3352 Federal Register / Vol. 72, No. 16 / Thursday, January 25, 2007 / Rules and Regulations 

products identified in this rulemaking 

action. 

Regulatory Findings 

We have determined that 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); 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 AD and placed it in the AD docket. 

See the ADDRESSES section for a location 

to examine the regulatory evaluation. 

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 Federal Aviation 

Administration (FAA) amends § 39.13 

by adding the following new 

airworthiness directive (AD): 

2007–02–15 Empresa Brasileira De 

Aeronautica S.A. (EMBRAER): 

Amendment 39–14902. Docket No. 

FAA–2006–25889; Directorate Identifier 

2006–NM–168–AD. 

Effective Date 

(a) This AD becomes effective March 1, 

2007. 

Affected ADs 

(b) None. 

Applicability 

(c) This AD applies to EMBRAER Model 

ERJ 170–100 LR, –100 STD, –100 SE, and 

–100 SU airplanes, certificated in any 

category; serial numbers 17000007, 

17000033, 17000034, 17000036 through 

17000046 inclusive, and 17000050 through 

17000067 inclusive. 

Unsafe Condition 

(d) This AD results from failure of an 

electrical bonding clamp, used to attach the 

electrical bonding straps to the fuel system 

lines. We are issuing this AD to prevent loss 

of bonding protection in the interior of the 

fuel tanks or adjacent areas that, in 

combination with lightning strike, could 

result in a fuel tank explosion and 

consequent loss of the airplane. 

Compliance 

(e) You are responsible for having the 

actions required by this AD performed within 

the compliance times specified, unless the 

actions have already been done. 

Replacement 

(f) Within 6,600 flight hours after the 

effective date of this AD: Replace all 

electrical bonding clamps having part 

number AN735D4 or AN735D6 with new 

clamps and replace the attaching hardware 

with new or serviceable attaching hardware, 

and do the other specified action, by 

accomplishing all of the actions specified in 

the Accomplishment Instructions of 

EMBRAER Service Bulletin 170–28–0009, 

Revision 01, dated February 23, 2006. The 

other specified action must be done before 

further flight. 

Credit for Previous Service Bulletin 

(g) Actions done before the effective date 

of this AD in accordance with EMBRAER 

Service Bulletin 170–28–0009, dated 

December 30, 2005, are acceptable for 

compliance with the requirements of 

paragraph (f) of this AD. 

Alternative Methods of Compliance 

(AMOCs) 

(h)(1) The Manager, International Branch, 

ANM–116, Transport Airplane Directorate, 

FAA, has the authority to approve AMOCs 

for this AD, if requested in accordance with 

the procedures found in 14 CFR 39.19. 

(2) Before using any AMOC approved in 

accordance with § 39.19 on any airplane to 

which the AMOC applies, notify the 

appropriate principal inspector in the FAA 

Flight Standards Certificate Holding District 

Office. 

Related Information 

(i) Brazilian airworthiness directive 2006–

06–03, effective July 7, 2006, also addresses 

the subject of this AD. 

Material Incorporated by Reference 

(j) You must use EMBRAER Service 

Bulletin 170–28–0009, Revision 01, dated 

February 23, 2006, to perform the actions that 

are required by this AD, unless the AD 

specifies otherwise. The Director of the 

Federal Register approved the incorporation 

by reference of this document in accordance 

with 5 U.S.C. 552(a) and 1 CFR part 51. 

Contact Empresa Brasileira de Aeronautica 

S.A. (EMBRAER), P.O. Box 343—CEP 12.225, 

Sao Jose dos Campos—SP, Brazil, for a copy 

of this service information. You may review 

copies at the Docket Management Facility, 

U.S. Department of Transportation, 400 

Seventh Street, SW., Room PL–401, Nassif 

Building, Washington, DC; on the Internet at 

http://dms.dot.gov; or at the National 

Archives and Records Administration 

(NARA). For information on the availability 

of this material at the 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 January 

11, 2007. 

Kevin M. Mullin, 

Acting Manager, Transport Airplane 

Directorate, Aircraft Certification Service. 

[FR Doc. E7–899 Filed 1–24–07; 8:45 am] 

BILLING CODE 4910–13–P 

DEPARTMENT OF TRANSPORTATION 

Federal Aviation Administration 

14 CFR Part 39 

[Docket No. FAA–2006–25328; Directorate 

Identifier 2006–NM–130–AD; Amendment 

39–14880; AD 2007–01–08] 

RIN 2120–AA64 

Airworthiness Directives; Bombardier 

Model DHC–8–400 Series Airplanes 

AGENCY: Federal Aviation 

Administration (FAA), Department of 

Transportation (DOT). 

ACTION: Final rule. 

SUMMARY: The FAA is adopting a new 

airworthiness directive (AD) for certain 

Bombardier Model DHC–8–400 series 

airplanes. This AD requires inspecting 

for fouling and chafing damage of the 

outboard brake control cable of the main 

landing gear, replacing the control cable 

if necessary, reworking the control cable 

cover, and, if applicable, 

manufacturing/installing an offset plate 

on the control cable cover. This AD 

results from a review of brake control 

cable operation conducted by the 

manufacturer. We are issuing this AD to 

prevent abrasion and wear of the 

outboard brake control cable, which 

could lead to cable separation and 

reduced control of airplane braking. 

DATES: This AD becomes effective 

March 1, 2007. 

The Director of the Federal Register 

approved the incorporation by reference 

of a certain publication listed in the AD 

as of March 1, 2007. 

ADDRESSES: You may examine the AD 

docket on the Internet at http:// 

dms.dot.gov or in person at the Docket 

Management Facility, U.S. Department 

of Transportation, 400 Seventh Street, 

SW., Nassif Building, Room PL–401, 

Washington, DC. 


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Federal Register / Vol. 72, No. 16 / Thursday, January 25, 2007 / Rules and Regulations 3353 

Contact Bombardier, Inc., Bombardier 

Regional Aircraft Division, 123 Garratt 

Boulevard, Downsview, Ontario M3K 

1Y5, Canada, for service information 

identified in this AD. 

FOR FURTHER INFORMATION CONTACT: Ezra 

Sasson, Aerospace Engineer, Systems 

and Flight Test Branch, ANE–172, FAA, 

New York Aircraft Certification Office, 

1600 Stewart Avenue, suite 410, 

Westbury, New York 11590; telephone 

(516) 228–7320; fax (516) 794–5531. 

SUPPLEMENTARY INFORMATION: 

Examining the Docket 

You may examine the airworthiness 

directive (AD) docket on the Internet at 

http://dms.dot.gov or in person at the 

Docket Management Facility office 

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

through Friday, except Federal holidays. 

The Docket Management Facility office 

(telephone (800) 647–5227) is located on 

the plaza level of the Nassif Building at 

the street address stated in the 

ADDRESSES section. 

Discussion 

The FAA issued a notice of proposed 

rulemaking (NPRM) to amend 14 CFR 

part 39 to include an AD that would 

apply to certain Bombardier Model 

DHC–8–400 series airplanes. That 

NPRM was published in the Federal 

Register on July 12, 2006 (71 FR 39244). 

That NPRM proposed to require 

inspecting for fouling and chafing 

damage of the outboard brake control 

cable of the main landing gear, replacing 

the control cable if necessary, reworking 

the control cable cover, and, if 

applicable, manufacturing/installing an 

offset plate on the control cable cover. 

Comments 

We provided the public the 

opportunity to participate in the 

development of this AD. We have 

considered the comments received. 

Request To Publish Service Information 

One commenter, the Modification and 

Replacement Parts Association 

(MARPA), requests that we revise our 

procedures for incorporation by 

reference (IBR) of service information in 

ADs. MARPA states that, as an AD is a 

public regulatory instrument, it can not 

rely upon private writings. MARPA 

asserts that such IBR documents lose 

any original proprietary, protected 

status and become public documents, 

and, therefore, that they must be 

published in the Docket Management 

System (DMS), keyed to the action that 

incorporates them. MARPA addresses 

the stated purpose of the Office of the 

Federal Register (OFR) IBR method, 

brevity, which is intended to relieve the 

OFR from needlessly publishing 

documents already supplied to affected 

individuals (owners and operators of 

affected aircraft). MARPA asserts that 

‘‘affected individuals’’ are no longer 

merely owners and operators, but, since 

most aircraft maintenance is now 

performed by specialty shops, that a 

new class of affected individuals has 

emerged. This new class includes 

maintenance and repair organizations, 

component servicing and repair shops, 

parts purveyors and distributors, and 

organizations manufacturing or 

servicing alternatively certified parts 

under section 21.303 of the Federal 

Aviation Regulations (14 CFR 21.303). 

Further, MARPA contends that the 

concept of brevity is now nearly archaic 

as most documents are kept in 

electronic files. MARPA therefore 

requests that IBR documents be posted 

in the DMS docket for the applicable 

AD. 

We understand MARPA’s comment 

concerning incorporation by reference. 

The OFR requires that documents that 

are necessary to accomplish the 

requirements of the AD be incorporated 

by reference during the final rule phase 

of rulemaking. This final rule 

incorporates by reference the document 

necessary for the accomplishment of the 

actions required by this AD. Further, we 

point out that while documents that are 

incorporated by reference do become 

public information, they do not lose 

their copyright protection. For that 

reason, we advise the public to contact 

the manufacturer to obtain copies of the 

referenced service information. 

We are currently in the process of 

reviewing issues surrounding the 

posting of service bulletins on the DMS 

as part of an AD docket. Once we have 

thoroughly examined all aspects of this 

issue and have made a final 

determination, we will consider 

whether our current practice needs to be 

revised. No change to the final rule is 

necessary in response to this comment. 

Request for Policy Changes and 

Clarification 

MARPA also expresses concern about 

several perceived inconsistencies in 

current FAA policy regarding parts 

manufacturing approval (PMA) parts. 

MARPA states that type certificate 

holders in their service documents 

universally ignore the possible existence 

of PMA parts and that this is especially 

true with foreign manufacturers where 

the concept may not exist or be 

implemented in the country of origin. 

Frequently the service document upon 

which an airworthiness directive is 

based will require the removal of a 

certain part-numbered part and the 

installation of a different part-numbered 

part as a corrective action. This practice 

‘‘runs afoul of 14 CFR 21.303,’’ which 

permits development, certification, and 

installation of alternatively certified 

parts. 

MARPA’s statement that ‘‘this 

practice runs afoul of 14 CFR 21.303,’’

under which the FAA issues PMAs, 

appears to reflect a misunderstanding of 

the relationship between ADs and the 

certification procedural regulations of 

part 21 of the Federal Aviation 

Regulations (14 CFR part 21). Those 

regulations, including 14 CFR 21.203, 

are intended to ensure that aeronautical 

products comply with applicable 

airworthiness standards. But ADs are 

issued when, notwithstanding those 

procedures, we become aware of unsafe 

conditions in these products or parts. 

Therefore, an AD takes precedence over 

design approvals when we identify an 

unsafe condition, and mandating 

installation of a certain part number in 

an AD is not at variance with section 

21.303. 

The AD provides a means of 

compliance for operators to ensure that 

the identified unsafe condition is 

addressed appropriately. For an unsafe 

condition attributable to a part, the AD 

normally identifies the replacement 

parts necessary to obtain that 

compliance. As stated in section 39.7 of 

the Federal Aviation Regulations (14 

CFR 39.7), ‘‘Anyone who operates a 

product that does not meet the 

requirements of an applicable 

airworthiness directive is in violation of 

this section.’’ Unless an operator obtains 

approval for an alternative method of 

compliance (AMOC), replacing a part 

with one not specified by the AD would 

make the operator subject to an 

enforcement action and result in a civil 

penalty. No change to the AD is 

necessary in this regard. 

Request for Agreement on Parts 

Replacement 

MARPA further states the belief that 

the practice of requiring an AMOC to 

install a PMA part should be stopped, 

asserting that this is somehow 

tantamount to illogically stating that all 

PMA parts are inherently defective and 

require an additional layer of approval 

when the original equipment 

manufacturer (OEM) part is determined 

to be defective. MARPA states that the 

FAA personnel who diligently labored 

to certify the PMA part might disagree 

with such a narrow, OEM-slanted view. 

MARPA states that if the PMA part is 

defective, it must be deemed so in the 

AD and not simply implied by a catchall AMOC requirement. MARPA states 

that this is the reason for its repeated 


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3354 Federal Register / Vol. 72, No. 16 / Thursday, January 25, 2007 / Rules and Regulations 

requests that language be adopted to 

trap such defective parts and suggests 

the Transport Airplane Directorate 

adopt the language used by the Small 

Airplane Directorate to accomplish this. 

MARPA asserts that the Small Airplane 

Directorate has developed a blanket 

statement that resolves this issue as set 

forth in AD 2006–20–10, amendment 

39–14779 (71 FR 57405, September 29, 

2006): 

(f) 14 CFR 21.303 allows for replacement 

parts through parts manufacturer approval 

(PMA). The phrase ‘‘or FAA-approved 

equivalent P/N’’ in this AD is intended to 

allow for the installation of parts approved 

through identicality to the design of the 

replacement parts. Equivalent replacement 

parts to correct the unsafe condition under 

PMA (other than identicality) may also be 

installed provided they meet current 

airworthiness standards, which include those 

actions cited in this AD. 

MARPA concludes that, typically, the 

Engine Directorate and the Rotorcraft 

Directorate avoid the issue by specifying 

‘‘airworthy parts’’ be installed, leaving 

the determination of exactly which parts 

to the installer. MARPA contends that, 

because this proposed action differs 

markedly in treatment of this issue from 

that of the other directorates, the 

mandates contained in Section 1, 

paragraph (b)(10), of Executive Order 

12866, which requires that all agencies 

act uniformly on a given issue, are not 

being met. MARPA therefore requests 

that steps be taken to bring the universe 

of PMA parts under the appropriate 

scope of this proposed action, both with 

respect to possible defective PMA parts 

and the use of possible present or future 

approved parts. 

The FAA recognizes the need for 

standardization on this issue and 

currently is in the process of reviewing 

it at the national level. However, the 

Transport Airplane Directorate 

considers that to delay this particular 

AD action would be inappropriate, since 

we have determined that an unsafe 

condition exists and that replacement of 

certain parts must be accomplished to 

ensure continued safety. Therefore, no 

change has been made to the AD in this 

regard. 

Request To Comply With Draft FAA 

Order 8040.2 

MARPA asserts that the NPRM, as 

written, does not comply with proposed 

FAA Order 8040.2 which states, ‘‘Parts 

Manufacturer Approval (PMA). MCAI 

(mandatory continuing airworthiness 

information) that require replacement or 

installation of certain parts could have 

replacement parts approved under 14 

CFR 21.303 based on a finding of 

identicality. We have determined that 

any parts approved under this 

regulation and installed should be 

subject to the actions of our AD and 

included in the applicability of our 

AD.’’

The NPRM did not address PMA 

parts, as provided in draft FAA Order 

8040.2, because the Order was only a 

draft that was out for comment at the 

time. After issuance of the NPRM, the 

Order was revised and issued as FAA 

Order 8040.5 with an effective date of 

September 29, 2006. FAA Order 8040.5 

does not address PMA parts in ADs. We 

acknowledge the need to ensure that 

unsafe PMA parts are identified and 

addressed in MCAI-related ADs. We are 

currently examining all aspects of this 

issue, including input from industry. 

Once we have made a final 

determination, we will consider how 

our policy regarding PMA parts in ADs 

needs to be revised. No change to the 

AD is needed in this regard. 

Conclusion 

We have carefully reviewed the 

available data, including the comments 

received, and determined that air safety 

and the public interest require adopting 

the AD as proposed. 

Costs of Compliance 

The following table provides the 

estimated costs for U.S. operators to 

comply with this AD, at an average 

labor rate of $80 per work hour. 

ESTIMATED COSTS

Action Work 

hours Parts Cost per airplane 

Number of U.S.-registered 

airplanes Fleet cost 

Inspect brake cable ..................................................... 1 N/A $80 17 ..................................... $1,360. 

Rework cable cover ..................................................... 3 N/A 240 17 ..................................... $4,080.

Manufacture/install offset plate, as applicable ............ 3 $200 440 Up to 17 ........................... Up to $7,480. 

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 have determined that 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); 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 AD and placed it in the AD docket. 

See the ADDRESSES section for a location 

to examine the regulatory evaluation. 

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: 


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Federal Register / Vol. 72, No. 16 / Thursday, January 25, 2007 / Rules and Regulations 3355 

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 Federal Aviation 

Administration (FAA) amends § 39.13 

by adding the following new 

airworthiness directive (AD): 

2007–01–08 Bombardier, Inc. (Formerly de 

Havilland, Inc.): Amendment 39–14880. 

Docket No. FAA–2006–25328; 

Directorate Identifier 2006–NM–130–AD. 

Effective Date 

(a) This AD becomes effective March 1, 

2007. 

Affected ADs 

(b) None. 

Applicability 

(c) This AD applies to Bombardier Model 

DHC–8–400 series airplanes, certificated in 

any category; having serial numbers 4003, 

4004, 4006, 4008 through 4064 inclusive, 

4072, and 4073. 

Unsafe Condition 

(d) This AD results from a review of brake 

control cable operation conducted by the 

manufacturer. We are issuing this AD to 

prevent abrasion and wear of the outboard 

brake control cable, which could lead to 

cable separation and reduced control of 

airplane braking. 

Compliance 

(e) You are responsible for having the 

actions required by this AD performed within 

the compliance times specified, unless the 

actions have already been done. 

Inspection of Control Cable 

(f) Within 12 months after the effective 

date of this AD, perform a general visual 

inspection for fouling and chafing damage of 

the outboard brake control cable of the main 

landing gear, in accordance with the 

Accomplishment Instructions of Bombardier 

Service Bulletin 84–53–37, Revision ‘C,’

dated December 5, 2005. 

Note 1: For the purposes of this AD, a 

general visual inspection is: ‘‘A visual 

examination of an interior or exterior area, 

installation, or assembly to detect obvious 

damage, failure, or irregularity. This level of 

inspection is made from within touching 

distance unless otherwise specified. A mirror 

may be necessary to ensure visual access to 

all surfaces in the inspection area. This level 

of inspection is made under normally 

available lighting conditions such as 

daylight, hangar lighting, flashlight, or 

droplight and may require removal or 

opening of access panels or doors. Stands, 

ladders, or platforms may be required to gain 

proximity to the area being checked.’’

Control Cable Cover Rework Only 

(g) If no fouling or damage is found during 

the inspection required by paragraph (f) of 

this AD: Within 24 months after the 

accomplishment date of the inspection, 

rework the control cable cover and, as 

applicable, manufacture/install the offset 

plate assembly; in accordance with the 

Accomplishment Instructions of Bombardier 

Service Bulletin 84–53–37, Revision ‘C,’

dated December 5, 2005. 

Cable Replacement and Control Cable Cover 

Rework 

(h) If any fouling or damage is found 

during the inspection required by paragraph 

(f) of this AD: Before further flight, replace 

the control cable with a new control cable, 

rework the control cable cover and, if not 

already installed, manufacture/install the 

offset plate assembly; in accordance with the 

Accomplishment Instructions of Bombardier 

Service Bulletin 84–53–37, Revision ‘C,’

dated December 5, 2005. 

Actions Accomplished According to 

Previous Issue of Service Bulletin 

(i) Actions accomplished before the 

effective date of this AD in accordance with 

Bombardier Service Bulletin 84–53–37, 

Revision ‘A,’ dated October 17, 2005; or 

Revision ‘B,’ dated November 24, 2005; are 

considered acceptable for compliance with 

the corresponding actions specified in this 

AD. 

Alternative Methods of Compliance 

(AMOCs) 

(j)(1) The Manager, New York Aircraft 

Certification Office, FAA, has the authority to 

approve AMOCs for this AD, if requested in 

accordance with the procedures found in 14 

CFR 39.19. 

(2) Before using any AMOC approved in 

accordance with § 39.19 on any airplane to 

which the AMOC applies, notify the 

appropriate principal inspector in the FAA 

Flight Standards Certificate Holding District 

Office. 

Related Information 

(k) Canadian airworthiness directive CF–

2006–05, dated March 31, 2006, also 

addresses the subject of this AD. 

Material Incorporated by Reference 

(l) You must use Bombardier Service 

Bulletin 84–53–37, Revision ‘C,’ dated 

December 5, 2005, to perform the actions that 

are required by this AD, unless the AD 

specifies otherwise. The Director of the 

Federal Register approved the incorporation 

by reference of this document in accordance 

with 5 U.S.C. 552(a) and 1 CFR part 51. 

Contact Bombardier, Inc., Bombardier 

Regional Aircraft Division, 123 Garratt 

Boulevard, Downsview, Ontario M3K 1Y5, 

Canada, for a copy of this service 

information. You may review copies at the 

Docket Management Facility, U.S. 

Department of Transportation, 400 Seventh 

Street, SW., Room PL–401, Nassif Building, 

Washington, DC; on the Internet at http:// 

dms.dot.gov; or at the National Archives and 

Records Administration (NARA). For 

information on the availability of this 

material at the 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 

December 26, 2006. 

Ali Bahrami, 

Manager, Transport Airplane Directorate, 

Aircraft Certification Service. 

[FR Doc. E7–911 Filed 1–24–07; 8:45 am] 

BILLING CODE 4910–13–P 

DEPARTMENT OF TRANSPORTATION 

Federal Aviation Administration 

14 CFR Part 39 

[Docket No. FAA–2006–26597; Directorate 

Identifier 2006–CE–86–AD; Amendment 39–

14900; AD 2007–02–13] 

RIN 2120–AA64 

Airworthiness Directives; DORNIER 

LUFTFAHRT GmbH Model 228–212 

Airplanes 

AGENCY: Federal Aviation 

Administration (FAA), DOT. 

ACTION: Final rule; request for 

comments. 

SUMMARY: The FAA is adopting a new 

airworthiness directive (AD) for 

DORNIER LUFTFAHRT GmbH Model 

228–212 airplanes. This AD requires 

you to inspect the landing gear carbon 

brake assembly. This AD results from 

mandatory continuing airworthiness 

information (MCAI) issued by the 

European Aviation Safety Agency 

(EASA), which is the airworthiness 

authority for the European Union. We 

are issuing this AD to inspect the 

landing gear carbon brake assembly to 

detect and replace loose bolts or selflocking nuts, which could result in the 

brake assembly detaching and 

malfunctioning, degrade brake 

performance and potentially cause loss 

of control of the aircraft during landing 

and roll-out. 

DATES: This AD becomes effective on 

March 1, 2007. 

As of March 1, 2007, the Director of 

the Federal Register approved the 

incorporation by reference of certain 

publications listed in the regulation. 

We must receive any comments on 

this AD by February 26, 2007. 

ADDRESSES: Use one of the following 

addresses to comment on this AD. 

• DOT Docket Web site: Go to 

http://dms.dot.gov and follow the 

instructions for sending your comments 

electronically. 

• Fax: (202) 493–2251. 

• Mail: Docket Management Facility, 

U.S. Department of Transportation, 400 

Seventh Street, SW., Nassif Building, 

Room PL–401, Washington, DC 20590–

0001. 


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