PFTL 101BER-2.0工控DCS系统备件
温度图（见第5.15小节）。字段长度考虑因素允许的最大值（见第5.20小节）。最大制动能量考虑因素允许的最大值（见第5.20小节）。障碍物清除考虑因素允许的最大值（见第5.25分节）。着陆重量最大着陆重量受以下最严格的限制：23350磅（10591千克）。如高度和温度最大着陆重量图所示（见第5.45小节）。字段长度考虑因素允许的最大值（见第5.50小节）。第4页第2节限制FAA批准的修订版A3:2005年3月22日Hawker 800XP Pro Line 21飞机飞行手册起飞场长度起飞重量不得超过第5.20小节所述的限制条件范围内场长度考虑因素允许的最大值。当符合上述要求时，应满足以下条件：图表中使用的起飞距离不应大于跑道长度加上净空长度（如有），但净空长度不应超过跑道长度的一半。图表中使用的起飞距离不得大于跑道长度。操作限制海拔高度起飞或着陆时的最大/最小场压海拔高度13000英尺和-2000英尺注：当场压海拔低于最低公布海拔高度时，应使用适用于最低公布海拔的性能。最大允许高度最大允许操作高度为41000英尺。襟翼放下或起落架伸展时的最大允许高度为20000英尺。所有飞行模式的最高气温ISA+35°C地面（发动机启动前）：暴露在阳光直射下的飞行舱（天空云层覆盖率低于10%），配有飞行舱遮阳板ISA+35℃，无飞行舱遮阳罩。ISA+31°C暴露在间接阳光下的飞行舱（云层超过10%的天空）ISA+35°C注意：如果使用了遮阳板，则应安装足够数量的遮阳板以保护整个飞行舱。最小起飞/着陆-40°C航路-75°C注：当温度低于最低计划温度时，应使用适合最低计划温度的性能。风分量适用于33英尺（10.1米）高度的起飞和着陆的最大顺风分量为10节。第5页第2节限制FAA批准版本A3：2005年3月22日Hawker 800XP Pro Line 21飞机飞行手册跑道坡度起飞时的最大有效跑道坡度为2%上坡和2%下坡。飞机配置必须遵守第5.05小节中规定的飞机配置。机舱装载限制飞机必须按照本《飞机飞行手册》第6节“重量和平衡”以及行李/积载舱标牌上的规定进行装载。载荷限制重心限制重心必须始终位于图2.1和2.2所示包络线中定义的前后极限之间。这些极限在起落架升起时适用。起落架在下降位置的影响可以忽略不计。重心基准位于机身参考点前方11英尺（3.4米）处。参考点由位于右发动机舱下方的机身蒙皮上的螺钉定义。第6页第2节FAA批准的A3版限制：2005年3月22日Hawker 800XP Pro Line 21飞机飞行手册装载和飞行包线-磅/英尺（起落架回缩力矩变化可忽略不计）标准平均弦长百分比，2005年Hawker 800XP Pro Line 21飞机飞行手册装载和飞行包线-公里/米标准平均弦长百分比（起落架回缩力矩变化可忽略不计）图2.2第8页第2节限制FAA批准的修订版A3:2005年3月22日Hawker 800XPPro Line 21飞机飞行手册故意留空第2页，共3页P/N
TEMPERATURE graphs (see Sub-section 5.15).The maximum permitted by field length considerations (see Sub-section 5.20).The maximum permitted by maximum brake energy considerations (see Sub-section 5.20).The maximum permitted by obstacle clearance considerations (see Sub-section 5.25). Landing Weight Maximum Landing Weight is limited by the most restrictive of the following:23,350 lb (10,591 kg).As shown on the MAXIMUM LANDING WEIGHT FOR ALTITUDE AND TEMPERATURE graph (see Sub-section 5.45).The maximum permitted by field length considerations (see Sub-section 5.50). Page 4 Section - 2 LIMITATIONS FAA Approved Revision A3: Mar 22, 2005 Hawker 800XP Pro Line 21 Airplane Flight Manual Take-off Field Length The take-off weight shall not exceed the maximum permitted by field length considerations as described in Sub-section 5.20 for the restricted range of conditions listed. When complying with the above, the following conditions shall be met:The take-off distance used in the graphs shall not be greater than the length of runway plus the length of clearway if present, except that the length of clearway shall not be greater than one-half of the length of the runway.The take-off run used in the graphs shall not be greater than the length of the runway. OPERATIONAL LIMITATIONS Altitude Maximum/Minimum field pressure altitudes for takeoff or landing13,000 ft and -2000 ft NOTE: Performance appropriate to the lowest published elevation shall be used when the field pressure altitude is below the lowest published elevation. Maximum Permissible Altitude Maximum permissible operating altitude is 41,000 ft. Maximum permissible altitude with flaps lowered or landing gear extended is 20,000 ft. Air Temperature Maximum All Flight Regimes ISA +35° C Ground (prior to engine start): Flight compartment exposed to direct sunlight (sky with less than 10% cloud cover)With flight compartment sunshields ISA +35° CWithout flight compartment sunshields. ISA +31° C Flight compartment exposed to indirect sunlight (sky with more than 10% cloud cover)ISA +35° C NOTE: If sunshields are utilized, a sufficient quantity shall be installed to protect the entire flight compartment. MinimumTakeoff/Landing -40° CEnroute. -75° C NOTE: When the temperature is below the lowest scheduled, performance appropriate to the lowest scheduled temperature shall be used. Wind Component The maximum tailwind component for takeoff and landing appropriate to a height of 33 ft (10.1 m) is 10 knots. Page 5 Section - 2 LIMITATIONS FAA Approved Revision A3: Mar 22, 2005 Hawker 800XP Pro Line 21 Airplane Flight Manual Runway Slope The maximum effective runway slopes for takeoff are 2% uphill and 2% downhill. Airplane Configurations The airplane configurations as stated in Sub-section 5.05 must be observed. COMPARTMENT LOADING LIMITATIONS The airplane must be loaded in accordance with Section 6 - WEIGHT & BALANCE of this Airplane Flight Manual and as provided on placards in the Baggage/Stowage Compartments. LOAD LIMITATIONS Center Of Gravity Limitations The center of gravity must always lie between the forward and aft limits as defined in the envelope shown in Figures 2.1 and 2.2. The limits apply with the landing gear up. The effect of the landing gear in the down position is negligible. The center of gravity datum is 11 ft (3.4 m) forward of the reference point on the fuselage. The reference point is defined by a screw on the fuselage skin located beneath the right engine pod. Page 6 Section - 2 LIMITATIONS FAA Approved Revision A3: Mar 22, 2005 Hawker 800XP Pro Line 21 Airplane Flight Manual LOADING and FLIGHT ENVELOPE - POUNDS/FEET (Landing Gear Retraction Moment Change is Negligible) Percent Standard Mean Chord Figure 2.1 Page 7 Section - 2 LIMITATIONS FAA Approved Revision A3: Mar 22, 2005 Hawker 800XP Pro Line 21 Airplane Flight Manual LOADING and FLIGHT ENVELOPE - KILOGRAMS/METERS Percent Standard Mean Chord (Landing Gear Retraction Moment Change is Negligible) Figure 2.2 Page 8 Section - 2 LIMITATIONS FAA Approved Revision A3: Mar 22, 2005 Hawker 800XP Pro Line 21 Airplane Flight Manual Intentionally left blank Page 2 of 3 P/N
