Section 9 - Supplements - Delta Aviation

Record of Revisions Rev Revised page Description of Revision Tecnam Approval EASA Approval Or Under DOA Privileges DO OoA HDO 0 all Editorial change A. Sabino C. Caruso M. Oliva DOA Privileges. List of Effective Pages Page Revision G13-1 Rev 0 G13-2 Rev 0 G13-3 Rev 0 G13-4 Rev 0 G13-5 Rev 0 G13-6 Rev 0 Page G13-2 Section 9 - Supplements Supplement no. G13 – Alternators with 70A installation 3rd Edition, Rev. 0 INTRODUCTION This section contains supplemental information to operate, in a safe and efficient manner, the aircraft when 70A alternators are installed replacing the standard, 40A ones (Design Change MOD 2006/202). The information contained herein supplements or supersedes the basic Aircraft Flight Manual: detailed instructions are provided to allow the owner for replacing the AFM pages containing information amended as per the Design Change in sub- ject. It is the owner’s responsibility to replace the mentioned pages in the AFM in accordance with the instructions herein addressed section by section. GENERAL When 70A alternators are installed replacing the standard, 40A ones, the electrical system logic is not affected by any substantial change. Primary DC power is pro- vided by two engine-driven alternators which, during normal operations, operate in parallel. Each alternator is rated at 14,2-14,8 Vdc (through two external voltage regula- tors), 70 Amp and is provided with an automatic overvoltage device protecting the circuits and the electric components from an excessive voltage caused by alterna- tor's failures. The power rating of the each generator is such that if one generator fails the other one can still supply the airplane equipment to maintain flight safety. Page G13-3 Section 9 - Supplements Supplement no. G13 – Alternators with 70A installation 4th Edition, Rev. 0 SECTION 3 - EMERGENCY PROCEDURES This section report some procedures which replace the same procedure in the basic AFM. The procedures affected from the replacement of existing 40A alternators with 70A are the following:  Single alternator failure/overvoltage  Both alternators failure  Both alternators overvoltage Alternators with 70A - Supplement Section 9 - Supplements Supplement no. G13 – Alternators with 70A installation 4th Edition, Rev. 0 Page G13-4 Section 3 – Emergency procedures INDEX SINGLE ALTERNATOR FAILURE / OVERVOLTAGE Annunciation window Alert window L ALT FAIL Lh Alternator OR R ALT FAIL Rh Alternator 1. FIELD LH (or RH) OFF 2. FIELD LH (or RH) ON If the LH (or RH) ALT caution stays displayed 3. FIELD LH (or RH) OFF Equipment will be lost accordingly to the following table: The battery and a single generator are able to supply the electri- cal power necessary for flight, but redundancy is lost. LH Gen Bus LH Avionic Bus RH Avionic Bus RH Gen Bus Pitot Heat DME ADF NAV Lights Landing Light Transponder COM 2 Rudder Trim Taxi Light A/P NAV 2 Stall Warning A/P Pitch Trim MFD AHRS/ADC 4. Land as soon as practicable NOTE Alternators with 70A - Supplement Section 9 - Supplements Supplement no. G13 – Alternators with 70A installation 4th Edition, Rev. 0 Page G13-5 Section 3 – Emergency procedures INDEX BOTH ALTERNATORS FAILURE Annunciation window Alert window L ALT FAIL Lh Alternator R ALT FAIL Rh Alternator In event of both L and R ALT FAIL caution alerts displayed: 1. FIELD LH and RH BOTH OFF 2. FIELD LH and RH BOTH ON (one at a time) If the LH (or RH) ALT caution stays displayed 1. Verify good ammeter indications on restored alternator 2. Refer to Single alternator failure / overvoltage drill (Para 2.1) If both LH and RH ALT cautions stay displayed 3. FIELD LH and RH BOTH OFF 4. CROSS BUS LH and RH BOTH OFF If engine starting battery modification is applied 5. EMERG BATT switch ON 6. Land as soon as possible. If engine starting battery modification is not applied 5. Land as soon as possible. Equipment will be lost accordingly to the following table: LH Gen Bus LH Avionic Bus RH Avionic Bus RH Gen Bus Pitot Heat DME ADF NAV Lights Landing Light Transponder COM 2 Rudder Trim Taxi Light A/P NAV 2 Stall Warning A/P Pitch Trim MFD AHRS/ADC The battery will supply electrical power for at least 30 minutes. NOTE Alternators with 70A - Supplement Section 9 - Supplements Supplement no. G13 – Alternators with 70A installation 4th Edition, Rev. 0 Page G13-6 Section 3 – Emergency procedures INDEX BOTH ALTERNATORS OVERVOLTAGE Annunciation window Alert window L BUS VOLT HIGH Lh overvoltage R BUS VOLT HIGH Rh overvoltage In event of both L and R BUS VOLT HIGH warning alerts displayed: 1. FIELD LH and RH BOTH OFF 2. FIELD LH and RH BOTH ON (one at a time) If the LH (or RH) BUS VOLT HIGH caution stays displayed 3. Verify good ammeter indications on restored alternator 4. Refer to Single alternator failure / overvoltage drill (Para 2.1) If both LH and RH BUS VOLT HIGH warning stay displayed 3. CROSS BUS LH and RH BOTH OFF 4. FIELD LH and RH BOTH OFF 5. FIELD LH and RH BOTH ON (one at a time) If LH (or RH) BUS VOLT HIGH warning stays displayed 6. Verify good ammeter indications on restored alternator 7. Switch CROSS BUS on the restored alternator side 8. Refer to Single alternator failure / overvoltage drill (Para 2.1) If both LH and RH BUS VOLT HIGH warning stay displayed 7. FIELD LH and RH BOTH OFF If engine starting battery modification is applied 7. EMERG BATT switch ON 8. Land as soon as possible. If engine starting battery modification is not applied 8. Land as soon as possible. Equipment will be lost accordingly to the following table: LH Gen Bus LH Avionic Bus RH Avionic Bus RH Gen Bus Pitot Heat DME ADF NAV Lights Landing Light Transponder COM 2 Rudder Trim Taxi Light A/P NAV 2 Stall Warning A/P Pitch Trim MFD AHRS/ADC The battery can supply electrical power for at least 30 minutes. NOTE Page G14-1 Section 9 - Supplements Supplement no. G14 – SMP FOR DIGITAL CONFIGURATION Ed.4, Rev.1 SUPPLEMENT NO. G14 - SMP FOR DIGITAL CONFIGURATION RECORD OF REVISIONS Rev Revised page Description of Revision Tecnam Approval EASA Approval Or Under DOA Privileges DO OoA HDO 0 - First issue D. Ronca C. Caruso M. Oliva DOA Approval 1 S4-26 Integration of information formerly contained in Sup- plement G18 A. Sabino C. Caruso M. Oliva DOA Approval Page G14-2 Section 9 - Supplements Supplement no. G14 – SMP FOR DIGITAL CONFIGURATION Ed.4, Rev.1 LOEP Pages Revision Cover pages G14 – 3 thru 22 Rev. 0 G14 – 1, 2 Rev. 1 Section 2 SMP2 – 3 Rev. 0 Section 3 SSMP3 – 3 thru 5 Rev. 0 SSMP3 – 7 thru 9 Rev. 0 SSMP3 – 21 Rev. 0 SSMP3 – 29 Rev. 0 SSMP3 – 36 thru 40 Rev. 0 SSMP3 – 49 thru 53 Rev. 0 Section 4 SSMP4 – 27 Rev. 0 SSMP4 – 26 Rev. 1 Section 7 SSMP7 – 41 Rev. 0 SSMP7 – 44 thru 48 Rev. 0 Page G14-3 Section 9 - Supplements Supplement no. G14 – SMP FOR DIGITAL CONFIGURATION Ed.4, Rev.0 INTRODUCTION This section contains supplemental information to operate, in a safe and efficient manner, the aircraft when equipped with Garmin G950 Integrated Flight Deck Sys- tem (Design Change MOD 2006/002) and with Special Mission Platform. The Spe- cial Mission Platform refers to the following design changes:  MOD2006/046 - Power supply from built-in generators  MOD2006/202 - Replacement of existing 40A alternators with 70A  MOD2006/204 - Installation of converter box For the two first design changes the supplements (n° A15 and G13) are already ap- proved by EASA and in this supplement we report the same information for refer- ence. The Rotax engine built-in generators, one for each engine, feed two bus bars made available for end user equipment, when the design change 2006/046 is installed. When 70A alternators are installed replacing the standard, 40A ones, the electrical system logic is not affected by any substantial change. Primary DC power is pro- vided by two engine-driven alternators which, during normal operations, operate in parallel. Each alternator is rated at 14,2-14,8 Vdc (through two external, first fuselage frame installed voltage regulators), 70 Amp and is provided with an automatic overvolt- age device protecting the circuits and the electric components from an excessive voltage caused by alternator's failures. The power rating of the each generator is such that if one generator fails the other one can still supply the airplane equipment to maintain flight safety. The information contained herein supplements or supersedes the basic Aircraft Flight Manual or the Supplement G1, as applicable: detailed instructions are pro- vided to allow the owner for replacing the Basic AFM/Supplement G1 pages con- taining information amended as per the Design Changes in subject. Usually, the Special Mission Platform P2006T is also equipped with holes in the cabin and/or tailcone, ready for third parties sensor's integration. While the Tecnam intent is to offer a plat- form ready for sensors' integration, it is end-user responsibility to receive the approval from authority for each equipment instal- lation. It is the owner’s/operator's responsibility to replace the mentioned pages in the AFM in accordance with the instructions herein addressed section by section. NOTE Page G14-4 Section 9 - Supplements Supplement no. G14 – SMP FOR DIGITAL CONFIGURATION Ed.4, Rev.0 INTENTIONALLY LEFT BLANK Page G14-5 Section 9 - Supplements Supplement no. G14 – SMP FOR DIGITAL CONFIGURATION Ed.4, Rev.0 SECTION 1 – GENERAL Apply following instruction: See Basic AFM - Section 1 Supplement G14: pages replacement instructions Page G14-6 Section 9 - Supplements Supplement no. G14 – SMP FOR DIGITAL CONFIGURATION Ed.4, Rev.0 INTENTIONALLY LEFT BLANK Page G14-7 Section 9 - Supplements Supplement no. G14 – SMP FOR DIGITAL CONFIGURATION Ed.4, Rev.0 SECTION 2 – LIMITATIONS Apply following pages replacement procedure: Supplement G14 - LIMITATIONS page Basic AFM Section 2 page SMP2 – 3 REPLACES Page 2 – 3 of Basic AFM, Section 2 Supplement G14: pages replacement instructions Page G14-8 Section 9 - Supplements Supplement no. G14 – SMP FOR DIGITAL CONFIGURATION Ed.4, Rev.0 INTENTIONALLY LEFT BLANK GARMIN G950 IFDS – SMP FOR DIGITAL CONFIGURATION Page SMP2-3 Section 2 – Limitations INTRODUCTION Ed.4, Rev.0 EASA Approved 1. INTRODUCTION Section 2 includes operating limitations, instrument markings and basic placards necessary for safe operation of P2006T aircraft, its engines and standard systems and equipment. LH and RH AUX FIELDS, enabling the converter box operations for Special Mission purpos- es, should be kept OFF during take-off, climb, landing and any abnormal procedure that affects electrical generating system (including single engine operation): During Take-off, Climb, Landing and Single Engine Operations: LH and RH AUX FIELD switches BOTH OFF This limitation only applies when both 70Amp alternators and converter box are installed. Safety provisions, as following described, automatically disengage the LH and RH AUX FIELDS in case of one main field malfunction (i.e. for OEI). Also, if only one AUX FIELD switch is ON, the converter box is not pow- ered. NOTE NOTE Page G14-9 Section 9 - Supplements Supplement no. G14 – SMP FOR DIGITAL CONFIGURATION Ed.4, Rev.0 INTENTIONALLY LEFT BLANK Page G14-10 Section 9 - Supplements Supplement no. G14 – SMP FOR DIGITAL CONFIGURATION Ed.4, Rev.0 SECTION 3 – EMERGENCY PROCEDURES Apply following pages replacement procedure: Supplement G14 - EMERGENCY PROCEDURES page Supplement G1 Section 3 page SSMP3 – 3 thru 5 REPLACE Page S3 – 3 thru 5 of Supplement G1, Section 3 SSMP3 – 7 thru 9 REPLACE Page S3 – 8 thru 11 of Supplement G1, Section 3 SSMP3 – 21 REPLACES Page S3 – 21 of Supplement G1, Section 3 SSMP3 – 29 REPLACES Page S3 – 29 of Supplement G1, Section 3 SSMP3 – 36 thru 40 REPLACE Page S3 – 36 thru 40 of Supplement G1, Section 3 SSMP3 – 49 thru 53 REPLACE Page S3 – 49 thru 53 of Supplement G1, Section 3 Supplement G14: pages replacement instructions Page G14-11 Section 9 - Supplements Supplement no. G14 – SMP FOR DIGITAL CONFIGURATION Ed.4, Rev.0 INTENTIONALLY LEFT BLANK GARMIN G950 IFDS – SMP FOR DIGITAL CONFIGURATION Page SSMP3-3 Section 3 – Emergency procedures INTRODUCTION Ed.4, Rev.0 1. INTRODUCTION Section 3 includes checklists and detailed procedures for coping with various types of emergency conditions that could arise after a system failure. The procedures affected from installation of the Special Mission Platform are the following:  Single alternator failure / overvoltage  Both alternators failure  Both alternators overvoltage  Engine securing  Total electrical failure  Inflight engine restart  Engine failure during takeoff run  Engine failure during climb  Engine failure in flight  Engine fire on the ground  Engine fire during takeoff run  Engine fire in flight  Electrical smoke in cabin on the ground  Electrical smoke in cabin during flight The main difference regarding aircraft systems, compared with the basic AFM, is the presence of the Power supply from built-in generators, Alternators with 70A and Converter Box. The powering and disconnection of converter box is very simple and, in most of abnormal cases, is automatically managed by relays and safety provisions. The converter box (following described in Section 7) is managed by the pilot only via two switches, located in the bottom LH side of pilot seat on a single panel provided by: two switches, two breakers and two indicating lamps. Only when pilot selects BOTH switches ON (right and left AUX) and both alter- nators are operative the system allows a surplus of power generated by the en- gines and alternators to flow into 4x converters and, then, into mission equipment, when installed. The health status of converters inside the box (located into the baggage compart- ment) is monitored by mission operator, via 4x failure indicating lamps. Follow- ing the key concepts when managing converter boxes: 1. Mission Power Switches: they enable the converter box ONLY when BOTH are set to ON; 2. Converter box power: enabled only if both LH and RH main alternators are generating power; 3. Converter box: automatically switches OFF in case LH or RH main alter- nators is faulty / not generating; 4. Converter box: automatically switches OFF in case LH or RH mission switch is set to OFF; GARMIN G950 IFDS – SMP FOR DIGITAL CONFIGURATION Page SSMP3-4 Section 3 – Emergency procedures INTRODUCTION Ed.4, Rev.0 5. Failure lamp: when illuminated, indicates that the correspondent converter is not working properly and needs to be replaced if the maximum available power from converter box is needed. When all converters are working properly, the system is capable to output 40A@28V. If one converter fails, 12A@28V are lost. For this reason, the end-user mission can continue if the equipment demand is less than 25/28A. On the contrary, the converter needs to be replaced. Before operating the aircraft, the pilot/operator should become thoroughly famil- iar with this manual and, in particular, with this Section. Further on a continued and appropriate training and self study should be done. Two types of emergency procedures are hereby given. a. “BOLD FACES” which must be known by heart by the pilot and executed, in the correct and complete sequence, immediately after the failure is detected and confirmed. These procedures characters are boxed and highlighted: 1.1 ENGINE FAILURE DURING TAKEOFF RUN BEFORE ROTATION: ABORT TAKE OFF 1. Throttle Lever BOTH IDLE 2. Rudder Keep heading control 3. - - 4. - - b. “other procedures” which should be well theoretically known and mastered, but that can be executed entering and following step by step the AFM current section appropriate checklist. Additionally operating the aircraft, the pilot should become thoroughly familiar with the Garmin G950 Pilot’s Guide for Tecnam P2006T (P/N 190-01146-XX) – last issue - and, in particular, with the present AFM Section. CAUTION Garmin G950 Pilot’s Guide for Tecnam P2006T (P/N 190- 01146-XX) – last issue - must be carried onboard the airplane at all times. WARNING Garmin G950 has a very high degree of functional integrity. However, the pilot must recognize that providing monitoring and/or self-test ca- pability for all conceivable system failures is not practical. Although unlikely, it may be possible for erroneous operation to occur without a fault indication shown by the G950. It is thus the responsibility of the pilot to detect such an occurrence by means of crosschecking with all redundant or correlated information available in the cockpit. GARMIN G950 IFDS – SMP FOR DIGITAL CONFIGURATION Page SSMP3-5 Section 3 – Emergency procedures INTRODUCTION Ed.4, Rev.0 In any case, as a failure or abnormal behaviour is detected pilots should act as follows: 1. Keep self-control and maintain aircraft flight attitude and parameters 2. Analyse the situation identifying, if required, the area for a possible emergency landing 3. Apply the pertinent procedure 4. Inform the Air Traffic Control as applicable For the safe conduct of later flights, any anomaly and/or failure must be communicated to the National Authorities in charge, in order to put the aircraft in a fully operational and safe condition. In this Chapter, following definitions apply: Land as soon as possible: land without delay at the nearest suitable area at which a safe approach and landing is assured. Land as soon as practical: land at the nearest approved landing ar- ea where suitable repairs can be made. NOTE NOTE GARMIN G950 IFDS – SMP FOR DIGITAL CONFIGURATION Page SSMP3-7 Section 3 – Emergency procedures AIRPLANE ALERTS Ed.4, Rev.0 2.1. SINGLE ALTERNATOR FAILURE / OVERVOLTAGE Annunciation window Alert window L ALT FAIL Lh Alternator OR R ALT FAIL Rh Alternator 1. FIELD LH (or RH) OFF 2. LH and RH AUX FIELD switch BOTH OFF 3. FIELD LH (or RH) ON If the LH (or RH) ALT caution stays displayed 1. FIELD LH (or RH) OFF If the LH (or RH) GENERATOR caution persists displayed 1. CROSS BUS LH (or RH) OFF 2. Land as soon as practical. The battery and a single generator are able to supply the electrical power necessary for the entire mission, but redundancy is lost. NOTE GARMIN G950 IFDS – SMP FOR DIGITAL CONFIGURATION Page SSMP3-8 Section 3 – Emergency procedures AIRPLANE ALERTS Ed.4, Rev.0 2.2 BOTH ALTERNATORS FAILURE Annunciation window Alert window L ALT FAIL Lh Alternator R ALT FAIL Rh Alternator In event of both L and R ALT FAIL caution alerts displayed: 1. FIELD LH and RH BOTH OFF 2. LH and RH AUX FIELD switch BOTH OFF 3. FIELD LH and RH BOTH ON If both LH and RH ALT cautions stay displayed 1. FIELD LH and RH BOTH OFF 2. CROSS BUS LH and RH BOTH OFF If engine starting battery modification is applied 1. EMERG BATT switch ON 2. Land as soon as possible. If engine starting battery modification is not applied 1. Land as soon as possible. The battery can supply electrical power for at least 30 minutes. NOTE GARMIN G950 IFDS – SMP FOR DIGITAL CONFIGURATION Page SSMP3-9 Section 3 – Emergency procedures AIRPLANE ALERTS Ed.4, Rev.0 2.3 BOTH ALTERNATORS OVERVOLTAGE Annunciation window Alert window L BUS VOLT HIGH Lh overvoltage R BUS VOLT HIGH Rh overvoltage In event of both L and R BUS VOLT HIGH warning alerts displayed: 1. FIELD LH and RH BOTH OFF 2. LH and RH AUX FIELD switch BOTH OFF 3. FIELD LH and RH BOTH ON (one at a time) if LH (or RH) OVERVOLT warning stays displayed 1. FIELD LH (or RH) OFF if both LH and RH OVERVOLT warning stay displayed 1. CROSS BUS LH and RH BOTH OFF 2. FIELD LH and RH BOTH OFF 3. FIELD LH and RH BOTH ON (one at a time) If LH (or RH) OVERVOLT warningt stays displayed 1. FIELD LH (or RH) OFF 2. CROSS BUS LH (or RH) ON If both LH and RH OVERVOLT warning stay displayed 1. FIELD LH and RH BOTH OFF 2. CROSS BUS LH and RH BOTH OFF If engine starting battery modification is applied 1. EMERG BATT switch ON 2. Land as soon as possible. If engine starting battery modification is not applied 1. Land as soon as possible. The battery can supply electrical power for at least 30 minutes. NOTE GARMIN G950 IFDS – SMP FOR DIGITAL CONFIGURATION Page SSMP3-21 Section 3 – Emergency procedures ENGINE SECURING Ed.4, Rev.0 3. ENGINE SECURING Following procedure is applicable to shut-down one engine in flight: 1. Throttle Lever IDLE 2. Ignition BOTH OFF 3. Propeller Lever FEATHER 4. Fuel Selector OFF 5. Electrical fuel pump OFF 6. LH and RH AUX FIELD switch BOTH OFF If necessary, this procedure is applicable to both engines. When both engines are secured, both CROSS BUS switches must be set to OFF. After securing engine(s), after analysing situation, refer immediately to following procedures: ENGINE FAILURE IN FLIGHT: see Para. 6.5 SINGLE GENERATOR FAILURE: see Para. 2.1 or BOTH GENERATOR FAILURE: see Para. 2.2 INFLIGHT ENGINE RESTART: see Para. 6.2 ONE ENGINE INOPERATIVE LANDING: see Para. 6.6 or LANDING WITHOUT ENGINE POWER: see Para. 10.1 NOTE GARMIN G950 IFDS – SMP FOR DIGITAL CONFIGURATION Page SSMP3-29 Ed.4, Rev.0 Section 3 – Emergency procedures OTHER EMERGENCIES 5. OTHER EMERGENCIES 5.1 EMERGENCY DESCENT CAUTION Descent with airspeed at VLE, idle power and gear down will provide high descent rates and pitch attitudes up to -15°. Anticipate altitude capture and return to level flight during emergency descent in order to assure a safe and smooth recov- ery from maneuver. 1. Power levers IDLE 2. Flaps UP 3. IAS below VLO/VLE 4. Landing gear DOWN 5. Airspeed Up to VLE 5.2 TOTAL ELECTRICAL FAILURE In case of electrical system overall failure, apply following procedure: 1. Emergency light ON 2. Standby attitude indicator switch ON 3. MASTER SWITCH OFF 4. FIELD LH and RH BOTH OFF 5. LH and RH AUX FIELD switch BOTH OFF 6. MASTER SWITCH ON 7. FIELD LH and RH BOTH ON If failure persists 9. EMERG BATT switch ON (if engine starting battery installed) 10. Land as soon as possible applying emergency landing gear extension procedure (see Para. 7.1) WARNING An electrical system overall failure prevents flaps operation: landing distance without flaps increases of about 25%. CAUTION A fully charged battery can supply electrical power for at least 30 minutes. GARMIN G950 IFDS – SMP FOR DIGITAL CONFIGURATION Page SSMP3-36 Ed.4, Rev.0 Section 3 – Emergency procedures ONE ENGINE INOPERTIVE PROCEDURES 6.2 INFLIGHT ENGINE RESTART WARNING After: - mechanical engine seizure; - fire; - major propeller damage engine restart is not recommended. 1. Carburettor heat ON if required 2. Electrical fuel pump ON 3. Fuel quantity indicator CHECK 4. Fuel Selector CHECK (Crossfeed if required) 5. FIELD OFF 6. LH and RH AUX FIELD switch BOTH OFF 7. Ignition BOTH ON 8. Operating engine Throttle Lever SET as practical 9. Stopped engine Throttle Lever IDLE 10. Stopped engine Propeller Lever FULL FORWARD 11. Start push-button PUSH 12. Propeller Lever SET at desired rpm 13. FIELD ON (check for positive ammeter) 14. Engine throttle levers SET as required If engine restart is unsuccessful 15. EMERG BATT switch ON (if starting battery installed) 16. Repeat engine restart procedure CAUTION After engine restart, if practical, moderate propeller rpm and throttle increase to allow OIL and CHT/CT temperatures for stabilizing in the green arcs. If the fuel quantity in the tank which feeds the stopped engine is low, select the opposite side fuel tank by means of the fuel selector. If engine restart is still unsuccessful: 17. Affected engine SECURE (see engine securing procedure Para. 3) 18. Land as soon as possible applying one engine inoperative landing procedure. See Para. 6.6 NOTE GARMIN G950 IFDS – SMP FOR DIGITAL CONFIGURATION Page SSMP3-37 Ed.4, Rev.0 Section 3 – Emergency procedures ONE ENGINE INOPERTIVE PROCEDURES 6.3 ENGINE FAILURE DURING TAKEOFF RUN BEFORE ROTATION: ABORT TAKE OFF 1. Throttle Lever BOTH IDLE 2. Rudder Keep heading control 3. Brakes As required When safely stopped: 4. Failed Engine Ignition BOTH OFF 5. Failed Engine Field OFF 6. LH and RH AUX FIELD switch BOTH OFF 7. Failed Engine Electrical fuel pump OFF IF THE DECISION IS TAKEN TO CONTINUE THE TAKEOFF: WARNING A take-off abort should always be preferred if a safe stop can be per- formed on ground. A suggested “GO-NO-GO” criteria is: abort take-off until LG is still down and locked. Once airborne accelerate to Blue Line Speed (VYSE) before command- ing LG retraction. Take-off planning should take into account that high density altitude and aircraft mass may result in OEI negative climb rate. VYSE with flap up shall be flown in order to achieve best possible rate of climb after landing gear retraction and engine feathering. 1. Operating engine Throttle Lever FULL POWER 2. Operating engine Propeller Lever FULL FORWARD 3. Heading Keep control using rudder and ailerons 4. Attitude Reduce as appropriate to keep airspeed over 62 KIAS 5. Inoperative engine Propeller Lever FEATHER 6. Landing gear control lever UP 7. Airspeed VXSE/VYSE as required 8. Flaps 0° 9. LH and RH AUX FIELD switch BOTH OFF GARMIN G950 IFDS – SMP FOR DIGITAL CONFIGURATION Page SSMP3-39 Ed.4, Rev.0 Section 3 – Emergency procedures ONE ENGINE INOPERTIVE PROCEDURES 6.4 ENGINE FAILURE DURING CLIMB 1. Autopilot OFF 2. Heading Keep control using rudder and ailerons 3. Attitude Reduce as appropriate to keep airspeed over 62 KIAS 4. Operating engine Throttle Lever FULL THROTTLE 5. Operating engine Propeller Lever FULL FORWARD 6. Operative engine Electrical fuel pump Check ON 7. LH and RH AUX FIELD switch BOTH OFF 8. Inoperative engine Propeller Lever FEATHER 9. Inoperative engine Confirm and SECURE If engine restart is possible: 10. Apply INFLIGHT ENGINE RESTART procedure see Para 6.2 If engine restart is unsuccessful or it is not recommended: 11. Land as soon as possible 12. One engine inoperative landing procedure. see Para. 6.6 WARNING Following a mechanical engine seizure, fire or a major propeller dam- age engine restart is not recommended. WARNING Continuation of flight to a safe landing runway must be planned taking into account maximum operating ceiling in OEI condition. Refer to Section 5 Para 1, “One-engine rate of climb”. GARMIN G950 IFDS – SMP FOR DIGITAL CONFIGURATION Page SSMP3-40 Ed.4, Rev.0 Section 3 – Emergency procedures ONE ENGINE INOPERTIVE PROCEDURES 6.5 ENGINE FAILURE IN FLIGHT 1. Autopilot OFF 2. Heading Keep control using rudder and ailerons 3. Attitude Adjust as appropriate to keep airspeed over 62 KIAS 4. LH and RH AUX FIELD switch BOTH OFF 5. Operating engine Monitor engine instruments 6. Operative engine Electrical fuel pump Check ON 7. Operating engine Fuel Selector Check correct feeding (crossfeed if needed) If engine restart is possible: 8. Apply INFLIGHT ENGINE RESTART procedure see Para 6.2 If engine restart is unsuccessful or it is not recommended: 9. Land as soon as possible 10. One engine inoperative landing procedure. see Para. 6.6 WARNING Following a mechanical engine seizure, fire or a major propeller dam- age engine restart is not recommended. WARNING Continuation of flight to a safe landing runway must be planned taking into account maximum operating ceiling in OEI condition. Refer to Section 5 Para 12. Rate of climb with One Engine Inoperative.