# Boeing Service Bulletin A3514: Revision 1, from page 25

- Rights: © The Boeing Company. Filed by the FAA in regulations.gov docket FAA-2018-0504; AD 2018-19-32 incorporates this document by reference. Not covered by OpenAirDocs’ CC0 dedication.
- Document: [Boeing Service Bulletin A3514](https://openairdocs.org/service-documents/boeing/a3514.md)
- Title as filed: SB-707-00A3514-01--
- Pages: 48
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## Text

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### Page 25

2.    MATERIAL INFORMATION
A. Material - Price and Availability
The operator can supply the parts and materials shown in Paragraph 2.C., Parts Necessary for Each
Airplane. As an alternative, operators can purchase the parts from Boeing Spares. This service bulletin
does not show the Boeing price and supply data.
B. Industry Support Information
Boeing warranty remedies are not available for the configuration changes, inspection, and/or repair
procedures given in this service bulletin.
C. Parts Necessary for Each Airplane
1. Kits/Parts:
None.
2. Parts and Materials Supplied by the Operator:
The following parts or materials are necessary to do the change in this service bulletin. Parts and
materials in the manuals given in Paragraph 1.J., References, can also be necessary. Examine
operator part and material supply to make sure all necessary parts and materials are available.
Group 1:
NotesNameQTYPart Number / Specifica-
tion
(a)Front Spar Fitting - Inboard (Strut num-
bers 2 and 3)
265-42128-1
(a)Front Spar Fitting - Outboard (Strut
numbers 1 and 4)
265-13347-9
(a) Fitting required only if the existing fitting is cracked.
Group 2:
NotesNameQTYPart Number / Specifica-
tion
(a)Front Spar Fitting - Inboard (Strut num-
bers 2 and 3)
265-42128-7
(a)Front Spar Fitting - Outboard (Strut
numbers 1 and 4)
265-13347-9
(a) Fitting required only if the existing fitting is cracked.
3. Parts Modified and Reidentified:
None.
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4. Parts Removed and Not Replaced:
None.
D. Parts Necessary to Change Spares
None.
E. Special Tooling - Price and Availability
None.
F. Special Tooling Necessary to do this Service Bulletin
No special tools or equipment are necessary to do the change in this service bulletin. But, maintenance
and overhaul tools in the manuals given in Paragraph 1.J., References, can be necessary. Examine
operator tool supply to make sure all necessary tools are available.
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### Page 27

3.    ACCOMPLISHMENT INSTRUCTIONS
A. GENERAL INFORMATION
NOTE: 1. Manual titles are referred to by acronyms. Refer to Paragraph 1.J., References, for
definition of the acronyms.
2. Obey all of the warnings and cautions given in the specified manual sections.
3. Unless shown differently, these dimensions and tolerances are used:
– Linear dimensions are in inches
– Tolerance on linear dimensions, other than rivet and bolt edge margins, is plus
or minus 0.03 inch
– Tolerance on rivet and bolt edge margin is plus or minus 0.05 inch
– Angular tolerance is plus or minus 2 degrees
– Hole dimensions for standard solid rivets and fasteners are in Structural Repair
Manual (SRM) Chapter 51
– Torque Values:
— Values for structural fasteners are given in 707 Structural Repair Manual,
Chapter 51.
— Values for airframe maintenance tasks are included in Chapter 20 of 707
Aircraft Maintenance Manual (AMM).
— Values for electrical maintenance tasks are included in Chapter 20 of
Standard Wiring Practices Manual (SWPM).
— Values for engine maintenance tasks are included in Chapter 70 of 707
Aircraft Maintenance Manual (AMM).
— Non-standard torque values for maintenance tasks are included in the
applicable installation step.
4. Use the approved fastener, process and material substitutions in accordance with
SRM Chapter 51.
5. A Detailed Inspection is defined as: An intensive examination of a specific item,
installation, or assembly to detect damage, failure, or irregularity. Available lighting
is normally supplemented with a direct source of good lighting at an intensity deemed
appropriate. Inspection aids such as mirrors, magnifying lenses, etc. may be
necessary. Surface cleaning and elaborate procedures may be required.
6. These work instructions refer to procedures included in other Boeing documents.
When the words "refer to" are used and the operator has an accepted alternative
procedure, the accepted alternative procedure can be used. When the words "in
accordance with" are included in the instruction, the procedure in the Boeing document
must be used.
7. The instructions in Paragraph 3.B., Work Instructions and the figures can include
operation of tools or test equipment. Boeing Engineering Tool Drawings, the Illustrated
Tool and Equipment Manual, and the Special Tool and Ground Handling Drawing
Index contain data on versions of the tools or test equipment that you can use. It is
permitted to use replaced tools. It is not permitted to use superseded tools.
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### Page 28

8. If it is necessary to remove more parts for access, you can remove those parts. If
you can get access without removing identified parts, it is not necessary to remove
all of the identified parts. Jacking and shoring limitations must be observed.
9. Where the work instructions include installation of a kept part, a new or serviceable
part with the same part number can be installed as an alternative to the kept part.
10. When more than one OPTION is given for a CONDITION, do only one of the OPTION
numbers. When more than one ACTION is given for a CONDITION number or an
OPTION number, do all of the ACTION numbers for that CONDITION number or
OPTION number.
11. The compliance times for the actions in Paragraph 3.B., WORK INSTRUCTIONS
are in Paragraph 1.E., Compliance.
B. WORK INSTRUCTIONS
Detailed Inspection of the Front Spar Fittings at Nacelle Struts, Numbers 1, 2, 3 and 4
WARNING: MAKE SURE THAT LOCK ASSEMBLY IS PROPERLY INSTALLED TO PREVENT
OPERATION OF LEADING EDGE FLAPS AND SLATS. OPERATION OF SLATS DURING
MAINTENANCE COULD RESULT IN DAMAGE TO THE AIRPLANE OR SERIOUS
INJURY TO MAINTENANCE PERSONNEL.
1. Deactivate the leading edge flaps. Refer to 707 AMM 27-16-202/201.
2. Deactivate all thrust reversers on the left side of the airplane. Refer to 707 AMM 78-5-0/201.
3. Inspect the nacelle strut number 1:
a. Remove access door 1742 on the left side of the strut nearest to the front spar fitting. Refer
to 707 AMM 12-2-0. Or, if the airplane was manufactured with removable inspection hole
caps, as shown in FIGURE 1, remove the inspection hole caps on both sides of the strut
centerline in the crown skin.
b. Do a Detailed Inspection of the upper surface of the front spar fitting as shown in FIGURE 2.
c. If cracks are found during inspection, then remove the cracked front spar fitting and install a
new front spar fitting. Refer to Paragraph 2.C., Parts Necessary for Each Airplane, for fitting
part number.
d. Replace the access door 1742 on the left side of the strut, if removed. Refer to 707 AMM
12-2-0. Or, replace the inspection hole caps.
4. Inspect the nacelle strut number 2:
a. Remove access door 1708 on the left side of the strut nearest to the front spar fitting. Refer
to 707 AMM 12-2-0. Or, if the airplane was manufactured with removable inspection hole
caps, as shown in FIGURE 1, remove the inspection hole caps on both sides of the strut
centerline in the crown skin.
b. Do a Detailed Inspection of the upper surface of the front spar fitting as shown in FIGURE 3.
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### Page 29

c. If cracks are found during inspection, then remove the cracked front spar fitting and install a
new front spar fitting. Refer to Paragraph 2.C., Parts Necessary for Each Airplane, for fitting
part number.
d. Replace the access door 1708 on the left side of the strut, if removed. Refer to 707 AMM
12-2-0. Or, replace the inspection hole caps.
5. Reactivate all thrust reversers on the left side of the airplane. Refer to 707 AMM 78-5-0/201.
6. Deactivate all thrust reversers on the right side of the airplane. Refer to 707 AMM 78-5-0/201.
7. Inspect the nacelle strut number 3:
a. Remove access door 1708 on the left side of the strut nearest to the front spar fitting. Refer
to 707 AMM 12-2-0. Or, if the airplane was manufactured with removable inspection hole
caps, as shown in FIGURE 1, remove the inspection hole caps on both sides of the strut
centerline in the crown skin.
b. Do a Detailed Inspection of the upper surface of the front spar fitting as shown in FIGURE 4.
c. If cracks are found during inspection, then remove the cracked front spar fitting and install a
new front spar fitting. Refer to Paragraph 2.C., Parts Necessary for Each Airplane, for fitting
part number.
d. Replace the access door 1708 on the left side of the strut, if removed. Refer to 707 AMM
12-2-0. Or, replace the inspection hole caps.
8. Inspect the nacelle strut number 4:
a. Remove access door 1742 on the left side of the strut nearest to the front spar fitting. Refer
to 707 AMM 12-2-0. Or, if the airplane was manufactured with removable inspection hole
caps, as shown in FIGURE 1, remove the inspection hole caps on both sides of the strut
centerline in the crown skin.
b. Do a Detailed Inspection of the upper surface of the front spar fitting as shown in FIGURE 5.
c. If cracks are found during inspection, then remove the cracked front spar fitting and install a
new front spar fitting. Refer to Paragraph 2.C., Parts Necessary for Each Airplane, for fitting
part number.
d. Replace the access door 1742 on the left side of the strut, if removed. Refer to 707 AMM
12-2-0. Or, replace the inspection hole caps.
9. Reactivate all thrust reversers on the right side of the airplane. 707 AMM 78-5-0/201.
10. Reactivate the leading edge flaps. Refer to 707 AMM 27-16-202/201.
11. Put the airplane back to a serviceable condition.
Surface High Frequency Eddy Current (HFEC) Inspection of the Aft Lug(s) on the Front Spar
Fittings at Nacelle Struts, Numbers 1, 2, 3 and 4:
1. Do PART 1: OPEN ACCESS.
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2. Do PART 2: SURFACE HFEC INSPECTION OF THE AFT LUG(S) ON THE FRONT SPAR
FITTINGS AT NACELLE STRUTS NUMBERS 1, 2, 3 AND 4 for any crack.
a. CONDITION 1: ANY CRACK FOUND
(1) CONDITION 1 (ACTION 1): Do PART 3: FRONT SPAR FITTING REPLACEMENT.
(2) CONDITION 1 (ACTION 2): Repeat PART 2: SURFACE HFEC INSPECTION OF THE
AFT LUG(S) ON THE FRONT SPAR FITTINGS AT NACELLE STRUTS NUMBERS 1,
2, 3 AND 4 for any crack at the repeat interval specified in Paragraph 1.E., Compliance.
b. CONDITION 2: NO CRACK FOUND
(1) Repeat PART 2: SURFACE HFEC INSPECTION OF THE AFT LUG(S) ON THE FRONT
SPAR FITTINGS AT NACELLE STRUTS NUMBERS 1, 2, 3 AND 4 for any crack at the
repeat interval specified in Paragraph 1.E., Compliance.
3. Do PART 4: CLOSE ACCESS.
4. Put the airplane back to a serviceable condition.
PART 1: OPEN ACCESS
WARNING: MAKE SURE THAT LOCK ASSEMBLY IS PROPERLY INSTALLED TO PREVENT
OPERATION OF LEADING EDGE FLAPS AND SLATS. OPERATION OF SLATS DURING
MAINTENANCE COULD RESULT IN DAMAGE TO THE AIRPLANE OR SERIOUS
INJURY TO MAINTENANCE PERSONNEL.
1. Deactivate the leading edge flaps. Refer to 707 AMM 27-16-202/201 as an accepted procedure.
2. Deactivate all thrust reversers. Refer to 707 AMM 78-5-0/201 as an accepted procedure.
3. Remove and keep the access panels shown in the table below. Refer to 707 AMM 12-2-0 for
access panel location.
Access Panel NumberNacelle Strut Number
1745, 17531
1709, 17212
1709, 17213
1745, 17534
4. At nacelle struts number 1, 2, 3 and 4, remove and keep the bolt from the aft lug(s) on each front
spar fitting. Disengage wing-to-spar fitting from front spar fitting. Refer to 707 AMM 54-00, Revision
Notice (RN) 54-18 as an accepted procedure.
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### Page 31

PART 2: SURFACE HFEC INSPECTION OF THE AFT LUG(S) ON THE FRONT SPAR FITTINGS
AT NACELLE STRUTS NUMBERS 1, 2, 3 AND 4
1. Do a magnetic inspection of the front spar fitting to find if the material is aluminum or steel, and
do a surface High Frequency Eddy Current (HFEC) inspection of the front spar fitting aft lug(s) for
any crack, in accordance with the figures below:
FigureNacelle Strut Number
FIGURE 61
FIGURE 72
FIGURE 83
FIGURE 94
PART 3: FRONT SPAR FITTING REPLACEMENT
1. Contact The Boeing Company for instructions to do the actions that follow, and do the instructions:
a. Remove the cracked front spar fitting.
b. Install a new front spar fitting. Refer to Paragraph 2.C., Parts Necessary for Each Airplane,
for fitting part number.
PART 4: CLOSE ACCESS
1. At nacelle struts number 1, 2, 3 and 4, engage wing-to-spar fitting to front spar fitting. Install the
kept bolt in the aft lug(s) on each front spar fitting. Refer to 707 AMM 54-00, RN 54-18 as an
accepted procedure.
2. Install the kept access panels shown in the table below. Refer to 707 AMM 12-2-0 for access panel
location.
Access Panel NumberNacelle Strut Number
1745, 17531
1709, 17212
1709, 17213
1745, 17534
3. Reactivate all thrust reversers. Refer to 707 AMM 78-5-0/201 as an accepted procedure.
4. Reactivate the leading edge flaps. Refer to 707 AMM 27-16-202/201 as an accepted procedure.
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### Page 32 (OCR)

BOEING SERVICE BULLETIN А3514
ALERT  ALERT
This Figure applies only to: Group 1.
INSPECTION
HOLE CAPS
UP
ACCESS  FWD <
PANEL
FIGURE 1: NACELLE ACCESS - FRONT SPAR FITTING - ALL NACELLES
(SHEET 1 OF 1)
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### Page 33

The step numbers shown below agree with the numbers shown in the circle symbols in the figure.
MORE DATAREFERENCESPROCEDURENAMETASKSTEP
(a)-Detailed InspectionFront Spar FittingInspect1
(a) Do a detailed inspection of the upper surface of the front spar fitting. Pay particular attention to the front
spar fitting surface around the fasteners.
FIGURE 2: NACELLE NUMBER 1 - FRONT SPAR FITTING - INSPECTION
(SHEET 1 OF 1)
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### Page 34

The step numbers shown below agree with the numbers shown in the circle symbols in the figure.
MORE DATAREFERENCESPROCEDURENAMETASKSTEP
(a)-Detailed InspectionFront Spar FittingInspect1
(a) Do a detailed inspection of the upper surface of the front spar fitting. Pay particular attention to the front
spar fitting surface around the fasteners.
FIGURE 3: NACELLE NUMBER 2 - FRONT SPAR FITTING - INSPECTION
(SHEET 1 OF 1)
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### Page 35

The step numbers shown below agree with the numbers shown in the circle symbols in the figure.
MORE DATAREFERENCESPROCEDURENAMETASKSTEP
(a)-Detailed InspectionFront Spar FittingInspect1
(a) Do a detailed inspection of the upper surface of the front spar fitting. Pay particular attention to the front
spar fitting surface around the fasteners.
FIGURE 4: NACELLE NUMBER 3 - FRONT SPAR FITTING - INSPECTION
(SHEET 1 OF 1)
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### Page 36

The step numbers shown below agree with the numbers shown in the circle symbols in the figure.
MORE DATAREFERENCESPROCEDURENAMETASKSTEP
(a)-Detailed InspectionFront Spar FittingInspect1
(a) Do a detailed inspection of the upper surface of the front spar fitting. Pay particular attention to the front
spar fitting surface around the fasteners.
FIGURE 5: NACELLE NUMBER 4 - FRONT SPAR FITTING - INSPECTION
(SHEET 1 OF 1)
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### Page 37

FIGURE 6: NACELLE NUMBER 1 - FRONT SPAR FITTING AFT LUGS - SURFACE HIGH FREQUENCY
EDDY CURRENT INSPECTION
(SHEET 1 OF 3)
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### Page 38

The step numbers shown below agree with the numbers shown in the circle symbols in the figure.
More DataQtyIdentificationNameTaskStep
(a)1-Front Spar FittingInspect1
(b) (c)2-Front Spar Fitting Aft
Lug
Inspect2
(a) Do a magnetic inspection of the front spar fitting to find if the material is aluminum or steel. Use a magnet
to find if there is a magnetic force that pulls the magnet to the front spar fitting. If there is a magnetic force,
the front spar fitting is made from steel. If there is no magnetic force, the front spar fitting is made from
aluminum.
(b) For aluminum front spar fitting, do a surface HFEC inspection around the lug hole on the two sides of
each aft lug of the front spar fitting for any crack in accordance with 707, 720 NDT Manual Part 6, 51-00-
00, Figure 4 or Figure 23.
FIGURE 6: NACELLE NUMBER 1 - FRONT SPAR FITTING AFT LUGS - SURFACE HIGH FREQUENCY
EDDY CURRENT INSPECTION
(SHEET 2 OF 3)
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More DataQtyIdentificationNameTaskStep
(c) For steel front spar fitting, do a surface HFEC inspection around the lug hole on the two sides of each aft
lug of the front spar fitting for any crack in accordance with 707, 720 NDT Manual Part 6, 51-00-00, Figure
13 or Figure 24.
FIGURE 6: NACELLE NUMBER 1 - FRONT SPAR FITTING AFT LUGS - SURFACE HIGH FREQUENCY
EDDY CURRENT INSPECTION
(SHEET 3 OF 3)
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FIGURE 7: NACELLE NUMBER 2 - FRONT SPAR FITTING AFT LUG - SURFACE HIGH FREQUENCY EDDY
CURRENT INSPECTION
(SHEET 1 OF 3)
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### Page 41

The step numbers shown below agree with the numbers shown in the circle symbols in the figure.
More DataQtyIdentificationNameTaskStep
(a)1-Front Spar FittingInspect1
(b) (c)1-Front Spar Fitting Aft
Lug
Inspect2
(a) Do a magnetic inspection of the front spar fitting to find if the material is aluminum or steel. Use a magnet
to find if there is a magnetic force that pulls the magnet to the front spar fitting. If there is a magnetic force,
the front spar fitting is made from steel. If there is no magnetic force, the front spar fitting is made from
aluminum.
(b) For aluminum front spar fitting, do a surface HFEC inspection around the lug hole on the two sides of the
aft lug of the front spar fitting for any crack in accordance with 707, 720 NDT Manual Part 6, 51-00-00,
Figure 4 or Figure 23.
FIGURE 7: NACELLE NUMBER 2 - FRONT SPAR FITTING AFT LUG - SURFACE HIGH FREQUENCY EDDY
CURRENT INSPECTION
(SHEET 2 OF 3)
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### Page 42

More DataQtyIdentificationNameTaskStep
(c) For steel front spar fitting, do a surface HFEC inspection around the lug hole on the two sides of the aft
lug of the front spar fitting for any crack in accordance with 707, 720 NDT Manual Part 6, 51-00-00, Figure
13 or Figure 24.
FIGURE 7: NACELLE NUMBER 2 - FRONT SPAR FITTING AFT LUG - SURFACE HIGH FREQUENCY EDDY
CURRENT INSPECTION
(SHEET 3 OF 3)
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FIGURE 8: NACELLE NUMBER 3 - FRONT SPAR FITTING AFT LUG - SURFACE HIGH FREQUENCY EDDY
CURRENT INSPECTION
(SHEET 1 OF 3)
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### Page 44

The step numbers shown below agree with the numbers shown in the circle symbols in the figure.
More DataQtyIdentificationNameTaskStep
(a)1-Front Spar FittingInspect1
(b) (c)1-Front Spar Fitting Aft
Lug
Inspect2
(a) Do a magnetic inspection of the front spar fitting to find if the material is aluminum or steel. Use a magnet
to find if there is a magnetic force that pulls the magnet to the front spar fitting. If there is a magnetic force,
the front spar fitting is made from steel. If there is no magnetic force, the front spar fitting is made from
aluminum.
(b) For aluminum front spar fitting, do a surface HFEC inspection around the lug hole on the two sides of the
aft lug of the front spar fitting for any crack in accordance with 707, 720 NDT Manual Part 6, 51-00-00,
Figure 4 or Figure 23.
FIGURE 8: NACELLE NUMBER 3 - FRONT SPAR FITTING AFT LUG - SURFACE HIGH FREQUENCY EDDY
CURRENT INSPECTION
(SHEET 2 OF 3)
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### Page 45

More DataQtyIdentificationNameTaskStep
(c) For steel front spar fitting, do a surface HFEC inspection around the lug hole on the two sides of the aft
lug of the front spar fitting for any crack in accordance with 707, 720 NDT Manual Part 6, 51-00-00, Figure
13 or Figure 24.
FIGURE 8: NACELLE NUMBER 3 - FRONT SPAR FITTING AFT LUG - SURFACE HIGH FREQUENCY EDDY
CURRENT INSPECTION
(SHEET 3 OF 3)
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FIGURE 9: NACELLE NUMBER 4 - FRONT SPAR FITTING AFT LUGS - SURFACE HIGH FREQUENCY
EDDY CURRENT INSPECTION
(SHEET 1 OF 3)
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### Page 47

The step numbers shown below agree with the numbers shown in the circle symbols in the figure.
More DataQtyIdentificationNameTaskStep
(a)1-Front Spar FittingInspect1
(b) (c)2-Front Spar Fitting Aft
Lug
Inspect2
(a) Do a magnetic inspection of the front spar fitting to find if the material is aluminum or steel. Use a magnet
to find if there is a magnetic force that pulls the magnet to the front spar fitting. If there is a magnetic force,
the front spar fitting is made from steel. If there is no magnetic force, the front spar fitting is made from
aluminum.
(b) For aluminum front spar fitting, do a surface HFEC inspection around the lug hole on the two sides of
each aft lug of the front spar fitting for any crack in accordance with 707, 720 NDT Manual Part 6, 51-00-
00, Figure 4 or Figure 23.
FIGURE 9: NACELLE NUMBER 4 - FRONT SPAR FITTING AFT LUGS - SURFACE HIGH FREQUENCY
EDDY CURRENT INSPECTION
(SHEET 2 OF 3)
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More DataQtyIdentificationNameTaskStep
(c) For steel front spar fitting, do a surface HFEC inspection around the lug hole on the two sides of each aft
lug of the front spar fitting for any crack in accordance with 707, 720 NDT Manual Part 6, 51-00-00, Figure
13 or Figure 24.
FIGURE 9: NACELLE NUMBER 4 - FRONT SPAR FITTING AFT LUGS - SURFACE HIGH FREQUENCY
EDDY CURRENT INSPECTION
(SHEET 3 OF 3)
Export Controlled ECCN: 9E991 - BOEING
PROPRIETARY - Copyright © Unpublished
Work - See page 1 for details.
Original Issue: July 29, 2004
A3514Revision 1 November 09, 2016
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