53554 Federal Register / Vol. 70, No. 174 / Friday, September 9, 2005 / Rules and Regulations 

TABLE 1.—GOODRICH ‘‘FASTPROP’’ PROPELLER DE-ICERS—Continued 

De-icer P/N Installed on, but not limited to 

Bombardier (deHavilland) DHC–2MK.III equipped with HC–B3TN–3, HC–B3TN–3B, or HC–B3TN–3BY props. 

Bombardier (deHavilland) DHC–6–300 equipped with Hartzell HC–B3TN–3(D)(Y) props. 

Embraer EMB–110P1/2 equipped with Hartzell HC–B3TN–3C or HC–B3TN–3D props. 

The following models equipped with Hartzell HC–B3TN–5( ) props: M7 Aerospace (Fairchild) SA226–AT, and 

SA226T. 

M7 Aerospace (Fairchild) SA226–TC equipped with Hartzell HC–B4TN–5( ) props. 

M7 Aerospace (Fairchild) SA226–TC with STC SA344GL equipped with Hartzell HC–B3TN–5( ) props. 

M7 Aerospace (Fairchild) SA226–TC with STC SA344Gl. 

The following models equipped with Hartzell HC–A3VF–7 or HC–3VH–7B props: AeroSpace Technologies of Australia 

(Government Aircraft Factories) N22B and N24A. 

The following models equipped with Hartzell HC–B3TN–3D props: IAI Arava 101 and 101B. 

The following models equipped with Hartzell HC–B3TN–3DY props: McKinnon (Grumman) G–21E and G–21G. 

The following models equipped with HC–B3TN–5( ) props: Mitsubishi Heavy Industries MU–2B, and MU–2B–10. 

The following models equipped with Hartzell HC–B3TN–5 props: Mitsubishi Heavy Industries MU–2B–15, MU–2B–20, 

MU–2B–25, MU–2B–26, MU–2B–30, MU–2B–35, and MU–2B–36. 

The following models equipped with Hartzell HC–B3TN–3C props: Pilatus PC–6, PC–6/B–H2, PC–6/B1–H2, PC–6/C–

H2, PC–6/C1–H2. 

The following models equipped with Hartzell HC–B3TN–3B props: Piper PA–31T and PA31T1. 

The following models equipped with Hartzell HC–B3TN–3B or HC–B3TN–3K props: Piper PA42 and PA42–720. 

The following model equipped with Hartzell HC–B3TN–5( ) props: Short Brothers SC–7 series 3 Variant 200. 

With STC SA02059AK on the following model equipped with HC–B4TN–5 props: Short Brothers SC–7 series 3 Variant 200. 

The following models equipped with Hartzell HC–B3TN–5( ) props: Twin Commander (Gulfstream) 690, 690A, and 

690B. 

Unsafe Condition 

(d) This AD results from reports of 

Goodrich ‘‘FASTprop’’ propeller de-icers 

becoming loose or debonded, and detaching 

from propeller blades during operation. We 

are issuing this AD to prevent Goodrich 

‘‘FASTprop’’ propeller de-icers from 

detaching from the propeller blade, resulting 

in damage to the airplane, and possible 

injury to passengers and crewmembers. 

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. 

(f) Properly certificated maintenance 

personnel must perform the initial inspection 

required in this AD. Thereafter, the pilot or 

properly certificated maintenance personnel 

may perform the repetitive visual check. 

Initial Visual Inspection of ‘‘FASTprop’’

Propeller De-Icers 

(g) Within 10 hours after the effective date 

of this AD, inspect the ‘‘FASTprop’’ propeller 

de-icers. If any ‘‘FASTprop’’ propeller de-icer 

fails the inspection, then the ‘‘FASTprop’’

de-icer must be repaired or replaced as 

necessary before the next flight. Use 

paragraphs 2.A(3) through (5) of the 

Accomplishment Instructions of Goodrich 

De-icing and Specialty Systems Alert Service 

Bulletin (ASB) No. 30–60–00–1, dated 

November 15, 2004 to do these actions. 

Repetitive Visual Inspections of 

‘‘FASTprop’’ Propeller De-Icers 

(h) After the initial inspection, visually 

check the ‘‘FASTprop’’ propeller de-icer once 

per day either during the pilot’s first preflight 

inspection of the day or when maintenance 

personnel are available. If any ‘‘FASTprop’’

propeller de-icer fails the visual check, then 

the ‘‘FASTprop’’ de-icer must be inspected, 

repaired, or replaced as necessary before the 

next flight. Terminating action is 

accomplished when the ‘‘FASTprop’’

propeller de-icer is removed and replaced 

with an approved propeller de-icer. Use 

paragraph 2.A(2) of the Accomplishment 

Instructions of Goodrich De-icing and 

Specialty Systems Alert Service Bulletin 

(ASB) No. 30–60–00–1, dated November 15, 

2004 to do these actions. 

Alternative Methods of Compliance 

(i) The Manager, Chicago Aircraft 

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. 

Special Flight Permits 

(j) Under 14 CFR part 39.23, we are 

limiting the special flight permits for this AD 

by requiring that any propeller found with a 

loose or debonded ‘‘FASTprop’’ de-icer must 

have all propeller blade de-icers removed 

before the flight, to maintain a balanced 

propeller. Information on removing de-icers 

can be found in paragraph 1.K.(1) of 

Goodrich De-icing and Specialty Systems 

ASB No. 30–60–00–1, dated November 15, 

2004. 

Related Information 

(k) None. 

Material Incorporated by Reference 

(l) You must use Goodrich De-icing and 

Specialty Systems Alert Service Bulletin No. 

30–60–00–1, dated November 15, 2004, to 

perform the inspections, repairs, and 

replacements 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 Goodrich De-icing 

and Specialty Systems, 1555 Corporate 

Woods Parkway, Uniontown, Ohio 44685, 

telephone (330) 374–3743, 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/ 

federal_register/code_of_federal_regulations/ 

ibr_locations.html. 

Issued in Burlington, Massachusetts, on 

September 1, 2005. 

Peter A. White, 

Acting Manager, Engine and Propeller 

Directorate, Aircraft Certification Service. 

[FR Doc. 05–17773 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–2004–19540; Directorate 

Identifier 2004–NM–110–AD; Amendment 

39–14258; AD 2005–18–18] 

RIN 2120–AA64 

Airworthiness Directives; Boeing 

Model 757 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 

Federal Register / Vol. 70, No. 174 / Friday, September 9, 2005 / Rules and Regulations 53555 

Boeing Model 757 airplanes. This AD 

requires inspections of certain wire 

bundles in the left and right engine-towing aft fairings for discrepancies; 

installation of back-to-back p-clamps 

between the wire and hydraulic supply 

tube at the aft end of the right-hand strut 

only; and associated re-routing of the 

wire bundles, if necessary. This AD 

results from a report indicating that a 

circuit breaker for the fuel shutoff valve 

tripped due to a wire that chafed against 

the structure in the flammable leakage 

zone of the aft fairing, causing a short 

circuit. We are 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. 

DATES: This AD becomes effective 

October 14, 2005. 

The Director of the Federal Register 

approved the incorporation by reference 

of certain publications 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 Boeing Commercial 

Airplanes, P.O. Box 3707, Seattle, 

Washington 98124–2207, for service 

information identified in this AD. 

FOR FURTHER INFORMATION CONTACT: 

Thomas Thorson, Aerospace Engineer, 

Propulsion Branch, ANM–140S, FAA, 

Seattle Aircraft Certification Office, 

1601 Lind Avenue, SW., Renton, 

Washington 98055–4056; telephone 

(425) 917–6508; fax (425) 917–6590. 

SUPPLEMENTARY INFORMATION: 

Examining the Docket 

You may examine the 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 supplemental 

notice of proposed rulemaking (NPRM) 

to amend 14 CFR part 39 to include an 

AD that would apply to certain Boeing 

Model 757 airplanes. That supplemental 

NPRM was published in the Federal 

Register on July 6, 2005 (70 FR 38823). 

That supplemental NPRM proposed to 

require inspections of certain wire 

bundles in the left and right engine-towing aft fairings for discrepancies; 

installation of back-to-back p-clamps 

between the wire and hydraulic supply 

tube at the aft end of the right-hand strut 

only; and associated re-routing of the 

wire bundles, if necessary. 

Comments 

We provided the public the 

opportunity to participate in the 

development of this AD. We have 

considered the comments received. The 

commenters support the supplemental 

NPRM. 

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 in the supplemental 

NPRM. 

Costs of Compliance 

There are about 618 airplanes of the 

affected design in the worldwide fleet. 

This AD will affect about 342 airplanes 

of U.S. registry. The actions will take 

between 16 and 44 work hours per 

airplane, depending on airplane 

configuration, at an average labor rate of 

$65 per work hour. Required parts will 

cost about $600 per airplane. Based on 

these figures, the estimated cost of this 

AD on U.S. operators is between 

$560,880 and $1,183,320, or between 

$1,640 and $3,460 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 

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): 

2005–18–18 Boeing: Amendment 39–14258. 

Docket No. FAA–2004–19540; 

Directorate Identifier 2004–NM–110–AD. 

Effective Date 

(a) This AD becomes effective October 14, 

2005. 

Affected ADs 

(b) None. 

Applicability 

(c) This AD applies to Model 757–200, 

–200PF, –200CB, and –300 series airplanes; 

certificated in any category; equipped with 

Rolls-Royce engines; as identified in Boeing 

Alert Service Bulletins 757–28A0073 and 

757–28A0074, both Revision 1, both dated 

February 24, 2005. 

Unsafe Condition 

(d) This AD was prompted by a report 

indicating that a circuit breaker for the fuel 

shutoff valve tripped due to a wire that 

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