Airworthiness Directives; Lockheed Model 382, 382B, 382E, 382F, 382G, and 382J Series Airplanes, 38311-38313 [E8-15181]
Download as PDF
pwalker on PROD1PC71 with RULES
Federal Register / Vol. 73, No. 130 / Monday, July 7, 2008 / Rules and Regulations
incurred by small handlers that are not
incurred by large handlers. While the
level of benefits of this rulemaking are
difficult to quantify, the stabilizing
effects of the volume regulations impact
small and large handlers positively by
helping them maintain and expand
markets even though raisin supplies
fluctuate widely from season to season.
Likewise, price stability positively
impacts small and large producers by
allowing them to better anticipate the
revenues their raisins will generate.
AMS is committed to complying with
the E-Government Act, to promote the
use of the Internet and other
information technologies to provide
increased opportunities for citizen
access to Government information and
services, and for other purposes.
There are some reporting,
recordkeeping and other compliance
requirements under the order. The
reporting and recordkeeping
requirements are necessary for
compliance purposes and for
developing statistical data for
maintenance of the program. The
requirements are the same as those
applied in past seasons. Thus, this
action imposes no additional reporting
or recordkeeping requirements on either
small or large raisin handlers. The forms
require information which is readily
available from handler records and
which can be provided without data
processing equipment or trained
statistical staff. The information
collection and recordkeeping
requirements have been previously
approved by the Office of Management
and Budget (OMB) under OMB No.
0581–0178, Vegetable and Specialty
Crops. As with all Federal marketing
order programs, reports and forms are
periodically reviewed to reduce
information requirements and
duplication by industry and public
sector agencies. In addition, as noted in
the initial regulatory flexibility analysis,
USDA has not identified any relevant
Federal rules that duplicate, overlap, or
conflict with this rule.
Further, the Committee’s meetings
were widely publicized throughout the
raisin industry and all interested
persons were invited to attend the
meetings and participate in the
Committee’s deliberations. Like all
Committee meetings, the August 14,
2007, October 4, 2007, and October 11,
2007, meetings were public meetings
and all entities, both large and small,
were able to express their views on this
issue.
Also, the Committee has a number of
appointed subcommittees to review
certain issues and make
recommendations to the Committee.
VerDate Aug<31>2005
16:13 Jul 03, 2008
Jkt 214001
The Committee’s Reserve Sales and
Marketing Subcommittee met on August
14, 2007, and October 4, 2007, and
discussed these issues in detail. Those
meetings were also public meetings and
both large and small entities were able
to participate and express their views.
An interim final rule concerning this
action was published in the Federal
Register on February 19, 2008. Copies of
the rule were mailed by the Committee’s
staff to all Committee members and
alternates and raisin handlers. In
addition, the rule was made available
through the Internet by USDA and the
Office of the Federal Register. That rule
provided a 60-day comment period
which ended April 21, 2008. No
comments were received during the
comment period.
A small business guide on complying
with fruit, vegetable, and specialty crop
marketing agreements and orders may
be viewed at: https://www.ams.usda.gov/
AMSv1.0/ams.fetchTemplateData.do?
template=TemplateN
&page=MarketingOrdersSmallBusiness
Guide. Any questions about the
compliance guide should be sent to Jay
Guerber at the previously mentioned
address in the FOR FURTHER INFORMATION
CONTACT section.
After consideration of all relevant
material presented, including the
Committee’s recommendation, and
other information, it is found that
finalizing the interim final rule, without
change, as published in the Federal
Register (73 FR 9005, February 19,
2008) will tend to effectuate the
declared policy of the Act.
List of Subjects in 7 CFR Part 989
Grapes, Marketing agreements,
Raisins, Reporting and recordkeeping
requirements.
PART 989—RAISINS PRODUCED
FROM GRAPES GROWN IN
CALIFORNIA
Accordingly, the interim final rule
amending 7 CFR part 989 which was
published at 73 FR 9005 on February 19,
2008, is adopted as a final rule without
change.
I
Dated: July 1, 2008.
Lloyd C. Day,
Administrator, Agricultural Marketing
Service.
[FR Doc. E8–15293 Filed 7–3–08; 8:45 am]
BILLING CODE 3410–02–P
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38311
DEPARTMENT OF TRANSPORTATION
Federal Aviation Administration
14 CFR Part 39
[Docket No. FAA–2008–0740; Directorate
Identifier 2008–NM–077–AD; Amendment
39–15605; AD 2008–14–10]
RIN 2120–AA64
Airworthiness Directives; Lockheed
Model 382, 382B, 382E, 382F, 382G,
and 382J Series Airplanes
Federal Aviation
Administration (FAA), DOT.
ACTION: Final rule; request for
comments.
AGENCY:
SUMMARY: We are adopting a new
airworthiness directive (AD) for all
Lockheed Model 382, 382B, 382E, 382F,
382G, and 382J series airplanes. This
AD requires, among other actions, an
inspection to determine whether a
certain upper engine mount bolt is
installed, and replacement of any
discrepant upper engine mount bolt
with a new one. This AD results from
a report indicating that several upper
engine mount bolts manufactured by a
certain supplier broke during
installation. We are issuing this AD to
prevent failure of the upper engine
mount bolts, which could result in
reduced structural capability of an
engine mount, and possible separation
of a strut and engine from the airplane
during flight.
DATES: This AD is effective July 22,
2008.
We must receive comments on this
AD by September 5, 2008.
ADDRESSES: You may send comments by
any of the following methods:
• Federal eRulemaking Portal: Go to
https://www.regulations.gov. Follow the
instructions for submitting comments.
• Fax: 202–493–2251.
• Mail: U.S. Department of
Transportation, Docket Operations, M–
30, West Building Ground Floor, Room
W12–140, 1200 New Jersey Avenue, SE.,
Washington, DC 20590.
• Hand Delivery: U.S. Department of
Transportation, Docket Operations, M–
30, West Building Ground Floor, Room
W12–140, 1200 New Jersey Avenue, SE.,
Washington, DC 20590, between 9 a.m.
and 5 p.m., Monday through Friday,
except Federal holidays.
Examining the AD Docket
You may examine the AD docket on
the Internet at https://
www.regulations.gov; or in person at the
Docket Management Facility between 9
a.m. and 5 p.m., Monday through
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07JYR1
38312
Federal Register / Vol. 73, No. 130 / Monday, July 7, 2008 / Rules and Regulations
Friday, except Federal holidays. The AD
docket contains this AD, the regulatory
evaluation, any comments received, and
other information. The street address for
the Docket Office (telephone 800–647–
5527) is in the ADDRESSES section.
Comments will be available in the AD
docket shortly after receipt.
FOR FURTHER INFORMATION CONTACT: Carl
Gray, Aerospace Engineer, Airframe
Branch, ACE–117A, FAA, Atlanta
Aircraft Certification Office, One Crown
Center, 1895 Phoenix Boulevard, Suite
450, Atlanta, Georgia 30349; telephone
(770) 703–6131; fax (770) 703–6097.
SUPPLEMENTARY INFORMATION:
Discussion
We have received a report indicating
that several upper engine mount bolts
broke during installation. These bolts
have part number (P/N) NAS 636 and
have ‘‘AFC’’ or ‘‘A’’ (AirFasco of
Canton, Ohio) stamped on the bolt head.
Upper engine mount bolts are used to
attach the quick engine change (QEC) to
the truss mounts in a four-bolt pattern
(two upper and two lower bolts). The
failures occurred on military versions of
Lockheed Model 382, 382B, 382E, 382F,
382G, and 382J series airplanes. The
discrepant bolts were located in the
upper two positions of the four bolt
pattern (different bolts are installed in
the lower two positions and are not
interchangeable with the bolts in the
upper two positions). Investigation
revealed that Lockheed has not
approved AirFasco as a supplier of these
bolts. Material hardness testing also
revealed that the discrepant bolts do not
meet hardness requirements. The cause
for the inadequate hardness is improper
heat treatment.
Failure of the upper engine mount
bolts could result in reduced structural
capability of an engine mount, and
possible separation of a strut and engine
from the airplane during flight.
The upper engine mount bolts are
commercially available. We do not
know whether any of the discrepant
bolts were sold to commercial operators
by the supplier or an agent. Therefore,
the discrepant bolts might be installed
on Lockheed Model 382, 382B, 382E,
382F, 382G, and 382J series airplanes.
pwalker on PROD1PC71 with RULES
FAA’s Determination and Requirements
of This AD
We are issuing this AD because we
evaluated all the relevant information
and determined the unsafe condition
described previously is likely to exist or
develop in other products of the(se)
same type design(s). This AD requires,
among other actions, an inspection to
determine whether a certain upper
VerDate Aug<31>2005
16:13 Jul 03, 2008
Jkt 214001
engine mount bolt is installed, and
replacement of any discrepant upper
engine mount bolt with a new one.
FAA’s Justification and Determination
of the Effective Date
It is not known when or if the
discrepant upper engine mount bolts
might have been installed on affected
airplanes. The QEC-to-truss mount joint
is designed to be failsafe for a single
failed upper engine mount bolt. If both
bolts in the upper position of an upper
engine mount are discrepant, the ability
for this joint to carry the QEC loads is
compromised, and consequently one
upper engine mount bolt could fail. If
one bolt in the upper position of an
upper engine mount fails, the other bolt
in the upper position of the upper
engine mount could also fail within a
short amount of time. Failure to replace
these discrepant bolts greatly increases
the risk of operating with a QEC
attachment system that might be
incapable of handling design level
loads. Because of our requirement to
promote safe flight of civil aircraft and
the critical need to ensure the structural
capability of an engine mount and the
short compliance time involved with
this action, this AD must be issued
immediately.
Because an unsafe condition exists
that requires the immediate adoption of
this AD, we find that notice and
opportunity for prior public comment
hereon are impracticable and that good
cause exists for making this amendment
effective in less than 30 days.
Comments Invited
This AD is a final rule that involves
requirements affecting flight safety, and
we did not provide you with notice and
an opportunity to provide your
comments before it becomes effective.
However, we invite you to send any
written data, views, or arguments about
this AD. Send your comments to an
address listed under the ADDRESSES
section. Include ‘‘Docket No. FAA–
2008–0740; Directorate Identifier 2008–
NM–077–AD’’ at the beginning of your
comments. We specifically invite
comments on the overall regulatory,
economic, environmental, and energy
aspects of this AD. We will consider all
comments received by the closing date
and may amend this AD because of
those comments.
We will post all comments we
receive, without change, to https://
www.regulations.gov, including any
personal information you provide. We
will also post a report summarizing each
substantive verbal contact we receive
about this AD.
PO 00000
Frm 00006
Fmt 4700
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Authority for This Rulemaking
Title 49 of the United States Code
specifies the FAA’s authority to issue
rules on aviation safety. Subtitle I,
section 106, describes the authority of
the FAA Administrator. ‘‘Subtitle VII:
Aviation Programs,’’ describes in more
detail the scope of the Agency’s
authority.
We are issuing this rulemaking under
the authority described in ‘‘Subtitle VII,
Part A, Subpart III, Section 44701:
General requirements.’’ Under that
section, Congress charges the FAA with
promoting safe flight of civil aircraft in
air commerce by prescribing regulations
for practices, methods, and procedures
the Administrator finds necessary for
safety in air commerce. This regulation
is within the scope of that authority
because it addresses an unsafe condition
that is likely to exist or develop on
products identified in this rulemaking
action.
Regulatory Findings
This AD will not have federalism
implications under Executive Order
13132. This AD will not have a
substantial direct effect 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.
For the reasons discussed above, I
certify that this AD:
(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.
You can find our regulatory
evaluation and the estimated costs of
compliance in the AD Docket.
List of Subjects in 14 CFR Part 39
Air transportation, Aircraft, Aviation
safety, Safety.
Adoption of the Amendment
Accordingly, under the authority
delegated to me by the Administrator,
the FAA amends 14 CFR part 39 as
follows:
I
PART 39—AIRWORTHINESS
DIRECTIVES
1. The authority citation for part 39
continues to read as follows:
I
Authority: 49 U.S.C. 106(g), 40113, 44701.
E:\FR\FM\07JYR1.SGM
07JYR1
Federal Register / Vol. 73, No. 130 / Monday, July 7, 2008 / Rules and Regulations
§ 39.13
[Amended]
2. The FAA amends § 39.13 by adding
the following new AD:
I
2008–14–10 Lockheed: Amendment 39–
15605. Docket No. FAA–2008–0740;
Directorate Identifier 2008–NM–077–AD.
Effective Date
(a) This airworthiness directive (AD) is
effective July 22, 2008.
Affected ADs
(b) None.
Applicability
(c) This AD applies to all Lockheed Model
382, 382B, 382E, 382F, 382G, and 382J series
airplanes, certificated in any category.
Unsafe Condition
(d) This AD results from a report indicating
that several upper engine mount bolts
manufactured by a certain supplier broke
during installation. We are issuing this AD to
prevent failure of the upper engine mount
bolts, which could result in reduced
structural capability of an engine mount, and
possible separation of a strut and engine from
the airplane during flight.
Compliance
(e) Comply with this AD within the
compliance times specified, unless already
done.
pwalker on PROD1PC71 with RULES
Access and Inspection
(f) Within 10 days after the effective date
of this AD do the actions specified in
paragraphs (f)(1), (f)(2), and (f)(3) of this AD.
(1) Make the airplane safe for maintenance
in accordance with a method approved by
the Manager, Atlanta Aircraft Certification
Office (ACO), FAA. Chapter 71–00 of the
Lockheed Hercules Maintenance Manual is
one approved method.
(2) Gain access to the upper engine mount
bolts by opening the left and right cowling
doors on each engine.
(3) Inspect the visible surface head of each
bolt in the upper position of each upper
engine mount to determine whether part
number (P/N) ‘‘NAS 636’’ is stamped across
the top, and whether the manufacturer’s code
‘‘AFC’’ or ‘‘A’’ (i.e., AirFasco) is stamped
across the bottom. All other manufacturers’
codes are acceptable.
Replacement and Corrective Actions
(g) If any upper position bolt, P/N NAS
636, having ‘‘AFC’’ or ‘‘A’’ stamped across
the bottom of the surface head is found
during the inspection required by paragraph
(f)(3) of this AD, before further flight, replace
that bolt with a new bolt, P/N NAS 636,
having a manufacturers’ code other than
‘‘AFC’’ or ‘‘A,’’ in accordance with a method
approved by the Manager, Atlanta ACO,
FAA. One approved method is the following:
To replace an engine mount bolt without
removing an engine, do the actions specified
in paragraphs (g)(1) through (g)(8) of this AD.
If both bolts in the upper position of an
engine mount must be replaced, the
replacements must be done one at a time to
prevent alignment problems.
(1) Shut down and disconnect external
electrical power in accordance with a method
VerDate Aug<31>2005
16:13 Jul 03, 2008
Jkt 214001
approved by the Manager, Atlanta ACO,
FAA. Chapter 24–40 of the Lockheed
Hercules Maintenance Manual is one
approved method.
(2) Attach a warning tag and close the
external power receptacle door.
(3) Install the nacelle hoist sling on the
power package.
(4) Lift the nacelle hoist sling enough to
take up load. Warning: When ‘‘NOLOADING’’ an engine with the sling, the
intention is to transfer most of the weight of
the engine from the airplane to the sling. This
requires some judgment on the part of the
technician. Under no circumstances should
the sling be raised enough to lift the airplane.
(5) Remove the discrepant upper engine
mount bolt and washer.
(6) Install the new upper engine mount
bolt, P/N NAS 636, having a manufacturers’
code other than ‘‘AFC’’ or ‘‘A,’’ and washer,
and torque to between 308 and 458 footpounds (3,700 to 5,500 inch-pounds).
(7) Remove the nacelle hoist sling from the
power package.
(8) Once all discrepant bolts in the upper
position of each upper engine mount have
been replaced, restore the airplane to service
in accordance with a method approved by
the Manager, Atlanta ACO, FAA. Chapter 71–
00 of the Lockheed Hercules Maintenance
Manual is one approved method.
Note 1: It is the intent of the actions
specified in paragraph (g) of this AD to allow
replacement of individual upper engine
mount bolts without having to do any other
maintenance.
Parts Installation
(h) As of the effective date of this AD, no
person may install a bolt, P/N NAS 636,
having ‘‘AFC’’ or ‘‘A’’ stamped across the
bottom of the surface head, in the upper
position of any upper engine mount, on any
airplane.
Alternative Methods of Compliance
(AMOCs)
(i)(1) The Manager, Atlanta ACO, FAA,
ATTN: Carl Gray, Aerospace Engineer,
Airframe Branch, ACE–117A, FAA, Atlanta
ACO, One Crown Center, 1895 Phoenix
Boulevard, suite 450, Atlanta, Georgia 30349;
telephone (770) 703–6131; fax (770) 703–
6097; has the authority to approve AMOCs
for this AD, if requested using the procedures
found in 14 CFR 39.19.
(2) To request a different method of
compliance or a different compliance time
for this AD, follow the procedures in 14 CFR
39.19. Before using any approved AMOC on
any airplane to which the AMOC applies,
notify your appropriate principal inspector
(PI) in the FAA Flight Standards District
Office (FSDO), or lacking a PI, your local
FSDO.
Material Incorporated by Reference
PO 00000
(j) None.
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38313
Issued in Renton, Washington, on June 24,
2008.
Ali Bahrami,
Manager, Transport Airplane Directorate,
Aircraft Certification Service.
[FR Doc. E8–15181 Filed 7–3–08; 8:45 am]
BILLING CODE 4910–13–P
DEPARTMENT OF TRANSPORTATION
Federal Aviation Administration
14 CFR Part 71
[Docket No. FAA–2008–0683; Airspace
Docket No. 08–ASW–11]
Establishment of Class E Airspace;
Plains, TX
Federal Aviation
Administration (FAA), DOT.
ACTION: Direct final rule; request for
comments.
AGENCY:
SUMMARY: This action establishes Class
E5 airspace at Plains, TX. Additional
controlled airspace is necessary to
accommodate aircraft using new RNAV
Global Positioning System (GPS)
Standard Instrument Approach
Procedures (SIAP) at Yoakum County
Airport, Plains, TX. This action will
enhance the safety and management of
Instrument Flight Rules (IFR) aircraft
operations at Yoakum County Airport.
DATES: Effective Date: 0901 UTC
September 25, 2008. Comments for
inclusion in the rules Docket must be
received August 21, 2008. The Director
of the Federal Register approves this
incorporation by reference action under
Title 1, Code of Federal Regulations,
part 51, subject to the annual revision of
FAA Order 7400.9 and publication of
conforming amendments.
ADDRESSES: Send comments on this
proposal to the U.S. Department of
Transportation, Docket Operations, 1200
New Jersey Avenue, SE., West Building
Ground Floor, Room W12–140,
Washington, DC 20590–0001. You must
identify the docket number FAA–2008–
0683/Airspace Docket No. 08–ASW–11,
at the beginning of your comments. You
may also submit comments through the
Internet at https://regulations.gov. You
may review the public docket
containing the proposal, any comments
received, and any final disposition in
person in the Dockets Office between 9
a.m. and 5 p.m., Monday through
Friday, except Federal holidays. The
Docket Office (telephone 1–800–647–
5527) is on the ground floor of the
building at the above address.
FOR FURTHER INFORMATION CONTACT: Gary
A. Mallett, Central Service Center,
Operations Support Group, Federal
E:\FR\FM\07JYR1.SGM
07JYR1
Agencies
[Federal Register Volume 73, Number 130 (Monday, July 7, 2008)]
[Rules and Regulations]
[Pages 38311-38313]
From the Federal Register Online via the Government Printing Office [www.gpo.gov]
[FR Doc No: E8-15181]
=======================================================================
-----------------------------------------------------------------------
DEPARTMENT OF TRANSPORTATION
Federal Aviation Administration
14 CFR Part 39
[Docket No. FAA-2008-0740; Directorate Identifier 2008-NM-077-AD;
Amendment 39-15605; AD 2008-14-10]
RIN 2120-AA64
Airworthiness Directives; Lockheed Model 382, 382B, 382E, 382F,
382G, and 382J Series Airplanes
AGENCY: Federal Aviation Administration (FAA), DOT.
ACTION: Final rule; request for comments.
-----------------------------------------------------------------------
SUMMARY: We are adopting a new airworthiness directive (AD) for all
Lockheed Model 382, 382B, 382E, 382F, 382G, and 382J series airplanes.
This AD requires, among other actions, an inspection to determine
whether a certain upper engine mount bolt is installed, and replacement
of any discrepant upper engine mount bolt with a new one. This AD
results from a report indicating that several upper engine mount bolts
manufactured by a certain supplier broke during installation. We are
issuing this AD to prevent failure of the upper engine mount bolts,
which could result in reduced structural capability of an engine mount,
and possible separation of a strut and engine from the airplane during
flight.
DATES: This AD is effective July 22, 2008.
We must receive comments on this AD by September 5, 2008.
ADDRESSES: You may send comments by any of the following methods:
Federal eRulemaking Portal: Go to https://
www.regulations.gov. Follow the instructions for submitting comments.
Fax: 202-493-2251.
Mail: U.S. Department of Transportation, Docket
Operations, M-30, West Building Ground Floor, Room W12-140, 1200 New
Jersey Avenue, SE., Washington, DC 20590.
Hand Delivery: U.S. Department of Transportation, Docket
Operations, M-30, West Building Ground Floor, Room W12-140, 1200 New
Jersey Avenue, SE., Washington, DC 20590, between 9 a.m. and 5 p.m.,
Monday through Friday, except Federal holidays.
Examining the AD Docket
You may examine the AD docket on the Internet at https://
www.regulations.gov; or in person at the Docket Management Facility
between 9 a.m. and 5 p.m., Monday through
[[Page 38312]]
Friday, except Federal holidays. The AD docket contains this AD, the
regulatory evaluation, any comments received, and other information.
The street address for the Docket Office (telephone 800-647-5527) is in
the ADDRESSES section. Comments will be available in the AD docket
shortly after receipt.
FOR FURTHER INFORMATION CONTACT: Carl Gray, Aerospace Engineer,
Airframe Branch, ACE-117A, FAA, Atlanta Aircraft Certification Office,
One Crown Center, 1895 Phoenix Boulevard, Suite 450, Atlanta, Georgia
30349; telephone (770) 703-6131; fax (770) 703-6097.
SUPPLEMENTARY INFORMATION:
Discussion
We have received a report indicating that several upper engine
mount bolts broke during installation. These bolts have part number (P/
N) NAS 636 and have ``AFC'' or ``A'' (AirFasco of Canton, Ohio) stamped
on the bolt head. Upper engine mount bolts are used to attach the quick
engine change (QEC) to the truss mounts in a four-bolt pattern (two
upper and two lower bolts). The failures occurred on military versions
of Lockheed Model 382, 382B, 382E, 382F, 382G, and 382J series
airplanes. The discrepant bolts were located in the upper two positions
of the four bolt pattern (different bolts are installed in the lower
two positions and are not interchangeable with the bolts in the upper
two positions). Investigation revealed that Lockheed has not approved
AirFasco as a supplier of these bolts. Material hardness testing also
revealed that the discrepant bolts do not meet hardness requirements.
The cause for the inadequate hardness is improper heat treatment.
Failure of the upper engine mount bolts could result in reduced
structural capability of an engine mount, and possible separation of a
strut and engine from the airplane during flight.
The upper engine mount bolts are commercially available. We do not
know whether any of the discrepant bolts were sold to commercial
operators by the supplier or an agent. Therefore, the discrepant bolts
might be installed on Lockheed Model 382, 382B, 382E, 382F, 382G, and
382J series airplanes.
FAA's Determination and Requirements of This AD
We are issuing this AD because we evaluated all the relevant
information and determined the unsafe condition described previously is
likely to exist or develop in other products of the(se) same type
design(s). This AD requires, among other actions, an inspection to
determine whether a certain upper engine mount bolt is installed, and
replacement of any discrepant upper engine mount bolt with a new one.
FAA's Justification and Determination of the Effective Date
It is not known when or if the discrepant upper engine mount bolts
might have been installed on affected airplanes. The QEC-to-truss mount
joint is designed to be failsafe for a single failed upper engine mount
bolt. If both bolts in the upper position of an upper engine mount are
discrepant, the ability for this joint to carry the QEC loads is
compromised, and consequently one upper engine mount bolt could fail.
If one bolt in the upper position of an upper engine mount fails, the
other bolt in the upper position of the upper engine mount could also
fail within a short amount of time. Failure to replace these discrepant
bolts greatly increases the risk of operating with a QEC attachment
system that might be incapable of handling design level loads. Because
of our requirement to promote safe flight of civil aircraft and the
critical need to ensure the structural capability of an engine mount
and the short compliance time involved with this action, this AD must
be issued immediately.
Because an unsafe condition exists that requires the immediate
adoption of this AD, we find that notice and opportunity for prior
public comment hereon are impracticable and that good cause exists for
making this amendment effective in less than 30 days.
Comments Invited
This AD is a final rule that involves requirements affecting flight
safety, and we did not provide you with notice and an opportunity to
provide your comments before it becomes effective. However, we invite
you to send any written data, views, or arguments about this AD. Send
your comments to an address listed under the ADDRESSES section. Include
``Docket No. FAA-2008-0740; Directorate Identifier 2008-NM-077-AD'' at
the beginning of your comments. We specifically invite comments on the
overall regulatory, economic, environmental, and energy aspects of this
AD. We will consider all comments received by the closing date and may
amend this AD because of those comments.
We will post all comments we receive, without change, to https://
www.regulations.gov, including any personal information you provide. We
will also post a report summarizing each substantive verbal contact we
receive about this AD.
Authority for This Rulemaking
Title 49 of the United States Code specifies the FAA's authority to
issue rules on aviation safety. Subtitle I, section 106, describes the
authority of the FAA Administrator. ``Subtitle VII: Aviation
Programs,'' describes in more detail the scope of the Agency's
authority.
We are issuing this rulemaking under the authority described in
``Subtitle VII, Part A, Subpart III, Section 44701: General
requirements.'' Under that section, Congress charges the FAA with
promoting safe flight of civil aircraft in air commerce by prescribing
regulations for practices, methods, and procedures the Administrator
finds necessary for safety in air commerce. This regulation is within
the scope of that authority because it addresses an unsafe condition
that is likely to exist or develop on products identified in this
rulemaking action.
Regulatory Findings
This AD will not have federalism implications under Executive Order
13132. This AD will not have a substantial direct effect 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.
For the reasons discussed above, I certify that this AD:
(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.
You can find our regulatory evaluation and the estimated costs of
compliance in the AD Docket.
List of Subjects in 14 CFR Part 39
Air transportation, Aircraft, Aviation safety, Safety.
Adoption of the Amendment
0
Accordingly, under the authority delegated to me by the Administrator,
the FAA amends 14 CFR part 39 as follows:
PART 39--AIRWORTHINESS DIRECTIVES
0
1. The authority citation for part 39 continues to read as follows:
Authority: 49 U.S.C. 106(g), 40113, 44701.
[[Page 38313]]
Sec. 39.13 [Amended]
0
2. The FAA amends Sec. 39.13 by adding the following new AD:
2008-14-10 Lockheed: Amendment 39-15605. Docket No. FAA-2008-0740;
Directorate Identifier 2008-NM-077-AD.
Effective Date
(a) This airworthiness directive (AD) is effective July 22,
2008.
Affected ADs
(b) None.
Applicability
(c) This AD applies to all Lockheed Model 382, 382B, 382E, 382F,
382G, and 382J series airplanes, certificated in any category.
Unsafe Condition
(d) This AD results from a report indicating that several upper
engine mount bolts manufactured by a certain supplier broke during
installation. We are issuing this AD to prevent failure of the upper
engine mount bolts, which could result in reduced structural
capability of an engine mount, and possible separation of a strut
and engine from the airplane during flight.
Compliance
(e) Comply with this AD within the compliance times specified,
unless already done.
Access and Inspection
(f) Within 10 days after the effective date of this AD do the
actions specified in paragraphs (f)(1), (f)(2), and (f)(3) of this
AD.
(1) Make the airplane safe for maintenance in accordance with a
method approved by the Manager, Atlanta Aircraft Certification
Office (ACO), FAA. Chapter 71-00 of the Lockheed Hercules
Maintenance Manual is one approved method.
(2) Gain access to the upper engine mount bolts by opening the
left and right cowling doors on each engine.
(3) Inspect the visible surface head of each bolt in the upper
position of each upper engine mount to determine whether part number
(P/N) ``NAS 636'' is stamped across the top, and whether the
manufacturer's code ``AFC'' or ``A'' (i.e., AirFasco) is stamped
across the bottom. All other manufacturers' codes are acceptable.
Replacement and Corrective Actions
(g) If any upper position bolt, P/N NAS 636, having ``AFC'' or
``A'' stamped across the bottom of the surface head is found during
the inspection required by paragraph (f)(3) of this AD, before
further flight, replace that bolt with a new bolt, P/N NAS 636,
having a manufacturers' code other than ``AFC'' or ``A,'' in
accordance with a method approved by the Manager, Atlanta ACO, FAA.
One approved method is the following: To replace an engine mount
bolt without removing an engine, do the actions specified in
paragraphs (g)(1) through (g)(8) of this AD. If both bolts in the
upper position of an engine mount must be replaced, the replacements
must be done one at a time to prevent alignment problems.
(1) Shut down and disconnect external electrical power in
accordance with a method approved by the Manager, Atlanta ACO, FAA.
Chapter 24-40 of the Lockheed Hercules Maintenance Manual is one
approved method.
(2) Attach a warning tag and close the external power receptacle
door.
(3) Install the nacelle hoist sling on the power package.
(4) Lift the nacelle hoist sling enough to take up load.
Warning: When ``NO-LOADING'' an engine with the sling, the intention
is to transfer most of the weight of the engine from the airplane to
the sling. This requires some judgment on the part of the
technician. Under no circumstances should the sling be raised enough
to lift the airplane.
(5) Remove the discrepant upper engine mount bolt and washer.
(6) Install the new upper engine mount bolt, P/N NAS 636, having
a manufacturers' code other than ``AFC'' or ``A,'' and washer, and
torque to between 308 and 458 foot-pounds (3,700 to 5,500 inch-
pounds).
(7) Remove the nacelle hoist sling from the power package.
(8) Once all discrepant bolts in the upper position of each
upper engine mount have been replaced, restore the airplane to
service in accordance with a method approved by the Manager, Atlanta
ACO, FAA. Chapter 71-00 of the Lockheed Hercules Maintenance Manual
is one approved method.
Note 1: It is the intent of the actions specified in paragraph
(g) of this AD to allow replacement of individual upper engine mount
bolts without having to do any other maintenance.
Parts Installation
(h) As of the effective date of this AD, no person may install a
bolt, P/N NAS 636, having ``AFC'' or ``A'' stamped across the bottom
of the surface head, in the upper position of any upper engine
mount, on any airplane.
Alternative Methods of Compliance (AMOCs)
(i)(1) The Manager, Atlanta ACO, FAA, ATTN: Carl Gray, Aerospace
Engineer, Airframe Branch, ACE-117A, FAA, Atlanta ACO, One Crown
Center, 1895 Phoenix Boulevard, suite 450, Atlanta, Georgia 30349;
telephone (770) 703-6131; fax (770) 703-6097; has the authority to
approve AMOCs for this AD, if requested using the procedures found
in 14 CFR 39.19.
(2) To request a different method of compliance or a different
compliance time for this AD, follow the procedures in 14 CFR 39.19.
Before using any approved AMOC on any airplane to which the AMOC
applies, notify your appropriate principal inspector (PI) in the FAA
Flight Standards District Office (FSDO), or lacking a PI, your local
FSDO.
Material Incorporated by Reference
(j) None.
Issued in Renton, Washington, on June 24, 2008.
Ali Bahrami,
Manager, Transport Airplane Directorate, Aircraft Certification
Service.
[FR Doc. E8-15181 Filed 7-3-08; 8:45 am]
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