Federal Register / Vol. 79, No. 221 / Monday, November 17, 2014 / Proposed Rules 68377 

‘‘highly compensated employee’’ solely 

because of a one-time or lump sum 

pension payment that occurred at the 

end of their career. Such a result would 

necessarily cause an otherwise highly 

compensated employee who is not a 

‘‘senior officer’’ to fall out of the top five 

highest compensated employees for that 

reporting period, and thus, to not be 

included in the disclosure required 

under § 620.6(c)(2)(i). 

This proposed rule would improve 

the quality of the disclosure required 

under existing § 620.6(c)(2)(i) by 

eliminating the potential for unintended 

results such as the one outlined above. 

Therefore, we propose to amend 

§ 620.6(c)(2)(i) to exclude any such 

employee from the Compensation Table 

if the employee would be considered 

highly compensated solely because of 

payments related to or change(s) in 

value of the employee’s qualified 

pension plan provided that the plan was 

available to all similarly situated 

employees on the same basis at the time 

the employee joined the plan. 

IV. Regulatory Flexibility Act 

Pursuant to section 605(b) of the 

Regulatory Flexibility Act (5 U.S.C. 601 

et seq.), the FCA hereby certifies that the 

proposed rule would not have a 

significant economic impact on a 

substantial number of small entities. 

Each of the banks in the Farm Credit 

System, considered together with its 

affiliated associations, has assets and 

annual income in excess of the amounts 

that would qualify them as small 

entities. Therefore, Farm Credit System 

institutions are not ‘‘small entities’’ as 

defined in the Regulatory Flexibility 

Act. 

List of Subjects in 12 CFR Part 620 

Accounting, Agriculture, Banks, 

banking, Reporting and recordkeeping 

requirements, Rural areas. 

For the reasons stated in the 

preamble, part 620 of chapter VI, title 12 

of the Code of Federal Regulations is 

proposed to be amended as follows: 

PART 620—DISCLOSURE TO 

SHAREHOLDERS 

■ 1. The authority citation for part 620 

continues to read as follows: 

Authority: Secs. 4.3, 4.3A, 4.19, 5.9, 5.19 

of the Farm Credit Act (12 U.S.C. 2154, 

2154a, 2207, 2243, 2252, 2254); sec. 424 of 

Pub. L. 100–233, 101 Stat. 1568, 1656, sec. 

514 of Pub. L. 102–552, 106 Stat. 4102. 

■ 2. Section 620.6(c)(2)(i) is revised to 

read as follows: 

§ 620.6 Disclosures in the annual report to 

shareholders relating to directors and 

senior officers. 

* * * * * 

(c) * * * 

(2) * * * 

(i) If applicable, when any employee 

who is not a senior officer has annual 

compensation at a level that is among 

the five highest paid by the institution 

during the reporting period, include the 

highly compensated employee(s) in the 

aggregate number and amount of 

compensation reported in the 

Compensation Table. However, exclude 

any such employee from the 

Compensation Table if the employee 

would be considered highly 

compensated solely because of 

payments related to or change(s) in 

value of the employee’s qualified 

pension plan provided that the plan was 

available to all similarly situated 

employees on the same basis at the time 

the employee joined the plan. 

* * * * * 

Dated: November 12, 2014. 

Dale L. Aultman, 

Secretary, Farm Credit Administration Board. 

[FR Doc. 2014–27192 Filed 11–14–14; 8:45 am] 

BILLING CODE 6705–01–P 

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. 

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 poststructural 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: 

• 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 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://

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68378 Federal Register / Vol. 79, No. 221 / Monday, November 17, 2014 / Proposed Rules 

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: 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–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 postmodification 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

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

Inspections [actions retained 

from AD 95–26–11, Amendment 39–9469 (60 FR 

66870, December 27, 

1995)].

23 work-hours × $85 per hour 

= $1,955 per inspection 

cycle.

$0 $1,955 per inspection cycle ... $50,830 per inspection cycle. 

Inspections and modification 

[new proposed action].

185 work-hours × $85 per 

hour = $15,725.

6,750 22,475 .................................... 584,350. 

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Federal Register / Vol. 79, No. 221 / Monday, November 17, 2014 / Proposed Rules 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

Action Labor cost Parts cost Cost per 

product 

Replacement of one fitting ........................................... 16 work-hour × $85 per hour = $1,360 ........................ $250 $1,610 

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 

■ 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. Amend § 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. 

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68380 Federal Register / Vol. 79, No. 221 / Monday, November 17, 2014 / Proposed Rules 

(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 

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Federal Register / Vol. 79, No. 221 / Monday, November 17, 2014 / Proposed Rules 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: carl.w.gray@faa.gov. 

(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 

L1011.support@lmco.com; 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 

DEPARTMENT OF TRANSPORTATION 

Federal Aviation Administration 

14 CFR Part 39 

[Docket No. FAA–2014–0772; Directorate 

Identifier 2014–NM–090–AD] 

RIN 2120–AA64 

Airworthiness Directives; the Boeing 

Company Airplanes 

AGENCY: Federal Aviation 

Administration (FAA), DOT. 

ACTION: Notice of proposed rulemaking 

(NPRM). 

SUMMARY: We propose to supersede 

Airworthiness Directive (AD) 2011–08– 

51, which applies to certain The Boeing 

Company Model 737–300, –400, and 

–500 series airplanes. AD 2011–08–51 

currently requires repetitive inspections 

of the lap joint at certain stringers along 

the entire length from certain body 

stations. Since we issued AD 2011–08– 

51, an evaluation by the design approval 

holder (DAH) has determined that the 

lower fastener holes in the lower skin of 

the fuselage lap splice are subject to 

widespread fatigue damage (WFD), and 

as a result the DAH specified revised 

compliance times, an expanded 

inspection area, and additional 

inspections for cracks and open pockets, 

and corrective actions if necessary. 

Additionally, this evaluation has also 

determined that the repetitive 

inspection interval can be increased for 

lap splices with certain new fay 

scratches. This proposed AD would 

expand the inspection area, require 

additional inspections for cracks and 

open pockets, and corrective actions if 

necessary, and revise the compliance 

times. We are proposing this AD to 

detect and correct fatigue cracking of the 

lower fastener holes in the lower skin of 

the fuselage lap splice, which could 

result in reduced structural integrity of 

the airplane. 

DATES: We must receive comments on 

this proposed AD 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: 

• 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 proposed AD, contact Boeing 

Commercial Airplanes, Attention: Data 

& Services Management, P. O. Box 3707, 

MC 2H–65, Seattle, WA 98124–2207; 

telephone 206–544–5000, extension 1; 

fax 206–766–5680; Internet https://

www.myboeingfleet.com. 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– 

0772; 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 

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