曝光臺 注意防騙 網(wǎng)曝天貓店富美金盛家居專營店坑蒙拐騙欺詐消費(fèi)者

R  milled. Stringers are riveted to them on the inner surface to make 
R  them stronger. Two lower side panels, a forward and a rear panel on 
R  each side, complete the center fuselage skin. They include: 
R  - a forward lower side panel, left and right, installed in front of 
R  the wing center box between FR35.8 and FR36. Each panel, complete 
R  with stringers on the outer face, is chemically milled. The panel 
R  contains openings for systems interface between the fuselage and 
R  the wing leading edge. You can get access to both forward lower 
R  side panels from behind the belly fairing structure, 
R  - a rear lower side-panel, left and right. The panels surround the 
R  wheel openings of the main landing-gear bay aft of the wing 
R  centerbox structure. They are installed between FR42 and FR47 and 
R  span between the middle side panel and keel beam structure. Two 
R  slanting frames (connected together at one end to make an inverted 
R  V-shape) support and strengthen each panel at the edges of the 
R  wheel opening. The panels are chemically milled and stringers are 
R  riveted on their outer face. You can get access to both rear lower 
R  side panels from behind the belly fairing structure. 
R  (3) Stringers and Skin Stiffeners 
R  (a) The stringers are the longitudinal stiffeners of the fuselage 
R  shell. They are made of aluminum-alloy Z-section which are formed 
R  or machined. They are riveted between the frames and the skin 
R  panels. 
R  (b) The skin stiffeners make the skin stronger. They are riveted to 
R  the skin in areas of high stress (fuselage section and skin panel 
R  joints, cabin windows, emergency exits and door openings). Skin 
R  stiffeners are chemically milled or machined from forgings. 

 

R **ON A/C 001-049, 051-099, 101-149, 201-299,
 (4) Floor Structure (Ref. Fig. 003) The passenger compartment is a pressurized zone. The area below the passenger compartment floor-structure is unpressurized. The floor pressure limit-zone consists of the top-skin panel of the wing center-box and two adjacent diaphragms. The diaphragms forward of the wing box connect with a pressure bulkhead installed in the lower part of FR35. The rear diaphragm (which is also the top panel of the main landing-gear bay) connects with the pressure bulkhead at FR46. Longitudinal beams extend the length of the center fuselage and hold the passenger compartment floor above the pressure limit structure. The forward beam section is supported between a crossbeam installed at FR35 and the wing center box. The rear beam section is supported between the wing box and a crossbeam installed at FR47. Support struts are attached to the crossbeams at each end. Seat and floor support tracks are installed on the longitudinal beams and screws attach floor panels to the track structure. You can remove the floor panels for maintenance work, or to replace them. The longitudinal beams, crossbeams, support-struts, seat-tracks and floor support tracks are made of aluminum alloy. They are either extruded or milled. The floor panels are made of honeycomb core which is bonded between Glassfiber Reinforced Plastic (GFRP)

 Center Fuselage - Floor Structure Figure 003 
R  EFF :  001-049, 051-099, 101-149, 201-299,  53-31-00 Page 14 May 01/05
 CES 

 

R **ON A/C 151-199, 401-499,
 (4) Floor Structure (Ref. Fig. 003A) The passenger compartment is a pressurized zone. The area below the passenger compartment floor-structure is unpressurized. The floor pressure limit-zone consists of the top-skin panel of the wing center-box and two adjacent diaphragms. The diaphragms forward of the wing box connect with a pressure bulkhead installed in the lower part of FR35. The rear diaphragm (which is also the top panel of the main landing-gear bay) connects with the pressure bulkhead at FR46. Longitudinal beams extend the length of the center fuselage and hold the passenger compartment floor above the pressure limit structure. The forward beam section is supported between a crossbeam installed at FR35 and the wing center box. The rear beam section is supported between the wing box and a crossbeam installed at FR47/51. Support struts are attached to the crossbeams at each end. Seat and floor support tracks are installed on the longitudinal beams and screws attach floor panels to the track structure. You can remove the floor panels for maintenance work, or to replace them. The longitudinal beams, crossbeams, support-struts, seat-tracks and floor support tracks are made of aluminum alloy. They are either extruded or milled. The floor panels are made of honeycomb core which is bonded between Glassfiber Reinforced Plastic (GFRP)
　
中國航空網(wǎng) m.k6050.com
航空翻譯 www.aviation.cn
本文鏈接地址：A320飛機(jī)維護(hù)手冊 AMM FUSELAGE 機(jī)身2(45)