
[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).

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

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

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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
------------------------------------------------------------------------
                                           Additional source of service
                 Action                   information for accomplishing
                                                    the action
------------------------------------------------------------------------
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.
------------------------------------------------------------------------

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
