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Airworthiness Directive ScheduleGlidersStemme S10 Series31 August 2022Notes 1.This AD schedule is applicable to Stemme S10 series gliders manufactured under EASA Type Certificate Numbers:AircraftModel: EASA Type Certificate No: Manufacturer:S 10 A.054 (formerly LBA TC No. 846) Stemme AGS 10-V A.054 (formerly LBA TC No. 846) Stemme AGS 10-VT A.054 (formerly LBA TC No. 846) Stemme AG2.The European Union Aviation Safety Agency (EASA) is the National AirworthinessAuthority (NAA) responsible for the issue of State of Design Airworthiness Directives(ADs) for these gliders. State of Design ADs can be obtained directly from the EASAwebsite at http://ad.easa.europa.eu/3. The date above indicates the amendment date of this schedule.4. New or amended ADs are shown with an asterisk*ContentsDCA/STEMME/1Air Brake Eye Bolt – Replacement, and Landing Gear Door - Inspection (2)DCA/STEMME/2Elevator Control Coupling – Inspection (2)DCA/STEMME/3Variable Pitch Propeller - Modification (2)DCA/STEMME/4MAN Drive Shafts – Inspection (3)DCA/STEMME/5Enhanced Fire Proofing - Modification (3)DCA/STEMME/6Lower Drive Cog – Replacement (3)DCA/STEMME/7Fuel Pressure Sensor Lines – Inspection (4)DCA/STEMME/8Exhaust System - Inspection (4)DCA/STEMME/9Flight Control System Bearings – Inspection (4)DCA/STEMME/10Engine Wastegate Control and Oil Lines – Inspection (5)DCA/STEMME/11Flap System Drive Rocker – Inspection (5)DCA/STEMME/12Fuel Line Connectors – Inspection (5)DCA/STEMME/13Evans NPG+ Coolant and Cylinder Head Temperature – Inspection and AFMAmendment (6)DCA/STEMME/14Propeller Blade Follower Type 10AP-VM – Inspection and AFM Amendment (6)DCA/STEMME/15Differential Fuel Pressure Sensor – Inspection (7)DCA/STEMME/16Cancelled – DCA/STEMME/17 refers (7)DCA/STEMME/17Fuel System Connectors – Inspection (7)DCA/STEMME/18Fuel Lines – Inspection (8)DCA/STEMME/19Fuel, Oil and Cooling System Hoses – Inspection (9)The State of Design ADs listed below are available directly from the National Airworthiness Authority(NAA) websites. Links to NAA websites are available on the CAA website athttps:///aircraft/airworthiness/airworthiness-directives/links-to-state-of-design-airworthiness-directives/ If additional NZ ADs need to be issued when an unsafe condition is found to existin an aircraft or aeronautical product in NZ, they will be added to the list below. (10)2017-0072-E Front Gearbox – Inspection (10)* 2021-0278R1Clutch P/N 12AK – Inspection (10)DCA/STEMME/1 Air Brake Eye Bolt – Replacement, and Landing Gear Door - Inspection Applicability:Model S 10 S/N 10-03 up to 10-63 and S10–V S/N 14-002 up to 14-030, 14-012M upto 14063M.Requirement:To prevent vibration of the air brake upper covering straps at airspeeds approaching Vne, accomplish the following:-1. Reduce the Vne to 119 KIAS (220 km/h). Mark a new “Red Line“ on the airspeedindicator at 119 KIAS (220 km/h).2. Replace the eye bolts on the air brake per Stemme SB A 31-10-055, Amendment-Index 02.a dated October 09, 2000. After this replacement, the reduced Vne nolonger applies and the “Red Line“ shall be removed.3. Check the clearance of the air brake sheets per the SB and if necessary, modifythem.4. Inspect the Landing Gear doors and area per the SB and if necessary replacedamaged parts.(LBA AD 2000-369 refers)Compliance: 1. Before further flight.2. By 16 November 2001.3. Before further flight.4. Before further flight.Effective Date:16 November 2000DCA/STEMME/2 Elevator Control Coupling – InspectionApplicability:Model S10 S/N 10-03 through 10-63, S10-V S/N 14-002 through 14-030, converted aircraft S/N 14-012M through 14-063M, S10-VT S/N 11-001, 11-004 through 11-013and 11-015.Requirement:Inspect and replace longitudinal control couplings per Stemme SB A 31-10-032, Amendment-Index 02.(LBA AD 1998-323/2 refers)Compliance:Within the next 100 hours TIS, unless already accomplished.Effective Date:30 November 2000DCA/STEMME/3 Variable Pitch Propeller - ModificationApplicability:Model S10-V S/N 14-001 thru 14-030 and 14-012M thru 14-063M.Model S10-VT, S/N 11-001 thru 11-037.Requirement:To prevent loss of a propeller blade in flight, modify the propeller to include new design forks P/N 10AP-V88 per Stemme SB No A 31-10-051.(LBA AD 199-224/5 refers)Compliance:Before further flightEffective Date:27 March 2003DCA/STEMME/4 MAN Drive Shafts – InspectionApplicability:All model S10Requirement:To prevent failure of the bonded joint between the CFRP shaft and the metal flanges at each end of the driveshaft, remove the driveshaft per Stemme SB No A31-10-058and return to Stemme factory, for inspection.(LBA AD 2002-113 refers)Compliance:By 28 May 2003 if not already accomplished.Effective Date:27 March 2003DCA/STEMME/5 Enhanced Fire Proofing - ModificationApplicability:Model S10-VT, S/N 11-002 thru 11-072.Requirement:To increase the aircraft’s protection against in-flight fire, modify the enginecompartment and fuel lines per Stemme SB No A31-10-057 and No A31-10-061.(LBA AD 2002-156 refers)Compliance:Within 100 hours TISEffective Date:27 March 2003DCA/STEMME/6 Lower Drive Cog – ReplacementApplicability:All Model S10-VT, with gearbox S/N 43YYQ001 thru 43YYQ088. (YY is last two digits of year, Q is quarter number)Requirement:To prevent failure of the lower drive cog, loss of power and possible damage to the aircraft, accomplish the following:1. Limit operation of the engine to 100% (max continuous power). Takeoffs at115% are prohibited, use alternative flight manual procedure. Place the followingplacard in clear view of the pilot.Do not exceed 100% Power2. Replace lower cog per Stemme SB A31-10-65 Amendment 02.a.Replacement is terminating action for this AD and removes the limitation and placardsrequired by Part 1.(LBA AD 2002-389/2 refers)Compliance: 1. Before further flight.2. By 31 December 2003.Effective Date:27 March 2003DCA/STEMME/7 Fuel Pressure Sensor Lines – InspectionApplicability:Model S10-VT S/N 11-089 thru 11-096 and all S/Ns where the pressure lines have been replaced during the period 27 July 2004 and 22 June 2005 and the parts wereprovided by Stemme AG.Requirement:To detect ripped pressure lines between the air box, carburettor and differential fuel pressure sensor which could affect engine power in the range between maximumcontinuous power and take off power, accomplish the following:1. Inspect all pressure lines for porosity or cracks per Stemme SB A31-10-073. Ifcracks or porosity is found, replace all pressure lines before further flight, per SB A31-10-073.2. Replace all 4mm x 7mm pressure lines with Rotax P/N 860 660 or Stemme P/NHZ-KLS041 pressure lines, per SB A31-10-073.(LBA AD D-2005-228 refers)Compliance: 1. Before further flight.2. Within the next 20 hours TIS or by 31 December 2005 whichever is the sooner. Effective Date:30 June 2005DCA/STEMME/8 Exhaust System - InspectionApplicability:Model S10-VT aircraft, S/N 11-001 through 11-103.Requirement:To prevent CO2 leaking into the cockpit due to the possibility of a cracked exhaust system, inspect the exhaust bends near the cylinder flange of each cylinder, perStemme Service Bulletin No. A31-10-075 revision 01, or later approved revisions.Accomplish the corrective actions per SB No. A31-10-075, before further flight.(EASA AD 2006-0217-E refers)Compliance:Within the next 10 hours TIS.Effective Date:27 July 2006DCA/STEMME/9 Flight Control System Bearings – InspectionApplicability:Model S10 aircraft, S/Ns 10-03 through 10-56, and model S10-V aircraft, S/Ns 14-001 through 14-030 and all converted versions 14-003M through 14- 056M.Model S10-VT aircraft, S/Ns 11-001 through 11-089.Requirement:To detect and correct loose bearings in the aircraft control system which couldbecome completely disengaged and result in loss of aircraft control, accomplish thefollowing:1. Inspect the joint between the aileron control rod P/N 10SQ-RMB and theconnecting shaft P/N 10SQ-RMW, per Stemme Service Bulletin No. A31-10-069amendment 01.a.If the bearing is loose, accomplish the corrective actions per SB No. A31-10-069,before further flight.2. Inspect all the control system joints which have circular caulked hinges or ballbearings and the aileron system for the installation of a safety washer, per SB No.A31-10-069.Accomplish corrective actions per SB No. A31-10-069, before further flight. Compliance: 1. At every daily pre-flight inspection until the accomplishment of requirement 2.2. Within the next 100 hours TIS, unless already accomplished, or by 31 December2006, whichever is the sooner.(LBA AD D-2004-443 refers)Effective Date:28 September 2006DCA/STEMME/10 Engine Wastegate Control and Oil Lines – InspectionApplicability:Model S 10-VT aircraft, S/Ns 11-004 through 11-006 and 11-008 through 11-013. Requirement:To detect and correct malfunction of the wastegate control due to the possibility ofheat damage to the wastegate control cable and damage to the turbochargerpressure oil lines and mountings, inspect per Stemme Service Bulletin No. A 31-10-034, amendment 01.a.Replace the wastegate control cable with a modified cable with a reinforced outercover for increased heat resistance, per SB No. A 31-10-034.Inspect and replace the turbocharger oil pressure lines and mountings as required,per SB No. A 31-10-034.(LBA AD D-1998-400 refers)Compliance: Within the next 100 hours TIS, unless already accomplished, or by 31 December 2006, whichever is the sooner.Effective Date:28 September 2006DCA/STEMME/11 Flap System Drive Rocker – InspectionApplicability:All model S 10 aircraft, S/Ns 10-03 through 10-26 and converted aircraft, S/Ns 14-012M through 14-026M.Requirement:To prevent fatigue failure of the flap drive rocker replace flap drive rocker P/N 10SW-RMW per Stemme Service Bulletin No. A 31-10-017, amendment 02.a.(LBA AD D-1998-324 refers)Compliance: Within the next 100 hours TIS, unless already accomplished, or by 31 May 2007 whichever is the sooner.Effective Date:28 September 2006DCA/STEMME/12 Fuel Line Connectors – InspectionApplicability: Model S10 aircraft, S/Ns 10-03 through 10-56.Model S10-V aircraft, S/Ns 14-001 through 14-030 and all converted model S10-Vaircraft, S/Ns 14-003M through 14-056M.Model S10-VT aircraft, S/Ns 11-001 through 11-100.Requirement:To prevent fuel leakage due to the fuel line connectors being susceptible to improper assembly, accomplish the following:Inspect both ends of the wing to fuselage fuel line and identify which brassconnectors are fitted. Accomplish this inspection per Stemme Service Bulletin (SB)No. A31-10-077 amendment-index 01.a.Replace fuel line connectors identified as design modification index 01.a. withconnectors having design modification index 02.a. per SB No. A31-10-077, beforefurther flight.(EASA AD 2006-0310-E refers)Compliance:Before further flight.Effective Date:18 October 2006DCA/STEMME/13 Evans NPG+ Coolant and Cylinder Head Temperature – Inspection and AFM AmendmentApplicability:Model S10-VT aircraft, S/Ns 11-001 through 11-104 with a liquid cooling system filled with Evans NPG+ coolant, per Rotax SB 914-029.Requirement:The liquid cooling system of the Stemme S10-VT is not designed to be filled with flammable liquid without prior modification. For this reason the Evans NPG+ coolantmust be replaced and the operating temperature limitation of the cylinder headsreduced.Replace the Evans NPG+ cooling liquid per the instructions in Stemme ServiceBulletin (SB) No. A31-10-076 amendment-index 01.a.Amend the cylinder head temperature operation limitation in the AFM to a temporaryoperating limit of 120°C / 248°F. This may be accomplished by inserting a copy of thisAD into the AFM. The affected pages in the AFM are 2-3, 2-6 and 4-12.Modify the cylinder head temperature gauge for both the LH and RH cylinder headtemperatures by applying a red line at the 120°C / 248°F mark, per the instructions inRotax Aircraft Engines SB 914-029 revision 1.(EASA AD 2006-0311-E refers)Compliance:Before further flight.Effective Date:18 October 2006DCA/STEMME/14 Propeller Blade Follower Type 10AP-VM – Inspection and AFM Amendment Applicability:Model S 10-V and S 10-VT aircraft fitted with model 10AP-F propellers, S/Ns 40001 through 40010, and model 10AP-V propellers, S/Ns 10661 and 20001 through 20051(except 20038 and 20043), and model 11AP-V propellers, S/Ns 30001 through 30111(except 30059 and 30027).Requirement:To prevent failure of the attachment screw of the propeller blade follower type 10AP-VM causing loss of the main part of the blade follower in flight and lead to highvibration and affect aircraft control, accomplish the following:1. Amend the Aircraft Flight Manual (AFM) to include the following warning:Attention – If the main part of the propeller blade follower is lost in flight•Reduce the engine power setting to lessen the vibration level.•Land the aircraft at an airfield as soon as possible.Note 1:Requirement 1 may be accomplished by inserting a copy of this AD into the AFM.2. Replace blade follower type 10AP-VM with new type 10AP-VP, per theinstructions in Stemme Service Bulletin A31-10-078.Note 2:Once requirement 2 has been accomplished, the warning may be removed from the AFM.(EASA AD 2006-0373R1-E refers)Note 3:Propeller types 10AP-F, 10A-PV or 11AP-V may not be installed on any aircraft unless the propeller has the new type 10AP-VP blade follower fitted, per theinstructions in Stemme Service Bulletin A31-10-078.Compliance: 1. Before further flight, unless already accomplished.2. Within the next 25 hours TIS or by 16 April 2007, whichever is the sooner. Effective Date:21 December 2006DCA/STEMME/15 Differential Fuel Pressure Sensor – InspectionApplicability:Model S10-VT aircraft, all S/N fitted with a fuel pressure sensor P/N 11AB-K01. Requirement:To prevent fuel from the differential fuel pressure sensor leaking through the airpressure line into the airbox and possibly resulting in the fuel escaping through thedrainage tubes into the engine compartment, accomplish the following:1. Amend the aircraft flight manual per the instructions in action 2 of Stemme SBA31-010-081 and inspect the differential fuel pressure sensor per the instructions inthe amended AFM.If any fuel leaks are detected, repair any damage found and replace differential fuelpressure sensor P/N 11AB-K01 with a fuel pressure sensor P/N 11AB-KD per theinstructions in SB A31-010-081, before further flight.Note:Sign log book for compliance of requirement 1 at time of amending the AFM.2. Replace differential fuel pressure sensor P/N 11AB-K01 with a fuel pressuresensor P/N 11AB-KD per the instructions in SB A31-010-081. After installation of adifferential fuel pressure sensor P/N 11AB-KD, remove the AFM amendmentintroduced by requirement 1 of this AD.3. Differential fuel pressure sensors P/N 11AB-K01 held as spares shall not befitted to any aircraft as a replacement part.(EASA AD 2007-0191-E refers)Compliance: 1. Amend the AFM before further flight, and thereafter inspect the differential fuel pressure sensor per the instruction in the amended AFM at every daily inspectionuntil replaced with a fuel pressure sensor P/N 11AB-KD.2. Within the next 100 hours TIS or annual inspection or by 30 September 2007whichever is the sooner.3. From the effective date of this AD.Effective Date:18 July 2007DCA/STEMME/16 Cancelled – DCA/STEMME/17 refersEffective Date:14 March 2008DCA/STEMME/17 Fuel System Connectors – InspectionApplicability: Model S10-VT aircraft, S/N 11-001 through to 11-112.Note 1: Since the release of DCA/STEMME/16 another fuel leak has been reported on a S10-VT aircraft on which the requirements of SB No. A31-10-082 had been implemented.This AD supersedes DCA/STEMME/16 and mandates the requirements in StemmeSB No. A31-10-083.Requirement:To prevent failure of plastic fuel system connectors possibly causing fuel leaks which could result in an engine fire, accomplish the following:1. For aircraft modified in accordance with SB A31-10-082:1.1 Inspect the aircraft fuel system for leaks per instructions 1.2 inparagraph 5 of Stemme Service Bulletin No. A31-10-083.If any leaks are found, repair in accordance with a manufacturer approved repairscheme and replace the single-ear clamps P/N M476 with clamps P/N 10M-181per instructions 3.2 in paragraph 5 of SB No. A31-10-083 before further flight.1.2 Replace the single-ear clamps P/N M476 with new clamps P/N 10M-181per instructions 3.2 in paragraph 5 of SB No. A31-10-083.2. For aircraft not modified in accordance with SB A31-10-082:2.1 Inspect all plastic connectors at the fuel pumps and the fuel shut-offvalve (behind the rear bulkhead of the front fuselage) for fuel leaks perinstructions 1.1 of paragraph 5 of SB No. A31-10-083.If any leaks are found, repair in accordance with a manufacturer approved repairscheme and replace the single-ear clamps P/N M476 with new clamps P/N 10M-181 per instructions 3.2 in paragraph 5 of SB No. A31-10-083 before furtherflight.2.2 Replace all plastic “T” and “Y” shape fuel connectors with new metalconnectors per instructions 3.1 in paragraph 5 of SB No. A31-10-083.Note 2: The accomplishment of requirement 2.2 of this AD terminates the repetitiveinspections required by requirement 2.1.2.3 Replace the single-ear clamps P/N M476 with new clamps P/N 10M-181per instructions 3.2 in paragraph 5 of SB No. A31-10-083.3. For all aircraft:Plastic “T” and “Y” shaped fuel connectors and single-ear clamps P/N M476shall not be fitted to any aircraft.(EASA AD 2008-0053-E refers)Compliance: 1.1 Before further flight.1.2 At the next scheduled maintenance inspection or by 14 March 2009, whicheveroccurs sooner.2.1 Before the first flight of every day until requirement 2.2 is accomplished.2.2 At the next scheduled maintenance inspection or by 14 April 2008, whicheveroccurs sooner.2.3 At the next scheduled maintenance inspection or by 14 March 2009, whicheveroccurs sooner.3. From the effective date of this AD.Effective Date:14 March 2008DCA/STEMME/18 Fuel Lines – InspectionApplicability:Model S10 and S10-V powered aircraft, S/N 10-32, 10-53, 14-025 and 14-027. Requirement:To prevent failure of fuel lines which could result in fuel leaks, accomplish thefollowing:1. Inspect the fuel lines per Stemme SB No. A31-10-084 initial issue or laterapproved revisions. If any damage is found replace all the fuel lines per SB No. A31-10-084 before further flight.2. Replace all the fuel lines per SB No. A31-10-084.(EASA AD 2008-0186-E refers)Compliance: 1. Before further flight.2. By 30 November 2008.Effective Date:30 October 2008DCA/STEMME/19 Fuel, Oil and Cooling System Hoses – InspectionApplicability:Model S10, S10-V and S10-VT powered gliders, all S/NRequirement:To prevent fuel, oil or cooling system hose failure, accomplish the requirements in EASA AD 2012-0154.Note: Stemme GmbH SB A31-10-093 at issue 1, dated 15 June 2012 or later approved revisions are acceptable for compliance with the requirements of this AD.(EASA AD 2012-0154 refers)Compliance:At the compliance time specified in EASA AD 2012-0154.Effective Date:31 August 2012The State of Design ADs listed below are available directly from the National Airworthiness Authority (NAA) websites. Links to NAA websites are available on the CAA website athttps:///aircraft/airworthiness/airworthiness-directives/links-to-state-of-design-airworthiness-directives/If additional NZ ADs need to be issued when an unsafe condition is found to exist in an aircraft or aeronautical product in NZ, they will be added to the list below.2017-0072-E Front Gearbox – InspectionEffective Date:28 April 2017* 2021-0278R1 Clutch P/N 12AK – InspectionApplicability: S10-VT and S12 powered gliders, all S/N.Note:This AD revised to introduce a freewheel clutch modification.Effective Date:EASA AD 2021-0278-E - 17 December 2021EASA AD 2021-0278R1 - 31 August 2022。
FY-31AP连接半双工电台使用说明1、FY-31AP与GCS连接数据不通畅的原因及解决办法为提高FY-31AP连接OSD后视频叠加数据的流畅度，FY-31AP默认出厂下行频率为10HZ。
由于频率高，且下传数据量较大，在用半双工电台连接GCS软件后容易造成遥测数据或GCS命令数据堵塞，即GCS表现为数据通信不畅。
同时，连接FY-31AP的电台状态显示LED表现为常亮，如图：为最大可能的降低遥控命令的延时，Remote Adapter的上行频率出厂设定都在10HZ以上，在下行频率也高的情况下，就会出现传输堵塞。
为解决这个问题，可以把下行频率降低，例如2HZ。
可以通过GCS软件更改，具体方法如下：通过USB-TTL串口线连接FY-31AP和电脑，连接“UART”端口：打开GCS软件，连接系统后，选择“工具”——“下传数据频率”——“2HZ”：更改后，需要把参数保存到飞控，才能在下次再上电后仍然保持下行频率为更改后的下行频率。
点击“参数设置”——“PID参数”——“保存设置到飞控”：连接系统后，点击“通信”——“遥测数据”——“2HZ”：更改成功后软件会弹出提示窗口，确定后可以发现“总开关”下的红色指示灯闪烁频率也随着降低：保存设置参数到飞控，以便在下次通电运行时为此次更改后的配置，点击“参数1”——“永久保存设置参数”，保存成功后下方状态栏会有提示：更改OK后，再次安装飞控，连接电台后，可以看见电台的状态指示LED 为连续闪烁的状态，说明下行频率已经调低。
2、FY-31AP数传电台、遥控切换配置方法31AP提供2种遥控方式：连接地面站组件，通过电台控制飞机；31AP连接接收机，遥控直接控制飞机。
这两种控制方式的组件可以同时安装，在GCS上任意切换其中一种控制方式来遥控飞机。
地面站组件包括：Remote Adapter、电台、接收机、USB-TTL串口线。
连接如下：Remote Adapter端口连接：“DATA RX TX”端口接电台，“PC RX TX”端口接USB-TTL串口线连接至电脑USB端口，接收机按副翼、升降、油门..顺序连接。
桂林飞宇电子科技有限公司E-mail: service@FY-31AP 惯性姿态平衡仪Feiyu TechGPS 模块工作电压 电流 外形尺寸 重量（不包括电线） 温度范围 ： 3.0～3.3 Volt； ： 60mA (3.3V)； ： 32 x32x 10 mm； ： 22g； ： -25°C~ +70°C；安装&操作指南尊敬的客户：您好！感谢您使用桂林飞宇电子科技产品，为了更好的使用本产品，请在使用前认真仔细 地阅读本说明书，以确保正确的使用及操作。
注意：l l l l 安装和使用本产品需要一定的多旋翼模型的遥控技巧。
假如您是一个从来都没有进行过任何一次飞行操作的初学者，我们建议您别独自安装本设 备。
请找有经验的人帮忙，您会需要他们为你提供一些基本知识以便您能成功地使用本设备。
如果您是一位富有经验的操作手，您会发现本设备的安装简单有序。
只需要按照本说明书 进行操作就不会有差错。
如需要任何技术支持您可以直接发送邮件到 service@。
适用机型标准版 FY-31AP 适用以下机型： 1. 正常布局固定翼飞机； 2. 飞翼布局带方向舵的飞机； 3. 飞翼布局无方向舵飞机； 4. 无副翼飞机； 5. 带副翼 V 尾飞机； 6. 无副翼 V 尾飞机； 7. 其他机型是否适用请发邮件到此邮箱进行咨询- service@。
1.工作原理：惯性姿态平衡仪（AFSS）FY-31AP 是一款先进的惯性姿态平衡仪（简称 AFSS）和简易自动驾驶仪。
可用于固定翼飞 机或者简易三轴云台。
FY-31AP 集成了三轴陀螺仪， 三轴加速度计组成一个精确无漂移的惯性姿态平衡系统。
同时， 它利用 GPS 和气压传感器获得飞行器精确的三维定位。
通过结合姿态控制和定位，实现惯性导 航和自动驾驶。
支持固件升级，通过升级不同的固件实现不同的自动驾驶功能。
可以进行各种 固定翼飞机的飞行控制。
· · ·FY-31AP 适用于以下遥控设备：Robbe-Futaba PPM / PCM 1024 / PCM G3 模式，2.4G 系统； Graupner/JR PPM 8, PPM 12, SPCM 模式； MPX PPM8, PPM 12 with UNI 模式 以及其他使用 1.5 ms 标准中立位置的遥控设备。
旗开得胜读万卷书行万里路11概述与适用范围1.1本程序阐述了当外航飞机在厦航各维修分支机构发生故障，并申请厦航支援时实施排故的管理程序。
1.2本程序适用于质量部、工程部、发动机管理中心、生产计划部、航空器材部、航线维修部、基地维修部、福州分公司机务部、各维修分支机构。
1.3程序属性□CCAR121 ■CCAR145航线■CCAR145定检/部件2依据文件2.1AC-145-6 “航空器航线维修”2.2《维修管理手册》“对其他航空营运人的飞机的航线维修”3术语和定义互援协议：厦航与南方航空（集团）公司、中国国际航空公司、东方航空公司、上海航空公司、山东航空公司、深圳航空公司、海南航空公司、奥凯航空公司、中国邮政航空公司等签订的飞机航线维修互援协议。
4要求4.1所需的人员岗位4.1.1飞机维修工程部值班经理4.1.2MCC调度人员4.1.3维修人员、维修工程师4.1.4航空器材部AOG值班人员4.2职责4.2.1飞机维修工程部值班经理：负责确定是否对外航飞机进行排故。
4.2.2生产计划部：a)负责与外航联系协调排故人员授权；旗开得胜读万卷书 行万里路2b) 组织对外航飞机的排故记录的填写，整理和上交飞机维修结算单。
4.2.3 各维修分支机构：负责实施对外航飞机的具体排故工作。
4.2.4 航空器材部：负责外航排故所需借用的厦航航材的准备，办理航材出借手续。
5 规定5.1 厦航对外航的排故工作内容不得超出适航当局批准的维修工作项目。
5.2 排故人员必须由外航进行书面临时工作授权。
5.3 厦航只负责排故，不负责对外航飞机的签字放行；飞机是否放行由该飞机的执管单位决定。
6 程序6.1 处理外航飞机的排故申请MCC 调度人员6.1.1 接到与厦航已签署了互援协议的航空公司提出支援飞机排故申请，立即向飞机维修工程部值班经理汇报。
6.1.2 安排航线维修部、质量部或相关维修单位派人支援排故。
6.1.3 与厦航没有签署互援协议的航空公司的飞机故障需要厦航帮助排除，需请示飞机维修工程部值班经理同意后，方可派人帮助排故。
CTLS轻型运动飞机飞行手册序列号：本文件为原版英文手册译本，在任何情况下，所有内容及数据以原版英文手册为准。
机型：CT类别：CTLS LSA页码：i目录1.概论....................................................................1-11.1.介绍............................................................. 1-11.2.制造商........................................................... 1-21.3.有关持续适航性的说明............................................. 1-31.4.三视图主尺寸..................................................... 1-51.5.发动机........................................................... 1-81.6.螺旋桨........................................................... 1-81.7.最低设备配置..................................................... 1-91.8.建议添加设备.................................................... 1-102.限制（中国民用航空局批准）................................................2-12.1.空速限制......................................................... 2-12.2.飞行负载因素限制................................................. 2-22.3.轮胎气压......................................................... 2-22.4.重量和重心限制................................................... 2-32.5.动力装置限制..................................................... 2-42.6.其他限制......................................................... 2-53.紧急程序（中国民用航空局批准）............................................3-13.1.紧急程序检查单................................................... 3-13.2.失速............................................................. 3-33.3.不慎引起尾旋的处理............................................... 3-33.4.紧急着陆......................................................... 3-43.5.着陆机体倾覆后................................................... 3-53.6.启动弹射回收系统................................................. 3-63.7.发动机失效....................................................... 3-73.8.汽化器或发动机着火............................................... 3-93.9.冷却剂缺失....................................................... 3-93.10.滑油缺失......................................................... 3-93.11.襟翼控制失效.................................................... 3-103.12.Dynon发动机监控系统EMS失效（如果装有）........................... 3-114.正常程序（中国民用航空局批准）............................................4-14.1.正常程序检查单................................................... 4-14.2.飞行前检查....................................................... 4-54.3.乘客讲解......................................................... 4-64.4.启动发动机....................................................... 4-74.5.自动驾驶操作..................................................... 4-84.6.起飞前........................................................... 4-94.7.典型的航线模式.................................................. 4-104.8.起飞和爬升...................................................... 4-11机型：CT类别：CTLS LSA页码：ii4.9.巡航............................................................ 4-134.10.转弯............................................................ 4-144.11.失速............................................................ 4-154.12.进近和着陆...................................................... 4-154.13.关闭发动机...................................................... 4-174.14.检查紧急定位发射机（ELT）....................................... 4-175.性能（中国民用航空局批准）................................................5-15.1.最大起飞重量600公斤（1320磅）性能数据........................... 5-15.2.飞行高度和密度................................................... 5-25.3.风分量的作用..................................................... 5-45.4.高度对发动机性能特性的影响....................................... 5-65.5.计算起飞距离..................................................... 5-75.6.计算爬升性能.................................................... 5-105.7.滑翔特性........................................................ 5-115.8.计算着陆距离6.重量和平衡、设备.........................................................6-16.1.重量限制......................................................... 6-16.2.称重............................................................. 6-16.3.飞行重量和重心................................................... 6-46.4.设备............................................................. 6-47.飞机和系统描述..........................................................7-17.1.机体............................................................. 7-17.2.系统............................................................. 7-47.3.飞行控制........................................................ 7-127.4.驾驶舱.......................................................... 7-207.5.标牌和标志...................................................... 7-268.操作、服务和维护.........................................................8-18.1.顶升............................................................. 8-18.2.陆路运输中固定飞机............................................... 8-28.3.降落伞回收系统维护............................................... 8-28.4.清洁和保养....................................................... 8-38.5.飞机强制性检查................................................... 8-58.6.机身维修......................................................... 8-68.7.控制面偏转....................................................... 8-79.拖曳滑翔机..............................................................9-110.横幅、标语拖曳..........................................................10-111.附录...................................................................11-111.1.现行称重报告.................................................... 11-111.2.现行设备清单.................................................... 11-211.3.飞行安全报告表.................................................. 11-3机型：CT类别：CTLS LSA页码：1-1 1.概述1.1.介绍每个飞行员都必须熟悉每架轻型运动飞机的特性。
1小时掌握终生受用的航空（运价）知识MS运价表（部分）最近有不少旁友提出，好像空运方面的文章很少，能否发一些空运方面的。
谢谢旁友们的建议，这次我就发空运的啦。
下面以MS（埃及航空）的“运价表”为例，对运价表的重要信息进行解读。
1起运港PEK & 币制CNY1）“起运港：PEK”——表明此报价，始发机场都是PEK“PEK”是北京首都国际机场的三字代码。
当一个城市只有一个机场时，有时也用城市码代替机场码。
北京的城市码为BJS。
目前北京（BJS）主要有两个民航机场——北京首都机场（PEK）和北京南苑机场（NAY）。
机场三字码由国际航空运输协会（International Air Transport Association，简称IATA）规定，三个英文字母组成。
例如：上海浦东国际机场PVG、深圳宝安国际机场SZX、开罗国际机场CAI等。
2）“币制：CNY”——表明此报价，计价币种都是CNY“CNY”是C hi n ese Y uan的简称。
人民币也经常写成RMB。
CNY和RMB意思一样，可以通用。
各国（地区）的货币代号由该国（地区）的两字代码，与当地货币的第一个英文字母组成。
例如：China的国家代码CN，货币英文名Yuan（开头字母Y），所以ISO货币代码是CNY；Australia的国家代码AU，货币英文名Dollar（开头字母D），所以ISO货币代码是AUD；Hong Kong的代码HK，货币英文名Dollar（开头字母D），所以ISO货币代码是HKD。
航空运价一般以始发地的本国货币表示。
不同于海运的基本以USD报价。
以北京（PEK）为始发地，当然以CNY来表示。
2区域—埃及、非洲等MS是埃及的国家航空公司，目的地以埃及和周边地区为主，到埃及的航班多，且一般是直飞。
此报价表，PEK-CAI（开罗）就是直飞航班。
然后再以CAI作为中转地，通过空运或卡车，转运到其他目的地——转运到埃及其他点，或周边其他国家。
