[Federal Register Volume 66, Number 109 (Wednesday, June 6, 2001)]
[Proposed Rules]
[Pages 30341-30343]
From the Federal Register Online via the Government Publishing Office [www.gpo.gov]
[FR Doc No: 01-14146]


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DEPARTMENT OF TRANSPORTATION

Federal Aviation Administration

14 CFR Part 39

[Docket No. 99-NE-39-AD]


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

AGENCY: Federal Aviation Administration, DOT.

ACTION: Notice of proposed rulemaking (NPRM).

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[[Page 30342]]



SUMMARY: The Federal Aviation Administration (FAA) proposes to revise 
an existing airworthiness directive (AD), applicable to CFE Company 
Model CFE738-1-1B turbofan engines. That AD currently requires a one-
time visual inspection of Stage 2 high pressure turbine (HPT) aft 
cooling plates for nicks, dents, raised metal, and scratches, and if 
necessary, repair of the cooling plates or replacement with serviceable 
parts. This proposal is prompted by an updated alert service bulletin 
(ASB) that reduces the number of stage 2 HPT aft cooling plates 
affected by this AD and identifies the applicable engines by engine 
serial numbers (SN's). In the event that the affected gas generator 
modules containing the affected parts have been transferred to another 
engine, the SN's of those gas generator modules have been added to this 
AD. The actions specified by the proposed AD are intended to prevent 
stage 2 HPT aft cooling plate failure, which could result in an 
uncontained engine failure and damage to the airplane.

DATES: Comments must be received by August 6, 2001.

ADDRESSES: Submit comments in triplicate to the Federal Aviation 
Administration (FAA), New England Region, Office of the Regional 
Counsel, Attention: Rules Docket No. 99-NE-39-AD, 12 New England 
Executive Park, Burlington, MA 01803-5299. Comments may also be sent 
via the Internet using the following address: ``<a href="/cdn-cgi/l/email-protection#2f16024e414a024e4b4c4042424a415b6f494e4e01484059"><span class="__cf_email__" data-cfemail="d7eefab6b9b2fab6b3b4b8babab2b9a397b1b6b6f9b0b8a1">[email protected]</span></a>.'' Comments sent via the Internet must contain the 
docket number in the subject line. Comments may be inspected at this 
location between 8:00 a.m. and 4:30 p.m., Monday through Friday, except 
Federal holidays.
    The service information referenced in the proposed rule may be 
obtained from CFE Company, Data Distribution, MS 64-03/2101-201, P.O. 
Box 29003, Phoenix, AZ 85038-9003; 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.

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:

Comments Invited

    Interested persons are invited to participate in the making of the 
proposed 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 above. All 
communications received on or before the closing date for comments, 
specified above, will be considered before taking action on the 
proposed rule. The proposals contained in this action may be changed in 
light of the comments received.
    Comments are specifically invited on the overall regulatory, 
economic, environmental, and energy aspects of the proposed 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 summarizing each FAA-public contact concerned with 
the substance of this proposal 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 99-NE-39-AD.'' The postcard will be date stamped and 
returned to the commenter.

Availability of NPRM's

    Any person may obtain a copy of this NPRM by submitting a request 
to the FAA, New England Region, Office of the Regional Counsel, 
Attention: Rules Docket No. 99-NE-39-AD, 12 New England Executive Park, 
Burlington, MA 01803-5299.

Discussion

    On December 29, 1999, the FAA issued AD 99-27-16, Amendment 39-
11497 (65 FR 691, January 6, 2000), to require a one-time visual 
inspection of 72 Stage 2 HPT aft cooling plates for nicks, dents, 
raised metal, and scratches. If any nicks, dents, raised metal, or 
scratches were found, that AD also required repair of the cooling 
plates or replacement with serviceable parts. That action was prompted 
by reports of Stage 2 HPT aft cooling plates that were dented during 
the assembly of the cooling plate to the Stage 2 disk due to raised 
metal on the stage 2 HPT disk post aft mating surface. The raised metal 
condition on the stage 2 HPT disk post was caused by an improperly 
installed locating pin in the assembly tool. That condition, if not 
corrected, could result in HPT aft cooling plate failure, which could 
result in an uncontained engine failure and damage to the airplane. 
Since AD 99-27-16 was issued, CFE Company has isolated the observed 
assembly damage to a known replacement of the locating pin in the 
assembly tooling. It has been determined that only ten of the original 
72 HPT cooling plate/stage 2 disk assemblies were assembled before tool 
correction occurred. Records show these ten HPT cooling plate/stage 2 
disk assemblies were subsequently assembled in ten gas generator 
modules, S/N's 800421-800430. These gas generator modules, along with 
the engines on which these modules were installed, are listed in this 
AD.

Manufacturer's Service Information

    The FAA has reviewed and approved the technical contents of CFE 
Company Alert Service Bulletin (ASB) CFE738-A72-8031, Revision 2, dated 
October 17, 2000, that describes the dimensional inspection procedures 
for indentation depth on stage 2 HPT aft cooling plates, inspection of 
the stage 2 HPT rotor disk for raised metal, and the acceptance and 
repair criteria of the stage 2 HPT aft cooling plate and HPT rotor 
disk.

Differences Between This AD and the Manufacturer's Service 
Information

    Although ASB CFE738-A72-8031, Revision 2, dated October 17, 2000, 
identifies ten engines by SN, the FAA is also listing the ten gas 
generator module SN's in which the affected HPT cooling plate/stage 2 
HPT disk assemblies are installed. This listing is made to assure that 
the gas generator modules containing the affected parts are identified 
and inspected regardless of which engine they are installed on. Gas 
generator modules may not necessarily stay installed in one and only 
one engine.

FAA's Determination of an Unsafe Condition and Proposed Actions

    Since an unsafe condition has been identified that is likely to 
exist or develop on other products of this same type design, the 
proposed AD would require, on gas generator modules identified by SN, a 
one-time visual inspection of stage 2 HPT aft cooling plates for nicks, 
dents, raised metal, and scratches, and if present, replacement with 
serviceable parts, or, dimensional inspection of indentation depth, 
repair if indentation is within acceptable limits, and if not, 
replacement with serviceable parts. This AD would also require 
inspection of the stage 2 HPT rotor disk post aft surface which mates 
with the stage 2 HPT aft cooling plate, for raised metal, and, removal 
of the raised metal, if present, or replacement with a serviceable 
part. The inspections would be required at the next shop visit

[[Page 30343]]

after the effective date of this AD where the HPT assembly is 
sufficiently disassembled to afford access to the stage 2 HPT aft 
cooling plate, but not later than 4,500 part cycles-since-new (CSN) in 
accordance with the ASB described previously.

Economic Impact

    There are approximately ten engines of the affected design in the 
worldwide fleet. The FAA estimates that nine engines installed on 
airplanes of US registry would be affected by this proposed AD, that it 
would take approximately four work hours per engine to accomplish the 
proposed inspection if the inspection did not take place during 
scheduled maintenance, and that the average labor rate is $60 per work 
hour. Required parts would cost approximately $1,536 per engine. Based 
on these figures, the total cost impact of the proposed AD on US 
operators is estimated to be $15,484.

Regulatory Impact

    This proposed 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 proposed rule.
    For the reasons discussed above, I certify that this proposed 
regulation (1) is not a ``significant regulatory action'' under 
Executive Order 12866; (2) is not a ``significant rule'' under the DOT 
Regulatory Policies and Procedures (44 FR 11034, February 26, 1979); 
and (3) if promulgated, 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 copy of the draft 
regulatory evaluation prepared for this action is contained in the 
Rules Docket. A copy of it may be obtained by contacting 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 proposes to amend 
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 removing Amendment 39-11497 (65 FR 
691, January 6, 2000), and by adding a new airworthiness directive, to 
read as follows:

CFE Company: Docket No. 99-NE-39-AD.

Revises AD 99-27-16, Amendment 39-11497.

Applicability

    This airworthiness directive (AD) is applicable to CFE Model 
CFE738-1-1B turbofan engines, part number (P/N) 3050000-5, with gas 
generator modules P/N 6091T09G01, serial numbers (SN's) 800421, 
800422, 800423, 800424, 800425, 800426, 800427, 800428, 800429, and 
800430 installed. These modules are currently installed in engine 
SN's 105323, 105324, 105325, 105326, 105328, 105329, 105331, 105332, 
105333, and 105392. These engines are installed on, but not limited 
to Dassault-Breguet 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 (b) 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 stage 2 high pressure turbine (HPT) aft cooling plate 
failure, which could result in an uncontained engine failure and 
damage to the airplane, accomplish the following:

Inspections and Follow-On Actions

    (a) At the next engine shop visit after the effective date of 
this AD where the HPT assembly is sufficiently disassembled to 
afford access to the Stage 2 HPT aft cooling plate, but not later 
than 4,500 part cycles-since-new (CSN), accomplish the following:
    (1) Inspect the stage 2 HPT aft cooling plate for nicks, dents, 
and scratches on surface D in accordance with the requirements of 
CFE Alert Service Bulletin (ASB) No. CFE738-A72-8031, Revision 2, 
dated October 17, 2000, paragraph 2.B.(1).
    (2) Repair those stage 2 HPT aft cooling plates with indentation 
0.003 inch deep or less in accordance with ASB No. CFE738-A72-8031, 
Revision 2, dated October 17, 2000, paragraph 2.B.(1).
    (3) Remove from service prior to further flight those stage 2 
HPT aft cooling plates that have nicks, dents, and/or scratches that 
exceed the acceptance limits in accordance with ASB No. CFE738-A72-
8031, Revision 2, dated October 17, 2000, paragraph 2.B.(1), and 
replace with serviceable parts.
    (4) Inspect the stage 2 HPT rotor disk post aft mating surface 
for raised metal, and remove raised metal if present in accordance 
with ASB No. CFE738-A72-8031, Revision 2, dated October 17, 2000, 
paragraph 2.B.(2).

Alternative Methods of Compliance

    (b) 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 request 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

    (c) 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 inspection requirements of this AD can be accomplished.

    Issued in Burlington, Massachusetts, on May 25, 2001.
Jay J. Pardee,
Manager, Engine and Propeller Directorate, Aircraft Certification 
Service.
[FR Doc. 01-14146 Filed 6-5-01; 8:45 am]
BILLING CODE 4910-13-U


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