[Federal Register Volume 65, Number 206 (Tuesday, October 24, 2000)]
[Rules and Regulations]
[Pages 63535-63537]
From the Federal Register Online via the Government Publishing Office [www.gpo.gov]
[FR Doc No: 00-26972]


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DEPARTMENT OF TRANSPORTATION

Federal Aviation Administration

14 CFR Part 39

[Docket No. 2000-NE-40-AD; Amendment 39-11942; AD 2000-21-10]
RIN 2120-AA64


Airworthiness Directives; CFE Company CFE738-1-1B Turbofan 
Engines

AGENCY: Federal Aviation Administration, DOT.

ACTION: Final rule; request for comments.

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SUMMARY: This amendment adopts a new airworthiness directive (AD) that 
is applicable to CFE Company CFE738-1-1B turbofan engines. This action 
requires removing certain support assemblies and replacing them with 
support assemblies that have a new design. This amendment is prompted 
by a report of the loss of seal retention that resulted in contact 
between the seal face and the stage 2 high pressure turbine (HPT) rotor 
disk, and subsequent wear of the stage 2 HPT rotor disk. That condition 
resulted in separation of the stage 2 HPT wheel rim, and an uncontained 
failure of the stage 2 HPT rotor wheel. The actions specified in this 
AD are intended to prevent the static seal from moving forward, which 
could result in contact between the seal face and stage 2 HPT rotor, 
wear, and the possibility of an uncontained failure of the stage 2 HPT 
rotor.

DATES: Effective November 8, 2000. The incorporation by reference of 
certain publications listed in the rule is approved by the Director of 
the Federal Register as of November 8, 2000.
    Comments for inclusion in the Rules Docket must be received on or 
before December 26, 2000.

ADDRESSES: Submit comments in triplicate to the Federal Aviation 
Administration (FAA), New England Region, Office of the Regional 
Counsel, Attention: Rules Docket No. 2000-NE-40-AD, 12 New England 
Executive Park, Burlington, MA 01803-5299. Comments may also be sent 
via the Internet using the following address: ``[email protected]''. Comments sent via the Internet must contain the 
docket number in the subject line.
    The service information referenced in this AD may be obtained from 
CFE Company, Data Distribution, MS 64-03/2101-201, P.O. Box 52170, 
Phoenix, AZ 85972-2170; telephone (602) 365-2493, fax (602) 365-5577. 
This information may be examined 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.

FOR FURTHER INFORMATION CONTACT: Keith Mead, Aerospace Engineer, Engine 
Certification Office, FAA, Engine and Propeller Directorate, 12 New 
England Executive Park, Burlington, MA 01803-5299; telephone (781) 238-
7744, fax (781) 238-7199.

SUPPLEMENTARY INFORMATION: On June 27, 2000, the FAA was notified of an 
uncontained engine failure of a CFE738-1-1B turbofan engine. A 
subsequent investigation determined that the rivets that retain the 
seal to the

[[Page 63536]]

No. 4 bearing support, part of the support assembly, wore and allowed 
the seal to migrate forward and contact the stage 2 HPT rotor disk. 
That contact caused a deep wear groove in the disk web, and subsequent 
separation of portions of the disk rim from the stage 2 HPT disk, 
resulting in an uncontained failure of the engine. This condition, if 
not corrected, could result in wear damage to the stage 2 HPT rotor 
disk that could result in fracture and a possible uncontained failure 
of the disk.

Manufacturer's Service Information

    The FAA has reviewed and approved the technical contents of the 
following CFE Company service information:
     Alert Service Bulletin (ASB) CFE738-A72-8042, Revision 1, 
dated September 25, 2000. That ASB describes procedures for replacing 
the support assembly with a new design support assembly, which has 
improved static seal retention.
     SB CFE738-72-8043, dated October 2, 2000, that provides 
procedures for the break-in of the engine support assembly seal.
    The FAA has also reviewed and approved the technical contents of 
ASB CFE738-A72-8041, dated August 21, 2000, that describes procedures 
for borescope inspection of:
     The stage 2 HPT rotor disk for contact rubs.
     The rivets that attach the static seal to the bearing 
frame support to ensure there are no anomalies.
     The bearing frame support and static seal to determine if 
there is a gap between them.
     The static seal to determine if there is any distortion or 
waviness.

Requirements of This AD

    Since an unsafe condition has been identified that is likely to 
exist or develop on other CFE Company CFE738-1-1B turbofan engines of 
the same type design, this AD is being issued to require replacing 
existing support assemblies, part numbers (P/N's) 3050860-2, -3, and -5 
through -9 inclusive, with new support assemblies, P/N 3050860-10, -11, 
P/N 3057005-1 through -5 inclusive, or P/N 3057006-1, -2. The 
replacement of the support assembly must be done in accordance with ASB 
CFE738-A72-8042, Revision 1, dated September 25, 2000. Break-in of the 
support assembly seal must be done in accordance with SB CFE738-72-
8043, Revision 1, dated October 2, 2000. For engines that have not been 
borescope inspected using ASB CFE738-A72-8041, dated August 21, 2000, 
the support assembly must be replaced or borescope inspected within the 
specified replacement interval for that group. The borescope inspection 
must be done in accordance with ASB CFE738-A72-8041, dated August 21, 
2000.

Immediate Adoption of This AD

    Since a situation exists that requires the immediate adoption of 
this regulation, it is found that notice and opportunity for prior 
public comment hereon are impracticable, and that good cause exists for 
making this amendment effective in less than 30 days.

Comments Invited

    Although this action is in the form of a final rule that involves 
requirements affecting flight safety and, thus, was not preceded by 
notice and an opportunity for public comment, comments are invited on 
this rule. Interested persons are invited to comment on this rule by 
submitting such written data, views, or arguments as they may desire. 
Communications should identify the Rules Docket number and be submitted 
in triplicate to the address specified under the caption ADDRESSES. All 
communications received on or before the closing date for comments will 
be considered, and this rule may be amended in light of the comments 
received. Factual information that supports the commenter's ideas and 
suggestions is extremely helpful in evaluating the effectiveness of the 
AD action and determining whether additional rulemaking action would be 
needed.
    Comments are specifically invited on the overall regulatory, 
economic, environmental, and energy aspects of the rule that might 
suggest a need to modify the rule. All comments submitted will be 
available, both before and after the closing date for comments, in the 
Rules Docket for examination by interested persons. A report that 
summarizes each FAA-public contact concerned with the substance of this 
AD will be filed in the Rules Docket.
    Commenters wishing the FAA to acknowledge receipt of their comments 
submitted in response to this notice must submit a self-addressed, 
stamped postcard on which the following statement is made: ``Comments 
to Docket Number 2000-NE-40-AD.'' The postcard will be date stamped and 
returned to the commenter.

Regulatory Impact

    This proposed rule does not have federalism implications, as 
defined in Executive Order No. 13132, because it 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. 
Accordingly, the FAA has not consulted with state authorities prior to 
publication of this proposed rule.
    The FAA has determined that this regulation is an emergency 
regulation that must be issued immediately to correct an unsafe 
condition in aircraft, and is not a ``significant regulatory action'' 
under Executive Order 12866. It has been determined further that this 
action involves an emergency regulation under DOT Regulatory Policies 
and Procedures (44 FR 11034, February 26, 1979). If it is determined 
that this emergency regulation otherwise would be significant under DOT 
Regulatory Policies and Procedures, a final regulatory evaluation will 
be prepared and placed in the Rules Docket. A copy of it, if filed, 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:

2000-21-10 CFE Company: Amendment 39-11942. Docket 2000-NE-40-AD.

    Applicability: This AD is applicable to CFE Company CFE738-1-1B 
turbofan engines with support assembly, part numbers (P/N's) 
3050860-2, -3, and -5 through -9 inclusive, installed. These engines 
are installed on, but not limited to, Dassault Aviation Falcon 2000 
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)

[[Page 63537]]

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: Compliance with this AD is required as indicated, 
unless already done.
    To prevent the static seal from moving forward, which could 
result in contact between the seal face and stage 2 HPT rotor, wear, 
and the possibility of an uncontained failure of the stage 2 HPT 
rotor, do the following:
    (a) Remove support assembly, P/N 3050860-2, -3, -5 through -9, 
and replace it with a serviceable seal assembly in accordance with 
the Accomplishment instructions 2.A.(3) through 2.A.(8)(d) and 
2.B.(1) through 2.B.(3) of ASB CFE738 A72-8042, Revision 1, dated 
September 25, 2000, as follows:

Engines That Have Already Been Inspected

    (1) For engines that have been inspected using CFE Company alert 
service bulletin (ASB) ASB CFE738 A72-8041, dated August 21, 2000, 
replace the support assembly as follows:

------------------------------------------------------------------------
  Operating hours time-since new
  (TSN) on the effective date of         Replace by the earlier of--
              this AD
------------------------------------------------------------------------
Fewer than 500 hours TSN..........  150 hours time-in-service (TIS) or
                                     90 days after the effective date of
                                     this AD.
500 hours to 1,000 hours TSN......  250 hours TIS or 150 days after the
                                     effective date of this AD.
More than 1,000 hours TSN.........  400 hours TIS or 240 days after the
                                     effective date of this AD.
------------------------------------------------------------------------

Engines That Have Not Been Inspected

    (2) For engines that have not been inspected using CFE Company 
alert service bulletin (ASB) ASB CFE738 A72-8041, dated August 21, 
2000, do EITHER of the following within the earlier of 50 hours TIS 
or 30 days after the effective date of this AD:
    (i) Replace the support assembly with a serviceable support 
assembly in accordance with the Accomplishment instructions 2.A.(3) 
through 2.A.(8)(d) and 2.B.(1) through 2.B.(3) of ASB CFE738 A72-
8042, and 2.A. or 2.B. of SB CFE738-72-8043, Revision 1, dated 
October 2, 2000;
    (ii) Inspect the engine in accordance with the Accomplishment 
Instructions 2.A. through 2.B.(6) of ASB CFE738-A72-8041, dated 
August 21, 2000, and then replace the support assembly in accordance 
with the replacement schedule in paragraph (a)(1) of this AD.

Support Assembly Seal Break-In

    (b) After the seal has been replaced, do the support assembly 
seal break-in procedure in accordance 2.A. (test cell) or 2.B. (on 
wing) of SB CFE738-72-8043, Revision 1, dated October 2, 2000.

Definition of a Serviceable Part

    (c) For the purposes of this AD, a serviceable support assembly 
is defined as a support assembly with P/N 3050860-10, or -11, P/N 
3057005-1 through -5 inclusive, or P/N 3057006-1, or -2.

Alternative Methods 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, Engine Certification Office (ECO). 
Operators shall submit their requests through an appropriate FAA 
Principal Maintenance Inspector, who may add comments and then send 
it to the Manager, ECO.

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

Special Flight Permits

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

Documents That Have Been Incorporated by Reference

    (f) The actions specified in this AD must be done in accordance 
with the following CFE Company service bulletins:

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            Document No.                     Pages               Revision                     Date
----------------------------------------------------------------------------------------------------------------
ASB CFE738-A72-8041................  All.................  Original...........  August 21, 2000.
Total pages: 26.
ASB CFE738-A72-8042................  All.................  1..................  September 25, 2000.
Total pages: 22.
SB CFE738-72-8043..................  All.................  1..................  October 2, 2000.
Total pages: 28.
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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 CFE Company, Data Distribution, MS 
64-03/2101-201, P.O. Box 52170, Phoenix, AZ 85972-2170; telephone 
(602) 365-2493, fax (602) 365-5577. 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 of This AD

    (g) This amendment becomes effective on November 8, 2000.

    Issued in Burlington, Massachusetts, on October 16, 2000.
Jay J. Pardee,
Manager, Engine and Propeller Directorate, Aircraft Certification 
Service.
[FR Doc. 00-26972 Filed 10-23-00; 8:45 am]
BILLING CODE 4910-13-P