Federal Register / Vol. 80, No. 72 / Wednesday, April 15, 2015 / Proposed Rules 20175 

3 79 FR 32172. 

4 80 FR 7980. 

eliminate unnecessary regulations to the 

extent that such action is appropriate. 

Finally, section 2222 requires the 

Council, of which the Agencies are 

members, to submit a report to Congress 

that summarizes any significant issues 

raised in the public comments and the 

relative merits of such issues. The report 

also must include an analysis of 

whether the Agencies are able to 

address the regulatory burdens 

associated with such issues by 

regulation or whether these burdens 

must be addressed by legislative action. 

For purposes of this review, the 

Agencies have grouped our regulations 

into 12 categories: Applications and 

Reporting; Banking Operations; Capital; 

Community Reinvestment Act; 

Consumer Protection; Directors, Officers 

and Employees; International 

Operations; Money Laundering; Powers 

and Activities; Rules of Procedure; 

Safety and Soundness; and Securities. 

On June 4, 2014, we published a 

Federal Register notice announcing the 

start of the EGRPRA review process and 

also asking for public comment on three 

of these categories—Applications and 

Reporting; Powers and Activities; and 

International Operations regulations.3 In 

that notice we published a chart, listing 

the Agencies’ regulations in the 12 

categories included in the EGRPRA 

review. On February 13, 2015, we 

published a Federal Register notice 

asking for public comment on three 

additional categories—Banking 

Operations; Capital; and the Community 

Reinvestment Act.4 The comment 

period for the current Federal Register 

notice closes on May 14, 2015. 

Recently, the Agencies have decided 

to expand the scope of the EGRPRA 

review in order to be as inclusive as 

possible. Accordingly, the Agencies will 

take comment on all of our regulations 

issued in final form up to the date that 

we publish our last EGRPRA notice for 

public comment and report back to the 

Congress on all such regulations. 

Dated: April 8, 2015. 

Thomas J. Curry, 

Comptroller of the Currency. 

By order of the Board of Governors of the 

Federal Reserve System, April 7, 2015. 

Robert deV. Frierson, 

Secretary of the Board. 

Dated: April 6, 2015. 

Federal Deposit Insurance Corporation by 

Robert E. Feldman, 

Executive Secretary. 

[FR Doc. 2015–08619 Filed 4–14–15; 8:45 am] 

BILLING CODE 6210–01P; 6714–01–P; 4810–33–P 

DEPARTMENT OF TRANSPORTATION 

Federal Aviation Administration 

14 CFR Part 39 

[Docket No. FAA–2015–0826; Directorate 

Identifier 2014–NM–221–AD] 

RIN 2120–AA64 

Airworthiness Directives; Airbus 

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 

Airbus Model A318, A319, and A320 

series airplanes modified by a particular 

supplemental type certificate (STC). 

This proposed AD was prompted by 

reports of cracks found during 

inspections of the in-flight 

entertainment system radome assembly. 

This proposed AD would require 

repetitive detailed inspections for cracks 

in the radome assembly, and 

replacement of the radome if necessary. 

We are proposing this AD to detect and 

correct cracks in the radome assembly, 

which could result in the radome (or 

pieces) separating from the airplane and 

striking the tail, consequently reducing 

the controllability of the airplane. 

DATES: We must receive comments on 

this proposed AD by June 1, 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 Live TV, 7415 

Emerald Dunes Drive, Orlando, FL 

32822; telephone 407–812–2643; email: 

CertificationEngineering@livetv.net; 

Internet: http://www.LiveTV.net. 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–2015– 

0826; 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: 

Barry Culler, Aerospace Engineer, 

Airframe Branch, ACE–117A, FAA, 

Atlanta Aircraft Certification Office 

(ACO), 1701 Columbia Avenue, College 

Park, GA 30337; phone: 404–474–5546; 

fax: 404–474–5605; email: 

william.culler@faa.gov. 

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– 

2015–0826; Directorate Identifier 2014– 

NM–221–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 received reports of cracks in the 

in-flight entertainment system radomes 

of certain Airbus airplanes. The cracks 

were found during inspections of the 

radome assembly on various Airbus 

Model A318, A319, and A320 series 

airplanes that had in-flight 

entertainment systems installed using a 

certain STC issued to Live TV (STC 

number STC ST00788SE, http://rgl.faa.

gov/Regulatory_and_Guidance_Library/

rgstc.nsf/0/6df40775b10ef09a86257

ae200613cfe/$FILE/ST00788SE.pdf). 

Investigation of the cause of the cracks 

revealed that radome manufacturing 

variation, due to a lack of dimensional 

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20176 Federal Register / Vol. 80, No. 72 / Wednesday, April 15, 2015 / Proposed Rules 

controls on the radome manufacturing 

drawings, can result in the introduction 

of preload stress on the radome during 

its assembly with the skirt fairing. 

Preload stress combined with flight or 

handling stress, such as maintenance 

personnel stepping on the radome 

fairing assembly, might initiate a crack. 

The radome manufacturing drawings 

were revised on September 13, 2010, to 

add a control dimension, which was 

incorporated into production at radome 

serial number 498. Cracks in the 

radome, if not corrected, could result in 

the radome (or pieces) separating from 

the airplane and striking the tail, 

consequently reducing the 

controllability of the airplane. 

Related Service Information Under 1 

CFR Part 51 

We reviewed Live TV Service Bulletin 

A320–53–006, Rev 01, dated September 

10, 2014. The service information 

describes procedures for repetitive 

detailed inspections for cracks in the 

outer ply of the radome, and 

replacement of the radome with a new 

or serviceable radome, if any crack is 

found. This service information is 

reasonably available; see ADDRESSES for 

ways to access this service information. 

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 these same 

type designs. 

Proposed AD Requirements 

This proposed AD would require 

accomplishing the actions specified in 

the service information described 

previously. In addition, if any crack is 

found in a radome during an inspection, 

this proposed AD would require 

sending the inspection results to Live 

TV. 

Explanation of ‘‘RC’’ Steps in Service 

Information 

The FAA worked in conjunction with 

industry, under the Airworthiness 

Directive Implementation Aviation 

Rulemaking Committee (ARC), to 

enhance the AD system. One 

enhancement was a new process for 

annotating which steps in the service 

information are required for compliance 

with an AD. Differentiating these steps 

from other tasks in the service 

information is expected to improve an 

owner’s/operator’s understanding of 

crucial AD requirements and help 

provide consistent judgment in AD 

compliance. The steps identified as RC 

(required for compliance) in any service 

information identified previously have a 

direct effect on detecting, preventing, 

resolving, or eliminating an identified 

unsafe condition. 

Steps that are identified as RC in any 

service information must be done to 

comply with the proposed AD. 

However, steps that are not identified as 

RC are recommended. Those steps that 

are not identified as RC may be deviated 

from using accepted methods in 

accordance with the operator’s 

maintenance or inspection program 

without obtaining approval of an 

alternative method of compliance 

(AMOC), provided the steps identified 

as RC can be done and the airplane can 

be put back in a serviceable condition. 

Any substitutions or changes to steps 

identified as RC will require approval of 

an AMOC. 

Costs of Compliance 

We estimate that this proposed AD 

affects 120 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 ......... 1 work-hour × $85 per hour = $85, 

per inspection cycle.

N/A $85, per inspection cycle ............... $10,200, per inspection cycle. 

We estimate the following costs to do 

any necessary replacements that would 

be required based on the results of the 

proposed inspections. We have no way 

of determining the number of aircraft 

that might need this replacement: 

ON-CONDITION COSTS

Action Labor cost Parts cost Cost per 

product 

Replacement .................................... 8 work-hours × $85 per hour = $680 ........................................................ $0 $680 

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. 

mstockstill on DSK4VPTVN1PROD with PROPOSALS

Federal Register / Vol. 80, No. 72 / Wednesday, April 15, 2015 / Proposed Rules 20177 

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. The FAA amends § 39.13 by adding 

the following new airworthiness 

directive (AD): 

Airbus: Docket No. FAA–2015–0826; 

Directorate Identifier 2014–NM–221–AD. 

(a) Comments Due Date 

We must receive comments by June 1, 

2015. 

(b) Affected ADs 

None. 

(c) Applicability 

This AD applies to the airplane models 

identified in paragraphs (c)(1), (c)(2), and 

(c)(3) of this AD, certificated in any category, 

with Live TV radomes having part number 

(P/N) 5063–100–XX (XX designates the color 

option) and a serial number in the range of 

001 through 497 inclusive, and modified by 

supplemental type certificate (STC) STC 

ST00788SE, http://rgl.faa.gov/Regulatory_

and_Guidance_Library/rgstc.nsf/0/6df407

75b10ef09a86257ae200613cfe/$FILE/

ST00788SE.pdf. 

(1) Airbus Model A318–111 and –112 

airplanes. 

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

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

(3) Airbus Model A320–111, 211, –212, 

–214, –231, –232, and –233 airplanes. 

(d) Subject 

Air Transport Association (ATA) of 

America Code 53, Fuselage. 

(e) Unsafe Condition 

This AD was prompted by reports of cracks 

found during inspections of the radome 

assembly. We are issuing this AD to detect 

and correct cracks in the in-flight 

entertainment system radome assembly, 

which could result in the radome (or pieces) 

separating from the airplane and striking the 

tail, consequently reducing the 

controllability of the airplane. 

(f) Compliance 

Comply with this AD within the 

compliance times specified, unless already 

done. 

(g) Repetitive Inspections and Corrective 

Actions 

Within 3,900 flight hours after the effective 

date of this AD: Perform a detailed inspection 

for cracks of the radome assembly, in 

accordance with the Accomplishment 

Instructions of Live TV Service Bulletin 

A320–53–006, Rev 01, dated September 10, 

2014. Repeat the inspection thereafter at 

intervals not to exceed 3,900 flight hours. If 

any crack is found during any inspection 

required by this paragraph, before further 

flight, replace the radome with a new or 

serviceable radome, in accordance with the 

Accomplishment Instructions of Live TV 

Service Bulletin A320–53–006, Rev 01, dated 

September 10, 2014. 

(h) Reporting Requirement 

If any crack is found during any inspection 

required by paragraph (g) of this AD, submit 

a report of the findings to Live TV, Attn: 

Oscar Hernandez, email: 

CertificationEngineering@livetv.net; at the 

applicable time specified in paragraph (h)(1) 

or (h)(2) of this AD. The report must include 

the information specified in the service 

bulletin reporting form provided in Live TV 

Service Bulletin A320–53–006, Rev 01, dated 

September 10, 2014. 

(1) If the inspection was accomplished on 

or after the effective date of this AD: Submit 

the report within 30 days after the 

inspection. 

(2) If the inspection was accomplished 

before the effective date of this AD: Submit 

the report within 30 days after the effective 

date of this AD. 

(i) Special Flight Permit 

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. 

(j) 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. 

(k) Alternative Methods of Compliance 

(AMOCs) 

(1) The Manager, Atlanta Aircraft 

Certification Office (ACO), FAA, has the 

authority to approve AMOCs for this AD, if 

requested using the procedures found in 14 

CFR 39.19. In accordance with 14 CFR 39.19, 

send your request to your principal inspector 

or local Flight Standards District Office, as 

appropriate. If sending information directly 

to the manager of the ACO, send it to the 

attention of the person identified in the 

Related Information section of this AD. 

(2) Before using any approved AMOC, 

notify your appropriate principal inspector, 

or lacking a principal inspector, the manager 

of the local flight standards district office/

certificate holding district office. 

(3) If any service information contains 

steps that are identified as RC (Required for 

Compliance), those steps must be done to 

comply with this AD; any steps that are not 

identified as RC are recommended. Those 

steps that are not identified as RC may be 

deviated from using accepted methods in 

accordance with the operator’s maintenance 

or inspection program without obtaining 

approval of an AMOC, provided the steps 

identified as RC can be done and the airplane 

can be put back in a serviceable condition. 

Any substitutions or changes to steps 

identified as RC require approval of an 

AMOC. 

(l) Related Information 

(1) For more information about this AD, 

contact Barry Culler, Aerospace Engineer, 

Airframe Branch, ACE–117A, FAA, Atlanta 

Aircraft Certification Office (ACO), 1701 

Columbia Avenue, College Park, GA 30337; 

phone: 404–474–5546; fax: 404–474–5605; 

email: william.culler@faa.gov. 

(2) For service information identified in 

this AD, contact Live TV, 7415 Emerald 

Dunes Drive, Orlando, FL 32822; telephone 

407–812–2643; email: 

CertificationEngineering@livetv.net; Internet: 

http://www.LiveTV.net. 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. 

mstockstill on DSK4VPTVN1PROD with PROPOSALS

20178 Federal Register / Vol. 80, No. 72 / Wednesday, April 15, 2015 / Proposed Rules 

Issued in Renton, Washington, on April 6, 

2015. 

John P. Piccola, Jr., 

Acting Manager, Transport Airplane 

Directorate, Aircraft Certification Service. 

[FR Doc. 2015–08465 Filed 4–14–15; 8:45 am] 

BILLING CODE 4910–13–P 

DEPARTMENT OF TRANSPORTATION 

Federal Aviation Administration 

14 CFR Part 39 

[Docket No. FAA–2015–0828; Directorate 

Identifier 2014–NM–146–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) 2013–23– 

03, which applies to certain The Boeing 

Company Model 747–100, 747–100B, 

747–100B SUD, 747–200B, 747–200C, 

747–200F, 747–300, 747–400, 747– 

400D, 747–400F, and 747SR series 

airplanes. AD 2013–23–03 currently 

requires doing a detailed inspection of 

certain attach fittings for a cylindrical 

defect and replacing if necessary. Since 

we issued AD 2013–23–03, we received 

a report that a machining defect was 

also found on some of the actuator 

assemblies inspected during 

manufacture. This defect could lead to 

fatigue cracking and subsequent 

fracture. For certain airplanes, this 

proposed AD would mandate new 

inspections of the inboard actuator 

attach fittings for machining defects, 

and overhaul or replacement, if 

necessary. This proposed AD would 

also limit the compliance time for doing 

the replacement for certain other 

airplanes. We are proposing this AD to 

detect and correct defective inboard 

actuator attach fittings which, combined 

with loss of the outboard actuator load 

path, could result in uncontrolled 

retraction of the outboard flap, damage 

to flight control systems, and 

consequent reduced controllability of 

the airplane. 

DATES: We must receive comments on 

this proposed AD by June 1, 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, Washington. 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– 

0828. 

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– 

0828; 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: 

Nathan Weigand, Aerospace Engineer, 

Airframe Branch, ANM–120S, FAA, 

Seattle Aircraft Certification Office, 

1601 Lind Avenue SW., Renton, WA 

98057–3356; phone: 425–917–6428; fax: 

425–917–6590; email: 

nathan.p.weigand@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–2015–0828; Directorate Identifier 

2014–NM–146–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 

On October 31, 2013, we issued AD 

2013–23–03, Amendment 39–17658 (78 

FR 68345, November 14, 2013), for 

certain The Boeing Company Model 

747–100, 747–100B, 747–100B SUD, 

747–200B, 747–200C, 747–200F, 747– 

300, 747–400, 747–400D, 747–400F, and 

747SR series airplanes. AD 2013–23–03 

requires inspecting to determine the 

part number of the inboard actuator 

attach fittings of the outboard flap. For 

affected attach fittings, AD 2013–23–03 

requires doing a detailed inspection of 

the attach fittings for a cylindrical defect 

and replacing if necessary. As an option 

to the detailed inspection, AD 2013–23– 

03 allows replacement of affected attach 

fittings. AD 2013–23–03 resulted from a 

report of the fracture of an inboard 

actuator attach fitting of the outboard 

flap. An inspection of the attach fitting 

revealed that it was incorrectly 

machined with a cylindrical profile 

instead of a conical profile, resulting in 

reduced wall thickness. We issued AD 

2013–23–03 to detect and correct 

defective inboard actuator attach fittings 

which, combined with loss of the 

outboard actuator load path, could 

result in uncontrolled retraction of the 

outboard flap, damage to flight control 

systems, and consequent reduced 

controllability of the airplane. 

Actions Since AD 2013–23–03, 

Amendment 39–17658 (78 FR 68345, 

November 14, 2013) Was Issued 

The preamble to AD 2013–23–03, 

Amendment 39–17658 (78 FR 68345, 

November 14, 2013), specified that we 

considered the requirements ‘‘interim 

action.’’ AD 2013–23–03 explained that 

we might consider further rulemaking to 

require a minimum thickness inspection 

of inboard actuator attach fittings that 

are conically machined. Since we issued 

AD 2013–23–03, we received a report 

that a machining defect was also found 

on some of the actuator assemblies 

inspected during manufacture at the 

point where the tapered machining 

transitioned to the hemispherical 

machining at the top of the inner 

surface. Revised service information has 

been issued and, for certain airplanes, 

this proposed AD would mandate new 

mstockstill on DSK4VPTVN1PROD with PROPOSALS