Airworthiness Directives; Robinson Helicopter Company Model R44 and R44 II Helicopters, 28830-28832 [E7-9687]

Download as PDF 28830 Federal Register / Vol. 72, No. 99 / Wednesday, May 23, 2007 / Rules and Regulations 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): I 2007–10–10 Airbus: Amendment 39–15051. Docket No. FAA–2006–26120; Directorate Identifier 2006–NM–184–AD. Effective Date (a) This AD becomes effective June 27, 2007. Affected ADs (b) None. Applicability (c) This AD applies to all Airbus Model A300–600 series airplanes, certificated in any category. Note 1: This AD requires revisions to certain operator maintenance documents to include new inspections and critical design configuration control limitations (CDCCLs). Compliance with the operator maintenance documents is required by 14 CFR 91.403(c). For airplanes that have been previously modified, altered, or repaired in the areas addressed by these inspections and CDCCLs, the operator may not be able to accomplish the inspections and CDCCLs described in the revisions. In this situation, to comply with 14 CFR 91.403(c), the operator must request approval for an alternative method of compliance according to paragraph (j) of this AD. The request should include a description of changes to the required inspections and CDCCLs that will preserve the critical ignition source prevention feature of the affected fuel system. Unsafe Condition (d) This AD results from fuel system reviews conducted by the manufacturer. We are issuing this AD to prevent the potential of ignition sources inside fuel tanks, which, in combination with flammable fuel vapors caused by latent failures, alterations, repairs, or maintenance actions, could result in fuel tank explosions and consequent loss of the airplane. cprice-sewell on PROD1PC71 with RULES 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. Revise Airworthiness Limitations Section (ALS) To Incorporate Fuel Maintenance and Inspection Tasks (f) Within 3 months after the effective date of this AD, revise the ALS of the Instructions for Continued Airworthiness to incorporate Airbus A300–600 ALS Part 5—Fuel Airworthiness Limitations, dated May 31, 2006, as defined in Airbus A300–600 Fuel Airworthiness Limitations, Document 95A.1929/05, Issue 1, dated December 19, 2005 (approved by the European Aviation Safety Agency (EASA) on March 13, 2006), Section 1, ‘‘Maintenance/Inspection Tasks’’ (hereafter referred to as ‘‘Section 1 of VerDate Aug<31>2005 15:35 May 22, 2007 Jkt 211001 Document 95A.1929/05’’). For all tasks identified in Section 1 of Document 95A.1929/05, the initial compliance times start from the later of the times specified in paragraphs (f)(1) and (f)(2) of this AD, and the repetitive inspections must be accomplished thereafter at the intervals specified in Section 1 of Document 95A.1929/05, except as provided by paragraph (g) of this AD. (1) The effective date of this AD. (2) The date of issuance of the original French standard airworthiness certificate or the date of issuance of the original French export certificate of airworthiness. Note 2: Airbus Operator Information Telex (OIT) SE 999.0076/06, dated June 20, 2006, identifies the applicable sections of the Airbus A300–600 airplane maintenance manual necessary for accomplishing the tasks specified in Section 1 of Document 95A.1929/05. Initial Compliance Time for Task 28–18–00– 03–1 (g) For Task 28–18–00–03–1, ‘‘Operational check of lo-level/underfull/calibration sensors,’’ identified in Section 1 of Document 95A.1929/05: The initial compliance time is the later of the times specified in paragraphs (g)(1) and (g)(2) of this AD. Thereafter, Task 28–18–00–03–1 must be accomplished at the repetitive interval specified in Section 1 of Document 95A.1929/05. (1) Prior to the accumulation of 40,000 total flight hours. (2) Within 72 months or 20,000 flight hours after the effective date of this AD, whichever occurs first. Revise ALS To Incorporate CDCCLs (h) Within 12 months after the effective date of this AD, revise the ALS of the Instructions for Continued Airworthiness to incorporate Airbus A300–600 ALS Part 5— Fuel Airworthiness Limitations, dated May 31, 2006, as defined in Airbus A300–600 Fuel Airworthiness Limitations, Document 95A.1929/05, Issue 1, dated December 19, 2005 (approved by the EASA on March 13, 2006), Section 2, ‘‘Critical Design Configuration Control Limitations.’’ No Alternative Inspections, Inspection Intervals, or CDCCLs (i) Except as provided by paragraph (j) of this AD: After accomplishing the actions specified in paragraphs (f) and (h) of this AD, no alternative inspections, inspection intervals, or CDCCLs may be used. Alternative Methods of Compliance (AMOCs) (j)(1) 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. (2) To request a different method of compliance or a different compliance time for this AD, follow the procedures in 14 CFR 39.19. Before using any approved AMOC on any airplane to which the AMOC applies, notify your appropriate principal inspector (PI) in the FAA Flight Standards District Office (FSDO), or lacking a PI, your local FSDO. PO 00000 Frm 00006 Fmt 4700 Sfmt 4700 Related Information (k) EASA airworthiness directive 2006– 0201, dated July 11, 2006, also addresses the subject of this AD. Material Incorporated by Reference (l) You must use Airbus A300–600 ALS Part 5—Fuel Airworthiness Limitations, dated May 31, 2006; and Airbus A300–600 Fuel Airworthiness Limitations, Document 95A.1929/05, Issue 1, dated December 19, 2005; as applicable; 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 Airbus, 1 Rond Point Maurice Bellonte, 31707 Blagnac Cedex, France, for a copy of this service information. You may review copies at the FAA, Transport Airplane Directorate, 1601 Lind Avenue, SW., Renton, Washington; 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/cfr/ibrlocations.html. Issued in Renton, Washington, on May 7, 2007. Stephen P. Boyd, Acting Manager, Transport Airplane Directorate, Aircraft Certification Service. [FR Doc. E7–9399 Filed 5–22–07; 8:45 am] BILLING CODE 4910–13–P DEPARTMENT OF TRANSPORTATION Federal Aviation Administration 14 CFR Part 39 [Docket No. FAA–2006–26696; Directorate Identifier 2006–SW–19–AD; Amendment 39– 15058; AD 2007–11–01] RIN 2120–AA64 Airworthiness Directives; Robinson Helicopter Company Model R44 and R44 II Helicopters Federal Aviation Administration, DOT. ACTION: Final rule. AGENCY: SUMMARY: This amendment adopts a new airworthiness directive (AD) for Robinson Helicopter Company (Robinson) Model R44 and R44 II helicopters that have a certain seat belt buckle (buckle) assembly installed, that requires removing the buckle assembly and the buckle assembly spacer, and replacing them with airworthy parts. This amendment is prompted by an accident in which a seat belt failed, and also by reports of cracking in the buckle assembly stainless support strap (support strap). The actions specified by this AD are intended to prevent cracking E:\FR\FM\23MYR1.SGM 23MYR1 cprice-sewell on PROD1PC71 with RULES Federal Register / Vol. 72, No. 99 / Wednesday, May 23, 2007 / Rules and Regulations in the support strap and failure of a seat belt. DATES: Effective June 27, 2007. The incorporation by reference of certain publications listed in the regulations is approved by the Director of the Federal Register as of June 27, 2007. ADDRESSES: You may get the service information identified in this AD from Robinson Helicopter Company, 2901 Airport Drive, Torrance, California 90505, telephone (310) 539–0508, fax (310) 539–5198. Examining The Docket: You may examine the docket that contains this AD, any comments, and other information on the Internet at http:// dms.dot.gov, or at the Docket Management System (DMS), U.S. Department of Transportation, 400 Seventh Street, SW., Room PL–401, on the plaza level of the Nassif Building, Washington, DC. FOR FURTHER INFORMATION CONTACT: Venessa Stiger, Aviation Safety Engineer, FAA, Los Angeles Aircraft Certification Office, 3960 Paramount Blvd., Lakewood, California 90712– 4137, telephone (562) 627–5337, fax (562) 627–5210. SUPPLEMENTARY INFORMATION: A proposal to amend 14 CFR part 39 to include an AD for the specified model helicopters was published in the Federal Register on January 9, 2007 (72 FR 918). That action proposed to require, for Robinson Model R44 helicopters, through serial number (S/N) 1576, and Model R44 II helicopters, through S/N 11107, that have a C628– 4, revision M or prior, buckle assembly installed, removing the buckle assembly and the A130–52 buckle assembly spacer and replacing them with a C628– 4, revision N buckle assembly and a new A130–52 buckle assembly spacer within 100 hours time-in-service. We have reviewed Robinson Service SB–56, dated March 29, 2006, which describes procedures for inspecting the buckle assemblies for cracks and replacing the buckle assemblies. This AD does not require inspecting the buckle assemblies for cracks. Interested persons have been afforded an opportunity to participate in the making of this amendment. No comments were received on the proposal or the FAA’s determination of the cost to the public. The FAA has determined that air safety and the public interest require the adoption of the rule as proposed. The FAA estimates that this AD will affect 900 helicopters of U.S. registry, and replacing a buckle assembly will take approximately 0.2 work hour per VerDate Aug<31>2005 15:35 May 22, 2007 Jkt 211001 buckle to accomplish at an average labor rate of $80 per work hour. Required parts will cost approximately $105 for each C628–4, revision N buckle assembly, and $8.25 for each A130–52 buckle assembly spacer. Based on these figures, we estimate the total cost impact of the AD on U.S. operators to be $517 for each helicopter, or $465,300 for the entire fleet, assuming that four buckle assemblies and buckle assembly spacers are replaced in each helicopter. 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 the regulation: 1. Is not a ‘‘significant regulatory action’’ under Executive Order 12866; 2. Is not a ‘‘significant rule’’ under the 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 an economic evaluation of the estimated costs to comply with this AD. See the DMS to examine the economic evaluation. 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. List of Subjects in 14 CFR Part 39 Air transportation, Aircraft, Aviation safety, Incorporation by reference, Safety. PO 00000 Frm 00007 Fmt 4700 Sfmt 4700 28831 Adoption of the Amendment Accordingly, pursuant to the authority delegated to me by the Administrator, the Federal Aviation Administration amends part 39 of the Federal Aviation Regulations (14 CFR part 39) as follows: I PART 39—AIRWORTHINESS DIRECTIVES 1. The authority citation for part 39 continues to read as follows: I Authority: 49 U.S.C. 106(g), 40113, 44701. § 39.13 [Amended] 2. Section 39.13 is amended by adding a new airworthiness directive to read as follows: I 2007–11–01 Robinson Helicopter Company: Amendment 39–15058. Docket No. FAA–2006–26696; Directorate Identifier 2006–SW–19–AD. Applicability: Model R44 helicopters, through serial number (S/N) 1576, and Model R44 II helicopters, through S/N 11107, with a seat belt buckle assembly (buckle assembly) part number C628–4, revision M or prior, installed, certificated in any category. Compliance: Required within 100 hours time-in-service, unless accomplished previously. To prevent cracking in the buckle assembly stainless support strap and failure of a seat belt, accomplish the following: (a) Remove the buckle assembly and any A130–52 buckle assembly spacer, and replace them with a C628–4, revision N buckle assembly and a new A130–52 buckle assembly spacer, in accordance with the Compliance Procedure, paragraph 3, in Robinson Helicopter Company Service Bulletin SB–56, dated March 29, 2006. The new A130–52 buckle assembly spacers have been redesigned to be slightly longer than the previous A130–52 buckle assembly spacers, to reduce friction in the joint. Note: Inspecting the buckle assembly for cracks is not required by this AD. (b) Replacing the buckle assembly and buckle assembly spacer with a C628–4, Revision N buckle assembly and a new A130–52 buckle assembly spacer is a terminating action for the requirements of this AD. (c) To request a different method of compliance or a different compliance time for this AD, follow the procedures in 14 CFR 39.19. Contact the Manager, Los Angeles Aircraft Certification Office, FAA, ATTN: Venessa Stiger, Aviation Safety Engineer, 3960 Paramount Blvd., Lakewood, California 90712–4137, telephone (562) 627–5337, fax (562) 627–5210, for information about previously approved alternative methods of compliance. (d) The replacements shall be done in accordance with Robinson Helicopter Company Service Bulletin SB–56, dated March 29, 2006. The Director of the Federal Register approved this incorporation by reference in accordance with 5 U.S.C. 552(a) and 1 CFR part 51. Copies may be obtained from Robinson Helicopter Company, 2901 E:\FR\FM\23MYR1.SGM 23MYR1 28832 Federal Register / Vol. 72, No. 99 / Wednesday, May 23, 2007 / Rules and Regulations Airport Drive, Torrance, California 90505, telephone (310) 539–0508, fax (310) 539– 5198. Copies may be inspected at the FAA, Office of the Regional Counsel, Southwest Region, 2601 Meacham Blvd., Room 663, Fort Worth, Texas 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. (e) This amendment becomes effective on June 27, 2007. [Docket No. FAA–2007–26864; Directorate Identifier 2006–NM–228–AD; Amendment 39–15053; AD 2007–10–12] the flight deck door and corrective actions if necessary. This proposed AD also removes certain airplanes from the applicability. This AD results from a report of smoke and fumes in the cockpit of a Model 737–300 series airplane. We are issuing this AD to prevent inadvertent release of the decompression latch and consequent opening of the decompression panel in the flight deck door, or penetration of the flight deck door by smoke, any of which could result in injury to the airplane flightcrew. We are also proposing this AD to detect and correct wire chafing, which could result in arcing, fire, and/or reduced controllability of the airplane. DATES: This AD becomes effective June 27, 2007. On July 19, 2005 (70 FR 34316, June 14, 2005), the Director of the Federal Register approved the incorporation by reference of certain service information. On July 25, 2003 (68 FR 41063, July 10, 2003), the Director of the Federal Register approved the incorporation by reference of certain other service information. RIN 2120–AA64 ADDRESSES: Issued in Fort Worth, Texas, on May 8, 2007. David A. Downey, Manager, Rotorcraft Directorate, Aircraft Certification Service. [FR Doc. E7–9687 Filed 5–22–07; 8:45 am] BILLING CODE 4910–13–P DEPARTMENT OF TRANSPORTATION Federal Aviation Administration 14 CFR Part 39 Airworthiness Directives; Boeing Model 737–200, –300, –400, –500, –600, –700, –800, and –900 Series Airplanes; Boeing Model 757–200 and –300 Series Airplanes; and McDonnell Douglas Model DC–10–10, DC–10–10F, DC–10– 30, DC–10–30F, DC–10–40, MD–10– 30F, MD–11, and MD–11F Airplanes; Equipped With Reinforced Flight Deck Doors Installed in Accordance With Supplemental Type Certificate (STC) ST01335LA, STC ST01334LA, and STC ST01391LA, Respectively Federal Aviation Administration (FAA), Department of Transportation (DOT). ACTION: Final rule. cprice-sewell on PROD1PC71 with RULES AGENCY: SUMMARY: The FAA is superseding an existing airworthiness directive (AD), which applies to certain transport category airplanes identified above. That AD currently requires modification of the reinforced flight deck door and other actions related to the reinforced flight deck door. Those other actions include modifying the door, inspecting and modifying wiring in the area, and revising the maintenance program to require more frequent testing of the decompression panels of the flight deck door. This new AD continues to require the existing requirements. This new AD adds airplanes to the existing requirement of a one-time inspection for chafing of wire bundles in the area of VerDate Aug<31>2005 15:35 May 22, 2007 Jkt 211001 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; Boeing Commercial Airplanes, Long Beach Division, 3855 Lakewood Boulevard, Long Beach, California 90846, Attention: Data and Service Management, Dept. C1–L5A (D800– 0024); or C&D Aerospace, 5701 Bolsa Avenue, Huntington Beach, California 92647–2063; for service information identified in this AD. FOR FURTHER INFORMATION CONTACT: Ron Atmur, Aerospace Engineer, Airframe Branch, ANM–120L, FAA, Los Angeles Aircraft Certification Office, 3960 Paramount Boulevard, Lakewood, California 90712–4137; telephone (562) 627–5224; fax (562) 627–5210. 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 PO 00000 Frm 00008 Fmt 4700 Sfmt 4700 the street address stated in the section. ADDRESSES Discussion The FAA issued a notice of proposed rulemaking (NPRM) to amend 14 CFR part 39 to include an AD that supersedes AD 2005–12–05, amendment 39–14121 (70 FR 34316, June 14, 2005). (A correction of that AD was published in the Federal Register on June 28, 2005 (70 FR 37152).) The existing AD applies to Boeing Model 737–200, –300, –400, –500, –600, –700, –800, and –900 series airplanes; Boeing Model 757–200 and –300 series airplanes; and McDonnell Douglas Model DC–10–10, DC–10–10F, DC–10–30, DC–10–30F, DC–10–40, MD– 10–10F, MD–10–30F, MD–11, and MD– 11F airplanes. That NPRM was published in the Federal Register on January 19, 2007 (72 FR 2475). That NPRM proposed to continue to require modification of the reinforced flight deck door and other actions related to the reinforced flight deck door. Those other actions include modifying the door, inspecting and modifying wiring in the area, and revising the maintenance program to require more frequent testing of the decompression panels of the flight deck door. That NPRM also proposed to add airplanes to the existing requirement of a one-time inspection for chafing of wire bundles in the area of the flight deck door and corrective actions if necessary. That NPRM also proposed to remove certain airplanes from the applicability. Comments We provided the public the opportunity to participate in the development of this AD. We have considered the comments that have been received on the NPRM. Support for the NPRM Boeing, United Airlines, and the Air Line Pilots Association, International (ALPA) support the intent of the NPRM. Request To Issue a Separate AD United Airlines requests that rather than superseding the existing AD, we issue a separate AD action since the new proposed actions are applicable only to the Model 737–300, –400, and –500 series airplanes. The commenter states that if the existing AD is superseded, numerous documents must be updated for all airplane models affected by the earlier actions. The commenter asserts that superseding an already complex compliance plan provides an opportunity for non-compliance and unnecessarily increases an operator’s workload. E:\FR\FM\23MYR1.SGM 23MYR1

Agencies

[Federal Register Volume 72, Number 99 (Wednesday, May 23, 2007)]
[Rules and Regulations]
[Pages 28830-28832]
From the Federal Register Online via the Government Printing Office [www.gpo.gov]
[FR Doc No: E7-9687]


-----------------------------------------------------------------------

DEPARTMENT OF TRANSPORTATION

Federal Aviation Administration

14 CFR Part 39

[Docket No. FAA-2006-26696; Directorate Identifier 2006-SW-19-AD; 
Amendment 39-15058; AD 2007-11-01]
RIN 2120-AA64


Airworthiness Directives; Robinson Helicopter Company Model R44 
and R44 II Helicopters

AGENCY: Federal Aviation Administration, DOT.

ACTION: Final rule.

-----------------------------------------------------------------------

SUMMARY: This amendment adopts a new airworthiness directive (AD) for 
Robinson Helicopter Company (Robinson) Model R44 and R44 II helicopters 
that have a certain seat belt buckle (buckle) assembly installed, that 
requires removing the buckle assembly and the buckle assembly spacer, 
and replacing them with airworthy parts. This amendment is prompted by 
an accident in which a seat belt failed, and also by reports of 
cracking in the buckle assembly stainless support strap (support 
strap). The actions specified by this AD are intended to prevent 
cracking

[[Page 28831]]

in the support strap and failure of a seat belt.

DATES: Effective June 27, 2007.
    The incorporation by reference of certain publications listed in 
the regulations is approved by the Director of the Federal Register as 
of June 27, 2007.

ADDRESSES: You may get the service information identified in this AD 
from Robinson Helicopter Company, 2901 Airport Drive, Torrance, 
California 90505, telephone (310) 539-0508, fax (310) 539-5198.
    Examining The Docket: You may examine the docket that contains this 
AD, any comments, and other information on the Internet at http://
dms.dot.gov, or at the Docket Management System (DMS), U.S. Department 
of Transportation, 400 Seventh Street, SW., Room PL-401, on the plaza 
level of the Nassif Building, Washington, DC.

FOR FURTHER INFORMATION CONTACT: Venessa Stiger, Aviation Safety 
Engineer, FAA, Los Angeles Aircraft Certification Office, 3960 
Paramount Blvd., Lakewood, California 90712-4137, telephone (562) 627-
5337, fax (562) 627-5210.

SUPPLEMENTARY INFORMATION: A proposal to amend 14 CFR part 39 to 
include an AD for the specified model helicopters was published in the 
Federal Register on January 9, 2007 (72 FR 918). That action proposed 
to require, for Robinson Model R44 helicopters, through serial number 
(S/N) 1576, and Model R44 II helicopters, through S/N 11107, that have 
a C628-4, revision M or prior, buckle assembly installed, removing the 
buckle assembly and the A130-52 buckle assembly spacer and replacing 
them with a C628-4, revision N buckle assembly and a new A130-52 buckle 
assembly spacer within 100 hours time-in-service.
    We have reviewed Robinson Service SB-56, dated March 29, 2006, 
which describes procedures for inspecting the buckle assemblies for 
cracks and replacing the buckle assemblies. This AD does not require 
inspecting the buckle assemblies for cracks.
    Interested persons have been afforded an opportunity to participate 
in the making of this amendment. No comments were received on the 
proposal or the FAA's determination of the cost to the public. The FAA 
has determined that air safety and the public interest require the 
adoption of the rule as proposed.
    The FAA estimates that this AD will affect 900 helicopters of U.S. 
registry, and replacing a buckle assembly will take approximately 0.2 
work hour per buckle to accomplish at an average labor rate of $80 per 
work hour. Required parts will cost approximately $105 for each C628-4, 
revision N buckle assembly, and $8.25 for each A130-52 buckle assembly 
spacer. Based on these figures, we estimate the total cost impact of 
the AD on U.S. operators to be $517 for each helicopter, or $465,300 
for the entire fleet, assuming that four buckle assemblies and buckle 
assembly spacers are replaced in each helicopter.

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 the regulation:
    1. Is not a ``significant regulatory action'' under Executive Order 
12866;
    2. Is not a ``significant rule'' under the 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 an economic evaluation of the estimated costs to comply 
with this AD. See the DMS to examine the economic evaluation.

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.

List of Subjects in 14 CFR Part 39

    Air transportation, Aircraft, Aviation safety, Incorporation by 
reference, Safety.

Adoption of the Amendment

0
Accordingly, pursuant to the authority delegated to me by the 
Administrator, the Federal Aviation Administration amends part 39 of 
the Federal Aviation Regulations (14 CFR part 39) as follows:

PART 39--AIRWORTHINESS DIRECTIVES

0
1. The authority citation for part 39 continues to read as follows:

    Authority: 49 U.S.C. 106(g), 40113, 44701.


Sec.  39.13  [Amended]

0
2. Section 39.13 is amended by adding a new airworthiness directive to 
read as follows:

2007-11-01 Robinson Helicopter Company: Amendment 39-15058. Docket 
No. FAA-2006-26696; Directorate Identifier 2006-SW-19-AD.

    Applicability: Model R44 helicopters, through serial number (S/
N) 1576, and Model R44 II helicopters, through S/N 11107, with a 
seat belt buckle assembly (buckle assembly) part number C628-4, 
revision M or prior, installed, certificated in any category.
    Compliance: Required within 100 hours time-in-service, unless 
accomplished previously.
    To prevent cracking in the buckle assembly stainless support 
strap and failure of a seat belt, accomplish the following:
    (a) Remove the buckle assembly and any A130-52 buckle assembly 
spacer, and replace them with a C628-4, revision N buckle assembly 
and a new A130-52 buckle assembly spacer, in accordance with the 
Compliance Procedure, paragraph 3, in Robinson Helicopter Company 
Service Bulletin SB-56, dated March 29, 2006. The new A130-52 buckle 
assembly spacers have been redesigned to be slightly longer than the 
previous A130-52 buckle assembly spacers, to reduce friction in the 
joint.

    Note: Inspecting the buckle assembly for cracks is not required 
by this AD.

    (b) Replacing the buckle assembly and buckle assembly spacer 
with a C628-4, Revision N buckle assembly and a new A130-52 buckle 
assembly spacer is a terminating action for the requirements of this 
AD.
    (c) To request a different method of compliance or a different 
compliance time for this AD, follow the procedures in 14 CFR 39.19. 
Contact the Manager, Los Angeles Aircraft Certification Office, FAA, 
ATTN: Venessa Stiger, Aviation Safety Engineer, 3960 Paramount 
Blvd., Lakewood, California 90712-4137, telephone (562) 627-5337, 
fax (562) 627-5210, for information about previously approved 
alternative methods of compliance.
    (d) The replacements shall be done in accordance with Robinson 
Helicopter Company Service Bulletin SB-56, dated March 29, 2006. The 
Director of the Federal Register approved this incorporation by 
reference in accordance with 5 U.S.C. 552(a) and 1 CFR part 51. 
Copies may be obtained from Robinson Helicopter Company, 2901

[[Page 28832]]

Airport Drive, Torrance, California 90505, telephone (310) 539-0508, 
fax (310) 539-5198. Copies may be inspected at the FAA, Office of 
the Regional Counsel, Southwest Region, 2601 Meacham Blvd., Room 
663, Fort Worth, Texas 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.
    (e) This amendment becomes effective on June 27, 2007.

    Issued in Fort Worth, Texas, on May 8, 2007.
David A. Downey,
Manager, Rotorcraft Directorate, Aircraft Certification Service.
 [FR Doc. E7-9687 Filed 5-22-07; 8:45 am]
BILLING CODE 4910-13-P