28152 Federal Register / Vol. 78, No. 93 / Tuesday, May 14, 2013 / Proposed Rules 

List of Subjects in 7 CFR Part 929 

Cranberries, Marketing agreements, 

Reporting and recordkeeping 

requirements. 

For the reasons set forth in the 

preamble, 7 CFR part 929 is proposed to 

be amended as follows: 

PART 929—CRANBERRIES GROWN IN 

THE STATES OF MASSACHUSETTS, 

RHODE ISLAND, CONNECTICUT, NEW 

JERSEY, WISCONSIN, MICHIGAN, 

MINNESOTA, OREGON, 

WASHINGTON, AND LONG ISLAND IN 

THE STATE OF NEW YORK 

■ 1. The authority citation for 7 CFR 

part 929 continues to read as follows: 

Authority: 7 U.S.C. 601–674. 

■ 2. Section 929.149 is amended by 

■ a. Revising paragraph (a); 

■ b. Revising the first sentence in 

paragraph (b); 

■ c. Revising paragraphs (c) and (d), and 

Table 1 to read as follows: 

§ 929.149 Determination of sales history. 

* * * * * 

(a) For each grower with acreage with 

6 or more years of sales history, a new 

sales history shall be computed using an 

average of the highest 4 of the most 

recent 6 years of sales. If the grower has 

acreage with 5 years of sales history and 

such acreage was planted more than 6 

years ago, a new sales history shall be 

computed by averaging the highest 4 of 

the 5 years. 

(b) For growers whose acreage has 5 

years of sales history and was planted 

6 years ago or later, the sales history 

shall be computed by averaging the 

highest 4 of the 5 years and shall be 

adjusted as provided in paragraph (d). 

* * * 

(c) For growers with acreage with no 

sales history or for the first harvest of replanted acres, the sales history will be 

75 barrels per acre for acres planted or 

re-planted 1 year ago and first harvested 

in the current crop year and 156 barrels 

per acre for acres planted or re-planted 

2 years ago and first harvested in the 

current crop year. 

(d) In addition to the sales history 

computed in accordance with 

paragraphs (a) and (b) of this section, 

additional sales history shall be 

assigned to growers with acreage 

planted in the last 6 years. The 

additional sales histories depending on 

the date the acreage is planted are 

shown in Table 1. 

TABLE 1—ADDITIONAL SALES HISTORY

ASSIGNED TO ACREAGE

Date planted 

Additional current 

crop year sales 

history per acre 

6 years ago ..................... 49 

5 years ago ..................... 117 

4 years ago ..................... 157 

3 years ago ..................... 183 

2 years ago ..................... 156 

1 year ago ...................... 75 

* * * * * 

Dated: May 9, 2013. 

David R. Shipman, 

Administrator, Agricultural Marketing 

Service. 

[FR Doc. 2013–11392 Filed 5–13–13; 8:45 am] 

BILLING CODE 3410–02–P 

DEPARTMENT OF TRANSPORTATION 

Federal Aviation Administration 

14 CFR Part 39 

[Docket No. FAA–2013–0416; Directorate 

Identifier 2012–NM–144–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 an 

existing airworthiness directive (AD) 

that applies to certain Airbus Model 

A318–111 and –112 airplanes, Model 

A319 series airplanes, Model A320 

series airplanes, and Model A321 series 

airplanes. The existing AD currently 

requires repetitive inspections of the 

80VU rack lower lateral fittings for 

damage; repetitive inspections of the 

80VU rack lower central support for 

cracking; and corrective action if 

necessary. That existing AD also 

specifies optional terminating action for 

the repetitive inspections. Since we 

issued that AD, we have received 

reports of worn lower lateral fittings of 

the 80VU rack. This proposed AD 

would reduce the inspection 

compliance time, add an inspection of 

the upper fittings and shelves of the 

80VU rack, and add airplanes to the 

applicability. We are proposing this AD 

to detect and correct damage or cracking 

of the 80VU fittings and supports, 

which could lead to possible 

disconnection of the cable harnesses to 

one or more computers and, if occurring 

during a critical phase of flight, could 

result in reduced control of the airplane. 

DATES: We must receive comments on 

this proposed AD by June 28, 2013. 

ADDRESSES: You may send comments by 

any of the following methods: 

• Federal eRulemaking Portal: Go to 

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

instructions for submitting comments. 

• Fax: (202) 493–2251. 

• Mail: U.S. Department of 

Transportation, Docket Operations, M– 

30, West Building Ground Floor, Room 

W12–140, 1200 New Jersey Avenue SE., 

Washington, DC 20590. 

• Hand Delivery: U.S. Department of 

Transportation, Docket Operations, M– 

30, West Building Ground Floor, Room 

W12–140, 1200 New Jersey Avenue SE., 

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

p.m., Monday through Friday, except 

Federal holidays. 

For service information identified in 

this proposed AD, contact Airbus, 

Airworthiness Office—EIAS, 1 Rond 

Point Maurice Bellonte, 31707 Blagnac 

Cedex, France; telephone +33 5 61 93 36 

96; fax +33 5 61 93 44 51; email 

account.airworth-eas@airbus.com; 

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

may review copies of the 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; 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: 

Sanjay Ralhan, Aerospace Engineer, 

International Branch, ANM–116, 

Transport Airplane Directorate, FAA, 

1601 Lind Avenue SW., Renton, WA 

98057–3356; telephone (425) 227 1405; 

fax (425) 227–1149. 

SUPPLEMENTARY INFORMATION: 

Comments Invited 

We invite you to send any written 

relevant data, views, or arguments about 

this proposed AD. Send your comments 

to an address listed under the 

ADDRESSES section. Include ‘‘Docket No. 

FAA–2013–0416; Directorate Identifier 

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Federal Register / Vol. 78, No. 93 / Tuesday, May 14, 2013 / Proposed Rules 28153 

2012–NM–144–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 November 15, 2010, we issued AD 

2010–24–07, Amendment 39–16526 (75 

FR 75878, December 7, 2010). That AD 

required actions intended to address an 

unsafe condition on the products listed 

above. 

Since we issued AD 2010–24–07, 

Amendment 39–16526 (75 FR 75878, 

December 7, 2010), the European 

Aviation Safety Agency (EASA), which 

is the Technical Agent for the Member 

States of the European Community, has 

issued EASA Airworthiness Directive 

2012–0134, dated July 18, 2012 (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: 

Damage to the lower lateral fittings of the 

80VU rack, typically elongated holes, 

migrated bushes, and/or missing bolts have 

been reported on in-service aeroplanes. The 

80VU rack contains computers for flight 

controls, communication and radionavigation. In addition, damage to the lower 

central support fitting (including cracking) 

has been reported. 

Failure of the 80VU fittings, in 

combination with a high load factor or strong 

vibration, could lead to failure of the rack 

structure and/or computers or rupture/ 

disconnection of the cable harnesses to one 

or more computers located in the 80VU rack. 

Even though the computer functions are 

duplicated across other racks, multiple 

system failures or (partial) disconnection of 

systems, if occurring during a critical phase 

of flight, could result in reduced control of 

the aeroplane. 

To address this potential unsafe condition, 

EASA issued AD 2007–0276 to require 

repetitive inspections of the lower lateral 

80VU fittings and the lower central 80VU 

support and, depending on findings, the 

accomplishment of corrective actions. 

[EASA] AD 2007–0276 was revised to 

introduce a reinforced lower central support 

as an optional terminating action for the 

repetitive inspections. 

Since issuance of EASA AD 2007–0276R1 

[which corresponds to FAA AD 2010–24–07, 

Amendment 39–16526 (75 FR 75878, 

December 7, 2010)], and prompted by inservice experience, the previous inspection 

programme has been reassessed. New 

conditions of inspection for a new finding on 

the lower central fitting attachment (crack in 

the lower of the lateral flanges), and a new 

visual inspection of the upper fittings and 

shelves of the 80VU are introduced by this 

inspection programme. In addition, the 

replacement of a cracked lateral fitting or 

central support with a lateral fitting or 

central support having the same part number 

is no longer preferable as corrective action. 

Instead, the installation of the reinforced 

lower central support is now defined as 

optional terminating action for the repetitive 

inspections required by this [EASA] AD. 

For the reasons described above, this 

[EASA] AD supersedes EASA AD 2007– 

0276R1 and requires implementation of an 

amended inspection programme with a 

reduced inspection threshold. 

This proposed AD would add 

airplanes to the applicability including 

Model A318–121 and –122 airplanes. 

Existing AD 2010–24–07, Amendment 

39–16526 (75 FR 75878, December 7, 

2010), exempted airplanes on which 

Airbus Modification 34804 has been 

embodied in production or on which 

Airbus Service Bulletins A320–25–1557 

and A320–53–1215 have been done in 

service. This AD exempts those 

airplanes from the restated paragraphs 

of AD 2010–24–07, which are 

paragraphs (g) and (i) of this proposed 

AD. You may obtain further information 

by examining the MCAI in the AD 

docket. 

Compliance times for the corrective 

actions specified in paragraph (m) of 

this proposed AD range from before 

further flight to within 4,500 flight 

cycles, depending on the condition 

found during the inspection required by 

paragraph (l) of this proposed AD. 

Relevant Service Information 

Airbus has issued Mandatory Service 

Bulletin A320–25A1555, including 

Appendix 01, Revision 03, dated 

February 28, 2012. The actions 

described in this service information are 

intended to correct the unsafe condition 

identified in the MCAI. 

FAA’s Determination and Requirements 

of This Proposed AD 

This product has been approved by 

the aviation authority of another 

country, and is approved for operation 

in the United States. Pursuant to our 

bilateral agreement with the State of 

Design Authority, we have been notified 

of the unsafe condition described in the 

MCAI and service information 

referenced above. We are proposing this 

AD because we evaluated all pertinent 

information and determined an unsafe 

condition exists and is likely to exist or 

develop on other products of the same 

type design. 

Differences Between This Proposed AD 

and the MCAI or Service Information 

This proposed AD differs from the 

MCAI and/or service information as 

follows: 

• Although the MCAI or service 

information allows further flight after 

cracks are found during compliance 

with the required action, this AD 

requires that you do a corrective action 

before further flight. 

• Although Airbus Mandatory Service 

Bulletin A320–25A1555, including 

Appendix 01, Revision 03, dated 

February 28, 2012, specifies to contact 

the manufacturer for instructions to 

repair certain conditions when certain 

kits are available, this proposed AD 

would require contacting the Manager, 

International Branch, ANM–116, 

Transport Airplane Directorate, FAA, 

for instructions when those kits are 

available and doing the repairs. 

Costs of Compliance 

Based on the service information, we 

estimate that this proposed AD would 

affect about 755 products of U.S. 

registry. 

The actions that are required by AD 

2010–24–07, Amendment 39–16526 (75 

FR 75878, December 7, 2010), and 

retained in this proposed AD, take about 

82 work-hours per product, at an 

average labor rate of $85 per work hour. 

Required parts cost about $2,592 per 

product. Based on these figures, the 

estimated cost of the currently required 

actions is $9,562 per product. 

We estimate that it would take about 

5 work-hours per product to comply 

with the new basic requirements of this 

proposed AD. The average labor rate is 

$85 per work-hour. Where the service 

information lists parts costs that are 

covered under warranty, we have 

assumed that there will be no charge for 

these parts. As we do not control 

warranty coverage for affected parties, 

some parties may incur costs higher 

than estimated here. Based on these 

figures, we estimate the cost of the 

proposed AD on U.S. operators to be 

$320,875, or $425 per product. 

In addition, we estimate that any 

necessary follow-on actions would take 

about 189 work-hours and require parts 

costing $7,047, for a cost of $23,112 per 

product. Where the service information 

lists required parts costs that are 

covered under warranty, we have 

assumed that there will be no charge for 

these parts. As we do not control 

warranty coverage for affected parties, 

some parties may incur costs higher 

than estimated here. We have no way of 

determining the number of products 

that may need these actions. 

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28154 Federal Register / Vol. 78, No. 93 / Tuesday, May 14, 2013 / Proposed Rules 

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) 

2010–24–07, Amendment 39–16526 (75 

FR 75878, December 7, 2010), and 

adding the following new AD: 

Airbus: Docket No. FAA–2013–0416; 

Directorate Identifier 2012–NM–144–AD. 

(a) Comments Due Date 

We must receive comments by June 28, 

2013. 

(b) Affected ADs 

This AD supersedes AD 2010–24–07, 

Amendment 39–16526 (75 FR 75878, 

December 7, 2010). 

(c) Applicability 

This AD applies to Airbus Model A318– 

111, –112, –121, and –122 airplanes; Model 

A319–111, –112, –113, –114, –115, –131, 

–132, and –133 airplanes; Model A320–111, 

–211, –212, –214, –231, –232, and –233 

airplanes; and Model A321–111, –112, –131, 

–211, –212, –213, –231, and –232 airplanes; 

certificated in any category; all manufacturer 

serial numbers. 

(d) Subject 

Air Transport Association (ATA) of 

America Code 25, Equipment/Furnishings, 

and Code 53, Fuselage. 

(e) Reason 

This AD was prompted by reports of worn 

lower lateral fittings of the 80VU rack. We are 

issuing this AD to detect and correct damage 

or cracking of the 80VU fittings and supports, 

which could lead to possible disconnection 

of the cable harnesses to one or more 

computers, and if occurring during a critical 

phase of flight, could result in reduced 

control 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 of the 

80VU Rack Lower Lateral Fittings 

This paragraph restates the requirements of 

paragraph (g) of AD 2010–24–07, 

Amendment 39–16526 (75 FR 75878, 

December 7, 2010). Except for Model A318– 

121 and –122 airplanes, and except for 

airplanes on which Airbus Modification 

34804 has been embodied in production or 

on which Airbus Service Bulletins A320–25– 

1557 and A320–53–1215 have been done in 

service, prior to the accumulation of 24,000 

total flight cycles, or within 500 flight cycles 

after January 11, 2011 (the effective date of 

AD 2010–24–07), whichever occurs later: Do 

a special detailed inspection of the 80VU 

rack lower lateral fittings for damage (e.g., 

broken fitting, missing bolts, migrated 

bushings, material burr, or rack in contact 

with the fitting) of the 80VU rack lower 

lateral fittings, in accordance with the 

Accomplishment Instructions of Airbus 

Mandatory Service Bulletin A320–25A1555, 

Revision 02, dated November 5, 2008. Repeat 

the inspection thereafter at the interval 

specified in paragraph (g)(1) or (g)(2) of this 

AD, as applicable. Modifying the 80VU lower 

lateral fittings, in accordance with the 

Accomplishment Instructions of Airbus 

Service Bulletin A320–25–1557, Revision 02, 

dated November 5, 2008, terminates the 

inspection requirements of this paragraph. 

Doing the initial inspection specified in 

paragraph (l) of this AD terminates the 

requirements of this paragraph. 

(1) For airplanes on which the 80VU rack 

lower lateral fittings have not been replaced 

in accordance with the Accomplishment 

Instructions of Airbus Mandatory Service 

Bulletin A320–25A1555, Revision 02, dated 

November 5, 2008: Repeat the inspection 

thereafter at intervals not to exceed 4,500 

flight cycles. 

(2) For airplanes on which the 80VU rack 

lower lateral fittings have been replaced in 

accordance with the Accomplishment 

Instructions of Airbus Mandatory Service 

Bulletin A320–25A1555, Revision 02, dated 

November 5, 2008: Do the next inspection 

within 24,000 flight cycles after doing the 

replacement and repeat the inspection 

thereafter at intervals not to exceed 4,500 

flight cycles. 

(h) Retained Corrective Actions for 

Paragraph (h) of This AD With New 

Corrective Actions 

This paragraph restates the requirements of 

paragraph (h) of AD 2010–24–07, 

Amendment 39–16526 (75 FR 75878, 

December 7, 2010), with new corrective 

actions. If any damage is found during any 

inspection required by paragraph (g) of this 

AD, do all applicable corrective actions 

(inspection and/or repair), in accordance 

with the Accomplishment Instructions and 

timeframes in Airbus Mandatory Service 

Bulletin A320–25A1555, Revision 02, dated 

November 5, 2008; or in accordance with and 

at the time specified in paragraph (q) of this 

AD. As of the effective date of this AD, if any 

damage is found, do all applicable corrective 

actions in accordance with and at the times 

specified in paragraph (q) of this AD. 

(i) Retained Repetitive Inspections of the 

80VU Rack Lower Central Support 

This paragraph restates the requirements of 

paragraph (i) of AD 2010–24–07, Amendment 

39–16526 (75 FR 75878, December 7, 2010). 

Except for airplanes on which Airbus 

Modification 34804 has been embodied in 

production or on which Airbus Service 

Bulletins A320–25–1557 and A320–53–1215 

have been done in service, prior to the 

accumulation of 24,000 total flight cycles, or 

within 500 flight cycles January 11, 2011 (the 

effective date of AD 2010–24–07), whichever 

occurs later: Do a special detailed inspection 

of the 80VU rack lower central support for 

cracking, in accordance with the 

Accomplishment Instructions of Airbus 

Mandatory Service Bulletin A320–25A1555, 

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Revision 02, dated November 5, 2008. Repeat 

the inspection thereafter at the interval 

specified in paragraph (i)(1) or (i)(2) of this 

AD, as applicable. Replacing the pyramid 

fitting on the 80VU rack with a new, 

reinforced fitting, in accordance with the 

Accomplishment Instructions of Airbus 

Service Bulletin A320–53–1215, dated 

November 5, 2008, terminates the inspection 

requirements of this paragraph. Doing the 

initial inspection specified in paragraph (n) 

of this AD terminates the requirements of this 

paragraph. 

(1) For airplanes on which the 80VU rack 

lower central support has not been repaired 

or replaced using Airbus Mandatory Service 

Bulletin A320–25A1555 or Airbus Service 

Bulletin A320–25–1557: Repeat the 

inspection thereafter at the interval specified 

in paragraph (i)(1)(i) or (i)(1)(ii) of this AD, 

as applicable. 

(i) For airplanes on which the lower central 

support has accumulated 30,000 total flight 

cycles or more: At intervals not to exceed 500 

flight cycles. 

(ii) For airplanes on which the lower 

central support has accumulated fewer than 

30,000 total flight cycles: At intervals not to 

exceed 4,500 flight cycles, without exceeding 

30,750 total flight cycles on the support for 

the first repetitive inspection. 

(2) For airplanes on which the 80VU rack 

lower central support has been repaired or 

replaced using Airbus Mandatory Service 

Bulletin A320–25A1555 or Airbus Service 

Bulletin A320–25–1557: Do the next 

inspection within 24,000 flight cycles after 

the repair or replacement and thereafter 

repeat the inspection at the interval specified 

in paragraph (i)(1)(i) or (i)(1)(ii) of this AD, 

as applicable. 

(j) Retained Corrective Actions for 

Paragraph (i) of This AD 

This paragraph restates the requirements of 

paragraph (j) of AD 2010–24–07, Amendment 

39–16526 (75 FR 75878, December 7, 2010). 

If any crack is found during any inspection 

required by paragraph (i) of this AD: Before 

further flight, replace the pyramid fitting on 

the 80VU rack with a new, reinforced fitting, 

in accordance with the Accomplishment 

Instructions of Airbus Service Bulletin A320– 

53–1215, dated November 5, 2008. Doing this 

replacement terminates the inspection 

requirements of paragraph (i) of this AD. 

(k) Retained Optional Terminating Action 

This paragraph restates the requirements of 

paragraph (k) of AD 2010–24–07, 

Amendment 39–16526 (75 FR 75878, 

December 7, 2010). Doing the actions 

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

this AD terminates the repetitive inspections 

required by this AD. 

(1) Replacing the pyramid fitting on the 

80VU rack with a new, reinforced fitting, in 

accordance with the Accomplishment 

Instructions of Airbus Service Bulletin A320– 

53–1215, dated November 5, 2008. 

(2) Modifying the 80VU lower lateral 

fittings, in accordance with Airbus Service 

Bulletin A320–25–1557, Revision 02, dated 

November 5, 2008. 

(l) New Requirement of This AD: Repetitive 

Inspection of Lower Lateral Support Fittings 

Except for airplanes on which Airbus 

Modification 34804 has been embodied in 

production, or on which the 80VU rack lower 

lateral support has been modified, as 

specified in the Accomplishment 

Instructions of Airbus Mandatory Service 

Bulletin A320–25–1557, dated June 14, 2007; 

Revision 01, dated February 7, 2008; or 

Revision 02, dated November 5, 2008: At the 

latest of the applicable times specified in 

paragraphs (l)(1) through (l)(4) of this AD, do 

a special detailed (borescope) inspection of 

the 80VU rack lower lateral fittings for 

damage (e.g., broken fitting, missing bolts, 

migrated bushings, material burr, or rack in 

contact with the fitting) of the 80VU rack 

lower lateral fittings, in accordance with the 

Accomplishment Instructions of Airbus 

Mandatory Service Bulletin A320–25A1555, 

Revision 03, dated February 28, 2012. Repeat 

the inspection thereafter at intervals not to 

exceed 500 flight cycles until the terminating 

action specified in paragraph (k) of this AD 

is done. Doing the initial inspection specified 

in this paragraph terminates the requirements 

of paragraph (g) of this AD. 

(1) Before the accumulation of 20,000 total 

flight cycles from the airplane first flight, or 

within 750 flight cycles after the effective 

date of this AD, whichever occurs later, 

without exceeding 24,000 total flight cycles. 

(2) Within 20,000 flight cycles after the 

most recent repair or replacement of the 

80VU rack lower lateral fittings was done, as 

specified in the Accomplishment 

Instructions of Airbus Mandatory Service 

Bulletin A320–25A1555, dated June 24, 2007; 

Revision 01, dated February 18, 2008; or 

Revision 02, dated November 5, 2008. 

(3) Within 500 flight cycles after the 

effective date of this AD, without exceeding 

4,500 flight cycles after the most recent 

inspection of the 80VU rack lower lateral 

fittings was done, as specified in the 

Accomplishment Instructions of Airbus 

Mandatory Service Bulletin A320–25A1555, 

dated June 14, 2007; Revision 01, dated 

February 18, 2008; or Revision 02, dated 

November 5, 2008. 

(4) Within 500 flight cycles after the 

effective date of this AD. 

(m) New Requirement of This AD: Corrective 

Action for Damage of Lower Lateral Support 

Fittings 

If any damage is found during any 

inspection required by paragraph (l) of this 

AD: At the applicable time given in 

paragraph E. (2), ‘‘Accomplishment 

Timescale,’’ in Airbus Mandatory Service 

Bulletin A320–25A1555, Revision 03, dated 

February 28, 2012, accomplish the applicable 

corrective actions, in accordance with the 

Accomplishment Instructions of Airbus 

Mandatory Service Bulletin A320–25A1555, 

Revision 03, dated February 28, 2012; except 

where this service information specifies to 

contact Airbus for further instructions, before 

further flight contact either the Manager, 

International Branch, ANM–116, Transport 

Airplane Directorate, FAA; or the European 

Aviation Safety Agency (EASA) (or its 

delegated agent) for instructions; and do 

those instructions. 

(n) New Requirement of This AD: Repetitive 

Inspection on Lower Central Support 

Except for airplanes on which Airbus 

Modification 34804 has been embodied in 

production, or on which the 80VU rack lower 

central support has been modified, as 

specified in the Accomplishment 

Instructions of Airbus Service Bulletin A320– 

53–1215, dated November 5, 2008: At the 

latest of the applicable times specified in 

paragraphs (n)(1) through (n)(6) of this AD, 

do a special detailed (borescope) inspection 

of the 80VU rack lower central support for 

cracking, in accordance with the 

Accomplishment Instructions of Airbus 

Mandatory Service Bulletin A320–25A1555, 

Revision 03, dated February 28, 2012. Repeat 

the inspection thereafter at intervals not to 

exceed 500 flight cycles until the terminating 

action specified in paragraph (k) of this AD 

is done. Doing the initial inspection specified 

in this paragraph terminates the requirements 

of paragraph (i) of this AD. 

(1) Before the accumulation of 20,000 total 

flight cycles from the airplane first flight, or 

within 750 flight cycles after the effective 

date of this AD, whichever occurs later, 

without exceeding 24,000 total flight cycles. 

(2) Within 20,000 flight cycles after the 

most recent repair or replacement of the 

80VU rack lower central support was done, 

as specified in the Accomplishment 

Instructions of Airbus Mandatory Service 

Bulletin A320–25A1555, dated June 14, 2007; 

Revision 01, dated February 18, 2008; or 

Revision 02, dated November 5, 2008. 

(3) Within 20,000 flight cycles after 

modification of the 80VU rack lower central 

support was done, as specified in the 

Accomplishment Instructions of Airbus 

Service Bulletin A320–25–1557, dated June 

14, 2007; or Revision 01, dated February 07, 

2008. 

(4) For airplanes on which, as of the 

effective date of this AD, the 80VU rack 

lower central support has accumulated fewer 

than 30,000 total flight cycles: Within 500 

flight cycles after the effective date of this 

AD, without exceeding 4,500 flight cycles 

after the most recent inspection of the 80VU 

rack lower central support was done, as 

specified in the Accomplishment 

Instructions of Airbus Mandatory Service 

Bulletin A320–25A1555, dated June 24, 2007; 

Revision 01, dated February 18, 2008; or 

Revision 02, dated November 5, 2008. 

(5) For airplanes on which, as of the 

effective date of this AD, the 80VU rack 

lower central support has accumulated 

30,000 total flight cycles or more: Within 500 

flight cycles after the most recent inspection 

of the 80VU rack lower central support was 

done, in accordance with the 

Accomplishment Instructions of Airbus 

Mandatory Service Bulletin A320–25A1555, 

dated June 14, 2007; Revision 01, dated 

February 18, 2008; or Revision 02, dated 

November 5, 2008. 

(6) Within 500 flight cycles after the 

effective date of this AD. 

(o) New Requirement of this AD: Corrective 

Action for Damage to Lower Central Support 

If any cracking is found during any 

inspection required by paragraph (n) of this 

AD: Before further flight do the actions in 

paragraph (o)(1) or (o)(2) of this AD. 

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28156 Federal Register / Vol. 78, No. 93 / Tuesday, May 14, 2013 / Proposed Rules 

(1) If kits 25A1555A01 thru A05 are 

available, contact the Manager, International 

Branch, ANM–116, Transport Airplane 

Directorate, FAA for instructions, and do the 

repair. 

(2) Do the actions specified in paragraph 

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

(p) New Requirement of this AD: Repetitive 

Inspection of Upper Fittings and Shelves 

Concurrently with each special detailed 

inspection required by paragraphs (m) and 

(o) of this AD: Do a general visual inspection 

for damage (cracking or deformation) of the 

upper fittings and shelves of the 80VU rack, 

in accordance with the Accomplishment 

Instructions of Airbus Mandatory Service 

Bulletin A320–25A1555, Revision 03, dated 

February 28, 2012. If any damage is found: 

Before further flight, repair the damage using 

a method approved by either the Manager, 

International Branch, ANM–116, Transport 

Airplane Directorate, FAA; or EASA (or its 

delegated agent). 

(q) New Requirement of This AD: Corrective 

Action for Previous Findings 

For airplanes that have been inspected 

before the effective date of this AD as 

specified in Airbus Service Bulletin A320– 

25A1555, dated June 14, 2007; Airbus 

Mandatory Service Bulletin A320–25A1555, 

Revision 01, dated February 18, 2008; or 

Airbus Mandatory Service Bulletin A320– 

25A1555, Revision 02, dated November 5, 

2008; and on which damage of the fittings 

was found, except for airplanes specified in 

paragraph (q)(1) or (q)(2) of this AD: At the 

applicable time given in paragraph E.(2)., 

‘‘Accomplishment Timescale,’’ of Airbus 

Mandatory Service Bulletin A320–25A1555, 

Revision 03, dated February 28, 2012, 

accomplish the applicable corrective actions, 

in accordance with the Accomplishment 

Instructions of Airbus Mandatory Service 

Bulletin A320–25A1555, Revision 03, dated 

February 28, 2012, except where this service 

information specifies to contact Airbus for 

further instructions, before further flight, 

contact either the Manager, International 

Branch, ANM–116, Transport Airplane 

Directorate, FAA; or EASA (or its delegated 

agent) for instructions; and follow those 

instructions. Accomplishing the actions 

required by this paragraph terminates the 

requirements of paragraph (h) of this AD. 

(1) Airplanes on which Airbus 

Modification 34804 has been embodied in 

production. 

(2) Airplanes on which the terminating 

action specified in paragraph (k) of this AD 

has been done. 

(r) Credit for Previous Actions 

This paragraph restates the credit given in 

paragraph (l) of AD 2010–24–07, Amendment 

39–16526 (75 FR 75878, December 7, 2010). 

(1) This paragraph provides credit for 

actions required by paragraphs (g), (h), and 

(i) of this AD, if those actions were performed 

before January 11, 2011 (the effective date of 

AD 2010–24–07, Amendment 39–16526 (75 

FR 75878, December 7, 2010)), using the 

service bulletins specified in paragraph 

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

(i) Airbus Mandatory Service Bulletin 

A320–25A1555, Revision 01, dated February 

18, 2008. 

(ii) Airbus Service Bulletin A320– 

25A1555, dated June 14, 2007. 

(2) This paragraph provides credit for 

actions required by paragraphs (g) and (k)(2) 

of this AD, if those actions were performed 

before January 11, 2011 (the effective date of 

AD 2010–24–07, Amendment 39–16526 (75 

FR 75878, December 7, 2010)), using the 

service bulletins specified in paragraph 

(r)(2)(i) or (r)(1)(ii) of this AD. 

(i) Airbus Service Bulletin A320–25–1557, 

dated June 14, 2007. 

(ii) Airbus Service Bulletin A320–25–1557, 

Revision 01, dated February 7, 2008. 

(s) Other FAA AD Provisions 

The following provisions also apply to this 

AD: 

(1) Alternative Methods of Compliance 

(AMOCs): The Manager, ANM–116, 

International Branch, Transport Airplane 

Directorate, FAA, has the authority to 

approve AMOCs for this AD, if requested 

using the procedures found in 14 CFR 39.19. 

In accordance with 14 CFR 39.19, send your 

request to your principal inspector or local 

Flight Standards District Office, as 

appropriate. If sending information directly 

to the International Branch, send it to ATTN: 

Sanjay Ralhan, Aerospace Engineer, 

International Branch, ANM–116, Transport 

Airplane Directorate, FAA, 1601 Lind 

Avenue SW., Renton, WA 98057–3356; 

telephone (425) 227 1405; fax (425) 227– 

1149. Information may be emailed to: 9- 

ANM-116-AMOC-REQUESTS@faa.gov. 

Before using any approved AMOC, notify 

your appropriate principal inspector, or 

lacking a principal inspector, the manager of 

the local flight standards district office/ 

certificate holding district office. The AMOC 

approval letter must specifically reference 

this AD. AMOCs approved previously in 

accordance with AD 2010–24–07, 

Amendment 39–16526 (75 FR 75878, 

December 7, 2010), are approved as AMOCs 

for the corresponding provisions of this AD. 

(2) Airworthy Product: For any requirement 

in this AD to obtain corrective actions from 

a manufacturer or other source, use these 

actions if they are FAA-approved. Corrective 

actions are considered FAA-approved if they 

are approved by the State of Design Authority 

(or their delegated agent). You are required 

to assure the product is airworthy before it 

is returned to service. 

(t) Related Information 

(1) Refer to Mandatory Continuing 

Airworthiness Information EASA 

Airworthiness Directive 2012–0134, dated 

July 18, 2012, and the service information 

listed in paragraphs (t)(1)(i) through (t)(1)(iv) 

of this AD; for related information. 

(i) Airbus Service Bulletin A320–53–1215, 

dated November 05, 2008. 

(ii) Airbus Mandatory Service Bulletin 

A320–25A1555, Revision 02, dated 

November 5, 2008. 

(iii) Airbus Mandatory Service Bulletin 

A320–25A1555, Revision 03, dated February 

28, 2012. 

(iv) Airbus Service Bulletin A320–25– 

1557, Revision 02, dated November 5, 2008. 

(2) For service information identified in 

this AD, contact Airbus, Airworthiness 

Office—EIAS, 1 Rond Point Maurice 

Bellonte, 31707 Blagnac Cedex, France; 

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

93 44 51; email account.airwortheas@airbus.com; Internet http:// 

www.airbus.com. You may review copies of 

the 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. 

Issued in Renton, Washington, on May 6, 

2013. 

Ali Bahrami, 

Manager, Transport Airplane Directorate, 

Aircraft Certification Service. 

[FR Doc. 2013–11381 Filed 5–13–13; 8:45 am] 

BILLING CODE 4910–13–P 

DEPARTMENT OF TRANSPORTATION 

Federal Aviation Administration 

14 CFR Part 39 

[Docket No. FAA–2013–0419; Directorate 

Identifier 2012–NM–129–AD] 

RIN 2120–AA64 

Airworthiness Directives; Bombardier, 

Inc. Airplanes 

AGENCY: Federal Aviation 

Administration (FAA), DOT. 

ACTION: Notice of proposed rulemaking 

(NPRM). 

SUMMARY: We propose to adopt a new 

airworthiness directive (AD) for certain 

Bombardier, Inc. Model DHC–8–400 

series airplanes. This proposed AD was 

prompted by reports of excessive wear 

on the lower latch surface of the main 

landing gear (MLG) up-lock hook. This 

proposed AD would require revising the 

maintenance program. We are proposing 

this AD to detect and correct up-lock 

hooks worn beyond the wear limit, 

which could prevent the successful 

extension of the MLG using the primary 

landing gear extension system, which in 

combination with an alternate extension 

system failure could result in the 

inability to extend the MLG. 

DATES: We must receive comments on 

this proposed AD by June 28, 2013. 

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. 

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