[Federal Register Volume 79, Number 221 (Monday, November 17, 2014)]
[Proposed Rules]
[Pages 68377-68381]
From the Federal Register Online via the Government Publishing Office [www.gpo.gov]
[FR Doc No: 2014-27067]


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DEPARTMENT OF TRANSPORTATION

Federal Aviation Administration

14 CFR Part 39

[Docket No. FAA-2014-0227; Directorate Identifier 2013-NM-211-AD]
RIN 2120-AA64


Airworthiness Directives Lockheed Martin Corporation/Lockheed 
Martin Aeronautics Company Airplanes

AGENCY: Federal Aviation Administration (FAA), DOT.

ACTION: Supplemental notice of proposed rulemaking (NPRM); reopening of 
comment period.

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SUMMARY: We are revising an earlier proposed airworthiness directive 
(AD) that proposed to supersede AD 95-26-11, for all Lockheed Martin 
Corporation/Lockheed Martin Aeronautics Company Model L-1011 series 
airplanes. AD 95-26-11 currently requires repetitive inspections to 
detect cracking of the fittings that attach the aft pressure bulkhead 
to the fuselage stringers, repetitive inspections to detect cracking of 
the fittings and of the splice tab of the aft pressure bulkhead, and 
corrective actions if necessary. The NPRM proposed to reduce the 
compliance time; add inspections for cracking of certain aft fuselage 
skin panels; add a structural modification; and also add a post-
modification inspection program. The NPRM was prompted by a 
determination that the fittings at stringer attachments to the upper 
region of the aft pressure bulkhead are subject to widespread fatigue 
damage (WFD), which could result in cracking in the aft pressure 
bulkhead. This action revises the NPRM by reducing the post-structural 
modification repetitive inspection interval. We are proposing this 
supplemental NPRM (SNPRM) to prevent simultaneous failure of multiple 
stringer end fittings through fatigue cracking at the aft pressure 
bulkhead, which could lead to rapid decompression of the airplane. 
Since this action imposes an additional burden over that proposed in 
the NPRM, we are reopening the comment period to allow the public the 
chance to comment on these proposed changes.

DATES: We must receive comments on this SNPRM by January 2, 2015.

ADDRESSES: You may send comments, using the procedures found in 14 CFR 
11.43 and 11.45, by any of the following methods:
    <bullet> Federal eRulemaking Portal: Go to http://www.regulations.gov. Follow the instructions for submitting comments.
    <bullet> Fax: 202-493-2251.
    <bullet> 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.
    <bullet> 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.
    For service information identified in this AD, contact Lockheed 
Martin Corporation/Lockheed Martin Aeronautics Company, L1011 Technical 
Support Center, Dept. 6A4M, Zone 0579, 86 South Cobb Drive, Marietta, 
GA 30063-0579; telephone 770-494-5444; fax 770-494-5445; email 
<a href="/cdn-cgi/l/email-protection#f1bdc0c1c0c0df828481819e8385b19d9c929edf929e9c"><span class="__cf_email__" data-cfemail="6a265b5a5b5b44191f1a1a05181e2a0607090544090507">[email protected]</span></a>; Internet http://www.lockheedmartin.com/ams/tools/TechPubs.html. You may view this referenced service information 
at the FAA, Transport Airplane Directorate, 1601 Lind Avenue SW., 
Renton, WA. 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 http://

[[Page 68378]]

www.regulations.gov by searching for and locating Docket No. FAA-2014-
0227; 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, GA 30337; phone: 404-474-
5554; fax: 404-474-5605; email: <a href="/cdn-cgi/l/email-protection#ddbebcafb1f3aaf3baafbca49dbbbcbcf3bab2ab"><span class="__cf_email__" data-cfemail="523133203e7c257c3520332b123433337c353d24">[email protected]</span></a>.

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-2014-0227; 
Directorate Identifier 2013-NM-211-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 http://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

    We issued an NPRM to amend 14 CFR part 39 by adding an AD that 
would apply to all Lockheed Martin Corporation/Lockheed Martin 
Aeronautics Company Model L-1011 series airplanes. The NPRM published 
in the Federal Register on April 14, 2014 (79 FR 20819). The NPRM 
proposed to supersede Airworthiness Directive AD 95-26-11, Amendment 
39-9469 (60 FR 66870, December 27, 1995), for all Lockheed Martin 
Corporation/Lockheed Martin Aeronautics Company Model L-1011 series 
airplanes. AD 95-26-11 currently requires repetitive inspections to 
detect cracking of the fittings that attach the aft pressure bulkhead 
to the fuselage stringers, repetitive inspections to detect cracking of 
the fittings and of the splice tab of the aft pressure bulkhead, and 
corrective actions if necessary. The NPRM proposed to reduce the 
compliance time; add inspections for cracking of certain aft fuselage 
skin panels; add a structural modification; and also add a post-
modification inspection program.

Actions Since Previous NPRM Was Issued

    Since we issued the NPRM, we have determined that the post-
structural modification repetitive inspection interval should be 
revised.

Comments

    We gave the public the opportunity to comment on the NPRM (79 FR 
20819, April 14, 2014). The following presents the comment received on 
the NPRM, and the FAA's response to the comment.

Request To Revise Repetitive Inspection Compliance Time

    Lockheed requested that we revise the post-structural modification 
repetitive inspection interval in paragraph (s) of the NPRM (79 FR 
20819, April 14, 2014) from 13,875 flight cycles to 1,750 flight 
cycles. Paragraph (s) of the NPRM is identified as paragraph (r) in 
this SNPRM. Lockheed explained that the 1,750 flight cycles inspection 
interval meets the intent of Lockheed Service Bulletin 093-53-105, 
Revision 3, dated May 31, 2013.
    We agree to revise the repetitive inspection interval in paragraph 
(r) of this SNPRM to 1,750 flight cycles. The 13,875 flight cycles 
interval was a typographical error.

Revised Compliance Time

    We have also determined that if any cracking is found during any 
inspection specified in this SNPRM, it must be repaired before further 
flight in order to address the identified unsafe condition. We have 
removed (q) of this SNPRM, which deferred replacement of cracked 
fittings/splice tabs and certain inspections. We have revised the 
compliance time inparagraph (m)(1)(ii) of this AD from ``within 1,750 
flight cycles after finding the crack'' to ``before further flight.'' 
In addition, we added ``The deferral specified in paragraphs (m)(1) and 
(m)(2) of this AD cannot be done as of the effective date of this AD.''
    We have also revised paragraphs (n) and (o) of this SNPRM to remove 
the reference to paragraph (q) of this SNPRM.

FAA's Determination

    We are proposing this SNPRM 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. 
The change described above expands the scope of the NPRM (79 FR 20819, 
April 14, 2014). As a result, we have determined that it is necessary 
to reopen the comment period to provide additional opportunity for the 
public to comment on this SNPRM.

Proposed Requirements of This SNPRM

    This SNPRM would retain certain requirements of AD 95-26-11, 
Amendment 39-9469 (60 FR 66870, December 27, 1995). This SNPRM would 
reduce the compliance time; add inspections for cracking of certain aft 
fuselage skin panels; add a structural modification; and also add a 
post-modification inspection program.

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:

                                                 Estimated Costs
----------------------------------------------------------------------------------------------------------------
                                                                                                 Cost on U.S.
              Action                    Labor cost        Parts cost      Cost per product        operators
----------------------------------------------------------------------------------------------------------------
Inspections [actions retained      23 work-hours x $85              $0  $1,955 per           $50,830 per
 from AD 95-26-11, Amendment 39-    per hour = $1,955                    inspection cycle.    inspection cycle.
 9469 (60 FR 66870, December 27,    per inspection
 1995)].                            cycle.
Inspections and modification [new  185 work-hours x              6,750  22,475.............  584,350.
 proposed action].                  $85 per hour =
                                    $15,725.
----------------------------------------------------------------------------------------------------------------


[[Page 68379]]

    We estimate the following costs to do any necessary replacements 
that would be required based on the results of the proposed inspection. 
We have no way of determining the number of aircraft that might need 
these replacements:

                                               On-Condition Costs
----------------------------------------------------------------------------------------------------------------
                                                                                                     Cost per
                    Action                                Labor cost               Parts cost        product
----------------------------------------------------------------------------------------------------------------
Replacement of one fitting...................  16 work-hour x $85 per hour =              $250           $1,610
                                                $1,360.
----------------------------------------------------------------------------------------------------------------

    We have received no definitive data that would enable us to provide 
cost estimates for the other on-condition actions specified in this 
proposed 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

    We 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 this proposed 
regulation:
    (1) Is not a ``significant regulatory action'' under Executive 
Order 12866,
    (2) Is not a ``significant rule'' under the DOT Regulatory Policies 
and Procedures (44 FR 11034, February 26, 1979),
    (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

0
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]

0
2. Amend Sec.  39.13 by removing Airworthiness Directive (AD) 95-26-11, 
Amendment 39-9469 (60 FR 66870, December 27, 1995), and adding the 
following new AD:

Lockheed Martin Corporation/Lockheed Martin Aeronautics Company: 
Docket No. FAA-2014-0227; Directorate Identifier 2013-NM-211-AD.

(a) Comments Due Date

    We must receive comments by January 2, 2015.

(b) Affected ADs

    This AD replaces AD 95-26-11, Amendment 39-9469 (60 FR 66870, 
December 27, 1995).

(c) Applicability

    This AD applies to 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.

(d) Subject

    Air Transport Association (ATA) of America Code 53, Fuselage.

(e) Unsafe Condition

    This AD was prompted by a determination that the fittings at 
stringer attachments to the upper region of the aft pressure 
bulkhead are subject to widespread fatigue damage (WFD). We are 
issuing this AD to prevent simultaneous failure of multiple stringer 
end fittings through fatigue cracking at the aft pressure bulkhead, 
which could lead to rapid decompression of the airplane.

(f) Compliance

    Comply with this AD within the compliance times specified, 
unless already done.

(g) Retained Detailed Visual Inspection

    This paragraph restates the requirements of paragraph (a) of AD 
95-26-11, Amendment 39-9469 (60 FR 66870, December 27, 1995), with 
no changes. Perform a detailed visual inspection to detect cracking 
of the fittings that attach the aft pressure bulkhead to the 
fuselage stringers (hereinafter referred to as ``fittings'') at 
stringers 1 through 10 (right side) and at stringers 56 through 64 
(left side), at the later of the times specified in either paragraph 
(g)(1) or (g)(2) of this AD.
    (1) Prior to the accumulation of 20,000 total flight cycles; or
    (2) Within the next 25 flight cycles or 10 days after September 
28, 1995 (the effective date of AD 95-18-52, Amendment 39-9366 (60 
FR 47465, September 13, 1995)), whichever occurs earlier.

(h) Retained Corrective Action for Cracked Fitting

    This paragraph restates the requirements of paragraph (c) of AD 
95-26-11, Amendment 39-9469 (60 FR 66870, December 27, 1995), with 
no changes. If any cracked fitting is detected during the inspection 
required by paragraph (g) of this AD: Before further flight, 
accomplish the requirements of paragraphs (h)(1) and (h)(2) of this 
AD.
    (1) Replace the cracked fitting with a new fitting, or with a 
serviceable fitting on which a detailed visual inspection has been 
performed previously to detect cracking and that has been found to 
be free of cracks.
    (2) Perform a detailed visual inspection to detect cracking in 
the radius at the lower end of the vertical leg of the bulkhead T-
shaped frame between the stringer locations on either side of the 
stringer having the cracked fitting. If any cracked T-shaped frame 
is detected: Before further flight, repair in accordance with a 
method approved by the Manager, Atlanta Aircraft Certification 
Office (ACO), FAA.

(i) Retained Repetitive Fitting Inspections

    This paragraph restates the requirements of paragraph (d) of AD 
95-26-11, Amendment 39-9469 (60 FR 66870, December 27, 1995), with 
no changes. Repeat the inspections and other necessary actions 
required by paragraphs (g) and (h) of this AD at intervals not to 
exceed 1,800 flight cycles or 3,000 flight hours, whichever occurs 
earlier, until paragraph (j) of this AD is accomplished.

[[Page 68380]]

(j) Retained Eddy Current Surface Scan (ECSS) Inspections, and Related 
Investigative and Corrective Actions

    This paragraph restates the requirements of paragraph (e) of AD 
95-26-11, Amendment 39-9469 (60 FR 66870, December 27, 1995), with 
revised compliance times specified in paragraph (k) of this AD, 
exclusion of an ECSS inspection for certain airplanes, and new 
service information. Except as provided by paragraph (l) of this AD: 
At the applicable time specified in paragraph (k)(1) of this AD, 
accomplish the requirements of paragraphs (j)(1) and (j)(2) of this 
AD. Repeat the ECSS inspections thereafter at the compliance time 
specified in paragraph (k)(2) of this AD. Accomplishment of the ECSS 
inspection constitutes terminating action for the repetitive 
inspection requirements of paragraph (i) of this AD.
    (1) Perform an ECSS inspection to detect cracking of the 
fittings at stringers 1 through 14 (right side) and at stringers 52 
through 64 (left side), in accordance with the Accomplishment 
Instructions of Lockheed L-1011 Service Bulletin 093-53-105, 
Revision 1, dated November 17, 1995; or Lockheed Service Bulletin 
093-53-105, Revision 3, dated May 31, 2013; except for airplanes 
with a large (47-inch-wide) aft passenger door, an ECSS inspection 
of stringers 12, 13, 53, and 54 is not required by this paragraph. 
Except as provided by paragraph (m) of this AD, if any cracking is 
detected, prior to further flight, replace the fitting with a new 
fitting without pilot holes, rework the fitting, and perform various 
follow-on actions (i.e., bolt hole eddy current (BHEC), ECSS, and 
borescope inspections; and repair) of the inner and outer tee caps, 
in accordance with the Accomplishment Instructions of Lockheed L-
1011 Service Bulletin 093-53-105, Revision 1, dated November 17, 
1995; or Lockheed Service Bulletin 093-53-105, Revision 3, dated May 
31, 2013, except as required by paragraph (p) of this AD. As of the 
effective date of this AD, use only Lockheed Service Bulletin 093-
53-105, Revision 3, dated May 31, 2013, for accomplishing the 
actions required by this paragraph.
    (2) Perform an ECSS inspection to detect cracking of the lower 
(or inner) surface of the upper bonded splice tab of the bulkhead 
assembly at stringers 1 through 14 (right side) and at stringers 52 
through 64 (left side), in accordance with the Accomplishment 
Instructions of Lockheed L-1011 Service Bulletin 093-53-105, 
Revision 1, dated November 17, 1995; or Lockheed Service Bulletin 
093-53-105, Revision 3, dated May 31, 2013. As of the effective date 
of this AD, use only Lockheed Service Bulletin 093-53-105, Revision 
3, dated May 31, 2013, for accomplishing the actions required by 
this paragraph.
    (i) Except as provided by paragraph (m) of this AD, if any 
cracking is detected at the upper bonded splice tab, repair in 
accordance with a method approved by the Manager, Atlanta ACO, FAA.
    (ii) Except as provided by paragraph (m) of this AD, if any 
cracking is detected at a fastener, prior to further flight, perform 
a BHEC inspection to detect cracking of the forward flange of the 
inner tee cap, in accordance with the Accomplishment Instructions of 
Lockheed L-1011 Service Bulletin 093-53-105, Revision 1, dated 
November 17, 1995; or Lockheed Service Bulletin 093-53-105, Revision 
3, dated May 31, 2013. If any cracking is detected, prior to further 
flight, repair in accordance with the Accomplishment Instructions of 
Lockheed L-1011 Service Bulletin 093-53-105, Revision 1, dated 
November 17, 1995; or Lockheed Service Bulletin 093-53-105, Revision 
3, dated May 31, 2013, except as required by paragraph (p) of this 
AD. As of the effective date of this AD, use only Lockheed L-1011 
Service Bulletin 093-53-105, Revision 3, dated May 31, 2013, for 
accomplishing the actions required by this paragraph.

(k) New Revised Compliance Times for Paragraph (j) of This AD

    (1) Do the initial inspections required by paragraph (j) of this 
AD at the earlier of the times specified in paragraphs (k)(1)(i) and 
(k)(1)(ii) of this AD.
    (i) Prior to the accumulation of 20,000 total flight cycles, or 
within 30 days after January 11, 1996 (the effective date of date of 
AD 95-26-11, Amendment 39-9469 (60 FR 66870, December 27, 1995)), 
whichever occurs later.
    (ii) At the later of the times specified in paragraphs 
(k)(1)(ii)(A) and (k)(1)(ii)(B) of this AD.
    (A) Before the accumulation of 13,875 total flight cycles.
    (B) Within 365 days or 1,000 flight cycles after the effective 
date of this AD, whichever occurs first.
    (2) Repeat the inspections specified in paragraph (j) of this AD 
within 2,500 flight cycles after accomplishing the most recent 
inspection required by paragraph (j) of this AD, and repeat the 
inspection thereafter at intervals not to exceed 1,750 flight 
cycles.

(l) Retained Inspection Deferral for Paragraph (j) of this AD

    This paragraph restates the requirements of paragraph (f) of AD 
95-26-11, Amendment 39-9469 (60 FR 66870, December 27, 1995). 
Accomplishment of the initial ECSS inspections required by paragraph 
(j) of this AD may be deferred to a date within 120 days after 
January 11, 1996 (the effective date of AD 95-26-11), provided that, 
in the interim, a visual inspection as specified in paragraph (g) of 
this AD is accomplished within 30 days after January 11, 1996 (the 
effective date of AD 95-26-11), and repeated thereafter at intervals 
not to exceed 50 flight cycles. Once the ECSS inspections begin, the 
visual inspections may be terminated.

(m) Retained Inspection Deferral With Revised Compliance Time and New 
Deferral

    This paragraph restates the requirements of paragraph (g) of AD 
95-26-11, Amendment 39-9469 (60 FR 66870, December 27, 1995), with a 
revised compliance time, service information, and a new deferred 
action. As of the effective date of this AD, the deferral specified 
in paragraphs (m)(1) and (m)(2) of this AD cannot be done. If 
cracking was found before the effective date of this AD, the 
deferrel specified in paragraphs (m)(1) and (m)(2) of this AD may be 
done.
    (1) If two or more adjacent fittings on both sides of the 
cracked fittings or bonded splice tabs/fasteners are determined to 
be free of cracks by the ECSS inspection required by paragraphs 
(j)(1) and (j)(2) of this AD, repeat the ECSS inspection of the 
adjacent fittings thereafter at intervals not to exceed 600 flight 
cycles until the cracked fittings or splice tabs/fasteners are 
replaced or repaired, in accordance with the Accomplishment 
Instructions of Lockheed L-1011 Service Bulletin 093-53-105, 
Revision 1, dated November 17, 1995; or Lockheed Service Bulletin 
093-53-105, Revision 3, dated May 31, 2013. At the applicable time 
specified in paragraphs (m)(1)(i) and (m)(1)(ii) of this AD: Replace 
the cracked fitting and/or splice tab/fasteners, in accordance with 
the Accomplishment Instructions of Lockheed L-1011 Service Bulletin 
093-53-105, Revision 1, dated November 17, 1995; or Lockheed Service 
Bulletin 093-53-105, Revision 3, dated May 31, 2013. As of the 
effective date of this AD, use only Lockheed Service Bulletin 093-
53-105, Revision 3, dated May 31, 2013, for accomplishing the 
actions required by this paragraph.
    (i) For any crack found before the effective date of this AD: 
Within 2,500 flight cycles after finding the crack.
    (ii) For any crack found on or after the effective date of this 
AD: Before further flight after finding the crack.
    (2) If two or more adjacent fittings on both sides of the 
cracked fittings or bonded splice tabs/fasteners are determined to 
be free of cracks by the ECSS inspection required by paragraphs 
(j)(1) and (j)(2) of this AD, the follow-on inspection (i.e., BHEC, 
ECSS, and borescope inspections) of the inner and outer tee caps 
required by paragraph (j)(1) of this AD may also be deferred until 
the cracked fittings are replaced as required by paragraph (m)(1) of 
this AD, but no later than before the accumulation of 20,800 total 
flight cycles.

(n) New Repetitive Borescope Inspections of Certain End Fittings and 
Corrective Actions

    For airplanes with a large (47-inch-wide) aft passenger door: At 
the later of the times specified in paragraphs (n)(1) and (n)(2) of 
this AD, do a borescope inspection for cracking of the stringer end 
fittings at stringer locations 12, 13, 53, and 54; and do all 
applicable related investigative and corrective actions; in 
accordance with the Accomplishment Instructions of Lockheed Service 
Bulletin 093-53-105, Revision 3, dated May 31, 2013, except as 
specified in paragraph (p) of this AD. Do all applicable related 
investigative and corrective actions before further flight. Repeat 
the inspection of the stringer end fittings thereafter at intervals 
not to exceed 1,750 flight cycles until the actions required by 
paragraph (q) of this AD have been done.
    (1) Before the accumulation of 13,875 total flight cycles.
    (2) Within 365 days or 1,000 flight cycles after the effective 
date of this AD, whichever occurs earlier.

(o) New Repetitive Borescope Inspections of Fuselage Skin Panels

    For airplanes with a large (47-inch-wide) aft passenger door: At 
the later of the times specified in paragraphs (o)(1) and (o)(2) of 
this AD, do an ECSS inspection for cracking

[[Page 68381]]

of the left and right aft fuselage skin panels; and do all 
applicable related investigative and corrective actions; in 
accordance with the Accomplishment Instructions of Lockheed Service 
Bulletin 093-53-105, Revision 3, dated May 31, 2013, except as 
specified in paragraph (p) of this AD. Do all applicable related 
investigative and corrective actions before further flight. Repeat 
the inspection of the aft fuselage skin panels thereafter at 
intervals not to exceed 1,750 flight cycles until the modification 
required by paragraph (q) of this AD is done.
    (1) Before the accumulation of 13,875 total flight cycles.
    (2) Within 365 days or 1,000 flight cycles after the effective 
date of this AD, whichever occurs first.

(p) New Service Information Exception

    If any cracking is found during any inspection required by this 
AD, and Lockheed Service Bulletin 093-53-105, Revision 3, dated May 
31, 2013, specifies contacting Lockheed for appropriate action: 
Before further flight, repair the cracking in accordance with a 
method approved by the Manager, Atlanta ACO, FAA. As of the 
effective date of this AD, for a repair method to be approved by the 
Manager, Atlanta ACO, as required by this paragraph, the Manager's 
approval letter must specifically refer to this AD.

(q) New Pre-Structural Modification Inspections and Structural 
Modification

    Before the accumulation of 20,800 total flight cycles: Do the 
applicable actions specified in paragraphs (q)(1) and (q)(2) of this 
AD.
    (1) Perform pre-structural modification inspections by doing the 
actions required by paragraphs (j), (n), and (o) of this AD.
    (2) Perform a structural modification of the aft pressure 
bulkhead by removing and replacing all stringer end fittings with 
new or refurbished fittings at stringers 1 through 14, and 52 
through 64, in accordance with the Accomplishment Instructions of 
Lockheed Service Bulletin 093-53-105, Revision 3, dated May 31, 
2013.

(r) New Post-Structural Modification Repetitive Inspections

    Within 13,875 flight cycles after performing the actions 
required by paragraph (q)(2) of this AD: Do the actions specified in 
paragraphs (j), (n), and (o) of this AD, and repeat thereafter at 
intervals not to exceed 1,750 flight cycles.

(s) No Reporting Requirement

    Although Lockheed Service Bulletin 093-53-105, Revision 3, dated 
May 31, 2013, referenced in this AD specifies to submit certain 
information to the manufacturer, this AD does not include that 
requirement.

(t) Alternative Methods of Compliance (AMOCs)

    (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 paragraph 
(u)(1) 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.

(u) Related Information

    (1) 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, GA 
30337; phone: 404-474-5554; fax: 404-474-5605; email: 
<a href="/cdn-cgi/l/email-protection#412220332d6f366f26332038012720206f262e37"><span class="__cf_email__" data-cfemail="fb989a8997d58cd59c899a82bb9d9a9ad59c948d">[email protected]</span></a>.
    (2) For service information identified in this AD, contact 
Lockheed Martin Corporation/Lockheed Martin Aeronautics Company, 
L1011 Technical Support Center, Dept. 6A4M, Zone 0579, 86 South Cobb 
Drive, Marietta, GA 30063-0579; telephone 770-494-5444; fax 770-494-
5445; email <a href="/cdn-cgi/l/email-protection#3d710c0d0c0c134e484d4d524f497d51505e52135e5250"><span class="__cf_email__" data-cfemail="fbb7cacbcacad5888e8b8b94898fbb97969894d5989496">[email protected]</span></a>; Internet http://www.lockheedmartin.com/ams/tools/TechPubs.html. You may view this 
service information at the FAA, Transport Airplane Directorate, 1601 
Lind Avenue SW., Renton, WA. For information on the availability of 
this material at the FAA, call 425-227-1221.

    Issued in Renton, Washington, on November 5, 2014.
Jeffrey E. Duven,
Manager, Transport Airplane Directorate, Aircraft Certification 
Service.
[FR Doc. 2014-27067 Filed 11-14-14; 8:45 am]
BILLING CODE 4910-13-P


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