Document ID: FAA-2007-27891-0002
Agency: faa
Document Type: Rule
Title: Airworthiness Directives; Honeywell International Inc. TFE731-2C, -3B, -3BR, -3C, -3CR, -3D, -3DR, -4R, -5AR, -5BR, -5R, -20R, -20AR, - 20BR, -40, -40AR, -40R, and -60 Series Turbofan Engines
Posted Date: 2008-01-31T05:00Z

[Federal Register: January 31, 2008 (Volume 73, Number 21)]
[Rules and Regulations]               
[Page 5735-5737]
From the Federal Register Online via GPO Access [wais.access.gpo.gov]
[DOCID:fr31ja08-6]                         

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DEPARTMENT OF TRANSPORTATION

Federal Aviation Administration

14 CFR Part 39

[Docket No. FAA-2007-27891; Directorate Identifier 2007-NE-14-AD; 
Amendment 39-15349; AD 2008-02-19]
RIN 2120-AA64

 
Airworthiness Directives; Honeywell International Inc. TFE731-2C, 
-3B, -3BR, -3C, -3CR, -3D, -3DR, -4R, -5AR, -5BR, -5R, -20R, -20AR, -
20BR, -40, -40AR, -40R, and -60 Series Turbofan Engines

AGENCY: Federal Aviation Administration (FAA), Department of 
Transportation (DOT).

ACTION: Final rule.

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SUMMARY: The FAA is adopting a new airworthiness directive (AD) for 
Honeywell International Inc. (Honeywell) TFE731-2C, -3B, -3BR, -3C, -
3CR, -3D, -3DR, -4R, -5AR, -5BR, -5R, -20R, -20AR, -20BR, -40, -40AR, -
40R, and -60 series turbofan engines. This AD requires removal from 
service of certain high pressure (HP) turbine rotor assemblies with 
part numbers (P/Ns) 3075772-1 and 3060841-1 using a drawdown schedule, 
and returning them to Honeywell for curvic root radius inspection. This 
AD results from the manufacturer's report

[[Page 5736]]

that some HP turbine rotor discs received improperly machined radii in 
the root of the forward and aft curvic teeth during manufacture. We are 
issuing this AD to prevent uncontained failure of the HP turbine rotor 
assembly, which could result in damage to the airplane.

DATES: This AD becomes effective March 6, 2008. The Director of the 
Federal Register approved the incorporation by reference of certain 
publications listed in the regulations as of March 6, 2008.

ADDRESSES: You can get the service information identified in this AD 
from Honeywell Technical Publications and Distribution, M/S 2101-201, 
P.O. Box 52170, Phoenix, AZ 85072-2170; telephone: (602) 365-2493 
(General Aviation), (602) 365-5535 (Commercial Aviation), fax: (602) 
365-5577 (General Aviation and Commercial Aviation).
    The Docket Operations office is located at Docket Management 
Facility, U.S. Department of Transportation, 1200 New Jersey Avenue 
SE., West Building Ground Floor, Room W12-140, Washington, DC 20590-
0001.

FOR FURTHER INFORMATION CONTACT: Joseph Costa, Aerospace Engineer, Los 
Angeles Aircraft Certification Office, FAA, Transport Airplane 
Directorate, 3960 Paramount Blvd., Lakewood, CA 90712-4137; e-mail: 
joseph.costa@faa.gov; telephone: (562) 627-5246; fax: (562) 627-5210.

SUPPLEMENTARY INFORMATION: The FAA proposed to amend 14 CFR part 39 
with a proposed AD. The proposed AD applies to Honeywell TFE731-2C, -
3B, -3BR, -3C, -3CR, -3D, -3DR, -4R, -5AR, -5BR, -5R, -20R, -20AR, -
20BR, -40, -40AR, -40R, and -60 series turbofan engines. We published 
the proposed AD in the Federal Register on September 4, 2007 (72 FR 
50648). That action proposed to require removal from service of certain 
HP turbine rotor assemblies with P/Ns 3075772-1 and 3060841-1 using a 
drawdown schedule, and returning them to Honeywell for curvic root 
radius inspection.

Examining the AD Docket

    You may examine the AD docket on the Internet at http://
www.regulations.gov; or in person at the Docket Operations office 
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 street address for 
the Docket Operations office (telephone (800) 647-5527) is provided in 
the ADDRESSES section. Comments will be available in the AD docket 
shortly after receipt.

Comments

    We provided the public the opportunity to participate in the 
development of this AD. We received no comments on the proposal or on 
the determination of the cost to the public.

Conclusion

    We have carefully reviewed the available data and determined that 
air safety and the public interest require adopting the AD as proposed.

Costs of Compliance

    We estimate that this AD will affect 400 HP turbine rotor discs 
installed in TFE731-20R, -20AR, -20BR, -40, -40AR, -40R, and -60 series 
turbofan engines, and 170 HP turbine rotor discs installed in TFE731-
2C, -3B, -3BR, -3C, -3CR, -3D, -3DR, -4R, -5AR, -5BR, and -5R series 
turbofan engines, installed in airplanes of U.S. registry. We also 
estimate that it will take about 42 work-hours per engine to perform 
the actions at an unscheduled removal, and about 2 work-hours at a 
scheduled removal. The average labor rate is $80 per work-hour. 
Required parts will cost about $46,535 per engine. We estimate that 50 
percent of the HP turbine rotor discs will fail the curvic root radius 
inspection. Based on these figures, we estimate the total cost of the 
AD to U.S. operators to be $13,490,000.

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

    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); and
    (3) 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.
    We prepared a summary of the costs to comply with this AD and 
placed it in the AD Docket. You may get a copy of this summary at the 
address listed under ADDRESSES.

List of Subjects in 14 CFR Part 39

    Air transportation, Aircraft, Aviation safety, Incorporation by 
reference, Safety.

Adoption of the Amendment

0
Accordingly, under the authority delegated to me by the Administrator, 
the Federal Aviation Administration 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:

2008-02-19 Honeywell International Inc. (formerly AlliedSignal Inc. 
and Garrett Turbine Engine Co.): Amendment 39-15349. Docket No. FAA-
2007-27891; Directorate Identifier 2007-NE-14-AD.

Effective Date

    (a) This airworthiness directive (AD) becomes effective March 6, 
2008.

Affected ADs

    (b) None.

Applicability

    (c) This AD applies to Honeywell International Inc. (Honeywell) 
TFE731-2C, -3B, -3BR, -3C, -3CR, -3D, -3DR, -4R, -5AR, -5BR, -5R, -
20R, -20AR, -20BR, -40, -40AR, -40R, and -60 series turbofan engines 
with certain high pressure (HP) turbine rotor discs part numbers and 
serial numbers. These engines are installed on, but not limited to, 
the following airplanes:

Avions Marcel Dassault Mystere-Falcon 10 and 50 Series

[[Page 5737]]

Cessna Model 650; Citations III, VI, and VII
Dassault-Aviation 20, 50, 50EX, 900, MF900, and 900EX (900DX) Series
Gulfstream Aerospace LP (formerly IAI) 1125 Westwind Astra, Astra SPX,
 Gulfstream 100 Series
Israel Aircraft Industries (IAI) 1124 Series (Westwind 1124)
Learjet 31, 35, 36, 45 (or Learjet 40), and 55 Series
Lockheed-Georgia 3329-25 Series (731 Jetstar, Jetstar II)
Raytheon Corporate Jets (formerly British Aerospace) Hawker 800 and 850
 Series
Sabreliner NA-265-65 (Sabreliner 65)

Unsafe Condition

    (d) This AD results from the manufacturer's report that some HP 
turbine rotor discs received improperly machined radii in the root 
of the forward and aft curvic teeth during manufacture. We are 
issuing this AD to prevent uncontained failure of the HP turbine 
rotor assembly, which could result in damage to the airplane.

Compliance

    (e) You are responsible for having the actions required by this 
AD performed within the compliance times specified unless the 
actions have already been done.

TFE731-2C, -3B, -3BR, -3C, -3CR, -3D, -3DR, -4R, -5AR, -5BR, and -5R 
Series Turbofan Engines

    (f) For TFE731-2C, -3B, -3BR, -3C, -3CR, -3D, -3DR, -4R, -5AR, -
5BR, and -5R series turbofan engines, remove HP turbine rotor 
assemblies from service containing HP turbine rotor discs, part 
number (P/N) 3075772-1, having any serial number (SN) in Table 1 of 
Honeywell Service Bulletin (SB) No. TFE731-72-3720, dated July 5, 
2006. Use the following drawdown schedule:
    (1) For HP turbine discs with 4,200 cycles-since-new (CSN) or 
more on the effective date of this AD, remove HP turbine rotor 
assemblies within 100 cycles-in-service (CIS) after the effective 
date of this AD.
    (2) For HP turbine discs with fewer than 4,200 CSN on the 
effective date of this AD, remove HP turbine rotor assemblies at the 
next access to the HP turbine rotor discs, but not to exceed 4,300 
CSN.

TFE731-20R, -20AR, -20BR, -40, -40AR, -40R, and -60 Series Turbofan 
Engines

    (g) For TFE731-20R, -20AR, -20BR, -40, -40AR, -40R, and -60 
series turbofan engines, remove HP turbine rotor assemblies from 
service containing HP turbine rotor discs, P/N 3060841-1, having any 
SN in Table 1 of Honeywell Alert SB No. TFE731-A72-5185, dated July 
5, 2006. Use the following drawdown schedule:
    (1) For HP turbine discs with 3,200 CSN or more on the effective 
date of this AD, remove HP turbine rotor assemblies within 100 CIS 
after the effective date of this AD.
    (2) For HP turbine discs with fewer than 3,200 CSN on the 
effective date of this AD, remove HP turbine rotor assemblies at the 
next access to the turbine rotor discs, but not to exceed 3,300 CSN.

For All Engines

    (h) HP turbine rotor discs removed per paragraphs (f) and (g) of 
this AD must pass a curvic root radius inspection performed by 
Honeywell Engines, Systems and Services, Phoenix, Arizona, 
Certificate Repair Station No. ZN3R030M, before the discs are 
eligible for reinstallation in an engine.
    (i) For the purposes of this AD, access to the HP turbine rotor 
discs is defined as the removal of the HP turbine rotor assembly 
from the engine.

Alternative Methods of Compliance

    (j) The Manager, Los Angeles Aircraft Certification Office, has 
the authority to approve alternative methods of compliance for this 
AD if requested using the procedures found in 14 CFR 39.19.

Related Information

    (k) Contact Joseph Costa, Aerospace Engineer, Los Angeles 
Aircraft Certification Office, FAA, Transport Airplane Directorate, 
3960 Paramount Blvd., Lakewood, CA 90712-4137; e-mail: 
joseph.costa@faa.gov; telephone: (562) 627-5246; fax: (562) 627-
5210, for more information about this AD.
    (l) For more information regarding the engine manufacturer's 
accomplishment instructions or material information, refer to 
Honeywell Alert SB No. TFE731-A72-5185, dated July 5, 2006, and SB 
No. TFE731-72-3720, dated July 5, 2006.
    (m) Also, for technical support regarding the curvic root 
dimensional inspection criteria, contact the Technical Operations 
Center: telephone: (800) 601-3099 (U.S.) or (602) 365-3099 
(International) and press option 9; e-mail: 
AeroTechSupport@Honeywell.com; or fax: (602) 365-3343.

Material Incorporated by Reference

    (n) You must use Table 1 of Honeywell Alert Service Bulletin No. 
TFE731-A72-5185, dated July 5, 2006, or Table 1 of Honeywell Service 
Bulletin No. TFE731-72-3720, dated July 5, 2006, as applicable, to 
determine SN applicability of HP turbine rotor discs requiring 
removal by this AD. The Director of the Federal Register approved 
the incorporation by reference of these service bulletins in 
accordance with 5 U.S.C. 552(a) and 1 CFR part 51. Contact Honeywell 
Technical Publications and Distribution, M/S 2101-201, P.O. Box 
52170, Phoenix, AZ 85072-2170; telephone: (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. You may review copies at the FAA, New England 
Region, 12 New England Executive Park, Burlington, MA; or at the 
National Archives and Records Administration (NARA). For information 
on the availability of this material at NARA, call 202-741-6030, or 
go to: http://www.archives.gov/federal-register/cfr/ibr-
locations.html.

    Issued in Burlington, Massachusetts, on January 16, 2008.
Peter A. White,
Assistant Manager, Engine and Propeller Directorate, Aircraft 
Certification Service.
[FR Doc. E8-1238 Filed 1-30-08; 8:45 am]

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