This section of the FEDERAL REGISTER

contains notices to the public of the proposed

issuance of rules and regulations. The

purpose of these notices is to give interested

persons an opportunity to participate in the

rule making prior to the adoption of the final

rules.

Proposed Rules Federal Register

33173 

Vol. 76, No. 110 

Wednesday, June 8, 2011 

NUCLEAR REGULATORY 

COMMISSION 

10 CFR Part 35 

[NRC–2008–0071 and NRC–2008–0175] 

RIN 3150–AI26, 3150–AI63 

Medical Use Regulations 

AGENCY: Nuclear Regulatory 

Commission. 

ACTION: Availability of preliminary draft 

rule language and notice of public 

workshops; correction. 

SUMMARY: This document corrects 

another document that was published in 

the Federal Register on May 20, 2011 

(76 FR 29171). That document 

announces plans to hold public 

workshops to solicit comments on 

certain issues under consideration to 

amend the medical use regulations, 

provides the date of the first of the two 

public workshops, and notices the 

availability of preliminary draft rule 

language concerning the U.S. Nuclear 

Regulatory Commission’s (NRC) 

proposed amendments to the medical 

use regulations. This document is 

necessary to correct a Regulatory 

Identifier Number (RIN) that appears in 

the heading, and to add additional 

information regarding the availability of 

the preliminary draft rule language. 

FOR FURTHER INFORMATION CONTACT: 

Cindy Bladey, Chief, Rules, 

Announcements, and Directives Branch, 

Office of Administration, Nuclear 

Regulatory Commission, Washington, 

DC 20555–0001, e-mail: 

Cindy.Bladey@nrc.gov, telephone: 301– 

492–3667. 

SUPPLEMENTARY INFORMATION: At the top 

of the first column of Page 29171 of 

Federal Register document 2011–12048, 

published on May 20, 2011 (76 FR 

29171), in the heading of the document, 

‘‘RIN 3150–AI28’’ is corrected to read 

‘‘RIN 3150–AI26’’. 

Also, in the ‘‘Background Information’’ 

section, at the top of the first column of 

Page 29176 of the same document, 

before the last paragraph of the 

document, add the following three 

paragraphs: 

The NRC is making a preliminary 

version of this draft rule language 

available to inform stakeholders of the 

current status of this proposed 

rulemaking. The NRC is inviting 

stakeholders to comment on the 

preliminary draft rule language. The 

preliminary draft rule language may be 

subject to significant revisions during 

the rulemaking process prior to 

publication for formal comment as a 

proposed rule. Public input at this stage 

will help inform the development of the 

proposed rule. 

The NRC will review and consider 

any comments received; however, the 

NRC will not formally respond to any 

comments received at this prerulemaking stage. As appropriate, the 

Statement of Considerations for the 

proposed rule may briefly discuss any 

substantive changes made to the 

proposed rule language as a result of 

comments received on this preliminary 

version. Stakeholders will also have an 

additional opportunity to comment on 

the rule language when it is published 

as a proposed rule in accordance with 

the provisions of the Administrative 

Procedures Act. The NRC will respond 

to such comments in the Statement of 

Considerations for the final rule. 

The NRC may post updates to the 

preliminary proposed rule language on 

the Federal rulemaking Web site under 

Docket ID NRC–2008–0175. 

Regulations.gov allows members of the 

public to set-up e-mail alerts so that 

they may be notified when documents 

are added to a docket. Users are notified 

via e-mail at an e-mail address provided 

at the time of registration for the 

notification. Directions for signing up 

for the e-mail alerts can be found at 

http://www.regulations.gov. To do so, 

navigate to a docket folder you are 

interested in and then click the ‘‘Sign up 

for E-mail Alerts’’ link. 

Dated at Rockville, Maryland, this 3rd day 

of June, 2011. 

For the Nuclear Regulatory Commission. 

Leslie Terry, 

Acting Chief, Rules, Announcements, and 

Directives Branch, Division of Administrative 

Services, Office of Administration. 

[FR Doc. 2011–14060 Filed 6–7–11; 8:45 am] 

BILLING CODE 7590–01–P 

DEPARTMENT OF TRANSPORTATION 

Federal Aviation Administration 

14 CFR Part 39 

[Docket No. FAA–2011–0479; Directorate 

Identifier 2010–NM–154–AD] 

RIN 2120–AA64 

Airworthiness Directives; Bombardier 

Inc. Model DHC–8–102, –103, –106, 

–201, –202, –301, –311, and –315 

Airplanes; Equipped With Certain 

Cockpit Door Installations 

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 that would 

supersede an existing AD. 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: 

During structural testing of the cockpit 

door, it was observed that the door lower 

hinge block rotated which resulted in 

disengagement of the mating hinge pin and 

excessive door deflection. The lower hinge 

block rotated because it was attached to its 

support structure with only one attachment 

bolt, which prevented it from reacting to any 

moment force. This condition, if not 

corrected could result in breakage and 

uncontrolled release of the cockpit door 

under certain decompression situations. 

After incorporation of Modsum 8Q900267 

* * *, an operator reported a failure to 

complete the cockpit door removal function 

test. This condition, if not corrected, could 

result in the inability to remove the cockpit 

door for emergency egress. * * * 

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 July 25, 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 


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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 service information identified in 

this proposed AD, contact Bombardier 

Inc., Q–Series Technical Help Desk, 123 

Garratt Boulevard, Toronto, Ontario 

M3K 1Y5, Canada; telephone 416–375– 

4000; fax 416–375–4539; e-mail 

thd.qseries@aero.bombardier.com; 

Internet http://www.bombardier.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: 

Andreas Rambalakos, Aerospace 

Engineer, Airframe and Mechanical 

Systems Branch, ANE–171, FAA, New 

York Aircraft Certification Office, 1600 

Stewart Avenue, Suite 410, Westbury, 

New York 11590; telephone (516) 228– 

7345; fax (516) 794–5531. 

SUPPLEMENTARY INFORMATION: 

Comments Invited 

We invite you to send any written 

relevant data, views, or arguments about 

this proposed AD. Send your comments 

to an address listed under the 

ADDRESSES section. Include ‘‘Docket No. 

FAA–2011–0479; Directorate Identifier 

2010–NM–154–AD’’ at the beginning of 

your comments. We specifically invite 

comments on the overall regulatory, 

economic, environmental, and energy 

aspects of this proposed AD. We will 

consider all comments received by the 

closing date and may amend this 

proposed AD based on those comments. 

We will post all comments we 

receive, without change, to http:// 

www.regulations.gov, including any 

personal information you provide. We 

will also post a report summarizing each 

substantive verbal contact we receive 

about this proposed AD. 

Discussion 

On June 5, 2006, we issued AD 2006– 

12–16, Amendment 39–14642 (71 FR 

34006, June 13, 2006). That AD required 

actions intended to address an unsafe 

condition on the products listed above. 

Since we issued AD 2006–12–16, an 

operator reported a failure to complete 

the cockpit door removal function test. 

This condition, if not corrected, could 

result in the inability to remove the 

cockpit door for emergency egress. The 

Transport Canada Civil Aviation 

(TCCA), which is the aviation authority 

for Canada, has issued Canadian 

Airworthiness Directive CF–2005–34R1, 

dated August 15, 2007 (referred to after 

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

condition for the specified products. 

The MCAI states: 

During structural testing of the cockpit 

door, it was observed that the door lower 

hinge block rotated which resulted in 

disengagement of the mating hinge pin and 

excessive door deflection. The lower hinge 

block rotated because it was attached to its 

support structure with only one attachment 

bolt, which prevented it from reacting to any 

moment force. This condition, if not 

corrected could result in breakage and 

uncontrolled release of the cockpit door 

under certain decompression situations. 

After incorporation of Modsum 8Q900267 

* * *, an operator reported a failure to 

complete the cockpit door removal function 

test. This condition, if not corrected, could 

result in the inability to remove the cockpit 

door for emergency egress. Therefore, * * * 

this [Canadian] directive is issued to require 

rework of the cockpit door striker plate and 

replacement of the latch block for the 

affected aircraft serial numbers. * * * 

You may obtain further information by 

examining the MCAI in the AD docket. 

Relevant Service Information 

Bombardier Inc. has issued Service 

Bulletins 8–52–58, Revision A, dated 

November 17, 2006; and 8–52–61, dated 

October 20, 2006. The actions described 

in this service information are intended 

to correct the unsafe condition 

identified in the MCAI. 

Change to Table 3 of the Existing AD 

We have revised Table 3 of the 

existing AD to remove reference to 

Bombardier Series 100/300 Modification 

Summary (Modsums) 8Q200015, 

8Q420101, and 8Q420143 in the column 

labeled ‘‘One approved method for 

doing these actions.’’ However, we have 

approved De Havilland Aircraft of 

Canada, Limited, Modification 8/2337 

as an additional source of guidance for 

reworking the cockpit door emergency 

release. We have approved De Havilland 

Aircraft of Canada, Limited, 

Modification 8/3339 as an additional 

source of guidance for installing a new 

label regarding the alternate release of 

the door. We have also approved 

Bombardier Series 100/300 Modsum 

8Q200015 as an additional source of 

guidance for installing the cockpit door. 

Operators may contact the Manager, 

New York Aircraft Certification Office, 

ANE–170, for information regarding the 

use of Bombardier Series 100/300 

Modsum 8Q200015 for installing the 

cockpit door, as required by paragraph 

(h) of this AD. We have not included 

Bombardier Series 100/300 Modsums 

8Q420101 and 8Q420143 in this AD 

because they are optional installations 

of the emergency locator transmitter and 

blow-out panel on the cockpit door and 

were done during production. 

FAA’s Determination and Requirements 

of This Proposed AD 

This product has been approved by 

the aviation authority of another 

country, and is approved for operation 

in the United States. Pursuant to our 

bilateral agreement with the State of 

Design Authority, we have been notified 

of the unsafe condition described in the 

MCAI and service information 

referenced above. We are proposing this 

AD because we evaluated all pertinent 

information and determined an unsafe 

condition exists and is likely to exist or 

develop on other products of the same 

type design. 

Differences Between This AD and the 

MCAI or Service Information 

We have reviewed the MCAI and 

related service information and, in 

general, agree with their substance. But 

we might have found it necessary to use 

different words from those in the MCAI 

to ensure the AD is clear for U.S. 

operators and is enforceable. In making 

these changes, we do not intend to differ 

substantively from the information 

provided in the MCAI and related 

service information. 

We might also have proposed 

different actions in this AD from those 

in the MCAI in order to follow FAA 

policies. Any such differences are 

highlighted in a Note within the 

proposed AD. 

Costs of Compliance 

Based on the service information, we 

estimate that this proposed AD would 

affect about 17 products of U.S. registry. 

The actions that are required by AD 

2006–12–16 and retained in this 

proposed AD take between 3 and 6 

work-hours per product, depending on 


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the airplane configuration, at an average 

labor rate of $85 per work hour. 

Required parts cost about $2,000 per 

product. Based on these figures, the 

estimated cost of the currently required 

actions is between $2,255 and $2,510 

per product. 

We estimate that it would take about 

3 work-hours per product to comply 

with the new basic requirements of this 

proposed AD. The average labor rate is 

$85 per work-hour. Required parts 

would cost about $2,000 per product. 

Where the service information lists 

required parts costs that are covered 

under warranty, we have assumed that 

there will be no charge for these costs. 

As we do not control warranty coverage 

for affected parties, some parties may 

incur costs higher than estimated here. 

Based on these figures, we estimate the 

cost of the proposed AD on U.S. 

operators to be $38,335, or $2,255 per 

product. 

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); and 

3. Will not have a significant 

economic impact, positive or negative, 

on a substantial number of small entities 

under the criteria of the Regulatory 

Flexibility Act. 

We prepared a regulatory evaluation 

of the estimated costs to comply with 

this proposed AD and placed it in the 

AD docket. 

List of Subjects in 14 CFR Part 39 

Air transportation, Aircraft, Aviation 

safety, Incorporation by reference, 

Safety. 

The Proposed Amendment 

Accordingly, under the authority 

delegated to me by the Administrator, 

the FAA proposes to amend 14 CFR part 

39 as follows: 

PART 39—AIRWORTHINESS 

DIRECTIVES 

1. The authority citation for part 39 

continues to read as follows: 

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

§ 39.13 [Amended] 

2. The FAA amends § 39.13 by 

removing Amendment 39–14642 (71 FR 

34006, June 13, 2006) and adding the 

following new AD: 

Bombardier Inc.: Docket No. FAA–2011– 

0479; Directorate Identifier 2010–NM–154– 

AD. 

Comments Due Date 

(a) We must receive comments by July 25, 

2011. 

Affected ADs 

(b) This AD supersedes AD 2006–12–16, 

Amendment 39–14642. 

Applicability 

(c) This AD applies to Bombardier Model 

DHC–8–102, –103, –106, –201, –202, –301, 

–311, and –315 airplanes, certificated in any 

category; serial numbers (S/Ns) 003 through 

557 inclusive; equipped with cockpit door 

installation part numbers (P/Ns) identified in 

Table 1 of this AD. 

TABLE 1—COCKPIT DOOR

INSTALLATIONS AFFECTED BY THIS AD 

P/N Dash number(s) 

82510074 ....... All 

82510294 ....... All 

82510310 ....... –001 

8Z4597 ........... –001 

H85250010 .... All 

82510700 ....... All 

82510704 ....... All except –502 and –503 

Subject 

(d) Air Transport Association (ATA) of 

America Code 52: Doors. 

Reason 

(e) The mandatory continuing 

airworthiness information (MCAI) states: 

During structural testing of the cockpit 

door, it was observed that the door lower 

hinge block rotated which resulted in 

disengagement of the mating hinge pin and 

excessive door deflection. The lower hinge 

block rotated because it was attached to its 

support structure with only one attachment 

bolt, which prevented it from reacting to any 

moment force. This condition, if not 

corrected could result in breakage and 

uncontrolled release of the cockpit door 

under certain decompression situations. 

After incorporation of Modsum 8Q900267 

* * * an operator reported a failure to 

complete the cockpit door removal function 

test. This condition, if not corrected, could 

result in the inability to remove the cockpit 

door for emergency egress. * * * 

Compliance 

(f) You are responsible for having the 

actions required by this AD performed within 

the compliance times specified, unless the 

actions have already been done. 

Restatement of Requirements of AD 2006– 

12–16, With New Service Information 

Modification 

(g) Within 24 months after July 18, 2006 

(the effective date of AD 2006–12–16), 

modify the cockpit door from a single-point 

attachment to a two-point attachment in 

accordance with the Accomplishment 

Instructions of the applicable service bulletin 

in Table 2 of this AD. For airplane serial 

numbers 452, 464, 490, 506, and 508 through 

557 inclusive: After the effective date of this 

AD, use Bombardier Service Bulletin 8–52– 

58, Revision A, dated November 17, 2006. 

TABLE 2—BOMBARDIER SERVICE BULLETINS FOR MODIFICATION REQUIRED BY PARAGRAPH (G) OF THIS AD 

Use this Bombardier Service Bulletin— For airplane serial numbers— 

8–52–54, Revision A, dated November 5, 2004 ...................................... 003 through 451 inclusive, 453 through 463 inclusive, 465 through 489 

inclusive, 491 through 505 inclusive, and 507. 

8–52–58, dated May 12, 2004, or Revision A, dated November 17, 

2006.

452, 464, 490, 506, and 508 through 557 inclusive. 


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Note 1: Bombardier Service Bulletin 8–52– 

54 refers to Bombardier Series 100/300 

Modification Summary (Modsum) 8Q100859 

as an additional source of guidance for 

installing a hinge pin with a two-point 

attachment. Bombardier Service Bulletin 8– 

52–58 refers to Bombardier Series 100/300 

Modsum 8Q900267 as an additional source 

of guidance for reworking and installing the 

cockpit door, and reworking the lower hinge 

attachment to provide a downward-facing 

pin with a two-point attachment. 

Prior/Concurrent Requirements 

(h) Prior to or concurrently with the 

modification in paragraph (g) of this AD, do 

the applicable actions specified in Table 3 of 

this AD, according to a method approved by 

either the Manager, New York Aircraft 

Certification (ACO), FAA; or Transport 

Canada Civil Aviation (TCCA) (or its 

delegated agent). 

TABLE 3—BOMBARDIER SERVICE BULLETINS FOR REQUIREMENTS OF PARAGRAPH (H) OF THIS AD 

For airplanes affected by Bombardier Service 

Bulletin— That have these serial numbers— Do these actions— 

8–52–54, Revision A, dated November 5, 2004 003 through 407 inclusive, 409 through 412 

inclusive, and 414 through 433 inclusive.

Rework the cockpit door emergency release. 

.......................................................................... Install a new label regarding alternate release 

of the door. 

8–52–58, dated May 12, 2004 ........................... 452, 464, 490, 506, and 508 through 557 inclusive.Install the cockpit door. 

Note 2: Bombardier Service Bulletin 8–52– 

54, Revision A, dated November 5, 2004, 

refers to De Havilland Aircraft of Canada, 

Limited, Modification 8/2337 as an 

additional source of guidance for reworking 

the cockpit door emergency release; and 

Modification 8/3339 as additional source of 

guidance for installing a new label regarding 

alternate release of the door, on airplanes 

having serial numbers 003 through 407 

inclusive, 409 through 412 inclusive, and 414 

through 433 inclusive. 

Note 3: Bombardier Service Bulletin 8–52– 

58, dated May 12, 2004; and Revision A, 

dated November 17, 2006; refer to 

Bombardier Modsum 8Q200015, as an 

additional source of guidance for installing 

the cockpit door, on airplanes having serial 

numbers 452, 464, 490, 506, and 508 through 

557 inclusive. 

Actions Done In Accordance With Previous 

Revision of Service Bulletin 

(i) Actions done before July 18, 2006, in 

accordance with Bombardier Service Bulletin 

8–52–54, dated May 12, 2004, are acceptable 

for compliance with the corresponding 

requirements in paragraph (g) of this AD. 

New Requirements of This AD 

(j) For airplanes having S/N 452, 464, 490, 

506, and 508 through 557 inclusive, and on 

which the requirements in paragraph (g) of 

this AD have been done as of the effective 

date of this AD: Within 12 months after the 

effective date of this AD rework the cockpit 

door striker plate and replace the latch block, 

in accordance with the Accomplishment 

Instructions of Bombardier Service Bulletin 

8–52–61, dated October 20, 2006. 

(k) For airplanes having S/Ns 452, 464, 

490, 506, and 508 through 557 inclusive, and 

on which the requirements in paragraph (g) 

of this AD have not been done as of the 

effective date of this AD: Prior to or 

concurrently with doing the modification 

required in paragraph (g) of this AD, rework 

the cockpit door striker plate and replace the 

latch block, in accordance with the 

Accomplishment Instructions of Bombardier 

Service Bulletin 8–52–61, dated October 20, 

2006. 

FAA AD Differences 

Note 4: This AD differs from the MCAI 

and/or service information as follows: No 

differences. 

Other FAA AD Provisions 

(l) The following provisions also apply to 

this AD: 

(1) Alternative Methods of Compliance 

(AMOCs): The Manager, New York Aircraft 

Certification Office, ANE–170, 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 ACO, send it to ATTN: Program 

Manager, Continuing Operational Safety, 

FAA, New York ACO, 1600 Stewart Avenue, 

Suite 410, Westbury, New York 11590; 

telephone 516–228–7300; fax 516–794–5531. 

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 

(m) Refer to MCAI Canadian Airworthiness 

Directive CF–2005–34R1, dated August 15, 

2007; Bombardier Service Bulletin 8–52–54, 

Revision A, dated November 5, 2004; 

Bombardier Service Bulletin 8–52–58, 

Revision A, dated November 17, 2006; and 

Bombardier Service Bulletin 8–52–61, dated 

October 20, 2006; for related information. 

Issued in Renton, Washington, on May 27, 

2011. 

Ali Bahrami, 

Manager, Transport Airplane Directorate, 

Aircraft Certification Service. 

[FR Doc. 2011–14091 Filed 6–7–11; 8:45 am] 

BILLING CODE 4910–13–P 

DEPARTMENT OF TRANSPORTATION 

Federal Aviation Administration 

14 CFR Part 39 

[Docket No. FAA–2011–0478; Directorate 

Identifier 2010–NM–138–AD] 

RIN 2120–AA64 

Airworthiness Directives; Airbus Model 

A300 B4–103, B4–203, and B4–2C 

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 that would 

supersede an existing AD. 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: 

One operator reported a failure of the MLG 

[main landing gear] retraction actuator 

sliding rod. This incident occurred at a 

number of operating flight cycles lower than 

the limit value imposed by the MLG 

manufacturer. 

This condition, if not detected and 

corrected, results in undampened extension 

of the MLG, leading to higher than usual 

loads on the MLG attachment. Higher loads 


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