44592 Federal Register / Vol. 69, No. 143 / Tuesday, July 27, 2004 / Rules and Regulations 

Docket at the location provided under 

the caption ADDRESSES.

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 

the following new airworthiness 

directive:

2004–15–09 Bombardier, Inc. (Formerly de 

Havilland, Inc.): Amendment 39–13743. 

Docket 2003–NM–285–AD.

Applicability: Model DHC–8–101, –102, 

–103, –106, –201, –202, –301, –311, and –315 

airplanes, serial number 003 through 585 

inclusive; certificated in any category; with 

auxiliary power unit (APU) installation per 

Standard Option Only (S.O.O.) 8155 or 

Change Request (CR) 849SO08155. 

Compliance: Required as indicated, unless 

accomplished previously. 

To prevent a fuel leak caused by chafing 

of the APU fuel tube assembly, which could 

result in fire in the center wing area, 

accomplish the following: 

Inspection, Relocation and Related 

Investigative and Corrective Actions 

(a) Within 6 months after the effective date 

of this AD: Do a general visual inspection of 

the APU fuel tube assembly for 

discrepancies. The inspection includes 

examining the routing of the fuel tube 

assembly to ensure that the tube has 

sufficient clearance between the shroud of 

the bleed air duct and the gust lock cable; 

and inspecting the fuel tube assembly and 

the bleed air duct shroud for other 

discrepancies such as nicks, dents, chafing, 

or other damage. If the inspection shows no 

discrepancies, before further flight, relocate 

the clamps on the fuel tube assembly. If the 

inspection shows discrepancies, before 

further flight, do the applicable related 

investigative and corrective actions, and 

relocate the clamps on the fuel tube 

assembly. Accomplish all actions per the 

Accomplishment Instructions of Bombardier 

Service Bulletin 8–49–19, Revision A, dated 

July 7, 2003.

Note 1: For the purposes of this AD, a 

general visual inspection is defined as: ‘‘A 

visual examination of an interior or exterior 

area, installation, or assembly to detect 

obvious damage, failure, or irregularity. This 

level of inspection is made from within 

touching distance unless otherwise specified. 

A mirror may be necessary to enhance visual 

access to all exposed surfaces in the 

inspection area. This level of inspection is 

made under normally available lighting 

conditions such as daylight, hangar lighting, 

flashlight, or droplight and may require 

removal or opening of access panels or doors. 

Stands, ladders, or platforms may be required 

to gain proximity to the area being checked.’’

Inspections Accomplished Per Previous 

Issue of Service Bulletin 

(b) Actions accomplished before the 

effective date of this AD per Bombardier 

Service Bulletin 8–49–19, dated May 13, 

2003, are considered acceptable for 

compliance with the corresponding action 

specified in this AD. 

Alternative Methods of Compliance 

(c) In accordance with 14 CFR 39.19, the 

Manager, New York Aircraft Certification 

Office, FAA, is authorized to approve 

alternative methods of compliance for this 

AD. 

Incorporation by Reference 

(d) Unless otherwise specified in this AD, 

the actions shall be done in accordance with 

Bombardier Service Bulletin 8–49–19, 

Revision A, dated July 7, 2003. This 

incorporation by reference was approved by 

the Director of the Federal Register in 

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

part 51. Copies may be obtained from 

Bombardier, Inc., Bombardier Regional 

Aircraft Division, 123 Garratt Boulevard, 

Downsview, Ontario M3K 1Y5, Canada. 

Copies may be inspected at the FAA, 

Transport Airplane Directorate, 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.

Note 2: The subject of this AD is addressed 

in Canadian airworthiness directive CF–

2003–22, dated September 3, 2003.

Effective Date 

(e) This amendment becomes effective on 

August 31, 2004.

Issued in Renton, Washington, on July 9, 

2004. 

Kevin M. Mullin, 

Acting Manager, Transport Airplane 

Directorate, Aircraft Certification Service.

[FR Doc. 04–16680 Filed 7–26–04; 8:45 am] 

BILLING CODE 4910–13–P

DEPARTMENT OF TRANSPORTATION

Federal Aviation Administration 

14 CFR Part 39 

[Docket No. 2003–NM–279–AD; Amendment 

39–13741; AD 2004–15–07] 

RIN 2120–AA64 

Airworthiness Directives; Airbus Model 

A310 Series Airplanes

AGENCY: Federal Aviation 

Administration, DOT.

ACTION: Final rule.

SUMMARY: This amendment adopts a 

new airworthiness directive (AD), 

applicable to certain Airbus Model 

A310 series airplanes, that requires 

repetitive inspections for fatigue 

cracking of the area around the fasteners 

of the landing plate of the aileron access 

doors of the bottom skin panel of the 

wings, and related corrective action. 

This amendment also provides for an 

optional terminating action, which ends 

the repetitive inspections. This action is 

necessary to prevent fatigue cracking of 

the area around the fasteners of the 

landing plate of the aileron access doors 

and the bottom skin panel of the wings, 

which could result in reduced structural 

integrity of the wings. This action is 

intended to address the identified 

unsafe condition.

DATES: Effective August 31, 2004. 

The incorporation by reference of 

certain publications listed in the 

regulations is approved by the Director 

of the Federal Register as of August 31, 

2004.

ADDRESSES: The service information 

referenced in this AD may be obtained 

from Airbus, 1 Rond Point Maurice 

Bellonte, 31707 Blagnac Cedex, France. 

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 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: Tim 

Backman, Aerospace Engineer, 

International Branch, ANM–116, FAA, 

Transport Airplane Directorate, 1601 

Lind Avenue, SW., Renton, Washington 

98055–4056; telephone (425) 227–2797; 

fax (425) 227–1149.

SUPPLEMENTARY INFORMATION: A 

proposal to amend part 39 of the Federal 

Federal Register / Vol. 69, No. 143 / Tuesday, July 27, 2004 / Rules and Regulations 44593

Aviation Regulations (14 CFR part 39) to 

include an airworthiness directive (AD) 

that is applicable to certain Airbus 

Model A310 series airplanes was 

published in the Federal Register on 

May 19, 2004 (69 FR 28867). That action 

proposed to require repetitive 

inspections for fatigue cracking of the 

area around the fasteners of the landing 

plate of the aileron access doors of the 

bottom skin panel of the wings, and 

related corrective action. That action 

also provided for an optional 

terminating action, which would end 

the repetitive inspections. 

Comments 

Interested persons have been afforded 

an opportunity to participate in the 

making of this amendment. No 

comments were submitted in response 

to the proposal or the FAA’s 

determination of the cost to the public. 

Conclusion 

The FAA has determined that air 

safety and the public interest require the 

adoption of the rule as proposed. 

Cost Impact 

The FAA estimates that 46 airplanes 

of U.S. registry will be affected by this 

AD, that it will take about 2 work hours 

per airplane to accomplish the required 

actions, and that the average labor rate 

is $65 per work hour. Based on these 

figures, the cost impact of the AD on 

U.S. operators is estimated to be $5,980, 

or $130 per airplane, per inspection 

cycle. 

The cost impact figure discussed 

above is based on assumptions that no 

operator has yet accomplished any of 

the requirements of this AD action, and 

that no operator would accomplish 

those actions in the future if this AD 

were not adopted. The cost impact 

figures discussed in AD rulemaking 

actions represent only the time 

necessary to perform the specific actions 

actually required by the AD. These 

figures typically do not include 

incidental costs, such as the time 

required to gain access and close up, 

planning time, or time necessitated by 

other administrative actions. 

Regulatory Impact 

The regulations adopted herein 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. Therefore, it is 

determined that this final rule does not 

have federalism implications under 

Executive Order 13132. 

For the reasons discussed above, I 

certify that this action (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. A final evaluation has 

been prepared for this action and it is 

contained in the Rules Docket. A copy 

of it may be obtained from the Rules 

Docket at the location provided under 

the caption ADDRESSES.

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 

the following new airworthiness 

directive:

2004–15–07 Airbus: Amendment 39–13741. 

Docket 2003–NM–279–AD.

Applicability: Model A310 series airplanes, 

certificated in any category; on which Airbus 

Modification 12525 has not been done during 

production. 

Compliance: Required as indicated, unless 

accomplished previously. 

To prevent fatigue cracking of the area 

around the fasteners of the landing plate of 

the aileron access doors and the bottom skin 

panel of the wings, which could result in 

reduced structural integrity of the wings, 

accomplish the following: 

Repetitive Inspections 

(a) For airplanes on which Airbus 

Modification 5106 (Airbus Service Bulletin 

A310–57–2004, Revision 2, dated March 5, 

1990) has not been done as of the effective 

date of this AD: Within 2,000 flight cycles 

after the effective date of this AD, or within 

3,000 flight cycles after the last inspection 

done per paragraph (k) of AD 98–26–01, 

amendment 39–10942 (63 FR 69179, 

December 16, 1998), whichever is first; do a 

high frequency eddy current (HFEC) 

inspection for cracking of the area around the 

fasteners of the landing plate of the wing 

bottom skin panel No. 2 of the left and right 

wings. Do the inspection per the 

Accomplishment Instructions of Airbus 

Service Bulletin A310–57–2082, dated June 

11, 2002. If no cracking is found, repeat the 

inspection thereafter at intervals not to 

exceed 1,900 flight cycles, until 

accomplishment of the terminating action 

specified in paragraph (d) of this AD. 

(b) For airplanes on which Airbus 

Modification 5106 has been done as of the 

effective date of this AD: Do the HFEC 

inspection required by paragraph (a) of this 

AD at the applicable time specified in 

paragraph (b)(1), (b)(2), (b)(3), or (b)(4) of this 

AD. If no cracking is found, repeat the 

inspection thereafter at intervals not to 

exceed 1,900 flight cycles, until 

accomplishment of the terminating action 

specified in paragraph (d) of this AD. 

(1) For airplanes that have accumulated 

fewer than 17,000 total flight cycles since the 

date of issuance of the original Airworthiness 

Certificate or the date of issuance of the 

original Export Certificate of Airworthiness, 

whichever is first, as of the effective date of 

this AD: Inspect prior to the accumulation of 

18,000 total flight cycles. 

(2) For airplanes that have accumulated 

17,000 or more total flight cycles, but fewer 

than 19,001 total flight cycles since the date 

of issuance of the original Airworthiness 

Certificate or the date of issuance of the 

original Export Certificate of Airworthiness, 

whichever is first, as of the effective date of 

this AD: Inspect within 2,000 flight cycles 

after the effective date of this AD. 

(3) For airplanes that have accumulated 

19,001 or more total flight cycles, but fewer 

than 21,001 total flight cycles since the date 

of issuance of the original Airworthiness 

Certificate or the date of issuance of the 

original Export Certificate of Airworthiness, 

whichever is first, as of the effective date of 

this AD: Inspect with 1,200 flight cycles after 

the effective date of this AD. 

(4) For airplanes that have accumulated 

21,001 or more total flight cycles since the 

date of issuance of the original Airworthiness 

Certificate or the date of issuance of the 

original Export Certificate of Airworthiness, 

whichever is first, as of the effective date of 

this AD: Inspect within 500 flight cycles after 

the effective date of this AD. 

Corrective Action 

(c) If any cracking is found during any 

inspection required by paragraph (a) or (b) of 

this AD: Before further flight, do the actions 

required by either paragraph (c)(1) or (c)(2) of 

this AD. 

(1) Do a permanent repair of the area by 

doing the applicable corrective actions per 

the Accomplishment Instruction of Airbus 

Service Bulletin A310–57–2082, dated June 

11, 2002. Accomplishment of the permanent 

repair terminates the repetitive inspections 

required by this AD for the repaired area 

only. 

(2) Do the terminating action specified in 

paragraph (d) of this AD. 

Optional Terminating Action 

(d) Modification of the landing plate of the 

aileron access doors of the wing bottom skin 

panel No. 2 of the left and right wings by 

doing all the actions, per the 

44594 Federal Register / Vol. 69, No. 143 / Tuesday, July 27, 2004 / Rules and Regulations 

Accomplishment Instructions of Airbus 

Service Bulletin A310–57–2081, dated June 

11, 2002, terminates the requirements of this 

AD. Where the service bulletin specifies 

contacting the manufacturer for disposition 

of certain repair conditions that may be 

associated with the modification procedure, 

this AD requires that the repair be done per 

a method approved by either the Manager, 

International Branch, ANM–116, FAA, 

Transport Airplane Directorate; or the 

Direction Ge ́ne ́rale de l’Aviation Civile, or its 

delegated agent. 

Alternative Methods of Compliance 

(e) In accordance with 14 CFR 39.19, the 

Manager, International Branch, ANM–116, is 

authorized to approve alternative methods of 

compliance for this AD. 

Incorporation by Reference 

(f) Unless otherwise specified in this AD, 

the actions shall be done in accordance with 

Airbus Service Bulletin A310–57–2082, 

dated June 11, 2002. The optional 

terminating action, if accomplished, shall be 

done in accordance with Airbus Service 

Bulletin A310–57–2081, dated June 11, 2002. 

This incorporation by reference was 

approved by the Director of the Federal 

Register in accordance with 5 U.S.C. 552(a) 

and 1 CFR part 51. Copies may be obtained 

from Airbus, 1 Rond Point Maurice Bellonte, 

31707 Blagnac Cedex, France. Copies may be 

inspected 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/

code_of_federal_regulations/

ibr_locations.html.

Note 1: The subject of this AD is addressed 

in French airworthiness directive 2003–

242(B), dated June 25, 2003.

Effective Date 

(g) This amendment becomes effective on 

August 31, 2004.

Issued in Renton, Washington, on July 9, 

2004. 

Kevin M. Mullin, 

Acting Manager, Transport Airplane 

Directorate, Aircraft Certification Service.

[FR Doc. 04–16675 Filed 7–26–04; 8:45 am] 

BILLING CODE 4910–13–P

DEPARTMENT OF TRANSPORTATION

Federal Aviation Administration 

14 CFR Part 39 

[Docket No. 2003–NM–172–AD; Amendment 

39–13739; AD 2004–15–05] 

RIN 2120–AA64 

Airworthiness Directives; BAE 

Systems (Operations) Limited Model 

BAe 146 and Avro 146–RJ Series 

Airplanes

AGENCY: Federal Aviation 

Administration, DOT.

ACTION: Final rule.

SUMMARY: This amendment adopts a 

new airworthiness directive (AD), 

applicable to certain BAE Systems 

(Operations) Limited Model BAe 146 

and Avro 146-RJ series airplanes, that 

requires replacing the existing bellows 

inlet duct of the auxiliary power unit 

(APU) system with a new, improved 

rectangular metallic bellows inlet duct. 

This action is necessary to prevent air 

from the APU bay being ingested into 

the flight deck and passenger cabin 

resulting in poor air quality and, if the 

air is contaminated, possible 

incapacitation of the flightcrew and 

passengers. This action is intended to 

address the identified unsafe condition.

DATES: Effective August 31, 2004. 

The incorporation by reference of 

certain publications listed in the 

regulations is approved by the Director 

of the Federal Register as of August 31, 

2004.

ADDRESSES: The service information 

referenced in this AD may be obtained 

from British Aerospace Regional 

Aircraft American Support, 13850 

Mclearen Road, Herndon, Virginia 

20171. 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 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:

Todd Thompson, Aerospace Engineer, 

International Branch, ANM–116, FAA, 

Transport Airplane Directorate, 1601 

Lind Avenue, SW., Renton, Washington 

98055–4056; telephone (425) 227–1175; 

fax (425) 227–1149.

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 BAE 

Systems (Operations) Limited Model 

BAe 146 and Avro 146–RJ series 

airplanes was published in the Federal 

Register on May 27, 2004 (69 FR 30244). 

That action proposed to require 

replacing the existing bellows inlet duct 

of the auxiliary power unit (APU) 

system with a new, improved 

rectangular metallic bellows inlet duct. 

Comments 

Interested persons have been afforded 

an opportunity to participate in the 

making of this amendment. No 

comments were submitted in response 

to the proposal or the FAA’s 

determination of the cost to the public. 

Conclusion 

The FAA has determined that air 

safety and the public interest require the 

adoption of the rule as proposed. 

Cost Impact 

The FAA estimates that 54 airplanes 

of U.S. registry will be affected by this 

AD, that it will take approximately 2 

work hours per airplane to accomplish 

the required actions, and that the 

average labor rate is $65 per work hour. 

Required parts will cost approximately 

$4,500 per airplane. Based on these 

figures, the cost impact of the AD on 

U.S. operators is estimated to be 

$250,020, or $4,630 per airplane. 

The cost impact figure discussed 

above is based on assumptions that no 

operator has yet accomplished any of 

the requirements of this AD action, and 

that no operator would accomplish 

those actions in the future if this AD 

were not adopted. The cost impact 

figures discussed in AD rulemaking 

actions represent only the time 

necessary to perform the specific actions 

actually required by the AD. These 

figures typically do not include 

incidental costs, such as the time 

required to gain access and close up, 

planning time, or time necessitated by 

other administrative actions. 

Regulatory Impact 

The regulations adopted herein 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. Therefore, it is 

determined that this final rule does not 

have federalism implications under 

Executive Order 13132. 

For the reasons discussed above, I 

certify that this action (1) is not a 

‘‘significant regulatory action’’ under