Federal Aviation Administration, DOT.
This amendment adopts a new airworthiness directive (AD), that is applicable to CFE Company Model CFE738-1-1B turbofan engines. This amendment requires 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 amendment is prompted by analysis of the existing life cycle limits by the engine manufacturer. The actions specified by this 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.
Effective date June 12, 2002.
Information regarding this action may be examined, by appointment, at the Federal Aviation Administration (FAA), New England Region, Office of the Regional 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.Start Further Info
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.End Further Info End Preamble Start Supplemental Information
A proposal to amend part 39 of the Federal Aviation Regulations (14 CFR part 39) to include an AD that is applicable to CFE Company Model CFE738-1-1B turbofan engines was published in the Federal Register on December 4, 2001 (66 FR 63008). That action proposed to require replacing the HPT stage 1 aft cooling plate and HPT stage 2 disk at or before they reach new reduced life cycle limits.
Interested persons have been afforded an opportunity to participate in the making of this amendment. Due consideration has been given to the comments received.
Create AD's for Limits
One commenter questions why the FAA has to create an AD for limits contained in maintenance manuals that are already FAA approved.
AD Issuance Not Required
Another commenter states that this AD is not necessary since all U.S operators must maintain these engines in accordance with Federal Aviation Regulations and manufacturers' recommendations. The commenter also points to section 91.409(e) of the Federal Aviation Regulations (14 CFR 91.409), which requires adherence to life limits established for the aircraft, engines, and other equipment, to say that the AD is not required.
The FAA disagrees with these comments. Life limits are established during the type certification process and initially published in the product's Airworthiness Limitation Section of the Instructions for Continued Airworthiness. The limits established at the time the type certificate is issued are the limits required to be followed by owners and operators until the FAA issues an AD to lower those limits. AD's that apply more restrictive life limits to products are issued when the original life limits contribute to an unsafe condition. Without an AD, unless owners and operators agree to lower life limits as part of a continuous airworthiness maintenance plan, owners and operators need not adhere to a reduction in a life limit appearing only in a revised manual, updated type certificate data sheet, or service document, even if those documents indicate they are FAA approved. After a product enters service the FAA oversees manufacturers, and, as in this instance, reviews analyses performed by the manufacturers of the life limits established at the time the type certificate was issued in order to determine if there is a need to make an adjustment to those limits. Therefore this AD is necessary. Start Printed Page 30775
The FAA comments that a typographical error exists in paragraph (c) of the proposal. Part number (P/N) 6038T38P07 is incorrect, and therefore is changed in the final rule to read P/N 6083T38P07.
After careful review of the available data, including the comments noted above, the FAA has determined that air safety and the public interest require the adoption of the rule with the indicated part number change.
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 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 of the AD on U.S. operators is estimated to be $14,614,990.
This final 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 final rule.
For the reasons discussed above, I certify that this action (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 final evaluation has been prepared for this action and it 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.Start List of Subjects
List of Subjects in 14 CFR Part 39End List of Subjects
Adoption of the AmendmentStart Amendment Part
Accordingly, pursuant to the authority delegated to me by the Administrator, the Federal Aviation Administration amends part 39 of the Federal Aviation Regulations (End Amendment Part Start Part
PART 39—AIRWORTHINESS DIRECTIVESEnd Part Start Amendment Part
1. The authority citation for part 39 continues to read as follows:End Amendment Part
2. Section 39.13 is amended by adding a new airworthiness directive to read as follows:End Amendment Part
2002-09-10 CFE Company: Amendment 39-12743. Docket No. 2001-NE-04-AD.
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.
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 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 P/N 6083T38P07 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 6083T38P07, 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.
Information concerning the existence of approved alternative methods of compliance with this airworthiness directive, if any, may be obtained from the ECO.
Special Flight Permits
(f) Special flight permits may be issued in accordance with §§ 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 done.
(g) This amendment becomes effective on June 12, 2002.Start Signature
Issued in Burlington, Massachusetts, on April 30, 2002.
Diane S. Romanosky,
Acting Manager, Engine and Propeller Directorate, Aircraft Certification Service.
[FR Doc. 02-11334 Filed 5-7-02; 8:45 am]
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