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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 / Specification
(a)Front Spar Fitting - Inboard (Strut numbers 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 / Specification
(a)Front Spar Fitting - Inboard (Strut numbers 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.
Export Controlled ECCN: 9E991 - BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details.
Original Issue: July 29, 2004 A3514Revision 1: November 09, 2016 25 of 48 BOEING SERVICE BULLETIN A3514
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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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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.
Export Controlled ECCN: 9E991 - BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details.
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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.
Export Controlled ECCN: 9E991 - BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details.
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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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Original Issue: July 29, 2004 A3514Revision 1: November 09, 2016 29 of 48 BOEING SERVICE BULLETIN A3514
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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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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.
Export Controlled ECCN: 9E991 - BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details.
Original Issue: July 29, 2004 A3514Revision 1: November 09, 2016 31 of 48 BOEING SERVICE BULLETIN A3514
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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) Original Issue: July 29, 2004 Revision 1 November 09, 2016 Export Controlled ECCN: 9E991 - BOEING PROPRIETARY - Copyright © Unpublished A3514 Work - See page 1 for details. 32 of 48
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) Export Controlled ECCN: 9E991 - BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details.
Original Issue: July 29, 2004 A3514Revision 1 November 09, 2016 33 of 48 BOEING SERVICE BULLETIN A3514
ALERTALERT
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) Export Controlled ECCN: 9E991 - BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details.
Original Issue: July 29, 2004 A3514Revision 1 November 09, 2016 34 of 48 BOEING SERVICE BULLETIN A3514
ALERTALERT
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) Export Controlled ECCN: 9E991 - BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details.
Original Issue: July 29, 2004 A3514Revision 1 November 09, 2016 35 of 48 BOEING SERVICE BULLETIN A3514
ALERTALERT
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) Export Controlled ECCN: 9E991 - BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details.
Original Issue: July 29, 2004 A3514Revision 1 November 09, 2016 36 of 48 BOEING SERVICE BULLETIN A3514