### 16403 Federal Register / Vol. 70, No. 61 / Thursday, March 31, 2005 / Rules and Regulations

the repetitive inspections requirement specified in paragraph (h) of this AD for that actuator. Credit for Actions Previously Completed

(j) Inspections completed before the effective date of this AD using GE ASB No. CF34

– 8C

–AL S/B 75

–A0007, Revision 1 dated November 7, 2003; or Revision 2 dated December 16, 2004; or Revision 3 dated February 14, 2005; are acceptable for compliance with the corresponding inspection in this AD. Alternative Methods of Compliance

(k) The Manager, Engine 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

(l) Under 39.23, we impose the following conditions and limitations on the issuance and use of Special Flight Permits for this AD:

(1) If both engines report FADEC fault 1 messages at the same time, whether intermittent or continuous, review the MDC for master VG actuator faults before further flight. If actuator faults are still present for both engines, then replace at least one master VG actuator before further flight.

(2) If a master VG actuator switches channels, replace the actuator before further flight. Material Incorporated by Reference

(m) You must use GE Alert Service Bulletin No. CF34

– 8C

–AL S/B 75

–A0007, Revision 3, dated February 14, 2005, to perform the reviews and actuator dispositions required by this AD. The Director of the Federal Register approved the incorporation by reference of GE Alert Service Bulletin No. CF34

– 8C

–AL S/B 75

–A0007, Revision 3, dated February 14, 2005, under 5 U.S.C. 552(a) and 1 CFR part 51. You can get a copy from General Electric Company via Lockheed Martin Technology Services, 10525 Chester Road, Suite C, Cincinnati, Ohio 45215, telephone (513) 672

– 8400, fax (513) 672

– 8422. You may review copies at the Federal Aviation Administration (FAA), New England Region, Office of the Regional Counsel, 12 New England Executive Park, Burlington, MA 01803

– 5299; 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. Related Information

(n) None. Issued in Burlington, Massachusetts, on March 23, 2005. Peter A. White, Acting Manager, Engine and Propeller Directorate, Aircraft Certification Service. [FR Doc. 05

– 6247 Filed 3

– 30

– 05; 8:45 am]
**BILLING CODE 4910**

**– 13** 

**– P**  **DEPARTMENT OF TRANSPORTATION**
**Federal Aviation Administration**
**14 CFR Part 39 [Docket No. FAA** 

**– 2004** 

**– 18876; Directorate**  **Identifier 2003**

**– NM** 

**– 254** 

**– AD; Amendment**  **39**

**– 14032; AD 2005** 

**– 07** 

**– 08]**  **RIN 2120**

**– AA64**  **Airworthiness Directives; Boeing Model 757** 

**– 200 and** 

**– 200PF 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 Boeing Model 757

– 200 and

– 200PF series airplanes. This AD requires repetitive inspections and audible tap tests of the upper and lower skins of the trailing edge wedges on certain slats, and related investigative and corrective actions if necessary. This AD also provides an optional terminating action for the repetitive inspections and audible tap tests. This AD is prompted by a report of damage to the No. 4 leading edge slat. We are issuing this AD to prevent delamination of the leading edge slats, possible loss of pieces of the trailing edge wedge assembly during flight, reduction of the reduced maneuver and stall margins, and consequent reduced controllability of the airplane. **DATES :**  This AD becomes effective May 5, 2005.

The incorporation by reference of a certain publication listed in the AD is approved by the Director of the Federal Register as of May 5, 2005. **ADDRESSES :**  For service information identified in this AD, contact Boeing Commercial Airplanes, P.O. Box 3707, Seattle, Washington 98124

– 2207. You can examine this information 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

. Docket: The AD docket contains the proposed AD, comments, and any final disposition. You can 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 U.S. Department of Transportation, 400 Seventh Street SW., room PL

– 401, Washington, DC. This docket number is FAA

– 2004

– 18876; the directorate identifier for this docket is 2003

–NM

– 254

–AD. **FOR FURTHER INFORMATION CONTACT :**  Dennis Stremick, Aerospace Engineer, Airframe Branch, ANM

– 120S, FAA, Seattle Aircraft Certification Office, 1601 Lind Avenue, SW., Renton, Washington 98055

– 4056; telephone (425) 917

– 6450; fax (425) 914

– 6590. **SUPPLEMENTARY INFORMATION :**  The FAA proposed to amend 14 CFR Part 39 with an AD for certain Boeing Model 757

– 200 and -200PF series airplanes. That action, published in the Federal Register on August 17, 2004 (69 FR 51015), proposed to require repetitive inspections and audible tap tests of the upper and lower skins of the trailing edge wedges on certain slats, and related investigative and corrective actions if necessary. The proposed AD also provided an optional terminating action for the repetitive inspections and audible tap tests. Comments

We provided the public the opportunity to participate in the development of this AD. We have considered the comments that have been submitted on the proposed AD. Supportive Comment

One commenter supports the proposed AD. Request To Correct Typographical Error in Applicability

One commenter requests that the typographical error in paragraph (c), Applicability, of the proposed AD, be corrected. The Applicability in the proposed AD states that the AD applies to Boeing Model 737

– 200 and

– 200F series airplanes, as listed in Boeing Alert Service Bulletin 757

– 57A0063, dated June 26, 2003. The commenter states that the reference to Model 737

– 200 and

– 200F series airplanes should be corrected to avoid confusion between the referenced service bulletin and proposed AD.

We agree and the Applicability section of this AD has been corrected to reference ‘‘ Boeing Model 757

– 200 and

– 200PF series airplanes identified in Boeing Alert Service Bulletin 757

– 57A0063. * * * ’’ We discovered this error after the proposed AD was published. We find that our intent in the proposed AD was clear, as all other references throughout the proposed AD were correct, and the referenced service


### 16404 Federal Register / Vol. 70, No. 61 / Thursday, March 31, 2005 / Rules and Regulations
bulletin applies to Boeing Model 757

– 200 and

– 200PF series airplanes. Thus, we find no reason to re-open the comment period. Request To Clarify Applicability

The Air Transport Association (ATA) states that its member airlines concur with the intent of the proposed AD, but that the applicability of the proposed AD is unclear. The commenter notes that actions specified in the proposed AD overlap or duplicate the requirements of AD 90

– 23

– 06, amendment 39

– 6794. The commenter also states that several slat wedge configurations exist in in-service airplanes as a result of AD 91

– 22

– 51, amendment 39

– 8129, and several other service bulletins that address trailing edge wedges. The commenter contends that the applicability of the proposed AD is unclear with respect to these configurations, and recommends that we revise the proposed AD to clearly state the applicability with respect to the various configurations resulting from the aforementioned airworthiness directives and service bulletins.

We do not agree that the applicability of this AD requires revision. The applicability of this AD states that the AD applies to Boeing Model 757

– 200 and -200PF series airplanes, certificated in any category, identified in Boeing Alert Service Bulletin 757

– 57A0063, dated June 26, 2003. The effectivity in that service bulletin is all Boeing Model 757 series airplanes with line numbers 1 through 139 inclusive. This AD addresses line numbers 1 through 139 inclusive, regardless of configuration. Also, the airplane applicability for AD 91

– 22

– 51 has different line numbers from those in this AD. The applicability for that AD is Boeing Model 757 series airplanes, line numbers 140 through 335. We have not changed this AD regarding this issue. Request To Give Credit for Actions Accomplished Previously

One commenter requests that the proposed AD be revised to indicate that actions accomplished previously in accordance with Boeing Service Bulletin 757

– 57A0038 or 757

– 57A0045 are acceptable for compliance with the requirements of the proposed AD. The commenter states that the actions described in those service bulletins have the same results as the actions described in Boeing Alert Service Bulletin 757

– 57A0063, dated June 26, 2003. 

### S ERVICE 

### B ULLETINS 

### W ITH 

### S IMILAR 

### A CTIONS

Service Bulletin

—Dated

—Is cited in

— As the appropriate source of service information for

— Boeing Alert Service Bulletin 757

–

57A0063. June 26, 2003 ........................... The proposed AD ..................... Inspecting, repairing, and replacing trailing edge wedges. Boeing Service Bulletin 757

– 57A0038,

Revision 2. October 10, 1990 ...................... AD 90

– 23

– 06, amendment 39

– 6794. Inspecting, repairing, and replacing trailing edge wedges. Boeing Service Bulletin 757

– 57A0045 ...... October 16, 1991 ...................... AD 91

– 22

– 51, amendment 39

– 8129. Repetitive detailed inspections of the trailing edge wedges of slats 1 through 4 and 7 through 10.

We agree that accomplishment of the actions specified in Boeing Service Bulletin 757

– 57A0038, Revision 5, dated July 16, 1992, or Revision 6, dated November 10, 1994, only, are acceptable for compliance with the requirements of this AD. We do not agree that accomplishment of the actions specified in Boeing Service Bulletin 757

– 57A0045 is acceptable for compliance with the requirements of this AD. As stated previously, the applicability of AD 91

– 22

– 51 is Boeing Model 757 series airplanes, line numbers 140 through 335 inclusive, and the applicability of this AD is line numbers 1 through 139 inclusive.

We have included a new paragraph (h) in this AD, and reidentified the subsequent paragraphs accordingly. Paragraph (h) specifies that accomplishment of the actions in the Accomplishment Instructions of Boeing Service Bulletin 757

– 57A0038, Revision 5 or Revision 6 only, in conjunction with the use of BMS 5

– 137 adhesive, is acceptable for compliance with the requirements of this AD. Request To Revise Compliance Time for Repetitive Inspections and Tests

One commenter requests an extension of the compliance time from 18 months to 24 months for the repetitive detailed inspections and audible tap tests of the upper and lower skins of the trailing edge wedges. The commenter states that it performs maintenance checks ( ‘‘ Cchecks ’’ ) on its fleet every 24 months. The commenter also states that a compliance time of 18 months would require special maintenance visits in addition to the normally scheduled ‘‘ Cchecks, ’’ and the associated costs and downtime would be considerable. The commenter has reviewed its maintenance program, and the subject slats are currently inspected every 48 months. A review of the associated maintenance task cards did not reveal any discrepancies. The commenter notes that this change to the proposed AD would prevent operators from having to request approval of an AMOC for the proposed AD.

We do not agree with the commenter ’ s request to extend the compliance time. In developing an appropriate compliance time for this AD, we considered the urgency associated with the subject unsafe condition, the manufacturer ’ s recommended compliance time, and the practical aspect of accomplishing the required inspections within a period of time that corresponds to the normal scheduled maintenance program for most affected operators. However, according to the provisions of paragraph (k) of this AD, we may approve a request to adjust the compliance time if the request includes data that prove that the new compliance time would provide an acceptable level of safety. Explanation of Additional Change to This AD

Since the publication of the proposed AD, Boeing has received a Delegation Option Authorization (DOA). We have revised this AD to delegate the authority to approve an AMOC for any repair required by this AD to the Authorized Representative for the Boeing DOA Organization rather than the Designated Engineering Representative. Conclusion

We have carefully reviewed the available data, including the comments that have been submitted, and determined that air safety and the


### 16405 Federal Register / Vol. 70, No. 61 / Thursday, March 31, 2005 / Rules and Regulations
public interest require adopting the AD with the changes described previously. We have determined that these changes will neither increase the economic burden on any operator nor increase the scope of the AD. Costs of Compliance This AD affects about 139 airplanes worldwide. The following table provides the estimated costs for U.S. operators to comply with this AD. 

### E STIMATED 

### C OSTS

Action Work hours Average labor rate per

hour Parts Cost per airplane Number of U.S.- registered airplanes Fleet cost

Inspection test, per inspection

cycle. 6 (1 work hour perslat, 6 slats per airplane.). $65 None .. $390, per inspection/ test cycle. 97 $37,830, per inspection/test 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. 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 FAA amends § 39.13 by adding the following new airworthiness directive (AD):
2005

– 07

– 08 Boeing: Amendment 39

– 14032. Docket No. FAA

– 2004

– 18876; Directorate Identifier 2003

– NM

– 254

–AD. Effective Date

(a) This AD becomes effective May 5, 2005. Affected ADs

(b) None. Applicability

(c) This AD applies to Boeing Model 757

– 200 and

– 200PF series airplanes, certificated in any category, identified in Boeing Alert Service Bulletin 757

– 57A0063, dated June 26, 2003. Unsafe Condition

(d) This AD was prompted by a report of damage to the No. 4 leading edge slat. We are issuing this AD to prevent delamination of the leading edge slats, possible loss of pieces of the trailing edge wedge assembly during flight, reduction of the reduced maneuver and stall margins, and consequent 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. Repetitive Inspections and Tests

(f) Within 18 months after the effective date of this AD: Do a detailed inspection and an audible tap test of the upper and lower skins of the trailing edge wedges on slats No. 2 through No. 4 inclusive and No. 7 through No. 9 inclusive, for evidence of damage or cracking, in accordance with the Accomplishment Instructions of Boeing Alert Service Bulletin 757

– 57A0063, dated June 26, 2003. Repeat the detailed inspection and audible tap test thereafter at intervals not to exceed 18 months.

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. ’’ Related Investigative and Corrective Actions

(g) If any damage or cracking is found during any inspection or audible tap test required by paragraph (f) of this AD: Before further flight, do the related investigative action, if applicable, and replace the affected part with a new trailing edge wedge assembly or repair the affected part, in accordance with the Accomplishment Instructions of Boeing Alert Service Bulletin 757

– 57A0063, dated June 26, 2003. Accomplishing the replacement terminates the repetitive inspections and audible tap tests required by paragraph (f) of this AD for that wedge assembly only. Actions Accomplished Previously

(h) Previous accomplishment of all of the actions specified in the Accomplishment Instructions of Boeing Service Bulletin 757

– 57A0038, Revision 5, dated July 16, 1992; or Revision 6, dated November 10, 1994; in conjunction with the use of BMS 5

– 137 adhesive; is acceptable for compliance with the inspection requirements of paragraph (f) of this AD.


### 16406 Federal Register / Vol. 70, No. 61 / Thursday, March 31, 2005 / Rules and Regulations

Parts Installation

(i) As of the effective date of this AD, no trailing edge wedge assembly having a part number listed in the ‘‘ Existing Part Number ’’ column of the table in paragraph 2.C.3. of Boeing Alert Service Bulletin 757

– 57A0063, dated June 26, 2003, may be installed on any airplane unless it has been inspected, tested, and had any necessary corrective actions accomplished in accordance with this AD. Optional Terminating Action

(j) Replacing all trailing edge wedge assemblies with new, improved wedge assemblies in accordance with Part III of the Accomplishment Instructions of Boeing Alert Service Bulletin 757

– 57A0063, dated June 26, 2003, terminates the requirements of paragraph (f) of this AD. Alternative Methods of Compliance (AMOCs)

(k)(1) The Manager, Seattle Aircraft Certification Office (ACO), FAA, has the authority to approve AMOCs for this AD, if requested in accordance with the procedures found in 14 CFR 39.19.

(2) An AMOC that provides an acceptable level of safety may be used for any repair required by this AD, if it is approved by an Authorized Representative for the Boeing Delegation Option Authorization Organization who has been authorized by the Manager, Seattle ACO, to make those findings. For a repair method to be approved, the repair must meet the certification basis of the airplane, and the approval must specifically refer to this AD. Material Incorporated by Reference

(l) You must use Boeing Alert Service Bulletin 757

– 57A0063, dated June 26, 2003, to perform the actions that are required by this AD, unless the AD specifies otherwise. The Director of the Federal Register approves the incorporation by reference of this document in accordance with 5 U.S.C. 552(a) and 1 CFR part 51. For copies of the service information, contact Boeing Commercial Airplanes, P.O. Box 3707, Seattle, Washington 98124

– 2207. For information on the availability of this material at the National Archives and Records Administration (NARA), call (202) 741

– 6030, or go to http://www.archives.gov/ federal

_register/code

_ of

_ federal

_regulations/ ibr

_locations.html

. You may view the AD docket at the Docket Management Facility, U.S. Department of Transportation, 400 Seventh Street SW., room PL

– 401, Nassif Building, Washington, DC.

Issued in Renton, Washington, on March 22, 2005. Ali Bahrami, Manager, Transport Airplane Directorate, Aircraft Certification Service. [FR Doc. 05

– 6259 Filed 3

– 30

– 05; 8:45 am]
**BILLING CODE 4910**

**– 13** 

**– P**  **DEPARTMENT OF TRANSPORTATION**
**Federal Aviation Administration**
**14 CFR Part 39 [Docket No. FAA** 

**– 2004** 

**– 18024; Directorate**  **Identifier 2003**

**– NE** 

**– 39** 

**– AD; Amendment 39** 

**– 14034; AD 2005** 

**– 07** 

**– 10]** 
**RIN 2120**

**– AA64**  **Airworthiness Directives; Rolls-Royce (1971) Limited, Bristol Engine Division**  **Model Viper Mk.601**

**– 22 Turbojet**  **Engines**
**AGENCY :**  Federal Aviation Administration (FAA), DOT. **ACTION :**  Final rule.

**SUMMARY :**  The FAA is superseding an existing airworthiness directive (AD) for Rolls-Royce (1971) Limited, Bristol Engine Division (RR) model Viper Mk.601

– 22 turbojet engines. That AD currently requires reducing the life of certain 1st stage turbine rotor blades from 7,000 hours time-in-service (TIS) to 4,600 hours TIS, and provides a drawdown schedule for blades that have already exceeded the new reduced life limit. This AD requires the same actions but changes certain compliance times to be in agreement with RR Alert Service Bulletin (ASB) No. 72

–A184, dated January 2001. This AD results from comments received on AD 2004

– 13

– 03, that the AD is unnecessarily more restrictive than the requirements in the associated RR ASB No. 72

–A184. We are issuing this AD to prevent multiple failures of 1st stage turbine rotor blades that could result in a dual-engine shutdown.
**DATES :**  This AD becomes effective May 5, 2005. **ADDRESSES :**  You can get the service information identified in this proposed AD from Rolls-Royce Limited, Bristol Engines Division, Technical Publications Department CLS

– 4, P.O. Box 3, Filton, Bristol, BS34 7QE England; telephone 117

– 979

– 1234, fax 117

– 979

– 7575.

You may examine the AD docket on the Internet at http://dms.dot.gov or in Room PL

– 401 on the plaza level of the Nassif Building, 400 Seventh Street, SW., Washington, DC. **FOR FURTHER INFORMATION CONTACT :**  Ian Dargin, Aerospace Engineer, Engine Certification Office, FAA, Engine and Propeller Directorate, 12 New England Executive Park, Burlington, MA 01803

– 5299; telephone (781) 238

– 7178; fax (781) 238

– 7199. **SUPPLEMENTARY INFORMATION :**  The FAA proposed to amend 14 CFR part 39 with a proposed airworthiness directive (AD). The proposed AD applies to Rolls-Royce (1971) Limited, Bristol Engine Division (RR) model Viper Mk.601

– 22 turbojet engines. We published the proposed AD in the Federal Register on October 29, 2004 (69 FR 63104). That action proposed to require reducing the life of certain 1st stage turbine rotor blades from 7,000 hours TIS to 4,600 hours TIS, provide a drawdown schedule for blades that have already exceeded the new reduced life limit, and change certain compliance times to be in agreement with RR ASB No. 72

–A184, dated January 2001. Examining the AD Docket

You may examine the docket that contains the AD, any comments received, and any final disposition in person at the DMS Docket Offices between 9 a.m. and 5 p.m., Monday through Friday, except Federal holidays. The Docket Office (telephone (800) 647

– 5227) is located on the plaza level of the Department of Transportation Nassif Building at the street address stated in **ADDRESSES** . Comments will be available in the AD docket shortly after the DMS receives them. Comments

We provided the public the opportunity to participate in the development of this AD. We received no comments on the proposal 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

We estimate that 84 RR model Viper Mk.601

– 22 turbojet engines installed on airplanes of U.S. registry will be affected by this AD. We estimate that no additional labor cost will be incurred to replace 1st stage turbine rotor blades when done at time of engine overhaul. A replacement set 1st stage turbine rotor blades costs about $166,987. Based on these figures, we estimate the total cost of the AD to U.S. operators to be $14,026,950. 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.