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[Federal Register Volume 65, Number 15 (Monday, January 24, 2000)]
[Proposed Rules]
[Pages 3621-3623]
From the Federal Register Online via the Government Publishing Office [www.gpo.gov]
[FR Doc No: 00-1641]

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DEPARTMENT OF TRANSPORTATION

Federal Aviation Administration

14 CFR Part 39

[Docket No. 99-NE-40-AD]
RIN 2120-AA64

Airworthiness Directives; CFM International CFM56-2, -2A, -2B, -
3, -3B, -3C, -5, -5B, -5C Series Turbofan Engines

AGENCY:  Federal Aviation Administration, DOT.

ACTION:  Notice of proposed rulemaking (NPRM).

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SUMMARY:  This document proposes the adoption of a new airworthiness 
directive (AD) that is applicable to CFM International (CFMI) CFM56-2, 
-2A, -2B, -3, -3B, -3C, -5, -5B, -5C series turbofan engines. This 
proposal would require initial and repetitive visual inspections of the 
fuel pump filter cover helicoil inserts and bolts for damage, and, if 
necessary, repair or replacement with serviceable parts. This proposal 
also would require the installation of new fuel pumps that incorporate 
an improved filter cover retention design (D-bolts) as terminating 
action to the inspections. This proposal is prompted by reports that 
fuel pump filter cover helicoil inserts have loosened or pulled out. 
The actions specified by the proposed AD are intended to prevent fuel 
leakage from between the fuel pump filter cover and gear housing, which 
could result in an engine fire and damage to the airplane.

DATES:  Comments must be received by February 23, 2000.

ADDRESSES:  Submit comments to the Federal Aviation Administration 
(FAA), New England Region, Office of the Regional Counsel, Attention: 
Rules Docket No. 99-NE-40-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.
    The service information referenced in the proposed rule may be 
obtained from CFM International, Technical Publications Department, 1 
Neumann Way, Cincinnati, OH 45215; telephone (513) 552-2981, fax (513) 
552-2816. 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:  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 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 notice 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 notice must submit a self-addressed, 
stamped postcard on which the following statement is made: ``Comments 
to Docket Number 99-NE-40-AD.'' The postcard will be date stamped and 
returned to the commenter.

Availability of NPRMs

    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-40-AD, 12 New England Executive Park, 
Burlington, MA 01803-5299.

Discussion

    The Federal Aviation Administration (FAA) has received reports of 
fuel leakage from between the fuel pump filter cover and gear housing 
on CFM International (CFMI) CFM56-2, -2A, -2B, -3, -3B, -3C, -5, -5B, -
5C series turbofan engines.

Investigation

    The investigation revealed that fuel pump filter cover helicoil 
inserts have loosened or pulled out. The FAA has identified excessive 
torque during the installation of fuel filter cover bolts as the cause.

Improved Filter Cover

    The manufacturer has introduced an improved filter cover retention 
design using a captured D-bolt and special locking nut that reduces the 
potential for filter cover bolt over torque damage and loss of bolted 
joint strength.

Unsafe Condition

    This condition, if not corrected, could result in fuel leakage from 
between the fuel pump filter cover and gear housing, which could result 
in an engine fire and damage to the airplane.

Service Information

    The FAA has reviewed and approved the technical contents of the 
following CFMI Service Bulletins (SBs), that describe procedures for 
visual inspections of inserts and bolts for damage, and provide 
criteria for rejection of hardware and necessary replacement with 
serviceable parts: CFM56-2 SB 73-110, Revision 2, dated April 29, 1999; 
CFM56
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    \1\ -2A SB 73-055, Revision 1, dated April 29, 1999; CFM56-2B SB 
73-076, Revision 1, dated April 29, 1999; CFM56-3/3B/3C SB 73-126, 
Revision 1, dated April 29, 1999; CFM56-5 SB 73-136, Revision 2, 
dated April 29, 1999; CFM56-5B SB 73-056, Revision 2, dated April 
29, 1999; CFM56-5C SB 73-073, Revision 2, dated April 29, 1999.
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    The FAA has also reviewed and approved the technical contents of 
the following CFMI SBs, that describe procedures for removal and 
replacement of fuel pumps (D-bolt fix): CFM56-2 SB 73--A113, dated 
August 17, 1999; CFM56-2A SB 73-A058, dated August 17, 1999; CFM56-2B 
SB 73-A079, dated August 17, 1999; CFM56-3/3B/3C SB 73-A129, dated 
August 17, 1999; CFM56-5 SB 73-A143, dated June 18, 1999; CFM56-5B SB 
73-A062, dated June 18, 1999; CFM56-5C SB 73-A078, dated June 21, 1999.

Differences Between Service Bulletins and This AD

    The referenced SBs describe a one-time inspection. This AD requires 
repetitive inspections at every filter change.

Proposed Inspections and Repair or Replacement

    Since an unsafe condition has been identified that is likely to 
exist or

[[Page 3622]]

develop on other products of this same type design, the proposed AD 
would require initial and repetitive visual inspections of helicoil 
inserts and bolts for damage defined in the applicable SBs. The 
inspections would be required at each fuel filter replacement. If the 
damage equals or exceeds the reject criteria, this AD would require, 
prior to further flight, removing the damaged hardware from service and 
replacement with serviceable parts, or repairing the damaged hardware.

Terminating Action

    This AD would also require the installation of new fuel pumps that 
incorporate an improved filter cover retention design (D-bolts) as a 
terminating action to the inspections. The actions would be required to 
be accomplished in accordance with the SBs described previously.

Economic Analysis

    There are approximately 8,781 engines of the affected design in the 
worldwide fleet. The FAA estimates that 4,063 engines installed on 
aircraft of U.S. registry would be affected by this proposed AD, that 
it would take approximately 0.3 work hours per engine to accomplish the 
proposed inspections and 3 work hours per engine to accomplish the 
proposed D-bolt installation, and that the average labor rate is $60 
per work hour. The FAA therefore estimates the total cost to US 
operators of this proposed rule is $73,134 for one inspection and 
$4,958,658 for hardware/D-bolt installation.

Regulatory Impact

    This proposal does not have federalism implications, as defined in 
Executive Order No. 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:

CFM International: Docket No. 99-NE-40-AD.

    Applicability: CFM International (CFMI) CFM56-2, -2A, -2B, -3, -
3B, -3C, -5, -5B, -5C series turbofan engines, installed on but not 
limited to McDonnell Douglas DC-8 series, Boeing 737 series, Airbus 
Industrie A319, A320, A321, and A340 series, and Boeing E-3, E-6, 
and KC-135 (military) series airplanes.

    Note 1:  This airworthiness directive (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 (d) 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: Required as indicated, unless accomplished 
previously.
    To prevent fuel leakage from between the fuel pump filter cover 
and gear housing, which could result in an engine fire and damage to 
the airplane, accomplish the following:

Inspections

    (a) Perform initial and repetitive visual inspections of fuel 
pump filter cover helicoil inserts and bolts for damage, as follows:
    (1) Initially inspect at the next fuel filter replacement, but 
not to exceed 200 cycles-in-service (CIS) after either the effective 
date of this AD or the last inspection, whichever occurs first, in 
accordance with section 2., Accomplishment Instructions, of the 
applicable CFMI Service Bulletins (SBs) listed in paragraph (a)(4) 
of this AD.
    (2) Thereafter, inspect at each fuel filter replacement in 
accordance with section 2., Accomplishment Instructions, of the 
applicable CFMI SBs listed in paragraph (a)(4) of this AD.

Replacement or Repair

    (3) If damage equals or exceeds the reject criteria stated in 
section 2., Accomplishment Instructions, of the SBs listed in 
paragraph (a)(4) of this AD, prior to further flight remove the fuel 
pump from service and replace with serviceable part, or repair the 
helicoil, in accordance with section 2., Accomplishment 
Instructions, of the SBs listed in paragraphs (a)(4) or (b), as 
applicable, of this AD.

Applicable Inspection SBs

    (4) Inspect, and replace, if necessary, in accordance with the 
following CFMI SBs, as applicable:
     CFM56-2 SB 73-110, Revision 2, dated April 29, 1999.
     CFM56-2A SB 73-055, Revision 1, dated April 29, 1999.
     CFM56-2B SB 73-076, Revision 1, dated April 29, 1999.
     CFM56-3/3B/3C SB 73-126, Revision 1, dated April 29, 
1999.
     CFM56-5 SB 73-136, Revision 2, dated April 29, 1999.
     CFM56-5B SB 73-056, Revision 2, dated April 29, 1999.
     CFM56-5C SB 73-073, Revision 2, dated April 29, 1999.

Terminating Action

    (b) Remove and replace the fuel pump at the next engine, 
gearbox, or fuel pump shop visit, but not later than 5 years from 
the effective date of this AD, in accordance with section 2., 
Accomplishment Instructions, of the following CFMI SBs, as 
applicable:
     CFM56-2 SB 73-A113, dated August 17, 1999.
     CFM56-2A SB 73-A058, dated August 17, 1999.
     CFM56-2B SB 73-A079, dated August 17, 1999.
     CFM56-3/3B/3C SB 73-A129, dated August 17, 1999.
     CFM56-5 SB 73-A143, dated June 18, 1999.
     CFM56-5B SB 73-A062, dated June 18, 1999.
     CFM56-5C SB 73-A078, dated June 21, 1999.

    Installation of a new fuel pump with a new filter cover 
attachment in accordance with this paragraph constitutes terminating 
action to the inspections required by paragraph (a) of this AD.

Definitions

    (c) For the purpose of this AD, a serviceable part is defined as 
a part with gear housing helicoil inserts that meet the inspection 
requirements of the applicable CFMI SBs listed in paragraph (a)(4) 
of this AD. A serviceable part is also defined as a part that has 
been modified in accordance

[[Page 3623]]

with the applicable CFMI SB listed in paragraph (b) of this AD.

Alternate Methods of Compliance

    (d) 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.

Ferry Flights

    (e) 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 January 14, 2000.
David A. Downey,
Assistant Manager, Engine and Propeller Directorate, Aircraft 
Certification Service.
[FR Doc. 00-1641 Filed 1-21-00; 8:45 am]
BILLING CODE 4910-13-U
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