[Federal Register Volume 79, Number 103 (Thursday, May 29, 2014)]
[Proposed Rules]
[Pages 30748-30751]
From the Federal Register Online via the Government Publishing Office [www.gpo.gov]
[FR Doc No: 2014-12448]


 ========================================================================
 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. 79, No. 103 / Thursday, May 29, 2014 / 
Proposed Rules  

[[Page 30748]]



DEPARTMENT OF TRANSPORTATION

Federal Aviation Administration

14 CFR Part 39

[Docket No. FAA-2014-0290; Directorate Identifier 2012-NM-210-AD]
RIN 2120-AA64


Airworthiness Directives; Lockheed Martin Corporation/Lockheed 
Martin Aeronautics Company 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 Lockheed Martin Corporation/Lockheed Martin Aeronautics Company 
Model L-1011 series airplanes. This proposed AD was prompted by reports 
of cracked rib cap castellations. This proposed AD would require 
repetitive inspections for castellation and skin clips cracked or 
damaged between stringers and cracked stringer clips of the wing box 
pylon back-up structure, and front spar to rear spar, repetitive 
inspections for cracking, damage, or failure of the pylon back-up 
torque box structure; repetitive inspections for cracking or damage of 
the wing box external areas at the drag brace aft wing fitting; and 
repetitive inspections of the outer surface of the wing upper and lower 
skins for cracks or damage along the rib attachment at the fastener 
holes and between the two rows of attachment; and corrective actions if 
necessary. We are proposing this AD to detect and correct cracked or 
damaged rib cap castellations, which could degrade the structural 
capabilities of the airplane.

DATES: We must receive comments on this proposed AD by July 14, 2014.

ADDRESSES: You may send comments, using the procedures found in 14 CFR 
11.43 and 11.45, 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: 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, 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 
[email protected]; 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://www.regulations.gov by searching for and locating Docket No. FAA-2014-
0290; 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: 404-474-5605; email: [email protected].

SUPPLEMENTARY INFORMATION:

Comments Invited

    We invite you to send any written relevant data, views, or 
arguments about this proposal. Send your comments to an address listed 
under the ADDRESSES section. Include ``Docket No. FAA-2014-0290; 
Directorate Identifier 2012-NM-210-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 have received multiple reports of cracked rib cap castellations 
on Model L-1011-385-1 airplanes. The predominance of cracked 
castellations have been found on the upper cap at inboard wing station 
(IWS) 555.0. Cracked castellations were also found on the lower cap at 
IWS 555.0, and at a few locations on the upper caps at IWS 529.4 and 
503.76. Castellation cracks may propagate into the rib cap proper, and 
with several castellations cracked and the rib cap severed, fail safe 
capability cannot be analytically proven. Continued operation in this 
condition can result in severe additional damage and loss of stiffness 
in the pylon back-up structure creating a potential flutter hazard. 
This condition, if not corrected, could result in degraded structural 
capabilities of the airplane.

Relevant Service Information

    We reviewed Lockheed Service Bulletin 093-57-207, Revision 5, dated 
November 14, 2008. This service bulletin describes procedures for:
     A repetitive detailed inspection of the wing box pylon 
back-up structure, front spar to rear spar, for castellation and/or 
skin clips cracked or damaged between stringers and cracked stringer 
clips.
     A repetitive general visual inspection for cracking or 
damage of the pylon back-up torque box structure.
     A repetitive general visual inspection for cracking, 
damage, or failure of the wing box external areas at the drag brace aft 
wing fitting.
     A repetitive general visual inspection for cracking or 
damage of the outer surface of the wing upper and

[[Page 30749]]

lower skins for cracks or damage along the rib attachment at the 
fastener holes and between the two rows of attachments.
    Lockheed Service Bulletin 093-57-207, Revision 5, dated November 
14, 2008, describes corrective actions as replacing cracked clips with 
a new clip, and stop drilling a single cracked castellation with a 
crack that is no longer than three quarters of an inch, provided the 
two adjacent castellations on either side are crack free (i.e., every 
third castellation may be cracked and stop drilled). Additionally, this 
service bulletin specifies that if more than two consecutive 
castellations are cracked, the airplane should be modified by 
installing new rib caps or the cracked castellations repaired by 
replacing a segment of the rib cap using cap splices. This service 
bulletin states that all other damaged structural items should be 
repaired in accordance with the best shop practices, following 
procedures in Structural Repair Manual 57-12-00 and to advise Lockheed 
of all such repairs.
    Lockheed Service Bulletin 093-57-207, Revision 5, dated November 
14, 2008, describes a compliance time of before the accumulation of 
15,000 total flight cycles or 27,000 total flight hours, whichever 
occurs first. The repetitive inspection interval is described as not to 
exceed 3,600 flight cycles or 7,200 flight hours, whichever occurs 
first.

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 require accomplishing the actions specified 
in the service information described previously, except as discussed 
under ``Differences Between the Proposed AD and the Service 
Information.'' This proposed AD also requires sending a report of crack 
findings during any inspection required by this AD to the Manager, 
Atlanta Aircraft Certification Office.

Differences Between the Proposed AD and the Service Information

    Although Lockheed Service Bulletin 093-57-207, Revision 5, dated 
November 14, 2008, specifies that operators may contact the 
manufacturer for disposition of certain repair conditions, this 
proposed AD would require operators to repair those conditions in 
accordance with a method approved by the FAA.

Related AD

    This proposed AD is related to AD 94-05-01, Amendment 39-8839 (59 
FR 10275, March 4, 1994). For Model L-1011-385 series airplanes, serial 
numbers 1002 through 1188, paragraph (c) of AD 94-05-01 specifies that 
doing the modification specified in Lockheed Service Bulletin 093-57-
207, Revision 3, dated November 22, 1991, constitutes terminating 
action for the repetitive inspection requirements of that service 
bulletin. We have determined that the modification no longer 
constitutes terminating action for the repetitive inspections, and this 
proposed AD would require repetitive inspections.

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
--------------------------------------------------------------------------------------------------------------------------------------------------------
               Action                         Labor cost             Parts cost       Cost per product                Cost on U.S. operators
--------------------------------------------------------------------------------------------------------------------------------------------------------
Inspections........................  41 work-hours x $85 per                  $0   $3,485 per inspection  $90,610 per inspection cycle.
                                      hour = $3,485 per                             cycle.
                                      inspection cycle.
--------------------------------------------------------------------------------------------------------------------------------------------------------

    We estimate the following costs to do any necessary repairs 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 
repairs:

                                               On-Condition Costs
----------------------------------------------------------------------------------------------------------------
             Action                      Labor cost              Parts cost              Cost per product
----------------------------------------------------------------------------------------------------------------
Modification (Up to 12 rib caps   96 work-hours x $85 per   $15,000 per rib cap  $23,160 per rib cap.
 per airplane).                    hour = $8,160 per rib
                                   cap.
----------------------------------------------------------------------------------------------------------------

    Other than the modification stated above, we have received no 
definitive data that would enable us to provide cost estimates for the 
crack repair actions specified in this proposed AD.

Paperwork Reduction Act

    A federal agency may not conduct or sponsor, and a person is not 
required to respond to, nor shall a person be subject to 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 control 
number for the collection of information required by this AD is 2120-
0056. The paperwork cost associated with this AD has been detailed in 
the Costs of Compliance section of this document and includes time for 
reviewing instructions, as well as completing and reviewing the 
collection of information. Therefore, all reporting associated with 
this AD is 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.

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

[[Page 30750]]

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. The FAA amends Sec.  39.13 by adding the following new airworthiness 
directive (AD):

Lockheed Martin Corporation/Lockheed Martin Aeronautics Company: 
Docket No. FAA-2014-0290; Directorate Identifier 2012-NM-210-AD.

(a) Comments Due Date

    We must receive comments by July 14, 2014.

(b) Affected ADs

    None.

(c) Applicability

    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, as 
identified in Lockheed Service Bulletin 093-57-207, Revision 5, 
dated November 14, 2008.

(d) Subject

    Joint Aircraft System Component (JASC)/Air Transport Association 
(ATA) of America Code 57, Wings.

(e) Unsafe Condition

    This AD was prompted by reports of cracked rib cap 
castellations. We are issuing this AD to detect and correct cracked 
or damaged rib cap castellations, which could degrade the structural 
capabilities of the airplane.

(f) Compliance

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

(g) Repetitive Wing Inspections

    For Model L-1011-385-1, L-1011-385-1-14, L-1011-385-1-15, and L-
1011-385-3 airplanes, serial numbers 1189 and subsequent: At the 
applicable compliance time specified in paragraphs (h)(1), (h)(2), 
and (h)(3) of this AD, do the inspections specified in paragraphs 
(g)(1) through (g)(4) of this AD. Repeat the inspections thereafter 
at intervals not to exceed 3,600 flight cycles or 7,200 flight 
hours, whichever occurs first.
    (1) Do a detailed inspection for castellation and skin clips 
cracked or damaged (including cracks, loose or missing fasteners, 
oversized and missed drilled fastener holes, corrosion, dents, 
scratches and other signs of distress) between stringers and cracked 
stringer clips of the wing box pylon back-up structure, and front 
spar to rear spar, in accordance with the Accomplishment 
Instructions of Lockheed Service Bulletin 093-57-207, Revision 5, 
dated November 14, 2008.
    (2) Do a general visual inspection for cracking or damage 
(including cracks, loose or missing fasteners, oversized and missed 
drilled fastener holes, corrosion, dents, scratches and other signs 
of distress) of the pylon back-up torque box structure, in 
accordance with the Accomplishment Instructions of Lockheed Service 
Bulletin 093-57-207, Revision 5, dated November 14, 2008.
    (3) Do a general visual inspection for cracking, damage 
(including cracks, loose or missing fasteners, oversized and missed 
drilled fastener holes, corrosion, dents, scratches and other signs 
of distress), or failure of the wing box external areas at the drag 
brace aft wing fitting, in accordance with the Accomplishment 
Instructions of Lockheed Service Bulletin 093-57-207, Revision 5, 
dated November 14, 2008.
    (4) Do a general visual inspection for cracking or damage 
(including cracks, loose or missing fasteners, oversized and missed 
drilled fastener holes, corrosion, dents, scratches and other signs 
of distress) of the outer surface of the wing upper and lower skins 
for cracks along the rib attachment at the fastener holes and 
between the two rows of attachments, in accordance with the 
Accomplishment Instructions of Lockheed Service Bulletin 093-57-207, 
Revision 5, dated November 14, 2008.

(h) Compliance Times for Paragraph (g) of This AD

    (1) For airplanes that have not accomplished the inspections 
described in Lockheed Service Bulletin 093-57-207 prior to the 
effective date of this AD: at the later of the compliance times 
specified in paragraphs (h)(1)(i) and (h)(1)(ii) of this AD.
    (i) Before the accumulation of 15,000 total flight cycles or 
27,000 total flight hours, whichever occurs first.
    (ii) Within 1,800 flight cycles or 3,600 flight hours, whichever 
occurs first, after the effective date of this AD.
    (2) For airplanes that have accomplished the inspections 
described in Lockheed Service Bulletin 093-57-207 prior to the 
effective date of this AD: Within 3,600 flight cycles or 7,200 
flight hours, whichever occurs first, after the competition of the 
most recent inspections, except as specified in paragraph (h)(3) of 
this AD.
    (3) For rib caps that have been modified as described in 
Lockheed Service Bulletin 093-57-207: Before the accumulation of 
15,000 total flight cycles or 27,000 total flight hours, whichever 
occurs first, for that rib cap only.

(i) Corrective Action

    If any cracking, damage, or failure is found during any 
inspection required by paragraph (g) of this AD: Before further 
flight, do all applicable corrective actions, in accordance with the 
Accomplishment Instructions of Lockheed Service Bulletin 093-57-207, 
Revision 5, dated November 14, 2008, except where this service 
bulletin specifies that all other damaged structural items should be 
repaired in accordance with the best shop practices, following 
procedures in Structural Repair Manual 57-12-00, this AD requires 
repairing the damage before further flight, 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.

(j) Reporting

    Submit a report of positive findings of the inspection for 
cracking required by this AD to the Manager, Atlanta ACO, at the 
applicable time specified in paragraph (j)(1) or (j)(2) of this AD. 
The report must include the inspection results, a description of the 
discrepancies found, the airplane serial number, and the number of 
landings and flight hours on the airplane.
    (1) If the inspection was done on or after the effective date of 
this AD: Submit the report within 30 days after the inspection.
    (2) If the inspection was done before the effective date of this 
AD: Submit the report within 30 days after the effective date of 
this AD.

(k) Paperwork Reduction Act Burden Statement

    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

[[Page 30751]]

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.

(l) Credit for Previous Actions

    This paragraph provides credit for actions required by 
paragraphs (g) and (i) of this AD, if those actions were performed 
before the effective date of this AD using Lockheed Service Bulletin 
093-57-207, Revision 3, dated November 22, 1991.

(m) 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 
(n)(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.

(n) 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, 
Georgia 30337; phone: 404-474-5554; fax: 404-474-5605; email: 
[email protected].
    (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 [email protected]; 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, Washington. For information on the 
availability of this material at the FAA, call 425-227-1221.

    Issued in Renton, Washington, on May 15, 2014.
Michael Kaszycki,
Acting Manager, Transport Airplane Directorate, Aircraft Certification 
Service.
[FR Doc. 2014-12448 Filed 5-28-14; 8:45 am]
BILLING CODE 4910-13-P