Page 1 of 17 

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S-76 ALERT 

SERVICE BULLETIN 

NOTICE TO ALL PERSONS RECEIVING THIS DOCUMENT: 

WARNING: THIS DOCUMENT, OR AN EMBODIMENT OF IT IN ANY MEDIA, DISCLOSES INFORMATION WHICH IS PROPRIETARY, IS THE PROPERTY OF SIKORSKY AIRCRAFT 

CORPORATION AND/OR ITS SUBSIDIARIES, IS AN UNPUBLISHED WORK PROTECTED UNDER APPLICABLE COPYRIGHT LAWS, AND IS DELIVERED ON THE EXPRESS CONDITION 

THAT IT IS NOT TO BE USED, DISCLOSED, REPRODUCED, IN WHOLE OR IN PART (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. 

ASB 76-65-67A 

June 13/12 

Revision A ▪ July 18/12 

SUBJECT: ROTORS – Spindle Assemblies – One-Time Non-Destructive Inspection (NDI) of 

Spindle/Cuff Assembly and Application of White Paint to Enhance Existing Inspection 

Procedure 

Section 1. PLANNING INFORMATION 

A. Effectivity All S-76 model helicopters with serial numbers up to and including 760822. 

Component: Spindle/Cuff Assembly, 76102-08001-045/-046, including spares. 

Blade Fold Cuff Assembly, 76150-09601-041, including spares. 

B. Purpose To perform an NDI to inspect the upper and lower cuff plate on each spindle/cuff 

assembly or blade fold cuff assembly for cracks, and apply white paint to lower cuff 

plate to enhance the existing 25 hour visual inspection procedure. 

C. Description For each spindle/cuff assembly or blade fold cuff assembly, including spares, 

leading and trailing edges of upper and lower cuff plate are cleaned and an NDI is 

performed to inspect for cracks. If any crack indications are detected, a different 

NDI is performed to verify cracks. If cracks are verified, spindle/cuff assembly or 

blade fold cuff assembly is removed from service. If cracks cannot be verified, 

Sikorsky Customer Service Engineering is contacted for further instruction. If no 

cracks are found, a portion of spindle/cuff assembly or blade fold cuff assembly 

lower cuff plate is painted white to enhance the existing inspection procedure. 

D. Compliance Compliance is essential. The instructions outlined herein shall be accomplished 

within 150 flight hours or 90 days from the issue date of Revision A of this ASB, 

whichever occurs first. 

For all spare spindle/cuff assemblies and/or blade fold cuff assemblies, the 

instructions outlined herein shall be accomplished within 150 flight hours or 90 

Sikorsky Aircraft Corporation

6900 Main Street P.O. Box 9729 

Stratford, Connecticut 06615-9129 

(203) 386-4000
S-76 ALERT ASB 76-65-67A 

SERVICE BULLETIN Revision A ▪ July 18/12 

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days from the issue date of Revision A of this ASB, or prior to installation on a 

helicopter, whichever occurs first. 

E. Approval Inspection item. 

F. Manpower (Estimated) 

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

Perform NDI 1 2.5 2.5 

Application of White Paint 1 2.0 2.0

Total Man-Hours 4.5 

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

G. Material 

None. 

H. Tooling 

(1) Phasec 3d flaw detector (or equivalent) (Eddy Current inspection only). 

(2) VM Products 2502RAFX-_ probe (or equivalent) (Eddy Current inspection only). 

(3) Olympus (or equivalent) flaw detector (ultrasonic inspection only). 

(4) Search unit, 45 degree miniature angle beam – 10 MHz (ultrasonic inspection only). 

(5) 5X or 10X magnifying glass (or equivalent) (visual inspection only). 

(6) Spray bottle (or equivalent) (Fluorescent Penetrant Inspection (FPI) only). 

(7) Handheld blacklight source that produces a minimum of 1200 micro W/cm2 at the 

examination surface (FPI only). 

(8) Titanium Reference Standard (3NotchEC.IT or equivalent). Available through HSI or 

PHTool. Website: www.phtool.com. (Eddy Current inspection only). 

I. Weight and Balance 

Not affected. 

J. Electrical Load Data 

Not affected. 

K. Software Load Data 

Not changed. 
ASB 76-65-67A S-76 ALERT

Revision A ▪ July 18/12 SERVICE BULLETIN

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Section 1. PLANNING lNFORMATION (Continued) 

L. References 

(1) Applicable Maintenance Manual. 

(2) S-76A Model Helicopters: 

(a) Temporary Revision No. 5-186 against Airworthiness Limitations and Inspection 

Requirements Manual SA 4047-76-2-1, Chapter/Section 5-20-00, 25-Hour 

Inspection Checklist, previously issued Jun 13/12. 

(b) Temporary Revision No. 5-187 against Airworthiness Limitations and Inspection 

Requirements Manual SA 4047-76-2-1, Chapter/Section 5-20-00, 1250-Hour 

Inspection Checklist, previously issued Jun 13/12. 

(c) Temporary Revision No. 5-188 against Airworthiness Limitations and Inspection 

Requirements Manual SA 4047-76-2-1, Chapter/Section 5-20-00, Calendar 

Inspection Checklist, previously issued Jun 13/12. 

(d) Temporary Revision No. 65-66 against Maintenance Manual SA 4047-76-2, 

Chapter/Section 65-12-02, Spindle Assemblies, previously issued Jun 13/12. 

(3) S-76B Model Helicopters: 

(a) Temporary Revision No. 5-163 against Airworthiness Limitations and Inspection 

Requirements Manual SA 4047-76B-2-1, Chapter/Section 5-20-00, 25-Hour 

Inspection Checklist, reissued concurrently with this ASB. 

(b) Temporary Revision No. 5-164 against Airworthiness Limitations and Inspection 

Requirements Manual SA 4047-76B-2-1, Chapter/Section 5-20-00, 1250-Hour 

Inspection Checklist, reissued concurrently with this ASB. 

(c) Temporary Revision No. 5-165 against Airworthiness Limitations and Inspection 

Requirements Manual SA 4047-76B-2-1, Chapter/Section 5-20-00, Calendar 

Inspection Checklist, reissued concurrently with this ASB. 

(d) Temporary Revision No. 65-40 against Maintenance Manual SA 4047-76B-2, 

Chapter/Section 65-12-02, Spindle Assemblies, reissued concurrently with this ASB. 

(4) S-76C Model Helicopters: 

(a) Temporary Revision No. 5-166 against Airworthiness Limitations and Inspection 

Requirements Manual SA 4047-76C-2-1, Chapter/Section 5-20-00, 25-Hour 

Inspection Checklist, reissued concurrently with this ASB. 

(b) Temporary Revision No. 5-167 against Airworthiness Limitations and Inspection 

Requirements Manual SA 4047-76C-2-1, Chapter/Section 5-20-00, 1250-Hour 

Inspection Checklist, reissued concurrently with this ASB. 
S-76 ALERT ASB 76-65-67A 

SERVICE BULLETIN Revision A ▪ July 18/12 

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Section 1. PLANNING lNFORMATION (Continued) 

(c) Temporary Revision No. 5-168 against Airworthiness Limitations and Inspection 

Requirements Manual SA 4047-76C-2-1, Chapter/Section 5-20-00, Calendar 

Inspection Checklist, reissued concurrently with this ASB. 

(d) Temporary Revision No. 65-36 against Maintenance Manual SA 4047-76C-2, 

Chapter/Section 65-12-02, Spindle Assemblies, reissued concurrently with this ASB. 

M. Publications Affected 

(1) Airworthiness Limitations and Inspection Requirements Manual, SA 4047-76-2-1, 

Chapter/Section 5-20-00. 

(2) Maintenance Manual SA 4047-76-2, Chapter/Section 65-12-02. 

(3) Airworthiness Limitations and Inspection Requirements Manual, SA 4047-76B-2-1, 

Chapter/Section 5-20-00. 

(4) Maintenance Manual SA 4047-76B-2, Chapter/Section 65-12-02. 

(5) Airworthiness Limitations and Inspection Requirements Manual, SA4047-76C-2-1, 

Chapter/Section 5-20-00. 

(6) Maintenance Manual SA 4047-76C-2, Chapter/Section 65-12-02. 

N. Attachment 

None. 

Section 2. MATERIAL INFORMATION 

A. Basis for Material Data 

Per helicopter. 

B. Bill of Material 

None. 
ASB 76-65-67A S-76 ALERT

Revision A ▪ July 18/12 SERVICE BULLETIN

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Section 2. MATERIAL INFORMATION (Continued) 

C. Consumable Material 

Qty Nomenclature Part No. Source

As Req’d White Paint Krylon® 51501 Gloss White 

or an equivalent acrylic enamel gloss 

white paint 

(1)(2) 

(Alternate) Plasti-Kote® 1109 Gloss 

White 

(2)(9) 

 (Alternate) Krylon® Industrial Tough 

Coat 

(2)(10) 

As Req’d Low-Lint Cloth A-A-59323, Type II or equivalent (2) 

As Req’d Isopropyl Alcohol Commercial grade or equivalent (2) 

As Req’d Masking Tape Commercial grade or equivalent (2) 

As Req’d Permanent Marker Commercial grade or equivalent (2) 

As Req’d Couplant Ultragel or equivalent (2)(7) 

As Req’d FPI Kit ZL-27A or equivalent (3)(6)(8) 

(Alternate) 985-P13 or equivalent (4)(6)(8) 

 (Alternate) FP-95A or equivalent (5)(6)(8) 

As Req’d Developer ZP-9F or equivalent (3)(6)(8) 

 (Alternate) 9D1B or equivalent (4)(6)(8) 

(Alternate) D-70 or equivalent (5)(6)(8) 

As Req’d Class 2 Solvent SKC-S or equivalent (3)(6)(8) 

(Alternate) 9PR50 or equivalent (4)(6)(8) 

 (Alternate) E-59 or equivalent (5)(6)(8) 

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. 
S-76 ALERT ASB 76-65-67A 

SERVICE BULLETIN Revision A ▪ July 18/12 

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Section 2. MATERIAL INFORMATION (Continued) 

(1) Available through Krylon. Website: www.krylon.com/ 

(2) Procure through local supply. 

(3) Manufactured by Magnaflux. Website: http://www.magnaflux.com/

(4) Manufactured by Chemetall. Website: http://www.chemetall.com/

(5) Manufactured by Met-L-Chek. Website: http://www.met-l-chek.com/

(6) For fluorescent penetrant, class 2 solvent and developer, equivalent materials shall be 

approved as Type 1, Method C, Level 3 sensitivity in accordance with SAE AMS2644 and 

listed for use in QPL-AMS2644. 

(7) For ultrasonic inspection only. 

(8) For FPI only. 

(9) Manufactured by Plasti-Kote®. Website: http://www.paint-markers.co.uk/

(10) Available through Krylon Products Group. Website: www.kpg-industrial.com/

Section 3. ACCOMPLISHMENT INSTRUCTIONS 

A. Prepare helicopter for inspection: 

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

(2) Engage rotor brake. 

(3) Using isopropyl alcohol and a clean, low-lint cloth, clean all spindle/cuff assembly or blade 

fold cuff assembly inspection area surfaces (Figure 1, Sheets 1 and 2). 

NOTE: • For spindle/cuff assemblies or blade fold cuff assemblies with 1900 flight hours or 

more, proceed to section B. 

• For spindle/cuff assemblies or blade fold cuff assemblies with less than 1900 flight 

hours, proceed to section C. 
ASB 76-65-67A S-76 ALERT

Revision A ▪ July 18/12 SERVICE BULLETIN

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Section 3. ACCOMPLISHMENT INSTRUCTIONS (Continued) 

B. Perform NDI per one of the following methods: 

NOTE: • Person performing NDI must be certified to Level 2, per NAS 410 or equivalent. If 

inspectors of other certification levels are utilized as permitted by NAS 410 or 

equivalent, this decision is the responsibility of the operator and their responsible 

Level 3 personnel. 

• Eddy Current inspection, FPI and ultrasonic inspection are acceptable alternates 

to each other. 

• Following applies to all spindle/cuff assemblies and blade fold cuff assemblies, 

including spares. 

(1) Perform Eddy Current inspection as follows: 

(a) Calibrate Eddy Current flaw detector (Phasec 3d or equivalent) (Figure 2): 

Parameter Setting

Probe drive Low 

Phase As required 

Differential gain X-axis -8db 

Filter High Pass DC 

Low Pass 30 Hz 

Gain 50 dB/As required 

Frequency 2 MHz 

1. Hold probe end perpendicular to surface of titanium reference standard in an 

area free of notches and balance/null the instrument. 

2. Raise probe slightly from surface of titanium reference standard and observe 

the direction of lift-off signal. 

3. Adjust phase control until lift-off signal moves to the left of the screen as the 

probe is raised from surface. 

4. Maintaining probe perpendicular to surface of titanium reference standard, scan 

probe tip across 0.040 inch (1mm) deep EDM notches and observe amplitude 

of indications on screen. 
S-76 ALERT ASB 76-65-67A 

SERVICE BULLETIN Revision A ▪ July 18/12 

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Section 3. ACCOMPLISHMENT INSTRUCTIONS (Continued) 

5. Adjust vertical\horizontal gain to produce a 40 percent vertical signal with 

approximately a 45 degree phase angle separate from lift off response. 

(b) Perform Eddy Current inspection: 

1. Place probe on spindle/cuff assembly or blade fold cuff assembly inspection 

area and press null button. Maintain the probe perpendicular to surface and 

scan inspection area (Figure 1, Sheets 1 and 2). 

a If no crack indications are found exceeding the response from the 0.020 

inch notch, proceed to section D. 

b Reject any crack indications exceeding the response from the 0.020 inch 

notch. Map out crack indications on cuff plate surface using a permanent 

marker (commercial grade or equivalent). Submit locations to Sikorsky 

Aircraft Corporation. Any repeatable crack indication is suspect and shall 

be investigated as follows: 

1. Lift main rotor blade off of droop stop and verify crack indications 

using visual, FPI and/or ultrasonic inspection as necessary. 

a. If cracks are verified, remove spindle/cuff assembly or blade 

fold cuff assembly from service. Refer to applicable 

maintenance manual. 

b. If visual, FPI and/or ultrasonic inspections do not confirm 

suspect cracks, contact Customer Service Engineering at 1-

800-WINGED-S or 1-203-416-4299 for further instruction. 

(2) Perform FPI inspection as follows: 

NOTE: • FPI shall be performed using only a Type 1, Method C, Level 3 process 

with Form D developer in accordance with ASTM E 1417. 

• All fluorescent penetrant, class 2 solvent and developer shall be from the 

same manufacturer. 

(a) Brush or swab fluorescent penetrant (ZL-27A, 985-P13, FP-95A or equivalent) on 

inspection area (Figure 1, Sheets 1 and 2). 

(b) After fluorescent penetrant dwell period, remove surplus fluorescent penetrant using 

a clean, low-lint cloth (A-A-59323 or equivalent), pressing firmly and wiping in one 

direction. Perform fluorescent penetrant removal under black light to ensure 

adequate removal but not over-removal. 

NOTE: Do not apply the class 2 solvent directly to NDI inspection area and do not 

allow solvent to flood or pool. 

(c) Use a clean, low-lint cloth (A-A-59323 or equivalent) dampened with class 2 solvent 

(SKC-S 9PR50, E-59 or equivalent) to perform a final wipe. Observe cleaned area 

under black light to evaluate penetrant removal step. 
ASB 76-65-67A S-76 ALERT

Revision A ▪ July 18/12 SERVICE BULLETIN

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Section 3. ACCOMPLISHMENT INSTRUCTIONS (Continued) 

NOTE: Developer shall be applied as a uniform thin coating over entire surface to 

be inspected. If developer coating thickness is too heavy such that surface 

is completely masked, the area shall be cleaned and reprocessed. Minimum 

and maximum development times are 10 minutes to one hour respectively. 

(d) Apply non-aqueous developer (ZP-9F, 9D1B, D-70 or equivalent) by spraying. The 

developer container shall be agitated vigorously prior to and during application. 

NOTE: Make sure the inspection area is not exposed to ambient white light for FPI 

procedure. 

(e) Conduct inspection with less than two foot-candles (20 lux) of ambient white light. 

1. If no crack indications are found proceed to step D. 

2. Map out crack indications on cuff plate surface using a permanent marker 

(commercial grade or equivalent). Submit locations to Sikorsky Aircraft 

Corporation. Any crack indication is suspect and shall be investigated as 

follows: 

1. Lift main rotor blade off of droop stop and verify crack indications using 

visual, Eddy Current and/or ultrasonic inspection as necessary. 

a. If cracks are verified, remove spindle/cuff assembly or blade fold cuff 

assembly from service. Refer to applicable maintenance manual. 

b. If visual, Eddy Current and/or ultrasonic inspections do not confirm 

suspect cracks, contact Customer Service Engineering at 1-800-

WINGED-S or 1-203-416-4299 for further instruction. 

(3) Perform ultrasonic inspection as follows: 

(a) Calibrate flaw detector (Olympus or equivalent): 

Parameter Setting

Pulse Echo Pulse Echo 

Frequency 10 MHz 

Range 2 inch 

Delay As necessary 

Gain Corner reflector to 100% 

Velocity 0.1207 in/μS 

Reject Off 

1. Using a two inch range with 0.1207 in/μS velocity, set search unit index point at 

“Zero” onscreen. 
S-76 ALERT ASB 76-65-67A 

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Section 3. ACCOMPLISHMENT INSTRUCTIONS (Continued) 

2. Maximize corner reflector and adjust gain for 100% full screen height using 

inside corner (Figure 3). 

(b) Perform ultrasonic inspection: 

1. Add 12 dB to calibration sensitivity. Back reflection monitoring is set to N/A. 

2. Scan inspection area in all directions (Figure 1, Sheets 1 and 2). 

a If no crack indications are found proceed to section D. 

b Map out crack indications on cuff plate surface using a permanent marker 

(commercial grade or equivalent). Submit locations to Sikorsky Aircraft 

Corporation. Any crack indication is suspect and shall be investigated as 

follows: 

1. Lift main rotor blade off of droop stop and verify crack indication 

using visual, Eddy Current and/or FPI inspections as necessary. 

a. If cracks are verified, remove spindle/cuff assembly or blade 

fold cuff assembly from service. Refer to applicable 

maintenance manual. 

b. If visual, Eddy Current and/or FPI inspection do not confirm 

suspect cracks, contact Customer Service Engineering at 1-

800-WINGED-S or 1-203-416-4299 for further instruction. 

C. Perform one-time visual inspection on spindle/cuff assemblies or blade fold cuff assemblies with 

less than 1900 flight hours as follows: 

(1) Using 5x or 10x magnifying glass (or equivalent), inspect white paint application area for 

cracks. 

(a) If cracks are found, remove spindle assembly or blade fold cuff assembly from 

service. Reference applicable maintenance manual. Contact Customer Service 

Engineering at 1-800-WINGED-S or 1-203-416-4299 and provide location of crack 

and spindle assembly or blade fold cuff assembly operating time. 

(b) If no cracks are found, proceed to section D. 

D. Apply white paint (Krylon® 51501 Gloss White, Plasti-Kote® 1109 Gloss White, Krylon Industrial 

Tough Coat, or an equivalent acrylic enamel gloss white paint) as follows: 

(1) If an FPI was performed thoroughly clean inspected area using isopropyl alcohol and a 

clean, low-lint cloth prior to application of white paint. 

(2) Mask white paint application area with masking tape (commercial grade or equivalent) 

(Figure 4, Sheets 1 and 2). 
ASB 76-65-67A S-76 ALERT

Revision A ▪ July 18/12 SERVICE BULLETIN

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Section 3. ACCOMPLISHMENT INSTRUCTIONS (Continued) 

(3) Apply white paint to masked area (Figure 4, Sheets 1 and 2). Let paint dry at room 

temperature for one hour minimum. 

(4) Remove masking tape. 

E. Return helicopter to service. 

F. 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. 
S-76 ALERT ASB 76-65-67A 

SERVICE BULLETIN Revision A ▪ July 18/12 

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Section 3. ACCOMPLISHMENT INSTRUCTIONS (Continued) 

NDI INSPECTION AREAS (SPINDLE/CUFF ASSEMBLY) 

FIGURE 1, SHEET 1 OF 2 

NDI INSPECTION AREA - 4 PLACES

UPPER AND LOWER PLATES,

SA

TD2708A

BOTH LEADING AND TRAILING EDGES

NDI INSPECTION AREA - 2 PLACES

UPPER AND LOWER PLATES

NOTE

BLADE NOT SHOWN FOR CLARITY.
ASB 76-65-67A S-76 ALERT

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Section 3. ACCOMPLISHMENT INSTRUCTIONS (Continued) 

NDI INSPECTION AREAS (BLADE FOLD CUFF ASSEMBLY) 

FIGURE 1, SHEET 2 OF 2 

NDI INSPECTION AREA - 4 PLACES

UPPER AND LOWER PLATES,

BOTH LEADING AND TRAILING EDGES

NDI INSPECTION AREA - 2 PLACES

UPPER AND LOWER PLATES NOTE

BLADE NOT SHOWN FOR CLARITY. SA

TD2788_1
S-76 ALERT ASB 76-65-67A 

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Section 3. ACCOMPLISHMENT INSTRUCTIONS (Continued) 

EDDY CURRENT INSPECTION METHOD 

FIGURE 2 

SA

XXxxxxPP TD2739
ASB 76-65-67A S-76 ALERT

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Section 3. ACCOMPLISHMENT INSTRUCTIONS (Continued) 

ULTRASONIC INSPECTION METHOD 

FIGURE 3 

SA

TD2378

LOWER

PLATE

PROBE PLACED AT

INSIDE CORNER OF

LOWER PLATE

SENSITIVITY SET TO 100%

FULL SCREEN HEIGHT
S-76 ALERT ASB 76-65-67A 

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Section 3. ACCOMPLISHMENT INSTRUCTIONS (Continued) 

WHITE PAINT APPLICATION AREA (SPINDLE/CUFF ASSEMBLY) 

FIGURE 4, SHEET 1 OF 2 

WHITE PAINT

APPLICATION AREA

WHITE PAINT

APPLICATION

AREA

LEADING EDGE OF LOWER CUFF PLATE ONLY

SA

TD2708

NOTE

BLADE NOT SHOWN FOR CLARITY.
ASB 76-65-67A S-76 ALERT

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Section 3. ACCOMPLISHMENT INSTRUCTIONS (Continued) 

WHITE PAINT APPLICATION AREA (BLADE FOLD CUFF ASSEMBLY) 

FIGURE 4, SHEET 2 OF 2 

WHITE PAINT APPLICATION AREA

NOTE

BLADE NOT SHOWN FOR CLARITY. SA

TD2788_2

WHITE PAINT APPLICATION AREA

LEADING EDGE OF LOWER CUFF PLATE ONLY
(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. 

If you have internet access, you may go to www.sikorsky.com to record your compliance. 

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 THE FOLLOWING SERIAL NUMBERS 

 ___________ ___________ ___________ ___________ ___________ ___________ 

 ___________ ___________ ___________ ___________ ___________ ___________ 

No. 76-65-67A 

ROTORS – Spindle Assemblies – One-Time Non-Destructive Inspection (NDI) of 

Spindle/Cuff Assembly and Application of White Paint to Enhance Existing 

Inspection Procedure 
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