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): 

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. 

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 

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. 

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 

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 


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Federal Register / Vol. 72, No. 99 / Wednesday, May 23, 2007 / Rules and Regulations 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 

■ 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 

■ 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. 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 


cprice-sewell on PROD1PC71 with RULES
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. 

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 

[Docket No. FAA–2007–26864; Directorate 

Identifier 2006–NM–228–AD; Amendment 

39–15053; AD 2007–10–12] 

RIN 2120–AA64 

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 

AGENCY: Federal Aviation 

Administration (FAA), Department of 

Transportation (DOT). 

ACTION: Final rule. 

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 

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. 

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; 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 

the street address stated in the 

ADDRESSES section. 

Discussion 

The FAA issued a notice of proposed 

rulemaking (NPRM) to amend 14 CFR 

part 39 to include an AD that 

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. 


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