Page 1 of 1 June 21, 2011 TRANSMITTAL SHEET Subject: ALERT SERVICE BULLETIN NO. 92-53-00 4B – FUSELAGE – Tail Rotor Pylon, One-Time Replacement of; and Joining-Tailcone – Installation of Doubler to Reinforce Aft Shear Deck Web Assembly This page transmits Revision B to Alert Service Bulletin No. 92-53-004 dated February 22, 2010. Alert Service Bulletin No. 92-53-004B supersedes Al ert Service Bulletin No. 92-53-004A dated July 13, 2010. For operators who have already complied with the original release or Revision A and received a modified tail rotor pylon, review and revise the Aircraft Component Log Card and Component Maintenance Record with the log card requirement s outlined in the Accomplishment Instructions (Section E.) of this ASB. For operators who have not complied with this ASB in its entirety, comply with Revision B within the original compliance time specified in the original ASB, dated February 22, 2010. The text changed by this revision is indicated by a vertical line in the outer margin of the page. Illustration changes are indicated by a vertical line adjacent to the title.
Revision Feature: PLANNING INFORMATION Revised description to include creation of tail rotor pylon log card. MATERIAL INFORMATION Revised shipping information to include coordinating with your Customer Service Manager. Added alternate primer specification. ACCOMPLISHMENT INSTRUCTIONS Added new log card procedures for AAR to review and revise log cards for tail rotor pylons that have been previously modified by the orig inal ASB from an approved Sikorsky Aircraft repair station. Revised compliance procedures. FIGURES Added Figures 5 and 6 to show log cards. SIKORSKY AIRCRAFT Technical Directives Section1. PLANNING INFORMATION A. Effectivity S-92A model helicopters, serial numbers 920006 through 920124 with tail rotor pylon 92000-06102-041 installed. Component Tail Rotor Pylon Structure and Equipment Assembly, part number 92000-06102-041. B. Purpose To provide instructions to remove and replace an existing tail rotor pylon 92000-06102-041 with tail rotor pylon 92070-20058-042. Some helicopters have experienced cracks of the tail rotor pylon in the forward lower spar region, which resulted in replacement of tail rotor pylons in the field. Sikorsky has developed a modification kit to improve the tail rotor pylon fatigue strength. Several structural parts are replaced with titanium and/or steel parts to improve strength. Cold working of the fastener holes is performed to improve the fatigue life of the parts. A doubler is added internal to the tail cone to reinforce the aft shear deck web assembly. A revision to Chapter 4 is being issued that implements a new life limit of 8,223 hours for tail rotor pylons with the modification installed. Tail rotor pylons that are modified will have the new life limit time added to the current T/R pylon aircraft hours annotated on a newly created log card. Also, there is a change to Chapter 5 inspection intervals after a modified tail rotor pylon is installed. The inspection is changed to 250 hours from existing inspection intervals. 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. 92-53-004B Subject: FUSELAGE - Tail Rotor Pylon, One-Time Replacement of; and Joining-Tailcone -

Installation of Doubler to Reinforce Aft Shear Deck Web Assembly

February 22/10 Page 1 of 25 53-60-05 Revision B - June 21/11C. Description

The helicopter is prepared for maintenance. The tail rotor pylon (TRP) replacement is accomplished through a rotable pool exchange program. Helicopter Support Incorporated (HSI) will contact each operator to plan and schedule the shipping of a replacement tail rotor pylon. Pylons will be shipped based on the flight time on the TRP per the compliance intervals established within the Alert Service Bulletin (ASB). A total indicated run-out (TIR) check is performed on the tail rotor pylon drive shaft per the Aircraft Maintenance Manual (AMM). All dynamic components and customer furnished equipment are removed from the existing tail rotor pylon. The existing tail rotor pylon is removed from the helicopter per the AMM using a lifting sling or equivalent straps as determined by the operator. A log card is created for the tail rotor pylon per the instructions outlined herein. The replacement tail rotor pylon is removed from the container and installed per the AMM. All dynamic components and customer furnished equipment are reinstalled. The removed tail rotor pylon and tail rotor pylon fairings are shipped to AAR Aircraft Services per instructions outlined herein. The applicable harness assemblies inside the tailcone are removed to facilitate the installation of a doubler, which is installed inside the tailcone on the aft tunnel shear deck web to reinforce the web. The harness assembly clamping installations are rearranged to prevent chafing between the wiring and the flight control cables. A TIR check is performed on the tail rotor pylon drive shaft per the AMM. Ground checks, hover checks, and flight test procedures are performed as required per the AMM. Helicopter is returned service D. Compliance Compliance is essential. The rotable pool process to accomplish the tail rotor pylon replacement is scheduled as follows: • All 92000-06102-041 tail rotor pylons with 3750 hours or more shall be replaced within 12 months of the original release date of this ASB. • All 92000-06102-041 tail rotor pylons with 1500 to 3749 hours shall be replaced within 24 months of the original release date of this ASB. • All 92000-06102-041 tail rotor pylons shall be replaced within 3 years of the original release date of this ASB. E. Approval The change effected by this document is classified as Major, and is FAA approved in accordance with the applicable requirements of Federal Aviation Regulations FAR 29. This constitutes EASA approval under the terms of the current interim procedures for working with the European Community on airworthiness certification and continued airworthiness. The repair data provided in this document is automatically approved by ED Decision 2004/04/CF, as amended by ED Decision 2007/001/C. Reference to the ED Decisions mentioned above shall be made in the release documents issued by the EASA 145 approved organization, releasing the relevant EU registered helicopter or component to service. No. 92-53-004B FUSELAGE - Tail Rotor Pylon, One-Time Replacement of; and Joining-Tailcone - Installation of Doubler to Reinforce Aft Shear Deck Web Assembly
1. PLANNING INFORMATION (Continued)

February 22/10 Page 2 53-60-05 Revision B - June 21/11F. Manpower (Estimated) No. of Men No. of Hours *Man-Hours

Removal of Tail Rotor Pylon 2 20.00 40.00 Installation of Doubler 2 4.00 8.00 Installation of Replacement Tail Rotor Pylon 2 36.00 72.00
Total 60.00 120.00

*Estimate does not include time required to prepare helicopter, access work area(s), or return it to flight status. G. Material None. H. Tooling NOTE: • The Drive Shaft Run-out Tool (1) listed below consists of Installation Tools (2), (3),

and (4). Installation Tools (2), (3), and (4) listed above are detail parts of the Drive Shaft Run-out Tool (1) and can be used with a customer supplied dial indicator. • For information regarding the Drive Shaft Run-out Installation Tools, contact Helicopter Support Incorporated (HSI). Refer to Section 2. MATERIAL INFORMATION for HSI contact information. • For information regarding Lifting Sling (or equivalent) details and availability, contact HSI. Refer to Section 2. MATERIAL INFORMATION for contact information. (1) Drive shaft Run-out Tool, part number 92320-05000-012T046 or equivalent. (2) Installation Tool, part number 92320-05000-012T046-115 (DMYNO-78286-800) or equivalent. (3) Installation Tool, part number 92320-05000-012T046-129 (DMYNO-78286-801) or equivalent. (4) Installation Tool, part number 92320-05000-012T046-133 (DMYNO-78286-802) or equivalent. No. 92-53-004B FUSELAGE - Tail Rotor Pylon, One-Time Replacement of; and Joining-Tailcone - Installation of Doubler to Reinforce Aft Shear Deck Web Assembly
1. PLANNING INFORMATION (Continued)

February 22/10 Page 3 53-60-05 Revision B - June 21/11I. Weight and Balance

For structure and equipment assembly part number 92070-20058-042: +20.8 at station 688.50, moment +14.30 inch-pounds/1000. J. Electrical Load Data Not affected. K. Software Load Data Not applicable. L. References (1) Maintenance Manual, SA S92A-AMM-000, Chapter/Section 53-60-05-900-001. (2) Maintenance Manual, SA S92A-AMM-000, Chapter/Section 53-60-05-900-002. (3) Maintenance Manual, SA S92A-AMM-000, Chapter/Section 65-10-00-820-001. M. Publications Affected (1) Airworthiness Limitations & Inspection Requirements Manual, SA S92A-AWL-000, Chapter 4. (2) Airworthiness Limitations & Inspection Requirements Manual, SA S92A-AWL-000, Chapter 5. N. Attachment None. No. 92-53-004B FUSELAGE - Tail Rotor Pylon, One-Time Replacement of; and Joining-Tailcone - Installation of Doubler to Reinforce Aft Shear Deck Web Assembly
1. PLANNING INFORMATION (Continued)

February 22/10 Page 4 53-60-05 Revision B - June 21/11A. Basis for Material Data Per helicopter. B. Bill of Material
New Part No. Qty Key Word Old Part No. Instructions/ Disposition 92070-20058-042 1 Tail Rotor Pylon Structure and Equipment ASSY 92000-06102-041 (1)(2)(4)
92070-20087-011 1 Tail Rotor Pylon Joining INSTL M/K (2) consisting of: AN743Z13 1 Bracket MS20002C6 2 Washer MS20470AD4-9 2 Rivet MS20470AD4-5 MS20470AD5-9 28 Rivet MS20470AD5-6 MS20470AD6-9 3 Rivet (3) MS21250-06011 1 Bolt, Tension MS21250-06009 MS21250-06015 1 Bolt MS21250-06013 MS27039-1-08 2 Screw NAS1097AD3-9 1 Rivet (3) NAS1097AD4-9 2 Rivet (3) NAS1149F0663P 2 Washer, Flat SS5089-06 2 Nut 92070-20087-101 1 Doubler

(1) Tail rotor pylon is available at no cost through the rotable pool exchange program. HSI will schedule and provide each operator with a replacement tail rotor pylon. No. 92-53-004B FUSELAGE - Tail Rotor Pylon, One-Time Replacement of; and Joining-Tailcone - Installation of Doubler to Reinforce Aft Shear Deck Web Assembly

2. MATERIAL INFORMATION

February 22/10 Page 5 53-60-05 Revision B - June 21/11(2) For Tail Rotor Pylon Structure and Equipment Assembly and Tail Rotor Pylon Joining Installation Modification Kit availability and lead time requirements contact your Customer Service Representative at HSI. Submit a purchase order referencing this ASB number and the helicopter serial number(s) upon which the Tail Rotor Pylon Structure and Equipment Assembly and Tail Rotor Pylon Joining Installation Modification Kit will be used. This will allow HSI and the operator to track shipment and receipt of the Tail Rotor Pylon Structure and Equipment Assembly and Tail Rotor Pylon Joining Installation Modification Kit. Orders will be accepted by letter, telephone, or facsimile (FAX). For prompt shipment, reference address of each shipping destination. Direct your order to: HELICOPTER SUPPORT INC. 124 Quarry Road P.O. Box 111068, Trumbull, Connecticut 06611 U.S.A. Attn: Customer Service FAX: (203) 416-4000 HSI website: www.HSIUS.com NOTE: Shipping of tail rotor pylon cores to AAR Aircraft Services is essential for meeting the Compliance interval established herein. Tail rotor pylon cores are to be shipped to AAR Aircraft Services (unless otherwise directed by your Customer Service Manager) within 5 days after removal of the tail rotor pylon from the helicopter. For information regarding the tail rotor pylon replacement schedule and shipping, contact your Customer Service Manager. (3) Procure from local supply. (4) Removed tail rotor pylons and tail rotor pylon fairings are to be packaged into the original shipping container provided by shipped tail rotor pylons. Clearly mark the following address on the outside of the container and ship to:

AAR Aircraft Services 6611 South Meridian Avenue Oklahoma City, OK 73159-1118 Attn: Customer Service Telephone: (405) 681-3000 AAR website: www.aarcorp.com

No. 92-53-004B FUSELAGE - Tail Rotor Pylon, One-Time Replacement of; and Joining-Tailcone - Installation of Doubler to Reinforce Aft Shear Deck Web Assembly

2. MATERIAL INFORMATION

February 22/10 Page 6 53-60-05 Revision B - June 21/11C. 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 PART NO. INSTRUCTIONS/ DISPOSITION AS REQ’D CORROSION COATING ALODINE 600 OR EQUIVALENT (1) AS REQ’D ISOPROPYL ALCOHOL COMMERCIAL GRADE OR EQUIVALENT (1) AS REQ’D LOW-LINT CLOTH A-A-59323 OR EQUIVALENT (1) AS REQ’D SEALANT AMS 3265 TYPE 2 OR EQUIVALENT (1)AS REQ’D PRIMER MIL-PRF-85582 OR MIL-P23377 OR EQUIVALENT (1)

(1) Procure from local supply.For a listing of the additional consumables required, refer to Maintenance Manual, SA S92AAMM-000, Chapter/Section 53-60-05-900-002. D. Tools Required Ref: Maintenance Manual, SA S92A-AMM-000, Chapter/Section 53-60-05. 3. ACCOMPLISHMENT INSTRUCTIONS A. Remove existing tail rotor pylon (92000-06102-041) as follows: (1) Prepare helicopter for maintenance. (2) Turn off electrical and hydraulic power. No. 92-53-004B FUSELAGE - Tail Rotor Pylon, One-Time Replacement of; and Joining-Tailcone - Installation of Doubler to Reinforce Aft Shear Deck Web Assembly

2. MATERIAL INFORMATION

February 22/10 Page 7 53-60-05 Revision B - June 21/11(3) Perform TIR check of No. 4 and No. 5 tail drive shafts. Refer to Maintenance Manual, SA S92A-AMM-000, Chapter/Section 65-10-00-820-001. (4) Remove customer furnished equipment from tail rotor pylon (92000-06102-041) as required. Save for reuse. NOTE: • When removing the tail rotor pylon, save all mounting hardware for reuse

except for the washers and nuts in positions 3 and 18 (see Maintenance Manual, SA S92A-AMM-000, Chapter/Section 53-60-05-900-002; Tail Rotor Pylon Installation - Torque Sequence Figure 402). New, longer bolts for these locations have been provided in the kit due to the new radius blocks installed on the frame at station 664. • Alternate straps may be used as required to remove and replace the tail rotor pylon if lifting sling is unavailable.(5) Remove tail rotor pylon (92000-06102-041). Refer to Maintenance Manual, SA S92A-AMM000, Chapter/Section 53-60-05, Task No. 53-60-05-900-001. NOTE: Use Figure 5 as a guide when filling out the initial Log Card for the -041 tail

rotor pylon. (6) Fill out Log Card for Original Install tail rotor pylon (92000-06102-041) and attach to Original Install tail rotor pylon. (7) Ship Original Install tail rotor pylon (92000-06102-041) and tail rotor pylon fairings to AAR Aircraft Services (unless otherwise directed by your Customer Service Manager). Refer to section 2.B., MATERIAL INFORMATION section of this ASB for shipping information. B. Install doubler (92070-20087-101) on aft shear deck tunnel assembly (92204-05103-041 and - 045) as follows (Figures 1, 2, and 4): NOTE: The installation of doubler (92070-20087-101) is dependent upon the configuration of the aft shear deck tunnel assembly. • For helicopters with serial numbers 920083 through 920124, proceed to section C. to install doubler (92070-20087-101) on aft shear deck tunnel assembly (92204-05103- 043). • For helicopters with serial numbers 920006 through 920082, install doubler (92070- 20087-101) on aft shear deck tunnel assembly (92204-05103-041 and -045) using the following instructions. • The following instructions are performed using the tail rotor pylon joining installation modification kit 92070-20087-011. No. 92-53-004B FUSELAGE - Tail Rotor Pylon, One-Time Replacement of; and Joining-Tailcone - Installation of Doubler to Reinforce Aft Shear Deck Web Assembly
3. ACCOMPLISHMENT INSTRUCTIONS (Continued)

February 22/10 Page 8 53-60-05 Revision B - June 21/11(1) At station 654.00, waterline 245.00, right buttline 9.00, locate aft shear deck tunnel assembly (92204-05103). (2) If connected, disconnect electrical connectors P600 and P602 from electrical receptacles J600 and J602 to gain access to work area. (3) If installed, remove TCAS cables (500-92925-103) as required to gain access to work area. Save hardware for reuse. (4) Remove harness assemblies as required to gain access to work area. Note location of harness assemblies for reinstallation. Save hardware for reuse. (5) Visually inspect aft shear deck tunnel assembly (92204-05103) to determine the quantity of brackets (AN743Z13) installed (Figures 1 and 2): (a) If one bracket (AN743Z13) is installed on aft shear deck assembly tunnel assembly (92204-05103), proceed to step (9). (b) If two brackets (AN743Z13) are installed on aft shear deck assembly tunnel assembly (92204-05103), proceed to next step. (6) Remove two rivets (MS20470AD4-5) securing bracket (AN743Z13) to aft shear deck tunnel assembly (92204-05103). Remove brackets. Typical two places. (7) If required, install 2 rivets (NAS1097AD4-9) flush nearside to plug existing holes in aft shear deck tunnel assembly (92204-05103). Trim rivets as required. (8) Locate doubler (92070-20087-101). (9) If required, install rivet (NAS1097AD3-9) flush farside to plug pilot hole in doubler (92070- 20087-101). Trim rivet as required. Proceed to step (10). (10) Remove two rivets (MS20470AD4-5) securing bracket (AN743Z13) to aft shear deck tunnel assembly (92204-05103). Remove bracket. (11) Remove two rivets (MS20470AD5-6) from side web - aft tunnel assembly (92202-05134) common to aft shear deck tunnel assembly (92204-05103). (12) Using low-lint cloth (A-A-59323 or equivalent) moistened with isopropyl alcohol (commercial grade or equivalent), clean surfaces of aft shear deck tunnel assembly (92204-05103) work area. (13) Remove two rivets (MS20470AD5-6) from side web - aft tunnel assembly (92202-05134) common to aft shear deck tunnel assembly (92204-05103). No. 92-53-004B FUSELAGE - Tail Rotor Pylon, One-Time Replacement of; and Joining-Tailcone - Installation of Doubler to Reinforce Aft Shear Deck Web Assembly
3. ACCOMPLISHMENT INSTRUCTIONS (Continued)

February 22/10 Page 9 53-60-05 Revision B - June 21/11(14) Using low-lint cloth (A-A-59323 or equivalent) moistened with isopropyl alcohol (commercial grade or equivalent), clean mating surfaces of doubler (92070-20087-101) and aft shear deck tunnel assembly (92204-05103). (15) Locate doubler (92070-20087-101). (16) Temporarily secure doubler (92070-20087-101) to mounting location of aft shear deck tunnel assembly (92204-05103). NOTE: Prior to performing the following steps, pay particular attention to the tab on the

doubler for clearance and line up lightning hole in aft shear deck tunnel assembly for orientation. (17) Mark layout of three 0.161-inch diameter holes on doubler (92070-20087-101) using dimensions provided in Figures 1 and 2. (18) Using pilot holes on doubler (92070-20087-101) as a guide, perform transfer drilling of fastener holes from doubler to aft shear deck tunnel assembly (92204-05103) as follows: NOTE: • For aft shear deck assemblies that were equipped with one AN743Z13 bracket,

perform step (a). • For aft shear deck assemblies that were equipped with two AN743Z13 brackets, perform steps (b) and (c). (a) Using drill bit No. 20, transfer drill 22 0.161-inch diameter holes from doubler (92070- 20087-101) to aft shear deck tunnel assembly (92204-05103). Proceed to step (19). (b) Using drill bit No. 20, transfer drill 18 0.161-inch diameter holes from doubler (92070- 20087-101) to aft shear deck tunnel assembly (92204-05103). (c) Using drill bit No. 11, transfer drill three 0.191-inch diameter holes from doubler (92070- 20087-101) to aft shear deck tunnel assembly (92204-05103). Proceed to step (19). (19) Using drill bit No. 20, transfer drill two 0.161-inch diameter holes from aft shear deck tunnel assembly (92204-05103) and side web - aft tunnel assembly (92202-05134) to doubler (92070-20087-101). (20) Using drill bit No. 20, drill three (marked) 0.161-inch diameter holes through doubler (92070-20087-101) and aft shear deck tunnel assembly (92204-05103). (21) Using drill bit No. 30, transfer drill two 0.128-inch diameter holes from bracket (AN743Z13) and aft shear deck tunnel assembly (92204-05103) to doubler (92070-20087-101). (22) Disassemble parts and deburr fastener holes as required. No. 92-53-004B FUSELAGE - Tail Rotor Pylon, One-Time Replacement of; and Joining-Tailcone - Installation of Doubler to Reinforce Aft Shear Deck Web Assembly
3. ACCOMPLISHMENT INSTRUCTIONS (Continued)

February 22/10 Page 10 53-60-05 Revision B - June 21/11(23) Using low-lint cloth (A-A-59323 or equivalent) moistened with isopropyl alcohol (commercial grade or equivalent), clean mating surfaces of doubler (92070-20087-101), bracket (AN743Z13), and aft shear deck tunnel assembly (92204-05103). (24) Apply primer (MIL-PRF-85582 or MIL-P-23377 or equivalent) as required. (25) Apply sealant (AMS 3265 Type 2 or equivalent) to mating surfaces of doubler (92070- 20087-101), aft shear deck tunnel assembly (92204-05103) and side web - aft tunnel assembly (92202-05134). (26) Install doubler (92070-20087-101) to aft shear deck tunnel assembly (92204-05103) as follows: NOTE: • For aft shear deck assemblies that were equipped with two AN743Z13 brackets,

perform step (a). • For aft shear deck assemblies that were equipped with one AN743Z13 bracket, perform step (b). (a) Install doubler (92070-20087-101) to aft shear deck tunnel assembly (92204-05103-041 or -045) and side web - aft tunnel assembly (92202-05134) using 23 rivets (MS20470AD5-9) and 3 rivets (MS20470AD6-9). Trim rivets as required. (b) Install doubler (92070-20087-101) to aft shear deck tunnel assembly (92204-05103-041 or -045) and side web - aft tunnel assembly (92202-05134) using 27 rivets (MS20470AD5-9). Trim rivets as required. (27) Apply sealant (AMS 3265 Type 2 or equivalent) to mating surfaces of bracket (AN743Z13) and doubler (92070-20087-101). (28) Install bracket (AN743Z13) to doubler (92070-20087-101) and aft shear deck tunnel assembly (92204-05103) using two rivets (MS20470AD4-9). Trim rivets as required. (29) If required, remove excess sealant (AMS 3265 Type 2 or equivalent) from work area. (30) Apply touch up paint to work area as required. NOTE: • When reinstalling harness assemblies in the following step, refer to Figure 4 for the recommended harness assembly clamping arrangement. • Perform safety and clearance checks between the flight control cables and the harness assemblies after clamping. Make sure harness assemblies do not chafe or interfere with the flight control cables. (31) If removed, reinstall harnesses assemblies as required. No. 92-53-004B FUSELAGE - Tail Rotor Pylon, One-Time Replacement of; and Joining-Tailcone - Installation of Doubler to Reinforce Aft Shear Deck Web Assembly
3. ACCOMPLISHMENT INSTRUCTIONS (Continued)

February 22/10 Page 11 53-60-05 Revision B - June 21/11(32) If removed, reinstall TCAS cables (500-92925-103).

(33) If disconnected, reconnect electrical connectors P600 and P602 to electrical receptacles J600 and J602. (34) Examine work area for security. Make sure work area is clean and free of foreign objects. (35) Proceed to section D. to perform installation of tail rotor pylon (92070-20058-042). C. Install doubler (92070-20087-101) on aft shear deck tunnel assembly (92204-05103-043) as follows (Figures 3 and 4): NOTE: • The following instructions are for helicopters with serial numbers 920083 through

920124. • The following instructions are performed using the tail rotor pylon joining installation modification kit 92070-20087-011. (1) At station 654.00, waterline 245.00, right buttline 9.00, locate aft shear deck tunnel assembly (92204-05103). (2) If connected, disconnect electrical connectors P600 and P602 from electrical receptacles J600 and J602 to gain access to work area. (3) If Installed, remove TCAS cables (500-92925-103) as required to gain access to work area. Save hardware for reuse. (4) Remove harness assemblies as required to gain access to work area. Note location of harness assemblies for reinstallation. Save hardware for reuse. (5) Remove two rivets (MS20470AD4-5) securing bracket (AN743Z13) to aft shear deck tunnel assembly (92204-05103). (6) Remove two rivets (MS20470AD5-6) from side web - aft tunnel assembly (92202-05134) common to aft shear deck tunnel assembly (92204-05103). (7) Temporarily secure doubler (92070-20087-101) to mounting location of aft shear deck tunnel assembly (92204-05103). NOTE: Prior to performing the following steps, pay particular attention to the tab on the

doubler for clearance and line up lightning hole in aft shear deck tunnel assembly for orientation. (8) Mark layout of three 0.161-inch diameter holes on doubler (92070-20087-101) using dimensions provided in Figure 3 View A-A. No. 92-53-004B FUSELAGE - Tail Rotor Pylon, One-Time Replacement of; and Joining-Tailcone - Installation of Doubler to Reinforce Aft Shear Deck Web Assembly
3. ACCOMPLISHMENT INSTRUCTIONS (Continued)

February 22/10 Page 12 53-60-05 Revision B - June 21/11(9) Using drill bit No. 20, transfer drill 22 0.161-inch diameter holes from doubler (92070- 20087-101) to aft shear deck tunnel assembly (92204-05103). (10) Using drill bit No. 20, transfer drill two 0.161-inch diameter holes from aft shear deck tunnel assembly (92204-05103) and side web - aft tunnel assembly (92202-05134) to doubler (92070-20087-101). (11) Using drill bit No. 20, drill three (marked) 0.161-inch diameter holes through doubler (92070-20087-101) and aft shear deck tunnel assembly (92204-05103). (12) Using drill bit No. 30, transfer drill two 0.128-inch diameter holes from bracket (AN743Z13) and aft shear deck tunnel assembly (92204-05103) to doubler (92070-20087-101). (13) Disassemble parts and deburr fastener holes as required. (14) Using low-lint cloth (A-A-59323 or equivalent) moistened with isopropyl alcohol (commercial grade or equivalent), clean surfaces of doubler (92070-20087-101) and mounting location of aft shear deck tunnel assembly (92204-05103). (15) Apply primer (MIL-PRF-85582 or MIL-P-23377 or equivalent) as required. (16) Apply sealant (AMS 3265 Type 2 or equivalent) to mating surfaces of doubler (92070- 20087-101), aft shear deck tunnel assembly (92204-05103) and side web - aft tunnel assembly (92202-05134). (17) Install doubler (92070-20087-101) to aft shear deck tunnel assembly (92204-05103) and side web - aft tunnel assembly (92202-05134) using 27 rivets (MS20470AD5-9). Trim rivets as required. (18) Apply sealant (AMS 3265 Type 2 or equivalent) to mating surfaces of bracket (AN743Z13) and doubler (92070-20087-101). (19) Install bracket (AN743Z13) to doubler (92070-20087-101) and aft shear deck tunnel assembly (92204-05103) using two rivets (MS20470AD4-9). Trim rivets as required. (20) If required, remove excess sealant (AMS 3265 Type 2 or equivalent) from work area. (21) Apply touch up paint to work area as required. NOTE: • When reinstalling harness assemblies in the following step, refer to Figure 4 for the recommended harness assembly clamping arrangement. • Perform safety and clearance checks between the flight control cables and the harness assemblies after clamping. Make sure harness assemblies do not chafe or interfere with the flight control cables.

No. 92-53-004B FUSELAGE - Tail Rotor Pylon, One-Time Replacement of; and Joining-Tailcone - Installation of Doubler to Reinforce Aft Shear Deck Web Assembly
3. ACCOMPLISHMENT INSTRUCTIONS (Continued)

February 22/10 Page 13 53-60-05 Revision B - June 21/11(22) If removed, reinstall harnesses assemblies as required.

(23) If removed, reinstall TCAS cables (500-92925-103). (24) If disconnected, reconnect electrical connectors P600 and P602 to electrical receptacles J600 and J602. (25) Examine work area for security. Make sure work area is clean and free of foreign objects. D. Install replacement tail rotor pylon (92070-20058-042) as follows: NOTE: • The following steps are referenced in Maintenance Manual, SA S92A-AMM-000,

Chapter/Section 53-60-05, Task No. 53-60-05-900-002. Read all notes before starting the installation procedures. Use the maintenance manual when installing the tail rotor pylon. • Due to the new radius blocks installed on the frame at station 664, the new bolts (positions 3 and 18) for these locations are longer than the bolts that are being removed. • When preparing mating surfaces of LHS and RHS bonding jumpers, make sure to apply a coat of corrosion coating (Alodine 600 or equivalent) to cleaned area of station 664 frame assembly (92201-05104) and on mid shear deck (92202-06304).(1) Install tail rotor pylon (92070-20058-042). Refer to Maintenance Manual, SA S92A-AMM000, Chapter/Section 53-60-05, Task No. 53-60-05-900-002 to complete installation of tail rotor pylon (92070-20058-042). (2) Reinstall customer furnished equipment as required. (3) Return helicopter to service. No. 92-53-004B FUSELAGE - Tail Rotor Pylon, One-Time Replacement of; and Joining-Tailcone - Installation of Doubler to Reinforce Aft Shear Deck Web Assembly
3. ACCOMPLISHMENT INSTRUCTIONS (Continued)

February 22/10 Page 14 53-60-05 Revision B - June 21/11E. Record information on SA7343-22 Aircraft Component Log Cards NOTE: AAR shall create log cards to reflect the example presented in Figure 5 and 6. (1) Create aircraft component log card and component maintenance record for New Install tail rotor pylon (92070-20058-042) as follows: NOTE: If access to Sikorsky360 website is not available, use blank AIRCRAFT

COMPONENT LOG CARDS (Figure 5, Sheet 1 of 3) and COMPONENT MAINTENANCE RECORD (Figure 6, Sheet 1 of 2). (a) Obtain a blank aircraft component log card forms SA7343-22. Log onto www.Sikorsky360.com and download form SA7343-22 Aircraft Component Log Card (page 1 of 2, front side) and form COMPONENT MAINTENANCE RECORD Card (page 2 of 2, back side). NOTE: This data appears on the New Install tail rotor pylon (92070-20058-042)

identification plate and the log card (reference step 3.A.(6)) attached to the Original Install tail rotor pylon (92000-06102-041). (b) On SA7343-22 AIRCRAFT COMPONENT LOG CARDS page (page 1 of 2, front side), enter the information from the original install tail rotor pylon using Figure 5 (sheet 2 of 3) as a guide. (c) On SA7343-22 AIRCRAFT COMPONENT LOG CARDS page (page 1 of 2, front side), enter the information for the new install tail rotor pylon using Figure 5 (sheet 3 of 3) as a guide. (d) On SA7343-22 COMPONENT MAINTENANCE RECORD form (page 2 of 2, back side), enter the information for the New Install tail rotor pylon using Figure 6 (sheet 2 of 2) as a guide. No. 92-53-004B FUSELAGE - Tail Rotor Pylon, One-Time Replacement of; and Joining-Tailcone - Installation of Doubler to Reinforce Aft Shear Deck Web Assembly
3. ACCOMPLISHMENT INSTRUCTIONS (Continued)

February 22/10 Page 15 53-60-05 Revision B - June 21/11NOTE: Log card must list New Install tail rotor pylon (92070-20058-042) as a lifelimited component per Airworthiness Limitations Manual, S92A-AWL-000. (e) Enter new retirement time in space labeled Retirement Time. New retirement time is the total time following modification plus 8,223. See example in Figure 5 (sheet 3 of 3). NOTE: Log card may have been filled out incorrectly, operators that have complied with original ASB dated February 22, 2010, please review and revise as necessary using Figures 5 and 6 as a guide. (2) For operators that have already received a tail rotor pylon from repair station, review and revise the log card using Figures 5 and 6 as a guide. F. Record of Compliance (1) Make an appropriate helicopter logbook or component log card entry to show compliance with this ASB. NOTE: If access to www.Sikorsky360.com is unavailable, complete attached ALERT

SERVICE BULLETIN COMPLIANCE RECORD CARD and return it Sikorksy Aircraft Corporation. (2) Make an appropriate electronic compliance entry in the E-Notification section at www.Sikorsky360.com. Refer to User Guide located on www.Sikorsky360.com/E-Notification Search page. No. 92-53-004B FUSELAGE - Tail Rotor Pylon, One-Time Replacement of; and Joining-Tailcone - Installation of Doubler to Reinforce Aft Shear Deck Web Assembly
3. ACCOMPLISHMENT INSTRUCTIONS (Continued)

February 22/10 Page 16 53-60-05 Revision B - June 21/11SA TD2255 92202−05134 SIDE WEB−AFT TUNNEL ASSEMBLY (REF) 92202−03412−102 SHEAR DECK PANEL BREAKER (REF)

REMOVE: AN743Z13 BRACKET (1) MS20470AD4−5 RIVET (2) INSTALL: AN743Z13 BRACKET − 1 REQ’D MS20470AD4−9 RIVET − 2 REQ’D

DOUBLER − 1 REQ’D MS20470AD5−9 RIVET − 25 REQ’D

92204−03412−104 SHELF INSTALLATION (REF)

92204−05102−102 AFT SHEAR DECK ANGLE (REF) REMOVE: MS20470AD5−6 RIVET (2) INSTALL: MS20470AD5−9 RIVET − 2 REQ’D

VIEW LOOKING UP AT SHEAR DECK 92204−05102−101 AFT SHEAR DECK ANGLE (REF) 92202−03412−103 SHEAR DECK PANEL BREAKER (REF) 92202−03412−101 SHEAR DECK PANEL AFT SHEAR DECK WEB (REF)

92202−03408−107 AFT TUNNEL PANEL BREAKER (REF) BREAKER (REF) BL 0.00

STA 653.95

F W
LEFT RIGHT D (SEE VIEW A−A)

VIEW A−A INSTALL: 92070−20087−101 11.2 O 2 PL 22.5 O

3.39 (REF) 4.35

(REF)

92204−05103−041 OR AFT SHEAR DECK TUNNEL ASSEMBLY (REF) 92204−05103−045 (SEE NOTE) SS1048−4 BRACKET (REF)

AN743Z13 BRACKET (REF) 92204−05101−045

NOTE MINIMUM 1.5 D EDGE DISTANCE ACCEPTABLE AT THIS LOCATION. IF AN743Z13 BRACKET EXISTS AT LOCATION, REFER TO DOUBLER INSTALLATION 92070−20087−101 DOUBLER (REF) TRACE

AN743Z13 BRACKET (REF) A

SHOWN IN FIGURE 2 FOR CLARITY A 92204−05103−041 OR AFT SHEAR DECK TUNNEL ASSEMBLY (REF) 92204−05103−045 MARK LAYOUT OF THREE 0.161−INCH DIAMETER HOLES ON DOUBLER 0.06 FROM 92202−03408−107 AFT TUNNEL PANEL BREAKER

92204-05103-041 OR 92204-05103-045 AFT SHEAR DECK WEB ASSEMBLY DOUBLER INSTALLATION

(HELICOPTERS WITH SERIAL NUMBERS 920006 THROUGH 920082) FIGURE 1 No. 92-53-004B

February 22/10 53-60-05 Page 17 Revision B - June 21/11SA TD2252 SIDE WEB−AFT TUNNEL ASSEMBLY (REF) BL 9.06

STA 653.97 92202−05134

NOTE MINIMUM 1.5 D EDGE DISTANCE ACCEPTABLE AT THIS LOCATION. TRACE

REMOVE: AN743Z13 BRACKET (1) MS20470AD4−5 RIVET (2) INSTALL: AN743Z13 BRACKET − 1 REQ’D MS20470AD4−9 RIVET − 2 REQ’D (SEE NOTE)

REMOVE: MS20470AD5−6 RIVET (2) INSTALL: MS20470AD5−9 RIVET − 2 REQ’D 3.39 (REF) 4.35 (REF)

INSTALL: MS20470AD6−9 RIVET − 1 REQ’D (SEE NOTE) INSTALL: MS20470AD6−9 RIVET − 1 REQ’D (SEE NOTE) PLUG EXISTING HOLE IN 92204−05101−045 AFT SHEAR DECK WEB BY INSTALLING NAS1097AD4−9 RIVET FLUSH NEARSIDE (BEFORE 92070−20087−101 DOUBLER INSTALLATION) PLUG EXISTING HOLE IN 92204−05101−045 AFT SHEAR DECK WEB BY INSTALLING NAS1097AD4−9 RIVET FLUSH NEARSIDE (BEFORE 92070−20087−101 DOUBLER INSTALLATION)
PLUG PILOT HOLE IN 92070−20087−101 DOUBLER BY INSTALLING NAS1097AD3−9 RIVET FLUSH FARSIDE REMOVE: AN743Z13 BRACKET (1) MS20470AD4−5 RIVET (2) RIVET − 1 REQ’D (SEE NOTE) INSTALL: MS20470AD6−9 RIVET − 21 REQ’D (SEE NOTE) INSTALL: MS20470AD5−9 92204−05101−045 AFT SHEAR DECK WEB (REF) 92070−20087−101 DOUBLER − 1 REQ’D INSTALL: 11.2 O 2 PL 22.5 O 0.06

F W
LEFT RIGHT D

VIEW LOOKING UP AT SHEAR DECK IF REQUIRED

IF REQUIRED MARK LAYOUT OF THREE 0.161−INCH DIAMETER HOLES ON DOUBLER

92204-05103-041 OR 92204-05103-045 AFT SHEAR DECK WEB ASSEMBLY DOUBLER INSTALLATION (HELICOPTERS WITH SERIAL NUMBERS 920006 THROUGH 920082 WITH DUAL BRACKET INSTALLATIONS) FIGURE 2 No. 92-53-004B

February 22/10 53-60-05 Page 18 Revision B - June 21/11SA TD2017_3 92202−05134 SIDE WEB−AFT TUNNEL ASSEMBLY (REF) 92202−03412−102 SHEAR DECK PANEL BREAKER (REF)

REMOVE: AN743Z13 BRACKET (1) MS20470AD4−5 RIVET (2) INSTALL: AN743Z13 BRACKET − 1 REQ’D MS20470AD4−9 RIVET − 2 REQ’D

DOUBLER − 1 REQ’D MS20470AD5−9 RIVET − 25 REQ’D

92204−03412−104 SHELF INSTALLATION (REF)

92204−05102−102 AFT SHEAR DECK ANGLE (REF) REMOVE: MS20470AD5−6 RIVET (2) INSTALL: MS20470AD5−9 RIVET − 2 REQ’D

VIEW LOOKING UP AT SHEAR DECK 92204−05103−043 92204−05102−101 AFT SHEAR DECK ANGLE (REF) 92202−03412−103 SHEAR DECK PANEL BREAKER (REF) 92202−03412−101 SHEAR DECK PANEL 92204−05101−047 AFT SHEAR DECK WEB (REF)

92202−03408−107 AFT TUNNEL PANEL BREAKER (REF) BREAKER (REF) BL 0.00

STA 653.95

F W
LEFT RIGHT D (SEE VIEW B−B) 1.41

VIEW B−B 0.34 1.41 0.94

0.94 INSTALL: 92070−20087−101

92204−05103−043 AFT SHEAR DECK TUNNEL ASSEMBLY (REF) (SEE NOTE)

AN743Z13 BRACKET (REF)

AFT SHEAR DECK TUNNEL ASSEMBLY (REF)

NOTE MINIMUM 1.5 D EDGE DISTANCE ACCEPTABLE AT THIS LOCATION. TRACE

DOUBLER (REF) 92070−20087−101

MARK LAYOUT OF THREE 0.161−INCH DIAMETER HOLES ON DOUBLER 0.06 FROM 92202−03408−107 AFT TUNNEL PANEL BREAKER

92204-05103-043 AFT SHEAR DECK WEB ASSEMBLY DOUBLER INSTALLATION (HELICOPTERS WITH SERIAL NUMBERS 920083 THROUGH 920124) FIGURE 3 No. 92-53-004B

February 22/10 53-60-05 Page 19 Revision B - June 21/11TD2256 SA STA 643.00

STA 649.00

STA 654.00

STATION 643.00 (RHS) LOOKING UP AND AFT TRANSITION F W D

MS27039-1-24 SCREW (REF) NAS1149D0332K FLAT WASHER (REF) MS21044N3 NUT (REF) NAS43DD3-56FC SPACER (REF) MS21919WDG4 CLAMP (REF) MS21919WDG6 CLAMP (REF) MS21919WDG8 CLAMP (REF) (SEE NOTE) 92400-00511 CABLE ASSEMBLY (REF) 92552-03118 RIPS T / R FEEDER HARNESS ASSEMBLY (REF) AN743Z13 BRACKET (REF) 92552-03102 RH TRANSITION MAIN HARNESS ASSEMBLY (REF) 500-92925-103 TCAS CABLES (REF) 92070-20087-101 DOUBLER (REF)

NOTE USE EXISTING HARDWARE TO RE-CLAMP HARNESS ASSEMBLIES OR PROCURE HARDWARE FROM LOCAL SUPPLY IF REQUIRED. CLAMP ARRANGEMENT MAY VARY PENDING BRACKET POSITION.

AFT SHEAR DECK WEB ASSEMBLY - RECOMMENDED CLAMPING ARRANGEMENT FIGURE 4 No. 92-53-004B

February 22/10 Page 20 53-60-05 Revision B - June 21/11SA TD2397_2NOMENCLATURE:PART NO:SERIAL NO:SECTION: 22PAGE:Page 1 of 2REASON FOR REMOVALCOMPONENT TIMET.T T.S.O.AIRCRAFT TIMEDATE REMOVEDDATE INSTALLEDAIRCRAFT NO.AIRCRAFT COMPONENT LOG CARDSNOTE:SA 7343-22 Revision 2/15/2005VERIFY CURRENT REVISION OF FORMREPAIR INTERVALOVERHAUL INTERVALRETIREMENT TIME

AIRCRAFT COMPONENT LOG CARD FIGURE 5 (SHEET 1 OF 3) No. 92-53-004B

February 22/10 Page 21 53-60-05 Revision B - June 21/11SA TD2397_1 920002 1/1/2011 5000 Comply with ASB 92-53-004B 92000-06102-041 TAI L RO TOR PYLON XXXX NOMENCLATURE: PAR T NO: SERIAL NO: SECTION: 22
Pag e 1 of 2

REASON FOR REMO VAL COMPONENT TIME T.T T.S .O. AIRCRAFT TIME DAT E REMOVED DAT E INSTALLED AIRCRAFT NO. AIRCRAFT COMPONENT LOG CARDS

DAT E:

SA 7343-22 Revision 2/15/2005 VERIFY CURRENT REVISION OF FORM REPAIR INTER VAL OVE RHAUL INTER VAL RETIREMENT TIME NEW NEW TAI L RO TOR PYLON PAR T NUMBER TAI L RO TOR PYLON SERIAL NUMBER (IF AVAILABLE)

REASON FOR REMOVAL

TOT AL TIME BAS ED ON ORIGINAL INSTALLATION OR AVAILABLE RECORDS 

# SAMPLE Associate Life Limited Component

5000

AIRCRAFT COMPONENT LOG CARD FIGURE 5 (SHEET 2 OF 3) No. 92-53-004B

February 22/10 Page 22 53-60-05 Revision B - June 21/11SA TD2397_3 920002 1/1/2011 5000 Comply with ASB 92-53-004B 92000-06102-041 TAIL ROTOR PYLON XXXX NOMENCLATURE: PART NO: SERIAL NO: SECTION: 22
Page 1 of 2

REASON FOR REMOVAL COMPONENT TIME T.T T.S.O. AIRCRAFT TIME DATE REMOVED DATE INSTALLED AIRCRAFT NO. AIRCRAFT COMPONENT LOG CARDS

DATE:

SA 7343-22 Revision 2/15/2005 VERIFY CURRENT REVISION OF FORM REPAIR INTERVAL OVERHAUL INTERVAL RETIREMENT TIME NEW NEW TAIL ROTOR PYLON

SERIAL NUMBER (IF AVAILABLE)

SUPPORTING DATA FOR INSTALLATION TOTAL TIME FOLLOWING MODIFICATION REMAINS UNCHANGED TOTAL TIME BASED ON ORIGINAL INSTALLATION OR AVAILABLE RECORDS 

# SAMPLE Associate Life Limited Component

5000

13,223 920005 5/13/2011 6250 5000 Modified per ASB 92-53-004B

92070-20058-042 NEW PART NUMBER FOLLOWING MODIFICATION

TOTAL TIME FOLLOWING MODIFICATION PLUS 8,223

AIRCRAFT COMPONENT LOG CARD FIGURE 5 (SHEET 3 OF 3) No. 92-53-004B

February 22/10 Page 23 53-60-05 Revision B - June 21/11SA TD2398_2TECHNICAL DIRECTIVESTITLE / REMARKSSTATUSSIGNATURE CERTIFICATE NO.TYPE and NUMBERDATEDATEREPAIRS OR OVERHAULSSIGNATURECERTIFICATE NO.SERIAL NO:NOMENCLATURE:PART NO:COMPONENT MAINTENANCE RECORD

COMPONENT MAINTENANCE RECORD FIGURE 6 (SHEET 1 OF 2) No. 92-53-004B

February 22/10 Page 24 53-60-05 Revision B - June 21/11SA TD2398_1 TECHNICAL DIRECTIVES TITLE / REMARKS STATUS SIGNATURE CERTIFICATE NO. TYPE and NUMBER DATE DATE REPAIRS OR OVERHAULS SIGNATURE CERTIFICATE NO. SERIAL NO: NOMENCLATURE: PART NO: COMPONENT MAINTENANCE RECORD

XX/XX/XX Modified per ASB 92-53-004B. New total time 0.0 per ASB

92-53-004B

XX/XX/XX Tail Rotor Pylon, One-Time Replacement of; and Joining-Tailcone-Installation of Doubler to Reinforce Aft Shear Deck Web Assembly (SIGNATURE) (CERTIFICATE #) ASB 92-53-004B C/W (SIGNATURE) (CERTIFICATE #) 92070-20058-042 TAIL ROTOR PYLON XXXXX

SIGNATURE OF INSPECTOR CERTIFICATE NUMBER OF MECHANIC OR REPAIR STATION DATE WORK PERFORMED TAIL ROTOR PYLON PART NUMBER TAIL ROTOR PYLON SERIAL NUMBER (IF AVAILABLE)

DESCRIPTION OF WORK WITH REFERENCE TO ASB AND NEW TOTAL TIME SIGNATURE OF INSPECTOR CERTIFICATE NUMBER OF MECHANIC OR REPAIR STATION

ASB NUMBER ASB TITLE C/W = COMPLIED WITH PCW = PREVIOUSLY COMPLIED WITH 

# SAMPLE

COMPONENT MAINTENANCE RECORD FIGURE 6 (SHEET 2 OF 2) No. 92-53-004B

February 22/10 Page 25 53-60-05 Revision B - June 21/11

# (860) 998-7565

Upon COMPLIANCE wit h t he a ttached ASB , Sik orsky requests your cooperation in completin g an d returning this ENTIR E P AGE by MAIL , FAX , or scan & EMAI L

. ATTE NTION: SAS PRODUCT SAFETY MANAGER S I KORSKY AEROSPACE SERVICES 

# EMAIL ADDRESS: GPSIKSASProductSafet@utc.com

No. 92-53-004B FUSELAGE - Tail Rotor Pylon, One-Time Replacement of; and Joining-Tailcone - Installation of Doubler to Reinforce Aft Shear Deck Web Assembly

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## Or scan and ema il to: EMAIL ADD RES S: GPSIKS ASPr oductSafet@utc.com