[Federal Register Volume 67, Number 125 (Friday, June 28, 2002)]
[Rules and Regulations]
[Pages 43528-43530]
From the Federal Register Online via the Government Publishing Office [www.gpo.gov]
[FR Doc No: 02-16176]


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DEPARTMENT OF TRANSPORTATION

Federal Aviation Administration

14 CFR Part 39

[Docket No. 99-NE-39-AD; Amendment 39-12791; AD 99-27-16R1]
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 revises an existing airworthiness directive 
(AD), that is applicable to CFE Company Model CFE738-1-1B turbofan 
engines. That AD currently requires a one-time visual inspection of 
stage 2 high pressure turbine (HPT) aft cooling plates for nicks, 
dents, raised metal, and scratches, and if necessary, repair of the 
cooling plates or replacement with serviceable parts. This amendment 
reduces the number of stage 2 HPT aft cooling plates affected by AD 99-
27-16, and identifies the applicable engines by engine serial numbers 
(SN's). This amendment is prompted by an updated alert service bulletin 
(ASB) that reduces the number of stage 2 HPT aft cooling plates 
affected by AD 99-27-16 and identifies the applicable engines by engine 
SN's. The actions specified by this AD are intended to prevent stage 2

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HPT aft cooling plate failure, which could result in an uncontained 
engine failure and damage to the airplane.

DATES: Effective date August 2, 2002. The incorporation by reference of 
certain publications listed in the regulations is approved by the 
Director of the Federal Register as of August 2, 2002.

ADDRESSES: The service information referenced in this AD may be 
obtained from CFE Company, Data Distribution, MS 64-03/2101-201, PO Box 
29003, Phoenix, AZ 85038-9003; telephone (602) 365-2493, fax (602) 365-
5577. This information 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.

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) by revising AD 99-27-16, 
Amendment 39-11497 (65 FR 691, January 6, 2000), which is applicable to 
CFE Company model CFE738-1-1B turbofan engines, was published in the 
Federal Register on June 6, 2001 (66 FR 30341). That action proposed to 
reduce the number of stage 2 HPT aft cooling plates affected by AD 99-
27-16, and identifies the applicable engines by engine SN's, in 
accordance with CFE Company Alert Service Bulletin (ASB) No. CFE738-
A72-8031, Revision 2, dated October 17, 2000. Since the proposal was 
published, CFE Company has issued ASB No. CFE738-A72-8031, Revision 4, 
dated March 27, 2002, which includes the engine SN's that have the 
affected gas generator modules installed. This final rule references 
ASB Revision 4 instead of ASB Revision 2 which was referenced in the 
proposal.

Comments

    Interested persons have been afforded an opportunity to participate 
in the making of this amendment. No comments were received on the 
proposal or the FAA's determination of the cost to the public. After 
careful review of the available data, including the ASB reference 
change noted above, the FAA has determined that air safety and the 
public interest require the adoption of the rule with the change 
described previously. The FAA has determined that this change will 
neither increase the economic burden on any operator nor increase the 
scope of the AD.

Economic Analysis

    There are approximately ten engines of the affected design in the 
worldwide fleet. The FAA estimates that ten engines installed on 
airplanes of US registry would be affected by this AD, that it would 
take approximately four work hours per engine to accomplish the 
inspection if the inspection did not take place during scheduled 
maintenance, and that the average labor rate is $60 per work hour. 
Required parts would cost approximately $1,536 per engine. Based on 
these figures, the total cost of the AD on US operators is estimated to 
be $17,760.

Regulatory Analysis

    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) 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.

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. 106(g), 40113, 44701.


Sec. 39.13  [Amended]

    2. Section 39.13 is amended by removing Amendment 39-11497 (65 FR 
691, January 6, 2000) and by adding a new airworthiness directive, 
Amendment 39-12791, to read as follows:
99-27-16R1  CFE Company: Amendment 39-12791. Docket No. 99-NE-39-AD. 
Revises AD 99-27-16, Amendment 39-11497.

    Applicability: This airworthiness directive (AD) is applicable 
to CFE Model CFE738-1-1B turbofan engines, part number (P/N) 
3050000-5, with gas generator modules P/N 6091T09G01, serial numbers 
(SN's) 800421, 800422, 800423, 800424, 800425, 800426, 800427, 
800428, 800429, and 800430 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 (b) 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 stage 2 high pressure turbine (HPT) aft cooling plate 
failure, which could result in an uncontained engine failure and 
damage to the airplane, do the following:

Inspections and Follow-On Actions

    (a) At the next engine shop visit after the effective date of 
this AD where the HPT assembly is sufficiently disassembled to 
afford access to the stage 2 HPT aft cooling plate, but not later 
than 4,500 part cycles-since-new (CSN), do the following:
    (1) Inspect the stage 2 HPT aft cooling plate for nicks, dents, 
and scratches on surface D in accordance with the requirements of 
CFE Alert Service Bulletin (ASB) No. CFE738-A72-8031, Revision 4, 
dated March 27, 2002, paragraph 2.B.(1).
    (2) Repair those stage 2 HPT aft cooling plates with indentation 
0.003 inch deep or less in accordance with ASB No. CFE738-A72-8031, 
Revision 4, dated March 27, 2002, paragraph 2.B.(1).
    (3) Remove from service before further flight those stage 2 HPT 
aft cooling plates that have nicks, dents, and/or scratches that 
exceed the acceptance limits in accordance

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with ASB No. CFE738-A72-8031, Revision 4, dated March 27, 2002, 
paragraph 2.B.(1), and replace with serviceable parts.
    (4) Inspect the stage 2 HPT rotor disk post aft mating surface 
for raised metal, and remove raised metal if present in accordance 
with ASB No. CFE738-A72-8031, Revision 4, dated March 27, 2002, 
paragraph 2.B.(2).

Alternative Methods of Compliance

    (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 (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.

Special Flight Permits

    (c) 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 done.

Documents That Have Been Incorporated By Reference

    (d) The inspections and follow-on actions must be done in 
accordance with the following CFE Company Alert Service Bulletin 
(ASB):

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               Document No.                   Pages               Revision                       Date
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ASB CFE738-A72-8031......................            1  4..........................  March 27, 2002.
                                                   2-5  Original...................  May 17, 1999.
    Total pages: 5.......................
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    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 CFE Company, Data Distribution, 
MS 64-03/2101-201, PO Box 29003, Phoenix, AZ 85038-9003; telephone 
(602) 365-2493, fax (602) 365-5577. Copies may be inspected, by 
appointment, 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.

Effective Date

    (e) This amendment becomes effective on August 2, 2002.

    Issued in Burlington, Massachusetts, on June 17, 2002.
Jay J. Pardee,
Manager, Engine and Propeller Directorate, Aircraft Certification 
Service.
[FR Doc. 02-16176 Filed 6-27-02; 8:45 am]
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