AlliedSignal Service Bulletin T53-L-13B-0100

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AD 2022-10-02Engine Controls · Honeywell International T53-L-703, T53-L-13B S/SB, T53-L-13B S/SA and 14 moreEffective Jun 28, 2022 · Revision 2

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Page 1Open in PDF

Aerospace Honeywell International Inc.

111 South 34th Street Phoenix, AZ 85034 USA

Date: July 18, 2014 To: Holders of Technical Publication no. T53-L-13B-0100

Subject: Technical Publications Export Classification Declaration

To Whom It May Concern,

The purpose of this attachment is to formally communicate to holders of the subject document its United States’ export classification.

Important: The following export classification hereby supersedes any previously assigned export classification found within the body of the Technical Publication.

Publication Number: T53-L-13B-0100 ATA Number: T53-L-13B-0100 Document Export Classification: 9E991 Document Title: ENGINE - GENERAL - INTRODUCTION OF A SPECIAL VIBRATION CHECK

Note: The enclosed technical data is to be used solely by the individual or organization to whom it is addressed.

Diversion contrary to U.S. export laws and regulations is prohibited.

Background And Reason For New Export Declaration:

Honeywell has historically included the export classification within the body of the technical publication. By doing so, changes to the document’s export classification required a formal revision to the document itself. This new Export Classification Declaration meets Honeywell’s legal obligation to communicate the document’s export classification to the recipient and allows for potential changes that will not require a formal document revision.

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AlliedSignal SERVICE BULLETIN AEROSPACE AlliedSignal Engines

REVISION TRANSMITTAL SHEET This sheet transmits Revision 2 to Service Bulletin T53-L- 13B-0100, titled ENGINE - GENERAL -

INTRODUCTION OF A SPECIAL VIBRATION CHECK This is a COMPLETE revision. This bulletin has been reprinted in its entirety. Please remove and discard all pages of prior issues and replace with pages of this revision.

Reason for Revision: To update Service Bulletin with guidance for recurring inspection requirements.

Paragraph 1.E, added safety issue.

Paragraph 3.A. (2), added shimming requirements and added WARNING and NOTE.

Paragraph 3.B, revised recheck procedure.

List of Effective Pages:

Page No. Date Page No. Date May 11/99 4 May 11/99 2 May 11/99 5 May 11/99 May 11/99 Previous Revisions:

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IliedSignal SERVICE BULLETIN AEROSPACE AlliedSignal Engines Category 1: Safety

ENGINE - GENERAL - INTRODUCTION OF A SPECIAL VIBRATION CHECK

1. Planning Information A. Effectivity This Service Bulletin applies to the following gas turbine engines:

Part No. Model No. Serial No. Application 1-000-060-10 T53-L-13B ALL Bell UH- 1 Series 1-000-060-17 T53-L- 13B S/SA ALL Augusta AB 205 1-000-060-22 T53-L-13B S/SB ALL Bell UH-1 Series B. Concurrent Requirements Does not apply.

C. Reason

(1) Problem: In U.S. Army aircraft, and aircraft supported by the U.S. Army, there have been several failures of N2 Spur Gear Part No. 1-070-062-04.

(2) Background: AlliedSignal Engines is conducting an engineering investigation with the U.S. Army to determine the cause of this failure mechanism. It has been determined that engines exhibiting certain vibration characteristics can produce unacceptable stress in the spur gear that can result in a spur gear failure.

(3) Action: Perform the special vibration check outlined in this Service Bulletin.

D. Description This Service Bulletin offers a complete vibration analysis method to determine if the T53-L-13B engine has vibration characteristics which have been associated with previous spur gear failures.

E. Compliance Compliance addresses a safety issue. AlliedSignal recommends compliance with this Service Bulletin for all T53 series engines. This Service Bulletin should be performed within 100 flight hours (not to exceed a 6 month time period) from the original issue date of this Service Bulletin for installed units. Perform as part of the installation procedures on all engines that are now uninstalled. If procedure has been accomplished during engine test by an authorized service center and noted in the engine logbook, this Service Bulletin does not need to be performed on engine installation.

F. Approval The technical data in this Service Bulletin has been approved by AlliedSignal Engines.

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IliedSignal SERVICE BULLETIN AEROSPACE AlliedSignal Engines G. Manpower An estimated 4.0 manhours are necessary to perform this Service Bulletin.

H. Weight and Balance No change.

Electrical Load Data No change.

Software Accomplishment Summary Does not apply.

K. References The data used to prepare this Service Bulletin include AlliedSignal engineering documents and the publications shown below:

(1) Publications.

Engine Maintenance Illustrated Parts Model No. Manual No Catalog No.

T53-L-13B 350.2 350.4

(2) Service bulletin references.

None.

L. Other Publications Affected Operational Information Letters (OIL) are issued to inform pilots and maintenance personnel of the effect that an adverse maintenance condition will have on the engine and resulting effects to the aircraft.

OIL T53-01 was issued to address the effect of a N2 system disconnect caused by a spur gear failure.

All personnel involved with the T53-L- 13B engine should become familiar with this OIL.

M. Interchangeability or Intermixability of Parts Does not apply.

2. Material Information A. Material - Price and Availability Does not apply.

B. Industry Support Information Does not apply.

May 5/98 T53-L-13B-0100 Revision 2, May 11/99 Page 2

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AlliedSignal SERVICE BULLETIN AEROSPACE AlliedSignal Engines C. Material Necessary for Each Engine Does not apply.

D. Material Necessary for Each Spare Does not apply.

E. Reidentified Parts Does not apply.

Tooling - Price and Availability The special tools necessary to do this Service Bulletin are in the manuals shown in paragraph 1.K. (1) and as follows:

(1) Chadwick Helmuth 192 and 8500 series vibration analyzers have been tested and have been able to detect the vibration of interest. When using this equipment the 7310 velocimeter, Mounting Bracket Part No. LTCT535, and Cable Part No. 11210-20/-50 must be used.

If other equipment is used it must have the capability to measure the vibration at a frequency of O to 5000 Hz. There cannot be any filters installed in either the velocimeter or vibration analyzer.

(3) To purchase Chadwick Helmuth equipment, send Fax request to (626) 350-4236. One alternate source of vibration equipment is Scientific Precision. For information concerning availability and use of equipment to meet these requirements, contact: Dave Lilly, Phone (619) 679-6228, Fax

(4) Refer questions on the ground support equipment to AlliedSignal Aerospace, Marketing, Sales & Service, P.O. Box 52170, Phoenix, AZ 85072-2170, Fax (602) 231-2328.

(5) Modification instructions for Bracket Part No LTCT535.

(a) Locate the center of three existing accelerometer mounting holes.

(D) Drill a 0.213 inch (No. 3 drill) through the bracket. Deburr holes.

Thread hole with a 0.250-28 tap. This hole is used to hold the accelerometer to the bracket. It must hold the accelerometer flush on the bracket. Any deviation from this will cause false information during the vibration check.

3. Accomplishment Instructions A. Perform Vibration Test of Engine

(1) Follow vibration equipment manufacturer's instructions for the warm-up and installation of the equipment.

(2) There will be one pick-up installed at the No. 1 pick up location (lifting eye on top of the engine inlet housing). Use mounting bracket LTCT535. The mounting bracket may require shimming to secure it tightly.

May 5/98 T53-L-13B-0100 Revision 2, May 11/99 Page 3

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IliedSignal SERVICE BULLETIN AEROSPACE AlliedSignal Engines WARNING: A LIMIT OF 0.2 IPS (INCHES PER SECOND) HAS BEEN ESTAB-

LISHED BY ALLIEDSIGNAL ENGINES FOR ANY PEAK WITHIN THE RPM/FREQUENCY BANDS. IF THIS LIMIT IS EXCEEDED IN THE 225,000 TO 250,000 RANGE THE TEST MUST BE TERMINATED AND THE ENGINE REMOVED FROM SERVICE.

NOTE: Contact AlliedSignal Customer Support Engineering with any high vibration data in the 200,000 to 225,000 or above the 250,000 ranges.

(3) After the equipment is installed perform the vibration test using the parameters listed in Table 1.

Table 1. Vibration Test Output Shaft N2 N1 Rpm/Frequency ud 0o29 %*6 90% 200,000 to 300,000 6400 грт %L6 85% 200,000 to 300,000 6400 pm 97% 90% 200,000 to 300,000 6300 rpm 95.5% 95% 200,000 to 300,000 6400 rpm 97% 95% 200,000 to 300,000 6500 rpm 98.5% 95% 200,000 to 300,000 6400 грт 97% MAX. 200,000 to 300,000 uds 0099 %O01 90% 200,000 to 300,000 THON A recheck is required every 500 hours when Gear Part No. 1-070-062-04 and every 1000 hours when Gear Part No. 1-070-062-06 is installed. A recheck is required whenever disassembly for parts replacement is performed on the Reduction Gearbox Part No. 1-030-350-08/-09/- 12/

- 16.

C. Engines Passing Vibration Check

(1) AlliedSignal recommends engines that pass this vibration check within the limit of 0.2 ips be returned to service without flights restrictions.

(2) Compliance with this Service Bulletin must be recorded in the Engine Logbook and the Service Bulletin Compliance Records.

(3) Complete and return the Notice of Service Bulletin Compliance (attached) to AlliedSignal Engines.

May 5/98 T53-L-13B-0100 Revision 2, May 11/99 Page 4

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AlliedSignal SERVICE BULLETIN AEROSPACE AlliedSignal Engines

4. Appendix Does not apply.

May 5/98 T53-L-13B-0100 Revision 2, May 11/99 Page 5