[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]
BILLING CODE 4910-13-U
