Airworthiness Directives; Allison Engine Company, Inc. AE 3007A and AE 3007C Series Turbofan Engines

[Federal Register Volume 65, Number 128 (Monday, July 3, 2000)]
[Rules and Regulations]
[Pages 40981-40983]
From the Federal Register Online via the Government Publishing Office [www.gpo.gov]
[FR Doc No: 00-16232]


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DEPARTMENT OF TRANSPORTATION

Federal Aviation Administration

14 CFR Part 39

[Docket No. 99-NE-15-AD; Amendment 39-11800; AD 2000-13-01]
RIN 2120-AA64


Airworthiness Directives; Allison Engine Company, Inc. AE 3007A 
and AE 3007C Series Turbofan Engines

AGENCY: Federal Aviation Administration, DOT.

ACTION: Final rule.

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SUMMARY: This amendment adopts a new airworthiness directive (AD) that 
is applicable to Allison Engine Company, Inc. AE 3007A and AE 3007C 
series turbofan engines. This AD requires the removal from service of 
certain turbine wheels before exceeding new, reduced cyclic life 
limits. This amendment is prompted by a refined life analysis that was 
performed by the manufacturer.

[[Page 40982]]

The actions specified by this AD are intended to prevent an uncontained 
turbine wheel failure, which could result in damage to the airplane.

DATES: Effective date September 1, 2000. The incorporation by reference 
of certain publications listed in the rule is approved by the Director 
of the Federal Register as of September 1, 2000.

ADDRESSES: The service information referenced in this AD may be 
obtained from Rolls-Royce Allison, P.O. Box 420, Indianapolis, IN 
46206-0420; telephone: (888) 255-4766. 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: John Tallarovic, Aerospace Engineer, 
Chicago Aircraft Certification Office, FAA, Small Airplane Directorate, 
2300 East Devon Avenue, Des Plaines, IL 60018; telephone (847) 294-
8180, fax (847) 294-7834.

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 Allison Engine Company, Inc. AE 3007A and 
AE 3007C series turbofan engines was published in the Federal Register 
on August 5, 1999 (64 FR 42622). That action proposed to require the 
removal of certain turbine wheels from service before exceeding new, 
reduced cyclic life limits listed in Rolls-Royce Alert Service Bulletin 
(ASB) AE 3007A-A-72-105/AE 3007C-A-72-105, dated January 29, 1999.
    Interested persons have been afforded an opportunity to participate 
in the making of this amendment. Due consideration has been given to 
the comments received.

Support for the Rule

    One commenter supports the proposed rule as written.

Part Numbers

    One commenter requests the addition of part numbers (P/N) to the 
compliance section. The commenter states that the way the NPRM is 
written, paragraphs (a)(2) and (b)(2) could be interpreted to mean that 
all stage 1 and stage 2 turbine wheels, respectively, should have lower 
lives. In fact, the life reduction is limited to a few part numbers. 
The addition of the affected part numbers would prevent confusion.
    The FAA agrees. To eliminate confusion, paragraph (a)(2) of the 
compliance section of the final rule has been revised to specify P/Ns 
23065891 and 23062373. Paragraph (b)(2) of the compliance section of 
the final rule has been revised to specify P/Ns 23065892 and 23063462.

Conclusion

    After careful review of the available data, including the comments 
noted above, the FAA has determined that air safety and the public 
interest require the adoption of the rule with the changes described 
previously. The FAA has determined that these changes will neither 
increase the economic burden on any operator nor increase the scope of 
the AD.

Economic Analysis

    There are approximately 325 engines of the affected design in the 
worldwide fleet. The FAA estimates that 260 engines installed on 
aircraft of U.S. registry will be affected by this AD, that it will 
take approximately 63 work hours per engine to accomplish the required 
actions, and that the average labor rate is $60 per work hour. The 
estimated cost of the lost cycles due to the reduction of the engine 
cycle life limit is $57,800 per engine. Based on these figures, the 
total cost impact of the AD on U.S. operators is estimated to be 
$15,028,000. The manufacturer of the affected turbine wheels has 
advised the FAA that it may defray the cost of the reduced life limits, 
thus reducing the overall cost to operators.

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 
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:

2000-13-01  Allison Engine Company, Inc.: Amendment 39-11800. Docket 
No. 99-NE-15-AD.

Applicability

    Allison Engine Company, Inc. AE 3007A and AE 3007C series 
turbofan engines, installed on, but not limited to, Cessna Aircraft 
Company 750 series airplanes and Empresa Brasileira de Aeronautica 
S.A. (Embraer) EMB-145 series 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 (d) 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 an uncontained turbine wheel failure, which could 
result in damage to the airplane, accomplish the following:

Remove and Replace

    (a) Remove stage 1 turbine wheels, part numbers (P/Ns) 23065891 
and 23062373, and replace with new or serviceable parts as follows:
    (1) For stage 1 turbine wheels with serial numbers (SNs) listed 
in Table 5 of Rolls-Royce Alert Service Bulletin (ASB) AE 3007A-A-
72-105 and AE 3007C-A-72-105, dated January 29, 1999, replace before 
accumulating 9,000 engine cycles since new (CSN).

[[Page 40983]]

    (2) For all other stage 1 turbine wheel SNs with P/Ns 23065891 
and 23062373, replace before accumulating 13,100 engine CSN.
    (b) Remove stage 2 turbine wheels, P/Ns 23065892 and 23063462, 
and replace with new or serviceable parts as follows:
    (1) For stage 2 turbine wheels with SNs listed in Table 6 of 
Rolls-Royce ASB AE 3007A-A-72-105 and AE 3007C-A-72-105, dated 
January 29, 1999, replace before accumulating 7,800 engine CSN.
    (2) For all other stage 2 turbine wheel SNs with P/Ns 23065892 
and 23063462, replace before accumulating 8,400 engine CSN.

Alternative Life Limits

    (c) This AD establishes new cyclic life limits for the turbine 
wheels identified in paragraphs (a) and (b) of this AD. Except in 
accordance with paragraph (d) of this AD, no alternative life limits 
may be approved for the turbine wheels identified in paragraphs (a) 
and (b) of this AD.

Alternative Method of Compliance

    (d) 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, Chicago Aircraft Certification 
Office. Operators shall submit their request through an appropriate 
FAA Principal Maintenance Inspector, who may add comments and then 
send it to the Manager, Chicago Aircraft Certification Office.

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

Special Flight Permits

    (e) 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

    (f) This AD references Rolls-Royce Alert Service Bulletin AE 
3007A-A-72-105/AE 3007C-A-72-105, dated January 29, 1999. 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 Rolls-Royce Allison, P.O. Box 420, 
Indianapolis, IN 46206-0420; telephone: (888) 255-4766. 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.

Effective Date

    (g) This amendment becomes effective on September 1, 2000.

    Issued in Burlington, Massachusetts, on June 19, 2000.
Jay J. Pardee,
Manager, Engine and Propeller Directorate, Aircraft Certification 
Service.
[FR Doc. 00-16232 Filed 6-30-00; 8:45 am]
BILLING CODE 4910-13-U

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