1. PLANNING INFORMATION A. Effectivity All S-92A model helicopters with upper housing assembly part number 92351-15110-042/- 043/-044/-045/-046 at the time of the issue date of this Alert Service Bulletin (ASB). NOTE: • Upper housing assembly with part number 92351-15110-042/-043/-044/-045/-046

is a component of main gearbox assembly 92351-15100-042/-043/-044. • This ASB does not apply to main module, main gearbox assembly 92351-15100- 045 with Phase III housings. B. Purpose To provide instructions to implement a recurring NDI of the main gearbox assembly mounting foot ribs. C. Description NOTE: Eddy Current and fluorescent penetrant inspection are acceptable alternates to

each other. A review of the helicopter logbook is conducted to determine upper housing assembly flight hours. Fairings and engine air inlet assemblies are opened/removed and inspection area cleaned. On left, right and forward mounting feet, each foot rib is inspected for cracks using NDI (Eddy Current or Fluorescent Penetrant). If cracks are found, Sikorsky Aircraft Corporation is notified. If no cracks are found, helicopter is returned to service. 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INFORMATION WHICH IS PROPRIETARY, IS THE PROPERTY OF SIKORSKY AIRCRAFT CORPORATION AND/OR ITS SUBSIDIARIES, IS AN UNPUBLISHED WORK PROTECTED UNDER APPLICABLE COPYRIGHT LAWS, AND IS DELIVERED ON THE EXPRESS CONDITION THAT IT IS NOT TO BE USED, DISCLOSED, REPRODUCED, IN WHOLE OR IN PART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 AUTHORIZATION OF EITHER THE DEPARTMENT OF STATE OR THE DEPARTMENT OF COMMERCE PRIOR TO EXPORT. EXPORT INCLUDES DISCLOSURE AND OR ACCESS TO COMMODITIES, TECHNICAL DATA OR SOFTWARE BY FOREIGN NATIONALS WHETHER LOCATED IN THE UNITED STATES OR ABROAD. THIS REQUIREMENT APPLIES EQUALLY TO FOREIGN NATIONAL EMPLOYEES OF U.S. COMPANIES AND THEIR FOREIGN SUBSIDIARIES. No. 92-63-025ASubject: ROTOR DRIVES - Main Module Assembly - Main Gearbox Assembly - One-Time NonDestructive Inspection (NDI) at Mounting Foot Ribs for Cracks

May 11/11 Page 1 of 19 63-20-01 Revision A - May 12/11D. Compliance

Compliance is essential. The instructions outlined herein shall be accomplished as follows:(1) Upper housing assemblies with between 500 and 700 flight hours, comply within 50 flighthours from the issue date of this ASB. (2) Upper housing assemblies with over 700 flight hours, comply within 30 flight hours from the issue date of this ASB. E. Approval Inspection item. F. Manpower (Estimated) No. of Men No. of Hours *Man-Hours Eddy Current Inspection of Main Gearbox Assembly Mounting Foot Ribs for Cracks 1 1.5 1.5

Fluorescent Penetrant Inspection of Main Gearbox Assembly Mounting Foot Ribs for Cracks 1 2.5 2.5

*Estimate does not include time required to prepare helicopter or return it to flight status. G. Material (1) Phasec 2200 Flaw Detector (or equivalent). (2) VM Products 202AF-6 Probe (or equivalent). H. Tooling (1) Non-metallic pick or probe (or equivalent). (2) Spray bottle (or equivalent). (3) Handheld blacklight source that produces a minimum of 1200W/cm _ at the examination surface. No. 92-63-025A ROTOR DRIVES - Main Module Assembly - Main Gearbox Assembly - One-Time Non-Destructive Inspection (NDI) at Mounting Foot Ribs for Cracks
1. PLANNING INFORMATION (Continued)

May 11/11 Page 2 63-20-01 Revision A - May 12/11(4) Soft bristled brush (or equivalent). (5) Permanent marker (or equivalent). (6) Personnel - ANST Level 2 or ISO 9712 Level 2 (or equivalent). I. Weight and Balance Not affected. J. Electrical Load Data Not changed. K. Software Load Data Not applicable. L. References (1) Maintenance Manual SA S92A-AMM-000, Chapter/Section 20-06-00-910-005. (2) Maintenance Manual SA S92A-AMM-000, Chapter/Section 54-40-01-900-001/-002. (3) Maintenance Manual SA S92A-AMM-000, Chapter/Section 54-40-02-900-001/-002. (4) Maintenance Manual SA S92A-AMM-000, Chapter/Section 71-60-01-900-001/-002. M. Publications Affected (1) Temporary Revision No. 5-86 against Airworthiness Limitations and Inspection Requirements Manual SA S92A-AWL-000 Task 5-20-00-200-004, Scheduled Maintenance Checks will be issued concurrently with this ASB. (2) Temporary Revision No. 63-32 against Maintenance Manual SA S92A-AMM-000 Chapter/ Section 63-20-01-210-001, Main Transmission Inspection/Serviceability Check will be issued concurrently with this ASB. N. Attachment None. No. 92-63-025A ROTOR DRIVES - Main Module Assembly - Main Gearbox Assembly - One-Time Non-Destructive Inspection (NDI) at Mounting Foot Ribs for Cracks
1. PLANNING INFORMATION (Continued)

May 11/11 Page 3 63-20-01 Revision A - May 12/11A. Basis for Material Data

Per helicopter. B. Bill of Material Qty Key Word Nomenclature Instructions/ Disposition 1 Magnesium Reference Block EWR213573-101 (7) C. Consumable Material 

## WARNING 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.
QTY KEY WORD NOMENCLATURE INSTRUCTIONS/ DISPOSITION AS REQ’D BRULIN CLEANER SD 1291 OR EQUIVALENT (1) AS REQ’D CLEAN, LOW-LINT CLOTH A-A-59323 OR EQUIVALENT (2) AS REQ’D FLUORESCENT PENETRANT

INSPECTION (FPI) KIT ZL-27A OR EQUIVALENT (3)(6) (ALTERNATE) 985-P13 OR EQUIVALENT (4)(6) (ALTERNATE) FP-95A OR EQUIVALENT (5)(6) AS REQ’D DEVELOPER ZP-9F OR EQUIVALENT (3)(6) (ALTERNATE) 9D1B OR EQUIVALENT (4)(6) No. 92-63-025A ROTOR DRIVES - Main Module Assembly - Main Gearbox Assembly - One-Time Non-Destructive Inspection (NDI) at Mounting Foot Ribs for Cracks
2. MATERIAL INFORMATION

May 11/11 Page 4 63-20-01 Revision A - May 12/11(ALTERNATE) D-70 OR EQUIVALENT (5)(6) AS REQ’D CLASS 2 SOLVENT SKC-S OR EQUIVALENT (3)(6) (ALTERNATE) 9PR50 OR EQUIVALENT (4)(6) (ALTERNATE) E-59 OR EQUIVALENT (5)(6) AS REQ’D TEFLON TAPE OML1005 OR EQUIVALENT (2)

(1) Manufactured by Brulin Corporation, Indianapolis, IN. Telephone Numbers: (317) 923-3211 or 800-776-7149; Website: http://www.brulin.com. (2) Procure from 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/pages/met_l_chekpag.html NOTE: All fluorescent penetrant, class 2 solvent and developer shall be from the same

manufacturer. (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) Parts are available at no cost. For part availability and lead time requirements contact your Customer Service Representative at Helicopter Support, Inc. (HSI). Submit a no-cost purchase order referencing this ASB number and the helicopter serial number(s) upon which these parts will be used. This will allow HSI and the operator to track shipment and receipt of the parts. Orders will be accepted by letter, telephone, facsimile (FAX), or HSI website: www.HSIUS.com. For prompt shipment, Reference address of each shipping destination. Direct your order to: No. 92-63-025A ROTOR DRIVES - Main Module Assembly - Main Gearbox Assembly - One-Time Non-Destructive Inspection (NDI) at Mounting Foot Ribs for Cracks
2. MATERIAL INFORMATION

May 11/11 Page 5 63-20-01 Revision A - May 12/11HELICOPTER SUPPORT INC. 124 Quarry Road P.O. Box 11068 Trumbull, Connecticut 06611, U.S.A. Attn: Customer Service FAX: (203) 416-4291 Telephone: (203) 416-4000 HSI website: www.HSIUS.com 3. ACCOMPLISHMENT INSTRUCTIONS A. Review helicopter records to determine upper housing assembly total flight hours: (1) If upper housing assembly total flight hours are more than 500 but less than 700, proceed to section 3.B and perform the NDI within 50 flight hours of release date of this ASB. (2) If upper housing assembly total flight hours are more than 700, proceed to section 3.B and perform the NDI within 30 flight hours of release date of this ASB. B. Prepare helicopter for maintenance: (1) Turn off all electrical and hydraulic power. 

## WARNING TO PREVENT ELECTRICAL SHOCK OF PERSONNEL, MAKE

SURE TO DEENERGIZE ELECTRICAL POWER. (2) Deenergize all electrical power. 

## WARNING TO PREVENT INJURY OF PERSONNEL, MAKE SURE TO

DEENERGIZE HYDRAULIC POWER. (3) Deenergize all hydraulic power. (4) Gain direct visual access to all main gearbox foot rib areas by removing the following: (a) Remove LH and RH lower covers. Refer to Maintenance Manual SA S92A-AMM-000, Chapter/Section 54-40-02-900-001. (b) Remove center cover. Refer to Maintenance Manual SA S92A-AMM-000, Chapter/ Section 54-40-01-900-001. (c) Remove No. 1 and No. 2 engine air inlet assembly. Refer to Maintenance Manual SA S92A-AMM-000, Chapter/Section 71-60-01-900-001. No. 92-63-025A ROTOR DRIVES - Main Module Assembly - Main Gearbox Assembly - One-Time Non-Destructive Inspection (NDI) at Mounting Foot Ribs for Cracks
2. MATERIAL INFORMATION

May 11/11 Page 6 63-20-01 Revision A - May 12/11C. Clean inspection areas: NOTE: • Do not remove sealant around mounting foot pads and mounting bolt heads. • Do not use abrasive material to clean the inspection area. (1) Remove loose or flaking paint. (2) Using clean, low-lint cloth (A-A-59323 or equivalent), and Brulin cleaner (SD 1291 or equivalent), clean inspection areas. (3) Using a soft bristle brush (or equivalent), clear any remaining dirt or debris from inspection areas. If paint is flaked or chipped, use brush bristles or non-metallic pick or probe (or equivalent) to remove flakes. D. Perform Eddy Current inspection: NOTE: • The person performing the NDI must be an ANST Level 2 or ISO 9712 Level 2 (or

equivalent) and cannot be the same person who performs the recurring 10-hour visual inspection. • Eddy Current and fluorescent penetrant inspection are acceptable alternates to each other. Equipment for Inspection:

Key Word Nomenclature Qty Flaw Detector Phasec 2200 (or equivalent) 1 Probe VM products 202AF-6 (or equivalent) 1 (1) Calibration of Phasec 2200

Parameter Setting Probe Drive Low Filter High Pass DC Frequency 250 KHz Low Pass 30 Hz Phase 210 deg/As required Null Pos. V-pos 10% H-pos 90% No. 92-63-025A ROTOR DRIVES - Main Module Assembly - Main Gearbox Assembly - One-Time Non-Destructive Inspection (NDI) at Mounting Foot Ribs for Cracks
3. ACCOMPLISHMENT INSTRUCTIONS (Continued)

May 11/11 Page 7 63-20-01 Revision A - May 12/11Parameter Setting X:Y/H:V/ Differential Gain x-6dB
Gain As required (a) Place 0.2 mm of Teflon tape (OML1005 or equivalent) over the notches of the magnesium reference standard (EWR213573-101) to simulate the lift off from the paint and Rockhard coating. (b) Hold probe end perpendicular to surface of the magnesium reference standard (Figure 2) in a flat area away from the calibration notch and BALANCE (NULL) the instrument placing the 9 dot9 approximately one screen division vertically from the bottom of the screen and two screen divisions horizontally from the right side of the screen. See Figure 1. (c) Raise probe slightly from the surface of the reference standard and observe the direction of the lift-off signal. (d) Adjust the phase control until the lift-off signal moves to the left of the screen as the probe is raised from the surface. See Figure 1. (e) Maintaining the probe perpendicular to the surface of the reference standard (see Figure 2), scan the probe tip across the 0.008 inch (0.2 mm), 0.020 inch (0.5 mm) and 0.040 inch (1 mm) deep EDM notches and observe the amplitude of the indications on the screen. NOTE: In Figure 2, a = 0.008 inch (0.2 mm), b = 0.020 inch (0.5 mm) and c = 0.040

inch (1 mm). (f) Adjust gain until vertical amplitude of signal from 0.040 inch (1 mm) EDM notch is at least 2 vertical screen divisions on the CRT screen. See Figure 1. (2) Inspection procedure: NOTE: • Inspection to be performed on right, left and forward mounting feet, on all rib faces. See Figures 3 through 6. • When inspecting 92351-15110-042 housing, make sure all three ribs of LH and RH mounting feet are inspected. See Figure 6. (a) Place the probe at bottom of rib face and balance instrument. No. 92-63-025A ROTOR DRIVES - Main Module Assembly - Main Gearbox Assembly - One-Time Non-Destructive Inspection (NDI) at Mounting Foot Ribs for Cracks
3. ACCOMPLISHMENT INSTRUCTIONS (Continued)

May 11/11 Page 8 63-20-01 Revision A - May 12/11(b) Inspect surface area of each rib face as shown in Figures 3 through 6. Starting approximately 0.2 inches (5 mm) from bottom of foot, scan upwards to within 0.5 inches (12mm) of servo pad bracket. Scan surface area of rib as shown in Figures 3 through 6, taking care to avoid edges. Make sure probe is perpendicular to surface throughout the scan. (c) Any repeatable Eddy Current response equal to or greater than that of the 0.020 inch (0.5 mm) deep notch response from the magnesium reference standard is a rejectable indication. (d) All rejectable Eddy Current indications shall be mapped out on the part surface with a permanent marker. (e) If rejectable indication is found remove and replace main gearbox assembly. Proceed to section 3.F. (f) If no rejectable Eddy Current indications are found proceed to section 3.F. E. Fluorescent penetrant inspection (FPI): NOTE: • The person performing the NDI must be an ANST Level 2 or ISO 9712 Level 2 (or

equivalent) and cannot be the same person who performs the recurring 10-hour visual inspection. • Eddy Current and fluorescent penetrant inspection are acceptable alternates to each other. • Inspection to be performed on right, left and forward mounting feet on all rib faces. See Figures 3 through 6. • FPI shall be performed using only a Type 1, Method C, Level 3 process with Form D developer in accordance with ASTM E 1417 and AMS 2647. • All fluorescent penetrant, class 2 solvent and developer shall be from the same manufacturer. • When inspecting 92351-15110-042 housing, make sure all three ribs of LH and RH mounting feet are inspected. See Figure 6. (1) Clean inspection areas using a clean, low-lint cloth (A-A-59323 or equivalent) moistened with class 2 solvent (SKC-S, 9PR50, E-59 or equivalent) and allow area to dry. NOTE: The fluorescent penetrant dwell period shall be a minimum of 20 minutes. (2) Brush or swab fluorescent penetrant (ZL-27A, 985-P13, FP-95A or equivalent) on outboard face of rib. No. 92-63-025A ROTOR DRIVES - Main Module Assembly - Main Gearbox Assembly - One-Time Non-Destructive Inspection (NDI) at Mounting Foot Ribs for Cracks
3. ACCOMPLISHMENT INSTRUCTIONS (Continued)

May 11/11 Page 9 63-20-01 Revision A - May 12/11(3) 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 the part and do not allow solvent to flood or pool. (4) 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. 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. (5) Non-aqueous developer (ZP-9F, 9D1B, D-70 or equivalent) shall be applied by spraying. The developer container shall be agitated vigorously prior to and during application. NOTE: Make sure the inspection area is covered from ambient white light for FPI

procedure. (a) Inspection will be conducted in an area with less than two foot-candles (20 lux) of ambient white light. (6) If cracks are found remove and replace main gearbox assembly. Proceed to section 3.F. (7) If no cracks are found proceed to section 3.F. F. Reinstallation of Covers:

CAUTION PENETRANT MATERIALS LEFT ON A PART WILL ATTRACT

MOISTURE AND MAY CAUSE CORROSION. PENETRANT AND DEVELOPER MATERIALS SHALL BE THOROUGHLY CLEANED FROM THE PART SURFACE AFTER THE COMPLETION OF INSPECTION. (1) If an FPI was performed thoroughly clean inspected area. Refer to Maintenance Manual SA S92A-AMM-000, Chapter/Section 20-06-00-910-005, Section 5, step D, removal of Penetrant. (2) Install covers, panels and/or components previously removed:(a) No. 1 and No. 2 engine air inlet assemblies. Refer to Maintenance Manual SA S92AAMM-000, Chapter/Section 71-60-01-900-002. No. 92-63-025A ROTOR DRIVES - Main Module Assembly - Main Gearbox Assembly - One-Time Non-Destructive Inspection (NDI) at Mounting Foot Ribs for Cracks
3. ACCOMPLISHMENT INSTRUCTIONS (Continued)

May 11/11 Page 10 63-20-01 Revision A - May 12/11(b) LH and RH lower covers. Refer to Maintenance Manual SA S92A-AMM-000, Chapter/ Section 54-40-02-900-002. (c) Center Cover. Refer to Maintenance Manual SA S92A-AMM-000, Chapter/Section 54-40- 01-900-002. (3) Make sure area is clean and free of foreign objects. (4) Return helicopter to service. No. 92-63-025A ROTOR DRIVES - Main Module Assembly - Main Gearbox Assembly - One-Time Non-Destructive Inspection (NDI) at Mounting Foot Ribs for Cracks
3. ACCOMPLISHMENT INSTRUCTIONS (Continued)

May 11/11 Page 11 63-20-01 Revision A - May 12/11G. Record of Compliance Electronically

NOTE: • Record using one of the following compliance methods: • Use section G. as a guide when completing the Record of Compliance Electronically on Sikorsky360 website. • Use section H. when completing the Record of Compliance Manually. Make an appropriate logbook entry to show compliance with this ASB. (1) Log onto www.Sikorsky360.com (2) Click on E-Notifications. NOTE: Please read the Export Control Statement before agreeing to the terms and

conditions. (3) Agree to the Export Control Statement. (4) Click on E-Notes Compliance. (5) To perform the E-Notification Compliance, select Search by DOCUMENT NUMBER tab and follow the steps 1 through 6 in Figure 7. (6) Once search is complete, select COMPLY next to the helicopter that is in compliance and follow step 7 through 11 in Figure 7. H. Record of Compliance Manually (1) Make an appropriate logbook entry to show compliance with this ASB. (2) Upon compliance with this Alert Service Bulletin, complete attached ALERT SERVICE BULLETIN COMPLIANCE RECORD CARD and return it to Sikorsky Aircraft Corporation. No. 92-63-025A ROTOR DRIVES - Main Module Assembly - Main Gearbox Assembly - One-Time Non-Destructive Inspection (NDI) at Mounting Foot Ribs for Cracks
3. ACCOMPLISHMENT INSTRUCTIONS (Continued)

May 11/11 Page 12 63-20-01 Revision A - May 12/11SA XXxxxxPP TD2526_5 LIFTOFF 

# A

B C

EDDY CURRENT RESULTS ON THE CRT SCREEN FOR THE MAGNESIUM REFERENCE STANDARD FIGURE 1 No. 92-63-025A

May 11/11 Page 13 63-20-01 Revision A - May 12/11SA XXxxxxPP TD2526_4 C B A

0.020" 0.008"

0.040"

MAGNESIUM REFERENCE STANDARD (EWR213573-101) FIGURE 2 No. 92-63-025A

May 11/11 Page 14 63-20-01 Revision A - May 12/11SA XXxxxxPP TD2526_1 INSPECTION ZONE INSPECTION ZONE

INSPECTION ZONES ON RIGHT MOUNTING FOOT RIB FIGURE 3 No. 92-63-025A

May 11/11 Page 15 63-20-01 Revision A - May 12/11SA XXxxxxPP TD2526_2 INSPECTION ZONE INSPECTION ZONE

INSPECTION ZONES ON LEFT MOUNTING FOOT RIB FIGURE 4 No. 92-63-025A

May 11/11 Page 16 63-20-01 Revision A - May 12/11SA XXxxxxPP TD2526_3 INSPECTION ZONE INSPECTION ZONE

INSPECTION ZONES ON FRONT MOUNTING FOOT RIB FIGURE 5 No. 92-63-025A

May 11/11 Page 17 63-20-01 Revision A - May 12/11SA XXxxxxPP TD2526_6 INSPECTION ZONE INSPECTION ZONE INSPECTION ZONE

PHASE 0 HOUSING (92351-15110-042) INSPECTION ZONES (LH AND RH MOUNTING FEET ONLY) FIGURE 6 No. 92-63-025A

May 11/11 Page 18 63-20-01 Revision A - May 12/11TD2393



### USE AS A GUIDE, INFORMA TION WILL V

ARY

E-No tification s - Comp liance S ubmi ssion Type Doc ument N umber Subj ect
Owne r/O per ato r Submi tted By Submi ssio n Da te Aut hor ize d By Comp liance Date Comp liance Status

Seri al Number

Submit Cancel ASB/SB 92-53 -00 4A FUSE LAGE - T

ail Rotor Py lon , O ne- Tim e Rep laceme nt o f; and Joi ningTai lco ne - I nst allation of Do ubler to Rei nforc e Af t S hea r D eckWe b As sem bly
ANYHe lic opters ANYUse r Feb 13, 2011
*

Select the air crafttha t t his com plia nce will ap ply to. HINT : H old t he CTRL bu tt on t o se lect mu lti ple item s.

* Sel ect *

920018 920024 920030 920034 920036 *
11 SELEC T S UBMIT SELEC T D OC STATUS9 ENTER COM PLIAN CE DAT E 8 ENT ER NAME HERE 7

SELECT SER IAL N UMBE R 1 0 User Guide Add New Aircraft E-Notes Search E-Notifications Compliance

Sear ch by DOCUM ENT NUM BER

S-92A E-Notificati on T

ype* SEL ECTALL - C LEAR ALL Mode l *

Load Li st ASB/SB 92-20-002A ASB/SB 92-21-001 ASB/SB 92-21-002 ASB/SB 92-22-001 ASB/SB 92-22-002A ASB/SB 92-24-001 ASB/SB 92-24-002 ASB/SB 92-25-001A ASB/SB 92-25-002A ASB/SB 92-25-003 ASB/SB 92-25-004 Docu men t N umb er * Comp liance Status* SEL ECTALL - C LEAR ALL Compli ed Not Applica ble Open Wai ting Part s

Search * Req uir ed To sea rch e-not ification comp liance by d ocument num ber: Select E-Noti fica tion Typ e(s ) an d Mode l(s) an d c lic k th e “ Load List ” b utton, t hen Select Documen t Nlumber(s ) an d Comp lianc e S tatus(e s) an d c lic k th e “ Sea rch” but ton
. HINT : Ho ld the CT RL but ton to select mul tip le item s. Clear ASB/SB - Ale rt Service Bulletin / Service Bulletin CSN - Custome r Se rvi ce Notice Sea rch by AIR CRAFT

SELECTLOAD L IST3 SELEC T D OC NUMBER 4

SELECTOP EN 5
2 SELECT MODEL 1 SE LECT DOC TYPE

6 SE LECT SEARCH
STEPS 1 THROU GH 6

STEPS 7 THROU GH 11
GUIDE FOR E-NOTIFICATION COMPLIANCE

FIGURE 7 No. 92-63-025A

May 11/11 Page 19 63-20-01 Revision A - May 12/11

# (860) 998-7565

Upon COMPLIANCE with the attached ASB , Sikorsky requests your cooperation in completing and returning this ENTIRE P AGE by MAIL , FAX , or scan & EMAI L
. ATTENTION: SAS PRODUCT SAFETY MANAGER S IKORSKY AEROSPACE SERVICES 

# EMAIL ADDRESS: GPSIKSASProductSafet@utc.com

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## Or scan andemail to: EMAIL ADD RES S: GPSIKSASProductSafet@utc.com