AD 2016-18-17

[Federal Register Volume 81, Number 190 (Friday, September 30, 2016)]
[Rules and Regulations]
[Pages 67100-67102]
From the Federal Register Online via the Government Publishing Office [www.gpo.gov]
[FR Doc No: 2016-23263]


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DEPARTMENT OF TRANSPORTATION

Federal Aviation Administration

14 CFR Part 39

[Docket No. FAA-2015-4866; Directorate Identifier 2015-NE-33-AD; 
Amendment 39-18648; AD 2016-18-17]
RIN 2120-AA64


Airworthiness Directives; Honeywell International Inc. Turboprop 
and Turboshaft Engines

AGENCY: Federal Aviation Administration (FAA), DOT.

ACTION: Final rule.

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SUMMARY: We are adopting a new airworthiness directive (AD) for certain 
Honeywell International Inc. (Honeywell) TPE331 model turboprop engines 
and TSE331-3U model turboshaft engines. This AD was prompted by the 
discovery of cracks in a 2nd stage compressor impeller during a routine 
shop visit. This AD requires removal of the 2nd stage compressor 
impeller. We are issuing this AD to prevent failure of the compressor 
impeller, uncontained part release, damage to the engine, and damage to 
the airplane.

DATES: This AD is effective November 4, 2016.

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-2015-
4866; or in person at the Docket Management Facility between 9 a.m. and 
5 p.m., Monday through Friday, except Federal holidays. The AD docket 
contains this AD, the regulatory evaluation, any comments received, and 
other information. The address for the Docket Office (phone: 800-647-
5527) is Document Management Facility, U.S. Department of 
Transportation, Docket Operations, M-30, West Building Ground Floor, 
Room W12-140, 1200 New Jersey Avenue SE., Washington, DC 20590.

FOR FURTHER INFORMATION CONTACT: Joseph Costa, Aerospace Engineer, Los

[[Page 67101]]

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: 

Discussion

    We issued a notice of proposed rulemaking (NPRM) to amend 14 CFR 
part 39 by adding an AD that would apply to certain Honeywell TPE331 
model turboprop engines and TSE331-3U model turboshaft engines. The 
NPRM published in the Federal Register on March 15, 2016 (81 FR 13764) 
(``the NPRM''). The NPRM was prompted by the discovery of cracks in a 
2nd stage compressor impeller during a routine shop visit. The NPRM 
proposed to require removal of the 2nd stage compressor impeller. We 
are issuing this AD to prevent failure of the compressor impeller, 
uncontained part release, damage to the engine, and damage to the 
airplane.

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 Change Compliance

    Bearskin Airlines and Turbine Standard, LTD requested that the 
compliance time interval be changed because many TPE331 engine 
operators are on a Continuous Airworthiness Maintenance (CAM) program. 
This program does not require impeller inspections per the overhaul 
manual and the impeller is not considered as ``overhauled''. AD 
compliance under CAM may be interpreted as being within 200 cycles or 
30 to 45 days.
    Other commenters requested that the compliance time be changed to a 
less aggressive time interval appropriate to the unsafe condition. Many 
high-usage operators have suspect impellers that currently exceed 7,000 
cycles since the last compressor inspection.
    We agree. We changed compliance interval in paragraph (e)(1) of 
this AD.

Request To Allow Other Inspection Facilities To Return Impellers to 
Service

    Turbine Standard, LTD requested that this AD allow other inspection 
facilities to return impellers to service. There are many inspection 
facilities that are capable of inspecting the 2nd stage compressor 
impeller.
    We partially agree. We agree that many inspection facilities are 
capable of performing a focused inspection of the 2nd stage compressor 
impeller. We disagree with allowing other inspection and regrinding 
facilities to return impellers to service. This AD does not address 
inspection or regrinding of the curvic area of the 2nd stage compressor 
impeller. Regrinding of the curvic area of the 2nd stage compressor 
impeller involves machining of a critical rotating part, which must be 
approved by the FAA. We did not change this AD.

Request To Change Costs of Compliance

    Honeywell; Perimeter Aviation, LP; and Intercontinental Jet Service 
Corp. requested that the costs of compliance be changed because the 
NPRM is not representative of the impeller's replacement costs. 
Honeywell quotes the cost of a new 2nd stage compressor impeller at 
$11,922.50.
    We partially agree. We agree with the comment because the costs 
were not clearly defined. We disagree with the comment because 
replacement costs are based on pro-rated costs that are estimated at 
50% of new parts costs. Since issuing the NPRM, the FAA estimated that 
30% of impellers will be scrapped; therefore, we changed the costs of 
compliance accordingly.

Request To Include Service Information

    The European Aviation Safety Agency, Honeywell, and Candler & 
Associates, Inc. requested that service information be included in this 
AD. Having the service information available would aid in understanding 
any differences between this AD and the service information.
    We agree. We added Honeywell Service Bulletin (SB) TPE331-72-2208, 
dated July 29, 2014, as related information in this AD.

Conclusion

    We reviewed the relevant data, considered the comments received, 
and determined that air safety and the public interest require adopting 
this AD with the changes described previously.
    We also determined that these changes will not increase the 
economic burden on any operator or increase the scope of this AD.

Related Service Information

    We reviewed Honeywell SB TPE331-72-2208, dated July 29, 2014. The 
SB describes procedures for replacing the 2nd stage compressor 
impeller.

Costs of Compliance

    We estimate that this AD will affect 4,000 engines installed on 
airplanes of U.S. registry. We estimate that it will take 2 hours per 
engine to comply with this AD. The average labor rate is $85 per hour. 
We also estimate that required parts will cost about $4,404.50 per 
engine. Based on these figures, we estimate the total cost of this AD 
on U.S. operators to be $18,298,000.

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

    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 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.

Adoption of the Amendment

    Accordingly, under the authority delegated to me by the 
Administrator, the FAA amends 14 CFR part 39 as follows:

[[Page 67102]]

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):

2016-18-17 Honeywell International Inc. (Type Certificate Previously 
Held by AlliedSignal Inc., Garrett Engine Division; Garrett Turbine 
Engine Company; and AiResearch Manufacturing Company of Arizona): 
Amendment 39-18648; Docket No. FAA-2015-4866; Directorate Identifier 
2015-NE-33-AD.

(a) Effective Date

    This AD is effective November 4, 2016.

(b) Affected ADs

    None.

(c) Applicability

    This AD applies to Honeywell International Inc. (Honeywell) 
TPE331-3U, -3UW, -5, -5A, -5AB, -5B, -6, -6A, -8, -10, -10AV, -10GP, 
-10GT, -10N, -10P, -10R, -10T, -10U, -10UA, -10UF, -10UG, -10UGR, -
10UR, and -11U model turboprop engines, and TSE331-3U model 
turboshaft engines, with a 2nd stage compressor impeller, part 
number (P/N) 893482-1 through -5, inclusive, or P/N 3107056-1 or P/N 
3107056-2, installed.

(d) Unsafe Condition

    This AD was prompted by the discovery of cracks in a 2nd stage 
compressor impeller during a routine shop visit. We are issuing this 
AD to prevent failure of the compressor impeller, uncontained part 
release, damage to the engine, and damage to the airplane.

(e) Compliance

    Comply with this AD within the compliance times specified, 
unless already done.
    (1) Remove from service the 2nd stage compressor impeller at 
next removal of the 2nd stage compressor impeller from the engine or 
before exceeding 11,500 cycles in service after the effective date 
of this AD, whichever occurs first.
    (2) Reserved.

(f) Installation Prohibition

    After the effective date of this AD, do not install a 2nd stage 
compressor impeller, part number (P/N) 893482-1 through -5, 
inclusive, or P/N 3107056-1 or P/N 3107056-2, into any engine.

(g) 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.

(h) 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 SB TPE331-72-2208, dated July 29, 2014, which is 
not incorporated by reference in this AD, can be obtained from 
Honeywell, using the contact information in paragraph (h)(3) of this 
AD.
    (3) For Honeywell 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 FAA, Engine & 
Propeller Directorate, 1200 District Avenue, Burlington, MA. For 
information on the availability of this material at the FAA, call 
781-238-7125.

(i) Material Incorporated by Reference

    None.

    Issued in Burlington, Massachusetts, on August 26, 2016.
Colleen M. D'Alessandro,
Manager, Engine & Propeller Directorate, Aircraft Certification 
Service.
[FR Doc. 2016-23263 Filed 9-29-16; 8:45 am]
 BILLING CODE 4910-13-P