[Federal Register Volume 64, Number 229 (Tuesday, November 30, 1999)]
[Rules and Regulations]
[Pages 66756-66758]
From the Federal Register Online via the Government Publishing Office [www.gpo.gov]
[FR Doc No: 99-30627]
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DEPARTMENT OF TRANSPORTATION
Federal Aviation Administration
14 CFR Part 39
[Docket No. 99-NM-122-AD; Amendment 39-11436; AD 99-24-12]
RIN 2120-AA64
Airworthiness Directives; Lockheed Model L-1011-385 Series
Airplanes
AGENCY: Federal Aviation Administration, DOT.
ACTION: Final rule.
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SUMMARY: This amendment supersedes an existing airworthiness directive
(AD), applicable to certain Lockheed Model L-1011-385 series airplanes,
that currently requires revision of the Airplane Flight Manual (AFM) to
prohibit operation of the fuel boost pumps when fuel quantities are
below certain levels, and to add maintenance procedures for operating
the airplane under certain conditions. That AD also requires the
installation of a placard on the engineer's fuel panel to advise the
maintenance crew that operation of the fuel boost pumps is prohibited
under certain conditions. This amendment adds a terminating
modification for the requirements of the existing AD. This amendment is
prompted by reports of internal electrical failures in the fuel boost
pump of the wing fuel tanks that could result in either electrical
arcing or localized overheating. The actions specified by this AD are
intended to prevent such electrical arcing or overheating, which could
breech the protective housing of the fuel boost pump and expose it to
fuel vapors and fumes, and consequent potential fire or explosion in
the wing fuel tank.
DATES: Effective January 4, 2000.
The incorporation by reference of certain publications listed in
the regulations is approved by the Director of the Federal Register as
of January 4, 2000.
ADDRESSES: The service information referenced in this AD may be
obtained from Lockheed Martin Aircraft & Logistics Center, 120 Orion
Street, Greenville, South Carolina 29605. This information may be
examined at the Federal Aviation Administration (FAA), Transport
Airplane Directorate, Rules Docket, 1601 Lind Avenue, SW., Renton,
Washington; or the FAA, Small Airplane Directorate, Atlanta Aircraft
Certification Office, One Crown Center, 1895 Phoenix Boulevard, Suite
450, Atlanta, Georgia; or at the Office of the Federal Register, 800
North Capitol Street, NW., suite 700, Washington, DC.
FOR FURTHER INFORMATION CONTACT: Thomas Peters, Aerospace Engineer,
Systems and Flight Test Branch, ACE-116A, FAA, Small Airplane
Directorate, Atlanta Aircraft Certification Office, One Crown Center,
1895 Phoenix Boulevard, suite 450, Atlanta, Georgia 30349; telephone
(770) 703-6063; fax (770) 703-6097.
SUPPLEMENTARY INFORMATION: A proposal to amend part 39 of the Federal
Aviation Regulations (14 CFR part 39) by superseding AD 98-08-09,
amendment 39-10492 (63 FR 20062, April 23, 1998), which is applicable
to certain Lockheed Model L-1011-385 series airplanes, was published in
the Federal Register on July 14, 1999 (64 FR 37920). The action
proposed to supersede AD 98-08-09 to continue to require revision of
the Airplane Flight Manual (AFM) to prohibit operation of the fuel
boost pumps when fuel quantities are below certain levels, and to add
maintenance procedures for operating the airplane with an inoperative
fuel boost pump assembly or with an inoperative flight station fuel
quantity indicating system. The action also proposed to continue to
require the installation of a placard on the engineer's fuel panel to
advise the maintenance crew that operation of the fuel boost pumps when
less than 1,200 pounds of fuel are in the corresponding wing fuel tank
is prohibited. It also proposed to require installation of a modified
fuel boost pump assembly, which would terminate the requirements of the
existing AD.
Comments
Interested persons have been afforded an opportunity to participate
in the making of this amendment. Due consideration has been given to
the comments received.
Support for the Proposal
One commenter supports the proposed rule.
Request to Revise Note 2
One commenter requests that the FAA revise Note 2 [following
paragraph (c) of the proposed AD] to read ``Note 2: Modification of the
fuel boost pump assemblies, prior to the effective date of this AD, in
accordance with Lockheed Service Bulletin 093-28-093, dated
[[Page 66757]]
January 15, 1999, or Revision 1, dated February 8, 1999, is considered
acceptable for compliance with paragraph (c) of this AD.'' The
commenter contends that accomplishment of the modification required by
Lockheed Service Bulletin 093-28-093, Revision 1, would be an
acceptable means of compliance with paragraph (c) of the proposed AD,
irrespective of whether the modification was accomplished prior to, or
within 18 months after the effective date of the proposed AD.
The FAA does not concur with the commenter's request. Operators are
given credit for work previously performed by means of the phrase in
the ``Compliance'' section of the AD that states, ``Required as
indicated, unless accomplished previously.'' The FAA's intent is that
operators accomplish the requirements of this AD after the effective
date of this AD in accordance with the latest FAA-approved revision of
Lockheed Service Bulletin 093-28-093 (i.e., Revision 1, dated February
8, 1999). Note 2 gives credit to operators that accomplished the
modification prior to the effective date of this AD in accordance with
the original version of the service bulletin. Therefore, no change to
the final rule is necessary.
Explanation of Change Made to Proposal
Since issuance of the proposed rule, the FAA has become aware that
Lockheed Service Bulletin 093-28-093, dated January 15, 1999, which was
referenced in Note 2 of the proposed AD, was never released by the
manufacturer. Therefore, the FAA has deleted Note 2 from the final rule
and renumbered the subsequent notes accordingly.
The FAA also has added paragraph (d)(2) to the final rule to inform
operators that alternative methods of compliance, approved previously
in accordance with AD 98-08-09, amendment 39-10492, are approved as
alternative methods of compliance for this final rule.
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 previously
described. The FAA has determined that these changes will neither
increase the economic burden on any operator nor increase the scope of
the AD.
Cost Impact
There are approximately 235 Model L-1011-385 series airplanes of
the affected design in the worldwide fleet. The FAA estimates that 117
airplanes of U.S. registry will be affected by this AD.
The actions that are currently required by AD 98-08-09 take
approximately 1 work hour per airplane to accomplish, at an average
labor rate of $60 per work hour. Based on these figures, the cost
impact of the currently required actions on U.S. operators is estimated
to be $7,020, or $60 per airplane.
The modification that is required in this AD action will take
approximately 8 work hours (1 hour per fuel pump assembly) per airplane
to accomplish, at an average labor rate of $60 per work hour. Required
parts will cost approximately $18,880 per airplane. Based on these
figures, the cost impact of the modification required by this AD on
U.S. operators is estimated to be $2,265,120, or $19,360 per airplane.
The cost impact figures discussed above are based on assumptions
that no operator has yet accomplished any of the requirements of this
AD action, and that no operator would accomplish those actions in the
future if this AD were not adopted.
Regulatory Impact
The regulations adopted herein will not have substantial direct
effects 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. Therefore, in
accordance with Executive Order 12612, it is determined that this final
rule does not have sufficient federalism implications to warrant the
preparation of a Federalism Assessment.
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 removing amendment 39-10492 (63 FR
20062, April 23, 1998), and by adding a new airworthiness directive
(AD), amendment 39-11436, to read as follows:
99-24-12 Lockheed Aeronautical Systems Company: Amendment 39-11436.
Docket 99-NM-122-AD. Supersedes AD 98-08-09, Amendment 39-10492.
Applicability: Model L-1011-385-1, -385-1-14, -385-1-15, and -
385-3 series airplanes, certificated in any category.
Note 1: This AD applies to each airplane 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 airplanes 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)(1)
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 a potential fire or explosion in the wing fuel tank,
accomplish the following:
Restatement of Requirements of AD 98-08-09, Amendment 39-10492 AFM
Revision
(a) Within 50 flight hours or 10 days after April 28, 1998 (the
effective date of AD 98-08-09, amendment 39-10492), whichever occurs
first, revise the Limitations and Procedures Sections of the FAA-
approved Airplane Flight Manual (AFM) to include the following
information. This may be accomplished by inserting a copy of this AD
into the AFM.
Add to Limitations Section:
``FUEL SYSTEM
Fuel Pumps
Do not operate the fuel boost pumps of the affected wing tank in
the air or on the ground when fuel quantities are less than the
following:
Wing tanks 1 and 3: Less than 1,200 lbs (545 kg) in each tank.
[[Page 66758]]
Wing tanks 2L and 2R: Less than 1,200 lbs (545 kg) total in the two
compartments (inboard and outboard) of each tank.
These quantities should be considered unusable fuel for the purposes
of fuel management.
When operating with a fuel boost pump assembly inoperative per
Master Minimum Equipment List (MMEL) item number 28-24-01, add the
following maintenance procedure:
Pull and collar the affected circuit breaker.
When operating with an inoperative flight station fuel quantity
indicating system per MMEL item 28-41-00, do not operate the fuel
boost pumps of the affected wing tank in the air or on the ground
when fuel quantities are less than the following:
Wing tanks 1 and 3: Less than 7,000 lbs (3,175 kg) in the affected
tank.
Wing tanks 2L and 2R: Less than 1,200 lbs (545 kg) total in the two
compartments (inboard and outboard) of the affected tank.''
Add to Procedures Section:
``FUEL SYSTEM
Fuel Pumps
If the circuit breaker for any wing tank fuel boost pump
(circuit breakers U3, U4, U7, U8, U9, U10, U13, U14) trips, do not
reset. If the pump trips while in flight, continue flight in
accordance with the procedures in the ``Tank Pumps LOW Lights On''
portion of the Procedures section of the AFM. If the breaker trips
while on the ground, do not reset without first identifying the
source of the electrical fault.
ELECTRICAL SYSTEM
Fuel Pumps
If the circuit breaker for any wing tank fuel boost pump
(circuit breakers U3, U4, U7, U8, U9, U10, U13, U14) trips, do not
reset. If the pump trips while in flight, continue flight in
accordance with the procedures in the ``Tank Pumps LOW Lights On''
portion of the Procedures section of the AFM. If the breaker trips
while on the ground, do not reset without first identifying the
source of the electrical fault.''
Placard Installation
(b) Within 50 flight hours or 10 days after April 28, 1998,
whichever occurs first, install a placard on the engineer's fuel
panel that states:
``If FQIS is operative, do not operate the fuel boost pumps when
less than 1,200 pounds of fuel are in the corresponding wing
tanks.''
New Requirements of this AD
Modification
(c) Within 18 months after the effective date of this AD: Modify
each fuel boost pump assembly in accordance with Parts 2.A. through
2.I. inclusive of the Accomplishment Instructions of Lockheed
Service Bulletin 093-28-093, Revision 1, dated February 8, 1999.
Accomplishment of this modification terminates the requirements of
this AD. Following accomplishment of the modification, the AFM
revision may be removed from the AFM, and the placard may be
removed.
Alternative Methods of Compliance
(d)(1) 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, Atlanta Aircraft Certification
Office (ACO), FAA, Small Airplane Directorate. Operators shall
submit their requests through an appropriate FAA Principal
Maintenance Inspector, who may add comments and then send it to the
Manager, Atlanta ACO.
(d)(2) Alternative methods of compliance, approved previously in
accordance with AD 98-08-09, amendment 39-10492, are approved as
alternative methods of compliance with this AD.
Note 2: Information concerning the existence of approved
alternative methods of compliance with this AD, if any, may be
obtained from the Atlanta ACO.
Special Flight Permits
(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 requirements of this AD can be accomplished.
Incorporation by Reference
(f) The modification shall be done in accordance with Lockheed
Service Bulletin 093-28-093, Revision 1, dated February 8, 1999,
which contains the following list of effective pages:
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Revision level
Page No. shown on page Date shown on page
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1-4, 6....................... Original....... January 15, 1999.
5............................ 1.............. February 8, 1999.
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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 Lockheed Martin Aircraft &
Logistics Center, 120 Orion Street, Greenville, South Carolina
29605. Copies may be inspected at the FAA, Transport Airplane
Directorate, 1601 Lind Avenue, SW., Renton, Washington; or at the
FAA, Small Airplane Directorate, Atlanta Aircraft Certification
Office, One Crown Center, 1895 Phoenix Boulevard, Suite 450,
Atlanta, Georgia; or at the Office of the Federal Register, 800North
Capitol Street, NW., suite 700, Washington, DC.
(g) This amendment becomes effective on January 4, 2000.
Issued in Renton, Washington, on November 18, 1999.
D.L. Riggin,
Acting Manager, Transport Airplane Directorate, Aircraft Certification
Service.
[FR Doc. 99-30627 Filed 11-29-99; 8:45 am]
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