Federal Register / Vol. 82, No. 180 / Tuesday, September 19, 2017 / Proposed Rules 43715 

persons were invited to attend the 

meeting and participate in Committee 

deliberations on all issues. Like all 

Committee meetings, the June 7, 2017, 

meeting was a public meeting, and all 

entities, both large and small, were able 

to express views on this issue. Finally, 

interested persons are invited to submit 

comments on this proposed rule, 

including the regulatory and 

informational impacts of this action on 

small businesses. 

In accordance with the Paperwork 

Reduction Act of 1995 (44 U.S.C. 

chapter 35), the order’s information 

collection requirements have been 

previously approved by OMB and 

assigned OMB No. 0581–0178 

(Vegetable and Specialty Crops). No 

changes in those requirements as a 

result of this action are necessary. 

Should any changes become necessary, 

they would be submitted to OMB for 

approval. 

This proposed rule would impose no 

additional reporting or recordkeeping 

requirements on either small or large 

South Texas onion handlers. As with all 

Federal marketing order programs, 

reports and forms are periodically 

reviewed to reduce information 

requirements and duplication by 

industry and public sector agencies. 

AMS is committed to complying with 

the E-Government Act, to promote the 

use of the internet and other 

information technologies to provide 

increased opportunities for citizen 

access to Government information and 

services, and for other purposes. 

USDA has not identified any relevant 

Federal rules that duplicate, overlap, or 

conflict with this action. 

A small business guide on complying 

with fruit, vegetable, and specialty crop 

marketing agreements and orders may 

be viewed at: http://www.ams.usda.gov/ 

rules-regulations/moa/small-businesses. 

Any questions about the compliance 

guide should be sent to Richard Lower 

at the previously mentioned address in 

the FOR FURTHER INFORMATION CONTACT

section. 

A 30-day comment period is provided 

to allow interested persons to respond 

to this proposed rule. Thirty days is 

deemed appropriate because: (1) The 

2017–18 fiscal period begins on August 

1, 2017, and the marketing order 

requires that the rate of assessment for 

each fiscal period apply to all assessable 

onions handled during such fiscal 

period; (2) the Committee needs to have 

sufficient funds to pay its expenses, 

which are incurred on a continuous 

basis; and (3) handlers are aware of this 

action, which was unanimously 

recommended by the Committee at a 

public meeting and is similar to other 

assessment rate actions issued in past 

years. 

List of Subjects in 7 CFR Part 959 

Marketing agreements, Onions, 

Reporting and recordkeeping 

requirements. 

For the reasons set forth in the 

preamble, 7 CFR part 959 is proposed to 

be amended as follows: 

PART 959—ONIONS GROWN IN 

SOUTH TEXAS 

■ 1. The authority citation for 7 CFR 

part 959 continues to read as follows: 

Authority: 7 U.S.C. 601–674. 

Subpart A—[Amended] 

■ 2. Designate the subpart labeled 

‘‘Order Regulating Handling’’ as subpart 

A. 

Subpart B—Administrative Provisions 

■ 3. Designate the subpart labeled 

‘‘Rules and Regulations’’ as subpart B 

and revise the heading as shown above. 

Subparts ‘‘Assessment Rates’’ and 

‘‘Handling Regulations’’—[Amended] 

■ 4. Remove the subpart headings 

‘‘Assessment Rates’’ and ‘‘Handling 

Regulations’’. 

■ 5. Transfer §§ 959.237 and 959.322 to 

subpart B. 

■ 6. Section 959.237 is revised to read 

as follows: 

§ 959.237 Assessment rate. 

On and after August 1, 2017, an 

assessment rate of $0.065 per 50-pound 

equivalent is established for South 

Texas onions. 

Dated: September 12, 2017. 

Bruce Summers, 

Acting Administrator, Agricultural Marketing 

Service. 

[FR Doc. 2017–19690 Filed 9–18–17; 8:45 am] 

BILLING CODE 3410–02–P 

DEPARTMENT OF TRANSPORTATION 

Federal Aviation Administration 

14 CFR Part 39 

[Docket No. FAA–2017–0812; Product 

Identifier 2016–NM–198–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 A330–200 series 

airplanes, Model A330–200 Freighter 

series airplanes, and Model A330–300 

series airplanes. This proposed AD was 

prompted by an evaluation by the 

design approval holder (DAH) 

indicating that certain fuselage 

structures are subject to widespread 

fatigue damage (WFD). This proposed 

AD would require reinforcement 

modifications of various structural parts 

of the fuselage, and related investigative 

and corrective actions if necessary. We 

are proposing this AD to address the 

unsafe condition on these products. 

DATES: We must receive comments on 

this proposed AD by November 3, 2017. 

ADDRESSES: You may send comments, 

using the procedures found in 14 CFR 

11.43 and 11.45, by any of the following 

methods: 

• Federal eRulemaking Portal: Go to 

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

instructions for submitting comments. 

• Fax: 202–493–2251. 

• Mail: U.S. Department of 

Transportation, Docket Operations, M– 

30, West Building Ground Floor, Room 

W12–140, 1200 New Jersey Avenue SE., 

Washington, DC 20590. 

• Hand Delivery: Deliver to Mail 

address above between 9 a.m. and 5 

p.m., Monday through Friday, except 

Federal holidays. 

For service information identified in 

this 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. You 

may view this referenced service 

information at the FAA, Transport 

Standards Branch, 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–2017– 

0812; 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. 


asabaliauskas on DSKBBXCHB2PROD with PROPOSALS
43716 Federal Register / Vol. 82, No. 180 / Tuesday, September 19, 2017 / Proposed Rules 

FOR FURTHER INFORMATION CONTACT: 

Vladimir Ulyanov, Aerospace Engineer, 

International Section, Transport 

Standards Branch, 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 proposal. Send your comments to 

an address listed under the ADDRESSES

section. Include ‘‘Docket No. FAA– 

2017–0812; Product Identifier 2016– 

NM–198–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 

Fatigue damage can occur locally, in 

small areas or structural design details, 

or globally, in widespread areas. 

Multiple-site damage is widespread 

damage that occurs in a large structural 

element such as a single rivet line of a 

lap splice joining two large skin panels. 

Widespread damage can also occur in 

multiple elements such as adjacent 

frames or stringers. Multiple-site 

damage and multiple-element damage 

cracks are typically too small initially to 

be reliably detected with normal 

inspection methods. Without 

intervention, these cracks will grow, 

and eventually compromise the 

structural integrity of the airplane. This 

condition is known as widespread 

fatigue damage. It is associated with 

general degradation of large areas of 

structure with similar structural details 

and stress levels. As an airplane ages, 

WFD will likely occur, and will 

certainly occur if the airplane is 

operated long enough without any 

intervention. 

The FAA’s WFD final rule (75 FR 

69746, November 15, 2010) became 

effective on January 14, 2011. The WFD 

rule requires certain actions to prevent 

structural failure due to WFD 

throughout the operational life of 

certain existing transport category 

airplanes and all of these airplanes that 

will be certificated in the future. For 

existing and future airplanes subject to 

the WFD rule, the rule requires that 

DAHs establish a limit of validity (LOV) 

of the engineering data that support the 

structural maintenance program. 

Operators affected by the WFD rule may 

not fly an airplane beyond its LOV, 

unless an extended LOV is approved. 

The WFD rule (75 FR 69746, 

November 15, 2010) does not require 

identifying and developing maintenance 

actions if the DAHs can show that such 

actions are not necessary to prevent 

WFD before the airplane reaches the 

LOV. Many LOVs, however, do depend 

on accomplishment of future 

maintenance actions. As stated in the 

WFD rule, any maintenance actions 

necessary to reach the LOV will be 

mandated by airworthiness directives 

through separate rulemaking actions. 

In the context of WFD, this action is 

necessary to enable DAHs to propose 

LOVs that allow operators the longest 

operational lives for their airplanes, and 

still ensure that WFD will not occur. 

This approach allows for an 

implementation strategy that provides 

flexibility to DAHs in determining the 

timing of service information 

development (with FAA approval), 

while providing operators with certainty 

regarding the LOV applicable to their 

airplanes. 

The European Aviation Safety Agency 

(EASA), which is the Technical Agent 

for the Member States of the European 

Union, has issued EASA Airworthiness 

Directive 2016–0207, dated October 19, 

2016 (referred to after this as the 

Mandatory Continuing Airworthiness 

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

an unsafe condition for all Airbus 

Model A330–200 series airplanes, 

Model A330–200 Freighter series 

airplanes, and Model A330–300 series 

airplanes. The MCAI states: 

An analysis conducted on A330 aeroplanes 

identified structural areas which are 

susceptible to widespread fatigue damage 

(WFD). 

This condition, if not corrected, could lead 

to crack initiation and undetected 

propagation, leading to reduced structural 

integrity of the aeroplane, possibly resulting 

in rapid depressurisation and consequent 

injury to occupants. 

To address this potential unsafe condition, 

Airbus developed a number of modifications 

(Mod) and published associated Service 

Bulletins (SB) for embodiment in service, to 

provide instructions to reinforce the various 

structural parts of the fuselage. 

For the reasons described above, this 

[EASA] AD requires accomplishment of these 

modifications and reinforcements [and 

related investigative and corrective actions]. 

Related investigative actions include a 

rotating probe hole inspection for 

cracking. 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–2017– 

0812. 

Related Service Information Under 1 

CFR Part 51 

Airbus has issued the following 

service information. This service 

information describes procedures for 

modifications and reinforcement of 

various structural parts of the fuselage. 

These documents are distinct since they 

apply to different airplane models in 

different configurations. 

• Airbus Service Bulletin A330–53– 

3144, Revision 01, dated July 25, 2006. 

• Airbus Service Bulletin A330–53– 

3144, Revision 04, dated November 23, 

2015. 

• Airbus Service Bulletin A330–53– 

3222, Revision 01, dated March 31, 

2016. 

• Airbus Service Bulletin A330–53– 

3223, Revision 00, dated January 19, 

2015. 

• Airbus Service Bulletin A330–53– 

3224, Revision 01, excluding Appendix 

01 and including Appendix 02, dated 

April 14, 2016. 

• Airbus Service Bulletin A330–53– 

3225, Revision 02, excluding Appendix 

01 and including Appendix 02, dated 

June 8, 2016. 

• Airbus Service Bulletin A330–53– 

3226, Revision 02, excluding Appendix 

01 and including Appendices 02, 03, 

and 04, dated October 27, 2016. 

• Airbus Service Bulletin A330–53– 

3236, Revision 02, excluding Appendix 

01 and including Appendices 02 and 03, 

dated March 23, 2016. 

• Airbus Service Bulletin A330–53– 

3237, Revision 01, dated February 8, 

2016. 

• Airbus Service Bulletin A330–53– 

3238, Revision 01, dated October 19, 

2015. 

• Airbus Service Bulletin A330–53– 

3239, Revision 01, dated July 4, 2016. 

• Airbus Service Bulletin A330–53– 

3244, Revision 01, dated August 2, 

2016. 

• Airbus Service Bulletin A330–53– 

3248, Revision 02, dated July 27, 2016. 

• Airbus Service Bulletin A330–53– 

3251, Revision 01, dated June 23, 2016. 

• Airbus Service Bulletin A330–53– 

3252, Revision 01, dated June 30, 2016. 

• Airbus Service Bulletin A330–53– 

3257, Revision 01, dated March 15, 

2016. 

• Airbus Service Bulletin A330–53– 

3258, Revision 00, dated April 20, 2015. 

• Airbus Service Bulletin A330–53– 

3259, Revision 02, dated July 18, 2016. 

• Airbus Service Bulletin A330–53– 

3263, Revision 01, excluding Appendix 

01 and including Appendix 02, dated 

December 1, 2015. 


asabaliauskas on DSKBBXCHB2PROD with PROPOSALS
Federal Register / Vol. 82, No. 180 / Tuesday, September 19, 2017 / Proposed Rules 43717 

• Airbus Service Bulletin A330–53– 

3273, Revision 00, dated September 28, 

2016. 

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. 

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. 

Explanation of Compliance Time 

The compliance time for the 

reinforcement modifications specified 

in this proposed AD for addressing WFD 

was established to ensure that 

discrepant structure is addressed before 

WFD develops in airplanes. Standard 

inspection techniques cannot be relied 

on to detect WFD before it becomes a 

hazard to flight. We will not grant any 

extensions of the compliance time to 

complete any AD-mandated service 

bulletin related to WFD without 

extensive new data that would 

substantiate and clearly warrant such an 

extension. 

Costs of Compliance 

We estimate that this proposed AD 

affects 99 airplanes of U.S. registry. 

We estimate the following costs to 

comply with this proposed AD: 

ESTIMATED COSTS

Action Labor cost Parts cost Cost per product Cost on U.S. 

operators 

Reinforcement modifications ............... Up to 317 work-hours × $85 per hour 

= $26,945.

Up to $41,050 ....... Up to $67,995 ....... Up to $6,731,505. 

We have received no definitive data 

that would enable us to provide cost 

estimates for the on-condition actions 

specified in this proposed AD. 

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. 

This proposed AD is issued in 

accordance with authority delegated by 

the Executive Director, Aircraft 

Certification Service, as authorized by 

FAA Order 8000.51C. In accordance 

with that order, issuance of ADs is 

normally a function of the Compliance 

and Airworthiness Division, but during 

this transition period, the Executive 

Director has delegated the authority to 

issue ADs applicable to transport 

category airplanes to the Director of the 

System Oversight Division. 

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–2017–0812; Product 

Identifier 2016–NM–198–AD. 

(a) Comments Due Date 

We must receive comments by November 

3, 2017. 

(b) Affected ADs 

None. 

(c) Applicability 

This AD applies to the Airbus airplanes 

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

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

all manufacturer serial numbers. 

(1) Model A330–201, –202, –203, –223, and 

–243 airplanes. 

(2) Model A330–223F and –243F airplanes. 

(3) Model A330–301, –302, –303, –321, 

–322, –323, –341, –342, and –343 airplanes. 

(d) Subject 

Air Transport Association (ATA) of 

America Code 53, Fuselage. 

(e) Reason 

This AD was prompted by an evaluation by 

the design approval holder (DAH) indicating 

that certain fuselage structures are subject to 

widespread fatigue damage (WFD). We are 

issuing this AD to prevent crack initiation 

and undetected propagation in the fuselage, 

which could result in reduced structural 

integrity of the airplane. 

(f) Compliance 

Comply with this AD within the 

compliance times specified, unless already 

done. 

(g) Modifications 

Except as specified in paragraphs (i)(1) and 

(i)(2) of this AD, before exceeding the 

applicable total flight cycles or total flight 


asabaliauskas on DSKBBXCHB2PROD with PROPOSALS
43718 Federal Register / Vol. 82, No. 180 / Tuesday, September 19, 2017 / Proposed Rules 

hours structural modification point (SMP) for 

each action, as specified in table 1 to 

paragraph (g) of this AD: Modify the airplane, 

including all applicable related investigative 

actions and corrective actions, based on the 

weight variant (WV) group designations 

specified in table 2 to paragraph (h) of this 

AD, and as specified in table 1 to paragraph 

(g) of this AD, except as specified in 

paragraph (i)(3) of this AD. Do all applicable 

related investigative actions and corrective 

actions before further flight. For the purposes 

of this AD, the short range (SR) and long 

range (LR) SMPs specified in table 1 to 

paragraph (g) of this AD must be used. 

TABLE 1 TO PARAGRAPH (g) OF THIS AD—MODIFICATION

Description of action Applicability SMP SR SMP LR 

Improve circumferential joints at frames (FR) 45 and 54 of the fuselage, in accordance with the Accomplishment Instructions of Airbus Service Bulletin A330-53-3144, Revision 04, dated November 

23, 2015 (‘‘A330–53–3144, R4’’).

Group 32A .................

Group 33A .................

Group 33B .................

32,500 total flight cycles .................................

23,700 total flight cycles or 71,300 total flight 

hours, whichever occurs first.

27,600 total flight cycles or 83,000 total flight 

hours, whichever occurs first.

26,600 flight cycles. 

20,400 total flight cycles 

23,700 total flight cycles. 

Group 33C ................. 23,300 total flight cycles or 70,000 total flight 

hours, whichever occurs first.

20,000 total flight cycles. 

Group 33D ................. 22,700 total flight cycles or 68,300 flight 

hours, whichever occurs first.

19,500 total flight cycles. 

Improve splicing area from FR48 to FR53–2 between stringers 

(STRG) 23 and 26 left hand (LH)/right hand (RH) of the fuselage, 

in accordance with the Accomplishment Instructions of Airbus 

Service Bulletin A330–53–3222, Revision 01, dated March 31, 

2016 (‘‘A330–53–3222, R1’’) (Airbus Modification 204315).

Groups 32A and 32E

Group 33A .................

Group 33B .................

23,100 total flight cycles or 80,900 total flight 

hours, whichever occurs first.

24,200 total flight cycles or 79,100 total flight 

hours, whichever occurs first.

19,700 total flight cycles or 64,300 total flight 

hours, whichever occurs first.

20,900 total flight cycles. 

21,800 total flight cycles. 

17,700 total flight cycles. 

Groups 33C, 33D, and 

33E.

21,600 total flight cycles or 70,600 flight 

hours, whichever occurs first.

19,400 total flight cycles. 

A330–200F ................ 27,400 total flight cycles or 82,200 total flight 

hours, whichever occurs first.

27,400 total flight cycles or 82,200 total 

flight hours, whichever occurs first. 

Reinforce couplings in area FR20—FR25/STRG20 RH—STRG22 

RH of the forward fuselage, in accordance with the Accomplishment Instructions of Airbus Service Bulletin A330-53-3223, Revision 00, dated January 19, 2015 (‘‘A330-53-3223, R0’’).

Groups 32A, 32E, 

33B, 33C, 33D and 

33E.

30,900 total flight cycles ................................. 30,900 total flight cycles. 

Reinforce circumferential joint at FR72 of the fuselage, in accordance with the Accomplishment Instructions of Airbus Service Bulletin A330-53–3224, Revision 01, excluding Appendix 01 and including Appendix 02, dated April 14, 2016 (‘‘A330-53–3224, R1’’).Group 33A ................. 29,700 total flight cycles or 89,600 total flight 

hours, whichever occurs first.

25,500 total flight cycles. 

Reinforce circumferential joint at FR58 of the fuselage, in accordance with the Accomplishment Instructions of Airbus Service Bulletin A330-53–3225, Revision 02, excluding Appendix 01 and including Appendix 02, dated June 8, 2016 (‘‘A330-53–3225, R2’’).Group 33A ................. 16,300 total flight cycles or 49,300 total flight 

hours, whichever occurs first.

13,300 total flight cycles or 90,700 total 

flight hours, whichever occurs first. 

Reinforce circumferential joint between FR53.6—FR53.7 for emergency door TYPE 1 area of the center fuselage, in accordance 

with the Accomplishment Instructions of Airbus Service Bulletin 

A330-53–3226, Revision 02, excluding Appendix 01 and including 

Appendices 02, 03, and 04, dated October 27, 2016 (‘‘A330–53– 

3226, R2’’); or Airbus Service Bulletin A330-53-3273, Revision 

00, dated September 28, 2016 (‘‘A330-53-3273, R0’’).

Group 32A .................

...............................

Groups 33C, 33D and 

33E.

.........................................................................

26,100 total flight cycles or 91,600 total flight 

hours, whichever occurs first.

15,600 total flight cycles or 46,800 total flight 

hours, whichever occurs first.

21,000 total flight cycles. 

12,600 total flight cycles or 84,800 total 

flight hours, whichever occurs first. 

Group 33A ................. 34,400 total flight cycles .................................

....................................................................

27,800 total flight cycles. 

Group 33B ................. 19,900 total flight cycles or 59,800 total flight 

hours, whichever occurs first.

16,100 total flight cycles. 

Group 32E ................. 19,900 total flight cycles or 69,900 total flight 

hours, whichever occurs first.

16,200 total flight cycles. 

Reinforce circumferential joint between FR53.6—FR53.7 LH/RH of 

option emergency door TYPE A area of the center fuselage, in 

accordance with the Accomplishment Instructions of Airbus Service Bulletin A330–53–3236, Revision 02, excluding Appendix 01 

and including Appendices 02 and 03, dated March 23, 2016 

(‘‘A330–53–3236, R2’’).

Group 33A ................. 30,900 total flight cycles or 93,200 total flight 

hours, whichever occurs first.

25,400 total flight cycles. 

Improve fatigue life of internal center fuselage structure on longitudinal beams above the center wing box, in accordance with the 

Accomplishment Instructions of Airbus Service Bulletin A330-53– 

3237, Revision 01, dated February 8, 2016 (‘‘A330-53–3237, R1’’).

Groups 32A, 33A, 

33B, 33C, and 33D.

Group 32A .................

27,300 total flight cycles .................................

38,400 total flight cycles .................................

27,300 total flight cycles. 

38,400 total flight cycles. 

Update lower/lateral frame splicing with corner fitting between 

FR53.3 and FR54 of the center fuselage, in accordance with the 

Accomplishment Instructions of Airbus Service Bulletin A330-53– 

3238, Revision 01, dated October 19, 2015 (‘‘A330-53–3238, 

R1’’).

Group 33A .................

Group 33B .................

Groups 33C and 33D 

28,800 total flight cycles .................................

36,200 total flight cycles .................................

34,700 total flight cycles .................................

28,800 total flight cycles. 

36,200 total flight cycles. 

34,700 total flight cycles. 

Reinforce longitudinal butt joints in section 13, in accordance with 

the Accomplishment Instructions of Airbus Service Bulletin 

A330-53–3239, Revision 01, dated July 4, 2016 (‘‘A330-53–3239, 

R1’’).

A330–200F ................ 15,100 total flight cycles ................................. 15,100 total flight cycles. 

Reinforce circumferential joint at FR31 between STRG 7LH and 

STRG 8RH of forward fuselage, in accordance with the Accomplishment Instructions of Airbus Service Bulletin A330-53–3244, 

Revision 01, dated August 2, 2016 (‘‘A330-53–3244, R1’’).

A330–200F ................ 15,500 total flight cycles or 46,500 total flight 

hours, whichever occurs first.

15,500 total flight cycles or 46,500 total 

flight hours, whichever occurs first. 

Reinforce frame couplings in section 13, 14, and 14A of the forward 

fuselage, in accordance with the Accomplishment Instructions of 

Airbus Service Bulletin A330-53–3248, Revision 02, dated July 

27, 2016 (‘‘A330-53–3248, R2’’).

Group 33A ................. 32,000 total flight cycles ................................. 32,000 total flight cycles. 


asabaliauskas on DSKBBXCHB2PROD with PROPOSALS
Federal Register / Vol. 82, No. 180 / Tuesday, September 19, 2017 / Proposed Rules 43719 

TABLE 1 TO PARAGRAPH (g) OF THIS AD—MODIFICATION—Continued 

Description of action Applicability SMP SR SMP LR 

Reinforce circumferential joint/stringer coupling in area of FR37.1 of 

the forward fuselage, in accordance with the Accomplishment Instructions of Airbus Service Bulletin A330-53–3251, Revision 01, 

dated June 23, 2016 (‘‘A330-53–3251, R1’’).

Group 33C 

Pre-Modification 

46636.

Groups 33C and 33D 

Post-Modification 

46636.

38,200 total flight cycles .................................

30,600 total flight cycles or 99,500 total flight 

hours, whichever occurs first.

32,000 total flight cycles. 

27,600 total flight cycles. 

Group 33E ................. 32,200 total flight cycles ................................. 29,100 total flight cycles. 

Reinforce circumferential joint/stringer coupling in area of FR37.1 of 

the forward fuselage, in accordance with the Accomplishment Instructions of Airbus Service Bulletin A330-53–3252, Revision 01, 

dated June 30, 2016 (‘‘A330-53–3252, R1’’).

Groups 33C and 33D, 

Post-Modification 

46636.

Group 33E .................

30,600 total flight cycles or 99,500 total flight 

hours, whichever occurs first.

32,200 total flight cycles .................................

27,600 total flight cycles. 

29,100 total flight cycles. 

Reinforce frame couplings in rear area of the fuselage, in accordance with the Accomplishment Instructions of Airbus Service Bulletin A330–53–3257, Revision 01, dated March 15, 2016 

(‘‘A330-53–3257, R1’’).

Groups 33A and 33B 24,000 total flight cycles ................................. 24,000 total flight cycles. 

Reinforce corner fittings in section 13 of the forward fuselage, in accordance with the Accomplishment Instructions of Airbus Service 

Bulletin A330-53-3258, Revision 00, dated April 20, 2015 

(‘‘A330-53-3258, R0’’).

Group 32A ................. 31,800 total flight cycles ................................. 31,800 total flight cycles. 

Reinforce circumferential joint at FR58 (aeroplane Post-Modification 

40556/D18255) of the rear fuselage, in accordance with the Accomplishment Instructions of Airbus Service Bulletin A330-53– 

3259, Revision 02, dated July 18, 2016 (‘‘A330-53–3259, R2’’).

Group 32E ................. 18,500 total flight cycles or 65,400 total flight 

hours, whichever occurs first.

14,600 total flight cycles or 95,700 total 

flight hours, whichever occurs first. 

Group 33A ................. 34,800 total flight cycles ................................. 28,400 total flight cycles. 

Group 33B ................. 33,500 total flight cycles ................................. 27,400 total flight cycles. 

Reinforce frames in rear area of the fuselage, in accordance with 

the Accomplishment Instructions of Airbus Service Bulletin 

A330-53–3263, Revision 01, excluding Appendix 01 and including 

Appendix 02, dated December 1, 2015 (‘‘A330-53–3263, R1’’).

Groups 32A, 32E, 

33B, 33C, 33D, and 

33E.

23,300 total flight cycles or 69,700 total flight 

hours, whichever occurs first.

20,800 total flight cycles. 

(h) Weight Variant (WV) Group Designations 

For the purposes of this AD, table 2 to 

paragraph (h) of this AD identifies the WV 

group designations specified in the 

‘‘Applicability’’ column of Table 1 to 

paragraph (g) and Table 3 to paragraph (i) of 

this AD: 

TABLE 2 TO PARAGRAPH (h) OF THIS AD—WV GROUP DESIGNATIONS

Airplane model WV group Weight variants 

A330–200 .................................. Group 32A ........................................................ 020, 021, 022, 023, 024, 025, 026, and 027. 

Group 32E ........................................................ 050, 051, 052, 053, 054, 055, 056, 057, 058, 059, 060, 061, 

062, 063, 064, 080, 081, 082, and 083. 

A330–200F ................................ N/A ................................................................... 000, 001, and 002. 

A330–300 .................................. Group 33A ........................................................ 000, 001, 002, 003, and 004. 

Group 33B ........................................................ 010, 011, 012, 013, and 014. 

Group 33C ........................................................ 020, 024, 025, 026, and 027. 

Group 33D ........................................................ 022. 

Group 33E ........................................................ 030, 031, 032, 033, 034, 035, 039, 050, 051, 052, 053, 054, 

055, 056, 057, 058, 059, 060, 080, 081, 082, and 083. 

(i) Exceptions to Service Information and 

Compliance Times 

(1) Do not do the applicable modifications 

required by paragraph (g) of this AD before 

the applicable times specified in table 3 to 

paragraph (i) of this AD. Where two limits 

(total flight cycles and total flight hours) 

within the same sub-row of the table are 

specified, both times must be exceeded 

before accomplishment of the modification. 

For airplanes already modified before the 

threshold specified in table 3 to paragraph (i) 

of this AD is reached, within 6 months after 

the effective date of this AD, obtain 

instructions for additional maintenance tasks 

(modifications/inspections) from and 

approved by the Manager, International 

Section, Transport Standards Branch, FAA; 

or the European Aviation Safety Agency 

(EASA); or Airbus’s EASA Design 

Organization Approval (DOA), and 

accomplish those tasks within the 

compliance time specified therein. 

(2) For airplanes that have already reached 

or exceeded the SMP threshold(s), as 

specified for each action in table 1 to 

paragraph (g) of this AD, as applicable, 

accomplishment of the modification can be 

deferred for a period not exceeding 12 

months after the effective of this AD; except 

for accomplishment of the modifications 

specified in A330–53–3237, R1, which can be 

deferred for a period not exceeding 15 

months after the effective date of this AD. 

(3) If any service information specified in 

paragraph (g) or (j) of this AD specifies to 

contact Airbus for appropriate action: Before 

further flight, accomplish corrective actions 

in accordance with the procedures specified 

in paragraph (l)(2) of this AD. 


asabaliauskas on DSKBBXCHB2PROD with PROPOSALS
43720 Federal Register / Vol. 82, No. 180 / Tuesday, September 19, 2017 / Proposed Rules 

TABLE 3 TO PARAGRAPH (i) OF THIS AD —COMPLIANCE TIME LOWER THRESHOLD

Airbus Service Bulletin 

(modification) Applicability Modification not before: 

A330–53–3222, R1 ......................... Groups 32A, 32E, 33A, 33C, 33D 

and 33E.

10,000 total flight cycles. 

Group 33B ..................................... 12,000 total flight cycles. 

A330–200F .................................... 8,900 total flight cycles and 26,600 total flight hours. 

A330–53–3224, R1 ......................... Group 33A ..................................... 10,000 total flight cycles and 6,600 total flight hours. 

A330–53–3225, R2 ......................... Group 33A ..................................... 3,900 total flight cycles and 10,200 total flight hours. 

A330–53–3237, R1 ......................... Groups 32A, 33A, 33B, 33C, and 

33D.

3,900 total flight cycles. 

A330–53–3238, R1 ......................... Groups 32A, 33A, 33B, 33C, and 

33D.

9,000 total flight cycles. 

(j) Additional Work for Certain Airplanes 

For airplanes that have been modified 

before the effective date of this AD, in 

accordance with Airbus Service Bulletin 

A330–53–3144, Revision 00, dated August 

23, 2005; Airbus Service Bulletin A330–53– 

3222, Revision 00, dated January 15, 2015; or 

Airbus Service Bulletin A330–53–3237, 

Revision 00, dated January 15, 2015, as 

applicable: Within 12 months after the 

effective date of this AD, accomplish the 

additional work specified in the 

Accomplishment Instructions of Airbus 

Service Bulletin A330–53–3144, Revision 01, 

dated July 25, 2006; A330–53–3222, R1; and 

A330–53–3237, R1; as applicable. 

(k) Credit for Previous Actions 

This paragraph provides credit for 

applicable actions required by paragraph (g) 

of this AD, if those actions were performed 

before the effective date of this AD using the 

applicable service information specified in 

paragraphs (k)(1) through (k)(19) of this AD. 

(1) Airbus Service Bulletin A330–53–3144, 

Revision 01, dated July 25, 2006. 

(2) Airbus Service Bulletin A330–53–3144, 

Revision 02, dated April 20, 2011. 

(3) Airbus Service Bulletin A330–53–3144, 

Revision 03, dated January 15, 2015. 

(4) Airbus Service Bulletin A330–53–3224, 

Revision 00, dated January 16, 2015. 

(5) Airbus Service Bulletin A330–53–3225, 

Revision 00, dated January 16, 2015. 

(6) Airbus Service Bulletin A330–53–3225, 

Revision 01, dated February 26, 2016. 

(7) Airbus Service Bulletin A330–53–3226, 

Revision 00, dated January 15, 2015. 

(8) Airbus Service Bulletin A330–53–3226, 

Revision 01, dated March 3, 2016. 

(9) Airbus Service Bulletin A330–53–3236, 

Revision 00, dated January 15, 2015. 

(10) Airbus Service Bulletin A330–53– 

3236, Revision 01, dated August 24, 2015. 

(11) Airbus Service Bulletin A330–53– 

3238, Revision 00, dated January 15, 2015. 

(12) Airbus Service Bulletin A330–53– 

3239, Revision 00, dated April 20, 2015. 

(13) Airbus Service Bulletin A330–53– 

3244, Revision 00, dated April 7, 2015. 

(14) Airbus Service Bulletin A330–53– 

3251, Revision 00, dated May 13, 2015. 

(15) Airbus Service Bulletin A330–53– 

3252, Revision 00, dated April 10, 2015. 

(16) Airbus Service Bulletin A330–53– 

3257, Revision 00, dated July 21, 2015. 

(17) Airbus Service Bulletin A330–53– 

3259, Revision 00, dated May 11, 2015. 

(18) Airbus Service Bulletin A330–53– 

3259, Revision 01, dated February 26, 2016. 

(19) Airbus Service Bulletin A330–53– 

3263, Revision 00, dated July 21, 2015. 

(l) Other FAA AD Provisions 

The following provisions also apply to this 

AD: 

(1) Alternative Methods of Compliance 

(AMOCs): The Manager, International 

Section, Transport Standards 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 Section, send it 

to the attention of the person identified in 

paragraph (m)(2) of this AD. Information may 

be emailed to: 9-ANM-116-AMOCREQUESTS@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. 

(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 Section, 

Transport Standards Branch, 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 DOAauthorized signature. 

(3) Required for Compliance (RC): Except 

as required by paragraph (i) of this AD: If any 

service information contains procedures or 

tests that are identified as RC, those 

procedures and tests must be done to comply 

with this AD; any procedures or tests that are 

not identified as RC are recommended. Those 

procedures and tests that are not identified 

as RC may be deviated from using accepted 

methods in accordance with the operator’s 

maintenance or inspection program without 

obtaining approval of an AMOC, provided 

the procedures and tests identified as RC can 

be done and the airplane can be put back in 

an airworthy condition. Any substitutions or 

changes to procedures or tests identified as 

RC require approval of an AMOC. 

(m) Related Information 

(1) Refer to Mandatory Continuing 

Airworthiness Information (MCAI) EASA AD 

2016–0207, dated October 19, 2016, 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–2017–0812. 

(2) For more information about this AD, 

contact Vladimir Ulyanov, Aerospace 

Engineer, International Section, Transport 

Standards Branch, FAA, 1601 Lind Avenue 

SW., Renton, WA 98057–3356; telephone 

425–227–1138; fax 425–227–1149. 

(3) For service information identified in 

this AD, contact Airbus SAS, Airworthiness 

Office—EAL, 1 Rond Point Maurice Bellonte, 

31707 Blagnac Cedex, France; telephone +33 

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

airworthiness.A330–A340@airbus.com; 

Internet http://www.airbus.com. You may 

view this service information at the FAA, 

Transport Standards Branch, 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 

September 7, 2017. 

Jeffrey E. Duven, 

Director, System Oversight Division, Aircraft 

Certification Service. 

[FR Doc. 2017–19760 Filed 9–18–17; 8:45 am] 

BILLING CODE 4910–13–P 

DEPARTMENT OF THE TREASURY 

Internal Revenue Service 

26 CFR Parts 1, 5f, and 46 

[REG–125374–16] 

RIN 1545–BN60 

Guidance on the Definition of 

Registered Form 

AGENCY: Internal Revenue Service (IRS), 

Treasury. 

ACTION: Partial withdrawal of notice of 

proposed rulemaking and notice of 

proposed rulemaking. 

SUMMARY: This document contains 

proposed regulations that provide 

guidance on the definitions of 

registration-required obligation and 

registered form, including guidance on 


asabaliauskas on DSKBBXCHB2PROD with PROPOSALS