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
Federal Register / Vol. 76, No. 120 / Wednesday, June 22, 2011 / Proposed Rules 36393 

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– 

2011–0572; Directorate Identifier 2011– 

NM–009–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 have received reports from 

Gulfstream that the third Halon bottle 

(third fire extinguisher bottle) is 

mounted in the auxiliary power unit 

(APU) small-fragment impact zone 

(rotor burst zone). Some operators might 

have installed this third fire 

extinguisher bottle in accordance with 

Supplemental Type Certificate 

ST01822AT–D; other operators might 

have installed the bottle under FAA 

approval means other than the 

supplemental type certificate. The bottle 

is mounted in a very confined area 

surrounded by primary airframe 

structure that carries the empennage 

loads. Primary flight controls for pitch 

and yaw are also routed through the 

area adjacent to the third fire 

extinguisher bottle. Failure of the APU 

rotor system could release fragments 

that could strike the bottle and cause 

explosive rupture of the high-pressure 

Halon bottle, and result in substantial 

damage to primary airframe structure 

and primary flight controls. 

Related Rulemaking 

We previously issued AD 2009–17– 

01, Amendment 39–15991 (74 FR 

40061, August 11, 2009), for all Model 

GV airplanes and certain Model GV–SP 

airplanes (and other Gulfstream 

airplanes). That AD requires, for certain 

airplanes, an inspection for sealant 

applied to the exterior of the APU 

enclosure (firewall), and, for certain 

airplanes, a revision of the airplane 

flight manual to prohibit operation of 

the APU during certain ground and 

flight operations. That AD was issued to 

prevent the flammable sealant from 

igniting the exterior surfaces of the 

firewall under certain anomalous 

conditions such as an APU failure or 

APU compartment fire, which could 

result in propagation of an uncontained 

fire to other critical areas of the 

airplane. 

We are considering revising AD 2009– 

17–01 to provide an optional 

terminating action (modification of the 

APU enclosure), which would allow 

removal of the APU limitations after the 

requirements of this new AD have been 

met. 

Relevant Service Information 

We reviewed Gulfstream V Alert 

Customer Bulletin 30A (for Model GV 

airplanes) Gulfstream G500 Alert 

Customer Bulletin 10A (for Model GV– 

SP airplanes); and Gulfstream G550 

Alert Customer Bulletin 10A (for Model 

GV–SP airplanes), all dated December 

20, 2010, all including Gulfstream GV/ 

GV–SP Airplane Flight Manual (AFM) 

Supplement CE51 628M001, Revision 

A, dated December 20, 2010, to the 

Gulfstream GV and GV–SP AFMs. These 

customer bulletins describe procedures 

for inspecting to determine whether a 

third fire extinguisher bottle is installed 

for engines, and, if so, determining 

whether the third bottle is installed as 

a spare or in a dedicated configuration. 

These bulletins also describe procedures 

for removing the third bottles installed 

as spares on Model GV and GV–SP 

airplanes. The Gulfstream GV/GV–SP 

AFM Supplement CE51 628M001, 

Revision A, dated December 20, 2010, 

adds restrictions for APU usage on 

Model GV and GV–SP airplanes having 

a third bottle in a dedicated or nondedicated (spare) configuration. 

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 these same 

type designs. 

Proposed AD Requirements 

This proposed AD requires 

accomplishing the actions specified in 

the service information described 

previously. 

Certain airplanes have a third Halon 

fire extinguisher bottle carried as a 

spare. These ‘‘spare’’ bottles are not 

connected to the aircraft fire 

suppression system electrical or 

plumbing provisions. In these cases, the 

bottle can be easily removed without 

affecting the aircraft fire suppression 

system. Operators can also leave the 

spare bottle installed, but must 

implement the revised APU operating 

limitations in this case. In some Model 

GV airplanes only, the third Halon fire 

extinguisher bottle is a functioning part 

of the aircraft fire suppression system. 

In these cases the bottle must remain 

installed in the airplane, and the revised 

APU operating limitations must be 

implemented. 

Interim Action 

We consider this proposed AD 

interim action. The manufacturer is 

currently developing a modification that 

will address the unsafe condition 

identified in this proposed AD. Once 

this modification is developed, 

approved, and available, we might 

consider additional rulemaking. 

Costs of Compliance 

We estimate that this proposed AD 

affects 1,000 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 

Inspection ................... 1 work-hour × $85 per hour = $85 ..................................................... $0 $85 $85,000 

We estimate the following costs to do 

any necessary actions that would be 

required based on the results of the 

proposed inspection. 


srobinson on DSK4SPTVN1PROD with PROPOSALS
36394 Federal Register / Vol. 76, No. 120 / Wednesday, June 22, 2011 / Proposed Rules 

ON-CONDITION COSTS

Action Labor cost Parts cost Cost per product 

AFM revision ............ 1 work-hour × $85 per hour = $85 ............................. $0 $85 (about 70 GV/GV–SP airplanes).

Bottle removal .......... 1 work-hour × $85 per hour = $85 ............................. $0 $85 (about 30 GV-SP airplanes).

According to the manufacturer, some 

of the costs of this proposed AD may be 

covered under warranty, thereby 

reducing the cost impact on affected 

individuals. We do not control warranty 

coverage for affected individuals. As a 

result, we have included all costs in our 

cost estimate. 

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): 

Gulfstream Aerospace Corporation: Docket 

No. FAA–2011–0572; Directorate 

Identifier 2011–NM–009–AD. 

Comments Due Date 

(a) We must receive comments by August 

8, 2011. 

Affected ADs 

(b) None. 

Applicability 

(c) This AD applies to the Gulfstream 

Aerospace Corporation airplanes, certificated 

in any category, identified in paragraphs 

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

(1) Model GV airplanes having serial 

numbers (S/Ns) 501 and subsequent. 

(2) Model GV–SP airplanes having S/Ns 

5001 through 5308 inclusive. 

Subject 

(d) Joint Aircraft System Component 

(JASC)/Air Transport Association (ATA) of 

America Code 2621, Fire bottle-fixed. 

Unsafe Condition 

(e) This AD was prompted by notification 

from the airplane manufacturer that the third 

fire extinguisher bottle is mounted in a smallfragment impact zone. We are issuing this AD 

to prevent penetration of the bottle by 

fragments released due to a failure of the 

auxiliary power unit (APU) rotor system. The 

bottle could rupture and cause substantial 

damage to primary airframe structure and 

primary flight controls. 

Compliance 

(f) Comply with this AD within the 

compliance times specified, unless already 

done. 

Inspection 

(g) For all airplanes: Within 21 days after 

the effective date of this AD, or before 

removing the APU flight restrictions required 

by AD 2009–17–01, Amendment 39–15991, 

whichever occurs first, inspect to determine 

whether a third Halon fire extinguisher bottle 

for engines is installed in the APU fragment 

impact zone (rotor fragment impact zone), in 

accordance with the Accomplishment 

Instructions of the applicable Gulfstream 

alert customer bulletin identified in table 1 

of this AD. 

TABLE 1—APPLICABLE GULFSTREAM ALERT CUSTOMER BULLETINS

For Model— Use— Which includes— To the— 

GV airplanes ......................... Gulfstream V Alert Customer Bulletin 30A, 

dated December 20, 2010.

Gulfstream GV/GV–SP Airplane Flight Manual 

(AFM) Supplement CE51 628M001, Revision 

A, dated December 20, 2010.

Gulfstream 

GV AFM. 

GV–SP (G500) airplanes ..... Gulfstream G500 Alert Customer Bulletin 10A, 

dated December 20, 2010.

Gulfstream GV/GV–SP AFM Supplement CE51 

628M001, Revision A, dated December 20, 

2010.

Gulfstream 

GV–SP 

AFM. 

GV–SP (G550) airplanes ..... Gulfstream G550 Alert Customer Bulletin 10A, 

dated December 20, 2010.

Gulfstream GV/GV–SP AFM Supplement CE51 

628M001, Revision A, dated December 20, 

2010.

Gulfstream 

GV–SP 

AFM. 


srobinson on DSK4SPTVN1PROD with PROPOSALS
Federal Register / Vol. 76, No. 120 / Wednesday, June 22, 2011 / Proposed Rules 36395 

(1) If the third fire extinguisher bottle is not 

installed, no further work is required by this 

paragraph. 

(2) For Model GV airplanes in which the 

third fire extinguisher bottle is installed as a 

dedicated APU fire bottle configuration, as 

defined in Gulfstream V Alert Customer 

Bulletin 30A, dated December 20, 2010 (as a 

functioning part of the aircraft fire 

suppression system): Before further flight, 

revise the Limitations section of the 

Gulfstream GV AFM to include the 

information in Gulfstream GV/GV–SP AFM 

Supplement CE51 628M001, Revision A, 

dated December 20, 2010 (which is included 

in Gulfstream V Alert Customer Bulletin 30A, 

dated December 20, 2010). This AFM 

supplement adds restrictions for APU usage. 

Operate the airplane thereafter according to 

the limitations in this AFM supplement. 

Note 1: This may be done by inserting a 

copy of Gulfstream GV/GV–SP AFM 

Supplement CE51 628M001, Revision A, 

dated December 20, 2010, in the applicable 

AFM. When information in this AFM 

supplement has been included in general 

revisions of the applicable AFM, the general 

revisions may be inserted in the applicable 

AFM, provided the relevant information in 

the general revision is identical to that in 

Gulfstream GV/GV–SP AFM Supplement 

CE51 628M001, Revision A, dated December 

20, 2010, and that AFM supplement may be 

removed. 

(3) For Model GV and GV–SP airplanes in 

which the third fire extinguisher bottle is 

installed as a spare fire bottle configuration 

(not connected to the airplane’s electrical or 

fire suppression systems), as defined in the 

applicable Gulfstream alert customer bulletin 

identified in table 1 of this AD: Do the 

actions required by paragraph (g)(3)(i) or 

(g)(3)(ii) of this AD. 

(i) Before further flight, remove the bottle, 

in accordance with the Accomplishment 

Instructions of the applicable Gulfstream 

alert customer bulletin identified in table 1 

of this AD. 

(ii) Before further flight, revise the 

limitations section of the applicable 

Gulfstream AFM specified in table 1 of this 

AD to include the information in Gulfstream 

GV/GV–SP AFM Supplement CE51 

628M001, Revision A, dated December 20, 

2010. This AFM supplement adds 

restrictions for APU usage. Operate the 

airplane thereafter according to the 

limitations in that AFM supplement. 

Note 2: This may be done by inserting a 

copy of Gulfstream GV/GV–SP AFM 

Supplement CE51 628M001, Revision A, 

dated December 20, 2010, in the applicable 

AFM. When information in this AFM 

supplement has been included in general 

revisions of the applicable AFM, the general 

revisions may be inserted in the applicable 

AFM, provided the relevant information in 

the general revision is identical to that in 

Gulfstream GV/GV–SP AFM Supplement 

CE51 628M001, Revision A, dated December 

20, 2010, and that AFM supplement may be 

removed. 

Credit for Actions Accomplished in 

Accordance With Previous Service 

Information 

(h) Actions accomplished before the 

effective date of this AD in accordance with 

Gulfstream V Alert Customer Bulletin 30 (for 

Model GV airplanes), dated December 6, 

2010, including Gulfstream GV AFM 

Supplement CE51 628M001, dated November 

18, 2010, to the Gulfstream GV AFM; or 

Gulfstream G550 (for Model GV–SP 

airplanes) or G500 (for Model GV–SP 

airplanes) Alert Customer Bulletin 10, both 

dated December 6, 2010; are acceptable for 

compliance with the corresponding actions 

required by paragraph (g) of this AD. 

Parts Installation 

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

person may install a third fire extinguisher 

bottle in the APU fragment impact zone 

(rotor fragment impact zone) of any airplane. 

No Reporting 

(j) Although Gulfstream V Alert Customer 

Bulletin 30A (for Model GV airplanes), 

Gulfstream G500 Alert Customer Bulletin 

10A (for Model GV–SP airplanes), and 

Gulfstream G550 Alert Customer Bulletin 

10A (for Model GV–SP airplanes); all dated 

December 20, 2010, all including Gulfstream 

GV/GV–SP AFM Supplement CE51 

628M001, Revision A, dated December 20, 

2010, to the Gulfstream GV, and GV–SP 

AFMs; specify to submit certain information 

to the manufacturer, this AD does not 

include that requirement. 

Special Flight Permit 

(k) 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 

following conditions are met: 

(1) If an airplane is grounded due to a 

single generator failure, the APU may be 

operated during a ferry flight, provided no 

passengers are carried. 

(2) Only the minimum required flight crew 

is allowed on any ferry flight. 

Alternative Methods of Compliance 

(AMOCs) 

(l)(1) The Manager, Atlanta 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. 

(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 

(m) For more information about this AD, 

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; telephone 404–474–5566; fax 

404–474–5606; sanford.proveaux@faa.gov. 

(n) For service information identified in 

this 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. 

Issued in Renton, Washington on June 10, 

2011. 

Ali Bahrami, 

Manager, Transport Airplane Directorate, 

Aircraft Certification Service. 

[FR Doc. 2011–15537 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–2011–0639; Directorate 

Identifier 2011–CE–016–AD] 

RIN 2120–AA64 

Airworthiness Directives; Piper 

Aircraft, Inc. Models PA–24, PA–24– 

250, and PA–24–260 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 either replacement of 

the stabilator horn assembly or 

repetitive inspection of the stabilator 

horn assembly for corrosion or cracks 

with replacement of the stabilator horn 

assembly if any corrosion or cracks are 

found. This proposed AD was prompted 

by reports of cracks developing in the 

stabilator horn assembly. We are 

proposing this AD to detect and correct 

corrosion or cracks in the stabilator horn 

assembly. Corrosion or cracks could 

lead to failure of the stabilator horn. 

Consequently, failure of the stabilator 

horn could lead to a loss of pitch control 

in flight. 

DATES: We must receive comments on 

this proposed AD by August 8, 2011. 

ADDRESSES: You may send comments by 

any of the following methods: 


srobinson on DSK4SPTVN1PROD with PROPOSALS