Airworthiness Directives; Honeywell International Inc. Turboprop Engines, 73020-73023 [2016-25268]

Download as PDF 73020 Federal Register / Vol. 81, No. 205 / Monday, October 24, 2016 / Rules and Regulations (d) The scheduling of an employee’s testimony, including the amount of time that the employee will be made available for testimony, will be subject to the OSC’s approval. ■ § 1820.20 Restrictions that apply to released records. (a) Generally. The General Counsel may condition the production of records or appearance for testimony upon advance payment of a reasonable estimate of the costs to the OSC. (b) Fees for records. Fees for producing records will include fees for searching, reviewing, and duplicating records, costs of attorney time spent in reviewing the request, and expenses generated by materials and equipment used to search for, produce, and copy the responsive information. Costs for employee time will be calculated on the basis of the hourly pay of the employee (including all pay, allowances, and benefits). Fees for duplication will be the same as those charged by the OSC in its Freedom of Information Act regulations at § 1820.7. (c) Witness fees. Fees for attendance by a witness will include fees, expenses, and allowances prescribed by the court’s rules. If no such fees are prescribed, witness fees will be determined based upon the rule of the federal district closest to the location where the witness will appear and on 28 U.S.C. 1821, as applicable. Such fees will include cost of time spent by the witness to prepare for testimony, in travel and for attendance in the legal proceeding, plus travel costs. (d) Payment of fees. A requester must pay witness fees for current OSC employees and any record certification fees by submitting to the General Counsel a check or money order for the appropriate amount made payable to the United States Department of Treasury. In the case of testimony of former OSC employees, the requester must pay applicable fees directly to the former OSC employee in accordance with 28 U.S.C. 1821 or other applicable statutes. (e) Waiver or reduction of fees. The General Counsel, in his or her sole discretion, may, upon a showing of reasonable cause, waive or reduce any fees in connection with the testimony, production, or certification of records. (f) De minimis fees. Fees will not be assessed if the total charge would be $10.00 or less. ■ 10. Add subpart D, consisting of § 1820.24, to read as follows: (a) The General Counsel may impose conditions or restrictions on the release of official records and information, including the requirement that parties to the proceeding obtain a protective order or execute a confidentiality agreement to limit access and any further disclosure. The terms of the protective order or of a confidentiality agreement must be acceptable to the General Counsel. In cases where protective orders or confidentiality agreements have already been executed, the OSC may condition the release of official records and information on an amendment to the existing protective order (subject to court approval) or confidentiality agreement. (b) If the General Counsel so determines, original OSC records may be presented for examination in response to a request, but they may not be presented as evidence or otherwise used in a manner by which they could lose their identity as official OSC records, nor may they be marked or altered. In lieu of the original records, certified copies may be presented for evidentiary purposes. § 1820.21 Procedure when a decision is not made prior to the time a response is required. If a response to a demand or request is required before the General Counsel can make the determination referred to in § 1820.28, the General Counsel, when necessary, will provide the court or other competent authority with a copy of this part, inform the court or other competent authority that the request is being reviewed, provide an estimate as to when a decision will be made, and seek a stay of the demand or request pending a final determination. jstallworth on DSK7TPTVN1PROD with RULES § 1820.22 Procedure in the event of an adverse ruling. If the court or other competent authority fails to stay a demand or request, the employee upon whom the demand or request is made, unless otherwise advised by the General Counsel, will appear, if necessary, at the stated time and place, produce a copy of this part, state that the employee has been advised by counsel not to provide the requested testimony or produce documents, and respectfully decline to comply with the demand or request, citing United States ex rel. Touhy v. Ragen, 340 U.S. 462 (1951). VerDate Sep<11>2014 14:53 Oct 21, 2016 Jkt 241001 9. Add subpart C, consisting of § 1820.23, to read as follows: Subpart C—Schedule of Fees § 1820.23 Fees. Subpart D—Penalties § 1820.24 Penalties. (a) An employee who discloses official records or information or gives testimony relating to official PO 00000 Frm 00006 Fmt 4700 Sfmt 4700 information, except as expressly authorized by the OSC, or as ordered by a federal court after the OSC has had the opportunity to be heard, may face the penalties provided in 18 U.S.C. 641 and other applicable laws. Additionally, former OSC employees are subject to the restrictions and penalties of 18 U.S.C. 207 and 216. (b) A current OSC employee who testifies or produces official records and information in violation of this part shall be subject to disciplinary action. ■ 11. Add subpart E, consisting of § 1820.25, to read as follows: Subpart E—Conformity With Other Laws § 1820.25 Conformity with other laws. This regulation is not intended to conflict with 5 U.S.C. 2302(b)(13). Dated: September 21, 2016. Lisa V. Terry, General Counsel. [FR Doc. 2016–23215 Filed 10–21–16; 8:45 am] BILLING CODE 7405–01–P DEPARTMENT OF TRANSPORTATION Federal Aviation Administration 14 CFR Part 39 [Docket No. FAA–2006–23706; Directorate Identifier 2006–NE–03–AD; Amendment 39– 18688; AD 2016–21–07] RIN 2120–AA64 Airworthiness Directives; Honeywell International Inc. Turboprop Engines Federal Aviation Administration (FAA), DOT. ACTION: Final rule. AGENCY: We are superseding airworthiness directive (AD) 2015–12– 04 for all Honeywell International Inc. (Honeywell) 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 Woodward fuel control unit (FCU) assemblies, installed. AD 2015–12–04 required initial and repetitive dimensional inspections of the affected fuel control drives and insertion of certain airplane operating procedures into the applicable flight manuals. This AD corrects the compliance requirements and relaxes the inspection interval. This AD was prompted by a request to change compliance time from 50 hours to 100 hours for affected fuel controls. We are SUMMARY: E:\FR\FM\24OCR1.SGM 24OCR1 Federal Register / Vol. 81, No. 205 / Monday, October 24, 2016 / Rules and Regulations issuing this AD to prevent failure of the fuel control drive, damage to the engine, and damage to the airplane. DATES: This AD is effective November 28, 2016. ADDRESSES: For service information identified in this final rule, contact Honeywell International Inc., 111 S. 34th Street, Phoenix, AZ 85034–2802; phone: 800–601–3099; Internet: https:// myaerospace.honeywell.com/wps/ portal. You may view this service information at the FAA, Engine & Propeller Directorate, 1200 District Avenue, 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 http://www.regulations.gov by searching for and locating Docket No. FAA–2006– 23706. jstallworth on DSK7TPTVN1PROD with RULES Examining the AD Docket You may examine the AD docket on the Internet at http:// www.regulations.govby searching for and locating Docket No. FAA–2006– 23706; 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 to supersede AD 2015–12–04, Amendment 39–18177, (80 FR 34534, June 17, 2015), (‘‘AD 2015–12–04’’). AD 2015–12–04 applied to all Honeywell 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 Woodward FCU assemblies, installed. The NPRM published in the Federal Register on March 29, 2016 (81 FR 17412). This AD requires correcting VerDate Sep<11>2014 14:53 Oct 21, 2016 Jkt 241001 the compliance requirements and relaxing the inspection interval. We are issuing this AD to prevent failure of the fuel control drive, damage to the engine, and damage to the airplane. Comments We gave the public the opportunity to participate in developing this AD. We received no comments on the NPRM 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 this AD as proposed. Related Service Information We reviewed Honeywell Operating Information Letter (OIL) OI331–12R6, dated May 26, 2009, for multi-engine airplanes; and OIL OI331–18R4, dated May 26, 2009, for single-engine airplanes, and Honeywell TPE331 maintenance manuals. That service information describes procedures for conducting fuel control drive inspections and engine shutdown. Costs of Compliance We estimate that this AD affects 2,250 engines installed on airplanes of U.S. registry. We also estimate that it would take about 8 hours per engine to comply with this AD. The average labor rate is $85 per hour. We estimate that 10% of affected engines will require FCU assembly stub shaft replacement and fuel pump or fuel control repair. We also estimate that repairs will cost about $10,000 per engine. Based on these figures, we estimate the cost of this AD on U.S. operators to be $525,587 per year. 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 PO 00000 Frm 00007 Fmt 4700 Sfmt 4700 73021 products identified in this rulemaking action. Regulatory Findings We have determined that this AD will not have federalism implications under Executive Order 13132. This AD will not have a substantial direct effect on the States, on the relationship between the national government and the States, or on the distribution of power and responsibilities among the various levels of government. For the reasons discussed above, I certify that this AD: (1) Is not a ‘‘significant regulatory action’’ under Executive Order 12866, (2) Is not a ‘‘significant rule’’ under DOT Regulatory Policies and Procedures (44 FR 11034, February 26, 1979), (3) Will not affect intrastate aviation in Alaska, 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 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 airworthiness directive (AD) 2015–12–04, Amendment 39–18177, (80 FR 34534, June 17, 2015), and adding the following new AD: ■ 2016–21–07 Honeywell International Inc.: Amendment 39–18688; Docket No. FAA–2006–23706; Directorate Identifier 2006–NE–03–AD. (a) Effective Date This AD is effective November 28, 2016. (b) Affected ADs This AD replaces AD 2015–12–04, Amendment 39–18177, (80 FR 34534, June 17, 2015). (c) Applicability This AD applies to all Honeywell International Inc. (Honeywell) TPE331–1, –2, –2UA, –3U, –3UW, –5, –5A, –5AB, –5B, –6, –6A, –10, –10AV, –10GP, –10GT, –10P, –10R, –10T, –10U, –10UA, –10UF, –10UG, E:\FR\FM\24OCR1.SGM 24OCR1 73022 Federal Register / Vol. 81, No. 205 / Monday, October 24, 2016 / Rules and Regulations –10UGR, –10UR, –11U, –12JR, –12UA, –12UAR, and –12UHR turboprop engines with Woodward fuel control unit (FCU) assemblies with Honeywell part numbers (P/ Ns) as listed in Table 1 to paragraph (c) of this AD, installed. TABLE 1 TO PARAGRAPH (c)—AFFECTED FCU ASSEMBLY P/NS Group # Engine FCU Assembly P/Ns 1 ................... TPE331–1, –2, and –2UA ......................... 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. P/N 869199–13, –20, –21, –22, –23, –24, –25, –26, –27, –28, –29, –31, –32, –33, –34, and –35. 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, –29; and P/N 897770–1, –3, –7, –9, –10, –11, –12, –14, –15, –16, –25, –26, and –28. 4 ................... 5 ................... (d) Unsafe Condition This AD was prompted by reports of loss of the fuel control drive, leading to engine overspeed and engine failure. We are issuing this AD to prevent failure of the fuel control drive, damage to the engine, and damage to the airplane. (e) Compliance Comply with this AD within the compliance times specified, unless already done. jstallworth on DSK7TPTVN1PROD with RULES (1) Inspection of Engines With FCU Assembly P/Ns in Groups 2 or 4 For FCU assembly P/Ns in Groups 2 or 4 listed in Table 1 to paragraph (c) of this AD: VerDate Sep<11>2014 14:53 Oct 21, 2016 Jkt 241001 P/N 893561–4, –5, –12, –13; and 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, –27; and 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, –38; and P/N 893561–17, –18, and –19. (i) At the next scheduled inspection of the fuel control drive, or within 500 hours-inservice (HIS) after the effective date of this AD, whichever occurs first, inspect the fuel control drive for wear. (ii) Thereafter, reinspect 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 900 HIS SLI, inspect the fuel control drive for wear within 1,000 HIS. (iii) Thereafter, reinspect 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, or 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 900 or more HIS SLI, inspect the fuel control drive for wear within 100 HIS after the effective date of this AD. 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 applicable Airplane Flight Manual (AFM), Pilot Operating Handbook (POH), or the Manufacturer’s Operating Manual (MOM). PO 00000 Frm 00008 Fmt 4700 Sfmt 4700 (3) Airplane Operating Procedures BILLING CODE 4910–13–P E:\FR\FM\24OCR1.SGM 24OCR1 Federal Register / Vol. 81, No. 205 / Monday, October 24, 2016 / Rules and Regulations (f) Optional Terminating Action Replacing the affected FCU assembly with an FAA-approved FCU assembly not listed in this AD by P/N 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. jstallworth on DSK7TPTVN1PROD with RULES (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. VerDate Sep<11>2014 14:53 Oct 21, 2016 Jkt 241001 (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 Operating Information Letter (OIL) OI331–12R6, dated May 26, 2009, for multi-engine airplanes; and 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 PO 00000 Frm 00009 Fmt 4700 Sfmt 9990 of the applicable TPE331 maintenance manuals. These Honeywell OILs and the TPE331 maintenance manuals can be obtained from Honeywell 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:// myaerospace.honeywell.com/wps/portal. (4) You may view this service information at FAA, Engine & Propeller Directorate, 1200 District Avenue, Burlington, MA. For information on the availability of this material at the FAA, call 781–238–7125. Issued in Burlington, Massachusetts, on October 14, 2016. Colleen M. D’Alessandro, Manager, Engine & Propeller Directorate, Aircraft Certification Service. [FR Doc. 2016–25268 Filed 10–21–16; 8:45 am] BILLING CODE 4910–13–P E:\FR\FM\24OCR1.SGM 24OCR1 ER24OC16.000</GPH> BILLING CODE 4910–13–C 73023

Agencies

[Federal Register Volume 81, Number 205 (Monday, October 24, 2016)]
[Rules and Regulations]
[Pages 73020-73023]
From the Federal Register Online via the Government Publishing Office [www.gpo.gov]
[FR Doc No: 2016-25268]


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DEPARTMENT OF TRANSPORTATION

Federal Aviation Administration

14 CFR Part 39

[Docket No. FAA-2006-23706; Directorate Identifier 2006-NE-03-AD; 
Amendment 39-18688; AD 2016-21-07]
RIN 2120-AA64


Airworthiness Directives; Honeywell International Inc. Turboprop 
Engines

AGENCY: Federal Aviation Administration (FAA), DOT.

ACTION: Final rule.

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

SUMMARY: We are superseding airworthiness directive (AD) 2015-12-04 for 
all Honeywell International Inc. (Honeywell) 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 Woodward fuel control 
unit (FCU) assemblies, installed. AD 2015-12-04 required initial and 
repetitive dimensional inspections of the affected fuel control drives 
and insertion of certain airplane operating procedures into the 
applicable flight manuals. This AD corrects the compliance requirements 
and relaxes the inspection interval. This AD was prompted by a request 
to change compliance time from 50 hours to 100 hours for affected fuel 
controls. We are

[[Page 73021]]

issuing this AD to prevent failure of the fuel control drive, damage to 
the engine, and damage to the airplane.

DATES: This AD is effective November 28, 2016.

ADDRESSES: For service information identified in this final rule, 
contact Honeywell International Inc., 111 S. 34th Street, Phoenix, AZ 
85034-2802; phone: 800-601-3099; Internet: https://myaerospace.honeywell.com/wps/portal. You may view this service 
information at the FAA, Engine & Propeller Directorate, 1200 District 
Avenue, 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 http://www.regulations.gov by searching for and locating 
Docket No. FAA-2006-23706.

Examining the AD Docket

    You may examine the AD docket on the Internet at http://www.regulations.govby searching for and locating Docket No. FAA-2006-
23706; 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 to supersede AD 2015-12-04, Amendment 39-18177, (80 FR 34534, 
June 17, 2015), (``AD 2015-12-04''). AD 2015-12-04 applied to all 
Honeywell 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 Woodward FCU assemblies, installed. The NPRM published in 
the Federal Register on March 29, 2016 (81 FR 17412). This AD requires 
correcting the compliance requirements and relaxing the inspection 
interval. We are issuing this AD to prevent failure of the fuel control 
drive, damage to the engine, and damage to the airplane.

Comments

    We gave the public the opportunity to participate in developing 
this AD. We received no comments on the NPRM 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 this AD as proposed.

Related Service Information

    We reviewed Honeywell Operating Information Letter (OIL) OI331-
12R6, dated May 26, 2009, for multi-engine airplanes; and OIL OI331-
18R4, dated May 26, 2009, for single-engine airplanes, and Honeywell 
TPE331 maintenance manuals. That service information describes 
procedures for conducting fuel control drive inspections and engine 
shutdown.

Costs of Compliance

    We estimate that this AD affects 2,250 engines installed on 
airplanes of U.S. registry. We also estimate that it would take about 8 
hours per engine to comply with this AD. The average labor rate is $85 
per hour. We estimate that 10% of affected engines will require FCU 
assembly stub shaft replacement and fuel pump or fuel control repair. 
We also estimate that repairs will cost about $10,000 per engine. Based 
on these figures, we estimate the cost of this AD on U.S. operators to 
be $525,587 per year.

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 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, 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 removing airworthiness directive (AD) 
2015-12-04, Amendment 39-18177, (80 FR 34534, June 17, 2015), and 
adding the following new AD:

2016-21-07 Honeywell International Inc.: Amendment 39-18688; Docket 
No. FAA-2006-23706; Directorate Identifier 2006-NE-03-AD.

(a) Effective Date

    This AD is effective November 28, 2016.

(b) Affected ADs

    This AD replaces AD 2015-12-04, Amendment 39-18177, (80 FR 
34534, June 17, 2015).

(c) Applicability

    This AD applies to all Honeywell International Inc. (Honeywell) 
TPE331-1, -2, -2UA, -3U, -3UW, -5, -5A, -5AB, -5B, -6, -6A, -10, -
10AV, -10GP, -10GT, -10P, -10R, -10T, -10U, -10UA, -10UF, -10UG,

[[Page 73022]]

-10UGR, -10UR, -11U, -12JR, -12UA, -12UAR, and -12UHR turboprop 
engines with Woodward fuel control unit (FCU) assemblies with 
Honeywell part numbers (P/Ns) as listed in Table 1 to paragraph (c) 
of this AD, installed.

          Table 1 to Paragraph (c)--Affected FCU Assembly P/Ns
------------------------------------------------------------------------
        Group #                 Engine             FCU Assembly P/Ns
------------------------------------------------------------------------
1.....................  TPE331-1, -2, and -    P/N 869199-13, -20, -21,
                         2UA.                   22, -23, -24, -25, -26,
                                                27, -28, -29, -31, -32,
                                                33, -34, and -35.
2.....................  TPE331-1, -2, and -    P/N 869199-9, -10, -11, -
                         2UA.                   12, -14, -16, -17, and -
                                                18.
3.....................  TPE331-3U, -3UW, -5, - P/N 893561-7, -8, -9, -
                         5A, -5AB, -5B, -6, -   10, -11, -14, -15, -16,
                         6A, -10AV, -10GP, -    20, -26, -27, -29; and
                         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, - P/N 893561-4, -5, -12, -
                         5B, -6, -6A, and -     13; and
                         10T.                  P/N 897770-5, -8, and -
                                                13.
5.....................  TPE331-10, -10R, -     P/N 897375-2, -3, -4, -5,
                         10U, -10UA, -10UF, -   -8, -9, -10, -11, -12, -
                         10UG, -10UGR, -10UR,   13, -14, -15, -16, -17,
                         -11U, -12JR, -12UA, -  19, -21, -24, -25, -26,
                         12UAR, and -12UHR.     27; and
                                               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,
                                                -38; and
                                               P/N 893561-17, -18, and -
                                                19.
------------------------------------------------------------------------

(d) Unsafe Condition

    This AD was prompted by reports of loss of the fuel control 
drive, leading to engine overspeed and engine failure. We are 
issuing this AD to prevent failure of the fuel control drive, damage 
to the engine, and damage to the 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 or 4

    For FCU assembly P/Ns in Groups 2 or 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, reinspect 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, or 
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 
900 or more HIS SLI, inspect the fuel control drive for wear within 
100 HIS after the effective date of this AD.
    (ii) If, on the effective date of this AD, the FCU assembly has 
fewer than 900 HIS SLI, inspect the fuel control drive for wear 
within 1,000 HIS.
    (iii) Thereafter, reinspect 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 applicable Airplane Flight 
Manual (AFM), Pilot Operating Handbook (POH), or the Manufacturer's 
Operating Manual (MOM).
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(f) Optional Terminating Action

    Replacing the affected FCU assembly with an FAA-approved FCU 
assembly not listed in this AD by P/N 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 Operating Information Letter (OIL) OI331-12R6, dated May 
26, 2009, for multi-engine airplanes; and 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 OILs and the TPE331 
maintenance manuals can be obtained from Honeywell 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://myaerospace.honeywell.com/wps/portal.
    (4) You may view this service information at FAA, Engine & 
Propeller Directorate, 1200 District Avenue, Burlington, MA. For 
information on the availability of this material at the FAA, call 
781-238-7125.

    Issued in Burlington, Massachusetts, on October 14, 2016.
Colleen M. D'Alessandro,
Manager, Engine & Propeller Directorate, Aircraft Certification 
Service.
[FR Doc. 2016-25268 Filed 10-21-16; 8:45 am]
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