AD 92-15-07

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AD Number:
92-15-07
Document Type:
AD Final Rules
Docket Number:
91-ANE-40
Subject Heading:
TEXTRON LYCOMING Model LTS101 Series and LTP101 Series Engines
Subject:
Integrally Cast Power Turbine (PT) Rotor Blade
Status:
Current
Citation:
This information is not available.
Citation Publish Date:
Effective Date:
09/02/1992
Make:
Honeywell International Inc.
Model:
LTP 101-600 | LTP 101-600A | LTP 101-600A-1A | LTP 101-700A-1A | LTS101-600A | LTS101-600A-1 | LTS10...Show more
Product Type:
Engine
Product Subtype:
Affected AD:
Superseded AD:
Affected By:
Superseded By:
Service/Office:
Office of Primary Responsibility:
CFR Part Reference:
Part 39
Comments:
AIRWORTHINESS DIRECTIVES FINAL RULES: 92-15-07
CITATION:   This information is not available.

PAGE NUMBER:  

DOCKET NUMBER:   91-ANE-40

AMENDMENT:   39-8301

AD NUMBER:   92-15-07

SUBJECT HEADING:   TEXTRON LYCOMING Model LTS101 Series and LTP101 Series Engines

ACTION:  

SUMMARY:  

DATES:   Effective September 2, 1992.

ADDRESSES:  

FOR FURTHER INFORMATION CONTACT:  

SUPPLEMENTARY INFORMATION:  

REGULATORY TEXT:   92-15-07 TEXTRON LYCOMING: Amendment 39-8301. Docket No. 91-ANE-40. Supersedes AD 87-11- 09, Amendment 39-5902.
Applicability: Textron Lycoming LTS101 series turboshaft and LTP101 series turboprop engines installed on but not limited to Aerospatiale AS350, Bell 222, and MBB BK117 helicopters; and Piaggio P166-DL3, Airtractor AT302, and Cessna 421 airplanes.
Compliance: Required as indicated, unless accomplished previously.
To prevent fracture of the integrally cast power turbine (PT) rotor blade, which can result in engine power loss and uncontained engine failure, accomplish the following:
(a) Perform a Type I, Method C fluorescent penetrant inspection of Part Number (P/N) 4-141-070-XX and P/N 4-143-010-XX PT rotors installed in engines, in accordance with the procedures in Textron Lycoming Service Bulletin (SB) Number LT 101-72-00-0093, Revision 5, dated January 15, 1990, as follows:
(1) Inspect for PT rotor blade cracks within 50 hours time in service (TIS) or 300 PT cycles in service (CIS), whichever occurs first, since accomplishing the last inspection performed in accordance with AD 87-11-09.
(2) Thereafter, reinspect for PT rotor blade cracks at intervals not to exceed 50 hours TIS or 300 PT CIS, whichever occurs first, since the last Type I, Method C fluorescent penetrant inspection performed in accordance with paragraph (a) of this AD.
(3) Remove from service prior to further flight, cracked PT rotors found during the inspections required by paragraphs (a)(1) and (a)(2) of this AD. Prior to returning to service, replace with a serviceable PT rotor.
NOTE: For information on PT rotor cycle and counting methodology consult the latest revision to Textron Lycoming SB No. LT 101-71-00-0002.
(b) Perform a Type I, Method D fluorescent penetrant inspection of P/N 4-141-070-XX and P/N 4-143- 010-XX PT rotors prior to installation into a PT module or prior to returning to service, in accordance with Textron Lycoming SB No. LT 101-72-00-0093, Revision 5, dated January 15, 1990. Cracked PT rotors found during this fluorescent penetrant inspection shall not be returned to service and must be replaced with a serviceable PT rotor.
(c) For PT rotors P/N 4-141-070-XX and P/N 4-143-010-XX installed in LTS101-650C-3, LTS101- 650C-3A, and LTS101-750C-1 series engines, avoid continuous operation at certain PT operating speeds in accordance with Textron Lycoming SB Number LTS 101C-72-00-0131, dated September 17, 1990, Bell Helicopter Textron Alert SB 222U-90-30, dated December 21, 1990, and Alert SB 22-90-57, dated December 21, 1990, within 20 hours time in service, after effective date of this AD, as follows:
(1) Avoid continuous engine operation at 97% to 98.5% power turbine (Np) speed, including autorotation and single engine operation. Operation in this speed range is only permitted for topping checks and when operations in this range are necessary to maintain safe flight.
(2) Install a cockpit tachometer decal and add the temporary rotorcraft flight manual supplement in accordance with applicable Bell Helicopter Textron ASB No. 222U-90-30 or Bell Helicopter Textron ASB No. 222-90-57, as applicable.
(d) An alternative method of compliance or adjustment of the compliance time that provides an acceptable level of safety may be used if approved by the Manager, Engine Certification Office, FAA, Engine and Propeller Directorate. The request should be forwarded through an appropriate FAA Principal Maintenance Inspector, who may add comments and then send it to the Manager, Engine Certification Office.
NOTE: Information concerning the existence of approved alternative methods of compliance with this airworthiness directive, if any, may be obtained from the Engine Certification Office.
(e) Special flight permits may be issued in accordance with FAR 21.197 and 21.199 to operate the airplane to a location where the requirements of this AD can be accomplished.
(f) The PT rotor inspection and removal criteria, the establishment of the PT rotor speed operation avoidance ranges, rotorcraft modification, and rotorcraft flight manual revisions shall be accomplished in accordance with the following service bulletins:


DOCUMENT NO.	PAGES	ISSUE/REVISION	DATE
Textron Lycoming SB LT 101-72-00-0093	1-4	Revision 5	1-15-90
including Commercial Service Letter CSL 063 R-1	1-2	Revision 1	5-31-91
Textron Lycoming SB LTS 101C-72-00-0131	1-2	Original	9-17-90
Bell Helicopter Textron Alert SB 222-90-57	1-4	Original	12-21-90
Bell Helicopter Textron Alert SB 222U-90-30	1-4	Original	12-21-90

This incorporation by reference was approved by the Director of the Federal Register in accordance with 5. U.S.C. 552(a) and 1 CFR Part 51. Copies may be obtained from Textron Lycoming, Technical Publications, Department 30V, 550 South Main Street, Stratford, Connecticut 06497, and Bell Helicopter Textron, P.O. Box 482, Fort Worth, Texas 76101. Copies may be inspected at the FAA, New England Region, Office of the Assistant Chief Counsel, Room 311, 12 New England Executive Park, Burlington, Massachusetts; or at the Office of the Federal Register, 1100 L Street NW., Room 8401, Washington, D.C.
(g) This amendment becomes effective on September 2, 1992.

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