AIRPLANEOPERATIONS MANUAL GENERAL REVISION 17 1-00-00 Page 1 Code 01 SECTION 1-00 GENERAL INFORMATION AND DEFINITION OF TERMS TABLE OF CONTENTS Page Block General Information ................................................................... 1-00-00 Definition of Terms..................................................................... 1-00-10 Units Conversion........................................................................ 1-00-20 EICAS Versions ......................................................................... 1-00-30 Service Bulletin Table ................................................................ 1-00-35 GENERAL AIRPLANE OPERATIONS MANUAL 1-00-00 Page 2 Code 01 REVISION 32 GENERAL INFORMATION This Airplane Operations Manual provides useful information to complement the Airplane Flight Manual, Weight and Balance Manual and the Master Minimum Equipment List. It must be used in conjunction with those publications to safe and efficiently operate all the EMB-135 and EMB-145 models. Any difference found between the data in the Airplane Operations Manual and the approved Manuals is due to airplane modifications and scheduling of amendments to publications. In the event of such a difference, the data in the approved manuals must prevail. The Airplane Operations Manual philosophy and structure are described on the next pages. In the EMBRAER Operational Manuals, the Brazilian Civil Aviation authority is identified as both ANAC and CTA. Therefore, whenever you find either, it corresponds to Brazilian certification. This is because since March 26, 2006, the Brazilian Civil Aviation authority was replaced by Civil Aviation National Agency (ANAC) instead of CTA. Similarly, the European Aviation Safety Agency (EASA) co-exists with JAA. So, from now on, you may find JAA/EASA or just JAA, with both corresponding to European certification. AIRPLANE OPERATIONS MANUAL GENERAL REVISION 27 1-00-00 Page 3 Code 01 OPERATIONAL REQUIREMENTS AND THE AIRPLANE OPERATIONS MANUAL The existence of fleets composed of airplanes or other kind of aircraft made by different manufacturers, led the Airworthiness Authorities to require operators' certification, in addition to the airplane's certification. The idea is to standardize manuals, training and operation, so as to make it easier for a pilot to change equipment. For instance, if a pilot used to fly an EMB-120 is scheduled to fly an EMB-145, the training syllabus from the EMB-145 has to be very similar to the ones for the EMB-120; the operator normal, abnormal and emergency procedures must be quite similar when different from AFM, as well as the manuals for both airplanes. By doing so, the operator will assure that human factors/ errors are minimized. Some operational requirements just define the main subjects that must be presented in an Airplane Operations Manual matter. However, even detailing the Airplane Operations Manual at that level, all the requirements let the operators free to use different Airplane Operations Manual structures, depending on the manuals. that have been already issued. Therefore, EMBRAER has developed this Airplane Operations Manual trying to cover, in the best possible way, the most currently used requirements. By doing so, it is possible for an operator to use the EMBRAER Airplane Operations Manual, by just adding some missing information that is specific to that operator. Following is a suggested Airplane Operations Manual structure to comply with most of the Operation Requirements: PART A Presents operator’s administrative information, such as who are the president , vice-president, the managers, who is the chief pilot for the EMB-145, who is the responsible for revising manuals, where the offices and bases are located, etc... PART B Presents airplane related information, like procedures, performance, dispatch procedures, Weight and Balance, bulletins and systems description. GENERAL AIRPLANE OPERATIONS MANUAL 1-00-00 Page 4 Code 01 REVISION 27 PART C Presents the operator’s airport and route information (performance and navigation). PART D Presents training information. EMBRAER AIRPLANE OPERATIONS MANUAL This EMBRAER Airplane Operations Manual covers only Part B. Parts A and D should be generated by the operator only. Part C can be generated by the operator with the help of EMBRAER operations software (runway analysis, driftdown , and route analysis). AIRPLANE OPERATIONS MANUAL STRUCTURE The EMBRAER Airplane Operations Manual is organized in two volumes, with the following contents: − Volume 1: − 1-00 General Information and Definition of Terms − 1-01 Limitations − 1-02 Normal Procedures − 1-03 Emergency and Abnormal Procedures − 1-04 Performance − 1-05 Flight Planning − 1-06 Weight and Balance − 1-07 Loading − 1-08 Configuration Deviation List − 1-09 Dispatch Deviations Procedures Manual − 1-10 Emergency Information − 1-11 Emergency Evacuation − 1-12 Ground Servicing AIRPLANE OPERATIONS MANUAL GENERAL REVISION 27 1-00-00 Page 5 Code 01 − Volume 2: − 2-1 Airplane Description − 2-2 Equipment and Furnishings − 2-3 Emergency Equipment − 2-4 Crew Awareness − 2-5 Electrical − 2-6 Lighting − 2-7 Fire Protection − 2-8 Fuel − 2-9 Auxiliary Power Unit − 2-10 Powerplant − 2-11 Hydraulic − 2-12 Landing Gear and Brakes − 2-13 Flight Controls − 2-14 Pneumatics, Air Conditioning and Pressurization − 2-15 Ice and Rain Protection − 2-16 Oxygen − 2-17 Flight Instruments − 2-18 Navigation and Communication − 2-19 Autopilot Each of the above sections may be divided into smaller parts, called blocks. Such blocks are identified by the number of the section followed by a two-digit number. For example: Section 1-04 can be divided as follows: − 1-04-00 Introduction − 1-04-05 Wind and altitude − 1-04-10 Thrust Setting − 1-04-15 Takeoff − 1-04-20 Supplementary Takeoff − 1-04-25 Approach − 1-04-30 Landing GENERAL AIRPLANE OPERATIONS MANUAL 1-00-00 Page 6 Code 01 REVISION 13 The page numbering of each part is independent from the remaining parts. Each page number is presented just to the right of the block number. As a complement, a code number is provided, to help identifying to which configuration each block is applicable. Some codes may be applicable to more than one configuration, whilst more than one code may be specific to one configuration. As an example, there could be: Block Codes Number of pages Numbering 1-04-00 01 2 1 to 2 1-04-05 01 6 1 to 6 01 20 1 to 20 1-04-10 02 20 1 to 20 03 20 1 to 20 01 6 1 to 6 1-04-15 02 6 1 to 6 03 10 1 to 10 04 4 1 to 4 01 24 1 to 24 1-04-20 02 24 1 to 24 05 20 1 to 20 01 4 1 to 4 1-04-25 03 4 1 to 4 04 4 1 to 4 07 4 1 to 4 01 6 1 to 6 1-04-30 02 4 1 to 4 03 6 1 to 6 04 4 1 to 4 AIRPLANE OPERATIONS MANUAL GENERAL REVISION 27 1-00-00 Page 7 Code 01 REVISIONS EMBRAER may revise this manual periodically as required to update information or to provide information not available at the time of printing the original issue. Revised data may result from EMBRAER approved airplane modifications or from improved techniques gained through operational experience. They are either replacements or additional pages. A vertical line in the outside margin indicates changes to the text. A vertical line adjacent to the page number indicates relocated or rearranged text or illustrations. The basic issuance date of this Manual is presented in the title page. The revisions affecting this Manual to be issued from the basic issuance date onwards, will be numbered sequentially (Rev. 1, 2, 3 etc.), even for such pages bearing those earlier revision-denoting symbols. LIST OF EFFECTIVE PAGES A list of Effective Pages for all Sections is located at the beginning of this Manual. This list presents the issuance date of each page and it is revised together with the Manual. Its purpose is to check if all the revised pages of a revision have been correctly sent to the purchaser. GENERAL AIRPLANE OPERATIONS MANUAL 1-00-00 Page 8 Code 01 REVISION 13 THIS PAGE IS LEFT BLANK INTENTIONALLY AIRPLANE OPERATIONS MANUAL GENERAL REVISION 13 1-00-10 Page 1 Code 01 DEFINITION OF TERMS The following definitions apply to the terms below: WARNING: OPERATING PROCEDURES, TECHNIQUES AND OTHER RELATED INFORMATION WHICH MAY RESULT IN PERSONAL INJURY OR LOSS OF LIFE, IF NOT CAREFULLY FOLLOWED. CAUTION: OPERATING PROCEDURES, TECHNIQUES AND OTHER RELATED INFORMATION WHICH MAY RESULT IN DAMAGE OR DESTRUCTION OF EQUIPMENT, IF NOT CAREFULLY FOLLOWED. NOTE: Operating procedures, techniques and other related information which are considered essential to emphasize. GENERAL AIRPLANE OPERATIONS MANUAL 1-00-10 Page 2 Code 01 REVISION 29 ABBREVIATIONS AND ACRONYMS ABBREVIATIONS OR ACRONYMS MEANING ºC Degree Celsius ºF Degree Fahrenheit ft Feet g Gravity Acceleration h Hour Hz Hertz in.Hg Inches of Mercury kg Kilogram km Kilometer kph Kilograms per Hour kt Knot lb Pounds m Meter mb Milibar min Minute mm Millimeter mph Miles per Hour nm Nautical Mile psi Pound per Square Inch sec Second A A Ampere A/C Aircraft AC Alternating Current ACM Air Cycle Machine AIRPLANE OPERATIONS MANUAL GENERAL REVISION 33 1-00-10 Page 3 Code 01 ABBREVIATIONS OR ACRONYMS MEANING ACOC Air Cooled Oil Cooler ACT Actuation, Active ADC Air Data Computer ADF Automatic Direction Finder ADJ Adjustment ADV Advance AFM Airplane Flight Manual AFS Autoflight System AGL Above Ground Level AHC Attitude and Heading Computer AHRS Attitude and Heading Reference System AIL Aileron ALC APU Line Contactor ALT Altitude ALTN Alternate AM Amplitude Modulation ANAC Agência Nacional de Aviação Civil (Brazilian Civil Aviation Authority) ANR Automatic Navigation Realignment ANT Antenna AOA Angle of Attack AP Autopilot API Antenna Position Indicator APR Automatic Power Reserve APU Auxiliary Power Unit ASC APU Starting Contactor ATC Air Traffic Control ATDT, ATTD Attendant GENERAL AIRPLANE OPERATIONS MANUAL 1-00-10 Page 4 Code 01 REVISION 13 ABBREVIATIONS OR ACRONYMS MEANING ATS Air Turbine Starter ATT Attitude ATTCS Automatic Takeoff Thrust Control System AUTO Automatic AUX Auxiliary AVAIL Available AWU Aural Warning Unit B B/C Back Course BACV Bleed Air Check Valve BAGG Baggage BATT Battery BBC Backup Battery Contactor BC Battery Contactor BCU Brake Control Unit BCV Brake Control Valve BFO Beat Frequency Oscillator BIT Built In Test BKUP INPH Back-Up Interphone BLD Bleed BTC Bus Tie Contactor BTL Bottle C CAB EMERG Cabin Emergency AIRPLANE OPERATIONS MANUAL GENERAL REVISION 13 1-00-10 Page 5 Code 01 ABBREVIATIONS OR ACRONYMS MEANING CAS Calibrated Airspeed, Crew Alerting System CBV Cross Bleed Valve CCDL Cross-Channel Data Link CDH Clearance Delivery Head CDL Configuration Deviation List CCW Counterclockwise CG Center of Gravity CIS Cabin Interphone System CL Climb CLB Climb CLR Clear CLSD Closed CMC Central Maintenance Computer COMM, COM Communication CON Continuous CPAM Cabin Pressure Acquisition Module CPCS Cabin Pressure Control System CR Cruise CRZ Cruise CVG Compressor Variable Geometry CVR Cockpit Voice Recorder CW Clockwise D DAP Digital Audio Panel GENERAL AIRPLANE OPERATIONS MANUAL 1-00-10 Page 6 Code 01 REVISION 32 ABBREVIATIONS OR ACRONYMS MEANING DAU Data Acquisition Unit DC Direct Current, Digital Controller DEC Decrease DET Detector DFDR Digital Flight Data Recorder DG Directional Gyro DH Decision Height DISC Disconnect DME Distance Measurement Equipment DMU Data Management Unit DN Down E EADI Electronic Attitude Director Indicator EBC Essential Bus Contactor EBV Engine Bleed Valve ECM Electronic Control Module ECS Environmental Control System ECU Environmental Control Unit EDL Electrical Distribution Logic EDS Electrical Distribution System EFIS Electronic Flight Instrument System EGPWS Enhanced Ground Position Warning System EGT Exhaust Gas Temperature EHSI Electronic Horizontal Situation Indicator AIRPLANE OPERATIONS MANUAL GENERAL REVISION 32 1-00-10 Page 7 Code 01 ABBREVIATIONS OR ACRONYMS MEANING EIC Essential Interconnection Contactor EICAS Engine Indication and Crew Alerting System ELEC Electrical ELEV Elevator ELT Emergency Locator Transmitter EMG, EMERG Emergency EMER PILOT Emergency Pilot ENG Engine ERR Error ESU Electronic Sequence Unit ET Elapsed Time EXT External EXTG Extinguish F FADEC Full Authority Digital Electronic Control FCOC Fuel Cooled Oil Cooler FDAU Flight Data Acquisition Unit FDRS Flight Data Recorder System FECU Flap Electronic Control Unit FLC Flight Level Change Mode FLX Flexible FMS Flight Management System FPDU Flap Power and Drive Unit FPLN Flight Plan FPMU Fuel Pump and Metering Unit FQIS Fuel Quantity Indicating System GENERAL AIRPLANE OPERATIONS MANUAL 1-00-10 Page 8 Code 01 REVISION 32 ABBREVIATIONS OR ACRONYMS MEANING FR Fuel Remaining FSBY Forced Standby FTB Flap Transmission Brake FU Fuel Used FVS Flap Velocity Sensor FWD Forward G G/S, GS Glide Slope GCU Generator Control Unit GI Ground Idle GLC Generator Line Contactor GMAP Ground Mapping GMT Greenwich Mean Time GND Ground GPC Ground Power Contactor GPS Global Positioning System GPU Ground Power Unit GPWS Ground Proximity Warning System H HDG Heading HF High Frequency HP High Pressure hPa HectoPascal HSCU Horizontal Stabilizer Control Unit AIRPLANE OPERATIONS MANUAL GENERAL REVISION 32 1-00-10 Page 9 Code 01 ABBREVIATIONS OR ACRONYMS MEANING HSI Horizontal Situation Indicator HSV High Stage Valve HYDR Hydraulic I IAC Integrated Avionics Computer IAS Indicated Airspeed IC Integrated Computer ICAO International Civil Aviation Organization ICU Integrated Communication Unit Interphone Control Unit IFR Instrument Flight Rules IFOG Interferometer Fiber Optic Gyros ILS Instrument Landing System IM Integrated Computer Configuration Module INBD Inboard INC Increase INOP Inoperative INTPH Interphone INU Integrated Navigation Unit IPS Inches Per Second IRS Inertial Reference System IRU Inertial Reference Unit ISA International Standard Atmosphere ISIS Integrated Standby Instrument System ITT Interturbine Temperature K KCAS Calibrated Airspeed in Knots KEAS Equivalent Airspeed in Knots kHz Kilohertz GENERAL AIRPLANE OPERATIONS MANUAL 1-00-10 Page 10 Code 01 REVISION 32 ABBREVIATIONS OR ACRONYMS MEANING K KIAS Indicated Airspeed in Knots L LAV Lavatory LEI Local Engine Inoperative LGEU Landing Gear Electronic Unit LH Left-hand LOC Localizer LOGO Logotype LP Low Pressure LRN Long Range LSB Lower Sideband LSS Lightning Sensor System LX Lightning Detection M M Mach MAC Mean Aerodynamic Chord MAN Manual MAX Maximum MB Marker Beacon MEA Minimum Enroute Altitude MFD Multifunction Display MFDU Magnetic Flux Detector Unit MHz Megahertz MIN Minimum MKR Marker MLS Microwave Landing System AIRPLANE OPERATIONS MANUAL GENERAL REVISION 32 1-00-10 Page 11 Code 01 ABBREVIATIONS OR ACRONYMS MEANING MLW Maximum Design Landing Weight MMEL Master Minimum Equipment List M MO Maximum Operating Mach MOW Maximum Design Operating Weight MRW Maximum Design Ramp Weight MSU Mode Select Unit MTOW Maximum Design Takeoff Weight MZFW Maximum Design Zero Fuel Weight N N1 Fan Speed N2 High-Pressure-Rotor Shaft Speed NAV Navigation NB Narrow Bandwidth NDB Non-directional Beacon O OM Operations Manual OUTBD Outboard OVHT Overheating OVLD Overload OVPRESS Overpressure OXY Oxygen P PAA Passenger Address Amplifier PAS Passenger Address System PAST Pilot Activated Self Test PAX Passenger PBE Protective Breathing Equipment GENERAL AIRPLANE OPERATIONS MANUAL 1-00-10 Page 12 Code 01 REVISION 32 ABBREVIATIONS OR ACRONYMS MEANING PCU Power Control Unit PDSV Pressure Drop Spill Valve PFD Primary Flight Display PMA Permanent Magnet Alternator POST Power On Self Test PRCS Process PRESS Pressure PRV Pressurizing Valve PSU Passenger Service Unit PTT Press To Transmit Q QFE Question Field Elevation - Field Elevation Pressure (Q-code) QNE Question Normal Elevation - Standard Pressure (1013 hPa/29.92 in.Hg) (Q-code) QNH Question Normal Height - Sea Level Pressure (Q-code) QTY Quantity R RA Radio Altimeter RTA Receiver/Transmitter/Antenna REACT Rain Echo Attenuation Compensation Technique REF Reference REI Remote Engine Inoperative RH Right-hand RMI Radio Magnetic Indicator RMS Radio Management System AIRPLANE OPERATIONS MANUAL GENERAL REVISION 32 1-00-10 Page 13 Code 01 ABBREVIATIONS OR ACRONYMS MEANING RMU Radio Management Unit RNG Range RPM Revolution Per Minute RSB Radio System Bus S SAT Static Air Temperature SBC Shed Bus Contactor SCV Starting Control Valve SELCAL Selective Call SL Sea Level SLVD Slaved SOV Shutoff Valve SPC Stall Protection Computer SPS Stall Protection System SQ Squelch STAB Stabilizer STBY Stand By SRN Short Range SSB Single Sideband T TA Traffic Advisory TAS True Airspeed TAT Total Air Temperature TCAS Traffic and Collision Avoidance System TDR Transponder TACAN Tactical Air Navigation Aid TEMP Temperature GENERAL AIRPLANE OPERATIONS MANUAL 1-00-10 Page 14 Code 01 REVISION 33 ABBREVIATIONS OR ACRONYMS MEANING TGT Target TKNB Turn Knob TLA Thrust Lever Angle TO Takeoff TRB Turbulence TST Test TWA Time Weighted Average V V Volt V 1 Decision Speed V 2 Takeoff Safety Speed VA Volt-Ampere VAPP VOR Approach Mode V A Design Maneuvering Speed V EF Critical Engine Failure Speed V FE Maximum Flaps Extended Speed VFR Visual Flight Rules VHF Very High Frequency V LE Maximum Landing Gear Extended Speed VLF Very Low Frequency V LO Maximum Landing Gear Operating Speed V LOF Lift Off Speed VLV Valve VMC Visual Minimum Condition V MCA Air Minimum Control Speed V MCG Ground Minimum Control Speed AIRPLANE OPERATIONS MANUAL GENERAL SEPTEMBER 20, 1999 1-00-10 Page 15 Code 01 ABBREVIATIONS OR ACCRONYMS MEANING V MO Maximum Operating Speed VOR VHF Omnidirectional Range V R Rotation Speed V REF Landing Reference Speed V REFXX Landing Reference Speed associated to the flap setting XX V S Stall Speed VS Vertical Speed W W/S Windshield WB Weight and Balance WB Wide Bandwidth WG Wing WX Weather Detection X X Cross XFR Transfer GENERAL AIRPLANE OPERATIONS MANUAL 1-00-10 Page 16 Code 01 SEPTEMBER 20, 1999 THIS PAGE IS LEFT BLANK INTENTIONALLY AIRPLANE OPERATIONS MANUAL GENERAL REVISION 27 1-00-10 Page 17 Code 01 SYMBOLS AND NOTATIONS SYMBOL MEANING OR SHUTOFF VALVE, PRIORITY VALVE CHECK VALVE RESTRICTOR RELIEF VALVE OPTIONAL EQUIPMENT SYSTEM MODULE COMMUNICATION LINE ELECTRIC PUMP MECHANIC PUMP ACCUMULATOR ELECTRIC CONTACTOR (OPEN POSITION) GENERAL AIRPLANE OPERATIONS MANUAL 1-00-10 Page 18 Code 01 REVISION 13 SYMBOL MEANING SWITCH NACA AIR INLET AIRPLANE OPERATIONS MANUAL GENERAL REVISION 25 1-00-20 Page 1 Code 01 UNITS CONVERSION TO CONVERT INTO MULTIPLY BY AND ADD Degree Celsius (ºC) Degree Fahrenheit (ºF) 1.8000 +32 Degree Fahrenheit (ºF) Degree Celsius (ºC) 0.5556 -17.7778 Feet (ft) Meter (m) 0.3048 - Inches (In) Millimeter (mm) 25.4000 - Inches of Mercury (in.Hg) Millibar (mb) 33.8636 - Kilogram (kg) Pounds (lb) 2.2046 - Kilogram force per Square meter (kgf/m 2 ) Pound per Square Inch (psi) 0.0014 - Kilometer (km) Nautical Mile (nm) 0.5396 - Kilometer per hour (km/h) Knot (kt) 0.5396 - Knot (kt) Kilometer per hour (km/h) 1.8532 - Pounds (lb) Kilogram (kg) 0.4536 - Meter (m) Feet (ft) 3.2808 - Millibar (mb) Inches of Mercury (in.Hg) 0.0295 - Millimeter (mm) Inches (In) 0.0394 - Nautical Mile (nm) Kilometer (km) 1.8532 - Pound per Square Inch (psi) Kilogram force per Square meter (kgf/m 2 ) 703.0740 - GENERAL AIRPLANE OPERATIONS MANUAL 1-00-20 Page 2 Code 01 REVISION 13 THIS PAGE IS LEFT BLANK INTENTIONALLY AIRPLANE OPERATIONS MANUAL GENERAL MARCH 30, 2001 1-00-30 Page 1 Code 01 EICAS VERSIONS VERSIONS 14A AND 15A − Fix the Pitch Trim Runaway Monitoring logic (airplanes equipped with EICAS 14 or 15 are not allowed to use the Autopilot below 1500 ft). VERSION 14 − CAT II capability. VERSION 15 − Oil pressure green indication increased to 95 psi and red above it (on EICAS 14 it was green up to 90 psi and amber above it). − Higher brake temperature limits for LR brakes. − ICE/SPS ADVANCED renamed SPS/ICE SPEEDS. − Flaps 18 capability. − Autopilot “wing rocking” improvements. VERSION 15B − Fixes the nuisance “Check PFD” message. VERSION 16 − ENG1 (2) REV DISAGREE message logic improved in order to avoid spurious alarms. − RUD HDOV PROT FAIL message logic improved in order to avoid spurious alarms. − Enhanced engine Time Limited Dispatch (TLD) incorporated: − E1 (2) CTL A (B) DEGRAD removed; − E1 (2) CTL A (B) FAIL revised (indicates loss of CVG/MMV control); − E1 (2) NO DISP incorporated; − E1 (2) SHORT DISP incorporated. GENERAL AIRPLANE OPERATIONS MANUAL 1-00-30 Page 2 Code 01 SEPTEMBER 29, 2000 − Improvements in other engine messages not TLD related: − E1 (2) LOW N1 revised (available only for takeoff below V1-15); − ENG1 (2) OUT incorporated; − ENG 1-2 OUT incorporated; − ENG1 (2) TLA FAIL revised; − FADEC ID NO DISP incorporated; − CHECK xxx PERF incorporated; − E1 (2) ADC DATA FAIL removed. − New FD control laws with different gain programming for FD modes in order to improve the Flight Director capture speed. − Incorporation of the VERTICAL and LATERAL MODE OFF messages. − IC CONFIG FAIL cyan message (dispatchable) created to indicate a IM-600 failure and use by the IC-600 of the lastest IM-600 valid data. − CONFIG MISMATCH cyan message (no takeoff) created to indicate that there is a discrepancy in the configuration module (IM- 600) of each IC-600. The configuration module stores several aircraft configuration parameters. VERSION 16.5 − Anti-Icing system improvements (new messages and logic): − A/I LOW CAPACITY incorporated; − WG1 (2) A/ICE FAIL and WG ASYMETRY removed; − WG A/ICE FAIL incorporated; − ENG A/ICE OVERPRES incorporated; − E1 (2) A/ICE FAIL renamed ENG1 (2) A/ICE FAIL. − TAT 1-2 HEAT INOP logic changed to improve TAT and SAT indications and to increase the probes life. − Brake messages logic changed to avoid failure messages due to power drop during APU start on ground. − A1P and A1/3 thrust labels renamed from ALT T/O and T/O, to T/O and T/O RSV respectivelly. − ATTCS NO MRGN improvements for the A3 engine. − Support to the 8.33 kHz tune function in the FMZ 2000 FMS. − APU FUEL LO PRESS logic changed to avoid spurious messages during APU pressure transients . − Support to Inertial System (IRS) as an AHRS replacement. − Improvement in the Cabin Pressure Control System (CPCS) indication in order to avoid unnecessary amber indication on the EICAS. AIRPLANE OPERATIONS MANUAL GENERAL MARCH 30, 2001 1-00-30 Page 3 Code 01 − Correction of autopilot disconnection logic discrepancy when a windshear condition is detected (removes the AFM limitation regarding use of autopilot coupled to FD#2 below 1500 ft). − Flight Director Altitude Pre-selection Mode Capture logic improved. − LNAV Flight Director logic changed when PFD FMS NAV source is changed from FMS 1 to 2 or vice-versa, in order to drop the LNAV FD mode. This change makes the FMS lateral navigation modes consistent with the VOR & LOC FD modes. − Correction of nuisance LATERAL/VERTICAL MODE OFF messages when both FD are deselected by the pilots. − Correction of nuisance LATERAL MODE OFF message when the pilot actuates the Turn Knob with a lateral mode (HDG, NAV, APR) active. − CHK IC CONFIG amber message (no takeoff) created to replace the CONFIG MISMATCH message in case of discrepancy between the following information stored in the IM-600: 135 or 145, Engine Type, Long Range Fuel Tank or English/Metric Units. CONFIG MISMATCH is still active in case of discrepancy of the other parameters that do not trigger the CHK IC CONFIG message. − Oil pressure green indication increased to 115 psi in takeoff mode. VERSION 17 − Provides interface with the Head-Up Guidance System to allow CAT IIIa operation. − Inclusion of FDR additional parameters according to FAR 121.344. − Autopilot improvement in the FD VOR mode capture and tracking for VOR stations without an associated DME. − Provides crosscheck of the CAT 2 annunciators in both PFD, avoiding a green CAT 2 indication on one side and an amber CAT 2 indication on the opposite side. − Automatic Radio Altimeter reversion in the case of one RA inop on aircraft equipped with two RA’s. − Adjustments to the Fuel Quantity indication on the MFD, adjusting scale according to the airplane version. − Inclusion of several messages related to IRS system. − ATTCS NO MRGN message logic improvements. − Electrical system display improvements : valid GPU 0V voltage and valid Generator 0A amperage. − Oil Pressure limits presented in both amber and red bands above the green one. GENERAL AIRPLANE OPERATIONS MANUAL 1-00-30 Page 4 Code 01 DECEMBER 20, 2002 OIL PRESSURE INDICATION (1) For any takeoff thrust mode selected and TLA higher than 65º or with thrust levers set to firewall (go-around), the upper limit of the green band is 115 psi. In all other thrust ratings it is 95 psi. (2) For EICAS version 17 with FADEC B 5.1.1 the amber band upper limit is 155 psi. (3) For N2 < 88% the amber band between 34 psi and 50 psi does not exist, and the green band lower limit is 34 psi. (4) For EICAS 14, a placard is installed in the cockpit allowing the operation in the amber band, between 91 and 115 psi, during the takeoff and go-around phases, time limited to 5 minutes. AIRPLANE OPERATIONS MANUAL GENERAL REVISION 24 1-00-30 Page 5 Code 01 VERSION 18 AND 18.5 − Pitch Trim System: − New caution messages PTRIM CPT SW FAIL, PTRIM F/O SW FAIL and PTRIM BKP SW FAIL; − PTRIM 1(2) INOP renamed to PTRIM MAIN INOP and PTRIM BACKUP INOP. − Autopilot system improvements: − Improved localizer capture performance using AP/FD, especially when under crosswind conditions; − Roll Command inbound during LOC capture; − New Roll Rate limit (7.5 degrees/sec) and Bank Angle limit (30.0 degrees) for ILS Approach mode and LNAV mode in Terminal and Approach phases; − Cancellation of APR light on Flight Guidance Controller (GC550) when glide slope mode is cancelled; − Inhibition of VERTICAL MODE OFF message if the FD mode is cancelled by changing the preselected altitude; − Inhibition of VERTICAL MODE OFF and/or LATERAL MODE OFF messages if a lateral and/or a vertical FD mode is cancelled by transferring the FD control to the cross-side; − Improvements in the Autopilot system to prevent the AP from disconnecting when the speed brake is deployed while operating in Touch Control Steering (TCS) mode; − Inhibition of LATERAL MODE OFF message when the navigation source is changed from one FMS to the cross-side FMS when LNAV mode is armed. − HGS: − Modification on the expanded localizer scale/display on the PFD to help pilot in Cat IIIa operations; − Information to HGS that TOGA button was pressed; − Change of HGS FAIL from ADVISORY to AMBER (caution) to comply with AC 120-28D requirements. − AHRS: − New advisory messages AHRS 1-2 NO PPOS, AHRS 1-2 NO MAG HDG. GENERAL AIRPLANE OPERATIONS MANUAL 1-00-30 Page 6 Code 01 REVISION 28 VERSION 19 The EICAS 19 features implemented in the software are described below: Air conditioning system − The Bleed Temperature Pointers were modified to remain amber at all the times that the messages BLD 1(2) LOW TEMP are displayed. Brake System − New digital brake temperature indication on MFD (if IM-600 Digital BRK TEMP parameter is enabled). EICAS Internal Logic − New message DAU AC ID MISCMP. Electrical System − GPU Voltage Indication modified in order to avoid dashes when the indication should be 0 V. Flap System − Flap 22 indication in red on EICAS display and NO TAKEOFF CONFIG message when the aircraft is not certified to take off with flaps 22º. Fuel System − New Message FUEL EQ XFEED OPN to inform that the imbalance was correct and the crossfeed valve is still open. − Fuel Test Page units label modified in order to show the correct English/Metric configuration. General Changes − Synchronization of the Speed Target Bug with the previous selected Speed Target instead of synchronizing with the current aircraft’s speed shown on the Speed Tape when VS Vertical Flight Director Mode is de-selected. − Windshear indication on PFD always in red when RA test button is pressed. − Due to mandatory installation of IM-600 on this EICAS version and on, the CAT II Operation is available and indicated. AIRPLANE OPERATIONS MANUAL GENERAL REVISION 26 1-00-30 Page 7 Code 01 Anti Ice System − PITOT 1-2-3 INOP messages modified in order to avoid spurious occurrences during APU starting. Powerplant System − ENG NO TO DATA message modified in order to avoid an unlikely scenario of a takeoff performed with only one engine running. − New messages : − CHECK A1E PERF (only applicable to EMB-145 XR model), − E1-2 FPMU NO DISP (only applicable to EMB-145 XR model), − E1-2 EXCEEDANCE. − A1E thrust rating modes included on EICAS/RMU/MFD. − New upper range limit for fuel flow indication due to A1E engine. − ITT and N2 Dynamic Redlines. − Oil Pressure Indication modified in order to avoid spurious indication of low oil pressure values. − ENG 1-2 REV DISAGREE message change in order to avoid a failure without indication on EICAS. Pressurization System − Changes to Cabin Altitude Rate. − New function HIGH ALT on MFD Bezel (only applicable to EMB-145 XR model). − New message HI ALT LDG-T/O (only applicable to EMB-145 XR model). − Changes to cabin altitude indication on EICAS display. GENERAL AIRPLANE OPERATIONS MANUAL 1-00-30 Page 8 Code 01 REVISION 30 VERSION 20.5 The EICAS 20.5 features implemented in the software are described below: Air conditioning system − "BLEED 1(2) VLV CLSD" message logic improved in order to avoid spurious alarms. Fuel System − "FUEL VENT OPEN" and "FUEL XFER INOP" messages logic improved in order to avoid spurious alarms (only applicable to EMB-145 XR model). Powerplant System − "ENG1(2) REV DISAGREE" message logic improved in order to avoid spurious alarms. Pressurization System − "HI ALT LDG-T/O" message changed from caution to advisory (only applicable to airplanes properly equipped for High Altitude Operation). Navigation System − The Radio Altimeter indication was modified in order to reduce the discrepancy between the current altitude of the aircraft and the PFD Radio Altitude indication. Autopilot System − Pitch Wheel Command Integrator - Correction to avoid poor Autopilot response when using the Pitch Wheel while coupled to the copilot’s Flight Director, which may cause the Autopilot logic to reset an integrator, resulting in sluggish Autopilot response. − Pitch Axes - Correction to avoid Autopilot nuisance disconnection due to the Pitch Primary Monitor during the Coupled Autopilot Go- Around test (only applicable to EMB-145 XR model). General Changes − New AZ-950 MADC Maintenance Page on PFD. AIRPLANE OPERATIONS MANUAL GENERAL REVISION 33 1-00-30 Page 9 Code 01 VERSION 20.7 The EICAS 20.7 features implemented in the software are described below: Autopilot: − Autopilot disengagement without aural warning Correction: It was verified that under certain circumstances the autopilot can disengage without aural warning. It occurs when autopilot is engaged and TCS button pressed. If any pitch trim switch is commanded while the TCS is being released the autopilot disengages with no aural warning. The same situation can occurs when deploying/retracting speed brake simultaneously to TCS releasing, due to the automatic pitch trim command during speed brake actuation. − Symbol Generator Reversion Correction: It was verified an abnormal behavior in the Automatic Flight Control System when a Symbol Generator reversion occurs on the pilot side. In this case the Autopilot reverts to basic mode and automatically couples to the co-pilot Flight Director as expected. If a vertical mode is selected to either climbing or descending following the Symbol Generator reversion, the Autopilot will not hold the pre-selected altitude although the Flight Director bars indicate level off and the PFD shows the correct mode transition from the selected vertical mode to ASEL mode and from ASEL mode to ALT HOLD mode. − CAT II operation at Providence Airport: Automatic Flight Control System changes were required in order to allow CAT II operation at Providence Airport, which has a RA Minimums of 80 ft. The current RA Minimums interval does not include 80 ft. Therefore, the 80 ft RA Minimums was included in the CAT II logic to allow proper operation in this airport. − Roll Oscillation Solution at high altitudes: Yaw Damper control law was modified in order to minimize the roll oscillation observed at high altitudes when autopilot is engaged. This modification is enabled only in the 135 family airplane (EMB-135ER, EMB-135LR and EMB-135BJ) via IM-600 new parameter called RUDDER BIAS. GENERAL AIRPLANE OPERATIONS MANUAL 1-00-30 Page 10 Code 01 REVISION 33 HGS: − HGS compatibility issue: version 20.7 (Phase 10.7) shall correct the compatibility issue between EICAS Version 20.5 (Phase 10.5) and HGS equipped airplane. Therefore the RA value shall be displayed again on the HGS combiner. There will be no modifications on the HGS system. Ice Protection: − “ICE COND – A/ICE INOP” message logic change: in the current logic, under ice condition on the ground, this message may undesirably appear because the Anti-Ice protection cannot be activated. The reason for this modification is to inhibit this message only on the ground, when the airplane speed is below 25 kt. AIRPLANE OPERATIONS MANUAL GENERAL REVISION 37 1-00-35 Page 3 Code 01 A O M - 1 4 5 / 1 1 1 4 SERVICE BULLETIN TABLE SB SUBJECT SB 145-34-0049 Changes the Integrated Standby Instrument System (ISIS) into new P/N C16221GC03 - Amendment A. SB 145-34-0089 Incorporates modifications related to Mode S Elementary Surveillance Transponders. SB 145-34-0096 Incorporates modifications related to Mode S Enhanced Surveillance Transponders. SB 145-34-0106 Reconfiguration of the TCAS Performance Limit. SB 145-36-0028 Changes EBV S/O Valve by a Pressure Regulator Valve. SB 145-49-0010 Improves the Airborne Auxiliary Power (APU). SB 145-49-0012 Changes Auxiliary Power Unit (APU) Electronic Sequence Unit (ESU) feeder bus. SB 145-49-0014 Replaces the APU Air Inlet Frame. SB 145-52-0040 Lock Pin Installation. SB 145-53-0064 Increases the MZFW of the EMB-145ER and EP Models. SB 145-53-0065 Reduces MTOW of the EMB-145LR Model. SB 145-53-0066 Updates MTOW of the EMB-145LR Model. SB 145-53-0068 Increases the maximum gross weights of the EMB-145LR Model. SB 145-71-0003 Implements the Protection Guard for the Engine Start Switches. SB 145-73-0010 Incorporates FADEC B5.1.1 Version on AE3007A and A1/1 Engines. SB 145-73-0011 Incorporates FADEC B5.1.1 Version on AE3007A1 Engines. SB 145-73-0012 Incorporates FADEC B5.1.1 Version on AE3007A1P Engines. GENERAL AIRPLANE OPERATIONS MANUAL 1-00-35 Page 4 Code 01 REVISION 36 A O M - 1 4 5 / 1 1 1 4 SERVICE BULLETIN TABLE SB SUBJECT SB 145-73-0013 Incorporates FADEC B5.1.1 Version on AE3007A1/3 Engines. SB 145-73-0014 Incorporates FADEC B5.1.1 Version on AE3007A3 Engines. SB 145-73-0021 Incorporates FADEC B7.6 Version on AE3007A and A1/1 Engines. SB 145-73-0022 Incorporates FADEC B7.6 Version on AE3007A1 Engines. SB 145-73-0023 Incorporates FADEC B7.6 Version on AE3007A1P Engines. SB 145-73-0024 Incorporates FADEC B7.6 Version on AE3007A1/3 Engines. SB 145-73-0025 Incorporates FADEC B7.6 Version on AE3007A3 Engines. SB 145-73-0026 Incorporates FADEC B7.6 Version on AE3007A1E Engines. SB 145-73-0027 Incorporates FADEC B8.0 Version on AE3007A1P Engines. SB 145-73-0028 Incorporates FADEC B8.0 Version on AE3007A1E Engines. SB 145-73-0029 Incorporates FADEC B8.0 Version on AE3007A1 Engines. SB 145-73-0030 Incorporates FADEC B8.0 Version on AE3007A1/1 Engines. SB 145-73-0031 Incorporates FADEC B8.0 Version on AE3007A1/3 Engines. SB 145-77-0002 Includes Placard for 95 psi Oil Pressure Limit. SB 145-77-0003 Includes Placard for 115 psi Oil Pressure Limit. SB T-62T-49-152 Incorporates Modification to Permit APU Start Above 25000 ft. AIRPLANE OPERATIONS MANUAL GENERAL REVISION 36 1-00-35 Page 3 Code 01 A O M - 1 4 5 / 1 1 1 4 SERVICE BULLETIN TABLE SB SUBJECT SB 145-34-0049 Changes the Integrated Standby Instrument System (ISIS) into new P/N C16221GC03 - Amendment A. SB 145-34-0089 Incorporates modifications related to Mode S Elementary Surveillance Transponders. SB 145-34-0096 Incorporates modifications related to Mode S Enhanced Surveillance Transponders. SB 145-36-0028 Changes EBV S/O Valve by a Pressure Regulator Valve. SB 145-49-0010 Improves the Airborne Auxiliary Power (APU). SB 145-49-0012 Changes Auxiliary Power Unit (APU) Electronic Sequence Unit (ESU) feeder bus. SB 145-49-0014 Replaces the APU Air Inlet Frame. SB 145-52-0040 Lock Pin Installation. SB 145-53-0064 Increases the MZFW of the EMB-145ER and EP Models. SB 145-53-0065 Reduces MTOW of the EMB-145LR Model. SB 145-53-0066 Updates MTOW of the EMB-145LR Model. SB 145-53-0068 Increases the maximum gross weights of the EMB-145LR Model. SB 145-71-0003 Implements the Protection Guard for the Engine Start Switches. SB 145-73-0010 Incorporates FADEC B5.1.1 Version on AE3007A and A1/1 Engines. SB 145-73-0011 Incorporates FADEC B5.1.1 Version on AE3007A1 Engines. SB 145-73-0012 Incorporates FADEC B5.1.1 Version on AE3007A1P Engines. GENERAL AIRPLANE OPERATIONS MANUAL 1-00-35 Page 4 Code 01 REVISION 36 A O M - 1 4 5 / 1 1 1 4 SERVICE BULLETIN TABLE SB SUBJECT SB 145-73-0013 Incorporates FADEC B5.1.1 Version on AE3007A1/3 Engines. SB 145-73-0014 Incorporates FADEC B5.1.1 Version on AE3007A3 Engines. SB 145-73-0021 Incorporates FADEC B7.6 Version on AE3007A and A1/1 Engines. SB 145-73-0022 Incorporates FADEC B7.6 Version on AE3007A1 Engines. SB 145-73-0023 Incorporates FADEC B7.6 Version on AE3007A1P Engines. SB 145-73-0024 Incorporates FADEC B7.6 Version on AE3007A1/3 Engines. SB 145-73-0025 Incorporates FADEC B7.6 Version on AE3007A3 Engines. SB 145-73-0026 Incorporates FADEC B7.6 Version on AE3007A1E Engines. SB 145-73-0027 Incorporates FADEC B8.0 Version on AE3007A1P Engines. SB 145-73-0028 Incorporates FADEC B8.0 Version on AE3007A1E Engines. SB 145-73-0029 Incorporates FADEC B8.0 Version on AE3007A1 Engines. SB 145-73-0030 Incorporates FADEC B8.0 Version on AE3007A1/1 Engines. SB 145-73-0031 Incorporates FADEC B8.0 Version on AE3007A1/3 Engines. SB 145-77-0002 Includes Placard for 95 psi Oil Pressure Limit. SB 145-77-0003 Includes Placard for 115 psi Oil Pressure Limit. SB T-62T-49-152 Incorporates Modification to Permit APU Start Above 25000 ft.