[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:

------------------------------------------------------------------------
  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.           
------------------------------------------------------------------------

    (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           
----------------------------------------------------------------------------------------------------------------
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]
BILLING CODE 4910-13-P