AD 2012-17-05

[Federal Register Volume 77, Number 167 (Tuesday, August 28, 2012)]
[Rules and Regulations]
[Pages 51892-51894]
From the Federal Register Online via the Government Publishing Office [<a href="http://www.gpo.gov">www.gpo.gov</a>]
[FR Doc No: 2012-21010]


=======================================================================
-----------------------------------------------------------------------

DEPARTMENT OF TRANSPORTATION

Federal Aviation Administration

14 CFR Part 39

[Docket No. FAA-2011-1045; Directorate Identifier 2011-NE-32-AD; 
Amendment 39-17168; AD 2012-17-05]
RIN 2120-AA64


Airworthiness Directives; Honeywell International Inc. Turbofan 
Engines

AGENCY: Federal Aviation Administration (FAA), DOT.

ACTION: Final rule.

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

SUMMARY: We are adopting a new airworthiness directive (AD) for certain 
Honeywell International Inc. models TFE731-4, -4R, -5, -5R, -5AR, and -
5BR series turbofan engines. This AD was prompted by a report of a rim/
web separation of a first stage low-pressure

[[Page 51893]]

turbine (LPT1) rotor assembly. This AD requires replacing affected LPT1 
rotor assemblies with assemblies eligible for installation. We are 
issuing this AD to prevent uncontained disk separation, engine failure, 
and damage to the airplane.

DATES: This AD is effective October 2, 2012.

ADDRESSES: For service information identified in this AD, contact 
Honeywell International Inc., 111 S. 34th Street, Phoenix, AZ 85034-
2802; Web site: <a href="http://portal.honeywell.com">http://portal.honeywell.com</a>; or call Honeywell toll 
free at phone: 800-601-3099 (U.S./Canada) or 602-365-3099 
(International Direct). 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 <a href="http://www.regulations.gov">http://www.regulations.gov</a>; 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 
Angeles Aircraft Certification Office, FAA, Transport Airplane 
Directorate, 3960 Paramount Blvd., Lakewood, CA 90712-4137; phone: 562-
627-5246; fax: 562-627-5210: email: <a href="/cdn-cgi/l/email-protection#e78d889482978fc98488949386a7818686c9808891"><span class="__cf_email__" data-cfemail="97fdf8e4f2e7ffb9f4f8e4e3f6d7f1f6f6b9f0f8e1">[email&#160;protected]</span></a>.

SUPPLEMENTARY INFORMATION: 

Discussion

    We issued a notice of proposed rulemaking (NPRM) to amend 14 CFR 
part 39 to include an AD that would apply to the specified products. 
That NPRM published in the Federal Register on February 21, 2012 (77 FR 
9868). That NPRM proposed to require replacing affected LPT1 rotor 
assemblies with LPT1 rotor assemblies eligible for installation.

Comments

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

Request To Clarify Definition Paragraph

    One commenter requested we change a term in paragraph (h) of the 
proposed AD. The commenter requested that ``tie rod'' be changed to 
``tie shaft.'' The commenter said that making this change would allow a 
level of disassembly to access the inlet total temperature harness and 
other hardware without affecting the low-pressure turbine (LPT) module.
    We do not agree. Mandating access to the LPT module in the AD and 
suspect disks when the tie rod is unstretched is consistent in 
achieving AD compliance sooner for the Falcon 20 and CASA 101 
airplanes. LPT disk separations in these airplanes have been determined 
to be higher risk than for engines in other applications. We did not 
change the AD.

Conclusion

    We reviewed the relevant data, considered the comment received, and 
determined that air safety and the public interest require adopting the 
AD as proposed except for minor editorial changes. We have determined 
that these minor changes:
    <bullet> Are consistent with the intent that was proposed in the 
NPRM (77 FR 9868, February 21, 2012) for correcting the unsafe 
condition; and
    <bullet> Do not add any additional burden upon the public than was 
already proposed in the NPRM (77 FR 9868, February 21, 2012).
    We also determined that these changes will not increase the 
economic burden on any operator or increase the scope of the AD.

Costs of Compliance

    We estimate that this AD will affect 1,550 engines installed on 
airplanes of U.S. registry. We also estimate that it will take about 1 
work-hour per engine to perform the actions at next access and 165 
work-hours per unscheduled engine disassembly, and that the average 
labor rate is $85 per work-hour. Replacement parts will cost about 
$175,000 per engine. Based on these figures, we estimate the total cost 
of the AD to U.S. operators to be $35,195,488 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

    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 adding the following new airworthiness 
directive (AD):

2012-17-05 Honeywell International Inc. (formerly AlliedSignal Inc., 
formerly Garret Turbine Engine Company): Amendment 39-17168; Docket 
No. FAA-2011-1045; Directorate Identifier 2011-NE-32-AD.

[[Page 51894]]

(a) Effective Date

    This AD is effective October 2, 2012.

(b) Affected ADs

    None.

(c) Applicability

    This AD applies to Honeywell International Inc.:
    (1) Model TFE731-5 series turbofan engines, with a first stage 
low-pressure turbine (LPT1) rotor assembly, part number (P/N) 
3075184-2, 3075184-3, or 3075184-4, installed, and
    (2) Models TFE731-5AR and -5BR series turbofan engines, with a 
first stage LPT1 rotor assembly, P/N 3075447-1, 3075447-2, 3075447-
4, 3075713-1, 3075713-2, 3075713-3, or 3074748-5, installed, and
    (3) Models TFE731-4, -4R, -5AR, -5BR, and -5R series turbofan 
engines, with an LPT1 rotor assembly, P/N 3074748-4, 3074748-5, 
3075447-1, 3075447-2, 3075447-4, 3075713-1, 3075713-2, or 3075713-3, 
installed.

(d) Unsafe Condition

    This AD was prompted by a report of a rim/web separation of an 
LPT1 rotor assembly. We are issuing this AD to prevent uncontained 
disk separation, engine failure, and damage to the airplane.

(e) Compliance

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

(f) Engines Installed in Dassault-Aviation Falcon 20 and Construcciones 
Aeronauticas, S.A. (CASA) 101 Airplanes

    (1) Remove the LPT1 rotor assembly at the next access to the 
LPT1 rotor assembly or at the next major periodic inspection, not to 
exceed 2,600 hours-in-service since last major periodic inspection, 
or 8 years after the effective date of this AD, whichever occurs 
first.
    (2) Install an LPT1 rotor assembly that is eligible for 
installation.

(g) Engines Not Installed in Dassault-Aviation Falcon 20 or CASA 101 
Airplanes

    (1) Remove the LPT1 rotor assembly at the next core zone 
inspection, not to exceed 5,100 hours-in-service since last core 
zone inspection, or at the next time the LPT1 rotor disc is removed 
for cause, or 8 years after the effective date of this AD, whichever 
occurs first.
    (2) Install an LPT1 rotor assembly that is eligible for 
installation.

(h) Definitions

    (1) For the purpose of this AD, ``next access'' is when the low-
pressure tie rod is unstretched.
    (2) For the purpose of this AD, an LPT1 rotor assembly 
``eligible for installation'' is an LPT1 rotor assembly not having a 
P/N listed in this AD.

(i) Installation Prohibition

    After the effective date of this AD, do not install any LPT1 
rotor assembly listed by P/N in paragraphs (c)(1), (c)(2), and 
(c)(3) of this AD, into any engine.

(j) Alternative Methods of Compliance (AMOCs)

    The Manager, Los Angeles Aircraft Certification Office, FAA, may 
approve AMOCs for this AD. Use the procedures in 14 CFR 39.19 to 
request an AMOC.

(k) 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: 
<a href="/cdn-cgi/l/email-protection#b2d8ddc1d7c2da9cd1ddc1c6d3f2d4d3d39cd5ddc4"><span class="__cf_email__" data-cfemail="82e8edf1e7f2eaace1edf1f6e3c2e4e3e3ace5edf4">[email&#160;protected]</span></a>.
    (2) Honeywell International Inc. Service Bulletin (SB) No. 
TFE731-72-3768; SB No. TFE731-72-3769; and SB No. TFE731-72-3770, 
pertain to the subject of this AD.
    (3) For service information identified in this AD, contact 
Honeywell International Inc., 111 S. 34th Street, Phoenix, AZ 85034-
2802; Web site: <a href="http://portal.honeywell.com">http://portal.honeywell.com</a>; or call Honeywell toll 
free at phone: 800-601-3099 (U.S./Canada) or 602-365-3099 
(International Direct).

(l) Material Incorporated by Reference

    None.

    Issued in Burlington, Massachusetts, on August 14, 2012.
Robert G. Mann,
Acting Manager, Engine & Propeller Directorate, Aircraft Certification 
Service.
[FR Doc. 2012-21010 Filed 8-27-12; 8:45 am]
BILLING CODE 4910-13-P