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
Federal Register / Vol. 76, No. 120 / Wednesday, June 22, 2011 / Proposed Rules 36391 

Yaw damper authority is limited to 

+/¥ 4 degrees of rudder command. The 

failure removed the yaw damper end 

stop and allowed the yaw damper input 

to exceed the maximum design yaw 

damper authority. Although 

commanding full retract, pilot pedal 

inputs were ineffective in moving the 

lower rudder back to the right. We also 

received three additional reports of 

cracking in the rudder PCM manifold. 

These events did not result in a hardover, but created the need for a retention 

feature solution specified in AD 2008– 

13–03, Amendment 39–15566, for 

Model 747–400, –400D, and –400F 

series airplanes. Upon investigation, it 

was determined that the Model 747SP 

fleet could be susceptible to the same 

failure because they use the same 

manifold sub-assembly as the Model 

747–400 series airplanes. Cracking in a 

rudder PCM manifold, if not corrected, 

could result in a failure of the upper or 

lower 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. 

Relevant Service Information 

We reviewed Boeing Alert Service 

Bulletin 747–27A2497, dated September 

30, 2010. The service information 

describes procedures for either 

replacing the upper and lower rudder 

PCMs having Boeing part number (P/N) 

60B80093–3 (Parker P/N 241700–1005) 

or Boeing P/N 60B80093–4 (Parker P/N 

241700–1007), with new rudder PCMs 

having Boeing P/N 60B80093–104 

(Parker P/N 241700–9007); or modifying 

the upper and lower rudder PCMs 

having Boeing P/N 60B80093–3 (Parker 

P/N 241700–1005) or Boeing P/N 

60B80093–4 (Parker P/N 241700–1007) 

by replacing the access cap with a two 

piece cap that includes a retention 

feature for the yaw damper modulating 

piston assembly in the rudder PCM. 

Boeing Alert Service Bulletin 747– 

27A2497, dated September 30, 2010, 

refers to Parker Service Bulletin 

241700–27–333, dated January 26, 2010, 

as an additional source of guidance for 

modifying the upper and lower rudder 

PCMs provided in Option 2 of Work 

Packages 1 and 2 of Boeing Alert Service 

Bulletin 747–27A2497, dated September 

30, 2010. 

FAA’s Determination 

We are proposing this AD because we 

evaluated all the relevant information 

and determined the unsafe condition 

described previously is likely to exist or 

develop in other products of the same 

type designs. 

Proposed AD Requirements 

This proposed AD would require 

accomplishing the actions specified in 

the service information described 

previously. 

Costs of Compliance 

We estimate that this proposed AD 

affects 7 airplanes of U.S. registry. 

We estimate the following costs to 

comply with this proposed AD: 

ESTIMATED COSTS

Action Labor cost Parts cost Cost per 

product 

Cost on U.S. 

operators 

Replace rudder PCM (P/N 241700–1007) ......... 11 work-hours × $85 per hour = $935 ............... $5,856 $6,791 $47,537 

Replace rudder PCM (P/N 241700–1005) ......... 11 work-hours × $85 per hour = $935 ............... 8,568 9,503 66,521 

Modify rudder PCM (P/N 241700–1007) ............ 3 work-hours × $85 per hour = $255 ................. 1,374 1,629 11,403 

Modify rudder PCM (P/N 241700–1005) ............ 3 work hours × $85 per hour = $255 ................. 4,086 4,341 30,387 

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. 

List of Subjects in 14 CFR Part 39 

Air transportation, Aircraft, Aviation 

safety, Incorporation by reference, 

Safety. 

The Proposed Amendment 

Accordingly, under the authority 

delegated to me by the Administrator, 

the FAA proposes to amend 14 CFR part 

39 as follows: 

PART 39—AIRWORTHINESS 

DIRECTIVES 

1. The authority citation for part 39 

continues to read as follows: 

Authority: 49 U.S.C. 106(g), 40113, 44701. 

§ 39.13 [Amended] 

2. The FAA amends § 39.13 by adding 

the following new airworthiness 

directive (AD): 

The Boeing Company: Docket No. FAA– 

2011–0571; Directorate Identifier 2010– 

NM–263–AD. 

Comments Due Date 

(a) We must receive comments by August 

8, 2011. 

Affected ADs 

(b) None. 

Applicability 

(c) This AD applies to all The Boeing 

Company Model 747SP series airplanes, 

certificated in any category. 


srobinson on DSK4SPTVN1PROD with PROPOSALS
36392 Federal Register / Vol. 76, No. 120 / Wednesday, June 22, 2011 / Proposed Rules 

Subject 

(d) Joint Aircraft System Component 

(JASC)/Air Transport Association (ATA) of 

America Code 27, Flight Controls. 

Unsafe Condition 

(e) This AD was prompted by a report of 

a rudder hard-over event on a Model 747–400 

series airplane, caused by a rudder power 

control module (PCM) manifold cracking and 

separating in the area of the yaw damper 

cavity end-cap. We are issuing this AD to 

prevent a failure of the lower or upper rudder 

PCM manifold, which could result in a hardover of the rudder surface leading to an 

increase in pilot workload and a possible 

high-speed runway excursion upon landing. 

Compliance 

(f) Comply with this AD within the 

compliance times specified, unless already 

done. 

Replace or Modify Rudder PCMs 

(g) Within 24 months or 8,400 flight hours 

after the effective date of this AD, whichever 

occurs first, do the replacement specified in 

paragraph (g)(1) of this AD or the 

modification specified in paragraph (g)(2) of 

this AD for the upper and lower rudder 

PCMs, in accordance with the 

Accomplishment Instructions of Boeing Alert 

Service Bulletin 747–27A2497, dated 

September 30, 2010. 

(1) Replace any rudder PCM having Boeing 

part number (P/N) 60B80093–3 (Parker P/N 

241700–1005) or Boeing P/N 60B80093–4 

(Parker P/N 241700–1007) with rudder PCM 

having Boeing P/N 60B80093–104 (Parker 

P/N 241700–9007). 

(2) Modify the rudder PCM having Boeing 

P/N 60B80093–3 (Parker P/N 241700–1005) 

or Boeing P/N 60B80093–4 (Parker P/N 

241700–1007). 

Note 1: Boeing Alert Service Bulletin 747– 

27A2497, dated September 30, 2010, refers to 

Parker Service Bulletin 241700–27–333, 

dated January 26, 2010, as an additional 

source of guidance for modifying the upper 

and lower rudder PCM manifold access caps 

provided in Option 2 of Work Packages 1 and 

2 of Boeing Alert Service Bulletin 747– 

27A2497, dated September 30, 2010. 

Parts Installation 

(h) As of the effective date of this AD, no 

person may install a rudder PCM having 

Boeing P/N 60B80093–3 (Parker P/N 241700– 

1005) or Boeing P/N 60B80093–4 (Parker P/ 

N 241700–1007), on any airplane. 

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. 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 manager of the ACO, send it to the 

attention of the person identified in the 

Related Information section of this AD. 

Information may be e-mailed to: 9–ANM– 

Seattle–ACO–AMOC–Requests@faa.gov. 

(2) 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. 

Related Information 

(j) For more information about this AD, 

contact Marie Hogestad, Aerospace Engineer, 

Systems and Equipment Branch, ANM–130S, 

FAA, Seattle Aircraft Certification Office, 

1601 Lind Avenue, SW., Renton, Washington 

98057–3356; telephone: 425–917–6418; fax: 

425–917–6590; e-mail: 

marie.hogestad@faa.gov. 

(k) For service information identified in 

this 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. 

Issued in Renton, Washington on June 14, 

2011. 

Ali Bahrami, 

Manager, Transport Airplane Directorate, 

Aircraft Certification Service. 

[FR Doc. 2011–15536 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–2011–0572; Directorate 

Identifier 2011–NM–009–AD] 

RIN 2120–AA64 

Airworthiness Directives; Gulfstream 

Aerospace Corporation Model GV and 

GV–SP 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 inspecting to 

determine whether a third Halon fire 

extinguisher bottle is installed in the 

auxiliary power unit (APU) fragment 

impact zone, revising the limitations 

section of the airplane flight manual to 

add restrictions for APU usage for 

certain airplanes having a third fire 

extinguisher bottle, and removing the 

third fire extinguisher bottle from 

certain airplanes. This proposed AD was 

prompted by notification from the 

airplane manufacturer that the third fire 

extinguisher bottle is mounted in a 

small-fragment impact zone. We are 

proposing this AD to prevent 

penetration of the bottle by fragments 

released due to a failure of the APU 

rotor system. The bottle could rupture 

and cause substantial damage to 

primary airframe structure and primary 

flight controls. 

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 Gulfstream 

Aerospace Corporation, Technical 

Publications Dept., P.O. Box 2206, 

Savannah, Georgia 31402–2206; 

telephone 800–810–4853; fax 912–965– 

3520; e-mail pubs@gulfstream.com; 

Internet http://www.gulfstream.com/ 

product_support/technical_pubs/pubs/ 

index.htm. 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: 

Sanford Proveaux, Aerospace Engineer, 

Continued Operational Safety and 

Certificate Management Branch, ACE– 

102A, FAA, Atlanta Aircraft 

Certification Office (ACO) 1701 

Columbia Avenue, College Park, Georgia 

30337; phone: 404–474–5566; fax: 404– 

474–5606; e-mail: 

sanford.proveaux@faa.gov. 


srobinson on DSK4SPTVN1PROD with PROPOSALS