# Boeing Alert Service Bulletin 717-55A0011: No revision named

- Rights: © The Boeing Company. Filed by the FAA in regulations.gov docket FAA-2011-1415; AD 2012-12-09 incorporates this document by reference. Not covered by OpenAirDocs’ CC0 dedication.
- Document: [Boeing Alert Service Bulletin 717-55A0011](https://openairdocs.org/service-documents/boeing/717-55a0011.md)
- Title as filed: U.S. DOT/FAA - Service Bulletin
- Pages: 49
- PDF: https://openairdocs.org/files/sha256/cf/37/cf37a5e88a04c5e2796ca784e4b5d36cbc7135076512b68aff964dd69f6bb218
- Page: https://openairdocs.org/service-documents/boeing/717-55a0011/file/cf37a5e88a04

## Text

Some pages are OCR from a scan. OCR can misread letters and numbers. Each page's text from the PDF; open the PDF at a page with #page=N.

### Page 1

Commercial 
Airplanes
717
Service Bulletin
ALERT
Number: 717-55A0011
Original Issue: May 17, 2011
ATA System: 5510
SUBJECT: STABILIZERS - Horizontal Stabilizer - Inspect/Repair/Replace Horizontal Stabilizer
Center Section Left and Right Rib Hinge Bearing Lugs
Export of this technology is controlled under the United States Export Administration Regulations (EAR) (15
CFR 730-774). 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.
9E991ECCN:
BOEING PROPRIETARY, CONFIDENTIAL, AND/OR TRADE SECRET
Copyright © 2011 The Boeing Company
Unpublished Work - All Rights Reserved
Boeing claims copyright in each page of this document only to the extent that the page contains copyrightable
subject matter. Boeing also claims copyright in this document as a compilation and/or collective work.
This document includes proprietary information owned by The Boeing Company and/or one or more third parties.
Treatment of the document and the information it contains is governed by contract with Boeing. For more
information, contact The Boeing Company, P.O. Box 3707, Seattle, Washington 98124.
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, KDC-10, MD-10, MD-11, MD-80, MD-88, MD-90, P-8A, Poseidon and the
Boeing livery 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.
BOEING PROPRIETARY -
Copyright © Unpublished Work - See page 1 for details.
Original Issue: May 17, 2011
717-55A0011
1 of 49
2.0

### Page 2

BOEING PROPRIETARY -
Copyright © Unpublished Work - See page 1 for details.
Original Issue: May 17, 2011
717-55A0011
2 of 49
BOEING SERVICE BULLETIN 717-55A0011
ALERTALERT
BLANK PAGE

### Page 3

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 ................................................ 1 0
D. Description .............................................. 1 0
E. Compliance .............................................. 1 1
F. Approval ............................................... 1 4
G. Manpower .............................................. 1 4
H. Weight and Balance Changes .................................... 1 4
I. Electrical Load Data ......................................... 1 4
J. References .............................................. 1 5
1. Existing Data .......................................... 1 5
2. Data supplied with this Service Bulletin ............................ 1 5
3. Installation Drawings Used in the Preparation of this Service Bulletin ............ 1 5
K. Publications Affected ........................................ 1 5
L. Interchangeability and Intermixability of Parts ........................... 1 5
2. MATERIAL INFORMATION ........................................ 1 7
A. Material - Price and Availability ................................... 1 7
B. Industry Support Information .................................... 1 7
C. Parts Necessary For Each Airplane ................................. 1 7
1. Kits/Parts ............................................ 1 7
2. Parts and Materials Supplied by the Operator ........................ 1 8
3. Parts Modified and Reidentified ................................ 1 8
4. Parts Removed and Not Replaced .............................. 1 8
D. Parts Necessary to Change Spares ................................. 1 8
E. Special Tooling - Price and Availability ............................... 1 8
F. Special Tooling Necessary to do this Service Bulletin ....................... 1 8
3. ACCOMPLISHMENT INSTRUCTIONS .................................. 1 9
A. GENERAL INFORMATION ..................................... 1 9
B. WORK INSTRUCTIONS ....................................... 2 0
FIGURE 1: INSPECT HORIZONTAL STABILIZER CENTER SECTION RIB HINGE BEARING LUGS . 23
FIGURE 2: CRACK LENGTH MEASUREMENT .............................. 2 7
FIGURE 3: BLEND OUT REPAIR ..................................... 3 0
FIGURE 4: INSPECT HORIZONTAL STABILIZER CENTER SECTION RIB HINGE BEARING LUGS . 40
APPENDIX A: TEMPLATE/SHIELD SHOP AID ................................ 4 2
BOEING PROPRIETARY -
Copyright © Unpublished Work - See page 1 for details.
Original Issue: May 17, 2011
717-55A0011
3 of 49
BOEING SERVICE BULLETIN 717-55A0011
ALERTALERT

### Page 4

BOEING PROPRIETARY -
Copyright © Unpublished Work - See page 1 for details.
Original Issue: May 17, 2011
717-55A0011
4 of 49
BOEING SERVICE BULLETIN 717-55A0011
ALERTALERT
BLANK PAGE

### Page 5

Commercial 
Airplanes
717
Service Bulletin
ALERT
SummaryNumber: 717-55A0011Original Issue: May 17, 2011
ATA System: 5510
SUBJECT: STABILIZERS - Horizontal Stabilizer - Inspect/Repair/Replace Horizontal Stabilizer
Center Section Left and Right Rib Hinge Bearing Lugs
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
Boeing has received reports of cracks found on either the left, right, or in few instances both, of the horizontal
stabilizer center section ribs on MD-80 and MD-90 airplanes. Two cracks were reported on MD-80 airplanes
with between 23,700 and 41,963 flight-hours and 23,300 and 35,294 flight cycles. Nine cracks were reported
on MD-90 airplanes with between 9,051 and 26,053 flight-hours and 8,939 and 25,260 flight cycles. These
cracks were found on the aft face of the horizontal stabilizer hinge bearing lugs. Although there have been no
reports of cracks found on 717 airplanes, they utilize the same rib design as the MD-80 and MD-90 airplanes,
and are susceptible to the same failure mode. Investigation by Boeing has yet to establish the definitive cause
of these cracks. Performing an Eddy Current, High Frequency (ETHF) inspection of the affected area will
determine the existence of any crack. Doing a blend out repair of any existing crack within repair limits will help
minimize crack growth. If not corrected, undetected cracks in the center section left and right rib hinge bearing
lugs could spread at the same time, which would cause both hinge bearing lugs to fail, resulting in the inability
of the horizontal stabilizer to sustain flight loads and consequent reduced controllability of the airplane.
ACTION
This service bulletin provides instructions to do an ETHF inspection for cracks on the horizontal stabilizer center
section left and right rib hinge bearing lugs. Refer to Paragraph 1.D., Description for the required corrective
action based on the results of the inspection.
EFFECTIVITY
717-200 Airplanes. Refer to Paragraph 1.A.1., Airplanes, for the list of affected airplanes.
BOEING PROPRIETARY -
Copyright © Unpublished Work - See page 1 for details.
Original Issue: May 17, 2011
717-55A0011
5 of 49

### Page 6

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, repair and/or replacement procedures given in
this service bulletin.
MANPOWER
Refer to Paragraph 1.G., Manpower.
MATERIAL INFORMATION
Boeing Supplied Kits/Parts.
Refer to Paragraph 2.A., Material - Price and Availability.
BOEING PROPRIETARY -
Copyright © Unpublished Work - See page 1 for details.
Original Issue: May 17, 2011
717-55A0011
6 of 49
BOEING SERVICE BULLETIN 717-55A0011
ALERTALERT

### Page 7

BOEING PROPRIETARY -
Copyright © Unpublished Work - See page 1 for details.
Original Issue: May 17, 2011
717-55A0011
7 of 49
BOEING SERVICE BULLETIN 717-55A0011
ALERTALERT

### Page 8

BOEING PROPRIETARY -
Copyright © Unpublished Work - See page 1 for details.
Original Issue: May 17, 2011
717-55A0011
8 of 49
BOEING SERVICE BULLETIN 717-55A0011
ALERTALERT
BLANK PAGE

### Page 9

Commercial 
Airplanes
717
Service Bulletin
ALERT
Number: 717-55A0011
Original Issue: May 17, 2011
ATA System: 5510
SUBJECT: STABILIZERS - Horizontal Stabilizer - Inspect/Repair/Replace Horizontal Stabilizer
Center Section Left and Right Rib Hinge Bearing Lugs
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
This service bulletin is for the airplanes shown below.
DESCRIPTIONCONFIGURATIONGROUP
Inspect Horizontal Stabilizer Center Section Left and Right Rib Hinge
Bearing Lugs on 717-200 airplanes.
-1
Airplane Models:
717-200
GroupFuselage Num-
ber
15002 - 5156
2. Spares Affected
None.
B. Concurrent Requirements
None.
BOEING PROPRIETARY -
Copyright © Unpublished Work - See page 1 for details.
Original Issue: May 17, 2011
717-55A0011
9 of 49

### Page 10

C. Reason
Boeing has received reports of cracks found on either the left, right, or in few instances both, of the
horizontal stabilizer center section ribs on MD-80 and MD-90 airplanes. Two cracks were reported on
MD-80 airplanes with between 23,700 and 41,963 flight-hours and 23,300 and 35,294 flight cycles.
Nine cracks were reported on MD-90 airplanes with between 9,051 and 26,053 flight-hours and 8,939
and 25,260 flight cycles. These cracks were found on the aft face of the horizontal stabilizer hinge
bearing lugs. Although there have been no reports of cracks found on 717 airplanes, they utilize the
same rib design as the MD-80 and MD-90 airplanes, and are susceptible to the same failure mode.
Investigation by Boeing has yet to establish the definitive cause of these cracks. Performing an Eddy
Current, High Frequency (ETHF) inspection of the affected area will determine the existence of any
crack. Doing a blend out repair of any existing crack within repair limits will help minimize crack growth.
If not corrected, undetected cracks in the center section left and right rib hinge bearing lugs could
spread at the same time, which would cause both hinge bearing lugs to fail, resulting in the inability of
the horizontal stabilizer to sustain flight loads and consequent reduced controllability of the airplane.
D. Description
This service bulletin provides instructions to do an ETHF inspection for cracks on the horizontal stabilizer
center section left and right rib hinge bearing lugs, and does as follows:
CONDITION 1 (No Crack Found in Rib Hinge Bearing Lug)
1. Does repeat ETHF inspection.
CONDITION 2 (Crack Found in Rib Hinge Bearing Lug)
1. Measures the length of the crack and does as follows:
CONDITION 2A (Crack Length Between Points 'A' and 'B' is Less Than or Equal to 0.15 Inch,
AND Crack Length Between Points 'C' and 'D' is Less Than or Equal to 0.05 Inch)
a. Does blend out repair to remove crack.
b. Does repeat ETHF inspection of the blend out area.
CONDITION 2B (No Crack Found During ETHF Inspection After Blend Out Repair)
(1) Does repeat ETHF inspection of the blend out area.
CONDITION 2C (Crack Found During ETHF Inspection After Blend Out Repair)
(1) Removes cracked horizontal stabilizer center section rib and installs new horizontal
stabilizer center section rib.
(2) Does ETHF inspection of the horizontal stabilizer center section rib hinge bearing lug.
BOEING PROPRIETARY -
Copyright © Unpublished Work - See page 1 for details.
Original Issue: May 17, 2011
717-55A0011
10 of 49
BOEING SERVICE BULLETIN 717-55A0011
ALERTALERT

### Page 11

CONDITION 2D (Crack Length Between Points 'A' and 'B' is Greater Than 0.15 Inch, OR
Crack Length Between Points 'C' and 'D' is Greater Than 0.05 Inch)
a. Removes cracked horizontal stabilizer center section rib and installs new horizontal stabilizer
center section rib.
b. Does ETHF inspection of the horizontal stabilizer center section rib hinge bearing lug.
The work in this service bulletin is done in the maintenance zone(s) given below.
Affected Maintenance Zones
ZoneModel
351, 361717-200
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.
Table 1 - Inspect Horizontal Stabilizer Center Section Left and Right Rib Hinge Bearing Lugs for Cracks:
Repeat Interval
(Not to Exceed)
Compliance Time (Whichever
Occurs Later)
ActionCondition
-Within 8,275
flight cycles af-
ter the original
issue date on
this service bul-
letin.
Before the accu-
mulation of
35,000 total
flight cycles.
Do an ETHF inspection
of the aft face of the hori-
zontal stabilizer center
section left and right rib
hinge bearing lugs in ac-
cordance with Paragraph
3.B.2., Work Instructions.
All Airplanes
10,500 flight cy-
cles.
Within 10,500 flight cycles from
last inspection.
Do an ETHF inspection
of the aft face of the un-
cracked horizontal stabiliz-
er center section rib hinge
bearing lug in accordance
with Paragraph 3.B.2.,
Work Instructions.
CONDITION 1
(No Crack Found in Rib
Hinge Bearing Lug)
-Before further flight.Measure the length of the
crack in accordance with
Paragraph 3.B.2., Work
Instructions.
CONDITION 2
(Crack Found In Rib Hinge
Bearing Lug)
BOEING PROPRIETARY -
Copyright © Unpublished Work - See page 1 for details.
Original Issue: May 17, 2011
717-55A0011
11 of 49
BOEING SERVICE BULLETIN 717-55A0011
ALERTALERT

### Page 12

Table 1 - Inspect Horizontal Stabilizer Center Section Left and Right Rib Hinge Bearing Lugs for Cracks:
Repeat Interval
(Not to Exceed)
Compliance Time (Whichever
Occurs Later)
ActionCondition
-Before further flight.Do blend out repair in ac-
cordance with Paragraph
3.B.2., Work Instructions.
CONDITION 2A
(Crack Length Between
Points 'A' and 'B' is Less
Than or Equal to 0.15 Inch,
AND Crack Length Be-
tween Points 'C' and 'D' is
Less Than or Equal to 0.05
Inch.)
AND
-Within 14,200 flight cycles after
blend out repair.
Do an ETHF inspection
of the blend out area on
the horizontal stabilizer
center section rib hinge
bearing lug in accordance
with Paragraph 3.B.2.,
Work Instructions.
5,400 flight cycles.-Do repetitive ETHF in-
spection of the blend out
area on the horizontal
stabilizer center section
rib hinge bearing lug in
accordance with Para-
graph 3.B.2., Work In-
structions.
CONDITION 2B
(No Crack Found During
ETHF Inspection After
Blend Out Repair)
BOEING PROPRIETARY -
Copyright © Unpublished Work - See page 1 for details.
Original Issue: May 17, 2011
717-55A0011
12 of 49
BOEING SERVICE BULLETIN 717-55A0011
ALERTALERT

### Page 13

Table 1 - Inspect Horizontal Stabilizer Center Section Left and Right Rib Hinge Bearing Lugs for Cracks:
Repeat Interval
(Not to Exceed)
Compliance Time (Whichever
Occurs Later)
ActionCondition
-Before further flight.Remove cracked horizon-
tal stabilizer center sec-
tion rib and install new
horizontal stabilizer cen-
ter section rib in accor-
dance with Paragraph
3.B.2., Work Instructions.
CONDITION 2C
(Crack Found During ETHF
Inspection After Blend Out
Repair)
AND
-Within 35,000 flight cycles after
the installation of the new rib.
Do an ETHF inspection
of the aft face of the hori-
zontal stabilizer center
section rib hinge bearing
lug in accordance with
Paragraph 3.B.2., Work
Instructions.
AND
-At the applicable compliance times
specified in CONDITION 1 or
CONDITION 2 of this table.
Do the applicable actions
specified in CONDITION
1 or CONDITION 2 of this
table.
-Before further flight.Remove cracked horizon-
tal stabilizer center sec-
tion rib and install new
horizontal stabilizer cen-
ter section rib in accor-
dance with Paragraph
3.B.2., Work Instructions.
CONDITION 2D
(Crack Length Between
Points 'A' and 'B' is Greater
Than 0.15 Inch, OR Crack
Length Between Points 'C'
and 'D' is Greater Than
0.05 Inch.)
AND
-Within 35,000 flight cycles after
the installation of the new rib.
Do an ETHF inspection
of the aft face of the hori-
zontal stabilizer center
section rib hinge bearing
lug in accordance with
Paragraph 3.B.2., Work
Instructions.
AND
-At the applicable compliance times
specified in CONDITION 1 or
CONDITION 2 of this table.
Do the applicable actions
specified in CONDITION
1 or CONDITION 2 of this
table.
BOEING PROPRIETARY -
Copyright © Unpublished Work - See page 1 for details.
Original Issue: May 17, 2011
717-55A0011
13 of 49
BOEING SERVICE BULLETIN 717-55A0011
ALERTALERT

### Page 14

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 this inspection 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.
Elapsed HoursTask HoursNumber of PersonsTask
1.02.02Open Access
2.02.01FIGURE 1
1.02.02Close Access
4.06.0TOTAL FOR EACH AIRPLANE
NOTE: The Manpower totals listed do not include the hours required to accomplish any blend out
repair(s) or replacement of center section rib(s), if required. Operators are to estimate the task
hours required based on inspection results.
H. Weight and Balance Changes
None.
I. Electrical Load Data
Not changed.
BOEING PROPRIETARY -
Copyright © Unpublished Work - See page 1 for details.
Original Issue: May 17, 2011
717-55A0011
14 of 49
BOEING SERVICE BULLETIN 717-55A0011
ALERTALERT

### Page 15

J. References
1. Existing Data
a. Boeing Service Bulletin MD90-55A016.
b. Boeing Service Bulletin MD80-55A069.
c. Non-Destructive Test Standard Practices Manual (NDTSPM) 06-10-01.001.
d. 717 Aircraft Maintenance Manual (AMM) 06-33-00.
e. 717 Structural Repair Manual (SRM) 51-10-04.
2. Data supplied with this Service Bulletin
None.
3. Installation Drawings Used in the Preparation of this Service Bulletin
ChangeTitleDocument Number
C Memo 2RIB CRACK REPAIR - HORIZ STAB,
STA XH=6.625
SR90550001
This drawing was used to prepare this service bulletin. This drawing is not necessary to make the
specified changes, and is not supplied with this service bulletin. This drawing may not be applicable
to all airplane configurations or operators.
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.
BOEING PROPRIETARY -
Copyright © Unpublished Work - See page 1 for details.
Original Issue: May 17, 2011
717-55A0011
15 of 49
BOEING SERVICE BULLETIN 717-55A0011
ALERTALERT

### Page 16

BOEING PROPRIETARY -
Copyright © Unpublished Work - See page 1 for details.
Original Issue: May 17, 2011
717-55A0011
16 of 49
BOEING SERVICE BULLETIN 717-55A0011
ALERTALERT
BLANK PAGE

### Page 17

2.    MATERIAL INFORMATION
A. Material - Price and Availability
NOTE: Parts are only required for Condition 2C or 2D.
Boeing can supply the kits/parts shown in Paragraph 2.C., Parts Necessary for Each Airplane if needed,
as shown below. If there is a limit to the quantity of available parts, a supply sequence is given by
Spares. More parts become available as shown in the Reorder Lead Time (ROLT). Operators are
encouraged to share schedule requirements with Boeing for incorporation of the service bulletin.
REFER TO THE BOEING PART PAGE ON MYBOEINGFLEET.COM OR CONTACT FIRST RESPONDER
AT FR@BOEING.COM FOR THE LATEST REORDER LEAD TIME (ROLT) AND PRICE INFORMATION
Unit Price (US
Dollars)
ROLT (Calendar
Days)
NamePart Number
$16,387.00120RIB - HORIZ STAB, STA XH=6.625 (LEFT)9911846-513
16,387.00120RIB - HORIZ STAB, STA XH=6.625 (RIGHT)9911846-514
The parts are subject to the terms and conditions of the Boeing standard purchase order
acknowledgment. Prices are in United States Dollars. Terms: Net 30 days.
Reference this service bulletin and submit your purchase order by one of these methods:
1. Order on-line via ATA Spec 2000 or The Boeing Part Page
2. Fax to (206) 662-7145
B. Industry Support Information
Boeing warranty remedies are not available for the inspection, repair and/or replacement procedures
given in this service bulletin.
C. Parts Necessary For Each Airplane
1. Kits/Parts
NOTE: Parts are only required for Condition 2C or 2D.
To get the parts shown below, refer to Paragraph 2.A., Material - Price and Availability.
Existing Part
Number
NameQTYNew Part Number
9911846-513RIB - HORIZ STAB, STA
XH=6.625 (LEFT)
19911846-513
9911846-514RIB - HORIZ STAB, STA
XH=6.625 (RIGHT)
19911846-514
BOEING PROPRIETARY -
Copyright © Unpublished Work - See page 1 for details.
Original Issue: May 17, 2011
717-55A0011
17 of 49
BOEING SERVICE BULLETIN 717-55A0011
ALERTALERT

### Page 18

2. Parts and Materials Supplied by the Operator
None.
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
The operator can supply the tools shown in Paragraph 2.F., Special Tooling Necessary to do this
Service Bulletin. Tool price and supply data are not given.
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.
BOEING PROPRIETARY -
Copyright © Unpublished Work - See page 1 for details.
Original Issue: May 17, 2011
717-55A0011
18 of 49
BOEING SERVICE BULLETIN 717-55A0011
ALERTALERT

### Page 19

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. The instructions identified in Paragraph 3.B., Work Instructions, and the Figure(s)
give the recommended sequence of steps. The sequence of steps to do this service
bulletin can be changed.
2. Manual titles are referred to by acronyms. Refer to Paragraph 1.J., References, for
definition of the acronyms.
3. Equivalent parts are listed in the AEPL, Drawing 7595071.
4. Use the approved fastener and process material substitutions, in accordance with
Structural Repair Manual (SRM) 51.
5. If the length of any fastener specified in this service bulletin does not meet installation
standards given in SRM Chapter 51, then a fastener of the same specification, or
an approved substitute, with a length which meets the installation standards given
in SRM Chapter 51 may be used. In addition, washers may be installed for fastener
grip length in accordance with SRM Chapter 51.
6. 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
7. Obey all of the warnings and cautions given in the specified manual sections.
8. 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.
BOEING PROPRIETARY -
Copyright © Unpublished Work - See page 1 for details.
Original Issue: May 17, 2011
717-55A0011
19 of 49
BOEING SERVICE BULLETIN 717-55A0011
ALERTALERT

### Page 20

9. Some Boeing parts are supplied in a temporary configuration. Those parts are
identified with a 'U' or 'Y' in place of the '-' (dash) in the part number. It is permitted
to install parts identified with a 'U' or 'Y' as an alternative to the '-' (dash) number
part. Boeing Drawing SE10000000, Sheets 5.0 and 6.0 contain more data.
10. The instructions in Paragraph 3.B., Work Instructions and the figures can include
operation of tools or test equipment. Boeing Engineering Tool Drawings, the Illustrated
Tool and Equipment Manual, and the Special Tool and Ground Handling Drawing
Index contain data on versions of the tools or test equipment that you can use. It is
permitted to use replaced tools. It is not permitted to use superseded tools.
11. 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.
12. 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.
The removed part can be discarded if a new or serviceable part is installed.
13. This service bulletin includes functional test procedures for the systems changed by
this service bulletin. More functional tests can possibly be necessary in accordance
with standard maintenance practices because of interruption to other airplane systems.
B. WORK INSTRUCTIONS
1. Remove and keep access panels. Refer to 717 AMM 06-33-00.
LocationAccess Panel
Left side lower horizontal stabilizer fairing350AB
Right side lower horizontal stabilizer fairing360AB
2. Do an Eddy Current, High Frequency (ETHF) inspection for cracks, on the aft face of the horizontal
stabilizer center section left and right rib hinge bearing lugs, in accordance with FIGURE 1 and do
as follows:
CONDITION 1 (No Crack Found in Rib Hinge Bearing Lug)
a. Install kept access panels. Refer to 717 AMM 06-33-00.
LocationAccess Panel
Left side lower horizontal stabilizer fairing350AB
Right side lower horizontal stabilizer fairing360AB
b. Put the airplane back to a serviceable condition.
c. Report inspection results, both positive and negative, fuselage number, and cycles and
flight-hours of affected airplane, through your local field service representative or by one of
the methods that follow:
BOEING PROPRIETARY -
Copyright © Unpublished Work - See page 1 for details.
Original Issue: May 17, 2011
717-55A0011
20 of 49
BOEING SERVICE BULLETIN 717-55A0011
ALERTALERT

### Page 21

— Mail: Boeing - Long Beach Division
P.O. Box 1771
Long Beach, California 90801
Attn: Senior Manager Technical and Fleet Support
Structures/Payloads & Repair Design
ATA CODE: 5510
Service Engineering D800-0032
(Service Bulletin 717-55A0011)
— Email: dse.boecom@boeing.com
ATA CODE: 5510
— Fax: Long Beach Service Engineering
FAX: (206) 766-5683
ATA CODE: 5510
d. Do an ETHF inspection, in accordance with FIGURE 1, of the aft face of the uncracked
horizontal stabilizer center section rib hinge bearing lug, at intervals in accordance with
Paragraph 1.E., Compliance.
CONDITION 2 (Crack Found in Rib Hinge Bearing Lug)
a. Measure the length of the crack in accordance with FIGURE 2 and do as follows:
CONDITION 2A (Crack Length Between Points 'A' and 'B' is Less Than or Equal To 0.15
Inch AND Crack Length Between Points 'C' and 'D' is Less Than or Equal To 0.05 Inch)
(1) Report inspection results, both positive and negative, fuselage number, and cycles and
flight-hours of affected airplane, through your local field service representative or by one
of the methods that follow:
— Mail: Boeing - Long Beach Division
P.O. Box 1771
Long Beach, California 90801
Attn: Senior Manager Technical and Fleet Support
Structures/Payloads & Repair Design
ATA CODE: 5510
Service Engineering D800-0032
(Service Bulletin 717-55A0011)
— Email: dse.boecom@boeing.com
ATA CODE: 5510
— Fax: Long Beach Service Engineering
FAX: (206) 766-5683
ATA CODE: 5510
(2) Do blend out repair in accordance with FIGURE 3.
NOTE: Drawings for a locally manufactured template/shield shop aid that can be used
to help define the blend out area are available in APPENDIX A.
(3) Install kept access panels. Refer to 717 AMM 06-33-00.
BOEING PROPRIETARY -
Copyright © Unpublished Work - See page 1 for details.
Original Issue: May 17, 2011
717-55A0011
21 of 49
BOEING SERVICE BULLETIN 717-55A0011
ALERTALERT

### Page 22

LocationAccess Panel
Left side lower horizontal stabilizer fairing350AB
Right side lower horizontal stabilizer fairing360AB
(4) Put the airplane back to a serviceable condition.
(5) Do an ETHF inspection of the blend out area on the horizontal stabilizer center section
rib hinge bearing lug in accordance with FIGURE 4, at intervals in accordance with
Paragraph 1.E., Compliance.
CONDITION 2B (No Crack Found During ETHF Inspection After Blend Out Repair)
(a) Do repeat ETHF inspection of the blend out area.
CONDITION 2C (Crack Found During ETHF Inspection After Blend Out Repair)
(a) Remove cracked horizontal stabilizer center section rib and install new horizontal
stabilizer center section rib.
(b) Do an ETHF inspection for cracks, on the aft face of the horizontal stabilizer center
section rib hinge bearing lug, in accordance with FIGURE 1, and do the applicable
actions specified in CONDITION 1 or CONDITION 2, at compliance times and intervals
in accordance with Paragraph 1.E., Compliance.
CONDITION 2D (Crack Length Between Points 'A' and 'B' is Greater Than 0.15 Inch OR
Crack Length Between Points 'C' and 'D' is Greater Than 0.05 Inch)
(1) Remove cracked horizontal stabilizer center section rib and install new horizontal stabilizer
center section rib.
(2) Do an ETHF inspection for cracks, on the aft face of the horizontal stabilizer center section
rib hinge bearing lug, in accordance with FIGURE 1, and do the applicable actions specified
in CONDITION 1 or CONDITION 2, at compliance times and intervals in accordance with
Paragraph 1.E., Compliance.
BOEING PROPRIETARY -
Copyright © Unpublished Work - See page 1 for details.
Original Issue: May 17, 2011
717-55A0011
22 of 49
BOEING SERVICE BULLETIN 717-55A0011
ALERTALERT

### Page 23 (OCR)

BOEING SERVICE BULLETIN 717-55A0011
ALERT  ALERT
FWD
2054544
FIGURE 1: INSPECT HORIZONTAL STABILIZER CENTER SECTION RIB HINGE BEARING LUGS
(SHEET 1 OF 4)
Original Issue: May 17, 2011
717-55A0011
Copyright © Unpublished Work - See page 1 for details.  BOEING PROPRIETARY -  23 of 49

### Page 24 (OCR)

BOEING SERVICE BULLETIN 717-55A0011
ALERT  ALERT
TYPICAL CRACK
B
2054557
FIGURE 1: INSPECT HORIZONTAL STABILIZER CENTER SECTION RIB HINGE BEARING LUGS
(SHEET 2 OF 4)
Original Issue: May 17, 2011
BOEING PROPRIETARY -  717-55A0011
Copyright © Unpublished Work - See page 1 for details.  24 of 49

### Page 25 (OCR)

BOEING SERVICE BULLETIN 717-55A0011
ALERT  ALERT
TYPICAL CRACK
2054561
FIGURE 1: INSPECT HORIZONTAL STABILIZER CENTER SECTION RIB HINGE BEARING LUGS
(SHEET 3 OF 4)
Original Issue: May 17, 2011
717-55A0011
Copyright © Unpublished Work - See page 1 for details.  BOEING PROPRIETARY -  25 of 49

### Page 26

The step number shown below agree with the number shown in the circle symbol in the figure.
ActionStep
Do an ETHF surface inspection of the rib at the hinge bearing lug aft radius at approximately Stations
Yh=76.000 and Xh=6.625. Scan the lug radius as shown, looking for cracks propagating across the
radius. Refer to NDTSPM 06-10-01.001 (ETHF - Procedure 1). Use Calibration Method "G" and
Scan Method "69".
1
Do an ETHF surface inspection of the rib at the hinge bearing lug aft radius at approximately Stations
Yh=76.000 and Xh=6.625. Scan the lug radius as shown, slightly above the scan done in Step 1,
looking for cracks propagating in the vertical direction. Refer to NDTSPM 06-10-01.001 (ETHF -
Procedure 1). Use Calibration Method "C" and Scan Method "62".
2
FIGURE 1: INSPECT HORIZONTAL STABILIZER CENTER SECTION RIB HINGE BEARING LUGS
(SHEET 4 OF 4)
BOEING PROPRIETARY -
Copyright © Unpublished Work - See page 1 for details.
Original Issue: May 17, 2011
717-55A0011
26 of 49
BOEING SERVICE BULLETIN 717-55A0011
ALERTALERT

### Page 27 (OCR)

BOEING SERVICE BULLETIN 717-55A0011
ALERT  ALERT
FIGURE 2: CRACK LENGTH MEASUREMENT
(SHEET 1 OF 3)
Original Issue: May 17, 2011
Copyright © Unpublished Work - See page 1 for details.  BOEING PROPRIETARY -  717-55A0011  27 of 49/

### Page 28 (OCR)

BOEING SERVICE BULLETIN 717-55A0011
ALERT  ALERT
TYPICAL CRACK
PT "A"
PT "B'
• "C"
"D"
FIGURE 2: CRACK LENGTH MEASUREMENT
(SHEET 2 OF 3)
Original Issue: May 17, 2011
BOEING PROPRIETARY -  717-55A0011
Copyright © Unpublished Work - See page 1 for details.  28 of 49

### Page 29

The step numbers shown below agree with the numbers shown in the circle symbols in the figure.
ActionStep
Measure the crack length from end point (Point A) to where crack intersects the chamfer (Point
B) on the outboard face of the hinge lug. Do not include the measurement of crack length in
chamfer. Record measurement.
1
Measure the crack length from end point (Point D) to where crack intersects the chamfer (Point
C) on the aft face of the hinge lug. Do not include measurement of crack length in the chamfer.
Record measurement.
2
FIGURE 2: CRACK LENGTH MEASUREMENT
(SHEET 3 OF 3)
BOEING PROPRIETARY -
Copyright © Unpublished Work - See page 1 for details.
Original Issue: May 17, 2011
717-55A0011
29 of 49
BOEING SERVICE BULLETIN 717-55A0011
ALERTALERT

### Page 30 (OCR)

BOEING SERVICE BULLETIN 717-55A0011
ALERT  ALERT
FWD
FIGURE 3: BLEND OUT REPAIR
(SHEET 1 OF 10)
Original Issue: May 17, 2011
BOEING PROPRIETARY -  717-55A0011
Copyright © Unpublished Work - See page 1 for details.  30 of 49

### Page 31 (OCR)

BOEING SERVICE BULLETIN 717-55A0011
ALERT  ALERT
LOWER SKIN
SURFACE
PT 2 E  0.58
D
O PT 1
1.59  0.05
(NORMAL TO LOWER SKIN  CONST
PANEL SURFACE)
3) PT4
2055467
FIGURE 3: BLEND OUT REPAIR
(SHEET 2 OF 10)
Original Issue: May 17, 2011
Copyright © Unpublished Work - See page 1 for details.  BOEING PROPRIETARY -  717-55A0011  31 of 49

### Page 32 (OCR)

BOEING SERVICE BULLETIN 717-55A0011
ALERT  ALERT
LOWER SKIN
SURFACE
0.50  0.19
4 РТ З
INBD
C-C
FIGURE 3: BLEND OUT REPAIR
(SHEET 3 OF 10)
Original Issue: May 17, 2011
BOEING PROPRIETARY -  717-55A0011
Copyright © Unpublished Work - See page 1 for details.  32 of 49

### Page 33 (OCR)

BOEING SERVICE BULLETIN 717-55A0011
ALERT  ALERT
(BLEND 'A) €1
BLEND 'A'
V-SHAPE
TYPICAL CRACK LOCATION
D-D
2055470
FIGURE 3: BLEND OUT REPAIR
(SHEET 4 OF 10)
Original Issue: May 17, 2011
BOEING PROPRIETARY -  717-55A0011
Copyright © Unpublished Work - See page 1 for details.  33 of 49

### Page 34 (OCR)

BOEING SERVICE BULLETIN 717-55A0011
ALERT  ALERT
PT 2
- 0.58
' PT 1
0.050
(NORMAL TO LOWER  1.59  CONST
SKIN PANEL SURFACE)
6>7
BLEND 'A' AREA
\PT4
FIGURE 3: BLEND OUT REPAIR
(SHEET 5 OF 10)
Original Issue: May 17, 2011
BOEING PROPRIETARY -  717-55A0011
Copyright © Unpublished Work - See page 1 for details.  34 of 49

### Page 35 (OCR)

BOEING SERVICE BULLETIN 717-55A0011
ALERT  ALERT
LOWER SKIN  - PT 1
PANEL SURFACE
0.05
•0.23
0.50
→ PT 3
BLEND 'A' AREA
F-F
2055980
FIGURE 3: BLEND OUT REPAIR
(SHEET 6 OF 10)
Original Issue: May 17, 2011
BOEING PROPRIETARY -  717-55A0011
Copyright © Unpublished Work - See page 1 for details.  35 of 49

### Page 36 (OCR)

BOEING SERVICE BULLETIN 717-55A0011
ALERT  ALERT
G  2055978
FIGURE 3: BLEND OUT REPAIR
(SHEET 7 OF 10)
Original Issue: May 17, 2011
BOEING PROPRIETARY -  717-55A0011
Copyright © Unpublished Work - See page 1 for details.  36 of 49

### Page 37 (OCR)

BOEING SERVICE BULLETIN 717-55A0011
ALERT  ALERT
LOWER SKIN
SURFACE
90
• TAPER
DIRECTION
-PT 4
(BLEND 'B')
2055998
FIGURE 3: BLEND OUT REPAIR
(SHEET 8 OF 10)
Original Issue: May 17, 2011
BOEING PROPRIETARY -  717-55A0011
Copyright © Unpublished Work - See page 1 for details.  37 of 49

### Page 38 (OCR)

BOEING SERVICE BULLETIN 717-55A0011
ALERT  ALERT
LOWER SKIN
SURFACE
PT 1  / INCH RADIUS
_ -
1.65
PT 4
INBD
J-J
2056019
FIGURE 3: BLEND OUT REPAIR
(SHEET 9 OF 10)
Original Issue: May 17, 2011
BOEING PROPRIETARY -  717-55A0011
Copyright © Unpublished Work - See page 1 for details.  38 of 49

### Page 39

The step numbers shown below agree with the numbers shown in the circle symbols in the figure.
ActionStep
Locate Point 1. Point 1 is identified as the intersecting point of a line offset from the horizontal stabi-
lizer lower surface 0.050 inch, and the outboard edge of the chamfer on the hinge lug.
1
Locate Point 2. Point 2 is identified as the point on a line offset from the horizontal stabilizer lower
surface 0.050 inch, and 0.58 inch forward of Point 1.
2
Locate Point 4. Point 4 is identified as the point located 1.59 inch measured normal to the horizontal
stabilizer lower surface at the aft edge of the hinge lug.
3
Locate Point 3. Point 3 is identified as the point located 0.19 inch from the inboard edge of the hinge
lug, and 0.50 inch from the horizontal stabilizer lower surface.
4
Blend out the crack. (Blend 'A') Do not exceed the limits of the area defined by points 1, 2, 3, and
4. The blend out should form a "V" shape, with the deepest portion of the "V" being in the area of
the crack, and approximately 127 degrees between the legs of the "V". Maintain a 0.25 inch radius
at the bottom of the "V". The majority of the blend should be at approximately 45 degrees from the
outboard face of the lug. It is recommended that a 0.50 inch diameter ball grinder be used to do the
blend out. Remove only enough material to remove the crack. Do not remove more than 0.25 inch
of material total depth as measured from a line drawn between the points B and C that were estab-
lished in Figure 2.
5
Do ETHF inspections during material removal to verify crack has been removed. Scan the blend out
as shown, looking for cracks in the upper forward to lower aft direction. Scan the blend out and give
more attention to the outside periphery. Refer to NDTSPM 06-10-01.001 (ETHF - Procedure 1). Use
Calibration Method "G" and Scan Method "69". If crack still is not removed, repeat Steps 5 and 6.
6
Once the crack has been removed, remove an additional 0.050 inch of material to ensure that a
crack that is too small to detect has been removed. Finish blend out to a 63 micro-inch finish.
7
Do a taper of the outboard face of the lug. (Blend 'B') The taper begins at a line between Point 4
and tangent to the radius on the aft portion of the bearing lug surface, and extends upward and aft
to a point 1.65 inches above Point 4. Finish blend out to a 63 micro-inch finish.
8
Break all reworked edges to a 0.12 inch radius. If adjacent structure prevents using a 0.12 inch radius,
use the largest radius possible in the area.
9
Apply corrosion protection to the rework area. Refer to 717 SRM 51-10-04.10
(Not
Shown)
FIGURE 3: BLEND OUT REPAIR
(SHEET 10 OF 10)
BOEING PROPRIETARY -
Copyright © Unpublished Work - See page 1 for details.
Original Issue: May 17, 2011
717-55A0011
39 of 49
BOEING SERVICE BULLETIN 717-55A0011
ALERTALERT

### Page 40 (OCR)

BOEING SERVICE BULLETIN 717-55A0011
ALERT  ALERT
POSSIBLE
CRACK
FWD |
2056021
FIGURE 4: INSPECT HORIZONTAL STABILIZER CENTER SECTION RIB HINGE BEARING LUGS
(SHEET 1 OF 2)
Original Issue: May 17, 2011
717-55A0011
BOEING PROPRIETARY -
Copyright © Unpublished Work - See page 1 for details.  40 of 49

### Page 41

The step number shown below agree with the number shown in the circle symbol in the figure.
ActionStep
Do an ETHF surface inspection of Blend 'A' area at the hinge bearing lug aft radius. Scan the
blend out as shown, looking for cracks in the upper forward to lower aft direction. Scan the blend
out and give more attention to the outside periphery. Refer to NDTSPM 06-10-01.001 (ETHF -
Procedure 1). Use Calibration Method "G" and Scan Method "69".
1
FIGURE 4: INSPECT HORIZONTAL STABILIZER CENTER SECTION RIB HINGE BEARING LUGS
(SHEET 2 OF 2)
BOEING PROPRIETARY -
Copyright © Unpublished Work - See page 1 for details.
Original Issue: May 17, 2011
717-55A0011
41 of 49
BOEING SERVICE BULLETIN 717-55A0011
ALERTALERT

### Page 42

This appendix provides instructions for the fabrication and usage of a template/shield shop aid to assist in
simplifying the identification of the extents of the blend out area, if required, identified in FIGURE 3.
This appendix provides instructions to build a template/shield for use on the left hand hinge bearing lug. A mirror
image template/shield is required for the right hand hinge bearing lug.
FABRICATION
1. Fabricate all parts from 0.050 Inch CRES Sheet, Type 321, per Aerospace Material Specification (AMS)
5510 or equivalent.
2. Identification of parts and assemblies at operator's option, and per operator's shop practice.
3. Fusion weld with Gas Tungsten Arc Welding (GTAW).
4. It is acceptable to fusion weld from opposite side than that specified by the welding symbol.
5. If surfaces on -3 and -9 parts are distorted by welding, straighten surfaces to within +/- .010 inch before
use.
6. Tack or continuous weld -11 to the sub assembly from sub-assembly step 3.
7. Trim -7 as shown.
8. Cut or grind radius on -7 as shown.
9. Unless shown differently, these dimensions and tolerances are used for the fabrication of a template/shield
shop aid:
– Linear dimensions are in inches.
– Angular tolerance is plus or minus 0 degrees, 30 minutes.
– Tolerance on 3 place decimal linear dimension is plus or minus 0.015 inch.
– Tolerance on 2 place decimal linear dimension is plus or minus 0.03 inch.
APPENDIX A:  TEMPLATE/SHIELD SHOP AID
(SHEET 1 OF 8)
BOEING PROPRIETARY -
Copyright © Unpublished Work - See page 1 for details.
Original Issue: May 17, 2011
717-55A0011
42 of 49
BOEING SERVICE BULLETIN 717-55A0011
ALERTALERT

### Page 43 (OCR)

BOEING SERVICE BULLETIN 717-55A0011
ALERT  ALERT
4.59 + .25
1.83
3 x R.25 25/  -3
1.47
2.42
2.40
1.43
R1.00 ‡ 25/
- 2.30
-5
2056023
APPENDIX A: TEMPLATE/SHIELD SHOP AID
(SHEET 2 OF 8)
Original Issue: May 17, 2011
Copyright © Unpublished Work - See page 1 for details.  BOEING PROPRIETARY -  717-55A0011  43 of 49

### Page 44 (OCR)

BOEING SERVICE BULLETIN 717-55A0011
ALERT  ALERT
7.09
6.67
2 x R.25 + .25,
CHAMFER 0.021
(APPROX 22.78 DEGREES)-
• R.19
R1.50  /R.25
3.32
~3 X R.50  1.25
2.23
1.97  1.82
1.11
1.13
• 1.00 -
5.65
6.57
-7
•50 + .25  - .00
2 x R.25 + .10
2 x.50 +.10  - .00
48  - 2.00
-11  R 1.50 + .25  - .00  -9
APPENDIX A: TEMPLATE/SHIELD SHOP AID
(SHEET 3 OF 8)
Original Issue: May 17, 2011
BOEING PROPRIETARY -  717-55A0011
Copyright © Unpublished Work - See page 1 for details.  44 of 49

### Page 45 (OCR)

BOEING SERVICE BULLETIN 717-55A0011
ALERT  ALERT
FUSION WELD
1.85 Д
131° 25
2.32 W
1.18 + .00  - .15  HEEL INTERSECTION POINT
- 2.40 -
SUB ASSEMBLY STEP 1
DIMENSIONS NOTED WITH W SYMBOL
ARE FOR THE FINAL CONFORMANCE
INSPECTION PURPOSE ONLY, NOT FOR
FABRICATION.
2.60 +.10  - .00
64° 12'
FUSION WELD
GRIND WELD FLUSH
ON THIS SURFACE
SUB ASSEMBLY STEP 2
A-A
2056042
APPENDIX A: TEMPLATE/SHIELD SHOP AID
(SHEET 4 OF 8)
Original Issue: May 17, 2011
717-55A0011
Copyright © Unpublished Work - See page 1 for details.  BOEING PROPRIETARY -  45 of 49

### Page 46 (OCR)

BOEING SERVICE BULLETIN 717-55A0011
ALERT  ALERT
90°
(VIEW ANGLE)
FUSION WELD
1.15 + .00  - 15 TRUE
- 1D
90°
1.15 +.00  -.15 TRUE
DIMENSIONS NOTED WITH  SYMBOL  FUSION WELD
ARE FOR THE FINAL CONFORMANCE
INSPECTION PURPOSE ONLY, NOT FOR
FABRICATION.
SUB ASSEMBLY STEP 3
126° 43'  112° 56'
REMOVE ANY WELD
PENETRATION ON
THIS SIDE FLUSH
TO SURFACE
B-B  C-C  2056043
APPENDIX A: TEMPLATE/SHIELD SHOP AID
(SHEET 5 OF 8)
Original Issue: May 17, 2011
717-55A0011
BOEING PROPRIETARY -
Copyright © Unpublished Work - See page 1 for details.  46 of 49

### Page 47 (OCR)

BOEING SERVICE BULLETIN 717-55A0011
ALERT  ALERT
-1.40 →
.47
1.82 Д
2.17 Д  • 3
D-D  DIMENSIONS NOTED WITH & SYMBOL
ARE FOR THE FINAL CONFORMANCE
INSPECTION PURPOSE ONLY, NOT FOR
FABRICATION.
2 X R.25 ‡ 25 TRUE
FUSION WELD
- 9
TRIM -7 AS SHOWN
.75
.50
-2x 36
FUSION WELD
- 2.50
FINAL ASSEMBLY STEP 4  2056045
APPENDIX A: TEMPLATE/SHIELD SHOP AID
(SHEET 6 OF 8)
Original Issue: May 17, 2011
717-55A0011
Copyright © Unpublished Work - See page 1 for details.  BOEING PROPRIETARY -  47 of 49

### Page 48

DIRECTIONS FOR TEMPLATE/SHIELD SHOP AID USE
1. After identifying points 1, 2, 3, and 4 in accordance with the instructions in FIGURE 3, place template/shield
on lug. Push upper portion of template/shield against the lower surface of the horizontal stabilizer, and push
the outer portion of the template/shield against the outboard surface of the lug.
2. Slide the template/shield fore and aft until the lower portion of the template is on Point 4, and check that
the template/shield is aligned with Point 2.
NOTE: The aft face of the template/shield may not be in contact with the aft face of the lug when the
template/shield is aligned with Points 2 and 4.
3. Using an appropriate marker, trace the template/shield shape on the aft face of the lug, and on the outboard
face of the lug, to visually define the shape of the blend out area. Do not exceed the limits of the blend out
area defined by Points 1, 2, 3, and 4 established in FIGURE 3 if they are different than the area defined by
the template/shield.
The template/shield may be secured to the lug and used as a shield to help while grinding the crack out in
accordance with FIGURE 3.
APPENDIX A:  TEMPLATE/SHIELD SHOP AID
(SHEET 7 OF 8)
BOEING PROPRIETARY -
Copyright © Unpublished Work - See page 1 for details.
Original Issue: May 17, 2011
717-55A0011
48 of 49
BOEING SERVICE BULLETIN 717-55A0011
ALERTALERT

### Page 49 (OCR)

BOEING SERVICE BULLETIN 717-55A0011
ALERT  ALERT
RIB ASSEMBLY
OUTBOARD LUG SURFACE
TEMPLATE / SHIELD USAGE
2056047
APPENDIX A: TEMPLATE/SHIELD SHOP AID
(SHEET 8 OF 8)
Original Issue: May 17, 2011
BOEING PROPRIETARY -  717-55A0011
Copyright © Unpublished Work - See page 1 for details.  49 of 49

---
OpenAirDocs.org is an independent research project of [Contrail Labs](https://contraillabs.com/). It is not affiliated with the FAA or the NTSB. Source documents are U.S. government works in the public domain, except the copies of manufacturers’ service documents, which belong to their rights holders.