[Federal Register Volume 66, Number 203 (Friday, October 19, 2001)]
[Proposed Rules]
[Pages 53131-53132]
From the Federal Register Online via the Government Publishing Office [www.gpo.gov]
[FR Doc No: 01-26325]


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DEPARTMENT OF TRANSPORTATION

Federal Aviation Administration

14 CFR Part 39

[Docket No. 2001-NE-20-AD]
RIN 2120-AA64


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

AGENCY: Federal Aviation Administration, DOT.

ACTION: Notice of proposed rulemaking (NPRM).

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

DATES: Comments must be received by December 18, 2001.

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-20-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, by 
appointment, between 8 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 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 FAA, New England 
Region, Office of the Regional Counsel, 12 New England Executive Park, 
Burlington, MA.

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:

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 2001-NE-20-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. 2001-NE-20-AD, 12 New England Executive 
Park, Burlington, MA 01803-5299.

Discussion

    The FAA has received three reports of uncontained failures of air 
turbine starters that resulted in cowl damage. A number of air turbine 
starters have been damaged by running without oil. Investigations of 
the incidents have shown that over torque of the magnetic drain plug, 
P/N 572-510-9004, can result in the failure of the plug, which can 
allow oil to drain from the starter housing. Failure of the plug may 
not be immediately evident when it is over torqued. Replacement of the 
existing magnetic drain plug, P/N 572-510-9004, with a new redesigned 
magnetic drain plug, P/N 572-8510-9152, would reduce the potential for 
oil loss from the turbine starter if the plug is inadvertently over 
torqued, and would prevent uncontained failure of the starter due to 
loss of oil and possible damage to the airplane.

Manufacturer's Service Information

    The FAA has reviewed and approved the technical contents of 
Honeywell Service Bulletin 3505582-80-1706, dated March 8, 2000, that 
describes procedures for replacing magnetic drain plugs, P/N 572-510-
9004 and packings, P/N S9413-555, with new redesigned drain plugs P/N 
572-8510-9152, and packings, P/N S3225-905; and re-

[[Page 53132]]

marking the air turbine engine starter with a new P/N.

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 CFMI CFM56-5 series turbofan engines of the 
same type design, with Honeywell Engines & Systems air turbine engine 
starters, P/N's 3505582-2, 3505582-3, 3505582-4, 3505582-12, 3505582-
14, 3505582-15, 3505582-22, and 3505582-23, installed, the proposed AD 
would require the following actions within 500 cycles-in-service after 
the effective date of the proposed AD:
     Replacement of magnetic drain plug, P/N 572-510-9004, with 
a new redesigned magnetic drain plug, P/N 572-8510-9152.
     Replacement of packing, P/N 39413-555, with packing, P/N 
S3225-905.
     Re-marking of the air turbine engine starter after 
replacement of the magnetic drain plug.

Cost Analysis

    The FAA estimates that about 512 engines installed on airplanes of 
U.S. registry would be affected by this proposed AD. The FAA also 
estimates that it would take approximately 0.1 work hours per engine to 
accomplish the proposed 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 impact of the proposed AD on 
U.S. operators is estimated to be $406,016.

Regulatory Analysis

    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.

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:

CFM International, S.A.: 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 752-8510-9152; replace the 
packing P/N S3225-905, with packing P/N 39413-555, 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.
    (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. 
Operators shall submit their request through an appropriate FAA 
Principal Maintenance Inspector, who may add comments and then send 
it to the Manager, Engine Certification Office.

    Note 2: Information concerning the existence of approved 
alternative methods of compliance with this airworthiness directive, 
if any, may be obtained from the Engine Certification Office.

Special Flight Permits

    (d) Special flight permits may be issued in accordance 
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 accomplished.


    Issued in Burlington, Massachusetts, on October 11, 2001.
Donald E. Plouffe,
Acting Manager, Engine and Propeller Directorate, Aircraft 
Certification Service.
[FR Doc. 01-26325 Filed 10-18-01; 8:45 am]
BILLING CODE 4910-13-U