iii Jan 6/86 SECTION 1 i dan 6/86 iv Jan 6/86 1-1 dan 6/86 y Jan 6/86 1-2 Jan 6/86 3-1 dan 6/86 1-3 Jan 6/86 3-2 lan 6/86 1-4 Jan 6/86 3-3 Jan 6/86 1-5 Jan 6/86 3-4 dan 6/86 1-6 Jan 6/86 3-5 Jan 6/86 1-7 dan 6/86 3-6 Jan 6/86 1-8 Jan 6/86 3-7 Jan 6/36 1-9 Jan 6/86 3-8 Jan 6/86 1-10 Jan 6/86 3-9 Jan 6/86 ill dan 6/86 3-10 dan 6/86 1-12 Jan 6/86 3-11 Jan 6/86 1-13 Jan 6/86 3-12 Jan 6/86 1-14 Jan 6/86 3-13 Jan 6/86 1-15 Jan 6/85 3-14 Jan 6/86 1-16 Jan 6/86 3-15 Jan 6/86 1-17 dan 6/86 3-16 Jan 6/86 1-18 Jan 6/86 3-17 Jan 6/86 1-19 Jan 6/86 3-18 Jan 6/86 1-20 Jan 6/86 3-19 Jan 6/86 1-21 Jan 6/86 3-20 Jan 6/86 1-22 Jan 6/86 3-21 Jan 6/86 1-23 Jan 6/86 4-22 Jan 6/86 1-24 Jan 6/86 3-23 Jan 6/86 1-25 Jan 6/86 3-24 Jan 6/86 1-25 Jan 6/86 3-25 Jan 6/86 1-27 Jan 6/86 3-26 Jan 6/86 3-27 Jan 6/86 SECTION 2 i Jan 6/86 3-28 Jan 6/36 2-1 Jan 6/86 329 Jan 6/86 2-2 Jan 6/86 3-30 Jan 6/86 * Denotes pages revised ** Denotes nages added () Denotes pages deleted Page 1 Jan 6/86 Rev 3. Apr 1/88MITSUBISHI PILOTS OPERATING MANUAL EFFECTIVE Mu-300 DIAMOND IA PAGES ) Section Date Section Page Date SECTION 3 Jan 6/86 SECTION 3 3-76 Jan 3/86 Jan 6/86 3:77 Jan 6/86 Jan 6/86 3-78 Jan 6/86 Jan 6/86 3:79 Jan 6/86 Jan 6/86 3:80 Jan 6/86 dan 6/86 3-81 Jan 6/86 Jan 6/86 3-82 Jan 6/86 Oct 15/86 3-83 Jan 6/86 Jan 6/86 3-84 Jan 6/86 Jan 6/86 Jan 6/86 Jan 6/86 Jan 6/86 Jan 6/86 Jan 6/86 Jan 6/86 Jan 6/86 Jan 6/86 Jan 6/85 Jan 6/86 Jan 6/86 Jan 6/86 Jan 6/86 Jan 6/86 Jan 6/86 Jan 6/86 dan 6/36 Jan 6/86 dan 6/86 Jan 6/86 Jan 6/86 Jan 6/86 Jan 6/86 Jan 6/86 Jan 6/86 Jan 6/86 Jan 6/86 y Jan 6/86 Jan 6/86 } Jan 6/86 Jan 6/86 Jan 6/86 Jan 6/86 Jan 6/86 Jan 6/86 Jan 6/86 Jan 6/86 Jan 6/86 Jan 6/86 Jan 6/86 Jan 6/86 Jan 6/85 van 6/86 Jan 6/86 Jan 6/86 Jan 6/88 Jan 6/86 Jan 6/86 van 6/86 Jan 6/85 Jan 6/86 Jan 6/86 San 6/86 Jan 6/86 Jan 6/86 Jaa 6/85 Jan 3/86 Jan 6/86 Jan 6/8" Jan 6/86 Jan 6/86 sul 1/87 Jan 6/36 sul 1/87 Jan 6/86 dan 6/86 Jan 6/86 Jan 6/86 Jan 6/86 Jan 6/86 Jan 6/86 * Denotes pages revised ** Denotes pages added ) {) Denotes pages deleted Page 2 / Jan 6/86 Rev 3. Apr 1/88MITSUBESHT PILOTS OPERATING MANUAL EFFECTIVE MU-300 DIAMOND IA PAGES: Section Page__Date Section Page Date SECTION 3 3-121 Jan 6/86 SECTION 4 4-18 Jan 6/86 3-122 Jan 6/86 4-16 Jan 6/86 3-123 Jan 6/86 4-17 dan 6/86 3-124 Jan 6/86 Jan 6/86 3-125 dan 6/86 Jan 6/86 3-126 Jan 6/86 0 dan 6/86 3-127 Jan 6/86 21 Jan 6/86 dan 6/86 22 Jan 6/86 Jan 6/86 23 Jan 6/86 Jan 6/86 24 Jan 6/85 Jan 6/86 4-25 Jan 6/86 3-132 Jan 6/86 4-26 Jan 6/86 3-133 Jan 6/86 4-27 lan 6/86 3-134 Jan 6/86 4-28 Jan 6/86 3-135 Jan 6/86 4-29 Jan 6/86 3-136 Jan 6/86 4-30 dan 6/86 3137 Jan 6/86 4-31 Jan 6/86 3-138 Jan 6/86 4-32 Jan 6/86 3-139 Jan 6/86 4-33 Jan 6/86 3-149 Jan 6/86 4-34 Jan 6/86 3-141 Jan 6/85 4-35 Jan 6/86 3-142 Jan 6/86 4-36 Jan 6/86 3-13 Jan 6/86 4-37 Jan 6/86 3-144 Jan 6/86 4-38 Jan 6/86 3-145 Jan 6/86 4-39 Jan 6/86 3-106 Jan 6/86 4-40 dan 6/86 3-147 Jan 6/86 4-41 Jan 6/86 3-148 Jan 6/86 4-42 Jan 6/86 3-143 Jan 6/86 4-43 Jan 6/86 3-150 Jan 6/86 4-44 Jan 6/86 4-45 Jan 6/86 SECTION 4 i Jan 6/86 4-46 Jan 6/86 4-1 Jan 6/86 4-47 Jan 6/86 4-2 Jan 6/85 13 dan 6/86 4-3 Jan 6/86 9 Jan 6/86 4-4 Jan 6/86 0 dan 6/86 4-5 Jan 6/86 4-51 Jan 6/86 4-6 Jan 6/36 4-52 Jan 6/86 4-7 Jan 6/86 4-53 Jan 6/86 4-8 Jan 6/36 4-54 dan 6/86 4:3 Jan 6/86 4-55 Jan 6/86 *4-10 Apr 1/88 4-56 Jan 6/85 4-11 Apr 1/88 4-57 Jan 6/86 4-12 Jan 6/86 4-58 Jan 6/86 4-13 Jan 6/86 4-59 Jan 6/85 4-14 Jan 6/26 4-60 Jan 6/86 * Denotes pages revised ** Denotes pages added () Denotes pages deleted Page 3 Jan 6/86 Rev 3 Apr 1/88MITSUBISHE PILOTS OPERATING MANUAL EFFECTIVE MU-300 DIAMOND TA PAGES Section Date Section Page Date SECTION 4 Jan 6/86 SECTION « 4-107 Jan 6/86 dan 6/86 4-108 Jan 6/86 Jan 6/86 4-109 Jan 6/86 Jan 6/86 4-110 Jan 6/85 Jan 6/86 4-110 Jan 6/86 Jan 6/86 4-111 Jan 6/86 Jan 6/86 4-112 dan 6/86 dan 6/86 4-113 Jan 6/36 Jan 6/86 4-114 Jan 6/86 Jan 6/86 4-115 Jan 6/86 Jan 6/86 4-116 Jan 6/86 Jan 6/86 4-117 Jan 6/86 Jan 6/86 4-118 Jan 6/86 Jan 6/86 4-119 Jan 6/86 Jan 6/36 4-120 Jan 6/86 Jan 6/86 4-121 Jan 6/85 Jan 6/86 4-122 Jan 6/86 Jan 6/86 4-123 Jan 6/86 dan 6/86 4-124 Jan $/86 Jan 6/86 4-125 Jan 6/86 Jan 6/86 4-126 Jan 6/86 Jan 6/86 4-127 Jan 6/86 Jan 6/86 4-128 dan 6/86 Jan 6/86 4-129 Jan 6/86 Jan 6/86 4-130 Jan 6/86 Jan 6/86 4-131 Jan 6/86 Jan 6/86 4-132 Jan 6/86 Jan 6/86 4-133 Jan 6/86 Jan 6/86 4-134 dan 6/86 Jan 6/86 4-135 Jan 6/86 Jan 6/86 4-136 Jan 6/86 Jan 6/86 4-137 Jan 6/86 Jan 6/86 4-138 Jan 6/86 Jan 6/86 4-139 dan 6/86 ‘lan 6/86 4-140 Jan 6/86 dan 6/86 4-141 Jan 6/86 Jan 6/86 4-142 Jan 6/86 Jan 6/86 4-143 Jan 6/86 san 6/86 4-144 Jan 6/86 Jan 6/86 4-145 Jan 6/86 Jan 6/86 4-146 Jan 6/86 dan 6/86 4-147 Jan 6/86 Jan 6/86 4-148 Jan 6/86 Jan 6/86 4-149 Jan 6/86 dan 6/86 4-150 dan 6/86 Jan 6/86 4-151 Jan 6/86 * Denotes pages revised * cenotes pages added () Denotes pages deleted Page 4 Jan 6/86 Rev 3. Apr 1/88 >MITSUBISHI PILOTS OPERATING MANUAL EFFECTIVE My-300 DIAMOND TA PAGES Section Page Date Page _Date SECTION 4 4-152 dan 6/66 4-153 Jan 6/86 4-154 Jan 6/86 4-155 dan 6/86 4-156 dan 6/86 4-157 Jan 6/86 4-158 Jan 6/86 4-159 dan 6/86 4-160 Jan 6/86 4-161 Jan 6/86 4-162 Jan 6/85 4-163 Jan 6/86 4-164 Jan 6/86 4-165 dan 6/86 4-166 Jan 6/86 4-167 Jan 6/86 4-168 Jan 6/86 4-169 Jan 8/96 4-170 Jan 6/86 4-171 Jan 6/86 4-172 Jan 6/86 4-173 Jan 6/86 4-174 Jan 6/86 4-175 dan 6/86 4-176 Jan 6/86 4-177 Jan 6/86 4-178 dan 6/86 4-179 dan 6/86 4-180 Jan 6/86 4-181 Jan 6/86 4-182 dan 6/86 4-183 Jan 6/86 4-184 Jan 6/86 4-185 Jan 6/86 4-186 Jan 6/86 4-187 Jan 6/36 4-188 Jan 6/86 4-189 Jan 6/86 4-190 Jan 6/86 * Denotes pages revised ** Denotes pages added () Denotes pages deleted Page 5 Jan 6/86 Rev 3 Apr 1/88MITSUBISHE PILOTS OPERATING MANUAL RECORD OF MU-300 DIAMOND TA REVISTONS RECORD OF REVISIONS eS TSSUE, DATE REV ISSUE. DATE No. DATE INSERTED BY No. DATE INSERTED BY 1 Oct 15/86 2 | oui 1/87 7 [3 | Aor 1/88 RECORD OF REVISIONS Page 1 Apr 1/88MITSUBISHI PILOTS OPERATING MANUAL ‘TEMPORARY MU-300 DIAMOND IA REVISIONS RECORD OF TEMPORARY REVISIONS TEMPORARY | PAGE ISSUE ~T DATE REV. NG. NUMBER DATE BY REMOVED BY [31 3-64 Mar 1/85 | MAL Jan 6/86 MAL Page 1 dan 6/86MITSUBISHI PILOTS OPERATING MANUAL REVISION MJ-300 DIAMOND TA INSTRUCTIONS REVISION INSTRUCTIONS Revisions will be prepared and issued as required to update or correct exis- ting material. It is the pilot's responsibility to assure revisions are ‘incorporated and that the manual is current at all times. For this purpose, a List of Effective Pages is included with each revision, The List of Effective Pages serves as a cross-check to validate the accuracy of the manual, Should the List of Effective Pages disagree with the actual pages after insertion into the manual, contact Mitsubishi Aircraft Interna tional, Engineering Technical Publications for clarification. The List of Effective Pages contains the section, page number and date of each page. Single and double asterisks are used next to the,page number to identify pages which are being revised or added, respectively. Parentheses are used to identify pages deleted. Revisions, additions, and deletions to material will be identified on individ— ual pages by the letter R along the left margin adjacent to that portion of the text affected. The revision date and revision number will be added to the bottom of each page which has been affected. The letter R in the left margin opposite the section, page number, and date will indicate the text is unchanged but relocated to a different page. Page 1 Jan 6/86MITSUBISHI PILOTS OPERATING MANUAL SECTION 1 MU-300 DIAMOND IA GENERAL SECTION 1 GENERAL CONTENTS. Page INTRODUCTION .... THE AIRPLANE . GENERAL ARRANGEMENT ....05 1-3 DIMENSION, AREAS, AND GENERAL DATA .. 1-22 Page i van 6/86MITSUBISHI PILOTS OPERATING MANUAL SECTION 1 MU-300, DIAMOND TA GENERAL INTRODUCTION This manual consists of four sections and contains necessary information for the safe and efficient operation of the MU-300 (DIAMOND TA), This docunent also provides general information on the airplane, its systems, operating limitations and performance, Section 1 provides general information such as location of control surfaces, their area dimensions, and deflection angles. Section 2 contains information on the operating limitations which affect the airplane. Section 3 provides a brief descriotion and operational procedures for the airplane and its systems, Section 4 contains flight planning data (tables and charts) and related information which affect the performance of the airptane. THE AIRPLANE The MU-300, certified in accordance with FAA FAR Part 25, is an all metal, low wing airplane powered by two Pratt and Whitney J7250-4D turbo- fan engines, The engines are mounted on the aft fuselage to improve directional control of the airplane in the event of engine failure. Structure The wings and fuselage are of conventional, semi-monocoaue construc- tion. The advanced design swept wing has a two spar, box beam structure. Fuselage The multiframe fuselage is oval shaped to provide more cabin room and passenger comfort, The major frames are the forward and aft pressure bulkheads, frames at the entrance and the escape hatch, mounting frames for front and rear wing spars, the engine carry-thry beam mounting frames, and the vertical tail mounting frame. Landing Gear The airplane is equipped with retractable landing gear consisting of nose and main gear assemblies. The nose gear assembly retracts for- ward into a well located in the nose. Mechanical linkage connected to the rudder pedals provide nose wheel steering capability. The two single-wheel, wing-nounted main landing gear retract inboard ‘into the fuselage. ach main wheel has anti-skid equipped brakes with independent systems and a pneumatic backup system. Emergency gear extension is accomplished through a free fall system. Page 1-1 Jan 6/86MITSUBISHI PILOTS OPERATING MANUAL SECTION 1 ‘-300 DIAMOND IA GENERAL Flight Controls Dual mechanical controls, with a three-axis electrical trim, operate the spoilers, rudder and elevator. A yaw damper system, independent of the rudder, is also provided. The spoilers are electrically actuated and hydraulically operated, providing a speed brake/lift dump capability, Full span, single and double slotted (aft) fowler flaps are also electrically actuated and hydraulically operated. Fuel System Two independent integral wing tanks and af aft fuselage tank are provided. Two Jet pumps with backup electric boost pumps feed the engines. The electric pumps also have crossfeed capability, Hydraulic System Each engine drives a hydraulic pump which provides 1,500 psi Aydrau- Vic pressure to operate Janding gear, flaps, gear doors, anti-skid/ power brake, speed brake/lift dump systems, and thrust reverser, if installed. Flectrica? System The electrical system includes two 20V DC, 400 ampere starter- generators, one 24¥ DC, 36 ampere-hour Nickel Cadmium (Ni-Cad) battery, two 600V ampere solid state inverters, a dual parallel bus power distribution system, and an external power receptacle. Environmental Pressurization of 9.1 psi provides a sea level altitude in the cabin up to 24,000 feet (7,315 m) and a comfortable 6,400 feet (1,950 m) cabin altitude up to 41,000 feet (12,497 m). Cabin air is’ condi- tioned by an 18,000 BTU/hr air conditioning system, Ice Protection Engine air intakes and wing leading edges are anti-ice heated by engine bleed air, The front windshields, pitot-static systems, AGA transmitter probes, and horizontal stabilizer leading edges are electrically heated. Windshield winers are provided for rain removal. Page 1-2 Jan 6/86MITSUBISHI PILOTS OPERATING MANUAL SECTION 1 Mu-300 DIAMOND TA GENERAL Standard Avionics Standard equipment on the MU-300 includes dual NAV-cOMM, ADF, DME, transponder, dual compass systems, dual RMI's, integrated Flight contro) system with pilot's flight director, altitude encoding, and dual audio systems. GENERAL ARRANGEMENT Exterior arrangement of the airplane is shown in Figure 1-1, Interior Arrangement The cabin compartment is divided into two sections: flight compart- ment and passenger compartment. The flight compartment contains the pilot and copilot seats, instrument control panels and other equip- ment. Refer to Figures 1-2 through 1-5 for instrument and contro? paneis. The passenger compartment contains the passenger seats. It is a private room including a toilet and baggage area, entry door, emergency escape hatch, and convenience equipment for passengers such as @ galley, coat rack, and card table, Page 1-3 dan 6/96MITSUBISHI PILOTS OPERATING MANUAL SECTION 2 MU-300 DIAMOND 1A GENERAL 2. RADOHE 2) NEATHER RADAR (OPTIONAL) 3] G5 ANTENNA al prray Tuae on ? ELECTRONIC EQUIPMENT COMPARTHENT WINOSHIELO WIPER ‘YHE CONM 1 ANTENNA {S/N AQO3SA THROUGH A0895A) 7k, VHF COMM 1 ANTENA (S/W AO90SA AND SUBSEQUENT) EMERGENCY HATCH 3 WAVIGATION LIGHT 16, STATIC OTSCHARGER (TYPICAL) 1) po. TRIM 12) MAW FLAP 130 AFT FLAP. 14. ouraoaRo spotter 15. sNpoaRO SPOILER 16. ADE ANTENNA, U7. aM AIR-TALET. 18. HRI ZONTAL $taszc17ER 19! ELevaroR (TYPICAL BOTH SIDES) 20. NAVIGATION LIGHT 212 ROTATING BEACON LtGHT 32. numer $3. AUODER TRIM TAB 24. ANTY-COLLISION LIGHT 25. VOR ANTENNA (TYPICAL 80TH SIDES) AFT FUSELAGE FIN ENTRANCE 0008 AOA TRANSKITTER (TYPICAL g0TH SIDES) STALL STRIP Fence LANDING. r6HT + HARKER BEACON TRANSPONDER 1 ANTENNA TRANSPONDER 2. ANTENNA 3. OME 2 ANTENNA (OPTIONAL) RADIO ALTIMETER + RADIO. ALTIMETER ANTENNA OWE 1 ANTENNA VHF CORY 2 ANTENNA STATIC PORT (TYPICAL BOTH SIDES) 2 s«q0 FLITEFORE ANTENA (OPTIONAL) > VENTRAL FW YAW DUMBER AE ANTENNA (OPTIONAL) General Arrangement Figure 1-1 Page 1-4 Jan 6/86MITSUBISHI MU-300 PILOTS OPERATING MANUAL DIAMOND TA (THIS PAGE INTENTIONALLY BLANK) SECTION 1 GENERAL Page 1-5 dan 6/86MITSUBISHI PILOTS OPERATING MANUAL SECTION 1 ‘MU-300 DIAMOND IA GENERAL 45% 7 Be own RBH es F493 oF ma 7076 75 74 73 ‘STANDBY COMPASS AOA INDEXER MASTER CAUTION RNMUNCTATOR AND RESET SWITCH | MASTER WARIING ARNUNCLATOR AND RESET SMLTCH 5. ENGINE FIRE RELL CUTOFF SWITCH 8. SMOKE WORN CUTOFF suITCH 1. TwRUST REVERSER EMER STOW SWITCH 8 SHROUD ALNUNCIATOR PAREL. 50, STAY POWER SwITCK. 9, OT 1 ARMED PUSH SUITCH STAY FUSE BYPASS. SWITCH 10; LH FUEL/MYD VALVE SHUTOFF SWETCH 52. COMPASS SLAVE SWITCH (COMP 1) DIL_PRESS & TENPERATIRE 1NOICATOR CONSUMED FUEL TOTAL IZER HYORAULIC PRESSURE “LADIcaTOR HYDRAULIC DRESSURE RELIEF. SWITCH ENGINE VERRATION [NOICATOR FLIGHT HOUR METER, BATTERY TEMPERATURE INDICATOR COM HOWE SKETCH VERTICAL GYRO FAST ERECT SWITCH 11. LH ENGINE FIRE PUSH SwITCH 53! COMPASS WOOE SuITCH (CORP 1) 12) AM ENGINE FIRE PUSH SwITCH 58) RADIO CONTROL PANEL, 13) RH FUEL/HYO VALVE SWTOFE SWITCH 55! WEATHER RADAR INOLCATOR (OPTIONAL) 24) gr 2 ARMED PUSH SuITCH 56) ADF coNTROL UNIT 15, NAV SELECT SWITCH (OPTIONAL) 57 ATC CONTROL UNIT 16) MARKER REACON LIGHT 58) eLacaRO (SPEEO LivITATLONS) 17, AIRSPEED Mace TNOTCATOR 58, AIRSPEED MACH THOTCATOR IB, ANGLE OF ATTACK (ADA) TuoLcaTOR 60! RADIO MAGNETIC INDICATOR (RMI) 19; RADIO MAGNETIC tROLCATOR (MI) 61 OME INOICATOR 20) FLIGHT TIME RESET SWITCH 62. FLIGHT DIRECTOR mone aNNUNCLATOR 21; icra cack 63. ATTITUDE DIRECTOR {NDLCATOR (401) 221 ONE INDICATOR (OPTIONAL) (oprtoat) TIGHT DIRECTOR MODE ANNUNCIATOR 64. HORIZONTAL STTUATION INDICATOR (HSI) 28) ATTITUDE DIRECTOR THOLCATOR (A01) |” (OPTIONAL) 25! MoRIZONTAL SITUATION INO[CATOR 65. AUTOPILOT TRANSFER SKITCH (ws) (oertawat | AL SETTING gus MARKER BEACON LIGHT 2AD10 ALTITUDE 1e9tcarOR RARONETIC PRESSURE ALTIMETER BAROMETIC PRESSURE ALTINETER INSTANTANEOUS VERTICAL SPEED TRSTANTAREOUS VERTICAL. SPEED TwolcaToR:(i¥st) ioicaroa (Tvs!) 89. Tua ema TNOLeATOR 30, fan ALR TESPERATURE (PAT) 10. SAT/TASITAT INDICATOR (OPTeOHAL} Two icaroe 71, eigat oay cLocK 31, THRO ATTITUDE tuorearoa 72) RAERGENTY LOCATOR TRANSMITTER SULTCH 32) ALTITUDE ALERT CONTROLLER 73. Conpass Wode SkiToH (oa 2), 33, a tav INDLCETOR (OPTIONAL) 74) cawmass SLAVE SaLTCH (COMP. 2) 34! QVERRINE SaTTon [LA¥OING Gene) 75! VERTICAL GFRO FAST ERECT SulTCH 35. FUEL TenpeRarUne. IROL ATOR 48. wav 2-AC SUITCH 260 AC 38) Lewo1ne GEAR cOnROL UNIT 77. cape Rare OF Ui¢a 1HOtcATOR 37. Fan gem (4) INOcCATOR 78! CABIN ALTITUDE OIFFERENTTAL, PRESSURE Je! inten TuRsine TeHPERATURE PaotcaroR Inotearoa 79, CaRLN AIR PRESSURE CONTROLLER 38. TuRpine APM (2) _worcaTor 80, CARIN PRESSURE & TEMPERATURE a0 Poet Fuow tnotekroR fanTaot BaNet Cockpit Forward View - Instrument Panel and Shroud Panel (Typical) Figure 1-2 (Sheet 1 of 2) EFFECTIVITY: S/N AQO3SA THROUGH AOB9SA Page 1-6 Jan 6/86MITSUBISHI PILOTS OPERATING MANUAL ‘SECTION 1 ‘MU-300, DIAMOND IA. ‘GENERAL hawk bt \d “ b hevesdstsd 1. STANDBY coMPass, 2 AOR THOERER 3, MASTER CAUTION ANNUNCTATOR AND RESET SWITCH 4, MASTER WARING ANNUNCTATOR AND RESET SWITCH ENGINE FIRE BELL _cUTOF SuITCH SMOKE HORN. CUTORF SWITCH 72 saROvO anowactaTOR PANEL 8 FOT 1 ARMED PUSH SUITCH 9 Li euEL/uvo VALUE SHUTOFE SuITcr 10) LH ENGINE FIRE PUSH SHITCH AL! RH ENGINE FIRE PUSH SWITCH 12) RH EUEL/HYD VALVE SHUTOFE SMITE 13) ROT 2 ARMED PUSH SWITCH 18) AUTOPILOT TRANSFER SWITCH? wolcaton 15, VLE/VHE NAY SELECT SUETCH Ig, AIRSPEED MACH [HOLCATOR 17. ANGLE OF ATTACK (AOA) TNDECATOR 1B. RADIO MAGNETIC INDICATOR (861) 19, EIGHT oay cLock 20. OME TxntcaToR 20, AUTO. CONTROL PANEL 22, COMP 1 Faee/SLAVE SWITCH 23) COMP I Man/SLAvE SuLTCH 24. VG 1 FAST ERET SwiTCH 25, HARKER REACON M1/LO SWITOU 26. FLIGHT DIRECTOR MODE ANNUNCIATA: 27° ATTITUDE DIRECTOR INDICATOR (AD 28, HORIZONTAL SITUATION INDICATOR (Hs) 29, ALTIMETER 30, INSTANTANEOUS VERTICAL SPEED INOICATOR (1VSI) 31. ALTITUDE ALERT ConTROLLER 32. OVERRIDE SWITCH (LANDING GEAR) 33. FUEL TEMPERATURE INDICATOR 38. LANDING GEAR CONTROL URET BATTERY TEMPERATURE [NOICATOR ENGINE VIBRATION THOLcATOR HYORAULIC PRESSURE RELIEF SWITCH HYORAULIC PRESSURE INDICATOR Ny sertine pus FAN REM (1) TNO tcATOR THTER TURSINE TEMPERATURE Enplcarom (111) TURBINE RPM (ho) twOICATOR FUEL, FLOW INOTCATOR ‘OIL PRESS ND TEMPERATURE INDICATOR ARNUNCLATOR PAWEL FLAP POSCTION INDICATOR THIRD. ATTITUDE. INDICATOR STBY POKER SWITCH ; STRY FUSE BYPASS swITcH CONSUMED FUEL TOTALIZER TRAN ALR TEMERATURE (RAT) INOICATOR FUEL QUANTITY [ROECATOR (FUSELAGE TANK) FUEL QUANTITY [NOICATOR (WING TANK) {WEATHER RADAR INDICATOR (OPTIONAL) AUTOPILOT TRANSFER INOICATOR RAROMETIC PRESURE ALTIMETER CABIN AIR PRESSURE CONTROLLER CABIN ALTITUDE /OLFFERENTIAL PRESSURE INDICATOR CARIN RATE OF CLIMB THOICATOR NAV 2 AC 26V AC SHITCH OrGrTAL clock ‘CABIN PRESSURE ARO TEMPERATURE CONTROL, PaMEL . CONP 2 MAN SLAVE. SUITCH COMP 2 FREE/SLAVE SAYTCH WG 2 FAST erect suite CLOCK FT RESET SwtTH 7 ENERSENCY LOCATOR’ TRANSMITTER SwITCH CABIN’ SMOKE. TNDTCATOR 4 H sa, 5, 60. a 62 n it 6, Cockpit Forward View - Instrument Panel and Shroud Panel (Typical) EFFECTIVITY: S/N AO9OSA AND SUBSEQUENT Figure 1-2 (Sheet 2 of 2) Page 1-7 Jan 6/86MITSUBISHI PILOTS OPERATING MANUAL SECTION 1 ‘NU-300 DIAMOND IA GENERAL 0139103 Cockpit Forward View - Center Pedestal Figure 1-3 (Sheet 1 of 4) EFFECTIVITY; S/N AQO3SA THROUGH A0B9SA Page 1-8 Jan 6/86MITSUB MU-300 ISHI EFFECTIVITY: PILOTS OPERATING MANUAL SECTION 1 DIAMOND 1A GENERAL, + FO MODE SELECTOR VLF/OMEGA NAV CONTROLLER (OPTIONAL) + FLIGHT RECORDER CONTROLLER (OPTIONAL) FO MODE SELECTOR (OPTIONAL) + FUEL QUANTITY INDICATOR (AFT FUSELAGE TANK) FUEL QUANTITY INDICATOR (¥ING) VOLT/ANP METER FLAP POSITION INDICATOR « ENGINE START SWITCH ENGINE START SELECT SWITCH + ENGINE START DISENGAGE SWITCH . NORM-EMER PITCH TRIM SELECT SWITCH ~ EMER PITCH TRIM SWITCH . RUDDER TRIM POSITION INDICATOR RUDDER TRIM SWITCH . ENGINE THRUST LEVERS + REVERSER LEVERS (OPTIONAL) ENGINE FRICTION LEVER }. AUTOPILOT ROLL TRIM CPL/OFF SWITCH . AUTOPILOT ROLL TRIM POSITION INDICATOR. ENGINE SYNCHRONIZER CONTROL SWITCH - SPEED BRAKE CONTROL SWITCH + SPEED BRAKE EMER BLOW DOW! SHITCH ROLL TRIM SELECT SWITCH + ROLL & RUDDER TRIM INTERRUPT SWITCH - ROLL TRIM INDICATOR + ANTI-SKIO CONTROL SWITCH . FLAP CONTROL LEVER . PITCH TRIM TEST SWITCH + PITCH TRIM POSITION INDICATOR + YAW DAMPER INDICATOR YAW DAMPER SWITCH : YAW DAMPER TEST SWITCH +. AUTOPILOT CONTROLLER « DUAL COURSE/HEADING CONTROLLER (OPTIONAL) - ADF(2ND) HF CONTROLLER (OPTIONAL) + LANDING SELECT SWITCH Cockpit Forward View - Center Pedestal Fiqure 1-3 (Sheat 2 of ¢) S/N AOD3SA THROUGH ADS9SA Page 1-9 Jan 6/86MITSUBISHI PILOTS OPERATING MANUAL SECTION 1 MU-300 ‘DIAMOND IA GENERAL, 1131002 EFFECTIVITY: S/N AOGOSA AND SUBSEQUENT Cockpit Forward View - Center Pedestal (Typical) Figure 1-3 (Sheet 3 of 4) Page 1-10 dan 6/86MITSUBISHI PILOTS OPERATING MANUAL SECTION 1 MU-300 DIAMOND 1A GENERAL - NO. 1 FD MODE SELECTOR VLF/OMEGA NAY CONTROLLER (OPTIONAL) - NO, 2 FD MODE SELECTOR (OPTIONAL) ENGINE START SWITCH + ENGINE START SELECT SWITCH ENGINE START DISENGAGE SWITCH + NORM-EMER PITCH TRIM SELECT SWITCH |. EMER PITCH TRIM SWITCH . RUDDER TRIM POSITION INDICATOR - RUDDER TRIM SWITCH « THRUST FRICTION LEVER - ENGINE THRUST LEVERS « ENGINE SYNCHRONIZER CONTROL SWITCH . SPEED BRAKE CONTROL SWITCH ROLL TRIM SELECT SWITCH ROLL & RUDNER TRIM INTERRUPT SWITCH + ROLL TRIM INDICATOR FLAP CONTROL LEVER . ANTI~SKID CONTROL SWITCH . SPEED BRAKE EMER RETRACT SWITCH + LANDING SELECT SWITCH + PITCH TRIM TEST SWITCH ~ PITCH TRIM POSITION INDICATOR © NO. 1 COMM CONTROL UNIT «NO, 2 COMM CONTROL UNIT . NO. 1 NAV CONTROL UNIT + NO. 2 NAV CONTROL UNIT . ADF CONTROL UNIT + ATC TRANSPONDER CONTROL UNIT }. AUTOPILOT ROLL TRIM POSITION INDICATOR + AUTOPILOT ROLL TRIM CPL/OFF SWITCH + AUTOPILOT CONTROLLER + DUAL COURSE/HEADING CONTROLLER (OPTIONAL) YAW DAMPER INDICATOR + YAW DAMPER SWITCH - YAW DAMPER TEST SWITCH Cockpit Forward View - Center Pedestal Figure 1-3 (Sheet 4 of 4) EFFECTIVITY: S/N AOSOSA AND SUBSEQUENT Page 1-11 dan 6/86MITSUBISHI PILOTS OPERATING MANUAL SECTION 1 MU-300 DIAMOND IA GENERAL OVERHEAD SWITCH PANEL Se el 2.9 "Eo a S20 TTT TT Pee jonsa | opsrane ) OOS] O #76 | 673/075) S ANNUNCIATOR PANEL Cockpit Forward View - Overhead Switch Panel and Annunciator Panel Figure 1-4 (Sheet 1 of 2) EFFECTIVITY: S/N AQO3SA THROUGH AQBOSA / Page 1-12 dan 6/86MITSUBISHT PILOTS OPERATING MANUAL SECTION 1 MU-300 DIAMOND TA GENERAL, OVERHEAD SWITCH PANEL kr xrallae xR! [pneas ua)lpness. wc Tx) |ov pnesd] ov pes a ee cee) \ovreral|a o rare ovrase|| evease TH PWe)| A euP| Press to) bores to} ene |) rene rc ofr ef OFF: BE Bees) 35h2| Hey re svac|fr sratc| Ina PALL Pa) i oun FLAS Ser || ASM toew | cen 0239085 EFFECTIVITY: S/N AOSOSA AND SUBSEQUENT Cockpit Forward View - Overhead Switch Pane? and Annunciator Panel (Typical) Figure 1-4 (Sheet 2 of 2) Page 1-13 Jan 6/86MITSUBISHI PILOTS OPERATING MANUAL SECTION 1 ‘MU-300 DIAMOND IA GENERAL FORWARD C/B PANEL ‘AFT C/B PANEL, _ 09 sae OCC0000O0 OCO000CC0O ©C0000000 O0000C000 0099000 soo09c000 009000C0 o00000000 o0g00000 + o0000000R0, VSS SS OQOEQ00G00 00000 900900600 00000 00000000 00000 20G80999G__ 00000 000000900000000 ©000000000000000 RADIO MASTER C/B PANEL MAIN C/B PANEL (S/N AOOSSA, ALISA AND SUBSEQUENT) NOTE : REFER TO FOLLOWING PAGES FOR OETAILS AND EFFECTIVITY. Side Panel - Circuit Breaker Panels (Typical) Figure 1-5 (Sheet 1 of 8) Page 1-14 Jan 6/86ML TSUBISHI PILOTS OPERATING MANUAL SECTION 1 ‘MU-300 DLANOND IA GENERAL, FORWARD C/B PANEL "390: (S/N AOO3SA THROUGH AOOSSA, AND AOO7SA THROUGH AOIOSA) aL = ——| 0000 06660 FORHARD C/B PANEL (S/N AOLISA AND AOJ2SA) 759015 Side Panel - Circuit Breaker Panels (Typical) Figure 1-5 (Sheet 2 of 8) Page 1-15 Jan 6/86MITSUBISHI MU-300 PILOTS OPERATING MANUAL DIAMOND IA — as Se009g0e6! 66060 66666 FORWARD C/B_ PANEL (S/N ADO6SA, AO13SA THROUGH AOB9SA) NoTE: @> S/N AOG6SA AND SUBSEQUENT ens; ——U OQOOOOOGO FORWARD C/8 PANEL, (S/N AOSOSA AND SUBSEQUENT) Side Panel - Circuit Breaker Panels (Typical) Figure 1-5 (Sheet 3 of 8) SECTION 1 GENERAL, 0133013 0233001 Page 1-16 dan 6/86MITSUBISHI PILOTS OPERATING MANUAL SECTION 1 ‘Mu-300 DIAMOND TA GENERAL CO8SEE val nN fit eiaees AFT C/B PANEL (S/N AOD3SA THROUGH ADOSSA, AND AQO7SA THROUGH AOLOSA) AFT C/B PANEL {S/N AOLISA AND AOL2SA) Side Panel - Circuit Breaker Panels (Typical) Figure 1-5 (Sheet 4 of 8) Page 1-17 Jan 6/86MITSUBISHT PILOTS OPERATING MANUAL SECTION 1 MU-300 DIAMOND IA GENERAL, 2139910 AFT C/8 PANEL (S/N AOOGSA, AO13SA THROUGH AB9SA) _ 66668666 666666666 660660606 666665656 07990034 AFT C/B_ PANEL (S/N AOSOSA AND SUBSEQUENT) Side Panel - Circuit Breaker Panels (Typical) Figure 1-5 (Sheet 5 of 8) Page 1-18 dan 6/86MITSUBISHI PILOTS OPERATING MANUAL SECTION 1 MU-300 DIAMOND IA GEHERAL come) aur ene enine 2180s nave comer srev ee Ne SA 0159006 AFT MAIN C/B PANEL (S/N AQO3SA THROUGH AOOSSA, AND AOO7SA THROUGH AOLOSA) eee aS OOC or38005 AFT MAIN C/B PANEL (S/N AOLISA AND AQL2SA) Side Panel - Circuit Breaker Panels (Typical) Figure 1-5 (Sheet 6 of 8) Page 1-19 Jan 6/86MITSUBISHT PILOTS OPERATING MANUAL 300 DIAMOND TA mi pot EMER prone (o'pos AFT MAIN C/B PANEL (S/N AOOESA, AOL3SA THROUGH AOBOSA) ‘ASTBY WRh BAGK-UPh THRUST REVI OOO SOOGS Somwe' SROME UOPCS Gt, pos cor HER GEM SAR one are oft, Soe FG | oe @QQOOOOOO 600000060 oFeREs SEPY wASHERS oBilen ke FER aa Sc AFT MAIN. C/8 PANEL {S/H ADSOSA AND SUBSEQUENT) Side Panel _- Circuit Breaker Panels (Typical) Figure 1-5 (Sheet 7 of 8) SECTION 1 GENERAL 1231001 Page 1-20 dan 6/86MITSUBISHI PILOTS OPERATING MANUAL SECTION 1 DIAMOND TA wu-300 GENERAL MAIN C/B PANEL 9158998 0139016 RADIO MASTER C/B PANEL (S/N AQOBSA, AOLISA AND SUBSEQUENT) Side Panel - Circuit Breaker Panels (Typical) Figure 1-5 (Sheet 8 of 8) Page 1-21 Jan 6/86MITSUBISHI PILOTS OPERATING MANUAL SECTION 1 MU-300 DIAMOND 1A GENERAL, DIMENSIONS, AREAS, AND GENERAL DATA (Refer to Figure 1-6 for details) Exterior Dimensions, Overall: Length 48 ft 5 in 14,75 m Span 43 ft 6 tn 13.25 Height 13 ft 9 in 4.20 m (Dimensions given for normal tire inflation and strut extension) Interior Dimensions, Cabin: Length (Incl. cockpit) 20 ft 11.0 in 6.37 @ Length (Excl. cockpit) 15 ft 7.8 in 477 Width 4 ft 111 in 1,51 m Height 4 ft 91 in 1,45 m Volume: Total 400 cu ft 11,33 cum Cockpit 95 cu ft 2.69 cum Cabin 305 cu ft 8,64 cum Landing Gear Main Wheel Tire TRA Type VII 24 X 7.7 12 or 14 ply rating, tubeless Mose Wheel Tire TRA Type VII 18 X 4.4 10 ply rating, tubeless Wheel Base 19 ft 3 in 5.86 m Tread 9 ft 4 in 2.84 m Capacities Fuel Capacity: U.S. GALLONS LITERS Wing Tanks “265.585 X 2 105.386 x 2 Fuseiage Tank 121.620 460.382 Total 652.810 2471155 Usable 635.800 2406.765 Oi] Capacity: Total 2.33 x2 8.822 X 2 Engine 2 Pratt & Whitney Qircraft of Canada, Ltd. JT15D-40 Turbofan Engine Specifications: Jet Thrust Max. Spec. Fuel Consumption L Lb./Hr/Lb. Thrust Take-Off Rating 2,500 * 0,562 available to 69°F (21°C). Page 1-22 Jan 6/86MITSUBISHT PILOTS OPERATING MANUAL SECTION 1. MU-300 DIAMOND IA GENERAL det Thrust Max. spec. Fuel Consumption Lb. Lb./Hr./Lb. Thrust Maximum Continuous 2,375 0,556 Maximum Climb 2,375 7 0,556 Maximum Cruise 2,375 0.585 Fuel Specifications ASTM-D-1655, Types det A, Jet B, and Jet A-1 IATA kerosene Type Fuel Wide Cut of JP-4 Type Fuel Page 1-23 Jan 6/86MITSUBISHI PILOTS OPERATING MANUAL MU-300 OIAWOND TA FUSELAGE Length 43 ft 1.7 in (13.150 m) Width = 5 ft 5.9 in (1.675 m) Height 6 ft 0.6 in (1.845 m) CABIN DIMENSIONS Length 15 ft 7.8 in (4.770 m) Width 4 ft 11.1 in (1.515 m) Height 4 ft 9.1 in (1.450 m) WING Area 201.4 sq ft (22.43 sq. m) Span (net) 43 ft 0.5 in (13.23 m) MAC 6 ft 1.0 in (1.857 m) Aspect Ratio 7,536 Incidence ~1,0° Wash Out 6. Dihedrat 2. Sweep Angle (25% Chord line) 20. FLAPS Type Fowler, Double Slotted MAIN FLAP Area 22.7 sq ft (2,106 sqm) x 2 Span 14 ft 1.5 in (4.305 m) Deflection 10° and 30° AFT FLAP Area 5.5 sq ft (0.511 sqm) x 2 Span 6 ft 8.5 in (2.048 m) Deflection 5° and 13.5° ROLL TRIM Area 1.6 sq ft (0.148 sqm) x 2 (Aft of Hinge Line) Span 2,0 ft 1.6 in (0.650 m) Deflection up 25° Down 25° SECTION 1 GENERAL Page 1-24 Jan 6/86MITSUBISHI PILOTS OPERATING MANUAL SECTION 1. MU-300 DIAMOND IA GENERAL SPOILERS, Area 3.08 sq ft (0,286 sqm) x 2 (Aft of Hinge Line) Span 12 ft 6.3 in (3,818 m) Deflection (No Load) Speed Brake retracted and Control Wheel fully rotated Spoiler Surface Full LH Full RH Inboard 68° “14° LH Outboard 7a? -14" Inboard -14" 68° RH Outboard 714° 72° Speed Brake extended Inboard 36° 36° LH Gutboard 36° 36° Inboard 36° 36° RH | gutboard =| 36" 36° Speed Brake extended and Control Wheel fully rotated Inboard 73° 14° LH Outboard 78° 14° Inboard 14° 73° RH Outboard 14° 78° Page 1-25 Jan 6/86MITSUBISHI MU-300 HORIZONTAL STABILIZER Area Span (net) mac Aspect Ratio Incidence Wash Out Dihedral Sweep Angle (25% Chord line) ELEVATORS Area Span Deflection VERTICAL STABILIZER Area Span MAC Sweep Rack (25% chord line) RUDDER Area (Aft of Hinge Line) Span (74.0% Chord Line) Deflection RUDDER TRIM TAR Area (Aft of Hinge Line) Span (Aft of Hinge Line) Def lect ion YAH DAMPER SURFACE Area (74% Chord Hinge tine) Span (74% Chord Hinge Line) flef lect ion DORSAL FIN Area VENTRAL FIN Area PILOTS OPERATING MANUAL SECTION 1 DIAMOND 1A GENERAL 56.5 sq ft (5.250 sq m) 16 ft § in (5.000 m) 3 ft 7.3 in (1,101 m) 4,762 0° through ~13° a 0! 26" 8.37 sa ft (0,788 sqm) x 2 16 Ft 4.9 in (5.000 m) UP 25° DOMN 12° 63. 7 8 (25 6 sq ft (5.911 sqm) #t 9.9 in (2.384 m) ft 4.7 in (2,557 m) chord line) 46.4° 10.7 sq ft (0.991 sqm) 4 ft 10.3 in (1.480 m) RH & LH 30° 1.6 sq ft (0.145 sq m) 2 Ft 5.0 in (0.736 m) RH & LH 24° 1,41 sq ft (0.131 sq m) 9.8 in (0.250 m) LH 27.6° & RH 26.6" 4.6 sa ft (0.429 sqm) 5.1 sa ft (0,477 sqm) Page 1-26 dan 6/86MUTSUBISHI PILOTS OPERATLNG MANUAL SECTLON 2 MU-300 DIAMOND TA GENERAL sa ft. 8 ine [26 mi ENTRAL FN ODER TRIM TAB (6.86 9) 19 e 3 a, o 98 fh. $f (1475 at + ofeensten given for Pormal tire. Inflation MACELLE Gna strut extensfon. ot. 8 ta (2.8 a) 63 fe. 5 tne iS a Gaus General Dimensions and Areas Figure 1-6 Page 1-27 dan 6/86MITSUBISHI PILOTS OPERATING MANUAL SECTION 2 Mu-200 DIAMOND IA OPERATING LIMITATIONS SECTION 2 OPERATING LINITATIONS CONTENTS Page GENERAL ..,.22-0006 REQUIRED PLACARDS/MARKINGS INSTRUMENTS MARKINGS Page i dan 6/86MITSUBISHI PILOTS OPERATING MANUAL SECTION 2 -300 DIAMOND TA OPERATING LIMITATIONS GENERAL For operating limitations, refer to the approved Airplane Flight Manual. REQUIRED PLACARDS/MARKINGS Placards/markings are required to remind the flight crew and occupants of operating limitations and safety instructions. Figures 1 through 3 illustrate typical exterior placards/markings which are of a limiting nature, Figure 4 illustrates those typical flight compartment placards/markings pertinent to operations and safety of flight. Refer to the approved Airplane Flight Manua? for those limiting placards/markings located in the passenger compartment, NOTE The placards/markings illustrated may vary slightly depending on arrangement and/or airplane configuration, Page 2-1 Jan 6/86MITSUBISHI PILOTS OPERATING MANUAL SECTION 2 MU-300 DIAMOND IA OPERATING LIMITATIONS ) AOR JET 8) \ iirens fenaun, Sc mB ROOITIVE we. rin FOR APPROVED rue 4 WONINCTEND FUELING PS Ou ont, 5 aL erm Typical Exterior Markings - Top Surface Figure 2-1 Page 2-2 Jan 6/86MITSUBISHI PILOTS OPERATING MANUAL SECTION 2 ‘MU-300 DIAMOND TA OPERATING LIMITATIONS + eatr0ossa PRECHARGE PRESSURE CAUTION 900. +50Psi CAUTION anit DISCONNECT DISCONNECT RATING. PRESSURE TORQUE TORQUE ARM 1500 PSI BEFORE BEFORE TOWING : ded RECONNECT RECONNECT AFTER AFTER TOWING TOWING CAP 8.8 LITERS 2.33 US GAL. CAUTION DO NOT MIX BRANDS OF OIL : all ; — 7 MITSUBISHI he Typical Exterior Markings - Left Side Figure 2-2 Page 2-3 dan 6/86MITSUBISHI PILOTS OPERATING MANUAL SECTION 2 MU~300 DIAMOND IA OPERATING LIMITATIONS oxttoorsa F U E [fe CAP 8.8 LITERS 2.33 US GAL. CAUTION ET ACAY OR JET B ONLY DO NOT MIX BRANDS OF GIL 4436 LTERS, 1177 US BAL PFASS MB an0ITVE REDO 0 IL 1 2 CAUTION DISCONNECT TORQUE ARM BEFORE TOWING RECONNECT AFTER TOWING Typical Exterior Markings - Right Side Figure 2-3 . Page 2-4 Jan 6/86MITSUBISHI PILOTS OPERATING MANUAL SECTION 2 MU-300 OIAMOND 1A OPERATING LIMITATIONS oe Ak *(1) S/N AQO3SA THROUGH AOB9SA (2) S/N AOQOSA AND SUBSEQUENT Typical Flight Compartment Markings Figure 2-4 (Sheet 1 of 3) Page 2-5 Jan 6/86PILOTS OPERATING MANUAL MI TSUBI SHI DLAMOND LA 0-300 SECTION 2 OPERATING LIMITATIONS. EA WITH a0TH OEFOGGEAS OFF 1 SPEEO LIMITATION (ip, MACH OR KT:1AS) (ABOVE 26,000 FT) (07.000-26,000 FT) (BELOW 14.g90e15 Ve (AT 41,000 FT) (@ELOW 20,000 #1) uo uo va Vie (FLAP 10) (FLAP 30) {FLAP 102) 4 5 Fj EMER Fe [TAREOFFETAND | 7 4 UNPRESSURIZED FIRE EXTINGUISHER 6 7 7 VW EMER DOOR CLOSE 9 "AUK GEAR CONTROL FUSH DOWN AND PULL TEE HANDLE TO UNLOCK: V EMER L/G DOWN Typical Flight Compartment Markings Figure 2-4 (Sheet 2 of 3) Page 2-6 Jan 6/86ME TSUBI SHI MU~300 7B IDENTIFICATION BUS’ RING. LH LOAO— BLUE RHLOAD— YELLOW EMER — RED STBY PWR— GREEN NON ESSN- WHT-STRIPE| AC PRIM— PNK «STRIPE AC SHED— GAN. STRIPE 10 agi PILOTS OPERATING HARUAL SECTION 2 DIAMOND TA OPERATING LIMITATIONS Y PARKING BRAKE oy 12 14 DOwoT TURN ON INCLOUDS 15 Typical Flight Compartment Markings Figure 2-4 (Sheet 3 of 3) Page 2-7 dan 6/86ALTSUBI SHI PILOTS OPERATING MANUAL SECTION 2 ‘MU-300 DIAMOND 1A OPERATING LIMITATIONS INSTRUMENT MARKINGS Various flight compartment instruments require periodic monitoring for the safe operation of the airplane. These instruments contain specific Color markings for easier identification of a system's or the airptane's conditional operating limitation. NON-OBSERVANCE OF THESE INSTRUMENTS COULD RESULT IN DAMAGE TO THE SYSTEM AND/OR AIRPLANE. Fue OTL pressure TENPERATORE mt Ss TERPERATURE Tune anspeco FAN RH caIN ALTITUDE DIFFERENTIAL PRESSURE Oo Aig soTTLe PRESSIRE oicen sarreny PRESSURE TeAPERATURE ane orate oF PRESSURE vourvere aTtack PITCH ‘TRIM : ovsaio2 {S/N AOO3SA THROUGH ADB9SA) Typical Instrument Markings Figure 2-3 (Sheet 1 of 5) Page 2-8 Jan 6/86MITSUBISHY PILOTS OPERATING MANUAL SECTION 2 MU-300 DIAMOND TA OPERATING LIMITATIONS INSTRUNENT MARKINGS Various flight compartment instruments require periodic monitoring for the safe operation of the airplane. These instruments contain specific color markings for easier identification of the airplane's or system’s conditional operat ing limitation, NON-OBSERVANCE OF THESE INSTRUMENTS COULD RESULT IN DAMAGE TO THE SYSTEM AND/OR AIRPLANE. O1L PRESSURE 1 TEMPERATURE. CABIN ALTITUDE DIFFERENTIAL \ \ ‘AIR BOTTLE \ PRESSIRE oD Do \ TEMPERATURE aaa / PRESSURE ATTACK, HYDRAULIC PRESSURE, (S/H AQSOSA AND SUBSEQUENT) 134103, Typical Instrument Markings Figure 2-5 (Sheet 2 of 3) Page 2-9 Jan 6/86MITSUBISHI PILOTS OPERATING MANUAL SECTION 2 Mu-300 DIAMOND IA OPERATING LIMITATIONS ALRSPEED FUEL TEMPERATURE Above 26,000 ft. 0.785 Mach Between 17,000 & 320 KIAS MI -40°C and 43°C (RED) 26,000 Between 14,000 & Linear 17,000 ft Variation Below 14,000 264 KIAS BATTERY TEMPERATURE B 150°F to 190°F (RED) @ 120°F to 10°F (YELLOW) 1 100°F to 120°F (GREEN) ANGLE OF ATTACK WM 0.85 to 1.0 (RED) @ 1850 PSI (REO) 0.6 too. Bou ‘ : ieee OO to 400 PSI (YELLOW) +6 (GI @ 1350 to 1550 PSI (GREEN) Typical Instrument Markings Figure 2-5 (Sheet 3 of 5) Page 2-10 Jan 6/86MITSUBISHI ‘MU-300 DIAMOND IA ax 104% (RED) Cl 32 to 104% (GREEN) OIL PRESSURE & TEMPERATURE 720°C (RED) sanec to 720°C (YELLOW) B lone to 680°C (GREEN) PILOTS OPERATING MANUAL SECTION 2 OPERATING LIMITATIONS TURBINE RPH AN 97% (RED) 1 49 to 97% (GREEN) 135 PSI (RED) 36 to 70 PSI (NARROW) a GREEN 70 to 85 PSI (HIDE) Jas pst h iso pst (re0) Pizitc fl 13e"c (RED) @-40"C to 10°C (YELLOK) Dore to 121°C (GREEN) CABIN ALTITUDE/DIFFERENTIAL PRESSURE @ 9.1 PSI (RED) C1 0 to 9.1 PSI (GREEN) Typical Instrument Yarkings Figure 2-5 (Sheet 4 of 5) Page 2-11 Jan 6/86MITSUBISHT PILOTS OPERATING MANUAL SECTION 2 MU-300 DIAMOND IA OPERATING LIMITATIONS AIR BOTTLE PRESSURE 1500 to 2100 PSI (WIDE RED) ANMETER Wb to 1200 PS (NARROW RED) 1200 to 1300 PSI (YELLOW) AMPS © 1350 to 1500 PSI (GREEN) xX 100 i) OXYGEN PRESSURE we ‘001800 USE MOO 00. oxroen. Suerey” Prcasune M4008 (RED) @ 280 to 4008 (YELLOW) C0 to 400A (GREEN) W200 PSI (RED) © to 200 PSI (YELLOW) VOLTMETER C1600 to 1850 PSI (GREEN) PITCH TRIM .3° and -11° (RED) eo ° (GREEN) M32 to 35V (REO) Typical Instrument Mark ings Figure 2-5 (Sheet 5 of 3) Page 2-12 dan 6/86 WS‘this publication is printed and/or distributed by Beech Aircratt Corporation under license from Mitsubishi Heavy Industries, Ltd. Address all comments or inqui- ries regarding this publication to: Beech Aircraft Corporation 9709 East Central Wichita, Kansas 67201 Attention: Manager, Technical PublicationsMITSUBISHI PILOTS OPERATING MANUAL SECTION 3 M-300 DIAMOND IA ‘SYSTEM DESCRIPTIONS SECTION 3. SYSTEM DESCRIPTIONS CONTENTS Page INTRODUCTION 3-1 ENGINE... 34 OIL SYSTEM... 33 ENGINE ANTI-ICE . 33 FUEL CONTROL SYSTEM .... 35 ENGINE START ..ccseeeees 37 ENGINE SHUTDOWN 3-9 ENGINE CONTROL .. aaa ee 39 ENGINE IGNITION SYSTEM . 3-12 ENGINE INDICATORS 314 THRUST REVERSER .. 3-15 FIRE PROTECTION 3-18 ENGINE FIRE PROTECTION ... 3-18 SMOKE DETECTION SYSTEM . 3-19 FUEL SYSTEM 3-21 FUEL TANKS woe 3-21 FUEL FEED 3-21 FUEL CROSSFEED 3-24 FUEL TRANSFER . 3.25 OEFUEL AND DRAIN , 3-26 REFUELING ... 3-26 TANK VENT 3-26 Page i Jan 6/86MITSUBISHI PILOTS OPERATING MANUAL MJ-300 GIAMOND IA SECTION 3 SYSTEMS DESCRIPTIONS CONTENTS FUEL QUANTITY INDICATING SYSTEM . HYDRAULIC SYSTEM... PUMPS ...., ee: HYDRAULIC PACKAGE LANDING GEAR SYSTEM , CONTROL UNIT .. LANDING GEAR RETRACTION LANDING GEAR EXTENSION .., EMERGENCY EXTENSION .... POSITION AND WARNING SYSTEM STEERING .... WHEEL BRAKE SYSTEM . POWER BRAKE SYSTEM ... ANTI-SKID SYSTEM PARKING BRAKE .. EMERGENCY BRAKING .... FLIGHT CONTROL SYSTEM . AUTOMATIC FLIGHT CONTROL SYSTEM .... PRIMARY CONTROL SYSTEM... SECONDARY CONTROL SYSTEM .. SPEED BRAKE CONTROL SYSTEM FLAP CONTROL SYSTEM YAW DAMPER SYSTEM SECTION 3 SYSTEM DESCRIPTIONS Page 3-27 3-28 3-28 3-28 3-31 3-31 3-31 3433 3-33 3-34 3-36 3-35 3435 3435 3-38 3-38 3-39 3-39 3.39 3-42 3-44 3-46 3-48 Page ii Jan 6/86MUTSUBISHT PILOTS OPERATING MANUAL SECTION 3 ¥U-300 DIAMOND IA SYSTEM DESCRIPTIONS SECTION 3. SYSTEMS DESCRIPTIONS CONTENTS Page ENVIRONMENTAL. 3-50 AIR CONDITIONING 3-50 PRESSURIZATION ...eseeeeeeeeeeee 3-58 ICE AND RAIN PROTECTION 3-63 WING LEADING EDGE ANTI-ICE SYSTEM 3-63 PITOT-STATIC AND ANGLE OF ATTACK ANTI-ICE SYSTEM ... 3-65 HEATED WINDSHTELD ... 3-66 WINDSHIELD DEFOG SYSTEM .. aa 3-66 WINDSHIELD WIPER SYSTEM .. aides 3-67 HORIZONTAL STARILIZER ANTI-ICE/DEICE SYSTEM , sees 367 OXYGEN 3-69 CREW OXYGEN SYSTEM 3-69 PASSENGER OXYGEN SYSTEM 3-72 ELECTRICAL SYSTEMS . 3-73 DC ELECTRICAL SYSTEM 3-73 AC ELECTRICAL SYSTEM .. Baan 3-83 EXTERIOR LIGHTING SYSTEM 3-84 INTERIOR LIGHTING SYSTEM 3-87 EMERGENCY LIGHTING SYSTEM .... 3-89 INSTRUMENTS. 3-90 PITOT-STATIC SYSTEM 3-90 HORIZON GYRO INDICATOR 3-90 TURN AND BANK INDICATOR 3-90 Page iii dan 6/86MITSUBISHI PILOTS OPERATING MANUAL SECTION 3 Mu-300 DIAMOND TA SYSTEM DESCRIPTIONS SECTION 3 SYSTEMS DESCRIPTIONS CONTENTS BAROMETRIC PRESSURE ALTIMETER ... QVERSPEED WARNING .. RAT INDICATOR BATTERY TEMPERATURE INDICATOR . FLIGHT HOUR METER se yeeseeee . CLOCK .., AIRSPEED MACH INDICATOR MASTER WARNING/CAUTION AND MASTER TEST SYSTEM . MASTER WARNING/CAUTION SYSTEM... ..cceeeceeceeeeveeeeerseeeee 3-94 MASTER TEST SYSTEM . AVIONICS SYSTEM (S/N AOOSSA THROUGH AOB9SA) ... COMMUNICATION ...... NAVIGATION . . AVIONICS SYSTEM (S/H AOSOSA AND SUBSEQUENT) ... COMMUNICATION .... NAVIGATION GROUND HANDLING «2.4.44 TOWING TAXTING PARKING MOORING Page iv van 6/86MITSUBISHE PILOTS OPERATING MANUAL ‘MU-300 SECTION 3 SERVICING .. FUEL .. ENGINE OIL . GEAR AND BRAKE PNEUMATIC .. FIRE EXTINGUISHER .....2-0+ OXYGEN HYDRAULIC .. TIRES v.45 WINDOW CLEANING .. CONSUMABLE MATERIAL DIAMOND IA SYSTEMS DESCRIPTIONS CONTENTS. SECTION 3 SYSTEM DESCRIPTIONS Page 3-144 3-148 3-147 3-148 3-148 3-148 3-148 3-149 3-150 3-150 Page v dan 6/86MITSUBISHI PILOTS OPERATING MANUAL SECTION 3 ‘MU-300 OFAMOND TA SYSTEM DESCRIPTIONS INTRODUCTION Section 3 of the Pilot's Operating Manual provides a description of the MU-300 and operational procedures for the airplane and its systems. ENGINE The MU-300 is powered by two aft pod mounted JT150-40 turbofan engines, manufactured by Pratt & Whitney Aircraft of Canada, Limited. The engine is a Vight-weight twin-spool, front turbofan jet propulsion engine having a full length annular bypass duct. A cross section of ‘the engine is shown in Figure 3-1. The low compressor consists of a low compressor fan followed by a primary gas path booster stage. A concentric shaft system supports the high and low rotors, The inner shaft supports the low compressor fan and booster stage and is driven by a two-stage turbine supported at the rear, The speed of this assembly fs designated as Nj rpm. The outer shaft supports the high pressure centrifugal compressor impeller. and is driven by a single-stage high pressure turbine. This speed is designated as No rpm, The JT180-40 will produce 2,500 pounds of static thrust on a standard day at sea level and a max-continuous thrust of 2,375 pounds. All intake air passes through the low compressor fan. Inmediately aft of the fan, the airflow is divided by concentric ducts. Most of the total airflow is bypassed around the engine through the outer annular bypass duct and is exhausted at the rear, Air entering the inner duct passes through a booster stage and is compressed by the impeller. The high pressure air then passes through a diffuser assem- bly and moves back to the combustion section. The combustion chanber ts a reverse-flow design to save space and reduce engine size. Most of the air entering the chamber is mixed with fuel and ignited while the remainder streams down the chamber Tiner outward for cooling. Fuel is introduced by twelve dual orifice nozzles supplied by a dual manifold, The mixture is ignited initially by spark igniters which extend into the combustion chamber at the 5 and 7 o'clock positions. After start, combustion becomes self-sus- taining, The hot gases expand guide vanes to the high pressure turbine. As the exoanding gases stove rearward, they pass through another set of guide vanes and enter the two stage low pressure turbine. A greater portion of the remaining eneray is extracted there and is transmitted by the inner shaft to the forward mounted fan. The hot gases are then exhausted into the atmos- phere. An accessory gearbox is mounted on the lower side of the engine's intermediate case and is driven by a tower shaft from the bevel gear on the outer shaft. Its function is to turn the engine during starting, and to drive the acces- sories for the engine and the airplane systems, The following components are driven by the accessory gearbox: DC starter-generator Fuel pump N2_ tach-generator Fuel control 041 pump Hydraulic pump Page 3-1 dan 6/86MITSUBISHI Mu-300 TOTAL AIR INTO ENGINE 13 wv INTAKE DUCT - LOW COMPRESSOR FAN BOOSTER STAGE + NI_TACH-GENERATOR - IMPELLER - DIFFUSER + COMBUSTION CHAMBER - HIGH COMPRESSOR TURBINE + ANNULAR BYPASS DUCT - FUEL NOZZLE LOW COMPRESSOR TURBINE 12. EXHAUST DUCT 13. STARTER-GENERATOR PRIMARY AIR FLOW SECONDARY AIR FLOW (BYPASS AIR) —_ —— PILOTS OPERATING MANUAL DIAMOND IA \ / i718 19 2 a 22 SECTION 3 SYSTEM DESCRIPTIONS 12 O171101 Np TACH-GENERATOR OIL PUMP ACCESSORY GEARBOX FUEL PUMP & HYDRAULIC PUMP FUEL CONTROL UNIT FUEL FLOW TRANSMITTER Tp SENSOR OIL-FUEL HEAT EXCHANGER EXCITER IGNITER FUEL DIVIDER VALVE EMERGENCY FUEL CUTOFF VALVE Cross Section Typical Installation of Engine System Figure 3-1 Page 3-2 Jan 6/86 NeMITSUBISHI PILOTS OPERATING MANUAL SECTION 3 Mu-300 DIAMOND TA SYSTEM DESCRIPTIONS OIL SYSTEM The system provides cooled, pressurized oi1 for lubrication and cooling of engine bearings and accessory drive gears nd bearings, An integral oi] tank on each engine has a capacity of 2.33 U.S, gallons (8.8 liters), of which 1.50 U.S. gallons (5.7 liters) are usable. O11 is drawn from the tank by a pressure element of the three element pump mounted on the accessory gearbox, It passes through a check valve, which prevents gravity flow when the engine is not running, and past 2 pressure relief valve en route to the oil cooler. If system pressure becomes excessive, the relief valve reduces its pressure by unseating and allowing oi1 to return to the pump inlet by means of a bypass line. 041 from the cooler, which is a fully automatic fuel-oi1 heat exchanger, passes through a filter and is routed to the ngine bearings and acces sory gearbox. If the filter becomes clogged a bypass valve opens allowing lubrication to continue and the L for’R) OIL FILT BYPASS (S/N AQO3SA through AO89SA) or L (or R) @ FLTR BYPASS (S/N AO9OSA and subse- quent) annunciator wit? illyminate. Circulated oi] is returned to the tank by two scavenge punp elenents in the 011 punp assembly, The engine oil system is shown in Figure 3-2, Oi] pressure is sensed by a transmitter and is displayed on two OC powered indicators with dual pointers (pressure and temperature) on the center instrument panel. The scale ranges on the dual indicators are 0 to 150 psi for oi] pressure and -40°C to 150°C far oi] temperature. The minimum oi1 pressure at idle rpm is 35 psi. The normal operating range is 70 to 85 psi when the power is over 60% No. The L or R OLL PRESS LO annunciator will illuminate when the system pressure decreases below 36 psi. Oi] temperature is sensed by a resistance bulb and transmitted to the dual indicators. Minimum oi] temperature for engine start is -40°C and normal operating range is +10°C to +121°C. ENGINE ANTI-ICE Each engine has two anti-ice systems installed to prevent the buildup of ice in the engine intake. One system circulates high compressor bleed air in a jacket around the nacelle air inlet duct leading edge and the other system extracts high compressor bleed air and routes it into the engine low compressor inner stators. Also, high compressor air is tapped off and supplies a small amount of air, fdr anti-ice protection, for the Ty temperature probe and the inlet cone. The nacelle inlet antizice con- trol valve is located on the lower part of the engine inlet case and the jnner stator enti-ice contro) vaive is located at the 10 o'clock position on the engine intermediate case, Page 3-3 Jan 6/86MITSUBISHY MU-300 (S/N AOD3SA THROUGH AOB9SA) i eck yALVE TreLcat PILOTS OPERATING MANUAL ‘DIAMOND TA SECTION 3 SYSTEM DESCRIPTIONS. oa (S/N AOSOSA AND SUBSEQUENT) No.2 seaaing HO GPeSEBRINS, 40.4 WeAninG arssune mele eae, ede IL FILTBWPASS ‘2 rut Tank EE (Inne Sars W037? Beinn, aut f a ACCESSORY sat riut srpAss Wale oul Tew TeawgarreR tu pass. TeaNSHIT TER Oi PRESS LOW SH iss 1 Trier wae (ies is A AUUneCATOR a TURN TO TAM “BHATT TaNOER THE ACCESSORY GEARBOX) Sivenie Wo.4 GERIG EEE PRESSURE OIL Line PASS OIL LUNE CEE scavemee on SS eeLEcratCAL crecutT Engine 011 Lubrication System Figure 3-2 on7si01 Page 3-4 Jan 6/86MITSUBISHI PILOTS OPERATING MANUAL SECTION 3 MU-300 DIAMOND IA SYSTEM DESCRIPTIONS Engine Anti-Ice Switches The engine anti-ice systems are controlled by the respective engine anti-ice switches located on the overhead switch panel. When the ENGINE ANTI-ICE switch is ON, the pressure regulator shutoff valve opens to regulate the bleed air pressure for the engine anti-ice system at 16 psi. At the same time, the engine anti-ice operating Vight will illuminate, Engine Anti-Ice Warning Light When the engine inlet bieed air temperature is below 120°F (49°C), the warning Jight L (or R) ENG ICE TEMP LO annunciator will i1lumi- nate, FUEL CONTROL SYSTEM Fuel flow to the engine is mechanically controlled by thrust lever move- ment and is regulated by the engine fuel control system, This system consists of an engine driven fuel pump unit, a motive flow valve, a fuel control unit (FCU), an oil cooler (oil/fuel heat exchanger), a flow divider valve (FDV), a shutoff valve, and a dual fuel manifold with 12 dual orifice fuel nozzles. The engine driven fuel pump is mounted on and driven by the engine accessory gearbox and ensures a positive fuel pres- sure to the FCU. The FCU, mounted on the rear face of the pump, deter- mines the proper fuel schedule for engine operation. The FOV receives fuel from the FCU and provides proper fuel distribution to the combustion chamber by dividing the flow into the primary and secondary fuel mani- folds. It also acts as a fuel shutoff valve bypassing fuel back to the pump during windmilling operation. When the throttle is closed, fuel Flow is terminated at the flow divider and the fuel is returned from its manifold through the dump valve to the aft fuselage tank through the drain box and the surge tank by the air pressure (refer to FUEL SYSTEM). The system is shown schematically in Figure 3-3. Fuel Flow Indicators The engine fuel flow indicating systems for both engines consists of transmitters, fuel flow indicators, a fuel flow conditioner, and a Fuel consumed totalizing indicator.” The fuel flow transmitter is an the outlet side of the FCU and measures the frequency signals pro- portional to the fuel flow rate that passes through it. The flow rate is converted into an electrical current by the signal condi- tioner and is sent to the fue) flow indicator. The fuel flow ind cators on the instrument panel display engine fuel consumption in pounds per hour, The scale range of the indicator is 0 to 1,700 LB/HR. The fuel consumed totalizer receives current from the signal conditioner and provides a digital display of the fuel consumed. Page 3-5 Jan 6/86MITSUBISHT MU-300 SECTION 3 SYSTEM DESCRIPTIONS. PILOTS OPERATING MANUAL DIAMOND JA 04730084 Engine Fuel Control and Start System Figure 3-3 Page 3-6 dan 6/86 eeMITSUBISHI PILOTS OPERATING MANUAL SECTION 3 Mu-300 DIAMOND TA SYSTEM DESCRIPTIONS ENGINE START Engine starts may be made by use of the airplane battery, external power, generator assist, or by air starting, The starter-generator operates as a starter until engine speed (Nz) reaches approximately 35% to 40% rpm. At this time, the starter ceases to turn the engine and the solenoid held ENG START button is automatically released, AS engine rpm increases, the starter-generator begins to function as a generator. The generator output is automatically connected to the DC bus system when the start selector is placed to the OFF position, The system is shown schematical- ly in Figure 3-3, Battery Start In a battery start the BATTERY switch must be ON with the battery supplying a minimum of 22 volts. Select the engine (left or right) to be started with the ENG START SELECT switch. Momentarily press the respective ENG START button then release, Verify illumination of the ENG START button and the ROOST PUMP Tight and that fuel flow js indicated, At 8% to 10% No rpm move the thrust lever to IDLE and check that the IGNITION light iJluminates. Ensure Ny, N2, ITT, and oi) pressure do not exceed limits during the start. THE STARTER-GENERATOR IS CAPABLE OF THREE ATTEMPTED ENGINE STARTS WITH ONE MINUTE REST PERIODS BETWEEN ATTEMPTS. AFTER THIRD ATTEMPT, ONE HOUR REST PERIOD IS REQUIRED. ‘External Power Start An external power start may be accomplished by connecting an externa] power source capable of supplying 1,000 to 1,500 amps and 28Y DC power, If both engines are to be started with external power, the GEN RESET switches must be OFF during the second engine LIMIT EXTERNAL PONER UNIT OUTPUT TO 28 VOLTS AND 1,000 TO 1,500 AMPS. Page 3-7 Jan 6/86MITSUBISHI PILOTS OPERATING MANUAL SECTION 3 ‘MU-300 DIAMOND IA SYSTEM DESCRIPTIONS Generator Assisted Start Because the external power unit is automatically disconnected when a generator comes on line, the second engine start is normally powered by the battery with an assist from the operating generator, even though external power is connected. The only difference between 2 generator assisted start and a battery only start is that the oper- ating engine must have the GEN MASTER switch in the NORM position, GEN RESET switch in the NORM position and the engine No set at 50% to 52%. DURING GENERATOR ASSISTED STARTS, 00 NOT START THE SECOND ENGINE UNTIL THE OPERATING GENERATOR'S LOAO IS RELOW 150 AMPS. CAUTION AN AIR START SHOULD NOT BE ATTEMPTED IF THE ENGINE SHUY- DOKN WAS QUE TO OBVIOUS MECHANICAL DIFFICULTIES. Air Start. Air starts can be accomplished by two methods: (2) Windmilling air start (2) Starter assisted air start Refer to the approved Airplane Flight Manual for air start procedures. Page 3-8 Jan 6/86 wsMITSUBISHI PILOTS OPERATING MANUAL SECTION 3 J-300 DIAMOND TA SYSTEM DESCRIPTIONS ENGINE SHUTDOWN Prior to engine shutdown, retard the thrust lever to IDLE and observe the TTT indicator, Allow the engine to idle for 2 minimum of one minute at the lowest stabilized observed temperature, then place the thrust lever to the CUT OFF position, If the engine is being shutdown due to an emer- gency, the ITT need not be stabilized. ENGINE CONTROL During normal operation, the engine power may be adjusted to any setting between idle and Takeoff Rated Thrust (TRT). TRT can be used for a maximum of five minutes. The ITT should not exceed 720°C and Ny should not exceed 104%, Ng should not exceed 97% and oi] temperature and pres- sure should be in the normal operating range of 50 to 250°F and 70 to 85 psi, respectively. Maximum continuous thrust has no time limit, but the IIT is limited to 680°C, of] temperature should be within 32 to 250°F and all other limits are the same as TRT. Idle speed is 49% to 51% Nz with the cabin pressure source selectar in 80TH position, generator load below 50 amps and the ITT should not exceed 580°C. During any acceleration the ITT should not exceed 720°C. Thrust Lever Engine thrust is controlled by the thrust levers, located on the center pedestal, Angular displacement of the thrust lever is trans- formed into stroke displacement of the cable connected to the engine fuel control. The thrust lever has two detent positions CUT OFF and IDLE. To move the thrust lever from CUT OFF to IDLE or from IDLE back into CUT OFF, it is necessary to pull up and move the levers over the detent on airplanes without thrust reversers or it is necessary to null up the detent release levers and move the thrust levers over the detents on airplanes with the thrust reverser. Friction Lever The friction lever is mounted on the left side adjacent to the thrust levers. To prevent creeping, the thrust levers may be fixed in any position after setting power by moving the friction lever forward. Engine Synchronizer The engine synchronizer function automatically synchronizes either fan or turbine speed of the slave engine to that of the master engine. The speed of the slave (RH) engine will follow changes in the speed of the master (LH) engine over a predetermined limited rpm range. This limited range in synchronizing prevents the slave engine from losing more than a fixed amount of rpm in case the Page 3-9 dan 6/86MITSUBISHI W300 PILOTS OPERATING MANUAL SECTION 3 DIAMOND TA SYSTEM DESCRIPTIONS master engine is shutdown while the ENG SYNC switch, located on the center pedestal, is in the FAN or TURBINE positian. Normal rpm setting and procedures are unchanged, A schematic diagram of the engine contre) and synchronization system is shown in Figure 3-4, Flight Procedures THE ENGINE SYNCHRONIZER MUST BE OFF DURING TAKEOFF, LANDING AND ONE ENGINE QUT OPERATION. (1) (2) Q) Turn the ENG SYNC switch to the OFF position during take- off, landing and single engine operation. When the switch is turned to OFF, the actuator runs to the center of its range before stopping. This ensures correct rigging between the throttle lever quadrant and fuel con- trol unit lever at the maximum and minimum positions. After making the first power reduction after takeoff, Manually synchronize the engines and select either FAN or TURBINE, as desired, with the ENG SYNC switch. The slave engine wit? match the speed of the master engine. When making subsequent rpm adjustments, move both thrust levers together. This will keep both engine fuel control speed settings close enough to remain within the limited adjustment range of the slave engine. If the synchronizer is unable to adjust the slave engine rpm to match the master engine, the actuator has reached the end of its travel. Turn the ENG SYNC switch OFF {which will allow the actuator to return to the centered position), synchronize manually and turn the switch to either FAN or TURBINE. When the synchronizer is turned ON, the indicator light on the shroud annunciator pane? illuminates. Page 3-10 Jan 6/86MITSUBISHI PILOTS OPERATING MANUAL SECTION 3 MU-300 DIAMOND IA SYSTEM DESCRIPTIONS ENGINE INDICATORS 22a) _ FUEL praca It ‘TURETNE TACN=GENERATOR ake a Pitan tat sceerar da CoNOTT HOMER {fp i re GLK ul | | ror cea | a ol ea | ae vos Fut HEA xcaanceR FARTING SYSTEM | om ‘iis Ne Foe ACTUATOR, ‘TRANSMITTER ‘TURBINE TAH. GENERATOR Fa TAC-eveRATOR J a0x L HEAT, ExcHancen See ia Skate Syston sie Fow ‘Taam TTER : o77K188 Engine Control and Synchronization System Figure 3-4 Page 3-11 Jan 6/86MITSUBISHI PILOTS OPERATING MANUAL SECTION 3 MJ-300 DIAMOND TA SYSTEM DESCRIPTIONS ENGINE IGNITION SYSTEM The engine ignition system provides the engine with a quick light up capability over a wide range of temperatures. The engine ignition system is controlled by an IGNITION switch, thrust lever cutoff switch, ENGINE ANTI-ICE switch, engine start control relay and stail warning control relay, An ignition system is provided for each engine. Refer to Figure 3-5 For a block diagran of the engine ignition system, Ignition Operating Modes Engine ignition is divided into three operating modes. Engine Start Mode The ignition is sequentially operated during engine starting. Depressing the respective ENG START button energizes the engine start control relay, Moving the thrust lever to IDLE during start directs voltage from the battery charge bus through the engine start control relay, thrust lever switch, and start ignition fuse to the exciter, The LH or RH ignition operat ing Tight illuminates, indicating that the exciter is receiving low voltage power unti] the engine start disengage switch is depressed or the start selector is turned off at the completion of the start. Manual Mode When the IGNITION switch is placed to the ON position, ignition Jow voltage is supplied through the engine thrust lever switch and the ignition circuit breaker to the exciter. Power source is the emergency bus in the LH system or RH load bus in the RH system, The respective IGNITION operating light (LH or RH) iMuminates when the ignition is on, Standby Mode The IGNITION switch should normally remain in the STBY posi- tion, Ignition low voltage power is supplied to the exciter when the ENG ANTI-ICE switch is actuated or when the stall warning ignition relay is energized. Page 3-12 dan 6/86 wy