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• Venugopal Krishna

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INDEX 1.

REFERENCES ...................................................................................................... 2

2.

INTRODUTION.................................................................................................... 2

3.

SHEET PARTS ..................................................................................................... 3

3.1 3.2 3.3 3.4

BEND RADIUS ........................................................................................................................... 3 LIGHTENING HOLES ................................................................................................................ 4 TOOLING HOLES ...................................................................................................................... 5 VARIOUS .................................................................................................................................... 5

4.

MACHINED PARTS ............................................................................................ 6

4.1

TOOL RADIUS ................................................................................................................................ 6

4.1.1 4.1.2 4.1.3

Standard ..................................................................................................................................................................... 6 Specials ...................................................................................................................................................................... 7 Spherical tool ............................................................................................................................................................. 8

4.2

THICKNESS-HEIGHT RATIO IN STIFFENERS ...................................................................................... 9

4.2.1

Transitions / Changes in thickness ............................................................................................................................. 9

4.3 4.4 4.5 4.6

CHAMFER................................................................................................................................. 10 STIFFENERS ENDINGS ............................................................................................................... 11 MINIMUM MACHINED THICKNESS .................................................................................... 11 TAPPING ................................................................................................................................... 12

5.

JOINS ................................................................................................................... 13

5.1 5.2

STEP........................................................................................................................................... 13 FOR INSTALLATION ...................................................................................................................... 13

5.2.1 5.2.2

Drilling diameter ...................................................................................................................................................... 13 Other requirements .................................................................................................................................................. 18

5.3

EDGE DISTANCES .................................................................................................................. 20

5.3.1 5.3.2

New parts ................................................................................................................................................................. 20 Parts reused existing holes ....................................................................................................................................... 20

5.4 5.5 5.6 5.7 5.8

RIVET STEP .................................................................................................................................. 21

6.

TOLERANCES ................................................................................................... 23

6.1 6.2 6.3

METALLIC PARTS ......................................................................................................................... 23

TYPICAL VALUES FOR EDGE AND STEP DISTANCES .................................................... 21 SHIMS ........................................................................................................................................ 22 CLEARANCES ............................................................................................................................... 22 RIVETS REPLACEMENT ................................................................................................................. 22

COMPOSITE PARTS ....................................................................................................................... 23 NO MODEL ELEMENTS .................................................................................................................. 24

7. MATERIAS, PROCESSES AND APPLICABLE CODES……. PROTECTION .............................................................................................................. 25

1.

REFERENCES 1. NT-FA-ID-05006: Selection of materials, processes, and corrosion prevention codes applicable to A330-200-MRTT programme. 2. NT-FA-ANC-05006: Standard parts applicable for EADS-CASA to A330-200 MRTT

2.

INTRODUTION

The purpose of this document is to present and summarize the design principles used in the transformation to a commercial Airbus A330-200 in a tanker aircraft (MRTT) It is important to remember that change is a repair, it will replace, modify or strengthen parts as needed. In particular, special attention should be paid to existing riveted, which will determine some design decisions.

3.

SHEET PARTS

In general, bent sheet metal parts used only when the tolerances are not smalls (although the charges are not very high, if they are fit enough pieces, small tolerances are required.) When the tolerances are tight or the part must be copied double-curved, bent sheet metal part is not the choice. In that case, double-curved, it is possible to do like ruled surface. The preferred material is 2024 aluminum cladding (Clad) and the normal state T3. Preferred thicknesses are in the following table (to reduce weight without penalizing supplies). Sizes larger than the standard must be communicated immediately to manufacturing / materials for availability / timing

3.1

BEND RADIUS

The most used bend radius are shown in the I+D-P-212 for aluminum and I+D-P-206 for steel and titanium, for thickness, treatment and selected material. The typical values for this materials are shown in the following table: MATERIAL

STATE THK IN mm

2024 2024 Clad

0 T3 T4

7075 Clad

0 T6

MATERIAL

STATE THK IN mm

2,0

2,3

2,5

3,0

3,2

3,5

4

4,8

5

6

0

3,0

4

4

5

5

5,6

7,2

9,5

10

12

T3 T4

8

9

10

12

12

12,7

17

21,4

25

0

3

4

4,8

-

5,6

-

7,9

9,6

-

T6

12,7

14,2

16,8

-

21,3

-

27

35

-

2024 2024 Clad 7075 Clad

BEND RADIUS (Minimum) en mm 0,3

0,4

0,5

0,63

0,8

1,0

1,2

1,3

1,4

1,5

1,6

1,8

0,6 1,0 0,8 2,3

0,6 1,0 0,8 2,3

0,6 1,6 0,8 3

0,6 2,0 0,80 4

1,0 2,5 0,8 4,8

1,2 3 1,6 6,4

1,6 4 1,6 -

1,8 4,5 1,6 7,9

2,0 5 -

2,0 5 -

2,0 5 2,3 10,4

3,0 6,0 3 11,2

6,4

9,5

12,7

16

35

64

30

32

48

-

-

22,9

35

63,5

-

50,8

-

-

BEND RADIUS (Minimum) en mm

In general, the used bend radius should be the minimums, unless the cargos will be small and the bend radius standard should be used. If it bend in 0 state, and it will be processed to final state (T4 or T6), it is necessary to explain this like: 2024-0  2024T42 7075-0  7075T62

3.2

LIGHTENING HOLES

To lightening and provide access while it gives rigidity to the piece, lightening holes are used according to CAN 16070. The edge of the lightening hole will, if it is possible, on the side of the flap of the piece. The preferred type is BT, whose dimensions listed in the CAN are: :

Designación

BT20 BT25 BT30 BT35 BT40 BT42 BT50 BT60 BT70 BT80 BT90 BT100 BT120 BT140 BT160 BT180

A aprox. 20 25 30 35 40 42 50 60 70 80 90 100 120 140 160 180

C aprox. 17 22 26 32 36 39 46 56 65 75 84 94 112 131 150 169

E mín. 9 9 9,5 10 10 10 10 10 10,5 11 11,5 12 13 14 15 16

H aprox. 3 3 4,5 4,5 5 5,5 5,5 6 6,5 7 7,5 8 9 10 11 12

R ± 1mm 3 3 4 4 5 5 6 7 7 8 8 8 8 8 8 8

The minimum distances to edges, some folded, some lightening, etc. are also included in the CAN 16070 According

to

the

material

and

treatment,

Material Estado Espesor max W 2,5 2024 O 2,5 T42 1,6 W 2,5 2024 O 2,5 Clad T4 1,6 7075 W 2,5 Clad O 2,5

thickness

Diametro Min Max 20 180 20 180 20 180 30 180 30 180 30 180 30 180 30 180

and

maximum

sizes

are:

3.3

TOOLING HOLES

To hold the piece in useful during complex bending operations (piecework, lightening, or flanges snare a curved shape), often are required tooling holes The standard diameter is 6.1 mm. The minimum number of drills to use a piece is two, but depending on the size might be needed more. In any case, the distance between them should be as large as possible. His position must be agreed with manufacturing.

3.4

VARIOUS

Cutout radius: The best cutout radius are 8 mm (4mm if it not possible 8mm). Minimum length flap. The minimum length required to bend a flap is defined in the standard DIN9003, if in a particular case appear not to use 2.5 times the bending radius. This minimum distance must be respected in all areas near the tip radius.

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4.

MACHINED PARTS

4.1

TOOL RADIUS

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4.1.1 Standard Como compromiso adecuado entre velocidad de avance, profundidades habituales de mecanizado y obtención de detalles con vida en fatiga aceptable y peso no penalizado, la herramienta típica es: diameter = 16 mm. Cutter radius = 4 mm To avoid stalls during the machining tool, the modeling radio parts must be greater than the tool. Therefore: Drafting radius = 9 mm. Cutter radius= 4 mm

D/2+1 R

R

ØD

Tipical tool: D = 16, R = 4

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4.1.2 Specials

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4.1.3 Spherical tool In general, it is prefer the use of cylindrical tools. The spherical tools increase the costs, but it can be used in special cases. The most used are: R4 R5 R6 In the next pictures it can be seen in which cases can be used spherical tool, and which is the alternative with cylindrical.

1

Alternative solution with cylindrical tool

Cylindrical tool USUAL USE

Spherical tool EXCEPCIONAL USE

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4.2

Pág. 9

THICKNESS-HEIGHT RATIO IN STIFFENERS

The following table lists the maximum height of stiffeners depending on the thickness and length.

h 25 36 42 60 75 96 120

t 1,5 1,8 2,0 2,5 3,0 4,0 6,0

R 10 16 20 20 20 25 25

E 150 180 200 250 300 450 450

These values are met if the cutter diameter D satisfies:  For Aluminum D ≥ h / 3  To Titanium & Steel D ≥ h / 2

4.2.1 Transitions / Changes in thickness Thickness transitions in the direction of the load must be done gently to avoid problems of fatigue. The value to use as a baseline to confirm with fatigue, 70% t1

t2

t3

Recommended value 0.7 t2≈ 0.7 t1 t3≈ 0.7 t2 ~ 0.4 t1

To make a piecework in a machined part (see figure below) are recommended in the following table values (thickness zone ≈ 7 x depth of piecework). It will seek to install a rivet in the area of additional thickness to withstand torque produced by the misalignment of loads.

S M X

0,6

0,8

1,0

1,2

1,6

2,0

2,5

3,2

4,0

5,0

4,2

5,6

7

8,4

11,2

14

17,5

22,4

28

35

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4.3

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CHAMFER

To attach machined parts, the preferred method is to chamfer the inner part. The chamfer is 1 mm greater than the radius of machining the part on which it rests (R1 +1). The inner radius R2 should be large enough to keep the throat, causing the thickness of the thin wing, ie, w ≥ min. (t1, t2)

Gap for sealant. Parts were designed, leaving a gap of 0.2 mm between the pieces. This gap is due to the thickness of sealant applied to the assembly between the bearing faces of the pieces.

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4.4

Pág. 11

STIFFENERS ENDINGS

Stiffeners that end not attached to another wing or stiffener, should be cut at an angle to improve the discharge. When the load is tension, the angle that produces the best allowable fatigue is 15 º. If compression, cutting two planes 15 and 30 º is recommended 1 1 5

r

P u e d e c o n tin u a rs e e lc o rte c o n 3 0 º .A lg o p e o r

1 5 º

4.5

r

1

3 0 º

MINIMUM MACHINED THICKNESS

The minimum thickness depends on the material, the size of the area to be machined, the support on the table and technology. The minimum values are

Tecnology Material Aluminium Titanium - steel

Conventional

High speed

One face

Two faces

One face

Two faces

1,2

1,5

0,7

0,8

1,5

1,7

-

-

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4.6

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TAPPING

In exceptional cases, with the consent of fatigue can be used tappings to allow the seat of the head of bolts or rivets. If you make will be made according to the following diagrams. By request of fatigue, the tapping fillet radius will be 2.5 mm.

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5.

JOINS

5.1

STEP

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Pág. 13

The typical step of riveting will be between 5 and 8 D (D = diameter of rivet) For joints staggered, the distances between rivets also apply. For sealing, at least one staggered riveted joint must be used

5.2

FOR INSTALLATION

5.2.1 Drilling diameter It will be identified and it will be used drill diameters and adjustments from CAN40027 for fixed joints: Hi-Loks

Typical drills (like I+D-P-117) AA

Drills with more tightening than AA (strong requirement for fatigue) A

Solid rivets

Drills presure limit ( like I+D-L-113) FF

Drills with greater ease than FF (without pressure limit) F

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For removable elements, are used preferably screws of 4.8 mm. The holes are as follows (see CAN16030 for drill rivet nut installation):

2D

5D**, 8D* D+1

D is the maximum diameter needed for bolt, according with CAN16030. For not anchor nuts it will be used the LOCK NUTS column. The diameter for anchor nuts only is necessary to apply in the part where nut is riveted, in the other(s) join part(s) the diameter will be LOCK NUTS column. Anchor nuts will be modeled with nominal diameter and measured with tolerances +/- 0,1; for not anchor nuts will be modeled with minimum diameter and measured with tolerances – 0,0 / +0,1.

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ANCHOR NUTS IN PRIMARY STRUCTURE, ACCORDING WITH CAN16030 Hole Min edge Min hole Min radius Bolt diameter diameter (D) distance(mm.) distance(mm.) distance (mm.) 2D 5D D+1 inch mm mm. .1120 2,84 3,3 -3,5 7 18 5 .1380 3,50 4,0 - 4,2 8 21 6 .1640 4,17 4,7 - 4,9 10 25 6 .1900 4,83 5,3 - 5,5 11 28 7 .2500 6,35 6,8 - 7,0 14 35 8 .3125 7,94 8,4 - 8,6 17 43 10 .3750 9,52 10,0 - 10,2 20 51 12 .4375 11,11 11,6 - 11,8 24 59 13 .5000 12,70 13,2 - 13,4 27 67 15

ANCHOR NUTS IN SECUNDARY STRUCTURE, ACCORDING WITH CAN16030 Hole Min edge Min hole Min radius Bolt diameter diameter (D) distance(mm.) distance(mm.) distance (mm.) 2D 5D D+1 inch mm mm. .1120 2,84 4,4 – 4,6 9 23 6 .1380 3,50 5,0 – 5,2 10 26 7 .1640 4,17 5,7 – 5,9 12 30 7 .1900 4,83 6,4 – 6,6 13 33 8 .2500 6,35 7,9 – 8,1 16 41 10 .3125 7,94 9,5 – 9,7 19 49 11 .3750 9,52 11,0 – 11,2 22 56 13 .4375 11,11 12,6 – 12,8 26 64 14 .5000 12,70 14,2 – 14,4 29 72 16

NOT ANCHOR NUTS, ACCORDING WITH CAN16030 Hole Min edge Min hole Min radius Bolt diameter diameter (D) distance(mm.) distance(mm.) distance (mm.) 2D 5D D+1 inch mm mm. .1120 2,84 3,0 – 3,1 6 16 5 .1380 3,50 3,7 – 3,8 8 19 5 .1640 4,17 4,3 – 4,4 9 22 6 .1900 4,83 5,0 – 5,1 10 26 7 .2500 6,35 6,5 – 6,6 13 33 8 .3125 7,94 8,1 – 8,2 16 41 10 .3750 9,52 9,7 – 9,8 20 49 11 .4375 11,11 11,3 – 11,4 23 57 13 .5000 12,70 12,9 – 13,0 26 65 14

Pág. 17

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Countersink the minimum thickness, according to the following tables: Fastener Diam. 4 4,8 6,4 8 9,6 11,1 12,7

Fastener Diam. 4 4,8 6,4 8 9,6 11,1 12,7

DAN6 H 1,041 1,194 1,549 1,727 1,981 2,461 2,713

t 1,6 1,8 2,3 2,6 3,0 3,7 4,1

FASTENER TYPE DAN8 NAS1097 H t H t 1,778 2,7 0,945 1,4 2,045 3,1 1,168 1,8 2,743 4,1 1,524 2,3 3,429 5,1 4,115 6,2 4,813 7,2 5,486 8,2

NAS1581 H

t

1,25 1,6 1,79 2,07 2,55 2,83

1,9 2,4 2,7 3,1 3,8 4,2

FASTENER TYPE ASNA0077 NASM 20426 H t H t 1,4 2,1 1,402 2,1 1,78 2,7 1,785 2,7 2,44 3,7 2,422 3,6 2,703 4,1 3,417 5,1

FASTENER Fastener TYPE Diam. NAS1153 4,8 NAS1154 6,4

H 2,04 2,703

t 3,1 4,1

H ≤ 2/3 t

Min 0,5 mm

H

“Knife edge”

t

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5.2.2 Other requirements  Distance to the nearest wall: The rivet head should not be on the radio. It should also be checked in the piece to which it binds. Typical values indicated in the diagram below. Taking into account the provision for the case of reusing existing holes (paragraph 5.3.2 below) Max. of

(Inst. Req; R+D+2; Rhead + 1)

1 min R

D 

Check installation possibilities, especially for blind rivets.

NO OK



OK

Check access hi-lok/hi-lite Installation In general, to allow the pass from the pilot holes to final diameter and the installation of the Hi-Loks with automatic tool, it should be left a free space. For Hi-Lok installation should be left on the side where it will go the collar, a clearance of 10 mm radius (not taking into account the radius of the piece) and 50 mm in height for automatic installation or 30 mm in height for manual installation. Should be left free access to one of the two sides of the junction (on the side of pilot if exists) for drilling. 20

50 mm automatic 30 mm manual

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

Pág. 19

The relation between the diameter of the rivet and junction thickness should be between 2.5 (for solid rivets in single shear) and 4 (for bolts in double shear)

D

t

Solid rivets t/D  2,5. Hi-Loks y structural bolts t/D  4* * In areas of high load transfer stress department should be consult by the convenience of used steel hi-loks.

CONTOURING CRITERIA Ø Fastener inch 3/32 4/32 5/32 3/16 7/32 1/4 5/16 7/16 1/2

mm. 2,38 3,2 3,96 4,82 5,56 6,35 7,94 9,52 11,11

Maximum thickness to join HI-LOKS Y BOLTS

Maximum thickness to join RIVETS

10 13 16 19 22 25 32 38 44

6 8 10 12 14 16 20 24 28

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5.3

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EDGE DISTANCES

5.3.1 New parts Typical values: 

Metal, all directions: 2D+1mm



Composites:

Perpendicular to principal load or compression: 2.5D+1mm Parallel to principal load: 3D + 1mm

5.3.2 Parts reused existing holes When it is reusing existing holes, the distances to edge should be considered sufficient additional margin to see the original assembly tolerances. The actual position of the drilling could oscillate a few mm from the original theoretical position. When reusing existing holes shall be increased by 2mm to-edge distances typical. The impact on weight, should be analyzed case by case basis

D+4

2D+4

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5.4

Pág. 21

RIVET STEP

General values for structural joints: Min: 4D Max: 8D Optimum step for structural joints: Metal: 5D Composites: Fibra Alto Módulo: 4,5D Fibra alta resistencia: 5D For non-structural joints, the maximum is used to 10D For removable joints, the typical step is 10D

5.5

TYPICAL VALUES FOR EDGE AND STEP DISTANCES

EDGE DISTANCE METAL Fastener Dia. 4 4,8 6,4 8 9,6

EDGE DISTANCE

METAL

COMPOSITE

FASTENER PITCH (P)

COMPOSITE

Std Shear/Comp. Tension Std Shear/Comp. dFastener et = des = 2 d Det +=1d des==22,5 D 1+ 1des =d2,5 et = 3 D + 1 D + D+1 es Dia. 11 4 9 9 1113 15,5 4,8 11 11 13 13 20,5 6,4 14 14 17 17 8 17 17 21 2125 9,6 20 20 25 2530

FASTENER PITCH (P)

Nominal Minimum Maximum Tension Nominal MetalMinimum (4D) Composite (4,5D) ( 4D ( 6D ) det = )3 D + 1 Metal (4D) Composite (4,5D) ( 4D ) 16 16 16 1816 24 18 13 19,2 19 19,2 2219 28,8 22 15,5 25,6 26 25,6 2926 38,4 29 20,5 25 32 32 32 3632 48 36 30 38,4 38 38,4 4438 57,6 44

P

P des

des det

det

Ma (

2 3

5

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5.6

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SHIMS

For easer installation or to take into account manufacturing tolerances and assembly, in some places it is necessary to consider the use of shims. The application to this program are:  

Liquid shim allowed to 0.5 mm Solid shim allowed to 1.0mm (standard solid shim LN29557-3.0255.32Axx, XX thickness)

Shim aplication rule: I+D-P-061

5.7

CLEARANCES

In the absence of other documents that define specific values for an installation, the following values are used for parts to be designed with security clearances or distances:   

5.8

Between joint parts but with relative movement between them: 6.5mm (1/4”) Between non-joint parts but with relative movement between them : 13 mm (1/2”) Between non-joint parts, relative movement between them and possible vibration: 25mm (1”)

RIVETS REPLACEMENT

The criteria for the replacement of rivets or other fasteners are:  Solid rivet replaced by solid rivet: Use the same diameter  Solid rivets replaced by hi-lok: Use oversized hi-lok  Hi-lok replaced by Hi-lok: Use oversized hi-lok

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6.

TOLERANCES

6.1

METALLIC PARTS

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Pág. 23

The typical values for machining parts are following as shown. In the drawings wil be indicated (always with the manufacturing agreement) those values that are required for assembly  0,15

BORE AND NERVE THICKNESS LENGHTS

30 mm  l 30 < l  100 100 < l  500 500 < l  1000 1000 < l < 2000

 0,2  0,3  0,5 1  1,2

ANGLES

30   31 <   120 120 <   315º

 1º  0,5º  0.25º

ACCORDING RADIUS

+ 1,0 - 0,5

DEPTH RADIUS

 0,5

ROUND OF EDGES

R = 0,3

+ 0,2 -0

FLATNESS

 0,5 / 100 mm. Max. 1.0mm

PARALLELISM SQUARENESS

 0,3 / 100 mm. Max. 1.0mm

RIGHTNESS

 0.1 / 100 mm. Max. 1.0mm

6.2

COMPOSITE PARTS

Tolerances in manufacturing parts depends of manufacturing methodology, material and the number of plies. Typical values are:

UD Tape Prepreg Fabric Prepreg Glass Fibre Prepreg

Thickness tolerance (CASA values) Less than 20 ply 20 - 40 ply +/- 6% Max of (+/- 5% , +/-0,22) +/- 7% Max of (+/- 4,5% , +/-0,20) +/- 7% Max of (+/- 6% , +/-0,14)

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6.3

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NO MODEL ELEMENTS

Primer and paint, tedlar, adhesives, bronze net and fiberglass patch are not modeled in CATIA but should be considered for the calculation / determination of the gaps between parts. For the clearance calculation, following values are used:     

Primer: Paint: Sealant: Fiberglass (for ply): Tedlar, bronze net and adhesives:

N/A N/A 0,2 mm 0,1 mm 0,3 mm

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7. MATERIAS, PROCESSES AND APPLICABLE CODES……. PROTECTION

EADS-CASA DESIGNATION

SEMIFINISHED PRODUCT STANDARD

AIRBUS MATERIAL SPECIFICATION

MATERIAL DESCRIPTION

ANTICORROSIVE PROTECTIONS (See 2.2.1) Z11.502

---

AIMS09-08-001Gr.2

Z11.505

---

AIMS09-08-003

CORROSION INHIBITING COMPOUND CORROSION INHIBITING COMPOUND

PRIMERS AND TOP COATS (See 2.2.2) Z12.113

---

AIMS04-04-004

Z12.129

---

AIMS04-04-002

FUEL TANK COATING NON CORROSION INHIBITING PRIMER

Z12.132

---

AIMS04-04-002

PRIMER FOR ANTIEROSION PAINT

Z12.201

---

---

EPOXY FILLER

Z12.210

---

---

EPOXY FILLER

Z12.211

---

AIMS04-04-011

Z12.380

---

AIMS04-04-003

POLYURETHANE PORE-FILLER INTERNAL PAINT SYSTEM (TOP COAT)

Z12.402

---

AIMS04-04-009

VARNISH FOR TOUCH-UP

Z12.412

---

AIMS04-04-023

U.V. RESISTANT VARNISH

Z12.512

---

AIMS04-04-024

ANTISLIP PAINT

Z12.520

---

AIMS04-04-007

Z12.524

---

AIMS04-04-010

ABRASION RESISTANT PAINT SEALANT BEAD PROTECTION PAINT

PLASTIC MATERIALS (See 2.2.3) Z14.501

LN9298

WL-5.1129.10

PTFE MOLDED (SHEETS)

Z14.502

---

Z14.510

---

AMS3652 L-P-1040B TYPE II, GRADE B, CLASS 1

PTFE SKIVED (FOILS) POLYVINYL FLUORIDE FILM (GREY)

Z14.512

---

L-P-1040B TYPE II, GRADES B AND C, CLASS 1

POLYVINYL FLUORIDE FILM (WHITE)

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EADS-CASA DESIGNATION

SEMIFINISHED PRODUCT STANDARD

AIRBUS MATERIAL SPECIFICATION

Pág. 26

MATERIAL DESCRIPTION

RESIN AND ADHESIVE MATERIALS (See 2.2.4) Z15.101

---

MMM-A-121

ELASTOMERIC ADHESIVE (NEOPRENE)

Z15.104

---

MIL-C-4003

ELASTOMERIC ADHESIVE (NITRILE)

Z15.201

---

I+D-N-200

EPOXY ADHESIVE

Z15.205

---

I+D-N-200

EPOXY ADHESIVE

Z15.209

---

DAN1284-01

EPOXY ADHESIVE

Z15.213

---

I+D-N-200

EPOXY ADHESIVE

Z15.301

---

I+D-N-200

SILICONE ADHESIVE

Z15.415

ABS5337

AIMS10-02-003

Z15.429

---

I+D-N-200

Z15.601

---

A-A-3097 TYPE I CL.2

Z15.915

---

I+D-N-200

BONDING PRIMER

Z18.115

---

I+D-N-200

EPOXY CORE FILLER (LOW VISCOSITY)

Z18.144

---

I+D-N-200

EPOXY CORE FILLER (R.T. CURING)

Z18.179

---

DAN1206-01

EPOXY CORE FILLER (HOT CURING)

CORE SPLICING ADHESIVE EPOXY FILM ADHESIVE (300 g/m2, 115 ± 5°C CURE) CYANOACRYLIC ADHESIVE

SEALANTS (See 2.2.5) Z11.903

---

AIMS04-05-005 TYPE I

Z16.101

---

AIMS04-05-002 INTERFAY

FAYING SURFACE SEALANT

MIL-PRF-81733 TYPE II-2

CORROSION INHIBITING COMPOUND

Z16.113 Z16.156 Z16.157 Z16.160 Z16.161 Z16.302 Z16.912

---

NON HARDENING JOINTING COMPOUND

AIMS04-05-002 BRUSH

INTEGRAL FUEL TANK SEALANT

AIMS04-05-002 FILLET

INTEGRAL FUEL TANK SEALANT

AIMS04-05-006 TYPE A

LOW ADHESION SEALANT

AIMS04-05-006 TYPE B

LOW ADHESION SEALANT

---

MIL-A-46106B GROUP I, TYPE I

SILICONE SEALANT

---

---

---------

ADHESION PROMOTER

HONEYCOMB CORES (See 2.2.6) Z17.607 Z17.622

-----

I+D-P-176 Class 1, Type 1

ARAMID HONEYCOMB CORE 3.0-1/8

I+D-P-176 Class 1, Type 1

ARAMID HONEYCOMB CORE 6.0-3/16

Edic./Issue A

NT-FA-ASO-05-087

AIRBUS MATERIAL SPECIFICATION

SEMIFINISHED PRODUCT STANDARD

EADS-CASA DESIGNATION

Pág. 27

MATERIAL DESCRIPTION

RESIN AND ADHESIVE MATERIALS (See 2.2.4) A-A-3097 TYPE I CLASS 2

---

Z15.601

CYANOACRYLIC ADHESIVE

AIMS10-02-003

ABS5337

Z15.415

CORE SPLICE ADHESIVE

Z18.179

EPOXY CORE FILLER (HOT CURING)

Z15.201

EPOXY ADHESIVE

Z15.205

EPOXY ADHESIVE

Z15.209

EPOXY ADHESIVE

Z15.213

EPOXY ADHESIVE

Z15.301

SILICONE ADHESIVE

Z15.429

EPOXY FILM ADHESIVE (300 g/m2, 115 ± 5°C CURE)

Z15.915

BONDING PRIMER

Z18.115

EPOXY CORE FILLER (LOW VISCOSITY)

Z18.144

EPOXY CORE FILER (R.T. CURING)

Z15.104

ELASTOMERIC ADHESIVE (NITRILE)

Z15.101

ELASTOMERIC ADHESIVE (NEOPRENE)

DAN1206-01 I+D-N-200 I+D-N-200 I+D-N-200 I+D-N-200 I+D-N-200 I+D-N-200 I+D-N-200 I+D-N-200 I+D-N-200 MIL-C-4003 MMM-A-121

-------------------------

SEALANTS (See 2.2.5) Z16.101

FAYING SURFACE SEALANT

Z16.156

INTEGRAL FUEL TANK SEALANT

Z16.157

INTEGRAL FUEL TANK SEALANT

---

Z11.903

NON HARDENING JOINTING COMPOUND

AIMS04-05-006 TYPE A

---

Z16.160

LOW ADHESION SEALANT

AIMS04-05-006 TYPE B MIL-A-46106B GROUP I, TYPE I

---

Z16.161

LOW ADHESION SEALANT

---

Z16.302

SILICONE SEALANT

---

---

Z16.912

ADHESION PROMOTER

AIMS04-05-002 INTERFAY

---

AIMS04-05-002 BRUSH

---

AIMS04-05-002 FILLET

---

AIMS04-05-005 TYPE I

HONEYCOMB CORES (See 2.2.6) I+D-P-156 Class 1, Type 1

---

Z17.607

ARAMID HONEYCOMB CORE 3.0-1/8

I+D-P-156 Class 1, Type 1

---

Z17.622

ARAMID HONEYCOMB CORE 6.0-3/16

NT-FA-ASO-05-087

AIRBUS MATERIAL SPECIFICATION

SEMIFINISHED PRODUCT STANDARD

EADS-CASA DESIGNATION

Edic./Issue A

Pág. 28

MATERIAL DESCRIPTION

WET LAY-UP MATERIALS (See 2.2.7) AIMS08-02-001 AMS-C-9084 T.III C2 AMS-C-9084 T.VIII C2 I+D-N-200

---------

Z18.170

EPOXY RESIN, R.T. CURING, FOR GLASS WET LAYUP

Z17.201

GLASS FIBER FABRIC (120 style, 104 g/m2)

Z17.208

GLASS FIBER FABRIC (181 style, 293 g/m2)

Z18.142

EPOXY RESIN, HOT CURING, FOR FILLING AND POTTING

PREPREG MATERIALS (See 2.2.8) AIMS05-10-001

ABS5047

Z19.607

GLASS/PHENOLIC PREPREG (7781 TYPE, 135°C CURE)

AIMS05-10-009

ABS5047-01

Z19.605

GLASS/PHENOLIC PREPREG (120 TYPE, 135°C CURE)

I+D-P-250A, Group I

---

Z19.101

GLASS/EPOXY PREPREG (181 TYPE, 125°C CURE)

I+D-P-250A, Group I

---

Z19.111

GLASS/EPOXY PREPREG (181 TYPE, 125°C CURE)

I+D-P-250A, Group I

---

Z19.301

GLASS/EPOXY PREPREG (120 TYPE, 125°C CURE)

I+D-P-250A, Group I

---

Z19.311

GLASS/EPOXY PREPREG (120 TYPE, 125°C CURE)

MISCELLANEOUS (See 2.2.9) A-A-1689, Type I, Class 2

---

Z24.310

VINYL ADHESIVE TAPE

A-A-59163, Type I

ABS5334

Z22.127

SELF-ADHERING INSULATION TAPE

A-A-59474, Type I, Class 1

---

Z24.330

PTFE ADHESIVE TAPE

MIL-L-23398

---

Z21.305

SOLID FILM LUBRICANT

---

--

Z24.273

DOUBLE SIDED ADHESIVE TAPE