AD Amdt-39-10492

[Federal Register Volume 63, Number 78 (Thursday, April 23, 1998)]
[Rules and Regulations]
[Pages 20062-20064]
From the Federal Register Online via the Government Publishing Office [<a href="http://www.gpo.gov">www.gpo.gov</a>]
[FR Doc No: 98-10756]


=======================================================================
-----------------------------------------------------------------------

DEPARTMENT OF TRANSPORTATION

Federal Aviation Administration

14 CFR Part 39

[Docket No. 98-NM-125-AD; Amendment 39-10492; AD 98-08-09]
RIN 2120-AA64


Airworthiness Directives; Lockheed Model L-1011-385 Series 
Airplanes

AGENCY: Federal Aviation Administration, DOT.

ACTION: Final rule; request for comments.

-----------------------------------------------------------------------

SUMMARY: This document publishes in the Federal Register an amendment 
adopting Airworthiness Directive (AD) 98-08-09 that was sent previously 
to all known U.S. owners and operators of certain Lockheed Model L-
1011-385 series airplanes by individual notices. This AD 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 new maintenance procedures for operating the airplane with an 
inoperative fuel boost pump assembly or with an inoperative flight 
station fuel quantity indicating system. This 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 when less than 
1,200 pounds of fuel are in the corresponding wing fuel tank is 
prohibited. This action 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 April 28, 1998, to all persons except those persons to 
whom it was made immediately effective by emergency AD 98-08-09, issued 
April 3, 1998, which contained the requirements of this amendment.
    Comments for inclusion in the Rules Docket must be received on or 
before June 22, 1998.

ADDRESSES: Submit comments in triplicate to the Federal Aviation 
Administration (FAA), Transport Airplane Directorate, ANM-114, 
Attention: Rules Docket No. 98-NM-125-AD, 1601 Lind Avenue, SW., 
Renton, Washington 98055-4056.
    This information may be examined at the FAA, Transport Airplane 
Directorate, 601 Lind Avenue, SW., Renton, Washington.

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: On April 3, 1998, the FAA issued emergency 
AD 98-08-09, which is applicable to certain Lockheed Model L-1011-385 
series airplanes.
    The FAA has received 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. Such electrical arcing or 
overheating could burn a hole in the pump housing and the protective 
housing of the fuel boost pump. If electrical arcing or overheating 
breeches the protective housing and the fuel in the wing fuel tank is 
at a sufficient level, the liquid fuel would prevent combustion. 
However, if electrical arcing or overheating breeches the protective 
housing of the fuel boost pump and the fuel level of the wing tank is 
low enough to expose the protective housing to fuel vapors and fumes, a 
potential fire or explosion could occur. The on-going investigation of 
the internal electrical failures has not revealed the cause of the 
failures as yet.

Explanation of Requirements of the Rule

    Since the unsafe condition described is likely to exist or develop 
on other airplanes of the same type design, the FAA issued emergency AD 
98-08-09 to prevent a potential fire or explosion in the wing fuel tank 
due to exposure of the fuel boost pump to fuel vapors and fumes. The AD 
requires revision of the Limitations and Procedures Sections of the 
FAA-approved Airplane Flight Manual (AFM) to prohibit operation of the 
fuel boost pumps when fuel quantities are below certain levels, and to 
add new maintenance procedures for operating the airplane with an 
inoperative fuel boost pump assembly or with an inoperative flight 
station fuel quantity indicating system (FQIS). The

[[Page 20063]]

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 when less than 1,200 pounds of fuel are in the corresponding wing 
fuel tank is prohibited.
    This is considered to be interim action until final action is 
identified, at which time the FAA may consider further rulemaking.
    Since it was found that immediate corrective action was required, 
notice and opportunity for prior public comment thereon were 
impracticable and contrary to the public interest, and good cause 
existed to make the AD effective immediately by individual notices 
issued to all known U.S. owners and operators of certain Lockheed Model 
L-1011-385 series airplanes. These conditions still exist, and the AD 
is hereby published in the Federal Register as an amendment to section 
39.13 of the Federal Aviation Regulations (14 CFR 39.13) to make it 
effective to all persons.

Comments Invited

    Although this action is in the form of a final rule that involves 
requirements affecting flight safety and, thus, was not preceded by 
notice and an opportunity for public comment, comments are invited on 
this rule. Interested persons are invited to comment on this rule by 
submitting such written data, views, or arguments as they may desire. 
Communications shall identify the Rules Docket number and be submitted 
in triplicate to the address specified under the caption ADDRESSES. All 
communications received on or before the closing date for comments will 
be considered, and this rule may be amended in light of the comments 
received. Factual information that supports the commenter's ideas and 
suggestions is extremely helpful in evaluating the effectiveness of the 
AD action and determining whether additional rulemaking action would be 
needed.
    Comments are specifically invited on the overall regulatory, 
economic, environmental, and energy aspects of the rule that might 
suggest a need to modify the 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 that 
summarizes each FAA-public contact concerned with the substance of this 
AD will be filed in the Rules Docket.
    Commenters wishing the FAA to acknowledge receipt of their comments 
submitted in response to this rule must submit a self-addressed, 
stamped postcard on which the following statement is made: ``Comments 
to Docket Number 98-NM-125-AD.'' The postcard will be date stamped and 
returned to the commenter.

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.
    The FAA has determined that this regulation is an emergency 
regulation that must be issued immediately to correct an unsafe 
condition in aircraft, and that it is not a ``significant regulatory 
action'' under Executive Order 12866. It has been determined further 
that this action involves an emergency regulation under DOT Regulatory 
Policies and Procedures (44 FR 11034, February 26, 1979). If it is 
determined that this emergency regulation otherwise would be 
significant under DOT Regulatory Policies and Procedures, a final 
regulatory evaluation will be prepared and placed in the Rules Docket. 
A copy of it, if filed, 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, 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:

98-08-09  Lockheed Aeronautical Systems Company: Amendment 39-10492. 
Docket 98-NM-125-AD.

    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 (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: Required as indicated, unless accomplished 
previously.
    To prevent a potential fire or explosion in the wing fuel tank, 
accomplish the following:
    (a) Within 50 flight hours or 10 days after the effective date 
of this AD, 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.
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

[[Page 20064]]

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.
''
    (b) Within 50 flight hours or 10 days after the effective date 
of this AD, 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.''
    (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, 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.

    Note 2: Information concerning the existence of approved 
alternative methods of compliance with this AD, if any, may be 
obtained from the Atlanta ACO.

    (d) 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.
    (e) This amendment becomes effective on April 28, 1998, to all 
persons except those persons to whom it was made immediately 
effective by emergency AD 98-08-09, issued on April 3, 1998, which 
contained the requirements of this amendment.

    Issued in Renton, Washington, on April 16, 1998.
Darrell M. Pederson,
Acting Manager, Transport Airplane Directorate, Aircraft Certification 
Service.
[FR Doc. 98-10756 Filed 4-22-98; 8:45 am]
BILLING CODE 4910-13-U