81_FR_17472 81 FR 17412 - Airworthiness Directives; Honeywell International Inc. Turboprop Engines

81 FR 17412 - Airworthiness Directives; Honeywell International Inc. Turboprop Engines

DEPARTMENT OF TRANSPORTATION
Federal Aviation Administration

Federal Register Volume 81, Issue 60 (March 29, 2016)

Page Range17412-17415
FR Document2016-06936

We propose to supersede airworthiness directive (AD) 2015-12- 04, which 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, -10UGR, - 10UR, -11U, -12JR, -12UA, -12UAR, and -12UHR turboprop engines with certain Woodward fuel control unit (FCU) assemblies, installed. AD 2015-12-04 currently requires initial and repetitive dimensional inspections of the affected fuel control drives and insertion of certain airplane operating procedures into the applicable flight manuals. This proposed AD would correct compliance requirements and relax the inspection interval. We are proposing this AD to prevent failure of the fuel control drive, damage to the engine, and damage to the airplane.

Federal Register, Volume 81 Issue 60 (Tuesday, March 29, 2016) 
[Federal Register Volume 81, Number 60 (Tuesday, March 29, 2016)]
[Proposed Rules]
[Pages 17412-17415]
From the Federal Register Online  [www.thefederalregister.org]
[FR Doc No: 2016-06936]


========================================================================
Proposed Rules
                                                Federal Register
________________________________________________________________________

This section of the FEDERAL REGISTER contains notices to the public of 
the proposed issuance of rules and regulations. The purpose of these 
notices is to give interested persons an opportunity to participate in 
the rule making prior to the adoption of the final rules.

========================================================================


Federal Register / Vol. 81, No. 60 / Tuesday, March 29, 2016 / 
Proposed Rules

[[Page 17412]]



DEPARTMENT OF TRANSPORTATION

Federal Aviation Administration

14 CFR Part 39

[Docket No. FAA-2006-23706; Directorate Identifier 2006-NE-03-AD]
RIN 2120-AA64


Airworthiness Directives; Honeywell International Inc. Turboprop 
Engines

AGENCY: Federal Aviation Administration (FAA), DOT.

ACTION: Notice of proposed rulemaking (NPRM).

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

SUMMARY: We propose to supersede airworthiness directive (AD) 2015-12-
04, which 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, -10UGR, -
10UR, -11U, -12JR, -12UA, -12UAR, and -12UHR turboprop engines with 
certain Woodward fuel control unit (FCU) assemblies, installed. AD 
2015-12-04 currently requires initial and repetitive dimensional 
inspections of the affected fuel control drives and insertion of 
certain airplane operating procedures into the applicable flight 
manuals. This proposed AD would correct compliance requirements and 
relax the inspection interval. We are proposing this AD to prevent 
failure of the fuel control drive, damage to the engine, and damage to 
the airplane.

DATES: We must receive comments on this proposed AD by May 31, 2016.

ADDRESSES: You may send comments, using the procedures found in 14 CFR 
11.43 and 11.45, by any of the following methods:
     Federal eRulemaking Portal: Go to http://www.regulations.gov. Follow the instructions for submitting comments.
     Fax: 202-493-2251.
     Mail: U.S. Department of Transportation, Docket 
Operations, M-30, West Building Ground Floor, Room W12-140, 1200 New 
Jersey Avenue SE., Washington, DC 20590.
     Hand Delivery: Deliver to Mail address above between 9 
a.m. and 5 p.m., Monday through Friday, except Federal holidays.
    For service information identified in this proposed AD, 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.gov by 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 proposed AD, the regulatory evaluation, any 
comments received, and other information. The street address for the 
Docket Office (phone: 800-647-5527) is in the ADDRESSES section. 
Comments will be available in the AD docket shortly after receipt.

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: [email protected].

SUPPLEMENTARY INFORMATION:

Comments Invited

    We invite you to send any written relevant data, views, or 
arguments about this NPRM. Send your comments to an address listed 
under the ADDRESSES section. Include ``Docket No. FAA-2006-23706; 
Directorate Identifier 2006-NE-03-AD'' at the beginning of your 
comments. We specifically invite comments on the overall regulatory, 
economic, environmental, and energy aspects of this NPRM. We will 
consider all comments received by the closing date and may amend this 
NPRM because of those comments.
    We will post all comments we receive, without change, to http://www.regulations.gov, including any personal information you provide. We 
will also post a report summarizing each substantive verbal contact we 
receive about this NPRM.

Discussion

    On June 5, 2015, we issued AD 2015-12-04, Amendment 39-18177, (80 
FR 34534, June 17, 2015) (``AD 2015-12-04''), for 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 Woodward FCU assemblies, installed. AD 2015-12-04 
requires initial and repetitive dimensional inspections of the affected 
fuel control drives and insertion of certain airplane operating 
procedures into the applicable flight manuals. AD 2015-12-04 resulted 
from reports of loss of the fuel control drive, leading to engine 
overspeed, overtorque, overtemperature, uncontained rotor failure, and 
asymmetric thrust in multi-engine airplanes. We issued AD 2015-12-04 to 
prevent failure of the fuel control drive, damage to the engine, and 
damage to the airplane.

Actions Since AD 2015-12-04 Was Issued

    We received a request to change compliance time from 50 hours to 
100 hours for fuel control part numbers affected by paragraph (e)(2) of 
this AD. We concluded that because the number of fuel control drives 
in-service that had not completed an initial inspection was small, 
changing the compliance time to 100 hours would not add additional risk 
of fuel control drive failure and, therefore, is appropriate.
    We also received reports that some airplanes do not use the 
condition lever to shut down the engine, and so could not comply with 
the AD. We concluded that references to a condition lever were 
inappropriate. This proposed AD eliminates references to a condition 
lever.

[[Page 17413]]

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. The service information describes 
procedures for conducting fuel control drive inspections and engine 
shutdown.

FAA's Determination

    We are proposing this NPRM because we information evaluated all the 
relevant and determined the unsafe condition described previously is 
likely to exist or develop in other products of the same type design.

Proposed AD Requirements

    This NPRM would increase the inspection time limits for the FCU 
assembly from 50 to 100 hours-in-service in Compliance paragraph (e)(2) 
of this AD. This NPRM would also delete reference to the condition 
lever.

Costs of Compliance

    We estimate that this proposed 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 proposed 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 proposed AD would not have federalism 
implications under Executive Order 13132. This proposed AD would not 
have a substantial direct effect on the States, on the relationship 
between the national Government and the States, or on the distribution 
of power and responsibilities among the various levels of government.
    For the reasons discussed above, I certify that the proposed 
regulation:
    (1) Is not a ``significant regulatory action'' under Executive 
Order 12866,
    (2) Is not a ``significant rule'' under the DOT Regulatory Policies 
and Procedures (44 FR 11034, February 26, 1979),
    (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.

The Proposed Amendment

    Accordingly, under the authority delegated to me by the 
Administrator, the FAA proposes to amend 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) (``AD 2015-
12-04''), and adding the following new AD:

Honeywell International Inc.: Docket No. FAA-2006-23706; Directorate 
Identifier 2006-NE-03-AD.

(a) Comments Due Date

    The FAA must receive comments on this AD action by May 31, 2016.

(b) Affected ADs

    This AD replaces AD 2015-12-04.

(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, -
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, -l0AV, -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, -l0R, -     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.
------------------------------------------------------------------------


[[Page 17414]]

(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, 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, 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, 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 applicable Airplane Flight 
Manual (AFM), Pilot Operating Handbook (POH), or the Manufacturer's 
Operating Manual (MOM).
[GRAPHIC] [TIFF OMITTED] TP29MR16.000

(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:

[[Page 17415]]

    (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: 
[email protected].
    (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 proposed 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 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.

    Issued in Burlington, Massachusetts, on March 15, 2016.
Ann C. Mollica,
Acting Manager, Engine and Propeller Directorate, Aircraft 
Certification Service.
[FR Doc. 2016-06936 Filed 3-28-16; 8:45 am]
 BILLING CODE 4910-13-P

17412 Proposed Rules Federal Register Vol. 81, No. 60 Tuesday, March 29, 2016 This section of the FEDERAL REGISTER W12–140, 1200 New Jersey Avenue SE., all comments received by the closing contains notices to the public of the proposed Washington, DC 20590. date and may amend this NPRM issuance of rules and regulations. The • Hand Delivery: Deliver to Mail because of those comments. purpose of these notices is to give interested address above between 9 a.m. and 5 persons an opportunity to participate in the We will post all comments we p.m., Monday through Friday, except rule making prior to the adoption of the final receive, without change, to http:// Federal holidays. rules. www.regulations.gov, including any For service information identified in this proposed AD, contact Honeywell personal information you provide. We International Inc., 111 S. 34th Street, will also post a report summarizing each DEPARTMENT OF TRANSPORTATION substantive verbal contact we receive Phoenix, AZ 85034–2802; phone: 800– 601–3099; Internet: https:// about this NPRM. Federal Aviation Administration myaerospace.honeywell.com/wps/ Discussion 14 CFR Part 39 portal. You may view this service information at the FAA, Engine & On June 5, 2015, we issued AD 2015– [Docket No. FAA–2006–23706; Directorate Propeller Directorate, 1200 District 12–04, Amendment 39–18177, (80 FR Identifier 2006–NE–03–AD] Avenue, Burlington, MA. For 34534, June 17, 2015) (‘‘AD 2015–12– RIN 2120–AA64 information on the availability of this 04’’), for all Honeywell International material at the FAA, call 781–238–7125. Inc. TPE331–1, –2, –2UA, –3U, –3UW, Airworthiness Directives; Honeywell It is also available on the Internet at –5, –5A, –5AB, –5B, –6, –6A, –10, International Inc. Turboprop Engines http://www.regulations.gov by searching –10AV, –10GP, –10GT, –10P, –10R, for and locating Docket No. FAA–2006– –10T, –10U, –10UA, –10UF, –10UG, AGENCY: Federal Aviation 23706. –10UGR, –10UR, –11U, –12JR, –12UA, Administration (FAA), DOT. –12UAR, and –12UHR turboprop Examining the AD Docket ACTION: Notice of proposed rulemaking engines with certain Woodward FCU (NPRM). You may examine the AD docket on assemblies, installed. AD 2015–12–04 the Internet at http:// requires initial and repetitive SUMMARY: We propose to supersede www.regulations.gov by searching for dimensional inspections of the affected airworthiness directive (AD) 2015–12– and locating Docket No. FAA–2006– fuel control drives and insertion of 04, which applies to all Honeywell 23706; or in person at the Docket certain airplane operating procedures International Inc. (Honeywell) TPE331– Management Facility between 9 a.m. into the applicable flight manuals. AD 1, –2, –2UA, –3U, –3UW, –5, –5A, and 5 p.m., Monday through Friday, 2015–12–04 resulted from reports of –5AB, –5B, –6, –6A, –10, –10AV, except Federal holidays. The AD docket loss of the fuel control drive, leading to –10GP, –10GT, –10P, –10R, –10T, –10U, contains this proposed AD, the engine overspeed, overtorque, –10UA, –10UF, –10UG, –10UGR, regulatory evaluation, any comments overtemperature, uncontained rotor –10UR, –11U, –12JR, –12UA, –12UAR, received, and other information. The and –12UHR turboprop engines with failure, and asymmetric thrust in multi- street address for the Docket Office certain Woodward fuel control unit engine airplanes. We issued AD 2015– (phone: 800–647–5527) is in the (FCU) assemblies, installed. AD 2015– 12–04 to prevent failure of the fuel ADDRESSES section. Comments will be 12–04 currently requires initial and control drive, damage to the engine, and available in the AD docket shortly after repetitive dimensional inspections of damage to the airplane. receipt. the affected fuel control drives and FOR FURTHER INFORMATION CONTACT: Actions Since AD 2015–12–04 Was insertion of certain airplane operating Joseph Costa, Aerospace Engineer, Los Issued procedures into the applicable flight Angeles Aircraft Certification Office, manuals. This proposed AD would FAA, Transport Airplane Directorate, We received a request to change correct compliance requirements and 3960 Paramount Blvd., Lakewood, CA compliance time from 50 hours to 100 relax the inspection interval. We are 90712–4137; phone: 562–627–5246; fax: hours for fuel control part numbers proposing this AD to prevent failure of 562–627–5210; email: joseph.costa@ affected by paragraph (e)(2) of this AD. the fuel control drive, damage to the faa.gov. We concluded that because the number engine, and damage to the airplane. of fuel control drives in-service that had SUPPLEMENTARY INFORMATION: DATES: We must receive comments on not completed an initial inspection was this proposed AD by May 31, 2016. Comments Invited small, changing the compliance time to ADDRESSES: You may send comments, We invite you to send any written 100 hours would not add additional risk using the procedures found in 14 CFR relevant data, views, or arguments about of fuel control drive failure and, 11.43 and 11.45, by any of the following this NPRM. Send your comments to an therefore, is appropriate. mstockstill on DSK4VPTVN1PROD with PROPOSALS methods: address listed under the ADDRESSES We also received reports that some • Federal eRulemaking Portal: Go to section. Include ‘‘Docket No. FAA– airplanes do not use the condition lever http://www.regulations.gov. Follow the 2006–23706; Directorate Identifier to shut down the engine, and so could instructions for submitting comments. 2006–NE–03–AD’’ at the beginning of not comply with the AD. We concluded • Fax: 202–493–2251. your comments. We specifically invite that references to a condition lever were • Mail: U.S. Department of comments on the overall regulatory, inappropriate. This proposed AD Transportation, Docket Operations, M– economic, environmental, and energy eliminates references to a condition 30, West Building Ground Floor, Room aspects of this NPRM. We will consider lever. VerDate Sep<11>2014 16:52 Mar 28, 2016 Jkt 238001 PO 00000 Frm 00001 Fmt 4702 Sfmt 4702 E:\FR\FM\29MRP1.SGM 29MRP1

Federal Register / Vol. 81, No. 60 / Tuesday, March 29, 2016 / Proposed Rules 17413 Related Service Information rules on aviation safety. Subtitle I, List of Subjects in 14 CFR Part 39 We reviewed Honeywell Operating Section 106, describes the authority of the FAA Administrator. Subtitle VII, Air transportation, Aircraft, Aviation Information Letter (OIL) OI331–12R6, safety, Incorporation by reference, dated May 26, 2009, for multi-engine Aviation Programs, describes in more detail the scope of the Agency’s Safety. airplanes; and OIL OI331–18R4, dated May 26, 2009, for single-engine authority. The Proposed Amendment We are issuing this rulemaking under airplanes and Honeywell TPE331 the authority described in Subtitle VII, Accordingly, under the authority maintenance manuals. The service Part A, Subpart III, Section 44701, delegated to me by the Administrator, information describes procedures for ‘‘General requirements.’’ Under that conducting fuel control drive the FAA proposes to amend 14 CFR part section, Congress charges the FAA with 39 as follows: inspections and engine shutdown. promoting safe flight of civil aircraft in FAA’s Determination air commerce by prescribing regulations PART 39—AIRWORTHINESS for practices, methods, and procedures DIRECTIVES We are proposing this NPRM because the Administrator finds necessary for we information evaluated all the safety in air commerce. This regulation ■ 1. The authority citation for part 39 relevant and determined the unsafe is within the scope of that authority continues to read as follows: condition described previously is likely because it addresses an unsafe condition to exist or develop in other products of Authority: 49 U.S.C. 106(g), 40113, 44701. that is likely to exist or develop on the same type design. products identified in this rulemaking § 39.13 [Amended] Proposed AD Requirements action. ■ 2. The FAA amends § 39.13 by This NPRM would increase the Regulatory Findings removing airworthiness directive (AD) inspection time limits for the FCU We have determined that this 2015–12–04, Amendment 39–18177 (80 assembly from 50 to 100 hours-in- proposed AD would not have federalism FR 34534, June 17, 2015) (‘‘AD 2015– service in Compliance paragraph (e)(2) implications under Executive Order 12–04’’), and adding the following new of this AD. This NPRM would also 13132. This proposed AD would not AD: delete reference to the condition lever. have a substantial direct effect on the Honeywell International Inc.: Docket No. Costs of Compliance States, on the relationship between the FAA–2006–23706; Directorate Identifier national Government and the States, or 2006–NE–03–AD. We estimate that this proposed AD on the distribution of power and affects 2,250 engines installed on responsibilities among the various (a) Comments Due Date airplanes of U.S. registry. We also levels of government. The FAA must receive comments on this estimate that it would take about 8 For the reasons discussed above, I AD action by May 31, 2016. hours per engine to comply with this certify that the proposed regulation: proposed AD. The average labor rate is (b) Affected ADs (1) Is not a ‘‘significant regulatory $85 per hour. We estimate that 10% of action’’ under Executive Order 12866, This AD replaces AD 2015–12–04. affected engines will require FCU (2) Is not a ‘‘significant rule’’ under (c) Applicability assembly stub shaft replacement and the DOT Regulatory Policies and This AD applies to all Honeywell fuel pump or fuel control repair. We Procedures (44 FR 11034, February 26, International Inc. (Honeywell) TPE331–1, –2, also estimate that repairs will cost about 1979), –2UA, –3U, –3UW, –5, –5A, –5AB, –5B, –6, $10,000 per engine. Based on these (3) Will not affect intrastate aviation –6A, –10, –10AV, –10GP, –10GT, –10P, –10R, figures, we estimate the cost of this AD in Alaska to the extent that it justifies –10T, –10U, –10UA, –10UF, –10UG, on U.S. operators to be $525,587 per making a regulatory distinction, and –10UGR, –10UR, –11U, –12JR, –12UA, year. (4) Will not have a significant –12UAR, and –12UHR turboprop engines economic impact, positive or negative, with Woodward fuel control unit (FCU) Authority for This Rulemaking on a substantial number of small entities assemblies with Honeywell part numbers (P/ Title 49 of the United States Code under the criteria of the Regulatory Ns) as listed in Table 1 to paragraph (c) of specifies the FAA’s authority to issue Flexibility Act. 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 ......................... P/N 869199–13, –20, –21, –22, –23, –24, –25, –26, –27, –28, –29, –31, –32, –33, –34, and –35. 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, –5B, P/N 893561–7, –8, –9, –10, –11, –14, –15, –16, –20, –26, –27, –29; and –6, –6A, –l0AV, –10GP, –10GT, –10P, P/N 897770–1, –3, –7, –9, –10, –11, –12, –14, –15, –16, –25, –26, and –28. and –10T. 4 ................... TPE331–3U, –3UW, –5, –5B, –6, –6A, P/N 893561–4, –5, –12, –13; and and –10T. P/N 897770–5, –8, and –13. mstockstill on DSK4VPTVN1PROD with PROPOSALS 5 ................... TPE331–10, –l0R, –10U, –10UA, –10UF, P/N 897375–2, –3, –4, –5, –8, –9, –10, –11, –12, –13, –14, –15, –16, –17, –19, –10UG, –10UGR, –10UR, –11U, –21, –24, –25, –26, –27; and –12JR, –12UA, –12UAR, and –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, –38; and P/N 893561–17, –18, and –19. VerDate Sep<11>2014 16:52 Mar 28, 2016 Jkt 238001 PO 00000 Frm 00002 Fmt 4702 Sfmt 4702 E:\FR\FM\29MRP1.SGM 29MRP1

17414 Federal Register / Vol. 81, No. 60 / Tuesday, March 29, 2016 / Proposed Rules (d) Unsafe Condition (i) At the next scheduled inspection of the (ii) If on the effective date of this AD the This AD was prompted by reports of loss fuel control drive, or within 500 hours-in- FCU assembly has fewer than 900 HIS SLI, of the fuel control drive, leading to engine service (HIS) after the effective date of this inspect the fuel control drive for wear within overspeed and engine failure. We are issuing AD, whichever occurs first, inspect the fuel 1,000 HIS. this AD to prevent failure of the fuel control control drive for wear. (iii) Thereafter, re-inspect the fuel control drive, damage to the engine, and damage to (ii) Thereafter, re-inspect the fuel control drive for wear within every 1,000 HIS SLI. the airplane. drive within every 1,000 HIS since-last- inspection (SLI). (3) Airplane Operating Procedures (e) Compliance (2) Inspection of Engines With FCU Within 60 days after the effective date of Comply with this AD within the Assembly P/Ns in Groups 1, 3, or 5 compliance times specified, unless already this AD, insert the information in Figure 1 to done. For FCU assembly P/Ns in Groups 1, 3, or paragraph (e) of this AD, into the Emergency 5 listed in Table 1 to paragraph (c) of this AD: Procedures Section of the applicable (1) Inspection of Engines With FCU (i) If on the effective date of this AD the Airplane Flight Manual (AFM), Pilot Assembly P/Ns in Groups 2 or 4 FCU assembly has 900 or more HIS SLI, Operating Handbook (POH), or the For FCU assembly P/Ns in Groups 2 or 4 inspect the fuel control drive for wear within Manufacturer’s Operating Manual (MOM). listed in Table 1 to paragraph (c) of this AD: 100 HIS after the effective date of this AD. mstockstill on DSK4VPTVN1PROD with PROPOSALS (f) Optional Terminating Action initial and repetitive inspections required by (g) Definitions Replacing the affected FCU assembly with this AD, and for inserting the information in For the purposes of this AD: an FAA-approved FCU assembly not listed in Figure 1 to paragraph (e) of this AD into the this AD by P/N is terminating action for the AFM, POH, and MOM. EP29MR16.000</GPH> VerDate Sep<11>2014 16:52 Mar 28, 2016 Jkt 238001 PO 00000 Frm 00003 Fmt 4702 Sfmt 4702 E:\FR\FM\29MRP1.SGM 29MRP1

Federal Register / Vol. 81, No. 60 / Tuesday, March 29, 2016 / Proposed Rules 17415 (1) The ‘‘fuel control drive’’ is a series of Notice of proposed rulemaking ACTION: Management Facility between 9 a.m. mating splines located between the fuel (NPRM). and 5 p.m., Monday through Friday, pump and fuel control governor. except Federal holidays. The AD docket (2) The fuel control drive consists of four SUMMARY: We propose to adopt a new contains this proposed AD, the drive splines: The fuel pump internal spline, airworthiness directive (AD) for all The the fuel control external ‘‘quill shaft’’ spline, regulatory evaluation, any comments Boeing Company Model 737–600, –700, received, and other information. The and the stub shaft internal and external –700C, –800, –900, and 900ER series street address for the Docket Office splines. airplanes. This proposed AD was (phone: 800–647–5527) is in the (h) Alternative Methods of Compliance prompted by an evaluation by the ADDRESSES section. Comments will be (AMOCs) design approval holder (DAH) available in the AD docket shortly after The Manager, Los Angeles Aircraft indicating that the S–14L and S–14R lap receipt. Certification Office, FAA, may approve splices are subject to widespread fatigue AMOCs for this AD. Use the procedures FOR FURTHER INFORMATION CONTACT: damage (WFD). This proposed AD found in 14 CFR 39.19 to make your request. Jason Deutschman, Aerospace Engineer, would require repetitive low frequency Airframe Branch, ANM–120S, FAA, (i) Related Information eddy current inspections for cracking in Seattle Aircraft Certification Office (1) For more information about this AD, the lower fastener row of the S–14L and (ACO), 1601 Lind Avenue SW., Renton, contact Joseph Costa, Aerospace Engineer, S–14R lap splices and repair if WA 98057–3356; phone: 425–917–6595; Los Angeles Aircraft Certification Office, necessary. We are proposing this AD to fax: 425–917–6590; email: FAA, Transport Airplane Directorate, 3960 detect and correct widespread cracking Paramount Blvd., Lakewood, CA 90712– Jason.deutschman@faa.gov. in the S–14L and S–14R lap splices that 4137; phone: 562–627–5246; fax: 562–627– could rapidly link up and result in SUPPLEMENTARY INFORMATION: 5210; email: joseph.costa@faa.gov. possible rapid decompression and (2) Information pertaining to operating Comments Invited reduced structural integrity of the recommendations for affected engines after a We invite you to send any written fuel control drive failure is contained in airplane. relevant data, views, or arguments about Honeywell Operating Information Letter DATES: We must receive comments on this proposal. Send your comments to (OIL) OI331–12R6, dated May 26, 2009, for this proposed AD by May 13, 2016. an address listed under the ADDRESSES multi-engine airplanes; and OIL OI331–18R4, ADDRESSES: You may send comments, section. Include ‘‘Docket No. FAA– dated May 26, 2009, for single-engine airplanes. Information on fuel control drive using the procedures found in 14 CFR 2016–5034; Directorate Identifier 2015– inspection can be found in Section 72–00–00 11.43 and 11.45, by any of the following NM–172–AD’’ at the beginning of your of the applicable TPE331 maintenance methods: comments. We specifically invite manuals. These Honeywell OILs and the • Federal eRulemaking Portal: Go to comments on the overall regulatory, TPE331 maintenance manuals can be http://www.regulations.gov. Follow the economic, environmental, and energy obtained from Honeywell using the contact instructions for submitting comments. aspects of this proposed AD. We will information in paragraph (i)(3) of this • Fax: 202–493–2251. consider all comments received by the proposed AD. • Mail: U.S. Department of closing date and may amend this (3) For service information identified in this AD, contact Honeywell International Transportation, Docket Operations, M– proposed AD because of those Inc., 111 S. 34th Street, Phoenix, AZ 85034– 30, West Building Ground Floor, Room comments. 2802; phone: 800–601–3099; Internet: W12–140, 1200 New Jersey Avenue SE., We will post all comments we https://myaerospace.honeywell.com/wps/ Washington, DC 20590. receive, without change, to http:// portal. • Hand Delivery: Deliver to Mail www.regulations.gov, including any (4) You may view this service information address above between 9 a.m. and 5 personal information you provide. We at the FAA, Engine & Propeller Directorate, p.m., Monday through Friday, except will also post a report summarizing each 1200 District Avenue, Burlington, MA. For Federal holidays. substantive verbal contact we receive information on the availability of this For service information identified in about this proposed AD. material at the FAA, call 781–238–7125. this NPRM, contact Boeing Commercial Issued in Burlington, Massachusetts, on Discussion Airplanes, Attention: Data & Services March 15, 2016. Management, P.O. Box 3707, MC 2H–65, Structural fatigue damage is Ann C. Mollica, Seattle, WA 98124–2207; telephone progressive. It begins as minute cracks, Acting Manager, Engine and Propeller 206–544–5000, extension 1; fax 206– and those cracks grow under the action Directorate, Aircraft Certification Service. 766–5680; Internet https:// of repeated stresses. This can happen [FR Doc. 2016–06936 Filed 3–28–16; 8:45 am] www.myboeingfleet.com. You may view because of normal operational BILLING CODE 4910–13–P this referenced service information at conditions and design attributes, or the FAA, Transport Airplane because of isolated situations or Directorate, 1601 Lind Avenue SW., incidents such as material defects, poor DEPARTMENT OF TRANSPORTATION Renton, WA. For information on the fabrication quality, or corrosion pits, availability of this material at the FAA, dings, or scratches. Fatigue damage can Federal Aviation Administration call 425–227–1221. It is also available occur locally, in small areas or on the Internet at http:// structural design details, or globally. 14 CFR Part 39 www.regulations.gov by searching for Global fatigue damage is general degradation of large areas of structure mstockstill on DSK4VPTVN1PROD with PROPOSALS [Docket No. FAA–2016–5034; Directorate and locating Docket No. FAA–2016– Identifier 2015–NM–172–AD] 5034. with similar structural details and stress levels. Multiple-site damage is global RIN 2120–AA64 Examining the AD Docket damage that occurs in a large structural Airworthiness Directives; The Boeing You may examine the AD docket on element such as a single rivet line of a Company Airplanes the Internet at http:// lap splice joining two large skin panels. www.regulations.gov by searching for Global damage can also occur in AGENCY:Federal Aviation and locating Docket No. FAA–2016– multiple elements such as adjacent Administration (FAA), DOT. 5034; or in person at the Docket frames or stringers. Multiple-site- VerDate Sep<11>2014 16:52 Mar 28, 2016 Jkt 238001 PO 00000 Frm 00004 Fmt 4702 Sfmt 4702 E:\FR\FM\29MRP1.SGM 29MRP1


Document Created: 2016-03-30 08:29:01
Document Modified: 2016-03-30 08:29:01
CategoryRegulatory Information
CollectionFederal Register
sudoc ClassAE 2.7:
GS 4.107:
AE 2.106:
PublisherOffice of the Federal Register, National Archives and Records Administration
SectionProposed Rules
ActionNotice of proposed rulemaking (NPRM).
DatesWe must receive comments on this proposed AD by May 31, 2016.
ContactJoseph 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: [email protected]
FR Citation81 FR 17412 
RIN Number2120-AA64
CFR AssociatedAir Transportation; Aircraft and Aviation Safety
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