Rule2023-25762
Airworthiness Directives; Lockheed Martin Corporation/Lockheed Martin Aeronautics Company Airplanes
Primary source
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Published
November 21, 2023
Effective
November 21, 2023
Issuing agencies
Transportation DepartmentFederal Aviation Administration
Abstract
The FAA is superseding Airworthiness Directive (AD) 96-12-20, which applied to certain Lockheed Martin Corporation/Lockheed Martin Aeronautics Company Model 382, 382B, 382E, 382F, and 382G airplanes. AD 96-12-20 required visual inspections to detect loose, missing, or deformed fasteners in the upper truss mounts of certain engines, visual inspections to detect cracking in the associated lugs, repetitive ultrasonic inspections to detect cracking of the upper lugs, and replacement of damaged or cracked parts. AD 96-12-20 also provided for an optional terminating action for the repetitive inspections. This AD was prompted by reports of fatigue cracking of the lugs of the upper truss mount, and by reports of cracks found prior to the initial inspection times required by AD 96-12-20 and the determination that the terminating action is no longer valid. This AD requires one-time inspections for cracked or severed engine truss mount upper lugs of the outboard engines, and replacement of the engine truss mount if necessary. This AD also revises the applicability to include all Model 382, 382B, 382E, 382F, and 382G airplanes, and all Model EC-130Q, C-130H, HP-C-130A, C-130A, and C-130B (including Model 282- 44A-05) airplanes. The FAA is issuing this AD to address the unsafe condition on these products.
Full Text
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<title>Federal Register, Volume 88 Issue 223 (Tuesday, November 21, 2023)</title>
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[Federal Register Volume 88, Number 223 (Tuesday, November 21, 2023)]
[Rules and Regulations]
[Pages 80952-80955]
From the Federal Register Online via the Government Publishing Office [<a href="http://www.gpo.gov">www.gpo.gov</a>]
[FR Doc No: 2023-25762]
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DEPARTMENT OF TRANSPORTATION
Federal Aviation Administration
14 CFR Part 39
[Docket No. FAA-2023-2140; Project Identifier AD-2023-01071-T;
Amendment 39-22590; AD 2023-22-06]
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 superseding Airworthiness Directive (AD) 96-12-20,
which applied to certain Lockheed Martin Corporation/Lockheed Martin
Aeronautics Company Model 382, 382B, 382E, 382F, and 382G airplanes. AD
96-12-20 required visual inspections to detect loose, missing, or
deformed fasteners in the upper truss mounts of certain engines, visual
inspections to detect cracking in the associated lugs, repetitive
ultrasonic inspections to detect cracking of the upper lugs, and
replacement of damaged or cracked parts. AD 96-12-20 also provided for
an optional terminating action for the repetitive inspections. This AD
was prompted by reports of fatigue cracking of the lugs of the upper
truss mount, and by reports of cracks found prior to the initial
inspection times required by AD 96-12-20 and the determination that the
terminating action is no longer valid. This AD requires one-time
inspections for cracked or severed engine truss mount upper lugs of the
outboard engines, and replacement of the engine truss mount if
necessary. This AD also revises the applicability to include all Model
382, 382B, 382E, 382F, and 382G airplanes, and all Model
[[Page 80953]]
EC-130Q, C-130H, HP-C-130A, C-130A, and C-130B (including Model 282-
44A-05) airplanes. The FAA is issuing this AD to address the unsafe
condition on these products.
DATES: This AD is effective November 21, 2023.
The FAA must receive comments on this AD by January 5, 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-2023-2140; 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; phone: 404-474-5507;
email: <a href="/cdn-cgi/l/email-protection#271e0a6674680a66736b6664680a6663546741464609404851"><span class="__cf_email__" data-cfemail="3d04107c6e72107c69717c7e72107c794e7d5b5c5c135a524b">[email protected]</span></a>.
SUPPLEMENTARY INFORMATION:
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-2023-2140 and Project Identifier
AD-2023-01071-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; phone: 404-474-5507; email: <a href="/cdn-cgi/l/email-protection#c5fce884968ae884918984868ae88481b685a3a4a4eba2aab3"><span class="__cf_email__" data-cfemail="f2cbdfb3a1bddfb3a6beb3b1bddfb3b681b2949393dc959d84">[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.
Background
The FAA issued AD 96-12-20, Amendment 39-9663 (61 FR 29279, June
10, 1996; corrected August 16, 1996 (61 FR 42549)) (AD 96-12-20), for
certain Lockheed Martin Corporation/Lockheed Martin Aeronautics Company
Model 382, 382B, 382E, 382F, and 382G airplanes. AD 96-12-20 required
visual inspections to detect loose, missing, or deformed fasteners in
the upper truss mounts of certain engines; inspections to detect
cracking in the associated lugs; repetitive ultrasonic inspections to
detect cracking of the upper lugs; and replacement of damaged and
cracked parts. This amendment also provides for an optional terminating
action for the repetitive inspections. AD 96-12-20 was prompted by
reports of fatigue cracking of the lugs of the upper truss mount. The
FAA issued AD 96-12-20 to prevent multiple failures of the upper truss
mounts due to problems associated with fatigue cracking, which could
adversely affect the integrity of the engine mount structure.
Actions Since AD 96-12-20 Was Issued
Since the FAA issued AD 96-12-20, the FAA has been notified of
additional crack findings in engine truss mount upper lugs occurring
prior to the initial inspection times required by AD 96-12-20. The
cracks were found to have progressed entirely through these parts and
have been found on multiple airplanes. In addition, modified parts,
required by the terminating action in AD 96-12-20, that were intended
to have a longer operational life have not resulted in longer periods
before cracks occur; therefore, the previous terminating action is not
valid, and airplanes on which the terminating action was done must be
inspected. The restricted category models EC-130Q, C-130H, HP-C-130A,
C-130A, and C-130B (including Model 282-44A-05) were added to the Model
382 airplanes affected by AD 96-12-20, since they share the same type
design in the area where cracking is occurring. Fatigue cracking of a
single engine truss mount upper lug could reduce the static strength of
an engine mount to limit load, while cracking of both lugs can lead to
separation of the engine, catastrophic structural damage, and 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
This AD does not retain the requirements of AD 96-12-20. This AD
revises the applicability of AD 96-12-20 by expanding to all Model 382,
382B, 382E, 382F, and 382G airplanes, and adding Model EC-130Q, C-130H,
HP-C-130A, C-130A, and C-130B (including Model 282-44A-05) airplanes.
This AD requires one-time inspections to detect cracking of the No. 1
and No. 4 engine truss mount upper lugs, lower surfaces, at outer wing
station (OWS) 162 and OWS 197; cracking of the No. 1 and No. 4 engine
truss mount upper lug side surfaces, inboard and outboard, at OWS 162
and OWS 197; and severed engine truss mount upper lugs; and replacement
of the engine truss mount if found with cracked or severed engine truss
mount upper lugs.
Interim Action
The FAA considers this AD to be an interim action. If final action
is later identified, the FAA might consider further rulemaking then.
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
earliest possible stages of AD development. This AD is based on those
considerations, and was developed with
[[Page 80954]]
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 fatigue cracking of a single engine truss mount upper lug
reduces the static strength of an engine mount to limit load, while
cracking of both lugs can lead to separation of the engine,
catastrophic structural damage, and loss of control of the airplane.
Further, based upon the additional applicability of affected airplanes
and the previously insufficient service information, it is likely that
further fatigue cracking and reduction in static strength has occurred
and could result in imminent separation of the engine, catastrophic
structural damage, and loss of control of the airplane. Finally, the
compliance time for the required action is shorter than the time
necessary for the public to comment and for publication of the final
rule. 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.
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 41 airplanes of U.S.
registry. The FAA estimates the following costs to comply with this AD:
Estimated Costs
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Cost per Cost on U.S.
Action Labor cost Parts cost product operators
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Inspections........................... 10 work-hours x $85 per $0 $850 $34,850
hour = $850.
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The FAA has received no definitive data on which to base the cost
estimates for the on-condition actions 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
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:
a. Removing Airworthiness Directive (AD) AD 96-12-20, Amendment 39-9663
(61 FR 29279, June 10, 1996; corrected August 16, 1996 (61 FR 42549));
and
b. Adding the following new AD:
2023-22-06 Lockheed Martin Corporation/Lockheed Martin Aeronautics
Company: Amendment 39-22590; Docket No. FAA-2023-2140; Project
Identifier AD-2023-01071-T.
(a) Effective Date
This airworthiness directive (AD) is effective November 21,
2023.
(b) Affected ADs
This AD replaces AD 96-12-20, Amendment 39-9663 (61 FR 29279,
June 10, 1996; corrected August 16, 1996 (61 FR 42549)) (AD 96-12-
20).
(c) Applicability
This AD applies to the airplanes identified in paragraphs (c)(1)
and (2) of this AD.
(1) All Lockheed Martin Corporation/Lockheed Martin Aeronautics
Company Model 382, 382B, 382E, 382F, and 382G airplanes,
certificated in any category.
[[Page 80955]]
(2) All airplanes specified in paragraphs (c)(2)(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 71, Powerplant.
(e) Unsafe Condition
This AD was prompted by reports of fatigue cracking of an upper
lug of the engine truss mount, and by reports of cracks found prior
to the initial inspection times required by AD 96-12-20. The FAA is
issuing this AD to address such fatigue cracking. Fatigue cracking
of a single engine truss mount upper lug could reduce the static
strength of an engine mount to limit load, while cracking of both
lugs can lead to separation of the engine, catastrophic structural
damage, and loss of control of the airplane.
(f) Compliance
Comply with this AD within the compliance times specified,
unless already done.
(g) Required Actions
Within 35 days after the effective date of this AD, do the
inspections specified in paragraphs (g)(1) and (2) of this AD, using
a method approved in accordance with the procedures specified in
paragraph (i) of this AD. If any cracked or severed engine truss
mount upper lug is found, the engine truss mount must be replaced
before further flight, using a method approved in accordance with
the procedures specified in paragraph (i) of this AD.
(1) Do a one-time detailed visual inspection for cracking of the
No. 1 and No. 4 engine truss mount upper lugs, lower surfaces, at
outer wing station (OWS) 162 and OWS 197; and for severed engine
truss mount upper lugs; at a total of four locations: two locations
per engine mount, one mount assembly at each OWS.
(2) Do a one-time borescope inspection for cracking of the No. 1
and No. 4 engine truss mount upper lug side surfaces, inboard and
outboard, at OWS 162 and OWS 197; and for severed engine truss mount
upper lugs; at a total of eight locations: two locations per engine
truss mount lug, two lugs per engine, one mount assembly at each
OWS.
Note 1 to paragraph (g): Guidance for accomplishing the
inspections and replacement can be found in Lockheed Martin
Aeronautics Company Alert Service Bulletin A382-57-103, dated
October 19, 2023.
(h) 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
inspections required by this AD can be performed, but special flight
permits may not be issued to operate the airplane after a visual or
borescope inspection has identified a cracked or severed lug, unless
the operator contacts the Manager, East Certification Branch, FAA,
for specific limitations that must be followed and complies with
those limitations.
(i) 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 (j) 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.
(j) Related Information
(1) For more information about this AD, contact Fred Caplan,
Aviation Safety Engineer, FAA, 1701 Columbia Avenue, College Park,
GA 30337; phone: 404-474-5507; email: <a href="/cdn-cgi/l/email-protection#e1d8cca0b2aecca0b5ada0a2aecca0a592a1878080cf868e97"><span class="__cf_email__" data-cfemail="427b6f03110d6f03160e03010d6f030631022423236c252d34">[email protected]</span></a>.
(2) For Lockheed Martin Aeronautics Company 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#fe9f938dd08e918c8a9f92be92939d91d09d9193"><span class="__cf_email__" data-cfemail="03626e702d736c7177626f436f6e606c2d606c6e">[email protected]</span></a>. You may view this service information at
the FAA, Airworthiness Products Section, Operational Safety Branch,
2200 South 216th St., Des Moines, WA. For information on the
availability of this material at the FAA, call 206-231-3195.
(k) Material Incorporated by Reference
None.
Issued on November 16, 2023.
Ross Landes,
Deputy Director for Regulatory Operations, Compliance & Airworthiness
Division, Aircraft Certification Service.
[FR Doc. 2023-25762 Filed 11-17-23; 4:15 pm]
BILLING CODE 4910-13-P
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