SUPPLEMENT OCTOBER CITATION PERFORMANCE CALCULATOR (CPCalc) MODEL AND ON REVISION 8 68FM-S17-08

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1 MODEL AND ON CITATION PERFORMANCE CALCULATOR (CPCalc) COPYRIGHT 2005 CESSNA AIRCRAFT COMPANY WICHITA, KANSAS, USA 68FM-S17-08 REVISION 8 17 OCTOBER MARCH 2014 U.S. S17-1

2 SECTION V - SUPPLEMENTS CITATION PERFORMANCE CALCULATOR (CPCalc) Use the Log of Effective Pages to determine the current status of this supplement. MODEL 680 Pages affected by the current revision are indicated by an asterisk (*) preceding the page number. Supplement Status Date Original 17 October 2005 Revision 1 19 July 2006 Revision 2 17 October 2006 Revision 3 23 November 2007 Revision 4 16 April 2010 Revision 5 24 May 2010 Revision 6 3 August 2011 Revision 7 14 November 2012 Revision 8 7 March 2014 LOG OF EFFECTIVE PAGES Page Number Page Status Revision Number Configuration Code * S17-1 thru S17-2 Revised 8 S17-AA S17-3 thru S17-4 Original 0 S17-AA * S17-5 thru S17-6 Revised 8 S17-AA S17-7 thru S17-8 Revised 6 S17-AA * S17-9 thru S17-10 Revised 8 S17-AA S17-2 U.S. Configuration S17-AA 68FM-S17-08

3 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 68FM-S17-00 Configuration S17-AA U.S. S17-3

4 SECTION V - SUPPLEMENTS AIRPLANE CONFIGURATION CODES MODEL 680 The following is a list of airplane configuration codes which 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 which have been incorporated into this supplement. Configuration Code S17-AA Effectivity by Serial Number Airplanes and On using the Citation Performance Calculator (CPCalc). S17-4 U.S. Configuration S17-AA 68FM-S17-00

5 MODEL 680 SECTION V - SUPPLEMENTS CITATION PERFORMANCE CALCULATOR (CPCalc) INTRODUCTION This supplement is part of, and must be placed in, the basic FAA Approved Airplane Flight Manual for Airplanes and On using performance information from the Citation Performance Calculator (CPCalc). The information contained herein supplements the information of the basic FAA Approved Airplane Flight Manual. For limitations, procedures and performance information not contained in this supplement, consult the basic FAA Approved Airplane Flight Manual. OPERATING LIMITATIONS GENERAL 1. CPCalc for Windows - the software version displayed on the main startup screen of the CPCalc must match the software version shown in the table below: 2. CPCalc for ipad - the software version displayed on the About screen and the data revision number displayed on the AFM Section screen (Home) must match the revision numbers shown in the table below: Operating System CPCalc Software Version Data Version Microsoft Windows 5.X NA ios for ipad 1.X* 1.X * Version 1.6 or later OPERATIONAL APPROVALS The CPCalc provides FAA approved Section IV Takeoff and Landing performance information and provides advisory Section IV Wet Landing performance information. 1. The CPCalc is approved for use as an alternative source to the takeoff and landing data presented in Section IV of the basic FAA Approved Airplane Flight Manual. 2. The CPCalc, AFM, and TOLD systems are each equally valid sources of performance data; however, the operator must use speed and distance data from only one of these sources. 3. Any modification to the FAA-approved computerized AFM software application, or subsequent alteration to the generated output, will cancel the airworthiness approval of the information. 4. Inputs with decimal values must be entered into CPCalc using the current decimal separator symbol selected in the Windows operating system regional control panel options. No other separator symbols are allowed as input values. 68FM-S17-08 Configuration S17-AA U.S. S17-5

6 SECTION V - SUPPLEMENTS OPERATING PROCEDURES MODEL 680 The operating procedures are the same as those in the basic FAA Approved Airplane Flight Manual except as follows: CYAN MESSAGE PROCEDURES AMBER MESSAGE PROCEDURES RED MESSAGE PROCEDURES EMERGENCY/ABNORMAL PROCEDURES NORMAL PROCEDURES OPERATING INFORMATION PERFORMANCE WARNING The CPCalc performance that is shown is for those conditions as specified. Any deviation from these conditions will result in different performance. There can be combinations of conditions (weight, altitude, and temperature) that could result in performance other than that which would normally be expected: e.g. as weight gets lighter, required distances are longer. DEFINITIONS Climb Gradient Surface: Imaginary surface located 35 feet above the end of the available runway and inclined at a required gradient. (Continued Next Page) S17-6 U.S. Configuration S17-AA 68FM-S17-08

7 MODEL 680 SECTION V - SUPPLEMENTS PERFORMANCE (Continued) NET TAKEOFF FLIGHT PATH METHODS The airplane is flown to Level Off Altitude per the Gross Takeoff Flight Path. Level Off Altitude is the sum of Airport Barometric Altitude and Takeoff Climb Increment. The Takeoff Climb Increment is based on Gross Takeoff Flight Path which is associated with Net Takeoff Flight Path meeting the requirements of one of the three methods the user specifies. CPCalc provides the level off altitude and the horizontal distances along the net takeoff flight path. The net takeoff flight path is used to plan obstacle clearance. CPCalc will reduce the gross weight, if necessary, to meet specific flight path performance requirements. CPCalc provides three methods for the user to specify net takeoff flight path performance. * TAKEOFF THRUST IS LIMITED TO TEN MINUTES MAXIMUM AND THEREAFTER TO MAXIMUM CONTINUOUS THRUST. 1. The net takeoff flight path will level off at a fixed height 1500 feet above the takeoff surface. Level Off Altitude 1500 ft Above Runway Surface Takeoff Climb Increment (TCI) Reference Zero Gear Up Takeoff Field Length Distance to End of 1st Segment Distance to End of 2nd Segment Distance to End of 3rd Segment 1st Segment Configuration = Takeoff Flaps, Gear Down Transitioning to Up, V 2 Speed 2nd Segment Configuration = Takeoff Flaps, Gear Up, V 2 Speed 3rd Segment Configuration = Flaps Transitioning to Up, Gear Up, Accelerating to V ENR Speed Figure S17-1* (Continued Next Page) 68FM-S17-06 Configuration S17-AA U.S. S17-7

8 SECTION V - SUPPLEMENTS MODEL 680 PERFORMANCE (Continued) NET TAKEOFF FLIGHT PATH METHODS (Continued) 2. The net takeoff flight path may continue the 2 nd segment climb beyond 1500 feet to clear an obstacle located anywhere along the path by at least 35 feet. Level Off Altitude Reference Zero Gear Up 35 Feet Clearance Obstacle Height Above Takeoff Surface Takeoff Climb Increment (TCI) Minimum 1500 ft Above Runway Surface Takeoff Field Length Distance to End of 1st Segment Distance to End of 2nd Segment Distance to End of 3rd Segment Horizontal Distance To Obstacle 1st Segment Configuration = Takeoff Flaps, Gear Down Transitioning to Up, V 2 Speed 2nd Segment Configuration = Takeoff Flaps, Gear Up, V 2 Speed 3rd Segment Configuration = Flaps Transitioning to Up, Gear Up, Accelerating to V ENR Speed Figure S17-2* 3. The net takeoff flight path may continue the 2 nd segment climb beyond 1500 feet until the aircraft reaches an assigned level off altitude. The net takeoff flight path is prevented from penetrating a defined climb gradient surface. Level Off Altitude Takeoff Climb Increment (TCI) Reference Zero Gear Up Minimum 1500 ft Above Runway Surface Takeoff Field Length Distance to End of 1st Segment Distance to End of 2nd Segment Distance to End of 3rd Segment 1st Segment Configuration = Takeoff Flaps, Gear Down Transitioning to Up, V 2 Speed 2nd Segment Configuration = Takeoff Flaps, Gear Up, V 2 Speed 3rd Segment Configuration = Flaps Transitioning to Up, Gear Up, Accelerating to V ENR Speed Figure S17-3* S17-8 U.S. Configuration S17-AA 68FM-S17-06

9 MODEL 680 DESCRIPTION SOFTWARE PROCEDURES SECTION V - SUPPLEMENTS The CPCalc software provides help with detailed information on how to use the CPCalc for calculating Takeoff and Landing performance information. 1. Operational landing distance factor requirements may be set under the menu selection Tools Options, or the keyboard shortcut CTRL+O. 2. Climb Gradient calculator is available under the menu selection Tools Climb Gradient Calculator, or the keyboard shortcut CTRL+G. 3. Help is available under the menu selection Help Contents. For help specific to the screen shown, press the F1 key. 4. The calculated performance data may be printed to a connected printer by selecting the Print All Takeoff or Print All Landing buttons on the appropriate output tabs. 5. Additional condition information is available from each output tab by selecting the Additional Conditions button or the keyboard shortcut Alt+C. SOFTWARE INFORMATION 1. The CPCalc software has been demonstrated to function with the following operating system versions: Microsoft Apple Windows XP Windows Vista Windows 7 ios 7.0 for ipad 2. The CPCalc software has been demonstrated to function with any 400 MHz or faster x86 or x64 based processor. (Continued Next Page) 68FM-S17-08 Configuration S17-AA U.S. S17-9

10 SECTION V - SUPPLEMENTS MODEL 680 DESCRIPTION (Continued) 3. It is recommended that CPCalc for Windows be installed on a system that meets the following system requirements: Microsoft Windows operating system (XP, Vista, or 7). Minimum CPU 400 MHz, recommended CPU 600 MHz or better (Intel or AMD ). Minimum memory 64 MB, recommended memory 128 MB or higher. 60 MB free disk space for installation. Desktop, laptop, or tablet PC with CD-ROM drive for installation. Input device (keyboard/mouse/pen). Display that supports a resolution of 600 x 600 at 96 DPI or 1024 x 768 at 120 DPI. Administrative rights to install programs. Microsoft Data Access Components (MDAC) Version 2.5 or higher (included on installation CD). S17-10 U.S. Configuration S17-AA 68FM-S17-08

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