Federal Register / Vol. 76, No. 151 / Friday, August 5, 2011 / Rules and Regulations 47427 

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 International Branch, send it to ATTN: 

Tom Rodriguez, Aerospace Engineer, 

International Branch, ANM–116, Transport 

Airplane Directorate, FAA, 1601 Lind 

Avenue, SW., Renton, Washington 98057– 

3356; phone: 425–227–1137; fax: 425–227– 

1149. 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 refer to 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 ensure the product is airworthy before it 

is returned to service. 

(3) Special Flight Permits: 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), are 

allowed, if conducted in accordance with a 

method approved by the Manager, ANM–116, 

International Branch, Transport Airplane 

Directorate, FAA. 

Related Information 

(o) For related information, refer to MCAI 

EASA Airworthiness Directive 2011–0114R2, 

dated July 7, 2011, and the service 

information identified in table 1 of this AD. 

TABLE 1—RELATED INFORMATION

Document Revision Date 

Dassault Mandatory Service Bulletin 7X–211, including FCS Data Loading Procedure, Issue D, dated May 

28, 2010, New Standard Installation Checklist, and Appendix A.

2 June 22, 2011. 

Dassault Mandatory Service Bulletin 7X–212 ..................................................................................................... 2 July 7, 2011. 

Dassault Falcon 7X Airplane Flight Manual ........................................................................................................ 12 June 16, 2011. 

Dassault Service Bulletin 7X–213 ....................................................................................................................... .................... June 22, 2011. 

Dassault Aviation, Falcon 7x Maintenance Manual, Falcon 7X—Chapter 5–40–00 after Rev 01 (Commonly 

referred to as Dassault Change Proposal (CP) CP009 to Chapter 5–40–00 of Dassault Falcon 7X Maintenance Manual).

.................... June 10, 2011. 

Material Incorporated by Reference 

(p) You must use the service information 

contained in table 2 of this AD to do the 

actions required by this AD, unless the AD 

specifies otherwise. Appendix A and New 

Standard Installation Checklist of the 

Dassault Mandatory Service Bulletin 7X–211 

are not dated or identified with a document 

number. The document date can only be 

found in the List of Revisions section of the 

Dassault Falcon 7X Airplane Flight Manual. 

(1) The Director of the Federal Register 

approved the incorporation by reference of 

this service information under 5 U.S.C. 

552(a) and 1 CFR part 51. 

(2) For service information identified in 

this AD, contact Dassault Falcon Jet, P.O. Box 

2000, South Hackensack, New Jersey 07606; 

telephone 201–440–6700; Internet http:// 

www.dassaultfalcon.com. 

(3) You may review copies of the 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. 

(4) You may also review copies of the 

service information that is incorporated by 

reference at the National Archives and 

Records Administration (NARA). For 

information on the availability of this 

material at NARA, call 202–741–6030, or go 

to: http://www.archives.gov/federal_register/ 

code_of_federal_regulations/ 

ibr_locations.html. 

TABLE 2—MATERIAL INCORPORATED BY REFERENCE

Document Revision Date 

Dassault Mandatory Service Bulletin 7X–211, including FCS Data Loading Procedure, Issue D, dated May 

28, 2010, New Standard Installation Checklist, and Appendix A.

2 June 22, 2011. 

Dassault Mandatory Service Bulletin 7X–212 ..................................................................................................... 2 July 7, 2011. 

Dassault Falcon 7X Airplane Flight Manual ........................................................................................................ 12 June 16, 2011. 

Dassault Service Bulletin 7X–213 ....................................................................................................................... .................... June 22, 2011. 

Dassault Aviation, Falcon 7x Maintenance Manual, Falcon 7X—Chapter 5–40–00 after Rev 01 (Commonly 

referred to as Dassault Change Proposal (CP) CP009 to Chapter 5–40–00 of Dassault Falcon 7X Maintenance Manual).

.................... June 10, 2011. 

Issued in Renton, Washington, on July 15, 

2011. 

Ali Bahrami, 

Manager, Transport Airplane Directorate, 

Aircraft Certification Service. 

[FR Doc. 2011–19866 Filed 8–4–11; 8:45 am] 

BILLING CODE 4910–13–P 

DEPARTMENT OF TRANSPORTATION 

Federal Aviation Administration 

14 CFR Part 39 

[Docket No. FAA–2011–0041; Directorate 

Identifier 2010–NM–227–AD; Amendment 

39–16764; AD 2011–16–06] 

RIN 2120–AA64 

Airworthiness Directives; The Boeing 

Company Model 747–400 and –400F 

Series Airplanes 

AGENCY: Federal Aviation 

Administration (FAA), DOT. 

ACTION: Final rule. 

SUMMARY: We are adopting a new 

airworthiness directive (AD) for the 

products listed above. This AD requires 

a general visual inspection for cracks 

and holes of the main equipment center 

(MEC) drip shields, and repairs if 

necessary; installation of a fiberglass 

reinforcing overcoat; and, for certain 

airplanes, installation of stiffening 

panels to the MEC drip shields. This AD 

was prompted by a report of a loss of 

bus control unit number 1 and generator 

control units numbers 1 and 2 while the 

airplane was on the ground, and 

multiple operator reports of cracked 


erowe on DSKG8SOYB1PROD with RULES
47428 Federal Register / Vol. 76, No. 151 / Friday, August 5, 2011 / Rules and Regulations 

MEC drip shields. We are issuing this 

AD to prevent water penetration into the 

MEC, which could result in the loss of 

flight critical systems. 

DATES: This AD is effective September 9, 

2011. 

The Director of the Federal Register 

approved the incorporation by reference 

of a certain publication listed in the AD 

as of September 9, 2011. 

ADDRESSES: 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; phone: 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 AD, the regulatory 

evaluation, any comments received, and 

other information. The address for the 

Docket Office (phone: 800–647–5527) is 

Document Management Facility, U.S. 

Department of Transportation, Docket 

Operations, M–30, West Building 

Ground Floor, Room W12–140, 1200 

New Jersey Avenue, SE., Washington, 

DC 20590. 

FOR FURTHER INFORMATION CONTACT: 

Francis Smith, Aerospace Engineer, 

Cabin Safety & Environmental Systems 

Branch, ANM–150S, FAA, Seattle 

Aircraft Certification Office (ACO), 1601 

Lind Avenue, SW., Renton, Washington 

98057–3356; phone: 425–917–6596; fax: 

425–917–6590; e-mail: 

Francis.Smith@faa.gov. 

SUPPLEMENTARY INFORMATION: 

Discussion 

We issued a notice of proposed 

rulemaking (NPRM) to amend 14 CFR 

part 39 to include an airworthiness 

directive (AD) that would apply to the 

specified products. That NPRM 

published in the Federal Register on 

February 10, 2011 (76 FR 7513). The 

NPRM proposed a general visual 

inspection for cracks and holes of the 

main equipment center (MEC) drip 

shields, and repairs if necessary; 

installation of a fiberglass reinforcing 

overcoat; and, for certain airplanes, 

installation of stiffening panels to the 

MEC drip shields. 

Comments 

We gave the public the opportunity to 

participate in developing this AD. The 

following presents the comments 

received on the proposal and the FAA’s 

response to each comment. 

Request To Reference Latest Service 

Bulletin Revision 

Both UPS and Boeing requested that 

we revise the NPRM to require that 

actions be done in accordance with 

Boeing Alert Service Bulletin 747– 

25A3588, Revision 1, dated April 7, 

2011. The NPRM referred to Boeing 

Alert Service Bulletin 747–25A3588, 

dated July 19, 2010, as the appropriate 

source of service information for the 

required actions. 

We agree. Boeing Alert Service 

Bulletin 747–25A3588, Revision 1, 

dated April 7, 2011, removes airplane 

RT101 from this service information 

effectivity and provides operators with 

additional material options. The 

procedures remain unchanged. We 

revised paragraphs (c), (g), (g)(1), and 

(g)(2) in this final rule to refer to Boeing 

Alert Service Bulletin 747–25A3588, 

Revision 1, dated April 7, 2011. We 

added new paragraph (h) to the final 

rule to give credit for actions done 

before the effective date of this AD in 

accordance with Boeing Alert Service 

Bulletin 747–25A3588, dated July 19, 

2010, and re-identified subsequent 

paragraphs accordingly. 

Request To Extend the Compliance 

Time 

UPS stated concern with Boeing’s 

ability to provide adequate modification 

kits to all affected operators within the 

proposed 24-month compliance time. 

UPS justified its concern by stating that 

the NPRM acknowledges it would affect 

an estimated 41 airplanes of U.S. 

registry. UPS stated that worldwide, 

there are more than 150 Model 747– 

400F airplanes that are affected by the 

referenced service information and 

many may attempt to accomplish this 

modification within the 24-month 

compliance time. At the time, Boeing 

had indicated it had materials available 

to produce only 6 kits, and will require 

190 days lead time to replenish the 

stock. As the referenced service 

information specifies to install the parts 

provided in the kit by part number, an 

alternative method of compliance 

(AMOC) would be required for any 

operators needing to fabricate their own 

modification parts from raw materials, if 

Boeing is unable to provide the required 

modification kits in a timely basis for 

the proposed installation. 

We infer that UPS is requesting that 

we extend the proposed compliance 

time. Boeing Alert Service Bulletin 747– 

25A3588, dated July 19, 2010; and 

Revision 1, dated April 7, 2011; were 

both coordinated between Boeing and 

the FAA. Proposed methods of 

compliance and the compliance time 

were weighed versus uncorrected risks 

in determining an acceptable and 

feasible corrective action. Boeing is 

most familiar with its ability to supply 

operators with instructions and kits to 

meet AD compliance, and determined it 

would be capable of reasonably 

achieving a 24-month compliance time 

with the proposed methods, when both 

Boeing Alert Service Bulletin 747– 

25A3588, dated July 19, 2010; and 

Revision 1, dated April 7, 2011; were 

drafted and approved. Although kits 

may not be available immediately for 

every airplane, Boeing has advised us 

that it is capable of creating and 

delivering additional kits for operators 

to use within the AD compliance time. 

Once we issue this AD, any person 

may request approval of an AMOC 

under the provisions of paragraph (i) of 

this AD. We have not changed this AD 

in this regard. 

Conclusion 

We reviewed the relevant data, 

considered the comments received, and 

determined that air safety and the 

public interest require adopting the AD 

with the change described previously. 

We also determined that this change 

will not increase the economic burden 

on any operator or increase the scope of 

the AD. 

Costs of Compliance 

We estimate that this AD affects 41 

airplanes of U.S. registry. 

We estimate the following costs to 

comply with this AD: 


erowe on DSKG8SOYB1PROD with RULES
Federal Register / Vol. 76, No. 151 / Friday, August 5, 2011 / Rules and Regulations 47429 

ESTIMATED COSTS

Action Labor cost Parts cost Cost per 

product 

Cost on U.S. 

operators 

Inspection and installation: Groups 1, 3 (24 

airplanes).

20 work-hours × $85 per hour = $1,700 .......... $1,109 ........ $2,809 $67,416 

Inspection and installation: Group 2 (17 airplanes).17 work-hours × $85 per hour = $1,445 .......... Negligible .... 1,445 24,565 

We estimate the following costs to do 

any necessary repairs that would be 

required based on the results of the 

inspection. We have no way of 

determining the number of aircraft that 

might need these repairs. 

ON-CONDITION COSTS

Action Labor cost Parts cost Cost per airplane 

Hole repair ........................................................ 1 work-hour × $85 per hour = $85 per hole ... Negligible .................... $85 per hole. 

According to the manufacturer, some 

of the costs of this 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 

This AD will not have federalism 

implications under Executive Order 

13132. This AD will 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 that this AD: 

(1) Is not a ‘‘significant regulatory 

action’’ under Executive Order 12866, 

(2) Is not a ‘‘significant rule’’ under 

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. 

Adoption of the Amendment 

Accordingly, under the authority 

delegated to me by the Administrator, 

the FAA amends 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): 

2011–16–06 The Boeing Company: 

Amendment 39–16764; Docket No. 

FAA–2011–0041; Directorate Identifier 

2010–NM–227–AD. 

Effective Date 

(a) This AD is effective September 9, 2011. 

Affected ADs 

(b) None. 

Applicability 

(c) This AD applies to The Boeing 

Company Model 747–400 and –400F series 

airplanes, certificated in any category, as 

identified in Boeing Alert Service Bulletin 

747–25A3588, Revision 1, dated April 7, 

2011. 

Subject 

(d) Joint Aircraft System Component 

(JASC)/Air Transport Association (ATA) of 

America Code 25: Equipment/Furnishings. 

Unsafe Condition 

(e) This AD was prompted by a report of 

a loss of bus control unit number 1 and 

generator control units numbers 1 and 2 

while the airplane was on the ground, and 

multiple operator reports of cracked main 

equipment center (MEC) drip shields. We are 

issuing this AD to prevent water penetration 

into the MEC, which could result in the loss 

of flight critical systems. 

Compliance 

(f) Comply with this AD within the 

compliance times specified, unless already 

done. 

Inspection 

(g) Within 24 months after the effective 

date of this AD, do the actions specified in 

paragraph (g)(1) or (g)(2) of this AD, as 

applicable, in accordance with the 

Accomplishment Instructions of Boeing Alert 

Service Bulletin 747–25A3588, Revision 1, 

dated April 7, 2011. 

(1) For Group 1 and Group 3 airplanes, as 

identified in Boeing Alert Service Bulletin 

747–25A3588, Revision 1, dated April 7, 

2011: Do a general visual inspection of the 

MEC drip shield to detect cracking and holes, 

do all applicable repairs, and install the MEC 

drip shield panel stiffeners and the fiberglass 

reinforcing overcoat to the MEC drip shield, 

in accordance with the Accomplishment 

Instructions of Boeing Alert Service Bulletin 

747–25A3588, Revision 1, dated April 7, 

2011. Do all applicable repairs before further 

flight. 

(2) For Group 2 airplanes, as identified in 

Boeing Alert Service Bulletin 747–25A3588, 

Revision 1, dated April 7, 2011: Do a general 

visual inspection of the MEC drip shield to 

detect cracking and holes, do all applicable 

repairs, and install the fiberglass reinforcing 

overcoat to the MEC drip shield, in 

accordance with the Accomplishment 

Instructions of Boeing Alert Service Bulletin 

747–25A3588, Revision 1, dated April 7, 

2011. Do all applicable repairs before further 

flight. 


erowe on DSKG8SOYB1PROD with RULES
47430 Federal Register / Vol. 76, No. 151 / Friday, August 5, 2011 / Rules and Regulations 

Credit for Actions Accomplished in 

Accordance With Previous Service 

Information 

(h) Accomplishing the actions required in 

paragraph (g) of this AD before the effective 

date of this AD in accordance with Boeing 

Alert Service Bulletin 747–25A3588, dated 

July 19, 2010, is considered acceptable for 

compliance with the corresponding actions 

specified in this AD. 

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-ANMSeattle-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 Francis Smith, Aerospace Engineer, 

Cabin Safety & Environmental Systems 

Branch, ANM–150S, FAA, Seattle Aircraft 

Certification Office (ACO), 1601 Lind 

Avenue, SW., Renton, Washington 98057– 

3356; phone: 425–917–6596 ; fax: 425–917– 

6590; e-mail: Francis.Smith@faa.gov. 

Material Incorporated by Reference 

(k) You must use Boeing Alert Service 

Bulletin 747–25A3588, Revision 1, dated 

April 7, 2011, to do the actions required by 

this AD, unless the AD specifies otherwise. 

(1) The Director of the Federal Register 

approved the incorporation by reference of 

this service information under 5 U.S.C. 

552(a) and 1 CFR part 51. 

(2) 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; phone: 

206–544–5000, extension 1; fax: 206–766– 

5680; e-mail: me.boecom@boeing.com; 

Internet: https://www.myboeingfleet.com. 

(3) You may review copies of the 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. 

(4) You may also review copies of the 

service information that is incorporated by 

reference at the National Archives and 

Records Administration (NARA). For 

information on the availability of this 

material at NARA, call 202–741–6030, or go 

to: http://www.archives.gov/federal_register/ 

code_of_federal_regulations/ 

ibr_locations.html. 

Issued in Renton, Washington, on July 26, 

2011. 

Ali Bahrami, 

Manager, Transport Airplane Directorate, 

Aircraft Certification Service. 

[FR Doc. 2011–19828 Filed 8–4–11; 8:45 am] 

BILLING CODE 4910–13–P 

DEPARTMENT OF TRANSPORTATION 

Federal Aviation Administration 

14 CFR Part 39 

[Docket No. FAA–2011–0388; Directorate 

Identifier 2010–NM–004–AD; Amendment 

39–16761; AD 2011–16–03] 

RIN 2120–AA64 

Airworthiness Directives; Airbus Model 

A300 B4–600, A300 B4–600R, and A300 

F4–600R Series Airplanes, and Model 

A300 C4–605R Variant F Airplanes 

(Collectively Called Model A300–600 

Series Airplanes); Model A310 Series 

Airplanes; Model A318 Series 

Airplanes; Model A319 Series 

Airplanes; Model A320–211, –212, 

–214, –231, –232, and –233 Airplanes; 

Model A321 Series Airplanes; Model 

A330–200 and A330–300 Series 

Airplanes; and Model A340–200, A340– 

300, A340–500, and A340–600 Series 

Airplanes 

AGENCY: Federal Aviation 

Administration (FAA), Department of 

Transportation (DOT). 

ACTION: Final rule. 

SUMMARY: We are adopting a new 

airworthiness directive (AD) for the 

products listed above. This 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. For Model A310 and A300–600 

series airplanes, the MCAI describes the 

unsafe condition as: 

Hamilton Sundstrand (HS), the 

manufacturer of the RAT [ram air turbine], 

reported the failure during a wind tunnel test 

of a balance weight fastening screw on the 

RAT turbine cover. After investigation, it has 

been discovered that a batch of screws, 

which are used to attach the balance washers 

of the HS RAT Turbine Assembly, has not 

been subject to the correct heat treatment and 

are consequently exposed to potential 

fracture. 

This condition, if not corrected, might lead 

to the ejection of screw heads and 

consequently to the detachment of the 

associated balance washers. The loss of 

balance washers could increase RAT 

vibrations, which might lead to a possible 

detachment of RAT parts and consequent 

loss of RAT functionality. The loss of the 

RAT, in combination with a total engine 

flame out, could result in loss of control of 

the aeroplane. 

* * * * * 

For Model A318, A319, A320, and 

A321 series airplanes, the MCAI 

describes the unsafe condition as: 

Hamilton Sundstrand (HS) reported the 

failure of a balance weight fastening screw on 

the RAT turbine cover during a wind tunnel 

test. After investigation, it has been 

discovered that a batch of screws, used to 

attach the balance washers of the RAT 

Turbine assembly, has not received the 

correct heat treatment, making them more 

subject to a potential failure. 

This condition, if left uncorrected, could 

lead to the ejection of screw heads and 

detachment of the associated balance 

washers. The loss of balance washers would 

increase RAT vibrations, which could lead to 

a possible detachment of RAT parts and loss 

of RAT functionality. The loss of the RAT, in 

combination with a double engine failure, or 

a total loss of normal electrical power 

generation, could result in loss of control of 

the aeroplane. 

* * * * * 

For Model A330 and A340 series 

airplanes, the MCAI describes the 

unsafe condition as: 

Hamilton Sundstrand (HS), the 

manufacturer of the RAT, reported the failure 

of a balance weight fastening screw on the 

RAT cover during a wind tunnel test. After 

investigation, it has been discovered that a 

batch of screws, which are used to attach the 

balance washers of the HS RAT turbine lower 

gear box assembly, has not been subject to 

the correct heat treatment and the screws are 

consequently exposed to potential fracture. 

This condition, if not corrected, might lead 

to the ejection of screw heads and 

consequently to the detachment of the 

associated balance washers. The loss of 

balance washers could increase RAT 

vibrations, which might lead to a possible 

detachment of RAT parts, and thus to damage 

to the aeroplane and risk of injury to persons 

on the ground. 

* * * * * 

We are issuing this AD to require 

actions to correct the unsafe condition 

on these products. 

DATES: This AD becomes effective 

September 9, 2011. 

The Director of the Federal Register 

approved the incorporation by reference 

of certain publications listed in this AD 

as of September 9, 2011. 

ADDRESSES: You may examine the AD 

docket on the Internet at http:// 

www.regulations.gov or in person at the 

U.S. Department of Transportation, 

Docket Operations, M–30, West 

Building Ground Floor, Room W12–140, 

1200 New Jersey Avenue, SE., 

Washington, DC. 

FOR FURTHER INFORMATION CONTACT: Dan 

Rodina, Aerospace Engineer, 

International Branch, ANM–116, 


erowe on DSKG8SOYB1PROD with RULES