U.S. Airplane Flight Manual Model 510

departure, and to provide minimal anti-icing protection as provided in the Type I holdover timetable (refer to applicable service letter). TWO STEP DEICE/ANTI-ICE - May be used to make sure that the airplane remains clean after deicing. Type II, Type III, or Type IV fluid is used to provide longer term anti-icing protection as provided in the Type II, Type III, or Type IV holdover timetable (refer to applicable service letter). CAUTION CAUTION Type I, Type II, Type III, and Type IV fluids are not compatible and may not be mixed. Additionally, most manufacturers prohibit mixing of brands within a type. Line personnel should be supervised by the PIC or SIC to make sure that deice and anti-ice fluids are applied properly. Make sure that the airplane is always sprayed from the front. Spraying from the rear can force fluid into aerodynamic quiet areas where it will not drain from the airplane. Refer to Figures 7-15 and 7-16. NOTE The first area to be deiced/anti-iced should be easily visible from the cabin/cockpit and should be used to provide a conservative estimate for unseen areas of the airplane before initiating takeoff roll. (Continued Next Page) 510FM TC-R07-01 TEMPORARY FAA APPROVED AIRPLANE FLIGHT MANUAL CHANGE DEICING/ANTI-ICING PROCEDURES (TYPE I, TYPE II, TYPE III, AND TYPE IV FLUIDS) (Continued) Holdover timetables (refer to applicable service letter) are only estimates and vary depending on many factors which include temperature, precipitation type, wind, and airplane skin temperature. Holdover times are based on mixture ratio. Times start when the last application begins. Guidelines for holdover times anticipated by SAE Type I, Type II, Type III, or Type IV, and ISO Type I, Type II, Type III, or Type IV fluid mixtures are a function of weather conditions and outside air temperature (OAT). CAUTION CAUTION • Airplane operators are solely responsible to make sure that holdover timetables contain current data. • Tables are for use in departure planning only and they should be used in conjunction with the pretakeoff contamination check procedures. NOTE • Tables do not apply to other than SAE or ISO Type I, Type II, Type III, or Type IV FPD fluids. • The responsibility for the application of this data remains with the user. • The freezing point of Type I, Type II, Type III, and Type IV fluid mixture must be at least 10°C (18°F) below the current OAT. (Continued Next Page) 510FM TC-R07-01 TEMPORARY FAA APPROVED AIRPLANE FLIGHT MANUAL CHANGE DEICING/ANTI-ICING PROCEDURES (TYPE I, TYPE II, TYPE III, AND TYPE IV FLUIDS) (Continued) SPRAYING TECHNIQUE - TYPE I FLUID Type I fluid should be sprayed on the airplane (with engines off) in a manner which minimizes heat loss to the air. If possible, fluid should be sprayed in a solid cone pattern of large coarse droplets at a temperature of +71°C to +82°C (+160°F to +180°F). The fluid should be sprayed as close as possible to the airplane surfaces, but not closer than 10 feet if a high pressure nozzle is used. Refer to Figures 7-15 and 7-16 for essential areas to be deiced/anti-iced. SPRAYING TECHNIQUE - TYPE II, III, AND IV FLUIDS Application techniques for Types II, III and IV fluids are the same as for Type I, except that since the airplane is already clean, the application should last only long enough to properly coat the airplane surfaces. Refer to Figure 7-15 and 7-16 for essential areas to be deiced/anti-iced. Types II, III and IV fluids should be applied cold to a “clean” airplane. It is, however, sometimes heated and sprayed as a deicing fluid. For this case, it should be considered a Type I fluid, as the heat may change the characteristics of the thickening agents in the fluid. Types II, III and IV fluids, therefore, applied in this manner, will not be as effective as if they were applied cold. NOTE • Holdover time starts when last application begins. • Some fluids can form a thick or high-strength gel during “dryout” and when rehydrated form a slippery film. • Heated areas of aircraft (i.e., heated engine inlets) should be avoided due to the fact that fluid may “dry-out” into hard globular nodules. • Refer to SAE Aerospace ARP 4737 Rev F or later revision. PRETAKEOFF CONTAMINATION CHECK - GROUND ICING CONDITIONS When ground icing conditions are present, a pretakeoff contamination check should be conducted by the PIC/SIC within 5 minutes prior to takeoff, preferably just prior to taxiing onto the active runway. Critical areas of the airplane such as empennage, wing, windshield, and control surfaces should be checked to make sure that they are free of ice, slush, and snow or that the deice/anti-ice fluids are still protecting the airplane. Refer to Figures 7-15 and 7-16 for essential areas to be deiced/anti-iced. 510FM TC-R07-01 TEMPORARY FAA APPROVED AIRPLANE FLIGHT MANUAL CHANGE TAKEOFF AND CLIMB PERFORMANCE - TYPE II, III, AND IV FLUIDS Takeoff and climb performance is degraded when Types II, III, and IV fluids are on the airplane. The fluid that remains on the airplane after takeoff causes the elevator forces at rotation to be increased, takeoff distance to be increased, and climb performance to be decreased. Takeoff and climb tests with anti-ice fluid applied were performed with Flaps Up only, and the data in this section are applicable to Flaps Up takeoffs only. Takeoffs with Flaps 15° were not tested. The following procedures are recommended when departing with anti-ice fluid on the airplane: 1. Use Flaps UP. 2. Anticipate a heavier than normal elevator force at rotation. 3. Determine the normal Flaps Up takeoff field length, and apply any adjustments to speed and field length required by runway gradients or runway contamination from the basic FAA Approved Airplane Flight Manual. Multiply the takeoff field length by 1.25. 4. Decrease the First or Second Segment Takeoff Net Climb Gradient by the appropriate delta from the tables below. 5. Multiply the Single-Engine Takeoff Flight Path Distances by 1.3. NOTE Flaps 15° takeoffs with Types II, III, or IV fluid applied are prohibited per limitation in Section II. 510FM TC-R07-01 TEMPORARY FAA APPROVED AIRPLANE FLIGHT MANUAL CHANGE POSTFLIGHT INSPECTION - TYPE II AND IV FLUIDS Cessna recommends all operators that use heated Type II or Type IV for deicing followed by Type II or Type IV for anti-icing perform periodic visual inspections for de-icing fluid residues. The visual inspection should include: 1. Along the wing rear spar area with the flaps extended. 2. Around the perimeter of the aileron surface. 3. The gaps around the elevator and elevator trim tab. 4. The gaps around the rudder and rudder trim tab. Initially these inspections should be performed after a maximum of three applications of Type II or Type IV fluid. If the airplane is washed or if Type I fluid is used for deicing then the frequency of inspection may be reduced. The frequency of inspections should be determined by the operator based on the results of the residue inspections, frequency of deicing/anti-icing operations as well as frequency of aircraft washing. 510FM TC-R07-01 TEMPORARY FAA APPROVED AIRPLANE FLIGHT MANUAL CHANGE AIRPLANE DEICING NOTE Shaded areas indicate essential areas to be deiced. Figure 7-15 MIMIMUM DIRECT SPRAY AREAS • BRAKES • ENGINE INLETS • ENGINE EXHAUST • PITOT HEADS • RAM AIR INLETS • STALL WARNING VANE • STATIC PORTS • WINDSHIELD • WINDOWS (CABIN) 510FM TC-R07-01 TEMPORARY FAA APPROVED AIRPLANE FLIGHT MANUAL CHANGE AIRPLANE ANTI-ICING NOTE The shaded areas indicate areas where anti-ice fluid is applied. Upper fuselage is anti-iced to preclude ice formation that could be ingested into engine inlets. Figure 7-16 MIMIMUM DIRECT SPRAY AREAS • BRAKES • ENGINE INLETS • ENGINE EXHAUST • PITOT HEADS • RAM AIR INLETS • STALL WARNING VANE • STATIC PORTS • WINDSHIELD • WINDOWS (CABIN) 510FM TC-R07-01 TEMPORARY FAA APPROVED AIRPLANE FLIGHT MANUAL CHANGE In Section II, Operating Limitations, page 2-18, Takeoff and Landing Operational Limits, after the limitation stating, “Refer to Section VII for takeoff and landing distance corrections applicable to runway surfaces other than dry”, add a new limitation as shown below: TAKEOFF AND LANDING OPERATIONAL LIMITS Refer to Section VII for takeoff and landing distance corrections applicable to runway surfaces other than dry. Flaps 15° takeoffs with Types II, III, or IV anti-ice fluid applied are prohibited. Refer to Section VII for anti-ice fluid procedures. Publication Affected: Model 510 Citation Mustang (510-0001 and On) basic FAA Approved Airplane Flight Manual, Revision 7, dated 21 November 2008. Airplane Serial Numbers Affected: Airplanes 510-0001 and On. Description of Change: Section II, Operating Limitations, Takeoff and Landing Operational Limits, add a limitation. Filing Instructions: Insert this temporary change in the Model 510 (510-0001 and On) basic FAA Approved Airplane Flight Manual adjacent to page 2-18. Removal Instructions: This temporary change must be removed and discarded when Revision 8 has been collated into the basic FAA Approved Airplane Flight Manual. 510FM TC-R07-05 TEMPORARY FAA APPROVED AIRPLANE FLIGHT MANUAL CHANGE In Section IV, Performance, page 4-40, Procedures for Use of Takeoff Performance Tables, add a Note after Item 11 as shown below: PROCEDURES FOR USE OF TAKEOFF PERFORMANCE TABLES 11. The first segment takeoff net climb tables are presented in Figures 4-41, 4-42, 4-43 and 4-44. NOTE For takeoffs with anti-ice fluid applied, refer to Section VII. Takeoff with Types II, III, or IV anti-ice fluid applied is prohibited with Flaps 15°. Publication Affected: Model 510 Citation Mustang (510-0001 and On) basic FAA Approved Airplane Flight Manual, Revision 7, dated 21 November 2008. Airplane Serial Numbers Affected: Airplanes 510-0001 and On. Description of Change: Section IV, Performance, Procedures for Use of Takeoff Performance Tables, add a Note. Filing Instructions: Insert this temporary change in the Model 510 (510-0001 and On) basic FAA Approved Airplane Flight Manual adjacent to page 4-40. Removal Instructions: This temporary change must be removed and discarded when Revision 8 has been collated into the basic FAA Approved Airplane Flight Manual. 510FM TC-R07-06 TEMPORARY FAA APPROVED AIRPLANE FLIGHT MANUAL CHANGE In Section III, Operating Procedures, Normal Procedures, page 3-144, Starting Engines Checklist, add a Caution after Step 4, change the Note after Step 4, and change Step 5 as shown below: STARTING ENGINES 4. Engine Instruments . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . CHECK NORMAL (Battery Current less than 100 Amps) CAUTION CAUTION If the operating generator drops off-line during a cross-generator start (GEN OFF L-R), an ENG CTRL SYS L or R CAS message posts, or ITT indication is lost at any time during the start sequence, abort the start immediately by bringing the throttle to CUTOFF to reduce the possibility of a hot or hung engine start. NOTE Following a battery start, the battery current should be allowed to decrease to 100 Amps or less prior to attempting a cross-generator start to make sure that sufficient battery capacity exists for the engine start. To make sure that adequate generator capacity exists, increase the operating engine N 2 to at least 10% above the current stable ground idle speed before a cross-generator start. 5. Operating Engine N2 . . . . . . . . . . . . . . . . . . . . . . . INCREASE to 10% above ground idle N 2 (for a cross-generator start) Publication Affected: Model 510 Citation Mustang (510-0001 and On) basic FAA Approved Airplane Flight Manual, Revision 7, dated 21 November 2008. Airplane Serial Numbers Affected: Airplanes 510-0001 and On. Description of Change: Section III, Operating Procedures, Normal Procedures, Starting Engines Checklist, add a Caution, change a Note and a step. Filing Instructions: Insert this temporary change in the Model 510 (510-0001 and On) basic FAA Approved Airplane Flight Manual adjacent to page 3-144. Removal Instructions: This temporary change must be removed and discarded when Revision 8 has been collated into the basic FAA Approved Airplane Flight Manual. 510FM TC-R07-07 TEMPORARY FAA APPROVED AIRPLANE FLIGHT MANUAL CHANGE In Section III, Operating Procedures, Emergency Procedures, page 3-11, ENGINE FIRE L OR R (ENGINE FIRE WARNING LIGHT ILLUMINATED) procedure, change Step 3 to read as follows:  ENGINE FIRE L OR R (ENGINE FIRE WARNING LIGHT ILLUMINITATED) (Continued)  IF ENGINE FIRE LIGHT ON AFFECTED SIDE DOES NOT ILLUMINATE (POSSIBLE DAMAGE TO FIRE SENSOR) 3. Affected ENGINE FIRE Switch . . . . . . . . . . . . . . . . . . . . . . LIFT COVER and PUSH Publication Affected: Model 510 Citation Mustang (510-0001 and On) basic FAA Approved Airplane Flight Manual, Revision 7, dated 21 November 2008. Airplane Serial Numbers Affected: Airplanes 510-0001 and On. Description of Change: Section III, Operating Procedures, Emergency Procedures, ENGINE FIRE L OR R (ENGINE FIRE WARNING LIGHT ILLUMINATED) procedure, change a step. Filing Instructions: Insert this temporary change in the Model 510 (510-0001 and On) basic FAA Approved Airplane Flight Manual adjacent to page 3-11. Removal Instructions: This temporary change must be removed and discarded when Revision 8 has been collated into the basic FAA Approved Airplane Flight Manual. 510FM TC-R07-09 TEMPORARY FAA APPROVED AIRPLANE FLIGHT MANUAL CHANGE This Page Intentionally Left Blank 510FM TC-R07-10 TEMPORARY FAA APPROVED AIRPLANE FLIGHT MANUAL CHANGE In Section III, Operating Procedures, Normal Procedures, page 3-147, BEFORE TAKEOFF procedure, add the following note after Step 12: NOTE Selecting LOW/OFF for takeoff and landing during night flight conditions improves visibility through the windshield. Publication Affected: Model 510 Citation Mustang (510-0001 and On) basic FAA Approved Airplane Flight Manual, Revision 7, dated 21 November 2008. Airplane Serial Numbers Affected: Airplanes 510-0001 and On. Description of Change: Section III, Operating Procedures, Normal Procedures, BEFORE TAKEOFF procedure, add a note. Filing Instructions: Insert this temporary change in the Model 510 (510-0001 and On) basic FAA Approved Airplane Flight Manual adjacent to page 3-147. Removal Instructions: This temporary change must be removed and discarded when Revision 8 has been collated into the basic FAA Approved Airplane Flight Manual. 510FM TC-R07-10 TEMPORARY FAA APPROVED AIRPLANE FLIGHT MANUAL CHANGE This Page Intentionally Left Blank 510FM TC-R07-11 TEMPORARY FAA APPROVED AIRPLANE FLIGHT MANUAL CHANGE In Section III, Operating Procedures, Normal Procedures, page 3-149, BEFORE LANDING procedure, add Step 7 and a note: 7. WINDSHIELD ANTI-ICE Switches . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . AS REQUIRED NOTE Selecting LOW/OFF for takeoff and landing during night flight conditions improves visibility through the windshield. Publication Affected: Model 510 Citation Mustang (510-0001 and On) basic FAA Approved Airplane Flight Manual, Revision 7, dated 21 November 2008. Airplane Serial Numbers Affected: Airplanes 510-0001 and On. Description of Change: Section III, Operating Procedures, Normal Procedures, BEFORE LANDING procedure, add a step and a note. Filing Instructions: Insert this temporary change in the Model 510 (510-0001 and On) basic FAA Approved Airplane Flight Manual adjacent to page 3-149. Removal Instructions: This temporary change must be removed and discarded when Revision 8 has been collated into the basic FAA Approved Airplane Flight Manual. 510FM TC-R07-11 TEMPORARY FAA APPROVED AIRPLANE FLIGHT MANUAL CHANGE This Page Intentionally Left Blank 510FM TC-R07-12 TEMPORARY FAA APPROVED AIRPLANE FLIGHT MANUAL CHANGE In Section I, Introduction, page 1-7/1-8, Airplane Configuration Codes, change the serial effectivity of configuration codes AJ and AK as follows: Publication Affected: Model 510 Citation Mustang (510-0001 and On) basic FAA Approved Airplane Flight Manual, Revision 7, dated 21 November 2008. Airplane Serial Numbers Affected: Airplanes 510-0001 and On. Description of Change: Section I, Introduction, Airplane Configuration Codes, change the serial effectivity for a configuration set. Filing Instructions: Insert this temporary change in the Model 510 (510-0001 and On) basic FAA Approved Airplane Flight Manual adjacent to page 1-7/1-8. Removal Instructions: This temporary change must be removed and discarded when Revision 8 has been collated into the basic FAA Approved Airplane Flight Manual. Configuration Code Effectivity by Serial Number Applicable Configuration Code AJ Airplanes 510-0001 thru -0177 incorporating SB510-34-09 and Airplanes 510-0178 and On. AK Airplanes 510-0001 thru -0177 not incorporating SB510-34-09. 510FM TC-R07-12 TEMPORARY FAA APPROVED AIRPLANE FLIGHT MANUAL CHANGE This Page Intentionally Left Blank 510FM TC-R07-13 TEMPORARY FAA APPROVED AIRPLANE FLIGHT MANUAL CHANGE In Section II, Operating Limitations, Garmin G1000 GPS Navigation System, page 2-31.1, add a new sentence to item number 5 as follows: 5. This limitation applies to airplanes incorporating GPS software version 2.4. Use of the Garmin G1000 system for GPS or WAAS navigation under Instrument Flight Rules (IFR) requires that: Publication Affected: Model 510 Citation Mustang (510-0001 and On) basic FAA Approved Airplane Flight Manual, Revision 7, dated 21 November 2008. Airplane Serial Numbers Affected: Airplanes 510-0001 thru -0065 not incorporating SB510-34-02 . Description of Change: Section II, Operating Limitations, Garmin G1000 GPS Navigation System, add a sentence. Filing Instructions: Insert this temporary change in the Model 510 (510-0001 and On) basic FAA Approved Airplane Flight Manual adjacent to page 2-31.1. Removal Instructions: This temporary change must be removed and discarded when SB 510-34-02 has been complied with or when Revision 8 has been collated into the basic FAA Approved Airplane Flight Manual. 510FM TC-R07-13 TEMPORARY FAA APPROVED AIRPLANE FLIGHT MANUAL CHANGE In Section I, Introduction, page 1-6, Service Bulletin Configuration List, change the software version and serial effectivity for SB510-34-09 as shown below and add SB510-34-11: Publication Affected: Model 510 Citation Mustang (510-0001 and On) basic FAA Approved Airplane Flight Manual, Revision 7, dated 21 November 2008. Airplane Serial Numbers Affected: Airplanes 510-0001 and On. Description of Change: Section I, Introduction, Service Bulletin Configuration List, change a Service Bulletin and add a Service Bulletin. Filing Instructions: Insert this temporary change in the Model 510 (510-0001 and On) basic FAA Approved Airplane Flight Manual adjacent to page 1-6. Removal Instructions: This temporary change replaces 510FM TC-R07-04 in its entirety. This temporary change must be removed and discarded when Revision 8 has been collated into the basic FAA Approved Airplane Flight Manual. Number Title Airplane Serial Effectivity Revision Incorporated Incorporated in Airplane SB510-34-09 Navigation - Garmin G1000 Software Version 010-00435-16 Upgrade. 510-0001 thru -0177 7 SB510-34-11 Navigation - Garmin G1000 Software Version 010-00435-21 Upgrade. 510-0001 thru -0371 510FM TC-R07-15 TEMPORARY FAA APPROVED AIRPLANE FLIGHT MANUAL CHANGE In Section II, Operating Limitations, add the following section: HEADSETS For two-pilot operations, both pilots must wear headsets when either overhead cockpit speaker audio is muted. For single-pilot operations, the pilot must wear a headset with microphone at all times. Publication Affected: Model 510 Citation Mustang (510-0001 and On) basic FAA Approved Airplane Flight Manual, Revision 7, dated 21 November 2008. Airplane Serial Numbers Affected: Airplanes 510-0001 and On. Description of Change: Section II, Operating Limitations, add a section. Filing Instructions: Insert this temporary change in the Model 510 (510-0001 and On) basic FAA Approved Airplane Flight Manual adjacent to page 2-33. Removal Instructions: This temporary change must be removed and discarded when Revision 8 has been collated into the basic FAA Approved Airplane Flight Manual. 510FM TC-R07-16 TEMPORARY FAA APPROVED AIRPLANE FLIGHT MANUAL CHANGE 510FM TC-R07-17 TEMPORARY FAA APPROVED AIRPLANE FLIGHT MANUAL CHANGE In Section III, Operating Procedures, Abnormal Procedures, replace the AUDIO PANEL FAILURE procedure with the following procedure:  AUDIO PANEL FAILURE; LOSS OF COM MIC; OR LOSS OF AURAL ALERTS This failure may be indicated by a GMA 1/2 FAIL Garmin System Message or the inability to communicate using the affected audio panel. This failure may be accompanied by the unannunciated loss of COM1 receiver audio, microphone audio or sidetone, and failure of the microphone key to transmit even though “TX” is annunciated on the display. Garmin generated aural alerts will be unavailable. These include autopilot disconnect tone, TIS traffic alerts only, TAWS alerts, and altitude alerts. VOR/LOC receiver audio will also be unavailable. 1. AUDIO 1 or AUDIO 2 Circuit Breaker (affected side) . . . . . . . . . . . . . . . . . . . . . . . . RESET • IF AUDIO PANEL, COM MIC, OR AURAL ALERTS ARE NOT RESTORED 2. COMM 1 or COMM 2 Circuit Breaker (affected side) . . . . . . . . . . . . . . . . . . . . . . . PULL 3. SPKR Button (operating audio panel). . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . ON 4. COM MIC Button (audio panel selection of operating COM radio). . . . . . . . . . . . . . . ON NOTE • In the event of an audio panel failure, a fail-safe circuit connects the affected side headset directly to the on-side COM radio. The speaker on the affected side will be inoperative. • The operating audio panel will not be able to listen to COM or NAV audio from the side with the inoperative audio panel. PROCEDURE COMPLETED • IF AUDIO PANEL, COM MIC, OR AURAL ALERTS ARE RESTORED PROCEDURE COMPLETED Publication Affected: Model 510 Citation Mustang (510-0001 and On) basic FAA Approved Airplane Flight Manual, Revision 7, dated 21 November 2008. Airplane Serial Numbers Affected: Airplanes 510-0001 and On. Description of Change: Section III, Operating Procedures, Abnormal Procedures, replace the AUDIO PANEL FAILURE procedure. Filing Instructions: Insert this temporary change in the Model 510 (510-0001 and On) basic FAA Approved Airplane Flight Manual adjacent to page 3-101. Removal Instructions: This temporary change must be removed and discarded when Revision 8 has been collated into the basic FAA Approved Airplane Flight Manual. 510FM TC-R07-17 TEMPORARY FAA APPROVED AIRPLANE FLIGHT MANUAL CHANGE In Section III, Operating Procedures, Normal Procedures, update the OXYGEN MASK MIC AND HEADSET MIC information as follows: OXYGEN MASK MIC AND HEADSET MIC A two-position MIC toggle switch is provided on the instrument panel just below the pilot’s and copilot’s control yokes. The switch positions are marked OXYGEN MASK and HEADSET. Depressing the MIC button on the appropriate control wheel allows a crew member to transmit through the headset microphone or oxygen mask microphone, whichever is selected. Transmit side- tone and intercom will be heard in both cockpit speakers. Received audio and aural warnings will be heard in both cockpit speakers. All audio is also available in the headsets. Publication Affected: Model 510 Citation Mustang (510-0001 and On) basic FAA Approved Airplane Flight Manual, Revision 7, dated 21 November 2008. Airplane Serial Numbers Affected: Airplanes 510-0001 thru -0371 incorporating SB510-34-11 and Airplanes 510-0372 and On . Description of Change: Section III, Operating Procedures, Normal Procedures, update OXYGEN MASK MIC AND HEADSET MIC information. Filing Instructions: Insert this temporary change in the Model 510 (510-0001 and On) basic FAA Approved Airplane Flight Manual adjacent to page 3-176. Removal Instructions: This temporary change must be removed and discarded when Revision 8 has been collated into the basic FAA Approved Airplane Flight Manual. 510FM TC-R07-18 TEMPORARY FAA APPROVED AIRPLANE FLIGHT MANUAL CHANGE  UNCOMMANDED REDUCTION IN ENGINE POWER DURING ICING CONDITIONS (Continued) PRIOR TO DESCENT 8. Engine Anti-Ice Circuit Breaker. . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . RESET 9. ENGINE ANTI-ICE Switches . . . . . . . . . . . . . ON until RAT indications are normal and icing conditions are exited. NOTE No maintenance corrective action as required after flight. Verify all Engine Anti-Ice circuit breakers are reset and the affected T2 probes are clear of ice or other contamination. PROCEDURE COMPLETED 510FM TC-R07-19 TEMPORARY FAA APPROVED AIRPLANE FLIGHT MANUAL CHANGE In Section III, Operating Procedures, Abnormal Procedures, delete the Uncommanded Reduction in Engine Power During Icing Conditions procedure:  UNCOMMANDED REDUCTION IN ENGINE POWER DURING ICING CONDITIONS In some icing encounters at high altitude, the heater on the engine T2 probe cannot keep the probe clear of ice. This can cause a false high RAT temperature indication to the FADEC. The result is the FADEC will command a lower N1 until the T2 probe is de-iced, or the engine Anti-Ice is selected OFF. This may occur with only a trace of ice accumulation visible on the airplane. If both Engine Anti-Ice circuit breakers are pulled, the engine inlets will both be heated, but an amber ENG A/I COLD CAS message will display due to the loss of nacelle temperature monitoring. No additional action is required to address the amber ENG A/I COLD CAS message, and the message will clear when either circuit breaker is reset. 1. Engine Sync . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . OFF 2. ENGINE ANTI-ICE Switch (affected engine) . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . OFF 3. RAT Indication on PFD . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . VERIFY decrease 4. Exit icing conditions as soon as practical. 5. Monitor for ice accumulation. • IF ICING INTENSITY IS TRACE OR LESS Go to Step 8 prior to descent. • IF ICING INTENSITY IS GREATER THAN TRACE 6. Engine Anti-Ice Circuit Breaker (affected engine). . . . . . . . . . . . . . . . . . . . . . . . . PULL 7. Exit icing conditions as soon as possible. (Continued Next Page) Publication Affected: Model 510 Citation Mustang (510-0001 and On) basic FAA Approved Airplane Flight Manual, Revision 7, dated 21 November 2008. Airplane Serial Numbers Affected: Airplanes 510-0001 and On. Description of Change: Section III, Operating Procedures, Abnormal Procedures, Icing, delete a procedure. Filing Instructions: Insert this temporary change in the Model 510 (510-0001 and On) basic FAA Approved Airplane Flight Manual adjacent to page 3-91/3-92. Removal Instructions: This temporary change must be removed and discarded when Revision 8 has been collated into the basic FAA Approved Airplane Flight Manual. 510FM TC-R07-19 TEMPORARY FAA APPROVED AIRPLANE FLIGHT MANUAL CHANGE In Section III, Operating Procedures, Abnormal Procedures, Table of Contents, add the Uncommanded Reduction in Engine Power procedure and delete the Uncommanded Reduction in Engine Power During Icing Conditions procedure. ENGINE / FUEL Uncommanded Reduction in Engine Power . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 3-63/3-64 ICING Uncommanded Reduction in Engine Power During Icing Conditions . . . . . . . . . . . . . . . 3-91/3-92 Publication Affected: Model 510 Citation Mustang (510-0001 and On) basic FAA Approved Airplane Flight Manual, Revision 7, dated 21 November 2008. Airplane Serial Numbers Affected: Airplanes 510-0001 and On. Description of Change: Section III, Operating Procedures, Abnormal Procedures, Table of Contents, add and delete a procedure. Filing Instructions: Insert this temporary change in the Model 510 (510-0001 and On) basic FAA Approved Airplane Flight Manual adjacent to page 3-45 or 3-45.1. Removal Instructions: This temporary change must be removed and discarded when Revision 8 has been collated into the basic FAA Approved Airplane Flight Manual. 510FM TC-R07-21 TEMPORARY FAA APPROVED AIRPLANE FLIGHT MANUAL CHANGE In Section III, Operating Procedures, Emergency Procedures, update the Inadvertent Stall procedure title as follows:  INADVERTENT STALL (STALL WARNING TONE, BUFFET, AND/OR ROLL-OFF) Publication Affected: Model 510 Citation Mustang (510-0001 and On) basic FAA Approved Airplane Flight Manual, Revision 7, dated 21 November 2008. Airplane Serial Numbers Affected: Airplanes 510-0001 and On. Description of Change: Section III, Operating Procedures, Emergency Procedures, update procedure title. Filing Instructions: Insert this temporary change in the Model 510 (510-0001 and On) basic FAA Approved Airplane Flight Manual adjacent to page 3-43/3-44. Removal Instructions: This temporary change must be removed and discarded when Revision 8 has been collated into the basic FAA Approved Airplane Flight Manual. 510FM TC-R07-22 TEMPORARY FAA APPROVED AIRPLANE FLIGHT MANUAL CHANGE In Section II, Operating Limitations, Fuel Limitations, page 2-14, update the Fuel Limitations section as shown below: FUEL LIMITATIONS The corresponding electric fuel boost pump must be turned ON when the FUEL LO L-R CAS message is displayed or at 170 pounds or less of indicated fuel in either tank. Maximum approved fuel imbalance is 200 pounds. NOTE An emergency fuel imbalance of 600 pounds has been demonstrated for safe return and landing. Minimum fuel quantity for takeoff is 200 pounds per wing. Figure 2-10 lists the fuel temperature limitations for each approved fuel. The fuel tank temperature indication on EICAS does not monitor for fuel temperature out of limits. APPROVED FUELS Figure 2-10 (Continued Next Page) Publication Affected: Model 510 Citation Mustang (510-0001 and On) basic FAA Approved Airplane Flight Manual, Revision 7, dated 21 November 2008. Airplane Serial Numbers Affected: Airplanes 510-0001 and On. Description of Change: Section II, Operating Limitations, Fuel Limitations, update the section. Filing Instructions: Insert this temporary change in the Model 510 (510-0001 and On) basic FAA Approved Airplane Flight Manual adjacent to page 2-14. Removal Instructions: This temporary change must be removed and discarded when Revision 8 has been collated into the basic FAA Approved Airplane Flight Manual. APPROVED FUEL GRADES (TYPE) FUEL ADDITIVES (REFER TO NOTES BELOW) SPECIFICATION MINIMUM FUEL TEMPERATURE °C MAXIMUM FUEL TEMPERATURE °C JET A 1, 5, 7 and 8 ASTM-D1655 -35 50 JET A-1 1, 5, 7 and 8 ASTM-D1655 -35 50 Jet No. 3 1, 4, and 5 GB6537 -35 50 JP-8 1, 5, 7 and 8 MIL-DTL-83133 -35 50 RT 2, 3, 5, 6, 7 and 8 GOST 10227 -35 50 RT (Ukraine) 2, 3, 5, 6, 7 and 8 GSTU 320.00149943.007 -35 50 TS-1 2, 3, 5, 6, 7 and 8 GOST 10227 -35 50 TS-1 (Ukraine) 2, 3, 5, 6, 7 and 8 GSTU 320.00149943.011 -35 50 510FM TC-R07-23 TEMPORARY FAA APPROVED AIRPLANE FLIGHT MANUAL CHANGE FUEL LIMITATIONS (Continued) NOTE The following optional fuel system additives may be added to the fuels as noted at the following concentrations. Use of these fuel additives is not required. Refer to Section III, Normal Procedures, ANTI-ICE ADDITIVES for blending instructions. 1. MIL-DTL-85470 (DiEGME) in a concentration of 0.10 to 0.15 percent by volume 2. GOST 8313 (Fluid I) in a concentration of 0.10 to 0.30 percent by volume 3. A mixture of 50% GOST 8313 (Fluid I) and 50% CIS TU6-10-1458 (Fluid I-M) in a concentration of 0.10 to 0.30 percent by volume 4. T1301 per SH0396-92 (EGME) in a concentration of 0.10 to 0.15 percent by volume 5. DuPont Stadis 450 as required to bring fuel up to 300 conductive units, not to exceed 3 ppm (parts per million) 6. Sigbol as required to bring fuel up to 300 conductive units, not to exceed 3 ppm 7. Biobor JF at a concentration not to exceed 270 ppm 8. Kathon FP 1.5 at a concentration not to exceed 100 ppm 510FM TC-R07-23 TEMPORARY FAA APPROVED AIRPLANE FLIGHT MANUAL CHANGE  ENGINE START MALFUNCTION (ENGINE DOES NOT START) (Continued) • IN FLIGHT  IF UNABLE TO ATTEMPT ANOTHER START 3. Land as soon as practical. Refer to Abnormal Procedures, ENGINE FAILURE/ PRECAUTIONARY SHUTDOWN. PROCEDURE COMPLETED  IF ABLE TO ATTEMPT ANOTHER START 3. Refer to Abnormal Procedures, INFLIGHT RESTART - ONE ENGINE. PROCEDURE COMPLETED 510FM TC-R07-24 TEMPORARY FAA APPROVED AIRPLANE FLIGHT MANUAL CHANGE In Section III, Operating Procedures, Abnormal Procedures, Page 3-53, replace the ENGINE START MALFUNCTION (ENGINE DOES NOT START) procedure with the following:  ENGINE START MALFUNCTION (ENGINE DOES NOT START) 1. Throttle (affected engine) . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . CUTOFF 2. ENGINE START DISENG Button . . . . . . . . . . . . PRESS 15 seconds after throttle CUTOFF • ON GROUND 3. IGN Switch (affected engine) . . . . . . . . . . . . . . . . . . . . . ON to check the maximum ITT (if FADEC commanded a start abort) NOTE • If the FADEC does not command a start abort or if the pilot aborts the start, the maximum ITT cannot be retrieved through use of the IGN Switch for the affected engine. • Refer to Operating Limitations, ENGINE START LIMITATIONS to determine required maintenance actions. 4. IGN Switch (affected engine) . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . NORM  IF UNABLE TO ATTEMPT ANOTHER START PROCEDURE COMPLETED  IF ABLE TO ATTEMPT ANOTHER START 5. Refer to Abnormal Procedures, DRY MOTORING prior to making another start attempt. PROCEDURE COMPLETED (Continued Next Page) Publication Affected: Model 510 Citation Mustang (510-0001 and On) basic FAA Approved Airplane Flight Manual, Revision 7, dated 21 November 2008. Airplane Serial Numbers Affected: Airplanes 510-0405 and On and Airplanes 510-0001 thru -0404 incorporating SB510-76-01. Description of Change: Section III, Operating Procedures, Abnormal Procedures, replace the ENGINE START MALFUNCTION (ENGINE DOES NOT START) procedure. Filing Instructions: Insert this temporary change in the Model 510 (510-0001 and On) basic FAA Approved Airplane Flight Manual adjacent to page 3-53. Removal Instructions: This temporary change must be removed and discarded when Revision 8 has been collated into the basic FAA Approved Airplane Flight Manual. 510FM TC-R07-24 TEMPORARY FAA APPROVED AIRPLANE FLIGHT MANUAL CHANGE 510FM TC-R07-25 TEMPORARY FAA APPROVED AIRPLANE FLIGHT MANUAL CHANGE In Section III, Operating Procedures, Abnormal Procedures, Page 3-87, replace the T2 HTR FAIL (ENGINE T2 HEATER FAILURE) procedure with the following procedure:  T2 HTR FAIL (ENGINE T2 HEATER FAILURE) Indicates there is no current to the T2 heater on the affected side when the ENGINE ANTI-ICE Switch is selected ON for that side. When operating above 4000 ft pressure altitude with ENGINE ANTI-ICE on, the FADEC automatically detects errors in the T2 temperature probe that may be caused by ice accumulation associated with operation in an ice crystal environment. When an error is detected, the FADEC implements temperature confirmation logic and automatically removes power from the T2 heater, causing the T2 HTR FAIL CAS message to illuminate. Resetting the ENGINE ANTI-ICE Switch during temperature confirmation will not reset the logic, will not reapply power to the T2 heater, will not clear the CAS message, and should not be attempted. Fault code logs may be checked after flight to determine if the message was illuminated due to activation of FADEC temperature confirmation logic or actual heater failure. • ON GROUND 1. Correct prior to flight. PROCEDURE COMPLETED • IN FLIGHT 1. Engine ANTI-ICE Switches. . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . ON 2. Exit icing environment PROCEDURE COMPLETED Publication Affected: Model 510 Citation Mustang (510-0001 and On) basic FAA Approved Airplane Flight Manual, Revision 7, dated 21 November 2008. Airplane Serial Numbers Affected: Airplanes 510-0405 and On and Airplanes 510-0001 thru -0404 incorporating SB510-76-01. Description of Change: Section III, Operating Procedures, Abnormal Procedures, replace the T2 HTR FAIL (ENGINE T2 HEATER FAILURE) procedure. Filing Instructions: Insert this temporary change in the Model 510 (510-0001 and On) basic FAA Approved Airplane Flight Manual adjacent to page 3-87. Removal Instructions: This temporary change must be removed and discarded when Revision 8 has been collated into the basic FAA Approved Airplane Flight Manual. 510FM TC-R07-25 TEMPORARY FAA APPROVED AIRPLANE FLIGHT MANUAL CHANGE  UNCOMMANDED REDUCTION IN ENGINE POWER (Continued) PRIOR TO DESCENT 8. Engine Anti-Ice Circuit Breaker. . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . RESET 9. ENGINE ANTI-ICE Switches . . . . . . . . . . . . . ON until RAT indications are normal and icing conditions are exited. NOTE No maintenance corrective action is required after flight. Verify all Engine Anti-Ice circuit breakers are reset and the affected T2 probes are clear of ice or other contamination. PROCEDURE COMPLETED 510FM TC-R07-26 TEMPORARY FAA APPROVED AIRPLANE FLIGHT MANUAL CHANGE In Section III, Operating Procedures, Abnormal Procedures, add the Uncommanded Reduction in Engine Power procedure after the Fuel Transfer Message On When Transfer Not Selected procedure:  UNCOMMANDED REDUCTION IN ENGINE POWER In some icing encounters, the heater on the engine T2 probe cannot keep the probe clear of ice. This can cause a false high RAT temperature indication to the FADEC. The result is the FADEC will command a lower N1 until the T2 probe is de-iced, or the engine Anti-Ice is selected OFF. This may occur with no ice accumulation visible on the airplane. If both Engine Anti-Ice circuit breakers are pulled, the engine inlets will both be heated, but an amber ENG A/I COLD CAS message will display due to the loss of nacelle temperature monitoring. No additional action is required to address the amber ENG A/I COLD CAS message, and the message will clear when either circuit breaker is reset. 1. Engine Sync . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . OFF 2. ENGINE ANTI-ICE Switch (affected engine) . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . OFF 3. RAT Indication on PFD . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . VERIFY decrease 4. Exit icing conditions as soon as practical. 5. Monitor for ice accumulation. • IF ICING INTENSITY IS TRACE OR LESS Go to Step 8 prior to descent. • IF ICING INTENSITY IS GREATER THAN TRACE 6. Engine Anti-Ice Circuit Breaker (affected engine). . . . . . . . . . . . . . . . . . . . . . . . . PULL 7. Exit icing conditions as soon as possible. (Continued Next Page) Publication Affected: Model 510 Citation Mustang (510-0001 and On) basic FAA Approved Airplane Flight Manual, Revision 7, dated 21 November 2008. Airplane Serial Numbers Affected: Airplanes 510-0001 thru -0404 not incorporating SB510-76-01. Description of Change: Section III, Operating Procedures, Abnormal Procedures, Engine/Fuel, add a procedure. Filing Instructions: Remove and discard 510FM TC-R07-20. Insert this temporary change in the Model 510 (510-0001 and On) basic FAA Approved Airplane Flight Manual adjacent to page 3-63/3-64. This temporary change replaces 510FM TC-R07-20 in its entirety. Removal Instructions: This temporary change must be removed and discarded when Revision 8 has been collated into the basic FAA Approved Airplane Flight Manual or when SB510-76-01 has been incorporated. 510FM TC-R07-26 TEMPORARY FAA APPROVED AIRPLANE FLIGHT MANUAL CHANGE GARMIN G1000 AVIONICS SYSTEM 1. The current Garmin G1000 Cockpit Reference Guide (CRG) Part Number and System Software Version that must be available to the pilot during flight are displayed on the MFD AUX group, SYSTEM STATUS page. 2. Category II approaches are prohibited. 3. Dispatch is prohibited following a flight where either a PFD/MFD COOLING or GIA 1-2 COOLING Garmin System Message was displayed, until the condition is identified and corrected. 4. Dispatch is prohibited with a PFD/MFD SERVICE, GIA 1-2 SERVICE, or GMA 1-2 SERVICE Garmin System Message displayed, until the condition is identified and corrected. 5. All display units must be installed and operational. 6. Dispatch with a display in reversionary mode is prohibited. 7. Autopilot: a. One pilot must remain seated, with the seatbelt fastened, during all autopilot operations. b. Autopilot operation is prohibited if either PFD is in AHRS reversion. c. Autopilot Minimum-Use-Height: (1) Takeoff and Climb ............................................................................ 700 feet AGL (2) Enroute and Descent ..................................................................... 1000 feet AGL (3) Approach (GP or GS Mode)............................................................. 200 feet AGL (4) Approach (FLC, VS, PIT or ALT Mode)............................ Higher of 400 feet AGL or Approach MDA 8. Use of VNAV is prohibited during an approach with a teardrop course reversal. VNAV will fail at the beginning of the teardrop. 9. Use of the NAVIGATION MAP page for pilotage navigation is prohibited unless required by AFM procedure. The NAVIGATION MAP is intended only to enhance situational awareness. Navigation is to be conducted using only current charts, data, and authorized navigation facilities. 10. Use of the TRAFFIC MAP to maneuver the airplane to avoid traffic is prohibited. The TRAFFIC INFORMATION SYSTEM (TIS) is intended for advisory use only. TIS is intended only to help the pilot to visually locate traffic. It is the responsibility of the pilot to see and maneuver to avoid traffic. 11. Use of the TERRAIN information for primary terrain avoidance is prohibited. The TERRAIN information is intended only to enhance situational awareness. It is the pilot’s responsibility to provide terrain clearance at all times. NOTE For terrain database cycle 08T2 and earlier cycles, TERRAIN information is not available in locations north of 75º North latitude or south of 60º South latitude due to the absence of terrain data in these geographical areas. 12. Use of the WEATHER MAP (XM Weather) for hazardous weather (thunderstorm) penetration is prohibited. LTNG information on the NAVIGATION MAP or WEATHER MAP is approved only as an aid to hazardous weather avoidance, not penetration. 13. The fuel quantity, fuel required, fuel remaining, and gross weight estimate functions of the G1000 are supplemental information only and must be verified by the flight crew. 14. Takeoff with a noticeably drifting heading indicator (1/2 degree per second or greater when the airplane is stationary) is prohibited. AHRS failure may occur when the heading is drifting in this manner. A constant heading offset is not an indication of a drifting heading. 2-29 U.S. Configuration AA TEMPORARY FAA APPROVED AIRPLANE FLIGHT MANUAL CHANGE In Section II, Operating Limitations, page 2-29 or 2-29.1, Garmin G1000 Avionics System, replace the information on the page as follows: Publication Affected: Model 510 Citation Mustang (510-0001 and On) basic FAA Approved Airplane Flight Manual, Revision 7, dated 21 November 2008. Airplane Serial Numbers Affected: Airplanes 510-0001 and On. Description of Change: Section II, Operating Limitations, Garmin G1000 Avionics System, replace the information on page 2-29 or 2-29.1. Filing Instructions: Insert this temporary change in the Model 510 (510-0001 and On) basic FAA Approved Airplane Flight Manual adjacent to page 2-29 or 2-29.1. This temporary change replaces the information on page 2-29 or 2-29.1 in its entirety. Removal Instructions: This temporary change replaces 510FM TC-R07-14 in its entirety. This temporary change must be removed and discarded when Revision 8 has been collated into the basic FAA Approved Airplane Flight Manual. 510FM TC-R07-27 TEMPORARY FAA APPROVED AIRPLANE FLIGHT MANUAL CHANGE In Section III, Operating Procedures, Normal Procedures, Taxi, Page 3-146, after step 3, add a warning as follows: TAXI 3. Flight Instruments (including standby instruments). . . . . . . . . . . . . . . . . . . . . . . . . . CHECK WARNING Takeoff with a noticeably drifting heading indicator is prohibited. Publication Affected: Model 510 Citation Mustang (510-0001 and On) basic FAA Approved Airplane Flight Manual, Revision 7, dated 21 November 2008. Airplane Serial Numbers Affected: Airplanes 510-0001 and On. Description of Change: Section III, Operating Procedures, Normal Procedures, Taxi, add a warning. Filing Instructions: Insert this temporary change in the Model 510 (510-0001 and On) basic FAA Approved Airplane Flight Manual adjacent to page 3-146. Removal Instructions: This temporary change must be removed and discarded when Revision 8 has been collated into the basic FAA Approved Airplane Flight Manual. 510FM TC-R07-28 MODEL 510 LOG OF EFFECTIVE PAGES U.S. FAA APPROVED Configuration LOG OF EFFECTIVE PAGES Use this page to determine the currency and applicability of your basic FAA Approved Airplane Flight Manual. Pages affected by the current revision are indicated by an asterisk (*) preceding the pages listed under the Page Number column. Determine which pages are applicable to your airplane under the Configuration Code column. As required by the FAA, only the pages applicable to your airplane should be retained in the basic FAA Approved Airplane Flight Manual. Pages that apply to certain airplanes have the applicable configuration code on the bottom of the page. Pages marked AA apply to all airplanes. Refer to Airplane Configuration Codes on page 1-7/1-8. Following is a description of the Log of Effective Pages columns: Page Number - Basic FAA Approved Airplane Flight Manual Page Numbers. Page Status - Indicates if the page has been added, revised or deleted by the current revision. Revision Number - Indicates the revision number. Configuration Code - Indicates page effectivity by two-letter code. (Continued Next Page) Revision Number Date Revision Number Date Original 30 August 2006 Revision 4 13 April 2007 Revision 1 8 September 2006 Revision 5 2 November 2007 Revision 2 20 November 2006 Revision 6 29 February 2008 Revision 2A 31 January 2007 Revision 7 28 November 2008 Revision 3 9 February 2007 Page Number Page Status Revision Number Configuration Code * Title Revised 7 AA * i thru v/vi Revised 7 AA * Contents Revised 7 AA 1-1/1-2 Original 0 AA * 1-3 thru 1-7/1-8 Revised 7 AA * 2-1/2-2 thru 2-3 Revised 7 AA * 2-4 Revised 7 AB * 2-4.1 Revised 7 AC 2-5 Revised 6 AA * 2-6 thru 2-8 Revised 7 AA 2-9 thru 2-10 Revised 2 AA * 2-11 Revised 7 AA * 2-12 Revised 7 AB * 2-12.1 Revised 7 AC * 2-13 thru 2-16 Revised 7 AA 2-17 Revised 4 AA * 2-18 thru 2-28 Revised 7 AA 510FM-07 i AA LOG OF EFFECTIVE PAGES MODEL 510 U.S. FAA APPROVED Configuration (Continued Next Page) LOG OF EFFECTIVE PAGES (Continued) Page Number Page Status Revision Number Configuration Code * 2-29 Revised 7 AJ * 2-29.1 Added 7 AK * 2-30 Revised 7 AA * 2-31 Revised 7 AH * 2-31.1 Revised 7 AI * 2-32 thru 2-41/2-42 Revised 7 AA * 3-1/3-2 thru 3-4 Revised 7 AA * 3-5/3-6 Revised 7 AB * 3-5.1/3-6 Revised 7 AC * 3-7 thru 3-14 Revised 7 AA * 3-15 Revised 7 AD * 3-15.1 Revised 7 AE * 3-16 Revised 7 AD * 3-16.1 Revised 7 AE * 3-17 thru 3-20 Revised 7 AA * 3-21 Revised 7 AD * 3-21.1 Revised 7 AE 3-22 Revised 5 AD 3-22.1 Revised 5 AE * 3-23 thru 3-31 Revised 7 AA * 3-32 Revised 7 AB 3-32.1 Revised 5 AC * 3-33 Revised 7 AB * 3-33.1 Revised 7 AC 3-34 Revised 5 AB 3-34.1 Revised 5 AC * 3-35 thru 3-36 Revised 7 AL * 3-35.1 thru 3-36.1 Revised 7 AM * 3-35.2 thru 3-36.2 Added 7 AN * 3-35.3 thru 3-36.3 Added 7 AO * 3-37 thru 3-43/3-44 Revised 7 AA * 3-45 Revised 7 AB * 3-45.1 Revised 7 AC * 3-46 Revised 7 AA * 3-47/3-48 Revised 7 AJ * 3-47.1/3-48 Added 7 AK ii 510FM-07 AA MODEL 510 LOG OF EFFECTIVE PAGES U.S. FAA APPROVED Configuration AA (Continued Next Page) LOG OF EFFECTIVE PAGES (Continued) Page Number Page Status Revision Number Configuration Code * 3-49 thru 3-73 Revised 7 AA * 3-74 thru 3-75 Revised 7 AB 3-74.1 Revised 5 AC * 3-75.1 Revised 7 AC 3-76 Revised 5 AB 3-76.1 Revised 5 AC * 3-77/3-78 thru 3-107 Revised 7 AA * 3-108 Revised 7 AJ * 3-108.1 Added 7 AK * 3-109/3-110 thru 3-129/3-130 Revised 7 AA * 3-131 Revised 7 AJ * 3-131.1 Added 7 AK * 3-132 thru 3-133/3-134 Revised 7 AA * 3-135/3-136 Revised 7 AJ * 3-135.1/3-136 Added 7 AK * 3-137 thru 3-142 Revised 7 AA * 3-143 Revised 7 AJ * 3-143.1 Added 7 AK * 3-144 thru 3-153 Revised 7 AA * 3-154 Revised 7 AF * 3-154.1 Revised 7 AG * 3-155 thru 3-156 Revised 7 AA * 3-157 Revised 7 AJ * 3-157.1 Added 7 AK * 3-158 thru 3-160 Revised 7 AA * 3-161 Revised 7 AD * 3-161.1 Revised 7 AE * 3-162 thru 3-174 Revised 7 AA * 3-175 thru 3-177 Added 7 AA * 3-178 Added 7 AF * 3-178.1 Added 7 AG 4-1/4-2 Revised 5 AA 4-3/4-4 Revised 2 AA 4-5 Revised 3 AA 510FM-07 iii LOG OF EFFECTIVE PAGES MODEL 510 U.S. FAA APPROVED Configuration (Continued Next Page) LOG OF EFFECTIVE PAGES (Continued) Page Number Page Status Revision Number Configuration Code 4-6 Revised 6 AA 4-7 Revised 5 AA * 4-8 Revised 7 AA 4-9 thru 4-10 Revised 5 AA * 4-11 Revised 7 AA * 4-12 thru 4-13/4-14 Revised 7 AA 4-15/4-16 Revised 5 AA 4-17 Revised 6 AH 4-17.1 Added 6 AI 4-18 thru 4-23 Original 0 AA 4-24 thru 4-25 Revised 5 AA 4-26 thru 4-35/4-36 Original 0 AA 4-37/4-38 thru 4-39 Revised 5 AA * 4-40 Revised 7 AA 4-41 thru 4-44 Revised 5 AA 4-45 thru 4-60 Revised 6 AH 4-45.1 thru 4-60.1 Added 6 AI 4-61 thru 4-76 Revised 6 AH 4-61.1 thru 4-76.1 Added 6 AI 4-77 thru 4-111 Revised 5 AA 4-112 thru 4-141/4-142 Revised 6 AA 4-143 thru 4-145 Revised 5 AA 4-146 thru 4-207 Revised 6 AA 4-208 thru 4-222 Revised 5 AA 4-223 thru 4-225/4-226 Revised 6 AA 4-227/4-228 thru 4-236 Revised 5 AA 4-237 thru 4-294 Added 5 AA 5-1/5-2 Original 0 AA 6-1/6-2 Revised 6 AA 7-1/7-2 Revised 6 AA * 7-3 Revised 7 AA 7-4 Revised 3 AA 7-5 thru 7-6 Revised 5 AA 7-7 thru 7-22 Revised 6 AH iv 510FM-07 AA MODEL 510 LOG OF EFFECTIVE PAGES U.S. FAA APPROVED Configuration AA LOG OF EFFECTIVE PAGES (Continued) Page Number Page Status Revision Number Configuration Code 7-7.1 thru 7-22.1 Added 6 AI 7-23 thru 7-38 Revised 6 AH 7-23.1 thru 7-38.1 Added 6 AI 7-39 Revised 6 AA 7-40 thru 7-54 Revised 5 AA 7-55 Revised 6 AA 7-56 thru 7-60 Revised 5 AA 7-61 thru 7-76 Added 5 AA 7-77 thru 7-79/7-80 Added 6 AA 510FM-07 v/vi MODEL 510 TABLE OF CONTENTS U.S. FAA APPROVED Configuration TABLE OF CONTENTS PAGE 510FM-07 Contents AA SECTION I SECTION II SECTION III SECTION IV SECTION V SECTION VI SECTION VII INTRODUCTION . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 1-1/1-2 OPERATING LIMITATIONS. . . . . . . . . . . . . . . . . . . . . . . . . . . 2-1/2-2 OPERATING PROCEDURES . . . . . . . . . . . . . . . . . . . . . . . . . 3-1/3-2 PERFORMANCE . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 4-1/4-2 SUPPLEMENTS. . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 5-1/5-2 WEIGHT AND BALANCE DATA . . . . . . . . . . . . . . . . . . . . . . . 6-1/6-2 ADVISORY INFORMATION. . . . . . . . . . . . . . . . . . . . . . . . . . . 7-1/7-2 MODEL 510 SECTION I - INTRODUCTION FAA APPROVED U.S. Configuration INTRODUCTION TABLE OF CONTENTS PAGE Introduction . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 1-3 Coverage . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 1-3 Unit and Serial Number. . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 1-3 Flight Manual Part Number . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 1-3 Revisions . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 1-4 Revised Material Indicators. . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 1-4 Symbols Used For Procedure Division . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 1-4 Definitions . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 1-4 Service Bulletin Configuration List . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 1-6 Airplane Configuration Codes . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 1-7/1-8 1-1/1-2 510FM-00 AA MODEL 510 SECTION I - INTRODUCTION FAA APPROVED U.S. Configuration INTRODUCTION The information in this publication is based on data available at the time of publication and is updated, supplemented, and automatically amended by Service Letters, Service Bulletins, Supplier Service Notices, Publications Changes, Revisions, Reissues, Temporary Revisions, and Temporary Changes that are issued through subscription services available from Citation Service Information. All such amendments become parts of, and are specifically incorporated within this publication. Users are urged to stay current with the latest amendments to this publication through Citation Service Information subscription services and/or Citation Service Centers and Citation Service Stations. COVERAGE The basic FAA Approved Airplane Flight Manual, including supplements in the airplane at the time of delivery from Cessna Aircraft Company, contains information applicable only to that particular airplane. The basic manual is applicable to airplane serial 510-0001 and On. UNIT AND SERIAL NUMBER On all Citation Model 510 airplanes, both the serial and unit numbers are stamped into the airplane identification nameplate. This manual uses serial numbers to describe airplane effectivity. FLIGHT MANUAL PART NUMBER Each page in the basic FAA Approved Airplane Flight Manual contains the part number of the manual and the page status of each page. Refer to the following example: Basic FAA Approved Airplane Flight Manual: 510 FM - 07 Page Status (Revision 7) Manual (Flight Manual) Airplane Model (510) FAA Approved Airplane Flight Manual Supplements: 510 FM - S02 - 01 Page Status (Revision 1) Supplement Number (Supplement 2) Manual (Flight Manual) Airplane Model (510) NOTICE THE SUPPLEMENTS IN SECTION V OF THIS FLIGHT MANUAL CONTAIN AMENDED OPERATING LIMITATIONS, OPERATING PROCEDURES, PERFORMANCE DATA, AND OTHER NECESSARY INFORMATION FOR AIRPLANES CONDUCTING SPECIAL OPERATIONS AND FOR AIRPLANES EQUIPPED WITH SPECIFIC OPTIONS. OPERATORS SHOULD REFER TO SECTION V TO MAKE SURE THAT ALL LIMITATIONS AND PROCEDURES APPROPRIATE FOR THEIR AIRPLANE ARE OBSERVED. 1-3 510FM-07 AA MODEL 510 SECTION I - INTRODUCTION FAA APPROVED U.S. Configuration REVISIONS As new information becomes available for your airplane, revisions will be issued to all registered owners. It is the pilot’s responsibility to make sure that this basic FAA Approved Airplane Flight Manual is complete and current at all times. REVISED MATERIAL INDICATORS A bar will extend the full length of deleted, new or revised text added on new or previously existing pages. This bar will be located adjacent to the applicable text in the margin on the left side of the page. A bar in the footer will indicate a revision to the footer, a new page, format or spelling/grammar changes and/or that information has slipped to or from that page. A bar located adjacent to the figure number in the margin on the left side of the page will be used to indicate that the figure number only has changed. An asterisk located at the end of a figure number will be used to indicate that an illustration has been revised or is all new material (Ex: Figure 3-4* ). All revised pages will carry the revision number opposite the page number on the applicable page. A list of revisions is located at the beginning of the Log of Effective Pages. SYMBOLS USED FOR PROCEDURE DIVISION Symbols are used to mark different parts of procedures. A decision must be made by the pilot to identify the applicable part of the procedure. After the initial choice has been made, a further division of the procedure is possible. In that case, a second choice must be made, etc. When a choice has been made, all remaining actions, consequences, and references are listed. When the procedure is no longer required, this will be indicated by “PROCEDURE COMPLETED”. The division symbols are identified as follows:  FIRST DIVISION • SECOND DIVISION  THIRD DIVISION O FOURTH DIVISION DEFINITIONS Performance definitions are available in Section IV; the remaining definitions are listed as follows: WARNING Operating procedures, techniques, etc., that will result in personal injury or loss of life if not carefully followed. (Continued Next Page) 510FM-07 1-4 AA MODEL 510 SECTION I - INTRODUCTION FAA APPROVED U.S. Configuration DEFINITIONS (Continued) CAUTION CAUTION Operating procedures, techniques, etc., that will result in damage to equipment if not carefully followed. NOTE An operating procedure, technique, etc., that is considered essential to emphasize. LAND AS SOON AS POSSIBLE Land at the nearest suitable airport. Unless reference to alternate Abnormal Before Landing procedures is made, use of Normal Approach and Before Landing procedures is assumed. Extreme situations can require an off airport landing. Primary consideration is safety of occupants. LAND AS SOON AS PRACTICAL Land at a suitable airport. Unless reference to alternate Abnormal Before Landing procedures is made, use of Normal Approach and Before Landing procedures is assumed. The primary consideration is the urgency of the emergency or abnormal situation. Continuing to the destination or an alternate with appropriate service facilities may be an option. EMERGENCY PROCEDURES An emergency procedure is one requiring the use of special systems and/or regular systems in order to protect the occupants and the airplane from serious or critical harm. These procedures usually require immediate action. ABNORMAL PROCEDURES An abnormal procedure is one requiring the use of special systems and/or the alternate use of regular systems that, if followed, will maintain an acceptable level of airworthiness or reduce operational risk resulting from a failure condition. NORMAL PROCEDURES A normal procedure is one that may be thought of as routine in day-to-day flying. CIRCUIT BREAKERS CHECK Make sure the circuit breaker has remained in the normal position or, if it has opened the circuit, push back into the normal position. RESET Place the circuit breaker in the normal position. If the circuit breaker is currently normal, pull to open the circuit then push to reset. 1-5 510FM-07 AA TEMPORARY FAA APPROVED AIRPLANE FLIGHT MANUAL CHANGE In Section I, Introduction, page 1-6, Service Bulletin Configuration List, change the software version and serial effectivity for SB510-34-09 as shown below and add SB510-34-11: Publication Affected: Model 510 Citation Mustang (510-0001 and On) basic FAA Approved Airplane Flight Manual, Revision 7, dated 21 November 2008. Airplane Serial Numbers Affected: Airplanes 510-0001 and On. Description of Change: Section I, Introduction, Service Bulletin Configuration List, change a Service Bulletin and add a Service Bulletin. Filing Instructions: Insert this temporary change in the Model 510 (510-0001 and On) basic FAA Approved Airplane Flight Manual adjacent to page 1-6. Removal Instructions: This temporary change replaces 510FM TC-R07-04 in its entirety. This temporary change must be removed and discarded when Revision 8 has been collated into the basic FAA Approved Airplane Flight Manual. Number Title Airplane Serial Effectivity Revision Incorporated Incorporated in Airplane SB510-34-09 Navigation - Garmin G1000 Software Version 010-00435-16 Upgrade. 510-0001 thru -0177 7 SB510-34-11 Navigation - Garmin G1000 Software Version 010-00435-21 Upgrade. 510-0001 thru -0371 510FM TC-R07-15 MODEL 510 SECTION I - INTRODUCTION FAA APPROVED U.S. Configuration SERVICE BULLETIN CONFIGURATION LIST The following is a list of Service Bulletins that are applicable to the operation of the airplane, and have been incorporated into this manual. This list contains only those Service Bulletins that are currently active. Number Title Airplane Serial Effectivity Revision Incorporated Incorporated in Airplane SB510-03-01 Certification Requirements - FAA to EASA Registration Conversion. 510-0001 thru -0020 4 SB510-34-02 Navigation - Hardware and Software Update for Garmin G1000 Avionics. 510-0001 thru -0065 6 SB510-34-09 Navigation - Garmin G1000 Software Version 010-00435-13 Upgrade. 510-0001 thru -0152 7 510FM-07 1-6 AA TEMPORARY FAA APPROVED AIRPLANE FLIGHT MANUAL CHANGE This Page Intentionally Left Blank 510FM TC-R07-12 TEMPORARY FAA APPROVED AIRPLANE FLIGHT MANUAL CHANGE In Section I, Introduction, page 1-7/1-8, Airplane Configuration Codes, change the serial effectivity of configuration codes AJ and AK as follows: Publication Affected: Model 510 Citation Mustang (510-0001 and On) basic FAA Approved Airplane Flight Manual, Revision 7, dated 21 November 2008. Airplane Serial Numbers Affected: Airplanes 510-0001 and On. Description of Change: Section I, Introduction, Airplane Configuration Codes, change the serial effectivity for a configuration set. Filing Instructions: Insert this temporary change in the Model 510 (510-0001 and On) basic FAA Approved Airplane Flight Manual adjacent to page 1-7/1-8. Removal Instructions: This temporary change must be removed and discarded when Revision 8 has been collated into the basic FAA Approved Airplane Flight Manual. Configuration Code Effectivity by Serial Number Applicable Configuration Code AJ Airplanes 510-0001 thru -0177 incorporating SB510-34-09 and Airplanes 510-0178 and On. AK Airplanes 510-0001 thru -0177 not incorporating SB510-34-09. 510FM TC-R07-12 MODEL 510 SECTION I - INTRODUCTION FAA APPROVED U.S. Configuration AIRPLANE CONFIGURATION CODES The following is a list of airplane configuration codes that appear at the bottom of each page of 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 the basic FAA Approved Airplane Flight Manual. From each grouping, identify and record the configuration code that applies to your airplane, then select and insert the correct pages into this FAA Approved Airplane Flight Manual. Configuration Code Effectivity by Serial Number Applicable Configuration Code AA Airplanes 510-0001 and On. AB Airplanes 510-0001 and On with NiCad battery option. AC Airplanes 510-0001 and On without NiCad battery option. AD Airplanes 510-0001 thru -0020 incorporating SB510-03-01 and Airplanes 510-0021 and On. AE Airplanes 510-0001 thru -0020 not incorporating SB510-03-01. AF Airplanes 510-0041 and On (Airplanes with Multifunction Change and Cabin Altitude Module Improvement). AG Airplanes 510-0001 thru -0040 (Airplanes without Multifunction Change and Cabin Altitude Module Improvement). AH Airplanes 510-0001 thru -0065 incorporating SB510-34-02 and Airplanes 510-0066 and On. AI Airplanes 510-0001 thru -0065 not incorporating SB510-34-02. AJ Airplanes 510-0001 thru -0152 incorporating SB510-34-09 and Airplanes 510-0153 and On. AK Airplanes 510-0001 thru -0152 not incorporating SB510-34-09. AL Airplanes 510-0001 thru -0020 incorporating SB510-03-01 and incorporating SB510-34-09 and Airplanes 510-0021 thru -0152 incorporating SB510-34-09 and Airplanes 510-0153 and On. AM Airplanes 510-0001 thru -0020 incorporating SB510-03-01, not incorporating SB510-34-09 and Airplanes 510-0021 thru -0152 not incorporating SB510-34-09 AN Airplanes 510-0001 thru -0020 not incorporating SB510-03-01, incorporating SB510-34-09. AO Airplanes 510-0001 thru -0020 not incorporating SB510-03-01 or SB510-34-09. 1-7/1-8 510FM-07 AA MODEL 510 SECTION II - OPERATING LIMITATIONS FAA APPROVED U.S. Configuration OPERATING LIMITATIONS TABLE OF CONTENTS PAGE Certification Status . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 2-3 Operations Authorized . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 2-3 Weight Limitations. . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 2-3 Center-of-Gravity Limitations . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 2-4 Weight and Balance Data . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 2-4 Powerplant Limitations . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 2-4 Engine Start Limitations . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 2-4 FADEC (Full Authority Digital Engine Control) . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 2-11 Engine Fan Inspection . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 2-11 Engine Start Limitations (Air) . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 2-12 Starter Cycle Limitations . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 2-12 Ground Power Unit Limitations for Starting . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 2-12 Battery Limitations . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 2-12 Electrical Power System . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 2-13 Hydraulic Power System. . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 2-13 Landing Gear and Tire Limitations . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 2-13 Ground Operation . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 2-14 Fuel Limitations. . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 2-14 Unusable Fuel. . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 2-14 Approved Oils . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 2-15 Speed Limitations . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 2-16 Takeoff and Landing Operational Limitations . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 2-18 Enroute Operational Limits . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 2-19 Minimum Crew . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 2-21 Load Factor. . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 2-21 Cabin Pressurization Limits . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 2-22 Maneuver Limitations . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 2-22 Passenger Compartment . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 2-22 Baggage Compartments . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 2-22 Vortex Generators and Static Wicks . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 2-22 EICAS and Instrument Markings. . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 2-23 Supplemental Oxygen System . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 2-28 Stall Warning and Low Speed Awareness Systems . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 2-28 Garmin G1000 System . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 2-29 Garmin G1000 GPS Navigation System. . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 2-30 Standby Instruments . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 2-32 AHRS Areas of Operation. . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 2-32 Ice and Rain Protection. . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 2-32 Operations in Severe Icing Conditions . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 2-33 Kinds of Operations Equipment List . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 2-34 2-1/2-2 510FM-07 AA MODEL 510 SECTION II - OPERATING LIMITATIONS FAA APPROVED U.S. Configuration OPERATING LIMITATIONS CERTIFICATION STATUS This airplane is certified in accordance with 14 CFR, Part 23 Normal Category, Part 34 (Fuel Venting and Exhaust Emissions), Part 36 (Noise Requirements) and Special Conditions as prescribed by the Administrator. OPERATIONS AUTHORIZED This airplane is approved for day and night, VFR and IFR operations, and flight into known icing conditions when the required equipment is installed as defined within the Kinds of Operations Equipment List. This airplane is approved for operations in Reduced Vertical Separation Minimum (RVSM) airspace when required equipment is maintained in accordance with the airplane Maintenance Manual. This does not constitute operational approval. Operational approval must be obtained in accordance with applicable operating rules. Acrobatic maneuvers, including spins, are prohibited. Intentional stalls are prohibited above 18,000 feet. WEIGHT LIMITATIONS Maximum Design Ramp Weight . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 8730 Pounds Maximum Design Takeoff Weight . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 8645 Pounds Maximum Design Landing Weight . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 8000 Pounds Maximum Design Zero Fuel Weight . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 6750 Pounds Minimum Weight in RVSM Airspace . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 6300 Pounds Takeoff weight is limited by the most restrictive of the following requirements: Maximum Certified Takeoff Weight (Flaps - TAKEOFF/APPROACH). . . . . . . . . . . . 8645 Pounds Maximum Takeoff Weight Permitted by Climb Requirements. . . . . . . . . . . . . . . . . . . . . . Refer to Section IV, Performance, TAKEOFF Takeoff Field Length . . . . . . . . . . . . . . . . . . . . . . . . Refer to Section IV, Performance, TAKEOFF Landing weight is limited by the most restrictive of the following requirements: Maximum Certified Landing Weight . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 8000 Pounds Maximum Landing Weight Permitted by Climb Requirements or Brake Energy Limits. . . . . Refer to Section IV, Performance, APPROACH AND LANDING Landing Distance . . . . . . . . . . . Refer to Section IV, Performance, APPROACH AND LANDING NOTICE CERTIFICATION AND OPERATIONAL LIMITATIONS ARE CONDITIONS OF THE TYPE AND AIRWORTHINESS CERTIFICATES AND MUST BE COMPLIED WITH AT ALL TIMES AS REQUIRED BY LAW. 2-3 510FM-07 AA MODEL 510 SECTION II - OPERATING LIMITATIONS FAA APPROVED U.S. Configuration CENTER-OF-GRAVITY LIMITATIONS Center-of-Gravity Moment Envelope . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .Refer to Figure 2-1 WEIGHT AND BALANCE DATA The airplane must be operated in accordance with the approved loading schedule. Refer to the Model 510 Weight and Balance Manual (510WB-00 or latest revision). POWERPLANT LIMITATIONS Engine Type . . . . . . . . . . . . . . . . . . . . . . . . . . . Pratt and Whitney Canada Inc. PW615F-A Turbofan Engine Operating Limits . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .Refer to Figure 2-2 Engine Inter-Turbine Temperature (ITT) Limits. . . . . . . . . . . . . . . . . . . . Refer to Figures 2-3 and 2-4 Engine Overspeed Limits . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . Refer to Figures 2-5 and 2-6 Engine Oil Pressure Limits . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .Refer to Figure 2-7 Takeoff/Go-Around Thrust (TO Detent). . . . . . . . . . . . . . . . . . . . . . . . Refer to Figures 4-13 and 4-14 Maximum Continuous Thrust, Single-Engine (CLB Detent) . . . . . . . . Refer to Figures 4-15 and 4-16 Maximum Continuous Thrust, Multi-Engine (CLB Detent) . . . . . . . . . Refer to Figures 4-17 and 4-18 ENGINE START LIMITATIONS Inter-Turbine Temperature (ITT) Limits . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .Refer to Figure 2-3 Maximum Tailwind Component. . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .10 Knots Maximum Quartering Tailwind (Within Tailwind Component Limits) . . . . . . . . . . . . . . . . . . . .15 Knots Maximum Crosswind Component. . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .25 Knots Maximum Time to Light-off . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 10 Seconds Maximum Time to Stabilized Idle (Ground or In-Flight/Starter Assist) . . . . . . . . . . . . . . . 45 Seconds Maximum Time to Stabilized Idle (In-Flight/Windmilling) . . . . . . . . . . . . . . . . . . . . . . . . . 90 Seconds NOTE Time to light-off is defined as the time after the throttle lever is moved from CUTOFF to IDLE detent and an increase in ITT is observed. Minimum Engine Oil Temperature (as indicated on EICAS) . . . . . . . . . . . . . . . . . . . . . . . . . . . -40°C NOTE • If engine oil temperature is below -40°C (-40°F), the engine must be preheated prior to conducting a start. • If the battery has been cold soaked for 2 hours or longer at ambient surface temperature of -18°C (0°F) or lower, it must be preheated to above -18°C (0°F) prior to start. • The Engine Indicating System may take up to 10 minutes to become usable after power is applied when cold soaked below -40°C (-40°F). Maximum Temperature For Engine Start . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .Refer to Figure 2-13 Maximum Airport Elevation For Ground Battery Start. . . . . . . . . . . . . . . . . . . . . . . . . . . . 10,000 Feet Maximum Airport Elevation For Ground Power Unit Start . . . . . . . . . . . . . . . . . . . . . . . . 14,000 Feet Minimum Battery Voltage For Battery Start. . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 24 Volts 510FM-07 2-4.1 AC MODEL 510 SECTION II - OPERATING LIMITATIONS FAA APPROVED U.S. Configuration CENTER-OF-GRAVITY LIMITATIONS Figure 2-1 2-5 510FM-06 AA MODEL 510 SECTION II - OPERATING LIMITATIONS FAA APPROVED U.S. Configuration ENGINE OPERATING LIMITS Figure 2-2 NOTE 1. The total time during which takeoff thrust may be used is limited to 5 minutes per flight. The 5-minute time limit commences when the throttle is first advanced to the TO detent. This time may be extended to 10 minutes for one engine inoperative operation. The takeoff thrust (N 1) for the airplane is defined in Figures 4-13 and 4- 14 and is more limiting than engine rotational limits and must be observed. Performance data including V MCA and V MCG in Section IV, is based on use of the appropriate takeoff thrust setting. 2. Maximum continuous thrust (CLB detent) for the airplane is defined by Figures 4-15 and 4-16 (single-engine) and Figures 4-17 and 4-18 (multi-engine). These thrust settings (N1) are more limiting than engine rotational limits and must be observed. Performance data in Section IV is based on the use of the appropriate maximum continuous thrust setting. 3. Oil temperature must be above 22°C for at least 5 minutes before takeoff. Once oil temperature is +10°C or warmer, it is acceptable to increase power-up to the CRU detent to decrease the time required to warm the oil to 22°C. 4. Idle speed is a function of ambient pressure and temperature. 5. After initiation of the start cycle, oil pressure should indicate a steady increase within 20 seconds of the start of N 2 rotation. OPERATING CONDITION OPERATING LIMITS THRUST SETTING TIME LIMIT (MINUTES) ITT TEMPERATURE °C N 2 % N 1 % OIL PRESSURE PSI OIL TEMPERATURE °C START --- 862 SEE FIGURE 2-3 --- --- 0 TO 250 (NOTE 5) -40 MINIMUM GND IDLE CONTINUOUS --- 48.6 --- 24 MINIMUM -40 TO 135 (NOTE 3) FLT IDLE CONTINUOUS --- 56.8 (MINIMUM) (NOTE 4) --- SEE FIGURE 2-7 22 TO 135 TAKEOFF (TO DETENT) 5 (NOTE 1) 830 100.0 100.0 (NOTE 1) SEE FIGURE 2-7 22 TO 135 (NOTE 3) MAXIMUM CONTINUOUS (CLB DETENT) CONTINUOUS 830 100.0 100.0 (NOTE 2) SEE FIGURE 2-7 22 TO 135 MAXIMUM CRUISE (CRU DETENT) CONTINUOUS 830 100.0 100.0 SEE FIGURE 2-7 22 TO 135 TRANSIENT 20 SECONDS 862 SEE FIGURE 2-4 102.0 SEE FIGURE 2-5 101.0 SEE FIGURE 2-6 --- --- 90 SECONDS --- --- --- SEE FIGURE 2-7 135 TO 141 15 / 500 SECONDS --- --- --- SEE FIGURE 2-7 --- 510FM-07 2-6 AA MODEL 510 SECTION II - OPERATING LIMITATIONS FAA APPROVED U.S. Configuration OVERTEMPERATURE LIMITS - STARTING Figure 2-3 2-7 510FM-07 AA MODEL 510 SECTION II - OPERATING LIMITATIONS FAA APPROVED U.S. Configuration OVERTEMPERATURE LIMITS - EXCEPT STARTING Figure 2-4 510FM-07 2-8 AA MODEL 510 SECTION II - OPERATING LIMITATIONS FAA APPROVED U.S. Configuration N2 ENGINE OVERSPEED LIMITS Figure 2-5* 2-9 510FM-02 AA MODEL 510 SECTION II - OPERATING LIMITATIONS FAA APPROVED U.S. Configuration N1 ENGINE OVERSPEED LIMITS Figure 2-6* 510FM-02 2-10 AA MODEL 510 SECTION II - OPERATING LIMITATIONS FAA APPROVED U.S. Configuration ENGINE OIL PRESSURE LIMITS Figure 2-7 FADEC (FULL AUTHORITY DIGITAL ENGINE CONTROL) Dispatch with an engine FADEC fault (ENG CTRL SYS L or R message displayed) is prohibited. ENGINE FAN INSPECTION Prior to engine start, the Engine Fan Duct and Fan inspection in Section III, Normal Procedures, must be satisfactorily completed. 2-11 510FM-07 AA MODEL 510 SECTION II - OPERATING LIMITATIONS FAA APPROVED U.S. Configuration ENGINE START LIMITATIONS (AIR) Inter-Turbine Temperature (ITT) Limits . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .Refer to Figure 2-3 Airspeed/Altitude Limits . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .Refer to Figure 3-1 Minimum Temperature for Windmill Start . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . -10°C RAT STARTER CYCLE LIMITATIONS Starter Cycle Limitation. . . . . . . . . . . .Three engine starts per 30 minutes. Three cycles of operation with a 60-second rest period between cycles is permitted. NOTE This limitation is independent of starter power source (i.e., battery, generator-assisted cross start, or ground power unit) and applies to both starting and dry motoring of the engine. GROUND POWER UNIT LIMITATIONS FOR STARTING Minimum/Maximum Current . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 800/1100 Amps Maximum Voltage . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 29 VDC CAUTION CAUTION Normal starter current draw is approximately 1000 amps peak. Ground power units with variable maximum current shutoff should be set to 1100 amps. Use of a ground power source with voltage in excess of 29 VDC or current in excess of 1100 amps may damage the starter. BATTERY LIMITATIONS Battery Start Limitation . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . Three engine starts per hour Minimum Voltage for Start. . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 24 Volts CAUTION CAUTION Battery starts are prohibited at airport elevations above 10,000 feet. Above 10,000 feet, engines must be started using a ground power unit or using a generator assisted cross start. NOTE • If battery limitation is exceeded, ground maintenance procedures are required. Refer to Chapter 24 of the Maintenance Manual for procedure. • Three generator-assisted cross starts are equal to one battery start. • If a ground power unit is used for start, no battery cycle is counted. 510FM-07 2-12.1 AC MODEL 510 SECTION II - OPERATING LIMITATIONS FAA APPROVED U.S. Configuration ELECTRICAL POWER SYSTEM Generator limits are as listed in Figure 2-8. Figure 2-8 NOTE The above limits are steady state limits. Following an engine battery start, generator current may exceed 150 amps at ground idle for up to 5 minutes while the battery is recharging. Above idle or during flight, transients up to 450 amps are permitted for up to 2 minutes. HYDRAULIC POWER SYSTEM T he only approved hydraulic fluid for the hydraulic power system is MIL-PRF-87257 . LANDING GEAR AND TIRE LIMITATIONS The only approved hydraulic fluid for the landing gear struts is MIL-PRF-87257. The tires listed in Figure 2-9 are the only tires approved. Tires must be inflated to the pressure shown. NOTE If the ground operating temperature is expected to drop more than 28°C (50°F) or the arrival airfield is expected to be more than 28°C (50°F) colder than the departure airfield, refer to the Airplane Maintenance Manual for tire servicing. Figure 2-9 STATUS LIMIT On Ground, Idle 150 Amps On Ground, Above Idle 300 Amps Air < 30,000 Feet 300 Amps Air > 30,000 Feet 280 Amps POSITION VENDOR PART NUMBER UNLOADED PRESSURE LOADED PRESSURE Nose Tire Michelin 079-606-0 120 ± 5 PSIG 125 ± 5 PSIG Dunlop DR17026T 120 ± 5 PSIG 125 ± 5 PSIG Main Tires Michelin 021-523-0 85 ± 5 PSIG 88 ± 5 PSIG Dunlop DR25526T 85 ± 5 PSIG 88 ± 5 PSIG 2-13 510FM-07 AA TEMPORARY FAA APPROVED AIRPLANE FLIGHT MANUAL CHANGE In Section II, Operating Limitations, Fuel Limitations, page 2-14, update the Fuel Limitations section as shown below: FUEL LIMITATIONS The corresponding electric fuel boost pump must be turned ON when the FUEL LO L-R CAS message is displayed or at 170 pounds or less of indicated fuel in either tank. Maximum approved fuel imbalance is 200 pounds. NOTE An emergency fuel imbalance of 600 pounds has been demonstrated for safe return and landing. Minimum fuel quantity for takeoff is 200 pounds per wing. Figure 2-10 lists the fuel temperature limitations for each approved fuel. The fuel tank temperature indication on EICAS does not monitor for fuel temperature out of limits. APPROVED FUELS Figure 2-10 (Continued Next Page) Publication Affected: Model 510 Citation Mustang (510-0001 and On) basic FAA Approved Airplane Flight Manual, Revision 7, dated 21 November 2008. Airplane Serial Numbers Affected: Airplanes 510-0001 and On. Description of Change: Section II, Operating Limitations, Fuel Limitations, update the section. Filing Instructions: Insert this temporary change in the Model 510 (510-0001 and On) basic FAA Approved Airplane Flight Manual adjacent to page 2-14. Removal Instructions: This temporary change must be removed and discarded when Revision 8 has been collated into the basic FAA Approved Airplane Flight Manual. APPROVED FUEL GRADES (TYPE) FUEL ADDITIVES (REFER TO NOTES BELOW) SPECIFICATION MINIMUM FUEL TEMPERATURE °C MAXIMUM FUEL TEMPERATURE °C JET A 1, 5, 7 and 8 ASTM-D1655 -35 50 JET A-1 1, 5, 7 and 8 ASTM-D1655 -35 50 Jet No. 3 1, 4, and 5 GB6537 -35 50 JP-8 1, 5, 7 and 8 MIL-DTL-83133 -35 50 RT 2, 3, 5, 6, 7 and 8 GOST 10227 -35 50 RT (Ukraine) 2, 3, 5, 6, 7 and 8 GSTU 320.00149943.007 -35 50 TS-1 2, 3, 5, 6, 7 and 8 GOST 10227 -35 50 TS-1 (Ukraine) 2, 3, 5, 6, 7 and 8 GSTU 320.00149943.011 -35 50 510FM TC-R07-23 TEMPORARY FAA APPROVED AIRPLANE FLIGHT MANUAL CHANGE FUEL LIMITATIONS (Continued) NOTE The following optional fuel system additives may be added to the fuels as noted at the following concentrations. Use of these fuel additives is not required. Refer to Section III, Normal Procedures, ANTI-ICE ADDITIVES for blending instructions. 1. MIL-DTL-85470 (DiEGME) in a concentration of 0.10 to 0.15 percent by volume 2. GOST 8313 (Fluid I) in a concentration of 0.10 to 0.30 percent by volume 3. A mixture of 50% GOST 8313 (Fluid I) and 50% CIS TU6-10-1458 (Fluid I-M) in a concentration of 0.10 to 0.30 percent by volume 4. T1301 per SH0396-92 (EGME) in a concentration of 0.10 to 0.15 percent by volume 5. DuPont Stadis 450 as required to bring fuel up to 300 conductive units, not to exceed 3 ppm (parts per million) 6. Sigbol as required to bring fuel up to 300 conductive units, not to exceed 3 ppm 7. Biobor JF at a concentration not to exceed 270 ppm 8. Kathon FP 1.5 at a concentration not to exceed 100 ppm 510FM TC-R07-23 MODEL 510 SECTION II - OPERATING LIMITATIONS FAA APPROVED U.S. Configuration GROUND OPERATION Continuous engine ground static operation up to and including 5 minutes at takeoff thrust is limited to ambient temperatures defined in Figure 2-13. Limit ground operation of pitot-static heat to 2 minutes to preclude damage to the pitot tubes and stall warning vane. Movement of the flaps is prohibited at temperatures colder than -40°C. FUEL LIMITATIONS The corresponding electric fuel boost pump must be turned ON when the FUEL LO L-R CAS message is displayed or at 170 pounds or less of indicated fuel in either tank. Maximum approved fuel imbalance is 200 pounds. An emergency fuel imbalance of 600 pounds has been demonstrated for safe return and landing. Minimum fuel quantity for takeoff is 200 pounds per wing. Figure 2-10 lists the fuel temperature limitations for each approved fuel. NOTE • The fuel tank temperature indication on EICAS does not monitor for fuel temperature out of limits. • Dupont Stadis 450 antistatic additive or equivalent is permitted to bring fuel up to 300 conductive units, but not to exceed 3 ppm (parts per million) by weight. • SOHIO Biobor JF biocide additive is approved at a concentration not to exceed 270 ppm by weight. • EGME/DIEGME anti-icing additive is approved for use, but not required, at a concentration not to exceed 0.15% by volume. Refer to Normal Procedures, ANTI-ICE ADDITIVES for blending instructions. Figure 2-10 UNUSABLE FUEL Unusable fuel is the fuel remaining in the fuel tanks when the fuel quantity indicator reads zero. This fuel is not usable in flight. GRADE (TYPE) SPECIFICATION MINIMUM FUEL TEMPERATURE °C (°F) JET A, JET A-1 ASTM-D1655 -35 (-31) RP-3 (JET No. 3) GB 6537-94 (China) -35 (-31) JP-8 MIL-T-83133 -35 (-31) 510FM-07 2-14 AA MODEL 510 SECTION II - OPERATING LIMITATIONS FAA APPROVED U.S. Configuration APPROVED OILS The following oils are approved for use: * Oils denoted with an asterisk are “THIRD GENERATION” lubricants. In addition, oils listed for the engine in the latest revision to PW615F Maintenance Manual (P/N 3059712) are approved. CAUTION CAUTION When changing from an existing lubricant formulation to a “third generation” lubricant formulation, the engine manufacturer strongly recommends that such a change should only be made when an engine is new or freshly overhauled. For additional information on use of third generation oils, refer to engine manufacturer’s pertinent oil service bulletins. Figure 2-11 Maximum oil consumption is 1 U.S. quart per 13.5-hour period. If oil consumption exceeds this amount, refer to the Pratt and Whitney PW615F-A Maintenance Manual. The oil level must be serviced to the MAX indication on the sight glass for any flight planned to exceed 5 hours in duration. Should it be necessary to replenish oil consumption losses when oil of the same brand (as tank contents) is unavailable, then the following requirements apply: For contingency purposes, oil replenishment using any other approved oil brand listed is acceptable provided: • The total quantity of added oil does not exceed 2 U.S. quarts in any 400-hour period. • If it is required to add more than 2 U.S. quarts of dissimilar oil brands, drain and flush complete oil system and refill with an approved oil in accordance with Engine Maintenance Manual instructions. Should oils of non-approved brands or of different viscosities become intermixed, drain and flush complete oil system and refill with an approved oil in accordance with Engine Maintenance Manual instructions. MOBIL JET OIL II AIR BP / EXXON 2380 MOBIL JET OIL 254* AIR BP / EXXON 2197* ROYCO TURBINE OIL 500 AEROSHELL TURBINE OIL 500 ROYCO TURBINE OIL 560* AEROSHELL TURBINE OIL 560* TurboNycoil TN 600 CASTROL 5000 2-15 510FM-07 AA MODEL 510 SECTION II - OPERATING LIMITATIONS FAA APPROVED U.S. Configuration SPEED LIMITATIONS Maximum Operating Limit Speeds: V MO (Between Sea Level and 27,120 Feet) . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 250 KIAS MMO (Above 27,120 Feet) . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 0.63 Mach (Indicated) NOTE The maximum operating limit speeds may not be deliberately exceeded in any regime of flight (climb, cruise or descent) unless a higher speed is authorized for flight test or pilot training. Maximum Operating Maneuvering Speeds - VO . . . . . . . . . . . . . . . . . . . . . . . . . .Refer to Figure 2-12 WARNING Avoid rapid and large alternating control inputs, especially in combination with large changes in pitch, roll, or yaw (i.e., large sideslip angles) as they may result in structural failures at any speed, including below VO . NOTE Full application of rudder and aileron controls, as well as maneuvers that involve angle-of-attack near the stall, should be confined to speeds below maximum maneuvering speed. EXAMPLE PROBLEM: Refer to Figure 2-12 PRESSURE ALTITUDE - 35,000 FEET WEIGHT - 8,000 POUNDS MAXIMUM MANEUVERING SPEED - 158 KNOTS Maximum Flap Extended Speed - V FE TAKEOFF / APPROACH Detent (15°) . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 185 KIAS LAND Position (30°) . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 150 KIAS Maximum Landing Gear Extended Speed - V LE . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 250 KIAS Maximum Landing Gear Operating Speed - V LO (Extending). . . . . . . . . . . . . . . . . . . . . . . . 250 KIAS Maximum Landing Gear Operating Speed - V LO (Retracting) . . . . . . . . . . . . . . . . . . . . . . . 185 K