12624 Federal Register / Vol. 76, No. 45 / Tuesday, March 8, 2011 / Proposed Rules 

method approved in accordance with 

paragraph (y) of this AD. 

(u) For Groups 3, 5, 9, 10, 12, 14, 15, 17, 

18, 19, 20, and 21 airplanes identified in 

Boeing Alert Service Bulletin 737–53A1210, 

Revision 3, dated July 16, 2009: Do the 

actions specified in paragraph (u)(1) or (u)(2) 

of this AD, as applicable. 

(1) For airplanes on which the inspections 

required by paragraph (g) of this AD have 

been done before the effective date of this 

AD: Within 4,500 flight cycles after doing the 

most recent inspection required by paragraph 

(g) of this AD, do external detailed and eddy 

current inspections for horizontal cracks 

along the chem-milled lines of the fuselage 

skin of the fuselage window belt area in 

accordance with Part 2 of the 

Accomplishment Instructions of Boeing Alert 

Service Bulletin 737–53A1210, Revision 3, 

dated July 16, 2009. Repeat the inspections 

thereafter at intervals not to exceed 4,500 

flight cycles. If any cracking is found, before 

further flight, repair in accordance with Part 

8 of Boeing Alert Service Bulletin 737– 

53A1210, Revision 3, dated July 16, 2009, 

except as required by paragraph (x) of this 

AD. 

(2) For airplanes on which the inspections 

required by paragraph (g) of this AD have not 

been done before the effective date of this 

AD: Before the accumulation of 25,000 total 

flight cycles or within 4,500 flight cycles 

after the effective date of this AD, whichever 

is later, do external detailed and eddy current 

inspections for horizontal cracks along the 

chem-milled lines of the fuselage skin of the 

fuselage window belt area in accordance with 

Part 2 of the Accomplishment Instructions of 

Boeing Alert Service Bulletin 737–53A1210, 

Revision 3, dated July 16, 2009. Repeat the 

inspections thereafter at intervals not to 

exceed 4,500 flight cycles. If any cracking is 

found, before further flight, repair in 

accordance with Part 8 of Boeing Alert 

Service Bulletin 737–53A1210, Revision 3, 

dated July 16, 2009, except as required by 

paragraph (x) of this AD. 

Repair and Preventive Modification 

(v) For airplanes on which cracking is 

found during any inspection required by 

paragraph (p), (q), (r), or (s) of this AD, as 

applicable, doing the repair of the chemmilled area in the skin, as specified in Part 

5 or Part 6 of the Accomplishment 

Instructions of Boeing Alert Service Bulletin 

737–53A1210, Revision 3, dated July 16, 

2009, ends the repetitive external detailed 

and eddy current inspections required by 

paragraph (p), (q), (r), or (s) of this AD, as 

applicable, for the repaired area only. 

Note 2: Part 8 of the Accomplishment 

Instructions of Boeing Alert Service Bulletin 

737–53A1210, Revision 3, dated July 16, 

2009, specifies a post-repair inspection of the 

skin chem-milled crack repair at stringer 12; 

that inspection is not required by this AD. 

The damage tolerance inspections specified 

in Table 7 of Boeing Alert Service Bulletin 

737–53A1210, Revision 3, dated July 16, 

2009, may be used in support of compliance 

with section 121.1109(c)(2) or 129.109(c)(2) 

of the Code of Federal Regulations (14 CFR 

121.1109(c)(2) or 14 CFR 129.109(c)(2)). 

(w) For airplanes on which no cracking is 

found during any inspection required by 

paragraph (p) or (q) of this AD, as applicable, 

doing the preventive modification of the 

chem-milled areas in the skin at stringer 

S–12, as specified in Part 7 of the 

Accomplishment Instructions of Boeing Alert 

Service Bulletin 737–53A1210, Revision 3, 

dated July 16, 2009, except as required by 

paragraph (x) of this AD, ends the repetitive 

external detailed and eddy current 

inspections required by paragraph (p) or (q) 

of this AD, as applicable, for the modified 

area only. 

Exception to Boeing Alert Service Bulletin 

737–53A1210, Revision 3 

(x) Where Boeing Alert Service Bulletin 

737–53A1210, Revision 3, dated July 16, 

2009, specifies to contact Boeing for repair 

instructions, before further flight, repair 

using a method approved in accordance with 

paragraph (y) of this AD. 

Alternative Methods of Compliance 

(AMOCs) 

(y)(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. 

(3) An AMOC that provides an acceptable 

level of safety may be used for any repair 

required by this AD if it is approved by the 

Boeing Commercial Airplanes ODA that has 

been authorized by the Manager, Seattle ACO 

to make those findings. For a repair method 

to be approved, the repair must meet the 

certification basis of the airplane, and the 

approval must specifically refer to this AD. 

(4) AMOCs approved previously in 

accordance with AD 2004–18–06, 

Amendment 39–13784, are approved as 

AMOCs for the corresponding provisions of 

this AD. 

Related Information 

(z) For more information about this AD, 

contact Wayne Lockett, Aerospace Engineer, 

Airframe Branch, ANM–120S, FAA, Seattle 

Aircraft Certification Office, 1601 Lind 

Avenue, SW., Renton, Washington 98057– 

3356; telephone (425) 917–6447; fax (425) 

917–6590; e-mail: wayne.lockett@faa.gov. 

Issued in Renton, Washington on February 

22, 2011. 

Kalene C. Yanamura, 

Acting Manager, Transport Airplane 

Directorate, Aircraft Certification Service. 

[FR Doc. 2011–5159 Filed 3–7–11; 8:45 am] 

BILLING CODE 4910–13–P 

DEPARTMENT OF TRANSPORTATION 

Federal Aviation Administration 

14 CFR Part 39 

[Docket No. FAA–2011–0152; Directorate 

Identifier 2010–NM–079–AD] 

RIN 2120–AA64 

Airworthiness Directives; DassaultAviation Model FALCON 7X 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: 

On some Falcon 7X aeroplanes, it has been 

determined potential low clearance between 

electrical wiring or hydraulic pipe and 

nearby structure. Although no in service 

incident has been reported, there is no 

certainty that the minimum clearances would 

be maintained over time. In the worst case, 

interference or contact with structure might 

occur and lead to electrical short circuits or 

fluid leakage, potentially resulting in loss of 

several functions essential for safe flight. 

* * * * * 

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 April 22, 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 service information identified in 

this proposed AD, contact Dassault 

Falcon Jet, P.O. Box 2000, South 

Hackensack, New Jersey 07606; 

telephone 201–440–6700; Internet 

http://www.dassaultfalcon.com. You 

mstockstill on DSKH9S0YB1PROD with PROPOSALS

Federal Register / Vol. 76, No. 45 / Tuesday, March 8, 2011 / Proposed Rules 12625 

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: Tom 

Rodriguez, Aerospace Engineer, 

International Branch, ANM–116, 

Transport Airplane Directorate, FAA, 

1601 Lind Avenue, SW., Renton, 

Washington 98057–3356; telephone 

(425) 227–1137; 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. 

FAA–2011–0152; Directorate Identifier 

2010–NM–079–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 

The European Aviation Safety Agency 

(EASA), which is the Technical Agent 

for the Member States of the European 

Community, has issued EASA 

Airworthiness Directive 2010–0029R1, 

dated November 25, 2010 (referred to 

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

unsafe condition for the specified 

products. The MCAI states: 

On some Falcon 7X aeroplanes, it has been 

determined potential low clearance between 

electrical wiring or hydraulic pipe and 

nearby structure. 

Although no in service incident has been 

reported, there is no certainty that the 

minimum clearances would be maintained 

over time. In the worst case, interference or 

contact with structure might occur and lead 

to electrical short circuits or fluid leakage, 

potentially resulting in loss of several 

functions essential for safe flight. 

Dassault Aviation has developed two 

Service Bulletins (SB) that provide corrective 

actions to ensure the minimum required 

clearance, as well as adequate protection 

between hydraulic pipe (SB n° 0 92) and 

electrical wiring (SB n° 006) and the 

aeroplane structure. 

This AD requires the implementation of 

both SBs on the affected aeroplanes. 

Since issuance of EASA AD 2010–0029, 

Dassault Aviation has developed 

modifications M1036 and M1037. M1036 is 

equivalent to M1007 while M1037 is 

equivalent to M1020. These modifications are 

embodied during production on new 

aeroplanes. 

This [EASA] AD has been revised to 

exclude from the AD applicability the 

aeroplanes on which those modifications are 

embodied. 

Required actions include general 

visual inspections for damage of wiring 

bundles and feeders. Damage includes, 

but is not limited to: signs of overheat, 

discoloration, or damaged and cut 

strands on the cables and insulating 

sleeves. Corrective actions for damage of 

wiring bundles and feeders include 

repairing damage. Other required 

actions include modifying the 

applicable wiring and layout, a general 

visual inspection for absence of marks 

of the rear tank wall at the contact area, 

installing a protective plate on the rear 

tank wall, and installing a hydraulic 

pipe if necessary. If contact marks are 

found, required actions include an eddy 

current inspection or a penetrant 

inspection for cracks, and repair if 

necessary. You may obtain further 

information by examining the MCAI in 

the AD docket. 

Relevant Service Information 

Dassault has issued Mandatory 

Service Bulletin 7X–006, Revision 1, 

dated March 3, 2010; and Mandatory 

Service Bulletin 7X–092, Revision 1, 

dated January 4, 2010. The actions 

described in this service information are 

intended to correct the unsafe condition 

identified in the MCAI. 

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 21 products of U.S. registry. 

We also estimate that it would take 

about 65 work-hours per product to 

comply with the basic requirements of 

this proposed AD. The average labor 

rate is $85 per work-hour. Required 

parts would cost about $0 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 $116,025, or $5,525 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 

mstockstill on DSKH9S0YB1PROD with PROPOSALS

12626 Federal Register / Vol. 76, No. 45 / Tuesday, March 8, 2011 / Proposed Rules 

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 adding 

the following new AD: 

Dassault-Aviation: Docket No. FAA–2011– 

0152; Directorate Identifier 2010–NM– 

079–AD. 

Comments Due Date 

(a) We must receive comments by April 22, 

2011. 

Affected ADs 

(b) None. 

Applicability 

(c) This AD applies to Dassault-Aviation 

Model FALCON 7X airplanes, certificated in 

any category; having serial numbers 2 

through 22 inclusive, 24 through 26 

inclusive, 29, 30, 32 and subsequent; except 

those on which modifications M964, M937, 

M976, M1007 or M1036, M1020 or M1037, 

and M1022 have all been implemented. 

Subject 

(d) Air Transport Association (ATA) of 

America Code 20: Air Frame Wiring; and 

ATA Code 29: Hydraulic Power. 

Reason 

(e) The mandatory continuing 

airworthiness information (MCAI) states: 

On some Falcon 7X aeroplanes, it has been 

determined potential low clearance between 

electrical wiring or hydraulic pipe and 

nearby structure. 

Although no in service incident has been 

reported, there is no certainty that the 

minimum clearances would be maintained 

over time. In the worst case, interference or 

contact with structure might occur and lead 

to electrical short circuits or fluid leakage, 

potentially resulting in loss of several 

functions essential for safe flight. 

* * * * * 

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. 

Inspections and Modification of Wiring and 

Rear Fuel Tank Panel 

(g) Within 10 months or 650 flight hours 

after the effective date of this AD, whichever 

occurs first, do the actions specified in 

paragraphs (g)(1), (g)(2), and (g)(3) of this AD. 

(1) Do a general visual inspection for 

damage of wiring bundles and feeders, in 

accordance with the Accomplishment 

Instructions of Dassault Mandatory Service 

Bulletin 7X–006, Revision 1, dated March 3, 

2010. If any damage is found, before further 

flight, repair, in accordance with Dassault 

Mandatory Service Bulletin 7X–006, Revision 

1, dated March 3, 2010. 

(2) Modify the applicable wiring and 

layout, in accordance with the 

Accomplishment Instructions of Dassault 

Mandatory Service Bulletin 7X–006, Revision 

1, dated March 3, 2010. 

(3) Do a general visual inspection for 

absence of marks on the rear tank wall at the 

contact area, in accordance with the 

Accomplishment Instructions of Dassault 

Mandatory Service Bulletin 7X–092, Revision 

1, dated January 4, 2010. 

(i) If no contact marks are found during the 

inspection required by paragraph (g)(3) of 

this AD, before further flight, modify the 

protective plate, and install a hydraulic pipe 

as applicable, in accordance with the 

Accomplishment Instructions of Dassault 

Mandatory Service Bulletin 7X–092, Revision 

1, dated January 4, 2010. 

(ii) If any contact marks are found during 

the inspection required by paragraph (g)(3) of 

this AD, before further flight, do either an 

eddy current inspection for cracks or a 

penetrant inspection for cracks, in 

accordance with the Accomplishment 

Instructions of Dassault Mandatory Service 

Bulletin 7X–092, Revision 1, dated January 4, 

2010. 

(A) If no crack is detected during any 

inspection required by paragraph (g)(3)(ii) of 

this AD, before further flight, do paragraph 

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

(B) If any crack is detected during any 

inspection required in paragraph (g)(3)(ii) of 

this AD, before further flight, repair the crack 

using a method approved by either the 

Manager, International Branch, ANM–116, 

Transport Airplane Directorate, FAA; or the 

European Aviation Safety Agency (EASA) (or 

its delegated agent); and modify the 

protective plate, and install a hydraulic pipe 

as applicable, in accordance with the 

Accomplishment Instructions of Dassault 

Mandatory Service Bulletin 7X–092, Revision 

1, dated January 4, 2010. 

Credit for Actions Accomplished in 

Accordance With Previous Service 

Information 

(h) Doing a general visual inspection for 

damage, repairing wiring bundles and 

feeders, and modifying the applicable wiring 

and layout, in accordance with Dassault 

Mandatory Service Bulletin 7X–006, dated 

December 18, 2009; and doing a general 

visual inspection for absence of marks on the 

rear tank wall at the contact area, modifying 

the protective plate, installing a hydraulic 

pipe as applicable, and doing either an eddy 

current inspection for cracks or a penetrant 

inspection for cracks, in accordance with 

Dassault Mandatory Service Bulletin 7X–092, 

dated July 17, 2009; before the effective date 

of this AD is acceptable for compliance with 

the corresponding actions required by 

paragraphs (g)(1), (g)(2), and (g)(3) of this AD. 

FAA AD Differences 

Note 1: This AD differs from the MCAI 

and/or service information as follows: No 

differences. 

Other FAA AD Provisions 

(i) The following provisions also apply to 

this AD: 

(1) Alternative Methods of Compliance 

(AMOCs): The Manager, International 

Branch, ANM–116, Transport Airplane 

Directorate, FAA, has the authority to 

approve AMOCs for this AD, if requested 

using the procedures found in 14 CFR 39.19. 

Send information to ATTN: Tom Rodriguez, 

Aerospace Engineer, International Branch, 

ANM–116, Transport Airplane Directorate, 

FAA, 1601 Lind Avenue, SW., Renton, 

Washington 98057–3356; telephone (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 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 

(j) Refer to MCAI EASA Airworthiness 

Directive 2010–0029R1, dated November 25, 

mstockstill on DSKH9S0YB1PROD with PROPOSALS

Federal Register / Vol. 76, No. 45 / Tuesday, March 8, 2011 / Proposed Rules 12627 

2010; Dassault Mandatory Service Bulletin 

7X–006, Revision 1, dated March 3, 2010; 

and Dassault Mandatory Service Bulletin 7X– 

092, Revision 1, dated January 4, 2010; for 

related information. 

Issued in Renton, Washington, on February 

22, 2011. 

Kalene C. Yanamura, 

Acting Manager, Transport Airplane 

Directorate, Aircraft Certification Service. 

[FR Doc. 2011–5165 Filed 3–7–11; 8:45 am] 

BILLING CODE 4910–13–P 

DEPARTMENT OF TRANSPORTATION 

Federal Aviation Administration 

14 CFR Part 39 

[Docket No. FAA–2011–0185; Directorate 

Identifier 2011–CE–002–AD] 

RIN 2120–AA64 

Airworthiness Directives; Diamond 

Aircraft Industries GmbH Models DA 

42, DA 42 NG, and DA 42 M–NG 

Airplanes 

AGENCY: Federal Aviation 

Administration (FAA), Department of 

Transportation (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: 

Since 2004, more than 30 reports have 

been received of in-flight loss of a rear 

passenger door on Diamond aeroplanes, the 

majority of which were DA 40. In additional, 

at least 18 doors have been replaced because 

of damage found on the hinge. 

Diamond Aircraft Industries conducted 

analyses and structural tests to determine the 

root cause of the door opening in flight. The 

conclusions were that the primary locking 

mechanism provided adequate strength to 

react to the loads in flight. It was also 

determined that the root cause was the crew 

not properly securing the rear passenger door 

by the main locking mechanism, prior to 

flight. Damage to the hinges has been caused 

primarily by external loads (wind gust 

conditions) while the aeroplane was parked. 

All DA 40 and DA 42 aeroplanes have a 

system installed that provides a warning if 

the main door latch is not fully closed and 

a secondary safety latch (with retaining 

bracket) design feature. The initial intended 

design function of the latch was to hold the 

rear passenger door in the ‘‘near closed’’ 

position while on the ground, protecting the 

door from wind gusts. However, the original 

retaining bracket Part Number (P/N) DA4– 

5200–00–69 might not hold the door in this 

‘‘near closed’’ position while in flight * * *. 

This condition, if not corrected, could 

result in the rear passenger door opening and 

departing the aeroplane in flight. 

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 April 22, 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 W12–140, 1200 New Jersey 

Avenue, SE., Washington, DC 20590, 

between 9 a.m. and 5 p.m., Monday 

through Friday, except Federal holidays. 

For service information identified in 

this proposed AD, contact Diamond 

Aircraft Industries GmbH, N.A. OttoStra+e 5, A–2700 Wiener Neustadt, 

Austria, telephone: +43 2622 26700; fax: 

+43 2622 26780; e-mail: 

office@diamond-air.at; Internet: http:// 

www.diamond-air.at. You may review 

copies of the referenced service 

information at the FAA, Small Airplane 

Directorate, 901 Locust, 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 

(telephone (800) 647–5527) is in the 

ADDRESSES section. Comments will be 

available in the AD docket shortly after 

receipt. 

FOR FURTHER INFORMATION CONTACT: 

Mike Kiesov, Aerospace Engineer, FAA, 

Small Airplane Directorate, 901 Locust, 

Room 301, Kansas City, Missouri 64106; 

telephone: (816) 329–4144; fax: (816) 

329–4090; e-mail: mike.kiesov@faa.gov. 

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–2011–0185; Directorate Identifier 

2011–CE–002–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 

The European Aviation Safety Agency 

(EASA), which is the Technical Agent 

for the Member States of the European 

Community, has issued AD No. 2010– 

0235, dated November 10, 2010 

(referred to after this as ‘‘the MCAI’’), to 

correct an unsafe condition for the 

specified products. The MCAI states: 

Since 2004, more than 30 reports have 

been received of in-flight loss of a rear 

passenger door on Diamond aeroplanes, the 

majority of which were DA 40. In additional, 

at least 18 doors have been replaced because 

of damage found on the hinge. 

Diamond Aircraft Industries conducted 

analyses and structural tests to determine the 

root cause of the door opening in flight. The 

conclusions were that the primary locking 

mechanism provided adequate strength to 

react to the loads in flight. It was also 

determined that the root cause was the crew 

not properly securing the rear passenger door 

by the main locking mechanism, prior to 

flight. Damage to the hinges has been caused 

primarily by external loads (wind gust 

conditions) while the aeroplane was parked. 

All DA 40 and DA 42 aeroplanes have a 

system installed that provides a warning if 

the main door latch is not fully closed and 

a secondary safety latch (with retaining 

bracket) design feature. The initial intended 

design function of the latch was to hold the 

rear passenger door in the ‘‘near closed’’ 

position while on the ground, protecting the 

door from wind gusts. However, the original 

retaining bracket Part Number (P/N) DA4– 

5200–00–69 might not hold the door in this 

‘‘near closed’’ position while in flight. To 

address this problem, DAI have designed an 

improved retaining bracket, P/N DA4–5200– 

00–69–SB, which has been satisfactory tested 

to hold the door closed in flight. In addition, 

DAI have revised the Airplane Flight Manual 

(AFM) emergency door unlocked/open 

procedure. 

mstockstill on DSKH9S0YB1PROD with PROPOSALS