01-29947. Airworthiness Directives; CFE Company Model CFE738-1-1B 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 CFE Company Model CFE738-1-1B turbofan engines. This proposal would require replacing the high pressure turbine (HPT) stage 1 aft cooling plate and HPT stage 2 disk at or before they reach new reduced life cycle limits. This proposal is prompted by analysis of the existing life cycle limits by the engine manufacturer. The actions specified by the proposed AD are intended to prevent failure of the HPT stage 1 aft cooling plate and HPT stage 2 disk, which could result in an uncontained engine failure and damage to the airplane.

DATES:

Comments must be received by January 18, 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-04-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: “[e-mail]”. 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 [phone], fax [phone].

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 filed in 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 Docket Number 2001-NE-04-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-04-AD, 12 New England Executive Park, Burlington, MA 01803-5299.

Discussion

CFE Company, the manufacturer of the CFE738-1-1B turbofan engine, recently notified the FAA that it has updated its life limits for critical rotating parts based on data developed since the original certification of the engine. Based on that new data, the manufacture has reduced the predicted safe life limit of the HPT stage 1 aft cooling plates and the HPT stage 2 disks to below previously published values. There have not been any part failures reported, and no parts in the field currently exceed the new reduced limits. This condition, if not corrected, could result in failure of the HPT stage 1 aft cooling plate and HPT stage 2 disk due to exceeding the life limit.

FAA's Determination of an Unsafe Condition and Proposed Actions

Since an unsafe condition has been identified that is likely to exist or develop on other CFE Company model CFE738-1-1B turbofan engines of the same type design, the proposed AD would require replacing HPT stage 1 aft cooling plates, part number (P/N) 6083T38P07 before accumulating 3,500 cycles-since-new (CSN) and HPT stage 2 disks P/N's 6083T92P06, 6083T92P07, 6083T92P08, 6083T92P10, and 6083T92P11 before accumulating 2,700 CSN.

Economic Analysis

There are approximately 331 CFE Company model CFE738-1-1B turbofan engines of the affected design in the worldwide fleet. The FAA estimates that 247 engines installed on airplanes of U.S. registry would be affected by this proposed AD. The FAA also estimates that it would take approximately 450 work hours per engine to accomplish the proposed actions (225 work hours to replace the HPT stage 1 aft cooling plate and 225 work hours to replace the HPT stage 2 disk), and that the average labor rate is $60 per work hour. Required parts would cost approximately $32,170 per engine ($11,775 for the HPT stage 1 aft cooling plate and $20,395 for the HPT stage 2 disk). Based on these figures, the total cost impact of the proposed AD on U.S. operators is estimated to be $14,614,990.

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

1. The authority citation for part 39 continues to read as follows:

Authority: 49 U.S.C. 106(g), 40113, 44701.

§ 39.13

[Amended]

2. Section 39.13 is amended by adding the following new airworthiness directive:

CFE Company: Docket No. 2001-NE-04-AD.

Applicability

This airworthiness directive (AD) is applicable to CFE Company model CFE738-1-1B turbofan engines with high pressure turbine (HPT) stage 1 aft cooling plates, part number (P/N) 6083T38P07, and HPT stage 2 disks, P/N's 6083T92P06, 6083T92P07, 6083T92P08, 6083T92P10, and 6083T92P11, installed. These engines are installed on, but not limited to Dassault-Breguet Falcon 2000 series airplanes.

Note 1:

This 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

Compliance with this AD is required as indicated, unless already done.

To prevent failure of the HPT stage 1 aft cooling plate and HPT stage 2 disk due to exceeding the life limit, do the following:

(a) Replace the HPT stage 1 aft cooling plate at or before the cooling plate accumulates 3,500 cycles-since-new (CSN).

(b) Replace HPT stage 2 disks, P/N's 6083T92P06, 6083T92P07, 6083T92P08, 6083T92P10, and 6083T92P11; at or before the disk accumulates 2,700 CSN.

(c) After the effective date of this AD, do not install any HPT stage 1 aft cooling plate, P/N 6038T38P07, that exceeds 3,500 CSN.

(d) After the effective date of this AD, do not install any HPT stage 2 disk, P/N 6083T92P06, 6083T92P07, 6083T92P08, 6083T92P10, or 6083T92P11, that exceeds 2,700 CSN.

Alternative Methods of Compliance

(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 (ECO). Operators must submit their request through an appropriate FAA Principal Maintenance Inspector, who may add comments and then send it to the Manager, ECO.

Note 2:

Information concerning the existence of approved alternative methods of compliance with this airworthiness directive, if any, may be obtained from the ECO.

(f) Special flight permits may be issued in accordance 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.

Issued in Burlington, Massachusetts, on November 27, 2001.

Francis A. Favara,

Acting Manager, Engine and Propeller Directorate, Aircraft Certification Service.