Federal Register / Vol. 69, No. 197 / Wednesday, October 13, 2004 / Rules and Regulations 60807

TABLE 1.—INCORPORATION BY REFERENCE

Service bulletin Revision Date 

Dornier Alert Service Bulletin ASB–328–71–006 .............................................................................................. 1 ................... February 16, 1995. 

Dornier Service Bulletin SB–328–30–020 ......................................................................................................... Original ......... March 17, 1994. 

Dornier Service Bulletin SB–328–30–432 ......................................................................................................... Original ......... April 26, 2002. 

Dornier Service Bulletin SB–328–71–122 ......................................................................................................... 1 ................... May 10, 1999. 

Dornier Service Bulletin SB–328–71–125 ......................................................................................................... 3 ................... May 10, 1999. 

(1) The incorporation by reference of the 

service bulletins listed in Table 2 of this AD 

is approved by the Director of the Federal 

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

and 1 CFR part 51:

TABLE 2.—NEW SERVICE BULLETINS FOR INCORPORATION BY REFERENCE

Service bulletin Revision Date 

Dornier Service Bulletin SB–328–30–432 ......................................................................................................... Original ......... April 26, 2002. 

Dornier Service Bulletin SB–328–71–122 ......................................................................................................... 1 ................... May 10, 1999. 

Dornier Service Bulletin SB–328–71–125 ......................................................................................................... 3 ................... May 10, 1999. 

(2) The incorporation by reference of the 

service bulletins listed in Table 3 of this AD 

was approved previously by the Director of 

the Federal Register as of April 6, 1995 (60 

FR 15037, March 22, 1995):

TABLE 3.—SERVICE BULLETINS PREVIOUSLY INCORPORATED BY REFERENCE

Service bulletin Revision Date 

Dornier Alert Service Bulletin ASB–328–71–006 .............................................................................................. 1 ................... February 16, 1995. 

Dornier Service Bulletin SB–328–30–020 ......................................................................................................... Original ......... March 17, 1994. 

(3) Copies may be obtained from AvCraft 

Aerospace GmbH, P.O. Box 1103, D–82230 

Wessling, Germany. 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 4: The subject of this AD is addressed 

in German airworthiness directives 1995–

156/3, dated July 1, 1999; and 2002–256, 

dated September 5, 2002.

Effective Date 

(m) This amendment becomes effective on 

November 17, 2004.

Issued in Renton, Washington, on 

September 30, 2004. 

Kevin M. Mullin, 

Acting Manager, Transport Airplane 

Directorate, Aircraft Certification Service.

[FR Doc. 04–22562 Filed 10–12–04; 8:45 am] 

BILLING CODE 4910–13–P

DEPARTMENT OF TRANSPORTATION

Federal Aviation Administration 

14 CFR Part 39 

[Docket No. 2002–NM–286–AD; Amendment 

39–13821; AD 2004–20–16] 

RIN 2120–AA64 

Airworthiness Directives; Boeing 

Model 747–200B, –200C, –200F, –300, 

–400, –400D, and –400F Series 

Airplanes; and Model 747SP Series 

Airplanes

AGENCY: Federal Aviation 

Administration, DOT.

ACTION: Final rule.

SUMMARY: This amendment adopts a 

new airworthiness directive (AD), 

applicable to certain Boeing Model 747–

200B, –200C, –200F, –300, –400, –400D, 

and –400F series airplanes; and Model 

747SP series airplanes, that requires 

repetitive functional tests of the 

auxiliary power unit (APU) and engine 

fire shutoff switches and repetitive 

replacements of the APU and engine fire 

shutoff switches. The AD also provides 

an optional terminating action for the 

repetitive functional tests and 

replacements. This action is necessary 

to prevent mineral build-up on the APU 

and engine fire shutoff switches, which 

could lead to failure of the switches to 

discharge fire suppressant in the 

affected area and could result in an 

uncontrolled fire that could spread to 

the strut, wing, or aft body of the 

airplane. This action is intended to 

address the identified unsafe condition.

DATES: Effective November 17, 2004. 

The incorporation by reference of a 

certain publication listed in the 

regulations is approved by the Director 

of the Federal Register as of November 

17, 2004.

ADDRESSES: The service information 

referenced in this AD may be obtained 

from Boeing Commercial Airplanes, 

P.O. Box 3707, Seattle, Washington 

98124–2207. 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:

Sulmo Mariano, Aerospace Engineer, 

60808 Federal Register / Vol. 69, No. 197 / Wednesday, October 13, 2004 / Rules and Regulations 

Propulsion Branch, ANM–140S, FAA, 

Seattle Aircraft Certification Office, 

1601 Lind Avenue, SW., Renton, 

Washington 98055–4056; telephone 

(425) 917–6501; fax (425) 917–6590.

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 Boeing 

Model 747–200B, –200C, –200F, –300, 

–400, –400D, and –400F series 

airplanes; and Model 747SP series 

airplanes, was published in the Federal 

Register on June 23, 2004 (69 FR 34971). 

That action proposed to require 

repetitive functional tests of the 

auxiliary power unit (APU) and engine 

fire shutoff switches and repetitive 

replacements of the APU and engine fire 

shutoff switches. That action also 

proposed to provide an optional 

terminating action for the repetitive 

functional tests and replacements. 

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. 

Clarification of Summary Language 

Since the proposed AD was published 

we noticed that in the Summary of the 

proposed AD we referred to 

‘‘inspections’’ instead of ‘‘functional 

tests.’’ We have corrected the Summary 

of this AD. 

Cost Impact 

There are approximately 316 

airplanes of the affected design in the 

worldwide fleet. We estimate that 50 

airplanes of U.S. registry will be affected 

by this AD, and that the average labor 

rate is $65 per work hour. Table 1 

provides the estimated costs for U.S. 

operators to comply with this AD.

TABLE 1.—ESTIMATED COSTS

Action Work hours Cost per airplane Total cost 

Inspection and Functional Test (per test cycle) 10–14 (depending on airplane model) ............. $650–910 $32,500–45,500 

The cost impact figures discussed 

above are 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:

2004–20–16 Boeing: Amendment 39–13821. 

Docket 2002–NM–286–AD.

Applicability: Model 747–200B, –200C, 

–200F, –300, –400, –400D, and –400F series 

airplanes; and Model 747SP series airplanes; 

as listed in Boeing Alert Service Bulletin 

747–26A2274, Revision 1, dated January 9, 

2003; certificated in any category. 

Compliance: Required as indicated, unless 

accomplished previously. 

To prevent mineral build-up on the 

auxiliary power unit (APU) and engine fire 

shutoff switches, which could lead to failure 

of the switches to discharge fire suppressant 

in the affected area and could result in an 

uncontrolled fire that could spread to the 

strut, wing, or aft body of the airplane, 

accomplish the following: 

Service Bulletin Reference 

(a) The term ‘‘service bulletin,’’ as used in 

this AD, means the Accomplishment 

Instructions of Boeing Alert Service Bulletin 

747–26A2274, Revision 1, dated January 9, 

2003. 

Initial and Repetitive Functional Test 

(b) At the later of the compliance times 

specified in paragraphs (b)(1) and (b)(2) of 

this AD, perform a functional test of the APU 

and engine fire shutoff switches, in 

accordance with the service bulletin. Repeat 

the functional test thereafter at intervals not 

to exceed 18 months. 

(1) Within 18 months since the date of 

issuance of the original Airworthiness 

Certificate or the original Export Certificate of 

Airworthiness. 

(2) Within 90 days after the effective date 

of this AD. 

Fire Shutoff Switch Failure 

(c) If any fire shutoff switch fails during 

any functional test required by paragraph (b) 

or (f) of this AD, before further flight, replace 

the switch with a new or serviceable switch, 

in accordance with the service bulletin. 

Repeat the switch replacement thereafter at 

intervals not to exceed 36 months. 

Replacement 

(d) Within 36 months after the effective 

date of this AD, replace all APU and engine 

fire shutoff switches that have not been 

previously replaced per paragraph (c) of this 

AD with new or serviceable switches, in 

accordance with the service bulletin. Repeat 

the switch replacement thereafter at intervals 

not to exceed 36 months.

Deactivation of Lucas Humidifier 

(e) Operators may terminate the repetitive 

requirements of paragraphs (b), (c), and (d) of 

this AD by accomplishing the actions in 

Federal Register / Vol. 69, No. 197 / Wednesday, October 13, 2004 / Rules and Regulations 60809

paragraphs (e)(1) and (e)(2) of this AD, except 

as provided by paragraph (f) of this AD. 

(1) Deactivate the Lucas humidifier, part 

number (P/N) M01AA0101, M01AB0101, 

M01AB0102, or M01AB0103, in accordance 

with the service bulletin. 

(2) Before further flight following the 

deactivation specified in paragraph (e)(1) of 

this AD, replace all APU and engine fire 

shutoff switches with new or serviceable 

switches in accordance with the service 

bulletin. 

Reactivation of Lucas Humidifier 

(f) For any airplanes on which Lucas 

humidifier, P/N M01AA0101, M01AB0101, 

M01AB0102, or M01AB0103 is reactivated 

after the effective date of this AD: Do the 

requirements of paragraphs (f)(1) and (f)(2) of 

this AD at the times specified in those 

paragraphs. 

(1) Within 18 months after reactivating the 

humidifier, and thereafter at intervals not to 

exceed 18 months, do the functional test 

required by paragraph (b) of this AD. 

(2) Within 36 months after reactivating the 

humidifier, and thereafter at intervals not to 

exceed 36 months, replace all APU and 

engine fire shutoff switches that have not 

been previously replaced per paragraph (c) of 

this AD. Do the replacements per paragraph 

(d) of this AD. 

Actions Accomplished Per Previous Issue of 

Service Bulletin 

(g) Unless otherwise specified in this AD, 

actions accomplished before the effective 

date of this AD per Boeing Alert Service 

Bulletin 747–26A2274, dated August 29, 

2002, are considered acceptable for 

compliance with the corresponding action 

specified in this AD. 

Alternative Methods of Compliance 

(h) In accordance with 14 CFR 39.19, the 

Manager, Seattle Aircraft Certification Office, 

FAA, is authorized to approve alternative 

methods of compliance for this AD. 

Incorporation by Reference 

(i) The actions shall be done in accordance 

with Boeing Alert Service Bulletin 747–

26A2274, Revision 1, dated January 9, 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 Boeing Commercial Airplanes, P.O. Box 

3707, Seattle, Washington 98124–2207. 

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.

Effective Date 

(j) This amendment becomes effective on 

November 17, 2004.

Issued in Renton, Washington, on 

September 30, 2004. 

Kevin M. Mullin, 

Acting Manager, Transport Airplane 

Directorate, Aircraft Certification Service.

[FR Doc. 04–22563 Filed 10–12–04; 8:45 am] 

BILLING CODE 4910–13–P

DEPARTMENT OF TRANSPORTATION

Federal Aviation Administration 

14 CFR Part 39 

[Docket No. 2002–NM–211–AD; Amendment 

39–13819; AD 2004–20–14] 

RIN 2120–AA64 

Airworthiness Directives; Airbus Model 

A300 B4 Series Airplanes and Model 

A300 B4–600, A300 B4–600R, and A300 

F4–600R (Collectively Called A300–

600) Series Airplanes

AGENCY: Federal Aviation 

Administration, DOT.

ACTION: Final rule.

SUMMARY: This amendment supersedes 

an existing airworthiness directive (AD), 

applicable to all Airbus Model A300 B4 

series airplanes and all Airbus Model 

A300–600 series airplanes. That AD 

currently requires a one-time high 

frequency eddy current inspection to 

detect cracking of the splice fitting at 

fuselage frame (FR) 47 between stringers 

24 and 25; and corrective actions if 

necessary. This amendment requires 

new repetitive inspections of an 

expanded area and adds airplanes to the 

applicability in the existing AD. The 

actions specified by this AD are 

intended to detect and correct cracking 

of the splice fitting at fuselage FR 47, 

which could result in reduced structural 

integrity of the airplane. This action is 

intended to address the identified 

unsafe condition.

DATES: Effective November 17, 2004. 

The incorporation by reference of 

certain publications listed in the 

regulations is approved by the Director 

of the Federal Register as of November 

17, 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, 

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 

Aviation Regulations (14 CFR part 39) 

by superseding AD 2001–03–14, 

amendment 39–12118 (66 FR 10957, 

February 21, 2001), was published as a 

supplemental notice of proposed 

rulemaking (NPRM) in the Federal 

Register on August 4, 2004 (69 FR 

47035). The proposal is applicable to all 

Airbus Model A300 series airplanes and 

all Airbus Model A300–600 series 

airplanes. The action proposed to 

require new repetitive high frequency 

eddy current inspections to detect 

cracking of an expanded area, and 

corrective actions, if necessary; and to 

add airplanes to the applicability in the 

existing AD. 

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.

Clarification of Service Information 

Requirements for Paragraph (b) of This 

AD 

In our response to comments in the 

Preamble of the supplemental NPRM, 

we stated our intent to revise paragraphs 

(a), (b), and (c) of the supplemental 

NPRM to refer to Revision 02 of the 

referenced Airbus service bulletins as 

the appropriate sources of service 

information for accomplishment of the 

required actions. (Revision 01 of those 

service bulletins was referenced in the 

original NPRM for accomplishment of 

the required actions.) However, while 

we revised paragraphs (a) and (c) of the 

supplemental NPRM, we inadvertently 

omitted the revision to paragraph (b). 

Therefore, we have revised paragraph 

(b) of this final rule to reference 

Revision 02 of Airbus Service Bulletin 

A300–53–6123 as the appropriate 

source of service information for the 

required actions in that paragraph. 

Conclusion 

After careful review of the available 

data, the FAA has determined that air 

safety and the public interest require the 

adoption of the rule with the change