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. 


ycherry on PROD1PC64 with RULES
3356 Federal Register / Vol. 72, No. 16 / Thursday, January 25, 2007 / Rules and Regulations 

• Hand Delivery: Room PL–401 on 

the plaza level of the Nassif Building, 

400 Seventh Street, SW., Washington, 

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

through Friday, except Federal holidays. 

• Federal eRulemaking Portal: http:// 

www.regulations.gov. Follow the 

instructions for submitting comments. 

To get the service information 

identified in this AD, contact RVAG 

Aerospace Services GmbH, Dornier 228 

Customer Support, PO Box 1253, D–

82231Wessling, Federal Republic of 

Germany; telephone: 49 8153 302280. 

To view the comments to this AD, go 

to http://dms.dot.gov. The docket 

number is FAA–2006–26597; 

Directorate Identifier 2006–CE–86–AD. 

FOR FURTHER INFORMATION CONTACT: Karl 

Schletzbaum, Aerospace Engineer, FAA, 

Small Airplane Directorate, 901 Locust, 

Room 301, Kansas City, Missouri 64106; 

telephone: (816) 329–4146; fax: (816) 

329–4090. 

SUPPLEMENTARY INFORMATION: 

Discussion 

The European Aviation Safety Agency 

(EASA), which is the airworthiness 

authority for the European Union, 

recently notified the FAA that an unsafe 

condition may exist on certain 

DORNIER LUFTFAHRT GmbH Dornier 

Model 228–212 airplanes. The EASA 

reports that during a maintenance 

inspection, loose bolts and nuts were 

detected on the landing gear carbon 

brake assembly. 

This condition, if not corrected, could 

result in the brake assembly detaching 

and malfunctioning, degrading brake 

performance, and potentially causing 

loss of control of the aircraft during 

landing or roll-out. 

Relevant Service Information 

We reviewed DORNIER LUFTFAHRT 

GmbH Dornier 228 Alert Service 

Bulletin (ASB) No. ASB–228–265, dated 

November 17, 2006. The service 

information describes procedures for a 

visual inspection of the landing gear to 

detect loose bolts and self-locking nuts 

at the carbon brake assembly. 

The EASA classified this service 

bulletin as mandatory and issued EASA 

AD Number EAD 2006–0352–E, dated 

November 24, 2006, to ensure the 

continued airworthiness of these 

airplanes in Germany. 

FAA’s Determination and Requirements 

of This AD 

These DORNIER LUFTFAHRT GmbH 

Model 228–212 airplanes are 

manufactured in Germany and are typecertificated for operation in the United 

States under the provisions of section 

21.29 of the Federal Aviation 

Regulations (14 CFR 21.29) and the 

applicable bilateral airworthiness 

agreement. 

Under this bilateral airworthiness 

agreement, the EASA has kept us 

informed of the situation described 

above. We are issuing this AD because 

we evaluated all the information and 

determined the unsafe condition 

described previously is likely to exist or 

develop on other products of the same 

type design. This AD requires an 

inspection of the landing gear carbon 

brake assembly to detect and replace 

loose bolts or self-locking nuts. 

Cost Impact 

None of the DORNIER LUFTFAHRT 

GmbH Model 228–212 airplanes 

affected by this action are currently on 

the U.S. Registry. All airplanes included 

in the applicability of this rule currently 

are operated by non-U.S. operators 

under foreign registry; therefore, they 

are not directly affected by this AD 

action at this time. However, the FAA 

considers this rule necessary to ensure 

that the unsafe condition is addressed in 

the event that any of these subject 

airplanes are imported and placed on 

the U.S. Registry. 

Should an affected airplane be 

imported and placed on the U.S. 

Registry, accomplishment of the 

required action would take 

approximately 10 workhours at an 

average labor rate of $80 per workhour. 

Based on these figures, the total cost 

impact of this AD would be $800 per 

airplane. 

Comments Invited 

Because there are no affected 

airplanes on the U.S. Registry, it has no 

adverse economic impact and imposes 

no additional burden on any person. 

Therefore, prior notice and public 

procedures hereon are unnecessary. We 

invite you to send any written relevant 

data, views, or arguments regarding this 

AD. Send your comments to an address 

listed under the ADDRESSES section. 

Include the docket number ‘‘FAA–

2006–26597; Directorate Identifier 

2006–CE–86–AD’’ at the beginning of 

your comments. We specifically invite 

comments on the overall regulatory, 

economic, environmental, and energy 

aspects of the AD. We will consider all 

comments received by the closing date 

and may amend the AD in light of those 

comments. 

We will post all comments we 

receive, without change, to http:// 

dms.dot.gov, including any personal 

information you provide. We will also 

post a report summarizing each 

substantive verbal contact we receive 

concerning this AD. 

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 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. 

Examining the AD Docket 

You may examine the AD docket that 

contains the AD, the regulatory 

evaluation, any comments received, and 

other information on the Internet at 

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

Docket Management Facility between 9 

a.m. and 5 p.m., Monday through 

Friday, except Federal holidays. The 

Docket Office (telephone (800) 647–

5227) is located at the street address 

stated in the ADDRESSES section. 

Comments will be available in the AD 

docket shortly after receipt. 


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Federal Register / Vol. 72, No. 16 / Thursday, January 25, 2007 / Rules and Regulations 3357 

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): 

2007–02–13 DORNIER LUFTFAHRT: 

Amendment 39–14900; Docket No. 

FAA–2006–26597; Directorate Identifier 

2006–CE–86–AD. 

Effective Date 

(a) This AD becomes effective on March 1, 

2007. 

Affected ADs 

(b) None. 

Applicability 

(c) This AD applies to DORNIER 

LUFTFAHRT GmbH Model 228–212 

airplanes, all serial numbers, if Carbon Brake 

Assemblies with Part Number (P/N) 

5009850–1, 5009850–2, 5009850–3 or 

5009850–4 are installed, that are certificated 

in any category. 

Unsafe Condition 

(d) This AD is the result of loose bolts and 

nuts being detected on the landing gear 

carbon brake assembly during a maintenance 

inspection. We are issuing this AD to require 

an inspection to detect loose bolts and selflocking nuts on the landing gear carbon brake 

assembly, which, if not corrected, could 

result in the brake assembly detaching and 

malfunctioning, degrading brake 

performance, and potentially causing loss of 

control of the aircraft during landing or rollout. 

Compliance 

(e) To address this problem, you must do 

the following, unless already done, before the 

next flight after the effective date of this AD: 

Inspect the landing gear carbon brake 

assembly in accordance with the instructions 

contained in DORNIER LUFTFAHRT GmbH 

Dornier 228 Alert Service Bulletin ASB–228–

265 dated November 17, 2006, and, if 

necessary, replace the affected brake 

assembly. 

Alternative Methods of Compliance 

(AMOCs) 

(f) The Manager, Standards Staff, FAA, 

ATTN: Karl Schletzbaum, Aerospace 

Engineer, Small Airplane Directorate, 901 

Locust, Room 301, Kansas City, Missouri 

64106; telephone: (816) 329–4146; fax: (816) 

329–4090, has the authority to approve 

AMOCs for this AD, if requested using the 

procedures found in 14 CFR 39.19. 

Related Information 

(g) This AD is related to EASA EAD No. 

2006–0352–E, dated November 24, 2006, 

which references Dornier Luftfahrt GmbH 

ASB–228–265, dated November 17, 2006. 

Material Incorporated by Reference 

(h) You must use DORNIER LUFTFAHRT 

GmbH Service Bulletin No. ASB–228–265, 

dated November 17, 2006, 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 RVAG Aerospace Services 

GmbH, Dornier 228 Customer Support, P.O. 

Box 1253, D–82231 Wessling, Federal 

Republic of Germany. 

(3) You may review copies at the FAA, 

Central Region, Office of the Regional 

Counsel, 901 Locust, Kansas City, Missouri 

64106; or 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 Kansas City, Missouri, on January 

12, 2007. 

Kim Smith, 

Manager, Small Airplane Directorate, Aircraft 

Certification Service. 

[FR Doc. E7–900 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–2006–25518; Directorate 

Identifier 2006–NM–092–AD; Amendment 

39–14881; AD 2007–01–09] 

RIN 2120–AA64 

Airworthiness Directives; Boeing 

Model 747–100B SUD, 747–200B, 747–

300, 747–400, 747–400D, and 747SP 

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 

Boeing Model 747–100B SUD, 747–

200B, 747–300, 747–400, 747–400D, and 

747SP series airplanes. This AD requires 

repetitive inspections for cracking of the 

crease beam and adjacent intercostals, 

stringers, frames, and skin panels; and 

related investigative and corrective 

actions if cracking is found. This AD 

results from a report indicating that an 

operator discovered crease beam 

cracking on two Model 747 airplanes. 

We are issuing this AD to detect and 

correct cracking of the crease beam and 

adjacent structure, which could become 

large and result in in-flight 

depressurization and inability of the 

airframe structure to sustain flight loads. 

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. 

Contact Boeing Commercial 

Airplanes, P.O. Box 3707, Seattle, 

Washington 98124–2207, for the service 

information identified in this AD. 

FOR FURTHER INFORMATION CONTACT: Ivan 

Li, Aerospace Engineer, Airframe 

Branch, ANM–120S, FAA, Seattle 

Aircraft Certification Office, 1601 Lind 

Avenue, SW., Renton, Washington 

98057–3356; telephone (425) 917–6437; 

fax (425) 917–6590. 

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 Boeing Model 747–100B SUD, 

747–200B, 747–300, 747–400, 747–

400D, and 747SP series airplanes. That 

NPRM was published in the Federal 

Register on August 8, 2006 (71 FR 

44933). That NPRM proposed to require 

repetitive inspections for cracking of the 

crease beam and adjacent intercostals, 

stringers, frames, and skin panels; and 

related investigative and corrective 

actions if cracking is found. 


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