Airworthiness Directives; Honeywell International Inc. Turboprop Engines (Type Certificate Previously Held by AlliedSignal Inc., Garrett Engine Division; Garrett Turbine Engine Company; and AiResearch Manufacturing Company of Arizona), 61091-61093 [2015-25606]

Download as PDF Federal Register / Vol. 80, No. 196 / Friday, October 9, 2015 / Rules and Regulations Issued in Renton, Washington, on September 30, 2015. Jeffrey E. Duven, Manager, Transport Airplane Directorate, Aircraft Certification Service. Examining the AD Docket [FR Doc. 2015–25495 Filed 10–8–15; 8:45 am] BILLING CODE 4910–13–P DEPARTMENT OF TRANSPORTATION Federal Aviation Administration 14 CFR Part 39 [Docket No. FAA–2012–0913; Directorate Identifier 2012–NE–23–AD; Amendment 39– 18261; AD 2015–18–03] RIN 2120–AA64 Airworthiness Directives; Honeywell International Inc. Turboprop Engines (Type Certificate Previously Held by AlliedSignal Inc., Garrett Engine Division; Garrett Turbine Engine Company; and AiResearch Manufacturing Company of Arizona) Federal Aviation Administration (FAA), DOT. ACTION: Final rule. AGENCY: rmajette on DSK7SPTVN1PROD with RULES SUPPLEMENTARY INFORMATION: Discussion We are adopting a new airworthiness directive (AD) for certain Honeywell International Inc. TPE331–5, –5A, –5AB, –5B, –10, –10R, –10U, –10UF, –10UG, –10UGR, and –10UR model turboprop engines. This AD was prompted by engine propeller shaft coupling failures, leading to unexpected propeller pitch changes causing increased aerodynamic and asymmetric drag on the airplanes using these engines. This AD requires removing certain part number (P/N) engine propeller shaft couplings from service. This AD also requires inserting a copy of certain airplane operating procedures into applicable flight manuals. We are issuing this AD to prevent loss of airplane control, leading to an accident. DATES: This AD is effective November 13, 2015. ADDRESSES: For service information identified in this AD, contact Honeywell International Inc., 111 S. 34th Street, Phoenix, AZ 85034–2802; phone: 800– 601–3099; Internet: https:// portal.honeywell.com. You may view this service information at the FAA, Engine & Propeller Directorate, 12 New England Executive Park, Burlington, MA. For information on the availability of this material at the FAA, call 781– 238–7125. It is also available on the Internet at https://www.regulations.gov by searching for and locating Docket No. FAA–2012–0913. SUMMARY: VerDate Sep<11>2014 15:01 Oct 08, 2015 Jkt 238001 You may examine the AD docket on the Internet at https:// www.regulations.gov by searching for and locating Docket No. FAA–2012– 0913; or in person at the Docket Management Facility between 9 a.m. and 5 p.m., Monday through Friday, except Federal holidays. The AD docket contains this AD, the regulatory evaluation, any comments received, and other information. The address for the Docket Office (phone: 800–647–5527) is Document Management Facility, U.S. Department of Transportation, Docket Operations, M–30, West Building Ground Floor, Room W12–140, 1200 New Jersey Avenue SE., Washington, DC 20590. FOR FURTHER INFORMATION CONTACT: Joseph Costa, Aerospace Engineer, Los Angeles Aircraft Certification Office, FAA, Transport Airplane Directorate, 3960 Paramount Blvd., Lakewood, CA 90712–4137; phone: 562–627–5246; fax: 562–627–5210; email: joseph.costa@ faa.gov. We issued a notice of proposed rulemaking (NPRM) to amend 14 CFR part 39 by adding an AD that would apply to certain Honeywell International Inc. TPE331–5, –5A, –5AB, –5B, –10, –10R, –10U, –10UF, –10UG, –10UGR, and –10UR model turboprop engines. The NPRM published in the Federal Register on May 12, 2014 (79 FR 26906). The NPRM was prompted by numerous reports of engine propeller shaft coupling failures, leading to engine overspeed and unexpected propeller pitch changes. This condition causes high aerodynamic and asymmetric drag that has resulted in uncommanded airplane yaw and roll. The NPRM proposed to require removing certain P/N engine propeller shaft couplings from service within certain compliance times to address the flight safety risk. The NPRM also proposed to insert a copy of certain airplane operating procedures into the applicable flight manuals. These procedures describe an emergency procedure for pilot reaction to an engine overspeed event after an engine propeller shaft coupling failure. We are issuing this AD to prevent loss of airplane control, leading to an accident. Comments We gave the public the opportunity to participate in developing this AD. The following presents the comment received on the NPRM (79 FR 26906, PO 00000 Frm 00005 Fmt 4700 Sfmt 4700 61091 May 12, 2014) and the FAA’s response to the comment. Request To Change Compliance Time Basis Honeywell International questioned whether compliance time should be stated in flight hours as opposed to flight cycles as used in the NPRM (79 FR 26906, May 12, 2014). Major periodic inspections are based on hours and not cycles. We disagree. The FAA practice of stating compliance time is based on the component’s mode of failure. In this case the failure mode was fatigue; therefore, a compliance time in flight cycles is appropriate. We did not change this AD. Clarified Requirement Since we issued the NPRM (79 FR 26906, May 12, 2014), we discovered that paragraph (e)(4) of the Compliance section required clarification. We clarified that paragraph in this AD by deleting the requirement to insert a copy of Honeywell International Inc. Operating Information Letter (OIL) and requiring that Figure 1 to Paragraph (e)—Airplane Operating Procedures be inserted. Reference to the OIL was added as related information. The replacement procedure provides simplified, more concise text, for increased clarity. Conclusion We reviewed the relevant data, considered the comment received, and determined that air safety and the public interest require adopting this AD with clarification. Costs of Compliance We estimate that this AD will affect 485 engines installed on airplanes of U.S. registry. We also estimate that it will take about one hour per engine to perform the actions required by this AD, if done at the next scheduled turbine hot section inspection (HSI), and 40 hours per engine if done during an unscheduled access of the engine propeller shaft coupling. We also estimate that 400 engines will have the replacement actions done at a scheduled time of next turbine HSI, and 85 engines will have the replacement actions done at an unscheduled access of the engine propeller shaft coupling. The average labor rate is $85 per hour. Required parts will cost about $12,000 per engine. Based on these figures, we estimate the total cost of this AD to U.S. operators to be $6,143,000. E:\FR\FM\09OCR1.SGM 09OCR1 61092 Federal Register / Vol. 80, No. 196 / Friday, October 9, 2015 / Rules and Regulations 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 rmajette on DSK7SPTVN1PROD with RULES 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), (3) Will not affect intrastate aviation in Alaska to the extent that it justifies making a regulatory distinction, and (4) Will not have a significant economic impact, positive or negative, on a substantial number of small entities VerDate Sep<11>2014 15:01 Oct 08, 2015 Jkt 238001 under the criteria of the Regulatory Flexibility Act. List of Subjects in 14 CFR Part 39 Air transportation, Aircraft, Aviation safety, Incorporation by reference, Safety. Adoption of the Amendment Accordingly, under the authority delegated to me by the Administrator, the FAA amends 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 adding the following new airworthiness directive (AD): ■ 2015–18–03 Honeywell International Inc. (Type Certificate previously held by AlliedSignal Inc., Garrett Engine Division; Garrett Turbine Engine Company; and AiResearch Manufacturing Company of Arizona): Docket No. FAA–2012–0913; Directorate Identifier 2012–NE–23–AD. (a) Effective Date This AD is effective November 13, 2015. (b) Affected ADs None. (c) Applicability This AD applies to Honeywell International Inc. TPE331–5, –5A, –5AB, –5B, –10, –10R, –10U, –10UF, –10UG, –10UGR, and –10UR model turboprop engines, with an engine propeller shaft coupling, part number (P/N) 3107065–1, 865888–3, 865888–6, or 865888–8, installed. (d) Unsafe Condition This AD was prompted by engine propeller shaft coupling failures, leading to unexpected propeller pitch changes causing increased PO 00000 Frm 00006 Fmt 4700 Sfmt 4700 aerodynamic and asymmetric drag on the airplanes using these engines. We are issuing this AD to prevent loss of airplane control, leading to an accident. (e) Compliance Comply with this AD within the compliance times specified, unless already done. (1) Engines Installed in Mitsubishi MU–2B Series (MU–2 Series) Airplanes: (i) Remove from service the affected engine propeller shaft coupling at the earliest of the following: (A) Next piece-part exposure; or (B) Next turbine (hot) section inspection (HSI); or (C) Before accumulating an additional 1,200 cycles after the effective date of this AD. (2) Engines Installed in Construcciones Aeronauticas, S.A. (CASA) C–212 Series, and Twin Commander 690 and 695 Series (Jetprop Commander) Airplanes: (i) Remove from service the affected engine propeller shaft coupling at the earliest of the following: (A) Next piece-part exposure; or (B) Next turbine HSI; or (C) Before accumulating an additional 2,400 cycles after the effective date of this AD. (3) Engines Installed in British Aerospace Jetstream 3101 Series, Dornier Luftfahrt Dornier 228 Series, and M7 (formerly Fairchild, Swearingen) SA226 and SA227 Series Airplanes, and all other airplanes not listed in this AD using affected engines: (i) Remove from service the affected engine propeller shaft coupling at the earliest of the following: (A) Next piece-part exposure; or (B) Next turbine HSI; or (C) Before accumulating an additional 3,600 cycles after the effective date of this AD. (4) Within 60 days after the effective date of this AD, for all airplanes that use the affected engines, insert a copy of Figure 1 to paragraph (e) of this AD, into the Emergency Procedures Section of the Airplane Flight Manual (AFM), Pilot Operating Handbook (POH), and the Manufacturer’s Operating Manual (MOM). E:\FR\FM\09OCR1.SGM 09OCR1 Federal Register / Vol. 80, No. 196 / Friday, October 9, 2015 / Rules and Regulations For the purpose of this AD, next piece-part exposure is when the nose cone assembly is removed from the engine. (g) Installation Prohibition After the effective date of this AD, do not install any engine propeller shaft coupling, P/N 3107065–1, 865888–3, 865888–6, or 865888–8, into any engine. (h) Alternative Methods of Compliance (AMOCs) rmajette on DSK7SPTVN1PROD with RULES (i) Related Information (1) For more information about this AD, contact Joseph Costa, Aerospace Engineer, Los Angeles Aircraft Certification Office, FAA, Transport Airplane Directorate, 3960 Paramount Blvd., Lakewood, CA 90712– 4137; phone: 562–627–5246; fax: 562–627– 5210; email: joseph.costa@faa.gov. (2) Allied-Signal Aerospace Company Service Bulletin No. TPE331–72–0873, Revision 1, dated May 20, 1993 and Honeywell International Inc. Operating Information Letter OI331–26, dated March 2, 2010, which are not incorporated by reference in this AD, can be obtained from Honeywell International, using the contact information in paragraph (i)(3) of this AD. (3) For service information identified in this AD, contact Honeywell International Inc., 111 S. 34th Street, Phoenix, AZ 85034– 2802; phone: 800–601–3099; Internet: https:// portal.honeywell.com. (4) You may view this service information at the FAA, Engine & Propeller Directorate, 12 New England Executive Park, Burlington, MA. For information on the availability of this material at the FAA, call 781–238–7125. None. VerDate Sep<11>2014 15:01 Oct 08, 2015 Jkt 238001 [FR Doc. 2015–25606 Filed 10–8–15; 8:45 am] BILLING CODE 4910–13–P DEPARTMENT OF TRANSPORTATION Federal Aviation Administration The Manager, Los Angeles Aircraft Certification Office, FAA, may approve AMOCs for this AD. Use the procedures found in 14 CFR 39.19 to make your request. (j) Material Incorporated by Reference Issued in Burlington, Massachusetts, on: October 2, 2015. Colleen M. D’Alessandro, Directorate Manager, Engine & Propeller Directorate, Aircraft Certification Service. 14 CFR Part 39 [Docket No. FAA–2012–0108; Directorate Identifier 2011–NM–049–AD; Amendment 39–18215; AD 2015–15–06] RIN 2120–AA64 Airworthiness Directives; The Boeing Company Airplanes Federal Aviation Administration (FAA), DOT. ACTION: Final rule. AGENCY: We are superseding Airworthiness Directive (AD) 2003–13– 01 for certain The Boeing Company Model 767 airplanes. AD 2003–13–01 required an inspection to detect cracks and fractures of the outboard hinge fitting assemblies on the trailing edge of the inboard main flap, and follow-on and corrective actions if necessary. For certain airplanes, AD 2003–13–01 required an inspection to determine if a tool runout option has been performed in the area. This new AD reduces certain compliance times, adds airplanes to the applicability, and provides optional terminating action for certain inspections. This AD was prompted by reports of hinge assembly fractures found before certain required SUMMARY: PO 00000 Frm 00007 Fmt 4700 Sfmt 4700 compliance times in AD 2003–13–01. We are issuing this AD to prevent the inboard aft flap from separating from the wing and potentially striking the airplane, which could result in damage to the surrounding structure and potential personal injury. DATES: This AD is effective November 13, 2015. The Director of the Federal Register approved the incorporation by reference of certain publications listed in this AD as of November 13, 2015. The Director of the Federal Register approved the incorporation by reference of certain other publications listed in this AD as of July 29, 2003 (68 FR 37402, June 24, 2003). ADDRESSES: For service information identified in this AD, contact Boeing Commercial Airplanes, Attention: Data & Services Management, P.O. Box 3707, MC 2H–65, Seattle, WA 98124–2207; telephone 206–544–5000, extension 1; fax 206–766–5680; Internet https:// www.myboeingfleet.com. You may view this referenced service information at the FAA, Transport Airplane Directorate, 1601 Lind Avenue SW., Renton, WA. For information on the availability of this material at the FAA, call 425–227–1221. It is also available on the Internet at https:// www.regulations.gov by searching for and locating Docket No. FAA–2012– 0108. Examining the AD Docket You may examine the AD docket on the Internet at https:// www.regulations.govby searching for and locating Docket No. FAA–2012– 0108; or in person at the Docket Management Facility between 9 a.m. and 5 p.m., Monday through Friday, E:\FR\FM\09OCR1.SGM 09OCR1 ER09OC15.000</GPH> (f) Definition 61093

Agencies

[Federal Register Volume 80, Number 196 (Friday, October 9, 2015)]
[Rules and Regulations]
[Pages 61091-61093]
From the Federal Register Online via the Government Publishing Office [www.gpo.gov]
[FR Doc No: 2015-25606]


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

DEPARTMENT OF TRANSPORTATION

Federal Aviation Administration

14 CFR Part 39

[Docket No. FAA-2012-0913; Directorate Identifier 2012-NE-23-AD; 
Amendment 39-18261; AD 2015-18-03]
RIN 2120-AA64


Airworthiness Directives; Honeywell International Inc. Turboprop 
Engines (Type Certificate Previously Held by AlliedSignal Inc., Garrett 
Engine Division; Garrett Turbine Engine Company; and AiResearch 
Manufacturing Company of Arizona)

AGENCY: Federal Aviation Administration (FAA), DOT.

ACTION: Final rule.

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

SUMMARY: We are adopting a new airworthiness directive (AD) for certain 
Honeywell International Inc. TPE331-5, -5A, -5AB, -5B, -10, -10R, -10U, 
-10UF, -10UG, -10UGR, and -10UR model turboprop engines. This AD was 
prompted by engine propeller shaft coupling failures, leading to 
unexpected propeller pitch changes causing increased aerodynamic and 
asymmetric drag on the airplanes using these engines. This AD requires 
removing certain part number (P/N) engine propeller shaft couplings 
from service. This AD also requires inserting a copy of certain 
airplane operating procedures into applicable flight manuals. We are 
issuing this AD to prevent loss of airplane control, leading to an 
accident.

DATES: This AD is effective November 13, 2015.

ADDRESSES: For service information identified in this AD, contact 
Honeywell International Inc., 111 S. 34th Street, Phoenix, AZ 85034-
2802; phone: 800-601-3099; Internet: https://portal.honeywell.com. You 
may view this service information at the FAA, Engine & Propeller 
Directorate, 12 New England Executive Park, Burlington, MA. For 
information on the availability of this material at the FAA, call 781-
238-7125. It is also available on the Internet at https://www.regulations.gov by searching for and locating Docket No. FAA-2012-
0913.

Examining the AD Docket

    You may examine the AD docket on the Internet at https://www.regulations.gov by searching for and locating Docket No. FAA-2012-
0913; or in person at the Docket Management Facility between 9 a.m. and 
5 p.m., Monday through Friday, except Federal holidays. The AD docket 
contains this AD, the regulatory evaluation, any comments received, and 
other information. The address for the Docket Office (phone: 800-647-
5527) is Document Management Facility, U.S. Department of 
Transportation, Docket Operations, M-30, West Building Ground Floor, 
Room W12-140, 1200 New Jersey Avenue SE., Washington, DC 20590.

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

SUPPLEMENTARY INFORMATION: 

Discussion

    We issued a notice of proposed rulemaking (NPRM) to amend 14 CFR 
part 39 by adding an AD that would apply to certain Honeywell 
International Inc. TPE331-5, -5A, -5AB, -5B, -10, -10R, -10U, -10UF, -
10UG, -10UGR, and -10UR model turboprop engines. The NPRM published in 
the Federal Register on May 12, 2014 (79 FR 26906). The NPRM was 
prompted by numerous reports of engine propeller shaft coupling 
failures, leading to engine overspeed and unexpected propeller pitch 
changes. This condition causes high aerodynamic and asymmetric drag 
that has resulted in uncommanded airplane yaw and roll. The NPRM 
proposed to require removing certain P/N engine propeller shaft 
couplings from service within certain compliance times to address the 
flight safety risk. The NPRM also proposed to insert a copy of certain 
airplane operating procedures into the applicable flight manuals. These 
procedures describe an emergency procedure for pilot reaction to an 
engine overspeed event after an engine propeller shaft coupling 
failure. We are issuing this AD to prevent loss of airplane control, 
leading to an accident.

Comments

    We gave the public the opportunity to participate in developing 
this AD. The following presents the comment received on the NPRM (79 FR 
26906, May 12, 2014) and the FAA's response to the comment.

Request To Change Compliance Time Basis

    Honeywell International questioned whether compliance time should 
be stated in flight hours as opposed to flight cycles as used in the 
NPRM (79 FR 26906, May 12, 2014). Major periodic inspections are based 
on hours and not cycles.
    We disagree. The FAA practice of stating compliance time is based 
on the component's mode of failure. In this case the failure mode was 
fatigue; therefore, a compliance time in flight cycles is appropriate. 
We did not change this AD.

Clarified Requirement

    Since we issued the NPRM (79 FR 26906, May 12, 2014), we discovered 
that paragraph (e)(4) of the Compliance section required clarification. 
We clarified that paragraph in this AD by deleting the requirement to 
insert a copy of Honeywell International Inc. Operating Information 
Letter (OIL) and requiring that Figure 1 to Paragraph (e)--Airplane 
Operating Procedures be inserted. Reference to the OIL was added as 
related information. The replacement procedure provides simplified, 
more concise text, for increased clarity.

Conclusion

    We reviewed the relevant data, considered the comment received, and 
determined that air safety and the public interest require adopting 
this AD with clarification.

Costs of Compliance

    We estimate that this AD will affect 485 engines installed on 
airplanes of U.S. registry. We also estimate that it will take about 
one hour per engine to perform the actions required by this AD, if done 
at the next scheduled turbine hot section inspection (HSI), and 40 
hours per engine if done during an unscheduled access of the engine 
propeller shaft coupling. We also estimate that 400 engines will have 
the replacement actions done at a scheduled time of next turbine HSI, 
and 85 engines will have the replacement actions done at an unscheduled 
access of the engine propeller shaft coupling. The average labor rate 
is $85 per hour. Required parts will cost about $12,000 per engine. 
Based on these figures, we estimate the total cost of this AD to U.S. 
operators to be $6,143,000.

[[Page 61092]]

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

    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),
    (3) Will not affect intrastate aviation in Alaska to the extent 
that it justifies making a regulatory distinction, and
    (4) 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.

List of Subjects in 14 CFR Part 39

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

Adoption of the Amendment

    Accordingly, under the authority delegated to me by the 
Administrator, the FAA 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):

2015-18-03 Honeywell International Inc. (Type Certificate previously 
held by AlliedSignal Inc., Garrett Engine Division; Garrett Turbine 
Engine Company; and AiResearch Manufacturing Company of Arizona): 
Docket No. FAA-2012-0913; Directorate Identifier 2012-NE-23-AD.

(a) Effective Date

    This AD is effective November 13, 2015.

(b) Affected ADs

    None.

(c) Applicability

    This AD applies to Honeywell International Inc. TPE331-5, -5A, -
5AB, -5B, -10, -10R, -10U, -10UF, -10UG, -10UGR, and -10UR model 
turboprop engines, with an engine propeller shaft coupling, part 
number (P/N) 3107065-1, 865888-3, 865888-6, or 865888-8, installed.

(d) Unsafe Condition

    This AD was prompted by engine propeller shaft coupling 
failures, leading to unexpected propeller pitch changes causing 
increased aerodynamic and asymmetric drag on the airplanes using 
these engines. We are issuing this AD to prevent loss of airplane 
control, leading to an accident.

(e) Compliance

    Comply with this AD within the compliance times specified, 
unless already done.
    (1) Engines Installed in Mitsubishi MU-2B Series (MU-2 Series) 
Airplanes:
    (i) Remove from service the affected engine propeller shaft 
coupling at the earliest of the following:
    (A) Next piece-part exposure; or
    (B) Next turbine (hot) section inspection (HSI); or
    (C) Before accumulating an additional 1,200 cycles after the 
effective date of this AD.
    (2) Engines Installed in Construcciones Aeronauticas, S.A. 
(CASA) C-212 Series, and Twin Commander 690 and 695 Series (Jetprop 
Commander) Airplanes:
    (i) Remove from service the affected engine propeller shaft 
coupling at the earliest of the following:
    (A) Next piece-part exposure; or
    (B) Next turbine HSI; or
    (C) Before accumulating an additional 2,400 cycles after the 
effective date of this AD.
    (3) Engines Installed in British Aerospace Jetstream 3101 
Series, Dornier Luftfahrt Dornier 228 Series, and M7 (formerly 
Fairchild, Swearingen) SA226 and SA227 Series Airplanes, and all 
other airplanes not listed in this AD using affected engines:
    (i) Remove from service the affected engine propeller shaft 
coupling at the earliest of the following:
    (A) Next piece-part exposure; or
    (B) Next turbine HSI; or
    (C) Before accumulating an additional 3,600 cycles after the 
effective date of this AD.
    (4) Within 60 days after the effective date of this AD, for all 
airplanes that use the affected engines, insert a copy of Figure 1 
to paragraph (e) of this AD, into the Emergency Procedures Section 
of the Airplane Flight Manual (AFM), Pilot Operating Handbook (POH), 
and the Manufacturer's Operating Manual (MOM).

[[Page 61093]]

[GRAPHIC] [TIFF OMITTED] TR09OC15.000

(f) Definition

    For the purpose of this AD, next piece-part exposure is when the 
nose cone assembly is removed from the engine.

(g) Installation Prohibition

    After the effective date of this AD, do not install any engine 
propeller shaft coupling, P/N 3107065-1, 865888-3, 865888-6, or 
865888-8, into any engine.

(h) Alternative Methods of Compliance (AMOCs)

    The Manager, Los Angeles Aircraft Certification Office, FAA, may 
approve AMOCs for this AD. Use the procedures found in 14 CFR 39.19 
to make your request.

(i) Related Information

    (1) For more information about this AD, contact Joseph Costa, 
Aerospace Engineer, Los Angeles Aircraft Certification Office, FAA, 
Transport Airplane Directorate, 3960 Paramount Blvd., Lakewood, CA 
90712-4137; phone: 562-627-5246; fax: 562-627-5210; email: 
joseph.costa@faa.gov.
    (2) Allied-Signal Aerospace Company Service Bulletin No. TPE331-
72-0873, Revision 1, dated May 20, 1993 and Honeywell International 
Inc. Operating Information Letter OI331-26, dated March 2, 2010, 
which are not incorporated by reference in this AD, can be obtained 
from Honeywell International, using the contact information in 
paragraph (i)(3) of this AD.
    (3) For service information identified in this AD, contact 
Honeywell International Inc., 111 S. 34th Street, Phoenix, AZ 85034-
2802; phone: 800-601-3099; Internet: https://portal.honeywell.com.
    (4) You may view this service information at the FAA, Engine & 
Propeller Directorate, 12 New England Executive Park, Burlington, 
MA. For information on the availability of this material at the FAA, 
call 781-238-7125.

(j) Material Incorporated by Reference

    None.

    Issued in Burlington, Massachusetts, on: October 2, 2015.
Colleen M. D'Alessandro,
Directorate Manager, Engine & Propeller Directorate, Aircraft 
Certification Service.
[FR Doc. 2015-25606 Filed 10-8-15; 8:45 am]
 BILLING CODE 4910-13-P
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