[Federal Register Volume 59, Number 180 (Monday, September 19, 1994)]
[Unknown Section]
[Page 0]
From the Federal Register Online via the Government Publishing Office [www.gpo.gov]
[FR Doc No: 94-23099]


[[Page Unknown]]

[Federal Register: September 19, 1994]


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DEPARTMENT OF TRANSPORTATION
14 CFR Part 39

[Docket No. 94-NM-88-AD]

 

Airworthiness Directives; Lockheed Model 382 Series Airplanes

AGENCY: Federal Aviation Administration, DOT.

ACTION: Notice of proposed rulemaking (NPRM).

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SUMMARY: This document proposes the adoption of a new airworthiness 
directive (AD) that is applicable to certain Lockheed Model 382 series 
airplanes. This proposal would require inspection of a kingpin riser on 
the lower surface of the outer wing to determine fastener placement. 
The proposed AD also would require repetitive inspections for fatigue 
cracks in the kingpin riser if the fasteners are positioned outside 
certain limits, and repair, if necessary. This proposal 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 the proposed AD are intended to prevent structural 
failure of the lower surface of the outer wing due to fatigue cracks in 
the kingpin riser.

DATES: Comments must be received by November 10, 1994.

ADDRESSES: Submit comments in triplicate to the Federal Aviation 
Administration (FAA), Transport Airplane Directorate, ANM-103, 
Attention: Rules Docket No. 94-NM-88-AD, 1601 Lind Avenue, SW., Renton, 
Washington 98055-4056. Comments may be inspected at this location 
between 9:00 a.m. and 3:00 p.m., Monday through Friday, except Federal 
holidays.
    -The service information referenced in the proposed rule 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 FAA, 
Transport Airplane Directorate, 1601 Lind Avenue, SW., Renton, 
Washington; or at the FAA, Small Airplane Directorate, Atlanta 
Certification Office, Suite 210C, 1669 Phoenix Parkway, Atlanta, 
Georgia 30349.

FOR FURTHER INFORMATION CONTACT: Thomas Peters, Aerospace Engineer, 
Flight Test Branch, ACE-160A, FAA, Small Airplane Directorate, FAA, 
Atlanta Certification Office, Suite 210C, 1669 Phoenix Parkway, 
Atlanta, Georgia 30349; telephone (404) 991-3915; fax (404) 991-3606.

SUPPLEMENTARY INFORMATION:

Comments Invited

    -Interested persons are invited to participate in the making of the 
proposed 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 above. All 
communications received on or before the closing date for comments, 
specified above, will be considered before taking action on the 
proposed rule. The proposals contained in this notice may be changed in 
light of the comments received.
    -Comments are specifically invited on the overall regulatory, 
economic, environmental, and energy aspects of the proposed 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 summarizing each FAA-public contact concerned with 
the substance of this proposal 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-88-AD.'' The postcard will be date 
stamped and returned to the commenter.

Availability of NPRMs

    -Any person may obtain a copy of this NPRM by submitting a request 
to the FAA, Transport Airplane Directorate, ANM-103, Attention: Rules 
Docket No. 94-NM-88-AD, 1601 Lind Avenue, SW., Renton, Washington 
98055-4056.

Discussion

    -The FAA has received reports that certain outer wing assemblies on 
Lockheed Model 382 series airplanes were manufactured with insufficient 
distance between the center of the outermost fastener on the kingpin 
riser and the edge of the riser (between outer wing stations 29.0 and 
36.0). Insufficient distance between the fastener and the riser edge 
adversely affects the fatigue resistance of the outer wing assembly due 
to fatigue cracks in the kingpin riser. Such fatigue cracking, if not 
corrected, could result in structural failure of the lower surface of 
the outer wing assembly.
    -The FAA has reviewed and approved Hercules Service Bulletin 382-
57-74 (82-688), dated January 31, 1994, which describes procedures for 
an ultrasonic inspection of kingpin riser number 18 on the lower 
surface of the outer wing to determine the distance between the center 
of the outermost fastener on the kingpin riser and the edge of the 
riser. In addition, for fasteners positioned outside certain limits 
described in the service bulletin, the service bulletin describes 
repetitive ultrasonic inspections to detect cracks in the kingpin 
riser, and repair, if necessary.
    -Since an unsafe condition has been identified that is likely to 
exist or develop on other products of this same type design, the 
proposed AD would 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. The inspections would be required to be accomplished in 
accordance with the service bulletin described previously. The repair 
would be required to be accomplished in accordance with a method 
approved by the FAA.
    -There are approximately 20 Lockheed Model 382 series airplanes of 
the affected design in the worldwide fleet. The FAA estimates that 20 
airplanes of U.S. registry would be affected by this proposed AD, that 
it would take approximately 4 work hours per airplane to accomplish the 
proposed actions, and that the average labor rate is $55 per work hour. 
Based on these figures, the total cost impact of the proposed AD on 
U.S. operators is estimated to be $4,400, or $220 per airplane.
    -The total cost impact figure discussed above is based on 
assumptions that no operator has yet accomplished any of the proposed 
requirements of this AD action, and that no operator would accomplish 
those actions in the future if this AD were not adopted.
    -The regulations proposed herein would 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 
proposal would not have sufficient federalism implications to warrant 
the preparation of a Federalism Assessment. -
    For the reasons discussed above, I certify that this proposed 
regulation (1) is not a ``significant regulatory action'' under 
Executive Order 12866; (2) is not a ``significant rule'' under the DOT 
Regulatory Policies and Procedures (44 FR 11034, February 26, 1979); 
and (3) if promulgated, 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 copy of the draft 
regulatory evaluation prepared for this action is contained in the 
Rules Docket. A copy of it may be obtained by contacting the Rules 
Docket at the location provided under the caption ADDRESSES.

List of Subjects in 14 CFR Part 39 -

    Air transportation, Aircraft, Aviation safety, Safety.

The Proposed Amendment -

    Accordingly, pursuant to the authority delegated to me by the 
Administrator, the Federal Aviation Administration proposes to amend 
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:

Lockheed Aeronautical Systems Company: 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. -
    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 1: For airplanes on which an outerwing 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 2: 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.

    Issued in Renton, Washington, on September 13, 1994.
Darrell M. Pederson,
Acting Manager, Transport Airplane Directorate, Aircraft Certification 
Service.
[FR Doc. 94-23099 Filed 9-16-94; 8:45 am]
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