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

[Federal Register Volume 66, Number 246 (Friday, December 21, 2001)]
[Rules and Regulations]
[Pages 65832-65834]
From the Federal Register Online via the Government Publishing Office [www.gpo.gov]
[FR Doc No: 01-31326]


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DEPARTMENT OF TRANSPORTATION

Federal Aviation Administration

14 CFR Part 39

[Docket No. 2001-NE-28-AD; Amendment 39-12570; AD 2001-26-06]
RIN 2120-AA64


Airworthiness Directives; CFE Company Model 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 model CFE738-1-1B turbofan engines. This 
action requires the removal of certain fan rotor disks from service. 
This amendment is prompted by a report from a forging manufacturer, of 
a metallurgical inclusion (contaminant) found in a forging made from a 
certain

[[Page 65833]]

ingot of titanium. Fan rotor disks for model CFE738-1-1B engines have 
been manufactured from this same ingot and are suspect for 
metallurgical inclusions. The actions specified in this AD are intended 
to remove from service affected fan rotor disks, which if not removed, 
could result in uncontained engine failure and damage to the airplane.

DATES: Effective January 7, 2002.
    Comments for inclusion in the Rules Docket must be received on or 
before February 19, 2002.

ADDRESSES: Submit comments in triplicate to the Federal Aviation 
Administration (FAA), New England Region, Office of the Regional 
Counsel, Attention: Rules Docket No. 2001-NE-28-AD, 12 New England 
Executive Park, Burlington, MA 01803-5299. Comments may be inspected at 
this location, by appointment, between 8 a.m. and 4:30 p.m., Monday 
through Friday, except Federal holidays. 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.

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: The FAA was recently notified of a report 
from a forging manufacturer of a metallurgical inclusion (contaminant) 
found by ultrasonic inspection in a certain forged part. This part was 
made from a certain ingot of titanium. The engine manufacturer also 
reports that CFE738 fan rotor disks were manufactured from this same 
ingot and are, therefore, suspected of containing these metallurgical 
inclusions. Metallurgical inclusions are known to be crack initiation 
sites in highly stressed engines parts. Cracks that have initiated from 
inclusions in disk material have caused uncontained disk failures. The 
FAA has therefore determined that these suspect fan rotor disks could 
fail as a result of having metallurgical inclusions. This condition, if 
not corrected, could result in uncontained engine failure and damage to 
the airplane.

Requirements of This AD

    Since an unsafe condition has been identified that is likely to 
exist or develop on other CFE Company model CFE738-1-1B turbofan 
engines of the same type design, this AD is being issued to remove from 
service affected fan rotor disks, which if not removed, could result in 
uncontained engine failure and damage to the airplane. This AD requires 
the removal from service of certain fan rotor disks, either before 
further flight or by an engine cycle schedule, based on fan rotor disk 
serial number.

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 action must submit a self-addressed, 
stamped postcard on which the following statement is made: ``Comments 
to Docket Number 2001-NE-28-AD.'' The postcard will be date stamped and 
returned to the commenter.

Regulatory Analysis

    This final rule does not have federalism implications, as defined 
in Executive Order 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 final 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, 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:

2001-26-06  CFE Company: Amendment 39-12570. Docket 2001-NE-28-AD.

    Applicability: This airworthiness directive (AD) is applicable 
to CFE Company model CFE738-1-1B turbofan engines that contain fan 
rotor disks part number (P/N) 3050745-2, serial numbers (SN's) 
000322903511 through 000322903536, and 000322903538 through 
000322903541. These engines are

[[Page 65834]]

installed on, but not limited to Dassault Aviation Falcon 2000 
series airplanes.

    Note 1: This 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 (g) 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 remove from service affected fan disks, which if not removed, 
could result in uncontained engine failure and damage to the 
airplane, do the following:
    (a) Remove from service before further flight, the following 
serial number (SN) fan rotor disks listed in Table 1:

Table 1. SN's of Fan Rotor Disks Requiring Removal Before Further Flight
------------------------------------------------------------------------
 
------------------------------------------------------------------------
   000322903512       000322903520       000322903528      000322903535
   000322903513       000322903521       000322903529      000322903536
   000322903516       000322903523       000322903530      000322903538
   000322903517       000322903524       000322903531      000322903539
   000322903518       000322903525       000322903533      000322903540
   000322903519       000322903527       000322903534      000322903541
------------------------------------------------------------------------

    (b) Remove from service within 10 engine cycles-in-service after 
the effective date of this AD, fan rotor disks SN's 000322903511, 
000322903515, and 000322903526.
    (c) Remove from service within 70 engine cycles-since-new (CSN), 
fan rotor disk SN 000322903514.
    (d) Remove from service within 140 engine CSN, fan rotor disks 
SN 000322903522 and 000322903532.
    (e) The manufacturer's records indicate that fan rotor disks 
identified in paragraphs (a) through (d) of this AD were installed 
in, and may still be installed in the engines listed by SN in the 
following Table 2. This AD, however, applies to any engine with the 
fan rotor disks installed, identified in paragraphs (a) through (d) 
of this AD. Table 2 is provided for informational purposes only to 
assist in locating engines that may be affected. For information on 
replacing the affected fan rotor disks in this AD, see CFE Company 
Alert Service Bulletin CFE738-A72-8053, dated July 24, 2001.

------------------------------------------------------------------------
 
------------------------------------------------------------------------
         105430             105446             105455            105467
         105432             105447             105456            105469
         105434             105448             105457            105471
         105438             105450             105459            105472
         105441             105451             105461            105474
         105443             105452             105462            105475
         105444             105453             105463
         105445             105454             105466
------------------------------------------------------------------------

    (f) After the effective date of this AD, do not install any fan 
rotor disks P/N 3050745-2, SN's 000322903511 through 000322903536, 
and 000322903538 through 000322903541 onto any engine.

Alternative Methods of Compliance

    (g) 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 must 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

    (h) 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 done.

Effective Date

    (i) This amendment becomes effective on January 7, 2002.


    Issued in Burlington, Massachusetts, on December 14, 2001.
Francis A. Favara,
Acting Manager, Engine and Propeller Directorate, Aircraft 
Certification Service.
[FR Doc. 01-31326 Filed 12-20-01; 8:45 am]
BILLING CODE 4910-13-P

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