MODEL 680 680-0001 AND ON HIGH ALTITUDE TAKEOFF AND LANDING (ABOVE 14,000 FEET PRESSURE ALTITUDE) COPYRIGHT 2010 CESSNA AIRCRAFT COMPANY WICHITA, KANSAS, USA 15 SEPTEMBER 2010 S28-1
SECTION V - SUPPLEMENTS HIGH ALTITUDE TAKEOFF AND LANDING (ABOVE 14,000 FEET PRESSURE ALTITUDE) MODEL 680 Use the Log of Effective Pages to determine the current status of this supplement. Pages affected by the current revision are indicated by an asterisk (*) preceding the page number. Supplement Status Date Original 15 September 2010 LOG OF EFFECTIVE PAGES Page Number Page Status Revision Number Configuration Code S28-1 thru S28-134 Original 0 S28-AA S28-2 Configuration S28-AA
MODEL 680 SERVICE BULLETIN CONFIGURATION LIST SECTION V - SUPPLEMENTS The following is a list of Service Bulletins that are applicable to the operation of the airplane, and have been incorporated into this supplement. This list contains only those Service Bulletins that are currently active. Number Title Airplane Serial Effectivity Revision Incorporated Incorporated in Airplane Configuration S28-AA S28-3
SECTION V - SUPPLEMENTS AIRPLANE CONFIGURATION CODES MODEL 680 The following is a list of airplane configuration codes that appear at the bottom of each page of this supplement to the basic FAA Approved Airplane Flight Manual, and indicate page effectivity by serial number. This list contains only the configurations that have been incorporated into this supplement. Configuration Code S28-AA Effectivity by Serial Number Airplanes 680-0297 and On Equipped with 15,000 Feet High Altitude Airfield Modification Option. Applicable Configuration Code S28-4 Configuration S28-AA
MODEL 680 INTRODUCTION SECTION V - SUPPLEMENTS This supplement is part of, and must be placed in, the basic FAA Approved Airplane Flight Manual (AFM) for airplanes incorporating the 15,000 feet high altitude airfield modification option. The information contained herein supplements the information of the basic FAA Approved AFM and is applicable to operations at airport field elevations above 14,000 feet up to 15,000 feet. For limitations, procedures, and performance information not contained in this supplement, consult the basic FAA Approved AFM. OPERATING LIMITATIONS TAKEOFF AND LANDING OPERATIONAL LIMITS Maximum Altitude Limit................................................ 15,000 Feet TAKEOFF/LANDING/ENROUTE TEMPERATURE LIMITS Figure S28-1 Configuration S28-AA S28-5
SECTION V - SUPPLEMENTS OPERATING PROCEDURES MODEL 680 The Operating Procedures remain the same as those shown in the basic FAA Approved Airplane Flight Manual except as follows: Cyan Message Procedures 5 CABIN ALTITUDE This message indicates the cabin altitude is above 8000 feet and the pressurization controller is set for the high elevation airfield mode (landing field elevation above 8000 feet). This message will be amber if the cabin altitude is above 9650 feet for more than 30 minutes. This message will be red if the cabin altitude is above 14,500 feet while operating in the high elevation airfield mode or 15,750 feet while operating in the >14K mode. NOTE If the cabin altitude exceeds 12,000 feet while operating in the high elevation airfield mode, it is recommended that at least one pilot don an oxygen mask. Amber Message Procedures 1 CABIN ALTITUDE This message is displayed when the cabin altitude exceeds 8500 feet due to failure of the pressurization system. This message is also displayed when the pressurization system is operating in high elevation airfield or >14K modes and (1) the cabin altitude exceeds 9650 feet for more than 30 minutes or (2) the cabin altitude exceeds 8500 feet and the airplane is above 24,500 feet MSL. The procedure in the basic AFM is unchanged. Red Message Procedures 2 CABIN ALTITUDE This message is displayed when the cabin altitude exceeds 10,000 feet in normal mode, 14,500 feet in high elevation airfield mode, or 15,750 feet in >14K mode. The procedure in the basic AFM is unchanged. S28-6 Configuration S28-AA
MODEL 680 Emergency/Abnormal Procedures SECTION V - SUPPLEMENTS 2 Maximum Glide/Emergency Landing When landing at a field elevation above 14,000 feet, modify the landing distance factor for flaps 15 in the basic AFM as follows: b. Landing Distance - Flaps 15........................ Multiply FLAPS 35 by 1.91 1 Dual Engine Flameout - Low Altitude When landing at a field elevation above 14,000 feet, modify the landing distance factor for flaps 15 in the basic AFM as follows: b. Landing Distance - Flaps 15...................... Multiply FLAPS 35 by 1.91 Normal Procedures Replace the following items. Expanded details are provided in the Expanded Preflight Procedures section of the basic FAA Approved AFM for items specified with an asterisk (*). Before Taxi For takeoff from an airport with a field elevation above 14,000 feet 1. AVN Buttons (both) (if not already ON)........................................... ON a. MCDU2 (if required)................................... Initialize Present Position b. ATIS/Clearance/FMS............................................. As Required 2. COCKPIT SPEAKERS Button (either)............... ON, or MUTE if headsets are to be used 3. Avionics Cooling Fans........................................... Check For Airflow 4. Gust Lock............................................................ Released 5. Flight Controls/Nosewheel Steering Disconnect................... Free and Correct/Check 6. Speedbrakes......................................................... Check/0% 7. Hydraulic Pressure and Volume............................................. Check 8. Flaps........................................................... Set for Takeoff 9. Attitude and Heading Displays...................................... Aligned/No Flags 10. Flight Instruments........................................................ Check 11. EICAS.................................. Check, all messages either normal or resolved 12. V Speeds............................................................ Set/Verify 13. Anti-Ice Systems.................................................... As Required a. Maintain a minimum of 65% N2 on both engines if bleed air anti-ice is selected on for more than 30 seconds. 14. Bleed Air System..................................................... Check/Set* 15. Environmental Controls............................................... As Required 16. Pressurization Controller.......................................... Set to 14,000 Feet 17. Pressurization Controller R Knob............................. Approximately 3 O'clock 18. ARPT ELEV Button........................................................ >14K 19. Aft Divider Doors................................................... Latched Open (Continued Next Page) Configuration S28-AA S28-7
SECTION V - SUPPLEMENTS MODEL 680 Normal Procedures (Continued) After Takeoff/Climb For climb after takeoff from an airport with a field elevation above 14,000 feet. 1. Landing Gear.............................................................. UP 2. Flaps................................. 0 (V 2 +10 knots and at or above 400 feet AGL) 3. Throttles............................................................ MCT Detent 4. Yaw Damper........................................................ As Desired 5. Autopilot (above 400 feet AGL).......................................... As Desired 6. Pressurization........................................................... Check 7. SEAT BELTS and PAX SAFETY Buttons.................................. As Required 8. Anti-Ice............................................................ As Required 9. Altimeters/RECOG Button (at transition altitude)................................ Set/OFF 10. ARPT ELEV Button (after climbing above FL245)................................ NORM 11. Pressurization Controller R Knob......................................... As Desired 12. Pressurization Controller............................... Set to Landing Field Elevation 13. APU (prior to climb above FL300).............................................. OFF (refer to Normal Procedures, APU Shutdown, in the basic FAA Approved AFM) Descent For descent to landing at an airport with a field elevation above 14,000 feet. 1. Pressurization Controller..................... Set Landing Field Elevation to 14,000 Feet 2. Pressurization Controller R Knob................. Dot Aligned With Arrow (or greater rate) 3. Anti-Ice............................................................ As Required a. The anti-ice system must be selected on at least one minute prior to an idle descent into an icing environment. 4. ARPT ELEV Button (after descending below FL245 and before reaching FL200)......................... >14K a. If the cabin altitude exceeds 12,000 feet while operating in high elevation airfield mode, it is recommended that at least one pilot don an oxygen mask. b. Use of barometric altitude corrected to the landing field elevation (QFE operations) is not approved for landing at an airport with a field elevation above 14,000 feet. 5. APU (below FL200)........................................ TEST/START as desired, refer to Normal Procedures, APU Ground or In-Flight Start (At or Below FL200) in the basic FAA Approved AFM 6. Altimeters/RECOG Buttons (at transition flight level).............................. Set/ON Approach For approach to landing at an airport with a field elevation above 14,000 feet. 1. Pressurization.............................. 0.5 PSI or Less Differential at touchdown CAUTION When landing at an airport with a field elevation above 14,000 feet, when the airplane has not climbed above 24,500 feet MSL during the flight, the airplane may descend faster than the pressurization auto-schedule can climb the cabin to 14,000 feet. To avoid landing with a cabin differential pressure greater than 0.5 psi, it may be necessary to slow the airplane descent rate and/or increase the pressurization controller R knob setting to ensure the cabin reaches 14,000 feet prior to landing. (Continued Next Page) S28-8 Configuration S28-AA
MODEL 680 SECTION V - SUPPLEMENTS Normal Procedures (Continued) All Engine Go-Around For a go-around from an attempted landing at an airport with a field elevation above 14,000 feet. NOTE The amber CABIN ALTITUDE message may be briefly displayed if the airplane climbs above FL245 before the cabin altitude can descend to below 8,000 feet. The message will clear as the cabin descends. After Landing After landing at an airport with a field elevation above 14,000 feet. 1. Thrust Reversers.......................................................... Stow 2. Speedbrakes............................................................... 0% 3. Flaps.............................................................. As Desired 4. Anti-Ice Switches........................................................ Confirm a. PITOT/STATIC Buttons (both)............................................. OFF b. ENGINE/STAB Buttons (both)...................................... As Required c. WING Buttons (both).................................................... OFF 5. Exterior Lights...................................................... As Required 6. Stabilizer Position.................................................... Set to -6.9 7. APU..................................................... TEST/START as desired (refer to APU Ground or In-Flight Start (At or Below FL200) in the basic FAA Approved AFM) WARNING Operation with engine bleed air and/or APU bleed air on with the cabin door closed will result in a slight positive pressure in the airplane. To avoid potential injury to persons or damage to the cabin door, engine and APU bleed air should be turned off or a cockpit side window opened prior to opening the cabin door. 8. BUS TIE Button (if only one generator)...................................... CLOSED 9. ENG BLD AIR Selectors (both)................................................ OFF 10. APU BLEED AIR Button..................................................... OFF Configuration S28-AA S28-9
SECTION V - SUPPLEMENTS MODEL 680 OPERATING INFORMATION Operations To/From Airfields From 14,000 Feet to 15,000 Feet Airfield Elevation The maximum altitude limit for takeoffs and landings is an airport field elevation of 15,000 feet when the airplane is equipped with the 15,000 feet high elevation airfield modification option. The cabin altitude selector is marked with an amber arc from 8000 feet to 14,000 feet designating that special procedures are required for operation to or from high elevation airports. Additionally, an ARPT ELEV button is provided to allow the pilot to configure the pressurization system, cabin altitude alerts, and passenger oxygen system for operations to or from airfields above 14,000 feet elevation up to a maximum of 15,000 feet. When the airplane is operated to or from airfields above 14,000 feet, the cabin altitude selector is set to 14,000 feet and the ARPT ELEV button is selected to >14K. For takeoff from airfields above 14,000 feet, the Pressurization Controller R knob is rotated to approximately the 3 o clock position to ensure the cabin can descend at a rate sufficient to ensure reaching a maximum cabin altitude of 8000 feet prior to climbing above 24,500 feet MSL. The ARPT ELEV button will illuminate amber >14K when this mode is selected. When the airplane is operated in this region the amber CABIN ALTITUDE message will activate if the cabin altitude exceeds 9650 feet for more than 30 minutes and the red CABIN ALTITUDE message is reset to 15,750 feet. Activation of emergency pressurization and deployment of passenger oxygen masks is also reset to 15,750 feet. Additional logic is included in the system to prevent automatic passenger oxygen mask deployment when either left or right main gear is on the ground and the ARPT ELEV button is selected to >14K. Activation of the CABIN DUMP button or selection of the CABIN PRESS MODE AUTO/MANUAL button to MANUAL will allow the cabin to rise to a maximum pressure altitude of 15,300 feet. The following is a summary of operating procedures using the >14K mode: CONDITIONS: PROCEDURE: PRESSURIZATION SYSTEM WILL: Takeoff from field Select normal auto schedule mode. After takeoff, maintain cabin altitude elevation <8000 feet Select pressurization controller to 14,000 per auto schedule. to airport above feet landing altitude. 14,000 feet. Select ARPT ELEV button to >14K after descending below FL245 and before reaching FL200. Climb cabin to 8000 feet after 10 minutes at level cruise and remain there until the airplane descends below FL245. Climb cabin to 14,000 feet when the airplane has descended below FL245. After landing, climb the cabin to field pressure altitude and after 60 seconds opens both outflow valves completely. (Continued Next Page) S28-10 Configuration S28-AA
MODEL 680 SECTION V - SUPPLEMENTS OPERATING INFORMATION (Continued) CONDITIONS: PROCEDURE: PRESSURIZATION SYSTEM WILL: Takeoff from field elevation >14,000 feet to airport above 14,000 feet, flight below 24,500 feet MSL. Takeoff from field elevation >14,000 feet to airport above 14,000 feet, longer distance flight above 24,500 feet MSL. Takeoff from field elevation >14,000 feet to airport > 8,000 but < 14,000 feet, flight below 24,500 feet MSL. Select normal auto schedule mode. Select pressurization controller to 14,000 feet. Select ARPT ELEV button to >14K. Set pressurization controller R knob to approximately the 3 o clock position. Select normal auto schedule mode. Select pressurization controller to 14,000 feet landing altitude. Select ARPT ELEV button to >14K. Set pressurization controller R knob to approximately the 3 o clock position. After climbing above FL245 select ARPT ELEV button to NORM. After reaching cruise altitude, set pressurization controller R knob as desired. During descent, align dot on R knob with arrow (or greater rate). When descending below FL245 and before reaching FL200, select ARPT ELEV button to >14K. Select normal auto schedule mode. Select pressurization controller to 14,000 feet. Select ARPT ELEV button to >14K. Set pressurization controller R knob to approximately the 3 o clock position. After reaching cruise altitude, select ARPT ELEV button to NORM. After reaching cruise altitude, set pressurization controller to landing field elevation. After takeoff, descend cabin to 8000 feet. Maintain cabin at 8000 feet until airplane descends 1000 feet below cruise altitude. Climb cabin to 14,000 feet when the airplane has descended 1000 feet below cruise altitude. After landing, climb cabin to field pressure altitude and after 60 seconds opens both outflow valves completely. After takeoff, descend cabin altitude at a rate sufficient to reach 8000 feet prior to climbing above FL245. Maintain cabin altitude at 8000 feet until descending below FL245. Climb cabin to 14,000 feet when the airplane has descended below FL245. After landing, climb the cabin to field pressure altitude and after 60 seconds opens both outflow valves completely. After takeoff, descend cabin to 8000 feet. Maintain cabin at 8000 feet until airplane descends 1000 feet below cruise altitude. Climb cabin to the selected elevation when the airplane has descended 1000 feet below cruise altitude. Takeoff from field elevation >14,000 feet to airport below 8,000 feet. Select normal auto schedule mode. Select pressurization controller to 14,000 feet. Select ARPT ELEV button to >14K. Set pressurization controller R knob to approximately the 3 o clock position. After climbing above FL245, select ARPT ELEV button to NORM. After reaching cruise altitude, set pressurization controller R knob as desired. After reaching cruise altitude, set pressurization controller to landing field elevation. After takeoff, descend cabin altitude at a rate sufficient to reach 8000 feet prior to climbing above FL245. Transition to the cabin altitude auto schedule. Configuration S28-AA S28-11
SECTION V - SUPPLEMENTS MODEL 680 OPERATING INFORMATION (Continued) NOTE The cyan CABIN ALTITUDE message will be displayed when the >14K airfield mode is selected and the cabin altitude is above 8000 feet. The amber CABIN ALTITUDE message will be displayed when the >14K airfield mode is selected and the cabin altitude has been above 9650 feet for more than 30 minutes or the cabin altitude is above 8500 feet with the airplane above 24,500 feet MSL. When displayed, at least one pilot should don an oxygen mask and use oxygen. If the ARPT ELEV button is selected to >14K, and 14,000 feet is selected on the cabin altitude controller, then the cabin will begin climbing up to 14,000 feet upon descent below 24,500 feet MSL. If the airplane subsequently returns to an altitude above 24,500 feet, the cabin will begin descending back down to 8000 feet. If the airplane reaches 24,500 feet while the cabin altitude is high, the amber or red CABIN ALTITUDE message will illuminate. When taking off from airfield above 14,000 feet field elevation, the cabin will begin to descend just after takeoff so as to reach a cabin altitude of 8000 feet or less prior to climbing above 24,500 feet MSL. If the airplane is to hold above 12,000 feet MSL, cabin altitude must be selected at or below 12,000 feet until holding is completed; otherwise at least one pilot should wear an oxygen mask and use oxygen. Engine Start During engine starts at high elevation airports (generally above 8000 feet), ITT may reach a temperature where the FADEC will schedule fuel flow to prevent exceeding an ITT limit. This will appear to the pilot as a cycling in the ITT display and corresponding aural engine indications. This is normal and acceptable provided N2 continues to increase. S28-12 Configuration S28-AA
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SECTION V - SUPPLEMENTS PERFORMANCE STANDARD CHARTS TAKEOFF/GO-AROUND THRUST SETTINGS ANTI-ICE - OFF MODEL 680 A81544 105 103 ENGINE FAN SPEED (N1) - % RPM 101 99 97 95 93 91 10,000 FEET 12,000 FEET TO 16,000 FEET 8000 FEET 6000 FEET 4000 FEET 2000 FEET SEA LEVEL 12,000 FEET 14,000 FEET TO 16,000 FEET 89 87 85 83-60 -50-40 -30-20 -10 0 10 20 30 40 50 60 STATIC AIR TEMPERATURE C Figure S28-2 (Sheet 1 of 2) -00 S28-14 Configuration S28-AA
MODEL 680 TAKEOFF/GO-AROUND THRUST SETTINGS ANTI-ICE - ON SECTION V - SUPPLEMENTS A81543 103 12,000 FEET 14,000 FEET TO 16,000 FEET 101 99 97 10,000 FEET 12,000 FEET TO 16,000 FEET 8000 FEET 6000 FEET ENGINE FAN SPEED (N1) - % RPM 95 93 91 4000 FEET 2000 FEET SEA LEVEL 89 87 85 83-60 -50-40 -30-20 -10 0 10 20 STATIC AIR TEMPERATURE C Figure S28-2 (Sheet 2) -00 Configuration S28-AA S28-15
SECTION V - SUPPLEMENTS TAKEOFF MODEL 680 PROCEDURES FOR USE OF TAKEOFF PERFORMANCE TABLES 1. Determine gross weight of airplane for type of loading desired. 2. Obtain airport information; i.e., active runway, available runway length and condition (wet or dry), temperature, altitude, wind, icing conditions, runway gradient (if applicable) and obstacles in the takeoff flight path. Determine that the temperature is within the ambient temperature limits found in Section II, Operating Limitations. 3. Determine wind component parallel to active runway from the crosswind component chart in Section IV, Performance, Standard Charts, in the basic FAA Approved AFM. 4. Check the maximum allowable weight permitted by climb requirements (Figures S28-3 and S28-4). If this limitation restricts the gross weight, the pilot must off-load weight until the requirement is met. 5. For takeoff from a dry runway, using the calculated takeoff gross weight from step 4, determine the takeoff field length, V 1, V R, V 2, and V ENR from the following figures. If the runway has a gradient, the takeoff field length and V 1 must be adjusted in accordance with the takeoff corrections from the corresponding figures: RUNWAY GRADIENT LEVEL RUNWAY ADJUSTMENT Flaps 7, Anti-Ice - OFF Figure S28-6 Figure S28-5 Flaps 7, Anti-Ice - ON Figure S28-8 Figure S28-7 Flaps 15, Anti-Ice - OFF Figure S28-10 Figure S28-9 Flaps 15, Anti-Ice - ON Figure S28-12 Figure S28-11 6. For takeoff from a wet runway, using the calculated takeoff gross weight from step 4, determine the wet runway or wet runway with thrust reverser(s) takeoff field length, V 1, V R, V 2, and V ENR from the following figures. If the runway has a gradient, the takeoff field length and V 1 must be adjusted in accordance with the takeoff corrections from the corresponding figures: NOTE Takeoff (With Reversers) Field Length for wet runways uses performance credit for reverse thrust. RUNWAY GRADIENT LEVEL RUNWAY ADJUSTMENT Flaps 7, Anti-Ice - OFF, with reversers(s) Figure S28-14 Figure S28-13 Flaps 7, Anti-Ice - ON, with reversers(s) Figure S28-16 Figure S28-15 Flaps 15, Anti-Ice - OFF Figure S28-18 Figure S28-17 Flaps 15, Anti-Ice - ON Figure S28-20 Figure S28-19 Flaps 15, Anti-Ice - OFF, with reversers(s) Figure S28-22 Figure S28-21 Flaps 15, Anti-Ice - ON, with reversers(s) Figure S28-24 Figure S28-23 Determine the dry runway takeoff field length as described in step 5 above. The required takeoff field length from a wet runway or wet runway with reverser(s) is the longer of the wet runway or wet runway with reverser(s) and the dry takeoff field lengths determined above. The takeoff speeds V 1, V R, V 2, and V ENR are the takeoff speeds associated with the wet runway or wet runway with reverser(s) figures. (Continued Next Page) S28-16 Configuration S28-AA
MODEL 680 SECTION V - SUPPLEMENTS PROCEDURES FOR USE OF TAKEOFF PERFORMANCE TABLES (Continued) NOTE For takeoffs with anti-ice fluid applied, refer to Section VII in the basic FAA Approved AFM. Takeoff with Type II, III, or IV anti-ice fluid applied is limited to the flaps 7 configuration. 7. If available runway length is less than the required takeoff field length, the airplane weight must be adjusted until this requirement can be met. 8. Determine level off altitude. Level off altitude is airport barometric altitude plus takeoff climb increment (Figure S28-27, S28-28, S28-31 or S28-32) required for obstacle clearance. 9. If the obstacle clearance is a factor, the single-engine takeoff flight path charts (Figures S28-25, S28-27, or S28-28 and S28-29, S28-31 or S28-32) must be used to determine if the net takeoff flight path provides the required obstacle clearance. If the required obstacle clearance is not achieved, the gross weight must be adjusted until the net takeoff flight path assures the required obstacle clearance. NOTE If the takeoff flight path has not been completed within ten (10) minutes, reduce power to maximum continuous thrust and continue with the takeoff flight path. 10. For second segment (Figure S28-37, S28-38, S28-39 or S28-40) and enroute (Figure 4-460-1 or 4-461-1 in the AFM) turning climb, up to and including a 15 bank angle, if the takeoff weight is 29,275 pounds or less, multiply the takeoff weight by 1.035 to obtain an adjusted weight. Enter the appropriate second segment or enroute climb table at the adjusted weight to find the actual climb performance of the airplane in the bank. If the takeoff weight is greater than 29,275 pounds, reduce the net climb gradient by 1.0. 11. The first segment takeoff net climb gradient tables are presented in Figures S28-33, S28-34, S28-35 and S28-36. EXAMPLE FOR FLAPS 15 WET RUNWAY: Ambient Temperature = 5 C Pressure Altitude = 14,000 FEET Gross Weight = 27,000 POUNDS Wind = 0 KNOTS (calm) Runway Gradient = ZERO (level) Anti-Ice - OFF From Figure S28-18, the wet runway Takeoff Field Length is 6970 FEET. V 1 is 95 KIAS V R is 104 KIAS V 2 is 107 KIAS V ENR is 180 KIAS From Figure S28-10, the dry runway Takeoff Field Length is 6510 FEET. Therefore, the Takeoff Field Length = 6970 FEET. Configuration S28-AA S28-17
SECTION V - SUPPLEMENTS MODEL 680 Figure S28-3 S28-18 Configuration S28-AA
MODEL 680 SECTION V - SUPPLEMENTS Figure S28-4 Configuration S28-AA S28-19
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MODEL 680 TAKEOFF FIELD LENGTH - FEET, WITH FLAPS 7 (DRY RUNWAY OVER A 35 FOOT SCREEN HEIGHT) (ANTI-ICE - OFF) SECTION V - SUPPLEMENTS Determine takeoff field length, V 1, V R, V 2 and V ENR from Figure S28-6. If the runway has a gradient, adjust V 1 and takeoff field length using Figure S28-5. If the required distance is greater than the available distance, the airplane weight must be reduced until distance required is less than or equal to distance available. Figure S28-5 Configuration S28-AA S28-21
SECTION V - SUPPLEMENTS MODEL 680 Figure S28-6 (Sheet 1 of 4) S28-22 Configuration S28-AA
MODEL 680 SECTION V - SUPPLEMENTS Figure S28-6 (Sheet 2) Configuration S28-AA S28-23
SECTION V - SUPPLEMENTS MODEL 680 Figure S28-6 (Sheet 3) S28-24 Configuration S28-AA
MODEL 680 SECTION V - SUPPLEMENTS Figure S28-6 (Sheet 4) Configuration S28-AA S28-25
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MODEL 680 TAKEOFF FIELD LENGTH - FEET, WITH FLAPS 7 (DRY RUNWAY OVER A 35 FOOT SCREEN HEIGHT) (ANTI-ICE - ON) SECTION V - SUPPLEMENTS Determine takeoff field length, V 1, V R, V 2 and V ENR from Figure S28-8. If the runway has a gradient, adjust V 1 and takeoff field length using Figure S28-7. If the required distance is greater than the available distance, the airplane weight must be reduced until distance required is less than or equal to distance available. Figure S28-7 Configuration S28-AA S28-27
SECTION V - SUPPLEMENTS MODEL 680 Figure S28-8 (Sheet 1 of 2) S28-28 Configuration S28-AA
MODEL 680 SECTION V - SUPPLEMENTS Figure S28-8 (Sheet 2) Configuration S28-AA S28-29
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MODEL 680 SECTION V - SUPPLEMENTS TAKEOFF FIELD LENGTH - FEET, WITH FLAPS 15 (DRY RUNWAY OVER A 35 FOOT SCREEN HEIGHT) (ANTI-ICE - OFF) Determine takeoff field length, V 1, V R, V 2 and V ENR from Figure S28-10. If the runway has a gradient, adjust V 1 and takeoff field length using Figure S28-9. If the required distance is greater than the available distance, the airplane weight must be reduced until distance required is less than or equal to distance available. Figure S28-9 Configuration S28-AA S28-31
SECTION V - SUPPLEMENTS MODEL 680 Figure S28-10 (Sheet 1 of 4) S28-32 Configuration S28-AA
MODEL 680 SECTION V - SUPPLEMENTS Figure S28-10 (Sheet 2) Configuration S28-AA S28-33
SECTION V - SUPPLEMENTS MODEL 680 Figure S28-10 (Sheet 3) S28-34 Configuration S28-AA
MODEL 680 SECTION V - SUPPLEMENTS Figure S28-10 (Sheet 4) Configuration S28-AA S28-35
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MODEL 680 SECTION V - SUPPLEMENTS TAKEOFF FIELD LENGTH - FEET, WITH FLAPS 15 (DRY RUNWAY OVER A 35 FOOT SCREEN HEIGHT) (ANTI-ICE - ON) Determine takeoff field length, V 1, V R, V 2 and V ENR from Figure S28-12. If the runway has a gradient, adjust V 1 and takeoff field length using Figure S28-11. If the required distance is greater than the available distance, the airplane weight must be reduced until distance required is less than or equal to distance available. Figure S28-11 Configuration S28-AA S28-37
SECTION V - SUPPLEMENTS MODEL 680 Figure S28-12 (Sheet 1 of 2) S28-38 Configuration S28-AA
MODEL 680 SECTION V - SUPPLEMENTS Figure S28-12 (Sheet 2) Configuration S28-AA S28-39
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MODEL 680 SECTION V - SUPPLEMENTS TAKEOFF (WITH REVERSERS) FIELD LENGTH - FEET, WITH FLAPS 7 (WET RUNWAY OVER A 15 FOOT SCREEN HEIGHT) (ANTI-ICE - OFF) Determine takeoff field length, V 1, V R, V 2 and V ENR from Figure S28-14. If the runway has a gradient, adjust V 1 and takeoff field length using Figure S28-13. If the required distance is greater than the available distance, the airplane weight must be reduced until distance required is less than or equal to distance available. Figure S28-13 Configuration S28-AA S28-41
SECTION V - SUPPLEMENTS MODEL 680 Figure S28-14 (Sheet 1 of 4) S28-42 Configuration S28-AA
MODEL 680 SECTION V - SUPPLEMENTS Figure S28-14 (Sheet 2) Configuration S28-AA S28-43
SECTION V - SUPPLEMENTS MODEL 680 Figure S28-14 (Sheet 3) S28-44 Configuration S28-AA
MODEL 680 SECTION V - SUPPLEMENTS Figure S28-14 (Sheet 4) Configuration S28-AA S28-45
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MODEL 680 SECTION V - SUPPLEMENTS TAKEOFF (WITH REVERSERS) FIELD LENGTH - FEET, WITH FLAPS 7 (WET RUNWAY OVER A 15 FOOT SCREEN HEIGHT) (ANTI-ICE - ON) Determine takeoff field length, V 1, V R, V 2 and V ENR from Figure S28-16. If the runway has a gradient, adjust V 1 and takeoff field length using Figure S28-15. If the required distance is greater than the available distance, the airplane weight must be reduced until distance required is less than or equal to distance available. Figure S28-15 Configuration S28-AA S28-47
SECTION V - SUPPLEMENTS MODEL 680 Figure S28-16 (Sheet 1 of 2) S28-48 Configuration S28-AA
MODEL 680 SECTION V - SUPPLEMENTS Figure S28-16 (Sheet 2) Configuration S28-AA S28-49
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MODEL 680 SECTION V - SUPPLEMENTS TAKEOFF FIELD LENGTH - FEET, WITH FLAPS 15 (WET RUNWAY OVER A 15 FOOT SCREEN HEIGHT) (ANTI-ICE - OFF) Determine takeoff field length, V 1, V R, V 2 and V ENR from Figure S28-18. If the runway has a gradient, adjust V 1 and takeoff field length using Figure S28-17. If the required distance is greater than the available distance, the airplane weight must be reduced until distance required is less than or equal to distance available. Figure S28-17 Configuration S28-AA S28-51
SECTION V - SUPPLEMENTS MODEL 680 Figure S28-18 (Sheet 1 of 4) S28-52 Configuration S28-AA
MODEL 680 SECTION V - SUPPLEMENTS Figure S28-18 (Sheet 2) Configuration S28-AA S28-53
SECTION V - SUPPLEMENTS MODEL 680 Figure S28-18 (Sheet 3) S28-54 Configuration S28-AA
MODEL 680 SECTION V - SUPPLEMENTS Figure S28-18 (Sheet 4) Configuration S28-AA S28-55
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MODEL 680 SECTION V - SUPPLEMENTS TAKEOFF FIELD LENGTH - FEET, WITH FLAPS 15 (WET RUNWAY OVER A 15 FOOT SCREEN HEIGHT) (ANTI-ICE - ON) Determine takeoff field length, V 1, V R, V 2 and V ENR from Figure S28-20. If the runway has a gradient, adjust V 1 and takeoff field length using Figure S28-19. If the required distance is greater than the available distance, the airplane weight must be reduced until distance required is less than or equal to distance available. Figure S28-19 Configuration S28-AA S28-57
SECTION V - SUPPLEMENTS MODEL 680 Figure S28-20 (Sheet 1 of 2) S28-58 Configuration S28-AA
MODEL 680 SECTION V - SUPPLEMENTS Figure S28-20 (Sheet 2) Configuration S28-AA S28-59
SECTION V - SUPPLEMENTS MODEL 680 This Page Intentionally Left Blank S28-60 Configuration S28-AA
MODEL 680 SECTION V - SUPPLEMENTS TAKEOFF (WITH REVERSERS) FIELD LENGTH - FEET, WITH FLAPS 15 (WET RUNWAY OVER A 15 FOOT SCREEN HEIGHT) (ANTI-ICE - OFF) Determine takeoff field length, V 1, V R, V 2 and V ENR from Figure S28-22. If the runway has a gradient, adjust V 1 and takeoff field length using Figure S28-21. If the required distance is greater than the available distance, the airplane weight must be reduced until distance required is less than or equal to distance available. Figure S28-21 Configuration S28-AA S28-61
SECTION V - SUPPLEMENTS MODEL 680 Figure S28-22 (Sheet 1 of 4) S28-62 Configuration S28-AA
MODEL 680 SECTION V - SUPPLEMENTS Figure S28-22 (Sheet 2) Configuration S28-AA S28-63
SECTION V - SUPPLEMENTS MODEL 680 Figure S28-22 (Sheet 3) S28-64 Configuration S28-AA
MODEL 680 SECTION V - SUPPLEMENTS Figure S28-22 (Sheet 4) Configuration S28-AA S28-65
SECTION V - SUPPLEMENTS MODEL 680 This Page Intentionally Left Blank S28-66 Configuration S28-AA
MODEL 680 SECTION V - SUPPLEMENTS TAKEOFF (WITH REVERSERS) FIELD LENGTH - FEET, WITH FLAPS 15 (WET RUNWAY OVER A 15 FOOT SCREEN HEIGHT) (ANTI-ICE - ON) Determine takeoff field length, V 1, V R, V 2 and V ENR from Figure S28-24. If the runway has a gradient, adjust V 1 and takeoff field length using Figure S28-23. If the required distance is greater than the available distance, the airplane weight must be reduced until distance required is less than or equal to distance available. Figure S28-23 Configuration S28-AA S28-67
SECTION V - SUPPLEMENTS MODEL 680 Figure S28-24 (Sheet 1 of 2) S28-68 Configuration S28-AA
MODEL 680 SECTION V - SUPPLEMENTS Figure S28-24 (Sheet 2) Configuration S28-AA S28-69
SECTION V - SUPPLEMENTS MODEL 680 This Page Intentionally Left Blank S28-70 Configuration S28-AA
MODEL 680 CLIMB SINGLE-ENGINE TAKEOFF FLIGHT PATH - FLAPS 7 FIRST AND SECOND SEGMENTS SECTION V - SUPPLEMENTS Knowing weight, altitude, temperature, wind, obstacle height above runway surface and the obstacle distance from reference zero, at the airport pressure altitude plus the takeoff climb increment (TCI) from Figure S28-27 or S28-28, determine the available climb gradient from Figure S28-37 or S28-38. Using this climb gradient, the required horizontal distance can be determined from Figure S28-25. If this required horizontal distance is less than the horizontal distance to the obstacle, the takeoff weight determined by other limitations is satisfactory; otherwise, the weight must be reduced to correspond with the required horizontal distance. Configuration S28-AA S28-71
SECTION V - SUPPLEMENTS MODEL 680 Figure S28-25 S28-72 Configuration S28-AA
MODEL 680 SINGLE-ENGINE TAKEOFF FLIGHT PATH DISTANCES - FLAPS 7 SECTION V - SUPPLEMENTS The data presented in Figure S28-27 (Anti-Ice - OFF) and Figure S28-28 (Anti-Ice - ON) is for the purpose of determining the takeoff climb increment (TCI) and the horizontal distances along the net takeoff flight path. The net takeoff flight path is used to plan obstacle clearance. * TAKEOFF THRUST IS LIMITED TO TEN MINUTES MAXIMUM AND THEREAFTER TO MAXIMUM CONTINUOUS THRUST. Figure S28-26 Configuration S28-AA S28-73
SECTION V - SUPPLEMENTS MODEL 680 Figure S28-27 (Sheet 1 of 4) S28-74 Configuration S28-AA
MODEL 680 SECTION V - SUPPLEMENTS Figure S28-27 (Sheet 2) Configuration S28-AA S28-75
SECTION V - SUPPLEMENTS MODEL 680 Figure S28-27 (Sheet 3) S28-76 Configuration S28-AA
MODEL 680 SECTION V - SUPPLEMENTS Figure S28-27 (Sheet 4) Configuration S28-AA S28-77
SECTION V - SUPPLEMENTS MODEL 680 Figure S28-28 (Sheet 1 of 4) S28-78 Configuration S28-AA
MODEL 680 SECTION V - SUPPLEMENTS Figure S28-28 (Sheet 2) Configuration S28-AA S28-79
SECTION V - SUPPLEMENTS MODEL 680 Figure S28-28 (Sheet 3) S28-80 Configuration S28-AA
MODEL 680 SECTION V - SUPPLEMENTS Figure S28-28 (Sheet 4) Configuration S28-AA S28-81
SECTION V - SUPPLEMENTS MODEL 680 This Page Intentionally Left Blank S28-82 Configuration S28-AA
MODEL 680 SINGLE-ENGINE TAKEOFF FLIGHT PATH - FLAPS 15 FIRST AND SECOND SEGMENTS SECTION V - SUPPLEMENTS Knowing weight, altitude, temperature, wind, obstacle height above runway surface and the obstacle distance from reference zero, at the airport pressure altitude plus the takeoff climb increment (TCI) from Figure S28-31 or S28-32, determine the available climb gradient from Figure S28-39 or S28-40. Using this climb gradient, the required horizontal distance can be determined from Figure S28-29. If this required horizontal distance is less than the horizontal distance to the obstacle, the takeoff weight determined by other limitations is satisfactory; otherwise, the weight must be reduced to correspond with the required horizontal distance. Configuration S28-AA S28-83
SECTION V - SUPPLEMENTS MODEL 680 Figure S28-29 S28-84 Configuration S28-AA
MODEL 680 SINGLE-ENGINE TAKEOFF FLIGHT PATH DISTANCES - FLAPS 15 SECTION V - SUPPLEMENTS The data presented in Figure S28-31 (Anti-Ice - OFF) and Figure S28-32 (Anti-Ice - ON) is for the purpose of determining the takeoff climb increment (TCI) and the horizontal distances along the net takeoff flight path. The net takeoff flight path is used to plan obstacle clearance. * TAKEOFF THRUST IS LIMITED TO 10 MINUTES MAXIMUM AND THEREAFTER TO MAXIMUM CONTINUOUS THRUST. Figure S28-30 Configuration S28-AA S28-85
SECTION V - SUPPLEMENTS MODEL 680 Figure S28-31 (Sheet 1 of 4) S28-86 Configuration S28-AA
MODEL 680 SECTION V - SUPPLEMENTS Figure S28-31 (Sheet 2) Configuration S28-AA S28-87
SECTION V - SUPPLEMENTS MODEL 680 Figure S28-31 (Sheet 3) S28-88 Configuration S28-AA
MODEL 680 SECTION V - SUPPLEMENTS Figure S28-31 (Sheet 4) Configuration S28-AA S28-89
SECTION V - SUPPLEMENTS MODEL 680 Figure S28-32 (Sheet 1 of 4) S28-90 Configuration S28-AA
MODEL 680 SECTION V - SUPPLEMENTS Figure S28-32 (Sheet 2) Configuration S28-AA S28-91
SECTION V - SUPPLEMENTS MODEL 680 Figure S28-32 (Sheet 3) S28-92 Configuration S28-AA
MODEL 680 SECTION V - SUPPLEMENTS Figure S28-32 (Sheet 4) Configuration S28-AA S28-93
SECTION V - SUPPLEMENTS MODEL 680 Figure S28-33 (Sheet 1 of 2) S28-94 Configuration S28-AA
MODEL 680 SECTION V - SUPPLEMENTS Figure S28-33 (Sheet 2) Configuration S28-AA S28-95
SECTION V - SUPPLEMENTS MODEL 680 Figure S28-34 (Sheet 1 of 2) S28-96 Configuration S28-AA
MODEL 680 SECTION V - SUPPLEMENTS Figure S28-34 (Sheet 2) Configuration S28-AA S28-97
SECTION V - SUPPLEMENTS MODEL 680 Figure S28-35 (Sheet 1 of 2) S28-98 Configuration S28-AA
MODEL 680 SECTION V - SUPPLEMENTS Figure S28-35 (Sheet 2) Configuration S28-AA S28-99
SECTION V - SUPPLEMENTS MODEL 680 Figure S28-36 (Sheet 1 of 2) S28-100 Configuration S28-AA
MODEL 680 SECTION V - SUPPLEMENTS Figure S28-36 (Sheet 2) Configuration S28-AA S28-101
SECTION V - SUPPLEMENTS MODEL 680 Figure S28-37 (Sheet 1 of 4) S28-102 Configuration S28-AA
MODEL 680 SECTION V - SUPPLEMENTS Figure S28-37 (Sheet 2) Configuration S28-AA S28-103
SECTION V - SUPPLEMENTS MODEL 680 Figure S28-37 (Sheet 3) S28-104 Configuration S28-AA
MODEL 680 SECTION V - SUPPLEMENTS Figure S28-37 (Sheet 4) Configuration S28-AA S28-105
SECTION V - SUPPLEMENTS MODEL 680 Figure S28-38 (Sheet 1 of 4) S28-106 Configuration S28-AA
MODEL 680 SECTION V - SUPPLEMENTS Figure S28-38 (Sheet 2) Configuration S28-AA S28-107
SECTION V - SUPPLEMENTS MODEL 680 Figure S28-38 (Sheet 3) S28-108 Configuration S28-AA
MODEL 680 SECTION V - SUPPLEMENTS Figure S28-38 (Sheet 4) Configuration S28-AA S28-109
SECTION V - SUPPLEMENTS MODEL 680 Figure S28-39 (Sheet 1 of 4) S28-110 Configuration S28-AA
MODEL 680 SECTION V - SUPPLEMENTS Figure S28-39 (Sheet 2) Configuration S28-AA S28-111
SECTION V - SUPPLEMENTS MODEL 680 Figure S28-39 (Sheet 3) S28-112 Configuration S28-AA
MODEL 680 SECTION V - SUPPLEMENTS Figure S28-39 (Sheet 4) Configuration S28-AA S28-113
SECTION V - SUPPLEMENTS MODEL 680 Figure S28-40 (Sheet 1 of 4) S28-114 Configuration S28-AA
MODEL 680 SECTION V - SUPPLEMENTS Figure S28-40 (Sheet 2) Configuration S28-AA S28-115
SECTION V - SUPPLEMENTS MODEL 680 Figure S28-40 (Sheet 3) S28-116 Configuration S28-AA
MODEL 680 SECTION V - SUPPLEMENTS Figure S28-40 (Sheet 4) Configuration S28-AA S28-117
SECTION V - SUPPLEMENTS MODEL 680 This Page Intentionally Left Blank S28-118 Configuration S28-AA
MODEL 680 LANDING SECTION V - SUPPLEMENTS PROCEDURES FOR USE OF APPROACH AND LANDING PERFORMANCE TABLES 1. Determine gross weight of the airplane at the time of arrival at the destination airport. 2. Obtain airport information, i.e., active runway, available runway length, temperature, altitude, wind, icing conditions and runway gradient if applicable. Determine that the temperature is within the ambient temperature limits found in Section II, Operating Limitations. 3. Determine wind component parallel to active runway from the crosswind component chart in Section IV, Performance, Standard Charts. 4. Determine the Maximum Landing Weight Permitted by Climb Requirements or Brake Energy Limits from Figure S28-42. If Anti-Ice - ON, determine also the Maximum Landing Weight Permitted By Climb Requirements from the Anti-Ice - ON table in Figure S28-41. Use the most restrictive of these two weights. If the maximum permissible landing weight is less than the airplane weight at destination, the airplane weight must be reduced. 5. Determine the landing distance, V APP and V REF from Figure S28-43. Apply the following correction factors to the landing distance obtained from Figure S28-43. If the available runway length is less than the required landing distance, the airplane weight must be reduced. LANDING CORRECTION FACTORS FLAP SETTING 35 Refer to Figure S28-43 RUNWAY GRADIENT* MULTIPLY DISTANCE BY -1% (DOWNHILL) 1.21-2% (DOWNHILL) 1.87 * For positive (uphill) runway gradients, use 0 gradient data from Figure S28-43. 6. The approach climb and landing climb gradient tables are presented in Figures S28-44, S28-45, S28-46 and S28-47. NOTE These procedures apply for normal landings at or below 27,100 pounds. Performance above 27,100 pounds is provided for additional information, for use in an emergency which requires a landing at a weight in excess of the maximum design landing weight. Configuration S28-AA S28-119
SECTION V - SUPPLEMENTS MAXIMUM LANDING WEIGHT PERMITTED BY CLIMB REQUIREMENTS OR BRAKE ENERGY LIMITS MODEL 680 The maximum allowable landing weight with Anti-Ice - OFF and for brake energy limits is determined from Figure S28-42 for a given set of conditions. The maximum allowable landing weight with Anti- Ice - ON due to climb requirements, is determined from Figure S28-41. Figure S28-41 does not include data for brake energy limits, therefore, when determining maximum landing weight with Anti- Ice - ON, refer to Figure S28-42 to determine if brake energy limits are a limiting factor, and use the lesser of the two weights. EXAMPLE: Anti-Ice - ON Ambient Temperature = -10 C Pressure Altitude = 14,000 FEET Wind = -10 KNOTS (TAILWIND) Runway Gradient = -2% (DOWNHILL) From Figure S28-41, Maximum Weight = 27,100 Pounds From Figure S28-42, Maximum Weight = 26,740 Pounds Therefore, Maximum Weight = 26,740 Pounds. MAXIMUM LANDING WEIGHT CONDITIONS: APPROACH CLIMB LANDING CLIMB LANDING LANDING GEAR WING FLAP DEGREES SPEEDBRAKES ENGINE(S) AIRSPEED UP 15 RETRACT T.O. THRUST/WINDMILLING V APP DOWN 35 RETRACT T.O. THRUST V REF DOWN 35 EXTEND AFTER TOUCHDOWN IDLE AT 50 FEET V REF AT 50 FEET Figure S28-41 S28-120 Configuration S28-AA
MODEL 680 SECTION V - SUPPLEMENTS Figure S28-42 Configuration S28-AA S28-121
SECTION V - SUPPLEMENTS MODEL 680 Figure S28-43 (Sheet 1 of 4) S28-122 Configuration S28-AA
MODEL 680 SECTION V - SUPPLEMENTS Figure S28-43 (Sheet 2) Configuration S28-AA S28-123
SECTION V - SUPPLEMENTS MODEL 680 Figure S28-43 (Sheet 3) S28-124 Configuration S28-AA
MODEL 680 SECTION V - SUPPLEMENTS Figure S28-43 (Sheet 4) Configuration S28-AA S28-125
SECTION V - SUPPLEMENTS APPROACH AND LANDING CLIMB MODEL 680 Figure S28-44 (Sheet 1 of 2) S28-126 Configuration S28-AA
MODEL 680 SECTION V - SUPPLEMENTS Figure S28-44 (Sheet 2) Configuration S28-AA S28-127
SECTION V - SUPPLEMENTS MODEL 680 Figure S28-45 (Sheet 1 of 2) S28-128 Configuration S28-AA
MODEL 680 SECTION V - SUPPLEMENTS Figure S28-45 (Sheet 2) Configuration S28-AA S28-129
SECTION V - SUPPLEMENTS MODEL 680 Figure S28-46 (Sheet 1 of 2) S28-130 Configuration S28-AA
MODEL 680 SECTION V - SUPPLEMENTS Figure S28-46 (Sheet 2) Configuration S28-AA S28-131
SECTION V - SUPPLEMENTS MODEL 680 Figure S28-47 (Sheet 1 of 2) S28-132 Configuration S28-AA
MODEL 680 SECTION V - SUPPLEMENTS Figure S28-47 (Sheet 2) Configuration S28-AA S28-133
SECTION V - SUPPLEMENTS MODEL 680 This Page Intentionally Left Blank S28-134 Configuration S28-AA