[Federal Register Volume 59, Number 234 (Wednesday, December 7, 1994)]
[Unknown Section]
[Page 0]
From the Federal Register Online via the Government Publishing Office [www.gpo.gov]
[FR Doc No: 94-28110]
[[Page Unknown]]
[Federal Register: December 7, 1994]
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DEPARTMENT OF TRANSPORTATION
Federal Aviation Administration
14 CFR Part 39
[Docket No. 93-ANE-39; Amendment 39-9066; AD 94-23-04]
Airworthiness Directives; Garrett Turbine Engine Company ATF3
Series 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 Garrett Turbine Engine Company ATF3 series turbofan
engines, that requires 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 amendment
is prompted by several reports of cracks discovered during routine
inspections of HPT rotor assembly disks. The actions specified by this
AD are intended to prevent an uncontained failure of the HPT rotor
assembly disk.
DATES: Effective on February 6, 1995.
The incorporation by reference of certain publications listed in
the regulations is approved by the Director of the Federal Register as
of February 6, 1995.
ADDRESSES: The service information referenced in this AD 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 Federal
Aviation Administration (FAA), New England Region, Office of the
Assistant Chief 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: 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: 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 Garrett Turbine Engine Company
Model ATF3-6 and -6A turbofan engines was published in the Federal
Register on February 11, 1994 (59 FR 6603). That action proposed to
require a one-time inspection for cracks of the curvic and bore area of
high pressure turbine (HPT) rotor assembly disks listed by serial
number 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.
Interested persons have been afforded an opportunity to participate
in the making of this amendment. No comments were received on the
proposal or the Federal Aviation Administration's (FAA) 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.
There are approximately 75 Garrett Turbine Engine Company Model
ATF3-6 and -6A turbofan engines of the affected design in the worldwide
fleet. The FAA estimates that 2 engines installed on aircraft of U.S.
registry will be affected by this AD, that it will take approximately
220 work hours per engine to accomplish the required actions, and that
the average labor rate is $55 per work hour. Based on these figures,
the total cost impact of the AD on U.S. operators is estimated to be
$24,200.
The regulations adopted herein will 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 final
rule does not have sufficient federalism implications to warrant the
preparation of a Federalism Assessment.
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 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 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. 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:
94-23-04 Garrett Turbine Engine Company: Amendment 39-9066. Docket
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
sections 21.197 and 21.199 of the Federal Aviation Regulations (14
CFR 21.197 and 21.199) to operate the aircraft to a location where
the requirements of this AD can be accomplished.
(e) The inspection, and replacement, if necessary, shall be done
in accordance with the following alert service bulletin:
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Document No. Pages Revision Date
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Allied-Signal Aerospace 1-6 1 Jan. 11, 1993.
Company, Garrett Engine
Division, ASB No. ATF3-A72-
6184.
Total Pages: 6.
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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 AlliedSignal Propulsion Engines,
Aviation Services Division, Data Distribution, Dept. 64-3/2102-1M,
P.O. Box 29003, Phoenix, AZ 85038-9003. Copies may be inspected at
the FAA, New England Region, Office of the Assistant Chief 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.
(f) This amendment becomes effective on February 6, 1995.
Issued in Burlington, Massachusetts, on November 3, 1994.
Jay J. Pardee,
Manager, Engine and Propeller Directorate, Aircraft Certification
Service.
[FR Doc. 94-28110 Filed 12-06-94; 8:45 am]
BILLING CODE 4910-13-P
