Federal Register / Vol. 80, No. 93 / Thursday, May 14, 2015 / Proposed Rules 27607 

(h) Additional Information 

The subject of this AD is addressed in the 

Direction General De L’Aviation Civile 

(DGAC) AD No. 67A005, Revision 1, dated 

February 6, 2002. You may view the DGAC 

AD on the Internet at http://

www.regulations.gov in Docket No. FAA– 

2015–1480. 

(i) Subject 

Joint Aircraft Service Component (JASC) 

Code: 2500, Cabin Equipment/Furnishings. 

Issued in Fort Worth, Texas, on May 1, 

2015. 

Lance T. Gant, 

Acting Directorate Manager, Rotorcraft 

Directorate, Aircraft Certification Service. 

[FR Doc. 2015–11522 Filed 5–13–15; 8:45 am] 

BILLING CODE 4910–13–P 

DEPARTMENT OF TRANSPORTATION 

Federal Aviation Administration 

14 CFR Part 39 

[Docket No. FAA–2015–1417; Directorate 

Identifier 2013–NM–159–AD] 

RIN 2120–AA64 

Airworthiness Directives; Airbus 

Airplanes 

AGENCY: Federal Aviation 

Administration (FAA), DOT. 

ACTION: Notice of proposed rulemaking 

(NPRM). 

SUMMARY: We propose to supersede 

Airworthiness Directive (AD) 2004–20– 

14, for all Airbus Model A300 B4–2C, 

B4–103, and B4–203 airplanes; and all 

Model A300 B4–600, B4–600R, and F4– 

600R series airplanes. AD 2004–20–14 

requires repetitive inspections to detect 

cracking of the splice fitting at fuselage 

frame (FR) 47 between stringers 24 and 

26 (left- and right-hand sides), and 

corrective actions if necessary. Since we 

issued AD 2004–20–14, we have 

determined that the inspection 

compliance time and repetitive 

inspection interval must be reduced to 

allow timely detection of cracks in the 

splice fitting at fuselage FR 47. This 

proposed AD would reduce the 

inspection compliance time and 

repetitive inspection intervals, and add 

Model A300 C4–605R Variant F 

airplanes to the applicability. We are 

proposing this AD to detect and correct 

cracking of the splice fitting at fuselage 

FR 47, which could result in reduced 

structural integrity of the airplane. 

DATES: We must receive comments on 

this proposed AD by June 29, 2015. 

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 SAS, 

Airworthiness Office—EAW, 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. 

Examining the AD Docket 

You may examine the AD docket on 

the Internet at http://

www.regulations.gov; 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 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: Dan 

Rodina, Aerospace Engineer, 

International Branch, ANM–116, 

Transport Airplane Directorate, FAA, 

1601 Lind Avenue SW., Renton, WA 

98057–3356; telephone 425–227–2125; 

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–2015–1417; Directorate Identifier 

2013–NM–159–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 

On September 30, 2004, we issued AD 

2004–20–14, Amendment 39–13819 (69 

FR 60809, October 13, 2004), which 

superseded AD 2001–03–14, 

Amendment 39–12118 (66 FR 10957, 

February 21, 2001). AD 2004–20–14 

requires actions intended to address an 

unsafe condition on all Airbus Model 

A300 B4–2C, B4–103, and B4–203 

airplanes; and all Model A300 B4–600, 

B4–600R, and F4–600R series airplanes. 

Since we issued AD 2004–20–14, 

Amendment 39–13819 (69 FR 60809, 

October 13, 2004), we have determined 

that the inspection compliance time and 

repetitive inspection interval must be 

reduced to allow timely detection of 

cracks in the splice fitting at fuselage FR 

47, and that Model A300 C4–605R 

Variant F airplanes must be added to the 

applicability. 

The European Aviation Safety Agency 

(EASA), which is the Technical Agent 

for the Member States of the European 

Union, has issued EASA Airworthiness 

Directive 2013–0184R1, dated August 

22, 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: 

In order to prevent crack development in 

the fastener holes at Frame (FR) 47 splicing 

joint on A300 aeroplanes, Airbus developed 

modification (Mod) 5890 for aeroplanes in 

production and issued corresponding Service 

Bulletin (SB) A300–53–0199 for aeroplanes 

in service. 

Subsequently, cracks were found on FR47 

splice fitting between stringers (STRG) 24 

and 26 on A300 aeroplanes previously 

modified by SB A300–53–0199. 

This condition, if not detected and 

corrected, could reduce the structural 

integrity of the aeroplane. 

To address this potential unsafe condition, 

DGAC [Direction Ge ́ne ́rale de l’Aviation 

Civile] France issued AD 2002–184 http://

ad.easa.europa.eu/blob/2002184tb_

superseded.pdf/AD_F-2002-184_2 [which 

corresponds to FAA AD 2004–20–14, 

Amendment 39–13819 (69 FR 60809, October 

13, 2004)], superseding [DGAC France] AD 

85–152–069 and [DGAC France] AD 1999– 

515–298 [which corresponds to FAA AD 

2001–03–14, Amendment 39–12118 (66 FR 

10957, February 21, 2001)], to require 

repetitive High Frequency Eddy Current 

(HFEC) rotating probe inspections of the 

splice fitting between STRG 24 and 26 and, 


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depending on findings, corrective action(s). 

DGAC France AD 2002–184(B) expanded the 

applicability to A300–600 aeroplanes, which 

have the same design. 

Since that [DGAC France] AD was issued, 

a fleet survey and updated Fatigue and 

Damage Tolerance analyses have been 

performed in order to substantiate the second 

A300–600 Extended Service Goal (ESG2) 

exercise. The results of these analyses have 

determined that the inspection threshold and 

intervals for A300–600 aeroplanes must be 

reduced to allow timely detection of these 

cracks and the accomplishment of an 

applicable corrective action. 

For the reasons described above, [EASA] 

AD 2013–0184 retains the requirements of 

DGAC France AD 2002–184, which is 

superseded, but requires accomplishment of 

the actions for A300–600 aeroplanes within 

the new thresholds and intervals introduced 

with Revision 05 of Airbus SB [service 

bulletin] A300–53–6123 [dated August 1, 

2011] . 

This [EASA] AD was revised to correct the 

splices Part Numbers (P/N) in Table 4 of 

Appendix 1 of this [EASA] AD. Also, 

reference is now made to Airbus SB A300– 

53–6123 Revision 06 [dated September 28, 

2011], which corrected this mistake 

compared to Revision 05. 

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– 

2015–1417. 

Related Service Information Under 1 

CFR Part 51 

Airbus has issued the following 

service bulletins: 

• Airbus Service Bulletin A300–53– 

6123, Revision 06, including Inspection 

Report, dated September 28, 2011. This 

service bulletin describes procedures for 

inspection for cracking of the splice 

fitting at fuselage FR 47 between 

stringers 24 and 26, and corrective 

actions. 

• Airbus Service Bulletin A300–53– 

0350, Revision 03, including Appendix 

03, dated July 26, 2007. This service 

bulletin describes procedures for 

inspection to detect cracking of the 

splice fitting at fuselage FR 47 between 

stringers 24 and 26, and corrective 

actions. 

The actions described in this service 

information are intended to correct the 

unsafe condition identified in the 

MCAI. 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 NPRM. 

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 the same 

type design. 

Costs of Compliance 

We estimate that this proposed AD 

affects 72 airplanes of U.S. registry. 

We also estimate that it would take up 

to 14 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 

$85,680, or $1,190 per product. 

In addition, we estimate that any 

necessary follow-on actions would take 

up to 204 work-hours and require parts 

costing up to $37,000, for a cost of up 

to $54,340 per product. We have no way 

of determining the number of aircraft 

that might need these actions. 

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. 

We prepared a regulatory evaluation 

of the estimated costs to comply with 

this proposed AD and placed it in the 

AD docket. 

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 

removing airworthiness directive (AD) 

2004–20–14, Amendment 39–13819 (69 

FR 60809, October 13, 2004), and 

adding the following new AD: 

Airbus: Docket No. FAA–2015–1417; 

Directorate Identifier 2013–NM–159–AD. 

(a) Comments Due Date 

We must receive comments by June 29, 

2015. 

(b) Affected ADs 

This AD replaces AD 2004–20–14, 

Amendment 39–13819 (69 FR 60809, October 

13, 2004). 

(c) Applicability 

This AD applies to the Airbus airplanes 

identified in paragraphs (c)(1) through (c)(5) 

of this AD, certificated in any category, all 

manufacturer serial numbers. 

(1) Airbus Model A300 B4–2C, B4–103, 

and B4–203 airplanes. 

(2) Airbus Model A300 B4–601, B4–603, 

B4–620, and B4–622 airplanes. 

(3) Airbus Model A300 B4–605R and B4– 

622R airplanes. 

(4) Airbus Model A300 F4–605R and F4– 

622R airplanes. 

(5) Airbus Model A300 C4–605R Variant F 

airplanes. 

(d) Subject 

Air Transport Association (ATA) of 

America Code 53, Fuselage. 


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(e) Reason 

This AD was prompted by a determination 

that the inspection compliance time and 

repetitive inspection interval must be 

reduced to allow timely detection of cracks 

in the splice fitting at fuselage frame (FR) 47. 

We are issuing this AD to detect and correct 

cracking of the splice fitting at fuselage FR 

47, which could result in reduced structural 

integrity of the airplane. 

(f) Compliance 

You are responsible for having the actions 

required by this AD performed within the 

compliance times specified, unless the 

actions have already been done. 

(g) Retained Repetitive Inspections for 

Airplanes Defined in Airbus Service Bulletin 

A300–53–0350, Revision 02, Dated 

November 12, 2002, With New Service 

Information 

This paragraph restates the requirements of 

paragraph (a) of AD 2004–20–14, 

Amendment 39–13819 (69 FR 60809, October 

13, 2004), with new service information. For 

airplanes defined in Airbus Service Bulletin 

A300–53–0350, Revision 02, dated November 

12, 2002: Do a high frequency eddy current 

(HFEC) inspection to detect cracking of the 

splice fitting at fuselage FR 47 between 

stringers 24 and 26 (left- and right-hand 

sides), at the applicable times specified in 

paragraph (g)(1) or (g)(2) of this AD. Repeat 

the inspection thereafter at the earlier of the 

flight-cycle/flight-hour intervals specified in 

the applicable column in Table 2 of Figure 

1 and Sheet 1 of the Accomplishment 

Instructions of Airbus Service Bulletin A300– 

53–0350, Revision 02, excluding Appendix 

01, dated November 12, 2002. Do the 

inspections in accordance with Airbus 

Service Bulletin A300–53–0350, Revision 02, 

excluding Appendix 01, dated November 12, 

2002; or Revision 03, excluding Appendix 

01, dated July 26, 2007. As of the effective 

date of this AD, use only Airbus Service 

Bulletin A300–53–0350, Revision 03, 

excluding Appendix 01, dated July 26, 2007. 

(1) For airplanes that have accumulated 

20,000 or more total flight cycles as of 

November 17, 2004 (the effective date of AD 

2004–20–14, Amendment 39–13819 (69 FR 

60809, October 13, 2004)): Do the initial 

inspection at the later of the times specified 

in paragraphs (g)(1)(i) and (g)(1)(ii) of this 

AD. 

(i) At the earlier of the flight-cycle/flighthour intervals after November 17, 2004 (the 

effective date of AD 2004–20–14, 

Amendment 39–13819 (69 FR 60809, October 

13, 2004)), as specified in the applicable 

column in Table 1 of Figure 1 and Sheet 1 

of the Accomplishment Instructions of 

Airbus Service Bulletin A300–53–0350, 

Revision 02, excluding Appendix 01, dated 

November 12, 2002. 

(ii) Within 750 flight cycles or 1,500 flight 

hours after November 17, 2004 (the effective 

date of AD 2004–20–14, Amendment 39– 

13819 (69 FR 60809, October 13, 2004)), 

whichever is first. 

(2) For airplanes that have accumulated 

fewer than 20,000 total flight cycles as of 

November 17, 2004 (the effective date of AD 

2004–20–14, Amendment 39–13819 (69 FR 

60809, October 13, 2004)): Do the initial 

inspection at the later of the times specified 

in paragraphs (g)(2)(i) and (g)(2)(ii) of this 

AD. 

(i) At the earlier of the flight-cycle/flighthour intervals after November 17, 2004 (the 

effective date of AD 2004–20–14, 

Amendment 39–13819 (69 FR 60809, October 

13, 2004)), as specified in the applicable 

column in Table 1 of Figure 1 and Sheet 1 

of the Accomplishment Instructions of 

Airbus Service Bulletin A300–53–0350, 

Revision 02, excluding Appendix 01, dated 

November 12, 2002. 

(ii) Within 1,800 flight cycles or 3,000 

flight hours after November 17, 2004 (the 

effective date of AD 2004–20–14, 

Amendment 39–13819 (69 FR 60809, October 

13, 2004)), whichever is first. 

(h) Retained Repetitive Inspections for 

Airplanes Defined in Airbus Service Bulletin 

A300–53–6123, Revision 02, Dated 

November 12, 2002, With New Service 

Information 

This paragraph restates the requirements of 

paragraph (b) of AD 2004–20–14, 

Amendment 39–13819 (69 FR 60809, October 

13, 2004), with new service information. For 

airplanes defined in Airbus Service Bulletin 

A300–53–6123, Revision 02, dated November 

12, 2002: Do the HFEC inspection required 

by paragraph (g) of this AD at the applicable 

times specified in paragraph (h)(1) or (h)(2) 

of this AD. Repeat the inspection thereafter 

at the earlier of the flight-cycle/flight-hour 

intervals specified in the applicable column 

in Table 2 of Figure 1 and Sheet 1 of the 

Accomplishment Instructions of Airbus 

Service Bulletin A300–53–6123, Revision 02, 

excluding Appendix 01, dated November 12, 

2002. Do the inspections in accordance with 

the Accomplishment Instructions of Airbus 

Service Bulletin A300–53–6123, Revision 02, 

excluding Appendix 01, dated November 12, 

2002, excluding Appendix 01; or Revision 

06, dated September 28, 2011. 

Accomplishment of the actions required by 

paragraph (j) of this AD terminates the 

requirements of this paragraph. 

(1) For airplanes that have accumulated 

10,000 or more total flight cycles as of 

November 17, 2004 (the effective date of AD 

2004–20–14, Amendment 39–13819 (69 FR 

60809, October 13, 2004)): Do the initial 

inspection within 750 flight cycles or 1,900 

flight hours after November 17, 2004, 

whichever is first. 

(2) For airplanes that have accumulated 

fewer than 10,000 total flight cycles as of 

November 17, 2004 (the effective date of AD 

2004–20–14, Amendment 39–13819 (69 FR 

60809, October 13, 2004)): Do the initial 

inspection at the later of the times specified 

in paragraphs (h)(2)(i) and (h)(2)(ii) of this 

AD. 

(i) At the earlier of the flight-cycle/flighthour intervals after November 17, 2004 (the 

effective date of AD 2004–2–14, Amendment 

39–13819 (69 FR 60809, October 13, 2004)), 

as specified in the applicable column in 

Table 1 of Figure 1 and Sheet 1 of the 

Accomplishment Instructions of Airbus 

Service Bulletin A300–53–6123, Revision 02, 

excluding Appendix 01, dated November 12, 

2002. 

(ii) Within 1,500 flight cycles or 3,800 

flight hours after November 17, 2004 (the 

effective date of AD 2004–20–14, 

Amendment 39–13819 (69 FR 60809, October 

13, 2004)), whichever is first. 

(i) Retained Repair, With Revised Repair 

Instructions 

This paragraph restates the requirements of 

paragraph (c) of AD 2004–20–14, 

Amendment 39–13819 (69 FR 60809, October 

13, 2004), with revised repair instructions. 

Repair any cracking found during any 

inspection required by paragraphs (g) and (h) 

this AD before further flight, in accordance 

with Airbus Service Bulletin A300–53–0350, 

Revision 02, excluding Appendix 01, dated 

November 12, 2002; or Airbus Service 

Bulletin A300–53–6123, Revision 02, 

excluding Appendix 01, dated November 12, 

2002; as applicable. Where Airbus Service 

Bulletin A300–53–0350, Revision 02, 

excluding Appendix 01, dated November 12, 

2002; or Airbus Service Bulletin A300–53– 

6123, Revision 02, excluding Appendix 01, 

dated November 12, 2002; specify to contact 

Airbus in case of certain crack findings, this 

AD requires that a repair be accomplished 

before further flight using a method approved 

by the Manager, International Branch, ANM– 

116, FAA, Transport Airplane Directorate; or 

the Direction Ge ́ne ́rale de l’Aviation Civile 

(DGAC) (or its delegated agent); or the 

European Aviation Safety Agency (EASA); or 

Airbus’s EASA Design Organization 

Approval (DOA). 

(j) New Requirement of This AD: Repetitive 

Inspections 

For airplanes identified in paragraphs 

(c)(2) through (c)(5) of this AD: At the 

applicable time specified in paragraph (j)(1) 

or (j)(2) of this AD: Remove the fasteners and 

accomplish an HFEC rotating probe 

inspection for cracking of the splice fitting 

between stringer 24 and 26, in accordance 

with the Accomplishment Instructions of 

Airbus Service Bulletin A300–53–6123, 

Revision 06, excluding Inspection Report, 

dated September 28, 2011. Repeat the 

inspection thereafter at the applicable 

intervals specified in paragraphs (k)(1) 

through (k)(4) of this AD. If no cracking is 

found: Before further flight after each 

inspection, install new fasteners, in 

accordance with the Accomplishment 

Instructions of Airbus Service Bulletin A300– 

53–6123, Revision 06, excluding Inspection 

Report, dated September 28, 2011. 

Accomplishment of the initial inspection 

required by this paragraph terminates the 

requirements of paragraph (h) of this AD for 

that airplane. 

(1) For airplanes on which Airbus 

Modification 5890, or the actions specified in 

Airbus Service Bulletin A300–53–6131, have 

not been done: At the applicable time 

specified in paragraphs (j)(1)(i) and (j)(1)(ii) 

of this AD. 

(i) For airplanes that have an average flight 

time (AFT) that is more than 1.5 hours: At 

the later of the times specified in paragraphs 

(j)(1)(i)(A) and (j)(1)(i)(B) of this AD. 

(A) Before the accumulation of 2,500 total 

flight cycles or 5,500 total flight hours, 

whichever occurs first. 


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(B) Within 800 flight cycles or 1,750 flight 

hours, whichever occurs first after the 

effective date of this AD. 

(ii) For airplanes that have an AFT that is 

equal to or less than 1.5 hours: At the later 

of the times specified in paragraphs 

(j)(1)(ii)(A) and (j)(1)(ii)(B) of this AD. 

(A) Before the accumulation of 2,700 total 

flight cycles or 4,100 total flight hours, 

whichever occurs first. 

(B) Within 800 flight cycles or 1,750 flight 

hours, whichever occurs first after the 

effective date of this AD. 

(2) For airplanes that have accomplished 

Airbus Modification 5890, or have 

accomplished the actions specified in Airbus 

Service Bulletin A300–53–6131: At the 

applicable time specified in paragraph 

(j)(2)(i) or (j)(2)(ii) of this AD. 

(i) For airplanes that have an AFT that is 

more than 1.5 hours: At the later of the times 

specified in paragraphs (j)(2)(i)(A) and 

(j)(2)(i)(B) of this AD. 

(A) Before the accumulation of 6,800 total 

flight cycles or 14,700 total flight hours, 

whichever occurs first. 

(B) Within 800 flight cycles or 1,750 flight 

hours, whichever occurs first after the 

effective date of this AD. 

(ii) For airplanes that have an AFT that is 

equal to or less than 1.5 hours: At the later 

of the times specified in paragraphs 

(j)(2)(ii)(A) and (j)(2)(ii)(B) of this AD. 

(A) Before the accumulation of 7,300 total 

flight cycles or 11,000 total flight hours, 

whichever occurs first. 

(B) Within 800 flight cycles or 1,750 flight 

hours, whichever occurs first after the 

effective date of this AD. 

(k) New Requirement of This AD: Repetitive 

Inspection Intervals for Actions Specified in 

Paragraph (j) of This AD 

For airplanes identified in paragraphs 

(c)(2) through (c)(5) of this AD: Repeat the 

inspection required by paragraph (j) of this 

AD at the applicable time specified in 

paragraphs (k)(1) through (k)(4) of this AD. 

(1) For airplanes that have an AFT of more 

than 1.5 hours and meet the applicable 

conditions specified in paragraphs (k)(1)(i) 

through (k)(1)(iv) of this AD: Inspect at 

intervals not to exceed 800 flight cycles or 

1,750 flight hours, whichever occurs first. 

(i) Airplanes on which Airbus Modification 

5890 has not been accomplished. 

(ii) Airplanes on which the actions 

specified in Airbus Service Bulletin A300– 

53–6131 have not been accomplished. 

(iii) Airplanes on which Airbus 

Modification 5890 has been accomplished 

and have splice part number (P/N) 

A53834139–202/–203 installed. 

(iv) Airplanes on which the actions 

specified in Airbus Service Bulletin A300– 

53–6131 have been accomplished and have 

splice P/N A53834139–202/–203 installed. 

(2) For airplanes that have an AFT that is 

equal to or less than 1.5 hours and meet the 

applicable conditions specified in paragraphs 

(k)(2)(i) through (k)(2)(iv) of this AD: Inspect 

at intervals not to exceed 800 flight cycles or 

1,750 flight hours. 

(i) Airplanes on which Airbus Modification 

5890 has not been accomplished. 

(ii) Airplanes on which the actions 

specified in Airbus Service Bulletin A300– 

53–6131 have not been accomplished. 

(iii) Airplanes on which Airbus 

Modification 5890 has been accomplished 

and have splice P/N A53834139–202/–203 

installed. 

(iv) Airplanes on which the actions 

described in Airbus Service Bulletin A300– 

53–6131 have been accomplished and have 

splice P/N A53834139–202/–203 installed. 

(3) For airplanes that have an AFT of more 

than 1.5 hours and meet the applicable 

conditions specified in paragraphs (k)(3)(i) 

and (k)(3)(ii) of this AD: Inspect at intervals 

not to exceed 800 flight cycles or 1,750 flight 

hours. 

(i) Airplanes on which Airbus Modification 

5890 has been accomplished and have splice 

P/N A53812635–200/–201/–202/–203 

installed. 

(ii) Airplanes on which the actions 

specified in Airbus Service Bulletin A300– 

53–6131 have been accomplished and have 

splice P/N A53812635–200/–201/–202/–203 

installed. 

(4) For the airplanes that have an AFT that 

is equal to or less than 1.5 hours and meet 

the applicable conditions specified in 

paragraphs (k)(4)(i) and (k)(4)(ii) of this AD: 

Inspect at intervals not to exceed 800 flight 

cycles or 1,750 flight hours. 

(i) Airplanes on which Airbus Modification 

5890 has been accomplished and have splice 

P/N A53812635–200/–201/–202/–203 

installed. 

(ii) Airplanes on which the actions 

specified in Airbus Service Bulletin A300– 

53–6131 have been accomplished and have 

splice P/N A53812635–200/–201/–202/–203 

installed. 

(l) New Requirement of This AD: Corrective 

Actions 

If, during any inspection required by 

paragraph (j) or (k) of this AD, any cracks are 

found: Before further flight, do the applicable 

corrective actions, in accordance with the 

Accomplishment Instructions of Airbus 

Service Bulletin A300–53–6123, Revision 06, 

excluding Inspection Report, dated 

September 28, 2011; except as provided by 

paragraph (m) of this AD. 

(m) New Requirement of This AD: Exception 

to Service Information 

If any crack is found during any inspection 

required by paragraph (j) or (k) of this AD 

and Airbus Service Bulletin A300–53–6123, 

Revision 06, excluding Inspection Report, 

dated September 28, 2011; or Airbus Service 

Bulletin A300–53–0350, Revision 03, dated 

July 26, 2007; specifies to contact Airbus: 

Before further flight, repair the crack using a 

method approved by the Manager, 

International Branch, ANM–116, Transport 

Airplane Directorate, FAA; or the EASA; or 

Airbus’s EASA DOA. 

(n) Credit for Previous Actions 

This paragraph provides credit for actions 

required by paragraphs (j) and (l) of this AD, 

if those actions were performed before the 

effective date of this AD using the applicable 

service information specified in paragraphs 

(n)(1) through (n)(7) of this AD. 

(1) Airbus Service Bulletin A300–53–0350, 

Revision 01, dated December 18, 2001, which 

is not incorporated by reference in this AD. 

(2) Airbus Service Bulletin A300–53–0350, 

Revision 02, excluding Appendix 01, dated 

November 12, 2002, which is incorporated by 

reference in AD 2004–20–14, Amendment 

39–13819 (69 FR 60809, October 13, 2004). 

(3) Airbus Service Bulletin A300–53–6123, 

Revision 01, dated December 18, 2001, which 

is not incorporated by reference in this AD. 

(4) Airbus Service Bulletin A300–53–6123, 

Revision 02, excluding Appendix 01, dated 

November 12, 2002, which is incorporated by 

reference in AD 2004–20–14, Amendment 

39–13819 (69 FR 60809, October 13, 2004). 

(5) Airbus Service Bulletin A300–53–6123, 

Revision 03, dated August 20, 2004, which is 

not incorporated by reference in this AD. 

(6) Airbus Service Bulletin A300–53–6123, 

Revision 04, dated April 25, 2008, which is 

not incorporated by reference in this AD. 

(7) Airbus Service Bulletin A300–53–6123, 

Revision 05, dated August 1, 2011, which is 

not incorporated by reference in this AD. 

(o) Other FAA AD Provisions 

The following provisions also apply to this 

AD: 

(1) Alternative Methods of Compliance 

(AMOCs): The Manager, International 

Branch, 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: 

Dan Rodina, Aerospace Engineer, 

International Branch, ANM–116, Transport 

Airplane Directorate, FAA, 1601 Lind 

Avenue SW., Renton, WA 98057–3356; 

telephone 425–227–2125; 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: As of the 

effective date of this AD, 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 EASA; or Airbus’s EASA DOA. If 

approved by the DOA, the approval must 

include the DOA-authorized signature. 

(p) Related Information 

(1) Refer to Mandatory Continuing 

Airworthiness Information (MCAI) 

Airworthiness Directive 2013–0184R1, dated 

August 22, 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 Docket No. 

FAA–2015–1417. 

(2) For service information identified in 

this AD, contact Airbus SAS, Airworthiness 

Office—EAW, 1 Rond Point Maurice 

Bellonte, 31707 Blagnac Cedex, France; 


tkelley on DSK3SPTVN1PROD with PROPOSALS
Federal Register / Vol. 80, No. 93 / Thursday, May 14, 2015 / Proposed Rules 27611 

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 April 30, 

2015. 

Michael Kaszycki, 

Acting Manager, Transport Airplane 

Directorate, Aircraft Certification Service. 

[FR Doc. 2015–11554 Filed 5–13–15; 8:45 am] 

BILLING CODE 4910–13–P 

DEPARTMENT OF JUSTICE 

Drug Enforcement Administration 

21 CFR Part 1308 

[Docket No. DEA–417N] 

Schedules of Controlled Substances: 

Placement of UR–144, XLR11, and 

AKB48 Into Schedule I 

AGENCY: Drug Enforcement 

Administration, Department of Justice. 

ACTION: Notice of proposed rulemaking. 

SUMMARY: The Drug Enforcement 

Administration (DEA) proposes placing 

(1-pentyl-1H-indol-3-yl)(2,2,3,3- 

tetramethylcyclopropyl)methanone 

(UR–144), [1-(5-fluoro-pentyl)-1H-indol3-yl](2,2,3,3- 

tetramethylcyclopropyl)methanone (5- 

fluoro-UR–144, XLR11), and N-(1- 

adamantyl)-1-pentyl-1H-indazole-3- 

carboxamide (APINACA, AKB48) 

including their salts, isomers, and salts 

of isomers whenever the existence of 

such salts, isomers, and salts of isomers 

is possible, into schedule I of the 

Controlled Substances Act. This 

proposed scheduling action is pursuant 

to the Controlled Substance Act which 

requires that such actions be made on 

the record after opportunity for a 

hearing through formal rulemaking. If 

finalized, this action would impose the 

regulatory controls and administrative, 

civil, and criminal sanctions applicable 

to schedule I controlled substances on 

persons who handle (manufacture, 

distribute, import, export, engage in 

research, conduct instructional 

activities, or possess), or propose to 

handle UR–144, XLR11, or AKB48. 

DATES: Interested persons may file 

written comments on this proposal in 

accordance with 21 CFR 1308.43(g). 

Electronic comments must be 

submitted, and written comments must 

be postmarked, on or before June 15, 

2015. Commenters should be aware that 

the electronic Federal Docket 

Management System will not accept 

comments after 11:59 p.m. Eastern Time 

on the last day of the comment period. 

Interested persons, defined at 21 CFR 

1300.01 as those ‘‘adversely affected or 

aggrieved by any rule or proposed rule 

issuable pursuant to section 201 of the 

Act (21 U.S.C. 811),’’ may file a request 

for hearing, notice of appearance, or 

waiver of hearing pursuant to 21 CFR 

1308.44 and in accordance with 21 CFR 

1316.45, 1316.47, 1316.48, or 1316.49, 

as applicable. Requests for hearing, 

notices of appearance, and waivers of an 

opportunity for a hearing or to 

participate in a hearing must be 

received on or before June 15, 2015. 

ADDRESSES: To ensure proper handling 

of comments, please reference ‘‘Docket 

No. DEA–417N’’ on all correspondence, 

including any attachments. 

• Electronic comments: The Drug 

Enforcement Administration encourages 

that all comments be submitted 

electronically through the Federal 

eRulemaking Portal, which provides the 

ability to type short comments directly 

into the comment field on the Web page 

or to attach a file for lengthier 

comments. Please go to http://

www.regulations.gov and follow the 

online instructions at that site for 

submitting comments. Upon completion 

of your submission you will receive a 

Comment Tracking Number for your 

comment. Please be aware that 

submitted comments are not 

instantaneously available for public 

view on Regulations.gov. If you have 

received a Comment Tracking Number, 

your comment has been successfully 

submitted and there is no need to 

resubmit the same comment. 

• Paper comments: Paper comments 

that duplicate the electronic submission 

are not necessary and are discouraged. 

Should you wish to mail a paper 

comment in lieu of an electronic 

comment, it should be sent via regular 

or express mail to: Drug Enforcement 

Administration, Attn: DEA Federal 

Register Representative/ODXL, 8701 

Morrissette Drive, Springfield, Virginia 

22152. 

• Hearing requests: All requests for 

hearing and waivers of participation 

must be sent to: Drug Enforcement 

Administration, Attn: Federal Register 

Representative/ODL, 8701 Morrissette 

Drive, Springfield, Virginia 22152. All 

requests for hearing and waivers of 

participation should also be sent to: 

Drug Enforcement Administration, Attn: 

Hearing Clerk/LJ, 8701 Morrissette 

Drive, Springfield, Virginia 22152. 

FOR FURTHER INFORMATION CONTACT: John 

R. Scherbenske, Office of Diversion 

Control, Drug Enforcement 

Administration; Mailing Address: 8701 

Morrissette Drive, Springfield, Virginia 

22152; Telephone: (202) 598–6812. 

SUPPLEMENTARY INFORMATION: 

Posting of Public Comments 

Please note that all comments 

received are considered part of the 

public record. They will, unless 

reasonable cause is given, be made 

available by the Drug Enforcement 

Administration (DEA) for public 

inspection online at http://

www.regulations.gov. Such information 

includes personal identifying 

information (such as your name, 

address, etc.) voluntarily submitted by 

the commenter. The Freedom of 

Information Act (FOIA) applies to all 

comments received. If you want to 

submit personal identifying information 

(such as your name, address, etc.) as 

part of your comment, but do not want 

it to be made publicly available, you 

must include the phrase ‘‘PERSONAL 

IDENTIFYING INFORMATION’’ in the 

first paragraph of your comment. You 

must also place all of the personal 

identifying information you do not want 

made publicly available in the first 

paragraph of your comment and identify 

what information you want redacted. 

If you want to submit confidential 

business information as part of your 

comment, but do not want it to be made 

publicly available, you must include the 

phrase ‘‘CONFIDENTIAL BUSINESS 

INFORMATION’’ in the first paragraph 

of your comment. You must also 

prominently identify confidential 

business information to be redacted 

within the comment. 

Comments containing personal 

identifying information and confidential 

business information identified as 

directed above will generally be made 

publicly available in redacted form. If a 

comment has so much confidential 

business information or personal 

identifying information that it cannot be 

effectively redacted, all or part of that 

comment may not be made publicly 

available. Comments posted to http://

www.regulations.gov may include any 

personal identifying information (such 

as name, address, and phone number) 

included in the text of your electronic 

submission that is not identified as 

directed above as confidential. 

An electronic copy of this document 

and supplemental information to this 

proposed rule are available at http://

www.regulations.gov for easy reference. 


tkelley on DSK3SPTVN1PROD with PROPOSALS