[Federal Register: August 8, 2003 (Volume 68, Number 153)]
[Proposed Rules]
[Page 47267-47269]
From the Federal Register Online via GPO Access [wais.access.gpo.gov]
[DOCID:fr08au03-29]
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Proposed Rules
Federal Register
________________________________________________________________________
This section of the FEDERAL REGISTER contains notices to the public of
the proposed issuance of rules and regulations. The purpose of these
notices is to give interested persons an opportunity to participate in
the rule making prior to the adoption of the final rules.
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[[Page 47267]]
DEPARTMENT OF TRANSPORTATION
Federal Aviation Administration
14 CFR Part 39
[Docket No. 2003-NE-02-AD]
RIN 2120-AA64
Airworthiness Directives; Honeywell International Inc. (formerly
AlliedSignal Inc., Garrett Turbine Engine Company, and AiResearch
Manufacturing Company of Arizona) TPE331-10 and -11 Series Turboprop
Engines
AGENCY: Federal Aviation Administration (FAA), DOT.
ACTION: Notice of proposed rulemaking (NPRM).
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SUMMARY: The FAA is proposing to adopt a new airworthiness directive
(AD) that applies to Honeywell International Inc. (formerly
AlliedSignal Inc., Garrett Turbine Engine Company, and AiResearch
Manufacturing Company of Arizona) TPE331-10 and -11 series turboprop
engines with certain part numbers and serial numbers of first stage
turbine disks. This proposal would require initial and repetitive
fluorescent penetrant inspections (FPIs) and eddy current inspections
(ECIs) of the affected first stage turbine disks. This proposal is
prompted by a report of a first stage turbine disk found cracked at the
disk bore. We are proposing this AD to prevent cracked first stage
turbine disks from causing uncontained disk separation, resulting in
engine damage and shutdown.
DATES: We must receive any comments on this proposed AD by October 7,
2003.
ADDRESSES: Use one of the following addresses to submit comments on
this proposed AD:
[sbull] By mail: Federal Aviation Administration (FAA), New England
Region, Office of the Regional Counsel, Attention: Rules Docket No.
2003-NE-02-AD, 12 New England Executive Park, Burlington, MA 01803-
5299.
[sbull] By fax: (781) 238-7055.
[sbull] By e-mail: 9-ane-adcomment@faa.gov. You may get the service information identified in this proposed AD
from Honeywell Engines, Systems & 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).
You may examine the AD docket 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
We invite you to submit any written relevant data, views, or
arguments regarding this proposal. Send your comments to an address
listed under ADDRESSES. Include ``AD Docket No. 2003-NE-02-AD'' in the
subject line of your comments. If you want us to acknowledge receipt of
your mailed comments, send us a self-addressed, stamped postcard with
the docket number written on it; we will date-stamp your postcard and
mail it back to you. We specifically invite comments on the overall
regulatory, economic, environmental, and energy aspects of the proposed
AD. If a person contacts us through a nonwritten communication, and
that contact relates to a substantive part of this proposed AD, we will
summarize the contact and place the summary in the docket. We will
consider all comments received by the closing date and may amend the
proposed AD in light of those comments.
We are reviewing the writing style we currently use in regulatory
documents. We are interested in your comments on whether the style of
this document is clear, and your suggestions to improve the clarity of
our communications that affect you. You may get more information about
plain language at http://www.plainlanguage.gov.
Examining the AD Docket
You may examine the AD Docket (including any comments and service
information), by appointment, between 8 a.m. and 4:30 p.m., Monday
through Friday, except Federal holidays. See ADDRESSES for the
location.
Discussion
On October 23, 2001, the FAA received a report of a first stage
turbine disk, part number (P/N) 3101520-1, found cracked in the bore
area. The manufacturer's investigation verified that the crack
originated from a localized, melt related, low alloy area of the disk.
The manufacturer has determined that certain serial numbers (SNs) of P/
N 3101520-1 first stage turbine disks, produced from the same forging
billet, may also contain localized, melt related, low alloy areas. Some
of the P/N 3101520-1 disks produced from this same forging billet were
later converted to P/N 3107079-1 first stage turbine disks. Therefore,
certain SNs of P/N 3107079-1 first stage turbine disks also may contain
localized, melt related, low alloy areas. At the time of conversion,
however, P/N 3107079-1 first stage turbine disks received an initial
FPI and ECI, so these disks only require repetitive inspections. This
condition, if not corrected, could result in uncontained disk
separation, resulting in engine damage and shutdown.
Relevant Service Information
We have reviewed and approved the technical contents of Honeywell
International Inc. Alert Service Bulletin (ASB) TPE331-A72-2102, dated
March 28, 2002, that describes procedures for initial and repetitive
FPI of the SNs of first stage turbine disks, P/N 3101520-1, and for
only repetitive FPI of the SNs of disks, P/N 3107079-1 listed in Table
1 of the ASB. For disks that pass FPI, the ASB also requires that those
disks pass ECI.
FAA's Determination and Requirements of the Proposed AD
We have evaluated all pertinent information and identified an
unsafe condition that is likely to exist or develop on other products
of this same type design. Therefore, we are proposing this AD, which
would require initial and repetitive FPIs of the SNs of first stage
turbine disks P/N 3101520-1,
[[Page 47268]]
and only repetitive FPIs of the disks P/N 3107079-1 listed in Table 1
of the ASB, and for disks that pass FPI, perform an ECI. The proposed
actions would be required to be done in accordance with the ASB
described previously.
Changes to 14 CFR Part 39--Effect on the Proposed AD
On July 10, 2002, we published a new version of 14 CFR part 39 (67
FR 47997, July 22, 2002), which governs the FAA's AD system. This
regulation now includes material that relates to altered products,
special flight permits, and alternative methods of compliance. This
material previously was included in each individual AD. Since this
material is included in 14 CFR part 39, we will not include it in
future AD actions.
Costs of Compliance
There are approximately 72 TPE331-10 and -11 series turboprop
engines of the affected design in the worldwide fleet. We estimate that
36 engines installed on airplanes of U.S. registry would be affected by
this proposed AD. We estimate that it would take approximately 5 work
hours per engine to perform the proposed disk inspections during a
scheduled disassembly, and 40 work hours per engine to perform the
proposed disk inspections for an unscheduled disassembly. The average
labor rate is $65 per work hour. Required parts would cost
approximately $5,000 per engine. Based on these figures, the total cost
of the proposed AD to U.S. operators for disassembly, inspections, and
part replacement is estimated to be $105,300.
Regulatory Findings
We have determined that this proposed AD would not have federalism
implications under Executive Order 13132. This proposed AD 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.
For the reasons discussed above, I certify that the 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. Would not have a significant economic impact, positive or
negative, on a substantial number of small entities under the criteria
of the Regulatory Flexibility Act.
We prepared a summary of the costs to comply with this proposal and
placed it in the AD Docket. You may get a copy of this summary by
sending a request to us at the address listed under ADDRESSES. Include
``AD Docket No. 2003-NE-02-AD'' in your request.
List of Subjects in 14 CFR Part 39
Air transportation, Aircraft, Aviation safety, Safety.
The Proposed Amendment
Accordingly, under the authority delegated to me by the
Administrator, the Federal Aviation Administration proposes to amend 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. The FAA amends Sec. 39.13 by adding the following new
airworthiness directive:
Honeywell International Inc. (formerly AlliedSignal Inc., Garrett
Turbine Engine Company and AiResearch Manufacturing Company of
Arizona): Docket No. 2003-NE-02-AD.
Comments Due Date
(a) The FAA must receive comments on this airworthiness
directive (AD) action by October 7, 2003.
Affected ADs
(b) None.
Applicability
(c) This AD applies to Honeywell International Inc. (formerly
AlliedSignal Inc., Garrett Turbine Engine Company and AiResearch
Manufacturing Company of Arizona) TPE331-10-501C, -10-511C, -10-
501K, -10-511K, -10-501M, -10-511M, -10AV-511B, -10AV-511M, -10GP-
511D, -10GT-511D, -10N-511S, -10N-512S, -10N-513S, -10N-514S, -10N-
515S, -10N-531S, -10N-532S, -10N-533S, -10N-534S, -10N-535S, -10P-
511D, -10R-501C, -10R-502C, -10R-511C, -10R-512C, -10R-513C, -10T-
511D, -10T-511K, -10T-511M, -10T-512K, -10T-513K, -10T-515K, -10T-
516K, -10T-517K, -10U-501G, -10U-502G, -10U-511G, -10U-512G, -10U-
503G, -10U-513G, -10UA-511G, -10UF-501H, -10UF-511H, -10UF-512H, -
10UF-513H, -10UF-514H, -10UF-515H, -10UF-516H, -10UG-513H, -10UG-
514H, -10UG-515H, -10UG-516H, -10UGR-513H, -10UGR-514H, -10UGR-516H,
-10UR-513H, -10UR-516H, -11U-601G, -11U-602G, -11U-611G, and -11U-
612G turboprop engines with first stage turbine disk part number (P/
N) 3101520-1 or P/N 3107079-1, with serial numbers (SNs) listed in
Table 1 of Honeywell International Inc. Alert Service Bulletin (ASB)
TPE331-A72-2102, dated March 28, 2002. These engines are installed
on, but not limited to Mitsubishi MU-2B series, Construcciones
Aeronauticas S.A. (CASA) C-212 series, Fairchild SA226 series
(Swearingen Merlin and Metro series), Twin Commander 680 and 690
series (Jetprop Commander), Dornier 228 series, Beech 18 and 45
series, Beech Models JRB-6, 3N, 3TM, and B100, Cessna Aircraft
Company Model 441 Conquest, and Jetsteam 3201 series airplanes.
Unsafe Condition
(d) This AD is prompted by a report of a first stage turbine
disk found cracked at the disk bore. We are issuing this AD to
prevent cracked first stage turbine disks, part number (P/N)
3101520-1 or P/N 3107079-1, with serial numbers listed in Table 1 of
Honeywell International Inc. ASB TPE331-A72-2102, dated March 28,
2002, from causing uncontained disk separation, resulting in engine
damage and shutdown.
Compliance
(e) You are responsible for having the actions required by this
AD performed within the compliance times specified unless the
actions have already been done.
Initial Inspection
(f) Perform a fluorescent penetrant inspection (FPI) of first
stage turbine disks, P/N 3101520-1, in accordance with 2.A.(4)(a)
through 2.A.(4)(d) of Accomplishment Instructions of ASB TPE331-A72-
2102, dated March 28, 2002, and the following:
(1) For first stage turbine disks with 4,100 cycles-since-new
(CSN) or less, inspect at next access, but no later than 4,500 CSN.
(2) For first stage turbine disks with more than 4,100 CSN,
inspect at next access, but within 400 cycles-in-service (CIS) after
the effective date of this AD.
(3) First stage turbine disks that pass FPI must be eddy current
inspected (ECI) before they are returned to service. Information on
procedures for returning disks to Honeywell Engines, Systems, &
Services, for ECI, can be found in ASB TPE331-A72-2102, dated March
28, 2002.
(4) First stage turbine disks, P/N 3107079-1, do not require
initial inspection because they received an initial FPI and ECI at
the time of conversion.
Repetitive Inspections
(g) Perform repetitive FPIs of first stage turbine disks P/N
3101520-1 and P/N 3107079-1, in accordance with 2.B.(3)(a) through
2.B.(3)(d) of Accomplishment Instructions of ASB TPE331-A72-2102,
dated March 28, 2002 and the following:
(1) FPI first stage turbine disks at each scheduled hot section
inspection.
(2) First stage turbine disks that pass FPI must be ECI before
they are returned to service. Information on procedures for
returning disks to Honeywell Engines, Systems, & Services, for ECI,
can be found in ASB TPE331-A72-2102, dated March 28, 2002.
Definition
(h) For the purposes of this AD, next access is defined as when
the turbine wheel assembly is removed from the engine.
[[Page 47269]]
Alternative Methods of Compliance (AMOCs)
(i) You must request AMOCs as specified in 14 CFR part 39.19.
All AMOCs must be approved by the Manager, Los Angeles Aircraft
Certification Office, FAA.
Material Incorporated by Reference
(j) The FPIs must be done in accordance with Honeywell
International Inc. ASB TPE331-A72-2102, dated March 28, 2002.
Approval of incorporation by reference from the Office of the
Federal Register is pending.
Related Information
(k) None.
Issued in Burlington, Massachusetts, on August 1, 2003.
Francis A. Favara,
Acting Manager, Engine and Propeller Directorate, Aircraft
Certification Service.
[FR Doc. 03-20231 Filed 8-7-03; 8:45 am]
BILLING CODE 4910-13-P