60804 Federal Register / Vol. 69, No. 197 / Wednesday, October 13, 2004 / Rules and Regulations 

or Change 02, dated February 26, 2004; 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, International Branch, ANM–116, 

Transport Airplane Directorate, FAA, is 

authorized to approve alternative methods of 

compliance for this AD. 

Incorporation by Reference 

(d) Unless otherwise specified in this AD, 

the actions must be done in accordance with 

EMBRAER Service Bulletin 145–32–0066, 

Change 03, dated April 19, 2004. 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 

Empresa Brasileira de Aeronautica S.A. 

(EMBRAER), P.O. Box 343—CEP 12.225, Sao 

Jose dos Campos—SP, Brazil. 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 3: The subject of this AD is addressed 

in Brazilian airworthiness directive 2002–12–

01, effective January 6, 2003. 

Effective Date 

(e) 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. 04–22561 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–294–AD; Amendment 

39–13820; AD 2004–20–15] 

RIN 2120–AA64 

Airworthiness Directives; Dornier 

Model 328–100 Series Airplanes

AGENCY: Federal Aviation 

Administration, DOT.

ACTION: Final rule.

SUMMARY: This amendment supersedes 

an existing airworthiness directive (AD), 

applicable to all Dornier Model 328–100 

series airplanes, that currently requires 

certain revisions to the airplane flight 

manual, replacement of certain de-icing 

boots in the air intake duct assemblies 

of the engine with re-designed units, 

repetitive inspections of the boots to 

find discrepancies, and corrective action 

if necessary. This amendment also 

requires modification of the engine air 

inlet de-icing system. This action 

extends the repetitive inspection 

interval required by the existing AD, 

and adds repetitive debonding/

delamination and leakage inspections of 

the de-icing boots, and corrective action 

if necessary. Initiation of the extended 

repetitive inspections and new 

repetitive inspections ends the 

repetitive inspections required by the 

existing AD. The actions specified by 

this AD are intended to prevent engine 

malfunction due to failure of the engine 

air inlet de-icing system, which could 

result in reduced controllability 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, as listed in the 

regulations, is approved by the Director 

of the Federal Register as of November 

17, 2004. 

The incorporation by reference of 

certain other publications, as listed in 

the regulations, was approved 

previously by the Director of the Federal 

Register as of April 6, 1995 (60 FR 

15037, March 22, 1995).

ADDRESSES: The service information 

referenced in this AD may be obtained 

from AvCraft Aerospace GmbH, P.O. 

Box 1103, D–82230 Wessling, Germany. 

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: Tom 

Groves, Aerospace Engineer, 

International Branch, ANM–116, FAA, 

Transport Airplane Directorate, 1601 

Lind Avenue, SW., Renton, Washington 

98055–4056; telephone (425) 227–1503; 

fax (425) 227–1149.

SUPPLEMENTARY INFORMATION: A 

proposal to amend part 39 of the Federal 

Aviation Regulations (14 CFR part 39) 

by superseding AD 95–04–51, 

amendment 39–9179 (60 FR 15037, 

March 22, 1995), which is applicable to 

all Dornier Model 328–100 series 

airplanes, was published in the Federal 

Register on April 1, 2004 (69 FR 17097). 

The action proposed to continue to 

require the revisions to the AFM, 

replacement of certain de-icing boots in 

the air intake duct assemblies of the 

engine with re-designed units, and 

repetitive inspections of the boots to 

find discrepancies, and corrective action 

if necessary. The action also would 

require modification of the engine air 

inlet de-icing system, and would add a 

new AFM revision which changes the 

compliance time for the functional test 

required by the existing AD. The 

proposed action would extend the 

repetitive inspection interval required 

by the existing AD, and would add 

repetitive debonding/delamination and 

leakage inspections of the de-icing 

boots, and corrective action if necessary. 

Initiation of the extended repetitive 

inspections and new repetitive 

inspections would end the repetitive 

inspections required by the existing AD. 

Comments 

We provided the public the 

opportunity to participate in the 

development of this AD. No comments 

have been submitted in response to the 

proposed AD or on the determination of 

the cost to the public. 

Conclusion 

We have determined that air safety 

and the public interest require the 

adoption of the AD as proposed. 

Clarification of Inspection 

We have updated the definition of the 

detailed inspection in Note 1 of the AD 

to reflect our current definition. 

Cost Impact 

There are about 53 airplanes of U.S. 

registry that will be affected by this AD. 

The AFM revision currently required 

by AD 95–04–51 takes about 1 work 

hour per airplane to accomplish, at an 

average labor rate of $65 per work hour. 

Based on these figures, the cost impact 

of the currently required AFM revision 

is estimated to be $65 per airplane. 

The inspections currently required by 

AD 95–04–51 take about 1 work hour 

per airplane to accomplish, at an 

average labor rate of $65 per work hour. 

Based on these figures, the cost impact 

of the currently required inspections is 

estimated to be $65 per airplane, per 

inspection cycle. 

The replacement currently required 

by AD 95–04–51 takes about 5 work 

hours per airplane to accomplish, at an 

average labor rate of $65 per work hour. 

Required parts will cost about $55,000 

per airplane. Based on these figures, the 

cost impact of the currently required 

replacement is estimated to be $55,325 

per airplane.

The modification required in this AD 

action will take about 10 work hours per 

Federal Register / Vol. 69, No. 197 / Wednesday, October 13, 2004 / Rules and Regulations 60805

airplane to accomplish, at an average 

labor rate of $65 per work hour. 

Required parts will be free of charge. 

Based on these figures, the cost impact 

of the required modification on U.S. 

operators is estimated to be $34,450, or 

$650 per airplane. 

The inspection/debonding/

delamination and leakage inspection 

required in this AD action will take 

about 1 work hour per airplane to 

accomplish, at an average labor rate of 

$65 per work hour. Based on these 

figures, the cost impact of the required 

inspection on U.S. operators is 

estimated to be $3,445, or $65 per 

airplane, per inspection cycle. 

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 

removing amendment 39–9179 (60 FR 

15037, March 22, 1995), and by adding 

a new airworthiness directive (AD), 

amendment 39–13820, to read as 

follows:

2004–20–15 Fairchild Dornier Gmbh 

(Formerly Dornier Luftfahrt GmbH):

Amendment 39–13820. Docket 2002–

NM–294–AD. Supersedes AD 95–04–51, 

Amendment 39–9179.

Applicability: All Model 328–100 series 

airplanes, certificated in any category. 

Compliance: Required as indicated, unless 

accomplished previously.

To prevent engine malfunction due to 

failure of the engine air inlet de-icing system, 

which could result in reduced controllability 

of the airplane, accomplish the following: 

Restatement of Certain Requirements of AD 

95–04–01 

AFM Revision 

(a) For all airplanes: Within 24 hours after 

April 6, 1995 (the effective date of AD 95–

04–51, amendment 39–9179), accomplish 

paragraphs (a)(1), (a)(2), and (a)(3) of this AD. 

(1) Revise the Limitations Section of the 

FAA-approved Airplane Flight Manual 

(AFM) by inserting the following limitation 

in the AFM. This may be accomplished by 

inserting a copy of this AD in the AFM. 

‘‘During flight, if the ‘ENG DEICE FAIL’

electronic indication and caution advisory 

system (EICAS) annunciation activates for 

either engine, flight into known or forecast 

icing conditions is prohibited.’’

(2) Revise the Abnormal Procedures 

Section of the FAA-approved AFM by 

removing page 4, dated September 1, 1994, 

of section 04–12–00, and replacing it with 

the following. This may be accomplished by 

inserting a copy of this AD in the AFM. 

‘‘1. Icing Conditions—Exit immediately. If 

unable, land at nearest suitable airport.’’

(3) Revise the Limitations Section of the 

FAA-approved AFM to include the following 

functional test. This may be accomplished by 

inserting a copy of this AD in the AFM. 

Continue to do the functional test until the 

AFM revision required by paragraph (e) of 

this AD is done. 

‘‘Accomplish the following test at the 

applicable time specified as follows: 

For airplanes equipped with air intake duct 

assemblies having de-icing boots with part 

numbers (P/Ns) 29S–5D5240–21, –23, and 

–25: As of 24 hours after the effective date 

of AD 95–04–51, accomplish the functional 

test prior to each flight. 

For airplanes equipped with air intake duct 

assemblies having de-icing boots with P/Ns 

29S–5D5240–211 (inlet lip), –231 (bypass 

duct), and –251 (aft ramp duct): Accomplish 

the functional test within 24 hours after the 

effective date of AD 95–04–51, and thereafter 

at daily intervals. 

Perform a functional test of the de-icing 

system of the air intake ducts of the left and 

right engines to determine the condition of 

the system, in accordance with the 

procedures specified below. Flight crew or 

maintenance personnel shall perform this 

test. 

Functional Test of the De-Icing System 

With engines running at idle power, 

display and monitor the ‘ICE PROTECT’

system page of the electronic indication and 

caution advisory system (EICAS), select left 

and right ‘ENGINE INTAKE’ pushbuttons in 

(‘ON’), for a minimum of 60 seconds. Monitor 

system page for normal indications of one 

complete boot inflation and deflation cycle. 

Monitor EICAS for normal messages, and 

absence of ‘ENG DEICE FAIL’ caution. 

After 60 seconds and observation of one 

complete inflation/deflation cycle, release 

‘ENGINE INTAKE’ pushbuttons to out (‘OFF’) 

position, confirm absence of system page and 

EICAS cautions, and deselect ‘ICE PROTECT’

system page. At completion of check, 

‘ENGINE INTAKE’ pushbuttons may be 

turned back on if required for departure. 

If any EICAS ‘ENG DEICE FAIL’

annunciation is observed, or if system normal 

inflate and deflate cycling is not observed: 

The system shall be considered inoperative. 

Prior to further flight, the detailed visual and 

tactile inspections required by paragraph (b) 

of AD 95–04–51 must be accomplished. 

If no discrepancy with the de-icing boots 

is found during these inspections, the deicing system may be inoperative for a period 

of time not to exceed that specified in the 

DO–328 Master Minimum Equipment List 

(MMEL). Flight into known or forecast icing 

conditions is prohibited.’’

Repetitive Inspections/Corrective Action 

(b) For airplanes equipped with air intake 

duct assemblies having de-icing boots with 

part numbers

(P/N) 29S–5D5240–21, –23, and –25: 

Accomplish paragraphs (b)(1) and (b)(2) of 

this AD at the times specified in those 

paragraphs. 

(1) Within 24 hours after April 6, 1995: 

Perform a detailed inspection and a tactile 

inspection of the de-icing boots in the air 

intake ducts on the engines to find flat spots, 

softness, or other discrepancies, and to 

ensure that the edges of the de-icing boots are 

sealed properly, in accordance with Dornier 

Service Bulletin SB–328–30–020, dated 

March 17, 1994.

Note 1: For the purposes of this AD, a 

detailed inspection is: ‘‘An intensive 

examination of a specific item, installation, 

or assembly to detect damage, failure, or 

irregularity. Available lighting is normally 

supplemented with a direct source of good 

lighting at an intensity deemed appropriate. 

60806 Federal Register / Vol. 69, No. 197 / Wednesday, October 13, 2004 / Rules and Regulations 

Inspection aids such as mirror, magnifying 

lenses, etc., may be necessary. Surface 

cleaning and elaborate procedures may be 

required.’’

(i) If no discrepancies are found and the 

edges of the de-icing boots are sealed 

properly (no debonding between the boot and 

the intake duct), repeat the detailed and 

tactile inspections required by paragraph 

(b)(1) of this AD thereafter at daily intervals 

until accomplishment of the modification 

required by paragraph (f) of this AD. 

(ii) If any discrepancy is found, or if any 

edge of a de-icing boot is sealed improperly 

(debonding between the boots and the intake 

duct), prior to further flight, replace all three 

de-icing boots having P/Ns 29S–5D5240–21, 

–23, and –25, with three new units having

P/Ns 29S–5D5240–211, –231, and –251, in 

accordance with the procedures specified in 

Dornier Alert Service Bulletin ASB–328–71–

006, Revision 1, dated February 16, 1995. 

(2) Within 5 days after April 6, 1995, 

replace all three de-icing boots having P/Ns 

29S–5D5240–21, –23, and –25, with three 

new units having P/Ns 29S–5D5240–211, 

–231, and –251, in accordance with Dornier 

Alert Service Bulletin ASB–328–71–006, 

Revision 1, dated February 16, 1995. 

Following such replacement, perform the 

detailed and tactile inspections and the 

functional tests required by paragraphs (c) 

and (e) of this AD, respectively, in 

accordance with the times and procedures 

specified in those paragraphs.

(c) For airplanes equipped with air intake 

duct assemblies having de-icing boots with 

P/Ns 29S–5D5240–211, –231, and –251: 

Within 7 days after April 6, 1995, perform a 

detailed inspection and a tactile inspection of 

the de-icing boots in the air intake ducts on 

the engines to find flat spots, softness, or 

other discrepancies, and to ensure that the 

edges of the de-icing boots are sealed 

properly, in accordance with the procedures 

specified in Dornier Service Bulletin SB–

328–30–020, dated March 17, 1994. 

(1) If no discrepancies are found and the 

edges of the de-icing boots are sealed 

properly (no debonding between the boot and 

the intake duct): Repeat the detailed and 

tactile inspections required by paragraph (c) 

of this AD thereafter at intervals not to 

exceed 7 days until accomplishment of the 

modification required by paragraph (f) of this 

AD. 

(2) If any discrepancy is found, or if any 

edge of a de-icing boot is sealed improperly 

(debonding between the boots and the intake 

duct): Prior to further flight, replace all three 

de-icing boots with three new units having P/

Ns 29S–5D5240–211, –231, and –251, in 

accordance with Dornier Alert Service 

Bulletin ASB–328–71–006, Revision 1, dated 

February 16, 1995. 

Parts Installation 

(d) As of April 6, 1995, no de-icing boot 

having P/N 29S–5D5240–21, –23, or –25 

shall be installed on any airplane. 

New Requirements of This AD 

AFM Revision 

(e) Within 24 hours after the effective date 

of this AD: Revise the Limitations Section of 

the AFM to include the following functional 

test. This may be accomplished by inserting 

a copy of this AD into the AFM. 

Accomplishment of this paragraph ends the 

requirements of paragraph (a)(3) of this AD, 

and the AFM revision required by that 

paragraph may be removed from the AFM. 

‘‘Accomplish the following test within 24 

hours after the effective date of this AD. 

Repeat the test thereafter at daily intervals. 

Perform a functional test of the de-icing 

system of the air intake ducts of the left and 

right engines to determine the condition of 

the system, in accordance with the 

procedures specified below. Flight crew or 

maintenance personnel shall perform this 

test. 

Functional Test of the De-Icing System 

With engines running at idle power, 

display and monitor the ‘ICE PROTECT’

system page of the electronic indication and 

caution advisory system (EICAS), select left 

and right ‘ENGINE INTAKE’ pushbuttons in 

(‘ON’), for a minimum of 60 seconds. Monitor 

system page for normal indications of one 

complete boot inflation and deflation cycle. 

Monitor EICAS for normal messages, and 

absence of ‘ENG DEICE FAIL’ caution. 

After 60 seconds and observation of one 

complete inflation/deflation cycle, release 

‘ENGINE INTAKE’ pushbuttons to out (‘OFF’) 

position, confirm absence of system page and 

EICAS cautions, and deselect ‘‘ICE 

PROTECT’ system page. At completion of 

check, ‘‘ENGINE INTAKE’ pushbuttons may 

be turned back on if required for departure. 

If any EICAS ‘ENG DEICE FAIL’

annunciation is observed, or if system normal 

inflate and deflate cycling is not observed: 

The system shall be considered inoperative. 

Prior to further flight, the detailed 

inspections required by paragraph (g) of this 

AD must be accomplished.

If no discrepancy with the de-icing boots 

is found during these inspections, the deicing system may be inoperative for a period 

of time not to exceed that specified in the 

DO–328 Master Minimum Equipment List 

(MMEL). Flight into known or forecast icing 

conditions is prohibited.’’

Modification of the Engine Air Intake Deicing System 

(f) Within 60 flight hours after the effective 

date of this AD: Modify the engine air inlet 

de-icing system (including a one-time 

detailed inspection and a debonding/

delamination and leakage inspection) by 

doing all the actions (including any 

applicable corrective action) per the 

Accomplishment Instructions of Dornier 

Service Bulletin SB–328–71–125, Revision 3; 

and by doing all the actions per the 

Accomplishment Instructions of Dornier 

Service Bulletin SB–328–71–122, Revision 1; 

both dated May 10, 1999. Do any applicable 

corrective action before further flight per the 

applicable service bulletin.

Note 2: The de-icing boots approved for 

installation on the modified engine inlet 

assembly are specified in paragraph 3., 

‘‘Material Information,’’ of the 

Accomplishment Instructions of Dornier 

Service Bulletin SB–328–30–432, dated April 

26, 2002.

Note 3: Dornier Service Bulletin SB–328–

71–122, Revision 1, dated May 10, 1999, 

references Westland Aerospace Limited 

Service Bulletin SB–WAL328–71–122, dated 

September 25, 1995, as an additional source 

of service information for modification of the 

air intake ducts; and Dornier Service Bulletin 

SB–328–71–125, Revision 3, dated May 10, 

1999, references Westland Aerospace Limited 

Service Bulletin SB–WAL328–71–125, 

Revision 1, dated September 25, 1995, as an 

additional source of service information for 

installation of the cover plate of the bypass 

duct outlet.

Repetitive Inspections 

(g) Within 60 flight hours after 

accomplishment of paragraph (f) of this AD: 

Do a detailed inspection of the engine air 

inlet de-icing boots to find discrepancies 

(including flat or soft spots in concave 

sections, defects on the de-icing boots, or 

improper sealing), per paragraph 2.B.1. of the 

Accomplishment Instructions of Dornier 

Service Bulletin SB–328–30–432, dated April 

26, 2002. Do any applicable corrective action 

before further flight per the service bulletin. 

Repeat the inspection thereafter at intervals 

not to exceed 60 flight hours. 

(h) Within 400 flight hours after 

accomplishment of paragraph (f) of this AD: 

Do a debonding/delamination and leakage 

inspection of the engine air inlet de-icing 

boots by doing all the applicable actions per 

the Accomplishment Instructions of Dornier 

Service Bulletin SB–328–30–432, dated April 

26, 2002. Do any applicable corrective action 

before further flight per the service bulletin. 

Repeat the inspection thereafter at intervals 

not to exceed 400 flight hours. 

(i) Initiation of the repetitive inspections 

required by paragraphs (g) and (h) of this AD 

terminates the repetitive inspections required 

by paragraphs (b) and (c) of this AD. 

No Reporting Required 

(j) Where Dornier Service Bulletin SB–328–

30–432, dated April 26, 2002, describes 

procedures for completing a reporting sheet 

with inspection results, this AD does not 

require that action. 

Alternative Methods of Compliance 

(k)(1) In accordance with 14 CFR 39.19, the 

Manager, International Branch, ANM–116, 

FAA, Transport Airplane Directorate, is 

authorized to approve alternative methods of 

compliance for this AD.

(2) Alternative methods of compliance, 

approved previously in accordance with AD 

95–04–51, amendment 39–9179, are not 

considered to be approved as alternative 

methods of compliance with this AD. 

Incorporation by Reference 

(l) Unless otherwise specified in this AD, 

the actions shall be done in accordance with 

the service bulletins listed in Table 1 of this 

AD, as applicable:

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,