[Federal Register Volume 77, Number 75 (Wednesday, April 18, 2012)]
[Proposed Rules]
[Pages 23166-23169]
From the Federal Register Online via the Government Publishing Office [www.gpo.gov]
[FR Doc No: 2012-9267]
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DEPARTMENT OF TRANSPORTATION
Federal Aviation Administration
14 CFR Part 39
[Docket No. FAA-2012-0413; Directorate Identifier 2011-NM-257-AD]
RIN 2120-AA64
Airworthiness Directives; The Boeing Company Airplanes
AGENCY: Federal Aviation Administration (FAA), DOT.
ACTION: Notice of proposed rulemaking (NPRM).
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SUMMARY: We propose to adopt a new airworthiness directive (AD) for all
The Boeing Company Model DC-10-10, DC-10-10F, DC-10-15, DC-10-30, DC-
10-30F (KC-10A and KDC-10), DC-10-40, DC-10-40F, MD-10-10F, MD-10-30F,
MD-11, and MD-11F airplanes. This proposed AD was prompted by fuel
system reviews conducted by the manufacturer. This proposed AD would
require adding design features to detect electrical faults, to detect a
pump running in an empty fuel tank, and to ensure that a fuel pump's
operation is not affected by certain conditions. We are proposing this
AD to reduce the potential of ignition sources inside fuel tanks,
which, in combination with flammable fuel vapors, could result in fuel
tank explosions and consequent loss of the airplane.
DATES: We must receive comments on this proposed AD by June 4, 2012.
[[Page 23167]]
ADDRESSES: You may send comments, using the procedures found in 14 CFR
11.43 and 11.45, by any of the following methods:
Federal eRulemaking Portal: Go to http://www.regulations.gov. Follow the instructions for submitting comments.
Fax: 202-493-2251.
Mail: U.S. Department of Transportation, Docket
Operations, M-30, West Building Ground Floor, Room W12-140, 1200 New
Jersey Avenue SE., Washington, DC 20590.
Hand Delivery: Deliver to Mail address above between 9
a.m. and 5 p.m., Monday through Friday, except Federal holidays.
Examining the AD Docket
You may examine the AD docket on the Internet at http://www.regulations.gov; or in person at the Docket Management Facility
between 9 a.m. and 5 p.m., Monday through Friday, except Federal
holidays. The AD docket contains this proposed AD, the regulatory
evaluation, any comments received, and other information. The street
address for the Docket Office (phone: 800-647-5527) is in the ADDRESSES
section. Comments will be available in the AD docket shortly after
receipt.
FOR FURTHER INFORMATION CONTACT: Serj Harutunian, Aerospace Engineer,
Propulsion Branch, ANM-140L, FAA, Los Angeles Aircraft Certification
Office (ACO), 3960 Paramount Boulevard, Lakewood, California 90712-
4137; phone: 562-627-5254; fax: 562-627-5210; email:
[email protected].
SUPPLEMENTARY INFORMATION:
Comments Invited
We invite you to send any written relevant data, views, or
arguments about this proposal. Send your comments to an address listed
under the ADDRESSES section. Include ``Docket No. FAA-2012-0413;
Directorate Identifier 2011-NM-257-AD'' at the beginning of your
comments. We specifically invite comments on the overall regulatory,
economic, environmental, and energy aspects of this proposed AD. We
will consider all comments received by the closing date and may amend
this proposed AD because of those comments.
We will post all comments we receive, without change, to http://www.regulations.gov, including any personal information you provide. We
will also post a report summarizing each substantive verbal contact we
receive about this proposed AD.
Discussion
The FAA has examined the underlying safety issues involved in fuel
tank explosions on several large transport airplanes, including the
adequacy of existing regulations, the service history of airplanes
subject to those regulations, and existing maintenance practices for
fuel tank systems. As a result of those findings, we issued a
regulation titled ``Transport Airplane Fuel Tank System Design Review,
Flammability Reduction and Maintenance and Inspection Requirements''
(66 FR 23086, May 7, 2001). In addition to new airworthiness standards
for transport airplanes and new maintenance requirements, this rule
included Special Federal Aviation Regulation No. 88 (``SFAR 88,''
Amendment 21-78, and subsequent Amendments 21-82 and 21-83).
Among other actions, SFAR 88 (66 FR 23086, May 7, 2001) requires
certain type design (i.e., type certificate (TC) and supplemental type
certificate (STC)) holders to substantiate that their fuel tank systems
can prevent ignition sources in the fuel tanks. This requirement
applies to type design holders for large turbine-powered transport
airplanes and for subsequent modifications to those airplanes. It
requires them to perform design reviews and to develop design changes
and maintenance procedures if their designs do not meet the new fuel
tank safety standards. As explained in the preamble to the rule, we
intended to adopt airworthiness directives to mandate any changes found
necessary to address unsafe conditions identified as a result of these
reviews.
In evaluating these design reviews, we have established four
criteria intended to define the unsafe conditions associated with fuel
tank systems that require corrective actions. The percentage of
operating time during which fuel tanks are exposed to flammable
conditions is one of these criteria. The other three criteria address
the failure types under evaluation: single failures, single failures in
combination with a latent condition(s), and in-service failure
experience. For all four criteria, the evaluations included
consideration of previous actions taken that may mitigate the need for
further action.
We have determined that the actions identified in this proposed AD
are necessary to reduce the potential of ignition sources inside fuel
tanks, which, in combination with flammable fuel vapors, could result
in fuel tank explosions and consequent loss of the airplane.
A fuel pump may cause an ignition source in a fuel tank when it has
internal electrical faults, or when the pump overheats due to prolonged
dry running in an empty fuel tank. Electrical faults inside fuel pumps
may cause arcing and burn through the pump housing into an empty fuel
tank. If a pump is not shut off in a timely manner when the tank is
emptied, the dry-running pump may cause excessive heat and become an
ignition source inside the tank.
FAA's Determination
We are proposing this AD because we evaluated all the relevant
information and determined the unsafe condition described previously is
likely to exist or develop in other products of the same type design.
Proposed AD Requirements
This proposed AD would prohibit operation of an affected airplane
as of 60 months after the effective date of the AD, unless the
following design features and requirements have been approved by the
FAA and installed on the airplane.
A protective device for each electrically powered fuel
pump that will detect electrical faults and shut off the pump
automatically when such faults are detected.
Additional design features that will detect any fuel pump
running in an empty fuel tank, notify the flight crew, and
automatically shut off each pump within a specified time if not
manually shut off by the flight crew.
Revisions of the airplane flight manual to include
procedures for manual pump shutoff.
Means to ensure the detection of a fuel pump running in an
empty tank that has previously been shut off.
Costs of Compliance
We estimate that this proposed AD affects 180 airplanes of U.S.
registry. We estimate the following costs to comply with this proposed
AD, based on the costs of similar STC installations:
[[Page 23168]]
Estimated Costs
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Cost per Cost on U.S.
Action Labor cost Parts cost product operators
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Installing design features.......... 65 work-hours x $85 per $55,000 $60,525 $10,894,500
hour = $5,525.
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Authority for This Rulemaking
Title 49 of the United States Code specifies the FAA's authority to
issue rules on aviation safety. Subtitle I, section 106, describes the
authority of the FAA Administrator. Subtitle VII: Aviation Programs,
describes in more detail the scope of the Agency's authority.
We are issuing this rulemaking under the authority described in
Subtitle VII, Part A, Subpart III, Section 44701: ``General
requirements.'' Under that section, Congress charges the FAA with
promoting safe flight of civil aircraft in air commerce by prescribing
regulations for practices, methods, and procedures the Administrator
finds necessary for safety in air commerce. This regulation is within
the scope of that authority because it addresses an unsafe condition
that is likely to exist or develop on products identified in this
rulemaking action.
Regulatory Findings
We determined that this proposed AD would not have federalism
implications under Executive Order 13132. This proposed AD 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.
For the reasons discussed above, I certify 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),
(3) Will not affect intrastate aviation in Alaska, and
(4) 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.
List of Subjects in 14 CFR Part 39
Air transportation, Aircraft, Aviation safety, Incorporation by
reference, Safety.
The Proposed Amendment
Accordingly, under the authority delegated to me by the
Administrator, the FAA proposes to amend 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. The FAA amends Sec. 39.13 by adding the following new
airworthiness directive (AD):
The Boeing Company: Docket No. FAA-2012-0413; Directorate Identifier
2011-NM-257-AD.
(a) Comments Due Date
We must receive comments by June 4, 2012.
(b) Affected ADs
None.
(c) Applicability
This AD applies to all The Boeing Company Model DC-10-10, DC-10-
10F, DC-10-15, DC-10-30, DC-10-30F (KC-10A and KDC-10), DC-10-40,
DC-10-40F, MD-10-10F, MD-10-30F, MD-11, and MD-11F airplanes;
certificated in any category.
(d) Subject
Joint Aircraft System Component (JASC)/Air Transport Association
(ATA) of America Code 28, Fuel.
(e) Unsafe Condition
This AD was prompted by fuel system reviews conducted by the
manufacturer. We are issuing this AD to reduce the potential of
ignition sources inside fuel tanks, which, in combination with
flammable fuel vapors, could result in fuel tank explosions and
consequent loss of the airplane.
(f) Compliance
Comply with this AD within the compliance times specified,
unless already done.
(g) Criteria for Operation
As of 60 months after the effective date of this AD, no person
may operate any airplane affected by this AD unless an amended type
certificate or supplemental type certificate that incorporates the
design features and requirements described in paragraphs (g)(1)
through (g)(4) of this AD has been approved by the Manager, Los
Angeles Aircraft Certification Office (ACO), FAA, and those design
features are installed on the airplane to meet the criteria
specified in 14 CFR Section 25.981(a) and (d), at amendment level
25-125.
(1) For all airplanes: Each electrically powered fuel pump
installed in any fuel tank that normally empties during flight--such
as center wing tanks, auxiliary fuel tanks, and tail tanks--must
have a protective device installed to detect electrical faults that
can cause arcing and burn through of the fuel pump housing and pump
electrical connector. The same device must shut off the pump by
automatically removing electrical power from the pump when such
faults are detected. When a fuel pump is shut off resulting from
detection of an electrical fault, the device must stay latched off,
until the fault is cleared through maintenance action and the pump
is verified safe for operation.
(2) For airplanes with a 2-person flight crew: Additional design
features, if not originally installed by the airplane manufacturer,
must be installed to meet 3 criteria: to detect a running fuel pump
in a tank that is normally emptied during flight, to provide an
indication to the flight crew that the tank is empty, and to
automatically shut off that fuel pump. The prospective pump
indication and shutoff system must automatically shut off each pump
in case the flight crew does not shut off a pump running dry in an
empty tank within 60 seconds after each fuel tank is emptied. The
airplane flight manual supplement (AFMS) must be revised to include
flight crew manual pump shutoff procedures in the Normal Operating
Procedures section of the AFMS.
(3) For airplanes with a 3-person flight crew: Additional design
features, if not originally installed by the airplane manufacturer,
must be installed to detect when a fuel pump in a tank that is
normally emptied during flight is running in an empty fuel tank, and
provide an indication to the flight crew that the tank is empty. The
flight engineer must manually shut off each pump running dry in an
empty tank within 60 seconds after the tank is emptied. The
Limitations section of the AFMS must be revised to specify that this
pump shutoff must be done by the flight engineer.
(4) For all airplanes: The empty-tank shutoff system design must
preclude the undetected running of a fuel pump in an empty tank
after the pump is commanded off automatically or manually.
(h) Alternative Methods of Compliance (AMOCs)
(1) The Manager, Los Angeles Aircraft Certification Office
(ACO), FAA, has the authority to approve AMOCs for this AD, if
requested using the procedures found in 14 CFR 39.19. In accordance
with 14 CFR 39.19, send your request to your principal inspector or
local Flight Standards District Office, as appropriate. If sending
information directly to the manager of the ACO, send it to the
attention of the person identified in the Related Information
section of this AD.
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(2) Before using any approved AMOC, notify your appropriate
principal inspector, or lacking a principal inspector, the manager
of the local flight standards district office/certificate holding
district office.
(i) Related Information
For more information about this AD, contact Serj Harutunian,
Aerospace Engineer, Propulsion Branch, ANM-140L, FAA, Los Angeles
ACO, 3960 Paramount Boulevard, Lakewood, California 90712-4137;
phone: 562-627-5254; fax: 562-627-5210; email:
[email protected].
Issued in Renton, Washington, on April 6, 2012.
Ali Bahrami,
Manager, Transport Airplane Directorate, Aircraft Certification
Service.
[FR Doc. 2012-9267 Filed 4-17-12; 8:45 am]
BILLING CODE 4910-13-P