STRUCTURAL REPAIR MANUAL

STRUCTURES − GENERAL

1. General

A. The chapter 51 describes general materials and typical repairs which are
applicable to all chapters of this manual:

− Refer to Figure 3.

2. Miscellaneous Aircraft Data

A. The diagrams shown below give you a general view of the structure and
its location. These diagrams are divided into:

(1) Aircraft Data and Breakdown

(a) Structure Breakdown:

− Refer to Figure 1

(b) Major Aircraft Dimensions:

− Refer to Figure 2.

(c) Aircraft Section Numbers:

− Refer to Figure 3.

(d) Fuselage Reference Axis:

− Refer to Figure 4.

(e) Major Aircraft Reference Axis:

− Refer to Figure 5.

(2) Station Reference Data

(a) Fuselage − Sections, Stations and Major Frames:

− Refer to Figure 6.

(b) Nacelle and Pylon Stations:

− Refer to Figure 7.
− Refer to Figure 8.

(c) Stabilizers − Stations and Ribs:

− Refer to Figure 9

(d) Wing − Stations and Ribs:

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− Refer to Figure 10.

(3) Zonings
(a) Fuselage, Vertical Stabilizer and Belly Fairing Zones:

− Refer to Figure 11.

(b) Wing and Horizontal Stabilizer Zones:

− Refer to Figure 12.

(c) Pylons and Nacelles Zones:

− Refer to Figure 13 for CFM56 Engine.

− Refer to Figure 14 for IAE V2500 Engine.

(d) Landing Gear Zones:

− Refer to Figure 15.

(e) Door Zones:

− Refer to Figure 16.

B. Honeycomb Component Materials

Some components of the aircraft structure are made of:
− Aramidfiber Reinforced Plastic (AFRP),
− Carbonfiber Reinforced Plastic (CFRP),
− Glassfiber Reinforced Plastic (GFRP). The locations of these materials
are given in Chapter 51−33−00.

3. Abbreviations
A. The main abbreviations used in the SRM are:

AD = Airplane Datum

AFRP = Aramidfiber Reinforced Plastic

A = As Required
c = Equal Margin

CFRP = Carbonfiber Reinforced Plastic

CL = Center Line

CONFIG = Configuration

CS = Center Spar

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CSK = Countersink

DBL = Doubler
DIA = Diameter

DWG = Drawing

E = Elevator Rib

EHL = Elevator Hinge Line

FD = Fuselage Datum

FIG = Figure

F = Frame

FS = Front Spar

FWD = Forward
GFRP = Glassfiber Reinforced Plastic

HD = Head

HHL = Horizontal Hinge Line

HT = Horizontal Tail
INTMD = Intermediate

L = Left

LH = Left−Hand (side)

LONGN = Longeron

MAX = Maximum
MID = Middle

MIN = Minimum

NO = Number

OH = Opposite Hand
OPTL = Optional

OPT = Optimum

R = Right

RH = Right−Hand (side)

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REF = Reference

RHL = Rudder Hinge Line

RPM = Revolutions Per Minute

R = Rudder Rib

RS = Rear Spar

SERNO = Serial Number

SPD BRK = Speec Brake

SPL = Spoiler

STA = Station

STG = Stringer

STIF = Stiffener
t = Rivet Spacing

T = Thickness

THS = Trimmable Horizontal Stabilizer

TYP = Typical
UNIV = Universal

V = Vertical parallel with fuselage axis

VERT = Vertical

VT = Vertical Tail

WD = Wing Datum
WIA = Wing Inner Aileron

WO = Wing Outer Rear

X = Fore and aft distance from any point to STA O:

− Refer to Figure 4.
Y = Lateral distance from any point to AD:

− Refer to Figure 4.

Z = Vertical distance from any point to FD:

− Refer to Figure 4.

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4. Special Terms

Term Definition
Interference Fit Mechanical pressure is required
for assembly and once assembled it
is not likely to be disassembled.
Transition Fit Only a light manual pressure is
(Close Tolerance) necessary to as

semble the parts. It is applicable
for detachable parts and locating
parts but not for moving parts.
Clearance Fit No manual pressure is required.
Applicable for different types of
parts.
VTX O (Refer to Figure 2 and Figure 5) A plane vertical to the fuselage
contour measured from a point 1165
mm (45.87 in.) in front of STA/
FR70. If the letter code is fol

lowed by a number, it denotes the
distance measured from VTX O.
VTZ O (Refer to Figure 2 and Figure 5) A plane horizontal to the fuselage
contour measured from a point 1975
mm (77.76 in.) above FD. If the
letter code is followed by a num

ber, it denotes the distance mea

sured from VTZ O.
XO (Refer to Figure 4) The zero point of the theoretical
trihedron, in which the aircraft
must be contained.
Operating Limits Operating limits are defined as
the limit for airplane operation
with an allowable damage. Example
of acceptable airplane operation:
Repair before 50 flight cycles at
the latest.
Circumferential Parallel to the frames.
Longitudinal Parallel to the stringers.

Table 1
5. Major Aircraft Dimensions
(Refer to Figure 2)

A. General

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(1) Overall length: 37573 mm (1479.25 in.)

(2) Overall height: 11755 mm (462.80 in.)

(3) Wheel base: 12640 mm (497.64 in.)

(4) Track: 7590 mm (298.82 in.)

B. Fuselage

(1) Reference length: 31115 mm (1225.00 in.)

(2) Width: 3950 mm (155.51 in.)

C. Stabilizer

(1) Span: 12450 mm (490.16 in.)

(2) Basic horizontal area: 31 m
(333.69 ft.
)

(3) Basic vertical area: 21.5 m
(231.43 ft.
)

D. Wings

(1) Span: 33913 mm (1335.16 in.) After Mod 20268 (Fence−Wing Tip)
34087 mm (1342 in.)

(2) Basic area: 122.4 m
(1317.55 ft.
)

(3) Sweep angle (at 25 % MAC) 24° 58 ’

E. Power Plant

(1) CFM56−5A

(a) Ground clearance: 548.45 mm (21.59 in.)

(b) Reference Length: 2581 mm (101.61 in.)

(2) CFM56−5B

(a) Ground clearance: 548.45 mm (21.59 in.)

(b) Reference Length: 3444 mm (135.59 in.)

(3) IAE V2500−A5

(a) Ground clearance: 640.7 mm (25.22 in.)

(b) Reference Length: 4260 mm (167.72 in.)

6. Figures applicable to the previous text

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Structure Breakdown
Figure 1

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Major Aircraft Dimensions

Figure 2

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Aircraft Section Numbers

Figure 3

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Fuselage Reference Axis

Figure 4

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Major Aircraft Reference Axis

Figure 5

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Fuselage − Sections, Stations and Major Frames

Figure 6

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Nacelle and Pylon Stations

CFM56 Engine
Figure 7 (sheet 1)

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Nacelle and Pylon Stations

CFM56 Engine
Figure 7 (sheet 2)

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Nacelle and Pylon Stations

IAE V2500 Engine
Figure 8

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Stabilizers − Stations and Ribs

Figure 9

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Wing − Stations and Ribs

Figure 10

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Fuselage, Vertical Stabilizer and Belly Fairing Zones

Figure 11

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Wing and Horizontal Stabilizer Zones (Unit Level)

Figure 12

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Pylons and Nacelles Zones (Unit Level)

CFM56 Engine
Figure 13

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Pylons and Nacelles Zones (Unit Level)

IAE V2500 Engine
Figure 14

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Landing Gear Zones (Unit Level)

Figure 15

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Door Zones (Unit Level)

Figure 16

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