Page 1 of 1 

June 21, 2011 

TRANSMITTAL SHEET 

Subject: ALERT SERVICE BULLETIN 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 

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 Alert 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 requirements 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 original 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 Section 
1. 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 21/11
C. 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 21/11
F. 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 21/11
I. 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 21/11
A. 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 21/11
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 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 21/11
E. 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 21/11
NOTE: 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 21/11
SA

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

RIGHT LEFT

D

(SEE VIEW A−A)

VIEW A−A

INSTALL:

92070−20087−101

11.2O

2 PL

22.5O

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 21/11
SA

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:

11.2O

2 PL

22.5O

0.06

F

W

RIGHT LEFT

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 21/11
SA

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

RIGHT LEFT

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 21/11
TD2256

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 21/11
SA

TD2397_2

NOMENCLATURE: PART NO: SERIAL NO:

SECTION: 22

PAGE:

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

NOTE:

SA 7343-22 Revision 2/15/2005 VERIFY CURRENT REVISION OF FORM

REPAIR INTERVAL

OVERHAUL INTERVAL

RETIREMENT 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 21/11
SA

TD2397_1

920002 1/1/2011 5000 Comply with ASB 92-53-004B

PART NO: 92000-06102-041 NOMENCLATURE: TAIL ROTOR PYLON SERIAL NO: XXXX

SECTION: 22

Page 1 of 2

COMPONENT TIME REASON FOR REMOVAL

T.T T.S.O.

AIRCRAFT NO. DATE INSTALLED DATE REMOVED AIRCRAFT TIME

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

PART NUMBER

TAIL ROTOR PYLON

SERIAL NUMBER

(IF AVAILABLE)

REASON FOR

REMOVAL

TOTAL TIME BASED 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 21/11
SA

TD2397_3

920002 1/1/2011 5000 Comply with ASB 92-53-004B

PART NO: 92000-06102-041 NOMENCLATURE: TAIL ROTOR PYLON SERIAL NO: XXXX

SECTION: 22

Page 1 of 2

COMPONENT TIME
 REASON FOR REMOVAL

T.T T.S.O.

AIRCRAFT NO. DATE INSTALLED DATE REMOVED AIRCRAFT TIME

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 21/11
SA

TD2398_2

TECHNICAL DIRECTIVES

DATE TYPE and NUMBER TITLE / REMARKS STATUS SIGNATURE CERTIFICATE 

DATE REPAIRS OR OVERHAULS SIGNATURE CERTIFICATE 

PART NO: NOMENCLATURE: SERIAL NO:

COMPONENT MAINTENANCE RECORD

COMPONENT MAINTENANCE RECORD

FIGURE 6 (SHEET 1 OF 2)

February 22/10 Page 24 53-60-05

Revision B - June 21/11
SA

TD2398_1

TECHNICAL DIRECTIVES

DATE TYPE and NUMBER TITLE / REMARKS STATUS SIGNATURE CERTIFICATE NO.

DATE REPAIRS OR OVERHAULS SIGNATURE CERTIFICATE NO.

PART NO: NOMENCLATURE: SERIAL 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

ASB 92-53-004B C/W (SIGNATURE) (CERTIFICATE #)

(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 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

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
BUSINESS REPLY MAIL

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SIKORSKY AEROSPACE SERVICES

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