[Federal Register Volume 65, Number 220 (Tuesday, November 14, 2000)]
[Rules and Regulations]
[Pages 68077-68078]
From the Federal Register Online via the Government Publishing Office [www.gpo.gov]
[FR Doc No: 00-28961]


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DEPARTMENT OF TRANSPORTATION

Federal Aviation Administration

14 CFR Part 39

[Docket No. 98-ANE-69-AD; Amendment 39-11982; AD 2000-23-12]
RIN 2120-AA64


Airworthiness Directives; CFE Company Model CFE738-1-1B Turbofan 
Engines

AGENCY: Federal Aviation Administration, DOT.

ACTION: Final rule.

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SUMMARY: This amendment adopts a new airworthiness directive (AD), 
applicable to CFE Company model CFE738-1-1B turbofan engines, that 
requires new life limits for certain HPC rotor components in all 
engines. This amendment is prompted by a reduction in the calculated 
service life of certain compressor rotor rotating parts to values below 
currently approved service lives. The actions specified by this AD are 
intended to prevent failure of certain HPC rotor components, which 
could result in an uncontained engine failure and damage to the 
airplane.

DATES: Effective January 16, 2001.

ADDRESSES: The rulemaking docket may be examined at the 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.

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: A proposal to amend part 39 of the Federal 
Aviation Regulations (14 CFR part 39) to include an airworthiness 
directive (AD) that is applicable to CFE Company Model CFE 738-1-1B 
turbofan engines was published in the Federal Register on December 14, 
1998 (63 FR 68707). Based on additional material stress testing, the 
FAA published a supplemental notice of proposed rule making (SNPRM) on 
September 23, 1999 (64 FR 51484). That SNPRM removed the proposal that 
would have required a dimensional inspection of the curvic couplings 
for parts that contain a machining mismatch and would have required 
those parts to be removed from service. That SNPRM, however, also 
introduced a requirement to remove parts prior to a new reduced cyclic 
life limit for specific high pressure compressor rotating parts. Since 
those changes expanded the scope of the originally proposed rule, the 
FAA determined that it was necessary to reopen the comment period. At 
the time the SNPRM was published, the manufacturer anticipated that the 
proposed reduced limits may be increased based upon further testing and 
analysis for the stage 4 and 5 blisk and impeller aft shaft.

Comments Received

    One comment was received. The manufacturer, using the data obtained 
from additional testing and analysis, and life analysis prediction 
techniques approved by the FAA, has requested that the cyclic life 
limits for the stage 4 and 5 blisk proposed in the published SNPRM be 
increased. This analysis showed that the life predictions of two of the 
three stage 4 and 5 blisk configurations met initial published part 
cyclic life requirements. The analysis showed that the life of the 
remaining stage 4 and 5 blisk configuration should be reduced from the 
previously approved cyclic life limit.
    The FAA agrees with the revised limits for the stage 4 and 5 blisk. 
This final rule has been revised accordingly by removing two of the 
stage 4 and 5 blisk configurations listed in the SNPRM and listing the 
recalculated cyclic life for the third stage 4 and 5 blisk 
configuration.
    In addition, reference to inspection work hours was removed from 
the economic analysis section. Inspection requirements for these parts 
were removed in the SNPRM, and are not applicable to this AD.

Economic Analysis

    There are approximately 245 engines of the affected design in the 
worldwide fleet. The FAA estimates that 156 engines would be affected 
by this proposed AD. Required parts, on a pro-rated basis, would cost 
approximately $13,613 per engine. Based on these figures, the total 
cost impact of the proposed AD on US operators is estimated to be 
$2,123628.

Regulatory Impact

    This 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

[[Page 68078]]

authorities prior to publication of this 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) 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 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.

Adoption of the 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.


Sec. 39.13  [Amended]

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

2000-23-12  CFE Company: Amendment 39-11982. Docket No. 98-ANE-69-
AD.

    Applicability: CFE Company Model CFE738-1-1B turbofan engines, 
installed on but not limited to the Dassault Aviation Falcon 2000 
series 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: Required as indicated, unless accomplished 
previously.
    To prevent failure of certain high pressure compressor
    (HPC) rotor components, which could result in an uncontained 
engine failure and damage to the airplane, accomplish the following:
    (a) Remove from service certain stage 4 and 5 blisks and 
impeller aft shafts prior to exceeding the new cyclic life limits as 
follows, and replace with serviceable parts:

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            Nomenclature                   Part No.  (P/N)                      Cyclic life limit
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Stage 4 and 5 Blisk.................  6079T74P08                6,700 cycles since new (CSN).
Impeller Aft Shaft..................  6079T80P04                5,100 CSN.
                                      6079T80P05                2,160 CSN.
                                      6079T80P06                7,100 CSN.
                                      6079T80P07                7,100 CSN.
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    (b) Except for the provisions of paragraph (c) of this AD, no 
parts, identified by P/N in paragraph (a) of this AD, that exceed 
the new life limits may be installed.

Alternative Methods 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 Manager, Engine Certification Office (ECO). 
Operators shall submit their requests 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.

Special Flight Permits

    (d) 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 airplane to a location where 
the requirements of this AD can be accomplished.

Effective Date of This AD

    (e) This amendment becomes effective on January 16, 2001.

    Issued in Burlington, Massachusetts, on November 6, 2000.
Donald Plouffe,
Acting Manager, Engine and Propeller Directorate, Aircraft 
Certification Service.
[FR Doc. 00-28961 Filed 11-13-00; 8:45 am]
BILLING CODE 4910-13-P