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

### 1. — G OODRICH 

### ‘‘ FAST PROP 

### ’’ P ROPELLER 

### D E 

### -I CERS 

### — 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 VerDate Aug<18>2005 15:11 Sep 08, 2005 Jkt 205001 PO 00000 Frm 00018 Fmt 4700 Sfmt 4700 E:\FR\FM\09SER1.SGM 09SER1

## 53555 Federal Register / Vol. 70, No. 174 / Friday, September 9, 2005 / Rules and Regulations Boeing Model 757 airplanes. This AD requires inspections of certain wirebundles 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 wirebundles 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 VerDate Aug<18>2005 15:11 Sep 08, 2005 Jkt 205001 PO 00000 Frm 00019 Fmt 4700 Sfmt 4700 E:\FR\FM\09SER1.SGM 09SER1

## 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. 

### T ABLE 

### 1. —A IRPLANE 

### M ODELS AND 

### S ERVICE 

### B ULLETINS 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. 

### T ABLE 

### 2. — M ATERIAL 

### I NCORPORATED BY 

### R EFERENCE 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