FR Doc 04-10241

[Federal Register: May 11, 2004 (Volume 69, Number 91)]
[Rules and Regulations]
[Page 26022-26024]
From the Federal Register Online via GPO Access [wais.access.gpo.gov]
[DOCID:fr11my04-16]

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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]

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