Federal Register / Vol. 80, No. 214 / Thursday, November 5, 2015 / Rules and Regulations 68429 

manages the Agency’s chartering 

activities; and analyzes policy and 

strategic risks to the System. 

(6) Office of Management Services. 

The Office of Management Services 

provides financial management services. 

It administers the Agency’s human 

resources management program, 

contracts, procurement, mail services, 

and payroll. 

(7) Office of Secondary Market 

Oversight. The Office of Secondary 

Market Oversight regulates and 

examines the Federal Agricultural 

Mortgage Corporation for safety and 

soundness and compliance with law 

and regulations. 

(8) Secretary to the Board. The 

Secretary to the Board serves as the 

parliamentarian for the Board and keeps 

permanent and complete records and 

minutes of the acts and proceedings of 

the Board. 

(9) Office of the Chief Operating 

Officer. The Chief Operating Officer has 

broad responsibility for planning, 

directing, and controlling the operations 

of the Offices of Management Services, 

Information Technology, Examination, 

Regulatory Policy, and General Counsel 

in accordance with the operating 

philosophy and policies of the FCA 

Board. 

(10) Designated Agency Ethics 

Official. The Designated Agency Ethics 

Official is designated by the FCA 

Chairman to administer the provisions 

of title I of the Ethics in Government Act 

of 1978, as amended, to coordinate and 

manage FCA’s ethics program, and to 

provide liaison to the Office of 

Government Ethics with regard to all 

aspects of FCA’s ethics program. 

(11) Office of Information Technology. 

The Office of Information Technology 

manages information resources 

management program and delivers the 

Agency’s information technology, data 

analysis infrastructure, and the security 

supporting Agency technology 

resources. 

(12) Equal Employment Opportunity 

and Inclusion. The Office of Equal 

Employment Opportunity and Inclusion 

manages and directs the Agency-wide 

Diversity, Inclusion, and Equal 

Employment Opportunity Program for 

FCA and FCSIC. The office serves as the 

chief liaison with the Equal 

Employment Opportunity Commission 

and the Office of Personnel Management 

on all Equal Employment Opportunity, 

diversity, and inclusion issues. The 

office provides counsel and leadership 

to Agency management to carry out its 

continuing policy and program of 

nondiscrimination, affirmative action, 

and diversity. 

(b) Additional Information. You may 

obtain more information on the FCA’s 

organization by visiting our Web site at 

http://www.fca.gov. You may also 

contact the Office of Congressional and 

Public Affairs: 

(1) In writing at FCA, 1501 Farm 

Credit Drive, McLean, Virginia 22102– 

5090; 

(2) By email at info-line@fca.gov; or 

(3) By telephone at (703) 883–4056. 

PART 606—ENFORCEMENT OF 

NONDISCRIMINATION ON THE BASIS 

OF HANDICAP IN PROGRAMS OR 

ACTIVITIES CONDUCTED BY THE 

FARM CREDIT ADMINISTRATION 

■ 4. The authority citation for part 606 

continues to read as follows: 

Authority: 29 U.S.C. 794. 

§ 606.670 [Amended] 

■ 5. Amend § 606.670 by removing the 

words ‘‘Director, Equal Employment 

Opportunity’’ and adding in their place, 

the words ‘‘Equal Employment 

Opportunity and Inclusion Director’’ in 

paragraph (i). 

Dated: October 30, 2015. 

Dale L. Aultman, 

Secretary, Farm Credit Administration Board. 

[FR Doc. 2015–28244 Filed 11–4–15; 8:45 am] 

BILLING CODE 6705–01–P 

DEPARTMENT OF TRANSPORTATION 

Federal Aviation Administration 

14 CFR Part 39 

[Docket No. FAA–2015–4211; Directorate 

Identifier 2015–NM–150–AD; Amendment 

39–18311; AD 2015–22–06] 

RIN 2120–AA64 

Airworthiness Directives; Airbus 

Airplanes 

AGENCY: Federal Aviation 

Administration (FAA), Department of 

Transportation (DOT). 

ACTION: Final rule; request for 

comments. 

SUMMARY: We are adopting a new 

airworthiness directive (AD) for all 

Airbus Model A318, A319, A320, and 

A321 series airplanes. This AD was 

prompted by reports of spoiler and 

elevator computer (SEC) latent failures; 

an undetected loss of a SEC in flight 

will result in loss in redundancy for 

elevator control. This AD requires 

revising the After Start Normal 

Procedures section of the airplane flight 

manual (AFM) to provide procedures 

that will address this loss of 

redundancy. We are issuing this AD to 

ensure that the flightcrew has 

procedures to address loss of 

redundancy of SEC 1 and SEC 2. A SEC 

failure, in conjunction with a loss of 

trimmable horizontal stabilizer (THS) 

electrical control due to jamming or 

rupture, could result in failure of an 

elevator and aileron computer, and 

consequent loss of elevator control and 

reduced control of the airplane. 

DATES: This AD becomes effective 

November 20, 2015. 

The Director of the Federal Register 

approved the incorporation by reference 

of a certain publication listed in this AD 

as of November 20, 2015. 

We must receive comments on this 

AD by December 21, 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, between 9 a.m. and 5 

p.m., Monday through Friday, except 

Federal holidays. 

For service information identified in 

this AD, contact Airbus, Airworthiness 

Office—EIAS, 1 Rond Point Maurice 

Bellonte, 31707 Blagnac Cedex, France; 

telephone +33 5 61 93 36 96; fax +33 5 

61 93 44 51; email account.airwortheas@airbus.com; Internet http://

www.airbus.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. It is also available on the Internet 

at http://www.regulations.gov by 

searching for and locating Docket No. 

FAA–2015–4211. 

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–2015– 

4211; or in person at the Docket 

Operations office 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 


jstallworth on DSK7TPTVN1PROD with RULES
68430 Federal Register / Vol. 80, No. 214 / Thursday, November 5, 2015 / Rules and Regulations 

other information. The street address for 

the Docket Operations office (telephone 

800–647–5527) is in the ADDRESSES

section. Comments will be available in 

the AD docket shortly after receipt. 

FOR FURTHER INFORMATION CONTACT: 

Sanjay Ralhan, Aerospace Engineer, 

International Branch, ANM–116, 

Transport Airplane Directorate, FAA, 

1601 Lind Avenue SW., Renton, WA 

98057–3356; telephone 425–227–1405; 

fax 425–227–1149. 

SUPPLEMENTARY INFORMATION: 

Discussion 

The European Aviation Safety Agency 

(EASA), which is the Technical Agent 

for the Member States of the European 

Union, has issued EASA Airworthiness 

Directive 2015–0191, dated September 

22, 2015 (correction September 25, 

2015) (referred to after this as the 

Mandatory Continuing Airworthiness 

Information, or ‘‘the MCAI’’), to correct 

an unsafe condition for all Airbus 

Model A318, A319, A320, and A321 

series airplanes. The MCAI states: 

With the introduction of new Spoiler and 

Elevator Computer (SEC) hardware C Part 

Number (P/N) B372CAM0100 with software 

standards 122, 124 and 125 (identified by P/ 

N B372CAM0101, P/N B372CAM0102 and P/ 

N B372CAM0103, respectively), some 

airlines have reported receiving maintenance 

messages, e.g. ‘‘SEC OR WIRING FROM L or 

R ELEV POS MON XDCR’’ and/or ‘‘SEC OR 

WIRING FROM G or Y ELEV POS XDCR’’, 

which are associated with servo control or 

elevator transducer monitoring. Such 

messages are triggered by a short data 

inconsistency due to power transients, when 

the engines are started. 

This condition, if not corrected, could lead 

to an undetected loss of redundancy during 

flight if an affected SEC cannot control the 

related elevator servo control(s), possibly 

resulting in reduced control of the aeroplane. 

It was determined that, to recover full 

redundancy, a reset of SEC 1 and SEC 2 must 

be done after engines start and Airbus have 

developed an Airplane Flight Manual (AFM) 

Temporary Revision (TR), published as TR 

572 Issue 1.1, to provide the necessary flight 

crew procedure. 

Required actions include revising the 

After Start Normal Procedures section of 

the AFM to provide procedures that will 

address this loss of redundancy. You 

may examine the MCAI on the Internet 

at http://www.regulations.gov by 

searching for and locating Docket No. 

FAA–2015–4211. 

Related Service Information Under 1 

CFR Part 51 

Airbus has issued A318/A319/A320/

A321 Temporary Revision TR572, Issue 

1.0, dated August 13, 2015, to the 

Airbus A318/A319/A320/A321 Airplane 

Flight Manual. The service information 

describes the reset of SEC 1 and SEC 2 

that must be done after engines start. 

This service information is reasonably 

available because the interested parties 

have access to it through their normal 

course of business or by the means 

identified in the ADDRESSES section of 

this AD. 

FAA’s Determination and Requirements 

of This AD 

This product has been approved by 

the aviation authority of another 

country, and is approved for operation 

in the United States. Pursuant to our 

bilateral agreement with the State of 

Design Authority, we have been notified 

of the unsafe condition described in the 

MCAI and service information 

referenced above. We are issuing this 

AD because we evaluated all pertinent 

information and determined the unsafe 

condition exists and is likely to exist or 

develop on other products of these same 

type designs. 

FAA’s Determination of the Effective 

Date 

An unsafe condition exists that 

requires the immediate adoption of this 

AD. The FAA has found that the risk to 

the flying public justifies waiving notice 

and comment prior to adoption of this 

rule because a SEC failure in 

conjunction with a loss of THS 

electrical control due to jamming or 

rupture, could result in failure of an 

elevator and aileron computer, and 

consequent loss of elevator control and 

reduced control of the airplane. 

Therefore, we determined that notice 

and opportunity for public comment 

before issuing this AD are impracticable 

and that good cause exists for making 

this amendment effective in fewer than 

30 days. 

Comments Invited 

This AD is a final rule that involves 

requirements affecting flight safety, and 

we did not precede it by notice and 

opportunity for public comment. We 

invite you to send any written relevant 

data, views, or arguments about this AD. 

Send your comments to an address 

listed under the ADDRESSES section. 

Include ‘‘Docket No. FAA–2015–4211; 

Directorate Identifier 2015–NM–150– 

AD’’ at the beginning of your comments. 

We specifically invite comments on the 

overall regulatory, economic, 

environmental, and energy aspects of 

this AD. We will consider all comments 

received by the closing date and may 

amend this AD based on 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 AD. 

Costs of Compliance 

We estimate that this AD affects 959 

airplanes of U.S. registry. 

We also estimate that it will take 

about 1 work-hour per product to 

comply with the basic requirements of 

this AD. The average labor rate is $85 

per work-hour. Based on these figures, 

we estimate the cost of this AD on U.S. 

operators to be $81,515, or $85 per 

product. 

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 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 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. 


jstallworth on DSK7TPTVN1PROD with RULES
Federal Register / Vol. 80, No. 214 / Thursday, November 5, 2015 / Rules and Regulations 68431 

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): 

2015–22–06 Airbus: Amendment 39–18311. 

Docket No. FAA–2015–4211; Directorate 

Identifier 2015–NM–150–AD. 

(a) Effective Date 

This AD becomes effective November 20, 

2015. 

(b) Affected ADs 

None. 

(c) Applicability 

This AD applies to the Airbus airplanes, 

certificated in any category, identified in 

paragraphs (c)(1) through (c)(4) of this AD, all 

manufacturer serial numbers. 

(1) Airbus Model A318–111, –112, –121, 

and –122 airplanes. 

(2) Airbus Model A319–111, –112, –113, 

–114, –115, –131, –132, and –133 airplanes. 

(3) Airbus Model A320–211, –212, –214, 

–231, –232, and –233 airplanes. 

(4) Airbus Model A321–111, –112, –131, 

–211, –212, –213, –231, and –232 airplanes. 

(d) Subject 

Air Transport Association (ATA) of 

America Code 27, Flight Controls. 

(e) Reason 

This AD was prompted by reports of 

spoiler and elevator computer (SEC) latent 

failures; an undetected loss of a SEC in flight 

will result in loss in redundancy for elevator 

control. This AD requires revising the After 

Start Normal Procedures section of the 

airplane fight manual (AFM) to provide 

procedures that will address this loss of 

redundancy. We are issuing this AD to 

ensure that the flightcrew has procedures to 

address loss of redundancy of SEC 1 and SEC 

2. A SEC failure, in conjunction with a loss 

of trimmable horizontal stabilizer (THS) 

electrical control due to jamming or rupture, 

could result in failure of an elevator and 

aileron computer, and consequent loss of 

elevator control and reduced control of the 

airplane. 

(f) Compliance 

Comply with this AD within the 

compliance times specified, unless already 

done. 

(g) Airplane Flight Manual Revision 

For airplanes equipped with SEC hardware 

C part number (P/N) B372CAM0100 with 

software standard 122 (P/N B372CAM0101), 

124 (P/N B372CAM0102), or 125 (P/N 

B372CAM0103), on SEC position 1 or 2, or 

both: Within 30 days after the effective date 

of this AD, revise the After Start Normal 

Procedures section of the AFM to include the 

statement specified in figure 1 to paragraph 

(g) of this AD. This may be done by inserting 

a copy of this AD, or Airbus A318/A319/

A320/A321 Temporary Revision TR572, 

Issue 1.0, dated August 13, 2015, to the 

Airbus A318/A319/A320/A321 Airplane 

Flight Manual, into the applicable AFM. 

FIGURE 1 TO PARAGRAPH (g) OF THIS

AD—AFM TEMPORARY REVISION

AFTER START NORMAL PROCEDURE 

After both engines start: 

Turn OFF then ON SEC 1 and SEC 2 one 

after another. 

Note 1 to paragraph (g) of this AD: When 

a statement identical to that in figure 1 to 

paragraph (g) of this AD has been included 

in the After Start Normal Procedures section 

of the general revisions of the AFM, the 

general revisions may be inserted into the 

AFM, and the copy of this AD or Airbus 

A318/A319/A320/A321 Temporary Revision 

TR572, Issue 1.0, dated August 13, 2015, may 

be removed from the AFM. 

Note 2 to paragraph (g) of this AD: Airbus 

Operations Engineering Bulletin OEB–50 

provides additional information on the 

subject addressed by this AD. 

(h) Optional Modification 

Modification of an airplane by installation 

of SEC hardware C with software standard 

126 (P/N B372CAM0104) (Airbus 

Modification 161208) allows removal of the 

AFM revision required by paragraph (g) of 

this AD for that airplane. 

(i) Parts Installation Limitation 

For all airplanes: As of the effective date 

of this AD, do not install SEC hardware C P/ 

N B372CAM0100 with software standard 122 

(P/N B372CAM0101), 124 (P/N 

B372CAM0102), or 125 (P/N B372CAM0103), 

on SEC position 1 or 2, or both, on any 

airplane, unless the AFM of the airplane is 

revised concurrently with that installation, as 

required by paragraph (g) of this AD. 

(j) Other FAA AD Provisions 

The following provisions also apply to this 

AD: 

(1) Alternative Methods of Compliance 

(AMOCs): The Manager, International 

Branch, ANM–116, Transport Airplane 

Directorate, 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 International Branch, send it to ATTN: 

Sanjay Ralhan, Aerospace Engineer, 

International Branch, ANM–116, Transport 

Airplane Directorate, FAA, 1601 Lind 

Avenue SW., Renton, WA 98057–3356; 

telephone 425–227–1405; fax 425–227–1149. 

Information may be emailed to: 9-ANM-116- 

AMOC-REQUESTS@faa.gov. 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. The AMOC approval letter 

must specifically reference this AD. 

(2) Contacting the Manufacturer: For any 

requirement in this AD to obtain corrective 

actions from a manufacturer, the action must 

be accomplished using a method approved 

by the Manager, International Branch, ANM– 

116, Transport Airplane Directorate, FAA; or 

the European Aviation Safety Agency 

(EASA); or Airbus’s EASA Design 

Organization Approval (DOA). If approved by 

the DOA, the approval must include the 

DOA-authorized signature. 

(k) Special Flight Permits 

Special flight permits, as described in 

Section 21.197 and Section 21.199 of the 

Federal Aviation Regulations (14 CFR 21.197 

and 21.199), are not allowed. 

(l) Related Information 

Refer to Mandatory Continuing 

Airworthiness Information (MCAI) EASA 

Airworthiness Directive 2015–0191, dated 

September 22, 2015 (corrected September 25, 

2015), for related information. You may 

examine the MCAI on the Internet at http:// 

www.regulations.gov by searching for and 

locating Docket No. FAA–2015–4211. 

(m) 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 this AD specifies otherwise. 

(i) Airbus A318/A319/A320/A321 

Temporary Revision TR572, Issue 1.0, dated 

August 13, 2015, to the Airbus A318/A319/ 

A320/A321 Airplane Flight Manual. 

(ii) Reserved. 

(3) For service information identified in 

this AD, contact Airbus SAS, Airworthiness 

Office—EAL, 1 Rond Point Maurice Bellonte, 

31707 Blagnac Cedex, France; telephone +33 

5 61 93 36 96; fax +33 5 61 93 45 80; email 

airworthiness.A330-A340@airbus.com; 

Internet http://www.airbus.com. 

(4) 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. 

(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://


jstallworth on DSK7TPTVN1PROD with RULES
68432 Federal Register / Vol. 80, No. 214 / Thursday, November 5, 2015 / Rules and Regulations 

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

Issued in Renton, Washington, on October 

22, 2015. 

Jeffrey E. Duven, 

Manager, Transport Airplane Directorate, 

Aircraft Certification Service. 

[FR Doc. 2015–27688 Filed 11–4–15; 8:45 am] 

BILLING CODE 4910–13–P 

DEPARTMENT OF TRANSPORTATION 

Federal Aviation Administration 

14 CFR Part 39 

[Docket No. FAA–2015–1425; Directorate 

Identifier 2014–NM–185–AD; Amendment 

39–18312; AD 2015–22–07] 

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 

188 series airplanes. This AD was 

prompted by an evaluation by the 

design approval holder (DAH) 

indicating that the circumferential 

fuselage splice at fuselage-station (FS) 

695 is subject to widespread fatigue 

damage (WFD). This AD requires an 

inspection for corrosion and previous 

repairs, severed stringers, cracking, and 

loose or distressed fasteners of the 

forward and aft ends of the stringer 

splices of certain stringers, inspection 

for cracking and modification of certain 

fastener holes common to the stringer 

and splice member at the forward and 

aft ends of the splice, and related 

investigative and corrective actions if 

necessary. We are issuing this AD to 

prevent loss of residual strength of the 

circumferential fuselage splice at FS 

695, which could lead to rapid 

decompression of the cabin and 

potential loss of the airplane. 

DATES: This AD is effective December 

10, 2015. 

The Director of the Federal Register 

approved the incorporation by reference 

of a certain publication listed in this AD 

as of December 10, 2015. 

ADDRESSES: For service information 

identified in this AD, contact Lockheed 

Martin Corporation/Lockheed Martin 

Aeronautics Company, Airworthiness 

Office, Dept. 6A0M, Zone 0252, Column 

P–58, 86 S. Cobb Drive, Marietta, GA 

30063; phone: 770–494–5444; fax: 770– 

494–5445; email: ams.portal@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. It is also available on the Internet 

at http://www.regulations.gov by 

searching for and locating Docket No. 

FAA–2015–1425. 

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–2015– 

1425; 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 188 series 

airplanes. The NPRM published in the 

Federal Register on May 28, 2015 (80 

FR 30391). The NPRM was prompted by 

an evaluation by the DAH indicating 

that a certain circumferential fuselage 

splice is subject to WFD. The NPRM 

proposed to require an inspection for 

corrosion and previous repairs, severed 

stringers, cracking, and loose or 

distressed fasteners of the forward and 

aft ends of the stringer splices of certain 

stringers, inspection for cracking and 

modification of certain fastener holes 

common to the stringer and splice 

member at the forward and aft ends of 

the splice, and related investigative and 

corrective actions if necessary. We are 

issuing this AD to prevent loss of 

residual strength of a certain 

circumferential fuselage splice, which 

could lead to rapid decompression of 

the cabin and potential loss of the 

airplane. 

Comments 

We gave the public the opportunity to 

participate in developing this AD. We 

received no comments on the NPRM (80 

FR 30391, May 28, 2015) 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 (80 FR 

30391, May 28, 2015) for correcting the 

unsafe condition; and 

• Do not add any additional burden 

upon the public than was already 

proposed in the NPRM (80 FR 30391, 

May 28, 2015). 

Related Service Information Under 1 

CFR Part 51 

We reviewed Lockheed Martin Electra 

Service Bulletin 88/SB–722, dated April 

30, 2014. This service bulletin describes 

procedures for doing the following 

actions: 

• A general visual inspection (GVI) 

for corrosion and previous repairs, 

severed stringers, cracking, and loose or 

distressed fasteners of the forward and 

aft ends of the stringer splices of 

stringers 1–7 and 66–72, and corrective 

actions if necessary. 

• At stringers 1–7 and 66–72, 

removing the four rivets common to the 

stringer and splice member at the 

forward and aft ends of the splice and 

doing a bolt hole eddy current (BHEC) 

inspection or an equivalent inspection 

procedure for cracking in each of the 

fastener holes, and corrective actions if 

necessary. 

• Corrective actions for cracked holes 

include reaming to the maximum 

permissible hole diameter of the next 

larger size rivet. If a crack indication 

remains after reaming, this service 

information specifies repairing the 

cracked stringer. 

• If a severed stringer is found during 

the GVI, doing related investigative 

actions of an eddy current surface scan 

inspection for cracking of the fuselage 

skin at the skin-to-stringer attachments 

immediately forward and aft of the 

stringer break and confirming skin 

cracks with a dye penetrant inspection. 

Corrective actions include repairing the 

severed stringer or skin cracks. 


jstallworth on DSK7TPTVN1PROD with RULES