Airworthiness Directives; Lockheed Martin Corporation/Lockheed Martin Aeronautics Company Model L-1011 Series Airplanes, 48049-48053 [2011-19968]
Download as PDF
Federal Register / Vol. 76, No. 152 / Monday, August 8, 2011 / Proposed Rules
For the reasons described above, this new
AD requires repetitive tests and inspections
of the air brake control system torsion tube
and applicable corrective actions, depending
on findings.
emcdonald on DSK2BSOYB1PROD with PROPOSALS
Actions and Compliance
(f) Unless already done, do the following
actions:
(1) Within the next 6 months after the
effective date of this AD, remove, test, and
inspect the air brake control system torsion
tube for corrosion damage following
Diamond Aircraft Industries GmbH Work
Instruction WI–MSB 36–105, dated April 21,
2011, as specified in Diamond Aircraft
Industries GmbH Service Bulletin No. MSB
36–105/1, dated May 2, 2011.
(2) If corrosion damage is found during the
inspection required in paragraph (f)(1) of this
AD or during any repetitive inspection
required in paragraphs (f)(2) and (f)(3) of this
AD, before further flight after the inspection
in which corrosion damage is found, replace
the affected torsion tube with a serviceable
part. Before installation, apply an
anticorrosive agent to the inside of the
torsion tube. Do these required actions
following Diamond Aircraft Industries GmbH
Work Instruction WI–MSB 36–105, dated
April 21, 2011. After replacement,
repetitively thereafter at intervals not to
exceed 60 months, remove, test, and inspect
the newly installed air brake control system
torsion tube for corrosion damage following
the procedures specified in paragraph (f)(1)
of this AD.
(3) If no corrosion damage is found during
the inspection required in paragraph (f)(1) of
this AD or during any repetitive inspection
required in paragraphs (f)(2) and (f)(3) of this
AD, before reinstalling the torsion tube,
apply an anticorrosive agent to the inside of
the torsion tube. Do these required actions
following Diamond Aircraft Industries GmbH
Work Instruction WI–MSB 36–105, dated
April 21, 2011. Repetitively thereafter at
intervals not to exceed 60 months, remove,
test, and inspect the air brake control system
torsion tube for corrosion damage following
the procedures specified in paragraph (f)(1)
of this AD.
(4) As of the effective date of this AD, do
not install an air brake control system torsion
tube on an affected airplane unless it has
been inspected following the procedures
specified in paragraph (f)(1) of this AD, is
found to be corrosion free, and an
anticorrosive agent has been applied to the
inside of the tube as specified in Diamond
Aircraft Industries GmbH Work Instruction
WI–MSB 36–105, dated April 21, 2011.
Note 1: Credit will be given for the initial
test and inspection required in paragraph
(f)(1) of this AD and the corrective actions
required in paragraphs (f)(2) and (f)(3) of this
AD if already done before the effective date
of this AD following Diamond Aircraft
Industries GmbH Service Bulletin No. MSB
36–105, original issue.
FAA AD Differences
Note 2: This AD differs from the MCAI
and/or service information as follows: No
differences.
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Other FAA AD Provisions
(g) The following provisions also apply to
this AD:
(1) Alternative Methods of Compliance
(AMOCs): The Manager, Standards Office,
FAA, has the authority to approve AMOCs
for this AD, if requested using the procedures
found in 14 CFR 39.19. Send information to
ATTN: Jim Rutherford, Aerospace Engineer,
FAA, Small Airplane Directorate, 901 Locust,
Room 301, Kansas City, Missouri 64106;
telephone: (816) 329–4165; fax: (816) 329–
4090; e-mail: jim.rutherford@faa.gov. 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.
(2) Airworthy Product: For any requirement
in this AD to obtain corrective actions from
a manufacturer or other source, use these
actions if they are FAA-approved. Corrective
actions are considered FAA-approved if they
are approved by the State of Design Authority
(or their delegated agent). You are required
to assure the product is airworthy before it
is returned to service.
(3) Reporting Requirements: For any
reporting requirement in this AD, a Federal
agency may not conduct or sponsor, and a
person is not required to respond to, nor
shall a person be subject to a penalty for
failure to comply with a collection of
information subject to the requirements of
the Paperwork Reduction Act unless that
collection of information displays a current
valid OMB Control Number. The OMB
Control Number for this information
collection is 2120–0056. Public reporting for
this collection of information is estimated to
be approximately 5 minutes per response,
including the time for reviewing instructions,
completing and reviewing the collection of
information. All responses to this collection
of information are mandatory. Comments
concerning the accuracy of this burden and
suggestions for reducing the burden should
be directed to the FAA at: 800 Independence
Ave. SW., Washington, DC 20591, Attn:
Information Collection Clearance Officer,
AES–200.
Related Information
(h) Refer to MCAI European Aviation
Safety Agency (EASA) AD No. 2011–0110,
dated June 16, 2011; Diamond Aircraft
Industries GmbH Service Bulletin No. MSB
36–105/1, dated May 2, 2011; and Diamond
Aircraft Industries GmbH Work Instruction
WI–MSB 36–105, dated April 21, 2011, for
related information. For service information
related to this AD, contact Diamond Aircraft
Industries GmbH, N.A. Otto-Stra+e 5, A–2700
Wiener Neustadt, Austria, telephone: +43
2622 26700; fax: +43 2622 26780; e-mail:
office@diamond-air.at; Internet: https://
www.diamond-air.at. You may review copies
of the referenced service information at the
FAA, Small Airplane Directorate, 901 Locust,
Kansas City, Missouri 64106. For information
on the availability of this material at the
FAA, call (816) 329–4148.
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48049
Issued in Kansas City, Missouri, on July 26,
2011.
Steven W. Thompson,
Acting Manager, Small Airplane Directorate,
Aircraft Certification Service.
[FR Doc. 2011–20038 Filed 8–5–11; 8:45 am]
BILLING CODE 4910–13–P
DEPARTMENT OF TRANSPORTATION
Federal Aviation Administration
14 CFR Part 39
[Docket No. FAA–2011–0723; Directorate
Identifier 2010–NM–080–AD]
RIN 2120–AA64
Airworthiness Directives; Lockheed
Martin Corporation/Lockheed Martin
Aeronautics Company Model L–1011
Series Airplanes
Federal Aviation
Administration (FAA), DOT.
ACTION: Notice of proposed rulemaking
(NPRM).
AGENCY:
We propose to supersede an
existing airworthiness directive (AD)
that applies to Model L–1011–385–1, L–
1011–385–1–14, and L–1011–385–1–15
airplanes. The existing AD currently
requires implementation of a
Supplemental Inspection Document
(SID) program of structural inspections
to detect fatigue cracking, and repair, if
necessary, to ensure continued
airworthiness of these airplanes as they
approach the manufacturer’s original
fatigue design life goal. Since we issued
that AD, an evaluation by the
manufacturer of usage and flight data
provided additional information about
certain Structurally Significant Details
(SSDs) where fatigue damage is likely to
occur. This proposed AD would add
airplanes to the applicability, change
certain inspection thresholds, add three
new SSDs, and remove an SSD that has
been addressed by a different AD. We
are proposing this AD to prevent fatigue
cracking that could compromise the
structural integrity of these airplanes.
DATES: We must receive comments on
this proposed AD by September 22,
2011.
SUMMARY:
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.
ADDRESSES:
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• Hand Delivery: Deliver to Mail
address above between 9 a.m. and
5 p.m., Monday through Friday, except
Federal holidays.
For service information identified in
this AD, contact Lockheed Martin
Corporation/Lockheed Martin
Aeronautics Company, Airworthiness
Office, Dept. 6A0M, Zone 0252, Column
P–58, 86 S. Cobb Drive, Marietta,
Georgia 30063; phone: 770–494–5444;
fax 770–494–5445; e-mail
ams.portal@lmco.com; Internet https://
www.lockheedmartin.com/ams/tools/
TechPubs.html. You may review copies
of the referenced service information at
the FAA, Transport Airplane
Directorate, 1601 Lind Avenue, SW.,
Renton, Washington. For information on
the availability of this material at the
FAA, call 425–227–1221.
emcdonald on DSK2BSOYB1PROD with PROPOSALS
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
Friday, except Federal holidays. The AD
docket contains this proposed AD, the
regulatory evaluation, any comments
received, and other information. The
street address for the Docket Office
(phone: 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 (ACO), 1701
Columbia Avenue, College Park, Georgia
30337; phone: 404–474–5554; fax 404–
474–5606; e-mail: Carl.W.Gray@faa.gov.
SUPPLEMENTARY INFORMATION:
Comments Invited
We invite you to send any written
relevant data, views, or arguments about
this proposed AD. Send your comments
to an address listed under the
ADDRESSES section. Include ‘‘Docket No.
FAA–2011–0723; Directorate Identifier
2010–NM–080–AD’’ at the beginning of
your comments. We specifically invite
comments on the overall regulatory,
economic, environmental, and energy
aspects of this proposed AD. We will
consider all comments received by the
closing date and may amend this
proposed 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 proposed AD.
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Discussion
On December 5, 1995, we issued AD
95–20–04 R1, Amendment 39–9454 (60
FR 63414, December 11, 1995), for all
Lockheed Model L–1011–385–1 series
airplanes. That AD requires
implementation of a Supplemental
Inspection Document (SID) program of
structural inspections to detect fatigue
cracking, and repair, if necessary, to
ensure continued airworthiness of these
airplanes as they approach the
manufacturer’s original fatigue design
life goal. That AD resulted from a
structural re-evaluation by the
manufacturer that identified certain
structural details where fatigue damage
is likely to occur. We issued that AD to
prevent fatigue cracking that could
compromise the structural integrity of
these airplanes.
describes procedures for supplemental
inspections of SSDs for all Model L–
1011 series airplanes. The Lockheed
Document identifies SSDs in fuselage,
stabilizer, and wing-critical areas. The
Lockheed Document changes certain
inspection thresholds, adds Model L–
1011–353–3 airplanes to the effectivity,
adds SSDs 57–3–10, 57–3–11, 57–4–1C,
and removes SSD 53–4–3. The
Lockheed Document also specifies that
operators submit the results of these
inspections to Lockheed.
FAA’s Determination
We are proposing 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 same
type design.
Actions Since Existing AD Was Issued
Proposed AD Requirements
Since we issued AD 95–20–04 R1, an
evaluation by the manufacturer of usage
and flight data provided additional
information about certain SSDs where
fatigue damage is likely to occur.
Therefore, this proposed AD changes
certain inspection thresholds and
intervals for Model L–1011–385–1, L–
1011–385–1–14, and L–1011–385–1–15
airplanes, adds three new SSDs, and
removes an SSD that has been addressed
by AD 99–08–20, amendment 39–11128
(64 FR 18324, April 14, 1999). AD 99–
08–20 requires repetitive inspections to
detect cracking of the bulkhead web and
cap at fuselage station 1363, and repair
if necessary.
When we issued AD 95–20–04 R1,
Model L–1011–385–3 airplanes were
not included in the applicability. These
long-range airplanes flew less frequently
and were neither imminently
approaching nor had exceeded the
manufacturer’s original fatigue design
life goal. In the NPRM for AD 95–20–04,
Amendment 39–9382 (60 FR 51713,
October 3, 1995) we stated that as these
airplanes accumulated more hours timein-service, and as the critical area
selection was developed and identified,
we anticipated that these airplanes
would be addressed in future
rulemaking actions. We now have
determined that further rulemaking is
indeed necessary for these airplanes,
and we have added them to the
applicability of this proposed AD.
This proposed AD would retain all
requirements of AD 95–20–04 R1. This
proposed AD would add Model L–
1011–385–3 airplanes to the
applicability, change certain inspection
thresholds and intervals for Model L–
1011–385–1, L–1011–385–1–14, and L–
1011–385–1–15 airplanes, add three
new SSDs for Model L–1011–385–3
airplanes, and remove an SSD that has
been addressed by a different AD action.
This proposed AD would also require
accomplishing the actions specified in
the service information described
previously. This proposed AD would
also require sending the inspection
results to the manufacturer.
Relevant Service Information
We reviewed Lockheed Document
Number LG92ER0060, ‘‘L–1011–385
Series Supplemental Inspection
Document,’’ revised April 2009
(hereafter referred to as ‘‘the Lockheed
Document’’). The Lockheed Document
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Change to Existing AD
This proposed AD would retain all
requirements of AD 95–20–04 R1. Since
AD 95–20–04 R1 was issued, the AD
format has been revised, and certain
paragraphs have been rearranged. As a
result, the corresponding paragraph
identifiers have changed in this
proposed AD, as listed in the following
table:
REVISED PARAGRAPH IDENTIFIERS
Requirement in
AD 95–20–04
Corresponding
requirement in this
proposed AD
paragraph (a)
paragraph (b)
paragraph (c)
paragraph (g)
paragraph (n)
paragraph (o)
Costs of Compliance
We estimate that this proposed AD
affects 26 airplanes of U.S. registry.
We estimate the following costs to
comply with this proposed AD:
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48051
ESTIMATED COSTS
Labor cost
Incorporate SID into maintenance program [retained actions from existing AD].
Initial inspections [retained
actions from existing
AD].
Repetitive inspections [retained actions from existing AD].
Incorporate SID into maintenance program [new
proposed action for
Model L–1011–385–3
airplanes].
Initial inspections [new proposed action for Model
L–1011–385–3 airplanes].
Repetitive inspections
[new proposed action for
Model L–1011–385–3
airplanes].
550 work-hours × $85 per
hour = $46,750.
$0
$46,750 .............................
26
$1,215,500.
245 work-hours × $85 per
hour = $20,825.
0
$20,825 .............................
26
$541,450.
52 work-hours × $85 per
hour = $4,420 per inspection cycle.
1 work-hour × $85 = $85 ..
0
$4,420 per inspection
cycle.
26
$114,920 per inspection
cycle.
0
$85 ....................................
2
$170.
48 work-hours × $85 per
hour = $4,080.
0
$4,080 ...............................
2
$8,160.
44 work-hours × $85 per
hour = $3,740 per inspection cycle.
0
$3,740 per inspection
cycle.
2
$7,480 per inspection
cycle.
emcdonald on DSK2BSOYB1PROD with PROPOSALS
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
We have determined that this
proposed AD would not have federalism
implications under Executive Order
13132. This proposed AD would 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 the proposed regulation:
(1) Is not a ‘‘significant regulatory
action’’ under Executive Order 12866,
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Parts cost
Number of
airplanes
affected
Action
Cost per product
(2) Is not a ‘‘significant rule’’ under
the DOT Regulatory Policies and
Procedures (44 FR 11034, February 26,
1979),
(3) Will not affect intrastate aviation
in Alaska, and
(4) 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.
List of Subjects in 14 CFR Part 39
Air transportation, Aircraft, Aviation
safety, Incorporation by reference,
Safety.
The Proposed Amendment
Accordingly, under the authority
delegated to me by the Administrator,
the FAA proposes to amend 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. 106(g), 40113, 44701.
§ 39.13
[Amended]
2. The FAA amends § 39.13 by
removing airworthiness directive (AD)
95–20–04 R1, Amendment 39–9454 (60
FR 63414, December 11, 1995), and
adding the following new AD:
Lockheed Martin Corporation/Lockheed
Martin Aeronautics Company: Docket
No. FAA–2011–0723; Directorate
Identifier 2010–NM–080–AD.
PO 00000
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Cost for U.S. operators
Comments Due Date
(a) The FAA must receive comments on
this AD action by September 22, 2011.
Affected ADs
(b) This AD supersedes AD 95–20–04 R1,
Amendment 39–9454.
Applicability
(c) All Lockheed Martin Corporation/
Lockheed Martin Aeronautics Company
Model L–1011–385–1, L–1011–385–1–14, L–
1011–385–1–15, and L–1011–385–3
airplanes, certificated in any category.
Subject
(d) Joint Aircraft System Component
(JASC)/Air Transport Association (ATA) of
America Code 53, Fuselage.
Unsafe Condition
(e) This AD was prompted by an evaluation
by the manufacturer of usage and flight data
that provided additional information about
certain Structurally Significant Details (SSDs)
where fatigue damage is likely to occur. We
are issuing this AD to prevent fatigue
cracking that could compromise the
structural integrity of these airplanes.
Compliance
(f) Comply with this AD within the
compliance times specified, unless already
done.
Restatement of the Requirements of AD 95–
20–04 R1: Revision and Inspections
(g) For Model L–1011–385–1, L–1011–385–
1–14, and L–1011–385–1–15 airplanes:
Within 12 months after November 2, 1995
(the effective date of AD 95–20–04 R1),
incorporate a revision into the maintenance
inspection program which provides for
inspection(s) of the structurally significant
details (SSD) defined in Lockheed Document
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emcdonald on DSK2BSOYB1PROD with PROPOSALS
Number LG92ER0060, ‘‘L–1011–385 Series
Supplemental Inspection Document,’’ revised
January 1994. Doing the revision required by
paragraph (h) of this AD terminates the
requirement to revise the maintenance
inspections program specified in this
paragraph. Doing the inspections required by
paragraph (i) of this AD terminates the
corresponding inspection requirements of
this paragraph.
(1) The initial inspection for each SSD
must be performed at the later of the times
specified in paragraph (g)(1)(i) or (g)(1)(ii) of
this AD.
(i) Within one repeat interval measured
from November 2, 1996 (12 months after
November 2, 1995).
(ii) Prior to the threshold specified in
Lockheed Document Number LG92ER0060,
‘‘L–1011–385 Series Supplemental
Inspection Document,’’ revised January 1994,
for that SSD.
(2) A 10 percent deviation from the
repetitive interval specified in Lockheed
Document Number LG92ER0060, ‘‘L–1011–
385 Series Supplemental Inspection
Document,’’ revised January 1994, for that
SSD is acceptable to allow for planning and
scheduling time.
(3) If Lockheed Document Number
LG92ER0060, ‘‘L–1011–385 Series
Supplemental Inspection Document,’’ revised
January 1994, specifies that inspection of any
SSD be performed at every ‘‘C’’ check, those
inspections must be performed at intervals
not to exceed 5,000 hours time-in-service or
2,500 flight cycles, whichever occurs earlier.
(4) If Lockheed Document Number
LG92ER0060, ‘‘L–1011–385 Series
Supplemental Inspection Document,’’ revised
January 1994, specifies either the initial
inspection or the repetitive inspection
intervals for any SSD in terms of flight hours
or flight cycles, the inspection shall be
performed prior to the earlier of the terms
(whichever occurs first on the airplane: either
accumulated number of flight hours, or
accumulated number of flight cycles).
(5) The non-destructive inspection
techniques referenced in Appendix VI of
Lockheed Document Number LG92ER0060,
‘‘L–1011–385 Series Supplemental
Inspection Document,’’ revised January 1994,
provide acceptable methods for
accomplishing the inspections required by
paragraph (g) of this AD.
New Requirements of this AD: New Revision
(h) For all airplanes: Within 12 months
after the effective date of this AD, incorporate
a revision into the maintenance inspection
program which provides for inspection(s) of
the SSDs defined in Lockheed Document
Number LG92ER0060, ‘‘L–1011–385 Series
Supplemental Inspection Document,’’ revised
April 2009. Doing this revision terminates
the requirement to revise the maintenance
inspection program as specified in paragraph
(g) of this AD.
Threshold and Intervals
(i) For all airplanes: Do all applicable
inspections specified in Lockheed Document
Number LG92ER0060, ‘‘L–1011–385 Series
Supplemental Inspection Document,’’ revised
April 2009. Do the initial inspection or next
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repetitive inspection at the applicable time
specified in paragraphs (i)(1) and (i)(2) of this
AD, except as provided by paragraphs (j), (k),
and (l) of this AD. Repeat the inspections
thereafter in accordance with the intervals
and actions specified in Lockheed Document
Number LG92ER0060, ‘‘L–1011–385 Series
Supplemental Inspection Document,’’ revised
April 2009, except as provided by paragraphs
(j), (k), and (l) of this AD. The nondestructive inspection techniques referenced
in Lockheed Document Number
LG92ER0060, ‘‘L–1011–385 Series
Supplemental Inspection Document,’’ revised
April 2009, provide acceptable methods for
accomplishing the inspections required by
this AD. Doing the inspections required by
this paragraph of this AD terminates the
corresponding inspection requirements of
paragraph (g) of this AD.
(1) For Model L–1011–385–3 airplanes;
and for Model L–1011–385–1, L–1011–385–
1–14, and L–1011–385–1–15 airplanes on
which the initial inspection required by
paragraph (g) of this AD has not been
accomplished before the effective date of this
AD: Do the initial inspection at the later of
the times specified in paragraphs (i)(1)(i) and
(i)(1)(ii) of this AD.
(i) Within one repeat interval measured
from a date 12 months after the effective date
of this AD.
(ii) Before the threshold specified for that
SSD in Lockheed Document Number
LG92ER0060, ‘‘L–1011–385 Series
Supplemental Inspection Document,’’ revised
April 2009.
(2) For Model L–1011–385–1, L–1011–385–
1–14, and L–1011–385–1–15 airplanes on
which the initial inspection required by
paragraph (g) of this AD has been
accomplished before the effective date of this
AD: Do the next repetitive inspection at the
earlier of the times specified in paragraphs
(i)(2)(i) and (i)(2)(ii) of this AD.
(i) Within the next repetitive inspection
interval specified in Lockheed Document
Number LG92ER0060, ‘‘L–1011–385 Series
Supplemental Inspection Document,’’ revised
January 1994, for that SSD.
(ii) Within one repeat interval measured
from a date 12 months after the effective date
of this AD; or within the next repetitive
interval specified in Lockheed Document
Number LG92ER0060, ‘‘L–1011–385 Series
Supplemental Inspection Document,’’ revised
April 2009, for that SSD; whichever occurs
later.
Exceptions to Threshold and Intervals
(j) For all airplanes: A 10 percent deviation
from the repetitive interval specified in
Lockheed Document Number LG92ER0060,
‘‘L–1011–385 Series Supplemental
Inspection Document,’’ revised April 2009,
for that SSD is acceptable to allow for
planning and scheduling time.
(k) For all airplanes: Where Lockheed
Document Number LG92ER0060, ‘‘L–1011–
385 Series Supplemental Inspection
Document,’’ revised April 2009, specifies that
inspection of any SSD be performed at every
‘‘C’’ check, those inspections must be
performed at intervals not to exceed 5,000
flight hours or 2,500 flight cycles, whichever
occurs earlier.
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(l) For all airplanes: Where Lockheed
Document Number LG92ER0060, ‘‘L–1011–
385 Series Supplemental Inspection
Document,’’ revised April 2009, specifies
either the initial inspection or the repetitive
inspection intervals for any SSD in terms of
flight hours or flight cycles, the inspection
must be performed prior to the earlier of the
terms (whichever occurs first on the airplane:
either accumulated number of flight hours, or
accumulated number of flight cycles).
Exception to Inspection Procedure
(m) For all airplanes: There should be no
repair or modification work done in the
inspection area before the initial inspections
required by paragraph (i) of this AD; any
changes in the inspection area could affect
the inspection procedure.
Repair
(n) For all airplanes: If any cracking is
found in any SSD during any inspection
required by this AD, prior to further flight,
repair in accordance with paragraph (n)(1),
(n)(2), or (n)(3) of this AD:
(1) In accordance with the applicable
service bulletin referenced in Lockheed
Document Number LG92ER0060, ‘‘L–1011–
385 Series Supplemental Inspection
Document,’’ revised January 1994; or revised
April 2009. After doing the revision required
by paragraph (h) of this AD, repair in
accordance with the applicable service
bulletin referenced in Lockheed Document
Number LG92ER0060, ‘‘L–1011–385 Series
Supplemental Inspection Document,’’ revised
April 2009.
(2) In accordance with the Structural
Repair Manual or in accordance with
Lockheed L–1011 Structural Repair Manual,
Revision 80, dated December 15, 2009. As of
the effective date of this AD, use Lockheed
L–1011 Structural Repair Manual, Revision
80, dated December 15, 2009.
(3) In accordance with a method approved
by the Manager, Atlanta Aircraft Certification
Office (ACO), FAA.
Reporting
(o) For all airplanes: At the later of the
times specified in paragraphs (o)(1) and (o)(2)
of this AD, submit a report of the results
(positive or negative) of the inspection(s) to
Lockheed in accordance with Section V.,
Data Reporting System (DRS), of the
applicable Lockheed Document specified in
paragraph (o)(1) of this AD. Under the
provisions of the Paperwork Reduction Act
(44 U.S.C. 3501 et seq.), the Office of
Management and Budget (OMB) has
approved the information collection
requirements contained in this AD and has
assigned OMB Control Number 2120–0056.
(1) Within 30 days after returning the
airplane to service, subsequent to
accomplishment of the inspection(s)
specified in Lockheed Document Number
LG92ER0060, ‘‘L–1011–385 Series
Supplemental Inspection Document,’’ revised
January 1994; or Lockheed Document
Number LG92ER0060, ‘‘L–1011–385 Series
Supplemental Inspection Document,’’ revised
April 2009.
(2) Within 30 days after the effective date
of this AD.
E:\FR\FM\08AUP1.SGM
08AUP1
Federal Register / Vol. 76, No. 152 / Monday, August 8, 2011 / Proposed Rules
Paperwork Reduction Act Burden Statement
(p) A federal agency may not conduct or
sponsor, and a person is not required to
respond to, nor shall a person be subject to
a penalty for failure to comply with a
collection of information subject to the
requirements of the Paperwork Reduction
Act unless that collection of information
displays a current valid OMB Control
Number. The OMB Control Number for this
information collection is 2120–0056. Public
reporting for this collection of information is
estimated to be approximately 5 minutes per
response, including the time for reviewing
instructions, completing and reviewing the
collection of information. All responses to
this collection of information are mandatory.
Comments concerning the accuracy of this
burden and suggestions for reducing the
burden should be directed to the FAA at: 800
Independence Ave., SW., Washington, DC
20591, Attn: Information Collection
Clearance Officer, AES–200.
Alternative Methods of Compliance
(AMOCs)
(q)(1) The Manager, Atlanta ACO, FAA, has
the authority to approve AMOCs for this AD,
if requested using the procedures found in 14
CFR 39.19. In accordance with 14 CFR 39.19,
send your request to your principal inspector
or local Flight Standards District Office, as
appropriate. If sending information directly
to the manager of the ACO, send it to the
attention of the person identified in the
Related Information section of this AD.
(2) Before using any approved AMOC,
notify your appropriate principal inspector,
or lacking a principal inspector, the manager
of the local flight standards district office/
certificate holding district office.
emcdonald on DSK2BSOYB1PROD with PROPOSALS
Related Information
(r) For more information about this AD,
contact Carl Gray, Aerospace Engineer,
Airframe Branch, ACE–117A, FAA, Atlanta
Aircraft Certification Office (ACO), 1701
Columbia Avenue, College Park, Georgia
30337; phone: 404–474–5554; fax: 404–474–
5606; e-mail: Carl.W.Gray@faa.gov.
(s) For service information identified in
this AD, contact Lockheed Martin
Corporation/Lockheed Martin Aeronautics
Company, Airworthiness Office, Dept. 6A0M,
Zone 0252, Column P–58, 86 S. Cobb Drive,
Marietta, Georgia 30063; phone: 770–494–
5444; fax: 770–494–5445; e-mail:
ams.portal@lmco.com; Internet https://
www.lockheedmartin.com/ams/tools/
TechPubs.htm. You may review copies of the
referenced service information at the FAA,
Transport Airplane Directorate, 1601 Lind
Avenue SW., Renton, Washington. For
information on the availability of this
material at the FAA, call 425–227–1221.
Issued in Renton, Washington, on July 29,
2011.
Ali Bahrami,
Manager, Transport Airplane Directorate,
Aircraft Certification Service.
[FR Doc. 2011–19968 Filed 8–5–11; 8:45 am]
BILLING CODE 4910–13–P
VerDate Mar<15>2010
18:42 Aug 05, 2011
Jkt 223001
CONSUMER PRODUCT SAFETY
COMMISSION
[CPSC Docket No. CPSC–2011–0053]
Consumer Registration of Durable
Infant or Toddler Products
Consumer Product Safety
Commission.
ACTION: Notice of proposed rulemaking.
AGENCY:
In accordance with section
104(d) of the Consumer Product Safety
Improvement Act of 2008 (‘‘CPSIA’’) the
Consumer Product Safety Commission
(‘‘Commission,’’ ‘‘CPSC,’’ or ‘‘we’’)
issued a final consumer product safety
rule requiring manufacturers of durable
infant or toddler products to establish a
consumer registration program. The
Commission is proposing an
amendment to clarify and correct some
of the requirements of the rule.
DATES: Written comments must be
received by October 24, 2011.
ADDRESSES: You may submit comments,
identified by Docket No. CPSC–2011–
0053, by any of the following methods:
SUMMARY:
Electronic Submissions
Submit electronic comments in the
following way:
Federal eRulemaking Portal: https://
www.regulations.gov. Follow the
instructions for submitting comments.
To ensure timely processing of
comments, the Commission is no longer
accepting comments submitted by
electronic mail (e-mail), except through
https://www.regulations.gov.
Written Submissions
Submit written submissions in the
following way:
Mail/Hand delivery/Courier (for
paper, disk, or CD–ROM submissions),
preferably in five copies, to: Office of
the Secretary, Consumer Product Safety
Commission, Room 820, 4330 East West
Highway, Bethesda, MD 20814;
telephone (301) 504–7923.
Instructions: All submissions received
must include the agency name and
docket number for this rulemaking. All
comments received may be posted
without change, including any personal
identifiers, contact information, or other
personal information provided to https://
www.regulations.gov. Do not submit
confidential business information, trade
secret information, or other sensitive or
protected information electronically.
Such information should be submitted
in writing.
Docket: For access to the docket to
read background documents or
Frm 00009
Fmt 4702
comments received go to https://
www.regulations.gov.
FOR FURTHER INFORMATION CONTACT:
16 CFR Part 1130
PO 00000
48053
Sfmt 4702
Celestine T. Kiss, Project Manager,
Division of Human Factors, Directorate
for Engineering Sciences, Consumer
Product Safety Commission, 4330 East
West Highway, Bethesda, MD 20814;
telephone (301) 504–7739;
ckiss@cpsc.gov.
SUPPLEMENTARY INFORMATION:
A. Background
On December 29, 2009, we published
a final rule requiring manufacturers of
durable infant or toddler products to: (1)
Provide with each product a postagepaid consumer registration form; (2)
keep records of consumers who register
such products with the manufacturer;
and (3) permanently place the
manufacturer’s name and contact
information, model name and number,
and the date of manufacture on each
such product. 74 FR 68668. The rule
specified formatting and text
requirements for the registration forms.
Subsequently, we published a
correction notice on February 22, 2010.
75 FR 7550. Since December 29, 2010,
registration forms have been required
for all durable infant or toddler products
covered by the rule.
Some manufacturers and testing
laboratories have brought to our
attention the need to clarify or correct
certain aspects of the rule. We are
proposing this amendment for that
purpose.
We note that, although manufacturers
of durable infant or toddler products
must comply with the registration
requirements, they are not required to
have a third party testing laboratory
‘‘test’’ their product’s compliance with
the registration requirements.
B. Proposed Clarifications and
Corrections
1. Simplifying the Provisions for the
Format and Text of Registration Forms
(Proposed § 1130.6)
The rule specifies requirements for
the format of registration forms in
§ 1130.6 and requirements for the text of
registration forms in § 1130.7. Given the
geometry of the registration forms,
which have four surfaces (front, back,
top, and bottom), we believe that it is
confusing to explain the requirements in
this way. Therefore, the proposed
amendment would eliminate this
framework, essentially collapsing the
requirements from §§ 1130.6 and 1130.7
into one section and clarifying them.
Proposed § 1130.6 would describe the
registration form more clearly, moving
logically from the front top of the form
E:\FR\FM\08AUP1.SGM
08AUP1
Agencies
[Federal Register Volume 76, Number 152 (Monday, August 8, 2011)]
[Proposed Rules]
[Pages 48049-48053]
From the Federal Register Online via the Government Printing Office [www.gpo.gov]
[FR Doc No: 2011-19968]
-----------------------------------------------------------------------
DEPARTMENT OF TRANSPORTATION
Federal Aviation Administration
14 CFR Part 39
[Docket No. FAA-2011-0723; Directorate Identifier 2010-NM-080-AD]
RIN 2120-AA64
Airworthiness Directives; Lockheed Martin Corporation/Lockheed
Martin Aeronautics Company Model L-1011 Series Airplanes
AGENCY: Federal Aviation Administration (FAA), DOT.
ACTION: Notice of proposed rulemaking (NPRM).
-----------------------------------------------------------------------
SUMMARY: We propose to supersede an existing airworthiness directive
(AD) that applies to Model L-1011-385-1, L-1011-385-1-14, and L-1011-
385-1-15 airplanes. The existing AD currently requires implementation
of a Supplemental Inspection Document (SID) program of structural
inspections to detect fatigue cracking, and repair, if necessary, to
ensure continued airworthiness of these airplanes as they approach the
manufacturer's original fatigue design life goal. Since we issued that
AD, an evaluation by the manufacturer of usage and flight data provided
additional information about certain Structurally Significant Details
(SSDs) where fatigue damage is likely to occur. This proposed AD would
add airplanes to the applicability, change certain inspection
thresholds, add three new SSDs, and remove an SSD that has been
addressed by a different AD. We are proposing this AD to prevent
fatigue cracking that could compromise the structural integrity of
these airplanes.
DATES: We must receive comments on this proposed AD by September 22,
2011.
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.
[[Page 48050]]
Hand Delivery: Deliver to Mail address above between 9
a.m. and 5 p.m., Monday through Friday, except Federal holidays.
For service information identified in this AD, contact Lockheed
Martin Corporation/Lockheed Martin Aeronautics Company, Airworthiness
Office, Dept. 6A0M, Zone 0252, Column P-58, 86 S. Cobb Drive, Marietta,
Georgia 30063; phone: 770-494-5444; fax 770-494-5445; e-mail
ams.portal@lmco.com; Internet https://www.lockheedmartin.com/ams/tools/TechPubs.html. You may review copies of the referenced service
information at the FAA, Transport Airplane Directorate, 1601 Lind
Avenue, SW., Renton, Washington. For information on the availability of
this material at the FAA, call 425-227-1221.
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 Friday, except Federal
holidays. The AD docket contains this proposed AD, the regulatory
evaluation, any comments received, and other information. The street
address for the Docket Office (phone: 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
(ACO), 1701 Columbia Avenue, College Park, Georgia 30337; phone: 404-
474-5554; fax 404-474-5606; e-mail: Carl.W.Gray@faa.gov.
SUPPLEMENTARY INFORMATION:
Comments Invited
We invite you to send any written relevant data, views, or
arguments about this proposed AD. Send your comments to an address
listed under the ADDRESSES section. Include ``Docket No. FAA-2011-0723;
Directorate Identifier 2010-NM-080-AD'' at the beginning of your
comments. We specifically invite comments on the overall regulatory,
economic, environmental, and energy aspects of this proposed AD. We
will consider all comments received by the closing date and may amend
this proposed 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 proposed AD.
Discussion
On December 5, 1995, we issued AD 95-20-04 R1, Amendment 39-9454
(60 FR 63414, December 11, 1995), for all Lockheed Model L-1011-385-1
series airplanes. That AD requires implementation of a Supplemental
Inspection Document (SID) program of structural inspections to detect
fatigue cracking, and repair, if necessary, to ensure continued
airworthiness of these airplanes as they approach the manufacturer's
original fatigue design life goal. That AD resulted from a structural
re-evaluation by the manufacturer that identified certain structural
details where fatigue damage is likely to occur. We issued that AD to
prevent fatigue cracking that could compromise the structural integrity
of these airplanes.
Actions Since Existing AD Was Issued
Since we issued AD 95-20-04 R1, an evaluation by the manufacturer
of usage and flight data provided additional information about certain
SSDs where fatigue damage is likely to occur. Therefore, this proposed
AD changes certain inspection thresholds and intervals for Model L-
1011-385-1, L-1011-385-1-14, and L-1011-385-1-15 airplanes, adds three
new SSDs, and removes an SSD that has been addressed by AD 99-08-20,
amendment 39-11128 (64 FR 18324, April 14, 1999). AD 99-08-20 requires
repetitive inspections to detect cracking of the bulkhead web and cap
at fuselage station 1363, and repair if necessary.
When we issued AD 95-20-04 R1, Model L-1011-385-3 airplanes were
not included in the applicability. These long-range airplanes flew less
frequently and were neither imminently approaching nor had exceeded the
manufacturer's original fatigue design life goal. In the NPRM for AD
95-20-04, Amendment 39-9382 (60 FR 51713, October 3, 1995) we stated
that as these airplanes accumulated more hours time-in-service, and as
the critical area selection was developed and identified, we
anticipated that these airplanes would be addressed in future
rulemaking actions. We now have determined that further rulemaking is
indeed necessary for these airplanes, and we have added them to the
applicability of this proposed AD.
Relevant Service Information
We reviewed Lockheed Document Number LG92ER0060, ``L-1011-385
Series Supplemental Inspection Document,'' revised April 2009
(hereafter referred to as ``the Lockheed Document''). The Lockheed
Document describes procedures for supplemental inspections of SSDs for
all Model L-1011 series airplanes. The Lockheed Document identifies
SSDs in fuselage, stabilizer, and wing-critical areas. The Lockheed
Document changes certain inspection thresholds, adds Model L-1011-353-3
airplanes to the effectivity, adds SSDs 57-3-10, 57-3-11, 57-4-1C, and
removes SSD 53-4-3. The Lockheed Document also specifies that operators
submit the results of these inspections to Lockheed.
FAA's Determination
We are proposing 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 same type design.
Proposed AD Requirements
This proposed AD would retain all requirements of AD 95-20-04 R1.
This proposed AD would add Model L-1011-385-3 airplanes to the
applicability, change certain inspection thresholds and intervals for
Model L-1011-385-1, L-1011-385-1-14, and L-1011-385-1-15 airplanes, add
three new SSDs for Model L-1011-385-3 airplanes, and remove an SSD that
has been addressed by a different AD action. This proposed AD would
also require accomplishing the actions specified in the service
information described previously. This proposed AD would also require
sending the inspection results to the manufacturer.
Change to Existing AD
This proposed AD would retain all requirements of AD 95-20-04 R1.
Since AD 95-20-04 R1 was issued, the AD format has been revised, and
certain paragraphs have been rearranged. As a result, the corresponding
paragraph identifiers have changed in this proposed AD, as listed in
the following table:
Revised Paragraph Identifiers
------------------------------------------------------------------------
Corresponding requirement in this
Requirement in AD 95-20-04 proposed AD
------------------------------------------------------------------------
paragraph (a) paragraph (g)
paragraph (b) paragraph (n)
paragraph (c) paragraph (o)
------------------------------------------------------------------------
Costs of Compliance
We estimate that this proposed AD affects 26 airplanes of U.S.
registry.
We estimate the following costs to comply with this proposed AD:
[[Page 48051]]
Estimated Costs
----------------------------------------------------------------------------------------------------------------
Number of
Action Labor cost Parts cost Cost per product airplanes Cost for U.S.
affected operators
----------------------------------------------------------------------------------------------------------------
Incorporate SID into 550 work-hours x $0 $46,750.......... 26 $1,215,500.
maintenance program [retained $85 per hour =
actions from existing AD]. $46,750.
Initial inspections [retained 245 work-hours x 0 $20,825.......... 26 $541,450.
actions from existing AD]. $85 per hour =
$20,825.
Repetitive inspections 52 work-hours x 0 $4,420 per 26 $114,920 per
[retained actions from $85 per hour = inspection cycle. inspection
existing AD]. $4,420 per cycle.
inspection cycle.
Incorporate SID into 1 work-hour x $85 0 $85.............. 2 $170.
maintenance program [new = $85.
proposed action for Model L-
1011-385-3 airplanes].
Initial inspections [new 48 work-hours x 0 $4,080........... 2 $8,160.
proposed action for Model L- $85 per hour =
1011-385-3 airplanes]. $4,080.
Repetitive inspections [new 44 work-hours x 0 $3,740 per 2 $7,480 per
proposed action for Model L- $85 per hour = inspection cycle. inspection
1011-385-3 airplanes]. $3,740 per cycle.
inspection cycle.
----------------------------------------------------------------------------------------------------------------
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
We have determined that this proposed AD would not have federalism
implications under Executive Order 13132. This proposed AD would 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 the 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),
(3) Will not affect intrastate aviation in Alaska, and
(4) 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.
List of Subjects in 14 CFR Part 39
Air transportation, Aircraft, Aviation safety, Incorporation by
reference, Safety.
The Proposed Amendment
Accordingly, under the authority delegated to me by the
Administrator, the FAA proposes to amend 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. 106(g), 40113, 44701.
Sec. 39.13 [Amended]
2. The FAA amends Sec. 39.13 by removing airworthiness directive
(AD) 95-20-04 R1, Amendment 39-9454 (60 FR 63414, December 11, 1995),
and adding the following new AD:
Lockheed Martin Corporation/Lockheed Martin Aeronautics Company:
Docket No. FAA-2011-0723; Directorate Identifier 2010-NM-080-AD.
Comments Due Date
(a) The FAA must receive comments on this AD action by September
22, 2011.
Affected ADs
(b) This AD supersedes AD 95-20-04 R1, Amendment 39-9454.
Applicability
(c) All Lockheed Martin Corporation/Lockheed Martin Aeronautics
Company Model L-1011-385-1, L-1011-385-1-14, L-1011-385-1-15, and L-
1011-385-3 airplanes, certificated in any category.
Subject
(d) Joint Aircraft System Component (JASC)/Air Transport
Association (ATA) of America Code 53, Fuselage.
Unsafe Condition
(e) This AD was prompted by an evaluation by the manufacturer of
usage and flight data that provided additional information about
certain Structurally Significant Details (SSDs) where fatigue damage
is likely to occur. We are issuing this AD to prevent fatigue
cracking that could compromise the structural integrity of these
airplanes.
Compliance
(f) Comply with this AD within the compliance times specified,
unless already done.
Restatement of the Requirements of AD 95-20-04 R1: Revision and
Inspections
(g) For Model L-1011-385-1, L-1011-385-1-14, and L-1011-385-1-15
airplanes: Within 12 months after November 2, 1995 (the effective
date of AD 95-20-04 R1), incorporate a revision into the maintenance
inspection program which provides for inspection(s) of the
structurally significant details (SSD) defined in Lockheed Document
[[Page 48052]]
Number LG92ER0060, ``L-1011-385 Series Supplemental Inspection
Document,'' revised January 1994. Doing the revision required by
paragraph (h) of this AD terminates the requirement to revise the
maintenance inspections program specified in this paragraph. Doing
the inspections required by paragraph (i) of this AD terminates the
corresponding inspection requirements of this paragraph.
(1) The initial inspection for each SSD must be performed at the
later of the times specified in paragraph (g)(1)(i) or (g)(1)(ii) of
this AD.
(i) Within one repeat interval measured from November 2, 1996
(12 months after November 2, 1995).
(ii) Prior to the threshold specified in Lockheed Document
Number LG92ER0060, ``L-1011-385 Series Supplemental Inspection
Document,'' revised January 1994, for that SSD.
(2) A 10 percent deviation from the repetitive interval
specified in Lockheed Document Number LG92ER0060, ``L-1011-385
Series Supplemental Inspection Document,'' revised January 1994, for
that SSD is acceptable to allow for planning and scheduling time.
(3) If Lockheed Document Number LG92ER0060, ``L-1011-385 Series
Supplemental Inspection Document,'' revised January 1994, specifies
that inspection of any SSD be performed at every ``C'' check, those
inspections must be performed at intervals not to exceed 5,000 hours
time-in-service or 2,500 flight cycles, whichever occurs earlier.
(4) If Lockheed Document Number LG92ER0060, ``L-1011-385 Series
Supplemental Inspection Document,'' revised January 1994, specifies
either the initial inspection or the repetitive inspection intervals
for any SSD in terms of flight hours or flight cycles, the
inspection shall be performed prior to the earlier of the terms
(whichever occurs first on the airplane: either accumulated number
of flight hours, or accumulated number of flight cycles).
(5) The non-destructive inspection techniques referenced in
Appendix VI of Lockheed Document Number LG92ER0060, ``L-1011-385
Series Supplemental Inspection Document,'' revised January 1994,
provide acceptable methods for accomplishing the inspections
required by paragraph (g) of this AD.
New Requirements of this AD: New Revision
(h) For all airplanes: Within 12 months after the effective date
of this AD, incorporate a revision into the maintenance inspection
program which provides for inspection(s) of the SSDs defined in
Lockheed Document Number LG92ER0060, ``L-1011-385 Series
Supplemental Inspection Document,'' revised April 2009. Doing this
revision terminates the requirement to revise the maintenance
inspection program as specified in paragraph (g) of this AD.
Threshold and Intervals
(i) For all airplanes: Do all applicable inspections specified
in Lockheed Document Number LG92ER0060, ``L-1011-385 Series
Supplemental Inspection Document,'' revised April 2009. Do the
initial inspection or next repetitive inspection at the applicable
time specified in paragraphs (i)(1) and (i)(2) of this AD, except as
provided by paragraphs (j), (k), and (l) of this AD. Repeat the
inspections thereafter in accordance with the intervals and actions
specified in Lockheed Document Number LG92ER0060, ``L-1011-385
Series Supplemental Inspection Document,'' revised April 2009,
except as provided by paragraphs (j), (k), and (l) of this AD. The
non-destructive inspection techniques referenced in Lockheed
Document Number LG92ER0060, ``L-1011-385 Series Supplemental
Inspection Document,'' revised April 2009, provide acceptable
methods for accomplishing the inspections required by this AD. Doing
the inspections required by this paragraph of this AD terminates the
corresponding inspection requirements of paragraph (g) of this AD.
(1) For Model L-1011-385-3 airplanes; and for Model L-1011-385-
1, L-1011-385-1-14, and L-1011-385-1-15 airplanes on which the
initial inspection required by paragraph (g) of this AD has not been
accomplished before the effective date of this AD: Do the initial
inspection at the later of the times specified in paragraphs
(i)(1)(i) and (i)(1)(ii) of this AD.
(i) Within one repeat interval measured from a date 12 months
after the effective date of this AD.
(ii) Before the threshold specified for that SSD in Lockheed
Document Number LG92ER0060, ``L-1011-385 Series Supplemental
Inspection Document,'' revised April 2009.
(2) For Model L-1011-385-1, L-1011-385-1-14, and L-1011-385-1-15
airplanes on which the initial inspection required by paragraph (g)
of this AD has been accomplished before the effective date of this
AD: Do the next repetitive inspection at the earlier of the times
specified in paragraphs (i)(2)(i) and (i)(2)(ii) of this AD.
(i) Within the next repetitive inspection interval specified in
Lockheed Document Number LG92ER0060, ``L-1011-385 Series
Supplemental Inspection Document,'' revised January 1994, for that
SSD.
(ii) Within one repeat interval measured from a date 12 months
after the effective date of this AD; or within the next repetitive
interval specified in Lockheed Document Number LG92ER0060, ``L-1011-
385 Series Supplemental Inspection Document,'' revised April 2009,
for that SSD; whichever occurs later.
Exceptions to Threshold and Intervals
(j) For all airplanes: A 10 percent deviation from the
repetitive interval specified in Lockheed Document Number
LG92ER0060, ``L-1011-385 Series Supplemental Inspection Document,''
revised April 2009, for that SSD is acceptable to allow for planning
and scheduling time.
(k) For all airplanes: Where Lockheed Document Number
LG92ER0060, ``L-1011-385 Series Supplemental Inspection Document,''
revised April 2009, specifies that inspection of any SSD be
performed at every ``C'' check, those inspections must be performed
at intervals not to exceed 5,000 flight hours or 2,500 flight
cycles, whichever occurs earlier.
(l) For all airplanes: Where Lockheed Document Number
LG92ER0060, ``L-1011-385 Series Supplemental Inspection Document,''
revised April 2009, specifies either the initial inspection or the
repetitive inspection intervals for any SSD in terms of flight hours
or flight cycles, the inspection must be performed prior to the
earlier of the terms (whichever occurs first on the airplane: either
accumulated number of flight hours, or accumulated number of flight
cycles).
Exception to Inspection Procedure
(m) For all airplanes: There should be no repair or modification
work done in the inspection area before the initial inspections
required by paragraph (i) of this AD; any changes in the inspection
area could affect the inspection procedure.
Repair
(n) For all airplanes: If any cracking is found in any SSD
during any inspection required by this AD, prior to further flight,
repair in accordance with paragraph (n)(1), (n)(2), or (n)(3) of
this AD:
(1) In accordance with the applicable service bulletin
referenced in Lockheed Document Number LG92ER0060, ``L-1011-385
Series Supplemental Inspection Document,'' revised January 1994; or
revised April 2009. After doing the revision required by paragraph
(h) of this AD, repair in accordance with the applicable service
bulletin referenced in Lockheed Document Number LG92ER0060, ``L-
1011-385 Series Supplemental Inspection Document,'' revised April
2009.
(2) In accordance with the Structural Repair Manual or in
accordance with Lockheed L-1011 Structural Repair Manual, Revision
80, dated December 15, 2009. As of the effective date of this AD,
use Lockheed L-1011 Structural Repair Manual, Revision 80, dated
December 15, 2009.
(3) In accordance with a method approved by the Manager, Atlanta
Aircraft Certification Office (ACO), FAA.
Reporting
(o) For all airplanes: At the later of the times specified in
paragraphs (o)(1) and (o)(2) of this AD, submit a report of the
results (positive or negative) of the inspection(s) to Lockheed in
accordance with Section V., Data Reporting System (DRS), of the
applicable Lockheed Document specified in paragraph (o)(1) of this
AD. Under the provisions of the Paperwork Reduction Act (44 U.S.C.
3501 et seq.), the Office of Management and Budget (OMB) has
approved the information collection requirements contained in this
AD and has assigned OMB Control Number 2120-0056.
(1) Within 30 days after returning the airplane to service,
subsequent to accomplishment of the inspection(s) specified in
Lockheed Document Number LG92ER0060, ``L-1011-385 Series
Supplemental Inspection Document,'' revised January 1994; or
Lockheed Document Number LG92ER0060, ``L-1011-385 Series
Supplemental Inspection Document,'' revised April 2009.
(2) Within 30 days after the effective date of this AD.
[[Page 48053]]
Paperwork Reduction Act Burden Statement
(p) A federal agency may not conduct or sponsor, and a person is
not required to respond to, nor shall a person be subject to a
penalty for failure to comply with a collection of information
subject to the requirements of the Paperwork Reduction Act unless
that collection of information displays a current valid OMB Control
Number. The OMB Control Number for this information collection is
2120-0056. Public reporting for this collection of information is
estimated to be approximately 5 minutes per response, including the
time for reviewing instructions, completing and reviewing the
collection of information. All responses to this collection of
information are mandatory. Comments concerning the accuracy of this
burden and suggestions for reducing the burden should be directed to
the FAA at: 800 Independence Ave., SW., Washington, DC 20591, Attn:
Information Collection Clearance Officer, AES-200.
Alternative Methods of Compliance (AMOCs)
(q)(1) The Manager, Atlanta ACO, FAA, has the authority to
approve AMOCs for this AD, if requested using the procedures found
in 14 CFR 39.19. In accordance with 14 CFR 39.19, send your request
to your principal inspector or local Flight Standards District
Office, as appropriate. If sending information directly to the
manager of the ACO, send it to the attention of the person
identified in the Related Information section of this AD.
(2) Before using any approved AMOC, notify your appropriate
principal inspector, or lacking a principal inspector, the manager
of the local flight standards district office/certificate holding
district office.
Related Information
(r) For more information about this AD, contact Carl Gray,
Aerospace Engineer, Airframe Branch, ACE-117A, FAA, Atlanta Aircraft
Certification Office (ACO), 1701 Columbia Avenue, College Park,
Georgia 30337; phone: 404-474-5554; fax: 404-474-5606; e-mail:
Carl.W.Gray@faa.gov.
(s) For service information identified in this AD, contact
Lockheed Martin Corporation/Lockheed Martin Aeronautics Company,
Airworthiness Office, Dept. 6A0M, Zone 0252, Column P-58, 86 S. Cobb
Drive, Marietta, Georgia 30063; phone: 770-494-5444; fax: 770-494-
5445; e-mail: ams.portal@lmco.com; Internet https://www.lockheedmartin.com/ams/tools/TechPubs.htm. You may review copies
of the referenced service information at the FAA, Transport Airplane
Directorate, 1601 Lind Avenue SW., Renton, Washington. For
information on the availability of this material at the FAA, call
425-227-1221.
Issued in Renton, Washington, on July 29, 2011.
Ali Bahrami,
Manager, Transport Airplane Directorate, Aircraft Certification
Service.
[FR Doc. 2011-19968 Filed 8-5-11; 8:45 am]
BILLING CODE 4910-13-P