Airworthiness Directives; Honeywell International Inc. Turboprop Engines, 42007-42010 [2015-16587]
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Federal Register / Vol. 80, No. 136 / Thursday, July 16, 2015 / Rules and Regulations
principal inspector, or lacking a principal
inspector, the manager of the local flight
standards district office/certificate holding
district office. The AMOC approval letter
must specifically reference this AD.
(2) Contacting the Manufacturer: For any
requirement in this AD to obtain corrective
actions from a manufacturer, the action must
be accomplished using a method approved
by the Manager, International Branch, ANM–
116, Transport Airplane Directorate, FAA; or
the European Aviation Safety Agency
(EASA); or Airbus’s EASA Design
Organization Approval (DOA). If approved by
the DOA, the approval must include the
DOA-authorized signature.
(i) Related Information
Refer to Mandatory Continuing
Airworthiness Information (MCAI) EASA
Airworthiness Directive 2014–0191, dated
August 29, 2014, for related information.
This MCAI may be found in the AD docket
on the Internet at https://
www.regulations.gov/
#!documentDetail;D=FAA-2015-0086-0003.
(j) Material Incorporated by Reference
(1) The Director of the Federal Register
approved the incorporation by reference
(IBR) of the service information listed in this
paragraph under 5 U.S.C. 552(a) and 1 CFR
part 51.
(2) You must use this service information
as applicable to do the actions required by
this AD, unless this AD specifies otherwise.
(i) Airbus Service Bulletin A310–71–2038,
including Appendices 01 and 02, dated April
8, 2014.
(ii) Reserved.
(3) For service information identified in
this AD, contact Airbus SAS, Airworthiness
Office—EAW, 1 Rond Point Maurice
Bellonte, 31707 Blagnac Cedex, France;
telephone +33 5 61 93 36 96; fax +33 5 61
93 44 51; email account.airworth-eas@
airbus.com; Internet https://www.airbus.com.
(4) You may view this 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.
(5) You may view this service information
that is incorporated by reference 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: https://
www.archives.gov/federal-register/cfr/ibrlocations.html.
Issued in Renton, Washington, on July 2,
2015.
Jeffrey E. Duven,
Manager, Transport Airplane Directorate,
Aircraft Certification Service.
[FR Doc. 2015–17202 Filed 7–15–15; 8:45 am]
tkelley on DSK3SPTVN1PROD with RULES
BILLING CODE 4910–13–P
DEPARTMENT OF TRANSPORTATION
Federal Aviation Administration
14 CFR Part 39
[Docket No. FAA–2006–23706; Directorate
Identifier 2006–NE–03–AD; Amendment 39–
18177; AD 2015–12–04]
RIN 2120–AA64
Airworthiness Directives; Honeywell
International Inc. Turboprop Engines
Federal Aviation
Administration (FAA), DOT.
ACTION: Final rule; correction.
AGENCY:
The FAA is correcting an
airworthiness directive (AD) that
published in the Federal Register. That
AD applies to all Honeywell
International Inc. TPE331–1, –2, –2UA,
–3U, –3UW, –5, –5A, –5AB, –5B, –6,
–6A, –10, –10AV, –10GP, –10GT, –10P,
–10R, –10T, –10U, –10UA, –10UF,
–10UG, –10UGR, –10UR, –11U, –12JR,
–12UA, –12UAR, and –12UHR
turboprop engines with certain
Honeywell part numbers (P/Ns) of
Woodward fuel control unit (FCU)
assemblies, installed. The AD number in
the document headings is incorrect.
Additionally, the Amendment number
in the regulatory text is incorrect. This
document corrects these two errors. In
all other respects, the original document
remains the same.
DATES: This final rule is effective on July
22, 2015. The effective date of AD 2015–
12–04, Amendment 39–18177 (80 FR
34534, June 17, 2015) remains July 22,
2015.
ADDRESSES: You may examine the AD
docket on the Internet at https://
www.regulations.gov; 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,
SUMMARY:
42007
FAA, Transport Airplane Directorate,
3960 Paramount Blvd., Lakewood, CA
90712–4137; phone: 562–627–5246; fax:
562–627–5210; email: joseph.costa@
faa.gov.
AD 2015–
12–04, Amendment 39–18177, 80 FR
34534, June 17, 2015), requires initial
and repetitive dimensional inspections
of the affected fuel control drives and
insertion of certain airplane operating
procedures into the applicable flight
manuals.
As published, the AD number in the
document headings is incorrect.
Additionally, the Amendment number
in the regulatory text of AD 2015–12–04
is incorrect.
No other part of the final rule has
been changed.
The effective date of AD 2015–12–04
remains July 22, 2015.
SUPPLEMENTARY INFORMATION:
Correction of Non-Regulatory Text
In the Federal Register of June 17,
2015, AD 2015–12–04; Amendment 39–
18177 (80 FR 34534) is corrected as
follows:
On page 34534, in the 2nd column, on
line 6, change ‘‘2014–12–04’’ to ‘‘2015–
12–04’’.
Correction of Regulatory Text
§ 39.13
[Corrected]
2. The FAA amends § 39.13 by
removing airworthiness directive (AD)
2006–15–08, Amendment 39–14688 (71
FR 41121, July 20, 2006), and adding the
following new AD:
■
2015–12–04 Honeywell International Inc.:
Amendment 39–18177; Docket No.
FAA–2006–23706; Directorate Identifier
2006–NE–03–AD.
(a) Effective Date
This AD is effective August 20, 2015.
(b) Affected ADs
This AD replaces AD 2006–15–08,
Amendment 39–14688 (71 FR 41121, July 20,
2006).
(c) Applicability
This AD applies to all Honeywell
International Inc. TPE331–1, –2, –2UA, –3U,
–3UW, –5, –5A, –5AB, –5B, –6, –6A, –10,
–10AV, –10GP, –10GT, –10P, –10R, –10T,
–10U, –10UA, –10UF, –10UG, –10UGR,
–10UR, –11U, –12JR, –12UA, –12UAR, and
–12UHR turboprop engines with Honeywell
part numbers (P/Ns) for Woodward fuel
control unit (FCU) assemblies listed in Table
1 to paragraph (c) of this AD, installed.
TABLE 1 TO PARAGRAPH (C)—AFFECTED FCU ASSEMBLY P/NS
Group No.
Engine
FCU Assembly P/Ns
1 .....................
TPE331–1, –2, and –2UA ........................
P/N 869199–13, –20, –21, –22, –23, –24, –25, –26, –27, –28, –29, –31, –32, –33,
–34, and –35.
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42008
Federal Register / Vol. 80, No. 136 / Thursday, July 16, 2015 / Rules and Regulations
TABLE 1 TO PARAGRAPH (C)—AFFECTED FCU ASSEMBLY P/NS—Continued
Group No.
Engine
2 * ...................
3 .....................
TPE331–1, –2, and –2UA ........................
TPE331–3U, –3UW, –5, –5A, –5AB, –5B,
–6, –6A, –10AV, –10GP, –10GT, –10P,
and –10T.
TPE331–3U, –3UW, –5, –5B, –6, –6A,
and –10T.
TPE331–10,
–10R,
–10U,
–10UA,
–10UF, –10UG, –10UGR, –10UR,
–11U, –12JR, –12UA, –12UAR, and
–12UHR.
4 * ...................
5 .....................
FCU Assembly P/Ns
P/N 869199–9, –10, –11, –12, –14, –16, –17, and –18.
P/N 893561–7, –8, –9, –10, –11, –14, –15, –16, –20, –26, –27, and –29; or
P/N 897770–1, –3, –7, –9, –10, –11, –12, –14, –15, –16, –25, –26, and –28.
P/N 893561–4, –5, –12, and –13 or P/N 897770–5, –8, and –13.
P/N 897375–2, –3, –4, –5, –8, –9, –10, –11, –12, –13, –14, –15, –16, –17, –19,
–21, –24, –25, –26, and –27; or
P/N 897780–1, –2, –3, –4, –5, –6, –7, –8, –9, –10, –11, –14, –15, –16, –17, –18,
–19, –20, –21, –22, –23, –24, –25, –26, –27, –30, –32, –34, –36, –37, and –38;
or
P/N 893561–17, –18, and –19.
* New/added FCU assembly P/Ns
(d) Unsafe Condition
We are issuing this AD to prevent failure
of the fuel control drive that could result in
damage to the engine and airplane.
(e) Compliance
Comply with this AD within the
compliance times specified, unless already
done.
tkelley on DSK3SPTVN1PROD with RULES
(1) Inspection of Engines With FCU Assembly
P/Ns in Groups 2 and 4
For FCU assembly P/Ns in Groups 2 and
4 listed in Table 1 to paragraph (c) of this AD:
(i) At the next scheduled inspection of the
fuel control drive, or within 500 hours-in-
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16:14 Jul 15, 2015
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service (HIS) after the effective date of this
AD, whichever occurs first, inspect the fuel
control drive for wear.
(ii) Thereafter, re-inspect the fuel control
drive within every 1,000 HIS since-lastinspection (SLI).
(ii) If on the effective date of this AD the
FCU assembly has fewer than 950 HIS SLI,
inspect the fuel control drive for wear before
reaching 1,000 HIS.
(iii) Thereafter, re-inspect the fuel control
drive for wear within every 1,000 HIS SLI.
(2) Inspection of Engines With FCU Assembly
P/Ns in Groups 1, 3, and 5
(3) Airplane Operating Procedures
For FCU assembly P/Ns in Groups 1, 3, or
5 listed in Table 1 to paragraph (c) of this AD:
(i) If on the effective date of this AD the
FCU assembly has 950 or more HIS SLI,
inspect the fuel control drive for wear within
50 HIS from the effective date of this AD.
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Frm 00022
Fmt 4700
Sfmt 4700
Within 60 days after the effective date of
this AD, insert the information in 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).
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Federal Register / Vol. 80, No. 136 / Thursday, July 16, 2015 / Rules and Regulations
(g) Definitions
For the purposes of this AD:
(1) The ‘‘fuel control drive’’ is a series of
mating splines located between the fuel
pump and fuel control governor.
(2) The fuel control drive consists of four
drive splines: the fuel pump internal spline,
the fuel control external ‘‘quill shaft’’ spline,
and the stub shaft internal and external
splines.
(h) Alternative Methods of Compliance
(AMOCs)
The Manager, Los Angeles Aircraft
Certification Office, FAA, may approve
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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) Information pertaining to operating
recommendations for affected engines after a
fuel control drive failure is contained in
Honeywell International Inc., Operating
Information Letter (OIL) OI331–12R6, dated
May 26, 2009, for multi-engine airplanes; and
in OIL OI331–18R4, dated May 26, 2009, for
single-engine airplanes. Information on fuel
control drive inspection can be found in
Section 72–00–00 of the applicable TPE331
maintenance manuals. These Honeywell
International Inc., OILs and the TPE331
maintenance manuals, which are not
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Fmt 4700
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incorporated by reference in this AD, can be
obtained from Honeywell International Inc.,
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; Internet: https://
myaerospace.honeywell.com/wps/portal/!ut;
phone: 800–601–3099.
(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.
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ER16JY15.000</GPH>
tkelley on DSK3SPTVN1PROD with RULES
(f) Optional Terminating Action
Replacing the affected FCU assembly with
an FAA-approved FCU assembly P/N not
listed in this AD is terminating action for the
initial and repetitive inspections required by
this AD, and for inserting the information in
Figure 1 to paragraph (e) of this AD into the
AFM, POH, and MOM.
42009
42010
Federal Register / Vol. 80, No. 136 / Thursday, July 16, 2015 / Rules and Regulations
Issued in Burlington, Massachusetts, on
June 26, 2015.
Ann C. Mollica,
Acting Directorate Manager, Engine and
Propeller Directorate, Aircraft Certification
Service.
[FR Doc. 2015–16587 Filed 7–15–15; 8:45 am]
BILLING CODE 4910–13–P
DEPARTMENT OF TRANSPORTATION
Federal Aviation Administration
14 CFR Part 39
[Docket No. FAA–2014–1123; Directorate
Identifier 2014–CE–037–AD; Amendment
[39–18209; AD 2015–06–02 R1]
RIN 2120–AA64
Airworthiness Directives; GA 8 Airvan
(Pty) Ltd Airplanes
Federal Aviation
Administration (FAA), Department of
Transportation (DOT).
ACTION: Final rule.
AGENCY:
We are revising an
airworthiness directive (AD) 2015–06–
02 for GA 8 Airvan (Pty) Ltd Model
GA8–TC320 airplanes. This AD results
from mandatory continuing
airworthiness information (MCAI)
issued by an aviation authority of
another country to identify and correct
an unsafe condition on an aviation
product. The MCAI describes the unsafe
condition as missing required engine
mount fire seal washers, which could
reduce the engine retention capability in
the event of a fire. We are issuing this
AD to require actions to address the
unsafe condition on these products.
DATES: This AD is effective August 20,
2015.
The Director of the Federal Register
approved the incorporation by reference
of a certain other publication listed in
this AD as of April 24, 2015 (80 FR
14810, March 20, 2015).
ADDRESSES: You may examine the AD
docket on the Internet at https://
www.regulations.gov by searching for
and locating Docket No. FAA–2014–
1123; or in person at the Docket
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 service information identified in
this AD, contact GA 8 Airvan (Pty) Ltd,
c/o GippsAero Pty Ltd, Attn: Technical
Services, P.O. Box 881, Morwell
Victoria 3840, Australia; telephone: + 61
03 5172 1200; fax: +61 03 5172 1201;
email: techpubs@gippsaero.com;
tkelley on DSK3SPTVN1PROD with RULES
SUMMARY:
VerDate Sep<11>2014
16:14 Jul 15, 2015
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Internet: https://www.gippsaero.com/
customer-support/technicalpublications.aspx. You may view this
referenced service information at the
FAA, Small Airplane Directorate, 901
Locust, Kansas City, Missouri 64106.
For information on the availability of
this material at the FAA, call (816) 329–
4148. It is also available on the Internet
at https://www.regulations.gov by
searching for and locating Docket No.
FAA–2014–1123.
FOR FURTHER INFORMATION CONTACT:
Doug Rudolph, Aerospace Engineer,
FAA, Small Airplane Directorate, 901
Locust, Room 301, Kansas City,
Missouri 64106; telephone: (816) 329–
4059; fax: (816) 329–4090; email:
doug.rudolph@faa.gov.
SUPPLEMENTARY INFORMATION:
Discussion
We issued a notice of proposed
rulemaking (NPRM) to amend 14 CFR
part 39 to add an AD that would apply
to GA 8 Airvan (Pty) Ltd Model GA8–
TC320 airplanes. The NPRM was
published in the Federal Register on
April 17, 2015 (74 FR 21193), and
proposed to revise AD 2015–06–02,
Amendment 39–18120 (80 FR 14810;
March 20, 2015).
The NPRM proposed to correct an
unsafe condition for the specified
products and was based on mandatory
continuing airworthiness information
originated by an airworthiness authority
of another country. The MCAI states
that:
A recent review of the engine mount
installation on the GA8–TC 320 aircraft has
highlighted the omission of engine mount
fire seal washers during the assembly
process.
The current engine mount configuration
does not meet the certification basis for the
aircraft, specifically regulation 23.865 of the
Federal Aviation Regulations of the United
States of America, where engine mounts
located in designated fire zones are required
to be suitably shielded so that they are
capable of withstanding the effects of a fire.
The Gippsland Aeronautics GA8–TC 320
aircraft require the installation of an
approved steel washer at each of the engine
mount locations to address a potential risk of
reduced engine retention capability in the
event of a fire.
This AD, AD/GA8/8 Amdt 1, amends the
applicability statement to be inclusive of the
affected aircraft serial number range.
The MCAI can be found in the AD
docket on the Internet at: https://
www.regulations.gov/
#!documentDetail;D=FAA-2014-11230007.
Comments
We gave the public the opportunity to
participate in developing this AD. We
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received no comments on the NPRM (74
FR 21193, April 17, 2015) or on the
determination of the cost to the public.
Conclusion
We reviewed the relevant data and
determined that air safety and the
public interest require adopting the AD
as proposed except for minor editorial
changes. We have determined that these
minor changes:
• Are consistent with the intent that
was proposed in the NPRM (74 FR
21193, April 17, 2015) for correcting the
unsafe condition; and
• Do not add any additional burden
upon the public than was already
proposed in the NPRM (74 FR 21193,
April 17, 2015).
Relative Service Information Under 1
CFR Part 51
We reviewed GippsAero Mandatory
Service Bulletin SB–GA8–2014–115,
Issue 1, dated October 6, 2014. The
service bulletin describes procedures for
inspecting the orientation of the engine
isolator mounts to verify proper
installation, re-installing if necessary,
and installing steel washers on the
forward side of each side of the engine
isolator mounts. This service
information is reasonably available
because the interested parties have
access to it through their normal course
of business or by the means identified
in the ADDRESSES section of this AD.
Costs of Compliance
We estimate that this AD will affect
13 products of U.S. registry. We also
estimate that it would take about 5
work-hours per product to comply with
the basic requirements of this AD. The
average labor rate is $85 per work-hour.
Required parts would cost about $10 per
product.
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
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]]>Agencies
[Federal Register Volume 80, Number 136 (Thursday, July 16, 2015)]
[Rules and Regulations]
[Pages 42007-42010]
From the Federal Register Online via the Government Publishing Office [www.gpo.gov]
[FR Doc No: 2015-16587]
-----------------------------------------------------------------------
DEPARTMENT OF TRANSPORTATION
Federal Aviation Administration
14 CFR Part 39
[Docket No. FAA-2006-23706; Directorate Identifier 2006-NE-03-AD;
Amendment 39-18177; AD 2015-12-04]
RIN 2120-AA64
Airworthiness Directives; Honeywell International Inc. Turboprop
Engines
AGENCY: Federal Aviation Administration (FAA), DOT.
ACTION: Final rule; correction.
-----------------------------------------------------------------------
SUMMARY: The FAA is correcting an airworthiness directive (AD) that
published in the Federal Register. That AD applies to all Honeywell
International Inc. TPE331-1, -2, -2UA, -3U, -3UW, -5, -5A, -5AB, -5B, -
6, -6A, -10, -10AV, -10GP, -10GT, -10P, -10R, -10T, -10U, -10UA, -10UF,
-10UG, -10UGR, -10UR, -11U, -12JR, -12UA, -12UAR, and -12UHR turboprop
engines with certain Honeywell part numbers (P/Ns) of Woodward fuel
control unit (FCU) assemblies, installed. The AD number in the document
headings is incorrect. Additionally, the Amendment number in the
regulatory text is incorrect. This document corrects these two errors.
In all other respects, the original document remains the same.
DATES: This final rule is effective on July 22, 2015. The effective
date of AD 2015-12-04, Amendment 39-18177 (80 FR 34534, June 17, 2015)
remains July 22, 2015.
ADDRESSES: You may examine the AD docket on the Internet at https://www.regulations.gov; 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: AD 2015-12-04, Amendment 39-18177, 80 FR
34534, June 17, 2015), requires initial and repetitive dimensional
inspections of the affected fuel control drives and insertion of
certain airplane operating procedures into the applicable flight
manuals.
As published, the AD number in the document headings is incorrect.
Additionally, the Amendment number in the regulatory text of AD 2015-
12-04 is incorrect.
No other part of the final rule has been changed.
The effective date of AD 2015-12-04 remains July 22, 2015.
Correction of Non-Regulatory Text
In the Federal Register of June 17, 2015, AD 2015-12-04; Amendment
39-18177 (80 FR 34534) is corrected as follows:
On page 34534, in the 2nd column, on line 6, change ``2014-12-04''
to ``2015-12-04''.
Correction of Regulatory Text
Sec. 39.13 [Corrected]
0
2. The FAA amends Sec. 39.13 by removing airworthiness directive (AD)
2006-15-08, Amendment 39-14688 (71 FR 41121, July 20, 2006), and adding
the following new AD:
2015-12-04 Honeywell International Inc.: Amendment 39-18177; Docket
No. FAA-2006-23706; Directorate Identifier 2006-NE-03-AD.
(a) Effective Date
This AD is effective August 20, 2015.
(b) Affected ADs
This AD replaces AD 2006-15-08, Amendment 39-14688 (71 FR 41121,
July 20, 2006).
(c) Applicability
This AD applies to all Honeywell International Inc. TPE331-1, -
2, -2UA, -3U, -3UW, -5, -5A, -5AB, -5B, -6, -6A, -10, -10AV, -10GP,
-10GT, -10P, -10R, -10T, -10U, -10UA, -10UF, -10UG, -10UGR, -10UR, -
11U, -12JR, -12UA, -12UAR, and -12UHR turboprop engines with
Honeywell part numbers (P/Ns) for Woodward fuel control unit (FCU)
assemblies listed in Table 1 to paragraph (c) of this AD, installed.
Table 1 to Paragraph (c)--Affected FCU Assembly P/Ns
----------------------------------------------------------------------------------------------------------------
Group No. Engine FCU Assembly P/Ns
----------------------------------------------------------------------------------------------------------------
1.......................... TPE331-1, -2, and -2UA......... P/N 869199-13, -20, -21, -22, -23, -24, -25, -26,
27, -28, -29, -31, -32, -33, -34, and -35.
[[Page 42008]]
2 *........................ TPE331-1, -2, and -2UA......... P/N 869199-9, -10, -11, -12, -14, -16, -17, and -
18.
3.......................... TPE331-3U, -3UW, -5, -5A, -5AB, P/N 893561-7, -8, -9, -10, -11, -14, -15, -16, -
-5B, -6, -6A, -10AV, -10GP, - 20, -26, -27, and -29; or
10GT, -10P, and -10T. P/N 897770-1, -3, -7, -9, -10, -11, -12, -14, -15,
-16, -25, -26, and -28.
4 *........................ TPE331-3U, -3UW, -5, -5B, -6, - P/N 893561-4, -5, -12, and -13 or P/N 897770-5, -
6A, and -10T. 8, and -13.
5.......................... TPE331-10, -10R, -10U, -10UA, - P/N 897375-2, -3, -4, -5, -8, -9, -10, -11, -12, -
10UF, -10UG, -10UGR, -10UR, - 13, -14, -15, -16, -17, -19, -21, -24, -25, -26,
11U, -12JR, -12UA, -12UAR, and and -27; or
-12UHR. P/N 897780-1, -2, -3, -4, -5, -6, -7, -8, -9, -10,
-11, -14, -15, -16, -17, -18, -19, -20, -21, -22,
-23, -24, -25, -26, -27, -30, -32, -34, -36, -37,
and -38; or
P/N 893561-17, -18, and -19.
----------------------------------------------------------------------------------------------------------------
* New/added FCU assembly P/Ns
(d) Unsafe Condition
We are issuing this AD to prevent failure of the fuel control
drive that could result in damage to the engine and airplane.
(e) Compliance
Comply with this AD within the compliance times specified,
unless already done.
(1) Inspection of Engines With FCU Assembly P/Ns in Groups 2 and 4
For FCU assembly P/Ns in Groups 2 and 4 listed in Table 1 to
paragraph (c) of this AD:
(i) At the next scheduled inspection of the fuel control drive,
or within 500 hours-in-service (HIS) after the effective date of
this AD, whichever occurs first, inspect the fuel control drive for
wear.
(ii) Thereafter, re-inspect the fuel control drive within every
1,000 HIS since-last-inspection (SLI).
(2) Inspection of Engines With FCU Assembly P/Ns in Groups 1, 3,
and 5
For FCU assembly P/Ns in Groups 1, 3, or 5 listed in Table 1 to
paragraph (c) of this AD:
(i) If on the effective date of this AD the FCU assembly has 950
or more HIS SLI, inspect the fuel control drive for wear within 50
HIS from the effective date of this AD.
(ii) If on the effective date of this AD the FCU assembly has
fewer than 950 HIS SLI, inspect the fuel control drive for wear
before reaching 1,000 HIS.
(iii) Thereafter, re-inspect the fuel control drive for wear
within every 1,000 HIS SLI.
(3) Airplane Operating Procedures
Within 60 days after the effective date of this AD, insert the
information in 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 42009]]
[GRAPHIC] [TIFF OMITTED] TR16JY15.000
(f) Optional Terminating Action
Replacing the affected FCU assembly with an FAA-approved FCU
assembly P/N not listed in this AD is terminating action for the
initial and repetitive inspections required by this AD, and for
inserting the information in Figure 1 to paragraph (e) of this AD
into the AFM, POH, and MOM.
(g) Definitions
For the purposes of this AD:
(1) The ``fuel control drive'' is a series of mating splines
located between the fuel pump and fuel control governor.
(2) The fuel control drive consists of four drive splines: the
fuel pump internal spline, the fuel control external ``quill shaft''
spline, and the stub shaft internal and external splines.
(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) Information pertaining to operating recommendations for
affected engines after a fuel control drive failure is contained in
Honeywell International Inc., Operating Information Letter (OIL)
OI331-12R6, dated May 26, 2009, for multi-engine airplanes; and in
OIL OI331-18R4, dated May 26, 2009, for single-engine airplanes.
Information on fuel control drive inspection can be found in Section
72-00-00 of the applicable TPE331 maintenance manuals. These
Honeywell International Inc., OILs and the TPE331 maintenance
manuals, which are not incorporated by reference in this AD, can be
obtained from Honeywell International Inc., 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; Internet: https://myaerospace.honeywell.com/wps/portal/!ut;
phone: 800-601-3099.
(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.
[[Page 42010]]
Issued in Burlington, Massachusetts, on June 26, 2015.
Ann C. Mollica,
Acting Directorate Manager, Engine and Propeller Directorate, Aircraft
Certification Service.
[FR Doc. 2015-16587 Filed 7-15-15; 8:45 am]
BILLING CODE 4910-13-P
