This section of the FEDERAL REGISTER

contains notices to the public of the proposed

issuance of rules and regulations. The

purpose of these notices is to give interested

persons an opportunity to participate in the

rule making prior to the adoption of the final

rules.

Proposed Rules Federal Register

49724 

Vol. 79, No. 163 

Friday, August 22, 2014 

DEPARTMENT OF TRANSPORTATION 

Federal Aviation Administration 

14 CFR Part 39 

[Docket No. FAA–2014–0574; Directorate 

Identifier 2013–NM–258–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 all 

Airbus Model A318 series airplanes, 

Model A319 series airplanes, Model 

A320–211, –212, –214, –231, –232, and 

–233 airplanes, and Model A321 series 

airplanes. This proposed AD was 

prompted by a report of skin disbonding 

on a composite side shell panel of a 

rudder. This proposed AD would 

require an inspection to determine if 

any rudder composite side shell panel 

has been repaired, a thermography 

inspection of each rudder that has 

received this repair, and related 

investigative and corrective actions if 

necessary. We are proposing this AD to 

detect and correct skin disbonding on 

the rudder, which could affect the 

structural integrity of the rudder, 

possibly resulting in reduced control of 

the airplane. 

DATES: We must receive comments on 

this proposed AD by October 6, 2014. 

ADDRESSES: You may send comments 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 proposed 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.airworth-eas@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. 

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– 

0574; 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 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: 

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–2014–0574; Directorate Identifier 

2013–NM–258–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 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 proposed AD. 

Discussion 

The European Aviation Safety Agency 

(EASA), which is the Technical Agent 

for the Member States of the European 

Community, has issued EASA 

Airworthiness Directive 2013–0302, 

dated December 19, 2013 (referred to 

after this as the Mandatory Continuing 

Airworthiness Information, or ‘‘the 

MCAI’’), to correct an unsafe condition 

for the specified products. The MCAI 

states: 

A case of skin disbonding was reported on 

a composite side shell panel of a rudder 

installed on an A310 aeroplane. Investigation 

results revealed that this disbonding had 

started from a skin panel area, previously 

repaired in-service, in accordance with 

Structural Repair Manual (SRM) instructions. 

The initial damage was identified as a 

disbonding between the core and the skin of 

the repaired area. This damage was not 

visually detectable and likely propagated 

during normal operation due to the variation 

of pressure during ground-air-ground cycles. 

Composite rudder side shell panels are also 

installed on A320 family aeroplanes, which 

may have been repaired in-service using a 

similar method. 

This condition, if not detected and 

corrected, could affect the structural integrity 

of the rudder, possibly resulting in reduced 

control of the aeroplane. 

To address this potential unsafe condition, 

Airbus issued Service Bulletin (SB) A320– 

55–1041 to provide instructions to inspect 

and correct any affected composite rudder 

side shell panels. 

For the reasons described above, this 

[EASA] AD requires [an inspection to 

determine if any rudder composite side shell 

panel has been repaired], a one-time [pulse] 

thermography inspection of each rudder that 

have received a composite rudder side shell 

panel repair, and, depending on the findings, 

accomplishment of applicable corrective and 

follow-up actions [related investigative 

actions and repetitive inspections]. 

The related investigative actions 

include elasticity laminate checker 

(ELCH) inspections, ultrasonic testing 

(UT) inspections, pulse thermography 

inspections, and tap test or woodpecker 

inspections. The repetitive inspections 

include ELCH inspections, UT 

inspections, pulse thermography 

inspections, and detailed inspections 


tkelley on DSK3SPTVN1PROD with PROPOSALS
Federal Register / Vol. 79, No. 163 / Friday, August 22, 2014 / Proposed Rules 49725 

(certain repetitive inspections are 

required if hole restoration is done; 

certain other repetitive inspections are 

options for certain corrective actions). 

The corrective actions include core 

venting through the inner skin, 

replacements, restorations, and repairs. 

Depending on the applicable 

conditions identified in paragraph 1.E., 

‘‘Compliance,’’ of Airbus Service 

Bulletin A320–55–1041, dated 

November 26, 2012, the compliance 

times for the related investigative 

actions range from within 24 months to 

before further flight after accomplishing 

certain inspections. 

The intervals for the repetitive 

inspections range from 750 flight cycles 

to 1,000 flight cycles, depending on the 

applicable conditions identified in 

paragraph 1.E., ‘‘Compliance,’’ of Airbus 

Service Bulletin A320–55–1041, dated 

November 26, 2012. 

Depending on the applicable 

conditions identified in paragraph 1.E., 

‘‘Compliance,’’ of Airbus Service 

Bulletin A320–55–1041, dated 

November 26, 2012, the compliance 

times for the corrective actions range 

from before further flight to 4,500 flight 

cycles but not to exceed 24 months after 

accomplishing the applicable 

inspection. 

The term ‘‘findings,’’ as used in this 

proposed AD, includes (but is not 

limited to) fluid ingress, damage, loose 

or lost tape, and repairs. 

You may examine the MCAI in the 

AD docket on the Internet at http://

www.regulations.gov by searching for 

and locating it in Docket No. FAA– 

2014–0574. 

Relevant Service Information 

Airbus has issued Service Bulletin 

A320–55–1041, dated November 26, 

2012. The actions described in this 

service information are intended to 

correct the unsafe condition identified 

in the MCAI. 

FAA’s Determination and Requirements 

of This Proposed 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 proposing this 

AD because we evaluated all pertinent 

information and determined an unsafe 

condition exists and is likely to exist or 

develop on other products of these same 

type designs. 

‘‘Contacting the Manufacturer’’ 

Paragraph in This Proposed AD 

Since late 2006, we have included a 

standard paragraph titled ‘‘Airworthy 

Product’’ in all MCAI ADs in which the 

FAA develops an AD based on a foreign 

authority’s AD. 

The MCAI or referenced service 

information in an FAA AD often directs 

the owner/operator to contact the 

manufacturer for corrective actions, 

such as a repair. Briefly, the Airworthy 

Product paragraph allowed owners/

operators to use corrective actions 

provided by the manufacturer if those 

actions were FAA-approved. In 

addition, the paragraph stated that any 

actions approved by the State of Design 

Authority (or its delegated agent) are 

considered to be FAA-approved. 

In an NPRM having Directorate 

Identifier 2012–NM–101–AD (78 FR 

78285, December 26, 2013), we 

proposed to prevent the use of repairs 

that were not specifically developed to 

correct the unsafe condition, by 

requiring that the repair approval 

provided by the State of Design 

Authority or its delegated agent 

specifically refer to the FAA AD. This 

change was intended to clarify the 

method of compliance and to provide 

operators with better visibility of repairs 

that are specifically developed and 

approved to correct the unsafe 

condition. In addition, we proposed to 

change the phrase ‘‘its delegated agent’’ 

to include a design approval holder 

(DAH) with State of Design Authority 

design organization approval (DOA), as 

applicable, to refer to a DAH authorized 

to approve required repairs for the 

proposed AD. 

One commenter to the NPRM having 

Directorate Identifier 2012–NM–101–AD 

(78 FR 78285, December 26, 2013) stated 

the following: ‘‘The proposed wording, 

being specific to repairs, eliminates the 

interpretation that Airbus messages are 

acceptable for approving minor 

deviations (corrective actions) needed 

during accomplishment of an AD 

mandated Airbus service bulletin.’’ 

This comment has made the FAA 

aware that some operators have 

misunderstood or misinterpreted the 

Airworthy Product paragraph to allow 

the owner/operator to use messages 

provided by the manufacturer as 

approval of deviations during the 

accomplishment of an AD-mandated 

action. The Airworthy Product 

paragraph does not approve messages or 

other information provided by the 

manufacturer for deviations to the 

requirements of the AD-mandated 

actions. The Airworthy Product 

paragraph only addresses the 

requirement to contact the manufacturer 

for corrective actions for the identified 

unsafe condition and does not cover 

deviations from other AD requirements. 

However, deviations to AD-required 

actions are addressed in 14 CFR 39.17, 

and anyone may request the approval 

for an alternative method of compliance 

to the AD-required actions using the 

procedures found in 14 CFR 39.19. 

To address this misunderstanding and 

misinterpretation of the Airworthy 

Product paragraph, we have changed the 

paragraph and retitled it ‘‘Contacting the 

Manufacturer.’’ This paragraph now 

clarifies that for any requirement in this 

proposed AD to obtain corrective 

actions from a manufacturer, the actions 

must be accomplished using a method 

approved by the FAA, the European 

Aviation Safety Agency (EASA), or 

Airbus’s EASA DOA. 

The Contacting the Manufacturer 

paragraph also clarifies that, if approved 

by the DOA, the approval must include 

the DOA-authorized signature. The DOA 

signature indicates that the data and 

information contained in the document 

are EASA-approved, which is also FAAapproved. Messages and other 

information provided by the 

manufacturer that do not contain the 

DOA-authorized signature approval are 

not EASA-approved, unless EASA 

directly approves the manufacturer’s 

message or other information. 

This clarification does not remove 

flexibility previously afforded by the 

Airworthy Product paragraph. 

Consistent with long-standing FAA 

policy, such flexibility was never 

intended for required actions. This is 

also consistent with the 

recommendation of the Airworthiness 

Directive Implementation Aviation 

Rulemaking Committee to increase 

flexibility in complying with ADs by 

identifying those actions in 

manufacturers’ service instructions that 

are ‘‘Required for Compliance’’ with 

ADs. We continue to work with 

manufacturers to implement this 

recommendation. But once we 

determine that an action is required, any 

deviation from the requirement must be 

approved as an alternative method of 

compliance. 

We also have decided not to include 

a generic reference to either the 

‘‘delegated agent’’ or ‘‘design approval 

holder (DAH) with State of Design 

Authority design organization 

approval,’’ but instead we have 

provided the specific delegation 

approval granted by the State of Design 

Authority for the DAH throughout this 

proposed AD. 


tkelley on DSK3SPTVN1PROD with PROPOSALS
49726 Federal Register / Vol. 79, No. 163 / Friday, August 22, 2014 / Proposed Rules 

Costs of Compliance 

We estimate that this proposed AD 

affects 851 airplanes of U.S. registry. 

We also estimate that it would take 

about 42 work-hours per product to 

comply with the basic requirements of 

this proposed AD. The average labor 

rate is $85 per work-hour. Based on 

these figures, we estimate the cost of 

this proposed AD on U.S. operators to 

be $3,038,070, or $3,570 per product. 

We have received no definitive data 

that would enable us to provide cost 

estimates for the on-condition actions 

specified in this proposed AD. 

Paperwork Reduction Act 

A federal agency may not conduct or 

sponsor, and a person is not required to 

respond to, nor shall a person be subject 

to penalty for failure to comply with a 

collection of information subject to the 

requirements of the Paperwork 

Reduction Act unless that collection of 

information displays a current valid 

OMB control number. The control 

number for the collection of information 

required by this proposed AD is 2120– 

0056. The paperwork cost associated 

with this proposed 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 proposed 

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 proposed 

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. The FAA amends § 39.13 by adding 

the following new airworthiness 

directive (AD): 

Airbus: Docket No. FAA–2014–0574; 

Directorate Identifier 2013–NM–258–AD. 

(a) Comments Due Date 

We must receive comments by October 6, 

2014. 

(b) Affected ADs 

None. 

(c) Applicability 

This AD applies to the Airbus airplanes 

specified in paragraphs (c)(1) through (c)(4) 

of this AD, certificated in any category, 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 55, Stabilizers. 

(e) Reason 

This AD was prompted by a report of skin 

disbonding on a composite side shell panel 

of a rudder. We are issuing this AD to detect 

and correct skin disbonding on the rudder, 

which could affect the structural integrity of 

the rudder, possibly resulting in reduced 

control of the airplane. 

(f) Compliance 

Comply with this AD within the 

compliance times specified, unless already 

done. 

(g) Inspection To Determine Repair Status 

Within 24 months after the effective date 

of this AD: Inspect the airplane maintenance 

records to determine if the rudder composite 

side shell panel has been repaired since first 

installation of the rudder on an airplane. 

(h) Inspection of Certain Repaired Rudders 

If the finding of the inspection required by 

paragraph (g) of this AD reveals that a rudder 

repair has been done as described in Figure 

A–GBBAA (Sheet 01 and 02) or Figure A– 

GBCAA (Sheet 02) of Airbus Service Bulletin 

A320–55–1041, dated November 26, 2012: 

Within 24 months after the effective date of 

this AD, do a pulse thermography inspection 

on the rudder, limited to the repaired area(s), 

to determine type, location, and size of the 

repair, in accordance with the 

Accomplishment Instructions of Airbus 

Service Bulletin A320–55–1041, dated 

November 26, 2012. 

(i) Inspection of Rudders With No Records 

or Incomplete Records 

For each rudder for which maintenance 

records are not available or are incomplete: 

Do the actions required by paragraphs (i)(1) 

and (i)(2) of this AD. 

(1) Not later than 3 months before 

accomplishment of the pulse thermography 

inspection required by paragraph (i)(2) of this 

AD, send the records of each rudder by serial 

number to Airbus. 

(2) Within 24 months after the effective 

date of this AD, do a pulse thermography 

inspection on complete rudder side shells to 

identify and mark the repair location, in 

accordance with the Accomplishment 

Instructions of Airbus Service Bulletin A320– 

55–1041, dated November 26, 2012. 

(j) Related Investigative Actions, Repetitive 

Inspections, and Corrective Actions 

After accomplishing the inspections 

required by paragraphs (h) and (i) of this AD, 

as applicable: Depending on findings, do the 

applicable actions specified in paragraphs 

(j)(1) and (j)(2) of this AD, in accordance with 

the Accomplishment Instructions of Airbus 

Service Bulletin A320–55–1041, dated 

November 26, 2012, except as required by 

paragraph (l)(2) of this AD. Findings are 

specified in Airbus Service Bulletin A320– 

55–1041, dated November 26, 2012. 

(1) Do all applicable related investigative 

actions and corrective actions at the 

applicable times specified in Tables 3, 4A, 

4B, 4C, 4D, and 5 in paragraph 1.E.(2), 


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Federal Register / Vol. 79, No. 163 / Friday, August 22, 2014 / Proposed Rules 49727 

‘‘Accomplishment Timescale,’’ of Airbus 

Service Bulletin A320–55–1041, dated 

November 26, 2012, except as required by 

paragraph (l)(1) of this AD. 

(2) Do all applicable repetitive inspections 

of the restored and repaired areas at the 

applicable intervals specified in Tables 3, 4A, 

4B, 4C, 4D, and 5 in paragraph 1.E.(2), 

‘‘Accomplishment Timescale,’’ of Airbus 

Service Bulletin A320–55–1041, dated 

November 26, 2012. 

(k) Airplanes Excluded From Certain 

Requirements 

Airplanes fitted with a rudder having a 

serial number which is not in the range TS– 

1001 to TS–1639 inclusive, or TS–2001 to 

TS–5890 inclusive; or is not TS–5927; are not 

affected by the requirements of paragraphs 

(h), (i), and (j) of this AD, provided it is 

determined that no repairs have been done as 

described in the structural repair manual 

(SRM) procedures identified in Figure A– 

GBBAA (Sheet 01 and 02) or Figure A– 

GBCAA (Sheet 02) of Airbus Service Bulletin 

A320–55–1041, dated November 26, 2012, on 

the composite side shell panel of that rudder 

since first installation on an airplane. 

(l) Exception to Service Information 

(1) Where the service bulletin specifies a 

compliance time ‘‘after the original Service 

Bulletin issue date,’’ this AD requires 

compliance within the specified compliance 

time after the effective date of this AD. 

(2) If any damage or fluid ingress is found 

during any inspection required by this AD 

and Airbus Service Bulletin A320–55–1041, 

dated November 26, 2012, specifies to 

contact Airbus: Before further flight, repair 

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. 

(m) Parts Installation Limitation 

As of the effective date of this AD, in case 

of rudder replacement, it is allowed to install 

a rudder on an airplane, provided that prior 

to installation the rudder is determined to be 

compliant with the requirements of 

paragraphs (h), (i), (j), and (k) of this AD. 

(n) Repair Prohibition 

As of the effective date of this AD, do not 

accomplish a composite side shell panel 

repair on any rudder using an SRM 

procedure identified in Figure A–GBBAA 

(Sheet 01 and 02) or Figure A–GBCAA (Sheet 

02) of Airbus Service Bulletin A320–55– 

1041, dated November 26, 2012. 

(o) 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. 

(3) Reporting Requirements: 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. 

(p) Related Information 

(1) Refer to Mandatory Continuing 

Airworthiness Information (MCAI) European 

Aviation Safety Agency Airworthiness 

Directive 2013–0302, dated December 19, 

2013, for related information. This MCAI 

may be found in the AD docket on the 

Internet at http://www.regulations.gov by 

searching for and locating it in Docket No. 

FAA–2014–0574. 

(2) 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.airworth-eas@

airbus.com; Internet http://www.airbus.com. 

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 August 

15, 2014. 

Jeffrey E. Duven, 

Manager, Transport Airplane Directorate, 

Aircraft Certification Service. 

[FR Doc. 2014–19979 Filed 8–21–14; 8:45 am] 

BILLING CODE 4910–13–P 

DEPARTMENT OF HEALTH AND 

HUMAN SERVICES 

Food and Drug Administration 

21 CFR Parts 610 and 680 

[Docket No. FDA–2014–N–1110] 

Revocation of General Safety Test 

Regulations That Are Duplicative of 

Requirements in Biological License 

Applications 

AGENCY: Food and Drug Administration, 

HHS. 

ACTION: Proposed rule. 

SUMMARY: The Food and Drug 

Administration (FDA) is proposing to 

amend the biologics regulations by 

removing the general safety test (GST) 

requirements for biological products. 

FDA is proposing this action because 

the existing codified GST regulations 

are duplicative of requirements that are 

also specified in biologics licenses, or 

are no longer necessary or appropriate 

to help ensure the safety, purity, and 

potency of licensed biological products. 

FDA is taking this action as part of its 

retrospective review of its regulations to 

promote improvement and innovation, 

in response to an Executive order. 

DATES: Submit either electronic or 

written comments on this proposed rule 

by November 20, 2014. See section V of 

this document for the proposed effective 

date of any final rule that may publish 

based on this proposal. 

ADDRESSES: You may submit comments 

by any of the following methods: 

Electronic Submissions 

Submit electronic comments in the 

following way: 

• Federal eRulemaking Portal: http:// 

www.regulations.gov. Follow the 

instructions for submitting comments. 

Written Submissions 

Submit written submissions in the 

following ways: 

• Mail/Hand Delivery/Courier (for 

paper submissions): Division of Dockets 

Management (HFA–305), Food and Drug 

Administration, 5630 Fishers Lane, Rm. 

1061, Rockville, MD 20852. 

Instructions: All submissions received 

must include Docket No. FDA–2014–N– 


tkelley on DSK3SPTVN1PROD with PROPOSALS