[Federal Register Volume 79, Number 53 (Wednesday, March 19, 2014)]
[Proposed Rules]
[Pages 15261-15266]
From the Federal Register Online via the Government Publishing Office [www.gpo.gov]
[FR Doc No: 2014-06029]


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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]
RIN 2120-AA64


Airworthiness Directives; Honeywell International Inc. Turboprop 
Engines

AGENCY: Federal Aviation Administration (FAA), DOT.

ACTION: Notice of proposed rulemaking (NPRM).

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SUMMARY: We propose to supersede airworthiness directive (AD) 2006-15-
08, which 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 part 
numbers (P/Ns) of Woodward fuel control unit (FCU) assemblies, 
installed. AD 2006-15-08 currently requires initial and repetitive 
dimensional inspections of the fuel control drive spline for wear, and 
replacement of the FCU and fuel pump. Since we issued AD 2006-15-08, we 
determined that additional FCU assembly P/Ns are affected, the 
compliance deadline and assembly replacement after removal for cause or 
overhaul are no longer required, and that cautionary engine operating 
information must be observed. This proposed AD was prompted by reports 
of loss of the fuel control drive, leading to engine overspeed, 
overtorque, overtemperature, uncontained rotor failure, and asymmetric 
thrust in multi-engine airplanes. This proposed AD would require 
initial and repetitive dimensional inspections of the affected fuel 
control drive splines, and insertion of certain airplane operating 
procedures into the applicable flight manuals. We

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are proposing this AD to prevent failure of the fuel control drive that 
could result in damage to the engine and airplane.

DATES: We must receive comments on this proposed AD by May 19, 2014.

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/!ut/. 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.

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 proposed AD. 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 proposed AD. We 
will consider all comments received by the closing date and may amend 
this proposed AD 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 proposed AD.

Discussion

    On July 14, 2006, we issued AD 2006-15-08, Amendment 39-14688 (71 
FR 41121, July 20, 2006), for all Honeywell International Inc. TPE331 
series turboprop engines with certain P/Ns of Woodward FCU assemblies 
installed. AD 2006-15-08 requires initial and repetitive dimensional 
inspections of the fuel control drive spline for wear that might cause 
replacement of the FCU and/or fuel pump assemblies. AD 2006-15-08 also 
requires the replacement of the FCU assembly when the FCU is removed 
for cause or overhaul, but not later than December 31, 2012. AD 2006-
15-08 was prompted by fuel control drive failures that resulted in a 
rapid, uncommanded, uncontrolled increase in fuel flow and overspeed of 
the engine during ground start. We issued AD 2006-15-08 to prevent 
failure of the fuel control drive, destructive overspeed that could 
result in uncontained rotor failure and damage to the airplane.

Actions Since AD 2006-15-08 Was Issued

    Since we issued AD 2006-15-08, Amendment 39-14688 (71 FR 41121, 
July 20, 2006), we determined that additional FCU assembly P/Ns are 
affected, certain repetitive fuel control drive inspections are 
necessary, and that additional flight crew emergency procedures and 
warnings are required. The warnings are required to inform flight crew 
of the probable engine response(s) following a loss of drive between 
the engine driven fuel pump and fuel control governor system. These 
engine responses are dependent on the phase of operation (ground engine 
start, ground or flight operations).
    Also since we issued AD 2006-15-08, Amendment 39-14688 (71 FR 
41121, July 20, 2006), we reviewed the in-service trends and engine in-
flight shutdowns (IFSDs) caused by the modified FCU and determined that 
the IFSD rate had not improved and the installation of the modified FCU 
assembly was not required.

FAA's Determination

    We are proposing this AD because we evaluated all the relevant 
information 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 proposed AD would require continued dimensional spline 
inspections required by AD 2006-15-08, add new P/Ns of affected FCU 
assemblies that require dimensional spline inspections. This proposed 
AD would require insertion of uncommanded engine overspeed procedures 
into the Airplane Flight Manual, Pilot Operating Handbook, and or 
Manufacturer's Operating Manual. This proposed AD would retain some but 
not all requirements of AD 2006-15-08, (71 FR 41121, July 20, 2006), 
but would no longer require the installation of a modified FCU.

Costs of Compliance

    We estimate that this proposed AD would affect 2,250 engines 
installed on airplanes of U.S. registry. We estimate that it would take 
8 hours per engine to perform an FCU inspection, and three inspections 
will be required over the life of the product. The average labor rate 
is $85 per hour. Due to the more frequent inspections proposed by this 
AD, we estimate 10% of affected engines would require FCU assembly stub 
shaft replacement, fuel pump or fuel control repair. We also estimate 
that repairs should not exceed $10,000 per engine. Based on these 
figures, we estimate the cost of this proposed AD on U.S. operators to 
be $6,307,044.

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

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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. Amend 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:

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 19, 2014.

(b) Affected ADs

    This AD supersedes 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 the 
part numbers (P/Ns) of 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               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, -   P/N 893561-7, -8, -9, -
                            5, -5A, -5AB, -5B,   10, -11, -14, -15, -16,
                            -6, -6A, -l0AV, -    -20, -26, -27, and -29;
                            10GP, -10GT, -l0P,   or P/N 897770-1, -3, -
                            and -l0T.            7, -9, -10, -11, -12, -
                                                 14, -15, -16, -25, -26,
                                                 and -28.
4*.......................  TPE331-3U, -3UW, -   P/N 893561-4, -5, -12,
                            5, -5A, -5AB, -5B,   and -13 or P/N 897770-
                            -6, -6A, -l0AV, -    5, -8, and -13.
                            10GP, -10GT, -l0P,
                            and -l0T.
5........................  TPE331-10, -l0R, -   P/N 897375-2, -3, -4, -
                            10U, -10UA, -10UF,   5, -8, -9, -10, -11, -
                            -10UG, -10UGR, -     12, -13, -14, -15, -16,
                            10UR, -11U, -12JR,   -17, -19, -21, -24, -
                            -12UA, -12UAR, and   25, -26, and -27; or P/
                            -12UHR.              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

    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 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 and 4

    For FCU assembly P/Ns in Groups 2 and 4 listed in Table 1 to 
paragraph (c) of this AD, 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:
    (i) Inspect the fuel control drive spline for wear.
    (ii) Thereafter, re-inspect the fuel control drive within 1,000 
HIS since-last-inspection (SLI) of the fuel control drive.

(2) Inspection of Engines with FCU Assembly P/Ns in Groups 1, 3, and 5

    (i) For FCU assembly P/Ns in Groups 1, 3, or 5 listed in Table 1 
to paragraph (c) of this AD:
    (A) If on the effective date of this AD the FCU assembly has 950 
or more HIS SLI, inspect the fuel control drive spline for wear 
within 50 HIS from the effective date of this AD.
    (B) If on the effective date of this AD the FCU assembly has 
fewer than 950 HIS SLI, inspect the fuel control drive spline for 
wear before reaching 1,000 HIS.
    (ii) Thereafter, re-inspect the fuel control drive spline 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).
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(f) Optional Terminating Action

    Replacing the affected FCU assembly with an 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: 
[email protected].
    (2) Honeywell International Inc., AFM, POH, and MOM, which are 
not incorporated by reference in this AD, can be obtained from 
Honeywell International Inc., using the contact information in 
paragraph (i)(4) of this AD.
    (3) 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

[[Page 15266]]

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 spline 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)(4) of this AD.
    (4) 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.
    (5) 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.

    Issued in Burlington, Massachusetts, on March 10, 2014.
Colleen M. D'Alessandro,
Assistant Directorate Manager, Engine & Propeller Directorate, Aircraft 
Certification Service.
[FR Doc. 2014-06029 Filed 3-18-14; 8:45 am]
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