Federal Register / Vol. 75, No. 149 / Wednesday, August 4, 2010 / Proposed Rules 46873 

done by inserting a copy of this AD into the 

AFM. 

‘‘Prior to descent in visible moisture and 

TAT less than 10 °C, including SAT less than 

¥40 °C, nacelle anti-ice switch must be in 

the ON position. At or below 22,000 ft, wing 

anti-ice selector must be in the ON position.’’ 

Note 1: When a statement identical to that 

in paragraph (g) of this AD has been included 

in the general revisions of the AFM, the 

general revisions may be inserted into the 

AFM, and the copy of this AD may be 

removed from the AFM. 

Special Flight Permits 

(h) Special flight permits, as described in 

Section 21.197 and Section 21.199 of the 

Federal Aviation Regulations (14 CFR 21.197 

and 21.199), may be issued to operate the 

airplane to a location where the requirements 

of this AD can be accomplished provided the 

operational requirements defined in the 

Limitations Section of the AFM are used if 

icing is encountered. 

Alternative Methods of Compliance 

(AMOCs) 

(i)(1) The Manager, Seattle Aircraft 

Certification Office (ACO), FAA, has the 

authority to approve AMOCs for this AD, if 

requested using the procedures found in 14 

CFR 39.19. Send information to Attn: 

Margaret Langsted, Aerospace Engineer, 

Propulsion Branch, ANM–140S, FAA, Seattle 

Aircraft Certification Office, 1601 Lind 

Avenue, SW., Renton, Washington 98057– 

3356; telephone (425) 917–6500; fax (425) 

917–6590. Information may be e-mailed to: 9- 

ANM-Seattle-ACO-AMOC-Requests@faa.gov. 

(2) To request a different method of 

compliance or a different compliance time 

for this AD, follow the procedures in 14 CFR 

39.19. Before using any approved AMOC on 

any airplane to which the AMOC applies, 

notify your principal maintenance inspector 

(PMI) or principal avionics inspector (PAI), 

as appropriate, or lacking a principal 

inspector, your local Flight Standards District 

Office. The AMOC approval letter must 

specifically reference this AD. 

Issued in Renton, Washington, on July 27, 

2010. 

Ali Bahrami, 

Manager, Transport Airplane Directorate, 

Aircraft Certification Service. 

[FR Doc. 2010–19154 Filed 8–3–10; 8:45 am] 

BILLING CODE 4910–13–P 

DEPARTMENT OF TRANSPORTATION 

Federal Aviation Administration 

14 CFR Part 39 

[Docket No. FAA–2008–0670; Directorate 

Identifier 2007–NM–339–AD] 

RIN 2120–AA64 

Airworthiness Directives; Airbus Model 

A318–111 and A318–112 Airplanes and 

Model A319, A320, and A321 Series 

Airplanes 

AGENCY: Federal Aviation 

Administration (FAA), DOT. 

ACTION: Supplemental notice of 

proposed rulemaking (NPRM); 

reopening of comment period. 

SUMMARY: We are revising an earlier 

NPRM for the products listed above. 

This action revises the earlier NPRM by 

expanding the scope. This proposed AD 

results from mandatory continuing 

airworthiness information (MCAI) 

originated by an aviation authority of 

another country to identify and correct 

an unsafe condition on an aviation 

product. The MCAI describes the unsafe 

condition as: 

Damage to the lower lateral fittings of the 

80VU rack, typically elongated holes, 

migrated bushes [bushings], and/or missing 

bolts have been reported in-service. In 

addition damage to the lower central support 

fitting (including cracking) has been 

reported. 

In the worst case scenario a complete 

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. This rack 

contains computers for Flight Controls, 

Communication and Radio-navigation. These 

functions are duplicated across other racks 

but during critical phases of flight the 

multiple system failures/re-configuration 

may constitute an unsafe condition. 

* * * * * 

The proposed AD would require actions 

that are intended to address the unsafe 

condition described in the MCAI. 

DATES: We must receive comments on 

this proposed AD by August 30, 2010. 

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 

W12–40, 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—EAS, 1 Rond 

Point Maurice Bellonte, 31707 Blagnac 

Cedex, France; telephone +33 5 61 93 36 

96; fax +33 5 61 93 44 51; e-mail: 

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, Washington. 

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: Tim 

Dulin, Aerospace Engineer, 

International Branch, ANM–116, 

Transport Airplane Directorate, FAA, 

1601 Lind Avenue, SW., Renton, 

Washington 98057–3356; telephone 

(425) 227–2141; 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–2008–0670; Directorate Identifier 

2007–NM–339–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. 


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46874 Federal Register / Vol. 75, No. 149 / Wednesday, August 4, 2010 / Proposed Rules 

Discussion 

We proposed to amend 14 CFR part 

39 with an earlier NPRM for the 

specified products, which was 

published in the Federal Register on 

June 24, 2008 (73 FR 35601). That 

earlier NPRM proposed to require 

actions intended to address the unsafe 

condition for the products listed above. 

Since that NPRM was issued, the 

European Aviation Safety Agency 

(EASA), which is the Technical Agent 

for the Member States of the European 

Community, has issued EASA 

Airworthiness Directive 2007–0276R1, 

dated March 18, 2010 (corrected April 

12, 2010) (referred to after this as ‘‘the 

MCAI’’), to revise EASA AD 2007–0276, 

dated October 26, 2007, which we 

referred to in the NPRM. The MCAI 

adds an optional terminating action to 

the repetitive inspections. The MCAI 

states: 

Damage to the lower lateral fittings of the 

80VU rack, typically elongated holes, 

migrated bushes [bushings], and/or missing 

bolts have been reported in-service. In 

addition damage to the lower central support 

fitting (including cracking) has been 

reported. 

In the worst case scenario a complete 

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. This rack 

contains computers for Flight Controls, 

Communication and Radio-navigation. These 

functions are duplicated across other racks 

but during critical phases of flight the 

multiple system failures/re-configuration 

may constitute an unsafe condition. 

For the reasons described above, EASA AD 

2007–0276 was issued to require repetitive 

[detailed] inspection of the lower lateral 

80VU fittings for damage and [repetitive 

detailed] inspection of the lower central 

80VU support for damage and cracking, and 

the accomplishment of associated corrective 

actions, depending on findings. 

Since AD 2007–0276 was issued, Airbus 

introduced a new reinforced lower central 

support for the 80VU. 

This [EASA] AD has been revised to 

introduce the new reinforced lower central 

support as an optional terminating action to 

the repetitive inspections. 

* * * * * 

The associated corrective actions 

include repair or replacement of the 

lower lateral fittings and/or replacement 

of the lower central support. Modifying 

the 80VU lower lateral fittings (the 

modification includes replacing the 

80VU lower lateral fittings) eliminates 

the need for the repetitive inspection of 

the lower lateral fittings. Replacing the 

80VU lower central support (i.e., 

replacing the pyramid fitting on the 

80VU rack with a new, reinforced 

fitting) eliminates the need for the 

repetitive inspection of the lower 

central support. You may obtain further 

information by examining the MCAI in 

the AD docket. 

Also, we have determined that for any 

cracking found during an inspection 

specified in paragraph (i) of this 

supplemental NPRM (referred to as 

paragraph (f)(3) in the NPRM), the 

corrective action specified in paragraph 

(j) of this supplemental NPRM (referred 

to as paragraph (f)(4) in the NPRM) must 

be done before further flight. Our policy 

specifies the requirement to repair 

known cracks before further flight 

(though we might make exceptions to 

this policy in certain cases of unusual 

need, as discussed below). This policy 

is based on the fact that such damaged 

airplanes do not conform to the FAAcertificated type design and, therefore, 

are not airworthy until a properly 

approved repair is made. We consider 

the compliance times in this AD to be 

adequate to allow operators to acquire 

parts to have on hand in the event that 

a crack is detected during inspection. 

Therefore, we have determined that, due 

to the safety implications and 

consequences associated with such 

cracking, any subject 80VU rack lower 

central support that is found to be 

cracked must be replaced or modified 

before further flight. 

Also, since the NPRM was issued, the 

AD format has been revised, and certain 

paragraphs have been rearranged. As a 

result, the corresponding paragraph 

identifiers have changed in this 

supplemental NPRM. 

Comments 

We have considered the following 

comments received on the earlier 

NPRM. 

Requests To Include Optional 

Terminating Action 

Northwest Airlines, and Air Transport 

Association (ATA) on behalf of its 

members United Airlines and US 

Airways, request that we refer to a new 

Airbus service bulletin under 

development that provides a permanent 

terminating action for the central 

support fitting. United points out that 

the terminating action is preferable 

because the inspection proposed in the 

NPRM is intrusive to aircraft systems 

and very time consuming. 

We agree with the commenters’ 

request to refer to the new Airbus 

service information as the appropriate 

source of service information for 

modification of the central support. 

Since issuance of the NPRM, Airbus has 

issued Service Bulletin A320–53–1215, 

dated November 5, 2008. That service 

bulletin describes procedures for 

replacing the lower central support of 

the 80VU rack with a new, reinforced 

support. We have added paragraph (k) 

to this supplemental NPRM to specify 

that doing this replacement terminates 

the requirements of paragraphs (g) and 

(i) of this AD. We have also revised 

paragraph (d) of this supplemental 

NPRM to include reference to the ATA 

Code 53: Fuselage, which is the subject 

of Airbus Service Bulletin A320–53– 

1215, dated November 5, 2008. 

Explanation of Additional Revised 

Service Information 

Since we issued the NPRM, Airbus 

has issued Mandatory Service Bulletin 

A320–25A1555, Revision 01, including 

Appendix 1, dated February 18, 2008; 

and Mandatory Service Bulletin A320– 

25A1555, Revision 02, including 

Appendix 1, dated November 5, 2008. 

Airbus has also issued Service Bulletin 

A320–25–1557, Revision 01, dated 

February 7, 2008; and Service Bulletin 

A320–25–1557, Revision 02, dated 

November 5, 2008. (We referred to 

Airbus Service Bulletins A320–25A1555 

and A320–25–1557, both dated June 14, 

2007, in the NPRM as the appropriate 

source of service information for doing 

the proposed actions.) Airbus issued 

Revision 01 of those service bulletins to 

include minor improvements in the 

procedures. Airbus issued Revision 02 

of those service bulletins to include a 

reference to the terminating action 

specified in Airbus Service Bulletin 

A320–53–1215, dated November 5, 

2008. 

No additional work is necessary for 

airplanes on which any revision of these 

service bulletins has been accomplished 

before the effective date of this AD; 

therefore, we have revised paragraphs 

(g) and (n) of this supplemental NPRM 

to refer to Revision 02 of Airbus Service 

Bulletins A320–25A1555 and A320–25– 

1557. We have also revised paragraphs 

(h) and (i) of this supplemental NPRM 

to refer to Revision 02 of Airbus 

Mandatory Service Bulletin A320– 

25A1555. We have also revised this 

supplemental NPRM to include a new 

paragraph (l) to give credit for actions 

accomplished before the effective date 

of this AD in accordance with the 

Airbus service bulletins listed in Table 

1 of this AD. 

Clarification of Repetitive Interval 

We have revised the repetitive 

interval specified in paragraph (g)(2) of 

this supplemental NPRM (referred to as 

paragraph (f)(1)(i) in the NRPM) to 

specify that the next inspection must be 

done within 24,000 flight cycles after 

doing the replacement and thereafter the 


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Federal Register / Vol. 75, No. 149 / Wednesday, August 4, 2010 / Proposed Rules 46875 

inspection must be done at intervals not 

to exceed 4,500 flight cycles. Paragraph 

(f)(1)(ii) of the NPRM specified a 

repetitive interval of 24,000 flight cycles 

for airplanes on which the repair 

(replacement) had been done. However, 

after exceeding 24,000 flight cycles 

since the replacement, the inspections 

must be done at intervals not to exceed 

4,500 flight cycles in order to 

adequately address the identified unsafe 

condition. 

We have also revised the repetitive 

interval specified in paragraph (i)(2) of 

this supplemental NPRM (referred to as 

paragraph (f)(3)(ii) in the NRPM) to 

specify that the next inspection must be 

done within 24,000 flight cycles after 

doing the repair or replacement and 

thereafter the inspection must be done 

at the applicable intervals specified in 

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

Paragraph (f)(3)(ii) of the NPRM 

specified a repetitive interval of 24,000 

flight cycles for airplanes on which the 

repair or replacement had been done. 

However, after exceeding 24,000 flight 

cycles since the repair or replacement, 

the inspections must be done within the 

applicable intervals specified in 

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

in order to address the identified unsafe 

condition. 

We have also revised paragraphs 

(i)(1)(i) and (i)(1)(ii) of this AD (referred 

to as paragraphs (f)(3)(i)(A) and 

(f)(3)(i)(B) of the NPRM) by removing 

the phrase ‘‘as of the effective date of the 

AD.’’ The repetitive intervals specified 

in those paragraphs are not dependent 

on how many flight cycles the support 

has accumulated as of the effective date 

of the AD, e.g., for a lower central 

support that has accumulated 23,000 

total flight cycles (at the time the 

inspection specified in paragraph (i) is 

done), the inspection should be 

repeated at intervals not to exceed 4,500 

flight cycles until the lower central 

support has accumulated 30,000 total 

flight cycles and then the inspection 

should be repeated at intervals not to 

exceed 500 flight cycles. 

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. 

Certain changes described above 

expand the scope of the earlier NPRM. 

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 proposed AD. 

Differences Between This AD and the 

MCAI or Service Information 

We have reviewed the MCAI and 

related service information and, in 

general, agree with their substance. But 

we might have found it necessary to use 

different words from those in the MCAI 

to ensure the AD is clear for U.S. 

operators and is enforceable. In making 

these changes, we do not intend to differ 

substantively from the information 

provided in the MCAI and related 

service information. 

We might also have proposed 

different actions in this AD from those 

in the MCAI in order to follow FAA 

policies. Any such differences are 

highlighted in a Note within the 

proposed AD. 

Costs of Compliance 

Based on the service information, we 

estimate that this proposed AD would 

affect about 678 products of U.S. 

registry. We also estimate that it would 

take about 82 work-hours per product to 

comply with the basic requirements of 

this proposed AD. The average labor 

rate is $85 per work-hour. Required 

parts would cost about $2,592 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 costs. 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 

$6,483,036, or $9,562 per product. 

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); and 

3. 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 adding 

the following new AD: 

Airbus: Docket No. FAA–2008–0670; 

Directorate Identifier 2007–NM–339–AD. 

Comments Due Date 

(a) We must receive comments by August 

30, 2010. 

Affected ADs 

(b) None. 

Applicability 

(c) This AD applies to Airbus Model A318– 

111, A318–112, A319–111, A319–112, A319– 

113, A319–114, A319–115, A319–131, A319– 


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46876 Federal Register / Vol. 75, No. 149 / Wednesday, August 4, 2010 / Proposed Rules 

132, A319–133, A320–111, A320–211, A320– 

212, A320–214, A320–231, A320–232, A320– 

233, A321–111, A321–112, A321–131, A321– 

211, A321–212, A321–213, A321–231, and 

A321–232 airplanes, certificated in any 

category, all manufacturer serial numbers, 

except 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. 

Subject 

(d) Air Transport Association (ATA) of 

America Code 25: Equipment/Furnishings, 

and Code 53: Fuselage. 

Reason 

(e) The mandatory continuing 

airworthiness information (MCAI) states: 

Damage to the lower lateral fittings of the 

80VU rack, typically elongated holes, 

migrated bushes [bushings], and/or missing 

bolts have been reported in-service. In 

addition damage to the lower central support 

fitting (including cracking) has been 

reported. 

In the worst case scenario a complete 

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. This rack 

contains computers for Flight Controls, 

Communication and Radio-navigation. These 

functions are duplicated across other racks 

but during critical phases of flight the 

multiple system failures/re-configuration 

may constitute an unsafe condition. 

* * * * * 

Compliance 

(f) You are responsible for having the 

actions required by this AD performed within 

the compliance times specified, unless the 

actions have already been done. 

Repetitive Inspections of the 80V Rack 

Lower Lateral Fittings 

(g) Prior to the accumulation of 24,000 total 

flight cycles, or within 500 flight cycles after 

the effective date of this AD, 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. 

(1) For airplanes on which the 80VU rack 

lower lateral fittings have not been replaced 

in accordance with the Airbus Mandatory 

Service Bulletin A320–25A1555: 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 Airbus Mandatory Service 

Bulletin A320–25A1555: 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) 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 given in Airbus Mandatory 

Service Bulletin A320–25A1555, Revision 02, 

dated November 5, 2008. 

Repetitive Inspections of the 80V Rack 

Lower Central Support 

(i) Prior to the accumulation of 24,000 total 

flight cycles, or within 500 flight cycles after 

the effective date of this AD, 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, 

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. 

(1) For airplanes on which the 80VU rack 

lower central support has not been repaired 

or replaced in accordance with 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 less 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 in accordance with 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) 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. 

Optional Terminating Action 

(k) Doing the actions specified in 

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

terminates the requirements of paragraphs (g) 

and (i) of 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. 

Credit Service Bulletins 

(l) Actions done before the effective date of 

this AD in accordance with the service 

information identified in Table 1 of this AD 

are acceptable for compliance with the 

corresponding requirements of this AD. 

TABLE 1—PREVIOUS REVISIONS OF SERVICE INFORMATION

Service information Revision level Date 

Airbus Mandatory Service Bulletin A320–25A1555 ................ 01 ............................................................................................ February 18, 2008. 

Airbus Service Bulletin A320–25A1555 .................................. Original ................................................................................... June 14, 2007. 

Airbus Service Bulletin A320–25–1557 .................................. Original ................................................................................... June 14, 2007. 

Airbus Service Bulletin A320–25–1557 .................................. 01 ............................................................................................ February 7, 2008. 

FAA AD Differences 

Note 1: This AD differs from the MCAI 

and/or service information as follows: 

(1) Although the MCAI or service 

information allows further flight after cracks 

are found during compliance with the 

required action, (j) of this AD requires that 

you do a corrective action before further 

flight. 

(2) Although the MCAI specifies doing a 

repair or replacement and repetitive 

inspections after the repair or replacement is 

done if cracking is found in the 80VU rack 

lower central support, paragraph (j) of this 

AD requires that you perform a replacement, 

which eliminates the need for further 

repetitive inspections of the part. 


jdjones on DSK8KYBLC1PROD with PROPOSALS-1
Federal Register / Vol. 75, No. 149 / Wednesday, August 4, 2010 / Proposed Rules 46877 

Other FAA AD Provisions 

(m) 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. 

Send information to ATTN: Tim Dulin, 

Aerospace Engineer, International Branch, 

ANM–116, Transport Airplane Directorate, 

FAA, 1601 Lind Avenue, SW., Renton, 

Washington 98057–3356; telephone (425) 

227–2141; fax (425) 227–1149. Before using 

any approved AMOC on any airplane to 

which the AMOC applies, notify your 

principal maintenance inspector (PMI) or 

principal avionics inspector (PAI), as 

appropriate, or lacking a principal inspector, 

your local Flight Standards District Office. 

The AMOC approval letter must specifically 

reference 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. 

(3) Reporting Requirements: For any 

reporting requirement in this AD, under the 

provisions of the Paperwork Reduction Act 

(44 U.S.C. 3501 et seq.), the Office of 

Management and Budget (OMB) has 

approved the information collection 

requirements and has assigned OMB Control 

Number 2120–0056. 

Related Information 

(n) Refer to MCAI EASA Airworthiness 

Directive 2007–0276R1, dated March 18, 

2010 (corrected April 12, 2010), and the 

service information identified in Table 2 of 

this AD, for related information. 

TABLE 2—RELATED SERVICE INFORMATION

Service information Revision level Date 

Airbus Mandatory Service Bulletin A320–25A1555 ................ 02 ............................................................................................ November 5, 2008. 

Airbus Service Bulletin A320–25–1557 .................................. 02 ............................................................................................ November 5, 2008. 

Airbus Service Bulletin A320–53–1215 .................................. Original ................................................................................... November 5, 2008. 

Issued in Renton, Washington, on July 27, 

2010. 

Ali Bahrami, 

Manager, Transport Airplane Directorate, 

Aircraft Certification Service. 

[FR Doc. 2010–19144 Filed 8–3–10; 8:45 am] 

BILLING CODE 4910–13–P 

DEPARTMENT OF THE INTERIOR 

Office of Surface Mining Reclamation 

and Enforcement 

30 CFR Part 938 

[PA–156–FOR; OSM 2010–0004] 

Pennsylvania Regulatory Program 

AGENCY: Office of Surface Mining 

Reclamation and Enforcement (OSM), 

Interior. 

ACTION: Proposed rule; public comment 

period and opportunity for public 

hearing on proposed amendment. 

SUMMARY: We are announcing receipt of 

an amendment to the Pennsylvania 

program (the ‘‘Pennsylvania program’’) 

under the Surface Mining Control and 

Reclamation Act of 1977 (SMCRA or the 

Act) (Administrative Record No. 

888.00). The revisions to the regulations 

specifically address fourteen required 

program amendments and the remining 

financial guarantee program, thereby 

addressing a portion of the 

Pennsylvania regulatory provisions that 

were previously determined not to be 

approvable. Pennsylvania intends to 

revise its program to be consistent with 

the corresponding Federal regulations. 

This document gives the times and 

locations that the Pennsylvania program 

and this submittal are available for your 

inspection, the comment period during 

which you may submit written 

comments, and the procedures that we 

will follow for the public hearing, if one 

is requested. 

DATES: We will accept written 

comments until 4 p.m., local time 

September 3, 2010. If requested, we will 

hold a public hearing on August 30, 

2010. We will accept requests to speak 

until 4 p.m., local time on August 19, 

2010. 

ADDRESSES: You may submit comments, 

identified by ‘‘PA–156–FOR; Docket ID: 

OSM–2010–0004’’ by either of the 

following two methods: 

• Federal eRulemaking Portal: http:// 

www.regulations.gov. The proposed rule 

has been assigned Docket ID: OSM– 

2010–0004. If you would like to submit 

comments through the Federal 

eRulemaking Portal, go to http:// 

www.regulations.gov and follow the 

instructions. 

• Mail/Hand Delivery/Courier: Mr. 

George Rieger, Chief, Pittsburgh Field 

Division, Office of Surface Mining 

Reclamation and Enforcement, 

Harrisburg Transportation Center, 415 

Market St., Suite 304, Harrisburg, PA 

17101. 

Instructions: For detailed instructions 

on submitting comments and additional 

information on the rulemaking process, 

see the ‘‘Public Comment Procedures’’ 

heading of the SUPPLEMENTARY

INFORMATION section of this document. 

Docket: In addition to obtaining 

copies of documents at http:// 

www.regulations.gov, information may 

also be obtained at the addresses listed 

below during normal business hours, 

Monday through Friday, excluding 

holidays. You may receive one free copy 

of the amendment by contacting OSM’s 

Pittsburgh Field Division Office. 

George Rieger, Chief, Pittsburgh Field 

Division, Office of Surface Mining 

Reclamation and Enforcement, 

Harrisburg Transportation Center, 415 

Market St., Suite 304, Harrisburg, 

Pennsylvania 17101, Telephone: (717) 

782–4036, E-mail: grieger@osmre.gov; 

William S. Allen Jr., Acting Director, 

Bureau of Mining and Reclamation, 

Pennsylvania Department of 

Environmental Protection, Rachel 

Carson State Office Building, P.O. Box 

8461, Harrisburg, Pennsylvania 

17105–8461, Telephone: (717) 787– 

5015, E-mail: wallen@state.pa.us. 

FOR FURTHER INFORMATION CONTACT: 

George Rieger, Telephone: (717) 782– 

4036. E-mail: grieger@osmre.gov. 

SUPPLEMENTARY INFORMATION: 

I. Background on the Pennsylvania Program 

II. Description of the Amendment 

III. Public Comment Procedures 

IV. Procedural Determinations 

I. Background on the Pennsylvania 

Program 

Section 503(a) of the Act permits a 

State to assume primacy for the 

regulation of surface coal mining and 

reclamation operations on non-Federal 

and non-Indian lands within its borders 

by demonstrating that its program 

includes, among other things, ‘‘a State 

law which provides for the regulation of 

surface coal mining and reclamation 

operations in accordance with the 

requirements of this Act * * *; and 

rules and regulations consistent with 

regulations issued by the Secretary 

pursuant to this Act.’’ See 30 U.S.C. 

1253(a)(1) and (7). On the basis of these 

criteria, the Secretary of the Interior 


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