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.

ECCN: 9E991

BOEING PROPRIETARY, CONFIDENTIAL AND/OR TRADE SECRET

Copyright © 2015 Boeing.

Unpublished Work. All Rights Reserved.

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Boeing Company.

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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

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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

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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.

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Planning Data Affected Reference

Spares Affected No Paragraph 1.A.2., Spares Affected

Paragraph 1.E., Compliance and Paragraph

1.F., Approval

AD Related Yes

Weight and Balance Change No Paragraph 1.H., Weight and Balance Changes

Electrical Load Changed No Paragraph 1.I., Electrical Load Data

Publications Affected No Paragraph 1.K., Publications Affected

Airplane Flight Operations Affected (Flight Crew No Paragraph 1.K., Publications Affected

Operations Manual and/or FAA Approved Airplane Flight Manual)

Kits/Parts Required No Paragraph 2.C.1., Kits/Parts

Paragraph 2.C.2., Parts and Materials Supplied

by the Operator

Operator Supplied Parts/Material No

Paragraph 2.F., Special Tooling Necessary to

do this Service Bulletin

Special Tooling Required No

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.

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BOEING SERVICE BULLETIN 717-55A0012

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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

GROUP CONFIGURATION DESCRIPTION

1 - 717-200 airplanes. Line numbers 2 - 156.

Airplane Models:

717-200

Fuselage Num- Group

ber

5002 - 5099 1

5100 - 5156 1

2. Spares Affected

None.

B. Concurrent Requirements

None.

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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

Model Zone

717-200 371

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.

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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 Interval (Not to Exceed)Compliance Time (Whichever Occurs Later)Condition Action

Within 6,200 -

flight cycles

after the original issue date

of this service

bulletin.

Before 15,000

total flight cycles.

Do PART 1: VERTICAL STABILIZER LEADING EDGE SKIN - DETAILED INSPECTIONS for any

distress (FASTENERS REMOVED).

All Airplanes.

CONDITION 1: OPTION 1: Before further flight. -

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.

OPTION 2: Before further flight. -

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.

Contact The Boeing Company for Before further flight. -

repair instructions and do the repair.

CONDITION 1.2:

ANY CRACK FOUND during OPTION 1 or OPTION

2 spar cap inspection.

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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 Interval (Not to Exceed)Compliance Time (Whichever Occurs Later)Condition Action

CONDITION 2: OPTION 1: Before further flight. -

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.

OPTION 2: Before further flight. -

Do PART 3: VERTICAL STABILIZER SPAR CAP - EDDY CURRENT, HIGH FREQUENCY

(ETHF) INSPECTION for any

crack.

CONDITION 2.1: CONDITION 2.1 (ACTION 1): Before further flight. -

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.

CONDITION 2.2: CONDITION 2.2 (ACTION 1): Before further flight. -

Do PART 5: VERTICAL STABILIZER LEADING EDGE SKIN REPAIR.ANY CRACK FOUND during OPTION 1 or OPTION

2 spar cap inspection.

CONDITION 2.2 (ACTION 2): Before further flight. -

Contact The Boeing Company for

repair instructions and do the repair.

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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)

Condition Action Compliance Time

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.

CONDITION 5: CONDITION 5 (ACTION 1): Before further flight. -

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.

CONDITION 6: CONDITION 6 (ACTION 1): Before further flight. -

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.

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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)

Condition Action Compliance Time

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 flight -

cycles 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.

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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)

Condition Action Compliance Time

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.

Contact The Boeing Company for Before further flight. -

repair instructions and do the repair.

CONDITION 9:

ANY CRACK FOUND ON AIRPLANES WHICH COMPLETE

OPTION 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.

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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

Task Number of Persons Task Hours Elapsed Hours

FIGURE 1 1 2.5 2.5

FIGURE 2 1 2.0 2.0

FIGURE 3 or FIGURE 4 1 1.0 1.0

FIGURE 6 1 2.5 2.5

FIGURE 7 1 2.0 2.0

FIGURE 8 or FIGURE 9 1 1.0 1.0

TOTAL FOR EACH AIRPLANE (a) (b) 11.0 11.0

(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

Task Number of Persons Task Hours Elapsed Hours

FIGURE 2 1 2.0 2.0

FIGURE 3 or FIGURE 4 1 1.0 1.0

FIGURE 5 1 0.5 0.5

FIGURE 7 1 2.0 2.0

FIGURE 8 or FIGURE 9 1 1.0 1.0

FIGURE 10 1 0.5 0.5

TOTAL FOR EACH AIRPLANE (a) (b) 7.0 7.0

(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.

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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:

Drawing No Title Sheet DCN/REV ADCN

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

FIXED LEADING EDGE SKIN REPAIR - 1 - -

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.

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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 in APPENDIX D and 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.

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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, Drawing 7595071.

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 in 717 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 to APPENDIX D for preparation of inspection.

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ALERT ALERT
7. Refer to APPENDIX A for 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

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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.

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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.

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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 1 and FIGURE 6.

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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 with FIGURE 2 and FIGURE

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 with FIGURE 3 and FIGURE 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 2 and FIGURE 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 4 and 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 5 and

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.

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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)

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ALERT ALERT
The step numbers shown below agree with the numbers shown in the circle symbols in the figure.

Step Task Name Identification QTY More Data

1 Inspect Skin - - (a) (b)

2 Remove/keep Fasteners - 3 (b) (c) (d)

Inspect Holes -

Install/kept Fasteners 3

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

Inspect Holes -

Install/kept Fasteners 4

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

Inspect Holes -

Install/kept Fasteners 4

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

Inspect Holes -

Install/kept Fasteners 3

(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)

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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)

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ALERT ALERT
The step numbers shown below agree with the numbers shown in the circle symbols in the figure.

Step Task Name Identification QTY More Data

1 Remove/keep Fasteners - - (a) (b) (c)

Inspect Hole

Install/kept Fasteners

(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 Manual NDTSPM 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 to NDTSPM 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)

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FIGURE 3: LEFT SIDE VERTICAL STABILIZER FRONT SPAR CAP AFT FLANGES AT STATION ZFS=52.267

RADIOGRAPHIC TESTING (RT) INSPECTION

(SHEET 1 OF 3)

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ALERT ALERT
The step numbers shown below agree with the numbers shown in the circle symbols in the figure.

Step Task Name Identification QTY More Data

(a) (b) (c) (d) (e)

(f) (g)

1 Inspect Skin - -

(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

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Step Task Name Identification QTY More Data

(g) Any crack indications found during RT inspection shall be verified. Refer to NDTSPM 02-00-07 for applicable Crack/Defect Evaluation/Verification section(s).

Exposure Table

EXPOSURE kV mas (a) DIM "A" FILM REMARKS

NUMBER ASTM QTY SIZE (Inch)

TYPE

1 80 600 36+/-0.5 1 (b) 2 5 X 7

2 80 600 36+/-0.5 1 and 2 (c) 2 5 X 7

3 80 600 36+/-0.5 1 and 2 (c) 2 5 X 7

4 80 600 36+/-0.5 1 (b) 2 5 X 7

5 80 600 36+/-0.5 1 (b) 2 5 X 7

(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

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

CURRENT, HIGH FREQUENCY (ETHF) INSPECTION

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ALERT ALERT
The step numbers shown below agree with the numbers shown in the circle symbols in the figure.

Step Task Name Identification QTY More Data

1 Inspect Skin - - (a)

(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

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

(FASTENERS NOT REMOVED) DETAILED INSPECTION

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ALERT ALERT
The step numbers shown below agree with the numbers shown in the circle symbols in the figure.

Step Task Name Identification QTY More Data

1 Inspect Skin - - (a)

(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)

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ALERT ALERT
FIGURE 6: RIGHT SIDE VERTICAL STABILIZER LEADING EDGE STRUCTURE AT THE SPLICE AT STATION

ZFS=52.267 DETAILED INSPECTION

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ALERT ALERT
The step numbers shown below agree with the numbers shown in the circle symbols in the figure.

Step Task Name Identification QTY More Data

1 Inspect Skin - - (a) (b)

2 Remove/keep Fasteners - 3 (b) (c) (d)

Inspect Holes -

Install/kept Fasteners 3

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

Inspect Holes -

Install/kept Fasteners 4

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

Inspect Holes -

Install/kept Fasteners 4

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

Inspect Holes -

Install/kept Fasteners 3

(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)

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ALERT ALERT
FIGURE 7: RIGHT SIDE VERTICAL STABILIZER FRONT SPAR CAP FORWARD FLANGE OPEN HOLE

EDDY CURRENT, HIGH FREQUENCY (ETHF) INSPECTION

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ALERT ALERT
The step numbers shown below agree with the numbers shown in the circle symbols in the figure.

Step Task Name Identification QTY More Data

1 Remove/Keep Fasteners - - (a) (b) (c)

Inspect Holes

Install/kept Fasteners

(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 Manual NDTSPM 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 to NDTSPM 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

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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)

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ALERT ALERT
The step numbers shown below agree with the numbers shown in the circle symbols in the figure.

Step Task Name Identification QTY More Data

(a) (b) (c) (d) (e)

(f) (g)

1 Inspect Skin - -

(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)

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ALERT ALERT
Step Task Name Identification QTY More Data

(g) Any crack indications found during RT inspection shall be verified. Refer to NDTSPM 02-00-07 for applicable Crack/Defect Evaluation/Verification section(s).

Exposure Table

EXPOSURE kV mas (a) DIM "A" FILM REMARKS

NUMBER ASTM QTY SIZE (Inch)

TYPE

1 80 600 36+/-0.5 1 (b) 2 5 X 7

2 80 600 36+/-0.5 1 and 2 (c) 2 5 X 7

3 80 600 36+/-0.5 1 and 2 (c) 2 5 X 7

4 80 600 36+/-0.5 1 (b) 2 5 X 7

5 80 600 36+/-0.5 1 (b) 2 5 X 7

(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)

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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)

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BOEING SERVICE BULLETIN 717-55A0012

ALERT ALERT
The step numbers shown below agree with the numbers shown in the circle symbols in the figure.

Step Task Name Identification QTY More Data

1 Inspect Skin - - (a)

(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)

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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)

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BOEING SERVICE BULLETIN 717-55A0012

ALERT ALERT
The step numbers shown below agree with the numbers shown in the circle symbols in the figure.

Step Task Name Identification QTY More Data

1 Inspect Skin - - (a)

(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)

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ALERT ALERT
Title Description

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

CONDITION 1 LEADING EDGE SKIN IS NOT DISTRESSED.

CONDITION 1.1 NO CRACK FOUND.

CONDITION 1.2 ANY CRACK FOUND.

CONDITION 2 LEADING EDGE SKIN IS DISTRESSED.

CONDITION 2.1 NO CRACK FOUND.

CONDITION 2.2 ANY CRACK FOUND.

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)

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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

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ALERT ALERT
Title Description

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 ON

AIRPLANES WHICH COMPLETED OPTION 1 INSPECTIONS.

CONDITION 5

ANY LOOSE OR MISSING FASTENERS FOUND ON

AIRPLANES WHICH COMPLETED OPTION 2 INSPECTIONS.

CONDITION 6

Flag Note More Data

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

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

ZFS=52.267

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ALERT ALERT
Title Description

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

Flag Note More Data

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

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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)

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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.

Test Equipment Type QTY CAGE Supplier

Staveley Instruments

1329 East Kemper

Road Cincinati, Ohio

45246

Portable X-ray ma- Sperry SPX 160 1 0M421

chine (1.5mm projected focal spot)

Eastman Kodak

Company 343 State

Street Rochester,

New York 14650

X-ray film Kodak M 10 19139

(Refer to Table 2 for

sizes)

X-ray film Kodak AA 4 19139

(Refer to Table 2 for

sizes)

For radiographic - - Source Optional

identification.

Lead numbers

Masking Tape - - - Source Optional

In conformance with - - Source Optional

environmental regulations and harmless

to surfaces contacted.

Cleaning Agent

NOTE:

The equipment/materials listed above were used to develop this procedure. Refer to NDTSPM

Part 02-00-04 and NDTSPM Part 06-00-04 for supplier/vendor information.

1.

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

may also be used. Refer to NDTSPM Part 01-00-03, NDTSPM Part 02-00-03, and NDTSPM

Part 06-00-03 for equipment/material information.

APPENDIX D: PREPARATION OF INSPECTION

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ALERT ALERT