Federal Register / Vol. 79, No. 192 / Friday, October 3, 2014 / Rules and Regulations 59643 

1601 Lind Avenue SW., Renton, WA. For 

information on the availability of this 

material at the FAA, call 425–227–1221. 

(5) You may view this service information 

that is incorporated by reference at the 

National Archives and Records 

Administration (NARA). For information on 

the availability of this material at NARA, call 

202–741–6030, or go to: http://

www.archives.gov/federal-register/cfr/ibrlocations.html. 

Issued in Renton, Washington, on 

September 19, 2014. 

Michael Kaszycki, 

Acting Manager, Transport Airplane 

Directorate, Aircraft Certification Service. 

[FR Doc. 2014–23145 Filed 10–2–14; 8:45 am] 

BILLING CODE 4910–13–P 

DEPARTMENT OF TRANSPORTATION 

Federal Aviation Administration 

14 CFR Part 39 

[Docket No. FAA–2014–0290; Directorate 

Identifier 2012–NM–210–AD; Amendment 

39–17981; AD 2014–20–08] 

RIN 2120–AA64 

Airworthiness Directives; Lockheed 

Martin Corporation/Lockheed Martin 

Aeronautics Company Airplanes 

AGENCY: Federal Aviation 

Administration (FAA), DOT. 

ACTION: Final rule. 

SUMMARY: We are adopting a new 

airworthiness directive (AD) for certain 

Lockheed Martin Corporation/Lockheed 

Martin Aeronautics Company Model L– 

1011 series airplanes. This AD was 

prompted by reports of cracked rib cap 

castellations. This AD requires 

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; 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 issuing this 

AD to detect and correct cracked or 

damaged rib cap castellations, which 

could degrade the structural capabilities 

of the airplane. 

DATES: This AD is effective November 7, 

2014. 

The Director of the Federal Register 

approved the incorporation by reference 

of a certain publication listed in this AD 

as of November 7, 2014. 

ADDRESSES: 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 

L1011.support@lmco.com; 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 AD, the regulatory 

evaluation, any comments received, and 

other information. The address for the 

Docket Office (phone: 800–647–5527) is 

Docket Management Facility, U.S. 

Department of Transportation, Docket 

Operations, M–30, West Building 

Ground Floor, Room W12–140, 1200 

New Jersey Avenue SE., Washington, 

DC 20590. 

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: carl.w.gray@faa.gov. 

SUPPLEMENTARY INFORMATION: 

Discussion 

We issued a notice of proposed 

rulemaking (NPRM) to amend 14 CFR 

part 39 by adding an AD that would 

apply to certain Lockheed Martin 

Corporation/Lockheed Martin 

Aeronautics Company Model L–1011 

series airplanes. The NPRM published 

in the Federal Register on May 29, 2014 

(79 FR 30748). The NPRM was 

prompted by reports of cracked rib cap 

castellations. The NPRM proposed to 

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; 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 issuing this 

AD to detect and correct cracked or 

damaged rib cap castellations, which 

could degrade the structural capabilities 

of the airplane. 

Comments 

We gave the public the opportunity to 

participate in developing this AD. We 

received no comments on the NPRM (79 

FR 30748, May 29, 2014) or on the 

determination of the cost to the public. 

Conclusion 

We reviewed the relevant data and 

determined that air safety and the 

public interest require adopting this AD 

as proposed except for minor editorial 

changes. We have determined that these 

minor changes: 

• Are consistent with the intent that 

was proposed in the NPRM (79 FR 

30748, May 29, 2014) for correcting the 

unsafe condition; and 

• Do not add any additional burden 

upon the public than was already 

proposed in the NPRM (79 FR 30748, 

May 29, 2014). 

Costs of Compliance 

We estimate that this AD affects 26 

airplanes of U.S. registry. 

We estimate the following costs to 

comply with this AD: 

ESTIMATED COSTS

Action Labor cost Parts cost Cost per product Cost on U.S. operators 

Inspections ........ 41 work-hours × $85 per hour = $3,485 per 

inspection cycle.

$0 $3,485 per inspection cycle .. $90,610 per inspection cycle. 


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59644 Federal Register / Vol. 79, No. 192 / Friday, October 3, 2014 / Rules and Regulations 

We estimate the following costs to do 

any necessary repairs that would be 

required based on the results of the 

inspections. 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 per airplane).96 work-hours × $85 per hour = 

$8,160 per rib cap.

$15,000 per rib cap ................ $23,160 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 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 

that is likely to exist or develop on 

products identified in this rulemaking 

action. 

Regulatory Findings 

This AD will not have federalism 

implications under Executive Order 

13132. This AD will not have a 

substantial direct effect on the States, on 

the relationship between the national 

government and the States, or on the 

distribution of power and 

responsibilities among the various 

levels of government. 

For the reasons discussed above, I 

certify that this AD: 

(1) Is not a ‘‘significant regulatory 

action’’ under Executive Order 12866, 

(2) Is not a ‘‘significant rule’’ under 

DOT Regulatory Policies and Procedures 

(44 FR 11034, February 26, 1979), 

(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. 

Adoption of the Amendment 

Accordingly, under the authority 

delegated to me by the Administrator, 

the FAA amends 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 adding 

the following new airworthiness 

directive (AD): 

2014–20–08 Lockheed Martin Corporation/ 

Lockheed Martin Aeronautics Company: 

Amendment 39–17981; Docket No. 

FAA–2014–0290; Directorate Identifier 

2012–NM–210–AD. 

(a) Effective Date 

This AD is effective November 7, 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 Martin Service 

Bulletin 093–57–207, Revision 5, dated 

November 14, 2008. 

(d) Subject 

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 

Martin 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 Martin 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 


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Federal Register / Vol. 79, No. 192 / Friday, October 3, 2014 / Rules and Regulations 59645 

drag brace aft wing fitting, in accordance 

with the Accomplishment Instructions of 

Lockheed Martin 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 

Martin Service Bulletin 093–57–207, 

Revision 5, dated November 14, 2008. 

(h) Compliance Times for the Actions 

Specified in Paragraph (g) of This AD 

(1) For airplanes that have not 

accomplished the inspections described in 

Lockheed Martin 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 

Martin 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 completion 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 Martin 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 Actions 

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 Martin 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 using 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, damage, or failure 

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 

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 

Martin 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, GA 30337; 

phone: 404–474–5554; fax: 404–474–5605; 

email: carl.w.gray@faa.gov. 

(2) Service information identified in this 

AD that is not incorporated by reference is 

available at the addresses specified in 

paragraphs (o)(3) and (o)(4) of this AD. 

(o) Material Incorporated by Reference 

(1) The Director of the Federal Register 

approved the incorporation by reference 

(IBR) of the service information listed in this 

paragraph under 5 U.S.C. 552(a) and 1 CFR 

part 51. 

(2) You must use this service information 

as applicable to do the actions required by 

this AD, unless the AD specifies otherwise. 

(i) Lockheed Martin Service Bulletin 093– 

57–207, Revision 5, dated November 14, 

2008. 

(ii) Reserved. 

(3) For Lockheed 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 L1011.support@lmco.com; Internet 

http://www.lockheedmartin.com/ams/tools/

TechPubs.html. 

(4) You may view this service information 

at 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. 

(5) You may view this service information 

that is incorporated by reference at the 

National Archives and Records 

Administration (NARA). For information on 

the availability of this material at NARA, call 

202–741–6030, or go to: http://

www.archives.gov/federal-register/cfr/ibrlocations.html. 

Issued in Renton, Washington, on 

September 23, 2014. 

Dionne Palermo, 

Acting Manager, Transport Airplane 

Directorate, Aircraft Certification Service. 

[FR Doc. 2014–23378 Filed 10–2–14; 8:45 am] 

BILLING CODE 4910–13–P 

DEPARTMENT OF TRANSPORTATION 

Federal Aviation Administration 

14 CFR Part 73 

[Docket No. FAA–2014–0722; Airspace 

Docket No. 14–AWP–9] 

RIN 2120–AA66 

Change of Controlling Agency for 

Restricted Areas; California 

AGENCY: Federal Aviation 

Administration (FAA), DOT. 

ACTION: Final rule; technical 

amendment. 

SUMMARY: This action updates the name 

of the controlling agency for restricted 

areas R–2502N Fort Irwin, CA; R–2505 

China Lake, CA; R–2506 China Lake 

South, CA; R–2508 Complex, CA; R– 

2515 Muroc Lake, CA and R–2524 

Trona, CA to read ‘‘FAA, Joshua Control 

Facility, Edwards AFB, CA.’’ This is an 

administrative change only as there are 

no changes to the dimensions, time of 

designation or activities conducted 

within the affected restricted areas. 


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