[Federal Register Volume 69, Number 91 (Tuesday, May 11, 2004)]
[Rules and Regulations]
[Pages 26022-26024]
From the Federal Register Online via the Government Publishing Office [www.gpo.gov]
[FR Doc No: 04-10241]


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DEPARTMENT OF TRANSPORTATION

Federal Aviation Administration

14 CFR Part 39

[Docket No. 2003-NE-02-AD; Amendment 39-13619; AD 2004-09-29]
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: Final rule.

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SUMMARY: The FAA is adopting a new airworthiness directive (AD) for 
Honeywell International Inc. (formerly AlliedSignal Inc., Garrett 
Turbine Engine Company, and AiResearch Manufacturing Company of 
Arizona) (Honeywell) TPE331-10 and -11 series turboprop engines with 
certain part numbers (P/Ns) and serial numbers (SNs) of first stage 
turbine disks. This AD requires initial and repetitive fluorescent 
penetrant inspections (FPIs) and eddy current inspections (ECIs) of the 
affected first stage turbine disks. This AD results from a report of a 
first stage turbine disk found cracked at the disk bore. The crack 
originated from a localized; melt related, low-alloy area of the disk. 
We are issuing this AD to prevent cracked first stage turbine disks 
from causing uncontained disk separation, resulting in engine damage 
and shutdown and damage to the airplane.

DATES: This AD becomes effective June 15, 2004. The Director of the 
Federal Register approved the incorporation by reference of certain 
publications listed in the regulations as of June 15, 2004.

ADDRESSES: You can 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, by appointment, at the FAA, New 
England Region, Office of the Regional Counsel, 12 New England 
Executive Park, Burlington, MA. You may examine the service 
information, at the FAA, New England Region, Office of the Regional 
Counsel, 12 New England Executive Park, Burlington, MA; or at the 
National Archives and Records Administration (NARA). For information on 
the availability of this material at NARA, call 202-741-6030, or go to: 
http://www.archives.gov/federal_register/code_of_federal_regulations/ibr_locations.html.

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: The FAA proposed to amend 14 CFR Part 39 
with a proposed airworthiness directive (AD). The proposed AD applies 
to Honeywell TPE331-10 and -11 series turboprop engines with certain P/
Ns and SNs of first stage turbine disks. We published the proposed AD 
in the Federal Register on August 8, 2003 (68 FR 47267). That action 
proposed to require:
     Initial and repetitive FPIs of the SNs of first stage 
turbine disks P/N 3101520-1, and
     Repetitive FPIs only of the disks P/N 3107079-1 listed in 
Table 1 of the Honeywell Alert Service Bulletin (ASB) TPE331-A72-2102, 
dated March 28, 2002, and
     An ECI on disks that pass the FPI.

Comments

    We provided the public the opportunity to participate in the 
development of this AD. We have considered the comments received.

Request To Clarify Relevant Service Information Section

    One commenter recommends that we clarify the Relevant Service 
Information Section of the NPRM to state that Honeywell ASB TPE331-A72-
2102, dated March 28, 2002, requires an initial FPI on disk P/Ns 
3101520-1 and 3107079-1 that are not installed in engines. The 
commenter believes that clarification of the Relevant Service 
Information is required to accurately reflect the Service Bulletin 
information. We agree. The section that the commenter is requesting us 
to change is not included in a final rule so there will not be any 
change to that section. However, we have changed the regulatory 
requirements to require performing an FPI before installation into the 
engine.

Question About Definition of Next Access

    The same commenter asks if the definition of next access includes 
parts before installation into the engine. The commenter states that 
disks that have already had an FPI and ECI may have been removed from 
another engine and may have accumulated substantial numbers of cycles 
before installation into an engine. We partially agree. We have changed 
the regulatory requirements to require performing an FPI of the disk 
before installation into an engine.

Addition of a Terminating Action

    We inadvertently left out a terminating action to the repetitive 
inspection requirements specified in this AD. We added the terminating 
action to the Regulatory text of the final rule.

Editorial Change To Clarify the Summary Section

    We made an editorial change to the Summary Section to the starting 
location of the crack in the disk bore. In addition, we added ``and 
damage to the airplane'' to the unsafe condition statement in the 
Summary and in the regulatory text.

Conclusion

    We have carefully reviewed the available data, including the 
comment[s] received, and determined that air safety and the public 
interest require adopting the AD with the changes described previously. 
We have determined that these changes will neither increase the 
economic burden on any operator nor increase the scope of the AD.

Changes to 14 CFR Part 39--Effect on the AD

    On July 10, 2002, the FAA published a new version of 14 CFR part 39 
(67 FR 47997, July 22, 2002), which governs the FAA's AD system. That 
regulation now includes material that relates to altered products, 
special flight permits, and alternative methods of compliance. The 
material previously was included in each individual AD. Since the 
material

[[Page 26023]]

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 will be affected by 
this AD. We estimate that it will take approximately 5 work hours per 
engine to perform the 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, we estimate the total cost of this AD to U.S. 
operators for disassembly, inspections, and part replacement to be 
$105,300.

Regulatory Findings

    We have determined that this AD will not have federalism 
implications under Executive Order 13132. This AD will 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 this AD:
    (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.
    We prepared a summary of the costs to comply with this AD 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, Incorporation by 
reference, Safety.

Adoption of the Amendment

0
Accordingly, under the authority delegated to me by the Administrator, 
the Federal Aviation Administration amends 14 CFR part 39 as follows:

PART 39--AIRWORTHINESS DIRECTIVES

0
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]

0
2. The FAA amends Sec.  39.13 by adding the following new airworthiness 
directive (AD):

2004-09-29 Honeywell International Inc. (formerly AlliedSignal Inc., 
Garrett Turbine Engine Company, and AiResearch Manufacturing Company 
of Arizona): Amendment 39-13619. Docket No. 2003-NE-02-AD.

Effective Date

    (a) This airworthiness directive (AD) becomes effective June 15, 
2004.

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, installed. 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 Jetstream 3201 series 
airplanes.

Unsafe Condition

    (d) This AD results from 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 from causing uncontained disk 
separation, resulting in engine damage and shutdown and damage to 
the airplane.

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 return 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.

Optional Terminating Action

    (h) Replacing a first stage turbine disk, that has a SN 
specified in this AD, with a disk that does not have a SN specified 
in this AD, is terminating action for the repetitive inspection 
requirements specified in paragraphs (g)(1) through (g)(2) of this 
AD.

Definition

    (i) For the purposes of this AD, next access is when the turbine 
wheel assembly is removed from the engine or before installation 
into an engine.

Alternative Methods of Compliance

    (j) The Manager, Los Angles Aircraft Certification Office, has 
the authority to approve alternative methods of compliance for this 
AD if requested using the procedures found in 14 CFR 39.19.

Material Incorporated by Reference

    (k) You must use Honeywell International Inc. ASB TPE331-A72-
2102, dated March 28, 2002 to perform the inspections required by 
this AD. The Director of the Federal Register approved the 
incorporation by reference of this service bulletin under 5 U.S.C. 
552(a) and 1 CFR part 51. You can get the service information 
identified in this AD from Honeywell Engines, Systems & Services, 
Technical Data Distribution, M/S 2101-201, P.O. Box 52170, Phoenix, 
AZ 85072-2170;

[[Page 26024]]

telephone: (602) 365-2493 (General Aviation); (602) 365-5535 
(Commercial); fax: (602) 365-5577 (General Aviation and Commercial). 
You may examine the service information, at the FAA, New England 
Region, Office of the Regional Counsel, 12 New England Executive 
Park, Burlington, MA; or at the National Archives and Records 
Administration (NARA). For information on the availability of this 
material at NARA, call 202-741-6030, or go to: http://www.archives.gov/federal_register/code_of_federal_regulations/ibr_locations.html.

Related Information

    (l) None.

    Issued in Burlington, Massachusetts, on April 28, 2004.
Jay J. Pardee,
Manager, Engine and Propeller Directorate, Aircraft Certification 
Service.
[FR Doc. 04-10241 Filed 5-10-04; 8:45 am]
BILLING CODE 4910-13-P