AD 98-02-04

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AD Number:
98-02-04
Document Type:
AD Final Rules
Docket Number:
97-ANE-29-AD
Subject Heading:
Airworthiness Directives; CFM International CFM56-5B/2P Series Turbofan Engines
Subject:
Low Pressure Turbine Case
Status:
Current
Citation:
Federal Register: September 18, 1998 (Volume 63, Number 181)
Citation Publish Date:
09/18/1998
Effective Date:
03/23/1998
Make:
CFM International, S.A.
Model:
CFM56-5B1/2P | CFM56-5B2/2P | CFM56-5B3/2P | CFM56-5B4/2P
Product Type:
Engine
Product Subtype:
Affected AD:
Superseded AD:
Affected By:
Superseded By:
Service/Office:
Office of Primary Responsibility:
CFR Part Reference:
Part 39 [63 FR 49819 NO. 181 09/18/98]
Comments:
AIRWORTHINESS DIRECTIVES FINAL RULES: 98-02-04
CITATION:   [Federal Register: September 18, 1998 (Volume 63, Number 181)]

PAGE NUMBER:   [Page 49819]

DOCKET NUMBER:   97-ANE-29-AD

AMENDMENT:   39-10286

AD NUMBER:   98-02-04

SUBJECT HEADING:   Airworthiness Directives; CFM International CFM56-5B/2P Series Turbofan Engines

ACTION:   Final rule; correction

SUMMARY:   This document makes a correction to Airworthiness Directive (AD) 98-02-04 applicable to CFM International (CFMI) CFM56-5B/2P series turbofan engines that was published in the Federal Register on January 21, 1998 (63 FR 3031). The low pressure turbine (LPT) case part number (P/N) in the compliance section is incorrect. This document corrects that P/N. In all other respects, the original document remains the same.

DATES:   Effective March 23, 1998.

ADDRESSES:  

FOR FURTHER INFORMATION CONTACT:   Robert J. Ganley, Aerospace Engineer, Engine Certification Office, FAA, Engine and Propeller Directorate, 12 New England Executive Park, Burlington, MA 01803-5299; telephone (781) 238-7138; fax (781) 238-7199.

SUPPLEMENTARY INFORMATION:  

REGULATORY TEXT:   98-02-04 CFM INTERNATIONAL: Amendment 39-10286. Docket 97-ANE-29-AD.
Applicability: CFM International (CFMI) CFM56-5B1/2P, -5B2/2P, -5B3/2P, and - 5B4/2P turbofan engines, installed with low pressure turbine (LPT) case, Part Number (P/N) 338-117-404-0, installed on but not limited to Airbus A320 and A321 series aircraft.
Note 1: This airworthiness directive (AD) applies to each engine identified in the preceding applicability provision, regardless of whether it has been modified, altered, or repaired in the area subject to the requirements of this AD. For engines that have been modified, altered, or repaired so that the performance of the requirements of this AD is affected, the owner/operator must request approval for an alternative method of compliance in accordance with paragraph (e) of this AD. The request should include an assessment of the effect of the modification, alteration, or repair on the unsafe condition addressed by this AD; and, if the unsafe condition has not been eliminated, the request should include specific proposed actions to address it.
Compliance: Required as indicated, unless accomplished previously.
To prevent a low cycle fatigue (LCF) failure of the LPT case, which could result in damage to the aircraft, accomplish the following:
(a) Remove from service LPT case, P/N 338-117-404-0, and replace with a serviceable part, as follows:
(1) For CFM56-5B2/2P and -5B3/2P engines, prior to accumulating 10,500 cycles.
(2) For CFM56-5B1/2P and -5B4/2P engines, prior to accumulating 15,500 cycles.
(b) This action establishes the new LCF retirement lives of 10,500 and 15,500 cycles for the engines stated in paragraphs (a)(1) and (a)(2) of this AD, which are published in Chapter 05 of CFM56-5B Engine Shop Manual, CFMI-TP.SM.9.
(c) For the purpose of this AD, a "serviceable part" is one that has not exceeded its respective new life limit as set out in this AD.
(d) Except as provided in paragraph (e) of this AD, no alternative replacement times may be approved for LPT case, P/N 338-117-404-0.
(e) 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. 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 2: Information concerning the existence of approved alternative methods of compliance with this airworthiness directive, if any, may be obtained from the Engine Certification Office.
(f) Special flight permits may be issued in accordance with sections 21.197 and 21.199 of the Federal Aviation Regulations (14 CFR 21.197 and 21.199) to operate the aircraft to a location where the requirements of this AD can be accomplished.
(g) This amendment becomes effective on March 23, 1998.

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