# Boeing Alert Service Bulletin 747-27A2515: No revision named

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- Title as filed: U.S. DOT/FAA - SB-747-27A2515-00
- Pages: 29
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## Text

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### Page 1

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
CFR 300-774). An export license may be required before it is used for development, production or use by foreign
persons from specific countries. The controller of this data has the individual responsibility to abide by all export
laws.
9E991ECCN:
BOEING PROPRIETARY, CONFIDENTIAL AND/OR TRADE SECRET
Copyright © 2013 Boeing.
Unpublished Work. All Rights Reserved.
Treatment of this document and its content is governed by contract with Boeing. Rights to use this document
are licensed on a per aircraft basis and such rights may not be transferable. For more information, contact The
Boeing Company.
Boeing, the Boeing signature, the Boeing symbol, 707, 717, 727, 737, 747, 757, 767, 777, 787, Dreamliner,
BBJ, DC-8, DC-9, DC-10, KC-10, KC-46, KDC-10, MD-10, MD-11, MD-80, MD-88, MD-90, P-8, Poseidon and
Boeing liveries are all trademarks owned by The Boeing Company; and no trademark license is granted in
connection with this document unless provided in writing by Boeing.
Original Issue: August 23, 2013
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2.0

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Table of Contents
Summary ...................................................... 5
1. PLANNING INFORMATION ........................................ 9
A. Effectivity ................................................ 9
1. Airplanes ............................................. 9
2. Spares Affected ........................................ 1 0
B. Concurrent Requirements ...................................... 1 0
C. Reason ................................................ 1 0
D. Description .............................................. 1 0
E. Compliance .............................................. 1 1
F. Approval ............................................... 1 1
G. Manpower .............................................. 1 2
H. Weight and Balance Changes .................................... 1 2
I. Electrical Load Data ......................................... 1 2
J. References .............................................. 1 2
1. Existing Data: ......................................... 1 2
2. Data Supplied with this Service Bulletin: ........................... 1 3
3. Installation Drawings Used in the Preparation of this Service Bulletin: ........... 1 3
K. Publications Affected ........................................ 1 3
L. Interchangeability and Intermixability of Parts ........................... 1 3
M. Software Accomplishment Summary ................................ 1 3
2. MATERIAL INFORMATION ........................................ 1 5
A. Material - Price and Availability ................................... 1 5
B. Industry Support Information .................................... 1 5
C. Parts Necessary for Each Airplane ................................. 1 5
1. Kits/Parts ............................................ 1 5
2. Parts and Materials Supplied by the Operator ........................ 1 5
3. Parts Modified and Reidentified ................................ 1 5
4. Parts Removed and Not Replaced .............................. 1 5
D. Parts Necessary to Change Spares ................................. 1 5
E. Special Tooling - Price and Availability ............................... 1 5
F. Special Tooling Necessary to do this Service Bulletin ....................... 1 5
3. ACCOMPLISHMENT INSTRUCTIONS .................................. 1 7
A. GENERAL INFORMATION ..................................... 1 7
B. WORK INSTRUCTIONS ....................................... 1 9
FIGURE 1: LEFT INBOARD ELEVATOR POWER CONTROL ACTUATOR (PCA) INSTALLATION -
BUSHING INSPECTION .................................... 2 2
FIGURE 2: RIGHT INBOARD ELEVATOR POWER CONTROL ACTUATOR (PCA) INSTALLATION -
BUSHING INSPECTION .................................... 2 6
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Commercial 
Airplanes
747
Service Bulletin
ALERT
SummaryNumber: 747-27A2515Original 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.
ReferenceAffectedPlanning Data
Paragraph 1.A.2., Spares AffectedNoSpares Affected
Paragraph 1.E., Compliance and Paragraph
1.F., Approval
YesAD Related
Paragraph 1.H., Weight and Balance ChangesNoWeight and Balance Change
Paragraph 1.I., Electrical Load DataNoElectrical Load Changed
Paragraph 1.K., Publications AffectedNoPublications Affected
Paragraph 1.K., Publications AffectedNoAirplane Flight Operations Affected (Flight Crew
Operations Manual and/or FAA Approved Air-
plane Flight Manual)
Paragraph 2.C.1., Kits/PartsNoKits/Parts Required
Paragraph 2.C.2., Parts and Materials Supplied
by the Operator
NoOperator Supplied Parts/Material
Paragraph 2.F., Special Tooling Necessary to
do this Service Bulletin
NoSpecial Tooling Required
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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BOEING SERVICE BULLETIN 747-27A2515
ALERT  ALERT
MATERIAL INFORMATION
None.
STABILIZER  REAR SPAR  DO A GENERAL VISUAL  INSPECTION FOR  DEFECTS OR DAMAGE
INBOARD
ELEVATOR
FWD
ELEVATOR
ACTUATOR
LUG
LEFT SIDE SHOWN
RIGHT SIDE OPPOSITE
NBD  ACTUATOR
DO A DETAILED  ROD
INSPECTION TO SEE IF A  BUSHING IS INSTALLED  FWD  2276950
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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.
DESCRIPTIONCONFIGURATIONGROUP
All affected airplanes-1
Airplane Models:
747-8, 747-8F
GroupVariable Number
1RC001 - RC008
1RC022 - RC029
1RC501 - RC508
1RC522 - RC523
1RC541
1RC546 - RC547
1RC551 - RC552
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GroupVariable Number
1RC554 - RC560
1RC571 - RC572
1RC574 - RC582
1RC601 - RC603
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
ZoneModel
334, 344747-8, 747-8F
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 In-
spections
Repeat Interval
(Not to Exceed)
Compliance TimeActionCondition
-Within 60 days after
the Original Issue
date of this service
bulletin.
Do PART 1: INBOARD ELEVA-
TOR PCA INSTALLATIONS -
DETAILED INSPECTION.
All Airplanes
Do PART 2: INBOARD ELEVA-
TOR PCA INSTALLATIONS -
GENERAL VISUAL INSPEC-
TION.
--No more work is necessary.CONDITION 1: BUSHING IN-
STALLED IN BOTH THE LEFT
AND RIGHT PCA INSTALLATIONS
AND NO DEFECT OR DAMAGE
FOUND DURING GENERAL VISU-
AL INSPECTION
-Before further flight.Contact Boeing for repair instruc-
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 VISU-
AL 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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If an airplane has a non-Boeing modification or repair that affects a component or system also affected
by this service bulletin, the operator is responsible for obtaining appropriate regulatory agency approval
before incorporating this service bulletin.
G. Manpower
The table below shows an estimate of the task hours necessary to do this inspection for each airplane.
This estimate is for direct labor only, done by an experienced crew. Adjust the estimate with operator
task hour data if necessary. The estimate does not include lost time. These are some examples of lost
time:
 Time to adjust to the workplace
 Time to schedule the work
 Time to inspect the work
 Time to cure the materials
 Time to make the parts
 Time to find the tools.
Elapsed HoursTask HoursNumber of PersonsTask
0.501.002Open Access
0.500.501PART 1, Figure 1
0.500.501PART 1, Figure 2
1.001.001PART 2, Left Side
1.001.001PART 2, Right Side
0.501.002Close Access
4.005.00TOTAL FOR EACH AIRPLANE
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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2. Data Supplied with this Service Bulletin:
None.
3. Installation Drawings Used in the Preparation of this Service Bulletin:
TitleDrawing Number
POWER CONTROL ACTUATOR INSTL - INBOARD ELEVATOR251U2500
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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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:
NameNumberRow/ColPanel
SYS 2 ELEV/RUD VALVEC00652E7DC Power Distribution
Panel, P180 SYS 4 ELEV/RUD VALVEC00657E22
SYS 1 ELEV/RUD VALVEC00648H8
SYS 3 ELEV/RUD VALVEC00654H23
STAB TRIM S/O-LEFTC08771E7Overhead Circuit Breaker
Panel, P7 STAB TRIM S/O-RIGHTC08773E20
6. Open access panels 334HBL, 344HBR, and 315AL. Refer to 747-8 AMM 06-09-05 and 747-8
AMM 06-09-06.
Export Controlled ECCN: 9E991 - BOEING
PROPRIETARY - Copyright © Unpublished
Work - See page 1 for details.
Original Issue: August 23, 2013
747-27A2515
19 of 29
BOEING SERVICE BULLETIN 747-27A2515
ALERTALERT

### Page 20

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:
NameNumberRow/ColPanel
SYS 2 ELEV/RUD VALVEC00652E7DC Power Distribution
Panel, P180 SYS 4 ELEV/RUD VALVEC00657E22
SYS 1 ELEV/RUD VALVEC00648H8
SYS 3 ELEV/RUD VALVEC00654H23
STAB TRIM S/O-LEFTC08771E7Overhead Circuit Breaker
Panel, P7 STAB TRIM S/O-RIGHTC08773E20
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.
Export Controlled ECCN: 9E991 - BOEING
PROPRIETARY - Copyright © Unpublished
Work - See page 1 for details.
Original Issue: August 23, 2013
747-27A2515
20 of 29
BOEING SERVICE BULLETIN 747-27A2515
ALERTALERT

### Page 21

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.
Export Controlled ECCN: 9E991 - BOEING
PROPRIETARY - Copyright © Unpublished
Work - See page 1 for details.
Original Issue: August 23, 2013
747-27A2515
21 of 29
BOEING SERVICE BULLETIN 747-27A2515
ALERTALERT

### Page 22 (OCR)

BOEING SERVICE BULLETIN 747-27A2515
ALERT  ALERT
STABILIZER
REAR SPAR
ACTUATOR'
ROD  INBOARD
ELEVATOR
ACTUATOR
LUG
FWD
2276951
FIGURE 1: LEFT INBOARD ELEVATOR POWER CONTROL ACTUATOR (PCA) INSTALLATION- BUSHING
INSPECTION
(SHEET 1 OF 4)
Original Issue: August 23, 2013
PROPRIETARY - Copyright © Unpublished  Export Controlled ECCN: 9E991 - BOEING  747-27A2515
Work - See page 1 for details.  22 of 29

### Page 23

FIGURE 1: LEFT INBOARD ELEVATOR POWER CONTROL ACTUATOR (PCA) INSTALLATION - BUSHING
INSPECTION
(SHEET 2 OF 4)
Export Controlled ECCN: 9E991 - BOEING
PROPRIETARY - Copyright © Unpublished
Work - See page 1 for details.
Original Issue: August 23, 2013
747-27A2515
23 of 29
BOEING SERVICE BULLETIN 747-27A2515
ALERTALERT

### Page 24 (OCR)

BOEING SERVICE BULLETIN 747-27A2515
ALERT  ALERT
POWER CONTROL
NUT  - ACTUATOR
WASHER
NUT.
0.31/
0.237
BUSHING NOT INSTALLED
BUSHING
POWER CONTROL
NUT  • ACTUATOR
WASHER
NUT
0.153
0.087
BUSHING INSTALLED
A-A  2276954
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)
Original Issue: August 23, 2013
Export Controlled ECCN: 9E991 - BOEING  PROPRIETARY - Copyright © Unpublished  747-27A2515
Work - See page 1 for details.  24 of 29

### Page 25

More DataQtyIdentificationNameTaskStep
(a) (b)169B81740-23BushingInspect1
(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)
Export Controlled ECCN: 9E991 - BOEING
PROPRIETARY - Copyright © Unpublished
Work - See page 1 for details.
Original Issue: August 23, 2013
747-27A2515
25 of 29
BOEING SERVICE BULLETIN 747-27A2515
ALERTALERT

### Page 26 (OCR)

BOEING SERVICE BULLETIN 747-27A2515
ALERT  ALERT
STABILIZER
REAR SPAR
* ACTUATOR
INBOARD  ROD
ELEVATOR
ACTUATOR  B
LUG
FWD
2276955
FIGURE 2: RIGHT INBOARD ELEVATOR POWER CONTROL ACTUATOR (PCA) INSTALLATION - BUSHING
INSPECTION
(SHEET 1 OF 4)
Original Issue: August 23, 2013
PROPRIETARY - Copyright © Unpublished  Export Controlled ECCN: 9E991 - BOEING  747-27A2515
Work - See page 1 for details.  26 of 29

### Page 27

FIGURE 2: RIGHT INBOARD ELEVATOR POWER CONTROL ACTUATOR (PCA) INSTALLATION - BUSHING
INSPECTION
(SHEET 2 OF 4)
Export Controlled ECCN: 9E991 - BOEING
PROPRIETARY - Copyright © Unpublished
Work - See page 1 for details.
Original Issue: August 23, 2013
747-27A2515
27 of 29
BOEING SERVICE BULLETIN 747-27A2515
ALERTALERT

### Page 28 (OCR)

BOEING SERVICE BULLETIN 747-27A2515
ALERT  ALERT
POWER CONTROL
ACTUATOR  NUT
WASHER
_ NUT
10.317  0.23
BUSHING NOT INSTALLED
BUSHING
POWER CONTROL  NUT
ACTUATOR
WASHER
_NUT
0.153
- 0.087
BUSHING INSTALLED
A-A  2276957
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)
Original Issue: August 23, 2013
Export Controlled ECCN: 9E991 - BOEING  PROPRIETARY - Copyright © Unpublished  747-27A2515
Work - See page 1 for details.  28 of 29

### Page 29

More DataQtyIdentificationNameTaskStep
(a) (b)169B81740-23BushingInspect1
(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)
Export Controlled ECCN: 9E991 - BOEING
PROPRIETARY - Copyright © Unpublished
Work - See page 1 for details.
Original Issue: August 23, 2013
747-27A2515
29 of 29
BOEING SERVICE BULLETIN 747-27A2515
ALERTALERT

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