[Federal Register Volume 67, Number 241 (Monday, December 16, 2002)]
[Rules and Regulations]
[Pages 76981-76982]
From the Federal Register Online via the Government Publishing Office [www.gpo.gov]
[FR Doc No: 02-31172]



 ========================================================================
 Rules and Regulations
                                                 Federal Register
 ________________________________________________________________________
 
 This section of the FEDERAL REGISTER contains regulatory documents 
 having general applicability and legal effect, most of which are keyed 
 to and codified in the Code of Federal Regulations, which is published 
 under 50 titles pursuant to 44 U.S.C. 1510.
 
 The Code of Federal Regulations is sold by the Superintendent of Documents. 
 Prices of new books are listed in the first FEDERAL REGISTER issue of each 
 week.
 
 ========================================================================
 

  Federal Register / Vol. 67, No. 241 / Monday, December 16, 2002 / 
Rules and Regulations  

[[Page 76981]]



DEPARTMENT OF TRANSPORTATION

Federal Aviation Administration

14 CFR Part 39

[Docket No. 2001-NE-11-AD; Amendment 39-12977; AD 2002-25-02]
RIN 2120-AA64


Airworthiness Directives; Honeywell International Inc. TPE331-3, 
-5, -6, -8, -10, and -11 Series Turboprop and TSE331-3 Series 
Turboshaft Engines

AGENCY: Federal Aviation Administration, DOT.

ACTION: Final rule.

-----------------------------------------------------------------------

SUMMARY: This amendment adopts a new airworthiness directive (AD), that 
is applicable to Honeywell International Inc. (formerly AlliedSignal 
Inc., Garrett Turbine Engine Company and AiResearch Manufacturing 
Company of Arizona) TPE331-3, -5, -6, -8, -10, and -11 series turboprop 
and TSE331-3 series turboshaft engines. This amendment requires 
removing weld repaired first stage compressor impellers from service. 
This amendment is prompted by an uncontained TPE331-11U turboprop 
engine failure and an in-flight shutdown due to the separation of the 
first stage Ti 6-4 compressor impeller. The actions specified by this 
AD are intended to prevent uncontained engine failures, in-flight 
shutdowns, and secondary damage.

DATES: Effective January 21, 2003. The incorporation by reference of 
certain publications listed in the regulations is approved by the 
Director of the Federal Register as of January 21, 2003.

ADDRESSES: The service information referenced in this AD may be 
obtained from Honeywell Engines, Systems and Services, Technical Data 
Distribution, M/S 2101-201, P.O. Box 52170, Phoenix, AZ 85072-2170; 
telephone: (602) 365-2493 (General Aviation), (602) 365-5535 
(Commercial); fax: (602) 365-5577 (General Aviation and Commercial). 
This information may be examined, by appointment, 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 AD that is 
applicable to Honeywell International Inc. (formerly AlliedSignal Inc., 
Garrett Turbine Engine Company and AiResearch Manufacturing Company of 
Arizona) TPE331-3, -5, -6, -8, -10, and -11 series turboprop and 
TSE331-3 series turboshaft engines was published in the Federal 
Register on July 25, 2002 (67 FR 48577). That action proposed to 
require removing weld repaired first stage compressor impellers from 
service, in accordance with Honeywell Alert Service Bulletin TPE331-
A72-2083, revision 1, dated May 17, 2002.

Comments

    Interested persons have been afforded an opportunity to participate 
in the making of this amendment. Due consideration has been given to 
the comment received.
    One commenter states that paragraph (a)(3) as-written in the 
proposal, implies that the 12,500 cycle limit applies only to weld 
repairs that would be performed after the effective date of the AD. The 
FAA agrees, and has moved the last phrase of that paragraph which 
states, after the effective date of the AD, to the beginning of the 
sentence, for clarity.
    After careful review of the available data, including the comment 
noted above, the FAA has determined that air safety and the public 
interest require the adoption of the rule with the change described 
previously. The FAA has determined that this change will neither 
increase the economic burden on any operator nor increase the scope of 
the AD.

Economic Analysis

    There are approximately 2,040 engines of the affected design in the 
worldwide fleet. The FAA estimates that 1,020 engines installed on 
aircraft of U.S. registry would be affected by this AD. The FAA 
estimates that 1,000 engines will have the required actions done during 
a scheduled engine overhaul. The FAA also estimates that it would take 
approximately 2 work hours per engine to do the actions during 
scheduled engine overhauls and 80 work hours per engine during 
unscheduled engine overhauls, and that the average labor rate is $60 
per work hour. Required parts would cost approximately $9,600 per 
engine to do the actions during scheduled engine overhauls and $14,600 
per engine which includes consumables, during unscheduled engine 
overhauls. Based on these figures, the total cost of the AD on U.S. 
operators is estimated to be $10,108,000.

Regulatory Analysis

    This final rule does not have federalism implications, as defined 
in Executive Order 13132, because it would 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. Accordingly, 
the FAA has not consulted with state authorities prior to publication 
of this final rule.
    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 the 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 
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, Incorporation by 
reference, Safety.

[[Page 76982]]

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 a new airworthiness directive 
to read as follows:

2002-25-02 Honeywell International Inc.: Amendment 39-12977. Docket 
No. 2001-NE-11-AD.

    Applicability: This airworthiness directive (AD) is applicable 
to Honeywell International Inc. (formerly AlliedSignal Inc., Garrett 
Turbine Engine Company and AiResearch Manufacturing Company of 
Arizona) TPE331-3, -5, -6, -8, -10, and -11 series turboprop and 
TSE331-3 series turboshaft engines. These engines are installed on, 
but not limited to Ayres S-2R series; Beech 18 and 45 series and 
Models JRB-6, 3N, 3NM, 3TM, and B100; Cessna Model 441; 
Construcciones Aeronauticas, S.A. (CASA) C-212 series; De Havilland 
DH 104 series 7AXC (Dove); Dornier 228 series; Fairchild SA226 and 
SA227 series (Swearingen Merlin and Metro series); Grumman American 
G-164 series; Jetstream 3101; Mitsubishi MU-2B series (MU-2 series); 
Prop-Jets, Inc. Model 400; Rockwell Commander S-2R; Shorts Brothers 
and Harland, Ltd. SC7 (Skyvan); Pilatus PC-6 series (Fairchild 
Porter and Peacemaker); and Schweizer G-164 series; and Twin 
Commander Aircraft Corp. (Jetprop Commander) Models 695 and 695A 
airplanes; and Sikorsky S-55 series (Helitec Corp. S55T) 
helicopters.

    Note 1: This 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 (c) 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: Compliance with this AD is required as indicated, 
unless already done.
    To prevent an uncontained engine failure, in-flight shutdown, 
and secondary damage, do the following:

Removal of Weld Repaired First Stage Compressor Impellers From Service

    (a) Remove from service weld repaired first stage compressor 
impellers, P/N's 896223-1, -2, -3, and -7 and 3107109-2, with SN's 
listed in Table 1 and Table 2 of the Accomplishment Instructions in 
2.A.(1) and 2.A.(2) of Honeywell Alert Service Bulletin TPE331-A72-
2083, revision 1, dated May 17, 2002, in accordance with the 
following schedule:
    (1) Remove impellers with no record of cycles since weld repair, 
within 3,600 cycles-in-service (CIS) or at the next engine overhaul, 
or at the next major Continuous Airworthiness Maintenance (CAM) 
compressor section inspection, after the effective date of this AD, 
whichever occurs first.
    (2) Remove impellers with more than 8,900 cycles since ``weld 
repair,'' within 3,600 CIS, or at the next engine overhaul, or at 
the next major CAM compressor section inspection after the effective 
date of this AD, whichever occurs first.
    (3) After the effective date of this AD, remove impellers with 
8,900 or less cycles since ``weld repair,'' before reaching 12,500 
cycles since weld repair.
    (b) For purposes of this AD, weld repaired or weld repair is 
defined as an impeller repair which involved heat treating and that 
was performed from 1980 through 1997 at Honeywell Aerospace 
Services, Aftermarket-Phoenix Repair and Overhaul, 1944 E. Sky 
Harbor Circle, Phoenix, AZ. 85034 (FAA Certificate Number ZN3R030M). 
Former names and FAA certificate numbers for Honeywell's Repair and 
Overhaul Facility are listed in section 2.A. of the Accomplishment 
Instructions in Honeywell Alert Service Bulletin TPE331-A72-2083, 
revision 1, dated May 17, 2002.

Alternative Methods of Compliance

    (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 (ACO). Operators must submit their request through an 
appropriate FAA Principal Maintenance Inspector, who may add 
comments and then send it to the Manager, Los Angeles ACO.

    Note 2: Information concerning the existence of approved 
alternative methods of compliance with this airworthiness directive, 
if any, may be obtained from the Los Angeles ACO.

Special Flight Permits

    (d) Special flight permits may be issued in accordance with 
Sec. Sec.  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 done.

Documents That Have Been Incorporated by Reference

    (e) The impeller removals must be done in accordance with 
Honeywell International Inc. Alert Service Bulletin TPE331-A72-2083, 
revision 1, dated May 17, 2002. 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 
Honeywell Engines, Systems and Services, Technical Data 
Distribution, M/S 2101-201, P.O. Box 52170, Phoenix, AZ 85072-2170; 
telephone: (602) 365-2493 (General Aviation), (602) 365-5535 
(Commercial); fax: (602) 365-5577 (General Aviation and Commercial). 
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.

Effective Date

    (f) This amendment becomes effective on January 21, 2003.

    Issued in Burlington, Massachusetts, on December 2, 2002.
Jay J. Pardee,
Manager, Engine and Propeller Directorate, Aircraft Certification 
Service.
[FR Doc. 02-31172 Filed 12-13-02; 8:45 am]
BILLING CODE 4910-13-P