Document ID: FAA-2018-0216-0003
Agency: faa
Document Type: Rule
Title: Airworthiness Directives: Honeywell International Inc. Turboprop Engines
Posted Date: 2018-11-05T05:00Z

[Federal Register Volume 83, Number 214 (Monday, November 5, 2018)]
[Rules and Regulations]
[Pages 55255-55258]
From the Federal Register Online via the Government Publishing Office [www.gpo.gov]
[FR Doc No: 2018-23775]

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DEPARTMENT OF TRANSPORTATION

Federal Aviation Administration

14 CFR Part 39

[Docket No. FAA-2018-0216; Product Identifier 1988-ANE-18-AD; Amendment 
39-19474; AD 2018-22-01]
RIN 2120-AA64

Airworthiness Directives; Honeywell International Inc. Turboprop 
Engines

AGENCY: Federal Aviation Administration (FAA), DOT.

ACTION: Final rule.

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SUMMARY: We are superseding Airworthiness Directive (AD) 88-12-10 for 
certain Honeywell International Inc. (Honeywell) TPE331 turboprop 
engines. AD 88-12-10 required reducing the life limit for certain 
second stage turbine rotors. This AD requires removing certain second 
stage turbine rotors from service at a reduced life limit. This AD was 
prompted by report that a TPE331-11U engine experienced an uncontained 
rotor separation. In addition, cracks were discovered through eddy 
current inspection (ECI) in the bore of the second stage turbine rotor 
assembly after publication of AD 88-12-10. We are issuing this AD to 
address the unsafe condition on these products.

DATES: This AD is effective December 10, 2018.

ADDRESSES: For service information identified in this final rule, 
contact Honeywell International Inc., 111 S 34th Street, Phoenix, AZ 
85034-2802; phone:

[[Page 55256]]

800-601-3099; internet: https://myaerospace.honeywell.com/wps/portal. 
You may view this service information at the FAA, Engine and Propeller 
Standards Branch, 1200 District Avenue, Burlington, MA 01803. For 
information on the availability of this material at the FAA, call 781-
238-7759. It is also available on the internet at http://www.regulations.gov by searching for and locating Docket No. FAA-2018-
0216.

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-2018-
0216; or in person at Docket Operations between 9 a.m. and 5 p.m., 
Monday through Friday, except Federal holidays. The AD docket contains 
this final rule, the regulatory evaluation, any comments received, and 
other information. The address for Docket Operations (phone: 800-647-
5527) is Document Operations, 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 ACO Branch, FAA, 3960 Paramount Blvd., Lakewood, CA 90712-4137; 
phone: 562-627-5246; fax: 562-627-5210; email: [email protected].

SUPPLEMENTARY INFORMATION: 

Discussion

    We issued a notice of proposed rulemaking (NPRM) to amend 14 CFR 
part 39 to supersede AD 88-12-10, Amendment 39-5910 (53 FR 19766, May 
31, 1988), (``AD 88-12-10''). AD 88-12-10 applied to Honeywell TPE331-
10, -10R, -10U, -10UA, -10UF, -10UG, -10UGR, -10UR, and -11U turboprop 
engines equipped with 2nd stage turbine rotors, part numbers 3102106-1, 
-6, and -8, installed. The NPRM published in the Federal Register on 
June 20, 2018 (83 FR 28550). The NPRM was prompted by a report that a 
TPE331-11U engine installed on an M7 Aerospace LP SA227 airplane 
experienced an uncontained rotor separation. In addition, cracks were 
discovered through ECI in the bore of the second stage turbine rotor 
assembly after publication of AD 88-12-10. The NPRM proposed to remove 
certain second stage turbine rotors from service at a reduced life 
limit. We are issuing this AD to address the unsafe condition on these 
products.

Comments

    We gave the public the opportunity to participate in developing 
this AD. The following presents the comments received on the NPRM and 
the FAA's response to each comment.

Request To Revise Compliance Times

    Honeywell requested that we remove from the NPRM the statement that 
the FAA finds that allowing an additional 100 cycles-in-service before 
their removal provides a sufficient level of safety for applicable 
second stage turbine rotors that have been in service for 30 years 
after the publication of AD 88-12-10. Honeywell indicated it believes 
that most of the IN100 rotors have been replaced at around 3,500 cycles 
during hot section inspection. Honeywell noted that the rotors would 
not make it to the next hot section inspection with a life of 4,800 
cycles. Honeywell noted that there is a not a lot of field experience 
for IN100 rotors beyond 3,500 cycles.
    Honeywell commented that the removal schedule in the Honeywell 
service bulletin needs to remain the same (within 100 cycles-in-service 
for 3,301 to 4,000 cycles since new (CSN) rotors and within 50 cycles-
in-service for 4,001 to 4,800 CSN rotors) since the event rotor failed 
at around 4,100 cycles. Additionally, Honeywell has also found rotors 
through eddy current inspection that had long cracks at around 4,300 
cycles.
    We disagree. We would normally only require removal of parts within 
50 cycles-in-service after the effective date of an AD when the risk 
justifies immediate action. The FAA assessed the risk of the affected 
rotors based on service experience and IN100 rotor propagation life of 
cracked and failed rotors. We found that the additional cycles in 
service allowed by this AD before the removal of the second stage 
turbine rotors provides an acceptable level of safety. We did not 
change this AD.

Conclusion

    We reviewed the relevant data, considered the comment received, and 
determined that air safety and the public interest require adopting 
this AD as proposed.

Related Service Information

    We reviewed Honeywell Service Bulletin (SB) TPE331-72-A2319, 
Revision 0, dated April 25, 2018, and TPE331-72-A2310, Revision 0, 
dated January 26, 2018. These SBs describe procedures for replacement 
of the second stage turbine rotor assembly installed on TPE331-8, -10, 
-10N, -10R, -10U, -10UA, -10UF, -10UG, -10UGR, -10UR, and -11U model 
engines.

Costs of Compliance

    We estimate that this AD affects 100 engines installed on airplanes 
of U.S. registry.
    We estimate that 20 commercial engines and 80 general aviation 
engines will need this turbine rotor replacement to comply with this 
AD:

                                                 Estimated Costs
----------------------------------------------------------------------------------------------------------------
                                                                                     Cost per      Cost on U.S.
                Action                         Labor cost           Parts cost        product        operators
----------------------------------------------------------------------------------------------------------------
Scheduled rotor replacement...........  1 work-hour x $85 per             $7,500          $7,585        $379,250
                                         hour = $85.
Unscheduled rotor replacement.........  41 work-hours x $85 per            7,500          10,985         549,250
                                         hour = $3,485.
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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.
    This AD is issued in accordance with authority delegated by the 
Executive Director, Aircraft Certification Service,

[[Page 55257]]

as authorized by FAA Order 8000.51C. In accordance with that order, 
issuance of ADs is normally a function of the Compliance and 
Airworthiness Division, but during this transition period, the 
Executive Director has delegated the authority to issue ADs applicable 
to engines, propellers, and associated appliances to the Manager, 
Engine and Propeller Standards Branch, Policy and Innovation Division.

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) 
88-12-10, Amendment 39-5910 (53 FR 19766, May 31, 1988), and adding the 
following new AD:

2018-22-01 Honeywell International Inc. (Type Certificate previously 
held by AlliedSignal Inc., Garrett Engine Division; Garrett Turbine 
Engine Company; and AiResearch Manufacturing Company of Arizona): 
Amendment 39-19474; Docket No. FAA-2018-0216; Product Identifier 
1988-ANE-18-AD.

(a) Effective Date

    This AD is effective December 10, 2018.

(b) Affected ADs

    This AD replaces AD 88-12-10, Amendment 39-5910 (53 FR 19766, 
May 31, 1988).

(c) Applicability

    This AD applies to Honeywell International Inc. (Honeywell) 
TPE331-8, -10, -10N, -10R, -10U, -10UA, -10UF, -10UG, -10UGR, -10UR, 
and -11U turboprop engines with second stage turbine rotor 
assemblies, part number (P/Ns) 3102106-1, -6, and -8 or P/N 3101514-
1, -10 and -12, installed.

(d) Subject

    Joint Aircraft System Component (JASC) Code 7250, Turbine 
Section.

(e) Unsafe Condition

    This AD was prompted by a report that a TPE331-11U engine 
installed on an M7 Aerospace LP SA227 airplane experienced an 
uncontained rotor separation and the discovery of cracks in the bore 
of the second stage turbine rotor assembly after publication of AD 
88-12-10. We are issuing this AD to prevent failure of the second 
stage turbine rotor. The unsafe condition, if not addressed, could 
result in uncontained release of the second stage turbine rotor, 
damage to the engine, and damage to the airplane.

(f) Compliance

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

(g) Required Actions

    (1) Remove from service the applicable second stage turbine 
rotor assembly, P/Ns 3102106-1, -6 and -8, according to the schedule 
in Table 1 to Paragraph (g)(1) of this AD:

Table 1 to Paragraph (g)(1) of This AD--Removal of Second Stage Rotor, P/
                         Ns 3102106-1, -6 and -8
------------------------------------------------------------------------
 Second stage turbine rotor cycles
 since new (CSN) on the effective             Removal schedule
          date of the AD
------------------------------------------------------------------------
0 to 2,600........................  Prior to 3,000 CSN.
2,601 to 3,300....................  Within 400 cycles-in-service (CIS)
                                     after the effective date of this AD
                                     or 3,600 CSN, or at next access,
                                     whichever occurs first.
3,301 to 4,000....................  Within 200 cycles-in-service after
                                     the effective date of this AD or
                                     4,100 CSN, or at next access,
                                     whichever occurs first.
4,001 to 4,800....................  Within 100 cycles-in-service after
                                     the effective date of this AD or
                                     4,800 CSN, or at next access,
                                     whichever occurs first.
------------------------------------------------------------------------

    (2) Remove from service the applicable second stage turbine rotor 
assembly, P/Ns 3101514-1, -10 and -12, per the schedule in Table 2 to 
Paragraph (g)(2) of this AD:

 Table 2 to Paragraph (g)(2) of This AD--Removal of Second Stage Rotors,
                       P/Ns 3101514-1, -10 and -12
------------------------------------------------------------------------
 Second stage turbine rotor CSN on
   the effective date of the AD               Removal schedule
------------------------------------------------------------------------
0 to 2,600........................  Prior to 3,000 CSN.
2,601 to 3,200....................  Within 400 CIS after the effective
                                     date of this AD or 3,600 CSN, or at
                                     next access, whichever occurs
                                     first.
3,201 to 3,800....................  Within 200 CIS after the effective
                                     date of this AD or 4,100 CSN, or at
                                     next access, whichever occurs
                                     first.
3,801 to 4,400....................  Within 100 CIS after the effective
                                     date of this AD or 4,400 CSN, or at
                                     next access, whichever occurs
                                     first.
------------------------------------------------------------------------

[[Page 55258]]

(h) Definition

    For the purpose of this AD, ``next access'' is defined as when 
the applicable second stage turbine rotor assembly is removed from 
the engine.

(i) Installation Prohibition

    As of the effective date of this AD, do not install second stage 
turbine rotor assemblies, P/Ns 3102106-1, -6, and -8 and P/Ns 
3101514-1, -10, and -12 on any engine.

(j) Alternative Methods of Compliance (AMOCs)

    (1) The Manager, Los Angeles ACO, FAA, has the authority to 
approve AMOCs for this AD, if requested using the procedures found 
in 14 CFR 39.19. In accordance with 14 CFR 39.19, send your request 
to your principal inspector or local Flight Standards District 
Office, as appropriate. If sending information directly to the 
manager of the certification office, send it to the attention of the 
person identified in paragraph (k) of this AD. You may email your 
request to: [email protected].
    (2) Before using any approved AMOC, notify your appropriate 
principal inspector, or lacking a principal inspector, the manager 
of the local flight standards district office/certificate holding 
district office.

(k) Related Information

    For more information about this AD, contact Joseph Costa, 
Aerospace Engineer, Los Angeles ACO Branch, FAA, 3960 Paramount 
Blvd., Lakewood, CA 90712-4137; phone: 562-627-5246; fax: 562-627-
5210; email: [email protected].

(l) Material Incorporated by Reference

    None.

    Issued in Burlington, Massachusetts, on October 23, 2018.
Karen M. Grant,
Acting Manager, Engine and Propeller Standards Branch, Aircraft 
Certification Service.
[FR Doc. 2018-23775 Filed 11-2-18; 8:45 am]
 BILLING CODE 4910-13-P