# Boeing Special Attention Service Bulletin 727-34-0245: No revision named

- Rights: © The Boeing Company. Filed by the FAA in regulations.gov docket FAA-2012-1041; AD 2013-19-08 incorporates this document by reference. Not covered by OpenAirDocs’ CC0 dedication.
- Document: [Boeing Special Attention Service Bulletin 727-34-0245](https://openairdocs.org/service-documents/boeing/sb-727-34-0245.md)
- Title as filed: U.S. DOT/FAA - Service Information - 1
- Pages: 21
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## Text

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### Page 1

Commercial        
Airplane
Group 
 727
Service Bulletin
SPECIAL ATTENTION
Number: 727-34-0245
Date: June 04, 2008
ATA System: 2732 3418
SUBJECT: NAVIGATION - Stall Warning System - Angle of Airflow Sensor Inspection
Export of this technology is controlled under the United States Export Administration Regulations (EAR) (15
CFR 730-774). An export license may be required before it is used for development, production or use by foreign
persons from specific countries. The controller of this data has the individual responsibility to abide by all export
laws.
9E991ECCN:
BOEING PROPRIETARY, CONFIDENTIAL, AND/OR TRADE SECRET
Copyright © 2008 The Boeing Company
Unpublished Work - All Rights Reserved
Boeing claims copyright in each page of this document only to the extent that the page contains copyrightable
subject matter. Boeing also claims copyright in this document as a compilation and/or collective work.
This document includes proprietary information owned by The Boeing Company and/or one or more third parties.
Treatment of the document and the information it contains is governed by contract with Boeing. For more
information, contact The Boeing Company, P .O. Box 3707, Seattle, Washington 98124.
Boeing, the Boeing signature, the Boeing symbol, 707, 717, 727, 737, 747, 757, 767, 777, 787, Dreamliner,
BBJ, DC-8, DC-9, DC-10, MD-10, MD-11, MD-80, MD-88, MD-90, and the Boeing livery are all trademarks
owned by The Boeing Company; and no trademark license is granted in connection with this document unless
provided in writing by Boeing.
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Table of Contents
Summary ..................................................... 5
1. PLANNING INFORMATION ......................................... 9
A. Effectivity ................................................ 9
1. Airplanes ............................................. 9
2. Spares Affected ........................................ 1 3
B. Concurrent Requirements ...................................... 1 3
C. Reason ................................................ 1 4
D. Description .............................................. 1 4
E. Compliance .............................................. 1 5
F . Approval ............................................... 1 5
G. Manpower .............................................. 1 5
H. Weight and Balance Changes .................................... 1 6
I. Electrical Load Data ......................................... 1 6
J. References .............................................. 1 6
1. Existing Data .......................................... 1 6
2. Data supplied with this Service Bulletin ............................ 1 6
3. Installation Drawings Used in the Preparation of this Service Bulletin ............ 1 6
K. Publications Affected ......................................... 1 6
L. Interchangeability and Intermixability of Parts ........................... 1 6
2. MATERIAL INFORMATION ........................................ 1 7
A. Material - Price and Availability ................................... 1 7
B. Industry Support Information .................................... 1 7
C. Parts Necessary For Each Airplane ................................. 1 7
1. Kits/Parts ............................................ 1 7
2. Parts and Materials Supplied by the Operator ........................ 1 7
3. Parts Modified and Reidentified ................................ 1 7
4. Parts Removed and Not Replaced .............................. 1 7
D. Parts Necessary to Change Spares ................................. 1 7
E. Special Tooling - Price and Availability ............................... 1 7
F . Special Tooling Necessary to do this Service Bulletin ....................... 1 8
3. ACCOMPLISHMENT INSTRUCTIONS .................................. 1 9
A. GENERAL INFORMATION ..................................... 1 9
B. WORK INSTRUCTIONS ....................................... 1 9
FIGURE 1: ANGLE OF AIRFLOW SENSOR - INSPECTION ....................... 2 1
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Commercial        
Airplane
Group 
 727
Service Bulletin
SPECIAL ATTENTION
SummaryNumber: 727-34-0245Date: June 04, 2008
ATA System: 2732 3418
SUBJECT: NAVIGATION - Stall Warning System - Angle of Airflow Sensor Inspection
BOEING RECOMMENDS THAT EACH OPERATOR EXAMINE THIS SERVICE BULLETIN IMMEDIATEL Y .
CONCURRENT REQUIREMENTS
None.
BACKGROUND
This service bulletin gives instructions for a one-time inspection of Conrac/Ametek/Gulton Angle of Airflow (AOA)
sensors with part numbers 2566A21 and 2566A30. This inspection will do a check for a misalignment between
the AOA sensor shaft and the sensor synchro transmitter. This misalignment is caused by a defective set screw
condition.The airplane could have incorrect control column shaker activation if the inspection given in this service
bulletin is not accomplished.
One 747-400 operator reported a control column shaker activation on takeoff. The control column shaker
activation continued while the airplane was in flight and EICAS messages ALT DISAGREE and IAS DISAGREE
were displayed. The flight crew used the alternative Air Data Computer (left ADC) and the altitude and airspeed
indications cancelled. After landing the right ADC was replaced. On the subsequent flight the control column
shaker operated again at takeoff and the flight crew had to do a Rejected Takeoff (RTO). Troubleshooting steps
found that the right AOA sensor was unserviceable. ADC installed on 727-100/200 airplanes do not use data
from the AOA sensor but they do use Conrac/Ametek/Gulton AOA sensors that are equivalent in design and
construction to the defective AOA sensor on the 747-400 airplane.
The inspection of the AOA sensor showed that the set screw connected to the synchro transmitter was not
correctly attached to the AOA sensor shaft. Accomplishment of this service bulletin will stop incorrect control
column shaker activation.
Boeing Service Related Problem (SRP) 727-SRP-34-0114 is related to this service bulletin.
Fleet Team Digest (FTD) 727 FTD 34-07001 is related to this service bulletin.
ACTION
Part 1
Do a visual inspection of the AOA sensor. If the AOA sensor is found to be a Conrac/Ametek/Gulton sensor, do
Part 2 of the service bulletin.
Part 2
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Do a test of the AOA sensor. If the AOA sensor fails to activate the control column shaker, do Part 3 of the
service bulletin.
Part 3
Do an Aircraft Maintenance Manual (AMM) Operational Test of the Stall Warning System. If the AOA sensor
fails to activate the control column shaker, replace the AOA sensor.
NOTE: New part is only necessary if the inspection and tests indicate that the existing sensor must be replaced.
EFFECTIVITY
727/727C/727-100/100C/200/200F Airplanes. Refer to Paragraph 1.A., Effectivity., Airplanes for the list of
affected airplanes.
COMPLIANCE
Refer to Paragraph 1.E., Compliance.
INDUSTRY SUPPORT INFORMATION
Boeing warranty remedies are not available for the inspection or tests given in this service bulletin.
MANPOWER
Refer to Paragraph 1.G., Manpower.
MATERIAL INFORMATION
None.
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Commercial        
Airplane
Group 
 727
Service Bulletin
SPECIAL ATTENTION
Number: 727-34-0245
Date: June 04, 2008
ATA System: 2732 3418
SUBJECT: NAVIGATION - Stall Warning System - Angle of Airflow Sensor Inspection
BOEING RECOMMENDS THAT EACH OPERATOR EXAMINE THIS SERVICE BULLETIN IMMEDIATEL Y .
1.    PLANNING INFORMATION
A. Effectivity
1. Airplanes
Refer to Service Bulletin Index Document D6-9825 Part 3 for Airplane Variable Number, Line
Number, and Serial Number data.
This service bulletin is for the airplanes shown below.
DESCRIPTIONCONFIGURATIONGROUP
All 727-100 and -200 airplanes that require Angle of Airflow sensor
inspection
-1
Airplane Models:
727, 727-100, 727-100C, 727-200, 727-200F , 727C
GroupVariable Number
1E0001 - E0042
1E0101 - E0140
1E0201 - E0216
1E0301 - E0351
1E0401 - E0423
1E3001 - E3006
1E3011 - E3014
1E3021 - E3040
1E3059
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GroupVariable Number
1E3061 - E3077
1E3101 - E3103
1E3111 - E3118
1E3141 - E3152
1E3171 - E3177
1E3201 - E3206
1E3221 - E3224
1E3241 - E3290
1E3341 - E3350
1E3401 - E3421
1E3451 - E3452
1E3471 - E3474
1E3501 - E3513
1E3516 - E3523
1E3551 - E3553
1E3571 - E3578
1E3601 - E3604
1E3621 - E3622
1E3651 - E3655
1E3677
1E3681 - E3684
1E3701 - E3704
1E3751 - E3755
1E3781 - E3784
1E5001 - E5011
1E5031 - E5068
1E5101 - E5116
1E5141 - E5143
1E5161 - E5164
1E5201 - E5203
1E5221 - E5245
1E5251 - E5252
1E5271 - E5281
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GroupVariable Number
1E5301 - E5306
1E5351 - E5353
1E5381 - E5382
1E5401 - E5424
1E5426 - E5429
1E5433
1E5435
1E5451 - E5455
1E5481 - E5483
1E5501 - E5502
1QA001 - QA046
1QA051 - QA099
1QA101 - QA199
1QA201 - QA225
1QA301 - QA349
1QA351 - QA376
1QA378
1QA401 - QA499
1QA501 - QA537
1QA551 - QA579
1QA581 - QA585
1QA601 - QA688
1QA701 - QA753
1QA801 - QA805
1QA851 - QA899
1QA901 - QA946
1QA949
1QB001 - QB002
1QB031 - QB049
1QB051 - QB068
1QB101 - QB110
1QB114 - QB119
1QB121 - QB149
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GroupVariable Number
1QB151 - QB158
1QB201 - QB220
1QB301 - QB316
1QB351 - QB352
1QB401 - QB407
1QB451 - QB458
1QB501 - QB575
1QB601 - QB629
1QB651
1QB701 - QB705
1QB801 - QB810
1QB901 - QB904
1QD001 - QD012
1QD031 - QD046
1QD085 - QD088
1QD101 - QD105
1QD121 - QD127
1QD141 - QD149
1QD161 - QD164
1QD191 - QD192
1QD201 - QD239
1QD281 - QD284
1QD301 - QD305
1QD321 - QD330
1QD351
1QD401 - QD403
1QD407
1QD410
1QD421 - QD427
1QD441 - QD453
1QD471 - QD475
1QD501 - QD518
1QD551 - QD558
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GroupVariable Number
1QD571 - QD572
1QD581 - QD583
1QD601 - QD607
1QD621 - QD624
1QD641
1QD661 - QD663
1QD681 - QD685
1QD691 - QD692
1QD701 - QD702
1QD711 - QD717
1QD741
1QD761 - QD769
1QD781 - QD782
1QD791
1QD801 - QD804
1QD821 - QD828
1QD901 - QD910
1QD931 - QD932
1QD951 - QD954
1QD971 - QD973
1QD991 - QD992
1QE001 - QE002
1QL001 - QL008
1QL031 - QL032
1QL081
1QL501 - QL515
2. Spares Affected
None.
B. Concurrent Requirements
None.
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C. Reason
This service bulletin gives instructions for a one-time inspection of Conrac/Ametek/Gulton Angle of
Airflow (AOA) sensors with part numbers 2566A21 and 2566A30. This inspection will do a check for a
misalignment between the AOA sensor shaft and the sensor synchro transmitter. This misalignment
is caused by a defective set screw condition. The airplane could have incorrect control column shaker
activation if the inspection given in this service bulletin is not accomplished.
One 747-400 operator reported a control column shaker activation on takeoff. The control column
shaker activation continued while the airplane was in flight and EICAS messages ALT DISAGREE and
IAS DISAGREE were displayed. The flight crew used the alternative Air Data Computer (left ADC) and
the altitude and airspeed indications cancelled. After landing the right ADC was replaced. On the
subsequent flight the control column shaker operated again at takeoff and the flight crew had to do a
Rejected Takeoff (RTO). Troubleshooting steps found that the right AOA sensor was unserviceable.
ADC installed on 727-100/200 airplanes do not use data from the AOA sensor but they do use
Conrac/Ametek/Gulton AOA sensors that are equivalent in design and construction to the defective
AOA sensor on the 747-400 airplane.
The inspection of the AOA sensor showed that the set screw connected to the synchro transmitter was
not correctly attached to the AOA sensor shaft. Accomplishment of this service bulletin will stop incorrect
control column shaker activation.
Boeing Service Related Problem (SRP) 727-SRP-34-0114 is related to this service bulletin.
Fleet Team Digest (FTD) 727 FTD 34-07001 is related to this service bulletin.
D. Description
Part 1
Do a visual inspection of the AOA sensor. If the AOA sensor is found to be a Conrac/Ametek/Gulton
sensor, do Part 2 of the service bulletin.
Part 2
Do a test of the AOA sensor. If the AOA sensor fails to activate the control column shaker, do Part 3
of the service bulletin.
Part 3
Do an Aircraft Maintenance Manual (AMM) Operational Test for the Stall Warning System. If the AOA
sensor fails to activate the control column shaker, replace the AOA sensor.
NOTE: New part is only necessary if the inspection and tests indicate that the existing sensor must
be replaced.
Affected Maintenance Zones
ZoneModel
2-21, 2-22727, 727-100, 727-100C,
727-200, 727-200F , 727C
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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 inspection given in this service bulletin be done within 36 months after
the date on this service bulletin.
If an AOA check (such as Maintenance Planning Document (MPD) Task 4-34-06 associated with a 'C'
check) has been accomplished within the last 15 months or if one is scheduled within the compliance
time, it can take the place of the required check and the service bulletin is considered accomplished.
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 visual inspection and test
for each sensor.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.
PART 1
Elapsed HoursTask HoursNumber of
Persons
Task
0.100.101Inspect
0.100.10TOTAL FOR EACH SENSOR
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PART 2
Elapsed HoursTask HoursNumber of
Persons
Task
0.250.502Test
0.250.50TOTAL FOR EACH SENSOR
PART 3
Elapsed HoursTask HoursNumber of
Persons
Task
0.501.002Test
0.501.00TOTAL FOR EACH SENSOR
H. Weight and Balance Changes
None.
I. Electrical Load Data
Not applicable.
J. References
1. Existing Data
a. Boeing Service Related Problem (SRP) 727-SRP-34-0114
b. 727 Aircraft Maintenance Manual (AMM) 24-22-00, 27-51-00, 34-18-01, 34-18-51
c. 727 Fleet Team Digest (FTD) 34-07001
d. Maintenance Planning Data (MPD) Task 4-34-06
2. Data supplied with this Service Bulletin
None.
3. Installation Drawings Used in the Preparation of this Service Bulletin
None.
K. Publications Affected
None.
L. Interchangeability and Intermixability of Parts
Accomplishment of this service bulletin does not affect interchangeability or intermixability of parts.
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2.    MATERIAL INFORMATION
A. Material - Price and Availability
None.
B. Industry Support Information
Boeing warranty remedies are not available for the inspection and tests given in this service bulletin.
C. Parts Necessary For Each Airplane
1. Kits/Parts
None.
2. Parts and Materials Supplied by the Operator
NotesNameQTYPart Number /
Specification
(a) (b) (c) (d)Angle of Attack Sensor12566A21 or
2566A30
(10-60878-3 or
10-60878-4)
(a) Part numbers are interchangeable.
(b) Some operators have 2 Stall Warning System Angle of Attack Sensors installed.
(c) This part is only necessary if the inspection and tests indicate the existing sensor must
be replaced.
(d) Ametek Aerospace (V92627), 1644 Whittier Ave, Costa Mesa, California 92627-4415.
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.
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F. Special Tooling Necessary to do this Service Bulletin
No special tools or equipment are necessary to do the change in this service bulletin. But, maintenance
and overhaul tools in the manuals given in Paragraph 1.J., References, can be necessary. Examine
operator tool supply to make sure all necessary tools are available.
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3.    ACCOMPLISHMENT INSTRUCTIONS
A. GENERAL INFORMATION
CAUTION: KEEP THE WORK AREA, WIRES AND ELECTRICAL BUNDLES CLEAN OF METAL
PARTICLES OR CONTAMINATION WHEN YOU USE TOOLS. UNWANTED MATERIAL,
METAL PARTICLES OR CONTAMINATION CAUGHT IN WIRE BUNDLES CAN CAUSE
DAMAGE TO THE BUNDLES. DAMAGED WIRE BUNDLES CAN CAUSE SPARKS OR
OTHER ELECTRICAL DAMAGE.
NOTE: 1. The instructions identified in Paragraph 3.B., Work Instructions and the Figure(s)
give the recommended sequence of steps. The sequence of steps to do this service
bulletin can be changed.
2. Manual titles are referred to by acronyms. Refer to Paragraph 1.J., References, for
definition of the acronyms.
3. Obey all of the warnings and cautions given in the specified manual sections.
4. 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 ensure visual access to all surfaces in the
inspection area. This level of inspection is made under normal 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.
5. 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 "as
given in" are included in the instruction, the procedure in the Boeing document must
be used.
B. WORK INSTRUCTIONS
PART 1: ANGLE OF AIRFLOW (AOA) SENSOR INSPECTION
1. Do a General Visual Inspection of the right AOA sensor as given in FIGURE 1.
a. If Conrac/Ametek/Gulton AOA sensor with a paddle type vane is installed, do PART 2: TEST
THE STALL WARNING SYSTEM.
b. If BF Goodrich/Rosemount AOA sensor with a swept vane is installed, no more work is
necessary.
2. If a Dual Stall Warning System is installed, do a General Visual Inspection of the left AOA sensor.
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a. If Conrac/Ametek/Gulton AOA sensor with a paddle type vane is installed, do PART 2: TEST
STALL WARNING SYSTEM.
b. If BF Goodrich/Rosemount AOA sensor with a swept vane is installed, no more work is
necessary.
PART 2:TEST THE STALL WARNING SYSTEM
1. Supply electrical power to the airplane. Refer to 727 AMM 24-22-00 as an accepted procedure.
2. Make sure the applicable stall warning circuit breakers on the P6 and P18 circuit breaker panels
are closed. Refer to 727 AMM 34-18-01 as an accepted procedure.
3. On the P2 circuit breaker panel, make sure that the LIGHT switch is in the DIM position.
4. Move the Stall Warning selector switch to the HTR OFF position.
5. At the P5 Aft Overhead panel, make sure that the OFF light on the Stall Warning Module is on.
6. Move the trailing edge flaps to the up (0 detent) position. Refer to 727 AMM 27-51-00 as an
accepted procedure.
WARNING: SENSOR VANE COULD CAUSE BURNS. ALLOW SUFFICIENT TIME TO COOL
BEFORE HANDLING.
CAUTION: DO NOT SPIN VANE. DAMAGE TO SYNCHROS MAY OCCUR.
7. Make sure the AOA sensor(s) is at the horizontal position.
8. Move the trailing edge of the AOA sensor up from the horizonal position to approximately 17
degrees with reference to the airplane waterline (13 degrees position on the AOA sensor scale).
9. On the flight deck, make sure the control column shaker is activated within a tolerance of +/-1
degree.
a. If the control column shaker is activated no more work is necessary. Put the airplane back to
a serviceable condition.
b. If the control column shaker is not activated, do PART 3: Operational Test of the Stall Warning
System.
10. If a Dual Stall Warning System is installed, do steps 8. and 9. again for the left AOA sensor.
PART 3: OPERATIONAL TEST OF THE STALL WARNING SYSTEM
1. Do an Operational Test of the Stall Warning System. Refer to 727 AMM 34-18-01 as an accepted
procedure.
2. If the AOA sensor fails to activate the control column shaker in this operational test, replace the
AOA sensor. Refer to 727 AMM 34-18-51 as an accepted procedure.
3. Put the airplane back to a serviceable condition.
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BOEING SERVICE BULLETIN 727-34-0245
SWEPT VANE
PADDLE-TYPE
VANE
BF GOODRICH/ROSEMOUNT SENSOR  (INSPECTION NOT REQUIRED)  CONRAC/AMETEK/GULTON SENSOR  (INSPECTION REQUIRED)  1548514
FIGURE 1: ANGLE OF AIRFLOW SENSOR - INSPECTION
(SHEET 1 OF 1)
June 04, 2008
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