Commercial 

Airplanes 747

Service Bulletin

ALERT

Number: 747-27A2515

Original Issue: August 23, 2013

ATA System: 2731 5520

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

Actuator (PCA) Installation - Inspection

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

BOEING PROPRIETARY, CONFIDENTIAL AND/OR TRADE SECRET

Copyright © 2013 Boeing.

Unpublished Work. All Rights Reserved.

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Table of Contents

Summary ...................................................... 5

1. PLANNING INFORMATION ........................................ 9

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

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

2. Spares Affected . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 10

B. Concurrent Requirements . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 10

C. Reason . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 10

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

E. Compliance . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 11

F. Approval . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 11

G. Manpower . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 12

H. Weight and Balance Changes . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 12

I. Electrical Load Data . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 12

J. References . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 12

1. Existing Data: . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 12

2. Data Supplied with this Service Bulletin: . . . . . . . . . . . . . . . . . . . . . . . . . . . 13

3. Installation Drawings Used in the Preparation of this Service Bulletin: . . . . . . . . . . . 13

K. Publications Affected . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 13

L. Interchangeability and Intermixability of Parts . . . . . . . . . . . . . . . . . . . . . . . . . . . 13

M. Software Accomplishment Summary . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 13

2. MATERIAL INFORMATION . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 15

A. Material - Price and Availability . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 15

B. Industry Support Information . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 15

C. Parts Necessary for Each Airplane . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 15

1. Kits/Parts . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 15

2. Parts and Materials Supplied by the Operator . . . . . . . . . . . . . . . . . . . . . . . . 15

3. Parts Modified and Reidentified . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 15

4. Parts Removed and Not Replaced . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 15

D. Parts Necessary to Change Spares . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 15

E. Special Tooling - Price and Availability . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 15

F. Special Tooling Necessary to do this Service Bulletin . . . . . . . . . . . . . . . . . . . . . . . 15

3. ACCOMPLISHMENT INSTRUCTIONS . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 17

A. GENERAL INFORMATION . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 17

B. WORK INSTRUCTIONS . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 19

FIGURE 1: LEFT INBOARD ELEVATOR POWER CONTROL ACTUATOR (PCA) INSTALLATION -

BUSHING INSPECTION . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 22

FIGURE 2: RIGHT INBOARD ELEVATOR POWER CONTROL ACTUATOR (PCA) INSTALLATION -

BUSHING INSPECTION . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 26

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Commercial 

Airplanes 747

Service Bulletin

ALERT

Summary Number: 747-27A2515

Original Issue: August 23, 2013

ATA System: 2731 5520

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

Actuator (PCA) Installation - Inspection

THIS BULLETIN IS SENT TO THE OPERATORS OF RECORD OF THE AIRPLANES SHOWN IN PARAGRAPH

1.A., EFFECTIVITY. IF AN AIRPLANE HAS BEEN LEASED OR SOLD, SEND THIS SERVICE BULLETIN TO

THE NEW OPERATOR. IF APPLICABLE SPARES HAVE BEEN SOLD, SEND THIS SERVICE BULLETIN TO

THE NEW OWNER.

CONCURRENT REQUIREMENTS

None.

BACKGROUND

This service bulletin gives instructions to inspect the left and right inboard elevator power control actuator (PCA)

installations to make sure that bushings are installed where the actuator rod ends are attached to the lugs. It

also gives instructions to inspect the general area around each actuator, to make sure that there are no other

defects or damage. If the bushings are not installed, the stiffness of the load path will be decreased, which will

cause wear of adjacent parts and increased freeplay of the elevator surfaces. Freeplay which exceeds acceptable

limits could result in divergent flutter for maneuvers above 1.6 g, which could lead to loss of controllability of the

airplane.

During a recent C-check, an operator heard an unusual noise coming from the left inboard elevator during a

functional check of the ram air turbine system. When investigating the cause of the noise, the operator found

too much freeplay in the left inboard elevator, which they traced to a missing bushing in the PCA installation. A

Boeing quality investigation found that the left inboard PCA had been disconnected from this airplane to replace

the left elevator, which had been damaged before delivery. When the PCA was reconnected, however, the

bushing was not installed. The operator did a detailed inspection of the PCA installation and a high-frequency

eddy current (HFEC) inspection of the PCA attachment lug assembly, and found no other defects or damage.

As part of the Boeing quality investigation, all 747-8 airplanes currently in production were inspected to make

sure that the bushings were installed on both the left and right sides. Boeing also inspected each production

airplane between the horizontal stabilizer rear spar and the elevator front spar to make sure that there were no

other defects or damage. This service bulletin was written for operators to do the same inspections on airplanes

that have been delivered.

Boeing Service Related Problem (SRP) 747-8-SRP-27-0241 is related to this service bulletin.

Boeing Fleet Team Digest (FTD) 747 FTD 27-13005 is related to this service bulletin.

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

information.

Planning Data Affected Reference

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

Paragraph 1.E., Compliance and Paragraph

1.F., Approval

AD Related Yes

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

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

Publications Affected No Paragraph 1.K., Publications Affected

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

Operations Manual and/or FAA Approved Airplane Flight Manual)

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

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

by the Operator

Operator Supplied Parts/Material No

Paragraph 2.F., Special Tooling Necessary to

do this Service Bulletin

Special Tooling Required No

ACTION

Open access to the left and right inboard elevator PCA installations. Do a detailed inspection of each PCA

installation to find if a bushing is installed, in accordance with PART 1. On each side, do a general visual

inspection for defects or damage in accordance with PART 2. If a bushing is not installed, or if any defect or

damage is found during the general visual inspection, contact Boeing for repair instructions and do the repair.

Close access.

EFFECTIVITY

747-8 and -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.

Refer to Paragraph 1.E., Compliance.

INDUSTRY SUPPORT INFORMATION

At the time of release of this service bulletin, warranty remedies have not been determined. A subsequent

revision or Information Notice will address the warranty remedies available, if any.

MANPOWER

Refer to Paragraph 1.G., Manpower.

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MATERIAL INFORMATION

None.

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BLANK PAGE
Commercial 

Airplanes 747

Service Bulletin

ALERT

Number: 747-27A2515

Original Issue: August 23, 2013

ATA System: 2731 5520

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

Actuator (PCA) Installation - Inspection

THIS BULLETIN IS SENT TO THE OPERATORS OF RECORD OF THE AIRPLANES SHOWN IN PARAGRAPH

1.A., EFFECTIVITY. IF AN AIRPLANE HAS BEEN LEASED OR SOLD, SEND THIS SERVICE BULLETIN TO

THE NEW OPERATOR. IF APPLICABLE SPARES HAVE BEEN SOLD, SEND THIS SERVICE BULLETIN TO

THE NEW OWNER.

1. PLANNING INFORMATION

A. Effectivity

1. Airplanes

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 airplane(s) shown below.

GROUP CONFIGURATION DESCRIPTION

1 - All affected airplanes

Airplane Models:

747-8, 747-8F

Variable Number Group

RC001 - RC008 1

RC022 - RC029 1

RC501 - RC508 1

RC522 - RC523 1

RC541 1

RC546 - RC547 1

RC551 - RC552 1

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Variable Number Group

RC554 - RC560 1

RC571 - RC572 1

RC574 - RC582 1

RC601 - RC603 1

2. Spares Affected

None.

B. Concurrent Requirements

None.

C. Reason

This service bulletin gives instructions to inspect the left and right inboard elevator power control actuator

(PCA) installations to make sure that bushings are installed where the actuator rod ends are attached

to the lugs. It also gives instructions to inspect the general area around each actuator, to make sure

that there are no other defects or damage. If the bushings are not installed, the stiffness of the load

path will be decreased, which will cause wear of adjacent parts and increased freeplay of the elevator

surfaces. Freeplay which exceeds acceptable limits could result in divergent flutter for maneuvers

above 1.6 g, which could lead to loss of controllability of the airplane.

During a recent C-check, an operator heard an unusual noise coming from the left inboard elevator

during a functional check of the ram air turbine system. When investigating the cause of the noise, the

operator found too much freeplay in the left inboard elevator, which they traced to a missing bushing

in the PCA installation. A Boeing quality investigation found that the left inboard PCA had been

disconnected from this airplane to replace the left elevator, which had been damaged before delivery.

When the PCA was reconnected, however, the bushing was not installed. The operator did a detailed

inspection of the PCA installation and a high-frequency eddy current (HFEC) inspection of the PCA

attachment lug assembly, and found no other defects or damage.

As part of the Boeing quality investigation, all 747-8 airplanes currently in production were inspected

to make sure that the bushings were installed on both the left and right sides. Boeing also inspected

each production airplane between the horizontal stabilizer rear spar and the elevator front spar to make

sure that there were no other defects or damage. This service bulletin was written for operators to do

the same inspections on airplanes that have been delivered.

Boeing Service Related Problem (SRP) 747-8-SRP-27-0241 is related to this service bulletin.

Boeing Fleet Team Digest (FTD) 747 FTD 27-13005 is related to this service bulletin.

D. Description

Open access to the left and right inboard elevator PCA installations. Do a detailed inspection of each

PCA installation to find if a bushing is installed, in accordance with PART 1. On each side, do a general

visual inspection for defects or damage in accordance with PART 2. If a bushing is not installed, or if

any defect or damage is found during the general visual inspection, contact Boeing for repair instructions

and do the repair. Close access.

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

Affected Maintenance Zones

Model Zone

747-8, 747-8F 334, 344

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.

Do the required actions in accordance with Paragraph 3. Accomplishment Instructions.

Table 1: Inboard Elevator Power Control Actuator (PCA) Installations - Detailed and General Visual Inspections

Repeat Interval

(Not to Exceed)

Condition Action Compliance Time

Within 60 days after -

the Original Issue

date of this service

bulletin.

Do PART 1: INBOARD ELEVATOR PCA INSTALLATIONS -

DETAILED INSPECTION.

All Airplanes

Do PART 2: INBOARD ELEVATOR PCA INSTALLATIONS -

GENERAL VISUAL INSPECTION.

CONDITION 1: BUSHING IN- No more work is necessary. - -

STALLED IN BOTH THE LEFT

AND RIGHT PCA INSTALLATIONS

AND NO DEFECT OR DAMAGE

FOUND DURING GENERAL VISUAL INSPECTION

Contact Boeing for repair instruc- Before further flight. -

tions and do the repair.

CONDITION 2: BUSHING NOT

INSTALLED IN THE LEFT OR

RIGHT PCA INSTALLATION, OR

ANY DEFECT OR DAMAGE

FOUND DURING GENERAL VISUAL INSPECTION

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.

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BOEING SERVICE BULLETIN 747-27A2515

ALERT ALERT
If an airplane has a non-Boeing modification or repair that affects a component or system also affected

by this service bulletin, the operator is responsible for obtaining appropriate regulatory agency approval

before incorporating this service bulletin.

G. Manpower

The table below shows an estimate of the task hours necessary to do this inspection for each airplane.

This estimate is for direct labor only, done by an experienced crew. Adjust the estimate with operator

task hour data if necessary. The estimate does not include lost time. These are some examples of lost

time:

• Time to adjust to the workplace

• Time to schedule the work

• Time to inspect the work

• Time to cure the materials

• Time to make the parts

• Time to find the tools.

Task Number of Persons Task Hours Elapsed Hours

Open Access 2 1.00 0.50

PART 1, Figure 1 1 0.50 0.50

PART 1, Figure 2 1 0.50 0.50

PART 2, Left Side 1 1.00 1.00

PART 2, Right Side 1 1.00 1.00

Close Access 2 1.00 0.50

TOTAL FOR EACH AIRPLANE 5.00 4.00

H. Weight and Balance Changes

None.

I. Electrical Load Data

Not applicable.

J. References

1. Existing Data:

a. Boeing Service Letter 747-SL-51-048

b. Boeing Service Related Problem (SRP) 747-8-SRP-27-0241

c. Service Bulletin Index D6-30300

d. 747 Fleet Team Digest (FTD) 27-13005

e. 747-8 Aircraft Maintenance Manual (AMM) 06-09-05, 06-09-06, 29-11-00

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BOEING SERVICE BULLETIN 747-27A2515

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2. Data Supplied with this Service Bulletin:

None.

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

Drawing Number Title

251U2500 POWER CONTROL ACTUATOR INSTL - INBOARD ELEVATOR

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.

K. Publications Affected

1. Publications:

None.

2. Damage Tolerance Based Structural Inspections:

Boeing has evaluated the repairs and/or changes in this service bulletin for effects on Fatigue

Critical Structure (FCS) and for changes to Damage Tolerance Inspections (DTI) required in the

Maintenance Program. This service bulletin does not affect FCS, therefore DTIs are not necessary.

L. Interchangeability and Intermixability of Parts

Accomplishment of this service bulletin does not affect interchangeability or intermixability of parts.

M. Software Accomplishment Summary

Not affected.

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2. MATERIAL INFORMATION

A. Material - Price and Availability

None.

B. Industry Support Information

At the time of release of this service bulletin, warranty remedies have not been determined. A subsequent

revision or Information Notice will address the warranty remedies available, if any.

C. Parts Necessary for Each Airplane

1. Kits/Parts

None.

2. Parts and Materials Supplied by the Operator

None.

3. Parts Modified and Reidentified

None.

4. Parts Removed and Not Replaced

None.

D. Parts Necessary to Change Spares

None.

E. Special Tooling - Price and Availability

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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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. A Detailed Inspection is defined as: An intensive examination of a specific item,

installation, or assembly to detect damage, failure, or irregularity. Available lighting

is normally supplemented with a direct source of good lighting at an intensity deemed

appropriate. Inspection aids such as mirrors, magnifying lenses, etc. may be

necessary. Surface cleaning and elaborate procedures may be required.

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6. A General Visual Inspection is defined as: A visual examination of an interior or

exterior area, installation or assembly to detect obvious damage, failure or irregularity.

This level of inspection is made from within touching distance unless otherwise

specified. A mirror may be necessary to enhance visual access to all exposed surfaces

in the inspection area. This level of inspection is made under normally available

lighting conditions such as daylight, hangar lighting, flashlight or drop-light and may

require removal or opening of access panels or doors. Stands, ladders or platforms

may be required to gain proximity to the area being checked.

7. 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.

8. Boeing Service Letter 747-SL-51-048, Damage Reporting and Repair Plan/Design

Guidelines, is an acceptable procedure to request information from Boeing for

additional structural repair instructions. The Service Letter describes what information

must be provided to Boeing before a structural repair can be provided.

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

non-authoritative information from the critical and authoritative information.

12. When more than one OPTION is given for a CONDITION, do only one of the OPTION

numbers. When more than one ACTION is given for a CONDITION number or an

OPTION number, do all of the ACTION numbers for that CONDITION number or

OPTION number.

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

are in Paragraph 1.E., Compliance.

14. The CONDITIONS, ACTIONS and OPTIONS shown apply to each side independently.

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.

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ALERT ALERT
B. WORK INSTRUCTIONS

WARNING: MAKE SURE THAT PERSONS AND EQUIPMENT ARE CLEAR OF ALL OF THE

CONTROL SURFACES BEFORE YOU DO THE PROCEDURE TO REMOVE HYDRAULIC

POWER. THE AILERONS, RUDDERS, ELEVATORS, FLAPS, SPOILERS, LANDING

GEAR, AND THRUST REVERSERS CAN MOVE QUICKLY. THIS CAN CAUSE INJURY

TO PERSONS AND DAMAGE TO EQUIPMENT.

1. To release the hydraulic pressure from the left inboard elevator power control actuator (PCA), do

these steps:

a. Release the pressure from hydraulic system No. 1. Refer to 747-8 AMM 29-11-00, Hydraulic

System Depressurization, as an accepted procedure.

b. Move the control column in each direction to remove all of the remaining pressure from the

PCA.

c. Release the pressure from hydraulic system No. 2. Refer to 747-8 AMM 29-11-00, Hydraulic

System Depressurization, as an accepted procedure.

2. To release the hydraulic pressure from the right inboard elevator PCA, do these steps:

a. Release the pressure from hydraulic system No. 4. Refer to 747-8 AMM 29-11-00, Hydraulic

System Depressurization, as an accepted procedure.

b. Move the control column in each direction to remove all of the remaining pressure from the

PCA.

c. Release the pressure from hydraulic system No. 3. Refer to 747-8 AMM 29-11-00, Hydraulic

System Depressurization, as an accepted procedure.

3. On the Overhead Maintenance Panel, set all FLT CONTROL HYD POWER TAIL switches to

SHUTOFF. Attach a DO-NOT-OPERATE tag to each switch.

4. On the control stand, set the STAB TRIM 2 and 3 switches to CUTOUT. Attach a

DO-NOT-OPERATE tag to each switch.

5. Open these circuit breakers and attach DO-NOT-CLOSE tags:

Panel Row/Col Number Name

DC Power Distribution E7 C00652 SYS 2 ELEV/RUD VALVE

Panel, P180 E22 C00657 SYS 4 ELEV/RUD VALVE

H8 C00648 SYS 1 ELEV/RUD VALVE

H23 C00654 SYS 3 ELEV/RUD VALVE

Overhead Circuit Breaker E7 C08771 STAB TRIM S/O-LEFT

Panel, P7 E20 C08773 STAB TRIM S/O-RIGHT

6. Open access panels 334HBL, 344HBR, and 315AL. Refer to 747-8 AMM 06-09-05 and 747-8

AMM 06-09-06.

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BOEING SERVICE BULLETIN 747-27A2515

ALERT ALERT
7. To prevent elevator linkage movement during the inspections, install rig pin E-2 at the bottom of

the elevator aft quadrant.

8. RC - Do PART 1: INBOARD ELEVATOR PCA INSTALLATIONS - DETAILED INSPECTION.

9. RC - Do PART 2: INBOARD ELEVATOR PCA INSTALLATIONS - GENERAL VISUAL INSPECTION.

10. Do the applicable step:

CONDITION 1: BUSHING INSTALLED IN BOTH THE LEFT AND RIGHT PCA INSTALLATIONS

AND NO DEFECT OR DAMAGE FOUND DURING GENERAL VISUAL INSPECTION

a. No more work is necessary.

CONDITION 2: BUSHING NOT INSTALLED IN THE LEFT OR RIGHT PCA INSTALLATION,

OR ANY DEFECT OR DAMAGE FOUND DURING GENERAL VISUAL INSPECTION

a. RC - Contact Boeing for repair instructions and do the repair.

11. Remove rig pin E-2 from the bottom of the elevator aft quadrant.

12. Close access panels 334HBL, 344HBR, and 315AL. Refer to 747-8 AMM 06-09-05 and 747-8

AMM 06-09-06.

13. Remove the DO-NOT-CLOSE tags and close these circuit breakers:

Panel Row/Col Number Name

DC Power Distribution E7 C00652 SYS 2 ELEV/RUD VALVE

Panel, P180 E22 C00657 SYS 4 ELEV/RUD VALVE

H8 C00648 SYS 1 ELEV/RUD VALVE

H23 C00654 SYS 3 ELEV/RUD VALVE

Overhead Circuit Breaker E7 C08771 STAB TRIM S/O-LEFT

Panel, P7 E20 C08773 STAB TRIM S/O-RIGHT

14. On the Overhead Maintenance Panel, remove the DO-NOT-OPERATE tags and set all FLT

CONTROL HYD POWER TAIL switches to NORM.

15. On the control stand, remove the DO-NOT-OPERATE tags and set the STAB TRIM 2 and 3

switches to ON.

16. Put the airplane back to a serviceable condition.

PART 1: INBOARD ELEVATOR PCA INSTALLATIONS - DETAILED INSPECTION

1. Do a detailed inspection of the left PCA installation to find if a bushing is installed, in accordance

with FIGURE 1.

2. Do a detailed inspection of the right PCA installation to find if a bushing is installed, in accordance

with FIGURE 2.

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ALERT ALERT
PART 2: INBOARD ELEVATOR PCA INSTALLATIONS - GENERAL VISUAL INSPECTION

1. Do a general visual inspection of the area between the left horizontal stabilizer rear spar and the

elevator front spar, and between STAB STA 235 and 260. Look for defects and damage.

2. Do a general visual inspection of the area between the right horizontal stabilizer rear spar and the

elevator front spar, and between STAB STA 235 and 260. Look for defects and damage.

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ALERT ALERT
FIGURE 1: LEFT INBOARD ELEVATOR POWER CONTROL ACTUATOR (PCA) INSTALLATION - BUSHING

INSPECTION

(SHEET 1 OF 4)

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ALERT ALERT
FIGURE 1: LEFT INBOARD ELEVATOR POWER CONTROL ACTUATOR (PCA) INSTALLATION - BUSHING

INSPECTION

(SHEET 2 OF 4)

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ALERT ALERT
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.

FIGURE 1: LEFT INBOARD ELEVATOR POWER CONTROL ACTUATOR (PCA) INSTALLATION - BUSHING

INSPECTION

(SHEET 3 OF 4)

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ALERT ALERT
Step Task Name Identification Qty More Data

1 Inspect Bushing 69B81740-23 1 (a) (b)

(a) Do a detailed inspection to find if the bushing is installed.

(b) If you cannot clearly see the bushing, use view A-A to find if the bushing is installed.

FIGURE 1: LEFT INBOARD ELEVATOR POWER CONTROL ACTUATOR (PCA) INSTALLATION - BUSHING

INSPECTION

(SHEET 4 OF 4)

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ALERT ALERT
FIGURE 2: RIGHT INBOARD ELEVATOR POWER CONTROL ACTUATOR (PCA) INSTALLATION - BUSHING

INSPECTION

(SHEET 1 OF 4)

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ALERT ALERT
FIGURE 2: RIGHT INBOARD ELEVATOR POWER CONTROL ACTUATOR (PCA) INSTALLATION - BUSHING

INSPECTION

(SHEET 2 OF 4)

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BOEING SERVICE BULLETIN 747-27A2515

ALERT ALERT
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.

FIGURE 2: RIGHT INBOARD ELEVATOR POWER CONTROL ACTUATOR (PCA) INSTALLATION - BUSHING

INSPECTION

(SHEET 3 OF 4)

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BOEING SERVICE BULLETIN 747-27A2515

ALERT ALERT
Step Task Name Identification Qty More Data

1 Inspect Bushing 69B81740-23 1 (a) (b)

(a) Do a detailed inspection to find if the bushing is installed.

(b) If you cannot clearly see the bushing, use view A-A to find if the bushing is installed.

FIGURE 2: RIGHT INBOARD ELEVATOR POWER CONTROL ACTUATOR (PCA) INSTALLATION - BUSHING

INSPECTION

(SHEET 4 OF 4)

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BOEING SERVICE BULLETIN 747-27A2515

ALERT ALERT