[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]


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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.

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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