### © 2005 Hamilton Sundstrand Corporation PROPRIETARY TH IS DOCUMENT AND THE INFORMATION CONTAINED HEREIN ARE THE PROPERTY OF HAMILTON SUNDSTRAND CORPORATION ( HSC). RECIPIENT AGREES TO HOLD ALL SUCH INFORMATION IN CONFIDENCE AND AGREES IT SHALL BE USED ONLY FOR RECIP I ENT'S INTERNAL PURPOS E S tO MAINTAIN RECIP I ENT'S EQUIPMENT OR AS MAY OTHERWISE BE PERMITIED IN AN APPLICABLE AGREEMENT BET'NEEN RECIPIENT AND HSC . THIS DOCUMENT AND THE INFORMATION CONTAI NED HERE IN SHALL NOT BE USED FOR ANY OTHER PURPOSE . INC LU DING THE CR EATION . MANUFACTURE , DE VE LOPMENT, OR DER IVATION OF A NY REPAIRS , MODIFICATIONS , SP ARE PARTS , DESIGN . OR CONFIGURATION CHANGES . OR TO OBTAIN FAA OR ANY OTHER GOVERNMENT OR REGULATORY APPROVAL FOR SAME . RECIPIENT AGREES NOT TO DISCLOSE SUCH INFORMATI ON TO ANY THIRD PARTY , EXCEPT AS MAY OTHERWISE BE PROVIDED FOR IN AN APPLICABLE AGR EEMENT BET'NEEN REC I PIENT AND HSC. COPYING OR DISCLOS URE OF THIS DOCUMENT AND THE INFORMATION CO NTAINED HEREIN BY ANYONE WITHOUT HSC 'S PRIOR WRITIEN PERMISSION IS NOT AUTHORIZED AND MA Y RESULT I N CRIMINAL AND/OR CIVIL LIABILITY . 

# I

THE DATA IN THI S DOCUMENT WERE DEVELOPED ONLY TO MAINTAI N SYSTEMS AND/ OR PARTS MANUFACTU RE D BY OR FOR HAMILTON SUN DSTRAND OR APPROVED BY HAMI LTON SUNDSTRAND . TH E DATA MAY NOT BE AP PL ICABLE TO ANY OTHE R SYSTEMS AND/ OR PARTS , REGARDLESS OF THEIR APPARENT S IM ILARITY TO SYST EM S AND /OR PAR TS MANUFACTURED BY OR FOR HAMILTON SUNDSTRAND OR APPROVED BY HAMILTON SUNOSTRAND. DO NOT RELY IN ANY WAY ON DATA I N TH I S DOCUMENT TO MAINTAIN OR OTHERWISE SUPPORT SYSTEMS AND/ OR PARTS THA T WERE NOT MAN UFACTURED BY OR FOFI HAM I LTON SUNDSTRAND OR AP PROV ED BY HAMILTON SUNDSTRAND WITHOUT EVIDENCE THAT THE FEDERAL AVIATION ADMINISTRATION OR OTHER REGULATORY AGENCY HAS DETERMINED THAT T HE DATA IN THIS DOCUMENT IS VALID FOR SUCH USE . Information Subject t o Export Cont rol Laws Export Permitted Under NLA Hydraulic Power- Ram Air Turbine - Replace Counterweight and Flyweight Assemblies 

### 1. Planning Information A . Effectivity Sundstrand Ram Air Turbine/Hydraulic Pump (RAT), part number 729548 series (Boeing part number S258T71 0 series), which contains turbine assembly, part number 734350 series , serial numbers 0666 , 0673 through 0684, 0686 , 0687 , and 0689, used on Boeing 767 aircraft . NOTE: Turbine assemblies (with the serial numbers listed above) were manufactured between 1989 and 1990 and were installed on aircraft delivered during 1990 and 1991 . However, this lot of turbine assemblies may now be installed on different Boeing model 767 aircraft or may be stocked as spares by an operator. 

### B. Reason During a sub-assembly spin test at Hamilton Sundstrand , a material defect in a tungsten counterweight was found on a RAT turbine assembly that had been returned for service . The material defect occurred within the normal RAT governing range . In-flight failure of a counterweight during RAT operation will cause turbine overspeed and probable loss of RAT function . In-service turbine assemblies which contain counterweight assemblies from the same lot are subject to replacement. 

### C. Description This bulletin gives the instructions necessary to return the turbine assembly to Hamilton Sundstrand for modification. It also gives the instructions necessary for Hamilton Sundstrand to modify the turbine assembly. 

### D. Compliance Incorporation of this service bulletin is to be accomplished at the earliest opportunity. 

### E . Approval This service bulletin has been reviewed by Boeing and the Federal Aviation Administration (FAA). The repairs and modifications herein comply with Title 14 of the Code of Federal Regulations (14CFR) Part 25 ; and are on record as FAA approved for i nstallation on Boeing Model 767 aircraft . Nov 30/05 

# 729548-29-15 Page 1 of 6HAMIL TON SUNDSTRAND 

# SERVICE BULLETIN F. Manpower A maximum of 13.0 man-hours will be required to disassemble the turbine assembly, modify the turbine assembly, and test the turbine assembly at a Hamilton Sundstrand repair facility . G. Material -Cost and Availability Hamilton Sundstrand will incorporate this modification into returned units at no charge until November 29, 2007 . A limited number of turbine assemblies will be placed in a rotable pool for operator use . These will be available to operators for exchange, based upon availability. Operators should contact Hamilton Sundstrand at the following address for scheduling information. Send repair units with a copy of your purchase order to: Hamilton Sundstrand Corporation Rockford Repair Station Plant 6 4747 Harrison Ave . Rockford, IL 61108 Attention : Repair Administration Telephone : 815-226-6849 Fax: 815-226-6826 If the unit was a scheduled removal , and it is returned to a Hamilton Sundstrand repair facility, the operator may be subject to charges for work done beyond the scope of this service bulletin . H. Tooling - Price and Availability No tooling other than that required for shop maintenance of the RAT is required to do this modification . 

### I. Weight and Balance None . J. Electrical Load Data Not affected . K. References Applicable Boeing Aircraft Maintenance Manual (AMM) , Hamilton Sundstrand Component Maintenance Manual (CMM ) 29-21-01 , Hamilton Sundstrand Standard Practices Manual (SPM) 20-00-00 , and Hamilton Sundstrand Engineering Changes 58250E and 58980E . 

### L. Other Publications Affected Hamilton Sundstrand CMM 29-21-01 will be revised to incorporate this service bulletin .

Nov 30/05 

# 729548-29-15 Page 2 U se or d isclosu re of th is data is subj ect to r est rictions on the fron t p age of th is d ocum ent.HAMILTON SUNDSTRAND 

# SERVICE BULLETIN 2 . Accomplishment Instructions A. General (1 ) The user should obtain the material safety data sheets [Occupational Safety and Health Act (OSHA) Form 20 or equivalent] from the manufacturers or suppliers of materials to be used . The user must become completely familiar with the manufacturer/supplier information and adhere to the procedures , recommendations, warnings , and cautions of the manufacturer/supplier for the safe use , handling , storage, and disposal of these materials . The user should also read the long version of the warnings contained in this service bulletin . The long version warnings are contained in Hamilton Sundstrand Warnings Registry 341-006 available free of charge to all organizations that are on distribution for this service bulletin . The Warnings Registry 341-006 is also available at www.hsvas .com. 

### B. Return for Modification NOTE : The turbine assembly part number and serial number are located on the identification plate (refer to Figure 1 of this bulletin ). NOTE : RAT turbine assemblies are line-replaceable units ( LRU) on the aircraft . Therefore , the suspect turbine assemblies may be removed while the RAT is installed on the aircraft (refer to the applicable Boeing AMM) . ( 1) Use the seed unit shipping container to return the turbine assembly (640 , -640A, -640B , or -640C, IPL Figure 1 , CMM 29-21-01 ) to Hamilton Sundstrand (refer to paragraph 1 .G. of this bulletin) . NOTE : A limited number of turbine assemblies will be placed in a rotable pool for operator use . Operators are to contact Hamilton Sundstrand for a replacement unit. 

### C . Modification (at Hamilton Sundstrand) (1 ) If necessary, disassemble the RAT (refer to CMM 29-21-01, DISASSEMBLY) as necessary to remove the turbine assembly (640 , -640A, -640B , or -640C , IPL Figure 1 ) . (2) Disassemble the turbine assembly as necessary to remove flyweight assemblies (-240 , IPL Figure 3) and counterweight assemblies (-650) . (3) Use new counterweight assemblies , part number 729759B , and new flyweight assemblies , part number 734277A, to assemble the turbine assembly ( refer to CMM 29-21 - 01 , ASSEMBL Y). (4 ) Balan ce the turb ine assembly (refer to CMM 29-21-01 , A SSEMBL Y) . (5 ) Identify the turbine assembly as follows (refer to SPM 20-00-00 , ASSEMBLY) :

Nov 30/05 (a) If the turbine assembly is part number 734350D , mark new part number 734350E and the symbol 29-15 on a new identification plate , part number 753432 . (b) If the turbine assembly is part number 734350/A/B/C , mark the existing part number and the symbol 29 - 15 on a new identification plate , part number 753432 . (c) Transfer all othe r information from the exi sting identification plate (40) or part number 753432 to the new identification plate , part number 7 53432. 

# 729548-29-15 Page 3 U se o r d isclos ure of this d ata is su bject to restr ict ions on the f ront pa ge of this document.HAMIL TON SUNOSTRAND 

# SERVICE BULLETIN (d) Remove and discard the existing identification plate (40) or part number 753432 (refer to CMM 29-21-01 , DISASSEMBLY) . (e) Install the new identification plate , part numbe r 753432 , as follows (refer to CMM 29-21-01 , ASSEMBL Y): WARNING : USE ISOPROPYL ALCOHOL , ASTM D770 , CORRECTLY. ISOPROPY L AL COHOL IS FLAMMABLE , EX PLOSI V E , AND A MILD POISON . IT CAN HAVE A BAD EFFECT ON YOUR HEALTH OR SAFETY. BEFORE YOU USE THE ALCOHOL , GET THE MATERIAL SAFETY DATA SHEET FROM THE MANUFACTURER OR SUPPLIER OF THE MATERIAL AND READ IT CAREFULLY. READ THE DETAILED WARNING , W0046SE , IN THE WARNING REGISTRY 341-006 . BEFORE YOU USE THE ALCOHOL , PUT ON CHEMICAL- SPLASH GOGGLES . MAKE SURE THAT YOU HAVE SUFFICIENT AIRFLOW TO KEEP THE ALCOHOL FUMES BELOW THE MATERIAL SAFETY DATA SHEET LIMIT. 1 Use clean isopropyl alcohol (ASTM D770) to clean the surface of the turbine assem bly where the identification plate is to be installed . 2 Let the isopropyl alcohol evaporate for five minutes minimum . 3 Remove the paper backing from the identification plate . 4 Secure the identification plate on the turbine assembly by pressing firmly to remove air pockets . (f) 

### Do a test of the turbine assembly (refer to CMM 29-21-01 , TESTING AND TROUBLESHOOTING) . D . Assembly ( 1) If the turbine assembly is to be installed in a RAT off the aircraft, do the following :



### E. Test (a) Use the modified turbine assembly, part number 734350E , or part number 734350/AJB/C (identified with the symbol29-15 ), to assemble the RAT (refer to CMM 29-21 -01 , ASSEMBLY). (1) Do one of the following: (a) If the turbine assembly is installed in a RAT off the aircraft , do a test of the RAT (refer to CMM 29-21-01 , TESTING AND TROUBLESHOOTING). (b) If the turbine assembly is installed in a RAT on the aircraft, do a ground check of the RAT ( refer to the applicable Boeing AMM). 

### F. Identification ( 1 ) No identification of the RAT is necessary.

Nov 30/05 

# 729548-29-15 Page 4 Use or disclosu re of th is data is subject to restrictions on the fron t page of this document.Nov 30/05 HAMIL TON SUN OSTRAND 

# SERVICE BULLETIN

T U R BINE ASS E M BLY IDE NT I F IC ATI O N PLAT E

SB-72 95482915- 30403 Location of Turbine Assembly Identifi cation Plate Figu re 1



# 729548-29-15 Page 5 U se or d isclosu re of thi s d ata is sub j ect t o rest r ictions on t he fro nt page of th is doc ument.HAMIL TON SUNDSTRAND 

# SERVICE BULLETIN 3. Materiallnformation NOT E : Refer to Hamilton Sundstrand CMM 29-21-01 for expendable parts information . Qty Per Unit Disposition/ New P/N Unit List Price Key Word Old P/N Instructions Same RF Not Applicable Ram Air Turbine/ 729548 Series Modify Hydraulic Pump (Note 1) 734350E 1 Not Applicable Turbine Assembly 7343500 Modify and reidentify Same 734350/A/B/C or identify with symbol 29-15 7297598 2 (Note 2) Counterweight 729759A Remove old and Assembly i nstall new 734277A 2 (N ote 2) Flywe ight Assembly 734277 Remove old and install new 753432 1 (Note 2) Identification Plate 753432 Remove and discard 734516 old , install new Note 1: End item interchangeability is not affected . Note 2 : Hamilton Sundstrand will install the noted parts at no charge (refe r to paragraph 1 .G . of this bulletin) .

Nov 30/05 

# 729548-29-15 Page 6 U se or disclosure of this data is subject to restrictions on the front page of th is document.

### © 2010 Hami lton Sundstran d Co rporation PROPRIETARY THIS DOCUMENT AND THE INFORMATION CONTAINED HEREIN ARE THE PROPERTY OF HAMILTON SUNDSTRAND CORPORATION ( HSC) . RECIPIENT AGREES TO HOLD ALL SUCH INFORMATION IN CONFIDENCE AND AGREES IT SHALL BE USED ONLY FOR RECIPIENTS INTERNAL PURPOSES TO MAINTAIN RECIPIENTS EQUIPMENT OR AS MAY OTHERWISE BE PERMITTED IN AN APPLICABLE AGREEMENT BETWEEN RECIPIENT AND HSC . THIS DOCUMENT AND THE INFORMATION CONTAINED HERE IN SHALL NOT BE USED FOR ANY OTHER PURPOSE, INCLUDING THE CREATION, MANUFACTURE , DEVELOPMENT , OR DERIVATION OF ANY REPAIRS , MODIFICATIONS , SPARE PARTS , DESIGN, OR CONFIGURATION CHANGES, OR TO OBTAIN F AA OR ANY OTHER GOVERNMENT OR REGULATORY APPROVAL FOR SAME . RECIPIENT AGREES NOT TO DISCLOSE SUCH INFORMATION TO ANY THIRD PARTY , EXC E PT AS MAY OTHERWISE BE PROVIDED FOR IN AN APPLICABLE AGREE MENT BETWEEN RECIPIENT A N D H SC . COPYING OR DISCLOSURE OF THIS DOCUMENT AN D TH E INFORMATION CONTAINED HEREIN BY ANYONE WITHOUT HSC'S PRIOR WRITTE N PERMISSIO N I S NOT A UTHO RI ZED A N D MAY RESULT I N CRIMI NAL ANOIOR CIVIL LIABILITY. 

# I

THE DATA IN T HIS DOCU M E NT W ER E DEVELO PED ONLY TO MA I NTA I N SYSTEM S AND/OR PARTS MANUFACTU R ED BY OR F OR HAMI LTON SUNDSTRAND OR APPROVED BY HAMI LTON SUNDSTRAND. THE DATA MAY NOT BE APPL I CABLE TO ANY OTHE R SYSTE M S AND /OR PARTS, REGARDLESS OF THEI R APPARENT SI MI LARITY TO SYSTEMS AND /OR PARTS M ANUFACTURED BY OR FOR HAMIL TON SUNDSTRAND O R APPROVED BY HAMI LTON SUNDSTRAND. DO NOT RELY I N ANY WAY ON DATA IN TH I S DOCUMENT TO MAI NTAI N OR OTHERWI SE SUPPORT SYSTE MS AND/ OR PARTS THAT WERE NOT M ANUFACTURED BY OR FOR HAMI LTON SUNDSTRAND OR AP PROVED BY HAMILTON SUNDSTRAND WITHOUT EVIDENCE THAT THE FEDERAL AVIATION AD M IN I STRATI ON OR OTHER REGULATORY AGENCY HAS DETERMINED THAT THE DATA IN TH I S DOCUMEN T IS VALID F OR SUCH USE . l nfoi'1NIII o n Subject to Ex port Contro l Laws THE TECHNICAL DATA IN THIS DOCUMENT (O R FILE ) IS CONTROLLED FOR EXPORT UNDER THE EXPORT ADMINISTRATION REGULATIONS ( EAR), 15 CFR PARTS 730- 77 4, ECCN· 9E991 VIOLATION S OF THESE LAWS MAY BE SUBJECT TO FINES AND PENALTIES UNDER THE EXPORT ADMINISTRATION ACT. 

### Emergency Hydra ul i c Power - Ram Ai r Tu rbi ne - Rep lace Balance Washer Rete nt ion Sc rews 

### 1 . Planning Information A. Effectivity The Ham i lton Sundstrand Turbin e Asse mblie s , part number 734350 se rie s , that are li sted be low and used on Boeing 767 aircraft : NOT E :
NOTE :

Part N umber Seri es 7343 50

Feb 10/ 10 The turb i ne assemblies m ay be stocked as spares , rotables , o r repair parts , or installed on Hamilton Sundst rand Ram Air Turbine/Hydraulic Pumps (RAT), part numbe r 72 9548 series (Boeing part number S2 58T71 0 series) . Nonconform i ng screws f rom the affected manufacturing lots were dist ri buted to other sources supp lying the airc raft industry. Turbine assemb lies or RATs repa i red o r ove rhauled by facilities other than Hamilton Sundstrand co ul d th erefore be suspe ct and not included i n th e seria l number li st that follows . Nonconforming screws known to be affe cted are those manufactured by Northeast Fasteners , I nc ., manu facturing lot 24057. Serial Nu mbe rs 0042 , 0074 , 0170 , 0183 , 0207, 0311,0312 , 0324 , 0336 , 0337 , 0 347,0 36 7, 0372, 0379 , 0381 , 0391 , 0427 , 0431 , 0469 , 0495 , 0500,0530 , 053 1 , 05 33 , 0538,0539 , 055 0 ,0551, 05 75 , 0584 , 0619 , 0626 , 0666 , 06 70 , 06 76 , 0690,07 00 , 701,0 734 , 0750 , 0800 , 0801 , 0813 , 0835 , 08 36 , 0908 , 09 2 3 , 0958 , 0968 , 0980, 1 009 , 1 012 , 1019 , 1046 , 1052, 1 054 , 1102 , 1127 , 1167 , 1264 , 1285 , 1300 , 1317 , 1 322 , 1 362 , 1372, 1394 , 1 398 , 1436, 1 594 , 1633 , 1634, 1635 , 1636 , 16 37 , 1 6 38 , 1639 , 1640 , 1 64 1' 1642 , 1643, 1 644 , 1645 , 1 646 , 1647 , 1648 , 1 649 , 1 650 , 1651 , 1652 ,X2063



# 729548-29-18 Page 1 of 15HAMIL TON SUNOSTRAND 

# SERVICE BULLETIN Records indicate the following Hamilton Sundstrand RATs , part number 729548 series (Boeing part number S258T710 series) , were delivered with affected turbine assemblies from the list above . This list is provided for reference only. Incorporation of this service bulletin shall be trac ked by turbine assembly serial number
. Part Number Series Serial Numbers 729548 01 3 1 , 0215 , 0349 , 0358 , 0382 , 0396 , 0670 , 0680 , 0839 , 0863 , 0894 , 1026 , 1036, 1037 , 1038 , 1039, 1040 , 1041 , 1042, 1043 , 1045 

### B. Concurrent Requirements None . 

### C. Reason Hamilton Sundstrand has discovered that RATs were manufactured with nonconforming screws . To date , there have been six instances of a fractured balance washer screw (PN MS24667-14) on multiple RAT part number configurations
. Four of the units were production returns . Two fractures were in a single unit discovered prior to production shipment. Another three screws have fractured on in service ai rcraft during removal for screw replacement. Fracture of a balance washer screw can result in the loss of the associated balance washer and create an unacceptable turb i ne imbalance
. Inspection of other screws in Hamilton Sundstrand stock revealed metallographic nonconformities consistent with those of the fractured screws . The suspect screws have been isolated to a lot from a specific supplier
. Analysis indicates the nonconformance could be a result of the supplier's heat treat process , which increases susceptibility to brittle fracture
. Replacement of the suspect screws with confirmed conforming screws will eliminate potential loss of a balance washer
. Incorporation of this bulletin will ensure that the RAT balance washer screws conform to specification
. 

### D. Description This bulletin gives instructions to replace the balance washer screws and identify the turbine assem bly. Refer to Figure 1 of th is bulleti n for the location of the balance washers and screws . For a turb i ne assembly or RAT with a m issing balance washer, or with a balance washer screw that cannot be removed in its entirety, instructions are also given to disassemble the unit as necessary to remove the fractured screw and balance washer, balance the turbine assembly, assemble the unit , and test the unit. 

### E . Compliance Incorporation of this service bulletin is to be accomplished at the earliest opportunity
. 

### F. Approval The repairs and modifications herein are minor per 14 Code of Federal Regulations (C FR) 21 .93/CS 21 . 93 and comply w ith the applicable regulations and are on record with the supplier as Federal Aviation Administration (FAA) approved , as well as EASA/JAA approved by process via 14 CFR 21 .95/CS 21 .95.

Feb 10/10 

# 729548-29-18 Page 2 U se or disclosure of this d ata is subject to restrictions on the fr ont page of this docu m ent. 

# . •HAMIL TON SUNOSTRAND 

# SERVICE BULLETIN G. Manpower A maximum of 0 .5 man-hour will be required to replace the balance washer sc rews and identify the turbine assembly. For a turbine assembly or RAT with a missing balance washer, or with a balance washer screw that cannot be removed in its entirety, a maximum of 9 .0 man-hours will be required to disassemble the unit as necessary to remo ve the fractured screw and balance washer, balance the turbine assembly, assemble the unit , and test the unit. H . Material -Cost and Availability (1 ) Hamilton Sundstrand will supply replacement parts on a no charge basis until February 

### 1, 2012. Replacement parts are currently available in limited quantities . Operators approved by Hamilton Sundstrand to perform modification of units at their facility should place a single " no charge " order to Hamilton Sundstrand . Operators can forward these orders to their assigned Hamilton Sundstrand Commercial Spares Administrator (or fax to + 1-815-226-2624 , if the responsible Administrator is not known) . In additi on , ope rators can also use the Hamilton Sundstrand webs ite at www.ha m iltonsundstra nd .com to contact the Commercial Spares group . Upon entering the website , select " Customer Service " followed by " Commercial Spares" for other contact and order processing options that are available . Orders must clearly reference fleet requirements , noting the service bulletin number, serial numbers of affected units , total quantity of parts , and anticipated incorporation schedule (refer to paragraph 3. for the parts breakdown) . Hamilton Sundstrand will acknowledge the operator order with an established delivery rate . (2 ) Hamilton Sundstrand will also give the following :

Feb 10/10 (a) A maximum labor allowance of 0 . 5 man-hour multiplied by the operator's current approved hourly rate for accomplishment of this service bulletin in the shop . The labor allowance will expire February 

### 1 , 2012 . (b ) A maximum labor allowance of 0 . 5 man - hour multiplied by the operator' s current approved hourly rate for replacement of the balance washer screws on the aircraft . The labor allowance will expire February 

### 1, 2012 . (c) If removal from the aircraft is required , a maximum labor allowance of 4 .0 man-hours multiplied by the operator's current approved hourly rate for replacement of the turbine assembly or RAT on the aircraft and test on wing . The labor allowance will expire February 

### 1, 2012 . (d ) Operators should forward a claim for labor reimbursement to their assigned Hamilton Sundstrand Rockford Warranty Administrator. If the responsible Administrator is not known , the claim should be mailed to Warranty Adm i nistration, 4747 Harrison Ave , Rockford , IL 61126 , USA , MS 106-6 . The claim should reference the service bulletin number, serial numbers modified , date modified , total hours , and approved labor rate .


# 729548-29-18 Page 3 Use or d is closu r e of th is data is subj ect to rest r ictions on the front page of this document.HAMIL TON SUNDSTRAND 

# SERVICE BULLETIN (3) For units with a missing balance washer, or with a balance washer screw that cannot be removed in its entirety, Hamilton Sundstrand will incorporate this modification into returned units at no charge until February 1, 2012 . Contact Hamilton Sundstrand at the address that follows for scheduling information : Ham i lton Sundstrand 4747 Harrison Avenue P.O . Box 7002 Rockford , IL 61125-7002 Attention : Repair Administration Mail Stop 151-6 Telephone : +1-815-226-6849 Fax : 815-394-2414 I. Tooling - Price and Availability No tooling other than that requ i red for shop maintenance of the turbine assembly or RAT is required to do this modifi cation . J. Weight and Balance None . K. Electrical Load Data Not changed
. L. References Hamilton S und strand C omponent Maintenance Manual s (CMM) 29-21-01 , Hamilton Sundstrand Standard Practices Manual (SPM) 20-00- 00 , and applicable Boeing Ai rc raft Maintenance Manua ls (AMM)
. M. Other Publications Affected Hamilton Sundstrand CMMs 29-2 1-01 will be revis ed to i nco rporate th is service bulletin
.

Feb 10/10 

# 729548-29-18 Page 4 U se o r d isclosure of this data is sub jec

t to r estrictions on the f ront page of th is doc um ent.Feb 10/10 HAMIL TON SUN OSTRAND 

# SERVICE BULLETIN

LOCATION O F BALANC E WAS HERS AND SC RE WS (QU ANTITY 1 2)

SB-7 2954829 1 8 -93 830 Location of Balance Washers and Screws Figure 1



# 729548-29-18 Page 5 U se o r d isclosu r e of t his data is subject to restrict ions on the f ront p age of this docu m ent.HAMIL TON SUNDSTRAND 

# SERVICE BULLETIN 2. Accomplishment Instructions A. General CAU TION : THE TURBINE ASSEMBLY OR RAT CONTA INS DESIGN CRITICAL CHARACTERISTICS, PROCESSES , AND PROCEDURES
. THE DESIGN CRITICAL CHARACTERISTICS ARE IDENTIFIED WITH THE SYMBOL »DCC«
. REFER TO THE INTRODUCTION SECTION OF CMM 29-21-01 FOR A COMPLETE EXP LANATION OF DESIGN CRITICAL CHARACTERISTICS
. (1) The user should obtain the material safety data sheets [Occupational Safety and Health Act (OS HA) Form 20 or equivalent] from the manufacturers or suppliers of materials to be used . The user must become completely familiar with the manufacturer/supplier info rm atio n and adhere to the procedures, recommendations , warnings , and cautions of the manufacturer/supplier for the safe use , handling , storage, and disposal of these materials
. The user should also read the long version of the warnings contained in this service bulletin. The lo ng version warnings are contained in Hamilton Sundstrand Warnings Registry 341-006 available free of charge to all organizations that are on distri bution for th is Service Bul letin . The Warnings Registry 341 -006 is also available at www. hsvas .com. (2) This service bulletin can be accomplished on a stand-alone RAT or turbine assembly, or on a RAT installed on aircraft , unless removal of the RAT or turbine assembly is specified here in . B. Modification (1) If the unit is installed on the aircraft, make sure the RAT is deployed (refer to the applicable AMM)
. CAU TION : THE RAT TURBINE BLADES SHOULD BE PROTECTIVELY COVERED DURING BALANCE WASHER SCREW REMOVAL AND INSTALLATION
. THE BLADES CAN BE EASILY DAMAGE D . (2) Install a protective covering on the RAT turbine blades to prevent damage to the blades from contact with the tooling or screws . (3) Manually rotate the turbine assembly and do a check for missing balance washers ( 10 through -101 , IPL Figure 3, C MM 29-21-01). NOTE : The 12 threaded holes around the turbine cover circumference (i n the fro nt balance plane) each have a balance washer installed and use a counters unk socket head cap screw MS24667-14 to secure the washers [refer to screw (20 , IPL Figure 3 , CMM 29- 21-01)]. NOTE : The rear balance plane is not affected by this bulletin . NOTE : Missing balance washers are evidenced by the remaining screw shank and the lack of a visible hexago nal screw socket on the turbine assembly
. (4) If any balance washers are miss ing (beca use of a fractured screw) , do the steps that follow :

Feb 10 /1 0 (a) If the unit is i nstalled on the aircraft , remove either the turbine assembly or the entire RAT from the aircraft (refer to the applicable AMM) for removal of the fractured screw and to ba lance the turbine assembly
. The un it must be returned to Hamilton Sundstrand or to a repair facility that has the capability to disassemble , repai r, balance , and test the RAT. 

# 729548-29-18 Page 6 Use o r disclosure of th is data is subject to re striction s on t he front page of th is d ocument.

### Feb 10/10 HAMIL TON SUNDSTRAND 

# SERVICE BULLETIN (b ) Report any occurrences of a fractured screw to Hamilton Sundstrand as follows : Gary D. Siegrist Hamilton Sundstrand Service Engineering Phone : +1-815-226-6644 Fax: + 1-860-660-5414 E-Mail : gary.siegrist@hs
.utc .com (c) Disassemble the turbine assembly or R AT (refer to CMM 29- 2 1-01 , DISASSEMBLY) as necessary to remove the following parts and to get access to the fractured screw.

- Balance washers (10 through -101 , IPL Figure 3, CMM 29-21-01)

- Screws (20 , IPL Figure 3 , CMM 29-21-01) NOTE : Some screws , depending on how near they are to a turbine blade , can not be ex

tracted unless the turbine blades are disassembled from the turbine assembly. In those cases , either the turbine assembly or the entire RAT must be removed from the aircraft and disassembled as necessary to remove the screw. (d) If the remaining portion of the fractured screw is protruding above the turbine cover surface , do the steps that follow : 1 Apply protective tape on the turbine (in the area of the screw) to prevent surface damage during the removal attempt. 2 Use pliers , a vice grip , or an equivalent gripping tool to remove the screw. 3 Remove the protective tape from the turbine . 4 If the screw is removed in its entirety, proceed to step 2 . B.(4)(f) of this bulletin . (e) If the remaining portion of the screw is flush or below the turbine cover surface , or if the screw cannot be removed in its entirety, use a screw extractor (or equivalent) to remove the remaining portion of the fractured screw. Make sure no filings or fragments enter the turbine assembly . Do not use heat or fluid to remove the screw. (f) Do a visual check of the self-locking screw thread insert to make sure there is no mechan ical damage . Do the following if the visual examination reveals no obvious mechanical damage : 1 Temporarily thread a balance weight screw (PN MS24667-14) i nto the insert to verify smooth engagement. Required torque should be less than the normal assembled torque of 18 to 22 pound inches (2 . 1 to 2.4 Newton meters).



### 2 

### 3 NOTE : For reference , the torque value through the self-locking segment of a new insert is approximately 5 pound inches (0 .6 Newton meters) . Remove the temporarily installed screw. If the engagement i s not smooth , requires excessive torque, or if the self-locking feature appears to be ineffective , replace the insert [refer to SPM 20-00-00 , Repair, SP R1 , paragraph 3 . Procedure Tang Drive Inserts ( MS21209 Series) ] . 

# 729548-29-18 Page 7 U se or disclosu r e of this data is subject to rest r ictions o n the front page of th is document.HAMILTON SUNOSTRAND 

# SERVICE BULLETIN (g) Assemble the turbine assembly as necessary ( refer to CMM 29-2 1-01 , ASSEMBLY)
. (h) Remove the prote ctive covering from the RAT turbine blades . (i) Balance the turbine assembly using new screws (PN MS24667- 1 4) (refer to CMM 29-21- 01 , ASSEMBLY)
. 

### 0) Assemble the RAT as necessary (refer to CMM 29-21-01 , ASSEMBLY). NOTE : If only the turbine assembly was removed from the aircraft , the turbine assembly must be installed into a slave RAT strut for testing. (k) Do a test of the RAT (refer to CMM 29-21-01 , TESTING AND TROUBLESHOOTING)

. (I) If necessary, remove the turbine assembly from the slave RAT strut that was used for testing . (m) Proceed to paragraph 2.B . (6) of this bulletin . CAUTION : REPLACE THE BALANCE WASHER SCREWS ONE AT A TIME . DO NOT REMOVE ALL OF THE SCREWS AT THE SAME TIME . IF MORE THAN ONE SCREW IS REMOVED AT A TIME , THE TURBINE ASSEMBLY MUST BE RE-BALANCED
. (5) If no balance washers are missing , do the steps that follow to replace the balance washer screws (one at a time) :

Feb 10/10 (a) Use a suitable temporary marking method (tape , indelible ink, or equivalent) to mark the radial orientation of the i nstalled balance washer. The orig in al installed radial orientation of the washer must be ma i ntained . (b) Do one of the steps that follow :



### 2 If the unit is installed on the aircraft, rotate the turbine assembly unti l the balance washer is positioned i n a manner to minimize the potential for the balance washer to fall out (when the associated screw is removed)
. If the turbine assembly or RAT is off the aircraft, position the unit to access the balance washer facing up .



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# SERVICE BULLETIN CAUTION: DO NOT USE A WORN HE X TOOL WITH ROUNDED CORNERS TO REMOVE THE SCREW. IF A WORN TOOL IS USED , THE POTENTIAL E X ISTS FOR STRIPPING THE SOCKET HEAD OF THE SCREW. CAUTION : USE CARE NOT TO DAMAGE EITHER THE BALANCE WASHER OR TURBINE ASSEMBLY IF IT IS NECESSARY TO STRIKE THE HEAD OF THE SCREW BECAUSE THE BREAK-AWAY TORQUE IS EXCESSIVE . (c) While holding the balance washer in place , use a 3/32-inch hex tool to remove one screw from one balance washer. NOTE : The use of a hex insert bit is preferred . NOTE : If the screw break-away torque is excessive , it is permissible to lightly stri ke the head of the screw using a small hammer and a 5/16-inch (8-millimeter) pin punch . It should not be necessary to strike more than two times. (d) If the screw is fractured (with the balance washer installed ) or if a screw fractures during removal , do the steps that follow to remove the remaining portion of the screw : 1 Report any occurrences of a fractured screw to Hamilton Sundstrand as follows : Gary D . Siegrist Hamilton Sundstrand Service Engineering Phone : + 1-815-226-6644 Fax: +1-860-660-5414 E- Mail : gary.siegrist@hs
. utc .com 2 If the remaining portion of the fractured sc rew is protrud i ng above the turbine cover surface , do the steps that follow :

b
d Apply protective tape on the turbine (in the area of the screw) to prevent surface damage during the removal attempt. Use pliers , a vice grip , or an equivalent gripping tool to remove the screw. Remove the protective tape from the turbine . If the screw is removed in its entirety , proceed to step 2 . B . (5)(e) of this bulletin .



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# SERVICE BULLETIN 3 If the remaining portion of the screw is flush or below the turbine cover surface , or if the screw can not be removed in its entirety, do the steps that follow : NOTE : If the unit is installed on the aircraft , Hamilton Sundstrand recommends either the turb ine assembly or the enti re RAT be removed from the aircraft (refer to the applicable AMM) for removal of the fractured screw. The unit should either be returned to Hamilton Sundstrand or to a repa ir facility that has the capability to disassemble, repair, balance, and test the RAT. However, as an option, and at the operator's discretion , an attempt to mechanically extract a screw while the unit is installed on the aircraft is allowed . The procedure to mechanically extract a fractured screw, or one with a stripped socket head , must not use any heat or fluid . Care must be taken to make sure no filings or fragments enter the turbine assembly
. The turbine hub and turbine blades should be protectively covered to prevent mechanically induced damage during the extraction procedure
. 

### £ For turbine assemblies or RATs removed from the ai rcraft , d isassemble the unit (refer to CMM 29-21-01, DISASSEMBLY) as necessary to get access to the fractured screw. NOTE : Some screws, depending on how near they are to a turb i ne blade , can not be extracted unless the turbine blades are disassembled from the turbine assembly
. In those cases , either the turbine assembly or the entire RAT must be rem oved from the aircraft and disassembled as necessary to remove the screw. b Use a screw ex tractor (o r equivalent) to remove the remaining portion of the fractured screw. Make sure no filings or fragments enter the turbine assembly
. Do not use heat or fluid to remove the screw. c Do a visual chec k of the self-locking screw th read insert to make sure there is no mechanical damage
. Do the following if the visual examination reveals no obvious mechan i cal damage : -Temporarily thread a balance we ight screw (PN MS24667-14) into the

insert to verify smooth engagement. Required torque shou ld be less than the normal assembled torque of 18 to 22 pound inches (2 .1 to 2.4 Newton meters). Note : For reference , the torque value through the self-locking segment of a new insert is approxi mately 5 pound inches (0 .6 Newton meters)
.

- Remove the temporarily installed screw.

- If the engagement is not smooth , requires excessive torque , or if the selflocking feature appears to be i neffective , replace the insert [refer to SPM 20-00-00 , Repair, SP R1 , paragraph 3. Procedure Tang Drive Inserts (MS21209 Series)]
. 

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### Feb10/10 HAMIL TON SUNDSTRAND 

# SERVICE BULLETIN 4 If disassembly of the turbine assembly was not required to remove the fractured screw, proceed to step 2 . B. (5)(e) of this bulletin . 5 For units removed from the aircraft, if disassembly of the turbine assembly was required to remove the fractured screw, do the following :**~** 

### Remove the remaining screws (20 , IPL Figure 3 , CMM 29-21-01) and the following balance washers : -Balance washers (10 through -101) b Do a visual check of the self-locking screw thread insert to make sure there is no mechanical damage . Do the following if the visual examination reveals no obvious mechanical damage: -Temporarily thread a balance weight screw (PN MS24667-14) into the

insert to verify smooth engagement. Required torque should be less than the normal assembled torque of 18 to 22 pound inches (2 . 1 to 2 .4 Newton meters). Note: For reference, the torque value through the self-locking segment of a new insert is approximately 5 pound inches (0 .6 Newton meters) .

- Remove the temporarily installed screw.

- If the engagement is not smooth, requires excessive torque , or if the selflocking feature appears to be ineffective , replace the insert [refer to SPM 20-00-00 , Repair, SP R1 , paragraph 3 . Procedure Tang Drive Inserts (MS21209 Series)) . 2 Assemble the turbine assembly as necessary (refer to CMM 29-21-01, ASSEM BLY) . d Remove the protective covering from the RAT turbine blades . e Balance the turbine assembly using new screws (PN MS24667-14) (refer to CMM 29-21-01 , ASSEMBLY) . f Assemble the RAT as necessary (refer to CMM 29-21 -01 , ASSEMBLY) . NOTE : If only the turbine assembly was removed from the aircraft, the turbine assembly must be installed into a slave RAT strut for testing . 

### 9. Do a test of the RAT (refer to CMM 29-21-01 , TESTING AND TROUBLESHOOTING) . h If necessary, remove the turbine assembly from the slave RAT strut that was used for testing . Proceed to paragraph 2 . B . (6) of this bulletin . 

# 729548-29-18 Page 11 U se o r d isclosu r e of th is data is subj ect to rest r icl io ns on t he fro nt p age of th is doc ume nt.HAMILTON SUNOSTRAND 

# SERVICE BULLETIN CAUTION: IF A BALANCE WASHER IS MISPLACED AFTER SCREW REMOVAL AND ITS ORIGINALLY INSTALLED ORIENTATION CANNOT BE DETERMINED , THE T URBINE ASSEMBLY OR ENTIRE RAT MUST BE RETURNED TO HAMILTON SUNDSTRAND OR TO A REPAIR FACILITY THAT HAS THE CAPABILITY TO BALANCE THE RAT. (e) If the balance washer inadvertently falls off after the screw is removed , i nstall the balance washer in its original installed orientation, as determined from the marking method used in step 2 . B .(5)(a) of this bulletin . 

### (f) While holding the balance washer in place , install a new screw MS24667-14
. Torque the screw 18 to 22 pound inches (2 . 1 to 2 .4 Newton meters)
. (g) Use a suitable temporary marki ng method (tape, indelible ink, or equivalent) to mark the locati on where the balance washer screw has been replaced. (h) Repeat steps 2 . B. (5)(a) through (g) of this bulletin for each balance washer screw. (i) Remove any tape {that was used to mark the orientation of the insta ll ed balance washers or the locations where the screws had been replaced). 

### 0) Remove the protective cove ring from the RAT turbine blades. (6) After all of the balance washer screws have been replaced , identify the turbine assembly as follows (refer to SPM 20-00-00 , ASSEMBLY) : (a) Ad d the symbol 29-18 to a blank area of the turbine assembly identification plate (40 or -40A, IPL Figure 3, CMM 29-21-01)
. (7) If the unit is installed on the aircraft, make sure the RAT is re-stowed (refer to the applicable AMM)
. 

### C. Identification NOTE : After all of the balance washer screws have been replaced , the turbine assembly is identified by adding the symbol 29-18 to a blank area of the turbine assembly identification plate . 

### D. Test (1) For units in the shop (if no balance washers were found missing , disassembly ofthe turbine was not required, and the balance washer screws were replaced one screw at a time) , a test of the RAT is not required (refer to CMM 29-21-01 , TESTING AND TROUBLESHOOTING)
. (2) For RATs on the aircraft , if no balance washers were missing and the screws have been replaced as directed by this service bulletin , then a test of the RAT is not required
.

Feb 10/10 

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# SERVICE BULLETIN E. Return Balance Washer Screws to Hamilton Sundstrand (1 ) If the unit had a missing balance washer or a fractured screw, return all of the removed screws (including the remnants of the fractured screw) to Hamilton Sundstrand for further investigation as follows: (a) Put the screws in a mailing package . (b) Tag the screws (or include a note) to identify the part number and serial number of the turbine assembly (and if applicable , the part number and serial number of the RAT) the screws were removed from and to identify the applicable aircraft MSN . (c) Return the screws with the applicable part numbers, serial numbers , and aircraft MSN to the address that follows : Hamilton Sundstrand Service Engineering 4747 Harrison Avenue P.O . Box 7002 Rockford, IL 61125-7002 Attention : Gary D . Siegrist Phone: + 1-815-226-6644 Fax: + 1-860-660-5414 E-Mail : gary.siegrist@hs
. utc.com 

### F. Notification of Completion Form (1) Do the following upon completion of this service bulletin :

Feb 10/10 (a) Make a copy of the " Notification of Completed SB 729548-29-18 " form (refer to Figure 2 of this bulletin), complete the form , and fa x the completed form to Hamilton Sundstrand as follows: Hamilton Sundstrand Corporation Retrofit Management Group Fax : +1-860-998-3695



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# SERVICE BULLETIN

SENT FROM : 

## Sender Name : NOTIFICATION OF COMPLETED 58 

### 729548-29-18 " Replace Balance Washer Screws " 

## Sender Company : Aircraft Operator: Sender Fax# : Send Date :
** PLEASE SUBMIT THIS NOTIFICATION SHEET WITHIN 10 DAYS AFTER MODIFICATION ** SEND TO : Hamilton Sundstrand Corporation Retrofit Management G roup Fax : + 1-860-998-3695 Turbine Assembly Serial Number

Feb10/10 Aircraft MSN or Tail Number Bulletin Completion Date

Notification of Completion Form Figure 2 Comments



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# SERVICE BULLETIN 3 . Material Information NOTE : Refer to Hamilton Sundstrand CMM 29-21 - 01 for ex pendable parts information . Qty Per Unit Disposition/ New P/N Unit List Price Key Word Old P/N Instructions Same RF Not Applicable Ram Air Turbine/ 729548 Series Change (Note 1 ) Hydraulic Pump (Note 2) Same 1 Not Applicable Turbine Assembly 734350 Series Change and identify with the symbol 29-18 Same 12 (Note 3) Screw MS24667-14 Remove suspect old screws , install new conforming screws Note 1 : Turbine assemblies or RATs modified according to this service bulletin are identified by marking the symbol 29-18 on the turbine assembly identification plate . Note 2 : End item interchangeability is not affected . Note 3: Hamilton Sundstrand will supply the noted part at no charge (refer to paragraph 1 . H. ofthis bulletin for details).

Feb 10/ 10 

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