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: 


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36396 Federal Register / Vol. 76, No. 120 / Wednesday, June 22, 2011 / Proposed Rules 

• 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 Piper 

Aircraft, Inc., 2926 Piper Drive, Vero 

Beach, Florida 32960; telephone: (772) 

567–4361; fax: (772) 978–6573; Internet: 

http://www.newpiper.com/company/ 

publications.asp. You may review 

copies of the referenced service 

information at the FAA, Small Airplane 

Directorate, 901 Locust St., Kansas City, 

Missouri 64106. For information on the 

availability of this material at the FAA, 

call (816) 329–4148. 

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: 

Gregory K. Noles, Aerospace Engineer, 

FAA, Atlanta Aircraft Certification 

Office, 1701 Columbia Avenue, College 

Park, Georgia 30337; phone: (404) 474– 

5551; fax: (404) 474–5606; e-mail: 

gregory.noles@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– 

2011–0639; Directorate Identifier 2011– 

CE–016–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 issued Special Airworthiness 

Information Bulletin (SAIB) CE–04–88, 

dated September 15, 2004. This SAIB 

alerted owners and operators of Piper 

Aircraft, Inc. (Piper) Models PA–23, 

PA–24, PA–30, and PA–39 airplanes of 

potential corrosion of the stabilator 

torque tube, attach fittings, and 

attaching fasteners and recommended 

inspections of these parts. Based on the 

information available at issuance of this 

SAIB, the FAA had determined that an 

unsafe condition did not exist under 14 

CFR part 39. 

After reviewing service data for 

corrosion on the stabilator torque tubes, 

Piper issued Piper Service Bulletin No. 

1160, dated December 26, 2005. This 

service information is for stabilator 

torque tube assembly inspection. We 

then received reports of cracks found in 

the stabilator horn, part number (P/N) 

20397–00, during maintenance 

inspections per SAIB CE–04–88 or 

Service Bulletin 1160. 

With FAA assistance, the National 

Institute for Aviation Research (NIAR) 

investigated and concluded the root 

cause of the stabilator horn cracking was 

stress corrosion. 

We found two service difficulty 

reports for this safety issue. In parallel, 

the International Comanche Society 

(ICS) surveyed operators and provided 

additional service data. The ICS survey 

included approximately 80 targeted 

inspections and found 18 incidences of 

stabilator horn cracking, with all 

incidences occurring on Models PA–24 

and PA–24–250 airplanes. The same 

configuration of horn and torque 

assembly exists on Model PA–24–260 

airplanes. 

This condition, if not corrected, could 

result in failure of the stabilator horn. 

Consequently, failure of the stabilator 

horn could lead to a loss of pitch control 

in flight. 

Relevant Service Information 

We reviewed Piper Aircraft, Inc. 

Service Bulletin No. 1189, dated April 

29, 2010. The service information 

describes procedures for stabilator horn 

assembly inspection. 

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 design. 

Proposed AD Requirements 

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. 

Differences Between the Proposed AD 

and the Service Information 

The service information requires an 

initial inspection of the stabilator horn 

assembly upon reaching the initial 1,000 

hours time-in-service (TIS), with a 

repetitive inspection every 100 hours 

TIS thereafter. After installation of a 

new stabilator horn assembly, the 

inspection cycle starts over with an 

initial inspection at 1,000 hours TIS 

since the new stabilator horn assembly 

was installed with the 100-hour TIS 

repetitive inspections thereafter. 

This proposed AD requires either one 

of the following options: (1) An initial 

inspection of the stabilator horn 

assembly upon reaching 1,000 hours TIS 

or within 100 hours TIS after the 

effective date of the AD, whichever 

occurs later, with repetitive inspections 

every 500 hours TIS or 3 years, 

whichever occurs first; or (2) 

replacement of the stabilator horn 

assembly upon reaching 1,000 hours TIS 

or within the next 100 hours TIS after 

the effective date of this AD, whichever 

occurs later. After replacement of the 

stabilator horn assembly, within 1,000 

hours TIS or 10 years, whichever occurs 

first, the stabilator horn assembly must 

be replaced or be initially inspected and 

start the inspection cycle in option 1. 

The service information applies to 

Piper Models PA–24, PA–24–250, PA– 

24–260, PA–24–400, PA–30, and PA–39 

airplanes. We only have service history 

on Models PA–24 and PA–24–250 

airplanes. 

While there is no service history of 

this unsafe condition on Model PA–24– 

260 airplanes, we are including it in the 

AD because it is an identical 

configuration to Models PA–24 and PA– 

24–250 airplanes for the horn and 

torque tube. 

There is no service history of this 

unsafe condition on the Models PA–24– 

400, PA–30, and PA–39 airplanes, 

including inspections from the ICS 

operator survey. Also, these models 

have a thicker torque tube, which 

reduces clamp-up forces; clamp-up 

forces are a key factor of the stress 

corrosion cracking. Therefore, we are 

not including the Models PA–24–400, 


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Federal Register / Vol. 76, No. 120 / Wednesday, June 22, 2011 / Proposed Rules 36397 

PA–30, and PA–39 airplanes in the 

applicability of this AD. 

Costs of Compliance 

We estimate that this proposed AD 

affects 3,100 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 

Stabilator horn assembly inspection ........... 12 work-hours × $85 per hour = $1,020 .... Not applicable ....... $1,020 $3,162,000 

We estimate the following costs to do 

any necessary replacements that would 

be required based on the results of the 

proposed inspection. We have no way of 

determining the number of airplanes 

that might need this replacement: 

ON-CONDITION COSTS

Action Labor cost Parts cost Cost per product 

Stabilator horn assembly replacement ......................... 12 work-hours × $85 per hour = $1,020 ...................... $572 $1,592 

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): 

Piper Aircraft, Inc.: Docket No. FAA–2011– 

0639, Directorate Identifier 2011–CE– 

016–AD. 

Comments Due Date 

(a) We must receive comments by August 

8, 2011. 

Affected ADs 

(b) None. 

Applicability 

(c) This AD applies to the following Piper 

Aircraft, Inc. airplanes, certificated in any 

category: 

(1) Model PA–24, serial numbers (SNs) 24– 

1 through 24–3687; 

(2) Model PA–24–250, SNs 24–1, 24–103 

through 24–3687; and 

(3) Model PA–24–260, SNs 24–3642 and 

24–4000 through 24–5034. 

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 reports of 

cracks developing in the stabilator horn 

assembly. We are issuing 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. 

Compliance 

(f) Comply with this AD following Piper 

Aircraft, Inc. Service Bulletin No. 1189, dated 

April 29, 2010, within the compliance times 

specified in this AD, unless already done 

(does not eliminate the repetitive actions of 

this AD). 

Inspection/Replacement 

(g) When the stabilator horn assembly 

reaches a total of 1,000 hours time-in-service 

(TIS) or within the next 100 hours TIS after 

the effective date of this AD, whichever 

occurs later, do either of the following 

actions: 

(1) Initially inspect the stabilator horn 

assembly for corrosion or cracks. Repetitively 

thereafter inspect at intervals not to exceed 

500 hours TIS or 3 years, whichever occurs 

first; or 

(2) Replace the stabilator horn assembly 

with a new stabilator horn assembly. 

Repetitively thereafter replace the stabilator 

horn assembly with a new stabilator horn 

assembly within the next 1,000 hours TIS 


srobinson on DSK4SPTVN1PROD with PROPOSALS
36398 Federal Register / Vol. 76, No. 120 / Wednesday, June 22, 2011 / Proposed Rules 

after the last replacement or within the next 

10 years after the last replacement, 

whichever occurs first. 

(h) If any corrosion or cracks are found 

during any of the inspections required in 

paragraph (g)(1) of this AD, before further 

flight, you must replace the stabilator horn 

assembly with a new stabilator horn 

assembly. After the new stabilator horn 

assembly reaches a total of 1,000 hours TIS 

or within the next 10 years after the last 

replacement, whichever occurs first, you 

must do either of the actions required in 

paragraphs (g)(1) or (g)(2) of this AD. 

(i) You may at any time replace the 

stabilator horn assembly with a new 

stabilator horn assembly, provided no 

corrosion or cracks were found during an 

inspection that would require replacement 

before further flight. After the new stabilator 

horn assembly reaches a total of 1,000 hours 

TIS or within the next 10 years after the last 

replacement, whichever occurs first, you 

must do either of the actions required in 

paragraphs (g)(1) or (g)(2) of this AD. 

(j) If you replace the stabilator horn 

assembly as specified in paragraph (g)(2) of 

this AD, after the new stabilator horn 

assembly reaches a total of 1,000 hours TIS 

or within the next 10 years after the last 

replacement, whichever occurs first, you may 

begin the inspection requirements of 

paragraph (g)(1) instead of the repetitive 

replacement requirements of paragraph (g)(2). 

Note: Piper Aircraft, Inc. Service Bulletin 

No. 1160, dated December 26, 2005; Special 

Airworthiness Information Bulletin CE–04– 

88, dated September 15, 2004; and AD 74– 

13–03, Amendment 39–2588 (41 FR 17371, 

April 26, 1976) are related to this AD action. 

For the attached torque tube, you may 

consider combining that inspection with the 

requirements of this AD. 

Special Flight Permit 

(k) Special flight permits are permitted 

with the following limitation: flight with 

known cracks is prohibited. 

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 Gregory K. Noles, Aerospace 

Engineer, FAA, Atlanta ACO, 1701 Columbia 

Avenue, College Park, Georgia 30337; phone: 

(404) 474–5551; fax: (404) 474–5606; e-mail: 

gregory.noles@faa.gov. 

(n) For service information identified in 

this AD, contact Piper Aircraft, Inc., 2926 

Piper Drive, Vero Beach, Florida 32960; 

telephone: (772) 567–4361; fax: (772) 978– 

6573; Internet: http://www.newpiper.com/ 

company/publications.asp. You may review 

copies of the referenced service information 

at the FAA, Small Airplane Directorate, 901 

Locust St., Kansas City, Missouri 64106. For 

information on the availability of this 

material at the FAA, call (816) 329–4148. 

Issued in Kansas City, Missouri on June 16, 

2011. 

John Colomy, 

Acting Manager, Small Airplane Directorate, 

Aircraft Certification Service. 

[FR Doc. 2011–15543 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–2011–0569; Directorate 

Identifier 2010–NM–240–AD] 

RIN 2120–AA64 

Airworthiness Directives; BAE 

SYSTEMS (OPERATIONS) LIMITED 

Model BAe 146 and Avro 146–RJ 

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: 

BAE Systems have received reports of inservice failure of the Main Landing Gear 

(MLG) shock absorber lower attachment pin. 

* * * * * 

This condition, if not detected and corrected, 

could lead to a MLG collapse on the ground 

or during landing and consequently damage 

to the aeroplane or injury to the occupants. 

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 

W12–40, 1200 New Jersey Avenue, SE., 

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

p.m., Monday through Friday, except 

Federal holidays. 

For BAE SYSTEMS (OPERATIONS) 

LIMITED service information identified 

in this proposed AD, contact BAE 

SYSTEMS (OPERATIONS) LIMITED, 

Customer Information Department, 

Prestwick International Airport, 

Ayrshire, KA9 2RW, Scotland, United 

Kingdom; telephone +44 1292 675207; 

fax +44 1292 675704; e-mail 

RApublications@baesystems.com; 

Internet http://www.baesystems.com/ 

Businesses/RegionalAircraft/index.htm. 

For Messier-Dowty service 

information identified in this proposed 

AD, contact Messier Services Americas, 

Customer Support Center, 45360 Severn 

Way, Sterling, Virginia 20166–8910; 

telephone 703–450–8233; fax 703–404– 

1621; Internet https://techpubs.services/ 

messier-dowty.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: 

Todd Thompson, Aerospace Engineer, 

International Branch, ANM–116, 

Transport Airplane Directorate, FAA, 

1601 Lind Avenue, SW., Renton, 

Washington 98057–3356; telephone 

(425) 227–1175; 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. 


srobinson on DSK4SPTVN1PROD with PROPOSALS