[Federal Register Volume 68, Number 153 (Friday, August 8, 2003)]
[Proposed Rules]
[Pages 47267-47269]
From the Federal Register Online via the Government Publishing Office [www.gpo.gov]
[FR Doc No: 03-20231]


 ========================================================================
 Proposed Rules
                                                 Federal Register
 ________________________________________________________________________
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 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.
 
 ========================================================================
 

  Federal Register / Vol. 68, No. 153 / Friday, August 8, 2003 / 
Proposed Rules  

[[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: [email protected].
    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