53556 Federal Register / Vol. 70, No. 174 / Friday, September 9, 2005 / Rules and Regulations 

chafed against the structure in the flammable 

leakage zone of the aft fairing, causing a short 

circuit. The FAA is issuing this AD to 

prevent chafing between the wire bundle and 

the structure of the aft fairing, which could 

result in electrical arcing and subsequent 

ignition of flammable vapors and possible 

uncontrollable fire. 

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. 

One-Time Inspections/Related Investigative 

and Corrective Actions 

(f) Within 60 months after the effective 

date of this AD, do the actions required by 

paragraphs (f)(1) and (f)(2) of this AD. 

(1) Accomplish the detailed inspections for 

discrepancies of the wire bundles in the left 

and right engine-to-wing aft fairings, and 

applicable and related investigative and 

corrective actions if necessary, as applicable, 

by doing all the actions specified in the 

Accomplishment Instructions of the 

applicable service bulletins listed in Table 1 

of this AD. Accomplish any related 

investigative and corrective actions before 

further flight in accordance with the 

applicable service bulletin. 

TABLE 1.—AIRPLANE MODELS AND SERVICE BULLETINS

Boeing airplanes 

Boeing Alert 

Service 

Bulletin 

Revision 

level Date 

Model 757–200, –200CB, 200PF series airplanes ............................................................ 757–28A0073 Original ...... November 20, 2003. 

Model 757–200, –200CB, 200PF series airplanes ............................................................ 757–28A0073 1 ................. February 24, 2005. 

Model 757–300 series airplanes ........................................................................................ 757–28A0074 Original ...... November 20, 2003. 

Model 757–300 series airplanes ........................................................................................ 757–28A0074 1 ................. February 24, 2005. 

(2) Install back-to-back p-clamps between 

the wire and hydraulic supply tube at the aft 

end of the right-hand strut only; and re-route 

the wire bundles, if necessary, by doing all 

the applicable actions specified in the 

Accomplishment Instructions of Boeing Alert 

Service Bulletin 757–28A0073 or 757–

28A0074, both Revision 1, both dated 

February 24, 2005; as applicable. 

Note 1: 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.’’

Alternative Methods of Compliance 

(AMOCs) 

(g) The Manager, Seattle 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. 

Material Incorporated by Reference 

(h) You must use the applicable service 

bulletin listed in Table 2 of this AD 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 these 

documents in accordance with 5 U.S.C. 

552(a) and 1 CFR part 51. Contact Boeing 

Commercial Airplanes, P.O. Box 3707, 

Seattle, Washington 98124–2207, 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. 

TABLE 2.—MATERIAL INCORPORATED BY REFERENCE

Boeing Alert Service Bulletin Revision 

level Date 

757–28A0073 ................................................................................................................................................ Original ...... November 20, 2003. 

757–28A0073 ................................................................................................................................................ 1 ................. February 24, 2005. 

757–28A0074 ................................................................................................................................................ Original ...... November 20, 2003. 

757–28A0074 ................................................................................................................................................ 1 ................. February 24, 2005. 

Issued in Renton, Washington, on August 

31, 2005. 

Kalene C. Yanamura, 

Acting Manager, Transport Airplane 

Directorate, Aircraft Certification Service. 

[FR Doc. 05–17772 Filed 9–8–05; 8:45 am] 

BILLING CODE 4910–13–P 

DEPARTMENT OF TRANSPORTATION 

Federal Aviation Administration 

14 CFR Part 39 

[Docket No. FAA–2005–21683; Directorate 

Identifier 2005–NM–021–AD; Amendment 

39–14259; AD 2005–18–19] 

RIN 2120–AA64 

Airworthiness Directives; Fokker 

Model F27 Mark 200, 400, 500, and 600 

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 

Fokker Model F27 Mark 200, 400, 500, 

and 600 airplanes. This AD requires a 

general visual inspection of the rotary 

knobs for the fuel tank isolation valves 

to determine if the seal wire has been 

installed correctly, and corrective 

actions if necessary. This AD results 

from investigation of a recent accident, 

which found that the rotary knobs 

controlling the fuel tank isolating valves 

had been in the shut position. We are 

issuing this AD to ensure that the rotary 

knobs are not inadvertently moved to 

the shut position, which could result in 

fuel starvation to both engines and 

Federal Register / Vol. 70, No. 174 / Friday, September 9, 2005 / Rules and Regulations 53557 

consequent inability to maintain 

controlled flight and landing. 

DATES: This AD becomes effective 

October 14, 2005. 

The Director of the Federal Register 

approved the incorporation by reference 

of a certain publication listed in the AD 

as of October 14, 2005. 

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 Fokker Services B.V., P.O. 

Box 231, 2150 AE Nieuw-Vennep, the 

Netherlands, for service information 

identified in this AD. 

FOR FURTHER INFORMATION CONTACT: Tom 

Rodriguez, Aerospace Engineer, 

International Branch, ANM–116, FAA, 

Transport Airplane Directorate, 1601 

Lind Avenue, SW., Renton, Washington 

98055–4056; telephone (425) 227–1137; 

fax (425) 227–1149. 

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 Fokker Model F27 Mark 

200, 400, 500, and 600 airplanes. That 

NPRM was published in the Federal 

Register on June 29, 2005 (70 FR 37291). 

That NPRM proposed to require a 

general visual inspection of the rotary 

knobs for the fuel tank isolation valves 

to determine if the seal wire has been 

installed correctly, and corrective 

actions if necessary. 

Correction to Final Rule 

We have revised paragraph (h) of this 

Final Rule to correct an incorrect part 

number. We have determined that the 

incorrect part number does not exist. 

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 with the change 

described previously. We have 

determined that this change will neither 

increase the economic burden on any 

operator nor increase the scope of the 

AD. 

Costs of Compliance 

This AD will affect about 1 airplane 

of U.S. registry. The required inspection 

will take about 2 work hours per 

airplane, at an average labor rate of $65 

per work hour. Based on these figures, 

the estimated cost of the AD for the one 

U.S. operator is $130. 

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): 

2005–18–19 Fokker Services B.V.: 

Amendment 39–14259. Docket No. 

FAA–2005–21683; Directorate Identifier 

2005–NM–021–AD. 

Effective Date 

(a) This AD becomes effective October 14, 

2005. 

Affected ADs 

(b) None. 

Applicability 

(c) This AD applies to Fokker Model F27 

Mark 200, 400, 500, and 600 airplanes, 

certificated in any category; serial numbers 

10505 through 10591 inclusive; not equipped 

with inboard wing fuel tanks. 

Unsafe Condition 

(d) This AD was prompted by investigation 

of a recent accident, which found that the 

rotary knobs controlling the fuel tank 

isolating valves had been in the shut 

position. We are issuing this AD to ensure 

that the rotary knobs are not inadvertently 

moved to the shut position, which could 

result in fuel starvation to both engines and 

consequent inability to maintain controlled 

flight and landing. 

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 Corrective Action if 

Applicable 

(f) Within 3 months after the effective date 

of this AD, do a general visual inspection of 

the rotary knobs for the fuel tank isolation 

valves to determine if the seal wire is 

installed correctly and do the corrective 

action(s) as applicable, in accordance with 

the Accomplishment Instructions of Fokker 

Service Bulletin F27/28–67, dated February 

53558 Federal Register / Vol. 70, No. 174 / Friday, September 9, 2005 / Rules and Regulations 

23, 2004. Do the applicable corrective actions 

before further flight. 

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.’’

Credit for Alternative Method of Compliance 

(g) Actions done before the effective date 

of this AD in accordance with Fokker Service 

Bulletin F27/28–58, dated May 12, 1986, are 

acceptable for compliance with the 

requirements of paragraph (f) of this AD. 

Parts Installation 

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

person may install a rotary knob having part 

number E10632–3, 10632–10003, or P80–004 

on any airplane, unless the corrective actions 

specified in paragraph (f) of this AD have 

been accomplished. 

No Reporting Requirement 

(i) Although the service bulletin referenced 

in this AD specifies to submit certain 

information to the manufacturer, this AD 

does not include that requirement. 

Alternative Methods of Compliance 

(AMOCs) 

(j) 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. 

Related Information 

(k) Dutch airworthiness directive NL–

2004–037 R1, dated April 14, 2005, also 

addresses the subject of this AD. 

Material Incorporated by Reference 

(l) You must use Fokker Service Bulletin 

F27/28–67, dated February 23, 2004, 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 Fokker Services B.V., P.O. 

Box 231, 2150 AE Nieuw-Vennep, the 

Netherlands, 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/federalregister/cfr/ibr-locations.html. 

Issued in Renton, Washington, on August 

31, 2005. 

Kalene C. Yanamura, 

Acting Manager, Transport Airplane 

Directorate, Aircraft Certification Service. 

[FR Doc. 05–17771 Filed 9–8–05; 8:45 am] 

BILLING CODE 4910–13–P 

DEPARTMENT OF TRANSPORTATION 

Federal Aviation Administration 

14 CFR Part 39 

[Docket No. FAA–2005–21435; Directorate 

Identifier 2004–NM–163–AD; Amendment 

39–14257; AD 2005–18–17] 

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 a one-time 

inspection of the fuel and hydraulic 

tubes, and corrective actions if 

necessary. This AD also requires 

modifying fairlead plate assemblies. 

This AD results from reports of chafing 

between fuel and hydraulic tubes and 

the fairlead plate where the tubes pass 

through the firewall. We are issuing this 

AD to prevent chafing of the fuel and 

hydraulic tubes, which could lead to 

fuel and/or hydraulic fluid leakage in 

the engine nacelle area and consequent 

fire or explosion. 

DATES: This AD becomes effective 

October 14, 2005. 

The Director of the Federal Register 

approved the incorporation by reference 

of a certain publication listed in the AD 

as of October 14, 2005. 

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: 

Richard Fiesel, Aerospace Engineer, 

Airframe and Propulsion Branch, ANE–

171, FAA, New York Aircraft 

Certification Office, 1600 Stewart 

Avenue, suite 410, Westbury, New York 

11590; telephone (516) 256–7504; 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 June 14, 2005 (70 FR 34409). 

That NPRM proposed to require a onetime inspection of the fuel and 

hydraulic tubes, and corrective actions 

if necessary. That NPRM also proposed 

to require modifying fairlead plate 

assemblies. 

Explanation of Change to Applicability 

We have revised the applicability of 

the proposed AD to identify model 

designations as published in the most 

recent type certificate data sheet for the 

affected models. 

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 with the change 

described previously. We have 

determined that this change will neither 

increase the economic burden on any 

operator nor increase the scope of the 

AD. 

Costs of Compliance 

This AD will affect about 18 airplanes 

of U.S. registry. The actions will take 

about 4 work hours per airplane, at an 

average labor rate of $65 per work hour. 

Required parts will cost about $200 per 

airplane. Based on these figures, the 

estimated cost of the AD for U.S. 

operators is $8,280, or $460 per 

airplane.