AD 2000-15-01

[Federal Register Volume 65, Number 149 (Wednesday, August 2, 2000)]
[Rules and Regulations]
[Pages 47248-47252]
From the Federal Register Online via the Government Publishing Office [<a href="http://www.gpo.gov">www.gpo.gov</a>]
[FR Doc No: 00-18523]


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DEPARTMENT OF TRANSPORTATION

Federal Aviation Administration

14 CFR Part 39

[Docket No. 99-NE-40-AD; Amendment 39-11830; AD 2000-15-01]
RIN 2120-AA64


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

AGENCY: Federal Aviation Administration, DOT.

ACTION: Final rule.

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SUMMARY: This amendment adopts a new airworthiness directive (AD), 
applicable to CFM International (CFMI) CFM56-2, -2A, -2B, -3, -3B, -3C, 
-5, -5A, -5B, -5C series turbofan engines, that requires 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 amendment also requires the installation 
of new or reworked fuel pumps that incorporate an improved filter cover 
retention design (D-bolts), or an on-wing repair of existing fuel 
pumps, as terminating action to the inspections. This amendment is 
prompted by reports that fuel pump filter cover helicoil inserts have 
loosened or pulled out. The actions specified by this 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: Effective date October 2, 2000. The incorporation by reference 
of certain publications listed in the rule is approved by the Director 
of the Federal Register as of October 2, 2000.

ADDRESSES: The service information referenced in this AD may be 
obtained from CFM International, Technical Publications Department, 1 
Neumann Way, Cincinnati, OH 45215; telephone: (513) 552-2800, fax: 
(513) 552-2816. This information may be examined 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.

[[Page 47249]]


SUPPLEMENTARY INFORMATION: A proposal to amend part 39 of the Federal 
Aviation Regulations (14 CFR part 39) to include an airworthiness 
directive (AD) that is applicable to CFM International (CFMI) CFM56-2, 
-2A, -2B, -3, -3B, -3C, -5, -5A, -5B, -5C series turbofan engines was 
published in the Federal Register on January 24, 2000 (65 FR 3621). 
That action proposed to 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. That action also proposed to require the installation of new 
fuel pumps that incorporate an improved filter cover retention design 
(D-bolts) as terminating action to the inspections.

Comments Received

    Interested persons have been afforded an opportunity to participate 
in the making of this amendment. Due consideration has been given to 
the comments received.

On-Wing Gearbox Replacement

    One comment requests that the requirement for on-wing gearbox 
replacements be removed from the terminating action since the fuel pump 
is routinely reinstalled and does not receive a shop visit. The comment 
also suggests that the fuel pump modification should be required at 
fuel pump shop visit only.
    The FAA agrees in part. The FAA agrees that it is not necessary to 
replace the fuel pump at on-wing gearbox replacement. However, the FAA 
does not agree that modification of the fuel pump should only be 
accomplished at fuel pump shop visit. The FAA believes fuel pump 
modifications should be accomplished at engine shop visit. The 
terminating action at on-wing gearbox replacement will be removed and 
the final rule revised accordingly. For clarity, the following 
definitions will also be added: A fuel pump shop visit is defined as 
introduction of an engine into a shop for the purpose of removal of the 
fuel pump from the gearbox. An engine shop visit is defined as 
introduction of an engine into a shop for the purpose of maintenance or 
inspection.

Credit for Previous Inspections

    Eight comments request that credit be given to operators who have 
performed initial inspections per the applicable service bulletins 
(SBs) or aircraft maintenance manuals. One comment requests a wording 
change so that operators will not have to repeat the initial 
inspection.
    The FAA agrees. This final rule has been revised accordingly.

Terminating Action

    One comment expresses concern that the fuel pump manufacturer and 
repair vendor will not be able to support the five-year compliance 
schedule. Another comment requests an extension of the terminating 
action date. Two comments request elimination of a five-year 
terminating-action requirement because there will be insufficent time 
to remove the fuel pumps on an attrition basis, and this requirement 
will disrupt planned component removal schedules.
    The FAA does not agree. The engine manufacturer has informed the 
FAA that the fuel pump vendor should be able to support this five-year 
compliance schedule. The FAA has revised the final rule in response to 
another comment to allow an on-wing repair as a terminating action, 
which should help to minimize disruption in current maintenance 
schedules.
    One comment requests that terminating action be mandated at the 
next shop visit or 6,000 hours because five years is too long.
    The FAA agrees in part. Terminating action will be required at the 
next shop visit, however the FAA has determined that the terminating 
action date in this AD provides an adequate level of safety and allows 
operators time to properly schedule the required activity.

On-Wing Repair

    Four comments request that an on-wing repair referenced in the 
inspection SBs be allowed as terminating action.
    The FAA agrees. The FAA will revise the final rule to allow the on-
wing repair as terminating action.

Military Operators

    One comment requests that military CFM56-2B operators not be 
required to perform periodic inspections since they already inspect 
fuel filters every 60 hours.
    The FAA does not agree. The FAA has a responsibility to manage the 
CFM56-2B type certificate. Military operators have the option to 
determine if incorporation of this part 39 amendment is appropriate for 
them.

Undue Burden

    One comment requests that the requirement to reinspect the fuel 
filter cover assembly after every fuel filter change be removed since 
the inspection is already performed in accordance with the B737-300/-
500 Aircraft Maintenance Manual, which is part of their FAA approved 
maintenance program. The comment also suggests that the documentation 
will create an undue burden.
    The FAA does not agree. The FAA has determined that although 
performing the inspections in accordance with the B737-300/-500 
Aircraft Maintenance Manual, may be prudent, it is not a requirement. 
This AD will mandate the inspection for all operators. The FAA does not 
consider the required documentation to be an undue burden.

Initial Inspection Interval

    Two comments request that the initial inspection be changed from 
200 to 300 cycles or 600 hours. Another comment states that preflight 
walk-around inspections will spot fuel leaks.
    The FAA does not agree. The FAA has determined that the initial 
inspection needs to be performed in a timely manner to detect damaged 
helicoil inserts and prevent additional fuel leaks. The FAA has also 
determined that this type of fuel leak may not be consistently detected 
by a preflight walk-around.

Inspection on Both Engines

    One comment suggests that a provision be included in the AD to not 
inspect all fuel pumps of an airplane during the same maintenance 
session.
    The FAA agrees. This final rule prohibits servicing, replacement, 
and inspection on all engines of an airplane at one time by the same 
individual.

Unnecessary Corrective Action

    One comment suggests that the AD is unnecessary because the 
inspections are already being carried out voluntarily.
    The FAA does not agree. The FAA has determined that an unsafe 
condition has been discovered that could cause substantial fuel loss 
and pose a fire hazard and that it is necessary to mandate action to 
correct the problem.

CFM56-7B Model

    One comment questions if the CFM56-7B model should be included.
    The FAA does not agree. The FAA has determined that it is 
unnecessary to include the CFM56-7B because its configuration is not 
similar to the design associated with the unsafe condition.

New vs. Reworked Fuel Pumps

    One comment requests that wording be added to the AD to indicate 
that there will be two groups of fuel pumps with D-bolts, reworked and 
newly made. Another comment requests that the definition of serviceable 
part be changed to include new fuel pumps.
    The FAA agrees. This final rule indicates that both reworked and 
newly made fuel pumps are serviceable parts.

[[Page 47250]]

Adoption of the Rule as Proposed

    One comment supports the adoption of the rule as proposed.

Conclusion

    After careful review of the available data, including the comments 
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 Impact

    No comments were received on the economic analysis contained in the 
proposed rules.

Regulatory Impact

    This 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 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 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 
from 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 the following new 
airworthiness directive:

2000-15-01  CFM International: Amendment 39-11830. Docket 99-NE-40-
AD.

Applicability

    CFM International CFM56-2, -2A, -2B, -3, -3B, -3C, -5, -5A, -5B, 
-5C series engines installed on but not limited to McDonnell Douglas 
DC-8 series, Boeing 737 series, Airbus Industrie A319, A320, A321 
and A340 series, as well as 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 (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

    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 the 
fuel pump filter cover helicoil inserts and bolts for damage in 
accordance with Section 2, Accomplishment Instructions, of the 
applicable Service Bulletins (SBs) listed in paragraph (a)(5) of 
this AD, as follows:
    (1) If the fuel pump has not been previously inspected prior to 
the effective date of this AD, inspect at the next fuel filter 
replacement, but not to exceed 200 cycles-in-service (CIS) after the 
effective date of this AD.
    (2) If the fuel pump has been previously inspected prior to the 
effective date of this AD, inspect at the next fuel filter 
replacement.
    (3) Thereafter, inspect at each fuel filter replacement.

Replacement or Repair

    (4) If damage equals or exceeds the reject criteria stated in 
Section 2, Accomplishment Instructions, of the SBs listed in 
paragraph (a)(5) of this AD, prior to further flight remove the fuel 
pump from service and replace or repair the helicoil in accordance 
with Section 2, Accomplishment Instructions, of the SBs listed in 
paragraph (a)(5), (b) or (c) as applicable, of this AD.

Applicable Inspection SB

    (5) Inspect and replace, if necessary, in accordance with the 
CFMI SB that applies to your engine from the following list:

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 with a newly manufactured 
or reworked fuel pump that incorporates a D-bolt filter cover 
attachment. This action must be done at the next engine or fuel pump 
shop visit, which ever occurs first, but no later than 5 years from 
the effective date of this AD in accordance with the CFMI SB that 
applies to your engine from the following list:

CFM56-2 SB 73-A113, dated August 17, 1999.
CFM56-2A SB 73-A058, dated August 17, 1999.
CFM56-2B SB 73-A079, Revision 1, dated October 22, 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 or reworked fuel pump that incorporates a 
D-bolt filter cover attachment in accordance with this paragraph 
constitutes terminating action to the inspections required by 
paragraph (a) of this AD.
    (c) An alternative terminating action is an on-wing repair that 
may be performed. Terminating action must be accomplished no later 
than 5 years from the effective date of this AD, in accordance with 
one of the following CFMI SB's that applies to your engine:

CFM56-2 SB 73-109, Revision 1, dated January 7, 1998.
CFM56-2A SB 73-054, Revision 1, dated January 7, 1998.
CFM56-2B SB 73-074, Revision 1, dated January 12, 1998.
CFM56-3/3B/3C SB 73-125, Revision 1, dated January 7, 1998.
CFM56-5 SB 73-135, Revision 1, dated January 7, 1998.
CFM56-5B SB 73-055, Revision 1, dated January 7, 1998.
CFM56-5C SB 73-070, Revision 1, dated January 7, 1998.

[[Page 47251]]

Prohibited Inspection or Replacement

    (d) Inspection, replacement or repair of fuel pumps, in 
accordance with paragraph (a), (b) or (c) of this AD, on all engines 
installed on the same airplane by the same individual prior to the 
same flight is prohibited.

Definitions

    (e) For the purpose of this AD:
    (1) 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)(5) of this AD. A 
serviceable part is also defined as a fuel pump that has been newly 
manufactured, reworked or repaired in accordance with the applicable 
CFMI SBs listed in paragraphs (a)(5), (b) or (c) of this AD.
    (2) A fuel pump shop visit is defined as introduction of an 
engine into a shop for the purpose of removal of the fuel pump from 
the gearbox.
    (3) An engine shop visit is defined as introduction of an engine 
into a shop for the purpose of maintenance or inspection.

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, Engine Certification Office (ECO). 
Operators shall submit their requests 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

    (g) 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 aircraft to a location where 
the requirements of this AD can be accomplished.

Incorporation By Reference Material

    (h) The FAA has reviewed and approved the technical content of 
the listed CFMI Service Bulletins (SBs). The actions required by 
this AD shall be done in accordance with the following CFMI SBs:

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           Document No.                     Pages               Revision                      Date
----------------------------------------------------------------------------------------------------------------
CFM56-2
SB No. 73-110.....................  1-10                  2                     April 29, 1999.
Total pages: 10
CFM56-2A
SB No. 73-055.....................  1-10                  1                     April 29, 1999.
Total pages: 10
CFM56-2B
SB No. 73-076.....................  1-10                  1                     April 29, 1999.
Total pages: 10
CFM56-3/3B/3C
SB No. 73-126.....................  1-10                  1                     April 29, 1999.
Total pages: 10
CFM56-5
SB No. 73-136.....................  1-10                  2                     April 29, 1999.
Total pages: 10
CFM56-5B
SB No. 73-056.....................  1-10                  2                     April 29, 1999.
Total pages: 10
CFM56-5C
SB No. 73-073.....................  1-10                  2                     April 29, 1999.
Total pages: 10
CFM56-2
SB No. 73-A113....................  1-6                   Original              August 17, 1999.
708600-73-113.....................  1-21                  Original              May 24, 1999.
Total pages: 27
CFM56-2A
SB No. 73-A058....................  1-3                   Original              August 17, 1999.
708400-73-101.....................  1-14                  Original              April 16, 1999.
Total pages: 17
CFM56-2B
SB No. 73-A079....................  1-4                   1                     October 22, 1999.
708600-73-112.....................  1-19                  Original              April 14, 1999.
Total pages: 23
CFM56-3/3B/3C
SB No. 73-A129....................  1-4                   Original              August 17, 1999.
708600-73-110.....................  1-19                  Original              April 14, 1999.
Total pages: 23
CFM56-5
SB No. 73-A143....................  1-4                   Original              June 18, 1999.
714900-73-106.....................  1-14                  Original              April 9, 1999.
Total pages: 18
CFM56-5B
SB No. 73-A062....................  1-4                   Original              June 18, 1999.
714900-73-107.....................  1-15                  Original              April 13, 1999.
Total pages: 19
CFM56-5C
SB No. 73-A078....................  1-4                   Original              June 21, 1999.
714900-73-108.....................  1-15                  Original              April 13, 1999.
Total pages: 19
CFM56-2
SB No. 73-109.....................  1-13                  1                     January 7, 1998.
Total pages: 13
CFM56-2A
SB No. 73-054.....................  1-13                  1                     January 7, 1998.

[[Page 47252]]

 
Total pages: 13
CFM56-2B
SB No. 73-074.....................  1-13                  1                     January 12, 1998.
Total pages: 13
CFM56-3/3B/3C
SB No. 73-125.....................  1-13                  1                     January 7, 1998.
Total pages: 13
CFM56-5
SB No. 73-135.....................  1-13                  1                     January 7, 1998.
Total pages: 13
CFM56-5B
SB No. 73-055.....................  1-13                  1                     January 7, 1998.
Total pages: 13
CFM56-5C
SB No. 73-070.....................  1-13                  1                     January 7, 1998.
Total pages: 13
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    The incorporations by reference were 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 CFM International, Technical 
Publications Department, 1 Neumann Way, Cincinnati, OH 45215; 
telephone: (513) 552-2800, fax: (513) 552-2816. Copies may be 
inspected at the FAA, New England Region, Office of the Regional 
Counsel, 12 New England Executive Park, Burlington, MA 01803-5299; 
or at the Office of the Federal Register, 800 North Capitol Street, 
NW., suite 700, Washington, DC.

Effective Date

    (i) This amendment becomes effective on October 2, 2000.

    Issued in Burlington, Massachusetts on July 14, 2000.
David A. Downey,
Assistant Manager, Engine and Propeller Directorate, Aircraft 
Certification Service.
[FR Doc. 00-18523 Filed 8-1-00; 8:45 am]
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