[Federal Register Volume 66, Number 164 (Thursday, August 23, 2001)]
[Proposed Rules]
[Pages 44316-44319]
From the Federal Register Online via the Government Publishing Office [www.gpo.gov]
[FR Doc No: 01-21222]


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DEPARTMENT OF TRANSPORTATION

Federal Aviation Administration

14 CFR Part 39

[Docket No. 99-NE-51-AD]
RIN 2120-AA64


Airworthiness Directives; Honeywell International, Inc. (formerly 
AlliedSignal Inc., and Textron Lycoming) ALF502 and LF507 Series 
Turbofan Engines

AGENCY: Federal Aviation Administration, DOT.

ACTION: Notice of proposed rulemaking (NPRM).

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SUMMARY: This document proposes to adopt a new airworthiness directive 
(AD) that is applicable to Honeywell International, Inc. (formerly 
AlliedSignal Inc. and Textron Lycoming) ALF502 and LF507 series 
turbofan engines. This proposal would require removing from service 
certain gas producer turbine (GPT) components prior to reaching new, 
lower cyclic life limits using drawdown plans, and replacing with 
serviceable parts. This proposal is prompted by continuous analysis of 
field-returned hardware indicating smaller service life margins than 
originally expected. The actions specified by the proposed AD are 
intended to prevent GPT component failure, which could result in an 
uncontained engine failure and damage to the airplane.

DATES: Comments must be received by October 22, 2001.

ADDRESSES: Submit comments to the Federal Aviation Administration 
(FAA), New England Region, Office of the Regional Counsel, Attention: 
Rules Docket No. 99-NE-51-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. 
Comments may be inspected at this location between 8:00 a.m. and 4:30 
p.m., Monday through Friday, except Federal holidays.

FOR FURTHER INFORMATION CONTACT: Robert Baitoo, Aerospace Engineer, Los 
Angeles Aircraft Certification Office, FAA, Transport Airplane 
Directorate, 3960 Paramount Blvd., Lakewood, CA 90712; telephone (562) 
627-5245; fax (562) 627-5210.

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 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-51-AD.'' The postcard will be date stamped and 
returned to the commenter.

[[Page 44317]]

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-51-AD, 12 New England Executive Park, 
Burlington, MA 01803-5299.

Discussion

    Honeywell International, Inc. (formerly AlliedSignal Inc.), the 
manufacturer of LF507 series turbofan engines and current type 
certificate holder of ALF502 series turbofan engines, has advised the 
FAA that continuous analysis of field-returned hardware indicates 
smaller service life margins than originally intended for certain first 
turbine rotor sealing plates, first turbine rotor discs, and turbine 
spacers. This analysis is supported by component tests. To date there 
has been no in-service failure of these components. This condition, if 
not corrected, could result in GPT component failure, which could 
result in an uncontained engine failure and damage to the airplane.

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 removing from service the first turbine rotor 
sealing plate, first turbine rotor disc, and turbine spacer prior to 
reaching new, lower cyclic life limits using drawdown plans, and 
replacing with serviceable parts. The actions would be required to be 
accomplished in accordance with the SB described previously.

Economic Analysis

    There are approximately 1,600 engines of the affected design in the 
worldwide fleet. The FAA estimates that 300 engines installed on 
airplanes of U.S. registry would be affected by this proposed AD, and 
that the prorated cost of the life reduction per engine would be 
approximately $7,980. Based on these figures, the total cost impact of 
the proposed AD on U.S. operators is estimated to be $2,394,000.

Regulatory Impact

    This proposal 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 proposal.
    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.

The Proposed 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 adding the following new 
airworthiness directive:

Honeywell International, Inc. (formerly AlliedSignal Inc., and 
Textron Lycoming): Docket No. 99-NE-51-AD.

    Applicability: This airworthiness directive (AD) is applicable 
to Honeywell International, Inc. (formerly AlliedSignal Inc. and 
Textron Lycoming) ALF502 and LF507 series turbofan engines, with 
certain first turbine rotor sealing plates, first turbine rotor 
discs, and turbine spacers installed. These engines are installed 
on, but not limited to, Bombardier (Canadair) CL600-1A11, and 
British Aerospace BAe 146 series and AVRO 146-RJ 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 (f) 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 gas producer turbine (GPT) component failure, which 
could result in an uncontained engine failure and damage to the 
airplane, do the following:

Drawdown Schedule for First Turbine Rotor Sealing Plate

    (a) Remove from service first turbine rotor sealing plate 
according to the drawdown plan described in the following Table 1 of 
this AD, and replace with serviceable parts:

Table 1.--First Turbine Rotor Sealing Plate P/N 2-121-075-15, -21, -27,
                               28, and -36
------------------------------------------------------------------------
                                   Cycles-in-service
                                  since new (CSN) on
          Engine model            the effective date        Replace
                                      of this AD
------------------------------------------------------------------------
(1) ALF502R, LF507-1F, and LF507- (i) Fewer than      Before
 1H series.                        15,000 CSN.         accumulating
                                                       20,000 CSN.
                                  (ii) 15,000 or      Within 5,000
                                   more CSN.           cycles-in-service
                                                       (CIS) after the
                                                       effective date of
                                                       this AD or at the
                                                       next access after
                                                       the effective
                                                       date of this AD,
                                                       whichever is
                                                       earlier, but do
                                                       not exceed 25,000
                                                       CSN.
(2) All ALF502L series..........  (i) Fewer than      Before
                                   17,500 CSN.         accumulating
                                                       18,000 CSN.
                                  (ii) 17,500 or      Within 500 CIS
                                   more CSN.           after the
                                                       effective date of
                                                       this AD or at the
                                                       next access after
                                                       the effective
                                                       date of this AD,
                                                       whichever is
                                                       earlier, but do
                                                       not exceed 23,000
                                                       CSN.
------------------------------------------------------------------------


[[Page 44318]]

Drawdown Schedule for First Turbine Rotor Disc

    (b) Remove from service first turbine rotor disc according to 
the drawdown plan described in the following Table 2 of this AD, and 
replace with serviceable parts:

 Table 2.--First Turbine Rotor Disc P/N 2-121-051-18, -24, -25, -R35, -
                      36, -37, -44, -R52, and -R55
------------------------------------------------------------------------
                                   Cycles-in-service
                                  since new (CSN) on
          Engine model            the effective date        Replace
                                      of this AD
------------------------------------------------------------------------
(1) ALF502R, LF507-1F, and LF507- (i) Fewer than      Before
 1H series.                        15,000 CSN.         accumulating
                                                       20,000 CSN.
                                  (ii) 15,000 or      Within 5,000 CIS
                                   more CSN.           after the
                                                       effective date of
                                                       this AD or at the
                                                       next access after
                                                       the effective
                                                       date of this AD,
                                                       whichever is
                                                       earlier, but do
                                                       not exceed 25,000
                                                       CSN.
(2) All ALF502L series..........  (i) Fewer than      Before
                                   13,500 CSN.         accumulating
                                                       14,000 CSN.
                                  (ii) 13,500 or      Within 500 CIS
                                   more CSN.           after the
                                                       effective date of
                                                       this AD or at the
                                                       next access after
                                                       the effective
                                                       date of this AD,
                                                       whichever is
                                                       earlier, but do
                                                       not exceed 21,000
                                                       CSN.
------------------------------------------------------------------------

Drawdown Schedule for Turbine Spacer

    (c) Remove from service turbine spacers according to the 
drawdown plan described in the following Table 3 of this AD, and 
replace with serviceable parts:

                             Table 3.--Turbine Spacer P/N 2-121-071-36, -37, and -42
----------------------------------------------------------------------------------------------------------------
                                                                Cycles-in-service since
                                         First turbine rotor        new (CSN) on the
             Engine model                    assembly P/N        effective date of this          Replace
                                                                           AD
----------------------------------------------------------------------------------------------------------------
(1) ALF502R series, (except ALF502R-   P/N 2-121-090-63, -64, - (i) Fewer than 10,000    Before accumulating
 3) LF507-1F, and LF507-1H series.      65, -R66, or -R67.       CSN.                     15,000 CSN.
                                                                (ii) 10,000 or more CSN  Within 5,000 CIS after
                                                                                          the effective date of
                                                                                          this AD or at the next
                                                                                          access after the
                                                                                          effective date of this
                                                                                          AD, whichever is
                                                                                          earlier, but do not
                                                                                          exceed 20,000 CSN.
(2) ALF502R series with turbine        P/N 2-121-090-41 or -42  .......................  Before accumulating
 spacer P/N 2-121-071-36, -37           or if rotor assembly P/                           12,000 CSN.
 installed.                             N cannot be determined.
(3) ALF502R-3 with turbine spacer P/N  P/N 2-121-090-63, -64, - (i) Fewer than 10,000    Before accumulating
 2-121-071-36 installed.                65, -R66, or -R67.       CSN.                     15,000 CSN.
                                                                (ii) 10,000 or more CSN  Within 5,000 CIS after
                                                                                          the effective date of
                                                                                          this AD or at the next
                                                                                          access after the
                                                                                          effective date of this
                                                                                          AD, whichever is
                                                                                          earlier, but do not
                                                                                          exceed 20,000 CSN.
(4) All ALF502L series...............  P/N 2-121-090-63, -64, - (i) Fewer than 13,500    Before accumulating
                                        65, -R66, -R67, -91, -   CSN.                     14,000 CSN.
                                        R92.
                                                                (ii) 13,500 or more CSN  Within 500 CIS after
                                                                                          the effective date of
                                                                                          this AD or at the next
                                                                                          access after the
                                                                                          effective date of this
                                                                                          AD, whichever is
                                                                                          earlier, but do not
                                                                                          exceed 19,500 CSN.
(5) All ALF502L series...............  P/N 2-121-090-41, -42    .......................  Before accumulating
                                        or if rotor assembly P/                           10,800 CSN.
                                        N cannot be determined.
----------------------------------------------------------------------------------------------------------------

Reduced Life Limits

    (d) Except for the drawdown provisions of paragraphs (a), (b), 
and (c) of this AD and the approvals granted under the provisions of 
paragraph (f) of this AD, no first turbine rotor sealing plates, 
first turbine rotor discs, or turbine spacers may remain in service 
beyond the cyclic life limits provided in paragraph (a), (b), or (c) 
of this AD.

Definitions

    (e) For the purposes of this AD, access is defined as when the 
engine has been disassembled to where the affected part may be 
removed.

Alternative Methods of Compliance

    (f) 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 must 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

    (g) 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 airplane to a

[[Page 44319]]

location where the requirements of this AD can be accomplished.

    Issued in Burlington, Massachusetts, on August 16, 2001.
Jay J. Pardee,
Manager, Engine and Propeller Directorate, Aircraft Certification 
Service.
[FR Doc. 01-21222 Filed 8-22-01; 8:45 am]
BILLING CODE 4910-13-P