REMOVAL/INSTALLATION 401 ALL Removal of the Support Fittings of 401 ALL the Trimmable Horizontal Stabilizer (THS) Installation of the Support 413 ALL Fittings of the Trimmable Horizontal Stabilizer (THS)
 TAIL CONE (APU COMPARTMENT) 53-58-00
 DESCRIPTION AND OPERATION 1 ALL General 1 ALL Component Location 1 ALL Description 1 ALL
 General 1 ALL
 Component Description 1 ALL
 TAIL CONE 53-58-11

 REMOVAL/INSTALLATION 401 ALL Removal of the Fuselage Tail Cone 401 ALL Installation of the Fuselage Tail 431 ALL
 53-CONTENTS Page 33 Aug 01/05 R CES

 CHAPTER 53
__________
 FUSELAGE
 TABLE OF CONTENTS
_________________
 SUBJECT_______ CH/SE/SU _ PAGE EFFECTIVITY
________ C ____ ___________ Cone
 MISCELLANEOUS (EG : DRAINS) 53-59-00 DESCRIPTION AND OPERATION 1 ALL General 1 ALL
 Drains 1 ALL
 Component Location 1 ALL
 Description 1 ALL

 MISCELLANEOUS (EG : DRAINS) 53-59-00
 INSPECTION/CHECK 601 ALL Operational Check of Single Drain 601 ALL Pipe Aft of FR70 from Outside Operational Check of Rubber Flap 604 001-049, 051-099 Drain Valve at Bulk Cargo 101-149, 221-221 Compartment Door from Outside 224-224, 228-228
 53-CONTENTS Page 34 Aug 01/05
 CES

 FUSELAGE - GENERAL - DESCRIPTION AND OPERATION______________________________________________
 1. General_______ 
R  The fuselage is a semi-monocoque structure. Light alloy circular frames and 
R  longitudinal stringers support and strengthen the main fuselage skin. There 
R  are no longitudinal stringers in the nose assembly. 
R 
R  The fuselage is made of separate assemblies which are put together to make 
R  the complete fuselage shell. The assemblies are as follows: 
R  - nose forward fuselage, 
R  - forward fuselage, 
R  - center fuselage, 
R  - rear fuselage, 
R  - cone/rear fuselage. 
R  Frames 24, 35, 47 and 70 make the joints for the assemblies. 
R 
R  Pressure bulkheads are installed at FR1 and FR70. The pressure bulkheads and 
R  the fuselage skin make the basic pressurized zone. The cockpit, cabin, 
R  avionics compartment and the FWD and AFT cargo compartments are included in 
R  the pressurized zone. 
R 
R  The structure is made of frames, stringers and skin panels. They are riveted 
R  together to make the fuselage shell. Crossbeams make the shell stronger in 
R  the forward and aft fuselage. Support struts are attached to each end of the 
R  crossbeams (Ref. AMM 533300/534300). Longerons and seat tracks that are 
R  attached to the crossbeams make the cabin floor structure. The belly fairing 
R  primary structure (Ref. AMM 533500) is installed on the exterior of the 
R  lower fuselage between FR31/35 and FR48/FR53. It is an extension to the 
R  lower fuselage and contains the air-conditioning and hydraulic services 
R  equipment. 
R 
R  The cabin floor structure divides the fuselage into two areas, the upper 
R  fuselage and the lower fuselage. The upper fuselage includes the cockpit and 
R  the cabin. The lower fuselage includes the avionics compartments, nose and 
R  main gear bays and the FWD and AFT cargo compartments. Crossbeams and 
R  support struts support the cabin floor structure at STGR23. 
R 
R  The floor panels are made of a honeycomb core which is bonded between Glass-
R  fiber Reinforced Plastic (GFRP) sheets (Ref. AMM 533200/534200). 
R 
R  The radome, wing center box, nose and main gear bays, belly fairing and 
R  cone/rear fuselage are not in the pressurized zone. 
R 
R  Skin stiffeners make the fuselage skin stronger. They are riveted to the 
R  skin in areas of high stress (door openings, emergency exits, cabin windows, 
R  etc.). 
R

 
EFF : ALL

  53-00-00Page 1
 Aug 01/04 CES 

 The cabin windows are installed between STGR14 and STGR18 (Ref. AMM 562100).
 2. Component Location
__________________
 **ON A/C 001-049, 051-099, 101-149, 201-299,

 (Ref. Fig. 001) R **ON A/C 151-199, 401-499,
 (Ref. Fig. 001A)
 **ON A/C 301-399,
　
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