# Dassault Service Bulletin 7X-042: Revision 1

- Rights: © Dassault Aviation. Filed by the FAA in regulations.gov docket FAA-2017-0694; AD 2018-03-19 incorporates this document by reference. Not covered by OpenAirDocs’ CC0 dedication.
- Document: [Dassault Service Bulletin 7X-042](https://openairdocs.org/service-documents/dassault/7x-042.md)
- Title as filed: SB 7X-042 R1
- Pages: 34
- PDF: https://openairdocs.org/files/sha256/d8/7c/d87c4880361bd9f7817dae6c915e447f2c42de07ddc96575d9d8adc6620682fd
- Page: https://openairdocs.org/service-documents/dassault/7x-042/file/d87c4880361b

## Text

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### Page 1

FALCON 7X
No 042-R1
MAY 03, 2016
MANDATORY
ATA 53
FUSELAGE
T5 LATERAL FUSELAGE PANELS
INSPECTION OF THE CHEMICALLY-MILLED PROFILES
FALCON SERVICE BULLETIN
Copyright © 2016 by Dassault Aviation
All rights reserved. No part of this work may be reproduced or copied
in any form or by any means without written permission
of Dassault Aviation.
769

### Page 2

FUSELAGE
T5 LATERAL FUSELAGE PANELS
INSPECTION OF THE CHEMICALLY-MILLED PROFILES
Initial issuance January 03, 2011
List of effective pages :
1 to 28
Revision 1 May 03, 2016
List of effective pages :
1 to 32
List of modified pages :
1, 3, 5, 6, 7, 9, 14 to 27, 29, 31 and 32
REASON:The Service Bulletin is now rendered mandatory.
Extension of the Service Bulletin to aircraft with serial numbers 16 and 19:
Evaluation of the thickness and profile on the T5 fuselage lateral panels chemically
milled.
This revision is not applicable to aircraft already modified per the initial issuance of
this Service Bulletin.
FALCON 7X 7X -042
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### Page 3

FUSELAGE
T5 LATERAL FUSELAGE PANELS
INSPECTION OF THE CHEMICALLY-MILLED PROFILES
 
1. PLANNING INFORMATION
A. EFFECTIVITY
This Service Bulletin is applicable to FALCON 7X aircraft with serial numbers 2, 4 through 17 and 19.
B. REASON
The purpose of this Service Bulletin is to inspect 4 pockets of the T5 fuselage lateral panels in order to
more accurately evaluate the profile obtained after the chemical milling performed during the
manufacturing process.
During the development and qualification of the aircraft, it has been determined that this evaluation
was necessary to confirm that all panels of the aircraft mentioned in the effectivity did not have a
limited service life.
C. DESCRIPTION
The operation consists in evaluating the thickness and the profile on different chemically milled
pockets of the T5 fuselage lateral panels:
• for S/N 2, 4 through 6: 4 pockets with one chemical milling step,
• for S/N 7 through 15: 3 pockets with two chemical milling steps and 1 pocket with one chemical
milling step,
• for S/N 16, 17 and 19: 3 pockets with two chemical milling steps and 1 pocket with one chemical
milling step but on the forward pocket, the inspection is not possible because of a doubler.
Consequently, the operation consists in installing a stiffener instead of inspecting the forward
pocket.
D. COMPLIANCE
Mandatory:
• It is anticipated that this Service Bulletin will be rendered mandatory by an EASA Airworthiness
Directive.
• As prescribed by the Airworthiness Authorities of the country of registration of the aircraft.
NOTE: THIS SERVICE BULLETIN MUST BE PERFORMED BY LEVEL-2 CERTIFIED PERSONNEL
ACCORDING TO THE EN4179 OR NAS410 STANDARDS.
E. APPROVAL
For aircraft with serial numbers 16, 17 and 19, this Service Bulletin covers DASSAULT AVIATION
modification FALCON 7X R1024 that has been approved under the authority of DOA nr. EASA.21J.
051.
The technical content of this document is approved under the authority of DOA nr. EASA.21J.051.
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DASSAULT AVIATION Proprietary Data

### Page 4

F. LABOR
Estimated labor-hours: Refer to Service Bulletin Commercial Summary.
NOTE: These labor-hours only concern the work described in this Service Bulletin and do not include
other maintenance work which may be performed on this occasion.
G. MATERIAL - PRICE AND AVAILABILITY
The modification kit may be obtained from either address listed below:
Western hemisphere: DASSAULT FALCON JET CORP.
SPARES DISTRIBUTION CENTER
200 RISER ROAD
LITTLE FERRY, NJ 07643 U.S.A.
Telephone:
• CANADA and U.S.A.: 1-800-800-4036
• MEXICO: 001-800-800-4036
• Other countries: 1-201-541-4809
Fax:
• CANADA and U.S.A.: 1-800-800-4817
• MEXICO: 001-800-800-4817
• Other countries: 1-201-440-7021
Other continents: DASSAULT AVIATION
Falcon Spares
BOITE POSTALE N°101
AEROPORT DU BOURGET
93350 - LE BOURGET Cedex (FRANCE)
Please contact your Dassault Aviation
Account Representative
Telephone: 33 (0)1.48.35.56.78
Fax: 33 (0)1.48.35.56.00
Price and availability on request.
H. TOOLING - PRICE AND AVAILABILITY
Normal maintenance tooling.
Ultrasonic equipment and local calibration standard.
Profile projector.
NOTE: Refer to Section 3 MATERIAL INFORMATION for more details.
I. WEIGHT AND BALANCE
Change in weight: None.
Change in balance with respect to 25% MAC: None.
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### Page 5

J. REFERENCES
Structural Repair Manual:
• RIVETING (Refer to RPI 51-40-04)
• DRILLING (Refer to RPI 51-40-03)
• PAINTING (Refer to TASK 20-60-00-370-803)
Maintenance Manual:
• GENERAL MAINTENANCE AND SAFETY PRECAUTIONS (Refer to TASK 20-00-00-910-801)
• REMOVAL / INSTALLATION OF THE AMSAC CHASSIS (Refer to TASK 21-61-09-900-801)
• REMOVAL / INSTALLATION OF THE BAGGAGE COMPARTMENT LININGS (Refer to TASK
25-52-01-900-801)
K. OTHER PUBLICATIONS AFFECTED
None
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### Page 6

2. ACCOMPLISHMENT INSTRUCTIONS
A. PRELIMINARY STEPS
fig. 2.
(1) The aircraft must be in the maintenance configuration (Refer to TASK 20-00-00-910-801).
(2) Remove the linings ( 272HZ), (272KZ), (272MZ) and (272NZ) (Refer to TASK 25-52-01-900-801).
(3) Remove the AMSAC chassis (103HN) (1-fig. 2) but do not disconnect it (Refer to TASK
21-61-09-900-801), and put it on the baggage compartment floor (fig. 2) .
(4) Remove the insulation blankets for the areas to be inspected.
(5) Clean the area to be inspected.
(6) Do a check of the inspection areas for any visible damage or discontinuities.
B. PROCEDURE
NOTE: The procedure of the service bulletin is defined to fig. 1 . Do the Ultrasonic test only if
moulding inspection value is out of criteria.
(1) Inspections and recording of the profile values according in fig. 1 (For S/N 2 and 4 through 6):
Refer to fig. 1, fig. 2, fig. 3, fig. 4, fig. 5, fig. 7, fig. 8, fig. 9, fig. 10, fig. 11, fig. 12 and fig. 21
(a) Use the modelling clay kit to measure the profile values (L, R, Ep and Hr) as described on 
fig. 4 at the critical areas (fig. 2 and fig. 5) for all the points identified in fig. 7 and fig. 8.
• Mix the green modelling clay and the white modelling clay in a proportion of 50%
each.
• Apply the mixture on the critical areas in order to obtain an impression of minimum
thickness 4 mm (0.16 in) (fig. 3).
• Let cure 10 to 15 min at ambient temperature.
• Identify the different points with the specific alpha-numeric codes in fig. 7 and fig. 8
before you remove the impression.
• Cut a 2 mm (0.08 in) thick strip in the impression for each point ( fig. 3).
• Measure the strip with the profile projector ( fig. 3).
• Record the values in the appropriate tables:
FIGURE AREA
- fig. 9 - Pocket Fr 37 - Fr 38, Str 11 - Str 12 (Detail A)
- fig. 10 - Pocket Fr 38 - Fr 39, Str 11 - Str 12 (Detail B)
- fig. 11 - Pocket Fr 39 - Fr 40, Str 11 - Str 12 (Detail C)
- fig. 12 - Pocket Fr 39 - Fr 40, Str 12 - Str 13 (Detail D)
(b) If Ep is out of value (Refer to the flow chart fig. 1), do the ultrasonic inspection:
CAUTION: THE ULTRASONIC MEASUREMENT MUST BE PERFORMED BY LEVEL-2
CERTIFIED PERSONNEL ACCORDING TO THE EN4179 OR NAS410
STANDARDS.
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NOTE: Refer to Section 3 MATERIAL INFORMATION for requested characteristics of the
ultrasonic equipment.
• Operate the equipment in accordance with the manufacturer’s instructions.
• Apply coupling gel on the area.
• Connect the transducer and verify the delay line.
• Adjust setting of the ultrasonic tool with local calibration standard ( fig. 21).
• If you must inspect the pocket between frame 38 and 39 and the stringer 11 and 12:
• Drill out the four rivets (3-fig. 2) in the frame 38 and 39 and remove them with a
drift punch.
• Remove the bracket (2-fig. 2)
• Use the ultrasonic tool to measure the profile values (Et, Em1 and Em2) as described
on fig. 21 at the critical areas (fig. 2 and fig. 5) for all the points identified in fig. 7 and 
fig. 8.
• Install the bracket (2-fig. 2) and the four rivets 21215DE40 (3-fig. 2) as applicable.
NOTE: For riveting methods (Refer to RPI 51-40-04).
• Compute Er value according to the fig. 21.
• Record the values in the appropriate tables ( fig. 9, fig. 10, fig. 11 and fig. 12).
(c) Send the completed tables to Dassault (Western : structures@dassault-falcon.com or
Eastern : structure-repair@dassault-aviation.com).
(2) Inspections and recording of the profile values according to fig. 1 (For S/N 7 through 17 and 19):
Refer to fig. 1, fig. 2, fig. 3, fig. 4, fig. 13, fig. 15, fig. 16, fig. 17, fig. 18, fig. 19, fig. 20 and fig.
21
(a) Use the modelling clay kit to measure the profile values (L, R, Ep and Hr) as described on 
fig. 4 at the critical areas (fig. 2 and fig. 13) for all the points identified in fig. 15 and fig. 16.
• Mix the green modelling clay and the white modelling clay in a proportion of 50%
each.
• Apply the mixture on the critical areas in order to obtain an impression of minimum
thickness 4 mm (0.16 in) (fig. 3).
• Let cure 10 to 15 min at ambient temperature.
• Identify the different points with the specific alpha-numeric codes in fig. 15 and fig. 16
before you remove the impression.
• Cut a 2 mm (0.08 in) thick strip in the impression for each point ( fig. 3).
• Measure the strip with the profile projector ( fig. 3).
• Record the values in the appropriate tables:
FIGURE AREA
- fig. 17 - Pocket Fr 37 - Fr 38, Str 11 - Str 12 (Detail E)
- fig. 18 - Pocket Fr 38 - Fr 39, Str 11 - Str 12 (Detail F)
- fig. 19 - Pocket Fr 39 - Fr 40, Str 11 - Str 12 (Detail G)
- fig. 20 - Pocket Fr 39 - Fr 40, Str 12 - Str 13 (Detail H)
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### Page 8

(b) If Ep is out of value (Refer to the flow chart fig. 1), do the ultrasonic inspection:
CAUTION: THE ULTRASONIC MEASUREMENT MUST BE PERFORMED BY LEVEL-2
CERTIFIED PERSONNEL ACCORDING TO THE EN4179 OR NAS410
STANDARDS.
NOTE: Refer to Section 3 MATERIAL INFORMATION for requested characteristics of the
ultrasonic equipment.
• Operate the equipment in accordance with the manufacturer’s instructions.
• Apply coupling gel on the area.
• Connect the transducer and verify the delay line.
• Adjust setting of the ultrasonic tool with local calibration standard ( fig. 21).
• If you must inspect the pocket between frame 38 and 39 and the stringer 11 and 12:
• Drill out the four rivets (3-fig. 2) in the frame 38 and 39 and remove them with a
drift punch.
• Remove the bracket (2-fig. 2)
• Use the ultrasonic tool to measure the profile values (Et, Em1 and Em2) as described
on fig. 21 at the critical areas ( fig. 2 and fig. 13) for all the points identified in fig. 15
and fig. 16.
• Install the bracket (2-fig. 2) and the four rivets 21215DE40 (3-fig. 2) as applicable.
NOTE: For riveting methods (Refer to RPI 51-40-04).
• Compute Er value according to the fig. 21.
• Record the values in the appropriate tables ( fig. 17, fig. 18, fig. 19 and fig. 20).
(c) Send the completed tables to Dassault (Western : structures@dassault-falcon.com or
Eastern : structure-repair@dassault-aviation.com).
(3) Stiffener installation (For S/N 16, 17 and 19)
Refer to fig. 22
(a) Removal of the rivets from the doubler
• Drill out the 12 rivets (A-fig. 22), (B-fig. 22), (C-fig. 22) and remove them with a drift
punch (Refer to RPI 51-40-03).
• Clean the holes.
(b) Removal of the rivets from the lower pylon angle
• Drill out the two rivets (D-fig. 22) and remove them with a drift punch (Refer to RPI
51-40-03).
• Clean the holes.
(c) Removal of the rivets from the stringer 12
• Drill out the two rivets (E-fig. 22) and remove them with a drift punch (Refer to RPI
51-40-03).
• Clean the holes.
(d) Stiffener installation
• Put stiffener SB7X0042 (1-fig. 22) in position on the lower pylon angle.
• Use the vices to hold stiffener SB7X0042 (1-fig. 22) from the holes (D-fig. 22).
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DASSAULT AVIATION Proprietary Data

### Page 9

• Counterdrill the holes (F-fig. 22) to Ø 4.16 mm (0.164 in.). Reaming tolerances
-95/+105 (-3.7/+4.1) (Refer to RPI 51-40-03).
• Use the vices to hold stiffener SB7X0042 (1-fig. 22) from the holes (F-fig. 22).
• Counterdrill the holes (A-fig. 22) to Ø 4.16 mm (0.164 in.). Reaming tolerances
-95/+105 (-3.7/+4.1) (Refer to RPI 51-40-03).
• Use the vices to hold stiffener SB7X0042 (1-fig. 22) from the holes (A-fig. 22).
• Counterdrill the holes (B-fig. 22) to Ø 3.35 mm (0.132 in.). Reaming tolerances
-95/+105 (-3.7/+4.1) (Refer to RPI 51-40-03).
• Use the vices to hold stiffener SB7X0042 (1-fig. 22) from the holes (B-fig. 22).
• Counterdrill the holes (C-fig. 22) to Ø 4.16 mm (0.164 in.). Reaming tolerances
-95/+105 (-3.7/+4.1) (Refer to RPI 51-40-03).
• Use the vices to hold stiffener SB7X0042 (1-fig. 22) from the holes (C-fig. 22).
• Counterdrill the holes (E-fig. 22) to Ø 4.16 mm (0.164 in.). Reaming tolerances
-95/+105 (-3.7/+4.1) (Refer to RPI 51-40-03).
• Use the vices to hold stiffener SB7X0042 (1-fig. 22) from the holes (E-fig. 22).
• Remove the vices from the holes (D-fig. 22).
• Counterdrill the holes (D-fig. 22) to Ø 4.16 mm (0.164 in.). Reaming tolerances
-95/+105 (-3.7/+4.1) (Refer to RPI 51-40-03).
• Remove the vices (A-fig. 22), (B-fig. 22), (C-fig. 22), (E-fig. 22) and (F-fig. 22) and
stiffener SB7X0042 (1-fig.22).
• Clean the area.
• Install the stiffener (1-fig. 22) in position with interlaying sealant (Refer to TASK
20-32-00-390-801).
• Install rivets P/N 35656C04006XF (2-fig. 22) with interlaying sealant under the rivet
heads (Refer to RPI 51-40-04).
• Install rivets P/N MS14218D5-7 (3-fig. 22) with interlaying sealant under the rivet
heads (Refer to RPI 51-40-04).
• Install rivets P/N MS14218D4-6 (4-fig. 22) with interlaying sealant under the rivet
heads (Refer to RPI 51-40-04).
• Install rivets P/N 35067-40-12 (5-fig. 22) with interlaying sealant under the rivet heads
(Refer to RPI 51-40-04).
(e) Make touch-up of paint on the fasteners with wash primer, anti-corrosion primer and top coat
PU66 (Refer to TASK 20-60-00-370-803).
C. IDENTIFICATION OF THE SERVICE BULLETIN
Refer to fig. 23
(1) If necessary, bond the new “Service Bulletin Compliance” label (1-fig. 23) with high-temperature
sealant on lower frame 42.
(2) With non-removable ink, write the reference SB 042 on the identification plate (1-fig. 23).
D. FINAL STEPS
Refer to fig. 2
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DASSAULT AVIATION Proprietary Data

### Page 10

(1) Make sure that the work area is clean and clear of tools and other items.
(2) Install the insulation blankets.
(3) Install the AMSAC chassis ( 103HN) (1-fig. 2) (Refer to TASK 21-61-09-900-801).
(4) Install the linings ( 272HZ), (272KZ), (272MZ) and (272NZ) (Refer to TASK 25-52-01-900-801).
E. RECORDING
Record compliance with this Service Bulletin in the appropriate aircraft documents.
Fill out the electronic Service Bulletin reply form located in the ”Service Bulletin" page on the Falcon
portal.
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### Page 11

3. MATERIAL INFORMATION
A. MODIFICATION KIT
Kit P/N SBF7X0042A
NEW P/N QTY KEY WORD ITEM FIG
SBF7X0042ALAT including :
- SBF7X0042 1 Stiffener 1 22
- 35656C04006XF 2 Rivet 2 22
- MS14218D5-7 8 Rivet 3 22
- MS14218D4-6 8 Rivet 4 22
- 35067-40-12 2 Rivet 5 22
- 79160 1 SB identification plate 1 23
B. LOCAL PROCUREMENT
As indicated in Consumable Products Manual (CPM):
• cleaner,
• wash primer,
• anti-corrosion primer,
• top coat PU66,
• interlaying sealant.
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DASSAULT AVIATION Proprietary Data

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DASSAULT  SERVICE BULLETIN
AVIATION
FALCON 7X  7X -042
Do the moulding inspection
NO  YES
Ep ≥ 0.05 mm
(Ep ≥0.002 in)
Do the ultrasonic
inspection for critical
points
Complete the
inspection report
Send the inspection
report to DASSAULT
Figure 1: INSPECTION PROCESS FLOW CHART
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DASSAULT  SERVICE BULLETIN
AVIATION
FALCON 7X  7X -042
FR 37  FR 38  FR 39  FR 40
ST 12
ST 13
FR 38  FR 39
ST 12 -
ST 13
Figure 2: INTERNAL VIEWS OF THE INSPECTED AREAS
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### Page 14 (OCR)

DASSAULT  SERVICE BULLETIN
AVIATION
FALCON 7X  7X -042
Figure 3: MOULDING METHOD DESCRIPTION
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DASSAULT  SERVICE BULLETIN
AVIATION
FALCON 7X  7X -042
Moulding and calculation methods necessary for each area:
L, R, Ep and Hr → Moulding method
Figure 4: MOULDING METHOD MEASURING VALUES
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DASSAULT  SERVICE BULLETIN
AVIATION
FALCON 7X  7X -042
Critical Pocket
Figure 5: RH FUSELAGE PANEL - CRITICAL POCKET LOCATION (INTERNAL VIEW) (FOR S/N 2 AND 4
THROUGH 6)
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DASSAULT  SERVICE BULLETIN
AVIATION
FALCON 7X  7X -042
A-A
Typical section of the normal profile
A-A
Typical section of the defective profile
Figure 6: TYPICAL SECTION OF THE CHEMICALLY-MILLED PROFILE (NORMAL AND DEFECTIVE) (FOR
S/N 2 AND 4 THROUGH 6)
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DASSAULT  SERVICE BULLETIN
AVIATION
FALCON 7X  7X -042
Fr37  Fr38
340
*A20  A6
--A19  A7
128
- A18-  •- 48 -
-A17  Aº _
_A16  A15  A14  A10
Str12
Pocket Frame 37-38 / Stringer 11-12 RHS
Fr38  Fr39
360
45
62
64  B20  B1  B2  B5
B6
-- B19  B7 -
120  . - B8 -
128  - B18-
B9_._
120  _B17  B15  B14  B13  B12  B11  B10 -
B16
Str 12
Pocket Frame 38-39 / Stringer 11-12 RHS
Figure 7: LOCATION OF THE MEASURED POINTS (FOR S/N 2 AND 4 THROUGH 6)
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DASSAULT  SERVICE BULLETIN
AVIATION
FALCON 7X  7X -042
Fr39 +  185  Fr40
C5  C6
* C20 C1  C2  C7
64  *C19  25
• C18  C8
96
• C17  25  125
C16 C15  C9
C13  C12  C11 C10
Str12
D20
D2
D19
D5
94  D18
20  D6
D17  D7
D8
D16
D15  D14  D9  130
D13  D12  D11  D10
Str13
(*)
Pocket Frame 39-40 / Stringer 11-13 RHS
Figure 8: LOCATION OF THE MEASURED POINTS (FOR S/N 2 AND 4 THROUGH 6) (CONT'D)
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DASSAULT  SERVICE BULLETIN
AVIATION
FALCON 7X  7X -042
Address  structures@dassault-falcon.com  Eastern : structure-repair@dassault-aviation.com  Calcul
I Fr 37 - Fr 38, Str 11 - Str 12 (Detail A)  Hr
Western  Measures  Moulding Method  Dassault approval
J  Controller
Ultrasonic Method  Em1
Aircraft owner  RH Panel  Et  Approval  Name  Company  Date  Visa
Inspection  points
Aircraft serial number
Figure 9: RECORDED MEASURES SHEET FR 37 - FR 38, STR 11 - STR 12 (DETAIL A) (FOR S/N 2 AND 4
THROUGH 6)
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DASSAULT  SERVICE BULLETIN
AVIATION
FALCON 7X  7X -042
Western : structures@dassault-falcon.com  Eastern : structure-repair@dassault-aviation.com  Calcul  Method
Address
RH Panel Fr 38 - Fr 39, Str 11 - Str 12 (Detail B)  Hr
Moulding Method  Ep  Dassault approval
Measures
Controller
Aircraft owner  Ultrasonic Method  Em1
Approval
Name  Company  Date  Visa
Aircraft serial number  Inspection  points
Figure 10: RECORDED MEASURES SHEET FR 38 - FR 39, STR 11 - STR 12 (DETAIL B) (FOR S/N 2 AND
4 THROUGH 6)
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DASSAULT  SERVICE BULLETIN
AVIATION
FALCON 7X  7X -042
Western : structures@dassault-falcon.com  Eastern : structure-repair@dassault-aviation.com  Calcul  Method
Address
RH Panel Fr 39 - Fr 40, Str 11 - Str 12 (Detail C)  Hr
Moulding Method  Ep  Dassault approval
Measures
Controller
Aircraft owner  Ultrasonic Method  Em1  Approval
Name  Company  Date  Visa
Inspection points
Aircraft serial number
Figure 11: RECORDED MEASURES SHEET FR 39 - FR 40, STR 11 - STR 12 (DETAIL C) (FOR S/N 2 AND
4 THROUGH 6)
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DASSAULT  SERVICE BULLETIN
AVIATION
FALCON 7X  7X -042
Western : structures@dassault-falcon.com  Eastern : structure-repair@dassault-aviation.com  Calcul Method
Address
RH Panel Fr 39 - Fr 40, Str 12 - Str 13 (Detail D)  Hr
Moulding Method  Ep  Dassault approval
Measures
J  Controller
Aircraft owner  Ultrasonic Method  Em1  Approval
Name  Company  Date  Visa
Aircraft serial number  Inspection  points
Figure 12: RECORDED MEASURES SHEET FR 39 - FR 40, STR 12 - STR 13 (DETAIL D) (FOR S/N 2 AND
4 THROUGH 6)
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DASSAULT  SERVICE BULLETIN
AVIATION
FALCON 7X  7X -042
Critical Pocket
Figure 13: RH FUSELAGE PANEL - CRITICAL POCKET LOCATION (INTERNAL VIEW) (FOR S/N 7
THROUGH 17 AND 19)
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DASSAULT  SERVICE BULLETIN
AVIATION
FALCON 7X  7X -042
A-A  Typical section of the defective profile  B-B  Typical section of the defective profile
Typical section of the normal profile  B-B  Typical section of the normal profile
A-A
Figure 14: TYPICAL SECTION OF THE CHEMICALLY-MILLED PROFILE (NORMAL AND DEFECTIVE) (FOR
S/N 7 THROUGH 17 AND 19)
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DASSAULT  SERVICE BULLETIN
AVIATION
FALCON 7X  7X -042
Fr37  340  Fr38
170
E5
E40  E26
E19 -  E39  E27
128  LT15  120
·E18—€  - E38  - E28  E8
E17-  E37  E29  E9
E36  E35  E34  E32  E30
40  40  40
• E10
E15  E13  • E12 g  E11
Str12
Pocket Frame 37-38 / Stringer 11-12 RHS
Fr38  360  Fr39
180
F4
45  45  45  +5
F6
62
64
F40  F25  F26
F19  F39  F27  F7
128  • F28 —  F8 ·
F18  20  F38  F29  F30  F9
F17.  F37  F35  F34  F33  F32  F31
F36
F10
45
F16
F15  F14
Str12
Pocket Frame 37-38 / Stringer 11-12 RHS
Figure 15: LOCATION OF THE MEASURED POINTS (FOR S/N 7 THROUGH 17 AND 19)
May 03, 2016  ATA 53
Revision 1  Page 24 / 32

### Page 27 (OCR)

DASSAULT  SERVICE BULLETIN
AVIATION
FALCON 7X  7X -042
185
Fr39  93  Fr40
G4  G5
G2
20, 20 ,  G6
20
G24  G25 G26
• G40 G21  G22  G23  G27  G7  63
64  G19  20  • G39
G1:  • G38  G28
96
G37  25  125
G36 G35  G34  G29
G32  G31 G30
• G14  G10
G12  y G11
• Str12
H20
H19
20
94  -H18
20
H17  H7  115
H8
H16  1D15
H15  30
H14  H13 H12  H11  H10
20"  20  Str13
Pocket Frame 39-40 / Stringer 11-13 RHS
Figure 16: LOCATION OF THE MEASURED POINTS (FOR S/N 7 THROUGH 17 AND 19) (CONT'D)
May 03, 2016  ATA 53
Revision 1  Page 25 / 32

### Page 28 (OCR)

DASSAULT  SERVICE BULLETIN
VIATION
FALCON 7X  7X -042
Eastern : structure-repair@dassault-aviation.com  Calcul  Method
Address  Western : structures@dassault-falcon.com  Measures  Moulding Method
Str 11 - Str 12 (Detail E)  Ultrasonic  Method  Em2  Dassault approval
Inspection  points  E21  E22  E23  E24  E25  E26  E27  E28  E29  E30  E31  E32  E33  E34  E35  E36  E37  E38  E39  E40
Aircraft owner  RH Panel Fr 37 - Fr 38,  Calcul  Moulding Method  Method  Ep  Controller
Approval
Company  Date
Ultrasonic Method  Em1
Aircraft serial number  Inspection  points
Figure 17: RECORDED MEASURES SHEET FR 37 - FR 38, STR 11 - STR 12 (DETAIL E) (FOR S/N 7
THROUGH 17 AND 19)
May 03, 2016  ATA 53
Revision 1  Page 26 / 32

### Page 29 (OCR)

DASSAULT  SERVICE BULLETIN
AVIATION
FALCON 7X  7X -042
Eastern : structure-repair@dassault-aviation.com  Calcul  Method  Er 2
Western : structures@dassault-falcon.com  Moulding Method  Ep
Address  Measures
Str 11 - Str 12 (Detail F)  Ultrasonic  Method  Em2  Dassault approval
Inspection  points  F21  F22  F23  F24  F25  F26  F27  F28  F29  F30  F31  F32  F33  F34  F35  F36  F37  F38  F39  F40
Aircraft owner  RH Panel Fr 38 - Fr 39,  Calcul  Moulding Method  Method  Er 1  Controller  Approval
Company  Date
Ultrasonic Method  Em1
Aircraft serial number  Inspection  points
Figure 18: RECORDED MEASURES SHEET FR 38 - FR 39, STR 11 - STR 12 (DETAIL F) (FOR S/N 7
THROUGH 17 AND 19)
May 03, 2016  ATA 53
Revision 1  Page 27 / 32

### Page 30 (OCR)

DASSAULT  SERVICE BULLETIN
AVIATION
FALCON 7X  7X -042
Eastern : structure-repair@dassault-aviation.com  Calcul  Method  Er 2
Address  Western : structures@dassault-falcon.com  Moulding Method
RH Panel Fr 39 - Fr 40, Str 11 - Str 12 (Detail G)  J
Ultrasonic  Method  Em2  Dassault approval
Inspection  points  G21  G22  G23  G24  G25  G26  G27  G28  G29  G30  G31  G32  G33  G34  G35  G36  G37  G38  G39  G40
Calcul  Method  Er 1  Controller
Aircraft owner  Moulding Method  Ep
Approval
Name  Company  Date  Visa
Aircraft serial number  Measures  Ultrasonic Method
Inspection  points
Figure 19: RECORDED MEASURES SHEET FR 39 - FR 40, (DETAIL G) (FOR S/N 7 THROUGH 17 AND 19)
May 03, 2016  ATA 53
Revision 1  Page 28 / 32

### Page 31 (OCR)

DASSAULT  SERVICE BULLETIN
AVIATION
FALCON 7X  7X -042
Western : structures@dassault-falcon.com  Eastern : structure-repair@dassault-aviation.com  Calcul  Method
Address  RH Panel Fr 39 - Fr 40, Str 12 - Str 13 (Detail H)  Measures  Moulding Method  Dassault approval
Controller
Aircraft owner  Ultrasonic Method  Em1  Approval
Name  Company  Date  Visa
Et
Aircraft serial number
Figure 20: RECORDED MEASURES SHEET FR 39 - FR 40, STR 12 - STR 13 (DETAIL H) (FOR S/N 7
THROUGH 17 AND 19)
May 03, 2016  ATA 53
Revision 1  Page 29 / 32

### Page 32 (OCR)

DASSAULT  SERVICE BULLETIN
AVIATION
FALCON 7X  7X -042
Ultrasonic methods:
Et, Em1, Em2
Er → Calculation method Er = Em + Hr - Ep
Range  3 to 5 mm  Logic: measure
Probe delay  Adjust on first back echo n°1  Amplitude: -45%
Velocity  To adjust on standard, in  Gate select A  Position: on back echo n°1
accordance with the depth  ( see A-scan picture )
measured
Display delay  0%  Logic: measure
Rectify  Damping  150 Ohms  RF  Gate select B  Amplitude: - 45%  Position: on back echo n° 2
(see A-scan picture)
Frequencr  10-25 MHZ HP
Reject  0%
Kesult  SBAMA
Amplitude  -60 % FSH
Back echo 1°2
A-scan view
Front echo
(Delay line)  Back echo u°1
Amplitude  Back echo n°2
Back echo n°3
¡ Gate A  Cate B
TOF
Nota: The gates positions are important for the measure, only positioned on the first negative back echo Nrl
Figure 21: ULTRASONIC MEASURING VALUES AND ULTRASONIC TOOL CALIBRATION
May 03, 2016  ATA 53
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### Page 33 (OCR)

DASSAULT  SERVICE BULLETIN
AVIATION
FALCON 7X  7X -042
STOR 12
SEE DETAIL A  RIGHT ASSY
VIEW LOOKING INBOARD
(NO SCALE)
ASSEMBLY REFERENCE
SIXTH FIXING STARTING FROM F37
SCREW ST38477
- 38
LOWER PYLON ANGLE
D
1-0.2
DOUBLER
- 3
STGR 12
5
DETAIL A
Figure 22: STIFFENER INSTALLATION
May 03, 2016  ATA 53
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### Page 34 (OCR)

DASSAULT  SERVICE BULLETIN
AVIATION
FALCON 7X  7X -042
FR41  FR42  FR43
FR44
Figure 23: IDENTIFICATION PLATE LOCATION
May 03, 2016  END OF DOCUMENT  ATA 53
Revision 1  Page 32 / 32

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