[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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Rules and Regulations
Federal Register
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to and codified in the Code of Federal Regulations, which is published
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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:
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Document No. Revision Pages Date
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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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