الدورة التنشيطية

للتجاوزات المسموحة فى التجميع K8-Eللطائرة

المعتمدة المواصفات استخدام يتم بل التجميع فى تستخدم ال و فقط للتدريب المحاضرات L8-JTهذه

الفنى الدعم مجموعة اعداد

2007اكتوبر

4ٍSpecification for installation of the Fuselage

مواصفات تجاوزات أعمال التجميع لجسم الطائرة K8-E L8-JT01-1 Book (ED 111)

استعمال و تطبق الرسم على اليها المشار التعليمات كلاالضافية التعليمات فى المواصفات

1-Fueslage Structureجسم 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 الخارجية الجسم تجاوزات

After installation check مساطر الى بالنسبة الجسم تجاوزاتالجيكاتFrame 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 الفريمات محاور انحراف تجاوزات

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

الكابينة و الجسم مقدمة بين االسكنات تقابل خط تجاوزات

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 الهواء مدخل

BUTT joint of the skin of Air intake tolerance الهواء مدخل فى االسكنات تقابل خط تجاوزات

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

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