### Commercial **Airplanes** 

# 717

Service Bulletin **ALERT Number:**  **717-55A0012** Original Issue: June 12, 2015 ATA System: 5532 **SUBJECT:** STABILIZERS - Vertical Stabilizer - Fixed Leading Edge Skin and Front Spar Cap at

Station Zfs=52.267 Inspection and Repair Export of this technology is controlled under the United States Export Administration Regulations (EAR) (15 CFR 300-774). An export license may be required before it is used for development, production or use by foreign persons from specific countries. The controller of this data has the individual responsibility to abide by all export laws. 9E991 ECCN: 

## BOEING PROPRIETARY, CONFIDENTIAL AND/OR TRADE SECRET Copyright © 2015 Boeing. Unpublished Work. All Rights Reserved. Treatment of this document and its content is governed by contract with Boeing. Rights to use this document are licensed on a per aircraft basis and such rights may not be transferable. For more information, contact The Boeing Company. Boeing, the Boeing signature, the Boeing symbol, 707, 717, 727, 737, 747, 757, 767, 777, 787, Dreamliner, BBJ, DC-8, DC-9, DC-10, KC-10, KC-46, KDC-10, MD-10, MD-11, MD-80, MD-88, MD-90, P-8, Poseidon and Boeing liveries are all trademarks owned by The Boeing Company; and no trademark license is granted in connection with this document unless provided in writing by Boeing.

Original Issue: June 12, 2015 717-55A0012 1of55 4.0Export Controlled ECCN: 9E991 - BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. Original Issue: June 12, 2015 717-55A0012 2of55 **BOEING SERVICE BULLETIN 717-55A0012 ALERT**  **ALERT**

BLANK PAGE**Table of Contents**

Summary

. . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 5 1. PLANNING INFORMATION

. . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 9 A. Effectivity

. . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 9 1. Airplanes

. . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 9 2. Spares Affected

. . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 9 B. Concurrent Requirements

. . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 9 C. Reason

. . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 10 D. Description

. . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 10 E. Compliance

. . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 10 F. Approval

. . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 15 G. Manpower

. . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 15 H. Weight and Balance Changes

. . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 16 I. Electrical Load Data

. . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 16 J. References

. . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 17 1. Existing Data:

. . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 17 2. Data Supplied with this Service Bulletin:

. . . . . . . . . . . . . . . . . . . . . . . . . . . 17 3. Installation Drawings Used in the Preparation of this Service Bulletin:

. . . . . . . . . . . 17 K. Publications Affected

. . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 17 L. Interchangeability and Intermixability of Parts

. . . . . . . . . . . . . . . . . . . . . . . . . . . 17 M. Software Accomplishment Summary

. . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 17 2. MATERIAL INFORMATION

. . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 19 A. Material - Price and Availability

. . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 19 B. Industry Support Information

. . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 19 C. Parts Necessary for Each Airplane

. . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 19 1. Kits/Parts

. . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 19 2. Parts and Materials Supplied by the Operator

. . . . . . . . . . . . . . . . . . . . . . . . 19 3. Parts Modified and Reidentified

. . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 19 4. Parts Removed and Not Replaced

. . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 19 D. Parts Necessary to Change Spares

. . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 19 E. Special Tooling - Price and Availability

. . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 19 F. Special Tooling Necessary to do this Service Bulletin

. . . . . . . . . . . . . . . . . . . . . . . 19 3. ACCOMPLISHMENT INSTRUCTIONS

. . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 21 A. GENERAL INFORMATION

. . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 21 B. WORK INSTRUCTIONS

. . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 22 FIGURE 1: LEFT SIDE VERTICAL STABILIZER LEADING EDGE STRUCTURE AT THE SPLICE AT

STATION ZFS=52.267 DETAILED INSPECTION

. . . . . . . . . . . . . . . . . . . . . . 27 FIGURE 2: LEFT SIDE VERTICAL STABILIZER FRONT SPAR CAP FORWARD FLANGE OPEN HOLE

EDDY CURRENT, HIGH FREQUENCY (ETHF) INSPECTION

. . . . . . . . . . . . . . . 29 FIGURE 3: LEFT SIDE VERTICAL STABILIZER FRONT SPAR CAP AFT FLANGES AT STATION

ZFS=52.267 RADIOGRAPHIC TESTING (RT) INSPECTION

. . . . . . . . . . . . . . . . 31 FIGURE 4: LEFT SIDE VERTICAL STABILIZER SIDE SKIN FRONT SPAR CAP AFT FLANGES EDDY

CURRENT, HIGH FREQUENCY (ETHF) INSPECTION

. . . . . . . . . . . . . . . . . . . 34 FIGURE 5: LEFT SIDE VERTICAL STABILIZER LEADING EDGE AT THE SPLICE AT STATION ZFS=52.267

(FASTENERS NOT REMOVED) DETAILED INSPECTION

. . . . . . . . . . . . . . . . . 36 FIGURE 6: RIGHT SIDE VERTICAL STABILIZER LEADING EDGE STRUCTURE AT THE SPLICE AT

STATION ZFS=52.267 DETAILED INSPECTION

. . . . . . . . . . . . . . . . . . . . . . 38

Export Controlled ECCN: 9E991 - BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. Original Issue: June 12, 2015 717-55A0012 3of55 **BOEING SERVICE BULLETIN 717-55A0012 ALERT**  **ALERT**FIGURE 7: RIGHT SIDE VERTICAL STABILIZER FRONT SPAR CAP FORWARD FLANGE OPEN HOLE EDDY CURRENT, HIGH FREQUENCY (ETHF) INSPECTION

. . . . . . . . . . . . . . . 40 FIGURE 8: RIGHT SIDE VERTICAL STABILIZER FRONT SPAR CAP AFT FLANGES AT STATION

ZFS=52.267 RADIOGRAPHIC TESTING (RT) INSPECTION

. . . . . . . . . . . . . . . . 42 FIGURE 9: RIGHT SIDE VERTICAL STABILIZER SIDE SKIN FRONT SPAR CAP AFT FLANGES EDDY

CURRENT, HIGH FREQUENCY (ETHF) INSPECTION

. . . . . . . . . . . . . . . . . . . 45 FIGURE 10: RIGHT SIDE VERTICAL STABILIZER LEADING EDGE AT THE SPLICE AT STATION

ZFS=52.267 (FASTENERS NOT REMOVED) DETAILED INSPECTION

. . . . . . . . . . 47 APPENDIX A: INITIAL DETAILED INSPECTION, EDDY CURRENT HIGH FREQUENCY (ETHF) OR

RADIOGRAPHIC TESTING (RT) INSPECTION: FIXED LEADING EDGE SKIN AND FRONT SPAR CAP AT STATION ZFS=52.267

. . . . . . . . . . . . . . . . . . . . . . . . . . . . 49 APPENDIX B: POST INITIAL DETAILED INSPECTION - FIXED LEADING EDGE SKIN AT STATION

ZFS=52.267

. . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 51 APPENDIX C: REPETITIVE EDDY CURRENT HIGH FREQUENCY (ETHF) OR RADIOGRAPHIC TESTING

(RT) INSPECTION - FRONT SPAR CAP AT STATION ZFS=52.267

. . . . . . . . . . . . 53 APPENDIX D: PREPARATION OF INSPECTION

. . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 55

Export Controlled ECCN: 9E991 - BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. Original Issue: June 12, 2015 717-55A0012 4of55 **BOEING SERVICE BULLETIN 717-55A0012 ALERT**  **ALERT**

### Commercial **Airplanes** 

# 717

Service Bulletin **ALERT Summary**  **Number: 717-55A0012**  Original Issue: June 12, 2015 ATA System: 5532 **SUBJECT:** STABILIZERS - Vertical Stabilizer - Fixed Leading Edge Skin and Front Spar Cap at

Station Zfs=52.267 Inspection and Repair THIS BULLETIN IS SENT TO THE OPERATORS OF RECORD OF THE AIRPLANES SHOWN IN PARAGRAPH 1.A., EFFECTIVITY. IF AN AIRPLANE HAS BEEN LEASED OR SOLD, SEND THIS SERVICE BULLETIN TO THE NEW OPERATOR. IF APPLICABLE SPARES HAVE BEEN SOLD, SEND THIS SERVICE BULLETIN TO THE NEW OWNER. **CONCURRENT REQUIREMENTS** None. **BACKGROUND** This service bulletin gives instructions to do inspections for distress and for any crack in the vertical stabilizer leading edge and front spar caps at the splice at station Zfs=52.267. Accomplishment of the inspections will determine the condition of the vertical stabilizer skin. Incorporation of the leading edge repair will minimize the possibility of crack growth. If not corrected, any crack in the vertical stabilizer leading edge and front spar cap may result in the structure unable to support limit load, and could adversely affect the structural integrity of the airplane. There have been ten cases reported of the 717 vertical stabilizer leading edge showing signs of fastener distress at the splice station Zfs=52.267. The affected 717s had accrued 22,594 through 40,985 flight-hours and 15,352 through 34,766 landing cycles. Similar reports have been found on MD-80 and MD-90 airplanes. One MD-90 operator reported finding elongated fastener holes at the leading edge of the vertical stabilizer at station Zfs=52.267. Two MD-80 operators reported finding a cracked vertical stabilizer skin at station Zfs=52.267, subsequent inspections revealed a severed front spar cap and a cracked front spar web. The affected MD-80 airplanes had accrued between 39,749 through 56,212 flight-hours and 32,176 through 44,001 landing cycles when the crack/ anomalies were found. The affected MD-90 airplane had accrued 15,555 flight-hours and 14,310 landing cycles. Missing fasteners, bushed or evidence of elongated fastener holes may be considered as an indication that there are undetected cracks in the underlying vertical stabilizer structure. Boeing investigation determined that high loading occurrences, such as, but not limited to, in-flight turbulence can adversely impact the fasteners and loading at the leading edge of the vertical stabilizer. This table is provided to operators for planning purposes only. Refer to the applicable sections for more information.

Export Controlled ECCN: 9E991 - BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. Original Issue: June 12, 2015 717-55A0012 5of55**Reference Affected**  **Planning Data** Paragraph 1.A.2., Spares Affected No Spares Affected Paragraph 1.E., ComplianceandParagraph 1.F., Approval Yes AD Related Paragraph 1.H., Weight and Balance Changes No Weight and Balance Change Paragraph 1.I., Electrical Load Data No Electrical Load Changed Paragraph 1.K., Publications Affected No Publications Affected Paragraph 1.K., Publications Affected No Airplane Flight Operations Affected (Flight CrewOperations Manual and/or FAA Approved Airplane Flight Manual) Paragraph 2.C.1., Kits/Parts No Kits/Parts Required Paragraph 2.C.2., Parts and Materials Supplied by the Operator No Operator Supplied Parts/Material Paragraph 2.F., Special Tooling Necessary to do this Service Bulletin No Special Tooling Required

**ACTION** Do a detailed inspection and Eddy Current High Frequency (ETHF) or Radiographic Testing (RT) inspection of the leading edge skin and front spar cap for any distress or any crack at station Zfs=52.267. If any distress in the leading edge is found, do the leading edge repair in accordance with service repair drawing SG95550001. If any crack in the vertical stabilizer front spar cap is found, contact The Boeing Company for Repair instructions and do the repair. **EFFECTIVITY** 717-200 Airplane(s). Refer to Paragraph 1.A.1., Airplanes, for the list of affected airplane(s). **COMPLIANCE** The Federal Aviation Administration (FAA) will possibly release an airworthiness directive related to this service bulletin. The airworthiness directive will make the compliance tasks and times given in this service bulletin mandatory. Refer to Paragraph 1.E., Compliance

. **INDUSTRY SUPPORT INFORMATION** Boeing warranty remedies are not available for the inspection procedures given in this service bulletin. **MANPOWER** Refer to Paragraph 1.G., Manpower

. **MATERIAL INFORMATION** None.

Export Controlled ECCN: 9E991 - BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. Original Issue: June 12, 2015 717-55A0012 6of55 **BOEING SERVICE BULLETIN 717-55A0012 ALERT**  **ALERT**Export Controlled ECCN: 9E991 - BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. Original Issue: June 12, 2015 717-55A0012 7of55 **BOEING SERVICE BULLETIN 717-55A0012 ALERT**  **ALERT**Export Controlled ECCN: 9E991 - BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. Original Issue: June 12, 2015 717-55A0012 8of55 **BOEING SERVICE BULLETIN 717-55A0012 ALERT**  **ALERT**

BLANK PAGE

### Commercial **Airplanes** 

# 717

Service Bulletin **ALERT Number:**  **717-55A0012** Original Issue: June 12, 2015 ATA System: 5532 **SUBJECT:** STABILIZERS - Vertical Stabilizer - Fixed Leading Edge Skin and Front Spar Cap at

Station Zfs=52.267 Inspection and Repair THIS BULLETIN IS SENT TO THE OPERATORS OF RECORD OF THE AIRPLANES SHOWN IN PARAGRAPH 1.A., EFFECTIVITY. IF AN AIRPLANE HAS BEEN LEASED OR SOLD, SEND THIS SERVICE BULLETIN TO THE NEW OPERATOR. IF APPLICABLE SPARES HAVE BEEN SOLD, SEND THIS SERVICE BULLETIN TO THE NEW OWNER. **1. PLANNING INFORMATION A.**  **Effectivity** 1. Airplanes

**DESCRIPTION**

**CONFIGURATION GROUP**  717-200 airplanes. Line numbers 2 - 156.

- 1
Airplane Models: 717-200 **Group Fuselage Num-**  **ber** 1 5002 - 5099 1 5100 - 5156 2. Spares Affected None. **B. Concurrent Requirements**  None.

Export Controlled ECCN: 9E991 - BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. Original Issue: June 12, 2015 717-55A0012 9of55**C. Reason** 

This service bulletin gives instructions to do inspections for distress and for any crack in the vertical stabilizer leading edge and front spar caps at the splice at station Zfs=52.267. Accomplishment of the inspections will determine the condition of the vertical stabilizer skin. Incorporation of the leading edge repair will minimize the possibility of crack growth. If not corrected, any crack in the vertical stabilizer leading edge and front spar cap may result in the structure unable to support limit load, and may lead to the loss of the vertical stabilizer. There have been ten cases reported of the 717 vertical stabilizer leading edge showing signs of fastener distress at the splice station Zfs=52.267. The affected 717s had accrued 22,594 through 40,985 flight-hours and 15,352 through 34,766 landing cycles. Similar reports have been found on MD-80 and MD-90 airplanes. One MD-90 operator reported finding elongated fastener holes at the leading edge of the vertical stabilizer at station Zfs=52.267. Two MD-80 operators reported finding a cracked vertical stabilizer skin at station Zfs=52.267, subsequent inspections revealed a severed front spar cap and a cracked front spar web. The affected MD-80 airplanes had accrued between 39,749 through 56,212 flight-hours and 32,176 through 44,001 landing cycles when the crack/ anomalies were found. The affected MD-90 airplane had accrued 15,555 flight-hours and 14,310 landing cycles. Missing fasteners, bushed or evidence of elongated fastener holes may be considered as an indication that there are undetected cracks in the underlying vertical stabilizer structure. Boeing investigation determined that high loading occurrences, such as, but not limited to, in-flight turbulence can adversely impact the fasteners and loading at the leading edge of the vertical stabilizer. **D. Description**  Do a detailed inspection and Eddy Current High Frequency (ETHF) or Radiographic Testing (RT) inspection of the leading edge skin and front spar cap for any distress or any crack at station Zfs=52.267. If any distress in the leading edge is found, do the leading edge repair in accordance with service repair drawing SG95550001. If any crack in the vertical stabilizer front spar cap is found, contact The Boeing Company for Repair instructions and do the repair. The work in this service bulletin is done in the maintenance zone(s) given below. **Affected Maintenance Zones Zone**  **Model** 371 717-200 **E. Compliance**  The Federal Aviation Administration (FAA) will possibly release an airworthiness directive related to this service bulletin. The airworthiness directive will make the compliance tasks and times given in this service bulletin mandatory. 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. Do the required actions in accordance with Paragraph 3. Accomplishment Instructions.

Export Controlled ECCN: 9E991 - BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. Original Issue: June 12, 2015 717-55A0012 10of55 **BOEING SERVICE BULLETIN 717-55A0012 ALERT**  **ALERT Table 1: Initial Detailed Inspection, Eddy Current High Frequency (ETHF) or Radiographic Testing (RT)** 

**Inspection: Fixed Leading Edge Skin and Front Spar Cap at Station Zfs=52.267 Repeat Inter** **val (Not to Ex ceed)** **Compliance Time (Whichev er Occurs Later)**  **Action Condition** 

- Within 6,200 flight cyclesafter the original issue date of this service bulletin. Before 15,000total flight cycles.Do PART 1: VERTICAL STABILIZER LEADING EDGE SKIN - DETAILED INSPECTIONS for anydistress (FASTENERS REMOVED). All Airplanes.

- Before further flight. OPTION 1: CONDITION 1: Do PART 2: VERTICAL STABILIZER SPAR CAP - EDDY CURRENT, HIGH FREQUENCY (ETHF) and RADIOGRAPHIC TESTING (RT) INSPECTION for any crack. LEADING EDGE SKIN IS NOT DISTRESSED.

- Before further flight. OPTION 2:Do PART 3: VERTICAL STABILIZER SPAR CAP - EDDY CURRENT, HIGH FREQUENCY (ETHF) INSPECTION for any crack.

- Refer to Table 2 for compli- ance information. CONDITION 1.1 (ACTION 1):Do Repetitive Detailed Inspections of the Fixed Leading Edge Skin at Station Zfs=52.267. CONDITION 1.1: NO CRACK FOUND during OPTION 1 or OPTION 2 spar cap inspection.

- Refer to Table 3 for compli- ance information. CONDITION 1.1 (ACTION 2): Do Repetitive Inspection of the Vertical Stabilizer Front Spar Cap at Station Zfs=52.267.

- Before further flight. Contact The Boeing Company forrepair instructions and do the repair. CONDITION 1.2:ANY CRACK FOUND during OPTION 1 or OPTION 2 spar cap inspection.

Export Controlled ECCN: 9E991 - BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. Original Issue: June 12, 2015 717-55A0012 11of55 **BOEING SERVICE BULLETIN 717-55A0012 ALERT**  **ALERT Table 1: Initial Detailed Inspection, Eddy Current High Frequency (ETHF) or Radiographic Testing (RT)** 

**Inspection: Fixed Leading Edge Skin and Front Spar Cap at Station Zfs=52.267 Repeat Inter** **val (Not to Ex ceed)** **Compliance Time (Whichev er Occurs Later)**  **Action Condition** 

- Before further flight. OPTION 1: CONDITION 2: Do PART 2: VERTICAL STABILIZER SPAR CAP - EDDY CURRENT, HIGH FREQUENCY (ETHF) and RADIOGRAPHIC TESTING (RT) INSPECTION for any crack. LEADING EDGE SKIN IS DISTRESSED.

- Before further flight. OPTION 2:Do PART 3: VERTICAL STABILIZER SPAR CAP - EDDY CURRENT, HIGH FREQUENCY (ETHF) INSPECTION for any crack.

- Before further flight. CONDITION 2.1 (ACTION 1): CONDITION 2.1: Do PART 5: VERTICAL STABILIZER LEADING EDGE SKIN REPAIR. NO CRACK FOUND during OPTION 1 or OPTION 2 spar cap inspection.

- Refer to Table 2 for compli- ance information. CONDITION 2.1 (ACTION 2):Do Repetitive Detailed Inspections of the Fixed Leading Edge Skin at Station Zfs=52.267.

- Refer to Table 3 for compli- ance information. CONDITION 2.1 (ACTION 3): Do Repetitive Inspection of the Vertical Stabilizer Front Spar Cap at Station Zfs=52.267.

- Before further flight. CONDITION 2.2 (ACTION 1): CONDITION 2.2: Do PART 5: VERTICAL STABILIZER LEADING EDGE SKIN REPAIR.ANY CRACK FOUND during OPTION 1 or OPTION 2 spar cap inspection.

- Before further flight. CONDITION 2.2 (ACTION 2): Contact The Boeing Company forrepair instructions and do the repair.

Export Controlled ECCN: 9E991 - BOEING

PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. Original Issue: June 12, 2015 717-55A0012 12of55 **BOEING SERVICE BULLETIN 717-55A0012 ALERT**  **ALERT Table 2: Post Initial Detailed Inspection - Repetitive Detailed Inspections of the Fixed Leading Edge Skin** 

**at Station Zfs=52.267 Repeat Interval**  **(Not to Exceed) Compliance Time**  **Action Condition** 

- Within 4,400 flight cycles after the initial inspection.Do PART 4: VERTICAL STABILIZER LEADING EDGE SKIN - DETAILED INSPECTIONS (FASTENERS NOT REMOVED) for any loose and missing fasteners. ALL AIRPLANES WHICH COMPLETED OPTION 1 AND NO CRACK WAS FOUND.

- Within 3,000 flight cycles after the initial inspection.Do PART 4: VERTICAL STABILIZER LEADING EDGE SKIN - DETAILED INSPECTIONS (FASTENERS NOT REMOVED) for any loose and missing fasteners. ALL AIRPLANES WHICH COMPLETED OPTION 2 AND NO CRACK WAS FOUND.
4,400 flight cycles (a) - Repeat PART 4: VERTICAL STABI- LIZER LEADING EDGE SKIN -DETAILED INSPECTIONS (FASTENERS NOT REMOVED) for any loose and missing fasteners. CONDITION 3: NO LOOSE AND NO MISSING FASTENERS ON AIRPLANES WHICH COMPLETED OPTION 1 INSPECTIONS. 3,000 flight cycles (a) - Repeat PART 4 VERTICAL STABI- LIZER LEADING EDGE SKIN -DETAILED INSPECTIONS (FASTENERS NOT REMOVED) for any loose and missing fasteners. CONDITION 4: NO LOOSE AND NO MISSING FASTENERS ON AIRPLANES WHICH COMPLETED OPTION 2 INSPECTIONS.

- Before further flight. CONDITION 5 (ACTION 1): CONDITION 5: Do PART 5: VERTICAL STABILIZER LEADING EDGE SKIN REPAIR. ANY LOOSE OR MISSING FASTENERS ON AIRPLANES WHICH COMPLETED OPTION 1 INSPECTIONS. 4,400 flight cycles (a) - CONDITION 5 (ACTION 2):Repeat PART 4: VERTICAL STABILIZER LEADING EDGE SKIN -DETAILED INSPECTIONS (FASTENERS NOT REMOVED) for any loose and missing fasteners.

- Before further flight. CONDITION 6 (ACTION 1): CONDITION 6: Do PART 5: VERTICAL STABILIZER LEADING EDGE REPAIR. ANY LOOSE OR MISSING FASTENERS ON AIRPLANES WHICH COMPLETED OPTION 2 INSPECTIONS. 3,000 flight cycles (a) - CONDITION 6 (ACTION 2):Repeat PART 4: VERTICAL STABILIZER LEADING EDGE SKIN -DETAILED INSPECTIONS (FASTENERS NOT REMOVED) for any loose and missing fasteners. (a) Changing from one inspection option to another option is acceptable, provided the repeat interval requirement is first complied with, before changing options.

Export Controlled ECCN: 9E991 - BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. Original Issue: June 12, 2015 717-55A0012 13of55 **BOEING SERVICE BULLETIN 717-55A0012 ALERT**  **ALERT Table 3: Repetitive Eddy Current High Frequency (ETHF) or Radiographic Testing (RT) Inspection: Front** 

**Spar Cap at Station Zfs=52.267 Repeat Interval**  **(Not to Exceed) Compliance Time**  **Action Condition** 

- Within 4,400 flight cycles after the initial inspection. OPTION 1:Do PART 2: VERTICAL STABILIZER SPAR CAP - EDDY CURRENT, HIGH FREQUENCY (ETHF) and RADIOGRAPHIC TESTING (RT) INSPECTION for any crack. ALL AIRPLANES WHICH COMPLETED OPTION 1 AND NO CRACK WAS FOUND.

OPTION 2:Do PART 3: VERTICAL STABILIZER SPAR CAP - EDDY CURRENT,HIGH FREQUENCY (ETHF) INSPECTION for any crack.

- Within 3,000 flightcycles after initial inspections. OPTION 1:Do PART 2: VERTICAL STABILIZER SPAR CAP - EDDY CURRENT, HIGH FREQUENCY (ETHF) and RADIOGRAPHIC TESTING (RT) INSPECTION for any crack. ALL AIRPLANES WHICH COMPLETED OPTION 2 AND NO CRACK WAS FOUND.

OPTION 2:Do PART 3: VERTICAL STABILIZER SPAR CAP - EDDY CURRENT,HIGH FREQUENCY (ETHF) INSPECTION for any crack. 4,400 flight cycles (a) - OPTION 1:Do PART 2: VERTICAL STABILIZER SPAR CAP - EDDY CURRENT, HIGH FREQUENCY (ETHF) and RADIOGRAPHIC TESTING (RT) INSPECTION for any crack. CONDITION 7:NO CRACK FOUND ON AIRPLANES WHICH COMPLETED OPTION 1 INSPECTION.

OPTION 2:Do PART 3: VERTICAL STABILIZER SPAR CAP - EDDY CURRENT,HIGH FREQUENCY(ETHF) INSPECTION for any crack.

Export Controlled ECCN: 9E991 - BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. Original Issue: June 12, 2015 717-55A0012 14of55 **BOEING SERVICE BULLETIN 717-55A0012 ALERT**  **ALERT Table 3: Repetitive Eddy Current High Frequency (ETHF) or Radiographic Testing (RT) Inspection: Front** 

**Spar Cap at Station Zfs=52.267 Repeat Interval**  **(Not to Exceed) Compliance Time**  **Action Condition**  3,000 flight cycles (a) - OPTION 1:Do PART 2: VERTICAL STABILIZER SPAR CAP - EDDY CURRENT, HIGH FREQUENCY (ETHF) and RADIOGRAPHIC TESTING (RT) INSPECTION for any crack. CONDITION 8:NO CRACK FOUND ON AIRPLANES WHICH COMPLETED OPTION 2 INSPECTION.

OPTION 2:Do PART 3: VERTICAL STABILIZER SPAR CAP - EDDY CURRENT,HIGH FREQUENCY(ETHF) INSPECTION for any crack.

- Before further flight. Contact The Boeing Company forrepair instructions and do the repair. CONDITION 9:ANY CRACK FOUND ON AIRPLANES WHICH COMPLETEOPTION 1 AND OPTION 2 INSPECTION. (a) Changing from one inspection option to another option is acceptable, provided the repeat interval requirement is first complied with, before changing options. **F. Approval**  This service bulletin was examined by the Federal Aviation Administration (FAA). The changes specified in this service bulletin comply with the applicable regulations and are FAA approved, as well as European Aviation Safety Agency (EASA)/Joint Aviation Authorities (JAA) approved for all EASA/JAA approved airplanes listed in the service bulletin effectivity. This service bulletin and its approval were based on the airplane in its original Boeing delivery configuration or as modified by other approved Boeing changes. If an airplane has a non-Boeing modification or repair that affects a component or system also affected by this service bulletin, the operator is responsible for obtaining appropriate regulatory agency approval before incorporating this service bulletin. **G. Manpower**  The table below shows an estimate of the task hours necessary to do these inspections for each airplane. This estimate is for direct labor only, done by an experienced crew. Adjust the estimate with operator task hour data if necessary. The estimate does not include lost time. These are some examples of lost time:

• Time to adjust to the workplace
• Time to schedule the work
• Time to inspect the work
• Time to cure the materials
• Time to make the parts
• Time to find the tools.

Export Controlled ECCN: 9E991 - BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. Original Issue: June 12, 2015 717-55A0012 15of55 **BOEING SERVICE BULLETIN 717-55A0012 ALERT**  **ALERT Table 1: Initial Detailed Inspection, Eddy Current High Frequency (ETHF) or Radiographic Testing (RT)** 

**Inspection: Fixed Leading Edge Skin and Front Spar Cap at Station Zfs=52.267 Elapsed Hours**  **Task Hours Number of Persons**  **Task** 2.5 2.5 1 FIGURE 1 2.0 2.0 1 FIGURE 2 1.0 1.0 1 FIGURE 3or FIGURE 4 2.5 2.5 1 FIGURE 6 2.0 2.0 1 FIGURE 7 1.0 1.0 1 FIGURE 8or FIGURE 9 11.0 11.0 TOTAL FOR EACH AIRPLANE(a) (b) (a) Inspection hours given are for each airplane. (b) Task hours required for repairs are not included and are to be determined by the operator based on inspection results. **Table 2: Post Initial Detailed Inspection, Repetitive Eddy Current High Frequency (ETHF) or Radiographic Testing (RT) Inspection: Fixed Leading Edge Skin and Front Spar Cap at Station Zfs=52.267**  **Elapsed Hours Task Hours**  **Number of Persons Task**  2.0 2.0 1 FIGURE 2 1.0 1.0 1 FIGURE 3or FIGURE 4 0.5 0.5 1 FIGURE 5 2.0 2.0 1 FIGURE 7 1.0 1.0 1 FIGURE 8or FIGURE 9 0.5 0.5 1 FIGURE 10 7.0 7.0 TOTAL FOR EACH AIRPLANE(a) (b) (a) Inspection hours given are for each airplane. (b) Task hours required for repairs are not included and are to be determined by the operator based on inspection results. **H. Weight and Balance Changes**  Weight and balance changes affected by incorporation of this drawing are contingent upon the modification of each particular aircraft. Weight data is to be computed by the operator by weighing parts installed or removed. Necessary revisions should be made to the appropriate weight and balance report. **I. Electrical Load Data**  Not changed.

Export Controlled ECCN: 9E991 - BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. Original Issue: June 12, 2015 717-55A0012 16of55 **BOEING SERVICE BULLETIN 717-55A0012 ALERT**  **ALERT J.**  **References** 1. Existing Data:
a. Non-Destructive Test Standard Practices Manual (NDTSPM)02-00-07,06-10-01.001, 06-10-01.003, Part 01-00-03, Part 02-00-03, Part 02-00-04, Part 06-00-03,Part 06-00-04 b. 717 Structural Repair Manual (SRM)51-40-08,51-41-01
c. Service Repair Drawing SG95550001 2. Data Supplied with this Service Bulletin:
a. Drawings: **ADCN DCN/REV**  **Sheet Title**  **Drawing No**

- Y 1 L.E. Instl. - Vert Stab 5930609

- - 1 FIXED LEADING EDGE SKIN REPAIR - VERTICAL STABILIZER, ZFS=52.267 SG95550001

- - 2 3. Installation Drawings Used in the Preparation of this Service Bulletin: None. **K. Publications Affected**  1. Publications: None. 2. Damage Tolerance Based Structural Inspections: Boeing has evaluated the repairs and/or changes in this service bulletin for effects on Fatigue Critical Structure (FCS) and for changes to Damage Tolerance Inspections (DTI) required in the Maintenance Program. This service bulletin affects FCS. DTI requirements for the structure affected are contained in Paragraph 1.E., Compliance of this service bulletin. **L. Interchangeability and Intermixability of Parts**  Accomplishment of this service bulletin does not affect interchangeability or intermixability of parts. **M. Software Accomplishment Summary**  Not affected.

Export Controlled ECCN: 9E991 - BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. Original Issue: June 12, 2015 717-55A0012 17of55 **BOEING SERVICE BULLETIN 717-55A0012 ALERT**  **ALERT**Export Controlled ECCN: 9E991 - BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. Original Issue: June 12, 2015 717-55A0012 18of55 **BOEING SERVICE BULLETIN 717-55A0012 ALERT**  **ALERT**

BLANK PAGE**2. MATERIAL INFORMATION A.**  **Material - Price and Availability** None. **B. Industry Support Information**  Boeing warranty remedies are not available for the inspection procedures given in this service bulletin. **C. Parts Necessary for Each Airplane**  1. Kits/Parts Based on inspection results, refer to Service General Repair Drawing SG95550001 for repair parts necessary for each airplane. 2. Parts and Materials Supplied by the Operator Based on inspection results, refer to Service General Repair Drawing SG95550001 for operator supplied parts and materials necessary to do the required repairs. 3. Parts Modified and Reidentified None. 4. Parts Removed and Not Replaced None. **D. Parts Necessary to Change Spares**  None. **E. Special Tooling - Price and Availability**  Inspection equipment required to accomplish this service bulletin are listed inAPPENDIX Dand in the NDTSPM and are to be procured from operator's stock or sources indicated. **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.

Export Controlled ECCN: 9E991 - BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. Original Issue: June 12, 2015 717-55A0012 19of55 **BOEING SERVICE BULLETIN 717-55A0012 ALERT**  **ALERT**Export Controlled ECCN: 9E991 - BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. Original Issue: June 12, 2015 717-55A0012 20of55 **BOEING SERVICE BULLETIN 717-55A0012 ALERT**  **ALERT**

BLANK PAGE**3. ACCOMPLISHMENT INSTRUCTIONS A.**  **GENERAL INFORMATION WARNING:**  IF ELECTRICAL POWER IS APPLIED TO THE AIRPLANE, MAKE SURE YOU OBEY

ALL PRECAUTIONS WHILE YOU DO WORK. IF YOU DO NOT OBEY THE PRECAUTIONS, DEATH OR INJURY TO PERSONS, AND DAMAGE TO THE AIRPLANE CAN OCCUR. **CAUTION:** ELECTRICALLY GROUND THE AIRPLANE. THIS WILL HELP TO PREVENT DAMAGE

TO THE AIRPLANE OR EQUIPMENT. **CAUTION:** KEEP THE WORK AREA, WIRES AND ELECTRICAL BUNDLES CLEAN OF METAL

PARTICLES OR CONTAMINATION WHEN YOU USE TOOLS. UNWANTED MATERIAL, METAL PARTICLES OR CONTAMINATION CAUGHT IN WIRE BUNDLES CAN CAUSE DAMAGE TO THE BUNDLES. DAMAGED WIRE BUNDLES CAN CAUSE SPARKS OR OTHER ELECTRICAL DAMAGE. **NOTE:** 1. Manual titles are referred to by acronyms. Refer to Paragraph 1.J., References, for

definition of the acronyms. 2. Equivalent parts are listed in the AEPL, Drawing7595071

. 3. Use the approved fastener and process material substitutions, in accordance with

717 SRM 51-41-01

. 4. 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 are in717 SRM 51-40-08

– Torque Values:

— Values for structural fasteners are given in 717 Structural Repair Manual, Chapter 51.

— Values for airframe maintenance tasks are included in Chapter 20 of 717 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 717 Aircraft Maintenance Manual (AMM).

— Non-standard torque values for maintenance tasks are included in the applicable installation step.

5. Obey all of the warnings and cautions given in the specified manual sections. 6. Refer toAPPENDIX Dfor preparation of inspection.

Export Controlled ECCN: 9E991 - BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. Original Issue: June 12, 2015 717-55A0012 21of55 **BOEING SERVICE BULLETIN 717-55A0012 ALERT**  **ALERT**7. Refer toAPPENDIX Afor logic diagram(s). Logic diagrams are provided as an aid only. Information contained in Paragraph 1.E., Compliance is the primary source for compliance times. Information contained in Paragraph 3.B., Work Instructions is the primary source for tasks required for compliance. 8. 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. 9. 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. 10. 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. 11. 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. 12. If shading is used, shaded areas in Figures are reference only. Shaded areas in Figures may look different than your airplane. 13. Use of colors in Figures is based on guidance from the ATA e-Business Program (ATA) iSpec 2200. 14. 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. 15. The compliance times for the actions in Paragraph 3.B., WORK INSTRUCTIONS are in Paragraph 1.E., Compliance

. 16. Some steps in the Work Instructions are labeled as Required for Compliance (RC). If this service bulletin is mandated by an Airworthiness Directive (AD), then the steps labeled as RC, including sub-steps under an RC step and any figures identified in an RC step, must be done to comply with the AD. An Alternative Method of Compliance (AMOC) is required for any deviations to RC steps, including sub-steps and identified figures. Steps not labeled as RC may be deviated from using accepted methods in accordance with the operator's maintenance or inspection program without obtaining approval of an AMOC. This is provided that the RC steps, including sub-steps and identified figures, can still be done as specified, and the airplane can be put back in an airworthy condition. **B. WORK INSTRUCTIONS** 

Export Controlled ECCN: 9E991 - BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. Original Issue: June 12, 2015 717-55A0012 22of55 **BOEING SERVICE BULLETIN 717-55A0012 ALERT**  **ALERT**1. RC - Do PART 1: VERTICAL STABILIZER LEADING EDGE SKIN - DETAILED INSPECTIONS for any distress (FASTENERS REMOVED).
a. CONDITION 1: LEADING EDGE SKIN IS NOT DISTRESSED. (1) OPTION 1: Do PART 2: VERTICAL STABILIZER SPAR CAP - EDDY CURRENT, HIGH FREQUENCY (ETHF) and RADIOGRAPHIC TESTING (RT) INSPECTION for any crack. (a) CONDITION 1.1: NO CRACK FOUND. 1) Put airplane back to a serviceable condition. 2) CONDITION 1.1 (ACTION 1): Do Repetitive Detailed Inspections of the Fixed Leading Edge Skin at Station Zfs=52.267. 3) CONDITION 1.1 (ACTION 2): Do Repetitive Inspection of the Vertical Stabilizer Front Spar Cap at Station Zfs=52.267. (b) CONDITION 1.2: ANY CRACK FOUND. 1) Contact The Boeing Company for repair instructions and do the repair. (2) OPTION 2: Do PART 3: VERTICAL STABILIZER SPAR CAP - EDDY CURRENT, HIGH FREQUENCY (ETHF) INSPECTION for any crack. (a) CONDITION 1.1: NO CRACK FOUND. 1) Put airplane back to a serviceable condition. 2) CONDITION 1.1 (ACTION 1): Do Repetitive Detailed Inspections of the Fixed Leading Edge Skin at Station Zfs=52.267. 3) CONDITION 1.1 (ACTION 2): Do Repetitive Inspection of the Vertical Stabilizer Front Spar Cap at Station Zfs=52.267. (b) CONDITION 1.2: ANY CRACK FOUND. 1) Contact The Boeing Company for repair instructions and do the repair. b. CONDITION 2: LEADING EDGE SKIN IS DISTRESSED. (1) OPTION 1: Do PART 2: VERTICAL STABILIZER SPAR CAP - EDDY CURRENT, HIGH FREQUENCY (ETHF) and RADIOGRAPHIC TESTING (RT) INSPECTION for any crack. (a) CONDITION 2.1: NO CRACK FOUND. 1) CONDITION 2.1 (ACTION 1): Do PART 5: VERTICAL STABILIZER LEADING EDGE SKIN REPAIR. 2) CONDITION 2.1 (ACTION 2): Do Repetitive Detailed Inspections of the Fixed Leading Edge Skin at Station Zfs=52.267.

Export Controlled ECCN: 9E991 - BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. Original Issue: June 12, 2015 717-55A0012 23of55 **BOEING SERVICE BULLETIN 717-55A0012 ALERT**  **ALERT**3) CONDITION 2.1 (ACTION 3): Do Repetitive Inspection of the Vertical Stabilizer Front Spar Cap at Station Zfs=52.267. (b) CONDITION 2.2: ANY CRACK FOUND. 1) CONDITION 2.2 (ACTION 1): Do PART 5: VERTICAL STABILIZER LEADING EDGE SKIN REPAIR. 2) CONDITION 2.2 (ACTION 2): Contact Boeing to get instructions for the repair for this service bulletin, and do the work instructed by Boeing. (2) OPTION 2: Do PART 3: VERTICAL STABILIZER SPAR CAP - EDDY CURRENT, HIGH FREQUENCY (ETHF) INSPECTION for any crack. (a) CONDITION 2.1: NO CRACK FOUND. 1) CONDITION 2.1 (ACTION 1): Do PART 5: VERTICAL STABILIZER LEADING EDGE SKIN REPAIR. 2) CONDITION 2.1 (ACTION 2): Do Repetitive Detailed Inspections of the Fixed Leading Edge Skin at Station Zfs=52.267. 3) CONDITION 2.1 (ACTION 3): Do Repetitive Inspection of the Vertical Stabilizer Front Spar Cap at Station Zfs=52.267. (b) CONDITION 2.2: ANY CRACK FOUND. 1) CONDITION 2.2 (ACTION 1): Do PART 5: VERTICAL STABILIZER LEADING EDGE SKIN REPAIR. 2) CONDITION 2.2 (ACTION 2): Contact The Boeing Company for repair instructions and do the repair. 2. Put the airplane back to a serviceable condition. 3. Repetitive Detailed Inspections of the Fixed Leading Edge Skin at Station Zfs=52.267:
a. RC - Do PART 4: VERTICAL STABILIZER SPAR CAP - DETAILED INSPECTION (FASTENERS NOT REMOVED) for any loose fasteners and missing fasteners. (1) CONDITION 3 or CONDITION 4: NO LOOSE AND NO MISSING FASTENERS ON AIRPLANES WHICH COMPLETED OPTION 1 OR OPTION 2 INSPECTION. (a) Put airplane back to a serviceable condition. (b) REPEAT PART 4: VERTICAL STABILIZER LEADING EDGE SKIN - DETAILED INSPECTION (FASTENERS NOT REMOVED) for any loose fasteners and missing fasteners. (2) CONDITION 5 or CONDITION 6: ANY LOOSE OR MISSING FASTENERS FOUND ON AIRPLANES WHICH COMPLETED OPTION 1 OR OPTION 2 INSPECTION.

Export Controlled ECCN: 9E991 - BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. Original Issue: June 12, 2015 717-55A0012 24of55 **BOEING SERVICE BULLETIN 717-55A0012 ALERT**  **ALERT**(a) CONDITION 5 or CONDITION 6 (ACTION 1): Do PART 5: VERTICAL STABILIZER LEADING EDGE SKIN REPAIR. (b) CONDITION 5 or CONDITION 6 (ACTION 2): REPEAT PART 4: VERTICAL STABILIZER LEADING EDGE SKIN - DETAILED INSPECTION (FASTENERS NOT REMOVED) for any loose fasteners and missing fasteners. 4. Repetitive Inspection of the Vertical Stabilizer Front Spar Cap at Station Zfs=52.267
a. RC - OPTION 1: Do PART 2: VERTICAL STABILIZER SPAR CAP - EDDY CURRENT, HIGH FREQUENCY (ETHF) and RADIOGRAPHIC TESTING (RT) INSPECTION for any crack. (1) CONDITION 7: NO CRACK FOUND ON AIRPLANES WHICH COMPLETED OPTION 1 INSPECTION. (a) Put airplane back to a serviceable condition. (b) Repeat OPTION 1 or Do OPTION 2 inspection for any crack: (2) CONDITION 9: ANY CRACK FOUND ON AIRPLANES WHICH COMPLETE OPTION 1 OR OPTION 2 INSPECTION. (a) Contact Boeing to get instructions for the repair for this service bulletin, and do the work instructed by Boeing. b. RC - OPTION 2: Do PART 3: VERTICAL STABILIZER SPAR CAP- EDDY CURRENT, HIGH FREQUENCY (ETHF) INSPECTION for any crack. (1) CONDITION 8: NO CRACK FOUND ON AIRPLANES WHICH COMPLETED OPTION 2 INSPECTION. (a) Put airplane back to a serviceable condition. (b) Do OPTION 1 or Repeat OPTION 2 inspection for any crack. (2) CONDITION 9: ANY CRACK FOUND ON AIRPLANES WHICH COMPLETED OPTION 1 OR OPTION 2 INSPECTION. (a) Contact The Boeing Company for repair instructions and do the repair. 5. Put airplane back to a serviceable condition. **PART 1: VERTICAL STABILIZER LEADING EDGE SKIN –** **DETAILED INSPECTIONS for any distress (FASTENERS REMOVED)**  1. Do a detailed inspection of the left and right side vertical stabilizer leading edge structure at the splice at Station Zfs=52.267 in accordance with FIGURE 1andFIGURE 6

.

Export Controlled ECCN: 9E991 - BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. Original Issue: June 12, 2015 717-55A0012 25of55 **BOEING SERVICE BULLETIN 717-55A0012 ALERT**  **ALERT PART 2: VERTICAL STABILIZER SPAR CAP** **– EDDY CURRENT, HIGH FREQUENCY (ETHF) and** 

**RADIOGRAPHIC TESTING (RT) INSPECTION for any crack** 1. Do an open hole Eddy Current, High Frequency (ETHF) inspection of the left and right side vertical stabilizer front spar cap forward flanges for any crack in accordance withFIGURE 2andFIGURE 7

. 2. Do a Radiographic Testing (RT) inspection of the left and right side vertical stabilizer front spar cap aft flanges at Station Zfs=52.267 for any crack in accordance withFIGURE 3andFIGURE 8

. **PART 3: VERTICAL STABILIZER SPAR CAP –** **EDDY CURRENT, HIGH FREQUENCY (ETHF) INSPECTION for any crack**  1. Do an open hole ETHF inspection of the left and right side vertical stabilizer front spar cap forward flanges for any crack in accordance with FIGURE 2andFIGURE 7

. 2. Do an ETHF surface inspection of the side skin at the left and right side vertical stabilizer front spar cap aft flanges within the specified dimensions in accordance with FIGURE 4and FIGURE 9

. **PART 4: VERTICAL STABILIZER LEADING EDGE SKIN - DETAILED INSPECTION (FASTENERS NOT REMOVED) for any loose and missing fasteners**  1. Do a detailed inspection of the vertical stabilizer leading edge at the splice at Station Zfs=52.267 (fasteners not removed) for any loose or missing fasteners in accordance with FIGURE 5and FIGURE 10

. **NOTE:** The inspection area is two rows of fasteners above the splice and two rows of fasteners below the splice at Station Zfs=52.267. **PART 5: VERTICAL STABILIZER - LEADING EDGE SKIN REPAIR** 1. Do leading edge repair in accordance with Service Repair Drawing SG95550001. **NOTE:** As an option to the repair, replace 9911813-503 vertical stabilizer leading edge splice band with new 9911813-503 vertical stabilizer leading edge splice band in accordance with drawing 5930609.

Export Controlled ECCN: 9E991 - BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. Original Issue: June 12, 2015 717-55A0012 26of55 **BOEING SERVICE BULLETIN 717-55A0012 ALERT**  **ALERT FIGURE 1:** **LEFT SIDE VERTICAL STABILIZER LEADING EDGE STRUCTURE AT THE SPLICE AT STATION ZFS=52.267 DETAILED INSPECTION** 

**(SHEET 1 OF 2)** Export Controlled ECCN: 9E991 - BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. Original Issue: June 12, 2015 717-55A0012 27of55 **BOEING SERVICE BULLETIN 717-55A0012 ALERT**  **ALERT**The step numbers shown below agree with the numbers shown in the circle symbols in the figure. **More Data QTY**  **Identification Name**  **Task Step**  (a) (b)
- - Skin Inspect 1 (b) (c) (d) 3
- Fasteners Remove/keep 2

- Holes Inspect 3

Fasteners Install/kept (b) (c) (d) 4
- Fasteners Remove/keep 3

- Holes Inspect 4

Fasteners Install/kept (b) (c) (d) 4
- Fasteners Remove/keep 4

- Holes Inspect 4

Fasteners Install/kept (b) (c) (d) 3
- Fasteners Remove/keep 5

- Holes Inspect 3

Fasteners Install/kept (a) Do a detailed inspection for any "distress" in the vertical stabilizer leading edge structure at the splice at Station Zfs=52.267. (b) "Distress" is defined as deformed holes, elongated holes, oversized holes or any crack in the leading edge skin and splice. (c) Remove and keep one row of fasteners. To prevent damage to the tail plane, only remove one row of fasteners at a time. (d) Do a detailed inspection for distress in each fastener hole location.

**FIGURE 1: LEFT SIDE VERTICAL STABILIZER LEADING EDGE STRUCTURE AT THE SPLICE AT STATION**  **ZFS=52.267 DETAILED INSPECTION**

**(SHEET 2 OF 2)** Export Controlled ECCN: 9E991 - BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. Original Issue: June 12, 2015 717-55A0012 28of55 **BOEING SERVICE BULLETIN 717-55A0012 ALERT**  **ALERT FIGURE 2:** **LEFT SIDE VERTICAL STABILIZER FRONT SPAR CAP FORWARD FLANGE OPEN HOLE EDDY CURRENT, HIGH FREQUENCY (ETHF) INSPECTION** 

**(SHEET 1 OF 2)** Export Controlled ECCN: 9E991 - BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. Original Issue: June 12, 2015 717-55A0012 29of55 **BOEING SERVICE BULLETIN 717-55A0012 ALERT**  **ALERT**The step numbers shown below agree with the numbers shown in the circle symbols in the figure. **More Data QTY**  **Identification Name**  **Task Step**  (a) (b) (c)
- - Fasteners Remove/keep 1 Hole

Inspect Fasteners Install/kept (a) Remove and keep fasteners common to the left side leading edge panel, the dorsal fin lower assembly and vertical stabilizer front spar cap forward flanges, above and below the leading edge skin splice at Station Zfs=52.267. (b) Do an open hole ETHF inspection of the left side vertical stabilizer front spar cap forward flanges at the fastener holes above and below the leading edge skin splice at Station Zfs=52.267 within the specified dimensions. Scan the circumference of the holes in accordance with the Non-destructive Testing Standard Practice ManualNDTSPM 06-10-01.003(ETHF - Procedure 3). (c) Scoring of the fastener hole bore caused by the removal of fasteners may cause crack-like indications. Removal of nut plate may be necessary for proper clean up of the hole. Refer toNDTSPM 06-10-01.003 "Access" and "Preparation and Cleaning" for more information. The nut plate may also interfere with the probe scan with some open hole eddy current probe designs.

**FIGURE 2: LEFT SIDE VERTICAL STABILIZER FRONT SPAR CAP FORWARD FLANGE OPEN HOLE** 

**EDDY CURRENT, HIGH FREQUENCY (ETHF) INSPECTION**

**(SHEET 2 OF 2)** Export Controlled ECCN: 9E991 - BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. Original Issue: June 12, 2015 717-55A0012 30of55 **BOEING SERVICE BULLETIN 717-55A0012 ALERT**  **ALERT FIGURE 3:** **LEFT SIDE VERTICAL STABILIZER FRONT SPAR CAP AFT FLANGES AT STATION ZFS=52.267 RADIOGRAPHIC TESTING (RT) INSPECTION** 

**(SHEET 1 OF 3)** Export Controlled ECCN: 9E991 - BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. Original Issue: June 12, 2015 717-55A0012 31of55 **BOEING SERVICE BULLETIN 717-55A0012 ALERT**  **ALERT**The step numbers shown below agree with the numbers shown in the circle symbols in the figure. **More Data QTY**  **Identification Name**  **Task Step**  (a) (b) (c) (d) (e) (f) (g) - - Skin Inspect 1 (a) Do a Radiographic Testing (RT) surface inspection of the vertical stabilizer front spar cap aft flange at station Zfs=52.267 for any crack. (b) Prepare exposure radiographic identification tag with the data as follows, using operator's shop practice:

– Service Bulletin number

– Exposure number and left side

– Aircraft I.D.

– Date (c) Attach the identification tag of each of the 5 exposures to the respective film pack using operator's shop practice. (d) Use masking tape to attach film to inspection element for the 5 exposures. (e) Expose film in accordance with x-ray parameters in exposure table below. (f) Any indication is considered a crack which exhibits the same relative phase angle and an amplitude of 50 percent or greater than the indication obtained from the calibration notch in the reference standard.

**FIGURE 3: LEFT SIDE VERTICAL STABILIZER FRONT SPAR CAP AFT FLANGES AT STATION ZFS=52.267**  **RADIOGRAPHIC TESTING (RT) INSPECTION**

**(SHEET 2 OF 3)** Export Controlled ECCN: 9E991 - BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. Original Issue: June 12, 2015 717-55A0012 32of55 **BOEING SERVICE BULLETIN 717-55A0012 ALERT**  **ALERT More Data**  **QTY Identification**  **Name Task**  **Step** (g) Any crack indications found during RT inspection shall be verified. Refer toNDTSPM 02-00-07for applicable Crack/Defect Evaluation/Verification section(s). **Exposure Table REMARKS**  **FILM DIM "A"**  **mas (a)**  **kV EXPOSURE**  **NUMBER SIZE (Inch)**  **QTY ASTM**  **TYPE** 5 X 7

2 1(b) 36+/-0.5 600 80 1 5 X 7 2 1 and 2(c) 36+/-0.5 600 80 2 5 X 7 2 1 and 2(c) 36+/-0.5 600 80 3 5 X 7 2 1(b) 36+/-0.5 600 80 4 5 X 7 2 1(b) 36+/-0.5 600 80 5 (a) Adjust mas to get a 1.7 to 3.5 H & D density in the area of interest. (b) Kodak M or equivalent type with similar speed. (c) Kodak M and AA or equivalent type with similar speed (double load film pack).

**FIGURE 3: LEFT SIDE VERTICAL STABILIZER FRONT SPAR CAP AFT FLANGES AT STATION ZFS=52.267**  **RADIOGRAPHIC TESTING (RT) INSPECTION**

**(SHEET 3 OF 3)** Export Controlled ECCN: 9E991 - BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. Original Issue: June 12, 2015 717-55A0012 33of55 **BOEING SERVICE BULLETIN 717-55A0012 ALERT**  **ALERT FIGURE 4:** **LEFT SIDE VERTICAL STABILIZER SIDE SKIN FRONT SPAR CAP AFT FLANGES EDDY CURRENT, HIGH FREQUENCY (ETHF) INSPECTION** 

**(SHEET 1 OF 2)** Export Controlled ECCN: 9E991 - BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. Original Issue: June 12, 2015 717-55A0012 34of55 **BOEING SERVICE BULLETIN 717-55A0012 ALERT**  **ALERT**The step numbers shown below agree with the numbers shown in the circle symbols in the figure. **More Data QTY**  **Identification Name**  **Task Step**  (a)
- - Skin Inspect 1 (a) Do an ETHF surface inspection of the side skin at the left side vertical stabilizer front spar cap aft flanges within the specified dimensions. Scan around the fasteners for any crack in the forward and aft direction. Scan around the fasteners in accordance with the Non-destructive Testing Standard Practice Manual NDTSPM 06-10-01.001(ETHF - Procedure 1). Use Calibration Method "P" and Scan Method "47".

**FIGURE 4: LEFT SIDE VERTICAL STABILIZER SIDE SKIN FRONT SPAR CAP AFT FLANGES EDDY**  **CURRENT, HIGH FREQUENCY (ETHF) INSPECTION**

**(SHEET 2 OF 2)** Export Controlled ECCN: 9E991 - BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. Original Issue: June 12, 2015 717-55A0012 35of55 **BOEING SERVICE BULLETIN 717-55A0012 ALERT**  **ALERT FIGURE 5:** **LEFT SIDE VERTICAL STABILIZER LEADING EDGE AT THE SPLICE AT STATION ZFS=52.267 (FASTENERS NOT REMOVED) DETAILED INSPECTION** 

**(SHEET 1 OF 2)** Export Controlled ECCN: 9E991 - BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. Original Issue: June 12, 2015 717-55A0012 36of55 **BOEING SERVICE BULLETIN 717-55A0012 ALERT**  **ALERT**The step numbers shown below agree with the numbers shown in the circle symbols in the figure. **More Data QTY**  **Identification Name**  **Task Step**  (a)
- - Skin Inspect 1 (a) Do a detailed inspection of the vertical stabilizer leading edge at the splice at Station Zfs=52.267 (fasteners not removed) for any loose or missing fasteners.

**FIGURE 5: LEFT SIDE VERTICAL STABILIZER LEADING EDGE AT THE SPLICE AT STATION ZFS=52.267**  **(FASTENERS NOT REMOVED) DETAILED INSPECTION**

**(SHEET 2 OF 2)** Export Controlled ECCN: 9E991 - BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. Original Issue: June 12, 2015 717-55A0012 37of55 **BOEING SERVICE BULLETIN 717-55A0012 ALERT**  **ALERT FIGURE 6:** **RIGHT SIDE VERTICAL STABILIZER LEADING EDGE STRUCTURE AT THE SPLICE AT STATION ZFS=52.267 DETAILED INSPECTION** 

**(SHEET 1 OF 2)** Export Controlled ECCN: 9E991 - BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. Original Issue: June 12, 2015 717-55A0012 38of55 **BOEING SERVICE BULLETIN 717-55A0012 ALERT**  **ALERT**The step numbers shown below agree with the numbers shown in the circle symbols in the figure. **More Data QTY**  **Identification Name**  **Task Step**  (a) (b)
- - Skin Inspect 1 (b) (c) (d) 3
- Fasteners Remove/keep 2

- Holes Inspect 3

Fasteners Install/kept (b) (c) (d) 4
- Fasteners Remove/keep 3

- Holes Inspect 4

Fasteners Install/kept (b) (c) (d) 4
- Fasteners Remove/keep 4

- Holes Inspect 4

Fasteners Install/kept (b) (c) (d) 3
- Fasteners Remove/keep 5

- Holes Inspect 3

Fasteners Install/kept (a) Do a detailed inspection for any "distress" in the vertical stabilizer leading edge structure at the splice at Station Zfs=52.267. (b) "Distress" is defined as deformed holes, elongated holes, oversized holes or any crack in the leading edge skin and splice. (c) Remove and keep one row of fasteners. To prevent damage to the tail plane, only remove one row of fasteners at a time. (d) Do a detailed inspection for distress in each fastener hole location.

**FIGURE 6: RIGHT SIDE VERTICAL STABILIZER LEADING EDGE STRUCTURE AT THE SPLICE AT STATION**  **ZFS=52.267 DETAILED INSPECTION**

**(SHEET 2 OF 2)** Export Controlled ECCN: 9E991 - BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. Original Issue: June 12, 2015 717-55A0012 39of55 **BOEING SERVICE BULLETIN 717-55A0012 ALERT**  **ALERT FIGURE 7:** **RIGHT SIDE VERTICAL STABILIZER FRONT SPAR CAP FORWARD FLANGE OPEN HOLE EDDY CURRENT, HIGH FREQUENCY (ETHF) INSPECTION** 

**(SHEET 1 OF 2)** Export Controlled ECCN: 9E991 - BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. Original Issue: June 12, 2015 717-55A0012 40of55 **BOEING SERVICE BULLETIN 717-55A0012 ALERT**  **ALERT**The step numbers shown below agree with the numbers shown in the circle symbols in the figure. **More Data QTY**  **Identification Name**  **Task Step**  (a) (b) (c)
- - Fasteners Remove/Keep 1 Holes

Inspect Fasteners Install/kept (a) Remove and keep fasteners common to the right side leading edge panel, the dorsal fin lower assembly and vertical stabilizer front spar cap forward flanges, above and below the leading edge skin splice at Station Zfs=52.267. (b) Do an open hole ETHF inspection of the right side vertical stabilizer front spar cap forward flanges at the fastener holes above and below the leading edge skin splice at Station Zfs=52.267 within the specified dimensions. Scan the circumference of the holes in accordance with the Non-destructive Testing Standard Practice ManualNDTSPM 06-10-01.003(ETHF - Procedure 3). (c) Scoring of the fastener hole bore caused by the removal of fasteners may cause crack-like indications. Removal of nut plate may be necessary for proper clean up of the hole. Refer toNDTSPM 06-10-01.003 "Access" and "Preparation and Cleaning" for more information. The nut plate may also interfere with the probe scan with some open hole eddy current probe designs.

**FIGURE 7: RIGHT SIDE VERTICAL STABILIZER FRONT SPAR CAP FORWARD FLANGE OPEN HOLE**  **EDDY CURRENT, HIGH FREQUENCY (ETHF) INSPECTION**

**(SHEET 2 OF 2)** Export Controlled ECCN: 9E991 - BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. Original Issue: June 12, 2015 717-55A0012 41of55 **BOEING SERVICE BULLETIN 717-55A0012 ALERT**  **ALERT FIGURE 8:** **RIGHT SIDE VERTICAL STABILIZER FRONT SPAR CAP AFT FLANGES AT STATION ZFS=52.267 RADIOGRAPHIC TESTING (RT) INSPECTION** 

**(SHEET 1 OF 3)** Export Controlled ECCN: 9E991 - BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. Original Issue: June 12, 2015 717-55A0012 42of55 **BOEING SERVICE BULLETIN 717-55A0012 ALERT**  **ALERT**The step numbers shown below agree with the numbers shown in the circle symbols in the figure. **More Data QTY**  **Identification Name**  **Task Step**  (a) (b) (c) (d) (e) (f) (g) - - Skin Inspect 1 (a) Do a Radiographic Testing (RT) surface inspection of the vertical stabilizer front spar cap aft flange at station Zfs=52.267 for any crack. (b) Prepare exposure radiographic identification tag with the data as follows, using operator's shop practice:

– Service Bulletin number

– Exposure number and right side

– Aircraft I.D.

– Date (c) Attach the identification tag of each of the 5 exposures to the respective film pack using operator's shop practice. (d) Use masking tape to attach film to inspection element for the 5 exposures. (e) Expose film in accordance with x-ray parameters in exposure table below. (f) Any indication is considered a crack which exhibits the same relative phase angle and an amplitude of 50 percent or greater than the indication obtained from the calibration notch in the reference standard.

**FIGURE 8: RIGHT SIDE VERTICAL STABILIZER FRONT SPAR CAP AFT FLANGES AT STATION ZFS=52.267**  **RADIOGRAPHIC TESTING (RT) INSPECTION**

**(SHEET 2 OF 3)** Export Controlled ECCN: 9E991 - BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. Original Issue: June 12, 2015 717-55A0012 43of55 **BOEING SERVICE BULLETIN 717-55A0012 ALERT**  **ALERT More Data**  **QTY Identification**  **Name Task**  **Step** (g) Any crack indications found during RT inspection shall be verified. Refer toNDTSPM 02-00-07for applicable Crack/Defect Evaluation/Verification section(s). **Exposure Table REMARKS**  **FILM DIM "A"**  **mas (a)**  **kV EXPOSURE**  **NUMBER SIZE (Inch)**  **QTY ASTM**  **TYPE** 5 X 7

2 1(b) 36+/-0.5 600 80 1 5 X 7 2 1 and 2(c) 36+/-0.5 600 80 2 5 X 7 2 1 and 2(c) 36+/-0.5 600 80 3 5 X 7 2 1(b) 36+/-0.5 600 80 4 5 X 7 2 1(b) 36+/-0.5 600 80 5 (a) Adjust mas to get a 1.7 to 3.5 H & D density in the area of interest. (b) Kodak M or equivalent type with similar speed. (c) Kodak M and AA or equivalent type with similar speed (double load film pack).

**FIGURE 8: RIGHT SIDE VERTICAL STABILIZER FRONT SPAR CAP AFT FLANGES AT STATION ZFS=52.267**  **RADIOGRAPHIC TESTING (RT) INSPECTION**

**(SHEET 3 OF 3)** Export Controlled ECCN: 9E991 - BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. Original Issue: June 12, 2015 717-55A0012 44of55 **BOEING SERVICE BULLETIN 717-55A0012 ALERT**  **ALERT FIGURE 9:** **RIGHT SIDE VERTICAL STABILIZER SIDE SKIN FRONT SPAR CAP AFT FLANGES EDDY CURRENT, HIGH FREQUENCY (ETHF) INSPECTION** 

**(SHEET 1 OF 2)** Export Controlled ECCN: 9E991 - BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. Original Issue: June 12, 2015 717-55A0012 45of55 **BOEING SERVICE BULLETIN 717-55A0012 ALERT**  **ALERT**The step numbers shown below agree with the numbers shown in the circle symbols in the figure. **More Data QTY**  **Identification Name**  **Task Step**  (a)
- - Skin Inspect 1 (a) Do an ETHF surface inspection of the side skin at the right side vertical stabilizer front spar cap aft flanges within the specified dimensions. Scan around the fasteners for any crack in the forward and aft direction. Scan around the fasteners in accordance with the Non-destructive Testing Standard Practice Manual NDTSPM 06-10-01.001(ETHF - Procedure 1). Use Calibration Method "P" and Scan Method "47".

**FIGURE 9: RIGHT SIDE VERTICAL STABILIZER SIDE SKIN FRONT SPAR CAP AFT FLANGES EDDY**  **CURRENT, HIGH FREQUENCY (ETHF) INSPECTION**

**(SHEET 2 OF 2)** Export Controlled ECCN: 9E991 - BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. Original Issue: June 12, 2015 717-55A0012 46of55 **BOEING SERVICE BULLETIN 717-55A0012 ALERT**  **ALERT FIGURE 10:** **RIGHT SIDE VERTICAL STABILIZER LEADING EDGE AT THE SPLICE AT STATION ZFS=52.267 (FASTENERS NOT REMOVED) DETAILED INSPECTION** 

**(SHEET 1 OF 2)** Export Controlled ECCN: 9E991 - BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. Original Issue: June 12, 2015 717-55A0012 47of55 **BOEING SERVICE BULLETIN 717-55A0012 ALERT**  **ALERT**The step numbers shown below agree with the numbers shown in the circle symbols in the figure. **More Data QTY**  **Identification Name**  **Task Step**  (a)
- - Skin Inspect 1 (a) Do a detailed inspection of the vertical stabilizer leading edge at the splice at Station Zfs=52.267 (fasteners not removed) for any loose or missing fasteners.

**FIGURE 10: RIGHT SIDE VERTICAL STABILIZER LEADING EDGE AT THE SPLICE AT STATION ZFS=52.267**  **(FASTENERS NOT REMOVED) DETAILED INSPECTION**

**(SHEET 2 OF 2)** Export Controlled ECCN: 9E991 - BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. Original Issue: June 12, 2015 717-55A0012 48of55 **BOEING SERVICE BULLETIN 717-55A0012 ALERT**  **ALERT Description** 

**Title** VERTICAL STABILIZER LEADING EDGE SKIN - DETAILED INSPECTIONS for any distress (FASTENERS REMOVED). PART 1

VERTICAL STABILIZER SPAR CAP - EDDY CURRENT, HIGH FREQUENCY (ETHF) and RADIOGRAPHIC TESTING (RT) INSPECTION for any crack. PART 2

VERTICAL STABILIZER SPAR CAP - EDDY CURRENT, HIGH FREQUENCY (ETHF) INSPECTION for any crack. PART 3

VERTICAL STABILIZER LEADING EDGE SKIN REPAIR. PART 5
LEADING EDGE SKIN IS NOT DISTRESSED. CONDITION 1 NO CRACK FOUND. CONDITION 1.1 ANY CRACK FOUND. CONDITION 1.2 LEADING EDGE SKIN IS DISTRESSED. CONDITION 2 NO CRACK FOUND. CONDITION 2.1 ANY CRACK FOUND. CONDITION 2.2

**APPENDIX A: INITIAL DETAILED INSPECTION, EDDY CURRENT HIGH FREQUENCY (ETHF) OR**  **RADIOGRAPHIC TESTING (RT) INSPECTION: FIXED LEADING EDGE SKIN AND FRONT SPAR CAP AT STATION ZFS=52.267**  **(SHEET 1 OF 2)** Export Controlled ECCN: 9E991 - BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. Original Issue: June 12, 2015 717-55A0012 49of55 **BOEING SERVICE BULLETIN 717-55A0012 ALERT**  **ALERT APPENDIX A:** **INITIAL DETAILED INSPECTION, EDDY CURRENT HIGH FREQUENCY (ETHF) OR**

**RADIOGRAPHIC TESTING (RT) INSPECTION: FIXED LEADING EDGE SKIN AND FRONT SPAR CAP AT STATION ZFS=52.267**  **(SHEET 2 OF 2)** Export Controlled ECCN: 9E991 - BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. Original Issue: June 12, 2015 717-55A0012 50of55 **BOEING SERVICE BULLETIN 717-55A0012 ALERT**  **ALERT Description** 

**Title** VERTICAL STABILIZER LEADING EDGE SKIN - DETAILED INSPECTION (FASTENERS NOT REMOVED) for any loose and missing fasteners. PART 4

VERTICAL STABILIZER LEADING EDGE SKIN REPAIR. PART 5
NO LOOSE AND NO MISSING FASTENERS FOUND ON AIRPLANES WHICH COMPLETED OPTION 1 INSPECTIONS. CONDITION 3

NO LOOSE AND NO MISSING FASTENERS FOUND ON AIRPLANES WHICH COMPLETED OPTION 2 INSPECTIONS. CONDITION 4

ANY LOOSE OR MISSING FASTENERS FOUND ONAIRPLANES WHICH COMPLETED OPTION 1 INSPECTIONS. CONDITION 5

ANY LOOSE OR MISSING FASTENERS FOUND ONAIRPLANES WHICH COMPLETED OPTION 2 INSPECTIONS. CONDITION 6

**More Data Flag Note**  Changing from one inspection option to another option is acceptable, provided the repeat interval requirement is first complied with, before changing options. (a)

**APPENDIX B: POST INITIAL DETAILED INSPECTION - FIXED LEADING EDGE SKIN AT STATION**  **ZFS=52.267 (SHEET 1 OF 2)**  Export Controlled ECCN: 9E991 - BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. Original Issue: June 12, 2015 717-55A0012 51of55 **BOEING SERVICE BULLETIN 717-55A0012 ALERT**  **ALERT APPENDIX B:** **POST INITIAL DETAILED INSPECTION - FIXED LEADING EDGE SKIN AT STATION ZFS=52.267**  **(SHEET 2 OF 2)** Export Controlled ECCN: 9E991 - BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. Original Issue: June 12, 2015 717-55A0012 52of55 **BOEING SERVICE BULLETIN 717-55A0012 ALERT**  **ALERT Description** 

**Title** VERTICAL STABILIZER SPAR CAP - EDDY CURRENT, HIGH FREQUENCY (ETHF) and RADIOGRAPHIC TESTING (RT) INSPECTION for any crack. PART 2

VERTICAL STABILIZER SPAR CAP - EDDY CURRENT, HIGH FREQUENCY (ETHF) INSPECTION for any crack. PART 3

NO CRACK FOUND ON AIRPLANES WHICH COMPLETED OPTION 1 INSPECTION. CONDITION 7
NO CRACK FOUND ON AIRPLANES WHICH COMPLETED OPTION 2 INSPECTION. CONDITION 8
ANY CRACK FOUND ON AIRPLANES WHICH COMPLETED OPTION 1 OR OPTION 2 INSPECTION. CONDITION 9

**More Data Flag Note**  Changing from one inspection option to another option is acceptable, provided the repeat interval requirement is first complied with, before changing options. (a)

**APPENDIX C: REPETITIVE EDDY CURRENT HIGH FREQUENCY (ETHF) OR RADIOGRAPHIC TESTING** 

**(RT) INSPECTION - FRONT SPAR CAP AT STATION ZFS=52.267 (SHEET 1 OF 2)**  Export Controlled ECCN: 9E991 - BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. Original Issue: June 12, 2015 717-55A0012 53of55 **BOEING SERVICE BULLETIN 717-55A0012 ALERT**  **ALERT APPENDIX C:** **REPETITIVE EDDY CURRENT HIGH FREQUENCY (ETHF) OR RADIOGRAPHIC TESTING (RT) INSPECTION - FRONT SPAR CAP AT STATION ZFS=52.267**  **(SHEET 2 OF 2)** Export Controlled ECCN: 9E991 - BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. Original Issue: June 12, 2015 717-55A0012 54of55 **BOEING SERVICE BULLETIN 717-55A0012 ALERT**  **ALERT Preparation for Inspection**  1. Remove all dirt, grease, and loose paint from the inspection area. 2. Thoroughly clean the inspection area with an approved cleaning agent. **Supplier CAGE**  **QTY Type**  **Test Equipment** Staveley Instruments 1329 East Kemper Road Cincinati, Ohio 45246 0M421 1 Sperry SPX 160 Portable X-ray ma-chine (1.5mm projected focal spot)
Eastman Kodak Company 343 State Street Rochester, New York 14650 19139 10 Kodak M X-ray film (Refer to Table 2 for sizes)
19139 4 Kodak AA X-ray film (Refer to Table 2 for sizes) Source Optional
- - For radiographic identification. Lead numbers Source Optional
- - - Masking Tape Source Optional
- - In conformance withenvironmental regulations and harmlessto surfaces contacted. Cleaning Agent

**NOTE:** The equipment/materials listed above were used to develop this procedure. Refer toNDTSPM

Part 02-00-04andNDTSPM Part 06-00-04for supplier/vendor information. 1.

2. Equipment/material substitutions producing results equivalent to those defined by this document

may also be used. Refer toNDTSPM Part 01-00-03,NDTSPM Part 02-00-03, andNDTSPM Part 06-00-03for equipment/material information.

**APPENDIX D: PREPARATION OF INSPECTION** 

**(SHEET 1 OF 1)** Export Controlled ECCN: 9E991 - BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. Original Issue: June 12, 2015 717-55A0012 55of55 **BOEING SERVICE BULLETIN 717-55A0012 ALERT**  **ALERT**