# AGENCY:

 Federal Aviation Administration, DOT. 

# ACTION:

 Notice of proposed rulemaking (NPRM). 

# 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: “9-ane-adcomment@faa.gov”. 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

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                     Start Printed 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. 

§ 39.13 

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                                 Start Printed 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. 

# Footnotes

1.                                                 
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[FR Doc. 00-1641 Filed 1-21-00; 8:45 am] 

BILLING CODE 4910-13-U