AD Amdt-39-9663

[Federal Register Volume 61, Number 160 (Friday, August 16, 1996)]
[Rules and Regulations]
[Pages 42549-42550]
From the Federal Register Online via the Government Publishing Office [<a href="http://www.gpo.gov">www.gpo.gov</a>]
[FR Doc No: 96-20872]


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DEPARTMENT OF TRANSPORTATION

Federal Aviation Administration

14 CFR Part 39

[Docket No. 95-NM-10-AD; Amendment 39-9663; AD 96-12-20]
RIN 2120-AA64


Airworthiness Directives; Lockheed Model 382, 382B, 382E, 382F, 
and 382G Series Airplanes

AGENCY: Federal Aviation Administration, DOT.

ACTION: Final rule; correction.

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SUMMARY: This document corrects information that appeared in 
airworthiness directive (AD) 96-12-20, amendment 39-9663, that was 
published in the Federal Register on June 10, 1996 (61 FR 29279). This 
AD is applicable to certain Lockheed Model 382, 382B, 382E, 382F, and 
382G series airplanes. Among other things, it requires visual 
inspections to detect loose, missing, or deformed fasteners in the 
upper truss mounts of certain engines. This action corrects a reference 
to the outboard and inboard engines, which should have referred to the 
outboard and inboard truss mounts.

DATES: Effective July 15, 1996.
    The incorporation by reference of certain publications listed in 
the regulations was previously approved by the Director of the Federal 
Register as of July 15, 1996 (61 FR 29279, June 10, 1996).

FOR FURTHER INFORMATION CONTACT: Thomas Peters, Aerospace Engineer, 
ACE-116A, Flight Test Branch, FAA, Small Airplane Directorate, Atlanta 
Aircraft Certification Office, Campus Building, Suite 2-160, 1701 
Columbia Avenue, College Park, Georgia 30337-

[[Page 42550]]

2748; telephone (404) 305-7367; fax (404) 305-7348.

SUPPLEMENTARY INFORMATION: On June 3, 1996, the FAA issued AD 96-12-20, 
amendment 39-9663; (61 FR 29279, June 10, 1996), to require visual 
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 cracked parts. That AD also 
requires repetitive ultrasonic inspections of the upper tang and 
replacement of cracked parts. Additionally, that AD provides an 
optional terminating action for the repetitive inspections.
    As published, paragraph (d)(2) of that AD refers to ``truss mounts 
in the No. 1 outboard engine'' and refers to ``truss mounts of the No. 
4 inboard engine.'' However, the correct references should have been to 
``outboard truss mounts of the No. 1 engine'' and ``inboard truss 
mounts of the No. 4 engine.'' In all other respects, as well as in 
other references to these items in the AD, the originally-issued AD is 
correct.
    Since no other part of the regulatory information has been changed, 
the final rule is not being republished.
    The effective date of the AD remains July 15, 1996.
    Accordingly, the final rule document (FR Doc. 96-14383), which was 
published on June 10, 1996, at 61 FR 29279, is corrected as follows:


Sec. 39.13  [Corrected]

    On page 29282, in the first column, the text of paragraph (d)(2) of 
AD 96-12-20, amendment 39-9663, is corrected to read as follows:
* * * * *
    (d) * * *
    (1) * * *
    (2) Replace the truss mount assembly with part number 360013-31 or 
subsequent (for the outboard truss mounts of the No. 1 engine), or part 
number 360017-31 or subsequent (for the inboard truss mounts of the No. 
4 engine), as applicable, in accordance with SMP 583. Such replacement 
constitutes terminating action for the requirements of this AD.
* * * * *
    Issued in Renton, Washington, on August 9, 1996.
Darrell M. Pederson,
Acting Manager, Transport Airplane Directorate, Aircraft Certification 
Service.
[FR Doc. 96-20872 Filed 8-15-96; 8:45 am]
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