64854 Federal Register / Vol. 69, No. 216 / Tuesday, November 9, 2004 / Rules and Regulations 

DEPARTMENT OF TRANSPORTATION

Federal Aviation Administration 

14 CFR Part 39

[Docket No. FAA–2004–18603; Directorate 

Identifier 2003–NM–14–AD; Amendment 39–

13850; AD 2004–22–22] 

RIN 2120–AA64

Airworthiness Directives; Airbus Model 

A310 Series Airplanes; and Model 

A300 B4–600, B4–600R, and F4–600R 

Series Airplanes; and Model C4–605R 

Variant F Airplanes (Collectively Called 

A300–600)

AGENCY: Federal Aviation 

Administration (FAA), DOT.

ACTION: Final rule.

SUMMARY: The FAA is superseding an 

existing airworthiness directive (AD), 

which applies to certain Airbus Model 

A310 series airplanes; and Model A300 

B4–600, B4–600R, and F4–600R series 

airplanes; and Model C4–605R Variant F 

airplanes (collectively called A300–

600). That AD currently requires 

modifying the ram air turbine (RAT) by 

replacing the ejection jack. This new AD 

requires a one-time inspection of the 

RAT ejection jack to determine the part 

number, and further investigative and 

corrective actions if necessary. This AD 

is prompted by the discovery of a 

rupture in the housing of one of the 

RAT ejection jacks installed as specified 

in the existing AD. We are issuing this 

AD to prevent rupture of the housing of 

the RAT ejection jack due to 

overpressure in the jack caused by 

overfilling the hydraulic fluid, and 

consequent failure of the RAT ejection 

jack. Failure of the ejection jack could 

result in a lack of hydraulic pressure or 

electrical power in an emergency.

DATES: This AD becomes effective 

December 14, 2004. 

The incorporation by reference of 

certain publications listed in the AD is 

approved by the Director of the Federal 

Register as of December 14, 2004. 

The incorporation by reference of 

certain other publications listed in the 

AD was approved previously by the 

Director of the Federal Register on 

August 6, 2001 (66 FR 34798, July 2, 

2001).

ADDRESSES: For service information 

identified in this AD, contact Airbus, 1 

Rond Point Maurice Bellonte, 31707 

Blagnac Cedex, France. 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.

You can examine the contents of this 

AD docket on the Internet at http://

dms.dot.gov, or at the Docket 

Management Facility, 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: 

Technical information: Dan Rodina, 

Aerospace Engineer; International 

Branch, ANM–116, FAA, Transport 

Airplane Directorate, 1601 Lind 

Avenue, SW., Renton, Washington 

98055–4056; telephone (425) 227–2125; 

fax (425) 227–1149. 

Plain language information: Marcia 

Walters, marcia.walters@faa.gov.

Examining the 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 DOT street address stated in the 

ADDRESSES section.

SUPPLEMENTARY INFORMATION: The FAA 

proposed to amend part 39 of the 

Federal Aviation Regulations (14 CFR 

Part 39) with an AD to supersede AD 

2001–13–16, amendment 39–12297, (66 

FR 34798, July 2, 2001). The existing AD 

applies to certain Airbus Model A310 

series airplanes; and Model A300 B4–

600, B4–600R, and F4–600R series 

airplanes; and Model C4–605R Variant F 

airplanes (collectively called A300–

600). The proposed AD was published 

in the Federal Register on July 15, 2004 

(69 FR 42363), to require a one-time 

inspection of the RAT ejection jack to 

determine the part number, and further 

investigative and corrective actions if 

necessary. 

Comments 

We provided the public the 

opportunity to participate in the 

development of this AD. No comments 

have been submitted on the proposed 

AD or on the determination of the cost 

to the public. 

Explanation of Change to Applicability 

We have revised the applicability of 

the AD to identify model designations 

as published in the most recent type 

certificate data sheet for the affected 

models. 

Conclusion 

We have carefully reviewed the 

available data and determined that air 

safety and the public interest require 

adopting the AD with the change 

described previously. We have 

determined that this change will neither 

increase the economic burden on any 

operator nor increase the scope of the 

AD. 

Costs of Compliance 

AD 2001–13–16 affects about 117 

airplanes of U.S. registry. The actions 

that are currently required by AD 2001–

13–16 and retained in this AD take 

about 6 work hours per airplane, at an 

average labor rate of $65 per work hour. 

There is no charge for required parts. 

Based on these figures, the estimated 

cost of the currently required actions for 

U.S. operators is $45,630, or $390 per 

airplane. 

This AD will affect approximately 149 

airplanes of U.S. registry. The new 

inspection will take about 1 work hour 

per airplane, at an average labor rate of 

$65 per work hour. Based on these 

figures, the estimated cost of the new 

actions specified in this AD for U.S. 

operators is $9,685, or $65 per airplane. 

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, 

Federal Register / Vol. 69, No. 216 / Tuesday, November 9, 2004 / Rules and Regulations 64855

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:

2004–22–22 Airbus: Amendment 39–13850. 

Docket No. FAA–2004–18603; 

Directorate Identifier 2003–NM–14–AD. 

Effective Date 

(a) This airworthiness directive (AD) 

becomes effective December 14, 2004. 

Affected ADs 

(b) This AD supersedes AD 2001–13–16, 

amendment 39–12297 (66 FR 34798, July 2, 

2001). 

Applicability 

(c) This AD applies to Airbus Model A310 

series airplanes; and Model A300 B4–600, 

B4–600R, and F4–600R series airplanes; and 

Model C4–605R Variant F airplanes 

(collectively called A300–600); certificated in 

any category; as listed in Airbus Service 

Bulletin A300–29–6050, Revision 02, dated 

April 16, 2003; or A310–29–2088, Revision 

01, dated February 3, 2003. 

Unsafe Condition 

(d) This AD was prompted by the 

discovery of a rupture in the housing of one 

of the ram air turbine (RAT) ejection jacks 

installed as specified in the existing AD. We 

are issuing this AD to prevent rupture of the 

housing of the RAT ejection jack due to 

overpressure in the jack caused by overfilling 

the hydraulic fluid, and consequent failure of 

the RAT ejection jack. Failure of the ejection 

jack could result in a lack of hydraulic 

pressure or electrical power in an emergency.

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. 

Requirements of AD 2001–13–16: 

Modification 

(f) For airplanes on which Airbus 

Modification 12259 has not been 

accomplished: Within 34 months after 

August 6, 2001 (the effective date of AD 

2001–13–16, amendment 39–12297), modify 

the RAT per Airbus Service Bulletin A310–

29–2086, Revision 01 (for Model A310 series 

airplanes), or A300–29–6048, Revision 01 

(for Model A300 B4–600, B4–600R, and F4–

600R series airplanes; and Model C4–605R 

Variant F airplanes (collectively called 

A300–600)), both dated July 12, 2000, as 

applicable.

Note 1: Modification of the RAT 

accomplished prior to August 6, 2001, in 

accordance with Airbus Service Bulletin 

A310–29–2086 or A300–29–6048, both dated 

April 6, 2000, as applicable, is considered 

acceptable for compliance with the action 

specified in paragraph (f) of this AD.

Parts Installation 

(g) As of August 6, 2001, no person may 

install on any airplane an ejection jack, part 

number 730820, unless it has been modified 

per paragraph (f) of this AD.

Note 2: Airbus Service Bulletin A310–29–

2086 and A300–29–6048, both Revision 01, 

refer to Hamilton Sundstrand Service 

Bulletin No. ERPS03/04EJ–29–1, as an 

additional source of service information for 

accomplishment of the modification of the 

RAT and testing of the modified RAT.

New Requirements of This AD: 

Inspection 

(h) Within 2,500 flight hours after the 

effective date of this AD: Inspect the RAT 

ejection jack to determine the part number 

(P/N), in accordance with the 

Accomplishment Instructions of the 

applicable Airbus service bulletin listed in 

Table 1 of this AD. If the P/N can be 

determined and is neither 772652 nor 

772654, no further action is required by this 

paragraph.

TABLE 1.—SERVICE INFORMATION

For this airplane 

model—

Airbus Service

Bulletin—

A300 B4–600, B4–

600R, and F4–600R 

series airplanes; 

and Model C4–605R 

Variant F airplanes 

(collectively called 

A300–600).

A300–29–6050, Revision 02, dated 

April 16, 2003. 

A310 series airplanes A310–29–2088, Revision 01, dated 

February 3, 2003. 

Note 3: Airbus Service Bulletins A300–29–

6050 and A310–29–2088 refer to Hamilton 

Sundstrand Service Bulletin ERPS03/04EJ–

29–2, dated May 8, 2002, as an additional 

source of service information for identifying 

subject RAT ejection jacks and performing 

the applicable related investigative and 

corrective actions.

Related Investigative and Corrective Actions 

(If Necessary) 

(i) If the P/N on the RAT ejection jack is 

either 772652 or 772654, or if the P/N cannot 

be determined: Before further flight, 

accomplish all applicable related 

investigative and corrective actions in 

accordance with the Accomplishment 

Instructions of the applicable Airbus service 

bulletin listed in Table 1 of this AD. 

Actions Accomplished Previously 

(j) Inspections and related investigative 

and corrective actions done before the 

effective date of this AD in accordance with 

Airbus Service Bulletin A300–29–6050 (for 

Model A300 B4–600, B4–600R, and F4–600R 

series airplanes; and Model C4–605R Variant 

F airplanes (collectively called A300–600)) or 

A310–29–2088 (for Model A310 series 

airplanes), both dated July 23, 2002, as 

applicable, are acceptable for compliance 

with the corresponding actions required by 

paragraphs (h) and (i) of this AD. 

Alternative Methods of Compliance 

(AMOCs) 

(k) 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. 

Related Information 

(l) French airworthiness directive 2002–

638(B), dated December 24, 2002, also 

addresses the subject of this AD. 

Material Incorporated by Reference 

(m) You must use the service information 

that is specified in Table 2 of this AD to 

perform the actions that are required by this 

AD, unless the AD specifies otherwise:

64856 Federal Register / Vol. 69, No. 216 / Tuesday, November 9, 2004 / Rules and Regulations 

TABLE 2.—MATERIAL INCORPORATED BY REFERENCE

Service bulletin Revision 

level Date 

Airbus Service Bulletin A300–29–6048 ............................................................................................................... 01 July 12, 2000. 

Airbus Service Bulletin A300–29–6050, excluding Appendix 01 ........................................................................ 02 April 16, 2003. 

Airbus Service Bulletin A310–29–2086 ............................................................................................................... 01 July 12, 2000. 

Airbus Service Bulletin A310–29–2088, excluding Appendix 01 ........................................................................ 01 February 3, 2003. 

(1) The Director of the Federal Register 

approved the incorporation by reference of 

Airbus Service Bulletin A300–29–6050, 

Revision 02, excluding Appendix 01, dated 

April 16, 2003; and Airbus Service Bulletin 

A310–29–2088, Revision 01, excluding 

Appendix 01, dated February 3, 2003; in 

accordance with 5 U.S.C. 552(a) and 1 CFR 

part 51. 

(2) The incorporation by reference of 

Airbus Service Bulletin A300–29–6048, 

Revision 01, dated July 12, 2000; and Airbus 

Service Bulletin A310–29–2086, Revision 01, 

dated July 12, 2000, was approved previously 

by the Director of the Federal Register as of 

August 6, 2001 (66 FR 34798, July 2, 2001). 

(3) For copies of the service information, 

contact Airbus, 1 Rond Point Maurice 

Bellonte, 31707 Blagnac Cedex, France. 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 October 

20, 2004. 

Kalene C. Yanamura, 

Acting Manager, Transport Airplane 

Directorate, Aircraft Certification Service.

[FR Doc. 04–24628 Filed 11–8–04; 8:45 am] 

BILLING CODE 4910–13–P

DEPARTMENT OF TRANSPORTATION

Federal Aviation Administration 

14 CFR Part 39

[Docket No. 2003–NM–11–AD; Amendment 

39–13851; AD 2004–22–23] 

RIN 2120–AA64

Airworthiness Directives; Bombardier 

Model CL–600–2B19 (Regional Jet 

Series 100 & 440) Airplanes

AGENCY: Federal Aviation 

Administration, DOT.

ACTION: Final rule.

SUMMARY: This amendment adopts a 

new airworthiness directive (AD), 

applicable to certain Bombardier Model 

CL–600–2B19 (Regional Jet Series 100 & 

440) airplanes, that requires a one-time 

inspection of the shafts of the main 

landing gear (MLG) side-brace fittings to 

detect corrosion, and the forward and 

aft bushings in the left-hand and righthand MLG side-brace fittings to detect 

discrepancies. This AD also requires 

corrective and related actions if 

necessary. This action is necessary to 

prevent fractures of the MLG side-brace 

fitting shafts, and possible collapse of 

the MLG. This action is intended to 

address the identified unsafe condition.

DATES: Effective December 14, 2004. 

The incorporation by reference of a 

certain publication listed in the 

regulations is approved by the Director 

of the Federal Register as of December 

14, 2004.

ADDRESSES: The service information 

referenced in this AD may be obtained 

from Bombardier, Inc., Canadair, 

Aerospace Group, PO Box 6087, Station 

Centre-ville, Montreal, Quebec H3C 

3G9, Canada. This information may be 

examined at the Federal Aviation 

Administration (FAA), Transport 

Airplane Directorate, Rules Docket, 

1601 Lind Avenue, SW., Renton, 

Washington; or at the FAA, New York 

Aircraft Certification Office, 1600 

Stewart Avenue, suite 410, Westbury, 

New York; 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.

FOR FURTHER INFORMATION CONTACT:

Serge Napoleon, Aerospace Engineer, 

Airframe and Propulsion Branch, ANE–

171, FAA, New York Aircraft 

Certification Office, 1600 Stewart 

Avenue, suite 410, Westbury, New York 

11590; telephone (516) 228–7312; fax 

(516) 794–5531.

SUPPLEMENTARY INFORMATION: A 

proposal to amend part 39 of the Federal 

Aviation Regulations (14 CFR part 39) to 

include an airworthiness directive (AD) 

that is applicable to certain Bombardier 

Model CL–600–2B19 (Regional Jet 

Series 100 & 440) airplanes was 

published in the Federal Register on 

June 14, 2004 (69 FR 32924). That action 

proposed to require a one-time 

inspection of the shafts of the main 

landing gear (MLG) side-brace fittings to 

detect corrosion, and the forward and 

aft bushings in the left-hand and righthand MLG side-brace fittings to detect 

discrepancies. That action also 

proposed to require corrective and 

related actions if necessary. 

Comments 

Interested persons have been afforded 

an opportunity to participate in the 

making of this amendment. Due 

consideration has been given to the 

comments received. 

Request for Credit for Actions Done per 

the Original Issue of the Service 

Bulletin 

One commenter requests that actions 

done per the original issue of 

Bombardier Service Bulletin 601R–57–

036 be considered acceptable for 

compliance with the corresponding 

actions in the proposed AD. The 

commenter notes that Revisions A and 

B of the service bulletin are mentioned 

in paragraph (c) of the proposed AD as 

being acceptable for compliance with 

the corresponding actions but the 

paragraph does not state that actions 

done per the original issue are 

considered acceptable for compliance 

with the corresponding actions. 

The FAA agrees that actions done per 

the original issue of the service bulletin 

are considered acceptable for 

compliance with the corresponding 

actions of the final rule. Revision C of 

the service bulletin, cited as the 

appropriate source of service 

information for the final rule, specifies 

that no additional action is needed for 

airplanes on which actions were done 

per previous issues of the service 

bulletin. We have revised paragraph (c) 

of the final rule accordingly. 

Request To Remove Reference to 

Functional Test 

The same commenter requests that 

references to the functional test in the 

proposed AD need not be specified. The 

commenter states that the ‘‘Explanation 

of Requirements of Proposed AD’’

paragraph of the proposed AD specifies 

that the Canadian airworthiness 

directive CF–2002–41, dated September 

20, 2002, does not include the