[Federal Register Volume 67, Number 143 (Thursday, July 25, 2002)]
[Proposed Rules]
[Pages 48577-48579]
From the Federal Register Online via the Government Publishing Office [www.gpo.gov]
[FR Doc No: 02-18816]


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DEPARTMENT OF TRANSPORTATION

Federal Aviation Administration

14 CFR Part 39

[Docket No. 2001-NE-11-AD]
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: Notice of proposed rulemaking (NPRM).

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SUMMARY: The Federal Aviation Administration (FAA) proposes to adopt 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 proposal would require removing weld repaired first stage 
compressor impellers from service. This proposal 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 the proposed AD are intended to 
prevent uncontained

[[Page 48578]]

engine failures, in-flight shutdowns, and secondary damage.

DATES: Comments must be received by September 23, 2002.

ADDRESSES: Submit comments in triplicate to the Federal Aviation 
Administration (FAA), New England Region, Office of the Regional 
Counsel, Attention: Rules Docket No. 2001-NE-11-AD, 12 New England 
Executive Park, Burlington, MA 01803-5299. Comments may be inspected at 
this location, by appointment, between 8 a.m. and 4:30 p.m., Monday 
through Friday, except Federal holidays. Comments may also be sent via 
the Internet using the following address: ``[email protected]''. 
Comments sent via the Internet must contain the docket number in the 
subject line. The service information referenced in the proposed rule 
may be obtained from Honeywell Engines, Systems and Services, Technical 
Data Distribution, M/S 2101-201, PO 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 FAA, New 
England Region, Office of the Regional 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, 3960 Paramount Blvd., Lakewood CA 90712-4137; telephone: 
(562) 627-5246; fax (562) 627-5210.

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 action 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 action must submit a self-addressed, 
stamped postcard on which the following statement is made: ``Comments 
to Docket Number 2001-NE-11-AD.'' The postcard will be date stamped and 
returned to the commenter.

Availability of NPRM's

    Any person may obtain a copy of this NPRM by submitting a request 
to the FAA, New England Region, Office of the Regional Counsel, 
Attention: Rules Docket No. 2001-NE-11-AD, 12 New England Executive 
Park, Burlington, MA 01803-5299.

Discussion

    On November 16, 1994, a TPE331-11U turboprop uncontained engine 
failure and in-flight shutdown occurred due to the separation of the 
first stage Ti 6-4 compressor impeller. The failed impeller, part 
number (P/N) 896223-3, which was weld repaired at 3,983 cycles-since-
new (CSN), had accumulated 27,456 CSN. The crack initiated in the 
backface at the fillet adjacent to the curvic arm and propagated 
forward along the bore in low cycle fatigue (LCF). Compressor 
impellers, P/N's 896223-1, -2, -3 and -7 and 3107109-2, are similarly 
designed to P/N 896223-3, and are affected by this proposal. The FAA 
has determined that weld repairs and the associated heat treatment on 
these impellers reduce LCF mechanical properties and may contribute to 
impeller failures. Failure of the first stage compressor impeller, if 
not corrected, could result in an uncontained separation of the 
impeller, in-flight shutdown and secondary engine and aircraft damage.

Manufacturer's Service Information

    The FAA has reviewed and approved the technical contents of 
Honeywell International Inc. Alert Service Bulletin (ASB) TPE331-A72-
2083, Revision 1, dated May 17, 2002, which provides a listing of 
certain impellers by serial number which have been weld repaired and 
provides impeller replacement information.

FAA's Determination of an Unsafe Condition and Proposed Actions

    Since an unsafe condition has been identified that is likely to 
exist or develop on other Honeywell International Inc TPE331-3, -5, -6, 
-8, -10, and -11 series turboprop and TSE331-3 series turboshaft 
engines of the same type design, the proposed AD would require the 
replacement of suspect impellers with serviceable impellers. The 
actions would be required to be done in accordance with the ASB 
described previously.

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 proposed 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 proposed 
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 proposed 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 
proposed AD on U.S. operators is estimated to be $10,108,000.

Regulatory Analysis

    This proposed 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 proposed rule.
    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.

[[Page 48579]]

The Proposed Amendment

    Accordingly, pursuant to the authority delegated to me by the 
Administrator, the Federal Aviation Administration proposes to amend 
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:

Honeywell International Inc.: 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 equipped with first stage compressor 
impeller, part number (P/N) 896223-1, -2, -3, -7, or 3107109-2. 
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 a 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) Remove impellers with 8,900 or less cycles since ``weld 
repair,'' before reaching 12,500 cycles since weld repair after the 
effective date of this AD.
    (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, Los Angeles ACO.

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


    Issued in Burlington, Massachusetts, on July 18, 2002.
Jay J. Pardee,
Manager, Engine and Propeller Directorate, Aircraft Certification 
Service.
[FR Doc. 02-18816 Filed 7-24-02; 8:45 am]
BILLING CODE 4910-13-P