Fuselage C

الدورة التنشيطية للتجاوزات المسموحة فى التجميع للطائرة K8-E هذه المحاضرات للتدريب فقط و لا تستخدم فى التجميع بل يتم استخدام المواصفات المعتمدة L8-JT

2-Fuselage اعداد مجموعة الدعم الفنى اكتوبر 2007

ٍ Specification for installation of the Fuselage مواصفات تجاوزات أعمال التجميع لجسم الطائرة K8-E
L8-JT01-1 Book (ED 111)
كل التعليمات المشار اليها على الرسم تطبق و استعمال المواصفات فى التعليمات الاضافية

1-Fueslage Structure جسم الطائرة
frames 1 and 4 is the nose landing gear well and the front & equipment bay.
frames 4 and 9 is the front and rear cockpits and the second equipment bay.
No.1 and No.2 fuel tank baths, air intake duct, air brake bay and the fuselage/wing
gun pod is suspended between frames 7 and 12.
frames 21 and 32 is for engine mounting & fitting of horizontal and vertical stabilizer

Frame 1,2,3,3B,4,5,5A,5E,6,7,7C,8,canted frame 9 contour tolerance  1.0 Frame 10,11,12,13,14,15,16,17,18,19,20,21,22,23,24,25,26,27,28,29,30,31,32, exhaust nozzle  1.2 Fuselage contour tolerance تجاوزات الجسم الخارجية After installation check تجاوزات الجسم بالنسبة الى مساطر الجيكات Frame 1,4,7,9 contour tolerance with the assy. JIG  1.2 Frame 12,14,16,21,27 ,37 contour tolerance with the assy. JIG  1.5 One max. tolerance in each frame allowed to be  2.0 and change uniformly within length  200 mm

Fuselage frame axis shift tolerance تجاوزات انحراف محاور الفريمات Frame axis shift  1.0 for frames 4,5A,6,7,7A,7C,12,14,16,21,23,25,26,27,29,31 Frame axis shift  2.0 for frames 1,2,3B,5E,8,9,10,11,13,15,17,20,22,24,28,30

Nose Dome and fuselage skin butt joint tolerance تجاوزات خط تقابل الاسكنات بين مقدمة الجسم و الكابينة Skin butt joint higher + 1.0 mm or lower- 0.8 mm than fuselage skin And in case+ 2.0 mm higher and- 1.0 lower chamfer 1:3

fuselage skins butt joint tolerance * Gap 1.0 longitudinal , and gap 1.2 is allowed for 40% of the seam length * Gap 0.8 laterally , and gap 1.2 is allowed for 40% of the seam length * higher skin is allow to chamfer 1:3 , paint H06-2

Air intake contour tolerance Contour lips tolerance  0.8 Side wall allowed 2 areas  1.0 and change uniformly Side wall check with assy. Jig template at frames 9 , 10,11,12,17,18,19,20,21  1.0 One dent at each frame 1.5 mm and change uniformly within length  200 mm

Special attention to riveting in the air inlet ,  2 ,  3.5 Rivet , threaded hollow rivet are not allowed No sink rivet Air intake stringer shift  2 mm Oversize for rivet  4 mm and not more than 10% of the total no. of rivets Air intake General recommendation مدخل الهواء BUTT joint of the skin of Air intake tolerance تجاوزات خط تقابل الاسكنات فى مدخل الهواء Gap 1.5 longitudinal , and after frame 12 gap 2.0 is allowed for 40% of the seam length Gap 0.8 laterally , and gap 1.2 is allowed for 40% of the seam length

fuselage Assembly. تجميع الجسم
Shim  1.5 mm is allowed (skin-fitting ) to add to smooth the contour
of the fuselage
Shim  2.0 mm as a wedge is allow to added
Shim along frame  1.2 mm
Joggle transition allowed 5 mm see fig
Countersink bolt protrusion is allow to flush
and allow to have a 0.3 mm protrusion

Skin butt seam joint ripple C
step  1 mm of the Access cover and skin seam joint
and higher skin is allow to chamfer 1:3 , paint H06-2
step  1.5 mm of the Engine Access doors, equipment access doors before frame 9 and skin seam joint

BUTT joint of the skin and access cover tolerance Gap 1.0 longitudinal , Gap 0.8 laterally , and gap 1.2 is allowed for 30% of the seam length Fuselage and wing and tail fairing Nut plate space tolerance  5 mm It is allowed to crimping as shown if not fit to fuselage ot tail

Speed brake and fuselage gap clearance Gap clearance 1 (+1/-0.5)

General Assembly recommendation

هذه المحاضرات للتدريب فقط و لا تستخدم فى التجميع بل يتم استخدام المواصفات المعتمدة شكرا

Fuselage C

by ahmad bassiouny on Nov 08, 2008

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