[Federal Register Volume 59, Number 29 (Friday, February 11, 1994)]
[Unknown Section]
[Page 0]
From the Federal Register Online via the Government Publishing Office [www.gpo.gov]
[FR Doc No: 94-3237]
[[Page Unknown]]
[Federal Register: February 11, 1994]
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DEPARTMENT OF TRANSPORTATION
Federal Aviation Administration
14 CFR Part 39
[Docket No. 93-ANE-39]
Airworthiness Directives; Garrett Turbine Engine Company ATF3
Series Turbofan Engines
AGENCY: Federal Aviation Administration, DOT.
ACTION: Notice of proposed rulemaking (NPRM).
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SUMMARY: This document proposes the adoption of a new airworthiness
directive (AD) that is applicable to Garrett Turbine Engine Company
ATF3 series turbofan engines. This proposal would require a one-time
inspection for cracks of the curvic and bore area of the high pressure
turbine (HPT) rotor assembly disk, and replacement, if necessary, with
a serviceable disk. This proposal is prompted by several reports of
cracks discovered during routine inspections of HPT rotor assembly
disks. The actions specified by the proposed AD are intended to prevent
an uncontained failure of the HPT rotor assembly disk.
DATES: Comments must be received by April 12, 1994.
ADDRESSES: Submit comments in triplicate to the Federal Aviation
Administration (FAA), New England Region, Office of the Assistant Chief
Counsel, Attention: Rules Docket No. 93-ANE-39, 12 New England
Executive Park, Burlington, MA 01803-5299. Comments may be inspected at
this location between 8 a.m. and 4:30 p.m., Monday through Friday,
except Federal holidays.
The service information referenced in the proposed rule may be
obtained from AlliedSignal Propulsion Engines, Aviation Services
Division, Data Distribution, Dept. 64-3/2102-1M, P.O. Box 29003,
Phoenix, AZ 85038-9003. This information may be examined at the FAA,
New England Region, Office of the Assistant Chief Counsel, 12 New
England Executive Park, Burlington, MA.
FOR FURTHER INFORMATION CONTACT: Joseph Costa, Aerospace Engineer, Los
Angeles Aircraft Certification Office, FAA, Transport Airplane
Directorate, 3229 East Spring Street, Long Beach, CA 90806-2425;
telephone (310) 988-5246; fax (310) 988-5210.
SUPPLEMENTARY INFORMATION:
Comments Invited
Interested persons are invited to participate in the making of the
proposed rule by submitting such written data, views, or arguments as
they may desire. Communications should identify the Rules Docket number
and be submitted in triplicate to the address specified above. All
communications received on or before the closing date for comments,
specified above, will be considered before taking action on the
proposed rule. The proposals contained in this notice may be changed in
light of the comments received.
Comments are specifically invited on the overall regulatory,
economic, environmental, and energy aspects of the proposed rule. All
comments submitted will be available, both before and after the closing
date for comments, in the Rules Docket for examination by interested
persons. A report summarizing each FAA-public contact concerned with
the substance of this proposal will be filed in the Rules Docket.
Commenters wishing the FAA to acknowledge receipt of their comments
submitted in response to this notice must submit a self-addressed,
stamped postcard on which the following statement is made: ``Comments
to Docket Number 93-ANE-39.'' The postcard will be date stamped and
returned to the commenter.
Availability of NPRMs
Any person may obtain a copy of this NPRM by submitting a request
to the FAA, New England Region, Office of the Assistant Chief Counsel,
Attention: Rules Docket No. 93-ANE-39, 12 New England Executive Park,
Burlington, MA 01803-5299.
Discussion
The Federal Aviation Administration (FAA) has received reports of
cracks discovered during routine inspections of four high pressure
turbine (HPT) rotor assembly disks installed on Garrett Turbine Engine
Company Model ATF3-6 and -6A turbofan engines. The FAA has determined
that the cracks were created by a double strike forging and quench
process employed by a vendor in 1978. This process produced small
cracks in the curvic and bore area. These cracks became more prominent
during the forging and quenching operation and subsequently propagated
in fatigue during field service. Seventy five disks created using this
forging process have been identified by serial number in this
airworthiness directive (AD). This condition, if not corrected, could
result in an uncontained failure of the HPT rotor assembly disk.
The FAA has reviewed and approved the technical contents of Allied-
Signal Aerospace Company, Garrett Engine Division, Alert Service
Bulletin (ASB) No. ATF3-A72-6184, Revision 1, dated January 11, 1993,
that describes procedures for a one-time inspection for cracks of the
curvic and bore area of the HPT rotor assembly disk, and replacement,
if necessary, with a serviceable disk.
Since an unsafe condition has been identified that is likely to
exist or develop on other products of this same type design, the
proposed AD would require a one-time inspection for cracks of the
curvic and bore area of HPT rotor assembly disks listed by serial
number in Table 1 of Allied-Signal Aerospace Company, Garrett Engine
Division, ASB No. ATF3-A72-6184, Revision 1, dated January 11, 1993.
The actions would be required to be accomplished in accordance with the
service bulletin described previously.
There are approximately 75 engines of the affected design in the
worldwide fleet. The FAA estimates that 2 engines installed on aircraft
of U.S. registry would be affected by this proposed AD, that it would
take approximately 220 work hours per engine to accomplish the proposed
actions, and that the average labor rate is $55 per work hour. Based on
these figures, the total cost impact of the proposed AD on U.S.
operators is estimated to be $24,200.
The regulations proposed herein would not have substantial direct
effects 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, in
accordance with Executive Order 12612, it is determined that this
proposal would not have sufficient federalism implications to warrant
the preparation of a Federalism Assessment.
For the reasons discussed above, I certify that this proposed
regulation (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 copy of the draft
regulatory evaluation prepared for this action 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.
The Proposed Amendment
Accordingly, pursuant to the authority delegated to me by the
Administrator, the Federal Aviation Administration proposes to amend 14
CFR part 39 of the Federal Aviation Regulations as follows:
PART 39--AIRWORTHINESS DIRECTIVES
1. The authority citation for part 39 continues to read as follows:
Authority: 49 U.S.C. App. 1354(a), 1421 and 1423; 49 U.S.C.
106(g); and 14 CFR 11.89.
Sec. 39.13 [Amended]
2. Section 39.13 is amended by adding the following new
airworthiness directive:
Garrett Turbine Engine Company: Docket No. 93-ANE-39.
Applicability: Garrett Turbine Engine Company Model ATF3-6 and -
6A turbofan engines equipped with high pressure turbine (HPT) rotor
assembly disk, Part Number (P/N) 3001765-1 and -2, listed by serial
numbers in Table 1 of Allied-Signal Aerospace Company, Garrett
Engine Division, Alert Service Bulletin (ASB) No. ATF3-A72-6184,
Revision 1, dated January 11, 1993. These engines are installed on
but not limited to Dassault Aviation Falcon Jet Falcon Series G
(Falcon 20G/HU-25) and Mystere-Falcon 200 aircraft.
Compliance: Required as indicated, unless accomplished
previously.
To prevent an uncontained failure of the HPT rotor assembly
disk, accomplish the following:
(a) For engines with 1550 or more HPT rotor assembly disk cycles
since new (CSN) on the effective date of this AD, perform a one-time
inspection for cracks of the curvic and bore area of the HPT rotor
assembly disk, and replace if necessary, with a serviceable disk, in
accordance with Allied-Signal Aerospace Company, Garrett Engine
Division, ASB No. ATF3-A72-6184, Revision 1, dated January 11, 1993,
within 50 cycles in service (CIS) after the effective date of this
AD.
(b) For engines with less than 1550 HPT rotor assembly disk CSN
on the effective date of this AD, perform a one-time inspection for
cracks of the curvic and bore area of the HPT rotor assembly disk,
and replace if necessary, with a serviceable disk, in accordance
with Allied-Signal Aerospace Company, Garrett Engine Division, ASB
No. ATF3-A72-6184, Revision 1, dated January 11, 1993, within 300
CIS after the effective date of this AD, or prior to accumulating
1600 CSN, whichever occurs first.
(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, Los Angeles Aircraft Certification
Office. The request should be forwarded through an appropriate FAA
Principal Maintenance Inspector, who may add comments and then send
it to the Manager, Los Angeles Aircraft Certification Office.
Note: Information concerning the existence of approved
alternative methods of compliance with this airworthiness directive,
if any, may be obtained from the Los Angeles Aircraft Certification
Office.
(d) Special flight permits may be issued in accordance with FAR
21.197 and 21.199 to operate the airplane to a location where the
requirements of this AD can be accomplished.
Issued in Burlington, Massachusetts, on February 3, 1994.
Jay J. Pardee,
Manager, Engine and Propeller Directorate, Aircraft Certification
Service.
[FR Doc. 94-3237 Filed 2-10-94; 8:45 am]
BILLING CODE 4910-13-P
