Document ID: FAA-2017-0020-0001
Agency: faa
Document Type: Proposed Rule
Title: Airworthiness Directives: Honeywell International Inc. Turbofan Engines
Posted Date: 2017-08-02T04:00Z

[Federal Register Volume 82, Number 147 (Wednesday, August 2, 2017)]
[Proposed Rules]
[Pages 35914-35918]
From the Federal Register Online via the Government Publishing Office [www.gpo.gov]
[FR Doc No: 2017-16148]

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DEPARTMENT OF TRANSPORTATION

Federal Aviation Administration

14 CFR Part 39

[Docket No. FAA-2017-0020; Directorate Identifier 2016-NE-33-AD]
RIN 2120-AA64

Airworthiness Directives; Honeywell International Inc. Turbofan 
Engines

AGENCY: Federal Aviation Administration (FAA), DOT.

ACTION: Notice of proposed rulemaking (NPRM).

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SUMMARY: We propose to adopt a new airworthiness directive (AD) for 
certain Honeywell International Inc. AS907 series turbofan engines. 
This proposed AD was prompted by two loss-of-thrust-control events, and 
two in-flight shutdowns (IFSDs) of new production, low-time engines 
attributed to water intrusion of the engine electronic control unit 
(ECU). This proposed AD would require applying sealant to identified 
areas of the ECU and requires inserting a copy of certain airplane 
operating procedures into the applicable flight manuals. We are 
proposing this AD to correct the unsafe condition on these products.

DATES: We must receive comments on this proposed AD by September 18, 
2017.

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 NPRM, 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, 1200 District Avenue, Burlington, MA 01803. 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-2017-
0020; 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: joseph.costa@faa.gov.

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

[[Page 35915]]

section. Include ``Docket No. FAA-2017-0020; Directorate Identifier 
2016-NE-33 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

    We received reports of two loss-of-thrust-control events and two 
IFSDs of new production, low-time AS907-2-1A engines, attributed to 
water intrusion into the ECU at the ECU cover-to-body splitline, cover 
screws and cavities, leading to internal board electrical faults. 
Similar events have occurred on AS907-1-1A engines when rainwater 
dripped through the ECU and T2 engine access panels at 10 and 2 o'clock 
locations onto the ECU and harnesses while the airplane was on the 
ground. This proposed AD would require application of sealant to 
identified areas of the ECU and requires inserting a copy of certain 
airplane operating procedures into the applicable flight manuals. These 
procedures describe interim actions for not dispatching the airplane 
under certain engine electronic fault conditions. This condition, if 
not corrected, could result in dual engine power loss, loss of thrust 
control, and damage to the engine and airplane.

Related Service Information Under 1 CFR Part 51

    We reviewed Honeywell Service Bulletin (SB); SB AS907-76-9021, 
Revision 1, dated April 20, 2017; Operating Information Letter (OIL) 
OIAS907-0001R00, dated March 14, 2017; Component Maintenance Manual 
(CMM) 2119576, Temporary Revision (TR) No. 76-1, Section 76-10-15, 
dated September 6, 2016; and CMM 2119576, TR No. 76-1, Section 76-10-
29, dated August 2, 2016.
    In combination, the SB and TRs describe procedures for applying 
sealant to identified areas of the ECU to prevent water from entering 
the ECU on AS907 series engines. The OIL provides instructions for 
interrogating the onboard Maintenance Data Computer to clear engine 
electronic fault conditions. This service information is reasonably 
available because the interested parties have access to it through 
their normal course of business or by the means identified in the 
ADDRESSES section.

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 applying sealant to identified areas 
of the ECU.

Differences Between This Proposed AD and the Service Information

    Honeywell SB AS907-76-9021, Revision 1, dated April 20, 2017 
recommends complying after 400 engine operating hours, not to exceed 18 
months from the date of issuance of the SB. This NPRM proposes 
complying within 200 engine operating hours or 9 months after the 
effective date of the AD, whichever occurs first.

Interim Action

    We consider this proposed AD interim action. Honeywell is 
developing design changes that will eliminate the need to apply sealant 
to the ECU.

Costs of Compliance

    We estimate that this ECU sealing affects 477 engines installed on 
airplanes of U.S. registry.
    We estimate the following costs to comply with this proposed AD:

                                                 Estimated Costs
----------------------------------------------------------------------------------------------------------------
                                                                                     Cost per      Cost on U.S.
               Action                         Labor cost            Parts cost        product        operators
----------------------------------------------------------------------------------------------------------------
Inserting Figure into AFM..........  2 work-hours x $85 per hour              $0         $170.00      $81,090.00
                                      = $170.00.
Application of sealant, on-wing....  5.5 work-hours x $85 per              50.00          517.50      246,847.50
                                      hour = $467.50.
----------------------------------------------------------------------------------------------------------------

    We estimate the following costs to do any necessary fault checks of 
the Maintenance Data Computer (MDC)/Onboard Messaging System (OMS). We 
estimate that 20 engines will need this fault check.

                                               On-Condition Costs
----------------------------------------------------------------------------------------------------------------
                                                                                                     Cost per
                   Action                                 Labor cost                Parts cost        product
----------------------------------------------------------------------------------------------------------------
Fault Check of Maintenance Data Computer...  5 work-hours x $85 per hour =                    $0         $425.00
                                              $425.00.
----------------------------------------------------------------------------------------------------------------

    According to the manufacturer, some of the costs of this AD may be 
covered under warranty, thereby reducing the cost impact on affected 
individuals. We do not control warranty coverage for affected 
individuals. As a result, we have included all costs in our cost 
estimate.

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

[[Page 35916]]

products identified in this rulemaking action.

Regulatory Findings

    We 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 this 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, 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 adding the following new airworthiness 
directive (AD):

Honeywell International Inc.: Docket No. FAA-2017-0020; Directorate 
Identifier 2016-NE-33-AD.

(a) Comments Due Date

    We must receive comments by September 18, 2017.

(b) Affected ADs

    None.

(c) Applicability

    This AD applies to all Honeywell International Inc. AS907-1-1A, 
-2-1A, -2-1G, and -3-1E model turbofan engines, with engine serial 
numbers (S/Ns) listed in Table 3 of Honeywell Service Bulletin (SB) 
AS907-76-9021 Revision 1, dated April 20, 2017; or with engine 
electronic control unit (ECU), part numbers (P/Ns) 2119576-1001 
through -1011, with no Mod Record or with a Mod Record 1 through 5 
(for the AS907-1-1A engine); or with ECU, P/N 2119576-1102, with no 
Mod Record (for the AS907-2-1A engine); or with ECU, P/Ns 2119576-
3002 and -3102, with no Mod Record (for the AS907-2-1G engine); or 
with ECU, P/Ns 2119576-4102 and -4103, with no Mod Record (for the 
AS907-3-1E), installed.

(d) Subject

    Joint Aircraft System Component (JASC) Code 7600, Engine 
Controls Section.

(e) Unsafe Condition

    This AD was prompted by two low-time loss-of-thrust-control 
events and two in-flight shut downs (IFSDs) attributed to water 
intrusion of the engine ECU. We are issuing this AD to prevent a 
dual engine power loss, and loss of thrust control and damage to the 
engine and airplane.

(f) Compliance

    Comply with this AD within the compliance times specified, 
unless already done.

(g) Required Actions

    (1) For applicable engines, apply sealant to both ECUs within 
200 engine operating hours, or 9 months after the effective date of 
this AD whichever occurs first, using Accomplishment Instructions, 
paragraph 3.C. of Honeywell SB AS907-76-9021, Revision 1, dated 
April 20, 2017.
    (2) If the ECU sealant is removed or becomes defective, re-apply 
sealant using Accomplishment Instructions, paragraph 3.C. of 
Honeywell SB AS907-76-9021, Revision 1, dated April 20, 2017; or 
Component Maintenance Manual (CMM) 2119576, Temporary Revision (TR) 
No. 76-1, Section 76-10-15, dated September 6, 2016; or CMM 2119576, 
TR No. 76-1, Section 76-10-29, dated August 2, 2016.
    (3) Within 60 days after the effective date of this AD, for all 
airplanes that have an affected engine installed with an ECU not in 
compliance with paragraph (g)(1) or (g)(2) of this AD, insert a copy 
of Figure 1, 2, or 3 to paragraph (g) of this AD, as applicable to 
your airplane, into the Emergency Procedures Section of the Airplane 
Flight Manual (AFM).
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    (4) If a cyan warning is announced, before next flight, check 
the current fault messages in the Maintenance Data Computer (MDC)/
Onboard Messaging System (OMS) for any of the following:

(i) FADEC ECU A
(ii) FADEC ECU B
(iii) THROTTLE LEVER 1A
(iv) THROTTLE LEVER 1B
(v) THROTTLE RIGGING 1A
(vi) THROTTLE RIGGING 1B

    (5) Replace the ECU if any of the fault messages listed in 
paragraph (g)(4) of this AD are in the MDC OMS. Refer to Operating 
Information Letter (OIL) OIAS907-0001R00, dated March 14, 2017 for 
information on returning and replacing the ECU.
    (6) Continued flight is permitted if none of the fault messages 
listed in paragraph (g)(4) of this AD are in the MDC OMS, or if 
paragraph (g)(5) of this AD was accomplished.

(h) Installation Prohibition

    (i) Do not install an ECU if any of the fault messages listed in 
paragraph (g)(4) of this AD are in the MDC OMS.
    (ii) Do not install an ECU that has a P/N and Mod Record listed 
in paragraph (c) of this AD unless it was either sealed as specified 
in paragraph (g)(1) of this AD or if the ECU is not affected by this 
AD.

(i) Terminating Action

    Remove from the AFM, Figure 1, 2, or 3 to paragraph (g) of this 
AD, after paragraph (g)(1) or (g)(2) of this AD is accomplished.

(j) Credit for Previous Actions

    You may take credit for the actions required by paragraphs 
(g)(1) or (g)(2) of this AD, if you performed those actions before 
the effective date of this AD using Honeywell SB AS907-76-9021, 
Revision 0, dated May 13, 2016.

(k) 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.

(l) 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) Honeywell SB AS907-76-9021, Revision 1, dated April 20, 
2017; OIL OIAS907-0001R00, dated March 14, 2017; CMM 2119576, TR No. 
76-1, Section 76-10-15, dated September 6, 2016; and CMM 2119576, TR 
No. 76-1, Section 76-10-29, dated August 2, 2016, can be obtained 
from Honeywell International using the contact information in 
paragraph (l)(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/!ut/.
    (4) You may view this service information at the FAA, Engine & 
Propeller Directorate,

[[Page 35918]]

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 June 21, 2017.
Thomas A. Boudreau,
Acting Manager, Engine & Propeller Directorate, Aircraft Certification 
Service.
[FR Doc. 2017-16148 Filed 8-1-17; 8:45 am]
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