[Federal Register: June 13, 2008 (Volume 73, Number 115)]
[Proposed Rules]
[Page 33740-33743]
From the Federal Register Online via GPO Access [wais.access.gpo.gov]
[DOCID:fr13jn08-26]
[[Page 33740]]
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DEPARTMENT OF TRANSPORTATION
Federal Aviation Administration
14 CFR Part 39
[Docket No. FAA-2008-0638; Directorate Identifier 2008-NM-035-AD]
RIN 2120-AA64
Airworthiness Directives; Lockheed Model 382, 382B, 382E, 382F,
and 382G Series 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
Lockheed Model 382, 382B, 382E, 382F, and 382G series airplanes. This
proposed AD would require revising the FAA-approved maintenance program
by incorporating new airworthiness limitations for fuel tank systems to
satisfy Special Federal Aviation Regulation No. 88 requirements. This
proposed AD would also require the accomplishment of certain fuel
system modifications, the initial inspections of certain repetitive
fuel system limitations to phase in those inspections, and repair if
necessary. This proposed AD results from a design review of the fuel
tank systems. We are proposing this AD to prevent the potential for
ignition sources inside fuel tanks caused by latent failures,
alterations, repairs, or maintenance actions, which, in combination
with flammable fuel vapors, could result in a fuel tank explosion and
consequent loss of the airplane.
DATES: We must receive comments on this proposed AD by July 14, 2008.
ADDRESSES: You may send comments 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: U.S. Department of Transportation, Docket
Operations, M-30, West Building Ground Floor, Room W12-140, 1200 New
Jersey Avenue, SE., Washington, DC 20590, between 9 a.m. and 5 p.m.,
Monday through Friday, except Federal holidays.
For service information identified in this AD, contact Lockheed
Martin Corporation/Lockheed Martin Aeronautics Company, Airworthiness
Office, Dept. 6A0M, Zone 0252, Column P-58, 86 S. Cobb Drive, Marietta,
Georgia 30063.
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 (telephone 800-647-5527) is in the
ADDRESSES section. Comments will be available in the AD docket shortly
after receipt.
FOR FURTHER INFORMATION CONTACT: Robert A. Bosak, Aerospace Engineer,
Propulsion and Services Branch, ACE-118A, FAA, Atlanta Aircraft
Certification Office, One Crown Center, 1895 Phoenix Boulevard, Suite
450, Atlanta, Georgia 30349; telephone (770) 703-6094; fax (770) 703-
6097.
SUPPLEMENTARY INFORMATION:
Comments Invited
We invite you to send any written relevant data, views, or
arguments about this proposed AD. Send your comments to an address
listed under the ADDRESSES section. Include ``Docket No. FAA-2008-0638;
Directorate Identifier 2008-NM-035-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 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 a fuel tank explosion and consequent loss of the airplane.
Relevant Service Information
We have reviewed Lockheed Service Bulletin 382-28-22, Revision 3,
dated March 28, 2008. The service bulletin describes procedures for
incorporating new airworthiness limitations for fuel tank systems into
the operator's FAA-approved maintenance program. The airworthiness
limitations for fuel tank systems include fuel system limitations
(FSLs) and critical design configuration control limitations (CDCCLs).
FSLs are modifications, design features, and periodic inspections of
certain features for latent failures that could contribute to an
ignition source. CDCCLs are limitation requirements to preserve a
[[Page 33741]]
critical ignition source prevention feature of the fuel tank system
design that is necessary to prevent the occurrence of an unsafe
condition. The purpose of a CDCCL is to provide instruction to retain
the critical ignition source prevention feature during configuration
change that may be caused by alterations, repairs, or maintenance
actions. A CDCCL is not a periodic inspection.
Lockheed Service Bulletin 382-28-22 refers to the following service
bulletins as additional sources of service information for
accomplishing certain FSLs and CDCCLs:
Lockheed Service Bulletin 382-28-9, dated May 13, 1983,
which describes procedures for replacing the dump masts with new,
improved dump masts and installing heavy duty ground clamps and jumper
wires.
Lockheed Service Bulletin 382-28-19, Revision 3, dated
November 30, 2006, which describes procedures for (1) doing a visual
inspection of the ground/bonding jumpers for corrosion and/or incorrect
resistance, misplaced or inappropriately installed ground/bonding
jumpers, and repairing as necessary, (2) installing new ground/bonding
jumpers, (3) doing a visual inspection of the fuel system electrical
wires, (4) doing a visual inspection of the fuel tanks for
contamination, a visual inspection of all fuel tank internal wire
conduits for evidence of temperature discoloration or arcing through
the conduit wall, and replacing the wire conduit with new conduit if
necessary, (5) installing color-coded cable markers or heat shrink
sleeving on the fuel quantity indicating system (FQIS) wiring, and (6)
doing a zonal inspection of the dry bay areas and other areas, which
includes inspections of the electrical systems, all units essential to
safe operation, lightning protection, pneumatic system failures,
structural and non-electrical equipment bonding, fuel tank access panel
bonding, fuel system pumps, and fuel level control valve bonding.
Lockheed Service Bulletin 382-28-20, Revision 4, dated May
21, 2007, which describes procedures for replacing the vent lines of
the fuel tank with improved vent line assemblies having flame
arrestors, installing ground fault interrupters (GFIs) in the cargo
compartment and modifying the wiring to protect the fuel system pumps
from short-circuiting.
Lockheed Service Bulletin 382-28-21, Revision 2, dated
November 20, 2006, which describes procedures for installing lightning
bonding jumpers across the fuel system fittings and fuel tube bulkhead
feed-through joints.
Lockheed Service Bulletin 382-28-24, Revision 1, dated
November 5, 2007, which describes procedures for applying a certain
sealant to the interior of fuel tanks 1 and 4 and to all external fuel
tank nose caps, tail sections, and mid-section tank skins.
FAA's Determination and Requirements of This Proposed AD
We are proposing this AD because we evaluated all relevant
information and determined the unsafe condition described previously is
likely to exist or develop in other products of the(se) same type
design(s). This proposed AD would require revising the FAA-approved
maintenance program to incorporate the FSLs and CDCCLs specified in
Lockheed Service Bulletin 382-28-22. This proposed AD would also
require the accomplishment of certain fuel system modifications, the
initial inspections of certain repetitive FSLs to phase in those
inspections, and repair if necessary.
This proposed AD would also allow accomplishing the maintenance
program revision in accordance with later revisions of Lockheed Service
Bulletin 382-28-22 as an acceptable method of compliance if they are
approved by the Manager, Atlanta Aircraft Certification Office (ACO),
FAA.
Differences Between the Proposed AD and Service Bulletin
Paragraph 2.C.(1)(c) of Lockheed Service Bulletin 382-28-22
specifies to change the maintenance program to indicate that repetitive
inspections of the lightning and static bonding jumpers must be done in
accordance with Lockheed Service Bulletin 382-28-21. However, Lockheed
Service Bulletin 382-28-21 does not contain inspection procedures. The
applicable inspection procedures are contained in Lockheed Service
Bulletin 382-28-19. Therefore, paragraph (g)(2) of the proposed AD
specifies that the repetitive inspections must be done in accordance
with Lockheed Service Bulletin 382-28-19.
Paragraph 2.C.(4)(c) of Lockheed Service Bulletin 382-28-22
specifies to install identification cable markers or sleeving on the
FQIS wires in accordance with the Hercules wiring diagram manual.
However, Table 1 of this proposed AD refers to Lockheed Service
Bulletin 382-28-19 as an additional source of service information for
accomplishing that action, since Lockheed Service Bulletin 382-28-19
refers to the Hercules wiring diagram manual.
Where Lockheed Service Bulletin 382-28-19 specifies to do a visual
inspection, this proposed AD would require a general visual inspection.
We have included Note 2 in this proposed AD to define this type of
inspection.
Although Lockheed Service Bulletin 382-28-19 describes procedures
for notifying Lockheed of any discrepancies found during inspection,
this proposed AD would not require that action.
Explanation of Compliance Time
In most ADs, we adopt a compliance time allowing a specified amount
of time after the AD's effective date. In this case, however, the FAA
has already issued regulations that require operators to revise their
maintenance/inspection programs to address fuel tank safety issues. The
compliance date for these regulations is December 16, 2008. To provide
for efficient and coordinated implementation of these regulations and
this proposed AD, we are using that same compliance date in this
proposed AD.
Explanation of Comment Period
Operators should note that because of the critical need to prevent
the potential for ignition sources inside fuel tanks, we have
determined that a comment period of 30 days, rather than 45 days, is
necessary in this case.
Costs of Compliance
We estimate that this proposed AD would affect 21 airplanes of U.S.
registry. The following table provides the estimated costs, at an
average labor rate of $80 per hour, for U.S. operators to comply with
this proposed AD.
Estimated Costs
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Number of U.S.-
Action Work hours Parts Cost per registered Fleet cost
product airplanes
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Maintenance program revision.... 1 None $80 21 $1,680
Installation of new, improved 12 $10,288 11,248 21 236,208
fuel dump masts................
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Dry bay zonal inspection, 952 None 76,160 21 1,599,360
inspection and repair of static
ground terminals, marking of
FQIS wiring, initial inspection
of lightning and static bonding
jumpers........................
Installation of GFIs and flame 120 115,000 124,600 21 2,616,600
arrestors......................
Initial inspection of GFIs and 8 None 640 21 13,440
flame arrestors................
Installation of lightning 910 10,000 82,800 21 1,738,800
bonding jumpers................
Sealant application............. 320 None 25,600 21 537,600
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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), 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.
You can find our regulatory evaluation and the estimated costs of
compliance in the AD Docket.
List of Subjects in 14 CFR Part 39
Air transportation, Aircraft, Aviation safety, 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 AD:
Lockheed: Docket No. FAA-2008-0638; Directorate Identifier 2008-NM-
035-AD.
Comments Due Date
(a) We must receive comments by July 14, 2008.
Affected ADs
(b) None.
Applicability
(c) This AD applies to all Lockheed Model 382, 382B, 382E, 382F,
and 382G series airplanes, certificated in any category.
Note 1: This AD requires revisions to certain operator
maintenance documents to include new inspections. Compliance with
these inspections is required by 14 CFR 91.403(c). For airplanes
that have been previously modified, altered, or repaired in the
areas addressed by these inspections, the operator may not be able
to accomplish the inspections described in the revisions. In this
situation, to comply with 14 CFR 91.403(c), the operator must
request approval for an alternative method of compliance according
to paragraph (k) of this AD. The request should include a
description of changes to the required inspections that will ensure
the continued operational safety of the airplane.
Unsafe Condition
(d) This AD results from a design review of the fuel tank
systems. We are issuing this AD to prevent the potential for
ignition sources inside fuel tanks caused by latent failures,
alterations, repairs, or maintenance actions, which, in combination
with flammable fuel vapors, could result in a fuel tank explosion
and consequent loss of the airplane.
Compliance
(e) Comply with this AD within the compliance times specified,
unless already done.
Service Bulletin Reference
(f) The term ``service bulletin,'' as used in this AD, means the
Accomplishment Instructions of Lockheed Service Bulletin 382-28-22,
Revision 3, dated March 28, 2008.
Maintenance Program Revision
(g) Before December 16, 2008, revise the FAA-approved
maintenance program to incorporate the fuel system limitations
(FSLs) and the critical design configuration control limitations
(CDCCLs) specified in the Accomplishment Instructions of the service
bulletin; except as provided by paragraphs (g)(1), (g)(2), and
(g)(3) of this AD, and except that the modifications and initial
inspections specified in Table 1 of this AD must be done at the
compliance time specified in paragraph (h) of this AD.
(1) For the CDCCLs specified in paragraphs 2.C.(3)(c),
2.C.(3)(h), 2.C.(4)(a), 2.C.(5)(c), 2.C.(7)(h), and 2.C.(8) of the
service bulletin, do the applicable actions using a method approved
in accordance with the procedures specified in paragraph (k) of this
AD. Lockheed Service Bulletin 382-28-19, Revision 3, dated November
30, 2006, is one approved method.
(2) Where paragraph 2.C.(1)(c) of the service bulletin specifies
to change the maintenance program to indicate that repetitive
inspections of the lightning and static bonding jumpers must be done
in accordance with Lockheed Service Bulletin 382-28-21, instead do
the repetitive inspections in accordance with Lockheed Service
Bulletin 382-28-19, Revision 3, dated November 30, 2006.
(3) Where the service bulletin specifies to inspect, this AD
requires doing a general visual inspection.
Note 2: For the purposes of this AD, a general visual inspection
is: ``A visual examination of an interior or exterior area,
installation, or assembly to detect obvious damage, failure, or
irregularity. This level of inspection is made from within touching
distance unless otherwise specified. A mirror may be necessary to
ensure visual access to all surfaces in the inspection area. This
level of inspection is made under normally available lighting
conditions such as daylight, hangar lighting, flashlight, or
droplight and may require removal or
[[Page 33743]]
opening of access panels or doors. Stands, ladders, or platforms may
be required to gain proximity to the area being checked.''
Fuel System Modifications, Initial Inspections, and Repair if Necessary
(h) Within 24 months after the effective date of this AD, do the
applicable actions specified in Table 1 of this AD, and repair any
discrepancy before further flight, in accordance with the service
bulletin.
Table 1.--Modifications and Initial Inspections
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Additional source of service
Action information for accomplishing
the action
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For airplanes having any serial number Lockheed Service Bulletin 382-
prior to 4962: Install new, improved 28-9, dated May 13, 1983.
fuel dump masts in accordance with
paragraph 2.C.(1)(d) of the service
bulletin.
Mark the fuel quantity indicating Lockheed Service Bulletin 382-
system (FQIS) wires in accordance with 28-19, Revision 3, dated
paragraph 2.C.(1)(a)2, 2.C.(4)(b), and November 30, 2006.
2.C.(4)(c) of the service bulletin.
Do the dry bay zonal inspection and Lockheed Service Bulletin 382-
inspect the static ground terminals of 28-19, Revision 3, dated
the fuel system plumbing in accordance November 30, 2006.
with paragraph 2.C.(1)(a) of the
service bulletin.
Install ground fault interrupters Lockheed Service Bulletin 382-
(GFIs) and flame arrestors for 28-20, Revision 4, dated May
protection of the fuel system in 21, 2007.
accordance with paragraphs 2.C.(1)(b)
and 2.C.(7)(c) of the service bulletin.
Inspect the GFIs for protection of the Paragraph 2.C.(2) of the
fuel system in accordance with service bulletin.
paragraph 2.C.(1)(b)1 of the service
bulletin.
Install the lightning bonding jumpers Lockheed Service Bulletin 382-
(straps) in accordance with paragraphs 28-21, Revision 2, dated
2.C.(1)(c) and 2.C.(6)(a) of the November 20, 2006.
service bulletin.
Inspect the lightning and static Lockheed Service Bulletin 382-
bonding jumpers (straps) in accordance 28-19, Revision 3, dated
with paragraphs 2.C.(1)(c) of the November 30, 2006.
service bulletin.
Apply a certain sealant to the interior Lockheed Service Bulletin 382-
of the main wing fuel tanks; and apply 28-24, Revision 1, dated
a certain sealant to the all external November 5, 2007, including
fuel tank nose caps, mid sections, and the Errata Notice, dated
tail sections; as applicable; in January 7, 2008.
accordance with paragraphs
2.C.(1)(e)1, 2.C.(1)(e)3, and
2.C.(7)(i)1 of the service bulletin.
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No Alternative Inspections, Inspection Intervals, or CDCCLs
(i) After accomplishing the actions specified in paragraphs (g)
and (h) of this AD, no alternative inspections, inspection
intervals, or CDCCLs may be used unless the inspections, intervals,
or CDCCLs are part of a later revision of the service bulletin that
is approved by the Manager, Atlanta Aircraft Certification Office
(ACO), FAA; or unless the inspections, intervals, or CDCCLs are
approved as an alternative method of compliance in accordance with
the procedures specified in paragraph (k) of this AD.
No Reporting Requirement
(j) Although Lockheed Service Bulletin 382-28-19, Revision 3,
dated November 30, 2006, specifies to notify Lockheed of any
discrepancies found during inspection, this AD does not require that
action.
Alternative Methods of Compliance (AMOCs)
(k)(1) The Manager, Atlanta ACO, FAA, ATTN: Robert A. Bosak,
Aerospace Engineer, Propulsion and Services Branch, ACE-118A, FAA,
Atlanta Aircraft Certification Office, One Crown Center, 1895
Phoenix Boulevard, Suite 450, Atlanta, Georgia 30349; telephone
(770) 703-6094; fax (770) 703-6097; has the authority to approve
AMOCs for this AD, if requested using the procedures found in 14 CFR
39.19.
(2) To request a different method of compliance or a different
compliance time for this AD, follow the procedures in 14 CFR 39.19.
Before using any approved AMOC on any airplane to which the AMOC
applies, notify your appropriate principal inspector (PI) in the FAA
Flight Standards District Office (FSDO), or lacking a PI, your local
FSDO.
Issued in Renton, Washington, on June 9, 2008.
Ali Bahrami,
Manager, Transport Airplane Directorate, Aircraft Certification
Service.
[FR Doc. E8-13322 Filed 6-12-08; 8:45 am]
BILLING CODE 4910-13-P