[Federal Register Volume 60, Number 94 (Tuesday, May 16, 1995)]
[Proposed Rules]
[Pages 26004-26007]
From the Federal Register Online via the Government Publishing Office [www.gpo.gov]
[FR Doc No: 95-11972]



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[[Page 26005]]


DEPARTMENT OF TRANSPORTATION

14 CFR Part 39

[Docket No. 95-NM-10-AD]


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

AGENCY: Federal Aviation Administration, DOT.

ACTION: Notice of proposed rulemaking (NPRM).

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SUMMARY: This document proposes the supersedure of an existing 
airworthiness directive (AD), applicable to certain Lockheed Model 382, 
382B, 382E, 382F, and 382G series airplanes, that currently requires 
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 damaged parts with 
new or serviceable parts. This action would require repetitive 
ultrasonic inspections to detect cracking of the upper tangs and 
replacement of cracked parts with certain new or serviceable parts. 
This action would also provide an optional terminating action for the 
repetitive inspections. Additionally, this action would revise the 
applicability of the existing rule to specify appropriate groupings of 
airplanes subject to the rule. This proposal is prompted by reports 
indicating that fatigue cracking of the tangs of the upper truss mount 
has been detected. The actions specified by the proposed AD are 
intended to prevent multiple failures of the upper truss mounts due to 
problems associated with fatigue cracking, which could adversely affect 
the integrity of the engine mount structure.

DATES: Comments must be received by June 26, 1995.

ADDRESSES: Submit comments in triplicate to the Federal Aviation 
Administration (FAA), Transport Airplane Directorate, ANM-103, 
Attention: Rules Docket No. 95-NM-10-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, Dept. 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 Aircraft Certification 
Office, Campus Building, Suite 2-160, 1701 Columbia Avenue, College 
Park, Georgia.

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 30337-2748; 
telephone (404) 305-7367; fax (404) 305-7348.

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 95-NM-10-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. 95-NM-10-AD, 1601 Lind Avenue, SW., Renton, Washington 
98055-4056.

Discussion -

    On January 21, 1994, the FAA issued AD 94-03-03, amendment 39-8809 
(59 FR 5078, February 3, 1994), applicable to certain Lockheed Model 
382, 382B, 382E, 382F,and 382G series airplanes, 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 damaged parts with new or 
serviceable parts. That action was prompted by a report of fatigue 
cracking of the upper tang of the truss mounts. The requirements of 
that 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. -
    In the preamble to AD 94-03-03, the FAA indicated that the actions 
required by that AD were considered ``interim action'' and that further 
rulemaking action was being considered. Subsequently, the FAA has 
determined that additional actions are necessary to adequately address 
the identified unsafe condition. -
    Based on the latest data available, the FAA finds that, due to the 
effects of engine torque, cracking can originate on the outboard truss 
mount for the No. 1 engine and the inboard truss mount for the No. 4 
engine. The ultrasonic inspection procedure described in Hercules 
Service Bulletin 382-71-20, dated March 18, 1994, (described below) 
will detect cracking in the critical truss mount before cracking begins 
in the other truss mount, and will detect cracking prior to the time 
that the fasteners in the truss mounts could be loaded to the degree 
that they could fail. The FAA has determined that, if this ultrasonic 
inspection is conducted repetitively in the subject area, then the 
currently-required visual inspection for loose, missing, or deformed 
fasteners is no longer necessary. -
    The FAA has reviewed and approved Hercules Service Bulletin 382-71-
20, dated March 18, 1994, which describes procedures for performing 
repetitive ultrasonic inspections to detect fatigue cracking of the 
upper tangs of the No. 1 engine outboard and No. 4 engine inboard truss 
mounts, and replacement of any cracked assembly with a new or 
serviceable unit. The service bulletin specifies that replacement of 
the truss mount assembly with an assembly having part number (P/N) 
360013-31 and subsequent (for the No. 1 outboard engine assembly) or P/
N 360017-31 and subsequent (for the No. 4 inboard engine assembly) 
eliminates the need for the repetitive ultrasonic inspections. -
    Additionally, the FAA has identified certain revisions that must be 
made to the applicability of the existing AD: -
    1. Model 382G series airplanes should have been listed in the 
applicability of the with the group of airplanes on which the outer 
wings have been [[Page 26006]] replaced in accordance with 
Manufacturing End Product (MEP) 12R/13R or MEP 9T/10T. -
    2. Model 382E series airplanes should have been included in the 
group of airplanes having serial numbers 4561 through 5225 inclusive. -
    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 supersede AD 94-03-03 to continue to require 
inspection 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 AD would also require repetitive ultrasonic 
inspections to detect cracking of the upper tangs on the No. 1 engine 
outboard truss mount and the No. 4 engine inboard truss mount, and 
replacement of the truss mount with a new part, if necessary. 
Replacement of the truss mount assembly with an assembly having P/N 
360013-31 (or subsequent) or P/N 360017-31 (or subsequent) would 
constitute terminating action for the inspection requirements of the 
AD. The inspections would be required to be accomplished in accordance 
with the service bulletin described previously. The replacement would 
be required to be accomplished in accordance with the Hercules 
Structural Repair Manual. -
    This proposed action would also revise the applicability of the 
existing AD to include the Model 382E and Model 382G in the appropriate 
groupings of airplanes that are subject to the rule. -
    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 included in this notice to clarify this long-standing requirement. 
-
    There are approximately 112 Lockheed Model 382, 382B, 382E, 382F, 
and 382G series airplanes of the affected design in the worldwide 
fleet. The FAA estimates that 18 airplanes of U.S. registry would be 
affected by this proposed AD. -
    Accomplishment of the visual inspections currently required by AD 
94-03-03, which would be retained in this proposed AD, take 
approximately 10 work hours per airplane, at an average labor rate of 
$60 per work hour. Based on these figures, the total cost impact of the 
currently-required inspections on U.S. operators is estimated to be 
$10,800, or $600 per airplane, per inspection cycle. -
    Accomplishment of the ultrasonic inspections that would be added by 
this AD would take approximately 6 work hours per airplane, at an 
average labor rate of $60 per work hour. Based on these figures, the 
total cost impact of the proposed inspections on U.S. operators is 
estimated to be $6,480, or $360 per airplane, per inspection cycle. -
    The total cost impact figures discussed above are 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. However, it is 
reasonable to assume that operators currently subject to the 
requirements of AD 94-03-03 have already implemented the repetitive 
visual inspections required by that AD. -
    Should an operator elect to accomplish the optional terminating 
action that would be provided by this AD action, it would take 
approximately 60 work hours per airplane to accomplish it, at an 
average labor rate of $60 per work hour. The cost of required parts 
would be approximately $17,000 per airplane. Based on these figures, 
the total cost impact of the optional terminating action would be 
$20,600 per airplane.-
    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 removing amendment 39-8809 (59 FR 
5078, February 3, 1994), and by adding a new airworthiness directive 
(AD), to read as follows:

Lockheed Aeronautical Systems Company: Docket 95-NM-10-AD. 
Supersedes AD 94-03-03, Amendment 39-8809.

     -Applicability: Model 382, 382B, 382E, 382F, and 382G 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 
382E and Model 382G series airplanes having serial numbers 4561 
through 5225 inclusive; 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 (f) 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 multiple failures of the upper truss mounts, 
[[Page 26007]] 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 airplanes); or within 30 days after February 18, 1994 (the 
effective date of AD 94-03-03, amendment 39-8809), 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 100 landings, whichever 
occurs later, until the requirements of paragraph (b) of this AD are 
accomplished. -
    (1) Perform a general visual inspection to detect loose, 
missing, or deformed fasteners on the inboard and outboard upper 
truss mounts of the No. 1 and No. 4 (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 (SRM), Document Number SMP 583. -
    (2) Perform a general visual inspection to detect cracking of 
the truss mount upper tangs of the No. 1 and No. 4 engine truss 
mounts 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 SRM, Document 
Number SMP 583, or in accordance with a method approved by the 
Manager, Atlanta Aircraft Certification Office (ACO), FAA, Small 
Airplane Directorate. -
    (b) Perform an ultrasonic inspection to detect cracking of the 
upper tangs of the No. 1 outboard and the No. 4 inboard engine truss 
mounts, in accordance with Hercules Service Bulletin 382-71-20, 
dated March 18, 1994, at the time specified in paragraph (b)(1) or 
(b)(2) of this AD, as applicable. Accomplishment of this inspection 
terminates the inspections required by paragraph (a) of this AD.-
    (1) For Model 382, 382B, 382E, 382F, and 382G series airplanes 
on which the outer wings have been replaced in accordance with MEP 
12R/13R or MEP 9T/10T: Accomplish the inspection at the earlier of 
the times specified in paragraphs (b)(1)(i) and (b)(1)(ii) of this 
AD. -
    (i) Prior to the accumulation of 15,000 total hours time-in-
service since replacement of the outer wings, or within 90 days 
after the effective date of this AD, whichever occurs later. Or -
    (ii) Within 300 hours time-in-service or 100 landings, whichever 
occurs later, following the immediately preceding visual inspection 
accomplished in accordance with paragraph (a) of this AD. -
    (2) For Model 382E and 382G series airplanes having serial 
number 4561 through 5225 inclusive, other than those identified in 
paragraph (b)(1) of this AD: Accomplish the inspection at the 
earlier of the times specified in paragraphs (b)(2)(i) and 
(b)(2)(ii) of this AD. -
    (i) Prior to the accumulation of 15,000 total hours time-in-
service, or within 90 days after the effective date of this AD, 
whichever occurs later. Or -
    (ii) Within 300 hours time-in-service or 100 landings, whichever 
occurs later, following the immediately preceding visual inspection 
accomplished in accordance with paragraph (a) of this AD. -
    (c) If no cracking is detected during the inspection required by 
paragraph (b) of this AD, repeat the inspection thereafter at 
intervals not to exceed 5,200 hours time-in-service. -
    (d) If any cracking is detected during the inspection required 
by paragraph (b) of this AD: Prior to further flight, accomplish the 
requirements of either paragraph (d)(1) or (d)(2) of this AD. -
    (1) Replace the truss mount assembly with a new or serviceable 
assembly having part number 360013-15, -19, or -23 (for the outboard 
truss mounts of the No. 1 engine), or part number 360017-15, -19, or 
-23 (for the inboard truss mounts of the No. 4 engine), as 
applicable, in accordance with SRM 515C. Prior to the accumulation 
of 15,000 hours time-in-service after installation of the engine 
truss mount assembly, perform an ultrasonic inspection as specified 
in paragraph (b) of this AD. Repeat that inspection thereafter at 
intervals not to exceed 5,200 hours time-in-service. Or -
    (2) Replace the truss mount assembly with part number 360013-31 
or subsequent (for the truss mounts in the No. 1 outboard engine), 
or part number 360017-31 or subsequent (for the truss mounts of the 
No. 4 inboard engine), as applicable, in accordance with SRM 515C. 
Such replacement constitutes terminating action for the requirements 
of this AD. -
    (e) As of the effective date of this AD, no person shall install 
a No. 1 outboard engine truss mount (part number 360013-15, -19, or 
-23), or a No. 4 inboard engine truss mount (part number 360017-15, 
-19, or -23), on any airplane unless the truss mount has been 
inspected in accordance with SRM 151C. -
    (f) 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 2: Information concerning the existence of approved 
alternative methods of compliance with this AD, if any, may be 
obtained from the Atlanta ACO.

     -(g) 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 May 10, 1995.
Darrell M. Pederson,
Acting Manager, Transport Airplane Directorate, Aircraft Certification 
Service.
[FR Doc. 95-11972 Filed 5-15-95; 8:45 am]
BILLING CODE 4910-13-P