Airworthiness Directives; CFM International, S.A. CFM56-5 Series Turbofan Engines

[Federal Register Volume 67, Number 31 (Thursday, February 14, 2002)]
[Rules and Regulations]
[Pages 6850-6852]
From the Federal Register Online via the Government Publishing Office [www.gpo.gov]
[FR Doc No: 02-3161]


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DEPARTMENT OF TRANSPORTATION

Federal Aviation Administration

14 CFR Part 39

[Docket No. 2001-NE-20-AD; Amendment 39-12461; AD 2002-02-13]
RIN 2120-AA64


Airworthiness Directives; CFM International, S.A. CFM56-5 Series 
Turbofan Engines

AGENCY: Federal Aviation Administration, DOT.

[[Page 6851]]


ACTION: Final rule.

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SUMMARY: This amendment adopts a new airworthiness directive (AD), that 
is applicable to CFM International, S.A. (CFMI) CFM56-5 series turbofan 
engines. This amendment requires replacement of the magnetic drain plug 
on certain part number (P/N) air turbine engine starters manufactured 
by Honeywell Engines & Systems. This amendment is prompted by three 
instances of uncontained air turbine engine starter failures, resulting 
in cowl damage. The actions specified by this AD are intended to 
prevent uncontained failure of the starter and possible damage to the 
airplane.

DATES: Effective date March 21, 2002. The incorporation by reference of 
certain publications listed in the regulations is approved by the 
Director of the Federal Register as of March 21, 2002.

ADDRESSES: The service information referenced in this AD may be 
obtained from Honeywell Engines & Systems, Technical Publications 
Department, 111 South 34th Street, Phoenix, Arizona 85034; telephone 
(602) 365-5535, fax (602) 365-5577. This information 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; or at the Office of the Federal 
Register, 800 North Capitol Street, NW., suite 700, Washington, DC.

FOR FURTHER INFORMATION CONTACT: James Rosa, Aerospace Engineer, Engine 
Certification Office, FAA, Engine and Propeller Directorate, 12 New 
England Executive Park, Burlington, MA 01803-5299; telephone (781) 238-
7152, fax (781) 238-7199.

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 CMFI CFM56-5 series turbofan engines was published in the 
Federal Register on October 19, 2001 (66 FR 53131). That action 
proposed to require replacement of the magnetic drain plug on certain 
P/N air turbine engine starters manufactured by Honeywell Engines & 
Systems, in accordance with Honeywell Service Bulletin 3505582-80-1706, 
dated March 8, 2000.

Comments

    Interested persons have been afforded an opportunity to participate 
in the making of this amendment. Due consideration has been given to 
the one comment received.
    The commenter states that the new drain plug P/N is incorrect, the 
replaced packing P/N is incorrect, and the new packing P/N is incorrect 
as called out in paragraph (a) of the NPRM.
    The FAA agrees. Paragraph (a) is now corrected to reflect new drain 
plug P/N 572-8510-9152, replaced packing P/N S9413-555, and new packing 
P/N S3225-905.
    After careful review of the available data, including the comment 
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

    The FAA estimates that about 512 engines installed on airplanes of 
U.S. registry would be affected by this AD. The FAA also estimates that 
it would take approximately 0.1 work hours per engine to accomplish the 
actions, and that the average labor rate is $60 per work hour. Required 
parts would cost approximately $787 per engine. Based on these figures, 
the total cost effect of this AD on U.S. operators is estimated to be 
$406,016. CFMI may provide parts at no cost, which would significantly 
reduce this figure.

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) 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 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, 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 a new airworthiness directive 
to read as follows:

2002-02-13  CFM International: Amendment 39-12461. Docket No. 2001-
NE-20-AD.

    Applicability: This airworthiness directive (AD) is applicable 
to CFM International, S.A. CFM56-5 series turbofan engines with 
Honeywell Engines & Systems air turbine engine starters, part 
numbers (P/N's) 3505582-2, 3505582-3, 3505582-4, 3505582-12, 
3505582-14, 3505582-15, 3505582-22, and 3505582-23 installed. These 
engines are installed on, but not limited to Airbus Industries A318, 
A319, A320, A321 and A340 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 (c) 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 within 500 
cycles-in-service after the effective date of this AD, unless 
already done.
    To prevent uncontained failure of the starter due to loss of oil 
and possible damage to the airplane, do the following:
    (a) Replace the magnetic drain plug, P/N 572-510-9004, with a 
new redesigned magnetic drain plug P/N 572-8510-9152; replace the 
packing P/N S9413-555, with packing P/N S3225-905, and remark the 
air turbine engine starter in accordance with paragraphs 2.A. 
through 2.C. of the Accomplishment Instructions of Honeywell Service 
Bulletin 3505582-80-1706, dated March 8, 2000.

[[Page 6852]]

    (b) Replenish the air turbine starter.

Alternative Methods of Compliance

    (c) 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 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

    (d) 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.

Documents That Have Been Incorporated by Reference

    (e) The inspection must be done in accordance with Honeywell 
Service Bulletin 3505582-80-1706, dated March 8, 2000. 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 Honeywell Engines & Systems, 
Technical Publications Department, 111 South 34th Street, Phoenix, 
Arizona 85034; telephone (602) 365-5535, fax (602) 365-5577. Copies 
may be inspected, by appointment, 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

    (f) This amendment becomes effective on March 21, 2002.

    Issued in Burlington, Massachusetts, on February 1, 2002.
Jay J. Pardee,
Manager, Engine and Propeller Directorate, Aircraft Certification 
Service.

[FR Doc. 02-3161 Filed 2-13-02; 8:45 am]
BILLING CODE 4910-13-U

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