# ()



# ~u~.~T~~.~~~.,~~~~strand SERVICE BULLETIN © 2005 H am i lton Sund strand Corpo ration PROPRIETARY THIS DOC U MENT AND THE INFORMATION CONTAINED HEREIN ARE THE PROPERTY OF HAMILTON SUNDSTRAND CORPORATION (H SC)
. RECIP I ENT AGREES TO HOLD ALL SUCH INFORMATION IN CONFIDENCE AND AGREES IT SHALL BE USED ONLY FOR RECIPIENTS I NTERNAL PURPOSES TO MAINT AI N REC I PIENTS EQUIPMENT OR AS MAY OTHERWI SE BE PERMITIED IN AN APPL ICABLE AGREEMENT BETWEEN RECIPIENT AND HSC
. THIS DOCUMENT AND THE INFORMATION CONTAINED HEREIN SHALL NOT BE USED FOR ANY OTHER PURPOSE
. INCLUDING THE CREATION , MANUFACTURE , DEVELOPMENT , OR DER IV ATION OF ANY REPAIRS , MODIFICATIONS , SPARE PARTS , DES IGN , OR CONF IGURATION CHANGES , OR TO OBTAIN FAA OR ANY OTHER GOVERNMENT OR REGULATORY APPROVAL FOR SA ME . RECIPIENT AGREES NOT TO DISCLOSE SUCH INFORMATION TO ANY THIRD PARTY , EXCEPT AS MAY OTHERWISE BE PROVIDED FOR IN AN APPLICABLE AGREEMENT BETWEEN RECI PIENT AND HSC
. COPYING OR DISCLOSURE OF THIS DOCUMENT AN D THE INFORMATION CONTAINED HEREIN BY ANYON E WITHOUT HSC' S PRIOR WR ITIEN PERMISSION IS NOT AUTHORIZED AND MAY RESULT IN CRIM I NAL AND/ OR CIVIL LI AB I LITY . 

# I

THE DATA IN TH IS DOCUMENT WERE DEVELOPED ONLY TO MAINTAIN SYSTEMS AND /OR PA RTS MANUFACTURED BY OR FOR HA MI LTON SUNDSTRAND OR APPROVED BY HAM I LTON SUNDSTRAND
. THE DATA MAY NOT BE APPLICABLE TO ANY OTH E R SYSTE MS AND/ OR PARTS , REGARDLESS OF THE I R APPARENT SIMILARITY TO SYSTEMS AND/O R PARTS MANUFACTURED BY OR FOR HAMIL TON SUNDSTRAND OR APPROVED BY HAMILTON SUNDSTRAND
. DO NOT RELY I N ANY WAY ON DATA IN THIS DOCUMENT TO MAINTAIN OR OTHERWISE SUPPORT SYSTEMS AND /OR PA R TS THAT WERE NOT MANUFACTURED BY OR FOR HAMILTON SUNDSTRAND OR APPROVE D B Y HAMIL TON SUNDSTRAND WITHOUT EVIDENCE THAT TH E FEDE RAL AVIATION ADMINISTRATION OR OTHER REGULATORY AGENCY HAS DETERMINED THAT TH E DATA I N THIS DOCUMENT IS VALID FOR SUCH USE
. Infor matio n Su b ject t o Export Control Laws Exp ort P e rmitted Under NLR Hydrau lic Powe r - Ram Air Tu rbine - Replace Coun terwe ight and Flywe ight Assembl ies 

### 1 . Planning Information A. Effectivity Sundstrand Ram Air Turbine/Hydraulic Pump (RAT) , part number 730814 series (Boeing part number S258T71 0 series) , which contains hub assembly, part number 733785 series , serial numbers 0410 through 0413 , 0415, 0417 through 0430 , 0432, and 0434, used on Boeing 757 aircraft
. NOTE: Hub 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 hub assembl ies may now be in stalled on different Boeing model 757 a i rcraft or may be stocked as spares by an operator. 

### B . Reason During a sub-assemb ly spin test at Hamilton Sundstrand , a material defect in a tungsten counterwe ight was found on a RAT hub assembly that had been returned for service . The material defect occurred with i n 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 hub assembl ies wh ich contain counterwe ight assembl ies fro m the same lot are subj ect to replacement. 

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

### D . Compliance In corporation of this service bulletin is to be accompl ished at the earliest opportun ity. 

### E. Approval This service bulleti n has bee n rev iewed by Boeing and the Fede ral Avi ation Admin istration (FAA)
. The repairs and mod ifi cations h ere i n comp ly with Title 14 of the Code of Federal Regulations ( 14CFR) Part 25 ; and are on record as F AA approved for i nstallation on Boeing Mode l 757 aircraft
.
Nov 30/05 

# 730814-29-12 Page 1 of6HAMIL TON SUN OSTRAND 

# SERVICE BULLETIN F. Manpower A maximum of 1 3 .0 man -hours will be required to disassemble the hub assembly, modify the hub assembly, and test the hub 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 l i mited number of hub 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 : 815-2 26-6849 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 Availab i lity 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 Ai rcraft Maintenan ce Manual (AMM ), Hamilton Sundstrand Component Maintenance Manual (C MM) 29-21 - 11 , Hamilton Sundstrand Standard Practices Manual (SPM ) 20-00-00 , and Hamilton Sundstrand Engineering Changes 58249E and 58980E . 

### L. Othe r Publications Affected Hamilton Sund strand CMM 29 -21-11 w ill be revised to incorporate this servi ce bulletin .

Nov 30/05 

# 730814-29-12 Page 2 U se or disclosure of th is data is subject to restrictions on the front page of this document.HAMILTON SUN OSTRAND 

# 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 hub assembly part number and serial number are located on the identification plate (refer to Figure 1 of this bulletin)
. NOTE : RAT hub assemblies are line-replaceable units (LRU) on the aircraft
. Therefore, the suspect hub 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 hub assembly (570, -570A , or -570B, IPL Figure 1, CMM 29-21-11) to Hamilton Sundstrand (refer to paragraph 1.G
. of this bulletin)
. NOTE: A limited number of hub 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 29-21-11 , DISASSEMBLY) as necessary to remove the hub assembly (570, -570A, or -570B , IPL Figure 1)
. (2) Disassemble the hub 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 hub assembly (refer to CMM 29-21-11 , ASSEMBLY)
. (4) Balance the hub assembly (refer to CMM 29-21-11, ASSEMBLY)
. (5) Identify the hub assembly as follows (refer to SPM 20-00-00, ASSEMBLY) :

Nov 30/05 (a) If the hub assembly is part number 733785B, mark new part number 733785C and the symbol 29-12 on a new identification plate (-40A, IPL Figure 3)
. (b) If the hub assembly is part number 733785/A , mark the existing part number and the symbol29-12 on a new identification plate (-40A)
. (c) Transfer all other information from the existing identification plate (40 or -40A) to the new identification plate (-40A)
. 

# 730814-29-12 Page 3 U se o r discl osure of this d ata is subj ect to restrictions on th e f ro nt page of th is docu m ent.HAMIL TON SUNDSTRAND 

# SERVICE BULLETIN (d) Remove and discard the existing identification plate (40 or - 40A) (refer to CMM 29-21-11, DISASSEMBLY)
. (e) Install the new identification plate (-40A) as follows (refer to CMM 29-21-11, ASSEMBLY) : WARNING : USE ISOPROPYL ALCOHOL, ASTM D770 , CORRECTLY. ISOPROPY L ALCOHOL IS FLAMMABLE , EX PLOSIVE, AND A MILD POISON
. IT CAN HAVE A BAD EFFECT ON YO UR 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 hub assembly 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 hub assembly by pressing firmly to remove air pockets . (f) 

### Do a test of the hub assembly (refer to CMM 29-21-11, TESTING AND TROUBLESHOOTING)
. D. Assembly (1) If the hub assembly is to be installed in a RAT off the aircraft , do the following :

E. Test (a) Use the modified hub assembly, part number 7 33785C , or part number 733785/A (identified with the symbol29-12) , to assemble the RAT (refer to CMM 29-21-11 , ASSEMBLY). ( 1) Do one of the following : (a) If the hub assembly is installed in a RAT off the aircraft , do a test of the RAT (refer to CMM 29-21-11 , TESTING AND TROUBLESHOOTING)
. (b) If the hub 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 

# 730814-29-12 Page 4 U se or d isclosu re of t h is data is subject to restrictions on t he f ront page of this d ocu ment.Nov 30/05 HAMIL TON SUNDSTRAND 

# SERVICE BULLETIN

HUB ASS EM BLY I DENTI F ICATIO N P L

ATE

S B-73081429 12-30883 Location of Hub Assembly Identification Plate Figure 1



# 730814-29-12 Page 5 U se or d isclosure of this data is subject to restrictions on the front page ol this document.HAMIL TON SUN OSTRAND 

# SERVICE BULLETIN 3. Material Information NOTE : Refer to Hamilton Sundstrand CMM 29-21-11 for expendable parts information
. Qty Per Un it Disposition/ New P/N Unit List Price Key Word Old P/N Instructions Same RF Not Applicable Ram Air Turbine/ 730814 Series Modify Hydraulic Pump (Note 1) 733785C 1 Not Applicable Hub Assembly 7337858 Modify and reidentify Same 733785/A or identify with symbol 29-12 7297598 2 (Note 2) Counterweight 729759A Remove old and Assembly install new 734277A 2 (N ote 2) Flyweight 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 (refer to paragraph 1 .G
. of this bulletin).

Nov 30/05 

# 730814-29-12 Page 6 U se or disclosu re of this data is s u bject to restr ictions o n the fron t page of this d ocu ment.

### © 2010 Hamilton Sundstrand Corporat ion 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 RECIPIENT'S INTERNAL PURPOSES TO MAINTAIN RECIP I ENT'S EQUIPMENT OR AS MAY OTHERWISE BE PERM ITIED IN AN APPLICABLE AGREEMENT BETWIEEN RECIPI ENT AND HSC
. THIS DOCUMENT AND THE INFORMATION CONTAINED HEREIN SHAL L NOT BE USED FOR ANY OTHER PURPOS E . INCLU DING THE CREATION
. MANUFACTURE, DEVELOPMENT
. OR DERIVATION OF ANY REPAIRS
. MODIFICATIONS , SPARE PARTS , DES IGN , OR CONFIGURATION CHANGES , OR TO OBTAIN FAA OR ANY OTHER GOVERNMENT OR REGULATORY APPROVAL FOR SAME
. RECIPIENT AGREES NOT TO DISCLOSE SUCH INFORMATION TO ANY TH I RD PARTY . EXCEPT AS MAY OTHERWISE BE PROVIDED FOR IN AN APPLICABLE AGREEMENT BETWEEN RECIP I ENT AND HSC
. COPY I NG OR DISC LOSURE OF THIS DOCUMENT AND THE I N FORMATION CONTAINED HEREIN BY ANYONE WITHOU T HSC' S PRIOR WR ITIEN PERMISS ION IS NOT AUTHORIZED AND MAY RESULT I N CRI M INAL AND /OR CIVI L LIABILITY . 

# I

THE DATA I N TH IS DOCUMENT WERE DEVELOPED ONLY TO MAI NTAI N SYSTE MS AND/OR PARTS MAN U FACT U RED BY OR FOR HAMILTON SUNDSTRAND OR AP P ROVED BY HAMILTON SUNDSTRAND. THE DATA MAY NOT BE APPLICABLE TO ANY OTHER SYSTE M S AND/ OR PARTS, REGARDLESS OF THEIR AP PARENT SI MI LARI TY TO SYSTEMS AND/ OR PARTS MANUFACTURED BY OR FOR HAM ILTON SUNDSTRAND OR APPROVED BY HAMILTON SUNDSTRAND
. DO NOT RELY IN ANY WAY ON DATA I N THIS DOCUMENT TO MAINTAIN OR OTHERWISE SUPPOR T SYSTEMS AND/ OR PARTS THAT WE R E NOT MANUFACTURED BY OR FOR HAMI LTON SUNDSTRAND O R APPROV E D BY HAMILTON SUNDSTRAND WITHOUT EVIDENCE T HAT THE FEDERAL AV IATION ADMIN I STRATION O R OTHE R REGULATORY AGENCY HAS DETER M IN E D THAT TH E DATA I N THIS DOCUMENT IS VALID FO R SUCH USE. Informa tion Subj ect t o Export Control Laws THE TECHN ICAL DATA IN THIS DOCUMENT (OR FI LE) IS CONTROLLE D FOR EXPORT UNDER THE EXPORT ADMINISTRATION REGULATIONS (EAR ). 15 CFR PARTS 730- 774 , ECCN: 9E99 1 . VIOLATIONS OF THESE LAWS MAY BE SUBJECT TO FINES AND PENALTIES UNDER THE EXPORT ADMINISTRATION ACT. 

### Emergency Hydraulic Power - Ram Air Turbine - Replace Balance Washer Retention Screws 

### 1 . Planning Information A . Effectivity The Hamilton Sundstrand Hub Assemblies , part number 733785 series, that are listed below and used on Boeing 757 aircraft : NOTE :
NOTE :

Part Number Series 733785

Feb10/ 10 The hub assemblies may be stocked as spares, rotables , or repair parts , or installed on Hamilton Sundstrand Ram Air Turbine/Hydraulic Pumps (RAT) , part number 730814 series (Boeing part number S258T71 0 series)
. Nonconforming screws from the affected manufacturing lots were distributed to other sources supplying the aircraft industry. Hub assemblies or RATs repaired or overhauled by facilities other than Hamilton Sundstrand could therefore be suspect and not included in the serial number list that follows
. Nonconforming screws known to be affected are those manufactured by Northeast Fasteners , Inc ., manufacturing lot 24057 . Serial Numbers 0107, 0105 , 0121 , 0151 , 0179 , 0204 , 0282 , 0289 , 0296 , 0315 , 0319 , 0337 , 0390 , 0403 , 0412 , 0421 , 0424 , 0426 , 0429 , 0430 , 0439 , 0445 , 0450 , 0477, 0503 , 0510 , 0512 , 0584 , 0585 , 0591, 0599 , 0609 , 0617 , 0624 , 0656 , 0673 , 0685 , 0789 , 0822 , 0841 , 0854 , 0911 , 0912 , 0936,0957 , 0961 , 0971 , 1061 , 1064 , 1096 , 1101 , 1102,1105 , 1113 , 1117,1170 , 11 72, 1173, X2069



# 730814-29-15 Page 1 of 14HAMILTON SUN OSTRAND 

# SERVICE BULLETIN Records indicate the following Hamilton Sundstrand RATs, part number 730814 series (Boeing part number S258T71 0 series), were delivered with affected hub assemblies from the list above. This list is provided for reference only . Incorporation of this service bulletin shall be tracked by hub assembly serial number. Part Number Series Serial Numbers 7 30814 0043 , 0167 , 0183 , 0266 , 0382 , 0411 , 0415 , 0722 , 0766 , 0803,0820 , 083 3, 0890 , 1100 , X2060 ,X2076 

### B. Concurrent Requirements None . 

### C . Reason Hamilton Sundstrand has discovered that RATs were manufactured with nonconforming screws . To date , there have been si x 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 inservice aircraft 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 turbine 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 elim i nate potential loss of a balance washer. Incorporation of this bulletin will ensure that the RAT balance washer screws conform to specification. 

### D. Description This bullet i n gives instructions to replace the balance washer screws and identify the hub assembly. Refer to Figure 1 of this bulletin for the location of the balance washers and screws . For a hub assembly or RAT with a missing 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 hub 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 (CFR) 21 .93/CS 2 1 .93 and comply with the applicable regulations and are on record with the supplier as Federal Avi ation Admin istration ( FAA) approved , as well as EASA/JAA approved by process via 14 CFR 21 .95/CS 21 . 95 .

Feb 10/ 10 

# 730814-29-15 Page 2 U se or disclosure of t h is data is sub j ect to rest rictions on the front p age of this document.HAMILTON SUNDSTRAND 

# SERVICE BULLETIN G. Manpower A maximum of 0 .5 man-hour will be required to replace the balance washer screws and identify the hub assembly. For a hub 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 remove the fractured screw and balance washer, balance the hub 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 addition , operators can also use the Hamilton Sundstrand website at www. ha miltonsundstrand.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 hub 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 Administration , 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 .



# 730814-29-15 Page 3 Use or discl osure of this data i s subject to restrictions on the front page of th is document.HAMILTON SUN OSTRAND 

# SERVICE BULLETIN (3) For units with a missing balance washer, or with a balance washer screw that cannot be removed in its enti rety, Hamilto n Sundstrand will incorporate this modification into returned un its at no charge until 

### February 1 , 2012 . Co ntact Hamilton Sundstrand at the address that follows for sc heduling information : Hamilto n 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 required for shop maintenan ce of the hub assembly or RAT is required to do this modification
. J . 

### Weight and Balance None . 

### K. Electrical Load Data Not changed . 

### L. References Hamilton Sundstrand Component Maintenance Manuals (CMM) 29-21-11 , Hamilton Sundstrand Standard Practices Manual (SPM ) 20-00-00 , and applicable Boeing Aircraft Maintenance Manuals (AMM)
. 

### M . Other Publications Affected Hamilton Sundstrand CMMs 2 9-21 - 11 will be revised to incorporate this service bulletin.

Feb 10 / 10 

# 730814-29-15 Page 4 Use or disclosu re of th is data is subj ect to restrictions on the f ront page of th is d ocument.

### Feb 10/10 HAMILTON SUN OSTRAND 

# SERVICE BULLETIN

LOCA TION OF B

ALA NCE WASHERS AN D SCR EWS (Q UANTITY 12)
SB-7308 142915-93829 

### Location of Balance Washers and Screws Figure 1



# 730814-29-15 Page 5 U se or d isclosu r e of th i s data is sub j ect to reslrictions on the fro nt page of th is document.HAMIL TON SUNOSTRAND 

# SERVICE BULLETIN
2. Accomplishment Instructions A. General CAUTION : THE HUB ASSEMBLY OR RAT CONTAINS DESIGN CRITICAL CHARACTERISTICS, PROCESSES , AND PROCEDURES
. THE DESIGN CRITICAL CHARACTERISTICS ARE IDENTIFIED WITH THE SYMBOL »DCC«
. REFER TO THE INTRODUCTION SECTION OF CMM 29-21-11 FOR A COMPLETE EXPLANATION OF DESIGN CRITICAL CHARACTERISTICS
. (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. (2) This service bulletin can be accomplished on a stand-alone RAT or hub assembly, or on a RAT installed on aircraft , unless removal of the RAT or hub assembly is specified herein . B. Modification (1) If the unit is installed on the aircraft, make sure the RAT is deployed (refer to the applicable AMM). CAUTION : THE RAT TURBINE BLADES SHOULD BE PROTECTIVELY COVERED DURING BALANCE WASHER SCREW REMOVAL AND INSTALLATION
. THE BLADES CAN BE EASILY DAMAGED
. (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 hub assembly and do a check for missing balance washers (10 through-10H , IPL Figure 3 , CMM 29-21-11)
. NOTE : The 12 threaded holes around the turbine cover circumference (in the front balance plane) each have a balance washer installed and use a countersunk socket head cap screw MS24667-14 to secure the washers [refer to screw (20, IPL Figure 3, CMM 29- 21-11)]. 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 hexagonal screw socket on the hub assembly. (4) If any balance washers are missing (because of a fractured screw), do the steps that follow :

Feb 10/10 (a) Ifthe unit is installed on the aircraft , remove either the hub assembly or the entire RAT from the aircraft (refer to the applicable AMM) for removal of the fractured screw and to balance the hub assembly. The unit must be returned to Hamilton Sundstrand or to a repair facility that has the capability to disassemble, repair, balance , and test the RAT. 

# 730814-29-15 Page 6 U se o r disclo sure of this data is subject to r estrictions o n the f ro nt page of th is document.Feb 10/10 HAMILTON SUNOSTRAND 

# 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) D isassemble the hub assembly or RAT ( refer to CMM 29-21-11 , DISASSEMBL Y) as necessary to remove the following parts and to get access to the fractured screw.

- Balance washers (10 through -10H , IPL Figure 3 , C MM 29-21-11 )

- Screws (20 , IPL Figure 3 , CMM 29-21-11 ) NOTE : Some screws , depending on how near they are to a turbine blade , can not be extracted unless the turbine blades are disassembled from the hub assembly. In those cases , either the hub 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 turb i ne (i n the area of the screw) to prevent surface dam age 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 hub 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 mechanical damage . Do the following if the visual examination reveals no obvious mechanical damage : 1 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)
.



### 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 is not smooth , requires e xcessive 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) ] . 

# 730814-29-15 Page 7 Use or disc losu re of this data is subject to restrictions on the fr ont page of th is document.HAMIL TON SUNOSTRAND 

# SERVICE BULLETIN (g) Assemble the hub assembly as necessary (refer to CMM 29-21-11 , ASSEMBLY)
. (h) Remove the protective covering from the RAT turbine blades . (i) Balance the hub assembly using new screws (PN MS24667-14) (refer to CMM 29-21-11 , ASSEMBLY)
. U) Assemble the RAT as necessary (refer to CMM 29-21-11 , ASSEMBLY)
. NOTE : If only the hub assembly was removed from the aircraft , the hub assembly must be installed into a slave RAT strut for testing . (k) Do a test of the RAT (refer to CMM 29-21-11 , TESTING AND TROUBLESHOOTING). (I) If necessary, remove the hub 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 HUB 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 installed balance washer. The original installed radial orientation of the washer must be maintained . (b) Do one of the steps that follow : 1 If the unit is installed on the aircraft , rotate the hub assembly until the balance washer is positioned in a manner to minimize the potential for the balance washer to fall out (when the associated screw is removed)
. 2 If the hub assembly or RAT is off the aircraft, position the unit to access the balance washer facing up . CAUTION : DO NOT USE A WORN HEX TOOL WITH ROUNDED CORNERS TO REMOVE THE SCREW. IF A WORN TOOL IS USED, THE POTENTIAL EX ISTS FOR STRIPPING THE SOCKET HEAD OF THE SCREW. CAUTION : USE CARE NOT TO DAMAGE EITHER THE BALANCE WASHER OR HUB 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 strike 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 . 

# 730814-29-15 Page 8 Use o r disclosure of thi s dat a is subject to restrictions on the front page of th is d ocu m ent.Feb 10/10 HAMIL TON SUN OSTRAND 

# SERVICE BULLETIN (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 screw is protruding above the turbine cover surface , do the steps that follow :**~** Apply protective tape on the turbine (in the area of the screw) to prevent surface damage during the removal attempt. b Use pliers, a vice grip, or an equivalent gripping tool to remove the screw. c Remove the protective tape from the turbine . d If the screw is removed in its entirety, proceed to step 2 . 8 .(5) (e) of this 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 hub assembly or the entire 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 repair 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 hub assembly. The turbine hub and turbine blades should be protectively covered to prevent mechanically induced damage during the extraction procedure . a For hub assemblies or RATs removed from the aircraft , disassemble the unit (refer to CMM 29-21-11 , DISASSEMBLY) as necessary to get access to the fractured screw. NOTE : Some screws , depending on how near they are to a turbine blade , can not be extracted unless the turbine blades are disassembled from the hub assembly. In those cases , either the hub assembly or the entire RAT must be removed from the aircraft and disassembled as necessary to remove the screw. 

# 730814-29-15 Page 9 U se or disclosure of this data is subject to restr ict ions on the front page of this document.Feb 10/10 HAMILTON SUN OSTRAND 

# SERVICE BULLETIN .Q Use a screw extractor (or equivalent) to remove the remaining portion of the fractured screw. Make sure no filings or fragments enter the hub assembly. Do not use heat or fluid to remove the screw.**~** 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)]. 4 If disassembly of the hub 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 hub assembly was required to remove the fractured screw, do the following:**~** Remove the remaining screws (20, IPL Figure 3 , CMM 29 -21-11) and the following balance washers :

- Balance washers ( 10 through -1 OH) 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 R 1 , paragraph 3 . Procedure Tang Drive Inserts (MS21209 Series)]. 

# 730814-29-15 Page 10 U se or disclosu re ol this data is subject to r estrictions on the lront pa ge of this d ocument.HAMIL TON SUNDSTRAND 

# SERVICE BULLETIN**~** 

### Assemble the hub assembly as necessary (refer to CMM 29-21-11 , ASSEMBLY)
. d Remove the protective covering from the RAT turbine blades.**~** 

### Balance the hub assembly using new screws (PN MS24667-14) (refer to CMM 29-21-11 , ASSEMBLY)
. f Assemble the RAT as necessary (refer to CMM 29-21-11 , ASSEMBLY)
. NOTE : If only the hub assembly was removed from the aircraft , the hub assembly must be installed into a slave RAT strut for testing . g Do a test of the RAT (refer to CMM 29-21-11 , TESTING AND TROUBLESHOOTING)
. h If necessary, remove the hub assembly from the slave RAT strut that was used for testing . Proceed to paragraph 2 .B . (6) of this bulletin . CAUTION : IF A BALANCE WASHER IS MISPLACED AFTER SCREW REMOVAL AND ITS ORIGINALLY INSTALLED ORIENTATION CANNOT BE DETERMINED , THE HUB ASSEMBLY OR ENTIRE RAT MUST BE RETURNED TO HAMIL TON 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, install 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 marking method (tape , indelible ink, or equivalent) to mark the location 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 installed balance washers or the locations where the screws had been replaced)
. U) Remove the protective covering from the RAT turbine blades . (6) After all of the balance washer screws have been replaced, identify the hub assembly as follows (refer to SPM 20-00-00 , ASSEMBLY) : (a) Add the symbol 29-15 to a blank area of the hub assembly identification plate (40 or -40A , IPL Figure 3 , CMM 29-21-11)
. (7) If the unit is installed on the aircraft, make sure the RAT is re-stowed (refer to the applicable AMM)
.

Feb 10/10 

# 730814-29-15 Page 11 U se or d isclosure ol th is data is su bj ect to restrictions on the front pa ge of th is docu ment .HAMIL TON SUN OSTRAND 

# SERVICE BULLETIN C. Identification NOTE : After all of the balance washer screws have been replaced , the hub assembly is identified by adding the symbol 29-15 to a blank area of the hub assembly identification plate . 

### D. Test (1) For units in the shop (if no balance washers were found missing, disassembly of the hub assembly 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 - 11 , 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 . 

### 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 hub 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 730814-29-15 " form (refer to Figure 2 of this bulletin), complete the form , and fax the completed form to Hamilton Sundstrand as follows : Hamilton Sundstrand Corporation Retrofit Management Group Fax: +1-860-998-3695 

# 730814-29-15 Page 12 U se or d isclosure of this data is subject to restricti o ns on the fr ont pag e of this docu m ent.HAMIL TON SUNDSTRAND 

# SERVICE BULLETIN

SENT FROM : 

## Sender Name: NOTIFICATION OF COMPLETED SB 730814-29- 15 "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 Group Fax: +1-860-998-3695 Hub Assembly Serial Number

Feb 10/10 Aircraft MSN or Tail Number Bulletin Completion Date

Notification of Completion Form Figure 2 Comments



# 730814-29-15 Page 13 U se or disclosu re of this data is subject to restrictions on the front page of this document.HAMIL TON SUNOSTRAND 

# SERVICE BULLETIN 3. Materiallnformation NOTE : Refer to Hamilton Sundstrand CM M 29-21-11 for expendable parts information
. Qty Per Unit Disposition/ New PIN Unit List Price Key Word Old P/N Instructions Same RF Not Applicable Ram Air Turbine/ 730814 Series Change (Note 1) Hydraulic Pump (Note 2) Same 1 Not Applicable Hub Assemb ly 733785 Series Change and identify with the symbol 29-15 Same 12 (Note 3) Screw MS24667-14 Remove suspect old screws, install new conforming screws Note 1 : Hub assembl ies or RATs modified according to this service bulletin are identified by marking the symbol 29-15 on the hub 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 

# 730814-29-15 Page 14 Use or d isclosure of !his dala is subjecllo reslriclions on ! he fran! page of !his document