[Federal Register Volume 59, Number 23 (Thursday, February 3, 1994)]
[Unknown Section]
[Page 0]
From the Federal Register Online via the Government Publishing Office [www.gpo.gov]
[FR Doc No: 94-1691]
[[Page Unknown]]
[Federal Register: February 3, 1994]
-----------------------------------------------------------------------
DEPARTMENT OF TRANSPORTATION
14 CFR Part 39
[Docket No. 94-NM-04-AD; Amendment 39-8809; AD 94-03-03]
Airworthiness Directives; Lockheed Model 382, 382B, 382E, 382F,
and 382G Series Airplanes
AGENCY: Federal Aviation Administration, DOT.
ACTION: Final rule; request for comments.
-----------------------------------------------------------------------
SUMMARY: This amendment adopts a new airworthiness directive (AD) that
is applicable to certain Lockheed Model 382, 382B, 382E, 382F, and 382G
series airplanes. This action requires inspections to detect loose,
missing, or deformed fasteners in the upper truss mounts of certain
engines, inspections to detect cracking in the associated tangs, and
replacement of damaged parts with new or serviceable parts. This
amendment is prompted by a report of fatigue cracking of the upper tang
of the truss mounts. The actions specified in this AD are intended to
prevent multiple failures of the upper truss mounts due to the problems
associated with fatigue cracking, which could adversely affect the
integrity of the engine mount structure.
DATES: Effective February 18, 1994. -
The incorporation by reference of certain publications listed in
the regulations is approved by the Director of the Federal Register as
of February 18, 1994. -
Comments for inclusion in the Rules Docket must be received on or
before April 4, 1994.
ADDRESSES: Submit comments in triplicate to the Federal Aviation
Administration (FAA), Transport Airplane Directorate, ANM-103,
Attention: Rules Docket No. 94-NM-04-AD, 1601 Lind Avenue, SW., Renton,
Washington 98055-4056. -
The service information referenced in this AD may be obtained from
Lockheed Western Export Company (LWEC), Zone 0755, 86 South Cobb Drive,
Marietta, Georgia 30063-0755. This information may be examined at the
FAA, Transport Airplane Directorate, 1601 Lind Avenue, SW., Renton,
Washington; or at the FAA, Small Airplane Directorate, Atlanta Aircraft
Certification Office, suite 210C, 1669 Phoenix Parkway, Atlanta,
Georgia; or at the Office of the Federal Register, 800 North Capitol
Street, NW., suite 700, Washington, DC.
FOR FURTHER INFORMATION CONTACT: Thomas Peters, Aerospace Engineer,
Flight Test Branch, ACE-160A, FAA, Small Airplane Directorate, Atlanta
Aircraft Certification Office, suite 210C, 1669 Phoenix Parkway,
Atlanta, Georgia 30349; telephone (404) 991-3915; fax (404) 991-3606.
SUPPLEMENTARY INFORMATION: Recently, the operator of Lockheed Model C-
130 (military) series airplanes reported that, during routine
maintenance inspections, the truss mounts on the upper tangs on the
outboard engines of several airplanes were found to be cracked. These
airplanes had accumulated between 9,000 and 14,000 total hours time-in-
service. Since these military airplanes are typically subjected to more
rigorous flight operations (such as low level penetration, air drop,
and soft landings during training missions) than their civilian
aircraft counterparts, the fatigue life of the components on these
military airplanes are affected more adversely. These findings of
cracking, which have been attributed to fatigue, were found in the
upper attach fittings between the engine truss mounts and the front
wing spars. This cracking occurred in the tangs that penetrate the
front wing spars and progressed to the point of overload failure. -
Similar cracking was also found on a civilian Model 382G series
airplane that had accumulated approximately 23,000 total hours time-in-
service.
Complete fracture of a single upper truss mount would not adversely
affect the fail-safe structure of the airplane; however, the effect on
the fatigue life of the remaining upper truss mount is unknown at this
time. Additional failures of the upper truss mount, if not corrected,
could adversely affect the integrity of the engine mount structure.
The engine mountings on the military Model C-130 and the civilian
Model 382G series airplanes are identical in design to the mountings on
civilian Model 382, 382B, 382E, and 382F series airplanes on which the
outer wings have been replaced in accordance with Manufacturing End
Product (MEP) 12R/13R or MEP 9T/10T. Although cracking has not been
found on these specific civilian airplanes, the FAA has determined that
those airplanes could be subject to the same type of fatigue cracking
in the subject engine mounts that was found in the military airplanes
and in the civilian Model 382G series airplane.
Additionally, although cracking has been detected only on the
engine mounts of the number one engine, the FAA has determined that
fatigue could similarly stress the engine mountings of both outboard
(number one and number four) engines, and that consequent fatigue
cracking is likely to occur on the mountings of both engines.
The FAA has reviewed and approved Lockheed Alert Service Bulletin
A382-71-19-A82-687, dated December 23, 1993, that describes procedures
for inspections to detect loose, missing, or deformed fasteners, and
cracking of the upper tangs of the truss mounts on the outboard
engines.
Since an unsafe condition has been identified that is likely to
exist or develop on other Lockheed Model 382, 382B, 382E, 382F, and
382G series airplanes of the same type design, this AD is being issued
to prevent multiple failures of the upper truss mounts, which could
adversely affect the integrity of the engine mount structure. This AD
requires repetitive general visual inspections to detect loose,
missing, or deformed fasteners on the inboard and outboard upper truss
mounts of the number one and number four (left and right outboard)
engines, and repetitive general visual inspections to detect cracking
in the upper tangs of the truss mounts of these engines. The actions
are required to be accomplished in accordance with the alert service
bulletin described previously.
This AD also requires replacement of loose, missing, or deformed
fasteners with new or serviceable fasteners, and replacement of cracked
truss mount upper tangs with new or serviceable tangs.
This is considered to be interim action until final action is
identified, at which time the FAA may consider further rulemaking.
Since a situation exists that requires the immediate adoption of
this regulation, it is found that notice and opportunity for prior
public comment hereon are impracticable, and that good cause exists for
making this amendment effective in less than 30 days.
Comments Invited
Although this action is in the form of a final rule that involves
requirements affecting flight safety and, thus, was not preceded by
notice and an opportunity for public comment, comments are invited on
this rule. Interested persons are invited to comment on this rule by
submitting such written data, views, or arguments as they may desire.
Communications shall identify the Rules Docket number and be submitted
in triplicate to the address specified under the caption ``ADDRESSES.''
All communications received on or before the closing date for comments
will be considered, and this rule may be amended in light of the
comments received. Factual information that supports the commenter's
ideas and suggestions is extremely helpful in evaluating the
effectiveness of the AD action and determining whether additional
rulemaking action would be needed.
Comments are specifically invited on the overall regulatory,
economic, environmental, and energy aspects of the rule that might
suggest a need to modify the rule. All comments submitted will be
available, both before and after the closing date for comments, in the
Rules Docket for examination by interested persons. A report that
summarizes each FAA-public contact concerned with the substance of this
AD will be filed in the Rules Docket.
Commenters wishing the FAA to acknowledge receipt of their comments
submitted in response to this notice must submit a self-addressed,
stamped postcard on which the following statement is made: ``Comments
to Docket Number 94-NM-04-AD.'' The postcard will be date stamped and
returned to the commenter.
The regulations adopted herein will not have substantial direct
effects 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. Therefore, in
accordance with Executive Order 12612, it is determined that this final
rule does not have sufficient federalism implications to warrant the
preparation of a Federalism Assessment.
The FAA has determined that this regulation is an emergency
regulation that must be issued immediately to correct an unsafe
condition in aircraft, and is not a ``significant regulatory action''
under Executive Order 12866. It has been determined further that this
action involves an emergency regulation under DOT Regulatory Policies
and Procedures (44 FR 11034, February 26, 1979). If it is determined
that this emergency regulation otherwise would be significant under DOT
Regulatory Policies and Procedures, a final regulatory evaluation will
be prepared and placed in the Rules Docket. A copy of it, if filed, may
be obtained from the Rules Docket at the location provided under the
caption ``ADDRESSES.''
List of Subjects in 14 CFR Part 39
Air transportation, Aircraft, Aviation safety, Incorporation by
reference, Safety.
Adoption of the Amendment
Accordingly, pursuant to the authority delegated to me by the
Administrator, the Federal Aviation Administration amends 14 CFR part
39 of the Federal Aviation Regulations as follows:
PART 39--AIRWORTHINESS DIRECTIVES
1. The authority citation for part 39 continues to read as follows:
Authority: 49 U.S.C. App. 1354(a), 1421 and 1423; 49 U.S.C.
106(g); and 14 CFR 11.89.
Sec. 39.13 [Amended]
2. Section 39.13 is amended by adding the following new
airworthiness directive:
94-03-03 Lockheed: Amendment 39-8809. Docket 94-NM-04-AD.
Applicability: Model 382, 382B, 382E, and 382F series airplanes
having serial numbers 3946 through 4512, inclusive, on which the
outer wings have been replaced in accordance with Manufacturing End
Product (MEP) 12R/13R or MEP 9T/10T; and Model 382G series airplanes
having serial numbers 4561 through 5225, inclusive; certificated in
any category.
Compliance: Required as indicated, unless accomplished
previously.
To prevent multiple failures of the upper truss mounts, which
could adversely affect the integrity of the engine mount structure,
accomplish the following:
(a) Prior to the accumulation of 15,000 total hours time-in-
service since wing replacement (for Model 382, 382B, 382E, and 382F
series airplanes on which the outer wings have been replaced in
accordance with MEP 12R/13R or MEP 9T/10T); or prior to the
accumulation of 15,000 total hours time-in-service (for Model 382G
series ariplanes); or within 30 days after the effective date of
this AD; whichever occurs later: Accomplish the requirements of
paragraphs (a)(1) and (a)(2) of this AD. Repeat the specified
inspections thereafter at intervals not to exceed 300 hours time-in-
service or l00 landings, whichever occurs later.
(1) Perform a general visual inspection to detect loose,
missing, or deformed fasteners on the inboard and outboard upper
truss mounts of the number one and number four (left and right
outboard) engines, in accordance with Lockheed Alert Service
Bulletin A382-71-19/A82-687, dated December 23, 1993. If any loose,
missing, or deformed fastener is found, prior to further flight,
replace it with a new or serviceable fastener in accordance with
Hercules Structural Repair Manual, Document Number SMP 583.
(2) Perform a general visual inspection to detect cracking of
the truss mount upper tangs of the number one and number four
engines in accordance with Lockheed Alert Service Bulletin A382-71-
19/A82-687, dated December 23, 1993. If cracking is detected in any
truss mount upper tang, prior to further flight, replace it with a
new or serviceable tang in accordance with Hercules Structural
Repair Manual, Document Number SMP 583, or in accordance with a
method approved by the Manager, Atlanta Aircraft Certification
Office (ACO), FAA, Small Airplane Directorate.
(b) An alternative method of compliance or adjustment of the
compliance time that provides an acceptable level of safety may be
used if approved by the Manager, Atlanta ACO. Operators shall submit
their requests through an appropriate FAA Principal Maintenance
Inspector, who may add comments and then send it to the Manager,
Atlanta ACO.
Note: Information concerning the existence of approved
alternative methods of compliance with this AD, if any, may be
obtained from the Atlanta ACO.
(c) Special flight permits may be issued in accordance with
Federal Aviation Regulations (FAR) 21.197 and 21.199 to operate the
airplane to a location where the requirements of this AD can be
accomplished.
(d) The inspections shall be done in accordance with Lockheed
Alert Service Bulletin A382-71-19/A82-687, dated December 23, 1993.
This incorporation by reference was approved by the Director of the
Federal Register in accordance with 5 U.S.C. 552(a) and 1 CFR part
51. Copies may be obtained from Lockheed Western Export Company
(LWEC), Zone 0755, 86 South Cobb Drive, Marietta, Georgia 30063-
0755. Copies may be inspected at the FAA, Transport Airplane
Directorate, 1601 Lind Avenue, SW., Renton, Washington; or at the,
FAA, Small Airplane Directorate, Atlanta Aircraft Certification
Office, suite 210C, 1669 Phoenix Parkway, Atlanta, Georgia; or at
the Office of the Federal Register, 800 North Capitol Street, NW.,
suite 700, Washington, DC.
(e) This amendment becomes effective on February 18, 1994.
Issued in Renton, Washington, on January 21, 1994.
Darrell M. Pederson,
Acting Manager, Transport Airplane Directorate, Aircraft Certification
Service.
[FR Doc. 94-1691 Filed 2-2-94; 8:45 am]
BILLING CODE 4910-13-U
