34004 Federal Register / Vol. 71, No. 113 / Tuesday, June 13, 2006 / Rules and Regulations 

this summary at the address listed 

under ADDRESSES. 

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 Federal Aviation Administration 

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: 

2006–12–19 Hamilton Sundstrand: 

Amendment 39–14645. Docket No. 

FAA–2005–21691; Directorate Identifier 

2005–NE–13–AD. 

Effective Date 

(a) This airworthiness directive (AD) 

becomes effective July 18, 2006. 

Affected ADs 

(b) None. 

Applicability 

(c) This AD applies to Hamilton 

Sundstrand Model 14RF–19 propellers with 

propeller system actuator yoke arms, part 

number (P/N) 810436–2, which might be 

installed in actuator assemblies P/N 790119–

6. These propellers are installed on, but not 

limited to, SAAB 340 airplanes. 

Unsafe Condition 

(d) This AD results from propeller system 

actuator yoke arms breaking during flight. We 

are issuing this AD to prevent actuator yoke 

arms breaking during flight, which could 

cause high propeller vibration and contribute 

to reduced controllability of the airplane. 

Compliance 

(e) You are responsible for having the 

actions required by this AD performed within 

60 days after the effective date of this AD, 

unless the actions have already been done. 

Install Improved Actuator Yoke Arms 

(f) Using the Accomplishment Instructions 

of Hamilton Sundstrand Service Bulletin 

14RF–19–61–113, Revision 1, dated 

September 2, 2003, replace all actuator yoke 

arms, P/N 810436–2 with improved actuator 

yoke arms, P/N 810436–3. 

(g) Mark newly installed actuators using 

the Accomplishment Instructions of 

Hamilton Sundstrand Service Bulletin 14RF–

19–61–113, Revision 1, dated September 2, 

2003. 

(h) After the effective date of this AD, do 

not install any actuator yoke arms, P/N 

810436–2, into any propeller assembly. 

Alternative Methods of Compliance 

(i) The Manager, Boston Certification 

Office, has the authority to approve 

alternative methods of compliance for this 

AD if requested using the procedures found 

in 14 CFR 39.19. 

Related Information 

(j) None. 

Material Incorporated by Reference 

(k) You must use Hamilton Sundstrand 

Service Bulletin 14RF–19–61–113, Revision 

1, dated September 2, 2003, to perform the 

replacements and marking required by this 

AD. The Director of the Federal Register 

approved the incorporation by reference of 

this service bulletin in accordance with 5 

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

Hamilton Sundstrand, A United 

Technologies Company, Publication 

Manager, Mail Stop 1A–3-Z63, One Hamilton 

Road, Windsor Locks, CT 06096; fax 1–860–

654–5107, 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., Nassif Building, Room PL–401, 

Washington, DC 20590–0001, 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 NARA, call 202–741–6030, 

or go to: http://www.archives.gov/federalregister/cfr/ibr-locations.html. 

Issued in Burlington, Massachusetts, on 

June 6, 2006. 

Thomas A. Boudreau, 

Acting Manager, Engine and Propeller 

Directorate, Aircraft Certification Service. 

[FR Doc. 06–5284 Filed 6–12–06; 8:45 am] 

BILLING CODE 4910–13–P 

DEPARTMENT OF TRANSPORTATION 

Federal Aviation Administration 

14 CFR Part 39 

[Docket No. FAA–2006–24365; Directorate 

Identifier 2006–NM–022–AD; Amendment 

39–14641; AD 2006–12–15] 

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 repetitive 

inspections for cracks of the first fuel 

access panel outboard of the nacelle on 

the left- and right-hand wings, and 

related investigative/corrective actions 

if necessary. This AD also requires 

eventual replacement of each access 

panel with a new access panel having a 

new part number. The replacement 

terminates the repetitive inspection 

requirements. This AD results from 

reports of cracks of the fuel access 

panels. We are issuing this AD to detect 

and correct cracked fuel access panels, 

which could lead to arcing and ignition 

of fuel vapor during a lightning strike, 

and result in fuel tank explosions and 

consequent loss of the airplane. 

DATES: This AD becomes effective July 

18, 2006. 

The Director of the Federal Register 

approved the incorporation by reference 

of a certain publication listed in the AD 

as of July 18, 2006. 

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: 

George Duckett, Aerospace Engineer, 

Airframe and Propulsion Branch, ANE–

171, New York Aircraft Certification 

Office, FAA, 1600 Stewart Avenue, 

Suite 410, Westbury, New York 11590; 

telephone (516) 228–7325; 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 April 11, 2006 (71 FR 

18239). That NPRM proposed to require 

repetitive inspections for cracks of the 

first fuel access panel outboard of the 

nacelle on the left- and right-hand 

wings, and related investigative/ 

corrective actions if necessary. That 

NPRM also proposed to require eventual 

replacement of each access panel with 

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Federal Register / Vol. 71, No. 113 / Tuesday, June 13, 2006 / Rules and Regulations 34005 

a new access panel having a new part 

number. The replacement would 

terminate the repetitive inspection 

requirements. 

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 

The following table provides the 

estimated costs for U.S. operators to 

comply with this AD. 

ESTIMATED COSTS

Action Work hours Average labor 

per rate hour Parts Cost per airplane 

Number of 

U.S.-registered 

airplanes 

Fleet cost 

Inspection, per inspection cycle ............... 1 $80 (1) $80 5 2 $400 

Replacement (for both wings) .................. 4 80 8,200 8,520 5 42,600 

1 None. 

2Per inspection cycle. 

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: 

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): 

2006–12–15 Bombardier, Inc. (Formerly de 

Havilland, Inc.): Amendment 39–14641. 

Docket No. FAA–2006–24365; 

Directorate Identifier 2006–NM–022–AD. 

Effective Date 

(a) This AD becomes effective July 18, 

2006. 

Affected ADs 

(b) None. 

Applicability 

(c) This AD applies to Bombardier Model 

DHC–8–400, DHC–8–401, and DHC–8–402 

airplanes, certificated in any category; serial 

numbers 4001, and 4003 through 4106 

inclusive. 

Unsafe Condition 

(d) This AD results from reports of cracks 

of the fuel access panels. We are issuing this 

AD to detect and correct cracked fuel access 

panels, which could lead to arcing and 

ignition of fuel vapor during a lightning 

strike, and result in fuel tank explosions 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. 

Inspection and Related Investigative and 

Corrective Actions 

(f) Within 400 flight hours after the 

effective date of this AD: Do an ultrasonic 

inspection for cracks of the first fuel access 

panel, part number (P/N) 85714230–001, 

outboard of the nacelle, on the left- and righthand wings, by doing all of the actions 

specified in the Accomplishment 

Instructions of Bombardier Service Bulletin 

84–57–13, dated August 17, 2005, except as 

provided by paragraph (i) of this AD. Do all 

applicable related investigative and 

corrective actions before further flight in 

accordance with the service bulletin. Repeat 

the applicable inspection, including the 

detailed inspection, thereafter at intervals not 

to exceed 1,200 flight hours. 

Note 1: Bombardier Service Bulletin 84–

57–13, refers to Bombardier Repair Drawing 

(RD) 8/4–57–451, dated February 2005, as an 

additional source of service information for 

doing certain corrective actions. 

Note 2: For the purposes of this AD, a 

detailed inspection is: ‘‘An intensive 

examination of a specific item, installation, 

or assembly to detect damage, failure, or 

irregularity. Available lighting is normally 

supplemented with a direct source of good 

lighting at an intensity deemed appropriate. 

Inspection aids such as mirror, magnifying 

lenses, etc., may be necessary. Surface 

cleaning and elaborate procedures may be 

required.’’

Terminating Action—Replacement 

(g) Within 6,000 flight hours after the 

initial inspection done in accordance with 

paragraph (f) of this AD: Replace any access 

panel P/N 85714230–001, with a new panel 

P/N 85714230–003 or P/N 85714230–005. Do 

the replacement in accordance with the 

Accomplishment Instructions of Bombardier 

Service Bulletin 84–57–13, dated August 17, 

2005. Replacing one access panel terminates 

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34006 Federal Register / Vol. 71, No. 113 / Tuesday, June 13, 2006 / Rules and Regulations 

the repetitive inspection requirements of this 

AD for that panel only. Replacing both access 

panels terminates all repetitive inspection 

requirements of this AD. 

Parts Installation 

(h) As of the effective date of this AD, no 

person may install a fuel access panel, P/N 

85714230–001, on any airplane unless the 

panel has been inspected, and all applicable 

related investigative and corrective actions 

have been accomplished, in accordance with 

paragraph (f) of this AD. 

No Report Required 

(i) Although the Accomplishment 

Instructions of Bombardier Service Bulletin 

84–57–13, dated August 17, 2005, specify to 

report certain information to the 

manufacturer, this AD does not include that 

requirement. 

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–

2005–37, dated October 11, 2005, also 

addresses the subject of this AD. 

Material Incorporated by Reference 

(l) You must use Bombardier Service 

Bulletin 84–57–13, dated August 17, 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 June 5, 

2006. 

Kalene C. Yanamura, 

Acting Manager, Transport Airplane 

Directorate, Aircraft Certification Service. 

[FR Doc. 06–5285 Filed 6–12–06; 8:45 am] 

BILLING CODE 4910–13–P 

DEPARTMENT OF TRANSPORTATION 

Federal Aviation Administration 

14 CFR Part 39 

[Docket No. FAA–2006–24411; Directorate 

Identifier 2006–NM–033–AD; Amendment 

39–14642; AD 2006–12–16] 

RIN 2120–AA64 

Airworthiness Directives; Bombardier 

Model DHC–8–102, –103, –106, –201, 

–202, –301, –311, –314, and –315 

Airplanes; Equipped With Certain 

Cockpit Door Installations 

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–8–102, –103, 

–106, –201, –202, –301, –311, –314, and 

–315 airplanes. This AD requires certain 

Bombardier Model DHC–8–102, –103, 

–106, –201, –202, –301, –311, –314, and 

–315 airplanes. This AD results from a 

report that, during structural testing of 

the cockpit door, the lower hinge block 

rotated and caused the mating hinge pin 

to disengage, and caused excessive door 

deflection. We are issuing this AD to 

prevent failure of a door attachment, 

which could result in uncontrolled 

release of the cockpit door under certain 

fuselage decompression conditions, and 

possible damage to the airplane 

structure. 

DATES: This AD becomes effective July 

18, 2006. 

The Director of the Federal Register 

approved the incorporation by reference 

of certain publications listed in the AD 

as of July 18, 2006. 

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: 

George Duckett, Aerospace Engineer, 

Airframe and Propulsion Branch, ANE–

171, New York Aircraft Certification 

Office, FAA, 1600 Stewart Avenue, suite 

410, Westbury, New York 11590; 

telephone (516) 228–7325; 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, –106, –201, –202, 

–301, –311, –314, and –315 airplanes. 

That NPRM was published in the 

Federal Register on April 11, 2006 (71 

FR 18244). That NPRM proposed to 

require modifying the hinge attachment 

for the cockpit door from a single-point 

attachment to a two-point attachment. 

Comments 

We provided the public the 

opportunity to participate in the 

development of this AD. We have 

considered the one comment received. 

The commenter, the Air Line Pilots 

Association, supports the NPRM. 

Conclusion 

We have carefully reviewed the 

available data, including the comment 

received, and determined that air safety 

and the public interest require adopting 

the AD as proposed. 

Costs of Compliance 

This AD will affect about 16 airplanes 

of U.S. registry. The required actions 

will take between 3 and 6 work hours 

per airplane, depending on the airplane 

configuration. The average labor rate is 

$80 per work hour. Required parts will 

cost about $2,000 per airplane. Based on 

these figures, the estimated cost of this 

AD for U.S. operators is between 

$35,840 and $39,680, or between $2,240 

and $2,480 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 

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