Federal Register / Vol. 76, No. 120 / Wednesday, June 22, 2011 / Proposed Rules 36387 

commercial distribution of byproduct 

material to allow recipients of exempt 

quantities of PCTE/MFP to 

commercially redistribute the material 

without a license. The petitioner states 

that once GE obtains an exempt quantity 

distribution license from the NRC, there 

should be no significant health, safety or 

common defense and security concerns 

that would preclude its customers from 

further redistribution of the material 

without a license. 

The NRC has determined that the 

petition meets the threshold sufficiency 

requirements for a petition for 

rulemaking under Title 10 of the Code 

of Federal Regulations (10 CFR), 2.802, 

and the petition has been docketed as 

PRM–30–65. The NRC is requesting 

public comment on the petition for 

rulemaking. 

Discussion of the Petition 

The petitioner states that under 

current NRC regulations (and with a 

specific license, if approved), it is able 

to manufacture and commercially 

distribute PCTE/MFP membranes to that 

segment of its customers that will not be 

further distributing the product for 

commercial purposes. However, current 

regulations at 10 CFR 30.18(c) and (d) 

prohibit the petitioner from distribution 

of the material to a substantial portion 

of its customer base that would 

commercially redistribute the material if 

authorized to do so. 

The petitioner proposes that 10 CFR 

30.18 be modified as follows: 

(c) This section does not authorize for 

purposes of commercial distribution the 

production, packaging, repackaging, or 

transfer of byproduct material or the 

incorporation of byproduct material into 

products intended for commercial 

distribution, except as provided in § 30.18(f). 

(d) Except as provided in § 30.18(f), no 

person may, for purposes of commercial 

distribution, transfer byproduct material in 

the individual quantities set forth in § 30.71 

Schedule B, knowing or having reason to 

believe that such quantities of byproduct 

material will be transferred to persons 

exempt under this section or equivalent 

regulations of an Agreement State, except in 

accordance with a license issued under 

§ 32.18 of this chapter, which license states 

that the byproduct material may be 

transferred by the licensee to persons exempt 

under this section or the equivalent 

regulations of an Agreement State. 

(f) Polymer track etch membrane 

containing mixed fission products in 

individual quantities, each of which does not 

exceed the applicable quantity set forth in 

§ 30.71 Schedule B, may be redistributed 

commercially to any person without the 

redistributor obtaining a specific license 

under § 32.18, so long as the person who 

initially manufactures, processes, produces, 

packages, repackages, or transfers quantities 

of byproduct material for commercial 

distribution obtains a specific license under 

§ 32.18. 

The petitioner has separately 

requested an NRC exempt distribution 

license under 10 CFR 32.18 to authorize 

it to commercially distribute the PCTE/ 

MFP membranes to its customers, and 

believes that once it obtains the license, 

there should be no significant health, 

safety or common defense and security 

concerns that would preclude its 

customers from further redistribution 

without a license. The petitioner 

included an analysis in the petition for 

rulemaking document to support its 

belief. The petitioner states that PCTE/ 

MFP membranes are used in a wide 

variety of research, medical, academic, 

scientific and industrial applications. In 

particular, PCTE/MFP membranes are 

used in pharmaceutical, medical device, 

and water filtration applications. The 

petitioner believes that the amendments 

are necessary to allow it to distribute the 

PCTE/MFP membranes to the full range 

of its customers. 

Dated at Rockville, Maryland this 16th day 

of June, 2011. 

For the Nuclear Regulatory Commission. 

Annette Vietti-Cook, 

Secretary of the Commission. 

[FR Doc. 2011–15593 Filed 6–21–11; 8:45 am] 

BILLING CODE 7590–01–P 

DEPARTMENT OF TRANSPORTATION 

Federal Aviation Administration 

14 CFR Part 39 

[Docket No. FAA–2011–0570; Directorate 

Identifier 2011–NM–014–AD] 

RIN 2120–AA64 

Airworthiness Directives; Airbus Model 

A300 Series Airplanes; Model A310 

Series Airplanes; and Model A300 B4– 

600, B4–600R, and F4–600R Series 

Airplanes, and Model C4–605R Variant 

F Airplanes (Collectively Called A300– 

600 Series Airplanes) 

AGENCY: Federal Aviation 

Administration (FAA), DOT. 

ACTION: Notice of proposed rulemaking 

(NPRM). 

SUMMARY: We propose to adopt a new 

airworthiness directive (AD) for the 

products listed above. 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: 

* * * * * 

A recent analysis conducted by the 

manufacturer showed a particular risk for 

explosive failure of the * * * hydraulic 

accumulator. 

This condition, if not detected and 

corrected, might, for some aeroplane 

installations, lead to damage to all three 

hydraulic circuits, possibly resulting in loss 

of control of the aeroplane or could, for 

certain other aeroplane installations, lead to 

an undetected fire in the wheel bay. 

* * * * * 

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 8, 2011. 

ADDRESSES: You may send comments by 

any of the following methods: 

• Federal eRulemaking Portal: Go to 

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

instructions for submitting comments. 

• Fax: (202) 493–2251. 

• Mail: U.S. Department of 

Transportation, Docket Operations, M– 

30, West Building Ground Floor, Room 

W12–140, 1200 New Jersey Avenue, SE., 

Washington, DC 20590. 

• Hand Delivery: U.S. Department of 

Transportation, Docket Operations, M– 

30, West Building Ground Floor, Room 

W12–140, 1200 New Jersey Avenue, SE., 

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

p.m., Monday through Friday, except 

Federal holidays. 

For service information identified in 

this proposed AD, contact Airbus SAS— 

EAW (Airworthiness Office), 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: Dan 

Rodina, Aerospace Engineer, 

International Branch, ANM–116, 


srobinson on DSK4SPTVN1PROD with PROPOSALS
36388 Federal Register / Vol. 76, No. 120 / Wednesday, June 22, 2011 / Proposed Rules 

Transport Airplane Directorate, FAA, 

1601 Lind Avenue, SW., Renton, 

Washington 98057–3356; telephone 

(425) 227–2125; fax (425) 227–1149. 

SUPPLEMENTARY INFORMATION: 

Comments Invited 

We invite you to send any written 

relevant data, views, or arguments about 

this proposed AD. Send your comments 

to an address listed under the 

ADDRESSES section. Include ‘‘Docket No. 

FAA–2011–0570; Directorate Identifier 

2011–NM–014–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 

The European Aviation Safety Agency 

(EASA), which is the Technical Agent 

for the Member States of the European 

Community, has issued EASA 

Airworthiness Directive 2011–0006, 

dated January 17, 2011 (referred to after 

this as ‘‘the MCAI’’), to correct an unsafe 

condition for the specified products. 

The MCAI states: 

Since 1984, the design of the hydraulic 

accumulator installed on all the affected 

Airbus types has changed. The Part Number 

(P/N) remained the same, but the 

manufacturer did not record the serial 

number of the part that was the first to be 

manufactured to the changed design 

specification. 

The new design hydraulic accumulator is 

manufactured with 2 pieces unit welded, 

instead of 4 pieces unit with 3 welds (old 

design) as pictured in Appendix 1 of this 

[EASA] AD. The welding process of the new 

design hydraulic accumulator provides a 

higher strength shell material and more 

reliability. 

A recent analysis conducted by the 

manufacturer showed a particular risk for 

explosive failure of the old design hydraulic 

accumulator. 

This condition, if not detected and 

corrected, might, for some aeroplane 

installations, lead to damage to all three 

hydraulic circuits, possibly resulting in loss 

of control of the aeroplane or could, for 

certain other aeroplane installations, lead to 

an undetected fire in the wheel bay. 

For the reasons explained above, this 

[EASA] AD requires a one time detailed 

visual inspection to identify the old designed 

accumulators installed on certain hydraulic 

systems, the replacement of those 

accumulators by new designed accumulators 

and, irrespective of findings, the installation 

of warning placards to avoid installation of 

old designed accumulators on the affected 

hydraulic systems. 

You may obtain further information 

by examining the MCAI in the AD 

docket. 

Relevant Service Information 

Airbus has issued the service 

bulletins identified in the following 

table. The actions described in this 

service information are intended to 

correct the unsafe condition identified 

in the MCAI. 

TABLE—SERVICE INFORMATION

Airbus mandatory service bulletin— Revision— Dated— 

A300–29–0126, including Appendices 01 and 02 ............................................................................ 01 ................................. October 12, 2010. 

A300–29–0127 .................................................................................................................................. Original ......................... August 12, 2010. 

A300–29–6063, including Appendix 01 ............................................................................................. Original ......................... August 12, 2010. 

A300–29–6064 .................................................................................................................................. Original ......................... August 12, 2010. 

A310–29–2099, including Appendix 01 ............................................................................................. Original ......................... August 12, 2010. 

A310–29–2100 .................................................................................................................................. Original ......................... August 12, 2010. 

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 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 184 products of U.S. 

registry. We also estimate that it would 

take about 7 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 $197 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 

$145,728, or $792 per product. 

In addition, we estimate that any 

necessary follow-on actions would take 

about 5 work-hours and require parts 

costing $10,700, for a cost of $11,125 

per product. We have no way of 

determining the number of products 

that may need these actions. 

Authority for This Rulemaking 

Title 49 of the United States Code 

specifies the FAA’s authority to issue 

rules on aviation safety. Subtitle I, 

section 106, describes the authority of 

the FAA Administrator. ‘‘Subtitle VII: 

Aviation Programs,’’ describes in more 

detail the scope of the Agency’s 

authority. 

We are issuing this rulemaking under 

the authority described in ‘‘Subtitle VII, 

Part A, Subpart III, Section 44701: 

General requirements.’’ Under that 

section, Congress charges the FAA with 

promoting safe flight of civil aircraft in 

air commerce by prescribing regulations 

for practices, methods, and procedures 


srobinson on DSK4SPTVN1PROD with PROPOSALS
Federal Register / Vol. 76, No. 120 / Wednesday, June 22, 2011 / Proposed Rules 36389 

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–2011–0570; 

Directorate Identifier 2011–NM–014–AD. 

Comments Due Date 

(a) We must receive comments by August 

8, 2011. 

Affected ADs 

(b) None. 

Applicability 

(c) This AD applies to the products 

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

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

all manufacturer serial numbers. 

(1) Model A300 B2–1A, B2–1C, B2K–3C, 

B2–203, B4–2C, B4–103, and B4–203 

airplanes. 

(2) Model A310–203, –204, –221, –222, 

–304, –322, –324, and –325 airplanes. 

(3) Model A300 B4–601, B4–603, B4–620, 

and B4–622 airplanes; A300 B4–605R and 

B4–622R airplanes; A300 F4–605R and F4– 

622R airplanes; and A300 C4–605R Variant F 

airplanes. 

Subject 

(d) Air Transport Association (ATA) of 

America Code 29: Hydraulic power. 

Reason 

(e) The mandatory continuing 

airworthiness information (MCAI) states: 

A recent analysis conducted by the 

manufacturer showed a particular risk for 

explosive failure of the * * * hydraulic 

accumulator. 

This condition, if not detected and 

corrected, might, for some aeroplane 

installations, lead to damage to all three 

hydraulic circuits, possibly resulting in loss 

of control of the aeroplane or could, for 

certain other aeroplane installations, lead to 

an undetected fire in the wheel bay. 

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. 

Inspection, Replacement, and Placard 

Installation 

(g) Within 30 months or 6,000 flight hours 

after the effective date of this AD, whichever 

occurs first: Do a detailed inspection of each 

type 5 hydraulic accumulator, part number 

(P/N) 3059103–1, P/N 3059103–2, P/N 

3059103–8, and P/N 3059103–9, to determine 

if an old design accumulator (i.e., pre-1984) 

is installed on any affected hydraulic circuit 

indicated in table 1 of this AD, as applicable, 

in accordance with the Accomplishment 

Instructions of the applicable Airbus 

mandatory service bulletin identified in table 

2 of this AD. 

TABLE 1—APPLICABLE HYDRAULIC

CIRCUITS

Airbus model Hydraulic circuit 

A300 airplanes pre-modification 02447.Blue and Green. 

A300 airplanes post-modification 02447.Blue. 

A300–600 airplanes ........... Blue. 

A310 airplanes ................... Green. 

TABLE 2—APPLICABLE SERVICE INFORMATION

Airbus mandatory service bulletin— Revision — Dated — 

A300–29–0126 (for Model A300 airplanes) ..................................................................................... 01 .................................... October 12, 2010. 

A300–29–6063 (for Model A300–600 airplanes) ............................................................................. Original ........................... August 12, 2010. 

A310–29–2099 (for Model A310 airplanes) ..................................................................................... Original ........................... August 12, 2010. 

(h) If, during any detailed inspection 

required by paragraph (g) of this AD, an old 

design hydraulic accumulator (i.e., pre-1984) 

is found installed on any affected hydraulic 

circuit as indicated in table 1 of this AD, as 

applicable to airplane model, before further 

flight replace each affected old design 

accumulator with a new design accumulator, 

in accordance with the Accomplishment 

Instructions of the applicable Airbus 

mandatory service bulletin identified in table 

2 of this AD. 

(i) Before further flight after accomplishing 

the inspection required by paragraph (g) of 

this AD: Install a placard at the designated 

location of any affected hydraulic circuit 

indicated in table 1 of this AD, as applicable 

to airplane model, in accordance with the 

Accomplishment Instructions of the 

applicable Airbus mandatory service bulletin 

identified in table 3 of this AD. 

TABLE 3—OTHER APPLICABLE SERVICE

INFORMATION

Airbus Mandatory Service 

Bulletin— Dated— 

A300–29–0127 ................. August 12, 2010. 

A300–29–6064 ................. August 12, 2010. 

A310–29–2100 ................. August 12, 2010. 

FAA AD Differences 

Note 1: This AD differs from the MCAI 

and/or service information as follows: No 

differences. 

Other FAA AD Provisions 

(j) The following provisions also apply to 

this AD: 

(1) Alternative Methods of Compliance 

(AMOCs): The Manager, International 

Branch, ANM–116, 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 


srobinson on DSK4SPTVN1PROD with PROPOSALS
36390 Federal Register / Vol. 76, No. 120 / Wednesday, June 22, 2011 / Proposed Rules 

appropriate. If sending information directly 

to the International Branch, send it to ATTN: 

Dan Rodina, Aerospace Engineer, 

International Branch, ANM–116, Transport 

Airplane Directorate, FAA, 1601 Lind 

Avenue SW., Renton, Washington 98057– 

3356; telephone (425) 227–2125; fax (425) 

227–1149. Information may be e-mailed to: 9- 

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

Before using any approved AMOC, notify 

your appropriate principal inspector, or 

lacking a principal inspector, the manager of 

the local flight standards district office/ 

certificate holding district office. The AMOC 

approval letter must specifically reference 

this AD. 

(2) 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. 

Related Information 

(k) Refer to MCAI European Aviation 

Safety Agency (EASA) Airworthiness 

Directive 2011–0006, dated January 17, 2011; 

and the service bulletins identified in table 

4 of this AD; for related information. 

TABLE 4—RELATED SERVICE INFORMATION

Airbus Mandatory Service Bulletin— Revision— Dated— 

A300–29–0126 ............................................................................................ 01 ......................................................................... October 12, 2010. 

A300–29–0127 ............................................................................................ Original ................................................................ August 12, 2010. 

A300–29–6063 ............................................................................................ Original ................................................................ August 12, 2010. 

A300–29–6064 ............................................................................................ Original ................................................................ August 12, 2010. 

A310–29–2099 ............................................................................................ Original ................................................................ August 12, 2010. 

A310–29–2100 ............................................................................................ Original ................................................................ August 12, 2010. 

Issued in Renton, Washington, on June 10, 

2011. 

Ali Bahrami, 

Manager, Transport Airplane Directorate, 

Aircraft Certification Service. 

[FR Doc. 2011–15535 Filed 6–21–11; 8:45 am] 

BILLING CODE 4910–13–P 

DEPARTMENT OF TRANSPORTATION 

Federal Aviation Administration 

14 CFR Part 39 

[Docket No. FAA–2011–0571; Directorate 

Identifier 2010–NM–263–AD] 

RIN 2120–AA64 

Airworthiness Directives; The Boeing 

Company Model 747SP Series 

Airplanes 

AGENCY: Federal Aviation 

Administration (FAA), DOT. 

ACTION: Notice of proposed rulemaking 

(NPRM). 

SUMMARY: We propose to adopt a new 

airworthiness directive (AD) for the 

products listed above. This proposed 

AD would require replacing or 

modifying the upper and lower rudder 

power control modules (PCM). This 

proposed AD was prompted by a report 

of a rudder hard-over event on a Model 

747–400 series airplane, caused by a 

rudder PCM manifold cracking and 

separating in the area of the yaw damper 

cavity end-cap. We are proposing this 

AD to prevent a failure of the lower or 

upper rudder PCM manifold, which 

could result in a hard-over of the rudder 

surface leading to an increase in pilot 

workload and a possible high-speed 

runway excursion upon landing. 

DATES: We must receive comments on 

this proposed AD by August 8, 2011. 

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: 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 proposed AD, contact Boeing 

Commercial Airplanes, Attention: Data 

& Services Management, P.O. Box 3707, 

MC 2H–65, Seattle, Washington 98124– 

2207; telephone 206–544–5000, 

extension 1; fax 206–766–5680; e-mail 

me.boecom@boeing.com; Internet 

https://www.myboeingfleet.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 Management Facility between 9 

a.m. and 5 p.m., Monday through 

Friday, except Federal holidays. The AD 

docket contains this proposed AD, the 

regulatory evaluation, any comments 

received, and other information. The 

street address for the Docket Office 

(phone: 800–647–5527) is in the 

ADDRESSES section. Comments will be 

available in the AD docket shortly after 

receipt. 

FOR FURTHER INFORMATION CONTACT: 

Marie Hogestad, Aerospace Engineer, 

Systems and Equipment Branch, ANM– 

130S, FAA, Seattle Aircraft Certification 

Office, 1601 Lind Avenue, SW., Renton, 

Washington 98057–3356; phone: 425– 

917–6418; fax: 425–917–6590; e-mail: 

marie.hogestad@faa.gov. 

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– 

2011–0571; Directorate Identifier 2010– 

NM–263–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 because of 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 

We received a report from an operator 

of a Model 747–400 series airplane of a 

lower rudder hard-over event caused by 

a lower rudder PCM manifold cracking 

and separating in the area of the yaw 

damper cavity end-cap. This allowed 

the yaw damper sleeve to shift, giving 

the system a lower rudder left input 

(beyond the yaw damper authority). 


srobinson on DSK4SPTVN1PROD with PROPOSALS