S-76® HELICOPTER

ALERT SERVICE 

BULLETIN

NOTICE TO ALL PERSONS RECEIVING THIS DOCUMENT:

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(INCLUDING REPRODUCTION AS A DERIVATIVE WORK), OR USED FOR MANUFACTURE FOR ANYONE OTHER THAN SIKORSKY AIRCRAFT CORPORATION AND/OR ITS SUBSIDIARIES WITHOUT ITS WRITTEN CONSENT,

AND THAT NO RIGHT IS GRANTED TO DISCLOSE OR SO USE ANY INFORMATION CONTAINED HEREIN. ALL RIGHTS RESERVED. ANY ACT IN VIOLATION OF APPLICABLE LAW MAY RESULT IN CIVIL AND CRIMINAL 

PENALTIES. 

EXPORT WARNING: THESE COMMODITIES, TECHNICAL DATA OR SOFTWARE ARE SUBJECT TO THE EXPORT CONTROL OF EITHER THE INTERNATIONAL TRAFFIC IN ARMS REGULATIONS (ITAR) OR THE EXPORT 

ADMINISTRATION REGULATIONS (EAR) AND CANNOT BE EXPORTED WITHOUT THE PRIOR AUTHORIZATION OF EITHER THE DEPARTMENT OF STATE OR THE DEPARTMENT OF COMMERCE. THE TERM “EXPORT”

INCLUDES ANY DISCLOSURE AND/OR PROVISION OF ACCESS TO COMMODITIES, TECHNICAL DATA OR SOFTWARE TO OR BY FOREIGN NATIONALS (WHETHER LOCATED IN THE UNITED STATES OR ABROAD). THIS 

REQUIREMENT ALSO APPLIES TO FOREIGN NATIONAL EMPLOYEES OF U.S. COMPANIES AND THEIR FOREIGN SUBSIDIARIES.

S-76® IS A REGISTERED TRADEMARK OF SIKORSKY AIRCRAFT CORPORATION.

ASB 76-66-52

Basic Issue ▪ April 1/14

SUBJECT: POWERTRAIN – Tail Drive Shaft – One-Time Inspection and Torque Verification of Tail 

Drive Shaft (TDS) Flange Bolt

Section 3. PLANNING INFORMATION

A. Effectivity All S-76A through D model helicopters up to and including serial number 761051

including spares.

Component: All S-76 TDS, with Part Numbers (P/N) 76361-04004 (all dash 

numbers) with serial numbers prior to A127-01093, and 76361-04604 (all dash

numbers) with serial number prefixes A240 (all serial numbers), B240 (all serial 

numbers), and C240 all serial numbers up to and including 00880.

B. Purpose To perform a one-time inspection of TDS flange-to-shaft attachment hardware for 

proper installation and torque.

There were instances where TDS flange-to-shaft attachment hardware has been 

found loose or fractured.

C. Description Helicopter is prepared for maintenance. TDS is removed. TDS flange-to-shaft 

attachment hardware is inspected for movement, torque stripe misalignment, and 

correct assembly. If movement, misalignment of torque stripe, or misassembled 

hardware is found, TDS flange-to-shaft attachment hardware is removed, returned 

to Sikorsky along with attached Return for Sikorsky Engineering Evaluation form

and Torque Verification of TDS Flange Bolt Data Sheet, and replaced with 

Sikorsky Aircraft Corporation

6900 Main Street P.O. Box 9729

Stratford, Connecticut 06615-9129

(203) 386-4000

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SERVICE BULLETIN Basic Issue ▪ April 1/14

Section 1. PLANNING lNFORMATION (Continued)

serviceable TDS flange-to-shaft attachment hardware. Helicopter is returned to 

service.

D. Compliance Compliance is essential. The instructions outlined herein shall be accomplished no 

later than November 30, 2014.

E. Approval Inspection item.

F. Manpower (Estimated)

Task No. of Men No. of Hours Man-Hours*

Remove Driveshaft 1 0.75 0.75

Inspect TDS Flange Attachment 

Hardware.

1 0.50 0.50

Install Driveshaft

(*Existing assembly or new if unit is found 

to be unserviceable).

1 1.00 1.00

Total Man-Hours 2.25

*Estimate does not include time required to prepare helicopter or return it to flight status.

G. Tooling

Qty Nomenclature Part No. Source

1 Locally Fabricated Special Tool Modified McMaster Carr P/N 

5543A35 or equivalent

(1)

1 Torque Wrench (30 - 150 inchpounds)Commercially Available or equivalent (2)

1 Caliper Commercially Available or equivalent (2)

(1) Available from McMaster Carr. Website: www.mcmaster.com

(2) Procure through local supply.

H. Weight and Balance

Not affected.

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Basic Issue ▪ April 1/14 SERVICE BULLETIN

Section 1. PLANNING lNFORMATION (Continued)

I. Electrical Load Data

Not affected.

J. Software Load Data

Not changed.

K. References

(1) Maintenance Manual SA 4047-76-2, Chapter/Section 20-04-00.

(2) Maintenance Manual SA 4047-76B-2, Chapter/Section 20-04-00.

(3) Maintenance Manual SA 4047-76C-2, Chapter/Section 20-04-00.

(4) Maintenance Manual SA S76D-AMM-000, Chapter/Section 20-04-00.

(5) Maintenance Manual SA S76D-AMM-000, Chapter/Section 65-11-01.

(6) Maintenance Manual SA S76D-AMM-000, Chapter/Section 65-11-02.

(7) Maintenance Manual SA S76D-AMM-000, Chapter/Section 65-11-04.

(8) Maintenance Manual SA S76D-AMM-000, Chapter/Section 65-13-02.

(9) Maintenance Manual SA 4047-76-2, Chapter/Section 66-40-00.

(10) Maintenance Manual SA 4047-76B-2, Chapter/Section 66-40-00.

(11) Maintenance Manual SA 4047-76C-2, Chapter/Section 66-40-00.

L. Publications Affected

(1) Temporary Revision No. 66-28 against Maintenance Manual, SA 4047-76B-2, 

Chapter/Section 66-40-00 is issued concurrently with this ASB.

(2) Temporary Revision No. 66-29 against Maintenance Manual, SA 4047-76C-2, 

Chapter/Section 66-40-00 is issued concurrently with this ASB.

(3) Temporary Revision No. 66-52 against Maintenance Manual, SA 4047-76-2, 

Chapter/Section 66-40-00 is issued concurrently with this ASB.

(4) Temporary Revision No. 65-02 against Maintenance Manual, SA S76D-AMM-000, 

Chapter/Section 65-13-02 is issued concurrently with this ASB.

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SERVICE BULLETIN Basic Issue ▪ April 1/14

Section 2. MATERIAL INFORMATION

A. Attachment

Return for Sikorsky Engineering Evaluation form.

B. Basis for Material Data

Per helicopter.

C. Bill of Material

None.

C. Consumable Material

Qty Nomenclature Part No. Source

A/R Corrosion Preventive Compound MIL-C-81309 Type 2, 3 or equivalent (1)

A/R Epoxy Polyamide Primer MIL-PRF-23377 or equivalent (1)

Epoxy Primer (Alternate) MIL-PRF-85582 or 

equivalent

(1)

(1) Procure through local supply.

Section 3. ACCOMPLISHMENT INSTRUCTIONS

A. Prepare helicopter for maintenance:

(1) Turn off all helicopter electrical and hydraulic power.

(2) Engage rotor brake.

(3) Remove driveshaft from helicopter. (Refer to applicable Maintenance Manual).

OBSERVE ALL CAUTIONS AND WARNINGS ON CONTAINERS 

WHEN USING CONSUMABLES. WHEN APPLICABLE, WEAR 

NECESSARY PROTECTIVE GEAR DURING HANDLING AND USE. IF 

A CONSUMABLE IS FLAMMABLE OR EXPLOSIVE, MAKE CERTAIN 

CONSUMABLE AND ITS VAPORS ARE KEPT AWAY FROM HEAT, 

SPARK AND FLAME. MAKE CERTAIN FIREFIGHTING EQUIPMENT 

IS READILY AVAILABLE PRIOR TO USE. FOR ADDITIONAL 

INFORMATION ON TOXICITY, FLASHPOINT AND FLAMMABILITY 

OF CHEMICALS, CONSULT YOUR MEDICAL PEOPLE OR THE 

MANUFACTURER OF THE CONSUMABLE.

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Basic Issue ▪ April 1/14 SERVICE BULLETIN

Section 3. ACCOMPLISHMENT INSTRUCTIONS (Continued)

B. Inspect TDS as follows:

NOTE: This inspection must be performed for all TDS’s listed in effectivity section.

(1) Inspect TDS flange attachment hardware at all four locations (four locations for each drive 

shaft) (Figures 1 and 2) for evidence of movement or torque stripe misalignment. If 

evidence of movement or torque stripe misalignment, proceed to Step D.

(2) Attempt to rotate each nut (SS5086-04) using finger pressure. If hardware can be rotated 

by hand, proceed to Step D.

(3) Check that hardware is assembled correctly as follows:

(a) Verify that only one radius washer is present under the head of the bolt and oriented 

correctly, with the radius side adjacent to the inner diameter. (Refer to Figure 3).

(b) Verify that one thick washer and one thin washer are present under the nut. (Refer 

to Figure 3).

(c) If hardware is not assembled correctly, proceed to Step D.

NOTE: If locally fabricated special tool (modified McMaster Carr, P/N 5543A35 or 

equivalent) is not available, proceed to Step B. (5).

(4) Using locally fabricated special tool (modified McMaster Carr, P/N 5543A35 or equivalent)

(Figure 4), check torque on each nut (SS5086-04) on TDS flange-to-shaft attachment. If 

torque on any nut is less than 105 inch-pounds, proceed to Step D.

(5) If locally fabricated special tool (modified McMaster Carr, P/N 5543A35 or equivalent) is 

not available, perform torque verification check as follows:

(a) Remove snap ring (S1635-61210), closest to flange, from bearing support assembly.

(b) Slide bearing support assembly away from flange to allow clearance for common 

tools. (Figure 5).

(c) Using torque wrench, check torque on each nut (SS5086-04) on tail rotor drive shaft 

flange-to-shaft attachment. If torque on any nut is less than 105 inch-pounds, 

proceed to Step D.

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SERVICE BULLETIN Basic Issue ▪ April 1/14

Section 3. ACCOMPLISHMENT INSTRUCTIONS (Continued)

(d) Reinstall snap ring (S1635-61210) to bearing support assembly.

C. If during the inspection, no evidence of movement was found, torque stripe was not misaligned, 

hardware could not be rotated by hand, hardware was assembled correctly, or torque of any nut 

was not less than 105 inch-pounds, perform the following:

(1) Re-apply torque stripe as required. (Refer to applicable Maintenance Manual, 

Chapter/Section 20-04-00). Inspection is complete, proceed to Section 3, Step E.

D. If during the inspection, evidence of movement was found, torque stripe was misaligned, 

hardware rotated by hand, hardware was not assembled correctly, or torque of any nut was less 

than 105 inch-pounds, perform the following:

NOTE: • Index mark is applied to flange and shaft to make sure flange is reinstalled in the 

same position and to maintain shaft balance.

• If applicable, record information in Torque Verification of TDS Flange Bolt Data 

Sheet.

(1) Apply index mark to flange and shaft.

NOTE: • With the exception of radius washers, all shaft to flange attaching hardware is 

one time use. After removal, return bolts, washers, and nuts to Sikorsky (address 

below) with attached Return for Sikorsky Engineering Evaluation form.

• Radius washers (SS4411-08S025NP or ALT SS4411-08S025) may be reused if 

inspected and no visible signs of wear or fretting is found. If radius washers are 

damaged return to Sikorsky (address below) with attached Return for Sikorsky 

Engineering Evaluation form.

(2) Unbolt and remove flange from shaft.

(3) Visually inspect radius washers (SS4411-08S025NP or ALT SS4411-08S025) for wear or 

fretting.

NOTE: • Include time since new (TSN) and time since overhaul (TSO) for returned 

hardware.

• Radius washers (SS4411-08S025NP or ALT SS4411-08S025) are only to be 

returned if found damaged.

Make sure snap ring is reseated in groove and locked. 

Failure to reseat snap ring in groove can cause unintended 

failure of drive shaft bearing.

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Basic Issue ▪ April 1/14 SERVICE BULLETIN

Section 3. ACCOMPLISHMENT INSTRUCTIONS (Continued)

(4) Return flange to shaft hardware (four sets: nuts, bolts, washers, and radius washers if 

necessary) to Sikorsky with attached Return for Sikorsky Engineering Evaluation form and 

Torque Verification of TDS Flange Bolt Data Sheet at the address below:

HELICOPTER SUPPORT INC. (H.S.I.)

URGENT: Engineering Evaluation

Attn: CSS Commercial Aircraft Product Support

300 Monotowese Avenue Extension

North Haven, CT 06473

(5) Replace TDS with a serviceable unit, or inspect flange and stub as follows:

(a) Inspect driveshaft and flange for cracks and fractures using fluorescent penetrant. 

No cracks or fractures allowed. (Refer to Figure 6, Reference Letters A and B).

(b) Inspect wear of mounting hole on driveshaft and flange. Hole diameter shall be no 

greater that 0.252 inch maximum. Holes may be up to 0.0015 inch out-of-round if 

diameter is met. (Refer to Figure 6, Reference Letter C).

(c) Using caliper (commercially available or equivalent), measure stub shaft outer

diameter. Diameter shall be no less than 1.7565 inches minimum. (Refer to Figure 6, 

Reference Letter D).

(d) Using caliper (commercially available or equivalent), measure flange inner diameter. 

Diameter shall be no more than 1.7585 inches. (Refer to Figure 6, Reference Letter 

E).

(e) Using caliper (commercially available or equivalent), measure flange face width. 

(Refer to Figure 6, Reference Letter F):

1. For driveshafts with P/N 76361-04004 (all dash numbers), width shall be no 

less than 0.210 inches minimum.

2. For driveshafts with P/N 76361-04604 (all dash numbers), width shall be no 

less than 0.275 inches minimum.

(f) If any parts fail any of the criteria listed here, the part is to be scrapped and replaced 

with a serviceable unit.

(6) If necessary, replace bearing support as follows:

(a) Remove bearing support from shaft.

(b) If necessary, remove snap rings (S1635-61210) and press out bearing from support.

(c) Coat Outer Diameter (OD) of new bearing and Inner Diameter (ID) of bearing liner 

with corrosion preventive compound (MIL-C-81309, Type 2, 3 or equivalent), and 

press bearing into support. Remove excess squeeze out. Install snap rings (S1635-

61210).

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S-76 ALERT ASB 76-66-52

SERVICE BULLETIN Basic Issue ▪ April 1/14

Section 3. ACCOMPLISHMENT INSTRUCTIONS (Continued)

(d) Install bearing support assembly on shaft so that bearing inner race is over liner of 

shaft.

(7) Align index marks and install flange on shaft.

NOTE: • When installing flange on shaft for shaft assemblies 76361-04004 or 76361-

04604, use new bolts, washers, and nuts.

• Radius washers (SS4411-08S025NP or ALT SS4411-08S025) may be reused if 

inspected and no damage is found.

(8) Coat grip length of bolts, and contact surfaces on radius washers and washers with epoxy 

polyamide primer (MIL-PRF-23377 or equivalent). Do not prime threads of bolts.

NOTE: Ensure that radius washer (SS4411-08S025NP or ALT SS4411-08S025) is 

properly seated against the inside diameter of the shaft.

(9) If using locally fabricated special torque tool (modified McMaster Carr, P/N 5543A35 or 

equivalent) to install flange to shaft, perform the following (Refer to Figure 4):

(a) Hand tighten attaching hardware in all locations.

(b) Measure prevailing torque of nuts (SS5086-04) at every location and record value. 

Prevailing torque values should be between 3.5 - 30 inch-pounds. If prevailing 

torque value is above or below 3.5 - 30 inch-pounds, replace nut.

(c) Torque nuts (SS5086-04) to 50 inch-pounds in the sequence shown in Figure 3.

(d) Repeat torque sequence on nuts at 75 inch-pounds.

(e) Repeat torque sequence on nuts at 110 inch-pounds plus measured prevailing 

torque for each location and until torque has stabilized for each location.

(10) If locally fabricated special torque tool (modified McMaster Carr, P/N 5543A35 or 

equivalent) is unavailable, perform the following:

(a) Remove snap ring (S1635-61210), closest to flange, from bearing support assembly.

(b) Slide bearing support assembly away from flange to allow clearance for common 

tools. (Figure 5).

(c) Hand tighten attaching hardware in all locations.

THE NUT (SS5086-04) IS TO BE TORQUED WHILE THE BOLT IS 

HELD STATIONARY.

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Basic Issue ▪ April 1/14 SERVICE BULLETIN

Section 3. ACCOMPLISHMENT INSTRUCTIONS (Continued)

(d) Measure prevailing torque of nuts (SS5086-04) at every location and record value. 

Prevailing torque values should be between 3.5 - 30 inch-pounds. If prevailing 

torque value is above or below 3.5 - 30 inch-pounds, replace nut.

(e) Torque nuts (SS5086-04) to 50 inch-pounds in the sequence shown in Figure 3.

(f) Repeat torque sequence on nuts at 75 inch-pounds.

(g) Repeat torque sequence on nuts at 110 inch-pounds plus measured prevailing 

torque for each location and until torque has stabilized for each location.

(h) Reinstall snap ring (S1635-61210) to bearing support assembly.

(11) Apply torque stripe, to nuts, washers, and bolt ends. (Refer to applicable Maintenance 

Manual, Chapter/Section 20-04-00).

(12) Service TDS assembly. (Refer to applicable Maintenance Manual).

(13) Reinstall TDS assembly. (Refer to applicable Maintenance Manual).

E. Perform inspection on all TDS assemblies listed in Effectivity section.

F. Return helicopter to service.

THE NUT (SS5086-04) IS TO BE TORQUED WHILE THE BOLT IS 

HELD STATIONARY.

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SERVICE BULLETIN Basic Issue ▪ April 1/14

Section 3. ACCOMPLISHMENT INSTRUCTIONS (Continued)

G. Torque Verification of TDS Flange Bolt Data Sheet.

(1) Report the following data back to Sikorsky Aircraft Design Engineering Point of Contact.

(Refer to Section 3, Step D. (4)).

(2) Record the following information for each helicopter:

Customer/Operator Name: 

Helicopter Serial Number: 

Helicopter Total Time Since New: 

Time Since Last Overhaul: 

Flange Location Between Driveshaft Sections I and II: 

Driveshaft Serial Number:

Last Hardware Replacement Date (if known): 

Number of Flange Bolts that Passed/Failed Torque Check: Passed Failed 

Flange Location Between Driveshaft Sections II and III: 

Driveshaft Serial Number:

Last Hardware Replacement Date (if known): 

Number of Flange Bolts that Passed/Failed Torque Check: Passed Failed 

Flange Location Between Driveshaft Sections III and IV: 

Driveshaft Serial Number:

Last Hardware Replacement Date (if known): 

Number of Flange Bolts that Passed/Failed Torque Check: Passed Failed 

Date Inspection is Performed: 

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ASB 76-66-52 S-76 ALERT

Basic Issue ▪ April 1/14 SERVICE BULLETIN

Section 3. ACCOMPLISHMENT INSTRUCTIONS (Continued)

TDS FLANGE-TO-SHAFT HARDWARE INSTALLATION

FIGURE 1

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SERVICE BULLETIN Basic Issue ▪ April 1/14

Section 3. ACCOMPLISHMENT INSTRUCTIONS (Continued)

TORQUE STRIPE VERIFICATION

FIGURE 2

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Basic Issue ▪ April 1/14 SERVICE BULLETIN

Section 3. ACCOMPLISHMENT INSTRUCTIONS (Continued)

HARDWARE STACK-UP AND TORQUE PATTERN

FIGURE 3

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SERVICE BULLETIN Basic Issue ▪ April 1/14

Section 3. ACCOMPLISHMENT INSTRUCTIONS (Continued)

LOCALLY FABRICATED SPECIAL TOOL (MCMASTER P/N 5543A35)

FIGURE 4

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Basic Issue ▪ April 1/14 SERVICE BULLETIN

Section 3. ACCOMPLISHMENT INSTRUCTIONS (Continued)

BEARING SUPPORT ASSEMBLY

FIGURE 5

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SERVICE BULLETIN Basic Issue ▪ April 1/14

Section 3. ACCOMPLISHMENT INSTRUCTIONS (Continued)

DRIVESHAFT INSPECTION

FIGURE 6 

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ASB 76-66-52 S-76 ALERT

Basic Issue ▪ April 1/14 SERVICE BULLETIN

Section 3. ACCOMPLISHMENT INSTRUCTIONS (Continued)

 H. Record of Compliance:

(1) Make helicopter logbook entries to show compliance with this ASB as follows:

(a) Make helicopter level logbook entry on form SA7343-15.

(b) When ASB modifies a component that can be removed from this helicopter:

1. Make component log card entries on forms SA7343-22 & SA7343-21 as 

applicable.

2. If a component modified by this ASB does not have a log card and the ASB 

does not create one, then annotate compliance on the next higher assembly 

that the component belongs to which does have a log card.

NOTE: If access to www.Sikorsky360.com is unavailable, complete attached ALERT 

SERVICE BULLETIN COMPLIANCE RECORD CARD and return it to Sikorsky 

Aircraft Corporation.

(2) Make an appropriate electronic compliance entry in the E-Notification section at 

www.Sikorsky360.com. Refer to User Guide located on the www.Sikorsky360.com/ENotification Search page.

Page 17

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(Fold over and tape closed)

SIKORSKY AIRCRAFT CORPORATION

FACSIMILE NUMBER (860) 998-7565

EMAIL ADDRESS: GPSIKSASProductSafet@utc.com

ATTENTION: SAS PRODUCT SAFETY MANAGER

SIKORSKY AEROSPACE SERVICES

(Fold Up to Arrows)

IMPORTANT NOTICE

Upon COMPLIANCE with the attached ASB, Sikorsky requests your cooperation 

in completing and returning this ENTIRE PAGE by MAIL, FAX, or scan & 

EMAIL.

Please fill in the requested information at the bottom of the page, so we may maintain 

proper records documenting the configuration of your aircraft. This information is useful 

when determining configuration and effectivity of issues affecting fielded aircraft.

This request is in keeping with our policy to assure that our customers receive the latest 

information applicable for the maintenance of your aircraft. Thank you.

ALERT SERVICE BULLETIN: ________________ Compliance Record Card

TITLE: ___________________________________________________________________

___________________________________________________________________

___________________________________________________________________

OWNER/OPERATOR: _____________________________________________________

SUBMITTED BY: ___________________________ DATE: ____________________

FOLLOWING SERIAL NUMBERS ARE NOT AFFECTED BY THIS ASB

ASB HAS BEEN COMPLIED WITH ON HELICOPTER SERIAL NUMBERS:

___________ ___________ ___________ ___________ ___________ ___________

___________ ___________ ___________ ___________ ___________ ___________

ASB No. 76-66-52

POWERTRAIN – Tail Drive Shaft – One-Time Inspection and Torque Verification 

of Tail Drive Shaft (TDS) Flange Bolt
No Postage 

Necessary

BUSINESS REPLY MAIL

FIRST-CLASS MAIL PERMIT NO. 432 BRIDGEPORT CT

POSTAGE WILL BE PAID BY ADDRESSEE

SIKORSKY AIRCRAFT CORPORATION

P.O. BOX 9729

6900 MAIN STREET

STRATFORD, CONNECTICUT 06615-9129 U.S.A.

MAILSTOP: S328A

ATTENTION: SAS PRODUCT SAFETY MANAGER

SIKORSKY AEROSPACE SERVICES

Please complete the form on the reverse side and FAX to

FACSIMILE NUMBER (860) 998-7565

Or scan and email to:

EMAIL ADDRESS: GPSIKSASProductSafet@utc.com

or fold and return ENTIRE form to Sikorsky Aircraft Corporation
Return for Sikorsky Engineering Evaluation

RETURN INSTRUCTIONS:

Return parts indicated below to Sikorsky Aircraft Corporation by the fastest traceable means with the 

following information: 

Send to: 

 Helicopter Support, Inc. (H.S.I.) 

 URGENT: Engineering Evaluation

Attn: CSS Commercial Aircraft Product Support

300 Montowese Avenue Extension

North Haven, CT 06473 

Mark for: S-61 S-70 S-76 S-92

Product Safety/Engineering Evaluation

Engineering 

 

HUMS Anomaly or Exceedance 

 

PART INFORMATION: 

Part Number _________ Serial Number: ____________

Nomenclature ____________________________________________________________

Reason for Removal Failed torque inspection per ASB 76-66-55

Helicopter Serial Number __________ A/C Hours at Removal: ________ 

Date Removed: ________ Component Hours at Removal: ________

TSR: ________ TSO: ________

Customer/Operator Name _______________________________________________________

Sikorsky FTR # _______________

Sikorsky RFA # _______________

Requested by customer or Sikorsky? Sikorsky per ASB 76-66-52 TRD Hardware Check

(if Sikorsky, please list requestor name)

Remarks: Notify Tim Tomasko upon part arrival and send to the materials lab

ADDITIONAL INSTRUCTIONS: 

1. Fax or email a copy of this form with shipping information (AWB#, Flight#, Shipper Tracking#)

as applicable to +1 860-353-6557 or sascommercialproduct@utc.com 

Include a copy of this form in the box with the part. 

2. If a Sikorsky FSR is on-site, obtain the FTR # from him and record in the spaces above, if not already 

annotated. 

3. Any questions regarding the return of this part should be directed to the Requestor listed above.

SA 1600 5/4/11

Verify current revision of form