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

[Federal Register Volume 65, Number 4 (Thursday, January 6, 2000)]
[Rules and Regulations]
[Pages 691-692]
From the Federal Register Online via the Government Publishing Office [www.gpo.gov]
[FR Doc No: 00-133]



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Federal Register / Vol. 65, No. 4 / Thursday, January 6, 2000 / Rules 
and Regulations

[[Page 691]]


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DEPARTMENT OF TRANSPORTATION

Federal Aviation Administration

14 CFR Part 39

[Docket No. 99-NE-39-AD; Amendment 39-11497; AD 99-27-16]
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. This AD 
requires, on certain engines identified by serial numbers: a one-time 
visual inspection of Stage 2 high pressure turbine (HPT) aft cooling 
plates for nicks, dents, and scratches, and if present, dimensional 
inspection of indentation depth; repair, if indentation is within 
acceptable limits, and, if necessary, replacement with serviceable 
parts. This AD also requires inspection for raised metal on the Stage 2 
HPT rotor disk post aft surface that mates with the Stage 2 HPT aft 
cooling plate, and removal of the raised metal, if present. This 
amendment is prompted by reports of Stage 2 HPT aft cooling plates that 
were dented during the assembly of the cooling plate to the Stage 2 
disk due to raised metal on the stage 2 HPT disk post aft mating 
surface. The actions specified by this AD are intended to prevent aft 
HPT cooling plate failure, which could result in an uncontained engine 
failure and damage to the airplane.

DATES: Effective February 10, 2000.

    The incorporation by reference of certain publications listed in 
the regulations is approved by the Director of the Federal Register as 
of February 10, 2000.

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 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) to include an airworthiness 
directive (AD) that is applicable to certain CFE Company Model CFE738-
1-1B turbofan engines was published in the Federal Register on 
September 28, 1999 (64 FR 52259). That action proposed to require, on 
certain engines identified by serial numbers: a one-time visual 
inspection of Stage 2 high pressure turbine (HPT) aft cooling plates 
for nicks, dents, and scratches, and if present, dimensional inspection 
of indentation depth; repair, if indentation is within acceptable 
limits, and, if necessary, replacement with serviceable parts. This Ad 
also requires inspection for raised metal on the Stage 2 HPT rotor disk 
post aft surface that mates with the Stage 2 HPT aft cooling plate, and 
removal of the raised metal, if present. That action was prompted by 
reports of Stage 2 HPT aft cooling plates that were dented during the 
assembly of the cooling plate to the Stage 2 disk due to raised metal 
on the stage 2 HPT disk post aft mating surface. That condition, if not 
corrected, could result in aft HPT cooling plate failure, which could 
result in an uncontained engine failure and damage to the airplane.

No Comments Received

    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. The FAA 
has determined that air safety and the public interest require the 
adoption of the rule as proposed.

Economic Analysis


    There are approximately 72 engines of the affected design in the 
worldwide fleet. The FAA estimates that 48 engines installed on 
aircraft of US registry will be affected by this AD, that it will take 
approximately 4 work hours per engine to accomplish the required 
inspection if the inspection does not take place during scheduled 
maintenance, and that the average labor rate is $60 per work hour. 
Required parts cost approximately $1,536 per engine. Based on these 
figures, the total cost impact of the AD on US operators is estimated 
to be $106,560.

Regulatory Impact

    The regulations adopted herein will 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. Therefore, it 
is determined that this final rule does not have federalism 
implications under Executive Order (EO) 13132.

    For the reasons discussed above, I certify that this action (1) is 
not a ``significant regulatory action'' under EO 12866; (2) is not a 
``significant rule'' under 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 from 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

[[Page 692]]

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:

99-27-16  CFE Company: Amendment 39-11497. Docket 99-NE-39-AD.

    Applicability: CFE Model CFE738-1-1B turbofan engines, serial 
numbers (S/Ns) 105267 through 105339, inclusive. These engines are 
installed on but not limited to Dassault-Breguet Falcon 2000 series 
aircraft.

    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 (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: Required as indicated, unless accomplished 
previously.
    To prevent aft HPT cooling plate failure, which could result in 
an uncontained engine failure and damage to the airplane, accomplish 
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 4500 part cycles-since-new (CSN), accomplish the following in 
accordance with CFE Alert Service Bulletin (ASB) No. CFE738-A72-
8031, Revision 1, dated June 23, 1999, as follows:
    (1) Inspect the stage 2 HPT aft cooling plate for nicks, dents, 
and scratches on surface D in accordance with the requirements of 
ASB No. CFE738-A72-8031, paragraph 2.B.(1).
    (2) Repair those stage 2 HPT aft cooling plates with indentation 
less than 0.003 inch deep in accordance with ASB No. CFE738-A72-
8031. paragraph 2.B.(1).
    (3) Remove from service prior to further flight those stage 2 
HPT aft cooling plates that have nicks, dents, and/or scratches that 
exceed the acceptance limits in accordance with ASB No. CFE738-A72-
8031 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, 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 shall 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.

Ferry Flights

    (c) 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 inspection requirements of this AD can be accomplished.

Incorporation by Reference

    (d) The actions required by this AD shall be done in accordance 
with the following CFE ASB:

------------------------------------------------------------------------
         Document No.             Revision     Pages         Date
------------------------------------------------------------------------
CFE738-A72-8031..............  1............       1  June 23, 1999.
                               Original.....     2-5  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, P.O. , PO Box 29003 Phoenix, AZ 85038-9003; 
telephone (602) 365-2493, fax (602) 365-5577. Copies may be 
inspected 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.
    (e) This amendment becomes effective on February 10, 2000.

    Issued in Burlington, Massachusetts, on December 29, 1999.
Jay J. Pardee,
Manager, Engine and Propeller Directorate, Aircraft Certification 
Service.
[FR Doc. 00-133 Filed 1-5-00; 8:45 am]
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