Commercial

Airplanes 747

Service Bulletin

Number: 747-27A2513

Original Issue: February 04, 2014

Revision 1: July 18, 2014

ATA System: 2731 2900 5510

SUBJECT: FLIGHT CONTROLS - Elevator Control System - Inboard Elevator Compensator

Installation and Power Control Package Replacement

Export of this technology is controlled under the United States Export Administration Regulations (EAR) (15

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persons from specific countries. The controller of this data has the individual responsibility to abide by all export

laws.

ECCN: 9E991

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BLANK PAGE
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 . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 13

G. Manpower . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 13

H. Weight and Balance Changes . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 14

I. Electrical Load Data . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 14

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

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

2. Data Supplied with this Service Bulletin: . . . . . . . . . . . . . . . . . . . . . . . . . . . 15

3. Installation Drawings Used in the Preparation of this Service Bulletin: . . . . . . . . . . . 15

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

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

M. Software Accomplishment Summary . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 16

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

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

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

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

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

2. Parts and Materials Supplied by the Operator . . . . . . . . . . . . . . . . . . . . . . . . 24

3. Parts Modified and Reidentified . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 25

4. Parts Removed and Not Replaced . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 25

D. Parts Necessary to Change Spares . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 25

E. Special Tooling - Price and Availability . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 25

F. Special Tooling Necessary to do this Service Bulletin . . . . . . . . . . . . . . . . . . . . . . . 25

3. ACCOMPLISHMENT INSTRUCTIONS . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 27

A. GENERAL INFORMATION . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 27

B. WORK INSTRUCTIONS . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 28

FIGURE 1: INBOARD ELEVATOR POWER CONTROL PACKAGE (PCP) AND HYDRAULIC TUBES

REMOVAL - LEFT SIDE . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 30

FIGURE 2: LOOSEN THE WIRE BUNDLE W1656 AND W4615 - LEFT SIDE . . . . . . . . . . . . . 34

FIGURE 3: FASTENERS AND BRACKETS REMOVAL - LEFT SIDE . . . . . . . . . . . . . . . . . . 36

FIGURE 4: INBOARD COMPENSATOR MOUNTING BRACKET INSTALLATION - LEFT SIDE . . . . 39

FIGURE 5: OUTBOARD COMPENSATOR MOUNTING BRACKET INSTALLATION - LEFT SIDE . . 47

FIGURE 6: COMPENSATORS AND HYDRAULIC TUBES INSTALLATION - LEFT SIDE . . . . . . . 55

FIGURE 7: WIRE BUNDLE W1656 AND W4615 ROUTING - LEFT SIDE . . . . . . . . . . . . . . . . 61

FIGURE 8: INBOARD ELEVATOR POWER CONTROL PACKAGE (PCP) INSTALLATION - LEFT SIDE

. . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 64

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BOEING SERVICE BULLETIN 747-27A2513
FIGURE 9: INBOARD ELEVATOR POWER CONTROL PACKAGE (PCP) AND HYDRAULIC TUBES

REMOVAL - RIGHT SIDE . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 68

FIGURE 10: LOOSEN THE WIRE BUNDLE W1912 AND W4616 - RIGHT SIDE . . . . . . . . . . . . 73

FIGURE 11: FASTENERS AND BRACKETS REMOVAL - RIGHT SIDE . . . . . . . . . . . . . . . . . 75

FIGURE 12: INBOARD COMPENSATOR MOUNTING BRACKET INSTALLATION - RIGHT SIDE . . . 78

FIGURE 13: OUTBOARD COMPENSATOR MOUNTING BRACKET INSTALLATION - RIGHT SIDE . 85

FIGURE 14: BRACKET INSTALLATION - RIGHT SIDE . . . . . . . . . . . . . . . . . . . . . . . . . . 92

FIGURE 15: COMPENSATORS AND HYDRAULIC TUBES INSTALLATION - RIGHT SIDE . . . . . . 95

FIGURE 16: WIRE BUNDLE W1912 AND W4616 ROUTING - RIGHT SIDE . . . . . . . . . . . . . . 102

FIGURE 17: INBOARD ELEVATOR POWER CONTROL PACKAGE (PCP) INSTALLATION - RIGHT SIDE

. . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 105

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BOEING SERVICE BULLETIN 747-27A2513
Commercial

Airplanes 747

Service Bulletin

Revision Transmittal Sheet Number: 747-27A2513

Original Issue: February 04, 2014

Revision 1: July 18, 2014

ATA System: 2731 2900 5510

SUBJECT: FLIGHT CONTROLS - Elevator Control System - Inboard Elevator Compensator

Installation and Power Control Package Replacement

This revision includes all pages of the service bulletin.

COMPLIANCE INFORMATION RELATED TO THIS REVISION

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.

No more work is necessary on the airplanes changed in accordance with the original issue of this service bulletin.

REASON FOR REVISION

This revision is sent to make corrections to fastener length and wire clamp size, revised the manpower as found

during the service bulletin validation.

As a part of a service bulletin validation program, this change was completed on airplane RC008 by Service

Bulletin 747-27A2513, Original Issue, before the release of Revision 1 of this service bulletin. The change

completed on airplane RC008 by Service Bulletin 747-27A2513 Original Issue is equivalent to the release of

Revision 1 of this service bulletin. Airplane RC008 has the configuration of a Group 1 airplane.

These sections were changed:

1. Paragraph 1.A.1., Airplanes: Removed the Notes paragraph.

2. Paragraph 1.G., Manpower: Changed the task hour table.

3. Paragraph 1.J.1., References: Revised Existing Data step h and i.

4. Paragraph 2.B., Industry Support Information: Changed the warranty statement

5. Paragraph 2.C.1., Kits/Parts: Changed the part numbers, added extra quantity to the kit, and added

the foot note (c).

6. Paragraph 2.C.2., Parts and Materials Supplied by the Operator: Changed the part number.

7. Figures 2 and 10: Revised the step table to add foot note (a).

8. Figures 4 and 7: Changed the step table and fastener table to correct the fastener length and clamp

size, and added extra quantity to the extra parts table.

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9. Figures 5: Changed sheet 2, step table, and added extra quantity to the extra parts table.

10. Figure 6: Changed sheet 2, step table, and added extra quantity to the extra parts table. Revised the

foot note (d).

11. Figure 8: Changed sheet 1.

12. Figures 9: Changed the step table.

13. Figures 12, 13, 14 and 16: Changed the step table and fastener table to correct the fastener length

and clamp size and added extra quantity to the extra parts table.

14. Figure 15: Changed sheet 3, step table and added extra quantity to the extra parts table. Revised the

foot note (d).

The data given in Information Notices 747-27A2513 IN 01 is included in this revision.

Vertical lines are put on the left edge of each page, except in Paragraph 1.A., Effectivity and format changes,

to show the location of all content changes.

Pages with no vertical lines have no changes.

REVISION HISTORY

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BOEING SERVICE BULLETIN 747-27A2513
Commercial

Airplanes 747

Service Bulletin

Summary Number: 747-27A2513

Original Issue: February 04, 2014

Revision 1: July 18, 2014

ATA System: 2731 2900 5510

SUBJECT: FLIGHT CONTROLS - Elevator Control System - Inboard Elevator Compensator

Installation and Power Control Package Replacement

CONCURRENT REQUIREMENTS

None.

BACKGROUND

The change given in this service bulletin will help to prevent divergent flutter or unacceptable vibration that can

occur in certain parts of the flight envelope if two hydraulic systems are not functional. Divergent flutter could

result in the possible loss of control of the airplane.

Boeing analysis found that the existing internal compensators to the two inboard elevator power control package

(PCP) provided insufficient hydraulic capacity for retained stiffness of the elevator surface when two hydraulic

systems are not functional. This service bulletin installs two (2) larger external compensators for each of the two

(2) inboard elevator PCP. This replacement provides sufficient hydraulic capacity to prevent divergent flutter or

unacceptable vibration.

This service bulletin also refers to a Parker service bulletin. The Parker service bulletin gives instructions to

rework the existing inboard elevator PCP that has internal compensators into the new inboard elevator PCP

with internal compensators removed. This service bulletin gives instructions to replace the existing PCP internal

compensators with larger external compensators and new design of inboard elevator PCP. Replace existing

brackets and hydraulic tubing to accommodate the new external compensators.

Boeing Service Related Problem (SRP) 747-SRP-27-0235 is related to this service bulletin.

Boeing Fleet Team Digest (FTD) 747 FTD 27-13004 is related to this service bulletin.

This table is provided to operators for planning purposes only. Refer to the applicable sections for more

information.

Planning Data Affected Reference

Spares Affected Yes Paragraph 1.A.2., Spares Affected

Paragraph 1.E., Compliance and Paragraph

1.F., Approval

AD Related Yes

Weight and Balance Change Yes Paragraph 1.H., Weight and Balance Changes

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

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Planning Data Affected Reference

Publications Affected Yes Paragraph 1.K., Publications Affected

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

Operations Manual and/or FAA Approved Airplane Flight Manual)

Kits/Parts Required Yes Paragraph 2.C.1., Kits/Parts

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

by the Operator

Operator Supplied Parts/Material Yes

Paragraph 2.F., Special Tooling Necessary to

do this Service Bulletin

Special Tooling Required No

ACTION (PRR 86601-5)

Open access to the left and right inboard elevator PCP. Remove the inboard elevator PCP, hydraulic tubes and

associated hardware. Remove the clamps and loosen the wire bundles. Remove the existing electrical brackets

and rivets. Install inboard and outboard compensator mounting brackets. Install inboard and outboard

compensators, and hydraulic tubes. Route the wire bundles. Install inboard elevator PCP. Bleed the hydraulic

systems. Do the operational test. Close access to the left and right inboard elevator PCP. Put the airplane back

to a serviceable condition.

EFFECTIVITY

747-8 and 747-8F Airplanes. Refer to Paragraph 1.A.1., Airplanes, for the list of affected airplanes.

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.

Boeing recommends that the change given in this service bulletin be done within 60 months after the Original

Issue date of this service bulletin.

INDUSTRY SUPPORT INFORMATION

Boeing warranty remedies are available for airplanes in warranty as of January 28, 2013. Please refer to

Paragraph 2.B., Industry Support Information. The warranty remedies will expire eight years from the original

issue date of 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.

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BOEING SERVICE BULLETIN 747-27A2513

BLANK PAGE
Commercial

Airplanes 747

Service Bulletin

Number: 747-27A2513

Original Issue: February 04, 2014

Revision 1: July 18, 2014

ATA System: 2731 2900 5510

SUBJECT: FLIGHT CONTROLS - Elevator Control System - Inboard Elevator Compensator

Installation and Power Control Package Replacement

1. PLANNING INFORMATION

A. Effectivity

1. Airplanes

Refer to Service Bulletin Index D6-30300 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 86601-5 for data about this change.

GROUP CONFIGURATION DESCRIPTION

747-8 and 747-8F airplanes line number 1420 through 1434, and

1436 through 1491.

1 -

Airplane Models:

747-8, 747-8F

Variable Number Group

RC001 - RC008 1

RC022 - RC030 1

RC501 - RC511 1

RC521 - RC528 1

RC541 1

RC546 - RC549 1

RC551 - RC563 1

RC571 - RC582 1

RC601 - RC605 1

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2. Spares Affected

Examine your spares supply for the parts or components identified below . If any parts or

components are found, refer to Paragraph 2.C.2., Parts and Materials Supplied by the Operator

for the recommended action.

Part Number Serial Number

327400-1009 N/A

B. Concurrent Requirements

None.

C. Reason

The change given in this service bulletin will help to prevent divergent flutter or unacceptable vibration

that can occur in certain parts of the flight envelope if two hydraulic systems are not functional. Divergent

flutter could result in the possible loss of control of the airplane.

Boeing analysis found that the existing internal compensators to the two inboard elevator power control

package (PCP) provided insufficient hydraulic capacity for retained stiffness of the elevator surface

when two hydraulic systems are not functional. This service bulletin installs two (2) larger external

compensators for each of the two (2) inboard elevator PCP. This replacement provides sufficient

hydraulic capacity to prevent divergent flutter or unacceptable vibration.

This service bulletin also refers to a Parker service bulletin. The Parker service bulletin gives instructions

to rework the existing inboard elevator PCP that has internal compensators into the new inboard elevator

PCP with internal compensators removed. This service bulletin gives instructions to replace the existing

PCP internal compensators with larger external compensators and new design of inboard elevator

PCP. Replace existing brackets and hydraulic tubing to accommodate the new external compensators.

Boeing Service Related Problem (SRP) 747-SRP-27-0235 is related to this service bulletin.

Boeing Fleet Team Digest (FTD) 747 FTD 27-13004 is related to this service bulletin.

As a part of a service bulletin validation program, this change was completed on airplane RC008 by

Service Bulletin 747-27A2513, Original Issue, before the release of Revision 1 of this service bulletin.

The change completed on airplane RC008 by Service Bulletin 747-27A2513 Original Issue is equivalent

to the release of Revision 1 of this service bulletin. Airplane RC008 has the configuration of a Group

1 airplane.

Revision 1 is sent to make corrections to fastener length and wire clamp size, revised the manpower

as found during the service bulletin validation.

The data given in Information Notices 747-27A2513 IN 01 is included in this revision.

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BOEING SERVICE BULLETIN 747-27A2513
D. Description

Open access to the left and right inboard elevator PCP. Remove the inboard elevator PCP, hydraulic

tubes and associated hardware. Remove the clamps and loosen the wire bundles. Remove the existing

electrical brackets and rivets. Install inboard and outboard compensator mounting brackets. Install

inboard and outboard compensators, and hydraulic tubes. Route the wire bundles. Install inboard

elevator PCP. Bleed the hydraulic systems. Do the operational test. Close access to the left and right

inboard elevator PCP. Put the airplane back to a serviceable condition.

Revision 1 - No more work is necessary on airplanes changed in accordance with the original issue

oft his service bulletin.

The work in this service bulletin is done in the maintenance zone(s) given below.

Affected Maintenance Zones

Model Zone

747-8, 747-8F 313, 314, 334, 335, 339, 344, 345, 349

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.

Boeing recommends that the change given in this service bulletin be done within 60 months after the

Original Issue date of this service bulletin.

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 change 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

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BOEING SERVICE BULLETIN 747-27A2513
• Time to make the parts

• Time to find the tools.

Task Number of Persons Task Hours Elapsed Hours

Open Access 1 1.00 1.00

Figure 1 3 6.90 2.30

Figure 2 1 1.00 1.00

Figure 3 1 1.00 1.00

Figure 4 2 4.00 2.00

Figure 5 2 4.00 2.00

Figure 6 2 4.00 2.00

Figure 7 1 3.00 3.00

Figure 8 3 9.00 3.00

Figure 9 3 6.90 2.30

Figure 10 1 1.00 1.00

Figure 11 1 1.00 1.00

Figure 12 2 4.00 2.00

Figure 13 2 4.00 2.00

Figure 14 1 0.50 0.50

Figure 15 2 4.00 2.00

Figure 16 1 3.00 3.00

Figure 17 3 9.00 3.00

Test 2 8.00 4.00

Close Access 1 1.00 1.00

TOTAL FOR EACH AIRPLANE 76.30 39.10

H. Weight and Balance Changes

Change in Moment

(Pound-Inches)

Change in Weight

Airplane (Pounds)

Group 1 + 34.0 lb + 91650.4 lb-in

I. Electrical Load Data

Not changed.

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BOEING SERVICE BULLETIN 747-27A2513
J. References

1. Existing Data:

a. Engineering Change Memo PRR 86601-5

b. Boeing Service Related Problem (SRP) 747-SRP-27-0235

c. Service Bulletin Index D6-30300

d. Standard Overhaul Practices Manual (SOPM) 20-41-01, 20-41-02, 20-43-03, 20-44-01,

20-50-01, 20-50-02, 20-50-05, 20-50-19

e. Standard Wiring Practices Manual (SWPM) 20-10-11, 20-10-12, 20-10-19, 20-20-00

f. 747 Fleet Team Digest (FTD) 27-13004

g. 747-8 Aircraft Maintenance Manual (AMM) 06-09-06, 20-11-05, 20-11-18, 20-51-01, 27-31-07,

29-11-00

h. 747-8F Structural Repair Manual (SRM) 51-40-02, 51-40-04

i. 747-8P Structural Repair Manual (SRM) 51-40-02, 51-40-04

j. Parker Service Bulletin 327400-27-001

2. Data Supplied with this Service Bulletin:

None.

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

Drawing Number Title

WIRE BUNDLE INSTALLATION LH HORIZONTAL STABILIZER

AND HORIZONTAL FUEL

288U8267

WIRE BUNDLE INSTALLATION RH HORIZONTAL STABILIZER

AND HORIZONTAL FUEL

288U8268

251U2500 POWER CONTROL ACTUATOR INSTL - INBOARD ELEVATOR

272U8101 HYDRAULIC TUBING INSTL - SECTION 81

272U8201 HYDRAULIC TUBING INSTL - SECTION 82

182U1000 SPAR INSTL - REAR, HORIZONTAL STAB

183U1000 TRAILING EDGE ASSY - FIXED HORIZONTAL STABILIZER

The table above lists applicable drawings used to prepare this service bulletin. The drawings are

not necessary to make the specified changes, and are not supplied with this service bulletin. The

drawings may not be applicable to all airplane configurations or operators.

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K. Publications Affected

1. Publications:

Publication Chapter-Section

747 Aircraft Maintenance Manual 27-31

747 Fault Isolation Manual 27-31

747 Illustrated Parts Catalog 11-32, 27-21, 27-31

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 but no new DTIs are necessary.

L. Interchangeability and Intermixability of Parts

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

information.

M. Software Accomplishment Summary

Not affected.

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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. Operators

are encouraged to share schedule requirements with Boeing for incorporation of the service bulletin.

The kit is 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

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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 as of

the original issue

date of this Service Bulletin (US

Dollars)

ROLT as of the

original issue

date of this Service Bulletin (Calendar Days)

Number Name Date QTY

December 20, 2 525 $51,789.00

2013

Top Kit - 747-8 INBOARD ELEVATOR

REMOTE COMPENSATOR - REVISION

015U1960-1

January 9, 1

2014

March 7, 2014 12

March 21, 2

2014

April 4, 2014 3

April 18, 2014 2

May 5, 2014 3

May 19, 2014 2

Jun 5, 2014 3

Jun 18, 2014 2

July 7, 2014 3

July 18, 2014 2

August 4, 2014 3

August 18, 2

2014

September 5, 3

2014

September 18, 2

2014

October 3, 3

2014

October 17, 3

2014

November 4, 3

2014

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B. Industry Support Information

Boeing warranty remedies are available for 747 airplanes in warranty as of January 28, 2013. For labor

hour reimbursement for airplanes in warranty as of that date, send a warranty claim to Fleet Support

Contracts - Warranty. The kits for airplanes in warranty as of that date will be supplied at no charge.

Send a purchase order for the kits to Boeing Spares. Please refer to this service bulletin number and

reference the airplane variable number(s) in your purchase order. In addition, labor hour and material

reimbursement is available for the PCP modification included in this service bulletin for 747 airplanes

in warranty as of January 28, 2013. The warranty remedies will expire eight years after the original

release date of this service bulletin.

A limited number of seed unit PCPs are available to support incorporation of this service bulletin. To

inquire about availability and scheduling, please contact Boeing Retrofit and Modification via e-mail at

the following address: MMRetrofitMods@boeing.com. Please reference the service bulletin number in

your message

C. Parts Necessary for Each Airplane

1. Kits/Parts

To get the kits/parts 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. The Top Kit is divided into Figure kits for

each installation figure shown in the table below.

Figure Kit

Top Kit 4 5 6 7 8 12

015U1960-1 1 1 1 1 1 1

Figure Kit

Top Kit 13 14 15 16 17

015U1960-1 1 1 1 1 1

ALL

KIT 015U1960-1

Notes

Existing Part

Name Number

Figure

New Part Number

4 5 6 7 8 12

Qty

MOUNTING

BRACKET, LEFT

OUTBD - COMPENSATOR, ELEVATOR PCU

252U3102-11 . 1 . . . .

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ALL

KIT 015U1960-1

Notes

Existing Part

Name Number

Figure

New Part Number

4 5 6 7 8 12

Qty

MOUNTING

BRACKET ASSY,

RIGHT INBD -

COMPENSATOR,

ELEVATOR PCU

252U3102-12 . . . . . 1

MOUNTING

BRACKET ASSY,

LEFT INBD - COMPENSATOR, ELEVATOR PCU

252U3102-13 1 . . . . .

272U8190-32 . . 1 . . . TUBE ASSY 272U8190-26 (a), (b)

272U8190-34 . . 1 . . . TUBE ASSY 272U8190-19 (a), (b)

272U8190-35 . . 1 . . . TUBE ASSY

272U8190-36 . . 1 . . . TUBE ASSY

272U8190-37 . . 1 . . . TUBE ASSY 272U8190-17 (a), (b)

BRACKET ASSEMBLY272U9405-25 . . 1 . . .

BRACKET ASSEMBLY287U0037-33 . 1 . . . .

293W6132-1 . . 2 . . . VALVE ASSY

REMOTE COMPENSATOR - UPPER RUDDER463430-1001 . . 2 . . .

AS1009W080810 . . 1 . . . TEE BACT16BM100810P (a), (b)

AS21919WCE08 . . 1 . . . CLAMP,LOOP

AS21919WCE10 . . 2 . . . CLAMP,LOOP

AS4140V100808P . . 1 . . . TEE

(BACT16BT100808P

optional)

NUT, TUBE,

BULKHEAD

AS5178W10 . . 1 . . .

BAC27EHY242 . . . . 2 . MARKER

BOLT, PROTRUDING HDBACB30MY10K12X 3 . . . . 3

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ALL

KIT 015U1960-1

Notes

Existing Part

Name Number

Figure

New Part Number

4 5 6 7 8 12

Qty

BOLT, PROTRUD- (c)

ING HD

BACB30MY10K8X 8 . . . . 8

BOLT, PROTRUD- (c)

ING HD

BACB30MY8K11X . 3 . . . .

BOLT, PROTRUDING HDBACB30MY8K12X 2 . . . . 1

BOLT, PROTRUD- (c)

ING HD

BACB30MY8K14X . 5 . . . .

BOLT, PROTRUD- (c)

ING HD

BACB30MY8K6X . 3 . . . .

BOLT, PROTRUD- (c)

ING HD

BACB30MY8K9X . 3 . . . .

BACB30NM4K11 . . 9 . . . BOLT, HEX HEAD (c)

CLAMP, WIRE

BUNDLE

BACC10GU103 . . . 3 . .

BACC30M10 13 . . . . 13 COLLAR (c)

BACC30M8 1 15 . . . 1 COLLAR (c)

ELBOW, SWVLRDCR, 45BACE21AU1010W . . 1 . . .

BACF3F015X026NN 1 . . . . 1 FILLER, FLAT

BACF3H10RF010HG . 2 . . . . RADIUS FILLER

FILLER, RECTANGULARBACF3H10RF024HF 2 . . . . 2

FILLER, RECTANGULARBACF3H10RF040HF . 2 . . . .

BACN10YR3CD . . 2 . . . NUT

BACN11Z4CD . . 9 . . . NUT

BACS12GU3K10 . . 5 . . . SCREW

BACS12GU3K26 . . . 3 . . SCREW

BACS12GU3K8 . . 1 . . . SCREW

BACS18AF4 . . 2 . . . SPACER

TEE, SWIVEL ON

RUN

BACT16AY080808W . . 1 . . .

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ALL

KIT 015U1960-1

Notes

Existing Part

Name Number

Figure

New Part Number

4 5 6 7 8 12

Qty

BACW10BP4AC . . 9 . . . WASHER

NAS1149D0316J . . 6 . . . WASHER

NAS1149D0332J . . . 4 . . WASHER

NAS1149D1490J . . 1 . . . WASHER, PLAIN

NAS1149E0432P . . 9 . . . WASHER, PLAIN

SPACERS FOR

RIVETS

NAS42DD6-64FC . . . 2 . .

(a) This part is used in production.

(b) You cannot use the existing part to replace the new or changed part.

(c) There are more parts than are necessary.

ALL

KIT 015U1960-1

Notes

Existing Part

Name Number

Figure

New Part Number

13 14 15 16 17

Qty

MOUNTING

BRACKET, RIGHT

OUTBD - COMPENSATOR, ELEVATOR PCU

252U3102-10 1 . . . .

272U8290-34 . . 1 . . TUBE ASSY 272U8290-7 (a), (b)

272U8290-35 . . 1 . . TUBE ASSY 272U8290-9 (a), (b)

272U8290-36 . . 1 . . TUBE ASSY

272U8290-37 . . 1 . . TUBE ASSY

272U8290-38 . . 1 . . TUBE ASSY

272U8290-39 . . 1 . . TUBE ASSY 272U8290-10 (a), (b)

272U8290-40 . . 1 . . TUBE ASSY 272U8290-20 (a), (b)

293W6132-1 . . 2 . . VALVE ASSY

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ALL

KIT 015U1960-1

Notes

Existing Part

Name Number

Figure

New Part Number

13 14 15 16 17

Qty

REMOTE COMPENSATOR - UPPER RUDDER463430-1001 . . 2 . .

69B80913-5 . 1 . . . BRACKET

AS1005W100808 . . 1 . . TEE, FLARELESS

AS21919WCE08 . . 6 . . CLAMP,LOOP

AS4134V100808P . . 1 . . TEE BACT16BM100810P (a), (b)

(BACT16BN100808P

optional)

BAC27EHY242 . . . . 2 MARKER

BOLT, PROTRUDING HDBACB30MY8K11X 2 . . . .

BOLT, PROTRUDING HDBACB30MY8K14X 4 . . . .

BOLT, PROTRUDING HDBACB30MY8K9X 2 . . . .

BACB30NM4K11 . . 9 . . BOLT, HEX HEAD (c)

CLAMP, WIRE

BUNDLE

BACC10GU103 . . . 2 .

BACC30M8 13 . . . . COLLAR (c)

ELBOW, SWVLRDCR, 90BACE21AW0808W . . 4 . .

BACF3H10RF010HG 2 . . . . RADIUS FILLER

FILLER, RECTANGULARBACF3H10RF040HF 2 . . . .

BACN10YD1 . . 1 . . NUT,CLIP-ON

BACN10YR3CD . . 3 . 1 NUT

BACN11Z4CD . . 9 . . NUT

RIVET, UNIVERSAL HD

BACR15BB5D8C . 4 . . .

BACS12GU3K26 . . . 2 . SCREW

BACS12GU3K8 . . 4 . . SCREW

BACS18AF4 . . 5 . . SPACER (c)

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ALL

KIT 015U1960-1

Notes

Existing Part

Name Number

Figure

New Part Number

13 14 15 16 17

Qty

TEE, SWIVEL ON

RUN

BACT16AY080808W . . 1 . .

BACW10BP4AC . . 9 . . WASHER

NAS1149D0316J . . 8 . . WASHER

NAS1149D0332J . . . 4 . WASHER

NAS1149D1432J . . 2 . . WASHER, PLAIN

NAS1149E0432P . . 9 . . WASHER, PLAIN

SPACERS FOR

RIVETS

NAS42DD6-64FC . . . 2 .

(a) This part is used in production.

(b) You cannot use the existing part to replace the new or changed part.

(c) There are more parts than are necessary.

2. Parts and Materials Supplied by the Operator

The following parts or materials are necessary to do the change in this service bulletin. Parts and

materials in the manuals given in Paragraph 1.J., References, can also be necessary. Examine

operator part and material supply to make sure all necessary parts and materials are available.

Qty Name Existing Part Number Notes

Part Number/

Specification

(b), (c), (d),

(e)

POWER CONTROL PACKAGE - 327400-1009

INBOARD ELEVATOR

327400-1011 2

ALODINE 600 5 Oz Chemical Conversion Coating (a)

BAC5710, TYPE 2 Oz Clear Skydrol Resistant Topcoating (f)

41

BMS 10-11, TYPE 2 Oz Primer (a)

1

BMS10-60, TYPE 2 Oz Gloss Enamel (a)

1

BMS5-142, TYPE 10 Oz Sealant (a)

II

BMS5-45 20 Oz Sealant (a)

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Qty Name Existing Part Number Notes

Part Number/

Specification

MS20995NC40 3 ft Lockwire

(MS20995C41 optional)

(a) Refer to the Qualified Products List at the end of the Boeing Material Specification (BMS) for supplier

data.

(b) This part is used in production.

(c) You cannot use the existing part to replace the new or changed part.

(d) Parker service bulletin 327400-27-001 gives instructions to change the existing part to the new part.

(e) The Boeing part specification for the new part is S252U201-4. The Boeing part specification for the existing part is S252U201-3.

(f) This is a two part protective coating available from Akzo Nobel Aerospace Coatings 1 East Water Street,

Waukegan, IL 60085. Refer to SOPM 20-44-01 for the recommended materials.

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

None.

F. Special Tooling Necessary to do this Service Bulletin

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

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

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

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BLANK PAGE
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

– Hole dimensions for standard solid rivets and fasteners are in Structural Repair

Manual (SRM) Chapter 51

– Torque Values:

— Values for structural fasteners are given in 747-8 Structural Repair Manual,

Chapter 51.

— Values for airframe maintenance tasks are included in Chapter 20 of 747-8

Airplane Maintenance Manual (AMM).

— Values for electrical maintenance tasks are included in Chapter 20 of

Standard Wiring Practices Manual (SWPM).

— Values for engine maintenance tasks are included in Chapter 70 of 747-8

Airplane Maintenance Manual (AMM).

— Non-standard torque values for maintenance tasks are included in the

applicable installation step.

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

SRM Chapter 51.

5. Refer to the SWPM 20-10-11 and SWPM 20-10-12 for the wire installation procedures,

and SWPM 20-10-19 for the wire separation requirements, as accepted procedures.

6. The necessary conditions for selection of clamp type and size are included in SWPM

20-10-12. If any wire bundle support clamp specified in this service bulletin does not

make a correct fit on the wire bundle, refer to SWPM 20-10-12 as an accepted

procedure to select a clamp that fits correctly.

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7. 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. Refer to SOPM 20-50-01 for alternate

full threaded fasteners (screws) needed for installation in this service bulletin.

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.

9. 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.

10. If it is necessary to remove more parts for access, you can remove those parts. If

you can get access without removing identified parts, it is not necessary to remove

all of the identified parts. Jacking and shoring limitations must be observed.

11. Where the work instructions include installation of a kept part, a new or serviceable

part with the same part number can be installed as an alternative to the kept part.

12. 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.

13. If shading is used, shaded areas in Figures are to separate the non-critical and

non-authoritative information from the critical and authoritative information.

14. The compliance times for the actions in Paragraph 3.B., WORK INSTRUCTIONS

are in Paragraph 1.E., Compliance.

15. Some steps in the Work Instructions are identified as Required for Compliance (RC).

If this service bulletin is mandated by an Airworthiness Directive (AD), then the steps

identified as RC must be done to comply with the AD. Alternative procedures for

steps not identified with RC can be used if the RC steps can still be done as specified,

and the airplane can be put back in a serviceable condition. An Alternative Method

of Compliance (AMOC) is not necessary for deviations to steps that are not identified

as RC.

B. WORK INSTRUCTIONS

1. Open access door panels 344HBR, 345DBR, 344AT, 344GBR, 344JBR, and 344KBR, right side.

Refer to 747-8 AMM 06-09-06.

2. Open access door panels 334HBL, 335DBL, 334AT, 334GBL, 334JBL, and 334KBL, left side.

Refer to 747-8 AMM 06-09-06.

3. Open access door panels 338AZ, 339AZ and 349AZ. Refer to 747-8 AMM 06-09-06.

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4. Horizontal stabilizer rear spar rework - left side. Do these steps:

a. RC - Remove the inboard elevator power control package (PCP) and hydraulic tubes in

accordance with FIGURE 1.

b. Loosen the wire bundles W1656 and W4615 in accordance with FIGURE 2.

c. Remove the fasteners and brackets in accordance with FIGURE 3.

d. RC - Install the inboard compensator mounting bracket in accordance with FIGURE 4.

e. RC - Install the outboard compensator mounting bracket in accordance with FIGURE 5.

f. RC - Install the compensators and hydraulic tubes in accordance with FIGURE 6.

g. Route the wire bundles W1656 and W4615 in accordance with FIGURE 7.

h. RC - Install the inboard elevator PCP in accordance with FIGURE 8.

5. Horizontal stabilizer rear spar rework - right side. Do these steps:

a. RC - Remove inboard elevator PCP and hydraulic tubes in accordance with FIGURE 9.

b. Loosen the wire bundles W1912 and W4616 in accordance with FIGURE 10.

c. Remove the fasteners and brackets in accordance with FIGURE 11.

d. RC - Install the inboard compensator mounting bracket in accordance with FIGURE 12.

e. RC - Install the outboard compensator mounting bracket in accordance with FIGURE 13.

f. RC - Install the bracket in accordance with FIGURE 14.

g. RC - Install the compensators and hydraulic tubes in accordance with FIGURE 15.

h. Route the wire bundles W1912 and W4616 in accordance with FIGURE 16.

i. RC - Install the inboard elevator PCP in accordance with FIGURE 17.

6. Bleed the hydraulic system 1, 2, 3 and 4. Refer to 747-8 AMM 29-11-00 as an accepted procedure.

7. RC - Do an Operational Test of each inboard elevator PCP. Refer to 747-8 AMM 27-31-07 as an

accepted procedure.

8. Close access door panels 344HBR, 345DBR, 344AT, 344GBR, 344JBR, and 344KBR, right side.

Refer to 747-8 AMM 06-09-06.

9. Close access door panels 334HBL, 335DBL, 334AT, 334GBL, 334JBL, and 334KB, left side. Refer

to 747-8 AMM 06-09-06.

10. Close access door panels 338AZ, 339AZ and 349AZ. Refer to 747-8 AMM 06-09-06.

11. Put the airplane back to serviceable condition.

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FIGURE 1: INBOARD ELEVATOR POWER CONTROL PACKAGE (PCP) AND HYDRAULIC TUBES REMOVAL

- LEFT SIDE

(SHEET 1 OF 4)

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FIGURE 1: INBOARD ELEVATOR POWER CONTROL PACKAGE (PCP) AND HYDRAULIC TUBES REMOVAL

- LEFT SIDE

(SHEET 2 OF 4)

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BOEING SERVICE BULLETIN 747-27A2513
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.

Step Task Name Identification Qty More Data

Keep all the screw,

washers and nut.

1 Remove / Keep Clamp - 2

2 Remove / Keep Hose Assy - 4 (a)

Refer to 747-8 AMM

27-31-07 as an accepted procedure.

Power Control Package 327400-1009 1

Inboard Elevator

3 Remove

Keep all the screws,

washers and clip

nuts.

4 Remove Clamp - 2

Remove Tube Assy 272U8190-19 1 (b)

FIGURE 1: INBOARD ELEVATOR POWER CONTROL PACKAGE (PCP) AND HYDRAULIC TUBES REMOVAL

- LEFT SIDE

(SHEET 3 OF 4)

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Step Task Name Identification Qty More Data

Keep all the fasteners and hardware.5 Remove / Keep Clamp Block Assy - 1

Keep all the screws,

washers and five (5)

clip nuts.

6 Remove / Keep Clamp - 6

Remove Tube Assy 272U8190-26 1 (b)

Keep all the screws,

washers and clip

nuts.

7 Remove / Keep Clamp - 6

Remove Tube Assy 272U8190-17 1 (b)

8 Remove Lock Nut - 1

Remove Washer - 1

Remove Tee BACT16BM100810P 1

9 Remove Screw - 1

Remove / Keep Clamp - 1

Remove / Keep Washer - 1

Remove Clip Nut - 1

(a) Refer to 747-8 AMM 20-11-18 as an accepted procedure.

(b) Refer to 747-8 AMM 20-11-05 as an accepted procedure.

FIGURE 1: INBOARD ELEVATOR POWER CONTROL PACKAGE (PCP) AND HYDRAULIC TUBES REMOVAL

- LEFT SIDE

(SHEET 4 OF 4)

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BOEING SERVICE BULLETIN 747-27A2513
FIGURE 2: LOOSEN THE WIRE BUNDLE W1656 AND W4615 - LEFT SIDE

(SHEET 1 OF 2)

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34 of 108

BOEING SERVICE BULLETIN 747-27A2513
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.

Step Task Name Identification Qty More Data

1 Remove Screw - 2

Remove Clamp - 2

Remove Washer - 2

2 Remove / Keep Screw - 12

Remove / Keep Washer - 12

Remove / Keep Clamp - 12

3 Loosen Wire Bundle W1656, W4615 - (a)

(a) Make sure cover wire bundle with plastic and tape to protect them from the chips.

FIGURE 2: LOOSEN THE WIRE BUNDLE W1656 AND W4615 - LEFT SIDE

(SHEET 2 OF 2)

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FIGURE 3: FASTENERS AND BRACKETS REMOVAL - LEFT SIDE

(SHEET 1 OF 3)

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FIGURE 3: FASTENERS AND BRACKETS REMOVAL - LEFT SIDE

(SHEET 2 OF 3)

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37 of 108

BOEING SERVICE BULLETIN 747-27A2513
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.

Step Task Name Identification Qty More Data

1 Remove Bolt - 4

Remove Bracket 287U0037-17 2

2 Remove Rivet - 5

3 Remove Bolt - 1

4 Remove Rivet - 2

Remove Bracket 287U0037-33 1

5 Remove Rivet - 8

FIGURE 3: FASTENERS AND BRACKETS REMOVAL - LEFT SIDE

(SHEET 3 OF 3)

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BOEING SERVICE BULLETIN 747-27A2513
FIGURE 4: INBOARD COMPENSATOR MOUNTING BRACKET INSTALLATION - LEFT SIDE

(SHEET 1 OF 8)

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FIGURE 4: INBOARD COMPENSATOR MOUNTING BRACKET INSTALLATION - LEFT SIDE

(SHEET 2 OF 8)

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FIGURE 4: INBOARD COMPENSATOR MOUNTING BRACKET INSTALLATION - LEFT SIDE

(SHEET 3 OF 8)

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41 of 108

BOEING SERVICE BULLETIN 747-27A2513
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.

Step Task Name Identification Qty More Data

On the fwd side, the

fillers are under the

collars.

FILLER, RECTANGU- BACF3H10RF024HF 2

LAR

1 Put / Hold

Two (2) holes for

each location. Back

drill the holes

through radius filler.

Refer to Fastener

Code table for the

hole diameter.

2 Drill / Ream Hole - 4

Clean/Deburr Hole - -

On mating surfaces

of filler, web. Refer

to SOPM 20-50-19

as an accepted procedure.

3 Apply Sealant BMS5-45 -

On the fwd side, under the collar. One

(1) for each location.

FILLER, RECTANGU- BACF3H10RF024HF 2

LAR

Install (New)

Refer to Fastener

Code table for fastener part number.

Install (New) Fastener - -

4 Microshave Rivet - 1 (d)

Clean Surface - -

Chemical Conversion ALODINE 600 - (a)

Coating

Apply

Apply Primer BMS 10-11, TYPE 1 - (b)

Apply Gloss Enamel BMS10-60, TYPE 1 - Optional, (e)

MOUNTING BRACKET 252U3102-13 1 As shown in figure.

ASSY, LEFT INBD -

COMPENSATOR, ELEVATOR PCU

5 Put / Hold

As shown in figure,

the filler is between

the bracket and the

spar.

Put / Hold FILLER, FLAT BACF3F015X026NN 1

FIGURE 4: INBOARD COMPENSATOR MOUNTING BRACKET INSTALLATION - LEFT SIDE

(SHEET 4 OF 8)

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BOEING SERVICE BULLETIN 747-27A2513
Step Task Name Identification Qty More Data

Back drill the holes

through the filler and

bracket. Refer to

Fastener Code table

for the hole diameter.

6 Drill / Ream Hole - 5

Back drill the holes

through the bracket.

Minimum edge margin of 0.30 is acceptable at this location.

Refer to Fastener

Code table for the

hole diameter.

7 Drill / Ream Hole - 1

MOUNTING BRACKET 252U3102-13 -

ASSY, LEFT INBD -

COMPENSATOR, ELEVATOR PCU

8 Disassemble

Disassemble FILLER, FLAT BACF3F015X026NN -

To the bracket, filler

and the web

Clean/Deburr Hole - -

Non-designated

bond. Refer to SWPM 20-20-00,

Cleaning Procedure

1, as an accepted

procedure.

9 Clean Surface - -

Chemical Conversion ALODINE 600 - (a)

Coating

Apply

To mating surface of

bracket and web.

Refer to SWPM 20-

20-00, Category 2

fay surface bond, as

an accepted procedure.

Apply Sealant BMS5-45 -

FIGURE 4: INBOARD COMPENSATOR MOUNTING BRACKET INSTALLATION - LEFT SIDE

(SHEET 5 OF 8)

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BOEING SERVICE BULLETIN 747-27A2513
Step Task Name Identification Qty More Data

Refer to SWPM 20-

20-00, Procedure 5,

as an accepted procedure.

10 Clean Surface - -

To mating surface of

bracket, filler, web.

Refer to SOPM 20-

50-19 as an accepted procedure.

Apply Sealant BMS5-45 -

MOUNTING BRACKET 252U3102-13 1

ASSY, LEFT INBD -

COMPENSATOR, ELEVATOR PCU

11 Install (New)

The filler is between

the bracket and the

spar.

Install (New) FILLER, FLAT BACF3F015X026NN 1

Refer to Fastener

Code table for fastener part number.

Install (New) Fastener - -

12 Measure Resistance - - (c)

Apply a fillet seal

around the bracket

where it connects to

the structure. Refer

to SOPM 20-50-19

as an accepted procedure.

13 Apply Sealant BMS5-142, TYPE II -

Chemical Conversion ALODINE 600 - (a)

Coating

14 Apply

Apply Primer BMS 10-11, TYPE 1 - (b)

(a) Apply to bare metal. Refer to SOPM 20-43-03, as an accepted procedure.

(b) Apply 2 layers of the primer over the chemical conversion coating. Refer to SOPM 20-41-02, as an accepted procedure.

(c) Between the bracket and structure. Maximum resistance is 0.0005 ohms. Refer to SWPM 20-20-00 as

an accepted procedure.

(d) Microshave the bucked tail of the existing rivet as necessary to allow the clearance for the bracket installation. Complete removal of bucked tail is acceptable.

(e) Refer to SOPM 20-41-01 code F-14.9812, as an accepted procedure.

FIGURE 4: INBOARD COMPENSATOR MOUNTING BRACKET INSTALLATION - LEFT SIDE

(SHEET 6 OF 8)

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BOEING SERVICE BULLETIN 747-27A2513
The codes shown below agree with the letter shown in the upper left corner of the fastener symbols in the figure.

A number in the lower right corner gives the grip length of the fastener. The QTY numbers shown below are the

number of fasteners necessary for this figure.

Code Name Identification Qty Hole Dia More Data

Install the fastener wet

with sealant BMS5-45. (a)

BOLT, PROTRUDING BACB30MY10K8X 7 0.325 - 0.328

HD

A

COLLAR BACC30M10 7 - (b)

Install the fastener wet

with sealant BMS5-45. (a)

BOLT, PROTRUDING BACB30MY10K12X 2 0.325 - 0.328

HD

B

COLLAR BACC30M10 2 - (b)

Install the fastener wet

with sealant BMS5-45. (a)

BOLT, PROTRUDING BACB30MY8K12X 1 0.263 - 0.266

HD

C

COLLAR BACC30M8 1 - (b)

(a) Install fasteners in accordance with 747-8P SRM 51-40-02 or 747-8F SRM 51-40-02

(b) Cap seal over the fastener threaded ends and collars inside the tank with sealant BMS5-45. Refer to

SOPM 20-50-19 as an accepted procedure.

The parts shown in the table below are provided as extra parts for this figure.

Name Identification Qty More Data

COLLAR BACC30M10 4

BOLT, PROTRUDING BACB30MY10K12X 1

HD

BOLT, PROTRUDING BACB30MY8K12X 1

HD

FIGURE 4: INBOARD COMPENSATOR MOUNTING BRACKET INSTALLATION - LEFT SIDE

(SHEET 7 OF 8)

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BOEING SERVICE BULLETIN 747-27A2513
Name Identification Qty More Data

BOLT, PROTRUDING BACB30MY10K8X 1

HD

FIGURE 4: INBOARD COMPENSATOR MOUNTING BRACKET INSTALLATION - LEFT SIDE

(SHEET 8 OF 8)

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BOEING SERVICE BULLETIN 747-27A2513
FIGURE 5: OUTBOARD COMPENSATOR MOUNTING BRACKET INSTALLATION - LEFT SIDE

(SHEET 1 OF 8)

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BOEING SERVICE BULLETIN 747-27A2513
FIGURE 5: OUTBOARD COMPENSATOR MOUNTING BRACKET INSTALLATION - LEFT SIDE

(SHEET 2 OF 8)

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BOEING SERVICE BULLETIN 747-27A2513
FIGURE 5: OUTBOARD COMPENSATOR MOUNTING BRACKET INSTALLATION - LEFT SIDE

(SHEET 3 OF 8)

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49 of 108

BOEING SERVICE BULLETIN 747-27A2513
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.

Step Task Name Identification Qty More Data

MOUNTING BRACK- 252U3102-11 1 As shown in figure.

ET, LEFT OUTBD -

COMPENSATOR, ELEVATOR PCU

1 Put / Hold

On the fwd side, the

fillers are under the

collars.

FILLER, RECTANGU- BACF3H10RF040HF 2

LAR

Put / Hold

The radius fillers are

between the head of

fasteners and bracket.

Put / Hold RADIUS FILLER BACF3H10RF010HG 2

Back drill the holes

through bracket and

radius fillers. Refer

to Fastener Code table for the hole diameter.

2 Drill / Ream Hole - 8

To the bracket, fillers

and web.

Deburr Hole - -

Non-designated

bond. Refer to SWPM 20-20-00,

Cleaning Procedure

1, as an accepted

procedure.

3 Clean Surface - -

Chemical Conversion ALODINE 600 - (b)

Coating

Apply

To mating surface of

bracket, fillers. Refer

to SWPM 20-20-00,

Category 2 fay surface bond, as an accepted procedure.

Apply Sealant BMS5-45 -

FIGURE 5: OUTBOARD COMPENSATOR MOUNTING BRACKET INSTALLATION - LEFT SIDE

(SHEET 4 OF 8)

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BOEING SERVICE BULLETIN 747-27A2513
Step Task Name Identification Qty More Data

Refer to SWPM 20-

20-00, Procedure 5,

as an accepted procedure.

4 Clean Surface - -

To mating surface of

bracket, fillers, web.

Refer to SOPM 20-

50-19 as an accepted procedure.

Apply Sealant BMS5-45 -

MOUNTING BRACK- 252U3102-11 1

ET, LEFT OUTBD -

COMPENSATOR, ELEVATOR PCU

5 Install (New)

On the fwd side, under the collars.FILLER, RECTANGU- BACF3H10RF040HF 2

LAR

Install (New)

Refer to Fastener

Code table for fastener part number.

Install (New) Fastener - -

To mating surface of

fillers. Refer to

SOPM 20-50-19 as

an accepted procedure.

6 Apply Sealant BMS5-45 -

Under the head of

fasteners.

Install (New) RADIUS FILLER BACF3H10RF010HG 2

Refer to Fastener

Code table for fastener part number.

Install (New) Fastener - -

7 Measure Resistance - - (a)

8 Put / Hold BRACKET ASSEMBLY 287U0037-33 1 As shown in figure.

Back drill the holes

through bracket. Refer to Fastener Code

table for the hole diameter.

9 Drill / Ream Hole - 2

Deburr Hole - -

FIGURE 5: OUTBOARD COMPENSATOR MOUNTING BRACKET INSTALLATION - LEFT SIDE

(SHEET 5 OF 8)

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BOEING SERVICE BULLETIN 747-27A2513
Step Task Name Identification Qty More Data

Non-designated

bond. Refer to SWPM 20-20-00,

Cleaning Procedure

1, as an accepted

procedure.

10 Clean Surface - -

Chemical Conversion ALODINE 600 - (b)

Coating

Apply

To mating surface of

bracket. Refer to

SWPM 20-20-00,

Category 2 fay surface bond, as an accepted procedure.

Apply Sealant BMS5-45 -

11 Install (New) BRACKET ASSEMBLY 287U0037-33 1

Refer to Fastener

Code table for fastener part number.

Install (New) Fastener - -

12 Measure Resistance - - (a)

Apply a fillet seal

around the bracket

where it connects to

the structure. Refer

to SOPM 20-50-19

as an accepted procedure.

13 Apply Sealant BMS5-142, TYPE II -

Chemical Conversion ALODINE 600 - (b)

Coating

14 Apply

Apply Primer BMS 10-11, TYPE 1 - (c)

(a) Between the bracket and structure. Maximum resistance is 0.0005 ohms. Refer to SWPM 20-20-00 as

an accepted procedure.

(b) Apply to bare metal surfaces. Refer to SOPM 20-43-03, as an accepted procedure.

(c) Apply 2 layers of the primer over the chemical conversion coating. Refer to SOPM 20-41-02, as an accepted procedure.

FIGURE 5: OUTBOARD COMPENSATOR MOUNTING BRACKET INSTALLATION - LEFT SIDE

(SHEET 6 OF 8)

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BOEING SERVICE BULLETIN 747-27A2513
The codes shown below agree with the letter shown in the upper left corner of the fastener symbols in the figure.

A number in the lower right corner gives the grip length of the fastener. The QTY numbers shown below are the

number of fasteners necessary for this figure.

Code Name Identification Qty Hole Dia More Data

Install the fastener wet

with sealant BMS5-45. (a)

BOLT, PROTRUDING BACB30MY8K14X 4 0.263 - 0.266

HD

D

COLLAR BACC30M8 4 - (b)

Install the fastener wet

with sealant BMS5-45. (a)

BOLT, PROTRUDING BACB30MY8K9X 2 0.263 - 0.266

HD

E

COLLAR BACC30M8 2 - (b)

Install the fastener wet

with sealant BMS5-45. (a)

BOLT, PROTRUDING BACB30MY8K11X 2 0.263 - 0.266

HD

F

COLLAR BACC30M8 2 - (b)

Install the fastener wet

with sealant BMS5-45. (a)

BOLT, PROTRUDING BACB30MY8K6X 2 0.263 - 0.266

HD

G

COLLAR BACC30M8 2 - (b)

(a) Install fasteners in accordance with 747-8P SRM 51-40-02 or 747-8F SRM 51-40-02

(b) Cap seal over the fastener threaded ends and collars inside the tank with sealant BMS5-45. Refer to

SOPM 20-50-19 as an accepted procedure.

The parts shown in the table below are provided as extra parts for this figure.

Name Identification Qty More Data

COLLAR BACC30M8 5

FIGURE 5: OUTBOARD COMPENSATOR MOUNTING BRACKET INSTALLATION - LEFT SIDE

(SHEET 7 OF 8)

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BOEING SERVICE BULLETIN 747-27A2513
Name Identification Qty More Data

BOLT, PROTRUDING BACB30MY8K14X 1

HD

BOLT, PROTRUDING BACB30MY8K9X 1

HD

BOLT, PROTRUDING BACB30MY8K11X 1

HD

BOLT, PROTRUDING BACB30MY8K6X 1

HD

FIGURE 5: OUTBOARD COMPENSATOR MOUNTING BRACKET INSTALLATION - LEFT SIDE

(SHEET 8 OF 8)

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BOEING SERVICE BULLETIN 747-27A2513
FIGURE 6: COMPENSATORS AND HYDRAULIC TUBES INSTALLATION - LEFT SIDE

(SHEET 1 OF 6)

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FIGURE 6: COMPENSATORS AND HYDRAULIC TUBES INSTALLATION - LEFT SIDE

(SHEET 2 OF 6)

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BOEING SERVICE BULLETIN 747-27A2513
FIGURE 6: COMPENSATORS AND HYDRAULIC TUBES INSTALLATION - LEFT SIDE

(SHEET 3 OF 6)

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BOEING SERVICE BULLETIN 747-27A2513
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.

Step Task Name Identification Qty More Data

REMOTE COMPEN- 463430-1001 2

SATOR - UPPER

RUDDER

1 Install (New)

Under the head of

fastener. Four (4)

per Compensator

2 Install (New) WASHER BACW10BP4AC 8

Four (4) per CompensatorInstall (New) BOLT, HEX HEAD BACB30NM4K11 8

Four (4) per CompensatorInstall (New) WASHER, PLAIN NAS1149E0432P 8

Four (4) per Compensator. Refer to

747-8P SRM 51-40-

04 and 747-8F SRM

51-40-04 as an accepted procedure for

the torque value.

Install (New) NUT BACN11Z4CD 8

Onto back of existing bracket

272U9405-10

3 Install (New) BRACKET ASSEMBLY 272U9405-25 1

To the tube assembly 272U8190-10.4 Install (Kept) Clamp - 1

Install (Kept) Washer - 1

Install (New) SCREW BACS12GU3K10 1

Connect the TEE to

the Compensator,

(b), (c)

AS4140V100808P 1

(BACT16BT100808P

optional)

5 Install (New) TEE

6 Install (New) TUBE ASSY 272U8190-32 1 (b), (c)

Use the kept screws,

washers and clip

nuts for the installation.

Install (Kept) Clamp - 5

Use the kept fasteners and hardware.7 Install (Kept) Clamp Block Assy - 1

FIGURE 6: COMPENSATORS AND HYDRAULIC TUBES INSTALLATION - LEFT SIDE

(SHEET 4 OF 6)

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BOEING SERVICE BULLETIN 747-27A2513
Step Task Name Identification Qty More Data

8 Install (New) SPACER BACS18AF4 1 (d)

Install (New) CLAMP,LOOP AS21919WCE10 1

Install (New) WASHER NAS1149D0316J 1

Install (New) SCREW BACS12GU3K10 1

9 Install (New) TUBE ASSY 272U8190-37 1 (b), (c)

Use all kept screws,

washers and clip

nuts for the installation.

Install (New) Clamp - 6

10 Install (New) TEE AS1009W080810 1 (b), (c)

Install (New) WASHER, PLAIN NAS1149D1490J 1

NUT, TUBE, BULK- AS5178W10 1

HEAD

Install (New)

(b), (c). Torque the

valve to 40-80 inchpounds to make

sure the valve is

seated.

11 Install (New) VALVE ASSY 293W6132-1 1

MS20995NC40 - (a)

(MS20995C41 optional)

Install (New) Lockwire

Connect the tube

assy to the tee and

compensator, (b), (c)

12 Install (New) TUBE ASSY 272U8190-36 1

Install (Kept) Clamp - 1

Install (Kept) Washer - 1

Install (New) SCREW BACS12GU3K10 1

Connect the elbow

to the tee. (b), (c)

ELBOW, SWVL-RDCR, BACE21AU1010W 1

45

13 Install (New)

Connect the tube

assy to the Compensator, (b), (c)

14 Install (New) TUBE ASSY 272U8190-34 1

Use all kept screw,

washer and clip nut

for the installation.

Install (Kept) Clamp - 1

15 Install (New) TEE, SWIVEL ON RUN BACT16AY080808W 1 (b), (c)

FIGURE 6: COMPENSATORS AND HYDRAULIC TUBES INSTALLATION - LEFT SIDE

(SHEET 5 OF 6)

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BOEING SERVICE BULLETIN 747-27A2513
Step Task Name Identification Qty More Data

(b), (c). Torque the

valve to 40-80 inchpounds to make

sure the valve is

seated.

16 Install (New) VALVE ASSY 293W6132-1 1

MS20995NC40 - (a)

(MS20995C41 optional)

Install (New) Lockwire

Connect the tube

assy to the Compensator and Tee. (b),

(c)

17 Install (New) TUBE ASSY 272U8190-35 1

Use all kept screw,

washer and clip nut

for the installation.

Install (Kept) Clamp - 1

18 Install (New) CLAMP,LOOP AS21919WCE08 1

Install (New) SPACER BACS18AF4 1 (d)

Install (New) WASHER NAS1149D0316J 2

Install (New) SCREW BACS12GU3K8 1

Install (New) NUT BACN10YR3CD 1

(a) Double-twist method. Refer to SOPM 20-50-02 as an accepted procedure.

(b) Refer to 747-8 AMM 20-11-05 as an accepted procedure.

(c) Refer to 747-8 AMM 20-51-01 as an accepted procedure for the torque value.

(d) Use spacers as necessary to make sure that the clamp holds the tube with minimum force. The maximum

permitted quantity of spacers for each clamp is 4.

The parts shown in the table below are provided as extra parts for this figure.

Name Identification Qty More Data

WASHER BACW10BP4AC 1

WASHER, PLAIN NAS1149E0432P 1

NUT BACN11Z4CD 1

WASHER NAS1149D0316J 3

SCREW BACS12GU3K10 2

NUT BACN10YR3CD 1

CLAMP,LOOP AS21919WCE10 1

BOLT, HEX HEAD BACB30NM4K11 1

FIGURE 6: COMPENSATORS AND HYDRAULIC TUBES INSTALLATION - LEFT SIDE

(SHEET 6 OF 6)

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BOEING SERVICE BULLETIN 747-27A2513
FIGURE 7: WIRE BUNDLE W1656 AND W4615 ROUTING - LEFT SIDE

(SHEET 1 OF 3)

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FIGURE 7: WIRE BUNDLE W1656 AND W4615 ROUTING - LEFT SIDE

(SHEET 2 OF 3)

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BOEING SERVICE BULLETIN 747-27A2513
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.

Step Task Name Identification Qty More Data

1 Route Wire Bundle W1656, W4615 -

One for each locationCLAMP, WIRE BUN- BACC10GU103 2

DLE

2 Install (New)

One for each locationSPACERS FOR RIV- NAS42DD6-64FC 2

ETS

Install (New)

One for each locationInstall (New) WASHER NAS1149D0332J 2

One for each locationInstall (New) SCREW BACS12GU3K26 2

3 Install (Kept) Clamp - 12

Install (Kept) Washer - 12

Install (Kept) Screw - 12

The parts shown in the table below are provided as extra parts for this figure.

Name Identification Qty More Data

WASHER NAS1149D0332J 2

CLAMP, WIRE BUN- BACC10GU103 1

DLE

SCREW BACS12GU3K26 1

FIGURE 7: WIRE BUNDLE W1656 AND W4615 ROUTING - LEFT SIDE

(SHEET 3 OF 3)

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BOEING SERVICE BULLETIN 747-27A2513
FIGURE 8: INBOARD ELEVATOR POWER CONTROL PACKAGE (PCP) INSTALLATION - LEFT SIDE

(SHEET 1 OF 4)

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FIGURE 8: INBOARD ELEVATOR POWER CONTROL PACKAGE (PCP) INSTALLATION - LEFT SIDE

(SHEET 2 OF 4)

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FIGURE 8: INBOARD ELEVATOR POWER CONTROL PACKAGE (PCP) INSTALLATION - LEFT SIDE

(SHEET 3 OF 4)

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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 this figure.

Step Task Name Identification Qty More Data

Refer to 747-8 AMM

27-31-07 as an accepted procedure.

POWER CONTROL 327400-1011 1

PACKAGE - INBOARD

ELEVATOR

1 Install (New)

2 Install (Kept) Hose Assy - 3 (a) (b)

Rotate the hose and

elbow to maintain

minimum 0.5 inches

clearance from

structure and tubing.

(a) (b)

3 Install (Kept) Hose Assy - 1

4 Torque Nut - - To 360 inch-pounds.

As shown in figure.

Refer to SOPM 20-

50-05 as an accepted procedure.

5 Install (New) MARKER BAC27EHY242 2

Refer to SOPM 20-

44-01, as an accepted procedure.

Clear Skydrol Resistant BAC5710, TYPE 41 -

Topcoating

6 Apply

(a) Refer to 747-8 AMM 20-11-18 as an accepted procedure.

(b) Refer to 747-8 AMM 20-51-01 as an accepted procedure for the torque value.

FIGURE 8: INBOARD ELEVATOR POWER CONTROL PACKAGE (PCP) INSTALLATION - LEFT SIDE

(SHEET 4 OF 4)

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FIGURE 9: INBOARD ELEVATOR POWER CONTROL PACKAGE (PCP) AND HYDRAULIC TUBES REMOVAL

- RIGHT SIDE

(SHEET 1 OF 5)

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FIGURE 9: INBOARD ELEVATOR POWER CONTROL PACKAGE (PCP) AND HYDRAULIC TUBES REMOVAL

- RIGHT SIDE

(SHEET 2 OF 5)

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FIGURE 9: INBOARD ELEVATOR POWER CONTROL PACKAGE (PCP) AND HYDRAULIC TUBES REMOVAL

- RIGHT SIDE

(SHEET 3 OF 5)

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FIGURE 9: INBOARD ELEVATOR POWER CONTROL PACKAGE (PCP) AND HYDRAULIC TUBES REMOVAL

- RIGHT SIDE

(SHEET 4 OF 5)

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BOEING SERVICE BULLETIN 747-27A2513
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.

Step Task Name Identification Qty More Data

Keep the screws,

washers, nut and

clip nut.

1 Remove / Keep Clamp - 3

2 Remove / Keep Hose Assy - 4 (a)

Refer to 747-8 AMM

27-31-07 as an accepted procedure.

Power Control Package 327400-1009 1

Inboard Elevator

3 Remove

Keep all the fasteners and hardware.4 Remove / Keep Clamp Block Assy - 1

Keep all the screws,

washers and clip

nuts.

5 Remove / Keep Clamp - 6

Remove Tube Assy 272U8290-20 1 (b)

Keep all the screws,

washers and clip

nuts.

6 Remove / Keep Clamp - 6

Remove Tube Assy 272U8290-7 1 (b)

Keep all the screws,

washers and clip

nuts.

7 Remove / Keep Clamp - 4

Remove Tube Assy 272U8290-10 1 (b)

Keep all the screws,

washers and clip

nuts.

8 Remove / Keep Clamp - 2

Remove Tube Assy 272U8290-9 1 (b)

9 Remove / Keep Lock Nut - 1

Remove Washer - 1

10 Remove Tee BACT16BM100810P 1

(a) Refer to 747-8 AMM 20-11-18 as an accepted procedure.

(b) Refer to 747-8 AMM 20-11-05 as an accepted procedure.

FIGURE 9: INBOARD ELEVATOR POWER CONTROL PACKAGE (PCP) AND HYDRAULIC TUBES REMOVAL

- RIGHT SIDE

(SHEET 5 OF 5)

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BOEING SERVICE BULLETIN 747-27A2513
FIGURE 10: LOOSEN THE WIRE BUNDLE W1912 AND W4616 - RIGHT SIDE

(SHEET 1 OF 2)

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BOEING SERVICE BULLETIN 747-27A2513
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.

Step Task Name Identification Qty More Data

1 Remove Screw - 2

Remove Clamp - 2

Remove Washer - 2

2 Remove / Keep Screw - 14

Remove / Keep Washer - 14

Remove / Keep Clamp - 14

3 Loosen Wire Bundle W1912, W4616 - (a)

(a) Make sure cover wire bundle with plastic and tape to protect them from the chips.

FIGURE 10: LOOSEN THE WIRE BUNDLE W1912 AND W4616 - RIGHT SIDE

(SHEET 2 OF 2)

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FIGURE 11: FASTENERS AND BRACKETS REMOVAL - RIGHT SIDE

(SHEET 1 OF 3)

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FIGURE 11: FASTENERS AND BRACKETS REMOVAL - RIGHT SIDE

(SHEET 2 OF 3)

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BOEING SERVICE BULLETIN 747-27A2513
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.

Step Task Name Identification Qty More Data

1 Remove Bolt - 4

Remove Bracket 287U0037-17 2

2 Remove Rivet - 5

3 Remove Bolt - 1

4 Remove Rivet - 3

Remove Bracket 272U8212-7 1

5 Remove Rivet - 5

FIGURE 11: FASTENERS AND BRACKETS REMOVAL - RIGHT SIDE

(SHEET 3 OF 3)

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BOEING SERVICE BULLETIN 747-27A2513
FIGURE 12: INBOARD COMPENSATOR MOUNTING BRACKET INSTALLATION - RIGHT SIDE

(SHEET 1 OF 7)

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BOEING SERVICE BULLETIN 747-27A2513
FIGURE 12: INBOARD COMPENSATOR MOUNTING BRACKET INSTALLATION - RIGHT SIDE

(SHEET 2 OF 7)

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BOEING SERVICE BULLETIN 747-27A2513
FIGURE 12: INBOARD COMPENSATOR MOUNTING BRACKET INSTALLATION - RIGHT SIDE

(SHEET 3 OF 7)

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BOEING SERVICE BULLETIN 747-27A2513
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.

Step Task Name Identification Qty More Data

On the fwd side, the

fillers are under the

collars.

FILLER, RECTANGU- BACF3H10RF024HF 2

LAR

1 Put / Hold

Two (2) holes for

each location. Back

drill the holes

through radius filler.

Refer to Fastener

Code table for the

hole diameter.

2 Drill / Ream Hole - 4

Clean/Deburr Hole - -

On mating surfaces

of filler, web. Refer

to SOPM 20-50-19

as an accepted procedure.

3 Apply Sealant BMS5-45 -

On the fwd side, under the collar. One

(1) for each location.

FILLER, RECTANGU- BACF3H10RF024HF 2

LAR

Install (New)

Refer to Fastener

Code table for fastener part number.

Install (New) Fastener - -

4 Microshave Rivet - 1 (d)

Clean Surface - -

Chemical Conversion ALODINE 600 - (a)

Coating

Apply

Apply Primer BMS 10-11, TYPE 1 - (b)

Apply Gloss Enamel BMS10-60, TYPE 1 - Optional, (e)

MOUNTING BRACKET 252U3102-12 1 As shown in figure.

ASSY, RIGHT INBD -

COMPENSATOR, ELEVATOR PCU

5 Put / Hold

As shown in figure,

the filler is between

the bracket and the

spar.

Put / Hold FILLER, FLAT BACF3F015X026NN 1

FIGURE 12: INBOARD COMPENSATOR MOUNTING BRACKET INSTALLATION - RIGHT SIDE

(SHEET 4 OF 7)

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BOEING SERVICE BULLETIN 747-27A2513
Step Task Name Identification Qty More Data

Back drill the holes

through the filler and

bracket. Refer to

Fastener Code table

for the hole diameter.

6 Drill / Ream Hole - 5

Back drill the holes

through the bracket.

Reduced edge margin of 0.30 is acceptable at this location.

Refer to Fastener

Code table for the

hole diameter.

7 Drill / Ream Hole - 1

MOUNTING BRACKET 252U3102-12 -

ASSY, RIGHT INBD -

COMPENSATOR, ELEVATOR PCU

8 Disassemble

Disassemble FILLER, FLAT BACF3F015X026NN -

To the bracket, filler

and the web

Clean/Deburr Hole - -

Non-designated

bond. Refer to SWPM 20-20-00,

Cleaning Procedure

1, as an accepted

procedure.

9 Clean Surface - -

Chemical Conversion ALODINE 600 - (a)

Coating

Apply

To mating surface of

bracket and web.

Refer to SWPM 20-

20-00, Category 2

fay surface bond, as

an accepted procedure.

Apply Sealant BMS5-45 -

FIGURE 12: INBOARD COMPENSATOR MOUNTING BRACKET INSTALLATION - RIGHT SIDE

(SHEET 5 OF 7)

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BOEING SERVICE BULLETIN 747-27A2513
Step Task Name Identification Qty More Data

Refer to SWPM 20-

20-00, Procedure 5,

as an accepted procedure.

10 Clean Surface - -

To mating surface of

bracket, filler, web.

Refer to SOPM 20-

50-19 as an accepted procedure.

Apply Sealant BMS5-45 -

MOUNTING BRACKET 252U3102-12 1

ASSY, RIGHT INBD -

COMPENSATOR, ELEVATOR PCU

11 Install (New)

The filler is between

the bracket and the

spar.

Install (New) FILLER, FLAT BACF3F015X026NN 1

Refer to Fastener

Code table for fastener part number.

Install (New) Fastener - -

12 Measure Resistance - - (c)

Apply a fillet seal

around the bracket

where it connects to

the structure. Refer

to SOPM 20-50-19

as an accepted procedure.

13 Apply Sealant BMS5-142, TYPE II -

Chemical Conversion ALODINE 600 - (a)

Coating

14 Apply

Apply Primer BMS 10-11, TYPE 1 - (b)

(a) Apply to bare metal. Refer to SOPM 20-43-03, as an accepted procedure.

(b) Apply 2 layers of the primer over the chemical conversion coating. Refer to SOPM 20-41-02, as an accepted procedure.

(c) Between the bracket and structure. Maximum resistance is 0.0005 ohms. Refer to SWPM 20-20-00 as

an accepted procedure.

(d) Microshave the bucked tail of the existing rivet as necessary to allow the clearance for the bracket installation. Complete removal of bucked tail is acceptable.

(e) Refer to SOPM 20-41-01 code F-14.9812, as an accepted procedure.

FIGURE 12: INBOARD COMPENSATOR MOUNTING BRACKET INSTALLATION - RIGHT SIDE

(SHEET 6 OF 7)

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BOEING SERVICE BULLETIN 747-27A2513
The codes shown below agree with the letter shown in the upper left corner of the fastener symbols in the figure.

A number in the lower right corner gives the grip length of the fastener. The QTY numbers shown below are the

number of fasteners necessary for this figure.

Code Name Identification Qty Hole Dia More Data

Install the fastener wet

with sealant BMS5-45. (a)

BOLT, PROTRUDING BACB30MY10K8X 7 0.325 - 0.328

HD

A

COLLAR BACC30M10 7 - (b)

Install the fastener wet

with sealant BMS5-45. (a)

BOLT, PROTRUDING BACB30MY10K12X 2 0.325 - 0.328

HD

B

COLLAR BACC30M10 2 - (b)

Install the fastener wet

with sealant BMS5-45. (a)

BOLT, PROTRUDING BACB30MY8K12X 1 0.263 - 0.266

HD

C

COLLAR BACC30M8 1 - (b)

(a) Install fasteners in accordance with 747-8P SRM 51-40-02 or 747-8F SRM 51-40-02

(b) Cap seal over the fastener threaded ends and collars inside the tank with sealant BMS5-45. Refer to

SOPM 20-50-19 as an accepted procedure.

The parts shown in the table below are provided as extra parts for this figure.

Name Identification Qty More Data

COLLAR BACC30M10 4

BOLT, PROTRUDING BACB30MY10K12X 1

HD

BOLT, PROTRUDING BACB30MY10K8X 1

HD

FIGURE 12: INBOARD COMPENSATOR MOUNTING BRACKET INSTALLATION - RIGHT SIDE

(SHEET 7 OF 7)

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BOEING SERVICE BULLETIN 747-27A2513
FIGURE 13: OUTBOARD COMPENSATOR MOUNTING BRACKET INSTALLATION - RIGHT SIDE

(SHEET 1 OF 7)

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FIGURE 13: OUTBOARD COMPENSATOR MOUNTING BRACKET INSTALLATION - RIGHT SIDE

(SHEET 2 OF 7)

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FIGURE 13: OUTBOARD COMPENSATOR MOUNTING BRACKET INSTALLATION - RIGHT SIDE

(SHEET 3 OF 7)

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BOEING SERVICE BULLETIN 747-27A2513
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.

Step Task Name Identification Qty More Data

MOUNTING BRACK- 252U3102-10 1 As shown in figure.

ET, RIGHT OUTBD -

COMPENSATOR, ELEVATOR PCU

1 Put / Hold

On the fwd side, the

fillers are under the

collars.

FILLER, RECTANGU- BACF3H10RF040HF 2

LAR

Put / Hold

The radius fillers are

between the head of

fasteners and bracket.

Put / Hold RADIUS FILLER BACF3H10RF010HG 2

Back drill the holes

through bracket and

radius fillers. Refer

to Fastener Code table for the hole diameter.

2 Drill / Ream Hole - 8

To the bracket, fillers

and web.

Deburr Hole - -

Non-designated

bond. Refer to SWPM 20-20-00,

Cleaning Procedure

1, as an accepted

procedure.

3 Clean Surface - -

Chemical Conversion ALODINE 600 - (b)

Coating

Apply

To mating surface of

bracket, fillers, web.

Refer to SWPM 20-

20-00, Category 2

fay surface bond, as

an accepted procedure.

Apply Sealant BMS5-45 -

FIGURE 13: OUTBOARD COMPENSATOR MOUNTING BRACKET INSTALLATION - RIGHT SIDE

(SHEET 4 OF 7)

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BOEING SERVICE BULLETIN 747-27A2513
Step Task Name Identification Qty More Data

Refer to SWPM 20-

20-00, Procedure 5,

as an accepted procedure.

4 Clean Surface - -

To mating surface of

bracket, fillers, web.

Refer to SOPM 20-

50-19 as an accepted procedure.

Apply Sealant BMS5-45 -

MOUNTING BRACK- 252U3102-10 1

ET, RIGHT OUTBD -

COMPENSATOR, ELEVATOR PCU

5 Install (New)

On the fwd side, under the collarsFILLER, RECTANGU- BACF3H10RF040HF 2

LAR

Install (New)

Refer to Fastener

Code table for fastener part number.

Install (New) Fastener - -

To mating surface of

fillers, Refer to

SOPM 20-50-19 as

an accepted procedure.

6 Apply Sealant BMS5-45 -

Under the head of

fasteners.

Install (New) RADIUS FILLER BACF3H10RF010HG 2

Refer to Fastener

Code table for fastener part number.

Install (New) Fastener - -

7 Measure Resistance - - (a)

Apply a fillet seal

around the bracket

where it connects to

the structure. Refer

to SOPM 20-50-19

as an accepted procedure.

8 Apply Sealant BMS5-142, TYPE II -

Chemical Conversion ALODINE 600 - (b)

Coating

9 Apply

Apply Primer BMS 10-11, TYPE 1 - (c)

(a) Between the bracket and structure. Maximum resistance is 0.0005 ohms. Refer to SWPM 20-20-00 as

an accepted procedure.

FIGURE 13: OUTBOARD COMPENSATOR MOUNTING BRACKET INSTALLATION - RIGHT SIDE

(SHEET 5 OF 7)

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BOEING SERVICE BULLETIN 747-27A2513
Step Task Name Identification Qty More Data

(b) Apply to bare metal surfaces. Refer to SOPM 20-43-03, as an accepted procedure.

(c) Apply 2 layers of the primer over the chemical conversion coating. Refer to SOPM 20-41-02, as an accepted procedure.

The codes shown below agree with the letter shown in the upper left corner of the fastener symbols in the figure.

A number in the lower right corner gives the grip length of the fastener. The QTY numbers shown below are the

number of fasteners necessary for this figure.

Code Name Identification Qty Hole Dia More Data

Install the fastener wet

with sealant BMS5-45. (a)

BOLT, PROTRUDING BACB30MY8K14X 4 0.263 - 0.266

HD

D

COLLAR BACC30M8 4 - (b)

Install the fastener wet

with sealant BMS5-45. (a)

BOLT, PROTRUDING BACB30MY8K9X 2 0.263 - 0.266

HD

E

COLLAR BACC30M8 2 - (b)

Install the fastener wet

with sealant BMS5-45. (a)

BOLT, PROTRUDING BACB30MY8K11X 2 0.263 - 0.266

HD

F

COLLAR BACC30M8 2 - (b)

(a) Install fasteners in accordance with 747-8P SRM 51-40-02 or 747-8F SRM 51-40-02

(b) Cap seal over the fastener threaded ends and collars inside the tank with sealant BMS5-45. Refer to

SOPM 20-50-19 as an accepted procedure.

The parts shown in the table below are provided as extra parts for this figure.

FIGURE 13: OUTBOARD COMPENSATOR MOUNTING BRACKET INSTALLATION - RIGHT SIDE

(SHEET 6 OF 7)

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Name Identification Qty More Data

COLLAR BACC30M8 5

FIGURE 13: OUTBOARD COMPENSATOR MOUNTING BRACKET INSTALLATION - RIGHT SIDE

(SHEET 7 OF 7)

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FIGURE 14: BRACKET INSTALLATION - RIGHT SIDE

(SHEET 1 OF 3)

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FIGURE 14: BRACKET INSTALLATION - RIGHT SIDE

(SHEET 2 OF 3)

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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 this figure.

Step Task Name Identification Qty More Data

1 Put / Hold BRACKET 69B80913-5 1 As shown in figure.

Up to 0.159 - 0.171

inch diameter.

2 Drill Hole - 2

Deburr Hole - -

To the bracket and

the frame. Refer to

SWPM 20-20-00,

Cleaning Procedure

5, as an accepted

procedure.

3 Clean Surface - -

Install (New) BRACKET 69B80913-5 1

RIVET, UNIVERSAL BACR15BB5D8C 2

HD

4 Install (New)

Chemical Conversion ALODINE 600 - (a)

Coating

5 Apply

Apply Primer BMS 10-11, TYPE 1 - (b)

(a) Apply to bare metal. Refer to SOPM 20-43-03, as an accepted procedure.

(b) Apply 2 layers of the primer over the chemical conversion coating. Refer to SOPM 20-41-02, as an accepted procedure.

The parts shown in the table below are provided as extra parts for this figure.

Name Identification Qty More Data

RIVET, UNIVERSAL BACR15BB5D8C 2

HD

FIGURE 14: BRACKET INSTALLATION - RIGHT SIDE

(SHEET 3 OF 3)

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FIGURE 15: COMPENSATORS AND HYDRAULIC TUBES INSTALLATION - RIGHT SIDE

(SHEET 1 OF 7)

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FIGURE 15: COMPENSATORS AND HYDRAULIC TUBES INSTALLATION - RIGHT SIDE

(SHEET 2 OF 7)

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FIGURE 15: COMPENSATORS AND HYDRAULIC TUBES INSTALLATION - RIGHT SIDE

(SHEET 3 OF 7)

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FIGURE 15: COMPENSATORS AND HYDRAULIC TUBES INSTALLATION - RIGHT SIDE

(SHEET 4 OF 7)

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BOEING SERVICE BULLETIN 747-27A2513
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.

Step Task Name Identification Qty More Data

REMOTE COMPEN- 463430-1001 2

SATOR - UPPER

RUDDER

1 Install (New)

Under the head of

fastener. Four (4)

per Compensator

2 Install (New) WASHER BACW10BP4AC 8

Four (4) per Compensator.Install (New) BOLT, HEX HEAD BACB30NM4K11 8

Four (4) per Compensator.Install (New) WASHER, PLAIN NAS1149E0432P 8

Four (4) per Compensator. Refer to

747-8P SRM 51-40-

04 and 747-8F SRM

51-40-04 as an accepted procedure for

the torque value.

Install (New) NUT BACN11Z4CD 8

ELBOW, SWVL-RDCR, BACE21AW0808W 1 (b), (c)

90

3 Install (New)

4 Install (New) TUBE ASSY 272U8290-40 1 (b), (c)

Use all kept screws,

washers and clip

nuts for the installation.

Install (Kept) Clamp - 5

5 Install (New) TUBE ASSY 272U8290-34 1 (b), (c)

Use all kept screws,

washers and clip

nuts for the installation.

Install (Kept) Clamp - 5

6 Install (New) TUBE ASSY 272U8290-39 1 (b), (c)

Use all kept screws,

washers and clip

nuts for the installation.

Install (Kept) Clamp - 5

7 Install (New) TEE, FLARELESS AS1005W100808 1 (b), (c)

FIGURE 15: COMPENSATORS AND HYDRAULIC TUBES INSTALLATION - RIGHT SIDE

(SHEET 5 OF 7)

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Step Task Name Identification Qty More Data

8 Install (New) TUBE ASSY 272U8290-35 1 (b), (c)

Use all kept screw,

washer and clip nut

for the installation.

Install (Kept) Clamp - 1

Use all the kept fastener and hardware9 Install (Kept) Clamp Block Assy - 1

To tubes assy

272U8290-39 and

272U8290-34.

10 Install (New) CLAMP,LOOP AS21919WCE08 2

Install (New) WASHER NAS1149D0316J 2

Install (New) SCREW BACS12GU3K8 1

Install (New) NUT BACN10YR3CD 1

ELBOW, SWVL-RDCR, BACE21AW0808W 2 (b), (c)

90

11 Install (New)

12 Install (New) TEE, SWIVEL ON RUN BACT16AY080808W 1 (b), (c)

(b), (c). Torque the

valve to 40-80 inchpounds to make

sure the valve is

seated.

13 Install (New) VALVE ASSY 293W6132-1 1

MS20995NC40 - (a)

(MS20995C41 optional)

Install (New) Lockwire

14 Install (New) TUBE ASSY 272U8290-38 1 (b), (c)

ELBOW, SWVL-RDCR, BACE21AW0808W 1 (b), (c)

90

15 Install (New)

AS4134V100808P 1 (b), (c)

(BACT16BN100808P

optional)

16 Install (New) TEE

Install (New) WASHER, PLAIN NAS1149D1432J 2

Install (Kept) Lock Nut - 1

(b), (c). Torque the

valve to 40-80 inchpounds to make

sure the valve is

seated.

17 Install (New) VALVE ASSY 293W6132-1 1

MS20995NC40 - (a)

(MS20995C41 optional)

Install (New) Lockwire

18 Install (New) TUBE ASSY 272U8290-37 1 (b), (c)

FIGURE 15: COMPENSATORS AND HYDRAULIC TUBES INSTALLATION - RIGHT SIDE

(SHEET 6 OF 7)

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BOEING SERVICE BULLETIN 747-27A2513
Step Task Name Identification Qty More Data

19 Install (New) NUT,CLIP-ON BACN10YD1 1

Install (New) CLAMP,LOOP AS21919WCE08 1

Install (New) WASHER NAS1149D0316J 1

Install (New) SCREW BACS12GU3K8 1

20 Install (New) CLAMP,LOOP AS21919WCE08 1

Install (New) SPACER BACS18AF4 1 (d)

Install (New) WASHER NAS1149D0316J 2

Install (New) SCREW BACS12GU3K8 1

Install (New) NUT BACN10YR3CD 1

Connect the tube

assy to the Compensator and Tee. (b),

(c)

21 Install (New) TUBE ASSY 272U8290-36 1

(a) Double-twist method. Refer to SOPM 20-50-02 as an accepted procedure.

(b) Refer to 747-8 AMM 20-11-05 as an accepted procedure.

(c) Refer to 747-8 AMM 20-51-01 as an accepted procedure for the torque value.

(d) Use spacers as necessary to make sure that the clamp holds the tube with minimum force. The maximum

permitted quantity of spacers for each clamp is 4.

The parts shown in the table below are provided as extra parts for this figure.

Name Identification Qty More Data

WASHER BACW10BP4AC 1

WASHER, PLAIN NAS1149E0432P 1

NUT BACN11Z4CD 1

WASHER NAS1149D0316J 3

NUT BACN10YR3CD 1

SCREW BACS12GU3K8 1

CLAMP,LOOP AS21919WCE08 2

BOLT, HEX HEAD BACB30NM4K11 1

SPACER BACS18AF4 4

FIGURE 15: COMPENSATORS AND HYDRAULIC TUBES INSTALLATION - RIGHT SIDE

(SHEET 7 OF 7)

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BOEING SERVICE BULLETIN 747-27A2513
FIGURE 16: WIRE BUNDLE W1912 AND W4616 ROUTING - RIGHT SIDE

(SHEET 1 OF 3)

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BOEING SERVICE BULLETIN 747-27A2513
FIGURE 16: WIRE BUNDLE W1912 AND W4616 ROUTING - RIGHT SIDE

(SHEET 2 OF 3)

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BOEING SERVICE BULLETIN 747-27A2513
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.

Step Task Name Identification Qty More Data

1 Route Wire Bundle W1912, W4616 -

One for each locationCLAMP, WIRE BUN- BACC10GU103 2

DLE

2 Install (New)

One for each locationSPACERS FOR RIV- NAS42DD6-64FC 2

ETS

Install (New)

One for each locationInstall (New) WASHER NAS1149D0332J 2

One for each locationInstall (New) SCREW BACS12GU3K26 2

3 Install (Kept) Clamp - 14

Install (Kept) Washer - 14

Install (Kept) Screw - 14

The parts shown in the table below are provided as extra parts for this figure.

Name Identification Qty More Data

WASHER NAS1149D0332J 2

FIGURE 16: WIRE BUNDLE W1912 AND W4616 ROUTING - RIGHT SIDE

(SHEET 3 OF 3)

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BOEING SERVICE BULLETIN 747-27A2513
FIGURE 17: INBOARD ELEVATOR POWER CONTROL PACKAGE (PCP) INSTALLATION - RIGHT SIDE

(SHEET 1 OF 4)

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FIGURE 17: INBOARD ELEVATOR POWER CONTROL PACKAGE (PCP) INSTALLATION - RIGHT SIDE

(SHEET 2 OF 4)

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BOEING SERVICE BULLETIN 747-27A2513
FIGURE 17: INBOARD ELEVATOR POWER CONTROL PACKAGE (PCP) INSTALLATION - RIGHT SIDE

(SHEET 3 OF 4)

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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 this figure.

Step Task Name Identification Qty More Data

Refer to 747-8 AMM

27-31-07 as an accepted procedure

POWER CONTROL 327400-1011 1

PACKAGE - INBOARD

ELEVATOR

1 Install (New)

2 Install (Kept) Hose Assy - 2 (a) (b)

Use the kept screw,

washer and clip nut

Install (Kept) Clamp - 1

3 Install (Kept) Hose Assy - 2 (a) (b)

Install (Kept) Clamp - 2

Install (Kept) Washer - 2

Install (Kept) Screw - 1

Install (New) NUT BACN10YR3CD 1

As shown in figure.

Refer to SOPM 20-

50-05 as an accepted procedure.

4 Install (New) MARKER BAC27EHY242 2

Refer to SOPM 20-

44-01 as accepted

procedures.

Clear Skydrol Resistant BAC5710, TYPE 41 -

Topcoating

5 Apply

(a) Refer to 747-8 AMM 20-11-18 as an accepted procedure.

(b) Refer to 747-8 AMM 20-51-01 as an accepted procedure for the torque value.

FIGURE 17: INBOARD ELEVATOR POWER CONTROL PACKAGE (PCP) INSTALLATION - RIGHT SIDE

(SHEET 4 OF 4)

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