Airworthiness Directives; Honeywell International Inc. TPE331-10 and TPE331-11 Series Turboprop Engines, 35354-35356 [2010-15068]

Download as PDF 35354 Federal Register / Vol. 75, No. 119 / Tuesday, June 22, 2010 / Proposed Rules principles and precedent for the award is required to be provided to the parties; (b) The language described in paragraph (a)(1) of this section shall immediately precede the following language, which must appear as follows on the signature page of the contract in bold conspicuous print: Right to Decline Arbitration. A poultry grower, livestock producer or swine production contract grower has the right to decline to be bound by the arbitration provision set forth in this agreement. A poultry grower, livestock producer or swine production contract grower shall indicate whether or not it desires to be bound by the arbitration provision by signing one of the following statements: I decline to be bound by the arbitration provisions set forth in this Agreement ________________________ ________________ I accept the arbitration provisions as set forth in this Agreement ___________ _____________________________ Failure to choose an option by signing one of the above renders the contract void. J. Dudley Butler, Administrator, Grain Inspection, Packers and Stockyards Administration. [FR Doc. 2010–14875 Filed 6–18–10; 11:15 am] BILLING CODE 3410–KD–P DEPARTMENT OF TRANSPORTATION Federal Aviation Administration 14 CFR Part 39 [Docket No. FAA–2009–0555; Directorate Identifier 2009–NE–18–AD] RIN 2120–AA64 Airworthiness Directives; Honeywell International Inc. TPE331–10 and TPE331–11 Series Turboprop Engines AGENCY: Federal Aviation Administration (FAA), DOT. ACTION: Notice of proposed rulemaking (NPRM). The FAA proposes to supersede an existing airworthiness directive (AD) for Honeywell International Inc. TPE331–10 and TPE331–11 series turboprop engines. That AD currently requires removing certain first stage turbine disks from service. This proposed AD would require the same actions, and would also require performing fluorescent penetrant inspections (FPI) and eddy current inspections (ECI) on certain first stage turbine disks that have a serial srobinson on DSKHWCL6B1PROD with PROPOSALS SUMMARY: VerDate Mar<15>2010 16:10 Jun 21, 2010 Jkt 220001 number (S/N) listed in this proposed AD. This proposed AD results from our determination that we need to expand the affected population to include other disks from the same heat lot as the failed first stage turbine disk, and that certain inspections are also required. We are proposing this AD to prevent uncontained failure of the first stage turbine disk and damage to the airplane. DATES: We must receive any comments on this proposed AD by August 23, 2010. ADDRESSES: Use one of the following addresses to comment on this proposed AD. • Federal eRulemaking Portal: Go to https://www.regulations.gov and follow the instructions for sending your comments electronically. • Mail: Docket Management Facility, U.S. Department of Transportation, 1200 New Jersey Avenue, SE., West Building Ground Floor, Room W12–140, Washington, DC 20590–0001. • Hand Delivery: Deliver to Mail address above between 9 a.m. and 5 p.m., Monday through Friday, except Federal holidays. • Fax: (202) 493–2251. FOR FURTHER INFORMATION CONTACT: Joseph Costa, Aerospace Engineer, Los Angeles Aircraft Certification Office, FAA, Transport Airplane Directorate, 3960 Paramount Blvd., Lakewood, CA 90712–4137; e-mail: joseph.costa@faa.gov; telephone (562) 627–5246; fax (562) 627–5210. SUPPLEMENTARY INFORMATION: Comments Invited We invite you to send any written relevant data, views, or arguments regarding this proposal. Send your comments to an address listed under ADDRESSES. Include ‘‘Docket No. FAA– 2009–0555; Directorate Identifier 2009– NE–18–AD’’ in the subject line of your comments. We specifically invite comments on the overall regulatory, economic, environmental, and energy aspects of the proposed AD. We will consider all comments received by the closing date and may amend the proposed AD in light of those comments. We will post all comments we receive, without change, to https:// www.regulations.gov, including any personal information you provide. We will also post a report summarizing each substantive verbal contact with FAA personnel concerning this proposed AD. Using the search function of the Web site, anyone can find and read the comments in any of our dockets, including, if provided, the name of the individual who sent the comment (or PO 00000 Frm 00017 Fmt 4702 Sfmt 4702 signed the comment on behalf of an association, business, labor union, etc.). You may review the DOT’s complete Privacy Act Statement in the Federal Register published on April 11, 2000 (65 FR 19477–78). Examining the AD Docket You may examine the AD docket on the Internet at https:// www.regulations.gov; or in person at the Docket Operations office between 9 a.m. and 5 p.m., Monday through Friday, except Federal holidays. The AD docket contains this proposed AD, the regulatory evaluation, any comments received, and other information. The street address for the Docket Operations office (telephone (800) 647–5527) is the same as the Mail address provided in the ADDRESSES section. Comments will be available in the AD docket shortly after receipt. Discussion The FAA proposes to amend 14 CFR part 39 by superseding AD 2009–17–05, Amendment 39–15996 (74 FR 41327, August 17, 2009). That AD requires removal from service of first stage turbine disks, P/Ns 3101520–1 and 3107079–1, serial numbers 2–03501– 2299, 2–03501–2300, 2–03501–2301, 2– 03501–2302, and 2–03501–2304, within 25 flight hours or 25 cycles-in-service (CIS) after the effective date of this AD, whichever occurs first. That AD was the result of a report of an uncontained failure of a first stage turbine disk that had a metallurgical defect. That condition, if not corrected, could result in uncontained failure of the first stage turbine disk and damage to the airplane. Actions Since AD 2009–17–05 was Issued Since that AD was issued, we determined that up to 360 other turbine disks have been produced from the same heat lot as the failed turbine disk and might have similar inclusions. These inclusions can result in cracks that could result in an uncontained separation of a turbine disks. Relevant Service Information We have reviewed and approved the technical contents of Honeywell International Inc. Alert Service Bulletin TPE331–72–A2156, dated December 2, 2008, that describes S/Ns of the affected turbine disks and procedures for initial and repetitive FPI and ECI of the first stage turbine disk. FAA’s Determination and Requirements of the Proposed AD We have evaluated all pertinent information and identified an unsafe E:\FR\FM\22JNP1.SGM 22JNP1 Federal Register / Vol. 75, No. 119 / Tuesday, June 22, 2010 / Proposed Rules condition that is likely to exist or develop on other products of this same type design. For that reason, we are proposing this AD, which would require: • For turbine disks that have a S/N listed in Table 1 of this proposed AD with 4,100 or fewer cycles-since-new (CSN) on the effective date of this proposed AD, performing an initial FPI and ECI within 4,500 CSN or at the next access, whichever occurs first. • For turbine disks that have a S/N listed in Table 1 of this proposed AD with more than 4,100 CSN on the effective date of this proposed AD, performing an initial FPI and ECI within 400 CIS after the effective date of this proposed AD or at the next access, whichever occurs first. • Thereafter, for turbine disks that have a S/N listed in Table 1 of this proposed AD, perform a repetitive FPI and ECI at each scheduled hot section inspection, but not to exceed 3,600 hours-since-last inspection. The proposed AD would require that you do these actions using the service information described previously. Costs of Compliance We estimate that this proposed AD would affect 90 engines installed on airplanes of U.S. registry. We also estimate that it would take about 20 work-hours per engine to perform the proposed actions, and that the average labor rate is $85 per work-hour. Required parts would cost about $19,000 per engine. We estimate that one disk would fail the initial inspection and that repetitive inspections would be performed on 89 engines. We estimate that one engine would fail the repetitive inspections and that further repetitive inspections would be performed on 88 engines. We estimate that an additional one disk would fail those repetitive inspections before retirement. Based on these figures, we estimate the total cost of the proposed AD to U.S. operators to be $511,155. Authority for This Rulemaking Title 49 of the United States Code specifies the FAA’s authority to issue rules on aviation safety. Subtitle I, Section 106, describes the authority of the FAA Administrator. Subtitle VII, Aviation Programs, describes in more detail the scope of the Agency’s authority. We are issuing this rulemaking under the authority described in Subtitle VII, Part A, Subpart III, Section 44701, ‘‘General requirements.’’ Under that section, Congress charges the FAA with promoting safe flight of civil aircraft in air commerce by prescribing regulations for practices, methods, and procedures the Administrator finds necessary for safety in air commerce. This regulation is within the scope of that authority because it addresses an unsafe condition that is likely to exist or develop on products identified in this rulemaking action. 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 AD: 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 regulatory evaluation of the estimated costs to comply with this proposed AD. See the ADDRESSES section for a location to examine the regulatory evaluation. List of Subjects in 14 CFR Part 39 Air transportation, Aircraft, Aviation safety, Incorporation by reference, Safety. 35355 The Proposed Amendment 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. § 39.13 [Amended] 2. The FAA amends § 39.13 by removing Amendment 39–15996 (74 FR 41327, August 17, 2009) and by adding a new airworthiness directive to read as follows: Honeywell International Inc. (formerly AlliedSignal Inc., Garrett Engine Division; Garrett Turbine Engine Company; and AiResearch Manufacturing Company of Arizona): Docket No. FAA–2009–0555; Directorate Identifier 2009–NE–18–AD. Comments Due Date (a) The Federal Aviation Administration (FAA) must receive comments on this airworthiness directive (AD) action by August 23, 2010. Affected ADs (b) This AD supersedes AD 2009–17–05, Amendment 39–15996. Applicability (c) This AD applies to Honeywell International Inc. TPE331–10 and TPE331–11 series turboprop engines with a first stage turbine disk, part number (P/N) 3101520–1 or 3107079–1, with a serial number (S/N) listed in Table 1 of this AD, installed. These engines are installed on, but not limited to, British Aerospace Jetstream 3201 series, Cessna Aircraft Company Model 441 Conquest, Construcciones Aeronauticas, S.A. (CASA) C–212 series, Dornier Luftfahrt Dornier 228 series, Hawker Beechcraft (formerly Raytheon, formerly Beech) B100, C90 and E90, M7 Aerospace (formerly Fairchild) SA226 and SA227 series (Swearingen Merlin and Metro series), Mitsubishi MU–2B series (MU–2 series), PZL M18 series, and Twin Commander 680 and 690 series (Jetprop Commander) airplanes. srobinson on DSKHWCL6B1PROD with PROPOSALS TABLE 1—FIRST STAGE TURBINE DISK S/NS Disk P/N Disk S/N 3101520–1 or 3107079–1 ............................................................................................................... VerDate Mar<15>2010 16:10 Jun 21, 2010 Jkt 220001 PO 00000 Frm 00018 Fmt 4702 Sfmt 4702 1–03501–4275 1–03501–4308 1–03501–4341 1–03501–4440 1–03501–4473 1–03501–4506 1–03501–4539 1–03501–4572 E:\FR\FM\22JNP1.SGM 22JNP1 thru thru thru thru thru thru thru thru 1–03501–4306 1–03501–4339 1–03501–4438 1–03501–4471 1–03501–4504 1–03501–4537 1–03501–4570 1–03501–4599 inclusive. inclusive. inclusive. inclusive. inclusive. inclusive. inclusive. inclusive. 35356 Federal Register / Vol. 75, No. 119 / Tuesday, June 22, 2010 / Proposed Rules TABLE 1—FIRST STAGE TURBINE DISK S/NS—Continued Disk P/N Disk S/N 2–03501–2260 thru 2–03501–2272 inclusive. 2–03501–2274 thru 2–03501–2298 inclusive. Unsafe Condition Installation Prohibition (d) This AD results from our determination that we need to expand the affected population to include other disks from the same heat lot as the failed first stage turbine disk. We are issuing this AD to prevent uncontained failure of the first stage turbine disk and damage to the airplane. (j) After September 1, 2009, do not approve for return to service, any engine that has a first stage turbine disk, P/N 3101520–1 and P/N 3107079–1, with S/N 2–03501–2299, 2– 03501–2300, 2–03501–2301, 2–03501–2302, and 2–03501–2304. (k) After the effective date of this AD, do not approve for return to service, any engine that has a first stage turbine disk, P/N 3101520–1 and P/N 3107079–1, and a S/N listed in Table 1 of this AD, unless that disk has passed an FPI as specified in paragraph 3.B.(3) through 3.B.(6) of Honeywell International Inc. ASB TPE331–72–A2156, dated December 2, 2008. 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. Removal of First Stage Turbine Disks From Service (f) Within 25 flight hours or 25 cycles-inservice (CIS) after September 1, 2009, remove from service first stage turbine disks, P/N 3101520–1 and P/N 3107079–1, serial numbers 2–03501–2299, 2–03501–2300, 2– 03501–2301, 2–03501–2302, and 2–03501– 2304. DEPARTMENT OF TRANSPORTATION Alternative Methods of Compliance (l) The Manager, Los Angles Aircraft Certification Office, FAA, has the authority to approve alternative methods of compliance for this AD if requested using the procedures found in 14 CFR 39.19. Definition (g) For first stage turbine disks, P/N 3101520–1 or 3107079–1, that have a S/N listed in Table 1 of this AD, perform a fluorescent penetrant inspection (FPI) on the disk as follows: (1) For turbine disks with 4,100 or fewer cycles-since-new (CSN) on the effective date of this proposed AD, perform an initial FPI by using paragraph 3.B.(2) through 3.B.(5) of Honeywell International Inc. Alert Service Bulletin (ASB) TPE331–72–A2156, dated December 2, 2008, within 4,500 CSN or at the next access, whichever occurs first. (2) For turbine disks with more than 4,100 CSN on the effective date of this proposed AD, perform an initial FPI by using paragraph 3.B.(2) through 3.B.(5) of Honeywell International Inc. ASB TPE331– 72–A2156, dated December 2, 2008, within 400 CIS after the effective date of this proposed AD or at the next access, whichever occurs first. (3) If you find a crack in the disk, remove the disk from service. (4) If the disk passes the FPI inspection, perform a special eddy current inspection (ECI) by using paragraph 3.B.(6) of Honeywell International Inc. ASB TPE331– 72–A2156, dated December 2, 2008. srobinson on DSKHWCL6B1PROD with PROPOSALS Initial Inspection (m) For the purpose of this AD, ‘‘next access to the first stage turbine disk’’ is defined as the removal of the second stage turbine nozzle from the turbine stator housing. Repetitive Inspection BILLING CODE 4910–13–P Related Information (n) Contact Joseph Costa, Aerospace Engineer, Los Angeles Aircraft Certification Office, FAA, Transport Airplane Directorate, 3960 Paramount Blvd., Lakewood, CA 90712–4137; e-mail: joseph.costa@faa.gov; telephone (562) 627–5246; fax (562) 627– 5210, for more information about this AD. (o) Honeywell International Inc. ASB TPE331–72–A2156, dated December 2, 2008, pertains to the subject of this AD. Contact Honeywell International Inc., 111 S. 34th Street, Phoenix, AZ 85034–2802; Web site: https://portal.honeywell.com, for a copy of this service information. Issued in Burlington, Massachusetts, on June 16, 2010. Peter A. White, Assistant Manager, Engine and Propeller Directorate, Aircraft Certification Service. [FR Doc. 2010–15068 Filed 6–21–10; 8:45 am] (h) Thereafter, perform repetitive FPI and ECI at each scheduled hot section inspection, but not to exceed 3,600 hours-since-last inspection. Use paragraph 3.B.(2) through 3.B.(6) of Honeywell International Inc. ASB TPE331–72–A2156, dated December 2, 2008. (i) If you find a crack in the disk, remove the disk from service. VerDate Mar<15>2010 16:10 Jun 21, 2010 Jkt 220001 PO 00000 Frm 00019 Fmt 4702 Sfmt 4702 Federal Aviation Administration 14 CFR Part 39 [Docket No. FAA–2010–0552; Directorate Identifier 2009–NM–095–AD] RIN 2120–AA64 Airworthiness Directives; The Boeing Company Model 747–100, 747–200B, and 747–200F Series Airplanes AGENCY: Federal Aviation Administration (FAA), Department of Transportation (DOT). ACTION: Notice of proposed rulemaking (NPRM). SUMMARY: The FAA proposes to supersede two existing airworthiness directives (AD) that apply to certain Model 747–100, 747–200B, and 747– 200F series airplanes. The existing ADs currently require inspections to detect fatigue-related skin cracks and corrosion of the skin panel lap joints in the fuselage upper lobe, and repair if necessary. One of the existing ADs, AD 94–12–09, also requires modification of certain lap joints and inspection of modified lap joints. The other AD, AD 90–15–06, requires repetitive detailed external visual inspections of the fuselage skin at the upper lobe skin lap joints for cracks and evidence of corrosion, and related investigative and corrective actions. This proposed AD would reduce the maximum interval of the post-modification inspections, and adds post-repair inspection requirements for certain airplanes. This proposed AD results from reports of cracking on modified airplanes. We are proposing this AD to detect and correct fatigue cracking and corrosion in the fuselage upper lobe skin lap joints, which could lead to rapid decompression of the airplane and inability of the structure to carry failsafe loads. DATES: We must receive comments on this proposed AD by August 6, 2010. ADDRESSES: You may send comments by any of the following methods: • Federal eRulemaking Portal: Go to https://www.regulations.gov. Follow the instructions for submitting comments. • Fax: 202–493–2251. • Mail: U.S. Department of Transportation, Docket Operations, E:\FR\FM\22JNP1.SGM 22JNP1

Agencies

[Federal Register Volume 75, Number 119 (Tuesday, June 22, 2010)]
[Proposed Rules]
[Pages 35354-35356]
From the Federal Register Online via the Government Printing Office [www.gpo.gov]
[FR Doc No: 2010-15068]

=======================================================================
-----------------------------------------------------------------------

DEPARTMENT OF TRANSPORTATION

Federal Aviation Administration

14 CFR Part 39

[Docket No. FAA-2009-0555; Directorate Identifier 2009-NE-18-AD]
RIN 2120-AA64

Airworthiness Directives; Honeywell International Inc. TPE331-10
and TPE331-11 Series Turboprop Engines

AGENCY: Federal Aviation Administration (FAA), DOT.

ACTION: Notice of proposed rulemaking (NPRM).

-----------------------------------------------------------------------

SUMMARY: The FAA proposes to supersede an existing airworthiness
directive (AD) for Honeywell International Inc. TPE331-10 and TPE331-11
series turboprop engines. That AD currently requires removing certain
first stage turbine disks from service. This proposed AD would require
the same actions, and would also require performing fluorescent
penetrant inspections (FPI) and eddy current inspections (ECI) on
certain first stage turbine disks that have a serial number (S/N)
listed in this proposed AD. This proposed AD results from our
determination that we need to expand the affected population to include
other disks from the same heat lot as the failed first stage turbine
disk, and that certain inspections are also required. We are proposing
this AD to prevent uncontained failure of the first stage turbine disk
and damage to the airplane.

DATES: We must receive any comments on this proposed AD by August 23,
2010.

ADDRESSES: Use one of the following addresses to comment on this
proposed AD.
Federal eRulemaking Portal: Go to https://www.regulations.gov and follow the instructions for sending your
comments electronically.
Mail: Docket Management Facility, U.S. Department of
Transportation, 1200 New Jersey Avenue, SE., West Building Ground
Floor, Room W12-140, Washington, DC 20590-0001.
Hand Delivery: Deliver to Mail address above between 9
a.m. and 5 p.m., Monday through Friday, except Federal holidays.
Fax: (202) 493-2251.

FOR FURTHER INFORMATION CONTACT: Joseph Costa, Aerospace Engineer, Los
Angeles Aircraft Certification Office, FAA, Transport Airplane
Directorate, 3960 Paramount Blvd., Lakewood, CA 90712-4137; e-mail:
joseph.costa@faa.gov; telephone (562) 627-5246; fax (562) 627-5210.

SUPPLEMENTARY INFORMATION:

Comments Invited

We invite you to send any written relevant data, views, or
arguments regarding this proposal. Send your comments to an address
listed under ADDRESSES. Include ``Docket No. FAA-2009-0555; Directorate
Identifier 2009-NE-18-AD'' in the subject line of your comments. We
specifically invite comments on the overall regulatory, economic,
environmental, and energy aspects of the proposed AD. We will consider
all comments received by the closing date and may amend the proposed AD
in light of those comments.
We will post all comments we receive, without change, to https://www.regulations.gov, including any personal information you provide. We
will also post a report summarizing each substantive verbal contact
with FAA personnel concerning this proposed AD. Using the search
function of the Web site, anyone can find and read the comments in any
of our dockets, including, if provided, the name of the individual who
sent the comment (or signed the comment on behalf of an association,
business, labor union, etc.). You may review the DOT's complete Privacy
Act Statement in the Federal Register published on April 11, 2000 (65
FR 19477-78).

Examining the AD Docket

You may examine the AD docket on the Internet at https://www.regulations.gov; or in person at the Docket Operations office
between 9 a.m. and 5 p.m., Monday through Friday, except Federal
holidays. The AD docket contains this proposed AD, the regulatory
evaluation, any comments received, and other information. The street
address for the Docket Operations office (telephone (800) 647-5527) is
the same as the Mail address provided in the ADDRESSES section.
Comments will be available in the AD docket shortly after receipt.

Discussion

The FAA proposes to amend 14 CFR part 39 by superseding AD 2009-17-
05, Amendment 39-15996 (74 FR 41327, August 17, 2009). That AD requires
removal from service of first stage turbine disks, P/Ns 3101520-1 and
3107079-1, serial numbers 2-03501-2299, 2-03501-2300, 2-03501-2301, 2-
03501-2302, and 2-03501-2304, within 25 flight hours or 25 cycles-in-
service (CIS) after the effective date of this AD, whichever occurs
first. That AD was the result of a report of an uncontained failure of
a first stage turbine disk that had a metallurgical defect. That
condition, if not corrected, could result in uncontained failure of the
first stage turbine disk and damage to the airplane.

Actions Since AD 2009-17-05 was Issued

Since that AD was issued, we determined that up to 360 other
turbine disks have been produced from the same heat lot as the failed
turbine disk and might have similar inclusions. These inclusions can
result in cracks that could result in an uncontained separation of a
turbine disks.

Relevant Service Information

We have reviewed and approved the technical contents of Honeywell
International Inc. Alert Service Bulletin TPE331-72-A2156, dated
December 2, 2008, that describes S/Ns of the affected turbine disks and
procedures for initial and repetitive FPI and ECI of the first stage
turbine disk.

FAA's Determination and Requirements of the Proposed AD

We have evaluated all pertinent information and identified an
unsafe

[[Page 35355]]

condition that is likely to exist or develop on other products of this
same type design. For that reason, we are proposing this AD, which
would require:
For turbine disks that have a S/N listed in Table 1 of
this proposed AD with 4,100 or fewer cycles-since-new (CSN) on the
effective date of this proposed AD, performing an initial FPI and ECI
within 4,500 CSN or at the next access, whichever occurs first.
For turbine disks that have a S/N listed in Table 1 of
this proposed AD with more than 4,100 CSN on the effective date of this
proposed AD, performing an initial FPI and ECI within 400 CIS after the
effective date of this proposed AD or at the next access, whichever
occurs first.
Thereafter, for turbine disks that have a S/N listed in
Table 1 of this proposed AD, perform a repetitive FPI and ECI at each
scheduled hot section inspection, but not to exceed 3,600 hours-since-
last inspection.
The proposed AD would require that you do these actions using the
service information described previously.

Costs of Compliance

We estimate that this proposed AD would affect 90 engines installed
on airplanes of U.S. registry. We also estimate that it would take
about 20 work-hours per engine to perform the proposed actions, and
that the average labor rate is $85 per work-hour. Required parts would
cost about $19,000 per engine. We estimate that one disk would fail the
initial inspection and that repetitive inspections would be performed
on 89 engines. We estimate that one engine would fail the repetitive
inspections and that further repetitive inspections would be performed
on 88 engines. We estimate that an additional one disk would fail those
repetitive inspections before retirement. Based on these figures, we
estimate the total cost of the proposed AD to U.S. operators to be
$511,155.

Authority for This Rulemaking

Title 49 of the United States Code specifies the FAA's authority to
issue rules on aviation safety. Subtitle I, Section 106, describes the
authority of the FAA Administrator. Subtitle VII, Aviation Programs,
describes in more detail the scope of the Agency's authority.
We are issuing this rulemaking under the authority described in
Subtitle VII, Part A, Subpart III, Section 44701, ``General
requirements.'' Under that section, Congress charges the FAA with
promoting safe flight of civil aircraft in air commerce by prescribing
regulations for practices, methods, and procedures the Administrator
finds necessary for safety in air commerce. This regulation is within
the scope of that authority because it addresses an unsafe condition
that is likely to exist or develop on products identified in this
rulemaking action.

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 AD:
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 regulatory evaluation of the estimated costs to
comply with this proposed AD. See the ADDRESSES section for a location
to examine the regulatory evaluation.

List of Subjects in 14 CFR Part 39

Air transportation, Aircraft, Aviation safety, Incorporation by
reference, Safety.

The Proposed Amendment

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 removing Amendment 39-15996 (74 FR
41327, August 17, 2009) and by adding a new airworthiness directive to
read as follows:

Honeywell International Inc. (formerly AlliedSignal Inc., Garrett
Engine Division; Garrett Turbine Engine Company; and AiResearch
Manufacturing Company of Arizona): Docket No. FAA-2009-0555;
Directorate Identifier 2009-NE-18-AD.

Comments Due Date

(a) The Federal Aviation Administration (FAA) must receive
comments on this airworthiness directive (AD) action by August 23,
2010.

Affected ADs

(b) This AD supersedes AD 2009-17-05, Amendment 39-15996.

Applicability

(c) This AD applies to Honeywell International Inc. TPE331-10
and TPE331-11 series turboprop engines with a first stage turbine
disk, part number (P/N) 3101520-1 or 3107079-1, with a serial number
(S/N) listed in Table 1 of this AD, installed. These engines are
installed on, but not limited to, British Aerospace Jetstream 3201
series, Cessna Aircraft Company Model 441 Conquest, Construcciones
Aeronauticas, S.A. (CASA) C-212 series, Dornier Luftfahrt Dornier
228 series, Hawker Beechcraft (formerly Raytheon, formerly Beech)
B100, C90 and E90, M7 Aerospace (formerly Fairchild) SA226 and SA227
series (Swearingen Merlin and Metro series), Mitsubishi MU-2B series
(MU-2 series), PZL M18 series, and Twin Commander 680 and 690 series
(Jetprop Commander) airplanes.

Table 1--First Stage Turbine Disk S/Ns
----------------------------------------------------------------------------------------------------------------
Disk P/N Disk S/N
----------------------------------------------------------------------------------------------------------------
3101520-1 or 3107079-1................... 1-03501-4275 thru 1-03501-4306 inclusive.
1-03501-4308 thru 1-03501-4339 inclusive.
1-03501-4341 thru 1-03501-4438 inclusive.
1-03501-4440 thru 1-03501-4471 inclusive.
1-03501-4473 thru 1-03501-4504 inclusive.
1-03501-4506 thru 1-03501-4537 inclusive.
1-03501-4539 thru 1-03501-4570 inclusive.
1-03501-4572 thru 1-03501-4599 inclusive.

[[Page 35356]]

2-03501-2260 thru 2-03501-2272 inclusive.
2-03501-2274 thru 2-03501-2298 inclusive.
----------------------------------------------------------------------------------------------------------------

Unsafe Condition

(d) This AD results from our determination that we need to
expand the affected population to include other disks from the same
heat lot as the failed first stage turbine disk. We are issuing this
AD to prevent uncontained failure of the first stage turbine disk
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.

Removal of First Stage Turbine Disks From Service

(f) Within 25 flight hours or 25 cycles-in-service (CIS) after
September 1, 2009, remove from service first stage turbine disks, P/
N 3101520-1 and P/N 3107079-1, serial numbers 2-03501-2299, 2-03501-
2300, 2-03501-2301, 2-03501-2302, and 2-03501-2304.

Initial Inspection

(g) For first stage turbine disks, P/N 3101520-1 or 3107079-1,
that have a S/N listed in Table 1 of this AD, perform a fluorescent
penetrant inspection (FPI) on the disk as follows:
(1) For turbine disks with 4,100 or fewer cycles-since-new (CSN)
on the effective date of this proposed AD, perform an initial FPI by
using paragraph 3.B.(2) through 3.B.(5) of Honeywell International
Inc. Alert Service Bulletin (ASB) TPE331-72-A2156, dated December 2,
2008, within 4,500 CSN or at the next access, whichever occurs
first.
(2) For turbine disks with more than 4,100 CSN on the effective
date of this proposed AD, perform an initial FPI by using paragraph
3.B.(2) through 3.B.(5) of Honeywell International Inc. ASB TPE331-
72-A2156, dated December 2, 2008, within 400 CIS after the effective
date of this proposed AD or at the next access, whichever occurs
first.
(3) If you find a crack in the disk, remove the disk from
service.
(4) If the disk passes the FPI inspection, perform a special
eddy current inspection (ECI) by using paragraph 3.B.(6) of
Honeywell International Inc. ASB TPE331-72-A2156, dated December 2,
2008.

Repetitive Inspection

(h) Thereafter, perform repetitive FPI and ECI at each scheduled
hot section inspection, but not to exceed 3,600 hours-since-last
inspection. Use paragraph 3.B.(2) through 3.B.(6) of Honeywell
International Inc. ASB TPE331-72-A2156, dated December 2, 2008.
(i) If you find a crack in the disk, remove the disk from
service.

Installation Prohibition

(j) After September 1, 2009, do not approve for return to
service, any engine that has a first stage turbine disk, P/N
3101520-1 and P/N 3107079-1, with S/N 2-03501-2299, 2-03501-2300, 2-
03501-2301, 2-03501-2302, and 2-03501-2304.
(k) After the effective date of this AD, do not approve for
return to service, any engine that has a first stage turbine disk,
P/N 3101520-1 and P/N 3107079-1, and a S/N listed in Table 1 of this
AD, unless that disk has passed an FPI as specified in paragraph
3.B.(3) through 3.B.(6) of Honeywell International Inc. ASB TPE331-
72-A2156, dated December 2, 2008.

Alternative Methods of Compliance

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

Definition

(m) For the purpose of this AD, ``next access to the first stage
turbine disk'' is defined as the removal of the second stage turbine
nozzle from the turbine stator housing.

Related Information

(n) Contact Joseph Costa, Aerospace Engineer, Los Angeles
Aircraft Certification Office, FAA, Transport Airplane Directorate,
3960 Paramount Blvd., Lakewood, CA 90712-4137; e-mail:
joseph.costa@faa.gov; telephone (562) 627-5246; fax (562) 627-5210,
for more information about this AD.
(o) Honeywell International Inc. ASB TPE331-72-A2156, dated
December 2, 2008, pertains to the subject of this AD. Contact
Honeywell International Inc., 111 S. 34th Street, Phoenix, AZ 85034-
2802; Web site: https://portal.honeywell.com, for a copy of this
service information.

Issued in Burlington, Massachusetts, on June 16, 2010.
Peter A. White,
Assistant Manager, Engine and Propeller Directorate, Aircraft
Certification Service.

[FR Doc. 2010-15068 Filed 6-21-10; 8:45 am]
BILLING CODE 4910-13-P

This site is protected by reCAPTCHA and the Google Privacy Policy and Terms of Service apply.