December 09, 2004

Revision 1: October 12, 2006 767-51A0028

BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. 1 of 52

Commercial

Airplane

Group 767

Service Bulletin

Number: 767-51A0028

Date: December 09, 2004

Revision 1: October 12, 2006

ATA System: 5141

SUBJECT: STRUCTURES - Airframe Drainage - Horizontal Stabilizer Center Section - Gutter 

Installation

BOEING PROPRIETARY, CONFIDENTIAL, AND/OR TRADE SECRET

Copyright © 2004 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Unpublished Work - All Rights Reserved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, 707, 717, 727, 737, 747, 757, 767, 777, BBJ, BOEING BUSINESS JET, DC-8, DC-9, DC-10, MD-10, 

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its subsidiaries. No intellectual property license (express or implied) is granted in connection with this document 

or otherwise.
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BLANK PAGE
 Table of Contents

December 09, 2004

Revision 1: October 12, 2006 767-51A0028

BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. 3 of 52

BOEING SERVICE BULLETIN 767-51A0028

Table of Contents

Revision Transmittal Sheet . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 5

Summary . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 7

1. PLANNING INFORMATION . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 11

A. Effectivity . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 11

1. Airplanes . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 11

2. Spares Affected . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 12

B. Concurrent Requirements . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 12

C. Reason . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 12

D. Description . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 13

E. Compliance. . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 13

F. Approval . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 14

G. Manpower . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 14

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

I. Electrical Load Data . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 15

J. References . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 15

1. Existing Data: . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 15

2. Data supplied with this Service Bulletin: . . . . . . . . . . . . . . . . . . . . . . . . . 16

3. Installation Drawings Used in the Preparation of this Service Bulletin: . . . . . . . . . . 16

K. Publications Affected . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 16

L. Interchangeability and Intermixability of Parts . . . . . . . . . . . . . . . . . . . . . . . . . 16

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

A. Material - Price and Availability. . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 17

B. Industry Support Information . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 17

C. Parts Necessary For Each Airplane . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 18

1. Kits/Parts: . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 18

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 . . . . . . . . . . . . . . . . . . . . . 20

3. ACCOMPLISHMENT INSTRUCTIONS . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 21

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

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

FIGURE 1: GUTTER PREPARATION AND PROTECTION . . . . . . . . . . . . . . . . . . . . . . . 25

FIGURE 2: REWORK SIDE BRACE FITTINGS - HORIZONTAL STABILIZER CENTER SECTION . . 26

FIGURE 3: GUTTER INSTALLATION - UPPER SURFACE, HORIZONTAL STABILIZER CENTER

SECTION - LEFT SIDE . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 28

FIGURE 4: GUTTER INSTALLATION - UPPER SURFACE, HORIZONTAL STABILIZER CENTER

SECTION - RIGHT SIDE . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 32

FIGURE 5: SPLICE INSTALLATION - HORIZONTAL STABILIZER CENTER SECTION. . . . . . . . 35

FIGURE 6: DISCONNECT HYDRAULIC LINES - HORIZONTAL STABILIZER CENTER SECTION . . 40

FIGURE 7: GUTTER PREPARATION - LOCATOR IDENTIFICATION . . . . . . . . . . . . . . . . . 42

FIGURE 8: GUTTER INSTALLATION - UPPER SURFACE, HORIZONTAL STABILIZER CENTER

SECTION . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 43
 Table of Contents

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BOEING SERVICE BULLETIN 767-51A0028

FIGURE 9: GUTTER SEALING - HORIZONTAL STABILIZER CENTER SECTION. . . . . . . . . . . 49

FIGURE 10: CONNECT HYDRAULIC LINES - HORIZONTAL STABILIZER CENTER SECTION . . . 51
December 09, 2004

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Commercial

Airplane

Group 767

Service Bulletin

Number: 767-51A0028 Revision Transmittal Sheet

Date: December 09, 2004

Revision 1: October 12, 2006

ATA System: 5141

SUBJECT: STRUCTURES - Airframe Drainage - Horizontal Stabilizer Center Section - Gutter 

Installation

This Revision includes all pages of the service bulletin.

COMPLIANCE INFORMATION RELATED TO THIS REVISION

No more work is necessary on airplanes changed as shown in the initial release of this service bulletin.

Federal Aviation Administration (FAA) Notice of Proposed Rule Making 2005-NM-058-AD is related to this 

service bulletin.

REASON FOR REVISION

This revision is sent to improve the work instructions as a result of access restrictions found during the validation 

of the related 767-200, 767-300, 767-300F service bulletin 767-51A0027. Additionally, based on one other 

operator report revision 1 is sent to provide instructions to install the gutter as a one piece assembly. Instructions 

throughout the service bulletin are changed to provide two options to install the gutter as one piece or as two 

pieces.

The related 767-200, 767-300 and 767-300F Boeing service bulletin is 767-51A0027. Service bulletin 

767-51A0027 was validated on airplane VN097. In the validation the gutter was installed in two pieces. The 

changes necessary as a result of the validation of service bulletin 767-51A0027 are included in this service 

bulletin.

Changes to this service bulletin include:

– References to a FAA Notice of Proposed Rule Making are added throughout the service bulletin.

– Material Information - A new 180T3250-9 gutter assembly is added. The 180T3250-4 gutter assembly is 

optional to the 180T3250-9 gutter assembly. The Boeing drawing number and parts modified and 

reidentified are changed. The quantity of optional rivets supplied by the operator is reduced.

– Accomplishment Instructions - An additional access door is added. Maintenance manual references to test 

the elevator control system, elevator power control actuator and autopilot systems are added. A stabilizer 

tool reference has been removed as it is acceptable to use another lock tool. A maintenance manual 

reference to install the service platform is changed.

– Figure 1 is changed to add a dimension for the gutter assembly cut location.

– Figure 2 is changed to give rework instructions if cracks are found and to add an alternative high frequency 

eddy current inspection for cracks. The two possible side brace fittings installed after the rework are 

identified.

– Figures 3 and 4 are changed to remove the option to install rivets and to change the quantity of hi loks used 

to install the gutter assembly at each hydraulic bracket.
 

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BOEING SERVICE BULLETIN 767-51A0028

– Figure 6 is added to disconnect and move the hydraulic lines at the hydraulic control brackets.

– Figure 7 is added to identify a locator mark on the gutter when installing the gutter as one piece.

– Figure 8 is added to install the gutter as one piece.

– Figure 9 is added to apply sealant between the upper spar chord and gutter when installing the gutter as 

one piece.

– Figure 10 is added to connect the hydraulic lines at the hydraulic control brackets.

Paragraph 1.A., Effectivity, shows changes of airplane operators. Each operator should examine the Effectivity 

paragraph for changes.

Vertical lines are put on the left edge of each page, except in Paragraph 1.A., Effectivity, to show the location 

of important changes.

Pages with no vertical lines have no important changes.

REVISION HISTORY

Original Issue: December 09, 2004

Revision 1: October 12, 2006
December 09, 2004

Revision 1: October 12, 2006 767-51A0028

BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. 7 of 52

Commercial

Airplane

Group 767

Service Bulletin

Number: 767-51A0028 Summary

Date: December 09, 2004

Revision 1: October 12, 2006

ATA System: 5141

SUBJECT: STRUCTURES - Airframe Drainage - Horizontal Stabilizer Center Section - Gutter 

Installation

CONCURRENT REQUIREMENTS

None.

BACKGROUND

This service bulletin gives instructions to install a gutter on the horizontal stabilizer center section. This gutter 

will channel water that enters Section 48 at the side of body seals away from the elevator control system 

components aft of the horizontal stabilizer. This will make it less likely that ice can accumulate on the elevator 

control system components. Ice on the elevator systems can restrict elevator movement which limits the ability 

of the flight crew to make elevator control inputs, resulting in reduced controllability of the airplane.

Boeing has received three reports of stiff or jammed elevator controls. Analysis of all three reports indicated that 

ice had formed on the elevator control components aft of the horizontal stabilizer, which restricted the movement 

of the elevator controls. Water was found to get into Section 48 of the airplane through the fairing panels at the 

side of the body. The ice then formed from water that had accumulated on the horizontal stabilizer center 

section. In one case, the water accumulated due to a leak in the Auxiliary Power Unit (APU) inlet duct. In another 

case, the water came from a leak in a galley water drain line.

After line number 921, a gutter is installed on the horizontal stabilizer center section in production.

Accomplishment of the modification shown in this service bulletin will make it less likely that movement of the 

elevator control system will be restricted due to the accumulation of ice on the elevator control system 

components aft of the horizontal stabilizer center section.

As a part of a service bulletin validation program, this change was completed on airplane VN097 by Service 

Bulletin 767-51A0027 before the release of Revision 1 of this service bulletin. The change completed on 

airplane VN097 by Service Bulletin 767-51A0027 is equivalent to the release of Revision 1 of this service 

bulletin.

The related 767-200, 767-300 and 767-300F Boeing service bulletin is 767-51A0027.

Boeing Service Related Problem (SRP) 767-SRP-27-0147 is related to this service bulletin.
December 09, 2004

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ACTION (PRR B12901-51S)

Get access to the horizontal stabilizer center section through the service doors 312AR and 313AL. Disconnect 

6 hydraulic lines. Rework the horizontal stabilizer side brace fittings to enlarge the drain holes.

Option 1: Install the gutter as two pieces along the rear spar upper chord of the horizontal stabilizer center 

section, on the controls brackets. Seal the gap between the gutter sections. Install two splices to re-join the 

gutter sections using shims between mating surfaces. Apply sealant between the gutter, the rear upper spar 

chord and splices.

Option 2: Install the gutter as one piece along the rear spar upper chord of the horizontal stabilizer center 

section, on the controls brackets. Apply sealant between the gutter and the rear upper spar chord.

Do system tests of the elevator control system, elevator power control actuator and autopilot systems.

EFFECTIVITY

767-400ER airplanes line number 758 through 878. Refer to Paragraph 1.A.1., Airplanes for the list of affected 

airplanes.

COMPLIANCE

Boeing recommends that operators accomplish the modifications shown in this bulletin within five years after 

the issue date of the initial release of this service bulletin.

FAA Notice of Proposed Rule Making 2005-NM-058-AD is related to this service bulletin.

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.

INDUSTRY SUPPORT INFORMATION

Boeing warranty remedies are available for airplanes in warranty as of April 27, 2001. Please refer to Paragraph 

2.B., Industry Support Information.

MANPOWER

Refer to Paragraph 1.G., Manpower.

MATERIAL INFORMATION

Boeing Supplied Kits/Parts. 

Refer to Paragraph 2.A., Material - Price and Availability.
 

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BOEING SERVICE BULLETIN 767-51A0028

STABILIZER CENTER SECTION

TO THE HORIZONTAL

INSTALL GUTTER ASSEMBLY

FWD

UP

438865
 

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BOEING SERVICE BULLETIN 767-51A0028

BLANK PAGE
December 09, 2004

Revision 1: October 12, 2006 767-51A0028

BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. 11 of 52

Commercial

Airplane

Group 767

Service Bulletin

Number: 767-51A0028

Date: December 09, 2004

Revision 1: October 12, 2006

ATA System: 5141

SUBJECT: STRUCTURES - Airframe Drainage - Horizontal Stabilizer Center Section - Gutter 

Installation

1. PLANNING INFORMATION

A. Effectivity

1. Airplanes

Refer to Service Bulletin Index Document D624T001 Part 3 for Airplane Variable Number, Line 

Number, and Serial Number data.

This service bulletin is for the airplanes shown below. An equivalent change is on subsequent 

production airplanes. Refer to PRR B12901-51S for data about this change.

Airplane models:

767-400ER

IDENTIFICATION BY CUSTOMER, CUSTOMER CODE, GROUP AND VARIABLE NUMBER

CONTINENTAL AIRLINES (CAL)

1 VQ071–VQ086

DELTA AIR LINES (DAL)

1 VQ001–VQ021

IDENTIFICATION BY VARIABLE NUMBER

GROUP CONFIGURATION DESCRIPTION

1 - 767-400ER airplanes, line number 758 through 

878.

Variable Group

VQ001–VQ021 1

VQ071–VQ086 1
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2. Spares Affected

None.

B. Concurrent Requirements

None.

C. Reason

This service bulletin gives instructions to install a gutter on the horizontal stabilizer center section. This 

gutter will channel water that enters Section 48 at the side of body seals away from the elevator control 

system components aft of the horizontal stabilizer. This will make it less likely that ice can accumulate 

on the elevator control system components. Ice on the elevator systems can restrict elevator 

movement which limits the ability of the flight crew to make elevator control inputs, resulting in reduced 

controllability of the airplane.

Boeing has received three reports of stiff or jammed elevator controls. Analysis of all three reports 

indicated that ice had formed on the elevator control components aft of the horizontal stabilizer, which 

restricted the movement of the elevator controls. Water was found to get into Section 48 of the airplane 

through the fairing panels at the side of the body. The ice then formed from water that had 

accumulated on the horizontal stabilizer center section. In one case, the water accumulated due to a 

leak in the Auxiliary Power Unit (APU) inlet duct. In another case, the water came from a leak in a 

galley water drain line.

After line number 921, a gutter is installed on the horizontal stabilizer center section in production.

Accomplishment of the modification shown in this service bulletin will make it less likely that movement 

of the elevator control system will be restricted due to the accumulation of ice on the elevator control 

system components aft of the horizontal stabilizer center section.

The related 767-200, 767-300 and 767-300F Boeing service bulletin is 767-51A0027.

Boeing Service Related Problem (SRP) 767-SRP-27-0147 is related to this service bulletin.

Revision 1 is sent to improve the work instructions as a result of access restrictions found during the 

validation of the related 767-200, 767-300, 767-300F service bulletin 767-51A0027. Additionally, 

based on one other operator report revision 1 is sent to provide instructions to install the gutter as a 

one piece assembly. Instructions throughout the service bulletin are changed to provide two options 

to install the gutter as one piece or as two pieces.

The related 767-200, 767-300 and 767-300F Boeing service bulletin is 767-51A0027. Service bulletin 

767-51A0027 was validated on airplane VN097. In the validation the gutter was installed in two pieces. 

The changes necessary as a result of the validation of service bulletin 767-51A0027 are included in 

this service bulletin.

Changes to this service bulletin include:

– References to a FAA Notice of Proposed Rule Making are added throughout the service bulletin.

– Material Information - A new 180T3250-9 gutter assembly is added. The 180T3250-4 gutter 

assembly is optional to the 180T3250-9 gutter assembly. The Boeing drawing number and parts 

modified and reidentified are changed. The quantity of optional rivets supplied by the operator is 

reduced.
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– Accomplishment Instructions - An additional access door is added. Maintenance manual 

references to test the elevator control system, elevator power control actuator and autopilot 

systems are added. A stabilizer tool reference has been removed as it is acceptable to use 

another lock tool. A maintenance manual reference to install the service platform is changed.

– Figure 1 is changed to add a dimension for the gutter assembly cut location.

– Figure 2 is changed to give rework instructions if cracks are found and to add an alternative high 

frequency eddy current inspection for cracks. The two possible side brace fittings installed after 

the rework are identified.

– Figures 3 and 4 are changed to remove the option to install rivets and to change the quantity of 

hi loks used to install the gutter assembly at each hydraulic bracket.

– Figure 6 is added to disconnect and move the hydraulic lines at the hydraulic control brackets.

– Figure 7 is added to identify a locator mark on the gutter when installing the gutter as one piece.

– Figure 8 is added to install the gutter as one piece.

– Figure 9 is added to apply sealant between the upper spar chord and gutter when installing the 

gutter as one piece.

– Figure 10 is added to connect the hydraulic lines at the hydraulic control brackets.

D. Description

Get access to the horizontal stabilizer center section through the service doors 312AR and 313AL. 

Disconnect 6 hydraulic lines. Rework the horizontal stabilizer side brace fittings to enlarge the drain 

holes.

Option 1: Install the gutter as two pieces along the rear spar upper chord of the horizontal stabilizer 

center section, on the controls brackets. Seal the gap between the gutter sections. Install two splices 

to re-join the gutter sections using shims between mating surfaces. Apply sealant between the gutter, 

the rear upper spar chord and splices.

Option 2: Install the gutter as one piece along the rear spar upper chord of the horizontal stabilizer 

center section, on the controls brackets. Apply sealant between the gutter and the rear upper spar 

chord.

Do system tests of the elevator control system, elevator power control actuator and autopilot systems.

NOTE: Boeing Service Bulletins 767-25A0323 and 767-27A0193 are also related to

767-SRP-27-0147. Boeing recommends that operators accomplish these service bulletins,

and this service bulletin, to make it less likely that movement of the elevator control system

will be restricted due to the accumulation of ice on the elevator control system components

aft of the horizontal stabilizer center section.

Revision 1 - No more work is necessary on airplanes changed as shown in the initial release of this 

service bulletin.

E. Compliance

Boeing recommends that operators accomplish the modifications shown in this bulletin within five 

years after the issue date of the initial release of this service bulletin.

FAA Notice of Proposed Rule Making 2005-NM-058-AD is related to this service bulletin.

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.
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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 modification 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 examine the work

— Time to cure the materials

— Time to make the parts

— Time to find the tools.

Option 1 - Two Piece Gutter Installation

Task

Number of 

Persons Task-Hours Elapsed Hours

Open Access 1 0.50 0.50

Figure 1 1 0.25 0.25

Figure 2 1 0.75 0.75

Figure 3 1 3.00 3.00

Figure 4 1 3.00 3.00

Figure 5 1 2.00 2.00

Figure 6 1 2.50 2.50

Figure 10 1 2.50 2.50

Close Access 1 0.50 0.50

TOTAL FOR EACH AIRPLANE 15 15

Option 2 - One Piece Gutter Installation

Task

Number of 

Persons Task-Hours Elapsed Hours

Open Access 1 0.50 0.50

Figure 2 1 0.75 0.75

Figure 6 1 2.50 2.50

Figure 7 1 0.25 0.25
 

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BOEING SERVICE BULLETIN 767-51A0028

H. Weight and Balance Changes

I. Electrical Load Data

Not changed.

J. References

1. Existing Data:

a. Engineering Change Memo PRR B12901-51S

b. Service Related Problem (SRP) 767-SRP-27-0147

c. 767 Aircraft Maintenance Manual (AMM) 06-42-00/201, 20-10-09, 20-10-10, 22-10-00/501, 

27-31-00/501, 27-31-05/601, 27-41-10/401, 29-11-00/201, 52-48-00

d. 767 Structural Repair Manual (SRM) 51-20-11

e. 767 Non-Destructive Testing (NDT) Manual, Part 6, 51-00-04, Part 6, 51-00-11, Part 6, 

51-00-16

f. Boeing Standard Overhaul Practices Manual (SOPM) Subject 20-20-02, 20-41-02, 

20-43-01, 20-43-03, 20-50-10, 20-50-19 and 20-50-20

g. Boeing Service Bulletin 767-25A0323, “EQUIPMENT/FURNISHINGS - Buffet/Galley - Aft 

Galley - A2 Galley Drain Leak Inspection” and 767-27A0193, “FLIGHT CONTROLS - 

Elevator Control System - Seal Block Hole Addition”

h. Boeing Parts Standards Document D-590

i. Boeing Drawing 012W6100 

j. FAA Notice of Proposed Rule Making 2005-NM-058-AD

Figure 8 1 4.00 4.00

Figure 9 1 0.50 0.50

Figure 10 1 2.50 2.50

Close Access 1 0.50 0.50

TOTAL FOR EACH AIRPLANE 11.5 11.5

Airplane

Change in Weight 

(Pounds)

Change in Moment 

(Pound-Inches)

767-400ER Airplanes +3.2 +6609.5

Option 2 - One Piece Gutter Installation

Task

Number of 

Persons Task-Hours Elapsed Hours
 

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BOEING SERVICE BULLETIN 767-51A0028

2. Data supplied with this Service Bulletin:

None.

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

None.

K. Publications Affected

None.

L. Interchangeability and Intermixability of Parts

Refer to Paragraph 2.C., Parts Necessary For Each Airplane, for interchangeability and intermixability 

information.
 

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2. MATERIAL INFORMATION

A. Material - Price and Availability

Boeing can supply the kits shown in Paragraph 2.C., Parts Necessary For Each Airplane as shown 

below. If there is a limit to the quantity (QTY) of available kits, a supply sequence is given by Spares. 

More kits become available as shown in the Reorder Lead Time (ROLT). ROLT is calculated from the 

date Boeing gets the purchase order.

The kit is subject to the terms and conditions of the Boeing standard purchase order acknowledgment. 

After the Unit Price date, new price data is applicable. Prices are in United States dollars. Terms: Net 

30 days.

Reference this service bulletin and submit your purchase order by one of the methods that follow: 

1. Order on-line via ATA Spec 2000 or Boeing Part Page

2. Fax to (206) 662-7145

3. Spares Customer Support - MC 36-65

Boeing Spares Department

P.O. Box 3707

Seattle, Washington 98124-2207 USA

B. Industry Support Information

Boeing warranty remedies are available for 767 airplanes in warranty as of April 27, 2001. For manhour reimbursement for airplanes in warranty as of that date, send a warranty claim to Boeing 

Commercial Airplanes Group - Warranties. The kits/parts for airplanes in warranty as of that date will 

be supplied at no charge. Send a purchase order for the kits/parts to Boeing Spares. Please refer to 

this service bulletin number and reference the airplane variable number(s) in your purchase order.

Kit Number Name Date QTY

ROLT

(Days)

Unit Price thru

Dec 31/06

015T1770-1 Top Kit 07/26/04 1 80 $ 1,902.00

09/21/04 22

10/19/04 22

11/16/04 22

12/16/04 22

01/24/05 22

02/21/05 22

03/21/05 22

04/18/05 22

05/16/05 22

06/14/05 22
 

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C. Parts Necessary For Each Airplane

1. Kits/Parts:

To get the kit shown below, refer to Paragraph 2.A., Material - Price and Availability.

NOTE: One top kit and the items shown in Paragraph 2.C.2., Parts and Materials Supplied by

the Operator, are necessary for each airplane.

Kit 015T1770 

New Part Number

QTY

Name

Existing Part 

-1 Number Notes

180T3250-9 

(180T3250-4 optional)

1 GUTTER ASSY

180T3251-2 1 SPLICE (c)

180T3251-3 1 SPLICE (c)

BACB30VT5HK3 24 BOLT, PROTRUDING HD (a) (b)

BACB30VT5HK4 9 BOLT, PROTRUDING HD (a) (b)

BACC30BL5 33 COLLAR, SHEAR (a)

BACS40R006C025F 4 SHIM, LAMINATED (a)

BACS40R007C046F 1 SHIM, LAMINATED (a)

BACS40R007D046F 2 SHIM,LAMINATED (a)

BACS40R009B015F 6 SHIM,LAMINATED (a)

BACS40R015B020F 2 SHIM, LAMINATED (a)

(a) There are more parts than are necessary.

(b) If grip length shown is not available at Boeing, fasteners supplied in kits may be 

one grip length longer than indicated. Also, if any fasteners part numbers listed are 

not available or have been superseded, substitute fasteners may be supplied in kits. 

Boeing Document D-590 and Boeing Drawing 012W6100 are used to determine the 

part numbers used as substitutes.

(c) This part is only necessary for option 1, two piece gutter installation.
 

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2. Parts and Materials Supplied by the Operator:

3. Parts Modified and Reidentified:

The parts shown below are changed as shown in this service bulletin. The quantity (QTY) is the 

number of parts changed on each airplane.

4. Parts Removed and Not Replaced:

None.

D. Parts Necessary to Change Spares

None.

E. Special Tooling - Price and Availability

None.

Part Number / 

Specification QTY Name Notes

BACR15BB5AD 16 Rivet (a)

BACR15BB5D 16 Rivet (a)

BACR15FT5AD 16 Rivet (a)

BACR15FT5D 16 Rivet (a)

BMS 10-11 1/2 pint Primer (b)

BMS 5-95, Type 1, 

Class B-1/2

1/2 pint Sealant (b)

Dye 1 ounce Dye Penetrant (b)

Alodine 1200, 

Type 2, Class A

1/2 pint Chemical Conversion Coating (b)

(a) This part is optional to BACB30VT5HK3 and BACB30VT5HK4 supplied in 

Kit 015T1770-1.

(b) See the Qualified Products List at the end of the Boeing Material 

Specification (BMS) for supplier data.

Existing Part 

Number QTY Name New Part Number Notes

182T1330-1 2 Side Brace Fitting 182T1330-3 (a) (b) (c) (d)

182T1330-2 2 Side Brace Fitting 182T1330-4 (a) (b) (c) (d)

(a) Make the change given in this service bulletin.

(b) This is the part number after the change given in this service bulletin.

(c) This part is used in production.

(d) The 182T1330-2 side brace fitting is optional to the 182T1330-1 side brace fitting.
 

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F. Special Tooling Necessary to do this Service Bulletin

No special tools or equipment are necessary to do the change in this service bulletin. But, 

maintenance and overhaul tools in the manuals given in Paragraph 1.J., References, can be 

necessary. Examine operator tool supply to make sure all necessary tools are available.
 

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3. ACCOMPLISHMENT INSTRUCTIONS

A. GENERAL INFORMATION

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. Obey all of the warnings and cautions given in the specified manual sections.

3. Unless shown differently, these dimensions and tolerances are used:

— Linear dimensions are in inches

— Tolerance on linear dimensions, other than rivet and bolt edge margins, is plus or 

minus 0.03 inch.

— Tolerance on rivet and bolt edge margin is plus or minus 0.05 inch

— Angular tolerance is plus or minus 2 degrees

— Torque limits to tighten nuts and bolts are given in 767 Structural Repair Manual, 

Chapter 51.

4. For approved fastener and process material substitutions, refer to 767 Structural Repair 

Manual, Chapter 51, Alternate fasteners are given in 767 Structural Repair Manual 

Chapter 51 and Boeing Drawing 012W6100.

5. If the length of fasteners specified in this service bulletin do not meet the installation 

standards, fasteners of the same specification, or an approved substitute, one grip 

length longer or shorter may be used.

B. WORK INSTRUCTIONS

1. Lock the horizontal stabilizer. Refer to 767 AMM 27-41-10/401.

2. Remove pressure from the Left, Right and Center hydraulic systems as shown in 

767 AMM 29-11-00/201 or equivalent approved procedure.

3. Put these switches on the right side panel, P61, in the off position and attach 

DO-NOT-OPERATE tags:

GRID SWITCH

S2 RIGHT TAIL HYD SHUT OFF VALVE SWITCH

S4 CENTER TAIL HYD SHUT OFF VALVE SWITCH

S6 LEFT TAIL HYD SHUT OFF VALVE SWICH
 

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4. Open these circuit breakers on the overhead circuit breaker panel, P11, and attach 

DO-NOT-CLOSE tags:

WARNING: BEFORE YOU BEGIN TO WORK, MAKE SURE THAT THERE IS NO MOVEMENT OF

THE HORIZONTAL STABILIZER.

WARNING: STAY OFF THE SERVICE ACCESS DOOR 312AR, AND THE ACCESS DOOR FOR

THE CONTROLS BAY 313AL. YOUR WEIGHT CAN CAUSE THE SPRING-LOADED

LATCHES TO RELEASE. IF YOU FALL THROUGH THE DOOR, INJURY CAN

OCCUR.

5. Get access to the horizontal stabilizer center section through access door 312AR and 313AL as 

shown in 767 AMM 06-42-00/201 or equivalent approved procedure.

WARNING: MAKE SURE THE SERVICE PLATFORM IS INSTALLED ABOVE THE SERVICE

ACCESS DOOR OPENING. IF YOU DO NOT INSTALL THE SERVICE PLATFORM,

YOU CAN FALL THROUGH THE SERVICE ACCESS DOOR OPENING AND INJURY

CAN OCCUR.

6. Install the service platform above the opening of the service access door as shown in 767 AMM 

52-48-00 or equivalent approved procedure.

7. Remove the hydraulic lines as given in Figure 6.

WARNING: REMOVE ALL PRESSURE FROM THE SYSTEM AS SPECIFIED IN THE APPLICABLE

MAINTENANCE INSTRUCTIONS BEFORE YOU START THE REMOVAL OF THE

FLARELESS TUBING ASSEMBLY. A PRESSURIZED SYSTEM CAN CAUSE INJURY.

WARNING: MAKE SURE EACH TUBE AND THE PORT FITTING HAVE TAGS TO IDENTIFY THE

CORRECT INSTALLATION LOCATION. IF YOU DO NOT PUT TAGS ON THE TUBES

AND PORT FITTINGS, CROSS-CONNECTION OF THE TUBES CAN OCCUR

DURING INSTALLATION. IF THIS OCCURS, UNINTENDED OPERATION OR

MALFUNCTION OF AIRPLANE SYSTEMS CAN RESULT AND CAUSE INJURY TO

PERSONS AND DAMAGE TO EQUIPMENT.

CAUTION: PUT CAPS ON THE HYDRAULIC LINES AND FITTINGS. UNWANTED MATERIAL

CAN CAUSE CONTAMINATION OF HYDRAULIC LINES, DAMAGE TO SYSTEM

COMPONENTS, AND LEAKAGE OF HYDRAULIC FLUID.

CAUTION: DO NOT LET HYDRAULIC FLUID LEAKAGE COLLECT. REMOVE IT IMMEDIATELY.

HYDRAULIC FLUID CAN CAUSE DAMAGE.

CAUTION: PUT CAPS ON THE HOSES AND FITTINGS. UNWANTED MATERIAL CAN CAUSE

CONTAMINATION OF HOSES, DAMAGE TO SYSTEM COMPONENTS, AND

LEAKAGE OF HYDRAULIC FLUID. REMOVE ALL HYDRAULIC FLUID LEAKAGE.

HYDRAULIC FLUID CAN CAUSE CORROSION OR OTHER DAMAGE.

GRID CIRCUIT BREAKER

H17 FLT CONT SHUTOFF TAIL LEFT

H18 FLT CONT SHUTOFF TAIL CENTER

H27 FLT CONT SHUTOFF TAIL RIGHT
 

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8. Do Option 1 to install the Gutter in two pieces OR do Option 2 to install the gutter as one piece.

OPTION 1 - TWO PIECE GUTTER INSTALLATION

a. Cut the gutter into two sections and finish the cut edges as given in Figure 1.

b. Rework the horizontal stabilizer side brace fittings as given in Figure 2.

c. Install left gutter section as given in Figure 3.

d. Install right gutter section as given in Figure 4.

e. Splice the gutter sections as given in Figure 5.

OPTION 2 - ONE PIECE GUTTER INSTALLATION

a. Rework the horizontal stabilizer side brace fittings as given in Figure 2.

b. Identity a locator mark on the gutter as given in Figure 7.

c. Install the gutter as given in Figure 8.

d. Seal the gutter as given in Figure 9.

CAUTION: ALWAYS KEEP THE CLAMPS TIGHT. TIGHT CLAMPS KEEP THE AREA BETWEEN

THE TUBE AND THE CLAMP SURFACES FREE OF UNWANTED MATERIALS AND

CONTAMINATION. IF SURFACES ARE NOT CLEAN, DAMAGE BY FRICTION CAN

OCCUR.

CAUTION: USE THE INDEX LINE ON THE SIDE OF THE HOSE TO MAKE SURE THE HOSE IS

NOT TWISTED. IF THE HOSE IS TWISTED, HOSE FAILURE OR HOSE COUPLING

LEAKAGE CAN OCCUR BEFORE THE USUAL TIME.

9. Install the hydraulic lines as given in Figure 10.

10. Remove the service platform and close access door 312AR and 313AL as shown in 767 AMM 

06-42-00/201 or equivalent approved procedure.

11. Close these circuit breakers on the overhead circuit breaker panel, P11, and remove 

DO-NOT-CLOSE tags:

GRID CIRCUIT BREAKER

H17 FLT CONT SHUTOFF TAIL LEFT

H18 FLT CONT SHUTOFF TAIL CENTER

H27 FLT CONT SHUTOFF TAIL RIGHT
 

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12. Put these switches on the right side panel, P61, in the ON position and remove 

DO-NOT-OPERATE tags:

13. Restore pressure to the Left, Right and Center hydraulic systems as shown in 

767 AMM 29-11-00/201 or equivalent approved procedure.

14. Unlock the horizontal stabilizer. Refer to 767 AMM 27-41-10/401.

15. Do an operational test of the elevator control system as shown in 767 AMM 27-31-00/501 or 

equivalent approved procedure and make sure that there is no leakage of hydraulic fluid.

16. Do a check of the Elevator Power Control Actuator as shown in 767 AMM 27-31-05/601 or 

equivalent approved procedure.

17. Do a systems test of the autopilot system as shown in 767 AMM 22-10-00/501 or equivalent 

approved procedure.

18. Put the airplane back to a serviceable condition.

GRID SWITCH

S2 RIGHT TAIL HYD SHUT OFF VALVE SWITCH

S4 CENTER TAIL HYD SHUT OFF VALVE SWITCH

S6 LEFT TAIL HYD SHUT OFF VALVE SWICH
 FIGURE 1: GUTTER PREPARATION AND PROTECTION

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FIGURE 1: GUTTER PREPARATION AND PROTECTION

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

numbers shown below are the number of parts necessary for each airplane.

NOTE: This figure applies to option 1, two piece gutter installation.

STEP TASK NAME PART NUMBER QTY NOTES

1 Cut Gutter Assy 180T3250-9 

(180T3250-4 optional)

1 (a)

2 Apply Chemical 

Conversion 

Coating

Type 2, Class A 2 layers To all bare aluminum surfaces. 

As given in SOPM 20-43-01.

3 Apply Primer BMS 10-11, Type 1 2 layers To all bare aluminum surfaces. 

As given in SOPM 20-41-02.

(a) Break all sharp edges, 0.015R to 0.03R.

34.0 + 0.050 -

36.0 + 0.050 -

1 2 3

438866

(SHEET 1 OF 1)
 FIGURE 2: REWORK SIDE BRACE FITTINGS - HORIZONTAL STABILIZER CENTER SECTION

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FIGURE 2: REWORK SIDE BRACE FITTINGS - HORIZONTAL STABILIZER CENTER SECTION

A

A

B

B

4.05

1.00

SIDE BRACE FITTING

UP

FWD

FWD

INBD

A-A

1 2 3 4 5

6

438867

(SHEET 1 OF 2)
 FIGURE 2: REWORK SIDE BRACE FITTINGS - HORIZONTAL STABILIZER CENTER SECTION

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

numbers shown below are the number of parts necessary for each airplane

STEP TASK NAME IDENTIFICATION QTY MORE DATA

1 Drill Drain Hole - 2 (a)

2 Deburr Drain Hole - 2

3 Inspect Drain Hole Dye Penetrant 2 (b) (c) (d)

4

Apply Chemical 

Conversion Coating, 

Type 2, Class A

Type 2, Class A - To all bare aluminum surfaces. 

As given in SOPM 20-43-03.

5 Apply Primer BMS 10-11, Type 1 - To all bare aluminum surfaces. 

As given in SOPM 20-41-02.

6

Identify Side Brace Fitting - 

Horizontal Stabilizer

182T1330-1 2 Part mark as 182T1330-3 as shown in 

SOPM 20-50-10. (e)

OR

182T1330-2 2 Part mark as 182T1330-4 as shown in 

SOPM 20-50-10. (e)

(a) Enlarge the existing drain hole to a 0.500 - 0.504 inch diameter. Blend any sharp edges created at the 

intersection of the hole and the fitting wall radius.

(b) Inspect drain hole for cracks. Refer to SOPM 20-20-02.

(c) It is optional to do a high frequency eddy current inspection for cracks as shown in 767 NDT, Part 6, 

51-00-04 or 767 NDT, Part 6, 51-00-11 or 767 NDT, Part 6, 51-00-16, instead of a dye penetrant inspection.

(d) If cracks or damage are found oversize the hole to remove the crack or damage. Hole size up to 0.625 

inches in diameter is acceptable. If damage still remains at a hole size of 0.625 inches contact Boeing with 

details of the damage for further rework instructions.

(e) The 182T1330-2 side brace fitting is optional to the 182T1330-1 side brace fitting.

4.05

1.00

SIDE BRACE FITTING

B-B

1 2 3 4 5

6

INBD

FWD

438868

(SHEET 2 OF 2)
 FIGURE 3: GUTTER INSTALLATION - UPPER SURFACE, HORIZONTAL STABILIZER CENTER SECTION - LEFT SIDE

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FIGURE 3: GUTTER INSTALLATION - UPPER SURFACE, HORIZONTAL STABILIZER CENTER SECTION 

- LEFT SIDE

0.02

0.08

LEFT GUTTER

1.65

RIGHT GUTTER

OF GAP

CENTER LINE

BRACKET

HYDRAULIC

B

B

D

D

A

A

C

C

INBD

FWD

UP

1

1 2

(3 LOCATIONS)

HYDRAULIC BRACKET

438870

A-A

(SHEET 1 OF 4)
 FIGURE 3: GUTTER INSTALLATION - UPPER SURFACE, HORIZONTAL STABILIZER CENTER SECTION - LEFT SIDE

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INBD

BRACKET

HYDRAULIC

BRACKET

CONTROLS

GUTTER

C-C

B-B

FWD

3 3

4 5

7 8

6

4 5

438871

(SHEET 2 OF 4)
 FIGURE 3: GUTTER INSTALLATION - UPPER SURFACE, HORIZONTAL STABILIZER CENTER SECTION - LEFT SIDE

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

numbers shown below are the number of parts necessary for each airplane.

NOTE: This figure applies to option 1, two piece gutter installation.

STEP TASK NAME IDENTIFICATION QTY MORE DATA

1 Align Gutter Sections

(Left and Right)

180T3250-9 

(180T3250-4 optional)

2 (a)

2 Remove / 

Keep

Gutter Section (Right) 180T3250-9 

(180T3250-4 optional)

1

3 Align Shim, Laminated BACS40R006C025F 2 (c)

4 Drill Controls bracket - 1 (b) 0.164 - 0.168 inch 

hole diameter. Shim, Laminated BACS40R006C025F 2

Gutter Section (Left) 180T3250-9 

(180T3250-4 optional)

1

5 Install Gutter Section (Left) 180T3250-9 

(180T3250-4 optional)

1

Shim, Laminated BACS40R006C025F 2

Bolt BACB30VT5HK3 4

Collar BACC30BL5 4

6 Align Shim, Laminated BACS40R007D046F 1 (c)

HYDRAULIC BRACKET

GUTTER

D-D

9 10 11

438872

(SHEET 3 OF 4)
 FIGURE 3: GUTTER INSTALLATION - UPPER SURFACE, HORIZONTAL STABILIZER CENTER SECTION - LEFT SIDE

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7 Drill Hydraulic Bracket - 1 (b) 0.164 - 0.168 inch 

hole diameter. Shim, Laminated BACS40R007D046F 1

Gutter Section (Left) 180T3250-9 

(180T3250-4 optional)

1

8 Install Shim, Laminated BACS40R007D046F 1 (d)

Gutter Section (Left) 180T3250-9 

(180T3250-4 optional)

1

Bolt BACB30VT5HK4 2

Collar BACC30BL5 2

9 Align Shim, Laminated BACS40R007C046F 1 (c)

10 Drill Hydraulic Bracket - 1 (b) 0.164 - 0.168 inch 

hole diameter. Shim, Laminated BACS40R007C046F 1

Gutter Section (Left) 180T3250-9 

(180T3250-4 optional)

1

11 Install Shim, Laminated BACS40R007C046F 1 (d)

Gutter Section (Left) 180T3250-9 

(180T3250-4 optional)

1

Bolt BACB30VT5HK4 2

Collar BACC30BL5 2

(a) Align the 36 inch section on the left side and the 34 inch section on the right side with an equal clearance 

on either end from the stabilizer hinges, and a gap of 0.08 +/- 0.02 inches between the left and right gutter 

sections.

(b) Make sure there is a minimum 2 D edge margin at fastener locations. Deburr all sharp edges.

(c) Shim gaps greater than 0.010 inches prior to installation. Remove 0.003 inch laminations as required. 

Refer to SOPM 20-50-20 and 767 SRM 51-20-11. Optional solid shim stock and multiple shims can be used 

to prevent bending the bracket and gutter flanges during installation.

(d) Install collars on the upper surface of the gutter. This is to prevent interference between the bolts and

hydraulic lines.

STEP TASK NAME IDENTIFICATION QTY MORE DATA

(SHEET 4 OF 4)
 FIGURE 4: GUTTER INSTALLATION - UPPER SURFACE, HORIZONTAL STABILIZER CENTER SECTION - RIGHT SIDE

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FIGURE 4: GUTTER INSTALLATION - UPPER SURFACE, HORIZONTAL STABILIZER CENTER SECTION 

- RIGHT SIDE

B B

A

A

C

C

UP

FWD

A-A 2 INBD 2

1

1

(3 LOCATIONS)

HYDRAULIC BRACKET

438873

(SHEET 1 OF 3)
 FIGURE 4: GUTTER INSTALLATION - UPPER SURFACE, HORIZONTAL STABILIZER CENTER SECTION - RIGHT SIDE

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BRACKET

HYDRAULIC

BRACKET

CONTROLS

GUTTER

HYDRAULIC BRACKET

GUTTER GUTTER

3 4

6 7

5

8

FWD

UP

3 4

438874

B-B

C-C

(SHEET 2 OF 3)
 FIGURE 4: GUTTER INSTALLATION - UPPER SURFACE, HORIZONTAL STABILIZER CENTER SECTION - RIGHT SIDE

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

numbers shown below are the number of parts necessary for each airplane.

NOTE: This figure applies to option 1, two piece gutter installation.

STEP TASK NAME IDENTIFICATION QTY MORE DATA

1 Align Gutter Section

(Left and Right)

180T3250-9 

(180T3250-4 optional)

2 (a)

2 Align Shim, Laminated BACS40R006C025F 2 (c)

3 Drill Controls bracket - 1 (b) 0.164 - 0.168 inch hole 

diameter. Shim, Laminated BACS40R006C025F 2

Gutter Section (Right) 180T3250-9 

(180T3250-4 optional)

1

4 Install Gutter Section (Right) 180T3250-9 

(180T3250-4 optional)

1

Shim, Laminated BACS40R006C025F 2

Bolt BACB30VT5HK3 4

Collar BACC30BL5 4

5 Align Shim, Laminated BACS40R007D046F 1 (c)

6 Drill Hydraulic Bracket - 1 (b) 0.164 - 0.168 inch hole 

diameter. Shim, Laminated BACS40R007D046F 1

Gutter Section (Right) 180T3250-9 

(180T3250-4 optional)

1

7 Install Shim, Laminated BACS40R007D046F 1 (d)

Gutter Section (Right) 180T3250-9 

(180T3250-4 optional)

1

Bolt BACB30VT5HK3 2

Collar BACC30BL5 2

8 Apply Sealant BMS 5-95 - Completely fill the gap 

between gutter sections. 

Refer to SOPM 20-50-19.

(a) Align the right gutter section with a gap of 0.08 +/- 0.02 inches between the left and right gutter sections. 

Make sure that the distance between the left gutter and left stabilizer hinge is equal to the distance between 

the right gutter and right stabilizer hinge.

(b) Make sure there is a minimum 2 D edge margin at fastener locations. Deburr all sharp edges.

(c) Shim gaps greater than 0.010 inches prior to installation. Remove 0.003 inch laminations as required. 

Refer to SOPM 20-50-20 and 767 SRM 51-20-11

(d) Install collars on the upper surface of the gutter. This is to prevent interference between the bolts and

hydraulic lines.

(SHEET 3 OF 3)
 FIGURE 5: SPLICE INSTALLATION - HORIZONTAL STABILIZER CENTER SECTION

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FIGURE 5: SPLICE INSTALLATION - HORIZONTAL STABILIZER CENTER SECTION

B

B

A

A

UP

FWD

A-A

0.1500 +0.0500

-0.1000

BRACKET

HYDRAULIC

GUTTER

BRACKET

CONTROL

1

(3 LOCATIONS)

HYDRAULIC BRACKET

438875

(SHEET 1 OF 5)
 FIGURE 5: SPLICE INSTALLATION - HORIZONTAL STABILIZER CENTER SECTION

December 09, 2004

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BOEING SERVICE BULLETIN 767-51A0028

E

E

C

C

FWD D D

8 C-C

HYDRAULIC BRACKET

GUTTER

5

6 7 6 7

438876

B-B

(SHEET 2 OF 5)
 FIGURE 5: SPLICE INSTALLATION - HORIZONTAL STABILIZER CENTER SECTION

December 09, 2004

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BOEING SERVICE BULLETIN 767-51A0028

HYDRAULIC BRACKET

GUTTER

GUTTER

2

3

2

4

3 4

3 4

438877

E-E

D-D

(SHEET 3 OF 5)
 FIGURE 5: SPLICE INSTALLATION - HORIZONTAL STABILIZER CENTER SECTION

December 09, 2004

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BOEING SERVICE BULLETIN 767-51A0028

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

numbers shown below are the number of parts necessary for each airplane.

NOTE: This figure applies to option 1, two piece gutter installation.

STEP TASK NAME IDENTIFICATION QTY MORE DATA

CAUTION: DO NOT ALLOW THE SEALANT TO CREATE HIGH SPOTS OR RIDGES THAT WILL

TRAP WATER ONTO THE UPPER SKIN.

1 Apply Sealant BMS 5-95 - (a)

2 Align (New) Splice 180T3251-2 1 Align splice and shims 

to Gutter Assembly.

Shim, Laminated BACS40R015B020F 2 On the vertical edge of 

the gutter. (c)

Shim, Laminated BACS40R009B015F 2 On the lower edge of 

the gutter. (c)

3 Drill Splice 180T3251-2 1 (b) (c)

0.164 - 0.168 inch hole 

diameter. Shim, Laminated BACS40R015B020F 2

Shim, Laminated BACS40R009B015F 2

Gutter Section

(left and Right)

180T3250-9 

(180T3250-4 optional)

2

4 Install Splice 180T3251-2 1 (c) (e)

Shim, Laminated BACS40R015B020F 2

Shim, Laminated BACS40R009B015F 2

Bolt

(Rivet)

BACB30VT5HK3 or

BACR15BB5AD (optional) or

BACR15BB5D (optional) 

BACR15FT5AD (optional) or

BACR15FT5D (optional)

12

Collar BACC30BL5 12

5 Align (New) Splice 180T3251-3 1 Align splice to Gutter 

Assembly.

6 Drill Splice 180T3251-3 1 (b) (c)

0.164 - 0.168 inch hole 

diameter.

Gutter Section

(left and Right)

180T3250-9 

(180T3250-4 optional)

2

7 Install Splice 180T3251-3 1 (c) (e)

Bolt

(Rivet)

BACB30VT5HK3 or

BACR15BB5AD (optional) or

BACR15BB5D (optional) or

BACR15FT5AD (optional) or

BACR15FT5D (optional)

4

Collar BACC30BL5 4

8 Apply Sealant BMS 5-95 - (d)

(SHEET 4 OF 5)
 FIGURE 5: SPLICE INSTALLATION - HORIZONTAL STABILIZER CENTER SECTION

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BOEING SERVICE BULLETIN 767-51A0028

(a) Inject sealant BMS 5-95 per SOPM 20-50-19 to fill void created beneath the three hydraulic brackets 

and the upper spar chord. Apply BMS 5-95 sealant per SOPM 20-50-19 at final installation of gutter to 

completely fill faying surfaces between upper spar chord and gutter, and to fair the upper skin to the 

forward flange of the gutter the entire length of the gutter. Allow sealant to dry for 2 hours.

(b) Make sure there is a minimum 2 D edge margin at fastener locations. Deburr all sharp edges.

(c) Shim gaps greater than 0.010 inches prior to installation. Remove 0.003 inch laminations as required. 

Refer to SOPM 20-50-20 and 767 SRM 51-20-11. Optional solid shim stock and multiple shims can be 

used to prevent bending the bracket and gutter flanges during installation

(d) Inject sealant BMS 5-95 per SOPM 20-50-19 to fill void between gutter and splice.

(e) It is acceptable to use solid rivets instead of bolts and collars. Install rivets in a 0.159 - 0.171 inch hole 

diameter.

STEP TASK NAME IDENTIFICATION QTY MORE DATA

(SHEET 5 OF 5)
 FIGURE 6: DISCONNECT HYDRAULIC LINES - HORIZONTAL STABILIZER CENTER SECTION

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BOEING SERVICE BULLETIN 767-51A0028

FIGURE 6: DISCONNECT HYDRAULIC LINES - HORIZONTAL STABILIZER CENTER SECTION

41.5

RBBL

41.5

LBBL

0

BBL

UP

FWD

1

3

7

9

5

2

4

6

8

12

10

11

J74432

(SHEET 1 OF 2)
 FIGURE 6: DISCONNECT HYDRAULIC LINES - HORIZONTAL STABILIZER CENTER SECTION

December 09, 2004

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BOEING SERVICE BULLETIN 767-51A0028

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

numbers shown below are the number of parts necessary for each airplane.

STEP TASK NAME IDENTIFICATION QTY MORE DATA

1

Remove/Keep Hydraulic tube 272T8200-188 1 Refer to 767 AMM 

20-10-09 or equivalent 

approved procedure.

2 Disconnect Hydraulic hose AS115-06D0274 1 (a)

3

Remove/Keep Hydraulic tube 272T8200-187 1 Refer to 767 AMM 

20-10-09 or equivalent 

approved procedure.

4 Disconnect Hydraulic hose AS115-08D0280 1 (a)

5

Remove/Keep Hydraulic tube 272T8200-202 1 Refer to 767 AMM 

20-10-09 or equivalent 

approved procedure.

6 Disconnect Hydraulic hose AS115-06D0274 1 (a)

7

Remove/Keep Hydraulic tube 272T8200-203 1 Refer to 767 AMM 

20-10-09 or equivalent 

approved procedure.

8 Disconnect Hydraulic hose AS115-08D0274 1 (a)

9

Remove/Keep Hydraulic tube 272T8200-186 1 Refer to 767 AMM 

20-10-09 or equivalent 

approved procedure.

10 Disconnect Hydraulic hose AS115-06D0274 1 (a)

11

Remove/Keep Hydraulic tube 272T8200-185 1 Refer to 767 AMM 

20-10-09 or equivalent 

approved procedure.

12 Disconnect Hydraulic hose AS115-08D0280 1 (a)

(a) Refer to 767 AMM 20-10-10 or equivalent approved procedure. Move the hydraulic line away from the 

modification area.

(SHEET 2 OF 2)
 FIGURE 7: GUTTER PREPARATION - LOCATOR IDENTIFICATION

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BOEING SERVICE BULLETIN 767-51A0028

FIGURE 7: GUTTER PREPARATION - LOCATOR IDENTIFICATION

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

numbers shown below are the number of parts necessary for this figure.

NOTE: This figure applies to option 2, one piece gutter installation.

STEP TASK NAME IDENTIFICATION QTY MORE DATA

1

Identify Locator Mark - 1 As a reference for 

subsequent installation 

alignment. (a)

(a) Use a method that does not damage the gutter or surface finish on the gutter.

34.35 + 0.050 -

1

U74059

(SHEET 1 OF 1)
 FIGURE 8: GUTTER INSTALLATION - UPPER SURFACE, HORIZONTAL STABILIZER CENTER SECTION

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BOEING SERVICE BULLETIN 767-51A0028

FIGURE 8: GUTTER INSTALLATION - UPPER SURFACE, HORIZONTAL STABILIZER CENTER SECTION

GUTTER

BRACKET

HYDRAULIC

B

B

D

D

A

A

C

C

E

E

F

F

INBD

FWD

UP

1

1

(3 LOCATIONS)

HYDRAULIC BRACKET

U74045

A-A

(SHEET 1 OF 6)
 FIGURE 8: GUTTER INSTALLATION - UPPER SURFACE, HORIZONTAL STABILIZER CENTER SECTION

December 09, 2004

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BOEING SERVICE BULLETIN 767-51A0028

INBD

BRACKET

HYDRAULIC

BRACKET

CONTROLS

GUTTER

C-C

B-B

FWD

2 2

3 4

8 9

7

3 4

U74048

(SHEET 2 OF 6)
 FIGURE 8: GUTTER INSTALLATION - UPPER SURFACE, HORIZONTAL STABILIZER CENTER SECTION

December 09, 2004

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BOEING SERVICE BULLETIN 767-51A0028

HYDRAULIC BRACKET

GUTTER

D-D

E-E INBD

10 11 12

2 2

U74050

(SHEET 3 OF 6)
 FIGURE 8: GUTTER INSTALLATION - UPPER SURFACE, HORIZONTAL STABILIZER CENTER SECTION

December 09, 2004

Revision 1: October 12, 2006 767-51A0028

BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. 46 of 52

BOEING SERVICE BULLETIN 767-51A0028

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

numbers shown below are the number of parts necessary for this figure.

NOTE: This figure applies to option 2, one piece gutter installation.

STEP TASK NAME IDENTIFICATION QTY MORE DATA

CAUTION: DO NOT TO DAMAGE THE GUTTER AND ADJACENT STRUCTURE. MORE WORK WILL BE 

NECESSARY FOR REPAIRS IF THE GUTTER OR ADJACENT STRUCTURE IS DAMAGED.

1 Align Gutter Assembly 180T3250-9 

(180T3250-4 optional)

2 (a)

2 Align Shim, Laminated BACS40R006C025F 4 (b)

3 Drill Controls bracket - 1 (c) 0.164 - 0.168 inch 

hole diameter. Shim, Laminated BACS40R006C025F 2

Gutter Assembly 180T3250-9 

(180T3250-4 optional)

1

4 Install Gutter Assembly 180T3250-9 

(180T3250-4 optional)

1

Shim, Laminated BACS40R006C025F 2

Bolt BACB30VT5HK3 4

Collar BACC30BL5 4

5 Drill Controls bracket - 1 (c) 0.164 - 0.168 inch 

hole diameter. Shim, Laminated BACS40R006C025F 2

Gutter Assembly 180T3250-9 

(180T3250-4 optional)

1

BRACKET

HYDRAULIC

BRACKET

CONTROLS

GUTTER

5 6

INBD

FWD

5 6

14 15

13

U74052

F-F

(SHEET 4 OF 6)
 FIGURE 8: GUTTER INSTALLATION - UPPER SURFACE, HORIZONTAL STABILIZER CENTER SECTION

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BOEING SERVICE BULLETIN 767-51A0028

6 Install Gutter Assembly 180T3250-9 

(180T3250-4 optional)

1

Shim, Laminated BACS40R006C025F 2

Bolt BACB30VT5HK3 4

Collar BACC30BL5 4

7 Align Shim, Laminated BACS40R007D046F 1 (b)

8 Drill Hydraulic Bracket - 1 (c) 0.164 - 0.168 inch 

hole diameter. Shim, Laminated BACS40R007D046F 1

Gutter Assembly 180T3250-9 

(180T3250-4 optional)

1

9 Install Shim, Laminated BACS40R007D046F 1 (d)

Gutter Assembly 180T3250-9 

(180T3250-4 optional)

1

Bolt BACB30VT5HK4 2

Collar BACC30BL5 2

10 Align Shim, Laminated BACS40R007C046F 1 (b)

11 Drill Hydraulic Bracket - 1 (c) 0.164 - 0.168 inch 

hole diameter. Shim, Laminated BACS40R007C046F 1

Gutter Assembly 180T3250-9 

(180T3250-4 optional)

1

12 Install Shim, Laminated BACS40R007C046F 1 (d)

Gutter Assembly 180T3250-9 

(180T3250-4 optional)

1

Bolt BACB30VT5HK4 2

Collar BACC30BL5 2

13 Align Shim, Laminated BACS40R007D046F 1 (b)

14 Drill Hydraulic Bracket - 1 (c) 0.164 - 0.168 inch 

hole diameter. Shim, Laminated BACS40R007D046F 1

Gutter Assembly 180T3250-9 

(180T3250-4 optional)

1

15 Install Shim, Laminated BACS40R007D046F 1 (d)

Gutter Assembly 180T3250-9 

(180T3250-4 optional)

1

Bolt BACB30VT5HK4 2

Collar BACC30BL5 2

(a) Align the locator mark to the right side edge of the hydraulic bracket when looking forward.

STEP TASK NAME IDENTIFICATION QTY MORE DATA

(SHEET 5 OF 6)
 FIGURE 8: GUTTER INSTALLATION - UPPER SURFACE, HORIZONTAL STABILIZER CENTER SECTION

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BOEING SERVICE BULLETIN 767-51A0028

(b) Shim gaps greater than 0.010 inches prior to installation. Remove 0.003 inch laminations as required. 

Refer to SOPM 20-50-20 and 767 SRM 51-20-11. Optional solid shim stock and multiple shims can be used 

to prevent bending the bracket and gutter flanges during installation.

(c) Make sure there is a minimum 2 D edge margin at fastener locations. Deburr all sharp edges.

(d) Install collars on the upper surface of the gutter. This is to prevent interference between the bolts and 

hydraulic lines.

STEP TASK NAME IDENTIFICATION QTY MORE DATA

(SHEET 6 OF 6)
 FIGURE 9: GUTTER SEALING - HORIZONTAL STABILIZER CENTER SECTION

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BOEING SERVICE BULLETIN 767-51A0028

FIGURE 9: GUTTER SEALING - HORIZONTAL STABILIZER CENTER SECTION

A

A

UP

FWD

A-A

0.1500 +0.0500

-0.1000

BRACKET

HYDRAULIC

GUTTER

BRACKET

CONTROL

1

U74054

(SHEET 1 OF 2)
 FIGURE 9: GUTTER SEALING - HORIZONTAL STABILIZER CENTER SECTION

December 09, 2004

Revision 1: October 12, 2006 767-51A0028

BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. 50 of 52

BOEING SERVICE BULLETIN 767-51A0028

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

numbers shown below are the number of parts necessary for this figure.

NOTE: This figure applies to option 2, one piece gutter installation.

STEP TASK NAME IDENTIFICATION QTY MORE DATA

CAUTION: DO NOT ALLOW THE SEALANT TO CREATE HIGH SPOTS OR RIDGES THAT WILL

TRAP WATER ONTO THE UPPER SKIN.

1 Apply Sealant BMS 5-95 - (a)

(a) Inject sealant BMS 5-95 per SOPM 20-50-19 to fill void created beneath the three hydraulic brackets 

and the upper spar chord. Apply BMS 5-95 sealant per SOPM 20-50-19 at final installation of gutter to 

completely fill faying surfaces between upper spar chord and gutter, and to fair the upper skin to the 

forward flange of the gutter the entire length of the gutter. Allow sealant to dry for 2 hours.

(SHEET 2 OF 2)
 FIGURE 10: CONNECT HYDRAULIC LINES - HORIZONTAL STABILIZER CENTER SECTION

December 09, 2004

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BOEING SERVICE BULLETIN 767-51A0028

FIGURE 10: CONNECT HYDRAULIC LINES - HORIZONTAL STABILIZER CENTER SECTION

41.5

RBBL

41.5

LBBL

0

BBL

UP

FWD

1

3

7

9

5

2

4

6

8

12

10

11

J74433

(SHEET 1 OF 2)
 FIGURE 10: CONNECT HYDRAULIC LINES - HORIZONTAL STABILIZER CENTER SECTION

December 09, 2004

Revision 1: October 12, 2006 767-51A0028

BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. 52 of 52

BOEING SERVICE BULLETIN 767-51A0028

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

numbers shown below are the number of parts necessary for each airplane.

STEP TASK NAME IDENTIFICATION QTY MORE DATA

1

Install (kept) Hydraulic tube 272T8200-188 1 Refer to 767 AMM 

20-10-09 or equivalent 

approved procedure.

2

Connect Hydraulic hose AS115-06D0274 1 Refer to 767 AMM 

20-10-10 or equivalent 

approved procedure.

3

Install (kept) Hydraulic tube 272T8200-187 1 Refer to 767 AMM 

20-10-09 or equivalent 

approved procedure.

4

Connect Hydraulic hose AS115-08D0280 1 Refer to 767 AMM 

20-10-10 or equivalent 

approved procedure.

5

Install (kept) Hydraulic tube 272T8200-202 1 Refer to 767 AMM 

20-10-09 or equivalent 

approved procedure.

6

Connect Hydraulic hose AS115-06D0274 1 Refer to 767 AMM 

20-10-10 or equivalent 

approved procedure.

7

Install (kept) Hydraulic tube 272T8200-203 1 Refer to 767 AMM 

20-10-09 or equivalent 

approved procedure.

8

Connect Hydraulic hose AS115-08D0274 1 Refer to 767 AMM 

20-10-10 or equivalent 

approved procedure.

9

Install (kept) Hydraulic tube 272T8200-186 1 Refer to 767 AMM 

20-10-09 or equivalent 

approved procedure.

10

Connect Hydraulic hose AS115-06D0274 1 Refer to 767 AMM 

20-10-10 or equivalent 

approved procedure.

11

Install (kept) Hydraulic tube 272T8200-185 1 Refer to 767 AMM 

20-10-09 or equivalent 

approved procedure.

12

Connect Hydraulic hose AS115-08D0280 1 Refer to 767 AMM 

20-10-10 or equivalent 

approved procedure.

(SHEET 2 OF 2)