Airworthiness directives: Royce plc,
[Federal Register: December 4, 2001 (Volume 66, Number 233)]
[Proposed Rules]
[Page 63009-63012]
From the Federal Register Online via GPO Access [wais.access.gpo.gov]
[DOCID:fr04de01-30]
DEPARTMENT OF TRANSPORTATION
Federal Aviation Administration
14 CFR Part 39
[Docket No. 2001-NE-36-AD]
RIN 2120-AA64
Airworthiness Directives; Rolls-Royce plc. Tay Model 650-15 and 651-54 Turbofan Engines
AGENCY: Federal Aviation Administration, DOT.
ACTION: Notice of proposed rulemaking (NPRM).
SUMMARY: The Federal Aviation Administration (FAA) proposes to adopt a new airworthiness directive (AD) that is applicable to Rolls-Royce plc. Tay Model 650-15 and 651-54 turbofan engines. This proposal would require revisions to the Airworthiness Limitations Section (ALS) of the Instructions for Continued Airworthiness (ICA) in the Time Limits Section of the Engine Manual for Rolls-Royce plc. Tay model 650-15 and 651-54 series turbofan engines to include required enhanced inspection of selected critical life-limited parts at each piece-part exposure. An FAA study of in-service events involving uncontained failures of critical rotating engine parts has indicated the need for mandatory inspections. The mandatory inspections are needed to identify those critical rotating parts with conditions, which if allowed to continue in service, could result in uncontained failures. The actions specified by this proposed AD are intended to prevent critical life-limited rotating engine part failure, which could result in an uncontained engine failure and damage to the airplane.
DATES: Comments must be received by February 4, 2002.
ADDRESSES: Submit comments in triplicate to the Federal Aviation Administration (FAA), New England Region, Office of the Regional Counsel, Attention: Rules Docket No.2001-NE-36-AD, 12 New England Executive Park, Burlington, MA 01803-5299. Comments may be inspected at this location, by appointment, between 8 a.m. and 4:30 p.m., Monday through Friday, except Federal holidays. Comments may also be sent via the Internet using the following address: 9-ane-adcomment@faa.gov. Comments sent via the Internet must contain the docket number in the subject line.
FOR FURTHER INFORMATION CONTACT: Keith Mead, Aerospace Engineer, Engine Certification Office, FAA, Engine and Propeller Directorate, 12 New England Executive Park, Burlington, MA 01803-5299; telephone (781) 238- 7744, fax (781) 238-7199.
SUPPLEMENTARY INFORMATION:
Comments Invited
Interested persons are invited to participate in the making of the proposed 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 above. All communications received on or before the closing date for comments, specified above, will be considered before taking action on the proposed rule. The proposals contained in this action may be changed in light of the comments received.
Comments are specifically invited on the overall regulatory, economic, environmental, and energy aspects of the proposed rule. All comments submitted will be available, both before and after the closing date for comments, in the Rules Docket for examination by interested persons. A report summarizing each FAA-public contact concerned with the substance of this proposal will be filedin the Rules Docket.
Commenters wishing the FAA to acknowledge receipt of their comments submitted in response to this action must submit a self-addressed, stamped postcard on which the following statement is made: ``Comments to
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Docket Number 2001-NE-36-AD.'' The postcard will be date stamped and returned to the commenter.
Availability of NPRM's
Any person may obtain a copy of this NPRM by submitting a request to the FAA, New England Region, Office of the Regional Counsel, Attention: Rules Docket No. 2001-NE-36-AD, 12 New England Executive Park, Burlington, MA 01803-5299.
Discussion
A recent FAA study analyzing 15 years of accident data for transport category airplanes identified several failure mode root causes that can result in serious safety hazards to transport category airplanes. This study identified uncontained failure of critical life- limited rotating engine parts as the leading engine-related safety hazard to airplanes. Uncontained engine failures have resulted from undetected cracks in rotating parts that initiated and propagated to failure. Cracks can originate from causes such as unintended excessive stress from the original design, or they may initiate from stresses induced from material flaws, handling, or damage from machining operations. The failure of rotating parts can present a significant safety hazard to the airplanes by release of high energy fragments that could injure passengers or crew by penetration of the cabin, damage flight control surfaces, sever flammable fluid lines, or otherwise compromise the airworthiness of the airplane.
Accordingly, the certifying authority responsible for the state of design for these engines, with FAA concurrence, has developed an intervention strategy to significantly reduce uncontained engine failures. This intervention strategy was developed after consultation with industry and will be used as a model for future initiatives. This intervention strategy is to conduct enhanced, nondestructive inspections of rotating parts which could most likely result in a safety hazard to the airplane in the event of a part fracture. The need for additional rule making is also being considered by the FAA. Future ADs may be issued introducing additional intervention strategies to further reduce or eliminate uncontained engine failures.
Properly focused enhanced inspections require identification of the parts whose failure presents the highest safety hazard to the airplane, identifying the most critical features to inspect on these parts, and utilizing inspection procedures and techniques that improve crack detection. The certifying authority, with close cooperation of the engine manufacturer, has completed a detailed analysis that identifies the most safety significant parts and features, and the most appropriate inspection methods.
Critical life-limited high energy rotating parts are currently subject to some form of recommended crack inspection when exposed during engine maintenance or disassembly. As a result of this AD, the inspections currently recommended by the manufacturer will become mandatory for those parts listed in the compliance section. Furthermore, the FAA intends that additional mandatory enhanced inspections resulting from this AD serve as an adjunct to the existing inspections. The FAA has determined that the enhanced inspections will significantly improve the probability of crack detection while the parts are disassembled during maintenance. All mandatory inspections must be conducted in accordance with detailed inspection procedures prescribed in the manufacturer's Engine Manual.
Additionally, this AD allows for air carriers operating under the provisions of 14 CFR part 121 with an FAA-approved continuous airworthiness maintenance program, and entities with whom those air carriers make arrangements to perform this maintenance, to verify performance of the enhanced inspections by retaining the maintenance records that include the inspections resulting from this AD, provided that the records include the date and signature of the person performing the maintenance action. These records must be retained with the maintenance records of the part, engine module, or engine until the task is repeated. This will establish a method of record preservation and retrieval typical to those in existing continuous airworthiness maintenance programs. Instructions must be included in an air carrier's maintenance manual providing procedures on how this record preservation and retrieval system will be implemented and integrated into the air carrier's record keeping system.
For engines or engine modules that are approved for return to service by an authorized FAA-certificated entity and that are acquired by an operator after the effective date of this AD, the mandatory enhanced inspections need not be done until the next piece-part opportunity. For example, there is no need for an operator to disassemble to piece-part level an engine or module returned to service by an FAA-certificated facility simply because that engine or module was previously operated by an entity not required to comply with this AD. Furthermore, the FAA intends for operators to perform the enhanced inspections of these parts at the next piece-part opportunity following the initial acquisition, installation, and removal of the part following the effective date of this AD. For piece parts that have not been approved for return to service prior to the effective date of this AD, the FAA does intend that the mandatory enhanced inspections required by this AD be performed before such parts are approved for return to service. Piece parts that have been approved for return to service prior to the effective date of this AD may be installed; however, enhanced inspection will be required at the next piece-part opportunity.
This proposal would require, within the next 30 days after the effective date of this AD, revisions to the Airworthiness Limitations Section (ALS) and Maintenance Scheduling Section (MSS) of the Instructions for Continued Airworthiness (ICA) (chapter 05-20-01-800- 001) of the Engine Manuals, as follows:
Rolls Royce plc. Tay model 650-15, and 651-54 series turbofan engines, respectively, and, for air carriers, the approved continuous airworthiness maintenance program. Rolls Royce plc., the manufacturer of Rolls Royce plc. Tay model 650-15, and 651-54 turbofan engines, used on 14 CFR part 25 airplanes, has provided the certifying authority, responsible for the state of design of these aircraft engines with a detailed proposal, with FAA concurrence, that identifies and prioritizes the critical life-limited rotating engine parts with the highest potential to hazard the airplane in the event of failure, along with instructions for enhanced, focused inspection methods. The enhanced inspections resulting from this AD will be conducted at piece- part opportunity, as defined below in the compliance section, rather than at specific time inspection intervals.
Proposed Requirements of This AD
Since an unsafe condition has been identified that is likely to exist or develop on other Rolls-Royce plc. Tay Model 650-15 and 651-54 turbofan engines of the same type design that are used on Boeing 727 and Fokker 100 airplanes registered in the United States, the proposed AD would require revisions to the Airworthiness Limitations Section (ALS) of the Instructions for Continued Airworthiness (ICA) in the Time Limits Manual of the Engine Manual for Rolls-Royce plc. Tay model 650- 15, and 651-54 series turbofan engines to include
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required enhanced inspection of selected critical life-limited parts at each piece-part exposure.
Economic Analysis
There are approximately 700 engines of the affected design in the worldwide fleet. The FAA estimates that 448 engines installed on aircraft of U.S. registry would be affected by this proposed AD. The FAA also estimates that it would take approximately twenty work hours per engine to accomplish the proposed inspections , and that the average labor rate is $60 per work hour. Since this is an added inspection requirement, included as part of the normal maintenance cycle, no additional part costs are involved. Based on these figures, the total cost impact of the proposed AD on U.S. operators is estimated to be $537,600.
Regulatory Impact
This proposed rule does not have federalism implications, as defined in Executive Order 13132, because it would not have a substantial direct effect 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. Accordingly, the FAA has not consulted with state authorities prior to publication of this proposed rule.
For the reasons discussed above, I certify that this proposed regulation (1) is not a ``significant regulatory action'' under Executive Order 12866; (2) is not a ``significant rule'' under the DOT Regulatory Policies and Procedures (44 FR 11034, February 26, 1979); and (3) if promulgated, will not have a significant economic impact, positive or negative, on a substantial number of small entities under the criteria of the Regulatory Flexibility Act. A copy of the draft regulatory evaluation prepared for this action is contained in the Rules Docket. A copy of it may be obtained by contacting the Rules Docket at the location provided under the caption ADDRESSES.
List of Subjects in 14 CFR Part 39
Air transportation, Aircraft, Aviation safety, Safety.
The Proposed Amendment
Accordingly, pursuant to the authority delegated to me by the Administrator, the Federal Aviation Administration proposes to amend part 39 of the Federal Aviation Regulations (14 CFR part 39) as follows:
PART 39--AIRWORTHINESS DIRECTIVES
-
The authority citation for part 39 continues to read as follows:
Authority: 49 U.S.C. 106(g), 40113, 44701.
Sec. 39.13 [Amended]
-
Section 39.13 is amended by adding the following new airworthiness directive:
Rolls-Royce, plc.: Docket No. 2001-NE-36-AD:
Applicability
This airworthiness directive (AD) is applicable to Rolls-Royce plc. Tay Model 650-15 and 651-54 turbofan engines. These engines are installed on, but not limited to Boeing 727 and Fokker 100 airplanes.
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 (c) 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
Compliance with this AD is required as indicated, unless already done. To prevent critical life-limited rotating engine part failure, which could result in an uncontained engine failure and damage to the airplane, accomplish the following:
(a) Within the next 30 days after the effective date of this AD, revise the Airworthiness Limitations Section (ALS) and Maintenance Scheduling Section (MSS) of the Instructions for Continued Airworthiness (ICA) in the Time Limits Manuals publication number (P/N) T-TAY-3RR, and T-TAY-5RR of the Engine Manuals, P/N E-TAY-3RR, and E-TAY-5RR as applicable, and for air carrier operations revise the approved continuous airworthiness maintenance program, by adding the following: ``GROUP A PARTS MANDATORY INSPECTION TASK 05-20-01- 800-001
(1) General: A full inspection of Group A Parts must be effected whenever the following conditions are satisfied.
(i) When the component has been completely disassembled to piece-part level in accordance with the appropriate disassembly procedures contained in the Engine Manual. and
(ii) The part has accumulated in excess of 100 flight cycles in service or since the last piece-part inspection. or
(iii) The component removal was for damage or a cause directly related to its removal.
(2) Mandatory inspections for individual Group A Parts are specified below: For time limits manual T-211(524)-7RR (reference engine manual M-211(524)-7RR) only, insert the following Table:
Inspected per overhaul Part nomenclature
Part No.
manual task
Low Pressure Compressor Rotor Disc............ All................................
72-31-11-200-000 I. P. Compressor Rotor--Stage 1 Disc.......... All................................
72-33-31-200--000 I. P. Compressor Rotor--Stage 2 Disc.......... All................................
72-33-32-200-000 I. P. Compressor Rotor--Stage 3 Disk.......... All................................
72-33-33-200-000 L. P. and I. P. Compressor Drive Shaft........ All................................
72-33-40-200-000 H. P. Compressor Rear Drive Shaft............. All................................
72-37-31-200-000 L. P. Compressor Rotor Drive Shaft............ All................................
72-37-32-200-002 H. P. Compressor Stage 1 Rotor Disc........... All................................
72-37-33-200-001 H. P. compressor Stages 2 and 3 Rotor Discs... All................................
72-37-33-200-002 H. P. Compressor Stages 4, 5, 6, and 7 Rotor All................................
72-37-34-200-000 Discs. H. P. Compressor Stages 8, 9, 10, and 11 Rotor All................................ 72-37-35-200-000/-001 Discs. H. P. Stage 12 Rotor Disc..................... All................................
72-37-36-200-001 H. P. Turbine Shaft........................... All................................
72-41-31-200-000 H. P. Stage 1 Rotor Disc...................... All................................
72-41-32-200-000 H. P. Turbine Stage 2 Rotor Disc.............. All................................
72-41-33-200-001 L. P. Turbine Shaft........................... All................................
72-52-21-200-003 L. P. Turbine Stage 1 Rotor Disc.............. All................................
72-52-22-200-000 L. P. Turbine Stage 2 Rotor Disc.............. All................................
72-52-23-200-000 L. P. Turbine Stage 3 Rotor Disc.............. All................................
72-52-24-200-000''
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(b) Except as provided in paragraph (c) of this AD, and notwithstanding contrary provisions in Sec. 43.16 of the Federal Aviation Regulations (14 CFR 43.16), these mandatory inspections shall be performed only in accordance with the TLM and applicable Engine Manual.
Alternative Method of Compliance
(c) 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 Engine Certification Office. Operators must submit their requests through an appropriate FAA Principal Maintenance Inspector (PMI), who may add comments and then send it to the 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.
(d) Special flight permits may be issued in accordance with Secs. 21.197 and 21.199 of the Federal Aviation Regulations (14 CFR 21.197 and 21.199) to operate the airplane to a location where the requirements of this AD can be accomplished.
(e) The records of the mandatory inspections required as a result of revising the TLM and the applicable Engine Manual and the air carrier's continuous airworthiness maintenance program as provided by paragraph (a) of this AD shall be maintained by FAA- certificated air carriers which have an approved continuous airworthiness maintenance program in accordance with the record keeping system currently specified in their manual required by Sec. 121.369 of the Federal Aviation Regulations (14 CFR 121.369); or, in lieu of the record showing the current status of each mandatory inspection required by Sec. 121.380(a)(2)(vi) of the Federal Aviation Regulations (14 CFR 121.380(a)(2)(vi)), certificated air carriers may establish an approved alternate system of record retention that provides a method for preservation and retrieval of the maintenance records that include the inspections resulting from this AD, and include the policy and procedures for implementing this alternate method in the air carrier's maintenance manual required by Sec. 121.369 (c) of the Federal Aviation Regulations (14 CFR 121.369 (c)); however, the alternate system must be accepted by the appropriate PMI and require the maintenance records be maintained either indefinitely or until the work is repeated.
Note 3: These record keeping requirements apply only to the records used to document the mandatory inspections required as a result of revising the ALS and the MSS of the Instructions for Continued Airworthiness in the Time Limits Manual (Chapter 05-10-00) of the Engine Manuals as provided in paragraph (a) of this AD, and do not alter or amend the record keeping requirements for any other AD or regulatory requirement.
Issued in Burlington, Massachusetts, on November 27, 2001. Francis A. Favara, Acting Manager, Engine and Propeller Directorate, Aircraft Certification Service.
[FR Doc. 01-29949Filed12-3-01; 8:45 am]
BILLING CODE 4910-13-U
