AD 84-10-06 R1

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AD Number:
84-10-06 R1
Document Type:
AD Final Rules
Docket Number:
Unknown
Subject Heading:
GARRETT TURBINE ENGINE COMPANY Model TPE331-25, -43, -47, -55, -1, -2, -3, -5, -6, -10 (except -10A...Show more
Subject:
Fuel Pump Assemblies
Status:
Current
Citation:
This information is not available.
Citation Publish Date:
12/27/1984
Effective Date:
12/26/1984
Make:
Honeywell International Inc.
Model:
TPE331-1 | TPE331-10 | TPE331-10B | TPE331-10G | TPE331-10GR | TPE331-10R | TPE331-10U | TPE331-10UA...Show more
Product Type:
Engine
Product Subtype:
Affected AD:
Superseded AD:
Affected By:
Superseded By:
Service/Office:
AIR-700: Compliance & Airworthiness Division
Office of Primary Responsibility:
AIR-790: Los Angeles ACO Branch
CFR Part Reference:
Part 39
Comments:
Updated RGL applicability to match AD applicability; CAR C-11-185 Updated to match AD applicability,...Show more
AIRWORTHINESS DIRECTIVES FINAL RULES: 84-10-06 R1
CITATION:   This information is not available.

PAGE NUMBER:  

DOCKET NUMBER:   Unknown

AMENDMENT:   39-4964

AD NUMBER:   84-10-06 R1

SUBJECT HEADING:   GARRETT TURBINE ENGINE COMPANY Model TPE331-25, -43, -47, -55, -1, -2, -3, -5, -6, -10 (except -10A), and -11 Engines

ACTION:  

SUMMARY:  

DATES:   Effective December 26, 1984.

ADDRESSES:  

FOR FURTHER INFORMATION CONTACT:  

SUPPLEMENTARY INFORMATION:  

REGULATORY TEXT:  
84-10-06 R1 GARRETT TURBINE ENGINE COMPANY (GTEC, formerly AIRESEARCH MANUFACTURING COMPANY OF ARIZONA): Amendment 39-4867 as amended by Amendment 39-4964. Applicable to all series of engine models TPE331-25, -43, -47, -55, -1, -2, -3, -5, -6, -10 (except -10A), and -11 equipped with the following fuel pump assemblies:


P/N	S/N
868531-7/-8	All.
869151-1/-3/-4/-5	All.
893573-1 through -7	All.
895413-1/-9	All.
897380-1/-2/-3	Series 1 & 2.
897380-4/-5	Series 1, 2, & 3.
897390-1/-2/-3/-4	Series 1 & 2.
897400-1/-2	Series 1 & 2.
897400-4	Series 1.

Compliance is required as indicated unless already accomplished.

To prevent possible engine failure, accomplish the following:

(a) Inspect low-time engine fuel control/pump assembly to determine drive shaft running torque as specified in Section 2.A.(2), "Accomplishment Instructions," of GTEC SB TPE331-73-0121, Revision 2 dated April 18, 1984, or equivalent approved by the Manager, Western Aircraft Certification Office, in accordance with the schedule below:

Fuel pump assembly time: since new or since last assembled; or engine total time: since new or since last overhauled; whichever is known to be least,


Hours	Inspect not later than
Less than 200	the next 100 hours in service
200 or more, and less than 1,000	the next 200 hours in service
1,000 or more	next fuel pump disassembly

NOTE: Engine Logbook Records should indicate if a new or reassembled fuel pump assembly has been installed on the engine since new or returned from overhaul.

Remove from further service fuel pump assemblies having unsatisfactory running torque inspection results unless modified as specified in Section 2, "Accomplishment Instructions," in SB TPE331-73-0121, Revision 2, or equivalent approved by the Manager, Western Aircraft Certification Office.

Fuel control/pump assemblies having satisfactory inspection results may be continued in service until fuel pump disassembly per Paragraph (b) below.

(b) Upon disassembly of fuel pump for any reason, reassemble to an approved parts configuration as specified in Section 2, "Accomplishment Instructions," in SB TPE331-73-0121, Revision 2, or equivalent approved by the Manager, Western Aircraft Certification Office.

(c) Special flight permits may be issued in accordance with Federal Aviation Regulation FAR 21.197 and FAR 21.199 to ferry aircraft to a maintenance base in order to comply with the requirements of this AD.

(d) Alternative means of compliance providing an equivalent level of safety may be used when approved by the Manager, Western Aircraft Certification Office, FAA, Northwest Mountain Region.

(e) Upon request of the operator, an FAA Maintenance Inspector, subject to prior approval of the Manager, Western Aircraft Certification Office, FAA, Northwest Mountain Region, may adjust the compliance schedule specified in this AD to permit compliance at an established inspection period of the operator if the request contains substantiating data to justify the adjustment for that operator.

(f) The Manager, Western Aircraft Certification Office has found GTEC SB TPE331-73-0121 Revision 3, dated November 5, 1984, to be equivalent to GTEC SB TPE331-73-0121 Revision 2 dated April 18, 1984. This revision only adds the fuel pump assembly P/N. There are no changes in inspections or accomplishment instructions.

The manufacturer's specifications and procedures identified and described in this directive are incorporated herein and made a part hereof pursuant to 5 U.S.C. 552(a)(1).

All persons affected by this directive who have not already received this document from the manufacturer may obtain copies upon request to Garrett Turbine Engine Company, 111 South 34th St., P.O. Box 5217, Phoenix, Arizona 85010; telephone (602) 231-1000. This document also may be examined at FAA Rules Docket 83-ANE-29, New England Region, Office of the Regional Counsel, 12 New England Executive Park, Burlington, Massachusetts 01803.

This amendment supersedes Amendment 39-4840 (49 FR 13487), AD 84-07-08.

Amendment 39-4867 became effective May 30, 1984.

This Amendment 39-4964 becomes effective on December 26, 1984.

FOOTER: