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

6185 

Vol. 81, No. 24 

Friday, February 5, 2016 

DEPARTMENT OF AGRICULTURE 

Grain Inspection, Packers and 

Stockyards Administration 

7 CFR Part 800 

RIN 0580–AB13 

Reauthorization of the United States 

Grain Standards Act 

Correction 

In Proposed Rule document 2016– 

01083 beginning on page 3970 in the 

issue of Monday, January 25, 2016, 

make the following correction: 

On page 3975, in the third column, 

preceding amendatory instruction 7 

insert the following text: 

§ 800.72 [Amended] 

■ 6. In § 800.72(b), remove the 

reference ‘‘§ 800.71’’ from the first 

sentence and add in its place the 

reference ‘‘§ 800.71(a)(1)’’. 

[FR Doc. C1–2016–01083 Filed 2–4–16; 8:45 am] 

BILLING CODE 1505–01–D 

DEPARTMENT OF TRANSPORTATION 

Federal Aviation Administration 

14 CFR Part 39 

[Docket No. FAA–2013–0828; Directorate 

Identifier 2012–NM–036–AD] 

RIN 2120–AA64 

Airworthiness Directives; Airbus 

Airplanes 

AGENCY: Federal Aviation 

Administration (FAA), DOT. 

ACTION: Supplemental notice of 

proposed rulemaking (NPRM); 

reopening of comment period. 

SUMMARY: We are revising an earlier 

proposed airworthiness directive (AD) 

for certain Airbus Model A330–200 and 

–300 series airplanes; and Model A340– 

200 and –300 series airplanes. The 

NPRM proposed to supersede AD 2009– 

15–17 to continue to require inspections 

for damage to the protective treatments 

or any corrosion of all main landing gear 

(MLG) bogie beams, application of 

protective treatments, and corrective 

action if necessary. The NPRM also 

proposed to require modification of the 

MLG bogie beams, to allow optional 

methods of compliance for certain 

actions, and to add airplanes to the 

applicability. The first supplemental 

notice of proposed rulemaking (SNPRM) 

proposed to revise the compliance times 

and add a one-time inspection for 

certain airplanes. The NPRM was 

prompted by reports of thin paint coats 

and paint degradation on enhanced 

MLG bogie beams. This second SNPRM 

proposes to clarify the required actions 

and the specific configurations to which 

the actions must be applied. We are 

proposing this second SNPRM to detect 

and correct damage or corrosion of the 

MLG bogie beams, which could cause a 

runway excursion event, bogie beam 

detachment from the airplane, or MLG 

collapse, and could result in damage to 

the airplane and injury to the occupants. 

Since these actions impose an 

additional burden over those proposed 

in the first SNPRM, we are reopening 

the comment period to allow the public 

the chance to comment on these 

proposed changes. 

DATES: We must receive comments on 

this SNPRM by March 21, 2016. 

ADDRESSES: You may send comments, 

using the procedures found in 14 CFR 

11.43 and 11.45, by any of the following 

methods: • Federal eRulemaking Portal: Go to 

http://www.regulations.gov. Follow the 

instructions for submitting comments. • Fax: 202–493–2251. • Mail: U.S. Department of 

Transportation, Docket Operations, M– 

30, West Building Ground Floor, Room 

W12–140, 1200 New Jersey Avenue SE., 

Washington, DC 20590. • Hand Delivery: U.S. Department of 

Transportation, Docket Operations, M– 

30, West Building Ground Floor, Room 

W12–140, 1200 New Jersey Avenue SE., 

Washington, DC, between 9 a.m. and 5 

p.m., Monday through Friday, except 

Federal holidays. For Airbus service information 

identified in this NPRM, contact Airbus 

SAS, Airworthiness Office—EAL, 1 

Rond Point Maurice Bellonte, 31707 

Blagnac Cedex, France; telephone: +33 5 

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

email: airworthiness.A330- 

A340@airbus.com; Internet: http:// 

www.airbus.com. 

For Messier-Dowty service 

information identified in this NPRM, 

contact Messier-Dowty: Messier 

Services Americas, Customer Support 

Center, 45360 Severn Way, Sterling, VA 

20166–8910; telephone 703–450–8233; 

fax 703–404–1621; Internet: https://

techpubs.services/messier-dowty.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–2013– 

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 

(telephone: 800–647–5527) is in the 

ADDRESSES section. Comments will be 

available in the AD docket shortly after 

receipt. 

FOR FURTHER INFORMATION CONTACT: 

Vladimir Ulyanov, Aerospace Engineer, 

International Branch, ANM–116, 

Transport Airplane Directorate, FAA, 

1601 Lind Avenue SW., Renton, WA 

98057–3356; telephone: 425–227–1138; 

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–2013–0828; Directorate Identifier 

2012–NM–036–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 

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6186 Federal Register / Vol. 81, No. 24 / Friday, February 5, 2016 / Proposed Rules 

will also post a report summarizing each 

substantive verbal contact we receive 

about this proposed AD. 

Discussion 

We issued an SNPRM to amend 14 

CFR part 39 by adding an AD that 

would apply to certain Airbus Model 

A330–200 Freighter series airplanes, 

Model A330–200 and A330–300 series 

airplanes, and Model A340–200 and 

A340–300 series airplanes. The SNPRM 

published in the Federal Register on 

March 5, 2014 (79 FR 12414). 

We preceded the SNPRM with a 

notice of proposed rulemaking (NPRM) 

that published in the Federal Register 

on September 25, 2013 (78 FR 58978). 

The NPRM was prompted by reports of 

thin paint coats and paint degradation 

on enhanced MLG bogie beams. The 

NPRM proposed to supersede AD 2009– 

15–17, Amendment 39–15980 (74 FR 

37523, July 29, 2009), to continue to 

require inspections for damage to the 

protective treatments or any corrosion of 

all MLG bogie beams, application of 

protective treatments, and corrective 

action if necessary. The NPRM also 

proposed to require modification of the 

MLG bogie beams, which would 

terminate the repetitive inspections for 

any modified bogie beam. In addition, 

the NPRM proposed to allow optional 

methods of compliance for certain 

actions, and to add Airbus Model A330– 

200 Freighter series airplanes to the 

applicability. 

The SNPRM (79 FR 12414, March 5, 

2014) (‘‘the first SNPRM’’) proposed to 

revise the compliance times and add a 

one-time inspection for airplanes that 

were inspected too early. 

Actions Since the First SNPRM Was 

Issued 

Since we issued the first SNPRM, we 

have determined that it is necessary to 

clarify the required actions and the 

specific configurations to which the 

actions must be applied. The European 

Aviation Safety Agency (EASA), which 

is the Technical Agent for the Member 

States of the European Union, has 

issued EASA AD 2013–0267R1, dated 

March 4, 2014, Corrected May 8, 2014 

(referred to after this as the Mandatory 

Continuing Airworthiness Information, 

or ‘‘the MCAI’’), to correct an unsafe 

condition on certain Airbus Model 

A330–200 Freighter, –200, and –300 

series airplanes; and Model A340–200 

and –300 series airplanes. The MCAI 

states: 

The operator of an A330 aeroplane (which 

has a common bogie beam with the A340) 

reported a fracture of the Right Hand (RH) 

main landing gear (MLG) bogie beam, which 

occurred while turning during low speed taxi 

maneuvers. The bogie fractured aft of the 

pivot point and remained attached to the 

sliding tube by the brake torque reaction 

rods. After this RH bogie failure, the 

aeroplane continued for approximately 40 

meters on the forks of the sliding member 

before coming to rest on the taxiway. 

The investigations revealed that this event 

was due to corrosion pitting occurring on the 

bore of the bogie beam. 

This condition, if not detected and 

corrected, could lead to a runway excursion 

event or to detachment of the bogie from the 

aeroplane, or to MLG collapse, possibly 

resulting in damage to the aeroplane and 

injury to the occupants. 

To enable early detection and repair of 

corrosion of the internal surfaces, EASA 

issued EASA AD 2007–0314 [http://ad.easa.

europa.eu/ad/2007-0314R1] to require a onetime inspection of all MLG bogie beams, 

except Enhanced MLG bogie beams, and the 

reporting of the results to Airbus. EASA AD 

2007–0314 was revised and later superseded 

by EASA AD 2008–0093 [http://ad.easa.

europa.eu/ad/2008-0093], reducing the 

inspection threshold period. 

The results of subsequent investigations 

showed thin paint coats and paint 

degradation, confirmed as well on Enhanced 

MLG bogie beams. To address this additional 

concern, EASA issued AD 2011–0141 [http:// 

ad.easa.europa.eu/ad/2011-0141] [which was 

not mandated by the FAA], retaining the 

requirements of EASA AD 2008–0093, which 

was superseded, to require a one-time visual 

inspection of all MLG bogie beams, including 

a visual examination of the internal diameter 

for corrosion or damage to protective 

treatments of the bogie beam and 

measurement of the paint thickness on the 

internal bore, accomplishment of the 

applicable corrective actions and a 

modification of the MLG bogie beam to 

improve the coat paint application method, 

and application of corrosion protection. 

Prompted by in-service requests, EASA 

issued EASA AD 2012–0015 [http://ad.easa.

europa.eu/ad/2012-0015] [corresponds with 

FAA NPRM (78 FR 58978, September 25, 

2013)] retaining the requirements of EASA 

AD 2011–0141, which was superseded, and 

introducing repetitive inspections of the 

MLG bogie beams, which allows extension of 

the compliance time for the MLG bogie beam 

modification from 15 years to 21 years. 

Modification of a MLG bogie beam 

constitutes terminating action for the 

repetitive inspections for that MLG bogie 

beam. 

Reports on inspection results provided to 

Airbus show that some aeroplanes were 

initially inspected too early (before 4 years 

and 6 months since aeroplane first flight with 

bogie beam installed/installed after overhaul) 

and have not been re-inspected as required. 

For the reasons described above, this 

[EASA] AD retains the requirements of EASA 

AD 2012–0015, which is superseded, and 

redefines the inspection periodicity. This 

[EASA] AD also introduces a specific onetime inspection for aeroplanes that have been 

inspected too early. 

Prompted by operator comments, this 

[EASA] AD is revised to clarify the required 

actions and the specific configurations to 

which the actions must be applied. Appendix 

1 of this [EASA] AD has been amended 

accordingly. 

This [EASA] AD is republished to 

editorially correct paragraph (4). 

You may examine the MCAI in the 

AD docket on the Internet at http://

www.regulations.gov by searching for 

and locating Docket No. FAA–2013– 

0828. 

Related Service Information Under 1 

CFR Part 51 

We reviewed the following Airbus 

service information. 

• Airbus Mandatory Service Bulletin 

A330–32–3225, Revision 2, dated 

October 26, 2012. The service 

information describes procedures for 

cleaning the internal bore and 

accomplishing a detailed inspection of 

internal surfaces of the left hand (LH) 

and right hand (RH) MLG bogie beams 

to detect any damage to the protective 

treatments and any corrosion, and 

measuring the paint thickness on the 

internal bore. 

• Airbus Mandatory Service Bulletin 

A330–32–3237, Revision 1, dated 

October 14, 2011. The service 

information describes procedures for a 

detailed inspection for damage and 

corrosion of the internal bores of the LH 

and RH MLG bogie beam and repair, as 

well as modification and reidentification. 

• Airbus Mandatory Service Bulletin 

A340–32–4268, Revision 3, dated 

January 14, 2013. The service 

information describes procedures for 

cleaning the internal bore and 

accomplishing a detailed inspection of 

internal surfaces of the LH and RH MLG 

bogie beams to detect any damage to the 

protective treatments and any corrosion, 

and measuring the paint thickness on 

the internal bore. 

• Airbus Mandatory Service Bulletin 

A340–32–4279, Revision 1, dated 

October 14, 2011. The service 

information describes procedures for a 

detailed inspection for damage and 

corrosion of the internal bores of the LH 

and RH MLG bogie beam, repair, 

modification, and reidentification. 

We reviewed the following MessierDowty service bulletins. 

• Messier-Dowty Service Bulletin 

A33/34–32–271, Revision 1, dated 

November 16, 2007. The service 

information describes procedures for 

inspections and corrective actions on 

both MLG bogie beams. 

• Messier-Dowty Service Bulletin 

A33/34–32–272, Revision 1, including 

Appendixes A, B, C, and D, dated 

September 22, 2008. The service 

information describes procedures for 

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Federal Register / Vol. 81, No. 24 / Friday, February 5, 2016 / Proposed Rules 6187 

inspections and corrective actions on 

both MLG bogie beams. 

• Messier-Dowty Service Bulletin 

A33/34–32–278, including Appendixes 

A and B, Revision 1, dated August 24, 

2011. The service information describes 

procedures for inspections for damage 

and corrosion to the protective 

treatment of the internal bores of the LH 

and RH MLG bogie beam, and repairs. 

• Messier-Dowty Service Bulletin 

A33/34–32–283, including Appendix A, 

Revision 1, dated July 10, 2012. The 

service information describes 

procedures for modification of the LH 

and RH MLG bogie beams. 

• Messier-Dowty Service Bulletin 

A33/34–32–284, including Appendix A, 

Revision 1, dated July 10, 2012. The 

service information describes 

procedures for modification of the LH 

and RH MLG bogie beams. 

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. 

Change to the First SNPRM 

Since the first SNPRM was issued, the 

AD format has been revised, and certain 

paragraphs have been rearranged. As a 

result, paragraphs (m)(1) and (m)(2) of 

the proposed AD (in the first SNPRM) 

have been redesignated as paragraphs 

(n)(1) and (n)(2) of this proposed AD. 

Comments 

We gave the public the opportunity to 

participate in developing this proposed 

AD. We considered the comment 

received. 

Request To Revise Paragraph (l) of the 

Proposed AD (in the First SNPRM) 

Air France requested that we revise 

paragraph (l) of the proposed AD (in the 

first SNPRM) by changing the references 

to paragraphs (n)(1) and (n)(2) to refer to 

paragraphs (m)(1) and (m)(2). 

We agree that the optional terminating 

action paragraph should refer to the 

optional methods of compliance 

paragraphs, which are paragraphs (m)(1) 

and (m)(2) of the proposed AD (in the 

first SNPRM). However, no change to 

this proposed AD is necessary because 

those paragraphs have been 

redesignated as paragraphs (n)(1) and 

(n)(2). 

FAA’s Determination and Requirements 

of This SNPRM 

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. 

Certain changes described above 

expand the scope of the first SNPRM. As 

a result, we have determined that it is 

necessary to reopen the comment period 

to provide additional opportunity for 

the public to comment on this SNPRM. 

Differences Between This SNPRM and 

the MCAI or Service Information 

The MCAI specifies repair and 

corrective actions in accordance with 

Airbus Mandatory Service Bulletin 

A330–32–3225, Revision 02, dated 

October 26, 2012; or A340–32–4268, 

Revision 03, dated January 14, 2013. 

However, Airbus Mandatory Service 

Bulletins A330–32–3225, Revision 02, 

dated October 26, 2012; and A340–32– 

4268, Revision 03, dated January 14, 

2013; do not describe repair and 

corrective actions. Paragraphs (i) and (j) 

of this proposed AD specify repair and 

corrective actions in accordance with 

Messier-Dowty Service Bulletin A33/

34–32–272, Revision 1, including 

Appendices A, B, C, and D, dated 

September 22, 2008. This difference has 

been coordinated with Airbus. 

Costs of Compliance 

We estimate that this proposed AD 

affects 51 airplanes of U.S. registry. 

We also estimate that it would take 

about 34 work-hours per product to 

comply with the new basic 

requirements of this proposed AD, and 

1 work-hour per product for reporting. 

The average labor rate is $85 per workhour. Based on these figures, we 

estimate the cost of this proposed AD on 

U.S. operators to be $151,725, or $2,975 

per product. 

In addition, we estimate that any 

necessary follow-on actions would take 

about 10 work-hours, for a cost of $850 

per product. We have no way of 

determining the number of aircraft that 

might need these actions. 

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 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. 

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6188 Federal Register / Vol. 81, No. 24 / Friday, February 5, 2016 / Proposed Rules 

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) 

2009–15–17, Amendment 39–15980 (74 

FR 37523, July 29, 2009), and adding the 

following new AD: 

Airbus: Docket No. FAA–2013–0828; 

Directorate Identifier 2012–NM–036–AD. 

(a) Comments Due Date 

We must receive comments by March 21, 

2016. 

(b) Affected ADs 

This AD replaces AD 2009–15–17, 

Amendment 39–15980 (74 FR 37523, July 29, 

2009). 

(c) Applicability 

This AD applies to the airplanes identified 

in paragraphs (c)(1) and (c)(2) of this AD, 

certificated in any category, all manufacturer 

serial numbers (MSN), except those on which 

Airbus modification 58896 has been 

embodied in production. 

(1) Airbus Model A330–223F, –243F, –201, 

–202, –203, –223, –243, –301, –302, –303, 

–321, –322, –323, –341, –342, and –343 

airplanes. 

(2) Airbus Model A340–211, –212, –213, 

–311, –312, and –313 airplanes. 

(d) Subject 

Air Transport Association (ATA) of 

America Code 32, Landing gear. 

(e) Reason 

This AD was prompted by reports of thin 

paint coats and paint degradation on 

enhanced main landing gear (MLG) bogie 

beams, as well as reports that some airplanes 

have been inspected too early and not reinspected as needed. We are issuing this AD 

to detect and correct damage or corrosion of 

the MLG bogie beams, which could cause a 

runway excursion event, bogie beam 

detachment from the airplane, or MLG 

collapse, and could result in damage to the 

airplane and injury to the occupants. 

(f) Compliance 

Comply with this AD within the 

compliance times specified, unless already 

done. 

(g) Repetitive Inspections for Certain 

Airplane Configurations 

For airplanes equipped with basic MLG 

(201252 series), or growth MLG (201490 

series): After 54 months at the earliest, but no 

later than 72 months since the left-hand (LH) 

or right-hand (RH) MLG bogie beam’s first 

flight on an airplane, or since its first flight 

on an airplane after overhaul, as applicable, 

clean the internal bore and accomplish a 

detailed inspection of internal surfaces of the 

LH and RH MLG bogie beams to detect any 

damage to the protective treatments and any 

corrosion, and measure the paint thickness 

on the internal bore, in accordance with the 

Accomplishment Instructions of Airbus 

Mandatory Service Bulletin A330–32–3225, 

Revision 2, dated October 26, 2012; or Airbus 

Mandatory Service Bulletin A340–32–4268, 

Revision 3, dated January 14, 2013; as 

applicable. Repeat the inspections thereafter 

at intervals not less than 54 months, but not 

exceeding 72 months, after the most recent 

inspection. During overhaul of a MLG bogie 

beam, any corrosion will be removed, which 

means that the first inspection after overhaul 

of that MLG bogie beam, as required by this 

paragraph, is between 54 months and 72 

months since its first flight on an airplane 

after overhaul. 

(h) One-Time Detailed Inspection for Certain 

Airplane Configurations 

For airplanes equipped with basic MLG 

(201252 series), or growth MLG (201490 

series) having a LH or RH MLG bogie beam 

that has already exceeded 72 months since its 

first flight on an airplane, or since its first 

flight on an airplane after overhaul, as 

applicable, as of the effective date of this AD; 

and that has been inspected as specified in 

Airbus Mandatory Service Bulletin A330–32– 

3225 or Airbus Mandatory Service Bulletin 

A340–32–4268, as applicable, earlier than 54 

months since first flight of the affected MLG 

bogie beam on an airplane, or since its first 

flight on an airplane after its most recent 

overhaul, as applicable: Within the 

applicable compliance time indicated in 

paragraphs (h)(1) through (h)(4) of this AD, 

clean the internal bore and accomplish a 

detailed inspection of the internal surfaces of 

the LH and RH MLG bogie beams to detect 

any damage to the protective treatments and 

any corrosion, and measure the paint 

thickness on the internal bore, in accordance 

with the Accomplishment Instructions of 

Airbus Mandatory Service Bulletin A330–32– 

3225, Revision 2, dated October 26, 2012; or 

Airbus Mandatory Service Bulletin A340–32– 

4268, Revision 3, dated January 14, 2013; as 

applicable. 

(1) For MLG bogie beams having the 

configurations specified in both paragraphs 

(h)(1)(i) and (h)(1)(ii) of this AD: Do the 

detailed inspection specified in paragraph (h) 

of this AD within 9 months after the effective 

date of this AD. 

(i) MLG bogie beams having between 72 

and 120 months since first flight on an 

airplane, or since the MLG bogie beam’s first 

flight on an airplane after the MLG bogie 

beam’s most recent overhaul, as applicable. 

(ii) MLG bogie beams on which the first 

inspection was done after 51 months and 

before 54 months since first flight of the MLG 

bogie beam on an airplane, or since the MLG 

bogie beam’s first flight on an airplane after 

the MLG bogie beam’s most recent overhaul, 

as applicable. 

(2) For MLG bogie beams having the 

configurations specified in both paragraphs 

(h)(2)(i) and (h)(2)(ii) of this AD: Do the 

detailed inspection specified in paragraph (h) 

of this AD within 3 months after the effective 

date of this AD. 

(i) MLG bogie beams having between 72 

and 120 months since first flight on an 

airplane, or since the MLG bogie beam’s first 

flight on an airplane after the MLG bogie 

beam’s most recent overhaul, as applicable. 

(ii) MLG bogie beams on which the first 

inspection was done after 45 months and 

before 51 months since first flight of the MLG 

bogie beam on an airplane, or since the MLG 

bogie beam’s first flight on an airplane after 

the MLG bogie beam’s most recent overhaul, 

as applicable. 

(3) For MLG bogie beams having the 

configurations specified in both paragraphs 

(h)(3)(i) and (h)(3)(ii) of this AD: Do the 

detailed inspection specified in paragraph (h) 

of this AD within 3 months after the effective 

date of this AD. 

(i) MLG bogie beams having between 72 

and 96 months since first flight on an 

airplane, or since the MLG bogie beam’s first 

flight on an airplane after the MLG bogie 

beam’s most recent overhaul, as applicable. 

(ii) MLG bogie beams which has 

accumulated, at the effective date of this AD, 

less than 96 months and on which the first 

inspection was done before 51 months since 

first flight of the MLG bogie beam on an 

airplane, or since the MLG bogie beam’s first 

flight on an airplane after the after the MLG 

bogie beam’s most recent overhaul, as 

applicable. 

(4) For MLG bogie beams having the 

configurations specified in both paragraphs 

(h)(4)(i) and (h)(4)(ii) of this AD: Do the 

detailed inspection specified in paragraph (h) 

of this AD within 1 month after the effective 

date of this AD. 

(i) MLG bogie beams having between 96 

and 120 months since first flight on an 

airplane, or since the MLG bogie beam’s first 

flight on an airplane after the MLG bogie 

beam’s most recent overhaul, as applicable. 

(ii) MLG bogie beams which has 

accumulated, at the effective date of this AD, 

96 months or more and on which the first 

inspection was done before 45 months since 

first flight of the MLG bogie beam on an 

airplane, or since the MLG bogie beam’s first 

flight on an airplane after the MLG bogie 

beam’s most recent overhaul, as applicable. 

(i) Application of Protective Treatment 

If, during any inspection required by 

paragraph (g) or (h) of this AD, no damage 

or corrosion is found, before further flight, 

apply the protective treatments to the MLG 

bogie beam, in accordance with the 

Accomplishment Instructions of MessierDowty Service Bulletin A33/34–32–272, 

Revision 1, including Appendixes A, B, C, 

and D, dated September 22, 2008. 

(j) Repair and Application of Protective 

Treatment 

If, during any inspection required by 

paragraph (g) or (h) of this AD, any damage 

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Federal Register / Vol. 81, No. 24 / Friday, February 5, 2016 / Proposed Rules 6189 

or corrosion is found, before further flight, 

repair and apply the protective treatments to 

the MLG bogie beam, in accordance with the 

Accomplishment Instructions of MessierDowty Service Bulletin A33/34–32–272, 

Revision 1, including Appendixes A, B, C, 

and D, dated September 22, 2008. 

(k) Inspection and Corrective Actions 

For airplanes equipped with basic MLG 

(201252 series), growth MLG (201490 series), 

or enhanced MLG (10–210 series): Before the 

accumulation of 252 total months on an MLG 

bogie beam, or within 90 days after the 

effective date of this AD, whichever occurs 

later, do the actions specified in paragraphs 

(k)(1) and (k)(2) of this AD concurrently and 

in sequence. 

(1) Except as provided by paragraph (k)(3) 

of this AD: Do a detailed inspection for 

damage and corrosion of the internal bores of 

the LH and RH MLG bogie beam, in 

accordance with the Accomplishment 

Instructions of Airbus Mandatory Service 

Bulletin A330–32–3237 or A340–32–4279, 

both Revision 1, both dated October 14, 2011, 

as applicable. If any damage or corrosion is 

found, before further flight, repair in 

accordance with the Accomplishment 

Instructions of Airbus Mandatory Service 

Bulletin A330–32–3237 or A340–32–4279, 

both Revision 1, both dated October 14, 2011, 

as applicable. 

(2) Except as provided by paragraph (k)(3) 

of this AD: Modify and re-identify, as 

applicable, the LH and RH MLG bogie beams, 

in accordance with the Accomplishment 

Instructions of Airbus Mandatory Service 

Bulletin A330–32–3237 or A340–32–4279, 

both Revision 1, both dated October 14, 2011, 

as applicable. 

(3) The inspection requirements of 

paragraph (k)(1) of this AD, and the 

modification requirements only of paragraph 

(k)(2) of this AD, do not apply to any MLG 

bogie beam with a serial number listed in 

Appendix A of Messier-Dowty Service 

Bulletin A33/34–32–283 or A33/34–32–284, 

both Revision 1, both dated July 10, 2012, as 

applicable. 

(l) Optional Methods of Compliance for 

Certain Airplane Configurations 

Inspections and corrective actions on both 

MLG bogie beams done in accordance with 

the instructions of Messier-Dowty Service 

Bulletin A33/34–32–271, Revision 1, dated 

November 16, 2007; or A33/34–32–272, 

Revision 1, including Appendixes A, B, C, 

and D, dated September 22, 2008; as 

applicable; are acceptable methods of 

compliance for the requirements of paragraph 

(g) of this AD, provided each inspection is 

accomplished between 54 months and 72 

months since the first flight of the affected 

MLG bogie beam on an airplane, or since the 

MLG bogie beam’s first flight after the MLG 

bogie beam’s most recent overhaul, as 

applicable. 

(m) Reporting 

(1) Submit a report of the findings (both 

positive and negative) of each inspection 

required by paragraph (g) or (k) of this AD, 

as applicable, to Airbus, Customer Service 

Directorate, 1 Rond Point Maurice Bellonte, 

31707 Blagnac Cedex, France, using the 

applicable reporting sheet in Airbus 

Mandatory Service Bulletin A330–32–3237, 

Revision 1, dated October 14, 2011; or Airbus 

Mandatory Service Bulletin A340–32–4279, 

Revision 1, dated October 14, 2011; at the 

applicable time specified in paragraph 

(m)(1)(i) or (m)(1)(ii) of this AD. 

(i) If the inspection was done on or after 

the effective date of this AD: Submit the 

report within 90 days after the inspection. 

(ii) If the inspection was done before the 

effective date of this AD: Submit the report 

within 90 days after the effective date of this 

AD. 

(2) Submit a report of the findings (both 

positive and negative) of the inspection 

required by paragraph (h) of this AD to 

Airbus, Customer Service Directorate, 1 Rond 

Point Maurice Bellonte, 31707 Blagnac 

Cedex, France, using the applicable reporting 

sheet in Airbus Service Bulletin A330–32– 

3237 or A340–32–4279, both dated January 

18, 2011, at the applicable time specified in 

paragraph (m)(2)(i) or (m)(2)(ii) of this AD. 

(i) If the inspection was done on or after 

the effective date of this AD: Submit the 

report within 30 days after the inspection. 

(ii) If the inspection was done before the 

effective date of this AD: Submit the report 

within 30 days after the effective date of this 

AD. 

(n) Optional Method of Compliance 

(1) Inspections for damage and corrosion to 

the protective treatment of the internal bores 

of the LH and RH MLG bogie beam, and 

repairs, done in accordance with MessierDowty Service Bulletin A33/34–32–278, 

including Appendixes A and B, Revision 1, 

dated August 24, 2011, are acceptable 

methods of compliance with the 

corresponding requirements of paragraph 

(k)(1) of this AD. 

(2) Modification of the LH and RH MLG 

bogie beams, done in accordance with 

Messier-Dowty Service Bulletins A33/34–32– 

283 and A33/34–32–284, both including 

Appendix A, both Revision 1, both dated July 

10, 2012, as applicable, is an acceptable 

method of compliance with the 

corresponding requirements of paragraph 

(k)(2) of this AD. 

(o) Optional Terminating Action 

Modification of both LH and RH MLG 

bogie beams on an airplane, done in 

accordance with paragraph (k) of this AD, or 

as specified in paragraphs (n)(1) and (n)(2) of 

this AD, terminates the repetitive inspections 

required by paragraph (g) of this AD for this 

airplane. 

(p) Credit for Previous Actions 

(1) This paragraph provides credit for the 

corresponding inspections and corrective 

actions done on an LH or RH MLG bogie 

beam required by paragraph (g) of this AD, 

if those actions were performed before the 

effective date of this AD using Airbus 

Mandatory Service Bulletin A330–32–3225, 

dated November 21, 2007; or Revision 1, 

dated October 30, 2008; provided the 

inspections and corrective actions were 

accomplished between 54 months and 72 

months since first flight of the affected MLG 

bogie beam on an airplane, or since its first 

flight after the MLG bogie beam’s most recent 

overhaul, as applicable. Airbus Mandatory 

Service Bulletin A330–32–3225, dated 

November 21, 2007, is not incorporated by 

reference in this AD. Airbus Mandatory 

Service Bulletin A330–32–3225, Revision 1, 

dated October 30, 2008, was incorporated by 

reference in AD 2009–15–07, Amendment 

39–15980 (74 FR 37523, July 29, 2009). 

(2) This paragraph provides credit for the 

corresponding inspections and corrective 

actions done on an LH or RH MLG bogie 

beam required by paragraph (g) of this AD, 

if those actions were performed before the 

effective date of this AD using Airbus 

Mandatory Service Bulletin A340–32–4268, 

dated November 21, 2007; Revision 1, dated 

October 30, 2008; or Revision 2, dated 

October 26, 2012; provided these inspections 

and corrective actions were accomplished 

between 54 months and 72 months since first 

flight of the affected MLG bogie beam on an 

airplane, or since its first flight after the MLG 

bogie beam’s most recent overhaul, as 

applicable. Airbus Mandatory Service 

Bulletin A340–32–4268, dated November 21, 

2007; and Revision 2, dated October 26, 

2012; are not incorporated by reference in 

this AD. Airbus Mandatory Service Bulletin 

A340–32–4268, Revision 1, dated October 30, 

2008, was incorporated by reference in AD 

2009–15–17, Amendment 39–15980 (74 FR 

37523, July 29, 2009). 

(3) This paragraph provides credit for the 

corresponding actions required by paragraph 

(n)(1) of this AD, if those actions were 

performed before the effective date of this AD 

using Messier-Dowty Service Bulletin A33/

34–32–271, dated September 13, 2007, which 

is not incorporated by reference in this AD. 

(4) This paragraph provides credit for the 

corresponding actions required by 

paragraphs (j) and (n)(1) of this AD, if those 

actions were performed before the effective 

date of this AD using Messier-Dowty Service 

Bulletin A33/34–32–272, including 

Appendixes A, B, C, and D, dated November 

16, 2007, which is not incorporated by 

reference in this AD. 

(5) This paragraph provides credit for the 

corresponding actions required by 

paragraphs (k), (m), and (r)(1)(i) of this AD, 

if those actions were performed before the 

effective date of this AD using Airbus 

Mandatory Service Bulletin A330–32–3237, 

dated January 18, 2011, which is not 

incorporated by reference in this AD. 

(6) This paragraph provides credit for the 

corresponding actions required by 

paragraphs (k), (m), and (r)(1)(i) of this AD, 

if those actions were performed before the 

effective date of this AD using Airbus 

Mandatory Service Bulletin A340–32–4279, 

dated January 18, 2011, which is not 

incorporated by reference in this AD. 

(7) This paragraph provides credit for the 

corresponding actions required by 

paragraphs (k)(3), (n)(2), (r)(1)(ii), and 

(r)(1)(iii) of this AD, if those actions were 

performed before the effective date of this AD 

using Messier-Dowty Service Bulletin A33/

34–32–283, including Appendix A, dated 

May 11, 2010, which is not incorporated by 

reference in this AD. 

(8) This paragraph provides credit for the 

corresponding actions required by 

paragraphs (k)(3), (n)(2), (r)(1)(ii), and 

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6190 Federal Register / Vol. 81, No. 24 / Friday, February 5, 2016 / Proposed Rules 

(r)(1)(iii) of this AD, if those actions were 

performed before the effective date of this AD 

using Messier-Dowty Service Bulletin A33/

34–32–284, including Appendix A, dated 

May 11, 2010, which is not incorporated by 

reference in this AD. 

(9) This paragraph provides credit for the 

corresponding actions required by 

paragraphs (n)(1) and (r)(1)(ii) of this AD, if 

those actions were performed before the 

effective date of this AD using Messier-Dowty 

Service Bulletin A33/34–32–278, including 

Appendixes A and B, dated February 17, 

2010, which is not incorporated by reference 

in this AD. 

(q) Clarification of Inspection Compliance 

Times 

After accomplishment of the one-time 

detailed inspection required by paragraph (h) 

of this AD, the repetitive actions required by 

paragraph (g) of this AD remain applicable, 

and must be done within the compliance 

times specified in paragraph (g) of this AD. 

(r) Parts Installation Limitations 

(1) After modification of an airplane, as 

required by paragraph (k) of this AD, or as 

specified in paragraphs (n)(1) and (n)(2) of 

this AD, do not install an MLG bogie beam 

on any airplane unless it is done in 

compliance with the requirements of 

paragraph (r)(1)(i), (r)(1)(ii), or (r)(1)(iii) of 

this AD. 

(i) The MLG bogie beam has been modified 

and re-identified in accordance with the 

Accomplishment Instructions of Airbus 

Mandatory Service Bulletin A330–32–3237 

or A340–32–4279, both Revision 1, both 

dated October 14, 2011, as applicable. 

(ii) The MLG bogie beam has been 

inspected and all applicable corrective 

actions have been done in accordance with 

the Accomplishment Instructions of MessierDowty Service Bulletin A33/34–32–278, 

Revision 1, dated August 24, 2011; and 

modified in accordance with the 

Accomplishment Instructions of MessierDowty Service Bulletin A33/34–32–283 or 

A33/34–32–284, both Revision 1, both dated 

July 10, 2012. 

(iii) The MLG bogie beam has a serial 

number listed in Appendix A of MessierDowty Service Bulletin A33/34–32–283 or 

A33/34–32–284, both Revision 1, both dated 

July 10, 2012. 

(2) As of the effective date of this AD, 

except as specified in paragraph (r)(1) of this 

AD, installation of an MLG bogie beam on an 

airplane is allowed, provided that following 

the installation it is inspected and all 

applicable repairs and corrective actions 

have been done in accordance with the 

requirements of this AD. 

(s) Related Information 

(1) Refer to Mandatory Continuing 

Airworthiness Information (MCAI) European 

Aviation Safety Agency (EASA) AD 2013– 

0267R1, dated March 4, 2014, corrected 

March 8, 2014, 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– 

2013–0828. 

(2) For Airbus service information 

identified in this AD, contact Airbus SAS, 

Airworthiness Office—EAL, 1 Rond Point 

Maurice Bellonte, 31707 Blagnac Cedex, 

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

+33 5 61 93 45 80; email: 

airworthiness.A330-A340@airbus.com; 

Internet http://www.airbus.com. 

(3) For Messier-Dowty service information 

identified in this AD, contact Messier-Dowty: 

Messier Services Americas, Customer 

Support Center, 45360 Severn Way, Sterling, 

VA 20166–8910; telephone 703–450–8233; 

fax 703–404–1621; Internet https://techpubs.

services/messier-dowty.com. 

(4) You may view this service information 

at the FAA, Transport Airplane Directorate, 

1601 Lind Avenue SW., Renton, WA. For 

information on the availability of this 

material at the FAA, call 425–227–1221. 

Issued in Renton, Washington, on January 

27, 2016. 

Michael Kaszycki, 

Acting Manager, Transport Airplane 

Directorate, Aircraft Certification Service. 

[FR Doc. 2016–02161 Filed 2–4–16; 8:45 am] 

BILLING CODE 4910–13–P 

DEPARTMENT OF JUSTICE 

Drug Enforcement Administration 

21 CFR Part 1308 

[Docket No. DEA–433] 

Schedules of Controlled Substances: 

Placement of PB-22, 5F-PB-22, ABFUBINACA and ADB-PINACA into 

Schedule I 

AGENCY: Drug Enforcement 

Administration, Department of Justice. 

ACTION: Notice of proposed rulemaking. 

SUMMARY: The Drug Enforcement 

Administration proposes placing 

quinolin-8-yl 1-pentyl-1H-indole-3- 

carboxylate (PB-22; QUPIC), quinolin-8- 

yl 1-(5-fluoropentyl)-1H-indole-3- 

carboxylate (5-fluoro-PB-22; 5F-PB-22), 

N-(1-amino-3-methyl-1-oxobutan-2-yl)- 

1-(4-fluorobenzyl)-1H-indazole-3- 

carboxamide (AB-FUBINACA) and N-(1- 

amino-3,3-dimethyl-1-oxobutan-2-yl)-1- 

pentyl-1H-indazole-3-carboxamide 

(ADB-PINACA), 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 Substances 

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 chemical analysis, or 

possess), or propose to handle PB-22, 

5F-PB-22, AB-FUBINACA, or ADBPINACA. 

DATES: Interested persons may file 

written comments on this proposal in 

accordance with 21 CFR 1308.43(g). 

Comments must be submitted 

electronically or postmarked on or 

before March 7, 2016. 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 or waiver of hearing 

pursuant to 21 CFR 1308.44 and in 

accordance with 21 CFR 1316.45 and/or 

1316.47, as applicable. Requests for 

hearing and waivers of an opportunity 

for a hearing or to participate in a 

hearing must be received on or before 

March 7, 2016. 

ADDRESSES: To ensure proper handling 

of comments, please reference ‘‘Docket 

No. DEA–433’’ on all electronic and 

written 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 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. 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/ODW, 

8701 Morrissette Drive, Springfield, 

Virginia 22152. 

• Hearing requests: All requests for a 

hearing and waivers of participation 

must be sent to: Drug Enforcement 

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