Rule2024-00300
Airworthiness Directives; Lockheed Martin Corporation/Lockheed Martin Aeronautics Company Airplanes
Primary source
Metadata and text below are from the Federal Register, a public-domain U.S. government work. Always verify the official published version before relying on it for any legal matter.
Published
January 9, 2024
Effective
January 24, 2024
Issuing agencies
Transportation DepartmentFederal Aviation Administration
Abstract
The FAA is adopting a new airworthiness directive (AD) for all Lockheed Martin Corporation/Lockheed Martin Aeronautics Company Model 382, 382B, 382E, 382F, 382G, and 382J airplanes; and Model C-130A, HP- C-130A, EC-130Q, 282-44A-05 (C-130B), C-130B, and C-130H airplanes. This AD was prompted by the determination that certain aft fuselage sloping longerons may have been exposed to excessively hot forming temperatures for excessive amounts of time, which will reduce the mechanical properties of the longerons and affect their static strength. This AD requires, for certain airplanes, a records review to determine if a conductivity check has been performed on the longerons and to determine if the check was measured at least every four inches. This AD also requires, for certain airplanes, an inspection and applicable repairs. This AD also prohibits installation of affected parts under certain conditions. The FAA is issuing this AD to address the unsafe condition on these products.
Full Text
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<title>Federal Register, Volume 89 Issue 6 (Tuesday, January 9, 2024)</title>
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[Federal Register Volume 89, Number 6 (Tuesday, January 9, 2024)]
[Rules and Regulations]
[Pages 1030-1033]
From the Federal Register Online via the Government Publishing Office [<a href="http://www.gpo.gov">www.gpo.gov</a>]
[FR Doc No: 2024-00300]
[[Page 1030]]
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DEPARTMENT OF TRANSPORTATION
Federal Aviation Administration
14 CFR Part 39
[Docket No. FAA-2024-0027; Project Identifier AD-2023-01202-T;
Amendment 39-22653; AD 2024-01-02]
RIN 2120-AA64
Airworthiness Directives; Lockheed Martin Corporation/Lockheed
Martin Aeronautics Company Airplanes
AGENCY: Federal Aviation Administration (FAA), DOT.
ACTION: Final rule; request for comments.
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SUMMARY: The FAA is adopting a new airworthiness directive (AD) for all
Lockheed Martin Corporation/Lockheed Martin Aeronautics Company Model
382, 382B, 382E, 382F, 382G, and 382J airplanes; and Model C-130A, HP-
C-130A, EC-130Q, 282-44A-05 (C-130B), C-130B, and C-130H airplanes.
This AD was prompted by the determination that certain aft fuselage
sloping longerons may have been exposed to excessively hot forming
temperatures for excessive amounts of time, which will reduce the
mechanical properties of the longerons and affect their static
strength. This AD requires, for certain airplanes, a records review to
determine if a conductivity check has been performed on the longerons
and to determine if the check was measured at least every four inches.
This AD also requires, for certain airplanes, an inspection and
applicable repairs. This AD also prohibits installation of affected
parts under certain conditions. The FAA is issuing this AD to address
the unsafe condition on these products.
DATES: This AD is effective January 24, 2024.
The FAA must receive comments on this AD by February 23, 2024.
ADDRESSES: You may send comments, using the procedures found in 14 CFR
11.43 and 11.45, by any of the following methods:
<bullet> Federal eRulemaking Portal: Go to <a href="http://regulations.gov">regulations.gov</a>. Follow
the instructions for submitting comments.
<bullet> Fax: 202-493-2251.
<bullet> 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.
<bullet> Hand Delivery: Deliver to Mail address above between 9
a.m. and 5 p.m., Monday through Friday, except Federal holidays.
AD Docket: You may examine the AD docket at <a href="http://regulations.gov">regulations.gov</a> by
searching for and locating Docket No. FAA-2024-0027; or in person at
Docket Operations between 9 a.m. and 5 p.m., Monday through Friday,
except Federal holidays. The AD docket contains this final rule, any
comments received, and other information. The street address for Docket
Operations is listed above.
FOR FURTHER INFORMATION CONTACT: Fred Caplan, Aviation Safety Engineer,
FAA, 1701 Columbia Avenue, College Park, GA 30337; telephone 404-474-
5507; email <a href="/cdn-cgi/l/email-protection#083125495b4725495c44494b4725494c7b486e6969266f677e"><span class="__cf_email__" data-cfemail="536a7e12001c7e12071f12101c7e121720133532327d343c25">[email protected]</span></a>.
SUPPLEMENTARY INFORMATION:
Background
The FAA previously issued AD 2023-11-10, Amendment 39-22456 (88 FR
41308, June 26, 2023) (AD 2023-11-10), for all Lockheed Martin
Corporation/Lockheed Martin Aeronautics Company Model 382, 382B, 382E,
382F, 382G, and 382J airplanes; and Model C-130A, HP-C-130A, EC-130Q,
282-44A-05 (C-130B), C-130B, and C-130H airplanes. AD 2023-11-10
requires, for certain airplanes, a review of the airplane maintenance
records to determine if the left or right aft fuselage sloping
longeron, having part number (P/N) 342986-( ), has been replaced on or
after December 31, 2012. AD 2023-11-10 also requires a conductivity
check on certain aft fuselage sloping longerons and applicable on-
condition actions, and prohibits the installation of certain aft
fuselage sloping longerons under certain conditions. Lockheed
determined that those longerons may have been exposed to excessively
hot forming temperatures for excessive amounts of time during
manufacturing. Exposure to the higher temperatures and extended time
will reduce the mechanical properties of the longerons and affect their
static strength. If both aft fuselage sloping longerons are
understrength, the structural integrity of the airplane would be
reduced below limit load, which could lead to failure of both
longerons.
Lockheed engineering analysis has since identified an increased
minimum acceptable hardness (above that required by AD 2023-11-10)
necessary to maintain a positive margin of safety from fuselage station
(FS) 750 to FS 770. In addition, Lockheed Martin engineering analysis
has since identified the vertical flange as the critical location, and
this location was not previously tested. As a result, Lockheed Martin
Aeronautics Company issued Alert Service Bulletin A382-53-70, dated
November 20, 2023, to provide procedures for a conductivity check and
hardness test, as applicable, for all affected airplanes, except for
Model 382J airplanes.
Lockheed has advised that related testing has been completed on all
Model 382J airplanes (there are currently five total Model 382J
airplanes), and that the test results have adequately determined that
the aft fuselage sloping longerons meet specifications and the unsafe
condition does not currently exist on Model 382J airplanes. Those
airplanes are therefore not included in paragraph (g) of this AD.
However, the parts installation limitation in paragraph (h)(2) of this
AD does apply to the Model 382J airplanes.
The FAA is issuing this AD to address a defective aft fuselage
sloping longeron, which could eventually fail, resulting in reduced
structural integrity of the airplane and possible loss of control of
the airplane.
FAA's Determination
The FAA is issuing this AD because the agency has determined the
unsafe condition described previously is likely to exist or develop in
other products of the same type design.
AD Requirements
For airplanes (except Model 382J airplanes) on which the left- or
right-hand aft fuselage sloping longeron, P/N 342986-( ), was replaced
on or after December 31, 2012, and for airplanes (except Model 382J
airplanes) on which a review of the airplane maintenance records cannot
conclusively determine whether the part has been replaced, this AD
requires a review of the airplane maintenance records to determine if a
conductivity check has been performed on both left- and right-hand aft
fuselage sloping longerons part number 342986-( ), from fuselage
station (FS) 750 to FS 770, as specified in Lockheed Martin Aeronautics
Company Alert Service Bulletin A382-53-69, dated April 12, 2023, and to
determine if the check was measured at least every four inches. This AD
also requires, for certain airplanes, an inspection of the airplane and
applicable repairs that must be done using a method approved by the
Manager, FAA East Certification Branch. The inspection could include a
conductivity check, a hardness test, and a verification that results
are within certain values.
This AD also prohibits installation of affected parts under certain
conditions.
Impact on Intrastate Aviation in Alaska
In light of the heavy reliance on aviation for intrastate
transportation in Alaska, the FAA fully considered the effects of this
AD (including costs to be borne by affected operators) from the
[[Page 1031]]
earliest possible stages of AD development. This AD is based on those
considerations, and was developed with regard to minimizing the
economic impact on operators to the extent possible, consistent with
the safety objectives of this AD. In any event, the Federal Aviation
Regulations require operators to correct an unsafe condition identified
on an airplane to ensure operation of that airplane in an airworthy
condition. The FAA has determined in this case that the requirements
are necessary and the indirect costs would be outweighed by the safety
benefits of the AD.
Justification for Immediate Adoption and Determination of the Effective
Date
Section 553(b)(3)(B) of the Administrative Procedure Act (APA) (5
U.S.C. 551 et seq.) authorizes agencies to dispense with notice and
comment procedures for rules when the agency, for ``good cause,'' finds
that those procedures are ``impracticable, unnecessary, or contrary to
the public interest.'' Under this section, an agency, upon finding good
cause, may issue a final rule without providing notice and seeking
comment prior to issuance. Further, section 553(d) of the APA
authorizes agencies to make rules effective in less than thirty days,
upon a finding of good cause.
An unsafe condition exists that requires the immediate adoption of
this AD without providing an opportunity for public comments prior to
adoption. The FAA has found that the risk to the flying public
justifies forgoing notice and comment prior to adoption of this rule
because numerous understrength aft fuselage sloping longerons have been
found on military airplanes of the same type design, and it is likely
that understrength longerons are also installed on in-service
airplanes. The possibility of both longerons being understrength
violates fail-safe design. If both aft fuselage sloping longerons are
understrength, the structural integrity of the airplane would be
reduced below limit load, which could lead to failure of both longerons
and result in loss of the airplane. Accordingly, notice and opportunity
for prior public comment are impracticable and contrary to the public
interest pursuant to 5 U.S.C. 553(b)(3)(B).
In addition, the FAA finds that good cause exists pursuant to 5
U.S.C. 553(d) for making this amendment effective in less than 30 days,
for the same reasons the FAA found good cause to forgo notice and
comment.
Comments Invited
The FAA invites you to send any written data, views, or arguments
about this final rule. Send your comments to an address listed under
ADDRESSES. Include Docket No. FAA-2024-0027 and Project Identifier AD-
2023-01202-T at the beginning of your comments. The most helpful
comments reference a specific portion of the final rule, explain the
reason for any recommended change, and include supporting data. The FAA
will consider all comments received by the closing date and may amend
this final rule because of those comments.
Except for Confidential Business Information (CBI) as described in
the following paragraph, and other information as described in 14 CFR
11.35, the FAA will post all comments received, without change, to
<a href="http://regulations.gov">regulations.gov</a>, including any personal information you provide. The
agency will also post a report summarizing each substantive verbal
contact received about this final rule.
Confidential Business Information
CBI is commercial or financial information that is both customarily
and actually treated as private by its owner. Under the Freedom of
Information Act (FOIA) (5 U.S.C. 552), CBI is exempt from public
disclosure. If your comments responsive to this AD contain commercial
or financial information that is customarily treated as private, that
you actually treat as private, and that is relevant or responsive to
this AD, it is important that you clearly designate the submitted
comments as CBI. Please mark each page of your submission containing
CBI as ``PROPIN.'' The FAA will treat such marked submissions as
confidential under the FOIA, and they will not be placed in the public
docket of this AD. Submissions containing CBI should be sent to Fred
Caplan, Aviation Safety Engineer, FAA, 1701 Columbia Avenue, College
Park, GA 30337; telephone 404-474-5507; email <a href="/cdn-cgi/l/email-protection#1c25315d4f53315d48505d5f53315d586f5c7a7d7d327b736a"><span class="__cf_email__" data-cfemail="fac3d7bba9b5d7bbaeb6bbb9b5d7bbbe89ba9c9b9bd49d958c">[email protected]</span></a>.
Any commentary that the FAA receives that is not specifically
designated as CBI will be placed in the public docket for this
rulemaking.
Regulatory Flexibility Act
The requirements of the Regulatory Flexibility Act (RFA) do not
apply when an agency finds good cause pursuant to 5 U.S.C. 553 to adopt
a rule without prior notice and comment. Because the FAA has determined
that it has good cause to adopt this rule without notice and comment,
RFA analysis is not required.
Costs of Compliance
The FAA estimates that this AD affects 36 airplanes of U.S.
registry. The FAA estimates the following costs to comply with this AD:
Estimated Costs
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Action Labor cost Parts cost Cost per product Cost on U.S. operators
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Records review........... 1 work-hour x $0 $85...................... $3,060.
$85 per hour =
$85.
Inspection *............. Up to 20 work- 0 Up to $1,700............. Up to $61,200.
hours x $85 per
hour = Up to
$1,700.
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* The inspection could include a conductivity check, a hardness test, and a verification that results are within
certain values.
The FAA has received no definitive data on which to base the cost
estimates for the on-condition repair specified in this AD.
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.
The FAA is 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
This AD will not have federalism implications under Executive Order
[[Page 1032]]
13132. This AD will 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 that this AD is not a
``significant regulatory action'' under Executive Order 12866.
List of Subjects in 14 CFR Part 39
Air transportation, Aircraft, Aviation safety, Incorporation by
reference, Safety.
The Amendment
Accordingly, under the authority delegated to me by the
Administrator, the FAA amends 14 CFR part 39 as follows:
PART 39--AIRWORTHINESS DIRECTIVES
0
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]
0
2. The FAA amends Sec. 39.13 by adding the following new airworthiness
directive:
2024-01-02 Lockheed Martin Corporation/Lockheed Martin Aeronautics
Company: Amendment 39-22653; Docket No. FAA-2024-0027; Project
Identifier AD-2023-01202-T.
(a) Effective Date
This airworthiness directive (AD) is effective January 24, 2024.
(b) Affected ADs
This AD affects AD 2023-11-10, Amendment 39-22456 (88 FR 41308,
June 26, 2023) (AD 2023-11-10).
(c) Applicability
This AD applies to the airplanes identified in paragraphs (c)(1)
through (3) of this AD.
(1) All Lockheed Martin Corporation/Lockheed Martin Aeronautics
Company Model 382, 382B, 382E, 382F, and 382G airplanes,
certificated in any category.
(2) All Lockheed Martin Corporation/Lockheed Martin Aeronautics
Company Model 382J airplanes, certificated in any category.
(3) All airplanes specified in paragraphs (c)(3)(i) through (xi)
of this AD, type certificated in the restricted category.
(i) LeSEA Model C-130A airplanes (transferred from Central Air
Services, Inc.), Type Certificate Data Sheet (TCDS) A34SO, Revision
1.
(ii) T.B.M., Inc., Model C-130A airplanes, TCDS A39CE, Revision
3.
(iii) Western International Aviation, Inc., Model C-130A
airplanes, TCDS A33NM.
(iv) USDA Forest Service Model C-130A airplanes, TCDS A15NM,
Revision 4.
(v) Snow Aviation International, Inc., Model C-130A airplanes,
TCDS TQ3CH, Revision 1.
(vi) International Air Response (transferred from Rogers
Helicopters, Inc., and Heavylift Helicopters Inc.) Model C-130A
airplanes, TCDS A31NM, Revision 3.
(vii) Heavylift Helicopters, Inc., Model C-130B airplanes, TCDS
A35NM, Revision 1.
(viii) Hawkins & Powers Aviation, Inc., Model HP-C-130A
airplanes, TCDS A30NM, Revision 1.
(ix) Coulson Aviation (USA), Inc., Model EC-130Q and C-130H
airplanes, TCDS T00019LA, Revision 4.
(x) Lockheed-Georgia Company Model 282-44A-05 (C-130B)
airplanes, TCDS A5SO.
(xi) Surplus Model C-130A airplanes.
(d) Subject
Air Transport Association (ATA) of America Code 53, Fuselage.
(e) Unsafe Condition
This AD was prompted by the determination that certain aft
fuselage sloping longerons may have been exposed to excessively hot
forming temperatures for excessive amounts of time, which will
reduce the mechanical properties of the longerons and affect their
static strength. The FAA is issuing this AD to address the
possibility of both aft sloping longerons being understrength, which
would reduce the structural integrity of the airplane below limit
load (i.e., maximum load to be expected in service) and could lead
to failure of both longerons. The unsafe condition, if not
addressed, could result loss of the airplane.
(f) Compliance
Comply with this AD within the compliance times specified,
unless already done.
(g) Records Review and Applicable Actions
For airplanes identified in paragraphs (c)(1) and (3) of this AD
on which the left- or right-hand aft fuselage sloping longeron, P/N
342986-( ), was replaced on or after December 31, 2012, and
airplanes identified in paragraphs (c)(1) and (3) of this AD on
which a review of the airplane maintenance records cannot
conclusively determine whether the part has been replaced: Do the
actions specified in both paragraphs (g)(1) and (2) of this AD.
(1) Within 35 days after the effective date of this AD, review
the airplane maintenance records to determine if a conductivity
check has been performed on both left- and right-hand aft fuselage
sloping longerons part number 342986-( ), from fuselage station (FS)
750 to FS 770, as specified in Lockheed Martin Aeronautics Company
Alert Service Bulletin A382-53-69, dated April 12, 2023, and to
determine if the check was measured at least every four inches.
(2) Within 90 days after the effective date of this AD, inspect
the airplane and do all applicable repairs using a method approved
by the Manager, FAA East Certification Branch.
(h) Parts Installation Limitation
(1) For airplanes identified in paragraphs (c)(1) and (3) of
this AD: As of the effective date of this AD, no person may install
an aft fuselage sloping longeron part number 342986-( ) on any
airplane, unless all applicable actions specified in paragraph (g)
of this AD have been accomplished. The parts installation limitation
required by this paragraph replaces the parts installation
limitation required by paragraph (n)(1) of AD 2023-11-10.
(2) For airplanes identified in paragraph (c)(2) of this AD: As
of the effective date of this AD, no person may install an aft
fuselage sloping longeron part number 342986-( ) on any airplane,
unless a conductivity check has been performed on the aft fuselage
sloping longeron, from fuselage station (FS) 750 to FS 770, using a
method approved by the Manager, FAA, East Certification Branch. The
parts installation limitation required by this paragraph replaces
the parts installation limitation required by paragraph (n)(2) of AD
2023-11-10.
(i) Special Flight Permit
Special flight permits may be issued in accordance with 14 CFR
21.197 and 21.199 to operate the airplane to a location where the
actions required by this AD can be performed, but special flight
permits may not be issued to operate the airplane after the actions
required by this AD have identified an aft fuselage sloping longeron
that does not meet the applicable requirements, unless the operator
contacts the Manager, East Certification Branch, FAA, for specific
limitations that must be followed and complies with those
limitations.
(j) Alternative Methods of Compliance (AMOCs)
(1) The Manager, East Certification Branch, 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 responsible Flight
Standards Office, as appropriate. If sending information directly to
the manager of the certification office, send it to the attention of
the person identified in paragraph (k)(1) of this AD.
(2) Before using any approved AMOC, notify your appropriate
principal inspector, or lacking a principal inspector, the manager
of the responsible Flight Standards Office.
(k) Related Information
(1) For more information about this AD, contact Fred Caplan,
Aviation Safety Engineer, FAA, 1701 Columbia Avenue, College Park,
GA 30337; telephone 404-474-5507; email <a href="/cdn-cgi/l/email-protection#f0c9ddb1a3bfddb1a4bcb1b3bfddb1b483b0969191de979f86"><span class="__cf_email__" data-cfemail="4e77630f1d01630f1a020f0d01630f0a3d0e282f2f60292138">[email protected]</span></a>.
(2) For Lockheed service information identified in this AD that
is not incorporated by reference, contact Lockheed Martin
Corporation/Lockheed Martin Aeronautics Company, Airworthiness
Office, Dept. 6A0M, Zone 0252, Column P-58, 86 S Cobb Drive,
Marietta, GA 30063; telephone 770-494-5444; fax 770-494-5445; email
<a href="/cdn-cgi/l/email-protection#73121e005d031c0107121f331f1e101c5d101c1e"><span class="__cf_email__" data-cfemail="a0c1cdd38ed0cfd2d4c1cce0cccdc3cf8ec3cfcd">[email protected]</span></a>. You may view this service information at the
FAA, Airworthiness Products Section, Operational Safety Branch,
[[Page 1033]]
2200 South 216th St., Des Moines, WA. For information on the
availability of this material at the FAA, call 206-231-3195.
(l) Material Incorporated by Reference
None.
Issued on January 4, 2024.
Ross Landes,
Deputy Director for Regulatory Operations, Compliance & Airworthiness
Division, Aircraft Certification Service.
[FR Doc. 2024-00300 Filed 1-5-24; 11:15 am]
BILLING CODE 4910-13-P
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