Airworthiness Directives; Honeywell International Inc. TFE731-2, -3, -4, and -5 Series Turbofan Engines

[Federal Register Volume 65, Number 153 (Tuesday, August 8, 2000)]
[Rules and Regulations]
[Pages 48353-48355]
From the Federal Register Online via the Government Publishing Office [www.gpo.gov]
[FR Doc No: 00-19666]


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DEPARTMENT OF TRANSPORTATION

Federal Aviation Administration

14 CFR Part 39

[Docket No. 99-NE-10-AD; Amendment 39-11841; AD 2000-15-09]
RIN 2120-AA64


Airworthiness Directives; Honeywell International Inc. TFE731-2, 
-3, -4, and -5 Series Turbofan Engines

AGENCY: Federal Aviation Administration, DOT.

ACTION: Final rule.

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SUMMARY: This amendment adopts a new airworthiness directive (AD), 
applicable to Honeywell International, Inc. (formerly AlliedSignal Inc. 
and Garrett Turbine Engine Company) high pressure compressor (HPC) 
impellers installed on TFE731-2, -3, -4, and -5 series turbofan 
engines. This AD requires the removal and inspection of the HPC 
impeller and, if necessary, replacement of the HPC impeller with a 
serviceable impeller. This amendment is prompted by an incident of an 
uncontained impeller failure due to cracking in the seal relief area of 
the HPC impeller. The actions specified by this AD are intended to 
prevent HPC impeller failure due to fatigue cracking.

DATES: Effective October 10, 2000. The incorporation by reference of 
certain publications listed in the regulations is approved by the 
Director of the Federal Register as of October 10, 2000.

ADDRESSES: The service information referenced in this AD may be 
obtained from Honeywell Engines and Systems (formerly AlliedSignal) 
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), fax: (602) 365-5577 (General Aviation), 
(602) 365-2832 (Commercial). This information may be examined at the 
Federal Aviation Administration (FAA), New England Region, Office of 
the Regional Counsel, 12 New England Executive Park, Burlington, MA; or 
at the Office of the Federal Register, 800 North Capitol Street, NW, 
suite 700, Washington, DC.

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

SUPPLEMENTARY INFORMATION: A proposal to amend part 39 of the Federal 
Aviation Regulations (14 CFR part 39) to include an airworthiness 
directive (AD) applicable to Honeywell International, Inc. (formerly 
AlliedSignal Inc. and Garrett Turbine Engine Company) high pressure 
compressor (HPC) impellers installed on TFE731-2, -3, -4, and -5 series 
turbofan engines was published in the Federal Register on July 28, 1999 
(64 FR 40789). That action proposed to require replacement of the HPC 
impeller with a serviceable impeller, which has been eddy-current 
inspected, at the next core zone inspection (CZI) or at the next access 
to the HPC module, and repetitive inspections at each subsequent CZI or 
each subsequent access to the HPC impeller for cause if the impeller 
has more than 1,000 cycles since the last eddy current inspection 
(ECI). The NPRM was prompted by the failure of a high pressure 
compressor (HPC) impeller, part number (P/N) 3073394-1, that separated 
and exited from a TFE731-3R-1D turbofan engine. Following that event, 
low-temperature fatigue testing with a sustained peak hold time (dwell) 
at higher than engine-operating stresses indicated that normal cyclic 
fatigue lives may be influenced by dwell times and an unfavorable 
titanium macrostructure. The FAA determined that low-cycle fatigue 
(LCF) cracking in high stressed areas of the HPC impeller may lead to 
an uncontained impeller separation.
    The FAA received a number of comments on that proposal. As a result 
of those comments, the FAA published a supplemental notice of proposed 
rulemaking (NPRM) in the Federal Register on March 7, 2000 (65 FR 
11942). This supplemental NPRM revised the proposed rule by eliminating 
the terminating action and adding impeller P/Ns to the suspect impeller 
population. The supplemental NPRM also clarified certain portions of 
the proposed AD based on comments received from the public.

Conclusion

    Interested persons have been afforded an opportunity to participate 
in the making of this amendment. No comments were received on the 
supplemental proposal or the FAA's revised economic analysis. All 
comments on the original NPRM were addressed in the discussion of the 
supplemental notice. The FAA has determined that air safety and the 
public interest require the adoption of the rule as proposed.

Economic Analysis

    There are approximately 7,510 engines of the affected design in the 
worldwide fleet. The FAA estimates that 5,482 engines installed on 
aircraft of U.S. registry will be affected by this AD, that it will 
take approximately three work hours per engine to accomplish the 
required actions, and that the average labor rate is $60 per work hour. 
The FAA also estimates that some of the impellers will be replaced and 
that each impeller will cost approximately $45,000. Based on these 
figures, the FAA estimates the total cost impact of the AD on U.S. 
operators for the next four years will be $2,201,760.

Regulatory Impact

    This rule does not have federalism implications, as defined in 
Executive Order 13132, because it does 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

[[Page 48354]]

responsibilities among the various levels of government. Accordingly, 
the FAA has not consulted with state authorities prior to publication 
of this rule.
    For the reasons discussed above, I certify that this action (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. A final evaluation has been prepared for this action 
and is contained in the Rules Docket. A copy of it may be obtained from 
the Rules Docket at the location provided under the caption ADDRESSES.

List of Subjects in 14 CFR Part 39

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

Adoption of the Amendment

    Accordingly, pursuant to the authority delegated to me by the 
Administrator, the Federal Aviation Administration amends part 39 of 
the Federal Aviation Regulations (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. Section 39.13 is amended by adding the following new 
airworthiness directive:

2000-15-09  Honeywell International Inc.: Amendment 39-11841. Docket 
99-NE-10-AD.

Applicability

    Honeywell International Inc. (formerly AlliedSignal Inc. and 
Garrett Turbine Engine Company) TFE731-2, -3, -4, and -5 series 
turbofan engines with high pressure compressor (HPC) impeller part 
numbers (P/Ns) 3073393-1, 3073394-1, 3073433-1, 3073434-1, 3073398-
All (All denotes all dash numbers), 3073435-All, and 3075171-All, 
installed on, but not limited to, Avions Marcel Dassault-Breguet 
Aviation (AMD-BA) Falcon 10, Dassault-Aviation Mystere-Falcon 50, 
and 900 series airplanes; Dassault Aviation Mystere-Falcon 20 series 
airplanes; Learjet Inc. Models 31, 35, 36, and 55 series airplanes; 
Lockheed-Georgia Corporation 1329-23 and 25 series airplanes; Israel 
Aircraft Industries Ltd. 1124 series and 1125 Westwind series 
airplanes; Cessna Aircraft Co. Model 650 Citation III, VI, and VII 
series airplanes; Raytheon Aircraft Co. HS-125 series airplanes; and 
Sabreliner Corporation NA-265-65 airplanes.

    Note 1: This airworthiness directive (AD) applies to each engine 
identified in the preceding applicability provision, regardless of 
whether it has been modified, altered, or repaired in the area 
subject to the requirements of this AD. For engines that have been 
modified, altered, or repaired so that the performance of the 
requirements of this AD is affected, the owner/operator must request 
approval for an alternative method of compliance in accordance with 
paragraph (e) of this AD. The request should include an assessment 
of the effect of the modification, alteration, or repair on the 
unsafe condition addressed by this AD; and, if the unsafe condition 
has not been eliminated, the request should include specific 
proposed actions to address it.

Compliance

    Required as indicated, unless accomplished previously.
    To prevent failure of the HPC impeller due to fatigue cracking, 
accomplish the following:

Initial Inspection

    (a) Remove and inspect the applicable HPC impeller in accordance 
with Section 2.A. of the Accomplishment Instructions of AlliedSignal 
Inc. Alert Service Bulletin (ASB) TFE731-A72-3641, Revision 1, dated 
October 20, 1999, or ASB TFE731-A72-3641 dated November 24, 1998, 
and, if necessary, replace the impeller with a serviceable impeller 
at the earlier of the following:
    (1) At the next core zone inspection (CZI) after the effective 
date of this AD; or
    (2) At the next access to the HPC module after the effective 
date of this AD.

Repetitive Inspection

    (b) Thereafter, remove and inspect the applicable HPC impeller 
in accordance with Section 2.A. of the Accomplishment Instructions 
of ASB TFE731-A72-3641, dated November 24, 1998, or ASB TFE731-A72-
3641, Revision 1, dated October 20, 1999, and, if necessary, replace 
the impeller with a serviceable impeller, whenever either of the 
following conditions are met:
    (1) At every CZI; or
    (2) At access to the HPC module if the impeller has accumulated 
more than 1,000 cycles since the last Eddy Current Inspection (ECI).

Definitions

    (c) This AD defines access to the HPC module as whenever the low 
pressure compressor case is removed from the compressor interstage 
diffuser.
    (d) For the purposes of this AD, a serviceable impeller is 
defined as an impeller that complies with all applicable visual, 
dimensional, and fluorescent penetrant inspections requirements for 
the level of maintenance being accomplished, as contained in the 
Heavy Maintenance Manual, and is either an impeller with fewer than 
1000 engine operation cycles since new or an impeller with fewer 
than 1000 engine operation cycles since last ECI.

Alternative Method of Compliance

    (e) An alternative method of compliance or adjustment of the 
compliance time that provides an acceptable level of safety may be 
used if approved by the Manager, Los Angeles Aircraft Certification 
Office (LAACO). Operators shall submit their request through an 
appropriate FAA Principal Maintenance Inspector, who may add 
comments and then send it to the Manager, LAACO.

    Note 2: Information concerning the existence of approved 
alternative methods of compliance with this airworthiness directive, 
if any, may be obtained from the LAACO.

Special Flight Permits

    (f) Special flight permits may be issued in accordance with 
Secs. 21.197 and 21.199 of the Federal Aviation Regulations (14 CFR 
21.197 and 21.199) to operate the aircraft to a location where the 
requirements of this AD can be accomplished.

Documents Incorporated by Reference

    (g) The actions required by this AD shall be done in accordance 
with the following AlliedSignal Inc. Alert Service Bulletins:

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           Document No.               Pages             Revision                            Date
----------------------------------------------------------------------------------------------------------------
TFE731-A72-3641...................         10  Original..................  November 24, 1998.
    Total pages: 10
TFE731-A72-3641...................         12  1.........................  October 20, 1999.
    Total pages: 12
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This incorporation by reference was approved by the Director of the 
Federal Register in accordance with 5 U.S.C. 552(a) and 1 CFR part 
51. Copies may be obtained from Honeywell Engines and Systems 
(formerly AlliedSignal) 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), fax: (602) 
365-5577 (General Aviation), (602) 365-2832 (Commercial). Copies may 
be inspected at the FAA, New England Region, Office of the Regional 
Counsel, 12 New England Executive Park, Burlington, MA; or at the 
Office of the Federal Register, 800 North Capitol Street NW., suite 
700, Washington, DC.

[[Page 48355]]

Effective Date

    (h) This amendment becomes effective on October 10, 2000.

    Issued in Burlington, Massachusetts, on July 10, 1999.
David A. Downey,
Assistant Manager, Engine and Propeller Directorate, Aircraft 
Certification Service.
[FR Doc. 00-19666 Filed 8-7-00; 8:45 am]
BILLING CODE 4910-13-P

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