Federal Register / Vol. 72, No. 38 / Tuesday, February 27, 2007 / Rules and Regulations 8619 

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 Fokker Services B.V., 

Technical Services Dept., P.O. Box 231, 2150 

AE Nieuw-Vennep, the Netherlands, for a 

copy of this service information. You may 

review copies at the FAA, Transport Airplane 

Directorate, 1601 Lind Avenue, SW., Renton, 

Washington; 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/ 

cfr/ibr-locations.html. 

Issued in Renton, Washington, on February 

12, 2007. 

Ali Bahrami, 

Manager, Transport Airplane Directorate, 

Aircraft Certification Service. 

[FR Doc. E7–2978 Filed 2–26–07; 8:45 am] 

BILLING CODE 4910–13–P 

DEPARTMENT OF TRANSPORTATION 

Federal Aviation Administration 

14 CFR Part 39 

[Docket No. FAA–2006–26558; Directorate 

Identifier 2006–NM–206–AD; Amendment 

39–14954; AD 2007–04–22] 

RIN 2120–AA64 

Airworthiness Directives; Bombardier 

Model DHC–8–102, –103, and –106 

Airplanes; and Model DHC–8–200 and 

DHC–8–300 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–8–100 (as 

described above), DHC–8–200, and 

DHC–8–300 series airplanes. This AD 

requires doing a one-time inspection for 

damage of the electrical cable harness 

assembly located on the left and right 

wing root-to-fuselage aft seal, and repair 

if necessary; and reworking the fuselage 

aft seal assembly (left and right) to 

create a clearance between the electrical 

cable assemblies and the edge of the 

fairing panel. This AD results from a 

report that an airplane encountered an 

uncommanded propeller feathering 

during climb, which resulted in an 

emergency landing. We are issuing this 

AD to prevent chafing or grounding of 

the wiring against the aft seal 

assemblies, which, if not corrected, 

could interrupt the operation of various 

systems, including the propeller feather 

control, alternating current (AC) 

electrical power, and standby hydraulic 

power, and result in reduced 

controllability of the airplane. 

DATES: This AD becomes effective April 

3, 2007. 

The Director of the Federal Register 

approved the incorporation by reference 

of a certain publication listed in the AD 

as of April 3, 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 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: 

Douglas Wagner, 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) 228–7306; 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–8–102, –103, and –106 airplanes, 

and Model DHC–8–200 and DHC–8–300 

series airplanes. That NPRM was 

published in the Federal Register on 

December 11, 2006 (71 FR 71492). That 

NPRM proposed to require doing a onetime inspection for damage of the 

electrical cable harness assembly 

located on the left and right wing rootto-fuselage aft seal, and repair if 

necessary; and reworking the fuselage 

aft seal assembly (left and right) to 

create a clearance between the electrical 

cable assemblies and the edge of the 

fairing panel. 

Comments 

We provided the public the 

opportunity to participate in the 

development of this AD. We received no 

comments on the NPRM or on the 

determination of the cost to the public. 

Conclusion 

We have carefully reviewed the 

available data and determined that air 

safety and the public interest require 

adopting the AD as proposed. 

Costs of Compliance 

This AD affects about 136 airplanes of 

U.S. registry. The required actions take 

about 4 work hours per airplane, at an 

average labor rate of $80 per work hour. 

Required parts cost about $75 per 

airplane. Based on these figures, the 

estimated cost of this AD for U.S. 

operators is $53,720, or $395 per 

airplane. 

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 


cprice-sewell on PROD1PC66 with RULES
8620 Federal Register / Vol. 72, No. 38 / Tuesday, February 27, 2007 / Rules and Regulations 

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): 

2007–04–22 Bombardier, Inc. (Formerly de 

Havilland, Inc.): Amendment 39–14954. 

Docket No. FAA–2006–26558; 

Directorate Identifier 2006–NM–206–AD. 

Effective Date 

(a) This AD becomes effective April 3, 

2007. 

Affected ADs 

(b) None. 

Applicability 

(c) This AD applies to Bombardier Model 

DHC–8–102, –103, and –106 airplanes, and 

Model DHC–8–200 and DHC–8–300 series 

airplanes, certificated in any category; serial 

numbers 003 through 606 inclusive. 

Unsafe Condition 

(d) This AD results from a report that an 

airplane encountered an uncommanded 

propeller feathering during climb, which 

resulted in an emergency landing. We are 

issuing this AD to prevent chafing or 

grounding of the wiring against the aft seal 

assemblies, which, if not corrected, could 

interrupt the operation of various systems, 

including the propeller feather control, 

alternating current (AC) electrical power, and 

standby hydraulic power, and result in 

reduced controllability 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. 

Inspection and Rework 

(f) Within 6,000 flight hours after the 

effective date of this AD, do the actions 

specified in paragraphs (f)(1) and (f)(2) of this 

AD. Do all actions in accordance with 

Bombardier Service Bulletin 8–24–83, 

Revision A, dated August 2, 2005. The 

actions in paragraph (f)(1) of this AD must be 

done before the rework in paragraph (f)(2) of 

this AD. 

Note 1: Bombardier Service Bulletin 8–24–

83, Revision A, contains the instructions for 

incorporating Bombardier Modification 

Summary Package 8Y122031, Revision B, 

dated December 2, 2004. (The technical 

content of Bombardier Modification 

Summary Package IS8Q2400005, Revision C, 

dated January 7, 2005, is equivalent to 

Bombardier Modification Summary Package 

8Y122031, Revision B.) 

(1) Do a general visual inspection for 

damage of the electrical cable harness 

assembly located on the left and right wing 

root-to-fuselage aft seal. If any damage is 

found, repair the damage before further 

flight. 

(2) Rework the fuselage aft seal assembly 

(left and right) to create a clearance between 

the electrical cable assemblies and the edge 

of the fairing panel. 

Note 2: 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.’’

Actions Accomplished in Accordance With 

Previous Revision of Service Bulletin 

(g) Actions done before the effective date 

of this AD in accordance with Bombardier 

Service Bulletin 8–24–83, dated December 

23, 2004, are acceptable for compliance with 

the corresponding requirements in paragraph 

(f) of this AD. 

Alternative Methods of Compliance 

(AMOCs) 

(h)(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 

(i) Canadian airworthiness directive CF–

2006–15, dated June 14, 2006, also addresses 

the subject of this AD. 

Material Incorporated by Reference 

(j) You must use Bombardier Service 

Bulletin 8–24–83, Revision A, dated August 

2, 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 

FAA, Transport Airplane Directorate, 1601 

Lind Avenue, SW., Renton, Washington; or at 

the National Archives and 

RecordsAdministration (NARA). For 

information on the availability of this 

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

to: http://www.archives.gov/federal-register/ 

cfr/ibr-locations.html. 

Issued in Renton, Washington, on February 

12, 2007. 

Ali Bahrami, 

Manager, Transport Airplane Directorate, 

Aircraft Certification Service. 

[FR Doc. E7–2972 Filed 2–26–07; 8:45 am] 

BILLING CODE 4910–13–P 

DEPARTMENT OF TRANSPORTATION 

Federal Aviation Administration 

14 CFR Part 39 

[Docket No. FAA–2006–26647; Directorate 

Identifier 2006–NM–194–AD; Amendment 

39–14957; AD 2007–04–24] 

RIN 2120–AA64 

Airworthiness Directives; Bombardier 

Model CL–600–2B19 (Regional Jet 

Series 100 & 440) 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 CL–600–2B19 

(Regional Jet Series 100 & 440) 

airplanes. This AD requires repetitive 

inspections of the bolts that attach the 

exhaust nozzle to the aft engine flange 

to determine if any bolts are missing or 

fractured, and replacement of the 

existing bolts with new, improved bolts. 

This AD results from reports of the 

engine exhaust nozzle and fairing 

departing from the airplane in flight due 

to missing attachment bolts. We are 

issuing this AD to detect and correct 

missing or fractured attachment bolts, 

which could lead to the loss of an 

engine exhaust nozzle during flight and 

consequent structural damage to the 

airplane and hazard to people or 

property on the ground. Damage to the 

airplane could cause the airplane to yaw 

and result in reduced controllability of 

the airplane. 

DATES: This AD becomes effective April 

3, 2007. 

The Director of the Federal Register 

approved the incorporation by reference 


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