666第二套

buttock line
connector
starter
horizontal stabilizer
manifold
solid line
extension
outflow valve
Bonding straps are installed to prevent the build-up of (static electricity).
Care should always be taken when working with oxygen, all (lines) should be capped as soon as possible and all tools used in maintenance functions should be free of oils and other petroleum products.
Charging valves are installed on the main landing gear to fill the shock absorber with (nitrogen).
Debonding is the separation of material due to an (adhesive) failure.
Do a check of the engine oil level and service the engine (within two hours of shutdown).
FADEC stands for ( ).
Flaps are secondary controls that increases the (angle of attack) of the wings that results in increase lift.
For surfaces that are wet or have ice, do the special mooring at lower (wind velocities)
Gas turbine engines use many types of starters, the most common starter is the (pneumatic starter).
If the airplane gross weight and center of gravity are in the SAFE ZONE limits, ( )to keep the airplane stable during engine removal.
If the male thread does not have a ( ), the male thread must extend one and one-half treads or more above the top of the nut.
In case of brake overheat, the (single chime) sounds and the MASTER CAUTION comes on.
In case of generator fault, the related AC BUS is supplied by the opposite generator and (galley loads are partially shed).
Instructions on using solvents/cleaning agents and sealants should not include ( ).
It is permitted to walk on the (THS) in the center section only to use protective mat.
(The fuel nozzles supply atomized fuel to the engine combustion chamber.)
(The ignition exciters are on the right side of the main gearbox.)
(thrust reverser deployment)
(VHF Communication System)
(Weigh the aircraft on jacks and calculate the position of the center of gravity.)
hydraulics
cowl
potable water
appropriate
shaft
cooling pack
redistribution
(涡轮风扇发动机)
(无线电高度低于750英尺)
Access doors and panels in a zone are identified by (alpha-numeric labels).
An inlet screen prevents (FOD) to the APU compressors.
Any (access panel) removed or opened to gain access to zones should be examined during the zonal inspection.
At 50% RPM, the starter is (   ) by the ECU since turbine power alone is now sufficient to complete the start.
At low airspeeds the (ram air) cooling for the dual heat exchangers is insufficient and must be supplemented by cooling air from the heat exchanger fans.
ATA Chapter 05 is about:( ).
ATA Chapter 47 is about:( ).
Before valve installation,make sure there is no unwanted material or contamination in the inlet duct to the valve or the ( ).
(lift to drag ratio)
(Lubrication Symbols)are the symbols used to represent the recommended lubrication method.
(Specific fuel consumption) of a large commercial jet liner engine is dramatically lower than a turbojet engine in a fighter aircraft.
(The battery is wired in parallel to the generator.)
(The bypass valve opens if the pressure exceeds 4000 psi.)
The flight controls provide increased lift for takeoff and landing as well as increased aerodynamic _____ both in flight and on the ground.
The PILOT CALL switch is on the P19 external power panel. This panel is forward of the nose wheel well on the right side of the airplane.
A mechanical pressure gage on the oxygen cylinder shows the cylinder pressure regardless of the cylinder shutoff valve position.
XX failure (jam, damage, water leakage, fault code appear, circuit breaker pop-up) was found by ground check.
Do external walk around check, check static ports for no damage and obstruction, check radome latches and angle of attack sensors for no damage.
WARNING: DO NOT OPERATE THE WEATHER RADAR UNLESS ALL PERSONNEL ARE MORE THAN 50 FT FROM THE RADAR. DO NOT OPERATE THE WEATHER RADAR IN A HANGAR. IF YOU DO NOT OBEY THESE PRECAUTIONS, INJURIES TO PERSONNEL CAN OCCUR.
When composite materials are cut or sanded, dust and loose particles are produced which are potential health hazards.
Variables such as the size of the fuel spill, weather conditions, equipment location, aircraft occupancy, emergency equipment and personnel available will determine the correct response to control the fire hazard.
Make sure you install the positive pressure relief valve and gasket correctly during installation. Incorrect installation can block sense ports for the valve servo mechanism.
Steer the aircraft with the rudder pedals or the nose wheel steering handwheels and align the aircraft with the taxiway centerline.
The minimum distance from the edge of the stiffener to the damaged area must equal 20 times component thickness.
Keep persons and equipment away from all control surfaces and the nose gear when hydraulic power is supplied. The ailerons, elevators, rudder, flaps, slats, spoilers, and the nose gear are supplied with power by the hydraulic systems.
Do not apply solvents, grease, or oil to stainless steel control cables. These materials can collect contamination that can cause damage to the internal surfaces of the CRES cable strands.
Do not let dirt, metal particles, and other unwanted material get in the lubricant. Contamination in the lubricant will cause damage to the component.
Normal Procedures associated with the subject installation shall be presented in a check list form when order of action is essential to safety, and any changes to the basic Normal Procedures of the Pilot's Operating Handbook shall be stated.
The Cockpit Door Surveillance System (CDSS) can monitor the cockpit entrance, the left and right Door 1 areas.
A fire can be due to flammable fluid leaks and can endanger the aircraft safety. Thermo sensitive elements detect fire or overheat conditions.
The fault information shows on the electrical meters, battery, and galley power module. The amber ELEC light on the module comes on when the module has an electrical system fault message.
There is a water overflow port in the water collection manifold. This port will discharge water into the pack bay in the event that the water spray nozzle becomes plugged.
If the microswitch becomes unserviceable, do the deactivation procedure of the actuator to prevent damage to the valve.
Two indicator pins on the inboard side of the brake housing show brake wear. You must apply the brakes to check the wear indicator pins.
The attach fittings on the fuselage are used for the attachment of doors, wings, stabilizers, landing gear, engine and rotor pylons and for the support of equipment within the fuselage.
CAUTION: WHEN YOU GET ACCESS TO THE REAR FUSELAGE THROUGH THE ACCESS PANEL, DO NOT PUT YOUR FEET ON THE APU LINE.
The wing auxiliary structure includes leading edge, trailing edge, wing tip, tip fuel tank and fuel or water cell backing boards. Does not include plates/skin.
It is very difficult to determine the effects of corrosion but, as the reports from the CAP inspections are received, the inspection times will be adjusted for any severe problems.
Some fixed or variable fairings such as those on the nose and tail and between the fuselage and the wing and the stabilizers are aerodynamic fairings.
The main frame of the fuselage includes frames, bulkheads, longerons, stringers, keel, frames around openings, etc.
Wherever the CAP is directed to a specific part or component, it is implied that the inspection will include observation and evaluation of the surrounding area of parts and equipment.
Continuing Airworthiness Program Inspections usually consist of two pages: one text page and one illustration page.
CAUTION: WHEN YOU REMOVE THE PROBES, DO NOT LET THEM TOUCH EACH OTHER. IF THEY TOUCH, THEY CAN BECOME DEMAGNETIZED.
The exact content of the Normal Procedures Section shall be determined by the applicable regulations of the certificating authority and by the operating and design features of each particular airplane.
The effects of corrosion have not been considered in the rationale in selecting inspection times or in the effects on the fatigue stresses.
That auxiliary hydraulic system is classified as auxiliary, emergency or standby system, and which is used to supplement or take the place of the main hydraulic system.
Pretreatment material for painting is poisonous and flammable which can cause injuries to persons or damage to equipment.
The Continuing /Airworthiness Program (CAP) Inspection Document is inspection data that, when combined with the operator's existing maintenance program, will help maintain the structural integrity and continued airworthiness of the airplanes.
The bleed air check valve is part of the engine bleed air manifold. It is on the left side of the engine high pressure compressor case.
It is possible for debris to accumulate on the engine internal face, the servo system outlet and exhaust vent filters.
The system monitors the flight of aircraft during approach and landing. The monitor system includes sensing, computing, indicating and warning devices such as computers, indicators, warning lights, etc.
Do not cause a blockage when you apply sealant near or around the fuselage drain holes, tubes, or paths. The function of the drain holes is to drain condensation and fluids overboard.
“Airplane" refers to the air frame and related components specified in the Type Certificate or made available as options by the airplane manufacturer.
This Section of the Pilot's Operating Handbook shall contain only those limitations required by regulation or necessary for safe operation of the airplane and approved by the regulatory authority.
At this altitude, the LAND mode provides the alignment on the runway centerline on the yaw axis and flare on the pitch axis.
Connect a ground hydraulic power supply with a flowmeter to the ground test connections of the Green hydraulic system.
The flight controls furnish a means of manually controlling the flight attitude characteristics of the aircraft, including items such as hydraulic boost system, rudder pedals, control column linkages, control cables, tab controls, mounting brackets, etc.
FAILURE TO DEACTIVATE THE HCU CAN RESULT IN ACCIDENTAL THRUST REVERSER OPERATION AND INJURY TO PERSONNEL.
The Protective Breathing Equipment is a vacuum sealed storage container with identifying and instructional placards.
The ground crew call signal goes through a relay in the integrated flight system accessory unit and then to the ground crew call horn.
The monitor instrumentation processor performs a validity check of the primary instrumentation processor deviation output.
Magnetic Chip Detector (MCD) is a magnetic plug in sumps of lubricated components for detection of internal failure of the component.
Life limited part means any part for which a mandatory replacement limit is specified in the type design or the maintenance manual.
OBEY THE EFFECTIVITY PER WEIGHT VARIANT AND AIRCRAFT TYPE GIVEN IN THE RELEVANT SHEET.
Push and release the TEST button to initiate self-test. The front panel LEDs with come on momentarily then will display fault status.
In designing schematic diagrams, it may be necessary to compromise between detail that is necessary to make the diagram self-explanatory and simplicity that is essential for ease of reading and understanding.
GPS (Global Positioning System) is a longrange navigation system that takes navigation input from transmissions generated by a series of satellites in synchronous orbit.
When you select the attitude mode, the ALIGN light comes on for 30 seconds. During this time, the ADIRU calibrates to 0 degrees in pitch and roll.
The propeller controlling system controls the pitch of the propeller blades, including items such as governor, synchronizers , switches, cables, levers. etc.
Put the wire bundle through an available cutout. Isolate the wires before you apply the seal. Wind the wire coil separators two to four turns around each wire.
Climb gradient is the demonstrated ratio of the change in height during a portion of a climb, to the horizontal distance traversed in the same time interval.
On a polished surface, this type of corrosion is first seen as a general dulling or etching of the surface and, if the attack is allowed to continue, the surface becomes rough and possibly frosted in appearance.
Cut the doubler to oversize and pre-shape it to match the fuselage contour to avoid stressing.The doubler must not end above a stringer or frame.
Unscheduled maintenance checks include inspections and checks such as hard landing, turbulent air, lightning strike, overweight landing, bird strike, slush ingestion, maintenance checks prior to engine-out ferry, etc.
The fuel dump system is used to dump fuel overboard during flight. It includes items such as plumbing, valves, chutes, controls, etc.
Do not let the paint stripper touch fiberglass or seams of adhesive bonded parts. The paint stripper can cause damage to fiberglass or seams of adhesive bonded parts.
Specific lifting & shoring materials are necessary to the aircraft operations in abnormal conditions such as belly landing, nose landing, etc.
The moisture/air contaminant control system is used to control moisture in the air, to control ozone concentrations, to filter radioactive debris from conditioned air, etc.
The distribution portion of the environmental system is used to induct and distribute air. It includes equipment rack cooling systems and items such as blowers, scoops, ducting, inlets, check valves, etc.
从法兰上拆卸铆钉。
关闭发动机。
检查地板是否有变形。
给飞机加油。
此程序仅适用于A型零件。
在锥套上涂上油脂。
在发动机启动前,远离排气区域。
隔离造成故障的部分。
泵安装在液压马达后面。
操纵控制杆是发动机启停的主要控制装置。
警告、警戒和注意可以来突出或强调重要的地方。
在给系统加新油之前,更换油滤是强制要求。
灰尘会污染所有的滤芯。
测量内外侧襟翼的运动。
执行排故程序来找到故障原因。
松开加油转接头(17)上的弯管接头(18)。
活门失效的主要原因是液压油污染。
气体在充气瓶中膨胀。
仪表近进着陆要求航空器有足够的离地高度。
生产主管应根据工卡执行指定的任务。
以下安全预防措施适用于爆炸物品。
如果风速超过20节,不要打开雷达罩。
启动发动机前,确认灭火瓶在正确的位置。
正常俯仰操作法则基本上是载荷系数的闭环操纵。
通过验证离散输入的状态以获得详细的故障隔离程序。
这个反馈被连接到下游的三极管Q1。
调整卡箍直到有足够的摩擦力使其保持在原位。
管道支架将头顶分配管道连接到顶板支架上。
重心随机翼上的载荷而移动。
让漆在室温和相对湿度适宜的环境下干燥。
油耗每小时不能超过0.6美制品脱。
确保能读懂标识牌。
如泵叶片有腐蚀,则更换泵。
如果转子突然停止,检查进气口是否有多余物质。
部件分解以后,小心拿取零件,并防止零件腐蚀。
给轮胎充氮气。
继电器2yg和8yg完全可互换。
如果配平调整片调节不正确,执行步骤7到10。
AMM 手册中规定了每一个航线可更换件的标准安全措施。
如果发现问题,参阅排故手册。
确保氧气软管的线圈不要在一起摩擦。
充分地拧松锁紧螺帽,直到活塞杆能够转动。
加油软管不能碰到油箱边缘。
横滚角度值为负意味着左翼低。
确保机长的头戴式耳机准确接收信号。
溶剂使用需遵守制造厂商的使用说明。
如果减震支柱轴的偏移位于左侧,则偏差标记为“-”。
使用清洁剂Ardrox 6025或等效物。
拧紧松紧螺套,直到钢索张力适当。
检查主连接电阻。
确保没有轴向负荷施加在杆上。
执行碳钢钢索的保存程序。
柱头的凹槽不要超过5毫米。
如果闻到客舱里有滑油味,更换再循环气滤。
按以下顺序进行称重。
脚蹬的两个止动螺栓是可调节的。
测量内侧和外侧襟翼的移动。
不允许在起落架轮轴的每个螺栓上安装两个以上垫片。
从油箱内排放大约2升燃油。
只能使用力矩扳手拧紧平衡调整片的螺母。
如果燃油经常积聚,检查是否有渗漏。
如果没有渗漏,衬套轴肩后的裂纹可被允许。
如果固态样品中有金属屑,更换液压泵。
调整吊索直到襟翼水平。
从接头处断开管路。
在脚蹬上施加适度的载荷。
经常清洗毛刷/海绵以防造成划痕。
从丝杠齿轮箱的刚性盖板上拆下螺钉。
如果温度升高,钢索上的张力会减小。
获取燃油样本并测量其比重。
机翼结构提供最大的燃油容量。
安装封严到滑油滤中时,不要过度拉伸封严。
把温度计校正到摄氏刻度。
密封件尺寸必须与凹槽匹配。
前起落架收进机身。
快速将油门杆收到慢车位置。
顺时针旋转燃油喷嘴40度。
如果堵塞指示器弹岀,则更换滤芯。
底漆含有防腐的材料。
起落架上位锁组件的卡爪必须立即打开。
确保模板的轮廓相同。
测量机身和克鲁格襟翼之间的距离。
在恒定温度下固化操纵面密封剂。
用托架将机翼上的载荷保持在最小值。
用圆形切割器或研磨机获得正确的切口尺寸。
不要让泡沫变硬。
将金属箔放置到位,并用胶带将其粘上。
切除损伤横梁,去除切口边缘毛刺。
对裸露表面进行保护处理。
与硬化剂混合后,请勿摇晃基材。
如果划痕没有划破保护层,则该组件可用。
这种冷却剂与铝合金不兼容。
在按压活门杆之前,把脸转到一边远离排放活门。
拆除襟翼铰链的内侧整流罩。
发生火警时,温度升高并引起探测器工作。
数据库同步正在进行中。
在大翼防冰系统上安装伸缩管。
可用一个清洁的塑料袋替代指定的容器承接滑油。
气流沿着缝翼的顶部和底部表面流动。
强风会阻止逃生滑梯的正常释放。
在车间里分解刹车组件。
这个步骤给出了连接吊架的说明。
如果知道调整片间隙,就能计算出垫片厚度。
燃油泵安装在隔框附近。
如果剪切销断裂,检查牵引杆。
释放刹车储压器中的液压压力。
发动机及其辅助设备使用同一种润滑剂。
过热开关保护气源总管免受过热影响。
同时拆卸旁通活门和排放活门。
把金属条弯曲成一条曲线。
用标记标识摇臂和轴,防止错误安装。
离心泵向组件提供液压油。
测量舱壁灯与液压管路之间的电阻。
确保静压探测管保护盖未安装。
定期安排轮胎检查。
电缆必须定期清洗、检查和润滑。
节流阀控制动力飞机的发动机速度或推力。
地面服务开关在前话务员面板上。
RMI由带有两个指示针的磁性罗盘组成。
这些新功能增加了飞机的有效载荷、服务上限和航程。
APU发电机向飞机电气系统供电。
安定面保证飞机稳定性,使其保持直线飞行。
打开活门,让氮气进入减震支柱。
接近1号液压系统的储压器。
化合物腐蚀在表格6001中有规定。
如感觉发动机过热,将电门设置在“关”位。
把分析结果告诉质量部。
制造商可以省略不适用于其产品的系统。
确保发动机进气道无外来物。
如果风速高的危险,请不要打开货舱门。
滚柱上没有过多的磨损且襟翼轨道上没有凹痕迹象。
当电表显示28伏特直流时,继电器闭合。
这种材料接触热表面时会释放出危险的气体。
只有批准人员才能操作刹车。
拧紧螺母,但此时不要打力矩。
燃油和氧气的混合物能引起爆炸。
全行程操作升降舵6次。
喷油孔堵塞会导致不正确的操作。
如果通气桅杆排气量不正常,做系统测试。
确保油箱中的燃油量不超过500升。
在重着陆过程中,发动机可能发生冲击载荷。
调节罗盘系统I直到和罗盘系统2一致。
测量硅胶吸收水分所需的时间。
把这些部分按概率的顺序列在每个故障下面。
在你继续测试之前,间隔5分钟是必要的。
无论飞机在地面还是顶升状态,该限制均适用。
要校正测试设置,参考制造商说明。
检查排水孔周围区域是否有腐蚀迹象。
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