[Federal Register Volume 67, Number 113 (Wednesday, June 12, 2002)]
[Rules and Regulations]
[Pages 40141-40143]
From the Federal Register Online via the Government Publishing Office [www.gpo.gov]
[FR Doc No: 02-14697]



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  Federal Register / Vol. 67, No. 113 / Wednesday, June 12, 2002 / 
Rules and Regulations  

[[Page 40141]]



DEPARTMENT OF TRANSPORTATION

Federal Aviation Administration

14 CFR Part 39

[Docket No. 99-NE-51-AD; Amendment 39-12780; AD 2002-12-08]
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: Final rule.

-----------------------------------------------------------------------

SUMMARY: This amendment adopts 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 amendment requires removal from service of certain gas producer 
turbine (GPT) components prior to reaching new, lower cyclic life 
limits using drawdown plans and replacing with serviceable parts. This 
amendment is prompted by continuous analysis of field-returned hardware 
indicating smaller service life margins than originally expected. The 
actions specified by this AD are intended to prevent GPT component 
failure, which could result in an uncontained engine failure and damage 
to the airplane.

DATES: Effective July 17, 2002.

ADDRESSES: Information regarding this action may be examined, by 
appointment, at the Federal Aviation Administration (FAA), New England 
Region, Office of the Regional Counsel, 12 New England Executive Park, 
Burlington, MA.

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: A proposal to amend part 39 of the Federal 
Aviation Regulations (14 CFR part 39) to include an AD that is 
applicable to Honeywell International, Inc. (formerly AlliedSignal 
Inc., and Textron Lycoming) ALF502 and LF507 series turbofan engines 
was published in the Federal Register on August 23, 2001 (66 FR 44316). 
That action proposed to require removal from service of certain GPT 
components prior to reaching new, lower cyclic life limits using 
drawdown plans, and replacing with serviceable parts.

Comments

    Interested persons have been afforded an opportunity to participate 
in the making of this amendment. No comments were received on the 
proposal or the FAA's determination of the cost to the public. However, 
since the proposal was published, the FAA has identified the need for a 
few corrections and clarifications.

Eliminate Redundant Part Numbers (P/N's)

    Because the title of Table 3 lists those turbine spacer P/N's 
affected, the spacer P/N's in item 2 of the table are redundant and 
have been deleted.

Engine Model Inadvertantly Listed

    Item 3 of Table 3, which is engine model ALF502R-3, has been 
identified as not having on its build list, spacer P/N 2-121-071-36. 
Therefore, this information has been deleted, and Table 3 has been 
renumbered accordingly.

Certain Spacer Installations Not Affected

    A note after Table 3 has been added, to clarify that this AD does 
not affect the life limit of spacers P/N's 2-121-071-37-42, installed 
in ALF502R-3 engines. The life limit remains at 11,600 cycles-since-
new.
    After careful review of the available data, including the changes 
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 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 AD, and that the 
prorated cost of the life reduction per engine would be approximately 
$7,980. Based on these figures, the total cost of the AD to U.S. 
operators is estimated to be $2,394,000.

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.
    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 the 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 it 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 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:


[[Page 40142]]


    Authority: 49 U.S.C. 106(g), 40113, 44701.


Sec. 39.13  [Amended]

    2. Section 39.13 is amended by adding a new airworthiness directive 
to read as follows:

2002-12-08 Honeywell International, Inc.: Amendment 39-12780. 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 plates 
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
        Part Numbers (P/N's) 2-121-075-15, -21, -27, -28, and -36
------------------------------------------------------------------------
                                Cycles-in-service
                                 since new (CSN)
         Engine model            on the effective         Replace
                                 date of this AD
------------------------------------------------------------------------
(1)ALF502R, LF507-1F, and       (i) Fewer than     Before accumulating
 LF507-1H series                 15,000 CSN         20,000 CSN.
                                (ii) 15,000 or     Within 5,000 cycles-
                                 more CSN           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 accumulating
                                 17,500 CSN         18,000 CSN.
                                (ii) 17,500 or     Within 500 CIS after
                                 more CSN           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.
------------------------------------------------------------------------

Drawdown Schedule for First Turbine Rotor Disc

    (b) Remove from service first turbine rotor discs 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's 2-121-051-18, -24, -25, -R35, -36, -37, -44, -R52, and -R55
------------------------------------------------------------------------
                                Cycles-in-service
                                 since new (CSN)
         Engine model            on the effective         Replace
                                 date of this AD
------------------------------------------------------------------------
(1) ALF502R, LF507-1F, and      (i) Fewer than     Before accumulating
 LF507-1H series                 15,000 CSN         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 accumulating
                                 13,500 CSN         14,000 CSN.
                                (ii) 13,500 or     Within 500 CIS after
                                 more CSN           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:

[[Page 40143]]



                                            Table 3.--Turbine Spacer
                                        P/N's 2-121-071-36, -37, and -42
----------------------------------------------------------------------------------------------------------------
                                                                Cycles-in-service
                                       First turbine rotor   since 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 15,000
 3, see information in Note 2),       -65, -R66, or -R67.     CSN                     CSN.
 LF507-1F, and LF507-1H series
                                                             (ii) 10,000 or more     Within 5,000 CIS after the
                                                              CSN                     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.................  P/N 2-121-090-41 or -                           Before accumulating 12,000
                                      42 or if rotor                                  CSN.
                                      assembly P/N cannot
                                      be determined.
(3) All ALF502L series.............  P/N 2-121-090-63, -64,  (i) Fewer than 13,500   Before accumulating 14,000
                                      -65, -R66, -R67, -91,   CSN                     CSN.
                                      -R92.
                                                             (ii) 13,500 or more     Within 500 CIS after the
                                                              CSN                     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.
(4) All ALF502L series.............  P/N 2-121-090-41, -42                           Before accumulating 10,800
                                      or if rotor assembly                            CSN.
                                      P/N cannot be
                                      determined.
----------------------------------------------------------------------------------------------------------------


    Note 2: For ALF502R-3 engines, turbine spacers P/N's 2-121-071-
37/-42 are not affected by this drawdown plan. Their life limit 
remains at 11,600 CSN.

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 paragraphs (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 3: 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 location where the 
requirements of this AD can be done.

Effective Date

    (h) This amendment becomes effective on July 17, 2002.

    Issued in Burlington, Massachusetts, on June 5, 2002.
Francis A. Favara,
Acting Manager, Engine and Propeller Directorate, Aircraft 
Certification Service.

[FR Doc. 02-14697 Filed 6-11-02; 8:45 am]
BILLING CODE 4910-13-P