Document ID: FAA-2011-0919-0001
Agency: faa
Document Type: Proposed Rule
Title: Airworthiness Directives: Lockheed Martin Corp./Lockheed Martin Aeronautics Co. Model L-1011 Series Airplanes
Posted Date: 2011-09-21T04:00Z

[Federal Register Volume 76, Number 183 (Wednesday, September 21, 2011)]
[Proposed Rules]
[Pages 58416-58420]
From the Federal Register Online via the Government Printing Office [www.gpo.gov]
[FR Doc No: 2011-24270]

 ========================================================================
 Proposed Rules
                                                 Federal Register
 ________________________________________________________________________
 
 This section of the FEDERAL REGISTER contains notices to the public of 
 the proposed issuance of rules and regulations. The purpose of these 
 notices is to give interested persons an opportunity to participate in 
 the rule making prior to the adoption of the final rules.
 
 ========================================================================
 

  Federal Register / Vol. 76, No. 183 / Wednesday, September 21, 2011 / 
Proposed Rules  

[[Page 58416]]

DEPARTMENT OF TRANSPORTATION

Federal Aviation Administration

14 CFR Part 39

[Docket No. FAA-2011-0919; Directorate Identifier 2010-NM-088-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 adopt a new airworthiness directive (AD) for 
certain Model L-1011 series airplanes. This proposed AD would require 
repetitive inspections for cracking of the wing rear spar and upper 
surface zones, and repair if necessary. This proposed AD results from a 
damage tolerance analysis conducted by the manufacturer indicating that 
fatigue cracking could occur in those areas. We are proposing this AD 
to detect and correct such fatigue cracking, which could result in 
cracking that grows large enough to reduce the wing strength below 
certificated requirements and possibly cause fracture of the rear spar, 
resulting in extensive damage to the wing and possible fuel leaks.

DATES: We must receive comments on this proposed AD by November 7, 
2011.

ADDRESSES: You may send comments by any of the following methods:
     Federal eRulemaking Portal: Go to http://www.regulations.gov. Follow the instructions for submitting comments.
     Fax: 202-493-2251.
     Mail: U.S. Department of Transportation, Docket 
Operations, M-30, West Building Ground Floor, Room W12-140, 1200 New 
Jersey Avenue, SE., Washington, DC 20590.
     Hand Delivery: U.S. Department of Transportation, Docket 
Operations, M-30, West Building Ground Floor, Room W12-140, 1200 New 
Jersey Avenue, SE., Washington, DC 20590, between 9 a.m. and 5 p.m., 
Monday through Friday, except Federal holidays.
    For service information identified in this proposed 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; telephone 770-494-5444; fax 770-494-
5445; e-mail ams.portal@lmco.com; Internet http://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 http://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-2011-0919; 
Directorate Identifier 2010-NM-088-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 previously issued AD 94-05-01, Amendment 39-8839 (59 FR 10275, 
March 4, 1994), and AD 2000-21-01, Amendment 39-11933 (65 FR 62994, 
October 20, 2000), which require modifications to extend the life of 
the wing rear spar inboard area. The modifications required by those 
two ADs removed cracks in the wing upper skin and installed repair 
bushings as necessary. The lower spar cap was modified by adding nested 
angles and cold working the attachment holes.
    Based upon a damage tolerance analysis, additional inspections are 
required to ensure the structural integrity of the structure modified 
in accordance with those two ADs as well as the adjoining baseline 
structure. If cracking is undetected and unrepaired, it could result in 
cracking that grows large enough to reduce the wing strength below 
certificated requirements and possibly cause fracture of the rear spar, 
resulting in extensive damage to the wing and possible fuel leaks.

Relevant Service Information

    We have reviewed Lockheed Service Bulletin 093-57-226, dated August 
31, 2009. This service bulletin describes procedures for repetitive 
eddy current non-destructive inspections (NDI) and detailed inspections 
for cracking of the wing rear spar and upper surface zones. The service 
bulletin identifies inspections for the airplane models in the zones 
identified in the following table, titled ``Inspections.''

[[Page 58417]]

                           Table--Inspections
------------------------------------------------------------------------
        Airplane models             Inspection type          Zone(s)
------------------------------------------------------------------------
L-1011-385-1, L-1011-385-1-14,  Non-destructive.......  1A through 1E.
 and L-1011-385-1-15.
                               -----------------------------------------
                                Detailed Visual.......  1F.
------------------------------------------------------------------------
L-1011-385-3..................  Non-destructive.......  3A through 3E.
                                Detailed Visual.......  3F.
------------------------------------------------------------------------

     For airplanes on which cracking is found during any inspection, 
this service information specifies a bolt hole eddy current inspection 
to verify the cracking. The corrective actions for cracking include 
repairing cracking if the cracking is within specified limits, or 
contacting the manufacturer for repair instructions if the cracking is 
not within specified limits.

Related Rulemaking

    AD 94-05-01, Amendment 39-8839 (59 FR 10275, March 4, 1994), and AD 
2000-21-01, Amendment 39-11933 (65 FR 62994, October 20, 2000), specify 
structural modification installations on Model L-1011 series airplanes. 
This proposed AD would not change the requirements of AD 94-05-01 and 
AD 2000-21-01. However, this proposed AD would require new inspections 
for structures affected by the modifications required by those two ADs.

FAA's Determination and Requirements of this Proposed AD

    We are proposing this AD because we evaluated all relevant 
information and determined the unsafe condition described previously is 
likely to exist or develop in other products of these same type 
designs. This proposed AD would require accomplishing the actions 
specified in Lockheed Service Bulletin 093-57-226, dated August 31, 
2009, described previously.

Differences Between the Proposed AD and the Service Information

    This proposed AD specifies initial compliance times and repetitive 
inspection intervals that differ from those contained in Lockheed 
Service Bulletin 093-57-226, dated August 31, 2009. The changes have 
been coordinated with Lockheed Martin and they concur with the FAA's 
position. The compliance times were changes to simplify the inspection 
requirements. We also propose that all crack findings be repaired 
before further flight. We have determined that the compliance times, as 
proposed, represent the maximum interval of time allowable for the 
affected airplanes to continue to safely operate before the inspections 
and repairs, if necessary, are done.
    Although that service bulletin specifies that operators may contact 
the manufacturer for disposition of certain repairs, this proposed AD 
would require operators to repair those conditions in accordance with a 
method approved by the FAA.

Interim Action

    We consider this proposed AD interim action. If final action is 
later identified, we might consider further rulemaking then.

Costs of Compliance

    We estimate that this proposed AD affects 4 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
----------------------------------------------------------------------------------------------------------------
Models: L-1011-385-1, L-1011-385- 21 work-hours x $85              $0   $1,785 per           $3,570 per
 1-14, L-1011-385-1-15, Zones 1A   per hour = $1,785                     inspection cycle.    inspection cycle
 through 1E (Non-destructive       per inspection                                             (2 airplanes).
 Inspection).                      cycle.
Models: L-1011-385-1, L-1011-385- 5 work-hours x $85                0   $425 per inspection  $850 per inspection
 1-14, L-1011-385-1-15, Zone 1F    per hour = $425                       cycle.               cycle
 (Detailed Inspection).            per inspection                                            (2 airplanes).
                                   cycle.
Model: L-1011-385-3, Zones 1A     24 work-hours x $85               0   $2,040 per           $4,080 per
 through 1E (Non-destructive       per hour = $2,040                     inspection cycle.    inspection cycle
 Inspection).                      per inspection                                            (2 airplanes).
                                   cycle.
Model: L-1011-385-3, Zone 1F      5 work-hours x $85                0   $425 per inspection  $850 per inspection
 (Detailed Inspection).            per hour = $425                       cycle.               cycle
                                   per inspection                                            (2 airplanes).
                                   cycle.
----------------------------------------------------------------------------------------------------------------

    We have received no definitive data that would enable us to provide 
cost estimates for the 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

[[Page 58418]]

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

    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 adding the following new AD:

Lockheed Martin Corporation/Lockheed Martin Aeronautics Company: 
Docket No. FAA-2011-0919; Directorate Identifier 2010-NM-088-AD.

Comments Due Date

    (a) We must receive comments by November 7, 2011.

Affected ADs

    (b) None.

Applicability

    (c) This AD applies to 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, serial numbers 1002 through 1250 inclusive.

Subject

    (d) Air Transport Association (ATA) of America Code 57, Wings.

Unsafe Condition

    (e) This AD results from a damage tolerance analysis conducted 
by the manufacturer that indicates fatigue cracking could occur in 
the wing rear spar and upper surface zones. The Federal Aviation 
Administration is issuing this AD to detect and correct such fatigue 
cracking, which could result in cracking that grows large enough to 
reduce the wing strength below certificated requirements and 
possibly cause fracture of the rear spar, resulting in extensive 
damage to the wing and possible fuel leaks.

Compliance

    (f) You are responsible for having the actions required by this 
AD performed within the compliance times specified, unless the 
actions have already been done.

Inspections of Wing Rear Spar and Upper Surface Zones, and Corrective 
Actions

    (g) At the applicable time specified in paragraph (k) of this 
AD, do eddy current non-destructive inspections (NDI) and detailed 
inspections for cracking at the applicable zones specified in 
paragraph (g)(1) or (g)(2) of this AD, in accordance with the 
Accomplishment Instructions of Lockheed Service Bulletin 093-57-226, 
dated August 31, 2009. Repeat the inspections thereafter at the 
applicable interval specified in Table 1 of this AD.
    (1) For Model L-1011-385-1, L-1011-385-1-14, and L-1011-385-1-15 
airplanes: Zones 1A through 1E, and Zone 1F.
    (2) For Model L-1011-385-3 airplanes: Zones 3A through 3E, and 
Zone 3F.

Additional Inspection if Cracking is Found

    (h) Except as specified in paragraph (j) of this AD, if any 
cracking is detected during any inspection required by paragraph (g) 
of this AD: Before further flight, remove the fastener(s) at the 
suspect area, as defined in Lockheed Service Bulletin 093-57-226, 
dated August 31, 2009; and do a secondary eddy current inspection to 
detect cracking of fastener holes with suspected crack indications; 
in accordance with the Accomplishment Instructions of Lockheed 
Service Bulletin 093-57-226, dated August 31, 2009.

Repair

    (i) Except as specified in paragraph (j) of this AD, if a crack 
finding is confirmed by the inspection required by paragraph (h) of 
this AD and the cracking is within the allowable repair limits 
specified in Lockheed Martin Repair Drawing LCC7622-369, Revision 
March 30, 1995: Before further flight, repair the cracking, in 
accordance with Lockheed Martin Repair Drawing LCC7622-369, Revision 
March 30, 1995. If a crack finding confirmed by the inspection 
required by paragraph (h) of this AD is not within the allowable 
repair limits specified in Lockheed Martin Repair Drawing LCC7622-
369, Revision March 30, 1995: Before further flight, repair the 
cracking, in accordance with a method approved by the Manager, 
Atlanta Aircraft Certification Office (ACO), FAA. 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.

Exception to Service Bulletin

    (j) If any cracking is found during any inspection required by 
this AD, and Lockheed Service Bulletin 093-57-226, dated August 31, 
2009; or Lockheed Martin Repair Drawing LCC7622-369, Revision March 
30, 1995; specifies contacting Lockheed for appropriate action: 
Before further flight, repair the cracking in accordance with a 
method approved by the Manager, Atlanta ACO, FAA. 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.

Compliance Times for Inspections

    (k) Do the inspections required by paragraph (g) of this AD at 
the applicable time specified in table 1 of this AD.

                                    Table 1--Compliance Times for Inspections
----------------------------------------------------------------------------------------------------------------
 
----------------------------------------------------------------------------------------------------------------
     Airplane models and zones                         Compliance time                      Repetitive interval
                                                   (whichever occurs later)                   (not to exceed)
----------------------------------------------------------------------------------------------------------------
L-1011-385-1 having accumulated     Within 7,000 flight cycles  Within 1,000 flight        1,100 flight cycles.
 fewer than 7,000 flight cycles      or 10 years after the       cycles after the
 after the accomplishment of         accomplishment of           effective date of this
 Lockheed Martin Service Bulletin    Lockheed Martin Service     AD.
 093-57-184, 093-57-196, or 093-57-  Bulletin 093-57-184, 093-
 215; as of the effective date of    57-196, or 093-57-215,
 this AD; Zones 1A through 1E (Non-  whichever occurs first.
 destructive Inspection (NDI)).

[[Page 58419]]

 
L-1011-385-1 having accumulated     Within 7,000 flight cycles  Within 90 flight cycles    90 flight cycles.
 fewer than 7,000 flight cycles      or 10 years after the       or 30 days after the
 after the accomplishment of         accomplishment of           effective date of this
 Lockheed Martin Service Bulletin    Lockheed Martin Service     AD, whichever occurs
 093-57-184, 093-57-196, or 093-57-  Bulletin 093-57-184, 093-   later.
 215; as of the effective date of    57-196, or 093-57-215,
 this AD; Zone 1F (Detailed          whichever occurs first.
 Inspection).
L-1011-385-1 having accumulated     Within 1,000 flight cycles  N/A......................  1,100 flight cycles.
 7,000 flight cycles or more         or 12 months after the
 flight cycles after the             effective date of this
 accomplishment of Lockheed Martin   AD, whichever occurs
 Service Bulletin 093-57-184, 093-   first.
 57-196, or 093-57-215; as of the
 effective date of this AD; Zones
 1A through 1E (NDI).
L-1011-385-1 having accumulated     Within 90 flight cycles     Within 30 days after the   90 flight cycles.
 7,000 flight cycles or more after   after the effective date    effective date of this
 the accomplishment of Lockheed      of this AD.                 AD.
 Martin Service Bulletin 093-57-
 184, 093-57-196, or 093-57-215;
 as of the effective date of this
 AD; Zone 1F (Detailed Inspection).
L-1011-385-1-14 having accumulated  Within 6,900 flight cycles  Within 1,000 flight        900 flight cycles.
 fewer than 6,900 flight cycles      or 10 years after the       cycles after the
 after the accomplishment of         accomplishment of           effective date of this
 Lockheed Martin Service Bulletin    Lockheed Martin Service     AD.
 093-57-184, 093-57-196, or 093-57-  Bulletin 093-57-184, 093-
 215; as of the effective date of    57-196, or 093-57-215,
 this AD; Zones 1A through 1E        whichever occurs first.
 (NDI).
L-1011-385-1-14 having accumulated  Within 6,900 flight cycles  Within 90 flight cycles    90 flight cycles.
 fewer than 6,900 flight cycles      or 10 years after the       or 30 days after the
 after the accomplishment of         accomplishment of           effective date of this
 Lockheed Martin Service Bulletin    Lockheed Martin Service     AD, whichever occurs
 093-57-184, 093-57-196, or 093-57-  Bulletin 093-57-184, 093-   later.
 215; as of the effective date of    57-196, or 093-57-215,
 this AD; Zone 1F (Detailed          whichever occurs first.
 Inspection).
L-1011-385-1-14 having accumulated  Within 1,000 flight cycles  N/A......................  900 flight cycles.
 6,900 or more flight cycles after   or 12 months after the
 the accomplishment of Lockheed      effective date of this
 Martin Service Bulletin 093-57-     AD, whichever occurs
 184, 093-57-196, or 093-57-215;     first.
 as of the effective date of this
 AD; Zones 1A through 1E (NDI).
L-1011-385-1-14 having accumulated  Within 90 flight cycles     Within 30 days after the   90 flight cycles.
 6,900 or more flight cycles after   after the effective date    effective date of this
 the accomplishment of Lockheed      of this AD.                 AD.
 Martin Service Bulletin 093-57-
 184, 093-57-196, or 093-57-215;
 as of the effective date of this
 AD; Zone 1F (Detailed Inspection).
L-1011-385-1-15 having accumulated  Within 5,600 flight cycles  Within 1,000 flight        500 flight cycles.
 fewer than 5,600 flight cycles      or 10 years after the       cycles after the
 after the accomplishment of         accomplishment of           effective date of this
 Lockheed Martin Service Bulletin    Lockheed Martin Service     AD.
 093-57-184, 093-57-196, or 093-57-  Bulletin 093-57-184, 093-
 215; as of the effective date of    57-196, or 093-57-215,
 this AD; Zones 1A through 1E        whichever occurs first.
 (NDI).
L-1011-385-1-15 having accumulated  Within 5,600 flight cycles  Within 60 flight cycles    60 flight cycles.
 fewer than 5,600 flight cycles      or 10 years after the       or 30 days after the
 after the accomplishment of         accomplishment of           effective date of this
 Lockheed Martin Service Bulletin    Lockheed Martin Service     AD, whichever occurs
 093-57-184, 093-57-196, or 093-57-  Bulletin 093-57-184, 093-   later.
 215; as of the effective date of    57-196, or 093-57-215,
 this AD; Zone 1F (Detailed          whichever occurs first.
 Inspection).

[[Page 58420]]

 
L-1011-385-1-15 having accumulated  Within 1,000 flight cycles  N/A......................  500 flight cycles.
 5,600 or more flight cycles after   or 12 months after the
 the accomplishment of Lockheed      effective date of this
 Martin Service Bulletin 093-57-     AD, whichever occurs
 184, 093-57-196, or 093-57-215;     first.
 as of the effective date of this
 AD; Zones 1A through 1E (NDI).
L-1011-385-1-15 having accumulated  Within 60 flight cycles     Within 30 days after the   60 flight cycles.
 5,600 or more flight cycles after   after the effective date    effective date of this
 the accomplishment of Lockheed      of this AD.                 AD.
 Martin Service Bulletin 093-57-
 184, 093-57-196, or 093-57-215;
 as of the effective date of this
 AD; Zone 1F (Detailed Inspection).
L-1011-385-3 having accumulated     Within 8,400 flight cycles  Within 1,000 flight        1,200 flight cycles.
 fewer than 8,400 flight cycles      or 10 years after the       cycles after the
 after the accomplishment of         accomplishment of           effective date of this
 Lockheed Martin Service Bulletin    Lockheed Martin Service     AD.
 093-57-184, 093-57-196, or 093-57-  Bulletin 093-57-184, 093-
 215; as of the effective date of    57-196, or 093-57-215,
 this AD; Zones 1A through 1E        whichever occurs first.
 (NDI).
L-1011-385-3 having accumulated     Within 90 flight cycles or  Within 85 flight cycles    85 flight cycles.
 fewer than 8,400 flight cycles      30 days after the           or 30 days after the
 after the accomplishment of         effective date of this      effective date of this
 Lockheed Martin Service Bulletin    AD, whichever occurs        AD, whichever occurs
 093-57-184, 093-57-196, or 093-57-  later.                      later.
 215; as of the effective date of
 this AD; Zone 1F (Detailed
 Inspection).
L-1011-385-3 having accumulated     Within 1,000 flight cycles  N/A......................  1,200 flight cycles.
 8,400 or more flight cycles after   or 12 months after the
 the accomplishment of Lockheed      effective date of this
 Martin Service Bulletin 093-57-     AD, whichever occurs
 184, 093-57-196, or 093-57-215;     first.
 as of the effective date of this
 AD; Zones 1A through 1E (NDI).
L-1011-385-3 having accumulated     Within 85 flight cycles     Within 30 days after the   85 flight cycles.
 8,400 or more flight cycles after   after the effective date    effective date of this
 the accomplishment of Lockheed      of this AD.                 AD.
 Martin Service Bulletin 093-57-
 184, 093-57-196, or 093-57-215;
 as of the effective date of this
 AD; Zone 1F (Detailed Inspection).
----------------------------------------------------------------------------------------------------------------

Alternative Methods of Compliance (AMOCs)

    (l)(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

    (m) For more information about this AD, contact Carl Gray, 
Aerospace Engineer, Airframe Branch, ACE-117A, FAA, Atlanta ACO, 
1701 Columbia Avenue, College Park, Georgia 30337; phone: 404-474-
5554; fax: 404-474-5606; e-mail: Carl.W.Gray@faa.gov.

    Issued in Renton, Washington, on September 14, 2011.
Ali Bahrami,
Manager, Transport Airplane Directorate, Aircraft Certification 
Service.

[FR Doc. 2011-24270 Filed 9-20-11; 8:45 am]
BILLING CODE 4910-13-P