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AIPC
Aircraft Illustrated Parts Catalog
ZEV · Rev 6 · 15 Jun 2024 · D638A001-ZEV-0298
AMM
Aircraft Maintenance Manual, Part II
ZEV · Rev 84 · 15 Jun 2024 · D633A101-ZEV
CHAPTER 05
TIME LIMITS/MAINTENANCE CHECKS
S
CHAPTER 06
DIMENSIONS AND AREAS
S
CHAPTER 07
LIFTING AND SHORING
S
CHAPTER 08
LEVELING AND WEIGHING
S
CHAPTER 09
TOWING AND TAXIING
S
CHAPTER 10
PARKING AND MOORING
S
CHAPTER 11
PLACARDS AND MARKINGS
S
CHAPTER 12
SERVICING
S
CHAPTER 20
STANDARD PRACTICES
S
CHAPTER 21
AIR CONDITIONING
S
CHAPTER 22
AUTOFLIGHT
S
CHAPTER 23
COMMUNICATIONS
S
CHAPTER 24
ELECTRICAL POWER
S
CHAPTER 25
EQUIPMENT/FURNISHINGS
S
CHAPTER 26
FIRE PROTECTION
S
CHAPTER 27
FLIGHT CONTROLS
S
CHAPTER 28
FUEL
S
CHAPTER 29
HYDRAULIC POWER
S
SECTION 29-09
HYDRAULIC RESERVOIR PRESSURIZATION SYSTEM
S
SECTION 29-11
HYDRAULIC SYSTEMS A AND B
S
SECTION 29-18
RESERVOIR FILL
S
SECTION 29-21
STANDBY HYDRAULIC SYSTEM
S
SECTION 29-22
HYDRAULIC POWER TRANSFER UNIT (PTU) SYSTEM
S
SECTION 29-31
SYSTEM PRESSURE TRANSMITTER
S
SECTION 29-32
HYDRAULIC FLUID OVERHEAT WARNING SYSTEM
S
SECTION 29-33
HYDRAULIC FLUID QUANTITY
S
SECTION 29-34
PUMP LOW PRESSURE WARNING SYSTEM
S
CHAPTER 30
ICE AND RAIN PROTECTION
S
CHAPTER 31
INDICATING/RECORDING SYSTEMS
S
CHAPTER 32
LANDING GEAR
S
CHAPTER 33
LIGHTS
S
CHAPTER 34
NAVIGATION
S
CHAPTER 35
OXYGEN
S
CHAPTER 36
PNEUMATIC
S
CHAPTER 38
WATER/WASTE
S
CHAPTER 47
INERT GAS SYSTEM
S
CHAPTER 49
AUXILIARY POWER UNIT
S
CHAPTER 51
STRUCTURES
S
CHAPTER 52
DOORS
S
CHAPTER 53
FUSELAGE
S
CHAPTER 54
NACELLES/PYLONS
S
CHAPTER 55
STABILIZERS
S
CHAPTER 56
WINDOWS
S
CHAPTER 57
WINGS
S
CHAPTER 70
STANDARD PRACTICES
S
CHAPTER 71
POWER PLANT
S
CHAPTER 72
ENGINE
S
CHAPTER 73
ENGINE FUEL AND CONTROL
S
CHAPTER 74
IGNITION
S
CHAPTER 75
AIR
S
CHAPTER 76
ENGINE CONTROLS
S
CHAPTER 77
ENGINE INDICATION
S
CHAPTER 78
EXHAUST
S
CHAPTER 79
OIL
S
CHAPTER 80
STARTING
S
FIM
Combined Fault Reporting And Fault Isolation Manual
ZEV · Rev 84 · 15 Jun 2024 · D633A103-ZEV
SDS
Aircraft Maintenance Manual, Part 1
ZEV · Rev 84 · 15 Jun 2024 · D633A101-ZEV
SRM
Structural Repair Manual
BCG · Rev 20 · 10 Mar 2024 · D634A209
SSM
System Schematic Manual
ZEV · Rev 0 · 15 Jun 2023 · D280A618
SWPM
Standard Wiring Practices Manual
BCG · Rev 86 · 15 Jun 2024 · D6-54446
WDM
Wiring Diagram Manual
ZEV · Rev 0 · 15 Jun 2023 · D280A518
   
      EXPORT CONTROLLED
Issue Date: 15 Jun 2024
发行日期:2024年6月15日
  the boeing company
 
 

TASK 29-00-00-790-801 任务 29-00-00-790-801

 
 

2.  Hydraulic System External Leakage Check (Table 602)
2.液压系统外部泄漏检查(表602)

 
 

A.   General 一个。  常规

 
 

(1)  The table of permitted external leakage gives the maximum external leakage rates for different parts for normal operation and for dispatch of the airplane to avoid a delay. You must make a decision on the total leakage you will permit from all of the parts.
(1) 允许外部泄漏表给出了不同部件的最大外部泄漏率,用于正常运行和飞机调度以避免延误。您必须决定所有部件允许的总泄漏量。

 
 

(2)  It is possible that a crack in a static seal housing can cause a leakage. This leakage can increase with increased pressure.
(2) 静密封外壳的裂纹可能会导致泄漏。这种泄漏会随着压力的增加而增加。

 
 

(3)  Some NAS1611 seals can leak at cold temperatures that occur in flight. If there is evidence of leakage near one of these seals that cannot be duplicated on the ground, the seal should be replaced with an improved seal (SL 20-048). Areas where these seals are used include:
(3) 一些NAS1611密封件在飞行中发生的低温下可能会泄漏。如果其中一个密封件附近有泄漏的证据,而这些密封件无法在地面上复制,则应用改进的密封件(SL 20-048)替换密封件。使用这些密封件的领域包括:

 
 

(a)  Leading edge swivel assembly (if evidence of leakage, replace assembly with improved seal assembly)
(a) 前缘旋转组件(如果有泄漏迹象,请用改进的密封组件替换组件)

 
 

(b)  Trailing edge swivel assembly (if evidence of leakage, replace assembly with improved seal assembly)
(b) 后缘旋转组件(如果有泄漏迹象,请用改进的密封组件替换组件)

 
 

(c)  Flight control actuators
(c) 飞行控制执行器

 
 

(d)  Brake metering valves
(d) 制动计量阀

 
 

(e)  MLG retract actuator
(e) MLG缩回执行器

 
 

(f)  MLG shimmy damper
(f) MLG摆动阻尼器

 
 

(g)  Standby rudder PCU
(g) 备用方向舵 PCU

 
 

(h)  Main rudder PCU.
(h) 主舵PCU。

 
 

(4)  Do a leakage check of these components:
(4) 对以下部件进行泄漏检查:

 
 

(a)  In the wing leading edge and trailing edge area:
(a) 在机翼前缘和后缘区域:

 
 

1)  Tighten tube and fitting connections to the correct torque.
1) 将管子和接头连接拧紧到正确的扭矩。

 
 

a)  Use table 405 in Flareless Tubing Assembly Installation, TASK 20-10-51-400-804 to find the correct torque values.
a) 使用无喇叭口管组件安装,任务 20-10-51-400-804 中的表 405 查找正确的扭矩值。

 
 

b)  Replace any tube or fitting connections that continue to leak.
b) 更换任何继续泄漏的管子或接头连接。

 
 

(b)  In the rudder and tail area:
(b) 在方向舵和尾部区域:

 
 

1)  Tighten tube, hose, and fitting connections to the correct torque.
1) 将管子、软管和接头连接拧紧到正确的扭矩。

 
 

a)  Use table 405 in Flareless Tubing Assembly Installation, TASK 20-10-51-400-804 to find the correct torque values.
a) 使用无喇叭口管组件安装,任务 20-10-51-400-804 中的表 405 查找正确的扭矩值。

 
 

b)  Replace any tube, hose, or fitting connections that continue to leak.
b) 更换任何继续泄漏的管子、软管或接头连接。

 
 

(c)  Replace these components in the main landing gear wheel well if there is any evidence of leakage:
(c) 如果有任何泄漏迹象,请更换主起落架轮中的这些部件:

 
 

1)  Hydraulic fuses 1) 液压保险丝

 
 

2)  Cracked hydraulic fittings
2) 液压配件破裂

 
 

3)  Loose frangible fittings.
3)易碎配件松动。

 
 

(5)  These conditions are important when you do a leakage check for the various components:
(5) 在对各种组件进行泄漏检查时,这些条件很重要:

 
 

(a)  The seal at the B-nut tube connections is made by metal-to-metal surfaces. If a leak will not stop when you tighten the B-nut to the correct torque, the joint is defective and must be repaired.
(a) B型螺母管连接处的密封件由金属对金属表面制成。如果在将 B 型螺母拧紧到正确的扭矩时泄漏不会停止,则接头有缺陷,必须修理。

 
 

(b)  Supply hydraulic pressure to the component while you measure the leakage.
(b) 在测量泄漏时向组件提供液压。

 
 

(c)  If it is possible, operate the actuators to see if the leakage changes during the travel.
(c) 如果可能,操作执行器以查看泄漏在行驶过程中是否发生变化。

 
 

(d)  Make sure that the leak is not a type which will increase to a much higher rate with time. Use the type of leak and the length of time the component is pressurized to make this decision.
(d) 确保泄漏不是会随着时间的推移而增加到更高速率的类型。使用泄漏类型和组件加压的时间长度来做出此决定。

 
 

(e)  Make sure that all the reservoirs are full before each flight.
(e) 确保每次飞行前所有储液罐都已满。

 
 

(f)  After each flight, do a check of the components which have a leak.
(f) 每次飞行后,检查有泄漏的部件。

 
 

(g)  If hydraulic fluid collects in the area of the leak, it must not cause damage to the airplane equipment.
(g) 如果液压油积聚在泄漏区域,则不得对飞机设备造成损坏。

 
 

B.   References B.  引用

 
 

Reference 参考

Title 标题

 

12-40-00-100-801

Clean (Wet Wash) the External Surfaces of the Airplane (P/B 201)
清洁(湿洗)飞机的外表面(P/B 201)

 

12-40-00-100-803

Clean (Waterless Wash) the External Surfaces of the Airplane (P/B 201)
清洁(无水清洗)飞机外表面 (P/B 201)

 

20-10-51-400-804

Flareless Tubing Assembly Installation (P/B 401)
无喇叭口管组件安装 (P/B 401)

 

29-11-00-860-801

Hydraulic System A or B Pressurization (P/B 201)
液压系统 A 或 B 加压 (P/B 201)

 

29-11-00-860-804

Hydraulic System A or B Pressurization with an Engine-Driven Pump (EDP) (P/B 201)
使用发动机驱动泵 (EDP) 进行液压系统 A 或 B 增压 (P/B 201)

 

29-11-00-860-805

Hydraulic System A or B Power Removal (P/B 201)
液压系统 A 或 B 动力移除 (P/B 201)

 

29-11-11 P/B 401 29-11-11 P/B 401

HYDRAULIC SYSTEMS A AND B ENGINE-DRIVEN PUMP (EDP) - REMOVAL/INSTALLATION
液压系统 A 和 B 发动机驱动泵 (EDP) - 拆卸/安装

 

29-21-00-000-801

Standby Hydraulic System Pressurization (P/B 201)
备用液压增压系统 (P/B 201)

 

29-21-00-000-802

Standby Hydraulic System Power Removal (P/B 201)
备用液压系统断电 (P/B 201)

 

32-00-01-480-801

Landing Gear Downlock Pins Installation (P/B 201)
起落架下锁销安装 (P/B 201)

 

32-41-41-700-802

Main Landing Gear Brake Fast Check (Wheel Installed on the Airplane) (P/B 601)
主起落架制动器快速检查(安装在飞机上的轮子)(P/B 601)

 

71-00-00-700-819-F00

Stop the Engine Procedure (Usual Engine Stop) (P/B 201)
停止发动机程序(通常的发动机停止)(P/B 201)

 

78-31-00-700-801-F00

Thrust Reverser Normal Operation Test (P/B 501)
反推器正常运行试验 (P/B 501)

 
 
 

C.   Location Zones
C. 位置区域

 
 

Zone 

Area 面积

 

100

Lower Half of Fuselage 机身下半部分

 

200

Upper Half of Fuselage 机身上半部分

 

300

Empennage 尾翼

 

400

Powerplant and Nacelle Struts
动力装置和机舱支柱

 

500

Left Wing 左翼

 

600

Right Wing 右翼

 
 
 

D.   Hydraulic System External Leakage Check
D. 液压系统外部泄漏检查

 
 

SUBTASK 29-00-00-480-021 
子任务 29-00-00-480-021

 
 

WARNING:  MAKE SURE THAT THE DOWNLOCK PINS ARE INSTALLED IN ALL OF THE LANDING GEAR. WITHOUT THE DOWNLOCK PINS, THE LANDING GEAR CAN RETRACT AND CAUSE INJURIES TO PERSONS AND DAMAGE TO EQUIPMENT.
警告:确保所有起落架中都安装了下锁销。如果没有下锁销,起落架可能会缩回并造成人员伤害和设备损坏。

 
 

(1)  If the downlock pins are not installed in the nose and main landing gear, do this task: Landing Gear Downlock Pins Installation, TASK 32-00-01-480-801.
(1) 如果前起落架和主起落架中未安装下锁销,请执行此任务:起落架下锁销安装,任务 32-00-01-480-801。

 
 

SUBTASK 29-00-00-010-001 
子任务 29-00-00-010-001

 
 

(2)  Get access to the part that has a leak.
(2) 接触有泄漏的部件。

 
 

SUBTASK 29-00-00-160-001 
子任务 29-00-00-160-001

 
 

(3)  Clean hydraulic fluid from the part, do this task: Clean (Wet Wash) the External Surfaces of the Airplane, TASK 12-40-00-100-801 or Clean (Waterless Wash) the External Surfaces of the Airplane, TASK 12-40-00-100-803.
(3) 清洁零件上的液压油,执行以下任务:清洁(湿洗)飞机的外表面,任务 12-40-00-100-801 或清洁(无水洗)飞机的外表面,任务 12-40-00-100-803。

 
 

SUBTASK 29-00-00-860-103 
子任务 29-00-00-860-103

 
 

WARNING:  KEEP PERSONS AND EQUIPMENT AWAY FROM THE FLIGHT CONTROL SURFACES. THE AILERONS, ELEVATORS, RUDDER, FLAPS, SLATS, SPOILERS, STABILIZER AND NOSE GEAR CAN MOVE SUDDENLY WHEN YOU SUPPLY HYDRAULIC POWER. THIS CAN CAUSE INJURY TO PERSONS AND DAMAGE TO EQUIPMENT.
警告:使人员和设备远离飞行控制表面。当您提供液压动力时,副翼、升降舵、方向舵、襟翼、板条、扰流板、稳定器和前起落架会突然移动。这可能会导致人身伤害和设备损坏。

 
 

(4)  Pressurize the applicable hydraulic system.
(4)对适用的液压系统加压。

 
 

(a)  To pressurize the hydraulic system A or B, do this task: Hydraulic System A or B Pressurization, TASK 29-11-00-860-801.
(a) 要对液压系统 A 或 B 加压,请执行以下任务:液压系统 A 或 B 加压,任务 29-11-00-860-801。

 
 

(b)  To pressurize the standby hydraulic system, do this task: Standby Hydraulic System Pressurization, TASK 29-21-00-000-801.
(b) 要对备用液压系统加压,请执行以下任务:备用液压系统加压,任务 29-21-00-000-801。

 
 

SUBTASK 29-00-00-790-004 
子任务 29-00-00-790-004

 
 

(5)  Do these steps to find the leakage rate:
(5)按照以下步骤求出泄漏率:

 
 

(a)  If it is possible, move the part through approximately three full cycles.
(a) 如果可能,将零件移动大约三个完整周期。

 
 

(b)  Measure the leakage rate of the part.
(b) 测量零件的泄漏率。

 
 

1)  For dynamic seals, measure the leakage rate when the part stops and moves, if it is possible.
1) 对于动态密封件,如果可能,测量零件停止和移动时的泄漏率。

 
 

(c)  Compare the leakage rate of the part with the external leakage limits (Table 602).
(c) 将零件的泄漏率与外部泄漏限值进行比较(表 602)。

 
 

NOTE:  For the Thrust Reverser actuator leakage limit rate, see TASK 78-31-00-700-801-F00.
注意: 对于反推器执行器泄漏限制率,请参阅任务 78-31-00-700-801-F00。

 
 

(d)  Remove the pressure from the applicable hydraulic system.
(d) 从适用的液压系统中移除压力。

 
 

1)  To remove the pressure from the hydraulic system A or B, do this task: Hydraulic System A or B Power Removal, TASK 29-11-00-860-805.
1) 要从液压系统 A 或 B 中移除压力,请执行以下任务:液压系统 A 或 B 电源移除,任务 29-11-00-860-805。

 
 

2)  To remove the pressure from the standby hydraulic system, do this task: Standby Hydraulic System Power Removal, TASK 29-21-00-000-802.
2) 要从备用液压系统中移除压力,请执行以下任务:备用液压系统电源移除,任务 29-21-00-000-802。

 
 

(e)  If the leakage rate is more than the external leakage limits, repair the cause of the leak (Table 602).
(e) 如果泄漏率超过外部泄漏限值,则修复泄漏原因(表 602)。

 
 

(f)  To remove the hydraulic fluid from the area of the leakage, do this task: Clean (Wet Wash) the External Surfaces of the Airplane, TASK 12-40-00-100-801 or Clean (Waterless Wash) the External Surfaces of the Airplane, TASK 12-40-00-100-803.
(f) 要从泄漏区域清除液压油,请执行以下任务:清洁(湿洗)飞机的外表面,任务 12-40-00-100-801 或清洁(无水洗涤)飞机的外表面,任务 12-40-00-100-803。

 
 

Table 602. Hydraulic Fluid Leakage Limits
表 602.液压油泄漏限值

 
 

COMPONENTS 组件

NORMAL OPERATION LIMITS *[1] *[2]
正常操作限值 *[1] *[2]

DISPATCH LIMITS TO AVOID DELAY *[1] *[2]
避免延迟的调度限制 *[1] *[2]

 

1. B-Nuts, Tubing and Hoses *[3]
1. B型螺母、管路和软管 *[3]

No leakage *[4] *[5]
无泄漏 *[4] *[5]

No leakage *[4] *[5]
无泄漏 *[4] *[5]

 

2. Quick Disconnect Fitting Seals
2. 快速断开接头密封件

1 drop in 10 min.
10分钟内滴1滴。

1 drop in 10 min.
10分钟内滴1滴。

 

3. Static Seals *[6]
3. 静态密封 *[6]

1 drop in 10 min.
10分钟内滴1滴。

Operator decides 运营商决定

 
 

A. MLG Shimmy Dampers *[7]
A. MLG 摆动阻尼器 *[7]

1 drop in 1 min.
1 分钟内滴 1 滴。

1 drop in 1 min.
1 分钟内滴 1 滴。

 

4. Dynamic seals *[8]
4. 动态密封 *[8]

   
 

A. Engine-Driven Pump A. 发动机驱动泵

30 drops in 1 min.
1分钟内滴30滴。

60 drops in 1 min.
1分钟内滴60滴。

 
 

B. Electric Motor- Driven Pump
B. 电动泵

   
 

(1) ABEX/PARKER (1) ABEX/派克

10 drops in 1 min.
1 分钟内滴 10 滴。

20 drops in 1 min.
1分钟内滴20滴。

 

(2) Vickers (Eaton) (2) 维克斯(伊顿)

20 drops in 1 min.
1分钟内滴20滴。

30 drops in 1 min.
1分钟内滴30滴。

 

(3) Vickers (Eaton) Standby Pump
(3) 维氏(伊顿)备用泵

10 drops in 1 min.
1 分钟内滴 10 滴。

20 drops in 1 min. (Correct at the next maintenance opportunity)
1 分钟内滴 20 滴(在下次维护机会时纠正)

 
 

C. Power Transfer Unit C. 动力传输单元

10 drops in 1 min.
1 分钟内滴 10 滴。

20 drops in 1 min.
1分钟内滴20滴。

 
 

D. Other dynamic seals when they stop, at any pressure *[9]
D. 其他动态密封,当它们停止时,在任何压力下 *[9]

1 drop in 10 min. (No repair is necessary)
10 分钟内滴 1 次(无需维修)

30 drops in 1 min. (Correct at the next maintenance opportunity)
1 分钟内滴 30 滴(在下次维护机会时纠正)

 
 

E. Other dynamic seals when they move *[9]
E.其他动态密封件移动时 *[9]

1 drop each cycle 每个循环 1 滴

1 drop each cycle 每个循环 1 滴

 

5. Landing gear brake assemblies
5. 起落架制动总成

No leakage 无泄漏

See Main Landing Gear Brake Fast Check (Wheel Installed on the Airplane), TASK 32-41-41-700-802
参见主起落架制动器快速检查(安装在飞机上的轮子),任务 32-41-41-700-802

 

Footnote Information: 附注信息:

*[1] There are approximately 20 drops in a cubic centimeter or 75600 drops in a gallon.
*[1] 每立方厘米大约有 20 滴或一加仑大约有 75600 滴。

Footnote Information: 附注信息:

*[2] Airplane can still dispatch if the leakage is above the Normal Limit but under the Dispatch Limit. The intent of this table specifying Normal Limits and Dispatch Limits are to distinguish the leakage rates that may be allowable for dispatch to avoid delays, but are not considered normal and maintenance action should be taken. Leakage checks are recommended after each flight when leakage rates are above Normal Limits but below Dispatch Limits.
*[2] 如果泄漏量高于正常限值但低于调度限值,飞机仍然可以调度。此表指定“正常限值”和“调度限值”的目的是区分可能允许调度以避免延迟但不被视为正常且应采取维护措施的泄漏率。当泄漏率高于正常限值但低于调度限值时,建议在每次飞行后进行泄漏检查。

Footnote Information: 附注信息:

*[3] Make sure the connection is tightened to the correct torque.
*[3] 确保连接拧紧到正确的扭矩。

Footnote Information: 附注信息:

*[4] Leakage is defined as the escape of fluid from any point of the fitting assembly including the fitting-tube junction, which returns within a time period after being cleaned up (see *[5]). This junction is defined to include one tube outside diameter in length beyond the fitting envelope. The fitting envelope is the area from free parent tube material to free parent tube material or boss.
*[4] 泄漏被定义为流体从接头组件的任何点(包括接头管接头)逸出,该流体在清理后的一段时间内返回(参见 *[5])。该结部被定义为包括一根外径超出接头包络线的管子。管接头包络是从游离母管材料到游离母管材料或凸台的区域。

Footnote Information: 附注信息:

*[5] Evidence of fluid on a fitting joint does not always indicate a leakage condition. For example, a fitting joint may appear moist due to: (a) residual assembly lubricant (MCS352); (b) residual fluid from previous leakage that was corrected but not properly cleaned up or; (c) residual fluid from previous leakage that was corrected and properly cleaned up, but later drained from an inaccessible area (such as fluid from threads within a flareless joint which does not return when re-wiped).
*[5] 接头上有液体的证据并不总是表明存在泄漏情况。例如,由于以下原因,接头可能显得潮湿:(a) 残留的装配润滑剂 (MCS352);(b) 先前泄漏的残余液体,该液体已得到纠正,但未得到适当清理,或;(c) 先前泄漏的残留液体,这些液体已得到纠正和适当清理,但后来从无法进入的区域排出(例如无喇叭口接头内螺纹的液体,在重新擦拭时不会返回)。

Footnote Information: 附注信息:

*[6] A static seal is a seal between two parts that do not move relative to each other (Example: manifold cover, pump housing cover).
*[6] 静态密封是两个部件之间的密封,它们不会相对移动(例如:歧管盖、泵壳盖)。

Footnote Information: 附注信息:

*[7] Leakage may be checked while the airplane is parked by cycling the landing gear lever with the “A” hydraulic system pressurized. Make sure the landing gear lock pins are installed before cycling the lever.
*[7] 在飞机停放时,可以通过在“A”液压系统加压的情况下循环起落架杆来检查泄漏。在循环操纵杆之前,确保安装起落架锁销。

Footnote Information: 附注信息:

*[8] A dynamic seal is a seal between two parts that move relative to each other (Example: piston rod seal, pump shaft seal, swivel seal).
*[8] 动态密封是两个相互相对移动的部件之间的密封件(例如:活塞杆密封件、泵轴密封件、旋转密封件)。

Footnote Information: 附注信息:

*[9] The center vent on the rudder PCU is actually the drain for the two dynamic seals. Thus, when evaluating leakage from the center vent at the rudder PCU, all dynamic seal limits can be doubled.
*[9] 方向舵 PCU 上的中央通风口实际上是两个动态密封件的排水口。因此,在评估方向舵 PCU 中心通风口的泄漏时,所有动态密封限值都可以加倍。

 
 

SUBTASK 29-00-00-360-001 
子任务 29-00-00-360-001

 
 

(6)  To check the leakage of the Engine Driven Pump (EDP), pressurize the hydraulic system by doing this task: Hydraulic System A or B Pressurization with an Engine-Driven Pump (EDP), TASK 29-11-00-860-804.
(6) 要检查发动机驱动泵 (EDP) 的泄漏,请执行以下任务对液压系统加压:使用发动机驱动泵 (EDP) 进行液压系统 A 或 B 加压,任务 29-11-00-860-804。

 
 

(a)  Stop the applicable engine when the hydraulic power has stabilized at 2800 psig (19,305 kPa) - 3200 psig (22,063 kPa) (TASK 71-00-00-700-819-F00).
(a) 当液压功率稳定在 2800 psig (19,305 kPa) - 3200 psig (22,063 kPa) 时停止适用的发动机(任务 71-00-00-700-819-F00)。

 
 

NOTE:  This task stops the hydraulic pump but the hydraulic system will remained pressurized.
注意: 此任务停止液压泵,但液压系统将保持加压状态。

 
 

(b)  Compare the leakage rate of the EDP with the external leakage limits in Table 602.
(b) 将EDP的泄漏率与表602中的外部泄漏限值进行比较。

 
 

(c)  If the leakage rate is more than the external leakage limits in the table, do the appropriate tasks to replace the EDP (PAGEBLOCK 29-11-11/401).
(c) 如果泄漏率大于表中的外部泄漏限值,请执行适当的任务以更换 EDP ( PAGEBLOCK 29-11-11/401)。

 
 

(d)  To remove the hydraulic fluid from the area of the leakage, do this task: Clean (Wet Wash) the External Surfaces of the Airplane, TASK 12-40-00-100-801 or Clean (Waterless Wash) the External Surfaces of the Airplane, TASK 12-40-00-100-803.
(d) 要从泄漏区域清除液压油,请执行以下任务:清洁(湿洗)飞机的外表面,任务 12-40-00-100-801 或清洁(无水洗)飞机的外表面,任务 12-40-00-100-803。

 
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Corrective Actions
737-800TASK 29-00-00-790-801Rev Date : 01 Jan 1970Copyright © 2007, 2014 BoeingBoeing ProprietaryECCN 9E991