[Federal Register Volume 60, Number 115 (Thursday, June 15, 1995)] [Rules and Regulations] [Pages 31388-31389] From the Federal Register Online via the Government Publishing Office [www.gpo.gov] [FR Doc No: 95-14638] ----------------------------------------------------------------------- DEPARTMENT OF TRANSPORTATION 14 CFR Part 39 [Docket No. 95-ANE-20; Amendment 39-9270; AD 95-12-19] Airworthiness Directives; Pratt & Whitney JT8D-200 Series Turbofan Engines AGENCY: Federal Aviation Administration, DOT. ACTION: Final rule; request for comments. ----------------------------------------------------------------------- SUMMARY: This amendment adopts a new airworthiness directive (AD) that is applicable to Pratt & Whitney (PW) JT8D-200 series turbofan engines. This action requires periodic inspection of fan blades for locked fan blade shrouds and foreign object damage (FOD); unlocking of fan blade shrouds, if necessary; and lubrication of fan blade shrouds. This amendment is prompted by reports of six recent fan blade failures, two of which resulted in the separation of the engine nose cowl from the aircraft. The actions specified in this AD are intended to prevent fan blade failure, which can result in damage to the aircraft. DATES: Effective June 30, 1995. The incorporation by reference of certain publications listed in the regulations is approved by the Director of the Federal Register as of June 30, 1995. Comments for inclusion in the Rules Docket must be received on or before August 14, 1995. ADDRESSES: Submit comments in triplicate to the Federal Aviation Administration (FAA), New England Region, Office of the Assistant Chief Counsel, Attention: Rules Docket No. 95-ANE-20, 12 New England Executive Park, Burlington, MA 01803-5299. The service information referenced in this AD may be obtained from Pratt & Whitney, 400 Main St., East Hartford, CT 06108. This information may be examined at the FAA, New England Region, Office of the Assistant Chief Counsel, 12 New England Executive Park, Burlington, MA; or at the Office of the Federal Register, 800 North Capitol Street NW., suite 700, Washington, DC. FOR FURTHER INFORMATION CONTACT: Mark A. Rumizen, Aerospace Engineer, Engine Certification Office, FAA, Engine and Propeller Directorate, 12 New England Executive Park, Burlington, MA 01803-5299; telephone (617) 238-7137, fax (617) 238-7199. SUPPLEMENTARY INFORMATION: The Federal Aviation Administration (FAA) has received six recent reports of engine failures due to fan blade failures on Pratt & Whitney (PW) JT8D-200 series turbofan engines. Fan blade failures can have serious secondary effects such as inlet cowl penetration or liberation, engine flange separation, fuel leaks, or impact damage to the aircraft. Most of these failures result from fractures that originate in the leading edge of the blade just above the platform. The FAA has determined that the primary cause of the failures is high cycle fatigue (HCF) cracking that is initiated by foreign object damage (FOD) to this area of the blade. Other factors have been found to increase the blade stresses such that the blade is more susceptible to FOD induced HCF cracking. These factors include locked fan blade shrouds, which increase blade stresses, and leading edge erosion, which can produce blade flutter. This condition, if not corrected, could result in fan blade failure, which can result in damage to the aircraft. The FAA has reviewed and approved the technical contents of PW All Operators Wire (AOW) No. JT8D/72-33/CTS: CRC-5-4-5-1, dated April 5, 1995, that describes procedures for periodic inspection of fan blades for locked rotors and FOD; unlocking of fan blade shrouds, if necessary; and lubrication of fan blade shrouds. Since an unsafe condition has been identified that is likely to exist or develop on other engines of the same type design, this airworthiness directive (AD) is being issued to prevent fan blade failure, which can result in damage to the aircraft. This AD requires periodic inspection of fan blades for locked rotors and FOD; unlocking of fan blade shrouds, if necessary; and lubrication of fan blade shrouds. The actions are required to be accomplished in accordance with the AOW described previously. Since a situation exists that requires the immediate adoption of this regulation, it is found that notice and opportunity for prior public comment hereon are impracticable, and that good cause exists for making this amendment effective in less than 30 days. Comments Invited Although this action is in the form of a final rule that involves requirements affecting flight safety and, thus, was not preceded by notice and an opportunity for public comment, comments are invited on this rule. Interested persons are invited to comment on this rule by submitting such written data, views, or arguments as they may desire. Communications should identify the Rules Docket number and be submitted in triplicate to the address specified under the caption ADDRESSES. All communications received on or before the closing date for comments will be considered, and this rule may be amended in light of the comments received. Factual information that supports the commenter's ideas and suggestions is extremely helpful in evaluating the effectiveness of the AD action and determining whether additional rulemaking action would be needed. Comments are specifically invited on the overall regulatory, economic, environmental, and energy aspects of the rule that might suggest a need to modify the rule. All comments [[Page 31389]] submitted will be available, both before and after the closing date for comments, in the Rules Docket for examination by interested persons. A report that summarizes each FAA-public contact concerned with the substance of this AD will be filed in the Rules Docket. Commenters wishing the FAA to acknowledge receipt of their comments submitted in response to this notice must submit a self-addressed, stamped postcard on which the following statement is made: ``Comments to Docket Number 95-ANE-20.'' The postcard will be date stamped and returned to the commenter. The regulations adopted herein will not have substantial direct effects on the States, on the relationship between the national government and the States, or on the distribution of power and responsibilities among the various levels of government. Therefore, in accordance with Executive Order 12612, it is determined that this final rule does not have sufficient federalism implications to warrant the preparation of a Federalism Assessment. The FAA has determined that this regulation is an emergency regulation that must be issued immediately to correct an unsafe condition in aircraft, and is not a ``significant regulatory action'' under Executive Order 12866. It has been determined further that this action involves an emergency regulation under DOT Regulatory Policies and Procedures (44 FR 11034, February 26, 1979). If it is determined that this emergency regulation otherwise would be significant under DOT Regulatory Policies and Procedures, a final regulatory evaluation will be prepared and placed in the Rules Docket. A copy of it, if filed, may be obtained from the Rules Docket at the location provided under the caption ADDRESSES. List of Subjects in 14 CFR Part 39 Air transportation, Aircraft, Aviation safety, Incorporation by reference, Safety. Adoption of the Amendment Accordingly, pursuant to the authority delegated to me by the Administrator, the Federal Aviation Administration amends part 39 of the Federal Aviation Regulations (14 CFR part 39) as follows: PART 39--AIRWORTHINESS DIRECTIVES 1. The authority citation for part 39 continues to read as follows: Authority: 49 U.S.C. App. 1354(a), 1421 and 1423; 49 U.S.C. 106(g); and 14 CFR 11.89. Sec. 39.13 [Amended] 2. Section 39.13 is amended by adding the following new airworthiness directive: 95-12-19 Pratt & Whitney: Amendment 39-9270. Docket 95-ANE-20. Applicability: Pratt & Whitney (PW) Models JT8D-209, -217, - 217A, -217C, and -219 turbofan engines that have installed fan blades, Part Numbers 798821, 798821-001, 808121, 808121-001, 809221, 811821, 851121, 851121-001, 5000021-02, 5000021-022, and 5000021- 032. These engines are installed on but not limited to McDonnell Douglas MD-80 series aircraft. Note: 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 use the authority provided in paragraph (b) to request approval from the FAA. This approval may address either no action, if the current configuration eliminates the unsafe condition, or different actions necessary to address the unsafe condition described in this AD. Such a request should include an assessment of the effect of the changed configuration on the unsafe condition addressed by this AD. In no case does the presence of any modification, alteration, or repair remove any engine from the applicability of this AD. Compliance: Required as indicated, unless accomplished previously. To prevent fan blade failure, which can result in damage to the aircraft, accomplish the following: (a) Inspect fan blades and shrouds, unlock fan blade shrouds, and lubricate fan blade shrouds, in accordance with the intervals and procedures described in Parts 1 and 2 of PW All Operators Wire (AOW) No. JT8D/72-33/CTS: CRC-5-4-5-1, dated April 5, 1995. (b) 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: Information concerning the existence of approved alternative methods of compliance with this airworthiness directive, if any, may be obtained from the Engine Certification Office. (c) 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. (d) The requirements of this AD shall be done in accordance with the following service document: ------------------------------------------------------------------------ Document no. Pages Date ------------------------------------------------------------------------ PW AOW No. JT8D/72-33/CTS: CRC-5-4-5-1...... 1-5 April 5, 1995. Total pages: 5. ------------------------------------------------------------------------ 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 Pratt & Whitney, 400 Main St., East Hartford, CT 06108. Copies may be inspected at the FAA, New England Region, Office of the Assistant Chief Counsel, 12 New England Executive Park, Burlington, MA; or at the Office of the Federal Register, 800 North Capitol Street NW., suite 700, Washington, DC. (e) This amendment becomes effective on June 30, 1995. Issued in Burlington, Massachusetts, on June 5, 1995. Ronald L. Vavruska, Acting Manager, Engine and Propeller Directorate, Aircraft Certification Service. [FR Doc. 95-14638 Filed 6-13-95; 9:16 am] BILLING CODE 4910-13-U