[Federal Register Volume 77, Number 34 (Tuesday, February 21, 2012)]
[Proposed Rules]
[Pages 9868-9869]
From the Federal Register Online via the Government Publishing Office [www.gpo.gov]
[FR Doc No: 2012-3861]


========================================================================
Proposed Rules
                                                Federal Register
________________________________________________________________________

This section of the FEDERAL REGISTER contains notices to the public of 
the proposed issuance of rules and regulations. The purpose of these 
notices is to give interested persons an opportunity to participate in 
the rule making prior to the adoption of the final rules.

========================================================================


Federal Register / Vol. 77, No. 34 / Tuesday, February 21, 2012 / 
Proposed Rules

[[Page 9868]]



DEPARTMENT OF TRANSPORTATION

Federal Aviation Administration

14 CFR Part 39

[Docket No. FAA-2011-1045; Directorate Identifier 2011-NE-32-AD]
RIN 2120-AA64


Airworthiness Directives; Honeywell International Inc. Turbofan 
Engines

AGENCY: Federal Aviation Administration (FAA), DOT.

ACTION: Notice of proposed rulemaking (NPRM).

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

SUMMARY: We propose to adopt a new airworthiness directive (AD) for 
certain Honeywell International Inc. models TFE731-4, -4R, -5, -5R, -
5AR, and -5BR series turbofan engines. This proposed AD was prompted by 
a report of a rim/web separation of a first stage low-pressure turbine 
(LPT1) rotor assembly. This proposed AD would require replacing 
affected LPT1 rotor assemblies with LPT1 rotor assemblies eligible for 
installation. We are proposing this AD to prevent uncontained disk 
separation, leading to fuel tank penetration, fire, personal injury, 
and damage to the airplane.

DATES: We must receive comments on this proposed AD by April 23, 2012.

ADDRESSES: You may send comments, using the procedures found in 14 CFR 
11.43 and 11.45, by any of the following methods:
    <bullet> Federal eRulemaking Portal: Go to http://www.regulations.gov. Follow the instructions for submitting comments.
    <bullet> Fax: 202-493-2251.
    <bullet> 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.
    <bullet> 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 Engines and Systems Technical Publications and Distribution, 
M/S 2101-201, P.O. Box 52170, Phoenix, AZ 85072-2170, phone: 602-365-
2493 (General Aviation), 602-365-5535 (Commercial Aviation), fax: 602-
365-5577 (General Aviation and Commercial Aviation). You may review 
copies of the referenced 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; 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: <a href="/cdn-cgi/l/email-protection#c1abaeb2a4b1a9efa2aeb2b5a081a7a0a0efa6aeb7"><span class="__cf_email__" data-cfemail="a4cecbd7c1d4cc8ac7cbd7d0c5e4c2c5c58ac3cbd2">[email protected]</span></a>.

SUPPLEMENTARY INFORMATION: 

Comments Invited

    We invite you to send any written relevant data, views, or 
arguments about this proposal. Send your comments to an address listed 
under the ADDRESSES section. Include ``Docket No. FAA-2011-1045; 
Directorate Identifier 2011-NE-32-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

    We received a report of a rim/web separation on an LPT1 rotor disk, 
part number (P/N) 3075446-2, in a TFE731-5BR engine. The crack 
propagated in sustained peak strain low-cycle-fatigue, and accumulated 
762 cycles-in-service (CIS) before failure. The current published life 
limit for this part is 10,000 CIS. The most probable cause for this 
separation was due to LPT1 blade walking. This condition, if not 
corrected, could result in an uncontained disk separation, fuel tank 
penetration, fire, personal injury, and damage to the airplane.

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 replacing affected LPT1 rotor 
assemblies with improved design LPT1 rotor assemblies that are eligible 
for installation.

Costs of Compliance

    We estimate that this proposed AD would affect 1,550 engines 
installed on airplanes of U.S. registry. We also estimate that it would 
take about 1 work-hour per engine to perform the proposed 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 
would cost about $175,000 per engine. Based on these figures, we 
estimate the total cost of the proposed 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:

[[Page 9869]]

``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

    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

    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]

    2. The FAA amends Sec.  39.13 by adding the following new 
airworthiness directive (AD):

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

(a) Comments Due Date

    We must receive comments by April 23, 2012.

(b) Affected ADs

    None.

(c) Applicability

    (1) This AD applies to Honeywell International Inc. model 
TFE731-5 series engines, with a first stage low-pressure turbine 
(LPT1) rotor assembly, part number (P/N) 3075184-2, 3075184-3, or 
3075184-4, installed.
    (2) This AD also applies to Honeywell International Inc. models 
TFE731-5AR and -5BR series 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.
    (3) This AD also applies to Honeywell International Inc. 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, leading to fuel tank penetration, fire, personal 
injury, 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, if the rotor assembly must 
be replaced as specified in paragraph (f)(1) or (g)(1) 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#93f9fce0f6e3fbbdf0fce0e7f2d3f5f2f2bdf4fce5"><span class="__cf_email__" data-cfemail="254f4a5640554d0b464a565144654344440b424a53">[email 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. Contact Honeywell Engines and 
Systems Technical Publications and Distribution, M/S 2101-201, P.O. 
Box 52170, Phoenix, AZ 85072-2170, phone: 602-365-2493 (General 
Aviation), 602-365-5535 (Commercial Aviation), fax: 602-365-5577 
(General Aviation and Commercial Aviation), for a copy of this 
service information.
    (3) You may review copies of the referenced 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 February 3, 2012.
Peter A. White,
Manager, Engine & Propeller Directorate, Aircraft Certification 
Service.
[FR Doc. 2012-3861 Filed 2-17-12; 8:45 am]
BILLING CODE 4910-13-P


</pre><script data-cfasync="false" src="/cdn-cgi/scripts/5c5dd728/cloudflare-static/email-decode.min.js"></script></body>
</html>