A320 起落架 LCSD

1、 飞机维修工作卡 深圳航空有限责任公司 MAINTENANCE JOB CARD MJC737- 此页有意空白 共 6 页 第 2 页深圳航空有限责任公司Shenzhen AirlinesA320 飞机航线维护指南A320 Line check supporting data 内 容CONTENTS【工卡描述】插好前起落架安全销【参考文献】 TASK 32-00-00-481-001 Installation of the Safety Devices on the Landing GearsTASK 32-00-00-481-002 Installation of the

2、 Safety Devices on the Landing Gear Doors【检查标准】 1）如果前起落架门打开，确认安装前起落架门安全销 （TASK 32-00-00-481-001 Installation of the Safety Devices on the Landing Gears）；检查前起落架五块舱门，特别注意最后面的三角门牢固，无松动。2）安装前起落架安全销（TASK 32-00-00-481-001 Installation of the Safety Devices on the Landing Gears）【图示说明】 【工卡描述】检查前起落

3、架轮胎的磨损情况，无异常损伤；对于正常磨损，轮胎见第一层线更换；确认机轮组件无明显损伤【参考文献】 TASK 32-41-00-210-002 Inspection/Check of the Wheels and Tires 【检查标准】A对A319/A320飞机安装的米其林轮胎正常磨损（均匀磨损）检查程序如下： 1在特定区域，胎槽超过1/8圆周磨平，更换轮胎；外站飞机可飞回基地再更换轮胎。 2在特定区域，保护帘布层超过1/8圆周暴露，更换轮胎；外站飞机可飞回基地再换轮胎。注1：特定区域指两相邻胎槽之间的胎面区域或胎肩区域。在任一特定区域内，互相不连接的磨损需累加在一起，不同区域内的

4、磨损则不需累加。注2： A319/320使用的米其林轮胎前轮1/8圆周长度为11.8英寸（约29.9厘米），主轮1/8圆周长度为18.1英寸（约45.9厘米）。米其琳轮胎侧面写有“MICHELIN”英文标识。 B异常磨损（MICHELIN）(1)Tread Surface -| OBSERVATION/DAMAGE LIMITS | CORRECTIVE ACTION |-|-| CUTS | | . Radial tires | | - the metallic protector is not damaged (no | Keep the tire on the | wires are b

5、roken) or you cannot see it. | aircraft. | | | - the metallic protector is damaged: | | if CL or LL or DL is more than the limits | Remove the tire. | given on the illustration: | | Table for cut and puncture limits - MICHELIN| | | | - if a cut or injury severs or goes | Remove the tire | across a t

6、read rib. | | | | . Bias tires | | - if casing belt plies are in view | Remove the tire | | | - if a cut or injury severs or goes | Remove the tire. | across a tread rib. | | | | BROKEN AWAY | | . Radial tires | | - if the protector ply is in view on more than| Remove the tire. | 6 cm2 (1 in2). | |

7、| | . Bias tires | | - if the reinforcing ply is in view on more | Remove the tire. | than 6 cm2 (1 in2). | | | | CHEVRON CUTTING | | . Radial tires | | - if chevron cutting goes to and exposes | Remove the tire | the protector ply. | | | | - if chevron cutting causes chunking | Remove the tire | wh

8、ich exposes the protector ply more than | | 6 cm2 (1 in2). | | | | . Bias tires | | - if chevron cutting goes to and exposes | Remove the tire | the reinforcing ply. | | | | - if chevron cutting causes chunking | Remove the tire | which exposes the reinforcing ply more than | | 6 cm2 (1 in2). | | |

9、| FLAT SPOTS | | . Radial tires | | - the flat spot does not go to the protector | Keep the tire on the | ply, the tread depth is more than the | aircraft (but only if the | minimum specified for tire removal | crew feel no vibration | (see "WEAR" paragraph) and there is no | when the land

10、ing gear | start of separation. | retracts or during taxi) | | | - the flat spot goes to the protector ply. | Remove the tire. | | | . Bias tires | | - the flat spot does not go to the reinforcing| Keep the tire on the | ply, the tread depth is more than the | aircraft (but only if the | minimum spe

11、cified for tire removal | crew feel no vibration | (see "WEAR" paragraph) and there is no | when the landing gear | start of separation. | retracts or during taxi) | | | - the flat spot goes to the reinforcing ply. | Remove the tire. | | | WEAR | | . Radial tires | | - if wear goes to the

12、bottom of any groove | Remove the tire | (outer, inner and central) along more than | A direct return-to-base | 1/8 of the circumference at a given | flight is permitted with | location. | tires in this condition. | | | - if the protector ply is in view on more | Remove the tire | than 1/8 of the ci

13、rcumference at a given | A direct return-to-base | location. | flight is permitted with | | tires in this condition. | | | . Bias tires | | - if wear goes to the bottom of any groove | Remove the tire | (outer, inner and central) along more than | A direct return-to-base | 1/8 of the circumference a

14、t a given | flight is permitted with | location. | tires in this condition. | | | - if the reinforcing ply is in view on more | Remove the tire | than 1/8 of the circumference at a given | A direct return-to-base | location. | flight is permitted with | | tires in this condition. | | | TREAD JOINT I

15、S OPENED | | . Radial and bias tires | | - as soon as you can see the opening | Remove the tire. | | | GROOVE CRACKING | | . Radial tires | | - if the protector ply is in view on more than| Remove the tire | 6 mm (0.25in.)(continuous). | | | | . Bias tires | | - if the reinforcing ply is in view on

16、more | Remove the tire | than 6 mm (0.25 in) (continuous). | | | | RIB UNDERCUTTING | | | . Radial and bias tires | | - if undercutting goes more than 5.5 mm | Remove the tire | (0.22 in) below the rib. | |-(2)Sidewalls -| OBSERVATIONS/DAMAGE LIMITS | CORRECTIVE ACTION |-|-| RADIAL or INCLINED CUTS,

17、 CRACKS OR SPLITS | | . Radial and bias tires | | - if the sidewall cords are in view or damaged| Remove the tire | | | SEPARATION/BULGES | | . Radial and bias tires | | - separation on the sidewalls : | Remove the tire. | none permitted. | | | | - blisters or bulges : | Remove the tire. | none perm

18、itted. | | | | WEATHER/OZONE CRACKING | | . Radial and bias tires | | - if weather or ozone checking or cracking | Remove the tire | goes to the cords | |-(3) Beads -| OBSERVATIONS/DAMAGE LIMITS | CORRECTIVE ACTION |-|-| 1. The bead wires are in view (radial and | Remove the tire. | bias tires): non

19、e permitted | | | | 2. The beads or the bead wires are deformed | Remove the tire. | (radial and bias tires): none permitted | | | | | | 3. The part of the bead that touches the rim | | flange is worn (radial only) | | - make an estimate of the depth of the wear : | | . depth > 1 mm (0.0394 in.)

20、| Remove the tire. | . depth < 1 mm (0.0394 in.) | Keep the tire on the | | aircraft. | | | 4. Blisters on the top of the bead above the | Remove the tire | rim flange (radial and bias tires): | | none permitted | | C机轮检查程序1机轮无固定螺栓剪断缺失。2轮缘无损伤，防尘帽在位。3防尘罩固定螺钉及保险完好 4过压释放塞固定完好。【图示说明】 斜交线轮胎 子午线轮胎 前轮胎：

21、无见线、脱层、剥块、起泡、开裂、划伤扎伤超标、漏气；无油污积存防尘罩：固定完好，螺杆保险在位过压释放塞：在位紧固定位红线对齐防尘帽在位螺杆齐全在位【工卡描述】检查前起减震支柱伸长正常并清洁镜面【参考文献】 TASK 12-14-32-614-004 Check Shock Absorber Charge Pressure【检查标准】1 检查减震支柱洁净，无划伤及液压油渗漏；使用清洁前起落架减震支柱。2根据前起铭牌压力-高度表，确认前起减震支柱高度与标准高度的误差在±5%范围内。【图示说明】 【工卡描述】检查前起落架舱门（可视范围内）无损伤；前起落架扭力杆、扭力杆阻尼器、阻力

22、杆、侧撑杆、上锁机构无损伤和渗漏【参考文献】【检查标准】1 检查前起落架五块舱门，特别注意后面的三角形舱门无松动。2 前起落架扭力杆、扭力杆阻尼器、阻力杆、侧撑杆、上锁机构无损伤和渗漏【图示说明】 装好地面安全销舱门：清洁无油迹血迹附着物；无损伤 【工卡描述】检查前轮转弯系统部件、起落架收放作动筒、锁作动筒以及前轮舱内电气导线及插头、液压导管及接头、各附件完好可靠且无液体渗漏【参考文献】【检查标准】 检查标准参照图示说明【图示说明】 转弯灯/滑行灯/起飞灯：清洁；完好；卡箍在位固定滑筒：无油液渗漏，无划痕，无腐蚀；无灰尘、水痕、污迹；伸长正确；封圈无脱出支柱：无损伤，无血污和附着物；附件：连接

23、牢固，无松动脱落刹车指示灯：刹车时灯亮；松刹车时灯灭测试灯工作正常 滑筒润滑加油孔：清洁，无油液漏出转弯作动筒：无渗漏接近电门：牢固，清洁；无损伤扭力连杆：连接固定完好，转动力矩正常导线束：无挤压损坏 电插头：连接完好转弯液压组件固定完好；油管连接处无渗漏【工卡描述】插好左、右主起落架安全销及舱门安全销【参考文献】 TASK 32-12-00-010-001 Open the Main Gear Doors for AccessTASK 32-12-00-410-001 Close the Main Gear Doors after Access【检查标准】 1安装主起落架

24、安全销，注意区分起落架安全销和舱门安全销的区别。【图示说明】 【工卡描述】检查主起落架轮胎胎面及凹槽无切口、断裂、分层、起泡等异常损伤，正常磨损见第一层线更换轮胎。确认机轮各组件无明显损伤，刹车毂完好无液压油渗漏或过热现象【参考文献】 TASK 32-40-00-200-001 Inspection/Check of the Wheels and Tires【检查标准】 A轮胎正常磨损检查程序（MICHELIN）参见前起落架部分 B轮胎异常损伤检查磨损检查程序参见前起落架部分 C机轮检查程序1机轮无固定螺栓剪断缺失。2轮缘无损伤，防尘帽在位。3防尘罩固定螺钉及保险完好 4过压释放塞固

25、定完好。 【图示说明】 主轮胎：无见线、脱层、剥块、起泡、开裂、划伤扎伤超标、漏气；无油污积存防尘罩：固定完好，螺杆保险在位过压释放塞：在位紧固定位红线对齐防尘帽在位螺杆齐全在位 滑筒无油液渗漏、划痕、腐蚀；无灰尘、水痕、污迹；伸长正确；封圈无脱出空地电门:清洁完好在位 刹车作动筒：伸缩量正常；无渗油；无过热现象温度传感器插头：在位指示杆：在位，使用停留刹车时伸出长度不小于0.5MM液压快卸接头：在位锁住，无渗油 舱门：清洁，无损伤；封条完好上锁组件：无渗漏无损伤上锁销：牢固无损伤 【工卡描述】使用停留刹车，目视检查左、右主起落架刹车片指示杆的最小伸出量L，当L1毫米时，更换刹车毂（在外站过夜

26、的飞机, 当在外站L0毫米时，更换刹车毂）【参考文献】AMM 12-14-32-614-004【检查标准】1刹车毂活塞以及液压管漏油渗漏放行标准：刹车状态：2 drops/min释放状态：不允许有渗漏热熔指示销在正确位置（未熔化脱离）。刹车冷却风扇无损伤刹车片指示杆检查标准：使用停留刹车，放行标准L0毫米时，更换刹车毂使用停留刹车，基地航后检查标准L毫米时，更换刹车毂【图示说明】 刹车作动筒：伸缩量正常；无渗油；无过热现象温度传感器插头：在位指示杆：在位，使用停留刹车时伸出长度不小于MM液压快卸接头：在位锁住，无渗油 【工卡描述】检查减震支柱伸长正常并清洁镜面，镜面无刮伤、凹坑等缺陷【参考文献

27、】 TASK 12-14-32-200-001 Inspection of the MLG Shock Absorbers Before Flight【检查标准】1检查主起落架镜面无划伤、凹坑等缺陷；无液压油渗漏；清洁镜面。2减震支柱高度正常 A 左右减震支柱镜面高度不能大于75 mm (2.9527 in.) B任一减震支柱高度不能小于33 mm (1.2992 in.)【图示说明】减震支柱的镜面高度标准见附图，一般在12-15CM；（参考AMM 12-14-32-614-004） 【工卡描述】检查主起落架舱门（可视范围内）无损伤；主起落架扭力杆、扭力杆阻尼器、阻力杆、侧撑杆、上锁

28、机构无损伤和渗漏【参考文献】【检查标准】1 起落架舱门（可视范围内）无损伤2 主起落架扭力杆、扭力杆阻尼器、阻力杆、侧撑杆、上锁机构无损伤和渗漏【图示说明】 【工卡描述】检查主起落架收放作动筒、锁作动筒以及主轮舱内电气导线及插头、液压导管及接头、各附件完好可靠且无液体渗漏【参考文献】【检查标准】 1起落架内各连接附件、搭铁线、保险销、搭铁线、卡箍及标牌完好 2液压软管与卡箍或其他部件无摩擦，软管无缠绕现象注：如果软管上标有使用期限，注意软管在可用期限内。3 液压管（硬管）无弯曲变形、开裂现象，液压弯管及液压管连接处无撞击或松动和液压油渗漏迹象；收放作动筒、锁作动筒及其他液压部件无液压油渗漏迹象

29、；电接头连接良好。【图示说明】 附件连接固定完好,无松动脱落;无油液渗漏;清洁,无血污；无损伤接近电门:清洁无损伤;在位,电插头无松动锁撑作动筒:无渗油侧撑杆 舱门：清洁，无损伤；封条完好上锁组件：无渗漏无损伤上锁销：牢固无损伤 【工卡描述】操作检查刹车蓄压器的预充压力在正常压力范围【参考文献】 TASK 32-45-00-720-002 Functional Check of the Brake Accumulator System with the Parking Brake Applied【检查标准】 确认刹车蓄压器的预充压力在下列表格允许的范围内 【图示说明】 【工卡描述】在ECAM上检查液压油箱（绿-蓝-黄）增压正常，油量正常，如低于绿色指示带的一半，补加液压油并在飞行技术记录本上记录【参考文献】 TASK 12-12-29-611-001 Fill the Hydraulic Fluid Reservoir with a Hand Pump TASK