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SIKORSKY AIRCRAFT CORPORATION AND/OR ITS SUBSIDIARIES, IS AN UNPUBLISHED WORK PROTECTED UNDER APPLICABLE COPYRIGHT LAWS, AND IS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. 92-63-025A

Subject: 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 12/11
D. 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.

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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.

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Inspection (NDI) at Mounting Foot Ribs for Cracks

1. PLANNING INFORMATION (Continued)

May 11/11 Page 3 63-20-01

Revision A - May 12/11
A. 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

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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 12/11
HELICOPTER 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.

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2. MATERIAL INFORMATION

May 11/11 Page 6 63-20-01

Revision A - May 12/11
C. 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

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Inspection (NDI) at Mounting Foot Ribs for Cracks

3. ACCOMPLISHMENT INSTRUCTIONS (Continued)

May 11/11 Page 7 63-20-01

Revision A - May 12/11
Parameter 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 9dot9 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

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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

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Inspection (NDI) at Mounting Foot Ribs for Cracks

3. ACCOMPLISHMENT INSTRUCTIONS (Continued)

May 11/11 Page 11 63-20-01

Revision A - May 12/11
G. 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 12/11
SA

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 12/11
SA

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 12/11
SA

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 12/11
SA

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 12/11
SA

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 12/11
SA

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 12/11
TD2393

USE AS A GUIDE, INFORMATION WILL VARY

E-Notifications - Compliance Submission

Type

Document Number

Subject

Owner/Operator

Submitted By

Submission Date

Authorized By

Compliance Date

Compliance Status

Serial Number

Submit Cancel

ASB/SB

92-53-004A

FUSELAGE - Tail Rotor Pylon, One-Time Replacement of; and JoiningTailcone - Installation of Doubler to Reinforce Aft Shear Deck Web Assembly

ANY Helicopters

ANY User

Feb 13, 2011

*

Select the aircraft that this compliance will apply to.

HINT: Hold the CTRL button to select multiple items.

Select *

 *

920018

920024

920030

920034

920036 *

11 SELECT SUBMIT

SELECT DOC STATUS 9

ENTER COMPLIANCE DATE 8

ENTER NAME HERE 7

SELECT SERIAL NUMBER 10

User Guide Add New Aircraft E-Notifications E-Notes Search

Compliance

Search by DOCUMENT NUMBER

S-92A

E-Notification Type*

SELECT ALL - CLEAR ALL

Model*

Load List

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

Document Number* Compliance Status*

SELECT ALL - CLEAR ALL

Complied

Not Applicable

Open

Waiting Parts

Search

* Required

To search e-notification compliance by document number:

Select E-Notification Type(s) and Model(s) and click the “Load List” button, then

Select Document Nlumber(s) and Compliance Status(es) and click the “Search”

button.

HINT: Hold the CTRL button to select multiple items.

Clear

ASB/SB - Alert Service Bulletin / Service Bulletin

CSN - Customer Service Notice

Search by AIRCRAFT

SELECT LOAD LIST 3

SELECT DOC NUMBER 4

SELECT OPEN 5

2 SELECT MODEL

1 SELECT DOC TYPE

6 SELECT SEARCH 

STEPS 1 THROUGH 6

STEPS 7 THROUGH 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 PAGE by MAIL, FAX, or scan & EMAIL.

ATTENTION: SAS PRODUCT SAFETY MANAGER

 SIKORSKY AEROSPACE SERVICES

EMAIL ADDRESS: GPSIKSASProductSafet@utc.com

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Non-Destructive Inspection (NDI) at Mounting Foot Ribs for Cracks
BUSINESS REPLY MAIL

MAILSTOP: S328A

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Or scan and email to:

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