[Federal Register Volume 63, Number 38 (Thursday, February 26, 1998)]
[Rules and Regulations]
[Pages 9732-9734]
From the Federal Register Online via the Government Publishing Office [www.gpo.gov]
[FR Doc No: 98-3798]
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DEPARTMENT OF TRANSPORTATION
Federal Aviation Administration
14 CFR Part 39
[Docket No. 97-ANE-13; Amendment 39-10327; AD 98-04-15]
RIN 2120-AA64
Airworthiness Directives; AlliedSignal Inc. TPE331 Series
Turboprop and TSE331 Turboshaft Engines
AGENCY: Federal Aviation Administration, DOT.
ACTION: Final rule.
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SUMMARY: This amendment adopts a new airworthiness directive (AD),
applicable to AlliedSignal Inc., (formerly Garrett Engine Division,
Garrett Turbine Engine Company and AiResearch Manufacturing Company of
Arizona) TPE331 series turboprop and TSE331 turboshaft engines, that
requires replacement or radiographic inspection, and replacement, if
necessary, of certain third stage turbine stators with serviceable
parts. This amendment is prompted by a report of an outer band weld
that cracked subsequent to a radiographic inspection required by a
previous AD. The actions specified by this AD are intended to prevent
third stage turbine wheel separation due to thermal fatigue cracking
and shifting of the third stage turbine stator, which could contact the
third stage turbine wheel and result in an uncontained engine failure
and damage to the aircraft.
DATES: Effective April 27, 1998.
The incorporation by reference of certain publications listed in
the regulations is approved by the Director of the Federal Register as
of April 27, 1998.
ADDRESSES: The service information on AlliedSignal Alert Service
Bulletin No. TPE331-A72-0861, Revision 2, dated April 23, 1997,
referenced in this rule may be obtained from AlliedSignal Aerospace,
Attn: Data Distribution, M/S 64-3/2101-201, P.O. Box 29003, Phoenix, AZ
85038-9003; telephone (602) 365-2493, fax (602) 365-5577. The service
information on National Flight Services Alert Service Bulletin No. NF-
TPE331-A72-10961, dated April 28, 1997, referenced in this rule may be
obtained from either National Flight Services, Inc. 10971 E. Airport
Services Road, Toledo Express Airport, Swanton, OH 43558; telephone
(419) 865-2311, fax (419) 867-4224, or http://www.natfs.com, or
National Flight Services of Arizona, Inc., 5170 W. Bethany Home Road,
Glendale, AZ 85301; telephone (602) 931-1143, fax (602) 931-7264. 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: Joseph Costa, Aerospace Engineer, Los
Angeles Aircraft Certification Office, FAA, Transport Airplane
Directorate, 3960 Paramount Blvd., Lakewood, CA 90712-4137; telephone
(562) 627-5246; fax (562) 627-5210.
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 AlliedSignal Inc., (formerly
Garrett Engine Division, Garrett Turbine Engine Company and AiResearch
Manufacturing Company of Arizona) TPE331 series turboprop and TSE331
turboshaft engines was published in the Federal Register on July 31,
1997 (62 FR 40985). That action proposed to require replacement of
certain third stage turbine stators or radiographic inspection, and
replacement, if necessary, with serviceable parts.
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.
There are approximately 1,000 engines of the affected design in the
worldwide fleet. The FAA estimates that 700 engines installed on
aircraft of U.S. registry will be affected by this AD. The FAA
estimates that 210 engines will require unscheduled replacement, that
it will take approximately 40 work hours per engine to accomplish the
required actions, and that the average labor rate is $60 per work hour.
Required parts will cost approximately $6,500 per engine. Approximately
350 engines will require replacement during hot section inspection,
which will take approximately 2 work hours per engine, with a parts
cost of $6,500. Approximately 14 engines will require unscheduled
inspection, which will take approximately 50 work hours to accomplish,
with a parts cost of $1,500. Approximately 21 engines will require
inspection during hot section inspection, which will take approximately
10 work hours to accomplish, with zero parts cost. Approximately 35
engines will require unscheduled inspection and replacement, which will
take approximately 50 work hours to accomplish, with a $6,500 parts
cost. Approximately 70 engines will require inspection and replacement
during hot section inspection, which will take approximately 10 work
hours to accomplish, with a $5,000 parts cost. The FAA has been
informed by AlliedSignal Inc. that they will provide a redesigned third
stage turbine stator assembly at a special program price and will pay
for the labor to install this assembly. Based on these figures, without
the special price program from the manufacturer, the total cost impact
of the AD on U.S. operators is estimated to be $4,986,100.
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
[[Page 9733]]
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. 106(g), 40113, 44701.
Sec. 39.13 [Amended]
2. Section 39.13 is amended by adding the following new
airworthiness directive:
98-04-15 AlliedSignal Inc.: Amendment 39-10327. Docket 97-ANE-13.
Applicability: AlliedSignal Inc., (formerly Garrett Engine
Division, Garrett Turbine Engine Company and AiResearch
Manufacturing Company of Arizona) Model TPE331-1, -2, -2UA, -3U, -
3UW, -5, -5A, -5AB, -5B, -6, and -6A turboprop and TSE331-3U
turboshaft engines with third stage turbine stators, Part Number (P/
N) 868379-3, except those engines with turbine stators listed by
Serial Number (S/N) in Table 1 of the National Flight Services Alert
Service Bulletin (ASB) No. NF-TPE331-A72-10961, dated April 28,
1997. These engines are installed on but not limited to: Mitsubishi
MU-2B series (MU-2 series); Construcciones Aeronauticas, S.A. (CASA)
C-212 series; Fairchild SA226 series (Swearingen Merlin and Metro
series); Prop-Jets, Inc. Model 400; Twin Commander 680 and 690
(Jetprop Commander); Rockwell Commander S-2R; Shorts Brothers and
Harland, Ltd. SC7 (Skyvan); Dornier 228 series; Beech 18 and 45
series and Models JRB-6, 3N, 3NM, 3TM, and B100; Pilatus PC-6 series
(Fairchild Porter and Peacemaker); De Havilland DH 104 series 7AXC
(Dove); Ayres S-2R series; Grumman American G-164 series; and
Schweizer G-164 series airplanes; and Sikorsky S-55 series (Helitec
Corp. S55T) helicopters.
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 (g) 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 third stage turbine wheel separation due to fatigue
cracking and shifting of the third stage turbine stator, which could
result in an uncontained engine failure and damage to the aircraft,
accomplish the following:
(a) For engines with third stage turbine stators with S/Ns
listed in Table 1 of National Flight Services ASB No. NF-TPE331-A72-
10961, dated April 28, 1997, no action is required.
(b) For engines with third stage turbine stators with S/Ns not
listed in Table 1 of National Flight Services ASB No. NF-TPE331-A72-
10961, dated April 28, 1997, remove the unserviceable third stage
turbine stator assembly in accordance with the applicable engine
maintenance manual and the following schedule:
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Third stage turbine stator
cycles in service (CIS) since
radiographic inspection in
accordance with AD 87-19-02 Removal schedule
paragraph (b) or AD 93-05-09
paragraph (h)
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Unknown CIS since inspection. Remove within 600 CIS after the effective
date of this AD, at next access, or
prior to March 31, 2002, whichever
occurs first.
2200 or more CIS since Remove within 600 CIS after the effective
inspection. date of this AD, at next access, or
prior to March 31, 2002, whichever
occurs first.
Less than 2200 CIS since Remove prior to accumulating 2,800 CIS,
inspection. at next access, or prior to March 31,
2002, whichever occurs first.
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(c) For the purpose of this AD, the next access to the third
stage stator assembly is defined as disassembly of the turbine
beyond the removal of the third stage rotor.
Note 2: This AD does not supersede AD 93-05-09. The removal
schedule in paragraph (b) of this AD does not affect the
requirements of AD 93-05-09.
(d) For the purpose of determining third stage turbine stator
removal under paragraph (b) of this AD, third stage turbine stator
hours time in service (TIS) may be converted to CIS since inspection
by multiplying by 1.5 the number of hours since radiographic
inspection in accordance with paragraph (b) of AD 87-19-02 or
paragraph (h) of AD 93-05-09.
(e) For third stage turbine stator assemblies removed in
accordance with paragraph (b) of this AD, accomplish either a
radiographic inspection for inadequate weld penetration and fatigue
cracking, and, if necessary, replace with a serviceable assembly in
accordance with the Accomplishment Instructions of National Flight
Services ASB No. NF-TPE331-A72-10961, dated April 28, 1997; or
replace with a serviceable assembly in accordance with the
Accomplishment Instructions of AlliedSignal Inc. ASB No. TPE331-A72-
0861, Revision 2, dated April 23, 1997. Accomplishing the
radiographic inspection required by this paragraph constitutes
compliance with the radiographic inspection requirement of paragraph
(h) of AD 93-05-09.
(f) 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. Operators shall submit their requests through an appropriate
FAA Principal Maintenance Inspector, who may add comments and then
send it to the Manager, Los Angeles Aircraft Certification Office.
Note 3: 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.
(g) 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.
(h) The actions required by this AD shall be done in accordance
with the following ASBs:
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Document No. Pages Revision Date
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National Flight Services ASB No. NF- 1-11 Original......................... Apr. 28, 1997.
TPE331-A72-10961.
Total Pages: 11.
AlliedSignal Inc. ASB No. TPE331- 1 2................................ Apr. 23, 1997.
A72-0861.
2 1................................ Oct. 25, 1996.
[[Page 9734]]
3-5 2................................ Apr. 23, 1997.
6 1................................ Oct. 25, 1996.
7 2................................ Apr. 23, 1997.
8 1................................ Oct. 24, 1996.
Total Pages: 8.
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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 of AlliedSignal Alert Service Bulletin No. TPE331-A72-
0861, Revision 2, dated April 23, 1997, may be obtained from
AlliedSignal Aerospace, Attn: Data Distribution, M/S 64-3/2101-201,
P.O. Box 29003, Phoenix, AZ 85038-9003; telephone (602) 365-2493,
fax (602) 365-5577. Copies of National Flight Services ASB No. NF-
TPE331-A72-10961, dated April 28, 1997, may be obtained from either
National Flight Services, Inc. 10971 E. Airport Services Road,
Toledo Express Airport, Swanton, OH 43558; telephone (419) 865-2311,
fax (419) 867-4224, or http://www.natfs.com, or National Flight
Services of Arizona, Inc., 5170 W. Bethany Home Road, Glendale, AZ
85301; telephone (602) 931-1143, fax (602) 931-7264. 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.
(i) This amendment becomes effective on April 27, 1998.
Issued in Burlington, Massachusetts, on February 6, 1998.
James C. Jones,
Assistant Manager, Engine and Propeller Directorate, Aircraft
Certification Service.
[FR Doc. 98-3798 Filed 2-25-98; 8:45 am]
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