[Federal Register Volume 60, Number 2 (Wednesday, January 4, 1995)]
[Rules and Regulations]
[Pages 327-328]
From the Federal Register Online via the Government Publishing Office [www.gpo.gov]
[FR Doc No: 95-48]



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DEPARTMENT OF TRANSPORTATION
14 CFR Part 39

[Docket No. 94-NM-88-AD; Amendment 39-9110; AD 94-26-15]


Airworthiness Directives; Lockheed Model 382 Series Airplanes

AGENCY: Federal Aviation Administration, DOT.

ACTION: Final rule.

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SUMMARY: This amendment adopts a new airworthiness directive (AD), 
applicable to certain Lockheed Model 382 series airplanes, that 
requires inspection of a kingpin riser on the lower surface of the 
outer wing to determine fastener placement. This AD would also require 
repetitive inspections for fatigue cracks in the kingpin riser if the 
fasteners are positioned outside certain limits, and repair, if 
necessary. This amendment is prompted by reports of insufficient 
distance between the center of the outermost fastener on the kingpin 
riser and the edge of the riser, which can adversely affect the fatigue 
resistance of the outer wing assembly. The actions specified by this AD 
are intended to prevent structural failure of the lower surface of the 
outer wing due to fatigue cracks in the kingpin riser.

DATES: Effective on February 3, 1995.
    The incorporation by reference of certain publications listed in 
the regulations is approved by the Director of the Federal Register as 
of February 3, 1995.

ADDRESSES: The service information referenced in this AD may be 
obtained from Lockheed Aeronautical Systems Support Company, Field 
Support Department, Department 693, Zone 0755, 2251 Lake Park Drive, 
Smyrna, Georgia 30080. This information may be examined at the Federal 
Aviation Administration (FAA), Transport Airplane Directorate, Rules 
Docket, 1601 Lind Avenue, SW., Renton, Washington; or at the FAA, Small 
Airplane Directorate, Atlanta Aircraft Certification Office,Campus 
Building, 1701 Columbia Avenue, Suite 2-160, College Park, Georgia 
30337-2748; 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, FAA, 
Atlanta Aircraft Certification Office, Campus Building, 1701 Columbia 
Avenue, Suite 2-160, College Park, Georgia 30337-2748; telephone (404) 
305-3915; fax (404) 305-7348.

SUPPLEMENTARY INFORMATION: A proposal to amend part 39 of the Federal 
Aviation Regulations (14 CFR part 39) to include an airworthiness 
directive (AD) that is applicable to certain Lockheed Model 382 series 
airplanes was published in the Federal Register on September 19, 1994 
(59 FR 47823). That action proposed to require an inspection of a 
kingpin riser on the lower surface of the outer wing to determine 
fastener placement; and repetitive inspections for fatigue cracks in 
the kingpin riser if the fasteners are positioned outside certain 
limits, and repair, if necessary. -
    Interested persons have been afforded an opportunity to participate 
in the making of this amendment. No comments were submitted in response 
to the proposal or the FAA's determination of cost to the public.-
    As a result of recent communications with the Air Transport 
Association (ATA) of America, the FAA has learned that, in general, 
some operators may misunderstand the legal effect of AD's on airplanes 
that are identified in the applicability provision of the AD, but that 
have been altered or repaired in the area addressed by the AD. The FAA 
points out that all airplanes identified in the applicability provision 
of an AD are legally subject to the AD. If an airplane has been altered 
or repaired in the affected area in such a way as to affect compliance 
with the AD, the owner or operator is required to obtain FAA approval 
for an alternative method of compliance with the AD, in accordance with 
the paragraph of each AD that provides for such approvals. A note has 
been added to this final rule to clarify [[Page 328]] this requirement. 
The FAA has determined that this addition will neither increase the 
economic burden on any operator nor increase the scope of the AD.-
    The FAA has recently reviewed the figures it has used over the past 
several years in calculating the economic impact of AD activity. In 
order to account for various inflationary costs in the airline 
industry, the FAA has determined that it is necessary to increase the 
labor rate used in these calculations from $55 per work hour to $60 per 
work hour. The economic impact information, below, has been revised to 
reflect this increase in the specified hourly labor rate.
    There are approximately 20 Lockheed Model 382 series airplanes of 
the affected design in the worldwide fleet. The FAA estimates that it 
will will take approximately 4 work hours per airplane to accomplish 
the required actions, and that the average labor rate is $60 per work 
hour. Based on these figures, the total cost impact of the AD on U.S. 
operators is estimated to be $4,800, or $240 per airplane.
    The total cost impact figure discussed above is based on 
assumptions that no operator has yet accomplished any of the 
requirements of this AD action, and that no operator would accomplish 
those actions in the future if this AD were not adopted.
    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.-
    For the reasons discussed above, I certify that this action (1) is 
not a ``significant regulatory action'' under Executive Order 12866; 
(2) is not a ``significant rule'' under 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. A final evaluation has been prepared for this action 
and it is contained in the Rules Docket. A copy of it 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 part 39 of 
the Federal Aviation Regulations (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. 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:

94-26-15 Lockheed Aeronautical Systems Company: Amendment 39-9110. 
Docket 94-NM-88-AD.-

    Applicability: Model 382, 382B, 382E, 382F, and 382G series 
airplanes, as listed in Hercules Service Bulletin 382-57-74 (82-
688), dated January 31, 1994; certificated in any category.

    Note 1: This AD applies to each airplane identified in the 
preceding applicability provision, regardless of whether it has been 
modified, altered, or repaired in the area subject to the 
requirements of this AD. For airplanes that have been modified, 
altered, or repaired so that the performance of the requirements of 
this AD is affected, the owner/operator must use the authority 
provided in paragraph (b) to request approval from the FAA. This 
approval may address either no action, if the current configuration 
eliminates the unsafe condition; or different actions necessary to 
address the unsafe condition described in this AD. Such a request 
should include an assessment of the effect of the changed 
configuration on the unsafe condition addressed by this AD. In no 
case does the presence of any modification, alteration, or repair 
remove any airplane from the applicability of this AD.

    Compliance: Required as indicated, unless accomplished 
previously. -
    To prevent structural failure of the outer wing assembly, 
accomplish the following: -
    (a) Within 30 days after the effective date of this AD, or prior 
to the accumulation of 18,000 total flight hours, whichever occurs 
later, perform an ultrasonic inspection to determine the distance 
between the edge of each of the six most outboard fasteners on 
kingpin riser number 18 and the edge of the riser, in accordance 
with Appendix A of Hercules Service Bulletin 382-57-74 (82-688), 
dated January 31, 1994.
    (1) If all six of these fasteners are positioned 0.31 inch or 
more from the kingpin riser edge: No further action is required by 
this AD.-
    (2) If any of the six most outboard fasteners is positioned less 
than 0.31 inch from the edge of the kingpin riser: Prior to the 
applicable threshold specified in Table 1 of Hercules Service 
Bulletin 382-57-74 (82-688), or prior to further flight if that 
threshold has been exceeded as of the effective date of this AD, 
perform an ultrasonic inspection to detect cracks in the kingpin 
riser, in accordance with Inspection Procedure SP-265 (Appendix B) 
of the service bulletin.

    Note 2: For airplanes on which an outer wing replacement is 
installed, the total flight hours threshold is counted from the time 
of outer wing replacement.

    (i) If no crack is found, repeat this inspection, thereafter, at 
intervals not to exceed 7,400 flight hours.
    (ii) If any cracked kingpin riser is found, prior to further 
flight, repair in accordance with a method approved by the Manager, 
Atlanta Aircraft Certification Office (ACO), FAA, Small Airplane 
Directorate. Repeat this inspection, thereafter, at intervals not to 
exceed 7,400 flight hours.-
    (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, FAA, Small Airplane 
Directorate. 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 3: 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 
sections 21.197 and 21.199 of the Federal Aviation Regulations (14 
CFR 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 Hercules 
Service Bulletin 382-57-74 (82-688), dated January 31, 1994 
(includes Attachment 1, and Appendices A and B). 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 Aeronautical Systems Support Company, Field 
Support Department, Department 693, Zone 0755, 2251 Lake Park Drive, 
Smyrna, Georgia 30080. Copies may be inspected at the FAA, Transport 
Airplane Directorate, 1601 Lind Avenue, SW., Renton, Washington; or 
at the FAA, Small Airplane Directorate, Atlanta Certification 
Office, Campus Building, 1701 Columbia Avenue, Suite 2-160, College 
Park, 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 3, 1995.

    Issued in Renton, Washington, on December 21, 1994.
Darrell M. Pederson,
Acting Manager, Transport Airplane Directorate, Aircraft Certification 
Service.
[FR Doc. 95-48 Filed 1-3-95; 8:45 am]
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